KingAir350_maintenance_manual

Super King Air® 350 and 350C (Model B300 and B300C) B300

(FL-1 and After)

B300C

(FM-1 and After)

Maintenance Manual Volume 1 Introduction thru Chapter 30 This manual includes the maintenance information required to be available by 14 CFR Part 23.

Copyright © 2010 Hawker Beechcraft Corporation. All rights reserved. Hawker and Beechcraft are trademarks of Hawker Beechcraft Corporation.

P/N 130-590031-11 Issued: December 1, 1989

P/N 130-590031-11A28 Revised: May 1, 2010

Super King Air® 350 and 350C (Model B300 and B300C) B300

(FL-1 and After)

B300C

(FM-1 and After)

Maintenance Manual Volume 2 Chapter 31 thru Chapter 80 This manual includes the maintenance information required to be available by 14 CFR Part 23.

Copyright © 2010 Hawker Beechcraft Corporation. All rights reserved. Hawker and Beechcraft are trademarks of Hawker Beechcraft Corporation.

P/N 130-590031-11 Issued: December 1, 1989

P/N 130-590031-11A28 Revised: May 1, 2010

NOTE Raytheon Aircraft Company, which has been renamed Hawker Beechcraft Corporation, is now owned by Hawker Beechcraft, Inc. Neither Hawker Beechcraft, Inc. nor Hawker Beechcraft Corporation are affiliated any longer with Raytheon Company. Any Raytheon marks contained in this document are owned by Raytheon Company and are employed pursuant to a limited license granted by Raytheon Company.

Published by Hawker Beechcraft Corporation P.O. Box 85 Wichita, Kansas 67201-0085 USA

The export of these commodities, technology or software are subject to the US Export Administration Regulations. Diversion contrary to US law is prohibited. For guidance on export control requirements, contact the Commerce Department’s Bureau of Export Administration at 202482-4811 or visit the US Department of Commerce website.

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Record of Revisions Note: When

a

revision is inserted, the revision number, the date the revision is inserted into the manual, and the

initials of the

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LIST OF EFFECTIVE REVISIONS PART NUMBER

DATE

CHAPTERS AFFECTED

130-590031-11

December 1, 1989

Original Issue

130-590031-11A1

August 31, 1990

4, 5, 6, 7, 8, 9, 10, 12, 20, 21, 23, 24, 25, 26, 27, 28, 30,32, 33, 34, 35, 37, 38, 39, 52, 53, 55, 56, 57, 61, 71, 76, 77, 78, 79, 80

130-590031-11A2

April 15, 1991

4, 5, 20, 21, 23, 24, 27, 32, 33, 34, 51, 61, 77

130-590031-11A3

March 16, 1992

Introduction, 5, 20, 22, 25, 26, 27, 28, 30, 31, 32, 33, 34, 35, 37, 39, 55, 56, 71

130-590031-11A4

July 9, 1993

12, 21, 22, 24, 27, 28, 30, 32, 33, 34, 52, 53, 55, 56, 57, 61, 79

130-590031-11A5

June 24, 1994

Introduction, 4, 5, 12, 21, 23, 24, 30, 31, 32, 35, 39, 53, 61, 71, 77, 79

130-590031-11A6

February 17, 1995

Introduction, 5, 12, 21, 24, 26, 27, 32, 33, 35, 52, 53, 55, 56, 61

130-590031-11A7

July 31, 1995

4, 5, 10, 21, 25, 26, 27, 28, 32, 52, 53, 61, 71, 77

130-590031-11A8

January 31, 1997

4, 57

130-590031-11A9

February 28, 1997

Introduction, 5, 7, 12, 20, 21, 25, 30, 32, 77

130-590031-11A10

October 18, 1998

Introduction, 4, 5, 12, 23, 24, 27, 32, 71

130-590031-11A11

May 31, 1999

53, 77

130-590031-11A12

March 9, 2001

4, 5, 10, 11, 12, 20, 21, 23, 24, 25, 26, 27, 28, 30, 31, 32, 33, 37, 39, 52, 57, 61, 76

130-590031-11A13

September 28, 2001

5, 12, 61, 76

130-590031-11A14

April 26, 2002

56

A27 Basic publications are assigned a part number which appears on the title page with the date of the issue. Subsequent revisions are identified by the addition of a revision code after the part number. A1 after a part number denotes the first revision to the basic publication, A2 the second, etc. Occasionally, it is necessary to completely reissue and reprint a publication for the purpose of obsoleting a previous issue and outstanding revisions thereto. As these replacement reissues are made, the code will also change to the next successive letter of the alphabet at each reissue. For example, B for the first reissue, C for the second, etc. When ordering a manual, give the basic number, and the reissue code when applicable, if a complete up-to-date publication is desired. Should only revision pages be required, give the basic number and revision code for the particular set of revision pages you desire.

A

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LIST OF EFFECTIVE REVISIONS PART NUMBER

DATE

CHAPTERS AFFECTED

130-590031-11A15

January 31, 2003

4, 5, 21, 26, 27, 35, 53

130-590031-11A16

October 31, 2003

5, 21, 34, 35

130-590031-11A17

October 31, 2004

4, 5, 12, 22, 26, 27, 30, 52, 55

130-590031-11A18

April 29, 2005

4

130-590031-11A19

October 31, 2005

25, 27, 53

130-590031-11A20

April 28, 2006

Introduction, 5, 24, 32

130-590031-11A21

October 31, 2006

6, 12, 20, 21, 27, 28, 33, 34, 56, 77

130-590031-11A22

May 1, 2007

Introduction, 20, 23, 25, 53, 56, 57

130-590031-11A23

November 1, 2007

20, 24, 27, 30, 35, 39, 52, 56, 61, 71, 76

130-590031-11A24

May 1, 2008

5, 7, 8, 9, 10, 12, 20, 21, 23, 24, 25, 26, 27, 28, 30, 36, 38, 39, 51, 52, 53, 55, 57, 61, 71, 79, 80

130-590031-11A25

February 1, 2009

11, 20, 21, 27, 30, 32, 33, 72, 74, 76, 78

130-590031-11A26

August 1, 2009

12, 22, 24

130-590031-11A27

February 1, 2010

Introduction, 6, 20, 21, 23, 24, 25, 27, 34, 35, 38, 52, 53, 56, 71

A27 B

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Log of Temporary Revisions Note: Insert this Log of Temporary Revisions after the Record of Revisions page. Previous Log of Temporary Revisions may be discarded. Update the Record of Temporary Revisions page(s) as required. Revision No.

Revision Date

Subject

5-1

Sep 19/97

Seat Belts and Shoulder Harnesses

A10

27-1

Jun 24/97

Flap and Aileron Clearance

A10

27-2

Sep 21/01

Stall Warning-Safe Flight System

A15

5-2

Feb 14/03

Environmental System Inspection Requirements

A16

21-1

Feb 14/03

Bleed Air Bypass Valve Operational Check

A16

27-3

Oct 31/04

Revised the ELEVATOR TAB CABLE REMOVAL procedure and ELEVATOR TAB CABLE INSTALLATION. Added the VERTICAL-ELEVATOR TRIM TAB CABLE REMOVAL and VERTICAL-ELEVATOR TRIM TAB CABLE INSTALLATION procedures.

A19

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Nov 09

Provides additional instructions on the application of de-ice/antiice fluids and the removal of thickened residue that may result from using these fluids.

Temporary Revision No. 12-1

Revision Incorporated

Page 1 Nov. 09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

P/N 130-590031-11, Revision A28, May 1/10 The chapters which have been revised or added are listed below with the Highlights of each change. Remove the affected pages and insert this Revision in accordance with the attached Instruction Page. Enter the revision number and the date inserted on the Record of Revisions page of this manual. The Highlights Page may be retained with the manual for future reference.

Highlights Chapter/Section

Description

5-00-00, 001

INSPECTION PROGRAM replaces COMPUTER INSPECTION TRACKING PROGRAMS and section revised. References revised throughout chapter.

5-11-00, 001

Page 4, Window Defog Air Filters - Revised.

5-21-01, 201

Reference AC43.13-1A/2A changed to AC43.13-1B/2B throughout document. Page 212, NOTE Revised. Q.62. added.

5-21-02, 201

Reference AC43.13-1A/2A changed to AC43.13-1B/2B throughout document. O.20.d added. Page 214, NOTE Revised.

5-21-03, 201

Reference AC43.13-1A/2A changed to AC43.13-1B/2B throughout document. F.22. Window Defog System revised. Page 214, NOTE revised. Q.62. added.

5-21-04, 201

Reference AC43.13-1A/2A changed to AC43.13-1B/2B throughout document. O.21. Revised. Page 214, NOTE REvised. Q.62. added

5-21-05, 201

1. LEFT SIDE ENGINE Revised. 11. RIGHT SIDE ENGINE Revised. References revised throughout chapter.

5-22-02, 201

Reference AC43.13-1A/2A changed to AC43.13-1B/2B throughout document. O.30.d. Added. Page 227, NOTE Revised. Q.62. added

20-06-00, 201

Page 201, Cautions added. TUBING, HOSES AND FITTINGS - INSPECT/CHECK added.

20-12-00, 001

New Chapter, ELECTRICAL WIRING - DESCRIPTION AND OPERATION added.

23-60-00, 201

Page 202, NOTE Revised.

27-21-00, 001

Divided into page blocks 1, 101 and 201.

27-21-00, 101

See 27-21-00, 001.

27-21-00, 201

See 27-21-00, 001.

27-50-00, 201

Page 201, FLAP INSTALLATION - NOTE - revised.

33-10-00, 201

Information regarding Control Wheel Map Light replacement.

52-10-00, 201

LATCH MECHANISM ADJUSTMENT, Revised. Figure 203 revised.

57-00-00, 201

Page 202, CAUTION, RAPID now Hawker Beechcraft Global Customer Support Parts and Distribution Division.

61-00-00, 001

Reformatted.

61-10-00, 001

Divided into page blocks 1 and 201.

HIGHLIGHTS

Page 1

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Highlights (Continued) Chapter/Section

Description

61-10-00, 201

See 61-10-00, 001.

61-21-00, 001

Actuation pressure for LH and RH autofeather pressure switches revised.

61-21-00, 201

AUTOFEATHER POWER LEVER SWITCH ADJUSTMENT - NOTE revised. AUTOFEATHER SYSTEM OPERATIONAL CHECK - Revised

61-22-00, 201

MAGNETIC PICKUP INSTALLATION AND ADJUSTMENT (WITH ELLIOT NOISE REDUCTION SYSTEM) Revised. Figure 202 Revised. Figure 203 Added.

71-00-00, 201

Page 218, CAUTION - ‘60 minutes OFF’, changed to ‘30 minutes OFF.’

Page 2

HIGHLIGHTS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CHAPTER

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NOTE - The chapter List of Effective Pages is located in the front of each chapter.

A28 C

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 04-00-00 00

1. INFORMATION The date on the Standard Airworthiness Certificate, issued with each airplane, must be considered as the starting time for all Inspection and Replacement Schedules presented in this manual. NOTE: Reissues and revisions are automatically provided to the subscription holders of the manual. Additional publications are listed on the web at http://pubs.hawkerbeechcraft.com. For more information on these publications, or to check subscription status, contact the Technical Manual Distribution Center (TMDC) at 1.800.796.2665 or 316.676.8238, fax 316.671.2540, E-mail [email protected]. An Interactive Maintenance Library (IML) contains selected Manuals in a digital format. This manual, along with others, is available on CD-ROM. Optional paper copies of the manuals on CD-ROM are available for purchase.

A. General The Super King Air B300/B300C Maintenance Manual is prepared in accordance with the requirements of ATA Specification 100 (Air Transport Association of America) with respect to the arrangement and content of the System/Chapters within the designated numbering system. This manual is supplemented by the following publications: •

Model B300/B300C Maintenance Manual Supplement for airplanes equipped with ProLine 21 Avionics, P/N 130-590031-191

•

Model B300/B300C Illustrated Parts Catalog, P/N 130-590031-9

•

Model B300/B300C Wiring Diagram Manual, P/N 130-590031-7

•

Model B300/B300C Avionics Wiring Diagram Manual, P/N 130-590031-197

•

King Air Series Component Maintenance Manual, P/N 101-590097-13

•

King Air Series Structural Inspection and Repair Manual, P/N 98-39006

•

Super King Air B300/B300C Airworthiness Limitations Manual, P/N 130-590031-211

•

King Air/1900 Series Printed Circuit Board Manual, P/N 98-39117

It shall be the responsibility of the owner/operator to make sure that the latest revision of the publications referenced in this manual are utilized during operation, servicing and maintenance of the airplane. In addition to this manual and its subsequent revisions, additional maintenance information is published in the form of Hawker Beechcraft Corporation service bulletins. The information contained in these service bulletins is an integral part of, and is to be used in conjunction with, the information contained in this manual. Hawker Beechcraft Corporation expressly reserves the right to supersede, cancel and/or declare obsolete any parts, part numbers, kits or publications that may be referenced in this manual without prior notice.

A27

INTRODUCTION

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WARNING: Use only parts obtained from sources approved by Hawker Beechcraft Corporation, in connection with the maintenance and repair of Hawker Beechcraft Corporation airplanes. Genuine Hawker Beechcraft Corporation parts are produced and inspected under rigorous procedures to insure airworthiness and suitability for use in Hawker Beechcraft Corporation airplane applications. Parts purchased from sources other than those approved by Hawker Beechcraft Corporation, even though outwardly identical in appearance, may not have the required tests and inspections performed, may be different in fabrication techniques and materials, and may be dangerous when installed in an airplane. Salvaged airplane parts, reworked parts obtained from sources not approved by the Hawker Beechcraft Corporation or parts, components or structural assemblies, the service history of which is unknown or cannot be authenticated, may have been subjected to unacceptable stresses or temperatures or have other hidden damage, not discernible through routine visual or usual nondestructive testing techniques. This may render the part, component or structural assembly, even though originally manufactured by the Hawker Beechcraft Corporation, unsuitable and unsafe for airplane use. Hawker Beechcraft Corporation expressly disclaims any responsibility for malfunctions, failures, damage or injury caused by use of parts not approved by the Hawker Beechcraft Corporation. WARNING: Any maintenance requiring the disconnection and reconnection of flight control cables, plumbing, electrical connectors or wiring requires identification of each side of the component being disconnected to facilitate correct reassembly. At or prior to disassembly, components should be color coded, tagged or properly identified in a way that it will be obvious how to correctly reconnect the components. After recondition of any component, remove all identification tags. Check all associated systems for correct function prior to returning the airplane to service.

B. Correspondence If a question should arise concerning the care of your airplane, it is important to include the airplane serial number in any correspondence. The serial number appears on the model designation placard. Refer to Chapter 11 for placard location.

C. Publications Change Request (PCR) If an irregularity or missing information is noted, the user of this manual may access a PCR form at http://pubs.hawkerbeechcraft.com. Instructions on how to submit a PCR are included on the web page.

D. Normal Revisions Normal Revisions to this manual are issued to provide changes to airworthiness limitation information. 1. Paper Revision That portion of text which has been revised by the addition of, or a change in, information is denoted by a solid revision bar adjacent to the text. The date printed on the bottom of each page can be compared to the “A” page to determine the revision number. Each revised page will ONLY show revision bars for text changed by the revision. There will not be a revision bar if text was deleted from the page. Page 2 Feb 1/10

INTRODUCTION

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Revised illustrations will be identified by a revision bar printed on the side of the page. 2. CD-ROM Revision Normal revised text on the CD-ROM will be highlighted yellow across the revised passage of text. For each revision of this manual, a new CD-ROM will be issued. The CD-ROM may contain revised illustrations. Revisions to the illustrations are not identified.

E. Temporary Revisions Temporary Revisions to this manual are issued to provide airworthiness information in the interim between normal revisions. Each temporary revision is issued by the chapter number to which it applies, followed by a sequential number in the order of publication (Temporary Revisions 12-1, 12-2, etc.). If relevant, the information in the temporary revision should be included in the next normal revision of the manual. 1. Paper Temporary Revisions Temporary Revisions are printed on yellow paper and are to be inserted in the maintenance manual in accordance with the instructions provided and adjacent to applicable chapter, section, and subject matter in the manual. 2. CD-ROM Temporary Revisions A new CD-ROM will be issued for each Temporary Revision to this manual. This information is listed in conjunction with the applicable chapter, section, subject on the CD-ROM.

F. Revised Text That portion of text which has been revised by the addition of, or a change in, punctuation and/or information is denoted by a solid revision bar adjacent to the textual column in the margin of this paragraph. Each page may or may not have revision bars. That date printed on the bottom of each page indicates when the information on that page was changed. Each page will ONLY show revision bars for punctuation and/or text changed by the current revision. Revised text in IML CD-ROM will be denoted by yellow highlighting.

G. Revised Illustrations When an illustration is modified or a new illustration is added, it will be noted by a solid line (revision bar) along the outside margin of the illustration.

H. Warnings, Cautions, and Notes

A27

•

WARNING - Brings attention to an operating procedure, inspection or maintenance practice, which if not correctly followed, could result in personal injury or loss of life.

•

CAUTION - Brings attention to an operating procedure, inspection, repair or maintenance condition, which if not strictly observed, could result in damage or destruction of equipment.

•

NOTE - Brings attention to an operating procedure, inspection, repair or maintenance condition, which is essential to highlight.

INTRODUCTION

Page 3 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I. Special Conditions Cautionary Notice Airplanes operated for Air Taxi, or other than normal operation, and airplanes operated in humid tropics, cold and damp climates, etc., may need more frequent inspections for wear, corrosion and/or lack of lubrication. Under these adverse conditions, perform periodic inspections in compliance with this guide at more frequent intervals until the owner or operator can set his own inspection periods based on the contingencies of field experience. CAUTION: The recommended periods do not constitute a guarantee the item will reach the period without malfunction as the aforementioned factors cannot be controlled by the manufacturer.

2. MANUAL LAYOUT A. Title Page A Title page is located at the beginning of the manual and provides the part number of the manual, and lists all aircraft models pertaining to this manual and their respective serial numbers. Information throughout this manual is applicable to all serial numbers listed on the title page except where specifically stated.

B. List of Effective Revisions/List of Effective Pages The printed manual will have a List of Effective Revisions/List of Effective Pages, (“A” page) following the title page of the manual. The List of Effective Revisions page lists the revisions currently effective for the manual. The List of Effective Pages section lists the page effectivity for the Title Page(s), “A” page(s) and Introduction chapter. It will also show the effective pages for an entire manual if the manual does not have individual Chapter List of Effective Pages.

C. Record of Revisions Page The printed manual will have a Record of Revisions page. The Record of Revisions is provided following the List of Effective Revisions/List of Effective Pages (“A” page). When a revision is inserted, the revision number, the date the revision is inserted into the manual, and the initials of the person(s) inserting the revision should be recorded on this page.

D. Log of Temporary Revisions Page The printed manual will have a Log of Temporary Revisions page. The Log of Temporary Revisions Page is located following the Record of Revisions page. The Log of Temporary Revisions page provides a history of each temporary revision, including the revision number which incorporated the temporary revision into the manual.

E. Record of Temporary Revisions Page The printed manual will have a Record of Temporary Revisions page. The Record of Temporary Revisions Page is located following the Log of Temporary Revisions page. When a temporary revision is inserted or removed from this manual, the appropriate information should be recorded on this page.

F. Introduction This section contains general and specific information on how to use this manual.

Page 4 Feb 1/10

INTRODUCTION

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

G. Chapter List of Effective Page The printed manual may have a Chapter List of Effective Pages. The List of Effective Pages follow the Chapter-Divider-Tab and lists the issue date of each page that is effective for that chapter.

H. Chapter Table of Contents Pages The printed manual may have a Chapter Table of Contents Pages. The Chapter Table of Contents Pages follow the Chapter List of Effective Pages and lists the contents of the data for that chapter.

3. HOW TO USE THE MANUAL A. ATA Subject Matter Assignment The contents of this manual are organized into four levels. The four levels are: (1) Level 1 - Group The various groups are identified by differently colored divider tabs. These are the primary divisions of the manual that enable broad separation of content. Typical of this division is the separation between Airframe Systems, Structure, and the Power Plant. (2) Level 2 - System/Chapter The various groups are broken down into major systems such as Air conditioning, Electrical Power, Landing Gear, etc. The systems are arranged more or less alphabetically rather than by precedence or importance. They are assigned a number, which becomes the first element of the standardized numbering system. Thus the element “24” of the number 24-30-01 refers to the chapter “ELECTRICAL POWER”. Everything concerning the electrical power system will be covered in this chapter. (3) Level 3 - Subsystem/Section The major systems/chapters of an airplane are broken down into subsystems/sections. These subsystems are identified by the second element of the standard numbering system. The element “30” of the number 24-30-01 concerns itself with the DC Generation system. (4) Level 4 - Unit/Subject The individual units within a subsystem/section may be identified by the third element of the standard numbering system. The element “01” of the number 24-30-01 is a subject designator. This element is assigned at the option of the manufacturer and may or may not be used. In this example, the subject is the “Starter-Generator”. (5) Additional Data - Page Block The data may be additionally broken down into page blocks. (a) Page Block 0 - Page 1 thru 99 System Description (b) Page Block 1 - Page 101 thru 199 Troubleshooting (c) Page Block 2 - Page 201 thru 299 Maintenance Practices

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INTRODUCTION

Page 5 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

B. Application Any publication conforming to the ATA format will use the same basic numbering system. Thus, whether the manual is a Maintenance Manual or a Wiring Diagram Manual, the person wishing information concerning the electrical system, would refer to the System/Chapter Tab “24 - ELECTRICAL POWER.” The table of contents in the front of this chapter will provide a list of subsystems covered in this chapter. For example, the electrical system chapter would contain: 24-00 - General 24-20 - AC Generation (portion of system used to generate, regulate, etc., AC electrical power) 24-30 - DC Generation (portion of system used to generate, regulate, etc., DC electrical power) 24-40 - External Power (portion of system used to connect external electrical power) 24-60- DC Electrical Load Distribution (portion of system used to supply DC electrical power to systems) The material is arranged within the chapter in ascending numerical sequence. The Chapter-Section-Subject number and page number are found at the lower outside corner of each page.

C. References to Procedures, Figures, Equipment and Materials A system has been developed to provide a method of allowing the user to quickly locate data referred to in the other manuals. This system provides information for both the printed manual as well as a hyperlink in electronic manuals. Here are a few examples: When the user is directed to a procedure in another manual, the text will be as follows: Perform the PASSENGER DOOR REMOVAL procedure (Ref. 52-10-01, 201, AMM). The procedure is found in Chapter 52-10-01 of the Maintenance Manual. When the user is in a procedure and is directed to information about a tool or piece of equipment, the text will be as follows: (Item, Chart, Chapter).

4. CHAPTER/SYSTEM INDEX GUIDE The following guide provides a list of Systems/Chapters used in this maintenance manual.

Page 6 Feb 1/10

INTRODUCTION

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

System/Chapter Index Guide System/Chapter

Subsystem/Section

Title

INTRODUCTION

5

6

TIME LIMITS/MAINTENANCE CHECKS 00

Time Limits/Maintenance Checks

11

Time Limits - Overhaul and Replacement

21

Scheduled Inspection Programs

22

Biennial Scheduled Inspection Programs

23

Continuous Corrosion Control Inspection

50

Unscheduled Maintenance Checks

DIMENSIONS AND AREAS 10

7

LIFTING AND SHORING 00

8

11

A27

Leveling and Weighing

TOWING AND TAXING 00

10

Lifting and Shoring

LEVELING AND WEIGHING 00

9

Dimensions and Areas

Towing and Taxing

PARKING AND MOORING 00

Parking and Mooring

10

Parking

20

Mooring

REQUIRED PLACARDS 00

Required Placards

20

Exterior Placards and Markings

INTRODUCTION

Page 7 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL System/Chapter Index Guide (Continued) System/Chapter

12

20

21

Page 8 Feb 1/10

Subsystem/Section

Title

SERVICING 00

General

10

Servicing

20

Scheduled Servicing

30

Unscheduled Servicing

STANDARD PRACTICES AIRFRAME 00

General

01

Torque Application

02

Electrostatic Discharge Sensitivity

03

Electrical Bonding

04

Control Cables and Pulleys

05

Bearings

06

Tube and Hose Assemblies and Fittings

07

Fastener Locking Devices

08

Airplane Finish

09

Corrosion

10

Sealing and Bonding

11

Fiberglass Repair

ENVIRONMENTAL SYSTEMS 00

Environmental System

10

Pressurization

20

Environmental Air Distribution

30

Pressurization Control

31

Auxiliary Pressurization Control

40

Heating

41

Radiant Heating, Cargo Door

50

Cooling

60

Temperature Control

INTRODUCTION

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL System/Chapter Index Guide (Continued) System/Chapter

22

Subsystem/Section

AUTO FLIGHT 10

23

24

25

26

A27

Title

Autopilot

COMMUNICATIONS 00

Communications

40

Interphone

60

Static Discharging

70

Cockpit Voice Recorder

ELECTRICAL POWER 00

Electrical Power

20

AC Generation

30

DC Generation and Control

31

Battery

32

Battery Monitor

40

External Power

50

Electrical Load Distribution

EQUIPMENT/FURNISHINGS 10

Flight Compartment

20

Passenger Compartment

30

Buffet/Galley

60

Emergency

80

Acoustics

FIRE PROTECTION 10

Fire Detection

11

Engine Bleed Air Warning

20

Fire Extinguishing

21

Portable Fire Extinguishers

INTRODUCTION

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL System/Chapter Index Guide (Continued) System/Chapter

27

28

30

31

Subsystem/Section

FLIGHT CONTROLS 00

Flight Controls

10

Aileron and Tab

20

Rudder Control System

21

Rudder Boost

30

Elevator and Tab (Pitch Control)

31

Stall Warning-Safe Flight System

50

Flaps

70

Gust Locks and Damper

FUEL 00

Fuel

10

Storage

20

Fuel Distribution

40

Indicating

ICE AND RAIN PROTECTION 00

Ice and Rain Protection

10

Airfoil Surface Deicer

20

Air Intakes

21

Brake Deice System

40

Windows and Windshields

60

Propeller Electric Deicers

INDICATING/RECORDING SYSTEM 50

Page 10 Feb 1/10

Title

INTRODUCTION

Central Warning Systems

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL System/Chapter Index Guide (Continued) System/Chapter

32

33

34

35

Subsystem/Section

LANDING GEAR 00

Landing Gear

10

Main Gear and Doors

20

Nose Gear and Doors

30

Extension and Retraction

40

Wheels and Brakes

41

Brake Deice

50

Steering

60

Position and Warning

LIGHTS 00

Lights

10

Flight Compartment

20

Passenger Compartment

40

Exterior Lighting

50

Emergency Lighting

NAVIGATION/PITOT and STATIC 00

Navigation/Pitot and Static

01

Navigational Components

10

Air Data System (For RVSM Compliant Airplanes)

OXYGEN 00

36

Oxygen

PNEUMATIC 00

A27

Title

Pneumatic

INTRODUCTION

Page 11 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL System/Chapter Index Guide (Continued) System/Chapter

37

Subsystem/Section

VACUUM 00

38

Vacuum System

WATER/WASTE 30

39

Title

Waste Disposal

ELECTRICAL PANELS, PARTS AND INSTRUMENTS 00

Electrical Panels and Components

10

Instrument and Control Panels

20

Center Section and Wings Electrical Panels

21

Fuselage Electrical Panels

STRUCTURES 51

STRUCTURES 00

52

53

Page 12 Feb 1/10

Structures

DOORS 00

Doors

10

Passenger/Crew Doors

11

Cargo and Airstair Door

20

Emergency Exit Doors

70

Passenger/Crew Door Warning

71

Cargo and Airstair Door Warning

FUSELAGE 00

Fuselage

10

Main Frame

11

Dynamic Vibration Absorbers

30

Plates and Skin

40

Attach Fittings

INTRODUCTION

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL System/Chapter Index Guide (Continued) System/Chapter 55

56

57

Subsystem/Section

Title

STABILIZERS 10

Horizontal Stabilizer

20

Elevators

30

Vertical Stabilizer

40

Rudder

WINDOWS 00

Windows

10

Windows - Crew Compartment

15

Window Inspection and Repair

20

Cabin Windows

WINGS 00

Wings

30

Plates/Skin

50

Flight Surfaces

PROPELLER 61

A27

PROPELLERS 00

Propellers

10

Propeller Assembly

20

Controlling

21

Autofeathering System

22

Synchrophasing

40

Indicating

INTRODUCTION

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL System/Chapter Index Guide (Continued) System/Chapter

Subsystem/Section

Title

POWER PLANT 71

POWER PLANT 00

Power Plant

10

Cowling

20

Mounts

30

Fireseals

50

Electrical Harness

70

Engine Drains

72

ENGINE

74

IGNITION 00

76

ENGINE CONTROLS 00

77

80

Exhaust

OIL SYSTEM 00

Oil System

30

Indicating

STARTING 00

Page 14 Feb 1/10

Engine Indicating

EXHAUST 00

79

Engine Controls

ENGINE INDICATING 00

78

Ignition

INTRODUCTION

Starting

A27

CHAPTER

Al RVVO RT H I N E SS

LIM ITATIONS

Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CHAPTER 4

AIRWORTHINESS LIMITATIONS

LIST OF EFFECTIVE PAGES CH-SE-SU

PAGE

DATE

4-LOEP

1

Apr 29/05

1

Apr

Chapter

A18

4

29/05

4-LOEP

Apr

29/05Pagel

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRWORTHINESS LIMITATIONS

mandatory Airworthiness Limitations, refer to the Super King (PIN 130-590031-211). For

Air B3001B300C Airworthiness Limitations Manual

John

Tigue

Raytheon Aircraft Company DOA-230339-CE

A1B

Chapter

4

Apr

29/05Page

1

C H A PT E R

TIME LIMITS/

MAINTENANCE CH EC KS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 5 - TIME LIMITS/MAINTENANCE CHECKS TABLE OF CONTENTS SUBJECT

PAGE 5-00-00

Time limits/Maintenance Checks - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Inspection Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Additional Requirements Introduced by Revision Action . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Conditions Cautionary Notice. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Inspection Programs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 200-Hour Phase Inspection Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Alternate Phase Inspection Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Biennial Inspection Program. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Special Inspection Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Overhaul and Replacement Schedule . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Unscheduled Maintenance Checks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Inspection and Maintenance Timetable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Inspection Program Squawk Sheet. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 5-11-00 Time Limits - Overhaul and Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Overhaul and Replacement Schedule . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 5-21-00 Scheduled Phase Inspection Program - Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 B300 Inspection Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Conditions Cautionary Notice. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 B300 Scheduled Inspection General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Inspection Interval Tolerance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Phase Inspections (Hour Interval) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Special Inspection Items - Calendar Date Limited . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Special Inspection Items - Flight Cycle Limited . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Special Inspection Items - Hourly Limited . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Purpose and Use . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Discrepancies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6

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5-CONTENTS

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CHAPTER 5 - TIME LIMITS/MAINTENANCE CHECKS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 5-21-01

Scheduled Inspection Program (Phase 1) - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Avionics Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pilot’s Compartment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rear Fuselage and Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Outboard Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Main Landing Gear Area. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Engine. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Outboard Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Main Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Landing Gear Retraction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operational Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Post Inspection Items. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inspection Completed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

201 201 201 201 201 202 203 203 204 205 207 207 208 209 210 211 212 212 216 217

5-21-02 Scheduled Inspection Program (Phase 2) - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Avionics Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pilot's Compartment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rear Fuselage and Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Outboard Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Main Landing Gear Area. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Engine. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Outboard Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Main Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Landing Gear Retraction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operational Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Post Inspection Items. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inspection Completed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

201 201 201 201 202 202 203 203 204 204 205 205 209 209 210 210 214 215 219 220

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PAGE 5-21-03

Scheduled Inspection Program (Phase 3) - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Nose Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Nose Avionics Compartment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Nose Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Nose Gear. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Pilot's Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Cabin Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Rear Fuselage and Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Left Side Outboard Wing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Left Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Left Side Main Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Left Side Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Right Side Outboard Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Right Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Right Side Main Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Right Side Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Landing Gear Retraction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Operational Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Post Inspection Items . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .219 Inspection Completed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 5-21-04 Scheduled Inspection Program (Phase 4) - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Nose Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Nose Avionics Compartment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Nose Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Nose Gear. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Pilot's Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Cabin Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Rear Fuselage and Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Left Side Outboard Wing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Left Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Left Side Main Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Left Side Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Right Side Outboard Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Right Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Right Side Main Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Right Side Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Landing Gear Retraction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Operational Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Inspection Completed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .219 Post Inspection Items . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .219

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PAGE 5-21-05

Scheduled Inspection Program (Special) - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Inspection Completed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 5-22-00 Biennial Scheduled Inspection Program - Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Biennial Inspection Program . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Special Conditions Cautionary Notice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Scheduled Inspection General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inspection Interval Tolerances. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Biennial Inspection (Calendar-Month Interval) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Special Inspection Items - Calendar Date Limited . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Special Inspection Items - Flight Cycle Limited. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Special Inspection Items - Hourly Limited . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inspection Compliance Option. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Purpose and Use. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Discrepancies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 1 2 2 2 2 2 3 3 3 3 4 5

5-22-01 Biennial Scheduled Inspection Program (Interim) - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . Operational Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Post Inspection Items. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inspection Completed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1 1 5 6

5-22-02 Biennial Scheduled Inspection Program (Complete) - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . Nose Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Avionics Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pilot's Compartment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rear Fuselage and Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Outboard Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Main Landing Gear Area. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left Side Engine. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Outboard Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Main Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Right Side Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

201 201 201 202 202 203 206 210 211 213 214 215 219 220 222 223

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PAGE

Landing Gear Retraction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .227 Operational Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .228 Post Inspection Items . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .232 Inspection Completed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .233 5-23-00 Continuous Corrosion Control Inspection - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Purpose and Use . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Wings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Empennage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Cowling and Truss . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Power Plant. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Propellers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Pilot’s Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Cabin Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Main Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Nose Landing Gear Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Nose Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Inspection Completed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6 Nose Avionics Compartment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6 Corrosion Temporary Treatment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6 5-50-00 Unscheduled Maintenance Checks - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Operation in Atmospheres of High Salt Content . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Operation in Atmospheres of High Industrial Air Pollution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 When Operating in Areas of High Dust Content . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 When Operating in Areas of High Humidity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Operating from Very Soft or Unusual Terrain . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Inspection after Hard Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Inspection after Encountering Turbulent Air . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10 Inspection after Lightning Strike . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .14 Engine Inspection after Sudden Stoppage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15 Inspection after Deployment of Landing Gear Above Critical Speed Condition . . . . . . . . . . . . . . . . . . . . . . . .16 Inspection after Deployment of Flaps Above Critical Speed Condition. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .18 Inspection in the Event of Deformed Steering Stop . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20

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List of Effective Pages CH-SE-SU

PAGE

DATE

5-LOEP

1

May 1/10

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1 thru 5

May 1/10

5-00-00

1 thru 31

May 1/10

5-11-00

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May 1/10

5-21-00

1 thru 6

Apr 28/06

5-21-01

201 thru 217

May 1/10

5-21-02

201 thru 220

May 1/10

5-21-03

201 thru 220

May 1/10

5-21-04

201 thru 219

May 1/10

5-21-05

201 thru 210

May 1/10

5-22-00

1 thru 5

Apr 28/06

5-22-01

1 thru 6

Apr 28/06

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Apr 28/06

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 5-00-00

TIME LIMITS/MAINTENANCE CHECKS - DESCRIPTION AND OPERATION WARNING: When an airplane has experienced abnormal landing gear procedures of any type, as a safety precaution, place the airplane on jacks prior to performing any inspection or maintenance. Make sure that all three landing gears are down and locked prior to removing the aircraft from jacks. CAUTION: Jacking of an airplane for the purpose of landing gear operation, inspection, servicing or maintenance should be accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary to jack the airplane in the open, wind velocity in any direction and terrain variations must be compensated for prior to jacking the airplane. This chapter contains an inspection and maintenance timetable, an overhaul and replacement schedule, all scheduled inspection forms and a chart for unscheduled maintenance checks.

INSPECTION PROGRAM The inspection program in this chapter is based on number of flight hours, cycles of operation and/or calendar time. The basis for calendar time limited inspections is the date on the “ORIGINAL STANDARD AIRWORTHINESS CERTIFICATE”, which is issued with a new airplane. Additionally, the Hawker Beechcraft Corporation recommends that operators record the number of cycles experienced on individual components for purposes of complying with inspections based on cycle count. Recorded hour-meter time or airplane log sheets can be used for determining when inspections and maintenance based on flight hours will be due. The method chosen for recording flight hours should remain consistent throughout the life of the airplane. NOTE: A flight cycle is defined as: Engine start-up and increase to full or partial power (as required during a normal flight), one landing gear retraction and extension, and a complete shutdown. The times in this inspection program have been established only as a guideline to give the owner/operator a benchmark from which to begin the program. The service history or fleet experience of a particular operation may indicate that departure from the times in this chapter could be beneficial. All inspections listed in this chapter should be accomplished with reference to the Super King Air B300/B300C Maintenance Manual and the appropriate supplier maintenance publications. Maintenance information on most of the major components of the airplane is contained in the King Air Series Component Maintenance Manual.

ADDITIONAL REQUIREMENTS INTRODUCED BY REVISION ACTION Unless otherwise directed by relevant notification or Service Bulletin, additional requirements introduced into the Inspection Schedule must be accomplished within 12 calender months.

SPECIAL CONDITIONS CAUTIONARY NOTICE Airplanes operated for Air Taxi, or other than normal operation and airplanes operated in humid tropics, cold and damp climates, etc., may need more frequent inspections for wear, corrosion and/or lack of lubrication. Under these adverse conditions, perform periodic inspections in compliance with this guide at more frequent intervals until the owner/operator can set his own inspection periods based on the contingencies of field experience. NOTE: The recommended periods do not constitute a guarantee the item will reach the period without malfunction as the aforementioned factors cannot be controlled by the manufacturer.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION PROGRAMS The Hawker Beechcraft Corporation approved inspection program contained in this chapter is specifically for the Super King Air B300/B300C airplanes. Any variation to the inspection program must be approved by an FAA Flight Standards District Office (FSDO) or Airworthiness Authority. 200-HOUR PHASE INSPECTION PROGRAM A complete inspection cycle is 800 hours or 24 calender months. The inspection cycle is divided into four phases and each inspection cycle is done at 200 hours with each consecutive phase 200 hours after the previous phase. The Phase 1, 2, 3 and 4 inspections provide a thorough inspection of specific components and systems. A complete inspection cycle is as follows:

PHASE

HOURS

1

-

200

2

-

400

3

-

600

4

-

800

NOTE: All four phase inspections must be completed within 24 calendar months. Although the times of the inspections may be altered, each item should be accomplished as stated in the inspection program. A detailed preamble to this subchapter is included and should be read and understood before beginning the Inspection Program. ALTERNATE PHASE INSPECTION PROGRAM For users flying less than 400 hours but more than 200 hours in 24 months, perform the Alternate Phase Inspection in Chapter 5-21-00. Alternate Phase Inspection: If an aircraft is not flown at least 400 hours in 24 months, the owner/operator has the option of inspecting the aircraft as follows: •

Perform scheduled phase inspections 1 and 2 together within 12 months after the last inspection; then perform scheduled phase inspections 3 and 4 together within 12 months after completing the phase 1 and 2 inspections.

NOTE: Hawker Beechcraft Corporation recommends that no aircraft exceed 12 months without completing at least one phase inspection.

PHASE

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5-00-00

HOURS

1&2

-

200

3&4

-

400

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL BIENNIAL INSPECTION PROGRAM For users flying less than 200 hours in 24 months, perform the Biennial Inspection Program in Chapter 5-22-01. Biennial Inspection: The inspection program is for users flying less than 200 hours in 24 months and it is made up of an INTERIM INSPECTION and a COMPLETE INSPECTION. •

Perform an INTERIM INSPECTION at 12 months. Thereafter, perform an INTERIM INSPECTION no later than 12 months from the last COMPLETE INSPECTION.

•

Perform a COMPLETE INSPECTION at 24 months. Thereafter, perform a COMPLETE INSPECTION no later than 24 months from the last COMPLETE INSPECTION.

SPECIAL INSPECTION REQUIREMENTS NOTE: The requirements of this portion of the Scheduled Inspection may be accomplished by either: (1) Inspection in accordance with the appropriate information in the applicable maintenance manual, or (2) Exchange parts from Hawker Beechcraft Global Customer Support Parts and Distribution Division may be purchased and installed. Compliance with one of these two options is at the discretion of the maintenance facility performing the inspection. This section consists of components that are subject to a thorough inspection based on calendar time, operating hours or cycles which do not coincide with the intervals established by the scheduled inspection program. These inspections should be done with reference to this maintenance manual and the King Air Series Component Maintenance Manual. When disassembly is required to accomplish these inspections, it should be performed in accordance with the applicable component manuals. Discrepancies noted during these inspections should be noted on worksheets for corrections. The first inspection must be performed no later than the recommended period. The condition of the item at the end of the first period can be used as a criterion for determining subsequent periods applicable to the individual airplane or fleet operation, provided the operator has an approved condition-monitoring system. The time periods for inspections noted in this manual are based on average usage and average environmental conditions.

OVERHAUL AND REPLACEMENT SCHEDULE The first overhaul and replacement must be performed no later than the recommended period. The time periods for overhaul and replacement noted in this manual are based on average usage and average environmental conditions. Items NOT listed are to be overhauled or replaced “On Condition.” If “On Condition” items are worn, inoperative, inaccurate, intermittent and are not repairable through normal maintenance practices, they must be overhauled or replaced.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

UNSCHEDULED MAINTENANCE CHECKS This subchapter is assembled in chart form to allow a technician to perform checks for damage after operating the airplane in conditions which could require unscheduled maintenance. Specific conditions, such as lightning strikes, turbulent air penetration or hard landing etc., are included. Inspection instructions are included for each of the conditions listed. NOTE: Additional inspections may be required by engine or propeller manufactures in their manuals. Refer to the unscheduled maintenance checks portion of the supplier issued manuals to make sure continued airworthiness.

INSPECTION AND MAINTENANCE TIMETABLE NOTE: This form is provided for reference purposes only and does not replace or take precedence over the scheduled inspection form in Chapter 5-21-00. The Inspection and Maintenance Timetable contains a listing of the components and system requiring scheduled inspection and/or maintenance action. Components are listed in order of chapter reference where applicable. This form has four columns labeled: Item, Inspection Timetable, Interval and Phase Inspection Area. Item Column - This list the various items to be inspected. Inspection Timetable Column - Items are marked to indicate at which phase (1, 2, 3 or 4) they are to be inspected or to indicate that an interim (INT), complete (COMP) or special inspection (SPL) is required. NOTE: The complete (COMP) inspection is a Phase 1 thru 4 inspection without the duplication. Interval Column - This column indicates the recommended hours, calendar time or cycles between inspection or maintenance actions. Phase Inspection Area Column - The letter(s) in this column represents the location of the inspection line item in the scheduled inspection forms.

INSPECTION PROGRAM SQUAWK SHEET In order to make this inspection program user friendly, we have included an Inspection Program Squawk Sheet. Write your suggestions concerning the Inspection Program on the Squawk Sheet and mail the Sheet to the address listed below: Hawker Beechcraft Corporation Technical Support Department 213 P.O. Box 85 Wichita, KS 67201-0085

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SUPER KING AIR B300/B300C INSPECTION PROGRAM SQUAWK SHEET

We are constantly striving to make this Inspection Program more usable in the field. In order to do this, we need your comments, criticism and suggestions concerning any aspect of this program. Please be sure that your correct mailing address and business phone number are provided. Thank You Hawker Beechcraft Corporation Technical Support PLEASE FURNISH THE FOLLOWING: INSPECTION GUIDE TITLE:____________________

YOUR NAME:________________________________

PART NUMBER:______________________________ MAILING ADDRESS:__________________________ REVISION DATE:_____________________________ ___________________________________________ PHASE NO.:_________________________________

BUSINESS PHONE NO.:_______________________

PAGE & LINE ITEM NO.:_______________________ COMMENTS: Briefly describe any errors you may have encountered or suggestions as to type of additional coverage you feel is needed. _________________________________________________________________________________________ _________________________________________________________________________________________ _________________________________________________________________________________________ _________________________________________________________________________________________ _________________________________________________________________________________________ _________________________________________________________________________________________ _________________________________________________________________________________________ _________________________________________________________________________________________ _________________________________________________________________________________________ _________________________________________________________________________________________ Please mail to:

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Hawker Beechcraft Corporation Technical Support Department 213 P.O. Box 85 Wichita, Kansas 67201-0085

5-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SCHEDULED INSPECTION WORKSHEET INSPECTION PHASE L ENG. TIME ___________ CYCLES ____________ R ENG. TIME ___________ CYCLES AC TIME ______________ CYCLES ______________ AC SERIAL ______________ DATE ITEM

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DISCREPANCY AND CORRECTIVE ACTION

5-00-00

MECH

CREW CHIEF

Q.C.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

IN-FLIGHT WORKSHEET (Page 1 of 2) S/N ______________ N NUMBER _____________ DATE __________________ NO. FLT NO

PILOT

COPILOT

TO

TIME

LND

TIME

NO LND

FLT TM

Today Total Previous Total Total

FUEL TYPE

ENG. OIL GAL

LEFT

CRUISE CONDITION RIGHT

WEATHER

LEFT

RIGHT

O.A.T. PA IAS ITT TORQUE PROP RPM N1 RPM FUEL FLOW FUEL PRESS OIL PRESS OIL TEMP

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

IN-FLIGHT WORKSHEET (Page 2 of 2) DISCREPANCY WORKSHEET S/N _______________ N NUMBER ____________________ DATE _________________ NO. A/C HRS

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DATE

DISCREPANCY

5-00-00

CORRECTIVE ACTION

DATE

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OVERHAUL AND REPLACEMENT WORKSHEET

COMPONENT

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DATE

REASON FOR REPLACEMENT

REPLACEMENT Part No. Serial No.

5-00-00

NEXT O. H. A/C Hours or Cycles Date

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AND MAINTENANCE TIMETABLE

ITEM

AC Inverter, Operational Check Access Doors Access Doors, Pilot’s Compartment Access Doors (Inspection Panels), Wing Access Doors, Wing Hinged

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

1, 2, 3, 4 INT, COMP

Q

1, 2, 3, 4 COMP

F, G

3 COMP

E

1, 2, 3, 4 COMP

H, I, L, M

1 COMP

H, L

Actuator Clevis, Main Landing Gear

SPL

1,000 CYCLES

Actuator Clevis, Nose Landing Gear

SPL

1,000 CYCLES

Actuator, Main Landing Gear

1, 2, 3, 4 COMP

J, N, P

Actuator, Nose Landing Gear

2, 4 COMP

D

1, 2, 3, 4 INT, COMP

R

Additional Inspection Requirements Aft Fuselage Area and Aft Pressure Bulkhead

SPL

10,000 CYCLES INITIAL/ 500 CYCLES RECURRING

Aileron and Outboard Flap

1 COMP

H, L

Aileron and Trim Tab

1, 3 COMP

H, L

Aileron Operational Check

1, 2, 3, 4 INT, COMP

Q

Aileron Quadrant Regulator

3 COMP

F

1, 2, 3, 4 INT, COMP

Q

Aileron Trim Tab Operational Check

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

Air Data System (For RVSM Compliant Airplanes)

SPL

24 Months

Air Inlet Duct, Engine Induction

PHASE INSPECTION AREA

2 COMP

K, O

Airplane Lubrication

1, 2, 3, 4 INT, COMP

R

Airplane Reweigh

Refer to 14 CFR 135

Airworthiness Directives and Service Bulletins Compliance Check

1, 2, 3, 4 INT, COMP

R

Alternate Air Valve

1, 2, 3, 4 INT, COMP

E

Alternate Air Valve Operational Check, Static System

1, 2, 3, 4 INT, COMP

Q

Altimeter-Pitot-Static System

SPL Refer to 14 CFR 91

24 MONTHS

Antennas

3 COMP

F

Autofeather Pressure Switch

2 COMP

K, O

1, 2, 3, 4 INT, COMP

Q

2 COMP

K, O

1, 2, 3, 4 INT, COMP

Q

3 COMP

F

Autopilot Operational Check

1, 2, 3, 4 INT, COMP

Q

Auxiliary Fuel Transfer Jet Pumps Operational Check

1, 2, 3, 4 INT, COMP

Q

Auxiliary Electric Heat Operational Check

1, 2, 3, 4 INT, COMP

Q

Autofeathering Operational Check Auto-ignition Pressure Switch Auto-ignition Operational Check Autopilot Components

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5-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

Avionics and Autopilot Equipment and Racks, Rear Fuselage and Empennage

4 COMP

G

Avionics Equipment and Racks, Cabin (If Installed)

3 COMP

F

Avionics Equipment and Racks, Nose

4 COMP

B

Axle Assembly and Torque Knee, Nose Landing Gear

SPL

Axle Assembly and Torque Knee, Nose Landing Gear (If operated on or from unimproved runways)

SPL

Axle Assembly and Torque Knee, Main Landing Gear

SPL

Axle Assembly and Torque Knee, Main Landing Gear (If operated on or from unimproved runways)

SPL

Battery

INTERVAL

8,000 CYCLES OR 6 YRS 3,000 CYCLES OR 3 YRS 8,000 CYCLES OR 6 YRS 3,000 CYCLES OR 3 YRS

1, 2, 3, 4 COMP

Battery, Emergency Capacity Test

Battery, Lead Acid

PHASE INSPECTION AREA

M

SPL

12 MONTHS OR 600 HR/ 12 MONTHS OR 200 HRS

SPL

90 DAYS

Bleed Air Bypass Valve

1 COMP

I, M

Bleed Air Flow Control Valve, Environmental

2 COMP

K, O

Boost Pumps Operational Checks

1, 2, 3, 4 INT, COMP

Q

Brake Deice System Operational Check (If Installed)

1, 2, 3, 4 INT, COMP

Q

1, 2, 3, 4 COMP

J, N

Brake Deicing (If Installed)

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Brake System, Pilot's Compartment Brakes Bulkhead, Forward Pressure

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

3 COMP

E

1, 2, 3, 4 COMP

J, N

SPL

2,500 CYCLES

Bulkheads

3 COMP

F

Bus Conformity Check

3 COMP

E

Cabin Door and Emergency Exits

3 COMP

F

Cabin Door and Fuselage Frame SPL

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

Cabin Door Operational Check

1, 2, 3, 4 INT, COMP

Q

Cabin Seats Operational Check

1, 2, 3, 4 INT, COMP

Q

4 COMP

F

1, 2, 3, 4 INT, COMP

Q

1 COMP

I, M

Cleanliness, Flight Compartment and Cabin

1, 2, 3, 4 INT, COMP

R

Compressor Drive Belt, Air-Conditioner

2 COMP, SPL

Cabin Section Area Cargo Door Operational Check Center Section Area

50 HRS

O

Compressor Drive Quill Shaft Lubrication

2 COMP

O

Compressor Inlet, Engine

2, 4 COMP

K, O

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

Compressor, Air-Conditioner

2, 4 COMP

O

Condenser Blower, Air-Conditioner

2, 4 COMP

C

1, 2, 3, 4 INT, COMP

Q

Control Cable Seals, Rear Fuselage and Empennage

4 COMP

G

Control Cable Seals, Cabin

3 COMP

F

Control Column

3 COMP

E

Crossfeed Fuel Valve Operational Check

1, 2, 3, 4 INT, COMP

Q

Deice System Operational Check, Surface

1, 2, 3, 4 INT, COMP

Q

Deicer Boots, Empennage

1, 2, 3, 4 COMP

G

Deicer Boots, Propeller

1, 2, 3, 4 COMP

K, O

Deicer Boots, Wing

1, 2, 3, 4 COMP

H, L

3 COMP

F

Condition Levers Operational Check

Deicer Distributor Valve Door, Cabin

1, 3 COMP, SPL

5,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

F

Door, Cabin (Replace Latch-Bolts) Refer to Chapter 4-00-00. Door, Cabin (Replace Upper Hook) Refer to Chapter 4-00-00.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

1, 3 COMP, SPL

5,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

F

Door, Cargo

Door, Cargo, Lower Attachment Lugs (FM-1 and After)

SPL

Door, Emergency Exit (Escape Hatch) 1, 3 COMP, SPL

AS REQ 5,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

Door, Nose Avionics

4 COMP

B

Door Latches, Aft Cowling Access

2, 4 COMP

K, O

Doors and Linkage, Landing Gear

1, 2, 3, 4 COMP

P

Downlock Mechanism, Landing Gear

1, 2, 3, 4 COMP

P

Drag Brace, Nose Landing Gear Drag Brace, Nose Landing Gear (If operated on or from unimproved runways) Drag Brace Stop Lugs, Nose Landing Gear Drag Brace, Main Landing Gear Drag Brace, Main Landing Gear (If operated on or from unimproved runways) Drag Leg, Nose Landing Gear

SPL

8,000 CYCLES OR 6 YRS

SPL

3,000 CYCLES OR 3 YRS

1, 2, 3, 4 COMP

D

1, 3 COMP, SPL

8,000 CYCLES OR 6 YRS

SPL

3,000 CYCLES OR 3 YRS

J, N

2, 4 COMP

D

Drain Holes, Rudder and Trim Tab

1, 2, 3, 4 COMP

G

Drain Holes, Ventral Fin

1, 2, 3, 4 COMP

G

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5-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Drain Holes, Wing Attach Fittings

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

1, 2, 3, 4 COMP

H, L

Drain Plugs, Engine

2, 4 COMP

K, O

Drain Valves, Belly

3 COMP

F

1, 2, 3, 4 COMP

G

Drains, Rear Fuselage Edgelighted Panel Assemblies

SPL

2,000 HRS OR 4 YRS

EFIS Cooling Blower Operational Check (If Installed)

1, 2, 3, 4 INT, COMP

Q

Electric Elevator Trim Operational Check

1, 2, 3, 4 INT, COMP

Q

Electrical System Operational Check

1, 2, 3, 4 INT, COMP

Q

Electrical Wiring and Equipment, Cabin

3 COMP

F

Electrical Wiring and Equipment, Center Section

1 COMP

I, M

Electrical Wiring and Equipment, Main Landing Gear

1, 2, 3, 4 COMP

J, N

Electrical Wiring and Equipment, Nose Avionics Compartment

4 COMP

B

Electrical Wiring and Equipment, Nose Landing Gear

1 COMP

D

Electrical Wiring and Equipment, Nose Landing Gear Area

1, 2, 3, 4 COMP

C

Electrical Wiring and Equipment, Pilot's Compartment

3 COMP

E

Electrical Wiring and Equipment, Rear Fuselage and Empennage

4 COMP

G

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

Electrical Wiring and Equipment, Wing

1 COMP

H, I, L, M

Elevator Trim Tab

2, 4 COMP

G

Elevator and Rudder Hinge Brackets

2, 4 COMP

G

1, 2, 3, 4 INT, COMP

R

1, 2, 3, 4 COMP

G

1, 2, 3, 4 INT, COMP

R

1, 2, 3, 4 COMP

F

ELT - ARMED ELT Battery ELT Battery (Replace) Refer to Chapter 5-11-00. Emergency and Survival Equipment Emergency Exit Light Batteries (Inspect) Emergency Exit Light Batteries (Replace) Refer to Chapter 5-11-00. Emergency Exits (Escape Hatches) Operational Check

1 YR 1, 2, 3, 4 INT, COMP

Q

1, 2, 3, 4 COMP

P

2, 4 COMP

G

1, 2, 3, 4 INT, COMP

Q

Emergency Exit Sign (Self-illuminating) Refer to Chapter 4-00-00. Emergency Extension, Landing Gear Empennage and Control Surfaces Empennage Control Surfaces Operational Check Engine Refer to Chapter 5-11-00.

2, 4 COMP

Engine and Propeller Controls

2, 4 COMP

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PER P&W S.B. 13303

K, O K, O

5-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Engine and Propeller Controls Operational Check

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

1, 2, 3, 4 INT, COMP

Q

Engine Control Cable Boots

2, 4 COMP

K, O

Engine Cowling

2, 4 COMP

K, O

Engine Hot Section

SPL

PER P&W S.B.13303

Engine Inertial Anti-Icer Operational Check

1, 2, 3, 4 INT, COMP

Q

Engine Inspection (After Ground Run-Up or Flight Test)

1, 2, 3, 4 INT, COMP

R

Engine Mount Truss Assembly

2 COMP

K, O

Engine Oil Cooler

2, 4 COMP

K, O

1, 2, 3, 4 INT, COMP

Q

Engine-Driven Fuel Pump Coupling Shaft

2, 4 COMP

K, O

Environmental System

3 COMP

E, F

1, 2, 3, 4 INT, COMP

Q

2, 4 COMP

K, O

1, 2, 3, 4 INT, COMP

Q

1, 3 COMP

F

1, 2, 3, 4 COMP

K, O

Engine Oil Temperature and Pressure Operational Check

Environmental System Operational Check Exhaust System, Engine External Power Relay Operational Check Filter, Aft Evaporator (Effectivity: FL-1 thru FL-492 and FL-494 thru FL-499) Filter, Engine Oil (Inspect)

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5-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

Filter, Engine Oil (Replace) Refer to Chapter 5-11-00 Filter, Forward Evaporator (Effectivity: FL-1 thru FL-492 and FL-494 thru FL-499)

2, 4 COMP

C

Filters and Screens, High Pressure Fuel Pump

2, 4 COMP

K, O

Filter, Instrument Air

2, 4 COMP

B

1, 2, 3, 4 COMP

E

Filter, Vacuum Regulator Valve

2, 4 COMP

B

Fire Detection System, Engine

2 COMP

K, O

1, 2, 3, 4 INT, COMP

Q

Filter, Pilot's Compartment Return Air Inlet

Fire Detection System Operational Check, Engine Fire Extinguisher Cartridge (Squib)

SPL

Fire Extinguisher, Cabin

3 COMP, SPL

12 YRS

Fire Extinguisher, Engine

1, 3 COMP, SPL

5 YRS

Fire Extinguisher System Operational Check, Engine

1, 2, 3, 4 INT, COMP

Fire Extinguisher, Pilot's Compartment

1, 3 COMP, SPL

Fireseals

F I, M Q

12 YRS

E

2, 4 COMP

K, O

1, 2, 3, 4 INT, COMP

Q

Flap Motor and Drives

3 COMP

F

Flap Tracks

1 COMP

H, I

Firewall Shutoff Fuel Valves Operational Check

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5-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

Flapper Valve

4 COMP

F

Flaps and Actuators

1 COMP

H, I, L, M

1, 2, 3, 4 INT, COMP

Q

1 COMP

H,L

Flaps and Actuators Operational Check Flap Safety Switch Flexible Shaft, Flaps

SPL

5,000 CYCLES

Flight Control Cable Tension

1 COMP

E, G

Flight Control Components, Cables and Pulleys; Cabin

3 COMP

F

Flight Control Components, Cables and Pulleys; Pilot's Compartment

3 COMP

E

Flight Control Components, Cables and Pulleys; Rear Fuselage and Empennage

4 COMP

G

Flight Control Components, Cables and Pulleys; Wing

1 COMP

H, I, L, M

Flight Control Pulley Brackets and Castings SPL

10,000 CYCLES INITIAL/ 5,000 CYCLES RECURRING

SPL

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

SPL

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

Frame Web, Fuselage

Frames, Fuselage Subfloor

Fuel Filler Cap and Antisiphon Valve

Page 20 May 1/10

5-00-00

1, 2, 3, 4 COMP

H, I, L, M

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Fuel Filters and Screens, Firewall

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

1, 2, 3, 4 COMP

K, O

Fuel Nozzle, Engine

2, 4 COMP

K, O

Fuel Plumbing, Leading Edge and Nacelle

1 COMP

I, M

Fuel Plumbing, Outboard Wing

1 COMP

H, L

Fuel Probe (Nacelle) Fuel Probes

SPL

2,400 HRS OR 30 MONTHS

1, 2, 3, 4 COMP

H, I, L, M

Fuel Pumps, Center Section

1, 3 COMP

I, M

Fuel Purge System

2, 4 COMP

K, O

Fuel Purge System Air Tank

2, 4 COMP

K, O

Fuel Purge System Check Valve

2, 4 COMP

K, O

Fuel Purge System Flow Divider/Purge Valve

2, 4 COMP

K, O

Fuel Purge System Tank Filter

2 COMP

K, O

Fuel Quantity Gages Operational Check

1, 2, 3, 4 INT, COMP

Q

Fuel Tank Heated Vents Operational Check

1, 2, 3, 4 INT, COMP

Q

Fuel Tank, Integral

1, 2, 3, 4 COMP

H, L

Fuel Tanks and Vents

1, 2, 3, 4 COMP

H, I, L, M

A28

5-00-00

Page 21 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Gyro Instruments Operational Check

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

1, 2, 3, 4 INT, COMP

Q

Hydraulic Lines, Landing Gear

3 COMP

F

Hydraulic Power Pack and Motor, Landing Gear

1, 3 COMP

I

Hoses, Brake System (Replace) Refer to Chapter 5-11-00. Hoses, Engine Compartment (Replace) Refer to Chapter 5-11-00. Hoses, Hydraulic Gear Extension/Retract (Replace) Refer to Chapter 5-11-00.

Hydraulic Power Pack Fill Reservoir Screen, Landing Gear

SPL

200 HRS/ 1,200 HRS

Hydraulic Power Pack Gear-Up/Gear-Down Port Screens, Landing Gear

1, 3 COMP

I

Hydraulic Reservoir Overboard Relief Orifice Screen, Landing Gear

1, 3 COMP

I

Hydraulic Hand Pump Suction Line Filter/Screen

3 COMP

F

1, 2, 3, 4 INT, COMP

Q

Igniter Plugs

2 COMP

K, O

Ignition Exciter

2 COMP

K, O

Ignition Operational Check

1, 2, 3, 4 INT, COMP

Q

Induction System, Engine

2 COMP

K, O

1, 2, 3, 4 INT, COMP

Q

Idle RPM Operational Check

Induction System Operational Check, Engine

Page 22 May 1/10

5-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Inertial Anti-Icer

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

2 COMP

K, O

1, 2, 3, 4 INT, COMP

Q

Inertial Separator

2 COMP

K, O

Inlet Screen, Engine Induction

2 COMP

K, O

Instrument Panel Plumbing and Wiring

3 COMP

E

Inertial Anti-Icer Operational Check

Instrument Panel Stringers and Support Brackets

SPL

10,000 CYCLES

Interstage Turbine Temperature Operational Check

1, 2, 3, 4 INT, COMP

Q

In-flight Worksheet Discrepancies

1, 2, 3, 4 INT, COMP

R

1, 2, 3, 4 COMP

D, F, G, H, L

Lights Operational Check, All

1, 2, 3, 4 INT, COMP

Q

Logbook Entry

1, 2, 3, 4 INT, COMP

R

Lights, All

Lower Attachment Lug, Cargo Door

SPL

AS REQ

Magnetic Chip Detector

2, 4 COMP

K, O

Main Landing Gear Area

1 COMP

J, N

Nose Avionics Compartment Area

4 COMP

B

Nose Landing Gear

4 COMP

D

Nose Landing Gear Area

4 COMP

C

A28

5-00-00

Page 23 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

Nose Section

4 COMP

A

Oil Cooler, Engine

2, 4 COMP

K, O

Orifice, Brake Fluid Reservoir Pressure Equalization

3 COMP

E

Outboard Wing Area

1 COMP

H, L

1, 2, 3, 4 COMP

F

Outflow and Safety Valves Oxygen Cylinder Test (Lightweight) (DOT 3HT 1850)

SPL

3 YRS

Oxygen Cylinder, (Lightweight Composite) (Replace) Refer to Chapter 4-00-00. Oxygen System Oxygen System Pressure

1, 3 COMP

F

1, 2, 3, 4 INT, COMP

R

1, 2, 3, 4 COMP

K, O

3 COMP

E

1, 2, 3, 4 INT, COMP

Q

3 COMP

E

1, 2, 3, 4 INT, COMP

Q

Oxygen System Passenger Shutoff Valve O-ring Refer to Chapter 5-11-00. P3 Air Filter (Inspect) P3 Air Filter (Replace) Refer to Chapter 5-11-00. Pedestal Pilot and Copilot Seats Operational Check Pilot’s Compartment Pitot Heat Operational Check Pitot System

Page 24 May 1/10

SPL

5-00-00

24 MONTHS

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Placards

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

1, 2, 3, 4 INT, COMP

R

4 COMP

G

1, 2, 3, 4 INT, COMP

Q

3 COMP

F

1, 2, 3, 4 INT, COMP

Q

Position Indicators, Landing Gear

1, 2, 3, 4 COMP

P

Power Levers Stop Pin, Pedestal

SPL

Plumbing, Rear Fuselage Pneumatic Pressure Gage Operational Check Pneumatic Pressure Regulator Pneumatic System Shutoff Valves Operational Check

1,200 HRS

Pressurization Controller and Filter

3 COMP

E

Pressurization System Ducts

2, 4 COMP

F

1, 2, 3, 4 INT, COMP

Q

4 COMP

G

Propeller Deicer

1, 2, 3, 4 INT, COMP

K, O

Propeller Deicer Operational Check

1, 2, 3, 4 INT, COMP

Q

Propeller Flight Idle Torque Operational Check

1, 2, 3, 4 INT, COMP

Q

Propeller Governor Operational Check

1, 2, 3, 4 INT, COMP

Q

Propeller Overspeed Governor

2 COMP

K, O

Propeller Primary Governor

2 COMP

K, O

Pressurization System Operational Check Pressurization System Overboard Dump System, Cabin

A28

5-00-00

Page 25 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Propeller Synchrophaser

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

2 COMP

K, O

1, 2, 3, 4 INT, COMP

Q

1, 2, 3, 4 COMP

K, O

4 COMP

A

1, 2, 3, 4 INT, COMP

Q

Refrigerant Lines and Pressure Switches, Wing Center Section

1 COMP

M

Refrigerant Lines, Service Valves and High Pressure Relief Valves, Nose Landing Gear Area

4 COMP

C

Refrigerant Lines and Service Valves, Pilot's Compartment

3 COMP

E

Refrigerant Lines and Service Valves, RH Engine Area

2, 4 COMP

O

Relief Tube, Cabin

3 COMP

F

Relief Tube, Pilot's Compartment

3 COMP

E

Retract Mechanism, Landing Gear

1, 2, 3, 4 COMP

P

Rudder Boost Operational Check

1, 2, 3, 4 INT, COMP

Q

Rudder Boost Transducer

2 COMP

K, O

Rudder Pedals

3 COMP

E

Rudder Torque Tube Shaft Arm

4 COMP

G

Propeller Synchrophaser Operational Check Propellers Refer to Chapter 5-11-00. Radome Refrigerant Level Operational Check

Page 26 May 1/10

5-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Rudder Trim Tab

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

2, 4 COMP

G

1, 2, 3, 4 COMP

P

Screen, Safety Valve (Clean/Test)

3 COMP

F

Seal and Fasteners, Nose Avionics Door

4 COMP

B

Seat Belts and Shoulder Harnesses

1, 3 COMP

E, F

1, 2, 3, 4 INT, COMP

Q

3 COMP

E, F

1, 2, 3, 4 COMP

D

Safety Switch, Landing Gear

Seat Belts and Shoulder Harnesses Operational Check Seat Tracks Shimmy Damper, Nose Landing Gear Shock Absorber, Nose Landing Gear Shock Absorber, Nose Landing Gear (If operated on or from unimproved runways) Shock Absorbers, Main Landing Gear Shock Absorbers, Main Landing Gear (If operated on or from unimproved runways)

SPL

8,000 CYCLES OR 6 YRS

SPL

3,000 CYCLES OR 3 YRS

SPL

8,000 CYCLES OR 6 YRS

SPL

3,000 CYCLES OR 3 YRS

Skin, Cabin Door and Emergency Exits

3 COMP

F

Skin, Cabin Section Area

3 COMP

F

Skin, Exterior Airframe SPL

Skin, Nose Avionics Compartment

A28

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

4 COMP

B

5-00-00

Page 27 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

Skin, Nose Landing Gear Area

4 COMP

C

Skin, Nose Section Area

4 COMP

A

Skin, Rear Fuselage and Empennage

4 COMP

G

Skin, Wing

1 COMP

H, I, L, M

Spar Cap, Forward Upper and Lower SPL

5 YRS INITIAL/ 1 YR RECURRING

Stall Warning Operational Check

1, 2, 3, 4 INT, COMP

Q

Stall Warning Heat Operational Check

1, 2, 3, 4 INT, COMP

Q

Starter-Generator Operational Check

1, 2, 3, 4 INT, COMP

Q

Starter-Generator Overhaul Refer to Chapter 5-11-00. Starter-Generator QAD Attachment Flange

SPL

WHEN S-G IS REMOVED

Starter-Generator Brushes

2, 4 COMP

K, O

Static Ground Receptacles

1, 2, 3, 4 COMP

H, L

Static System

SPL

Static Wicks Steering Linkage, Nose Landing Gear Steering Stop, Nose Landing Gear Stringers, Fuselage

Page 28 May 1/10

5-00-00

24 MONTHS

1, 2, 3, 4 COMP

G, H, L

1, 3 COMP

D

1, 2, 3, 4 COMP

D

SPL

AS REQ

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

Structure, Cabin Door and Emergency Exits

3 COMP

F

Structure, Cabin Section Area

3 COMP

F

Structure, Main Landing Gear Area

1, 3 COMP

J, N

Structure, Nose Landing Gear Area

4 COMP

C

Structure, Nose Section Area

4 COMP

A

Structure, Pilot's Compartment

3 COMP

E

Structure, Rear Fuselage and Empennage

4 COMP

G

Structure, Wing

1 COMP

H, I, L, M

Strut, Nose Landing Gear

1 COMP

D

Struts, Main Landing Gear

1, 2, 3, 4 COMP

J, N

Tires

1, 2, 3, 4 COMP

D, J, N

Toilet

1, 3 COMP

F

Transponder Recertification

REFER TO 14 CFR

24 MONTHS

Underwater Locator Beacon, Cockpit Voice Recorder. Refer to Chapter 5-11-00. Upholstery Panels, Cabin

2 COMP

F

Upholstery Panels, Pilot's Compartment

1 COMP

E

A28

5-00-00

Page 29 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

Vacuum Ejector

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

PHASE INSPECTION AREA

3 COMP

F

1, 2, 3, 4 INT, COMP

Q

4 COMP

G

Warning Horn, Landing Gear

1, 2, 3, 4 COMP

P

Weather Seal (Silicone), Windshield

1, 2, 3, 4 COMP

E

Wheel Bearings

1, 2, 3, 4 COMP

D, J, N

Wheel, Nose Landing Gear

1, 2, 3, 4 COMP, SPL

D

Wheels, Main Landing Gear

1, 2, 3, 4 COMP, SPL

J, N

3 COMP

F

1, 2, 3, 4 COMP

F

3 COMP

F

1, 2, 3, 4 COMP

E

3 COMP

E

Vacuum System Instruments Operational Check Vertical Stabilizer

Window Attach Frames, Cabin Windows, Cabin Window Defog System Windows, Pilot's Compartment Side Windshield (Heated) Antistatic Coating and Tabs Windshield Attach Torque Screws (Inspect)

SPL

200 HRS INITIAL/ 800 HRS RECURRING

Windshield Attach Torque Screws (Replace) Refer to Chapter 4-00-00.

Page 30 May 1/10

5-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION AND MAINTENANCE TIMETABLE (Continued)

ITEM

INSPECTION TIMETABLE 1, 2, 3, 4 INT, COMP or SPL

INTERVAL

SPL

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

Windshield Corners Doublers and Clips

Windshield (Heated) Operational Check

PHASE INSPECTION AREA

1, 2, 3, 4 INT, COMP

Q

Windshields

1, 2, 3, 4 COMP

E

Wing Attach Fitting Drain Holes

1, 2, 3, 4 COMP

H, L

Wing Bolt, Inconel (Inspect)

SPL

5 YRS

SPL

600 HOURS INITIAL/ 18 MONTHS RECURRING

Wing Bolt, Inconel (Replace) Refer to SIRM. Wing Bolt, Shear (Replace) Refer to SIRM. Wing Center Section Upper Bonded Surface Panel

90° Drive and Cable, Flaps

A28

1 COMP

I

5-00-00

Page 31 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 5-11-00

TIME LIMITS - OVERHAUL AND REPLACEMENT OVERHAUL AND REPLACEMENT SCHEDULE The first overhaul and replacement must be performed not later than the recommended period. The condition of the item at the end of the first period can be used as a criterion for determining subsequent periods applicable to the individual airplane or fleet operation, provided the operator has an approved condition-monitoring system. The time periods for overhaul and replacement noted in this manual are based on average usage and average environmental conditions. CAUTION: The recommended periods do not constitute a guarantee the item will reach the period without malfunction as the aforementioned factors cannot be controlled by the manufacturer. NOTE: The date on the “ORIGINAL AIRWORTHINESS CERTIFICATE”, FAA Form No. 8100-2, which is issued with each new airplane, is to be used as the basis for all TBO or replacement components listed in the following schedule. Hawker Beechcraft Corporation recommends that operators record the number of cycles used on individual components for purposes of complying with inspections based on cycle count. For purposes of establishing the intervals that follow, the experience of Hawker Beechcraft Corporation indicates that each component experiences approximately one cycle per airplane flight hour in normal operation. Items NOT listed are to be overhauled or replaced “On Condition”. If “On Condition” items are worn, inoperative, inaccurate, intermittent and are not repairable through normal maintenance practices, they must be overhauled or replaced.

A28

5-11-00

Page 1 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OVERHAUL AND REPLACEMENT SCHEDULE ITEM

OVERHAUL OR REPLACE

Landing Gear Main Gear Wheels, Bearings and Tires (Ref. Chapter 32-40-00)

Refer to the King Air Series Component Maintenance Manual for limits.

Nose Gear Wheels, Bearings and Tires (Ref. Chapter 32-40-00)

Refer to the King Air Series Component Maintenance Manual for limits.

Main Gear Brakes (Ref. Chapter 32-40-00)

Refer to the King Air Series Component Maintenance Manual for limits.

Landing Gear Brake Hoses (Only Hoses Exposed in the Wheel Well) (Ref. Chapter 32-40-00)

Replace 5 years from the factory aircraft-certification date and every 5 years thereafter.

Landing Gear Retraction and Extension Teflon Hydraulic Hoses (Ref. Chapter 32-30-00)

Replace 10 years from the factory aircraft-certification date and every 10 years thereafter or on condition, whichever occurs first.

Landing Gear Hydraulic System Filter and O-Ring (Ref. Chapter 32-30-00)

Replace filter and O-rings at first 200-hour inspection and every 1,200 hours or 1,000 cycles thereafter, whichever occurs first. In addition to these replacement frequencies, whenever a hydraulic component is replaced, this filter must be replaced after the system has been checked for operation. This filter must also be replaced at the next inspection after component replacement was made.

Electrical System Emergency Locator Transmitter Battery (Ref. Chapter 25-60-00)

Replace at 50% of useful life as stated on the battery or anytime the transmitter is used more than one cumulative hour.

Cockpit Voice Recorder Underwater Locator Beacon (Ref. Chapter 23-70-00)

Replace batteries every 6 years. Test the batteries and the unit every two years.

Power Plant Engine TBO (Ref. Chapter 71-00-00)

Refer to Pratt & Whitney Service Bulletin Number 13303 or subsequent. NOTE: A TBO (Time Between Overhaul) recommendation is in no way to be construed as a warranty or engine life proration basis. The TBO recommendation is based on the projected time for most advantageous initial overhaul. The individual operator’s experience may indicate a departure in either direction from the recommended TBO for the particular operation.

Page 2 May 1/10

5-11-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE (Continued) ITEM

OVERHAUL OR REPLACE

Power Plant (Continued) Engine Accessories Engine-Driven High Pressure Fuel Pump

Refer to Pratt & Whitney Service Bulletin Number 13303 or subsequent.

Overspeed Governor

Refer to Woodward Service Bulletin 33580A or subsequent.

Propeller Governor

Refer to Woodward Service Bulletin 33580A or subsequent.

Starter/Generator

1,000 hours.

Low Pressure Fuel Boost Pump

On condition.

Tachometer Generator

On condition.

Engine Vibration Isolator Mounts

Replace at engine overhaul or 4,000 hours, whichever occurs first.

Oil Cooler (Ref. Chapter 79-00-00)

Replace when contaminated.

Engine Oil Filter (Ref. Chapter 79-00-00)

Replace at 1,000 hours. Refer to the Engine Maintenance Manual for procedures.

P3 Air Filter (Ref. Chapter 73-16-72)

Replace at 1,000 hours. Refer to the Engine Maintenance Manual for procedure.

Flammable-Liquid-Carrying Hoses (Hawker Beechcraft Corporation Supplied Hoses Only) (Ref. Chapter 71-00-00)

5 years from date of delivery and every 5 years thereafter and on condition at engine overhaul. Hawker Beechcraft Corporation Supplied Hoses Only, which include all hoses between the airframe and the engine or its components, and between HBC installed components, such as torque and oil pressure sensors, and the engine.

Propeller Propeller (Refer to Chapter 61)

Refer to Hartzell Service Letter 61M or subsequent. (Ref. Chapter 61-10-00)

Fuel System Firewall Shutoff Valve (Ref. Chapter 28-20-00)

Replace when the leakage rate reaches 2.0 c.c. per minute.

Utility Systems Passenger Oxygen Shutoff Valve (Autodeployment Valve) (Ref. Chapter 35-00-00)

Replace O-rings every 24 months.

Engine Fire Extinguisher Bottle (Ref. Chapter 26-20-00)

Hydrostatically test bottle in accordance with Title 49 CFR Chapter 1, Section 173.34 or replace with a new bottle at the interval specified in the miscellaneous limitations (Ref. Airworthiness Limitations Manual, P/N 130-590031-211).

A28

5-11-00

Page 3 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE (Continued) ITEM

OVERHAUL OR REPLACE

Utility Systems (Continued) Engine Fire Extinguisher Cartridge (Squib) (Ref. Chapter 26-20-00)

Replace at the interval specified in the miscellaneous limitations. (Ref. Airworthiness Limitations Manual, P/N 130-590031-211)

Emergency Exit Light Batteries

Replace annually.

Instrument Air Filter (Ref. Chapter 37-00-00)

Replace every 600 hours or sooner if necessary.

Window Defog Air Filters (if installed) (Ref. Chapter 30-40-00)

Replace every 800 hours or sooner if necessary. (Recommend replacing at the Phase 3 or Complete inspections when the interior is removed for inspection purposes.)

Structure Upper Door Hook Mechanism (Includes the pins, bracket, spring, arm and hooks.) (Ref. Chapter 52-10-00)

Replace at the interval specified in the structural limitations. (Ref. Airworthiness Limitations Manual, P/N 130-590031-211)

Eight Wing Attach Bolts (Ref. Chapter 57-00-00)

Replace as outlined in the Structural Inspection and Repair Manual, P/N 98-39006B or subsequent.

Windshield Frame Screws

Replace at the interval specified in the structural limitations. (Ref. Airworthiness Limitations Manual, P/N 130-590031-211)

Cabin Door Latch-Bolts

Replace at the interval specified in the structural limitations. (Ref. Airworthiness Limitations Manual, P/N 130-590031-211)

Page 4 May 1/10

5-11-00

A28

Ray~heon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SCHEDULED PHASE INSPECTION PROGRAM

DESCRIPTION

B300 INSPECTION PROGRAM NOTE: Additional

inspections may be required by engine or propeller manufactures in their manuals. Refer to the unscheduled maintenance checks portion of the supplier issued manuals to ensure continued airworthiness.

The

operator is ultimately responsible for maintaining the airplane in

an airworthy condition, including compliance applicable Airworthiness Directives as specified in Part 39 of the Title 14 of the Code of Federal Regulations (14 CFR). The owner or operator should select only qualified personnel to maintain the airplane, and ensure that the airframe and power plant mechanic inspecting the airplane has access to all necessary manuals and service information as well as to an approved inspection guide.

owner or

with all

Airirame and power plant mechanics must have had previous experience in the satisfactory performance of the tasks required by this inspection before being qualified to supervise, approve and return to service the airplane or any part thereof in need of maintenance,

preventative maintenance, repair or alteration.

responsibility of the owner or operator to ensure that the airplane is inspected in conformity with the requirements covered in 14 CFR Part 91.409 (f) (3) of the Federal Aviation Regulations. This 14 CFR Part covers the requirements concerning approved airplane inspection programs. Raytheon Aircraft Company has prepared the 8300 Inspection Program to assist the owner or operator in meeting the foregoing responsibilities. It is further the

It is the

responsibility of the owner or operator to inspection Program.

obtain

specific approval from

their local airworthiness

authority

for

any alteration to the

NOTE: When warranted

by

experience or engineering recommendations, an approved maintenance inspection intervals, may be changed at any time with the approval of the local

service

program, including the airworthiness authority.

a portion of the publications by which Raytheon Aircraft Company provides the inspection requirements and maintenance schedules for the continued airworthiness of the airframe of your airplane. Remember, maintenance requirements for some supplier-supplied components (such as engines, propellers, avionics and other equipment) are separately provided by their respective manuals. Those maintenance requirements and schedules are adopted by reference in the airframe maintenance instructions for continued airworthiness. Have your maintenance personnel review the equipment installed on your airplane to ensure the current, up-to-date supplier maintenance publications and manuals are available and that all required maintenance is scheduled and performed as required under 14 CFR 91.403(c).

This document is

Inspection Program is provided to enable the owner/operator to inspect and maintain the airplane on an ongoing basis. Included in the program is a sequence for conducting the program along with suggested times. The times and sequence are recommendations that may be altered to suit a particular operation. While this program may be used as an outline, detailed information of the systems and components in the airplane will be found in the various chapters/sections of the maintenance manual and the pertinent supplier publications. It is also recommended that reference be made to the applicable maintenance handbooks, service instructions, applicable FAA Regulations, Publications and supplier’s specification for torque values, clearance, settings, tolerances and other requirements.

This

This program is not intended to be all-inclusive, for no such program airframe and power plant mechanic in the performance of his duties.

can

replace

the

good judgement

of

a

certified

NOTE: In addition to the

inspections prescribed by this schedule, the altimeter instrument and static system and all transponders MUST be tested and inspected in compliance with the requirements specified in 14 CFR 91.411 and 91.413 at 24-month intervals or anytime the system is opened.

ATC

n~2o

5-21-00

1

I

Ral~heon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: Information contained herein is indicated

by

serial number

applicable effectivity.

to all 8300 series

airplanes except

where differences

are

SPECIAL CONDITIONS CAUTIONARY NOTICE CAUTION: The time

periods

malfunction

as

in this schedule do not constitute

a

guarantee the item will reach the period without

the aforementioned factors cannot be controlled

by the

manufacturer.

WARNING: Use

only genuine Raytheon aircraft company, or Raytheon aircraft company-approved parts from Raytheon aircraft company approved sources in connection with the maintenance and repair of Raytheon aircraft company airplanes to assure that the airplane is returned to service in a condition at least equal to its original or properly altered condition. Genuine Raytheon aircraft company parts are produced and inspected under rigorous procedures to ensure airworthiness and suitability for use in Raytheon aircraft company airplane applications Parts purchased from sources other than Raytheon aircraft company, even though outwardly identical in appearance, may not have had the required tests and inspections performed, may be different in fabrication techniques and materials, and may be dangerous when installed in an airplane. obtained

Salvaged airplane parts,

reworded

parts obtained from non-Raytheon aircraft company assemblies, the service history of which is

structural

parts, components, authenticated, may have been subjected to unacceptable stresses or other hidden damage not discernible through routine visual or usual have or temperatures nondestructive testing techniques. This may render the part, component, or structural sources,

or

unknown

or

assembly, unsafe for

or

cannot be

though originally manufactured by Raytheon airplane use.

even

aircraft company, unsuitable and

Raytheon aircraft company expressly disclaims any responsibility for malfunctions, failures, damage or injury caused by use of non-Raytheon aircraft company-approved parts or procedures. periods for the inspections noted in this schedule are based on normal usage under average environmental Airplanes operated for Air Taxi or other than normal operations and airplanes operated in humid tropics, or in cold damp climates, etc., may need more frequent inspections for wear, corrosion, lubrication, and/or lack of maintenance. Under these adverse conditions, perform periodic inspections in compliance with this guide at more frequent intervals until the owner or operator can set his own inspection periods based on the contingencies of field experience.

The time

conditions.

B300 SCHEDULED INSPECTION GENERAL INFORMA TION INSPECTION INTERVAL TOLERANCE To facilitate

scheduling inspection, Raytheon Aircraft Company

authorizes the

following inspection

interval

tolerances:

PHASE INSPECTIONS A tolerance of

(HOUR INTERVAL)

20 hours is allowed. Each

phase inspection

must be

completed

within 20 hours of the

prescribed

time. EXAMPLE: A PHASE 1 INSPECTION, due at 200 hours, may be accomplished anytime between 180 and 220 hours. A PHASE 2 INSPECTION, due at 400 hours, may be accomplished anytime between 380 and 420 hours, etc.

Apr

28/065-21-00

nno

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SPECIAL INSPECTION ITEMS A tolerance of

12

days

per 12 calendar months is allowed, not to exceed

SPECIAL INSPECTION ITEMS A tolerance of

a

total of 60 calendar

days.

FLIGHT CYCLE LIMITED

10% is allowed.

SPECIAL INSPECTION ITEMS A tolerance of

CALENDAR DATE LIMITED

HOURL Y LIMITED

10% is allowed.

NOTE: Tolerances

specified by suppliers,

intervals and tolerances authorized

regulations or FAA regulations by Raytheon Aircraft Company.

DOT

take

precedence

over

inspection

PURPOSE AND USE

Raytheon Aircraft Company-recommended 8300 Inspection Program is provided to maintain the 8300 Series airplanes that are utilized by owners and operators on a continuous basis. The complete program must be accomplished at least one time every 24 calendar months.

The

NOTE: Owners and operators wishing to utilize inspection intervals of less than 200 hours may do so without obtaining Raytheon Aircraft Company concurrence. Refer to the latest revision of this form for inspection procedure details to meet 14 CFR 91/409 (f) (3).

Inspection timetables

are a

follows:

Inspection Phase

1:To be

performed

at 200 hours and every 800 hours thereafter.

Inspection Phase

2. To be

performed

at 400 hours and every 800 hours thereafter.

Inspection Phase

3: To be

performed

at 600 hours and every 800 hours thereafter.

Inspection Phase

4: To be

performed

at 800 hours and every 800 hours thereafter.

Alternate Phase

option

of

Inspection: If an aircraft is inspecting the aircraft as follows:

Perform scheduled phase perform scheduled phase

inspections 1 inspections 3

not flown at least 400 hours in 24

and 2 and 4

together within together within

months, the owner/operator has the

12 months after the last aircraft

12 months after

completing

the

inspection; then phase 1 and 2

inspections. NOTE:

Raytheon Aircraft Company phase inspection.

recommends that

no

aircraft exceed 12 months without

completing

at least on

Special Inspections: Although this inspection program is based on 200-hour intervals, there are items which require more, or less, frequent inspection or whose inspection interval is based on flight time, calendar elapsed time, or cycles. These unique inspection items and their time intervals are described under SPECIAL INSPECTIONS and should be reviewed prior to commencing any scheduled inspection. complete scheduled inspection (ali Phase 1, 2, 3 and 4 Inspections) must be accomplished within a 24-calendarperiod. Any part of the inspection which has not been accomplished will become due immediately. Completion of the Phase 1, 2, 3 and 4 Inspections shall be considered as a complete inspection.

A

month

5-21-00Page

3

RaytheMI

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

hourly or calendar intervals and is then no longer in compliance with the Phase Inspection Program, a complete (COMP) inspection is required. The complete (COMP) inspection consists of Phase 1 thru 4 without the duplication of items.

NOTE: If

an

aircraft exceeds the

INSPECTION SCHEDULE OUTLINE INSPECTION PHASE A/C TIME

(HOURS)

1

2

I

X

200

4

3

TYPE OF INSPECTION

Nose Landing Gear Area, Nose Gear, Pilot’s Compartment, Cabin Section, Rear Fuselage and I Empennage, Wings, Main Gear Area, Engines, Landing Gear Retraction, Operational Inspection, Post Inspection.

I

Compartment, Nose Landing Gear Area, Nose Gear, Pilot’s Compartment, Cabin Section, Rear Fuselage and Empennage, Wings, Main Landing Gear Area, Engines, Landing Gear Retraction, Operational Inspection, Post Inspections. Nose Avionics

X

400

Landing Gear Area, Nose Gear, Pilot’s Compartment, Cabin Section, Rear Fuselage and Empennage, Wings, Main Landing Gear Area, Engines, Landing Gear Retraction, Operational Inspection, Post Inspections. Nose

X

600

Nose Section, Nose Avionics Compartment, Nose Landing Gear Area, Nose Gear, Pilot’s

1

800

I

I

IX

Cabin Section, Rear Fuselage and Empennage, Wings, Main Landing Gear Area, Engines, Landing Gear Retraction, Operational Inspection, Post Inspection.

I Compartment,

AFTER THE "PHASE 4" INSPECTION IS COMPLETED, REPEAT THE INSPECTION SEQUENCE. NOTE:

Raytheon

Aircraft

Company’s

Recommended

Inspection Program

in accordance with 14 CFR 91.409

(f) (3)

consists of, but is not limited to, inspection items listed in this Inspection Guide, any applicable Airworthiness Directives issued against the airframe or any equipment installed therein, conformity to Type Certificate Data

Sheet and Maintenance Manual WARNING: Ascertain that all

placards

touched up after

Chapter are

in

4

as

applicable.

place and legible whenever the airplane has been repainted any placards that have been inadvertently defaced

repairs. Replace

or

or

removed.

While this

airplane

guide

may be used

outline, detailed information of the many systems and components in the sections/chapters of this Maintenance Manual and the Engine Maintenance

as an

will be found in the various

Whitney Canada PT6A-60A Maintenance applicable supplier maintenance handbooks, Raytheon Aircraft Company senrice bulletins, applicable FAA Regulations and supplier bulletins and specifications for torque values, clearances, settings, tolerances and other requirement. It is the responsibility of the owner or operator to ensure that the airframe and power plant mechanic inspecting the airplane has access to the previously noted documents as well as to this inspection guide. Manual. Reference to the

Engine

Maintenance Manual is to the Pratt

Manual. It is also recommended that reference be made to the

Apr

5-21-00

no

NaYIiNeepl

nircrait

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Raytheon Aircraft Company issues

service information for the benefit of

owners

and fixed-base operators in the form

of two classes of service bulletins. The first class, MANDATORY Service Bulletins (red border) are changes, inspections and modifications that could affect safety or crashworthiness. Raytheon Aircraft Company considers

compliance with these service bulletins to be mandatory. Raytheon Aircraft Company also issues a service bulletin having no borde r designated as either RECOMM ENDED or OPTIONAL in the compliance section within the bulletin. In the case of a RECOMMENDED Service Bulletin, Raytheon Aircraft Company feels the changes, modifications, improvements or inspections will benefit the owner and although highly recommended, they are not considered mandatory at the time of issuance. In the case of OPTIONAL Service Bulletins, the changes, modifications, improvements or inspections compliance is at the owner/operator’s discretion. In the final

analysis

responsibility of the owner or operator to ensure that pertinent to his particular operation are complied with.

it is the

service bulletins which

are

all

Raytheon

Aircraft

Company

DEFINITIONS The

terminology pertaining

Flight

Time

to the

inspection procedures

and their

use

is defined

as

follows:

Flight time shall mean the total time from the moment the airplane first moves under its own power for flight until the moment it comes to rest at the next point of landing. ("Block-to-block" time).

the purpose of

Means

Maintenance

preventive

inspection, overhaul, repair, preservations and the replacement of parts, but excludes

maintenance.

Pilot in Command

Pilot in command shall

the time defined

during replacement of

the

as

flight

pilot responsible for the operation and safety of the airplane Means simple or minor preservative operations and involving complex assembly operations.

mean

the

time.Preventive Maintenance

small standard parts not

Time in Service

Time in Service, as used in computing maintenance and inspection time records, is the time from the moment the airplane leaves the ground until it touches the ground at the end of the flight.

Flight Cycle A flight cycle is defined as: Engine start-up and increase to full or partial normal flight), one landing gear retraction and extension and a complete shutdown. surface breakdown of

Corrosion

Fitting,

moisture

other agents.

Wear

or

Material

Damaged

or

or a

part consumed

as a

a

material due to chemical

result of exposure to

operation

or

or

power

las required during

electro-chemical attack

a

by atmosphere,

usage.

Rendered unusable for its intended purpose.

Calendar Time

The time from the date

8100-2, which is issued with each

Special Inspection

new

on

the "ORIGINAL AIRWORTHINESS CERTIFICATE", FAA Form No.

airplane,

Inspections of components inspection.

to be used as the basis for all TBO or

systems based

on

or

of

replacement components.

calendar time, hours

or

cycles

which do not

coincide with the scheduled

Unscheduled Maintenance Checks which could

require

Inspections

and checks for

unscheduled maintenance, i.e.

damage after operating the airplane in conditions lightning strikes, hard landing, polluted atmospheric conditions,

etc.

5-21-00Page

5

Ral~heon

Aircraft

Campany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DISCREPANCIES

Discrepancies

that affect the airworthiness of the

accomplished before

Discrepancies carried

over

the

airplane

airplane

will

that do not affect the airworthiness of the

to the next

require the

necessary corrective action to be

is returned to service.

inspection period.

All

airplane may, discrepancies thus carried

at the discretion of the over

should be

owner/operator, be retained in the ship file until

corrected.

Discrepancies which occur during flight responsible person.

should be entered

on

the

"ln-Flight Work

Sheet"

by

the

pilot

in command

or

another

Apr

5-21-00

n?o

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 5-21-01

SCHEDULED INSPECTION PROGRAM (PHASE 1) - MAINTENANCE PRACTICES

Owner______________________________________

LH Eng. S/N_________________________________

W/O Number_________________________________

Total Time ____________ Total Cycles_____________

Date In ________________ Date Out______________ TSOH ________________ Cycles SOH____________ Serial No. _____________ Reg. No._______________ TSHSI _______________ Cycles SHSI____________ Last Inspection ____________ Phase______________ RH Eng. S/N_________________________________ Last Inspection Date___________________________

Total Time ____________ Total Cycles ____________

Last Inspection Hours__________________________

TSOH ________________ Cycles SOH____________

Hourmeter _______________ Total Time___________ TSHSI _______________ Cycles SHSI ____________ Total Cycles__________________________________ LH Prop S/N _________________________________ Researched By_______________________________

LH Prop Total Time ____________ TSOH __________ RH Prop S/N _________________________________ RH Prop Total Time ____________ TSOH __________

A.

NOSE SECTION

ATA/GAMA REFERENCE

MECH

INSP

NOTE There are no inspections required in this section during this phase. B.

NOSE AVIONICS COMPARTMENT NOTE There are no inspections required in this section during this phase.

C.

NOSE LANDING GEAR AREA 1. ELECTRICAL WIRING and EQUIPMENT - Inspect all exposed electrical wiring and equipment for chafing, damage and security of attachment.

D.

AC43.13-1B/2B

NOSE GEAR 1. WHEEL a. Inspect wheel for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

A28

CMM

5-21-01

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

D. NOSE GEAR (Continued)

ATA/GAMA REFERENCE

MECH

INSP

2. TIRE a. Inspect for wear and deterioration. b. Check for correct inflation. 3. SHIMMY DAMPER - Inspect for leaks, security and attachment.

12-10-00 32-20-00 12-10-00

4. NOSE GEAR DRAG BRACE STOP LUGS - Inspect for cracks, damage or distortion. 5. NOSE GEAR STEERING STOP - Inspect steering stop for damage or distortion. 6. LANDING and TAXI LIGHTS - Inspect for broken lenses or bulbs.

33-40-00

7. STEERING LINKAGE - Inspect nose gear steering mechanism and attaching hardware for wear, damage and corrosion. 8. STRUT - Check strut for leakage and correct extension. 9. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment. E.

12-10-00 AC43.13-1B/2B

PILOT’S COMPARTMENT 1. RETURN AIR INLET FILTERS - Inspect filters in return air inlet of the forward vent blower.

21-50-00

2. WINDSHIELDS a. Inspect windshields for cracks, visibility impairment.

56-10-00

b. Inspect windshield silicon weather seal for debonding, cracks or wear. 3. WINDOWS - Inspect exterior surface of cockpit side windows for deep scratches, cracks, chips or excess crazing or other damage.

56-15-00

4. SEAT BELTS and SHOULDER HARNESSES - Inspect seat belts and shoulder harness for deterioration.

AC43.13-1B/2B

5. FIRE EXTINGUISHER (PORTABLE) - Inspect the bottle for signs of damage and mount for security of attachment. 6. UPHOLSTERY PANELS - Inspect for security of attachment. 7. ALTERNATE AIR VALVE - Drain off all moisture. 8. FLIGHT CONTROL CABLE TENSION - Check aileron control cable tension.

Page 202 May 1/10

5-21-01

34-00-00 27

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

F.

CABIN SECTION

ATA/GAMA REFERENCE

1. WINDOWS - Inspect exterior surfaces of windows for deep scratches, cracks, chips and excessive crazing or other damage.

56-15-00

2. ROTATING (FLASHING) BEACON - Inspect for cracked or broken lenses.

33-40-00

MECH

INSP

3. ACCESS DOORS - Inspect for fit and attachment. 4. EMERGENCY EXIT LIGHT - Inspect emergency exit light for battery leakage and security of lamp.

33-20-00

5. OUTFLOW and SAFETY VALVES - Drain outflow valve control line (two locations).

21-30-00

6. AFT EVAPORATOR FILTERS - Inspect aft evaporator filter.

21-50-00

7. SEAT BELTS and SHOULDER HARNESSES a. Inspect seat belt and shoulder harness for deterioration and missing components.

AC43.13-1B/2B

b. Inspect shoulder harness attachment post for cracked, worn, brittle or missing grommets.

AC43.13-1B/2B

8. OXYGEN SYSTEM - Test all masks for oxygen flow. 9. TOILET - Inspect for spillage and leakage below the toilet. 10. CABIN ENTRANCE DOOR (FL-1 and After) a. Inspect the door seal for cuts, abrasions and security of attachment.

52-10-00

b. Inspect the cabin door support cables for wear, damage and security.

52-10-00

11. CABIN CARGO DOOR and CABIN ENTRANCE DOOR (FM-1 and After) - Inspect door seals for cuts, abrasions, deterioration and security of attachment. G.

52-11-00

REAR FUSELAGE AND EMPENNAGE 1. REAR FUSELAGE DRAINS - Inspect rear fuselage drains.

53-00-00

2. ELT BATTERY a. Inspect for leakage, corrosion or loose leads.

25-60-00

b. Determine remaining useful life.

25-60-00

3. NAVIGATION LIGHTS and ROTATING (FLASHING) BEACONS - Inspect for broken or cracked lenses.

33-40-00

4. ACCESS DOORS - Inspect for fit and security of attachment. 5. VENTRAL FIN DRAIN HOLES - Inspect the drain holes in the bottom of the ventral fin for obstructions.

A28

53-00-00

5-21-01

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

G. REAR FUSELAGE AND EMPENNAGE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

6. DEICER BOOTS - Inspect for deterioration, damage and attachment. 7. RUDDER and TRIM TAB DRAIN HOLES - Inspect the drain holes for obstructions.

55-40-00

8. STATIC WICKS - Inspect for damage and security of attachment.

23-60-00

9. FLIGHT CONTROL CABLE TENSION - Inspect elevator, elevator tab, rudder and rudder tab control cable tensions. H.

27

LEFT SIDE OUTBOARD WING 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

3. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

33-40-00

b. Inspect the strobe light for broken or cracked lenses.

33-40-00

4. FUEL TANKS and VENTS a. Inspect exterior openings of vents for obstructions.

28-10-00

b. Inspect fuel filler cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

5. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

6. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

7. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

8. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

9. STATIC WICKS a. Inspect for damage and security of attachment.

23-60-00

b. Check the static wick for proper bonding to the airplane.

23-60-00

10. AILERON and TRIM TAB - Check trim tab free play.

27-10-00

11. LEFT-HAND OUTBOARD WING - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

57-00-00

Page 204 May 1/10

5-21-01

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

H. LEFT SIDE OUTBOARD WING (Continued)

ATA/GAMA REFERENCE

12. AILERON and OUTBOARD FLAP - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

27-10-00 27-50-00

13. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

AC43.13-1B/2B

MECH

INSP

14. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control system cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given three-foot cable length or have evidence of corrosion.

27

c.

Inspect aileron control cable tensions.

27

d. Inspect aileron tab control cable tensions.

27

15. FLAPS and ACTUATORS a. Inspect flap 90° drive, cable and actuator for attachment.

27-50-00

b. Inspect flap tracks for wear.

27-50-00

c.

I.

Perform FLAP SAFETY MECHANISM FUNCTIONAL TEST. Refer to Chapter 27-50-00.

27-50-00

16. FUEL PLUMBING - Inspect for leaks, chafing or damage and attachment.

28-20-00

17. HINGED ACCESS DOORS ABOVE DOORS NO. 13 and 14 Inspect for cracks or damage to hinge and fasteners.

57-30-00

LEFT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS a. Inspect the exterior of the center section for leaks.

28-10-00

b. Inspect fuel filler cap and antisiphon valve for damage and attachment.

28-10-00

c.

A28

Inspect the exterior openings of the vents for obstructions.

3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

4. FUEL PUMPS - Inspect the pumps for leaks and security of attachment.

28-20-00

5-21-01

Page 205 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I. LEFT SIDE WING CENTER SECTION (Continued) 5. ENGINE FIRE EXTINGUISHER a.

Inspect plumbing for security of attachment.

b. Check fire bottle pressure gage. c.

Check for presence of activation voltage to the cartridge/ squib. Perform the EXTINGUISHER ACTIVATION CHECK procedure.

ATA/GAMA REFERENCE

MECH

INSP

26-20-00 26-20-00 26-20-00 26-20-00

6. LANDING GEAR POWER PACK and MOTOR a. Inspect the hydraulic power pack gear-up and gear-down port screens.

32-30-00

b. Inspect the landing gear hydraulic system bleed air pressure overboard relief orifice screen for blockage.

32-30-00

c.

Inspect all plumbing attach points for leaks and security of attachment.

32-30-00

7. LEFT-HAND WING CENTER SECTION - Inspect wing center section and inboard flap, skin structure and attaching hardware for wear, damage and corrosion. If damage is found in a given area, check the adjacent area. 8. FLAPS and ACTUATORS a. Inspect flap 90° drive, cable and actuator for attachment.

27-50-00

b. Inspect flap tracks for wear.

27-50-00

9. LEADING EDGE and NACELLE FUEL PLUMBING - Inspect fuel plumbing for leaks, damage and security of attachment.

28-20-00

10. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given three-foot cable length or have evidence of corrosion.

27

11. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage and proper routing of wire bundles and security of attachment.

AC43.13-1B/2B

12. BLEED AIR BYPASS VALVE - Check bleed air valve at heat exchanger for operation of linkage to butterfly valve and operation of actuator motor.

21-40-00

13. UPPER SURFACE BONDED PANEL - Inspect bonded panel.

51-00-00

Page 206 May 1/10

5-21-01

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

J.

LEFT SIDE MAIN LANDING GEAR AREA

ATA/GAMA REFERENCE

MECH

INSP

1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage. 2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

CMM 32-40-00

3. BRAKE DEICING (IF INSTALLED) a. Inspect manifold for blocked orifices.

32-41-00

b. Inspect exterior of lines, hoses and connections for leakage and attachment.

32-41-00

4. TIRES - Inspect tires for wear, deterioration and correct inflation.

32-40-00 12-10-00 CMM

5. STRUT - Check strut for leaks and proper extension.

12-10-00

6. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

AC43.13-1B/2B

7. MAIN GEAR ACTUATOR - Inspect actuator and plumbing for leakage and attachment.

32-30-00

8. DRAG BRACE a. Inspect for security of attach fittings. b. Inspect downlock bolts for proper torque (finger tight and safetied). 9. MAIN LANDING GEAR AREA - Inspect wheel well and gear door structure, all components and attaching hardware for wear, damage and corrosion. If damage or corrosion is found, check the adjacent area. K.

32-10-00 CMM

AC43.13-1B/2B

LEFT SIDE ENGINE 1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00

2. P3 AIR FILTER - Inspect the filter for cleanliness. Refer to the engine maintenance manual for procedure.

A28

3. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

28-20-00 12-10-00

4. PROPELLERS - Inspect for damage and attachment (spinner removal required).

61-10-00

5-21-01

Page 207 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

5. ENGINE OIL FILTER - Inspect for metal particles. Refer to the engine maintenance manual. L.

RIGHT SIDE OUTBOARD WING 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

3. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

33-40-00

b. Inspect the strobe light for broken or cracked lenses.

33-40-00

4. FUEL TANKS and VENTS a. Inspect exterior openings of vents for obstructions.

28-10-00

b. Inspect fuel filler cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

5. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

6. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

7. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

8. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

9. STATIC WICKS a. Inspect for damage and security of attachment.

23-60-00

b. Check the static wick for proper bonding to the airplane.

23-60-00

10. AILERON and TRIM TAB - Check trim tab free play.

27-10-00

11. RIGHT-HAND OUTBOARD WING - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

57-00-00

12. AILERON and OUTBOARD FLAP - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

27-10-00 27-50-00

13. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

AC43.13-1B/2B

Page 208 May 1/10

5-21-01

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

L. RIGHT SIDE OUTBOARD WING (Continued)

ATA/GAMA REFERENCE

MECH

INSP

14. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control system cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given three-foot cable length or have evidence of corrosion.

27

c.

27

Inspect aileron control cable tension.

15. FLAPS and ACTUATORS a. Inspect flap 90° drive, cable and actuator for attachment.

27-50-00

b. Inspect flap tracks for wear.

27-50-00

c.

M.

Perform FLAP SAFETY MECHANISM FUNCTIONAL TEST. Refer to Chapter 27-50-00.

27-50-00

16. FUEL PLUMBING - Inspect for leaks, chafing or damage and attachment.

28-20-00

17. HINGED ACCESS DOORS ABOVE DOORS NO. 13 and 14 Inspect for cracks or damage to hinge and fasteners.

57-30-00

RIGHT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS a. Inspect the exterior of the center section for leaks.

28-10-00

b. Inspect fuel filler cap and antisiphon valve for damage and attachment.

28-10-00

3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

4. BATTERY a. Service battery as required.

12-10-00

b. Remove battery and inspect the battery box, cables and vent tubes for deterioration or obstructions. (FL-1 thru FL-214; FM-1 thru FM-9)

24-31-00

c.

Remove battery and inspect the battery box and cables for deterioration or obstructions. (FL-215 and After; FM-10 and After)

5. FUEL PUMPS - Inspect the pumps for leaks and security of attachment.

A28

24-31-00

28-20-00

5-21-01

Page 209 May 1/10

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M. RIGHT SIDE WING CENTER SECTION (Continued) 6. ENGINE FIRE EXTINGUISHER a.

Inspect plumbing for security of attachment.

b. Check fire bottle pressure gage. c.

Check for presence of activation voltage to the cartridge/ squib. Perform the EXTINGUISHER ACTIVATION CHECK procedure.

ATA/GAMA REFERENCE

MECH

INSP

26-20-00 26-20-00 26-20-00 26-20-00

7. RIGHT-HAND WING CENTER SECTION - Inspect wing center section and inboard flap, skin structure and attaching hardware for wear, damage and corrosion. If damage is found in a given area, check the adjacent area. 8. FLAPS and ACTUATORS a. Inspect flap 90° drive, cable and actuator for attachment.

27-50-00

b. Inspect flap tracks for wear.

27-50-00

9. LEADING EDGE and NACELLE FUEL PLUMBING - Inspect fuel plumbing for leaks, damage and security of attachment.

28-20-00

10. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given three-foot cable length or have evidence of corrosion.

27

11. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage and proper routing of wire bundles and security of attachment.

N.

AC43.13-1B/2B

12. BLEED AIR BYPASS VALVE - Check bleed air valve at heat exchanger for operation of linkage to butterfly valve and operation of actuator motor.

21-40-00

13. UPPER SURFACE BONDED PANEL - Inspect bonded panel.

51-00-00

14. REFRIGERANT LINES and PRESSURE SWITCHES - Inspect lines and switches for leakage, damage and attachment.

21-50-00

RIGHT SIDE MAIN LANDING GEAR AREA 1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

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CMM

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

N. RIGHT SIDE MAIN LANDING GEAR AREA (Continued) 2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

ATA/GAMA REFERENCE

MECH

INSP

32-40-00

3. BRAKE DEICING (IF INSTALLED) a. Inspect manifold for blocked orifices.

32-41-00

b. Inspect exterior of lines, hoses and connections for leakage and attachment.

32-41-00

4. TIRES - Inspect tires for wear, deterioration and correct inflation.

32-40-00 12-10-00 CMM

5. STRUT - Check strut for leaks and proper extension.

12-10-00

6. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

AC43.13-1B/2B

7. MAIN GEAR ACTUATOR - Inspect actuator and plumbing for leakage and attachment.

32-30-00

8. DRAG BRACE a. Inspect for security of attach fittings. b. Inspect downlock bolts for proper torque (finger tight and safetied). 9. MAIN LANDING GEAR AREA - Inspect wheel well and gear door structure, all components and attaching hardware for wear, damage and corrosion. If damage or corrosion is found, check the adjacent area. O.

32-10-00 CMM

AC43.13-1B/2B

RIGHT SIDE ENGINE 1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00

2. P3 AIR FILTER - Inspect the filter for cleanliness. Refer to the engine maintenance manual for procedure. 3. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

28-20-00 12-10-00

4. PROPELLERS - Inspect for damage and attachment (spinner removal required).

61-10-00

5. ENGINE OIL FILTER - Inspect for metal particles. Refer to the engine maintenance manual.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

P.

LANDING GEAR RETRACTION

ATA/GAMA REFERENCE

MECH

INSP

1. RETRACT MECHANISM NOTE Since battery voltage is not sufficient to properly cycle the landing gear, use only an exterior power source capable of delivering and maintaining 28.25 ±0.25 volts throughout the extension and retraction cycles when performing the landing gear retraction inspection. When cycling the landing gear with the power pack, allow a one minute cooling period between cycles and a five minute cooling period every five cycles. Also, an exterior supply of dry air at 18 to 20 psi must be applied to the fill reservoir to prevent cavitation. If an exterior air supply is not available, use an exterior hydraulic pressure source. a. Check hydraulic power pack and motor for proper operation.

32-30-00

b. Check retraction system for proper operation of all components through at least two complete cycles.

32-30-00

c.

32-30-00

Check for unusual noises and evidence of binding.

2. DOORS and LINKAGE - Check door for operation, fit and rigging.

32-30-00

3. POSITION INDICATORS - Check for proper operation of switches.

32-60-00

4. WARNING HORN - Check operation.

32-60-00

5. DOWNLOCKS MECHANISM a. Check locking mechanism for positive engagement in extended position.

32-10-00 32-20-00

b. Check downlock switch for proper adjustment.

32-60-00

6. SAFETY SWITCH - Check for proper operation.

32-60-00

7. ACTUATOR - Check for noise, binding and proper rigging.

32-30-00

8. EMERGENCY EXTENSION - Check system for freedom of operation and positive engagement of downlocks.

32-30-00

CAUTION Do not continue operation after receiving a gear-down indication on all gears. Q.

OPERATIONAL INSPECTION NOTE

The following Operational Inspection procedures are to be applied during start and run of the engine. Refer to the Super King Air B300 and B300C Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual for the engine start and run procedures. 1. FIREWALL SHUTOFF VALVES - Check for proper operation. 2. CROSSFEED FUEL VALVE - Check for proper operation.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

3. STANDBY PUMPS - Check for proper operation. 4. STARTER - Check operation. 5. IGNITION - Check for annunciator panel light illumination. 6. ENGINE OIL TEMPERATURE and PRESSURE - Check for proper pressure and temperature limits. 7. FUEL QUANTITY GAGES - Check operation. 8. INTERSTAGE TURBINE TEMPERATURE - Check for correct limits on engine start. 9. VACUUM SYSTEM INSTRUMENTS - Check for correct limits. 10. PNEUMATIC PRESSURE GAGE - Check for correct pressure. 11. PNEUMATIC SYSTEM SHUTOFF VALVES - Check for proper operation. 12. GYRO INSTRUMENTS - Check for erratic or noisy operation. 13. PROPELLERS - Perform flight idle torque check.

76-00-00

14. AUTOFEATHERING CHECK - Refer to AUTOFEATHER SYSTEM OPERATIONAL CHECK.

61-21-00

15. PROPELLER SYNCHROPHASER - Refer to the SYNCHROPHASER SYSTEM FUNCTIONAL TEST and confirm proper synchronization.

61-22-00

16. PROPELLER GOVERNOR - Check governor operation (including feathering and reversing).

76-00-00

17. IDLE RPM - Check for correct rpm (both high and low rpm).

76-00-00

18. AC INVERTERS (If installed) - Check for proper operation.

24-20-00

19. RUDDER BOOST - Check for proper operation. 20. AUTOIGNITION - Check for proper operation. 21. PROPELLER DEICER - Check for proper operation and cycling. Refer to Chapter 30 of the King Air Series Component Maintenance Manual.

POH 74-00-00 CMM

22. ENGINE INERTIAL ANTI-ICER - Check for proper operation and rigging. 23. DEICE SYSTEM a. Check for proper operation and cycling. b. Functionally test tail and wing deice annunciator lights for operation. 24. BRAKE DEICE SYSTEM (IF INSTALLED) - Check for proper operation with engines running.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION Continued)

ATA/GAMA REFERENCE

25. ELECTRICAL SYSTEM - Perform functional checks.

MECH

INSP

24-50-00

26. ENVIRONMENTAL SYSTEM - Check for proper operation in: a. Manual heat mode. b. Manual cool mode. c.

Automatic mode.

27. AUTOPILOT - Check for proper operation as outlined in the applicable Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement. 28. STALL WARNING - Check for proper operation. 29. GENERATORS - Check the output. 30. ENGINE FIRE DETECTORS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 31. ENGINE FIRE EXTINGUISHERS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 32. PRESSURIZATION SYSTEM - Check for proper operation. NOTE Refer to the Super King Air B300 and B300C Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual and perform system test. 33. AUXILIARY FUEL TRANSFER JET PUMPS - Check for operation. 34. CONDITION LEVER - Check for clean shutdown at IDLE-CUTOFF. 35. PITOT TUBE - Check for proper heating at the unit and for obstructions. 36. LANDING and TAXI LIGHTS - Check operation of all lights.

33-40-00

37. OUTBOARD WING LIGHTS (Right Side and Left Side) - Check operation of all navigation and strobe lights.

33-40-00

38. COCKPIT LIGHTS - Check operation of all cockpit lights.

33-10-00

39. EFIS COOLING BLOWERS (If Installed) - Check operation.

34-20-00

40. ELECTRIC ELEVATOR TRIM - Check for proper operation.

27-30-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued) 41. ENGINE and PROPELLER CONTROLS - Check for freedom of movement, full travel and friction lock operation.

ATA/GAMA REFERENCE

MECH

INSP

76-00-00

42. PILOT'S and COPILOT'S SEATS and SEAT BELTS - Check seat adjustment mechanism and shoulder harness inertia reel for operation. 43. STATIC SYSTEM - Inspect alternate air valve for operation.

34-00-00

44. WINDSHIELDS - Perform heated operational check.

30-40-00

45. THRESHOLD LIGHT - Check for proper operation. 46. AUXILIARY ELECTRIC HEAT - Check for proper operation of the Electric Heat System. 47. CABIN and COMPARTMENT LIGHTS - Check for proper operation. 48. CABIN SEATS and SEAT BELTS - Check seat adjustment mechanism and shoulder harness inertia reel for operation. 49. CABIN ENTRANCE DOOR (FL-1 and After) a. Check that folding steps do not fold too soon and that they fold properly without interference. b. Check cabin DOOR UNLOCK annunciator for proper operation. c.

Inspect cabin door damper for leakage and proper operation.

50. CABIN CARGO DOOR and CABIN ENTRANCE DOOR (FM-1 and After) a. Inspect door latching mechanism for operation and security of attachment. b. Check latching mechanism, folding steps and gas springs for proper operation. 51. EMERGENCY EXITS (With door installed and properly rigged) a. Check emergency release handles (inside and outside) and latch mechanism for operation. b. Check that latches open and close freely. 52. EMPENNAGE CONTROL SURFACES a. Check for freedom of movement. b. Check optional trim actuators and motors for smoothness of operation. 53. REAR FUSELAGE and EMPENNAGE LIGHTS - Check operation of all lights.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

54. AILERON (Left Side and Right Side) - Check for freedom of movement. 55. AILERON TRIM TAB - Check trim tab actuator for smoothness of operation and attachment. 56. FUEL TANK VENTS (Left Side and Right Side) - Check the operation of the heated vents. They should be warm to the touch.

28-10-00

57. STALL WARNING HEAT - Check for proper operation. 58. FLAPS and ACTUATORS (INBOARD, OUTBOARD, Left Side and Right Side) - Check flaps for noisy or erratic operation.

27-50-00

59. WING CENTER SECTION LIGHTS - Check operation of all lights.

33-40-00

60. ENGINE INDUCTION SYSTEM (Left Side and Right Side) Check the inertial vane and bypass door for movement with the main and standby actuator motors.

R.

61. EXTERNAL POWER RELAY - Check for proper operation.

24-40-00

62. ELECTRIC HEATER POWER RELAYS - Check for proper operation.

21-40-00

POST INSPECTION ITEMS 1. AIRPLANE CLEANED and SERVICED AS REQUIRED.

12-00-00

2. LUBRICATE AS NECESSARY.

12-20-00

3. ENGINES INSPECTED AFTER GROUND RUN-UP OR FLIGHTTEST - Check for oil leaks, security and attachment of all components. 4. AIRWORTHINESS DIRECTIVES and SERVICE BULLETINS Must be reviewed and complied with as required. 5. ADDITIONAL INSPECTION REQUIREMENTS - Make sure Chapter 5, Special Inspection, and Airworthiness Limitations Manual (P/N 130-590031-211) requirements are complied with at the appropriate intervals. 6. IN-FLIGHT WORKSHEETS DISCREPANCIES - All discrepancies noted by the pilot must be checked and corrected as required. 7. EMERGENCY LOCATOR TRANSMITTER - Check for proper operation and make sure ELT is ARMED before returning airplane to service. 8. OXYGEN SYSTEM PRESSURE - Check for proper pressure.

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35-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

R. Post Inspection Items (Continued)

ATA/GAMA REFERENCE

MECH

INSP

9. EMERGENCY and SURVIVAL EQUIPMENT - (If required) Make sure all necessary emergency and survival equipment is installed in the airplane and is serviceable. 10. PLACARDS - Determine that all required placards are in place and legible.

11-20-00 and POH

11. LOGBOOK ENTRY - Make sure that log books are filled out properly.

INSPECTION COMPLETED I certify that Phase 1 Inspection was performed in accordance with the Model B300/B300C Inspection Program and that the airplane is approved for return to service: DATE:.......................................................................................................................................................................... MECHANIC:................................................................................................................................................................ CREW CHIEF:............................................................................................................................................................. QUALITY CONTROL INSPECTOR:............................................................................................................................

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 5-21-02

SCHEDULED INSPECTION PROGRAM (PHASE 2) - MAINTENANCE PRACTICES

Owner _____________________________________

Total Time ____________ Total Cycles___________

W/O Number _________________________________ TSOH ________________ Cycles SOH ____________ Date In ________________ Date Out ______________ TSHSI _______________ Cycles SHSI ____________ Serial No. _____________ Reg. No. _______________ RH Eng. Gas Gen. S/N _________________________ Last Inspection ____________ Phase _____________ RH Eng. Power Module S/N _____________________ Last Inspection Date ___________________________ Total Time ____________ Total Cycles ____________ Last Inspection Hours __________________________ TSOH ________________ Cycles SOH ____________ Hourmeter _______________ Total Time __________

TSHSI _______________ Cycles SHSI ____________

Total Cycles _________________________________

LH Prop S/N _________________________________

Researched By _______________________________ LH Prop Total Time ____________ TSOH __________ Inspection Being Conducted _____________ Phase

RH Prop S/N _________________________________

LH Eng. Gas Gen. S/N _________________________ RH Prop Total Time ____________ TSOH __________ LH Eng. Power Module S/N ______________________

A.

NOSE SECTION

ATA/GAMA REFERENCE

MECH

INSP

NOTE There are no inspections required in this section during this phase. B.

NOSE AVIONICS COMPARTMENT 1. INSTRUMENT AIR FILTER - Inspect for cleanliness. 2. VACUUM REGULATOR VALVE FILTER - Inspect for blockage.

C.

NOSE LANDING GEAR AREA 1. ELECTRICAL WIRING and EQUIPMENT - Inspect all exposed electrical wiring and equipment for chafing, damage and security of attachment.

A28

37-00-00

AC43.13-1B/2B

2. FORWARD EVAPORATOR FILTER - Inspect forward evaporator filter.

21-50-00

3. CONDENSER BLOWER - Inspect fittings for dirt, grease, moisture and security of attachment.

21-50-00

5-21-02

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

D.

NOSE GEAR

ATA/GAMA REFERENCE

MECH

INSP

1. WHEEL a. Inspect wheel for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

CMM

2. TIRE a. Inspect for wear and deterioration. b. Check for correct inflation. 3. SHIMMY DAMPER - Inspect for leaks, security and attachment.

12-10-00 32-20-00 12-10-00

4. NOSE GEAR DRAG BRACE STOP LUGS - Inspect for cracks, damage or distortion. 5. NOSE GEAR STEERING STOP - Inspect steering stop for damage or distortion. 6. LANDING and TAXI LIGHTS - Inspect for broken lenses or bulbs. 7. NOSE GEAR LOWER DRAG LEG - Remove nose gear drag brace bolt and inspect lower drag leg hole for corrosion and wear.

33-40-00

CMM

8. NOSE GEAR ACTUATOR a. Inspect actuator support brackets for damage, cracks and loose or missing fasteners. b. Inspect actuator and plumbing for leakage. E.

PILOT'S COMPARTMENT 1. RETURN AIR INLET FILTERS - Inspect filters in return air inlet of the forward vent blower.

21-50-00

2. WINDSHIELDS a. Inspect windshields for cracks and visibility impairment.

56-10-00

b. Inspect windshield weather seal for debonding, cracks or wear.

56-10-00

3. WINDOWS - Inspect exterior surface of cockpit side windows for deep scratches, cracks, chips, excess crazing or other damage.

56-15-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

E. PILOT'S COMPARTMENT (Continued) 4. ALTERNATE AIR VALVE - Drain off all moisture. F.

ATA/GAMA REFERENCE

MECH

INSP

34-00-00

CABIN SECTION 1. WINDOWS - Inspect exterior surfaces of windows for deep scratches, cracks, chips, excessive crazing or other damage.

56-15-00

2. ROTATING (FLASHING) BEACON - Inspect for cracked or broken lenses.

33-40-00

3. ACCESS DOORS - Inspect for fit and attachment.

G.

4. EMERGENCY EXIT LIGHT - Inspect emergency exit light for battery leakage and security of lamp.

33-20-00

5. OUTFLOW and SAFETY VALVES - Drain outflow valve control line (two locations).

21-30-00

6. UPHOLSTERY PANELS - Inspect for attachment and security.

25-20-00

REAR FUSELAGE AND EMPENNAGE 1. REAR FUSELAGE DRAIN HOLES - Inspect the rear fuselage drains.

53-00-00

2. ELT BATTERY a. Inspect for leakage, corrosion or loose leads.

25-60-00

b. Determine remaining useful life.

25-60-00

3. NAVIGATION LIGHTS and ROTATING (FLASHING) BEACONS - Inspect for broken or cracked lenses.

33-40-00

4. ACCESS DOORS - Inspect for fit and security of attachment. 5. VENTRAL FIN DRAIN HOLES - Inspect the drain holes in the bottom of the ventral fin for obstructions.

53-00-00

6. DEICER BOOTS - Inspect for deterioration, damage and attachment. 7. RUDDER and TRIM TAB DRAIN HOLES - Inspect the drain holes for obstructions.

55-40-00

8. STATIC WICKS - Inspect for damage and security of attachment.

23-60-00

9. EMPENNAGE and CONTROL SURFACES

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

G. REAR FUSELAGE and EMPENNAGE (Continued)

H.

ATA/GAMA REFERENCE

a. Check elevator trim tab free play.

27-30-00

b. Check rudder trim tab free play.

27-20-00

c.

27-20-00 27-30-00

Inspect elevator and rudder hinge brackets and their spar attach areas.

MECH

INSP

LEFT SIDE OUTBOARD WING 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

3. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

33-40-00

b. Inspect the strobe light for broken or cracked lenses.

33-40-00

4. FUEL TANKS and VENTS

I.

a. Inspect exterior openings of vents for obstructions.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

5. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

6. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

7. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

8. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

9. STATIC WICKS - Inspect for damage and security of attachment.

23-60-00

LEFT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS a. Inspect the exterior of the center section for leaks.

Page 204 May 1/10

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28-10-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I. LEFT SIDE WING CENTER SECTION (Continued) b. Inspect fuel cap and antisiphon valve for damage and attachment. c.

MECH

INSP

28-10-00

Inspect the exterior openings of the vents for obstructions.

3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment. J.

ATA/GAMA REFERENCE

57-30-00

LEFT SIDE MAIN LANDING GEAR AREA 1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

K.

CMM

2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

32-40-00

3. BRAKE DEICING (IF INSTALLED) - Inspect manifold for blocked orifices.

32-41-00

4. TIRES - Inspect tires for wear, deterioration and correct inflation.

32-40-00 12-10-00 CMM

5. STRUT - Check strut for leaks and proper extension.

12-10-00

6. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

AC43.13-1B/2B

7. MAIN GEAR ACTUATOR - Inspect actuator and plumbing for leakage and attachment.

32-30-00

LEFT SIDE ENGINE 1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00

2. P3 AIR FILTER - Inspect the filter for cleanliness. Refer to the engine maintenance manual for procedure. 3. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

28-20-00 12-10-00

4. PROPELLERS a. Inspect for damage and attachment (spinner removal required).

A28

61-10-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

b. Inspect the carbon block pin for freedom of movement. c.

Check for no metal-to-metal contact between the brass ring and the reversing lever.

61-10-00

d. Inspect the reversing linkage for correct adjustment, evidence of binding and security of attachment.

76-00-00

e. Inspect mechanical feedback ring, stop rods and springs for damage.

61-10-00

5. HIGH PRESSURE FUEL PUMP FILTER - Inspect the enginedriven high pressure fuel pump filters as instructed in the appropriate engine maintenance manual. 6. ENGINE OIL FILTER - Inspect for metal particles. Refer to the engine maintenance manual. 7. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT - If Sunstrand fuel pump is installed, check the exterior of the fuel pump coupling for fretting and corrosion as instructed by the engine maintenance manual.

P&W 72-00-00 P&W 73-10-02

8. DRAIN PLUGS - Inspect all drain plugs for leakage, security and safetying.

79-00-00

9. COWLING - Remove entire cowling and inspect skin, structure and attaching hardware for wear, damage and corrosion.

71-10-00

10. OIL COOLER - Inspect oil cooler and plumbing for leakage, damage and attachment.

79-00-00

11. AFT COWLING ACCESS DOOR - Check adjustment of latches.

71-10-00

12. FIRESEALS - Inspect for condition.

71-30-00

13. EXHAUST SYSTEM a. Inspect attaching hardware for wear, damage and corrosion. b. Inspect the exhaust system and visible portions of the power turbine for burning, distortion, damage and cracks. If any of these conditions are found, refer to the engine maintenance manual for corrective action. 14. ENGINE and PROPELLER CONTROLS a. Check controls and associated equipment for binding, stiff operation, full travel and friction lock.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

b. Inspect controls, bolts, nuts, cotter pins and safeties for corrosion, damage and attachment. c.

Inspect control cables for damage such as crimps, cuts, abrasions or tight bends. If exterior covering is ruptured, perform leak test.

76-00-00

15. CONTROL CABLE BOOTS - Inspect the control cable boots for excessive compression, twist, wear or aging which could cause binding. 16. STARTER-GENERATOR BRUSHES - Inspect one set of brushes for indications of excessive wear or damage (determine wear by observing diagonal groove on brush).

24-30-00

17. COMPRESSOR INLET - Remove the air inlet screen and inspect the compressor inlet area, struts, first stage blades and vanes for dirt deposits, corrosion, erosion, cracks and damage by foreign objects. Refer to the engine maintenance manual for corrective action. 18. MAGNETIC CHIP DETECTOR a. Check plug.

79-30-00

b. Check light in annunciator panel.

79-30-00

19. ENGINE a. Inspect fuel nozzles per manufacturer's manual. b. Inspect engine in accordance with the instructions found in the engine manufacturer's manual (refer to Chapter 72). 20. ENGINE MOUNT TRUSS ASSEMBLY a. Inspect for cracks, dents, chafing and corrosion. Special attention should be made to areas around clamps.

71-20-00

b. Inspect vibration isolators (mounts) for deterioration, damage and attachment.

71-20-00

21. INDUCTION SYSTEM a. Check the inertial anti-icer vanes for proper travel.

30-20-00

b. Inspect the engine inlet screen, inertial separator and air inlet duct for obstruction and damage.

71-00-00 30-20-00

22. FIRE DETECTION SYSTEM a. Inspect fire detection cable for kinks, abrasions or bends with a radius of less than 2 inches.

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26-10-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

b. Inspect the fire detection cables to make sure they do not contact the surrounding structure and for security of attachment.

26-10-00

c.

26-10-00

Perform a check of the system.

23. PROPELLER SYNCHROPHASER - Inspect for proper gap between pickups and targets.

61-22-00

24. AUTOFEATHER and AUTOIGNITION PRESSURE SWITCHES - Inspect security of attachment, leakage and electrical connection for security.

61-21-00 74-00-00

25. PRIMARY PROPELLER GOVERNOR - Inspect for security of attachment, leakage and security of electrical connectors and wiring.

61-20-00

26. OVERSPEED GOVERNOR - Inspect for security of attachment, leakage and security of electrical connectors and wiring.

61-20-00

MECH

INSP

27. RUDDER BOOST TRANSDUCER - Inspect for security of attachment, leakage and security of electrical connectors and wiring. 28. IGNITION EXCITER a. Inspect exciter and electrical harness for damage and security of attachment.

74-00-00

b. Inspect that supply cable and ignition cable connectors are installed and safetied.

74-00-00

29. SPARK IGNITER PLUGS - Inspect the igniter plugs as described in the engine maintenance manual. 30. FUEL PURGE SYSTEM a. Remove fuel purge system air tank and inspect. Clean as required.

71-70-00

b. Remove fuel purge tank filter and inspect for corrosion. Clean as required.

71-70-00

c.

Page 208 May 1/10

Remove the fuel purge system check valves. Inspect, pressure flush and perform internal leakage test. Replace as required.

71-70-00

d. Perform the Fuel Purge System Flow Divider/Purge Valve Leakage Test.

71-70-00

5-21-02

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued) 31. ENVIRONMENTAL BLEED AIR FLOW CONTROL VALVE Inspect valve and associated equipment, electrical wiring and ducts for damage, security of connections and attachment. L.

ATA/GAMA REFERENCE

MECH

INSP

21-10-00

RIGHT SIDE OUTBOARD WING 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

3. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

33-40-00

b. Inspect the strobe light for broken or cracked lenses.

33-40-00

4. FUEL TANKS and VENTS

M.

a. Inspect exterior openings of vents for obstructions.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

5. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

6. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

7. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

8. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

9. STATIC WICKS - Inspect for damage and security of attachment.

23-60-00

RIGHT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS

A28

a. Inspect the exterior of the center section for leaks.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior openings of the vents for obstructions.

5-21-02

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

M. RIGHT SIDE WING CENTER SECTION (Continued)

N.

ATA/GAMA REFERENCE

3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

4. BATTERY - Service battery as required.

12-10-00

MECH

INSP

RIGHT SIDE MAIN LANDING GEAR AREA 1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

O.

CMM

2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

32-40-00

3. BRAKE DEICING (IF INSTALLED) - Inspect manifold for blocked orifices.

32-41-00

4. TIRES - Inspect tires for wear, deterioration and correct inflation.

32-40-00 12-10-00 CMM

5. STRUT - Check strut for leaks and proper extension.

12-10-00

6. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

AC43.13-1B/2B

7. MAIN GEAR ACTUATOR - Inspect actuator and plumbing for leakage and attachment.

32-30-00

RIGHT SIDE ENGINE 1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00

2. P3 AIR FILTER - Inspect the filter for cleanliness. Refer to the engine maintenance manual for procedure. 3. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

28-20-00 12-10-00

4. PROPELLERS

Page 210 May 1/10

a. Inspect for damage and attachment (spinner removal required).

61-10-00

b. Inspect the carbon block pin for freedom of movement.

61-10-00

5-21-02

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O. RIGHT SIDE ENGINE (Continued) c.

Check for no metal-to-metal contact between the brass ring and the reversing lever.

ATA/GAMA REFERENCE

MECH

INSP

61-10-00

d. Inspect the reversing linkage for correct adjustment, evidence of binding and security of attachment.

76-00-00

e. Inspect mechanical feedback ring, stop rods and springs for damage.

61-10-00

5. HIGH PRESSURE FUEL PUMP FILTER - Inspect the enginedriven high pressure fuel pump filters as instructed in the appropriate engine maintenance manual. 6. ENGINE OIL FILTER - Inspect for metal particles. Refer to the engine maintenance manual. 7. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT - If Sunstrand fuel pump is installed, check the exterior of the fuel pump coupling for fretting and corrosion as instructed by the engine maintenance manual.

P&W 72-00-00 P&W 73-10-02

8. DRAIN PLUGS - Inspect all drain plugs for leakage, security and safetying.

79-00-00

9. COWLING - Remove entire cowling and inspect skin, structure and attaching hardware for wear, damage and corrosion.

71-10-00

10. OIL COOLER - Inspect oil cooler and plumbing for leakage, damage and attachment.

79-00-00

11. AFT COWLING ACCESS DOOR - Check adjustment of latches.

71-10-00

12. FIRESEALS - Inspect for condition.

71-30-00

13. EXHAUST SYSTEM a. Inspect attaching hardware for wear, damage and corrosion. b. Inspect the exhaust system and visible portions of the power turbine for burning, distortion, damage and cracks. If any of these conditions are found, refer to the engine maintenance manual for corrective action. 14. ENGINE and PROPELLER CONTROLS a. Check controls and associated equipment for binding, stiff operation, full travel and friction lock.

A28

5-21-02

Page 211 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O. RIGHT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

b. Inspect controls, bolts, nuts, cotter pins and safeties for corrosion, damage and attachment. NOTE Special attention should be directed to the cam box. c.

Inspect control cables for damage such as crimps, cuts, abrasions or tight bends. If exterior covering is ruptured, perform leak test.

76-00-00

15. CONTROL CABLE BOOTS - Inspect the control cable boots for excessive compression, twist, wear or aging which could cause binding. 16. STARTER-GENERATOR BRUSHES - Inspect one set of brushes for indications of excessive wear or damage (determine wear by observing diagonal groove on brush).

24-30-00

17. COMPRESSOR INLET - Remove the air inlet screen and inspect the compressor inlet area, struts, first stage blades and vanes for dirt deposits, corrosion, erosion, cracks and damage by foreign objects. Refer to the engine maintenance manual for corrective action. 18. MAGNETIC CHIP DETECTOR a. Check plug.

79-30-00

b. Check light in annunciator panel.

79-30-00

19. ENGINE a. Inspect fuel nozzles per manufacturer's manual. b. Inspect engine in accordance with instructions found in the engine manufacturer's manual (refer to Chapter 72). 20. AIR-CONDITIONER COMPRESSOR a. Inspect for security of attachment and oil leaks.

21-50-00

b. Inspect for wear and lubricate the spline on the pulley end of the quill shaft.

21-50-00

c.

Inspect drive belt for deterioration, wear and proper tension. 21-50-00

Page 212 May 1/10

5-21-02

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O. RIGHT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

d. Inspect the integrity and security of the clutch assembly. Remove the belt from the compressor. Inspect for freedom of rotation, bearing roughness and free play (wobble). Check for corrosion or evidence of inappropriate wear (belt dust, metal shavings). Install belt on compressor.

21-50-00

21. REFRIGERANT LINES and SERVICE VALVES - Inspect lines and valves for leakage, damage and attachment.

21-50-00

MECH

INSP

22. ENGINE MOUNT TRUSS ASSEMBLY a. Inspect for cracks, dents, chafing and corrosion. Special attention should be directed to areas around clamps.

71-20-00

b. Inspect vibration isolators (mounts) for deterioration, damage and attachment.

71-20-00

23. INDUCTION SYSTEM a. Check the inertial anti-icer vanes for proper travel.

30-20-00

b. Inspect the engine inlet screen, inertial separator and air inlet duct for obstruction and damage.

71-00-00 30-20-00

24. FIRE DETECTION SYSTEM

A28

a. Inspect fire detection cable for kinks, abrasions or bends with a radius of less than 2 inches.

26-10-00

b. Inspect fire detection cables to make sure they do not contact the surrounding structure and for security of attachment.

26-10-00

c.

26-10-00

Perform a check of the system.

25. PROPELLER SYNCHROPHASER - Inspect for proper gap between pickups and targets.

61-22-00

26. AUTOFEATHER and AUTOIGNITION PRESSURE SWITCHES - Inspect for security of attachment, leakage and electrical connection for security.

61-21-00 74-00-00

27. PRIMARY PROPELLER GOVERNOR - Inspect for security of attachment, leakage and security of electrical connectors and wiring.

61-20-00

28. OVERSPEED GOVERNOR - Inspect for security of attachment, leakage and security of electrical connectors and wiring.

61-20-00

5-21-02

Page 213 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O. RIGHT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

29. RUDDER BOOST TRANSDUCER - Inspect for security of attachment, leakage and security of electrical connectors and wiring. 30. IGNITION EXCITER a. Inspect exciter and electrical harness for damage and security of attachment.

74-00-00

b. Inspect that supply cable and ignition cable connectors are installed and safetied.

74-00-00

31. SPARK IGNITER PLUGS - Inspect the igniter plugs as described in the engine maintenance manual. 32. FUEL PURGE SYSTEM a. Remove fuel purge system air tank and inspect. Clean as required.

71-70-00

b. Remove fuel purge tank filter and inspect for corrosion. Clean as required.

71-70-00

c.

P.

Remove fuel purge check valves. Inspect, pressure flush and perform internal leakage test. Replace as required.

71-70-00

d. Perform the Fuel Purge System Flow Divider/Purge Valve Leakage Test.

71-70-00

33. ENVIRONMENTAL BLEED AIR FLOW CONTROL VALVE Inspect valve and associated equipment, electrical wiring and ducts for damage, security of connections and attachment.

21-10-00

LANDING GEAR RETRACTION 1. RETRACT MECHANISM NOTE

Since battery voltage is not sufficient to properly cycle the landing gear, use only an exterior power source capable of delivering and maintaining 28.25 ±0.25 volts throughout the extension and retraction cycles when performing the landing gear retraction inspection. When cycling the landing gear with the power pack, allow a one minute cooling period between cycles and a five minute cooling period every five cycles. Also, an exterior supply of dry air at 18 to 20 psi must be applied to the fill reservoir to prevent cavitation. If an exterior air supply is not available, use an exterior hydraulic pressure source.

Page 214 May 1/10

a. Check hydraulic power pack and motor for proper operation.

32-30-00

b. Check retraction system for proper operation of all components through at least two complete cycles.

32-30-00

5-21-02

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

Check for unusual noises and evidence of binding.

P. LANDING GEAR RETRACTION (Continued)

32-30-00 ATA/GAMA REFERENCE

2. DOORS and LINKAGE - Check door for operation, fit and rigging.

32-30-00

3. POSITION INDICATORS - Check for proper operation of switches.

32-60-00

4. WARNING HORN - Check operation.

32-60-00

MECH

INSP

5. DOWNLOCKS MECHANISM a. Check locking mechanism for positive engagement in extended position.

32-10-00 32-20-00

b. Check downlock switch for proper adjustment.

32-60-00

6. SAFETY SWITCH - Check for proper operation.

32-60-00

7. ACTUATORS - Check for noise, binding and proper rigging.

32-30-00

8. EMERGENCY EXTENSION - Check system for freedom of operation and positive engagement of downlocks.

32-30-00

CAUTION Do not continue operation after receiving a gear-down indication on all gears. Q.

OPERATIONAL INSPECTION NOTE

The following Operational Inspection procedures are to be applied during start and run of the engine. Refer to the Super King Air B300 and B300C Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual for the engine start and run procedures. 1. FIREWALL SHUTOFF VALVES - Check for proper operation. 2. CROSSFEED FUEL VALVE - Check for proper operation. 3. BOOST PUMPS - Check for proper operation. 4. STARTERS - Check operation. 5. IGNITION LIGHTS - Check for annunciator panel light illumination. 6. ENGINE OIL TEMPERATURE and PRESSURE - Check for proper pressure and temperature limits. 7. FUEL QUANTITY GAGES - Check operation. 8. INTERSTAGE TURBINE TEMPERATURE - Check for correct limits on engine start.

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5-21-02

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

9. VACUUM SYSTEM INSTRUMENTS - Check for correct limits. Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

10. PNEUMATIC PRESSURE GAGE - Check for correct pressure. 11. PNEUMATIC SYSTEM SHUTOFF VALVES - Check for proper operation. 12. GYRO INSTRUMENTS - Check for erratic or noisy operation. 13. PROPELLERS - Perform flight idle torque check.

76-00-00

14. AUTOFEATHERING CHECK - Refer to AUTOFEATHER SYSTEM OPERATIONAL CHECK.

61-21-00

15. PROPELLER SYNCHROPHASER - Refer to the SYNCHROPHASER SYSTEM FUNCTIONAL TEST and confirm proper synchronization.

61-22-00

16. PROPELLER GOVERNOR - Check governor operation (including feathering and reversing).

76-00-00

17. IDLE RPM - Check for correct rpm (both high and low rpm).

76-00-00

18. AC INVERTERS (If installed) - Check for proper operation.

24-20-00

19. RUDDER BOOST - Check for proper operation. 20. AUTOIGNITION - Check for proper operation. 21. PROPELLER DEICER - Check for proper operation and cycling. Refer to Chapter 30 of the King Air Series Component Maintenance Manual.

POH 74-00-00 CMM

22. ENGINE INERTIAL ANTI-ICER - Check for proper operation and rigging. 23. DEICE SYSTEM a. Check for proper operation and cycling. b. Functionally test tail and wing deice annunciator lights for operation. 24. BRAKE DEICE SYSTEM (IF INSTALLED) - Check for proper operation with engines running. 25. ELECTRICAL SYSTEM - Perform functional check.

24-50-00

26. ENVIRONMENTAL SYSTEM - Check for proper operation in: a. Manual heat mode. b. Manual cool mode.

Page 216 May 1/10

5-21-02

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

Automatic mode.

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

27. AUTOPILOT - Check for proper operation as outlined by the applicable Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement. 28. STALL WARNING - Check for proper operation. 29. GENERATORS - Check the output. 30. ENGINE FIRE DETECTORS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 31. ENGINE FIRE EXTINGUISHERS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 32. PRESSURIZATION SYSTEM - Check for proper operation. NOTE Refer to the Super King Air B300 and B300C Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual and perform system test. 33. AUXILIARY FUEL TRANSFER JET PUMPS - Check for operation. 34. CONDITION LEVER - Check for clean shutdown at IDLE-CUTOFF. 35. PITOT TUBE - Check for proper heating at the unit and for obstructions.

A28

36. LANDING and TAXI LIGHTS - Check operation of all lights.

33-40-00

37. OUTBOARD WING LIGHTS (Right Side and Left Side) - Check operation of all navigation and strobe lights.

33-40-00

38. COCKPIT LIGHTS - Check operation of all cockpit lights.

33-10-00

39. EFIS COOLING BLOWERS (If Installed) - Check operation.

34-20-00

40. ELECTRIC ELEVATOR TRIM - Check for proper operation.

27-30-00

41. ENGINE and PROPELLER CONTROLS - Check for freedom of movement, full travel and friction-lock operation.

76-00-00

5-21-02

Page 217 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

42. PILOT'S and COPILOT'S SEATS and SEAT BELTS - Check seat adjustment mechanism and shoulder harness inertia reel for operation. 43. STATIC SYSTEM - Inspect alternate air valve for operation.

34-00-00

44. WINDSHIELDS - Perform heated operational check.

30-40-00

45. THRESHOLD LIGHT - Check for proper operation. 46. AUXILIARY ELECTRIC HEAT - Check for proper operation of the Electric Heat System. 47. CABIN and COMPARTMENT LIGHTS - Check for proper operation. 48. CABIN SEATS and SEAT BELTS - Check seat adjustment mechanism and shoulder harness inertia reel for operation. 49. CABIN ENTRANCE DOOR (FL-1 and AFTER) a. Check that folding steps do not fold too soon and that they fold properly without interference. b. Check cabin DOOR UNLOCK annunciator for proper operation. c.

Inspect cabin door damper for leakage and proper operation.

50. CABIN CARGO DOOR and CABIN ENTRANCE DOOR (FM- 1 and After) a. Inspect door latching mechanism for operation and security of attachment. b. Check latching mechanism, folding steps and gas springs for proper operation. 51. EMERGENCY EXITS (With door installed and properly rigged) a. Check emergency release handles (inside and outside) and latch mechanism for operation. b. Check that latches open and close freely. 52. EMPENNAGE CONTROL SURFACES a. Check for freedom of movement. b. Check optional trim actuators and motors for smoothness of operation.

Page 218 May 1/10

5-21-02

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued) 53. REAR FUSELAGE and EMPENNAGE LIGHTS - Check operation of all lights.

ATA/GAMA REFERENCE

MECH

INSP

33-40-00

54. AILERON (Left Side and Right Side) - Check for freedom of movement. 55. AILERON TRIM TAB - Check trim tab actuator for smoothness of operation and attachment. 56. FUEL TANK VENTS (Left Side and Right Side) - Check the operation of the heated vents. They should be warm to the touch.

28-10-00

57. STALL WARNING HEAT - Check for proper operation. 58. FLAPS and ACTUATORS (INBOARD, OUTBOARD, Left Side and Right Side) - Check flaps for noisy or erratic operation.

27-50-00

59. WING CENTER SECTION LIGHTS - Check operation of all lights.

33-40-00

60. ENGINE INDUCTION SYSTEM (Left Side and Right Side) Check the inertial vane and bypass door for movement with the main and standby actuator motors.

R.

61. EXTERNAL POWER RELAY - Check for proper operation.

24-40-00

62. ELECTRIC HEATER POWER RELAY S - Check for proper operation.

21-40-00

POST INSPECTION ITEMS 1. AIRPLANE CLEANED and SERVICED AS REQUIRED.

12-00-00

2. LUBRICATE AS NECESSARY.

12-20-00

3. ENGINES INSPECTED AFTER GROUND RUN-UP OR FLIGHT TEST - Check for oil leaks, security and attachment of all components. 4. AIRWORTHINESS DIRECTIVES and SERVICE BULLETINS Must be reviewed and complied with as required. 5. ADDITIONAL INSPECTION REQUIREMENTS - Make sure Chapter 5, Special Inspection, and Airworthiness Limitations Manual (P/N 130-590031-211) requirements are complied with at the appropriate intervals. 6. IN-FLIGHT WORKSHEETS DISCREPANCIES - All discrepancies noted by the pilot must be checked and corrected as required.

A28

5-21-02

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

R. POST INSPECTION ITEMS (Continued) 7. EMERGENCY LOCATOR TRANSMITTER - Check for proper operation and make sure ELT is ARMED before returning airplane to service.

ATA/GAMA REFERENCE

MECH

INSP

25-60-00

8. OXYGEN SYSTEM PRESSURE - Check for proper pressure. 9. EMERGENCY and SURVIVAL EQUIPMENT - (If required) Make sure all necessary emergency and survival equipment is installed in the airplane and is serviceable. 10. PLACARDS - Determine that all required placards are in place and legible.

11-20-00 and POH

11. LOGBOOK ENTRY - Ensure that log books are filled out properly.

INSPECTION COMPLETED I certify that Phase 2 Inspection was performed in accordance with the Model B300/B300C Inspection Program and that the airplane is approved for return to service: DATE: ............................................................................................................................................................ MECHANIC: .................................................................................................................................................. CREW CHIEF: ............................................................................................................................................... QUALITY CONTROL INSPECTOR: ..............................................................................................................

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SUPER KING AIR B300/B300C MAINTENANCE MANAUL 200200200 5-21-03

SCHEDULED INSPECTION PROGRAM (PHASE 3) - MAINTENANCE PRACTICES

Owner _____________________________________

Total Time ____________ Total Cycles ___________

W/O Number _________________________________ TSOH ________________ Cycles SOH ____________ Date In ________________ Date Out ______________ TSHSI _______________ Cycles SHSI ____________ Serial No. _____________ Reg. No. _______________ RH Eng. Gas Gen. S/N _________________________ Last Inspection ____________ Phase _____________ RH Eng. Power Module S/N _____________________ Last Inspection Date ___________________________ Total Time ____________ Total Cycles ____________ Last Inspection Hours __________________________ TSOH ________________ Cycles SOH ____________ Hourmeter _______________ Total Time __________

TSHSI _______________ Cycles SHSI ____________

Total Cycles _________________________________

LH Prop S/N _________________________________

Researched By _______________________________ LH Prop Total Time ____________ TSOH __________ Inspection Being Conducted _____________ Phase

RH Prop S/N _________________________________

LH Eng. Gas Gen. S/N _________________________ RH Prop Total Time ____________ TSOH __________ LH Eng. Power Module S/N ______________________

A.

NOSE SECTION

ATA/GAMA REFERENCE

MECH

INSP

NOTE There are no inspections required in this section during this phase. B.

NOSE AVIONICS COMPARTMENT NOTE

There are no inspections required in this section during this phase. C.

NOSE LANDING GEAR AREA 1. ELECTRICAL WIRING and EQUIPMENT - Inspect all exposed electrical wiring and equipment for chafing, damage and security of attachment.

D.

AC43.13-1B/2B

NOSE GEAR 1. WHEEL a. Inspect wheel for wear, damage and corrosion.

A28

5-21-03

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

D. NOSE GEAR (Continued) b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

ATA/GAMA REFERENCE

MECH

INSP

CMM

2. TIRE a. Inspect for wear and deterioration. b. Check for correct inflation. 3. SHIMMY DAMPER - Inspect for leaks, security and attachment.

12-10-00 32-20-00 12-10-00

4. NOSE GEAR DRAG BRACE STOP LUGS - Inspect for cracks, damage or distortion. 5. NOSE GEAR STEERING STOP - Inspect steering stop for damage or distortion. 6. LANDING and TAXI LIGHTS - Inspect for broken lenses or bulbs.

33-40-00

7. STEERING LINKAGE - Inspect nose gear steering mechanism and attaching hardware for wear, damage and corrosion. E.

PILOT'S COMPARTMENT 1. RETURN AIR INLET FILTERS - Inspect filters in return air inlet of the forward vent blower.

21-50-00

2. WINDSHIELDS a. Inspect windshields for cracks, visibility impairment.

56-10-00

b. Inspect windshield weather seal for debonding, cracks or wear. 3. WINDOWS - Inspect exterior surface of cockpit side windows for deep scratches, cracks, chips or excess crazing or other damage.

56-15-00

4. SEAT BELTS and SHOULDER HARNESSES - Inspect seat belts and shoulder harness for deterioration.

AC43.13-1B/2B

5. FIRE EXTINGUISHER, (PORTABLE) - Inspect the bottle for signs of damage and mount for security of attachment. 6. PILOT'S COMPARTMENT - Inspect skin, structure, seats and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area. 7. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

Page 202 May 1/10

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AC43.13-1B/2B

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SUPER KING AIR B300/B300C MAINTENANCE MANAUL

E. PILOT'S COMPARTMENT (Continued)

ATA/GAMA REFERENCE

MECH

INSP

8. REFRIGERANT LINES and SERVICE VALVES - Inspect lines for leakage, damage and attachment. 9. RUDDER PEDALS a. Inspect rudder pedals for wear, clearance and attachment.

27-20-00

b. Inspect rudder pedal linkage for wear, damage, attachment and operation.

27-20-00

10. BRAKE FLUID RESERVOIR PRESSURE EQUALIZATION ORIFICE - Inspect for blockage.

32-40-00

11. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given three-foot cable length or have evidence of corrosion.

27

12. BRAKE SYSTEM - Inspect brake system components and plumbing for leakage and attachment. 13. INSTRUMENT PANEL, PLUMBING and WIRING - Inspect instrument panel, subpanels, placards, shock mounts and instrument plumbing for damage, attachment, chafing and hoses for hardness or cracks. 14. CONTROL COLUMN a. Inspect for wear, damage, corrosion, attachment and operation. b. Inspect control wheel adapter for cracks in the weld area of adapter or forward side of control wheel. c.

Inspect control wheel switches for condition and security of attachment.

d. Operate control wheel full forward and aft, left and right. Check for binding or interference.

27-10-00

15. PEDESTAL a. Inspect pedestal components and plumbing for damage, attachment and chafing and hoses for hardness or cracks.

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5-21-03

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

E. PILOT'S COMPARTMENT (Continued) b. Inspect condition lever catch gates for wear.

ATA/GAMA REFERENCE

MECH

INSP

76-00-00

16. PRESSURIZATION CONTROLLER a. Inspect for security of attachment, plumbing and wiring for damage and connection security.

21-30-00

b. Inspect and clean filter in controller assembly located within the pedestal.

21-30-00

17. SEAT TRACKS - Inspect seat tracks for damage and wear.

53-40-00

18. ACCESS DOORS - Inspect for fit and attachment. 19. WINDSHIELDS - Inspect heated windshield antistatic coating and tab bonding.

56-10-00

20. RELIEF TUBE (If installed) a. Inspect plumbing and storage box for corrosion. b. Inspect relief tube outlet area for corrosion. 21. ALTERNATE AIR VALVE - Drain off all moisture.

34-00-00

22. BUS CONFORMITY CHECK - Perform the bus conformity check. Refer to procedure in Chapter 24-50-00.

24-50-00

23. ENVIRONMENTAL SYSTEM a. Inspect ducts for condition and security of installation. b. Check ducts for evidence of thermal leaks and/or degradation, such as discoloration of duct insulator, adjacent structure or components. c.

Page 204 May 1/10

Physically inspect ducts by touching ducts, checking for thermal deterioration, deformation of the ducts, and proper connection at the joints. If any damage is found in steps a., b. or c., perform the following procedures:

5-21-03

A28

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

E. PILOT'S COMPARTMENT (Continued)

ATA/GAMA REFERENCE

MECH

INSP

24. MANUAL LANDING GEAR EXTENSION HANDLE - Inspect the manual extension handle assembly and linkage from the handle to the manual extension pump for proper installation, wear and security of attachment. F.

CABIN SECTION 1. WINDOWS - Inspect exterior surfaces of windows for deep scratches, cracks, chips and excessive crazing or other damage.

56-15-00

2. ROTATING (FLASHING) BEACON - Inspect for cracked or broken lenses.

33-40-00

3. ACCESS DOORS - Inspect for fit and attachment. 4. EMERGENCY EXIT LIGHT a. Inspect emergency exit light for battery leakage and security of lamp. b. Inspect electrical wiring and equipment for chafing, damage, proper routing of wire bundles and security of attachment.

33-20-00

AC43.13-1B/2B

5. OUTFLOW and SAFETY VALVES a. Drain outflow valve control line (two locations).

21-30-00

b. Inspect plumbing and components for attachment.

21-30-00

c.

21-30-00

Inspect and clean safety valve screen.

d. Inspect poppet and seat of both valves.

21-30-00

e. Perform functional test of outflow and safety valves and cabin altitude limit controllers.

21-30-00

6. AFT EVAPORATOR FILTER - Inspect aft evaporator filter.

21-50-00

7. SEAT BELTS and SHOULDER HARNESSES a. Inspect seat belts and shoulder harness for deterioration and missing components.

AC43.13-1B/2B

b. Inspect shoulder harness attachment post for cracked, warn, brittle or missing grommets.

AC43.13-1B/2B

8. SEAT TRACKS - Inspect seat tracks for damage and wear.

53-40-00

9. OXYGEN SYSTEM a. Test all masks for oxygen flow.

A28

35-00-00

5-21-03

Page 205 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

F. CABIN SECTION (Continued) b. Inspect oxygen system installation for damage and security of attachment.

ATA/GAMA REFERENCE

MECH

INSP

35-00-00

10. TOILET - Inspect for spillage and leakage below the toilet. 11. CABIN ENTRANCE DOOR (FL-1 and After) a. Inspect the door seal for cuts, abrasions and security of attachment.

52-10-00

b. Inspect door seal solenoid valve and pressure regulator valve for security and electrical connection.

52-10-00

c.

Inspect the cabin door support cables for wear, damage and security.

d. Inspect door latching mechanism and cables for damage, deterioration and security of attachment. e.

f.

52-10-00 52-10-00

Inspect upper latch hooks and retaining pins for rigging, wear and damage. Replace pin at 10% diameter wear. (Pin removal required)

52-10-00

Inspect upper latch hooks for proper tension.

52-10-00

g. Inspect side latch bolts (bayonets) and rollers for rigging and freedom of movement.

52-10-00

h. Inspect the cabin door unlocked annunciator switch spring.

52-10-00

12. CABIN CARGO DOOR and CABIN ENTRANCE DOOR (FM-1 and After) - Inspect door seals for cuts, abrasions, deterioration and security of attachment.

52-11-00

13. AVIONICS EQUIPMENT and RACKS (IF INSTALLED) Inspect avionics equipment and racks for security of attachment. 14. BULKHEADS - Inspect for water traps. 15. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS

Page 206 May 1/10

a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends and cracks which are conditions for replacement.

27

b. Inspect control cables, pulleys and associated equipment for cracks, damage, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given three-foot cable length or have evidence of corrosion.

27

5-21-03

A28

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

F. CABIN SECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

16. HYDRAULIC LINES, LANDING GEAR - Inspect for leaks, damage and security of attachment. 17. FLAP MOTOR and DRIVES - Inspect for damage and attachment.

27-50-00

18. AILERON QUADRANT REGULATOR - Inspect for security, attachment, operation and travel.

27-10-00

19. BELLY DRAIN VALVES - Inspect for possible obstructions. 20. CABIN WINDOW ATTACH FRAMES - Inspect windows for looseness or movement.

56-15-00

21. PNEUMATIC PRESSURE REGULATOR, VACUUM EJECTOR and DEICER DISTRIBUTION VALVE - Inspect equipment and plumbing for security. 22. WINDOW DEFOG SYSTEM - Inspect associated plumbing for kinks, security and general condition. Inspect the three inline filters (if installed) for moisture, contamination and proper installation (recommend replacement to coincide with Chapter 5-11-00 requirements).

30-40-00

23. CONTROL CABLE SEALS - Inspect for damage, security, cleanliness and lubrication. 24. AUTOPILOT COMPONENTS - Inspect components for security of attachment. 25. RELIEF TUBE (If installed) a. Inspect plumbing and storage box for corrosion. b. Inspect relief tube outlet area for corrosion. 26. ANTENNAS - Inspect all external antennas for leading edge erosion and condition of base seals. 27. FIRE EXTINGUISHER, (PORTABLE) - Inspect bottle for signs of damage and security. 28. CABIN DOOR and EMERGENCY EXITS

A28

a. Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

AC43.13-1b/2A

b. Inspect corner areas of emergency exit (removed) for cracks and abrasion in area of curvature between seal and outer face of exit.

52-20-00

5-21-03

Page 207 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

F. CABIN SECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

29. EMERGENCY EXITS a. Inspect latches for damage and check all moving parts for proper operation. b. Check for proper latch adjustment and seal of closed latches. 30. ELECTRICAL WIRING and EQUIPMENT - Inspect all exposed electrical wiring and equipment for chafing, damage and security of attachment. 31. CABIN AREA - Inspect skin, structure, seats and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

AC43.13-1B/2B

25-20-00

32. ENVIRONMENTAL SYSTEM a. Inspect ducts for condition and security of installation. b. Check ducts for evidence of thermal leaks and/or degradation, such as discoloration of duct insulator, adjacent structure or components. c.

G.

Physically inspect ducts by touching ducts, checking for thermal deterioration, deformation of the ducts, and proper connection at the joints.

REAR FUSELAGE AND EMPENNAGE 1. REAR FUSELAGE DRAINS - Inspect rear fuselage drains.

53-00-00

2. ELT BATTERY a. Inspect for leakage, corrosion or loose leads.

25-60-00

b. Determine remaining useful life.

25-60-00

3. NAVIGATION LIGHTS and ROTATING (FLASHING) BEACONS - Inspect for broken or cracked lenses.

33-40-00

4. ACCESS DOORS - Inspect for fit and security of attachment. 5. VENTRAL FIN DRAIN HOLES - Inspect the drain holes in the bottom of the ventral fin for obstructions.

53-00-00

6. DEICER BOOTS - Inspect for deterioration, damage and attachment. 7. RUDDER and TRIM TAB DRAIN HOLES - Inspect the drain holes for obstructions.

Page 208 May 1/10

5-21-03

55-40-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

H.

LEFT SIDE OUTBOARD WING

ATA/GAMA REFERENCE

1. STATIC WICKS - Inspect for damage and security of attachment.

23-60-00

2. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

3. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

MECH

INSP

4. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

33-40-00

b. Inspect the strobe light for broken or cracked lenses.

33-40-00

5. FUEL TANKS and VENTS a. Inspect exterior openings of vents for obstructions.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

6. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

7. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

8. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

9. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

10. STATIC WICKS a. Inspect for damage and security of attachment.

23-60-00

b. Check the static wick for proper bonding to the airplane.

23-60-00

11. AILERON and TRIM TAB - Check trim tab free play. I.

27-10-00

LEFT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS

A28

a. Inspect the exterior of the center section for leaks.

28-10-00

b. Inspect fuel filler cap and antisiphon valve for damage and attachment.

28-10-00

5-21-03

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

I. LEFT SIDE WING CENTER SECTION (Continued) c.

ATA/GAMA REFERENCE

57-30-00

4. FUEL PUMP - Inspect the pumps for leaks and security of attachment.

28-20-00

5. ENGINE FIRE EXTINGUISHER

26-20-00

Inspect plumbing for security of attachment.

b. Check fire bottle pressure gage. c.

INSP

Inspect the exterior openings of the vents for obstructions.

3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

a.

MECH

Check for presence of activation voltage to the cartridge/ squib. Perform the EXTINGUISHER ACTIVATION CHECK procedure.

26-20-00 26-20-00 26-20-00

6. LANDING GEAR POWER PACK and MOTOR a. Inspect the hydraulic power pack gear-up and gear-down port screens.

32-30-00

b. Inspect the landing gear hydraulic system bleed air pressure overboard relief orifice screen for blockage.

32-30-00

c.

J.

Inspect all plumbing attach points for leaks and security of attachment.

32-30-00

d. Inspect the landing gear emergency extension hand pump suction line filter.

32-30-00

LEFT SIDE MAIN LANDING GEAR AREA 1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage. 2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

CMM 32-40-00

3. BRAKE DEICING (IF INSTALLED)

Page 210 May 1/10

a. Inspect manifold for blocked orifices.

32-41-00

b. Inspect exterior of lines, hoses and connections for leakage and attachment.

32-41-00

5-21-03

A28

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

J. LEFT SIDE MAIN LANDING GEAR AREA (Continued)

ATA/GAMA REFERENCE

4. TIRES - Inspect tires for wear, deterioration and correct inflation.

32-40-00 12-10-00 CMM

5. STRUT - Check strut for leaks and proper extension.

12-10-00

6. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

AC43.13-1B/2B

7. MAIN GEAR ACTUATOR - Inspect actuator and plumbing for leakage and attachment.

32-30-00

MECH

INSP

8. DRAG LEG a. Inspect for security of attach fittings. b. Inspect downlock bolts for proper torque (finger tight and safetied). 9. MAIN LANDING GEAR AREA - Inspect wheel well and gear door structure, all components and attaching hardware for wear, damage and corrosion. If damage or corrosion is found, check the adjacent area. K.

32-10-00 CMM

AC43.13-1B/2B

LEFT SIDE ENGINE 1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00

2. P3 AIR FILTER - Inspect the filter for cleanliness. Refer to the engine maintenance manual for procedure. 3. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

28-20-00 12-10-00

4. PROPELLERS - Inspect for damage and attachment (spinner removal required).

61-10-00

5. ENGINE OIL FILTER (Left) - Inspect for metal particles. Refer to engine maintenance manual.

A28

5-21-03

Page 211 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

L.

RIGHT SIDE OUTBOARD WING

ATA/GAMA REFERENCE

1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

MECH

INSP

3. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

33-40-00

b. Inspect the strobe light for broken or cracked lenses.

33-40-00

4. FUEL TANKS and VENTS a. Inspect exterior openings of vents for obstructions.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

5. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

6. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

7. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

8. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

9. STATIC WICKS a. Inspect for damage and security of attachment.

23-60-00

b. Check the static wick for proper bonding to the airplane.

23-60-00

10. AILERON and TRIM TAB - Check trim tab free play. M.

27-10-00

RIGHT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS a. Inspect the exterior of the center section for leaks.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

Page 212 May 1/10

Inspect the exterior openings of the vents for obstructions.

5-21-03

A28

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

M. RIGHT SIDE WING CENTER SECTION (Continued) 3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

4. BATTERY - Service Battery as required.

12-10-00

5. FUEL PUMPS - Inspect the pumps for leaks and security of attachment.

28-20-00

6. ENGINE FIRE EXTINGUISHER

26-20-00

a.

Inspect plumbing for security of attachment.

b. Check fire bottle pressure gage. c.

N.

ATA/GAMA REFERENCE

Check for presence of activation voltage to the cartridge/ squib. Perform the EXTINGUISHER ACTIVATION CHECK procedure.

MECH

INSP

26-20-00 26-20-00 26-20-00

RIGHT SIDE MAIN LANDING GEAR AREA 1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

CMM

2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

32-40-00

3. BRAKE DEICING (IF INSTALLED) - Inspect manifold for blocked orifices.

32-41-00

4. TIRES - Inspect tires for wear, deterioration and correct inflation.

32-40-00 12-10-00 CMM

5. STRUT - Check strut for leaks and proper extension.

12-10-00

6. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

AC43.13-1B/2B

7. MAIN GEAR ACTUATOR - Inspect actuator and plumbing for leakage and attachment.

32-30-00

8. DRAG LEG

A28

a. Inspect for security of attach fittings.

32-10-00

b. Inspect downlock bolts for proper torque (finger tight and safetied).

32-10-00

5-21-03

Page 213 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

N. RIGHT SIDE MAIN LANDING GEAR AREA (Continued) 9. MAIN LANDING GEAR AREA - Inspect wheel well and gear door structure, all components and attaching hardware for wear, damage and corrosion. If damage or corrosion is found, check the adjacent area. O.

ATA/GAMA REFERENCE

MECH

INSP

AC43.13-1B/2B

RIGHT SIDE ENGINE 1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00

2. P3 AIR FILTER - Inspect the filter for cleanliness. Refer to the engine maintenance manual for procedure. 3. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

28-20-00 12-10-00

4. PROPELLERS - Inspect for damage and attachment (spinner removal required).

61-10-00

5. ENGINE OIL FILTER - Inspect for metal particles. Refer to engine maintenance manual. P.

LANDING GEAR RETRACTION 1. RETRACT MECHANISM NOTE

Since battery voltage is not sufficient to properly cycle the landing gear, use only an exterior power source capable of delivering and maintaining 28.25 ±0.25 volts throughout the extension and retraction cycles when performing the landing gear retraction inspection. When cycling the landing gear with the power pack, allow a one minute cooling period between cycles and a five minute cooling period every five cycles. Also, an exterior supply of dry air at 18 to 20 psi must be applied to the fill reservoir to prevent cavitation. If an exterior air supply is not available, use an exterior hydraulic pressure source. a. Check hydraulic power pack and motor for proper operation.

32-30-00

b. Check retraction system for proper operation of all components through at least two complete cycles.

32-30-00

c.

32-30-00

Check for unusual noises and evidence of binding.

2. DOORS and LINKAGE - Check door for operation, fit and rigging.

32-30-00

3. POSITION INDICATORS - Check for proper operation of switches.

32-60-00

4. WARNING HORN - Check operation.

32-60-00

Page 214 May 1/10

5-21-03

A28

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

P. LANDING GEAR RETRACTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

5. DOWNLOCKS MECHANISM a. Check down locking mechanism for positive engagement in extended position.

32-10-00 32-20-00

b. Check downlock switch for proper adjustment.

32-60-00

6. SAFETY SWITCH - Check for proper operation.

32-60-00

7. ACTUATORS - Check for noise, binding and proper rigging.

32-30-00

8. EMERGENCY EXTENSION - Check system for freedom of operation and positive engagement of downlocks.

32-30-00

CAUTION Do not continue operation after receiving a gear-down indication on all gears. Q.

OPERATIONAL INSPECTION NOTE

The following Operational Inspection procedures are to be applied during start and run of the engine. Refer to the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual for the engine start and run procedures. 1. FIREWALL SHUTOFF VALVES - Check for proper operation. 2. CROSSFEED FUEL VALVE - Check for proper operation. 3. STANDBY PUMPS - Check for proper operation. 4. STARTERS - Check operation. 5. IGNITION LIGHT - Check for annunciator panel light illumination. 6. ENGINE OIL TEMPERATURE and PRESSURE - Check for proper pressure and temperature limits. 7. FUEL QUANTITY GAGES - Check operation. 8. INTERSTAGE TURBINE TEMPERATURE - Check for correct limits on engine start. 9. VACUUM SYSTEM - Check for correct limits. 10. PNEUMATIC PRESSURE GAGE - Check for correct pressure. 11. PNEUMATIC SYSTEM SHUTOFF VALVES - Check for proper operation. 12. GYRO INSTRUMENTS - Check for erratic or noisy operation.

A28

5-21-03

Page 215 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

13. PROPELLERS - Perform flight idle torque check.

76-00-00

14. AUTOFEATHERING CHECK - Refer to AUTOFEATHER SYSTEM OPERATIONAL CHECK.

61-21-00

15. PROPELLER SYNCHROPHASER - Refer to the SYNCHROPHASER SYSTEM FUNCTIONAL TEST and confirm proper synchronization.

61-22-00

16. PROPELLER GOVERNOR - Check governor operation (including feathering and reversing).

76-00-00

17. IDLE RPM - Check for correct rpm (both high and low rpm).

76-00-00

18. AC INVERTERS (If installed) - Check for proper operation.

24-20-00

19. RUDDER BOOST - Check for proper operation. 20. AUTOIGNITION - Check for proper operation. 21. PROPELLER DEICER - Check for proper operation and cycling. Refer to Chapter 30 of the King Air Series Component Maintenance Manual.

MECH

INSP

POH 74-00-00 CMM

22. ENGINE INERTIAL ANTI-ICER - Check for proper operation and rigging. 23. DEICER SYSTEM a. Check for proper operation and cycling. b. Functionally test tail and wing deice annunciator lights for operation. 24. BRAKE DEICE SYSTEM (IF INSTALLED) - Check for proper operation with engines running. 25. ELECTRICAL SYSTEM - Perform functional checks.

24-50-00

26. ENVIRONMENTAL SYSTEM - Check for proper operation in: a. Manual heat mode. b. Manual cool mode. c.

Page 216 May 1/10

Automatic mode.

5-21-03

A28

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

27. AUTOPILOT - Check for proper operation as outlined by the applicable Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement. 28. STALL WARNING - Check for proper operation. 29. GENERATORS - Check the output. 30. ENGINE FIRE DETECTORS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 31. ENGINE FIRE EXTINGUISHERS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 32. PRESSURIZATION SYSTEM - Check for proper operation. NOTE Refer to the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual and perform system test. 33. AUXILIARY FUEL TRANSFER JET PUMPS - Check for operation. 34. CONDITION LEVERS - Check for clean shutdown at IDLECUT-OFF. 35. PITOT TUBE - Check for proper heating at the unit and for obstructions.

A28

36. LANDING and TAXI LIGHTS - Check operation of all lights.

33-40-00

37. OUTBOARD WING LIGHTS (Right Side and Left Side) - Check operation of all navigation and strobe lights.

33-40-00

38. COCKPIT LIGHTS - Check operation of all cockpit lights.

33-10-00

39. EFIS COOLING BLOWERS (If Installed) - Check operation.

34-20-00

40. ELECTRIC ELEVATOR TRIM - Check for proper operation.

27-30-00

41. ENGINE and PROPELLER CONTROLS - Check for freedom of movement, full travel and friction-lock operation.

76-00-00

5-21-03

Page 217 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

42. PILOT'S and COPILOT'S SEATS and SEAT BELTS - Check seat adjustment mechanism and shoulder harness inertia reel for operation. 43. STATIC SYSTEM - Inspect alternate air valve for operation.

34-00-00

44. WINDSHIELDS - Perform heated operational check.

30-40-00

45. THRESHOLD LIGHT - Check for proper operation. 46. AUXILIARY ELECTRIC HEAT - Check for proper operation of the Electric Heat System. 47. CABIN and COMPARTMENT LIGHTS - Check for proper operation. 48. SEAT BELTS and SHOULDER HARNESSES, CABIN - Check seat adjustment mechanism and shoulder harness inertia reel for operation. 49. CABIN ENTRANCE DOOR (FL-1 and After) a. Check that folding steps do not fold too soon and that they fold properly without interference. b. Check cabin DOOR UNLOCK annunciator for proper operation. c.

Inspect cabin door damper for leakage and proper operation.

50. CABIN CARGO DOOR and CABIN ENTRANCE DOOR (FM-1 and After) a. Inspect door latching mechanism for operation and security of attachment. b. Check latching mechanism, folding steps and gas springs for proper operation. 51. EMERGENCY EXITS (With door installed and properly rigged) a. Check emergency release handles (inside and outside) and latch mechanism for operation. b. Check that latches open and close freely. 52. EMPENNAGE CONTROL SURFACES a. Check for freedom of movement. b. Check optional trim actuators and motors for smoothness of operation.

Page 218 May 1/10

5-21-03

A28

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

Q. OPERATIONAL INSPECTION (Continued) 53. REAR FUSELAGE and EMPENNAGE LIGHTS - Check operation of all lights.

ATA/GAMA REFERENCE

MECH

INSP

33-40-00

54. AILERON (Left Side and Right Side) - Check for freedom of movement. 55. AILERON TRIM TAB - Check trim tab actuator for smoothness of operation and attachment. 56. FUEL TANK HEATED VENTS (Left Side and Right Side) Check the operation of the heated vents. They should be warm to the touch.

28-10-00

57. STALL WARNING HEAT - Check for proper operation. 58. FLAPS and ACTUATORS (INBOARD, OUTBOARD, Left Side and Right Side) - Check flaps for noisy or erratic operation.

27-50-00

59. WING CENTER SECTION LIGHTS - Check operation of all lights.

33-40-00

60. ENGINE INDUCTION SYSTEM (Left Side and Right Side) Check the inertial vane and bypass door for movement with the main and standby actuator motors.

R.

61. EXTERNAL POWER RELAY - Check for proper operation.

24-40-00

62. ELECTRIC HEATER POWER RELAYS - Check for proper operation.

21-40-00

POST INSPECTION ITEMS 1. AIRPLANE CLEANED and SERVICED AS REQUIRED.

12-00-00

2. LUBRICATE AS NECESSARY.

12-20-00

3. ENGINES INSPECTED AFTER GROUND RUN-UP OR FLIGHT TEST - Check for oil leaks, security and attachment of all components. 4. AIRWORTHINESS DIRECTIVES and SERVICE BULLETINS Must be reviewed and complied with as required. 5. ADDITIONAL INSPECTION REQUIREMENTS - Make sure Chapter 5, Special Inspection, and Airworthiness Limitations Manual (P/N 130-590031-211) requirements are complied with at the appropriate intervals. 6. IN-FLIGHT WORKSHEETS DISCREPANCIES - All discrepancies noted by the pilot must be checked and corrected as required.

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Page 219 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANAUL

R. POST INSPECTION ITEMS (Continued) 7. EMERGENCY LOCATOR TRANSMITTER - Check for proper operation and make sure ELT is ARMED before returning airplane to service.

ATA/GAMA REFERENCE

MECH

INSP

25-60-00

8. OXYGEN SYSTEM PRESSURE - Check for proper pressure. 9. EMERGENCY and SURVIVAL EQUIPMENT - (If required) Make sure all necessary emergency and survival equipment is installed in the airplane and is serviceable. 10. PLACARDS - Determine that all required placards are in place and legible.

11-20-00 and POH

11. LOGBOOK ENTRY - Ensure that log books are filled out properly.

INSPECTION COMPLETED I certify that Phase 3 Inspection was performed in accordance with the Model B300/B300C Inspection Program and that the airplane is approved for return to service: DATE: ............................................................................................................................................................ MECHANIC: .................................................................................................................................................. CREW CHIEF: ............................................................................................................................................... QUALITY CONTROL INSPECTOR: ..............................................................................................................

Page 220 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 5-21-04

SCHEDULED INSPECTION PROGRAM (PHASE 4) - MAINTENANCE PRACTICES

Owner _____________________________________

Total Time ____________ Total Cycles ___________

W/O Number _________________________________ TSOH ________________ Cycles SOH ____________ Date In ________________ Date Out ______________ TSHSI _______________ Cycles SHSI ____________ Serial No. _____________ Reg. No. _______________ RH Eng. Gas Gen. S/N _________________________ Last Inspection ____________ Phase _____________ RH Eng. Power Module S/N _____________________ Last Inspection Date ___________________________ Total Time ____________ Total Cycles ____________ Last Inspection Hours __________________________ TSOH ________________ Cycles SOH ____________ Hourmeter _______________ Total Time __________

TSHSI _______________ Cycles SHSI ____________

Total Cycles _________________________________

LH Prop S/N _________________________________

Researched By _______________________________ LH Prop Total Time ____________ TSOH __________ Inspection Being Conducted _____________ Phase

RH Prop S/N _________________________________

LH Eng. Gas Gen. S/N _________________________ RH Prop Total Time ____________ TSOH __________ LH Eng. Power Module S/N ______________________

A.

NOSE SECTION

ATA/GAMA REFERENCE

MECH

INSP

1. NOSE SECTION - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area. 2. RADOME - Inspect the exterior surface for cracks in the paint and fiberglass substrate. B.

NOSE AVIONICS COMPARTMENT 1. INSTRUMENT AIR FILTER - Inspect for cleanliness. 2. VACUUM REGULATOR VALVE FILTER - Inspect for blockage.

37-00-00

3. AVIONICS EQUIPMENT and RACKS - Inspect for security of attachment. 4. AVIONICS COMPARTMENT - Inspect for corrosion, trapped water and indications of water leakage.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

B. NOSE AVIONICS COMPARTMENT (Continued) 5. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

ATA/GAMA REFERENCE

MECH

INSP

AC43.13-1B/2B

6. DOORS, FASTENERS and SEAL - Inspect seal for deterioration and doors and latches for proper adjustment and fit. 7. NOSE AVIONICS COMPARTMENT - Inspect skin, structure, all components and attaching hardware for general condition and security of attachment. C.

AC43.13-1B/2B

NOSE LANDING GEAR AREA 1. ELECTRICAL WIRING and EQUIPMENT - Inspect all exposed electrical wiring and equipment for chafing, damage and security of attachment. 2. FILTER, FORWARD EVAPORATOR - Inspect forward evaporator filter.

AC43.13-1B/2B

21-50-00

3. NOSE LANDING GEAR AREA - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area. 4. REFRIGERANT LINES, SERVICE VALVES and HIGH PRESSURE RELIEF VALVES - Inspect lines and valves for leakage, damage, attachment and surface corrosion. 5. CONDENSER BLOWER - Inspect fittings for dirt, grease, moisture and security of attachment. D.

21-50-00

NOSE GEAR 1. WHEEL a. Inspect wheel for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

CMM

2. TIRE a. Inspect for wear and deterioration. b. Check for correct inflation. 3. SHIMMY DAMPER - Inspect for leaks, security and attachment.

12-10-00 32-20-00 12-10-00

4. NOSE GEAR DRAG BRACE STOP LUGS - Inspect for cracks, damage or distortion.

Page 202 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

D. NOSE GEAR (Continued)

ATA/GAMA REFERENCE

MECH

INSP

5. NOSE GEAR STEERING STOP - Inspect steering stop for damage or distortion. 6. LANDING and TAXI LIGHTS a. Inspect for broken lenses or bulbs.

33-40-00

b. Confirm correct focus of landing and taxi lights.

33-40-00

7. NOSE GEAR LOWER DRAG LEG - Remove nose gear drag brace bolt and inspect lower drag leg hole for corrosion and wear.

CMM

8. NOSE GEAR ACTUATOR a. Inspect actuator support brackets for damage, cracks and loose or missing fasteners. b. Inspect actuator and plumbing for leakage. 9. ALL COMPONENTS - Inspect all components and attaching hardware for wear, damage and surface corrosion. E.

PILOT'S COMPARTMENT 1. RETURN AIR INLET FILTERS - Inspect filters in return air inlet of the forward vent blower.

21-50-00

2. WINDSHIELDS

F.

a. Inspect windshields for cracks, visibility impairment.

56-10-00

b. Inspect windshield weather seal for debonding, cracks or wear.

56-10-00

3. WINDOWS - Inspect exterior surface of cockpit side windows for deep scratches, cracks, chips or excess crazing or other damage.

56-15-00

4. ALTERNATE AIR VALVE - Drain off all moisture.

34-00-00

CABIN SECTION 1. WINDOWS - Inspect exterior surfaces of windows for deep scratches, cracks, chips and excessive crazing or other damage.

56-15-00

2. ROTATING (FLASHING) BEACON - Inspect for cracked or broken lenses.

33-40-00

3. ACCESS DOORS - Inspect for fit and attachment.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

F. CABIN SECTION (Continued)

G.

ATA/GAMA REFERENCE

4. EMERGENCY EXIT LIGHT - Inspect emergency exit light for battery leakage and security of lamp.

33-20-00

5. OUTFLOW and SAFETY VALVES - Drain outflow valve control line (two locations).

21-30-00

6. PRESSURIZATION DUCTS - Inspect for security of attachment.

21-20-00

7. FLAPPER VALVE - Inspect for proper operation and excessive air noise.

21-20-00

MECH

INSP

REAR FUSELAGE AND EMPENNAGE 1. REAR FUSELAGE DRAINS - Inspect rear fuselage drains.

53-00-00

2. ELT BATTERY a. Inspect for leakage, corrosion or loose leads.

25-60-00

b. Determine remaining useful life.

25-60-00

3. NAVIGATION LIGHTS and ROTATING (FLASHING) BEACONS - Inspect for broken or cracked lenses.

33-40-00

4. ACCESS DOORS - Inspect for fit and security of attachment. 5. VENTRAL FIN DRAIN HOLES - Inspect the drain holes in the bottom of the ventral fin for obstructions.

53-00-00

6. DEICER BOOTS - Inspect for deterioration, damage and attachment. 7. RUDDER and TRIM TAB DRAIN HOLES - Inspect the drain holes for obstructions.

55-40-00

8. STATIC WICKS a. Inspect for damage and security of attachment.

23-60-00

b. Inspect for proper bonding to the airplane.

23-60-00

9. EMPENNAGE and CONTROL SURFACES a. Check elevator trim tab free play.

27-30-00

b. Check rudder trim tab free play.

27-20-00

10. REAR FUSELAGE and EMPENNAGE - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

Page 204 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

G. REAR FUSELAGE and EMPENNAGE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

11. CABIN PRESSURIZATION OVERBOARD DUMP SYSTEM Inspect louver and screen for obstruction and hoses for security. 12. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

AC43.13-1B/2B

13. AVIONICS and AUTOPILOT EQUIPMENT and RACKS Inspect avionics and autopilot equipment and racks for security, corrosion and signs of water leakage. 14. VERTICAL STABILIZER - Inspect front and rear spars of the vertical stabilizer for loose or missing rivets or fasteners. 15. CONTROL CABLE SEALS - Inspect for deterioration, security, cleanliness and lubrication. 16. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect the control system components (pushrods, turnbuckles, castings, etc.) for bulges, splits or cracks which are conditions for replacement. Inspect rudder torque shaft arm for loose or working fasteners.

27

b. Inspect control cables, pulleys and associated equipment for cracks, wear, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given three-foot cable length or have evidence of corrosion.

27

17. PLUMBING - Inspect plumbing for security of attachment. H.

LEFT SIDE OUTBOARD WING 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

3. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

33-40-00

b. Inspect the strobe light for broken or cracked lenses.

33-40-00

4. FUEL TANKS and VENTS a. Inspect exterior openings of vents for obstructions.

A28

28-10-00

5-21-04

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

H. LEFT SIDE OUTBOARD WING (Continued)

I.

ATA/GAMA REFERENCE

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

5. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

6. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

7. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

8. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

9. STATIC WICKS - Inspect for damage and security of attachment.

23-60-00

MECH

INSP

LEFT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS a. Inspect the exterior of the center section for leaks.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

Inspect the exterior openings of the vents for obstructions.

3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment. J.

57-30-00

LEFT SIDE MAIN LANDING GEAR AREA 1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

CMM

2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

32-40-00

3. BRAKE DEICING (IF INSTALLED) - Inspect manifold for blocked orifices.

32-41-00

4. TIRES - Inspect tires for wear, deterioration and correct inflation.

32-40-00 12-10-00 CMM

Page 206 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

J. LEFT SIDE MAIN LANDING GEAR AREA (Continued) 5. STRUT - Check strut for leaks and proper extension. 6. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

ATA/GAMA REFERENCE

MECH

INSP

12-10-00 AC43.13-1B/2B

7. MAIN GEAR ACTUATOR

K.

a. Inspect actuator support brackets for damage, cracks and loose or missing fasteners.

32-30-00

b. Inspect actuator and plumbing for leakage and attachment.

32-30-00

c.

32-30-00

Inspect actuator bearing support.

LEFT SIDE ENGINE 1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00

2. P3 AIR FILTER - Inspect the filter for cleanliness. Refer to the engine maintenance manual for procedure. 3. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

28-20-00 12-10-00

4. PROPELLERS a. Inspect for damage and attachment (spinner removal required).

61-10-00

b. Inspect the carbon block pin for freedom of movement. c.

Check for no metal-to-metal contact between the brass ring and the reversing lever.

61-10-00

d. Inspect the reversing linkage for correct adjustment, evidence of binding and security of attachment.

76-00-00

e. Inspect mechanical feedback ring, stop rods and springs for damage.

61-10-00

5. HIGH PRESSURE FUEL PUMP FILTERS - Inspect the enginedriven high pressure fuel pump filters as instructed in the appropriate engine maintenance manual. 6. ENGINE OIL FILTER - Inspect for metal particles. Refer to the engine maintenance manual.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

7. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT - If Sunstrand fuel pump is installed, check the exterior of the fuel pump coupling for fretting and corrosion as instructed by the engine maintenance manual.

MECH

INSP

P&W 72-00-00 P&W 73-10-02

8. DRAIN PLUGS - Inspect all drain plugs for leakage, security and safetying.

79-00-00

9. COWLING - Remove entire cowling and inspect skin, structure and attaching hardware for wear, damage and corrosion.

71-10-00

10. OIL COOLER - Inspect oil cooler and plumbing for leakage, damage and attachment.

79-00-00

11. AFT COWLING ACCESS DOOR - Check adjustment of latches.

71-10-00

12. FIRESEALS - Inspect for condition.

71-30-00

13. EXHAUST SYSTEM - Inspect attaching hardware for wear, damage and corrosion. 14. ENGINE and PROPELLER CONTROLS a. Check controls and associated equipment for binding, stiff operation, full travel and friction lock. b. Inspect controls, bolts, nuts, cotter pins and safeties for corrosion, damage and attachment. NOTE Special attention should be made to the cam box. c.

Inspect control cables for damage such as crimps, cuts, abrasions or tight bends. If exterior covering is ruptured, perform leak test.

76-00-00

15. ENGINE CONTROL CABLE BOOTS - Inspect the control cable boots for excessive compression, twist, wear or aging which could cause binding. 16. STARTER-GENERATOR BRUSHES - Inspect one set of brushes for indications of excessive wear or damage (determine wear by observing diagonal groove on brush).

24-30-00

17. COMPRESSOR INLET - Remove the air inlet screen and inspect the compressor inlet area, struts, first stage blades and vanes for dirt deposits, corrosion, erosion, cracks and damage by foreign objects. Refer to the engine maintenance manual for corrective action.

Page 208 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

18. MAGNETIC CHIP DETECTOR a. Check plug.

79-30-00

b. Check light in annunciator panel.

79-30-00

19. ENGINE a. Inspect fuel nozzles per manufacturer's manual. b. Inspect engine in accordance with the instructions in the engine manufacturer's manual (refer to chapter 72). 20. FUEL PURGE SYSTEM

L.

a. Remove fuel purge system air tank and inspect. Clean as required.

71-70-00

b. Remove fuel purge system check valves. Inspect, pressure flush and perform internal leakage test. Replace as required.

71-70-00

c.

71-70-00

Perform Fuel Purge System Flow Divider/Purge Valve Leakage Test.

RIGHT SIDE OUTBOARD WING 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

3. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

33-40-00

b. Inspect the strobe light for broken or cracked lenses.

33-40-00

4. FUEL TANKS and VENTS

A28

a. Inspect exterior openings of vents for obstructions.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

5. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

6. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

5-21-04

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

L. RIGHT SIDE OUTBOARD WING (Continued)

M.

ATA/GAMA REFERENCE

7. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

8. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

9. STATIC WICKS - Inspect for damage and security of attachment.

23-60-00

MECH

INSP

RIGHT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS a. Inspect the exterior of the center section for leaks.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

N.

Inspect the exterior openings of the vents for obstructions.

3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

4. BATTERY - Service battery as required.

12-10-00

RIGHT SIDE MAIN LANDING GEAR AREA 1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

CMM

2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

32-40-00

3. BRAKE DEICING (IF INSTALLED) - Inspect manifold for blocked orifices.

32-41-00

4. TIRES - Inspect tires for wear, deterioration and correct inflation.

32-40-00 12-10-00 CMM

5. STRUT - Check strut for leaks and proper extension.

12-10-00

6. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

Page 210 May 1/10

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AC43.13-1B/2B

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

N. RIGHT SIDE MAIN LANDING GEAR AREA (Continued)

ATA/GAMA REFERENCE

MECH

INSP

7. MAIN GEAR ACTUATOR

O.

a. Inspect actuator support brackets for damage, cracks and loose or missing fasteners.

32-30-00

b. Inspect actuator and plumbing for leakage and attachment.

32-30-00

c.

32-30-00

Inspect actuator bearing support.

RIGHT SIDE ENGINE 1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00

2. P3 AIR FILTER - Inspect the filter for cleanliness. Refer to the engine maintenance manual for procedure. 3. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

28-20-00 12-10-00

4. PROPELLERS a. Inspect for damage and attachment (spinner removal required).

61-10-00

b. Inspect the carbon block pin for freedom of movement. c.

Check for no metal-to-metal contact between the brass ring and the reversing lever.

61-10-00

d. Inspect the reversing linkage for correct adjustment, evidence of binding and security of attachment.

76-00-00

e. Inspect mechanical feedback ring, stop rods and springs for damage.

61-10-00

5. HIGH PRESSURE FUEL PUMP FILTERS - Inspect the enginedriven high pressure fuel pump filters as instructed in the appropriate engine maintenance manual. 6. ENGINE OIL FILTER - Inspect for metal particles. Refer to engine maintenance manual. 7. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT - If Sunstrand fuel pump is installed, check the exterior of the fuel pump coupling for fretting and corrosion as instructed by the engine maintenance manual. 8. DRAIN PLUGS - Inspect all drain plugs for leakage, security and safetying.

A28

P&W 72-00-00 P&W 73-10-02

79-00-00

5-21-04

Page 211 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O. RIGHT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

9. COWLING - Remove entire cowling and inspect skin, structure and attaching hardware for wear, damage and corrosion.

71-10-00

10. OIL COOLER - Inspect oil cooler and plumbing for leakage, damage and attachment.

79-00-00

11. AFT COWLING ACCESS DOOR - Check adjustment of latches.

71-10-00

12. FIRESEALS - Inspect for condition.

71-30-00

MECH

INSP

13. EXHAUST SYSTEM - Inspect attaching hardware for wear, damage and corrosion. 14. ENGINE and PROPELLER CONTROLS a. Check controls and associated equipment for binding, stiff operation, full travel and friction lock. b. Inspect controls, bolts, nuts, cotter pins and safeties for corrosion, damage and attachment. NOTE Special attention should be directed to the cam box. c.

Inspect control cables for damage such as crimps, cuts, abrasions or tight bends. If exterior covering is ruptured, perform leak test.

76-00-00

15. CONTROL CABLE BOOTS - Inspect the control cable boots for excessive compression, twist, wear or aging which could cause binding. 16. STARTER-GENERATOR BRUSHES - Inspect one set of brushes for indications of excessive wear or damage (determine wear by observing diagonal groove on brush).

24-30-00

17. COMPRESSOR INLET - Remove the air inlet screen and inspect the compressor inlet area, struts, first stage blades and vanes for dirt deposits, corrosion, erosion, cracks and damage by foreign objects. Refer to the engine maintenance manual for corrective action. 18. MAGNETIC CHIP DETECTOR a. Check plug.

79-30-00

b. Check light in annunciator panel.

79-30-00

19. ENGINE a. Inspect fuel nozzles per manufacturer's manual.

Page 212 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O. RIGHT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

b. Inspect engine in accordance with instructions in the engine manufacturer's manual (refer to Chapter 72). 20. FUEL PURGE SYSTEM a. Remove fuel purge system air tank and inspect. Clean as required.

71-70-00

b. Remove fuel purge system check valves. Inspect, pressure flush and perform internal leakage test. Replace as required.

71-70-00

c.

71-70-00

Perform Fuel Purge System Flow Divider/Purge Valve Leakage Test.

21. AIR-CONDITIONER COMPRESSOR a. Inspect for security of attachment and oil leaks.

21-50-00

b. Inspect for wear and lubricate the spline on the pulley end of the quill shaft.

21-50-00

c.

Inspect drive belt for deterioration, wear and proper tension.

21-50-00

d. Inspect the integrity and security of the clutch assembly. Remove the belt from the compressor. Inspect for freedom of rotation, bearing roughness and free play (wobble). Check for corrosion or evidence of inappropriate wear (belt dust, metal shavings). Install belt on compressor.

21-50-00

22. REFRIGERANT LINES and SERVICE VALVES - Inspect lines and valves for leakage, damage and attachment.

A28

21-50-00

5-21-04

Page 213 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

P.

LANDING GEAR RETRACTION

ATA/GAMA REFERENCE

MECH

INSP

1. RETRACT MECHANISM NOTE Since battery voltage is not sufficient to properly cycle the landing gear, use only an exterior power source capable of delivering and maintaining 28.25 ±0.25 volts throughout the extension and retraction cycles when performing the landing gear retraction inspection. When cycling the landing gear with the power pack, allow a one minute cooling period between cycles and a five minute cooling period every five cycles. Also, an exterior supply of dry air at 18 to 20 psi must be applied to the fill reservoir to prevent cavitation. If an exterior air supply is not available, use an exterior hydraulic pressure source. a. Check hydraulic power pack and motor for proper operation.

32-30-00

b. Check retraction system for proper operation of all components through at least two complete cycles.

32-30-00

c.

32-30-00

Check for unusual noises and evidence of binding.

2. DOORS and LINKAGE - Check door for operation, fit and rigging.

32-30-00

3. POSITION INDICATORS - Check for proper operation of switches.

32-60-00

4. WARNING HORN - Check operation.

32-60-00

5. DOWNLOCK MECHANISM a. Check locking mechanism for positive engagement in extended position.

32-10-00 32-20-00

b. Check downlock switch for proper adjustment.

32-60-00

6. SAFETY SWITCH - Check for proper operation.

32-60-00

7. ACTUATORS - Check for noise, binding and proper rigging.

32-30-00

8. EMERGENCY EXTENSION - Check system for freedom of operation and positive engagement of downlocks.

32-30-00

CAUTION Do not continue operation after receiving a gear-down indication on all gears.

Page 214 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q.

OPERATIONAL INSPECTION

ATA/GAMA REFERENCE

MECH

INSP

NOTE The following Operational Inspection procedures are to be applied during start and run of the engine. Refer to the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual for the engine start and run procedures. 1. FIREWALL SHUTOFF VALVES - Check for proper operation. 2. CROSSFEED FUEL VALVE - Check for proper operation. 3. STANDBY PUMPS - Check for proper operation. 4. STARTERS - Check operation. 5. IGNITION LIGHT - Check for annunciator panel light illumination. 6. ENGINE OIL TEMPERATURE and PRESSURE - Check for proper pressure and temperature limits. 7. FUEL QUANTITY GAGES - Check operation. 8. INTERSTAGE TURBINE TEMPERATURE - Check for correct limits on engine start. 9. VACUUM SYSTEM - Check for correct limits. 10. PNEUMATIC PRESSURE GAGE - Check for correct pressure. 11. PNEUMATIC SYSTEM SHUTOFF VALVES - Check for proper operation. 12. GYRO INSTRUMENTS - Check for erratic or noisy operation. 13. PROPELLERS - Perform flight idle torque check.

76-00-00

14. AUTOFEATHERING CHECK - Refer to AUTOFEATHER SYSTEM OPERATIONAL CHECK.

61-21-00

15. PROPELLER SYNCHROPHASER - Refer to the SYNCHROPHASER SYSTEM FUNCTIONAL TEST and confirm proper synchronization.

61-22-00

16. PROPELLER GOVERNOR - Check governor operation (including feathering and reversing).

76-00-00

17. IDLE RPM - Check for correct rpm (both high and low rpm).

76-00-00

18. AC INVERTERS (If installed) - Check for proper operation.

24-20-00

19. RUDDER BOOST - Check for proper operation. 20. AUTOIGNITION - Check for proper operation.

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POH 74-00-00

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Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

21. PROPELLER DEICER - Check for proper operation and cycling. Refer to Chapter 30 of the King Air Series Component Maintenance Manual.

MECH

INSP

CMM

22. ENGINE INERTIAL ANTI-ICER - Check for proper operation and rigging. 23. DEICE SYSTEM a. Check for proper operation and cycling. b. Functionally test tail and wing deice annunciator lights for operation. 24. BRAKE DEICE SYSTEM (IF INSTALLED) - Check for proper operation with engines running. 25. ELECTRICAL SYSTEM - Perform functional checks.

24-50-00

26. ENVIRONMENTAL SYSTEM - Check for proper operation in: a. Manual heat mode. b. Manual cool mode. c.

Automatic mode.

27. AUTOPILOT - Check for proper operation as outlined by the applicable Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 28. STALL WARNING - Check for proper operation. 29. GENERATORS - Check the output. 30. ENGINE FIRE DETECTORS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 31. ENGINE FIRE EXTINGUISHERS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 32. PRESSURIZATION SYSTEM - Check for proper operation. NOTE Refer to the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual and perform system test.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

33. AUXILIARY FUEL TRANSFER JET PUMPS - Check for operation. 34. CONDITION LEVERS - Check for clean shutdown at IDLECUT-OFF. 35. PITOT TUBE - Check for proper heating at the unit and for obstructions. 36. LANDING and TAXI LIGHTS - Check operation of all lights.

33-40-00

37. OUTBOARD WING LIGHTS (Right Side and Left Side) - Check operation of all navigation and strobe lights.

33-40-00

38. COCKPIT LIGHTS - Check operation of all cockpit lights.

33-10-00

39. EFIS COOLING BLOWERS (If Installed) - Check operation.

34-20-00

40. ELECTRIC ELEVATOR TRIM - Check for proper operation.

27-30-00

41. ENGINE and PROPELLER CONTROLS - Check for freedom of movement, full travel and friction lock operation.

76-00-00

42. PILOT'S and COPILOT'S SEATS and SEAT BELTS - Check seat adjustment mechanism and shoulder harness inertia reel for operation. 43. STATIC SYSTEM - Inspect alternate air valve for operation.

34-00-00

44. WINDSHIELDS - Perform heated operational check.

30-40-00

45. THRESHOLD LIGHT - Check for proper operation. 46. AUXILIARY ELECTRIC HEAT - Check for proper operation of the Electric Heat System. 47. CABIN and COMPARTMENT LIGHTS - Check for proper operation. 48. CABIN SEATS and SEAT BELTS - Check seat adjustment mechanism and shoulder harness inertia reel for operation. 49. CABIN ENTRANCE DOOR (FL-1 and After) a. Check that folding steps do not fold too soon and that they fold properly without interference. b. Check cabin DOOR UNLOCK annunciator for proper operation. c.

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Inspect cabin door damper for leakage and proper operation.

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Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

50. CABIN CARGO DOOR and CABIN ENTRANCE DOOR (FM- 1 and After) a. Inspect door latching mechanism for operation and security of attachment. b. Check latching mechanism, folding steps and gas springs for proper operation. 51. EMERGENCY EXITS (With door installed and properly rigged) a. Check emergency release handles (inside and outside) and latch mechanism for operation. b. Check that latches open and close freely. 52. EMPENNAGE CONTROL SURFACES a. Check for freedom of movement. b. Check optional trim actuators and motors for smoothness of operation. 53. REAR FUSELAGE and EMPENNAGE LIGHTS - Check operation of all lights.

33-40-00

54. AILERON (Left Side and Right Side) - Check for freedom of movement. 55. AILERON TRIM TAB - Check trim tab actuator for smoothness of operation and attachment. 56. FUEL TANK HEATED VENTS (Left Side and Right Side) Check the operation of the heated vents. They should be warm to the touch.

28-10-00

57. STALL WARNING HEAT - Check for proper operation. 58. FLAPS and ACTUATORS (INBOARD, OUTBOARD, Left Side and Right Side) - Check flaps for noisy or erratic operation.

27-50-00

59. WING CENTER SECTION LIGHTS - Check operation of all lights.

33-40-00

60. ENGINE INDUCTION SYSTEM (Left Side and Right Side) Check the inertial vane and bypass door for movement with the main and standby actuator motors. 61. EXTERNAL POWER RELAY - Check for proper operation.

24-40-00

62. ELECTRIC HEATER POWER RELAYS - Check for proper operation.

21-40-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

R.

POST INSPECTION ITEMS

ATA/GAMA REFERENCE

1. AIRPLANE CLEANED and SERVICED AS REQUIRED.

12-00-00

2. LUBRICATE AS NECESSARY.

12-20-00

MECH

INSP

3. ENGINES INSPECTED AFTER GROUND RUN-UP OR FLIGHT TEST - Check for oil leaks, security and attachment of all components. 4. AIRWORTHINESS DIRECTIVES and SERVICE BULLETINS Must be reviewed and complied with as required. 5. ADDITIONAL INSPECTION REQUIREMENTS - Make sure Chapter 5, Special Inspection, and Airworthiness Limitations Manual (P/N 130-590031-211) requirements are complied with at the appropriate intervals. 6. IN-FLIGHT WORKSHEETS DISCREPANCIES - All discrepancies noted by the pilot must be checked and corrected as required. 7. EMERGENCY LOCATOR TRANSMITTER - Check for proper operation and make sure ELT is ARMED before returning airplane to service.

25-60-00

8. OXYGEN SYSTEM PRESSURE - Check for proper pressure. 9. EMERGENCY and SURVIVAL EQUIPMENT - (If required) Make sure all necessary emergency and survival equipment is installed in the airplane and is serviceable. 10. PLACARDS - Determine that all required placards are in place and legible.

11-20-00 and POH

11. LOGBOOK ENTRY - Make sure that log books are filled out properly.

INSPECTION COMPLETED I certify that Phase 4 Inspection was performed in accordance with the Model B300/B300C Inspection Program and that the airplane is approved for return to service: DATE: ............................................................................................................................................................ MECHANIC: .................................................................................................................................................. CREW CHIEF: ............................................................................................................................................... QUALITY CONTROL INSPECTOR: ..............................................................................................................

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 5-21-05

SCHEDULED INSPECTION PROGRAM (SPECIAL) - MAINTENANCE PRACTICES

Owner _____________________________________

Total Time ____________ Total Cycles ___________

W/O Number _________________________________ TSOH ________________ Cycles SOH ____________ Date In ________________ Date Out ______________ TSHSI _______________ Cycles SHSI ____________ Serial No. _____________ Reg. No. _______________ RH Eng. Gas Gen. S/N _________________________ Last Inspection ____________ Phase _____________ RH Eng. Power Module S/N _____________________ Last Inspection Date ___________________________ Total Time ____________ Total Cycles ____________ Last Inspection Hours __________________________ TSOH ________________ Cycles SOH ____________ Hourmeter _______________ Total Time __________

TSHSI _______________ Cycles SHSI ____________

Total Cycles _________________________________

LH Prop S/N _________________________________

Researched By _______________________________ LH Prop Total Time ____________ TSOH __________ Inspection Being Conducted _____________ Phase

RH Prop S/N _________________________________

LH Eng. Gas Gen. S/N _________________________ RH Prop Total Time ____________ TSOH __________ LH Eng. Power Module S/N ______________________ NOTE: If two inspection intervals are shown (i.e. 2,400 HOURS or 30 MONTHS), this indicates the inspection requirement is due at whichever time occurs first.

SPECIAL INSPECTIONS

INSPECTION INTERVAL

MECH

INSP

1. LEFT SIDE ENGINE a. Perform hot section inspection as required, refer to Pratt and Whitney Service Bulletin No. 13303 or subsequent. b. Oil Filter, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

First 100 HOURS

c.

First 100 HOURS

Chip Detector, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

d. Ignitor Box, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

First 100 HOURS

e. Ignitor Plugs, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

First 100 HOURS

f.

First 100 HOURS

P3 Filter, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

g. External Linkages, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

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P&W S. B. 13303

First 100 HOURS

5-21-05

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SPECIAL INSPECTIONS (Continued)

INSPECTION INTERVAL

2. LEFT SIDE STARTER-GENERATOR - Inspect QAD attachment flange.

ANYTIME S-G IS REMOVED

3. LEFT SIDE (NACELLE) FUEL CELL and PROBE - Inspect for microbiological sludge buildup. If sludge buildup if found, inspect all fuel probes and tanks. Clean as required. If needed, use BIOBOR JF additive described in Chapter 12-10-00. Refer to Chapter 28-10-00.

2,400 HOURS OR 30 MONTHS

MECH

INSP

4. LEFT SIDE MAIN GEAR SHOCK ABSORBER ASSEMBLY Inspect for cracks, wear and interior and exterior corrosion. (Disassembly required.) a. IF OPERATED FROM A PAVED RUNWAY

8,000 CYCLES OR 6 YEARS

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME

8,000 CYCLES OR 3 YEARS

NOTE One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles. 5. LEFT SIDE MAIN GEAR DRAG BRACE ASSEMBLY - Inspect for cracks, wear and interior and exterior corrosion. (Disassembly required.) a. IF OPERATED FROM A PAVED RUNWAY

8,000 CYCLES OR 6 YEARS

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME

8,000 CYCLES OR 3 YEARS

NOTE One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles. 6. LEFT SIDE MAIN GEAR AXLE ASSEMBLY and TORQUE KNEES - Inspect for cracks, wear and interior and exterior corrosion. (Disassembly required.) a. IF OPERATED FROM A PAVED RUNWAY

8,000 CYCLES OR 6 YEARS

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME

8,000 CYCLES OR 3 YEARS

NOTE One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SPECIAL INSPECTIONS (Continued) 7. LEFT SIDE MAIN GEAR ACTUATOR CLEVIS - Inspect clevis hole as instructed in Chapter 32-30-00. 8. LEFT SIDE MAIN LANDING GEAR WHEELS - Inspect main wheels in accordance with manufacturer’s instructions. 9. LEFT SIDE FLAP FLEXIBLE SHAFT - Inspect for wear and freedom of operation with both ends disconnected. Refer to Chapter 27-50-00. 10. LEFT SIDE WING FRONT SPAR CAP - Inspect and check for corrosion. Refer to Structural Inspection and Repair Manual, Chapter 57-00-00.

INSPECTION INTERVAL

MECH

INSP

1,000 CYCLES CMM

5,000 CYCLES 5 YEARS INITIAL/ 1 YEAR RECURRING

11. RIGHT SIDE ENGINE a. Perform hot section inspection as required, refer to Pratt and Whitney Service Bulletin No. 13303 or subsequent.

P&W S.B. 13303

b. Oil Filter, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

First 100 HOURS

c.

First 100 HOURS

Chip Detector, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

d. Ignitor Box, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

First 100 HOURS

e. Ignitor Plugs, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

First 100 HOURS

f.

First 100 HOURS

P3 Filter, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

g. External Linkages, refer to Pratt and Whitney Maintenance Manual P/N 3034342, Section 72-00-00, pages 601-610.

First 100 HOURS

12. RIGHT SIDE STARTER-GENERATOR - Inspect QAD attachment flange any time starter-generator is removed.

ANYTIME S-G IS REMOVED

13. RIGHT SIDE (NACELLE) FUEL CELL and PROBE - Inspect for microbiological sludge buildup. If needed, use BIOBOR JF additive. Refer to Chapter 12-10-00 and Chapter 28-10-00.

2,400 HOURS OR 30 MONTHS

14. RIGHT SIDE MAIN GEAR SHOCK ABSORBER ASSEMBLY Inspect for cracks, wear and interior and exterior corrosion. (Disassembly required.) a. IF OPERATED FROM A PAVED RUNWAY

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8,000 CYCLES OR 6 YEARS

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SPECIAL INSPECTIONS (Continued)

INSPECTION INTERVAL

MECH

INSP

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME NOTE

8,000 CYCLES OR 3 YEARS

One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles. 15. RIGHT SIDE MAIN GEAR DRAG BRACE ASSEMBLY - Inspect for cracks, wear and interior and exterior corrosion. (Disassembly required.) a. IF OPERATED FROM A PAVED RUNWAY

8,000 CYCLES OR 6 YEARS

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME NOTE

8,000 CYCLES OR 3 YEARS

One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles. 16. RIGHT SIDE MAIN GEAR AXLE ASSEMBLY and TORQUE KNEES - Inspect for cracks, wear and interior and exterior corrosion. (Disassembly required.) a. IF OPERATED FROM A PAVED RUNWAY

8,000 CYCLES OR 6 YEARS

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME NOTE

8,000 CYCLES OR 3 YEARS

One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles. 17. RIGHT SIDE MAIN GEAR ACTUATOR CLEVIS - Inspect clevis hole as instructed in Chapter 32-30-00.

1,000 CYCLES

18. RIGHT SIDE MAIN LANDING GEAR WHEELS - Inspect main wheels in accordance with manufacturer’s instructions.

CMM

19. RIGHT SIDE FLAP FLEXIBLE SHAFT - Inspect for wear and freedom of operation with both ends disconnected. Refer to Chapter 27-50-00.

5,000 CYCLES

20. RIGHT SIDE WING FRONT SPAR CAP - Inspect and check for corrosion. Refer to the Structural Inspection and Repair Manual, Chapter 57-00-00.

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5 YEARS INITIAL/ 1 YEAR RECURRING

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SPECIAL INSPECTIONS (Continued) 21. FUSELAGE STRINGER INSPECTION (FL-1 thru FL-103; FM-1 thru FM-8) - Inspect the non reworked and reworked stringers per the Priority Area Inspection Guide for Fuselage Stringers 5 through 11 (Ref. Chapter 53-10-00)

INSPECTION INTERVAL

INSP

AS REQUIRED IN CHAPTER 53-10-00

22. FUSELAGE STRINGER INSPECTION (FL-104 thru FL-110; FM-1 thru FM-8) - Inspect for cracks above and below the stringer cutouts in the bend radius of the rear pressure bulkhead flange (Ref.Chapter 53-10-00).

10,000 CYCLES INITIAL/ 2,500 CYCLES RECURRING

23. UPPER and LOWER WINDSHIELD CORNERS - Inspect doublers and clips of the fuselage at the upper and lower windshield corners for cracks and loose rivets. Refer to Chapter 53-00-00 and Airworthiness Limitations Manual (P/N 130-590031-211).

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

24. EDGELIGHTED PANEL ASSEMBLIES (FL-1 thru FL-380, FL-382; FM-1 thru FM-11) - Inspect for condition. Refer to Chapter 33-10-00.

MECH

2,000 HOURS OR 4 YEARS

25. AIR-CONDITIONER COMPRESSOR DRIVE BELTS - Check for proper tension. Refer to Chapter 21-50-00 or Chapter 21-51-00.

50 HOURS AFTER INSTALLATION

26. CABIN DOOR and FUSELAGE FRAME - Inspect structure at all four corners of the door frame and the upper latch hook catches. Refer to Chapter 53-10-00.

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

27. NOSE GEAR SHOCK ABSORBER ASSEMBLY - Inspect for cracks, wear and interior and exterior corrosion. (Disassembly required.) a. IF OPERATED FROM A PAVED RUNWAY

8,000 CYCLES OR 6 YEARS

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME NOTE

8,000 CYCLES OR 3 YEARS

One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles. 28. NOSE GEAR DRAG BRACE ASSEMBLY - Inspect for cracks, wear and interior and exterior corrosion. (Disassembly required.) a. IF OPERATED FROM A PAVED RUNWAY

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8,000 CYCLES OR 6 YEARS

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SPECIAL INSPECTIONS (Continued)

INSPECTION INTERVAL

MECH

INSP

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME NOTE

8,000 CYCLES OR 3 YEARS

One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles. 29. NOSE GEAR AXLE ASSEMBLY and TORQUE KNEES - Inspect for cracks, wear and interior and exterior corrosion. (Disassembly required.) a. IF OPERATED FROM A PAVED RUNWAY

8,000 CYCLES OR 6 YEARS

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME NOTE

8,000 CYCLES OR 3 YEARS

One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles. 30. NOSE GEAR ACTUATOR CLEVIS - Inspect clevis hole as instructed in Chapter 32-30-00. 31. NOSE LANDING GEAR WHEEL - Inspect nose wheel in accordance with manufacturer’s instructions. 32. ALTIMETER and PITOT AND STATIC SYSTEM - As required by FAR 91.411. Refer to Chapter 34-00-00 for system check and leak test.

1,000 CYCLES CMM

24 MONTHS

33. COMMUNICATIONS and NAVIGATION - Inspect and calibrate per FAA regulations. Refer to Chapter 34-00-00.

AS REQUIRED

34. POWER LEVER STOP PIN PEDESTAL - Inspect for wear. Maximum allowable wear is 1/3 of pin diameter. Refer to Chapter 76-00-00.

1,200 HOURS

35. PILOT’S COMPARTMENT FIRE EXTINGUISHER (PORTABLE) Hydrostatically test extinguisher. Refer to Chapter 26-21-00.

12 YEARS

36. CABIN FIRE EXTINGUISHER (PORTABLE) - Hydrostatically test extinguisher. Refer to Chapter 26-21-00.

12 YEARS

37. OXYGEN CYLINDER (LIGHTWEIGHT) DOT 3HT 1850 Hydrostatically test to DOT Regulation. Overhaul regulator when oxygen bottle is hydrostatically tested. Refer to Chapter 35-00-00.

3 YEARS

38. ENGINE FIRE EXTINGUISHER - Hydrostatically test engine fire extinguisher bottle in accordance with Title 49 CFR Chapter 1, Section 173.34 or replace with a new bottle. (DOT Regulation.) Refer to Chapter 26-20-00.

5 YEARS

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SPECIAL INSPECTIONS (Continued)

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INSPECTION INTERVAL

39. CARGO DOOR LOWER ATTACHMENT LUG (FM-1 and After) After each heavy equipment loading and unloading, inspect for cracks, breakage, proper alignment and security of attachment. Refer to Chapter 52-11-00.

AS REQUIRED

40. WING ATTACHMENT BOLTS - Inspect the eight bolts as outlined in the Beech Structural Inspection and Repair Manual. Refer to Chapter 57-00-00.

5 YEARS

41. LANDING GEAR HYDRAULIC RESERVOIR FILL SCREEN - At first 200 hours and every 1,200 hours thereafter or anytime the system is contaminated. Refer to Chapter 32-30-00.

200 HOURS INITIAL/ 1,200 HOURS RECURRING

42. FIRE EXTINGUISHER CARTRIDGE - Total cartridge life is 6 years, which includes any combination of storage and installed service. Service life is not to exceed 4 years.

6 YEARS TOTAL LIFE/ 4 YEARS TOTAL SERVICE

43. WINDSHIELD SCREWS - Check windshield screws for 20 inchpounds of torque.

200 HOURS INITIAL/ 800 HOURS RECURRING

44. AIRSTAIR DOOR, CARGO DOOR and ESCAPE HATCHES Inspect these areas and the associated closure areas for cracks (including all upper latches and hinges for B300 and camlock latch mechanisms and hinges for B300C).

5,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

45. BULKHEAD FORWARD PRESSURE - Inspect the rivet pattern for indications of sheared or loose rivets on each side of the forward pressure bulkhead (FS 84). Check for cracks in the skin or supporting structure emanating from the attaching rivets. Inspect the bulkhead web and stiffener flanges for cracks or other structural damage.

2,500 CYCLES

46. EXTERIOR SKIN - Inspect exterior skin (including nose wheel well keels) for cracks and loose and missing fasteners. If any repetitive damage is found, inspection of the internal structure for degradation in the local area is required.

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

47. FUSELAGE FRAME FS 143 THROUGH FS 382 - Inspect the fuselage frames in the underfloor area for cracks in the flanges, web, stringer cutouts, bend radii, doublers, clips and angles.

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

MECH

5-21-05

INSP

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SPECIAL INSPECTIONS (Continued) 48. FRAME WEB FS 179 THROUGH FS 271 - Inspect the frame webs for cracks from the lightning holes and stringer cutouts. The frames should be inspected from the lower centerline to stringer #4. Examine the crossties closely at stringer #7 position. 49. STRINGERS FROM FS 88 THROUGH FS 125 and INSTRUMENT PANEL SUPPORT BRACKETS - Inspect stringers 7, 8, 9 and 10 in area of FS 88 through FS 125 and the instrument panel support brackets for cracks.

INSPECTION INTERVAL

10,000 CYCLES 10,000 CYCLES INITIAL/ 5,000 CYCLES RECURRING

51. AFT FUSELAGE AREA and AFT PRESSURE BULKHEAD Inspect the entire aft side of the rear pressure bulkhead for cracks and loose or missing rivets. Check the oxygen bottle mounting brackets for cracks and loose or missing rivets. Check the outflow and safety valve box for cracks and loose or missing rivets.

10,000 CYCLES INITIAL/ 500 CYCLES RECURRING

52. WING CENTER SECTION UPPER SURFACE BONDED PANEL SKIN - Inspect bonded panel. Refer to Chapter 51-00-00.

600 HOURS INITIAL/ 18 MONTHS RECURRING

53. BATTERY, EMERGENCY CAPACITY TEST (FL-215 and After; FM-10 and After) - Perform initial test at 12 months or 600 hours which ever comes first and subsequent test at 12 months or 200 hours which ever comes first. Replace Battery which does not pass capacity test.

12 MONTHS OR 600 HOURS INITIAL/ 12 MONTHS OR 200 HOURS RECURRING

54. LEAD ACID BATTERY (FL-215 and After; FM-10 and After) - A Battery stored in an airplane must be boost charged every 90 days.

90 DAYS

55. STANDBY POWER SUPPLY BATTERY (JET MODEL - PS835) Check, load test, and recharge if necessary (Ref. Chapter 24, King Air Series Component Maintenance Manual).

6 MONTHS

56. CABIN ALTITUDE WARNING SYSTEM - Perform the CABIN ALTITUDE WARNING PRESSURE SWITCH CHECK procedure. Refer to Chapter 21-30-00.

12 MONTHS

57. OXYGEN SYSTEM - Perform the BAROMETRIC PRESSURE SWITCH CHECK procedure. Refer to Chapter 35-00-00.

12 MONTHS

5-21-05

INSP

10,000 CYCLES INITIAL/ 1,000 CYCLES RECURRING

50. FLIGHT CONTROLS - Inspect all flight control pulley brackets and castings for cracks, corrosion, wear and attachment.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SPECIAL INSPECTIONS (Continued)

INSPECTION INTERVAL

58. FUSELAGE INSPECTION PRIORITY AREAS (FL-1 thru FL-103; FM-1 thru FM-8) - Inspect for cracks on non-reworked stringers 5 thru 11 (both Left Side and Right Side) on the aft side of the rear pressure bulkhead at the point where the zee stiffeners are attached to the stringers with 6 rivets. Refer to Fuselage Inspection in Chapter 53-10-00.

2,500 CYCLES INITIAL/ 500 CYCLES RECURRING

59. FUSELAGE INSPECTION PRIORITY AREAS (FL-1 thru FL-103; FM-1 thru FM-8) - Inspect for cracks on non-reworked stringers on the aft side of the rear pressure bulkhead if stringers 8, 9, and 10 (both Left Side and Right Side) have internal reinforcement kits installed. Refer to Fuselage Inspection in Chapter 53-10-00.

2,500 CYCLES INITIAL/ 1,000 CYCLES RECURRING

60. FUSELAGE INSPECTION PRIORITY AREAS (FL-1 thru FL-103; FM-1 thru FM-8, with External Doublers) - Inspect for cracks above and below the stringer cutouts in the bend radius of the rear pressure bulkhead flange. Refer to Fuselage Inspection in Chapter 53-10-00.

2,500 CYCLES INITIAL/ 2,500 CYCLES RECURRING

61. FUSELAGE INSPECTION PRIORITY AREAS (FL-1 thru FL-103; FM-1 thru FM-8, with Internal Doublers) - Inspect for cracks above and below the stringer cutouts in the bend radius of the rear pressure bulkhead flange. Refer to Fuselage Inspection in Chapter 53-10-00.

2,500 CYCLES INITIAL/ 2,500 CYCLES RECURRING

62. FUSELAGE INSPECTION PRIORITY AREAS (FL-104 thru FL-110) - Inspect for cracks above and below the stringer cutouts in the bend radius of the rear pressure bulkhead flange. Refer to Fuselage Inspection in Chapter 53-10-00.

MECH

INSP

10,000 CYCLES INITIAL/ 2,500 CYCLES RECURRING

63. AIR DATA SYSTEM (FOR RVSM COMPLIANT AIRPLANES) (FL-352 thru FL-380, FL-382; FM-11; and Airplanes that have complied with Service Bulletin No. 34-3507, if Equipped with Collins EFIS-85B(14)) - Perform the AIRWORTHINESS INSPECTION REQUIREMENTS. Refer to Chapter 34-10-00.

24 MONTHS

64. PILOT’S SIDE FUEL CONTROL PANEL, CIRCUIT BREAKER PANEL and LOWER EDGELIGHTED PANEL, COPILOT’S SIDE EDGELIGHTED CIRCUIT BREAKER PANEL- Inspect for burned out bulbs, delamination, corrosion, and evidence of moisture ingress. (Panel removal to inspect aft side is required.)

12 MONTHS

65. NOSE AND MAIN LANDING GEAR TRUNNION BOLT HOLES AND DRAG BRACE ATTACH HOLES - Inspect for cracks, corrosion, damage, and elongation of holes. a. IF OPERATED FROM A PAVED RUNWAY

A28

8,000 CYCLES OR 6 YEARS

5-21-05

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SPECIAL INSPECTIONS (Continued)

INSPECTION INTERVAL

MECH

INSP

b. IF OPERATED ON OR FROM UNPAVED (GRASS / GRAVEL) RUNWAYS 20% OR MORE OF THE TIME NOTE

8,000 CYCLES OR 3 YEARS

One unpaved runway landing (URL) = Three paved runway landings (PRL) EXAMPLE: 1,000 URL plus 5,000 PRL equals 8,000 cycles.

INSPECTION COMPLETED I certify that the Special Inspection was performed in accordance with the Model B300/B300C Inspection Program and that the airplane is approved for return to service: DATE: _____________________________________________________________________________________ MECHANIC: ________________________________________________________________________________ CREW CHIEF: ______________________________________________________________________________ QUALITY CONTROL INSPECTOR: ______________________________________________________________

Page 210 May 1/10

5-21-05

A28

Ral~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BIENNIAL SCHEDULED INSPECTION PROGRAM

DESCRIPTION

BIENNIAL INSPECTION PROGRAM

inspection is Chapter 5-00-00.

NOTE: This

an

optional

program for aircraft

operating

200 hours

or

less in

a

24-Month

period.

Referto

inspections may be required by engine or propeller manufactures in their manuals. Refer to the unscheduled maintenance checks portion of the supplier issued manuals to ensure continued airworthiness.

Additional

owner/operator is ultimately responsible for maintaining the airplane in an airworthy condition, including compliance with all applicable Airworthiness Directives as specified in Part 39 of Title 14 of the Code of Federal Regulations (14 CFR). The owner/operator should select only qualified personnel to maintain the airplane, and ensure that the airframe and power plant mechanic inspecting the airplane has access to all necessary manuals and service information as well as to an approved inspection guide. Airframe and power plant mechanics must have had previous experience in the satisfactory performance of the tasks required by this inspection before being qualified to supervise, approve, and return to service the airplane or any part thereof in need of maintenance, preventive maintenance, repair or alteration. It is further the responsibility of the owner/operator to ensure that the airplane is inspected in conformity with the requirements covered in 14 CFR Part 91.409 (f) (3) of the Federal Aviation Regulations. This 14 CFR Part covers the requirements concerning approved airplane inspection programs. Raytheon Aircraft Company has prepared the Inspection Program to assist the owner/operator in meeting the foregoing responsibilities. It is the responsibility of the owner/operator to obtain specific approval from their local airworthiness authority for any alteration to the inspection program.

The

NOTE: When warranted

by

service

experience

or

engineering recommendations, changed at any

maintenance program, including the inspection intervals, may be approval of the local airworthiness authority. This document is

a

portion

of the

publications by

which

Raytheon

Aircraft

an

approved

time with the

Company provides

the

inspection

and maintenance schedules for the continued airworthiness of the airframe of your airplane. Remember, maintenance requirements for some suppliers components (such as engines, propellers, avionics and other equipment) are separately provided by their respective manuals. Those maintenance requirements and

requirements

adopted by reference in the airframe maintenance instructions for continued aimorthiness. Have your personnel review the equipment installed on your airplane to ensure that current, up-to-date supplier maintenance publications and manuals are available and that all required maintenance is scheduled and performed as required under 14 CFR 91.403(c).

schedules

are

maintenance

This

Inspection Program

is

provided

to enable the

owner/operator

to

inspect

and maintain the

airplane

on an

basis. Included in the program is a sequence for conducting the program along with suggested times. The times and sequence are recommendations that may be altered to suit a particular operation. While this program may be used as an outline, detailed information of the systems and components in the airplane will be found in the various

ongoing

pertinent supplier publications. It is also recommended that applicable maintenance handbooks, service instructions, applicable FAA regulations and publications and supplier’s specifications for torque values, clearances, settings, tolerances and other requirements.

chapters/sections

of the maintenance manual and the

reference be made to the

This program is not intended to be all-inclusive, for no such program airframe and power plant mechanic in the performance of his duties.

can

replace the good judgement of

a

certified

inspections prescribed by this schedule, the altimeter instrument and static system and all transponders MUST be tested and inspected in compliance with the requirements specified in 14 CFR 91.411 and 91.413 at 24-month intervals or anytime the system is opened.

NOTE: In addition to the ATC

A20

5-22-00

Apr 28/06Page

1

I

RalfheMI

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Information contained herein is differences

are

indicated

by

applicable

Super King effectivity.

to all

serial number

Air B300/B300C Series

airplanes except where

SPECIAL CONDITIONS CAUTIONARY NOTICE periods for the inspections noted in this schedule are based on normal usage under average environmental Airplanes operated for Air Taxi or other than normal operations and airplanes operated in humid tropics, or in cold damp climates, etc., may need more frequent inspections for wear, corrosion, lubrication and/or lack of maintenance. Under these adverse conditions, perform periodic inspections in compliance with this guide at more frequent intervals until the owner/operator can set his own inspection periods based on the contingencies of field experience.

The time

conditions.

CAUTION: The time

periods in this schedule do

malfunction

as

not constitute

a

guarantee the item will reach the period without

the aforementioned factors cannot be controlled by the manufacturer.

only genuine Raytheon Aircraft Company, or Raytheon Aircraft Company-approved parts from Raytheon Aircraft Company-approved sources in connection with the maintenance and repair of Raytheon Aircraft Company airplanes to assure that the airplane is returned to service in a condition at least equal to its original or properly altered condition. Genuine Raytheon Aircraft Company parts are produced and inspected under rigorous procedures to ensure airworthiness and suitability for use in Raytheon Aircraft Company airplane applications. Parts purchased from sources other than Raytheon Aircraft Company, even though outwardly identical in appearance, may not have had the required tests and inspections performed, may be different in fabrication techniques and materials, and may be dangerous when installed in an airplane. Salvaged airplane parts, reworked parts obtained from non-Raytheon Aircraft Company-approved sources, or parts, components, or structural assemblies, the service history of which is unknown or cannot be authenticated, may have been subjected to unacceptable stresses or temperatures or have other hidden damage not discernible through routine visual or usual nondestructive testing techniques. This may render the part, component, or structural assembly, even though originally manufactured by Raytheon Aircraft Company, unsuitable and unsafe for airplane use. Raytheon Aircraft Company expressly disclaims any responsibility for malfunctions, failures, damage or injury caused by use of non-Raytheon Aircraft Company-approved parts or procedures.

WARNING: Use

obtained

SCHEDULED INSPECTION GENERAL INFORMATION INSPECTION INTERVAL TOLERANCES To facilitate

scheduling inspections, Raytheon

Aircraft

Company

authorizes the

following inspection

interval

tolerances:

BIENNIAL INSPECTION A tolerance of

12

days

(CALENDAR-MONTH INTERVAL) per 12 calendar months is allowed, not to exceed

a

total of 60 calendar

days.

EXAMPLE: AN INTERIM INSPECTION, due on Jan 1, 1998, may be accomplished anytime between Dec 20, 1997 and Jan 13, 1998. A COMPLETE INSPECTION, due on Jan 1, 1998, may be accomplished anytime between Dec

8, 1997 and Jan 25, 1998. SPECIAL INSPECTION ITEMS A tolerance of

Apr

28/06Page2

12

days

CALENDAR DATE LIMITED

per 12 calendar months is allowed, not to exceed

5-22-00

a

total of 60 calendar

days.

nno

Raltheon

AiKraft Company

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

SPECIAL INSPECTION ITEMS A tolerance of

FLIGHT CYCLE LIMITED

10% is allowed.

SPECIAL INSPECTION ITEMS A tolerance of

HOURLY LIMITED

10% is allowed.

NOTE: Tolerances specified by suppliers, DOT regulations over

inspection

intervals and tolerances authorized

or

FAA

regulations

take

precedence

by Raytheon Aircraft Company.

INSPECTION COMPLIANCE OPTION

permissible to complete sections of a given inspection at the end of each flight day. Moreover, all line items of a given inspection would be deemed complete on the last day of the inspection due date, regardless of the day within the inspection period wherein they were performed. It is

PURPOSE AND USE

Raytheon Aircraft Company’s recommended 8300/8300C Inspection Program is provided to maintain the Super King Air 8300/8300C Series airplanes that are utilized by owners/operators on a continuous basis. The complete program must be accomplished at least one time every 24 calendar months.

The

NOTE:

Owners/operators wishing to utilize inspection intervals of less than 200 hours may do so obtaining Raytheon Aircraft Company’s concurrence. Refer to the latest revision of this form for inspection procedure details to meet 14 CFR 91.409 (f) (3). without

Inspection timetables Perform

an

are as

follows:

INTERIM INSPECTION at 12 months. Thereafter,

perform

an

INTERIM INSPECTION

no

later than

12 months from the last COMPLETE INSPECTION.

Perform

a

COMPLETE INSPECTION at 24 months. Thereafter,

perform

a

COMPLETE INSPECTION

no

later

than 24 months from the last COMPLETE INSPECTION.

NOTE:

Raytheon

Aircraft

Company

recommends that

no

aircraft exceed 12 months without

completing

at least

one

inspection.

Special Inspections: Although this inspection program is based on 24-month intervals, there are items which require more, or less, frequent inspection or whose inspection interval is based on flight time, elapsed calendar time, or cycles. These unique inspection items and their time intervals are described under SPECIAL INSPECTIONS in Chapter 5-21-05, and should be reviewed prior to commencing any scheduled inspection. Raytheon Aircraft Company’s Recommended Inspection Program in accordance with 14 CFR (f) (3) consists of, but is not limited to, inspection items listed in this Inspection Guide, any applicable Airworthiness Directives issued against the airframe or any equipment installed therein and conformity to Type Certificate Data Sheet as applicable. 91.409

WARNING: Ensure that all

placards

touched up after

nzo

are

in

place

repairs. Replace

any

legible whenever the airplane has been painted placards that have been defaced or removed.

and

5-22-00

or

3

Ral~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

guide may be used as an outline, detailed information of the many systems and components in the will be found in the various sections/chapters of this Maintenance Manual and the Engine Maintenance

While this

airplane

Manual. Reference to the

Engine

Maintenance Manual is to the Pratt 6

Whitney Canada PT6A-41/-42

Maintenance

Manual. It is also recommended that reference be made to the

Aircraft

Raytheon

Company

service bulletins,

applicable

FAA

applicable supplier maintenance handbooks, Regulations, and supplier bulletins and specifications

for torque values, clearances, settings, tolerances and other operator to ensure that the airframe and power plant mechanic noted documents as well as to this inspection guide. Aircraft

Raytheon

Company issues

requirements. It is the responsibility inspecting the airplane has access to

service information for the benefit of

of the owner/ the

previously

and fixed-base operators in the form

owners

of two classes of service bulletins. The first class, MANDATORY Service Bulletins (red border) are changes, inspections and modifications that could affect safety or crashworthiness. Raytheon Aircraft Company considers

compliance with these service bulletins to be mandatory. Raytheon Aircraft Company also issues a service bulletin having no border designated as either RECOMMENDED or OPTIONAL in the compliance section within the bulletin. In the case of a RECOMMENDED Service Bulletin, Raytheon Aircraft Company feels the changes, modifications, improvements or inspections will benefit the owner/operator, and although highly recommended, they are not considered mandatory at the time of issuance. In the case of OPTIONAL Service Bulletins, the changes, modifications, improvements or inspections compliance is at the owner/operator’s discretion. In the final

it is the responsibility of the owner/operatorto ensure that pertinent to his particular operation are complied with.

analysis

bulletins which

are

all

Raytheon Aircraft Company service

DEFINITIONS

The

terminology pertaining

inspection procedures

Pilot in command shall

Pilot in Command

the time defined

during

to the

as

flight

mean

the

and their

use

is defined

pilot responsible for

the

as

follows:

operation

and

safety

of the

airplane

time.

Flight Cycle A flight cycle is defined as: Engine start-up and increase to full or partial flight), one landing gear retraction and extension and a complete shutdown.

power

las required during

a

normal

Flight

Flight time shall mean the total time from the moment the airplane first moves under its own power for flight until the moment it comes to rest at the next point of landing. ("Block-to-block" time).

Time

the purpose of

Time in Service the moment the

Time in Service, as used in computing maintenance and inspection time records, is the time from leaves the ground until it touches the ground at the end of the flight.

airplane

simple or minor preservative operations and the replacement involving complex assembly operations.

Preventive Maintenance

parts

not

Maintenance

preventive

Means

inspection, overhaul, repair, preservations

surface breakdown of

Fitting

moisture

other agents.

or

Material

Damaged

Apr 28/06Page

new

4

replacement

of parts, but excludes

or

or a

part consumed

as a

a

material due to chemical

result of exposure to

operation

or

or

electro-chemical attack

by atmosphere,

usage.

Rendered unusable for its intended purpose.

Calendar Time each

and the

of small standard

maintenance.

Corrosion

Wear

Means

The time from the date

airplane,

to be used

as

on

the "ORIGINAL AIRWORTHINESS CERTIFICATE", which is issued with or of replacement components.

the basis for all TBO

5-22-00

A20

Ral~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Special Inspection of components the scheduled inspection.

or

Unscheduled Maintenance Checks which could

require

systems based

Inspections

on

calendar time, hours

or

cycles

which do not coincide with

and checks for

unscheduled maintenance, i.e.

damage after operating the airplane in conditions lightning strikes. hard landing, polluted atmospheric conditions,

etc.

DISCREPANCIES

Discrepancies

that affect the airworthiness of the

airplane

accomplished

before the

Discrepancies

that do not affect the airworthiness of the

carried

over

to the next

airplane

will

require

the necessary corrective action to be

is retumed to service.

inspection period.

All

airplane may, discrepancies thus carried

at the discretion of the over

owner/operator, be ship file until

should be retained in the

corrected.

Discrepancies another

which

responsible

occur

"ln-Flight Sheet," are provided at the inspection. Forms for the

p~O

during flight

should be entered

on

the

"In-Flight

Work Sheet"

by

the

pilot

in command

or

person. Work Sheet", "Scheduled Inspection Work Sheet", and "Overhaul and Replacement Work the end of subchapter 5-00-00. These forms may be copied for use during each phase of

5-22-00Page

5

Ray~heon

AiKraft Company

SUPER KING AIR B300/B300C MA)NTENANCE MANUAL

BIENNIAL SCHEDULED INSPECTION

PROGRAIVI(INTERIIW) MAINTENANCE PRACTICES

Total

Cycles

Owner

Total Time

W/O Number

TSOH

Cycles SOH

TSHSI

Cycles SHS1

Date Out

Date In

Reg.

SerialNo.

RH Eng. Gas Gen. S/N

No.

PH Eng. Power Module SIN

Phase

Last

Inspection

Last

Inspection

Date

Total Time

Last

Inspection

Hours

TSOH

Total

Phase

Inspection Being Conducted

LH

Eng.

A.

Cycles SOH Cycles SHSI

TSOH

LH Prop Total Time

Researched By

Eng. Gas

Cycles

LH Prop S/N

Cycles

LH

_

TSHSI

Total Time

Hourreter

Total

Gen. S/N

S/N

RH

Prop

RH

Prop TotalTime ~TSOH

Power Module S/N

ATAIGAMA REFERENCE

OPERATIONAL INSPECTION

MECH

INSP

NOTE

following Operational Inspection procedures are to be applied during Air B300 and B300C start and run of the engine. Refer to the Super King Flight Manual FAA and Airplane Handbook Approved Pilot’s Operating and run procedures. for the engine start

The

1.

FIREWALL SHUTOFF VA~VES

2.

CROSSFEED FUEL VALVE

3.

STANDBY PUMPS

4.

STARTER

5.

IGNITION

Check for proper

Check for proper

Check for proper

Check for proper

operation.

operation.

operation.

operation.

operation.

a.

Check forproper

b.

Check for annunciator

panel tight illumination.

5-22-01

Apr 28/06Page

1

Ral~heMI

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A. OPERATIONAL INSPECTION

ATAIGAMA

(Continued)

REFERENCE 6.

ENGINE OIL TEMPERATURE and PRESSURE

MECH

INSP

Check for

proper pressure and temperature limits. 7. 8.

FUEL QUANTITY GAGES

operation.

INTERSTAGE TURBINE TEMPERATURE limits

9.

Check

on

engine

Check for correct

start.

VACUUM SYSTEM INSTRUMENT

Check for correct limits.

Check for correct pressure.

10. PNEUMATIC PRESSURE GAGE

11. PNEUMATIC SYSTEM SHUTOFF VALVES

Check for proper

operation. 12. GYRO INSTRUMENTS 13. PROPELLERS

Check for erratic

Perform

flight

or

noisy operation.

idle torque check.

14. AUTOFEATHERING CHECK

76-00-00

Refer to AUTOFEATHER

OPERATIONAL CHECK. Refer to the

15. PROPELLER SYNCHROPHASER

SYNCH ROPHAS ER SYSTEM FU N CTIO NAL TEST and confirm

proper

61-21-00

61 -22-00

synchronization.

16. PROPELLER GOVERNOR

(including feathering 17. IDLE RPM

and

Check governor

Check for correct rpm

18. AC INVERTERS

(both high

and low

Check for proper

(If installed)

19. RUDDER BOOST

operation

reversing).

Check for proper

rpm).

operation.

76-00-00

24-20-00

POH

operation.

20. AUTOIGNITION

74-00-00

properoperation.

a.

Checkfor

b.

Check for annunciator

21. PROPELLER DEICER

Refer to

76-00-00

Chapter

panel light illumination.

Check for proper operation and cycling. King Air Series Component

30-60-00 of the

CMM

Maintenance Manual. 22. ENGINE INERTIAL ANTI-ICER

Check for proper operation and

rigging. 23. DEICE SYSTEM

Apr

a.

Check for proper

b.

Functionally operation.

operation and cycling.

test tail and

28/065-22-01

wing

deice annunciator

lights for

A20

Raytheon

nireraft Company

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

A. OPERATIONAL INSPECTION

ATA/GAMA

(Continued)

REFERENCE 24. BRAKE DEICE SYSTEM

operation

with

(IF INSTALLED) engines running.

25. ELECTRICAL SYSTEM

a.

Manual heatmode.

b.

Manual cool mode.

c.

Automatic mode.

INSP

Check for proper

Perform functional checks.

26. ENVIRONMENTAL SYSTEM

MECH

Check for proper

24-20-00

operation

in:

Check for proper operation as outlined in the Super King Air 8300 and 8300C Pilot’s Operating

27. AUTOPILOT

applicable

Handbook and FAA

Approved Airplane Flight

Manual

Supplement. 23. STALL WARNING 29. GENERATORS

Check for proper

operation.

Check for output.

30. ENGINE FIRE DETECTORS

instructions found in the

Operating

Perform system test according to Super King Air 8300 and 8300C Pilot’s

Handbook and FAA Approved

31. ENGINE FIRE EXTINGUISHERS

according

Flight

Perform system test

to instructions found in the

8300C Pilot’s

Operating

Airplane Flight Manual.

Super King Air 8300 and Approved Airplane

Handbook and FAA

Manual.

32. PRESSURIZATION SYSTEM

Check for proper

operation.

NOTE

Super King Air 8300 and 8300C Pilot’s Operating Handbook Approved Airplane Flight Manual and perform system test.

Refer to the and FAA

33. AUXILIARY FUEL TRANSFER JET PUMPS

Check for proper

operation. 34. CONDITION LEVERS

Check for clean shutdown at IDLE-CUT-

OFF. 35. PITOT TUBE

Check for proper

heating

at the unit and for

obstructions. 36. LANDING and TAXI LIGHTS 37. OUTBOARD WING LIGHTS

operation

of all

navigation

Check operation of all

(RIGHT

and strobe

LEFT) lights.

and

lights.

Check

33-40-00

33-40-00

5-22-01

3

Ray~Reon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A. OPERATIONAL INSPECTION

ATAIGAMA

(Continued)

REFERENCE 38. COCKPIT LIGHTS

Check

operation of

39. EFIS COOLING BLOWERS

all

cockpit lights.

(IF INSTALLED)

40. ELECTRIC ELEVATOR TRIM

33-10-00

operation.

Check for freedom of

movement, full travel and friction lock operation. 42. PILOT’S and COPILOT’S SEATS and SEAT BELTS

adjustment operation.

seat

INSP

Check operation.

Check for proper

41. ENGINE and PROPELLER CONTROLS

MECH

27-30-00

76-00-00

Check

mechanism and shoulder harness inertia reel for

43. STATIC SYSTEM 44. WINDSHIELDS

Inspect

alternate air valve for

Perform heated

45. THRESHOLD LIGHT

Check for proper

46. AUXILIARY ELECTRIC HEAT

the Electric Heat

operational

operation.

check.

34-00-00 30-40-00

operation.

Check for proper

operation of

System.

47. CABIN and COMPARTMENT LIGHTS

Check for proper

operation. 48. CABIN SEATS and SEATBELTS

Check seat

adjustment operation.

mechanism and shoulder harness inertia reel for 49. CABIN ENTRANCE DOOR a.

b.

folding steps do not fold properly without interference.

Check that fold

(FL-1 and After) too soon and that

they

Check cabin DOOR UNLOCK annunciator for proper

operation c.

d.

Inspect cabin door damper for leakage Inspect

door

latching

mechanism for

and proper

operation

operation.

and

security

of attachment. 50. CABIN CARGO DOOR and CABIN ENTRANCE DOOR

(FM-1 a.

and

After)

Inspect

door

latching

mechanism for

operation

and

security

of attachment. b.

Check proper

latching mechanism, folding steps and gas springs for operation.

51. EMERGENCY EXITS

Apr

(With

28/065-22-01

door installed and

properly rigged)

aao

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A, OPERATIONAL INSPECTION

ATAIGAMA

(Continued)

REFERENCE a.

Check emergency release handles latch mechanism for operation.

(inside

b.

Check that latches open and close

freely.

and

MECH

INSP

outside) and

52. EMPENNAGE CONTROL SURFACES a.

Checkforfreedom of movement.

b.

Check

optional operation.

trim actuators and motors for smoothness of

53. REAR FUSELAGE and EMPENNAGE LIGHTS

operation 54. AILERON

of all

(LH and RH)

55. AILERON TRIM TAB

operation

Check for freedom of movement.

Check trim tab actuator for smoothness of

and attachment.

56. FUEL TANK HEATED VENTS

operation

Check

lights.

of the heated vents.

(LH and RH) Check the They should be warm to the

28-10-00

touch. 57. STALL WARNING HEAT 58. FLAPS and ACTUATORS

Check flaps for noisy

or

Check for proper

operation.

(INBOARD, OUTBOARD, LH and RH) operation.

erratic

59. WING CENTER SECTION LIGHTS

Check

operation

of all

lights. 60. ENGINE INDUCTION SYSTEM vane

and

bypass

(LH

and

RH)

27-50-00

33-40-00

Check the inertial

door for movement with the main and

standby

actuator motors.

61. EXTERNAL POWER RELAY B.

Check for proper

operation.

24-40-00

POSTINSPECTIONITEMS 1.

AIRPLANE CLEANED and SERVICED AS REQUIRED.

12-00-00

2.

LUBRICATEAS NECESSARY.

12-20-00

3.

ENGINES INSPECTED AFTER GROUND RUN-UP OR FLIGHT TEST

Check for oil leaks,

security

and attachment of all

components. 4.

AIRWORTHINESS DIRECTIVES and SERVICE BULLETINS Must be reviewed and

A20

complied

with

as

required.

5-22-01

5

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

B. POST INSPECTION ITEMS

ATAIGAMA

(Continued)

REFERENCE ADDITIONAL INSPECTION REQUIREMENTS

5.

Ensure

MECH

INSP

Chapter

5, Special Inspection, and Airworthiness Limitations Manual (P/N

130-590031-211) requirements appropriate intervals.

with at the

complied

are

IN-FLIGHTWORKSHEETS DISCREPANCIES-AII

6.

noted

discrepancies as required.

by the pilot

must be checked and corrected

EMERGENCY LOCATOR TRANSMITTER

7.

operation

and

ensure

ELT is ARMED before

Check for proper

returning airplane to

25-60-00

service. Check for proper pressure.

8.

OXYGEN SYSTEM PRESSURE

9.

EMERGENCY and SURVIVAL EQUIPMENT Ensure all necessary emergency and survival installed in the airplane and is serviceable.

10. PLACARDS

and

Determine that all

(IF INSTALLED)equipment is

required placards

are

in

11-20-00

and POH

legible.

11. LOGBOOK ENTRY

place

Ensure that

log

books

are

filled out

properly. INSPECTION COMPLETED I

certify that Interim Inspection was performed in accordance airplane is approved for return to service:

that the

DATE: MECHANIC: CREW CHIEF: QUALITY CONTROL INSPECTOR:

Apr

28/06Page

6

5-22-01

with the Model B300/B300C

Inspection Program

and

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 5-22-02

BIENNIAL SCHEDULED INSPECTION PROGRAM (COMPLETE) - MAINTENANCE PRACTICES

Owner______________________________________

Total Time ____________ Total Cycles____________

W/O Number _________________________________ TSOH ________________ Cycles SOH ____________ Date In ________________ Date Out ______________ TSHSI _______________ Cycles SHSI ____________ Serial No. _____________ Reg. No. _______________ RH Eng. Gas Gen. S/N _________________________ Last Inspection ____________ Phase _____________ RH Eng. Power Module S/N _____________________ Last Inspection Date ___________________________ Total Time ____________ Total Cycles ____________ Last Inspection Hours __________________________ TSOH ________________ Cycles SOH ____________ Hourmeter _______________ Total Time __________

TSHSI _______________ Cycles SHSI ____________

Total Cycles _________________________________

LH Prop S/N _________________________________

Researched By _______________________________ LH Prop Total Time ____________ TSOH __________ Inspection Being Conducted _____________ Phase

RH Prop S/N _________________________________

LH Eng. Gas Gen. S/N _________________________ RH Prop Total Time ____________ TSOH __________ LH Eng. Power Module S/N ______________________ NOTE: The complete (COMP) inspection is a Phase 1 thru 4 inspection without the duplication.

A.

B.

NOSE SECTION

ATA/GAMA REFERENCE

1. NOSE SECTION AREA - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

AC43.13-1B/2B

2. RADOME - Inspect the exterior surface for cracks in the paint and fiberglass substrate.

AC43.13-1B/2B

MECH

INSP

NOSE AVIONICS COMPARTMENT 1. INSTRUMENT AIR FILTER - Inspect for cleanliness.

12-20-00 37-00-00

2. VACUUM REGULATOR VALVE FILTER - Inspect for blockage.

12-20-00 37-00-00

3. AVIONICS EQUIPMENT and RACKS - Inspect for security of attachment.

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Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

B. NOSE AVIONICS COMPARTMENT (Continued)

ATA/GAMA REFERENCE

MECH

INSP

4. NOSE AVIONICS COMPARTMENT AREA - Inspect for corrosion, trapped water and indications of water leakage.

C.

5. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

AC43.13-1B/2B

6. DOORS, FASTENERS and SEAL - Inspect seal for deterioration and doors and latches for proper adjustment and fit.

52-30-00

7. NOSE AVIONICS COMPARTMENT - Inspect skin, structure, all components and attaching hardware for general condition and security of attachment.

AC43.13-1B/2B

NOSE LANDING GEAR AREA 1. ELECTRICAL WIRING and EQUIPMENT - Inspect all exposed electrical wiring and equipment for chafing, damage and security of attachment. 2. FORWARD EVAPORATOR FILTER - Inspect forward evaporator filter.

21-50-00

3. CONDENSER BLOWER - Inspect fittings for dirt, grease, moisture and security of attachment.

21-50-00

4. REFRIGERANT LINES, SERVICE VALVES and HIGH PRESSURE RELIEF VALVES - Inspect lines and valves for leakage, damage, attachment and surface corrosion.

21-50-00

5. NOSE LANDING GEAR AREA - Inspect skin, structure, components and attaching hardware for general condition and security of attachment. If damage or corrosion is found in a given area, check the adjacent area. D.

AC43.13-1B/2B

AC43.13-1B/2B

NOSE GEAR 1. WHEEL a. Inspect wheel for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

CMM

2. TIRE a. Inspect for wear and deterioration. b. Check for correct inflation. 3. SHIMMY DAMPER - Inspect for leaks, security and attachment.

Page 202 May 1/10

5-22-02

12-10-00 12-20-00 32-20-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

D. NOSE GEAR (Continued)

ATA/GAMA REFERENCE

MECH

INSP

4. NOSE GEAR DRAG BRACE STOP LUGS - Inspect for cracks, damage or distortion. 5. NOSE GEAR STEERING STOP - Inspect steering stop for damage or distortion. 6. LANDING and TAXI LIGHTS a. Inspect for broken lenses or bulbs.

33-40-00

b. Confirm correct focus of landing and taxi lights. 7. STEERING LINKAGE - Inspect nose gear steering mechanism and attaching hardware for wear, damage and corrosion. 8. STRUT - Check strut for leakage and correct extension. 9. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment. 10. NOSE GEAR LOWER DRAG LEG - Remove nose gear drag brace bolt and inspect lower drag leg hole for corrosion and wear.

32-50-00 12-20-00 32-30-00 AC43.13-1B/2B

CMM

11. NOSE GEAR ACTUATOR a. Inspect actuator support brackets for damage, cracks and loose or missing fasteners.

32

b. Inspect actuator and plumbing for leakage.

32

12. ALL COMPONENTS - Inspect all components and attaching hardware for wear, damage and surface corrosion. E.

32

PILOT'S COMPARTMENT 1. RETURN INLET AIR FILTERS - Inspect filters in return air inlet of the forward vent blower.

21-50-00

2. WINDSHIELDS a. Inspect windshields for cracks and visibility impairment.

56-10-00

b. Inspect windshield weather seal for debonding, cracks or wear.

56-10-00

3. WINDOWS - Inspect exterior surface of cockpit side windows for deep scratches, cracks, chips or excess crazing or other damage.

A28

56-15-00

5-22-02

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

E. PILOT'S COMPARTMENT (Continued)

ATA/GAMA REFERENCE

4. SEAT BELTS and SHOULDER HARNESSES - Inspect seat belts and shoulder harnesses for deterioration.

AC43.13-1B/2B

5. SEAT TRACKS - Inspect seat tracks for damage and wear.

25-10-00

6. FIRE EXTINGUISHER (PORTABLE) - Inspect the bottle for signs of damage and mount for security of attachment.

26 CMM

MECH

INSP

7. UPHOLSTERY PANELS - Inspect for security of attachment. 8. REFRIGERANT LINES and SERVICE VALVES - Inspect lines for leakage, damage and attachment. 9. ALTERNATE AIR VALVE - Drain off all moisture. 10. FLIGHT CONTROL CABLE TENSION - Check aileron control cable tension.

34-00-00 27

11. PILOT'S COMPARTMENT AREA - Inspect skin, structure, seats and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

AC43.13-1A

12. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

AC43.13-1A

13. RUDDER PEDALS a. Inspect rudder pedals for wear, clearance and attachment.

27-20-00

b. Inspect rudder pedal linkage for wear, damage, attachment and operation.

27-20-00

14. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than 3 broken wires in any given 3-foot length of cable or have evidence of corrosion.

27

15. BRAKE FLUID RESERVOIR PRESSURE EQUALIZATION ORIFICE - Inspect for blockage.

32-40-00

16. BRAKE SYSTEM - Inspect brake system components and plumbing for leakage and attachment.

32-40-00

Page 204 May 1/10

5-22-02

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

E. PILOT'S COMPARTMENT (Continued) 17. INSTRUMENT PANEL, PLUMBING and WIRING - Inspect instrument panel, subpanels, placards, shock mounts and instrument plumbing for damage, attachment, chafing and hoses for hardness or cracks.

ATA/GAMA REFERENCE

MECH

INSP

39-10-00

18. CONTROL COLUMN a. Inspect for wear, damage, corrosion, attachment and operation.

27-10-00

b. Inspect control wheel adapter for cracks in the weld area of adapter or forward side of control wheel.

27-10-00

c.

Inspect control wheel switches for condition and security of attachment.

d. Operate control wheel full forward and aft, left and right. Check for binding or interference. 19. PEDESTAL

27-10-00 27-10-00 39-10-00

a. Inspect pedestal components and plumbing for damage, attachment and chafing and hoses for hardness or cracks. b. Inspect condition lever catch gates for wear.

76-00-00

20. PRESSURIZATION CONTROLLER a. Inspect for security of attachment, plumbing and wiring for damage and connection security.

21-30-00

b. Inspect and clean filter in controller assembly located within the pedestal.

21-30-00

21. ACCESS DOORS - Inspect for fit and attachment. 22. WINDSHIELD HEATED - Inspect windshield antistatic coating and tab bonding.

56-10-00

23. RELIEF TUBE (If installed) a. Inspect plumbing and storage box for corrosion. b. Inspect relief tube outlet area for corrosion. 24. BUS CONFORMITY CHECK - Perform the bus conformity check. Refer to procedure in Chapter 24-50-00.

24-50-00

25. ENVIRONMENTAL SYSTEM a. Inspect hot air ducts for condition and security of installation.

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5-22-02

Page 205 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

E. PILOT'S COMPARTMENT (Continued)

ATA/GAMA REFERENCE

MECH

INSP

b. Check ducts for evidence of thermal leaks and/or degradation, such as discoloration of duct insulator, adjacent structure or components. c.

Physically inspect ducts by touching ducts, checking for thermal deterioration, deformation of the ducts, and proper connection at the joints.

26. MANUAL LANDING GEAR EXTENSION HANDLE - Inspect the manual extension handle assembly and linkage from the handle to the manual extension pump for proper installation, wear and security of attachment. F.

CABIN SECTION 1. WINDOWS - Inspect exterior surfaces of windows for deep scratches, cracks, chips and excessive crazing or other damage.

56-15-00

2. ROTATING OR FLASHING BEACON - Inspect for cracked or broken lenses.

33-40-00

3. ACCESS DOORS - Inspect for fit and attachment. 4. OUTFLOW and SAFETY VALVES a. Drain outflow valve control line.

21-30-00

b. Inspect plumbing and components for attachment. c.

Inspect and clean safety valve screen.

21-30-00

d. Inspect poppet and seat of both valves.

21-30-00

e. Perform functional test of outflow and safety valves and cabin altitude limit controllers.

21-30-00

5. PRESSURIZATION DUCTS - Inspect for security of attachment.

21-20-00

6. FLAPPER VALVE - Check for proper operation and excessive air noise.

21-20-00

7. SEAT TRACKS - Inspect seat tracks for damage and wear.

25-20-00

Page 206 May 1/10

5-22-02

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

F. CABIN SECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

8. CABIN SECTION - Inspect skin, structure, seats and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area. 9. SEAT BELTS and SHOULDER HARNESSES a. Inspect seat belts and shoulder harness for deterioration and missing components.

AC43.13-1A

b. Inspect shoulder harness attachment post for cracked, warn, brittle or missing grommets.

AC43.13-1A

10. OXYGEN SYSTEM a. Test all masks for oxygen flow.

35-00-00

b. Inspect oxygen system installation for damage and security of attachment.

35-00-00

11. TOILET - Inspect for spillage and leakage below the toilet. 12. CABIN ENTRANCE DOOR (FL-1 and After) a. Inspect the door seal for cuts, abrasions and security of attachment.

52-10-00

b. Inspect door seal solenoid valve and pressure regulator valve for security and electrical connection.

52-10-00

c.

Inspect the cabin door support cables for wear, damage and security.

d. Inspect door latching mechanism and cables for damage, deterioration and security of attachment. e.

f.

A28

52-10-00 52-10-00

Inspect upper latch hooks and retaining pins for rigging, wear and damage. Replace pin at 10% diameter wear. (Pin removal required)

52-10-00

Inspect upper latch hooks for proper tension.

52-10-00

g. Inspect side latch bolts (bayonets) and rollers for rigging and freedom of movement.

52-10-00

h. Inspect the cabin door unlocked annunciator switch spring.

52-10-00

13. CABIN CARGO DOOR and CABIN ENTRANCE DOOR (FM-1 and After) - Inspect door seals for cuts, abrasions, deterioration and security of attachment.

52-11-00

14. EMERGENCY EXIT

25-20-00

5-22-02

Page 207 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

F. CABIN SECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

a. Inspect latches for damage and check all moving parts for proper operation. b. Check for proper latch adjustment and seal of closed latches. 15. CABIN DOOR and EMERGENCY EXITS a. Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

AC43.13-1b/2A

b. Inspect corner areas of emergency exit (removed) for cracks and abrasion in area of curvature between seal and outer face of exit.

52-20-00

16. AVIONICS EQUIPMENT and RACKS (IF INSTALLED) - Inspect avionics equipment and racks for security of attachment. 17. BULKHEADS - Inspect for water traps. 18. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends and cracks which are conditions for replacement.

27

b. Inspect control cables, pulleys and associated equipment for cracks, damage, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given three-foot cable length or have evidence of corrosion.

27

19. FLAP MOTOR and DRIVES - Inspect for damage and attachment.

27-50-00

20. AILERON QUADRANT REGULATOR - Inspect for security, attachment, operation and travel.

27-10-00

21. BELLY DRAIN VALVES - Inspect for possible obstructions. 22. CABIN WINDOW ATTACH FRAMES - Inspect windows for looseness or movement.

56-15-00

23. PNEUMATIC PRESSURE REGULATOR, VACUUM EJECTOR and DEICER DISTRIBUTION VALVE - Inspect equipment and plumbing for security.

Page 208 May 1/10

5-22-02

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

F. CABIN SECTION (Continued) 24. WINDOW DEFOG SYSTEM - Inspect associated plumbing for kinks, security and general condition. Inspect the three inline filters (if installed) for moisture, contamination and proper installation (recommend replacement to coincide with Chapter 5-11-00 requirements).

ATA/GAMA REFERENCE

MECH

INSP

30-40-00

25. CONTROL CABLE SEALS - Inspect for damage, security, cleanliness and lubrication.

27

26. AUTOPILOT COMPONENTS - Inspect components for security of attachment.

22

27. RELIEF TUBE (If installed) a. Inspect plumbing and storage box for corrosion. b. Inspect relief tube outlet area for corrosion. 28. ANTENNAS - Inspect all external antennas for leading edge erosion and condition of base seals. 29. FIRE EXTINGUISHER, (PORTABLE) - Inspect bottle for signs of damage and security. 30. ELECTRICAL WIRING and EQUIPMENT - Inspect all exposed electrical wiring and equipment for chafing, damage and security of attachment.

AC43.13-1B/2B

31. UPHOLSTERY PANELS - Inspect for security of attachment. 32. EMERGENCY EXIT LIGHT a. Inspect emergency exit light for battery leakage and security of lamp.

33-20-00

b. Inspect electrical wiring and equipment for chafing, damage, proper routing of wire bundles and security of attachment.

AC43.13-1B/2B

33. AFT EVAPORATOR FILTER - Inspect aft evaporator filter.

21-50-00

34. HYDRAULIC LINES, LANDING GEAR - Inspect for leaks, damage and security of attachment. 35. CABIN AREA - Inspect skin, structure, seats and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

25-20-00

36. ENVIRONMENTAL SYSTEM a. Inspect ducts for condition and security of installation.

A28

5-22-02

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

F. CABIN SECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

b. Check ducts for evidence of thermal leaks and/or degradation, such as discoloration of duct insulator, adjacent structure or components. c.

G.

Physically inspect ducts by touching ducts, checking for thermal deterioration, deformation of the ducts, and proper connection at the joints.

REAR FUSELAGE AND EMPENNAGE 1. REAR FUSELAGE DRAIN HOLES - Inspect rear fuselage drains.

53-10-00

2. ELT BATTERY a. Inspect for leakage, corrosion or loose leads.

25-60-00

b. Determine remaining useful life.

25-60-00

3. NAVIGATION LIGHTS and ROTATING OR FLASHING BEACONS - Inspect for broken or cracked lenses.

33-40-00

4. ACCESS DOORS - Inspect for fit and security of attachment. 5. VENTRAL FIN DRAIN HOLES - Inspect the drain holes in the bottom of the ventral fin for obstructions.

53-00-00

6. DEICER BOOTS - Inspect for deterioration, damage and attachment. 7. RUDDER and TRIM TABS DRAIN HOLES - Inspect the drain holes for obstructions. 8. STATIC WICKS a. Inspect for damage and security of attachment.

23-60-00

b. Inspect for proper bonding to the airplane.

23-60-00

9. EMPENNAGE and CONTROL SURFACES a. Check elevator trim tab free play.

27-30-00

b. Check rudder trim tab free play.

27-20-00

c.

27-20-00 27-30-00

Inspect elevator and rudder hinge brackets and their spar attach areas.

10. PRESSURIZATION OVERBOARD DUMP SYSTEM (IF INSTALLED) - Inspect louver and screen for obstruction and hoses for security.

Page 210 May 1/10

5-22-02

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

G. REAR FUSELAGE and EMPENNAGE (Continued) 11. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

ATA/GAMA REFERENCE

MECH

INSP

AC43.13-1A

12. AVIONICS and AUTOPILOT EQUIPMENT and RACKS Inspect avionics and autopilot equipment and racks for security, corrosion and signs of water leakage. 13. VERTICAL STABILIZER - Inspect front and rear spars of the vertical stabilizer for loose or missing rivets or fasteners. 14. CONTROL CABLE SEALS - Inspect for deterioration, security, cleanliness and lubrication.

55-30-00 27

15. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect the control system components (pushrods, turnbuckles, castings, etc.) for bulges, splits or cracks which are conditions for replacement. Inspect rudder torque shaft arm for loose or working fasteners. b. Inspect control cables, pulleys and associated equipment for cracks, wear, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given 3-foot length of cable or have evidence of corrosion. 16. FLIGHT CONTROL CABLE TENSION - Inspect elevator and elevator tab, rudder and rudder tab control cable tension. 17. OXYGEN SYSTEM - Inspect plumbing for security of attachment. 18. REAR FUSELAGE and EMPENNAGE AREA - Inspect skin, structure, all components and attaching hardware for general condition and security of attachment. If damage or corrosion is found in a given area, check the adjacent area.

27

27

27 35-00-00

AC43.13-1A

19. PLUMBING - Inspect plumbing for security of attachment. H.

LEFT SIDE OUTBOARD WING 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

3. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

A28

33-40-00

5-22-02

Page 211 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

H. LEFT SIDE OUTBOARD WING (Continued) b. Inspect the strobe light for broken or cracked lenses.

ATA/GAMA REFERENCE

MECH

INSP

33-40-00

4. FUEL TANKS and VENTS a. Inspect exterior openings of vents for obstructions.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

5. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

6. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

7. ACCESS DOORS (INSPECTION PANELS), WINGS - Inspect for fit and attachment.

57-30-00

8. STATIC WICKS a. Inspect for security of attachment.

23-60-00

b. Inspect for proper bonding to the airplane.

23-60-00

9. AILERON and TRIM TAB - Check trim tab free play.

27-10-00

10. LEFT-HAND OUTBOARD WING - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

AC43.13-1B/2B

11. AILERON and OUTBOARD FLAP - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

27-10-00 27-50-00

12. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

AC43.13-1B/2B

13. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control system cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given 3-foot length of cable or have evidence of corrosion.

27

c.

27

Page 212 May 1/10

Inspect aileron control cable tensions.

5-22-02

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

H. LEFT SIDE OUTBOARD WING (Continued) d. Inspect aileron tab control cable tensions.

ATA/GAMA REFERENCE

MECH

INSP

27

14. FLAP and ACTUATORS a. Inspect flap 90° drive, cable and actuator for attachment.

27-50-00

b. Inspect flap tracks for wear.

27-50-00

c.

Perform FLAP SAFETY MECHANISM FUNCTIONAL TEST. Refer to Chapter 27-50-00.

15. FUEL PLUMBING - Inspect for leaks, chafing, damage and attachment.

I.

27-50-00 28

16. HINGED ACCESS DOORS ABOVE DOORS NO. 13 and 14 Inspect for cracks or damage to hinge and fasteners.

57-30-00

17. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

LEFT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS a. Inspect the exterior of the center section for leaks.

28-10-00

b. Inspect fuel filler cap and antisiphon valve for damage and attachment.

28-10-00

c.

Inspect the exterior openings of the vents for obstructions.

3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

57-30-00

4. FUEL PUMP, CENTER SECTION - Inspect the pumps for leaks and security of attachment.

28-20-00

5. ENGINE FIRE EXTINGUISHER

26-20-00

a.

Inspect plumbing for security of attachment.

b. Check fire bottle pressure gage. c.

Check for presence of activation voltage to the cartridge/ squib. Perform the EXTINGUISHER ACTIVATION CHECK procedure.

26-20-00 26-20-00 26-20-00

6. LEFT-HAND WING CENTER SECTION - Inspect wing center section and inboard flap, skin structure and attaching hardware for wear, damage and corrosion. If damage is found in a given area, check the adjacent area. 7. FLAPS and ACTUATORS

A28

5-22-02

Page 213 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I. LEFT SIDE WING CENTER SECTION (Continued)

ATA/GAMA REFERENCE

a. Inspect flap 90° drive, cable and actuator for attachment.

27-50-00

b. Inspect flap tracks for wear.

27-50-00

8. LEADING EDGE and NACELLE FUEL PLUMBING - Inspect fuel plumbing for leaks, damage and security of attachment.

MECH

INSP

28-20-00

9. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given three-foot cable length or have evidence of corrosion.

27

10. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage and proper routing of wire bundles and security of attachment. 11. BLEED AIR BYPASS VALVE - Check bleed air valve at heat exchanger for operation of linkage to butterfly valve and operation of actuator motor.

AC43.13-1B/2B

21-40-00

12. LANDING GEAR POWER PACK and MOTOR a. Inspect the hydraulic power pack gear-up and gear-down port screens.

32-30-00

b. Inspect the landing gear hydraulic system bleed air pressure overboard relief orifice screen for blockage.

32-30-00

c.

J.

Inspect all plumbing attach points for leaks and security of attachment.

32-30-00

d. Inspect the landing gear emergency extension hand pump suction line filter.

32-30-00

13. UPPER SURFACE BONDED PANEL - Inspect bonded panel.

51-00-00

LEFT SIDE MAIN LANDING GEAR AREA 1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage.

Page 214 May 1/10

5-22-02

CMM

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

J. LEFT SIDE MAIN LANDING GEAR AREA (Continued)

ATA/GAMA REFERENCE

2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

32-40-00 CMM

3. TIRES - Inspect tires for wear, deterioration and correct inflation

32-40-00 12-10-00 CMM

4. STRUT - Check strut for leaks and proper extension.

12-10-00

5. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

AC43.13-1B/2B

6. ACTUATOR MAIN GEAR - Inspect actuator and plumbing for leakage and attachment.

32-30-00

a. Check actuator support brackets for visible damage, wear and loose or missing fasteners.

32-30-00

b. Check actuator and plumbing for leakage.

32-30-00

MECH

INSP

7. DRAG LEG a. Inspect for security of attach fittings. b. Inspect downlock bolts for proper torque (finger-tight and safety-wired). 8. MAIN LANDING GEAR AREA - Inspect wheel well and gear door structure, all components and attaching hardware for wear, damage and corrosion. If damage or corrosion is found, check the adjacent area.

32-10-00 CMM

AC43.13-1B/2B

9. BRAKE DEICING (IF INSTALLED) - Inspect manifold for blocked orfices. K.

LEFT SIDE ENGINE 1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00 CMM

2. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

12-10-00

3. PROPELLERS a. Inspect for damage and attachment (spinner removal required).

61

b. Inspect the carbon block pin for freedom of movement.

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Page 215 May 1/10

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K. LEFT SIDE ENGINE (Continued) c.

ATA/GAMA REFERENCE

Check for no metal-to-metal contact between the brass ring and the reversing lever.

d. Inspect the reversing linkage for correct adjustment, evidence of binding and security of attachment. e. Inspect mechanical feedback ring, stop rods and springs for damage. 4. HIGH PRESSURE FUEL PUMP FILTERS - Inspect the enginedriven high pressure fuel pump filters.

MECH

INSP

61 76-00-00 61 P&W

5. ENGINE OIL FILTER - Inspect for metal particles. Refer to the engine maintenance manual. 6. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT - If Sunstrand fuel pump is installed, check the exterior of the fuel pump coupling for fretting and corrosion as instructed by the engine maintenance manual.

P&W 72-00-00 P&W 73-10-02

7. DRAIN PLUGS - Inspect all drain plugs for leakage, security and safetying.

79-00-00

8. COWLING - Remove entire cowling and inspect skin, structure and attaching hardware for wear, damage and corrosion.

71-10-00

9. OIL COOLER - Inspect oil cooler and plumbing for leakage, damage and attachment.

79-00-00

10. AFT COWLING ACCESS DOOR - Check adjustment of latches.

71-10-00

11. FIRESEALS - Inspect for condition.

71-30-00

12. EXHAUST SYSTEM a. Inspect attaching hardware for wear, damage and corrosion.

78-00-00

b. Inspect the exhaust system and visible portions of the power turbine for burning, distortion, damage and cracks. If these conditions are found refer to the engine maintenance manual for corrective action.

P&W

13. ENGINE and PROPELLER CONTROLS a. Check controls and associated equipment for binding, stiff operation, full travel and friction lock. b. Inspect controls, bolts, nuts, cotter pins and safeties for corrosion, damage and attachment. NOTE Special attention should be made to the cam box.

Page 216 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued) c.

Inspect control cables for damage such as crimps, cuts, abrasions or tight bends. If exterior covering is ruptured, perform leak test.

ATA/GAMA REFERENCE

MECH

INSP

76-00-00

14. ENGINE CONTROL CABLE BOOTS - Inspect the control cable boots for excessive compression, twist, wear or aging which could cause binding. 15. STARTER-GENERATOR BRUSHES - Inspect one set of brushes for indications of excessive wear or damage (determine wear by observing diagonal groove on brush).

24-30-00

16. COMPRESSOR INLET - Remove the air inlet screen and inspect the compressor inlet area, struts, first stage blades and vanes for dirt deposits, corrosion, erosion, cracks and damage by foreign objects. Refer to the engine maintenance manual for corrective action.

P&W

17. MAGNETIC CHIP DETECTOR a. Remove and visually inspect plug for metal particles and damage.

79-30-00

b. Check light in annunciator panel for proper operation.

79-30-00

18. ENGINE a. Inspect fuel nozzles per manufacturer's manual. b. Inspect engine in accordance with the instructions in the engine manufacturer's manual.

P&W P&W 72-00-00

19. ENGINE MOUNT TRUSS ASSEMBLY a. Inspect for cracks, dents, chafing and corrosion. Special attention should be directed to areas around clamps.

71-20-00

b. Inspect vibration isolators (mounts) for deterioration, damage and attachment.

71-20-00

20. INDUCTION SYSTEM a. Check the inertial anti-icer vane for proper travel.

30-20-00

b. Inspect the engine inlet screen, inertial separator and air inlet duct for obstruction and damage.

30-20-00 71-00-00

21. FIRE DETECTION SYSTEM a. Inspect fire detection cable for kinks, abrasions or bends with a radius of less than 2 inches.

A28

26-10-00

5-22-02

Page 217 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

b. Inspect the fire detection cables to make sure they do not contact the surrounding structure and for security of attachment.

26-10-00

c.

26-10-00

Perform a check of the system.

22. PROPELLER SYNCHROPHASER - Inspect for proper gap between pickups and targets.

61-22-00

23. AUTOFEATHER and AUTOIGNITION PRESSURE SWITCHES - Inspect security of attachment, leakage and electrical connection for security.

61-21-00 74-00-00

24. PROPELLER PRIMARY GOVERNOR - Inspect for security of attachment, leakage and security of electrical connectors and wiring.

61-20-00

25. OVERSPEED GOVERNOR - Inspect for security of attachment, leakage and security of electrical connectors and wiring.

61-20-00

MECH

INSP

26. IGNITION EXCITER a. Inspect exciter and electrical harness for damage and security of attachment.

74-00-00

b. Inspect that supply cable and ignition cable connectors are installed and safetied.

74-00-00

27. SPARK IGNITER PLUGS - Inspect the igniter plugs as described in the engine maintenance manual.

P&W

28. FUEL PURGE SYSTEM a. Remove the fuel purge system air tank and inspect. Clean as required.

71-70-00

b. Remove fuel purge tank filter and inspect for corrosion. Clean as required.

71-70-00

c.

Remove fuel purge system check valves. Inspect, pressure flush and perform internal leakage test. Replace as required,

d. Perform the Fuel Purge System Flow Divider/Purge Valve Leakage Test. 29. P3 AIR FILTER - Inspect the filter for cleanliness. 30. ENVIRONMENTAL, BLEED AIR FLOW CONTROL VALVE Inspect valve and associated equipment, electrical wiring and ducts for damage, security of connections and attachment.

Page 218 May 1/10

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71-70-00 71-70-00 P&W 21-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

K. LEFT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

MECH

INSP

31. RUDDER BOOST TRANSDUCER - Inspect for security of attachment, leakage and security of electrical connectors and wiring. L.

RIGHT SIDE OUTBOARD WING 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. WING ATTACH FITTING DRAIN HOLES - Determine that the drain holes are open in the wing center and upper section attach fittings.

57-00-00

3. LIGHTS a. Inspect the navigation and recognition lights for broken or cracked lenses.

33-40-00

b. Inspect the strobe light for broken or cracked lenses.

33-40-00

4. FUEL TANKS and VENTS a. Inspect exterior openings of vents for obstructions.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior of the wing for leaks.

5. INTEGRAL FUEL TANK - Inspect the exterior surface of the integral tank access doors for leaks.

28-10-00

6. DEICER BOOTS - Inspect exterior surface for deterioration, damage and attachment.

30-10-00

7. ACCESS DOORS (INSPECTION PANELS), WING - Inspect for fit and attachment.

57-30-00

8. STATIC WICKS

A28

a. Inspect for damage and security of attachment.

23-60-00

b. Inspect for proper bonding to the airplane.

23-60-00

9. AILERON and TRIM TAB - Check trim tab free play.

27-10-00

10. RIGHT-HAND OUTBOARD WING - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

57-00-00

11. AILERON and OUTBOARD FLAP - Inspect skin, structure and attaching hardware for wear, damage and corrosion. If damage or corrosion is found in a given area, check the adjacent area.

27-10-00 27-50-00

5-22-02

Page 219 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

L. RIGHT SIDE OUTBOARD WING (Continued) 12. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage, proper routing of wire bundles and security of attachment.

ATA/GAMA REFERENCE

MECH

INSP

AC43.13-1B/2B

13. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control system cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given 3-foot length of cable or have evidence of corrosion.

27

c.

27

Check aileron control cable tension.

14. FLAPS and ACTUATORS a. Inspect flap 90° drive, cable and actuator for attachment.

27-50-00

b. Inspect flap tracks for wear.

27-50-00

c.

M.

Perform FLAP SAFETY MECHANISM FUNCTIONAL TEST. Refer to Chapter 27-50-00.

27-50-00

15. FUEL PLUMBING - Inspect for leaks, chafing or damage and attachment.

28-20-00

16. HINGED ACCESS DOORS ABOVE DOORS NO. 13 and 14 Inspect for cracks or damage to hinge and fasteners.

57-30-00

17. STATIC GROUND RECEPTACLES - Inspect for damage.

10-10-00

RIGHT SIDE WING CENTER SECTION 1. FUEL PROBES - Inspect for leaks at points of attachment.

28-40-00

2. FUEL TANKS and VENTS a. Inspect the exterior of the center section for leaks.

28-10-00

b. Inspect fuel cap and antisiphon valve for damage and attachment.

28-10-00

c.

28-10-00

Inspect the exterior openings of the vents for obstructions.

3. ACCESS DOORS (INSPECTION PANELS) - Inspect for fit and attachment.

Page 220 May 1/10

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57-30-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

M. RIGHT SIDE WING CENTER SECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

4. BATTERY a. Service battery as required.

12-10-00

b. Remove battery and inspect the battery box, cables and vent tubes for deterioration or obstructions. (FL-1 thru FL-214. FM-1 thru FM-9)

24-31-00

c.

Remove battery and inspect the battery box and cables for deterioration or obstructions. (FL-215 and After; FM-10 and After)

24-31-00

5. FUEL PUMPS - Inspect the pumps for leaks and security of attachment.

28-20-00

6. ENGINE FIRE EXTINGUISHER

26-20-00

a.

Inspect plumbing for security of attachment.

b. Check fire bottle pressure gage. c.

Check for presence of activation voltage to the cartridge/ squib. Perform the EXTINGUISHER ACTIVATION CHECK procedure.

26-20-00 26-20-00 26-20-00

7. RIGHT-HAND WING CENTER SECTION - Inspect wing center section and inboard flap, skin structure and attaching hardware for wear, damage and corrosion. If damage is found in a given area, check the adjacent area. 8. FLAPS and ACTUATORS a. Inspect flap 90° drive, cable and actuator for attachment.

27-50-00

b. Inspect flap tracks for wear.

27-50-00

9. LEADING EDGE and NACELLE FUEL PLUMBING - Inspect fuel plumbing for leaks, damage and security of attachment.

28-20-00

10. FLIGHT CONTROL COMPONENTS, CABLES and PULLEYS

A28

a. Inspect control system components (pushrods, turnbuckles, end fittings, castings, etc.) for bulges, splits, bends or cracks which are conditions for replacement.

27

b. Inspect control cables, pulleys and associated equipment for wear, cracks, breaks, attachment, alignment, clearance and proper operation. Replace cables that have more than three broken wires in any given 3-foot length of cable or have evidence of corrosion.

27

5-22-02

Page 221 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

M. RIGHT SIDE WING CENTER SECTION (Continued) 11. ELECTRICAL WIRING and EQUIPMENT - Inspect for chafing, damage and proper routing of wire bundles and security of attachment.

N.

ATA/GAMA REFERENCE

MECH

INSP

AC43.13-1B/2B

12. BLEED AIR BYPASS VALVE - Check bleed air valve at heat exchanger for operation of linkage to butterfly valve and operation of actuator motor.

21-40-00

13. UPPER SURFACE BONDED PANEL - Inspect bonded panel.

51-00-00

14. REFRIGERANT LINES and PRESSURE SWITCHES - Inspect lines and switches for leakage, damage and attachment.

21-50-00

RIGHT SIDE MAIN LANDING GEAR AREA 1. WHEELS a. Inspect wheels for wear, damage and corrosion. b. Inspect wheel bearings and races for wear, pitting, cracks, discoloration, rust or other indications of damage. 2. BRAKES - Inspect brake discs, linings and plumbing for wear, damage, leaks, corrosion and security of all components.

CMM 32-40-00

3. TIRES - Inspect tires for wear, deterioration and correct inflation.

32-40-00 12-10-00 CMM

4. STRUT - Check strut for leaks and proper extension.

12-10-00

5. ELECTRICAL WIRING and EQUIPMENT - Inspect exposed wiring and equipment for chafing, damage and proper routing and security of attachment.

AC43.13-1B/2B

6. MAIN GEAR ACTUATOR - Inspect actuator and plumbing for leakage and attachment.

32-30-00

7. DRAG LEG a. Inspect for security of attach fittings. b. Inspect downlock bolts for proper torque (finger-tight and safety-wired). 8. MAIN LANDING GEAR AREA - Inspect wheel well and gear door structure, all components and attaching hardware for wear, damage and corrosion. If damage or corrosion is found, check the adjacent area. 9. BRAKE DEICING (IF INSTALLED) - Inspect manifold for blocked orifices.

Page 222 May 1/10

5-22-02

32-10-00 CMM

AC43.13-1B/2B

32-41-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O.

RIGHT SIDE ENGINE

ATA/GAMA REFERENCE

1. PROPELLER DEICER BOOTS - Inspect propeller deice system (spinner removal required).

30-60-00 CMM

2. FUEL FILTERS and SCREENS - Inspect the firewall filter for evidence of foreign matter, corrosion or microbiological growth in the fuel system. If any microbiological growth is found, use BIOBOR JF additive.

12-10-00 28-20-00

MECH

INSP

3. PROPELLERS a. Inspect for damage and attachment (spinner removal required).

61-10-00

b. Inspect the carbon block pin for freedom of movement.

61-10-00

c.

Check for no metal-to-metal contact between the brass ring and the reversing lever.

d. Inspect the reversing linkage for correct adjustment, evidence of binding and security of attachment. e.

Inspect mechanical feedback ring, stop rods and springs for damage.

61-10-00 76-00-00 61-10-00

4. HIGH PRESSURE FUEL PUMP FILTERS - Inspect the enginedriven high pressure fuel pump filters.

P&W

5. ENGINE OIL FILTER - Inspect for metal particles.

P&W

6. ENGINE-DRIVEN FUEL PUMP COUPLING SHAFT - If Sunstrand fuel pump is installed, check the exterior of the fuel pump coupling for fretting and corrosion as instructed by the engine maintenance manual.

P&W 72-00-00 P&W 73-10-02

7. DRAIN PLUGS - Inspect all drain plugs for leakage, security and broken safety wire.

79-00-00

8. COWLING - Remove entire cowling and inspect skin, structure and attaching hardware for wear, damage and corrosion.

71-10-00

9. OIL COOLER - Inspect oil cooler and plumbing for leakage, damage and attachment.

79-00-00

10. AFT COWLING ACCESS DOORS - Check adjustment of latches.

71-10-00

11. FIRESEALS - Inspect for condition.

71-30-00

12. EXHAUST SYSTEM a. Inspect attaching hardware for wear, damage and corrosion.

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Page 223 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O. RIGHT SIDE ENGINE (Continued)

ATA/GAMA REFERENCE

b. Inspect the exhaust system and visible portions of the power turbine for burning, distortion, damage and cracks. If any of these conditions are found, refer to the engine maintenance manual for corrective action.

MECH

INSP

P&W

13. ENGINE and PROPELLER CONTROLS a. Check controls and associated equipment for binding, stiff operation, full travel and friction lock. b. Inspect controls, bolts, nuts, cotter pins and safeties for corrosion, damage and attachment NOTE Special attention should be directed to the cam box. c.

Inspect control cables for damage such as crimps, cuts, abrasions or tight bends. If exterior covering is ruptured, perform leak test.

76-00-00

14. ENGINE CONTROL CABLE BOOTS - Inspect the control cable boots for excessive compression, twist, wear or aging which could cause binding. 15. STARTER-GENERATOR BRUSHES - Inspect one set of brushes for indications of excessive wear or damage (determine wear by observing diagonal groove on brush).

24-30-00

16. COMPRESSOR INLET - Remove the air inlet screen and inspect the compressor inlet area, struts, first stage blades and vanes for dirt deposits, corrosion, erosion, cracks and damage by foreign objects. Refer to the engine maintenance manual for corrective action. 17. MAGNETIC CHIP DETECTOR a. Check plug.

79-30-00

b. Check light in annunciator panel for proper operation.

79-30-00

18. ENGINE a. Inspect fuel nozzles per manufacturer's manual.

P&W

b. Inspect engine in accordance with instructions found in the engine manufacturer's manual.

P&W

19. ENGINE MOUNT TRUSS ASSEMBLY a. Inspect for cracks, dents, chafing and corrosion. Special attention should be directed to areas around clamps.

Page 224 May 1/10

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71-20-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O. RIGHT SIDE ENGINE (Continued) b. Inspect vibration isolators (mounts) for deterioration, damage and attachment.

ATA/GAMA REFERENCE

MECH

INSP

71-20-00

20. INDUCTION SYSTEM a. Check the inertial anti-icer vane for proper travel.

30-20-00

b. Inspect the engine inlet screen, inertial separator and air inlet duct for obstruction and damage.

30-20-00 71-00-00

21. FIRE DETECTION SYSTEM a. Inspect fire detection cable for kinks, abrasions or bends with a radius of less than 2 inches

26-10-00

b. Inspect fire detection cables to make sure they do not contact the surrounding structure and for security of attachment

26-10-00

c.

26-10-00

Perform a check of the system.

22. PROPELLER SYNCHROPHASER - Inspect for proper gap between pickups and targets.

61-22-00

23. AUTOFEATHER and AUTOIGNITION PRESSURE SWITCHES - Inspect security of attachment, leakage and electrical connection for security.

61-21-00 74-00-00

24. PRIMARY PROPELLER GOVERNOR - Inspect for security of attachment, leakage and security of electrical connectors and wiring.

61-20-00

25. OVERSPEED GOVERNOR - Inspect for security of attachment, leakage and security of electrical connectors and wiring.

61-20-00

26. IGNITION EXCITER a. Inspect exciter and electrical harness for damage and security of attachment.

74-00-00

b. Inspect that supply cable and ignition cable connectors are installed and safetied.

74-00-00

27. SPARK IGNITER PLUGS - Inspect the igniter plugs as described in the engine maintenance manual.

P&W

28. FUEL PURGE SYSTEM

A28

a. Remove fuel purge air tank and inspect. Clean as required.

71-70-00

b. Remove fuel purge tank filter and inspect for corrosion. Clean as required.

71-70-00

5-22-02

Page 225 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O. RIGHT SIDE ENGINE (Continued) c.

Remove fuel purge system check valves. Inspect, pressure flush and perform internal leakage test. Replace as required.

d. Perform the Fuel Purge System Flow Divider/Purge Valve Leakage Test. 29. P3 AIR FILTER - Inspect the filter for cleanliness. Refer to the engine maintenance manual for procedure.

ATA/GAMA REFERENCE

MECH

INSP

71-70-00 71-70-00 P&W

30. AIR-CONDITIONER COMPRESSOR a. Inspect for security of attachment and oil leaks.

21-50-00

b. Inspect for wear and lubricate the spline on the pulley end of the quill shaft.

21-50-00

c.

Inspect drive belt for deterioration, wear and proper tension.

21-50-00

d. Inspect the integrity and security of the clutch assembly. Remove the belt from the compressor. Inspect for freedom of rotation, bearing roughness and free play (wobble). Check for corrosion or evidence of inappropriate wear (belt dust, metal shavings). Install belt on compressor.

21-50-00

31. REFRIGERANT LINES and SERVICE VALVES - Inspect lines and valves for leakage, damage and attachment.

21-50-00

32. ENVIRONMENTAL, BLEED AIR FLOW CONTROL VALVE Inspect valve and associated equipment, electrical wiring and ducts for damage, security of connections and attachment.

21-10-00

33. RUDDER BOOST TRANSDUCER - Inspect for security of attachment, leakage and security of electrical connectors and wiring. 34. FUEL FILTERS and SCREENS - Inspect the engine-driven high pressure fuel pump filters as instructed in the appropriate engine maintenance manual.

Page 226 May 1/10

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P&W

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

P.

LANDING GEAR RETRACTION

ATA/GAMA REFERENCE

MECH

INSP

1. RETRACT MECHANISM NOTE Since battery voltage is not sufficient to properly cycle the landing gear, use only an exterior power source capable of delivering and maintaining 28.25 ±0.25 volts throughout the extension and retraction cycles when performing the landing gear retraction inspection. When cycling the landing gear with the power pack, allow a one minute cooling period between cycles and a five minute cooling period every five cycles. Also, an exterior supply of dry air at 18 to 20 psi must be applied to the fill reservoir to prevent cavitation. If an exterior air supply is not available, us an exterior hydraulic pressure source. a. Check hydraulic power pack and motor for proper operation.

32-30-00

b. Check retraction system for proper operation of all components through at least two complete cycles.

32-30-00

c.

32-30-00

Check for unusual noises and evidence of binding.

2. DOORS and LINKAGE a. Check door for damage, operation and fit.

32-30-00

b. Check door linkage for wear, damage and rigging.

32-30-00

3. POSITION INDICATORS

32-60-00

a. Check for security and proper operation of switches.

32-60-00

b. Clean terminals and connectors as required. c.

Check wiring for damage and security of connection.

4. WARNING HORN - Check operation.

32-60-00

5. DOWNLOCK MECHANISM a. Check locking mechanism for positive engagement in extended position.

32-10-00 32-20-00

b. Check downlock switch for proper adjustment.

32-60-00

6. SAFETY SWITCH - Check for security and proper operation.

32-60-00

7. ACTUATOR - Check for noise, binding and proper rigging.

32-30-00

8. EMERGENCY EXTENSION - Check system for freedom of operation and positive engagement of downlocks.

32-30-00

CAUTION Do not continue operation after receiving a gear-down indication on all gears.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q.

OPERATIONAL INSPECTION

ATA/GAMA REFERENCE

MECH

INSP

NOTE The following Operational Inspection procedures are to be applied during start and run of the engine. Refer to the Super King Air B300 and B300C Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual for the engine start and run procedures. 1. FIREWALL SHUTOFF VALVES - Check for proper operation. 2. CROSSFEED FUEL VALVE - Check for proper operation. 3. STANDBY PUMPS - Check for proper operation. 4. STARTER - Check for proper operation. 5. IGNITION - Check for annunciator panel light illumination 6. ENGINE OIL TEMPERATURE and PRESSURE - Check for proper pressure and temperature limits. 7. FUEL QUANTITY GAGES - Check operation. 8. INTERSTAGE TURBINE TEMPERATURE - Check for correct limits on engine start. 9. VACUUM SYSTEM INSTRUMENT - Check for correct limits. 10. PNEUMATIC PRESSURE GAGE - Check for correct pressure. 11. PNEUMATIC SYSTEM SHUTOFF VALVES - Check for proper operation. 12. GYRO INSTRUMENTS - Check for erratic or noisy operation. 13. PROPELLERS - Perform flight idle torque check.

76-00-00

14. AUTOFEATHERING CHECK - Refer to AUTOFEATHER OPERATIONAL CHECK.

61-21-00

15. PROPELLER SYNCHROPHASER - Refer to the SYNCHROPHASER SYSTEM FUNCTIONAL TEST and confirm proper synchronization.

61-22-00

16. PROPELLER GOVERNOR - Check governor operation (including feathering and reversing).

76-00-00

17. IDLE RPM - Check for correct rpm (both high and low rpm).

76-00-00

18. AC INVERTERS (If installed) - Check for proper operation.

24-20-00

19. RUDDER BOOST - Check for proper operation.

Page 228 May 1/10

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POH

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued) 20. AUTOIGNITION

ATA/GAMA REFERENCE

MECH

INSP

74-00-00

a. Check for proper operation. b. Check for annunciator panel light illumination. 21. PROPELLER DEICER - Check for proper operation and cycling. Refer to Chapter 30-60-00 and the King Air Series Component Maintenance Manual.

30-60-00 CMM

22. INERTIAL ANTI-ICER ENGINE - Check for proper operation and rigging. 23. DEICE SYSTEM a. Check for proper operation and cycling. b. Functionally test tail and wing deice annunciator lights for operation. 24. BRAKE DEICE SYSTEM (IF INSTALLED) - Check for proper operation with engines running. 25. ELECTRICAL SYSTEM - Perform functional checks.

24-50-00

26. ENVIRONMENTAL SYSTEM - Check for proper operation in: a. Manual heat mode. b. Manual cool mode. c.

Automatic mode.

27. AUTOPILOT - Check for proper operation as outlined in the applicable Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement. 28. STALL WARNING - Check for proper operation. 29. GENERATORS - Check for output. 30. ENGINE FIRE DETECTORS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 31. ENGINE FIRE EXTINGUISHERS - Perform system test according to instructions found in the Super King Air B300 and B300C Pilot's Operating Handbook and FAA Approved Airplane Flight Manual.

A28

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

32. PRESSURIZATION SYSTEM - Check for proper operation NOTE Refer to the Super King Air B300 and B300C Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual and perform system test. 33. AUXILIARY FUEL TRANSFER JET PUMPS - Check for proper operation. 34. CONDITION LEVERS - Check for clean shutdown at IDLE-CUTOFF. 35. PITOT TUBE - Check for proper heating at the unit and for obstructions. 36. LANDING and TAXI LIGHTS - Check operation of all lights.

33-40-00

37. OUTBOARD WING LIGHTS (Right Side and Left Side) - Check operation of all navigation and strobe lights.

33-40-00

38. COCKPIT LIGHTS - Check operation of all cockpit lights.

33-10-00

39. EFIS COOLING BLOWERS (If Installed) - Check operation.

34-20-00

40. ELECTRIC ELEVATOR TRIM - Check for proper operation.

27-30-00

41. ENGINE and PROPELLER CONTROLS - Check for freedom of movement, full travel and friction lock operation.

76-00-00

42. PILOT’S and COPILOT’S SEATS and SEAT BELTS - Check seat adjustment mechanism and shoulder harness inertia reel for operation. 43. STATIC SYSTEM - Inspect alternate air valve for operation.

34-00-00

44. WINDSHIELDS - Perform heated operational check.

30-40-00

45. THRESHOLD LIGHT - Check for proper operation. 46. AUXILIARY ELECTRIC HEAT - Check for proper operation of the Electric Heat System. 47. CABIN and COMPARTMENT LIGHTS - Check for proper operation. 48. CABIN SEATS and SEATBELTS - Check seat adjustment mechanism and shoulder harness inertia reel for operation.

Page 230 May 1/10

5-22-02

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued)

ATA/GAMA REFERENCE

MECH

INSP

49. CABIN ENTRANCE DOOR (FL-1 and After) a. Check that folding steps do not fold too soon and that they fold properly without interference. b. Check cabin DOOR UNLOCK annunciator for proper operation. c.

Inspect cabin door damper for leakage and proper operation.

50. CABIN CARGO DOOR and CABIN ENTRANCE DOOR (FM-1 and After) a. Inspect door latching mechanism for operation and security of attachment. b. Check latching mechanism, folding steps and gas springs for proper operation. 51. EMERGENCY EXITS (With door installed and properly rigged) a. Check emergency release handles (inside and outside) and latch mechanism for operation. b. Check that latches open and close freely. 52. EMPENNAGE CONTROL SURFACES a. Check for freedom of movement. b. Check optional trim actuators and motors for smoothness of operation. 53. REAR FUSELAGE and EMPENNAGE LIGHTS - Check operation of all lights. 54. AILERON (Left Side and Right Side) - Check for freedom of movement. 55. AILERON TRIM TAB - Check trim tab actuator for smoothness of operation and attachment. 56. FUEL TANK HEATED VENTS (Left Side and Right Side) Check the operation of the heated vents. They should be warm to the touch.

28-10-00

57. STALL WARNING HEAT - Check for proper operation. 58. FLAPS and ACTUATORS (INBOARD, OUTBOARD, Left Side and Right Side) - Check flaps for noisy or erratic operation.

A28

27-50-00

5-22-02

Page 231 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Q. OPERATIONAL INSPECTION (Continued) 59. WING CENTER SECTION LIGHTS - Check operation of all lights.

ATA/GAMA REFERENCE

MECH

INSP

33-40-00

60. ENGINE INDUCTION SYSTEM (Left Side and Right Side) Check the inertial vane and bypass door for movement with the main and standby actuator motors.

R.

61. EXTERNAL POWER RELAY - Check for proper operation.

24-40-00

62. ELECTRIC HEATER POWER RELAYS - Check for proper operation.

21-40-00

POST INSPECTION ITEMS 1. AIRPLANE CLEANED and SERVICED AS REQUIRED.

12-00-00

2. LUBRICATE AS NECESSARY.

12-20-00

3. ENGINES INSPECTED AFTER GROUND RUN-UP OR FLIGHT TEST - Check for oil leaks, security and attachment of all components 4. AIRWORTHINESS DIRECTIVES and SERVICE BULLETINS Must be reviewed and complied with as required. 5. ADDITIONAL INSPECTION REQUIREMENTS - Make sure Chapter 5, Special Inspection, and Airworthiness Limitations Manual (P/N 130-590031-211) requirements are complied with at the appropriate intervals. 6. IN-FLIGHT WORKSHEETS DISCREPANCIES - All discrepancies noted by the pilot must be checked and corrected as required. 7. EMERGENCY LOCATOR TRANSMITTER - Check for proper operation and make sure ELT is ARMED before returning airplane to service.

25-60-00

8. OXYGEN SYSTEM PRESSURE - Check for proper pressure. 9. EMERGENCY and SURVIVAL EQUIPMENT (IF INSTALLED) - Make sure all necessary emergency and survival equipment is installed in the airplane and is serviceable. 10. PLACARDS - Determine that all required placards are in place and legible.

11-20-00 POH

11. LOGBOOK ENTRY - Make sure that log books are filled out properly.

Page 232 May 1/10

5-22-02

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION COMPLETED I certify that Complete Inspection was performed in accordance with the Model B300/B300C Inspection Program and that the airplane is approved for return to service: DATE: ............................................................................................................................................................ MECHANIC: .................................................................................................................................................. CREW CHIEF: ............................................................................................................................................... QUALITY CONTROL INSPECTOR: ..............................................................................................................

A28

5-22-02

Page 233 May 1/10

RBytheMI

nircraft

Campany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTINUOUS CORROSION CONTROL INSPECTION

MAINTENANCE PRACTICES

PURPOSE AND USE NOTE: Additional

inspections may be required by engine or propeller manufactures in their manuals. Refer to the unscheduled maintenance checks portion of the supplier issued manuals to ensure continued airworthiness.

a optional guideline for corrosion control inspections to be used during a scheduled inspection. Use inspection is dependent upon the operational environment. It is recommended that accessible areas applicable to this inspection be inspected during the phase of the Extended or Continuous Inspection Program that

This checklist is

of this

is in progress.

Internal portions of the wings, fuselage preventatives at the appropriate inspection. a.

Perform the corrosion

b.

Action must be taken and corrosion

c.

The corrosion

d.

The

areas

and empennage

inspection if required by

or

to be

inspected

and treated with

applicable

the environmental conditions encountered.

discrepancies

that need to be treated

are

corrected

painted

prior to

the next

inspection.

should be noted.

airplane landing gear and exposed areas must be lubricated in accordance with Manual instructions after each aircraft washing.

applicable Maintenance

Aircraft S/N Aircraft No.

Inspection

Date

Aircraft T.T.

CONTINUOUS CORROSION CONTROL INSPECTION A.

WINGS

IVIECH NOTE

It is the intention of this

inspection

that the

LH

access/inspection panels only

INSP

RH

be removed if

evidence of corrosion is found. 1.

SKIN

Inspect skin for corrosion and paint for blistering and scratches. Check or missing rivets. If corrosion is found, inspect adjacent structure.

for loose 2.

FLAP AND AILERON WELL AREA

Inspect for corrosion and paint for blistering

and scratches. Areas should be clean. 3.

ACCESS/INSPECTION PANELS

Check for corrosion

hardware. If corrosion is found, remove the structure. Replace all corroded hardware.

nm

panel

on

panels and attaching adjacent

and check the

5-23-00

Apr

28/06Page

1

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTINUOUS CORROSION CONTROL INSPECTION A. WINGS

(Continued)

MECH LH

4.

AILERON AND TAB

Inspect

skin for corrosion and

paint

for

blistering

and

Inspect

skin for corrosion and

paint

for

blistering

and

INSP

RH

scratches. 5.

OUTBOARD FLAPS scratches.

6.

FLAPTRACKS-

7.

FLAP ACTUATOR

8.

WINGLET

Inspectforcorrosion. Inspect attaching

hardware and rollers for corrosion.

Inspect attaching hardware for corrosion

and

paint for blistering and

scratches. 9.

FUEL VENTS AND DRAINS

10. FUEL FILLER CAPS

for

blistering

B.

for corrosion.

Inspect caps and surrounding area for corrosion and paint

and scratches.

11. DEICER BOOTS

scratches

Inspect

Inspect the boots

adjacent

for

secure

bond and

paint for blistering

and

to boots.

WING CENTER SECTION

MECH

LH 1.

SKIN loose

2.

Inspect for or

missing

corrosion and

paint

for

blistering

rivets. If corrosion is found, check

ACCESS/INSPECTION DOORS

INBOARD FLAPS

Inspect

structure.

Check for corrosion and condition of

skin for corrosion and

RH

and scratches. Check for

adjacent

blistering and scratches. Check for loose or missing rivets. check adjacent structure. Replace all corroded hardware. 3.

INSP

paint for

If corrosion is found,

paint for blistering

and

scratches.

C.

4.

FLAP TRACKS

Inspect for

5.

FLAP ACTUATOR

corrosion.

Inspect attaching hardware and

rollers for corrosion.

FUSELAGE 1.

SKIN

MECH

INSP

Inspect skin for corrosion and paint for blistering and scratches. Check or missing rivets. If corrosion is found, check adjacent structure.

for loose 2.

ACCESS/INSPECTION DOORS hardware. If corrosion is found,

Replace 3.

4.

Apr

28/06Page

2

Check for corrosion

remove

on panels and attaching panel and check adjacent structure.

all corroded hardware.

ANTENNAS

Inspect

leading edges

for

DRAIN HOSES

antenna bases for water

severe

tight

seal.

Inspect

antenna

erosion.

Inspect for

5-23-00

obstruction.

A20

RaYlIheOn

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTINUOUS CORROSION CONTROL INSPECTION C. FUSELAGE

(Continued)

INSP

MECH

INSP

MECH

INSP

for corrosion and obstructions.

5.

STATIC PORTS

6.

RELIEF TUBE

7.

AVIONICS

8.

FLIGHT CONTROL CABLES

Inspect

MECH

Inspect outlet

area

for corrosion.

and hold-down racks for corrosion.

Inspect components

Inspect for chaffing, security, corrosion and

lubrication. 9. D.

BULKHEADS

EMPENNAGE 1.

Inspect empennage and flight control surface skins for corrosion and blistering and scratches. Check for loose or missing rivets. If corrosion found, check adjacent structure.

SKIN

paint is 2.

3.

for

DEICER BOOTS

Inspect boots for cracks and bond scratches adjacent to boots. ELEVATOR BRACKETS corrosion.

Replace

Inspect

brackets and

ELEVATOR TRIM TAB

Inspect

5.

DRAIN HOLES

for obstructions.

6.

RUDDER BRACKETS

7.

RUDDER TRIM TAB

8.

FAIRINGS

9.

and

paint for blistering and

attaching

hardware for

if corroded.

4.

Inspect

Inspect

trim tab and

brackets and

attaching

hardware for corrosion.

attaching

hardware for corrosion.

Inspect trim tab and attaching

Inspect fairings for condition

Inspect attaching

E.

for water traps.

Inspect

and

hardware for corrosion.

paint for blistering

and scratches.

hardware for corrosion.

ANTENNAS

Inspect

leading edges

for

tight seal. Inspect antenna Inspect attaching hardware for corrosion.

antenna bases for water

severe

erosion.

COWLING AND TRUSS

LH

NOTE Panels

or

cowlings need not inspected.

be removed unless corrosion is discovered and

RH

adjacent

structure must be i.

COWLING SKIN

Inspect for corrosion and paint for blistering and scratches. If adjacent structure. Check for loose or missing rivets.

corrosion is found, check 2.

AIR INLET

blistering

A20

Inspect inlet and surrounding

area

for corrosion and

paint for

and scratches.

3.

DRAIN HOLES

Check for obstruction.

4.

LOWER COWLING

5.

COWLING ATTACHING HARDWARE

Inspect for

sediment and water traps.

Inspect for corrosion.

5-23-00

Apr

28/06Page

3

Ral~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL CONTINUOUS CORROSION CONTROL INSPECTION E. COWLING AND TRUSS

MECH

(Continued)

LH

TRUSS TUBING

7.

CLAMPS ATTACHED TO TRUSS corrosion and

F.

Inspect for corrosion and paint for blistering

6.

Inspect

truss area around

for

clamps

chafing. MECH LH

2.

Inspect stacks

EXHAUST STACKS

Inspect

RH

and scratches.

POWER PLANT

1.

INSP

and

INSP

RH

hardware for corrosion.

attaching

stacks for cracks.

ENGINE CONTROLS

Inspect controls, bolts, nuts,

cotter

pins

and safeties for

corrosion and lubrication.

NOTE

Special 3.

G.

FIRESEALS

attention should be made to the

cam

box.

Inspect for condition. MECH

PROPELLERS

LH 1.

BLADES

INSP

RH

Inspect for corrosion; dress if necessary. Inspect paint for blistering

and scratches. H.

PILOT’S COMPARTMENT 1.

INSTRUMENT PANEL

Inspect paint for blistering

and scratches and

MECH

INSP

MECH

INSP

attaching

hardware for corrosion and cracks. 2.

3.

CONTROL COLUMN

UPHOLSTERY PANELS corrosion. Clean

I.

Inspect for corrosion.

as

Inspect

for tears and

SEATS

5.

SEAT TRACKS

hardware for

necessary.

Inspect frames for corrosion

4.

attaching

Inspect tracks

and

and

paint

for

blistering

and scratches.

attaching hardware for corrosion.

CABIN COMPARTMENT 1.

UPHOLSTERY PANELS corrosion. Clean

as

Inspect for tears and attaching

necessary.

Inspect frames for corrosion and paint for blistering and scratches.

2.

SEATS

3.

SEAT TRACKS

Inspect tracks

4.

TOILET

for proper service and

Apr 28/06Page

4

hardware for

Inspect

5-23-00

and

attaching

hardware for corrosion.

spillage

or

leakage.

A20

RBytheMI

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTINUOUS CORROSION CONTROL INSPECTION J.

MAIN LANDINGGEARAREA

MECH LH

1.

WHEEL WELL AREA

INSP

RH

Inspect skin for corrosion and paint for blistering and or missing rivets. If corrosion is found, check

scratches. Check for loose

adjacent 2.

structure.

LANDING GEAR DOORS

Inspect for corrosion and paint Inspect hinges for loose or missing rivets.

scratches. 3.

for

blistering

or

DRAG LEG ASSEMBLY

inspect for corrosion and paint for blistering or Inspect attaching bolts for corrosion and lubrication. If corrosion is found, remove and inspect the bolts. scratches.

4.

5.

Inspect components for corrosion Inspect strut for leakage.

STRUT AND BRACE ASSEMBLY for

and scratches.

blistering

WHEEL ASSEMBLIES

and

Inspect

for corrosion and

paint for blistering and

Inspect

for corrosion and

leakage.

paint

scratches.

K.

6.

BRAKE ASSEMBLIES

7.

WIRING AND PLUMBING

Inspect for corrosion, chafing

or

bare spots.

NOSE LANDING GEAR AREA 1.

WHEEL WELL AREA

MECH

INSP

MECH

INSP

Inspect skin for corrosion and paint for blistering and or missing rivets. If corrosion is found, check

scratches. Check for loose

adjacent 2.

structure.

LANDING GEAR DOORS scratches.

3.

Inspect hinges

Inspect for corrosion and paint or missing rivets.

for

blistering

or

for loose

Inspect for corrosion and paint for blistering or Inspect attaching bolts for corrosion and lubrication. If corrosion found, remove and inspect the bolts. DRAG LEG ASSEMBLY

scratches.

4.

STRUT AND BRACE ASSEMBLY for

5.

blistering

and scratches.

WHEEL ASSEMBLY

Inspect

Inspect

Inspect components strut for leakage.

for corrosion and

paint

for corrosion and

for

blistering

is

paint

and

scratches. 6. L.

WIRING AND PLUMBING

Inspect for corrosion, chafing

bare spots.

NOSESECTION 1.

RADOME

attaching 2.

SKIN loose

3.

Inspect for cracks

in the

hardware for corrosion.

paint and fiberglass structure. Inspect Replace any corroded hardware.

Inspect for corrosion and paint for blistering and scratches. Check for missing rivets. if corrosion is found, check adjacent structure.

or

ACCESS/INSPECTION DOORS hardware. If corrosion is found,

A2a

or

Inspect for corrosion on doors and attaching doors and inspect adjacent structure.

remove

5-23-00

Apr 28/06Page

5

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTINUOUS CORROSION CONTROL INSPECTION M.

NOSE AVIONICS COMPARTMENT

Inspect skin

1.

DOORS

2.

DOOR SEALS

for corrosion and

corrosion and

INSP

MECH

INSP

paint for blistering and scratches.

Inspect seals for condition

HYDRAULIC BRAKE SYSTEM

3.

MECH

and

sealing.

Inspect fluid reservoir

and

plumbing

for

leakage.

Inspect area for corrosion and paint for blistering and Inspect fasteners for corrosion. Replace if necessary. Inspect water traps. Clean and inspect the shelves.

AVIONICS BAY

4.

scratches. for

MOUNTING RACKS

5.

Inspect

area

rack and associated hardware for corrosion and

attachment.

Inspect for corrosion and security of attachment. Clean and inspect components.

6.

N.

AVIONICS

CORROSION TEMPORARY TREATMENT CHIPPED PAINT SURFACES

1.

(AMALGARD)

to all

chipped

Apply

corrosion

surfaces until the

preventive compound is treated and repainted.

area

Apply MIL-C-16173 to applicable portions of the phase of the inspection, i.e., exposed rod ends, hinges and

EXPOSED PORTIONS

2.

airplane

in this

swivels.

DISCREPANCIES

3.

inspection

Record all

checklist and

discrepancies on attached applicable publications.

corrosion control

INSPECTION COMPLETED I

certify

that

Program

a

Corrosion Control

and that the

airplane

is

Inspection approved

was

performed

in accordance with the Model B300/B300C

Inspection

for return to service:

DATE: MECHANIC:

CREW CHIEF: QUALITY CONTROL INSPECTOR:

Page

rpA6

28/06

5-23-00

A20

Raythwm

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

UNSCHEDULED MAINTENANCE CHECKS

MAINTENANCE PRACTICES

This

subchapter is assembled in chart form to allow a technician to perform checks for damage after operating the airplane in conditions which could require unscheduled maintenance. Specific conditions, such as lightning strikes, turbulent air penetration or hard landings, etc., are included. Inspection instructions are included for each of the conditions listed.

NOTE: Additional

inspections may be required by engine or propeller manufactures in their manuals. Refer to the unscheduled maintenance checks portion of the supplier issued manuals to ensure continued airworthiness,

I

OPERA TION IN A TMOSPHERES OF HIGH SAL T CONTENT

OPERATION IN ATMOSPHERES OF HIGH SALT CONTENT ITEM A.

INSPECTION REQUIREMENT

Engine Motoring Compressor Wash

Engines operated

in

a

INSPECTION INTERVAL

salty atmosphere should appropriate

be washed in accordance with

Engine

Daily

Maintenance Manual.

OPERA TION IN A TMOSPHERES OF HIGH INDUSTRIAL AIR POLLUTION

OPERATION IN ATMOSPHERES OF HIGH INDUSTRIAL AIR POLLUTION ITEM A.

Engine Motoring Compressor Wash

INSPECTION REQUIREMENT When there is

loss of

engine performance ingestion of air pollution deposits, perform wash procedures in accordance with appropriate Engine Maintenance Manual. a

attributed to

Inspect

pso

INSPECTION INTERVAL

for corrosion

As

required

As

required

5-50-00

I

1

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WHEN OPERA TING IN AREAS OF HIGH DUST CONTENT

WHEN OPERATING IN AREAS OF HIGH DUST CONTENT

INSPECTION REQUIREMENT

ITEM

I

A.

B.

Nose

LandingGear

Clean off and

Shock Strut

surfaces.

InstrumentAir Filters

Replace

INSPECTION INTERVAL

wipe dry exposed polished

Routine

instrument line

100 hours under

supply filters at or before extremely dusty conditions.

As noted

CAUTION Disconnect the lines to prevent

I

C.

I

D.

autopilot barometric altitude sensor line before applying damage to the barometric altitude sensor.

Pitot and Static Lines

Check for obstructions

by applying

reverse

air pressure to

.stnemurtsniria

neces ary.Inspect

for obstruction of air flow.

static

reverse

pressure (not to exceed 20 psi.) to the ends of the pitot and static lines disconnected from the

Environmental AirFilter

pitot and

Replace

200 Hours

if

As

or as

required

required

WHEN OPERA TING IN AREAS OF HIGH HUMIDIP/

WHEN OPERATING IN AREAS OF HIGH HUMIDITY

INSPECTION REQUIREMENT

ITEM A.

Floor Structure

1.

INSPECTION INTERVAL

Checkstructure underthefloorfor corrosion

by removing a floor panel and inspecting structure, especially channel

sections.

B.

1.

AftCabin

Removeaftcabin accesscoversand check for corrosion, bulkhead

C.

Wing

1.

Remove covers

especially

aft of

a

scheduled

but not

more

inspection,

than 6 months

apart. At

a

scheduled

but not

points,

wing

At

more

inspection,

than 6 months

apart.

andcentersection

access

and check for corrosion,

At

a

scheduled

but not

more

inspection,

than 6 months

apart. D.

Empennage

1.

Remove aft

fuselage

check for corrosion.

access covers

and

At

a

scheduled

but not

more

inspection,

than 6 months

apart.

Apr 28/06Page

2

5-50-00

A20

Raytheon

AiKraft

company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OPERATING FROM VERY SOFT OR UNUSUAL TERRAIN

OPERATING FROM VERY SOFT OR UNUSUAL TERRAIN INSPECTION REQUIREMENT

ITEM A.

Main

Landing

Gear check for cuts, wear, deterioration

1.

Tires

Visually

2.

Struts

Check strut inflation

3.

Wheels

.VV.~

U"V’’

as

noted in

Chapter

I

Routine

12.

inspect for abrasions, cracks chipped rims, bearings for wear, fretting and bluing; check seals for distortion, deterioration, proper fit, security and obvious

egamad,noisorroc

cylinders and associated damage and leaks Check

BrakeUnits

Check for evidence of Check discs for

plating

lines for obvious

overheating.

scoring, distortion, damaged

and evidence of

overheating.

Check surfaces for cleanliness, free from oil or grease deterioration. Check strut inflation as 5.

Shock Strut

noted in

Clean

Chapter

exposed

WheelWells

Every

I

100 hours

I

Routine

Every

100 hours

Every

200 hours

Every

100 hours

Every

100 hours

12.

surface of shock strut

clean cloth moistened with 6.

Routine

Remove and clean;

and

4.

INSPECTION INTERVAL

hydraulic

piston

with

fluid

foreign material (dirt, etc.) from wheel Inspect supports between main and aft in spars upper wheel well and the lift leg attach bracket at the main spar for deformation, cracks, Clean

wells.

As

required

etc.

B.

Nose 1.

Landing

Tires

Gear

Visually

check for cuts, wear, deterioration

Visually

check for obvious

Remove and clean. 2.

A20

Wheels

and

andI

Routine

damage.

Inspect for abrasions,

chipped rims, bearings for

Routine

I

cracks

wear, corrosion, for distortion, check seals and bluing; fretting deterioration, proper fit and security.

Every

I

100 hours

5-50-00

Apr 28/06Page

3

Ray~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OPERATING FROM VERY SOFT OR UNUSUAL TERRAIN

Check for obvious

exposed

damage

and leaks. Clean

surface of shock strut

piston with

hydraulic fluid. Chapter 12.

cloth moistened with

inflation 3.

INSPECTION INTERVAL

INSPECTION REQUIREMENT

ITEM

ShockStrut

as

noted in

Check for correct extension

as

clean

Check strut

noted in

Chapter

32 of this Maintenance Manual.

Thoroughly clean and inspect for leaks, damage and security. Service as necessary.

I 4. 5.

i

Fork

Assembly

Check for cleanliness and obvious

Nose Wheel

Check for obvious

Steering

connections for

6.

Actuator

7.

Actuator

Linkage

damage.

damage, associated damage.

Check for excessive

play, safety

and

rods and

security.

Check actuator and support brackets for visible damage and condition. Inspect bracket for loose

missing rivets. Inspect cover and bottom assembly of actuator for cracks at mounting lug. or

Apr

28/065-50-00

(Continued)

Routine

Every

100 hours

Every

100 hours

Routine

Every

100 hours

Every

100 hours

Every

100 hours

uo

Ral~heon

nircrart Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION A~TER HARD LANDING

INSPECTION AFTER HARD LANDING

A.

General

INSPECTION INTERVAL

INSPECTION REQUIREMENT

ITEM

Appearance

inspection should be carried out after a hard landing and before the airplane is certified as ready for further flight. The inspections are conducted at two levels. The first level consists of determining if any external damage has occurred and looking for evidence of internal structural failure. The second level is concerned with a more detailed inspection of any damage areas which were indicated in the findings of the first level inspection. If it is determined by the first level inspection that there is no damage to the airplane, it is not necessary to proceed to the second level inspection.

This

WARNING

though "wrinkles" in the wing negligible, a close inspection of the Even

or

fuselage skin surface may be slight enough to be considered supporting structure may reveal serious damage.

as

internal

FIRST LEVEL B.

LandingGear

tires for excessive wear,

Inspect

splits

in the

After hard

Landing

After hard

Landing

After hard

Landing

After hard

Landing

After hard

Landing

between main and aft spars in upper wheel well and the lift leg attach bracket at the main spar for deformation, cracks, etc.

After hard

Landing

landing gear attach points.

After hard

Landing

tread, bottoming

out or

folding

over

Check the wheels for flat spots

or

the side walls.

cracked

castings. Check shock struts and attachment cracks

Inspect hydraulic brake

Inspect downlock, drag linkage for damage. Inspect landing gear

lugs

for

lines for leaks.

link and gear door retract

actuator attachment

lugs.

I I I

i

Inspect supports

Inspect

areas

around

5-50-00

Apr 28/06Page

5

RBYtheOn

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER HARD LANDING

INSPECTION REQUIREMENT

ITEM B.

Landing

Gear

(Continued)

(Continued)

Inspect the structure 1.

main

as

landing

gear

drag

INSPECTION INTERVAL

brace support

follows:

Placethe

After hard

Landing

airplaneonjacks.

Disconnect the upper drag brace from airplane structure in both the LH and

2.

the

RH wheel wells. 3.

a flashlight and mirror, inspect all drag brace support structure for possible cracks, particularly at the lower

Using

of the

radius of the U-channel where it attaches to the main spar.

If cracks

4.

are

suspected

but

defined, the suspect

are

not

should clearly be dye penetrant inspected, using visible dyes as outlined in AC43.13.1A/2A. If cracks

5.

are

found,

Aircraft Technical

findings If

6.

no

area

contact Raytheon Support and report the

for evaluation.

cracks

are

found, reinstall the drag

brace.

Raytheon Aircraft Company recommends that airplanes having experienced severe, or hard landings or other abnormal landing incidents which may have placed undue stress on the landing gears, are to be inspected within the first 100 service hours after such hard landing and at each 600 service hours thereafter.

Airplanes having received repairs in this area, upon Raytheon Aircraft Company recommendations, are exempt from this inspection except in the event of a future hard or abnormal landing incident.

I

C.

external skin surfaces for distortion, loose

tcepsnI.stevir

Nacelles or

missing

Check or

cowling damage.

attachment

fittings for alignment

Inspect engine control cables for smooth operation and check plumbing and wiring security and attachment.

Apr 28106Page

6

5-50-00

for

After hard

landing

After hard

landing

After hard

landing

nlo

Ray~hwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER HARD LANDING

INSPECTION INTERVAL

INSPECTION REQUIREMENT

ITEM

C. Nacelles

(Continued)

(Continued)

Inspect engine support

mounts for cracks

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

Check external skin surface the entire length for cracks, abnormal wrinkles and loose or

After hard

landing

Inspect empennage and control surfaces for

After hard

landing

Check

propeller spinner

and

evidence of interference with

Inspect

backplate for cowling.

wheel well structure for

cracks. Check

surrounding

damage or the landing

tpoints. nemhcattaraeg

D.

Wing CenterSection

Inspect

area

external skin surface

(upper

gnissim)rewol

Inspect plumbing, wiring and actuators damage and security of attachment. of E.

OutboardWing

Panels

fuselage

for

rear

damage

spat

and

on

or

for

the lower side

alignment.

Inspect external wing surface skin for cracks, or missing rivets.

abnormal wrinkles and loose

access

tcepsnI.la

internal structure and fuel cells

and

F.

Fuselage Nose Section

wiring for security

or

missing

area

I

surrounding

Inspect avionics, radar antenna, wiring plumbing for security and attachment. Fuselage Center Section

of

rivets.

Check wheel well structure and gear attach point for damage.

G.

through

Check external skin surface for cracks, abnormal wrinkles and loose

and

Inspect external skin surface for cracks, abnormal or missing rivets.

wrinkles and loose

cracks.Inspect H.

Fuselage Aft Section

around cabin windows for structural

.stevirgnissim

freedom of movement.

A20

I I

and

for cracks, abnormal wrinkles and loose rivets.

Check keel, front and

I

or

tips of propellers

.egamadrof

structural failure. Check

5-50100

Apr

I I I I I I I

I

281QgPage

7

RBYtheOn

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER HARD LANDING

(Continued) INSPECTION INTERVAL

INSPECTION REQUIREMENT

ITEM SECOND LEVEL

NOTE

loading may be transmitted along one structural member to another, carefully inspect supporting structure in any damaged area found in the first level inspection

Because shock

rounding I.

and

Landing

Place the

Gear

airplane on jacks and

check shock strut

for free up and down movement. Remove the tires and broken

inspect internally for cuts or

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

areas.

Disassemble and examine wheels for cracks

or

distortion.

Visually inspect

axle with

suspect, dye

check

Remove and

replace

or

10-power glass.

If

magnaflux.

or

the

sur-

magnaflux the landing

gear attach bolts, check bolt holes for cracks

or

elongation. Remove and

replace

or

magnaflux drag

link bolts

and supports. Make J.

landing gear

retraction test.

tips of propeller have been damaged, refer to Engine Maintenance Manual for engine inspection procedure for propeller strike. If

Nacelles

the

Inspect

areas

surrounding

the

engine

mounts.

Check the internal structure of the wheel well for cracks

Test K.

Wing CenterSection

or

damage.

plumbing

and

wiring

Remove floorboards and

for proper access

operation.

plates

and

inspect spar and keel structure for evidence of deformation or structural failure. the front and

Test plumbing,

rear

wiring, flaps, control cables, pulley

mounts and any other

for proper L.

OutboardWing

Panels

Test

plumbing and wiring

Inspect fuel damage.

Apr

28/06Page

8

5-50-00

system found in this

area

operation. for proper

cells and lines for

operation.

leakage and

p~o

RayTheon

AiKraff

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER HARD LANDING

Fuselage

Nose Section

baggage compartment floorboards supporting members for damage. Remove

inspect

the keel structure and

Inspect

wheel well structure and

areas

for

Fuselage

Center and Aft

Section

Examine

stringers,

deformation Test

or

plumbing

and

surrounding

of structural failure.

signs

Test avionics, radar antenna, wiring for proper operation. N.

INSPECTION INTERVAL

INSPECTION REQUIREMENT

ITEM M.

(Continued)

plumbing

and

frames and side walls for

structural failure. and

wiring for proper

.egamad.noitarepo

Inspect heating

and air

conditioning

Examine the control cables and

ducts for

.noitarepota locations. Ensure

landing

I

After hard

landing

I

After hard

landing

After hard

landing

After hard

landing

After hard

landing

After hard

landing

I

pulley mountings

and check for clearance from structure

pass-through

After hard

a

smooth

I

REPAIR OF DAMAGE

variety and degree of structural damage which may be involved, the best repair or replacement findings of the individual airplane. If the hard landing inspection indicates that procedure serious structural damage has occurred, contact the Customer Support Department, Raytheon Aircraft Company, Due to the

must be based on the

Wichita Kansas, 67201 for assistance.

LOG BOOK ENTRY

Following a hard landing inspection, an entry covering the extent (if applicable) must be noted in the airplane permanent records.

~ao

of

inspection,

the

damage

and the

5-50-00

repair

Apr 28/06Page

9

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER ENCOUNTERING TURBULENT AIR

INSPECTION AFTER ENCOUNTERING TURBULENT AIR

ITEM A.

General

INSPECTION INTERVAL

INSPECTION REQUIREMENT

Appearance

airplane has been subjected to high G loading while flying through airplane is retumed to service. The inspection is conducted on two levels. The first level consists of determining if any external damage has occurred and looking for evidence of internal structural failure. The second level is concerned with a more detailed inspection of damaged areas which were indicated in the findings of the first level inspection. If it is determined by the first inspection that there is no damage to the airplane, it is not necessary to proceed to the second level inspection. inspection should

This

be carried out after the

turbulent air and before the

WARNING

though "wrinkles" in the wing negligible, a close inspection of the Even

or

fuselage skin surface may be slight enough to be considered supporting structure may reveal serious damage.

Determine that the airframe components

(nacelles, wings, fuselage

and

empennage)

are

in their normal

configuration.

i

FIRST LEVEL B.

Wing CenterSection

Inspect the external skin surface (upper and lower) for cracks, wrinkles and loose or missing rivets.

Inspect plumbing, wiring and actuators for damage and security of attachment.

I

Check the keel and the front and lower side of the

fuselage

for

rear

C.

Nacelles

spar on the and

damage

Check

After

cowling attachment fittings damage.

Inspect the engine support or

for

alignment

Inspect

mounts for

cracks,

structural failure.

10

5-50-00

structure in wheel well for

encountering

encountering

turbulent air

encountering

turbulent air After

encountering

turbulent air

Inspect engine control cables for smooth operation and check plumbing and wiring for security and attachment. cracks.

encountering

turbulent air After

deformation

Apr 28/06Page

After

Inspect the external skin surfaces for wrinkles and or missing rivets.

or

encountering

turbulent air

turbulent air

loose

I

After

After

alignment.

I I

as

internal

damage

or

After

encountering

turbulent air

After

encountering

turbulent air

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER ENCOUNTERING TURBULENT AIR

INSPECTION REQUIREMENT

ITEM

D.

Outboard

(Continued)

Wing

Panels

Inspect the top

and bottom

cracks, wrinkles and loose

Inspect aileron, or

INSPECTION INTERVAL After

wing surface for or missing rivets.

aileron tab and

flaps

for wrinkles

Inspect

Internal structure and fuel cells

access

panel openings,

Inspect plumbing Fuselage

Nose Section

and

through

for

security

After

of

Check external skin surface for cracks, abnormal

missing

or

or

failure.

Inspect avionics, antenna security and attachment.

Fuselage

Aft Section

and components for

entire

length of

the external skin

surface for cracks, stress wrinkles and loose missing rivets.

After

After

After

After

encountering encountering encountering

juncture of the fuselage and empennage.

encountering

turbulent air After

or

Check the empennage surfaces for damage and freedom of movement. Inspect for skin wrinkles at the

encountering

turbulent air

Inspect external skin surface for cracks, abnormal or missing rivets, Inspect the

I

turbulent air

wrinkles and loose G.

encountering

turbulent air

rivets,

Inspect area forward of windshield for evidence of

CenterSection

After

turbulent air

wiring

structural deformation

Fuselage

encountering

turbulent air

wrinkles and loose

F.

After

turbulent air

cracks.

attachment. E.

encountering

turbulent air

encountering

turbulent air

After

encountering

turbulent air

Check controls for freedom of movement.

SECOND LEVEL

NOTE

and

loading may be transmitted along one structural member to another, carefully inspect the surrounding supporting structure in any damaged area found in the first level inspection

H.

Wing Center

Because G

Section

Remove floorboards and the front and

access

plates

and

inspect spar and keel structure for evidence of deformation or structural failure. Test

rear

plumbing, wiring,flaps,

mounts and any other

for proper

~ao

operation.

control cables, pulley system found in this area

After

encountering

turbulent air

After

encountering

turbulent air

5-50-00Page

11

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER ENCOUNTERING TURBULENT AIR ITEM

I I I

I.

I

J.

I I

INSPECTION REQUIREMENT

Inspect

Nacelles

areas

Inspect

Panels

surrounding

the

engine

internal structure for cracks

Operational

OutboardWing

(Continued)

test

plumbing

If there is evidence of

and

or

INSPECTION INTERVAL After

mounts.

damage.

After

wiring. to the fuel cells

damage

or

fuel lines, remove the cells and inspect the fuel cell liners and liner support structure.

Operational

test the

plumbing

and

wiring, flap

actuator, aileron and tab mounting. K.

Fuselage Nose Section

Remove the floorboards and structure and

supporting

inspect

I I I

the keel

members for

damage.

equipment for loose, broken or mountings.

Operational test the avionics, plumbing and wiring. L.

Fuselage Section

Centerand Aft

Examine

stringers,

deformation

or

Operational

test

radar antenna,

frames and side walls for

Inspect heating damage,

and air

and

wiring.

conditioning

Examine the control cables and

Apr

5150100

air

encounteringturbulent

air

encountering

turbulent air After

encountering

After

encountering

turbulent air After

encountering

turbulent air

After

encountering

locations. Ensure

After

encountering

turbulent air

ducts for

After

After

encounteringturbulent

air

encountering

turbulent air

pulley mountings

and check for clearance from structure at

pass-through operation.

encounteringturbulent

turbulent air

structural failure.

plumbing

After

air

turbulent air

Examine any fixed cracked

After

encounte~ngturbulent

a

smooth

After

encountering

turbulent air

A20

Raytheon

Aircraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER ENCOUNTERING TURBULENT AIR

INSPECTION INTERVAL

INSPECTION REQUIREMENT

ITEM M.

(Continued)

tubes and bell

Inspect elevator pushrods, torque

Empennage

crank for

Inspect

encountering

I

turbulent air

damage.

the attachment of the vertical stabilizer

spars to the top of the

fuselage

After

for evidence of

Inspect skin surfaces missing rivets.

for condition and loose

I

encountering

turbulent air

damage.

After

or

encountering

turbulent air

Check structu re for cracks, loose and/or concealed

After

or

missing

rivets

After

encountering

I

turbulent air

damage.

Check rudder for freedom of movement and

After

encountering

turbulent air

attachment,

Check elevator for freedom of movement and

After

encountering

turbulent air

attachment.

Check trim tab actuators for smoothness of

operation and attachment. Check the wiring of the electrical trim tab actuator for connection, security

After

of attachment and condition. Check the electrical trim tab actuator for full travel and

encountering

turbulent air

security of

attachment. REPAIR OF DAMAGE Due to the

variety

procedure

must be based

serious structural

and

degree of

damage

on

the

structural

findings

damage

which may be involved, the best repair or replacement airplane. If the turbulent air inspection indicates that

of the individual

has occurred, contact the Customer

Support Department, Raytheon Aircraft Company,

Wichita Kansas, 67201 for assistance. LOG BOOK ENTRY

Following a turbulent air inspection, an entry covering the extent (if applicable) must be noted in the airplane permanent records.

of

inspection,

the

damage

and the

5-50-00

repair

Apr

28/06Page

13

Ral~hwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER LIGHTNING STRIKE

INSPECTION AFTER LIGHTNING STRIKE

INSPECTION

INSPECTION REQUIREMENT

ITEM

INTERVAL

CAUTION

Propellers must be inspected and/or replaced utilizing the Hartzell Standard Practices Manual 202A or subsequent prior to returning the airplane to service following any lightning strikes or other impact damage. A.

difficulty

inspecting the airplane, but in determining a strike has taken place. Most times, an exit location will show which has caused damage to the components. The entry point is most often the propeller. A darkened area in the propeller tip may be noticeable after a lightning strike. A 3- to 5-power magnifier will show slag at the bottom of a "nick" in the propeller blade. If a strike is suspected, inspect deep nicks in the blade. Damage after a lightning strike should be corrected utilizing the applicable propeller manufacturer procedure. Blade overhaul must be accomplished by a certified propeller At times, the

Propeller

is not in

if

After

lightning

strike

After

lightning

strike

After

lightning

strike

After

lightning

strike

After

lightning

strike

mechanic.

by light- After lightning replaced or overhauled. Woodward Service Bulletin 33574 or subsequent

Whenever the

propeller

has been struck

strike, the propeller governors Refer to

must be

revision. B.

Inspect

Engine

as

instructed in the

appropriate Engine

Maintenance

Manual. C.

Carefully inspect the exterior of the airplane. usually appear as a burned hole or as a

Fuselage, Empennage and Wing

will

Surfaces

or

Evidence of

a

strike

series of burned

holes in metallic surfaces. Plastic parts may be delaminated and/ deformed due to high internal pressures. Normally two or more

points will be found, the entry and the exit points. Antennas are frequently an entry point of lightning and should be carefully inspected for evidence of arcing, sooting or pitting. From

point

small holes

of entry, the strike usually spreads aft in a series of or burn marks. After points of entry and exit are

found, the structure between these points should be carefully

inspected. Attention should be given to hinges and hinge pins for possible pitting. Cables, pulleys, bearings, bolts and all bonding jumpers in the area should be inspected for possible damage. Antennas and electrical and electronic equipment should be visually checked for damage and functionally checked for operation. If the strike was near the fuel vent, all plumbing should be carefully inspected for damage. Steel components may exhibit magnetism and require degaussing so as not to affect compass systems.

Apr

5-50-00

A2()

Raytheon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE INSPECTION AFTER SUDDEN STOPPAGE

ENGINE INSPECTION AFTER SUDDEN STOPPAGE ITEM A.

Engine

INSPECTION REQUIREMENT

Inspect

as

instructed in the

INSPECTION INTERVAL After sudden

appropriate Engine

engine stoppage

Maintenance Manual. B.

C.

Propeller

Propeller

Governor

The

propeller governors should be overhauled or replaced as instructed in Woodward Maintenance Manual P/N 33048F or subsequent. Refer to Woodward Service Bulletin 33574 or subsequent. Whenever the

propeller

engine

has

a

After sudden

sudden stoppage, the

must be overhauled

or

replaced.

engine

stoppage After sudden

engine

I

stoppage

5-50-00Page

15

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I

INSPECTION AFTER DEPLOYMENT OF LANDING GEAR ABOVE CRITICAL SPEED CONDITION

INSPECTION AFTER DEPLOYMENT OF LANDING GEAR

I

ABOVE CRITICAL SPEED CONDITION INSPECTION REQUIREMENT

ITEM

INSPECTION INTERVAL

NOTE

inspection should be carried out after the landing gear doors have been deployed at an airspeed above the deployment speed and before the airplane is returned to service. The inspection will be conducted on two levels. The first level consists of determining if any external damage has occurred and looking for evidence of internal structural failure. The second level is concerned with a more detailed inspection of damaged areas which were indicated in the findings of the first level inspection. If it is determined by the first level of inspection that there is no damage to the landing gear door and surrounding structure, it is not necessary to proceed to the second level inspection. This

critical

WARNING

though wrinkles in gible, a close inspection Even

the surfaces

i

are

the skin surfaces may be considered

of the internal

in their normal

slight enough

to be considered as

structure may reveal serious

supporting configuration when

stowed

or

neglidamage. Determine that

deployed.

LEVEL

A.

General

Appearance

TSRIFgnidnal(

Determine that the airframe components gear and flaps) are in their normal configuration.

After landing gear doors been opened above critical

deepsevah condition.

B.

Landing Gearaoor

Inspect the skin panels for wrinkles, cracks and bond separation.

After landing gear doors have been opened above

deepslacitirc condition.

Inspect for

loose

or

missing rivets, bolts,

and

bearings. Inspect hinges, linkages, fittings

and support

damage, alignment and security attachments. Check required clearances and overcenter requirements. structure for

Check gear door free

Apr

28/065-50-00

play (Ref. Chapter 32).

~O

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER DEPLOYMENT OF LANDING GEAR

ABOVE CRITICAL SPEED CONDITION

(Continued) INSPECTION INTERVAL

INSPECTION REQUIREMENT

ITEM

SECOND LEVEL

I

NOTE Since loads may be transmitted along one structural member to another, damaged element found in the first level inspection.

carefully inspect

the

adjacent members

to any

A.

Inspection of Damaged Areas

Remove the skin

employing

panels

and conduct

inspection by

(acoustic, inspection). Inspect Repair or replace as of the damage.

nondestructive test methods

x-ray, and/or dye penetrant fastener holes for cracking. determined

by the

extent

After landing gear doors have been opened above critical

speed

I

condition.

of missing or loose fasteners, disassemble inspect holes and fittings for distortion of holes and cracking. Repair or replace accordingly as determined by the extent of damage. In

case

and

Hinges, linkages, fittings, bearings and support structure which exhibit damage, alignment, and/or security attachment will be disassembled if possible and inspected. Repair or replace accordingly as determined by extent of damage. Inspect gear door free play after all repairs, checks alignments have been made. Check operation of door from stowed through deployment (Ref. Chapter 32). Repair or replace accordingly as determined by extent of damage. and

REPAIR OF DAMAGE

Due to the

variety

and

degree of

structural

damage

which may be involved, the best repair or replacement procedure must be based on the

inspection findings of the individual airplane. If the preceding inspection indicates that serious structural damage has occurred, contact Raytheon Technical Support, Raytheon Aircraft Company, Wichita, KS, 67201, for assistance. LOG BOOK ENTRY

Following extent of

the inspection, an entry covering inspection, damage and repair (if

applicable)

nzo

must be noted in the

the

permanent records.

5-50-00Page

17

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER DEPLOYMENT OF FLAPS ABOVE CRITICAL SPEED CONDITION

INSPECTION AFTER DEPLOYMENT OF FLAPS

I

ABOVE CRITICAL SPEED CONDITION INSPECTION REQUIREMENT

ITEM

INSPECTION INTERVAL

NOTE

inspection should be carried out after the flaps have been deployed at an airspeed above the critical deployspeed and before the airplane is returned to service. The inspection will be conducted on two levels. The first level consists of determining if any extemal damage has occurred and looking for evidence of internal structural failure. The second level is concerned with a more detailed inspection of damaged areas which were indicated in the findings of the first level inspection. If it is determined by the first level of inspection that there is no damage to the flaps and surrounding structure, it is not necessary to proceed to the second level inspection.

This

ment

WARNING

Even

gible,

though a

close

the surfaces

i I

wrinkles in the skin surfaces may be considered slight enough to be considered as negliinspection of the internal supporting structure may reveal serious damage. Determine that

are

in their normal

configuration. LEVEL

A.

B.

General

Flaps

Appearance

TSRIFgnidnal(

Determine that the airframe components gear and flaps) are in their normal configuration.

After the

Inspect the skin panels for wrinkles, cracks, separation.

After the

and

bond

flaps

have

.noitidnocneeb

actuated above critical

flaps

speed

have been

actuated above critical

speed

condition.

Inspect for bearings.

loose

or

missing rivets, bolts,

and

Inspect tracks, screws, linkages, fittings, flap brackets, actuators, wing brackets and support structure for

damage, alignment

and

security

attachment. Check

phase alignment

between

Check correlation between

cockpit

Apr

28/065-50-00

adjacent flaps. flap position and

indicator.

P~O

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSPECTION AFTER DEPLOYMENT OF FLAPS ABOVE CRITICAL SPEED CONDITION

(Continued) INSPECTION INTERVAL

INSPECTION REQUIREMENT

ITEM

SECOND LEVEL

I

NOTE

maybe transmitted along one structural member to another, carefully inspect the damaged element found in the first level inspection.

Since loads to any

A.

Inspection Areas

of

Damaged

panels and conduct inspection by employing nondestructive test (acoustic, x-ray, and/or dye penetrant inspection). Inspect fastener holes for cracking. Repair or replace as determined by the extent of the Remove the skin

.egamadsdohtem

In

case

of

missing

or

After the

members

flaps

adjacent

have been

actuated above critical

speed

condition.

loose fasteners,

disassemble and inspect holes and fittings for distortion of holes and cracking. Repair or replace accordingly as determined by the extent of

damage.

Hinges, linkages, fittings, bearings and support damage, alignment, and/ or security attachment must be disassembled if possible and inspected. Repair or replace accordingly as determined by extent of damage. structure which exhibit

Inspect hinges, linkages, fittings and support damage, alignment, and security attachments. Check required clearances and over-center requirements. structure for

REPAIR OF DAMAGE Due to the

variety

and

degree

of structural

may be involved, the best repair or procedure must be based on the

damage which

replacement inspection findings of the individual airplane. If the inspection indicates that serious structural damage has occurred, contact Raytheon Technical Support, Raytheon Aircraft Company, Wichita, KS, 67201, for assistance. LOG BOOK ENTRY

Following the inspection, an entry covering the inspection, damage and repair (if applicable) must be noted in the permanent extent of

records.

5-50-00PagelS

I

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I

INSPECTION IN THE EVENT OF DEFORMED STEERING STOP

INSPECTION IN THE EVENT OF DEFORMED STEERING STOP

I

A.

Nose

landing gear

INSPECTION INTERVAL

INSPECTION REQUIREMENT

ITEM

Inspect the lower portion of the

nose

landing

gear

If

an

steering

external leak is visible from the side of the

upper

landing gear brace assembly, the part replaced.

nose

must be

evidence of fluid

fI.steering pots no

After

stop is deformed

for evidence of fluid leaks,

leakage

is found,

remove

the

Visually inspect the inner and outer sides of both stop support lugs on the aft side of the nose landing gear upper brace for cracks. If

I

a

crack is visible, replace the stop support brace assembly).

lugs

(upper If

no

evidence of cracks

are

detected

visually,

the inner and outer sides of both stop support lug areas using fluorescent penetrant.

inspect

If evidence of

I

a

support lugs (upper brace If

no

replace the stop assembly).

crack is detected,

evidence of cracks is detected

fluorescent penetrant,

replace

the

using steering stop.

installing the steering stop, peel shim as required to maintain a total clearance of 0.00 to

When

0.002 inch between the stop and brace. Install shim on each side of the steering stop to center the

stop between the lugs. minimum of

one

bolts, snug (finger tight) washer to allow

installation of cotter

pin.

Do not overtorque nuts.

When

using

Apr

28/062"2~,

5-50-00

installing a

nuts and

P~20

HAPT E R

DIMENSIONS AND AR EAS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 6 - DIMENSIONS AND AREAS TABLE OF CONTENTS SUBJECT

PAGE 6-00-00

Airplane Dimensions and Stations Diagrams - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . .1 6-50-00 Airplane Access Panels - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1

A27

6-CONTENTS

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

6-LOEP

1

Feb 1/10

6-CONTENTS

1

Feb 1/10

6-00-00

1 thru 6

Oct 31/06

6-50-00

1 thru 14

Feb 1/10

A27

6-LOEP

Page 1 Feb 1/10

Ral~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRPLANE DIMENSIONS AND STATIONS DIAGRAMS

DESCRIPTION AND OPERATION

chapter provides illustrations only, specifying overall exterior dimensions of the airplane (Ref. Figure 1), and specific station lines, water lines etc. (Ref. Figure 2). The illustrations aid maintenance personnel in locating various components on the airplane as referenced elsewhere in this manual.

This

A21

6-00-00

I

Rayrheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

46 ’8"

"i""

000 a

9’2"

I 1 .49"

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57’ 1 I

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4

I

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Airplane Dimensions (FL-1 and After) Figure 1 (Sheet 1 of 2)

Page

tcO2

31/06

8-00-00

A21

RaytheMI

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

06 ’8"

9’

OOio01

2"

14’

o

4"

0)11.5" I

16’

1

3"

57’ 11"

24.0’i/

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I 1 .58"

8’

5.79"

7" 500-c07-009 C

17’

2"

Airplane Dimensions (FAII-1 and After)

Figure

A21

1

(Sheet 2

of

2)

6-00-00

Oct

31/06Page

3

RaynReon

Aircraft Company

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

153.735 5.735 140.110

159.735 166.735 180.782

236.923

249.610 263.298

328.735276.0161 I

1´•I

(32.485

I121.Q66

223.235 213.907

FS 204.2387

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1111 li/

FS 259.9797

FS 204.562 WL 87.575

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WL 98.1577

WL 86.9498

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147.735 135.110

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FS 228.650

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r

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241.125-. 232.650 221.375 zll.sm 201.715

1

158.000 148.900

147.600

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PRESSURE BULKHEAD 47.500

1

i

260.250 280.875 270.125

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CANT 5TA

280.625 289.875 zss.lso 300.375

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PRESSURE BU~KHEAD_

jJ j j

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423.750

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371.250

360.750

350.000 DOOR HINGE (WL 81.00)

94.000 100.500

332.562

307.520 299.750

115.900 125.000 134.000

290.250

143.

150.

188.750 178.525 191

202.

204.400~

280.750 270.500 261.000 251.200 241.400 1.400 221.400 L-211.900

350603-7

M*IN SPAR

Station Diagram (FL-1 and After)

Figure 2 (Sheet 1

Oct

31/06Page

4

6-00-00

of

2)

A21

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

180.728

194.829 204.395

166.735

209.016

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153.735

223.235~

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i

I

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328.735 318.7

ATTACH POINTS BL 122.682

´•WING AT

II I II

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263.298 FS

111

58.000 66.000

46.500

132.485

82.000 90.225 98.197 107.684

WING 232.650

241.125

HORIZONTAL STABILIZER

250.650 FS

161.400-J

I

I

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289.875

1

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NACELLE

111,260.250

FS228.650

L--

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38 1 .750

360.750371

.25

350.000

343.250 332.812

325.875

319.437

84.000

312.500

94.000

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100.500 107.000 116.000

I i I II I I II

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I I

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I

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C

"21 1 .900

Station Diagram (FM-1 and After)

Figure 2 (Sheet 2

A21

of

2)

6I00-00

Oct

31/06Page

5

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 6-50-00

AIRPLANE ACCESS PANELS - DESCRIPTION AND OPERATION There are various panels throughout the airplane to allow entry into enclosed areas for maintenance and servicing purposes. These consist of access panels, floorboard panels, service doors and fairings. Figure 1 shows the fuselage access openings. Figure 2 shows the floorboard access openings. Figure 3 shows the wing center section access openings. Figure 4 shows the wing access openings. Figures 1 thru 4 also include a list of components and areas accessible through each panel.

A27

6-50-00

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Fuselage Access Openings (FL-1 and After) Figure 1 (Sheet 1 of 4)

Page 2 Feb 1/10

6-50-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Fuselage Access Openings (FL-1 and After) Figure 1 (Sheet 2 of 4)

A27

6-50-00

Page 3 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Fuselage Access Openings (FM-1 and After) Figure 1 (Sheet 3 of 4)

Page 4 Feb 1/10

6-50-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Fuselage Access Openings (FM-1 and After) Figure 1 (Sheet 4 of 4)

A27

6-50-00

Page 5 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Floorboard Access Openings (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) Figure 2 (Sheet 1 of 6) Page 6 Feb 1/10

6-50-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Floorboard Access Openings (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) Figure 2 (Sheet 2 of 6)

A27

6-50-00

Page 7 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1 2

36

3 4

35 34

5 6 7 8 9

33 32 COCKPIT / CABIN PARTITION 31 30 29 28 27 MAIN SPAR 26 25

10

11

24 23 22 21

12 20 13 14

19 18 17

15

16

FL06B 985649AA.AI

Floorboard Access Openings (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 2 (Sheet 3 of 6)

Page 8 Feb 1/10

6-50-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1. CONDENSER BLOWER. 2. REFRIGERANT PLUMBING AND ELECTRICAL WIRING 3. PILOT'S RUDDER LINKAGE, MASTER CYLINDER ATTACHEMENT, PARKING BRAKE VALVE, SHUTTLE VALVE, HYDRAULIC LINES, AND VACUUM LINES. 4. RUDDER PEDAL BELLCRANK, ELEVATOR BELLCRANK. CONTROL CABLE PULLEYS, VACUUM LINES, HYDRAULIC PLUMBING, AND CONDENSER BLOWER RELAY. 5. TRIPLE FED BUS AND DIODES, REFRIGERANT AND VACUUM PLUMBING AND CENTER BUS. 6. CONTROL SURFACE CABLES AND PULLEYS, REFRIGERANT AND VACUUM PLUMBING AND HEATED DUCT. 7. CONTROL SURFACE CABLES AND PULLEYS, AIR DUCTING, REFRIGERANT AND VACUUM PLUMBING, ENGINE CONTROL CABLES AND ELECTRICAL WIRING.

23. FLAP MOTOR GEARBOX, FLEXIBLE DRIVES, AILERON AUTOPILOT SERVO, DOOR SEAL PNEUMATIC VALVE AND SOLENOID VALVE, FLIGHT HOUR METER PRESSURE SWITCH, AND HEATED AIR DUCT AND FLAP.

8. CONTROL SURFACE CABLES AND PULLEYS, REFRIGERANT SERVICE VALVE, VACUUM PLUMBING AND BLEED AIR LINE.

28. ELECTRICAL PANEL CONTAINING PROP PITCH, FIRE EXTINGUISHER, AND EXTERNAL POWER CONTROL MODULES, GENERATOR CONTROL PANELS.

9. CONTROL CABLES AND VACUUM PLUMBING.

29. BLEED AIR LINE AND VENTURI, HEATED AIR DUCT AND POWER CONTROL CABLES. 30. BATTERY CHARGE MONITOR MODULE, CABIN TEMPERATURE CONTROLLER, NI SPEED, LOW PITCH AND ICE VANE MODULES, TIME DELAY ANNUNCIATOR ADVISORY AND DEICER TIMER MODULES, FUEL TRANSFER CONTROL MODULE, ANNUNCIATOR CONTROL MODULE, ANNUNCIATOR FAULT DETECTION MODULES, BLEED AIR PRESSURE TEST CONNECTIONS. 31. HEATED AIR DUCT BLEED AIR LINE. 32. VENT BLOWER RELAY AND CONTROL CIRCUIT BREAKER, AND RADIANT HEART RELAY. 33. TRIPLE FED BUS AND DIODES, BLEED AIR WARNING PRESSURE SWITCHES. 34. RUDDER PEDAL BELLCRANK, HEATING AND COOLING DUCTS, PNEUMATIC AND HYDRAULIC PLUMBING, BLEED AIR LINE RELAY (RH ONLY), AND BATTERY BUS.

10. AILERON QUADRANT, REFRIGERANT AND DEICER PLUMBING, DOOR SEAL LINE, CONTROL CABLE, PULLEYS AND CABLE SEALS, INSTRUMENT AIR LINE AND FLAP FLEXIBLE LINES. 11. CONTROL CABLES, DOOR SEAL LINE, REFRIGERANT, DEICER AND VACUUM PLUMBING. 12. CONTROL CABLES AND PULLEYS, ANTENNA, LEADS, HEATED AIR DUCT, AFT BLEED AIR HEATER SHUTOFF VALVE. 13. CONTROL CABLES AND PULLEYS. 14. CONTROL CABLES AND PULLEYS. 15. CONTROL CABLES AND PULLEYS AND FAIRLEADS. 16. CONTROL CABLES AND PULLEYS FAIRLEADS AND SEALS. 17. HEATED AIR DUCT AND DEICER PLUMBING. 18. HEATED AIR DUCT AND DEICER PLUMBING. 19. HEATED AIR DUCT AND DEICER PLUMBING. 20. PRIMARY PORT CONTROLLER, SECONDARY PORT CONTROLLER, CABIN POWER INVERTER, LIGHTING CONTROLLER, INPUT/OUTPUT CONCENTRATOR, CABIN TELECOM ROUTER, CALL ALERTER, AFT EVAPORATOR BLOWER AND BLOWER RELAY, AFT ELECTRIC HEATER AND ELECTRIC HEATER RELAY. 21. HEATED AIR DUCT AND DEICER PLUMBING. 22. HEATED AIR DUCT AND DEICER PLUMBING.

24. FLAP FLEXIBLE DRIVES, RUDDER BOOST PRESSURE TRANSDUCERS, CONTROL CABLES, CABLE SEALS, DEICER PLUMBING, DEICER PLUMBING BLEED AIR PRESSURE REGULATOR, CHECK VALVES BLEED AIR WARNING LINES, HEATED AIR DUCT AND EJECTER. 25. CENTER BUS RIGHT AND LEFT VOLTAGE REGULATORS, PROP DEICE TIMER. HIGH DEFINITION AUDIO/VIDEO (HDAV) DISTRIBUTOR. A-429 CONVERTER. 26. BLEED AIR PLUBING, HEATED AIR DUCT BLEED AIR LINE CHECK VALVE AND PLUMBING. 27. HEATED AIR DUCT, REFRIGERANT PLUMBING AND BLEED AIR LINE.

35. AIR DUCT TEMPERATURE SENSING ELEMENT, COPILOTS'S RUDDER PEDAL SHAFT, MASTER CYLINDER ATTACHMENT, SHUTTLE VALVE, BLEED AIR LINES, HEATED AIR DUCT WITH ELECTRIC HEATER AND HYDRAULIC PLUMBING. 36. VENT BLOWER FRESH AIR SOLENOID VALVE, EVAPORATOR ICING SWICH AND EVAPORATOR, DUCT OVERTEMPERATURE SWITCH.

FL06B 985648AA.AI

Floorboard Access Openings (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 2 (Sheet 4 of 6)

A27

6-50-00

Page 9 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Floorboard Access Openings (FM-1 and After) Figure 2 (Sheet 5 of 6)

Page 10 Feb 1/10

6-50-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Floorboard Access Openings (FM-1 and After) Figure 2 (Sheet 6 of 6)

A27

6-50-00

Page 11 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Wing Center Section Access Openings Figure 3 (Sheet 1 of 2)

Page 12 Feb 1/10

6-50-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

14.

HEAT EXCHANGER, BLEED AIR PLUMBING, BLEED AIR BYPASS VALVE, BLEED AIR BYPASS VALVE MICRO SWITCH (LH ONLY), COMPRESSOR CLUTCH CONTROL PANEL, COMPRESSOR CLUTCH VOLTAGE DROP RESISTOR, ELECTRONIC TIME DELAY PRINTED CIRCUIT BOARD, BATTERY AIR VENT LINE (RH ONLY), STARTER SOLENOIDS, BLEED AIR PLUMBING.

FUEL CONTROL PURGE VALVE, TRANSFER CONTROL MOTIVE FLOW VALVE, FIRE EXTINGUISHER PLUMBING, ENGINE CONTROL CABLES, FIREWALL ELECTRICAL CONNECTOR, PNEUMATIC LINE AND SOLENOID VALVE (LH ENGINE).

15.

LANDING GEAR BOLTS.

16.

BLEED AIR PLUMBING FLAP TORQUE SHAFT AILERON CONTROL CABLES, FLAP ACTUATOR AILERON TAB CABLES (LH ONLY), EMERGENCY BUS FUSES (RH ONLY)

4.

ACCESS TO NACELLE FUEL CELL, FUEL QUANTITY PROBE, FUEL PLUMBING, CHECK VALVE.

17.

FUEL OUTLET STRAINER AND DRAIN, CHECK VALVES, TRANSFER JET PUMP, FUEL SWITCH.

5.

FORWARD ELECTRICAL POWER DISTRIBUTION PANEL.

18.

EXTERNAL POWER RECEPTACLE.

19. 6.

AFT ELECTRICAL POWER DISTRIBUTION PANEL.

ELECTRICAL WIRING AND CONNECTORS, FUEL LINE, LOWER FORWARD WING BOLTS, EXTERNAL POWER RELAY (RH ONLY).

7.

BATTERY.

20.

LOWER AFT WING BOLTS.

8.

AUXILIARY FUEL SYSTEM FILLER.

21.

UPPER AFT WING BOLTS.

9.

AUXILIARY FUEL CELL ACCESS, FUEL QUANTITY PROBE.

22.

PLUMBING FITTINGS, PRESSURE SEALS, AND AILERON CABLE SEALS.

10.

FUEL QUANTITY PROBE.

23.

HYDRAULIC LANDING GEAR SERVICE.

11.

WHEEL WELL-HYDRAULIC, FUEL AND PNEUMATIC PLUMBING, POWER CONTROL CABLES, ENGINE FIRE EXTINGUISHER CYLINDERS, ELECTRICAL WIRING, FLAP RIGGING TERMINALS (RH ONLY).

24.

FLAP SWITCHES.

25.

FUEL FIREWALL SHUTOFF VALVE, ENGINE FIRE EXTINGUISHER PLUMBING, PNEUMATIC LINE AND SOLENOID VALVE, (RH ENGINE). FIREWALL ELECTRICAL CONNECTOR AND WIRING, AIR CONDITIONER PLUMBING (RH ONLY).

26.

ENGINE CONTROL CABLES, DEICER PLUMBING, HYDRAULIC PLUMBING, WIRE BUNDLES, INSTRUMENT AIR LINES, REFRIGERANT LINES (RH ONLY), AIR CONDITIONER HIGH AND LOW PRESSURE SWITCHES (RH ONLY).

1.

LANDING GEAR ATTACH BOLTS, DEICER PLUMBING, ELECTRICAL WIRING, FUEL LINE, EXTERNAL POWER RELAY (RH ONLY).

2.

FUEL PRESSURE SWITCH (MOTIVE FLOW VALVE). CHECK VALVE, WIRING BOLT, DEICE PLUMBING, EXTERNAL POWER RECEPTACLE (RH ONLY). WING DEICE PRESSURE SWITCH.

3.

12.

13.

OUTLET STRAINER AND DRAIN, STANDBY BOOST PUMP INLET STRAINER, PUMP DRAIN, RADIO FILTER, FUEL QUANTITY PROBE SUPPORT. HEAT EXCHANGER, BLEED AIR PLUMBING, BLEED AIR BYPASS VALVE MICRO SWITCH (LH ONLY), FUSE PANEL WITH SPARE FUSES, HYDRAULIC LANDING GEAR PUMP AND MOTOR (LH ONLY). COMPRESSOR CLUTCH CONTROL PANEL, COMPRESSOR CLUTCH VOLTAGE DROP RESISTOR, ELECTRONIC TIME DELAY PRINTED CIRCUIT BOARD (RH ONLY).

FL12B 002551AA.AI

Wing Center Section Access Openings Figure 3 (Sheet 2 of 2)

A27

6-50-00

Page 13 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Wing Access Openings Figure 4

Page 14 Feb 1/10

6-50-00

A27

CHAPTER

LIFTING AND

SHORING

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 7

LIFTING AND SHORING

TABLE OF CONTENTS

PAGE

SUBJECT 7-00-00

Lifting And Shoring Maintenance Hoisting the Airplane. Jacking

Practices

............201

7-CONTENTS

May

1/08Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

7-LOEP

1

May 1/08

7-CONTENTS

1

May

1/08

7-00-00

201 and 202

May

1/08

A24

Pages

7-LOEP

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

LIFTING AND SHORING WARNING: When

an

airplane

experienced abnormal landing gear procedures of any type, as a safety on jacks prior to performing any inspection or maintenance. three landing gears are down and locked prior to removing the aircraft from

has

precaution, place the airplane Make the CAUTION:

sure

that all

jacks.

Jacking of an airplane for the purpose of landing gear operation, inspection, servicing or maintenance should be accomplished within an enclosed building or hanger. In the interest of safety should if become necessary to jack the airplane in the open wind velocity in any direction and terrain variation must be

compensated for prior to jacking

the

airplane.

HOISTING ~HE AIRPLANE hoisting sling is not available from Hawker Beechcraft Corporation, however, a hoisting sling similar to the one shown in (Ref. Figure 201), or the equivalent, may be obtained or fabricated locally to lift the airplane should it become necessary. The hoisting sling shown is constructed of two nylon straps (4 inches or more in width) supported by a structural steel crossbar with cables for attachment to an overhead crane. The sling is to be designed to support approximately 33,000 pounds to make sure a high safety factor during hoisting. The straps of the sling encircle the nose and midsection of the fuselage when the airplane is being hoisted as follows: At the

present time

Place

a.

one

a

band at

Fuselage

Station 107.0 in the

Station 300.0 in the midsection of the b.

Attach the

c.

Guy

sling

d.

to the overhead crane at a

wing tip and wings. weight

ropes between the

any imbalanced

Remove all loose

nose area

of the

and the other band at

fuselage,

Fuselage

fuselage.

lift

position corresponding

point,

or a

to

Fuselage

person stationed at each

Station 198.0.

wing tip,

may be

required

to offset

in the

equipment from

the

airplane. Gently

take up slack in the hoist and lift the

airplane.

JACKING Each of the three

CA UTION:

jacks

used to lift the

airplane should

have

a

lifting capacity

of at least 7,000

pounds.

Jacking for landing gear operation should only be accomplished within an enclosed building or hanger. Should it become necessary to jack the airplane in the open, no more than one jack point should be utilized at

a

time. For

safety of personnel and

the

airplane,

terrain variations and wind

velocity in

any

direction must be considered prior to jacking the airplane in the open. CAUTION: The fuel must be

evenly distributed in

both

wings

to ensure

stability

while the

airplane

is

on

jacks.

airplane is provided with three jacking points to raise the airplane for servicing. The forward point is on the left opening near the aft end of the nose wheel doors. The aft points are on the rear spar just inboard of the each nacelle fairing. All three points are easily identified by the placarding titled, JACK PAD, adjacent to the jack points. The areas around the jack pads are unobstructed, to facilitate the use of jacks.

This

side of the wheel well

7-00-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PICK UP POINT TO CORRESPOND WITH F.S. 198.0

CONNECTING LINK

CABLE BAR

STRAP

9

AIRPLANE HOISTING SLING

F.S. 300.0

d

oD

4

PHLE~E

*FT STRAP

t3

F. S. 107.0

PLACE FWD STRAP HERE

JACK

(7000 POUND CAPACIP/)

350-17-23

Airplane Hoisting Sling and Lifting Figure 201

May

7I00-00

Jack

A24

CHAPTER

LEVELING AND VV EIGHING

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 8

LEVELING AND WEIGHING

TABLE OF CONTENTS

SUBJECT

PAGE 8-00-00

Leveling

and

Weighing

Maintenance Practices

................._

8-CONTENTS

.........201

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

8-LOEP

1

May

1/08

8-CONTENTS

1

May

1/08

8-00-00

201 and 202

May

1/08

A24

Pages

8-LOEPPage

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LEVELING AND WEIGHING The

I

MAINTENANCE PRACTICES

airplane must be operated within defined weight gravity (CG) be accurately determined.

and balance limits; therefore, it is essential that the

weight

and

center of

Most maintenance, other than weighing the airplane, requires the airplane to be placed on jacks in a level/flight attitude. When accomplishing these requirements as specified elsewhere in this manual, leveling procedures may be

accomplished

as

indicated in this

chapter.

airplane may be leveled by inflating or deflating the main or nose gear struts. To level the airplane laterally, use bubble level across the two inboard seat tracks and deflate the tire or strut on the high side of the airplane until

The a

airplane longitudinally, attach a cord and plumb bob to the upper Phillips-head (Ref. Figure 201 and 202), just forward of the cabin door on standard airplanes and just aft of the cargo door on cargo door equipped airplanes. Inflate or deflate the nose gear shock strut as required to pass the cord over the center line of a second Phillips-head screw directly below at W.L 91.0 (Ref. Figure 201) at the bottom of the door. Suspending the plumb bob in a container filled with light engine oil will dampen its movement. the bubble centers. To level the screw, located at W.L. 122.0

UPPER PHILLIPS HEAD SCREW W.L. 122.0

000?1

lo

LOWER PHILLIPS

CORD ------I

OJ

HEAD SCREW W.L. 91.0 PLUMB 80B

CONTAINER FILLED WITH

LIGHT ENGINE OIL

350-MU-23

Leveling (FL-1 and Atter) Figure 201

8-00-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

UPPER PHILLIPS

HEAD SCREW W.L. 122.0

00

o

LEVEL POINTS’ WICARGO DOOR

LOWER PHILLIPS HEAD SCREW

CORD

-I

W.L. 91.0

PLUMB BOB

O CONTAINER PILLED WITH LIGHT ENGINE OIL

350-604-33

Leveling (FM-1 and After) Figure 202

Page

800-00

A24

CHAPTER

TOVVING AND TAXIING

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 9

TOWING AND TAXIING

TABLE OF CONTENTS

PAGE

SUBJECT 9-00-00

Towing andTaxiing Special Tools. Towing.

nz4

Maintenance Practices.

...........201

9-CONTENTS

1/08Page May

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

9-LOEP

1

May

9-CO NTE NTS

1

May 1 /08

9-00-00

201 and 202

May

A24

Pages

1/08

1/08

9-LOEP

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TOWING AND TAXIING

MAINTENANCE PRACTICES

Towing the airplane on hard surfaces is accomplished using either a manual or tractor tow landing gear. No provision for towing the airplane by the main landing gear is provided,

bar connected to the nor

is

towing by

nose

the main

gear recommended. When

towing

with

who is familiar with

a

tractor

or

operating

always have a qualified vehicle operator, a person in the cockpit congested areas, wing observers (wing walkers) to make sure wing

other tow vehicle,

the brakes, and in

clearance of obstructions.

SPECIAL TOOLS Each tool listed in Chart 201 is Generic

though

or

locally

provided

as an

example of

equipment designed to perform requirements of the specification

the

manufactured tools which conform to the

a

specific

function.

may be used

even

not included in the chart.

Chart 201

Special Tool Name 1. Tow Bar

Tools and

Part Number

(manual)

Equipment Use

Supplier Hawker Beechcraft

50-590001

Corporation

Manually moving the airplane on the ground.

Wichita, KS 67201 2. Tow Bar

(tractor)

Hawker Beechcraft

50-590017

Corporation

Moving the airplane on ground by tractor tow.

the

Wichita, KS 67201

TOWING airplane is steered with the nose wheel when moving it by hand or with a tug, using a tow bar connected to the towing lugs on the upper torque knee fitting of the nose gear strut. Before moving the airplane, make sure the rudder locks have been removed, and position a person in the crew compartment to operate the brakes in the event of an emergency. When using a tug, observe the turning limits marked on the nose gear strut to prevent damage to the nose gear and steering linkage. When maneuvering the airplane by hand, do not push on the propellers or control The

surfaces.

CAUTION: Do not exceed the

on the nose gear strut at any time during ground handling block is designed to withstand only the loads normally imposed gear steering stop from the crew compartment; it is not made to bear the stress which may be exerted

turning

limits marked

operations. through steering through possibly exceeding turn stop limitations during towing. If the stop handling, damage to the steering linkage and nose strut could result. The

CAUTION: Never

n24

use

nose

the manual tow bar with

a

is

overcome

during ground

tow vehicle.

9-00-00

PMa Syel~:May

1/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

000

r]

IOR-´•ll

511-.90011

TRACTOR TOW BAR

50´•590001 MANUAL TOW BAA

350-17-21

Tow Bars

Figure

201

pWDI-l

Towing the Airplane Figure 202

Page

yaM202

1/08

9-00-00

A24

CMA P´•TER

PARKING, MOORING, STO RAG E, RTN TO SVC.

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 10

FLIGHT CONTROLS

TABLE OF CONTENTS

PAGE

SUBJECT 10-00-00

Parkingand Mooring- Descriptionand Operation SpecialTools and Recommended Materials.

.........1

.............1 ..1

Shock Strut Collar Fabrication 10-10-00

Parking-

...201

Maintenance Practices

Control Locks .203

Storage.. Engine Flight-Ready Storage(OTo7 Days) Short-Term Storage (8To28 Days). Intermediate-Term Storage (29To 90 Days). Long-Term Storage (91 Days and Longer) Airplane Battery Compartment

...........203

...........203 ....203 ......204

....205

Fuel Cells

Propellers Avionics ...........206

Instruments Seats

......206

Warning Unit Landing, Strobes, andTaxi Light. Flight Control Surfaces. Wing FlapTracksand Rollers Landing Gear Hydraulic System LooseToolsand Equipment Stall

.............206 ..206 ................206 ..........206 .......207 .207

Airframe

Grounding Removal From

Storage.

........207

10-20-00

..201

Mooring- Maintenance Practices Mooring For Normal Winds Mooring For Normal Winds. Mooring For HighWinds

a4

.......201 .....201 ........201

10-CONTENTS

May 1/08Page

1

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

10-LOEP

1

May

1/08

10-CONTENTS

1

May

1/08

10-00-00

1 thru 6

Mar 9/01

10-10-00

201 thru 209

May

10-20-00

201 thru 203

May 1/08

A24

Pages

1/08

1 O-LOEP

May

1/08Pagel

Ral~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PARKING AND MOORING

DESCRIPTION AND OPERATION

SPECIAL TOOLS AND RECOMMENDED MA TERIALS The

special

tools and recommended materials listed in Charts 1 and 2

meeting federal, military or supplier specprovided specifically prescribed by Raytheon Aircraft Company. The only in included have these tested charts been and products approved ior aviation usage by Raytheon Aircraft Company, the with the or by by compliance supplier, applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification listed may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used. ifications

for reference

are

and

are

as

not

SHOCK STRUT COLLAR FABRICATION A hardwood collar is used to act

as a

support for each landing gear shock

strut to

prevent the

strut from

bottoming

when deflated for storage. Make the collar from a square of hardwood at least 4.75 inches on a side and at least 0.75 inches thick. At the center of the square, cut a hole 2.875 inches in diameter through the wood. Cut away one side of the square

along

lines

tangent to the hole

and

parallel

to the sides of the square as shown in

Figure 1,

Sheet

CHART1

SPECIAL TOOLS AND EQUIPMENT TOOL NAME 1.

PART NO.

Controllocks

101-590016-7

SUPPLIER

USE

Raytheon Aircraft Company I

Prevent movement of controls

9709 E. Central

when

parked.

Wichita, KS 67201 2.

Propellersling exhaust

FL-126; FM-1 3.

Bleed

and

covers

101-590098-51

(FL-1 FM-8)

Aircraft

Company I Prevent movement of propellers when parked and entry of debris into exhaust stacks.

Wichita, KS 67201

to

air´•inletscoop

Raytheon

9709 E. Central

to

101-590107-1

Raytheon

Aircraft

Company I

9709 E. Central

plug

Prevent entry of debris into bleed air system.

Wichita, KS 67201 4.

Shock strut collar,

Fabricate

Prevent shock strut from

locally

hardwood 5.

bottoming

Air inletcover

101-590098-7

Raytheon

Aircraft

when deflated.

Company I Prevent entry of debris

9709 E. Central

into

engines.

Wichita, KS 67201 6.

Pitottube

cover

101-590105-1

Raytheon

Aircraft

Company I

9709 E. Central

Prevent entry of debris into

pitot

system.

Wichita, KS 67201 7.

Main

gearstrutlimiter

115-590023-1

Raytheon

Aircraft

Company i

9709 E. Central

Limit travel of main

landing gear

shock struts.

Wichita, KS 67201

nln

10-00-00

Mar

9/01Page

1

I

Ral~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL CHART1 SPECIAL TOOL NAME 8.

Nose

gearstrutlimiter

TOOL’S

PART NO.

AND EQUIPMENT

USE

SUPPLIER

paytheon

115-590035

Aircraft

Limit travel of

Company I

nose

landing gear

shock struts.

9709 E. Central

Wichita, KS 67201 9.

Raytheon Aircraft Company I

Prevent movement of

and after; FM-9 and

9709 E. Central

when

after)

Widhita, KS

Propellersling (FI-127

10. Exhaust

covers

(FL-127

and after; FM-9 and

130-590004-1

propellers

parked.

67201

130-910003-1

Raytheon

130-910003-2

9709 E. Central

Aircraft

Company I

Prevent

entry of debris into

exhaust stacks.

Wichita, KS 67201

after)

CHART 2 RECOMMENDED MATERIALS MATERIALS

SPECIFICATION

PRODUCT

SUPPLIER

1.

Desiccant(&oz. bags)

MIL-D-3464

Obtain

locally

2.

Humidity

MS20003

Obtain

locally

3.

Moisture Barrier

MIL-B-1 21

Obtain

locally

4.

Preservative Oil

MIL-L- 6081, Grade

Obtain

locally

H3B03

Obtain

locally

Refertochapterlefor

Obtain

locally

Obtain

locally

Obtain

locally

Indicator

1

I

1010 5.

BoricAcid

6.

Fuel, Engine,

Jet

Recommended

F-30,F-34),

A(NATO Jet A-1

(JP-5, NATO F-42), (JP-4, NATO

fuel Brand and type

designation

Jet B

F-40), MIL-T-5624. 7.

Light Engine

Oil

MIL-L-22851,Grade 1100

8.

Cleaning

Solvent

P-D 680

Type

III

Stoddard Solvent

I

(Mineral Spirits) 9.

Corrosion Preventive

MIL-C-16173,

Compound

Grade 1

Petrotect

Pennsylvania Refining 1686 Lisbon

Co.

Rd.,

Cleveland, OH 44104 10.

Primer, Zinc Chromate

MIL-P-8585

Hydraulic

MIL-H-6083

11. Preservative

Fluid

Obtain Avrex 904

locally

Mobil Oil

Corp.,

150 E. 42nd

St.,

New York, NY

Mar

9/0110-00-00

A12

Ral~heon Aircraft BEECH SUPER KING AIR MODEL B30~0/B300C MAINTENANCE MANUAL CHART 2

RECOMMENDED MATERIALS MATERIALS

SPECIFICATION

SUPPLIER

PRODUCT

Royco

Royal

783C

Lubricants Co.,

River Rd., East Hanover, NJ 07936 12.

Hydraulic

Fluid

MIL-H-5606

3126

Hydraulic

oil

Exxon Co., U.S.A.

Box 2180, Houston, TX 77001 Standard Oil Co. of California,

FED 3337

225 Bush St., San Francisco, CA 84120 13.

Strippable Coating

14. Adhesive

Protective

Spraylat

Spraylat Corp.

A

Mount Vernon, NY 10550

Paper

Mask-Off Co.,

Protex #5

345 W.

Maple,

Monrovia, CA 91016 15.

Engine

Oil

NOTE For the various

Type II (5Centistoke Oils) engine

oils

approved by

Pratt and

Whitney,

refer to the latest revision

or

Pratt and

Whitney

Service Bulletin No. 13001.

A12

10-00-00

Mar

9/01Page

3

Ray~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

101-590016 GUST CONTROL SURFACE LOCK ASSEMBLY

B

OEfAILC B B

101-590107-1 BLEED AIR INTAKE SCOOPPLUG

O p

I

I

130-590004-1 PROPELLER SLING (EFFECTIVITY: FL- 1 27 AND AFTER: FM-9 AND AFTERI

(C/ Q3

DETAIL

DETAIL

B

A

101-590098-51 PROPELLER SLING AND EXHAUST COVERS (EFFECTIVITY: FL-I TO FL-126: FM-I TO FM-8)

C9YLIOB1223 2

Special Tools (Sheet t of 3) Figure 1

Mar

9/0110-00-00

A12

Ral~heon Aircraft BEECH SUPER KING AIR MODEL B~OO/B300C MAINTENANCE MANUAL

o~jo/aooo

o

A

B o 130-910003-1 EXHAUST COVERS (EFFECTIVITY: FL-127 AND AFTER: o

;D r~ll

0/

FM-9

C-~-l

AND

AFTER:

AND AIRCRAFT WITH CONSTANT AREA STACK KITS INSTALLED].

lo I"

OETAIL

C

COVER

1/2 INCHES MINIMUM 4

DETAIL

A

I

101-54~098-7

AIR INLET COVER

L

MATERIAL: HARDWOOD THICKNESS:

OE

3/4MINIIJICj~"

I

b

Cd

i

DETAIL

INCHES-I

1/2 MINIMUM

DETAIL

B

D C95FL108122~ C

Special Tools (Sheet 2 of 3) Figure 1

A12

10-00-00

Mar

9/01Page

5

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

~51(1

DETAIL

115´•590035 NOSE LANDING GEAR SHOCK STRL~T UMTTER

A

B

Oq

´•P C

JACK CAPACITY 7000 LB

RMUIRED

DETAn

Itsssam~ MAIN LANDING GEAR SHOCK STRL~ LIMITER

B

111

6\?1\ DETAIL

C

Special Tools (Sheet 3 of 3) Figure 1

Mar

9/01Page

6

10-00-00

art

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PARKING

MAINTENANCE PRACTICES

CAUTION: When the

position

to

airplane is

prevent fading The brakes

can

to be

parked in areas of intense sunlight,

rotate the

polarized

windows to the clear

prevent deterioration of the polarized material. Sufficient ultra violet protection is provided

be set for

of the

to

upholstery.

parking by depressing

the

pilot’s

or

copilot’s

brake

pedals,

then

pulling

out the

parking

brake control. Do not attempt to lock the parking brake by applying force to the parking brake handle. The handle controls a valve only, and cannot apply pressure to the brake system. To release the brakes, depress the brake

pedals

and

push the parking brake

NOTE: Do not set the

parking

brakes to freeze,

brakes

when

or

control in.

during low temperatures when they are hot from severe use.

an

accumulation of moisture may

cause

the

CONTROL LOCKS (Item No.l, Chart 1,10-00-00) consist of a U-shaped clamp and two pins connected by a chain The pins lock the primary flight controls and the U-shaped clamp fits around the engine power control levers to prevent the pilot from starting the engines with the control locks installed. It is important that the locks be installed or removed together to preclude the possibility of an attempt to taxi or fly the airplane with the power levers released and the pins still installed in the flight controls. Install the control locks in the following

The control locks

(Ref. Figure 201).

sequence: a.

Position the

b.

Push the control wheel

U-shaped clamp

fully

Center the rudder rudder

d.

pedals

to

engine

forward and rotate it

column, then install the small c.

around the

pin

align

control levers.

approximately

15" to the left to

align

the holes in the control

in the holes. the hole in the rudder bellcrank with the hole

provided

in the floor aft of the

pedals.

Insert the

L-shaped pin

into the hole in the floor until the

flange

is

resting against

the floor. This will prevent any

rudder movement.

Remove the locks in

reverse

order, i.e, the rudder pin first, then the control column pin and the engine control lever

clamp. WARNING: Remove the control locks before the rudder lock is

towing

the

installed, serious damage

airplane. If the airplane is towed with to the steering linkage could result.

10-10-00

a

tug while

Page

yaM102

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

I:.s´•,´•.´•.´•.´•

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a

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mr"~-´•x!

~n

cc´•~:c´•

´•is~

II

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~8

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ct

x

~zr´•

´•m

Control Locks

Figure 201

ORIGINAL

As Aecelvecl 8y ATP

May

1/08Page

202

10-10-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STORAGE ENGINE

engine preservation procedure to be followed depends upon the period of inactivity, the type of preservation not the engines may be rotated during the period of inactivity. To establish the procedure, refer to the preservation records (tags) secured to the engine and the engine service records (logbooks). The anticipated period of inactivity should also be established. Record the type of preservation used on the tags and in the logbook. The

used, and whether or

sprayed into the compressor or turbine section or foreign particles adhered by the preservative oil will alter engine. the airfoil shape of the turbine blades and vanes to adversely affect compressor efficiency during engine

CAUTION: Under no circumstances should preservative oil be Dirt and other

turbine sections of the

operation.

FLIGHT-READY STORAGE

(0 TO

7

DAYS)

inactive up to seven days may be left in an inactive state without preservation provided that: the engines sheltered; the humidity is not excessively high; and the engines are not subject to extreme temperature changes

Engines are

which

condensation.

produce

damage to the reduction gears caused by the propellers windmilling propellers by installing the propeller sling and exhaust covers 2, Item No. 9 and Item No. 10 Chart i, 10-00-00).

CAUTION: To prevent restrain the

(Item

No.

SHORT-TERM STORAGE

(8

with

no

oil pressure,

TO 28 DA YS)

Engines inactive longer than seven days, but less than 29 days, require no preservation provided that all engine openings are sealed off and the relative humidity in the engines is maintained at less than 40% as follows: CA UTION: To avoid damage

by the ingestion of an overlooked desiccant bags at the next engine operation, record bags used in the engine logbook and on the preservation record tag secured to sure that the same number of bags are removed from the engine prior to its next

the number desiccant

engine. operation. the

a.

Place six 8-ounce duct. Make

b.

c.

sure

Place

humidity inspection. Seal off all

Make

bags

indicators

(Item

Inspect no

No. 2, Chart 2,

engine openings with

windows in the material used d.

the

(Item

in the ducts

No. 3, Chart 2,

so

that

they

engine

exhaust

will be visible for later

10-00-00). Provide suitable moisture-proof humidity indicators.

the exhaust ducts for observation of the

engines and the humidity indicators periodically. If the relative humidity indicated is less than 40%, required. If the humidity indicated is 40% or greater, replace the desiccant bags with freshly

bags.

INTERMEDIA TE-TERM STORAGE

engines

inactive for

In addition, preserve the

M4

barrier material

over

10-00-00)

in each

further action is

activated

Seal

(Item No. 1, Chart 2, 10-00-00) on wooden racks bags are not in contact with any engine parts.

of desiccant

that the desiccant

(29 TO

90 DA YS)

a period exceeding 28 days, but engine fuel system as follows:

less than 91

days,

as

instructed in Short -Term

10-10-00

Storage.

1/08

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION: Extreme Make

prevent foreign material from being drawn into the engine fuel system. equipment used is equipped with filters, strainers, or screens rated at 10 microns or

must be taken to

care

that the

sure

finer. Close the normal fuel

a.

supply shutoff

to-fuel heater and connect b.

a

valve. Disconnect and cap the fuel inlet line at the fuel pump supply line to the fuel pump or to the oil-to-fuel heater.

or

at the oil-

suitable oil

To prevent oil from entering the fuel manifold, disconnect the No. 1 and No. 2 manifolds and the bypass and dump lines at the starting flow control. Cap the No. 1 manifold and the bypass and dump outlets. Allow the No. 2 manifold to drain into

a

suitable container.

CAUTION: Under

no circumstances permit preservative oil to enter the engine where it may come in contact with thermocouple probe assembly. Oil contamination of the wiring harness may cause complete failure of the thermocouple system.

the

Supply preservative oil (Item No. 4, Chart 2, 10-00-00) to psig and a temperature of at least 16" C (60" Fl.

c.

the fuel pump

or

the oil to fuel heater at

a

pressure of

5 to 25

CA UTION: Do not exceed the starter operating time of 30 seconds on, 5 minutes off, 30 seconds on, 5 minutes off, 30 seconds on, then 30 minutes off.

while

ignition system OFF, the power lever at TAKEOFF position, and the condition lever at LOW IDLE, engine while moving the condition lever from LOW IDLE to CUTOFF and back to LOW IDLE, and moving the power lever from TAKEOFF to IDLE and back to TAKEOFF.

After

motoring

d.

With the

motor the

e.

the

engine,

check to

see

that oil is

draining

from the No. 2 manifold outlet. If necessary, repeat

step "d" until oil drains from the outlet. Return the power lever to IDLE and the condition lever to CUTOFF. Disconnect the oil supply and drain lines. bypass and dump lines and the No. 1 and No. 2 manifolds to the starting flow control. Connect the

f.

Connect the

fuel inlet line to the fuel pump g.

or

the oil-to fuel heater.

caps, and covers to prevent the entry of foreign materials and the accumulation of moisture. Install desiccant bags, humidity indicators, and moisture barriers as instructed in Short-Term Storage. Install all

shipping plugs,

LONG-TERM STORAGE Preserve

engine

engines

(91

inactive

DA YS AND

longer

than 90

LONGER)

days

as

instructed in Intermediate-Term

oil and spray the unused accessory drive-ends

as

Storage.

In addition, drain the

follows:

CA UTION: Do not exceed the starter operating time of 30 seconds on, 5 minutes off, 30 seconds on, 5 minutes off, 30 seconds on, then 30 minutes off. a.

Close the fuel shutoff valve and motor the

b.

Drain the

c.

Allow the oil filter element to drain to

plugs,

engine

and the

d.

Remove the

e.

Spray

the

oil

chip

cover

as

instructed in the oil a

engine

until oil pressure and compressor

changing procedure

slow

in

speed (N1)

are

indicated.

(Ref. Chapter 12-10-00).

drip (approximately one-half hour), then install the filter, all drain

detector.

plates

from the

pads

of the accessory drives.

exposed surfaces and gearshafts cover plates.

with

engine

oil

(Item

No. 15, Chart

2,10-00-00)

and install the

accessory drive

May

1/08Page

204

10-10-00

n24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

the oil filler cap with the date of

i.

Tag

g.

Install all

caps, and

shipping plugs,

preservation. covers

to

Enter the date and type of

preservation

in the

engine log

book.

prevent the entry of foreign materials and accumulation of

moisture. h.

If the

engines

are

to remain in the

instructed in Short-Term

airplane,

install desiccant

and moisture barriers

bags, humidity indicators,

as

Storage.

NOTE: Inspect the preserved unit every two weeks ii the airplane is stored outside, or every thirty days if the airplane is stored inside. If the relative humidity indicated is less than 40%, no further action is required. If the i.

If the

engines

humidity are

indicated is 40%

to be

or

greater, replace the desiccant bags with freshly activated bags

removed, preserve the engines

as

instructed in the vendor maintenance manual.

AIRPLANE

imperative that the storage areas of nickel-cadmium batteries be separated tin different buildings possible) from lead acid batteries so that no contamination, even from fumes is possible.

CA UTION: It is

if

BA TTER Y COMPARTMENT a.

Disconnect and

b.

Clean the boric acid to

c.

remove

the nickel-cadmium

battery,

then

place

it in

a

suitable storage

battery compartment, quick disconnect plug, cables, and vent hoses (Item No. 5, Chart 2, 10-00-00) dissolved in one gallon of water, then

with

a

area.

solution of five

ounces

of

rinse with clean water and allow

dry.

Seal the

(Item

battery

vent tubes and

No. 3, Chart 2,

cover

the

quick-disconnect plug

with barrier material

10-00-00).

FUEL CELLS a.

b.

is to be in storage 90 days or less, fill the fuel cells to capacity with fuel 10-00-00) to minimize fuel vapor and protect the cell inner liners.

If the

airplane

(Item

No. 6, Chart 2,

airplane is to be in storage longer than 90 days, drain the fuel cells, then flush, spray, of light engine oil (Item No. 7, Chart 2, 10-00-00). If the

or

rub

a

thin

coating

PROPELLERS a.

bug accumulation from the propellers with cleaning solvent 0-00-00), then coat the blades with corrosion preventive compound (Item Chart No. 9, 2, 10-00-00). Wrap the propeller blades with barrier material (Item Chart No. 3, 2, 10-00-00) and secure with tape. Touch up the propeller spinners with paint as necessary, (Item then secure the blades with the propeller sling (Item No. 2 or Item No. 9, Chart i, 10-00-00) to prevent rotation. Remove dirt, oil, and

No. 8, Chart 2, f

AVIONICS Clean and

cover

with barrier material

Take any additional

nw

precautions

(Item

10-00-00) any equipment sensitive to dust the manufacturer of such equipment.

No. 3, Chart 2,

recommended

by

10-10-00

or

moisture.

Page

yaM502

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSTRUMENTS is to be in storage for more than 90 days, 10-00-00) and secure with tape.

If the

airplane

(Item

No. 3, Chart 2,

cover

the instrument

with barrier material

panel

SEATS Clean the seats and install

protective

covers.

STALL WARNING UNIT is to be in storage for 90

If the

airplane

(Item

No. 3, Chart 2,

10-00-00)

to

days

or

more, cover the stall

warning

unit with barrier material

prevent collection of dust, debris and moisture

on

the transducer.

LANDING, STROBES, AND TAXI LIGHT If the

airplane

(Item

No. 3, Chart 2,

is to be in storage for 90 days or longer, 10-00-00) and secure with tape.

cover

the

landing, strobe,

and taxi

lights

with barrier material

FLIGHT CONTROL SURFACES a.

If the

airplane

is to be in

storage up

to 90

days,

install the control surface locks

instructed in

as

CONTROL LOCKS. b.

If the

airplane is to be in storage longer than 90 days, lubricate all hinges, bearings, chains, and quadrants as (Ref. Chapter 12-20-00) and apply corrosion preventive compound (Item No. 9, Chart 2, 10-00-00). Place the flaps in the retracted position. instructed

WING FLAP TRACKS AND ROLLERS

If the

airplane

(Item

No. 9, Chart 2,

is to be in storage

10-00-00)

over

to the

days, apply flap tracks and 90

corrosion

preventive compound flaps in the retracted position.

rollers. Place the

LANDING GEAR a.

Clean the brakes and

b.

Cover the wheels with barrier material

c.

Check the air pressure in the tires

apply

a

coating

of

primer (Item

(Item

No. 10, Chart 2,

No. 3, Chart 2,

periodically.

10-00-00)

10-00-00) and

to the brakes disc.

secure

with tape.

It is recommended that unserviceable tires be used for

prolonged

storage. CA UTION: Do not

apply corrosion preventive compound to the exposed surface hydraulic cylinders.

of the

landing gear strut piston

or

the extended polished surfaces of the d.

exposed surfaces of the shock strut pistons and the nose gear shimmy dampener piston with preservative hydraulic fluid (Item No. 1 1, Chart 2, 10-00-00). Cover the surfaces with barrier material and

Coat the

secure

with tape. e.

Fabricate

a

hardwood shock strut collar

(Item

the strut when deflated. Install the collars

No. 4, Chart 1

over

10-00-00) for each strut piston to prevent bottoming Slowly deflate the struts until they rest on the

the barrier material.

wooden collars.

Page

20610_10_00

P124

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

HYDRAULIC SYSTEM

hydraulic reservoir with MIL-H-5606 hydraulic fluid (Item (Ref. Chapter 32-40-00) and inspect the system for leaks. Fill the

No. 12, Chart 2,

10-00-00)

as

instructed in

LOOSE TOOLS AND EQUIPMENT If the low

is to be in storage

airplane humidity.

over

90

days,

the loose tools and

remove

equipment

and store them in

a room

of

AIRFRAME a.

b.

Install the air inlet

covers

(Item

No. 5, Chart 1,

10-00-00).

Install the pitot tube covers (Item No. 6, Chart 1, 10-00-00). Cover the static ports with barrier material No. 3, Chart 2, 10-00-00) and secure with tape.

(Item c.

Install the bleed air intake scoop

d.

Clean all

e.

exposed

f.

wipers

in the

10-00-00).

wipers, wrap with barrier material (Item No. 3, Chart 2, 10-00-00), cockpit or with the loose tools and equipment.

(Item

No. 14, Chart 2,

and

strippable coating (Item No. 13, Chart 2, 10-00-00),

Cover the windows and windshield with

adhesive paper

No. 3, Chart 1,

antennas and connections.

Remove the windshield

Store the

plugs (Item

secure

or

the

with

tape.

preferred

10-00-00).

GROUNDING To protect the

airplane (Ref. Figure 202).

from static

discharge, ground

the

airplane securely and effectively

at the locations shown

REMOVAL FROM STORAGE a.

Remove all barrier material and all

CAUTION: To avoid

caused

damage engine.

from each

Make

shipping plugs, by

b.

Remove all desiccant

c.

Remove all covers, tape, tie downs, and

d.

Remove the control locks

e.

Service the oil tanks with

Make

care

sure

engines.

of an overlooked desiccant

bag,

count the

bags

removed on

the

and wooden racks from each exhaust duct.

tags from

the

airplane.

instructed in CONTROL LOCKS.

engine

oil

(Item

must be taken to

that the

from the

engine.

bags, humidity indicators,

as

covers

that the number of bags removed matches the number recorded

sure

preservation tag attached to the

CAUTION: Extreme

ingestion

the

caps, and

equipment

No. 15, Chart 2,

10-00-00)

as

instructed in

Chapter

12-10-00.

prevent foreign material from being drawn into the engine fuel system. equipped with filters, strainers, or screens rated at 10 microns or

used is

finer. f.

g.

Connect

supply of engine fuel (Item

No. 6, Chart 2,

Disconnect the fuel line between the fuel control control

~a4

a

assembly

10-00-00)

assembly

to the fuel inlet

port

on

the fuel control

and the fuel shutoff valve. Connect

a

assembly.

line to the fuel

to drain overboard.

10-10-00

Page

yaM702

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

h.

Motor the

engine, without ignition, moving the power

IDLE and while

while

moving

the condition lever from LOW IDLE to OFF and back to LOW

lever from TAKEOFF to IDLE and back to TAKEOFF, until clean fuel flows

from the overboard drain. CAUTION: Do not exceed the starter operating time of 30 seconds on, 5 minutes off, 30 seconds on, 5 minutes off, 30 seconds on, then 30 minutes off.

Stop motoring the engine. Return the power control lever to IDLE and the condition lever to CUTOFF. Disconnect the overboard drain line. Connect the fuel line between the fuel shutoff valve and the fuel control

i.

assembly. Start the

j.

engine by

the normal start

procedure

and operate it for

approximately

three minutes.

CA UTION: Do not exceed the starter operating time of 30 seconds on, 5 minutes off, 30 seconds on, 5 minutes off, 30 seconds on, then 30 minutes off. k.

Stop

I.

Inspect all

the

engine.

When the

engine

has

lubrication and fuel lines for evidence of

as

instructed

n.

Remove, inspect, clean, and install the fuel strainer element

o.

Thoroughly

May

clean the

airplane, then perfdrm

10-10-00

a

supply

to the

engine.

leakage.

Remove, inspect, clean, and install the oil filter element

m.

shut off the fuel

completely stopped,

visual

as

inspection

(Ref. Chapter 12-10-00).

instructed in and

a

test

(Ref. Chapter 12-10-00).

flight.

n24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I

HERE

ORIGINAL By

As Received

ATP BOTTOM

VIEW

1~ 0)

GROUND HERE

O

io

(TY?ICAL

L~/RH)

rreo-sos-ool

c

Ground Points

Figure

A24

202

10-10-00

Page

yaM902

1/08

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

MOORING Three as an

mooring eyes are provided, one on each wing and one on the tail. In addition, each landing gear may point for a mooring line when additional security is required (Ref. Figure 201).

be used

attach

MOORING FOR NORMAL WINDS a.

Chock the wheels fore and aft.

NOTE:

In ice are

b. c.

(Item

No. 1, Chart 1,

10-00-00)

instructed in CONTROL LOCKS.

as

airplane down at all three mooring eyes as shown in (Ref. Figure 201), using chain, aircraft cable 1/4 inch in diameter with wire rope clips or clamps, or rope 3/8 inch in diameter. Do not use hemp or manila rope. Allow sufficient slack in the mooring lines to compensate for the lines tightening because of moisture absorption

Tie the

the rope

of the the If

or

thermal contraction of the chain

airplane

that the

e.

not

Install the control locks

by

d.

conditions, ice-grip wheel chocks are preferred. Sandbags may be used if ice-grip chocks available, or if the airplane is parked on a steel mat.

or snow

nose

up

so

strut is

compressed, reducing

cable. Avoid

or

far that wind will create lift the

the

on

angle

wings.

overtightening

the

rear

It is recommended that

of attack of the

line and a

tail

wings and, therefore,

pulling

the

nose

support be used the lift

so

generated by

wings. attach lines to the

required,

Install the

nose

and main

nose

and main

landing gear

landing

gear

shock strut limiters

shown in

as

(Item

(Ref. Figure 201).

No. 7 and Item No. 8, Chart 1,

10-00-00).

MOORING FOR HIGH WINDS CAUTION: High winds inside

weather a.

Separate

the

can cause

hangar.

a

structural

airplane from all others by

airplane with its

Position the

the fixed locations of the

by satisfactory. c.

Centerthe nosewheel.

d.

Deflate the

nose

reduce the

angle of

nose

a

f.

g.

If time

permits,

Install the

nose

into the

ground

airplane. Therefore, if time permits, park the airplane are expected, move the airplane to a safe

distance

ground

slightly greater than

expected wind,

tiedown

or

rings.

taxi the aircraft

fill all fuel tanks to and main gear

the

wing

span, with the

nose

mooring

anchor. or as

nearly so as possible within the a 45-degree difference

If necessary, up to

gear shock strut to within 3/4 inch of the attack of the wings.

CAUTION: Do not attempt to tow e.

to the

area.

eye three to five feet downwind from the b.

damage

If at all possible, when winds above 75 knots

once

the

fully

deflated

nose

position

limits determined

in direction is

in order to lower the

nose

and

gear shock strut is deflated.

capacity.

landing gear shock

strut limiters

(Item

No. 7 and Item No. 8, Chart 1,

Chock the wheels fore and aft with the proper size and type of wheel chock. Tie each or join wooden chocks together with wooden cleats nailed to the chocks.

pair

10-00-00).

of chocks

together

with rope

a24

10-20-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: In ice not

or snow

available,

conditions, ice grip wheel chocks or

if the

airplane

is

parked

on a

are

preferred. Sandbags

may be used if

ice-grip

chocks

are

steel mat.

airplane down at all three mooring eyes and all three landing gear (Ref. Figure 201), using aircraft cables 1/4 inch in diameter with two wire rope clips or bolts, or using chain tested for a 3000-pound pull. Do not use rope. Remove all slack from the mooring lines.

h.

Tie the

i.

Place the trim tab controls in the neutral

j.

Install the control locks

k.

Disconnect the

I.

extremely high winds are expected, mooring security can be further increased by placing sandbags along the wings to break up the aerodynamic flow of air over the wing, thereby reducing the lift generated by the wing. Place the sandbags on the spar cap, distributed so that the weight does not exceed 20 pounds per inch.

m.

After the

(Item

position.

No. 1, Chart 1,

Place the

10-00-00)

as

wing flaps

in the UP

position.

instructed in CONTROL LOCKS.

battery.

If

of

May

1/08Page

high winds have passed, inspect the airplane for visible signs of structural damage and for evidence damage from flying objects. Service the nose gear shock strut and connect the battery.

202

10-20-00

nz4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DETAIL

A

DETAIL

B NOSE WHEEL

(NOSE 8 MAIN)

MOORING EYE

WING MOORING EYE

jb

B\

DETAIL

C

I

MOORING POINT

j

TAIL MOORING POINT

.i 70

C

A350-605-2

Mooring the Airplane Figure 201

A24

10-20-00

PMa Sye~May

1/08

C H A PTE R

PLACARDS AND MARKINGS

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 11

REQUIRED PLACARDS

TABLE OF CONTENTS

SUBJECT

PAGE 11-00-00

Required Placards Description and Operation Model Designation Placard Exterior Placards and Markings Interior Placards and Limitation Markings

........._____

........._____

............1

........._____

........1

........._____

................._

Recommended Materials

................._

....1

............._.2

................._

.........2

11-20-00 Exterior Placardsand

n25

Markings-

Maintenance Practices.

.201

11-CONTENTSPagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

11-LOEP

1

Feb 1/09

II-CONTENTS

1

Feb 1/09

11-00-00

1 and 2

Feb 1/09

11-20-00

201 thru 223

Feb 1/09

A25

Pages

11-LOEP

Feb

1/09Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

REQUIRED PLACARDS

DESCRIPTION AND OPERATION

MODEL DESIGNA nON PLACARD The model

designation placard (Ref. Figure 1) is located on the external fuselage (left side), below the vertical (Ref. Chapter 11-20-00). The placard identifies the airplane by its model and serial number. Should a question arise concerning the care of the airplane, it is important to include the airplane serial number in any correspondence to Hawker Beechcraft Corporation (HBC). stabilizer

EXTERIOR PLACARDS AND MARKINGS The exterior maintenance

NOTE:

placards,

with their locations

indicated,

are

shown in the

Chapter

11-20-00.

time

an airplane is repainted or touched up, inspect all placards to make sure that they are not covered paint, are legible, and are securely attached. If the decals on the wing attach fittings are being replaced. Sand the wing attach fittings lightly in the required area but do not remove primer. Wash the area with solvent (Item No. 2, Chart 1, 11-00-00), apply the decal and seal the decal edges with edge sealer (Item No.l,Chart 1, 11-00-00).

Any

with

o

o

MANUFACTURED BY

MANUFACTURED BY

I

BEECH AIRCRAFT CORP.

I

RAYTHEON AIRCRAFT COMPANY

WICHITA,KS.USA SERIAL NO.

I

I

I

I

FM-8) O

Raytheon Aircraft

n

MANUFACTURED BY

MANUFACTURED BY

RAYTHEON AIRCRAFT

HAWKER BEECHCRAFT

COMPANY

CORPORATION

,,cHITA. KS. VSA

WlcHITA. KS. USA

I

SERIAL NO.

MODELNO.

I

I

MODEL NO.

I

TYPE CERTIFICATE

I

132540-1

(FL-244

I

I I

I

PRODUCTION CERTIFICATE 8

PRODUCTION CERTIFICATE 8

THRU FL-525; FM-10 THRU

O

O

FM-13)

Model

A25

O

I

O

I p´•C. B

O

SERIALNO.

TYPE CERTIFICATE

1

(FL-137THRuFL-243;FM-9)

O

Raytheon

I

T.C.

o

FM-1 THRU

I

I

MODELNO.

P.C.8

o

(FL-1 THRU FL-136;

I

SERIAL NO.

I

MODELNO. T.C.

WICHITA.KS. VSA

I

132766-1

(FL-526

Designation Figure 1

AND

O

AFTER; FM-14 AND AFTER)

Placards

11-00-00

Feb

1409Pagel

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

INTERIOR PLACARDS AND LIMITA nON MARKINGS All

required

interior

Handbook and FAA

placards and limitation markings are Approved Airplane Flight Manual.

listed in "Section II Limitations" of the Pilot’s

Operating

RECOMMENDED MATERIALS The recommended materials Listed in Chart 1

as meeting federal, military or supplier specifications are provided for only and are not specifically required by Hawker Beechcraft Corporation (HBC). Any product conforming to the specification may be used subject to availability. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation (HBC), by the supplier, or by compliance to the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE

reference

REOUIREMENTS OF THE SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART. the basic number of each

Only

specification

is listed. No attempt has been made to update the listing to the latest or mechanic to determine the current revision of the applicable

of the technician

revision. It is the

responsibility

specification prior

to usage of the

product

listed. This

can

be done

by contacting

the

supplier

of the

product

to be

used.

Chart 1

Recommended Materials MATERIAL i.

SPECIFICATION

EdgeSealer

PRODUCT

SUPPLIER Minnesota

#3960

Mining

Co., St. Paul

12.

Solvent

Page

beF2

1/09

A-A-59282

11-00-00

Methyl Propyl

Ketone

Obtain

Manufacturing

MN

Locally

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

EXTERIOR PLACARDS AND MARKINGS

27

15

D

o,

28

MAINTENANCE PRACTICES

27

12

13

41

oi~a/a oo

I

42

o

(O

Exterior Placard Locations (Left Hand (FL-1 and After)

Figure

27

15

28

201

(Sheet

27

1 of

13

View)

2)

12

41

42

O

o)

(O

Exterior Placard Locations

(Left Hand View) (FM-1 and After) Figure 201 (Sheet 2 of 2)

A25

11-20-00

PFBe9be121~:Feb

1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

14

1

28

27

4

41

15

27

23

a

o

38 9

11

6

7

i

0)

36~

(0)

\35

37

FL~le

Exterior Placards Locations

Figure

(Right

Hand

View)

202

n o

o

37

29~34 35

5~0-016-042

Exterior Placard Locations

Figure

Page

beF202

1/09

11-20-00

(Front View)

203

A25

Hawker Beechcraft Corporation SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

23

17

16

17

16

20

3 ?~H23

IU

UI

23

H~? 3

23

20 9

21

1’8

9

i

4

h

1

U

1

42

9

21

4

9

1’8

FL128

42

002553Ar.

Exterior Placard Locations (Top View) (FL-I thru FL-416, FM-1 thru FM-11)

Figure

23

1 of

2)

17

25

16

20 3

2

P~H23

20 21

18

(Sheet

32

17

16

204

2

IU

UI

23

E~

Y

20

h

1

LI

1

42

H~tr 2

23

3

21

2

18

FLIPB

42

sss531Rnal

Exterior Placard Locations (Top View) (FL-417 and After, FM-12 and After)

Figure

A25

204

(Sheet

2 of

2)

11-20-00

Page

beF302

1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

ns

33

22

22 24

11

33

391

33

Y

_24

11

30

111 1 I~

RH

I

---~I,

LH

42 19

2

8

19

26

26

Exterior Placard Locations

Figure

Page

beF402

1/09

11-20-00

19

8

19

(Bottom View)

205

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

NOTICE:

AVIATORS

BREATHING OXYGEN

KEEP FILL AREA

CLEAN, DRY 8 FREE FROM OIL 70"F PRESSURIZE TO 1850 PSI 14.7 PSIA 350-1627

Detail 1:

of Door

(Figure 202) Inside Figure 206

WARNING LUBRICATED BOLTS

SEE MAINT. MANUAL

FOR TOROUE VALUES Detail 2:

(Figures

205) Inside Figure 207

204 4

(?m’hh6

of Access Panel

NOTICE WING ATTACHMENT FITTINGS NEW ALUMINUM WASHERS

101-110023-3(1100-0 ALUM .032 SHT) MUST

INSTALLED

BE

BETWEEN

SERRATED

FITTINGS EACH TIME JOINT IS DISENGAGED. LIMIT

ONE

SERRATED

WASHER FITTING

BETWEEN

EACH

I

JOINT

20018TI

Detail 3:

n25

Inside of Wing Join Figure 208

(Figure 204)

11-20-00

Page

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1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

OXYGEN 350-16-29

Detail 4:

(Figure 202) Outside Figure 209

of Door

SIGHT GAUGE 200- t 6-68

Detail 5:

(Figure 203) Figure 210

EMERGENCY LOCATOR TRANSMITTER SWITCH TEST

AUTO

XMIT

FOR AVIATION EMERGENCY USE ONLY. UNLICENSED OPERATION UNLAWFUL. OPERATION IN VIOLATION OF FCC RULES SUBJECT TO FINE OR LICENSE REVOCATION

FLIIB 985413AA.AI

Detail 6:

(Figure 202) Margolin Figure

Page

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211

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

EMERGENCY LOCATOR TRANSMITTER SWITCH TEST

ARM

XMIT

FOR AVIATION EMERGENCY USE ONLY.

UNLICENSED OPERATION UNLAWFUL. OPERATION IN VIOLATION OF FCC RULES SUBJECT TO FINE OR LICENSE REVOCATION. 350-16-30

Detail 6:

(Figure 202) Figure 212

NARCO

EM ERGENCY LOC ATOR TRANSMITTER

SWITCH ARM

ED/

RESET

ON

FOR AVIATION EMERGENCY USE ONLY.

UNLICENSED OPERATION UNLAW FUL. OPERATION IN VIOLATION OF FCC RULES SUBJECT TO FINE OR LICENSE REVOCATION. 35016´•57

Detail 6:

n25

(Figure 202) Figure 213

ARTEX

11-20-00

Page

beF702

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Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

ISTATIC

AIR.

KEEP CLEAN

Detail 7:

(Figures 201 Figure 214

8

202)

GRAVITY LINE DRAIN 200-~6-71

Detail 8:

(Figure 205)

Figure

215

NO PUSH Detail 9:

Page

beF802

1/09

11-20-00

(Figures 201,203 Figure 216

8

204)

A25

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

o

o

MANUFACTUREDBY

O

BEECH AIRCRAFT CORP.

WICHITA,KS.USA SERIAL NO.

I I

I P.C. 8

THRU FL-136; FM-1 THRU

FM-8)

O

i

I P.C. 8 o

(FL-137 THRU FL-243; FM-9) O

Raytheon Aircraft

I

T.C. o

O

Raytheon

I

I

MODELNO.

o

(FL-1

i

SERIAL NO.

I

I

T.C.

WICHITA.KS.USA

I

MODELNO.

O

MANUFACTURED BY RAYTHEON AIRCRAFT COMPANY

O

O

MANUFACTURED BY

MANUFACTURED BY

RAYTHEON AIRCRAFT

HAWKER BEECHCRAFT

COMPANY

CORPORATION

WICHITA. KS. USA

WICHITA. KS. USA

SERIALNO.

I

I

SERIAL NO.

I

i

MODELNO.

I

I

MODEL NO.

I

I

I

TYPE CERTIFICATE

TYPE CERTIFICATE

I

132540-1

O

I

I

PRODUCTION CERTIFICATE 8

PRODUCTION CERTIFICATE 8 O

O

132766-1

O FL208

(FL-244 THRU FL-525; FM-10 THRU FM-13)

(FL-526

AND

AFTER; FM-14 AND AFTER)

W2531ABAI

Detail 10:

(Figure 201) Figure 217

TIE DOWN

L

i F,

Detail 11:

A25

(8199888 201 Figure 218

202)

11-20-00

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

LEVEL POINT ?00-~6´•75

Detail 12:

(Figure 201) Figure 219

PUSH BUTTON AND TURN HANDLE

TO OPEN 200-16-76

Detail 13:

(FL-1

thru

(Figure 201)

FL-195; FM-1 thru FM-9 Prior

Figure

to

Compliance

With SE

52-3096)

220

1. PUSH BVTTON AND HOLD

2. TURN HANDLE TO OPEN

CLOSE

´•´•´•~f

i

(FL-196 and After;

Detail 13: (Figure 201) FM-10 and After and all Prior Airplanes that have

Figure

Page

11-20-00

Complied

With SE

52-3096)

221

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

t (FL.-I

LOCK

LOCK

THRU

FL-127;

FM-1 MRU

(FL-128 AND AFTER; FM-9 AND AFTER)

FM-8)

FORWARD AND AFT COWLING

FORWARD COWLING

I

LOCK

(FL-128

AND

AFTER;

FM-9 AND AFTER) AFT COWLING

FL2DB 0026YL~ei.lll

Detail 14:

f

LOCK

(FL-I

THRV

FM-1 THRU

(Figures 201 Figure 222

LOCK

FL-127;

FM-8)

FORWARD AND AFT COWLING

202)

::::r

\I LOCK

(FL-128 AND AFTER; FM-9 AND AFTER)

(FL-128 AND AFTER; FM-9 AND AFTER)

FORWARD COWLING

AFT COWLING

FL208

M2635Alllll

Detail 15:

A25

(Figures 201 Figure 223

202)

11 I20I00

Page

beF1 2

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Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

FWD

i

oosloau.u

Detail 16:

(Figure 204) Figure 224

I

ENGINE OIL

I

ENGINE OIL

SERVICE INSTRUCTIONS

SERVICE INSTRUCTIONS D

I

I

I

FILL WITH APPROVED OIL

TO MAXIMUM MARKING ON

I

DIP STICK

1

P

I 2

1 S

REFILL WHEN NO. 1 MARK

131

T

ON OIL DIP STICK IS EXPOSED

I.I

I

SEE AIRCRAFT FLIGHT MANUAL

I

I

TO MAXIMUM MARKING ON

I I

I I

I

I ON OIL DIP STICK IS EXPOSED

I

P

’I

~----1

S

3

T

1

SEE AIRCRAFT FLIGHT MANUAL

K

D

DIP STICK REFILL WHEN NO. 2 MARK

C

FOR APPROVED OILS

Inilavl FILL WITH APPROVED OIL

1

1,1

APPROVAL OF ADDITIONAL OILS

APPROVAL OF ADDITIONAL OILS

SHALL BE BY SEECH AIRCRAFT CO.

SHALL BE BY BEECH AIRCRAFT CO.

ENGINE OIL SYSTEM CAPACITY

ENGINE OIL SYSTEM CAPACITY

14 US QUARTS

C K

FOR APPROVED OILS

14 US QUARTS

I

DIP STICK GRADUATED IN US QUARTS

I DIP STICK GRADUATED IN US QUARTS

1 US QUART =.946 LITERS

1 US QUART =.946 LITERS

1 US QUART =.833 IMP. QUART

1 US QUART

.833 IMP. QUART

CHECK ONLY WHEN ENGINE IS SHUT DOWN

CHECK ONLY WHEN ENGINE IS SHUT DOWN

DO NOT FILL WHILE ENGINE IS RUNNING

DO NOT FILL WHILE ENGINE IS RUNNING

(FL-1

THRU FL-287; FM-1 THRU

(FL-288 AND AFTER; FM-12 AND AFTER

FM-11)

AND FOR SPARES ON PRIOR

FL((B

AICRAFT)

(Figure 204) Figure 225

Detail 17:

Page

beF212

1/09

11-20-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

MAIN TANK JET FUEL ONLY

Ba" SEE PILOTS OPERATING MANUAL FOR ALTERNATES 719 LITERS) (USEABLE 190 GALLONS CAPACITY 193 GALLONS=730.5 LITERS

WITH WINGS LEVEL

(Figure 204) Figure 226

Detail 18:

DRAIN

IUEL

200-16-as

(Figure 205) Figure 227

Detail 19:

A25

11-20-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

I NO?

LSTE~J

(Figure 204) Figure 228

Detail 20:

AUX TANK JET FUEL ONLY

SEE PILOTS OPERATING

MANUAL

FOR ALTERNATES 301 LITERS) (USEABLE 79.5 GALLONS CAPACITY 80.0 GALLONS=302.8 LITERS

WITH

WINGS LEVEL

350-16-24

(Figure 204) Figure 229

Detail 21:

Page

214~b"el:o’g"

11-20-00

A25

Hawker Beechcraft

Corporation

SUPER KING A\R B300/B300C SERIES MAINTENANCE MANUAL

r-----~

FILTER

IDRAIN

1

(Figure 205) Figure 230

Detail 22:

B+O 4ER~t 350-1632

Detail 23:

(Figures 202 Figure 231

204)

STRAINER DRAIN 200-16-89

(Figure 205) Figure 232

Detail 24:

n?s

1 1 -20-00

Page 215 Feb 1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

IBATTE RY

(Figure 204) Figure 233

Detail 25:

IJACK PADI 200-16-91

(Figure 205) Figure 234

Detail 26:

I PUSH IN AFTER RELEASE 200-16-92

(FL-1

Detail 27: (Figures 201 202) thru FL-252; FM-1 thru FM-9 Prior to Compliance With SE

Figure

Page

21611-20-00

52-3096)

235

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

EMERGENCY EXIT

PUSH PULL HANDLE TO RELEASE ~00-1693

Detail 28:

(FL-1

thru

(Figures

FL-252; FM-1 thru FM-9 Prior

Figure

201 8 202) to Compliance With SE

52-3096)

236

PUSH DOOR IN

2 PULL HANDLE TO RELEASE DOOR

EMERGENCY EXIT Detail 28:

(FM-253

and

(Figures Figure

n25

201 8

202)

After; FM-10 and After and all Prior Airplanes that have Complied With SE 52-3096) 237

11-20-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

JACK (Figure 203) Figure 238

Detail 29:

EXTERNAL POWER RECEPTACLE 28.25

.25 VOLTS

BATTERY VOLTAGE 20 VOLTS MIN (NO LOAD) CLOSE BATTERY SWITCH

CLOSE EXTERNAL POWER SWITCH AVOID EXCESSIVE BATTERY CHARGE OR DISCHARGE CURRENT

(Figure 205) Figure 239

Detail 30:

ACCESS INVERTER 115 VAC

391

(Figure 204) Figure 240

Detail 31:

Page

218~:b"el:o’g"

11-20-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

r

HYDRAULIC LANDING GEAR

ACCUMULATOR PLACE AIRCRAFT ON J~ACKS PRIOR TO CMARGING ACCUMULATOR

CHARGE TO 750-850 PSIG USING BOTTLED NITROGEN

FILL

I I I I I

MAINTAIN OIL AT INDICATED OIL TEMPERATURE MARK ON DIP STICK

I I

USE MIl-H-5606 HYDRAULIC FLUID

SEE MAINTENANCE MANUAL

L

-FOR GROUND OPERATIONAPPLY 18-20 PSIG AIR PRESSURE TO THE HYDRAULIC POWER PACK

350-16-23

ON INSIDE OF DOOR Detail 32:

(Figure 204) Inside Figure 241

_I

of Access Panel

r CAUTION HYDRAULIC LANDING GEAR SERVICE VALVE KNOB MUST BE IN DOWN POSITION AND STOWED BEFORE REMOVING AIRCRAFT FROM JACKS

_I

L (Figure 205) Figure 242

Detail 33:

n25

11-20-00

Page 219 Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING A\R B300/B300C SERIES MAINTENANCE MANUAL

I CAUTION: DO NOT 1 TOW ~JITH RUDDER

LLOCK INSTALLED~

(Figure 203) Figure 243

Detail 34:

J

LIMITS1.9L,

TURN REACHED WHEN RED LINES ALIGN

DO NOT EXCEED

Detail 35:

Page

22011-20-00

(Figures 202 Figure 244

3

203)

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

(i3eefhcraft´• OIL AIR STRUT INSTL NO. SlRIAL NO.

BEECH AIRCRAFT CORPORATION WKI~II, 1*111*5. UI*.

INSTRUCTIONS TO CHECK FLUID AND FILL REMOVE VALVE CAP. DEPRESS VALVE CORE AND ALLOW STRUT TO FULLY COMPRESS. REMOVE VALVE CORE ASSEMBLY AND FILL WITH HYDRAULIC 011 CONFORMING fO INSTRUCTION MANUAL SPEC)RCAIIONf. SLOWLY CYCLE STRUT. REPEAT UNTIL ADDITIONAL 011

CAN NOT BE ADDED. REPLACE VALVE CORE. WITH AIRPLANE EMPTY EXCEPT FOR FULL FUEL AND 011 KEEP STRUT TO INFLATED fO INCHES OF PISTON SHOWING.

WARNING RELEASE A(R IN STRUT BEFORE DISAJSEhBLING

TORQUE DRAG SRACE BOLTS TO 200-400 INCH-POUNDS YH)’b´•8

Detail 36: (Figure 202)

Figore 245

(i)eechcra f~m OIL AIR STR~I INSIL NO. we

sle,m NO. _

BEECn AIRCRAFT CORPORATION WICHI~*. **H5´•i~. U.~.*.

INS7RUCTIONS TO CHECK FLUID AND FILL AND ALLOW STRUT TO REMOVE VALVE CAP. DEPRESS VALVE CORE ASSEMBLY AND FILL WITH BODY VALVE REMOVE COMPILESS. FULLY

MANUAL SI~C(HYDRAULIC 011 CONH)IIMINC TO INSTRUCTION UNTIL ADDITIONAL 011 REPEAT STI~UT. CYCLE FICATIONS. SLOWLY VALVE BODY. CAN NOT BE ADDED. REPLACE FUEL AND O(L KEEP STRUT WITH AIRPLANE EMPTY EXCEPT FOR FULL INCHES OF PISTON SHOWING. INFLATED 10

WARNING RELEASE AIR IN STRUT BEFORE DISASSEMBLING ~ni, Ic

Detail 37:

A25

(Figures 201, 202, Figure 246

6

ct

203)

11-20-00

Page 221 Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING AIR 8300/B300C SERIES MAINTENANCE MANUAL

i MIC i IJACKI (Figure 202) Figure 247

Detail 38:

HYDRAULIC LAN DING GEAR OVERFILL DRAIN

(Figure 205) Figure 248

Detail 39:

ACCESS ASN FLUX DETECTOR CAUTION: USE NON-MAGN ETIC SCRE~S IN COMPASS (Figure 204) Figure 249

Detail 40:

11 L20-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

350-16-40

Detail 41:

(Figures 201 Figure 250

202)

NOTICE USE DOW CORNING #33 LIGHT SILICON GREASE ONLY, WHEN SERVICING TRIM ACTUATOR. WIPE OFF EXCESS GREASE

PURGED FROM VENT

HOLE(S)

ON TOP.

PROTECT FINISH FROM SILICON GREASE. SEE SERVICE MANUAL FOR INSTRUCTIONS

(FL-192

and

Detail 42: (Figures 201, 204 205) Inside of Access Panel After; FM-10 and After and all prior airplanes that have complied with SE 27-3044 and have installed P/N 130-524052-13, 130-524052-15, 130-521034-11 or 130-524051-11)

Figure

n25

251

11-20-00

Page

beF32

1/09

C H A PT E R

SERVICING

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 12 - SERVICING TABLE OF CONTENTS SUBJECT

PAGE 12-00-00

Servicing - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 12-10-00 Servicing - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Replenishing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Fuel Handling Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Fuel Handling Safety Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Fuel Grades and Types. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Jet Fuel Additives . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 MIL-I-85470 Jet Fuel Anti-Icing Inhibitor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Biocidal Agent. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Filling the Tanks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Draining Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Fuel System Defueling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Fuel System Purging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Fuel Cell Preservation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .217 Oil System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .217 Landing Gear System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .218 Brake System Replenishing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .218 Landing Gear Accumulator Precharging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .218 Landing Gear Power Pack Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .219 Hydraulic System Filters and Screens Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Main Landing Gear Strut Servicing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Nose Landing Gear Strut Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Shimmy Damper Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .221 Tires . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .222 Cabin Entrance Door Damper Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .222 Battery. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .223 Nickel-Cadmium Battery (FL-1 thru FL-214; FM-1 thru FM-9) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .223 Lead Acid Battery (FL-215 and After; FM-10 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .223 Air-Conditioning System Refrigerant Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .224 Precautionary Refrigerant Servicing Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .224 Air-Conditioning System Refrigerant and Oil Capacities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .224 R-12 Air-Conditioning Refrigerant Level Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .225 R-134a Air-Conditioning Refrigerant Level Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .225 Charging the R-12 Air-Conditioning System (FL-1 thru FL-127, FM-1 thru FM-8) . . . . . . . . . . . . . . . . . .226 Charging the R-134a Air-Conditioning System (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .230 Charging the Air-Conditioning System (FL-493, FL-500 and After; FM-14 and After) . . . . . . . . . . . . . . .231 Compressor Oil Check (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) . . . . . . . . . . . . . . . . .231 Compressor Oil Level Check (FL-493, FL-500 and After; FM-14 and After) . . . . . . . . . . . . . . . . . . . . . .232 Oxygen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .233

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CHAPTER 12 - SERVICING TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 12-20-00

Scheduled Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Washing Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Compressor Washing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Desalination Wash Procedures. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Performance Recovery Wash Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . External Engine Washing (Surface Washing) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Surface Salt Contamination . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning Airplane Exteriors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning Exteriors During the First Month of Paint Curing Period . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning Airplane Exteriors after the First Month of Paint Curing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Surface Deicer Boot Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Inertial Anti-Icing System Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Interior Care . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning Leather or Vinyl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fabric Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning of Laminates. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Servicing the Toilet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dry Nonflushing Toilet (FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Monogram Toilet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Alamo Toilet (FL-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Alamo Waste Container Servicing (FL-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Lubrication Schedule . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Lubrication Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Landing Gear Lubrication. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Main Landing Gear Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Control System Lubrication. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aileron Control System and Flap Control System Lubrication. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Control Column, Elevator Control System and Wings Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Controls Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Controls and Propeller Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Emergency Exit Door and Cabin Door Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cargo Door Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Spline Drive Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Spline Drives Attached to the Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Spline Drives for Accessories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Compressor Quill Shaft Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Thread Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Gaskets and Seals Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Control Cable Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

301 301 301 301 301 302 302 302 303 303 303 303 304 304 304 304 304 304 304 305 306 308 308 310 312 314 316 318 320 322 324 326 328 328 328 329 329 329 329

Page 2 Aug 1/09

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12-CONTENTS

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CHAPTER 12 - SERVICING TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 12-30-00

Unscheduled Servicing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .301 Deicing and Anti-Icing of Airplanes on the Ground . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .301 Snow Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .301 Frost Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .301 Ice Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .301 SAE Type I Anti-Icing Fluids (Unthickened-Type Fluids) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .302 SAE Type II Anti-Icing Fluids (Thickened-Type Fluids) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .302 SAE Type IV Anti-Icing Fluids (Thickened-Type Fluids). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .302 Deicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .302 One Step Deicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .302 Anti-Icing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .302 Holdover Time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .302 Precautions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .302 Checks for the Need to Deice. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .303 Final Checks after Airplane Deicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .303 Check of Complete Deicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .303 Functional Test of Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .303 Check of Engine Inlets and Probes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .303 Deicing and Anti-Icing Fluids. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .303 Handling Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .304 Fluid Application . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .305 Fluid Spills . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .305

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12-CONTENTS

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

12-LOEP

1

Aug 1/09

12-CONTENTS

1 thru 3

Aug 1/09

12-00-00

1

Oct 31/06

12-10-00

201 thru 233

Aug 1/09

12-20-00

301 thru 329

Aug 1/09

12-30-00

301 thru 305

Oct 31/06

A26

12-LOEP

Page 1 Aug 1/09

Ralfheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SERVICING

DESCRIPTION AND OPERATION

WARNING: When

airplane has experienced abnormal landing gear procedures of any type, as a safety precaution, place the airplane on jacks prior to performing any inspection or maintenance. Ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

CAUTION:

an

Jacking

airplane for the purpose of landing gear operation inspection, servicing or maintenance accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary to jack the airplane in the open, wind velocity in any direction and terrain variations, must be compensated for prior to jacking the airplane. of an

should be

Information contained in this maintenance information for

chapter is limited to general overall types of servicing for this airplane. Detailed specific components and systems of the airplane are in the chapter applicable to the

component. Section 12-10-00 is

replenishing

information for fuel, oil,

Section 12-20-00 is scheduled lubrication and Section 12-30-00 is unscheduled Service time limits for parts in Chapter 5.

or

servicing

hydraulic fluid,

tire pressure, etc.

airplane cleaning information.

information such

as

ice and

snow

removal from the

airplane

surface.

components that are serviced in accordance to a specified time schedule will be found

Lubrication necessary for the performance of maintenance procedures, such as packing of gearboxes or lubrication spline drives, will be covered under Maintenance Practices in the applicable system or component chapter.

of

12-00-00

o~X:

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 200200200 12-10-00

SERVICING - MAINTENANCE PRACTICES RECOMMENDED MATERIALS The recommended materials listed in Chart 201 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance to the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the chart. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used. CAUTION: Take precautions when using MIL-PRF-23827, MIL-G-21164, MIL-PRF-81322, and engine oil. These lubricants contain chemicals harmful to painted surfaces. DO NOT MIX different greases. If the grease is changed, make certain that all the affected components are thoroughly cleaned before lubrication. When changing over from one type or brand name grease to another, the recommended practice is to remove all of the old grease from the bearing surfaces and internal cavities of the lubricated mechanism prior to application of the new grease. Hawker Beechcraft Corporation does not recommend intermixing different types or brand names of grease, even if they are considered optional to each other, because of possible incompatibility. Different greases approved to the same specification may be incompatible with each other. Mixing of greases made with different thickener types should be avoided; thus clay-based thickened greases should not be mixed with a metallic soap-based thickened greases as this can lead to breakdown of the thickener structure.

Chart 201 Recommended Materials MATERIAL 1. Hydraulic Fluid

2. Anti-icing, Additive

A26

SPECIFICATION MIL-PRF-5606

MIL-DTL-85470B

PRODUCT

SUPPLIER

Mobil Aero HF

Exxon Mobil Corporation 3225 Gallows Rd. Fairfax, VA 22037

Brayco Micronic 756

Castrol Industrial North America Inc. 150 West Warrenville Rd. Naperville, IL 60563

Hi-Flo Prist Anti-Icing Agent 20

Houston Solvents and Chemical Co. 1010 W. Loop Rd. Houston, TX 77055-7216

Hoechst Safewing MP IV 1957

Hoechst AG Werk Gendorf Burgkirchen, D-84508 Germany

12-10-00

Page 201 Aug 1/09

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL Chart 201 Recommended Materials (Continued) MATERIAL

SPECIFICATION MIL-I-85470A

3. Biocidal Agent

4. Isopropyl Alcohol

TT-I-735

5. Refrigerant (Air-Conditioning)

R-12

6. Aviator’s Breathing Oxygen

MIL-PRF-27210

7. Tape, Anti-Seize Size 1 Teflon Tape

A-A-58092

8. Grease, Aircraft and Instrument, Gear and Actuator

MIL-PRF-23827* Type I or Type II

PRODUCT

SUPPLIER

High Flash Prist

Van Dusen Aircraft Supplies Div. Teterboro Airport 500 Industrial Ave. Teterboro, NJ 07608

Biobor JF

U.S. Borax and Chemical Corp. P.O. Box 2781 Terminal Annex 3075 Wilshire Blvd. Los Angeles, CA 90010-1207 Obtain Locally

Racon 12

Racon Inc. 6040 S. Ridge Rd. Wichita, KS 67201

Genetron 12

Allied Chemicals Columbia Rd. and Park Ave. P.O Box 1087R Morristown, NJ 07460

Freon 12

DuPont Inc., Freon Products Div. 1251 Brandywine Bldg. Wilmington, DE 19898 Obtain Locally

P-412

Permacel 7201, 108th Street Pleasant Prairie, WI 53158

Scotch 48 Thread Sealant and Lubricant

3M Electrical Products Division 6801 River Place Blvd. Austin, TX 78726

Aeroshell 7 Type II (Clay Thickened)

Shell Oil Co. One Shell Plaza Houston, TX 77001

Royco 27 Type I (Metallic Soap Thickened)

ANDEROL Inc. 215 Merry Lane East Hanover, NJ 07936

Castrol Aeroplex AI Type II (Clay Thickened)

Castrol Industrial North America Inc. 150 West Warrenville Rd. Naperville, IL 60563

AeroShell 33 Type I (Metallic Soap Thickened)

Shell Oil Co. One Shell Plaza Houston, TX 77001

9. Refer to Item No. 11

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL Chart 201 Recommended Materials (Continued) MATERIAL

SPECIFICATION

PRODUCT

SUPPLIER

10. Toilet Antifreeze

Clean Flush

Alamo Industries Inc. 10843 Vandale San Antonio, TX 78216

11. Toilet Chemical

Clean Flush

Alamo Industries Inc. 10843 Vandale San Antonio, TX 78216

12. Protective Coating

VV-P-236

Petrolatum (Commercial Vaseline)

Obtain Locally

13. Grease, Aircraft General Purpose, Wide Temp. Range

MIL-PRF-81322

Mobilgrease 28

Exxon Mobil Corporation 3225 Gallows Rd. Fairfax, VA 22037

Aeroshell Grease 22

Shell Oil Co. One Shell Plaza Houston TX, 77001

Royco 22CF

ANDEROL Inc. 215 Merry Lane East Hanover, NJ 07936

Royco 363

ANDEROL Inc. 215 Merry Lane East Hanover, NJ 07936

Brayco 363

Castrol Industrial North America Inc. 150 West Warrenville Rd. Naperville, IL 60563

Lubribond A

Everlube Products 100 Cooper Circle Peachtree City, GA 30269

Perma-Slik G

Everlube Products 100 Cooper Circle Peachtree City, GA 30269

LPS No. 3

LPS Laboratories 4647 Hugh Howell Rd. Tucker, GA 30084-5004

Nox-Rust 5200 KPR

ADCOR Inc. 1711 Cudaback Ave., Unit 1048 Niagara Falls, NY 14303

14. Lubricating Oil, General Purpose Low Temp.

MIL-PRF-7870

15. Refer to Item No. 19 16. Lubricant, (Air Drying Solid Film)

17. Metal Protector

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MIL-L-23398

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL Chart 201 Recommended Materials (Continued) MATERIAL 18. Lubricating Oil, Special Preservative

SPECIFICATION MIL-PRF-32033

19. Lubricating Grease, MIL-G-21164 Molybdenum Disulfide

20. Grease

MIL-PRF-10924

21. Lubricating Oil, Gear, Subzero

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SAE J2360 Grade 75

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PRODUCT

SUPPLIER

Brayco 300

Castrol Industrial North America Inc. 150 West Warrenville Rd. Naperville, IL 60563

Royco 308

ANDEROL Inc. 215 Merry Lane East Hanover, NJ 07936

Nox Rust 518 (Code R-62-203-1)

Daubert Chemical Co. 4700 So. Central Ave. Chicago, IL 60638-1531

CRC3-36

CRC Chemicals, U.S.A. Warmister, PA

LPS No.1

LPS Laboratories 4647 Hugh Howell Rd. Tucker, GA 30084-5004

WD-40

WD-40 Company 1061 Cudahy PI. P.O. Box 80607 San Diego, CA 92138

Royco 64 (Metallic Soap Thickened)

ANDEROL Inc. 215 Merry Lane East Hanover, NJ 07936

Aeroshell Grease 17 (Clay Thickened)

Shell Oil Co. One Shell Plaza Houston TX, 77001

Aeroshell Grease 33MS (Metallic Soap Thickened)

Shell Oil Co. One Shell Plaza Houston TX, 77001

Braycote 610

Castrol Industrial North America Inc. 150 West Warrenville Rd. Naperville, IL 60563

Tectyl 858

Daubert Chemical Co. 4700 South Central Avenue Chicago, IL 60638

101-380016-1

Hawker Beechcraft Service Centers International Distributors and Dealers

Mobil Delvac Synthetic Gear Oil 75W-90

Exxon Mobil Corporation 3225 Gallows Rd. Fairfax, VA 22037

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL Chart 201 Recommended Materials (Continued) MATERIAL 22. Dry Powder Lubricant

SPECIFICATION

PRODUCT

SAE AMS-M-7866 Molykote Z

SUPPLIER Haskell Inc. 100 E. Graham Place Burbank, CA 91502-2077

Molykote Z

Wilco Co. 4425 Bandini Blvd. Los Angeles, CA 90023

Molykote Z Moly-Powder

Dow Corning Corporation Midland, MI 48686-0994

TECTYL 502C

Daubert Chemical Co. 4700 South Central Avenue Chicago. IL 60638

VpCI-369 M

Cortec Corporation 4119 White Bear Parkway St. Paul, MN 55110

Stoddard Solvent (Mineral Spirits)

Barton Solvents, Inc. 201 S. Cedar Street Valley Center, KS 67147

25. Lubricating Grease

Lubriplate No. 130AA

Lubriplate Lubricants Company 129 Lockwood Newark, NJ 07105-4720

26. Lubricant - Paste

Molykote M77

Dow Corning P.O. Box 997 3901 So. Saginaw Rd. Midland, MI 48641

27. Lubricating Oil

Marvel Mystery Oil

Turtle Wax, Inc. Westmont, IL 60559-0247

28. Lubricant - Paste

Molykote G-n

Dow Corning P.O. Box 592 3901 S. Saginaw Rd. Midland, MI 48641

Lube-Lok 5306

Everlube Products 100 Cooper Circle Peachtree City, GA 30269

Molykote 3402

Dow Corning P.O. Box 592 3901 S. Saginaw Rd. Midland, MI 48641

Drilube No. 2

Drilube Co. 711 W. Broadway Glendale, CA 91204

23. Corrosion Preventive Compound

24. Cleaning Solvent

29. Lubricant Solid Film, Heat Cured, and Corrosion Inhibiting

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MIL-PRF-16173 Grade 2

MIL-PRF-680 Type III

MIL-L-46010

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL Chart 201 Recommended Materials (Continued) MATERIAL 30. Lubricating Grease, Gasoline and Oil Resistant

SPECIFICATION

PRODUCT

SAE AMS-G-6032 Royco 32

SUPPLIER ANDEROL Inc. 215 Merry Lane East Hanover, NJ 07936

Molykote 3452

Dow Corning P.O. Box 592 3901 S. Saginaw Rd. Midland, MI 48641

NYCO Grease GN HC

NYCO S. A. 66 Avenue des Champs-Elysees BP 414, 75366 Paris Cedex 8 France

AeroShell S.7108

Shell Oil Co. One Shell Plaza Houston TX, 77001

TT-S-1732 31. General Purpose Sealing Compound; Pipe Joint and Thread, Lead Free

RectorSeal® No. 5

The RectorSeal Corporation 2601 Spenwick Drive Houston, Texas 77055

32. Fluid Deicing/Antiicing, Aircraft

Type I per SAE AMS 1424 or ISO 11075

UCAR ADF Concentrate

Union Carbide Customer Center 10235 W Little York Rd. Houston, TX 77040

Type II per SAE AMS 1428 or ISO 11078

UCAR ADF 50/50

Union Carbide Customer Center 10235 W Little York Rd. Houston, TX 77040

Type IV per SAE AMS 1428

Hoechst Safewing MP IV 1957

Hoechst AG Werk Gendorf Burgkirchen, D-84508 Germany

Type IV per SAE AMS 1428

UCAR ULTRA+

Union Carbide Customer Center 10235 W Little York Rd. Houston, TX 77040

Type IV per SAE AMS 1428

Octagon Max Flight Type IV

Octagon Process Inc. 596 River Rd. Edgewater, NJ 07020-1105

MIL-PRF-6081 Grade 1010

Royco 481

ANDEROL Inc. 215 Merry Lane East Hanover, NJ 07936

Brayco 460

Castrol Industrial North America Inc. 150 West Warrenville Rd. Naperville, IL 60563

33. Oil, Preservative

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL Chart 201 Recommended Materials (Continued) MATERIAL

SPECIFICATION

PRODUCT AeroShell Turbine Oil 2

34. Air-Conditioning R-134a Refrigerant (Charging)

SUPPLIER Shell Oil Co. One Shell Plaza Houston TX, 77001 Obtain Locally

35. Grease

Dow Corning #33 Light or Molykote #33 Light silicone grease

Dow Corning P.O. Box 997 3901 S. Saginaw Rd. Midland, MI 48641

36. Refrigerant Leak Detector

Trace®

Highside Chemicals, Inc. P.O. Box 3748 Gulfport, MS 39505

CAUTION Use Trace® in R-12 and compatible refrigerant systems. DO NOT USE in R-134a System. Fluoro-Lite® TP-3830

Tracer Products 956 Brush Hollow Road P.O. Box 483 Westbury, NY 11590

CAUTION Use Fluoro-Lite® TP-3830 in R-12 and compatible refrigerant systems. DO NOT USE in R-134a System. 37. Refrigerant Leak Detector

Trace2®

Highside Chemicals, Inc. P.O. Box 3748 Gulfport, MS 39505

CAUTION Use Trace2® in R-134a, other CFC, HFC and HCFC systems. DO NOT USE in R-12 System. Fluoro-Lite® TP-3840

Tracer Products 956 Brush Hollow Road P.O. Box 483 Westbury, NY 11590

CAUTION Use Fluoro-Lite® TP-3840 in R-134a, other CFC, HFC and HCFC systems. DO NOT USE in R-12 System. 38. Refer to Item No. 37. 39. Lubricant/corrosion Preventive Compound

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MIL-L-87177

Super-Corr B

Lectro-Tech, Inc 4556 South Manhattan Avenue Suite L Tampa, FL 33611

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL Chart 201 Recommended Materials (Continued) MATERIAL

SPECIFICATION

PRODUCT

SUPPLIER

40. Oil (Air-Condition)

525 Viscosity

Delco Air Refrigerant Oil (Viscosity 525)

White Consolidated Industries Inc. 6000 Perimeter Dr. Dublin, OH 43017

41. Oil (Air-Condition)

Ester Oil

Emkarate RL 100E

CPI Engineering Services, Inc. 2300 James Savage Road Midland, MI 48642

Air-conditioning Flush

Castrol North America Special Products Division 16715 Von Karmen Ave. Irvine, CA 92714-4918

ISO 68

National Refrigerants Inc. 661 Kenyon Ave. Bridgeton, NJ 08302

42. Air-Conditioning Refrigerant Flush Fluid 43. Oil, Air-Conditioning

Polyol Ester Oil

44. Oil, Chain Lubricant

45. Grease

46. Grease

MIL-PRF-27617 Type III

SAE 30W Mineral Oil

Obtain Locally

Mobil Delvac Synthetic Gear Oil 75W-90

Obtain Locally

Mobil Aviation Grease SHC 100

Exxon Mobil Corporation 3225 Gallows Rd. Fairfax, VA 22037

Krytox 240AC

Miller-Stephenson George Washington Hwy. Danbury, CT 06810

47. Lubricating Grease

Aeroshell Grease No. 6 Shell Oil Company 1 Shell Plaza P.O. Box 2463 Houston, TX 77001

48. Lubricating Grease

Aeroshell Grease No. 7 Shell Oil Company 1 Shell Plaza P.O. Box 2463 Houston, TX 77001

* Take precaution when using MIL-PRF-23827, MIL-G-21164, MIL-PRF-81322, and engine oil as these contain chemicals harmful to painted surfaces.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

REPLENISHING FUEL HANDLING PRACTICES All hydrocarbon fuels contain some dissolved and suspended water. The quantity of water contained in the fuel depends upon the temperature and type of fuel. Jet fuel, with its higher aromatic content, tends to absorb and suspend more water than aviation gasoline. Along with the water, it will suspend rust, lint and other foreign materials longer. Given sufficient time, these contaminants will settle to the bottom of the tank. However, the settling time for jet fuel is five times that of aviation gasoline. Due to this fact, jet fuels require good fuel handling practices to ensure that the airplane is serviced with clean fuel. If recommended ground procedures are carefully followed, solid contaminants will settle to the bottom of the fuel cell and free water can be reduced to 30 parts per million (ppm), a value that is currently accepted by major airlines. Since most suspended materials can be removed from the fuel by sufficient settling time and proper filtration, they are not a major problem. Dissolved water has been found to be the major fuel contamination problem. Its effects are multiplied in airplanes operated primarily in humid regions and warm climates. Dissolved water cannot be removed from the jet fuel by micronic filters, but can be released by lowering the fuel temperature, such as will occur in flight. For example, a jet fuel may contain 65 ppm (8 ounces per 1000 gallons) of dissolved water at 80° F. When the fuel temperature is lowered to 14° F, only about 25 ppm will remain in solution. The difference of 40 ppm will have been released as supercooled water droplets which need only a piece of solid contaminant, or an impact shock to convert them to ice crystals. Tests indicate that these water droplets will not settle during flight and are pumped freely through the system. If they become ice crystals in the tank, they will not settle since the specific gravity of ice is approximately equal to that of jet fuel. Although 40 ppm of suspended water seems like a very small quantity, when added to suspended water in the fuel at the time of delivery, it is sufficient to ice a filter. While the critical fuel temperature range is from 0° to -20° F, which produces severe system icing, water droplets can freeze at any temperature below 32° F. Water in jet fuel also creates an environment favorable to the growth of a microbiological “sludge” in the settlement areas of the fuel cells. This sludge, plus other contaminants in the fuel, can cause corrosion of metal parts in the fuel system as well as clogging the fuel filters. Although this airplane uses bladder-type fuel cells, except for the outboard aft integral (wet wing) cell in each wing, and although all metal parts, except the standby boost pumps and jet transfer pumps, are mounted above the settlement areas, the possibility of filter clogging and corrosive attacks on fuel pumps exists if contaminated fuels are consistently used. Since fuel temperature and settling time affect total water content and foreign matter suspension, contamination can be minimized by keeping equipment clean, using adequate filtration equipment and careful water drainage procedures, storing the fuel in the coolest areas possible, and adequate settling time. Underground storage is recommended for fuels. Filtering the fuel each time it is transferred will minimize the quantity of suspended contaminants carried by the fuel. The primary means of fuel contamination control by the owner/operator is “Good Housekeeping”. This applies not only to the fuel supply, but to keeping the airplane system clean. The following is a list of steps that may be taken to prevent and recognize contamination problems: a. Know your supplier. It is impractical to assume that fuel free of contaminants will always be available. b. Exercise caution and watch for signs of fuel contamination. c.

Assure, as much as possible, that the fuel obtained has been properly stored.

d. The fuel should be filtered as it is pumped from storage to the truck. e. The fuel should be filtered as it is pumped from the truck to the airplane.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL f.

Perform filter inspections to determine if sludge is present.

g. Maintain good housekeeping by periodically flushing the fuel tankage system. The frequency of flushing will be determined by the climate and presence of sludge. h. Use only clean fuel servicing equipment. i.

After refueling, allow a three hour settling period whenever possible, then drain a small amount of fuel from each drain.

CAUTION: Remove spilled fuel immediately to prevent the fuel-contaminated surface from causing deicer boot and/ or tire deterioration. FUEL HANDLING SAFETY INFORMATION The following fuel handling safety information must be complied with during maintenance of the airplane fuel system. a. Make sure that the airplane is statically grounded to the servicing unit and to the ramp. b. Avoid damaging the deice boots when using refueling equipment. The deice boots are made of soft, flexible stock which may be damaged if refueling hoses, ladders or platforms are dragged across or rested against the deice boot surfaces. c.

Do not rest the fuel nozzle in the filler neck of the tanks.

d. If filling the wing tip tanks, allow sufficient time for the fuel to flow from the tip tank to the main tank. e. Remove the filler cap during draining or defueling to prevent damage or collapse of fuel cells. WARNING: The airplane and all equipment used in performing the operation must be properly grounded. This includes defueling equipment, work stands, purging equipment, and any powered or pneumatic devices. Equip work stands with a personnel static discharge plate of copper or zinc, affixed in such a position that personnel can contact the plate before coming in contact with the airplane. High static electrical charges are created by the contact and separation of unlike substances, or by any sort of motion of persons or material, and are a constant source of danger when generated in the presence of fuels or flammable vapors. Do not drain fuel tanks near the end of the working day and allow them to stand empty overnight. It could make conducive conditions for producing explosive vapors. If the system is not completely empty, residual fuel drains down the sides of the tank and forms puddles. During the night, fuel from the puddles evaporates into the air in the tank and a critical fuel-air ratio develop. An explosion could be set off by a spark. Avoid such a lapse of time between draining and purging of the fuel tanks. Ensure that the area is well ventilated before draining fuel. No smoking within 50 feet of the airplane. Place battery and generator switches in the OFF position. Disconnect all electrical power to airplane. If fuel contacts the eyes, rinse with cool, fresh water and seek medical attention immediately. Avoid allowing fuel to contact skin. When contact cannot be avoided, wash with mild soap and water. Visually inspect all connections and hoses for leaks. If any leaks are indicated or develop, discontinue servicing. CAUTION: Ensure that all equipment used for servicing the fuel system (draining, filling, defueling etc.) is properly grounded. Grounding jacks are located near the fuel filler ports on each wing. Do not fill the auxiliary fuel tanks until the main tanks and (if installed) the wing tip tanks are full.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FUEL GRADES AND TYPES WARNING: All maintenance and service personnel: Reference: FAA order 8110.34, dated March 31, 1988, “PROCEDURES FOR THE USE OF ALTERNATE FUELS FOR TURBINE-POWERED AIRCRAFT.” Switch fueling is the practice of mixing fuels with a flashpoint of less than 100° F (38° C) with fuels having a flashpoint of more than 100° F or vice versa. Mixing kerosene base JP-5, Jet-A or Jet-A1 fuels with wide-cut distillants, JP-4 and Jet-B is considered switch fueling. Switch fueling changes the fuel/air mixture flammability characteristics. When switch fueling must be accomplished, fueling rates must be reduced to 1/2 of the normal rates. Chart 202 gives fuel refiners’ brand names, along with the corresponding designations established by the American Petroleum Institute (API) and the American Society of Testing Material (ASTM). The brand names are listed for ready reference and are not specifically recommended by Hawker Beechcraft Corporation. Any product conforming to the recommended specification may be used. Jet A, Jet A-1, Jet B, JP-4, JP-5 and JP-8 fuels may be mixed in any ratio. Aviation gasoline, grades 80 red (formerly 80/87), 91/96, 100LL Blue, 100 Green (formerly 100/130) and 115/145 Purple are emergency fuels and may be mixed in any ratio with normal fuels when necessary. However, use of the lowest octane rating available is suggested due to its lower lead content. CAUTION: The use of aviation gasoline shall be limited to 150 hours of operation during each Time Between Overhaul (TBO) period. NOTE: In some countries 100LL Blue is colored Green and designated 100L. The use of aviation gasoline as a jet fuel should be minimized wherever possible due to the adverse effects on the hot section parts and the corrosion of turbine vanes.

Chart 202 Fuel Brands And Type Designations Company

Product Name

Designation

American Oil Company

American Jet Fuel Type A American Jet Fuel Type A-1

Jet A Jet A-1

Atlantic Refining Company

Arcojet-A Arcojet-A-1 Arcojet-B

Jet A Jet A-1 Jet B

BP Trading Company

BP A.T.K. BP A.T.G.

Jet A-1 Jet B

California Texas Company

Caltex Jet A-1 Caltex Jet B

Jet A-1 Jet B

Cities Service Company

Turbine Type A

Jet A

Continental Oil Company

Conoco Jet-40 Conoco Jet-50 Conoco Jet-60 Conoco Jet JP-4

Jet A Jet A Jet A-1 Jet B

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL Chart 202 Fuel Brands And Type Designations (Continued) Company

Product Name

Designation

Exxon Oil Company

Exxon Turbo Fuel A Exxon Turbo Fuel 1-A Exxon Turbo Fuel 4

Jet A Jet A-1 Jet B

Gulf Oil Company

Gulf Jet A Gulf Jet A-1 Gulf Jet B

Jet A Jet A-1 Jet B

Mobil Oil Company

Mobil Jet A Mobil Jet A-1 Mobil Jet B

Jet A Jet A-1 Jet B

Phillips Petroleum Company

Philjet A-50 Philjet JP-4

Jet A Jet B

Pure Oil Company

Purejet Turbine Fuel Type A Purejet Turbine Fuel Type A-1P

Jet A Jet A-1

Richfield Petroleum Company

Richfield Turbine Fuel A Richfield Turbine Fuel A-1

Jet A Jet A-1

Shell Oil Company

Aeroshell Turbine Fuel 640 Aeroshell Turbine Fuel 650 Aeroshell Turbine Fuel JP-4

Jet A Jet A-1 Jet B

Sinclair Oil Company

Sinclair Superjet Fuel Sinclair Superjet Fuel

Jet A jet A-1

Standard Oil of California

Chevron TF-1 Chevron JP-4

Jet A-1 Jet B

Standard Oil of Kentucky

Standard JF A Standard JF A-1 Standard JF B

Jet A Jet A-1 Jet B

Standard Oil of Ohio

Jet A Kerosene Jet A-1 Kerosene

Jet A Jet A-1

Texaco

Texaco Avjet K-40 Texaco Avjet K-58 Texaco Avjet JP-4

Jet A Jet A-1 Jet B

Union Oil Company

76 Turbine Fuel Union JP-4

Jet A-1 Jet B

Jet A - Aviation Kerosene Type fuel with -40° F(-40° C) Freeze Point. Jet A-1 - Aviation Kerosene Type Fuel with -58° F (-50° C) Freeze Point Jet B - A low grade, Kerosene Type fuel with a freeze point of -60° F (-51° C), similar to MIL-T-5624 grade JP-4, which has a freeze point of -76° F (-60° C).

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

JET FUEL ADDITIVES Condensation of water in the fuel tanks increases the possibility of microbiological contamination of the fuel which can damage skins, coatings and sealants in the fuel tanks. Fuel additives, such as the anti-icing additives conforming to MIL-I-85470 and a specific fuel Biocide manufactured under the trade name Biobor JF, are compounds which contain anti-fungal and biocidal agents to reduce the possibility of contamination of the fuel, as well as clogging of fuel filters and lines. Either of these agents may be used separately or together in the fuel system with no detrimental effect on the fuel system components. The following is a description of the two available fuel additive compounds which are effective biocidal and anti-fungal agents.

Chart 203 BIOBOR JF STERILIZATION AND MAINTENANCE TREATMENT LEVELS TURBINE FUEL

BIOBOR JF @ 270 PPM

BIOBOR JF @ 135 PPM

LBS.

GALS.

LBS.

GALS.

FL. OZS.

LBS.

GALS

FL. OZS.

670

100

0.18

0.02

2.63

0.09

0.01

1.32

1,340

200

0.36

0.04

5.26

0.18

0.02

2.63

2,010

300

0.54

0.06

7.89

0.27

0.03

3.95

2,680

400

0.72

0.08

10.53

0.36

0.04

5.26

3,350

500

0.90

0.10

13.16

0.45

0.05

6.58

6,700

1,000

1.18

0.21

26.46

0.90

0.10

13.16

13,400

2,000

3.62

0.41

52.92

1.81

0.21

26.46

16,750

2,500

4.52

0.52

66.08

2.26

0.26

33.04

33,500

5,000

9.01

1.03

132.16

4.52

0.52

66.08

67,000

10,000

18.09

2.07

264.47

9.05

1.03

132.31

To estimate the fluid ounces of biocidal agent required to give a concentration of 270 ppm, multiply pounds of fuel by 0.004. For 135 ppm multiply pounds of fluid by 0.002. MIL-I-85470 JET FUEL ANTI-ICING INHIBITOR Jet fuel anti-icing inhibitor (2, Chart 201) is primarily an anti-icing agent, but also has excellent microbiological sludge deterrent characteristics. Very soluble in water, but only slightly soluble in fuel, this additive must be precisely blended in the fuel by a metering device that permits injection of the agent into a flowing stream of fuel to ensure even dispersal. Fuel distributors may tank or batch blend, or it may be preferred to blend at the airplane when fueling. If the tanker truck is not equipped with the proper metering device, it may be necessary to carry the anti-icing agent and the blending device in the airplane. When blending the anti-icing agent with fuel, the concentration of additive should not be less than 20 fluid ounces per 260 gallons of fuel or more than 20 fluid ounces per 104 gallons of fuel. When adding previously blended fuel, the additive concentration should not be less than 0.06 percent by volume or more than 0.15 percent by volume. This additive should be used on a continuous basis.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL BIOCIDAL AGENT CAUTION: Drain all sumps prior to refueling. Excessive water concentrations in contact with excessive BIOBOR JF concentrations can result in formation of solid crystalline products in a fuel system. The biocidal agent (3, Chart 201) is not an anti-icing agent, but is intended to be used specifically as a fuel biocide. The compound is an extremely efficient biocidal agent and is very soluble in fuel as well as water. Biocidal agent disperses throughout the entire fuel system to even the most remote areas soon after introduction into the system. The compound is used as a periodic treatment in concentrations of 135 ppm when the airplane has been operated in an environment conducive to fungal or microbial contamination, or when such contamination is evidenced by dirty sump drains, clogged filters, odor or visual evidence in the tanks, etc. Biocidal agent may also be used in concentrations of 270 ppm as a single dose shock treatment to clean out and sterilize a very contaminated system. Any system that is contaminated should be treated at the 270 ppm level. When sterility is achieved, the 135 ppm level may be used. Parked airplanes require only one treatment until fuel is burned off or replaced. The biocidal agent is not volatile and may remain in the tank until the fuel is used. The preferred method of introducing biocidal agent into the fuel is by injection through a metering device. If no metering device is available, blending may be accomplished by batch blending or by over-the-wing blending while filling the tanks. When half of the required quantity of fuel has been added, gradually introduce the compound directly into the stream of fuel while adding the other half of the fuel. Complete mixing is necessary for fungicidal activity. Tank surface, gages, filters and linings should be inspected or replaced as necessary, depending upon the severity of the contamination. The biocidal agent must be used at a high enough concentration to kill, not just control the infestation, and when used only periodically, it must be used often enough to prevent new growth. The mixture must be able to contact the entire surface of the fuel tank interiors and remain in contact up to 72 hours to effect the kill. Treated airplanes which are flown should be re-treated at consecutive fills so that a 72-hour contact time is accomplished. Refer to Chart 203 for fuel ratios for specified concentrations as an aid in blending. Be sure to account for residual fuel in the tanks so that the proper mixture is maintained.

FILLING THE TANKS WARNING: All maintenance and service personnel: Reference: FAA order 8110.34, dated March 31, 1988, “PROCEDURES FOR THE USE OF ALTERNATE FUELS FOR TURBINE-POWERED AIRCRAFT.” Switch fueling is the practice of mixing fuels with a flashpoint of less than 100° F (38° C) with fuels having a flashpoint of more than 100° F or vice versa. Mixing kerosene base JP-5, Jet-A or Jet-A1 fuels with wide-cut distillants, JP-4 and JET-B is considered switch fueling. Switch fueling changes the fuel/air mixture flammability characteristics. When switch fueling must be accomplished, fueling rates must be reduced to 1/2 of the normal rates. The safety information under the heading fuel handling safety information in this chapter must be complied with. When filling the airplane fuel tanks, always observe the following: a. Statically ground the airplane to the servicing unit and to the ramp. b. Service the main tanks first; main filler caps are located in the outboard fuel cell on the leading edge of each wing near the wing tip. c.

Service the auxiliary tanks second through the auxiliary filler caps located on top of the wing center section inboard of each nacelle.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL d. Allow a three hour settling period if possible. e. Drain a small amount of fuel from each drain point.

DRAINING FUEL SYSTEM WARNING: The fuel handling safety information under the heading FUEL HANDLING SAFETY INFORMATION in this chapter must be complied with. A defueling adapter is provided as an integral part of the nacelle fuel cell. The defueling adapter, located aft of the standby boost pump, contains a check valve to prevent fuel drainage when the plug is removed. Drain each wing fuel system as follows: a. Remove the cover on the bottom of the nacelle to gain access to the adapter plug. b. Place a suitable container under the drain plug. c.

Remove the plug and screw an AN832-12 union into the adapter. The fuel will begin draining as the check valve is unseated by the union.

d. After fuel is drained, remove the AN832-12 union and replace plug. e. Replace the access cover. f.

Install the filler cap.

NOTE: The fuel crossfeed will not transfer fuel from the LH to RH fuel system or vice versa. FUEL SYSTEM DEFUELING WARNING: The fuel handling safety information under the heading FUEL HANDLING SAFETY INFORMATION in this chapter must be complied with. Defuel the airplane with the aid of a fuel truck. Defueling shall be accomplished in accordance with the following: a. Remove fuel filler caps. b. Connect a static ground cable from the airplane to a ground stake. c.

Connect a static ground cable from the defueling vehicle to a ground stake.

d. Connect a static ground cable from the defueling truck to the airplane. e. Remove the cover on the bottom of the nacelle to gain access to the adapter plug. f.

Attach the hose from the defueling truck to the AN832-12 union.

g. Remove the plug from the defueling adapter, located aft of the standby boost pump, and screw the AN832-12 union into the adapter. This will allow fuel to flow from the airplane to the defueling vehicle. Attach the clamp to the hose to prevent fuel leakage around the hose-union-adapter connection. Start the defueling pump. h. When defueling is completed, shut off defueling pump. Disconnect the hose and the AN832-12 union from the defueling adapter. i.

Install the adapter plug.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL j.

Disconnect the AN832-12 union from the hose.

k.

Disconnect the static ground cable from the defueling vehicle to the airplane.

l.

Disconnect the static ground cable from the defueling vehicle to the ground stake.

m. Disconnect the static ground cable from the airplane to the ground stake. n. Install the fuel filler caps on the airplane. FUEL SYSTEM PURGING WARNING: The fuel handling safety information under the heading FUEL HANDLING SAFETY INFORMATION in this chapter must be complied with. a. Secure the airplane for maintenance. Disconnect the external power. Disconnect the battery. b. Ground the airplane and defuel the fuel cells in accordance with FUEL SYSTEM DEFUELING procedures in this chapter. c.

Pour approximately 5 gallons of lubricating oil (33, Chart 201) into each cell to reduce the flash point of the empty cells.

d. Drain the lubricating oil from each cell and apply inert gas, such as carbon dioxide or nitrogen, as follows: CAUTION: Use only dehydrated gas. 1. Open the fuel cell drain and vents. Remove the filler cap. 2. Insert an air hose with a 1/4 inch orifice into the filler neck. Apply inert gas at approximately 50 psi for approximately 30 minutes. 3. Close the drain. WARNING: Remove the fiber horn when using any fire extinguisher bottle as a carbon dioxide source. The horn is too large to fit into the filler neck and may build a static electrical charge as the gas passes rapidly through it. Ground both the fire extinguisher nozzle and the bottle to the airplane. Discharge the carbon dioxide into the fuel cells slowly, at a rate of one pound or less per minute, to avoid building a static electrical charge or damaging the cells with low temperature. The size of the carbon dioxide bottle used can be varied to meet existing conditions. The 15-pound size is handy. The total amount recommended is based on the quantity usually needed to purge a tank or tanks of the size under discussion. However, more may be needed to obtain a safe reading on the combustible gas indicator. It is permissible to use nitrogen or any other inert gas in place of the carbon dioxide gas called out in any of the purging procedures. The same precautionary measures stated above shall be observed. 4. Continue applying purging gas to the fuel cells at a rate of one pound or less of gas per minute. Use at least 3 pounds of purging gas in each cell.

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NOTE: Larger amounts of carbon dioxide or nitrogen gas must be used to purge large fuel cells or multiple fuel cells with one filler neck. After the purging process has been completed, wait 2 to 3 hours, then test each fuel cell for the presence of dangerous fuel vapors with a combustible gas indicator. If fuel vapors are present, continue purging the fuel cells until the test results indicate no vapors remain. e. After completing the maintenance tasks that required purging of the fuel system, fuel the airplane in accordance with FILLING THE TANKS. f.

Disconnect the static ground cable from the fueling vehicle to the airplane.

g. Disconnect the static ground cable from the defueling vehicle to the ground stake. h. Disconnect the static ground cable from the airplane to the ground stake. i.

Install the fuel filler caps and return the airplane to service.

FUEL CELL PRESERVATION CAUTION: Never store fuel cells in the vicinity of electrical equipment, such as generators and motors. The movement of brushes across the commutators of these units results in minute sparks that cause the formation of ozone gas. Ozone has a highly destructive effect on fuel cells. Although it leaves no visible indication, ozone makes the material of which the cells are formed brittle so that the cells will disintegrate upon the application of stress. NOTE: Preservation is not necessary for in-service fuel cells when the cell is to be empty for an indefinite period. The fuel cell should not be open to the atmosphere except for the normal vent lines in the airplane. If AVGAS was in the fuel cell prior to emptying, purge the cell with aviation kerosene prior to leaving the fuel cell empty for an indefinite period. For information pertaining to the storage of Uniroyal fuel cells, refer to Report FC 1473-73 entitled “Recommended Handling and Storage Procedures for Bladder Type Fuel and Oil Cells” which is published by Uniroyal Inc., Engineered Systems Department, Mishawaka, Indiana. Loral (formerly Goodyear) fuel cells are constructed of polyethylene, they need not be treated for storage. The only stipulation on storage of Loral fuel cells is that they be carefully wrapped for protection against dust, then be stored at room temperature in a location shaded from sunlight.

OIL SYSTEM CAUTION: Any time the oil system has been contaminated by metal particles, the oil cooler must be replaced and the oil system flushed to prevent engine damage. In addition, all airplane components and associated plumbing utilizing the engine oil system, such as the propeller governors, must be flushed until free of contamination. Servicing the engine oil system primarily involves maintaining the engine oil at the proper level. The oil tank is provided with an oil filler neck and quantity dipstick cap which protrudes through the accessory gear case at the eleven o’clock position. The dipstick is marked in U.S. quarts and indicates the amount of oil required to fill the tank. Access to the dipstick cap is gained by opening the small access door in the upper aft cowling. Service the oil system with oil as specified in Pratt and Whitney Service Bulletin No. 13001.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL CAUTION: Do not mix different brands of oil when adding oil between oil changes. Different brands of oil may be incompatible because of differences in their chemical structure. The total oil tank capacity is 2.5 U.S. gallons (10 quarts), of which only 1.5 gallons (6 quarts) are usable. Additionally approximately 4 quarts of oil are required to fill the lines and cooler, giving a total system capacity of approximately 14 quarts; however, because of the residual oil trapped in the system, no more than 11 quarts should be added during an oil change. Check the oil level as follows any time the oil has been changed or the engine has remained stationary for more than 12 hours as follows: a. Run the engine at idle for 2 minutes. b. Shut down the engine. c.

Check the oil level.

d. Add only oil of the same brand as that already in the engine, when the No. 2 mark is exposed on the dip stick. The normal oil level is at the one quart mark. Overfilling the engine with oil may cause a discharge of oil through the breather until a satisfactory level is reached. CAUTION: Remove any spilled oil and clean any oil contaminated area immediately to prevent tire deterioration.

LANDING GEAR SYSTEM BRAKE SYSTEM REPLENISHING Brake system replenishing is limited primarily to maintaining the hydraulic fluid level in the reservoir mounted on the upper left side of the nose avionics compartment aft bulkhead. A dipstick is provided for measuring the fluid level. When the reservoir level is low, add a sufficient quantity of hydraulic fluid (1, Chart 201) to fill the reservoir to within one inch of the top. LANDING GEAR ACCUMULATOR PRECHARGING The landing gear accumulator may be charged as follows: WARNING: The airplane must be placed on jacks anytime the landing gear system accumulator is serviced and anytime maintenance or rigging of the landing gear system is performed. When jacking the airplane in an unsheltered area where winds in excess of 35 kts may be encountered, never jack more than one wheel off the ground at one time. If the landing gear is only partially retracted during maintenance, always cycle the landing gear with the power pack through at least one complete cycle before removing the airplane from the jacks. a. Place the airplane on jacks. b. Open the access door on the top of the left wing center section. c.

Remove the cap from the accumulator filler valve (Ref. Figure 201).

d. Connect a regulated nitrogen source to the accumulator filler valve e. Open the accumulator filler valve by rotating the swivel nut. f.

Open the valve on the nitrogen supply source.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL g. When the pressure gage reads 800 ±50 psi, rotate the swivel nut of the accumulator filler valve to the closed position. Tighten the swivel nut to a torque of 50-70 inch-pounds. h. Close the valve on the nitrogen supply source. i.

Slowly bleed off the pressure in the nitrogen supply source line and disconnect the line from the accumulator filler valve.

j.

Replace the cap on the accumulator filler valve.

k.

Close the access door on the left wing center section.

Accumulator Filler Valve Figure 201 LANDING GEAR POWER PACK SERVICING a. Open the access door on the top of the left wing center section. b. Slowly bleed off the air pressure in the landing gear power pack. c.

Add hydraulic fluid (1, Chart 201) to the reservoir until level with the mark indicated on the dipstick.

d. Install the dipstick. e. Close the access door on the top of the left wing center section.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL HYDRAULIC SYSTEM FILTERS AND SCREENS SERVICING Filters, screens and associated O-rings of the landing gear hydraulic power pack system should be replaced or cleaned according to the inspection intervals given in Chapter 5-11-00. Access and procedures for servicing and replacement are described in the landing gear hydraulic power pack section of Chapter 32-30-00. Filters and screens to be serviced include the landing gear power pack system filter, the finger screens, the bleed air orifice screens, and their associated O-rings. NOTE: All filters and screens in the hydraulic landing gear system must be replaced or cleaned anytime any hydraulic landing gear system component (other than filters or screens and O-rings) is replaced, then at the first inspection after component replacement. MAIN LANDING GEAR STRUT SERVICING CAUTION: Never tow or taxi with a flat strut. Even brief towing or taxiing with a deflated strut can cause damage. Damage to the torque knee may result if the strut is inflated while the airplane is on jacks. a. Remove the valve cap on the top of the main gear strut. b. Depress the valve core and slowly release the air. WARNING: All air pressure must be released from the main landing gear struts before removing the valve cores from the valve stems. c.

Allow the strut to fully compress.

d. Remove the valve core from the valve stem. e. Place one end of a 1/4-inch I.D. hose over the valve stem. f.

Submerge the other end of the hose in a container of clean hydraulic fluid (1, Chart 201).

g. Slowly extend the strut to draw hydraulic fluid into the strut. h. When the strut is fully extended, slowly compress the strut to expel any excess hydraulic fluid and air. i.

Recycle the strut as many times as necessary to relieve the air.

j.

With the strut compressed and all of the air removed, remove the hose and install the valve core.

k.

With the airplane on the ground and empty except for full fuel and oil, inflate the main strut with dry filtered air until the piston is extended 3.23 to 3.49 inches.

NOSE LANDING GEAR STRUT SERVICING CAUTION: Never tow or taxi with a flat strut. Even brief towing or taxiing with a deflated strut can cause damage. Damage to the torque knee may result if the strut is inflated while the airplane is on jacks. a. Remove the valve cap on the top of the nose gear strut. b. Depress the valve core and slowly release the air. WARNING: All air pressure must be released from the nose landing gear strut before the valve core is removed from the valve stem.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL c.

Allow the strut to fully compress.

d. Remove the valve core from the valve stem. e. Connect one end of a 1/4-inch I.D. hose to the valve stem. Submerge the other end of the 1/4-inch I.D. hose in a container of clean hydraulic fluid (1, Chart 201). f.

Slowly extend the nose landing gear strut to draw hydraulic fluid into the nose landing gear strut.

g. When the nose landing gear strut is fully extended, slowly compress the strut to expel any excess hydraulic fluid and air. h. Recycle the nose landing gear strut as many times as necessary to relieve the air. i.

With the nose landing gear strut compressed and all of the air removed, remove hose and install the valve core.

j.

With the airplane on the ground and empty except for full fuel and oil, inflate the nose strut with dry filtered air until the piston is extended 3.77 to 4.06 inches.

SHIMMY DAMPER SERVICING Check and replenish the fluid in the shimmy damper as follows: Insert a wire, approximately 1/8 inch in diameter, through the hole in the aft end of the piston rod until the wire is touching the bottom of the hole in the plug. a. Mark the wire at the rod assembly end. b. Remove the wire from the shimmy damper rod assembly. c.

Measure the distance from the mark to the end of the wire that was inside of the shimmy damper rod assembly.

NOTE: To determine if the wire is inserted into the hole of the plug, insert the wire several times. Note the depth of the wire at each insertion. When the wire is inside the shimmy damper plug hole and touching bottom, the wire depth should be approximately 1/2 inch deeper in the shimmy damper rod assembly. d. If the measured distance on the wire is 2.63 to 2.88 inches, the shimmy damper is full of fluid and no further action is required. If the measured distance on the wire is 3.125 inches or longer, the shimmy damper should be removed and filled as follows: 1. Remove the shimmy damper assembly from the nose landing gear. 2. Count and note the number of threads visible on the end fitting above the end fitting locknut. 3. Loosen the locknut and remove the end fitting from the end of the rod assembly. 4. Secure the shimmy damper in a vise in a fixed vertical position with the fitting end down. 5. Carefully remove the snap ring, washer and spring from inside of the upper end of the piston rod. CAUTION: The snap ring, washer and spring in the piston and rod assembly are under compression. 6. Remove the plug from the piston and rod assembly upper end by screwing a long 10/32 bolt into the plug and pulling it out of the shimmy damper piston and rod assembly. 7. Fill the piston rod assembly with hydraulic fluid (1, Chart 201). 8. Screw another long 10/32 bolt in the plug in the lower end of the piston and rod assembly.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 9. Pull down on the bolt screwed into the lower plug while inserting the upper plug, spring, washer and snap ring in the piston and rod assembly upper end. 10. Remove the two 10/32 bolts from the upper and lower plug. 11. Install the end fitting in the upper rod and piston assembly upper end, keep the locknut at the thread distance on the end fitting noted in the preceding steps, then insert the end fitting into the rod and piston assembly until the locknut is tight. 12. Tighten the locknut on the end fitting. 13. Install the shimmy damper on the airplane. TIRES The main landing gear is equipped with 10-ply, 19.5 x 6.75 x 8 rim-inflated tubeless tires. The proper inflation for the main gear tires with the airplane fully loaded with fuel and oil is 90 ±2 psi or 85 ±2 psi with the airplane unloaded. The nose landing gear is equipped with an 8-ply, 22 x 6.75 x 10 rim-inflated tubeless tire. The proper inflation for the nose gear tire is 55 to 60 psi with the airplane fully loaded with fuel and oil. See chapter 32-40-00 in this Maintenance Manual for tire maintenance.

CABIN ENTRANCE DOOR DAMPER SERVICING Service the damper with hydraulic fluid (1, Chart 201) as follows: a. Remove the damper from the cabin door and the fuselage (Ref. Figure 202). b. Place the damper assembly with the barrel down. c.

Loosen the cap end on the barrel end by loosening the 3 set screws securing the cap end to the barrel.

d. Push down on the rod end until the piston is bottomed in the barrel. e. Slide the cap end up the rod and fill the barrel with a maximum of 215cc or 7.2 ounces of hydraulic fluid (1, Chart 201). f.

Replace the O-Rings and seal assembly on the cap end.

g. Slide the cap end down the rod into the barrel assembly. h. Secure the cap end in the barrel by tightening the 3 set screws.

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Cabin Door Damper Figure 202

BATTERY NICKEL-CADMIUM BATTERY (FL-1 THRU FL-214; FM-1 THRU FM-9) a. Check the battery electrolyte level. b. Fill with additional electrolyte as necessary. Refer to Chapter 24-31-00. LEAD ACID BATTERY (FL-215 AND AFTER; FM-10 AND AFTER) The battery does not require electrolyte servicing. The battery is constructed to prevent the loss of electrolyte during the charging process.

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AIR-CONDITIONING SYSTEM REFRIGERANT SERVICING Servicing the air-conditioning system consists of periodically checking the refrigerant level, checking compressor oil level and changing the system air filters. Charge the system whenever the refrigerant level is low, air has entered the system or components carrying refrigerant are replaced. Refrigerant leaks may be detected by inspection with a flameless leak detector. WARNING: Due to the air quality control regulations enacted in the United States, you are not permitted to vent refrigerant R-12 or R-134a into the atmosphere. When performing maintenance on the airconditioning system where refrigerant R-12 or R-134a can escape from the system, evacuate the system with a recovery or recycle servicing unit that will salvage the refrigerant. CAUTION: Airplanes originally equipped with an R-12 system may have been converted to an R-134a system even if Kit 130-5009 was not installed. R-12 and R-134a are not compatible. Therefore it is important to ensure that the correct refrigerant is used when servicing the system. PRECAUTIONARY REFRIGERANT SERVICING PROCEDURES Before attempting maintenance that requires opening of refrigeration lines or compressor fittings, maintenance personnel should be thoroughly familiar with the pertinent instructions. These instructions should be followed carefully to ensure that the system functions properly. If moisture is allowed to enter refrigerant lines, ice can form in the lines and hydrofluoric acid can form, causing damage to system components. Contamination of the system can cause damaging wear in the compressor. Care should be taken to prevent damage to all fittings and connections. Minute damage to a connection could cause it to leak. Any fittings contaminated with grease or dirt should be cleaned with a cloth dampened with alcohol (4, Chart 201). Do not use a chlorinated solvent, such as trichloroethylene, as a cleaning agent because it adds contaminants. WARNING: Eye protection must be worn when servicing the air-conditioning system. Do not smoke when servicing the system with refrigerant because it converts into a highly toxic gas when exposed to an open flame. Airplane serials FL-1 thru FL-127 and FM-1 thru FM-8, use refrigerant R-12 (5, Chart 201) in this system. Airplane serials FL-128 and after, FM-9 and after, and prior airplanes with Beech Kit No. 130-5009 installed use refrigerant R-134a (34, Chart 201). All other refrigerants, particularly those containing methyl chloride, will cause deterioration of the aluminum components. AIR-CONDITIONING SYSTEM REFRIGERANT AND OIL CAPACITIES NOTE: Refer to Chart 204. The chart column identified as (1) is the total quantity of oil in fluid ounce in the system, (2) is the quantity of oil in fluid ounce charged to a new compressor before it is shipped, (3) is the quantity of oil in fluid ounce which must be added to the system before initial operation. If simple conversions have been accomplished (Refrigerant change without compressor change) rely on kit instructions for proper servicing levels. If compressor type changes have occurred rely on applicable kit directions which should meet the serial group class for refrigerant type used (Ref. Chart 204).

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Chart 204 Air-Conditioning System Refrigerant Capacities (1) Sys. Oil Qty., Fl. Oz.

(2) New Comp. Oil, Fl. Oz.

(3) Add. Oil, Fl. Oz.

MINERAL/ 525

32

8

24

9.5

MINERAL/ 525

32

8

24

R-134A

8.2

POE 100

32

8

24

FM-1 thru FM-8 with Kit 130-5009-1 Installed

R-134A

8.2

POE 100

32

8

24

FL-128 thru FL-492, FL-494 thru FL-499

R-134A

8.2

POE 100

31

10

21

FM-9 thru FM-13

R-134A

8.2

POE 100

31

10

21

FL-493, FL-500 and After

R-134A

3.5

POE ISO68

11

8

3

FM-14 and After

R-134A

3.5

POE ISO68

11

8

3

Serial Group

Refrig. Type

Sys. Refrig. Qty., LBS.

FL-1 thru FL-127

R-12

9.5

FM-1 thru FM-8

R-12

FL-1 thru FL-127 with Kit 130-5009-1 Installed

Oil Type

R-12 AIR-CONDITIONING REFRIGERANT LEVEL CHECK NOTE: Refer to Chart 204 for the air-conditioning refrigerant capacity. a. Remove the access door on top of the fuselage nose section to observe the sight glass (Ref. Figure 203). On aircraft that do not have the sight glass, connect pressure gauges to the service ports and use the Suction and Discharge Pressure Chart. Refer to Figure 205 for airplanes with the R-12 air-conditioning system. A low pressure reading indicates refrigerant level is low. b. Start the RH engine and place the CABIN TEMP MODE switch in the MANUAL COOL position. c.

Hold the DECR switch for one minute to position the bypass valves in the cool position.

d. Allow the system to operate for approximately two minutes. e. Observe the sight glass on the receiver-dryer. f.

If the sight glass seems milky or if bubbles appear, the system is low on refrigerant.

R-134A AIR-CONDITIONING REFRIGERANT LEVEL CHECK NOTE: Refer to Chart 204 for the air-conditioning refrigerant capacity. The only way to ensure a proper charge of the R-134a system is to recover the refrigerant currently in the system and to recharge the system with the proper amount of refrigerant.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL CHARGING THE R-12 AIR-CONDITIONING SYSTEM (FL-1 THRU FL-127, FM-1 THRU FM-8) NOTE: Refer to Chart 204 for the air-conditioning refrigerant capacity. a. The air-conditioning system should be charged with refrigerant as noted when: 1. There are bubbles in the refrigerant in the sight glass indicating the refrigerant quantity is low. 2. Leaks have been detected in the system. 3. Air has entered the system. 4. Components that carry refrigerant have been replaced. NOTE: It is permissible to add refrigerant leak detector (36, Chart 201), in the quantity of 1/8 ounce per pound of refrigerant, to the suction side of the refrigerant system to detect leaks. A red film will appear in the areas of leakage. b. Charge the air-conditioning system with refrigerant as follows: 1. The system should be serviced by a qualified air-conditioning service person. 2. Refrigerant service valves are located in the nose wheel well (Ref. Figure 204), and under the cabin floorboards aft of the forward partition. 3. It is recommended that the service unit used for charging be equipped with a supply cylinder heated to maintain sufficient pressure to force refrigerant into the system without operating the compressor. 4. If a heated cylinder is not available, the system may be charged without operating the compressor by allowing refrigerant to flow into the system until equilibrium pressure is reached. 5. After equilibrium pressure is reached, start the compressor in the MAN COOL mode. 6. Hold the DECR switch for one minute to position the bypass valves in the cool position. 7. With the RH engine operating at approximately 65 percent N1, add refrigerant vapor to the suction side of the glass. 8. The compressor should operate until no bubbles are seen in the sight glass. 9. Add approximately 6 ounces of refrigerant to the suction port of the system after all bubbles have disappeared in the sight glass.

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Air-Conditioner Receiver-Dryer Figure 203

Air-Conditioning Nose Wheel Well Service Valves (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) Figure 204 (Sheet 1 of 2)

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A FS 57.50 REF

FS 70.75 REF

TO CONDENSER ASSEMBLY

FS 30.00 REF

HIGH PRESSURE SERVICE PORT

B FS 95.50 REF

LOW PRESSURE SERVICE PORT

FS 79.00 REF

VIEW LOOKING OUTBOARD LEFT DETAIL

FS 53.62 REF

A

HIGH PRESSURE PORT (RED)

LOW PRESSURE PORT (BLUE)

DETAIL

B

BB21B 061454AA.AI

Air-Conditioning Nose Wheel Well Service Valves (FL-493, FL-500 and After; FM-14 and After) Figure 204 (Sheet 2 of 2)

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Compressor Suction and Discharge Pressure (Dual Evaporator and High Blower) R-12 System (FL-1 thru FL-127; FM-1 thru FM-8) Figure 205

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL CHARGING THE R-134A AIR-CONDITIONING SYSTEM (FL-1 THRU FL-492, FL-494 THRU FL-499; FM-1 THRU FM-13) NOTE: Refer to Chart 204 for the air-conditioning refrigerant capacity. WARNING: Due to the air quality control regulations enacted in the United States, you are not permitted to vent refrigerant R-134a into the atmosphere. When performing maintenance on the airconditioning system where refrigerant R-134a can escape from the system, evacuate the system with a recovery/recycle service unit that will recover the refrigerant. The air-conditioning system is a high pressure system. Before disconnecting a refrigerant line, the system must be discharged with a recovery/recycle service unit. Evacuate the entire system for 15 minutes. Use only R-134a compatible recovery/recycle service unit. NOTE: It is permissible to add refrigerant leak detector (either 37 or 38, Chart 201) to the suction side of the refrigerant system to detect leaks. The correct quantity for detector (37, Chart 201) is 1/8 ounce per pound of refrigerant, a red film will appear in the areas of leakage. The correct quantity for detector (38, Chart 201) is 1/4 ounce per three pounds of refrigerant, a fluorescent mark will appear in the areas of leakage. Use a recovery/recycle service unit to charge the refrigerant system. A qualified air-conditioning serviceman is required to operate the service equipment. Refrigerant service ports are located on the left side of the nose wheel well. Service ports are provided so the air-conditioning system can be serviced without the necessity of working close to the propellers with the engines running (Ref. Figure 204). a. Connect the recovery/recycle service unit to the service valves on the airplane. b. Evacuate system prior to charging (Ref. EVACUATING THE AIR-CONDITIONING SYSTEM, 21-50-00). c.

Add the amount of compressor oil removed from the system during discharging.

d. Charge the air conditioning system in accordance with the recovery/recycle service unit’s instructions with the refrigerant. Charge to the capacity referenced in Chart 204 (Ref. Chart 204). e. Disconnect and remove the recovery/recycle service unit when charging is complete.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL CHARGING THE AIR-CONDITIONING SYSTEM (FL-493, FL-500 AND AFTER; FM-14 AND AFTER) WARNING: Due to the air quality control regulations enacted in the United States, you are not permitted to vent refrigerant R-134a into the atmosphere. When performing maintenance on the airconditioning system where refrigerant R-134a can escape from the system, evacuate the system with a recovery/recycle service unit that will recover the refrigerant. The air-conditioning system is a high pressure system. Before disconnecting a refrigerant line, the system must be discharged with a recovery/recycle service unit. Evacuate the entire system for 15 minutes. Use only R-134a compatible recovery/recycle service unit. Use a recovery/recycle service unit to charge the refrigerant system. A qualified air-conditioning serviceman is required to operate the service equipment. Refrigerant service ports are located on the left side of the nose wheel well. Service ports are provided so the air-conditioning system can be serviced without the necessity of working close to the propellers with the engines running (Ref. Figure 204, Sheet 2). a. Connect the recovery/recycle service unit to the service valves on the airplane. b. Evacuate system prior to charging (Ref. EVACUATING THE AIR-CONDITIONING SYSTEM, 21-51-00). c.

Add the amount of compressor oil removed from the system during discharging.

d. Charge the air conditioning system in accordance with the recovery/recycle service unit’s instructions with the refrigerant. Charge to the capacity referenced in Chart 204 (Ref. Chart 204). e. Disconnect and remove the recovery/recycle service unit when charging is complete. COMPRESSOR OIL CHECK (FL-1 THRU FL-492, FL-494 THRU FL-499; FM-1 THRU FM-13) Measuring the oil accurately in an in-service vapor cycle air-conditioning system is difficult. EXPERIENCED personnel have to use good judgement and care to determine if additional oil is to be added and how much. If a refrigerant leak or oil leak has occurred or if it is suspected that the system is low on oil, a small amount of oil may be added to the system. NOTE: A few drops of oil on refrigerant plumbing joints may look like a major leak when the actual oil loss is negligible. If a refrigerant leak appears to carry a large amount of oil with the refrigerant, a small quantity of refrigerant may be added to the system. Airplane serials FL-1 thru FL-127 and FM-1 thru FM-8, use viscosity oil (Item 40, Chart 201). Airplane serials FL-128 and after, FM-9 and after, and prior airplanes with Kit 130-5009 installed use oil (Item 41, Chart 201). Too much oil in the system may cause a reduction in the cooling capacity of the system. If the oil in the system becomes excessive, the oil may “slug” the compressor, damaging the compressor and compressor drive. Do not substitute or intermix oil types between systems. If there is a small refrigerant leak which does not appear to carry oil with it, oil probably should not be added with the refrigerant when the system is recharged. If the refrigerant leak is more severe and oil is being carried out with the refrigerant, 1 to 2 ounces of oil may be added to the system once a year. If the oil loss is severe and the amount cannot be calculated, the leak(s) should be repaired and the system flushed to remove all the oil and any contaminants. Airplane serials FL-1 thru FL-127

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL and FM-1 thru FM-8, use air-conditioning flush fluid (Item 42, Chart 201) and dry nitrogen. Airplane serials FL-128 and after, FM-9 and after, and prior airplanes with Kit 130-5009 installed utilize refrigerant R-134a (Item 34, Chart 201) and dry nitrogen. NOTE: Any time the oil is drained from a component of the system, a small quantity of oil will remain in that component. Calculate the amount of oil remaining in the component (up to one ounce in the compressor) and add this amount to the amount of oil drained from the component. When the system is reassembled, this amount of oil should be added back into the system. When draining the oil from the compressor, rotate the compressor to keep from trapping oil in the compressor. COMPRESSOR OIL LEVEL CHECK (FL-493, FL-500 AND AFTER; FM-14 AND AFTER) Check compressor oil level when a system component is replaced or an oil level problem is suspected (Ref. Chart 204). a. Operate the air-conditioning system for ten minutes to collect as much oil as possible in the compressor. b. Discharge the system (Ref. DISCHARGING THE AIR-CONDITIONING SYSTEM, 21-51-00). c.

Remove the compressor and cap all fittings (Ref. COMPRESSOR REMOVAL, 21-51-00).

d. Remove oil fill plug and drain oil from compressor. Rotate clutch several times to drain all the oil. e. Add new oil (Item 43, Chart 201) to the compressor oil fill port. f.

Clean oil fill port area and install oil fill plug. Torque plug to 6 to 9 ft-lbs.

g. Remove fitting caps and install the compressor (Ref. COMPRESSOR INSTALLATION, 21-51-00). h. Charge the system (Ref. CHARGING THE AIR-CONDITIONING SYSTEM).

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OXYGEN CAUTION: Use only Aviators Breathing Oxygen (6, Chart 201) for servicing the oxygen system. Do not use oxygen intended for medical purposes or such industrial uses as welding. Such oxygen may contain excessive moisture that could freeze up the valves and lines of the oxygen system. Access to the pressure indicator and filler valve of the oxygen system may be gained through an access door located on the right side of the aft fuselage. To recharge the oxygen system, remove the protective cap from the filler valve and attach the hose from an oxygen (6, Chart 201) recharging unit to the filler valve. Make sure that both the airplane oxygen system and the servicing equipment are properly grounded before servicing the system. WARNING: Avoid making sparks and keep all burning cigarettes or fire away from the vicinity of the airplane. Make sure that the oxygen shutoff valve control is in the closed position. Inspect the filler connection for cleanliness before attaching it to the filler valve. Make certain that your hands, tools and clothing are clean, particularly of grease or oil, for these contaminants will ignite upon contact with pure oxygen under pressure. As a further precaution against fire, open and close all oxygen valves slowly during filling. To prevent overheating, fill the oxygen system slowly by adjusting the recharging rate with the pressure regulating valve on the recharging unit. All oxygen cylinders should be filled to 1,850 ±50 psi at a temperature of 70° F. This pressure may be increased an additional 3.5 psi for each degree of increase in temperature; similarly, for each degree of drop in temperature, reduce the pressure for the cylinder by 3.5 psi. When the oxygen system is properly charged, disconnect the filler hose from the filler valve and replace the protective cap on the filler valve. If at any time in the process of servicing, purging the system or replacing the oxygen cylinder, it becomes necessary to disconnect a fitting, the threads of the fitting should be wrapped with anti-seize tape (7, Chart 201) prior to being connected back into the system. NOTE: Refer to Advisory Circular 43.13-1A for the additional servicing precautions recommended by the FAA on the oxygen systems.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 300300300 12-20-00

SCHEDULED SERVICING ENGINE WASHING PROCEDURES Engine washing consists of compressor washing and surface washing. Washing should be performed to remove salt deposits, dirt, and other deposits which build up over a period of time. In order to properly wash an engine, you must follow the instructions listed here in addition to the detailed engine washing procedures recommended by the engine manufacturer. Refer to the Engine Maintenance Manual (P/N 3034342) and Aircraft Gas Turbine Operation Information Letter No. 7, Rev. 4, or subsequent, by Pratt and Whitney of Canada Limited. CAUTION: Any time the engine compressor is to be washed, both the compressor bleed air and the P3 air filter to the flow control unit must be capped off. NOTE: Normally when the engine fire extinguisher is discharged, the engine baffling will prevent ingestion of the fire extinguishing agent into the engine. Engine cleaning should not then normally be required following discharge of the engine fire extinguisher unless it is positively known that the fire extinguishing agent has been ingested into the engine. Most ingestion is caused by ground personnel using an extinguisher external to the airframe during engine operation. COMPRESSOR WASHING There are two types of compressor washing, desalination wash and performance recovery wash. The desalination wash is used to remove salt deposits while the performance recovery wash is used to remove baked-on deposits. DESALINATION WASH PROCEDURES Prior to performing these instructions, refer to the Pratt & Whitney Engine Maintenance Manual (P/N 3034342) and Aircraft Gas Turbine Operation Information Letter No. 7, Rev. 4, or subsequent by Pratt and Whitney of Canada Limited. a. Install cleaning equipment. b. Motor engine for 30 seconds while injecting wash mixture. c.

Allow starter/generator to cool down for a period of 15 minutes.

d. Motor engine for 30 seconds. e. Allow starter/generator to cool down for 30 minutes. f.

Remove cleaning equipment and reconnect compressor bleed air and the P3 air filter.

g. Start engine. PERFORMANCE RECOVERY WASH PROCEDURES Prior to performing these instructions, refer to the Pratt & Whitney Engine Maintenance Manual (P/N 3034342) and Aircraft Gas Turbine Operation Information Letter No. 7, Rev. 4, or subsequent by Pratt and Whitney of Canada Limited. a. Install cleaning equipment.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL b. Motor engine for 30 seconds while injecting wash mixture. c.

Allow starter/generator to cool down and the cleaning solution to soak for 30 minutes.

d. Motor engine for 30 seconds while injecting rinse mixture. e. Allow starter/generator to cool down for 15 minutes. f.

Motor engine for 30 seconds while injecting rinse mixture.

g. Allow starter/generator to cool down for 30 minutes. h. Motor engine for 30 seconds. i.

Allow starter/generator to cool down for 15 minutes.

j.

Remove cleaning equipment and reconnect compressor bleed air and the P3 air filter.

k.

Start engine.

EXTERNAL ENGINE WASHING (SURFACE WASHING) CAUTION: Before any external engine washing, cover or protect all electrical components and plugs located on the engine or in the engine compartment. Do not allow water to enter the engine air inlet or exhaust. Precautions should be taken against contaminating the clutch portion of the air-conditioner compressor with cleaning solvent during the engine wash procedure. Such contamination may dilute the grease in the compressor pulley bearing and result in premature failure. High pressure water or solvent should not be directed on electrical components or mechanical parts having air vent holes. After washing the engine blow dry the components with dry shop air. Do not use gasoline or similar toxic substances for external engine cleaning. Do not attempt to wash an engine that is still hot or running. Allow engine to cool for a minimum period of 40 minutes or longer. Fresh water external washing is recommended when an engine is contaminated with salt or corrosive chemicals such as those found in industrial smog. ENGINE SURFACE SALT CONTAMINATION When the exterior surface of the engine is contaminated with salt, it should be washed clean with water prior to flight of the airplane. Demineralized water is not required for this purpose. At no time should an engine be left in a contaminated (salted) condition for any extended period of time (such as overnight). CAUTION: Do not use gasoline or similar toxic substances for external engine cleaning. Do not attempt to wash an engine that is still hot or running. Allow engine to cool for a minimum period of 40 minutes or longer.

CLEANING AIRPLANE EXTERIORS Prior to washing, attach the pitot cover securely and plug or mask off all other openings. Be particularly careful to mask off all static air buttons before washing or waxing. Use special care to avoid washing away grease from any lubricated area. Prior to cleaning, cover such areas as wheels, brakes, etc., and relubricate as necessary after cleaning. Always be sure all maskings and coverings are removed before returning the airplane to service. The urethane finish undergoes a curing process for a period of time after application. During the first month after paint application, some special care is required. Airplane owners and operators should observe the following recommendations in order to preserve the durability and appearance of the airplane paint.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL CLEANING EXTERIORS DURING THE FIRST MONTH OF PAINT CURING PERIOD a. Avoid prolonged flights in heavy rain or sleet. b. Avoid any operating conditions which might cause abrasion or premature finish deterioration. c.

Clean the airplane with mild detergents and water only.

d. Use only soft clean rags, keeping the rag free from dirt and grime. Rinse the rag often using clear water. e. Use no waxes, polishes, rubbing compound or abrasive cleaners of any type. f.

Remove stubborn oil or soot deposits from the cowlings, wheel wells etc. by gently using an automotive tar remover.

CLEANING AIRPLANE EXTERIORS AFTER THE FIRST MONTH OF PAINT CURING a. Clean the airplane on a regular basis. b. Use mild detergents and water only. c.

Rinse thoroughly with clear water to prevent a residue buildup that can dull the airplane finish.

d. Normally waxing is not necessary. If waxing is desired, select a high quality automotive or airplane wax product. e. Never use rubbing compound or abrasive cleaners on the airplane painted surface. f.

Do not use a wax containing silicone because silicone products are hard to remove from the airplane surfaces.

SURFACE DEICER BOOT CLEANING The deicer boots should be checked after servicing and at the end of each flight. a. Inspect the deice boots for oil spots. b. Remove any oil spots using a non-detergent soap and water. c.

Avoid scrubbing the boot surface because the conductive coating could be removed from the surface of the deicer boot.

d. Do not drag fuel hoses on the surface of the deicer boot. e. Do not lean a platform or ladder against the surface of the deicer boot.

ENGINE INERTIAL ANTI-ICING SYSTEM SERVICING An inertial separator vane (ice vane) is installed in each lower forward cowling section to preclude entry of freezing rain and snow to the compressor inlet screen. A bypass door in the lower aft cowling section provides an outlet for the ice particles and snow. Servicing consists of lubricating the actuating linkage periodically with grease (8, Chart 1, 12-10-00), to assure freedom of movement and to reduce wear.

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INTERIOR CARE CLEANING LEATHER OR VINYL CAUTION: The color of leather may be a surface dye only. Do not rub leather with hard or coarse materials. While working in the cabin, use protective covers on upholstery. Use only mild detergent and soft cloths to clean soiled leather. To remove a light film of grit and dust, an occasional dusting is required. Almost any stain can be removed by washing. NOTE: Never use saddle soap, furniture polish, oil, varnish, ammonia water, or solvent of any kind on leather or vinyl. a. Use lukewarm or cool water only. b. With Castile, Ivory, or any other mild soap, work up a thin layer of suds on a piece of cheesecloth. c.

Apply the suds to the stained area of the material.

d. With a piece of cheesecloth dampened in clean water remove the soap suds film. e. Dry the dampened area with a clean, dry, soft piece of cheesecloth. FABRIC CLEANING Dust has impurities which affect fabrics, therefore vacuum at regular intervals. Dry clean at regular intervals before excessive soil has accumulated. Actual dry cleaning of draperies and upholstery must be performed by a professional dry cleaner. Very few fabrics are washable. CLEANING OF LAMINATES The decorative surface may be readily cleaned with warm water and a mild soap. The use of abrasive or “special” cleansers should be avoided. Stubborn stains may be removed with organic solvents or with a two minute exposure to a hydrochloride bleach such as “Clorox”. Rinse with clean water.

SERVICING THE TOILET NOTE: For sanitary reasons, wear rubber gloves for any work requiring contact with tank fluids or parts within the tank area. DRY NONFLUSHING TOILET (FM-1 AND AFTER) The dry nonflushing type toilet may be serviced with either a dry powder toilet chemical or an appropriately sized plastic bag liner, however, the toilet container should be removed from the airplane, emptied and cleaned after each period of use. MONOGRAM TOILET NOTE: During cold weather operation, add an ethylene glycol base automotive antifreeze to the toilet with a ratio of water to antifreeze similar to that used for an automobile. a. Open the hinged door on the front of the toilet cabinet (Ref. Figure 301). b. Depress the lock ring of the flush hose guide. Disconnect the coupling on the right side at the front of the waste container top.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL c.

Drain any residue of flush liquid in the hose by partially disengaging the plug from the quick disconnect and manipulating the hose to assist drainage.

d. Remove the flush hose from the quick disconnect coupling and place the hose in the retaining clip provided on the underside of the toilet mounting plate. e. Install the plug attached to the quick disconnect coupling to seal the coupling. f.

Close the blade valve at the bottom of the toilet bowl by pushing the actuator handle until the valve is fully closed.

g. Press the two Press-Lock fasteners on each side of the blade valve actuator to unlock the waste container. h. Remove the waste container from the toilet assembly by pulling the recessed carrying handle on top of the waste container. i.

Invert the tank over a commode or other suitable sanitary disposal station and pull out the blade valve to empty the waste container contents.

j.

Pour approximately two quarts of fresh water into the waste container. Push in on the blade valve and slosh the water for a few seconds.

k.

Drain the waste container as in step i.

l.

Repeat steps j and k as required.

NOTE: Commercial detergents and disinfectants may be included in the rinse water if desired. m. Service the waste container with two quarts of fresh water and three ounces of toilet chemical (9, Chart 1, 12-10-00) in accordance with the manufacturer’s instructions. Push the blade valve in. n. Align the waste container and cabinet tracks, then push the waste container in. Engage the waste container latch. o. Remove the male plug and connect the quick-disconnect fitting at the waste container. p. Depress the flush switch and check for correct flushing action and the absence of leaks. Close the cabinet door. NOTE: If the toilet is to remain inactive for an extended period of time, empty the water chemical solution and thoroughly flush the system with fresh water, then, drain the system. ALAMO TOILET (FL-1 AND AFTER) NOTE: During cold weather operation, add antifreeze (10, Chart 1, 12-10-00) to the waste container and the flushing liquid reservoir as instructed on the antifreeze container. a. Initial charge of the flushing liquid reservoir is approximately two quarts of water mixed with 2 oz. of toilet chemical (11, Chart 1, 12-10-00) per each quart of water. The reservoir should be filled to the line marked “Fill To Here” on the inner wall of the reservoir. NOTE: The flushing liquid needs changing only occasionally, depending upon toilet usage, usually once to every 5 to 10 times that the waste container is serviced. If the flushing liquid has been changed recently and appears to have correct chemical balance, it does not necessarily need changing. b. To change the flushing liquid, activate the toilet pump by inserting a small object (such as a pencil) into the hole marked “Service Switch”. Maintain contact for several seconds until the flushing liquid has been pumped into the waste container.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL c.

Empty the waste container as directed under ALAMO WASTE CONTAINER SERVICING.

d. Clean the toilet assembly inside and out with Lysol spray or equivalent (obtain locally) to provide a disinfected, more hygienic and odor-free toilet. e. Install the waste container as directed under ALAMO WASTE CONTAINER SERVICING and recharge the flushing fluid reservoir as instructed in step a. f.

Close the bowl assembly and press the fastener into place. Stow the hanger bracket and close the upholstered seat assembly onto the toilet assembly.

ALAMO WASTE CONTAINER SERVICING (FL-1 AND AFTER) a. Raise the upholstered toilet seat and secure it in the fully raised position. b. Slip the hanger bracket (stowed in the toilet compartment) over the front of the seat cushion. c.

Open the sliding doors in the top of the toilet surface and lift the front edge of the bowl assembly. The snap latch will release and the front of the bowl assembly may be raised and secured in the lifted position with the hanger bracket over the front of the cushion.

d. Remove the waste container cap from its stowage position in the toilet assembly and snap it into place in the opening in the top of the waste container. e. Raise the two handles on the waste container and firmly lift the waste container from its position in the toilet assembly. A steady pull will release the container from the perimeter seal. f.

Remove the container cap and empty the waste container contents into a commode or a sanitary disposal station.

g. Rinse the container thoroughly prior to precharging and clean the entire toilet assembly with Lysol spray or equivalent (obtain locally). h. Mix 2 oz. of “Clean-Flush” fluid (11, Chart 1, 12-10-00) or equivalent with one quart of water and pour the mixture into the waste container as a precharge. i.

Position the waste container in the toilet assembly and press down firmly on all corners to assure proper placement of the seal in the groove to prevent leakage of the flushing liquid into the waste receptacle.

NOTE: The seal should be lubricated with protective coating (12, Chart 1, 12-10-00) prior to inserting the container. j.

Remove the container cap and stow it on the bracket provided in the toilet assembly.

k.

Lower the toilet bowl and snap it into place.

l.

With electrical power on, press the operating switch and check for proper flushing cycle. (Approximately 6 to 10 seconds).

m. Check for freedom of movement of the waste container gate valve. Binding could indicate improper seating of the container. n. Stow the hanger bracket and lower the seat cushion into place. NOTE: If the toilet is to remain inactive for an extended period of time, empty the water chemical solution and thoroughly flush the system with fresh water, then drain the system.

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Side Facing Electric Toilet Installation (FL-1 and After) Figure 301

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LUBRICATION SCHEDULE Prior to performing the various lubrication tasks in each area, it is important that proper safety precautions and access to the specified areas be accomplished. Use only clean and approved lubricants. Remove all excess oil and grease that accumulates near the lubrication fittings and areas. Refer to the Lubrication Schedules, for proper lubricants and the hourly intervals for lubrication. The following lubrication schedule is organized so that related items requiring lubrication are grouped together. Each lubrication point is identified and indexed for location on the accompanying illustration. Lubrication time intervals are incremented to occur at times coincident with the inspection intervals in Chapter 5. LUBRICATION PRECAUTIONS CAUTION: DO NOT MIX different grease. If the grease is changed, make certain that all the affected components are thoroughly cleaned before relubrication. When changing over from one type or brand name grease to another, the recommended practice is to remove all of the old grease from the bearing surfaces and internal cavities of the lubricated mechanism prior to application of the new grease. Hawker Beechcraft Corporation does not recommend intermixing different types or brand names of grease, even if they are considered optional to each other, because of possible incompatibility. Different grease approved to the same specification may be incompatible with each other. Mixing of grease made with different thickener types should be avoided; thus clay thickened grease should not be mixed with metallic soap thickened grease as this can lead to breakdown of the thickener structure. a. Cleanliness is essential to good lubrication. Lubricants and dispensing equipment must be kept clean. Use only one lubricant in a grease gun or oil can. b. The lubricant used for relubrication and the lubricant used in the assembly or installation of parts should be of the same type. c.

Store lubricants in protected containers kept closed at all times when not in use.

d. Wipe grease fittings and areas to be lubricated with clean dry cloths before lubricating. e. All lubricant containers should have a label showing contents and shelf life. f.

To lubricate threads, apply a small quantity of the specified lubricant on external threads only.

g. To apply lubricant on press-type fittings, lubricate only to the extent that lubricant comes out slightly around the bushing and bearing. h. After any lubrication, clean excess lubricant from all but actual working parts. i.

All sealed or prepacked antifriction bearings are lubricated by the manufacturer with grease (8, Chart 201, 1210-00) unless otherwise specified.

j.

Do not oil antifriction bearings or expose them to spray from steam or chemical cleaners. When exterior bearing surfaces are cleaned, wipe with a cloth dampened with solvent (24, Chart 201, 12-10-00).

k.

Friction bearings of the porous, sintered type are prelubricated. An occasional oiling of such bearings by a squirt can of general purpose oil (14, Chart 201, 12-10-00) will extend their service life.

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Use general purpose oil (14, Chart 201, 12-10-00) to lubricate unsealed pulley bearings, rod ends, pivot ends, hinge points and any other friction points obviously needing lubrication.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL NOSE LANDING GEAR LUBRICATION

INDEX NO.

ITEM

LUBRICANT

HOUR INTERVAL

NOSE LANDING GEAR (Ref. Figure 302) 1.

Wheel Bearings

MIL-PRF-81322 (13, Chart 201, 12-10-00) or Mobil Aviation Grease SHC 100 (45, Chart 201, 12-10-00)

200

CAUTION DO NOT MIX different brands of grease as this will cause decreased bearing life. If the grease is changed, make certain that all the affected components are thoroughly cleaned before relubrication. 2.

Grease Fittings

MIL-G-21164 Grease (19, Chart 201, 12-10-00) 200 or MIL-PRF-23827 Grease (8, Chart 201, 12-1000) Aeroshell Grease 33MS Preferred

3.

Door Hinges and Retract Linkage

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

4.

Upper and Lower Strut Bearing MIL-G-21164 Grease (19, Chart 201, 12-10-00) Aeroshell Grease 33MS Preferred (Molybdenum Disulfide Grease Only)

800

200

CAUTION DO NOT MIX different brands of grease as this will cause decreased bearing life. If the grease is changed, make certain that all the affected components are thoroughly cleaned before relubrication. 5.

Unsealed Actuator Support Bearings

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) 800

NOTE After washing the airplane, lubricate all lubrication points.

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Nose Landing Gear Lubrication Figure 302

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL MAIN LANDING GEAR LUBRICATION

INDEX NO.

ITEM

LUBRICANT

HOUR INTERVAL

MAIN LANDING GEAR (Ref. Figure 303) 1.

Door Linkage

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

400

2.

Retract Actuator Clevis

MIL-G-21164 Grease (19, Chart 201, 12-10-00) 200 or MIL-PRF-23827 Grease (8, Chart 201, 12-1000) Aeroshell Grease 33MS Preferred

3.

Grease Fittings

MIL-G-21164 Grease (19, Chart 201, 12-10-00) 200 or MIL-PRF-23827 Grease (8, Chart 201, 12-1000) Aeroshell Grease 33MS Preferred

4.

Wheel Bearings

MIL-PRF-81322 (13, Chart 201, 12-10-00) or Mobil Aviation Grease SHC 100 (45, Chart 201, 12-10-00)

200

CAUTION DO NOT MIX different brands of grease as this will cause decreased bearing life. If the grease is changed, make certain that all the affected components are thoroughly cleaned before relubrication. 5.

Downlock Hooks and Pin Contact areas

Lubribond A or an air-drying solid film lubricant per MIL-L-23398 (16, Chart 201, 12-10-00)

800 hours or 24 months

6.

Drag Leg Hook, Spring and Guide

LPS 3 Metal Protector (17, Chart 201, 12-10-00) (Apply sparingly)

200

7.

Unsealed Actuator Support Bearings

MIL-G-21164 Grease (19, Chart 201, 12-10-00) 800 or MIL-PRF-23827 Grease (8, Chart 201, 12-1000) Aeroshell Grease 33MS Preferred NOTE

After washing the airplane, lubricate all lubrication points.

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Main Landing Gear Lubrication Figure 303

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL RUDDER CONTROL SYSTEM LUBRICATION

INDEX NO.

ITEM

LUBRICANT

HOUR INTERVAL

RUDDER CONTROL SYSTEM (Ref. Figure 304) 1.

Rudder Trim Tab Tube

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

200

2.

Rudder Trim Tab Actuator

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) (FL-1 thru FL-137; FM-1 thru FM-9 airplanes that have not installed P/N 130-524051-11) (1 to 2 pumps of the grease gun only)

400

Grease (35, Chart 201, 12-10-00) (FL-138 and After; FM-10 and After and all prior airplanes that have installed P/N 130-524051-11) (1 to 2 pumps of the grease gun only)

400

200

3.

Rudder Trim Tab Hinge

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

4.

Rudder Trim Tab Cable Seal

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) 1,200

5.

Rudder Cable Seals

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) 1,200

6.

Pedal and Bellcrank Linkage

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00) or MIL-PRF-7870 Oil (14, Chart 201, 12-10-00)

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400

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Rudder Control System Lubrication Figure 304

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL AILERON CONTROL SYSTEM AND FLAP CONTROL SYSTEM LUBRICATION

INDEX NO.

ITEM

LUBRICANT

HOUR INTERVAL

AILERON CONTROL SYSTEM (Ref. Figure 305) 1.

Aileron Bellcranks

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

400

2.

Trim Tab Actuator

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) (FL-1 thru FL-137; FM-1 thru FM-9 airplanes that have not installed P/N 130-521034-11) (1 to 2 pumps of the grease gun only)

400

Grease (35, Chart 201, 12-10-00) (FL-138 and After; FM-10 and After and all prior airplanes that have installed P/N 130-521034-11) (1 to 2 pumps of the grease gun only)

400

3.

Aileron Tab Cable Seals

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) 1,200

4.

Aileron Cable Seals

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) 1,200

5.

Aileron Trim Tab Hinge

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

200

6.

Aileron Trim Tab Tube End Pivot Points

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

200

FLAP CONTROL SYSTEM (Ref. Figure 305) 7.

Flap Actuator Pistons

SAE-J2360 Oil (21, Chart 201, 12-10-00)

1,200

8.

Flap Limit Safety Switch

LPS 1 or equivalent (18, Chart 201, 12-10-00)

200

9.

Flap Motor Gearbox

MIL-PRF-10924 Grease (20, Chart 201, 12-10-00)

1,200

10.

Flap Tracks

SAE AMS-M-7866 (22, Chart 201, 12-10-00)

200

Page 316 Aug 1/09

12-20-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

6 3

2

5

4

1

10

8

7

9

FL20B 002571AA.AI

7

Aileron Control System and Flap Control System Lubrication Figure 305

A26

12-20-00

Page 317 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL CONTROL COLUMN, ELEVATOR CONTROL SYSTEM AND WINGS LUBRICATION

INDEX NO.

ITEM

LUBRICANT

HOUR INTERVAL

CONTROL COLUMN (Ref. Figure 306) 1.

Chain

Preclean chain with a cloth dampened with Stoddard Solvent (mineral spirits) (24, Chart 201, 12-10-00). Lubricate chain with Oil (44, Chart 201, 12-10-00). Wipe off excess oil.

800

ELEVATOR CONTROL SYSTEM (Ref. Figure 306) 2.

Elevator Trim Tab Actuator

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) 400 (FL-1 thru FL-137; FM-1 thru FM-9 airplanes that have not installed P/N 130-524052-13 or 130524052-15) (1 to 2 pumps of the grease gun only)

Grease (35, Chart 201, 12-10-00) (FL-138 and After; FM-10 and After and all prior airplanes that have installed P/N 130-524052-13 or 130-524052-15) (1 to 2 pumps of the grease gun only)

400

3.

Elevator Trim Tab Tube End Pivot Points

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

200

4.

Elevator Trim Tab Hinges

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

200

5.

Elevator Trim Tab Cable Seal

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) 1,200

6.

Elevator Cable Seal

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00) 1,200

WINGS (Ref. Figure 306) 7.

Page 318 Aug 1/09

Upper Forward Wing Bolts

12-20-00

MIL-PRF-16173 Grade 2 Corrosion Preventive Compound (23, Chart 201, 12-10-00)

First scheduled inspection after wing installation and annually thereafter.

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Control Column, Elevator Control System and Wings Lubrication Figure 306

A26

12-20-00

Page 319 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL ENGINE CONTROLS LUBRICATION

INDEX NO.

ITEM

LUBRICANT

HOUR INTERVAL

ENGINE CONTROLS (Ref. Figure 307) 1.

Control Rod Ends

MIL-PRF-23827 Grease (8, Chart 201, 12-10-00)

200

2.

Cam Plates and Pins

Lubriplate No. 130AA (25, Chart 201, 12-10-00)

200

3.

Air-Conditioner Compressor Quill Shaft

Molykote M77 (26, Chart 201, 12-10-00)

400

Page 320 Aug 1/09

12-20-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Controls Lubrication Figure 307

A26

12-20-00

Page 321 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL ENGINE CONTROLS AND PROPELLER LUBRICATION

INDEX NO.

ITEM

LUBRICANT

HOUR INTERVAL

ENGINE CONTROLS (Ref. Figure 308) 1.

Linkage (all moving parts)

MIL-G-21164 Grease (19, Chart 201, 12-10-00)

As required for proper operation.

Aeroshell Grease No. 6 (47, Chart 201, 12-10-00), Aeroshell Grease No. 7 (48, Chart 201, 12-10-00), Aeroshell Grease No. 22 (13, Chart 201, 12-10-00), Royco 22C (13, Chart 201, 12-10-00), as defined by the manufacturer’s decal on the piston hub of the propeller.

200

PROPELLER (Ref. Figure 308) 2.

Propeller Blade Bearings (2 lube fittings per blade)

WARNING Remove the lubrication fitting opposite the one being serviced. Failure to do so could result in damage to the propeller bearings and seals. 3.

Page 322 Aug 1/09

Low Pitch Stop Rods (4 per propeller)

12-20-00

Marvel Mystery Oil (27, Chart 201, 12-10-00)

200

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Controls and Propeller Lubrication Figure 308

A26

12-20-00

Page 323 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL EMERGENCY EXIT DOOR AND CABIN DOOR LUBRICATION

INDEX NO.

ITEM

LUBRICANT

HOUR INTERVAL

EMERGENCY EXIT DOOR (Ref. Figure 309) 1.

Track

MIL-G-21164 Grease (19, Chart 201, 12-10-00)

800

2.

Guide

MIL-L-23398 (16, Chart 201, 12-10-00) (sparingly)

800

3.

Latch

MIL-L-23398 (16, Chart 201, 12-10-00) (sparingly)

800

MIL-PRF-32033 Oil (18, Chart 201, 12-10-00)

200

CABIN DOOR (Ref. Figure 309) 4.

Page 324 Aug 1/09

Latching Mechanism (pins included)

12-20-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Emergency Exit Door and Cabin Door Lubrication Figure 309

A26

12-20-00

Page 325 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL CARGO DOOR LUBRICATION

INDEX NO.

ITEM

LUBRICANT

HOUR INTERVAL

CARGO DOOR (Ref. Figure 310) 1.

Gas Spring End Fittings

Disassemble joint and lubricate sparingly with MIL-PRF-23827 Grease (8, Chart 201, 12-1000).

200

2.

Door Camlocks

Wipe clean and lubricate lip of camlock with Door-ease. Do not apply to face of camlock.

200

3.

Step Hinge Bushings

Lubricate sparingly with MIL-PRF-32033 Oil (18, Chart 201, 12-10-00).

200

4.

Entrance Door Hinge

Lubricate sparingly with MIL-PRF-32033 Oil (18, Chart 201, 12-10-00).

200

5.

Latch Pin and Latch Plate

Wipe clean and lubricate pin and hole in latch plate with Door-ease.

200

Page 326 Aug 1/09

12-20-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Cargo Door Lubrication Figure 310

A26

12-20-00

Page 327 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 301 Thread Lubricants Item

Type of Line

Lubricant

1.

Pressurization Control

Tapered Threads and Straight Threads, Loctite® 592TM PST®

2.

Brakes

MIL-PRF-5606 Hydraulic Fluid

3.

Fuel and Fuel Press. Lines

VV-P-236, Technical Petrolatum

4.

Oil and Oil Press. Lines

SAE AMS-G-6032, Lubricating Grease (Oil and Gasoline Resistant)

5.

Autopilot

Straight and Tapered Threads, Loctite® 592TM PST®

6.

Oxygen

A-A-58092 Size 1 Teflon Tape or MIL PRF-27617 Type III Grease on Straight Threads

7.

Pitot and Static

Straight Threads and Tapered Threads, Loctite® 592TM PST®

8.

Hydraulic

Fluid of the System or Loctite® 569TM Pneumatic/Hydraulic Thread Sealant

9.

Vacuum

RectorSeal® No. 5

10. Refrigerant

Brayco 815Z

11. Deicer

Straight Threads and Tapered Threads, Loctite® 592TM PST®

12. Fire Extinguisher

Loctite® 592TM PST®

13. Bleed Air

M77 (P/N of Dow Corning) NOTE Lubricate engine threads with the fluid contained in the particular line.

SPLINE DRIVE LUBRICATION SPLINE DRIVES ATTACHED TO THE ENGINE When spline drives of any type are to be mated to the engine, they must be properly lubricated. Use lubricating grease (25, Chart 1, 12-10-00) on all tight press-fit splines unless otherwise specified in the Engine Maintenance Manual. Excessive lubricant may cause malfunctioning or even failure of the engine. SPLINE DRIVES FOR ACCESSORIES Lubricating grease (26, Chart 1, 12-10-00) should be used on all loose-fit splines which are external to the engine and have no other means of lubrication. Take care to apply the grease in a thin, even coat, only on the surfaces where they are required.

Page 328 Aug 1/09

12-20-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

COMPRESSOR QUILL SHAFT LUBRICATION The quill shaft that provides the drive for the air-conditioning compressor should be lubricated at the pulley end at the intervals specified in ENGINE CONTROLS LUBRICATION. Refer to Chapter 21 for quill shaft lubrication instructions.

THREAD LUBRICATION All plumbing fittings on external lines, including their points of attachment on the engine and other components, and the threads on the oil pressure and torque pressure transmitters shall be lubricated with the proper lubricant as specified in Chart 301. a. Clean threads before applying lubricant (Ref. Figure 311). b. Use only thin coats of thread lubricant. c.

Apply lubricant to male threads only.

d. On straight thread fittings, lubricate the first 3 threads. e. On tapered thread fittings, do not lubricate first 2 threads. Apply lubricant to next 3 threads only. f.

Never allow lubricant to enter fittings of flare areas.

g. Engine fittings should be lubricated only with the fluid transported in the line unless otherwise specified.

GASKETS AND SEALS LUBRICATION Lubricate gaskets, seals, and preformed packings with the system fluid type.

CONTROL CABLE LUBRICATION Using solvent (24, Chart 1, 12-10-00) clean the control cables for the length of travel through the pressure seals. Lubricate to one inch beyond each end of the cleaned area with grease (8, Chart 1, 12-10-00).

Thread Lubrication Figure 311

A26

12-20-00

Page 329 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000

Manual Affected:

Super King Air B300/B300C Maintenance Manual (130-590031-11).

Instructions:

Insert this Temporary Revision (TR) before page 301, Chapter 12-30-00. This TR completely replaces Chapter 12-30-00, page block 301.

Reason:

Provides additional instructions on the application of de-ice/anti-ice fluids and the removal of thickened residue that may result from using these fluids.

INFORMATION DE-ICING AND ANTI-ICING OF AIRPLANES ON THE GROUND De-icing is the removal of ice, frost and snow from the airplane’s exterior after it has formed. Anti-icing is a means of keeping the surface clear of subsequent accumulations of ice, snow and frost. Snow and ice on an airplane will seriously affect its performance. Even formation of a smooth covering of ice on the wing will change the contour of the wing, producing an increase in drag and a reduction in effective lift coefficient. Frost or frozen snow may present an even greater hazard since the surface texture is rough and will seriously disrupt the smooth flow of air across the wing.

DE-ICING AND ANTI-ICING FLUIDS Hawker Beechcraft Corporation has evaluated and approved the following de-ice/anti-ice fluids for use on this model: SAE TYPE I ANTI-ICING FLUIDS (UNTHICKENED-TYPE FLUIDS) Type I fluids (32, Chart 201, 12-10-00) mainly provide protection against refreezing when there is no precipitation. SAE TYPE II ANTI-ICING FLUIDS (THICKENED-TYPE FLUIDS) Type II fluids (32, Chart 201, 12-10-00) provide protection against refreezing when precipitation occurs. SAE TYPE IV ANTI-ICING FLUIDS (THICKENED-TYPE FLUIDS) Type IV fluids (32, Chart 201, 12-10-00) provide protection against refreezing when precipitation occurs.

All approved Type I, Type II, and Type IV fluids may be used for either de-icing or anti-icing at any dilution as allowed by the fluid manufacturer's recommendations. Hawker Beechcraft Corporation cannot accept responsibility for damage to the airplane finish, windows, rubber seals, etc. resulting from the use of de-icing fluids not conforming to the specified specifications.

Temporary Revision No. 12-1

Page 1 of 7 Nov. 09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL These fluids were chosen according to the following specifics: a. Noncorrosive. b. Do not deteriorate rubber, painted surfaces, or plastics. c.

Have a high flash point.

d. Nontoxic. e. Good self-wetting and antifoaming characteristics.

REMOVE FROST, SNOW OR ICE WARNING: Remove all snow, ice and frost before flight. Type I, Type II and Type IV; Glycols are listed in the ‘harmful’ category. You must wear protective goggles, protective gloves and clothing when you handle this material. Keep the material away from skin and eyes. Inhalation of glycol mists, aerosols, or high concentration of heated vapors poses a hazard to humans. Apply deicing fluid only in well-ventilated areas. Avoid inhaling vapors or mists. If adequate ventilation, designed to keep mists or vapors below harmful levels, is not available, maintenance personnel must wear approved respiratory protective devices. De-icing fluid Type I, has a limited period of effectiveness (referred to as ‘Holdover Times (HOT)’). The use of Type I fluid should only be considered where Type II or Type IV fluids are not available. CAUTION: Make sure that the correct fluid application equipment and correct procedures are used by qualified personnel so that the fluid will perform to the specifications Fluid failure is complex and dependent on: • Outside air temperature (OAT) •

Percent mix

•

Type and rate of precipitation

•

Product Holdover Time (HOT), and other variables

Each product is unique and reference must be made to the manufacturers recommendations and the FAA guidelines which are published each year. Though these fluids pass the DTD crazing test for transparent panels, do not apply hot spray directly onto window panels or seals as damage may occur. The fluids identified in this procedure are for ground de-icing/anti-icing only and are not intended for and do not provide protection during flight. Residue from thickened de-icing/anti-icing fluids (Type ll or Type lV) can remain in aerodynamically quiet areas and accumulate over time. This residue can re-hydrate and expand into a gel-like material that could freeze during flight and cause restrictions in the flight control systems. The accumulation of residual fluid is more prevalent when using a one-step de-icing/anti-icing process which is commonly used in Europe. Page 2 of 7 Nov. 09

Temporary Revision No. 12-1

SUPER KING AIR B300/B300C MAINTENANCE MANUAL For operators using the one-step application process, visually inspect flight control systems for the presence of dry or re-hydrated fluid at least twice during the winter operations season. For operators using the two-step application process, visually inspect flight control systems for the presence of dry or re-hydrated fluid once at the end of the winter operations season, as a recommended minimum procedure. Each operator must determine their own frequency of inspection based on the operational tempo of their airplane or fleet. For additional information concerning this guidance please contact the HBC field service representative or the Technical Support telephone line.

GUIDELINES TO HOLDOVER TIMES (HOT) a. Visit FAA web site (www.faa.gov) and in the search field type [Holdover Time Tables] and press go/search. A listing will be called up that will include (but is not limited to) documents that read “FAA - Approved de-icing Program Updates” for the current year. When the Web Site cannot be accessed or questions arise, contact FAA Flight Standards, Washington DC at 202.267.8166 or Hawker Beechcraft Corporation 1.800.429.5372 or 316.676.3140. b. Before take-off the pilot in command must be satisfied the airplane is clear of frost, snow or ice, within the limitations stated in the applicable Aircraft Flight Manual. c.

If the holdover time is exceeded and visual/tactile investigation of flight surfaces is not possible, then the airplane should be returned for further treatment with de-icing/anti-icing fluid prior to takeoff.

d. Freezing point of SAE/ISO Type I fluid mixture used must be at a minimum of 10°C (18°F) below OAT.

GENERAL APPLICATION WARNING: Make sure the airplane is grounded before any work is started. While these procedures are done, the surfaces will be very slippery due to snow, ice, or de-icing/anti-icing fluid; use a servicing stand whenever possible. If a stand is not available, use mainplane mats, safety belts, and take other similar precautions. Always stand upwind of the airplane. De-icing/anti-icing fluids are toxic. Avoid contact with skin and eyes, use goggles and protective clothing. Functional check of flight controls - If an airplane has been extremely iced or snow covered, a flight control check should be done. This check should be repeated after de-icing. CAUTION: Wing skin temperatures may differ and in some instances be lower than the OAT. A stronger mix (more glycol) can be used under these conditions. The de-icing/anti-icing fluid used must be to a concentration and at a temperature in accordance with the fluid manufacturer's instructions, provided the following limitations are not exceeded: • For heated fluids, a temperature of 60° C (140° F) at the nozzle is desirable. The upper temperature limit shall not exceed fluid and airplane manufacturer’s recommendations.

Temporary Revision No. 12-1

Page 3 of 7 Nov. 09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

• Before you apply fluid, ground the airplane and make sure the covers and blanks are installed to the equipment that follows: - Static vents - Pitot heads - Stall detector vanes • To prevent possible ingestion of de-icing fluid, do not operate the engines or APU (if applicable) while de-icing is in progress. • After snow is cleared from the surfaces, make sure the areas listed below are free from snow or ice: - All air intakes - Control surface hinges - Gaps between wing trailing edge shroud and flaps, airbrakes and ailerons - Gaps between horizontal stabilizer and elevators - Gaps between rudder and vertical stabilizer - Wheel brakes - Landing gear bays - All doors and external drains - Cold air unit ram air exhaust outlet and duct The directions given in the fluid manufacturer’s instructions with reference to the possibility of mixing UCAR ULTRA with the residues of other fluids must be strictly adhered to. Minor contamination with Type I fluids can significantly degrade the anti-icing performance.

REMOVE FROST a. Spray with de-icing/anti-icing fluid to fluid manufacturer’s instructions. b. Under severe frost forming conditions, after defrosting, give a further light application of the concentrated fluid to make sure the maximum holdover period.

REMOVE SLEET AND FREEZING RAIN CAUTION: After spraying, examine surface thoroughly, as ice formed by freezing rain can be difficult to see under the de-icing fluid and may require touch for confirmation. •

Spray with undiluted de-icing/anti-icing fluid.

Page 4 of 7 Nov. 09

Temporary Revision No. 12-1

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

REMOVE SNOW DRY SNOW a. Remove by brushing, or by the application of a cold air blast, taking care not to trap the snow in the control surface gaps and hinges. b. If the ambient temperature is above freezing, the snow can be removed by the application of a hot air blast, and the cleared surface sprayed with diluted de-icing/anti-icing fluid. WET SNOW a. Remove with rubber squeegees, taking care not to trap the snow in the control surface gaps and hinges. b. If ice has formed under the snow, clear by spraying with de-icing/anti-icing fluid. FROZEN SNOW AND ICE FILMS a. Clear off any loose snow, then apply a heavy spray of de-icing/anti-icing fluid to the manufacturer’s instructions. •

Brush the snow as the fluid is being applied; this will assist in breaking up the deposit and help to retain the fluid on the deposit. When all frozen deposits have been removed, give a final light spray.

b. If the ambient temperature is above 0°C (32°F), ducted hot air blasts may be used to disperse the ice. •

Do not use hot air blasts near windows, and take extreme care to prevent damage by overheating to painted surfaces, rubber, glass, acrylic or glass fibre, hydraulic pipelines, grease or oiled surfaces.

•

Brush off or mop up water resulting from melted ice, as soon as possible.

DE-ICE THE WINDSHIELD •

Lightly spray windshield with fluid, windshield washing (DTD.900AA/4939A). If smearing occurs, wipe clear using a warm damp rag.

DE-ICE THE LANDING GEAR CAUTION: De-icing/anti-icing fluid must not come into contact with landing gear electrical plugs and harnesses. Do not let de-icing/anti-icing fluid contact brake units. a. Brush-off loose accumulations of snow with soft brush. b. Remove stubborn deposits with a rag soaked in de-icing/anti-icing fluid.

Temporary Revision No. 12-1

Page 5 of 7 Nov. 09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ANTI-ICING •

If meteorological reports predict the onset of freezing rain or heavy frost deposits, an anti-icing spray of cold (or hot if cold not available) concentrated ground de-icing/anti-icing fluid Type II or Type IV, will give limited holdover protection times, guidance for which is contained in Web Site mentioned in paragraph GUIDELINES TO HOLDOVER TIMES (HOT). If the precipitation is extremely heavy, deposits will form on top of the coating, but these will have little, if any, adhesion to the surfaces and can be easily removed with a light spray of hot diluted fluid.

FLUID SPILLS Glycol-based deicing fluids are biodegradable in water. Only gross contamination of slow moving or restricted bodies of water would be likely to cause any serious environmental impact. Typical field-use concentrations of deicing fluids, particularly when diluted by snow, ice or water, causes little or no injury to most broad leaf plants, grasses perennial ground cover, and woody plants. Minor leaks or spills of deicing fluid in storage areas must be soaked up with an absorbent material, such as sawdust, vermiculite, an all-purpose commercial oil absorbent, or sand. Carefully shovel the absorbent/deicing fluid into an appropriate container for disposal. Spilled, leaked, or contaminated deicing fluid must be disposed of in strict compliance with all applicable federal, state, and local regulations and ordinances.

REMOVE SALT OR CHEMICAL AGENTS CAUTION: Do not use high pressure water; damage may result to electrical equipment and lubricated components. a. Where contamination has occurred on the structure, due to the airplane landing on airfields where the snow or ice has been dispersed with salt or chemical melting agents: 1. Wash down the affected areas with clean water as soon as possible. A wetting agent, such as detergent cleaner (Teepol TS610) or Comprex A, may be added in small quantities. 2. When the time or conditions prevent removal of the contamination at outstations, this must be noted in the technical log, so that appropriate action may be taken to remove it at main base.

RESIDUE FROM DE-ICE/ANTI-ICE FLUIDS INSPECTION a. Gain access to areas, potentially affected by residue, where flight controls and other systems components are located. b. Visually inspect for the presence of dry or rehydrated residue anywhere in these areas. The residue may be difficult to see, especially if dry. Dry residue tends to be in the form of a thin film that may be partially covered with grease or dirt. Rehydrated residue often appears as a gel-like substance which is thicker and therefore more visible.

Page 6 of 7 Nov. 09

Temporary Revision No. 12-1

SUPER KING AIR B300/B300C MAINTENANCE MANUAL CLEANING a. After identifying any residue it should be removed by using warm water with rags and/or soft bristle brushes to clean the gel-like material away. CAUTION: Make sure the water or compressed air does not cause any residue to enter areas that are not accessible. Do not allow runoff from the cleaning process to enter other areas of the airplane. Avoid spraying cleaning fluids onto bearings, fittings, control cables and electrical connectors. Do not spray controls with water if the ambient temperature is below freezing unless the airplane is located in a heated hangar. This cleaning process can, potentially, remove grease from control system bearings and fittings, and remove corrosion inhibitors from control cables. b. The use of a low-pressure stream of water or compressed air to rinse away any residue may prove helpful. Using Type I de-icing fluid, or a mixture of water and Type I fluid, is also a good cleaning agent for removal of residue. RELUBRICATION (IF REQUIRED) •

If residue has been found and removed by cleaning, it is recommended that all bearings, fittings, and control cables in the affected area be relubricated (Ref. Chapter 12-20-00, 301, SCHEDULED SERVICING).

Temporary Revision No. 12-1

Page 7 of 7 Nov. 09

Ray~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

UNSCHEDULED SERVICING DEICING AND ANTI-ICING OFAIRPLANES ON THE GROUND

Deicing is the removal of ice, frost and snow from the airplane’s exterior surface. Anti-icing airplane exterior surface clear of subsequent accumulations of ice, snow and frost.

is

a means

of

keeping

the

Snow and ice will

seriously affect the performance of an airplane. Ice formations on the wing, even a smooth change the contour of the wing, producing an increase in drag and a reduction in effective lift coefficient. Frost or frozen snow may present an even greater hazard since the surface texture is rough and will seriously disrupt the smooth flow of air across the wing. covering of it,

will

SNOW REMOVAL The best way to

is to brush it off with a squeegee, soft brush or mop. Exercise care so as not to that damage any components may be attached to the exterior of the airplane, such as antennas, vents, stall waming devices, etc. Remove loose snow from the airplane before heating the airplane interior; otherwise, at low remove snow

temperatures, the frozen an

may melt and refreeze to build up a considerable depth of ice. Never attempt to chip or break airplane. If the airplane has been hangared and snow is falling, coat the airplane surfaces with

snow

snow

from the

anti-icing

solution:

After

snow

snow

falling

has been removed,

on

the

inspect

warm

the

surface will have

airplane

a

tendency to melt, then refreeze.

for evidence of residual snow,

particularly

in the

area

of control

surface gaps and in the hinge areas; carefully inspect these two areas visually to ensure that all ice or snow has been removed and that no puddles of water remain which may refreeze. Carefully inspect the static ports for evidence of obstruction. Check the exterior of the airplane for damage to external components that may have occurred

during

the

snow

removal

operations.

Control surfaces should be moved to ascertain that

they have full and free movement. The landing gear mechanism, doors, wheel wells, uplocks and microswitches should be checked for ice deposits that may impair function. When the airplane is hangared to melt snow, any melted snow may freeze again if the airplane is subsequently moved into freezing temperatures. Any measures taken to remove frozen deposits while the airplane is on the

ground

must also

Following

snow

prevent the possible refreezing of the liquid.

removal, should freezing precipitation continue, the airplane surface should be treated for anti-icing.

FROST REMOVAL

Heavy frost that cannot be removed by wiping airplane in a warm hangar or by the application After removal of all frost from the occurred

during

with

of

a

a gloved hand deicing fluid.

airplane exterior,

or

soft towel must be removed

check all external components for

damage

by placing

the

that may have

frost removal.

ICE REMOVAL Moderate made to

or

heavy

remove

ice

ice and residual

deposits

or

snow

break

an

deposits should be by force.

removed with

a

deicing

fluid. No attempt should be

ice bond

After

completing the deicing process, inspect the airplane to ensure that its condition is satisfactory for flight. All external surfaces should be examined for residual ice or snow, particularly in the vicinity of control surface gaps and hinges. Carefully inspect

the static ports for any

signs

of obstruction.

Control surfaces should be moved to ascertain that

they have full and free movement. The landing gear mechanism, doors, wheel wells, uplocks and microswitches should be checked for ice deposits that may impair function.

12-30-00

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

airplane is hangared to melt ice, any melted ice may freeze again if the airplane is subsequently moved into subzero temperatures. Any measures taken to remove frozen deposits while the airplane is on the ground must also prevent the possible refreezing of the liquid.

When the

Following

ice removal, should

freezing precipitation continue,

SAE TYPE I ANTI-ICING FLUIDS SAE

Type

I fluids

Type

II fluids

Type

provide protection against refreezing

IV fluids

when

anti-icing.

when there is

no

precipitation.

precipitation

occurs.

(THICKENEPTYPE FLUIDS)

provide protection against refreezing

approved Type I, Type II,

by

the fluid manufacturer’s recommendations.

Type

when

precipitation

IV fluids may be used for either

All

and

surface should be treated for

(THICKENED-TYPE FLUIDS)

SAE TYPE IV ANTI-ICING FLUIDS SAE

airplane

(UNTHICKENED-TYPE FLUIDS)

mainly provide protection against refreezing

SAE TYPE II ANTI-ICING FLUIDS

SAE

the

occurs.

deicing

or

anti-icing

at any dilution as allowed

DEICLNG a procedure by which frost, ice or snow are removed from the airplane. To preserve holdover time, the should be continuous and as brief as possible. It shall be carried out at the last possible moment prior to process takeoff. The deicing agent should be applied in a heated state to assure maximum efficiency.

Deicing

is

ONE STEP DEICING

One step deicing is done with a heated mixture of at least 10" C below the ambient temperature.

anti-icing

fluid/water formulated to

provide

a

freezing point buffer

ANTI-ICING

Anti-icing is a precautionary measure protected surface of the airplane.

which prevents frost, ice

CAUTION: If an additional treatment after

deicing/anti-icing

is

or snow

from

required before

forming

the next

or

accumulating

on

flight, anti-icing alone

the

is not

recommended. AL WA YS PERFORM A COMPLETE DNCING.

HOLDOVER TIME

anti-icing fluid will prevent frost, ice or snow from forming or accumulating on the protected surfaces of an airplane under average weather conditions. Holdover time tables shall only be used as part of an approved ground-deicing program. Holdover time is the estimated duration of the time that

PRECAUTIONS All reasonable

precautions

must be taken to minimize the

entry of fluid into engines, intakes and control surface

cavities. a.

Deicing/anti-icing must not be directed into the orifices of pitot heads or static vents; these fluids applied directly onto airstream-direction detectors, probes, angle-of-attack airflow sensors, or on

b.

The

c.

Both

Oct

engines

wings,

must be shut down

during deicing/anti-icing.

and tail section must receive the

31/0612-30-00

same

complete

treatment.

must not be

windows.

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Any traces

of

deicing/anti-icing

fluid

windscreens After

e.

on

cockpit windows

must be removed

prior to departure. Pay particular

In addition, any forward area from which the fluid may flow back onto taxi and takeoff must be clean prior to departure.

attention to windows fitted with

during

wipers.

prolonged periods of deicing/anti-icing, it is advisable to check for aerodynamical cove areas and cavities like balance bays, and

fluids in

residues of thickened

deicing/anti-icing

spars of the

and stabilizers.

rear

wing

CHECKS FOR THE NEED TO DEICE The

tail section and

wings,

If frost

or

ice has formed

have to be checked for

fuselage

the lower surface of the

on

wing

possible ice,

snow

in the fuel tank

area

and frost accumulation.

while the

airplane

is

being exposed

the upper surface of the wing must be carefully examined for the formation of clear ice. In conclusion, it should be noted that heavy freezing has been reported as forming at temperatures up to +15" C~ 59" F (caused by cold fuel).

to

precipitation train, drizzle,

or

fog),

CA UTION: It must always be remembered that clear ice which is very difficult to detect may underlie slush.

a

layer of snow/

FINAL CHECKS AFTER AIRPLANE DNCING

Wing

and stabilizers have to be free of frost, ice and snow as well as water accumulation. drifting snow, snow and melting ice could penetrate and refreeze in slots, balance

During snowfall, freezing bays, drainage openings, be checked with special attention

rain and

hinges and operating linkage. Consequently, the areas just-mentioned have to airplanes have been parked outside for a long period of time under the inclement conditions. The same precautions apply to inlet scoops, ram tubes and landing gear areas, including landing gear, latching mechanism and electrical switching elements.

when

CHECK OF COMPLETE DEICING If ice all

was

upper surface, recheck the entire wing through all accessible of ice have been removed after deicing/anti-icing has been accomplished.

found

deposits

CAUTION: In

Fuselage

the

wing

some cases

areas

inlet and outlet

on

the presence of ice

in front of the

openings

can

only be

openings

to

ensure

that

determined by touch.

flight compartment windows must be free of ice and air-conditioning as well as their adjacent areas.

snow.

This is also valid for all air

of the

FUNCTIONAL TEST OF FLIGHT CONTROLS in

a case

where

an

airplane has been extremely repeated after deicing.

iced

or snow

covered,

a

flight

control check should be

performed.

This check should be

CHECK OF ENGINE INLETS AND PROBES

Engines that

exposed to heavy snowfall and/or freezing rain during cold temperatures prior to start-up for accumulation of snow and/or ice in the inlet area.

have been

must be checked

DNCING AND ANTI-ICING FLUIDS Raytheon

Aircraft

Company

has evaluated and

Type

I fluid per SAE AMS 1424

Type

II fluid per SAE AMS 1428

nn

or

or

approved

the

following deice/anti-ice

fluids:

ISO 11075.

ISO 11078.

12-30-00

and strong winds

Raythwm

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Type

IV fluid per SAE AMS 1428.

These fluids

are

authorized for

use on

Super King

Air Model B300/B300C

Airplanes.

Raytheon Aircraft Company cannot accept responsibility for damage to the airplane finish, windows, resulting from the use of deicing fluids not conforming to the specified specifications.

rubber seals,

etc.

These fluids

were

chosen

according

a.

Noncorrosive.

b.

Do not deteriorate rubber,

c.

Have

d.

Nontoxic.

e.

Good

a

to the

following specifics:

painted surfaces,

or

plastics.

high flash point.

self-wetting

antifoaming characteristics.

specially inhibited, glycol-based solutions that leave a fairly tough, viscous coating on the absorbing at least its own weight of water. As moisture is absorbed, it becomes soluble with the deicing fluid. While the fluid remains liquid, snow and ice will not adhere to it. This protection will remain until the fluid becomes overly diluted by falling snow or freezing rain.

These

deicing

surface. Each

fluids

and

are

drop is capable of

glycol mists, aerosols, or high concentration of heated vapors poses a hazard to humans. Thus, workers must apply deicing fluid only in well-ventirated areas, and must avoid Inhaling vapors or mists. If adequate ventilation, designed to keep mists or vapors below harmful levels, is not available, workers must wear approved respiratory protective devices.

WARNING: Inhalation of

HANDLING PRECAUTIONS The

following precautions

a.

Do not

permit glycol

If the solution is

b.

should be taken when

solution to

spilled

on

come

gloves

or

using deicing

and

anti-icing fluids:

in contact with the skin. It may

clothing,

remove

cause

serious frostbite.

immediately. Rapid evaporation of the

solution

can

lower

temperature of material and destroy insulating qualities. c.

Avoid contact with skin

d.

Stay on the windward

or

side

eyes.

during application. Prolonged exposure to heavy concentrations

of

glycol vapors

are

to be avoided. e.

Don’t let solution contact

f.

Avoid

g.

Take

applying the care

when

bearings.

solution

walking

on

on

It may dilute the grease.

windows because it may reduce

surfaces that

are

coated with

visibility.

glycol.

The mixture leaves

a

slippery film

that is

hazardous to walk upon. h.

Take

precautions to keep the solution from entering air ducts or cabin entering the cabin or cockpit during taxi or takeoff.

heater and ventilator ducts, because of

toxic fumes

Oct

12-30-00

*21

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FLUID APPLICATION fluids may be used diluted or undiluted according to manufacturer’s recommendations for applied either heated or unheated.

Aircraft

deicing

Deicing

fluids may be

General recommendations for deicing and anti-icing treatments may be summarized a.

Cold

application

of

deicing

fluid is achieved with normal spray

as

equipment operating

deicing.

follows: at about 60

80

psig air

pressure.

b.

Hot

c.

Remove

d.

Use

e.

require heated fluid. Use only the appropriate spray equipment for the being applied. The spray must be fine and applied in a thin uniform coating. If a sprayer is not type available, brush or paint the deicing fluid onto the airplane’s surface.

application

a

as

much

stream

Anti-icing

must be carried out with a

or

heavy

snow as

spray of fluid

of ice-free

200" F.

possible before applying deicing

sufficiently

airplanes

temperature of 180

coarse

fluids.

to float away loose

pieces

of ice.

does not

of fluid

FLUID SPILLS

Glycol-based deicing

fluids

are

bodies of water would be

biodegradable

in water.

Only

gross contamination of slow moving or restricted impact. Typical field-use concentrations of

to cause any serious environmental

likely deicing fluids, particularly when diluted by snow, ice grasses, perennial ground cover and woody plants.

or

water,

causes

little

or no

injury

to most broadleaf

plants,

deicing fluid in storage areas must be soaked up with an absort~ent material, such as sawdust, vermiculite, an all-purpose commercial oil absorbent, or sand. Carefully shovel the absorbent/deicing fluid into an appropriate container for disposal. Minor leaks

or

Spilled, leaked,

spills

or

of

contaminated

deicing

fluid must be

disposed of

in strict

compliance

with all

applicable federal,

state, and local regulations and ordinances.

12-30-00

Oct

31/06Page

305

C H A PT E R

STANDARD

PRACTICES

(ARFRAME)

REV34, 4/20/07

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 20 - STANDARD PRACTICES - AIRFRAME TABLE OF CONTENTS SUBJECT

PAGE 20-00-00

Standard Practices - Airframe - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 20-01-00 - Nut and Bolt Torque Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 20-02-00 - Electrostatic Discharge Sensitivity Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 20-03-00 - Electrical Bonding Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 20-04-00 - Control Cable and Pulley Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 20-05-00 - Bearing Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 20-06-00 - Tubing Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 20-07-00 - Fastener Locking Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 20-08-00 - Airplane Finish Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 20-09-00 - Corrosion Removal and Control Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 20-10-00 - Sealing and Adhesive Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 20-11-00 - Fiberglass Repair Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 20-01-00 Torque Wrenches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 20-02-00 Electrostatic Discharge Sensitivity - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Electrostatic Discharge Sensitivity Classification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Electrostatic Discharge Sensitivity - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 ESDS Equipment Removal/Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Handling of ESDS Components and Equipment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Controlling Static Charge Build Up . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Permanent Static Control Workstation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Portable Static Control Workstation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Humidity and Dust Effects on ESDS Components and Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Packaging of ESDS Components and Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Marking of ESDS Components and Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Storage and Transit of ESDS Components and Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205

A28

20-CONTENTS

Page 1 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 20 - STANDARD PRACTICES - AIRFRAME TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 20-03-00

Electrical Bonding - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Electrical Bonding Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Direct Electrical Bonding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Indirect Electrical Bonding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Electrical Bonding of Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Electrical Power Returns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Special Tools and Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Electrical Bonding - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Metal Surface Preparation and Electrical Bonding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Aluminum Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Corrosion-Resistant (CRES) Steel Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Stainless Steel and Titanium Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Electrical Bonding Examples . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Typical Blind Ground Stud. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 CRES Steel or Titanium Electrical Bonding. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Aluminum Electrical Bonding. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 211 Tubing Clamp to Bonding Jumper Electrical Bonding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 211 Bonding Jumper across Tubing Clamp Electrical Bonding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 211 Typical Ground Stud Electrical Bonding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 211 Electrical Bonding of Ground Tabs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 212 Resistance Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 212 20-04-00 Control Cables and Pulleys - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Control Cables and Pulleys - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Control Cable System Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Control Cable Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Control Cable Pulley Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 20-05-00 Bearings - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Bearings - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Hydraulic Press Bearing Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Mechanical Press Bearing Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Bearing Housing Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Bearing Installation using Retaining Compound . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Bearing Installation by Staking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202

Page 2 May 1/10

20-CONTENTS

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 20 - STANDARD PRACTICES - AIRFRAME TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 20-06-00

Tube and Hose Assemblies and Fittings - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Tubing and Hose Assemblies and Fittings - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Leakage at Thread Coupling. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Tube Manufacturing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Removal of Tube and Hose Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Hose Assembly Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Tube Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Fluid Line Fitting Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Non Positioning Type Fitting Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Pipe Thread Fitting Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Tube Damage Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Tubing, Hoses and Fittings Inspection/Check. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 20-07-00 Locking Devices - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Self-Locking Nuts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Slotted, Steel Locknuts (Prevailing Torque Type). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Lockwire and Cotter Pin Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Locking Devices - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Lockwire Installation Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Lockwire Hole Alignment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Lockwire Twisting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Cotter Pin Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Keywashers (Tab and Cup Types) Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Retaining Rings (Spirolex, etc.) Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Turnbuckle Lock Clip Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 20-08-00 Airplane Finish Care - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Airplane Finish Care - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Airplane Finish Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Environmental Fallout (Acid Rain). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Waxing Airplane Finishes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Placard Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Urethane Paints . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 During the Cure Period (One Month) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Touch Up. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Functional Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Decorative or Buffed Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203

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Similar and Dissimilar Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Condition of Paint Before Use . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Finishing Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Temperature and Environment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Safety Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Spray Paint Guns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Conventional Spray Guns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . High Volume / Low Pressure (HVLP) Spray Guns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Airplane Surface Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Initial Inspection of Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Initial Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stripping and Cleaning Urethane Paint . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Filling of Eyebrows . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning and Preparation of Unprimed Aluminum Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning and Preparation of Acrylics (Plexiglas). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning and Preparation of Fiberglass Laminates. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning and Preparation of ABS and PVC Acrylic Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning and Preparation of Polycarbonate Surfaces. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning and Preparation of Composite Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning and Preparation of Preprimed Airplane Skins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning and Preparation of Stainless Steel Airplane Skins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning and Preparation of Anodized Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Application of Chromate Conversion Coating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Masking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Final Clean Before Urethane Compatible Primer. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pretreatment (Wash) Primer for Urethane Paints . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Application of Urethane Compatible Primer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Topcoat Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Sanding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Topcoat Application . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Topcoat Cure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Preparation and Application of Color Markings (Stripes or Trim). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rework of Color Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Repaired Area Thickness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Limit of Repair Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Topcoat Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Urethane Touch-Up Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Overspray Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Spot Repair of Solid Colors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Spot Repair of Metallic and Non-Metallic Colors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Paint Adhesion Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Special Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Radome . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installation of Bonded Lightning Diverter Strips. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installing Self-Adhesive Lightning Diverters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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Radome Protective Boot. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Radome Protective Boot Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Radome Protective Boot Maintenance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Radome Protective Boot Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .222 Protective Tape . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .223 Protective Tape Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .223 Protective Tape Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .224 Protective Tape Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .224 Air Intake Protective Boot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .225 Air Intake Protective Boot Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .225 Air Intake Protective Boot Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .225 Air Intake Protective Boot Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .225 Bullet Protective Boot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .226 Bullet Protective Boot Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .227 Bullet Protective Boot Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .227 Bullet Protective Boot Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .227 Tape and Residue Removal (Alternate Method) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .228 Tape Residue Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .228 Protective Tapes and Neoprene Rubber Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .229 Abrasion Resistant Polyurethane Spray Coating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .229 Abrasion Resistant Polyurethane Spray Coating Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .229 Abrasion Resistant Polyurethane Spray Coating Application . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .229 Erosion Prevention Sealant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .231 Air Inlet Ducts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .232 Urinal Surface Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .232 Battery Box and Lid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .232 Rubber Seals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .232 Laminated Fiberglass Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .232 Painting Wet Wing Fuel Access Plates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .233 20-09-00 Corrosion - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Uniform Etch Corrosion. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Intergranular Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Pitting Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Exfoliation Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Electrolytic Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Galvanic Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Corrosion - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Corrosion Prevention . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Corrosion Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Corrosion Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Safety Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Vapor Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202

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PAGE

Solvent Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Kerosene. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dry Cleaning Solvent and Toluene . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Naphtha and Methyl Propyl Ketone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Abrasive Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Blast Abrasive Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Manual Abrasive Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Alkaline Water Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Corrosion Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aluminum Corrosion Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Removal of Corrosion from Aluminum Surfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aluminum Corrosion Treatment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Magnesium Alloy Corrosion Treatment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Steel Corrosion Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Corrosion Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

202 202 202 203 203 203 203 203 204 204 204 204 205 205 206

20-10-00 Sealing/Bonding - Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Sealing/Bonding - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Surface Preparation for Bonding/Sealing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Sealer/Adhesive Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Sealer/Adhesive Application . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Sealing and Bonding Material Charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Supplier Information Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 214 20-11-00 Fiberglass Repair - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Fiberglass Repair - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Fiberglass Minor Damage Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Fiberglass Major Damage Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201

Page 6 May 1/10

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PAGE 20-12-00

Electrical Wiring - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Wiring Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Routing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Slack in Wire and Cable. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Electromagnetic Compatibility . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Power Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Flight Essential Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Parallel Circuits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Splice Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Support and Protection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Wire and Cable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Primary Wiring Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Lightening Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Plastic Loop Clamps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Grommets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Hole Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Clamp Size . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Secondary Wiring Supports . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Tie-Down Straps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 J-Stringer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6 Limitations of Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7 Anti-Chafing Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .8 R.F. Coaxial Cable Support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 Radius of Bend. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 Drip Loop . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 Wires and Cables Near Moving Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 Special Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 Line Separation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 Wire Routing Near Hot Areas. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10 Support and Protection of Cables and Wires in Flammable Areas . . . . . . . . . . . . . . . . . . . . . . . . . . .10 Line Separators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .10 Electrical Wiring - Routine Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .13

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List of Effective Pages CH-SE-SU

PAGE

DATE

20-LOEP

1

May 1/10

20-CONTENTS

1 thru 7

May 1/10

20-00-00

1 and 2

May 1/08

20-01-00

1 thru 6

May 1/08

20-02-00

1 thru 3 201 thru 211

May 1/08 May 1/08

20-03-00

1 thru 3 201 thru 212

Feb 1/10 Feb 1/10

20-04-00

1 and 2 201 thru 203

May 1/08 May 1/08

20-05-00

1 201 thru 204

May 1/08 May 1/08

20-06-00

1 201 thru 209

May 1/08 May 1/10

20-07-00

1 201 thru 207

May 1/08 May 1/08

20-08-00

1 thru 5 201 thru 236

Feb 1/09 Feb 1/09

20-09-00

1 thru 3 201 thru 206

Feb 1/09 Feb 1/09

20-10-00

1 201 thru 216

May 1/07 May 1/07

20-11-00

1 201 thru 204

May 1/08 May 1/08

20-12-00

1 thru 15

May 1/10

A28

20-LOEP

Page 1 May 1/10

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STANDARD PRACTICES

AIRFRAME

DESCRIPTION AND OPERATION

WARNING: Any maintenance requiring the disconnection and reconnection of flight control cables, plumbing, electrical connectors or wiring requires identification of each side of the component

being

disconnected to facilitate correct reassembly. At tagged or properly identified in

correctly

reconnect the

identification

airplane

or

prior

to

disassembly, components

way that it will be obvious how to After reconnection of any component, remove all

should be color coded,

components. tags. Check all associated systems for

a

correct function

prior

to

returning

the

to service.

This

chapter describes the standard maintenance practices used in maintaining the airplane in an airworthy chapter is applicable during maintenance in several chapters of this maintenance manual. Maintenance procedures in a particular chapter supersede the general information in this chapter.

condition. The information in this

The information is broken down in several

unit/subjects.

The

following

is

a

list of the information contained in each

chapter. 20-01-00 This

NUT AND BOL T TORQUE INFORMA TION

unit/subject

of torque

contains the

adapters

20-02-00

general information for installation of torqued fasteners. It has information showing the torque of different types of nuts and bolts.

on

the

use

and torque charts

ELECTROSTA TIC DISCHARGE SENSITIVITY INFORI~IA TION

unit/subject contains the general information for maintenance of components that are subject to electrostatic damage. Information is included for electrostatic free workstations, symbols, packaging requirements, storage and transit requirements, static charge buildup and humidity and dust effects. This

20-03-00 This

ELECTRICAL BONDING INFORMA TION

unit/subject

contains the

general information for installation of electrical wiring grounding,

tube

grounding

and

electrical power returns.

20-04-00 This

CONTROL CABLE AND PULLEY INFORMA TION

unit/subject

contains the

information for maintenance and

general

inspection

of control cables and

pulleys.

20-05-00- BEARING INFORMATION

unit/subject contains the general information for installation and removal of bearings. The removal is described use of the hydraulic and mechanical press method. The installation is described by use of the retaining by compound and the staking method. This

the

20-06-00- TUBING INFORMATION This

unit/subject contains the general

information for maintenance of hoses,

tubing and fittings. Components are not applications. Any specific information on the system is for the landing gear is in Chapter 32. Includes information hydraulic tubing

identified, but the information is basic and applies contained the on

applicable chapter such bending

as

to most

tube mismatch and

20-07-00 This

FASTENER LOCKING INFORMATION

unit/subject

contains the

general information for the installation of

cotter

pins, lockwire,

tab and cup type

key

washers, retaining rings and turnbuckle locking clips.

nz,

20-00-00Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

20-08-00 This

AIRPLANE FINISH INFORIVIA TION

unit/subject contains application.

the

information for maintenance of the finishes used

general

on

the

airplane

and

paint

removal and

20-09-00 This

unit/subject

20- 10-00 This

CORROSION REMOVAL AND CONTROL INFORMATION contains the

general information for

the control, treatment and removal of corrosion.

SEALING AND ADHESIVE INFORMA TION

unit/subject

contains the

general

information for

application

recommendations and solvents used to clean the sealer

20- 1 i-00

or

of sealer and adhesives, sealer

cure

FIBERGLASS REPAIR INFORMA TION

unit/subject contains the general information for repair of minor and major fiberglass damage. conditioning ducts, heat ducts or interior plastic or fiberglass parts repair.

This air

applications,

adhesive.

It does not

cover

SPECIAL TOOLS AND RECOMMENDED MA TERIALS The

special tools and subchapterforconvenience.

May

1/08Page

2

recommended materials for this

20-00-00

chapter

are

included in charts located in the

applicable

na4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TORQUE WRENCHES Threads of nuts and bolts to be

of normal friction NOTE:

Torque

by

torqued

must be clean and free of all lubricants unless otherwise

contamination may result in

specified.

The loss

overtorquing.

wrenches should be exercised before

they

are

used.

NOTE: A measurable torque may be required to initiate the turning of some locknuts. This initial torque must then be added to the desired torque to attain the proper torque setting. For example: a locknut that requires 20

inch-pounds of

force to turn

freely

should be

torqued

at 20

inch-pounds

above the desired torque. If the

desired torque is 80 inch-pounds, the torque wrench must indicate 100 inch-pounds to achieve the desired torque. This method compensates for the friction of the locknut or fastener. an adapter is used with a torque wrench (Ref. Figure 1), compensation must be made for the increased or leverage. A new torque requirement must be calculated before the final torquing. To figure the desired torque which will actually give the torque specified, use the following formula:

When

lost

Basic

Torque

Formula:

TxL

L~E

LEGEND:

(Desired) Torque

T

Actual

Y

Apparent (Indicated) Torque

L

Effective Lever

E

Effective

Length

Length of

Extension

EXAMPLE:

T =135 Y

inch-pounds

Unknown

L=10.0

E

1.5 inches

Formula for increased effective

Y=

Y =117

A24

135 x10

1350

10+1.5

11.5

length:

117.3E

inch-pounds.

20-01-00Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Formula for decreased effective

Y=

Y If

135 x10

1350

10-1.5

8.5

=158.82

inch-pounds.

159 a

torque wrench is

(Ref. Figure 2)

to

perpendicular to

a

an

not

inch-pounds by specified torque

available,

imaginary

method of

checking the torque is to attach a spring scale an adaptor. Force should be applied in a direction center of the bolt through the spring scale attaching point.

"T" handle inserted into

extending

from the

pounds (scale reading) required

is 200

inch-pounds

to obtain the

and the distance is 15 inches,

torque wrench adaptor is used, the length of the adaptor

a

and

value calculated for that

Effective

length of flex

Handle wrench

length

specified torque, divide the torque in attaching point. For example, of 13.3 pull pounds must be applied.

or

particular

combination. The

a

if the

length of the flex or’7" handle typical example in finding a desired value.

must be added to the

following

is

a

"T"

12 inches

Length of adaptor

3 inches

15 inches

Desired torque

on

(2000 in-lbs.)

May

line

acceptable or

distance in inches between the center of the bolt and the scale

When

Total

an

conventional flex

To calculate the force in

a

length:

bolt

2000

(15 in.)=

inch-pounds 133.3

1/0820-01-00

n24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I

j

TOROUE WRENCH DRIVE CENTERLINE

I

CENTERLINE (PREDETERWINED)

HANDGRIP

ADAPTER DRIVE CENTERLINE

ORIGINAL As Received

2000-017-01

By

ATP

Torque

Wrench and

Figure

A24

Adaptor

1

20-0100

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

G?(L31 L

TORQUE

(IN-IBS. 30"

TOTAL

LENGTH 2000-3

Computing Torque With Figure 2

a

Spring

7-02

Scale

ORIGINAL By

As necelvad

ATP

Page

4~f

20-01-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

FINE THREAD SERIES, CLASS 3, CADMIUM PLATED AND NONLUBRICATED

Torque Limits Recommended (Inch-Pounds)

5/3236

3/1 632

1/428

5/1 624

3/824

7/1 620

1/220

9/1 618

5/818 3/416

7/814

This is

Tightening Torque (Inch-Pounds) Column 4

Column 3

MS21042

MS 20364

MS21245

Dry-Film

8 AN320

Dry-Film

AN310

Dry-Film

AN320

Dry-Film

Nuts

Lub Nut

Nuts

Lub Nut

Nuts

Lub Nut

Nuts

Lub Nut

(Tension)

(Tension)

(Shear)

(Shear)

(Tension)

(Tension)

(Shear)

(Shear)

12-15

MS20365

7-9

20

MS21042

MS 20364

MS21245

12

20-25

15-19

12-15

40

30

25

50-70

37-47

30-40

100

70

60

100-140

56-78

60-85

225

135

140

160-190

72-108

95-110

390

200

240

450-500

270-300

840

500

480-690

290-410

210-230

1100

660

415

800-1000

480-600

310-430

1600

960

660

1100-1300

660-780

485-605

2400

1400

1060

2300-2500

1300-1500

1090-1250

5000

3000

2500

2500-3000

1800-2400

1640-2100

7000

4200

3740

a coarse

(.1 640-32) with inch-pounds.

thread

tightening torque of

A24

NOTED)

AN310

MS20365

Size

AS

Maximum Allowance

Column 2

Column 1

(EXCEPT

14

recommended torque ii mits of 9-1 1

inch-pou nds

and

a

maximu m allowable

20-01-00Page

5

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 COARSE THREAD SERIES, CLASS 3, CADMIUM PLATED AND NONLUBRICATED

Torque Limits Recommended (Inch-Pounds) Size

AN365

AN310 Nuts

AN364

AN320 Nuts

Maximum Allowable AN365

AN310 Nuts

(Torque Inch-Pounds) AN364

AN320 Nuts

(Tension)

(Shear)

(Tension)

(Shear)

8-32

12-15

7-9

20

12

10-24

20-25

12-15

35

21

1/4-20

40-50

25-30

75

45

5/1 6-18

80-90

48-55

160

100

3/8-16

160-185

95-110

275

170

7/1 6-14

235-255

140-1 55

475

280

1/2-13

400-480

240-290

880

520

9/16-12

500-700

300-420

1100

650

5/8-11

700-900

420-540

1500

900

3/4-10

1150-1600

700-950

2500

1500

7/8-9

2200-3000

1300-1 800

4600

2700

1-8

3700-5000

2200-3000

7600

4500

5500-6500

3300-4000

12000

7200

6500-8000

4000-5000

16000

10000

11/8-

11/4-

Page

620-01-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTROSTATIC DISCHARGE SENSITIVITY

DESCRIPTION AND OPERATION

discharge (ESD), and require special charge which has been generated by actions such as contact, rubbing, or separating of materials. A charge of this type can damage electrical and electronic equipment installed in the airplane. In some instances, the damage may not be immediate, but progressive. Components and items of equipment that can be damaged by electrostatic discharge are considered to be electrostatic discharge sensitive (ESDS). Electronic components that are considered to be electrostatic discharge sensitive include integrated circuits, transistors and diodes, monolithic and hybrid microelectronics, MOS capacitors, thin film resistors, and piezoelectric crystals. Any circuit or piece of equipment containing ESDS components is subject to ESD damage if certain handling precautions are not observed. Some types of electronic components are handling and storage procedures. ESD is

easily damaged by

a

electrostatic

release of stored electrostatic

Personnel who remove, inspect, test or install instruments and equipment containing ESDS components must be of the possibility of ESD damage, and should handle ESDS components in accordance with procedures

aware

chapter. Proper procedures and policies following reasons:

covered in this

for the

handling

of ESDS components and

equipment

should be adhered to for the

Control of ESD

damage,

and must be maintained

from time of component manufacture to time of actual installation, must be verifiable use of established industry standards.

by

policy dictates that all personnel follow certain procedures to prevent damage to equipment.

Established and

Interacting

areas

of

responsibility

must be aware of their

obligation

ESDS components

to maintain proper ESD-controlled

environments.

charge polarity and magnitude for each. Materials at I capable of producing the greatest amount of positive electrostatic charge, while materials at are capable of producing a similar negative electrostatic charge. Items of dissimilar polarity provide the greatest potential for electrostatic discharge. Numeric values have not been assigned to the listed materials, as static charge levels are not constant, and will vary with ambient conditions. A greater possibility of ESD exists when the positions of listed items in Chart 1 are farther apart. For example, an individual using his/her hands to pick up a PVC pipe has more potential for producing ESD than does an aluminum part contacting a steel part. Chart 1 lists several materials and the associated electrostatic

the top of the list are the bottom of the list

Chart 2 identifies

some

typical

electrostatic

charge

levels and the actions that

can

produce

the electrostatic

charge. I

ELECTROSTA TIC DISCHARGE SENSITIVITY CLASSIFICA TION sensitivity classification are established for electrostatic discharge sensitivity devices. Classification or supplier in providing packaging and handling requirements that protect the ESD sensitive item, device or component through all phases of handling and packaging of the device during its service life. The three classes of ESD sensitivity are as follows:

Three levels of

is used to aid the manufacturer

Class 1

Sensitivity

range is from 0 to 1,999 volts.

Class 2

Sensitivity

range is from 2,000 to 3,999 volts.

Class 3

Sensitivity range

nn,

is from 4,000 to 15,999 volts.

20-02-00Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

Electrostatic Charge Levels

1

MATERIALS

CHARGE

(Relative Magnitude

Polarity)

IPositive

Air Human Hands

Positive

Asbestos

Positive

Rabbit Fur

Positive

Glass

Positive

Mica

Positive

Human Hair

Positive

Nylon

Positive

Wool

If>ositive

Fur

IPositive

Lead

IPositive

Silk

Positive

Aluminum

Positive

Paper

Positive

Cotton

J--Neutral--

Steel

I Negative Negative

Wood

I Negative

Amber Wax

Negative

Hard Rubber

Negative

Nickel, Copper

Negative

Sealing

Il\legative

Brass, Silver

Negative

Gold, Platinum

(Negative

Sulfur

Acetate, Rayon

Negative

Polyester

Negative

Celluloid

Negative

Orion

Negative

Saran

\Negative Negative

Polyurethane

May 1/08Page

and

2

20-02-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 Electrostatic

Charge

Levels

MATERIALS

CHARGE

Polyethylene

Negative

Polypropylene

Negative

PVC

Negative

(Vinyl)

KEL-F

(CTFE)

(Relative Magnitude

and

Polarity)

Negative

SILICON

Negative

TEFLON

Negative

Chart 2

Typical Action of Person

Walking

across

carpet.

Walking

across

vinyl

Seated in

Picking

up

Most Common

tile floor.

polyurethane

foam chair.

poly bag.

Inserting papen~vork

into

Electrostatic

vinyl envelopes.

Voltages

Reading (Volts)

Highest Reading (Volts)

12,000

39,000

4,000

13,000

1,800

18,000

1,500

20,000

800

7,000

NOTE This data based

A24

on an

ambient relative

humidity

of 15 to 36%.

20-02-00

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTROSTATIC DISCHARGE SENSITIVITY

MAINTENANCE PRACTICES

ESDS EQUIPMENT REMO VAUINS TA LLA TIQN Observe the

following procedures

CA UTION: Tools with plastic

removing

or

installing ESDS equipment

at the

airplane:

insulated handles should not be used around ESDS devices. These tools

can carry Insulated tools should charge readily discharge during grounding process. be used only during power-on testing of aircraft systems to prevent electrical shock to maintenance personnel performing the tests. a

static

or

when

which does not

the

CAUTION: Some circuit board assemblies may be protected by plastic covers. These covers can store an electrostatic charge. Use a static control work station to neutralize any electrostatic charge on the before a.

b.

touching

When

using

Use

portable static airplane.

a

at the

test

a

printed

circuit board. Store the

equipment, discharge

all test leads to

control work station when

covers a

safe distance from the work

ground prior to

removing

connection to the ESDS circuit under test.

ESDS circuit boards from card cages and enclosures

Place removed ESDS

c.

shielding Just

d.

container

equipment on the work station static dissipative holding the replacement ESDS equipment.

prior to engaging

a

cable connector with its

shell to neutralize any electrostatic

Maintain

e.

protective coverings

on

charge

on

or

work surface before

opening

touch the connector shell to the

mating receptacle,

the connector

stored ESDS

covers

area.

the installer’s

the static

receptacle

body.

equipment.

HANDLING OF ESDS COII~PONENTS AND EQUIPMENT All

personnel handling ESDS components and equipment should receive instruction in the proper handling of following handling rules to prevent damage to ESDS components and equipment:

such

items. Observe the a.

Keep ESDS components

and

equipment

inside ESD

protective packaging

until

opened

at a static control work

station b.

Before

unsealing

ESD

protective packages, place the packages

on

the work surface of

a

static control work

station. c.

Do not use pressure air nozzles to remove dust from ESDS printed circuit boards. Rapid movement of air, combined with airborne dust particles, can create an electrostatic charge that will destroy ESDS components.

d.

Always

e.

Avoid

f.

place any ESDS component, before or after assembly, specifically designed for storage of ESDS devices.

g.

wear a

touching

grounding

wrist strap when

circuit components

or

opening

connector

Never

Protect ESDS components and

equipment

with

any ESD

pins

when

protective package.

handling ESDS components on a

or

nonconductive surface

protective containers,

equipment.

or

in

conductive caps, and/or

a

container not

pin-shorting

devices. h.

Store and transport ESDS components and equipment in ESD an ESD warning label prior to shipment.

protective

containers. Seal all

protective

containers with

P~4

20-02-00

1/08

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Place all loose ESDS components and wrist strap.

i.

equipment

into ESD

protective

containers BEFORE

removing

a

grounding

the work station free of any material not

j.

Keep

k.

Follow established ESD

I.

Always use a static control work station, equipment from protective packaging.

m.

Use

protection

rules and

only grounded, electrically isolated,

required

to

the

accomplish

assigned

task.

procedures.

either permanent

or

portable,

and temperature controlled

when

soldering

removing

ESDS components and

irons that have been rated for

use

with ESDS components and equipment. Use only hand tools that have conductive or static dissipative handles or grips. Test equipment, such as scopes and meters, must be rated for use around ESDS components and

equipment. n.

exposing ESDS components and equipment transformers or transmitting antennas. Avoid

to

large electromagnetic

or

electrostatic fields such

as

CONTROLLING STATIC CHARGE BUILD UP Four basic a.

techniques

are

employed

in ESD control. These

MINIMIZE THE CHARGE BUILDUP

are:

Minimize electrostatic

dissipative flooring and static-dissipative

charge buildup by using

DRAIN OFF THE CHARGE TO GROUND

charges on the body can strap. Always wear a grounding

The human

dissipated by

electrostatic

be

ankle

wrist strap when

body is

a

good

ESD

static

grounding ionized

electrical conductor and for that

reason

or

synthetics.

Use

grounding device such as a wrist or containers or handling exposed ESDS

skin contact with

opening

or

a

an

ankle strap to dissipate body charge buildup. Wear cotton clothing instead of wool air blower to dissipate charges from nonconductive items. b.

conductive

work surfaces. Wear leather shoes, cotton socks, and

a

components and equipment. c.

Nonconductors, such as polystyrene coffee cups, plastic bags, and some electrostatic that cannot be neutralized by grounding. lonized air flow will neutralize charges develop clothing an electrostatic charge on a nonconductor as long as the ionized air blower puts out both positive and negative NEUTRALIZE THE CHARGE

ions. d.

MINIMIZE THE EFFECTS OF ELECTROSTATIC FIELDS

The immediate environment

components and equipment must be free of electrostatic fields induced effects from electrostatic fields.

or

must have suitable static

surrounding ESDS shielding to minimize

PERMANENT STA TIC CONTROL WORKSTA TION

provides for static-free handling of ESDS components ground, electrostatic charges on conductive objects (Ref. Figure 201).

A static control work station

A

and

equipment by diverting,

to

permanent static control work station consists of the following items:

Page

20-02-00

,4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

wear a grounding wrist strap over clothing. The strap must be in contact with the wearer’s skin adequately dissipate any electrostatic charge. Under certain conditions, personnel using a grounding wrist strap may need to use a lotion-type skin moisture enhancer to provide a low resistance connection

CAUTION: Never to

between the wrist and the wrist

strap.

Each person that handles ESDS components and equipment must wear a wrist to dissipate bodily electrostatic charges. The wrist strap must fit firm against the skin and strap grounding release quickly in case of an emergency. The wrist strap incorporates a 1 megohm current-limiting resistor, in

GROUNDING WRIST STRAP

a.

series with the

ground cord,

to

protect the

wearer

STATIC-DISSIPATIVE WORK SURFACE

b.

remove

electrostatic

charges

maintain total control

Conductive

flooring

over

ESD,

use

in ESD control

HARD GROUND CONNECTION

d.

Conductive mats

from conductive items Conductive

CONDUCTIVE FLOORING

c.

from electrical shock hazards.

flooring

areas

Make e.

sure

that the

grounding wax or

required. To

heel strap, and conductive shoes. other nonconductive coatings.

accomplished through one or depth sufficient to provide a low resistance path from the to ground are made through a one megohm resistor to hazards by limiting current flow to ground.

need to be checked to make

source

to

a

protect work station personnel from electrical shock

building grounds grounds.

designed

are

of the static control work station is

copper ground work station to ground. All work station connections

NOTE: Some

a

must be free of all

Grounding

on

the work bench surface

the mat.

is used when additional control of ESD is

conductive chairs,

rods driven into moist earth to

more

placed

on

sure

that there is

no

current

looping

from other

nearby

of current is external and not static.

provides a constant flow of positive and negative ions over the charges on nonconductive materials in the air flow path. The use of an ionized air blower, in combination with a static control work station, provides additional protection for ESDS components and equipment. Since it is not always possible to eliminate all static charge accumulators (styrofoam, plastic, etc.) from a work area, the ionized air blower is used to provide additional protection by flooding the work area with balanced negative/positive ionized air. Static charge accumulators should always be kept away from static-free areas, but inadvertent static is hard to control, especially when developed by such common items as clothing, footwear, combs, and pens. An ionized air blower will help control some of this IONIZED AIR BLOWER

The ionized air blower

work station surface to neutralize electrostatic

inadvertent

f.

STATIC DISSIPATIVE SEATING

padded, g.

buildup. Chairs used at ESD

must be covered with static

dissipative

protected

work stations must be conductive, and if

material.

ESDS devices must be transported in approved containers to prevent ESD special containers are made of metal or special conductive plastic. Before static-sensitive components and equipment are removed from a static control work station, they must be packaged in containers that provide at least as much protection as that provided by the work station. Conductive boxes, kit trays, and similar types of approved containers provide complete ESD protection to ESDS components and equipment

CONDUCTIVE CONTAINERS

damage.

These

while in transit. h.

GROUNDING HEEL STRAP

A

grounding

heel strap

can

provide additional ESD protection.

The heel

strap

makes contact with the wearer’s skin at the ankle, and extends to the bottom of footwear to make contact with a conductive mat or conductive flooring. The grounding heel strap can be used in combination with a grounding wrist strap to

~a4

provide maximum ESD protection.

20-02-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i.

ANTISTATIC/CON DUCTIVE CLOTHING

Many types of clothing generate electrostatic charges. To remove personnel should wear outer garments that help dissipate electrostatic charges. Cotton ranks among the best fabrics for antistatic protection. Do not wear synthetic or wool fabrics around ESDS devices, as these fabrics retain electrostatic charges. of this

some

buildup,

work station

PORTABLE STA TIC CONTROL VVORKSTA TION A

portable

used to A a.

provides for static-free handling of ESDS components and equipment during airplane. The typical portable work station is available as a field service kit that is charges before the charges can damage ESDS components and equipment.

static control work station at the

maintenance

operations dissipate electrostatic

typical portable

static control work station consists of the

following

items:

Each person who handles ESDS components and equipment must wear a wrist strap to dissipate bodily electrostatic charges. The wrist strap must fit firm against the skin and should release quickly in case of emergency. The wrist strap incorporates a 1 megohm current-limiting resistor,

GROUNDING WRIST STRAP

grounding

in series with the b.

to

protect the

designed

to

remove

(Ref. Figure 202).

portable

from electrical shock hazards. an

integral part of the portable work station,

and

conductive items when those items contact the mat.

charges from

electrostatic

Ground the portable work station to the airframe or to a common ground ground are made through 1 megohm current-limiting

HARD GROUND CONNECTION

All

wearer

A conductive mat is

STATIC-DISSIPATIVE WORK SURFACE is

c.

ground cord,

work station connections to

resistors to protect maintenance

personnel from

electrical shock hazards.

HUMIDITY AND DUST EFFECTS ON ESDS COMPONENTS AND EQUIPMENT Humidity iS

a

factor in the control of ESD. The lower the

components and equipment. Humidity

humidity,

the greater the chance of

damage

at the work station should be maintained between 30 and 65

Repair of ESDS circuit boards, including replacement of ESDS components, should be performed

to ESDS

percent. in

a

dust-free

envi ro nme nt.

PACKAGING OF ESDS COMPONENTS AND EQUIPMENT All ESDS

components and equipment require special ESD protective packaging. Seal all ESDS packages with label (Ref. Figure 203, Figure 204, Figure 205, Figure 206, Figure 207 and Figure 208).

an

appropriate cautionary

staples

when

sealing any ESDS package.

CAUTION: Do not

use

clips

Do not

use

carbon-filled, conductive bags.

or

Remove ESDS components and

equipment from protective, static-shielded containers only at a static a grounding wrist strap and verifying that ESD producing items are

control work station after attaching not on the static

ESD

dissipative

protective packaging requirements,

Class 1

Package

in

work surface.

unless otherwise defined

by specification,

multi-layer conductive type bags consisting

of

an

shall conform to the

inner and outer

following:

layer of antistatic (surface

of 109 to 1014 ohms per square inch) or static dissipative (surface resistivity of 105 to 109 ohms per square inch) material with a middle layer of conductive material (surface resistivity of 10 ohms or less).

resistivity

Class 2

Package in a static dissipative material possessing specified for Class 1 may also be used.

a

surface

resistivity of

105 to 109 ohms per square

inch. Materials

Page

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Hawker Beechcraft

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Class 3

Package

in

an

antistatic material

possessing

a

surface

Place all ESDS devices in

static

containers. Use antistatic

fill materials. Do not

styrofoam,

or

approved cushioning or

shielding

resistivity of

1 09 to 1014 ohms per square inch.

containers before use

static

packing in shipper’s generating materials, such

normal exterior as

polyethylene,

paper.

packaging is generally pink or blue in color. The material differs from common plastic in that an antistatic compound is incorporated into the material during the manufacturing process. This type of packaging DOES NOT provide static shielding, and is generally used to package instruction sheets, data sheets, and other non-ESDS materials prior to introduction into a static-free environment. All non-ESDS items, that are to enter an ESD work station, require repackaging in antistatic materials. Antistatic

Conductive static

shielding packaging differs from antistatic packaging, in that it has the ability to shield devices, charges. Conductive static shielding packaging is available in the form of bags

contained within, from external static and

rigid

containers.

MARKING OF ESDS COMPONENTS AND EQUIPMENT All ESDS

components and equipment should be marked appropriately with

an

ESDS

symbol (Ref. Figure 205).

symbols (circle with arrows pointing into the circle from equidistant positions or a hand triangle with an angling bar across the triangle) are yellow on a black background or black on background.

NOTE: ESDS

inside of a

a

yellow

package. Mark exterior containers with an (Ref. Figure 208). Apply printed circuit board, assembly cover, directly if door that would ESDS removed. Mark appropriately using decal or access enclosure, devices, equipment expose transfer, stencil, silk screen, or any other method meeting permanent legibility requirements. Mark unit containers with the ESDS caution label ESD caution label

on

marks

the outside of the

to each ESDS

Display ESDS symbols in a prominent package location to alert all personnel to the presence of ESDS devices and equipment. The ESDS symbol should be at least 1/4 inch diameter. ESDS symbols that are attached to circuit boards should contrast with the circuit board base color. Enclosures that contain ESDS circuit boards should be identified

by bright

orange

paint

on

the outer face of the enclosure.

STORA GE AND TRANSIT OF ESDS COMPONENTS AND EQUIPMENT CAUTION: Never

use

ordinary plastic

containers

or

packing

materials when

transporting

ESDS components and

equipment. preparing ESDS devices for shipment, make sure all assemblies through appropriate handling at static controlled work stations.

When ESD

and

equipment

have been

protected against

packages, which have been properly enclosed in protective packages, require proper storage and transfer in conductive static-dissipative, or static-free containers. Shipping information and other instructions, accompanying ESD-protected packages, shall be contained in anti-static materials. ESDS components, that are received in damaged or opened packing containers, are not acceptable, and should be returned for replacement. ESDS

nw

20-02-00May

1/08

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

11

7

2

5

9

lo,

1"

B

I

6

SIATIC

CONTROLLED

WORK

ST~ilDN

1. GROUND CORD ASSEMBLY

6. STATIC CONTROLLED CHAIR

2. STATIC DISSIPATIVE MAT OR

7. CONDUCTIVE CONTAINERS AND

CONDUCTIVE BAGS

WORK BENCH SURFACE

8. HEEL GROUNDING STRAP

3. STATIC DISSIPATIVE/CONDUCTIVE FLOOR OR MAT

9. ANTISTATIC/CONDUCTIVE CLOTHING OR OUTER GARMENT

4. GROUND CONNECTION

’10. SIGN

5. IONIZED AIR BLOWER

ESD CONTROLLED

WORK STATION ’11. SNUG-TO-SKIN PERSONNEL

WRIST STRAP TO GROUND

NOTE

ITEMS MARKED WITH AN

ARE REQUIRED FOR A STATIC CONTROLLED WORK STATION. ALL OTHER ITEMS ARE OPTIONAL, BUT PROVIDE ADDED PROTECTION OR ENHANCE WORKER MOBILITY.

NOTE KEEP STATIC GENERATORS, SUCH AS PLASTIC CUPS, CIGARETTE WRAPPERS,

SURPLUS CLOTHING, HANDBAGS, LUNCH CONTAINERS, PLASTIC BAGS, FOAM PACKING, READING MATERIAL, ETC. AWAY FROM STATIC CONTROL WORK STATIONS. Awl*les

Permanent Static Control Work Station

Figure

Page

20I02-00

201

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1

a~

I’

fl

V

1

2

i. ALLIGATOR CLIP TO

RELIABLE GROUND CONNECTION 2. SNUG-TO-SKIN PERSONNEL

WRIST STRAP 3. STATIC DISSIPATIVE

WORK SURFACE

Apoc4~ee

Permanent Static Control Work Station

Figure

A24

202

20-02-00May

1/08

Hawker BeeChcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION THIS EQUIPMENT CONTAINS DEVICES SENSITIVE TO DAMAGE BY ELECTROSTATIC DISCHARGE (ESD). USE ESD PRECAUTIONARY PROCEDURES WHEN TOUCHING, REMOVING, OR INSERTING PARTS OR ASSEMBLIES.

Permanent Static Control Work Station

Figure

203

CAUTION

ELECTROSTATIC DISCHARGE SENSITIVE ELECTRONIC DEVICES, SPECIAL HANDLING REQUIRED.

Permanent Static Control Work Station

Figure

May

20102100

204

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

t9 MIL-STD-1285 ESD SYMBOL

RS-471 ESD SYMBOL

MIL-STD-129H ESD SYMBOL AW14193

Permanent Static Control Work Station

Figure

A24

205

20-02-00

Hawker BeeChCraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION

ATTENTION

SENSITIVE ELECTRONIC DEVICES. SPECIAL HANDLING REQUIRED. DO NOT OPEN EXCEPT AT AN APPROVED WORK STATION.

CONTENTS STATIC SENSITIVE

HANDLING PRECAUTIONS

(PREFERRED)

REQUIRED

CONTENTS

(ACCEPTABLEI AP014111

Permanent Static Control Work Station

Figure

206

C,3 ATTEI\ITIOI\I CONTENTS STATIC SENSITIVE HANDLING PRECAUTIONS

REQUIRED APOI~IP*

Permanent Static Control Work Station

Figure

May

1/08Page

210

20-02-00

207

nn4

Hawker Beechcraft

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION SENSITIVE 00

NOT

SHIP

ELECTRONIC OR

STORE

DEVICES

NEAR

ELECTROSTATIC,ELECTROMAGNETIC, MAGNETIC, OR RADIOACTIVE

STRONG

FIELDS.

AP014195 Permanent Static Control Work Station

Figure

208

20-02-00May

1/08

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 20-03-00

ELECTRICAL BONDING - DESCRIPTION AND OPERATION The following terms are defined as used in the system description: •

ELECTRICAL BOND: A reliable electrical connection between conductive parts which provides electrical conductivity.

•

ELECTRICAL BONDING: Conductive parts are considered electrically bonded when they are mechanically inter-connected to maintain a common electrical potential.

•

GROUND: A conducting connection, whether intentional or accidental, by which an electrical current or equipment is connected to maintain a common electrical potential.

ELECTRICAL BONDING METHODS There are two basic types of electrical bonding; direct and indirect. Both are accomplished by using mechanical methods to attach the electrical conductors. Bolts, rivets, conductive laminates, flashing and bonding jumpers are commonly used. Whether direct or indirect, all electrical bonding must reflect high maintenance standards to maintain the electrical integrity. Many times, an ill-prepared surface may initially provide sufficient grounding properties, but experience a rapid deterioration in conductivity when corrosion from contaminants or moisture appears on the bonding surface. All bonding surfaces should be free of primer or coatings not compatible with electrical conductance. This includes but is not limited to, all protective films such as anodize, grease, oil, paint, lacquer, or other finishes with high resistance properties. Once the electrical bonding surface is cleaned, and the necessary protective coatings applied, the component is installed and a resistance check is performed to verify continuity of the electrical bond. DIRECT ELECTRICAL BONDING Direct electrical bonds are frequently used for metal-to-metal joints. Before assembly, the joints are treated with a conductive film that prevents corrosion of the bonding surface. Most direct electrical bonds involve the installation of components on aluminum. INDIRECT ELECTRICAL BONDING When direct electrical bonding methods are impractical, indirect bonding methods are used. Indirect electrical bonding is most commonly accomplished by using bonding jumpers to make the desired connection. These flexible metal straps are attached to a prepared metal surface using screws, studs, nuts and washers. The connection is always as short as possible and uses a single jumper. Two bonding jumpers connected in a series is unacceptable, as this can double the resistance between the ground plane and bonded component. Bonding jumpers are also used to electrically connect tubes between joints. CAUTION: Anytime maintenance is performed on or around these flexible bonding jumpers, the wire should not be bent or damaged as this has a tendency to weaken the jumper and reduce its effectiveness. “Waggling” the bonding jumper to see if the end terminals are tight is unacceptable as this may also induce fatigue on the crimped portion of the bonding jumper. Indirect electrical bonding is also used to connect the airplane wire harness shielding terminals to a ground. The tubular braiding attaches to the electrical connectors with clamps and shields the airplane wire harness for its entire length.

A27

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Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTRICAL BONDING OF TUBES All metallic tubes that carry petroleum products or other fluids, including gases, must have a mechanically secure connection to the ground plane for static dissipation. Plumbing sections must be electrically bonded to each other to eliminate a potential electrical charge on the individual segments. Continuity between the plumbing segments is achieved with electrical bonding clamps or jumpers. Electrical bonding clamps, used in some applications, have a wire that contacts the plumbing on either side of the clamp, ensuring continuity across the joint.

ELECTRICAL POWER RETURNS Electrical power returns should be direct with the shortest possible path from the operating equipment to ground when practical. Current return leads 4 AWG or larger, should not be connected directly to the airplane structure, but should be connected to a electrical bonding stud attached to the structure. This method prevents damage should a faulty connection induce high current flow through the connection. A maximum of four wire terminals may be installed on an individual grounding stud. If two or more wires are grounded to an individual stud, each wire must form a mechanically sound connection and meet applicable maximum resistance values. Component case electrical bonding and current return bonding are separate, with the connections made to separate ground studs. As a general rule and precaution, note the power return configuration before removal of a component, and make sure the right configuration is used during installation.

SPECIAL TOOLS AND RECOMMENDED MATERIALS The recommended materials listed in Chart 1 and special tools and equipment listed in Chart 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification may be used subject to availability. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or compliance to the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE REQUIREMENTS OF A SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

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A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 Recommended Materials MATERIALS

SPECIFICATION

PRODUCT

1. Cleaner

A-A-59282

Methyl Propyl Ketone

2. Coating

-

Alodine 1200

MIL-I-46058

Conothane CE-1155

3. Conformal Coating

4. Primer

MIL-P-2337

SUPPLIER Obtain Locally Amchem Products Inc. Spring Garden St. Ambler, PA 19002 Conap Inc. 1405 Buffalo St. Olean, NY 14706

1-1Y-12/1-1H-7

Advanced Coatings & Chemicals 4343 Temple City Blvd. Temple City, CA 91780 Products Research and Chemical Corp. 5426 San Fernando Rd. Glendale, CA 91203

5. Sealant

MIL-S-8802 Type 1

PR1422

6. Cleaner

ASTM-D4080

Trichloroethane

BF Goodrich, 500 S. Main Street Akron, OH 44318

Chart 2 Special Tools and Equipment TOOL NAME 1. Milliohmeter

A27

PART NO. Keithly Model 580A

SUPPLIER Obtain Locally

USE Bonding Testing

20-03-00

Page 3 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

ELECTRICAL BONDING - MAINTENANCE PRACTICES METAL SURFACE PREPARATION AND ELECTRICAL BONDING Surface preparation for electrical bonding requires the complete removal of anodic film, grease, oil, paint, lacquer, metal finishes and other resistive coatings from an area slightly larger than the bonding surface. A clean, smooth, properly contoured electrical bonding surface should be obtained, while removing the least amount of metal possible. NOTE: Do not use emery cloth or iron oxide sandpaper. Use only aluminum oxide or silicon carbide sandpaper. WARNING: When working in an enclosed area with solvents, cleaners or finishes, provide a means of adequate ventilation to prevent a concentration of harmful vapors. The procedures that follow describe preparation of the various types of metal surfaces for electrical bonding. ALUMINUM SURFACES a. Remove any nonsoluble protective finishes or corrosion from an area slightly larger than the area to be bonded (minimum of 0.25 inch) by sanding with fine sandpaper. NOTE: A stainless steel wire brush with a pilot may be used to clean small areas (Ref. Figure 201). b. Clean the bonding surface thoroughly with MPK (Item No.1, Chart 1, 20-03-00) to remove any oils or contaminants. NOTE: Do not touch the bonding surface with bare hands. Body oils or acids may prevent adhesion of the alodine film or cause corrosion. c.

Shake the alodine solution (Item No. 2, Chart 1, 20-03-00) vigorously just prior to application, then apply to the bonding surface with a clean Scotch Brite pad, sponge, brush or cloth.

NOTE: The alodine solution should have an amber color. If the solution is coffee colored it has been contaminated. Repeat the cleaning procedure if contaminated alodine has been applied to the bonding surface. d. Keep the treated area wet with alodine for approximately 3 to 5 minutes until a yellow color develops. Should the alodine not change color, it is an indication that the surface was not properly cleaned. e.

After the alodine has changed color rinse the area with clean, deionized water and gently wipe dry. Touch-up any areas where the alodine does not cover the bonding surface. Care must be taken not to damage the alodine coating as it is still soft when bonding.

NOTE: The bonding surfaces must be assembled within one hour of alodine treatment. Once dried, alodine must be softened before it can be effectively used in bonding. If more than an hour has passed, soften the alodine by applying wet alodine to the dried surface. f.

Install the component being electrically bonded.

g. Seal around the edges of the electrical bond with conformal coat per MIL-I-46058 (Item No. 3, Chart 1, 20-03-00). If the assembly was originally protected by primer, prime the assembly with primer (Item No. 4, Chart 1, 20-03-00) and reapply the original finish as required.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Use of Stainless Steel Wire Brush On Aluminum (With Pilot) Figure 201

Page 202 Feb 1/10

20-03-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL NOTE: The bond area must be refinished within 24 hours of electrical bonding to preserve the integrity of the bond. If the bond involves a structural component, it must be fillet sealed at the edges or seams with sealant (Item No. 5, Chart 1, 20-03-00) to prevent moisture from entering and deteriorating the electrical bonding surfaces. Refer to Chapter 20-08-00 for information on airplane finishes. CORROSION-RESISTANT (CRES) STEEL SURFACES a. Remove all grease and oil from the electrical with cleaner (Item No. 6, Chart 1, 20-03-00) b. Remove all paint or lacquer from the electrical bonding surface with MPK (Item No. 1, Chart 1, 20-03-00). NOTE: Use care not to remove any zinc or cadmium plating from the steel surfaces. c.

Allow the electrical bonding surfaces time to thoroughly dry.

d.

Install the component being electrically bonded.

NOTE: The bond area must be refinished within 24 hours of bonding to preserve the integrity of the bond. If the bond involves a structural component, it must be fillet sealed at the edges or seams with sealer (Item No. 5, Chart 1, 20-03-00) to prevent moisture from entering and deteriorating the electrical bonding surfaces. Refer to Chapter 20-08-00 for information on airplane finishes. STAINLESS STEEL AND TITANIUM SURFACES a. Remove all oil and grease from the electrical bonding surface with cleaner solvent (Item No. 6, Chart 1, 20-03-00). b. Remove all paint or lacquer from the electrical bonding surfaces with MPK (Item No.1, Chart 2, 20-03-00). c.

Lightly sand the electrical bonding surface.

d. Allow the electrical bonding surface to thoroughly dry. e. Use cleaner solvent (Item No. 6, Chart 1, 20-03-00) to clean the electrical bonding surfaces and wipe dry with a clean rag. f.

Install the component being electrically bonded.

g. After a good bond has been verified with the resistance check procedures, it must be fillet sealed at the edges or seams with sealant (Item No. 5, Chart 1, 20-03-00) to prevent moisture from entering and deteriorating the electrical bonding surfaces.

ELECTRICAL BONDING EXAMPLES TYPICAL BLIND GROUND STUD Installation of a typical blind ground stud (Ref. Figure 203) may be accomplished as follows: NOTE: MS35338 lock washers shall be used on all bolted electrical bonding/grounding connections. Their function is to ensure a tight connection with plain or self-locking nuts under conditions where thermal expansion of the screw may occur.

A27

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 Hardware Used With Ground Studs Structure

Screw, Bolt Lock-Nut

Plane Nut

Washer A

Washer B

Washer C&D

Lock Washer E MS35338

Lock Washer F MS35338

Tinned Copper Terminal and Jumper Aluminum Alloys

Cad. Plated Steel

Cad. Plated Steel

Alum. Alloy

Alum. Alloy

Cad. Plated Steel

Cad. Plated Steel

Cad. Plated Steel

Steel, Cadmium Plated

Cad. Plated Steel

Cad. Plated Steel

None

None

Cad. Plated Steel

Cad. Plated Steel

Cad. Plated Steel

Steel, CRES (corrosion resistant)

CRES Steel CRES Steel

None

None

Cad. Plated Steel

Cad. Plated Steel

Cad. Plated Steel

a. The sidewalls of the mounting hole must be clean and free of all chemical films, grease and paint (cleaning of the upper and lower surfaces is not required). b. Make sure the blind ground stud is of sufficient size to distribute the current it will be subjected to. CRES STEEL OR TITANIUM ELECTRICAL BONDING a. Prepare the electrical bonding surfaces (Ref. Figure 204) as outlined under METAL SURFACE PREPARATION AND ELECTRICAL BONDING in this chapter. b. Screw size: Use a No. 10 screw where edge distance will permit. A No. 8 or No. 6 screw may be substituted for the No. 10 screw if necessary to meet edge distance requirements. A Titanium or CRES steel screw must be used. c.

For 100 amp current returns, use a 1/4-inch diameter fastener.

d. For 200 amp current returns, use a 5/16-inch diameter fastener. e. MS35206 cad plated or steel screw used for applications below 330°F. f.

MS35206 CRES steel or titanium screw is used for applications above 330°F.

NOTE: MS35338 lock washers shall be used on all bolted electrical bonding/grounding connections. Their function is to ensure a tight connection with plain or self-locking nuts under conditions where thermal expansion of the screw may occur. g. MS21042L self-locking nut, MS21047L or MS21069L self-locking nutplate should be used to retain the screw. h. No sealing is required where the maximum temperature exceeds 600°F.

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20-03-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Galvanic Table Couples List Figure 202

A27

20-03-00

Page 205 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Typical Blind Ground Stud Figure 203

CRES Steel or Titanium Electrical Bonding Figure 204

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20-03-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Aluminum Electrical Bonding Figure 205

Tubing Clamp to Bonding Jumper Electrical Bond Figure 206

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Bonding Jumper Across Tubing Clamp Electrical Bonding Figure 207

Page 208 Feb 1/10

20-03-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Typical Ground Stud Electrical Bonding Figure 208

Electrical Bonding of Ground Tabs Figure 209

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Electrical Bonding of Equipment Installed With Mounting Feet Figure 210

Electrical Bonding of Equipment Installed With Shock Mounts Figure 211

Page 210 Feb 1/10

20-03-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL ALUMINUM ELECTRICAL BONDING a. Prepare the electrical bonding surfaces (Ref. Figure 205) as outlined under METAL SURFACE PREPARATION AND ELECTRICAL BONDING in this chapter. b. Screw size: Use a No. 10 screw where edge distance will permit. A No. 8 or No. 6 screw may be substituted for the No. 10 screw if necessary to meet edge distance requirements. c.

For 100 amp current returns, use a 1/4-inch diameter fastener.

d. For 200 amp current returns, use a 5/16-inch diameter fastener. NOTE: MS35338 lock washers shall be used on all bolted electrical bonding/grounding connections. Their function is to ensure a tight connection with plain or self-locking nuts under conditions where thermal expansion of the screw may occur. e. MS21042L self-locking nut, MS21047L or MS21069L self-locking nutplate should be used to retain the screw. TUBING CLAMP TO BONDING JUMPER ELECTRICAL BONDING Electrical bonding of tubing clamps (Ref. Figure 206) using bonding jumpers may be accomplished as follows: a. Prepare the electrical bonding surfaces as outlined under METAL SURFACE PREPARATION AND ELECTRICAL BONDING in this chapter. b. MS35206 cad plated steel screw is used below 330°F. c.

MS35206 CRES steel screw is used above 330°F.

d. Clamps of the same tube material may be used to avoid dissimilar metal contact. BONDING JUMPER ACROSS TUBING CLAMP ELECTRICAL BONDING Electrical bonding of tubing segments (Ref. Figure 207) using bonding jumpers across clamps is accomplished as follows: a. Prepare the electrical bonding surfaces as outlined under METAL SURFACE PREPARATION AND ELECTRICAL BONDING in this chapter. b. MS35206 cad plated steel screw is used below 330°F. c.

MS35206 CRES steel screw is used above 330°F.

d. AN960 cad plated washer is installed under the screw head and nut. e. MS21042L self-locking cad plated steel nuts are used. TYPICAL GROUND STUD ELECTRICAL BONDING Electrical bonding of ground studs (Ref. Figure 208) for current returns may be accomplished as follows: a. Screw size: Use a No. 10 screw where edge distance will permit. A No. 8 or No. 6 screw may be substituted for the No. 10 screw if necessary to meet edge distance requirements. b. For 100-amp current returns, use a 1/4-inch diameter fastener.

A27

20-03-00

Page 211 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL c.

For 200-amp current returns, use a 5/16-inch diameter fastener.

NOTE: MS35338 lock washers shall be used on all bolted electrical bonding/grounding connections. Their function is to make a tight connection with plain or self locking nuts under conditions where thermal expansion of the screw may occur. d. Refer to Chart 201 for a listing of compatible hardware used with grounding studs. ELECTRICAL BONDING OF GROUND TABS a. Prepare the electrical bonding surfaces (Ref. Figure 209) as outlined under METAL SURFACE PREPARATION AND ELECTRICAL BONDING in this chapter. Electrical bonding of ground tabs may be accomplished with the following steps. b. NAS1919M04S rivets should be used to attach the ground tab. c.

A minimum of three rivets must be used to attach the ground tab.

NOTE: If it is necessary to remove the tab for any reason, the surface must be recleaned to remove all films.

RESISTANCE TEST Perform a resistance test using a milliohmeter (Item No 1, Chart 2, 20-03-00, 001). Make sure the resistance indicated does not exceed the maximum value (Ref. Chart 202).

Chart 202 Table of Maximum Permissible Resistance Values ITEMS TO BE ELECTRICALLY BONDED

RESISTANCE IN OHMS

Antenna’s, grounded type

0.0025

Cables, coaxial (HF only)

0.0025

Page 212 Feb 1/10

20-03-00

A27

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTROL CABLES AND PULLEYS

DESCRIPTION AND OPERATION

airplane uses carbon steel control cables of multiple wire construction with the number according to the diameter of the cable. The carbon steel wire is helically twisted into strands and about other strands forming the flexible carbon steel cable.

This

of strands

varying

the strands wound

Control cable pressure seals are installed on the control cables where they pass from a pressurized area to a non pressurized area. The pressure seal is molded synthetic rubber and is split to the center permitting removal of pressure seal without disturbing the control cable. A light grease (Item No. i) is packed into the pressure seals to maintain minimum friction between the control cables and pressure seals and improve the cabin pressure retention on the section of the control cables which pass through pressure seals. Refer to

seal. Grease should be visible

Chapter 27-00-00

for information

on

the control cable pressure seals.

RECOM~ENDED I1IIATERIALS

meeting federal, military or supplier specifications are provided for specifically required by Hawker Beechcraft Corporation. Any product conforming to the I used subject to availability. The products included in these charts have been tested and usage by Hawker Beechcraft Corporation, by the supplier or compliance to the applicable I

The recommended materials listed in Chart 1 reference

and

only specification may be approved for aviation specifications. GENERIC are

as

not

OR

LOCALLY

MANUFACTURED

PRODUCTS

WHICH

CONFORM

TO

REQUIREMENTS OF A SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART. the basic number of each It is the

prior

nw

Only

No attempt has been made to update the listing to the latest revision. mechanic to determine the current revision of the applicable specification

specification is listed.

responsibility of the technician or product listed. This can

to usage of the

THE

be done

by contacting

the

supplier of

the

product

to be used.

20-04-00

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 Recommended Materials

Material 1. Lubricant

Specification MIL-G-23827

Product

Supermil

Grease

A722823

Supplier American Oil Co. 165 N. Canal

Chicago,

IL

60606

Royco

27A

Royal

Lubricants Co.

River Road

Hannover,NJ 07936

Aeroshell Grease 7

Shell Oil Co. 1 Shell Plaza

P.O Box 2463

Houston, TX 77001

BP Aero Grease 31B

BP

Trading

Limited

Moore Lane Britannic House

London E.C. 2 2. Corrosion Preventive

MIL-C-16173

Petrotect Grade 2

Compound

Pennsylvania Refining

Co.

1686 Lisbon Road

Cleveland, OH 44104

Braycote

Page

yaM2

1/08

20-04-00

130

Bray Oil Co. Los Angeles,

CA

A24

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTROL CABLES AND PULLEYS

MAINTENANCE PRACTICES

CONTROL CABLE SYSTEM INSPECTION WARNING: When

inspecting control cables, always (Ref. Figure 201). When

a

gloves to

wear

avoid

injury from frayed

control cable is removed from the

corrosion

preventive.

Excess corrosion

airplane, the cable should be dipped preventive may be removed by wiping

or

broken wires

in MIL-C-16173 with

a

clean

cloth.

Inspect a.

the control cable

Inspect the

system

as

follows:

control cables for incorrect

routing, fraying

twisting.

and

Look for interference with adjacent

airplane

structure, equipment, wiring, plumbing and other control cables. b.

Monitor control cable movement for freedom, looseness and full travel.

c.

Visually inspect

d.

Turnbuckles should have the proper thread exposure and be

e.

Locate any control cable broken

all

swaged fittings

for distortion, cracks

or

corroded wires

as

or

broken wires at the

correctly safety

fitting.

wired.

follows:

1.

Inspect the control cables near fairlead pulleys by passing a cloth along the length of the cable. If a found, closely examine the cable to determine the extent of the damage as shown in Figure 201.

2.

Any suspect cable should as shown in Figure 201.

be removed and

NOTE: Individual broken wires when there 3.

are

are no more

placed

acceptable

in

in

a

primary

than three broken wires

snag is

loop position and checked for additional broken wires

and secondary along any three

control cables at random locations foot segment.

Inspect the control cables with broken wires for evidence of corrosion. If necessary, remove the control cable, form it into a loop, and check the center strand for corrosion. Replace any control cable that shows evidence of corrosion.

NOTE: The interior of all turnbuckles should be coated

(Item

No. 1, Chart 1,

20-04-00)

for corrosion

or

filled with MIL-G-23827 grease

protection.

CONTROL CABLE STORAGE Control cables should be stored

straight

or

in

a

coil. When stored in coil form, the coil inside diameter should not be

less than 150 times the control cable diameter,

diameter. Coils should not be flattened, twisted the control cable is installed in its normal

assembly,

~as

control cable storage

or

or

bent in

a

radius of not less than 75 times the control cable

folded

during storage. Storage requirements should apply until airplane. If only a part of the control cable is installed in an the uninstalled portion of the control cable.

in the

position requirements apply

to

20-04-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BROKEN WIRES ARE CABLE IS REMOVED

VISIBLE WHEN AND BENT

NOT BEND T~E CASLE INTO LOOP SMALLER THAN 50 TIMES IEE CABLE DIAMETER

~O

BROKEN WIRES ARE NORMALLY DETECTABLE By WIPING A CLOTH ALONG THE CABLE

A

2aoo-6io-s I

Control Cable With Broken Wires

Typical

Figure

201

CONTROL CABLE PULLEY INSPECTION Inspect all control cable pulleys NOTE: Control cable a.

Inspect

pulleys

all control cable

as

are

follows:

installed

pulleys

for

along

the control cables where

roughness, sharp edges

a

change of

and the presence of

direction is needed.

foreign

material embedded in

the grooves.

I

b.

Inspect

all control cable

pulley bearings

c.

Inspect

all control cable

pulleys

d.

Inspect

the control cable

e.

Control cable

pulleys

pulley

for smooth rotation, freedom from flat spots and

for proper

a

material.

alignment (Ref. Figure 202).

brackets and

which turn for

foreign

guards for damage, misalignment and

short distance must be rotated

periodically

to

looseness.

provide

a new

bearing

surface for the control cable.

ORIGINAL As Received

Page 202 May 1/08

20-04-00

By

ATP

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WEAR MARK r~

XC~SSIVE

CABLE

PULLEY

TENSION

MISALIGNMENT

j P~ILEV

100

LARGE

FOR

CABLE

CABLE

MISALIeNMEN~

i

(-I_

;ROZEN

NORMAL

BEARING

CONOITION 23006

Control Cable

Pulley Wear Figure 202

060

Patterns

ORIGINAL As Received

By

ATP

A24

20-0400

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BEARINGS

DESCRIPTION AND OPERATION

RECOMMENDED MA TERIALS following recommended materials listed as meeting federal, military or supplier specifications are provided for only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification may be used subject to availability. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or compliance to the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE REQUIREMENTS OF A SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used. The

reference

Chart 1 Recommended Materials MATERIALS 1. Cleaner

2. Primer

SPECIFICATION A-A-59282

SUPPLIER

PRODUCT

Methyl Propyl

Locquic

Ketone

Primer "T"

Obtain

locally

Loctite

Corp.

705 N Mountain Rd

Newington CT, 06111 Loctite

3.

Retaining Compound

609

Corp.

705 N Mountain Rd

Newington CT, 06111

A24

20-05-00

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BEARINGS

MAINTENANCE PRACTICES

HYDRAULIC PRESS BEARING REMOVAL a.

Remove the

b.

Place two supports on the hydraulic press table under the should be at least 1/2-inch thicker than the bearing width.

c.

Center be

bearing housing

from the

airplane. bearing housing (Ref. Figure 201).

a bearing removal and installation tool on the bearing outer race. The bearing and approximately 1/8-inch smaller than the outside diameter of the bearing outer race.

CA UTION: The

hydraulic press plunger and bearing removal and installation bearing being removed at all times.

The supports

installation tool should

fool should remain in direct

alignment

with the d.

Align

the

bearing

and the

pressure to force the

bearing removal and installation bearing from the bearing housing.

tool with the

hydraulic

press

plunger

and

apply

MECHANICAL PRESS BEARING REMOVAL a.

Remove the

from the

airplane.

than the

bearing removal socket, with an inner diameter larger than bearing width, on the bearing housing.

c.

Center

bearing

d.

Install

b.

Center

bearing housing

a

a

opposite Install

f.

Tighten

a

through one of (Ref. Figure 201).

washer and bolt

a

e.

removal socket smaller in diameter than the

socket

washer and nut

the nut

on

on

the sockets,

through

the

bearing

bearing

outer

race

and 1/2 inch

deeper

outer race.

the center of the

bearing

and then

through

the

the bolt threads.

the bolt until the pressure is sufficient to release the

bearing

from the

bearing housing.

BEARING HOUSING INSPECTION

Inspect

the

bearing housing

for any grooves, cracks, warpage

or

hole

elongation. The bearing housing bearing

contact surface must be smooth and uniform.

BEARING INSTALLATION USING RETAINING COMPOUND a.

Clean the outer surface of the

bearing

race

with

Methyl Propyl

Ketone

(Item

No. 1, Chart 1,

20-05-00)

and

wipe

dry. CAUTION: When

cleaning bearing surfaces never allow solvent to enter the bearing. Never touch the bearing or bearing housing with bare hands. Use a clean cloth to cover the bearing to prevent contamination after they have been cleaned.

b.

Coat the surfaces where includes the

bearing

a

outer

retaining compound is to be applied with primer (Item No. 2, Chart 1, 20-05-00). This surface, bearing housing mating surface and the bearing housing retention flange if

applicable. CAUTION: Make

sure

that

no

primer is applied

to the

bearing

oil grooves

or

lubrication ports.

20-05-00

PMaaSVe~:Mayl/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR B3O0/B30OC MAINTENANCE MANUAL

NOTE: All cadmium, zinc, corrosion-resistant and anodized steel, proper adhesion of the Allow the

c.

NOTE: The

primer (Item

retaining compound (Item

No. 2, Chart 1,

retaining compound (Item bearing housing.

20-05-00)

to air

No. 3, Chart 1,

No.

including plastic items, 3, Chart 1,20-05-00).

dry

for at least 30 minutes at

20-05-00)

may be

applied before

must be

room

or

primed

to assure

temperature.

after

bearing

installation

in the

Apply a thin coat of the retaining compound (Item No. 3, Chart 1, 20-05-00) to the bearing housing mating surfaces where the primer (Item No. 2, Chart 1,20-05-00) was applied.

I"

and the

bearing

e.

Center the

I

f.

Using the hydraulic or mechanical pressure method (Ref. Figure 201), apply pressure to the bearing until it is firmly seated in the bearing housing. Pressure on the bearing must be applied in direct alignment to the bearing housing for the bearing to seat properly.

I

g.

Apply retaining compound (Item housing.

h.

The

bearing

on

the

retaining compound following:

bearing housing.

must

No. 3, Chart 1,

cure

before the

20-05-00)

bearing

is

to the area between the

bearing

and the

bearing

put into service. Curing may be accomplished with

one

of the 1.

Allow the

and

bearing

temperature for

24 hours without any movement

10x F and maintain that

temperature for 15 minutes only.

to remain at

bearing housing

room

of parts. 2.

1

Heat the

bearing

and

bearing housing

to 275x

Chart 201 RECOMMENDED STAKES FOR ALL BEARINGS NUMBER OF STAKES

BEARING O.D. to 0.734 Inch

4

0.735 Inch to 0.984

6

0.985 Inch to 1.234 Inch

8

Up

BEARING INSTALLATION BY STAKING a.

I

Center the

Using

b.

the

bearing

on

hydraulic

or

firmly seated bearing

I

mechanical pressure method

bearing housing. Pressure properly.

bearing

staked. The inner d.

bearing housing.

in the

to seat

Place the

c.

the

(Ref. Figure 201), apply pressure to the bearing until it is applied in direct alignment to the bearing housing for the

must be

bearing housing on two supports (Ref. Figure 202), bearing race must not touch the supports.

and

if both sides of the

bearing

are

to be

bearing housing was previously staked, the new stakes should be centered between the existing stakes. bearing housing is being used, the stake pattern should be the same as the one on the old bearing housing. If the

if

May

a new

1/0820-05-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: When

a

ring

stake is used, combined total

e.

Pin stakes should be located 0.030

f.

Pin stakes should

only

length

should be 25 percent of the

0.010 inch from the outer diameter of the

be 0.010 to 0.032 inch

deep

to retain

bearings

bearing circumference.

bearing

when the

on

the

bearing housing.

bearing housing

is staked

on

both sides.

g.

The number of

After the

pin

bearing

stakes around

a

bearing housing

has been secured in the

should be

housing by staking airplane.

or

as

indicated

by the

use

(Ref.

of

a

Chart

201).

retaining compound,

relubricate

with the proper lubrication and reinstall in the

CAUTION: If the

bearing

should slip

or move

bearing housing bearing housing.

recleaned. The reinstall in the

REMOVAL

IN~TALLAIIONj

AND TOOL

in the

bearing housing,

the

bearing must be removed and bearing for any damage and

must be recleaned. Examine the

LOAD MUST BE A?PLIED TO OUTER BEARING RACE ONLY.

NL’T WASHER

HOUSING

\Y

SaCXET

BEARING

SUPPORT HOUSING SOCKET

WASHER

SEARING

BOLT APPLY THE INSTALLING OR REMOVAL LOAD TO THE OUTER RACE OF THE ~EARING.

HYDRAULIC

PRESS

METHOD

REMOVAL

OR

INSTALLATION

MECHANICAL

PRESS

TOOL

METHOD 2000-6

0-49

Bearing Removal Figure 201

ORIGINAL As Received ATP

A24

By

20-05-00

Page 203 May 1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OUTER BEARING RACE HOUSINe

.010 .025

TO R

I

´•030

+.OIOINC~

ij

.oio.03~ TOIi\lCH

SUPPORT INNER BEARII\JG RACE

STAKE.

NOTE

DO

NOT

SUPPORT

AGAINST

INNER

BEARING

RACE

DURIN~

STAKING. 2000-610-53

Bearing Staking Figure 202

OR\GINAC As Received By ATP

May

1/08Page

204

20-05-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TUBE AND HOSE ASSEMBLIES AND FITTINGS This

chapter

DESCRIPTION AND OPERATION

contains information to remove, maintain and install hose and tube assemblies and

fittings. Although

all hoses and tubes may not be specifically identified herein, the basic maintenance practices normally apply. Any handling and installation of individual system hoses, tubes and fittings is identified in the appropriate system chapter. The

majority

of tube assemblies used in the

airplane

are

aluminum

NOTE: See for Hoses

are

or

Chapter 29 of the Hawker Beechcraft Corporation, King procedures to install Cryofit fittings for tubing repair. used in

areas

of the

airplane

where

a

flexible line is

steel machine formed

Air Series

more

Component

tubing assemblies. Maintenance Manual

I

suitable for installations and freedom of

movement is necessary.

20-06-00Page

1

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

TUBING AND HOSE ASSEMBLIES AND FITTINGS - MAINTENANCE PRACTICES Observe all WARNINGS, CAUTIONS and NOTES throughout this maintenance manual when performing maintenance, repair or servicing on any fluid or pneumatic operated system. CAUTION: Make sure that systems which operate from fluids or pneumatics under pressure are fully depressurized before opening or disconnecting a tubing or hose. The following list of maintenance practices is provided as an aid for handling, removal, installation and repairing of tubing and hoses. a. Cap or plug all disconnected tubing and hose assembles and fittings immediately to prevent contamination of the system. b. Visually check for cleanliness, evidence of contamination and obstructions prior to reconnection of tube or hose assemblies. c.

Any hose and tube assemblies that did not have protective covers installed must be cleaned and checked for obstruction prior to installation.

d. When connecting tube assemblies, do not force the tube assembly to the installed position. If a mismatch between the male and female fittings should result, see Figure 201 for the allowable mismatch. e. Never stretch a hose to make a connection. f.

The hose material must be compatible with the applicable system fluids. Substitution of a hose material that is not compatible with the system fluid will contaminate the system.

CAUTION: Clamping of tubing or hoses near movable flight controls, control cables, push-pull tubes, bell cranks, mechanical landing gear torque tubes etc. must be attached with steel hardware and must be spaced so that the failure of a single attachment point will not result in interference with any of these movable components (Ref. Figure 203). The minimum separation between any tubing or hoses and movable components must be at least 0.5 inches when the tubing or hoses are displaced by light hand pressure in the direction of the movable component(s). There must be a positive separation between any tubing or hoses and non electrical components, structures or non movable components (Ref. Figure 203). The minimum separation between any tubing or hoses carrying flammable fluids and wire harnesses if they cross is 0.5 inches and 2.0 inches if running parallel. g. When installing hoses or tubes make sure that there is clearance between the hoses, tubes, nuts, clamps, and other structures or components. Pay particular attention to make sure there is clearance between control cables, push-pull tubes, bell cranks, mechanical landing gear torque tubes, etc.

A28

20-06-00

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Tubing Installation Mismatch Figure 201

LEAKAGE AT THREAD COUPLING If leakage appears at a coupling, do not attempt to correct it by over tightening the fittings. Disassemble the coupling and check the fittings for nicks, burrs and/or foreign matter. Use new fittings to correct the problem.

Page 202 May 1/10

20-06-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TUBE MANUFACTURING The new tube must be manufactured from the correct material to the specific application for which it is to be used. Before cutting the tube to length, make sure it is long enough to make all bends and any forming that must be made at the ends. Prepare the tubing ends to match the connecting fittings. All bends must be made with the appropriate bending tool and the limits specified (Ref. Figure 202 and Chart 201).

Tube Bending Figure 202

A28

20-06-00

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 Tubing Bending Limits Tube Outside Diameter

Recommended Bend Radii

(D)

3D

Additional Bend Radii

4D

6D

Inch

Millimeter

Inch

Millimeter

Inch

Millimeter

Inch

Millimeter

1/8

3.175

.375

9.525

.500

12.700

.750

19.050

3/16

4.762

.563

14.286

.750

19.048

1.125

28.572

1/4

6.350

.750

19.050

1.000

25.400

1.500

38.100

5/16

7.937

.938

23.811

1.250

31.748

1.875

47.622

3/8

9.525

1.125

28.575

1.500

38.100

2.250

57.150

7/16

11.112

1.312

33.336

1.750

44.448

2.625

66.672

1/2

12.700

1.500

38.100

2.000

50.800

3.000

76.200

5/8

15.875

1.875

47.625

2.500

63.500

3.750

95.250

3/4

19.050

2.250

57.150

3.000

79.200

4.500

114.300

7/8

22.225

2.625

66.675

3.500

88.900

5.250

133.350

1

25.400

3.000

76.200

4.000

101.600

6.000

152.400

1 1/8

28.575

3.375

85.725

4.500

114.300

6.750

171.450

1 1/4

31.750

3.750

95.250

5.000

127.000

7.500

190.500

1 3/8

34.925

4.125

104.775

5.500

139.700

8.250

209.550

1 1/2

38.100

4.500

114.300

6.000

152.400

9.000

228.600

1 5/8

41.275

4.875

123.825

6.500

165.100

9.750

247.650

1 3/4

44.450

5.250

133.350

7.000

177.800

10.500

266.700

1 7/8

47.625

5.625

142.875

7.500

189.500

11.250

285.750

2

50.800

6.000

152.400

8.000

203.200

12.000

304.800

2 1/4

57.150

6.750

171.450

9.000

228.600

13.500

342.900

2 1/2

63.500

7.500

190.500

10.000

254.000

15.000

381.000

3

76.200

9.000

228.600

12.000

304.800

18.000

457.200

Page 204 May 1/10

20-06-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

REMOVAL OF TUBE AND HOSE ASSEMBLIES Tube and hose assemblies may be removed as follows: a. Relieve all system pressure. b. Disconnect both ends of the hose or tube assembly and immediately cap or plug the tube or hose ends and fittings. c.

Remove all clamps securing the hose or tube assembly.

d. Remove the tube or hose assembly and tag identify both ends to aid in reinstallation.

HOSE ASSEMBLY INSTALLATION Hose assemblies may be installed as follows: NOTE: If a new hose assembly is to be installed, the hose assembly must be clean, the correct length, clear of obstructions and material compatible with the system fluid. a. Observe the maintenance practices outlined under the heading TUBE AND HOSE ASSEMBLIES AND FITTINGS - MAINTENANCE PRACTICES in this chapter. b. Connect the "B" nuts of the hose assembly to the proper fittings. c.

Torque the "B" nuts to the fittings using the torque specified in Chart 202.

d. After torquing the "B" nuts, inspect the hose to ensure that the hose is not under tension and that no indication of twisting is present. e. Inspect the hose for proper length. f.

Inspect the hose for freedom to expand and contract.

g. Inspect the hose for clearance to all structure. If inadequate clearance exists between the hose and structure, protection must be provided for the hose to prevent damage from chafing.

A28

20-06-00

Page 205 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 202 Flared Fitting Torque Chart (Inch-Pounds)

Hose Size

Tubing O.D. (Inches)

Aluminum Tubing Flare Min. Max

Steel Tubing Flare Min. Max

Aluminum Tubing Flareless Min. Max

Steel Tubing Flareless Min. Max

Oxygen Line Fitting (Aluminum) Min. Max

Hose End Fitting Min. Max

-3

3/16

---- ----

90 100

75 90

90 100

---- ----

70 100

-4

1/4

40 65

135 150

80 100

135 150

---- ----

70 120

-5

5/16

60 80

180 200

100 130

180 120

100 125

85 180

-6

3/8

75 125

270 300

100 130

270 300

---- ----

100 250

-8

1/2

150 250

450 500

200 240

450 500

---- ----

210 420

-10

5/8

200 350

700 800

360 400

700 800

---- ----

300 480

-12

3/4

300 500

1100 1150

390 430

1100 1150

---- ----

500 850

-16

1

500 700

1200 1400

600 900

1200 1400

---- ----

700 1150

-20

1 1/4

600 900

1300 1450

600 900

1300 1450

---- ----

---- ----

-24

1 1/2

600 900

1350 1500

600 900

1350 1500

---- ----

---- ----

TUBE INSTALLATION NOTE: If a new hose assembly is to be installed, the hose assembly must be clean, the correct length, clear of obstructions and material compatible with the system fluid. a. Observe the maintenance practices outlined under the heading TUBE AND HOSE ASSEMBLIES AND FITTINGS - MAINTENANCE PRACTICES in this chapter. b. Inspect the tube for damage, particularly at tube ends, fittings, and bends. Damaged tube assemblies should be replaced or repaired. c.

Make certain that the fittings are properly installed before connection of the tube assembly.

d. Check alignment and fit of the tube assembly as follows before installation: 1. Place the tube assembly in the proper position and tighten one coupling nut at one end of the tube assembly. 2. The opposite end of the tube must be within two degrees of parallel with the fitting as shown in Figure 201. 3. The free tubing end must be aligned within 1/32 inch of the fitting per every 10 inches of tube length as shown in Figure 201. 4. The free end of the tube must match the fitting cone lengthwise within 1/32 inch per every 10 inches of tube length as shown in Figure 201. e. If necessary, apply the proper antiseize compound to fittings. f.

Install the tube assembly on the fittings and tighten the "B" nuts to the torque values specified in Chart 201.

Page 206 May 1/10

20-06-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FLUID LINE FITTING INSTALLATION Fluid line fittings may be installed as follows: a. Lubricate the male threads of the fitting, backup ring and packing sparingly with the system fluid or petrolatum (AN-P-51, Vaseline). b. Install the nut (AN6289) on the fitting until the nut is clear of the thread relief. c.

Install the teflon backup ring in the counterbore of the nut.

d. Install the packing (O-ring) on the thread relief. NOTE: The packing must be compatible with the system fluid. e. Turn the nut down until the packing is pushed firmly against the lower threaded section of the fitting. f.

Install the fitting into the boss with the nut turning with the fitting until the packing contacts the boss.

NOTE: This point can be detected by a sudden increase in torque. g. Holding the nut with a wrench to prevent it from turning, rotate the fitting in an additional 1 1/2 turns. Position the fitting in the proper direction by turning in no more than one additional turn. h. Holding the fitting, turn the nut down tightly against the boss. Slight extrusion of the ring around the backup ring is acceptable.

NON POSITIONING TYPE FITTING INSTALLATION Nonpositioning type fittings may be installed as follows: a. Lubricate the packing with the system fluid or petrolatum (AN-P-51, Vaseline). b. Install the packing in the fitting thread relief. c.

Thread the fitting into the boss until it bottoms tightly on the boss.

d. Tighten the fitting to the specified torque value.

PIPE THREAD FITTING INSTALLATION Pipe thread fittings may be installed as follows: a. Apply teflon tape to the threads as follows: 1. Start tape at or close to narrow end of threads. 2. Wrap the tape around the fitting in the direction of the threads. Wrap clockwise for right hand threaded fittings. Wrap counterclockwise for left hand threaded fittings. 3. Apply tension to the tape to conform the tape to the shape of the threads. 4. The tape should overlap the previous wrap of tape up to one-half inch to seal pipe thread fittings up to two inches in diameter. b. Thread the fitting into the boss and tighten until it bottoms tightly on the boss.

A28

20-06-00

Page 207 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TUBE DAMAGE LIMITS NOTE: Nicks and scratches not exceeding the following limitations may be repaired by polishing out the damaged area, using fine grade of emery cloth and oil. Finish polishing with crocus cloth and oil. Flush and clean all grit from line assembly. a. Replace steel tubes which have nicks or scratches deeper than 10 percent of tubing wall thickness. b. Replace any aluminum tube which has nicks or scratches deeper than 20 percent of the tube wall thickness. Replace any tubes which have dents deeper than 5 percent of the tube outside diameter.

TUBING, HOSES AND FITTINGS - INSPECTION/CHECK It is essential that all areas of the airplane be periodically inspected for potential chafing between flammable fluidcarrying tubes/hoses and other components, structures or electrical wire harnesses. Information for the inspection of the electrical wiring and the criteria for the repair or replacement of the electrical wiring is contained in FAA Advisory Circular AC 43. 13-1B or subsequent. a. Check the condition, attachment method and security of tubing and hoses. Make sure there is clearance between tubing, hoses and other components and structures. CAUTION: Clamping of tubing or hoses near movable flight controls, control cables, push-pull tubes, bell cranks, mechanical landing gear torque tubes etc. must be attached with steel hardware and must be spaced so that the failure of a single attachment point will not result in interference with any of these movable components. The minimum separation between any tubing or hoses and movable components must be at least 0.5 inches when the tubing or hoses are displaced by light hand pressure in the direction of the movable component(s). There must be a positive separation between any tubing or hoses and non electrical components, structures or non movable components. The minimum separation between any tubing or hoses carrying flammable fluids and wire harnesses if they cross is 0.5 inches and 2.0 inches if running parallel. 1. Make sure the stand-off clearance between tubing, hoses, wire harnesses, nuts, clamps and structural components is a minimum of 0.5 inches. For acceptable stand-off methods refer to Figure 203. b. Make sure the inspected area is clean and free from all foreign objects.

Page 208 May 1/10

20-06-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PLUMBING LINE

AN-3A BOLT NYLON TUBE (MAXIMUM LENGTH 2 INCHES) WIRE HARNESS

NAS1149F0322P WASHER

MS21919WDG CLAMP

MS3367 TIE STRAP

STAND-OFF METHOD 2 MS21919WDG CLAMP AN743-12 ANGLE BRACKET

NAS43DD3 SPACER (MAXIMUM LENGTH 2 INCHES)

MS21919WDG CLAMP

MS21043-3 NUT MS21919WDG CLAMP

STAND-OFF METHOD 1

STAND-OFF METHOD 3 FL20B 093575AA.AI

Typical Stand-off Methods Figure 203

A28

20-06-00

Page 209 May 1/10

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LOCKING DEVICES

DESCRIPTION AND OPERATION

Except for specific instructions required to satisfy a certain application, the following procedures methods used to install various locking devices used in conjunction with bolts, screws and nuts.

are

standard

SELF-LOCKING NUTS Where

self-locking

nuts are

used, the following procedure applies:

a.

For

b.

Add the above torque to the value detailed in the as the total applied torque.

self-locking nuts,

note the

torque necessary

to turn the

self-locking

assembly

nut before the

instruction for the

self-locking

application.

nut is seated.

Use this

new

value

SLOTTED, STEEL LOCKNUTS (PREVAILING TORQUE TYPE) Effective

of slotted, steel locknuts

locking

on

bolts

requires

chamfered section of the locknut ID does not exert force

protrude

on

the full engagement of all locknut threads. The

the bolt. It is not necessary that the bolt be flush with

or

from the outer face of the locknut.

LOCKWIRE AND COTTER PIN REQUIREMENTS When

tightening

a

castellated nut for cotter

pin installation, alignment of the

slot must be obtained without

exceeding

torque. If this is not possible, replace the nut. After tightening the nut to the recommended torque, the nut must not be loosened to permit insertion of a cotter pin. If the slot in the nut or lockwire hole in the bolt or screw

the maximum

correctly aligned at the minimum torque value given, the nut, screw or bolt should be further tightened to the alignment position, but the maximum torque value given must not be exceeded. Should alignment still be impossible without exceeding the maximum torque, back off the nut one-half turn and retorque. is not next

Lockwire and cotter

bolts and studs for lockwire

bushing

unless otherwise

pins

must never be reused. All lockwire and cotter

and

pins

snugly into drilled holes in the adjacent boss or casing. Never

must fit

must be lockwired to the

locking purposes. Bushings plugs plug. Cotter pins should be installed so that the head fits into the slot of the castellated nut and, specified, one end of the pin should be bent over the stud or bolt and the other end flat against the

to

flat of the nut.

20-07-00

May

1/08Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LOCKING DEVICES

MAINTENANCE PRACTICES

LOCKWIRE INSTALLA TION PROCEDURES NOTE:

Figure

Observe the

a typical lockwire procedure. Although there are numerous iockwire operations airplane, practically all are derived from the basic examples shown in Figure 202.

201 illustrates

performed

on

the

following guidelines

a.

New lockwire must be used.

b.

Use the

same

when

installing

on

the

lockwire:

employed during the initial assembly. Except where airplane power plant is heat and corrosion resistant steel wire of

type and diameter of lockwire

otherwise specified, the wire used

I

that

as

0.025-inch diameter. c.

d.

Lockwire must be

g.

tendency

Lockwire must

pulled f.

after installation to prevent failure due to

Lockwire must be installed in the natural

e.

tight

never

taut when

a manner

that tends to

safety

a

Internal

wiring

and

keep

a

or

vibration.

part locked in place, thus counteracting

of the part to loosen. be overstressed. It will break under vibrations if twisted too

being

tightly.

The lockwire shall be

twisted, but shall have minimum tension, if any, when secured.

Lockwire ends must be bent toward the engine,

present

tighten

rubbing

hazard

or

or

structure, to avoid sharp

or

projecting

ends which

might

vibrate in the air stream.

must not cross over or obstruct a flow passage when an alternate method can be used.

LOCKWIRE HOLE ALIGNMENT Check the units to be lockwired to make

properly positioned units be in the

sure

that

they

have been

in relation to each other. When there

are

two

correctly torqued

or more

and that the

wiring

holes

are

units, it is desirable that the holes in the

relationship to each other. Never overtorque or loosen units to obtain proper alignment of the possible to align the wiring holes when the units are torqued within the specified limits. However, if it is impossible to obtain a proper alignment of the holes without either over or undertorquing, select another unit which will permit proper alignment within the specified torque limits. same

holes. It should be

LOCKWIRE TWISTING To

prevent mutilation of the twisted section of the wire when using pliers, grasp the wire at the ends or at a point that will not be twisted. Lockwire must not be nicked, kinked or mutilated. Never twist the wire ends off with the pliers and, when cutting off ends, leave at least three complete twists after the loop, exercising extreme care to prevent the wire ends from

falling

into

areas

where

they might

create a hazard

or

damage.

The

strength

of lockwire holes is

marginal.

nas

20-07-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

THE

HOLES.

THE

THROUGH

WHISH

LIES

WIRE WIRE

TWELVE

END

THE

OF

PULL

AN~

THE

PAIR

A

O; T’iE

TIGHT.

BRING BOLT

ENU

FREE

THE

AROUND

WIRE

THE

HOLE

POSITIONS.

WITH

"LIERS

THE

BEiWEEN

AND

NINE

THE

2RASP

INSERT

SECOND

BOLT.

3’CLOCK

CAGE

FOINiS

WHLC

TOWARD

POSITION

UPPERMOST

THE

INSERT

WIRE.

5

IN

HEAO

GF

THE

A

CO~NTERCLDCKWISE AND UNDER

PROPER

WIRE.

’ROTRUOING

END

TEE FROM

BOLT

THE

TWIST

THE

WIRE

HOLE. IN

A

CCUNTERCLOCXWISE DIRECTION.

UPPER END WIRE AND BEND IT AROUND THE HEAO OF THE BOLT. i~EN UNDER THE OTHER END OF THE WIRE 6~ \ISURE WIRE IS iIGHS AROUND HEAD. WRAP OF

THE WIRE BEYOND TWISTED PORTION AND TWIST THE WIRE ENDS COUNTERCLOCKWISE UNTIL TIGHT. GRASP

THE

DURING

WIRE UNTIL WIRE IS JUST SHORT OF HOLE IN THE SECOND BOLI TWIST

WIRE UNDER IWIST lN A CLOCKWISE DIRECTION ?JNTTL THE WIRE ‘i S WHEN TIGHTENED TIGHT. THE WIRE SHALL HAVE APPROXIMATELY 7 TO iO TWISTS PER INCH.

THE

FINAL

TWISTING MOTION OF THE PLIERS. BEND THE WIRE DOWN AND UNDER TH~ HEAD OF THE ~OLT.

KEEPING

TENSION.

WIRE EXCESSCUIIERS

2UT OFF WITH CIAGONAL

2003-60L- 18

RH Thread

Lockwiring Figure 201

Procedure

ORIGINAL Page 202 May 1/08

20I07-00

As Received ~TP

By A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXAMPLE

3

EXAMPLE

EXA~PLE

EXA~PLE

4

FILLISTER HEAD SCREWS, SOUARE HEAD PLUGS, AND OTHER SIMILAR WIRED SO THAT THE LOOSENING TENDENCY OF EITHER PART IS THE DIRECTION COUNTERACTED BY THE TIGHTENIN2 OF THE OTHER PART. OF TWIST FROM THE SECOND TO THE THIRD UNIT IS COUNTERCLOCKWISE TO THE WIRE XEEP THE LOOP IN POSITION AGAINST THE HEAD OF THE BOLT. ENTERING THE HOLE IN THE THIRD UNIT WILL BE THE LOWER WIRE kND BY ~AKING k COU~TER3LOCKWISE TWIST AFTER IT LEAVES THE HOLE, TSE LCOP WILL BE SECURED IN PLACE AROUND THE HEAD O’ THAT ~OLT. BOLTS PARTS

ARE

i 9a

s EXAMPLE

5

EXAMPLE

EXAMPLE

6

7

EXAMPLE

8

WIRE MAY BE WRAPPED METHODS FOR WIRING; VARIOUS STANDARD ITEMS. OVER THE UNIT RATHER THAN AROUND IT WHEN WIRING ZASTELLATED NUTS OR ON OTHER ITEMS WHEN THERE iS A CLEARANCE PROBLEM.

r:

a EXAMPLE IHE

METHOD IN

BOLTS NOTE

THAT

FOR

EXAMPLE

9 WIRING

DIFFERENT PLANES. WIRE SHOULD

ALWAYS

BE APPLIED SO TENSION IS IN THE TIGHTENING DIRECTION. THAT

EXAMPLE

10

HOLLOW HEAD PLUGS WIRED WITH THE TAB BENT INSIDE THE HOLE TO AVOID SNAGS AND POSSIBLE INJURY TO

CORRECT

ii

APPLICATION

SINGLE WIRE CLOSELY SPACED GROUP. OF

10 MULTIPLE

~000-60L19

PERSONNEL

RH Thread

Lockwiring Examples Figure 202

ORIGINAL By

As Received ATP

A24

20-07-00

Page

203Mayl/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

COTTER PIN INSTALLA TION Use the

following

Install

a.

pins for

the desired

application:

newcotterpins.

Select cotter

b.

to select and install cotter

pin

material in accordance with temperature,

atmosphere

and service limitations

as

specified

in

Chart 201.

I

When nuts

c.

are

to be secured to a fastener with cotter

applicable specified or selected torque range, until the nut slot aligns with the fastener hole. Castellated nuts installed

d.

bent

parallel

on

fasteners

are

pins, tighten the fastener to the low side (minimum) of the specified, and if necessary, continue tightening Maximum torque must never be exceeded.

unless otherwise

safetied with cotter

to the axis of the fastener. The alternate

the axis of the

fastener, may be used when the

preferred method is with the cotter pin pin is mounted perpendicular to method is apt to become a snag. preferred

pins.

The

method, where the cotter

cotter

pin

in the

If 50 percent or more of the cotter pin diameter is above the nut castellation, a washer should be used under the a shorter fastener should be installed. A maximum of two washers may be permitted under a nut.

e.

nut or

f.

Use the largest application of a

nominal diameter cotter cotter

pin

hole and slot size for the cotter Install the cotter

g.

pin

pin head firmly

fastener shank. Bend the cotter

i.

if the fastener hole size is less than the

pin prongs against the

so

that the cotter

pin

pin eye at right angles to the head and upper prong are firmly seated against

nut.

pin or rod end applications, install the cotter pin with the axis of the eye parallel to the shank of pin or rod end. Bend the prongs around the shank of the clevis pin or rod end (Ref. Figure 203).

Cadmium or

required

in the slot of the nut with the axis of the cotter

In clevis

clevis

I

permitted

pin.

the fastener and the lower prong h.

listed in MS24665 that the hole and slots will accommodate. No

to any nut or fastener is

plated cotter pins synthetic lubricants.

should not be used in

applications bringing

them in contact with fuel,

the

hydraulic fluid

Chart 201 COTTER PIN INFORMATION MATERIAL

TEMPERATURE

MS24665 Cotter Pins

Ambient

Carbon Steel

up to 460" F

Temperature

SERVICE

Normal atmosphere cotter pins, contacting cadmium plated bolts

or

nuts.

MS24665 Cotter Pins

Ambient

Corrosion-Resistant Steel

up to 800" F

Temperature

Non-magnetic requirements cotter pins, contacting corrosion-resistant steel bolts

or

nuts in a corrosive

atmosphere.

May

1/0820-07-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ORIGINAL By

As Received C;TP

TO PROV-)E C~EARANCE PRONG ~AY eE CUT HERE

PRONG ~UST SU~FICIENT AS SHOWN.

BE OF LENGT~

FRON~S MUST BE OF SUFFICIENT LENGTH r0 EXTEND 90’ BEYOND HOLE AS SHOWN.

CA’TELLATED NUT ON BOLT PREFERRED MEIHOD

PIN

APPLICATION 2000-61 046

Cotter Pin Installation

Figure

(TAB AND CUP TYPES) INSTALLATION

KEYWASHERS The terms

203

keywasher, tabwasher and cupwasher are interchangeable. following when installing new keywashers, tabwashers and cupwashers:

Observe the a.

Always

b.

When

use new

washers for each

assembly.

bending or setting the washer tabs, do not use sharp pointed tools. Use of such tools can lead to subsequent failure of the locking tabs which, upon becoming detached, can cause extensive damage.

RETAINING RINGS

(SPIROLEX, ETC.) INSTALLATION

must be installed

a.

Retaining rings

b.

Internal

c.

External type

d.

After installation, make

rings

must not be

rings

using approved retaining ring pliers.

compressed beyond

must be

sure

the

expanded only enough each

retaining ring

is

point

where ends of the

ring

to allow installation without

completely

meet.

becoming

bent.

seated in its groove, without looseness

or

distortion.

A24

20-07-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TURNBUCKLE LOCK CLIP INSTALLA TION NOTE: The turnbuckle barrel must be filled with MIL-G-23827 grease before the threaded terminals into the turnbuckle barrel.

I Safety

turnbuckles with lock

clips (Ref. Figure 204)

a.

New lock

b.

Screw both threaded terminals

clips

screwed

follows:

must be used.

of either terminal is c.

as

are

exposed

an

equal

outside the

distance into the turnbuckle barrel

so

that

no more

than three threads

body.

adjust the terminals until the cable is to the proper tension, adjust the turnbuckle to the locking position (groove on terminals and slot indicator notch on barrel should be aligned) and insert the end of the locking clip into the terminal and turnbuckle barrel end until the "U" curved end of the locking clip is over the hole If necessary,

in the center of the turnbuckle barrel.

locking clip

in the hole in the center of the turnbuckle barrel to its full extent.

d.

Press the

e.

The curved end of the

f.

To check proper

g.

Repeat

h.

Both locking clips may be inserted in the the turnbuckle barrel center hole.

locking clip

will latch in the hole in the center of the turnbuckle barrel.

seating of the locking clip, attempt to remove the pressed "U" end from the turnbuckle barrel using fingers only. Do not use a tool to check the lock clip installation as the locking clip could be distorted.

May

1/08Page

206

the

previous steps

for installation of the

20-07-00

same

locking clip

on

the

opposite

end of the turnbuckle barrel.

side of the turnbuckle barrel center hole

or

in

opposite

sides of

A24

Hawker Beechcraft

Corporation

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

OPIGINAL

As EODK

HOOK

Received By AfP

LI?

IOCKING

I

SWkGED

LGDP

I

CLI"

ii

I

TURNGUCKLE BARREL

SWAGED IE~MINAL

2000-610-L7

furnbuckle

A24

Safetying Using Figure 204

Lock

Clips

20-07-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRPLANE FINISH CARE

DESCRIPTION AND OPERATION

CAUTION: Clean the windshields and windows

as

instructed in CLEANING WINDSHIELDS and CLEANING

I

PLASTIC WINDOWS, Chapter 56-00-00. Windshields and windows must be cleaned using approved cleaners. If approved cleaners are not used, the result could necessitate windshield and window

replacement.

RECOMMENDED MA TERIALS The recommended materials listed in Chart 1

as meeting federal, military or supplier specifications are provided for only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification may be used subject to availability. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or compliance to the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE REQUIREMENTS OF A SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

reference

Chart 1 Recommended Materials

MATERIAL 1.

Solvent

2.

Solvent

SPECIFICATION ASTM D4080

PRODUCT

SUPPLIER

Acetone

Obtain

Locally

Methyl Propyl

Obtain

Locally

Obtain

Locally

Obtain

Locally

Ketone 3.

Solvent

4.

Acid

5.

BasePrimer

TT-N-95

Etching

Primer

Type

II

Aliphatic Naphtha

MIL-C-8514 EX2016G

Sherwin Williams P.O. Box 2153 16116 East 13th Street

Wichita, Ks 67201 6.

Catalyst

T607

Sherwin Williams P.O. Box 2153 16116 East 13th Street

Wichita, Ks 67201 7.

Urethane Primer

38-Y-3

Sherwin Williams P.O. Box 2153 16116 East 13th Street

Wichita, Ks 8.

Cleaner

9.

Anti-Static

Coating

Lacquer

Thinner

528-104

or

Obtain

528-306

67201

Locally

DeSoto Inc. Southwestern Plant Forrest Ln. and Shiloh Rd. P.O. Box 401268

Garland, TX 75042

A25

20-08-00

Feb

1/09Pagel

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 Recommended Materials MATERIAL 10.

SPECIFICATION

(Continued)

PRODUCT

Lord Chemical Products

Elastomeric

WhiteBase

Polyurethane

SUPPLIER

M-213

Group

P.O. Box 10038 2000 W. Grandview Blvd.

Erie, PA 16154 11.

Curing

Lord Chemical Products

Elastomeric

Solution

Polyurethane

M-210

Group

P.O. Box 10038 2000 W. Grandview Blvd.

Erie, PA 16154

13.

Obtain

EC750

12. Sealer

Oakite Products Inc.

Oakite No. 6

Soap (Paste form)

Locally

Berkeley Hts., 14.

Sanding

Ameritex Chemical And

F900 Primer

Surfacer

N.J. 07922

Coatings

Companylnc.

Surfacer

801 ELee

INing, 15. Solvent

A-A-59107

Toluol

TX 75060

Obtain

(toluene)

Locally

(Supersedes TT-T-548) 16.

Isopropyl Alcohol

MIL-23377

17. Primer

Obtain Locally

TT-I-735

Primer, Epoxy

Sherwin Williams P.O. Box 2153

Polyamide

16116 East 131h Street

Wichita, Ks 67201 18. Urethane Paint

6160 Matterhorn

U.S. Paint,

Lacquer

and Chemical

Co.

White

St. Louis, MO 19.

Epoxy

Adhesive

Dexter

EA9309NA

Hysol Aerospace

Inc.

P.O. Box 312 2850 Willow Pass Road

Pittsburg, CA 20. Adhesive Promoter

21.Tape

and Residue

Remover

Obtain

3m86

35975/60-4300-

5079-3, 16

oz.

35976/60-4300-

94565

Locally

3M Center

St. Paul, MN 55144-1000 www.3m.com

5084-3, Gallon 22. Sealant

PR-1425B-1/2 PR-14258-2

(Alt)

PRC-DeSoto 5454 San Fernando Road

P.O. Box 1800

Glendale, CA 91209 www.ppg.com

Feb

1/0920-08-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 Recommended Materials

SUPPLIER

PRODUCT

SPECIFICATION

MATERIAL

(Continued)

3M Center

DP-190

23. Adhesive

St. Paul, MN 55144-1000 www.3m.com

3M Center

86-A

24. Adhesion Promoter

St. Paul, MN 55144-1000 www.3m.com

3M Center

ES2000

25. Adhesive

St. Paul, MN 55144-1000 www.3m.com

PRC-DeSoto

PR-1440B-1/2

SAE-AMS-S-8802

26. Sealant

5454 San Fernando Road P.O. Box 1800

Glendale, CA 91209 www.ppg.corn NOTE

Any

alternate

products

certified to

SAE-AMS-S-8802 requirements

28. Alodine

acceptable.

23T3-90/PC216

27. Abrasion Resistant

Polyurethane Spray Coating

are

I

I

Akzo Nobel

I

www.akzonobel.com

Henkel Surface

Technologies Stephenson Highway Madison Heights, MI 48071

Alodine 1132

Touch-N-Prep

I

32100

29. Solvent

I

I Desoclean CA

120

PRC-DeSoto 5454 San Fernando Road P.O. Box 1800

Glendale, CA

91209

www.ppg.com 30. Urethane Paint

SV-S5PMA

Stripper

Napier Environmental Technologies 720 Eaten Way Delta, BC

www.napiere.com Turco 6776/6813

Solvent Kleene 119 Foster St.

Peabody,

Bldg.

#6

MA01960

www.solventkleene.com

D-Zolve Gl 15-32

Solvent Kleene 119 Foster St.

Peabody,

Bldg.

#6

MA01960

www.solventkleene.com

A25

20-08-00

Feb

1/09Page

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 Recommended Materials

31. Filler

PRODUCT

SPECIFICATION

MATERIAL

(Continued) SUPPLIER

Henkel Surface

EA960

Putty

Technologies Stephenson Highway Madison Heights, MI 48071

32100

Akzo Nobel

467-9

www.akzonobelcorn 369-11

Mankiewicz

Coatings

LLC

8 Carlisle Drive

Simpsonville, SC

29681

www.mankiewics.de/kontakt 32. Aluminum

3M Center

FoilTape

St. Paul, MN 55144-1000 www.3m.com

I

34. Promoter

Obtain

Grade A, Type II

33. Kraft Barrier Material

I CA 100

Locally

PRC-DeSoto 5454 San Fernando Road

P.O. Box 1800

Glendale, CA

91209

www. ppg.com

35.

CA 1900

Blending Solvent

PRC-DeSoto

5454 San Fernando Road P.O.Box1800

Glendale, CA 91209 www.ppg.com 36.

396

Tape

1

I

3M Center St. Paul, MN 55144-1000 www.3m.com

37. Ethanol Solvent

I

I MIL-C-81706 per MIL-C-5541

38. Chemical Conversion

Coating

I

Henkel Surface

1200S, 1201, 1203

32100

600

1

Technology Stephenson Highway Madison Heights, M148071

1

5454 San Fernando Road

CA7630

Epoxy Sanding

Surfacer

I

I

Locally

Alodine 1200,

or

39.

Obtain

PRC-DeSoto P.O. Box 1800

Glendale, CA 91209 www.ppg.com

Page

beF4

1/09

20-08-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 SPECIAL TOOLS AND EQUIPMENT Tool Name

SPECIFICATION

SUPPLIER

1. Scotch-Brite Pad

3M Center

USE

Light sanding

St. Paul, MN 55144-1000 www.3m.com 2.

Sandpaper

100 Grit

Obtain

Locally

Light sanding

3.

Sandpaper

400 Grit

Obtain

Locally

Light sanding

4.

Sandpaper

240 Grit

Obtain

Locally

Light sanding

5.

Sandpaper

320 Grit

Obtain

Locally

Light sanding

6. Grace Air

Cap and Gage

7.Tack Cloth 8.

Polishing

G528CB Pads

2860

Tack

Rags (Scott Rags) 3M Center

Remove dust

Overspray

particles

removal

St. Paul, MN 55144-1000 www.3m.com 9. Wet and

10.

Dry

2000 Grit

C-Clamp

11. Scotch-Brite Pad

Small 3774

Obtain

Locally

Obtain

Locally

3M Center

Light sanding

Light sanding

St. Paul, MN 55144-1000 www.3m.com

n25

20-08-00

Feb

1 09Page

5

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRPLANE FINISH CARE

MAINTENANCE PRACTICES

AIRPLANE FINISH CLEANING The

following cleaning, waxing, placard and urethane paint the airplane exterior in an approved condition.

information

provides

finish

care

information needed to

keep

CAUTION: When

washing the airplane with mild soap and water attach the pitot covers securely and plug or mask openings, use special care to avoid washing away grease from any lubricated area. After washing the wheel well areas with solvent, lubricate all lubrication points. Premature wear of lubricated

all other

surfaces may result if these a.

Remove dust and dirt from

b.

Remove oil and grease with

c.

Remove insects with

a

Carefully

e.

Dry

painted surfaces a

the cleaned surface

remove

thoroughly

are

with

a

not obsen/ed

cellulose sponge and cool

tap

water.

dampened with Solvent (29, Chart 1,20-08-00).

detergents

rinse the surface to

ENVIRONMENTAL

cloth

cellulose sponge and

CAUTION: Harsh soaps and d.

precautions

will

a

mild soap and water solution.

damage

the

airplane finish.

all soap.

with

a

chamois to

prevent

water marks.

FALLOUT(ACID RAIN)

After the

specified curing period of new paint, avoid outside storage when conditions exist where moisture may recently painted surfaces. Acids which remain in standing water can stain the paint topcoat and cause permanent damage to the finish. Flush off residual moisture with clean tap water and dry the surface. At this time, waxing the surface can provide protection from acid rain damage. collect

on

WAXING AIRPLANE FINISHES A

good coat of wax will protect the airplane finish good automotive polish or wax may be used.

from the sun’s rays and protect the surface

against

oxidation.

Any

PLACARD REPLACEMENT All

placards

inspect

that

must be in place and legible. Whenever the airplane has been repainted or touched up after repairs placards have not been painted over. Replace any placard that has been defaced or is missing.

URETHANE PAINTS The need for

extremely hard finish for protection against sandblast during takeoff and landings led to the coatings for airplanes. Urethane paint dries to a high gloss and retains color much better finishes. It is unaffected by the chemicals in hydraulic fluids, deicer fluids and fuels, it also requires an

development of than standard

less

care

urethane

and maintenance than standard finishes.

This

airplane is finished with urethane primer and a top coat of urethane enamel. The following procedures include cleaning, paint stripping, repaint preparation, priming, applying a urethane topcoat and an alternate method for small repairs not requiring paint stripping. Careful observance of these procedures should result in a smooth, hard, glossy

finish with firm adhesion for maximum life.

n25

20-08-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE:

Any

paint on the airplane is stripped for repainting, whether the repainting is to be on a localized area airplane, or on the entire airplane, a thorough inspection for possible hidden corrosion should be

time

of the

conducted. REQUIREMENTS WARNING: Health and CAOTION: Prior to any

explosions NOTE:

safety requirements

for

personnel

in

paint

areas

must be

painting procedures the airplane must be grounded by means fires caused by electricity discharge.

strictly adhered of

a

to.

static line to prevent

or

Any conflicting finish requirements specified take precedence over these specifications.

on

engineering drawings

or

model finish

specifications

shall

assembly must be checked after each operation so that it is correct for the next operation. All operations must completed properly prior to proceeding to the next operation. It should be standard practice that if a finish is removed for any reason, including shaved rivet heads the finish shall be replaced by the department that removed it. Each

be

one person who has of all finishes.

Where´• possible there shall be at least

be

responsible

for the proper

mixing

DURING THE CURE PERIOD

prolonged flights in heavy premature finish deteriorations.

a.

Avoid

b.

Clean the

c.

Thoroughly rinse clean

airplane

with mild

been;designated

to mix

paint products,

and

they

shall

(ONE MONTH) rain

or

sleet. Avoid any

detergents and

water

only,

operating

use a

conditions which

clean soft cloth

might

keeping

cause

abrasion

it free from dirt and

or

grime.

surfaces with clean water.

TOUCH UP

through the protective coating, the raw surfaces shall be touched up to engineering drawing requirements. These requirements do not apply to drilled, punched, or machine countersunk holes or cut ends of tubing. Cut edges of parts need not be painted in detail, they may be touched up with a coat of Primer (17, Chart 1, 20-08-00) after assembly.

Where treated material is cut return the

part

or

assembly

or

machined

back to

FUNCTIONAL SURFACES Paint

applied to functional working or wearing surfaces, adjustable screw threads, oil holes, application will cause malfunction of the part. Where portions of functional parts not be applied in such a manner as to cause malfunction of the working the shall painted paint

coatings

shall not be

or

to other surfaces where such

or

fittings are adjustable surface.

or

NOTE: Control cables, control chains and parts housed in grease not be painted.

Page

20220-08-00

or

permanently

coated with oil

or

grease must

n25

Hawker Beechcraft Corporation SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DECORA TIVE OR BUFFED PARTS Buffed aluminum

parts such

cabin door frames, decorative nickel

as

color anodized parts should not be

plate, decorative chrome plate,

and decorative

painted.

SIMILAR AND DISSIMILAR MA TERIALS Where similar and dissimilar material surface finish is not

specification

for

specified, refer

to the

engineering drawing

or

model finish

paint procedure.

CONDITION OF PAINT BEFORE USE All

finishing

agitated by shaking on a paint conditioner, stirring with a paddle, or both. A check heavy settling is off of the bottom of the container and thoroughly dispersed be at room temperature (75" Fl when mixing and spraying.

materials must be

should be made to make

sure

before use. Materials should

that all

FINISHING EQUIPMENT Equipment such as spray guns, airfilters, hoses, and spray equipment is clean and functioning correctly. Pressure gage readings can be checked at any time.

booths must be

inspected to make sure that all regularly so that pressure

dials must be cleaned

TEMPERA TURE AND ENVIRONMENT

working environment humidity of 90% or less. If

for

painting operations should be at a temperature of 70" F or higher, and a relative humidity is higher than 90% painting operations shall proceed with caution until it is determined that moisture blisters or a "blushing" appearance will not occur during curing. If the temperature is less than 65" F. The working area should also be free of excess dust particles and strong drafts.

The

relative

SAFETY REQUIREMENTS

requisite safety precautions must be observed by personnel in accordance with existing instructions and regulations. Adequate paint spray regulators, protective gloves, eye protection and clothing must also be used where applicable.

All

SPRA Y PAINT GUNS NOTE:

Always

filter materials

strain out metallic

through pigments.

cone

strainers

or

milk filters when

filling

cup guns

or

pressure pots. Do not

CONVENTIONAL SPRAY GUNS The air pressure of conventional spray guns should be maintained at between 45 and 55 be set at 17 to 20 psi.

HIGH VOLUME

LOW PRESSURE

(HVLP)

psi,

the

pot pressure

should

SPRAY GUNS

For high volume low pressure spray guns (HVLP), flow rate for 15 seconds by spraying into a suitable sized measuring beaker. The flow rate shall be 90 to 120 mi per minute, with 100 to 110 mi being preferred. The atomizing air at the gun tip shall be measured using a Grace Air Cap and Gage (6, Chart 2, 20-08-00) or equivalent. This reading should not exceed 10 psi of atomizihg air with 9 psi being desired.

A25

20-08-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRPLANE SURFACE PREPARA TION INITIAL INSPECTION OF AIRPLANE

Each airplane must be inspected for dents, condition of fiberglass and plastic parts, rain erosion coatings, deep scratches, excessive gaps in skin joint, and loose or missing rivets. Any discrepancy found must be corrected. To evaluate the

lifting

paint condition, inspect

blistering

for the

following

is evidence of corrosion underneath.

a.

Paint

b.

Cracking

of

coating

around fastener heads and

c.

Cracking

or

peeling

of

d.

Deterioration of

or

conditions:

coating

on

panel butt joints.

panel surface.

paint caused by environmental agents, ultraviolet light

or

corrosive fluids

as

evident

by a chalky

the surface.

residue

on

NOTE:

Any time work is done to the RVSM area, a RVSM REGION INSPECTION and STATIC PORT INSPECTION are required (Ref. Chapter 34-10-00).

INITIAL CLEANING

CAOTION: Never use aluminum foil to mask electrothermal windshields

during painting,

most metal

brighteners

will

hydrogen gas that eats away the stannous oxide used as an anti-static electrothermal windshields. If metal brighteners are used, cover the windshield with paper or

combine with aluminum to form

coating

on

paste board material. a.

To

prevent damage

and

provide adequate protection prior

to the use of

cleaning

solutions and

paints,

mask

windows, light lenses and deicer boots using suitable barrier material. Propellers, spinners and other surfaces as necessary shall be sufficiently protected from cleaning solutions, overspray, dirt and scratches. NOTE:

Always

wash toward

or

parallel´• to tape edges

so

adhesive from the tape is not

wiped

into the

area

to be

painted. b.

airplane surfaces as necessary with Solvent (29, Chart 1, 20-08-00) or an approved solvent to remove general dirt from the surface. Solvent should be applied using´• a clean cloth, use a dry cloth in the other hand to wipe the solvent dry. Replace cloths frequently. Repeat the solvent washing until the wipe cloth remains clean. In areas that are hard to clean due to surface configuration such as rivets and seams, a stiff stub bristle brush can be used to facilitate cleaning. Do not allow the solvent to dry on the airplane.

Wash

marks and

NOTE:

Page

Any

sealer

squeeze-out should be removed manually using

20420-08-00

a

plastic

or

wooden tool.

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STRIPPING AND CLEANING URETHANE PAINT CAUTION: Do not

strippers

use

of any

type for removing paint from fiberglass, nylon or composite sandpaper, using care not to sand into

must be removed from these surfaces with fine

Never use aluminum foil to mask electrothermal windshields combine with aluminum to form

during painting,

most metal

surfaces. Paint the material.

brighteners

will

gas that eats away the stannous oxide used as an anti-static coating on electrothermal windshields. If metal brighteners are used cover the windshield with paper or paste board material.

hydrogen

Because of their resistance to chemicals and solvents, urethane

paints and primers require a Urethane Stripper (30, Chart 1, 20-08-00). If a urethane stripper is not available, a good enamel stripper may be Removing the finish with such a substitute will require several applications while working the stripper in with brush a.

or

edge of the skin or skins containing the damaged area. Use a double thickness splashes of paint stripper from penetrating the masking.

and usable

pot

paper

mixing

and

application procedures, chemical reaction, drying times,

Apply Urethane Paint Stripper (30, Chart 1, 20-08-00), keep the stripper approximately 1/8 inch away from the masking tape. This will necessitate a little more cleanup upon finishing but will prevent damage to the finish on the adjacent skin. The stripper will not attack aluminum during the stripping process and can be neutralized afterwards by rinsing the affected area with water. strippers usually contain protection when using stripper.

c.

Rinsetheareawith

d.

Wash the

00),

stripped

acids that irritate

or

burn the skin. Wear rubber gloves and eye

wateranddry.

carefully with Solvent(l, Chart 1, 20-08-00, 2, Chart 1, 20-08-00 tiny particles of loose paint from adhering to the stlipped area.

area

this will prevent

Using a Scotch-Brite good scouring will

A f.

heavy

life.

CAUTIONI Urethane

e.

of

prevent accidental

NOTE: Refer to manufacturer’s instructions for

b.

stiff

a

wooden scraper.

Mask around the to

Paint used.

Pad

(1 Chart 2, 20-08-00) d i pped in clean water, completely clean.

or

clean the surf ace with

3, Chart 1, 20-08-

a scou

ring

cleaner.

leave the surface

Thoroughly rinse with clean water and carefully dry the affected area. If the stripped area includes several joints of skin laps, let the airplane sit until all moisture has dried. This may be accelerated by blowing the skin laps and seams with compressed air. Any skin lap or seam sealant loss should be restored before repainting. Wet masking should be replaced before proceeding with further surface finishing.

FILLING OF EYEBROWS

NOTE: a.

Eyebrows

are

Clean the affected

NOTE:

Epoxy

defined area

as a

with

and urethane

paint

do not

Lightly

c.

Clean the sanded surface twice

d.

Allow

area

to air

dry

cavity around

a

rivet which is not flush.

Isopropyl Alcohol (16, Chart 1,20-08-00).

b.

n25

sand the cleaned

small

area

with

a

require stripping

Scotch-Brite Pad

using

a

if adhesion is

(1,

clean cloth and

for 10 minutes before

applying

Chart 2,

adequate.

20-08-00).

Isopropyl Alcohol (16, Chart 1, 20-08-00).

Filler

Putty.

20-08-00

Page

beF502

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: Refer to manufacturer’s instructions for

mixing

and

application procedures, chemical reaction, drying times,

and usable pot life. e.

Using

apply Filler Putty (31, Chart 1, 20-08-00) firmly sufficiently to fair-in smoothly with the adjacent area.

squeegee

a

Fill the

area

f.

Wipe

off

g.

After the filler

h.

Prime and

excess

filler

putty during application and allow

to

into the

depression, eliminating air pockets.

cure.

putty has fully cured, smooth finish the area starting with course 100 Grit Sandpaper (2, Chart 2, 20-08-00) progressing to a finer 400 Grit Sandpaper (3, Chart 2, 20-08-00) or a Scotch-Brite Pad (1, Chart 2, 20-08-00). Feather the edges flush to the surrounding surface.

paint the affected

area as

necessary.

CLEANING AND PREPARATION OF UNPRIMED ALUMINUM SURFACES a.

a Scotch-Brite Pad (1, Chart 2, 20-08-00) or 240 Grit Sandpaper (4, Chart 2, 20-08-00), sand the surface airplane using a scouring motion to clean and abrade the metal surface. Care must be taken to get close laps, around rivet heads, and other restricted areas. Any area not abraded shall be considered unclean.

Using of the to all

b.

Blow and tack the

c.

Wash surfaces

Tack Cloth

(7, Chart 2, 20-08-00),

remove

NOTE:

using

frequeritiy,

Always wash painted.

sanding

residue.

CONVERSION

a

cloth

use a

towards

or

parallel

to the

tape edge

so

adhesive from the tape is not

areas

two hours after

CLEANING AND PREPARATION OF ACRYLICS

when

coming in contact with acrylic will cause damage and crazing cleaning metal frames around acrylic windows.

a.

When necessary to finish an acrylic surface abl.ade the surface with or 320 Grit Sandpaper (5, Chart 2, 20-08-00).

b.

Wipe

the

prepared

surface with Solvent

(3, Chart 1, 20-08-00) until

NOTE: Refer to manufacturer’s instructions for and usable

to be

coating

CHROMATE

a

to the surface. Use extreme

Scotch-Brite Pad

(1,

Chart 2,

20-08-00)

clean.

mixing and application procedures, chemical reaction, drying times,

pot life.

Apply Primer (17, finishing.

Page

conversion

area

(PLEXIGLAS)

CAUTION: Most solvents care

wiped into the

(including shaved rivet heads) must be treated with chromate cleaning has been completed (Ref. APPLICATION OF COATING).

All bare aluminum

(Alodine) within

c.

any free

dampened with Solvent (2, Chart 1, 20-08-00) or an alternative. Change washing dry wipe cloth in the other hand to wipe solvent dry. Repeat the solvent washing until the wipe cloth remains clean. In areas that are hard to clean due to surf ace configuration such as rivets or seams a stiff stub brush can be used to facilitate cleaning. cloths

d.

airplane using

Chart 1,

20-08-00)

20620-08-00

to the worked surface and allow to

dry. Surfaces

are now

ready

for further

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CLEANING AND PREPARATION OF FIBERGLASS LAMINATES

NOTE: Refer to manufacturer’s instructions for

mixing

and

application procedures,

chemical reaction,

drying times,

and usable pot life. a.

Clean the surface

Surfacer b.

by sanding as required 1,20-08-00).

and fill

laminates

fiberglass

as

necessary

using ~Epoxy Sanding

Chart

(39,

Sand smooth worked surfaces

using

Scotch-Brite Pad

a

(1,

Chart 2,

20-08-00)

or

320 Grit

Sandpaper (5,

Chart

2,20-08-00). c.

Remove any free

sanding

residue with

a

cloth

prior

to any further

finishing.

CLEANING AND PREPARATION OF ABS AND PVC ACRYLIC PARTS a.

Scuff sand ABS

NOTE: b.

Any

ABS

or

or

PVC items

PVC items which

Clean abraded surfaces with

400 Grit

using

a

are

cloth

Sandpaper (3,

not abraded before

Chart 2,

priming

20-08-00)

or

finer

grit sandpaper.

shall be considered unclean.

dampened with Solvent (3, Chart 1, 20-08-00), wipe

until all

sanding

dust

is removed and the surface is clean.

NOTE: The ABS

or

PVC

acrylic parts which accordingly

and may be assembled

have been on

NOTE: Refer to manufacturer’s instructions for and usable c.

the

prepared may airplane.

mixing

and

or

may not receive

priming

as

detailed parts,

application procedures, chemical~reaction, drying times,

pot life.

Apply Primer(l7,

Chart i,

20-08-00)

or

urethane

compatible primer

to the cleaned

parts prior to further finishing.

CLEANING AND PREPARATION OF POLYCARBONATE SURFACES NOTE: a.

b.

Polycarbonate parts

are

finished with

Clean any polycarbonate surfaces to be until surface is clean. Prime surfaces with Primer COMPATIBLE

Epoxy-Polyamide

prepared using

a

Primer to protect the surfaces from solvent.

cloth

dampened

with Solvent

(3, Chart i, 20-08-00)

(17, Chart 1, 20-08-00) before further finishing (Ref. APPLICATION OF URETHANE

PRIMER).

CLEANING AND PREPARATION OF COMPOSITE SURFACES The

following procedure

CAUTION: Do not sand a.

is for

composite winglets

lightning

composite surface with agents.

CAUTION: Do not allow solvent to b.

n25

Using a clean Wipe dry with

cloth a

wipe

composite details which

strike surface material if

Sand the release

and

across

320 Grit

dry

on

part of

an

aluminum

assembly.

applicable.

Sandpaper (5,

Chart 2,

20-08-00),

to remove debris and mould

the surface.

the sanded surface in

second clean cloth,

are

a

unifonn pattern with Solvent

(29, Chart i, 20-08-00).

replace cloths frequently.

20-08-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: Refer to manufacturer’s instructions for and usable c.

Apply

coat of Primer

a

temperature (750 Fl, NOTE:

Do not

mixing

and

application procedures, chemical reaction, drying times,

pot life.

(17, Chart 1, 20-08-00)

or

force

for

a

or

force

cure

0.4 to 0.9 mils thick and allow to

30 minutes flash at

surfacer to the

apply sanding

temperature (75" Fl,

cure

primed surface

with

a

NOTE: Refer to manufacturer’s instructions for

room

until the

30 minute flash at

mixing

and

cure

for 3 hours at

temperature followed by

primer

room

room

2 hours at 120" F.

has cured for 3 hours at

room

temperature followed by 2 hours

at 120" F.

application procedures, chemical reaction, drying times,

and usable pot life. d.

Apply a wet coat of Epoxy Sanding Surfacer (39, Chart 1, 20-08-00) and allow sanding surfacer is required then apply within 5 to 7 minutes. Cure at 135" F

CAUTION: Don not sand CAUTION: Do not e.

strike surface material if

Ketone solvents to

wipe

(3,

If

Chart

cure.

If

a

second coat of

15 minutes for 3 hours.

applicable.

down surface. The

Hand sand the surfacer back to the substrate without

Solvent f.

use

lightning

to

sanding

exposed surface

into the surface.

is not solvent resistant.

Wipe

the surface clean with

1,20-08-00).

required, pinholes and irregularities found in the composite substrate may cosmetically be improved by using Putty (31, Chart 1, 20-08-00) with 320 Grit Sandpaper (5, Chart 2, 20-08-00) to smooth

fillers. Sand the Filler

the surface. of filler

coating

NOTE: A continuous

over

the

winglet

NOTE: Refer to manufacturer’s instructions for

mixing

surface is not and

acceptable.

application procedures, chemical reaction, drying times,

and usable pot life.

g.

Wipe the surface clean with Solvent (3, Chart 1, 20-08-00).

h.

Apply 1 (75" Fl

i.

Final

coat of or

force

Primer(l7, cure

preparation

for

with

Chart 1,

a

20-08-00) 0.4

30 minute flash at

topcoat paint

to 0.9 mils thick. Allow to

room

will be when the

cure

for 3 hours at

temperature (75" Fl followed by

winglet

is assembled

on

the

room

temperature

2 hours at 120" F.

airplane.

CLEANING AND PREPARATION OF PREPRIMED AIRPLANE SKINS a.

airplane preprimed skin using a Scotch-Brite Pad (1, Chart 2, 20-08-00) or 240 Grit Sandpaper (4, 20-08-00), sand the surface using a scouring motion to clean and abrade the metal surface. Care must be taken to get close to all laps, around rivet heads, and other restricted areas. Any area not abraded shall be Sand the Chart 2,

considered unclean. b.

Blow and tack the

airplane using

c.

Wash surfaces

necessary with Solvent

as

Tack Cloths

(7, Chart 2, 20-08-00).

(29, Chart 1, 20-08-00)

or an

approved

alternative. Solvent should be

applied using a clean cloth, use a dry cloth in the other hand to wipe the solvent dry. Replace cloths frequently. Repeat the solvent washing until the wipe cloth remains clean. In areas that are hard to clean due to surface configuration such as rivets and seams a stiff stub bristle brush can be used to facilitate cleaning. NOTE:

Page

Always wash painted.

towards

or

parallel

20-08-00

to the

tape edge

so

adhesive from the tape is not

wiped into the

area

to be

~25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

(including shaved rivet heads) must be treated with chromate conversion coating cleaning has been completed (Ref. APPLICATION OF CHROMATE COATING).

All bare aluminum

(Alodine),

CONVERSION NOTE: The or

areas

within two hours after

skins should be

airplane

preprimed

with

primer.

The skins should be smooth and free from dirt, sags

other surface contamination.

CLEANING AND PREPARATION OF STAINLESS STEEL AIRPLANE SKINS Exterior stainless steel skins should be a.

Sand the stainless steel

processed and primed prior

to

being

installed

on

the

airplane.

panel using a Scotch-Brite Pad (1, Chart 2, 20-08-00) or 240 Grit Sandpaper (4, Chart using a scouring motion to clean and abrade the metal surface. Care must be around rivet heads, and other restricted areas. Any area not abraded shall be laps,

sand the surface

2, 20-08-00), taken to get close

to all

considered unclean.

b.

Blow and tack the

NOTE:

c.

Always wash painted.

airplane using

towards

or

Tack Cloths

parallel

to the

Wash stainless steel surfaces with Solvent

(7, Chart 2, 20-08-00)

tape edge

(29,

so

Chart 1,

to remove any free

adhesive from the tape is not

20-08-00)

or an

approved

sanding

wiped into

residue. the

area

to be

alternative. Solvent should

applied using clean cloth, use a dry cloth in the other hand to wipe the solvent dry. Replace cloths frequently, repeat the solvent washing until the wipe cloth remains clean. In areas that are hard to clean due to surface configuration such as rivets, seams etc, a stiff stub bristle brush can be used to facilitate cleaning. be

a

NOPE: Refer to manufacturer’s instructions for and usable d.

and

application procedures, chemical reaction, drying times.

When

cleaning has been completed, apply a coat of Base Primer (5, Chart 1, 20-08-00) to the stainless steel (WASH) PRIMER FOR URETHANE PAINT). Allow to dry for 1 hour at ambient temperature until the wash primed surface is nail hard before further finishing. (Ref.

PRETREATMENT

NOTE: The e:

mixing

pot life.

Apply

a

dry

film coat shall be 0.5 to 0.7 mils thick.

piimer using Primer (17, Chart 1,20-08-00) (Ref. APPLICATION OF URETHANE PRIMER). Allow to dry prior to topcoat application.

second coat of

COMPATIBLE

CLEANING AND PREPARATION OF ANODIZED PARTS NOTE: a.

Special

Using

a

n25

using

a

Blow and tack the

NOTE:

c.

must be taken not to remove the anodized

coating

when

cleaning.

Scotch-Brite Pad

of the part unclean. b.

care

(1, Chart 2, 20-08-00) or 240 Grit Sandpaper (4, Chart 2, 20-08-00), sand scouring motion to clean and abrade the surface. Any area not abraded shall be

part using Tack Cloths (7, Chart 2, 20-08-00)

Always wash towards painted.

or

parallel

to the

tape edge

so

to

remove

any free

wiped

considered

residue.

sanding

adhesive from the tape is not

the surface

into the

area

to be

Using a cloth dampened with Solvent (2, Chart 1 20-08-00) or approved alternative, wash the surfaces. Change washing cloths frequently, use a dry wipe cloth in the other hand to wipe solvent dry. Repeat the solvent washing until the wipe cloth remains clean.

20-08-00

Page

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Apply Chromate Conversion Coating CONVERSION COATING).

to the anodized surfaces

NOTE: Refer to manufacturer’s instructions for and usable e.

Apply primer to PRIMER).

mixing

and

(Ref. APPLICATION OF

application procedures,

CHROMATE

chemical reaction,

drying times,

pot life. the surface before

topcoat application (Ref. APPLICATION OF URETHANE COMPATIBLE

APPLICATION OF CHROMATE CONVERSION COATING CAUTION: All

personnel must

NOTE: Alodine 600

or

approved

rubber

gloves

when

applying

chromate conversion

coating.

Alodine 1200S is the

aluminum. Other NOTE:

wear

products

are

preferred solution used to apply a chromate conversion coating acceptable if the requirements of MIL-C-5541 are met.

Apply Chemical Conversion Coating (38, Chart 1, 20-08-00) only

to

to aluminum surfaces that have been

cleaned per CLEANING AND PREPARATION OF UNPRIMED ALUMINUM SURFACES AND PREPARATION OF PREPRIMED AIRPLANE SKINS procedures in this chapter.

or

CLEANING

Chart 201

Application

Operating Conditions

Solution

Alodine 1200S

Alodine 600

a.

Operating Range

Concentration

2.5

pH

1.3-1.8

Time

0.5

4 minutes

Concentration

2.5

3.5

pH

1.5

2.0

Time

3

3.5

oz/gal

oz/gal

5 minutes

after cleaning (within 2 hours) treat applicable surfaces with a Chemical Conversion Coating (38, 20-08-00) using a clean cloth pad, use light pressure and a continuous even motion. On curved or surfaces begin the application at the lower surface of the work area to minimize streaking.

Immediately Chart 1, inclined

b.

of Alodine Products

Keep the applicable

surfaces wet with solution for the

designated length

of time. The chemical film

produced

may vary in color from light green or tan color, through iridescent to dull brown. A continuous film is required, different color matches between different surfaces and different areas of the same surface are not acceptable.

NOTE: A NOTE: c.

grayish

Generally

or

a

dark

powdery

light chemical

non

film

adherent

coating

coating

for

indicates

paint base

is

an

unsatisfactory

film.

preferred.

Remove excess chemical conversion coating from the surface with clean distilled or deionized water. Use a light rinsing motion, do not apply any force to the newly formed chemical conversion coating as the coating can be easily removed. Excess water may be blotted from the surface or blown off with clean compressed air, being careful not to damage the fresh chemical conversion coating.

Page

21020-08-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

permissible to use Alodine Touch-N-Prep pens (28, Chart 1, 20-08-00) to touch up small areas of bare (shaved rivets). These areas shall be less than 1 inch by 1 inch and applied in 2 coats. Apply the second coat 15 minutes after the first coat, and applied 90" to the first coat. It is

NOTE:

aluminum

d.

Allow the film to air

e.

Any

dry completely

showing

area not

a

for 4 to 18 hours

satisfactory

or

force

cure

visible colored film must be recleaned

PREPARATION OF UNPRIMED ALUMINUM SURFACES, steps f.

at 120" F for 1 hour.

a

to

(Ref. CLEANING

AND

c).

(Ref. APPLICATION OF URETHANE COMPATIBLE PRIMER), the chemical primer applied within 18 hours. Chemical conversion coating older than 18 reapplied.

Prime all worked surfaces

conversion

must have

coating

must be removed and

hours

MASKING parts housed in grease or permanently coated with static pressure ports, windows, light lenses, deicer boots must not be painted.

NOTE: Control cables, control chains,

Mask all

areas

which do not

Kraft Barrier Material

oil orgrease, all antenna,

require paint. Use Aluminum Foil Tape (32, Chart 1, 20-08-00) where appropriate and 20-08-00). For protective boot and tape locations (non paint areas) refer to Figure

Chart 1,

(33,

204.

CAUTION: Make

that all

sure

maskings

and

removed before

covers are

returning

the

airplane

to service.

FINAL CLEAN BEFORE URETHANE COMPA TIBLE PRIMER CAUTION: Do not touch the white

gloves

a.

Wipe (final clean)

b.

Tack the

the

prepared

cloths may

cause

Primer

Etching

(5,

Chart

after this final

cleaning

place.

Use clean

Chart 1,

20-08-00).

has taken

prepared

area

before

surface down with

applying

a

clean cloth

the urethane

primer.

dampened

Use

only

with Solvent

Tack Cloths

(7,

(3,

Chart 2,

20-08-00),

other

streaks.

PRETREA TMENT An Acid

prepared surface with bare hands moving the assembly.

when

(WASH)

PRIMER FOR URETHANE PAINTS

(4, Chart 1, 20-08-00) may be used to improve the adhesion of the finishing coats. A Base 1, 20-08-00) and Catalyst (6, Chart 1, 20-08-00) are used in equal parts as a pretreatment wash

Primer

primer. NOTE: Refer to manufacturer’s instructions for

mixing

and

application procedures,

chemical reaction,

drying times,

and usable pot life. a.

Mixtheurethanewash primer.

b.

Apply

primer with a spray gun which is PAINT GUNS). The wash primer should be permitted to dry for at least 1 the next coat of Primer (17, Chart 1, 20-08-00) is applied.

n25

a

thin wet coat of urethane wash

set at a low pressure

hour but not

more

(Ref. SPRAY

than 6 hours before

20-08-00

Page

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1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

APPLICA TION OF URETHANE COMPA nSLE PRIMER NOTE:

In

of

Urethane

properly cure

temperature, humidity, film thickness, dry time, air pressures and thinners, only a general limit given. Weather and atmospheric conditions produce daily changes which prevent the establishment

areas

can

be

rigid

of

values.

Regulate

the

required changes necessary

to

produce

the standard and

quality

of finish.

be applied using siphon cup guns or pressure pot system (Ref. SPRAY PAINT GUNS). When applied the urethane primer should cure in approximately 3 hours at 750 F. For an accelerated primer to flash for 30 minutes at room temperature and then cure at 120" F for 2 hours.

primer

can

mixed and

allow the

Painting application should start at a point on the airplane furthest from the booth exhaust, this will reduce problems over spray and dirt contaminating the surface. Avoid high air pressure, use the minimum fluid pressure and atomization pressure necessary to give an acceptable spray pattern. Spray at 10 psi maximum at the spray gun head due to material atomizing very easily. with

NOTE: Refer to manufacturer’s instructions for

mixing

and

application procedures, chemical reaction, drying times,

and usable pot life. a.

Mix the urethane

c.

to

catalyzation.

catalyst as a thinner. Failure to mix the base component proper ratio will seriously impair the quality of the finish.

WARNING:

b.

primer, check for pigment settling prior

Do not

use

and the

catalyst

in the

20-08-00), coverage

must be complete for proper adhesion. A the surface. Hold the spray gun 8 to 12 inches from cover or speckled the surface to make sure the film is wet. If the paint lands dry the adhesion of the primer will be poor. A dry film thickness of urethane primer 0.0004 to 0.0009 inches thick shall be applied.

Apply a spotted

uniform wet coat of Primer

(17,

Chart 1,

finish indicates the film did not

Allowtodry.

TOPCOA T PREPA RA TION CAUTION: Do not

(75" Fl NOTE:

apply topcoat if the primer has conditions

or a

not been allowed to

30 minute flash at

room

dry

for at least 3 hours at

temperature and then

a

2 hour

cure

room

temperature

at 1200F.

primet has cured over 72 hours then sand the primed surface to allow adequate adhesion using Sandpaper (4, Chart 2, 20-08-00) to 340 Grit Sandpaper (5, Chart 2, 20-08-00).

If the

Grit

240

SANDING Sand the

primed

surfaces

smooth surface

as

necessary,

taking special

care

around rivets to prevent removal of primer. Sand to roughness due to orange peel and other surface

provide only, overspray, sags irregularities. When properly cured the primer surfaces should form a powder when sanded, if the primer balls up or clogs the primer has not cured. If sufficient dry time has been allowed and provided that the ambient temperature has been 75" F or higher uncured primer usually indicates that the materials were not correctly mixed. a

remove

or

runs,

CLEANING a.

b.

Remove any sanding particles by wiping the surf ace with a clean cloth or clean white gloves. Crevices and joints may have dust removed by blowing pure, dry compressed air over the surface toward the exhaust system of the spray booth.

Very lightly

tack the entire surface

using

Tack Cloths

(7, Chart 2, 20-08-00).

Do not

use

heavy pressure

on

the

surface.

Page

21220-08-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: The direction of work shall be towards the spray booth exhaust to the rear.

system. Spray from the front of the airplane

TOPCOA T APPLICA nON NOTE: In

areas

be

can

of

of temperature, humidity, film thickness, dry time, air pressures and thinners only a general limit Weather and atmospheric conditions produce daily changes which prevent the establishment

given.

rigid

values.

Regulate

the

required changes necessary

to

produce

the standard and

quality

of finish.

multiple component material, care must be taken to make sure that the proper materials and mixing ratios are apply the topcoat unless the primed surface has been allowed to dry for at least 3 hours at room temperature (75" Fl, or a 30 minute flash at room temperature followed by a 2 hour cure at 120" F. Make sure that materials from the supplier are not mixed with the products of another supplier. Paint is

a

used. Do not

Painting application

should start at

a

point

on

the

airplane furthest from the booth exhaust, this

will reduce

problems

spray and dirt contaminating the surface. Application of topcoat usually consists of at least 2 coats. Avoid air high pressure, use the minimum fluid pressure and atomization pressure necessary to give an acceptable spray pattern (Ref. SPRAY PAINT GUNS).

with

over

WARNING: Do not

the catalyst (converter or activator) as a thinner. Failure to mix catalyst in the proper ratio will seriously impair the quality of the

use

and the

NOTE: Refer to manufacturer’s instructions for and usable

mixing

and

application procedures,

the base component finish.

chemical reaction,

drying times,

pot life.

a.

Mix the

b.

Using a spray gun apply the first application of topcoat to the prepared surface. Hold the spray gun 8 to 12 inches from the surface. The first coat (tack coat) should be applied as a uniform wet film, not sufficient to cause hiding of the

topcoat, check for pigment settling prior

to the

catalyst being

added.

primer.

NOTE: The total

dry

film thickness of urethane shall be 0.0014 to 0.0025 inches.

as necessary, allow sufficient time between the coats. Each coat shall achieve that successive coats will hang to the previous coat with out running or sagging.

c.

Apply further coat(s)

d.

Apply the

e.

Allow to

NOTE:

final coat

full wet coat, sufficient to flow out to

TOPCOAT

dry (Ref.

Orange peel

as a

is

a

smooth

glossy

a

tack

so

finish.

CURE).

a common

surface defect when

using polyester

or

polycarbonate

of orange peel are paint not thinned correctly, paint is cold, gun stroke too the surface resulting in a dry coat, insufficient or too much air pressure. causes

urethane. Some of the

rapid

or

too far away from

TOPCOA T CURE specified, the finished topcoat shall be allowed to air dry for a minimum of 16 hours prior to sanding. Cure time can be reduced by the application of heat, not exceeding 130" F. If heat is used to accelerate curing the paint should be allowed to flash for 1 hour at room temperature, then cure at 120" F for 8 hours. Failure to do so may result in solvent popping or blisters. Unless otherwise

masking

or

PREPARA TION AND APPLICATION OF COLOR MARKINGS a.

nzs

Lay

out and

mask,

as

necessary, the surface to be detailed

(STRIPES

using appropriate

OR

materials

TRIM)

(Ref. MASKING).

20-08-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION: Failure to abrade the

stripe

area

will result in

paint peeling.

b.

stripe or trim application area using a Scotch-Brite Pad (1, Chart 2, 20-08-00) or 320 Grit Sandpaper (5, Chart 2, 20-08-00) to 400 Grit Sandpaper (3, Chart 2, 20-08-00). Remove all nibs and orange peel etc, sand as close to the tape edges as possible. Sand the surface of the airplane using a scouring motion to clean and abrade the metal surface. Care must be taken to get close to all laps, around rivet heads and other restricted areas.Any area not abraded shall be considered unclean.

c.

Remove any sanding particles by wiping the surface with a clean cloth or clean white gloves. Crevices and joints may have dust removed by blowing pure, dry compressed air over the surface toward the exhaust system of the

Scuff sand the

spray booth. d.

Very lightly

tack the entire surface

using

Tack Cloths

(7,

Chart 2,

20-08-00). Do

not

use

heavy

pressure

the

on

surface.

NOTE: Refer to manufacturer’s instructions for and usable e.

Apply Adhesion adhesion of the the

mixing

and

application procedures,

chemical reaction,

drying times,

pot life. Promoter

(34,

Chart

1,20-08-00)

to

stripes that

are

1 inch wide

stripe

trim

required using

Apply

g.

A clear coat may be applied over the stripe to enhance the buffing process, enhance the de-masking operation, preventing damage to the stripe.

or

less to enhance the

paint

established methods and processes.

f.

stripes

or

to the base coat. as

imagery

and

gloss.

This will also

NOTE: Total film thickness must not exceed 0.006 inches. h.

Masking tape can be carefully removed immediately after paint application, always peel tape slowly away from painted surface. Care should be taken to remove masking tape before the finish has cured to a state where tape removal will cause chipping to the paint edges.

the

NOTE: Allow the finished

assembly

to

cure

at least 24 hours before exposure to incletnental weather.

REWORK OF COLOR MARKINGS Rework a.

panels

Abrade surface remove

riveted b.

and

stripe edges

using

as

240 Grit

follows:

Sandpaper (4, Chart 2, 20-08-00) to 320 Grit Sandpaper (5, Chart 2, 20-08-00), topcoat. Use a Scotch-Brite Pad (1, Chart 2, 20-08-00) to scuff sand

at least one-half of the urethane areas.

exposed, if bare metal is exposed equivalent and reprimed before reapplying

Bare metals must not be used conversion

coating

or

the

area

must be treated with chromate

the urethane

CONVERSION COATING and APPLICATION OF URETHANE COMPATIBLE c.

Express, and Sherwin Williams Acry Glo paints accomplished using established methods and processes.

For PRC Desoto Desothane, Sherwin Williams RAC Jet Glo

"spotting d.

topcoat (Ref. CHROMATE PRIMER).

in" method is

preferred and should

be

can be applied over the stripe to enhance the buffing demasking operation preventing damage to the stripe.

A clear coat

the

process,

imagery

and

gloss.

the

This will enhance

NOTE: Total film thickness must exceed 0.006 inches.

Page

21420-08-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Masking tape can be carefully removed immediately after paint application, always peel tape slowly away from the painted surface. Care should be taken to remove tape before the finish has cured to a state where tape removal will cause chipping of the paint edges.

e.

REPAIRED AREA THICKNESS The total

paint thickness in

reworked

a

area

shall be from at least 5 measurements taken from

rivets the

or

area

edges.

If the surface of the

is limited to

panel

is

average of 0.006 inches. This average thickness the toward center of the panels and not from areas around

must not exceed areas

an

cosmetically acceptable, exceeding

0.006 inches is

permitted provided

smaller than 9 square inches and does not exceed 0.008 inches.

an area

NOTE: Repair thickness does not

to surfaces that

apply

balances.

require

hiding of colors, such as white and yellows may require additional thickness to achieve hiding and can be dealt exception. Areas such as the wing to fuselage area are expected to receive overlapping coats and will have additional paint thickness. Poor

with

as an

NOTE: On extended range fuel tanks assemblies there shall be or

no area

with

a

paint thickness of

total

0.006 inches

greater.

LIMIT OF REPAIR AREAS

repaired panels are allowed, a panel is defined as being Technical Support for all airplanes that exceed this condition.

Only

4

at least 5 square feet. Contact Hawker Beechcraft

TOPCOA T REPAIR PROCEDURE URETHANE TOUCH-UP REPAIR a.

Mask around the skin

b.

Remove all loose

c.

Using

d.

Abrade the

coarse

containing the damaged of

edges

paint by using

edge of

the

high

a

20-08-00)

Chart 2,

Sandpaper

area.

tack adhesive tape around the fair the

edge

of the

damaged

edge

area

of the

damaged

area.

with the metal.

paint until the surface begins to fair into a smooth joint, use finer grade of sandpapers by the coarse paper. Take care to avoid removing any more material than is

to eliminate the scratches left

absolutely necessary. e.

Wash the abraded so

that all of the

area

with Solvent

sanding

(2, Chart 1,20-08-00) picked up.

or

approved

alternative.

Change

cloths

frequently

residue will be

NOTE: Refer to manufacturer’s instructions for

mixing

and

application procedures,

chemical reaction,

drying times,

and usable pot life. f.

Clean the

(4,

area

Chart 1,

to be touched up until all traces of discoloration are gone,

20-08-00)

to the

damaged

apply

a

thin coat of Acid

Etching

Primer

area.

primer coating can be dispensed with. If the no wash primer is available, carefully clean the surface to be touched up and apply Primer (17, Chart 1, 20-08-00) to the bare metal (Ref. APPLICATION OF URETHANE COM PATIBLE PRIM ER). This should produce a satisfactory undercoat for the repair area.

NOTE: If

a

metal conversion

coating such

metal has not been treated with

n25

a

as

alodine is used the wash

metal conversion

coating

but

20-08-00

Page

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1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

g.

primer has cured for 24 hours sand the repair area with medium fine Sandpaper (3, Chart 2, 20-08edge of the repair area until the indentation where the metal and old paint meet has gone. If necessary apply additional primer until the juncture of old paint with metal is no longer visible.

After the

00).

h.

Sand the

Spray

on

topcoats (Ref. TOPCOAT APPLICATION).

two urethane

OVERSPRAY REMOVAL a.

Remove overspray with a clean cloth approved alternative.

dampened

with Solvent

(3, Chart 1,20-08-00

or

29, Chart 1,20-08-00)

or

an

b.

If necessary lightly water sand the overspray Grit (9, Chart 2, 20-08-00) and water.

NOTE: Care should be taken to c.

Apply

a

suitable fine cut

Pads

(8,

Chart 2,

much of the overspray without

remove as

polish

using Polishing

20-08-00)

sanding

into the

or

Wet and

Dry,

2000

topcoat.

repair area and work in the polish using a buffer with low RPM and light polisher back and forth until the polish is removed, replace the polish

to the

pressure. Increase the RPM and work the

pad

as

d.

Repeat

e.

Wipe

necessary. the

polishing

surface clean

until overspray is removed and

using

a

gloss

is restored.

soft, clean cotton cloth.

SPOT REPAIR OF SOLID COLORS

opacity (hide) at different thicknesses such as repair area should be the same as its surrounding area. topcoat when removing the surface defect, sanding through the topcoat will

In order to avoid mismatch in

untinted white, the

repairing

colors that have different

thickness of the topcoat in the

dry

Therefore, avoid sanding through the require additional coats of topcoat to obtain a.

Scuff sand the surface

b.

Wet and the

c.

that the

Wipe

topcoat

beyond

the

Sandpaper (5, Chart 2, 20-08-00)

repair by

sanding using repair area.

wet

will bond to the blended

the worked surface

clean from all

full hide.

necessary.

with 320 Grit

Abrade the surface so

d.

dry sand repair coat.

as

a

sanding

using

a

clean cloth

dampened

or

finer,

400 Grit

with Solvent

so

scratches do not

telegraph through

Sandpaper (3, Chart 2, 20-08-00)

(29,

Chart

or

finer,

1,20-08-00) until the surface is

residue.

NOTE: Refer to manufacturer’s instructions for

mixing

and

application procedures,

chemical

reaction, drying times,

and usable pot life. e.

f.

Using a low air pressure, apply the (Ref. TOPCOAT APPLICATION). Remove the

pressure

to the

repair area

topcoat from the spray gun and add blending Solvent (35, Chart i, 20-08-00), using low air to the spot repair to blend in the overspray area.

spraying blending

Allow the blend

Page

prepared surface, keep the spray confined

apply the blending solvent

NOTE: Avoid g.

excess

base coat to the

area

to

solvent outside the

dry completely,

21620-08-00

prepared repair

then buff the

repair

area

area.

(Ref.

OVERSPRAY

REMOVAL).

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Spray techniques can affect color. As an example if gray is sprayed "wet", it will appear lighter than if it were sprayed "dry". A sagged area usually is sprayed too wet. To make a repair that matches the surrounding area it is recommended to spray "wet" to match the

NOTE: The clear coat process is also

same

color.

acceptable

for touch up defects in the clear coat

only.

SPOT REPAIR OF METALLIC AND NON-METALLIC COLORS Small repairs

can

(Ref.

observed

be made

using gravity GUNS).

or

siphon guns providing

that the

same

paint application

as

the

original

is

SPRAY PAINT

NOTE: Refer to manufacturer’s instructions for

mixing

and

application procedures, chemical reaction, drying times,

and usable pot life.

a.

Sand the surface with 320 Grit

Sandpaper (5, Chart 2, 20-08-00)

NOTE: Care should be taken not to sand

through

or

400 Grit

Sandpaper (3,

Chart 2,

20-08-00).

to bare metal.

b.

Apply

the base solid color to the

c.

Apply

2

d.

paint guns, one with clear coat and one with topcoat, apply clear coat extending approximately 3 beyond the repair area. Check for color match, if the outer edge of the repair is lighter in color than the original surface then apply topcoat into the extended area of the clear (Ref. Figure 201).

Using

or

3 metallic

or

prepared

surface.

non-metallic coats.

2 spray

inches

WARNING: e.

After

Do not spray color

blending

the outer

beyond

edge repair

the clear

area

area.

to achieve a

good

color match, spray the

complete repair

coat of clear coat.

f.

When the

repair surface

has cured the clear coated

NOTE: The clear coat process is also

n25

repair

may be buffed.

acceptable for the touching

up of defects in the clear coat

20-08-00

only.

area

with 1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

COLOR COAT

CLEAR COAT

POLISH COAT

NOTE! THIS CLEAR COAT PROCESS IS ALSO ACCEPTABLE FOR TOUCH-UP DEFECTS IN THE CLEAR COAT ONLY.

Spot Blending Figure 201 PAINT ADHESION TEST

dry time after application of the final coat for most finishes, and 72 hours for epoxy and polyurethane topcoats. Drying times may be reduced if parts/panels have been force cured. Allow 48 hours

NOTE: Refer to manufacturer’s instructions for and usable a.

Apply

a

pot

2 inch wide

the tape to make

mixing and application procedures,

chemical reaction,

drying times,

life.

strip

sure

of

Tape (36, Chart 1, 20-08-00) or an approved equivalent, rolling tape adheres to the full length of the panel.

or

rubbing

down

on

that the

rapid motion, pulling

at 90" to the surface to the

panel.

b.

Remove the tape in

c.

Check the tape for paint, if any paint has been removed from the surface then the adhesion test has failed. The panel must be stripped, prepared and re-painted.

Page

beF812

1/09

one

20108-00

nzs

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SPECIAL PROCEDURES Follow these

special procedures when repainting

the indicated items:

NOSE RADOME

CAUTION: Radar nose

operation

can

be

adversely affected by abrupt

variations in the thickness of the material in the

radome, which could be caused by excessive and/or

repair

of

damage.

It is recommended that

a

uneven

damaged nose

buildup of repair material during replaced rather than repaired.

radome be

Repainting the radome will affect the transmissibility requirements of the radome, therefore a maximum of three thin only of polyurethane paint can be applied and should not be exceeded. The use of any paint other than polyurethane is not recommended. When preparing the radome for repainting, use a fine grit sandpaper but do not sand into the black anti-static coating beneath the finish paint coat.

coats

NOTE:

Multiple coats of anti-static coating will change resistance, therefore anti-static coating repaired with additional coats of anti-static coating or flat black paint.

should NOT be

purchased irom Hawker Beechcraft Corporation are finished complete with primer and anti-static are ready for final painting, The new radome must be fit, trimmed, drilled and countersunk to the coating individual airplane. To make sure that there is an electrical bond to the fuselage a small metal tab or strap should be attached to the inner aft edge of radome with one rivet after.fitting. After installation of the tab’the rivet head on the exterior surface of the radome should be painted with one coat of flat black Anti-static Coating (9, Chart 1, 2008-00). New radomes and

INSTALLATION OF BONDED LIGHTNING DIVERTER STRIPS a.

Place

diverter

strip on the radome and align the diverter strip’s countersunk end with the radome’s attaching place masking tape 0.08inch away from the edge of the diverter for the entire length of the diverter (Ref. Figure 202). a

hole. Then

b.

Scuff sand the bottom of the diverter

c.

Clean the sanded

area

with

a

strip with fine Grit Sandpaper (3, Chart 2, 20-08-00).

clean, lint free cloth dampened with Solvent (2, Chart 1, 20-08-00)

or an

approved

alternative. d.

Wipe immediately with

e.

Clean the

00) f.

or an

Tape the

bonding

a

clean, dry, lint free cloth and then allow the diverter

surface of the radome with

approved

alternative. Then

center 1M-inch of the

lightning

mixing

Adhesive

Position the diverter strip in the proper location C-Clamp (10, Chart 2, 20-08-00).

n25

to the

Epoxy edge

(19,

Chart 1,

h.

Fair in the

masking tape.

and

application procedures,

chemical

reaction, drying times,

pot life.

Apply Epoxy

strip

clean, lint free cloth dampened with Solvent (2, Chart 1, 20-08with a clean, dry, lint free cloth.

diverter with

g.

i.

dry completely.

wipe immediately

NOTE: Refer to manufacturer’s instructions for and usable

a

to air

Adhesive of the

20-08-00)

to the

bonding

surface of the diverter

and fasten the aft end of the

(19, Chart 1, 20-08-00), approximately masking tape.

strip

strip.

with

a screw

0.06-inch from the outer

and small

edge

20-08-00

of the diverter

Page

beF912

1109

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

j.

Fair in the epoxy adhesive around the forward end of the the first nickel segment.

k.

Clean the

excess

epoxy adhesive from the sides of the

lightning diverter, overlapping

strips

and

the diverter

as

far

as

tape in place with release tape.

INSTALLING SELF-ADHESIVE LIGHTNING DIVERTERS a.

Place

a

strip on the radome and align the diverter strip’s countersunk end with the radome’s attaching place masking tape O.O&inch away from the edge of the diverter along the entire length (Ref. Figure

diverter

hole. Then

202). b. c.

Scuff sand the bond surface of radome with Clean the sanded

Wipe

with

a

the radome

bonding

fine

sandpaper.

clean, lint free cloth dampened with Solvent (2, Chart 1,20-08-00)

wipe with another clean, dry,

alternative. Then d.

area

a

area

or an

approved

lint free cloth.

(20,

with Adhesive Promoter

Chart 1,

20-08-00)

and let the

area

dry for

15

minutes. the self-adhesive diverter

e.

Remove the

f.

Center the diverter within the taped

g.

Apply

even

protective paper

on

area on

strip.

the radome surface.

pressure to the surface of the diverter

strip, allowing

no

voids

or

separations along its edge.

RADOME PROTECTIVE BOOT

airplane is equipped with a radome protective boot, procedures must be followed precisely to allow serviceability If the

the

following removal,

installation and maintenance

of the boot installation.

RADOME PROTECTIVE BOOT REMOVAL CAUTION: Use extreme caution radome

painted

dur~ng

the

trimming

of the

protective

boot. The

razor

blade must not cut into the

surface.

a.

Using a razor blade carefully score the surface of the protective boot dissecting the protective boot into triangular pie-shaped sections. Each section should be approximately 4 to 6 inches wide at the base. Do not cut into the radome (Ref. Figure 204).

b.

Pull the

pie-shaped sections from the radome beginning at the top and pulling previously pulled section until all sections are removed.

down. Pull

the

next section at

180" from the c.

Remove any adhesive residue from the radome using a clean cloth dampened with a 75% Solvent (2, Chart i, 20-08-00) and 25% Solvent (15, Chart 1, 20-08-00) solution. Wipe dry using a dry clean cloth. Do not allow the

cleaning

solution to

dry

on

the radome surface,

CAUTION: Observe the manufacturer’s

possibly causing damage

to the radome.

safety recommendations when using cleaners

to clean the radome.

RADOME PROTECTIVE BOOT MAINTENANCE Maintenance of the

protective

Page

unpainted protective boot is a paste wax application replaced at the first indication of damage.

when needed to prevent

staining.

The

boot should be

22020-08-00

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

C

DIVERTER STRIPS

o

RADOME

B DETAIL

A

FAIR ADHESIVE OVER LEADING EDGE OF DIVERTER STRIP

NICKEL

SEGMENTS

S’CREW

SIDE DIVERTER STRIP

VIEW

DETAIL

B

MASKING TAPE

LIGHTING STRIP

FAIRED ADHESIVE

PAINT TOPSIDE

RADOME SURFACE

APPROXIMATELY 0.06" TYPICAL

I-

DETAIL

C FLPOB a03872AL,

Radome

ORIGINAL By

As Received

A25

ATP

Lightning Diverter Strips Figure 202

20 08-00

Page

221

Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RADOME PROTECTIVE BOOT INSTALLA nON a.

Thoroughly

b.

Wipe

wash the radome with

the surface with

a

Isopropyl

Trim the boot with

d.

Position the

Chart 1,

dry

a

pair

protective

1.

Rotate the

2.

Mark three index

t24,

Chart 1,

for 10 minutes. For best results

boot with the

protective

protective

boot until the best fit

liner still in

place

over

area

may be

area

under the boot must be

painted

the

same

color

NOTE: The entire adhesive surface of the

Carefully

(wrinkle free) is obtained

on

the radome.

as

water and 1

place

over

the radome. At

painted and cured prior to installation of the protective boot. This airplane topcoat or an optional black color.

the

protective boot

must be saturated with the

wetting solution.

the transparent protective liner from the protective boot. Saturate the exposed adhesive protective boot with a wetting solution of 25% Isopropyl Alcohol (16, Chart 1, 20-08-00), 75%

Joy) per gallon of wetting solution. Apply bonding. A sponge or spray bottle can be used.

teaspoon of liquid detergent tIvory

removed to prevent adhesive-to-adhesive

side

protective boot adhesive right side in.

Place the

NOTE: Care must be taken to avoid

or

protective boot

Saturate the entire surface of the

will be

out and

remove

surface of the

i.

2

the radome.

protective boot from the radome, turn the protective boot inside disregard the index points but do not remove them.

NOTE: The radome

h.

20-08-00) using the minimum apply the protective boot within

of scissors about 1/2 inch above the trim line.

Remove the

g.

wipe dry tRef. Figure 204).

points on the radome and protective boot using small triangles of masking tape so that the protective boot can be returned to the exact centered location after the adhesive liner has been removed. Place the triangle pieces of tape tinder points) at the top and sides of the radome about 90" apart.

this time

f.

and

20-08-00)

of the adhesion promoter.

application

c.

(16,

clean cloth wet with Adhesion Promoter

amount that will coat the surface. Allow to

hours of

Alcohol

on

leaving

contact area

the radome and

blisters under the

on

the radome with the

carefully align

the index

as

wetting

points.

the liner is

being

solution.

The

protective

boot

protective boot.

Using a plastic squeegee with rounded edges, squeegee the wetting solution from under the protective boot. Start at the center of the protective boot and work the blisters back to the end and out from under the protective boot.

i.

If air

with k.

wetting solution is still trapped pull the boot back to wetting solution and squeegee the boot back down. or

If small blisters still remain under the or

wetting

airplane painted Using are

an

Page

industrial

present

from the

222

Feb 1/09

air/wetting

solution

pocket, re-spray

the

area

protective boot, pierce them with a safety pin and relieve the entrapped or wetting solution with the squeegee.

air

solution. Work out entrapped air

CAUTION: Use extreme caution

i.

relieve

on

edge

razor

during

the

trimming of the protective boot. The

razor

blade must not cut into the

surface. blade trim the

the radome do not of the diverter

protective

cover

edge to the proper dimension. If static diverters protective boot. Trim the material of the protective boot

boot at the

them with the

strip.

20-08-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: Refer to manufacturer’s instructions for

and usable m.

When

00) n.

trimming

is

and

application procedures,

chemical reaction,

drying times,

complete

mask off the

area

and

apply Adhesive (23, Chart 1, strip.

20-08-00

or

25, Chart 1, 20-08-

to the radome around the cutout for the diverter

Thoroughly dry for at least

the surface of the boot with

hour

an

prior

a

cloth. Allow the

protective

boot installation to dwell at 70"F

(21"C)

flight.

to

o.

Remove orientation marks after

p.

Paint the radome and 1.

mixing

life.

pot

complete installation.

protective boot

as

follows:

the surface of the radome and

Wipe

20-08-00)

or an

protective boot with a clean cloth dampened with Solvent (2, Chart 1, approved alternative. Observe the manufacturer’s safety recommendations at all times.

2.

If solvent is not desirable use a Scotch-Brite Pad (11, Chart 2, 20-08-00) and lightly scuff the surface of the protective boot and radome surface. Using a clean cloth dampened with Ethanol Solvent (37, Chart 1,2q08-00), wipe the protective boot and radome clean.

3.

Do not

4.

Allow the radome and

5.

Apply

prime

the

the

protective

boot before

protective boot

topcoat paint directly

to

painting.

dry

for

approximately

to the ~radome and

protective

30 minutes.

boot

as

instructed

by

the

paint

manufacturer.

PROTECTIVE TAPE If the

airplane is equipped with protective tape on the leading edge surfaces then the following removal, installation procedures must be followed precisely to allow serviceability of the tape installation.

and maintenance

PROTECTIVE TAPE REMOVAL

WARNING: When

using tape

clothing.

and residue remover, avoid eye and skin contact. Do not get on skin or gloves and protective clothing. Avoid breathing vapors. Use only with

Wear suitable

adequate ventilation.

Do not

ingest.

Wash

thoroughly after handling.

Close container after each

use.

CAUTION:

Tape

and residue

compatibility a.

Using

b.

Cover

remover may cause with the substrate prior to

paint softening

and

acrylic crazing.

Test residue

a squeegee apply a uniform layer of Tape and Residue Remover (21, Chart 1, 20-08-00) 1/8 inch thick to the entire surface of the tape being removed (surface should look brown).

Tape and Residue

Remover with

a

remover

use.

clear

plastic cellophane like film

to

approximately

prevent evaporation of the

remover.

c.

Let

remover

stand until the

F. Elevated d.

temperatures

tape wrinkles, lifts

or

bubbles. This

requires approximately

4 hours dwell time at 75

will shorten the dwell time.

Remove tape and any adhesive residue from the bonding surface using a clean cloth dampened with a 75% (1, Chart 1, 20-08-00) and 25% Solvent (15, Chart 1, 20-08-00) solution. Wipe dry using a dry clean

Solvent cloth.

n25

20-08-00

Page

beF32

1/09

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

e.

Using a clean cloth dampened with a 75% Solvent t1, Chart 1, 20-08-00) and 25% Solvent t29, Chart 1, 20-0800) solution, scrub remaining adhesive residue from the bonding surface. A Scotch-Brite Pad (1, Chart 2, 2008-00) may aid in removing any stubborn areas of adhesive, especially around any surface protrusions such as rivet heads.

f.

Finally, 00).

g.

Repair

clean the entire

any

areas

bonding

of removed

surface

paint

NOTE: Observe the manufacturer’s

or

safety

using

a

clean cloth soaked with

bare metal

Alcohol

Isopropyl

(16,

Chart 1, 20-08-

tRef. AIRPLANE SURFACE PREPARATION).

recommendations when

using

cleaners to clean the

bonding

surface.

PROTECTIVE TAPE MAINTENANCE

unpainted protective tape is a paste wax application protective tape should be replaced at the first indication of damage. Maintenance of the

when needed to

prevent staining. The

PROTECTIVE TAPE INSTALLA TION a.

Thoroughly

b.

Wipe

wash the

bonding

the surface with

a

surface with

c.

d.

application of the

Position the

Alcohol

t16, Chart 1, 20-08-00) and wipe dry.

clean cloth wetted with Adhesion Promoter

amount that will coat the surface. Allow to

hours of

Isopropyl

adhesion

protective tape

over

the

dry

(24, Chart 1,20-08-00) using the minimum apply the protectivetape within 2

for 10minutes. For best results

promoter.

airplane

surface with the

protective

liner still in

place.

points on the airplane surface and protective tape using small triangles of masking tape so that protective tape can be returned to the exact centered location after the adhesive liner has been removed. Place the triangle pieces of tape tinder points) at the top and sides on the airplane surface. Mark three index

the

NOTE: The entire adhesive surface of the e.

protective tape

must be saturated with the

wetting

solution.

transparent protective liner from the protective tape. Saturate the exposed adhesive protective tape with a wetting solution of 25% Isopropyl Alcohol (16, Chart 1, 20-08-00), 75% water and 1 teaspoon of liquid detergent (Ivory or Joy) per gallon of wetting solution, apply as the liner is being removed to prevent adhesive-to-adhesive bonding. A sponge or spray bottle can be used.

Carefully

remove

the

surface of the

attaching airplane

f.

Saturate the

g.

Place the tape

over

the

surface with the

attaching airplane

NOTE: Care must be taken to avoid h.

edges

If air with

j.

surface

(adhesive

blisters under the

side to

airplane).

protective tape.

After proper alignment has been made, squeegee out the wetting solution starting at the center and working out toward the edges. Take care to avoid blisters under the tape surface. Use a clean cloth to remove the liquid at the

i.

leaving

wetting solution.

of the

tape.

wetting solution is still trapped, pull the tape back to wetting solution and squeegee the tape back down. or

relieve

air/wetting

solution

protective tape, pierce them with a safety pin and relieve entrapped air or wetting solution with the squeegee.

If small blisters still remain under the or

wetting

solution. Work out

CAUTION: Use extreme caution

during airplane painted surface.

Page

pocket, re-spray

22420-08-00

the

trimming

of the

protective tape.

The

razor

the

the

area

entrapped air

blade must not cut into the

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

k.

Final trim

NOTE: The i.

with

required

as

an

industrial

protective tape installation

razor

with

NOTE: Refer to manufacturer’s instructions for

m.

If any of the

08-00)

being

careful not to cut into the

must set for 24 hours at room

Thoroughly dry the surface of the tape "C) for at least an hour prior to flight.

and usable

blade

a

cloth. Allow the

and

mixing

airplane painted

temperature for the adhesive

protective tape installation

surface.

to cure.

to dwell at 700 F

(21

application procedures, chemical reaction, drying times,

pot life.

edges can be picked up by the airstream, apply Adhesive (23, Chart 1, edges as an edge sealer.

20-08-00

or

25, Chart 1, 20-

to the

AIR INTAKE PROTECTIVE BOOT If the airplane is equipped with an air procedures must be followed precisely

intake

protective boot the following removal, serviceability of the protective boot.

installation and maintenance

to allow

AIR INTAKE PROTECTIVE BOOT REMOVAL CAUTION: Use extreme caution

during the trimming of~the protectiveboot. The airplane painted surface.

a.

Using a razor blade carefully score the surface of the protective approximately 4 to 6 inches wide at the base (Ref. Figure 203).

b.

Peel back the section from the

bonding

surface at

affect how much adhesive residue is left c.

an

angle of paint is

how much

blade must not cut into the

boot in sections. Each section should be

90" to 180".

Speed

and

of removal may

angle

removed from the substrate.

Remove any adhesive residue from the bonding surface using a clean cloth dampened with a 75% Solvent (2, Chart 1, 20-08-00) and 25% Solvent (15, Chart 1, 20-08-00) solution. Wipe dry using a dry clean cloth. Do not allow the

d.

or

razor

Using

a

solution to

cleaning

clean cloth

A Scotch-brite Pad e.

Carry out a 20-08-00).

final

f.

Repair any

areas

dry

on

the surface

possibly causing damage

to the surface.

dampened with the solution, scrub the remaining adhesive residue (1, Chart 2, 20-08-00) may be used to help remove any stubborn

clean

of the entire

of removed

paint

NOTE: Observe the manufacturer’s

bonding

or

surface

bare metal

using

using

a

clean cloth wet with

from the bonded surface. areas

Isopropyl

of adhesive.

Alcohol

established methods and processes

safety recommendations when cleaning

the

bonding

as

(16,

Chart 1,

necessary.

surface.

AIR INTAKE PROTECTIVE BOOT MAINTENANCE

Maintenance of the

protective

unpainted protective boot is a paste wax application replaced at the first indication of damage.

when needed to prevent

staining.

The

boot should be

AIR INTAKE PROTECTIVE BOOT INSTALLA nON a.

/\25

Thoroughly 203).

wash the

bonding

surfaces with

Isopropyl

Alcohol

(16, Chart i, 20-08-00)

and

wipe dry (Ref. Figure

20-08-00

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

b.

Wipe the surface with

a

clean cloth wet with Adhesion Promoter

amount that will coat the surface. Allow to

hours of

application

c.

Trim the boot with

d.

Position the

e.

a

dry

for 10

t24, Chart 1,20-08-00) using

the minimum

minutes, for best results apply the protective boot within

2

of the adhesion promoter.

pair of scissors approximately 1/2

protective

boot

over

the air intake with the

an

inch above the trim line.

protective

liner still in

place.

points on the airplane surface and protective boot using small triangles of masking tape so that protective tape can be returned to the exact centered location after the adhesive liner has been removed. Place the triangular pieces of tape tinder points) at the top and sides of the air intake.

Mark three index

the

f.

protective

Remove the

boot from the air intake, turn the

NOTE: The entire adhesive surface of the

g.

Carefully surfacing

protective boot

protective

boot inside out.

must be saturated with the

wetting

solution.

the transparent protective liner from the protective boot. Saturate the exposed adhesive protective boot with a wetting solution of 25% Isopropyl Alcohol t16, Chart 1, 20-08-00), 75% teaspoon of liquid detergent tIvory or Joy) per gallon of wetting solution. Apply as the liner is being prevent adhesive-to-adhesive bonding. A sponge or spray bottle can be used.

remove

of the

water and 1

removed to

attaching airplane surface with wetting solution.

h.

Saturate the

i.

Place the

j.

After proper alignment has been made, squeegee out the wetting solution at the center and the edges. Use a clean cloth to remove the liquid at the edges of the boot.

k.

If air

protective

boot

over

the

or wetting solution is trapped, pull back the protective boot to relieve Respray the area with wetting solution and sqeegee the boot back down.

NOTE: Care must be taken to avoid i.

wetting

Final trim

NOTE: The n.

leaving blisters under the protective

to

airplane).

air and

wetting

solution. Work out the as

required

protective

with

an

protective boot, pierce them with a safety pin and entrapped air or wetting solution with a sqeegee.

industrial

razor

blade

being

careful not to cut into the

boot installation must set for 24 hours at

Thoroughly dry the surface of the boot C) for at least an hour prior to flight.

with

NOTE: Refer to manufacturer’s instructions for

a

room

and

solution

relieve the

out toward

pocket.

temperature for the adhesive

application procedures,

entrapped air

airplane painted

cloth, allow the protective boot installation

mixing

working

boot.

If small blisters still remain under the or

m.

attaching airplane surface tadhesive side

surface.

to cure.

to dwell at 70" F

(21"

chemical reaction,

drying times,

Chart 1,

to the

and usable pot life.

d.

If any of the

edges

edge

sealer.

as an

can

be

picked up by

the airstream then

apply

Adhesive

t23,

20-08-00)

edges

BULLET PROTECTIVE BOOT

airplane is equipped with a bullet protective boot, the following removal, installation procedures must be followed precisely to allow serviceability of the protective boot installation. If the

Page

22620-08-00

and maintenance

n25

-lz~´•’

4-

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BUL LET PRO TECTI VE BOOT REMO VAL

CAUTION: Use extreme caution

the

during airplane painted surface.

a.

b.

Using a razor blade, carefully score the approximately 4 to 6 inches wide at the tRef. Figure 204). Peel back the sections from the

trimming

surface of the base. The

bonding

affect how much adhesive residue is left c.

of the

boot. The

an

how much

razor

blade must not cut into the

in sections. Each section should be

protective boot

razor

surface at or

protective

blade must not cut into the

airplane painted surface

angle of 90" to 180". Speed and angle paint is removed from the substrate.

of removal may

Remove any adhesive residue from the bonding surface using a clean cloth dampened with a 75% Solvent t2, Chart 1, 20-08-00) and 25% Solvent (15, Chart 1, 20-08-00) solution. Wipe dry using another dry clean cloth. Do not allow the

cleaning

solution to set

the surface,

on

possibly causing damage

to the surface.

d.

Using a clean cloth dampened with a 75% Solvent t2, Chart 1, 20-08-00) and 25% Solvent t15, Chart 1, 20-0800) solution, scrub remaining adhesive residue from the bonding surface. A Scotch-Brite Pad t1, Chart 2, 2008-00) can aid in removing any stubborn areas of adhesive.

e.

Finally, 00).

f.

Repair

clean the entire

any

areas

bonding

of removed

surface

paint

NOTE: Observe the manufacturer’s

or

using

a

clean cloth soaked with

bare metal

safety

(Ref.

Isopropyl

AIRPLANE SURFACE

recommendations when

Alcohol

(16,

PREPARATION).

cleaners to clean the

using

Chart 1, 20-08-

bonding

surface.

BULLET PROTECTIVE BOOT MAINTENANCE Maintenance of the

protective

unpainted protective boot is a paste wax application replaced at the first indication of damage.

when needed to prevent

staining.

The

boot should be

BULLET PROTECTIVE BOOT INSTALLA nON a.

Thoroughly 204).

b.

Wipe

wash the

bonding

the surface with

a

surface with

clean cloth wetted with Adhesion Promoter

amount that will coat the surface. Allow to

hours of

Trim the boot with

d.

Position the

a

pair

points

boot

on

with the

the

protective liner

airplane

Turn boot inside out and

of

surface and

tape tinder points)

place

over

bullet.

NOTE: The entire adhesive surface of the

a25

t24, Chart 1, 20-08-00), using the minimum apply the protective boot within 2

for 10 minutes. For best results

still in

place

over

the

airplane surface.

protective boot using small triangles

of

masking tape

so

that

be returned to the exact centered location after the adhesive liner has been removed.

protective triangle pieces can

Place the f.

wipe dry (Ref. Figure

of scissors about 1/2 inch above the trim line.

protective boot

Mark three index the

dry

and

application of the adhesion promoter.

c.

e.

Isopropyl Alcohol (16, Chart 1, 20-08-00)

at the

Disregard

protective

top and sides

the index

point

on

the boot.

marks at this time but do not

boot must be saturated with the

wetting

remove

solution.

20-08-00

them.

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

g.

Carefully

remove

surface of the water and 1

removed to

the transparent protective liner from the protective boot. Saturate the exposed adhesive boot with a wetting solution of 25% Isopropyl Alcohol (16, Chart 1, 20-08-00), 75%

protective

teaspoon of liquid detergent (Ivory or Joy) per gallon of wetting solution. Apply prevent adhesive-to-adhesive bonding. A sponge or spray bottle can be used.

attaching airplane

surface with the

Saturate the

i.

Place the

j.

After proper alignment has been made, squeegee out wetting solution back. Use a clean cloth to remove liquid at the edges of the boot.

protective

boot

over

the

leaving

NOTE: Care must be taken to avoid

wetting

solution. Work out the

during airplane painted surface.

Final trim

NOTE: The n.

blisters under the

as

required

with

an

industrial

protective boot installation

Thoroughly dry the surface C) for at least an hour prior

the

trimming

razor

protective

and usable

of the

at the center and

working

blade

being

of the boot with

a

razor

the

area

relieve the

airplane painted surface.

temperature for the adhesive

protective

entrapped air

blade must not cut into the

careful not to cut into the

cloth. Allow the

out and

boot.

boot. The

protective

must set for 24 hours at room

to cure.

boot installation to dwell at 70" F

(210

flight.

to

NOTE: Referto manufacturer’s instructions for

o.

starting

protective boot, pierce them with a safety pin and entrapped air or wetting solution with the squeegee.

CAUTION: Use extreme caution

being

airplane).

If small blisters still remain under the or

m.

side to

attaching airplane surface (adhesive

or wetting solution is still trapped, pull the boot back to relieve air/wetting solution pocket, re-spray wetting solution and squeegee the boot back down.

If air with

i.

the liner is

solution.

h.

k.

I

wetting

as

mixing

and

application procedures, chemical reaction, drying times,

pot life.

If any of the edges edge sealer.

can

be

picked

up

by

the airstream,

apply

Adhesive

(23,

Chart 1,

20-08-00)

to the

edges

as

an

TAPE AND RESIDUE REMOVAL

Tape

and residue

remover

(ALTERNATE METHOD)

use in removing polyurethane protective tapes, neoprene rubber, carpet tape residue from interior cabin composite surfaces.

is recommended for

and other tape residues, such

as

TAPE RESIDUE REMOVAL

using tape and residue remover, avoid eye and skin contact. Do not get on skin or clothing. Wear suitable gloves and protective clothing. Avoid breathing vapors. Use only with adequate ventilation. Do not ingest. Wash thoroughly after handling. Close container after each

WARNING: When

use.

CAUTION:

a.

Apply tape

NOTE:

Page

a

Tape and residue remover may cause paint softening compatibility with the substrate prior to use. uniform

and

acrylic crazing.

Test residue

remover

layer of Tape and Residue Remover (21, Chart 1, 20-08-00) approximately 1/8 inch thick using a squeegee type tool (surface should look brown).

to the

residue surface

Removing tape residues typically require require longer dwell times.

22820-08-00

a

dwell time from 1 to 15 minutes,

although

some

residues may

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

b.

Waitfor 1 to 15 minutes.

c.

Wipe

d.

Clean surface

with

area

clean cloth to

a

using

a

remove

damp cloth,

residue.

and final

wipe using

a

substrate

compatible

solvent.

PROTECTIVE TAPES AND NEOPRENE RUBBER REMOVAL WARNING: When

using tape and residue remover, avoid eye and skin contact. Do not get on skin or clothing. Wear suitable gloves and protective clothing. Avoid breathing vapors. Use only with adequate ventilation. Do not ingest. Washthoroughly after handling. Close container after each use.

CAUTION:

a.

Apply

a

Tape and residue remover may cause paint softening compatibility with the substrate prior to use. uniform

entire surface of b.

Cover residue Let

c.

acrylic crazing.

Test residue

layer of Tape and Residue Remover (21, Chart 1, 20-08-00) approximately being removed using a squeegee (surface should look brown).

remover

stand until

remover

and

using tape

a

or

clear

rubber wrinkles,

thicker materials may take 12 hours

d.

Pull and

e.

Wipe surface and surrounding

f.

Clean surface

remove

plastic cellophane like

using

a

damp cloth,

or

1/8 inch thick to the

prevent evaporation.

bubbles. Thinner tapes may take 2 to 6 hours while

or more.

tape. If any residue remains, area

lifts,

film to

remover

using

a

and final

remove

using

a

cloth

dampened

with residue

compatible

solvent.

remover.

clean cloth.

wipe using

a

substrate

ABRASION RESISTANT POLYURETHANE SPRAY COATING

polyurethane Spray Coating (27, Chart 1,20-08-00) may protection (Ref. Figure 205).

Abrasion Resistant area

for erosion

be

applied

to the

wing leading edge

ABRASION RESISTANT POL YURETHANE SPRA Y COA TING REMOVAL If the

airplane

is

stub,

remove

the

If the

airplane has had abrasion resistant polyurethane spray coating applied between the nacelle and wing stub, remove the spray coating in accordance with the procedures in step

or

equipped with protective tape between the nacelle and the deice boot or the nacelle and protective tape (Ref. PROTECTIVE TAPES AND NEOPRENE RUBBER REMOVAL).

the nacelle and the

the

wing

the deice boot c, ABRASION

RESISTANT POLYURETHANE SPRAY COATING APPLICATION. ABRA SION RESISTA NT POL YURETHANE SPRA Y COA TING APPL ICA nON a.

Layout as

and mask off the

NOTE: The 1.

2.

area

to be

where the spray

sprayed

Use the deice boot width Measure corner

,2,

area

coating

will be installed between the nacelle and the deice boot

follows:

approximately

should be masked to

as a

guide

provide straight edges.

to define the upper and lower limits for the spray

7 inches true from the center of the

leading edge

coating.

to determine the upper inboard

location.

20-08-00

Page

beF92

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Measure

3.

approximately

7.5 inches true from the center of the

leading edge

to determine the lower inboard

location.

corner

Use the nacelle/nacelle fillet seal and the deice boot to define the inboard and outboard limits for the spray

4.

coating. NOTE:

Make

sure

that there is

the external power If

a screw

Layout and mask off the as

or

area

to be

sprayed

and

edge of the masked the’spray area.

area,

adjust the masking

so

that the entire

screw

omitted from

where the spray

coating

will be installed between the nacelle and the

area

to be

be masked to

sprayed should

wing

stub

inside the

provide straight edges.

inlets to avoid overspray

1.

Mask the heat

2.

Use the deice boot width to define the upper and lower limits for the spray

3.

Use the nacelle, deice boot and

NOTE:

If

exchanger

a screw

the entire

Clean the 1.

area

door.

follows:

NOTE: The

c.

minimum of 2 inches of clearance between the

head intersects the

head is included b.

a

access

area

wing

head intersects the screw

and

masking,

use

on

the fins.

coating.

stub to define the inboard and outboard limits for the spray

of the masked

edge

head is included

where abrasion resistant

Following layout

wing

or

area

adjust the masking tape

omitted from the spray

polyurethane spray coating

320 Grit

Sandpaper (5,

sure

that

area.

is to be

Chart 2,

to make

coating.

applied

20-08-00)

or

as

follows:

400 Grit

Sandpaper (3,

Chart 2, 20-08-00) or Scotch-Brite Pad (1, Chart 2, 20-08-00j to scuff sand the application area. Remove all nibs, orange peel, etc. Use a scouring motion to clean and abrade the surface, care must be taken to get close to all

laps,

around rivet heads and other restricted

areas.

Any

area

not abraded shall be considered

unclean. 2.

Blow the sanded down the worked

3.

Using

a

clean

area area

with pure, dry compressed air towards the exhaust of the spray booth and then with Tack Cloth (7, Chart 2, 20-08-00) to remove any free sanding residue.

(29, Chart i, 20-08-00), wash the application area. Use another cleaning solvent air dry on the surface. Repeat the dry,

clean cloth wetted with Solvent cloth to

the solvent

do not let the

wipe dry washing until the wipe cloth remains clean. In areas that are hard to clean due configuration such as rivets, a stiff stub bristle brush can be used to facilitate cleaning. solvent

NOTE:

4.

wipe

Always wash towards to be painted.

or

parallel

to the

tape edge

so as

not to

wipe

to surface

adhesive from the

tape

to the

area

After

cleaning immediately treat any bare aluminum with Alodine. It is permissible to use a Alodine Touchpen (28, Chart i, 20-08-00) to touch up small areas of bare aluminum, such as shaved rivets etc. These areas shall be less than t inch by 1 inch. Apply Alodine in two coats. The second coat shall be applied 15 minutes after the first coat and shall be applied at 90" to the first coat (Ref. APPLICATION OF CHROMATE CONVERSION COATING). N-Prep

5.

Wipe

down the

application

area

with clean cloths that have been

dampened with Solvent (3, Chart

1. 20-

08-00). NOTE: Refer to manufacturer’s instructions for

mixing

and

application procedures,

chemical reaction,

drying times,

and usable pot life.

Page

23020-08-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Apply 1.

abrasion resistant

polyurethane

Mix the abrasion resistant

spray

polyurethane

coating spray

as

follows:

coating.

WARNING: When

using abrasion resistant polyurethane spray coating, avoid eye and skin contact. get on skin or clothing. Wear suitable gloves and protective clothing. Avoid breathing vapors. Use only with adequate ventilation. Do not ingest. Wash thoroughly after handling. Do not

NOTE:

Refer to manufacturer’s instructions for

mixing

and

application procedures, chemical reaction, drying

times, and usable pot life. 2.

Apply the

Abrasion Resistant

Polyurethane Spray Coating (27, Chart 1, 20-08-00) in two wet coats, with 15 applications. Make sure that there is a smooth and continuous look to the area sprayed polyurethane spray coating.

minutes between with the NOTE: 3.

Do not

remove

masking tape

Allow the abrasion resistant

NOTE: The abrasion

until the abrasion resistant

polyurethane

coating

spray

resistant:polyurethane spray coating by 3 hours minimum at

temperature flash followed 4.

After the abrasion resistant

5.

If removed, install

polyurethane

spray

coating

polyurethane

spray

coating is cured.

to cure for 6 hours at ambient

may be force cured with 120" F. has cured,

remove

a

temperature.

30 minuteambient

masking tape.

wraparound fairing.

EROSION PREVENTION SEALANT Sealant is

applied around t~e´•windshield perimeters, around cabin window perimeters paint erosion. Use the following procedure to apply the sealant.

and between the hot

lip

and

the nacelle to prevent a.

Remove any

b.

Mask off the

previously applied area

being

sealed

sealant.

Thoroughly

clean the surface

being

sealed.

(Ref. Figure 205).

NOTE: Referto manufacturer’s instructions for

mixing

and

application procedures,

chemical reaction,

drying times,

and usable pot life. c.

Apply sealant, two different sealants are applicable, Sealant (26, Chart 1, 20-08-00) is for use around windshield perimeters, and Sealant (22, Chart 1 20-08-00) is for use around cabin window perimeters and between the hot lip and the nacelle.

d.

Fairsealant intoaflatsurface

e.

Fair sealant to

f.

Remove

excess

g.

Remove

masking

n25

a

minimum of 1/32 inch between hot

lip

and nacelle.

sealant. and allow sealant to

cure.

20-08-00

PFBe9be~l)

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIR INLET DUCTS

The heat

exchanger

side. The

air inlet ducts

that

areas

are

are

located

the

on

leading edge

center section

to be reworked consist of the entire air inlet

wing

assemblies

on

the inboard

ducts, including the full circumference of the

cu Nes.

NOTE: The air inlet ducts is too coarse, a.

Remove the

are

or a

lined with

urethane

a

coated

stripper

topcoat of urethane enamel primer material.

glass

could

fabric which is to be left intact. The

cause

damage

the affected

on

areas

to the

area

with

fine

a

when

grade

use

removing

of

of

sandpaper

that

the topcoat.

sandpaper, being

careful not

to remove the

NOTE: Refer to manufacturer’s instructions for

mixing

and

application procedures, chemical reaction, drying times,

and usable pot life. b.

Apply the first coat of White to dry for one hour.

c.

Apply the

d.

Apply

e.

After the

second coat and allow to

the third coat and allow to

forty-eight

hour

Chart 1,

(10,

Base

dry

for

20-08-00) and Curing Solution (11, Chart 1, 20-08-00) then

one

hour.

dry for forty-eight

drying period,

the

allow

hours.

topcoat may be applied (Ref. TOPCOAT APPLICATION).

URINAL SURFACE AREA

Seal all the belly applying paint.

skin

laps aft of

the venturi tube outlet with Sealer

(12, Chart 1, 20-08-00),

or

equivalent, before

BATTERY BOX AND LID The a.

battery

thoroughly prior

and usable

Apply

a

as

follows:

Apply

a

pot

mixing

and

application procedures,

chemical reaction,

surface

drying times,

life.

minimum of two coats of Primer

COMPATIBLE c.

repainting

good paint adherence, apply Chemical Conversion Coating (38, Chart 1, 20-08-00) to the entire repainted (Ref. APPLICATION OF CHROMATE CONVERSION COATING).

NOTE: Refer to manufacturer’s instructions for

b.

to

To allow to be

I

box and lid must be cleaned

(17,

Chart 1,

20-08-00) (Ref. APPLICATION

OF URETHANE

PRIMER).

minimum of three coats of Urethane Paint (18, Chart 1, 20-08-00).

RUBBER SEALS

Apply

one

coat of a

thoroughly dissolved solution containing

one

part Soap (13, Chart 1, 20-08-00) and

two

parts

water to all rubber surfaces that are to come in contact with either metal or other rubber surfaces.

LAMINATED FIBERGLASS SURFACES

Apply Sanding Surfacer (14,

Feb

1/09Page

232

Chart 1,

20-08-00)

20-08-00

until the surface to be

painted

is smooth.

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PAINTING WET WING FUEL ACCESS PLATES access plates on the lower surface of each outboard wing wet fuel cell (Ref. Chapter 12-20-00) are nylon material. If paint must be removed from these access plates, use only fine sandpaper, using care

The five oval made from

not to sand into the material.

WAR~jlNG: Do

not use

paint stripper of any kind

on

these surfaces.

preparing the access plates for painting, scuff sand the exterior surface only with 240 Grit Sandpaper (4, 2, 20-08-00) and wipe with a clean cloth soaked in Solvent (2, Chart~l, 20-08-00 or 3, Chart i, 20-08-00).

When

Chart

drying application procedures, mixing d n a , s e m i t pot

NOTE: Refer to manufacturer’s instructions for usable

d.

Apply Primer (17, Chart i, 20-08-00) COMPATIBLE PRIMER).

e.

When

dry

scuff sand with fine

CAUTION: Do not

a25

chemical reaction,

and

life.

to the exterior surface

sandpaper prior to applying

apply primer or paint

to the inferior

only (Ref. APPLICATION

finish

OF URETHANE

paint coating (Ref. TOPCOAT AIPPLICATION).

surface, the O-ring

seat area or the threaded attach holes.

20-08-00

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

12 INCH WIDE TAPE

(31.5 INCHES LONG) (X TO X) BOTH SIDES

a

I\

I

h an

II

a

NE

1.5 INCH WIDE TAPE

(15 INCHES LONG) ON HORIZONTAI. STABILIZER TIPS. BOTH SIDES 2 INCH WIDE TAPE

(15.25

INCHES

LONG)

ON WINGLET LEADING EDGE

BOTH SIDES 1 INCH WIDE TAPE

(5LOUVERSEACH 13 INCHES LONG)

0.75 INCH WIDE TAPE

ON A/C LOUVERS

(15.25 INCHES LONG) ON GLARE FIN EDGES

BOTH SIDE

2 INCH WIDE TAPE

(41NCHESLONG) APPLY LOWER EDGE FIRST THEN WRAP UPWARDS. CUTTING OUT FOR GLARE FIN

12 INCH WIDE TAPE

BOTH SIDES

(3.5 INCHES LONG) BOTH SIDES

12 INCH WIDE TAPE

(14.5 INCHES LONG) (BOOT TO FAIRING) BOTH SIDES

Protective

BootTTape Locations Figure

Page

beF432

1/09

20-08-00

FL2W

203

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BOOT-BULLET 4 INCH WIDE TAPE

(9 INCHES LONG) 4 INCH WIDE TAPE

(64 INCHES LONG) RADOME BOOT

b

Q)

O

(O FL2OB

Protective

n25

BootTTape Locations Figure 204

20-08-00

Page

beF532

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SEALANT AROUND WINDSHIELD PERIMETER

OnO

SEALANT BE~TWEEN HOT LIP AND NACELLE BOTH SIDES

SEALAN~’ BETWEEN NAV L.IGHT AND WINGTIP

BOTH SIDES

SEALANT AROUND CABIN WINDOWS BOTH SIDES

0)

(O Fuoe 061441AA.AI

Abrasion Resistant

Polyurethane Spray Coating Figure

Page

beF632

1/09

20I08-00

Locations

205

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

CORROSION

DESCRIPTION AND OPERATION

Corrosion is the

gradual eating away of material by chemical action or electro-chemical reaction with the environment. Corrosion may develop at areas where the protective coating has been damaged. When this happens, it is important to restore the protective coating. Corrosion also occurs when dissimilar metals are in contact with any moisture

present. High levels of humidity, high levels of environmental impurities (such as salt spray, acid rain, deposits, or chemical fumes), or high ambient temperatures will increase the rate of corrosion. Some of the more common types of corrosion are uniform etch corrosion, intergranular corrosion, pitting corrosion, exfoliation corrosion, and electrolytic corrosion or galvanic corrosion. exhaust

UNIFORM ETCH CORROSION Uniform etch corrosion may be recognized by a uniform dull appearance of a further, it becomes rough and frosty (or icy) in appearance. This chemical attack. to corrode

polish surface.

If the surface is allowed

type of corrosion is the result of direct

INTERGRANULAR CORROSION Intergranular corrosion may be recognized by a streaky or discolored appearance on aluminum alloy surfaces. Alloys consist of quantities of individual grains, separated from each other with clearly defined grain boundaries which differ chemically from the element in the grain center. The adjacent grains of different elements can react with each other as anode and cathode in the presence of moisture to produce rapid selective electrochemical attack at the grain boundaries. Aluminum

alloys (2024

constituents

are

and

7075)

are

the most

susceptible

to

intergranular corrosion, since their alloying

ideal for electro-chemical attack.

FITTING CORROSION

Fitting corrosion may be recognized by a white or gray powdery deposit blotching the surface of aluminum or magnesium alloys and a brown or red powdery deposit on steel. When the deposit is removed, tiny pits or holes can be seen on the surface. This type of corrosion is the result of direct chemical attack between the metal and foreign materials

on

the surface of the metal in the presence of moisture.

EXFOL IA TION CORROSION Exfoliation corrosion is

actual

separation

intergranular

and is

of the metal around

predominate

or near

rivets

or

in aluminum

alloys.

It may be

recognized by blistering

or

I

along grain

I

bolt holes.

ELECTROLYTIC CORROSION Electrolytic

corrosion

originates

boundaries until the metal

n25

can no

in

unprotected

longer

surfaces of

a

rivet

or

bolt hole and will continue

contain the corrosion. This action results in

blistering

of the outer surface.

20-09-00Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

GAL VANIC CORROSION

galvanic series shown below which metals are attacked when in contact with a dissimilar metal. The wider the separation in the series, from the top to the bottom, the faster the rate of corrosion. A partial galvanic series list The

follows: Anodic.

or

corroded end of series

Magnesium alloys Aluminum

alloys 5052, 5056, 5356, 6061,

All other aluminum

6063

alloys

Zinc Cadmium Lead Tin

Steel

Copper alloys Nickel

alloys

Titanium

Cathodic,

or

protected

end of series

Note that corrosion is relative. For

example: aluminum alloys corrode

when in contact with steel; steels corrode

when in contact with copper.

RECOMMENDED MA TERIALS meeting federal, military or supplier specifications are provided for specifically required by Hawker Beechcraft Corporation. Any product conforming to the used subject to availability. The products included in these charts have been tested and usage by Hawker Beechcraft Corporation, by the supplier or compliance to the applicable

The recommended materials listed in Chart 1 reference

and

only specification may be approved for aviation specifications. GENERIC are

as

not

OR

LOCALLY

MANUFACTURED

PRODUCTS

WHICH

CONFORM

TO

REQUIREMENTS OF A SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART.

THE

Only

specification is listed. No attempt has been made to update the listing to the latest revision. responsibility of the technician or mechanic to determine the current revision of the applicable specification usage of the product listed. This can be done by contacting the supplier of the product to be used.

the basic number of each It is the

prior

to

Page

beF2

1/09

20´•09-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 1 Recommended Materials MATERIAL

1.Coating

SPECIFICATION

PRODUCT

MIL-C-5541

Alodine 1200

SUPPLIER Amchem Products Inc

Spring

Garden St

Ambler PA 19002 Amchem Products Inc St.

MIL-P-23377

2. Primer

Epoxy

Primer

Joseph

MO

Ameron Industrial

Coatings

Div

P.O. Box 2153 Wichita KS 67201 3. Rust Remover

MIL-M-10578 TT-T-548

4. Toluene

A-A-59107 5.

TT-X-916

Xylene

A-A-59282

6. Solvent

7.

Naphtha

8.

Dry cleaning

Methyl Propyl

Ketone

Obtain Locally

TT-N-95 Type II solvent

9. Kerosene

P-D-680

Type

III

VV-K-21 1 ASTRTM-D3699

10. Acetone

11.Cleaning Solvent

ASTM D-329

MIL-PRF-680, Type 1

Acetone Stoddard Solvent

(Mineral 12. ChemicalConversion

Coating for Aluminum and Aluminum Alloys

MIC-DTL-81706 per MILDTL-5541

Obtain Locally

or

White

Obtain

Locally

Spirit)

Alodine 1200, 1200S, 1201, 1203 and 600

Corporation Aerospace Surface Henkel

Treatment 32100

Stephenson Highway Heights

Madison

M148071

A25

20-09-00

Feb

1/09Page

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

MAINTENANCE PRACTICES

CORROSION

CORROSION PREVENTION Preventative maintenance provides the only substantial control over corrosion. The following procedures are used Initially, the airplane must be thoroughly cleaned to rid it of impurities such as salt, dirt, urine

to control corrosion.

spray, and exhaust deposits. Secondly, external and internal inspections must be made for various forms of corrosion. Thirdly, if corrosion is found, the area should be cleaned of all corrosive substances and treated in a manner

prescribed

for the individual metals.

CORROSION CONTROL degree or rate of corrosion is dependent on the temperature of the atmosphere and the quality of impurities present such as dust, salt, smoke, etc. Other variables that affect the degree of corrosion are material section size, type of material, material heat treatment, and quality of corrosion-preventive maintenance. Good preventative maintenance and regular cleaning are the most effective methods of corrosion control. The

CORROSION CLEANING the airplane serves the purpose of eliminating foreign deposits and prepares the surface for corrosion inspection. Either of two types of cleaners, solvents, and alkaline base cleaners may be utilized in hand-cleaning or spray-cleaning. The airplane may be cleaned by degreasing using vapor, solvent cleaning, abrasive cleaning, or

Cleaning

alkaline water cleaning. The most practical cleaning cleaning operation to be performed. The solvents listed in Chart 1,

contaminants

on

Chapter 20-09-00,

method should be used

may be used to

remove

dependent

upon the nature of the

grease, oil, stains and other surface

most materials.

WARNING: Do not

use

solvents in

chlorides areas

on

titanium. Do not

close to the oxygen

use

exotic solvents

on

composites.

Do not

use

any

system.

SAFETY PRECAUTIONS

Cleaning procedures require the use of volatile chemicals burns. The.following precautions must be observed: a.

Protective

clothing

protection, etc., b.

Chemical

c.

If chemicals

d.

and

produce

toxic vapors and/or

skin

cause severe

equipment such as rubber gloves, aprons, boots, air respirators, appropriate provide adequate safety protection for personnel.

eye

must be used to

compounds coming

in contact with the skin should be washed off

are splashed in the eyes, flush receive immediate medical attention.

Many

which

of the chemicals

are

promptly

and

thoroughly

immediately

with water. The

flammable and should be used in well ventilated

areas

with soap and water.

injured person

should

away from sparks and/or

an

open flame. e.

The and

airplane and removed parts from the airplane painting will produce static electricity.

f.

Smoking

g.

Avoid be

n25

is not

breathing

permitted

in the

solvent vapors

must be

statically grounded. Cleaning, corrosion removal,

area.

as

much

as

possible.

In

areas

of

heavy

vapor concentrations,

respirators

must

worn.

20-09-00

Page

beF102

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

h.

Tools used made of

i.

inopening and closing spark-proof material.

Electrical equipment, including flashlights, operated accomplished, shall be an explosion-proof type. Any operated in the area while work is being performed.

j.

Personnel

k.

Rags

area

shall have

wet with solvent or solvent

purpose I.

in the

working

mixing

containers of these materials and used in

no

metal

area in which cleaning and painting is being equipment capable of producing a spark must

in the other

objects

containing coating

these materials must be

on

their shoes

shall

or

wear

material shall be discarded in

a

shoe

not be

covers.

container

specified

for this

only.

Any part capable

of

producing sparks, such as metal stands, steel drums, etc., must not be dragged across or platforms having rubber or plastic wheels must be statically grounded.

a

concrete floor. Work stands m.

involving the use of spark producing tools or motors shall be performed assembly until the coating is dry and free from concentrated solvent vapors.

n.

Solvents must be

No work

dispensed

in

safety

on a

freshly

coated part

or

containers.

VAPOR CLEANING

Vapor degreasing

parts may be used when the proper equipment is available.

of

Vapor degreasing is one of the preferable methods for cleaning metal conversion and organic finishes. Vapor degrease the parts as follows: a.

Place the part in

NOTE: When the

a

surfaces

prior

to the

part is severely contaminated by grease and oil, wipe off the part using or

other

Severely contaminated parts, tubings

and assemblies should be cleaned

c.

Place the

vapor condenses

d.

Remove the part from the vapor tank and cool

a

vapor tank until

are

clean after two

no

not clean should be

on

completely

recycled through

the

a

cloth moistened with

approved solvent.

b.

NOTE: Parts which

of chemical

vapor tank to eliminate vapor loss.

acetone, solvent, (10, Chart i, Chapter 20-09-00)

part in

application

by´•spray-cleaning

with solvent.

part.

until the solvent has

the steps

evaporated.

again. Chemically

clean if the parts

are

not

cycles.

SOLVENT CLEANING When vapor degreasing is not feasible because the part is too large to use a vapor tank, cleaning can be performed by means of immersion or hand wiping. For hand wiping, generous amounts of fresh solvent and clean cloths must be used. KEROSENE Kerosene

can

be used for

cleaning

when

a

slight

oil film is

required

for corrosion

protection.

DRY CLEANING SOLVENTAND TOLUENE

These materials

are

used for removal of

surfaces, where hand wiping

Page

can

be

oil, grease and inspection marks and

are

suitable for

cleaning

wide

easily performed.

20220-09-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

NAPHTHA AND METHYL PROPYL KETONE CAUTION: Do not

sparks These materials and then

they

Naphtha (6, Chart I, Chapter 20-09-00)

use or

are

and solvent

(6, Chart 1, Chapter 20-09-00)

near

open flame.

used

only when other cleaning provided the parts clean

may be used

solvents with

no

are

not suitable because the

drying

time is too

long,

deterioration.

ABRASIVE CLEANING If

dirt, rust, and scale

cannot be removed

by alkaline cleaning,

abrasive

cleaning

may be used to clean metallic

cleaning may not be used to clean plates of aluminum alloy, magnesium alloy, precision finished surfaces.

NOTE: Abrasive and

Two methods of abrasive

cleaning

can

be used: blast abrasive

cleaning

and manual abrasive

parts.

machined surfaces,

cleaning.

BLASTABRASIVE CLEANING Clean the surfaces

using aluminum oxide abrasive with a nozzle pressure (457 to 610 mm) from the surface being cleaned.

not

exceeding

70

psi. The

nozzle should

be held 18 to 24 inches

MANUAL ABRASIVE CLEANING Manual abrasive

cleaning

is

usually performed using

CAUTION: A wire brush must not be used to clean

abrasive paper

alloy surfaces

or

cloth, 280 grit for rough and 400 grit for fine.

to avoid scratch

damage

to the surface.

ALKALINE WATER CLEANING

preferred for cleaning large parts removed from the airplane. If the parts are extremely dirty, washings may be required. Accomplish the cleaning using an alkaline base MIL-C-25769 cleaning compound. Steam cleaning is not to be used. Apply the solution to the surface using the following procedure:

An alkaline solution is

several

CAUTION: When

cleaning

hinged part, cleaning solution must be removed from the hinge pin holes. Extreme remove cleaning solution from the skin splices, fastener heads, or other areas where the solution may be trapped. These areas may be blown dry with clean dry air. When cleaning honeycomb or other bonded areas, prevent excess cleaning solution from contacting the bonding care must

a

be taken to

adhesive. the

cleaning

solution in liberal

quantities

to the surfaces with clean brushes or cheesecloth.

a.

Apply

b.

Allow the solution to stand for five minutes and then scrub with

NOTE: If the solution dries c.

d.

Remove the If

some

of the

dry cleaning

n25

cleaning areas

solvent

on

the surface,

solution with

remain

(11,

dirty

a

apply

more

cleaning

a

clean, nonmetallic fiber brush.

solution before

scrubbing.

clean cheesecloth and clean water.

oily, lightly scrub the area with a piece of clean cheesecloth dampened with Chapter 20-09-00). Rewash any area with this solvent.

or

Chart 1,

20-09-00

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

I

CORROSION INSPECTION damage requires inspection to determine the depth of penetration and the cross-sectional area of change. damaged area must be thoroughly cleaned. If deterioration has significantly reduced the structural strength of a part (e.g., a reduction of thickness more than 5%), the component must be repaired or replaced. Upon completion of the clean-up or repair, all elements must be treated and refinished as applicable. In all instances, good preventative maintenance and regular cleaning will be the most effective corrosion control. Corrosion The

ALUMINUM CORROSION REMOVAL Corrosion may be removed mechanically or chemically. In mechanical removal, it is essential that the abrasive material on the tool leave no residue or particles that could cause future corrosion. An abrasive previously used on ferrous metals will contain minute A steel wire brush used

on

particles which will imbed in aluminum alloys and start a new cycle of corrosion. alloys will leave tiny particles sufficient to initiate corrosion of the aluminum.

aluminum

alloy parts, corrosion is best removed with aluminum oxide abrasive paper or aluminum wool. On clad alloys, use a chemical alkaline cleaner. Mix and store alkaline solutions in plastic, stainless steel, or glass containers. Mask off all dissimilar metals as well as all cracks and sheet laps. Apply cleaner with a soft brush. Rinse thoroughly with clean water and dry with compressed air. On aluminum aluminum

WARNING:

Always wear

rubber

gloves

and

protective clothing

when

working with

acids. A face mask may

be necessary, depending upon ventilation in the area. If acid accidentally contacts skin immediately flush with fresh water and seek medical advice.

or

eyes,

REMOVAL OF CORROSION FROM ALUMINUM SURFACES

Strip

b.

Mechanically

c.

Inspect the surface carefully

d.

Clean the corrosion removed

all

paint

from the surface

a.

remove

(12,

Chart 1,

1.

Rinse the treated

NOTE: 2.

corrosion

directed under STRIPPING AND CLEANING URETHANE PAINT.

by sanding

or

rubbing

as

necessary.

to ensure that sufficient material remains to area

with

a

satisfy

structural

requirements.

chemical alkaline cleaner. Treat all aluminum surfaces with

coating

Chapter 20-09-00).

If cold

area

running

Brush 2 coats

reworked

as

(a

area.

in COLD

water is not

running

water and

in

an oven or

by exposure

available, rinsing may be eliminated and the

apart) of primer (2, adequate penetration of primer into

minimum of 30 minutes

Assure

dry

Chart 1,

area

to hot air blast.

dried

Chapter 20-09-00).

the treated

as

on

stated above. and around the

area.

ALUMINUM CORROSION TREATMENT After corrosion removal and surface treatment of aluminum

adhesion of the

Page

alloys

forms

cleaning, metals should be given protective treatment and painted. Alodine protective coating which resists corrosion and provides a good surface for

a

paint primer.

20420-09-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

WARNING: Brushes and cloths should not be left in the alodine solution. The should be washed after

immediately

If such items

use.

are

left to

dry

in the open

air, they could

create a fire hazard.

CAUTION: Keep the alodine solution confined to the affected area. mask or seal all cracks and crevices, all steel parts, and any mechanical components. Wash all brushes and cloths immediately after use to prevent inadvertent contact with the acid solution and to eliminate without

dry

being

a

possible fire hazard from

such materials that

washed.

coating (12, Chart 1, Chapter 20-09-00) or equivalent, when mixed 2 ounces per gallon of acceptable treatment material. Mix only in rubber, plastic or stainless steel containers. Alodine 1200 series products contain fluorides that should not be mixed in glass containers. Coat the area with the Alodine solution and allow the coating to dwell for approximately five minutes. After the dwell time has elapsed, wash the area with water and blow dry (Do not wipe dry). Paint the coated area with primer (2, Chart 1, Chapter 20-09-00) and allow to dry. Chemical conversion

water, will be

an

MA GNESIUM ALLOY CORROSION TREA TMENT After corrosion removal and surface Section

9),

the

"Dow 19" is not available a.

must be

component

as a

cleaning of a magnesium alloy component (Ref. FAA AC43.13-1B, Chapter 6, given a protective coating using "Dow 19".

prepared "ready-to-apply"

gallon of distilled water polyethylene container which will Place 3/4

of chromic acid

b.

Add 1.33

c.

Add distilled water to make 1

d.

Leave the solution for

ounce

a

at 700 to 900F

mixture but

can

(21.1" to 32.2"C) gallon of fluid.

in

be made up a

as

follows:

stainless steel, aluminum

or

vinyl

measure/hold 1

(CrO),

gallon

then 1

ounce

of calcium

of solution and stir

further 15 minutes

prior

to

sulphate (CaSO)

vigorously

decanting

into

to the distilled water.

for at least 15 minutes. a

suitable

polyethylene oi glass

container.

by brush, swab or flow on using low-pressure spray (non-atomizing) until the metal surface (the color can vary from green-brown, brassy, yellow-brown to dark brown dependant upon supplier provided materials). For good paint adhesion, a dark-brown color, free of power should be obtained. Apply

the solution

becomes

a

dull color

Observe the

coating closely during

free of loose

changes. Rinse with cold running water and allow to air dry satisfactory coating is uniform in color/density, adheres well and is

treatment for color

when the desired condition/color is achieved. A

powder.

STEEL CORROSION REMOVAL

usually preferred to remove corrosion from steel parts by steel wool, or 400-grit abrasive paper may be used. It is

WARNING:

mechanical

means.

A steel wire brush,

a

steel scraper,

gloves and protective clothing when working with acids. A face mask may be necessary, depending upon ventilation in the area. If acid accidentally contacts skin or eyes, immediately flush with fresh water and seek medical advice.

Always

wear

rubber

If acid cleaning must be used, it is essential that all plated areas, operating mechanisms, braided lines, or material laps which could trap the acid be adequately masked. Mix one part of metal conditioner and rust remover (3, Chart 1, Chapter 20-09-00) part of clean water in a stainless steel, plastic or glass container. Apply solution to the corroded area using an acid-resistant brush. Allow to stand one minute, then thoroughly rinse with hot water and wipe dry.

n25

20-09-00

Page

beF502

1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

In most cases, steel that has been cleaned shall be treated with

(2, Chart 1, Chapter 20-09-00)

to

a

minimum of

one coat

of

primer

protect against future corrosion.

CORROSION PROTECTION

subject to corrosion in varying degrees. Airplane parts are protected against corrosion by airplane aluminum alloy sheet has a thin cladding layer of pure aluminum (ALCLAD) applied at the mill. Other aluminum alloy parts may be protected with an anodic coating system or chromate treatment. Many steel parts are protected by cadmium plating. Most parts have protective primer.

All

common

metals

are

several methods. Most

Page

20620-09-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SEALING/BONDING- DESCRIPTION The instructions for

sealing

adhesives listed in the charts

and

bonding the airplane and components by Hawker Beechcraft Corporation.

used

are

The

in this chapter. The sealers following is a list of the charts

and and

I

as meeting federal, military or supplier specifications provided for reference only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification may be used subject to availability. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or compliance to the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE REQUIREMENTS OF A SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

I

the

applicable

are

use.

Chart 201

i-Part Sealers

Chart 202

2-Part Sealers

Chart 203

Rubber-to-Rubber Adhesives

Chart 204

Rubber-to-Metal Adhesives

Chart 205

Rubber-to-Acrylic

Chart 206

Metal-to-Metal Adhesives

Chart 207

Textiles-to-Textiles

Chart 208

Insulation-to-Metal Adhesives

Chart 209

Honeycomb

Chart 210

Aerodynamic

Chart 211

Metal Primers

Chart 212

Coatings

Chart 213

Sound Deadeners

Chart 214

Potting Compounds

Chart 215

Supplier Listing

or

Panel

Acrylic-to-Acrylic

or

Adhesives

Textiles-to-Metal Adhesives

Edge

Filler Adhesives

Smoothers

RECOMMENDED MA TERIALS The recommended materials listed in Chart 201 thru Chart 214 are

nz2

20-10-00

May

1/07Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR 8300/8300C SERIES MAINTENANCE MANUAL

SEALING/BONDING

fuselage

The

leakage. Most

following

The

is sealed to

other sealed

MAINTENANCE PRACTICES prevent air loss for airplane pressurization. The fuel cells are sealed areas are sealed to protect the airplane from damaging elements.

instructions aid in

to

prevent fuel

resealing the airplane:

a.

Two part sealers should not be six months old when used.

b.

Sealers which have been premixed and flash frozen should be maintained at -40"F or lower and should not be received more than two weeks beyond the date of mixing. These sealers should not be used more than six weeks after the date of

c.

which does not

time of the sealer. 60 to 80"F at the

room

than

temperature before being used. Frozen sealer may be defrosted by any

contamination

cause

or

overheating

of the sealer and does not shorten the

Defrosting temperature time the sealer is applied.

and time should be

adjusted

application give the sealer a temperature between

to

d.

Frozen sealers which have been defrosted should not be refrozen.

e.

Surfaces must be clean and dry, free from dust, lint, grease, chips, oil condensation other contaminating substances prior to the application of sealer.

f.

Naphtha Type II transparencies.

g.

Sealers may be applied to unprimed

or

more

mixing.

Frozen sealers should be at means

than two months old when obtained. The sealer should not be

more

Isopropyl

Alcohol

(TT-I-735)

or

are

the

only

or

other moisture and all

cleaners which may be used

primed surfaces, primer

must be

applied

on

48 hours

plastic

prior

to sealer

application. h.

Sealers should not be applied when the temperature of either the sealer

i.

PR1425B-1/2

j.

Sealers applied by brush coat method should always be applied

k.

After

I.

Extruded sealer should be evident around the

or

8-2

(Ref. Chart 202)

application, all sealers should

are

the

Any

n.

Sealer should not be applied

pressure

testing

On sealers to be

o.

over

the cleaned

should not be

applied area.

over

over

sealers

ink, pencil

primed

areas

on

the

plastic transparencies.

pressurized

pressed into the

structure is below 60"F.

I

side of the seal.

seam or

joint.

fastener to indicate

adequate sealing.

until the sealer has cured to the manufacturer’s instructions.

or wax

(grease) pencil

from which the

exposed

airplane

use on

complete periphery of the rivet shank before bucking.

attempted

Touch up the

for

approved

be smoothed down and

Sealer should be wiped from the end of the m.

only

or

areas

with

primer

primer

marks.

was

removed

during cleaning, seal directly applied and is tack

after the sealer has been

free.

p. q.

Sealed components should not be handled

Drilling

holes and

installing

fasteners

or

through

moved until the sealer is not a

sealed

area

shall be

tacky when

performed during

touched. the

working

life of the

sealer. NOTE: The surface to receive the sealer

application

must be clean for proper sealer adhesion. a surface.

Any type of

oil

or

contamination will not allow the sealer to adhere to

nzz

20-~ 0-00

Page

yaM102

1/07

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

SURFA CE PREPARA TION FOR BONDINGISEALING The surface may be

prepared

as

follows:

any burrs from around the holes and between any material.

a.

Drill all holes to their proper size and

b.

Remove any previously applied sealer. Use a plexiglass or stiff plastic scraper and a rag dampened with methyl propyl ketone (metal surfaces) or naphtha (plastic surfaces) to aid in the removal of the old sealer. Do not use

I

metal scraper to

a

remove

remove

the old sealer. Do not

use

methyl propyl

ketone

Wipe the surface clean with a clean white cloth dampened with methyl propyl (plastic surfaces) and wipe dry. Let the solvent air dry after wiping. d. e.

Wipe the surface clean with If zinc chromate

a

on an

acrylic

ketone

scraper.

(metal surfaces)

or

naphtha

clean white cloth.

primer was removed during the cleaning, reprime the surface with zinc chromate primer, dry for 48 hours. Reclean to remove the excess primer and any overspray.

TT-P-1757. Allow to

I

SEALERIADHESIVE PREPARA TION The time needed to

determining

complete the repair and the work

time of the sealer/adhesive

are

important factors

in

the proper sealer/adhesive.

NOTE: The manufacturers recommendations and instructions must be followed at all times. Frozen sealer/ adhesive cannot be refrozen. 2

Any from

part sealer/adhesive must be mixed with the base

a

or

catalyst

it

was

with. The base

shipped

order should not be used unless the batch number of the base and

previous

catalyst

are

or

the

catalyst left

same.

The 2

follows:

part

sealers/adhesives may be mixed

a.

Using

b.

Before removing any catalyst, stir the catalyst with a clean spatula. Discard the spatula. Using a clean spatula, weigh the correct amount of catalyst in the cup with the base. Do not allow the catalyst to touch the side of the mixing cup or spill during the weighing or mixing of the sealer/adhesive.

c.

Hand mix the base and

a

clean

spatula, weigh

as

out the proper amount of base

catalyst together

required for

the

repair

until the mixture is uniform in color with

in

no

a

clean

streaks

wax

or

free cup.

lumps.

SEALERIADHESIVE APPLICA TION The sealer/adhesive may be a.

applied

as

follows:

Ensure the surface is clean and free of oil

or

contamination

as

instructed under the

heading

"SURFACE

PREPARATION FOR BONDING/SEALING".

I" c.

Apply sealer/adhesive Figure 201 and 202).

1/32-inch thick to the cleaned surface

using

a

spatula

or

air pressure

applicator (Ref.

part in place and install temporary or permanent fasteners. If temporary fasteners are installed, enough pressure must be applied to ensure solid contact of the surfaces with no gaps existing in the applied Place the

sealerl adhesive. NOTE:

Any

fasteners to be installed in the

installation.

May

107Page

202

20-~ 0-00

airplane pressurized

area

must be

dipped

in sealer before

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

2

3

~I

2

1.

2. 3.

EXTRUDED ASSEMBLY

FILLETEC.

SEALING SEALING SEALING

SEALANT (MAY BE OR

BETWEEN CONTACT

HOLES.

CONTACT SURFACES ELEMENT EDGES RIVETS AND BOLTS

AFIE~

REMOVED. IF EXPOSED)

FAIRED,

ORIGINAL By As Received ATP

a-----SEkLANT

1/3~

INCH

THICK

C9aLJ20B

Typical Sealer Application

Figure

A22

201

20-1 0-00

Page

yaM302

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

ORIGINAL Pas Received

By

ATP

~..I

SI~IN SKIN

d_~uj7

f

FAY SEAL SKIN ikP

SKIN

FAY SEAL S1
BETWE~N

GETWEEN STRINGER

J/

C94LJ20B1210

C

Typical Faying Sealing Figure 202

Page

20110100

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

d.

All

permanent fasteners required

to

accomplish

the

repair should be installed during the work by the manufacturer of the sealer.

time of the sealer.

The recommended work time of the sealer is established

NOTE: Fasteners with torque requirements must be torqued to final torque requirements during the recommended work time of the sealer. The nut should be turned to take torque readings if possible. No

torque may be applied after the sealer has reached the maximum recommended sealer work time. It is recommended that torque sealer, either EC1252 or F900, from Chart 201 be applied to all torqued fittings and fasteners after the final torque has been applied.

I

SEALING AND BONDING hAA TERIAL CHARTS NOTE: The

following

by Hawker Beechcraft Corporation. The Chapter. Cure per the unless other temperatures are given.

Charts 201 thru 214 contain the materials used

number in the "SUP." column indicates the

supplier listed

manufacturers recommendations. Cure time is at 77"F

in Chart 215 of this

Chart 201 1-PART SEALERS

MATERIAL

SUP.

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

SOLVENT

REMARKS

Permatex No. 2

1.

Soft sealing compound for gaskets.

576 Presstite

4.

Caulking compound.

Scotch-Seal and

5.

Weatherban 2084

24 Hrs.

MPK

(1/8" bead)

Naphtha

or

Sealer for skin and window

laps

glass.

Not to be used with

Plexiglas or any plastic surfaces. EC776 SR

5.

1

I

I MPK

I

Used under flush rivet heads

I

the

on

fuselage. PR810

6.

72 Hrs. at

MPK

PF5422

EC1252

sealer.Extruded Tape

5.

Tamper

5.

Proof Sealer

Used to seal hot air ducts.

75"F

1

I

I

IMPK

Form

Used to mark torque and fasteners

fittings

after final torque has been applied. F900

Torque

Seal

7.

Used to mark

fittings

torque

and fasteners

after final

torque has applied. Available in a variety been

of colors.

nzz

20-~ 0-00

Page

yaM502

1/07

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 202 5-PART SEALERS

(Ref. MATERIAL

Pro-Seal 700

SUP.

NOTE

Chart

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

90 Min.

SAE-AMS 3374

6.

preceding

Type

I

1

SOLVENT

72 Hrs.

REMARKS

Firewall connector,

MPK

I

I

I

hole and crack sealer. Withstands

2,000"F for 15 minutes.

Pro-Seal 860

SAE-AMS-S-83318 I

6.

I

I Cabin and fuel cell

I

fast

cure

sealer for

quick repairs. PR14258-1/2

Cabin window

24 Hrs.

30 Min.

6´•

sealer. PR1425B-2

2 Hrs.

6.

Cabin window

48 Hrs.

sealer.

PR1435

6.

1

I

I

I

Cabin and fuel cell

integral quick repair

sealer. PR1440A-1/2

6´•

30 Min.

SAE-AMS-S-8802

Cabin and

30 Hrs.

integral

fuel cell sealer. PR1440A-2

6.

SAE-AMS-S-8802

2 Hrs.

Cabin and

72 Hrs.

integral

fuel cell sealer. PR14408-1/2

6.

30 Min.

SAE-AMS-S-8802

Cabin and

30 Hrs.

integral

fuel cell sealer. NOTE

PR1440B-1/2 is the sealer PR14408-2

6.

applied

at windshield

(Ref.

SAE-AMS-S-8802

EROSION PREVENTION SEALANT,

2 Hrs.

Chapter 20-08-00). Cabin and

48 Hrs.

integral

fuel cell sealer.

Chart 203

RUBBER-TO-RUBBER ADHESIVES

(Ref. MATERIAL

R-380-6

SUP.

9.

NOTE

preceding

Chart

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

MMM-A-132

50 Min.

SOLVENT

REMARKS

24 Hrs. at

77"F,

or

1

Hr. at

200"F

Page

20620-~ 0-00

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 203

RUBBER-TO-RUBBER ADHESIVES

(Ref. MATERIAL

SUP.

NOTE

APPLICABLE SPEC

preceding

Chart

(Continued) 201)

WORK

CURE

TIME

TIME

SOLVENT

EC678

5.

MIL-PRF-9117

MPK

Scotch-Grip 847

5.

MMM-A-1617

Acetone

Bostik 1009A with

13.

MMM-A-121

MPK

MMM-A-1617

MPK

REMARKS

Bostik 10088 5.

Scotch-Grip 1300L

Scotch-Grip

1357

5.

Type Scotch-Grip 5452

5034

Hadley

Vangrip

14-30

II

5´•

Water

10´•

MPK

39.

MPK

Chart 204 RUBBER-TO-METAL ADHESIVES

(Ref. MATERIAL

SUP.

NOTE

preceding

Chart

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

SOLVENT

Pliobond No. 20

11´•

MPK

Pliobond HT30

11´•

MPK

Scotch-Grip

847

Bostik 1009A with

5.

MMM-A-1617

Acetone

5.

MMM-A-121

MPK

MPK

REMARKS

13.

Bostik 10088

Scotch-Grip 1300L

Scotch-Grip

1357

5.

MMM-A-121

Scotch-Grip

2141

5.

MMM-A-1617

5452

Hadley

Vangrip

A22

14-30

Type

Toluol

10´•

MPK

39.

MPK

20-~ 0-00

Page

yaM702

1107

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 205

RUBBER-TO-ACRYLIC OR ACRYLIC-TO-ACRYLIC ADHESIVES

(Ref. SUP.

MATERIAL

NOTE

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

REMARKS

SOLVENT

Does not discolor

8 Hrs.

25 Min.

15.

PS30

Chart

preceding

like PS18.

I

Resin/HW8680

A fast

24 Hrs.

15 Min.

16.

AW8680

curing

I

I urethane adhesive.

I

I

I

I

I

I

I Apply

I

I

I

1 0.001- to 0.003-inch

I

I

I

I

I

1 I

Hardener

I

A fast

24 Hrs.

10 Min.

11.

Pliogrip 7779 Polymer/7779

curing

urethane adhesive.

Curative 17.

Bond Master

I

G590

adhesive

thick. Two

may be

layers applied on

porous materials. The bond should be made after 10 minutes and before 45

minutes. Bonds

immediately upon Light

contact to itself.

pressure should be

applied contact

for

complete during cur-

ing. Scotch-Grip

5034

5´•

1

I

I

I\l\later

Used where are

to

sparks possible. Allow

dry

20 to 30 min-

utes before

joining

surfaces. Uralane 5776 A/B

Page

18.

20-~ 0-00

30 to 40

5 to 7

Min.

Days

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 205 RUBBER-TO-ACRYLIC OR ACRYLIC-TO-ACRYLIC ADHESIVES

(Ref. MATERIAL

Cyclehexanone or Tetrahydrofuran

SUP.

NOTE

(Continued)

preceding Chart 201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

SOLVENT

Used

4 Hrs.

19´•

REMARKS

as

solvents in

well ventilated

away from

areas

sparks

and open flame, to bond "Tygon" tubing to

"Tygon" tubing. tubing to

Allow

soften, then press the two softened ends together. Hold together until solvent dries.

Chart 206

METAL-TO-METAL ADHESIVES

(Ref. MATERIAL

SUP.

NOTE

preceding

201)

Chart

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

REMARKS

SOLVENT

NOTE

Positioning EASO1NA/B-1

fabric should be used when

metal to metal.

bonding

Only

12 Hrs.

21.

contact

pressure is required. Assemble parts

immediately. EA934NA

21.

40 Min.

24 Hrs. at

77"F,

or

1 Hr. at 200"F

EA9309NA

21.

40 Min.

24 Hrs. at

77"F,

or

1 Hr. at

200"F RTV 106

2.

MIL-A-46106

24 Hrs.

Can withstand 600"F

(1/8"

for

a

short time.

bead)

A22

20-1 0-00May

1/07

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 206 METAL-TO-METAL ADHESIVES

(Ref. SUP.

MATERIAL

Epon

NOTE

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

21.

828

(Continued) 201)

Chart

preceding

SOLVENT

REMARKS

Contact pressure required for

8 Hrs.

30 Min.

approximately6 hours. No stress may be applied for 48 hours. 5.

Scotch-Grip 847

Not to be used where

Acetone

MMM-A-1617

strength of over psi is required. Bostik shear

100

I I

I

I

I

I

I

I

1007M is the

recommended

primer. Scotch-Grip A

I

2216

5.

2 Hrs.

24 Hrs.

"A"

B

or

type sealer in

gray color. "B" type sealer in white color.

Scotch-Weld 3549

5.

10 to 15

5 to 7

Min.

days

Chart 207

TEXTILES-TO-TEXTILES, TEXTILES-TO-METAL ADHESIVES

(Ref. MATERIAL

SUP.

NOTE

Chart

preceding

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

SOLVENT

I

Weld-On 1707

I

Scotch-Grip

847

5.

I

Scotch-Grip

1099

5.

1

I

I

I MPK

1

45518

10.

1

I

I

I MPK

REMARKS

35.

Hadley

Acetone

MMM-A-1617

Good

on

light

colored leathers.

I

Vangrip

39.

14-31

1

I

I

I MPK

Good

on

light

colored leathers.

I IEC1781

5.

I IEC2141

5.

IScotch-Grip

Page

yaM012

1107

2262

5.

1

I MMM-A-1617

1

20-~0-00

I

Type

I MPK Toluol

I

I

I MPK

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 207 TEXTILES-TO-IEXTILES, TEXTILES-TO-METAL ADHESIVES

(Ref. MATERIAL

Barge

SUP.

Rubber

36.

NOTE

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

1

(Continued)

preceding Chart 201)

I

SOLVENT

I

REMARKS

Can be used

I Naphtha

Cement

I

over

zinc chromate

pri mer.

Chart 208 INSULATION-TO-METAL ADHESIVES

(Ref. MATERIAL

Scotch-Grip 77 Spray

44

SUP.

or

NOTE

preceding

Chart

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

SOLVENT

REMARKS

Naphtha

5.

Adhesives

Scotch-Grip

2141

5.

Scotch-Grip

4550

5.

MMM-A-1617

Toluol

Type

1

I

I

I

I

I I

I

I

Chart 209 HONEYCOMB PANEL EDGE FILLER ADHESIVES

(Ref. MATERIAL

Epi-Bond

104

SUP.

NOTE

preceding

201)

Chart

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

45 Min.

26.

SOLVENT

REMARKS

Aluminum

10 Hrs.

powder

may be mixed into the filler for

appearance. R-380-6

9.

MMM-A-132

50 Min.

24 Hrs. at

77"F,

or

Clean metal with Enviro Clean A2904

1

before

Hr. at

applying

filler.

200"F EA960 F

21.

30 Min.

24 Hrs. at

77"F,

or

1

Hr. at

160"F Devcon F

28.

45 Min.

3 Hrs.

Flex may be added a non-brittle

for

smoother.

A22

20-10-00May

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 209 HONEYCOMB PANEL EDGE FILLER ADHESIVES

(Ref. MATERIAL

White Star

SUP.

NOTE

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

29.

(Continued)

preceding Chart 201)

3 Min.

SOLVENT

30 Min.

REMARKS

Do not allow solvents to

come

into contact

with mixed smoother.

Chart 210 AERODYNAMIC SMOOTHERS

(Ref. MATERIAL

Epi-Bond

104

SUP.

NOTE

preceding Chart 201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

26.

45 Min.

SOLVENT

10 Hrs.

REMARKS

Aluminum

powder

may be mixed into the filler for

appearance. R-380-6

9.

1 MMM-A-132

50 Min.

24 Hrs. at

77"F,

or

1

Clean metal with Enviro Clean A2904 before

Hr. at

applying

filler.

200"F EA960 F

27.

30 Min.

24 Hrs. at

77"F,

or

1

Hr. at

160"F Devcon F

28.

45 Min.

3 Hrs.

Flex may be added a non-brittle

for

smoother. White Star

29.

3 Min.

30 Min.

Do not allow solvents to

come

into contact

with mixed smoother.

Page

yaM212

1107

20-~ 0-00

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 211 METAL PRIMERS

(Ref. MATERIAL

SUP.

13.

Bostik 1007M

NOTE

preceding

Chart

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

1

I

SOLVENT

I

I

REMARKS

Adhesive

primer for

metal, fiberglass and coat of

primer. Each primer should

dry for

at least 30

epoxy

minutes.

Zinc chromate

primer

should be

reapplied

on

any

exposed

metal that

was

previously

coated with zinc chromate

primer.

Chart 212 COATINGS

(Ref. MATERIAL

EC776 SR

SUP.

5.

NOTE

preceding

Chart

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

REMARKS

SOLVENT

Methyl Isobutyl

SAE-AMS-S-4383

Sealer overcoat for fuel cells.

Ketone

Uralane 8267

Printed circuit board

24 Hrs.

26.

protection.

Chart 213 SOUND DEADENERS

(Ref. MATERIAL

Coating R1931

931 and

SUP.

40.

NOTE

preceding

Chart

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

REMARKS

SOLVENT

Water based,

non-flammable, non-toxic, corrosion resistant.

A22

20-~ 0-00

Page

yaM312

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 214 POTTING COMPOUNDS

(Ref. MATERIAL

CS-3100

SUP.

NOTE

preceding

Chart

201)

APPLICABLE

WORK

CURE

SPEC

TIME

TIME

SOLVENT

REMARKS

MIL-PRF-8516

37.

Potting compound for electrical connections.

AC-521

MIL-PRF-8516

38.

Type Type Type

I

Potting compound

II Class 1

30 Min.

22 Hrs.

for electrical

II Class 2

60 Min.

44 Hrs.

connections.

II Class 3

120 Min.

70 Hrs.

SUPPLIER INFORMATION CHART

Chart 215 SUPPLIER LISTING SUPPLIER NO.

SUPPLIER NAME

II’

Permatex

1 12

Silicone Products

(a

brand of ITW

SUPPLIER ADDRESS 30 Endicott Street

Devcon)

Danvers, MA 01923

Department, General

Electric

Company

Hudson River Road

Waterford, NY 12188 3901 S.

Coming Corporation

II"

Dow

1 14

Inmont

Saginaw

Road

Midland, MI 48640 3738 Chauteau Ave.

Corporation

St. Louis, MO 63110 3M Center

Company

II"

3M

II~ II’

PRC-Desoto International, Inc.

St. Paul, MN 55144-1000

P.O. Box 1800 5454 San Fernando Road

Glendale, CA 91209

Organic

Products

1963 E.

Company

Irving

Blvd.

P.O.Box170428

Irving,

8.

Special Chemicals Division, Coast Pro-Seal, Corporation

1 19´•

Composite

Material

Essex Chemical

Department, Ciba-Geigy Corporation

TX 75060-4555

19451 Susana Road

Compton, CA

10910 Talbert Ave. Fountain

Page

yaM412

1107

20-~ 0-00

90221-5713

Valley,

CA 92708

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 215 SUPPLIER LISTING

SUPPLIER ADDRESS

SUPPLIER NAME

SUPPLIER NO. 10.

(Continued)

Hadley Adhesives Division, Sherwin-Williams Company

2827

Breckenridge

Industrial Court

St. Louis, MO 63144-2811 11.

12.

Specialty Chemicals Company D Aircraft Products

Adhesive Division, Ashland Chemical

PO Box 2219

Columbus, OH 43215 1191 Hawk Circle

Company

Anaheim, CA 92708 13.

Bostik Division, USM

Corporation,

a

subsidiary

of Emhart

14.

Rohm and Haas

211 Boston Street

Middleton, MA 01949-2128

Industries, Inc.

Company

712 Locust Street

Philadelphia, 15.

I

Cadillac Plastic and Chemical

PA 19106

15111 Second Ave.

Company

Detroit, MI 48203 16.

Ren Plastics Division,

5656 S. Cedar Street

Ciba-Geigy Corporation

Lansing, 17.

MI 48910

268 Madison Ave.

Products Division, National Adhesives Inc.

New York, NY 10016 18.

Chemical Products Division, Hexcel

20701 Nordhoff Street

Corporation

PO. Box 2197

Chattsworth, CA 91311 19.

201 S. Cedar

Barton Solvents Inc.

KS 67147

Valley Center, 20.

Union Chemicals Division, Union Oil

Company

of California

2100 E. 37th N.

Wichita, KS 67208 21.

Aerospace-Structural Adhesives,

The Henkel

Group

2850 Willow Pass Road

PO Box 312

Bay Point, 22.

J.G.

Milligan

and

Company

CA 94565-0031

7300 S. Tenth Street

Oak Creek, WI 53154 23.

Kode Inc.,

a

subsidiary of Odetics

2757 Walnut Street

Tustin, CA

Company,

Inc.

92680

24.

Cats Paw Rubber

25.

Paisley

Products Inc.

Chicago,

26.

Vantigo

A&T US Inc.

5121 San Fernando Road W.

Baltimore, MD

Los

A22

1

IL 60600

Angeles,

20-’1 0-00

CA 90039

Page

yalN512

1/07

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 215 SUPPLIER LISTING SUPPLIER NO. 27.

(Continued) SUPPLIER ADDRESS

SUPPLIER NAME

Smooth-On Inc.

1000

Road

Valley

Gillette, NJ 07933

1

ITW Devcon

28

61 Endicott Street

Danvers, MA 01923 29.

Fibre Glass-Evercoat

6600 Cornell Road

Company

Cincinnati. OH 45242 30.

Plastics Division, Dynatron Corporation

500 Permalume PI.

Atlanta, GA 30318 31.

Allied Trade Sales Division, Acme

32.

Anderson Prichard Oil Corporation

Quality

Paints Inc.

Roseville, MI

Liberty

Oklahoma Allied Chemical

33.

Bldg. City, OK

Bank

P.O. Box 1087R

Morristown, NJ 07960 Shell Chemical

34.

Corporation

1 Shell Plaza

Houston, -TX77001

Regal

II"" II""

Plastic

Company,

4405 East Ilth Street

Inc.

Kansas

City,

MO 64127

Barge Cement Division., National Starch and Chemical Corporation

Towaco, NJ 07082-1063

II"’

Chemical Seal Division, Flamemaster

PO Box 1458

II"" II"" II""

Advanced

Corporation

100 Jacksonville Road

11120 Sherman Sun

Chemistry

Technology,

Inc.

Valley,

Way

CA 91352

7341 Anaconda Ave.

Garden Grove, CA 92841

Mid-West Industrial Chemical

Company

1509 Sublette Ave. St. Louis, MO 63110

Mortell

Company

550 N. Hobble Ave.

Kankakee, IL 69001

Page

yaM612

1107

20-~ 0-00

n2z

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

FIBERGLASS REPAIR

repair of fiberglass components should be limited to those areas without an excessive amount of heat. In areas fiberglass is used, with heat reaching a temperature near 300" F (149" C) or above, a special phenolic resinimpregnated fiberglass is used. It is recommended that these parts not be repaired unless there is a shop available which is equipped for this type of fiberglass repair. Field

where

RECOMI\IIENDED II/IA TERIALS as meeting federal, military or supplier specifications are specifically required by Hawker Beechcraft Corporation. Any product only provided be used to the to subject availability. The products included in these charts have been specification may conforming tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or compliance to the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE

The

following

recommended materials listed in Chart 1

for reference

and

are

not

REQUIREMENTS OF THE SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART.

Only

the basic number of each

specification

is listed. No attempt has been made to update the listing to the latest or mechanic to determine the current revision of the applicable

of the technician

revision. It is the

responsibility

specification prior

to usage of the

product

listed. This

can

be done

by contacting

the

supplier of the product

to be

used.

Chart 1

Recommended Materials MATERIAL

A-A-59282

1. Cleaner 2.

Aerodynamic

Smoother

SUPPLIER

PRODUCT

SPECIFICATION

Methyl Propyl EA960F

Ketone

Obtain

locally

Hysol Div Headquarters

Main Office

Olean

NY, 3.

Aerodynamic

Smoother

Epon

828

14760

Shell Chemical 2001

Kirby

Drive

Houston

TX, 77019 4. Hardener

951

M&T Chemicals Inc 5121 San Fernando Rd Los

Angeles

CA, 90039 5. Flex

Flexilizer "T’

Furane Plastics Inc 5121 San Fernando Rd

Los

Angeles

CA, 90039

20-11-00

M~5:Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

FIBERGLASS REPAIR

Fiberglass damage WARNING:

may be repaired

Goggles

and

as

respirators

following appropriate headings.

instructed under the should be

worn

when

cutting

or

sanding fiberglass.

CAUTION: This repair is not applicable for use on air conditioning ducts, heating ducts or interior plastic or fiberglass pa~fs of the airplane. These components are not repairable and must be replaced if damaged.

FIBERGLASS MINOR DAMAGE REPAIR Minor

damage

diameter If the

or

damage

Fiberglass a.

Sand

c.

is

minor

damage

area

may be

area

repaired

45"

a

with

For EA960F

aerodynamic by weight.

d.

Apply

angle

as

repaired

as

instructed under

major damage repair.

follows:

to the

depth required to damaged area.

e.

After 4 hours at

methyl propyl

smoother

(Item

ketone

(Item

remove

room

No. i, Chart

No. 2, Chart 1, 20-1

the mixed resin to the clean sanded surface

all the

damage. Sand

a

1 inch

temperature, sand any high

1-00),

1,20-11-00)

and

larger

wipe dry.

mix 2 parts of brown resin to 1 part of white

area.

smooth with

areas

course

sandpaper.

may be used to accelerate the cure time of the mixture. Cure times are approximate, temperature and relative humidity. DO NOT sand if tacky or rubbery, since the material is not

NOTE: Heat on

which do not break the surface, exceed 1 inch in

around the circumference of the

Clean the sanded

hardener

must be

greater than stated above, the repair

V-cut at less than

or

diameter b.

dings

gouges, and

fiberglass are scratches, depth.

to

0.050 inch in

lamps

depending sufficiently

cured. f.

After the resin has cured at

room

temperature for 8

to 12

hours, sand with 320 grit sandpaper for the final

smoothing. g.

Repaint

if necessary.

FIBERGLASS MAJOR DAMAGE REPAIR CAUTION: This repair is not applicable for

fiberglass pa~fs of the airplane. Major damage

to

fiberglass

is

damage

use on

the air

conditioning ducts, heating

ducts

that extends

through

the

glass

cloth

plies

interior plastic or replaced if damaged.

or

These components are not repairable and must be

but is less than 2 inches in

length

and 1/2 inch wide.

Damage

that exceeds the

made

follows:

as

major damage specifications require part replacement.

NOTE: It may be necessary for of the damaged part. The

aerodynamic

shop area should be clean, fiberglass repair conditions.

,4

smoothness

the temperature

or

The

appearance to install the

approximately

major damage repair

may be

repair glass plies to the

70" F and the relative

humidity

inside

at 50% for ideal

20-11-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I

a.

Clean the

b.

Push down

c.

Remove the

damaged fiberglass by sanding

d.

Remove any

flaky edges

damaged the

on

area

area

with

methyl propyl the

surrounding

ketone

damage or

(Item

No. 1, Chart 1,

20-11-00).

to determine the full extent of the

cutting

angle (Ref. Figure

at a 1 5"

and feather the surface back at 1 5",

approximately

damage.

201

1/2 inch from the cut out

area

(Ref.

Figure 201). e.

I

f. g.

Sand the

area

allow the

glass

Clean with

surrounding the damaged area approximately 1 1/2-inches from cloth patches to lay in the feathered area (Ref. Figure 201).

methyl propyl

ketone

No. 1, Chart 1,

(Item

20-11-00)

and

the

edge.

Feather the

edges

to

wipe dry.

glass cloth plies for the repair. The first ply should be i-inch larger in diameter than the repair area. glass cloth plies should be 1 inch larger in diameter than the preceding ply and should overlap preceding glass cloth ply by 1/2 inch on all sides.

Prepare

the

The additional the

NOTE: A

h.

Apply

the

glass cloth ply may be used for the plies applied to the interior glass cloth ply is recommended for the exterior ply.

mesh

course

repair.

of the

damaged part for this

A fine mesh

glass

plies impregnated with Epon 828 (Item No. 3, Chart 1, 20-11-00) with the smallest patch patch 1 inch larger in diameter than the preceding patch. Work any air bubbles from patches are applied. Mix the Epon 828 (Item No. 3, Chart 1, 20-11-00) resin as described

cloth

first and each additional the mixture

as

the

below: 1.

2.

Epon 828 (Item No. 3, Chart 1, 20-11-00) to 10 parts of 951 hardener(ltem No. 4, Chart 1, 20-11-00) by weight, with 5" Flex T (Item No. 5, Chart 1, 20-11-00) added. Application time is 30 minutes. Mix 100 parts of

Brush the mixture

on

both sides of the

prepared glass

cloth

plies.

Work the mixture

through

the

glass

cloth.

Work the air bubbles to the surface. i.

After the

(Item

glass

cloth

No. 3, Chart

NOTE: Cure times

plies

have been

1,20-11-00)

are

applied on the inner or outer approximately 4-hours.

approximate, depending

since the material has not

rubbery, methyl propyl

with

ketone

side

(Ref. Figure 201), allow the Epon

828

to cure

(Item

on

temperature and relative humidity. DO NOT sand if tacky cured. Sand smooth with

sufficiently 1,20-11-00).

course

sandpaper

and

wipe

or

clean

No. 1,Chart

glass cloth plies may be necessary during the repair. The support may be any object with as the damaged part. Release films should be used to separate the support from the glass cloth plies. Use C-clamps or blocking to hold the support in place. After the material has sufficiently cured, remove the support and sand smooth with course sandpaper.

NOTE: A support for the the

j.

same

Feather the

damaged

I

contour

opposite

Clean with

i.

Brush both sides of

methyl propyl

Step i.,

m.

Center the

n.

Allow to

Page

repair approximately

0.050 inch

deep

and 1 inch

larger

in diameter than the

area.

k.

mixed in

side of the

patch

cure

a

ketone

fine mesh

(Item

No. 1, Chart

glass cloth ply with glass cloth ply.

1,20-11-00) a

mixture of

and

wipe dry.

Epon

828

(Item

No. 3, Chart 1,

20-11-00),

as

and work into the on

the sanded

area

and

remove

for 4-hours and sand smooth with

20-11-00

any air bubbles.

course

sandpaper.

a24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: Cure times

rubbery, o.

are

approximate, depending on temperature sufficiently cured.

and relative

humidity.

DO NOT sand if

tacky

or

since the material has not

After 8-hours, sand with

320-grit sandpaper to

the

original

thickness

(Ref. Figure 201),

to obtain the

required

finish smoothness. p.

n24

Repaint if necessary.

20-11-00

Page

yaM302

1/08

Hawker Beechcraft Corporation SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CRACKED OR DAMAGED AREA

CLEAN DAMAGED AREA OUT

THOROUGHLY

’1’/2 THICKNESS

DAMAGE REMOVAL

AREA SAND AND CLEAN SURROUNDING AREA

BACK SIDE HAS 1 PLY FIRST PATCH

NECESSARY TO OBTAIN ORIGINAL THICKNESS

I SECOND PATCH

THIRD PATCH

(900-SRM-75

Fiberglass Major Damage Repair Figure 201

Page 204 May 1/00

20I11-00

A24

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 20-12-00

ELECTRICAL WIRING - DESCRIPTION AND OPERATION GENERAL CAUTION: Existing wiring should not be removed from the airplane (as much as possible) to minimize additional wire damage. Damaged wiring should be capped and stowed and new wire should be installed in its place. Particular attention should be given to wire insulation compatibility and routing to reduce future wire damage. Information for the inspection of the electrical wiring and the criteria for the repair or replacement of the electrical wiring is contained in FAA Advisory Circular AC 43. 13-1B or subsequent. If wiring is modified, repaired or relocated, it is imperative that it is correctly secured and protected from chafing in accordance with guidelines in FAA Advisory Circular AC 43. 13-1B or subsequent. Particular attention must be given to the following: •

Wiring with sharp bends.

•

Wiring that is close to movable components such as flight control systems and landing gear.

•

Wiring that is close to fluid lines/tubes.

Factory installed conduit, wraps and sleeving, (spiral wrap, Varglas, etc.), used to enclose wire bundles are required for mechanical protection of wiring. Factory installed wire bundle protection is important to minimize the likelihood of chafing damage and should never be left open and unprotected after maintenance. This information is intended to be used as general guidance. Special inspections should be conducted as deemed appropriate by each operator, based on airplane experience. Any discrepancies found should be repaired. Operators and maintenance organizations should make sure that before any maintenance activity takes place which is likely to generate conductive debris, wiring bundles and electrical equipment in the work area are provided with temporary protection against associated contamination. After maintenance is completed, the work area must be specifically inspected to be free from such contamination.

REQUIREMENTS WIRING INSTALLATION If it is required to install cable/harnesses during modifications or routine maintenance the following requirements are to be strictly followed. Wiring shall be fabricated and installed to achieve the following objectives: a. Maximum reliability. b. Minimum interference and coupling between systems. c.

Accessibility for inspection and maintenance.

d. Prevention of damage.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL ROUTING Wires, cables and bundles shall be routed to protect them from the following hazards: a. Chafing. b. Use as handholds, or as support for personal equipment. c.

Damage by personnel moving within the airplane.

d. Damage by stowage or shifting cargo. e. Damage by battery or acid fumes and fluids. f.

Abrasion in wheel wells where exposed to rocks, ice, mud, and heat.

g. Damage by moving parts. h. Damage due to cable or wire movement. SLACK IN WIRE AND CABLE There shall be no excess slack in any wire, cable or harness except to allow: a. Replacement of terminations at least two times. Wire sizes larger than No. 2 copper shall have slack for one replacement. Excess slack shall be in the area of the terminations. b. Replacement of one connector. Slack shall be provided in the area of the connector. c.

Prevention of mechanical strain at cables, junctions, connectors and supports.

d. Drip loops, service loops, and free movement of shock and vibration mounted equipment. Service loops may be left long enough to allow removal of Line Replacement Units (LRUs) for maintenance without the need to gain access to the rear of the LRU in its mounted position. e. Shifting of wiring and equipment while performing maintenance within the airplane including removal, replacement, and test of LRUs. ELECTROMAGNETIC COMPATIBILITY Wires, cables, and harnesses shall be routed to minimize the affects of electromagnetic interference within the airplanes systems. To reduce interference, all wires and shielded cables shall be routed at least fourteen inches from any ignition, power distribution, strobe light, or generator control wire where physically possible. Whenever avionics and electrical equipment wiring cross they shall cross at 90° angles to each other. POWER SYSTEMS Electrically unprotected wires and cables (wires and cables that have no circuit breaker, fusible link or other means of electrical protection), shall not be bundled or grouped with distribution circuit wires and cables. Wires and cables from two or more sources shall not be in the same bundle or group, to prevent a single damage from affecting more than one power source. Power Systems shall be routed following existing or as delivered from the factory routing and when this is not possible ‘best shop practices’ and FAA Advisory Circular AC 43. 13-1B or subsequent.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL FLIGHT ESSENTIAL SYSTEMS Wire and cable to flight control systems of the airplane which are required to operate during normal and emergency conditions shall be routed separately from other wire and cable, and identified and noted and shall be routed following existing or as delivered from the factory routing and when this is not possible ‘best shop practices’ and FAA Advisory Circular AC 43. 13-1B or subsequent. PARALLEL CIRCUITS Wiring to equipment performing duplicate functions shall be routed in separate bundles to prevent one system from affecting the other. Parallel Circuits shall be routed following existing or as delivered from the factory routing and when this is not possible ‘best shop practices’ and FAA Advisory Circular AC 43. 13-1B or subsequent. SPLICE CONNECTIONS Insulated permanent splices shall be used for assembly of subassemblies, incorporation of changes, and to facilitate repairs. Splices are subject to the following restrictions: a. There shall be no more than one splice in any wire between any two disconnect points. b. Splices in bundles shall be staggered and shall not increase the size of the bundle or cause congestion which will affect maintenance. c.

Crimp style connections shall be made with the correct crimping tools as specified by the terminal manufacturer.

d. It is permissible to crimp a maximum of three (3) wires in the same crimp style terminal or splice, provided the terminal barrel is of sufficient circular MIL range to hold all the wires. e. Crimp style connections shall not be subject to a mechanical load. f.

If a wire is too small for the crimp style device, reducing sleeves shall be used. If reducing sleeves are not available, a short length of the same wire may be added to increase the circular MIL area and to be used as a filler. Do not fold wire to take up gaps in the crimp style device.

SUPPORT AND PROTECTION This section covers the methods of supporting and protecting wire and cables installed within the airplane. WIRE AND CABLE Wires and cable harnesses shall be supported to meet the following requirements: a. Prevent chafing (Ref. ANTI-CHAFING PROVISIONS) b. Secure wires, cables and harnesses where routed through bulkheads and structural members (Ref. PRIMARY SUPPORT) c.

Correctly group, support and route wires in junction boxes, panels, and bundles.

d. Prevent mechanical strain or work hardening that would tend to break conductors and connections. e. Prevent arcing or overheated wires and cables from causing damage to mechanical control cables, and associated moving equipment. f.

Facilitate re-assembly to equipment terminal boards.

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Page 3 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL g. Prevent interference between wiring and other equipment. h. Provide support for wires to prevent excessive movement in areas of high vibration. PRIMARY WIRING SUPPORT Wire bundles shall be attached when crossing a rib or structural member (Ref. Figure 1). Nylon edging or equivalent shall be used to provide protection when necessary. The maximum distance a wire or bundle may run without support shall be 24 inches, except when there is no danger of chafing. Open wire contained in troughs, ducts, or conduits are exempt from this requirement. Clamps for harnesses, other than round shall be shaped to fit the contour of the harness and shall provide a snug fit. Plastic clamps are subject to restrictions of SECONDARY WIRING SUPPORTS. Plastic cable straps shall not be used as primary supporting devices. Primary support of wires, cables and wire harnesses shall not be attached to adjacent wires, cables or harnesses. Lightening Holes Wiring that passes through a lightening hole, where support is required, shall have an MS3340 lightening hole mount installed. Grommets, although not required where this support method is used, are required when wiring passes through a series of three or more lightening holes in a line forming a duct-like installation. The lightening holes will have grommets installed (Ref. GROMMETS). The wiring shall be clamped within 24 inches of the beginning and end of each lightening hole mount installation to prevent lengthwise movement. Install the lightening hole mounts in accordance with the following instructions and as shown in Figure 1. a. Drill a 0.138/0.148 diameter hole, 0.50 inches below the lip of the lightening hole. b. Install the MS3340 mount to the bulkhead with a MS335206 screw (head on the mount side) of appropriate size and length, an AN960-6L washer (installed between the nut and the bulkhead), and a MS31042L06 nut. c.

Secure the wiring to the mount with a MS3367 tie-down strap of appropriate size and length to retain the wiring.

Plastic Loop Clamps Plastic loop clamps shall be in accordance with ‘best shop practices’ and FAA Advisory Circular AC 43. 13-1B or subsequent and MIL-S-23190. They may be used for wire support noting the following provisions: a. Every fourth clamp must be a MS21919 cushion support clamp. b. Wire slack must not accumulate between clamping points. c.

Plastic clamps shall not be used to support rigid portions of wiring.

Grommets Wiring passing through a cutout shall have a MS21266 or MS35489 grommet bonded with adhesive in the cutout according to ‘best shop practices’ and FAA Advisory Circular AC 43. 13-1B or subsequent. MS35489 grommets are to be used whenever possible, especially for single wires or small wire bundles. Maximum opening in a split grommet after installation shall be 0.06 inch. The split shall be diagonal, and installed so the wire pressure will be on the side opposite from the split.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL Hole Locations Fastener holes shall not be drilled in any structural flange, such as frames, ribs, and longerons unless approved by Hawker Beechcraft Customer Support. Holes for wiring supports (e.g. holes drilled to mount clamps or brackets) shall be done according to ‘best shop practices’ and FAA Advisory Circular AC 43. 13-1B or subsequent. Clamp Size Primary supporting devices shall hold the wires, cables, and wire harnesses firmly in place without damaging the insulation.

TIE

TIE MOUNT

BULKHEAD LIGHTENING HOLE

FL20B 093569AA.AI

Lightening Hole Mount Installation Figure 1 SECONDARY WIRING SUPPORTS Secondary wiring supports shall be installed between primary wiring supports as required to restrict movement. The supports shall be in accordance with the following: Tie-Down Straps Wiring may be supported by using a tie-down strap (MS3367) in accordance with ‘best shop practices’ and FAA Advisory Circular AC 43. 13-1B or subsequent. The strap is installed with an MS90387 installation tool or equivalent.

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20-12-00

Page 5 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL J-Stringer Wiring shall be supported on a J-stringer by installing a TM2S6 tie mount on the stringer and using a MS3367 tiedown strap of appropriate size and length to secure the wiring. When two or more TM2S6 tie mounts are to be installed on a stringer, the minimum spacing between the tie mounts is to be 12 inches as shown in Figure 2. Additionally, tie mounts shall be installed a minimum of 12 inches from all bulkheads in order to provide access for connecting or turning of the wiring. The mounting holes for tie mounts are to be 0.128/0.133 inch diameter and are to be located in the center third of the stringer flat as shown in Figure 3. Each tie mount is secured to the stringer with a MS20470B4 rivet. Wiring routed perpendicular to and secured to stringers is to have the weight distributed between more than one stringer to prevent stringer deformation.

J-STRINGER

12.00 TYPICAL

FL20B 093570AA.AI

J-Stringer Tie Mount Spacing Figure 2

Page 6 May 1/10

20-12-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

J-STRINGER

MS3367 TIE-DOWN STRAP

MS20470B4 RIVET

FL20B 093571AA.AI

J-Stringer Tie Mount Installation Figure 3 LIMITATIONS OF SUPPORT The following are limitations which are placed on wiring or cable harnesses: a. Continuous lacing is not to be used except in panels and junction boxes where this practice is optional. b. Plastic tapes with volatile plasticizers, which produce chemical reaction with wire or cable insulation or absorb moisture, shall not be used. c.

Use of insulated sleeving for the protection of wire and cable shall be kept to a minimum.

d. Moisture absorbent materials shall not be used as a ‘fill’ for clamps or adapters. e. Wires and cables shall not be tied or fastened together in conduit or insulated tubing. f.

Cable supports shall not restrict the wires or cables or interfere with the operation of shock mounts.

g. Tape or cord shall not be used for primary support or as a substitute for any clamp. h. Plastic cable straps shall not be used in areas where: 1. Total ambient temperature exceeds 85°C (185°F). 2. Failure of the strap would permit movement of the wires, cables or harness against parts which could damage the insulation or foul mechanical linkage. 3. Failure would allow the strap to fall into moving mechanical parts.

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Page 7 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL ANTI-CHAFING PROVISIONS Route and clamp wiring to avoid contact with edges of equipment and structure. Where physical separation of at least 0.4 inch cannot be maintained, use a MS21266 grommet to cover the edges of the equipment structure. The grommet shall be bonded to the equipment or structure in accordance with ‘best shop practices’ and FAA Advisory Circular AC 43. 13-1B or subsequent. In areas of possible chafing, install Varglas sleeving (Chart 1, item 1) or spiral wrapping (Chart 1, item 2) over the wiring in accordance with ‘best shop practices’ and FAA Advisory Circular AC 43. 13-1B or subsequent (Ref. Figure 5, for typical use of Varglas Sleeving or Figure 6 for typical use of Spiral Wrap). In areas of possible chafing that require protection with flexibility, high temperature, and/or resistance to fluids, the use of Raychem HCTE, P/N RT-1162 (Chart 1, item 3), spiral wrap, P/N 500017-X (Chart 1, item 2), or fire retardant tape, P/N 52672 (Chart 1, item 4) is permissible. If an environmentally sealed harness is not required, use HCTE material with drain holes.

Chart 1 Recommended Materials MATERIAL

SPECIFICATION

1. Varglas Sleeving

2. Spiral Wrap

PRODUCT

SUPPLIER Varflex Corporation 512 W. Court Street Rome, NY 13440 Panduit Corporation 17301 Ridgeland Avenue Tinley Park, IL 60477-3093 Tyco Electronics 1050 Westlakes Drive Berwyn, PA 19312

3. Raychem Helical Convolex Tubing (HCTE) 4. Fire Resistant Tape

Page 8 May 1/10

20-12-00

Raychem Corporation 300 Constitution Drive Menlo Park, CA 94025 Armet Industries Corp. 7725 Jane Street Suite 205 Concord, Ontario L4K 181 Canada

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL R.F. COAXIAL CABLE SUPPORT Support of individual coaxial cables and of bundles containing coaxial cables shall be subject to the following requirements: a. Primary and secondary support devices shall be installed to exert no greater pressure on the cable than the minimum required to prevent slipping. b. Pressure shall be evenly distributed around bundles containing coaxial cables, or around the coaxial cable if individually supported. c.

Support devices shall not deform the cables so that the electrical characteristics are degraded.

d. Tape in accordance with A-A-52081, Finish C shall be used for tying bundles containing coaxial cables. For installation of plastic tie-down straps refer to Tie-Down Straps. Tension adjustment on the MS90387 tool should be set so that the requirements of a., b., and c. is met. e. Excessive lengths of coaxial cable shall not be coiled up in the airplane. All coaxial cables shall not have more one foot extra wire, or that required for field repair of damaged cable. RADIUS OF BEND Minimum radius of bend for wire or cable shall be ten times the outside diameter of the wire or cable including insulation. At terminal strips where the wire is suitably supported, the radius may be three times the diameter of the wire. Where it is impracticable to install these cables within these requirements, the bend shall be enclosed in insulating tubing. DRIP LOOP Wires and cables routed downwards to a connector, terminal block, panel, or junction box, shall have a trap or drip loop provided to prevent fluids or condensation from running into the device. WIRES AND CABLES NEAR MOVING PARTS Wires, cables, and harnesses attached to assemblies where movement occurs (such as at hinges and rotating pieces, particularly control sticks, control wheels, control columns, and flight control surfaces) shall be installed or protected to prevent deterioration. This includes abrasion of one wire or cable upon the other, and excess twisting and bending. Bundles shall be installed to twist, instead of bend across hinges. SPECIAL PROTECTION Power feeders, including wires, cables, and buses shall be given protection such as extra insulation, standoff mounting, and separation. Wires and cables shall be located or protected so they will not be damaged by maintenance personnel during normal maintenance or crew movements. Wires and cables installed in locations where fluids may be trapped and wires and cables contaminated shall be routed and protected against fluid damage. LINE SEPARATION Separation shall be maintained between static, instrument air, fuel, and oxygen lines, to prevent contact with wires or cables (Ref. LINE SEPARATORS).

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Page 9 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL WIRE ROUTING NEAR HOT AREAS To prevent insulation breakdown, all wiring, wiring devices and equipment, shall be installed to minimize the danger of fires, smoke hazards and toxicity. All wires shall be routed at least two inches from high temperature equipment, such as hot resistors, exhaust stacks, heating ducts, etc. SUPPORT AND PROTECTION OF CABLES AND WIRES IN FLAMMABLE AREAS Electrical wiring or equipment shall be supported independently from lines or tubing used to carry fluid or gas which presents a potential hazard of fire or explosion. Wiring shall not be clamped or attached to such lines and tubing. Wiring shall not be attached to associated equipment except to provide separation or electrical connection. Wiring shall have distinct physical separation from all fluid and gas carrying lines and tubes, except as provided below. When wires or cables are to be routed through these areas, no special provision need be taken if the wires and cables are kept at least six inches away from such lines or equipment. If wires or cables are less than six inches, but more than two inches from such lines, and equipment, they must be rigidly supported by the use of conduit or clamps so that it is impossible to deflect or otherwise bring any wire or cable within two inches of the line or equipment (Ref. Figure 4). When crossing at right angles and clearance is less than 2 inches, separation shall be maintained by use of cable clamps, clamping to a fitting on the equipment, or a clamp on the line, with a minimum separation of 1/2 inch. Clamps shall not be used as a means of supporting the wire bundle. Install additional clamps to support the bundle, fastening the clamps to the same structure used to support the fluid line to prevent relative motion. LINE SEPARATORS When separators are used, the weight of the wiring shall not be transferred to the line it is separated from. To prevent wiring from coming into contact with static, instrument air, fuel, or oxygen lines, separation shall be in accordance with either of the two methods that follow: a. Method 1 - Use a MS3367 tie-down strap and a 130936-N-5 nylon tube as shown in Figure 4. The nylon tube shall be a maximum of two inches long. Any excess length of tie-down strap shall be trimmed off after installation. Use care during installation tie-down strap to prevent damage to or deformation of lines from overtightening. b. Method 2 - Use two MS21919WDG clamps of the appropriate diameter, one NAS43DD3 spacer not to exceed two inches, one MS35207 #10 screw of the appropriate length, one AN960-10L washer, and one MS21042L3 nut as shown in Figure 4.

Page 10 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PLUMBING LINE

NYLON TUBE (MAXIMUM LENGTH 2 INCHES) WIRE HARNESS

MS3367 TIE STRAP

LINE SEPARATOR - METHOD 1

MS35207 SCREW

MS21919DG CLAMP

AN960-10L WASHER

NAS43DD3 SPACER

MS21919DG CLAMP MS21042L3 NUT

LINE SEPARATOR - METHOD 2 FL20B 093572AA.AI

Line Separator Methods Figure 4

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20-12-00

Page 11 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Use of Varglas Sleeving (Typical) - Example Figure 5

Page 12 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Use of Spiral Wrap (Typical) - Example Figure 6

ELECTRICAL WIRING - ROUTINE INSPECTIONS During routine electrical inspections the following items should be inspected. Any items that do not conform to the standards described in the GENERAL and REQUIREMENTS sections must be corrected. a. Wire/Wire Bundle - Inspect for: •

Aluminum drill shavings, lint or dust on or inside wire bundles. Aluminum shavings can, with vibration or other motion, cut through wire insulation and provide a conductive path between wires in a bundle or to adjacent grounded structure. Lint and dust can accumulate on wire bundles and may, if subjected to overheated wires, ignite or possibly feed, an electrical fire.

•

Wire insulation that has become brittle. Wire may be more susceptible to cracking.

•

Damaged insulation and/or exposed conductor material of wires. Cracked, chafed and cut insulation can provide a conductive path between wires in a bundle or to adjacent grounded structure.

•

Pinched wires can occur at wire clamps, connector backshell clamps, excessively tight cable ties, etc.

•

Inappropriate/improper wiring repairs such as the use of duct tape, electrical tape, poor crimp splices, etc.

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Page 13 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

•

Wire insulation damage due to fluid leaks (i.e. fuel, hydraulic fluid, etc.).

•

Separation of electrical wires from hydraulic, fuel and oxygen lines. Make sure a minimum of 0.5 inch separation and any wiring routed within 2.0 inches must be clamped to provide separation.

•

Small bend radii of wire. Wiring subjected to excessively tight bend radii may sustain damage to the wire insulation.

•

Sagging wire bundles. Make sure bundles are not allowed to droop onto structure, components, cables, hoses, other bundles, etc.

•

Wire attached to the outside of a wire bundle using plastic ties instead of being installed under existing wire clamps. Can cause chafed and cut wire insulation.

•

Unsupported wires running into conduit or wire supported in such a way as to pull the wire against the side of the conduit entrance instead of into the center. Can cause chafed and cut wire insulation.

•

Proximity to high temperature equipment. Wiring shall be kept separate from high temperature equipment, such as resistors, exhaust stacks, heating ducts and deicers, to prevent wire insulation deterioration.

•

Wires with different insulation types should not be routed together, where possible. Certain wire insulations may be easily abraded by other types of wire insulation.

b. Wire Harness Clamps - Inspect for:

c.

•

Condition. Make sure any protective material on the wire clamp (i.e. rubber, plastic, etc.) is in serviceable and functional condition. Clamps should be secured to structure and wire bundle should be snug in clamp.

•

Make sure clamps are not installed over splices.

Connectors - Inspect for: •

Condition. Make sure connectors are free of corrosion, moisture, dust and metal shavings. Check for worn environmental seals, loose contact tension, proper contact locking, missing seal plugs, missing dummy contacts, etc. Drip loops should be maintained when connectors are below the level of the harness and tight bends at connectors should be avoided or corrected.

d. Backshells - Inspect for: •

Condition. Wires may break at connector backshells due to excessive flexing, lack of strain relief or improper buildup. Loss of backshell bonding may also occur due to these and other factors.

e. Electrical Conduits and Sleeving - Inspect for: •

Susceptibility to water/moisture entrance. Conduits should not be susceptible to the entrance of moisture. If moisture going into conduits and sleeving is unavoidable, provisions should be made in the lower portions of the conduit to drain any moisture and prevent accumulation.

•

Condition. Damage to sleeving and conduits, if not corrected, will often lead to wire damage. Make sure components are free from corrosion, moisture, dust, and metal shavings. Check that conduit is secured to structure.

Page 14 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

f.

Terminations - Inspect for: •

Condition. Terminal lugs and splices are susceptible to mechanical damage, corrosion, heat damage and chemical contamination. Also, the buildup and nut torque on wire lugs is critical to their performance.

g. Grounding Points - Inspect for: •

A28

Condition. Grounding points should be checked for security (i.e. tightness) condition of termination, cleanliness and corrosion. Any grounding points that are corroded or have lost their protective coating should be repaired and be checked for proper resistance.

20-12-00

Page 15 May 1/10

CHAPTER

AIR

CONDITIONING

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 21 - ENVIRONMENTAL SYSTEMS TABLE OF CONTENTS SUBJECT

PAGE 21-00-00

Environmental System - Description and Operation (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Environmental Bleed Air . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Pressurization Control. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Air-Conditioning. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Temperature Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 21-01-00 Environmental System - Description and Operation (FL-493, FL-500 and After; FM -14 and After) . . . . . . . .1 Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Cooling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Temperature Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 21-10-00 Pressurization - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Pressurization - Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Test Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Flow Control Valve Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Troubleshooting the Flow Control Valve (With 1E30-2 Test Box). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .104 Troubleshooting the Flow Control Valve (Without the 1E30-2 Test Box) . . . . . . . . . . . . . . . . . . . . . . . . . . . .109 Ambient-Air Time Delay Test Procedure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .110 Ambient-Air Temperature Sensor Functional Test Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .111 Pressurization - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flow Control Valve Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flow Control Valve Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Electronic Controller Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Electronic Controller Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Flow Control Valve Flight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Environmental Bleed Air Ducts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Bleed Air Flow Rate Flight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Bleed Air Flow Rate Ground Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Manometer Construction. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208

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Environmental Air Distribution - Description and Operation (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Air Distribution (Blowers) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Aft Blower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Bleed Air Heat Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Defrost and Flight Compartment Heat. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Environmental Air Distribution - Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 Environmental Air Distribution - Maintenance Practices (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Vent Blower Removal, Forward . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Vent Blower Installation, Forward . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Vent Blower Removal, Aft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Vent Blower Installation, Aft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Butterfly Valve Rigging, Heat and Defrost . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Butterfly Valve Rigging, Main Duct . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Flapper Valve Test Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Check (Flapper) Valve Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Check (Flapper) Valve Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 21-21-00 Environmental Air Distribution - Description and Operation (FL-493, FL-500 and After; FM-14 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Air Distribution (Blowers) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Cockpit Blower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Cabin Blowers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Environmental Air Distribution - Maintenance Practices (FL-493, FL-500 and After; FM-14 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Servo Positioning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Forward Plenum Servo Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Forward Plenum Servo Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Forward Plenum Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Forward Plenum Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Mixing Box Servo Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Mixing Box Servo Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Mixing Box Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Mixing Box Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Cabin Add Heat Servo Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 206 Cabin Add Heat Servo Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 206

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Pressurization Control - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Pressurization Control - Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Pressurization Check Procedures (Flight Test). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Pressurization Control - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Pressurization Controller Filter Cleaning. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Outflow and Safety Valve Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Safety Valve Filter Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Pressurization Control System - Operational Check. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Cabin Pressurization Leakage Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Outflow Valve and Safety Valve Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Outflow Valve and Safety Valve Functional Test (Method 1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Outflow Valve and Safety Valve Functional Test (Method 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Outflow Valve and Safety Valve Functional Test (Method 3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Outflow Valve and Safety Valve Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Outflow Valve and Safety Valve Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Pressurization Controller Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Pressurization Controller Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Cabin Altitude Pressure Switch Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Cabin Altitude Pressure Switch Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Cabin ALT HI Warning Pressure Switch Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Cabin ALT HI Warning Pressure Switch Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Cabin Altitude Warning Pressure Switch Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .217 Method 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .217 Method 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .218 Method 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .219 21-40-00 Heating - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Bleed Air Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Electric Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Heating - Troubleshooting (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) . . . . . . . . . . . . . . . . .101 Heating - Maintenance Practices (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) . . . . . . . . . . . .201 Microswitch Adjustment (Bleed Air Bypass) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Bleed Air Bypass Valve Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Bleed Air Bypass Valve Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Bleed Air Bypass Valve Operational Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Bleed Air Shutoff Valve Removal (Aft Heat) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Bleed Air Shutoff Valve Installation (Aft Heat). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Electric Heat Element Removal, Forward . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Electric Heat Element Installation, Forward . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Electric Heat Element Removal, Aft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Electric Heat Element Installation, Aft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Electric Heater Power Relays Operational Check. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204

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Heating - Troubleshooting (FL-493, FL-500 and After; FM-14 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . Inadequate or No Heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electric Heater Power Relays Operational Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Heating - Maintenance Practices (FL-493, FL-500 and After; FM-14 and After) . . . . . . . . . . . . . . . . . . . . . . Electric Heater Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electric Heater Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Thermal Fuse Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

101 101 101 201 201 201 202

21-42-00 Radiant Heating, Cargo Door - Description and Operation (FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Radiant Heat Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 21-50-00 Cooling - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Hot Gas Bypass Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Pressure Cutout Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Vent Blowers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Pressure Relief Valve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Cooling - Troubleshooting (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) . . . . . . . . . . . . . . . . . 101 Air-Conditioning System - Operational Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 Cooling - Maintenance Practices (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13) . . . . . . . . . . . 201 Precautionary Maintenance Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Air-Conditioning System Maintenance Notes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Refrigerant Level Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Refrigerant Leak Detection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Depressurizing the Air-Conditioning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Evacuating the Air-Conditioning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Cleaning the Air-Conditioning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Charging the Air-Conditioning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Evaporator Filters. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Return Air Inlet Filters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Evaporator Removal, Forward . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Evaporator Installation, Forward . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Evaporator Removal, Aft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Evaporator Installation, Aft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 206 Compressor Quill Shaft Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 209 Compressor Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 209 Compressor Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 210 Compressor Mount Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 213 Compressor Mount Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 213 Compressor Mount Support Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 213 Compressor Mount Support Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 213

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Compressor Belt Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Compressor Belt Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Compressor Belt Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Condenser Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Condenser Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Condenser Blower Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Condenser Blower Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Receiver-Drier Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Receiver-Drier Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Reset of Overpressure or Underpressure Indication System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .218 21-51-00 Cooling - Troubleshooting (FL-493, FL-500 and After; FM-14 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Refrigeration System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Measuring Temperature Drop Across the Evaporator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Measuring Suction and Discharge Pressure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 System Diagnosis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Compressor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Condenser . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .102 Receiver/Dryer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .102 Expansion Valve. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .102 Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .102 Step One . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .102 Step Two . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .103 Cooling - Maintenance Practices (FL-493, FL-500 and After; FM-14 and After) . . . . . . . . . . . . . . . . . . . . . .201 Precautionary Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Air-Conditioning System Maintenance Notes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Refrigerant Level Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Refrigerant Leak Detection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Discharging the Air-Conditioning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Evacuating the Air-Conditioning System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Cleaning the Air-Conditioning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Charging the Air-Conditioning System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Compressor Quill Shaft Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Compressor Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Compressor Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Compressor Mount Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Compressor Mount Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Compressor Mount Support Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Compressor Mount Support Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Compressor Belt Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Compressor Belt Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Compressor Belt Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Condenser Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Condenser Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213

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Condenser Inlet Duct Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Condenser Inlet Duct Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Condenser Blower Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Condenser Blower Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Receiver/Dryer Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Receiver/Dryer Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit Evaporator Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit Evaporator Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit Evaporator Blower Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit Evaporator Blower Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit Evaporator Blower Motor Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit and Cabin Expansion Valve Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit and Cabin Evaporator Coil Cleaning. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Evaporators Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Evaporators Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Blowers Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Blowers Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Evaporator Blower Motor Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pressure Switch Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

214 214 214 214 215 215 219 219 220 220 220 222 222 224 224 224 224 225 227

21-60-00 Temperature Control - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Temperature Controller (300-0750-1) (FL-493, FL-500 thru FL-536; and Airplanes Without Service Bulletin 21-3838) . . . . . . . . . . . . . . . . . . . . . . . . 3 Temperature Controller (300-0750-2) (FL-537 and After; FM-15 and After and Airplanes With Service Bulletin 21-3838). . . . . . . . . . . . . . . . . . . . . . 3 Passenger Cabin Temperature Control (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . . 3 Temperature Control - Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 Temperature Control - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Air Duct Temperature Sensor Resistance Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Duct Temperature Sensor Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Duct Temperature Sensor Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Cabin Temperature Indicator Adjustment (FL-1 thru FL-492, FL-494 thru FL-499, FM-1 thru FM-14) . . . . . 205 Cabin Temperature Controller - Functional Test (FL-1 thru FL-492, FL-494 thru FL-499, FM-1 thru FM-14) 206 Cabin Temperature Controller - Test Equipment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 206 Cabin Temperature Controller Test Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 207 Cabin Temperature Controller Removal (FL-1 thru FL-492, FL-494 thru FL-499, FM-1 thru FM-14) . . . . . . 208 Cabin Temperature Controller Installation (FL-1 thru FL-492, FL-494 thru FL-499, FM-1 thru FM-14) . . . . . 208 Cabin Temperature Controller Removal (FL-493, FL-500 and After; FM-15 and After). . . . . . . . . . . . . . . . . 209 Cabin Temperature Controller Installation (FL-493, FL-500 and After; FM-15 and After) . . . . . . . . . . . . . . . 210 Cabin Temperature Controller - Functional Test (FL-493, FL-500 and After; FM-15 and After) . . . . . . . . . . 210

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Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ENVIRONMENTAL SYSTEM DESCRIPTION AND OPERATION (FL-1 THRU FL-492, FL-494 THRU FL-499; PM-1 THRU FM-13) The environmental system makes use of engine bleed air for cabin pressurization and cabin heating. The airconditioning system, driven by the RH engine, provides cool air to the airplane cabin (Ref. Figures 1 and 2). An electronic controller receives ambient temperature indications from the thermistor and sends appropriate commands to the flow control valve. With the airplane in flight, the flow control valve mixes ambient air with bleed air and controls the flow to the cabin. The bleed air is

through

the flow control valve

mounted a

on

prior

produced by the

compressor section of the engine and routed system. Outflow and safety valves,

to introduction into the environmental

the aft pressure bulkhead, allow for the controlled release of pressurized cabin air in order to maintain pressure differential between the cabin environment and ambient air.

preselected

Conditioned bleed air is distributed and recirculated

ducting systems connected only at the blower. The heating. The adjustable outlets in the headliner air-conditioning system. by

two

outlets in the cabin lower sidewall deliver conditioned bleed air for

provide

for cabin air recirculation and

cooling by

the

Temperature regulation is provided by the cabin temperature controller mounted in the center cabin overhead upholstery. Various modes of temperature control are provided by the controlling circuitry. The system can be controlled manually by the flight crew or automatically by the cabin temperature controller. The evaporator blowers can be operated independently of temperature control. ENVIRONMENTAL BLEED AIR Bleed air from the compressor stages of the engines provides for pressurization and heating of the cabin. The flow control valve passes the bleed air into the bleed air duct system. When the airplane is in flight, the flow control valve mixes ambient air with bleed air in amounts determined

air is

required,

it is

passed through

the heat

by input from the thermistor. If further cooling exchangers in the leading edge of the wings.

of the bleed

DISTRIBUTION Bleed air from the

engines is delivered to the cabin through outlets in the lower cabin sidewalls for pressurization heating. air-conditioning system recirculates and further cools the cabin air as required before distributing it though cabin sidewall and adjustable overhead outlets. The air-conditioning system makes use of the two evaporator blowers in order to recirculate the cooled cabin air. Evaporator coils are mounted on the outlet side of the evaporator blowers to facilitate the exchange of heat between the cabin air and the refrigerant when the system is operating. Refer to Chapter 21-50-00 for a more detailed explanation of the operation of this system. and

The

21-00-00

Oct

31/06Page

1

Raytheon

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PRESSURIZATION CONTROL Cabin

pressurization is maintained at a selected level by the pressurization controller mounted in the pedestal. The settings for cabin altitude and rate of change. The sole function of the pressurization controller is to control the outflow valve which opens or closes proportionally to the degree of vacuum being provided by the controller. The outflow valve automatically maintains cabin pressure at a level slightly less than the pressure differential that corresponds to the pressure altitude setting on the controller. If a fault in the system fails to maintain a cabin pressure differential below the maximum, the outflow and safety valves have maximum differential valves that are calibrated to open and dump the excess cabin pressure. controller has

Vacuum is

supplied to the pressurization controller through a normally open solenoid-type valve (preset solenoid valve) safety valve through a normally closed solenoid-type valve (safety solenoid valve). These two valves are energized through the DUMP position of the control switch on the pedestal. When the switch is in the dump mode, both solenoid valves are energized and the vacuum is shunted from the pressurization controller to the safety valve, opening it and dumping the cabin pressure to the outside. Chapter 21-30-00 contains information pertaining to troubleshooting and maintaining of this system. and to the

HEATING Bleed air from the engines enters the cabin distribution ducts for

I (the

LH and RH bleed air

compressor in When the

or

out of

airplane

is

bypass valves). operation.

on

the

ground,

The LH valve also

bleed air heat

can

be

heating through ´•two electrically operated valves the purpose of switching the air-conditioning

serves

supplemented by forward

and aft electric heat elements.

These heat elements

are located in the forward main heat duct and in the aft blower plenum adjacent to the aft beneath the cabin floorboards. For more specific information on heating, refer to Chapter 21-40-00. evaporator,

AIR-CONDITIONING The

air-conditioning system

is similar to automobile

valve in the bleed air line reaches the

bypass

fully

or

air-conditioning systems and is activated when the LH position in response to the cool commands of the cabin

home

closed

temperature controller. When the temperature mode switch is set to MAN COOL or AUTO, the fully closed switch is allowed to complete the circuitry that causes the refrigerant compressor clutch to engage, thereby turning the compressor and initiating cabin cooling. A

condensing

coil and blower

assembly, located

in the

nose

of the

airplane,

removes excess

heat from the

high

temperature, high pressure gaseous refrigerant being discharged from the compressor, allowing the refrigerant to condense to the liquid state. The high pressure, low temperature liquid refrigerant passes through a metering device (thermostatic expansion valve) into the evaporator where the pressure is reduced and the refrigerant is allowed to evaporate into the gaseous state, producing a heat deficit in the gaseous refrigerant. Cabin air is circulated over the evaporator coil where heat is transferred from cabin air to the gaseous refrigerant. The low pressure, low

temperature refrigerant Once the

cooling system

movement of the switch

Certain

measures

Overpressure maximum into the

proper

Page

then returns to the compressor and the entire

or

and

is activated, it will remain in

cam

ton

the LH bleed air

cycle

operation unless bypass valve) to the

is

repeated.

the compressor clutch is disengaged by the 30 position or by the protective devices.

have been taken to protect the air-conditioning system from damage during normal operation. underpressure switches deactivate the system in the event operating pressures exceed the

minimum safe

operating limits. For further overpressure protection, a pressure relief valve is plumbed 21-50-00 contains information to aid in troubleshooting the system and maintaining it in the

system. Chapter operating condition.

221-00-00

C121

Raytheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

TEMPERA TURE CONTROL

Temperature

control in the

airplane

accomplished by the cabin temperature register cabin temperature.

cabin is

temperature sensitive resistance devices

to

controller. It makes

use

of

Power from the "heat command" output of the cabin temperature controller causes the bleed air bypass valves to open and allow hot bleed air into the cabin. When heating is required and the LH bypass valves opens beyond the

position, the air-conditioning system relay is de-energized, removing power from the compressor clutch which disengages. "Cool command" output from the cabin temperature controller causes the bypass valves to direct the bleed air through the wing intercoolers. The refrigerant compressor can be engaged by the LH bypass valve if additional cooling is required. Chapter 21-60-00 contains information pertaining to troubleshooting and maintenance 30

of the temperature controls.

SPECIAL TOOLS AND RECOMMENDED MA TERIALS special tools and recommended materials listed in Charts 1 and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Raytheon Aircraft Company. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Raytheon Aircraft Company, by the supplier or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

The

21-00-00Page

3

RBYtheOn

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 1

SPECIAL TOOLS AND EQUIPMENT

1.

SUPPLIER

PART NO.

TOOL NAME

121 1-8WM

Manometer

Dwyer

USE

Instruments Inc., P.O.

Bleed air flow check.

Box 373

Michigan City, 2.

3.

Cabin Pressurization Unit

Adapter

Kitfor

IN. 46360

15-7600-1000 (60 Hz) 15-7602-1000 (50 Hz)

Tronair

Check pressure vessel

1740 S. Eber Road

integrity.

K-1285

Tronair

Holland, Ohio 43528 1740 S. Eber Road

Pressurization Test Unit

Holland, Ohio 43528 4.

Lamps (28-vdc, 40-ma)

5.

TestAltimeter

MS25231-1819

(Certified

Obtain

Locally

Obtain

Locally

Test item. Pressurization check

procedures.

Accurate) 6. 7.

SmoothJaw Pliers

Obtain

Bleed Air Control Test Box

1E30-2

Parker-Hannifin 711

Pressurization test.

Locally

Taylor

Flow Control Valve Test

Corp

St.

P.O. Box 4032

Elyria, 8.

1811-F-D

Pitot StaticTester

OH 44036

Barfield Instrument

Corp

P.O.

To check outflow valves.

Box 420537

Miami, FL 33242-0537 9.

Safety

Net

(Cabin Door)

97-000000/939-1

Raytheon Aircraft Company

Secure cabin door

9709 East Central

during

pressure

testing.

P.O. Box 85

Wichita, KS 67201-0085 10.

Temperature

Model 913881AC

Bath

11. R-134a Service Valves

Thermistor Functional

1256TrappRoad Eagan, MN 55121-1217

Test

MT.

To service R-134a air-

JD13-1019-04-04

Aeroquip

JD13-1019-05-05

Clemens, MI.

conditioning.

Digi-Key Corp.

Test Item

12. Resistor

(25 ohm, 100 ohm, 115 ohm)

Rosem~unt Inc

107 ohm,

701Brooks Ave. South

Thief River Falls, MN 56701

www.digikey.com Newark InOne

4801North Ravenswood

Chicago,

IL 60640-4496

www.newarkinone.com

Oct

31/06~;f

21-00-00

A21

Raythwm

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 1 SPECIAL TOOLS AND EQUIPMENT

TOOL NAME 13. Air

PART NO.

Temperature Gage.

USE

SUPPLIER

Raytheon

50-380026-1

Aircraft

Test Item

Company

9709 East Central

P.O. Box 85

Wichita, KS 67201-0085

Chart 2 RECOMMENDED MATERIALS

MATERIALS 1.

Air-Conditioning Refrigerant (Charging)

SPECIFICATION R-l 2

PRODUCT

SUPPLIER Racon Inc.,

Racon 12

6040 S.

Ridge

Road

Wichita, KS 67215 Genetron 12

Racon Inc

Specialty

Chemicals Div.,

Columbia Rd. and Park Ave., P.O. Box 1087R

Morristown, NJ 07460

2.

3.

Oil

(Air-Condition)

525

Viscosity

Refrigerant Leak Detector Dye

Freon 12

Dupont Inc., Freon Products Div., 1251 Brandywine Bldg. Wilmington, DE 19898

Delco Air

White Consolidated Industries Inc.,

Refrigerant Oil (Viscosity 525)

6000 Perimeter Dr.

Trace

Highside

Dublin, OH 43017 Chemical Inc.,

Reichhold Rd., P.O. Box 3748

Gulfport, MS 4.

Air-Conditioning Refrigerant Flush

Air-conditioning

Castrol North America

Flush

Products Division

Special

16715 Von Karmen

Ave., Irvine, CA 92714-4918

Fluid

5.

39505

Molykote

Lubricant

M77

Dow

Coming

3901 S.

Saginaw Rd.,

P.O. Box 997

Midland, MI 48640 6.

Aluminum Pressure Sensitive Foil

Tape

3 X 0.002 inch

Coming Fiberglass Corp., Fiberglass Tower

Owens

Toledo, OH 43604-1540 7.

Industrial Oven Insulation

(Specify or

A21

2-inch

i-inch

Coming Fiberglass Corp., Fiberglass Tower

Owens

Toledo, OH 43604-1540

thick)

21-00-00

Oct

31/06Page

5

RaIIlNaaa

AiKraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL Chart 2

RECOMMENDED MATERIALS MATERIALS 8.

Isopropyl Alcohol

9.

Mild

10.

Cleaning Solvent

(Continued)

Obtain

locally.

Joy (Etc.)

Obtain

locally.

Stoddard Solvent

Obtain

locally

TT-I-735

Detergent P-D 680

Type

III

SUPPLIER

PRODUCT

SPECIFICATION

(Mineral Spirits) MIL-S-8802

11. Sealer

PR-1440

Products Research and Chemical Corp., 410

Jersey Ave.,

Glouster City, NJ 08030-2350 Pro Seal 890

Essex Chemical

Corp.,

Pro-Seal Div., 19451 Susana Rd.,

Compton,

Glyptol

12. Sealer

1201

CA 90221-5713

General Electric Co

Turnpike

3135 Easton

Fairfield, CT 06431 13.

Air-Conditioning

Obtain

R-l 34a

locally.

Refrigerant (Charging) 14.

15.

Oil

(Air-Condition)

Ester Oil

Thread

Locking Compound

ICI Americas Inc.

RL 100S, RL 100H Emkarate, SW 100

3411 Silverside Road

Castrol Icematic

Wilmington,

242

Loctite

DE 19850

Corp.

705 North Mountain Road

Newington, CT

Oct

ES49000-1

Sealant

16.

3106Page

6

21-00-00

Obtain

06111

locally

A21

Illaytne~

Aiaeraft

Company

SUPER KING AIR B300iB300C MAINTENANCE MANIUAL

/-FIREWALL SHUTOFF VALVE

AMBIENT AIR INLET

rBLEED AIR SHUTOFF VALVE

AMBIENT ENGINE

TEMPSENSOR

BLEED AIR

i

FLOW CONTROL VAL vE

FIREWALL

I~s

i

REFRIGERANT

AIR INLET SCOOP

COMPRESSOR

OVERPRESSURE

PLENUM ASSY HEAT MIXING PLENUM

HEAT AND VENT

7

t

R.H. C.B. PANEL

VEI\ITBLOWER

-~1 1111

PRESSURE SWITCH

VALVE ASSY

FWD EVAPORATOR

~EAT EXCHANGER

OR HIGH

ELEMENT

7

I

BL-ED AIR

N#l

PRESSURE SOLENOID VALVE

BYPASS VALVE

CHECK VALVE r

UNDERPRESSURE

TEMP BULB

DUCT OVERTEMP

EXPANSION VALVE

REFRIGERANT

MUFFLER VENTVRI

R.H.

EVAPORATOR BYPASS

CABIN TEMP CONTROLLER

SWITCH

SENSOR SWITCH

CABIN COOL AIR

LINES

OUTLETS

OUTFLOW VALVE OVERBOARD DUCTS

(8 PLACES)

SUBPAN~EL

SENSE SWITCH

LIMIT CONTROLLERS g DRAW VALVES

OR LOW PRESSURE

RAtul AIR INLET DOOR& VALVE INLET AIR CONDENSER

rm]

RECEIVER DRYER RELIEF VALVE CONDENSER BLOWER OUTLET AIR

II

I

‘----~CU

i

I

=f

L-I_C_

REFRIGERANT SERVICE VALVES

I

II

f

I

f II I I

HOT GAS BYPASS SOLENOID VALVE

COCKPIT HEAT

I

I

i

f COCK~IT COOL

I

i

I

-5

SAFEN VALVE

i

AFT EVAPORATOR

I

AND BLOWER

AFT ELEC HEAT RELAY PANEL

AFT COMPARTMENT

/I

i

BLEED AIR HEAT

HEAT OUTLET

I

I

AFT SHUTOFF VALVE

CIRCUIT CARD BDX

DEFROST Alft

REFRIGERANT CABIN PRESSURE PRESET

COOL AIR OUTLETS

A(ROUTLETS

SERVICE VALVES

SOLENOID VALVE

CABIN HEAT OUTLETS AIR INLET SCOOP

RND ELEC HEAT

ENGINE BLEED AIR

RELAY PANEL

PRESSURIZATION

(8 PLACES)

DUCT

ilEAT EXCHANGER

-1

FLOW CONTROL VAL

II

!le.

FIREWALL

DC POWER

DISTRIBUTION PANEL AMBIENT AIR BLEED AIR BYPASS COOLEOAIR

VALVE ASSY AND

30" POSITION SWITCH HEATEDAIR

ENGINE BLEED AIR

I

BLEED AIR SHUTOFF VALVE

FIREWALL SHUTOFF AMBIENT AIR INLET

FU13

VALVE

Environmental

(FL-I

ORIGINAL As Received

ATP A21

By

thru

System

FL-492,

Schematic

FL-494 thru

Figure

FL-499)

1

21-80-08

Page

7

Oct 31/06

R5~eQn nircraft Company SUPER KING AIR B300/B300C MAINTENANCE MANUAL

rFIREWALL

AMBIENT AIR INLET

r

SHUTOFF VALVE

BLEED AIR SHUTOFF VALVE

AMBIENT ENGINE

TEMP

BLEED AIR

FLOW CONTROL VALVE

SENSOR

FIREWALL REFRIGERANT SERVICE VALVES

:I

REFRIGERANT

AIR INLET SCOOP

COMPRESSOR

OVERPRESSURE

PLENUM ASSY HEAT

HEAT AND VENT

FWD EVAPORATOR

VALVE ASSY

-7

PRESSURE

TEMP BULB 8

DUCT OVERTEMP SENSOR SWITGH

UNDERPRESSURE

LIMIT CONTROLLERS

OR LOW PRESSURE

B DRAW VALVES

CABIN TEMP CONTROLLER

SWITCH

REFRIGERANT MUFRER

R.H.

CABIN COOL AIR

UNES

AFT COMPARTMENT HEAT OUTLET

OUTLETS

VENTURI

~SUBPANEL

SENSE SWITCH

PRESSURE SOLENOID VALVE

BYPASS VALVE

CHECK VALVE

EXPANSIONVALVE EVAPORATOR BYPASS

BLEED AIH

SWITCH

R.H. C.B. PANEL

VENT BLOWER

HEAT EXCHANGER

OR HIGH

ELEMENT

MIXING PLENUM

OVERBOARD DUCTS

OUTFLOW VALVE

,_1Ul~il i’

RAM AIR INLET DOOR &VALVE

INLET AIR CONDENSER RECEIVER DRYER RELIEF VALVE

7

CONDENSERBLOWER OUTLET AIR

II

I

’---YM I

~Jh

I

SAFETYVALVE

REFRIGERANT SERVICE VALVES

AFT EVAPORATOR

I

I I

HOT GAS BYPASS SOLENOID VALVE

COCKPIT HEAT g

--i

DEFROST AIR

I

CO~f
REFRIGERANT

Y

I

I

RELAY PANEL

/1 I

~7

i

BLEED AIR HEAT AFT SHUTOFF VALVE

I

SERVICE VALVES

SOLENOID VALVE

CABIN HEATOUTLETS AIR INLET SCOOP

FND ELEC HEAT

ENGINEBLEEDAIR DUCT

RELAY PANEL

(8 PLACES) i~ HEAT

I

RMBIENTAIR

CONTROLLE_RIC

~ONTROL \IPILI;E~

ii

BLEED AIR BYPASS

VALVE ASSY AND

FIREWALL

ENGINE BLEED AIR

’DCPOWER DISTRIBUTION PANEL

EXCHANGER

PRESSURIZATION

r

6001AIR

OUTLETS AFT ELEC HEAT

CIRCUITCARDBOX

Il

CABIN PRESSURE PRESET

AND BLOWER

AIR OUTLETS

I

COOLED AIR

30’ POSITION SWITCH

HEATED A[R

BLEED AIR SHUTOFF VALVE

FIREWALL SHUTOFF AMBIENT AIR INLET

VALVE

FUIS ill

Environmental

System Schematic (FRA-I FRll-13) Figure 2 thru

Page

tcO8

31106

21-gg0-0g)

A21

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 000 21-01-00

ENVIRONMENTAL SYSTEM - DESCRIPTION AND OPERATION (FL-493, FL-500 AND AFTER; FM -14 AND AFTER) The environmental system utilizes a vapor cycle air conditioning system to provide cooling. Engine bleed air is used to provide heat and pressurization. If additional heating is required while the airplane is on the ground, it is provided by electrical heating elements within the system. For control panel operation, refer to the airplane flight manual.

DISTRIBUTION Ducting underneath the floor, in the headliner, in the space between the headliner and the fuselage (through frame lightening holes) is used to distribute air to the cabin through sidewall outlets, adjustable overhead outlets, and a center aisle floor outlet. Air is distributed in the cockpit through ducts to the glareshield outlets, adjustable overhead outlets, and to the pilot and copilot’s feet and floor outlets. The air is forced through the ducts and plenums by electric blowers and pressure from the engine bleed air. Air is directed by servo-actuated air valves controlled by the electronic controller, and by passive one-way flap valves moved by air pressure within the ducts. The controller moves air valve servos on the mixing plenum to direct excess bleed air to the aft cabin when maximum cooling is required. The excess warm bleed air is gradually drawn overboard by the normal venting of the cabin outflow valves. For a more detailed explanation of the operation of this system refer to Chapter 21-21-00.

HEATING Bleed air is used to heat and pressurize the cabin. Before bleed air from the engines enters the cabin distribution ducts, it passes through two electrical bleed air bypass valves (Left and Right) that are controlled by the electronic controller. The bypass valves determine whether bleed air will pass through, or bypass, the heat exchangers in the wings. If the environmental system requires heat, then the bypass valves open to allow fully heated bleed air to enter the system. If less heat is required, the bypass valves close and send the bleed air through the wing heat exchangers to reduce the temperature of the bleed air before it enters the cabin. An electric heater located aft of the forward plenum provides additional heating when the airplane is on the ground. When electric heat is selected on the cockpit mode switch, electrically heated air is directed to the center aisle floor outlet. For a more detailed explanation of the operation of this system refer to Chapter 21-41-00.

COOLING Cooling is provided by a vapor cycle air conditioning system using R134a refrigerant. A forward evaporator located under the avionics bay on the right side of the nose compartment, provides cooled air to the glareshield outlets and center aisle floor outlet. Two aft evaporators located under the center aisle provide cooled air to the cabin sidewall outlets and adjustable overhead outlets. The condenser, located in the nose, transfers the heat in the refrigerant to the outside air. The compressor located on the left side of the right engine provides refrigerant compression and circulation. A system pressure switch in the plumbing of the right center wing section and relief plugs on the compressor and receiver/dryer bottle, prevent system damage from over or under pressure operation. When air conditioning is selected, the mixing plenum directs the conditioned bleed air to the rear sidewall outlets. For a more detailed explanation of the operation of this system refer to Chapter 21-51-00.

A27

21-01-00

Page 1 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

TEMPERATURE CONTROL The cabin temperature controller manages the dual zone system, which allows independent control of the cabin and cockpit environments. Thermistors measure cockpit and cabin temperatures and are monitored by the controller. The controller manipulates the bleed air bypass valves in the wings, to pre-cool the bleed air through the heat exchangers, or bypass the heat exchangers and give full bleed air heat. Cockpit and cabin temperatures are achieved by combining cockpit and cabin ambient air, cooled air and heated engine bleed air. An evaporator under the nose avionics compartment floor and dual evaporators under the cabin floor provide independent sources of cooled air for the two temperature zones. The controller opens and closes various fuselage duct valves to maintain cockpit and cabin temperatures as selected on the copilot’s environmental control sub panel. A multi-servo mixing plenum blends the air sources before the air is distributed through the duct outlets. The controller also automatically adjusts evaporator blower speeds, and controls the on/off cycles of the compressor clutch and condenser blower, which operate simultaneously.

Page 2 Feb 1/10

21-01-00

A27

Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PRESSURIZATION

DESCRIPTION AND OPERATION

Bleed air is routed from the compressor section of each engine to the flow control valves mounted on the firewalls. The flow control unit controls the flow of ambient and bleed air. Each flow control unit consists of an ambient air

temperature sensor, a

bleed air flow

an

electronic controller and

flow control valve. The flow control valve consists of

an

air

ejector,

bypass, bleed air valve switch, ambient air flow modulating valve, firewall modulating check valve that prevents the bleed air from escaping through the ambient air intake, a solenoid

shutoff valve, a valve, a bleed air flow transducer, and

Three-position, toggle these switches

a

valve with

an

ambient air flow transducer

(Ref. Figures

1 and

2).

on the RH subpanel control the individual modes of the flow control valves. When position (BLEED AIR VALVES OPEN), the flow control valves provide the required pressurization. Bleed air is also supplied for pneumatic system operation. With the neutral position (ENVIR OFF), the flow controls shut off all environmental bleed air. In this

switches

in the up bleed air for cabin heat and are

switches in the center

position

the

operation.

or

pneumatic

bleed air, which tees off the bleed air lines forward of the flow control valves, is still in ENVIR OFF), all bleed air to the are moved to the down or keying position (PNEU

When the switches

cabin is shut off at the firewalls. The ambient air flow

modulating valve is actuated by a safety switch located on the LH landing gear. When weight landing gear, the ambient air valve is closed off, preventing entry of contaminants into the environmental system during ground operations. After the engine is started and the flow control unit energized, the bleed air modulating valve will close and actuate the bleed air shaft microswitch. When the microswitch is actuated, the electronic controller signals the solenoid to open; this enables the pneumatic line to the firewall shutoff valve to be pressurized and to open the valve. The bleed air shaft continues to open until the desired bleed air flow rate to the cabin is attained. The correct flow rate is determined by the bleed air flow transducer, the ambient air temperature is

on

the

sensor, and the electronic controller.

On takeoff the

safety switch immediately reopens the LH ambient air valve. A time delay module delays opening of approximately seven seconds after opening of the LH valve. This delay prevents cabin

the RH valve for

pressurization As the

surges.

airplane

climbs to

higher

altitudes

or

enters a cooler

environment, the ambient air flow is gradually reduced approximately O"F ambient temperature, the ambient

and the bleed air flow is increased to maintain cabin heat. At air flow valve is

around the air

completely ejector.

closed and the bleed air valve

bypass

section is

opened

to allow more bleed air flow

The rate of ambient air flow

through the flow control valve is in direct proportion to the temperature of the air in which high atmospheric temperatures, the amount of bleed air used is minimized by mixing ambient air inside the control valve through an air ejector. When atmospheric temperatures drop, the ambient air is reduced or shutoff. An ambient air temperature sensor (thermistor), adjacent to the ambient air inlet, sends temperature signals to the electronic controller enabling the controller to determine the correct mix of ambient and

the

airplane is operating.

At

bleed air for the cabin environment. If bleed air pressures or temperatures become excessive, the electronic automatically shutoff the environmental air at the affected valve.

controller will

anl

21-10-00

I

Raytheon

AiKraft company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

The bleed air mixture passes from the flow control valves to heat exchangers located in the center section of each wing. The heat exchangers remove any excess heat from the bleed air mixture by passing it through an air cooled The cooling air for the heat exchanger core is ducted from the leading edge of the wing, through the heat exchanger core, and exhausted through louvered plates on the lower side of the wing. Should full utilization of the bleed air be required for the cabin environment, bypass valves provide an alternate path around the heat exchangers. At the juncture of the LH and RH bleed air ducts is a check valve that assures continued cabin pressurization and heat, even though one engine is shutdown. Forward of the check valve is the muffler which quiets the movement of the air in the system. From the muffler the bleed air mixture moves to the mixing plenum where it is mixed with recirculated cabin air. If additional cooling of the bleed air mixture is desired, cool air from the air conditioner may be injected into the mixing plenum.

core.

Oct

31/0621-10-00

121

NolltNeorr

Aircraft Campany

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 1 FLOW CONTROL UNIT PINOUT

Electronic Controller

Flow Control Valve

P30

P31 28 vdc Power

(1)

A

Circuit

B

B

28 vdc Solenoid

C

C

12 vdc Motors

D

12 vde Ambient Air

(1)

Temp.

Sensor

Squat Switch

E F

F

Bleed Flow Transducer

G

(1)(2)

G

Solenoid Valve

H

(1)

H

Valve Switch

Ground

J K

K

Bleed Flow Transducer

L

L

Bleed Flow Transducer

Output

M

(1)

M

Bleed Flow Transducer

N

(1)

N

Ambient Air Flow Sensor

P

(1)

R

(2)

R

Ambient Motor

Winding

S

(2)

S

Ambient Motor

Winding

T

(2)

T

Ambient Motor

Winding

U

(2)

U

Ambient Motor

Winding

V

(2)

V

Bleed Motor

Winding

W

Bleed Motor

Winding

W

Ambient Air

(2)

Temp. Sensor

x

(2)

X

Bleed Motor

Winding

v

(2)

Y

Bleed Motor

Winding

z

(1)

Z

Ground

I Relay Voltage

b

I-

c

I Relay

I

Coil

NOTE

(1) Exposed terminal (2)

A21

on

test box 1E30-2.

Fused line in test box 1E30-2.

Requires continuity

check of the test box

prior to

use.

21-10-00

Oct

31/06Page

3

Raytheon

AiKraft

tompany

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

AMBIENT AIR TEMPERATURE SENSOR

BLEED AIR FLOW TRANSDUCER

ELECTRONIC CONTROLLER

AMBIENT AIR FLOW CONTROL MOTOR

~--POWER I

SOUAT

SWITCH

BLEED AIR FLOW CONTROL MOTOR SOLENOID

AMBIENT AIR

FIREWALL SHUTOFF

INLET

VALVE

TO

DUCTSYSTEM

DISTRIBUTION

AMBIENT ALR FLOW

II

TRANSDUCER (MASS FLOW SENSOR

CHECK VALVE

\AIR EJECTOR

T

ENGINE BLEED AIR

BLEED AIR (HIGH FLOW) BYPASS

C9488218a941

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Figure

Oct

21-10-00

Mixing System 1

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nircraft

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

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A21

2

21-10-00

Oct

31/06Page

5

Raytheon

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PRESSURIZATION- TROUBLESHOOTING The flow control unit consists of

interconnected

by

a

wiring

an

The flow control valve consists of

ambient air flow

an

electronic controller, and

a

flow control valve

an

air

ejector,

bleed air flow

modulating

valve with

bypass,

bleed air valve switch,

firewall shutoff solenoid valve, a check valve that prevents bleed air from bleed air flow transducer, and an ambient air flow transducer.

modulating valve,

the ambient air intake, This

ambient air temperature sensor,

harness.

chapter provides

a

the

entering

following troubleshooting procedures:

Pressurization Flow Control, Flow Control Valve with the 1E30-2 Test Box, Flow Control Valve without the 1 E30-2 Test Box,

Ambient-Air Time Delay Test Procedure, and Ambient Air Temperature Sensor Functional Test Procedure

TEST EQUIPMENT equipment used to troubleshoot flow control problems (7, Chart 1,21-00-00).

Test

The

digital

multimeter is used to

loaded with

a

measure

voltage

are a

digital

multimeter and the 1 E30-2 test box

and resistance values. It MUST NOT exceed

a

current 5 mA when

greater than 5 mA will cause the ambient temperature erroneous resistive reading.

1000 ohm resistive load. A current

ambient air flow

sensor

to self-heat

causing

an

sensor

and

FLOW CONTROL VAL VE OPERA TION The ambient air flow

entering

modulating

valve is

the cabin. This valve is actuated

normally closed during ground operations to prevent by the iH main landing gear safety switch.

contaminants from

engines are started and the flow control unit is energized, the bleed air modulating valve will begin a limit switch. This causes the electronic controller to signal the firewall shutoff valve to cycle Once the bleed air modulating valve reaches its fully closed position, it begins to enter the cabin. air can open so continues It to cycle open. open until the desired flow rate to the cabin is reached. The flow rate is sensed by the bleed air flow transducer and controlled by the electronic controller and ambient air temperature sensor. When the airplane to

closed and actuate

After takeoff, the landing gear safety switch provides an input to the electronic controller to operate the ambient air flow modulating valve until the desired flow rate is reached.

airplane gains altitude or the ambient air temperature becomes cooler, the ambient air flow modulating valve gradually reduces the ambient air flow and the bleed air flow bypass valve is gradually opened to maintain sufficient heating of the cabin. At approximately O"F ambient air temperature, the ambient air flow modulating valve is completely closed and the bleed air bypass valve is opened to allow more bleed air flow.

As the

an

21-10-00

Oct

31/06Page

101

Raytheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 101

TROUBLESHOOTING PRESSURIZATION FLOW CONTROL Trouble 1. No bleed air flow

Probable Cause or

a.

Tripped circuit

Remarks

breaker.

a.

deficient air flow.

Reference

Figure

1 to locate the short circuit in the

output of the tripped circuit breaker. b. Flow control valve stuck

b. Troubleshoot the flow control valve.

open. c.

Obstruction in the line

from the

c.

Clear the obstruction

or

replace the

line.

engine to the flow

control valve. d. Firewall shutoff valve

damaged e.

Faulty

or

d. Troubleshoot the flow control valve.

leaking.

controller.

f. Failure in

an

e.

f. Perform pressurization system located in Chapter 21-30-00.

associated

system. 2. Excessive cabin

pressure fluctuation takeoff.

a. on

Faulty time delay

a.

Perform ambient-air time

troubleshooting

delay test.

module.

b.

Faulty outflow

valve

b. Perform

or

electronic controller. 3. Initial rate of climb

a.

exceeds

leakage.

approximately

Troubleshoot the flow control valve.

Chapter

Excessive cabin

a.

pressurization troubleshooting located

in

21-30-00.

Perform

located in

pressurization system troubleshooting Chapter 21-30-00.

2400 feet per minute when both bleed air valves are turned off

(with the airplane at 18,000 feet and fully pressurized). b. Excessive

leakage

due

b. Perform

to malfunction in the

pressurization

located in

pressurization system troubleshooting Chapter 21-30-00.

control

system. 4. Bleed air inflow too hot or

too cold.

Damaged or malfunctioning ambientair temperature

Damaged or malfunctioning controller. Damaged or malfunctioning bleed bypass valves.

d. Clogged heat exchanger.

I

sensor

functional

procedure.

b. Troubleshoot the flow control valve.

c.

c.

3110621-10-00

Perform ambient air temperature

test

sensor.

b.

Oct

a.

a.

air

or

Check the

replace

bypass valves required.

for proper

operation; adjust

as

d. Clean the heat

exchanger

as

required.

Raythwm

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 101

TROUBLESHOOTING PRESSURIZATION FLOW CONTROL

5. Cabin

temperature

a.

Short circuit,

a.

Reference

Figure

1 and check the circuit from the

landing gear safety switch for a short is found, check for a short circuit from the LH landing gear safety switch to the A170 PWB circuit breaker to the LH

control circuit breaker trips on

Remarks

Probable Cause

Trouble

(Continued)

short. If

landing,

no

module. If

safety

no

short is found, replace the LH landing gear a short is found, measure J1-32 on the

switch. If

A170 PWB module for

replace

repair b.

Faulty

time

delay

a

short. If

a

the A170 PWB module. If

the

wiring

short is found,

no

short is found,

harness.

b.

Replace A170 PWB

c.

Troubleshoot the flow control valve.

module.

module. c.

Faulty

electronic

controller. 6. Cabin temperature control circuitbreakertrips

approximately

a.

Faulty

time

delay

a.

Perform ambient-air time

delay

test

procedure.

module.

7 seconds

after takeoff.

A21

21-10-00

Oct

31/06Page

103

Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

TROUBLESHOOTING THE FLOW CONTROL VALVE (WITH IE30-2 TEST BOX) Inspect the airplane wiring harness prior to performing this test.

b.

Disconnect P31 from the flow control valve.

c.

Use the multimeter to check for 82-100 ohms are

d.

OPEN

or

FrompinRtoC

2.

FrompinStoC

3.

FrompinTtoC

4.

FrompinUtoC

5.

FrompinVtoC

6.

FrompinWtoC

7.

FrompinXtoC

8.

FrompinYtoC

or

pins

SHORTED

f.

using

are

replace

of

damage. Repair any damage found

of the flow control valve. If any of the

pins

pins B

and G

on

the flow control valve. If the

pins

are

the flow control valve.

the 1 E30-2 test box,

pins G, R, S, T, U, V, W, X, and Y prior to use.

must be checked for

continuity. These

fused inside the test box and must be tested

Connect the 1 E30-2 test box controller

I

following pins

the

Use the multimeter to check for 58-70 ohms between

NOTE: Priorto

e.

on

signs

SHORTED replace the flow control valve.

1.

OPEN

I

and the flow control unit for any

a.

(7,

Chart 1,

21-00-00)

to P30. Do NOT connect the test box to the electronic

(Ref. Figure 101).

On the 1 E30-2 test box, set the switches 1.

PowerSwitch-OFF

(OUT)

2.

Squat Switch

OFF

(OUT)

3.

Valve Switch

BLEED

4.

Bleed Flow-HI

NOTE: When

performing the

next

as

follows:

step, the test current of the multimeter must be less that 5 mA

to

prevent self-

heating. g.

Record the ambient air temperature. Use the multimeter to measure the ambient air temperature sensor resistance by measuring the resistance between pins D and P on the 1E30-2 test box. Record this resistance beside the ambient air temperature. Compare the resistance reading taken in this step with that shown in Chart 102 for the same ambient air temperature. If resistance is incorrect, replace the ambient air temperature sensor.

h.

Record the ambient air temperature. Use the multimeter to measure the ambient air flow sensor resistance measuring the resistance between pins N and Z on the 1 E30-2 test box. Record this resistance beside the

by

ambient air temperature. Compare the resistance reading taken in this step with that shown in Chart 103 for the same ambient air temperature. If resistance is incorrect, replace the flow control valve.

I

Oct

31/06Page

104

21-10-00

Raytheon

nircrdrt

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

i.

Connect the 1 E30-2 test box to the electronic controller.

j.

Apply

k.

On the 1 E30-2 test box, turn power

electrical power to the

on.

Use the multimeter to check for +28 vdc between

i.

present,

a

problem exists

in the

airplane wiring

pins A(+)

not

present, replace

and

Z(-)

on

the 1 E30-2 test box. If +28 vdc is not

harness to the 1 E30-2 test box

Use the multimeter to check for +12 ~1 vdc between

m.

n.

and turn the environmental control switch ON.

airplane

pins D(+) and Z(-)

on

or

airplane

power.

the 1 E30-2 test box. If +12 ~1 vdc is

the electronic controller.

pins M(+)

and

Z(-) on the 1 E30-2 test box. If the voltage is less than +0.3 vdc, substitute a voltage is greater than +0.6 vdc, replace known good electronic controller. If voltage is good after substituting an electronic controller, replace the original electronic controller. If voltage is still less than +0.3 vdc after substituting an electronic controller, replace the Use the multimeter to check for +0.3 to +0.6 vdc between

the flow control valve. If the

flow control valve. o.

Cycle

power

on

the I E30-2 test box and observe the

following

indications

on

the test box:

1.

CLOSE and MOTOR WINDINGS

2.

Bleed air shaft rotates to the closed

3.

After the microswitch is actuated, the OPEN light starts to blink, the FIREWALL SOLENOID and the bleed air shaft rotates to the open position.

lights

blink.

position, light comes

on,

If any of the events do not occur, replace the electronic controller and return to step i. If the electronic controller does not correct the problem, replace the flow control valve. p.

q.

On the 1 E30-2 test box, set the VALVE switch to AMBIENT and observe the box: 1.

OPEN and MOTOR WINDINGS

2.

Ambientshaftstays inopenposition.

1.

SQUATswitch lampilluminates.

2.

CLOSE and MOTOR WINDINGS

3.

Ambient air shaft rotates to the closed

If the CLOSE

lamp does

p~l

completes configuration.

This

not

indications

on

the test

blink.

On the 1 E30-2 test box, press the SQUAT switch and observe the

air shaft does not rotate, r.

lights

following

lamps

I following

conditions

on

the test box:

blink.

position.

blink, replace the electronic controller. If the CLOSE lamp blinks but the ambient

replace

the flow control valve.

the test. Turn power OFF

on

the 1 E30-2 test box and the

airplane. Restore airplane

to

original

21-10-00Page

105

Ray~heon

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FIREWALL SHUTOFF VALVE AIR CONTROL VALVE

AMBIENT

o

ENVIRONMENTAL BLEEC) AIR LINE

o

ELECTRONIC CONTROLLER

´•in iiHPFibW

O

GNO

.~s S~L

SNSSENS

nSW

OPEN

YINDINGS

O

FIREVALL

0

0000 HOTCB

Cj;L OUT

GND

SOLENOID

0

O CLOSE

SOUAT

BLEED FLOW

O

O

HI

BLEED

C] LOW

O O

V~LYE

O PCWER

P

AMBIENT

O IE30-2 TEST BOX

*IaeoaK

O

ATTACH TO CONTROLLER WIRING HARNESS

cs~FL2leldJe c

1E30-2 Test Box Connection

Figure

Oct

31/0621-10-00

101

A21

RaYIIheOn

Aireraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 102

AMBIENT AIR TEMPERATURE SENSOR RESISTANCE

Temp

"F

Resist W.

Temp "F

Resist W

Temp

"F

Resist W.

Temp

"F

Resist W

30

2822

58

1492

86

834

114

490

31

2756

59

1460

87

818

115

481

32

2691

60

1429

88

802

116

472

33

2628

61

1399

89

786

117

464

34

2567

62

1369

90

771

118

455

35

2507

63

1340

91

756

119

447

36

2449

64

1312

92

741

120

439

37

2393

65

1284

93

727

121

432

38

2338

66

1257

94

713

122

424

39

2285

67

1231

95

699

123

416

40

2232

68

1205

96

686

124

409

41

2182

69

1180

97

673

125

402

42

2132

70

1156

98

660

126

395

43

2084

71

1132

99

648

127

388

44

2037

72

1109

100

635

128

381

45

1991

73

1086

101

623

129

375

46

1947

74

1064

102

612

130

368

47

1903

75

1042

103

600

131

362

48

1861

76

1021

104

589

132

356

49

1820

77

1000

105

578

133

350

50

1780

78

980

106

567

134

344

51

1740

79

960

107

557

135

338

52

1702

80

941

108

547

136

332

53

1665

81

922

109

537

137

327

54

1629

82

904

110

527

138

321

55

1593

83

886

111

517

139

316

56

1559

84

868

112

508

57

1525

85

851

113

499

NOTE Tolerance:

A21

3"F

21-10-00

Oct

31/06Page

107

Ral~heon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 103 AMBIENT AIR FLOW SENSOR RESISTANCE

Temp "F

Resist W.

Temp

"F

Resist W

Temp

"F

Resist W.

Temp

"F

Resist W

30

2997

58

1527

86

826

114

471

31

2923

59

1492

87

809

115

462

32

2850

60

1458

88

792

116

453

33

2780

61

1425

89

776

117

445

34

2711

62

1393

90

760

118

436

35

2644

63

1362

91

744

119

428

36

2580

64

1332

92

729

120

420

37

2517

65

1302

93

714

121

412

38

2455

66

1273

94

700

122

405

39

2396

67

1245

95

686

123

397

40

2338

68

1218

96

672

124

390

41

2282

69

1191

97

658

125

383

42

2227

70

1165

98

645

126

376

43

2174

71

1140

99

632

127

369

44

2122

72

1115

100

620

128

362

45

2072

73

1091

101

608

129

356

46

2022

74

1067

102

596

130

349

47

1975

75

1044

103

584

131

343

48

1928

76

1022

104

572

132

337

49

1883

77

1000

105

561

133

331

50

1839

78

979

106

550

134

325

51

1796

79

958

107

540

135

319

52

1755

80

938

108

529

136

313

53

1714

81

918

109

519

137

308

54

1675

82

899

110

509

138

302

55

1636

83

880

111

499

139

297

56

1599

84

861

112

490

57

1562

85

843

113

480

NOTE Tolerance:

Page

tcO801

31/06

21-10-00

25%

A21

Rayfheon

Aircraft company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

TROUBLESHOOTING THE FLOW CONTROL VALVE a.

b.

Use the multimeter to check for 82-100 ohms OPEN

1.

FrompinRtoC

2.

FrompinStoC

3.

FrompinTtoC

4.

FrompinUtoC

5.

FrompinVtoC

6.

FrompinWtoC

7.

FrompinXtoC

8.

FrompinYtoC

the

following pins

Use the multimeter to check for 58-70 ohms between OPEN

c.

on

SHORTED

or

1E30-2 TEST BOX)

pins

of the flow control valve. If any of the

SHORTED replace the flow control valve.

are

or

(WITHOUT THE

Check for low inflow

replace the flow control

pins

B and G

on

the flow control valve. If the

pins

are

valve.

through the ambient air valve by disconnecting checking pin E for 28 vdc (Ref. Figure 1).

the electrical connector

(P30)

at the

I

electronic controller and NOTE:

Step

a

switch d.

must be arm

gear

or

with the

and extend the strut or disconnect the landing gear safety switch arm and position it as though extended. Use the multimeter to check P30-E for 0 vdc. If voltage is present, a fault is indicated

airplane

the strut

were

landing

safety switch arm connected and weight on the landing position as though the landing gear were compressed.

with the

disconnected and in

Jack the in the

performed

gear

switch.

safety

NOTE: If the 5-amp cabin temperature circuit breaker is open (pulled out), the ambient air will not operate. If the RH flow control valve appears deficient, perform the ambient air time delay test procedure. e.

only

flow from the flow control valve, check P30-A for 28 vdc. The valve cannot function without power When pin. power at P30-A is assured, connect the plug to the controller. The bleed air motor should rotate the bleed air shaft until it contacts the microswitch. When contact is made, the microswitch should activate the solenoid which allows the firewall shutoff valve to open. If actuation of the solenoid is not audible, the valve must If there is

no

at this

be considered suspect. NOTE: If the flow

pack

functioning f.

has

a

shorted motor, it will damage the controller. If controllers are to be swapped, the on the functioning side to ensure the controller is functioning properly.

non

side should be put

The ambient air temperature sensor may be checked by taking a resistance reading between P30-D and P30P. See Chart 102 for resistance values at specific temperatures. If further testing is desired, perform the AMBIENT AIR TEMPERATURE SENSOR FUNCTIONAL TEST PROCEDURE.

g.

The ambient air flow

sensor

103 for resistance values at

NOTE: A resistance h.

nn

When power is

reading

applied

may be tested

by taking

a

resistance

reading

within 25% of the values shown in Chart 103 is

to

between P30-N and P30-Z. See Chart

specific temperatures.

acceptable.

P30-A, actuation of the microswitch should not require

more

than 20 seconds.

21-10-00Page

109

Raytheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

When power is applied to P30-E, the ambient air flow exceed 45 seconds.

i.

modulating

NOTE: If the time limits exceed those noted in steps f or g, the valve is only if the fuselage leak rate is within specifications.

valve travel from stop to stop should not

probably faulty.

These checks

are

meaningful

AMBIENT-AIR TIME DELA Y TEST PROCEDURE

ii

the time

a.

Setup

delay

b.

Closeswitch S3.

c.

Closeswitch S1.

d.

The

e.

Openswitch

f.

To

module

(Ref. Figure 102).

voltage at pin 30 should be voltage should drop to 1 vdc.

verify

27 fl vdc when S1 is closed. After

a

time

lapse of

5 to 8 seconds, the indicated

S1.

manual

operation of

the ambient air solenoid, close switch S2. Indicated

voltage

at

pin

30 should be

27 ~1 vdc.

SI

28

~0.

1

IN

34

GROUND

32

MANUAL

30

OUTPUT

VDC 52

POWER

36 SWITCH

SWITCH

SOURCE TIME

DELAY

MODULE

30 OHM LOAD 53

SWITCH

C9dBB21809dS C

Ambient-Air Time

Delay Test Setup Figure 102

Oct

31/06Page

110

21-10-00

A21

Ray~heon

AiKraff

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

AMBIENT-AIR TEMPERA TURE SENSOR FUNCTIONAL TEST PROCEDURE The following test

uses a

temperature bath

to stabilize the ambient air

temperature

sensor

After the ambient air temperature sensor temperature is stabilized, its resistance is read If the resistance is incorrect, replace the ambient air temperature sensor. a.

Stabilize the temperature bath

(10,

Chart 1,

b.

Immerse 1/4 to 1/2 inch of the

sensor

c.

Measure tenninals A and B for

a

d.

Stabilize the temperature bath at 42" ~1"F.

e.

Immerse 1/4 to 1/2 inch of the

f.

Measure terminals A and B for

tip

21-00-00)

at a

specific temperature.

across

at 90" ~10F.

into the bath. Allow

sensor

to soak for

a

minimum of

resistance of 763 to 778 ohms. If the resistance is incorrect,

sensor

a

tip

terminals A and B.

into the bath. Allow

sensor

one

minute.

replace the

sensor.

to soak for a minimum of one minute.

resistance of 2110 to 2153 ohms. If the resistance is incorrect,

replace the

sensor.

21-10-00Page

111

AiKraft Company SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PRESSURIZATION

MAINTENANCE PRACTICES

FLOW CONTROL VALVE REMOVAL a.

Raise the

b.

Disconnect the flow control valve (11) and electronic controller

cowl door.

engine

(10)

electrical connectors

(1

and

8)

(Ref. Figure 201). c.

Remove the electronic controller

(10)

from the flow control valve

(11) (Ref.

ELECTRONIC CONTROLLER

REMOVAL). d.

Loosen the ambient air line clamp (7) and the environmental bleed air line clamp (13) to the flow control valve

(11). e.

f.

Disconnect the pneumatic bleed air line

(6)

and the P3 line

(12) from

the flow control valve

(11).

Remove the bolts (9), flow control valve (11), washers (5), washers (3), and locknuts (2) from the

mounting

bracket (4).

FLOW CONTROL VALVE INSTALLATION NOTE: When installing the flow control valve, the distance between the flow control valve and the firewall is adjusted by adding washers (5) between the flow control valve (Il)and the mounting bracket (4). Add washers (5) until all the flow control valve a.

Install the flow control valve (11)

mounting b.

bracket

the

the

on

(4) with washers (5)

Install the ambient air line clamp

(11). Torque

plumbing aligns

clamp

(7)

mounting

and

secure

with the flow control valve.

bracket

(4), adjust the flow control valve distance from the (9), washers (3), and locknuts (2) (Ref. Figure 201).

with bolts

and the environmental bleed air line

nuts to 32 to 37

clamp (13)

to the flow control valve

inch-pounds.

c.

Connect the pneumatic bleed air line (6) and the P3 line (12) to the flow control valve (11).

d.

Install the electronic controller

(10)

on

the flow control valve

(11) (Ref.

ELECTRONIC CONTROLLER

INSTALLATION). e.

Connect the flow control valve (11) and electronic flow controller (10) electrical connectors (1 and 8).

f.

Check the system for proper operation.

~21

21-10-00

Oct

31/06Page

201

1

Raytheon

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

5. 6. 7. 8.

FLOW CONTROL VALVE CONNECTOR LOCKNUT WASHER MOUNT WASHER PNEUMATIC BLEED AIR LINE AMBIENT AIR LINE CLAMP ELECTRONIC CONTROLLER CONNECTOR

9.

BOLi

I.

2. 3. 4.

10. Il.

12. 13.

ELECTRONIC CONTROLLER ;LOW CONTROL VALVE P3 LINE ENVI~ONMENTAL BLEED AIR

LINE

CLAMP

A

:~------2 13

12

4

io

8

9

DETAIL LH

SHOWN

A

C(J1FL2181139

TYPICAL

Flow Control Valve Removal and Installation

Figure 201

Oct

21-1000

A21

Raytheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

i.

2. 3. 4. 5.

6.

FLOW CONTROL VALVE SPACER ELECTRICAL CONNECTOR ELECTRONIC CONTROLLER WASHER MOUNTING BOLTS

2

65

43

C91882180951

C

Electronic Controller Removal and Installation

Figure

A21

202

21-10-00

Oct

31/06Page

203

RBytheMI

Aircraft Company

SUPER KING AIR MODEL 8300/B300C MAINTENANCE MANUAL

ELECTRONIC CONTROLLER REMOVAL

I

a.

Disconnect the electrical connector

b.

Remove the lockwire from the

(3)

mounting

on

the electronic controller

bolts

(4) (Ref. Figure 202).

(6) that secure the electronic controller (4)

to the flow control valve

(1). c.

Remove four

mounting

(6), washers (5),

bolts

spacers

(2),

and the electronic controller

(4).

ELECTRONIC CONTROLLER INSTALLATION a.

1

(4) on the flow control (2) (Ref. Figure 202).

Install the electronic controller

(5),

and spacers

bolts

b.

Install lockwire

c.

Connect electrical connector

on

mounting

(3)

valve

(1)

and

secure

with four

mounting

bolts

(6),

washers

(6).

to the electronic controller

(4).

FLOW CONTROL VALVE FLIGHT CHECK a.

Fly

the

system b.

airplane

in normal cruise mode at

to stabilize

(approximately

15

Verify that the pressurization system further action is necessary; steps d

c.

If both flow control valves

pressurization d.

altitude of

Turn

approximately 16,000 feet. Allow the pressurization

is able to maintain maximum differential pressure f are optional.

(6.5

~0.1

psi).

If it is,

no

through

working together cannot maintain maximum differential pressure, troubleshoot as instructed in Chapter 21-30-00.

the

control system

Turn off the LH flow control valve and allow the

Verify e.

an

seconds).

pressurization system

to stabilize

(approximately

15

seconds).

that the RH flow control valve is able to maintain maximum differential pressure.

on

stabilize

the LH flow control valve and turn off the RH flow control valve. Allow the

(approximately

15

seconds). Verify

pressurization system

to

that the LH flow control valve is able to maintain maximum

differential pressure. If

f.

one

by itself, that is not cause for rejection unless the valve does requirements of BLEED AIR FLOW RATE FLIGHT CH ECK or BLEED AIR FLOW RATE GROUND is satisfactory if both valves working together can maintain the pressure.

valve cannot maintain maximum differential

not meet the

CHECK. It

I

g.

With the cabin at maximum differential pressure, turn off both flow control valves and monitor the cabin pressure altitude. The normal leak rate is 2200 to 2400 feet per minute. If the rate exceeds 2400 feet per minute, check the pressure vessel for leaks and seal until the leak rate is within the limits.

Oct

21-10-00

Raytheon

nircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ENVIRONMENTAL BLEED AIR DUCTS Bleed air ducts

are

insulated with 2-inch-thick industrial

oven

insulation

(7,

Chart 2,

pressure sensitive, plain foil tape (6, Chart 2, 21-00-00). Wrap the tape in

approximately

one

and one-half inches. The

0.25-inch clearance from the

adjacent

wrapping may

compressed locally

as

in

place by

each wrap maintain to a necessary

hardware.

CAUTION: To prevent between

be

21-00-00) held spiral, overlapping

a

damage to the airplane electrical wiring, a the wiring and all bleed air lines located aft

minimum distance of 0.5 inch must be maintained

exchanger. At least 2 inches of space wiring forward of the heat exchanger. bleed air lines are wrapped with industrial

of the heat

must be maintained between uninsulated bleed air lines and all

This 2-inch distance may be reduced to 0.5 inch where the insulation.

oven

BLEED AIR FLOW RA TE FLIGHT CHECK Two environmental bleed air test ports

are

located under the center aisle floorboards in line with the cabin forward

partition. a.

Connect

a

manometer

Chart 1,

(1,

21-00-00)

to the venturi and

fly

the

airplane

to

approximately 16,000

feet

(Ref. Figure 203). b.

the

Operate

airplane

1 at several different outside air

temperatures. A variation of

at least 10" F between each

check is recommended. c.

Set the ENVIR BLEED AIR switch to NORMAL.

d.

Turn off the RH flow control valve. Allow the cabin record the manometer

e.

Turn

on

(approximately

15

seconds)

and record the manometer

(approximately

readings

as

faulty

if the

readings

are

NOTE: Use both tubes of the

not

precisely

seconds)

as

pressurization

and

zero

to

properly. However, the automatically be rejected

shown in the chart.

manometer(l, Chart 1, 21-00-00) when taking flow readings. For example,

shows 0.5 inch of water up from

reading

15

and outside air temperature.

If the bleed air flow is within the limits shown in Chart 201, the valves are functioning are provided only as a general guideline; a valve should not

values shown in Chart 201

An

to stabilize

the RH flow control valve. Tum off the LH flow control valve and allow the cabin

stabilize f.

reading

pressurization

and temperature.

if

one

tube

and the other tube shows 0.5 inch of water down from zero, the correct

would be 1 inch of water.

21-10-00

205

RayWleon

AiKraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

A ENVIRONMENTAL BLEED AIR TEST PORTS

MANOMETER

DETAIL

A C94FL2181545 C

Bleed Air Flow Check

Figure

Oct

31/0621-10-00

203

A21

Ray~heon

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

BLEED AIR FLOW RA TE GROUND CHECK If troubleshooting of the pressurization control system indicates that the inflow of bleed inadequate, the flow rate may be verified by the following procedure. Two environmental bleed purpose a.

or

located under the center aisle floorboards in line with the cabin floorboard partition.

are

Connect

a

(1, Chart 1, 21-00-00) (Ref. Figure 203).

manometer

floorboards b.

air is excessive

air test ports for this

Operate the airplane engines

to the venturi test

port connections under the center aisle

and note the ambient air temperature readings. Perform the readings corresponding to each engine.

following steps

in

order to record the manometer c.

Set the

d.

Set the ENVIR BLEED AIR switch to NORMAL.

e.

Set the temperature mode switch to MAN HEAT and hold the manual temperature control switch to DECR for 60 seconds.

f.

Set the LH bleed air control switch to OPEN. Set the RH bleed air control switch to ENVIR OFF. Record the

engine

manometer

power lever to

readings

flight

idle.

I

and ambient air temperatures.

NOTE: Use both tubes of the manometer

(1,

Chart 1,

indicates 0.5 inches of water up from

zero

21-00-00)

when

taking

a

reading. For example,

if the RH tube

and the LH tube indicates 0.5 inches down, the correct

reading

would be 1 inch of water. g.

Set the RH bleed air control switch to OPEN. Set the LH bleed air control switch to ENVIR OFF. Record the manometer

readings

and ambient air temperatures.

h.

Set the LH bleed air control switch to OPEN.

i.

through the LH and RH valves is within the limits shown in Chart 201 the flow control valves are working properly. However, the values shown in Chart 201 am provided only as a general guideline; a valve should not automatically be rejected as faulty if the readings are not precisely as shown in the chart.

j.

If bleed air flow

If the

readings

are

extremely high, inspect the check valve assembly for damage (the junction of the LH and RH bleed air lines).

check valve is located

under the floorboards at the k.

If the flow rate is

inadequate

or

excessive, troubleshoot the bleed air control system.

21-10-00Page

207

Raytheon

AiKraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

MANOMETER CONSTRUCTION a.

Obtain 3

b.

Mount the ruler in the center of the board.

c.

Mount the

yards

of 1/4-inch I.D. clear

plastic

tube

as

plastic hose,

Make

2.

The

3.

The tube should then travel up the board

4.

With the board in

loop (approximately

loop

12-inch ruler, and

2-inch

3- to 4-inch wide

by

12-inch

long board.

center of the tube.

radius) in the

in the tube should be attached to the board with the

an

a

follows:

1.

a

a

upright position

add

on

loop around the bottom of the ruler.

each side of the ruler and be attached to the board.

enough

water into the tube to indicate

approximately

5 inches

on

the ruler. d.

Attach the ends of the tube to the venturi.

The movement of the water up and down the tube will indicate the inches of water created

by

the venturi.

Chart 201 ELECTRONIC FLOW CONTROL VALVE FLOW VALUES With Ambient

With Ambient

MIN

MAX

MIN

MAX

80" And Above

.3

.7

.8

1.6

60"

.4

.8

.8

1.55

40"

.55

.95

20"

.65

1.05

0"

.8

1.2

-20" And Below

.9

1.3

TEMP "F

Bleed Air

Only

Bleed Air

Only

NOTE All values

Oct

31/06Page

208

21-10-00

are

inches of water.

A21

Raytheon

nircraft Company

SUPER KING AIR MODEL B300/8300C MAINTENANCE MANUAL

RULER ---ttt--i

CLEAR

PLASTIC

I

II

BOARD

TUBE -tS

---t---’ 2

O

IN.

_I_ WATER

IN

TUBE

I

1

3 4

131

1

5

~i

I

AT REST THE WATER EXAMPLE: IS AT O TN. ON BOTH SIDES. IF THE WATER GOES TO +I IN. ON ONE SIDE AND -I IN. ON THE OTHER SIDE THIS INDICATES 2 IN. OF WATER.

I

~M)-80-001

C

Manometer Construction

Figure

A21

204

21-10-00

Oct

31/06Page

209

Raythean

nircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ENVIRONMENTAL AIR DISTRIBUTION

(FLI1

DESCRIPTION AND OPERATION

THRU FL-492, FL-494 THRU FL-499; PM-1 THRU

FM-13)

through insulated ducting to outlets, located on the cabin floor and in the headliner in the passenger compartment and the flight compartment. Distribution ducting for bleed air heating is connected to the distribution ducting for the cooling system at the mixing plenum in the flight compartment and at Cooled and heated cabin air is distributed

the aft evaporator

plenum.

AIR DISTRIBUTION

(BLOWERS)

the air conditioning system is distributed by the vent blowers through insulated ducts to the and the flight compartment. The eyeball outlets can be adjusted to control the direction and compartment passenger

Cool air

produced by

amount of airflow and are located in the passenger

compartment headliner and in the flight compartment overhead

panel. The forward vent blower, located

adjacent to the forward evaporator under the

nose

compartment floor, is controlled

by the cabin temperature mode switch, the blower control switch and the speed controller. The speed controller controls only the forward blower. When the blower control switch is set to AUTO, the blower will operate in the LO speed when

the mode switch is set to each

position except OFF.

When the blower control switch is set to HI

or

LO,

the blower will operate in the selected speed regardless of the position of the mode switch (Ref. Figure 1). When the mode switch is set to OFF, the speed controller is energized through the LO or HI position of the blower control

switch. The controller is

energized through

the mode switch and the blower control switch when the blower control

is set to AUTO. The forward blower and aft blower circuit breakers

are

located

on

the DC power distribution

panel

under the center

aisle floorboards aft of the cabin forward partition. AFT BLOWER

The aft blower is controlled

by

the switch

placarded

AFT BLOWER, located

on

the

copilot’s subpanel,

and the aft

blower power relay. Cool air produced by the aft evaporator is distributed to the aft outlets in the headliner and to the aft floor outlets. The aft blower and the relay are located under the center aisle floorboards in line with the sixth

cabin window. Operation of the electric heat system will also require the aft blower. Refer to section 21-40-00 for information on the electric heating system.

BLEED AIR HEA T DISTRIBUTION

wing leading edge structure, is distributed through flight compartment. This warm air is then distributed through insulated ducting to floor outlets. The floor outlets include protective coverings and are located adjacent to the sidewalls on the floor of the passenger compartment and the flight compartment. A butterfly valve installed in the ducting is controlled by a push-pull cable located on the copilot’s inboard subpanel. The butterfly valve is located under the RH floorboards in line with the cockpit side window. The control cable can be pulled to divert most of the conditioned bleed air forward to the flight compartment. If conditioned bleed air in the main duct aft of the mixing plenum exceeds 300" F, an annunciator placarded DUCT OVERTEMP, illuminates when the overtemperature switch closes. The switch is located in the main distribution duct for cabin heating downstream of the mixing plenum (forward of the butterfly valve). Conditioned bleed air, cooled insulated

to the

ducting

Ambient air

can

solenoid latch

be

on

1\21

the heat

exchangers

in the

in the RH side of the

through the evaporator door located adjacent to the mixing plenum. A de-energized when the cabin pressure control switch is set to DUMP, allowing mixing plenum.

supplied

the door

ambient air to enter the

by

mixing plenum

to the cabin

can

be

21-20-00Page

1

RayHheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL DEFROST A1~ID FLIGHT COMPARTMENT HEAT Conditioned bleed air is distributed

through insulated ducting to outlets located forward of the instrument panel for heating Push-pull cables allow the pilot and copilot to control butterfly valves that regulate the amount of conditioned bleed air flow from the outlets. Controls for the pilot and the copilot are located on each outboard subpanel. Conditioned bleed air for windshield defrost is controlled by a push-pull control cable located on the pilot’s inboard subpanel. The control cable is pulled to allow conditioned bleed air flow through a butterfly valve and windshield defrost.

to the windshield.

Oct

31/06Page

2

21-20-00

azl

RBytheMI

nircraft

Company

SUPER KING AIR MODEL B300/8300C MAINTENANCE MANUAL

30A

A

VENT BLOWER

(M ~H

POWER

i..

H’

I

FOWARD BLOWER

LO

BLOWERSPEED

AUTO

CONTROLLER

OFF

1

I

f VENT BLOWER

12

P

S--f-~

CONTROLSWITCH

MNLHT

;s

13

17

MODE

CONTROL CABIN TEMP

MNL

SWITCH

(T

COOL

CONTROL 5A

ON

4

I~

2

20A

1 I

AFT EVAPORATOR

AFT BLOWER

1

63 OFF

BLOWERPOWER

AFT ELECTRIC

AFT BLOWER

I

I

HEAT ELEMENT

SWITCH CIRCUIT CARD ASSY A278

AFT

AFT BLOWER RELAY 13

BLOWER SWITCH

BLOWERPOWER

RELAY

1151

HEATERls SENSEONI

I-rLsd

5A

I

I

I

100A

1

I

AFT

I

I

ELECTRIC HEAT

I

AFT POWER RELAY II ANN OUT 14

GND

IN

191

CHANNEL OUT 118

1

AFT ELECTRIC HEAT POWER

ELECTRIC HEAT

RELAY

ON ANNUNCIATOR

CIRCUIT CARD ASSY A140 Fule

06125MA.AI

Vent Blowers Electrical Control Schematic

Figure

A21

1

21-20-00

Oct

31/06Page

3

Ray~heon

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ENVIRONMENTAL AIR DISTRIBUTION MAINTENANCE PRACTICES (FL-1 THRU FL-492, FL-494 THRU FL-499; PM-1 THRU FM-13) CAUTION: To prevent damage to the airplane electrical system, maintain a minimum clearance of 2 inches between uninsulated bleed air lines and any electrical wiring. The clearance requirement may be reduced to 0.5 inch if the bleed air lines

are

insulated.

inspecting or installing environmental ducts anywhere in the airplane, ensure there is proper Pay particular attention to control cables, push-pull tubes, bellcranks, torque tubes, etc. for clearance. Ensure any clamps and attaching hardware is secure and have proper clearance. proper When

clearance.

REMOVAL, FORWARD

VENT BLOWER

from the RH side of the

a.

Remove all avionics

b.

Remove the RH floorboard in the

c.

Disconnect the electrical leads from the blower.

d.

Remove the

e.

attaching bolts

Loosen the nut the

clamp

equipment

and

on

the

to

gain

access

the blower to the evaporator the blower and motor

secures

the blower and motor

to the forward vent blower.

plenum.

assembly to

the

mounting

bracket to release

assembly.

INSTALLATION, FORWARD

a.

Position the blower and motor

b.

Secure the blower and motor

c.

Connect the electrical leads to the blower.

d.

Install the

nose

compartment.

baggage compartment

secure

clamp which

remove

VENT BLOWER

which

nose

nose

assembly

assembly

the evaporator

on

on

its

mounting

plenum

and

bracket with the

secure

attaching bolts.

it with the

attaching clamp.

compartmentfloor.

VENT BLOWER REMOVAL, AFT a.

Remove the center aisle carpet and floorboards in line with the fifth cabin window to

b.

Disconnect the electrical leads from the terminals

c.

Remove the 7

d.

Loosen the nut remove

p~,

attaching bolts securing on

the

clamp

which

the motor and blower

on

access

to the blower.

the blower.

the blower to the evaporator

secures

gain

the blower motor to the

plenum.

mounting

bracket to release the

clamp and

assembly.

21-20-00

Oct

31/06Page

201

RaYCLeOn

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

VENT BLOWER INSTALLA TION, AFT a.

Install the blower and motor

b.

Install the

clamp

assembly on

around the motor and

the evaporator

plenum

tighten the locking

nut to

and

secure

secure

it with 7

attaching

the motor and blower

bolts.

assembly

to the

mounting bracket. c.

Connect the electrical leads to the blower terminals.

d.

Install the floorboard and carpet in the center aisle.

BUTTERFLY VALVE RIGGING, HEATAND DEFROST The

butterfly

valves in the

pilot’s

copilot’s heat outlet, and the defrost duct shut off the flow of air rigged completely closed when the applicable cable is pushed in to its stop.

heat outlet, the

the outlets. Each valve should be

to

BUTTERFLY VALVE RIGGING, MAIN DUCT The

butterfly

valve in the main distribution duct is located in the main distribution duct in line with the

compartment side window. The valve should be

rigged completely

closed when the cable is

pushed

in to its

flight stop

I (Ref. Figure 201). NOTE: Even

though

the valve is

rigged closed,

it does not shut off airflow

completely

due to the holes in the valve

shutter.

OVERTEMPERATURE SENSOR

BUTTERFLY VALVE

\j

i

CABLE

MAIN DUCT

DETAIL

FLIGHT COMPARTMENT FLOOR OUTLET

ro

A

Butterfly

Oct

HEATING

31/0621-20-00

Valve

Rigging, Main Heating Figure 201

Duct

A21

Raytheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FLAPPER VALVE TEST PROCEDURE The

flapper valve

air noise is noted

should be checked for proper operation at the interval specified in Chapter 5 or sooner if excessive during operation of the pressurization system. The following steps should be utilized for the flapper

valve test: a.

Disconnect the air duct at the LH firewall shutoff valve

b.

Operate

the RH

engine

with both bleed air switches

(Ref. Figure 202).

on.

If

no

significant

air flow is noted at the open duct, the

duct may be reconnected to the flow control valve. c.

Shutdownthe RH

d.

Disconnect the air duct at the RH firewall shutoff valve.

e.

Operate the

LH

engine.

engine

with both bleed air switches

on.

If

no

significant air flow

is noted at the open duct, it may

be reconnected to the firewall shutoff valve.

significant air flow was noted at either of the open ducts during the test procedure, the flapper valve assembly operating properly. If significant air flow was noted at either of the open ducts during the test, the flapper valve assembly must be replaced, and the downstream ducts must be examined to assure that none of the flapper valve components are lodged in them. If

no

is

CHECK (FLAPPER) VAL VE REMOVAL a.

Remove the RH foMlard cabin chair and the RH carpet and floor

b.

Remove the tape and insulation from the valve

c.

Loosen the

clamps

on

the

connecting

assembly and connecting

hoses and

NOTE: It may be necessary to slide the hoses back check valve.

CHECK

(FLAPPER)

a.

Position the

b.

Tighten

c.

Install the

the

panel just forward of

remove

on

the

hoses

the main spar.

(Ref. Figure 203).

flapper valve.

the ducts in order to

gain sufficient

clearance to

remove

the

VALVE INSTALLA TION

flapper valve

in line with the ducts and slide the

attaching clamps

connecting

hoses onto the valve

(Ref. Figure 203).

and install the insulation and tape.

inspection plate, soundproofing, carpet,

and

furnishings.

21-20-00

Oct

31/06Page

203

1

Raytheon

AiKraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

DISCONNECT AT THIS POINT

FIREWALL FLOW CONTROL VALVE

DETAIL

B

FLAPPER VALVE

FLOW CONTROL VALVE

VENTURI

DETAIL

DETAIL

C

A 350-452-27

Check

Page

tcO402

31/06

21-20-00

(Flapper) Valve Test Figure 202

Procedure

A21

222622288

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FS 188 00

FLAPPER VALVE ASSEMBLY RH SEAT

PEDESTAL 66 167 62

A

CONNECTING HOSE

DETAIL

A

350-452-28

Check

A21

(Flapper) Valve Replacement Figure 203

Procedure

21-20-00

Page

205

Oct 31/06

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ENVIRONMENTAL AIR DISTRIBUTION

(FL-493,

FL-500 AND

DESCRIPTION AND OPERATION

FM-14 AND

AFTER;

AFTER)

accomplished through the use of electrical servo valves controlled by the mixing box and forward plenum. Mechanical check valves within the ducting, prevent back flow direction changes when portions of the ducting are used for both cooling and heat.

Distribution of bleed air and cooled air is

system controller, if the airflow

a

The forward evaporator pulls air from the cockpit through an inlet located in front of the copilot’s rudder pedals. Air from the forward evaporator is directed into the forward plenum. A servo valve in the forward plenum controls airflow direction.

During

electric heat mode, all of the forward evaporator air is directed through the electric heater and During all other modes, the air is directed primarily to the glare shield outlets and

ducted to the center aisle outlet.

secondarily

excess

air flow is directed

through

the electric heat

ducting

to the center aisle outlet.

fitting located under the right cabin seats, forward of the wing spar. The engines and directs it into the intake of a venturi connected to the mixing box plenum. Bleed air flowing through the venturi pulls ambient cabin air from under the floorboards into the venturi through a muffled air intake. The bleed air is cooled by mixing it with the ambient cabin air in the venturi. Two ports check the pressure of the bleed air before entering the venturi, and the pressure within the venturi, to assist in troubleshooting the system. A thermostatic switch measures the temperature of the air leaving the venturi. If the air temperature exceeds 300" F, an amber annunciator (Duct Overtemp) in the cockpit will illuminate. Bleed air from both

tee

fitting

engines flows

to

a

tee

combines the bleed air from both

mixing box assembly is located under the cabin floor at FS 168.75. The mixing box assembly directs the blended specific duct outlets. When the airplane heat load (cooling requirement) is low, the mixing box will temper cold evaporator air with warm air, and direct excess bleed air to the aft compartment to be exhausted by the outflow valves. The mixing box has one inlet for engine bleed air, and four outlets controlled by three separate servo valves. The servos are cockpit heat, cockpit add heat, and cabin heat.

The

air to

cockpit heat servo valve sends warm bleed air through a muffler at cockpit floor outlets and the outlets forward of the copilot’s rudder pedals.

The

the

mixing box,

and then forward to the

cockpit add heat servo valve sends warm bleed air to the forward plenum. When activated for heating, the cockpit add heat servo will divert warm bleed air to the cockpit evaporator. The system controller decides how much heat is required, and positions the cockpit add heat servo valve to provide full heat or partial heat.

The

The Cabin Heat

servo

simultaneously adjusts two separate

air valves, in two of the

mixing plenum outlets. One valve

a bypass valve that routes bleed air to the cabin aft compartment. The other valve routes air to the cabin sidewall outlets. The two valves are mechanically linked so that as the servo moves, one valve will close as the other valve

is

opens. When the cabin heat servo is at full travel, one valve will be fully closed and the other will be fully open. When the servo is at the midpoint of its travel and both valves are partially open, there will be reduced airflow to both the cabin sidewall outlets and the aft compartment outlets. Since both valves cannot be closed at the air will always supply pressurization for the cabin. When the

system controller requires heat, the cabin heat bypass valve

to the aft

same

time, bleed

compartment is closed and the

cabin heat valve to the sidewall ducts is open so warm bleed air will be directed to the cabin sidewall outlets. Mechanical flapper valves in the aft end of the ducting are closed by the bleed air pressure, to prevent it from

entering

the overhead outlets.

The cabin evaporators pull air through sidewall floor return air outlets into the evaporator plenum with the evaporator blowers. During cooling mode, the cabin heat bypass valve on the mixing box is open, to send the warm bleed air to the aft cabin

compartment outlets. The mechanically linked valve that is connected

to the cabin sidewall

outlets,

is closed to prevent warm bleed air from entering the cabin sidewall ducts from the forward end. The cabin evaporator blowers force the mechanical flapper valves in the duct open and supply cooling airto the sidewall outlets

from the aft end.

Cooling

air is also sent to the overhead outlets.

21-21-00

Raytheon

nircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL The Cabin add Heat an

opening

warm

the

bleed air

servo

plenum

servo

is located forward of the cabin evaporators at FL 261.00. The servo valve is attached to right inboard duct. When activated for heating, the cabin add heat servo will divert

in the bottom of the

valve

normally through

sent to the aft a

compartment, back

flex duct and into

a

tube

to the cabin

assembly,

for the evaporators. The system controller decides how or partial heat.

evaporators. The

warm

air is carried from

through the bulkhead and into the much heat is required, and positions the cabin add which passes

heat valve to provide full heat

When the system is operating in the man cool mode, the cabin heat and cockpit heat valves are both driven to direct bleed air to the aft compartment outlets, when the system is in man heat mode, both valves are driven to allow bleed air into the cockpit and cabin floor outlets. When in man heat or man cool mode, the cockpit add heat and cabin add heat valves

are

directly

controlled

AIR DISTRIBUTION

by

the

cockpit

and cabin temp rheostats,

respectively.

(BLOWERS)

Cool air produced by the air conditioning system, is distributed by blowers through insulated ducts to the cabin and cockpit. An electronic system controller monitors temperatures and controls airflow with electrically controlled

the

servos

and blower

airflow, and

are

speeds.

The

adjustable

air outlets

located in the cabin headliner and

are

used to control the direction and amount of individual

cockpit overhead panel.

COCKPIT BLOWER The cockpit blower is located forward of the FS 84.00 bulkhead and is part of the forward evaporator assembly. When the air conditioning system is active, the cockpit blower draws air from under the cockpit floorboards and

through the floor air-return filter at the copilot’s feet. Blower speed is controlled by the system controller. The return air flows over an angled plate, through the bulkhead opening and is pulled into the sealed compartment forward of the bulkhead, containing the forward evaporator and cockpit blower. The cockpit blower pulls the cockpit return air in the chamber through the forward evaporator, where the air is cooled, and discharges it through the bulkhead duct into the forward plenum on the aft side of the FS 84.00 bulkhead. The position of the plenum servo flapper valve determines how the air is routed. The forward plenum can then distribute the cooled air to the glare shield outlets and to the forward cabin center floor outlet. Except in electric heat mode, the cockpit blower speed can also be manually selected using the cockpit blower rheostat. CABIN BLOWERS The cabin blowers blowers with each

are

located

on

the

airplane centerline,

between FS 261.00 and FS 280.75. There

are

two cabin

having separate evaporator and thermal expansion valve. Blower speeds are commanded by the system controller. The cabin blowers draw air through the sidewall floor return air inlets into the compartment where the blowers and evaporators are located. The blowers then push the air through both evaporators into ducting a

that carries the air to the overhead outlets. Cabin blower speed rheostat.

Oct

21-21-00

can

also be

manually selected using the cabin blower

Raytheon

AiKraft

company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ENVIRONMENTAL AIR DISTRIBUTION MAINTENANCE PRACTICES (FL-493, FL-500 AND AFTER; FM-14 AND AFTER) SERVO POSITIONING CAUTION: Do not apply power other than 14 vde to the a.

Connect the

b.

Turnthe

servo

battery

to its

mating

connector

The the

servo can

the electrical harness.

on

switchtoON.

NOTE: The electronic controller will then c.

servos.

be

positioned

position

to its neutral

the

servo

in the open

or

closed

(midway) position by grounding

position

Pin 3 and

to allow installation.

applying

14 vdc to

pin

1 of

servo connector.

FORWARD PLENUM SERVO REMOVAL a.

Remove the

copilots

b.

Remove the

flight compartment

c.

Disconnect the flexible duct from the forward

d.

Disconnect the electrical connector from the

e.

Remove four bolts with the servo,

seat

(Ref. 25-10-00). on

the

copilots side

plenum

to

gain

between FS 84.00 and FS 100.50.

access

to the

servo

(Ref. Figure 201).

servo.

plenum and

the

servo

to the

it from the

servo

and reassemble the shaft

connecting

remove

floorboards

remove

the

servo.

adapter

If the shaft

adapter

comes

out

onto the valve shaft.

FORWARD PLENUM SERVO INSTALLA TION Install the

a.

plenum and secure with four bolts (Ref. Figure 201). Note the position of the servo and matching position to assist installation. If the servo position is rotated such that the servo be assembled with the shaft position, adjust the servo position (Ref. Servo Positioning). servo on

the

rotate the valve to the

cannot

b.

Connect the electrical connector to the

c.

Connect the flexible duct to the forward

d.

Install the

flight compartment floorboards

e.

Install the

copilots

pal

seat

servo

and

plenum on

the

secure

and

wiring.

secure

copilots

with

clamp.

side between FS 84.00 and FS 100.50.

(Ref. 25-10-00).

21-21-00

Oct

31/06Page

201

Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

INLET AIR FILTER

INLET SCREEN

WASHER

(2)

BOLT

(2)

BULKHEAD

(4)

BOLTS

SERVO BOLTS

(4 EA) SERVO FOOT OUTLET TEE

COPILOT FOOT OUTLET

SERVO CONNECTOR

.I .I

FS 84.00 BULKHEAD

.I ~I

00

I WL 105.00

I I

.35W.

I´•

I

REF

1

I

CLAMP PllOTFOOT

I

II

OUTLET FLU(IBLE

LEFT DUCT

II I

G

U

BI

I

CLAMP

FORWARD PLENUM

RIGHT FLU(IBLE DUCT

ASSEMBLY

SERVO CONNECTOR

DETAIL

A

SERVO

Fonnrard Plenum Servo

Figure

Oct

31/062121-00

201

A21

Raytheon

AiKraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FORWARD PLENUM REMOVAL WARNING: Never

place fingers

between the valve

plate

and side wall when

plenum

is

electrically

connected. a.

Remove the

copilots

b.

Remove the

flight compartment floorboards

c.

Remove the electric heater

d.

Remove the inlet filter,

seat

(Ref. 25-10-00). on

the

copilots

side between FS 84.00 and FS 107.00.

(Ref. 21-41-00). clamp, and disconnect the LH side flexible duct from

remove

the foot outlet tee

(Ref. Figure 201). e.

Remove two bolts and washers that

f.

Remove two

g.

Remove four bolts

h.

Remove the forward

i.

Remove three

j.

Remove Four bolts

screws

secure

that attach the upper

securing

the

plenum

screws

the inlet

servo

to the

ducting

angled plate

and

screen.

plenum

remove

the

remove

plate and inlet

Forward Plenum Servo

(Ref.

and

the

plenum

ducting.

screen.

Removal).

that attach the forward duct to the forward side of the

attaching

the

plenum.

to the forward bulkhead and remove the

plenum.

FORWARD PLENUM INSTALLATION WARNING: Never

between the valve

place fingers

plate and side

wall when

plenum

is

electrically

connected. forward bulkhead with four bolts

a.

Place

b.

Install the forward duct to the forward side of the

c.

Install the forward

d.

Install the

e.

Install the upper

plenum

mating

into

position and

plenum

secure to

servo

and inlet

angled plate

ducting

to the

(Ref.

plenum

and

Forward Plenum Servo

screen

plenum

and

and

secure

secure

secure

with three

screws.

Removal).

with four bolts.

with two

screws.

Wrap

foam insulation tape around duct

seam.

f.

Install the inlet

g.

Connect LH side flexible duct to the foot outlet tee and install inlet filter.

h.

Install the electric heater

j.

(Ref. Figure 201).

screen

and

secure

screws.

(Ref. 21-41-00).

Install the

flight compartment

Install the

copilots

seat

with two

floorboards

on

the

copilots

side between FS 84.00 and FS 107.00.

(Ref. 25-10-00).

21-21-00

Raldheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

MIXING BOX SERVO REMOVAL a.

Remove the

b.

Remove the cabin floorboards at FS 168.75.

c.

Disconnect the electrical connector from the

d.

right passenger

Remove four bolts

seats at FS 168.75

connecting the

with the servo, remove it from the

servo

(Ref. Figure 202).

servo

to the

servo

(Ref. 25-20-00).

mixing

box and

remove

and reassemble the shaft

the

servo.

adapter

If the shaft

adapter comes

out

onto the valve shaft.

MIXING BOX SERVO INSTALLATION a.

Install the

mixing box and secure with four bolts (Ref. Figure 202). Note the position of the servo matching position to assist installation. If the servo position is rotated such that the assembled with the shaft position, adjust the servo position (Ref. Servo Positioning).

servo on

the

and rotate the valve to the servo

cannot be

b.

Connect the electrical connector to the

c.

Install the cabin floorboards at FS 168.75.

d.

Install the passenger seats

servo

and

secure

wiring.

(Ref. 25-20-00).

MIXING BOX REMOVAL WARNING: Never

place fingers

between the valve

plate

and tube wall when

mixing

box is

electrically

connected.

right passenger seats

a.

Remove the

b.

Remove the cabin floorboards at FS 168.75.

c.

Disconnect the venturl

d.

Disconnect the electrical connector and

e.

Removethe

mixing

assembly

at FS 168.75

(Ref. 25-20-00).

mixing

and flex duct attached to the remove

the

mixing

box

box

(Ref. Figure 202).

mounting hardware.

box.

MIXING BOX INSTALLATION WARNING: Never

place fingers between

the valve

plate

and tube wall when

mixing

box is

electrically

connected. Place the

mixing box

and

secure

with

b.

Connect the electrical connector to the

mixing

box and

c.

Connect the venturi

d.

Install the cabin floorboards at FS 168.75.

e.

Install the passenger seats

a.

Page

tcO31/06 402

into

position

assembly

and flex duct to the

mounting

hardware

secure

mixing

(Ref. Figure 202).

wiring.

box.

(Ref. 25-20-00).

21-21-00

nnl

Raytheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COCKPIT ADD HEAT SERVO BLEED AIR TEMP

FS 168.75

158.00

FS 179.53

SENSOA

INBD

SERVO 2

EA)

SERVO

I

,FLOOR OUTLET

COCKPIT HEATSERVO MIXING BOX

BOLTS

(3 EA)

I

I

I

VENTURI

/I

I I/

LdY VI

/V I

I

ASSEMBLY

I

L

FLEX DUCT THERMAL

SWITCH

O

SERVO BOLTS

(4 EA)

A

ELECTRICAL

MIXING BOX

CONNECTOR

BOLTS (2

EA)

(3 EA) ELECTRICAL CONNECTOR COCKPIT

I

CABIN

HEAT SERVO

I

HEAT SERVO

i

MIXING BOX

VIEW

A

PLENUM FLEX DUCT

ORI@INAL As Received

ATP

A21

By Mixing Box and Servos Figure 202

21-21-00

Oct

31/06Page

205

Raytheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CABIN ADD HEA T SERVO REMOVAL a.

Remove the passenger seats at FS 261.00

b.

Remove the cabin floorboards forward of FS 261.00.

c.

Disconnect the outboard square duct at FS 261.00 from the duct aft of FS 261.00 to

(Ref. 25-20-00).

gain

access

to the servo

(Ref. Figure 203). d.

Disconnect the electrical connector from the

e.

Remove four bolts

adapter

comes

connecting

the

out with the servo,

servo

servo.

to the heater duct

remove

it from the

assembly bracket,

servo

and

remove

and reassemble the shaft

the

servo.

If the shaft

adapter onto the valve

shaft.

CABIN ADD HEA T SERVO INSTALLA TION a.

Install the

position

servo on

of the

the heater duct

servo

rotated such that the

(Ref.

Servo

(Ref. Figure 203). Note the servo position is matching position assembled with the shaft position, adjust the servo position

assembly

bracket and

secure

servo

cannot be

with four bolts

to assist installation. If the

and rotate the valve to the

Positioning).

b.

Connect the outboard square duct at FS 261.00 to the duct aft of FS 261.00 and

c.

Connect the electrical connector to the

d.

Install the cabin floorboards at FS 261.00.

e.

Install the passenger seats at FS 261.00

Oct

31/06Page

206

21-21-00

servo

and

secure

(Ref. 25-20-00).

wiring.

secure.

Raytheon

AiKraft Company

SUPER KING AIR MODEL B300/8300C MAINTENANCE MANUAL

HEAT OUTLET

SERVO

HEATER DUCT

A

B CLAMP

CLAMP

DETAII

HEATER

A

AIR

DE LBTCUD

BYP~5S

FS

FLEX DUCT

261.00

FS 251.20

SERVO

c´•-"-~.

);7

~ia

BRACKET

CLAMP

C´•´•’ ’7

e

\´•´•~i WASHER

BOLT(4EA)

INSULATING

HEATER DUCT

WASHER

ASSEMBLY TUBE FLEX DUCT

B Cabin Add Heat Servo

Figure 203

A21

21-21-00

Oct

31/06Page

207

Ral~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURIZATION CONTROL

DESCRIPTION AND OPERATION

The outflow of

pressurized cabin air is controlled by the outflow valve and safety valve, a cabin pressure controller, safety solenoids. The cabin pressure control switch, the climb rate indicator, the cabin differential pressure indicator, and the pressure controller selectors are located on the pedestal. Orifices installed in the vacuum line and in the vacuum control line help limit the amount of change in cabin pressurization. Filters are incorporated

and preset and

in the cabin air port

the cabin pressure controller and in the safety valve. Outflow and safety valves sense atmospheric pressure through vents that protrude through the aft pressure bulkhead. A moisture accumulation drain in the vacuum control line is located under the RH side panel in line with the cabin window farthest aft. The outflow and

safety

into the

valves

on

are

access area

installed in

immediately

a

recessed

area on

aft of the valves

the aft pressure bulkhead. Excess cabin pressure is vented 1 and 2).

(Ref. Figures

Vacuum pressure for the pressure controller is controlled by the vacuum regulator that also regulates instrument vacuum. The regulator is located immediately forward of the forward pressure bulkhead. Refer to Chapter 37-00-00 for further information

the

on

The inflow of air for cabin is controlled

by

vacuum

regulator.

pressurization

is environmental bleed air from the LH and RH

bleed air/ambient flow control valves that

compressor. Refer to

Chapter 21-10-00 for information

on

are

engines.

The rate of inflow

connected to bleed air lines from each

the valves and the control of bleed air from each

engine engine

compressor. When the cabin pressure control switch is set to PRESS (pressurize) prior to takeoff, the energized preset solenoid shuts off the regulating vacuum to the pressurization controller (Ref. Figure 1). The energized pressure safety

solenoid opens, making safety valve to open the pressure controller. the

In

vacuum so

control available to the

safety

valve. The

that the cabin pressure altitude and the rate of

vacuum

control allows the

change

of cabin pressure

in

diaphragm can

be set

on

flight (when

the squat switch is in the up position), the preset solenoid (normally open) is de-energized and allows applied to the controller. The safety solenoid valve (normally closed) de-energizes and shuts off direct vacuum to the safety valve. The controller then allows the outflow valve to relieve excess cabin pressure according to the altitude and rate of change set on the controller. A door seal solenoid is de-energized when the preset and safety solenoids are de-energized, and the door seal valve (normally open) allows pneumatic bleed air to pressurize the door seal. If atmospheric pressure exceeds cabin pressure, a "negative pressure" relief diaphragm in the outflow valve opens to allow atmospheric pressure to relieve cabin negative pressure. When the cabin pressure control switch is set to the PRESS position, the solenoid latch is energized to the closed position and magnetically holds the ram air door closed. When landing (the LH squat switch being in the down position), the preset solenoid and the dump solenoid are energized and the cabin is allowed to depressurize through the opened safety valve. The preset solenoid is located forward of the flight compartment pedestal and the safety solenoid is located adjacent to the vacuum

to be

outflow valve and When the

safety valve.

on the ground with the squat switch in the down position, the cabin pressure control switch can position to de-energize the preset and safety solenoids and allow the pressure control system though the airplane were in flight.

airplane

is

be set to the TEST to function

as

Ambient air

can

enter the cabin when the cabin pressure differential is minimal and the

evaporator door solenoid

latch is

opened (de-energized) by setting the cabin pressure control switch to DUMP. Ambient air is then allowed flow into the fresh air inlet, through the solenoid controlled door, and into the forward evaporator plenum.

~21

21-30-00

Oct

to

31/06Pagel

Ray~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Cabin pressure altitude and the cabin-to-atmosphere pressure differential are indicated on the differential pressure indicator. The pressure differential is expressed in psig and the pressure altitude is expressed in thousands of feet. The climb rate indicator allows

monitoring of the rate of change of cabin pressurization. Cabin pressure altitude and of cabin pressure altitude can be controlled by using the appropriate adjustment knob located on the cabin pressure controller; however, the differential pressure indicator and the climb rate indicator are not directly

the rate of

change

connected to the controller.

pressurization and turning

Turning

the

rate-of-change

selector clockwise will increase the rate of

the selector counterclockwise will decrease the rate of

change

of cabin

change.

If cabin pressure altitude exceeds 12,500 +0 -500 feet, the cabin altitude warning pressure switch closes, and the annunciator light labeled CABIN ALT will illuminate. The cabin altitude warning circuit is separate from the

warning

pressu rization control circuit. The pressure switch in the altitude warning circuit is installed on the ove rhead electrical equipment panel located on the flight compartment. Refer to Chapter 39-20-00 for switch maintenance practices. A red

warning

annunciator

light (placarded

CABIN DIFF

HI)

in the

glare

shield will illuminate if the cabin differential

pressure should become excessive. This system is protected by a 5-amp circuit breaker (placarded CABIN DIFF HI) which is located in the right circuit breaker panel. There is also a test switch in the right inboard subpanel.

(absolute air pressure regulator) provides automatic override of an open outflow/safety valve signal to limit cabin altitude to 13,500 ~1500 feet. This is accomplished by airflow between the controller and the outflow/safety valve being regulated to close the modulating valve if cabin pressure altitude exceeds limits within the calibrated range. A bellows inside the limit controller chamber is controlled by the cabin pressure reference and expands if cabin pressure decreases, thereby activating a poppet valve internally to relieve the vacuum pressure pulling the outflow/safety valves towards open. This causes the outflow/safety valve to close. This will effectively reduce cabin pressure loss rate by automatically overriding the valve if the control system malfunctions. Altitude limit controllers

Oct

31/06Page

2

21-30-00

nz~

RayIheon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

000

ALTITUDE LIMTT CONTROLLER

00_

E

8,

D--1’

I

A

n n

Y

D

I I

a

I I

MOISTURE

TO VACUUM SOURCE

n n

It

RED

I

I

6C~

I

I I

I I

I I

I I

I I

I I

PORT "2" CONTROL CONNECTION

n

HEAD

DRAIN VALVE

NORMALLY OPEN

ORIFICE ASSY

c ~iPh’l

MOISTURE DRAIN VALVE

CABIN PRESSURE PRESET SOLENOID VALVE

OUTFLOW VALVE POPPET

CONTROL CHAMBER POPPET VALVE RETURN SPRING

’d

G

DETAIL

ASSEMBLY

DIFFERENTIAL CONTROL CALIBRATION SPRING

i

DIAPHRAGM

METERING VALVE

DIAPHRAGM DETAIL

F

B

SUPPORT DIFFERENTIAL CALIBRATION SCREW

TO LH SUBPANEL GROUNDING PLUG

CABIN PRESSURE SAFETY SOLENOID VALVE

NOISE SUPPRESSION SCREEN

DIAPHRAGM ASSEMBLY DIFFERENTIAL CONTROL

POPPET VALVE COVER

PORT "1" TRUE NORMALLY CLOSED

II

I

JSTATICATNIOSPHERE CONNECTION WITH ORIFICE

I I

UPPERVALVEDIAPHRAGM DETAIL

PLUG

OUTFLOW

I

VALVE

WHITE 24 VDC

CABIN AIR FILTER

ELECTRICAL SYSTEM

RATECONTROLVALVE,\ RAM AIR DOOR MAGNETIC TCH I

REUEFVALVE

5 AMP PRESSURE

CONTROL CIRCUIT BREAKER

II

RH CIRCUIT BREAKER CONTROL PANEL)

RELIEF VALVE

Ll~ii

ROCKER ARM

DUMP

9 LANDING GEAR SAFETY SWITCH

DETAIL

E

BASE ASSEMBLY INNER

DIAPHRAGM

F

SUPPORT

DIFFERENTIAL CALIBRATION SCREW

DIFFERENTIAL CONTROL DIAPHRAGM ASSEMBLY

CABIN PRESSURE

C

COFTTROLSWITCH

REFERENCE PRESSUAE

Q. SHOWN IN

TRUE STATIC ATYOSPHERE

PRESS. POSITION

2 oump

’6,

DETAIL

L

3

SCREEN

CABIN AIR FILTER WITH ORIFICE K

1

PRESS.

SUPPRESSION

POPPET VALVE RETURN SPRING

UP ~urs

K

DETAIL

NOISE

PORT "1" TRUE STATIC ATMOSPHERE CONNECTION WITH ORIFICE

AIACRAFTV~CUUM

O

OUTFLOW VALVE POPPET

METERING VALVE

0~9;

TEST

~I

HEAD

CONTROL CHAMBER

DIAPHRAGM

D

RATE PRESSURE

1213

PORT"P" DEPRESSURIZATION CONNECTION

DIFFERENTIAL CONTROL CALIBRATION SPRING

RED

DETAIL

FWD

M

I

~ESF

6

K

VALVE TEST PORT

NORMALLY OPEN

OUTFLOW VALVE CONNECTION PRESS. TE DIAPHRAGM

CABIN PRESSURIZATION CONTROLLER DETAIL

H~

I

SAFEIY~

CABIN ALTITUDE CALIBRATION

J

‘f7

RATE SPRING

CABIN PRESSURE

DETAIL

ALTITUDE LIMIT CONTROLLER

H

DOOR SEAL SOLENOID

VACUUM

K

C

DETAIL

IREFERENCEPRESSURE METERING VALVE

Il~tlllllllhllK11

CABIN ALTITUDE CALIBRATION SCREW

(ON

4

I

TEE

I

ABSOLUTE BELLOWS CABIN ALTITUDE SELECTOR KNOB

A

I I

DIAL LIGHT

CABIN RATE CONTROL SELECTOR RATE CONTROL VALVE posmoN ACTUATOR ATTITUDE INDICAT

DETAIL

II i

;L

L~--l DETAIL

P~PPET VALVE

COVER

UPPER VALVE DIAPHRAGM

SWITCH SHOWN WITH WEIGHTONVV~ELS SAFETY VALVE

DETAIL

M

J

350603-94

39 DETAIL

N Pressurization Control Pneumatic

Figure

1

ORIGINAL As Received A21

ATP

By

21-30-00

Page

3

Oct 31/06

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

~jacts"3,4,6

21-30-00

Page Intentionally Left

Blank

A21

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CABIN ALTITUDE WARNING ANNUNCIATOR

5A

b

CABIN HIGH ALTITUDE

CABIN ALTITUDE WARNING SWITCH CABIN

ALTITUDE

WARNING

CIRCUIT

TEST UP

1

o

DOWN LH LANDING GEAR SQUAT SWITCH

PRESS

DUMP CABIN PRESSURE CONTROL

EVAPORATOR DOOR SOLFNOID LATCH

SWITCH

CABIN PRESSURE CONTROL

NO

DOOR SEAL SOLENOID VALVE

NC

NO

CABIN PRESSURE SAFETY VALVE

CABIN PRESSURE PRESET VALVE CABIN

PRESSURIZATION

CONTROL

CIRCUIT

C94FL2181060

C

Pressurization Control Electrical Schematic

Figure

A21

2

2130I00

Oct

31/06Page

5

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURIZATION CONTROL- TROUBLESHOOTING

Troubleshooting

of the

pressurization system is

best carried out in two

operational checks and data is then applied to the troubleshooting chart (Chart 102) where corrective actions are suggested.

The data is collected

as a

result of

a

series of

phases: data certain

collection and data

analysis. (Chart 101). The fault possibilities and appropriate

recorded

on a

worksheet

I

pressurization checks are performed in four stages: prestart, preflight, climb and cruise. Occasionally, at certain points during the checks, the procedure suggests terminating the entire check procedure until the currently revealed fault is corrected. Beyond these points, any further data collection would most likely yield unreliable results.

The

suggested that no attempt to analyze data be made during the data collection phase of the troubleshooting. It suggested that, when performing the pressurization checks and analyzing the data, the technician not deviate from the logical progression established by these procedures. It is

is also

The PRESSURIZATION CHECKS WORKSHEET, Chart 101, may be machine copied such copying will not constitute a violation of Raytheon Aircraft Company copyrights.

PRESSURIZATION CHECK PROCEDURES

by

maintenance

personnel;

(FLIGHT TEST)

PRESTART PROCEDURE a.

Remove the aft

security b. c.

upholstery panel covering

the outflow and

safety

valves. Check all components and lines for

of attachment.

Notice the

positions

Connect

manometer

a

of the outflow and

safety

valves: both should be closed. to the venturi test

(1, Chart 1, 21-00-00)

port connections under the center aisle

floorboards.

PREFLIGHT PROCEDURE d.

Place the bleed air controller switch in PNEU

e.

Start the

f.

Turn

on

engines according

the instrument air

valve to open

g.

to the

only

ENVIRO OFF

procedure outlined

and time the

safety

position.

in the Pilot’s

valve’s

Operating

Handbook.

opening cycle: it may take up

to 30 seconds for the

fully.

copilot’s altimeter and the test altimeter (5, Chart 1, 21-00-00) to 29.92 and record the field pressure (FPA) from the copilot’s altimeter and the cabin pressure altitude (CPA) from the test altimeter. If a discrepancy exists between the two altimeter readings, set the copilot’s altimeter to the same altitude setting as Set the

altitude

the test altimeter. h.

pressurization controller to 500 feet above the FPA and set the rate knob to opening and the safety valve’s closing cycles when the pressurization test in the TEST placed position. Opening time and closing time for these valves should be between 1 5 and

Set the cabin altitude dial of the

maximum. Time the outflow valve’s

switch is

30 seconds.

NOTE: A

safety

valve which closes too

quickly

or an

outflow valve which opens too

slowly

can cause

"bumps"

on

takeoff. i.

Turn

on

both environmental bleed air switches and increase

engine

rpm to at least 70%

Nt.

21-30-00Page

101

I

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Set the cabin altitude dial of the controller to 1,000 feet below FPA higher altitude.

j.

NOTE: At low elevation

airports during days

of

to

or

-1,000 feet

on

the dial, whichever is the

barometric pressure, when the FPA is below -500 feet, this cause to condemn any component in the pressurization

high

check may not be accurate and should not be

system. k.

While

monitoring

the outflow valve

switch in the TEST I.

(valve

should

begin to

close

immediately),

hold the

pressurization

control

position.

The cabin

seconds. If the cabin will not

at this

or

rate-of-change indicator should indicate a descent within 45 point, discontinue these checks: the cabin leak rate is too great

the cabin

ram

pressurize

air door may not be

closed. m.

When the cabin rate of rate of

n.

change stabilizes, change decreases.

When the cabin altitude stabilizes

tum the rate knob to minimum

~rate-of-change

indicator reads

zero),

(fully CCW)

and notice that the cabin

record the cabin altitude from the test

altimeter, from the airplane’s cabin altitude indicator, and from the cabin altitude setting

on

the

pressurization

controller. o.

While still

holding

p.

The cabin

rate-of-change

the test switch in the TEST

position,

indicator should indicate

a

turn the cabin altitude select dial to 500 feet above FPA.

rate of climb. Turn the

rate-of-change

knob to the maximum

rate and notice an increase in the rate of climb: the cabin should stabilize at FPA.

q.

Set cabin altitude

on

the controller to 500 feet above FPA and the rate knob to 12 o’clock

the test

switch.)

Turn

both environmental bleed air

on

according

to the

guidelines

sources

listed in the Pilot’s

and select NORMAL

Operating

or

LOW

on

or

higher. (Release

the bleed air flow switch

Handbook.

DURING CLIMB s.

Select NORMAL

on

the bleed air flow switch.

NOTE: Should the cabin fail to

begin pressurizing after passing through the cabin altitude selected on the controller, landing gear squat switch may not be opening the preset and dump

discontinue these checks: the left

I

solenoids circuit. t.

Turn

on

the alternate static air, select SL

on

the controller and increase

airplane altitude until the test altimeter higher 1,000 ft. increment according

indicates between 500 and 1,000 feet, then increase the altitude to the next to the copilot’s altimeter: record this altitude.

Page

tcO201

31/06

21-30-00

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DURING CRUISE CAUTION: When u.

turning

off the environmental bleed air, take

not to turn the instrument air off.

Turn off RH and LH environmental bleed air and record the cabin rate of climb when the rate stabilizes: the cabin rate of climb will

gradually.

initially

indicate

a

rate above the actual leak rate, then

Record the cabin climb rate at the

manometer

reading

v.

Turn

w.

Turn the left environmental bleed air off.

on

point

at this time. There should be

NOTE: If the cabin leak rate exceeds 2,400

x.

care

both bleed air

sources

and

fpm,

permit

where the cabin rate

no

stabilize, and begin

to decrease

begins

gradually.

to decrease

Take

flow indicated with both LH and RH bleed air off.

terminate these checks and correct the cabin leak rate.

the cabin altitude to stabilize

once

again.

Reduce power towards flight idle on the RH engine and record the engine N1 at the point where cabin altitude to climb. Do not reduce power below flight idle. Record the manometer reading at this time.

begins y.

Restore power to the RH

z.

Permit the cabin altitude to stabilize

aa.

engine and

turn the left bleed air on.

again

and turn the

right

environmental bleed air off.

Reduce the power towards flight idle on the LH engine and record the engine N1 at the point where cabin altitude to climb. Do not reduce the power below flight idle. Record the manometer reading at this time.

begins

ab. Restore power to the LH Before

ac.

beginning

WARNING:

and tum the RH bleed air

the next check

Carefully checks to altitude

engine

that the

airplane

is at the pressure altitude selected earlier in step

s.

monitor the cabin pressure differential during the following differential pressure ensure that cabin pressure does not exceed the maximum allowable limit. Should the

on

Releasing

ensure

on.

the test altimeter descend the static reference line

or

than 550 feet, discontinue this check immediately. placing the pressurization control switch in DUMP will

more

allow cabin pressure to return to normal limits.

ad.

Clamp

off the static reference line to the

safety valve with

the test altimeter, cabin differential from the

airplanes cabin ae.

smooth jawed pliers and record cabin altitude from airplanes differential pressure gage and cabin altitude from the

altimeter.

Remove the pliers from the static reference line

on

the

safety

valve and

clamp off the static reference

line

on

the outflow valve. af.

Record cabin altitude from the test altimeter, cabin differential from the

cabin altitude from the

airplane’s

cabin altimeter, then

remove

the

airplane’s differential pressure gage and pliers from the static reference line on the

outflow valve.

ag. Select MIN rate and 8,000 feet cabin altitude on the controller, allow the rate of climb to stabilize and time the amount of change in cabin pressure altitude for sixty seconds. Record this minimum up-rate on the worksheet. ah. Select MAX rate, allow the rate of climb to stabilize and time the amount of for sixty seconds. Record this maximum up-rate on the worksheet. ai.

When the cabin altitude stabilizes and the

rate-of-change

change

in cabin pressure altitude

indicator has returned to zero, record the cabin

pressure altitude from the test altimeter.

net

21-30-00

Oct

31/06Page

103

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

aj.

Select MIN rate and 2,000 feet cabin altitude on the controller, allow the rate of descent to stabilize and time the change in cabin pressure altitude for sixty seconds.

amount of

ak. Select MAX rate, allow the rate of descent to stabilize and time the amount of for sixty seconds. Record this maximum down-rate on the worksheet. al.

When the cabin altitude stabilizes and the

rate-of-change

change

in cabin pressure altitude

indicator has returned to zero, record the cabin

pressure altitude from the test altimeter.

I

NOTE: At about 12,500 ft., with the oxygen system armed, all the oxygen masks will am.

deploy.

Set the cabin altitude to 11,000 feet. Ensure that the white CABIN ALT annunciator illuminates and the warning as cabin altitude increases to between 10,000 and 10,500 feet. Cancel the warning tone. As cabin

tone sounds

altitude

approaches airplane altitude, place the Cabin

Press switch to

Dump.

Continue the climb and

the red CABIN ALT HI annunciator illuminates between 1 1 ,500 and 12,000 feet. Cancel the

warning

ensure

tone

that

again.

Check that the maximum cabin altitude is limited to between 12,000 and 15,000 feet. an.

Refer to the

troubleshooting

charts in this section for

a

complete analysis

of the data collected

during these

pressurization check procedures.

Oct

311~21-30-00

n?l

Raythwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 101

PRESSURIZATION CONTROL

TROUBLESHOOTING

PRESSURIZATION CHECKS WORKSHEET Prestart From

Step

b:

Were Both Outflow Valves Closed Yes

No

Preflight Safety

Valve

Open

From

Step

e:

Did

From

Step

f:

FRA From

From

Step

g:

Did Outflow Valve Did

Safety

Copilot’s

No~

Yes

CPA From Test Altimeter

Altimeter

Open

Yes

Valve Close Yes

Did Outflow Valve

Tol:15 to 30 Sec.

No No

Begin Closing

Tol:15 to 30 Sec.

Yes

No

From

Step j:

From

Step

k:

Did Cabin Rate Indicate A Descent Within 45 Seconds? Yes

From

Step

I:

Can Cabin Rate Be

From

Step

m:

CPA From Test Altimeter

Changed

Yes

No

No~ CPA Set On

CPA From Cabin Altimeter

Controller From

Step

Did Cabin Indicate A Climb Yes

o:

Can Cabin Rate Be

No

Changed Yes~

Did CPA Stabilize At FPA Yes

During

No

No

Climb

Setting

From

Step

p:

Cabin Controller

From

Step

r:

Did Cabin Pressurize

From

Step

s:

Cruising

(FPA

During

500

ft.)

Climb Yes

No~

Pressure Altitude

Outside Air Temperature CPA From Test Altimeter

During

Cruise

From

Step

t:

Cabin Climb Rate

From

Step

w:

RH

Engine N1

Tol: 2,400

fpm

or

Tol: Not More Than

less

Flight

Idle RH Manometer

Reading

Ref. Chart 101,21-10-00 From

Step

LH

z:

Engine N1

Tol: Not

more

than

flight

idle LH Manometer

Reading

Ref.

Chart 101, 21-10-00

From

Step

Altitude From

ab:

(Same WARNING:

As

Copilot’s Altimeter___ Step s)

the following differential pressure checks, carefully monitor the cabin differential pressure gage and the test altimeter. Any descent in cabin altitude over 550 ft. may exceed the maximum cabin pressure differential and will necessitate terminating this check. Remove

During

the

pliers from the immediately

valve static reference line

or

place

the

pressurization

control switch in

DUMP

n2l

21-30-00

Oct

31/06Page

105

Raytheon

Aircraft

Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL Chart 101 TROUBLESHOOTING PRESSURIZATION CONTROL PRESSURIZATION CHECKS WORKSHEET (Continued) From

I

CPA From Test Altimeter~ (Safety Valve Disabled) Differential Pressure Tol: 6.2 to 6.8 Differential Pressure From Gage Reading

ac:

I

I From

I

Step

Step

ae:

I

Figure

Measured Value:6.4 to 6.6

101

CPA From Test Altimeter___ (Oufflow Valve Disabled) Differential Pressure 6.2 to 6.8 Differential Pressure From Figure 101 Gage Reading Measured Value:6.4 to 6.6

Up-rate

From

Step af:

Minimum

From

Step

ag:

Maximum

From

Step

ah:

CPA From Test Altimeter

From

Step ai:

Minimum Down-rate

From

Step aj:

Maximum Down-rate

From

Step ak:

CPA From Test Altimeter

tcO601

Page

31/06

21-30-00

Up-rate

(Controller set at 8,000 ft.) (less

than 300

fpm)

(greater than 1,500 fpm) Tol: 8,000 ft.

(Controller set

at

400

2,000 ft.) (less than 300 fpm)

(greater than 1,500 fpm) Tol: 2,000 ft.

400

RaytheMI

nircrart Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102 TROUBLESHOOTING Data

PRESSURIZATION CONTROL

Analysis

STEP 1

In step b of Pressurization Check Procedures, were both outflow/safety

YES

Proceed to step 2

YES

Proceed to step 6

YES

Proceed to step 5

YES

Replace dump

YES

Test

YES

Proceed to step 9

YES

Proceed to step 8

YES

Replace

YES

Proceed to

YES

Proceed to step 14

valves closed? NO

Replace STEP 2

open valve.

safety valve open in step e of Pressurization Check Procedures?

Did

NO STEP 3

Is

dump solenoid opening?

NO STEP 4

dump solenoid receiving through squat switch? Is

current

solenoid.

NO

Correct open circuit. STEP 5

Is valve

receiving vacuum?

safety

valve and

replace

if

faulty.

NO Correct STEP 6

vacuum

leaks

(see

note

1).

Did outflow valve open in step g of Pressurization Check Procedures? NO

STEP 7

Is preset solenoid

opening?

NO

Replace preset solenoid. STEP 8

receiving vacuum?

Is outflow valve

outflow valve.

NO Correct STEP 9

vacuum

leaks

(see

note

1).

safety valve close in step g of Pressurization Check Procedures?

Did

step 10

NO

Replace dump STEP 10

Did cabin

solenoid.

pressurize

in step k of

Pressurization Check Procedures? NO

A21

21-30-00

Oct

31/06Page

107

RBYtheOn

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102

TROUBLESHOOTING STEP 11

PRESSURIZATION CONTROL

Is outflow valve closed in step j of Pressurization Check Procedures?

(Continued)

YES

Proceed to step 13

YES

Replace

YES

Cabin leak rate too

YES

Proceed to step 15

YES

Proceed to step 16

YES

Proceed to step 17

steps

YES

Proceed to step 18

Are differential pressure checks good from steps ac and ae of Pressurization

YES

Proceed to step 10

NO

STEP 12

Leak in preset solenoid?

solenoid.

NO Fault in STEP 13

Is

ram

controller.

pressurization

air door closed?

high (see

note

2).

NO

Magnetic STEP 14

latch

Is cabin rate

malfunctioning.

adjustable

in step I of

Pressurization Check Procedures? NO

Damaged STEP 15

controller.

Did airplane

pressurize during

climb-

out? NO

Squat switch not opening preset dump solenoid circuits. STEP 16

Did leak rate check

good

and

in step t of

Pressurization Check Procedures? NO

STEP 17

Seal cabin leaks

(see

Are

checks

w

single

and

z

source

note

2).

good

in

of Pressurization Check

Procedures? NO

Troubleshoot bleed air control. STEP 18

Check Procedures. NO

Replace

Oct

31/06Page

108

out-of-tolerance valve.

21-30-00

A21

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102 TROUBLESHOOTING STEP 19

PRESSURIZATION CONTROL

Are minimum rates within tolerance in

(Continued)

YES

Proceed to step 21

YES

Correct

vacuum

YES

System

is

steps af and aj of Pressurization Check Procedures? NO

Replace STEP 20

out-of-tolerance valve.

Are rates unbalanced

(see

note

3)?

leaks

(see

note

1).

NO

Controller out of STEP 21

adjustment.

Did CPA in steps ah and ak fall within tolerance of Pressurization Check

operating

as

designed.

Procedures? NO Controller out of

adjustment.

NOTES: 1. Vacuum leaks may occur in any of the lines the controller and the outflow valve head.

supplying

vacuum

to the outflow valve

or

may

occur

internally

in

2. Perform the checks under CABIN LEAKS in this section and seal excessive leaks until the cabin leak rate is

reduced to

an

acceptable

level.

determining the minimum up and down rates of the controller, should the minimum down-rate be tolerance and high, and the minimum up-rate be low (either in or out of tolerance), the minimum rates are 3. While

out of

unbalanced.

A21

21-30-00

Oct

31/06Page

109

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXAMPLE: AIRCRAFT PRES. AL7: 16,000 ft. -CABIN PRES. ALT. +425 ft.

CABIN PSI s.0

j i

ENTER GRAPH AT "A"

(+425 ft.),

FOLLOW LINE UP TO "B" 1(16,000 ft.), FOLLOW LINE LEFT TO CABIN DELTA PSI (6.5).

7.5

7.0

6.5

6.0

Ct~-’"’

’"’f’

~t

tt t tt t

ff:

5.5

5.0

4.5

4.0

3.5

~00 H t tf t f t t U-1 t ff

fTi~t flfrf

3.0

500

250

SL

+250

+500

750

1000

1250

1500

CABIN PRESSURE ALTITUDE Cabin Differential Pressure

Figure

Graph

101

ORIG3NAL Page

tcO01

31/06

21-30-00

As Receivea Bu

ATP

A21

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURIZATION CONTROL- MAINTENANCE PRACTICES PRESSURIZATION CONTROLLER FILTER CLEANING The pressurization controller filter is to be cleaned assembly within the pedestal.

as

specified

in

Chapter

a.

Remove the left and

b.

Disconnect the two plumbing lines from the controller assembly.

c.

Identify and

d.

5. The filter is located in the controller

right pedestal sidepanels.

disconnect the two electrical wires from the controller.

Remove the four

screws

which attach the controller

assembly to

the

pedestal.

Lift the controller from the

pedestal e.

Remove the lockwire, washers, spring washer, screen, and filter from the controller

NOTE: Observe the method of lockwire installation

during

removal to facilitate the reinstallation.

f.

Wash the screen, washers, and filter element in solvent

g.

Ensure that the orifice in the controller

CAUTION: Use

care

not to

damage

housing

is free of

the orifice in the

housing.

(10,

Chart 2,

foreign

housing.

21-00-00). Dry

with

shop air.

material.

The proper

operation

of the system is

dependent on

the size of the orifice.

and washers. Secure with lock wire.

h.

Install the filter element, screen,

spring washer,

i.

Position the controller

in the

j.

Connect the two electrical wires to the controller assembly.

k.

Connect the two

I.

Install the left and

~al

assembly

plumbing

pedestal and

lines to the controller

install the four

attaching

screws.

assembly.

right pedestal sidepanels.

21-30-00

Oct

31/06Page

201

RaytheMI

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ooooooo

o

cD

C

A

CABIN ALTITUDE

LIMIT CONTROLLER -r\

r-

TO SAFETY VALVE DUMP PORT TO OUTFLOW VALVE

SAFETY VALVE--I

SOLENOID

II

DUMP PORT

OUTFLOW VALVE TO CONTROLLER

j

TO CONTROLLER OUTFLOW PORT----I

SAFETY VALVE

~1*TUOSPHERIC VENT

ATMOSPHERE PORT

FILTER U

Il~gW

DRAIN VALVES

DETAILA

TOALTITUDE LIMIT

CONTROLLER TO VACUUM

ATMOSPHERIC TO OUTFLOW VALVE

VENT TO TEST PLUG

DETAIL

ORIFICE

B

PRESET SOLENOIO

j

PEDESTAL

_I

PRESSURE CONTROLLER

TER

nn VIEW LOOKING AT LH SIDE OF PEDESTAL

DETAIL

C

Baoo~53-15

Pressurization Controller Filters

Figure 201

Oct

31/0621-3000

A21

Ral~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OU~FLOW AND SAFETY VAL VE SERVICING Fluctuation of cabin pressure often indicates a dirty poppet, seat, or filter of the outflow of the valves should be inspected and cleaned per Chapter 5 (Ref. Figure 201). a.

Working through the tail seat and noise

b.

section

suppression

opening

access

screen

in the bottom of the aft

fuselage

or

area,

safety

valves. The seats

inspect the valve poppet,

for accumulation of dust and tobacco smoke residue.

Using a suitable liquid dispenser filled with detergent (9, Chart 2, 21-00-00) and water or isopropyl alcohol (8, Chart 2, 21-00-00) flush the valve poppet, seat, and noise suppression screen. It may be necessary to remove the noise suppression screen and wipe the poppet and seat with a clean rag dampened with detergent or isopropyl alcohol.

CA UTION: Use

only the products listed. Unapproved products may have a damaging effect on the component parts

of the valve

or

may leave

a

residue which will interfere with the valve action.

SAFEN VALVE FILTER CLEANING The

safety

valve filter should be

inspected

and cleaned at intervals

a.

Working

b.

Removethe filterfromthe safetyvalve.

inside the cabin,

remove

NOTE: When the filter is cleaned without

disassembling.

upholstery

regularly and

or

if there is

required

is not

to

gain

in

access to

Chapter the

5.

safety

valve

(Ref. Figure 201).

subjected to severe residue deposits, the filter can be cleaned (10, Chart 2, 21-00-00) and dried with shop air.

It may be rinsed in solvent

Ensure that the orifice of the filter

regularly,

as

specified

a

housing

foreign material. If the filter has not been cleaned residue deposit, the filter may be disassembled and

is free of

considerable amount of

cleaned. c.

Remove the

remaining d.

is Install

nn

not to

dependent

over

from the filter

housing

assembly housing. Remove assembly.

to a

enlarge

screen, the copper

ribbon, and the

damage

assembly

in solvent

(10,

Chart 2,

21-00-00). Ensure

the orifice in the filter housing. The proper

operation

that the

of the system

the size of the orifice.

on

in the

or

one

of the filter

housing

of the filter

compress the ribbon. Install

Install the filter

Tighten g.

care

one screen

Do not f.

from the

Wash both screens, the copper ribbon, and filter orifice in the housing is free of foreign material.

CAUTION: Use

e.

retaining ring

screen

assembly

torque of 15

in the to 20

assembly. the remaining

safety valve, using inch-pounds.

the

Install the copper ribbon in the filter screen and retaining ring.

preformed packing

assembly housing.

removed with the filter

Replacethe upholstery panel.

21-30-00

assembly.

Ray~heon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURIZATION CONTROL SYSTEM a.

Prior to takeoff, set the controller at the control switch to the TEST

an

OPERATIONAL CHECK

altitude

position (hold

in

approximately position for at

500 feet below field pressure altitude and

least 45 seconds at

an

N, speed

of

70%).

move

The

climb-rate indicator and the cabin pressure altitude should show a decrease. If the controller is set above field pressure altitude, the climb-rate indicator will drop, then stabilize at zero when the control switch is held in the

TEST b.

position.

Pressurization will not

unless the controller is set below field pressure altitude.

After

performing the procedures outlined in step a, operate the system with the control switch in the PRESS position. Prior to takeoff, set the desired cabin pressure altitude and the rate of climb on the pressure controller.

As the

airplane

leaves the

discomfort. The cabin will is reached

according a

occur

ground, cabin pressurization may fluctuate momentarily but should not cause passenger pressurize at the rate set on the cabin rate-of-climb selector until the preset cabin altitude

until the maximum pressure differential is reached. The cabin will then maintain pressurization safety valve (6.5 psig). Cabin altitude will continue to climb at

or

to the maximum differential pressure of the

slower rate than the

airplane

until cruise altitude is reached. Cabin pressure will then stabilize and maintain

maximum differential control.

CABIN PRESSURIZA TION LEAKAGE TEST WARNING: A

qualified operator

must remain at the test unit

Personnel assigned to work under

disorders, respiratory and

ear

pressurized

infections, and

as

long

as

the

fuselage

is

conditions must be free of

must be

pressurized, obesity, heart

emotionally stable.

Test

I

equipment used to ground test the cabin for pressurization leaks and for troubleshooting the pressurization system must be capable of delivering 7 psi of air at 80 cubic feet per minute, and must be protected by a complete safety system to prevent damage to the pressure vessel. The test units listed in the following text consist of an electric motor and blower assembly, a dry air filter, a cabin pressure gage and a large relief valve to protect the pressure capsule of the airplane from overpressurization (Ref. Figure 202). NOTE:

Carefully review the procedure.

instructions

provided

with the test unit

(3

thru 10, Chart 1,

21-00-00) prior to initiating

the test a.

Remove the small

access

panel

the lower

on

right

sidewall of the aft cabin

approximately

1 foot forward of the

aft pressure bulkhead. Under this panel is a drain valve which must be opened to assure that the outflow valve remains closed during the pressurization test. Determine that the pressurization control circuit breaker on the RH circuit breaker b.

Open

the

panel

is

large rectangular

engaged access

so

that the evaporator door will be locked closed

door from the RH bottom side of the

during

the test.

fuselage immediately

aft of the aft

pressure bulkhead. c.

Remove the cap from the fitting on the aft pressure bulkhead and run a wire through it to assure that the fitting is unobstructed. The fitting is located at the bottom of the aft pressure bulkhead in line with the inboard side of the access door.

NOTE: If the end of the

fitting inside the pressurized area is capped, it will be baggage area to gain access to the fitting cap.

necessary to

remove

the rearmost

floorboard in the aft d.

Connect

a

high

pressure hose between the aft end of the fitting and the INSTRUMENT AIR fitting on the side ensure operation of the RATE-OF-CLIMB and CABIN PRESSURE gages

of the test unit. This connection will on

e.

Oct

the test unit.

Connect the two pneumatic hoses from the pressurization unit to the pneumatic air firewall Figure 202. Cap the end of the disconnected flow control valve pneumatic tube.

31/06Page

204

21-30-00

fittings

as

shown in

Raychwm

AiKraft

company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

f.

Close and latch the emergency exit hatch and the cabin door.

g.

Place

a

safety

CAUTION: The

net

(9, Chart 1, 21-00-00)

pressurization

valve. Do not

may be

use

machine

around the

pressurization

fuselage

and cabin door.

hose MUST NOT be hooked forward of the flow control

the ambient air tube located forward of the flow control valve. The flow control valve

damaged and require replacement if pressurized air is

h.

Set the controller knob to minimum altitude and maximum rate.

i.

Pressure the 1.

airplane

as

directed

through

the flow control valve.

follows:

pressurization bosses installed between the firewall and the flow control firewall shutoff valve. The pressurization hose should be connected to these bosses if these tube assemblies are installed on the airplane. If the airplane does not have the tubes installed, an adapter panel may be fabricated to allow pressurized air induction to the airplane as follows: Some

airplanes

a)

Remove the

b)

Using

c)

Using the panel.

d)

the

have

a new

access

access

panel aft of the

panel

removed

tube with

as a

access

nose

as a

Determine the size of aluminum tube diameter than the tube

make

template,

panel

required

landing gear doors. a

panel of the

template,

drill the

same

size from 1/8-inch aluminum sheet.

attaching

screw

holes

through

the fabricated

required for the pressurization hoses. Using a hole saw of smaller pressurization hose, cut a hole in the center of the fabricated

for the

panel.

e)

Weld

a

piece of aluminum tubing of the size required for the pressurization machine panel centered around the hole cut in the preceding step.

hose to the

fabricated

f)

Install the fabricated

g)

Attach the

panel aft of the

pressurization

nose

landing

gear doors

hose from the test unit to the tube

using on

the

regular panel attaching

the installed fabricated

screws.

panel.

CA UTION: The maximum rate of pressure increase must not exceed 2 000 ft./min. If personnel are to be stationed inside the pressure vessel, the rate of pressure increase must not exceed 1,000 ft./min. Make certain no way restricted prior to starting the test unit. Refer the proper electrical connections and power source.

that the BYPASS AIR OUTLET of the test unit is in to the test unit instructions for information

on

then activate the start button.

j.

Rotate the INCREASE-DECREASE valve

k.

Rotate the INCREASE-DECREASE valve clockwise. The RATE-OF-CLIMB gage should indicate a descent while the CABIN PRESSURE and the RATE- OF-FLOW gages indicate progressively higher readings. The FLOW METER should stay approximately one to two psi higher than the CABIN PRESSURE gage.

I.

Gradually slow the pressure increase as the correct pressure value (6.5 psi) is approached. When the correct reading is attained, the RATE-OF-CLIMB gage should stabilize at a reading of zero and the RATE- OF-FLOW gage should indicate no higher than 53 cfm.

m.

If the correct differential pressure of 6.5 satisfactorily air tight.

fully

psi

open

can

(counterclockwise)

be maintained with

a

flow rate of 53 cfm

or

less, the pressure

vessel is n.

If the correct pressure differential cannot be maintained at the

specified

flow rate, check the

following

leaks:

21-30-00

areas

for

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL NOTE: Pressurization leaks may be detected by sound and pinpointed by feel. It may be necessary to attain maximum pressure, then shutdown the test unit so that the noise of the operating blower will not cover the sound of the leaks. 1.

Windshield

2.

The seal around the storm window

3.

The seal around the emergency exit hatch.

4.

Thecabin doorseal.

5.

The outflow and

6.

The control cable seals in the aft pressure bulkhead and in the

7.

The

8.

The electrical

9.

Thefuselageskin laps.

attaching

safety

fuselage belly

10. The flexible

screws.

valve

drain

wiring

ducting

(if installed).

mountings

and

gaskets. at the center section.

plugs.

bundles from the

fuselage

in the center section in the

to the nose, center

area

section, and empennage.

of the intercoolers,

NOTE: A leak rate of 3 cfm is considered normal for the outflow and o.

fuselage

safety

Rapidly turn the INCREASE-DECREASE valve fully counterclockwise, while monitoring the RATE-OF-CLIMB gage.

bypass valves,

etc.

valve.

then

immediately

hit the STOP button

NOTE: The stop button will not shut down the test unit until the INCREASE-DECREASE valve is counterclockwise. The RATE-OF-CLIMB gage should not indicate more than 2400 FPM greater than 2400 FPM indicates an excessive rate of leakage. p. q.

Wait 15 minutes after all gages indicate ZERO before Disconnect the test

airplane r.

to

s.

and reconnect all

shutdown

tcO602

31/06

A

reading

the cabin door.

pressurization system fittings, lines,

and hoses to return the

temporary

access

panel

aft of the

nose

gear doors and install the

regular access panel using

screws.

Close the drain valve in the line between the outflow valve and the controller and install all

Page

period.

flight worthy configuration.

Remove the

attaching

equipment

opening

during the

fully

21-30-00

access

panels.

the

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ATTACH CABIN PRESSURE HOSE TO iH FITTTNG ON AFT PRESSURE BULKHEAD

A

)P~j

ATTACH PNEUMATIC AIR HOSE FROM TEST UNIT AND CAP THE LINE

ATTACH PRESSURIZING AIR HOSE FROM TEST UNIT

DETAIL LH

SHOWN

A

TYPICAL

Pressurization Test

Figure

A21

C94FL2181066

Setup

202

21-30-00

Oct

31/06Page

207

Raytheon

nircraft Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

OUTFLOW VAL VE AND SAFEN VAL VE TESTING The outflow and The

safety

valves should be

regulating function

of the outflow and

differential pressure of 6.5~0.1 There 1 is

a

tests

are

inspected

safety

at the interval

valves

can

be tested

in

Chapter

5.

by observing

that

they

a

cabin

three different methods that may be used to verify the operation of the outflow and safety valves. Method and 3 are ground tests; however, it is only necessary to perform one of the following

flight test and methods 2 to verify their operation.

Refer to PRESSURIZATION CHECK PROCEDURES CONTROL

TROUBLESHOOTING in this

Set the cabin pressure controller to

(METHOD 1)

(FLIGHT TEST) presented

under PRESSURIZATION

subchapter.

OUTFLOW VALVE AND SAFETY VALVE FUNCTIONAL TEST

feet and

zero

ensure

(METHOD 2)

that all

personnel

are

out of the

NOTE: Secure

heavy strength, nylon safety straps to the cabin door. The straps should have strength of 26,000 pounds. If making structural repairs to the pressure vessel, attach enough to cover the fuselage.

b.

maintain

psig.

OUTFLOW VALVE AND SAFETY VALVE FUNCTIONAL TEST

a.

specified

Plug

the

atmospheric

vent

on

the

safety

valve. The vent for the

safety

airplane. a

minimum

a

safety

breaking large

net

valve is located adjacent to the outboard

side of the outflow valve. c.

Increase the cabin pressure to 6.4 psig. The outflow valve should pressure is between 6.4 and 6.6 psig.

d.

Reduce the pressure differential below 5.9

e.

Plug

the

atmospheric

side of the

safety

vent

on

psig

and

remove

the

dump cabin pressure

plug

from the

safety

when the differential

valve.

the outflow valve. The vent for the outflow valve is located

adjacent to the inboard

valve.

f.

Increase the cabin pressure to 6.4 psig. The pressure is between 6.4 and 6.6 psig.

g.

Remove the

h.

Stabilize cabin pressure at 5.9 psig. Quickly close the increase/decrease valve, press the start button, and record the cabin rate of climb after five seconds.

i.

The rate-of-climb gage should not indicate

j.

Reduce the cabin pressure to zero. Remove the safety straps from the fuselage. Disconnect the test equipment and open the cabin door. Ensure that all plugs have been removed from the outflow valve and safety valve.

Oct

31/06Page

208

plug

safety

valve should

dump

cabin pressure when the differential

from the outflow valve.

21-30-00

a

rate

greater than 2400 fpm.

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OUTFLOW VALVE AND SAFETY VALVE FUNCTIONAL TEST

regulating function

The

cabin pressure at

of the outflow valve and

differential of 6.5 ~0.1

a

safety

valve

can

(METHOD 3) be tested

by observing

that

they

can

maintain the

psig.

a.

This test is to be

b.

Remove all electrical power from the

c.

Remove the aft

d.

Verify that the poppets

e.

Connect the

f.

the test, set the pitot static tester altimeter to 29.92 inches of mercury (or international equivalent). pitot static tester altimeter reading to a pressure value (PQ). Refer to Table IIA of Allied and Maintenance Signal’s Operation Report 4-270 or subsequent in the Beech King Air Series Component Prior to

performed using

a

pitot

static tester

pitot

static tester to

port

Chart 1,

21-00-00).

airplane.

upholstery panel covering´•the of the outflow

(8,

(1)

and

(2)

1

on

outflow

(1)

safety (5)

and

valves

safety (5) are

valves

(Ref. Figure 203).

1

both closed.

the outflow valve.

starting

Convert the

Maintenance Manual (P/N 101-590097-13). Record this pressure g.

Calculate test pressures P1 and P2 P1

PQ

6.10

psia

P2

PQ

6.60

psia

by using

the

as

following formulas

PQ

and record the values:

h.

Use Table IIA to convert P1 and P2 to ALT1 and ALT2 respectively. Referto Table IIA of Allied Signal’s Operation and Maintenance Report 4-270 or subsequent in the Seech King Air Series Component Maintenance Manual (P/N 101-590097-13). Record the values of ALT1 and ALT2

i.

On the

j.

Verify that the fully closed.

k.

On the

I.

Verify that

pitot static tester, slowly increase

pitot

outflow valve

static tester,

(1). Slowly

m.

Remove the

vacuum

n.

Connect the

pitot static

o.

Prior to

starting

is

(1)

return

fully

closed. There is

increase the simulated

slowly

the outflow valve

outflow valve

(1)

the simulated

airplane altitude a

fault in the outflow valve if the outflow valve

airplane

fully open. If the outflow valve (1) is the pitot static tester to field elevation.

tester to

the test, set the

(3)

of the

safety

valve

(5). Cap

not

fully

open,

the port and

a

p.

plug

the line.

port 1 (4) of the safety valve (5).

pitot

static tester altimeter to 29.92 inches of mercury (or International reading to a pressure value (PQ). Refer to Table IIA in Allied

n?l

static tester altimeter

Calculate test pressures P1 (closed) and P2 (open) by using the P1

PQ

6.10

psia

P2

PQ

6.80

psia

is not

fault is indicated in the

equivalent). pitot Signal’s Operation and Maintenance Report No. 4-270 or subsequent located in the Seech King Component Maintenance Manual (P/N 101-590097-13). Record the pressure as PQ. Convert the

(1)

altitude to the value of ALT2.

is

line from port 2

to the value of ALT1

following

Air Series

formulas and record the values.

21-30-00Page

209

Ray~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

q.

Use Table IIA in Allied

Seech

King

Air Series

P2 to ALT1 and ALT2

Signal’s Operation and Maintenance Report No. 4-270 Component Maintenance Manual P/N, 101-590097-13. respectively. Record the values of ALT1 and ALT2.

pitot static tester, slowly

On the

s.

Verify that the safety safety valve (5).

t.

On the pitot static tester,

u.

Verify that the safety valve (5) is fully open. If the safety valve (5) is valve (5). Slowly return the pitot static testerto field elevation.

v.

Disconnect the

w.

(5)

is

slowly

pitot static

fully

closed. If the

safety valve (5)

as

P1 and

is not

fully closed,

a

fault is indicated in the

increase the simulated aircraft altitude to the value of ALT2.

tester from

port 1 (4)

on

the

safety

2

(3)

and the

static tester from port 1

(2)

on

Remove the cap from the

located in the

subsequent

Record the pressure

increase the simulated aircraft altitude to the value of ALT1.

r.

valve

or

safety valve port

plug

fully open,

not

valve

(5)

from the

a

fault is indicated in the

and connect

vacuum

vacuum

safety

line.

line. Connect the

vacuum

line to

port 2 (3) of the safety valve (5). x.

Disconnect the

y.

Install the

Page

tcO012

31/06

pitot

the outflow valve

(1)

and connect

vacuum

line.

upholstery panel.

21-30-00

AZ1

sellsteott

Aircraft Company

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

I

I

/P/

~I s U

u

--~-1;I

4

TO VACUUM SOURCE

2

3

DETAIL

Ih j

VIEW

DETAIL

B

i. 2. 3. 4.

I_

a

5. 6. 7.

8.

OUTFLOW VALVE OUTFLOW VALVE PORT 1 SAFETY VALVE PORT 2 SAFETY VALVE PORT 1 SAFETY VALVE CABIN PRESSURIZATION VACUUM SUPPLY LINE PRESET SOLENOID

C

LOOKING

AFT

CONTROLLER

6

b o~ooooo

C

i

C

B

A

C94FL21BOP05

DETAIL

A Pressurization Control Pneumatic

ORIGINAL As CaeCeived

By

Figure

203

ATP A21

21-30-00

Page 211 Oct 31/06

Ralltheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

21130100

Page Intentionally

Left Blank

A21

Raytheon

Aircraft

company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OUTFLOW VALVE AND SAFEN VALVE REMOVAL a.

b.

Disconnect the

plumbing lines from the

Remove the nuts

valve

(Ref. Figure 203).

the valve to the recessed structure

securing

on

the aft pressure bulkhead and

remove

the

valve.

OUTFLOW VAL VE AND SAFETY VAL VE INSTALLA TION a.

Secure the valve and

b.

Connect the

gasket

plumbing

as

shown in

lines to the valve

Figure

204.

Torque the attach

nuts to 12 to 15 inch

pounds.

(Ref. Figure 203).

PRESSURIZATION CONTROLLER REMOVAL from the

a.

Remove the side

b.

Remove the top

c.

Disconnect the controller

lighting

d.

Disconnect and label the

plumbing

e.

Remove the

panels

panel

attaching

from the

pedestal.

pedestal

to

gain

access

to the controller

leads. Do not cut off the

screws

(Ref. Figure 203).

at the end of the controller wires.

lines from the controller.

and the controller from the

screws

plug

mounting

pedestal.

PRESSURIZATION CONTROLLER INSTALLATION a.

panel of the pedestal pedestal (Ref. Figure 203).

Install the controller on

the

on

the top

secure

with the

attaching

screws.

Install the top

lines to the controller.

b.

Connect the

plumbing

c.

Connect the

lighting leads

d.

Install the side

panels

and

on

to the controller.

the

pedestal.

21-30-00

panel

1

Raycheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OPEN SPACE BEFORE INSTALLATION

~M521044 y

~AN960-8L

y

MOUNTING

NO.

8

NUT

WASHER

STRUCTURE

!01-540023-1 GASKET i

MS35649-282 AN960-8

VALVE

BASE

NUT

WASHER

PLATE

C9aFL2181067

Gasket Installation

Outflow Valve and

Figure

C

Safety Valve

204

ORIGINAL As Received By ATP

Page

tcO412

31/06

21-30-00

A21

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CABIN ALTITUDE PRESSURE SWITCH REMOVAL NOTE: The cabin altitude switch is

airplane approximately

one

on

the

printed

foot aft of the

a.

Remove electrical power from the

b.

Identify, tag

c.

Remove the

circuit card rack located under the floorboard in the center of the

pedestal between FS143 and FS158 (Ref. 39-21-00).

airplane.

and disconnect the wires from the cabin altitude pressure switch.

attaching

hardware and the cabin altitude pressure switch from the

airplane.

CABIN ALTITUDE PRESSURE SWITCH INSTALLA TION NOTE: The cabin altitude switch is

airplane approximately a.

one

on

the

printed

circuit card rack located under the floorboard in the center of the

foot aft of the pedestal between FS143 and FS158 (Ref.

If not previously accomplished, perform the CABIN ALTITUDE WARNING procedure (Method 3) if a vacuum chamber is available before installing a the activation and deactivation points of the switch under test.

b.

Use

an

insulated 22 gauge wire, connect

when installed in

an

a

jumper wire

39-21-Ob).

PRESSURE SWITCH CHECK new

switch. Refer to Table 201 for

between the wires that connect to the pressure switch

airplane.

c.

Applyelectrical powertotheairplane.

d.

Verify

the CABIN ALTITUDE annunciator illuminates. The CABIN ALTITUDE annunciator is located

on

the

CAUTION-ADVISORY ANNUNCIATOR PANEL. e.

Remove electrical power from the

f.

Remove the

g.

Install the cabin altitude

h.

Connect the wires to the pressure switch and

i.

airplane.

jumper wire from the airplane wiring harness.

warning switch,

with the

attaching hardware

remove

in the

airplane.

identification tags.

chamber was not available, perform the CABIN ALTITUDE WARNING PRESSURE SWITCH procedure (Method 2 or 3) to verify proper operation of the pressure switch. Refer to Table 201 for the activation and deactivation points of the switch under test. If

a vacuum

CHECK

azl

21-30-00

Oct

31/06Page

215

Raytheon

Aircraft

company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CABIN ALT HI WARNING PRESSURE SWITCH REMOVAL NOTE: The cabin altitude

high warning

switch is located within the overhead switch

a.

Remove electrical power from the

b.

Identify, tag

and disconnect the wires from the cabin altitude

c.

Remove the

attaching

panel.

airplane.

hardware and the cabin altitude

pressure switch.

high warning

high warning pressure

switch from the

airplane.

CABIN AL T H1 WARNING PRESSURE SWITCH INSTALLA TION NOTE: The cabin altitude a.

I

high warning

switch is located within the overhead switch

previously accomplished, perform the CABIN ALTITUDE WARNING procedure (Method 3) if a vacuum chamber is available before installing a If not

b.

insulated 22 gauge wire, connect when installed in an airplane.

c.

Applyelectrical powertotheairplane.

d.

Verify the

Use

an

a

jumper wire between

panel.

PRESSURE SWITCH CHECK new

switch.

the wires that connect to the pressure switch

CABIN ALT HI annunciator illuminates. The CABIN ALT HI annunciator is located

on

the WARNING

ANNUNCIATOR PANEL. e.

Remove electrical power from the

f.

Remove the

g.

Install the cabin altitude

h.

Connect the wires to the pressure switch and

i.

If

a vacuum

CHECK

Page

jumper

wire from the

chamber

airplane. airplane wiring

high warning

was

not

harness.

pressure switch, with the remove

attaching

hardware in the

airplane.

identification tags.

available, perform the CABIN ALTITUDE WARNING PRESSURE SWITCH

procedure (Method l)to verify proper operation of

21-30-00

the pressure switch.

A21

Raycheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CABIN ALTITUDE WARNING PRESSURE SWITCH CHECK procedure is being performed due to a Special Inspection requirement of Chapter 5-20-00, METHOD performed. If the procedure is being perf ormed solely to check the operation of the pressu re switch, then METHOD 1, 2 or 3 may be performed.

NOTE: If this 1

or

2 MU ST be

If this

procedure

is

being performed

due to

a

Special Inspection requirement of Chapter 5-20-00, perform procedure in Chapter 35-00-00 in conjunction with this

the BAROMETRIC PRESSURE SWITCH CHECK

procedure.

METHOD 1

WARNING:

Comply

with standard FAA

regulations

NOTE: Refer to Table 201 for the activation and deactivation It is not necessary to exceed performing this check.

an

points

of the switch under test.

altitude of 500 feet above the

a.

Fly the unpressurized airplane to the altitude triggers the cabin altitude aural warning.

b.

As

this test.

performing

for oxygen usage when

Increasing

Altitude Activation Point while

at which the CABIN ALTITUDE annunciator illuminates and

airplane altitude increases, note the cabin altitude on a certified altimeter static test set or hand held certified Hg. at which the CABIN ALTITUDE annunciator light illuminates. Record the altitude reading in Table 201. The annunciator light shall illuminate at the Increasing Altitude Activation Point.

altimeter set to 29.92 inch

c.

Cancelthe

d.

Increase the

airplane altitude until the CABIN altitude aural warning.

e.

As

airplane

auralwarning.

altitude increases, note the cabin altitude

altimeter set to 29.92 inch

reading

Hg.

f.

Cancel the aural

g.

The

h.

As the

warning

on a

annunciator illuminates and

certified altimeter static test set

triggers the cabin

or

hand held certified

light illuminates. Record the altitude the Increasing Altitude Activation Point.

at which the CABIN ALT HI annunciator

in Table 201. The annunciator

pilot

ALT HI

light

shall illuminate at

warning.

shall then descend to

an

altitude below the

Decreasing

Altitude Activation Point.

airplane descends, the pilot will note the cabin altitude at which the CABIN ALT HI annunciator light extinguishes. Record the altitude reading in Table 201. The annunciator light shall extinguish at the Decreasing

Altitude Activation Point. i.

Continue to descend to

an

altitude below the

descending altitude activation point for the CABIN ALTITUDE

pressure switch.

j.

airplane descends, the pilot will note the cabin altitude at which the CABIN ALTITUDE annunciator light extinguishes. Record the altitude reading in Table 201. The annunciator light shall extinguish at the Decreasing

As the

Altitude Activation Point. k.

The CABIN ALTITUDE

or

CABIN ALT HI pressure switch must be

replaced

if it does not meet these

specifications.

21-30-00

Rayeheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

METHOD 2 a.

Fabricate

a vacuum

chamber from 3 inch schedule 40 PVC

plumbing pipe

or

suitable

4 to 8 inches

equivalent,

with two end caps. One end cap is permanently attached to the plumbing pipe with PVC cement then drilled and tapped for an AN816-4D fitting. The other end cap is a removable closure. Material required for the vacuum

long

chambers may be obtained NOTE: The cabin altitude

locally.

Refer to

high warning switch

The cabin altitude switch is

airplane approximately

on

one

Figure

or

206 for

an

example of a fabricated

is located within the overhead switch

printed

the

205

foot aft of the

vacuum

chamber.

panel.

circuit card rack located under the floorboard in the center of the

pedestal between FS143

and FS158

(Ref. 39-21-00).

attaching hardware and the pressure switch from the overhead switch panel or the circuit card rack. Do not disconnect the wires from the pressure switch. Cut the tie wraps from the wire harness to allow adequate length to place the pressure switch in the vacuum chamber.

b.

Remove the

c.

Identify the part

number of the pressure switch that will be tested in the

NOTE: Refer to Table 201 for the activation and deactivation It is not necessary to exceed performing this check.

an

points

airplane.

of the switch to be checked.

altitude of 500 feet above the

Increasing

Altitude Activation Point while

d.

Suspend the vacuum chamber from the airplane structure to eliminate strain on the pressure switch wires. Place the pressure switch inside the vacuum chamber with the wires exiting the chamber from the location referenced in Figure 205 or 206. Install the end cap then apply plumbers putty or equivalent around the wires to seal the chamber.

e.

Applyelectrical powertotheairplane.

f.

Connect

g.

Slowly increase the vacuum in the chamber and check for leaks. Make adjustments to the end cap and apply plumbers putty or equivalent as required to reduce leak rate to a manageable amount. Total sealing may not be possible.

h.

Slowly increase the vacuum or

an

altimeter test unit

i.

a

certified altimeter to the

on

in Table 201.The annunciator

on vacuum

light

shall

light extinguishes.

chamber.

the test unit at which the CABIN ALTITUDE on

the Caution

Warning Annunciator Panel. Record the illuminate at the Increasing Altitude Activation Point. on

the

in the chamber and note the altitude

CABIN ALT HI annunciator

fitting

The CABIN ALTITUDE annunciator is located

light illuminates.

The CABIN ALT HI annunciator is located

Slowly decrease the vacuum or

similar device with

in the chamber and note the altitude

CABIN ALT HI annunciator

Advisory Panel. altitude reading

or

on

the test unit at which the CABIN ALTITUDE

The CABIN ALTITUDE annunciator is located

on

the Caution

Advisory Panel. The CABIN ALT HI annunciator is located on the Warning Annunciator Panel. Record the altitude reading in Table 201. The annunciator light shall extinguish at the Decreasing Altitude Activation Point. Allow the

vacuum

chamber to return to

replaced if it

does not meet these

j.

The switch must be

k.

Disconnect the test unit from the

I.

Disconnect electrical power from the

m.

Remove the pressure switch from the

n.

Install pressure switch with

Page

atmospheric pressure.

fitting

on

the

vacuum

chamber.

airplane. vacuum

chamber.

attaching hardware

21130100

specifications.

and

secure

wire harness with tie wraps.

A21

Ray~heon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

METHOD 3 a.

Fabricate

a vacuum

chamber from 3 inch schedule 40 PVC

plumbing pipe

or

suitable

equivalent,

4 to 8 inches

long with two end caps. One end cap is permanently attached to the plumbing pipe with PVC cement then drilled and tapped for an AN816-4D fitting. The other end cap is a removable closure. Material required for the vacuum chambers may be obtained b.

If

locally. Refer to Figure

205

or

206 for

an

example

of

a

fabricated

required, perform the CABIN ALT HI WARNING PRESSURE SWITCH REMOVAL procedure.

or

vacuum

chamber.

CABIN ALTITUDE

PRESSURE SWITCH REMOVAL c.

Place the pressure switch inside the vacuum chamber with wires connected to the terminals (COM and NO) of the switch. Route the wires out of the chamber from the location referenced in Figure 205 or 206. Connect an ohmmeter to these wires for the test. Install the end cap then wires to seal the chamber.

d.

Connect

an

altimeter test unit

or

similar device with

a

certified altimeter to the

NOTE: Refer to Table 201 for the activation and deactivation e.

Slowly

increase the

Slowly

increase the

Record the altitude

g.

After

vacuum

reading

or

fitting

equivalent around

on vacuum

the

chamber.

points of the switch under test. adjustments to the end cap and apply manageable amount. Total sealing may not be

in the chamber and check for leaks. Make

vacuum

plumbers putty or equivalent as required possible. f.

apply plumbers putty

to reduce leak rate to a

in the chamber and check for

continuity

at the

increasing

altitude activation

point.

in Table 201.

continuity is acquired, slowly decrease the vacuum in the chamber and check for termination of continuity decreasing altitude activation point. Record the altitude reading in Table 201. Allow the vacuum chamber

at the

to return to

atmospheric

pressure.

h.

Disconnect the test unit from the

i.

The switch must be

j.

Remove the pressure switch from the

replaced if

fitting

on

the

vacuum

it does not meet these vacuum

chamber.

specifications.

chamber.

NOTE: Perform step k. if the pressure switch will be installed in k.

airplane.

Perform the CABIN ALT HI WARNING PRESSURE SWITCH INSTALLATION PRESSURE SWITCH INSTALLATION

~al

an

or

CABIN ALTITUDE

procedure.

21-30-00Page

219

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Table 201

Switch Part Number

1

Increasing

Operation

Data

Altitude Activation

Point

Decreasing

Altitude Activation

Point

101-384028-11, -19, -25, -31,-45

12,000

000/- 500 feet

10,000 feet

101-384028-3 -27, -33, -47

10,000

500/- 000 feet

9,000 feet

or

or

higher higher

Recorded Altitude Value Method Used

Oct

31/0621-30-00

,1

Ray~heon Aircraft Company SUPER KING AIR B300/8300C MAINTENANCE MANUAL

THE END CAP IS PERMANENTLY

ATTACHED WITH PVC CEMENT. END CAP IS DRILLED AND TAPPED FOR AN ANB16-4D FITTING.

RELIEFS PROVIDED FOR THE PRESSURE SWITCH WIRES AS THEY EXIT.

THIS IS A COMMON PLUMBING CLEAN OUT PLUG. BEFORE USING CLEAN THE RUBBER SEAL AND APPLY SILICONE LUBE.

7/

CLEAN EDGES AND SMOOTH WITH FINE SANDPAPER.

PRESSURE SWITCH WIRES

AN816-4D FITTING PLUMBERS PUTTY

FL2tB 0328641~Pd

Vacuum Chamber

Figure

A21

(Sample)

205

21-30-00

Oct

31/06Page

221

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

APPLY PLUMBERS PLITTY TO SEAL AROUND WIRES.

APPLY TAPE TO SEAL THE SLOT AFTER SWITCH IS PLACED INTO VACUUM CHAMBER

c

LATCH

WATER TANK TO TOILET BOWL SEAL, CHOOSE ONE THAT FITS INSIDE END CAP. APPLY SMALL BEAD OF PUTTY TO BASE OF SEAL BEFORE INSERTING INTO CAP.

COAT FACE OF SEAL WITH SILICONE LUBE.

THE END CAP IS PERMANENTLY ATTACHED WITH PVC CEMENT. END CAP IS DRILLED AND

TAPPED FOR AN AN816-4D FITTING FOR ALTIMETER TESTER CONNECTION.

ANB16-4D FITTING

FL21B M2865MAI

Vacuum Chamber

Figure

Oct

31/0621-30-00

(Sample)

206

A21

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 ALtitude to Pressure Conversion ALTITUDE FEET

A21

PRESSURE

IN-NC

ALTITUDE

PRESSURE

METERS

MM-HG

PSIA

-1,000

31.016

15.233

-305

787.806

-900

30.906

15.179

-274

785.012

-800

30.796

15.126

-244

782.230

-700

30.686

15.072

-213

779.423

-600

30.576

15.018

-1 83

776.624

-500

30.466

14.964

-152

773.833

-400

30.356

14.910

-122

771.050

-300

30.247

14.856

-91

768.276

-200

30.138

14.803

-61

765.509

-100

30.030

14.749

-30

762.750

0

29.921

14.696

0

760.000

100

29.813

14.643

30

757.258

200

29.706

14.590

61

754.523

300

29.598

14.537

91

751.797

400

29.491

14.485

122

749.078

500

29.385

14.432

152

746.368

600

29.278

14.380

183

743.665

700

29.172

14.328

213

740.971

800

29.066

14.276

244

738.284

900

28.961

14.224

274

735.605

1,000

28.856

14.173

305

732.934

1,100

28.751

14.121

335

730.271

1,200

28.646

14.070

366

727.616

1,300

28 .542

14.019

1,400

28.438

13.968

427

722.329

1,500

28.335

13.917

457

719.697

1,600

28.231

13.866

488

717.073

1,700

28.128

13.815

518

714.459

1,800

28.026

13.765

549

711.849

396

724.969

21-30-00

Oct

31/06Page

223

RBYtheOll

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201

ALtitude to Pressure Conversion

ALTITUDE FEET

Page

tcO42

31/06

PRESSURE IN-MG

PSIA

(Continued)

ALTITUDE

PRESSURE

METERS

MM-HG

1,900

27.923

13.715

579

709.248

2,000

27.821

13.665

610

706.655

2,100

27.719

13.615

640

704.069

2,200

27.618

13.565

671

701.491

2,300

27.517

13.515

701

698.921

2,400

27.416

13.465

732

696.359

2,500

27.315

13.416

762

693.804

2,600

27.215

13.367

792

691.257

2,700

27.115

13.318

823

688.717

2,800

27.015

13.269

853

686.185

2,900

26.916

13.220

884

683.660

3,000

26.817

13.171

914

681.143

3,100

26.718

13.123

945

678.634

3,200

26.619

13.074

975

676.1 31

3,300

26.521

13.026

1,006

673.637

3,400

26.423

12.978

1,036

671.150

3,500

26.326

12.930

1,067

668.670

3,600

26.228

12.882

1,097

666.1 98

3,700

26.131

12.835

1,128

663.733

3,800

26.034

12.787

1,158

661.275

3,900

25.938

12.740

1,189

658.825

4,000

25.842

12.692

1,219

656.382

4,100

25.746

12.645

1,250

653.947

4,200

25.850

12.697

1,280

656.599

4,300

25.555

12.552

1,311

649.098

4,400

25.460

12.505

1,341

646.685

4,500

25.365

12.458

1,372

644.278

4,600

25.271

12.412

1,402

641.879

4,700

25.177

12.366

1,433

639.488

4,800

25 .083

12.320

1,463

637.1 03

4,900

24.989

12.274

1,494

634.726

21-30-00

A21

Raytbeon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201

ALtitude to Pressure Conversion ALTITUDE FEET

A21

PRESSURE

IN-NC

PSIA

(Continued)

ALTITUDE

PRESSURE

METERS

MM-HG

5,000

24.896

12.228

1,524

632.356

5,100

24.803

12.182

1,554

629.993

5,200

24.710

12.137

1,585

627.637

5,300

24.618

12.091

1,615

625.288

5,400

24.525

12.046

1,646

622.947

5,500

24.434

12.001

1,676

620.612

5,600

24.341

11.956

1,707

618.272

5,700

24.251

11.911

1,737

615.965

5,800

24.160

11.866

1,768

613.652

5,900

24.069

11.822

1,798

611.345

6,000

23.978

11.777

1,829

609.046

6,100

23.888

11.733

1,859

606.754

6,200

23.798

11.689

1,890

604.469

6,300

23.708

11.645

1,920

602.191

6,400

23.619

11.601

1,951

599.920

6,500

23.530

11.557

1,981

597.655

6,600

23.441

11.513

2,012

595.398

6,700

23.352

11.470

2,042

593.147

6,800

23.264

11.426

2,073

590.904

6,900

23.176

11.383

2,103

588.667

7,000

23.088

11.340

2,134

586.437

7,100

23.001

11.297

2,164

584.215

7,200

22.913

11.254

2,195

581.998

7,300

22.826

11.211

2,225

579.789

7,400

22.740

11.169

2,256

577.586

7,500

22.653

11.126

2,286

575.391

7,600

22.567

11.084

2,316

573.202

7,700

22.481

11.042

2,347

571.019

7,800

22.395

11.000

2,377

568.844

7,900

22.310

10.958

2,408

566.675

8,000

22.225

10.916

2,438

564.513

21-30-00

Oct

31/06Page

225

ReYtheepp

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 ALtitude to Pressure Conversion ALTITUDE FEET

Page

tcO62

31/06

PRESSURE IN-NC

PSIA

~Continued)

ALTITUDE

PRESSURE

METERS

MM-HG

8,100

22.140

10.874

2 ,469

562.358

8,200

22.055

10.833

2,499

560.209

8,300

21.971

10.791

2,530

558.067

8,400

21.887

10.750

2,560

555.931

8,500

21.803

10.709

2,591

553.803

8,600

21.720

10.668

2,621

551.680

8,700

21.636

10.627

2,652

549.565

8,800

21.553

10.586

2,682

547.456

8,900

21.471

10.545

2,713

545.353

9,000

21.388

10.505

2,743

543.257

9,100

21.306

10.465

2,774

541.168

9,200

21.224

10.424

2,804

539.085

9,300

21.142

10.384

2,835

537.008

9,400

21.061

10.344

2,865

534.933

9,500

20.958

10.293

2,896

532.333

9,600

20.898

10.264

2,926

530.818

9,700

20.818

10.225

2,957

528.767

9,800

20.737

10.185

2,987

526.723

9,900

20.657

10.146

3,018

524.685

10,000

20.577

10.107

3,048

522.654

10,100

20.497

10.067

3,078

520.629

10,200

20.418

10.028

3,109

518.610

10,300

20.339

9.989

3,139

516.593

10,400

20.260

9.951

3,170

514.592

10,500

20.181

9.912

3,200

512.592

10,600

20.102

9.873

3,231

510.599

10,700

20.024

9.835

3,261

508.612

10,800

19.946

9.797

3,292

506.631

10,900

19.868

9.759

3,322

504.657

11,000

19.791

9.720

3,353

502.688

11,100

19.714

9.683

3,383

500.726

21-30-00

A21

Ray~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 AMitude to Pressure Conversion

PRESSURE

ALTITUDE FEET

A21

IN-NC

PSIA

(Continued)

ALTITUDE

PRESSURE

METERS

MM-HG

11,200

19.637

9.645

3,414

498.770

11,300

19.560

9.607

3,444

496.820

11,400

19.483

9.569

3,475

494.877

11,500

19.407

9.532

3,505

492.940

11,600

19.331

9.495

3,536

491.008

11,700

19.255

9.457

3,566

489.084

11,800

19.180

9.420

3,597

487.164

11,900

19.104

9.383

3,627

485.251

12,000

19.029

9.346

3,658

483.345

12,100

18.954

9.310

3,688

481.444

12,200

18.880

9.273

3,719

479.549

12,300

18.806

9.237

3,749

447.661

12,400

18.731

9.200

3,780

475.778

12,500

18.658

9.164

3,810

473.901

12,600

18.584

9.128

3,840

472.031

12,700

18.510

9.092

3,871

470.166

12,800

18.437

9.056

3,901

468.308

12,900

18.384

9.030

3,932

466.963

13,000

18.292

8.984

3,962

464.608

13,100

18.219

8.949

3,993

462.767

13,200

18.147

8.913

4,023

460.932

13,300

18.075

8.878

4,054

459.103

13,400

18.003

8.842

4,084

457.280

13,500

17.932

8.807

4,115

455.463

13,600

17.860

8.772

4,145

453.652

13,700

17.789

8.737

4,176

451.846

13,800

17.718

8.703

4,206

450.046

13,900

17.648

8.668

4,237

448.252

14,000

17.577

8.633

4,267

446.464

14,100

17.507

8.599

4,298

444.682

14,200

17.437

8.564

4,328

442.905

21-30-00

Oct

31/06Page

227

Rayrheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 ALtitude to Pressure Conversion ALTITUDE FEET

Page

tcO82

31/06

PRESSURE IN-NC

PSIA

(Continued)

ALTITUDE

PRESSURE

METERS

MM-HG

14,300

17.367

8.530

4,359

441.134

14,400

17.248

8.472

4,389

438.099

14,500

17.229

8.462

4,420

437.610

14,600

17.160

8.428

4,450

435.856

14,700

17.091

8.394

4,481

434.108

14,800

17.022

8.361

4,511

432.366

14,900

16.954

8.327

4,542

430.629

15,000

16.886

8.294

4,572

428.898

15,100

16.818

8.260

4,602

427.173

15,200

16.750

8.227

4,633

425.453

15,300

16.683

8.194

4,663

423.739

15,400

16.615

8.161

4,694

422.030

15,500

16.548

8.128

4,724

420.328

15,600

16.482

8.095

4,755

418.630

15,700

16.415

8.062

4,785

416.938

15,800

16.349

8.030

4,816

41 5.252

15,900

16.282

7.997

4,846

413.571

16,000

16.216

7.965

4,877

411.896

16,100

16.151

7.933

4,907

41 0.226

16,200

16.085

7.900

4,938

408.562

16,300

16.020

7.868

4,968

406.903

16,400

15.955

7.836

4,999

405.250

16,500

15.890

7.804

5,029

403.602

16,600

15.825

7.773

5,060

401.960

16,700

15.761

7.741

5,090

400.323

16,800

15.697

7.709

5,121

398.691

16,900

15.632

7.678

5,151

397.065

17,000

15.569

7.647

5,182

395.444

17,100

15.505

7.615

5,212

393.829

17,200

15.442

7.584

5,243

392.218

17,300

15.378

7.553

5,273

390.614

21-30-00

A21

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201

ALtitude to Pressure Conversion PRESSURE

ALTITUDE FEET

A21

IN-MG

PSIA

(Continued)

ALTITUDE

PRESSURE

METERS

MM-HG

17,400

15.316

7.522

5,304

389.026

17,500

15.253

7.492

5,334

387.420

17,600

15.190

7.461

5,364

385.831

17,700

15.128

7.430

5,395

384.247

17,800

15.066

7.400

5,425

382.669

17,900

15.004

7.369

5,456

381.096

18,000

14.942

7.339

5,486

379.528

18,100

14.881

7.309

5,517

377.965

18,200

14.819

7.279

5,547

376.408

18,300

14.758

7.249

5,578

374.856

18,400

14.697

7.219

5,608

373.309

18,500

14.636

7.189

5,639

371.767

18,600

14.576

7.159

5,669

370.230

18,700

14.516

7.130

5,700

368.699

18,800

14.456

7.100

5,730

367.172

18,900

14.396

7.071

5,761

365.651

19,000

14.336

7.041

5,791

364.1 35

19,100

14.277

7.012

5,822

362.624

19,200

14.217

6.983

5 ,852

361.118

19,300

14.158

6.954

5,883

359.617

19,400

14.099

6.925

5,913

358.121

19,500

14.041

6.896

5,944

356.630

19,600

13.982

6.867

5,974

355.1 44

19,700

13.924

6.839

6,005

353.664

19,800

13.866

6.810

6,035

352.1 88

19,900

13.808

6.782

6,066

350.717

20,000

13.750

6.753

6,096

349.251

20,100

13.693

6.725

6,126

347.790

20,200

13.635

6.697

6,157

346.334

20,300

13.578

6.669

6,187

344.883

20,400

13.521

6.641

6,218

343.437

21-30-00

Oct

31/06Page

229

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 ALtitude to Pressure Conversion

ALTITUDE FEET

Page

tcO032

31/06

PRESSURE IN-NC

PSIA

(Continued) ALTITUDE

PRESSURE

METERS

MM-HG

20,500

13.464

6.613

6,248

341.996

20,600

13.408

6.585

6,279

340.560

20,700

13.352

6.558

6,309

339.129

20,800

13.295

6.530

6,340

337.702

20,900

13.239

6.503

6,370

336.281

21,000

13.184

6.475

6,401

334.864

21,100

13.128

6.448

6,431

333.452

21,200

13.073

6.421

6,462

332.045

21,300

13.017

6.394

6,492

330.643

21,400

12.962

6.367

6,523

329.245

21,500

12.908

6.340

6,553

327.852

21,600

12.953

6.362

6,584

329.005

21,700

12.798

6.286

6,614

325.081

21,800

12.744

6.259

6,645

323.703

21,900

12.690

6.233

6,675

322.329

22,000

12.636

6.206

6,706

320.960

22,100

12.583

6.180

6,736

319.596

22,200

12.529

6.154

6,767

318.237

22,300

12.476

6.128

6,797

316.882

22,400

12.423

6.101

6,828

315.532

22,500

12.370

6.075

6,858

314.186

22,600

12.317

6.049

6,888

312.845

22,700

12.264

6.024

6,919

311.509

22,800

12.212

5.998

6,949

310.177

22,900

12.159

5.972

6,980

308.850

23,000

12.107

5.947

7,010

307.528

23,100

12.056

5.921

7,041

306.210

23,200

12.004

5.896

7,071

304.897

23,300

11.952

5.870

7,102

303.588

23,400

11.901

5.845

7,132

302.284

23,500

11.850

5.820

7,163

300.985

21-30-00

A21

RBYtheoll

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201

ALtitude to Pressure Conversion ALTITUDE FEET

IN-NC

PSIA

ALTITUDE

PRESSURE

METERS

MM-HG

23,600

11.799

5.795

7,193

299.690

23,700

11.748

5.770

7,224

298.399

23,800

11.697

5.745

7,254

297.113

23,900

11.647

5.720

7,285

295.832

24,000

11.597

5.696

7,315

294.555

24,100

11.547

5.671

7,346

293.282

24,200

11.497

5.647

7,376

292.014

24,300

11.447

5.622

7,407

290.750

24,400

11.397

5.598

7,437

289.491

24,500

11.348

5.574

7,468

288.236

24,600

11.299

5.549

7,498

286.986

24,700

11.250

5.525

7,529

285.740

24,800

11.201

5.501

7,559

284.498

24,900

11.152

5.477

7,590

283.261

7,620

282.028

25,000

A21

PRESSURE

(Continued)

11.103

5.454

25,100

11.055

5.430

7,650

280.799

25,200

11.007

5.406

7,681

279.575

25,300

10.959

5.383

7,711

278.355

25,400

10.911

5.359

7,742

277.140

25,500

10.863

5.336

7,772

275.928

25,600

10.816

5.312

7,803

274.721

25,700

10.768

5.289

7,833

273.519

25,800

10.721

5.266

7,864

272.320

25,900

10.674

5.243

7,894

271.126

26,000

10.627

5.220

7,925

269.936

26,100

10.581

5.197

7,955

268.750

26,200

10.534

5.174

7,986

267.569

26,300

10.488

5.151

8,016

266.392

26,400

10.442

5.129

8,047

265.218

26,500

10.396

5.106

8,077

264.050

26,600

10.350

5.083

8,108

262.885

21-30-00

Oct

31/06Page

231

RayYheon

AiKraft Campany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 ALtitude to Pressure Conversion ALTITUDE FEET

Oct

31/06Page

232

PRESSURE IN-NC

PSIA

(Continued)

ALTITUDE

PRESSURE

METERS

MM-HG

26,700

10.304

5.061

8,138

261.724

26,800

10.259

5.039

8,169

260.568

26,900

10.213

5.016

8,199

259.416

27,000

10.168

4.994

8,230

258.268

27,100

10.123

4.972

8,260

257.124

27,200

10.078

4.950

8,291

255.984

27,300

10.033

4.928

8,321

254.848

27,400

9.989

4.906

8,352

252.716

27,500

9.944

4.884

8,382

252.588

27,600

9.900

4.863

8,412

251.465

27,700

9.856

4.841

8,443

250.345

27,800

9.812

4.819

8,473

249.230

27,900

9.768

4.798

8,504

248.118

28,000

9.725

4.776

8,534

247.011

28,100

9.681

4.755

8,565

245.907

28,200

9.638

4.734

8,595

244.808

28,300

9.595

4.713

8,626

243.712

28,400

9.552

4.692

8,656

242.621

28,500

9.509

4.671

8,687

241.533

28,600

9.467

4.650

8,717

240.450

28,700

9.424

4.629

8,748

239.370

28,800

9.382

4.608

8,778

238.294

28,900

9.339

4.587

8,809

237.223

29,000

9.297

4.567

8,839

236.1 55

29,100

9.256

4.546

8,870

235.091

29,200

9.214

4.525

8,900

234.031

29,300

9.172

4.505

8,931

232.974

29,400

9.131

4.485

3,961

231.922

29,500

9.090

4.464

8,992

230.877

29,600

9.048

4.444

9,022

229.829

29,700

9.007

4.424

9,053

228.788

21-30-00

A21

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201

AMitude to Pressure Conversion ALTITUDE FEET

A21

PRESSURE IN-NC

PSIA

(Continued)

ALTITUDE

PRESSURE

METERS

MM-HG

29,800

8.967

4.404

9,083

227.751

29,900

8.926

4.384

9,114

226.718

30,000

8.853

4.348

9,144

224.875

30,100

8.845

4.344

9,174

244.663

30,200

8.805

4.325

9,205

223.641

30,300

8.765

4.305

9,235

222.625

30,400

8.725

4.285

9,266

221.608

30,500

8.685

4.266

9,296

220.598

30,600

8.645

4.246

9,327

219.591

30,700

8.606

4.227

9,357

218.583

30,800

8.566

4.207

9,388

217.588

30,900

8.527

4.188

9,418

216.593

31,000

8.488

4.169

9,449

215.601

31,100

8.449

4.150

9,479

214.612

31,200

8.411

4.131

9,510

213.628

31,300

8.372

4.112

9,540

212.647

31,400

8.333

4.093

9,571

211.669

31,500

8.295

4.074

9,601

210.695

31,600

8.257

4.055

9,632

209.725

31,700

8.219

4.037

9,662

208.759

31,800

8.181

4.018

9,693

207.796

31,900

8.143

4.000

9,723

206.837

32,000

8.106

3.981

9,754

205.881

32,100

8.068

3.963

9,784

204.929

32,200

8.031

3.944

9,815

203.981

32,300

7.994

3.926

9,845

203.036

32,400

7.956

3.908

9,876

202.094

32,500

7.920

3.890

9,906

201.156

32,600

7.883

3.872

9,936

200.222

32,700

7.846

3.854

9,967

199.291

32,800

7.810

3.836

9,997

198.364

21-30-00

Oct

31/06Page

233

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201

ALtitude to Pressure Conversion

ALTITUDE FEET

Oct

31/06Page

234

PRESSURE

IN-NC

PSIA

(Continued)

ALTITUDE

PRESSURE

METERS

MM-HG

32,900

7.773

3.818

10,028

197.440

33,000

7.737

3.800

10,058

196.520

33,100

7.701

3.782

10,089

195.603

33,200

7.685

3.775

10,119

195.197

33,300

7.629

3.747

10,150

193.779

33,400

7.593

3.730

10,180

192.873

33,500

7.558

3.712

10,211

191.970

33,600

7.522

3.695

10,241

191.070

33,700

7.487

3.677

10,272

190.174

33,800

7.452

3.660

10,302

189.281

33,900

7.417

3.643

10,333

188.392

34,000

7.382

3.626

10,363

187.506

34,100

7.347

3.609

10,394

186.623

34,200

7.322

3.596

10,424

185.973

34,300

7.278

3.575

10,455

184.868

34,400

7.244

3.558

10,485

183.995

34,500

7.210

3.541

10,516

183.126

34,600

7.175

3.524

10,546

182.260

34,700

7.142

3.508

10,577

181.398

34,800

7.108

3.491

10,607

180.538

34,900

7.074

3.475

10,638

179.682

35,000

7.041

3.458

10,668

178.830

21-30-00

A21

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

HEATING

BLEED AIR HEAT

produced in the P3 stage of each engine is routed through the flow control valves and the wing heat exchangers as required to provide heated air at the floor outlets. The bypass valves, located downstream of the wing heat exchangers, direct bleed air into the heat exchangers or allow bleed air to bypass them. Refer to Chapter 21-60-00 for a schematic showing the use of the valves in controlling cabin air temperature. Bleed air heat

When the aft bleed air control switch is set to

HEAT, conditioned bleed air flows through the aft bleed air heat valve

and the aft floor outlets. The motor-driven valve, located under the LH floorboards in line with the sixth cabin window, opens approximately 30 seconds after the control switch is set to ON. An aft bleed air heat line, connected to the check valve

assembly

in the main bleed air line,

joins

the aft

heating

ducts in line with the seventh cabin window.

ELECTRIC HEAT The electric heat system is used to preheat the interior of the airplane prior to engine operation and is not designed to supplement engine bleed air heat. The electric heat system should be powered through a ground power unit, as the airplanes battery cannot power the system. Electric heat is normally operated when cold weather makes it

necessary to heat the cabin area prior to the boarding of passengers. The system is designed so that it only operates airplane is on the ground and the ambient temperature inside is at or below 55"F to 60"F. At 55"F to 60"F,

when the

the thermistors in the main heat ducts will reach 16K ~2K ohms in resistance and the electric heat PCB will provide a voltage output to close the electric heat power relays. Once on, the thermostatically controlled system will continue to

provide heat until the

thermistors in the heat duct reach

a

resistance value of 5.1K lt1.5K ohms, at which time the remove power to the system

duct temperature will have reached 113"F to 118"F. The electric heat PCB will then and the power relays will open. The magnetically held switch will also release. NOTE:

Manually holding

the electric heat switch in the ON

position will

not override the electric heat control PCB to

operate the electric heat system. Control of the electric heat system is separate from the automatic and manual temperature controls for bleed air heat. A control switch (S179), placarded ELEC HEAT on the right inboard subpanel, energizes the heater power relays for the forward and aft electric heaters. The aft vent blower switch, placarded AFT BLOWER ON, is located next to the ELEC HEAT switch. The forward electric heat circuit is enabled when the cabin

is set to the MAN HEAT

or

AUTO

position.

temperature mode switch

The aft electric heat circuit is enabled when MAN HEAT

or

AUTO is

selected and the AFT BLOWER switch is set to ON. The vent blowers that distribute cool air also distribute the heat

produced by

the electric heaters.

sensors (RT106 and RT108) and the electric heat circuit card (A321) provide a safety cutoff of power to the electric heaters. If duct temperature reaches approximately 113"F to 118"F, a sensor (RT106 or RT108) in the duct signals the electric heat control circuits on the electric heat circuit card (A321) to shut down the system. The forward and aft heater power relays and the solenoid-held control switch are then de-energized and power is

Overheat

removed from the heaters. The forward heater and the overtemperature sensor is located in the main heating duct immediately aft of the mixing plenum. The duct overtemperature switch is located in the main heating duct

immediately

aft of the

mixing plenum.

The

corresponding relay

is located under the

flight compartment

center

floorboard. The aft heater element and overtemperature sensor are located in the aft evaporator plenum, under the center aisle floorboard in line with the sixth cabin window. The corresponding relay is located adjacent to the heater. Circuit breakers

(100-amp) in the electric heat system are located under partition on the DC power distribution panel.

the center aisle floorboards

aft of the cabin forward

n21

21-40-00

immediately

Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

HEATING- TROUBLESHOOTING (FL-I THRU FL-492, FL-494 THRU FL-499; FM-1 THRU FM-13) Refer to Charts 101, 102, and 103 and

Figure

101 to troubleshoot the

heating system.

ELECT HEAT ON ANNUNCIATOR

kb--p~-;

FWD

HEATER

AFT

HEATER

5FI

100A FWD ELECT HEAT

FWD HEATER POWER RELAY

k-b--T; 5A

I

100A AFT ELECT HEAT

TO I

F~FT HEFITER POWER RELAY

5

P1

~FT

6

AFT

BLOWER

20A

BLOWER

RELAY

AFT

BLOWER SWITCH

P455 14

OFF AUTO

17

C-

MF\N

023

Q

RH LANDING GEAR SQUAT SWITCH

21 MODE

GND

COOL

27

16

.AIR

\n22 Y 28rL~I

OFF

1

3

1

SWITCH AFT BLOWER SWITCH

n

IELECTRIC HEAT

SWITCH

(SOLENOID

´•r,

HELD)

21

15 b

5A

I

CABIN TEMP CONTROL

I 10

A278 ELECTRIC HEAT CIRCUIT CARD ASSEMBLY

22

((I 23 RT 106 FWD OVERHEAT

SENSOR 24

Ill 25 RT 108 FIFT OVERHEAT

SENSOR

FLZIB oso59au(

Electric Heat Control Schematic

Figure

A21

101

2140-00

Oct

31/06Page

101

Raythwm

AiKraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 101 Bleed Air

Troubleshooting STEP 1

Do

bypass

valves

Heating Inadequate Heating

operate manually (1)?

YES

Proceed to step 5

YES

Proceed to step 2

YES

Proceed to step 3

NO Is power at

A of LH

pin

bypass

valve

(3)?

NO

Troubleshoot temperature control system

(21-60-00). STEP 2

Is

pin

E of LH

bypass valve well grounded?

NO Correct STEP 3

ground.

Is power at pin C of LH

bypass

valve?

YES

Replace

LH

bypass

valve?

YES

Proceed to step 4

YES

Replace

YES

Troubleshoot bleed air

bypass

valve

NO Is power at pin A

or

RH

NO Locate open in cabin temperature mode

circuit. STEP 4

Is

pin E of RH bypass grounded?

valve well

RH

bypass

valve.

NO

Correct

STEP 5

ground.

Do

bypass valves operate automatically (2)?

system

(21-10-00).

NO

Troubleshoot temperature control system

(21-60-00). NOTE 1. Turn

battery switch

on,

place cabin temperature mode switch

ature control switch in INCR. Valve motor noise should be

will

run

from

fully

closed to

fully open

in

approximately

in MAN HEAT and hold the manual temperat the left inboard wing. The two valves

apparent

60 seconds for

a

normally operating system.

battery switch on, place cabin temperature mode switch in AUTO and rotate the auto temperature potentiometer clockwise. Listen for the valve motor noise in the left inboard wing. Rotate the auto temperature potentiometer counterclockwise. The valves will run from fury open to fully closed in approximately 60 seconds for a normally operating system.

2. Turn

3. Power will be

present only with the cabin temperature mode switch in MAN COOL, the manual temperature

control switch in INCREASE and the

Page

tcO31/06 201

21-40-00

battery

switch ON.

,1

Raytheon

Aireraft

company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 102

Troubleshooting STEP 1

Do

bypass

valves operate

Bleed Air

Heating

YES

Proceed to step 5

(3)? YES

Proceed to step 2

manually (1)?

NO Is power at

pin B of RH bypass

valve

NO Troubleshoot temperature control system

(21-60-00). Is pin E of RH bypass grounded?

STEP 2

valve well

YES

Proceed to step 3

YES

Replace

YES

Proceed to step 4

YES

Replace

YES

Troubleshoot bleed air system

NO Correct

ground.

Is power at

STEP 3

pin

D

or

RH

bypass

valve?

LH

bypass

valve.

NO Is power at

pin B of LH bypass valve?

NO Locate open in cabin temperature mode circuit.

.STEP 4

Is pin E of LH bypass grounded?

valve well

LH

bypass

valve.

NO

Correct STEP 5

Do

ground.

bypass valves operate automatically?

(21-10-00).

(2) NO Troubleshoot temperature control system

(21-60-00). NOTE 1. Turn

battery

switch on,

place cabin temperature mode switch

in MAN COOL and hold the manual

temperature

control switch in DECR. Valve motor noise should be apparent at the left inboard wing. The two valves will fully open to fully closed in approximately 60 seconds for a normally operating system. 2. Turn

battery

switch on,

place cabin temperature mode switch

in AUTO and rotate the auto

run

from

temperature poten-

wing root. Rotate the auto temperature porun from fully open to fully closed in approximately 60 seconds for a normally

tiometer counterclockwise. Listen for the valve motor noise in the left tentiometer clockwise. The valves will

operating system. 3. Power will be

present only with the cabin temperature mode switch in MAN COOL, the manual temperature

trol switch in DECREASE and the

A21

battery

con-

switch ON.

21-40-00

Oct

31/06Page

103

Ral4heon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 103

Troubleshooting STEP 1

Are

heating

grounded (1)?

elements

Electric

Heating

YES

Proceed to step 2

YES

Replace

YES

Close circuit breaker.

YES

Replace defective relay.

YES

Correct lack of

YES

Proceed to step 3

YES

Replace thermoswitch.

NO Ground STEP 2

properly.

Is power at heater elements?

defective heater element

NO Are FWD ELECT HEAT

HEAT circuit breaker

or

AFT ELECT

open?

NO Is power at heater power electric heat switch?

relays

and

NO Is squat switch

open?

continuity.

NO Have duct thermoswitches closed

(overheated)? NO

Correct STEP 3

continuity

thru mode switch.

Is duct temperature lower than

closing

limits? NO

System has designed.

been

disengaged

as

NOTE 1. Set the mode switch to any position except OFF. The airplane should be on the ground (squat switch closed), ENVIR OFF, and the electric heat control switch should be set to the bleed air switches should be set to PNEU

ON.

Page

tcO401

31/06

21-40-00

A21

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 200200200

HEATING - MAINTENANCE PRACTICES (FL-1 THRU FL-492, FL-494 THRU FL-499; FM-1 THRU FM-13) MICROSWITCH ADJUSTMENT (BLEED AIR BYPASS) The bypass valves open and close as required to modulate the amount of bleed air that is routed into the heat exchanger in each wing leading edge. As the left hand bypass valve passes through the 30° position, the externally mounted cam switch closes and energizes the air conditioning compressor, when the mode switch is in MANUAL COOL. In the AUTO mode, the 30° switch arms the air conditioner system and the internal switch completes the circuit to turn on the compressor when the bypass valve reaches full travel. When the mode switch is in MANUAL COOL, If the air conditioning system does not engage and all control switches in the system are set correctly, adjust the bypass valve as follows: a. Remove the access panel on the underside of the left hand center section forward of the main spar to gain access to the bypass valve. b. Remove the insulation as necessary to gain access to the microswitch. c.

Using the manual temperature control switch, run the valve to the point where the valve AN3-4A/M/ bolt centers on the 30° position mark on the bypass valve plate (Ref. Figure 201).

d. Disconnect the electrical power from the airplane. e. Loosen the two screws securing the microswitch. f.

Adjust the cam on the microswitch roller to activate and deactivate the microswitch at the proper position and tighten the attaching parts.

g. Connect electrical power to the airplane and run the valve through a full cycle to make sure that the valve is functioning properly. The manual temperature control switch should be held in the INCR and DECR positions to fully open and close the bypass valve. h. Replace the insulation on the bypass valve and wrap with pressure sensitive aluminum tape (6, Chart 2, 21-00-00).

BLEED AIR BYPASS VALVE REMOVAL a. Remove the access panel from the underside of the inboard wing center section, just inboard of the heat exchanger discharge duct. b. Disconnect the electrical connector from the valve motor (Ref. Figure 202). c.

Push back the insulation covering the couplings and remove the coupling clamps.

d. Remove the clamps securing the bypass valve to the three bleed air lines and remove the valve.

A27

21-40-00

Page 201 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

BLEED AIR BYPASS VALVE INSTALLATION a. Install the valve and secure with the clamps (Ref. Figure 202). b. Install the insulation around the couplings. c.

Install the electrical connector on the valve motor.

d. Install the access panel on the underside of the inboard wing.

BLEED AIR BYPASS VALVE OPERATIONAL CHECK The bleed air bypass valves (left and right) are located on the underside of the inboard wing center section, just inboard of the heat exchanger discharge ducts. NOTE: Two personnel are required to perform this procedure. a. Remove the access panels covering the bleed air bypass valves. b. Apply external electrical power to the airplane. c.

While operating the heating system in the MANUAL HEAT mode: 1. Hold the manual temperature control switch to the DECR position for 60 seconds. Make sure that the bleed air bypass valve’s position is to the OPEN position. 2. Hold the manual temperature control switch to the INCR position for 60 seconds. Make sure that the bleed air bypass valve’s position is to the CLOSED position.

d. Remove electrical power from the airplane. e. Install the access panels.

BLEED AIR SHUTOFF VALVE REMOVAL (AFT HEAT) a. Remove the left hand floorboard in line with the sixth cabin window. b. Disconnect the electrical connector from the valve motor. c.

Push back the insulation covering the couplings and remove the coupling clamps.

d. Remove the clamps securing the shutoff valve to the bleed air line and remove the valve.

BLEED AIR SHUTOFF VALVE INSTALLATION (AFT HEAT) a. Install the valve and secure with the clamp. b. Install the insulation around the couplings. c.

Install the electrical connector on the valve motor.

d. Install the left hand floorboard and carpet.

Page 202 Feb 1/10

21-40-00

A27

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ELECTRIC HEAT ELEMENT REMOVAL, FORWARD a. Remove the copilot’s chair. b. Remove the right hand floorboard in the crew compartment to gain access to the heater element duct assembly immediately aft of the mixing plenum. c.

Disconnect the electrical wiring from the heater element and remove the sensors from the duct.

d. Remove the insulation wrap from the heat element duct and portions of the ducts immediately forward and aft of the heat element duct. e. Remove the clamps from the forward and aft ends of the heat element duct which secure the duct segments together. f.

Work the heat element duct aft to release it from the forward duct segment, then forward to release the heat element duct from the duct system.

g. Disconnect the two bond jumpers from the heat element duct and remove the duct from the airplane. h. Remove the nuts and washers from each side of the duct to release the heat element inside of the duct. i.

Remove screws which connect the two halves of the duct together and remove the heat element from the duct.

ELECTRIC HEAT ELEMENT INSTALLATION, FORWARD a. Position the heat element in one of the duct halves and install the other half of the duct, securing the two halves together with screws in the top and bottom of the duct. b. Install the nuts and washers on each side of the duct to secure the heat element inside of the duct. c.

Position the duct in the airplane beneath the crew compartment floor and attach the two bond jumpers to each end of the duct.

d. Wrap the duct with the self-adhesive oven insulation. e. Install the two sensors in the top of the duct and connect the electrical wiring to the element connections. f.

Install the right hand floorboard in the crew compartment.

g. Install the copilot’s chair.

A27

21-40-00

Page 203 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ELECTRIC HEAT ELEMENT REMOVAL, AFT a. Remove the right hand aft cabin chairs. b. Remove the center aisle and right hand carpet and floorboards in line with the fifth cabin window. c.

Disconnect the electrical wiring from the heater element.

d. Remove the insulation from the heater and evaporator plenum. e. Remove the screws from the evaporator and the heater plenum, and remove the covers. f.

Remove two nuts and washers from each end of the heating element and remove the element from the plenum.

ELECTRIC HEAT ELEMENT INSTALLATION, AFT a. Position the heater element in the plenum and install the nuts and washers on each end of the element. b. Install the covers on top of the heat and evaporator plenums and secure them with the attaching screws. c.

Install the self-adhesive oven insulation on the plenums.

d. Connect the electrical wiring to the element connections. e. Install the floorboards, carpet and cabin chairs.

ELECTRIC HEATER POWER RELAYS OPERATIONAL CHECK a. Gain access to the A278 card in the FWD center floor area. b. Observe the two LED’s. c.

With airplane power ON and Electric Heat OFF, there should be no LED’s illuminated.

d. With Electric Heat ON, both LED’s should be illuminated. e. With the press-to-test momentary switch engaged, only one LED should be illuminated. f.

If at any time this is not the case, the relays should be inspected for stuck contactors.

Page 204 Feb 1/10

21-40-00

A27

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Microswitch Adjustment - Left Hand Bleed Air bypass Valve Figure 201

A27

21-40-00

Page 205 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Bleed Air Bypass Valve Installation Figure 202

Page 206 Feb 1/10

21-40-00

A27

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 100100100 21-41-00

HEATING - TROUBLESHOOTING (FL-493, FL-500 AND AFTER; FM-14 AND AFTER) The following procedures are used to perform typical troubleshooting of the electric heating system. In order for the electric heater to function, the airplane must be on the ground to activate the safety squat switch and must have external power applied to the airplane or generators operating. Verify that circuit breakers CB48, CB22, and CB24 (located on the A145 Panel assembly are pressed in and select ELEC HEAT on the environmental control panel.

INADEQUATE OR NO HEATING a. Is there airflow from center aisle outlet? 1. No, inspect forward evaporator blower operation. 2. Yes, below normal, inspect forward plenum valve plate position and operation. 3. Yes, normal, proceed to next step. b. Is there continuity between L/H connector pin 2 and R/H connector pin 2 of heater assembly? 1. No, replace thermal fuses (Ref. Thermal Fuse Replacement). 2. Yes, proceed to next step. c.

Is there continuity between L/H connector pin 3 and R/H connector pin 3 of heater assembly? 1. No, failed thermostat switch, replace heater assembly. 2. Yes, proceed to next step.

d. Measure the resistance between the power terminals of the heater assembly. Is the resistance less than 1 ohm? 1. No, failed heating element, replace heater assembly. 2. Yes, inspect power relays and heater controller.

ELECTRIC HEATER POWER RELAYS OPERATIONAL CHECK a. Gain access to the A278 card in the FWD center floor area. b. Observe the two LED’s. c.

With airplane power ON and Electric Heat OFF, there should be no LED’s illuminated.

d. With Electric Heat ON, both LED’s should be illuminated. e. With the press-to-test momentary switch engaged, only one LED should be illuminated. f.

If at any time this is not the case, the relays should be inspected for stuck contactors.

A27

21-41-00

Page 101 Feb 1/10

Ral~heon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

HEATING

MAINTENANCE PRACTICES

(FL-493, FL-500

AND

AFTER; FM-14 AND AFTER)

ELECTRIC HEATER REMOVAL a.

Disconnect

b.

Remove the

copilot’s

c.

Remove the

flight compartment

d.

Disconnect the flexible duct from the forward

e.

Disconnect the electrical connections from the heater.

f.

battery.

Remove three

seat

screws

(Ref. 25-10-00). floorboards

on

the

copilot’s

plenum

to

side between FS 84.00 and FS 107.00.

gain

access

to the heater

~Ref. Figure 201).

connecting the heater to the plenum. Remove two bolts attaching the heater to the frame screws connecting the heater to the aft duct. Remove the heater from the airplane.

bracket. Remove three

ELECTRIC HEA TER INSTALLA TION a.

Place the heater in position below the rudder pedals and into the forward plenum with the electrical connectors Install two bolts attaching the heater to the frame bracket. Install three screws connecting the heater

pointing aft. to the

plenum.

Install three

screws

attaching

b.

Install the flexible duct to the forward

c.

Connect and

d.

Install

flight compartment

e.

Install

copilot’s

f.

Connect

secure

seat

the aft duct to the heater

plenum with

attachment

(Ref. Figure 201).

screws.

the electrical connections. floorboards

on

the

copilot’s

side between FS 84.00 and FS 107.00.

(Ref. 25-10-00).

battery.

21-41-00

RayCheon

AiKraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

THERMAL FUSE REPLACEMENT CAUTION: The thermal fuses

are

safety backup devices

used to ensure the heater assembly temperature does not

increase above temperature limits. A single point failure in the heating system should not cause thermal fuse activation. Investigation to determine the cause of thermal fuse activation is recommended prior to thermal fuse

replacement.

a.

Disconnect

b.

Remove the electric heater assembly.

c.

Remove six

d.

Remove two thermal fuses, retain the attachment hardware, and discard thermal fuses.

e.

Crimp

f.

Install top plate to heater with

g.

Install electric

h.

Connect

Oct

new

battery.

screws

from the top

plate

and

thermal fuses and terminals

remove

together

top plate.

and install into heater.

screws.

heaterassembly.

battery.

21-41-00

~1

RB~heOn AiKrdft Company SUPER KING AIR MODEL B300/8300C MAINTENANCE MANUAL

84.00

FS 94.00 FS 100.50 FS 107.00

FS 116.00 FS 125.00

FS 134.00

FRAME

BOLTS

Rn~D PLENUM

ELECTRICAL CONNECTORS

HEATER DUCT

(3 EA)

DUCT SCREWS ELECTRIC HEATER ASSY

(3 EA)

O

a

ORIGINAL As Received By ATP

FL2(8 0613n~u\.AI

Electric Heater Installation

Figure 201

A21

21-41-00

Oct

31/06Page

203

RaytheOn

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RADIANT

HEATING, CARGO DOOR DESCRIPTION AND OPERATION (FM-1 AND AFTER) I

in the cargo door area is provided by a radiant heat panel located below the window in the cargo door behind the upholstery. The radiant heat panel operates automatically th rough a self contained thermostat on the panel any time the CABIN TEMP control is placed in either the MANUAL HEAT or AUTO HEAT position. In

Supplemental heating

addition to

a

10-amp

circuit breaker

on

the DC power distribution on the panel.

panel,

overheat

protection

is also

provided by

a

thermal fuse mounted next to the thermostat

RADIANT HEA T PANEL

easily removed following removal of the cargo door upholstery by disconnecting the removing four screws tone at each corner of the panel). Installation is accomplished by positioning the panel on the door, installing the four screws and reconnecting the electrical connector (Ref. Figure 1).

The radiant heat

panel

is

electrical connector and

nn

21-42-00

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OFPIGINAL As Received

By

ATP

I~

SCREW

r

SPACER

ELECTRICAL CONNEC’FOR

DETAIL

A

RADIANT HEATER PANEL ASSEMBLY

DETAIL

B 350-412-2

Radiant Heat Panel Installation

Figure

Oct

21-42-00

(FM-1

and

After)

1

A21

Raytheon

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COOLING

DESCRIPTION AND OPERATION

air-conditioning system utilizes refrigerant to provide cooling for the airplane cabin. Airplane serials FL-1 thru FL-127 and FM-1 thru FM-8, use refrigerant R-12 (1, Chart 2, 21-00-00). For airplane serials FL-128 and after, FM9 and after, and prior airplanes with Seech Kit 130-5009 installed use refrigerant R-l 34a (13, Chart 2, 21-00-00). A

The

compressor plus one condenser with a 36,000-BTU capacity, and two 12,500-BTU evaporators are utilized to cycle the refrigerant from a gas to a liquid state to provide cooling of the passenger compartment and flight compartment

(Ref. Figure 1). Adjustable outlets, located in the headliner in the passenger compartment and in the flight compartment overhead panel, distribute cool air produced by the air-conditioning system.

I

The temperature control switches used to control the heating systems are also used to control the air-conditioning system. The cabin temperature mode switch, the cabin temperature selector, and the manual temperature control

switch

are

located

on

the

copilot’s

inboard

subpanel.

Refer to 21-60-00 for further information

on

the

operation of

the temperature controls.

The compressor is equipped with an electric clutch and is installed in the accessory gear box section of the RH engine. The discharge line of the compressor is connected to the condenser, located adjacent to its blower in the nose of the airplane. The receiver-drier removes moisture from the refrigerant and is located adjacent to the condenser. The forward evaporator and the corresponding blower are located in the RH nose keel section. The aft are located under the center aisle floorboards in line with the sixth cabin window. The aft cool air to the aft overhead outlets and to the toilet compartment. The forward blower distributes cool air to the forward outlets in the passenger compartment and to the flight compartment outlets.

evaporator and blower blower

supplies

Refer to 21-20-00 for further information

on

the blowers and cool air distribution.

An overpressure cutout switch and an underpressure cutout switch are located on refrigerant lines in the RH wing leading edge. The reset switch for an underpressure or overpressure condition is located on the LH side wall of the nose

wheel well. Service valves

are

located in the condenser section in the

line with the first cabin window. Service valves differ for the R-12

When RH

engine speed

switch to AUTO

30"

position

or

exceeds 62%

MAN COOL

N,,

the

air-conditioning system can

(Ref. Figure 2).

and under the LH floorboards in

be activated

system.

by setting

When in MAN COOL, when the bleed air

bypass

temperature/pressure switch is closed, the clutch control relay command input of the N1 speed sensor PCB. (In the AUTO MODE, the

and the low

power to the cool

system

nose

and the R-l 34a

is

the mode control

valve reaches the

energized, supplying

30" switch

arms

the air-

conditioner system and the internal switch completes the circuit). The compressor clutch is then allowed to engage 10 seconds after the RH engine speed increases above 62% N1. The relay panel is located under the center aisle forward floorboards in line with the cabin forward

partition.

landing gear downlock switch is closed, a ground circuit is completed and energizes the coil of the condenser blower relay. Power is then supplied to the condenser blower and the blower moves air across the condenser and out the vents in the nose. When the airplane is in flight and the down lock switch is not closed (the landing gear is up), the condenser is cooled by the flow of ram air that enters through the inlet in the nose. When the cabin has been cooled to a preset temperature, the temperature control box sends the appropriate command to the bypass valves. The 30" position switch then opens, power is removed from the compressor clutch and it disengages. When the

nose

N1 speed of the RH engine falls below 62% while the compressor is operating, the annunciator light labeled N1 LOW (green) will illuminate, power will be removed from the compressor clutch and it will disengage (Ref. Figure 2). This compressor cutout provision prevents overloading the engine when it is operating at low I speeds. If the

AIR COND

The circuit breakers which protect the condenser blower, the air-conditioner clutch, the forward blower, and the aft blower are located on the DC power distribution panel, under the center aisle floorboards immediately aft of the

forward cabin

nn

partition.

21-50-00

Raytheon

AiKraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

I

relay is located in the main power distribution panel under the center aisle floor forward of the main spar. The N, speed sensor is located under the center aisle floorboards in the PCB rack, just aft of the pedestal. Refer to Chapter 39-20-00 for further information on the relays and the N, speed sensor PCB. The condenser blower

When the electric clutch

on

the compressor is

engaged,

the

refrigerant

is

compressed

temperature gas. As this gas is pumped through the condenser, cooling air is vented

i

into

a

across

high pressure, high the condenser and

(Ref. Figure 1). This liquid refrigerant passes through are removed. The refrigerant is then metered by the thermostatic expansion valves (TEV) and flows into the evaporators. The liquid evaporates (returns to a gas in the low pressure of the evaporator) cooling the evaporators. Heat from recirculating cabin air is absort~ed by the refrigerant in the evaporators. Vent blowers draw the recirculating air through the coils in the forward and aft evaporator assemblies. This heated gas is returned to the compressor where it is compressed into the high pressure hot discharge gas.

heat from the gas, condensing it into a the receiver-drier where moisture and impurities removes

liquid

state

HOT GAS BYPASS VALVE A temperature sensing switch is installed on the inlet line of the forward evaporator. If the temperature of the refrigerant inlet line is 33"F or below, the switch opens a solenoid valve in a hot gas line containing discharge gas

from the compressor. This hot gas bypasses the condenser and the expansion valves and flows directly into the evaporator to prevent moisture from freezing on the evaporator. When the temperature in the evaporator outlet line reaches 45"F, the thermoswitch closes the hot gas bypass valve and refrigerant flow is returned to its normal flow

through

the condenser and the

expansion valve.

PRESSURE CUTOUT SWITCHES

discharge pressure in the system increases beyond a safe limit, the overpressure cutout switch will open, removing power from the compressor clutch. If the suction pressure in the refrigerant line falls below a preset limit, the underpressure cutout switch will open and remove power from the compressor clutch. If power has been removed from the clutch by an open cutout switch, the switch must be reset to allow the compressor clutch to If the

engage. The reset switch is located in the RH side of the

nose

well.

An additional low pressure switch, located in the inlet line of the receiver-drier, will located under the floorboards, and power is removed from the compressor clutch.

de-energize

the control

relay,

VENT BLOWERS

by the vent blower switch and the mode control switch. Both switches are subpanel. The blower will operate at high speed or low speed when the temperature mode switch is set to any position. When the blower switch is set to AUTO, the forward blower will operate at low speed while the mode switch is set to any position except OFF. The control for the aft blower is the switch placarded AFT BLOWER. Refer to Chapter 21-20-00 for further information on the operation of the blowers and the relays.

The forward vent blower is controlled

located

on

the

copilot’s

inboard

PRESSURE RELIEF VAL VE A pressure relief valve is located on the discharge line in the nose wheel well. The valve is located downstream of the receiver-drier and protects system from an overpressure condition. The valve relieves pressure at 450 ~t20 psig.

Oct

31/06Page

2

21-50-00

A21

nireran

ConaQany

SUPER KING A18 MODEL B300/B300C MAINTENANCE MANUAL

ORIGINAL As Received BY ATP VkCUUM GAUGE

VACUUUPUtrlP

~ANUALOR SOLENOID VALVES

CO~PRESSOR SUCTION GAUGE OVER PRESSURE SWITCH D

/s

UFIDER PRESSURE

OIL-AIR SEPARATOR

PRESSURE RELIEF

DISCHARGE GAUGE

VALVE

REFRIGERANT CYLINDER

(HEATED)

PRESSURE SWITCH

CONDENSER

t

1

f

j

RECEIVERDRYER

BLOWER

HOT GAS BYF/I.SSVALVE OPENS 33" CLOSES 45’

THERMOSTATIC U(PANSIOFI

EOUAUZER

VALVE r----

1

THERI~OSWITCH OT

EXPANSION~ALVE

f

GAS

--s

TEMPERATURE SENSINGTUBE

TEUPERATUAE SENSING TUBE

I i I j

MERMOSTATIC

LINE

i I i

i

I i FILTER

I

Q---

)II

BLO’rSER

i

i I I j I I I

FILTER

FORWARD

AFT

EVAPORATOR

EVAPORATOR

NOR~ALFLOW SERVICE LIFIES

SERVICE VAC1’ES ARE LOCATED IN ME NOSE WHEEL WELL AND UNDER THE FLOORBOARDS ADJACENT TO ME LEFT HAND FORWARD PARTITION. SERVICE VALVES DIFFER FOA SYS~EMS USING A-12 AND R-1392.

-laR

Air-Conditioning System Refrigerant Figure 1

A21

Flow Schematic

21-50-00

Oct

31/06Page

3

Ray~heon

AiKraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

AIR CONDITIONING

I (COMPRESSOR CLUTCH PRESSUREI

27

I

137

PROTECT SWITCH

19

OVER PRESSURE

36

PROTECT SWITCH AIR CONQ

Ni

LOW

ANNUNCIATOR

It~

20 18

TACHOMETER

40 21

33

RESET SWITCH

CONDENSERBLOWER

AIR COND

CLUTCH

60A

CONDENSER

I

07.5 b+--------130

r

128

1

BLOWER

17

NOSE GEAR

POWER

DOWN LOCK SWITCH

CONDENSER BLOWER RELAY

N1

SPEED SENSOR PCB

LH BLEED AIR BYPASS HOT GAS

VALVE

THERMOSWITCH

HOT GAS BYPASS SOLENOID VALVE

I

30’ POSITION SWITCH

I

I

I

I

I

(FORWARD EVAPORATOR)

(LH BYPASS VALVE)

R Y~ R LOW PRESSURE SHUTOFF SWITCH

AUTO

OFF MNL HEAT O

AUTO

OFF MNL HEAT O

O

O

CLUTCH CONTROL RELAYS

MNL

COOL

COOL

MODE SWITCH

TEMP

LH

RH

BYPASS

BYPASS

VALVE

VALVE FU1B 061252AAAI

Air-Conditioning System Electrical Figure 2

Oct

31/06Page

4

21-50-00

Control Schematic

A21

Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COOLING- TROUBLESHOOTING

(FL-1 THRU FL-492, FL-494 THRU FL-499; FM-1 THRU FM-13) Refer to Charts 101, 102 and 103 and can be used to evaluate the

procedure

AIR-CONDITIONING SYSTEM

Figures 1 and 2 to troubleshoot the air-conditioning system. operational efficiency of the air-conditioning system.

The

following

OPERATIONAL CHECK aft

a.

Place

b.

Start the

c.

Place the cabin temperature mode switch in MAN COOL and hold the manual temperature control switch in DECREASE for 60 seconds.

d.

Take

the e.

accurately

calibrated thermometers in

right engine

and increase the

a

engine

forward and

an

rpm to 62%

N1.

eyeball outlet.

Do not turn the environmental bleed air

on.

cabin air temperature reading near the floor of the cabin. After the temperature of the air-coming out of eyeball outlets has stabilized (5 to 10 minutes), record the temperatures of the air at the outlets. a

Subtract each of the temperature

readings at the eyeball outlets from the cabin air temperature recorded earlier. eyeball outlets should be indicative of a properly operating system.

A differential of at least 20"F at both

Chart 101

Troubleshooting

Condenser Blower Control

Condenser Blower Is STEP 1

Is blower well

Inoperative

grounded (1)?

YES

Proceed to step 2.

YES

Close circuit breaker.

YES

Proceed to step 4.

YES

Proceed to step 3.

YES

Replace N1 speed

YES

Replace

NO

Ground blower STEP2

properly.

IsAIR-CONDITION CLUTCH

circuitbreakeropen?

NO

Is power at coil of condenser blower

relay?

NO Is there PCB to

continuity relay?

in

wiring

from

N1 speed

sensor

NO

Correct lack of STEP 3

Is RH

landing

continuity.

gear down lock switch closed?

sensor

PCB.

NO Correct fault in switch.

STEP 4

Is power at blower motor?

blower.

NO

Replace relay. 1. The cabin

A21

temperature mode switch should be

set to AUTO

or

MAN.

21-50-00

Oct

31/06Page

101

RBytheMI

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 102

Troubleshooting

Cabin

Cooling System

Control

Inadequate Cooling Compressor Operating STEP 1

Are vent blowers

YES

inoperative (1)?

Troubleshoot vent blower and control

(21-20-00). NO Are bubbles present in

sight glass?

YES

Add

YES

Proceed to step 2.

refrigerant.

NO Are blowe r filte rs and evaporator coils clean and free of obstructions?

NO Clean evaporators

or

YES

replace filters.

NO STEP 2

cooling equally?

Are evaporators

YES

Proceed to step 3.

YES

Replace solenoid valve.

YES

Replace

YES

System

YES

Compressor

NO Has the hot gas

bypass

valve failed to

open?

NO Is the TEV

sense

bulb mounted

correctly?

the TEV.

NO Remount the

STEP 3

sense

Is there at least

high and gages?

a

bulb.

130

low pressure

psig differential between readings on the service

the

is

operating

as

designed.

NO Is airflow

across

condenser unobstructed?

is defective

or

there is

a

restriction in the lines. NO Clean condenser

or

clear obstructions.

1.The cabin temperature mode switch should be set to AUTO

or

MAN and ambient temperature should be above

80"F.

Oct

31/06Page

102

21-50-00

A21

Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 103

Troubleshooting

Cabin

Inadequate Cooling STEP 1

Is

Cooling System

Compressor is

below 62%?

N1 speed

not

Control

operating

YES

Increase

YES

Proceed to step 2.

YES

Proceed to step 5.

YES

Adjust

YES

Troubleshoot temperature control

N1 speed.

NO Did unit

cycle

out on low

cycle

out

pressure?

NO Did unit

on

high pressure?

NO Is drive belt loose?

belt tension.

NO Is compressor drive intact?

(21-60-00). NO

Check compressor STEP 2

Is system low

on

Correct fault.

bearings.

YES

refrigerant?

Airplane serials FL-1 thru FL-127 and PM-1 thru FM-8, add R-12. Airplane serials FL-128 and after, FM-9 and after, and prior airplanes with Beech Kit 130-5009 installed add R-134a.

NO Are

bypass

thermoswitches

closing?

YES

Proceed to step 3.

YES

Proceed to step 4.

YES

Replace

YES

Proceed to step 6.

NO

Replace/Adjust STEP 3

Are

bypass

thermoswitches.

valves

opening?

NO

Replace STEP 4

valves.

Is low pressure cutout in

wing

or

in

nose

faulty?

cutout switch.

NO

There is STEP 5

a

restriction in system.

Is condenser blower

operating?

NO Troubleshoot blower and control.

A21

21-50-00

Oct

31/06Page

103

Raytheon

nircraff Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 103

Troubleshooting

Cabin

Cooling System

Inadequate Cooling STEP 6

Control

Compressor is

Is condenser inlet vent obstructed?

not

(Continued)

operating

YES

Clear inlet.

YES

Replace

YES

Replace relay.

NO Is

high

pressure cutout

faulty?

cutout switch.

NO Is power at A122K4

relay?

NO Correct lack of or

continuity thru

low

temp/press switch

mode switch.

1.The cabin temperature mode switch should be set to AUTO to the service valves.

Oct

31/0621-50-00

or

MAN. Service

equipment

should be connected

A21

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COOLING

(FL-I

MAINTENANCE PRACTICES

THRU FL-492, FL-494 THRU FL-499; PM-1 THRU

FM-13)

air-conditioning system consists of periodically checking the refrigerant level, checking compressor oil changing the system air filters. Charge the system whenever the refrigerant level is low, air has entered system or components carrying refrigerant are replaced. Refrigerant leaks may be detected by inspection with

Servicing

the

level and

the a

flameless leak detector.

quality control regulations enacted in the United States, you are not permitted to refrigerant R-12 and R-134a into the atmosphere. When performing maintenance on the air-conditioning system where refrigerant R-12 and R-134a can escape from the system, evacuate the system with a recovery or recycle servicing unit that will salvage the refrigerant.

WARNING: Due to the air vent

The the

air-conditioning system is a high pressure system. Before disconnecting a refrigerant line, must be discharged with a recovery servicing unit. Purge the entire system to a 125-

system

micron level.

PRECA UTIONAR Y MAINTENANCE INSTRUCTIONS

attempting maintenance that requires opening of refrigeration lines or compressor fittings, maintenance personnel should be thoroughly familiar with the pertinent instructions. These instructions should be followed carefully to make sure that the system functions properly. If moisture is allowed to enter refrigerant lines, ice and hydrofluoric acid can form, causing damage to system components. Contamination of the system with dirt can cause damaging wear in the compressor. Before

replacement subassemblies for the air-conditioning system are sealed and dehydrated. They should remain immediately prior to making connections. Refrigerant lines and other components should be at room temperature before uncapping to prevent the moisture condensation from entering the system. If a connection is not made immediately after uncapping a component, it should not remain unsealed for more than 15 minutes. If the time period is longer, reseal the connections. All

sealed until

For airplanes with an R-12 system, compressors are shipped with eight ounces of 525 viscosity refrigerant oil (Item 2, Chart 2, 21-00-00). They are charged with a mixture of R-12 (Item 1, Chart 2, 21-00-00) and dry nitrogen provide an internal pressure that is slightly above atmospheric pressure.

to

airplanes with an R-134a system, compressors are shipped with eight ounces of oil (Item 14, Chart 2, 21-0000). They are charged with a mixture of R-l 34a (Item 13, Chart 2, 21-00-00) and dry nitrogen to provide an internal pressure that is slightly above atmospheric pressure. For

Care should be taken to prevent damage to all fittings and connections. Minute it to leak. Any fittings contaminated with grease or dirt should be cleaned with

damage to a connection could cause a cloth dampened with alcohol (Item 8, Chart 2, 21-00-00). Do not use a chlorinated solvent, such as trichloroethylene, as a cleaning agent because it adds contaminants. If dirt, grease or moisture inside lines cannot be removed, the line must be replaced. Airplanes with an R-12 system use refrigeration oil (Item 2, Chart 2, 21-00-00). Airplanes with an R-134a system use refrigeration oil (Item 14, Chart 2, 21-00-00). Apply a small amount of clean refrigeration oil as previously stated to all line connections and dip O-rings in the oil to help make a leak-resistant connection.

M4

21-50-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

AIR-CONDITIONING SYSTEM MAINTENANCE NOTES air-conditioning system is a high pressure system. Before disconnecting a refrigerant line, the system discharged with a recovery or recycle servicing unit. Purge the entire system to a 125-micron level.

The

a.

be

WARNING: A face shield should be

coming

Do not smoke when

gas when b.

worn

when

in contact with the eyes

exposed

performing

can cause

to

an

on

the lines because

refrigerant

sight.

servicing the system with refrigerant

because it converts into

a

highly toxic

open flame.

connecting aluminum fittings in the system, torque fittings to 11 to 13 foot-pounds.

When

maintenance

loss of

must

all 5/8-inch

fittings

to 18 to 20

foot-pounds

and all

1/2-inch

CAUTION: Insufficient torque can result in loose joints and excessive torque parts. Either condition can result in refrigerant leakage.

Airplane serials

c.

can

result in deformed

connecting

refrigerant R-l 2 (Item 1, Chart 2, 21-00-00). Airplane prior airplanes with Kit 130-5009 installed use refrigerant R-l 34a refrigerants, particularly those containing methyl chloride, will cause

FL-I thru FL-127 and FM-1 thru FM-8,

use

serials FL-128 and after, FM-9 and after, and

I

(Item 13,

Chart 2,

21-00-00).

All other

deterioration of the aluminum components. NOTE: The receiver-drier should be the last component connected. It should be connected last to protection of the air-conditioning system against moisture.

ensure

maximum

REFRIGERANT LEVEL CHECK Refer to

Chapter

1 2-1 0-00 to check the ref rigerant level.

REFRIGERANT LEAK DETECTION system cooling ability or the continual presence of bubbles in the refrigerant system may indicate a refrigerant. The sight glass should be checked during system operation at maximum available ambient and cabin temperatures. The sight glass is located on the receiver-drier in the condenser section in the nose. Streams of bubbles or foam seen in the glass indicate the refrigerant quantity is low. A reduction of

partial

loss of

suspected, the system plumbing should be inspected to determine the source of the leak. by the appearance of oily spots where oil has been carried out by escaping refrigerant. Large Smaller leaks can be detected by a detergent test or by an electronic detector. The system must contain a partial charge in order to detect leaks. The detergent test is accomplished by applying soap to an area suspected of leaking. Bubbles may form if leaks are present. An electronic detector includes a probe that is moved along the plumbing to detect escaping refrigerant. The probe should be held below the line because refrigerant is heavier than air. The probe should be capable of detecting leaks equal to 1/2 ounce per year and will emit a flashing light or a high-pitched sound when escaping refrigerant is detected. If a connection does not seal by the normal torque procedures, the use of soft flare gaskets in the flare fitting is permissible. If

a

loss of

refrigerant

leaks

NOTE: If

a

is

can

be located

leak

occurs

at a flare

fitting containing

a

soft seal,

replacement of the fitting

is recommended.

Copper gaskets should be used in copper and brass fittings and aluminum gaskets should be used fittings. Minor leakage of less than 2 ounces per year is permissible at the compressor shaft seal.

May

1/0821-50-00

in aluminum

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

NOTE: It is

permissible

port

to add 8

ounces

of Trace,

(Item 3,

to detect leaks. A red film will appear in the

Chart 2,

area

21-00-00)

where leaks

a

are

red

dye,

to the low pressure service

present.

DEPRESSURIZING THE AIR-CONDITIONING SYSTEM or recycle service u nit to depressu rite the ref rigerant system. A quaiif led ai r-conditioni ng serviceman operate the service equipment. Refrigerant service ports are located on the left hand side of the nose wheel well and under the floorboards adjacent to the left hand forward partition. Service ports are provided so the air-conditioning system can be serviced without the necessity of working close to the propellers with the engines

Use

is

a

recovery

required

to

running (Ref. Figure 201). a.

b.

Attach the service hoses to the service valves.

Slowly open the high pressure valve to allow a slow escape of the system. If oil accompanies refrigerant is escaping too rapidly. When hissing ceases, close the valve.

the

refrigerant,

the

EVACUATING THE AIR-CONDITIONING SYSTEM The recovery

or

recycle

service unit used for evacuation should be

obtaining an absolute pressure of 125 microns pressure of 125 microns or less. a.

Connect the service unit to the service valves and the

b. c.

or

less and

nose

Start the

wheel well vacuum

a

equipped

pressure gage

depressurize

with

a vacuum

capable

of

pump

indicating

the system. The service valves

capable

an

are

of

absolute

located in

(Ref. Figure 201).

pump,

Crack the ballast valve

gradually opening

on

the

vacuum

the

pump

vacuum

slightly

valve until it is

fully

until the pressure is

open.

approximately 200 microns,

then close

the valve. d.

~a4

The system should be evacuated to 125 microns or less. This than four hours if there are no leaks in the system.

pump-down procedure should require

no more

21-50-00May

1/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ORIGINAL As Received By ATP

PRESSURE RELIEF

VALVE

r! irirul

HIGH "´•li´•

1111.

;fC

LOW PRE SSURE SERVICE VALVE

VIEW.LOOHING UP AT NOSE WHE EL WELL

Servicing Figure 201

Nose Wheel Well

Valves

CLEANING THE AIR-CONDITIONING SYSTEM If it is necessary to clean the system, it can be flushed. Airplane serials FL-1 thru FL-127 and FM-1 thru FM-8, use air-condition flush fluid (Item 4, Chart 2, 21-00-00) and dry nitrogen. Airplane serials FL-128 and after, FM-9 and

I after,

and

prior airplanes

with Kit 130-5009 installed utilize

refrigerant

R-134a

(Item 13,

Chart 2,

21-00-00) and dry

nitrogen. CAUTION: Do not

use

solvent, it will

cause

contamination of the

refrigerant oil.

CHARGING THE AIR-CONDITIONING SYSTEM Refer to

Chapter

12-10-00 for

charging

instruction.

EVAPORATOR FILTERS Two

springs

installed

on

the inlet side of each evaporator

secure

the filters. The

optional

aft evaporator is installed

under the center aisle floorboards in line with the sixth cabin window. The forward evaporator is installed in the hand nose keel section (Ref. Figure 202 and Figure 203).

right

An additional filter is located above the

the aft side of the door that allows recirculation of cabin

air. This filter is located behind the

and

Page

mixing plenum on copilot’s rudder pedals

20421-50-00

no

component removal is required for

access.

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

RETURN AIR INLET FIL TERS To protect the vent blower the

copilot’s

rudder

against restriction by debris, two filters are installed at the return pedals (Ref. Figure 202). Replace the filters as specified in Chapter 5.

air inlet

just forward of

EVAPORATOR REMOVAL, FORWARD a.

Raisethe righthand nosecompartmentdoor.

b.

Connect

c.

Remove all avionics equipment from the right hand

d.

Remove the right hand

e.

Remove the insulation from the evaporator plenum.

f.

Remove the

g.

recycle servicing unit

screws

nose

to the service valve and

compartment floor

which attach the

access

Disconnect the inlet line, outlet line, and or

h.

a

panel

bypass

the system.

compartment.

nose

gain

to

discharge

access

to the

evaporator (Ref. Figure 202).

top of the evaporator plenum and

to the

line from the evaporator

fittings

and

plug

or

remove

the

cover.

cap all open lines

fittings.

Carefully

lift the evaporator coil up and out of the

plenum.

EVAPORATOR INSTALLATION, FORWARD a.

Carefully position

b.

Connect the inlet line, the outlet line and the bypass line to the evaporator

c.

Install the self-adhesive

oven

d.

Install the

on

e.

Reinstall the right hand

f.

Reinstall the avionics equipment in the

g.

Charge

access

the evaporator down into the

panel

the system

as

insulation

the

nose

on

plenum (Ref. Figure 202).

the evaporator

fittings.

plenum.

top of the evaporator plenum assembly with the attaching

screws.

compartment floor.

indicated in

nose

Chapter

compartment.

12-10-00.

EVAPORA TOR REMOVAL, AFT a.

Connect

b.

Removetheaftcabin chairs.

c.

Remove the carpet and floorboards in the center aisle in line with the fifth cabin window.

d.

Remove the insulation from the evaporator plenum.

e.

Remove the

f.

Disconnect the inlet line and outlet line at the

quick-disconnect fittings adjacent

g.

Carefully

plenum.

P~4

a

recycle servicing unit

screws

which

to the service valve and

secure

the

cover

to the

lift the evaporator up and out of the

discharge

the system.

evaporator plenum and

remove

the

to the

cover

(Ref. Figure 203).

evaporator.

21-50-00

Page

yaM502

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

EVAPORA TOR INSTALLA nON, AFT evaporator in the aft evaporator plenum (Ref. Figure 203).

a.

Carefully position

b.

Connect the inlet line and outlet line to the evaporator

c.

Install the

d.

Reinstall the self-adhesive

e.

Install the floorboards, carpet and aft cabin chairs.

f.

Charge

Page

the

cover on

the

the evaporator with the oven

refrigerant system

insulation

as

attaching

screws.

the aft

plenum.

on

indicated in

20621-50-00

fittings.

Chapter

12-10-00.

124

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

3

,ACCESS PANEL

FILTER

A RECIRCULATING a

AIR DOOR

FILTER SPRING

TO COCKPIT

HEATING AND DEFROST EVAPORATOR COIL TO

HEATING

OUTLETS

62

MIXING

CLAMP

PLENUM

TO COOLING OUTLETS

EVAPORATOR

EVAPORATOR

BLOWER

PLENUM o;

B(´•

EVAPORATOR DOORLATCH

Q

B~OWER SPEED

CONTROLLER

SOLENOID

DETAIL

A 8300-427-13

Forward

A24

Evaporator Installation Figure 202

21-50-00

Page

yaM702

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

-::ii-

-a

i;iii

:´•sil:a~.-

:~t iIii

i’´•li~

ilfiii

u

ORIGINAL As Received ATP

Aft

Page

20821-50-00

Evaporator and Blower Figure 203

By

Installation

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COMPRESSOR QUILL SHAFT LUBRICA TION The

quill shaft that provides the drive for the air-conditioning compressor should be

specified

in

Chapter

lubricated at the interval

5.

a.

Remove the compressor belt according to the procedures under COMPRESSOR BELT REMOVAL, being careful to retain the spacer and shim between the belt housing and the drive pulley (Ref. Figure 204).

b.

Remove the drive

c.

pulley, bearings

Clean the end of the the

quill

shaft with

quill

quill shaft.

and a

clean cloth moistened with solvent

(Item 10, Chart 2, 21-00-00)

and

dry

shaft with shop air.

quill shaft

with

d.

Lubricate the compressor end of the

e.

Install the

f.

Install the compressor drive belt, compressor drive COMPRESSOR BELT INSTALLATION procedure.

quill shaft

and

spring

a

thin

even

coat of lubricant

(Item 5,

Chart 2,

21-00-00).

in the compressor mount.

pulley

and drive belt

housing

per the

COMPRESSOR REMOVAL door

the

hand nacelle to

gain

a.

Open the cowling

b.

Slowly discharge

c.

Disconnect the electrical leads from the compressor clutch.

d.

Disconnect the

removing

on

right

the system with the recovery and

to the compressor

recycle servicing

(Ref. Figure 204).

unit until all pressure is bled off.

high pressure (discharge) hose and the low pressure (suction) hose from the compressor by the metric bolt securing the retaining plate and adapters to the compressor. DISCARD the O-rings.

Cut the

the aft

pivot bolt,

then loosen both

e.

safety attaching bolt.

f.

Remove the bolt

g.

Remove the drive belt from the compressor.

h.

access

wire

on

attaching

the tension

the tension

adjuster lock

nuts and lower

the compressor.

pivot bolt and nut. Note the number of compressor aligning shims aligning the compressor pulley with the drive pulley when installing the

the forward

Remove the aft

pivot bolt and

their

locations to aid in

respective

adjuster to

pivot bolts,

and

compressor i.

If the compressor is to be

replaced,

remove

the

mounting plate

and tension

adjuster plate.

These

plates

are

attached with metric bolts.

nz,

21-50-00

Page

yaM902

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COMPRESSOR INSTALLA nON CAUTION: Bolts

screwing into bosses damage the threads.

If not installed, install the

a.

pounds b.

and

safety

on

the compressor are metric. Do not attempt

mounting plate

and tension

using inch

bolts

adjuster plate with metric bolts. Tighten

as

to 60

this would

86 inch-

wire.

Install the compressor on the compressor mount with the compressor pulley aligning shims installed in locations from which they were removed in step h of the COMPRESSOR REMOVAL procedure. Install the forward and aft

pivot

bolts but do not

Install the drive belt

c.

on

until the belt has been installed

tighten

(Ref. Figure

204 and

Figure 205).

the compressor.

NOTE: If the compressor clutch pulley is not parallel with the drive pulley, loosen the pivot mount attaching bolts slightly and align the pulleys by turning the slider adjusting bolt. When alignment is obtained, tighten the

pivot d.

mount

attaching

bolts.

Attach the belt tension

adjuster to the compressor and adjust as instructed under COMPRESSOR BELT TENSION ADJUSTMENT. Tighten the attaching bolt from 60 to 85

e.

The compressor

f.

Connect the

pivot

bolt should be

tightened

from 95 to 110

inch-pounds. Safety

inch-pounds.

wire the aft

pivot

bolts.

pressure (discharge) hose and the low pressure (suction) hose and adapters to the Use new O-rings between the retaining plate, the adapters and the compressor. Tighten the metric compressor. bolt from 60 to 86 inch-pounds and safety wire.

NOTE: Make

fitting.

high

sure

For

130-5022

that the high pressure (discharge) and low pressure (suction) hoses are connected to the proper airplanes FL-217 and after; FM-10 and after and prior airplanes with Kit No. 130-5009 or installed, refer to Figure 205 for placard labeling the fittings at the firewall.

g.

Connect the electrical leads to the compressor clutch.

h.

Evacuate the system, then

i.

Close the

May

1/08Page

210

charge

right inboard cowling

the system refer to

Chapter

12-10-00.

door.

21-50-00

nz4

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

GEAR BOX HOUSING

00 SURFACES OF THE MOUNT SUPPORT MUST BE LEVEL WITHIN 0.002 INCH WITH THE SURFACE ON THE GEAR BOX MOUNT PAD

~3-

DRIVE BELT HOUSING

SEAL

j SHIM

COMPRESSOR

C

000

.sg

y?ln:i*IOR MOUNT

-i

i ‘b,

SPRING QUILL

PLATEMOUNT,

SLIDERPIVOT MOUNT SUPPORT

~x

~"rC

e´•-

B

‘‘I SPACER

SHIM

i.

PIVOT’i MOUNT

SHIM

B

SLIDER ADJUSTING BOLT

SHIM

RETAINING RING

TURNBUCKLE (BELT ADJUSTER)

DRIVE BELT HOUSING

--RETAINING

RING

SPACER

BE~RINGii

SHIMS GAP .010 t. 002 INCH GAP ALLOWED AFTER SHIMMING

DETAIL

DETAIL

A

B FL21FI 003557AA

Air-Conditioning Compressor Figure 204

A24

Installation

21-50-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COMPRESSOR

HIGH PRESSURE HOSE

i

i,,,,,:,,,

pa

i

HOSE

rY 101-555215-1

VIEW

VIEW

A

B

LOOKING AFT

Placard Location at Firewall

Figure

Page

21221-50-00

205

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COMPRESSOR MOUNT REMOVAL a.

Remove the compressor belt per COMPRESSOR BELT REMOVAL procedure.

b.

Remove the compressor per COMPRESSOR REMOVAL

c.

Cut the

safety wire and remove (Ref. Figure 204).

the

seven

bolts

securing

procedure.

the compressor mount to the

engine gearbox housing

and support d.

Remove the compressor mount and quill shaft. Exercise care not to lose the spring at the end of the the two seals between the compressor mount and the engine gearbox housing.

quill

shaft

or

COMPRESSOR MOUNT INSTALLA TION a.

Install the mount support per COMPRESSOR MOUNT SUPPORT INSTALLATION

b.

Install the

quill

CAUTION: Make

shaft in the compressor mount sure

that the mount seals,

mount. If the

existing

NOTE: The quill shaft and

seals

spring

c.

Install the compressor mount. the lower bolt in place.

d.

Install the compressor tighten the pivot bolts.

e.

Install the compressor drive

on

can

procedure

(Ref. Figure 204).

quill shaft, and quill shaft spring are damaged, install new seals.

in

place prior to installation

of the

are worn or

be installed after the compressor mount is installed.

Tighten

the compressor mount bolts to 40 to 50

inch-pounds. Safety

the compressor mount per the COMPRESSOR INSTALLATION

pulley,

if removed.

belts and drive belt

housing

wire all but

procedure

but do not

per the COMPRESSOR BELT INSTALLATION

procedure.

COMPRESSOR MOUNT SUPPORT REMOVAL a.

Remove the compressor mount per COMPRESSOR MOUNT REMOVAL

b.

Remove the two

c.

Note the number of shims at each location and retain for reinstallation at the

d.

Install the two nuts

engine gearbox housing

on

the studs

they

nuts

were

securing

the support to the

procedure.

gearbox housing (Ref. Figure 204). same

location.

removed from.

COMPRESSOR MOUNT SUPPOR T INSTALLA nON (Ref. Figure 204).

a.

Remove the two nuts at the location the support will be installed

b.

Install the support with the shims removed in step c. of the COMPRESSOR MOUNT SUPPORT REMOVAL procedure. The shims should level the mounting surfaces of the support to within 0.002 inch of the compressor mount pad on the gearbox housing.

c.

Install the

gearbox housing

nuts and

tighten between

20 and 30 inch-bounds.

21-50-00

Page

yaM312

1/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COMPRESSOR EEL T REMO VAL

I

a.

Open

b.

Remove the

c.

Release the tension

d.

Remove the drive belt from the compressor and the drive

the inboard

cowling

attaching

door

screws

on

on

the

right

hand nacelle to

and the drive belt

the tension

adjuster.

gain

to the compressor

access

from the compressor mount

housing

Remove the

attaching parts

and

one

(Ref. Figure 204).

assembly.

end of the tension

adjuster.

pulley.

COMPRESSOR EEL T INSTALLA TION a.

b.

Install the drive belt Prior to

installing

they

NOTE: Before a

are

not

Bearings installing

brush. Make

the drive belt

are

d.

I

e.

and drive

housing

pulley (Ref. Figure 204).

pulley, measure the shims to provide a clearance of no more bearing (Ref. Figure 204, Detail B). The shims may be reused

press fit to the

pulley

shaft.

pulley, apply a coat of lubricant (Item 5, Chart 2, 21-00-00) to the quill shaft splines with quill shaft and spring (prior to FL-244) or O-ring and washer (FL-244 and after) are properly pulley engages the quill shaft properly.

the

attaching

pulley

and drive belt

bolts to 25 to 30

Install the tension as

the drive

the drive

sure

Install the drive the

on

damaged.

installed and the drive c.

the compressor and

0.002 inch between the spacer and

than 0.010

if

on

adjuster and

housing on the compressor mount inch-pounds and safety wire bolts. secure

with the

and

attaching parts. Adjust the

secure

tension

it with three bolts.

adjuster to the

Torque

correct tension

noted under COMPRESSOR BELT TENSION.

Charge

the system and close the

cowling

door

on

the

right

hand nacelle.

COMPRESSOR EEL T TENSION The tension of the compressor belt should be checked after 50 hours of operation. A 4.5- to 6-pound force applied at the midspan of the belt should deflect the belt approximately 0.13 inch. Adjust the belt tension as follows: bolts and the tension

a.

Loosen the

b.

Loosen the locknut at each end of the tension

pivot

adjuster

lower attachment bolt

adjuster

(Ref. Figure 204).

barrel and turn the barrel to

lengthen

or

shorten the

adjuster. c.

When correct tension is obtained,

safety d.

tighten

the

adjuster

lower attachment bolt from 60 to 85

inch-pounds

and

wire the bolt head.

Tighten

pivot bolts and the barrel locknuts. Safety wire the

the

locknuts to the

adjuster barrel.

CONDENSER REMOVAL

I

a.

Using

b.

Remove the

c.

Remove all avionics

Page

the recovery and

right

recycle servicing unit, discharge

hand louvered

equipment

access

panel

and the

the

right

system slowly until all pressure is bled off.

hand avionics compartment door from the

and the avionics shelf from the

21-50-00

nose

compartment.

airplane.

Hawker Beechcraff

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

d.

e.

Remove the

g.

panel from the top side of the airplane nose and disconnect plug all open lines and fittings (Ref. Figure 206).

receiver-dryer. Cap

or

Remove the

which attach the forward avionics

the f.

access

screws

the

compartment bulkhead panel

plumbing

lines from the

to the bulkhead and remove

panel.

Remove the inlet line and the outlet line from the condenser Remove the

screws

which attach the condenser in

position

fittings

and

and cap

remove

or

plug

all lines and

the condenser from the

fittings. nose

compartment.

CONDENSER INSTALLATION compartment location and

a.

Position condenser in its

b.

Connect the inlet line and the outlet line to the condenser.

c.

Install the forward bulkhead

d.

Connect the

e.

Install the

f.

Reinstall the avionics shelf and all avionics

g.

Install the louvered

h.

Charge

plumbing

access

nose

panel

to the

panel

on

access

the top of the

panel

the ref rigerant system

as

and the

it with the

attaching

screws

compartment bulkhead with the attaching

nose

to the receiver-drier

secure

by

access

through

the

opening

in the

(Ref. Figure 206).

screws.

top of the airplane

nose.

nose.

equipment

nose

compartment door

nose

indicated in

in the

Chapter

compartment. on

the

right

hand side of the

nose.

t 2-1 0-00.

CONDENSER BLOWER REMOVAL the system

a.

Discharge

b.

Remove the louvered

airplane

slowly using access

the recovery and

panel from

recycle

the left hand side and the

right hand

and open the left hand

d.

Working through the opening in the top left hand of the and cap or plug all lines and fittings (Ref. Figure 206).

e.

Remove all avionics and the avionics shelf from the

f.

Remove the

h.

the left hand top side of the

compartment doors.

Remove the

g.

panel from

nose.

c.

remove

service unit until ail pressure is bled off.

the

screws

which attach the forward

nose

nose

nose, disconnect the

nose

plumbing

from the receiver-drier

compartment.

compartment bulkhead panel

to the forward bulkhead and

panel.

Remove the electrical leads from the terminals Remove the four bolts which

secure

the blower

on

the blower.

assembly

to the

mounting

bracket and

remove

the blower

assembly.

A24

21-50-00

Page

215Mayl/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CONDENSER BLOWER INSTALLA TION a.

Position the blower

assembly

on

the

bracket and

mounting

secure

with the four

attaching

bolts

(Ref. Figure 206). b.

Connect the electrical leads to the terminals

c.

Install the forward

d.

Connect the

e.

nose

plumbing

Install the louvered side of the

g.

Install the

h.

Charge

the blower.

compartment bulkhead panel

on

the bulkhead with the

attaching

screws.

to the receiver-drier.

access

panel

on

the left hand side of the

nose

and the

access

panel

on

the top left hand

nose.

Install the avionics

I

on

right

the

in the

equipment and shelf

hand and close the left hand

refrigerant system

as

nose

nose

compartment.

compartment doors.

Chapter

indicated in

12-10-00.

RECEIVER-DRIER REI~IIOVAL a.

b.

Using

the recovery and

Remove the

Loosen the

unit

discharge

the

air-conditioning system slowly until all pressure is bled off.

panel on the top of the airplane nose and disconnect Cap or plug all lines and fittings (Ref. Figure 206).

access

the receiver-drier. c.

recycle

clamps securing

the receiver-drier to its

mounting

the inlet line and the outlet line from

bracket and

remove

the receiver-drier.

RECEIVER-DRIER INSTALLATION a.

Install the receiver-drier and

through

the

opening

on

tighten

the

top of airplane

clamps securing

it to the

nose.

b.

Connect the inlet line and the outlet line to the receiver-drier.

c.

Install the

d.

Charge

Page

access

the

panel

on

the top of the

refrigerant system

as

airplane

indicated in

21-50-00

nose.

Chapter

12-10-00.

mounting

bracket

(Ref. Figure 206).

Access

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ORIGINAL Rs Received

;j

BECES’dEF~

By

i

BRYER 1’1 ii;i

I´•

CONDENSt2R

~NsEn.

Condenser and Blower Installation

Figure

A24

206

21-50-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

RESET OF OVERPRESSURE OR UNDERPRESSURE INDICATION SYSTEM a.

Remove center floorboard forward of the spar to

b.

Place master switch to the ON

c.

Make

d.

Place the mode select switch in MAN COOL

e.

Reset switch

f.

Place master switch to the OFF

g.

Install center floorboard forward of the spar.

sure

which

(S1)

light

on

tripped

latch circuit for

is

May

on

position.

Hold the INCR/DECR switch to DECR for 60 seconds.

Vane/N1 speed

PCB.

position.

nose

wheel well

on

the left side

of the open circuit but does allow for the system to reset with this switch.

indication for the

required

to A130 PCB.

troubleshooting.

the left top of the Al 30 Ice

NOTE: An alternate reset button is located in the no

access

position.

indicates

located

gain

cause

21-50-00

panel. resetting PCB

This

indicating

switch

gives

for either indication. Power

nn4

Raytheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COOLING

TROUBLESHOOTING

(FL-493, FL-500

AND

AFTER; FM-14 AND AFTER)

Refer to Chart 101 to troubleshoot the

low, air has entered the system

or

air-conditioning system. Charge the system components carrying refrigerant are replaced.

whenever the

refrigerant

level is

quality control regulations enacted in the United States, you are not permitted to vent refrigerant R-134a into the atmosphere. When performing maintenance on the air-conditioning system where refrigerant R-134a can escape from the system, evacuate the system with a recovery/recycle service unit that will recover the refrigerant.

WARNING: Due to the air

The air-conditioning system is a high pressure system. Before disconnecting a refrigerant line, the system must be discharged with a recovery/recycle service unit. Evacuate the entire

system for 15 minutes.

REFRIGERATION SYSTEM A vapor

cycle refrigeration system

is

dynamic

in nature. It is difficult to

give

exact

temperature drops

or

suction

pressures and discharge pressures for troubleshooting purposes without knowing ail the variables. It is recommended that the maintenance personnel read and become familiar with this section before attempting to troubleshoot the air should

help

the

conditioning system. below troubleshooting precess.

are

examples

of the

dynamic

nature of the

refrigeration system

that

MEASURING TEMPERATURE DROP ACROSS THE EVAPORATOR to associate a specific temperature drop across the evaporator is dependent on many factors such as inlet air temperature, moisture content (relative humidity) and airflow. On a day with extreme humidity, up to 70% of the evaporator capacity will go towards dehumidification (Latent Heat). That only leaves 30% available to actually lower

Trying

the air temperature (Sensible Heat). A mechanic encountering this scenario may assume that because he can only measure a 10" F (5.6" C) drop in temperature that the system is not operating properly. This assumption is incorrect

because he is not

considering

the amount of work it takes to condense moisture in the air and convert it to water

that pours out of the condensate drain. To further complicate the issue, if you eliminate the source of this humidity by closing the cabin door, your initial temperatu re readings will have a smaller tempe rature drop than measurements taken later. This is because you sensible heat.

are

drying

out the air in the cabin and the

evaporator is allowed

to remove

more

MEASURING SUCTION AND DISCHARGE PRESSURE diagnosing the system is to start with checking the pressures. However, you must remember that these pressures are affected by many different conditions such as outside air temperature, cabin temperature, cabin humidity and charge level. It is impossible to give an accurate head pressure at a specific temperature without knowing these other factors. These pressures can even vary during the troubleshooting

The most accurate method to start

process, as the system continues to run, you are removing heat from the cabin and This lowered heat load will result in lower suction and discharge pressures.

lowering

the cabin temperature.

SYSTEM DIAGNOSIS It is

important

to understand the basic

the system. The

following

is

a

principles

of vapor

cycle air-conditioning

before

attempting

to troubleshoot

brief overview.

COMPRESSOR

compressor’s only function is to raise the pressure of the refrigerant to a point where it can be condensed to liquid at ambient temperature. The compressor creates heat in the process of compression and produces superheated high-pressure vapor.

The

21-51-00

a

a

101

Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/8300C MAINTENANCE MANUAL

CONDENSER The condenser function is to

begin

to condense into a

remove

the heat from the

liquid. Condensing

occurs

superheated

in accordance to

vapor. As the heat is removed, the vapor will temperature i pressure ratio. (i.e. The higher

a

the condenser air inlet temperature is, the greater the pressure required to condense, while the lower the condenser air inlet temperature is, the lower the pressure is required for condensing. This is why on a hot day there will be higher discharge pressure than on a cool day.)

RECEIVER/DRVER

receiver/dryer is a reservoir for liquid refrigerant. It also contains a filter screen and a desiccant material to particles and moisture from the refrigerant. It ensures that a filtered and dried column of liquid refrigerant is to the expansion valve.

The

remove

sent

EXPANSION VALVE

expansion valve is a device that meters liquid refrigerant into the inlet of the evaporator where it will be evaporated. It has an orifice with a metering pin to vary the flow of refrigerant. This pin is attached to a diaphragm that balances suction and spring pressure on one side and capillary sense bulb pressure on the other, which moves

The

pin

the

in and out of the orifice.

capillary sensing bulb contains a charge of refrigerant that is permanently sealed. This charge exerts pressure diaphragm to move the metering pin. Pressure is generated from the expansion or contraction of the gas charge contained in the bulb as it is warmed or cooled.

The on

the

refrigerant exits the evaporator. refrigerant flowing through the evaporator the

This bulb attaches to the suction line where the line. If there is insufficient

It

measures

the temperature of this

gas will be warmer than desired the gas within and exerting pressure on

(superheated). This in turn will warm the sense bulb, therefore expanding diaphragm. The diaphragm will then move the metering pin and increase the flow of refrigerant to the evaporator. With the increased flow of refrigerant, the gas temperature exiting the evaporator will be reduced, therefore cooling

the

the

sense

diaphragm

bulb, which lowers the pressure within and reduces the pressure exerted on the diaphragm. The will then move the metering pin to reduce the refrigerant flow. The valve will make adjustments until a

balance has been reached. One of the most attachment of the suction tube

sense

problems associated with expansion valves is a bad along its entire length and be securely attached to the metallic be thoroughly insulated with foam tape to ensure that outside air

common

bulb. It must make contact

exiting the evaporator reading.

case.

It must

does not affect its

TROUBLESHOOTING This section blowers

or

applies

to

the refrigeration circuit only. It will not cover the obvious, such (Ref. Chart 101,Troubleshooting Air-Conditioning System).

troubleshooting

bumed out drive motors

as

failed

the air-conditioning system is reported as not functioning properly. The report from the pilot may "poor cooling". From this report the mechanic must decide where to start the investigation. If the outside air temperature (OAT) is below 70" F it is much more difficult to troubleshoot because of the lack of heat load. Lets

assume

reference

STEP ONE the system and allow it to stabilize for ten minutes. Observe suction and discharge pressures and temperatures across evaporator(s). If the evaporator does not have an adequate temperature drop or you suspect a loss of refrigerant charge, stop the system and evacuate and recharge to the

Install gage set to the service ports. Turn

prescribed weight

of

refrigerant

on

system charged to the required weight you system as being the cause of the problem.

Oct

air-conditioning refrigerant capacity is 56 ounces of R-134a. With the have now eliminated the possibility of an overcharged or undercharged

R-134a. The

21-51-00

~1

Raytheon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

STEP TWO on and allow it to stabilize for ten minutes. Check the suction and discharge pressure. A normal for the suction side should be between 25 psi (172.4 KPa) and 40 psi (275.8 KPa). The normal reading pressure discharge pressure should be between 150 psi (1034.2 KPa) and 300 psi (2068.4 KPa).

Turn the system

NOTE: The suction pressure and Lets

assume

discharge pressure is dependant

the condenser blower and evaporator blowers metering the

components that are involved in compressing and pressures will indicate the nature of the problem.

on

OAT and evaporator heat load.

functioning properly. This leaves only those refrigerant as suspect. The suction and discharge

are

expansion valve is the brain of the system. It controls how much liquid refrigerant is released evaporation coil. When this component fails, it is important to understand the different ways it can fail

The

into the and the

associated symptoms. valve is stuck in mid range: This is

expansion

The

evaporator will have

refrigerant The

flow at

a

high

expansion valve

usually

associated with

a

contaminated system. The

poor temperature drop at extreme operating parameters and therefore there is heat loads and excessive refrigerant flow at low heat loads (coil flooding).

inadequate

is stuck wide open: This will cause excessive ref rigerant to flow into the evaporator coil. The liquid refrigerant. The result will be poor temperature drop because the refrigerant is

coil will become "Flooded" with

evaporating into a vapor. Because the expansion valve is wide open, the suction pressure will be higher than normal and the return line will be very cold because the liquid refrigerant is evaporating in the line instead of the evaporator. The discharge pressure will be lower than normal because there is very little pressure drop across an not

open

expansion

valve. There may also be bubbles in the

sight glass

under this condition.

expansion valve is stuck closed: This will result in minimal refrigerant flow in to the evaporator. The coil is being starved for refrigerant. The result will be poor temperature drop because there is a lack of refrigerant available to evaporate. The suction line exiting the evaporator will be warmer than normal. The suction and discharge pressures in this scenario will not look much different from normal. The biggest clue will be a very warm suction line The

at the compressor.

21-51-00Page

103

Raldtteett

nircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 101

Troubleshooting Air-Conditioning System Service

egaGerReading userP

Condition

Refrigerant

Insufficient

Charge: Insufficient

cooling, sight glass (Ref. Note).

bubbles appear in

Suction pressure: below normal.

Discharge pressure:

Corrective Action

Probable Cause

below

Leak test.

Refrigerant leaking.

is low

or

Repair leak. Charge system. Evacuate and

normal.

as

necessary

recharge system.

Stop compressor immediately. Leak test. Almost No

Refrigerant:

Suction pressure: much below normal.

No cooling action. A lot of bubbles or a mist appears in sight glass (Ref. Note).

Serious

refrigerant leak.

pressure: much below normal.

Discharge

Discharge system. Repair leak(s). Replace receiver dryer,

if

necessary. Check system oil level. Evacuate and

recharge

system. Check low pressure switch circuit. Air In

System:

Insufficient cooling. Sight glass shows occasional bubbles

(Ref. Note). Moisture In

vacuum

pressure reading. During this condition, discharge air will be

Discha rge pressure: above

Airmixedwith

refrigerantin

system.

system.

normal.

warm.

As

Discharge system. Dryer

is saturated with

Replace receiver dryer (twice if necessary).

Suction pressure: below normal.

moisture.

Moisture has frozen at

Evacuate system

Discharge pressure: above

expansion valve. Refrigerant flow is

completely. (Repeat

restricted,

times.) Recharge system.

normal.

of this,

reading shows approximately 6-psi

warning

Discharge system. Replace receiver dryer. Evacuate and charge

System:

After operation for a while, pressure on suction side

may show

Suction pressure: above normal.

minute

evacuating

30

three

oscillation.

Faulty Expansion

Valve:

Suction pressure: below normal.

Slight cooling. Sweating

or

expansion

frosted

valve outlet,

Discharge pressure: normal.

below

Expansion valve refrigerant. Expansion valve clogged.

restricts

is

Replace expansion

valve.

Valve is stuck closed. Thermal bulb has lost

charge.

Oct

21-51-00

nnl

Ray~heon

Aircraft Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 101

Troubleshooting Air-Conditioning System (Continued) Condition

Faulty Expansion Insufficient

Valve:

cooling.

Sweated suction line.

Faulty Expansion

Valve:

Service Pressure

Suction pressure: above normal

Discharge pressure: above normal

Corrective Action

Probable Cause

Gage Reading

Check valve for

evaporator,

show a pressure decrease, replace valve.

Sensing

bulb

suction

on

line not well insulated

properly

or

attached to line.

Suction pressure: above normal.

No

cooling. Sweating orfrosted suction

Discharge

line,

normal,

operation.

Expansionvalve allowstoo much refrigerant through

Faulty expansion

valve.

pressure: below

If suction side does not

Check

security and on sensing

insulation

bulb.

Discharge system. Replace valve. Evacuate and recharge system. Check condenser for dirt

accumulation.

Faulty Condenser: Insufficient

cooling.

Suction line is very hot.

High Pressure

Line

Blocked:

Insufficient Frosted

cooling. high-pressure

liquid line.

Suction pressure: above normal.

Check for

restricted.

refrigerant overcharge. If pressure remains high in spite of all above actions taken, remove and inspect condenser for possible oil clogging.

Dryer clogged, or restriction in high-pressure

Discharge system. Replace receiver dryer. Evacuate and charge

Condenser air

refrigerant Discharge pressure: above

or

flow is

normal.

Suction pressure: much below normal.

Discharge pressure: much above normal.

line.

system.

Discharge system. Remove and check

Faulty Compressor: Insufficient

cooling.

Suction pressure: much below normal.

Discharge pressure: much below normal.

compressor. Internal

problem

in

compressor, or damaged gasket and valve.

Repair or replace compressor. Check oil level.

Replace

dryer. charge

receiver

Evacuate and

system. Too Much Oil In Insufficient

System:

cooling.

Suction pressure: above normal.

Discharge

Too much oil circulates

pressure: above

normal

The

nz~

Sight glass

is located

on

the

receiver/dryer,

refrigerant, causing cooling capacity of the

with the

system to be reduced.

Check oil level

(Ref. CompressorOil Level Check).

ETON.eson

in the condenser section in the

I

airplane

21-51-00

Oct

31/06Page

105

Raytheon

Aircraft

Company

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

This

Oct

31/06Page

106

21151100

Page Intentionally Left Blank

A21

Aircraft Company SUPER I
FIREWALL SHUTOFF VALVE AMBIENT

BLEED AIR SHUTOFF VALVE

AMBIENT AIR INLET

TEMP

ENGINE

AMBIENT AIR

SENSOR

FLOW CONTROL VALVE

BLEED AIR

COOLED AIR

ENGINE

(FIREWALL)

ELECTRIC HEATER ASSEMBLY

REFRIGERANT

Alft INLET SCOOP _

WHI

HIGH i LOW

NVD EVAPORATOR ASSY AND COCKPIT BLOWER

ELECTRIC HEAT OUTLET R.H.C.B. PANEL

i

ELECTRIC HEATED AIR

j

(WHEN

ON

GROUND)

HEAT U(CHANGER

COMPRESSOR

FWD PLENUM AND SERVO

)‘7_=

(BLEED)

HEATED Alft

BLEED AIR

BYPASS VALVE

´•raj´•w

CABIN COOL AIR

PRESSURE SWITCH

OUTLETS

THERMAL SWITCH

REFRIGERANT LINES

t

[I1P

I CHECKVALVE

MIXING

LIMIT CONTROLLERS FLAPPER

VENTURI

R.t-f. SUBPANEL

(8 PLACES)

PRESSURE SOLENOID VALVE

i

1I1I

X

(4~ DRAW VALVES

VALVES OUTFLOW VALVE

/i

PLENUM

CONDENSER BLOWER

I_IUL~I

1

OVERBOARD DUCTS

INLET AIR TEFnP BULB

FWD

EXPANSION VALVE

CONDENSER

RECEIVER DRYER WITH SIGHT GLASS

I

SAFETY VALVE

OUTLETAIR REFRIGERANT SERVICE

CIRCUIT

VALVES

CARD BOX

I

TEMP CONTROLLER ---I

GLARESWIELD DUCTS COCKPIT COOL

Dc POWER

I

AFT EVAPORATORS

AFT COMPARTMENT

DISTRIBUTION

I

(AND CABIN BLOWERS)

COOL AIR OUTLET

PANEL

CABIN SIDEWALL HEAT OUTLETS AFT COMPARTMENT

(8 PLACES)

AIR INLET SCOOP

HEAT OUTLETS

AIR OUTLETS ENGINE BLEED

PRESSURIZATION

--~2-

AIR DUCT

I

GONTROLLER

BLEED AIR BYPASS VALVE ASSYAND 30" POSITION SWITCH

II

I!Q

;~I

I I

FLOW CONTROL VALVE

l‘c- HEAT EXCHANGER

FIREWAFL

ORIGINAL As Received

ENGINE BLEED AIR

By

ATP AMBIENT AIR INLET

BLEED AIR SHUTOFF VALVE

sazte 3314i9MAI

FIREWALL SHUTOFF VALVE

System Schematic Figure 101

Environmental

821

21-51-00

Oct

3106Page

f 07

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COOLING

MAINTENANCE PRACTICES

(FL-493,

FL-500 AND AFTER; FM-14 AND

AFTER)

Servicing the air-conditioning system consists of periodically checking the refrigerant level, checking compressor oil level. Charge the system whenever the refrigerant level is low, air has entered the system or components carrying refrigerant are replaced. Refrigerant leaks may be detected by inspection with a flameless leak detector, or with an ultraviolet blue lamp, if a fluorescent leak-detection dye has been used in the system. quality control regulations enacted in the United States, you are not permitted to refrigerant R-134a into the atmosphere. When performing maintenance on the air-conditioning system where refrigerant R-134a can escape from the system, evacuate the system with a recovery/recycle service unit that will recover the refrigerant.

WARNING: Due to the air vent

The

air-conditioning system

is

a

high pressure system. Before disconnecting a refrigerant line, a recovery/recycle service unit. Evacuate the entire

the system must be discharged with system for 15 minutes.

PRECAUTIONARY SERVICE PROCEDURES Before attempting maintenance that requires opening of refrigeration lines or compressor fittings, maintenance personnel should be thoroughly familiar with the pertinent instructions. These instructions should be followed carefully to insure that the system functions properly. If moisture is allowed to enter refrigerant lines, ice and hydrofluoric acid can form, causing damage to system components. Contamination of the system with dirt can cause damaging wear in the compressor.

replacement subassemblies for the air-conditioning system are sealed and dehydrated. They should remain immediately prior to making connections. Refrigerant lines and other components should be at room temperature before uncapping to prevent the moisture condensation from entering the system. If a connection is not All

sealed until

made

immediately

after

uncapping

a

component, reseal the component.

airplanes with an R-134a system, compressors are shipped with eight ounces of oil (Item 14, Chart 2, 21-0000). They are charged with a mixture of R-134a (Item 13, Chart 2, 21-00-00) and dry nitrogen to provide an internal pressure that is slightly above atmospheric pressure. For

damage to a connection could cause a cloth dampened with alcohol (Item 8, Chart 2, 21-00-00). Do not use a chlorinated solvent, such as trichloroethylene, as a cleaning agent because it adds contaminants. If dirt, grease or moisture inside lines cannot be removed, the line must be replaced. Airplanes with an R-l 34a system use refrigeration oil (Item 14, Chart 2, 21-00-00). Apply a small amount of clean refrigeration oil as previously stated to all line connections and dip O-rings in the oil to help make a leak-resistant connection. Care should be taken to prevent damage to all fittings and connections. Minute it to leak. Any fittings contaminated with grease or dirt should be cleaned with

AIR-CONDITIONING SYSTEM MAINTENANCE NOTES a.

air-conditioning system is a high pressure system. Before disconnecting a refrigerant line, the system discharged with a recovery/recycle service unit. Evacuate the entire system for 15 minutes.

The

be

WARNING: A face shield should be

coming in

b.

when

exposed

the lines because

servicing the system with refrigerant because

connecting fittings in the system, lubricate new O-rings mating surface and tighten fittings to the following torque:

5/8-inch

on

refrigerant

fittings torque

10

it converts into

a

highly toxic

to an open flame.

When to

performing maintenance sight.

contact with the eyes can cause loss of

Do not smoke when

gas when

worn

must

15

with oil

(Item 14,

Chart 2,

21-00-00), apply

sealant

foot-pounds

21-51-00

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Corporation

Hawker Beechcraft

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

3/4-inch

fittings

torque 15

20

foot-pounds

7/8-inch

fittings

torque 20

30

foot-pounds

1 1/16-inch

fittings

torque 25

35

foot-pounds

CAUTION: Insufficient torque can result in loose joints and excessive torque parts. Either condition can result in refrigerant leakage. NOTE: The

receiver/dryer

contains desiccant

bags

that

remove

can

result in deformed

moisture from the

should be the last component connected. It should be connected last to air-conditioning system against moisture.

refrigerant.

ensure

connecting

receiver/dryer protection of the

The

maximum

REFRIGERANT LEVEL CHECK Refer to

Chapter

12-10-00 to check the

refrigerant

level.

REFRIGERANT LEAK DETECTION system cooling ability, the continual presence of bubbles in the refrigerant may indicate a partial loss of refrigerant. The sight glass should be checked during system operation at maximum available ambient and cabin A reduction of

temperatures. The sight glass is located bubbles

If

or

loss of

a

foam

in the

seen

refrigerant

is

glass

on

indicate the

suspected,

receiver/dryer in refrigerant quantity

the

the system

plumbing

should be

inspected

to determine the

The system must contain a partial charge in order to detect leaks. Large leaks can be located oily spots where oil has been carried out of the system by escaping refrigerant. Smaller leaks

detergent The

test

detergent

or

by

an

test is

nose.

Streams of

source

of the leak.

the condenser section in the is low.

the appearance of can be detected by a

by

electronic detector.

accomplished by applying

bubbles form and grow, leaks

are

soapy water to

an area

suspected of leaking

with

a

small brush. If

present.

probe that is moved along the plumbing at a maximum distance of about 1/8’" of along the bottom of the lines and fittings may aid in detecting leaks, since the is heavier than the air. The test should be conducted with no ambient airflow around the lines and fittings refrigerant to disrupt the detection of refrigerant. The probe should be capable of detecting leaks as small as 1/2 ounce per year. The detector should give an audible or visual alarm when escaping refrigerant is detected. An electronic detector includes an

a

inch. Small circular motions

DISCHARGING THE AIR-CONDITIONING SYSTEM quality control regulations enacted in the United States, you are not permitted to refrigerant R-134a into the atmosphere. When performing maintenance on the air-conditioning system where refrigerant R-134a can escape from the system, evacuate the system with a recovery/recycle service unit that will recover the refrigerant.

WARNING: Due to the air vent

The

air-conditioning system is

a

high

the system must be discharged with system for 15 minutes. Use

Page

only

R-134a

pressure system. Before disconnecting a refrigerant line, recovery/recycle service unit. Evacuate the entire

a

compatible recovery/recycle

20221-51-00

service unit.

n24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

recovery/recycle service unit to depressurize the refrigerant system. A qualified air-conditioning serviceman required to operate the service equipment. Refrigerant service ports are located on the left side of the nose wheel well under the floorboards adjacent to the left forward partition. Service ports are provided so the air-conditioning system can be serviced without the necessity of working close to the propellers with the engines running (Ref. Figure 201). Use

a

is

Connect the

a.

b.

If

recovery/recycle

possible, operate the

air

service unit to the service valves

conditioning system

on

the

airplane (Ref. Figure 201).

for five minutes. This will collect

as

much oil

as

possible

in the

compressor. and take note of oil level

c.

Turn off the air

d.

Discharge

e.

Note the amount of compressor oil removed from the system be added back to the system during charging.

f.

Disconnect and

conditioning system

the air

conditioning system

remove

the

on

in accordance with the

recovery/recycle

the

refrigerant recovery/recycle

recovery/recycle

service unit’s instructions.

during discharging.

service unit when

discharging

is

service unit.

This amount of oil will need to

complete.

EVACUATING THE AIR-CONDITIONING SYSTEM

quality control regulations enacted in the United States, you are not permitted to refrigerant R-134a into the atmosphere. When performing maintenance on the air-conditioning system where refrigerant R-134a can escape from the system, evacuate the system with a recovery/recycle service unit that will recover the refrigerant.

WARNING: Due to the air vent

air-conditioning system is a high pressure system. Before disconnecting a refrigerant line, system must be discharged with a recovery/recycle service unit. Evacuate the entire system for 15 minutes.

The the

Use

Evacuating the

the

only

R-134a

system will

compatible recovery/recycle

remove

service unit.

any moisture from the system. The system must be evacuated

prior to charging

system with refrigerant.

a.

Connect the

recovery/recycle

unit to the service valves located in the

wheel well. If recovery/recycle air-conditioning system

nose

does not have pressure gauges, connect service pressure gauges to the

unit

(Ref. Figure 201). system in accordance with the recovery/recycle unit’s instructions for

b.

Evacuate the

c.

Once the system has been evacuated, it is then

ready for charging

with R-134a

a

minimum of 15 minutes.

refrigerant.

CLEANING THE AIR-CONDITIONING SYSTEM CAUTION: Do not

use

solvent, it will

If it is necessary to clean the

cause

system, it

can

contamination of the

be flushed with

refrigerant oil.

refrigerant

R-134a

(Item 13, Chart 2, 21-00-00)

and

dry

nitrogen.

nw

21-51-00

’M"a~Z:May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

00000

o

A

57.50 REF

FS 70.75 REF

HIGH PRESSURE

TO CONDENSER

FS 30.00 REF

ASSEMBLY

FI O

II

O

SERVICE PORT

o"\l

FS\ 95.50

REF/

LOW

PRESSURE

FS\ (79.00

IIII

\O

FS 53.62

VIEW LOOKING

\REF

OUTBOARD LEFT

REF

DETAIL

SERVICE PORT

A

HIGH

PRESSURE PORT

(RED)

O

ci(i

LOW

PRESSURE

c

(i~

PORT(BLUE)

0

B Nose Wheel Well Service Valves

Figure

May

21-51-00

201

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CHARGING THE AIR-CONDITIONING SYSTE~II

quality control regulations enacted in the United States, you are not permitted to refrigerant R-134a into the atmosphere. When performing maintenance on the air-conditioning system where refrigerant R-134a can escape from the system, evacuate the system with a recovery/recycle service unit that will recover the refrigerant.

WARNING: Due to the air vent

air-conditioning system is a high pressure system. Before disconnecting a refrigerant line, system must be discharged with a recovery/recycle service unit. Evacuate the entire system for 15 minutes.

The the

Use

only

R-134a

compatible recovery/recycle

service unit.

recovery/recycle service unit to charge the refrigerant system. A qualified air-conditioning serviceman is required to operate the service equipment. Refrigerant service ports are located on the left side of the nose wheel well. Service ports are provided so the air-conditioning system can be serviced without the necessity of working close to the propellers with the engines running (Ref. Figure 201). Use

a

recovery/recycle

service unit to the service valves

a.

Connect the

b.

Evacuate

c.

Add the amount of compressor oil removed from the system

d.

Charge

system prior

charging (Ref.

the

airplane.

EVACUATING THE AIR-CONDITIONING SYSTEM).

during discharging.

conditioning system in accordance with the recovery/recycle service refrigerant or alternatively, until the sight glass just clears of bubbles.

the air

Ibs of R-134a

Disconnect and

e.

to

on

remove

the

recovery/recycle

service unit when

charging

is

unit’s instructions with 3.5

complete.

COI1IIPRESSQR QUILL SHAFT LUBRICA nON quill shaft that provides the specified in Chapter 5.

The

a.

air-conditioning

compressor should be lubricated at the interval

Remove the compressor drive belt (Ref. COMPRESSOR BELT REMOVAL) and shim between the belt housing and the drive pulley (Ref. Figure 202). Remove the drive

b. c.

drive for the

pulley, bearings

Clean the end of the the

quill shaft

with

and

quill shaft with shop air.

a

clean cloth moistened with solvent

shaft with

Lubricate the compressor end of the

e.

Install the

f.

Install the compressor drive belt, compressor drive (Ref. COMPRESSOR BELT INSTALLATION).

n~z4

drive

careful to retain the spacer

quill shaft.

d.

quill shaft, spring,

being

quill

pulley

and

a

thin

even

(Item 10, Chart 2, 21-00-00)

coat of lubricant

and

dry

(Item 5, Chart 2, 21-00-00).

bearings. pulley,

spacer and shim, and drive belt

housing

21-51-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COMPRESSOR REMOVAL the inboard

a.

Open

b.

Using the service valves on the forward end of the recycle service unit until all pressure is bled off.

c.

Disconnect the electrical leads from the compressor clutch.

d.

Disconnect the

high pressure (discharge) hose and the low pressure (suction) hose from the compressor by removing the metric bolt securing the retaining plate and adapters to the compressor. Discard the O-rings and cap or plug all open lines and fittings.

e.

Cut the

safety attaching bolt.

f.

Remove the bolt

g.

Remove the drive belt from the compressor.

wire

Remove the aft

h.

their

cowling

on

the aft

attaching

pivot

door

on

the

right

nacelle to

access

compressor,

pivot bolt, then loosen

the drive belt tension

gain

both

adjuster

to the compressor

slowly discharge

pivot bolts,

the tension

(Ref. Figure 202).

the system with the

adjuster

recovery/

lock nuts and lower

to the compressor.

pivot bolt and nut. Note the number of compressor aligning shims aligning the compressor pulley with the drive pulley when installing the

bolt and the forward

respective locations

to aid in

and

compressor.

CAUTION: Bolts i.

securing

the

mounting plate

If the compressor is to be replaced, attached with metric bolts.

May

1/08Page

206

21-51-00

and tension

remove

the

adjuster plate

mounting plate

on

the compressor

and tension

are

metric.

adjuster plate. These plates

are

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COMPRESSOR INSTALLA TION CAUTION: Bolts a.

the

If not installed, install the

inch-pounds b.

securing

and

mounting plate

and tension

adjuster plate

mounting plate and tension adjuster plate (Ref. Figure 202).

on

the compressor

are

metric.

Tighten

with metric bolts.

to 60 to 86

wire

safety

Install the compressor on the compressor mount with the compressor pulley aligning shims installed in locations from which they were removed. Install the forward and aft pivot bolts but do not tighten until the belt has been installed.

c.

Install the drive belt

NOTE:

attaching

bolts.

Attach the belt tension the

the compressor.

If the compressor clutch pulley is not parallel with the drive pulley, loosen the pivot mount attaching bolts slightly and align the pulleys by turning the adjusting bolt. When alignment is obtained, tighten the pivot mount

d.

on

attaching

adjuster to the compressor and adjust (Ref. COMPRESSOR inch-pounds.

BELT

TENSION). Tighten

bolt to 60 to 85

the compressor

pivot bolts

to 95 to 110

inch-pounds. Safety

wire the aft

pivot

bolts.

e.

Tighten

f.

pressure (discharge) hose and the low pressure (suction) hose and adapters to the Use new O-rings between the retaining plate, the adapters and the compressor. Tighten the metric compressor. bolt to 60 to 86 inch-pounds and safety wire.

Connect the

high

NOTE: Ensure that the

high

pressure

(discharge)

and low pressure

(suction)

hoses

are

connected to the proper

fitting. g.

Connect the electrical leads to the compressor clutch.

h.

Evacuate the system, then

i.

Close the

right

inboard

charge

cowling

the system.

door.

21-51-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

AIR CONDITIONER COMPRESSOR

TENSION LOCKNUTS

COMPRESSOR MOUNT

I

+~Y

~h

A~TACHING BOLT

+I+

PIVOT BRACKET MOUNT ASSEMBLY VIEW LOOKING FWD DETAIL

O

A

BELT

HIGH PRESSURE

(DISCHARGE) COMPRESSOR

LOW PRESSURE

I

Y

II

1 ~31 1 II 1111101C~ \C-

OlL FILL PORT

(SUCTION)

AFT PIVOT BOLT

olh

n

DETAIL

~r

FWDPIVOTBOLT

B FLPIB ososs7nn nl

Air-Conditioning Compressor Installation Figure 202 (Sheet 1 of 3)

May

1/08Page

208

21-51-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PULLEY BELT

O-RING QUILL SHAFT

~WASHER

GEARSHAFT SCREW

A

RETAINING

RINGIREF)

//A

SPACER

(REF)

j~4

LAMINATED

O-RING

SHIM A/R TO

WASHER

V

/U C~-

FILL GAP

I

MOUNTASSY

(REF)

II

GAP .010

.002

BEARING 2 PLACES

(PRESS FIT ON PULLEY)

TO

ROUTE FROM DRAIN MANIFOLD ON POWER PLANT

DRAIN TUBE

VIEW

A-A

VIEW LOOKING FWD

~I

‘VI

,O-RING QUILL SHAFT

MOUNTING

B TEFLON WASHER

O/

OUILL SHAFT

BEARING DETAIL

(D

B

ENGINE INTERFACE SIDE

BEARING SHIMS

DRIVE PULLEY

O PIVOT PLATE

O WASHER

DETAIL

IBOL

BEARING SPACER RETAINING RING

A

FL21B

050868~A Al

Air-Conditioning Compressor Installation Figure 202 (Sheet 2 of 3)

A24

21-51-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

I

COMPRESSOR

MOUNT ASSEMBLY

II

I" HIGH PRESSURE

(DISCHARGE) O

LOW PRESSURE

10

(SUCTION)

tB"

B

HIGH PRESSURE

HOSE

i

LOWPRtSSUR~

HOSE

7 FIREWALL REF

VIEW

A

Placard Location at Firewall

Figure

Page

21-51-00

202

(Sheet

3 of

3)

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COMPRESSOR MOUNT REMO VAL a.

Remove the compressor belt

b.

Remove the compressor

c.

Cut the

(Ref.

(Ref.

COMPRESSOR BELT

COMPRESSOR

safety wire and remove (Ref. Figure 202).

the

eight

bolts

REMOVAL).

REMOVAL).

securing

the compressor mount to the

engine gearbox housing

and support d.

Remove the compressor mount and quill shaft. Exercise care not to lose the spring at the end of the the two seals between the compressor mount and the engine gearbox housing.

quill shaft

or

engine gearbox housing

nuts that

e.

Remove two

f.

Remove the compressor mount support

secure

the support to the

gearbox housing.

(Ref. COMPRESSOR MOUNT SUPPORT REMOVAL).

COMPRESSOR MOUNT INS TA LLA TION a.

Install the mount support

(Ref.

COMPRESSOR MOUNT SUPPORT

quill shaft, and quill shaft spring are in place prior to damaged, install new seals.

CAUTION: Ensure that the mount seals, mount. If the

existing

seals

quill shaft, spring gearbox.

shaft in the compressor mount

b.

Install the

c.

Install the compressor mount. the lower bolt in place.

d.

Install the compressor

pivot e.

quill

on

installation of the

are worn or

NOTE: It is recommended to install the compressor mount to the

INSTALLATION).

Tighten

and seals in the compressor mount

prior to installing

the

(Ref. Figure 202).

the compressor mount bolts to 40 to 50

the compressor mount

inch-pounds. Safety

(Ref. COMPRESSOR INSTALLATION).

Do not

wire all but

tighten

the

bolts.

Install the compressor drive

pulley,

belt and drive belt

housing (Ref.

COMPRESSOR BELT

INSTALLATION).

COMPRESSOR MOUNT SUPPORT REMOVAL (Ref. COMPRESSOR MOUNT REMOVAL).

a.

Remove the compressor mount

b.

Remove the two

c.

Note the number of shims at each location and retain for reinstallation at the

d.

Install the two nuts

engine gearbox housing

on

the studs

they

nuts

were

securing

the support to the

gearbox housing (Ref. Figure 202). same

location.

removed from.

COMPRESSOR MOUNT SUPPORT INSTALLA TION a.

b.

Install the two nuts at the location the support will be installed Install the support with the shims. The shims should level the pad on the gearbox housing.

(Ref. Figure 202). mounting surfaces of

the support to within 0.002

inch of the compressor mount

gearbox housing

nuts and

c.

Install the

d.

Install the compressor mount

nz4

(Ref.

tighten

to 20 to 30

inch-pounds.

COMPRESSOR MOUNT

INSTALLATION).

21-51-00Mayl/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COMPRESSOR EEL T REMOVAL the inboard

a.

Open

b.

Remove the

cowling

door

attaching bolts

the

on

right nacelle

to

gain

and the drive belt

the spacer and shim between the

housing from the housing and pulley.

c.

Release the tension

d.

Remove the drive belt from the compressor and the drive

on

access

the tension

adjuster.

Remove the

to the compressor

compressor mount

attaching parts

and

one

(Ref. Figure 202).

assembly.

Use

care

end of the tension

to retain

adjuster.

pulley.

COMPRESSOR EEL T INSTALLA TION a.

Install the drive belt onto the compressor and drive

b.

Assemble the turnbuckle end and mount

assembly. Torque

c.

Tension the drive belt

d.

Close the

cowling

(Ref.

door

secure

the drive belt

on

the tension

housing

right

adjuster.

housing to the compressor safety wire bolts.

Install the drive belt

bolts to 25 to 30

COMPRESSOR BELT

the

pulleys (Ref. Figure 202).

inch-pounds

and

TENSION).

nacelle.

COMPRESSOR EEL T TENSION NOTE: The tension of the compressor belt should be checked after 50 hours of operation. A 21 to 26-pound force applied at the midspan of the belt should deflect the belt approximately 0.50 inch. Adjust the belt tension as follows:

pivot

bolts and the tension

adjuster

a.

Loosen the

b.

Loosen the locknut at each end of the tension

lower attachment bolt

adjuster

(Ref. Figure 202).

barrel and turn the barrel to

lengthen

or

shorten the

adjuster. c.

When correct tension is

obtained, tighten the adjuster lower attachment bolt

to 60 to 85

inch-pounds

and

safety

wire the bolt head. d.

Tighten

Page

yaM212

1/08

the

pivot

bolts and the barrel locknuts.

21-51-00

Safety

wire the locknuts to the

adjuster

barrel.

na4

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CONDENSER REI~OVAL NOTE:

Replace the receiver/dryer whenever the compressor is replaced plumbing is left open to the atmosphere for more than one hour.

a.

Discharge the system slowly until all pressure is bled off (Ref. DISCHARGING THE AIR-CONDITIONING SYSTEM).

b.

Remove the

c.

Remove all avionics

d.

Remove the condenser inlet duct

e.

Remove the

right

access

receiver/dryer. f.

panels

and the

right

and the avionics shelf from the

equipment

panel from

Discard old

access

(Ref. CONDENSER

when the

INLET DUCT

airplane.

compartment.

nose

REMOVAL).

the top side of the airplane nose and disconnect the plumbing lines from the and cap or plug all open lines and fittings (Ref. Figure 203).

O-rings

panel

to the bulkhead and remove

panel.

Remove the inlet line and the outlet line from the condenser fittings. Discard old and

air-conditioning system

avionics compartment door from the

Remove fasteners which attach the forward avionics compartment bulkhead the

g.

and left louvered

or

O-rings

and cap

or

plug

all lines

fittings.

h.

Remove six fasteners that attach the upper support bracket and

i.

Remove the fasteners which attach the condenser in

position

remove

and

upper support bracket.

remove

the condenser from the

nose

compartment.

CONDENSER INSTALLA TION NOTE:

Replace the receiver/dryer whenever the compressor is replaced plumbing is left open to the atmosphere for more than one hour.

when the

air-conditioning system

with the

attaching

fasteners

a.

Position condenser in its

b.

Install the upper support bracket and

c.

Connect the inlet line and the outlet line to the condenser. Lubricate

00-00)

and torque

nose

fittings (Ref.

d.

Install the forward bulkhead

e.

Connect the

compartment location and

or

secure

new

O-rings

AIR-CONDITIONING SYSTEM MAINTENANCE

panel

to the nose

plumbing lines to the receiver/dryer by access through the opening O-rings with oil (14, Chart 2, 21-00-00) and torque fittings (Ref. AIR-CONDITIONING SYSTEM MAINTENANCE NOTES).

f.

Install the

access

g.

Install the condenser inlet duct

h.

Install the avionics shelf and all avionics

equipment

i.

Install the left and

panels

j.

Charge

the

right

on

the top of the

(Ref.

louvered

(Item 14, Chart 2, NOTES).

21-

in the top of the

airplane

nose.

nose.

CONDENSER INLET DUCT

access

with oil

compartment bulkhead with the attaching fasteners.

new

panel

(Ref. Figure 203).

to frame and condenser with fasteners.

Lubricate

p~s

secure

in the

and the

nose

nose

INSTALLATION).

compartment.

compartment door

on

the

right

side of the

nose.

system (Ref. CHARGING THE AIR-CONDITIONING SYSTEM).

21-51-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CONDENSER INLET DUCT REMOVAL louvered inlet from the

of the

airplane.

a.

Remove the

b.

Remove bracket from the forward side of the inlet duct

c.

Remove five fasteners that attach the inlet duct to the condenser blower and

right

nose

(Ref. Figure 203). remove

inlet duct.

CONDENSER INLET DUCT INSTALLA TION a.

Install the inlet duct seal

b.

against

on

the condenser blower and

the blower

Install the bracket

on

secure

with five fasteners. Ensure the inlet duct forms

a

tight

(Ref. Figure 203).

the forward side of the inlet duct. Ensure the forward

flange

forms

a

tight

seal

against

the

structure.

c.

Install the

right

louvered inlet to the

nose

of the airplane.

CONDENSER BLOWER REMOVAL

(Ref.

CONDENSER INLET DUCT

a.

Remove the condenser inlet duct

b.

Disconnect the electrical connector from the condenser blower

c.

Remove four fasteners that attach the blower to the

d.

Rotate the blower and

remove

blower

through

mounting

the inlet

access

REMOVAL).

(Ref. Figure 203).

bracket.

opening.

CONDENSER BLOWER INSTALLATION a.

Install the blower into

position on the mounting bracket through the inlet access opening and secure with a positive seal exists between the blower and condenser seal (Ref. Figure 203).

fasteners. Ensure that b.

Install four fasteners that attach the blower to the

c.

Connect the electrical connector to the condenser blower.

d.

Install the condenser inlet duct

Page

mounting

(Ref. CONDENSER

21421-51-00

bracket.

INLET DUCT

INSTALLATION).

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

RECEIVER/DRYER RE~IOVAL NOTE:

a.

b.

or

when the

air-conditioning system

Discharge the system slowly until all pressure is bled off (Ref. DISCHARGING THE AIR-CONDITIONING SYSTEM). Disconnect the inlet line and the outlet line from the and

c.

Replace the receiver/dryer whenever the compressor is replaced plumbing is left open to the atmosphere for more than one hour.

receiver/dryer.

Discard old

O-rings

and cap

or

plug

all lines

fittings (Ref. Figure 204).

Remove the

receiver/dryer from

the

airplane

NOTE: For troubleshooting purposes, the exists in the system.

and discard.

receiver/dryer can

be cut open

carefully to determine

if any contamination

RECEIVER/DRYER INSTALLATION NOTE:

Replace the receiver/dryer whenever the compressor is replaced plumbing is left open to the atmosphere for more than one hour.

or

when the

air-conditioning system

receiver/dryer has a designated "IN" side, indicating refrigerant flow. Proper orientation is important. The hose from the condenser needs to be attached to the side marked "IN".

WARNING: The

a.

Install the

b.

Connect the inlet line and the outlet line to the

(Item c.

receiver/dryer (Ref. Figure 204).

14, Chart 2,

Charge

the

21-00-00)

and torque

refrigerant system (Ref.

receiver/dryer. Lubricate new O-rings with oil fittings (Ref. AIR-CONDITIONING SYSTEM MAINTENANCE NOTES).

CHARGING THE AIR-CONDITIONING

SYSTEM).

21-51-00

Page

yaM512

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CONDENSER

ASSEMBLY

C CONDENSER BLOWER

O

B

V EW LOOKING FWL)

:NLET

DUCT

FROM FS 57.50

DETAILA

AN3-5A

AN3-5A AN960-10L WASHER

AN960-10L WASHER

PPLIICES

PPLACES

OETAIL

B

BOLTS AND WASHERS

C FUIB ~0865AA Al

Condenser and Blower Installation

Figure

May

21-51-00

203

(Sheet

1 of

2)

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

BRACKET AN3-5A BOLT AN960-10L WASHERS 3 PLACES

AN3-5A BOLT

AN3-6A BOLT

AN960-10L WASHER

AN960-10L WASHERS

2 PLACES

PPLACES DETAIL

D BLOWER ASSEMBLY

INLET DUCT FS 57.50

BULKHEAD

BRACKET

D,,,,,

E FUIB

060866~A.AI

Condenser and Blower Installation

Figure

A24

203

(Sheet

2 of

2)

21-5100

Page

yaM712

1/08

Hawker Beechcraff

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

A

-O

8-8,~

8

VIEW LOOKING AFT

RECEIVERIDRYER BOTTLE

~SIGHT GLASS

BRACKET CLAMP

FWD BULKHEAD FS 57.50

RECEIVEWDRYER OUTLET LINE

RECEIVEWDRYER INLET LINE

O

FWD

O

VIEW LOOKING INBD

DETAIL

A FL218 060871AA Al

Receiver/dryer

Figure

Page

yaM812

1/08

21-51-00

204

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COCKPIT EVAPORA TOR REIMOVAL a.

Discharge the system slowly until all pressure is bled off (Ref. DISCHARGING THE AIR-CONDITIONING SYSTEM).

b.

Remove the

right

nose

avionics compartment door, all avionics

equipment

nose

compartment floor panel

to the

and avionics shelf from the

nose

compartment. c.

Remove the

d.

Remove the duct between the evaporator blower and the

e.

Remove the

f.

Remove the evaporator inlet and outlet lines. Discard old

g.

Working

right

hydraulic

line

cover

thru the wheel well

and blower motor

opening,

access

gain

to

access

plenum (Ref. Figure 205).

access

remove

cockpit evaporator.

panel

O-rings

in the wheel well. and cap

or

plug

all lines and

fittings.

four bolts from left side bracket attached to the intercostal

and evaporator. h.

Remove the forward bolt from

i.

Working

j.

Remove four forward side bolts

thru the top

access

side bracket attached to the evaporator.

right

opening,

remove

attaching

the aft bolt from the

right side

bracket attached to the

evaporator.

the evaporator to the forward frame. Remove evaporator from the

airplane. COCKPIT EVAPORA TOR INSTALLA TION NOTE:

Replace the receiver/dryer whenever the compressor is replaced plumbing is left open to the atmosphere for more than one hour.

a.

Install evaporator into

b.

Install the aft bolt

c.

Install the forward bolt

d.

Working

position

attaching

and

the

right

attaching

thru the wheel well

secure to

the

access

or

when the

the fon~vard frame with four bolts

air-conditioning system

(Ref. Figure 205).

side bracket attached to the evaporator.

right

side bracket attached to the evaporator.

opening,

install four bolts and attach left side bracket to the intercostal and

evaporator. e.

Install the evaporator inlet and outlet lines. Lubricate new O-rings with oil AIR-CONDITIONING SYSTEM MAINTENANCE NOTES).

(Item 14,

Chart 2, 21

-00-00)

and torque

fittings (Ref. f.

Install the blower motor

g.

Install the duct between the evaporator blower and the

h.

Install the

i.

right

nose

Install all avionics

access

panel

and

hydraulic

line

cover

in the wheel well.

plenum.

compartment floor panel.

equipment

and the avionics shelf in the

nose

compartment. Install right

nose

avionics

compartment door.

j.

Charge

the

system (Ref. CHARGING

THE AIR-CONDITIONING

SYSTEM).

21-51-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COCKPIT EVAPORA TOR BLOWER REMOVAL a.

Remove the blower

b.

Remove the three bolts that connect the blower motor

c.

Disconnect the electrical connector.

d.

Rotate and

remove

access

panel

located

on

the

right

keel in the

nose

adapter plate

the blower motor and wheel thru the

access

wheel well.

to the blower

housing (Ref. Figure 205).

opening.

COCKPIT EVAPORA TOR BLOWER INSTALLA TION a.

Rotate and install the blower motor and wheel thru the

b.

Connect the electrical connector.

c.

Install three bolts and connect the blower motor Install the blower

d.

Ensure

adapter plate

panel located on the right during airplane pressurization.

access

air leaks

no

access

keel in the

opening (Ref. Figure 205).

to the blower

nose

housing.

wheel well. Seal the

panel

as

required

to

COCKPIT EVAPORATOR BLOWER MOTOR REPLACEMENT improperly set distance between the blower wheel and blower motor adapter plate rubbing of the blower wheel on the housing inlet and cause blower wheel binding.

CAUTION: An

Remove the

a.

b.

can

result in

cockpit evaporator blower (Ref. COCKPIT EVAPORATOR BLOWER REMOVAL).

Measure the distance between the blower wheel and blower motor

duplicated. Mark the symmetrical (Ref. Figure 205).

distance will need to be

pattern is

not

orientation of motor

the wheel hub and

c.

Loosen the blower wheel set

d.

Remove three nuts and washers and the blower motor from the

e.

Install

f.

Install blower wheel. Ensure blower wheel is

g.

Apply

new

screw on

blower motor, washers and nuts to

thread

locking compound (Item 15,

adapter plate and record the distance. This plate with respect to the motor as the hole

remove

the blower wheel.

adapter plate.

adapter plate.

correctly

Chart 2,

set at the distance recorded in

21-00-00)

Step

b.

to blower wheel set screw and

torque

to 6 to 9

in-lbs. h.

Install the

May

1/08~el’m’8"

cockpit evaporator blower (Ref. COCKPIT EVAPORATOR BLOWER INSTALLATION).

21-51-00

124

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

84.00

P Fs 61.75 REF

FS 84.00 REF

BOLT AND FS61.75

WASHERS

(6 EA)

COCKPITEVAPORATOR

411trioq BLOWER

MID PLENUM

DETAIL

B

ACCESS THIS BOLT THRU CUT OUT IN KEEL

g

FS 84.00

CO\CKPITEVAPORATORASSY DETAIL

A FL21B asos64aAal

Fon~vard

Evaporator Figure 205

A24

21-51-00

Page

yaM12

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COCKPIT AND CABIN EXPANSION VAL VE REPLACEI~ENT a.

Discharge the system slowly until all pressure is bled off (Ref. DISCHARGING THE AIR-CONDITIONING SYSTEM).

b.

Remove the

line

hydraulic

cover

in the

wheel well to

nose

gain

access

to the

expansion

valve

(forward

valve

only).

insulation d.

Install the

plumbing line to the expansion or plug all lines and fittings.

valve and

remove

the

expansion

valve from the coil. Discard old

expansion valve, O-rings and connect plumbing line. Lubricate new O-rings with oil (Item 21-00-00) and torque fittings (Ref. AIR-CONDITIONING SYSTEM MAINTENANCE NOTES).

length

sensing

g.

Install the

h.

Charge

hydraulic

the system

sensing element makes contact with the suction tube along its position on the tube. Insulate the sensing element thoroughly with

element. Ensure the

and locate it at the 3

insulation and install

or

9 O’clock

clamp.

line

cover

in the

nose

(Ref. CHARGING

wheel well

(forward

valve

THE AIR-CONDITIONING

only).

SYSTEM).

COCKPIT AND CABIN EVAPORA TOR COIL CLEANING a.

Discharge the system slowly until all pressure is bled off (Ref. DISCHARGING THE AIR-CONDITIONING SYSTEM).

b.

Remove the evaporator

c.

Use

d.

Spray

e.

Allow coil to

f.

Install the evaporator

g.

Charge

May

remove

new

Install the thermal entire

carefully

and cap

14, Chart 2, f.

suction tube of the evaporator and

the

covering

Disconnect the

O-rings e.

sensing element from its clamp on the sensing element (Ref. Figure 206).

Remove the thermal

c.

a vacuum

(Ref. COCKPIT OR

cleaner to

coil cleaner

on

remove

large

CABIN EVAPORATOR

REMOVAL).

debris from the coil face.

coil face and wash with water. Ensure

no

water enter the

fittings.

thoroughly dry.

the system

(Ref. COCKPIT

(Ref.

OR CABIN EVAPORATOR

CHARGING THE AIR-CONDITIONING

1/0821-51-00

INSTALLATION).

SYSTEM).

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FS 70.75 THERMAL SENSING

COCKPIT EVAPORAT

ELEMENT

(INSULATION

´•I,

o

COCKPIT EXPANSION VALVE DETAIL

A

CABIN

EVAPORATPRS (INSULATION REMOVED)

THERMAL SENSING

ELEMENT

(INSULATION REMOVED)

G CABIN EXPANSION VALVES

B

LIATEoSEVLAV

CABIN EXPANSION

FWD and AFT

FS

FS

FS

261.00

270.50

280.75

Expansion Figure 206

A24

FUIB osos7onnni

Valves

21 I51-00

Page

yaM32

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CABIN EVAPORA TORS REMOVAL a.

Discharge the system slowly until all pressure is bled off (Ref. DISCHARGING THE AIR-CONDITIONING SYSTEM).

b.

Remove center aisle floorboards between FS 261.00 and FS 280.75.

c.

Remove the aft evaporator blowers

d.

Disconnect the plumbing (Ref. Figure 207).

e.

Remove

eight

(Ref.

lines to the

attachment bolts and

CABIN BLOWERS

REMOVAL).

evaporators. Discard old O-rings and cap

remove

or

plug all lines and fittings

both evaporators.

CA BIN EVA PORA TORS INSTALLA TION NOTE:

Replace the receiver/dryer whenever the compressor is replaced plumbing is left open to the atmosphere for more than one hour. and

position

with

eight

or

attachment bolts

when the

air-conditioning system

(Ref. Figure 207).

a.

Install evaporators into

b.

Connect the plumbing lines to the evaporators. Lubricate new O-rings with oil (Item 14, Chart 2, 21-00-00) and torque fittings (Ref. AIR-CONDITIONING SYSTEM MAINTENANCE NOTES).

c.

Install the aft evaporator blowers

d.

Install center aisle floorboards between FS 261.00 and FS 280.75.

e.

Charge

the

secure

(Ref.

CABIN BLOWERS

INSTALLATION).

system (Ref. CHARGING THE AIR-CONDITIONING SYSTEM).

CABIN BL~OWERS REMOVAL a.

Remove center aisle floorboards between FS 261.00 and FS 280.75.

b.

Disconnect the

c.

Remove the

d.

Remove the transition ducts from the blowers and

bonding straps

eight

and the blower electrical connectors

(Ref. Figure 207).

attachment bolts and both blowers.

reposition

onto the

evaporators.

CABIN BLOWERS INSTALLA TION CAUTION: The two cabin blowers

use

the forward and aft motor a.

Install the transition ducts

b.

Install both blowers and

on

motors and blower wheels that rotate in

or

wheel will result in

the blower outlets

secure

with

eight

a

attachment bolts.

and the blower electrical connectors.

Connect the

d.

Install center aisle floorboards between FS 261.00 and FS 280.75.

May

in airflow.

(Ref. Figure 207).

c.

bonding straps

opposite directions. Interchanging

significant decrease

21-51-00

P124

Hawker Beechcraff

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CABIN EVAPORA TOR BLOWER MOTOR REPLACEMENT CAUTION: An

improperly set distance between the blower wheel and inlet ring on the inlet ring and cause blower wheel binding.

can

result in

rubbing

of the blower

wheel

The two cabin blowers

use motors

the forward and aft motor

or

a.

Remove the aft evaporator blowers

b.

Remove three attachment

c.

Loosen the blower wheel set

d.

screws

and blower wheels that rotate in

wheel will result in

(Ref.

significant

CABIN BLOWERS

and the inlet

screw on

a

opposite

directions.

Interchanging

decrease in airflow.

REMOVAL).

ring (Ref. Figure 207).

the wheel hub and

remove

the blower wheel.

Remove five

screws

from the motor bracket and blower motor. Remove two bolts from motor bracket and hat

channel and

remove

the bracket.

e.

Remove three nuts and washers from the blower motor and

f.

Install

g.

Install motor bracket to blower motor with five

h.

Install blower wheel. Ensure blower wheel is 0.22-inch from inlet

i.

Apply thread locking compound (Item 15, Chart 2, 21-00-00)

new

blower motor, washers and nuts to

adapter plate

and

remove

blower motor.

adapter plate.

screws.

Install two bolts and attach motor bracket to hat channel.

ring.

to blower wheel set screw and

torque

to 6 to 9

in-lbs.

j.

A24

Install the aft evaporator blowers

(Ref.

CABIN BLOWERS

INSTALLATION).

21-51-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CABIN

EVAPORATOR CABIN

(RND)

EVAPORATOR

(AFT) TRANSITION

TRANSITION

DUCT(FWD) JLP~

7ntrr

A

DUCT(AFT)

-lI~WI

Fs CABIN

[II

CABIN EVAPORATOR BLOWER

IIlI

1

ql~u

UI

EVAPORATOR

Ib~onU

BLOWER(AFT)

(FWD)

B

FS75

70.50

ELECTRICAL

VIEW LOOKING DOWN

CONNECTOR

DETAILA

INLET

I

CABIN BLOWER INLET RING

II

I I II

1

II

I

RING

h/

SCREW

(3)

ELECTRICAL CONNECTOR

FAN SHROUD

CABIN BLOWER INLET RING

FS 280.75 BLOWER WHEEL

BLOWER MOTOR FS 270.50

0.22 INCH

C

CABIN EVAPORATOR BLOWERS

(WITH TRANSITION DUCT REMOVED)

B mDs69nnal

Aft

Evaporators Figure 207

May

1/08Page

226

21-51-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PRESSURE SWITCH REPLACEMENT The pressure switch monitors the refrigerant gas pressure and is located in the right inboard wing leading edge. This switch will open at a compressor over pressure of 384.0 28.4 psig and under pressure of 30.0 psig. This will

interrupt NOTE:

the power to the compressor clutch coil

Replace

the

plumbing

receiver/dryer

is left open to the

(Ref. Figure 208).

whenever the compressor is replaced atmosphere for more than one hour.

a.

Discharge the system slowly until all pressure is bled off (Ref. DISCHARGING THE AIR-CONDITIONING SYSTEM).

b.

Remove the

c.

right

inboard

or

when the

air-conditioning system

wing leading edge.

Disconnect the pressure switch from the plumbing lines and electrical connector. Discard old plug all lines and fittings.

O-rings

and cap

or

d.

Install

new

pressure switch, connect plumbing lines and electrical connector. Lubricate new O-rings with oil and torque fittings (Ref. AIR-CONDITIONING SYSTEM MAINTENANCE NOTES).

(Item 14, Chart 2, 21-00-00) e.

Install the

f.

Charge

right

inboard

the system

wing leading edge.

(Ref.

CHARGING THE AIR-CONDITIONING

SYSTEM).

21-51-00

Page

yaM72

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

BL 93.0

ENGINE

NACELLE80 HOSE ASSEMBLY

O

(REF)

(REF)HOSE

nssEhneLv

o

O

FUSELAGE

PRESSURE SWITCH

NOTE:

VIEW SHOWN WITH

RIGHT INBOARD WING LEADING EDGE REMOVED.

UP

t

INBOARD

VIEW LOOKING AFT

Pressure Switch

Figure

Page

22821-51-00

208

A24

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 000 21-60-00

TEMPERATURE CONTROL - DESCRIPTION AND OPERATION The temperature of the cabin can be automatically controlled by setting the temperature selector potentiometer to the desired temperature and setting the mode control switch to AUTO. The cabin temperature controller then sends the appropriate “heat” or “cool” command to the bleed air bypass valves. A dual-element temperature sensor installed in the bleed air line immediately upstream of the mixing plenum, completes the Wheatstone Bridge resistance circuitry of the cabin temperature controller. When the cabin temperature falls, the Wheatstone Bridge becomes unbalanced and current flows from the heat command output of the cabin temperature controller. The bleed air bypass valves receive the command and open to allow more bleed air to bypass the wing heat exchanger and flow into the conditioned air ducts (Ref. Figure 1). The bypass valves modulate the amount of bleed air flow in automatic response to the requirements indicated by the changing resistance of the duct temperature sensors and the temperature sensor located in the cabin temperature controller. The duct temperature sensors are installed in the conditioned bleed air main duct immediately aft of the mixing plenum (under the flight compartment floorboards). The solid-state temperature controller is installed under the headliner access panel in line with the second cabin window. The environmental temperature control switches and the cabin air temperature indicator are located on the copilot’s inboard subpanel.

A27

21-60-00

Page 1 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Temperature Control Schematic (FL-1 thru FL-492, FL-494 thru FL-499) Figure 1

Page 2 Feb 1/10

21-60-00

A27

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

TEMPERATURE CONTROLLER (300-0750-1) (FL-493, FL-500 THRU FL-536; AND AIRPLANES WITHOUT SERVICE BULLETIN 21-3838) The temperature controller monitors the temperature sensors to determine if they are out-of-range. The temperature sensors lower end range is set at -49° F. When the temperature sensors sense an out-of-range condition the temperature controller operates all valves and servos to a full cold position and pulses the cockpit blowers to alert the pilots.

TEMPERATURE CONTROLLER (300-0750-2) (FL-537 AND AFTER; FM-15 AND AFTER AND AIRPLANES WITH SERVICE BULLETIN 21-3838) The temperature controller monitors the temperature sensors to determine if they are out-of-range. The temperature sensors lower end range is set at -100° F. When the temperature sensors sense an out-of-range condition the temperature controller operates all valves and servos to a full cold position and pulses the cockpit blowers to alert the pilots. The temperature of environmental air can be controlled manually by setting the mode control switch to MAN HEAT or MAN COOL and holding the manual temperature control switch in the INCR or the DECR positions. When the manual control switch is set to INCR or DECR, power is supplied through the CABIN TEMP CONTROL circuit breaker, the mode switch, and the manual temperature control switch to the appropriate bypass valve. When the switch is set to INCR, the bypass valve opens, allowing warm bleed air to bypass the heat exchanger and flow through the floor outlets. The bypass valves close, as required, to direct bleed air into the heat exchangers to cool the bleed air when the manual switch is set to DECR.

PASSENGER CABIN TEMPERATURE CONTROL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) Passenger cabin temperature is controllable from the flight compartment or from the designated cabin programmable switch (PSW) (Ref. Figure 2) of the cabin management system (Ref. Airplane Maintenance Manual Supplement, CABIN MANAGEMENT SYSTEM, 23-30-03). To allow control from the cabin (PSW) the cabin temperature potentiometer must be set to the CMS position (fully counterclockwise). This energizes relay K158 and transfers control of the passenger cabin temperature from the flight compartment to the cabin management system. The cabin management system outputs a resistance to the temperature control system according to the settings selected on the cabin PSW which then operates per TEMPERATURE CONTROLLER (300-0750-2) (FL-537 and After; FM-15 and After and airplanes with Service Bulletin 21-3838).

A27

21-60-00

Page 3 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CABIN MANAGEMENT SYSTEM 23-30-03

CABIN TEMP CONTROL POT OUT CABIN TEMP CONTROL POT RETURN K158 RELAY CMS TEMP CONT RL24 POT - CABIN TEMP CONT CMS

S4 SERVO POSITION

PANEL ASSEMBLY SUBPANEL, INBOARD, R +14VDC INPUT GROUND E1 SERVO ASSY CABIN ADD HEAT

AUTO ENABLE

DUCT ASSY - SERVO BLEED DUCT TEMP SENSOR OUT BLEED DUCT TEMP SENSOR RETURN COCKPIT TEMP CONTROL POT OUT COCKPIT TEMP CONTROL POT RETURN + 14V POWER SUPPLY - +

R122 POT - COCKPIT TEMP CONT

RT1 TEMP SENSOR HEAT GROUND INPUT +14VDC

PANEL ASSEMBLY SUBPANEL INBOARD, R

E3 SERVO - COCKPIT ADD HEAT GROUND INPUT +14VDC

S3 SERVO POSITION

E1 SERVO - CABIN HEAT AUTO ENABLE

GROUND INPUT +14VDC MAN COOL AUTO

S1 SERVO POSITION

OFF

1

E2 SERVO - COCKPIT HEAT MAN HEAT AUX HEAT

MIXING BOX ENVIRONMENTAL AIR

S2 SERVO POSITION

2

3

CONTROL UNIT - CABIN TEMP

5A CB24 AIR COND CLUTCH

CABIN TEMP MODE SWITCH

FL21B 985702AA.AI

Temperature Control Schematic (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 2

Page 4 Feb 1/10

21-60-00

A27

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 100100100

TEMPERATURE CONTROL - TROUBLESHOOTING Troubleshooting of the environmental temperature controls is outlined in Chart 101.

Chart 101 Troubleshooting - Cabin Temperature Controls Inadequate Control of Cabin Temperature STEP 1

Does cabin temperature respond to manual control (Note 1)?

YES

Proceed to STEP 2.

YES

Close circuit breaker.

YES

Troubleshoot heating (Ref. Chapter 2140-00) or cooling (Ref. Chapter 21-5000).

YES

System is OK.

YES

Proceed to STEP 3.

YES

Proceed to STEP 4.

YES

Correct lack of continuity to bypass valves.

NO Is CABIN TEMP CONTROL circuit breaker open? NO Are bypass valves opening and closing (make sure aurally). NO Correct lack of continuity. STEP 2

Does temperature respond to automatic control (Note 2)? NO Is resistance through duct temperature sensors correct? NO Replace temperature sensors.

STEP 3

Does temp select potentiometer have correct resistance? NO Replace potentiometer

STEP 4

Does temperature controller test OK? NO Replace controller.

NOTE 1. Set the mode control switch to MAN HEAT and MAN COOL and set the manual control to INCR or DECR. 2. Set the mode control switch to AUTO and turn the temperature select potentiometer fully clockwise or counterclockwise.

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TEMPERATURE CONTROL - MAINTENANCE PRACTICES AIR DUCT TEMPERATURE SENSOR RESISTANCE CHECK If the temperature control of the heating and cooling systems is responding to manual control but is not responding to automatic control, the fault may be found in the temperature sensing elements or in the cabin temperature controller. It is suggested that the sensing elements be tested before testing the controller because the controller is less susceptible to failure. A dual-element temperature sensor is installed below the instrument panel in the bleed air line immediately upstream of the mixing plenum. One of the elements has been thermally insulated to provide a response that lags behind the response of the noninsulated element. The lag in response prevents uncomfortably wide temperature ranges that would be caused by the overshoot of cabin heating. NOTE: In order for the resistance measurements of the elements to comply with the readings shown on the graph in Figure 201, it is important that the temperature at the location of the elements be determined accurately. a. Remove the access cover in the headliner panel in line with the second cabin window to gain access to the electrical connector on the temperature controller. b. Disconnect the electrical connector from the cabin temperature controller. c.

Remove the right side floorboard below the instrument panel in order to gain access to the temperature sensors and take temperature readings.

d. Using the graph in Figure 201, determine the correct resistance corresponding to the temperature measurement taken at the element location. e. Using a precision ohmmeter, measure the resistance between pins 10 and 11 on the connector of the cabin temperature controller. This resistance should correspond to the resistance indicated on line A-B on the graph in Figure 201. The resistance measured between pins 11 and 12 on the controller should correspond to line C-D on the graph. Line A-B represents the thermally lagged element. f.

If the measured resistance from a sensing element varies from the resistance shown on the graph by more than 1%, the elements should be replaced.

g. If the operation of the heating and cooling system is abnormal or intermittent when the temperature mode switch is set to AUTO, the internal connections of the sensing elements may be loose. h. The following steps are recommended as an effective method for identifying malfunctioning sensing elements. Removal of the duct sensing element from the airplane is required for testing. The electrical connections in faulty sensing elements are either open or intermittently open and may be checked for excessively high resistance as follows: 1. Remove the copilot’s seat, carpet and floorboards on the right side of the crew compartment. 2. Remove the four screws that attach the temperature sensing element to the air duct. Remove the element for testing. 3. Connect a digital ohmmeter to each of the two windings (A-D and C-D) of the sensing element. Without any heat applied, each winding should have a resistance of 99.1 ± 0.1 ohms at 25° C (77° F). 4. Apply heat to the sensing element until the resistance of the C-D winding is about 150 ohms (at approximately 150° C or 300° F). The resistance of the A-B winding will change much more slowly that of the C-D winding due to the thermal lag designed into the element.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 5. After exposure of the sensing element to a temperature of 300° F for two to three minutes, check for a resistance of 126 ohms in the A-B winding and a resistance of 152 ohms in the C-D winding. Intermittent and radical changes are an indication of a loose internal connection. Replace faulty sensing element. 6. Install the temperature sensing element to the air duct with attaching screws. 7. Install floorboards carpet and copilot’s seat. i.

The following procedure may be used to test the duct-mounted temperature sensor without removing it from the airplane: 1. Disconnect the electrical plug from the temperature control box. 2. Determine the correct resistance for the element (Ref. Figure 201). 3. Use two precision ohmmeters to measure the resistance between pins 10 and 11 and 11 and 12 at the cabin temperature control box connector. Measurements taken between pins 10 and 11 correspond to line A-B on the chart while measurements taken between pins 11 and 12 correspond to line C-D on the chart. If the resistance does not equal the value determined from the chart, the element is not functioning properly and should be replaced. 4. With one engine running, select MANUAL HEAT on the cabin temperature node selector switch, then hold the manual temperature control toggle switch in the INCREASE position for one minute. 5. Check both ohmmeters for intermittent or radical changes in resistance. Such readings would indicate the loose internal connection and the element is not functioning properly and should be replaced. The maximum reading observed on the ohmmeters should not exceed 200 ohms. 6. Disconnect the ohmmeters from the temperature control box connector. 7. Connect the electrical plug to the temperature control box.

j.

Install the access cover in the headliner panel in line with the second cabin window.

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Resistance Values of Duct Temperature Sensors Figure 201

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

DUCT TEMPERATURE SENSOR REMOVAL a. Remove the right side carpet and floorboards in the flight compartment to gain access to the sensor (installed on the bleed air line upstream of the mixing plenum). b. Disconnect the electrical connector from the duct temperature sensor (Ref. Figure 202). c.

Remove the attaching screws and the cabin temperature sensor from the bleed air line.

DUCT TEMPERATURE SENSOR INSTALLATION a. Install the temperature sensor and secure with the attaching screws (Ref. Figure 202). b. Install the electrical connector on the sensor. c.

Install the floorboards and carpet.

Duct Temperature Sensor Figure 202

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CABIN TEMPERATURE INDICATOR ADJUSTMENT (FL-1 THRU FL-492, FL-494 THRU FL499, FM-1 THRU FM-14) The temperature control unit is equipped with an adjustable potentiometer which permits adjustment of the cabin air temperature indicator (Ref. Figure 203). a. Apply external power (Ref. CONNECTING AND APPLYING EXTERNAL POWER, 24-40-00). b. Remove the snap-in escutcheon covering the control unit. The cover is located in the center of the headliner, just aft of the forward partition. c.

Turn the temperature mode switch to the AUTO position.

d. Hold a certified thermometer (capable of indications ranging from 25° F to 125° F) close to the aft end of the controller for a period of two minutes. The reading on the temperature indicator, mounted on the right side subpanel must be within ± 2% of the thermometer reading. If the indicator does not fall within tolerance, adjust the indicator potentiometer as required to reflect the proper reading. e. Remove the two screws that secure the unit to the mounting plates in the headliner. Holes in the PC board provide access to the mounting screws. After the screws have been removed, lower the unit from the headliner. CAUTION: The adjusting potentiometer is round and located on the upper side of the PC board. The rectangular potentiometer is factory adjusted and must not be changed. f.

Using a small common screw driver, rotate the potentiometer as required to bring the indicator into agreement with the thermometer.

g. Reseal the adjustment screw with Glyptol 1201 (12, Chart 2, 21-00-00). h. Remove external electrical power (Ref. DISCONNECTING EXTERNAL POWER, 24-40-00). i.

Reinstall the control unit and the escutcheon.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Temperature Indicator Adjustment (FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM14) Figure 203

CABIN TEMPERATURE CONTROLLER - FUNCTIONAL TEST (FL-1 THRU FL-492, FL-494 THRU FL-499, FM-1 THRU FM-14) If a fault in the operation of the automatic mode of the heating or cooling systems cannot be found in the duct sensing elements, the cabin temperature controller should be tested. The temperature at the inlet of the controller should be between 65° F and 85° F to perform the test procedures. A connected test circuit can be used to test the controller (Ref. Figure 204). CABIN TEMPERATURE CONTROLLER - TEST EQUIPMENT a. A 28-vdc, 2-amp power supply that is accurate within 1%. b. A 107-ohm, 1/8-watt resistor (R1) (12, Chart 1, 21-00-00). c.

A 115-ohm, 1/8-watt resistor (R2) (12, Chart 1, 21-00-00).

d. Two 25-ohm (± 5%), 50-watt resistors (R3 and R4) (12, Chart 1, 21-00-00). e. A 100-ohm (± 5%), 0.5% minimum resolution, wire-wound potentiometer (TR1) (12, Chart 1, 21-00-00). f.

Two 28-vdc, 40-ma, lamps or their equivalent (DS1 and DS2) (4, Chart 1, 21-00-00).

g. An air temperature gage (M1) or equivalent (13, Chart 1, 21-00-00).

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL h. Connectors that mate with the cabin temperature controller and the air temperature gage. Refer to the Super King Air Series Wiring Diagram Manual for the appropriate part numbers.

DUCT TEMP SENS

9

11

10

12

3

4

CABIN TEMP IND

CABIN TEMP SEL POT

2

HEAT COMM

GROUND

1

COOL COMM

POWER

HYLZ 50336-001

13

14

COOLING

CW

28VDC

TR1

DS 1

R1

R2

R3

DS 2

C D B A

M1

R4

AIR FLOW DIRECTION

FL21B 061251AA.AI

Cabin Temperature Controller Test Circuit Figure 204 CABIN TEMPERATURE CONTROLLER TEST PROCEDURE a. Remove the headliner access panel immediately aft of the forward partition and remove the controller. b. Connect a power supply and test circuit to the cabin temperature controller (Ref. Figure 204). c.

Turn the potentiometer (TR1) fully counterclockwise and turn on the power supply to apply 28 vdc to the controller. The lamp (DS1) should illuminate.

d. Turn the potentiometer (TR1) clockwise until it is approximately mid-position between where DS1starts pulsing on and DS2 starts pulsing on (this is a deadband area and both DS1 and DS2 lights should be extinguished). e. Turn the potentiometer (TR1) counterclockwise until DS1 begins to pulse, then continue to turn until the lamp is illuminated continuously. f.

Turn the potentiometer clockwise until DS1 extinguishes, then continue turning TR1 until DS2 pulses. Continue turning TR1 until the lamp (DS2) illuminates continuously.

g. Turn off the power supply and disconnect the test circuit from the temperature controller. h. Install the controller and ensure the direction of airflow through the control box. i.

If the controller does not perform as described above, the controller may be assumed to be defective and must be replaced.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CABIN TEMPERATURE CONTROLLER REMOVAL (FL-1 THRU FL-492, FL-494 THRU FL499, FM-1 THRU FM-14) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove the headliner access panel, located immediately aft of the cabin forward partition (Ref. Figure 205).

d. Remove the attaching screws from the cabin temperature controller and remove the controller sufficiently to gain access to the electrical connector. e. Remove the electrical connector from the controller. f.

Remove the controller from the airplane.

CABIN TEMPERATURE CONTROLLER INSTALLATION (FL-1 THRU FL-492, FL-494 THRU FL-499, FM-1 THRU FM-14) a. Install the electrical connector on the controller receptacle (Ref. Figure 205). b. Install the controller on the mounting bracket and secure with the attaching screws. c.

Install the headliner access panel to cover the controller.

d. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Cabin Temperature Controller (FL-1 thru FL-492, FL-494 thru FL-499, FM-1 thru FM-14) Figure 205

CABIN TEMPERATURE CONTROLLER REMOVAL (FL-493, FL-500 AND AFTER; FM-15 AND AFTER) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove center aisle floor board (Ref. Item 20, Figure 2, Sheet 4, 06-50-00) to gain access to the cabin temperature controller.

d. Electrically disconnect the cabin temperature controller (Ref. Figure 206). e. Remove the four screws and washers from the cabin temperature controller and remove the controller from the airplane.

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CABIN TEMPERATURE CONTROLLER INSTALLATION (FL-493, FL-500 AND AFTER; FM-15 AND AFTER) a. Place the cabin temperature controller in the installed position and secure using the four screws and washers (Ref. Figure 206). b. Electrically reconnect the cabin temperature controller. c.

Install the center aisle floor board (Ref. Item 20, Figure 2, Sheet 4, 06-50-00).

d. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

CABIN TEMPERATURE CONTROLLER - FUNCTIONAL TEST (FL-493, FL-500 AND AFTER; FM-15 AND AFTER) a. Apply external power (Ref. CONNECTING AND APPLYING EXTERNAL POWER, 24-40-00). b. Place both blower switches in the AUTO position. c.

Place the mode selector switch in the AUTO position. Make sure the blowers are operating.

d. Rotate the temperature control knob from full cold to full hot and back to full cold. If the actual cabin temperature is 60° F to 80° F, the blower speed will adjust as the temperature knobs are rotated. As the selected temperature reaches the actual cabin temperature, the blower speeds should decrease. NOTE: It is normal for the blowers to operate at high speed momentarily and then adjust to a fixed speed according to the temperature selections. If the temperature is above 80° F or below 60° F, the blowers will operate at a fixed speed because of the limited range of the temperature control knob. e. With the mode switch in the AUTO position and the blowers operating in a high speed, move the blower switches from the AUTO position. f.

Rotate the blower control knob and the blower motor speed should vary.

g. The airplane should be flown (or run long enough on the ground) for the environmental system to change the cabin temperature. Blower speeds should reduce as the cabin temperature approaches the temperature set by the temperature control knob. h. Remove external electrical power (Ref. DISCONNECTING EXTERNAL POWER, 24-40-00).

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A

F.S. 179.525 (REF)

F.S. 168.75 (REF)

LH SUPPORT ASSEMBLY (REF)

ANGLE (REF)

RELAY (REF)

K157

K158

SCREW, WASHER (4 PLACES)

K136

SUPPORT (REF)

FORWARD

MOUNTING PLATE

A

DETAIL (VIEW LOOKING DOWN)

CABIN TEMPERATURE CONTROLLER

FL21B 985647AA.AI

Cabin Temperature Controller Installation (FL-493, FL-500 and After; FM-15 and After) Figure 206

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CHAPTER

AUTO FLIGHT

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 22 - AUTO FLIGHT TABLE OF CONTENTS SUBJECT

PAGE 22-10-00

APS-65 Automatic Flight Control System - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Collins Publications List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Miscellaneous Publications List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Aileron Servo. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Rudder Servo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Elevator Servo. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 APS-65 Automatic Flight Control System - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Servo Clutch Torque Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Pinion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Capstan . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Aileron Servo Cable Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Aileron Servo Cable Installation and Rigging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Rudder Servo Cable Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Rudder Servo Cable Installation and Rigging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Elevator Servo Cable Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Elevator Servo Cable Installation and Rigging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 22-10-01 KFC 400 Automatic Flight Control System - Description And Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Bendix/King Publications List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Miscellaneous Publications List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Aileron Servo. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Rudder Servo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Rudder Trim Servo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Elevator Servo. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Elevator Trim Servo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 KFC 400 Automatic Flight Control System - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Servo Clutch Torque Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Aileron Servo Cable Removal (King KFC-400) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Aileron Servo Cable Installation and Rigging (King KFC-400) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Rudder Servo Cable Removal (King KFC-400) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Rudder Servo Cable Installation and Rigging (King KFC-400) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Rudder Trim Tab Servo Cable Installation and Rigging (King KFC-400) . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Elevator Servo Cable Removal (King KFC-400) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Elevator Servo Cable Installation and Rigging (King KFC-400) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Elevator Trim Tab Servo Cable Installation and Rigging (King KFC-400) . . . . . . . . . . . . . . . . . . . . . . . . . . .211

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List of Effective Pages CH-SE-SU

PAGE

DATE

22-LOEP

1

Aug 1/09

22-CONTENTS

1

Aug 1/09

22-10-00

1 thru 4 201 thru 210

Aug 1/09 Aug 1/09

22-10-01

1 thru 3 201 thru 212

Aug 1/09 Aug 1/09

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 22-10-00

APS-65 AUTOMATIC FLIGHT CONTROL SYSTEM - DESCRIPTION AND OPERATION The Collins APS-65 Automatic Flight Control System is certified for use on this airplane. Collins APS-65 integrated flight control system consists of full three axis autopilot and flight director system. As such, it is a combination of sensors, electrical servos, guidance displays, mode selectors and computers which perform the necessary flight computations. The system provides either full autopilot control of the airplane, with simultaneous flight director monitoring when integrated with the flight director system, or manual control by using the pitch and roll command control on the autopilot controller. When the autopilot is disengaged, the pilot assumes control in response to the flight director display steering commands. The yaw axis may be engaged independently of roll and pitch for use as a yaw damper. For maintenance of individual components, refer to the latest revision of the appropriate manual for further information. The following is a list of the various autopilot equipment manuals which may be applicable to the autopilot system installed in the airplane.

COLLINS PUBLICATIONS LIST •

331A-3G Course Indicator Overhaul Manual (Repair) (with illustrated parts list) 331A-3G Course Indicator 523-0762672

•

ADF-60 Automatic Direction Finder Instruction Book (Installation and Repair) ADF-60 Automatic Direction Finding System 523-0766184

•

APC-65/FGC-65 Autopilot Computer and Flight Guidance Computer Instruction Book (Repair) APC-65 Autopilot Computer and FGC-65 Flight Guidance Computer 523-0771868

•

APP-65A Autopilot Panel Instruction Book (Repair) APP-65A Autopilot Panel 523-0771874

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL •

CAD-62 Control Adapter Instruction Book (Repair) CAD-31/CAD-62 Control Adapter 523-0773216

•

EFD-74 Electronic Flight Display Instruction Book (Repair) EFD-74 Electronic Flight Display 523-0772699

•

EFIS-85B (4/14) Electronic Flight Instrument Systems Installation Manual EFIS-85B (4/14) and EFIS-86B (4/14) 523-0775353

•

EHSI-74/74B Electronic HSI System Instruction Book (Installation) EHSI-74/74B Electronic HSI System 523-0772693

•

FIS-84 Flight Instrument System Instruction Book (Installation) FIS-84 Flight Instrument System 523-0768867

•

FIS-85 Flight Instrument System Instruction Book (Installation) FIS-85 Flight Instrument System 523-0769518

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL •

FPA-80 Flight Profile Advisory Instruction Book (Repair) FPA-80 Flight Profile Advisory 523-0769151

•

HCP-74 HSI Control Panel Instruction Book (Repair) HCP-74 HSI Control Panel 523-0772704

•

HPU-74 HSI Processor Unit Instruction Book (Repair) HPU-74 HSI Processor Unit 523-0772709

•

SSS-65 Slip/Skid Sensor Instruction Book (Installation and Repair) SSS-65 Slip/Skid Sensor 523-0771647

•

SVO-65/SMT-65 ( ) Primary Servo and SMT-65 ( ) Servo Mount Instruction Book (Repair) SVO-65 Primary Servo and SMT-65 ( ) Servo Mount 523-0771890

•

SVO-85 ( ) Primary Servo and SMT-85 ( ) Servo Mount SVO-85 ( ) Primary Servo and SMT-85/86/87 ( ) Servo Mount Instruction Book/ Repair Manual 523-0772-563

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MISCELLANEOUS PUBLICATIONS LIST •

UNS1A-JR Long Range Navigation System P/N 2206

AILERON SERVO The aileron servo on the automatic flight control system, certified for use on this airplane, is mounted beneath the cabin center aisle floorboards forward of the aft spar. Cables from the servo capstan are connected to the aileron quadrant regulator. When the autopilot is engaged, the servo rotates, causing aileron deflection in a direction dependent on the direction of servo rotation. NOTE: Improper cable tension may cause unstable or erratic response to autopilot signals.

RUDDER SERVO The rudder servo is located in the tail section aft of the pressure bulkhead. The cable is wrapped around the servo capstan and connected to the main left rudder torque shaft bell crank and the right rudder cable. When the yaw axis is engaged, the servo rotates in response to autopilot signals, causing rudder deflection in a direction dependent upon the direction of servo rotation. NOTE: Improper cable tension may cause unstable or erratic response to autopilot signals.

ELEVATOR SERVO The elevator servo is located in the tail section aft of the pressure bulkhead next to the rudder servo. Cables wrapped around the servo capstan are connected to the primary (up and down) elevator control cables. When the autopilot is engaged, the servo rotates, causing elevator deflection in a direction dependent upon the direction of servo rotation. NOTE: Improper servo cable tension may cause unstable or erratic response to autopilot signals.

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APS-65 AUTOMATIC FLIGHT CONTROL SYSTEM - MAINTENANCE PRACTICES SERVO CLUTCH TORQUE ADJUSTMENT If replacement of the servos or capstans becomes necessary, or if any of the servo clutch torque settings are to be checked, refer to the applicable manufacturer’s instructions for clutch adjustment procedures. Specific torque values are listed below for Collins APS-65H and APS-65J autopilots. PINION Aileron..............................................28.4 + 2/-0 inch-pounds Rudder Servo (APS-65J only)...........23.5 + 2/-0 inch-pounds Elevator Servo...................................7.4 + 1/-0 inch-pounds Elevator Trim.....................................6.0 + 1/-0 inch-pounds CAPSTAN Aileron..............................................165 ± 13 inch-pounds Rudder Servo...................................137 ± 11 inch-pounds Elevator Servo...................................43 ± 3 inch-pounds Elevator Trim.....................................35 ± 1 inch-pounds

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1/16" AILERON AND RUDDER SERVO CABLE TENSION GRAPH 40

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Aileron and Rudder Servo Cable Tension Graph (Collins APS-65) Figure 201

1/16" ELEVATOR SERVO CABLE TENSION GRAPH 40

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Elevator Servo Cable Tension Graph (Collins APS-65) Figure 202

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1/16" ELEVATOR TRIM SERVO CABLE TENSION GRAPH 40

POUNDS OF TENSION

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Elevator Trim Servo Cable Tension Graph (Collins APS-65) Figure 203

AILERON SERVO CABLE REMOVAL a. Remove the cable guards (Ref. Figure 204). b. Loosen the servo cable turnbuckle. c.

Disconnect the aileron cable locking plates from the aileron quadrant regulator by removing the plate attaching screws.

d. Remove the cables from the aileron quadrant. e. Unwrap the cable and disconnect it from the capstan, or remove the capstan from the mounting bracket with the cables attached.

AILERON SERVO CABLE INSTALLATION AND RIGGING NOTE: Before the autopilot control cables can be rigged, the respective flight control primary cables must be rigged (Ref. Chapter 27-10-00). a. Place the aileron in the neutral position and install the rig pins in the quadrant and bell cranks (Ref. Figure 204). b. Attach the cable with the turnbuckle to the upper recess of the capstan and the cable without the turnbuckle to the lower recess of the capstan. c.

Wrap the cables on the capstan as follows:

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 1. Wrap the aileron servo cable with the turnbuckle approximately 1-1/2 turns clockwise on the capstan and attach it to the outboard cable groove for the autopilot on the quadrant regulator with the locking plate and attaching screw. 2. Wrap the aileron servo cable without the turnbuckle approximately 2 turns counterclockwise around the capstan and attach it to the inboard cable groove for the autopilot on the aileron quadrant regulator with the locking plate and attaching screw. d. Install and safety the cable guards. e. Using the turnbuckle, temporarily adjust the aileron servo cable tension to 50 pounds. f.

Remove the rig pins.

g. Move the control surface through full travel several times and make sure cable/clamp clearance is maintained and that no binding exists. h. Using the turnbuckle, adjust the servo cable tension to the tension shown in the tension graph and safety the turnbuckle (Ref. Figure 201). Tension should be measured and adjusted with aileron in neutral position.

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Aileron Servo Cable Installation Figure 204

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RUDDER SERVO CABLE REMOVAL a. Loosen the cable turnbuckle (Ref. Figure 205). b. Disconnect the servo cables from the rudder torque shaft bell crank and from the primary rudder cable by removing the cable clamp and the locking plates and screws. c.

Remove the cable guard pins from the servo.

d. Unwrap and remove the cables from the capstan.

RUDDER SERVO CABLE INSTALLATION AND RIGGING NOTE: Before the autopilot control cables can be rigged, the respective flight control primary cables must be rigged (Ref. Chapter 27-20-00). a. With the rudder in the neutral position, place one rig pin in the front rudder bell crank and another in the rig pin hole in the torque shaft assembly of the aft bell crank (Ref. Figure 205). b. Attach the cables to the capstan. c.

Wrap the servo cables on the capstan as follows: 1. Wrap the cable with the turnbuckle approximately 1-3/4 turns counterclockwise around the capstan and attach it to the primary rudder cable with the cable clamp. 2. Wrap the cable without the turnbuckle 1-3/4 turns clockwise around the capstan and connect it to the rudder torque shaft bell crank with the locking plate and screw.

d. Install the cable guard pins. e. Set the rudder cable tension to approximately twice the required setting indicated by the tension graph (Ref. Figure 201). f.

Remove the rig pins.

g. Move the control surface through full travel several times to make sure cable/clamp clearance is maintained and that no binding exists. h. Using the turnbuckle, adjust the servo cable to the tension shown in the graph and safety the turnbuckle (Ref. Figure 201). Tension should be measured and adjusted with rudder in neutral position.

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Rudder Servo Cable Installation (Collins APS-65) Figure 205

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ELEVATOR SERVO CABLE REMOVAL a. Disconnect the servo cables from the main elevator control cables by removing the clamps and attaching bolts (Ref. Figure 206). b. Remove the cable guard pins from the servo. c.

Unwrap the cables from the capstan and remove the cables.

ELEVATOR SERVO CABLE INSTALLATION AND RIGGING NOTE: Before the autopilot control cables can be rigged, the respective flight control primary cables must be rigged (Ref. Chapter 27-30-00). a. Install one rig pin in the forward bell crank and another in the elevator bell crank. Access to the aft elevator bell crank is through an opening in the skin on the left side of the vertical stabilizer just below the horizontal stabilizer (Ref. Figure 206). b. Attach the servo cables to the capstan. c.

Wrap the cables on the capstan as follows: 1. Wrap the cable with the turnbuckle approximately 1 turn clockwise around the capstan; route the cable through the idler pulley (if installed) and attach it to the main elevator up cable with the cable clamp. 2. Wrap the servo cable without the turnbuckle approximately 3-1/2 turns counterclockwise around the capstan, then route it through the idler pulley (if installed) and attach it to the cable with the cable clamp.

d. Install the cable guard pins. e. Set the elevator servo cable tension at approximately twice the required setting indicated by the graph (Ref. Figure 202). f.

Remove the rig pins.

g. Move the control surface through full travel several times to make sure cable/clamp clearance is maintained with no binding. h. Reinstall the rig pins. i.

Using the turnbuckle, adjust the servo cable to the tension shown in the graph and safety the turnbuckle (Ref. Figure 202).

j.

Remove the rig pins.

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Elevator Servo Cable Installation (Collins APS-65) Figure 206

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KFC 400 AUTOMATIC FLIGHT CONTROL SYSTEM - DESCRIPTION AND OPERATION The King KFC 400 Automatic Flight Control System is certified for use on this airplane. The King KFC 400 integrated flight control system consists of full three axis autopilot and flight director system. As such, it is a combination of sensors, electrical servos, guidance displays, mode selectors and computers which perform the necessary flight computations. The system provides either full autopilot control of the airplane, with simultaneous flight director monitoring when integrated with the flight director system, or manual control by using the pitch and roll command control on the autopilot controller. When the autopilot is disengaged, the pilot assumes control in response to the flight director display steering commands. The yaw axis may be engaged independently of roll and pitch for use as a yaw damper. For maintenance of individual components, refer to the latest revision of the appropriate manual for further information. The following is a list of the various autopilot equipment manuals which may be applicable to the autopilot system installed in the airplane.

BENDIX/KING PUBLICATIONS LIST •

EFIS 10A Electronic Flight Instrument System 006-05992-003

•

KA44/KA44B ADF Loop Sense Antenna 006-05535-0003

•

SG-101B Symbol Generator 006-05305-0000

•

KRG-350 Yaw Rate Gyro 006-05119-0000

•

KFC-400 Autopilot Flight Director System 006-05668-0000

•

KVG-350 Vertical Gyro 006-05199-0000

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KCP-420 AP/FD Computer Adapter Module 006-05664-0000

•

KAV-485 ALT/VSI Indicator 006-05650-0001

•

KPI-552/KPI-553 HSI 006-05601-0001

•

KCU-567/KCU-568 Control Display Long Range Nav System 006-05645-0002

•

KDL Data Loader 006-05616-0001

•

KDF-806 ADF Receiver 006-05511-0004

MISCELLANEOUS PUBLICATIONS LIST •

UNS1A-JR Long Range Navigation System P/N 2206

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AILERON SERVO The aileron servo on the automatic flight control system, certified for use on this airplane, is mounted beneath the cabin center aisle floorboards forward of the aft spar. Cables from the servo capstan are connected to the aileron quadrant regulator. When the autopilot is engaged, the servo rotates, causing aileron deflection in a direction dependent on the direction of servo rotation. NOTE: Improper cable tension may cause unstable or erratic response to autopilot signals.

RUDDER SERVO The rudder servo is located in the tail section aft of the pressure bulkhead. The cable is wrapped around the servo capstan and connected to the main left rudder torque shaft bell crank and the right rudder cable. When the yaw axis is engaged, the servo rotates in response to autopilot signals, causing rudder deflection in a direction dependent upon the direction of servo rotation. NOTE: Improper cable tension may cause unstable or erratic response to autopilot signals.

RUDDER TRIM SERVO The rudder trim servo is located in the tail section aft of the pressure bulkhead. The rudder trim cable is wrapped around the servo capstan, idler pulley and the rudder trim tab actuator pulley. When the yaw axis is engaged, the servo rotates in response to autopilot signals, causing rudder tab deflection in a direction dependent upon the direction of servo rotation. NOTE: Improper cable tension may cause unstable or erratic response to autopilot signals.

ELEVATOR SERVO The elevator servo is located in the tail section aft of the pressure bulkhead next to the rudder servo. Cables wrapped around the servo capstan are connected to the primary (up and down) elevator control cables. When the autopilot is engaged, the servo rotates, causing elevator deflection in a direction dependent upon the direction of servo rotation. NOTE: Improper servo cable tension may cause unstable or erratic response to autopilot signals.

ELEVATOR TRIM SERVO The elevator trim servo is located in the tail section aft of the pressure bulkhead forward of the rudder and elevator servos. The elevator trim cable is wrapped around the servo capstan, idler pulley and the elevator trim tab actuator pulleys. When the autopilot is engaged, the servo rotates, causing elevator tab deflection in a direction dependent upon the direction of servo rotation. NOTE: Improper servo cable tension may cause unstable or erratic response to autopilot signals.

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KFC 400 AUTOMATIC FLIGHT CONTROL SYSTEM - MAINTENANCE PRACTICES SERVO CLUTCH TORQUE ADJUSTMENT If replacement of the servos or capstans becomes necessary, or if any of the servo clutch torque settings are to be checked, refer to the applicable manufacturer’s instructions for clutch adjustment procedures. Specific torque values are listed below for King KFC 400 autopilot. Aileron..............................................76.0 ± 9 inch-pounds Rudder Trim......................................43.0 ± 4 inch-pounds Rudder Servo..................................135.0 ± 10 inch-pounds Elevator Servo..................................29.0 ± 3 inch-pounds Elevator Trim....................................43.0 ± 4 inch-pounds

1/16" AILERON, RUDDER AND ELEVATOR SERVO CABLE TENSION GRAPH 40

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Aileron, Rudder and Elevator Servo Cable Tension Graph (King KFC 400) Figure 201

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1/16" RUDDER TRIM SERVO CABLE TENSION GRAPH 40

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Rudder Trim Servo Cable Tension Graph (King KFC 400) Figure 202

1/16" ELEVATOR TRIM SERVO CABLE TENSION GRAPH 40

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AILERON SERVO CABLE REMOVAL (KING KFC-400) a. Remove the cable guards from the aileron servo capstan (Ref. Figure 204). b. Loosen the servo cable turnbuckle. c.

Disconnect the aileron cable locking plates from the aileron quadrant regulator by removing the plate attaching screws.

d. Remove the cables from the aileron quadrant. e. Unwrap the cable and disconnect it from the capstan, or remove the capstan from the mounting bracket with the cables attached.

AILERON SERVO CABLE INSTALLATION AND RIGGING (KING KFC-400) NOTE: Before the autopilot control cables can be rigged, the respective flight control primary cables must be rigged (Ref. Chapter 27-10-00). a. Place the aileron in the neutral position and install the rig pins in the quadrant and bellcranks. Refer to the Chapter 27-10-00 AILERON CONTROL SYSTEM illustration for the location of the rig pin holes. b. Move the capstan to the middle of its travel (Ref. Figure 204). c.

Attach the two cables to the aileron capstan using the two attaching screws and lockwashers. The cable with the turnbuckle attaches to the right side of the capstan.

d. Wrap the cables on the capstan as follows: 1. Wrap the aileron servo cable without the turnbuckle approximately 1-1/2 turns counterclockwise around the upper half of the capstan and attach it to the inboard cable groove for the autopilot cable on the aileron quadrant regulator with the locking plate and screw. 2. Wrap the aileron servo cable with the turnbuckle approximately 1-1/2 turns clockwise on the lower 1/2 of the capstan and attach it to the outboard cable groove for the autopilot on the quadrant regulator with the locking plate and screw. e. Install and safety the cable guards. f.

Using the turnbuckle, temporarily adjust the aileron servo cable to a tension of 50 pounds.

g. Remove the rig pins. h. Move the control surface through full travel several times and make sure cable/clamp clearance is maintained with no binding. i.

Using the turnbuckle, adjust the servo cable to the tension shown in the graph and safety the turnbuckle (Ref. Figure 201). Tension should be measured and adjusted with the aileron in the neutral position.

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Aileron Servo Cable Installation (King KFC-400) Figure 204

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RUDDER SERVO CABLE REMOVAL (KING KFC-400) a. Loosen the cable turnbuckle (Ref. Figure 205). b. Disconnect the servo cables from the rudder torque shaft bell crank and from the primary rudder cable by removing the cable clamp and the locking plates and screws. c.

Remove the cable guard pins from the servo.

d. Unwrap and remove the cables from the capstan.

RUDDER SERVO CABLE INSTALLATION AND RIGGING (KING KFC-400) NOTE: Before the autopilot control cables can be rigged, the respective flight control cables must be rigged (Ref. Chapter 27-20-00). a. With the rudder in the neutral position, place one rig pin in the front rudder bellcrank and another in the rig pin hole in the torque shaft assembly of the aft bellcrank. Refer to the Chapter 27-20-00 RUDDER CONTROL SYSTEM illustration for the location of the rig pin holes. b. Place the rudder servo capstan in the center of its travel (Ref. Figure 205). c.

Attach the cable with the turnbuckle to the upper position on the capstan.

d. Attach the cable without the turnbuckle to the lower position on the capstan. e. Wrap the servo cables on the capstan as follows: 1. Wrap the cable without the turnbuckle 1-1/2 turns clockwise around the servo capstan and connect it to the rudder torque shaft bellcrank with the locking plate and screw. 2. Wrap the cable with the turnbuckle 1-1/2 turns counterclockwise around the capstan and attach it to the primary right rudder cable with the cable clamp. f.

Install the cable guard pins.

g. Using the turnbuckle, temporarily adjust the rudder servo cable to 50 pounds of tension. h. Remove the rig pins. i.

Move the control surface through full travel several times and make sure cable/clamp clearance is maintained with no binding.

j.

Using the turnbuckle, adjust the servo cable to the tension shown in the graph and safety the turnbuckle (Ref. Figure 201). Tension should be measured and adjusted with the rudder in the neutral position.

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RUDDER TRIM TAB SERVO CABLE INSTALLATION AND RIGGING (KING KFC-400) a. Install the rudder tab cable as instructed in Chapter 27-20-00, except that the cable must be routed around the idler pulley and capstan (Ref. Figure 206). b. Using the turnbuckle, adjust the rudder trim servo cable to the tension shown in the graph and safety the turnbuckle (Ref. Figure 202). Tension measurement and adjustment should be made with the rudder and trim tab in the neutral position.

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Rudder Trim Tab Servo Cable Installation (King KFC-400) Figure 206

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ELEVATOR SERVO CABLE REMOVAL (KING KFC-400) a. Disconnect the servo cables from the main elevator control cables by removing the clamps and attaching bolts (Ref. Figure 207). b. Remove the cable guard pins from the servo. c.

Unwrap the cables from the capstan and remove the cables.

ELEVATOR SERVO CABLE INSTALLATION AND RIGGING (KING KFC-400) NOTE: Before the autopilot control cables can be rigged, the respective flight control primary cables must be rigged (Ref. Chapter 27-30-00). a. Install one rig pin in the forward bellcrank and another in the aft elevator bellcrank. Access to the aft elevator bellcrank is through an opening in the skin on the left side of the vertical stabilizer just below the horizontal stabilizer. Refer to the Chapter 27-30-00 ELEVATOR CONTROL SYSTEM illustration for the location of the rig pin holes. b. Attach the servo cables to the capstan (Ref. Figure 207). c.

Wrap the cables on the capstan as follows: 1. Wrap the lower cable 1-1/2 turns counterclockwise. 2. Wrap the upper cable 1-1/2 turns clockwise.

d. Install the cable guard pins. e. Using the turnbuckle, temporarily adjust the elevator servo cable to 50 pounds of tension. f.

Remove the rig pins.

g. Move the control surface through full travel several times to make sure cable/clamp clearance is maintained with no binding. h. Reinstall the rig pins. i.

Using the turnbuckle, adjust the servo cable to the tension shown in the graph and safety the turnbuckle (Ref. Figure 201).

j.

Remove the rig pins.

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Elevator Servo Cable Installation (King KFC-400) Figure 207

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ELEVATOR TRIM TAB SERVO CABLE INSTALLATION AND RIGGING (KING KFC-400) a. Install the elevator tab cable as instructed in Chapter 27-30-00 except that the cable must be routed around the idler pulley and capstan (Ref. Figure 208). b. Using the turnbuckle, adjust the elevator trim tab servo cable to the tension shown in the graph and safety the turnbuckle (Ref. Figure 203). Tension measurement and adjustment should be made with the elevator pined in neutral and the tab in the neutral position. Remove rig pins when adjustment is completed.

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Elevator Trim Tab Servo Cable Installation (King KFC-400) Figure 208

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COMMUNICATIONS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 23 - COMMUNICATIONS TABLE OF CONTENTS SUBJECT

PAGE 23-00-00

Communications - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Communications - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Controller Removal from the Radio Instrument Panel. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Controller Installation in the Radio Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 COMM, NAV, ADF, Transponder, etc. Antennas Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 COMM, NAV, ADF, Transponder, etc. Antennas Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Antenna Bonding Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 23-30-00 Passenger Address System - Description And Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 23-40-00 Interphone - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Ground Interphone System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Interphone - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Interphone Amplifier Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Interphone Amplifier Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 23-60-00 Static Discharging - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Static Discharging - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flight Surface and Winglet Static Discharger Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flight Surface and Winglet Static Discharger Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Main Landing Gear Static Discharger Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Main Landing Gear Static Discharger Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Inspection of Static Dischargers (Wicks) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202

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CHAPTER 23 - COMMUNICATIONS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 23-70-00

Cockpit Voice Recorder - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Cockpit Voice Recorder (FL-114 and After; FM-9 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Cockpit Voice Recorder Readout Procedure (FL-114 and After; FM-9 and After). . . . . . . . . . . . . . . . . . . . . . . 1 Cockpit Voice Recorder Readout Procedure (FL-289 and After; FM-9 and Prior Airplanes With Kit No. 130-3407-1 Installed) . . . . . . . . . . . . . . . . . . . . . . . 1 Cockpit Voice Recorder - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cockpit Voice Recorder Control Unit Removal (FL-114 and After; FM-9 and After) . . . . . . . . . . . . . . . . . . . 201 Cockpit Voice Recorder Control Unit Installation (FL-114 and After; FM-9 and After). . . . . . . . . . . . . . . . . . 201 Cockpit Voice Recorder Microphone Removal (FL-114 and After; FM-9 and After) . . . . . . . . . . . . . . . . . . . 201 Cockpit Voice Recorder Microphone Installation (FL-114 and After; FM-9 and After) . . . . . . . . . . . . . . . . . . 201 Cockpit Voice Recorder Removal (FL-114 and After; FM-9 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Cockpit Voice Recorder Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Impact Switch Removal (FL-114 and After; FM-9 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Impact Switch Installation (FL-114 and After; FM-9 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 206 Cockpit Voice Recorder (CVR-A100S) Operational Test (FL-114 and After; FM-9 and After) . . . . . . . . . . . 206 Cockpit Voice Recorder (CVR-30B) Operational Test (FL-187 and After; FM-9 and After). . . . . . . . . . . . . . 206 Cockpit Voice Recorder (CVR-FA2100) Operational Test (FL-289 and After and Prior Airplanes With Kit No. 130-3407-1 Installed) . . . . . . . . . . . . . . . . . . . . . . . . . . 207 Underwater Locator Beacon Functional Test. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 208

Page 2 Feb 1/10

23-CONTENTS

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

23-LOEP

1

May 1/10

23-CONTENTS

1 and 2

Feb 1/10

23-00-00

1 thru 3 201 thru 203

May 1/07 May 1/07

23-30-00

1

Feb 1/10

23-40-00

1 201

May 1/08 May 1/08

23-60-00

1 and 2 201 and 202

May 1/08 May 1/10

23-70-00

1 and 2 201 thru 208

May 1/08 May 1/08

A28

23-LOEP

Page 1 May 1/10

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

COMMUNICATIONS

DESCRIPTION AND OPERATION

on the following pages are typical of the installations used in the airplane. Because equipment and installations, your airplane may differ somewhat from the illustrations, approximate locations of components as shown may be beneficial during maintenance operations. For more specific information applicable to individual airplanes, refer to the Hawker Beechcraft Corporation Avionics Wiring Diagrams and to the appropriate supplier equipment operators manuals which are furnished with each airplane.

The communications installations of the many variations of however, reference to the

For maintenance of the individual

components, refer

to the LATEST revision of the

appropriate

list of the various communication manuals which may be following communication systems installed in the airplane. information. The

is

a

I

manual for further

applicable

to the

DB SYSTEMS PUBLICATIONS LIST P/N 218-16

Passenger Speaker Amplifier Equipment

P/N 600-16

Aural

P/N 418-16

Audio Control

Warning

Tone Generator

Manual

Equipment Manual

Amplifier

COLLINS PUBLICATIONS LIST P/N 523-0772864

HF-230

High-Frequency

Communication

System

Instruction Book

(Installation)

Volume I

P/N 523-0772868

HF-230

High-Frequency

Communication

System

Instruction Book

(Installation)

Volume II

WULFSBERG PUBLICATIONS LIST P/N 150-0119-000

Flitefone VI Manual

SP~CIAL TOOLS AND RECOMMENDED MA TERIALS special tools and recommended materials listed in Charts I and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically prescribed by Hawker Beechcraft Corporation. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used. The

n2i

23-00-00Page

1

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 1

Special Tools TOOL NAME 1.

ULB Portable Test Set

and

PART NO.

TS100

Equipment SUPPLIER

Dukane

Corporation,

USE Check ULB

St. Charles, IL 60174 2.

CVRTest Panel

9300A860

L-3 Communications

Corporation

Aviation

Check CVR

Recorders,

P.O. Box 3041, Sarasota, FL 34230 3.

CVRAudio Monitor

17TES0200

Adapter

L-3 Communications

Corporation

Check CVR

Aviation Recorders,

P.O. Box 3041, Sarasota, FL 34230 4.

Megohmmeter

2471 F Tester

Barfield Instrument

Corporation,

Check Static Wicks

1478 Central Avenue, Atlanta, GA 39344 5.

*CVRTestSet

1623-01

Universal Avionics

System Corp.

Check CVR

3260 E Lerdo Road,

Tucson, AZ 85706 6.

*ULBTestSet

1623-1

Universal Avionics

System Corp.

Check ULB

3260 E Lerdo Road,

Tucson, AZ 85706 7.

*CVRAudio Monitor

RS232C

Universal Avionics

Adapter 8.

System Corp.

Check CVR

3260 E Lerdo Road, Tucson, AZ 85706

**CVR Portable

17TES0043

Interface

L-3 Communications

Corporation

Aviation

Play

back recorded data

Recorders,

P.O. Box 3041,

Sarasota, FL 34230 9.

**CVR

SystemTest

9300A860

Panel

L-3 Communications

Corporation

Aviation

Check CVR

Recorders,

P.O. Box 3041, Sarasota, FL 34230 10. **Cable

Assembly

024E1122-00

L-3 Communications

Corporation

Check CVR

Aviation Recorders,

P.O. Box 3041,

Sarasota, FL 34230 11. **ULB Ultrasonic Test

15977

Dukane

Set

*For airplanes using the CVR30B Cockpit Voice Recorder For airplanes using the FA2100CVR 130-3407-1 installed)

Page

yaM2

1/07

Corp.,

Seacom Division

Check ULB

St. Charles, IL. 60174 Ph. (630) 584-2300

23-00-00

Cockpit

(FL-187

Voice Recorder

and after, FM-9 and

(FL-289

after).

and after and serials with Kit No.

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 2 Recommended Materials

MATERIAL

PRODUCT

SPECIFICATION

SUPPLIER

MIL-C-38736

Obtain

locally

Obtain

locally

1.

Solvent

2.

Sealer

3.

Chemical

MIL-DTL-81706

Alodine 1200, 1200S,

Parker and Amchem, Inc.

Conversion

per MIL-DTL-5541

1201, 1203 and 600

32100

EC1239

Coating 4.

A22

Solvent

I

Stephenson Highway, Heights, MI 48071

Madison TT-T-548

Toluol

(Toluene)

Obtain

locally

23-00-00

May

1 07Page

3

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

COMMUNICATIONS- MAINTENANCE PRACTICES CONTROLLER REMOVAL FROM THE RADIO INSTRUMENT PANEL All of the

COMM, NAV, ADF, TRANSPONDER, etc. controllers in the radio instrument panel may be removed

as

follows: a.

Remove all electrical power from the

b.

Loosen the three

c.

Pull the controller out of the radio

panel

NOTE:

to

d.

Use

captive alien-head

padding

as

required

Remove the controller from the

airplane. screws

which

secure

the controller to the radio

panel.

and disconnect the electrical connector.

prevent marring the finish of the radio

or

instrument

panels.

airplane.

CONTROLLER INSTALLA TION IN THE RADIO INSTRUMENT PANEL NOTE:

Use

padding

as

required

to

a.

Position the controller

b.

Slide the controller into

c.

Tighten

d.

Restore electrical power to the

near

prevent marring the finish of the radio

the radio

position

panel

in the radio

the fasteners in the controller to

or

instrument

panels.

and connect the electrical connector to the controller.

panel.

secure

the controller to the radio

panel.

airplane.

COMM, NAV, ADF, TRANSPONDER, ETC. ANTENNAS REMOVAL NOTE:

Nearly

Refer to

Figure

201 for

typical

antenna locations.

all the antennas may be removed in the

following

a.

Remove all electrical power from the

b.

Remove the

c.

Carefully

d.

Disconnect the coaxial cable from the antenna and

e.

Remove the antenna from the

attaching

I manner:

airplane.

hardware from around the antenna base.

break the seal between the antenna and the

airplane

secure

skin surface.

the cable

so

it will not fall into the antenna

opening.

airplane.

COMM, NAV ADF, TRANSPONDER, ETC. ANTENNAS INSTALLATION a.

Ensure that all electrical power is off.

b.

Perform antenna

c.

Connect the coaxial connector to the antenna and position the antenna for installation

d.

Secure the antenna to the

e.

Restore electrical power to the

nit

bonding procedures

airplane

as

outlined under ANTENNA BONDING PROCEDURES.

skin with the

attaching

(Ref. Figure 201).

hardware.

airplane.

23-00-00

PMa gyB:l~:May

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/8300C SERIES MAINTENANCE MANUAL

ANTENNA BONDING PROCEDURES NOTE: The

pattern and efficiency of an antenna is dependant upon a low impedance (2) path to the ground plane. imperative that a uniform resistance and capacitance be maintained between the contacting surface of the antenna and the surface on which it is mounted. The mating surface between the antenna and the base must be smooth and contoured to match, keeping the mating surfaces in actual contact. It is

a.

b.

Determine the contact

Using

solvent

(1

area

Chart 2,

of the antenna to be mounted.

23-00-00) clean all grease, oil and other nonconductive films from the contact surfaces mounting surface of the fuselage.

of the antenna, spacer and the WARNING: Use solvent c.

a

Chart 2,

23-00-00)

CAUTION: Do not

and

use

surfaces

area.

with fine garnet paper or silicon aluminum surface may be cleaned with should then be brushed clean and wiped with solvent

contacting

by sanding

area

and

polishing

on an

clean cloth.

a

emery

or

iron oxide

paperlcloth

in

removing

nonsoluble films from the contact

Apply chemical conversion coating (3, Chart 2, 23-00-00) to the area with applicator. Keep the area wet for 5 minutes or until the film develops. WARNING: Use rubber

Using

f.

Allow the

a

area

time exceeds Attach

a

sealer

(2,

to

thoroughly dry for

one

Chart 2,

torquing

to neutralize and

area

maximum of

area

with

Any

one

coating

excess

hour

prior to

length

screws.

All

pad,

sponge

or

equivalent

excess

installation of the

coating.

mating parts.

If the

coaxial cable should be stored inside the

screws

Change

should be

in

through

length

airplane. Apply

the skin.

could affect

uniformly torqued.

system operation.

Refer to Chapter 20-01-00

information.

If the

screws are

Seal around the entire

j.

Retouch the

painted

not

uniformly torqued,

periphery

area

the radiation

of the antenna with sealer

around the antenna

20223-00-00

as

drying

and neutralize with water.

of any coaxial cable. A

attaching

the

remove

around the coaxial cable where it passes

23-00-00)

i.

Page

a

coaxial cable to the antenna.

Install the antenna with the

NOTE:

wash the

hour, retouch the

CAUTION: Do not alter the

for

gently

clean

a

area.

alodine.

gloves when handling

low pressure water,

e.

h.

ventilated

adequately

an

not to remove excessive metal. Small areas

care

stainless steel wire brush. The

(1,

g.

in

Clean nonsoluble films from the

carbide, taking

d.

only

required.

pattern of the

(2,

Chart 2,

antenna may be affected.

23-00-00).

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

----L~-----L--

~WEATHER !INSIDE

RADAR

ANTENNA

------i-

RADOME)

r

COMM

ANTENNA COMM

ANTENNA

:U

ii

o~ev ~O Ci

~41O

r 11

Y

I

f

:i

NAV

i

ANTENNA

ANTENNk DME #I ~TC L& R TRANSPONDER ANT NNAS RADIO ALTIMEIER ANTENNA ANTENNA ALTIMETER ANTENNA

I

L

COMM VHF ANTENNA ANTENNA DME MARKER BEACON ANTENNAS ANTENNAS

i

GLIDESLOPE (INSIDE RADOME!

STANDARD

AVIONICS

350-490-024

ANTENNA

C

INSTALLATION

Standard Avionics Antenna Installation

Figure

201

ORIGINAL As Received BY ATP

A22

23-00-00May

1107

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 23-30-00

PASSENGER ADDRESS SYSTEM - DESCRIPTION AND OPERATION The passenger address system provides audio links between the flight crew and the passengers to ensure their safety and comfort. The passenger address system provides the passengers with various flight information as provided by the flight crew. The dB Systems Model 240 Passenger Speaker Amplifier is a rack mounted unit located in the top left nose avionics shelf. In addition to paging functions, it provides Seat Belt and No Smoking sign chimes tones. It also powers both left and right speaker amplifier channels. There is one dB Systems Model 700 audio control amplifier for each pilot station. The audio control amplifiers are also rack-mounted units located in the left nose avionics bay. The Audio Control Panel (ACP) continuously reads the status of all audio control switches and settings of potentiometers and compiles this information into the form of a digital signal. The digital signal is sent to the Model 700 amplifier. The Model 700 amplifier receives the signal, demultiplexes this signal, and converts it into audio control information. Receiver, sidetone, headphone, interphone, and speaker audio and all operating modes are electronically switched and controlled by the signal from the ACP. The speakers produce amplified Seat Belt and No Smoking sign chime tones and cabin paging. Audio signals to the speakers are routed from both cockpit Audio Control Panels. On airplane serials FL-601, FL-672, FL-688 and After With Cabin Management System Installed, the output of the passenger address system is fed to the cabin speakers and through the CABIN MANAGEMENT SYTEM (Ref. Airplane Maintenance Manual Supplement, Chapter 23-30-03) to the passenger headphones.

A27

23-30-00

Page 1 Feb 1/10

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INTERPHONE

DESCRIPTION AND OPERATION

GROUND INTERPHONE SYSTEM microphone jacks are located on the nose landing gear landing light bracket to provide ground personnel outside of the airplane and inside the crew compartment. The ground interphone system is wired through the hot battery bus and turned on automatically when a headset and microphone are plugged into the jacks on the nose landing gear. The ground interphone system has its own amplifier located on the top shelf in the nose avionics compartment. the airplane’s standard crew compartment headset and microphone can be used by personnel. When the avionics master switch is turned on, the ground interphone is automatically turned Headset and

communication between

off. When the

airplane

ground, operation

leaves the

prevent interference with the

the

ground interphone system

is deactivated

of other avionics systems while the

airplane

by the right squat flight.

switch to

is in

23-40-00

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INTERPHONE

MAINTENANCE PRACTICES

INTERPHONE AMPLIFIER REMOVAL the left

avionics compartment panel.

a.

Open

b.

Disconnect the electrical

wiring

c.

Remove the four

and washers from the

d.

Remove the

nose

screws

from the

amplifier

mounted

on

the top shelf.

amplifier flange.

from the avionics shelf.

amplifier

INTERPHONE AMPLIFIER INSTALLA TION in

a.

Place the

b.

Install the four

c.

Connect the electrical

d.

Close and fasten the left

aas

amplifier

position

screws

on

the top avionics shelf.

and washers in the

wiring

to the

nose

flange

of the

amplifier.

amplifier.

avionics

compartment panel.

23-40-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STATIC DISCHARGING A static electrical

retained, an

may build up on the surface of the airplane while it is in flight. This electrical charge, if interference in radio, avionics and electrical equipment operation. Static buildup can also effect

charge

can cause

uncomfortable

DESCRIPTION AND OPERATION

discharge through personnel disembarking from the airplane after landing; therefore, static on the airplane to dissipate the static electrical charge. Two static dischargers are installed

installed

dischargers on each winglet, three on each aileron, three on tip, one each on the horizontal stabilizer forward and left hand main landing gear (Ref. Figure 1). are

each elevator, four and aft bullet,

on

one on

the rudder,

one on

the ventral fin and

each horizontal stabilizer

one

each

on

the

right

hand

dischargers installed on the forward bullet and the tips of the horizontal stabilizer are 4 inches in length. dischargers installed on the horizontal stabilizer aft bullet, ventral fin, rudder, elevators, ailerons and winglets are 6.37 inches in length. The static dischargers installed on the right hand and left hand main landing gear assembly are short wire cable assemblies 10.20 inches in length.

The static

The static

NOTE: To

ensure

the best

dischargers

possible function

dischargers, the resistance between the base of the static discharger is attached must be less than .0100 ohms, and surfaces on which static dischargers are installed and the airplane

of the static

and the surface to which each static

the resistance between the

flight

control

structure must be less than .0025 ohms.

23-60-00

May

1/OSPage

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ORIGINAL By

As Received

ATP

L.O INCH STATIC DISCHA~GEF;

6.37

INCH STATIC DISCHARGE~S

DETAIL

B

i

II

ii 10.2 INCH STATIC DISCHARGER MAIN LANDING GEAR

[CABLE ASSEMBLY) [TVPICAL 2 PLACES)

R

6.37 INCH STATIC DISCHARG~RS (TYPICAL 5 PLAeESI

DETAIL

4.0 INCH STATIC DTSCHARGER

A

I

5.37 INCH STATIC OISCHARGERS 7 PLACES! (TYPICA!

B STATIC OISC~ARGER

(IYPICAL)

A b

37

INCH

STATIC

4.0 INCH STATIC DISCHARGER

D~SCHARGERS (iYFICAL

5

PLACES)

C34FL2JB1402 C

Static

Discharger Figure

Page

2~’ms

23 II60I00

Installation 1

A24

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 23-60-00

STATIC DISCHARGING - MAINTENANCE PRACTICES FLIGHT SURFACE AND WINGLET STATIC DISCHARGER REMOVAL a. Static dischargers may be removed by turning the threaded discharger assembly counterclockwise until it is disconnected from the base. The static discharger bases should remain attached to the airplane and need not be removed. b. If the static discharger is to be reinstalled, do not discard the lock washer installed on each static discharger.

FLIGHT SURFACE AND WINGLET STATIC DISCHARGER INSTALLATION NOTE: When installing new static discharger assemblies, discard the locknut which is installed on each new static discharger assembly. This locknut is used merely as a retainer nut to make sure against loss of the lock washer. a. To make sure of proper functioning of the static dischargers, all threaded connections should be cleaned with Toluene (Item No. 4, Chart 2, 23-00-00) prior to installation of the static dischargers. b. To install the static dischargers, insert the threaded connection, with the lock washer installed, into the base and turn clockwise until the lock washer is compressed.

MAIN LANDING GEAR STATIC DISCHARGER REMOVAL NOTE: The static dischargers are attached to a bracket which is attached to the landing gear assembly by a bolt passing through the axle assembly. a. Cut the safety wire connected to the static discharger and the two static discharger attaching nuts. b. Loosen and remove the static wick nut on the top of the bracket which is attached to the axle assembly. c.

Remove the static discharger from the bracket.

MAIN LANDING GEAR STATIC DISCHARGER INSTALLATION a. If necessary, prepare the static discharger attach bracket for proper electrical bonding as instructed in Chapter 20-03-00. b. If necessary, install a nut on the threads of the static discharger. c.

Insert the static discharger threaded end into the attaching bracket.

d. Install a nut on the threads of the static discharger. e. Adjust the static discharger attaching nuts so that the end of the static discharger is 9.1 inches from the bottom of the attaching bracket. f.

Tighten the static discharger attaching nuts.

g. Install safety wire through the static discharger and attaching nuts as instructed in Chapter 20-03-00.

A28

23-60-00

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL INSPECTION OF STATIC DISCHARGERS (WICKS) The static dischargers should be inspected at the interval specified in Chapter 5-00-00 or when there is a noticeable static build-up from precipitation and any time there is a lightning strike. This will make sure of proper discharging capabilities. Check the static dischargers using a megohmmeter with a minimum test voltage of 500 volts to measure resistance of the static dischargers. Test voltages of less than 500 volts will not generate a sufficient leakage rate to provide an accurate reading. NOTE: To make sure of the best possible functioning of the static dischargers, the resistance between the base of the static discharger and the surface to which each static discharger is attached must be less than 0.0100 ohms. The resistance between the flight control surface on which the static discharger is attached and the airplane structure must be less than 0.0025 ohms. The rudder protuberance bonding should be measured from the static wick base to the skin of the protuberance. If the rudder is painted, it is acceptable to measure bonding from one wick base to the other static wick base. The winglet mounted static dischargers should have a resistance of less than 20 ohms between the base of the static dischargers and the central ground (spar). Check the static dischargers using the following procedure: CAUTION: Electrical shock can result if the megohmmeter is improperly used. Refer to the applicable manufacturer’s operating handbook for proper operating procedures. a. Connect a test lead from the megohmmeter to the tip of the static discharger. b. Connect the other test lead from the megohmmeter to the base of the static discharger. c.

Place the megohmmeter power switch to ON and observe meter indication. A reading of between 1 - 100 megohms indicates the static discharger is satisfactory. A reading of less than 1 or in excess of 100 megohms indicates the static discharger is unsatisfactory and must be replaced.

d. Place the megohmmeter power switch to OFF and disconnect the test leads from the static discharger tip and its base.

Page 202 May 1/10

23-60-00

A28

Hawker Beechcraft

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SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

COCKPIT VOICE RECORDER COCKPIT VOICE RECORDER

DESCRIPTION AND OPERATION

(FL-114 AND AFTER; Fllll-9 AND AFTER)

three different models of Cockpit Voice Recorders used on the airplane (Ref. Figure 1). CVR-A100S is airplane serials FL-114 and after and FM-9 and after; CVR-30B is used on airplane serials FL-187 and after and FM-9 and after and FA2100CVR is used on airplane serials FL-289 and after and prior airplanes with Kit No. 130-3407-1 installed. The cockpit voice recorder (CVR) is on any time the airplane power is on. The CVR-A100S and CVR-30B have 4 channels capable of storing the last 30 minutes of conversation at all times. The CVR-30B and CVR-FA2100 are also capable of storing other data such as; Greenwich Mean Time (GMT) and CVR internal Built In Test Equipment (BITE) or (BIT) status. The CVR-FA2100 is a 6-channel recorder capable of storing 120minutes of conversation at all times, and the (BIT) system continuously monitors itself for fault conditions. All three CVR’s have an impact switch which will shut off the recorder on impact. This prevents the recorder from recording There used

over

are

on

the last conversation before

impact.

The

cockpit voice recorder microphone is mounted in the glareshield to the right of the centerline in front of the copilot. The control unit for the cockpit voice recorder is mounted in the pedestal extension. The control unit consists of a headset jack, test switch, erase switch and test circuit meter. With the airplane on the ground, the erase switch may be used to

The

cockpit

erase

what is stored in the recorder.

voice recorder and

impact

switch

are

located

time the

the avionics shelves aft of the aft pressure bulkhead. light on the switch should illuminate to indicate that the

on

Any impact switch has been activated, the indicator reset button needs to be depressed.

an underwater locator beacon (ULB). The ULB is water-activated. This ULB is battery operated with a service life as indicated in Chapter 5-11-00. The actual operating life of the batteries is at least 30 days. The expiration date for the batteries is noted on the front panel. The ULB must be functionally tested as indicated in Chapter 5-1 1-00 to ensure proper operation. Whether in the airplane or the shop, a portable test set (Item 1, Chart 1, 23-00-00), (Item 6, Chart 1,23-00-00) or (Item 11, Chart 1, 23-00-00) should be used to test the ULB. For ULB model DK100 if the battery life has expired or other maintenance is indicated, the ULB must be removed from the CVR and returned to Dukane for service no maintenance on the ULB is required or allowed in the field. ULB model DK120 has a user replaceable battery, for other maintenance the ULB must be removed from the CVR and returned to Dukane for service. (Loral will not service the ULB).

Attached to the front of the CVR is

For

more

information refer to the Hawker Beechcraft

Corporation King

Air Series

Component

Maintenance Manual.

COCKPIT VOICE RECORDER READOUT PROCEDURE

(FL-I

14 AND

AFTER; FM-9 AND AFTER)

The CVR cannot download while mounted in the

1, 23-00-00)

and monitor

airplane. A test panel (Item 2, Chart 1, 23-00-00) or (Item 5, Chart 23-00-00) or (Item 7, Chart 1, 23-00-00) are required to access

3, Chart 1,

adapter (Item shop.

the individual CVR channels in the

COCKPIT VOICE RECORDER READOUT PROCEDURE (FL-289 AND AFTER; FM-9 AND PRIOR AIRPLANES WITH KIT NO. 130-3407- 1

INSTALLED)

The CVR cannot download while mounted in the

airplane. A portable interface (PI) (Item 8, Chart 1, 23-00-00) and appropriate power to the CVR’s main (rear) connector can be used to play assembly (Item 10, Chart 1, 23-00-00) and a cockpit voice recorder system test panel (Item 9, Chart 1, 23-00-00) with the portable interface can also be used to play back previously recorded data. Refer to portable interface operator’s manual for procedures. customer-fabricated cable to provide back previously recorded data. A cable a

n24

23-70-00Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

A

i 4

2

-i\X

g

B

$5

3

DETAIL

A lo

i.

Oj

2.

3. 4.

5.

6. 7.

8.

DETAIL

B

i 1

10. 11.

IMPACT SWITCH ELECTR~CAL CONNECTOR INDICFIIOR LIGHT SCREW AND WASHER RESET BUTTON COCKPIT VOICE RECORDER UNDERWATER LOCATOR BEACON RETFIINTNG NUT MOUNTING TRAY BLE MEMORY UNIT(CSMU) GSE CONNECTOR(BEHIND DUST COVER)

FA2100CVR AND AFTER AND PRIOR AIRPANES WITH KIT NO. 130-3407-i INSTALLED)

(FL-289

II

I

,8

~3

DETCIILB

oETnILB CVR-30B (FL-187 AND AFTER; FM-9 FIND AFTER)

CVR-~100S

(FL-114 AND AFTER, FM-9 AND AFTER)

FL23B psz864nn

Cockpit Voice Recorder (FL-114 and After; FM-9 and After) Figure 1 ORIGINAL

Page 2 May 1/08

23I70-00

As Received

ATP

By A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

MAINTENANCE PRACTICES

COCKPIT VOICE RECORDER

COCKPIT VOICE RECORDER CONTROL UNIT REMOVAL

(FL-114

AND AFTER; FM-9 AND

AFTER)

a.

Pull the VOICE RCDR circuit breaker located in the

b.

Rotate the four 1/4-turn fasteners

NOTE: Use

padding the

as

required

cockpit

to

Slowly pull wiring.

d.

Remove the CVR control unit

counterclockwise.

(3) (Ref. Figure 201)

prevent marring the finish of the pedestal.

voice recorder

c.

right sidepanel.

(2)

control unit

(CVR)

from the

(2)

from the

pedestal (1)

and disconnect the electrical

pedestal (1).

COCKPIT VOICE RECORDER CONTROL UNIT INSTALLA TION

(FL-114

AND AFTER; FM-9 AND

NOTE: Use

padding

as

required

to

AFTER)

prevent marring the finish of the pedestal.

a.

Connect the electrical connector to the CVR control unit

b.

Slide the CVR control unit

c.

Rotate the four 1/4-turn fasteners

d.

ResettheVOICE RCDRcircuitbreaker.

(2)

into the

(2) (Ref. Figure 201).

pedestal (1).

(3) clockwise.

COCKPIT VOICE RECORDER MICROPHONE REMOVAL

(FL-114 a.

AND AFTER; FM-9 AND

Remove the three

AFTER)

(1) (Ref. Figure 202) holding

screws

the aft end of the

glareshield (3)

and

tip the glareshield

up. NOTE: The ENG FIRE EXT

light

switch may need to be removed.

and washers

(5)

from the left hand side of the bracket and

b.

Remove the two

c.

Disconnect the electrical connector from the

d.

Removethe

screws

microphone (4).

microphone (4).

microphone (4).

COCKPIT VOICE RECORDER MICROPHONE INSTALLA TION

(FL-1 14

AND AFTER; FM-9 AND

microphone (4) (Ref. Figure 202)

a.

Place the

b.

Install the two

c.

Install the ENG FIRE EXT

d.

Lower the

n24

AFTER)

screws

and washers

glareshield (3)

light

into

in

position

(5) through

and connect the electrical connector.

the bracket into the left hand side of the

microphone (4).

switch if removed.

position and install the

three

screws

(1).

23-70-00May

1/08

I

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

TEST

SliJITCH

~ETER,

SWITC~

O

rEsT

3

o

O

ERASE

o

HEADSET 600 CHMS CO~KPIT

O

VOICE

RECORDER

DETAIL AND

Llld

A

FM-9

AFTER:

AND

AFTER:

A

ORIGINAL As Received

By

ATP

i.

PEO~STAL ZOCKPIT CONTROL

3.

/n

TURN

I VOICE UNIT

RECORDER

CUNIVERS~-)

I I I

I

SIGNAI

O

I

O

LEVEI

FASTENER

DETAIL OPTIONAL:

(;1-187

AND

AFTER;

A FM9

AND

AFTERI FL238 982863Ae

Cockpit Voice Recorder Control Unit (FL-114 and After; FM-9 and After) Figure 201

May

1/OSPage

202

23I70-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

A C70

ilLi

i

ji~J)

i:)

Oi jj

loll

joo

000000

i

L_’o 1

I

O

g

,I

O

n

c,)U: 011: )L J

oo1111

00

C()(

r

9 As Received By ATP

DETAIL 2.

CLARESHIELi3 SCREW COCKPIT VOICE RECORDER

3.

GLARESHIELD

SCREWS

ANC

KICROPHONE

WASHERS

FL2~B 98467LAA

Cockpit

Voice Recorder

(FL-114

and

Microphone

After; FM-9 and After)

Figure

A24

A

202

23-70-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

COCKPIT VOICE RECORDER RENIOVAL

Pull the VOICE RCDR circuit breaker located in the

b.

Rotate the 1/4-turn fasteners counterclockwise and unlock the bottom

on

right

airplane

from the flexduct for

c.

Loosen the

clamps

d.

Reposition

the duct

e.

Loosen the two

f.

Slide the recorder

g.

Lift the recorder

assembly

retaining (6)

(6)

side of the

right

free of the

AFTER)

the aft

(if applicable)

fuselage

access

door

(aft

of F.S.

and open the door.

pressurization

overboard

dump

and disconnect the flex duct.

to the CVR.

access

(8) (Ref. Figure 203)

nuts

to the

gain

to

AND AFTER; FM-9 AND

right sidepanei.

a.

381.75)

I

(FL-114

on

the

right

side of the

mounting tray (9).

to disconnect the electrical connector.

mounting tray (9).

COCKPIT VOICE RECORDER INSTALLA TION

I

a.

Place the recorder

(6) (Ref. Figure 203)

in its

mounting tray (9)

right

side of the

and slide it to the left to make the electrical

connection. the two

retaining

(8)

the

b.

Tighten

c.

Check that the reset button

d.

Install the flex duct

e.

Tighten

f.

Close the aft

g.

Reset the VOICE RCDR circuit breaker.

the

nuts

(5)

assembly

retaining clamps fuselage

on

on

in on

the

impact

position and

switch

(1)

mounting tray (9).

is

depressed.

connect the assemblies.

the flex duct.

door and rotate the 1/4-turn fasteners clockwise

(lock

the door if

applicable).

IIMPACT SWITCH REI~IIOVAL FM-9 AND

(FL-114 AND AFTER;

NOTE: Note the directional a.

b.

the switch

so

that the switch may be installed in its

Pull the VOICE RCDR circuit breaker located in the

Rotate the 1 /4-tu m fasteners

381.75)

I

arrows on

AFTER)

on

the bottom

right

cou nterclockwise

side of the

c.

Disconnect the electrical connector

d.

Remove the four

e.

Removethe switch

May

screws

right sidepanel.

and unlock

airplane

original position.

(if applicable) the aft fuselage

access

door

(aft of F.S.

and open the door.

(2) (Ref. Figure 203).

and washers

(4)

from the bottom of the

impact

switch

(1).

(1).

1/0823-70-00

ans

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

bB~L-i,--

A 2

41;-

d B 3

DETAIL

A

/3, io

i.

3. 4. 5. 6.

7. 8.

DETAIL

B

10. 11.

ii

IMP~CT SWITCH ELECTRICAL CONNECTOR INDICATOR LIGHT SCREW AND WASHER RESET BUTTON COCKPIT VOICE RECORDER UNDERWATER LOCATOR BEACON RETFIINING NUT MOUNTING TRAY CRASH SURVIVABLE MEMORY UNIT(CSMU) GSE CONNECTOR(BEHIND DUST COVER)

FA2100CVR AFTER FlND PRIOR WITH KII NO.

(FL-289 AND AIRPANES

130-3407-1

INSTALLED)

DETAILB

OET~ILB

CVR-30B (FL-187 AND AFTER; FM-9 AND AFTER)

CVR-AlaOS AND AFTER: FM-9 AND AFTER)

(FL-114

ps2ss4nn

Cockpit Voice Recorder Control Unit (FL-114 and After; FM-9 and After)

Figure

203

ORIGINAL As Received

ATP

A24

By

23-70-00

Page

205

May 1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

IMPACT SWITCH INSTALLA TION

(FL-1

14 AND

NOTE: Be

that the directional

impact switch (1) (Ref. Figure 203).

Place the

a.

switch

I

sure

AFTER; FM-9 AND AFTER)

in

arrows are

position

Connect the electrical connector

c.

Check that the reset button

d.

Close the aft

e.

Reset the VOICE RCDR circuit breaker.

fuselage

(FL-I

direction

as

screws

when the switch

and washers

was

removed.

(4) through

the

flange

on

the

impact

switch

(1)

is

depressed.

door and rotate the 1/4-turn fasteners clockwise

(CVR-A IOOS) OPERATIONAL AFTER)

(lock

the door if

applicable).

TEST

AFTER; FM-9 AND

of the control unit.

To test the

b.

Turn the

c.

Speak into the microphone: within less than half second you should hear distinctly what was just said significant distortion. You should also hear a 640-hertz test tone when the test switch is depressed.

system, plug

battery

a

600-ohm headset into the headset

jack

a.

d.

of the

(2).

COCKPIT VOICE RECORDER 14 AND

same

and install the four

b.

(5)

in the

master switch

on.

For another test of the system without

a

headset, press the

that the meter needle raises to the green

are:

without

test switch for a minimum of five seconds and note

the needle may oscillate, but will not fall out of the green

are.

(CVR-30B) OPERA TIONAL TEST (FL-187 AND AFTER; FM-9 AND AFTER) COCKPIT VOICE RECORDER

NOTE: Self test will not start if the ERASE feature is in process. a.

To test the system, put

b.

Push the TEST button

c.

During self test,

make

on

on

the headset and

plug

into the control unit

the control unit. Hold for

sure

the PASS and FAIL

one

Lights

headphone jack.

second and release. This starts the CVR self test. illuminate

alternately, indicating

that self test is in

progress. Self test takes approximately 15 seconds to perform. After 10 seconds of self test, cockpit conversation should be heard through the headset and visible on the SIGNAL LEVEL Indicator. The test tone audio will be heard. No audio will be recorded d.

Upon completion

of

a

during

self test.

successful self test, the PASS Light will illuminate for by an illuminated FAIL Light (usually

out. A failed self test will be indicated

indicates the nature of the failure. FAIL will flash

a

of flashes. Refer to Chart 1 for fail condition based

approximately ten seconds then go flashing). The flashing FAIL Light

number of times, pause, and then repeat that on the number of FAIL flashes.

NOTE: Should self test fail and it is desired to do another self test, the TEST button must be least one second to engage self test.

May

1/08Page

206

23-70-00

same

number

pressed firmly

for at

az4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 201

OPTIONAL CVRSOB TEST CONDITIONS FAIL

CVR Conditions

Number of Fail Flashes

PASS

Light

None

Pass

Off

On

1

Channel 1

On

Off

On

Off

On

Off

On

Off

On

Off

On

Off

Alternating

Alternating

Simultaneous

Simultaneous

Light

Fail Channel 2

2

Fail Channel 3

3

Fail

Channel 4

4

Fail

Memory Fail

5

Flash

Steady

General Fail

Alternating

System

Simultaneous

Bulk Erase

Test in

Progress

NOTE General fail is

a

miscellaneous failure of channel 5, 6,

Frequency

Shift

Keying (FSK),

Rotor

Speed, ARINC

Channels etc. The BITE status code indicates which function has failed. Please contact Universal Avionics for assistance with

determining

a

particular

BITE status failure indication.

COCKPIT VOICE RECORDER (CVR-FA~100) OPERA TIONAL TEST (FL-289 AND AFTER AND PRIOR AIRPLANES WITH KIT NO. 130-3407- 1 600-ohm headset into the headset

a.

To test the system,

b.

Press and hold the test button for

plug

a

a

of the control unit.

minimum of 5 seconds.

Observe that the needle of the test meter

c.

jack

INSTALLED)

moves

to and remains in the green

area

during

and

only during

the

test.

d.

A 620-660 hz test tone is heard for

Speak

e.

audio f.

g.

approximately

1.6 seconds in the headset.

6-inches away from area microphone, covering others if necessary, to activate the cabin briefer. The the mics and cabin briefer should be heard on the headset without any significant distortion.

on

Verify the

erase

button for

a

function, with the aircraft resting

on

it’s

landing

gear, press and hold the control unit’s bulk

erase

minimum of 2 seconds.

A 5 -10 second 400 HZ tone should be heard in the headset.

A24

23-70-00

Page

yaM702

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

COCKPIT VOICE RECORDER OPERA TIONAL Turn

a.

b.

on

Using

a

(CVR-A I I OS) UNDERWA TER LOCA TOR BEACON TEST (FL- 1 14 AND AFTER; FM-9 AND AFTER)

the Beacon Tester.

ground strap

or

similar conductive material, short the beacon center conductor, located

the

on

underside of the beacon, to the cradle.

NOTE:

Proper operation sound

waves

of the ULD is indicated

While the beacon is shorted to the cradle,

c.

detected,

the

If

is

produced

from converted ultrasonic

an

audible tone should be heard at the beacon test set. Once

(CVR-FA21OO) OPERATIONAL

TEST

AND AFTER AND PRIOR AIRPLANES WITH KIT NO. 130-3407- 1

NOTE: This test verifies the proper CVR-FA2100 front panel. To test the ULD,

use

Turn

b.

On the front of the test set,

c.

Rotate TUNING control to

d.

Using

on

a

the test set

braid

NOTE: Make

or

sure

operation

of the beacon

the Dukane Ultrasonic Test Set, P/N

a.

by rotating

the front

place

a

panel

(Underwater Locating Device)

INSTALLED) mounted

on

the

42A12(

GAIN control clockwise until it clicks.

the INT-EXT switch to INT.

setting

between 35 and 40 KHz.

other flexible metal conductor, temporarily short the ULD switch, thereby activating the unit.

the test set’s

microphone

test set will detect the proper e.

repetitive "beep", which working properly.

an

COCKPIT VOICE RECORDER BEACON

(FL-289

a

audible tone is not detected, proceed to the System Level shorting jumper. (Ref. COMPONENT MAINTENANCE MANUAL, 300 SERIES COMMUNICATIONS).

remove

Troubleshooting

by

emitted from the ULD when it is

has

a

line of

sight

unobstructed view of the ULD. This will

the

ensure

output of the ULD.

functioning properly, it will emit inaudible, ultrasonic sound waves the test set will receive and lower, audible frequency. Proper operation of the ULD is indicated by a repetitive "beep" reproduce from the test set speaker. emanating If the ULD is

at a

f.

Turn off the test set. If

required,

record the ULD’s serial number and

expiration data

on

the

appropriate

recorder

data record. g.

May

If the ULD is not

1/08Page

208

operating properly, replace

23-70-00

the ULD batteries and repeat this test.

nn4

C H A PT E R

ELECTRICAL POVVER

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 24 - ELECTRICAL POWER TABLE OF CONTENTS SUBJECT

PAGE 24-00-00

Electrical Power - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Electrical System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 24-20-00 AC Electrical System - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Inverters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Bus-Transfer Relays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 AC Power Monitor PCB. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 AC Electrical System - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Inverter System Operational Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 26 VAC Output Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Inverter Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 24-30-00 DC Generation and Control - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 DC Starter/Generators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Generator Control Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Field Flash Circuit and Voltage Regulation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Line-Contactor Relay Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Starter/Generator Paralleling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Overexcitation Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Reverse Current and Polarity Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Overvoltage Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Cross-Start Overload Current Limiting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Generator Control Relay . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Bus-Tie Control PCB. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Generator Bus-Tie and Bus-Sense Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Bus-Tie Relays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 DC Generation and Control - Troubleshooting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Generator Control Panel Test Unit (TK1999/935). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Starter/Generator Paralleling Equalizer Circuit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .104 Generator Control Panel Overvoltage Circuit Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .104 Generator Control Panel Reverse Current Circuit Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .105 DC Generation and Control - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Starter/Generator Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Starter/Generator Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Starter/Generator Brush Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Starter/Generator Brush Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Generator Control Panel Voltage Check and Adjustment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Generator Control Relay Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207

A27

24-CONTENTS

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 24 - ELECTRICAL POWER TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 24-31-00

Battery - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nickel-Cadmium Battery (FL- 1 thru FL-214, FL-318; FM-1 thru FM-9). . . . . . . . . . . . . . . . . . . . . . . . . . . . . Lead-Acid battery (FL-215 and After, except FL-318; FM-10 and after) . . . . . . . . . . . . . . . . . . . . . . . . . . . . Servicing Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nickel-Cadmium Battery Servicing Precautions (FL-1 thru FL-214, FL-318; FM-1 thru FM-9) . . . . . . . . Lead-Acid Battery Servicing Precautions (FL-215 and After, except FL-318; FM-10 and After) . . . . . . . Battery Power - Disconnect . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Battery Power - connect. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Battery Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Battery Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Battery Terminal/Connector Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Battery Charging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nickel-Cadmium Battery Charging (FL-1 thru FL-214, FL-318; FM-1 thru FM-9) . . . . . . . . . . . . . . . . . . Lead-Acid Battery Charging (FL-215 and After, except FL-318; FM-10 and after) . . . . . . . . . . . . . . . . . Constant Potential Charging for Lead-Acid Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Constant Current Charging for Lead-Acid Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . In-Airplane Charging for Lead-Acid Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Reserve or Emergency Capacity Test for Lead-Acid Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maintenance Log (FL-1 thru FL-214, FL-318; FM-1 thru FM-9). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

201 201 201 202 202 202 202 203 203 203 203 204 204 205 206 206 207 207 207

24-32-00 Battery Monitor - Description and Operation (FL-1 THRU FL-214, FL-318; FM-1 THRU FM-9) . . . . . . . . . . . 1 Battery Monitor - Maintenance Practices (FL-1 THRU FL-214, FL-318; FM-1 THRU FM-9) . . . . . . . . . . . . . 201 Battery Monitor Calibration Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Battery Monitor Functional Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Battery Gas Barrier Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 24-40-00 External Power - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 External Power - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Connecting and Applying External Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Disconnecting External Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 24-50-00 Electrical Load Distribution - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Power Distribution on the Busses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Bus-Tie Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Avionics Power Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Electrical Load Distribution - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Bus Conformity Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Electrical Load Utilization Charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203

Page 2 Feb 1/10

24-CONTENTS

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

24-LOEP

1

Feb 1/10

24-CONTENTS

1 and 2

Feb 1/10

24-00-00

1 thru 3 201

Apr 28/06 Apr 28/06

24-20-00

1 thru 3 201 thru 203

Apr 28/06 Nov 1/07

24-30-00

1 thru 8 101 thru 120 201 thru 207

Apr 28/06 May 1/08 Apr 28/06

24-31-00

201 thru 208

Feb 1/10

24-32-00

1 201 thru 203

Apr 28/06 Apr 28/06

24-40-00

1 201

Apr 28/06 Feb 1/10

24-50-00

1 thru 20 201 thru 230

Aug 1/09 Feb 1/10

A27

24-LOEP

Page 1 Feb 1/10

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

ELECTRICAL POWER ELECTRICAL SYSTEM The 8300 electrical system is

a

28-volt de,

single-loop, triple-fed system

with

a

negative ground. During

normal

operation, two 28-volt, 300-ampere starter-generators and a 24-volt nickel-cadmium battery (FL-1 thru FL-214, FL-318, FM-1 thru FM-9) or a 24-volt lead acid battery (FL-215 and after, FM-10 and after) supply all of the airplane electrical needs. These power sources are brought on-line by the pilot with three switches, placarded MASTER SWITCH, BATT, ON-OFF, L GEN, R GEN, RESET-ON-OFF, under the master switch gang bar on the pilot’s outboard subpanel. An auxiliary power unit (APU) may be connected to the airplane external power receptacle when an

external power

source

is

required (Ref. Figure 1).

battery is installed in the RH wing center section between the RH nacelle and fuselage. Battery power is connected a battery bus, the center bus and the triple-fed bus. Selected equipment is powered from the "hot" battery bus to allow operation without turning on the battery switch. Refer to Chapter 24-31-00 for maintenance information on the battery. Control of the two starter/generators is accomplished with two generator control panels, the bus-tie control PCB (A257), current sensors, switches and the bus tie, line contactor and generator control relays. The generator control panels provide line-contactor relay control, voltage regulation, generator paralleling, differential voltage sensing and control, reverse current sensing and control, overvoltage and overexcition protection and cross-start current limiting. For more information on the starter/generators and a detailed schematic of the de generation and control system, refer to Chapter 24-30-00.

A

to

Five

primary

consist of

a

buses distribute power to all of the sub-buses from the three main power sources. The primary buses battery bus, center bus, triple-fed bus, and the left and right generator buses. This system is termed

"hot"

triple-fed bus system, with each bus receiving power from the three de power sources. This design minimizes the a complete power loss should a power source become isolated. For example, the triple-fed bus is powered from both generator buses and the battery. a

risk of

primary buses are also individually pr’otected by current sensors, limiters, diodes and relays. The triple-fed protected by a diode and 60-ampere current limiter wired between it and each feeder bus. This configuration provides overcurrent protection and prevents current flow away from the triple-fed bus. Load-shedding is accomplished by isolating a faulty bus from those that are still functional, thereby preventing a failure of the entire electrical system. Refer to Chapter 24-50-00 for more details on each bus feeder and the distribution of power to the individual airplane systems. Chapter 24-50-00 also includes a simplified schematic of avionics power distribution.

The five

bus is

SPECIAL TOOLS AND RECOMMENDED MATERIALS special tools and recommended materials listed in Charts 1 and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically prescribed by Raytheon Aircraft Company. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Raytheon Aircraft Company, by the supplier, or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification listed may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

The

24-00-00

Apr 28/06Page

1

Raytheon

nircraff

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

SPECIAL TOOLS AND EQUIPMENT PART NO.

TOOL NAME 1.

USE

SUPPLIER

GeneratorControlPanei

TK1999/935or

Raytheon AircraftCompany.

For

Test Unit

fabricate per instructions in this

Wichita, Kansas

generator control

gaining

access

to the

panel

pins.

chapter 2.

3.

DigitalMultimeter(4

1/2

digit,

1%)

accurate within

Multimeter

8060A

John Fluke

equivalent

or

N/A

Manufacturing,

Measure

voltage

Everrett, Wash.

resistance.

Obtain

Perform

locally.

voltage

and

and

resistance checks. 4.

AC

Volt/Frequency

N/A

Obtain

locally.

Perform AC system check.

battery temp. during charging.

Meter 5.

Thermometer

N/A

Obtain

locally.

6.

28-vdc, 2-amp Power

N/A

Obtain

locally.

Monitor

Perform check of the

Supply 7.

battery

Battery Charger/ Analyzer

RF80F

or

Christie

equivalent

Charge nickel-cadmium airplane battery.

Corp.,

20665 Manhattan

monitor circuit.

Place,

Torrance, CA 90501 Power Products, Inc.,

Beta 540

Charge battery.

lead-acid

airplane

Teledyne Battery Products,

Charge

lead-acid

airplane

840 W. Brockton

battery. lead-acid

airplane

522 E. 85th St., New York, NY 10028 8.

BattelyChargerl Analyzer

TDMC-90

or

equivalent

Redlands, CA 92374 RF80K

or

Christie

equivalent

Corp.,

20665 Manhattan

Place,

Charge battery.

Torrance, CA 90501

Chart 2

RECOMMENDED MATERIALS MATERIAL 1.

Solvent, Dry Cleaning

SPECIFICATION

P-D-680, Type III

PRODUCT

SUPPLIER

Stoddard Solvent

Barton Solvents, Inc.

(Mineral Spirits)

201 S. Cedar Street

Valley Center, KS 2.

Solvent

ASTM D-740

or

O-C-265

Methyl Ethyl Ketone

Obtain

Locally

Obtain

Locally

67147

TT-M-261

(Supersedes MIL-M-13999)

and 3.

Apr

Dryfilm

lubricant

MIL-L-81329

28/0624-00-00

A20

Ray~heon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LH LOADMETER SHUNT

LH STARTER/

GENERATOR

LH

RH

LOADMETER

(141)

(A251RI)

OVERHEAD

INSTRUMENT

(A213GI)

(LINE

CONTACTOR] A25 I)

(M2)

PANEL

RH

STARTER/ GENERATOR

(A252RI)

(A214GI)

(A133)

LH LH FORWARD POWER DISTRIBUTION PANEL

RH LOADMETER SHUNT

LOADMETER

RH

AFT POWER DISTRIBUTION PANEL (BUS TIE)

AFT POWER DISTRIBUTION PANEL (BUS TIEI

I

I

~------I--1

I

GEN

I

________

________

LH

I

IRH

I

I

DC

MAIN

POWER

DISTRIBUTION

I

I

_--_----

t---~-1LH GEN SUB-BUSI

BUS

RH

(A254)

(A~53)

I

GEN

SUB-BUSI

RH

I

ri

I

BUS

GEN

I

FORWARD POWER DISTRIBUTION PANEL (LINE CONTACTOR]

I

I

(A~52)

PANEL

(A145)

r-------,

LH GENERATOR CONTROL PANEL

TRIPLE-FED

I

I I

I 1

RH GENERATOR CONTROL PANEL

BUS

-----T----I

I

I

I

I

I

I

I

I

T

I

I

I

I

L______-~

(VRI) CENTER

BATTERY AMMETER

BATTERY SHUNT

I

j

I

I

I

I

BATTERY

I

I

I BATTERY SWITCH AND RELAY

BATTERY POWER DISTRIBUTION PANEL [BUS TIE)

BATTERY

I

I

[A133M3)

(R120)

(VR21

BUS

LH

VOLTMETER SELECT SWITCH

I

VOLTMETER I

(A133M3)

(A133S2)

OUTBOARD SUBPANEL (A221

BUS I

(A228]

(BTIOI

1

I

EXTERNAL

POWER RELAY

EXTERNAL POWER

´•7J;

RECEPTACLE

(A228K 1 24)

(J1121

Electrical

C94FL2480860

System Block Diagram Figure 1

ORIGINAL As Received AIP

A20

By

24-00-00

Page 3 Apr 28/06

gaYPheen

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTRICAL POWER

MAINTENANCE PRACTICES

repairs on the 8300, methods used must be in accordance with the Federal Aviation Administration’s "Aircraft Inspection and Repair manual AC43.13-1A and with the "Aircraft Alterations" manual AC43.13-2A. Any components replaced, and any wire, cable or terminals used in the maintenance of the electrical system must be of airplane quality. Any solder connections must be made in an approved manner. Any solderless terminals or splices used must be applied with tooling specified by the supplier. Always remove power from the system being repaired and ensure that all electrical bonding requirements are met. Detailed schematics of connectors and wiring may be found in the Super King Air B300 Wiring Diagram Manual. When

making

electrical

24-00-00Page

201

Ral~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AC ELECTRICAL SYSTEM

DESCRIPTION AND OPERATION

The AC electrical system is a 115-vac and 26-vac, single phase, 400 Hz system. It operates on 28 vdc and provides ac power to certain avionics and electrical equipment. The system consists of two static inverters, two bus-transfer

relays,

an ac

power monitor circuit card and associated switches, circuit breakers and annunciators

(Ref. Figure 1).

INVERTERS wing center section, outboard of each nacelle. Two inverter control switches on the pilot’s outboard subpanel provide individual control of the inverters. In the OFF or TRANSFER position, the output of the inverter is zero even though the de input is not interrupted. In the ON position, the inverters are remotely switched on to provide 115 vac and 26 vac outputs (Ref. Figure 1).

The two static inverters

are

located in the

a 28 vdc input to single phase 400 Hz ac at 115 vac and 26 vac. Voltage and frequency regulation are accomplished internally. Voltage regulation is 5% to -7% and frequency is 400 1%. The continuous rated capacity of each inverter is 150 va from the 26-volt output and 750 va total output. The outputs of the inverters are synchronized during simultaneous operation. The No. 1 inverter is powered from the center bus and the No. 2 inverter is powered from the right generator bus.

The inverters convert

BUS-TRANSFER RELA YS The bus-transfer draw from

one

relays,

located in the fuel control

inverter to the other should

control of the bus-transfer

one

panel, provide the capability to manually transfer ac equipment inoperative. The inverter switches provide manual

inverter become

relays (Ref. Figure 1).

The outputs of the inverters are connected to the normally closed (NC) contacts of their respective bus-transfer relay and to the NO (normally open) contacts of the opposite bus-transfer relay. When the inverter switches are ON, the inverters provide power to their corresponding buses. When one inverter switch is in the TRANSFER position, its inverter is shut down and the

During operation ac

corresponding bus-transfer relay

transfers its

ac

buses to the

remaining

inverter.

in the TRANSFER mode, all ac loads are connected to one inverter. Therefore, the total capacity of one inverter to avoid overload when a transfer is necessary.

airplane

load is limited to the

~20

24-20-00

Apr

28/06Page

1

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AC POWER MONITOR PCB ac power monitor printed circuit card (A320) monitors both 115 vac buses, both 26 vac buses and both inverter switches. It provides outputs to the #1 AC BUS or #2 AC BUS annunciator when a voltage or frequency is out of

The

I

tolerance. It also closes the sync line between the two inverters when both inverters ac annunciators is provided by two separate circuits that sense frequency inputs are within limits, the ac annunciators are extinguished when Acceptable limits for the ac system are as follows:

Control of the

115 V 26 V

input--------------l 03.5

input-------------------23.4

Frequency (115

V

are

each

operating (Ref. Figure 1). ac

bus. If all

the system is

voltage brought on

and line.

to 126.5 VAC

to 28.6 VAC

input)----380

to 420 Hz

If any of the inputs are outside of the above limits, the ac monitor pcb outputs a signal to the appropriate ac annunciator to identify the failed system. The annunciator remains illuminated as long as the condition exists and

extinguishes

when the condition is corrected.

pcb senses the position of both inverter switches and monitors both ac annunciator signals to control synchronization. When both inverter switches are ON and both ac annunciators are extinguished, the ac monitor pcb closes the sync line between both inverters to phase-lock both inverter outputs.

The

ac

Page

monitor

224-20-00

n2o

Raytheon

Aircraft Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

BUS AC

BUS

CONTROL

CB

INVERTER

(A12dAC824)

NO. I

26 VAC NO.I CB (A12aC828)

NO.2

26 VAC BUS

CB

(A124CB26) INVERTER NO.2

CB

3A

(A145C81 i

b!

(--O

3A

0----7

1

115 VAC NO.2 BUS CB (A124CB25)

115 VAC NO.I CB (A124CB27)

BUS

40An

5A

BATTERY

AC BUS TRANSFER

NO.I

CEBN~ER

BUS

(A12dK5)

RELAY

3A

Aaq

Al I

A31\

I

831\

81

NO.2 AC BUS TRANSFER

3A

82q

1

i

I

I

82P

I

I

/lBa

RELAY

A2

I

NO. I

ON

VOC

REMOTE

IN

01

(A22jS136]:6

1

I

115

REMOTE

VAC

I

IN

I

26

VAC

A I

VAC

81

I

I

I

I

il!lll

I

I

I

I

I

I

I

I

I

i

I

I

I

I

I

i

I

i

I

I

I

COMMON

GROUND

115 VAC INVERTER MONITOR CB (A263CBI)

C

SYNCHROPHASER

I

GROUND

F

NO. I 26 MONITOR INVERTER

NO. I

[A231PSI I I

IN

IE

I

I

I

I

I

I

I

I

VAC

CB

115

VAC

IHIREMOTE IN VAC

I

IA

26

I

IB

115

VAC COMMON

GROUND

C

AC

I

SYNCHROPHASER

F

DC

5A

N0.2

INVERTER

I TOROUEMETER (A146CBd31

5A ´•R

TOROUEMETER

b--I

I

I

I

I

I

I

I

I

I

CB

(A146CB441

77-00-00

DATA RECOROERI (AldbCB88)

AC

I

I

T

I

I

’.5A

I ’FLIGHT

CB

POWEF´•

d~b!

REF CHAPTER 77-00-00

DATA

I*

CB

TEST

JACK AND CB

EL

NO.2

PANEL

(REF

(A232PS

1 12]

POWER

CHAPTER 33)

PANEL

(A263CB5)

I I

RECORDER

GROUND

INVERTER

I

EL

I

IFLIGHT

,r

VAC INVERTER CB (A263CB41

I

CB

REF

POWER

26

MONITOR

(A263C821

I ´•L

GIEMERGENCY

NO.2 115 VAC INVERTER MONITOR CB (A263CB3)

I

OUT

REMOTE

O

I

5A DC

0128 VOC

I

NO.I

AC

SELECT SWITCH

TRANSFER

HI

115

I

III

TRANSFER

G

2

11\10.2

(A221S236) O

EMERGENCY

GENERATOR BUS

I INVERTER OFF

OFF

El

OUT

03

II

SWITCH 28

RH

II

/IA3 IAl

Bl

20 INVERTER SELECT

I

(A124K4)

ON

3

CB

(A145(3826)

I I

I

I

I I

I I

-.5A

I

(J186) (J190)

66CB871 TEST

JACK

(A220)

SUBPANEL 2A

#1

AC

I

BUS

I

I

I

I

I

i

-h

i

I

I

I

I

I

R

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9

1

~VIONICS hC POWER WARNING ANNUNCIATOR PANEL (E192)

I

I

R

9

g o

z

z

4Q~U

m~"6 S J 9 m

N

FL-I

THRU

Y

B

N

FL-122

AND

FM-9 AND AFTER. AFTER ONLY.

FL-120

""~’8 d m

ANO

w

r-

9

Z

z

o

U

9 N

m

Z

m N

o

dz z

B ~B n

P" B H

ZZ ’g,, ~O gg

BUS

rrom

n

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z

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r c~

61

EFFECTIVE

5~""

v,

4, EFFECIIVE FMTHRU FH-8. 19 ANO FL-I2 FLONLY.

P)NN

P]

U~

AC

WARNING ANNUNCIATOR PANEL (E192)

z U

#2

Z

Z

0

o~

u

P

g~ ~a

d’U ’4

8

U)

B t u

S C94FL2dB1249 C

c

AC

POWER

MONITOR

CIRCUIT

CARD

(A320~

AC Electrical

System Schematic Figure 1

ORIGINAL

A20

Ao Received By A~P

24-20-00

Page 3 Apr 28/06

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

AC ELECTRICAL SYSTEM

one of the inverter system circuits may be difficult to detect during normal operation of the system; therefore, it is recommended that an Inverter System Operational Check be performed at regular intervals to verify proper operation of the inverters and inverter transfer circuit. Check results that are contrary to those expected for a normally operating system indicate the need for point-to-point troubleshooting to isolate the fault.

A failure in

check verifies the inverter 115

following

The

of the 26

vac

inverter circuit without

a

vac

output. As

failure of the 115

a

vac

general

rule it is

highly unlikely

circuit. A failure of the 26

to

vac

experience

a

failure

inverter circuit will be

accompanied by flags on all avionics equipment that operates on 26 vac. As long as the 26 vac avionics are powered, a test verifying the 115 vac output is an acceptable verification of the 26 vac output also. If the 115 vac checks indicate a good system, but a problem still exists, perform the check of the 26 vac circuit to isolate the fault. INVERTER SYSTEM OPERATIONAL CHECK NOTE:

External power may be used to

provide

power for this check if the technician does not wish to

run

the

engines. a.

Connect external power to the power is being used.

b.

Start both

engines

with

airplane and apply 28.25

procedures

outlined in the

0.25 vdc to the buses.

Super King

each

Bring both starter/generators on-line by momentarily placing

c.

position Connect

d.

the

and

an ac

copilot’s

NOTE: The

releasing

ac

Operating

step d if external

Handbook.

generator control switch

in the RESET

volt/frequency meter (4, subpanel.

Chart i,

24-00-00)

to the blue

jack (J186)

test

located underneath

inboard

jack only monitors 1 15 vac for the No. 2 inverter during used to monitor output of the No. 1 inverter.

Select the

f.

Engage the AC BUS CONTROL

g.

Place the NO. 1 INVERTER select switch in the ON

appropriate range

extinguishes.

on

the

volt/frequency

e.

ac

ac

operation. The

transfer function

vac.

circuit breaker.

The voltmeter should indicate

The

normal

meter to read 115

zero

position

and

verify

that the #1 AC BUS annunciator

volts.

Place the NO. 2 INVERTER select switch in the TRANSFER

extinguishes. i.

with

to ON.

test

must be

h.

Air B300 Pilot’s

Begin

voltmeter should indicate 115

vac

Place the NO. 1 INVERTER select switch in the OFF

position and verify that the #2 AC BUS annunciator

+5% -7% from the No. 1 inverter.

position

and

verify

I

that both AC BUS annunciators

illuminate.

j.

Place the NO. 2 INVERTER select switch in the ON

extinguishes. k.

ac

voltmeter should indicate 115

The

ac

voltmeter should still indicate 115

and

verify

ac

that the #2 AC BUS annunciator

+5% -7%.

vac

position and verify that the #1 AC BUS annunciator +5% -7%.

Place both the NO. 1 and NO. 2 INVERTER select switches in the OFF AC BUS annunciators should illuminate and the

A23

position

vac

Place the NO. 1 INVERTER select switch in the TRANSFER

extinguishes. I.

The

position.

voltmeter should indicate

Both the #1 AC BUS and #2

zero

volts.

24-20-00

’N~b:

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

If the ac system performs the functional check as described, and no flags are present on any 26 vac powered instruments, the system has passed the functional test. If flags are present, perform the following check to isolate a

problem

in the 26

vac

circuit.

26 VAC OUTPUT CHECK a.

ac power distribution panel to perform this check. The panel is located under the center aisle forward of the emergency exit door between FS 168 and FS 180. Refer to Chapter 39-21-00 for

Access the A263

floorboard an

just

illustration of the

panel.

CAUTION: Ensure that the inverters

I

are

off before

(4,

making any

Chart 1,

24-00-00) to terminals

b.

Connect the

c.

Set the

d.

Place the NO. 1 INVERTER select switch in the ON

panel. e.

volt/frequency

meter

safely

meter to a range that can

3

position.

read 26

position.

Read

2

and 3

of TB1

on

the A263

panel.

vac.

voltage from

terminal 2 of the

ac

distribution

vac.

Place the NO. 1 INVERTER select switch in the OFF

The voltmeter should indicate

zero

and

position

place

the NO. 2 INVERTER select switch in

volts.

Place the NO. 1 INVERTER select switch in the TRANSFER 3

g.

volt/frequency

The meter should indicate 26

the ON f.

ac

ac

voltmeter connections to the test terminals.

position

and note that the voltmeter indicates 26

vac.

Place both INVERTER select switches in the OFF

CAUTION: Ensure that the inverters

are

position.

off before disconnecting

or

connecting

the voltmeter leads to

or

from the

test terminals.

h.

Disconnect the voltmeter

negative i.

j.

lead from terminal 2 and connect it to terminal 5

position.

The voltmeter should indicate

zero

The voltmeter should indicate 26

position.

Place the NO. 2 INVERTER select switch in the OFF

position

and

position

Place the NO. 2 INVERTER select switch in the OFF

position.

m.

Place the NO. 1 INVERTER select switch in the OFF

position.

n.

Disconnect the voltmeter leads from the terminals.

If the system has "no

the NO. 1 INVERTER select switch in

and

verify that

the voltmeter indicates 26

passed

this test

assume

that there is

a

possible wiring fault

to any instrument that

displays

a

power" flag.

Page

voN202

vac.

vac.

I.

o.

place

3

volts.

Place the NO. 2 INVERTER select switch in the TRANSFER 3

and disconnect the

lead from terminal 3 and connect it to terminal 6

Place the NO. 2 INVERTER select switch in the ON

the ON k.

positive

1107

24-20-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INVERTER TEST When

lengthy operation

of

an

inverter is in

to maintain the total ac load. The test

unit

on

a.

No. 1 inverter- ON.

b.

No. 2 inverter

c.

All ac loads- ON.

d.

line

as

Operate

BUS TRANSFER.

the No. 1 inverter for one-half hour minimum and are

extinguished

and the inverter

e.

No. 2 inverter

ON.

f.

No. 1 inverter

BUS TRANSFER.

Operate

verify that output is 115 VAC.

the No. 2 inverter for one-half hour minimum and

annunciators

A23

question, perform the following check to verify the ability of each inverter be conducted with the airplane generators on line or an external power

follows:

annunciators

g.

can

are

extinguished

and the inverter

verify

the #1 AC BUS and #2 AC BUS

that the #1 AC BUS and #2 AC BUS

output is 115 VAC.

24-20-00

Page

voN302

1107

Ral~heon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DC GENERATION AND CONTROL The de

generation

generator control control switches, load and

and control

panels,

DESCRIPTION AND OPERATION

system consists of

two line-contactor

starter/generators, the battery, three current sensors, two relays, two generator control relays, two generator switch and the bus-tie control pcb. The system also includes

two de

relays,

three bus-tie

bus-tie control switch, bus-sense indication for all three power sources and five annunciators that indicate status of the system a

voltage e rugiF.feR( 1).

I

DC STARTER/GENERA TORS dual-purpose, 28-volt, 300-ampere units which produce torque for engine starts or generate electrical current to meet the airplane electrical loads. A quick-disconnect mounting adapter is bolted to a mounting pad on the engine accessory geart~ox, providing the starter/generator with a pin-aligned mount. The unit mates with the engine gearbox by means of a splined drive shaft, providing a direct torque transfer for both generator and starter functions. Should a condition occur causing excessive torque at the starter/generator splined drive-shaft, the shaft will shear, minimizing damage to the starter/generator and engine components. An internal shaft-driven fan draws outside air through the starter/generator to provide ground cooling.

The

starter/generators

are

winding is used for starter operation, and a shunt field winding is used during generator operation. Chapter 80-00-00 for general information on starter operation. The starter/generator interpole and compensating windings are in series with the armature and provide a voltage proportional to starter/generator output current. Voltage developed across the interpole and compensating windings is output at terminal D of the starter/ generator. The generator control panel senses this voltage at pin D to provide equalization during dual generator operation. Each generator control panel also provides a field excitation voltage from pin M to terminal A on the starter/generator. While monitoring starter/generator output at pin B, the generator control panel adjusts field excitation voltage accordingly, thereby regulating starter/generator output at terminal B within the normal range of

A series starter

Refer to

28.25 ~0.25 vdc.

GENERATOR CONTROL PANELS The generator control panels are self-contained units mounted on the Main Power Distribution Panel (A145). Each starter/generator has its own generator control panel to provide line-contactor relay control, voltage regulation,

generator paralleling, differential voltage sensing and control, reverse current sensing and control, overvoltage and overexcitation protection and cross-start current limiting. There are two voltage-measurement jacks and a voltageadjustment screw on the face of each unit to allow for the adjustment of starter/generator output through the generator control panel regulator circuit. Refer to GENERATOR CONTROL PANEL VOLTAGE ADJUSTMENT in this

n,o

chapter for voltage adjustment procedures (Ref. Figure 1).

I

24-30-00

Rayfheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIELD FLASH CIRCUIT AND VOLTAGE REGULATION The generator control panel monitors starter/generator output voltage and controls the shunt field excitation to maintain a constant voltage under varying operating conditions such as speed, load and temperature. Before the control panel can regulate starter/generator output, it must use residual voltage to build starter/generator output to

regulation circuit can control. Residual voltage, normally 0.3 to 2.0 vdc, is present at terminal B of the starter/generator as long as the unit is spinning and the control panel is not supplying a regulator voltage to the shunt field at terminal A of the starter/generator. When either generator control switch is placed in the GEN RESET position, a low-resistance path is established from terminal B of the starter/generator to pin K on the control panel, through an internal relay, then out pin M and back to the starter/generator at terminal A. Upon reaching terminal A of the starter/generator, residual voltage excites the shunt field and increases output at terminal B of the starter/ generator until the control panel internal relay energizes, breaking the field flash path. At this point, starter/generator output voltage should be sufficient to allow the regulator circuit to take over and continue increasing starter/ generator output until 28.25 ~0.25 vdc is reached. The control panel will continue to regulate the starter/generator by adjusting output at pin M to maintain starter/generator output at 28.25 ~0.25 vdc. Anytime the generator control switch is placed in the OFF position, this switch must be placed in the GEN RESET position to excite the field, increase starter/generator output and bring it back on line (Ref. Figure 1). a

level the

LINE-CONTACTOR RELAY CONTROL a line-contactor relay. The line-contactor (A251 LH, A252 RH). When the generator control switch is in the ON position and the generator control relay is de-energized (start signal removed), voltage from terminal B of the starter/generator is applied to pin C of the generator control panel. Bus voltage is sensed at pin A of the control panel and compared to starter/generator output voltage at pin B of the generator control panel. When these voltages are nearly equal, an output from pin H of the generator control panel will close the linecontactor relay. The yellow R DC GEN or L DC GEN caution annunciator will extinguish and generator output is applied to the bus-tie relay contacts for distribution. The generator control panel monitors a number of inhibiting signals and will open the line-contactor relay should a fault occur requiring isolation of the starter/generator from the generator bus (Ref. Figure 1).

Each

starter/generator

relays

are

located

on

is connected to its

their

respective

respective generator

bus

by

Forward Power Distribution Panel

STARTER/GENERATOR PARALLELING The generator control panels incorporate circuitry to maintain the starter/generator electrical loads within 10 percent of each other for their entire operating range. An equalizer relay in each generator control panel is used to connect

starter/generator equalizer channels when the line-contactor relay is closed, enabling the generator control panel equalizer circuit only when load-sharing is possible. The bus-tie control pcb also incorporates an internal relay to provide an interconnect between pin E of each generator control panel. The bus-tie control pcb internal circuitry will not close its intemal relays until it receives signals indicating that the line-contactor and bus-tie relays are closed for both sides of the system. Once these conditions for load-sharing are met, each generator control panel will compare the interpole winding voltages from terminal D of both starterlgenerators to determine the relative amount of load current being supplied by each starter/generator. The generator control panels accomplish this by sensing interpole voltage (of the starter/generator they are regulating) at pin D and the opposite side starter/generator interpole voltage at pin E. The generator control panels then bias their voltage regulation circuits accordingly, adjusting voltage output at pin M to accomplish equal load-sharing. Precise load distribution from the generator I control panels is provided without the need for adjustment while the units are in service (Ref. Figure 1). both

Apr

28/06Page

2

24-30-00

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OVEREXCITATION PROTECTION

causing excessive field excitation, the affected starter/generator will attempt to carry all of the airplane’s During parallel operation, this is sensed at the generator control panel by comparing of the interpole voltages starter/generators. The starter/generator will be de-energized if generator bus voltage is than vdc the output current differential between starter/generators is greater than 15 percent for 28.25 and greater 5 seconds. This circuit functions during parallel operation only and does not require an overvoltage condition to function (Ref. Figure 1). When

a

failure

occurs

electrical load.

REVERSE CURRENT AND POLARITY PROTECTION When the generator field becomes underexcited for any reason, or when the starter/generator slows down to a point where it can no longer maintain a positive load, it will begin to draw current from the center bus. The reverse-current-

protection function senses starter/generator interpole voltage at pin D of the generator control panel to determine if starter/generator has become a load rather than a power source. If reverse current is present, indicated by positive voltage at pin D, the generator control panel will open the line-contactor relay and remove the starter/ generator from the bus. During engine shutdown, the unit will have a tendency to wait longer to open the linecontactor relay. This will eliminate unnecessary cycling of the line-contactor relay during a normal condition 1).

the

erugiF.feR(

NOTE: The

I

starter/generator does not require a reset when the generator control panel reverse-current-protection tripped. The generator control panel will automatically reset its internal circuitry.

circuit has been

starter/generator reverse-polarity buildup, the generator control panel protects by damage tripping an internal-field relay to de-energize the affected starter/generator.

In the from

case

of

the electrical system

OVERVOLTAGE PROTECTION

starter/generator output or bus voltage is supplied to the generator field at terminal A of the voltage regulation circuit fail, the affected starter/generator will attempt to assume the full load as its input voltage increases. If bus voltage increases above 28.25 ~t0.25 vdc, reverse current will begin to flow to the regulated starter/generator and the line-contactor relay will be opened, isolating the regulated starter/ generator from the buses. If the affected starter/generator output voltage rises above 32.5 vdc, it will be removed from the bus and the unaffected starter/generator will automatically be reconnected. The resultant voltage depends upon starter/generator speed, electrical load and the nature of the fault (Ref. Figure 1). I If

fault

a

occurs

where

starter/generator,

or

should the

panels monitor starter/generator output voltage at pin J for excessive voltage that could airplane electrical system. If starter/generator output exceeds 32.5 vdc, an inverse time delay will trip an intemal field relay to de-energize the starter/generator and open the line-contactor relay. Slight voltage surges will normally be associated with a longer time delay to prevent nuisance trips of the internal field relay, whereas a severe increase will cause an immediate trip. This overvoltage protection circuit requires a manual reset of the starter/generator to bring the starter/generator back on-line.

The generator control potentially damage the

completely separate circuit is used to open the line-contactor relay if voltage exceeds 40 vdc. This provides extra protection of the electrical system and allows a faster response to a fault because it does not work on a time delay. Manual reset of this individual circuit is not required because there is no time-delay mechanism.

A

An

overvoltage

can

condition

a

resistive connection in the

signal ground

wire to the generator control panel

generator

by the generator control panel with an alternate ground-return path. This ground allows the control panel to sense an otherwise undetectable overvoltage condition and provide an automatic trip of

the internal field

~ao

arising from

be detected

relay.

24-30-00

Apr 28/06Page

3

Raytheon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Provisions are made within the generator control panel to exercise the oven/oltage-protection circuit. When the generator control switch is moved from ON to OFF, voltage is removed from pin C of the generator control panel (line-contactor in), opening the line-contactor relay. Once in the OFF position, the generator control switch applies starter/generator output to pin P (overvoltage test) of the generator control panel, tripping the control panel overvoltage circuit and shutting down the starter/generator. This circuit allows the generator control panel to shut down its

starter/generator

without

creating

PANEL OVERVOLTAG E CIRCUIT CHECK

an actual overvoltage condition. Refer to GENERATOR CONTROL procedures in this chapter to verify proper operation of the overvoltage

circuit.

CROSS-START OVERLOAD CURRENT LIMITING The

generator control panels have

a

feature that limits the on-line

starter/generator output

current

during engine

cross-starts. This circuit

being or

used

as a

prevents the on-line starter/generator from providing excess current to the starter/generator starter. When either ignition/start switch on the pilot’s outboard subpanel is placed in either the ON

STARTER ONLY

position,

a

signal

circuit. The generator control

limiting R (Ref. Figure 1).

applied to pin R of the opposite generator control panel, enabling its current panel will then limit starter/generator output until the signal is removed from

is

pin

GENERATOR CONTROL RELAY The generator control relays are located on the Main Power Distribution Panel (A145) with the generator control panels. Each relay utilizes three sets of contacts and is energized when the respective ignition/start switch is placed in the ON

or

STARTER ONLY position. One set of contacts supplies

starter/generator output to voltage

at

pin

J of

the generator control panel, allowing the control panel to sense any overvoltage that may be present when the relay is de-energized. When the generator control relay is energized, the same set of contacts opens and removes power

from

J of the control

panel. This inhibits any generator output during starter operation. The two remaining sets only when the relay is energized. One set provides 28 vdc to energize the engine start relay and the other set shorts the shunt field of the starter/generator during engine starts, preventing transients from entering the generator control panel. are

pin

closed

BUS-TIE CONTROL PCB The bus-tie control

provide control of the bus-tie relays. relay is closed, the bus-tie sensing control pcb will close the generator bus-tie relays, powering the center, battery and opposite generator bus with I generator power (Ref. Figure 1). Whenever reverse current of 275 amperes or greater flows through one of the current sensors, the affected current sensor will signal the bus-tie control pcb to open the applicable generator bustie relay, thereby isolating the overcurrent to that bus. The bus-tie control pcb will close the battery bus-tie relay anytime the battery switch is placed in the ON position and no overcurrent exists. Battery power is then connected to the battery bus, center bus and triple-fed bus. Refer to Chapter 24-50-00 for more information on current sensor When the current

pcb

monitors the current

sensors are not

sensor

an

signals

and other

overcurrent and at least

inputs one

to

line-contactor

function.

Apr

24-30-00

~O

RaytheMI

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

GENERATOR BUS-TIE AND BUS-SENSE SWITCHES The

generator bus-tie switch, located on the pilot’s outboard subpanel, has several functions implemented through positions. The MAN CLOSED position manually closes the generator bus-tie relays through the bus-tie

three switch

pcb which also illuminates the green MAN TIES CLOSE annunciator. The NORM position allows the bus-tie analyze bus voltages and automatically close the generator bus-tie relays when no fault exists (Ref. Figure 1). I

control

pcb

to

The bus-sense switch,

adjacent to the bus-tie control switch, simulates an overcurrent condition by applying voltage anytime it is placed in the TEST position. The switch must be moved to RESET anytime the bus-tie relays have been opened by an overcurrent or test. The switch does not influence the system when in the NORM position. Refer to Chapter 24-50-00 for detailed information on operation of the MAN TIES and BUS to all three current

sensors

SENSE switches. BUS-TIE RELAYS three bus-tie relays used to connect the three DC power sources to the main buses. They consist of the LH generator and RH generator bus-ties. The generator bus-tie relays are located on their respective Aft battery, Power Distribution Panel (A253 LH, A254 RH) and the battery bus-tie relay is located on the Battery Power

There

are

Distribution Panel

generator control when

they

are

(A228).

panel

to

Each generator bus-tie relay has two sets of auxiliary contacts. The first set allows the cente r bus voltage when the contacts are open and to sense gene rater bus voltage

sense

closed. The second set

provides

28 vdc to illuminate the

respective yellow

L GEN TIE OPEN

or

R

GEN TIE OPEN caution annunciator when the bus-tie

auxiliary contacts which provides is open (Ref. Figure 1). The bus-tie control

pcb

also

relay is open. The battery bus-tie relay has only one set of 28 vdc to illuminate the yellow BAT TIE OPEN caution message when the bus-tie

provides

an

interconnect for the generator control

panels during starter/generator

a connection from each generator control unit pin E to the bus-tie control pcb at pins parallel operation. 17 and 18. The bus-tie control pcb uses an internal relay to connect the paralleling channels when the line-contactor

It consists of

and bus-tie are

relays

are

closed. This feature

on-line with their bus-tie

nao

relays

ensures

that

load-sharing

is

possible only when

both

starter/generators

closed.

24-30-00

5

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Page

6~"226

24130100

Page Intentionally

Left Blank

A20

RBYtheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LH TART

(AIdSCRI

bOA

HGWBUSr E-

2)

(SHEET

TRIPLE-FED BUS FEEDER LIMITER

Ae

8´•

A

TR

D

(A253FB)

C´•

5A

I

I

I

BUS-TIE CONTROL CB

(A145CB29)

LH

ENGINE

STARTRELAYI (A251K2) I

i LH

LH

SENSE

13

SHUNT (A251RI)

6 CB

1

I

I

I

I

I

GND

I

I

I

I

I

IGNTTION/STARS SWITCH

I

I

I

I

FROM

I

12_9

LOADMETER

GENERATOR FIELD

I

(A251CB31

L CAUTION/

1

ISORY

LH

PANEL

BUS-TIE

LIMITER T E OPEN i CAUTION/ADVISORY

(A253FI)

(Ei53)

Al

A2

~50A

H

LINECONTACTOR

~5A

FEO

I

C9

I

I

I

I

I

I

i

PANEL

(SSEET

F

2)

REF

NO

3

NC

3

REF

(A2215211)

CB

(A251C85)

23

(Alr6CB63) RESET

(SHEET

SWITCH

GENERATOR

LH

CONTROL

RESET

CHAPTER

22

1

3

RESET

6

NORM

CHAPTER 32-30-00

VDC

SIGNAL

(LH)

IN

SIGNAL

OPEN

SWITCH

EXTERNAL

POWER

ON

SIGNAL

LH

NO

13 5

12

(A251t841

I I

4TEST

NC

di. a

arr

BUS-TIE

JNO

Cg NO

EXT

SIGNAL

CB

91LH

I

(SHEET

J

(SHEET (SHEET

2)

CURRENT

SENSOR

GENERATOR

POWER

SIGNAL

SENSOR

CURRENT

IIGROUND

POSITIVE

ENGINE

START

GENER/ITOR PIR*LLEL

SIGNAL

TEIIM

IN

(LH)

(LH)

(Ald6CB65)

2

LH GENERATOR CONTROL SWITCH

GEAR

21LH GEN BUS-TIE RELAY CONTROL

GENERATOR CONTROL PANEL CB LH

CI

NC

LANDING

2

C3

2)

28

TTE

IN START

ENGINE

BUS-SENSE

9US GEN

GEN

RESET

PANEL

24-40-00

RELAY (A251KI)

LH

SIGNAL

ON

(E153)

I

iH

TRIPLF_-

I3MLH GEN

NEGATIVE II

c

LEFT BUS-TIE

OFF

(SHEET BUS-TIE

RELAY

I

(A221S137)

I

I

I

I

I

I

I

i

I 03

1

i

CONTROL

PCB

[A2571

(A253Kll

I

275A

02

CENTER

Di

BUS

B

(SHEET

2)

C3 LH

C2

GROUND

POWER GEN

SENSE GROUND

VOLTAGE

FIELD

SENSE

POWER

I

G1

I

I

I

I

I

I

I

I

I

I

I

A2

L

Al I

8’

IN

J

OUT

H

I

I

I

i

I

i

I

I

1

I

I

I

I

I

I

LH

LINE

CONTACTOR

INTERPOLE

VOLTAGE

FIELD BUS

CONT

SENSE

VOLTAGE

VOLTAGE

OUT

M A

TEST

P

IN

C

PWR

K

OVERVOLTAGE LINE

CONTACTOR

GENERATOR

START-UP

ANTI-CYCLE CURRENT

PWR

LIMIT

SIGNAL

F

SIGNAL

R~

EOUALIZER

GENERATOR (AILSVRI

LH

CONTROL

BUS

E

GENERTOR

CONTROL

I

Dl

SENSE

CURRENT SENSOR (A227E285)

A3

I

GENERATOR

BUS-TIE

CI

(SHEET

(A145K1151

I

L

1

.28

VDC

SIGNAL

G

(SHEET

2)

RELAY

START IN

2)

E

PANEL C94FL2480862

C

System 2)

DC Generation and Control

Figure

A20

1

(Sheet

1 of

24-30-00

Page 7 Apr 28/06

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RH

(A145CR3)

A

bOA

I)~i

(SHEET

7.

TRIPLE-FED BUS FEEDER LIMITER

B

(SHEET

(SHEET

H

(A254F8)

[Ala5CR21

BUS-TIE CONTROL CB

D

BUS

RH

5

8+ C~

BUS-TIE LIMITER

(A254F

CLOSE 6

I

A2.

TTERY

.Al

IOA

NORM

RH GENERATOR CONTROL PANEL CB

2

Y

30

OPEN 60A I

_h

I

(A252C851 ENGINE START RELAY RH

GENERATOR

(A228FIOI

BUS-TIE SWITCH

(A252K2)

(A221210)

28 R RH

START

ENGINE GEN

SWITCH BUS

MANUAL

ON

SIGNAL

´•I

I

I

12’

SENSOR

BATTERY

RH

I

SWITCH

ON

SENSOR

SIG

CURRENT

SENSOR

PWR

CURRENT

SENSOR

SIG

RELAY

TIE

I

I

I

31

1

MAN

GROUND FROM IGNITION/START SWITCH

i

CAUTION/ADVISORY

BUS

TIE

SORY

GEN

TIE

OPEN

RH

RH

GENERATOR FIELD 6 SENSE CB

(A252C831

GENERATOR

R

CONTROL

12

3

11

71

I

RIGHT BUS-TIE

4

(SHEEI

CURRENT

7

PANEL CB (A252C84)

II

GENERATOR

RH LINECONTACTOR RELAY

I

SENSOR

A2

Al

(A228E2361

(A252KI

RIGHT

4

CONT

SIGNAL

(A252RI)

A21~1

13

PANEL

1351

CONTROL

RELAY

I~b

LOAOMETER SHUNT

12 II

NO

BUS-TIE

BATTERY

RH

1

13_

PANEL

(E153)

1 122

T

POWER

BATTERY BUS

I

IOA

ANN

BATTERY

GEN

I

CLOSE

CLOSE

GEN CURRENT

RH

I

21

ON/ CURRENT

I

23

OPEN

(E153) RH

I

IN

(NEG)

MANUAL TIE

I

61

VOC

SIGNAL

SWITCH MAN

IIE

TIE

GEN

GEN

E-

BUS

4 MANUAL

CEN

GEN

(A146C866)

250A

11

I

/START

LH

c

IN

GROUND

3

RESET

(SHEET

(SHEET NO

5

CI NC

RH

ENGINE

START

SIGNAL

RH GENERATOR PARALLEL

(POS)

TERM

ON

IN

BUS-TIE

CONTROL

PCB

BATTERY BUS-TIE CURRENT SENSOR (A228E2343

(A257)

j

(SHEET

23

a 31-

1

I

CAU

-1

~21

TON/

RH GENERATOR CONTROL SWITCH (A221S1381

(E153)

SORY

2

OFF PANEL

PANEL

2

275A

NO

R GEN T CAUTION/ADVISORY

T

22

c2

(SHEET

D

(E153)

1

03

A2

02

01 BATTERY

I

CURRENT

..I

I

I

I

I

I

SHUNT

I-

I

I

I_Ca C2

MONITOR

(BTioi

A2

BATTERY BUS-TIE RELAY (K121Kll

-1

:P Al

G

(SHEET

RH GENERATOR CONTROL

SWITCH

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

28

II

I I

I

I

L--1LIPOWER ,BIGEN

I

VDC START IN’ SICN"L

U

I

I

I

I

L--~--IHILINE

C

BATTERY BUS

(n124C814]

3

SENSE IN

CONTACTOR CONT

INTERPOLE

OUT

VOLTAGE SENSE

~PIOVERVOLTAGE

jh

BATTERY BUS CONTROL CB

GROUND

VOLTAGE

MI FIELD VOLTAGE OUT

(AldSKI16)

h

I

D

RELAY

(A221S1771

i*aaslrlsal

I

JI FIELD POWER

BATTERY BATTERY RELAY

2

GIGROUNO SENSE

A3

REF CHAPTER 24-31 -00

BATTERY

SWITCH

I

I

(R1201 5

(A2215277)

I

2

BATTERY

~"3

n I r

CI

L

LINE

TEST

CONTACTOR POWER

KIGEN START-UP

5A

IN

POWER

FI ANTI-CYCLE SIGNAL

I

I

p A2

BATTERY BuS RCcB

I

o´•-----

IAIBUS E

BATTERY RELAY CB

E

(A124CB151

(SHEET

(A228CB156)

VOLTAGE

EOUALILER

I) Z----IRICURRENT

SENSE

BUS

LIMIT

SIGNAL

GENERATOR CONTROL (Al 45VR2)

RH

PANEL C9dFL2dB0861

C

DC Generation and Control

Figure

Page 8 Apr 28/06

24-30-00

1

(Sheet

2 of

System 2)

A20

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TROUBLESHOOTING

DC GENERATION AND CONTROL

generation troubleshooting is best accomplished by monitoring each of the generator control panel pins for voltage values shown in Chart 101, Chart 102 and Chart 103. All three charts clarify the operating mode and electrical check to be performed with chart headings and notes. By using the TK1999/935 generator control panel test unit (1, Chart 1, 24-00-00), readings can be obtained during the different operating modes and compared to those of a normal system. Refer to GENERATOR CONTROL PANEL TEST UNIT (TK1999/935) in this chapter for detailed information on building and operating the control panel test unit when troubleshooting the de generation system. All de

the resistance and

NOTE: The resistance values shown in Chart 101 will be obtained

during

checkout, but

even

approximate values. It is not expected that slight deviations may indicate a system fault.

are

identical values

it should not be necessary to check each of the inputs given in Chart 101, Chart 102 and Chart 103 to isolate defective component. Many times the description of the system malfunction is sufficient to indicate which circuits to check. Checking the ground wires and one or two specific circuits will normally isolate a fault. The Hawker

Usually

a

Corporation Super King Air B300 Wiring Diagram Manual should be used to trace specific wire routes pin and plug numbers. Many times a loose or faulty pin connection will cause a fault. Make sure that there are no loose, damaged or corroded pins in any system connectors. If a fault cannot be isolated with these general troubleshooting guidelines or checks, refer to the applicable chart in this chapter to isolate the fault. The steps in each chart should be followed sequentially unless otherwise specified. An example would be to proceed to the next step when there are no directions immediately following a NO condition. Beechcraft

and locate

CA UTION: Never apply make

sure

voltage

to

pin

H of the

that pins G and L

are

generator control panel. Never apply a ground to pins H or M. Always

well

grounded.

GENERA TOR CONTROL PANEL TEST UNIT

(TK1999/935)

generator control panel test unit (1, Chart 1, 24-00-00) should be used to gain access to the individual pins on the generator control panels when troubleshooting the de generation system. Refer to Figure 101 for component part numbers and a schematic for use when building the control panel test unit. Since maximum starter/generator output is 300 amperes, the 50 percent load specified in Chart 103 should be established by turning on enough electrical equipment to establish approximately 150 amperes of load on the electrical system. Refer to Chapter 24-50-00 for loads utilized by the various electrical systems and components.

A

Set up the generator control CAUTION: Never connect this may a.

Disconnect the

receptacle b.

panel

the control

airplane wiring panel

of the control

Connect the

plug

troubleshooting

disconnect the generator control

or

damage

test unit for

from the

as

follows:

panel

wire harness when the

engine

is

running

as

panel.

harness electrical connector from the control

panel

and connect it to the

test unit.

generator control panel

test unit to the control

panel receptacle

perform voltage

to

checks. NOTE: Do not connect the generator control

CAUTION: Never apply make

~a4

sure

voltage

panel

to pin H of the

that pins G and L

are

to the test unit when

checking

resistance and

continuity

values.

generator control panel. Never apply a ground to pins H or M. Always

well

grounded.

24-30-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

A multimeter

or

volt/ohmmeter

(2,

measu re ments.

A d ig ital readout is

panel, ensuring

proper

polarity

24-00-00) accurate within 1 percent should be used for electrical pref erred. Connect the mete r to the jacks on the face of the generator control

Chart 1,

of the connections.

d.

Attach the generator control panel test unit alligator clip to the airplane structure to achieve a nonresistive ground. A nonresistive path to ground ensures the accuracy required for these electrical checks.

e.

Rotate the knob meter

f.

If

a

reading

on

the face of the

generator control panel

with the normal value shown in the chart

check of the

equalizer

generator control panel. A

circuit is

test unit to the

being

required, use the press-to-test drop at pin B is an indication

2 to 3 vdc

regarding potential equalizer

CAUTION: Never

replace

a

apply a ground to pin E of the good equalizer circuit. Refer to Chart 106 for further troubleshooting

switch to

of

a

STARTER/GENERATOR PARALLELING EQUALIZER CIRCUIT and information

pin being checked, then compare the

used.

circuit faults.

damaged generator control panel until proper operation being checked.

of the generator control

relay

is confirmed for the side g.

check of the generator control relay on the side being tested is required, rotate the knob control panel test unit to the OFF position and perform the check as instructed under If

a

on

the face of the

GENERATOR CONTROL RELAY CHECK in this chapter. CAUTION: Never connect or disconnect the generator control panel as

this may

damage

the control

h.

Disconnect the generator control

i.

Perform any

May

required

panel

when the

test unit when all electrical checks have been

maintenance before

24-30-00

wiring harness plug

engine is running

panel.

reconnecting

the control

panel.

performed.

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

P/N

RECEPTACLE

3

’irlrl

PLUG

I

F

I

I

G

I

.I.

Ki LI M

I

I

1

i

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i

1111

i

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Illir 1~11111

7’1

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I

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I

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I

i

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i

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i

i

1

1

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1

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I

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i

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i

i

I

I

I

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I

1

I

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I

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1

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P/N

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1

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K

1

CLIP

E D

AMP. CLIP. GROMI~IET.

N

C

2 EA REOD. ~OUNi CLAMFS INSIDE eox To SUPPORT WIRE SUNDLE

I

INI

24

i

P

C

a

SLACX

sy I I

A

’LEXIBLE T Si WIRE

OFF

ORIGINAL As Received By ATP

3

MS~S041-8 327

BULB

LIGHT

i 30-1 OR-3 GRAYHILL N/O SWITCH

REGBANPNA-JACK

ROTARY

SWITCH CENIRALA? P/N

[OR

pOS

AND KNOB PA 300

NEG

2~

BOX, P/N

EOUIV.)

BLACK BANANA IACK

6UD CU-~iOG-A

NOTE: A

i

WIR_

WIRE, iO

EXCEPT BLACK GROUNO BE 8 GAGE MIL-W-50e6

C94FL24B08

Generator Control Panel Test Unit

Figure

A24

7

C

(TK1999/935)

101

24-30-00

Page

yaM301

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STARTER/GENERA TOR PARALLELING EQUALIZER CIRCUIT One of the

problems encountered with the equalizer circuit during starter/generator paralleling is a starter/generator and the control panel itself. To assist in troubleshooting the Chart 106, the following information is provided to explain the effect of resistive connections

more common

resistive connection between the

equalizer on

the

circuit with

equalizer circuit.

operating in parallel, proper operation of the equalizer circuit is dependant starter/generator and its generator control panel. Voltage at pin B of upon the generator control panel must be the same as voltage at terminal B of the starter/generator. Voltage at pin D of the generator control panel must also be the same as voltage at terminal D of the starter/generator. If either of these connections for either side of the system causes a voltage drop between the generator control panel and the starter/ generator, an adjustment of field voltage by the generator control panel will cause an out-of-parallel condition. For example, if the output at terminal B of the starter/generator was subject to a 2.0-vdc drop before reaching pin B of its generator control panel, the control panel would compensate and raise the starter/generator output by 2.0 vdc. This rise in starter/generator output will cause the affected starter/generator to carry more of a load. An out-ofparallel condition would exist, with the control panel unable to compensate because it had adjusted to an erroneous input. With both a

starter/generators

on-line and

nonresistive connection between each

NOTE: The generator control panel regulator circuit will not adjust starter/generator output more than 2.0 vdc in either direction; consequently, the control panel will not parallel the starter/generators if the voltage difference is too great.

Many times a resistive connection to ground potential ground faults in the equalizer circuit.

will also

cause an

equalization

fault. Use Chart 106 to isolate any

GENERATOR CONTROL PANEL OVERVOLTAGE CIRCUIT CHECK NOTE: A multimeter

or

volt/ohmmeter

measurements. A

digital

(2,

Chart 1,

readout is

24-00-00) preferred.

accurate within 1

percent should be used for electrical

overvoltage circuit of the generator control panel can be tested during the performance of a normal inspection without disturbing the voltage adjustment and without subjecting the electrical system voltage. Refer to Chapter 5-00-00 for the specified inspection interval.

The

maintenance to excessive

Connect the meter to pin J of the generator control panel. With the generator to be tested operating, set the respective generator control switch to OFF and observe the meter. The voltage on the meter should change from 28.25

0.25 vdc to residual

indicates

May

a

faulty overvoltage

voltage (approximately

24-30-00

vdc). panel.

0.3 to 2.0

circuit in the generator control

Failure of

pin

J to

drop

to residual

voltage

nn4

Hawker Beechcraff

Corporation

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

GENERA TOR CONTROL PANEL REVERSE CURRENT CIRCUIT CHECK a.

Refer to the Hawker Beechcraft hand

b.

c.

Corporation Super King

Operating

Handbook and start the left

engine.

Bring the left hand starter/generator position, then release to ON. Refer to the Hawker Beechcraft hand

Air 8300 Pilot’s

on-line

by placing

the left hand generator control switch in the RESET

Corporation Super King

Air 8300 Pilot’s

Operating

Handbook and start the

right

engine.

d.

Bring the right hand starter/generator position, then release to ON.

e.

Place the fuel-shutoff valve for the

f.

Monitor the right hand loadmeter. It should gradually decrease the reading until a spike or zero is indicated, signaling that the generator control panel has sensed reverse current and has shut down the starter/generator. If the engine is motored by the starter/generator after engine shutdown, a faulty reverse-current-protection

on-line

by placing

right engine

the

in the OFF

Fight

hand generator control switch in the RESET

position

to shut down the

right

hand

engine.

circuit is indicated.

g.

Refer to Section IV of the Hawker Beechcraft start the

right

h.

Bring

i.

Repeat steps

nas

the

hand

right

hand

e

Corporation Super King

Air 8300 Pilot’s

Operating

Handbook and

engine.

starter/generator

on

line.

and f for the left hand side of the system.

24-30-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 101

Troubleshooting DC Generation and Control Continuity Values in ohms at Control Unit Connector (1) GEN SWITCH POSITION

FUNTION

PIN

ON

OFF

I

A

Bus

Voltage Signal Input Signal

B

Gen Voltage

C

Line Contactor

In

D

I Interpole Voltage Signal

E

I Equalizer Battery

F

In

(2) (3)

138

(2) (3)

0.3

(4) (5)

0.3

(4) (5)

0.3

(4) (5)

0.7

(4) (5)

I Line Contactor Control Out

Ground

Regulator

0 to 0.4

0 to 0.3

0 to 0.3

0 to 0.3

38k

38k

38k

0.4

Power In

Gen Start-Up Power in

0.4

(4) (5)

(4) (5)

(Reset)

Power Ground

L

0 to 0.4

C

(4) (7)

18(6) (7)

H

I

138

(Reset)

I Signal

K

(2) (3)

In

G

J

138

In

Voltage Signal

RESET

I Regulator

P

I Overvoltage

R

I Cross-start Current Limiting

(4) (5)

0.8

(4) (5)

0 to 0.3

0 to 0.3

0 to 0.3

2.6

2.6

2.6

386

386

Power Out

M

0.4

0.5

Test

386

NOTES: 1. Chart 101 resistance and

continuity

checks should be made with the

battery OFF,

external power

OFF, engines

OFF and the GCU disconnected.

2. Bus sense circuit breaker closed. Resistance may vary due to bus loads.

3. Bus

sense

circuit breaker open.

4. Generator field and

5. Generator field and

sense

sense

circuit breaker closed.

Reading

may vary due to

wiring and circuit breaker resistance.

circuit breaker open.

6. Generator reset circuit breaker closed. Resistance may vary due to bus loads.

7. Generator reset circuit breaker open.

Page

yaM601

1/08

24-30-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102 DC Generation and Control

Troubleshooting Voltage Values at

Control Unit Connector

(1)

GEN SWITCH POSITION

ENGINE

FUNTION

PIN

ON

OFF Bus

A

Voltage Signal Input

24 0

B

Gen

Voltage Signal

Line Contactor

C

In

Voltage

In

Signal

Interpole Voltage Signal

D

I Equalizer

E F

Battery

G

I Signal

In

(Reset)

Ground

Line Contactor Control

H

Out

J

Regulator

Power In

Gen

Start-Up (Reset)

K

Power in

Power Ground

L

I Regulator

M

Power Out

Overvoltage

P

Test

Cross-start Current

R

Limiting

(2) (3)

24

0

RESET

(2) (3)

24 0

CRANKING

(2) (3)

15/20

0

0

0

12/18

0

0

0

0/0

0

0

0

6/2

0

0

24

6/2

0

0

0

0/0

0

0

0

0/0

0

0

0

0/0

0

0

0

0/0

O

0

O

0/0

0

0

0

0/0

0

0

0

6/2

0

0

0

0/0

0

0

0

15/20

(4)

NOTES: 1. Chart 102

voltage

exception

2. Bus

sense

circuit breaker closed.

3. Bus

sense

circuit breaker open.

4. With the

battery ON, external engine cranking (see note 4).

checks should be made with the

GCU connected, with the

of

Voltage may

vary with

power OFF,

battery charge

engines OFF

and the

and loads.

generator control switch in the OFF position, crank the engine on the side being checked. The initially, while the second value occurs just before cranking is discontinued.

first value is obtained

A24

24-30-00May

1/08

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 103

Troubleshooting

DC Generation and Control ENGINE

Bus

Voltage Signal Input

B

Gen

Voltage Signal

C

Line Contactor

A

I

In

Voltage Signal

I Interpole Voltage Signal

E

IEqualizer

G

Battery

I Signal

In

26

In

Ground

J

Regulator Gen

26

(Reset)

Line Contactor Control Out

I

RESET

In

H

K

Power In

Start-Up

1

Power in

(Reset)

Power Ground

L

M

I Regulator

P

I Overvoltage

R

I Cross-start

(4)

ENGINE SHUTDOWN

1

Limiting

ON

OFF

(2)

(3)

28

(6)

28/28

28/28

28

(6)

28/25

i/0

(4)

28.2

28/25

0/0

(5)

0/0.2

0/0

-1(5)

0/0.2

0/0

26

0

0/0

0/0

0

0

0

0/0

0/0

0

0

26 to 28

26 to 28/0

0/0

0

0

0

0

0

0

0

-1

1

(4)

28

(6)

0

28

(6)

0

Test

Connector(l)

GEN SWITCH POSITION

ON

(6)

28

0

Power Out

Current

70% N1 LOAD 8 50%

OFF

1

D

F

Values at Control Unit

GEN SWITCH POSITION

FUNTION

PIN

Voltage

(4) 0

0 4

(7)

0.2

(8)

0.035

(8)

8

1/0

28/25

(6)

28

(4)

0

0/0

0/0

0

0/0

0/0

4/22

0/0

(7)

0.2

0.2/0

(8)

0.035

(8)

(8)

1/0(8) 0/0

0.035(8)

NOTES:

voltage measurements are made position unless otherwise indicated. 1. All

with

one

engine running

and the generator control switch in the

specified

voltage measurements for this switch position should be made with both generators on-line and operating in parallel. Shut down the engine on the side of the starter/generator under test. The first value given is at engine shutdown. The second value is just before the line contactor relay opens.

2. All

relay opens, place the generator control switch in the OFF The second value is when the engine stops rotating.

3. After the line contactor

reading. 4.

Approximation of

residual

voltage. May

position

and take the first

vary from 0.3 to 2.0 vdc.

Starter/generator current, interpole voltage is negative with respect to ground. The voltage will upon starter/generator current. A negative 2 volt is proportional 300 amperes of output current.

5.

6. Generator 7. Variable

voltage

0.25 vdc after

approximately

one

depending

second.

output. The average voltage value will vary with starter/generator speed and load.

8. GCU internal

Page

should stabilize at 28.25

vary

voltage.

24-30-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 104

DC Generation and Control Starter/Generator Does Not Reset

STEP 1

Is 0.3-2.0 vdc at

(See

Note

pin

B of the control

panel?

YES

Proceed to

Step

7.

YES

Proceed to

Step

4.

YES

Close circuit breaker after

1.)

NO STEP 2

Is the generator field and

sense

circuit

breaker closed?

NO STEP 3

pins B, K (See Note 2.)

Are

or

J shorted to

ground?

correcting

locating

and

short.

NO

Close circuit breaker. STEP 4

Is a negative voltage panel? (See Note 7.)

at

pin

B of the control

YES

Shut down both the

YES

Proceed to

starter/generator and engine, then operate the unit as a starter to eliminate reverse polarity build-up.

NO STEP 5

Is there 0.3-2.0 vdc at terminal B of the

starter/generator? (See

Step

6.

1.)

Note

NO

Faulty starter/generator. STEP 6

Does the generator field and breaker check for

sense

circuit

YES

continuity?

Locate fault in on

the

control

siring between terminal B starter/generator and pin B on the panel.

NO

Replace faulty STEP 7

circuit breaker.

Is there 0.3-2.0 vdc at

panel? (See

Note

pin

J of the control

YES

Proceed to

Step

11.

YES

Proceed to

Step

9.

1.)

NO

STEP 8

Is there 0.3-2.0 vdc at terminal D3 of the

generator control relay? (See Note 1.) NO Find wiring break between the starter/ generator terminal B and the generator control relay. NO

A24

24-30-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 104 DC Generation and Control

Starter/Generator Does Not Reset STEP 9

Is there 0.3-2.0 vdc at terminal D2 of the

YES

generator control relay?

(Continued) fault between

Locate and correct

wiring

terminal D2

generator control relay

and

pin

J

on

on

the

the control

panel.

NO

STEP 10

Is

voltage being applied to the generator relay coil at any time other than engine start?

YES

control

Locate the circuit

so

source

that the

of power and correct the

generator control relay

energizes during engine

start

only.

NO

Replace faulty relay. STEP 11

Is there 0.3-2.0 vdc at

panel during

pin

K of the control

YES

Proceed to

Step

12.

YES

Proceed to

Step

14.

YES

System

reset?

NO

Faulty generator control

switch

or

wiring

fault

between switch and generator control panel pin K. Locate and correct the wiring fault or

replace STEP 12

the switch.

(See Note 2.)

Is there 0.3-2.0 vdc at

panel during

pin

M of the control

reset?

NO

STEP 13

Is there field voltage at pin M of the control panel during reset? (See Note 6.)

is functional.

NO Proceed to STEP 14

Step

15.

Is there

continuity between terminal A of the starter/generator and pin M on the generator control panel? (See Note 2.)

YES

If it is determined that residual

voltage is at starter/generator, and the building to 28.25 0.25 vdc,

terminal A of the

unit is not

suspect

an

internal fault of the starter/

generator. NO

wiring fault between terminal A on the starter/generator and pin M on the generator control panel. Correct

I STEP 15

Is

pin G properly grounded? (See

Note

2.)

YES

Proceed to

Step

16.

NO Restore full

(See

Page

Note

continuity 5.)

to

ground.

11024-30-00

n24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 104 DC Generation and Control

Starter/Generator Does Not Reset STEP 16

Is

pin

L

properly grounded?

(Continued)

YES

Suspect a fault of the generator control panel. (See Note 4.) If the fault is still not identified, perform the steps in Chart 104 again to recheck the system. Chart 101 and Chart 102 may provide enough information to isolate the fault if still unidentified.

NO Restore full

(See

Note

continuity 5.)

to

ground.

NOTES: 1. This check is for residual

in the OFF

voltage

and should be made with

one

engine running

and the

generator control switch

position.

(3, Chart 1 24-00-00) is sufficient for these resistance and continuity checks. The engines battery and external power switched off, and the control panel disconnected.

2. An ohmmeter

be off, both the 3. The

generator control switch

4. Failure of the

must be

generator control relay

placed

in the RESET

position

to receive this

should

reading.

to short the shunt field of the

starter/generator can produce transient voltage spikes pin panel during engine spikes may be of sufficient magnitude to the control internal Before the control damage panel circuitry. panel, perform an operational check of replacing the generator control relay as outlined under GENERATOR CONTROL RELAY CHECK in this chapter. at

M of the control

start. These

System operation without a proper ground at pin G or L of the generator control panel may cause permanent damage to the internal circuitry of the control panel. If the system still does not function properly after restoring full continuity, suspect control panel internal damage due to operation with an inadequate ground. 5.

6. Field 7.

voltage

Voltage

at

indication of

na,

is variable

depending

upon

engine

RPM and electrical load. An indication of 5 to 10 vdc is normal.

pin B of the generator control panel must be positive for generator reset. A negative voltage starter/generator reverse polarity, and will prevent the starter/generator from resetting.

is

24-30-00May

an

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 105 DC Generation and Control Starter/Generator Does Not Come On Line STEP 1

starter/generatoroutput voltage at pin panel build to 28.25 f 0.25 vdc when the starter/generator is reset? (See Note 4.) Does

YES

Proceed to step 3 when bringing the first starter/generator on-line and to Step 4 when bringing the second on-line.

YES

Zero volts at

B of the control

NO

STEP 2

Isacondition

inthewiring betweenterminal starter/generator and pin B of the control panel causing a differential of output voltage between two pins when sensed by the control panel. (See Note 6.)

pin B of the control panel tripped field and sense circuit breaker, complete wiring break, or a trip of the control panel overvoltage circuit. A voltage differential indicates excess resistance in the circuit. (See Note 6.) indicates

B of the

a

Locate and correct the fault. NO

Starter/generator

is not

28.25 f 0.25 vdc

during

building output

to

reset. Use

Chart 104 to isolate the fault. STEP 3

YES

Proceed to

Step

1 1.

starter/generator voltage at pin B at least greater than the opposite unit’s voltage when sensed at pin A of the control panel? (See Note 3.)

YES

Proceed to

Step

11.

voltage readings at the center bus pin A of the control panel equivalent? (See Note 5.)

YES

starter/generator voltage at pin B at least greater than center bus voltage as sensed at pin A of the control panel? (See Note 2.) Is

0.5 vdc

NO The control

voltage

at

panel is sensing a higher pin A than pin B. Make sure that

external power is off. If it is, locate the source of voltage and correct the problem. STEP 4

Is

0.5 vdc

STEP 5

Are the

Possible

equalization fault. Use Chart

106 to

isolate the fault.

and

NO

STEP 6

Is there center bus

voltage at the center bus

YES

Proceed to

Step

7.

side of the current sensor?

NO Locate and correct

wiring

center bus and current

Page

fault between the

sensor.

11224-30-00

n24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 105 DC Generation and Control

Starter/Generator Does Not Come On Line STEP 7

Is there center bus

voltage

at the bus-tie

(Continued)

YES

Proceed to

Step

8.

YES

Proceed to

Step

9.

YES

Proceed to

Step

10.

side of the current sensor? NO Check the current STEP 8

sensor

Is there center bus

for

voltage

continuity.

at both

terminals of the generator control circuit breaker?

panel

NO

Reset circuit breaker. breaker if

STEP 9

continuity

Is there center bus

Replace faulty circuit

is not restored.

voltage

at

pin

23 of the

relay?

bus-tie

NO Locate and correct current

sensor

and

wiring fault between pin 23 on the bus-tie

relay. STEP 10

Is there center bus bus-tie

voltage

at

pin

22 of the

YES

relay?

wiring fault relay and pin control panel. generator Locate and correct

22

on

the bus-tie

between A

on

pin

the

NO

Faulty STEP 11

bus-tie

relay auxiliary

Is there 28 vdc at

control

pin C of

contacts.

the

generator

YES

Proceed to

Step

13.

panel?

NO STEP 12

Does the

generator control switch check for

continuity across the contacts when ON position? (See Note 1.)

YES

Locate and correct

wiring

fault between

generator control switch and pin C control panel.

in the

on

the

NO

Replace faulty STEP 13

switch.

pin H of the generator panel? (See Note 7.)

Is there 28 vdc at control

YES

Proceed to

Step

14.

YES

Proceed to

Step

15.

NO

Faulty generator STEP 14

control

panel.

Is there 28 vdc at the line-contactor

relay

coil? NO

A24

24-30-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 105 DC Generation and Control

Starter/Generator Does Not Come On Line

(Continued)

Locate and correct the line-contactor

generator control STEP 15

wiring break between relay coil and pin H on the panel.

Is the line-contactor

relay

coil

grounded.

YES

Proceed to

Step

16.

NO Restore full

STEP 16

continuity

to

ground.

starter/generator voltage

Is there

terminal Al of the line-contactor

If the L DC GEN

YES

at

or

R DC GEN annunciator

is illuminated troubleshoot the annunciator

relay?

circuit for

a

fault.

NO

Replace faulty line-contactor relay. NOTES: i. Resistance and

continuity

checks should be made with the

switches off and the generator control

panel

2.The

generator control panel circuit breaker

3.The

opposite starter/generator

engines off,

both the

battery

and external power

disconnected. must be closed to receive this

must be on-line with the bus-tie

relay

reading.

and generator control circuit breakers

closed. 4. The 5.

generator field and

sense

circuit breaker must be closed to receive this

Voltage check should be made on the applies to Steps 5 through 10.

side that is

being brought on-line.

reading.

This bus-tie

relay should

be open. This

note

starter/generator output reading at pin B of the generator control panel will cause the equalization circuit voltage; consequently, the affected side will try to carry more of a load with both starterl on-line or generators go into overvoltage with only one on-line. 6. A false

to increase the field

7.

Anytime pin

8. If the

H is

to

generator control panel will not be

voltage replacing

Page

subjected

supplied panel.

a

voltage input, damage

senses

to the

generator control panel could result.

voltage, reverse current or an overvoltage condition, a control relay coil. Make sure that these faults do not exist before

differential

to the line-contactor

the control

24-30-00

P124

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 106

DC Generation and Control Generators Do Not Share Loads STEP 1

Are the loadmeters

of each

indicating the actual load starter/generator? (See Note 1.)

YES

Proceed to

Step

2.

YES

Proceed to

Step

3.

YES

The

NO Check the loadmeter shunt and associated

wiring forfaults. If faulty loadmeter. STEP 2

Use the

~1

none are

found, replace the

generator control panel

Chart 1

24-00-00)

to

apply

a

test unit

ground

to

pin

E of the generator control panel. Is there approximately a 2.0 vdc suppression of

generator output voltage indicated? (See Note 2.) NO

Faulty generator STEP 3

control

panel.

Connect the generator control panel test unit opposite side control panel. Is

generator

control

panel equalization properly for both sides Proceed to Step 4.

to the

ci rcu it is fu nctioning

approximately a 2.0 vdc suppression of starter/generator output voltage indicated

during

when

a

ground

is

this test.

applied to pin E by the (See Note 2.)

control panel test unit?

NO

Faulty generator STEP 4

control

panel.

voltage from pin E of the applicable generator control panel present at pin 40 (left hand) or pin 29 (right hand) of the bus-tie control pcb? Is the

YES

Proceed to

Step

5.

NO

wiring fault between the pcb pin 40 (left hand) or and 29 pin E on the applicable (right hand) pin control panel. generator Locate and correct

bus-tie control

STEP 5

and

Read voltage at terminal D of the starter/ generator and pin D of the generator control panel. Are the voltages approximately equivalent between the starter/generator and generator control panel? (See Note 2 and Note 3.) (Perform check on both sides of the

system.)

YES

If the

voltage reading was approximately proceed to Step 6. If a reading of

-1.0 vdc,

was obtained, check the starter/ generator for a fault. If the unit is good,

0.0 vdc

locate and correct short to

generator

performed

control

if

a

relay

short is not evident.

NO

nz,

ground.

A

check should be

24-30-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 106 DC Generation and Control Generators Do Not Share Loads Locate the

source

starter/generator

(Continued)

of resistance between the

terminal D and

pin

D of the

generator control panel. Restore full continuity so there is no loss of voltage to the STEP 6

control

panel.

Does

condition exist in the

a

wiring between starter/generator and pin B panel that causes output

YES

terminal B of the

of the control

voltage

to differ before it is sensed at the

control

panel? (See

Note

4.)

pin B of the generator control panel indicates a tripped generator field and sense circuit breaker, complete wiring break or a starter/generator with no output. A slight drop in voltage indicates a loose or Zero vdc at

faulty

wire. Correct indicated fault.

NO

STEP 7

starter/generator have as the opposite potential ground E? terminal (See Note 5.) starter/generator Does terminal E of the

the

YES

Proceed to

YES

The system should be functional now. If not, repeat the steps in this chart to find

Step

8.

same

NO

ground connections to the affected starter/generator. Restore full continuity to any inferior grounds. Check all

STEP 8

pins G and L of the control panel grounded? (See Note 6.)

Are

well

a

fault that may not have been evident the first time. If a problem is still apparent,

suspect

a

fault of the bus-tie control

pcb to

connect the

A check

of

in

equalizer channels. voltage and continuity values

Chart 101 and Chart 102 may isolate fault that has not been detected.

a

NO Restore full all

Page

ground

continuity

to

ground by checking

connections.

24-30-00

P124

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 106 DC Generation and Control Generators Do Not Share Loads

(Continued)

NOTES 1.

Bring

one

starter/generator on-line

and establish

a

constant 50% load

on

generator from the line and connect the opposite side. Record the reading indication should be the

same

if the loadmeters

are

indicating accurately,

the loadmeter. Disconnect the starter/

the

on

opposite loadmeter. The

and circuit resistance is the

same

for

both sides. 2. Use the control

conducted with

panel test unit (1, Chart 1,24-00-00) shown starter/generator on-line and a 50% load.

in

Figure

101 to

perform

this test. It should be

one

is negative with respect to ground and will change with respect to starter/generator output current. A -1.0 vdc is normal for a 50% load. A small variation in circuit resistance will cause the approximately reading equalizer circuit to adjust to an out-of-parallel condition when none exists. 3.

Voltage of

4. A false

starter/generator output reading at pin B on the control panel voltage, and consequently the affected side will carry

increase the field 5. a

Many times voltmeter,

an

one

ohmmeter will not be sufficient to

engine running,

and

a

50% load. A

measure a

will

cause

more

of

a

the

small deviation from

voltage reading

of 1.0-3.0 vdc

equalization

circuit to

load.

ground.

or

Make the check with

greater indicates

an

inferior

ground. 6. An ohmmeter is insufficient for this check. Make the check with

load.

M4

Voltage readings

of

approximately

0.0 for

pin

G and -0.1 for

a

one engine running, acceptable

voltmeter,

pin

L

are

24-30-00

and

a

50%

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 107 DC Generation and Control Bus-Ties Not STEP 1

When Generator Is

generator bus-tie control

Are either of the

circuit breakers

Closing

Brought

On-line

YES

Close circuit breaker.

YES

Proceed to

Step

3.

YES

Proceed to

Step

4.

YES

Check the buses for

open?

NO STEP 2

Isthere28vdcatpins2 (lefthand)or4(right hand) of the bus-tie control pcb. (See Note 3.) NO Locate and correct

wiring

fault between the

bus-tie control circuit breaker and

hand) STEP 3

or

pin

4

(right hand) of

Is there 28 vdc at

pin

2

pin

2

(left pcb.

the bus-tie

(left hand) or pin pcb?

4

of the bus-tie control

(right hand) (See Note 3.) STEP 4

Is the bus-tie control overcurrent

pcb receiving an signal from the current sensors?

a

275 amp

or

greater

overcurrent.

NO

STEP 5

Fault is in the bus-tie control

pcb.

Is there 28 vdc at the bus-tie

relay coil?

YES

Proceed to

YES

Faulty

Step

6.

NO

continuity from pin 2 (left hand) or pin (right hand) on the bus-tie control pcb to the applicable bus-tie relay coil. Restore

4

STEP 6

Does the bus-tie

relay

coil have

continuity

to

bus-tie

relay.

ground? NO Restore

continuity

to

ground.

NOTES: 1. The generator bus-tie switch should be in voltage checks.

2.

Manually closing

the bus-tie

relays

when

the normal

an

position

overcurrent is

with both

present may

generators on-line for all generator

cause

damage to the airplane

electrical

system.

Many times a voltage will continuity. 3.

May

1/08Page

118

be present at the connector, but

24-30-00

a

loose connection at the

pin

itself will not allow circuit

na4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 108 DC Generation and Control

Bus-Ties Not STEP 1

Is 28 vde at

test?

during

pin 4 of each current (See Note 1.)

Opening During

sensor

Test

YES

Proceed to

YES

Close circuit breaker.

Step

5.

NO STEP 2

Is the bus-tie indicator circuit breaker

(A146CB65) open? NO STEP 3

Is there 28 vdc at terminal 4 of the bus-sense

YES

Locate and correct

wiring

fault between

terminal 4 of the bus-sense switch and

switch?

4 of the current sensor for the bus-tie

that is not

pin relay

opening.

NO STEP 4

Is 28 vdc at terminal 5 of the bus-sense

bus-sense switch.

YES

Faulty

YES

Proceed to

switch? NO

Locate and correct

wiring

fault between bus-

tie indicator circuit breaker and the bus-sense switch. STEP 5

Is 28 vdc at

pin

3 of each current sensor?

Step

9.

NO

STEP 6

Is there 28 vdc at bus-tie control

STEP 7

pins 13, pcb?

Is there 28 vdc at

control

pins

14 and 15 of the

1 and 6 of the bus-tie

YES

YES

pcb?

Locate and correct

wiring

bus-tie control

and current

pcb

fault between

sensor(s).

Faulty bus-tie control circuitry. Repair replace the pcb as required.

or

NO STEP 8

Are the bus-tie control circuit breakers

YES

Locate and correct

the bus-tie control

closed?

wiring fault between pcb and bus-tie control

circuit breakers. NO

Close circuit STEP 9

breaker(s).

Are the current

signal

sensors

receiving a ground pcb at pin i?

YES

Proceed to

Step

12.

from the bus-tie control

NO

A24

24-30-00

Page

yaM91

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 108

DC Generation and Control Bus-Ties Not

STEP 10

pins 7, 9 grounded?

Are

Opening During

and 36 of the bus-tie control

pcb

YES

Test

(Continued) Locate and correct the bus-tie control current

wiring fault pcb and pin

between 1 of the

sensor(s).

NO

being applied during test. Repair replace faulty bus-tie control pcb as required.

Ground not or

STEP 11

Is

pin

2 of each current

sensor

grounded?

YES

Faulty

current

YES

Faulty

bus-tie control

sensor.

NO

continuity sensor(s).

Restore current

STEP 12

to

ground

for

pin

Is 28 vdc at the coil of any bus-tie

2 of the

relay?

replace

as

pcb. Repair

or

required.

NO

Faulty

bus-tie

relay(s). Replace

as

required.

NOTES: 1. Make

sure

that

battery voltage

is

on

the buses

by selecting

the L GEN, R GEN and BAT

positions

with the

VOLTMETER SELECT switch.

May

24-30-00

A24

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SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

DC GENERATION AND CONTROL

STARTEF/GENERA TOR REMOVAL Removal of the

NOTE:

unscheduled

Chapter

starter/generator may require additional inspections per the engine manufactures inspections. The inspections should be complied with prior to returning the airplane to service. 71-10-00 and

a.

Refer to

b.

Removeallelectrical

c.

Remove the

d.

Tag

e.

Loosen the

adapter clamp (10)

adapter(l)

from the unit.

f.

the

engine cowling.

powerfromtheairplane.

cover screws

and disconnect all

Pull the

remove

and terminal block

wiring

cooling adapter (11)

from the

cover

to access the terminal

lugs.

starter/generator (9) (Ref. Figure 201).

at the forward end of the

down from the unit

enough

starter/generator (9)

to

and

remove

the

cooling

cap

prevent interference during starter/generator (9)

removal.

mandatory that the starter-generator be fully supported from the time the quick-disconnect clamp is engine. The starter-generator must never be allowed to support its own weight through the splined-shaft engagement, as damage to the shaft-shear section will

CAUTION: It is

loosened until the unit is removed from the result.

g.

(7) on the quick-disconnect clamp (2) mounting adapter (5).

Loosen the T-bolt disconnect the

clamp (2)

and

h.

Open

i.

Remove and discard the

remove

the

O-ring (8)

which attaches the

starter/generator (9)

from the

splined

from the

starter/generator (9)

to the

quick-

mounting adapter (5).

drive shaft.

STARTEWGENERA TOR INSTALLA TION NOTE:

Removal of the unscheduled

a.

Install

a new

starter/generator

may

inspections. The inspections

O-ring (8)

on

require

additional

should be

the starter-generator

splined

complied

inspections per the engine manufactures prior to returning the airplane to service.

with

drive shaft

(Ref. Figure 201).

mandatory that the starter/generator be fully supported from the time the unit is placed in position, clamp is installed and properly torqued. The starter/generator must never be allowed to support own weight through the splined-shaft engagement, or damage to the shaft-shear section will result.

CAUTION: It is

until the its b.

Align

mating pins on the starter/generator (9) with the quick-disconnect mounting adapter (5), then flanges with the quick-disconnect clamp (2). Using an inspection mirror, ensure that the clamp fully captures both mating flanges to provide a secure mount.

the four

encompass the

groove NOTE: The c.

engine

uses

wet

splines,

therefore lubrication of the

splines

is necessary.

correctly positioned, use a soft-headed hammer to tap around the circumference clamp (2). Tighten the T-bolt (7) to 32 inch-pounds, then tap around the circumference disconnect clamp (2) again. The clamp should now be evenly seated around both flanges.

When the unit is

of the

disconnect

of the

NOTE:

~20

Apply dry film

lubricant

(3,

Chart 2,

24-00-00)

to T-bolt

(7) threads before

quickquick-

final torque.

24-30-00Page

201

I

Ray~heon

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SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

d.

While the

clamp (2)

e.

Slide the

adapter clamp (10) onto the starter/generator (9) starter/generator (9).

is

correctly positioned, torque the T-bolt (7) retaining and

position

nut to

the

a

final torque of 50

cooling adapter (11)

inch-pounds.

on

the lower

end of the

cooling adapter (11).

Place the

g.

Adjust the cooling cap adapter(l) until the alignment provides a good seal; then position clamp (10) to 25 inch-pounds. Verify that the ductwork is properly aligned and secure.

cooling

cap

adapter (1)

CA UTION: The self-locking nuts

torque h.

or

damage

over

the

starter/generator (9)

and

with the

f.

align

and

tighten the adapter

securing the airplane wiring to the starter/generator must be tightened to the proper starter/generator or attaching hardware.

to the

or the Seech Super King Air 8300 Torque the 3/8-inch terminal nuts to 220-235 inch-pounds. Torque the 5/18inch 125-135 inch-pounds. Torque any #10-32 terminal nuts to 20-25 inch-pounds.

Connect all electrical wiring to the starter/generator (9) according to tags

Wiring Diagram terminal nuts to

Manual.

i.

Secure the terminal block

j.

Restore electrical power to the

k.

Start the

cover

to the

starter/generator (9)

with

screws

and washers.

airplane.

engine using procedures

outlined in Section IV of the Seech

Super King

Air 8300 Pilot’s

Operating

Handbook. I.

engine at idle speed for at least two minutes. Shut the engine down using procedures outlined in Section Super King Air 8300 Pilot’s Operating Handbook, and retorque the clamp (2) T-bolt (7) to 50 inch-pounds. Run the

IV of the 8eech

NOTE: If

torque has fallen below 25 inch-pounds, loosen the quick-disconnect clamp (2), check the starter/generator (9) for proper alignment, then follow steps b thru d and j thru 1 again to ensure proper installation of the unit.

m.

Safety

n.

Refer to

Apr

wire the T-bolt

(7) after torque

Chapter 71-10-00

has been verified.

and install the

28/0624-30-00

engine cowling.

A20

Ray~heon

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

7 8

10

‘I

I

12 13

I. 2. 3. 4. 5. 6. 7.

8. 9. 10. II. 12. 13.

COOLING CAP ADAPTER QUICK-OISCONNECT CLAMP NUT WASHER OUICK-DISCONNECT MOUNTING GASKET

ADAPTER

T-BOLT O-RING STARTER/GENERATOR ADAPTER CLAMP COOLING ADAPTER CLAMP COOLING

HOSE

C94FLadB1054

ORIGINAL As Recetved By ATP

Starter/Generator Installation

Figure 201

A20

24-30ooPage

203

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STARTER/GENERA TOR BRUSH INSPECTION

specified in Chapter 5. Replace the brushes if the wear limit will prior to the next inspection. When performing a thorough inspection of the brushes and commutator, remove the starter/generator from the engine using STARTER/GENERATOR REMOVAL procedures outlined in this chapter(Ref. Figure 202). I Inspect

the brushes in accordance with the interval

be reached

NOTE: Brush life varies with different

accordingly. are provided

operating conditions; consequently, inspection

intervals should be shortened

diagonal groove from one side of the contact surface to a point on the opposite wear can by the position of the groove on the contact surface. If the wear grooves indicate final brush is the 1/4 of its remaining life, or if inspection reveals the need for any maintenance, at or near any one the unit should be removed from the airplane and maintenance be performed in accordance with the Lucas Aerospace Power Equipment Corporation Manual in the Super King Air Series Component Maintenance Manual for the respective model starter/generator. Refer to STARTER/GENERATOR BRUSH REPLACEMENT procedures for simple brush replacement procedures.

The brushes side. Brush

with

a

be estimated

STARTER/GENERATOR BRUSH REPLACEMENT a.

Refer to

CAUTION:

b. c.

71-10-00 and

remove

the

engine cowling.

Always replace the starter/generator brushes as a set. inspection criteria or will exceed the wear limit before the

Refer to STARTER/GENERATOR REMOVAL in this Use the

d.

Chapter

a

clean rag moistened with solvent

(1,

Chart 2,

chapter and

24-00-00)

only one brush does not inspection, replace the entire set.

Even when next

remove

the

meet

starter/generator from the engine.

to remove any

foreign

matter

on

the exterior of

starter/generator.

Loosen the brush-cover

retaining screw and spread the

brush

cover

open. Remove the brush

cover

if necessary

(Ref. Figure 202). e.

f.

Using a low-pressure air supply, blow as much carbon and copper dust as possible out of the armature, windings, brush holder and commutator area. Use care not to blow particles into the bearings. Use

a

clean rag moistened with solvent

(1, Chart 2, 24-00-00)

to

remove

any

foreign

stater

matter in the starter/

generator.

low-pressure air supply, dry the

g.

Using

h.

Remove the

i.

Remove the brush

j.

Pull the brushes out of the holder.

k.

Make

with

a

a

screws

securing

areas

cleaned with solvent.

the brush leads to the brush holders.

spring clips.

visual check of the commutator before

installing

new

brushes. It should have

a

burnished appearance

only light filming.

NOTE: The

starter/generator uses cored brushes. This type of brush may cause the commutator to become grooved during normal operation. If any of the grooves are 0.020-inch deep or deeper, the unit should be overhauled.

I

I.

Perform brush run-in

m.

Install

Apr

28/06Page

204

new

procedures

as

outlined in the

Super King

brushes, ensuring that the top bevel is oriented

24-30-00

Air Series

Component

Maintenance Manual.

to the commutator’s rotation as shown in

Figure

202.

Raytheon

Aircraft

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

brushspringclips.

n.

Installthe

o.

Secure the brush leads with

p.

Install the brush cover,

q.

Install the

Refer to

ensuring

starter/generator

Chapter

screws

as

a

and

ensure

that the brush leads

proper seat in the

laid

over

the brush

spring clips.

recess.

outlined under STARTER/GENERATOR INSTALLATION in this

71-10-00 and install the

chapter.

engine cowling.

LAY BRUSH OVER SPRING AS

BRUSH WEAR GROOVE

housing

are

LEADS CLIPS SHOWN

I

-7t~

1/4 LIFE REMAINING

BRUSH LEAD SCREW

BRUSH SPRING CLIP

1/2 LIFE REMAINING

ROTATION

NEW

ORIGINAL As Received By ATP

A20

i/

O

f

C9dFL2dB1053

C

StarterlGenerator Brush Installation and Wear Limits

Figure

202

24-30-00

205

RBytheOn

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

GENERATOR CONTROL PANEL VOLTAGE CHECKAND ADJUSTMENT

Any time a voltage adjustment proper parallel operation.

I

NOTE: Do not

(Ref. a.

b.

Refer to

use

required

generator control panel, both panels

on one

the generator control

Starter/Generator

panel adjustments Paralleling).

Chapter 39-21-00 to

access

c.

Connect

d.

A multimeter

a

voltage adjustment voltage adjustment screw.

voltmeter to the voltmeter jacks located or

volt/ohmmeter

measurements. A

Start the

digital

to

compensate for

the Main Power Distribution Panel

Remove the screw, washer and expose each

e.

is

access

adjusted

to ensure

Out-Of- Parallel condition

(Al 45).

cover on

both generator control

the top of the RH control

on

(2, Chart 1, 24-00-00) preferred.

hole

an

must be

panels

to

panel.

accurate within 1% should be used for electrical

readout is

engines with procedures outlined in Section IV of the Beech Super King Air 8300 Pilot’s Operating Bring the RH starter/generator on-line by placing the RH generator control switch in the RESET

Handbook.

position;

I’ g. h.

then release to ON.

Place the generator bus-tie switch in the OPEN position to open the generator bus-tie relays. Adjust the generator control unit voltage with a light load or the generator control switch held in the reset position.

Insert

small screwdriver into the

a

Adjust

the

screw

voltage adjustment

clockwise to increase,

or

screw access

hole of the RH generator control

counterclockwise to decrease output until

a

reading

panel.

of 28.25 ~I0.25

vdc is obtained. i.

Place the RH generator control switch in the OFF

j.

Bring

k.

Repeat the adjustment procedure for the

I.

Shut down the

the LH

Operating m.

n.

Apr

starter/generator on-line.

engines

with

LH

generator control panel.

procedures outlined

in Section IV of the Beech

Super King Air

8300 Pilot’s

Handbook.

Disconnect the voltmeter.

Replace both voltage adjustment screws

a.

position.

access

hole

covers

and

secure

to the

generator control panels with

cover

and washers.

Refer to

Chapter 39-21-00

and install the

24-30-00

upholstery

and floorboards removed to

access

the distribution

panel.

uo

RBYtheOl

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

GENERA TOR CONTROL RELA Y CHECK a.

Refer to

Chapter

39-21-00 for the location and instructions

an

accessing

the Main Power Distribution Panel

(Al 45). b.

Referto GENERATOR CONTROL PANEL TEST UNIT in this test unit

(1,

Chart 1,

24-00-00)

to the

chapter and appropriate generator control panel.

connect the

monitoring the test lamp on the control panel test unit, place the battery switch appropriate ignition/start switch in the STARTER ONLY position.

generator control panel

in the ON

position and the

c.

While

d.

A normal indication is for the generator control panel test unit test lamp to glow continuously for the duration of the engine start. A bright flash when the ignition/start switch is released to OFF is normal. If the test lamp flashes

brightly at the instant the ignition/start switch Replace a faulty generator control relay.

is activated, the generator control

CA UTION: Never connect or disconnect the generator control panel as this may damage the control panel. test unit from the control

e.

Disconnect the generator control

f.

Reconnect the electrical connector to the generator control

g.

Install the floorboard and

~ao

panel

upholstery

as

outlined in

Chapter

relay

wiring harness plug

is not

operating properly.

when the

engine is running

panel.

panel. 39-21-00.

24-30-00Page

207

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 24-31-00

BATTERY - MAINTENANCE PRACTICES CAUTION: Methods of servicing nickel-cadmium batteries do not apply for the servicing of lead-acid batteries.

NICKEL-CADMIUM BATTERY (FL- 1 THRU FL-214, FL-318; FM-1 THRU FM-9) The airplane is equipped with a 24-volt, 36-ampere-hour, nickel-cadmium battery. To obtain optimum service, regular maintenance MUST be performed. A systematic Battery Maintenance Program should be established and carefully followed. WARNING: The electrolyte used in nickel-cadmium batteries is a caustic solution of potassium hydroxide. Use rubber gloves, a rubber apron, and protective goggles when handling this solution. If electrolyte gets into eyes, flush them with water and obtain immediate medical attention. The electrolyte used in nickel-cadmium batteries may be neutralized with acetic acid, boric acid, lemon juice or vinegar. CAUTION: The electrolyte in the nickel-cadmium battery is an alkali. Never use equipment contaminated by leadacid batteries. Even minute traces of acid can damage a nickel-cadmium battery. a. The battery should be removed from the airplane for service. b. A log of the services performed on each battery should be maintained (Ref. Figure 201). c.

The log of battery services performed should be evaluated to determine the proper servicing. Accurate water consumption data and battery capacity are valid barometers to use for the servicing intervals. Battery servicing should be frequent enough so that water usage does not exceed the consumable amount of electrolyte and battery capacity is not less than 85% of nameplate rating.

d. Unless otherwise indicated by a red warning tag, a nickel-cadmium battery is shipped in a fully discharged state and contains the proper amount of electrolyte.

LEAD-ACID BATTERY (FL-215 AND AFTER, EXCEPT FL-318; FM-10 AND AFTER) The airplane is equipped with a 24-volt, 42-ampere-hour Capacity Rate (C Rate), valve-regulated sealed lead-acid battery. The battery is a recombinant gas (RG) starved electrolyte battery constructed to prevent the loss of electrolyte during the charging process and does not require electrolyte servicing. To obtain optimum service, regular maintenance MUST be performed. A systematic Battery Maintenance Program should be established and carefully followed. NOTE: Batteries that are sealed can be charged and capacity checked in the same room or area. Because the electrolyte in both the sealed nickel-cadmium battery and the valve-regulated sealed (RG) lead-acid battery is absorbed in the separators and porous plates, they cannot contaminate each other when they are serviced in the same room or area. a. The battery should be removed from the airplane when placed on a charger (8, Chart 1, 24-00-00) or to capacity check. b. A battery log should be maintained and evaluated to determine the proper servicing intervals. Accurate battery capacity data is a valid barometer to use for adjustment of the servicing intervals. Battery servicing should be frequent enough so that the battery capacity is not less than 80% of nameplate rating. c.

The valve-regulated sealed lead-acid battery is shipped in a fully charged state and contains the proper amount of electrolyte.

A27

24-31-00

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL d. For additional information on battery charging and checking capacity, refer to the battery manufacturer’s owner’s manual.

SERVICING PRECAUTIONS NICKEL-CADMIUM BATTERY SERVICING PRECAUTIONS (FL-1 THRU FL-214, FL-318; FM-1 THRU FM-9) Observe the following precautions and manufacturer’s recommendations to make sure of maximum performance and protect the warranty. a. Do not remove the shorting strap until prepared to charge the battery. Batteries from which the shorting straps have been removed must be considered in an unknown state-of-charge condition and must be completely discharged prior to charging and installation. b. Check the terminal connections securing the cell links for security. Refer to the service sheet furnished with the battery or the manufacturer’s maintenance manual for the proper torque value. c.

After determining that the battery is properly assembled and in good physical condition, it should be charged as outlined under NICKEL-CADMIUM BATTERY CHARGING, and the electrolyte level adjusted.

LEAD-ACID BATTERY SERVICING PRECAUTIONS (FL-215 AND AFTER, EXCEPT FL-318; FM-10 AND AFTER) Observe the following precautions and manufacturer’s recommendations to make sure of maximum performance and protect the warranty. a. For maximum service life, disconnect the battery from external power when the airplane is in maintenance that continues for more than four hours to prevent the battery from being overcharged. b. A battery’s state of health or airworthy condition must be determined by making sure it has the ability to provide sufficient stored energy (battery capacity) for reserve or emergency power requirements. Good starting performance is not a safe indication of the battery state of health or airworthy condition. An airworthy battery must be able to provide reserve or emergency power in the event of a failure of the generating system. Therefore, a periodic capacity check of the battery at the one hour Capacity Rate (C Rate) is required. Refer to the RESERVE OR EMERGENCY CAPACITY TEST FOR LEAD-ACID BATTERY. c.

The open-circuit voltage at room temperature is a good indicator of the state-of-charge for lead-acid batteries. However, open-circuit voltage cannot be used to determine the battery state of health or airworthy condition. Load testing is the only proven way to determine the condition or airworthiness of rechargeable batteries. Refer to the RESERVE OR EMERGENCY CAPACITY TEST FOR LEAD-ACID BATTERY.

d. After performing the RESERVE OR EMERGENCY CAPACITY TEST FOR LEAD-ACID BATTERY to determine the airworthy condition of the battery, it should be charged as outlined under LEAD-ACID BATTERY CHARGING.

BATTERY POWER - DISCONNECT a. Turn Battery Switch to OFF. b. Remove the battery access panel located on the upper right hand center section between the fuselage and nacelle to gain access to the wing mounted battery. c.

Remove the battery cover on FL-215 and after, except FL-318.

Page 202 Feb 1/10

24-31-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL d. Cut the safety wire and disconnect the battery connector from the battery. Cover or insulate the battery terminals.

BATTERY POWER - CONNECT a. Connect the battery connector to the battery and secure with safety wire. b. Install the battery cover on FL-215 and after, except FL-318. c.

Turn Battery Switch to ON. Confirm proper operation of the battery power system.

d. Install the access panel in the center wing section.

BATTERY REMOVAL a. Perform the BATTERY POWER - DISCONNECT procedure. b. Cut the safety wire and loosen the hold-down wing nuts. Push the wing nuts aside to clear the battery hold-down bar. c.

Disconnect vent and drain lines from the nickel-cadmium battery on FL-1 through FL-214, FL-318.

d. Lift the battery out of the battery well.

BATTERY INSTALLATION a. Place the battery in the battery well. b. Connect vent and drain lines to nickel-cadmium battery on FL-1 through FL-214, FL-318. c.

Secure the battery in place with the wing nuts, then safety the wing nuts.

d. Perform the BATTERY POWER - CONNECT procedure.

BATTERY TERMINAL/CONNECTOR INSPECTION a. Clean the battery terminals with a nonmetallic, acid-resistant brush and clean cloth. b. Inspect the battery connector to the terminal bayonet pins locking tension by pulling the connector away from the battery. c.

Check for loose terminal connections or burning and discoloration of the terminal connections.

d. Inspect the battery connector positive and negative sockets for corrosion. Replace the connector if the sockets are corroded or worn beyond limits.

A27

24-31-00

Page 203 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BATTERY CHARGING CAUTION: Airplanes are certified with batteries that have reserve capacity for emergency operation. Therefore, never “jumpstart” an airplane that has a “dead” or discharged battery (airplane’s voltmeter reads 20 volts or less). charge the battery as outlined under IN-AIRPLANE CHARGING FOR LEAD-ACID BATTERY or CONSTANT CURRENT CHARGING FOR LEAD-ACID BATTERY. It takes approximately three hours to fully charge a discharged battery with the airplane generating system. NOTE: Sealed nickel-cadmium and sealed lead-acid batteries can be charged and capacity checked in the same room or area.

NICKEL-CADMIUM BATTERY CHARGING (FL-1 THRU FL-214, FL-318; FM-1 THRU FM-9) The two basic methods of charging nickel-cadmium batteries are the constant voltage and constant current. Variations of the two may be incorporated in automatic equipment. Special notes on charging: a. Charging is most efficient at battery temperatures between 40° - 80° F. b. Two or more batteries may be charged in parallel on a constant voltage charging bus, provided the charging equipment has the proper current producing capability. c.

Do not charge batteries in parallel when using the constant current method.

d. Do not charge individual cells unless the plastic case is supported on each side. A special frame may be built to fit the cell, or two boards or plates may be placed on each side of the cell and held together by a C-clamp. The sides of the cell must be kept flat during charging. e. Perform necessary cleaning, inspection and repairs before charging. f.

Do not energize charging equipment until after the battery has been connected to the charging equipment.

g. When charging a battery in the shop, a thermometer (5, Chart 1, 24-00-00) should be placed so that the bulb is below and between the top of the cells. Do not charge any battery that has a temperature of 100° F or higher. h. The foam sometimes seen in cells during charging does not indicate a defect. Foam usually appears when water is added and disappears after a few cycles of operation. The recommended charging rates and procedures are given in the manufacturers manual and service sheet furnished with the battery. WARNING: Complete servicing of the battery is required if the battery is subjected to more than 32 volts for 2 minutes. Since the proper battery servicing requires two days, an additional battery will be required where airplane utilization warrants. For additional information on battery maintenance, refer to the manufacturer’s maintenance manual and servicing instructions. Additional information may also be found in the Department of Transportation, Federal Aviation Administration, advisory circular, AC 00-33. NOTE: To reduce the possibility of corrosion and to prolong battery service life, battery vents should be covered when washing the airplane.

Page 204 Feb 1/10

24-31-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL LEAD-ACID BATTERY CHARGING (FL-215 AND AFTER, EXCEPT FL-318; FM-10 AND AFTER) The two basic methods of charging lead-acid batteries are the constant potential and constant current. Variations of the two may be incorporated in automatic equipment. Special notes on charging: a. Charging is most efficient at battery temperatures above 59° F. b. Two or more batteries may be charged in parallel on a constant potential charging bus, provided the charging equipment has the proper current producing capability. c.

Do not charge batteries in parallel when using the constant current method.

d. Perform necessary cleaning, inspection and repairs before charging. e. Make sure that the charger switch is turned to OFF before connecting or disconnecting the charger leads to the battery. CAUTION: Do not charge or continue charging any battery that has a temperature of 120° F or higher. f.

In colder operating climates the battery may require more frequent monitoring of it’s charge and capacity to make sure that it does not freeze and to optimize performance. To prevent freezing damage maintain the battery’s charged state.

NOTE: Batteries not meeting the RESERVE OR EMERGENCY CAPACITY TEST FOR LEAD-ACID BATTERY specifications must be removed from service. g. Check the battery reserve or emergency capacity at the scheduled inspection intervals outlined in Chapter 5 to make sure of continued airworthiness. NOTE: The battery should be charged every 90 days while in storage. h. Charge the battery as outlined under CONSTANT POTENTIAL CHARGING FOR LEAD-ACID BATTERY when the open-circuit voltage is below 25 volts. i.

Charge the battery as outlined under CONSTANT CURRENT CHARGING FOR LEAD-ACID BATTERY when the battery has not been charged for 90 days.

j.

Charge the battery as outlined under IN-AIRPLANE CHARGING FOR LEAD-ACID BATTERY when the battery has been inadvertently discharged and does not require a battery charger (8, Chart 1, 24-00-00).

A27

24-31-00

Page 205 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL CONSTANT POTENTIAL CHARGING FOR LEAD-ACID BATTERY a. Remove the battery. Refer to BATTERY REMOVAL procedure. b. Connect a constant potential charger (8, Chart 1, 24-00-00) to the battery. 1. Set the charger to charge at 1/2 of the Capacity Rate (C Rate) with the charger regulated at 28.2 volts. 2. Turn the charger on and allow to charge until the charge current stabilizes for one hour. c.

Turn the charger off and disconnect it from the battery.

d. Allow battery to rest for one hour. e. Check the open-circuit battery voltage. The voltage must be 25 volts or greater. If the voltage is less than 25 volts, perform the RESERVE OR EMERGENCY CAPACITY TEST FOR LEAD-ACID BATTERY. f.

Install the battery. Refer to BATTERY INSTALLATION procedure.

CONSTANT CURRENT CHARGING FOR LEAD-ACID BATTERY a. Remove the battery. Refer to BATTERY REMOVAL procedure. b. The battery should be “conditioned” by discharging at the 80% Test Rate of 36 amperes for one hour. c.

Connect a constant current charger (8, Chart 1, 24-00-00) to the battery. 1. Set the charger at 1/10 of the Capacity Rate (C Rate) for a 4.2 ampere charge. 2. Turn the charger on and charge for 14 to 18 hours or until the battery voltage reaches 32 volts.

d. Turn the charger off and disconnect from the battery. e. Allow the battery to rest for one hour. f.

Perform the RESERVE OR EMERGENCY CAPACITY TEST FOR LEAD-ACID BATTERY.

g. Install the battery. Refer to BATTERY INSTALLATION procedure.

Page 206 Feb 1/10

24-31-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL IN-AIRPLANE CHARGING FOR LEAD-ACID BATTERY Batteries that have been inadvertently discharged (airplane’s voltmeter reads 20 volts or less) may be charged in the airplane with regulated external power at 1/2 of the Capacity Rate (C Rate). If the external power current is not adjustable, complete the following steps: a. Reduce the voltage to 24 volts. b. Charge for ten minutes. c.

Stop charging and let battery rest for ten minutes.

d. Resume charging until the current stabilizes. e. Increase voltage to 28 volts and continue charging until current stabilizes for at least thirty minutes. RESERVE OR EMERGENCY CAPACITY TEST FOR LEAD-ACID BATTERY a. Make sure that the battery has been charged as outlined under LEAD-ACID BATTERY CHARGING. b. Make sure that the battery temperature is above 59° F. c.

Discharge the battery at the 80% Test Rate of 36 amperes for one hour.

d. After one hour of discharge, check for an open-circuit voltage of 20 volts or greater. If the battery fails to deliver 80% of its rated ampere-hour capacity, the battery has reached the end of its service life and is no longer considered to be in airworthy condition and must be replaced. e. Allow the battery to cool to room temperature before charging. f.

Charge the battery as outlined under CONSTANT POTENTIAL CHARGING FOR LEAD-ACID BATTERY.

MAINTENANCE LOG (FL-1 THRU FL-214, FL-318; FM-1 THRU FM-9) Customers are advised to keep an accurate and up-to-date maintenance log on each battery. This information will help determine the source of any maintenance problems and will assist in substantiating warranty claims (Ref. Figure 201).

A27

24-31-00

Page 207 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE LOG - NICKEL-CADMIUM BATTERY (FL-1 thru FL-214, FL-318; FM-1 thru FM-9) Figure 201

Page 208 Feb 1/10

24-31-00

A27

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BATTERY MONITOR

(FL-1 A

THRU

DESCRIPTION AND OPERATION

I

FL-214, FL-318; PM-1 THRU FM-9)

battery charge

system provides

current monitor is installed to

provide

a

visual indication of abnormal

indication when the conditions exist for

battery charge

current. The

thermal runaway of the nickel-cadmium battery. The battery may then be removed from the charging system before further battery damage occurs. The most common cause of the thermal runaway is damage to the gas barrier between the plates, resulting from overcharging the

battery

at

a

high

an

a

high temperatures. Once it has sustained gas barrier damage, the battery charged on a constant voltage charging system over a period of time.

rate at

thermal runaway when

is

subject

to

operation, the idle current of the battery is less than one amp. It increases significantly above the battery is charged at an elevated temperature or from a high charge voltage. A high idle current increases water consumption and may destroy the gas barrier (cellophane separator) between the plates. Once a battery has sustained damage to the gas barrier, it will have a high idle current and be subject to thermal runaway. The battery monitor system provides an indication of high charge current resulting from high battery temperature, high charging voltage, or gas barrier damage. During

normal

normal level when the

The

battery

and

a

center

section, while the detector module is mounted in

aisle floor The

monitor system consists of a shunt in the negative lead of the battery, a battery charge current detector, light in the annunciator panel. The shunt is located below the battery box in the right

BA‘TTERY CHARGE

immediately

charge

aft of the

partition

between the

a printed circuit cockpit and cabin.

board box

assembly

beneath the center

current detector circuit

amplifies the signal from the shunt and provides a 28-volt output for the light when the signal exceeds the trigger level of 1.5 ~0.2 MV. This trigger level corresponds 7.5 ~1 amp with the 250-amp shunt. The circuit resets when the signal decreases 0.3 MV below the trigger level provide 1.5-amp hysteresis. There is a six-second time delay to override momentary recharges when heavy loads

BATTERY CHARGE to

to

are

switched

on.

The system illuminates the yellow BATTERY CHARGE caution annunciator during battery recharge to provide a self-test of the system. Following an engine start, the BATTERY CHARGE annunciator illuminates and remains on for about five minutes until the

charge current decreases to the current detector reset level as the battery approaches full charge. The time the light remains on exceeds five minutes if the trigger level of the current detector is too low or if the battery is in a low state of charge, has been previously discharged at a low rate, has a low charge voltage per cell, has gas barrier damage or is at a low temperature. After the BATTERY CHARGE

light extinguishes, it should remain off unless either a thermal runaway has begun, or idle increases in response to an increase in electrical system voltage. Such a voltage increase current battery from results normally poor generator paralleling or load switching. The BATTERY CHARGE light may illuminate for short intervals as the battery recharges when the generator speed is increased above cut-in speed.

the

~20

24-32-00

Apr 28/06Page

1

Raythwm

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BATTERY MONITOR

(FL-1

THRU

MAINTENANCE PRACTICES

I

FL-214, FL-318; FM-1 THRU FM-9)

BA TTERY MONITOR CALISRA TION CHECK Calibration of the

on

to

is recommended that system calibration be checked at

battery monitor system can be checked trigger the current detector circuit (Ref. Figure 201). It regular intervals when the battery is removed for service.

the

airplane by simulating

a

charge

current sufficient

I

signal level is very low and susceptible to resistance unbalance in the shunt signal leads. All connections in these leads must be clean and tight to prevent improper system calibration and erratic operation.

NOTE: The

a.

b.

c.

Disconnect the

battery (Ref. Figure 201).

and connect

a

variable resistor and 0-1 amp ammeter to the

battery

connector

1

Apply external power to the buses to energize the battery relay and apply 28 volts to the center bus, then the variable resistor until the battery charge current detector triggers. Monitor the

voltage

at

pin

43

on

the current detector to determine when the circuit

43 switches from two volts to ten volts when the circuit

triggers,

adjust

triggers. The voltage at pin yellow BATTERY

then six seconds later the

CHARGE annunciator will illuminate. d.

As the current is reduced to the reset level, the

CHARGE annunciator

voltage

at

pin

43 switches back to two volts when the BATTERY

extinguishes.

BA TTERY MONITOR FUNCTIONAL CHECK Connect

a

28-volt, 2-amp power supply (6, Chart 1, 24-00-00)

to bench test the current detector for proper

operation

(Ref. Figure 202). a.

With 28 volts

reading

applied to pin

of 2 volts at

Increase the

b.

1

signal

Decrease the

approximately d.

nm

Replace

signal

signal

light

pin

43 switches to

a

reading

adjusted to a minimum, light remains off.

current

43 of the current detector and that the indicator

current until

amp and the indicator c.

the current detector circuit and the

of 10 volts. The

signal

check for

a

current should be 0.75 ~1

should illuminate within 6 seconds.

current until the

voltage at pin 43 switches back to 2 volts. The current reading in step b and the light should extinguish.

should be

0.15 amp less than the

the current detector

assembly

if found defective.

24-32-00

Apr 28/06Page

201

RBYtheon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BA TTERY GAS BARRIER CHECK It is

imperative that the condition of the battery gas barrier be checked whenever the battery is acceptability of the battery in relation to thermal stability.

removed and serviced

to determine the a.

Overcharge a fully charged battery for four hours with a rating of the battery.) This current must be CONSTANT

b.

Check individual cell

c.

Any

cell with

a

voltage

voltage of

of the

battery while

still

constant current of 0.1 C.

rather than

charging

a

pulsing

(C

is the

it at the end of the four-hour

less than 1.50 volts is defective and should be

one

hour

capacity

average of 0.1 C.

period.

replaced.

BATTERY CONNECTOR

(WIOIPII

I

T

A

A2

0-IOA AMMETER

BATTERY RELAY (A228K135)

O TRIPLE-FED

Al

!Ip_

ne

5

BATTERY BUS-TIE RELAY (K121KI)

(REF

CHAPTER

CB

EXTERNAL POWER

RECEPTACLE

5A ~-----1 44 ANNUNCIATOR WARNING

IND~CATOR

24-30-00)

BATTERY RELAY

(A124CB15)

(5177A221]

TRIPLEFED BUS

BUS

5A

BATTERY SWITCH 8 CHM 500W

CENTER

Al

3

BUS O

I4

I

28

VOC

IN

A2O

Al

(AldbC84) EXTERNAL

BATTERY CHARGE

300W

3

OHM

Y

I

POWER

OUT

RELAY

(A20BK12d)

(REF CHAPTER 31-50-00) 39

I I

CHECK

TRIGGER

CAUTION/ADVISORY/STATUS PANEL (E193)

BATTERY

MONITOR SHUNT

FAULT

65

I I

I I

I VOLTAGE /SENSE IN

I I 38

(R120)

1 POSITIYE~

43

1 NEGATIVEI TEST

REFERENCE

46IGROUNO VOLTMETER

BATTERY

CHARGE MONITOR

PCB C94FL2PB161O C

(A1701

Calibration Circuit

Figure

201

ORIGINAL

Page 202 Apr28/06

24-3200

As Received By nTp

A20

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

44

0-IA

AMMETER

f 25

OHM

25W

80 OHM 50W

39

25A 50MV SHUNT 38

2-AMP SUPPLY

2B-VOLT. POWER

46 LTGHT

45

43 VOLTMETER BATTERY MONITOR

CHARGE MOOULE C94FL2481609

C

Functional Test Circuit

Figure

202

ORIGINAL As Received

ATP

A20

By

24-32-00

Page 203 Apr 28/06

Raythwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXTERNAL POWER

DESCRIPTION AND OPERATION

The external power receptacle is located underneath the right wing, outboard of the engine nacelle. The receptacle is designed for use with an auxiliary ground power unit having a standard AN plug. An extemal power sensor

module, installed in a printed circuit board box assembly under the center aisle floorboard, protects the airplane electrical system from an auxiliary ground power unit with reversed polarity or an excessively high output voltage.

voltage from the airplane center bus and the continuity of the circuit between the positive terminal and the polarizing terminal of the GPU plug to illuminate the yellow EXT PWR caution annunciator when an GPU is plugged into the receptacle. The unit does not necessarily need to be tumed on to illuminate the

The

sense

module utilizes the

annunciator. If the GPU output has the correct polarity, and the external power switch is ON, the external power printed circuit a voltage to close the external power relay and to close the bus tie relays. The external power unit

board outputs

automatically powers all de buses. External power is routed through the external power relay to the center bus. A voltage from the small polarizing pin of the external power receptacle is routed through a 3-ampere circuit breaker, mounted in the outboard right center section, to the voltmeter select switch in the overhead instrument panel. This permits monitoring the voltage of the GPU before the external power relay is closed. CAUTION:

Voltage is required to energize the avionic master power relays to remove the power from the avionics equipment. If external power is used for ground maintenance, such as landing gear rigging, use care to ensure

~30

that each and eve~y avionics unit is turned off.

24-40-00Pagel

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

EXTERNAL POWER - MAINTENANCE PRACTICES A ground power unit, for engine starts or for use during ground operation without the engines running, must be capable of supplying load requirements without excessive voltage drop. The unit must be capable of delivering up to 1000 amperes for 0.1 second and be capable of delivering up to 300 amperes continuously at 24 to 30 volts. Use of an inadequate ground power unit can cause a voltage drop below the dropout voltage of the external power relay and the starter relay. This will result in relay chatter and/or welded contacts. A continuous load in excess of 350 amperes will damage the external power relay and power cables of the airplane.

CONNECTING AND APPLYING EXTERNAL POWER a. Use only an ground power unit that is negatively grounded. If the polarity of the power source is unknown, determine the polarity with a voltmeter before connecting the unit to the airplane. b. Before connecting an external power unit, turn all radio equipment, the generator switches, the battery switch, and the external power switch to the OFF position. Place the overhead voltmeter select switch in the EXT PWR position. CAUTION: Voltage is required to energize the avionics master power relays to remove the power from the avionics equipment; therefore, never apply external power to the airplane without first applying battery voltage. If the battery switch is to be placed in the off position, connect an external battery parallel to the external power unit prior to energizing the power unit. c.

Adjust the voltage setting of the external power unit before connecting it into the external power receptacle.

d. Connect external power unit cable to the external power unit receptacle on the airplane. e. Turn the external power unit ON. f.

Monitor the voltage of the external power unit on the overhead meter panel voltmeter.

g. Turn the battery switch to the ON position. h. Turn the external power switch in the cockpit to the ON position. CAUTION: The battery may be damaged if exposed to voltages higher than 32 volts for extended periods of time.

DISCONNECTING EXTERNAL POWER a. Turn the external power switch in the cockpit to the OFF position. b. Turn the battery switch to the OFF position. c.

Turn the external power unit OFF.

d. Disconnect external power unit cable from the external power receptacle on the airplane.

A27

24-40-00

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 24-50-00

ELECTRICAL LOAD DISTRIBUTION - DESCRIPTION AND OPERATION The electrical load distribution system provides the means of supplying direct and alternating current to the various airplane systems (Ref. Figures 1, 2, 3, 4, 5, 6, 7 and 8). Direct current is provided from three separate DC power sources: the battery, and the LH and RH starter/generators. A ground auxiliary power unit (GPU) may be connected to the airplane to supply power to the primary busses during ground operation. Refer to the applicable section for detailed information on all power sources.

POWER DISTRIBUTION ON THE BUSSES DC power is distributed from five main busses: left and right generator busses, center bus, triple-fed bus and the battery bus. The generator busses and battery are interconnected to provide a triple-fed, single-loop system that is protected through the respective limiters, hall-effect current sensors, and bus-tie relays which also tie these power sources together through the center bus. The battery bus is located in the cockpit fuel control panel. It is connected to the battery through the remote control circuit breaker (RCCB). Refer to Chapter 39-10-00 for an illustration of the fuel control panel. The battery switch and the battery bus switch are both located on the pilot’s outboard subpanel. The generator busses are located aft of the engine firewall on the inboard side of their respective nacelle. The center bus (lower forward cabin limiter assembly) is located under the forward center aisle floor and is powered from each generator bus through a 250-amp limiter and generator bus-tie relay.

BUS-TIE CONTROL The GEN TIES and BUS SENSE switches are located on the pilot’s outboard subpanel to provide control over the bus-tie system. Placing the BUS SENSE switch in the TEST position applies a control voltage from the busses to each current sensor’s test input. This voltage simulates an overcurrent condition to exercise the hall-effect device circuitry. The current sensors signal the bus-ties control printed circuit board (PCB) to open the respective bus-tie relay for the test. All three caution annunciators should illuminate. Auxiliary contacts within the bus tie relays control their respective bus tie annunciator. Reaction time of the battery current sensor is 0.1 second and 0.01 second for the generator current sensors. Because reaction time is so fast, only a momentary actuation of the BUS SENSE switch to TEST is necessary. By momentarily moving the BUS SENSE switch to RESET, power will be removed from the bus-tie relay coils on the PCB. Voltage is then re-applied to the bus-tie relay coils by the bus-tie control PCB to close the bus-tie relays. All three annunciators will extinguish. The GEN TIES switch is used to manually open or close the generator bus-ties without applying voltage to the current-protection circuits. When the GEN TIES switch is placed in the MAN CLOSE position, the bus-tie control PCB manually closes the generator bus-tie relays. This allows power to be applied to the generator busses during ground maintenance or testing without running the engines. The MAN TIES CLOSE annunciator is illuminated anytime the generator bus-tie relays are closed using the MAN TIES CLOSE switch. The GEN TIES switch will manually open the generator bus-tie relays anytime it is placed in the OPEN position. While in the NORM position, control of the generator bus-tie relays is automatic through the bus-tie control PCB.

A26

24-50-00

Page 1 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AVIONICS POWER DISTRIBUTION Electrical power is distributed to the avionics equipment from three primary busses through three power relays and three feeder circuit breakers (Ref. Figure 6). The avionics bus feeder circuit breakers and power relays are located on the A145 main-power-distribution panel. The avionics master control and avionics-power circuit breakers are located on the copilot’s circuit breaker panel. Refer to Chapter 39-10-00 for an illustration of the copilot’s circuit breaker panel. The avionics-power relays are energized with triple-fed bus voltage through the avionics master power switch placarded AVIONICS MASTER POWER/OFF on the pilot’s outboard subpanel. When the avionics master switch is placed in the AVIONICS MSTER POWER position, voltage is removed from each avionics relay coil and the contacts are closed to supply power to the avionics power circuit breakers. The circuit is such that the avionics relays are opened by a control voltage when the master switch is OFF. This configuration allows power to be supplied to the relay-controlled avionics busses in the event a switch or relay malfunctions. Memory power for selected avionics equipment is pulled from the “hot” battery bus.

Page 2 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A

LANDING GEAR MOTOR (CB101)

FORWARD ELECTRIC HEAT (A145CB49) 100A

AFT ELECTRIC HEAT (A145CB48) 100A

CONDENSER BLOWER POWER (A145CB47) 60A

30A

15A

LH MANUAL PROP DEICE (A145CB11)

DC TEST JACK (A145CB9)

SUBPANEL FEEDER (A145CB7) 20A

40A

INVERTER NO. 1 (A145CB1) 15A

BUS-TIE POWER (A145CB10) 7.5A

30A

TAXI LIGHT (CB122)

ICE LIGHT (CB126) 5A

10A

FLASHING BEACON LIGHTS (CB123)

RH MANUAL PROP DEICE (A145CB12)

FL24B 091518AA.AI

Center Bus Power Distribution (FL-1 thru FL-380, FL-382; FM-1 thru FM-11) Figure 1 (Sheet 1 of 3)

A26

24-50-00

Page 3 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A

LANDING GEAR MOTOR (CB101)

FORWARD ELECTRIC HEAT (A145CB49) 100A

AFT ELECTRIC HEAT (A145CB48) 100A

CONDENSER BLOWER POWER (A145CB47) 60A

30A

15A

LH MANUAL PROP DEICE (A145CB11)

DC TEST JACK (A145CB9)

SUBPANEL FEEDER (A145CB7) 20A

BUS-TIE POWER (A145CB10) 7.5A

30A

RH MANUAL PROP DEICE (A145CB12)

15A

TAXI LIGHT (CB122)

ICE LIGHT (CB126) 5A

10A

FLASHING BEACON LIGHTS (CB123)

FL24B 091519AA.AI

Center Bus Power Distribution (FL-381, FL-383 thru FL-492, FL-494 thru FL-499; FM-12 thru FM-13) Figure 1 (Sheet 2 of 3) Page 4 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A

LANDING GEAR MOTOR (CB101)

ELECTRIC HEAT (A145CB48) 160A

30A

15A

LH MANUAL PROP DEICE (A145CB11)

DC TEST JACK (A145CB9)

SUBPANEL FEEDER (A145CB7) 20A

40A

CONDENSER BLOWER POWER (A145CB2)

BUS-TIE POWER (A145CB10) 7.5A

30A

15A

TAXI LIGHT (CB122)

ICE LIGHT (CB126) 5A

10A

FLASHING BEACON LIGHTS (CB123)

RH MANUAL PROP DEICE (A145CB12)

FL24B 091520AA.AI

Center Bus Power Distribution (FL-493, FL-500 and After; FM-14 and After) Figure 1 (Sheet 3 of 3)

A26

24-50-00

Page 5 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

5A

5A

5A

5A

10A

5A

LH ENGINE FIRE EXTINGUISHER (A124CB20)

RH ENGINE FIRE EXTINGUISHER (A124CB19)

ENTRY LIGHTS (A124CB18)

AVIONICS (A124CB17)

GROUND COMM (A124CB16)

BATTERY RELAY (A124CB15)

FL24B 091521AA.AI

Battery Bus Power Distribution (FL-1 thru FL-119, FL-121; FM-1 thru FM-8) Figure 2 (Sheet 1 of 3) Page 6 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

5A

5A

5A

5A

10A

5A

LH ENGINE FIRE EXTINGUISHER (A124CB43)

RH ENGINE FIRE EXTINGUISHER (A124CB42)

ENTRY LIGHTS (A124CB41)

AVIONICS (A124CB39)

GROUND COMM (A124CB40)

BATTERY RELAY (A124CB38)

FL24B 091522AA.AI

Battery Bus Power Distribution (FL-120, FL-122 thru FL-492, FL-494 thru FL-499; FM-9 thru FM-13) Figure 2 (Sheet 2 of 3)

A26

24-50-00

Page 7 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

5A

5A

5A

5A

10A

5A

LH ENGINE FIRE EXTINGUISHER (A124CB43)

RH ENGINE FIRE EXTINGUISHER (A124CB42)

ENTRY LIGHTS (A124CB41)

AVIONICS (A124CB39)

GROUND COMM (A124CB40)

BATTERY RELAY (A124CB38)

GROUND HEAT (A124CB36)

FL24B 091523AA.AI

Battery Bus Power Distribution (FL-493, FL-500 and After; FM-14 and After) Figure 2 (Sheet 3 of 3)

Page 8 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A TRIPLE-FED BUS FEEDER (A253F8)

5A

LH ENGINE CHIP DETECTOR (A146CB39)

35A

5A

NO SMOKE, FSB AND BAGGAGE LIGHTS (A146CB35)

5A

AVIONICS AND ENGINE INSTRUMENT LIGHTS (A146CB33)

7.5A

PILOT FLIGHT INSTRUMENT & SIDE PANEL (A146CB31)

CB PANEL FEEDER (A253F7)

LH GENERATOR BUS

35A

LEFT LANDING LIGHTS (CB177)

10A SUBPANEL FEEDER (A253F6)

ALTITUDE ALERT (A146CB29) NAV LIGHTS (CB121)

7.5A

COPILOT'S ENCODING ALTIMETER (A146CB27)

150A LH SUB BUS FEEDER (A253F2)

50A

5A

TAIL FLOODLIGHTS (CB162)

7.5A

PILOT WINDSHIELD ANTI-ICE POWER (CB153)

5A

FLAP INDICATOR CONTROL (A146CB25)

20A

FLAP MOTOR (A146CB23)

5A

RIGHT BLEED AIR CONTROL (A146CB67)

PILOT WINDSHIELD ANTI-ICE CONTROL (CB194) 10A

FURNISHINGS MASTER CONTROL (A146CB71) AM/FM STEREO (A146CB73)

AVIONICS BUS FEEDER (A145CB15)

35A

** INVERTER CABIN 20A

*

10A

LH FUEL VENT (A146CB77)

5A

LH STANDBY ENGINE ANTI-ICE (A146CB79)

7.5A

NO. 1 GENERATOR BUS-TIE POWER (A146CB85)

OUTLETS (A145CB25)

AUTO PROPELLER DEICE (A145CB37)

40A

EFFECTIVE: FM-1 THRU FM-11

5A REFRESHMENT BAR (A145CB19)

25A

EFFECTIVE: FL-352 THRU FL-380 AND FL-382; FM-11

CIGAR LIGHTER (A146CB75)

VENT BLOWER POWER (A145CB17)

30A

**

5A

*

RADIANT HEAT CARGO DOOR (A145CB13) FL24B 091524AA.AI

LH Generator Bus Power Distribution (FL-1 thru FL-380, FL-382; FM-1 thru FM-11) Figure 3 (Sheet 1 of 4)

A26

24-50-00

Page 9 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A 7.5A

PILOT INSTRUMENT LIGHTS CONTROL (A124CB21)

2A

DBU (A124CB17)

2A

EDC 1 (A124CB16)

2A

DCU 1 (A124CB15)

20A

LH CB PANEL, L GEN (A146CB43)

10A

LEFT LANDING LIGHTS (CB177)

5A

LH ENGINE CHIP DETECTOR (A146CB39)

7.5A

NAV LIGHTS (CB121)

5A

NO SMOKE, FSB AND BAGGAGE LIGHTS (A146CB35)

7.5A

TAIL FLOODLIGHTS (CB162)

15A

ESIS BATTERY CHARGE (A124CB32)

7.5A

PILOT FLIGHT INSTRUMENT & SIDE PANEL (A146CB31)

5A

50A

PILOT WINDSHIELD ANTI-ICE POWER (CB194)

FLAP INDICATOR CONTROL (A146CB25)

5A

PILOT WINDSHIELD ANTI-ICE CONTROL (CB194)

20A

FLAP MOTOR (A146CB23)

5A

RIGHT BLEED AIR CONTROL (A146CB67)

TRIPLE-FED BUS FEEDER (A253F8)

35A CB PANEL FEEDER (A253F7)

LH GENERATOR BUS

35A SUBPANEL FEEDER (A253F6)

150A LH SUB BUS FEEDER (A253F2)

FURNISHINGS MASTER CONTROL (A146CB71)

35A

AVIONICS BUS FEEDER (A145CB15)

30A

VENT BLOWER POWER (A145CB17) 5A

CIGAR LIGHTER (A146CB75)

25A

REFRESHMENT BAR (A145CB19)

5A

LH FUEL VENT (A146CB77)

20A

INVERTER CABIN OUTLETS (A145CB25)

5A

LH STANDBY ENGINE ANTI-ICE (A146CB79)

40A

AUTO PROPELLER DEICE (A145CB37)

7.5A

NO. 1 GENERATOR BUS-TIE POWER (A146CB85)

10A

PILOT PFD HEATER (A146CB87)

10A

AM/FM STEREO (A146CB73)

FL24B 091525AA.AI

LH Generator Bus Power Distribution (FL-381, FL-383 thru FL-424) Figure 3 (Sheet 2 of 4) Page 10 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A TRIPLE-FED BUS FEEDER (A253F8)

7.5A

PILOT INSTRUMENT LIGHTS CONTROL (A124CB21)

2A

DBU (A124CB17)

2A

EDC 1 (A124CB16)

35A CB PANEL FEEDER (A253F7)

2A 35A 10A

LEFT LANDING LIGHTS (CB177)

20A

LH CB PANEL, L GEN (A146CB43)

7.5A

NAV LIGHTS (CB121)

5A

LH ENGINE CHIP DETECTOR (A146CB39)

7.5A

TAIL FLOODLIGHTS (CB162)

5A

NO SMOKE, FSB AND BAGGAGE LIGHTS (A146CB35)

15A

ESIS BATTERY CHARGE (A124CB32)

7.5A

PILOT FLIGHT INSTRUMENT & SIDE PANEL (A146CB31)

5A

FLAP INDICATOR CONTROL (A146CB25)

20A

FLAP MOTOR (A146CB23)

5A

RIGHT BLEED AIR CONTROL (A146CB67)

SUBPANEL FEEDER (A253F6)

150A LH SUB BUS FEEDER (A253F2)

PILOT WINDSHIELD ANTI-ICE POWER (CB153)

50A

5A

*

DCU 1 (A124CB15)

PILOT WINDSHIELD ANTI-ICE CONTROL (CB194)

FURNISHINGS MASTER CONTROL (A146CB71)

35A

AVIONICS BUS FEEDER (A145CB15)

10A

30A

VENT BLOWER POWER (A145CB17)

5A

CIGAR LIGHTER (A146CB75)

25A

REFRESHMENT BAR (A145CB19)

5A

LH FUEL VENT (A146CB77)

20A

INVERTER CABIN OUTLETS (A145CB25)

5A

LH STANDBY ENGINE ANTI-ICE (A146CB79)

40A

AUTO PROPELLER DEICE (A145CB37)

7.5A

NO. 1 GENERATOR BUS-TIE POWER (A146CB85)

10A

PILOT PFD HEATER (A146CB87)

EFFECTIVE: FM-12 THRU FM-13

* 10A

RADIANT HEAT CARGO DOOR (A145CB13)

FL24B 091526AA.AI

LH Generator Bus Power Distribution (FL-425 thru FL-492, FL-494 thru FL-499; FM-12 thru FM-13) Figure 3 (Sheet 3 of 4)

A26

24-50-00

Page 11 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A TRIPLE-FED BUS FEEDER (A253F8)

7.5A

PILOT INSTRUMENT LIGHTS CONTROL (A124CB21)

2A

DBU (A124CB17)

2A

EDC 1 (A124CB16)

35A CB PANEL FEEDER (A253F7)

2A 35A 10A

LEFT LANDING LIGHTS (CB177)

20A

LH CB PANEL, L GEN (A146CB43)

7.5A

NAV LIGHTS (CB121)

5A

LH ENGINE CHIP DETECTOR (A146CB39)

7.5A

TAIL FLOODLIGHTS (CB162)

5A

NO SMOKE, FSB AND BAGGAGE LIGHTS (A146CB35)

15A

ESIS BATTERY CHARGE (A124CB32)

7.5A

PILOT FLIGHT INSTRUMENT & SIDE PANEL (A146CB31)

5A

FLAP INDICATOR CONTROL (A146CB25)

20A

FLAP MOTOR (A146CB23)

5A

RIGHT BLEED AIR CONTROL (A146CB67)

SUBPANEL FEEDER (A253F6)

150A LH SUB BUS FEEDER (A253F2)

PILOT WINDSHIELD ANTI-ICE POWER (CB153)

50A

5A

*

DCU 1 (A124CB15)

PILOT WINDSHIELD ANTI-ICE CONTROL (CB194)

FURNISHINGS MASTER CONTROL (A146CB71)

35A

AVIONICS BUS FEEDER (A145CB15)

10A

30A

FWD CABIN BLOWER POWER (A145CB17)

5A

CIGAR LIGHTER (A146CB75)

25A

REFRESHMENT BAR (A145CB19)

5A

LH FUEL VENT (A146CB77)

20A

INVERTER CABIN OUTLETS (A145CB25)

5A

LH STANDBY ENGINE ANTI-ICE (A146CB79)

40A

AUTO PROPELLER DEICE (A145CB37)

7.5A

NO. 1 GENERATOR BUS-TIE POWER (A146CB85)

10A

PILOT PFD HEATER (A146CB87)

EFFECTIVE: FM-14 AND AFTER

* 10A

RADIANT HEAT CARGO DOOR (A145CB13)

FL24B 091527AA.AI

LH Generator Bus Power Distribution (FL-493, FL-500 and After; FM-14 and After) Figure 3 (Sheet 4 of 4)

Page 12 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A

TRIPLE-FED BUS FEEDER (A254F8)

35A 10A RH GENERATOR BUS

ENGINE PROPELLER GOVERNOR TEST (A146CB37)

CB PANEL FEEDER (A254F7) 5A

* WINDOW DEFOG (CB103)

5A

RH ENGINE CHIP DETECTOR (A146CB40)

35A 15A

STALL WARNING HEAT (CB185)

5A

ENGINE PROPELLER SYNCHRONIZATION (A146CB38)

7.5A

RH PITOT HEAT (CB112)

5A

READING LIGHTS (A146CB36)

10A

RH LANDING LIGHTS (CB178)

5A

COPILOT FLIGHT INSTRUMENT (A146CB34)

7.5A

RECOGNITION LIGHTS (CB134)

SUBPANEL FEEDER (A254F6)

150A RH SUBPANEL BUS FEEDER (A254F2)

5A

5A

STROBE LIGHTS (CB135)

COPILOT WINDSHIELD ANTI-ICE CONTROL (CB193)

SUBPANEL OVERHEAD & CONSOLE LIGHTS (A146CB32)

5A

FUEL VENT (A146CB78)

5A

RH STANDBY ENGINE ANTI-ICE (A146CB80)

5A

BRAKE DEICE (A146CB82)

GEN NO. 2 BUS TIE POWER (A146CB86)

50A

COPILOT'S WINDSHIELD ANTI-ICE (A145CB14)

35A

AVIONICS BUS FEEDER (A145CB16)

5A

COPILOT TURN & SLIP (A146CB24)

20A

AFT EVAPORATOR BLOWER POWER (A145CB18)

3A

PITCH TRIM (A146CB28)

7.5A

AIR CONDITIONER CLUTCH (A145CB24)

40A

INVERTER NO. 2 (A145CB26)

10A

TOILET (A145CB38)

FL-73 THRU * EFFECTIVE FL-380 AND FL-382; FM-4 THRU FM-11 FN-1

7.5A

7.5A

FL24B 091528AA.AI

RH Generator Bus Power Distribution (FL-1 thru FL-380, FL-382; FM-1 thru FM-11) Figure 4 (Sheet 1 of 3)

A26

24-50-00

Page 13 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A

7.5A

COPILOT INSTRUMENT LIGHTS CONTROL (A124CB23)

7.5A

PEDESTAL LIGHTS CONTROL (A124CB22)

TRIPLE-FED BUS FEEDER (A254F8)

35A

2A

EDC 2 (A124CB31)

2A

DCU 2 (A124CB30)

3A

EGPWS (A145CB104)

20A

LH CB PANEL R GEN (A146CB44)

CB PANEL FEEDER (A254F7)

RH GENERATOR BUS

5A

WINDOW DEFOG (CB103)

15A

STALL WARNING HEAT (CB185)

7.5A

RH PITOT HEAT (CB112)

10A

RH LANDING LIGHTS (CB178)

7.5A

RECOGNITION LIGHTS (CB134)

35A

SUBPANEL FEEDER (A254F6)

150A

RH SUBPANEL BUS FEEDER (A254F2)

5A

5A

*

STROBE LIGHTS (CB135)

COPILOT WINDSHIELD ANTI-ICE CONTROL (CB193)

50A

COPILOT'S WINDSHIELD ANTI-ICE (A145CB14)

35A

AVIONICS BUS FEEDER (A145CB16)

20A

AFT EVAPORATOR BLOWER POWER (A145CB18)

7.5A

AIR CONDITIONER CLUTCH (A145CB24)

* SMS

EFFECTIVE FL-425 THRU FL-474

10A

ENGINE PROPELLER GOVERNOR TEST (A146CB37)

5A

RH ENGINE CHIP DETECTOR (A146CB40)

5A

ENGINE PROPELLER SYNCHRONIZATION (A146CB38)

5A

READING LIGHTS (A146CB36)

5A

COPILOT FLIGHT INSTRUMENT (A146CB34)

7.5A

SUBPANEL OVERHEAD & CONSOLE LIGHTS (A146CB32)

5A

FUEL VENT (A146CB78)

5A

RH STANDBY ENGINE ANTI-ICE (A146CB80)

5A

BRAKE DEICE (A146CB82)

7.5A

GEN NO. 2 BUS TIE POWER (A146CB86)

(A145CB20)

10A

TOILET (A145CB38)

5A

MFD HEATER (A146CB121)

3A

PITCH TRIM (A146CB28)

FL24B 091529AA.AI

RH Generator Bus Power Distribution (FL-381, FL-383-thru FL-492, FL-494 thru FL-499; FM-12 thru FM-13) Figure 4 (Sheet 2 of 3) Page 14 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

60A 7.5A

COPILOT INSTRUMENT LIGHTS CONTROL (A124CB23)

7.5A

PEDESTAL LIGHTS CONTROL (A124CB22)

2A

EDC 2 (A124CB31)

TRIPLE-FED BUS FEEDER (A254F8)

35A

RH GENERATOR BUS

CB PANEL FEEDER (A254F7)

3A 2A

DCU 2 (A124CB30)

35A 5A

WINDOW DEFOG (CB103)

15A

STALL WARNING HEAT (CB185)

7.5A

RH PITOT HEAT (CB112)

SUBPANEL FEEDER (A254F6)

10A

MFD HEATER (A146CB121)

10A

ENGINE PROPELLER GOVERNOR TEST (A146CB37)

150A

RH SUBPANEL BUS FEEDER (A254F2)

10A

7.5A

*

EFFECTIVE FL-493, FL-500 THRU FL-599; FM-14 THRU FM-24; CB NOMENCLATURE "EGPWS" IS USED

20A

RH ENGINE CHIP DETECTOR (A146CB40)

5A

ENGINE PROPELLER SYNCHRONIZATION (A146CB38)

5A

READING LIGHTS (A146CB36)

5A

COPILOT FLIGHT INSTRUMENT (A146CB34)

RECOGNITION LIGHTS (CB134)

STROBE LIGHTS (CB135)

COPILOT WINDSHIELD ANTI-ICE CONTROL (CB193)

50A

COPILOT'S WINDSHIELD ANTI-ICE (A145CB14)

35A

LH CB PANEL R GEN (A146CB44)

5A RH LANDING LIGHTS (CB178)

5A

5A

TAWS (A146CB104)

7.5A

SUBPANEL OVERHEAD & CONSOLE LIGHTS (A146CB32)

3A

PITCH TRIM (A146CB28)

AVIONICS BUS FEEDER (A145CB16)

5A

FUEL VENT (A146CB78)

30A

AFT CABIN BLOWER POWER (A145CB18)

5A

RH STANDBY ENGINE ANTI-ICE (A146CB80)

5A

AIR CONDITIONER CLUTCH (A145CB24)

5A

BRAKE DEICE (A146CB82)

15A

COCKPIT BLOWER (A145CB22) 7.5A

10A

GEN NO. 2 BUS TIE POWER (A146CB86)

TOILET (A145CB38)

FL24B 091530AA.AI

RH Generator Bus Power Distribution FL-493, FL-500 and After; FM-14 and After) Figure 4 (Sheet 3 of 3)

A26

24-50-00

Page 15 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This Page Intentionally Left Blank

Page 16 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TRIPLE-FED BUS

20A

20A

20A

35A

20A

15A SUBPANEL FEEDER (A145CB33)

FUEL PANEL FEEDER NO. 1 (A145CB31)

LANDING GEAR WARNING (A146CB1)

20A FUEL PANEL FEEDER NO. 2 (A145CB27)

TRIPLE-FED BUS AVIONICS FEEDER (A145CB46)

CB PANEL FEEDER NO. 4 (A145CB34)

CB PANEL FEEDER NO. 3 (A145CB32)

CB PANEL FEEDER NO. 2 (A145CB30)

5A

EFFECTIVITY FL-73 THRU FL-119 AND FL-121; FM-4 THRU FM-8 IF INSTALLED

CB PANEL FEEDER NO. 1 (A145CB28)

*

20A

7.5A

PITOT HEAT (A223CB111)

2A

LANDING GEAR CONTROL (A223CB107)

SEE APPLICABLE AVIONICS DRAWING

ANNUNCIATOR POWER WARNING (A146CB3)

5A

LANDING GEAR WARNING INDICATOR (A146CB2)

5A

LH BLEED AIR WARNING (A146CB5)

5A

ANNUNCIATOR WARNING INDICATOR (A146CB4)

5A

LH ENGINE OIL PRESSURE WARNING (A146CB7)

5A

RH BLEED AIR WARNING (A146CB6)

7.5A

LH ENGINE START CONTROL (A146CB13)

5A

RH ENGINE OIL PRESSURE WARNING (A146CB8)

5A

LH ENGINE IGNITOR POWER (A146CB15)

7.5A

5A

ENGINE AUTOFEATHER (A146CB11)

5A

5A

LH BLEED AIR CONTROL (A146CB46)

PILOT TURN & SLIP (A146CB45)

5A

TEMPERATURE CONTROL (A146CB48)

PILOT AIR DATA ALTIMETER (A146CB47)

5A

PRESSURE CONTROL (A146CB50)

5A

OUTSIDE AIR TEMP (A146CB49)

5A

OXYGEN CONTROL (A146CB52)

5A

RH FIREWALL VALVE (A124CB12)

RH ENGINE START CONTROL (A146CB14)

5A

AIRSPEED WARN (A146CB51)

5A

CABIN ALTITUDE HIGH (A146CB54)

10A

RH STANDBY PUMP (A124CB10)

5A

RH ENGINE IGNITOR POWER (A146CB16)

5A

INSTRUMENT INDIRECT LIGHTS (A146CB53)

5A

CABIN DIFFERENTIAL HIGH (A146CB56)

5A

RH FUEL PRESSURE WARNING (A124CB4)

5A

LH FIREWALL VALVE (A124CB13)

LH ENGINE OIL PRESSURE (A146CB9)

5A

RH ENGINE OIL PRESSURE (A146CB10)

15A

CABIN LIGHTS (A146CB55)

10A

WINDSHIELD WIPER (A146CB59)

5A

RH FUEL QUANTITY WARNING (A124CB2)

10A

LH STANDBY PUMP (A124CB11)

5A

LH ENGINE OIL TEMP (A146CB17)

5A

STALL WARNING CONTROL (A146CB12)

AVIONICS ANNUNCIATOR (A146CB60)

5A

RH MAIN ENGINE ANTI-ICE (A146CB58)

5A

RH FUEL QUANTITY (A124CB6)

5A

LH AUXILIARY FUEL QUANTITY WARN AND TRANSFER (A124CB9)

5A

LH ENGINE FIRE DETECTION (A146CB19)

5A

RH ENGINE OIL TEMPERATURE (A146CB10)

5A

LH MAIN ENGINE ANTI-ICE (A146CB57)

5A

PROP DEICE CONTROL (A146CB62)

5A

RH AUXILIARY FUEL QUANTITY WARN AND TRANSFER (A124CB8)

5A

LH FUEL QUANTITY (A124CB7)

5A

LH ENGINE FUEL FLOW (A146CB21)

5A

RH ENGINE FIRE DETECTION (A146CB20)

5A

SURFACE DEICE (A146CB61)

7.5A

BATTERY BUS-TIE (A146CB64)

5A

FUEL CROSSFEED (A124CB1)

5A

LH FUEL QUANTITY WARNING (A124CB3)

5A

AVIONICS MASTER CONTROL (A146CB90)

5A

RH ENGINE FUEL FLOW (A146CB22)

5A

GENERATOR RESET (A146CB63)

5A

BATTERY TEMP INDICATOR (A146CB94)

5A

AC BUS CONTROL (A124CB24)

5A

LH FUEL PRESSURE WARNING (A124CB5)

7.5A

5A

*

FL24B 091531AA.AI

Triple-Fed Bus Power Distribution (FL-1 thru FL-119, FL-121; FM-1 thru FM-8) Figure 5

A26

24-50-00

Page 17 Aug 1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TRIPLE-FED BUS

20A

15A SUBPANEL FEEDER (A145CB33)

FUEL PANEL FEEDER NO. 1 (A145CB31)

FUEL PANEL FEEDER NO. 2 (A145CB27)

TRIPLE-FED BUS AVIONICS FEEDER (A145CB46)

CB PANEL FEEDER NO. 4 (A145CB34)

CB PANEL FEEDER NO. 3 (A145CB32)

LANDING GEAR WARNING INDICATOR (A146CB2)

5A

LH BLEED AIR WARNING (A146CB5)

5A

ANNUNCIATOR WARNING INDICATOR (A146CB4)

5A

LH ENGINE OIL PRESSURE WARNING (A146CB7)

5A

RH BLEED AIR WARNING (A146CB6)

7.5A

LH ENGINE START CONTROL (A146CB13)

5A

RH ENGINE OIL PRESSURE WARNING (A146CB8)

5A

LH ENGINE IGNITOR POWER (A146CB15)

7.5A

5A

ENGINE AUTOFEATHER (A146CB11)

5A

5A

20A

7.5A

PITOT HEAT (CB111)

2A

LANDING GEAR CONTROL (CB107)

SEE APPLICABLE AVIONICS DRAWING 5A

7.5A

20A

35A

20A

LANDING GEAR WARNING (A146CB1) ANNUNCIATOR POWER WARNING (A146CB3)

7.5A

20A CB PANEL FEEDER NO. 2 (A145CB30)

5A

EFFECTIVITY FL-120, FL-122 THRU FL-214; FM-9 IF INSTALLED

CB PANEL FEEDER NO. 1 (A145CB28)

*

20A

5A

LH BLEED AIR CONTROL (A146CB46)

PILOT TURN & SLIP (A146CB45)

5A

TEMPERATURE CONTROL (A146CB48)

PILOT AIR DATA ALTIMETER (A146CB47)

5A

PRESSURE CONTROL (A146CB50)

5A

OUTSIDE AIR TEMP (A146CB49)

5A

OXYGEN CONTROL (A146CB52)

5A

RH FIREWALL VALVE (A124CB1)

RH ENGINE START CONTROL (A146CB14)

5A

AIRSPEED WARN (A146CB51)

5A

CABIN ALTITUDE HIGH (A146CB54)

10A

RH STANDBY PUMP (A124CB2)

5A

RH ENGINE IGNITOR POWER (A146CB16)

5A

INSTRUMENT INDIRECT LIGHTS (A146CB53)

5A

CABIN DIFFERENTIAL HIGH (A146CB56)

5A

RH FUEL PRESSURE WARNING (A124CB5)

5A

LH FIREWALL VALVE (A124CB13)

LH ENGINE FIRE DETECTION (A146CB19)

5A

STALL WARNING CONTROL (A146CB12)

15A

CABIN LIGHTS (A146CB55)

10A

WINDSHIELD WIPER (A146CB59)

5A

RH FUEL QUANTITY WARNING (A124CB6)

10A

LH STANDBY PUMP (A124CB12)

LH ENGINE INSTRUMENT (A146CB21)

5A

RH ENGINE FIRE DETECTION (A146CB20)

AVIONICS ANNUNCIATOR (A146CB60)

5A

RH MAIN ENGINE ANTI-ICE (A146CB58)

5A

RH FUEL QUANTITY (A124CB4)

5A

LH AUXILIARY FUEL QUANTITY WARN AND TRANSFER (A124CB11)

AVIONICS MASTER CONTROL (A146CB90)

7.5A

RH ENGINE INSTRUMENT (A146CB22)

5A

LH MAIN ENGINE ANTI-ICE (A146CB57)

5A

PROP DEICE CONTROL (A146CB62)

5A

RH AUXILIARY FUEL QUANTITY WARN AND TRANSFER (A124CB3)

5A

LH FUEL QUANTITY (A124CB10)

5A

SURFACE DEICE (A146CB61)

7.5A

BATTERY BUS-TIE (A146CB64)

5A

FUEL CROSSFEED (A124CB7)

5A

LH FUEL QUANTITY WARNING (A124CB8)

5A

GENERATOR RESET (A146CB63)

5A

AC BUS CONTROL (A124CB24)

5A

LH FUEL PRESSURE WARNING (A124CB9)

5A

* 5A

BATTERY TEMP INDICATOR (A146CB94)

FL24B 091532AA.AI

Triple-Fed Bus Power Distribution (FL-120, FL-122 thru FL-380, FL-382; FM-9 thru FM-11) Figure 6 Page 18 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TRIPLE-FED BUS

20A

15A SUBPANEL FEEDER (A145CB33)

FUEL PANEL FEEDER NO. 1 (A145CB31)

ANNUNCIATOR POWER WARNING (A146CB3)

20A FUEL PANEL FEEDER NO. 2 (A145CB27)

TRIPLE-FED BUS AVIONICS FEEDER (A145CB46)

7.5A

CB PANEL FEEDER NO. 4 (A145CB34)

LANDING GEAR WARNING (A146CB1)

20A

35A

20A CB PANEL FEEDER NO. 3 (A145CB32)

5A

20A CB PANEL FEEDER NO. 2 (A145CB30)

FM-15 AND AFTER

5A

CB PANEL FEEDER NO. 1 (A145CB28)

* EFFECTIVITY FL-538, FL-544 AND AFTER; FGC 1 SERVO (A146CB29)

20A

7.5A

PITOT HEAT (CB111)

2A

LANDING GEAR CONTROL (CB107)

5A

LH BLEED AIR WARNING (A146CB5)

5A

LH ENGINE OIL PRESSURE WARNING (A146CB7)

5A

LANDING GEAR WARNING INDICATOR (A146CB2)

7.5A

LH ENGINE START CONTROL (A146CB13)

5A

ANNUNCIATOR WARNING INDICATOR (A146CB4)

5A

LH BLEED AIR CONTROL (A146CB46)

5A

LH ENGINE IGNITOR POWER (A146CB15)

5A

RH BLEED AIR WARNING (A146CB6)

5A

TEMPERATURE CONTROL (A146CB48)

5A

ENGINE AUTOFEATHER (A146CB11)

5A

RH ENGINE OIL PRESSURE WARNING (A146CB8)

5A

PRESSURE CONTROL (A146CB50)

5A

LH ENGINE FIRE DETECTION (A146CB19)

5A

RH TORQUEMETER (A146CB10)

5A

OXYGEN CONTROL (A146CB52)

2A

DCU 2 SECONDARY (A124CB29)

3A

COCKPIT VOICE RECORDER (A146CB89)

7.5A

RH ENGINE START CONTROL (A146CB14)

5A

CABIN ALTITUDE HIGH (A146CB54)

5A

RH FIREWALL VALVE (A124CB1)

5A

AVIONICS MASTER CONTROL (A146CB90)

5A

RH ENGINE IGNITOR POWER (A146CB16)

5A

INSTRUMENT INDIRECT LIGHTS (A146CB53)

5A

CABIN DIFFERENTIAL HIGH (A146CB56)

10A

RH STANDBY PUMP (A124CB2)

5A

LH FIREWALL VALVE (A124CB13)

1A

AURAL WARNING (A146CB95)

5A

STALL WARNING CONTROL (A146CB12)

15A

CABIN LIGHTS (A146CB55)

10A

WINDSHIELD WIPER (A146CB59)

5A

RH FUEL PRESSURE WARNING (A124CB5)

10A

LH STANDBY PUMP (A124CB12)

3A

PILOT AUDIO (A146CB99)

5A

RH ENGINE OIL PRESSURE (A146CB18)

AVIONICS ANNUNCIATOR (A146CB60)

5A

RH MAIN ENGINE ANTI-ICE (A146CB58)

5A

RH FUEL QUANTITY WARNING (A124CB6)

5A

LH AUXILIARY FUEL QUANTITY WARN AND TRANSFER (A124CB11)

1A

PILOT AUDIO CONTROL (A146CB98)

5A

RH ENGINE FIRE DETECTION (A146CB20)

5A

LH MAIN ENGINE ANTI-ICE (A146CB57)

5A

PROP DEICE CONTROL (A146CB62)

5A

RH FUEL QUANTITY (A124CB4)

5A

LH FUEL QUANTITY (A124CB10)

CABIN AUDIO (A146CB97)

3A

CCP (A146CB26)

5A

SURFACE DEICE (A146CB61)

BATTERY BUS-TIE (A146CB64)

5A

RH AUXILIARY FUEL QUANTITY WARN AND TRANSFER (A124CB3)

5A

LH FUEL QUANTITY WARNING (A124CB8)

LH IAPS (A146CB122)

15A

DC CONVERTER 2 (A146CB76)

5A

GENERATOR RESET (A146CB63)

RH IAPS (A146CB127)

5A

FUEL CROSSFEED (A124CB7)

5A

LH FUEL PRESSURE WARNING (A124CB9)

7.5A

7.5A

SEE APPLICABLE AVIONICS DRAWING

*

5A

5A

OUTSIDE AIR TEMP (A146CB49)

7.5A

7.5A

FGC 2 SERVO (A146CB30)

2A

DCU 1 SECONDARY (A124CB14)

FL24B 091533AA.AI

Triple-Fed Bus Power Distribution (FL-381, FL-383 and After; FM-12 and After) Figure 7

A26

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Battery and Center Bus Power Distribution Figure 8

Page 20 Aug 1/09

24-50-00

A26

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

ELECTRICAL LOAD DISTRIBUTION - MAINTENANCE PRACTICES BUS CONFORMITY CHECK The following procedure should be performed to determine the need for system repairs or after any system maintenance has been performed: a. Place the battery switch in the OFF position and the battery bus switch in the EMER position. 1. Rotate the VOLTMETER BUS SELECT switch through each switch position. 2. Verify that the voltmeter indicates zero volts for each position. b. Place the BAT BUS switch in the NORM position. 1. Rotate the VOLTMETER BUS SELECT switch through each switch position. 2. Verify that all switch positions indicate zero on the voltmeter with the exception of the BAT position which should indicate battery voltage. c.

Place the battery switch in the ON position. 1. Rotate the VOLTMETER BUS SELECT switch through each switch position again. Battery voltage should be indicated on the voltmeter for the BAT and CTR positions. The voltmeter should indicate slightly less than battery voltage for the TPL FED position. The voltmeter should indicate zero volts for all other positions. Verify that the BAT TIE OPEN annunciator light extinguishes. 2. Verify that the yellow L DC GEN, R DC GEN, L GEN TIE OPEN, R GEN TIE OPEN and red #1 AC BUS (Prior to FL-383 Except FL-381; Prior to FM-12) and #2 AC BUS (Prior to FL-383 Except FL-381; Prior to FM-12) warning annunciators are illuminated.

d. Place the GEN TIES switch to the MAN CLOSE position, then release it to the NORM position. 1. Verify that the green MAN TIES CLOSE annunciator is illuminated and that the amber L GEN TIE OPEN and R GEN TIE OPEN annunciators are extinguished. 2. Rotate the VOLTMETER BUS SELECT switch through each switch position. Observe that the voltmeter indicates battery voltage for the BAT, L GEN, R GEN, and CTR positions and slightly less than battery voltage for the TPL FED position. 3. The voltmeter should indicate zero volts for the EXT PWR position. 4. Verify that the loadmeters indicate zero percent. e. Place the BUS SENSE switch in the TEST position and observe the following: 1. The amber L GEN TIE OPEN, R GEN TIE OPEN and BAT TIE OPEN annunciators should be illuminated and the green MAN TIES CLOSE annunciator should extinguish. 2. Rotate the VOLTMETER BUS SELECT switch through each switch position and verify that the voltmeter indicates zero volts for each position with the exception of BAT and TPL FED. f.

Place the BUS SENSE switch in the RESET position and release to NORM. Verify that the yellow L GEN TIE OPEN, R GEN TIE OPEN and BAT TIE OPEN annunciators are extinguished and that the green MAN TIES CLOSE annunciator is illuminated.

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Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL g. Place the GEN TIES switch in the OPEN, then return it to the NORM position and observe that the yellow L GEN TIE OPEN and R GEN TIE OPEN annunciators illuminate and that the green MAN TIES CLOSE annunciator extinguishes. h. Start the RH engine with procedures outlined in the Super King Air B300 Pilot’s Operating Handbook. i.

When engine N1 speed has reached high idle, move the RH GEN control switch to RESET, then release to ON. Verify that the yellow R DC GEN, R GEN TIE OPEN and L GEN TIE OPEN annunciators are extinguished. 1. Observe that the right loadmeter initially indicates a high load and that on FL-1 thru FL-214 and FM-1 thru FM-9, the amber BATTERY CHARGE annunciator is temporarily illuminated (If the airplane has a lead acid battery installed the BATT CHARGE light may be disabled. Check the applicable STC). 2. Rotate the VOLTMETER BUS SELECT switch to L GEN and CTR, then to R GEN and note that the voltmeter indicates 28.25 ±0.25 vdc for each position. Rotate the VOLTMETER BUS SELECT switch to the TPL FED position and note that the voltmeter indicates slightly less than 28.25 ±0.25 vdc. 3. Verify that the right loadmeter indicates 50% load or less.

j.

Start the LH engine with procedures outlined in the Super King Air B300 Pilot’s Operating Handbook.

k.

Once high idle is established, place the L GEN switch in the RESET position, then release it to ON. 1. Verify that both loadmeters are approximately equal (within 10%). 2. The yellow L DC GEN annunciator should extinguish.

l.

Place the GEN TIES switch in the OPEN position and verify that the yellow L GEN TIE OPEN and R GEN TIE OPEN annunciators are illuminated. 1. Rotate the VOLTMETER BUS SELECT switch through each switch position. 2. Verify that the voltmeter indicates 28.25 ± 0.25 vdc for the L GEN and R GEN positions and slightly less than 28.25 ±0.25 vdc for the TPL FED position. 3. Verify that the voltmeter indicates battery voltage in the both the BAT and CTR position. 4. Verify that the voltmeter indicates zero voltage for the EXT PWR position.

m. Place the L GEN control and BAT switches in the OFF position and observe the following: 1. The yellow BAT TIE OPEN and L DC GEN annunciators should be illuminated. 2. Rotate the VOLTMETER BUS SELECT switch to the R GEN and TPL FED positions and verify 28.25 ±0.25 volts for the R GEN bus and slightly less on the TPL FED bus. Rotate the select switch to L GEN and CTR and verify that the voltmeter indicates zero volts. n. On FL-1 thru FL-382 Except FL-381; FM-1 thru FM-11; and FN-1, place the No. 2 inverter switch in the ON position and verify that the #2 AC BUS annunciator extinguishes. o. On FL-1 thru FL-382 Except FL-381; FM-1 thru FM-11; and FN-1, place the No. 1 inverter switch in the BUS TRANSFER position and verify that the #1 AC BUS annunciator extinguishes. p. Place the L GEN switch in the RESET position, then release to ON. Verify that the L DC GEN annunciator is extinguished. q. Advance both condition levers to HIGH IDLE. Page 202 Feb 1/10

24-50-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL CAUTION: Maintain propeller RPM minimum idle speed when the RH generator bus looses power and the props go to flight idle pitch, otherwise the engine components may be damaged. r.

Place the R GEN switch in the OFF position. 1. Verify that the #1 AC BUS and the #2 AC BUS on FL-1 thru FL-382 Except FL-381; FM-1 thru FM-11; and FN-1, and the R DC GEN annunciators are illuminated. 2. Rotate the VOLTMETER BUS SELECT switch to the L GEN and TPL FED positions and note 28.25 ±0.25 volts on the L GEN bus and slightly less than 28.25 ±0.25 volts on the TPL FED bus. Rotate the select switch to the CTR or R GEN positions and verify that the voltmeter indicates zero volts.

s.

On FL-1 thru FL-382 Except FL-381; FM-1 thru FM-11; and FN-1, place the No. 1 inverter select switch in the ON position and verify that the #1 AC BUS annunciator remains illuminated.

t.

Place the BAT switch in the ON position and verify that the yellow BAT TIE OPEN and, on FL-1 thru FL-382 Except FL-381; FM-1 thru FM-11; and FN-1, the red #1 AC BUS annunciators extinguish.

u. Place the GEN TIES switch in the NORM position and verify that the yellow L GEN TIE OPEN, R GEN TIE OPEN and, on FL-1 thru FL-382 Except FL-381; FM-1 thru FM-11; and FN-1, the red #2 AC BUS annunciator extinguishes. v.

On FL-1 thru FL-382 Except FL-381; FM-1 thru FM-11; and FN-1, place the No. 2 inverter switch in the OFF position and verify that the red #2 AC BUS annunciator illuminates.

w. On FL-1 thru FL-382 Except FL-381; FM-1 thru FM-11; and FN-1, place the No. 2 inverter switch in the BUS TRANSFER position and verify that the red #2 AC BUS annunciator extinguishes. x.

Shut down the engines as outlined in the Super King Air B300 Pilot’s Operating Handbook.

ELECTRICAL LOAD UTILIZATION CHARTS The following chart lists the electrical load requirements for each item of electrical equipment on the airplane. To determine the total electrical load of the airplane, determine the electrical load of all optional equipment installed in the airplane and add that number to the total electrical load of the standard equipment. The total load shall not exceed 90 percent (540 amperes) of the total generating capacity of the two 28-volt, 300-ampere starter/generators. When an item of equipment functions in more than one system, the load value per unit listed in Chart 201 represents the highest value required to operate that item. Each starter/generator supplies half the load of the triple-fed bus when both starter/generators are operating in parallel with the bus-tie relays closed.

A27

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 Electrical Load Distribution Units Used

Load Ea. Unit (Amps DC)

LH Fire Extinguisher Bottle

1

3.00

LH Eng Fire Extinguisher Test Module

1

0.01

LH Eng Fire Ext. Arm Light

2

0.04

LH Fire Ext. Discharge Light

2

0.04

RH Fire Extinguisher Bottle

1

3.00

RH Eng Fire Extinguisher Test Module

1

0.01

RH Eng Fire Ext. Arm Light

2

0.04

RH Fire Ext. Discharge Light

2

0.04

Cabin Door Handle Position Obsv. Light

1

0.17

3

Cabin Door Fwd Hook Obsv. Light

1

0.20

3

Cabin Door Aft Hook Obsv. Light

1

0.20

3

Threshold light

1

0.17

3

Spar Cover Light (Fwd)

1

0.29

3

Spar Cover Light (Aft)

1

0.29

3

Exterior Entry Light

1

1.43

3

Emergency Glareshield Light

4

0.17

LCD Digital Clock

1

0.03

Baggage Light

2

0.30

Airstair Door Step Light

3

0.17

Battery Relay

1

0.50

Head Phone Amp

1

0.012

3

101

Gnd Comm Control Relay

1

0.09

3

101

Gnd Comm Power Relay

1

0.09

3

101

Gnd Comm Power Switch Lt

4

0.04

3

101

Comm No 1 Control Head Lt

1

0.10

3

101

Pilot Mic Relay

2

0.09

Comm No. 1 (Receive) VHF-22A No. 1

1

0.40

3

101

Comm No. 1 (Transmit)

1

5.00

3

101

Aural Warning Unit

1

0.06

3

101

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Battery Bus

Page 204 Feb 1/10

24-50-00

0.01

0.01

0.03 117 3 0.50

101

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

GND COM switch Solenoid

1

GND COM Ann Light

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

0.06

3

102

4

0.024

3

102

Ground Com RTU Relay

1

0.09

3

102

Ground Com Com 1 Relay

1

0.09

3

102

Ground Com Select Relay

1

0.09

Ground Com Pilot Audio Relay

1

0.06

3

102

Ground Com Copilot Audio Relay

1

0.06

3

102

Nose Interphone Inhibit Relay

1

0.06

3

102

RTU Panel Lights

1

1.50

3

102

Pilot Audio Amp

1

1.00

3

102

Pilot Audio Cont

1

0.30

3

102

Copilot Audio Amp

1

1.00

3

102

Copilot Audio Cont

1

0.30

3

102

Refreshment Bar Clock (Optional)

1

0.04

3

102, 117

Com No. 1 (Receive)

1

0.58

3

102

Com No. 1 (Transmit)

1

4.28

3

102

ELT Panel

1

0.10

RTU Control

0

0.54

Cockpit Blower Motor (Low Speed)

1

0.30

17

113

Forward Plenum Servo

1

0.15

17

113

Electric Heat Circuit Card Assembly

1

0.07

17

113

Cockpit Entry Lights Control Switch

1

0.10

25

116

R Fwd Club Table Light Power Supply

1

0.25

25

116

Reading Light Controller

1

0.20

25

116

Entry Lights Mini-Switch

1

0.14

Vestibule Light

1

0.20

24

116

Baggage Light No. 1

1

0.20

24

116

Baggage Light No. 2

1

0.20

24

116

Entry Lights Power Relay

1

0.09

Battery Bus (Continued)

A27

102

0.04

0.10

102 102

116

116

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Page 205 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Flap Motor

1

28.00

Flap Position Transmitter

1

0.06

0.06

Flap Position Indicator

1

0.08

0.08

Flap Motor Relay

1

1.25

Flight Hour Meter

1

0.01

0.01

Fuel Quantity Indicator Lights

2

0.15

0.15

Pilot Overhead Flood Lights

1

0.30

0.30

117

Copilot Overhead Flood Lights

1

0.30

0.30

117

Side Panel Light Dim Control

1

0.04

0.04

Pilot Overhead Flood Light Dim Control

1

0.04

0.04

117

Copilot Overhead Flood Lt Dim Control

1

0.04

0.04

117

Pilot Flight Instruments Lights

11

0.155

1.70

101

Flight Instrument Dim Control

2

0.04

0.08

101

Engine Instrument Lights

1

1.21

1.21

101

Map Lights

2

0.30

0.30

101

Radio Instruments Dim Control

1

0.04

0.04

101

Glareshield Placard Light Panel

1

0.05

0.05

101

Radio Panel Lights

32

0.024

0.77

101

Radio Panel Control Heads

6

0.10

0.60

101

Map Light

1

0.30

Electroluminescent Pwr Supply Chan 2

1

2.00

No. 1 DCU-Primary Power

1

0.53

Cabin FSB & No Smoke Sign Lt Vanity

2

0.10

0.20

117

Cabin FSB & No Smoke Sign Lt Aft

2

0.10

0.20

117

Cabin FSB & No Smoke Sign Lt Forward

2

0.10

0.20

117

Baggage Light

3

0.30

0.90

117

Left Chip Detector Caution Ann Light

2

0.04

4

Pilot Instr Pnl Lts Pwr Supply

1

3.34

21

102

DBU-4000

1

0.32

3

103

DBU/FSU Switching Relays

5

0.02

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Left Generator Bus

Page 206 Feb 1/10

24-50-00

11

11

102 2.00

102 102

103

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

DBU-5000

1

0.43

No. 1 EDC - Primary Power

1

0.36

Right Bleed Air Flow Control Valve

1

0.03

0.03

Right Bleed Air Flow Control Valve

1

1.00

1.00

Right Pneumatic Bleed Air Shutoff Valve

1

0.80

Right Bleed Air Off Caution Ann Light

2

0.04

Bleed Air Time Delay

1

0.06

Left Bleed Air Bypass Valve

1

0.15

16

Right Bleed Air Bypass Valve

1

0.15

16

Furnishings Pwr Relay

1

0.10

0.10

117

Prepco (hot beverage tank)

1

3.57

3.57

117

Prepco Pwr Sw

1

0.04

0.04

117

Prepco ON Lt

1

0.11

0.11

117

Pedestal Cigar Lighter

1

6.30

Left Fuel Vent Heater

1

2.20

Left Auxiliary Actuator

1

3.00

Left Eng Anti-Ice Pwr Off Relay

1

0.04

Left Eng Anti-Ice Pwr On Relay

1

0.04

Control Relays

7

0.04

2

Left Bus Tie Relay

1

0.60

2

Right Bus Tie Relay

1

0.60

2

Battery Bus Tie Relay

1

0.60

2

Battery Tie Open Caution Ann Light

2

0.04

2, 4

Left Generator Tie Open Caution Ann Lt

2

0.04

2, 4

Right Generator Tie Open Caution Ann Lt

2

0.04

2, 4

Left DC Generator Warning Ann Light

2

0.04

2, 4

Right DC Generator Warning Ann Light

2

0.04

2, 4

Manual Tie Close Advisory Light

2

0.04

2, 4

Battery Bus Tie Current Sensor

1

0.04

2

Left Generator Bus Tie Current Sensor

1

0.04

2

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

3

104

Left Generator Bus (Continued)

A27

102

4 0.06

10

24-50-00

Page 207 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Right Generator Bus Tie Current Sensor

1

0.04

Pilot PFD - Heater Power

1

8.16

Left Landing Light

1

8.93

Left Nav Light

2

0.92

Right Nav Light

2

0.92

Tail Nav Light

1

0.89

Tail Flood Light

2

2.68

ESIS Battery

1

4.60

102

ESIS display +28VDC

1

0.80

102

Magnetometer +28VDC

1

0.05

102

Prop Deice Timer

1

0.44

10

Prop Deice Boots

4

7.35

10

Copilot Enco Altn

1

0.50

0.50

101

Alt Alert

1

0.30

0.30

101

Vent Blower Motor

1

25.0

114

Forward Cabin Blower Motor

1

16.50

113

Inverter 60Hz

1

20.00

102, 117

Refreshment Bar Lts

3

0.17

0.51

117

Refreshment Bar Lt Sw

1

0.04

0.04

117

Hot Cup (Optional)

1

23.30

23.30

117

Hot Cup Control Module (Optional)

1

2.00

2.00

117

Pilot Windshield Anti-Ice Controller

1

0.08

10

Pilot Windshield Anti-Ice Contr Hi Cont Relay

1

0.35

10

Pilot Wndshld Anti-Ice Contr Lo Cont Relay

1

0.35

10

Pilot Windshield

1

42.70

10

Pilot Windshield RCCB

1

0.01

10

Pilot Windshield RCCB

1

0.01

10

Pilot Overhead Flood Light Power Supply

1

0.25

0.25

116

Copilot Overhead Flood Light Pwr Supply

1

0.25

0.25

116

Pilot Overhead Flood Light Dim Control

1

0.01

0.01

116

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Left Generator Bus (Continued)

Page 208 Feb 1/10

24-50-00

2 102 13

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Copilot Overhead Flood Lt Dim Control

1

0.01

0.01

116

Cabin FSB & No Smoke Sign Lt Vanity

2

0.01

0.01

116

Cabin FSB & No Smoke Sign Lt Aft

1

0.01

0.01

116

Cabin FSB & No Smoke Sign Lt Forward

1

0.01

0.01

116

Vestibule Light

1

0.20

0.20

24

116

Baggage Light No. 1

1

0.20

0.20

24

116

Baggage Light No. 2

1

0.20

0.20

116

Left Interiors Bus Relay

1

0.35

0.35

116

Right Interiors Bus Relay

1

0.10

0.10

116

Inverter Power Relay

1

0.35

0.35

116

Aircell Telephone Transceiver

1

6.00

6.00

116

Aircell Telephone Router

1

4.00

4.00

116

XM Radio

1

2.00

2.00

116

Primary Environmental Controller

1

1.00

1.00

116

Secondary Envir Controller (Optional)

1

1.00

1.00

116

MCD-3000 (Optional)

1

5.50

5.50

116

Fwd Entertainment Cabinet Monitor

1

1.11

1.11

116

Aft Cabinet Monitor (Optional)

1

1.11

1.11

116

Individual Seat Monitors (Optional)

8

0.46

3.71

116

Seat No. 3 Heater (Optional)

1

2.70

2.70

116

Seat No. 5 Heater (Optional)

1

2.70

2.70

116

Seat No. 7 Heater (Optional)

1

2.70

2.70

116

Seat No. 9 Heater (Optional)

1

2.70

2.70

116

ARINC 429 to RS232 Converter

1

0.10

0.10

116

Programmable Switch Panels

9

0.25

2.25

116

IPOD ECM

1

0.43

0.43

116

ECS Control Relay

2

0.08

0.08

116

Entry Lights Mini-Switch

1

0.14

0.14

116

Lavatory Mini-Switch

1

0.07

0.07

116

High Definition Audio/Video Unit HDAV-3000

1

4.64

4.64

116

Equipment

Notes

Effectivity

Left Generator Bus (Continued)

A27

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Page 209 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Window Shade Controllers

15

0.07

1.02

Cabin Refreshment Bar Drawer Lights

4

0.12

116

Left Midship Cabinet Drawer Light

1

0.12

116

Right Midship Cabinet Drawer Light

1

0.12

116

Left Aft Low Profile Cabinet Drawer Light

1

0.12

116

Right Aft Low Profile Cabinet Drawer Light

1

0.12

116

Aft Entertainment Cabinet Lights (Optional)

2

0.12

116

Vanity Water Valve Assembly

1

0.25

116

Vanity Drain Valve Assembly

1

0.25

116

Vanity LED Strip Light

1

0.12

116

Vanity Touch Switch

1

0.10

Vanity Light Block

1

0.64

116

Vanity Light Block Power Supply

1

0.10

116

Equipment

Notes

Effectivity

Left Generator Bus (Continued)

Page 210 Feb 1/10

24-50-00

0.10

116

116

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Skywatch HP

1

2.00

2.00

102

TCAS II (Optional)

1

2.80

2.80

102

TCAS II Mounting Tray Fan

1

0.25

0.25

102

No. 1 GPS

1

0.32

0.32

102

No. 1 CDU

1

1.25

1.25

102

No. 1 DME

1

0.64

0.64

102

Radar

1

3.10

3.10

102

Nose Equipment Cooling Fan

1

0.19

0.19

102

Sound Management System

1

15

15

105

HF Radio (Transmit) (Optional)

1

14.20

HF Radio (Receive) (Optional)

1

1.10

1.10

106

HF Antenna Coupler (Optional)

1

2.10

2.10

106

HF Sidetone Relay (Optional)

1

0.06

SELCAL Unit (Optional)

1

0.25

0.25

106

Aircell Satellite Telephone (Optional)

1

3.30

3.30

106

Telephone Adapter (Optional)

1

0.50

0.50

106

FSU

1

1.07

1.07

107

FSU Fan

1

0.12

0.12

107

VHF 22A (Transmit)

1

5.00

5.00

VHF 22A (Receiver)

1

0.40

0.40

101

ADF 60A

1

0.60

0.60

101

DME 42

1

0.80

0.80

101

WXR 300

1

3.75

3.75

101

TDR 90

1

1.90

1.90

101

Equipment

Notes

Effectivity

Avionics Left Generator Bus

A27

106

106

14

24-50-00

101

Page 211 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Overhead Control Panel Lights

54

0.024

1.30

101

Overhead Instrument Panel Lights

9

0.024

0.22

101

Overhead Instrument Lights

4

0.05

0.20

101

Right Inboard Subpanel Lights

22

0.024

0.53

101

Left Outboard Subpanel Lights

24

0.024

0.58

101

Right Outboard Subpanel Lights

20

0.04

0.48

101

Left Inboard Subpanel Lights

21

0.024

0.50

101

Pedestal Lights

4

0.024

0.10

101

Right CB Panel Lights

78

0.024

1.87

101

Upper and Lower Fuel Control Panel Lights

30

0.024

0.72

101

Copilot Turn and Slip

1

0.50

0.50

101

Ovhd, Subpanel & Console Lts Dim Cont

1

0.04

0.04

Right Outboard Subpanel Lights

1

0.43

0.43

Engine Control Edgelit Lights

1

0.07

0.07

Rudder Control Edgelit Lights

1

0.05

0.05

Left Loadmeter

1

0.05

0.05

Right Loadmeter

1

0.05

0.05

Voltmeter

1

0.05

0.05

Prop Deice Ammeter

1

0.05

0.05

Magnetic Compass Light

2

0.04

0.08

Cabin Pressure Control Light

2

0.04

0.08

Electroluminescent Pwr Supply Chan 1

1

2.00

2.00

Copilot Flight Instrument Dim Control

1

0.04

0.04

Map Light

1

0.03

0.03

102

Reading Lights

8

0.03

0.24

117

Table Lights

4

0.03

0.12

117

Prop Sync Control Box

1

0.50

0.50

Right Chip Detector Caution Ann Light

2

0.04

4

Ground Idle Stop Enable Relay

2

0.09

3

Voltage Dropping Relay

2

0.09

3

Equipment

Notes

Effectivity

Right Generator Bus

Page 212 Feb 1/10

24-50-00

102

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Ground Idle Stop Relay

2

0.09

3

Prop Ground Solenoid Ann Light

2

0.04

4

Left Prop Speed Reset Solenoid

1

1.20

3, 8

Right Prop Speed Reset Solenoid

1

1.20

3, 8

Left Ground Idle Stop Solenoid

1

1.80

3

Right Ground Idle Stop Solenoid

1

1.80

3

Right Fuel Vent Heater

1

2.20

10

Right Auxiliary Actuator

1

3.00

Right Eng Anti-Ice Pwr Off Relay

1

0.04

Right Eng Anti-Ice Pwr On Relay

1

0.04

Control Relays

7

0.04

2

Left Bus Tie Relay

1

0.60

2

Right Bus Tie Relay

1

0.60

2

Battery Bus Tie Relay

1

0.60

2

Battery Tie Open Caution Ann Light

2

0.04

2, 4

Left Generator Tie Open Caution Ann Lt

2

0.04

2, 4

Right Generator Tie Open Caution Ann Lt

2

0.04

2, 4

Left DC Generator Warning Ann Light

2

0.04

2, 4

Right DC Generator Warning Ann Light

2

0.04

2, 4

Manual Tie Close Advisory Light

2

0.04

2, 4

Battery Bus Tie Current Sensor

1

0.04

2

Left Generator Bus Tie Current Sensor

1

0.04

2

Right Generator Bus Tie Current Sensor

1

0.04

2

MFD - Heater Power

1

8.16

TAWS+

1

1.25

Copilot Instr Pnl Lt Pwr Supply

1

1.34

20

102

Pedestal Lts Pwr Supply

1

1.05

19

102

No. 2 EDC

1

0.36

102

No. 2 DCU

1

0.53

102

Trim Servo Power

1

0.75

102

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Right Generator Bus (Continued)

A27

0.04

8.16

102 108

24-50-00

Page 213 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Brake Deice Solenoid

2

0.80

18

Left Brake Deice On Advisory Ann Lts

2

0.04

18

Right Brake Deice On Advisory Ann Lts

2

0.04

18

Right Landing Light

1

8.93

13

Stall Warning Sensor Heat Control Relay

1

0.09

3

Stall Warning Lift Transducer

1

8.50

10

Right Pitot Heat Element

1

4.29

4.29

Window Defog Valve

1

0.20

0.20

Left Wing Strobe Light Power Supplies

1

1.50

1.50

Right Wing Strobe Light Power Supplies

1

1.50

1.50

Tail Strobe Light Power Supplies

1

1.50

1.50

Left Recognition Light

1

1.25

Right Recognition Light

1

1.25

Toilet

1

5.50

Air Conditioner Clutch

1

1.70

15

114

Air Conditioner Clutch

1

3.80

15

113

N1 Speed Module Assembly

1

0.03

Electric Heat Circuit Card Assembly

1

0.05

Electric Heat Lockout Relay

1

0.09

Electric Heat Relay

2

0.60

3

Aft Evaporator Blower Motor

1

17.60

15

Cabin Blower Motor, AFT

1

16.50

16.50

113

Cockpit Blower Motor

1

9.50

9.50

113

Cockpit Blower Relay

1

0.09

0.09

113

Copilot Windshield

1

42.70

10

Copilot Windshield Anti-Ice Controller

1

0.08

10

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Right Generator Bus (Continued)

Page 214 Feb 1/10

24-50-00

117

0.03 3

114

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Copilot Windshield Anti-Ice Hi Cont Relay

1

0.35

10

Copilot Windshield Anti-Ice Lo Cont Relay

1

0.35

10

Copilot Flight Instruments Lights

8

0.155

1.24

101

Gyro Instrument Light

2

0.25

0.50

101

Gyro Instrument Dim Control

2

0.04

0.08

101

Prop Sync Control Switch Lights

4

0.04

0.16

101

No. 2 Inverter

1

39.00

Trim Motor

1

2.00

101

Electric Trim Annunciator Light

2

0.04

101

Electric Trim Disconnect Relay

1

0.81

101

Control Relay

1

0.09

101

EGPWS Mark VII

1

3.00

Condenser Blower Relay

1

0.35

Hot Gas Bypass Solenoid

1

0.89

Electric Heat Power Relays

2

0.60

3

103

Electric Heat Circuit Card

1

0.05

3

103

Cockpit Entry Lights Control Switch

2

0.10

0.10

25

116

Reading Lights Controller

2

0.20

0.20

25

116

Reading Light No. 3 Power Supply

1

0.25

0.25

116

Reading Light No. 4 Power Supply

1

0.25

0.25

116

Reading Light No. 5 Power Supply

1

0.25

0.25

116

Reading Light No. 6 Power Supply

1

0.25

0.25

116

Reading Light No. 7 Power Supply

1

0.25

0.25

116

Reading Light No. 8 Power Supply

1

0.25

0.25

116

Reading Light No. 9 Power Supply

1

0.25

0.25

116

Reading Light No. 10 Power Supply

1

0.25

0.25

116

Left Fwd Club Table Light Power Supply

1

0.25

0.25

116

Left Aft Club Table Light Power Supply

1

0.25

0.25

116

Right Fwd Club Table Light Power Supply

1

0.25

0.25

Right Aft Club Table Light Power Supply

1

0.25

0.25

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Right Generator Bus (Continued)

A27

6

3.00

101

109 5

104 104

25

24-50-00

116 116

Page 215 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Floor Level Accent Lights

6

0.08

0.45

116

Vanity Reading Light Power Supply

1

0.25

0.25

116

Left Baggage Reading Lt Pwr Supply (Opt.)

1

0.25

0.25

116

Right Baggage Reading Lt Pwr Supply (Opt.)

1

0.25

0.25

116

Aft Cabinet AC Controller (Optional)

1

0.08

0.08

116

Left Fwd Club AC Controller

1

0.08

0.08

116

Left Aft Club AC Controller

1

0.08

0.08

116

Right Fwd Club AC Controller

1

0.08

0.08

116

Right Aft Club AC Controller

1

0.08

0.08

116

Cockpit AC Controller

1

0.08

0.08

116

Toilet

1

7.50

Seat No. 4 Heater

1

2.70

2.70

116

Seat No. 6 Heater

1

2.70

2.70

116

Seat No. 8 Heater

1

2.70

2.70

116

Seat No. 10 Heater

1

2.70

2.70

116

115 VAC 60 Hz Inverter

1

41.50

41.50

116

230 VAC 60 Hz Inverter (Optional)

0

41.50

Equipment

Notes

Effectivity

Right Generator Bus (Continued)

Page 216 Feb 1/10

24-50-00

116

116

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Notes

Effectivity

No. 2 VHF Com (Receive)

1

0.58

0.58

14

102

No. 2 VHF Com (Transmit)

1

4.28

14

102

Copilot Audio Control Panel

1

0.30

0.30

102

Copilot Audio Amplifier

1

1.00

1.00

102

No. 2 Transponder

1

1.00

1.00

102

No. 2 DCP

1

0.27

0.27

102

No. 2 PFD

1

3.93

3.93

102

No. 2 AHC

1

0.70

0.70

102

No. 2 ADC

1

0.36

0.36

102

P/O IAPS - IEC Power

1

0.60

0.60

102

Right Instrument Panel Cooling fan

1

0.19

0.19

102

Left Instrument Panel Cooling fan

1

0.19

0.19

102

Copilot PFD - Heater Power

1

8.16

8.16

102

Radio Altimeter

1

1.00

1.00

102

No. 2 CDU (Optional)

1

1.25

1.25

102

No.2 NAV (NAV-4000) (Optional)

1

0.64

0.64

102

No. 2 NAV (NAV-5000) (Optional)

1

0.43

0.43

102

No. 2 GPS (Optional)

1

0.32

0.32

102

No. 2 DME (Optional)

1

0.64

0.64

102

No. 3 VHF Com (Receive) (Optional)

1

0.58

0.58

No. 3 VHF Com (Transmit) (Optional)

1

4.28

CMU (Optional)

1

0.48

0.48

107

XM WX (Optional)

1

0.40

0.40

107

ALT 50A

1

0.80

0.80

101

VIR-32

1

1.00

1.00

101

DME 670

1

2.25

2.25

101

RMI-30

1

0.60

0.60

101

MCS 65

1

1.00

1.00

101

TDR 90

1

1.90

1.90

101

Equipment Avionics Right Generator Bus

A27

14

107

14

107

24-50-00

Page 217 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Upper Flashing Beacon

1

3.20

3.20

Lower Flashing Beacon

1

3.20

3.20

Left Ice Light

1

1.43

10

Right Ice Light

1

1.43

10

Taxi Light

1

8.93

Landing/Taxi Light On Advisory Light

2

0.04

Right Prop Deice Boot

4

7.35

Left Prop Deice Boot

4

7.35

Control Relays

7

0.04

External Power Control

1

0.03

Battery Tie Open Caution Ann Light

2

0.04

2

Left Generator Tie Open Caution Ann Lt

2

0.04

2

Right Generator Tie Open Caution Ann Lt

2

0.04

2

Left DC Generator Warning Ann Light

2

0.04

2

Right DC Generator Warning Ann Light

2

0.04

2

Manual Tie Close Advisory Light

2

0.04

2

External Power Caution Ann Light

2

0.04

Left Generator Bus Tie Current Sensor

1

0.04

0.04

2

Right Generator Bus Tie Current Sensor

1

0.04

0.04

2

Battery Bus Tie Current Sensor

1

0.04

0.04

2

Battery Bus Tie Relay

1

0.60

0.06

2

Left Bus Tie Relay

1

0.60

0.06

2

Right Bus Tie Relay

1

0.60

0.06

2

Electric Heat Caution Ann Lights

2

0.04

3

Landing Gear Motor

1

150.00

11

Time Delay Module Assembly

1

0.02

11

Time Delay Relay

1

0.09

11

No. 1 Inverter

1

39.00

6

Equipment

Notes

Effectivity

Center Bus

Page 218 Feb 1/10

24-50-00

4

2 0.03

101

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Condenser Blower Motor

1

Condenser Blower Motor

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

51.28

5

114

1

30.00

15

113

Forward Electric Heater

1

100.00

3

114

Electric Heater

1

150.00

3

113

Aft Electric Heater

1

98.00

3

114

Center Bus (Continued)

A27

24-50-00

Page 219 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

P/0 IAPS - Aileron/Rudder Servo Power

1

2.75

102

P/0 IAPS - Aileron/Rudder Servo Power

1

2.75

102

FGP - FGS A Power

1

0.36

0.36

Rudder Boost Transducer, Left

1

0.50

0.50

Rudder Boost Transducer, Right

1

0.50

0.50

Rudder Boost Relay

1

0.06

0.06

Landing Gear Warning Silence Relay

1

0.09

Landing Gear Warning Silence Relay

1

0.09

Hydraulic Fluid Level Sensor

1

0.12

Hydraulic Fluid Low Caution Light

2

0.04

Annunciator Control Module

1

0.20

Caution Advisory Light Assembly

104

0.04

Master Warning Lights

16

0.04

Annunciator Warning Light Assembly

40

0.04

8

Left Bleed Fail Warning Ann Light

2

0.04

4

Left Eng Oil Pressure Low Warn Ann Lt

2

0.04

4

Autofeather Relay

4

0.09

11

Left Autofeather Advisory Ann Light

2

0.04

11

Right Autofeather Advisory Ann Light

2

0.04

11

Left Auto Dump Solenoid Valve

1

0.80

11

Right Auto Dump Solenoid Valve

1

0.80

11

Left Start Relay

1

4.50

9

Left Generator Control Relay

1

0.10

9

Left Control Relay

4

0.09

9

Right Generator Control

1

0.04

9

Bus Tie Control Relay

1

0.04

9

Left Ignitor Exciter

1

1.00

9

Left Ignitor On Advisory Ann Light

2

0.04

9

Left Engine Torque Pressure Transmitter

1

0.02

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Triple Fed Bus

Page 220 Feb 1/10

24-50-00

102

0.12 4 0.20 8

0.02

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Left Oil Pressure Transmitter

1

0.17

0.17

Left Engine Fire Detector Switch Light

1

0.04

4

Left Engine Fire Detector Switch Light

1

0.04

4

Cockpit Voice Recorder

1

0.43

0.43

Aural Warning Generator (Idle)

1

0.10

0.10

Aural Warning Generator (Operate)

1

0.10

Number 1 Avionics Relay

1

0.50

7

Number 2 Avionics Relay

1

0.50

7

Number 3 Avionics Relay

1

0.50

7

Pilot Audio Amplifier

1

1.00

1.00

Pilot Audio Control Panel

1

0.30

0.30

Cabin Audio

1

0.10

0.10

Left IAPS Power

1

1.18

1.18

Handle Lamps

2

0.04

Landing Gear Position Lights

4

0.04

Landing Gear Handle Lights Relay

1

0.09

Left Firewall Valve Lights

2

0.04

4

Right Firewall Valve Lights

2

0.04

4

Duct Overtemp Caution Ann Light

2

0.04

4

Oxygen Not Armed Caution Ann Light

2

0.04

4

Passenger Oxygen On Advisory Ann Lt

2

0.04

4

Left Engine Ice Fail Caution Ann Light

2

0.04

4

Right Engine Ice Fail Caution Ann Light

2

0.04

4

Left Prop Pitch Advisory Ann Light

2

0.04

4

Right Prop Pitch Advisory Ann Light

2

0.04

4

Left Prop Pitch Indicator Relay

1

0.04

0.04

Right Prop Pitch Indicator Relay

1

0.04

0.04

Left Prop Pitch Proximity Switch

1

0.02

0.02

Right Prop Pitch Proximity Switch

1

0.02

0.02

Battery charge Monitor Module

1

0.03

0.03

Equipment

Notes

Effectivity

Triple Fed Bus (Continued)

A27

102

5

24-50-00

110

Page 221 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Battery charge Caution Light

2

Left Engine Anti-Ice Advisory Ann Lt

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

0.04

4

110

2

0.04

10

Right Engine Anti-Ice Advisory Ann Lt

2

0.04

10

Cabin Altitude Advisory Annunciator Lt

2

0.04

4

Left Pitot Heat Caution Annunciator Lt

2

0.04

4

Right Pitot Heat Caution Annunciator Lt

2

0.04

4

Right Bleed Fail Warning Ann Light

2

0.04

4

Right Eng Oil Pressure Low Warn Ann Lt

2

0.04

4

Stall Warning Lift Computer

1

2.00

Right Start Relay

1

4.50

9

Right Generator Control Relay

1

0.10

9

Right Control Relay

2

0.09

9

Bus Tie Control Relay

1

0.04

9

Left Oil Temp/Pressure Indicator

2

0.17

0.34

101

Left Fuel Flow Indicator and Transmitter

1

0.05

0.05

101

Left Generator Control

1

0.04

9

Right Ignitor Exciter

1

1.00

9

Right Ignitor On Advisory Ann Light

2

0.04

9

Right Engine Torque Pressure Transmitter

1

0.02

0.02

Right Oil Pressure Transmitter

1

0.17

0.17

Right Engine Fire Detector Switch Light

2

0.04

No. 2 DC Converter

1

0.14

0.14

CCP

1

0.14

0.14

Digital OAT Remote Processor

1

0.29

0.29

Digital OAT Indicator

1

0.01

0.01

Indirect Instrument Lights Dim Control

1

0.04

Glareshield Light

8

0.17

102

Glareshield Light

10

0.17

111

Glareshield Light

11

0.17

112

Cabin Light Power Supply

6

2.10

Triple Fed Bus (Continued)

Page 222 Feb 1/10

24-50-00

2.00

4

12.60

23

102 107

117

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Cabin Light Dimmer Control Relay

1

0.09

0.09

117

Cabin Light Dimmer Switch Relay

1

0.09

0.09

117

Cabin Light Dimmer

1

0.03

0.03

117

Avionics Annunciator

1

1.00

1.00

102

Right Oil Temperature/Pressure Indicator

2

0.17

0.34

101

Right Fuel Flow Indicator and Transmitter

1

0.05

0.05

101

Pilots Turn and Slip

1

0.30

0.30

101

Left Main Engine Anti-Ice Actuator

1

3.00

Left Main Engine Anti-Ice Off Relay

1

0.04

Left Main Engine Anti-Ice On Relay

1

0.04

Right Adv Lt Test/Surface Deice Module

1

0.20

10

Wing Deice Advisory Annunciator Light

2

0.04

10

Tail Deice Advisory Annunciator Light

2

0.04

10

Deice Distributor Valve

1

1.50

10

Left Generator Control Panels

1

0.01

Right Generator Control Panels

1

0.01

P/0 IAPS - Elevator Servo Power

2

2.75

FGP - FGS B Power

1

0.36

0.36

Rudder Boost Relay

1

0.06

0.06

Left Bleed Air Flow Control

1

0.03

0.03

Left Bleed Air Flow Control Valve

1

1.00

1.00

Left Pneumatic Bleed Air Shutoff Valve

1

0.80

Left Bleed Air Off Caution Ann Light

2

0.04

Cabin Temperature Control Unit

1

0.50

0.50

113

Cabin Air Temperature Indicator

1

0.33

0.33

113

Air Conditioner N1 Low Advisory Ann Lt

2

0.04

Left Bleed Air Bypass Valve

1

0.15

Right Bleed Air Bypass Valve

1

0.15

Cabin Add Heat Servo

1

0.15

113

Cabin Heat Servo

1

0.15

113

Equipment

Notes

Effectivity

Triple Fed Bus (Continued)

A27

10 0.04

102 102

4

4

24-50-00

Page 223 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cockpit Heat Servo

1

0.15

113

Cockpit Add Heat Servo

1

0.15

113

Cockpit Temp Sensor Fan

1

0.06

0.06

113

Cabin Temp Sensor Fan

1

0.06

0.06

113

Forward Plenum Servo

1

0.15

Cabin Pressure Preset Solenoid Valve

1

0.62

3

Door Seal Solenoid Valve

1

0.62

3

Cabin Pressure Safety Valve

1

0.62

3

Lockout Relay

1

0.09

Cabin Oxygen Control Solenoid

1

0.50

Cabin Altitude High Warning Ann Light

2

0.04

4

Cabin Altitude Advisory Ann Light

2

0.04

4

Cabin Differential High Warning Ann Lt

2

0.04

4

Windshield Wiper Motor

1

5.20

11

Right Main Engine Anti-Ice Actuator

1

3.00

10

Right Main Engine Anti-Ice Off Relay

1

0.04

Right Main Engine Anti-Ice On Relay

1

0.04

Left Prop De-Ice Control Relay

1

0.10

Right Prop De-Ice Control Relay

1

0.10

Left Bus Tie Relay

1

0.60

2

Right Bus Tie Relay

1

0.60

2

Battery Bus Tie Relay

1

0.60

2

Control Relays

7

0.04

2

Battery Tie Open Caution Ann Light

2

0.04

2

Left Generator Tie Open Caution Ann Lt

2

0.04

2

Right Generator Tie Open Caution Ann Lt

2

0.04

2

Left DC Generator Warning Ann Light

2

0.04

2

Right DC Generator Warning Ann Light

2

0.04

2

Manual Tie Close Advisory Light

2

0.04

2

Battery Bus Tie Current Sensor

1

0.04

2

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Triple Fed Bus (Continued)

Page 224 Feb 1/10

24-50-00

113

0.09

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Left Generator Bus Tie Current Sensor

1

0.04

2

Right Generator Bus Tie Current Sensor

1

0.04

2

Right IAPS Power

1

1.55

Left Fuel Quantity Caution Ann Light

2

0.04

Left Fuel Warning Sensor

1

0.12

Left Fuel Pressure Low Warning Ann Lt

2

0.04

Left Fuel Quantity Indicator

1

0.03

Fuel Quantity Gauging Select Relay

1

0.15

8

Left No Fuel Transfer Caution Ann Lt

2

0.04

4

Auto Fuel Transfer Module Assembly

1

0.01

0.01

Left Auxiliary Fuel Transfer Valve

1

0.43

1.43

Left Standby Pump

1

8.50

Left Firewall Shutoff Valve

1

2.00

No. 1 DCU - Secondary Power

1

0.43

Fuel Crossfeed Valve

1

0.68

Left Standby Pump Relay

1

0.09

Right Standby Boost Pump Relay

1

0.09

Fuel Crossfeed Advisory Annunciator Lt

2

0.04

4

Right Fuel Quantity Caution Ann Light

2

0.04

4

Right Fuel Warning Sensor

1

0.12

Right Fuel Pressure Low Warning Ann Lt

2

0.04

Right Fuel Quantity Indicator

1

0.03

Right No Fuel Transfer Caution Ann Lt

2

0.04

Auto Fuel Transfer Module Assembly

1

0.01

0.01

Right Auxiliary Fuel Transfer Valve

1

1.43

1.43

Right Standby Pump

1

8.50

Right Firewall Shutoff Valve

1

2.00

No. 2 DCU - Secondary Power

1

0.43

0.43

Left Pitot Heat Element Assembly

1

4.29

4.29

Hydraulic Landing Gear Power Relay

1

0.62

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Triple Fed Bus (Continued)

A27

1.55

102 4

0.10 4 0.03

12

0.43

4 0.02 4

12

102

11

24-50-00

Page 225 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Hydraulic Landing Gear Down Lock Solenoid

1

0.34

Hydraulic Landing Gear Selector Solenoid

1

1.00

Hydraulic Landing Gear Level Sensor

1

0.12

8

Reverse Not Ready Caution Ann Light

2

0.04

4

Vent Blower Controller

1

0.10

0.10

114

Cabin Temperature Control Box

1

0.28

0.28

114

Cabin Temperature Control Unit

1

0.50

0.50

113

Fwd Electric Heat Power Relay

1

0.50

3

114

Aft Electric Heat Power Relay

1

0.50

3

114

Electric Heat Control Switch

1

0.13

3

114

Evaporator Door Solenoid Valve

1

0.21

Cool Command Lockout Relay

1

0.09

15

114

Cool Command Control Relay

1

0.09

15

114

Aft Evaporator Blower Relay

1

0.35

15

114

Aft Bleed Air Heat Valve

1

0.40

Module Assy - Elec Heat Control

1

0.04

0.04

114

AC Power Monitor

1

0.01

0.01

101

No. 1 AC Bus Warning Annunciator Light

2

0.04

4

101

No. 2 AC Bus Warning Annunciator Light

2

0.04

4

101

No. 1 AC Bus Relay

1

0.09

101

No. 2 AC Bus Relay

1

0.09

101

Left Engine Torquemeter Indicator

1

0.36

0.36

101

Right Engine Torquemeter Indicator

1

0.36

0.36

101

Left Engine Turbine Tachometer Indicator

1

0.36

0.36

101

Right Engine Turbine Tachometer Indicator

1

0.36

0.36

101

Left Engine Propeller Tachometer Indicator

1

0.09

0.09

101

Right Engine Propeller Tachometer Indicator

1

0.09

0.09

101

Left Engine Turbine Gas Temp Indicator

1

0.09

0.09

101

Right Engine Turbine Gas Temp Indicator

1

0.09

0.09

101

Pilots Altimeter

1

1.43

1.43

101

Equipment

Cruise Load (Amps DC)

Notes

Effectivity

Triple Fed Bus (Continued)

Page 226 Feb 1/10

24-50-00

11 1.00

0.21

114

114

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Avionics Annunciator

56

0.02

1.12

101

Cabin Lights Dimming Resistors

1

0.01

0.01

116

Cabin Lights Controller

1

0.15

0.15

116

Cabin Downwash Light Assembly

1

0.51

0.51

116

Cabin Downwash Light Assembly

1

0.72

0.72

116

Cabin Downwash Light Assembly

1

0.72

0.72

116

Cabin Downwash Light Assembly

1

0.72

0.72

116

Cabin Downwash Light Assembly

1

0.38

0.38

116

Cabin Downwash Light Assembly

1

0.72

0.72

116

Cabin Downwash Light Assembly

1

0.72

0.72

116

Cabin Downwash Light Assembly

1

0.72

0.72

116

Cabin Downwash Light Assembly

1

0.44

0.44

116

Cabin Downwash Light Assembly

1

0.44

0.44

116

Cabin Lights Control Relay

1

0.09

0.09

116

Equipment

Notes

Effectivity

Triple Fed Bus (Continued)

A27

24-50-00

Page 227 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Notes

Effectivity

No. 1 VHF Com (Receive)

1

0.58

0.58

14

102

No. 1 VHF Com (Transmit)

1

4.28

14

102

No. 1 ADC

1

0.36

0.36

102

No. 1 AHC

1

0.70

0.70

102

No. 1 DCP

1

0.27

0.27

102

No. 1 Transponder

1

1.00

1.00

102

No. 1 NAV

1

0.82

0.82

102

RTU

1

0.54

0.54

102

No. 1 DC Converter

1

4.63

4.63

Equipment Avionics Bus Triple-Fed

VHF 22A (Transmit)

5.00

22

102

14

101

VHF 22A (Receiver)

1

0.40

0.40

101

VIR 32

1

1.00

1.00

101

DB 418 (Cabin Audio)

1

5.00

5.00

101

DB 418 (Pilot Audio)

1

1.00

1.00

101

RMI 30

1

0.60

0.60

101

MCS-650

1

1.00

1.00

101

APS 65 Servo

1

2.25

2.25

101

FCS 85

1

1.44

1.44

101

LNS-616B

1

1.75

1.75

101

ESIS ON Light

1

0.02

Battery Test Light

1

0.02

ESIS display +28VDC

1

0.80

102

Magnetometer +28VDC

1

0.05

102

Bezel Lighting 5V Convertor

1

0.29

102

ESIS Battery Bus

Page 228 Feb 1/10

24-50-00

102 3, 8

102

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Equipment

Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Notes

Effectivity

NOTE 1. Only one operates at a time. 2. Equipment can be powered from the left generator bus, right generator bus, center bus, and triple fed bus. 3. Used only on the ground. 4. Loads are active only when warning or caution legends are energized. 5. Operates only when landing gear is down. 6. Load is dependent upon AC load. DC load is 1.5 amps at no load and 39 amps at 750 va. 7. Relays are energized when avionics master switch is OFF. 8. Energized by momentary switch. 9. Starting loads are not tabulated in cruise load as they should be ground loads only. 10. Used during deice operation only. 11. Used during takeoff and landing only. 12. Used only when engine-driven boost pump fails. 13. Used five minutes before landing. 14. Only one transmitter is considered in operation at a time. 15. Used when cooling is required. 16. Used only during Manual Heat or Manual Cool modes of operation. 17. Used only after aircraft shutdown in order to cool electric heat heating element. Blower operates at low speed. 18. Loads stop operating 10 minutes after landing gears are raised. 19. Supplies power to the following 5V loads: CDU 1 Lt (2.20 A) and CDU 2 Lts (2.20 A). Based on a 75% efficiency for the power supply, the total input load is 1.05 A. 20. Supplies power to the following 5V loads: Copilot PFD Lts (2.30 A), DCP 2 Lts (1.60 A), Radio Call Panel Lts (0.23 A), and Copilot Audio Control Panel Lts (1.50 A). Based on a 75% efficiency for the power supply, the total input load is 1.34 A. 21. Supplies power to the following 5V loads: FGP Lts (2.60 A), RTU Lts (1.50 A), MFD Lts (2.30 A), DCP 1 Lts (1.60 A), Pilot PFD Lts (2.30 A), Pilot Audio Control Panel Lts (1.50 A), ESIS Lts (0.14 A), and Reversionary Switch Panel Lts (2.1 A). Based on a 75% efficiency for the power supply, the total input load is 3.34 A. 22. Supplies power to the Pilot PFD (3.93 A) and AHC 1 Secondary power input (0.70 A). 23. Supplies power to the MFD (3.93 A) and AHC 2 Secondary power input (0.70 A). 24. Load is connected to Battery Bus and Left Generator Bus. 25. Load is connected to Battery Bus and Right Generator Bus.

A27

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 201 Electrical Load Distribution (Continued) Equipment

Units Used

Load Ea. Unit (Amps DC)

Cruise Load (Amps DC)

Notes

Effectivity

Effectivity (Airplane Serial Number) Reference 101. FL-1 thru FL-380, FL-382; FM-1 thru FM-11; FN-1 102. FL-381, FL-383 and After; FM-12 and After 103. FL-381, FL-383 thru FL-599, FL-601, FL-603; FM-12 thru FM-26 104. FL-600, FL-602, FL-604 and After, FM-27 and After 105. FL-381, FL-383 thru FL-424 106. FL-425 and After; FM-12 and After 107. FL-538, FL-544 and After; FM-15 and After 108. FL-600 and After; FM-25 and After 109. FL-381, FL-383 thru FL-599; FM-12 thru FM-24 110. FL-1 thru FL-214; FM-1 thru FM-9; FN-1 111. FL-1 thru FL-119, FL-121; FM-1 thru FM-8; FN-1 112. FL-120, FL-122 thru FL-380, FL-382; FM-9 thru FM-11 113. FL-493, FL-500 and After; FM-14 and After 114. FL-1 thru FL-492, FL-494 thru FL-499; FM-1 thru FM-13 115. FL-1 thru FL-492, FL-494 thru FL-500; FM-1 thru FM-13 116. FL-601, FL672, FL-688 and After With Cabin Management System Installed 117. FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After

Page 230 Feb 1/10

24-50-00

A27

C H A PT E R

EQUIPMENT/ FU RN ISM I NGS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 25 - EQUIPMENT/FURNISHINGS TABLE OF CONTENTS SUBJECT

PAGE 25-00-00

Equipment and Furnishings - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 25-10-00 Flight Compartment - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flight Compartment Chair Removal (FL-1 thru FL-238; FM-1 thru FM-9) . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flight Compartment Chair Installation (FL-1 thru FL-238; FM-1 thru FM-9) . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flight Compartment Chair Removal (FL-239 and After; FM-10 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Flight Compartment Chair Installation (FL-239 and After; FM-10 and After) . . . . . . . . . . . . . . . . . . . . . . . . .202 Flight Compartment Carpet Removal and Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Flight Compartment Upholstery Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Flight Compartment Upholstery Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Flight Compartment Headliner Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Flight Compartment Headliner Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Flight Compartment Right Side Jeppesen Cabinet Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .209 Flight Compartment Right Side Jeppesen Cabinet Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .209 Flight Compartment Left Side Jeppesen Cabinet Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .209 Flight Compartment Left Side Jeppesen Cabinet Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .209 25-20-00 Passenger Compartment - Description and Operation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . .1 Acoustic Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Rail System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Passenger Compartment Interior Trim Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Cabin Partitions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Forward Passenger Cabin Partition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Aft Passenger Cabin Partition . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Right Side Baggage Compartment Partition. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Cabinetry. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Forward Entertainment Cabinet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Forward Refreshment Cabinet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Mid-ship Cabinets. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Armcaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6 Aft Entertainment Cabinet (Optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6 Low Profile Cabinets. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6 Vanity Cabinet (Optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6 Passenger Seating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7

A27

25-CONTENTS

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 25 - EQUIPMENT/FURNISHINGS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE

Ottomans (2 ea) (Optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flex-Cabin Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Tables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Lavatory . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Baggage Compartment Cargo Web. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7 7 7 7 7

25-20-01 Passenger Compartment Chair and Ottoman - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Chair Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Chair Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Chair Recliner Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Chair Forward and Aft Tracking Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Chair Lateral Tracking Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Passenger Chair Swivel Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Seat Belt and Shoulder Harness Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ottoman Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . Ottoman Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . .

201 201 201 202 202 203 204 204 204 205

25-20-03 Passenger Compartment Partition - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Partition Removal (Forward Left and Right or Left Aft) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . Cabin Partition Installation (Forward Left and Right or Left Aft) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . Right Aft Cabin Partition Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . Right Aft Cabin Partition Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . Aft Right Side Baggage Compartment Partition Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . Aft Right Side Baggage Compartment Partition Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . Left Forward Cabin Partition Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Left Forward Cabin Partition Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Right Forward Cabin Partition Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Right Forward Cabin Partition Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Left Aft Cabin Partition Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Left Aft Cabin Partition Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .

Page 2 Feb 1/10

25-CONTENTS

201 201 201 201 201 202 202 206 206 207 207 208 208

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 25 - EQUIPMENT/FURNISHINGS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE

Right Aft Cabin Partition Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Right Aft Cabin Partition Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Right Aft Baggage Compartment Partition Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Right Aft Baggage Compartment Partition Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Cabin Partition Mounting Bracket Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Cabin Partition Mounting Bracket Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed)

. . . . . . . . . . . . . . . . . . . . . .209 . . . . . . . . . . . . . . . . . . . . . .209 . . . . . . . . . . . . . . . . . . . . . .210 . . . . . . . . . . . . . . . . . . . . . .210 . . . . . . . . . . . . . . . . . . . . . .211 . . . . . . . . . . . . . . . . . . . . . .211

25-20-05 Passenger Compartment Cabinet - Maintenance Practices (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .201 Forward Right Side Entertainment Cabinet Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Forward Right Side Entertainment Cabinet Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Right Aft Side Entertainment Cabinet Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Right Aft Side Entertainment Cabinet Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Mid-ship Cabinet (Left Side) Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Mid-ship Cabinet (Left Side) Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Mid-ship Cabinet (Right Side) Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Mid-ship Cabinet (Right Side) Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Aft Low Profile Cabinet Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Aft Low Profile Cabinet Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Magazine Rack Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Magazine Rack Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Vanity Unit Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Vanity Unit Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Cabin Isolator Plate Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Cabin Isolator Plate Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 25-20-07 Passenger Compartment Table and Armrest - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Passenger Table Closeout Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .201 Passenger Table Closeout Panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .201 Cabin Sidewall Armrest Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . .201 Cabin Sidewall Armrest Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . .201 Armcap Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . .203

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 25 - EQUIPMENT/FURNISHINGS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE

Armcap Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . Passenger Table Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . Passenger Table Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . Passenger Table Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Passenger Table Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .

204 204 204 205 205

25-20-09 Passenger Compartment Carpet - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Passenger Compartment Carpet Removal and Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . 201 Passenger Compartment Carpet Removal and Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 201 25-20-11 Passenger Compartment Sidewall Panel - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Lower Cabin Sidewall Console Panel, Scuff Panel, Inner Panel and Upholstered Panel Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Lower Cabin Sidewall Console Panel, Scuff Panel, Inner Panel and Upholstered Panel Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Upper Cabin Sidewall Window Panel Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . Upper Cabin Sidewall Window Panel Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . Cabin Window Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Cabin Window Panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Cabin Lower Sidewall Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Cabin Lower Sidewall Panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Lower Carpet Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Lower Carpet Panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . Emergency Exit Window Panel Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Emergency Exit Window Panel Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Page 4 Feb 1/10

25-CONTENTS

201

201

201 202 203 205 205 206 206 206 207 210 210

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 25 - EQUIPMENT/FURNISHINGS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE

Upper Right Vestibule Upholstery Panel Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . .211 Upper Right Vestibule Upholstery Panel Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . .211 Vestibule Window Panel and Lower Sidewall Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .211 Vestibule Window Panel and Lower Sidewall panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .212 Aft Compartment Upper Sidewall Panel Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . .214 Aft Compartment Upper Sidewall Panel Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . .214 Aft Baggage Compartment Window Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .215 Aft Baggage Compartment Window Panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .215 Aft Compartment Lower SideWall Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .215 Aft Compartment Lower SideWall Panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .216 Aft Bulkhead Upholstery Panel Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .218 Aft Bulkhead Upholstery Panel Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .218 Entry Door Closeout Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .218 Entry Door Closeout Panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .218 Coat Rod Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). . . . . . .221 Coat Rod Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . .221 25-20-13 Passenger Compartment Headliner Panel - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Headliner Panel Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . .201 Headliner Panel Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . .201 Cabin Headliner Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .201 Cabin Headliner Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .202 Cabin Headliner Closeout Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .202 Cabin Headliner Closeout Panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .202 Aft Compartment Headliner Panel Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . .204

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 25 - EQUIPMENT/FURNISHINGS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE

Aft Compartment Headliner Panel Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . 204 Vestibule and Aft Compartment Headliner Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 204 Vestibule and Aft Compartment Headliner Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 205 25-30-00 Buffet/Galley - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Refreshment Cabinet (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . 1 Buffet/Galley - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Refreshment Cabinet Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . 201 Refreshment Cabinet Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) . . . . . . . . . . . . . . . . . . . . 201 Refreshment Cabinet Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 203 Refreshment Cabinet Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 203 Isolator Plate Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . 203 Isolator Plate Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). . 203 20-60-00 Emergency-Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Emergency Locator Transmitter. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Emergency-Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Emergency Locator Transmitter Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Battery Pack Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Narco ELT Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Dorne and Margolin ELT Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Artex ELT Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Testing the Emergency locator Transmitter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202

Page 6 Feb 1/10

25-CONTENTS

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 25 - EQUIPMENT/FURNISHINGS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 25-80-00

Passenger Compartment Acoustics - Description and Operation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Passenger Compartment Acoustics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Between Frame Insulation Blankets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Over Frame Insulation Blankets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Mass Loaded Vinyl Layer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Passenger Compartment Acoustics - Maintenance Practices (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .201 Mass Loaded Vinyl Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Mass Loaded Vinyl Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Between Frame Insulation Blanket Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Between Frame Insulation Blanket Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Over Frame Insulation Blanket Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Over Frame Insulation Blanket Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203

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25-CONTENTS

Page 7 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

25-LOEP

1

Feb 1/10

25-CONTENTS

1 thru 7

Feb 1/10

25-00-00

1

Feb 1/10

25-10-00

201 thru 210

Feb 1/10

25-20-00

1 thru 8

Feb 1/10

25-20-01

201 thru 210

Feb 1/10

25-20-03

201 thru 216

Feb 1/10

25-20-05

201 thru 212

Feb 1/10

25-20-07

201 thru 207

Feb 1/10

25-20-09

201 thru 205

Feb 1/10

25-20-11

201 thru 222

Feb 1/10

25-20-13

201 thru 205

Feb 1/10

25-30-00

1 and 2 201 thru 204

Feb 1/10 Feb 1/10

25-60-00

1 201 thru 204

May 1/08 May 1/08

25-80-00

1 thru 4 201 thru 204

Feb 1/10 Feb 1/10

A27

25-LOEP

Page 1 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 000 25-00-00

EQUIPMENT AND FURNISHINGS - DESCRIPTION AND OPERATION RECOMMENDED MATERIALS The recommended materials listed in Chart 1 as meeting federal, military or supplier specifications are provided for reference only and are not specifically recommended by Hawker Beechcraft Corporation. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or by compliance to the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the chart. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

Chart 1 Recommended Materials MATERIAL

SPECIFICATION

1. Tape, 2-inch Wide, Double-Faced 2. Acetone 3. Naphtha, Aliphatic 4. Methyl Propyl Ketone (MPK) 5. Adhesive 6. Glass Cloth Tape 7. Aluminum Foil Tape 8. Tape, 2-inch Wide, Double-Faced

A27

PRODUCT No. 445

SUPPLIER Minn. Mining & Mfg. Co. St. Paul, Minn.

ASTM D-329

Obtain Locally

TT-N-95

Obtain Locally

A-A59282

Obtain Locally EC-1781

Minn. Mining & Mfg. Co. St. Paul, Minn.

No. 361

Minn. Mining & Mfg. Co. St. Paul, Minn.

No. 425

Minn. Mining & Mfg. Co. St. Paul, Minn.

No. 9579

Minn. Mining & Mfg. Co. St. Paul, Minn.

25-00-00

Page 1 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 200200200 25-10-00

FLIGHT COMPARTMENT - MAINTENANCE PRACTICES FLIGHT COMPARTMENT CHAIR REMOVAL (FL-1 THRU FL-238; FM-1 THRU FM-9) WARNING: Do not release the vertical adjustment handle at the front of the chair without weight on preloaded slides, personal injury or damage to the airplane interior could occur. NOTE: Push all circuit breakers in to prevent damage during chair removal. a. Remove the forward seat stops from the seat tracks. b. Roll the carpet forward as far as possible. c.

Lower the chair to its lowest vertical position.

d. Release the chair from its locked position and slide the chair forward until it clears the seat track. e. Reposition the outboard armrest before removing the chair so it will not strike and/or damage the components of the fuel control panel. f.

Remove the chair from the flight compartment by rotating the chair (headrest first) between the cabin partitions.

NOTE: If necessary, inspect wear limits on flight compartment seat tracks (Ref. Chapter 53-40-00).

FLIGHT COMPARTMENT CHAIR INSTALLATION (FL-1 THRU FL-238; FM-1 THRU FM-9) WARNING: Do not release the vertical adjustment handle at the front of the chair without weight on preloaded slides, personal injury or damage to the airplane interior could occur. NOTE: Push all circuit breakers in to prevent damage during chair installation. a. Lower the chair to its lowest vertical position. b. Reposition the outboard armrest before sliding the chair into place so the armrest will not strike the fuel control panel during installation of the chair. c.

Rotate the chair (base first) thru the cabin partitions and position forward of the seat tracks.

d. Align the chair base with the seat tracks and slide the chair aft while holding the locking lever (on the inboard side of the chair) in the up position until the chair engages the seat stop. e. Release the locking lever allowing the lockpin to engage one of the locking holes in the seat track. f.

Install the forward seat stops on the seat tracks.

g. Unroll the carpet under the chair and secure in place.

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FLIGHT COMPARTMENT CHAIR REMOVAL (FL-239 AND AFTER; FM-10 AND AFTER) WARNING: Do not release the vertical adjustment handle at the front of the chair without weight on preloaded slides, personal injury or damage to the airplane interior could occur. NOTE: Push all circuit breakers in to prevent damage during chair removal. a. Fabricate an armrest removal/installation tool (Ref. Figure 201). b. Position the armrest tool, behind the frame of the chair, above the outboard armrest. Place the pad of the tool against the back of the chair and push towards the chair frame to expose the head of the attaching bolt. Remove attaching hardware from the chair frame. Remove armrest from the chair frame. c.

Remove the forward seat stops from the seat tracks by releasing the seat stop pull-pins.

d. Roll the carpet forward as far as possible. e. Lower the chair to its lowest vertical position. f.

Release the chair from its locked position and slide the chair forward until it clears the seat track.

g. Remove the chair from the flight compartment by rotating the chair (headrest first) between the cabin partitions. NOTE: If necessary, inspect wear limits on flight compartment seat tracks (Ref. Chapter 53-40-00).

FLIGHT COMPARTMENT CHAIR INSTALLATION (FL-239 AND AFTER; FM-10 AND AFTER) WARNING: Do not release the vertical adjustment handle at the front of the chair without weight on preloaded slides, personal injury or damage to the airplane interior could occur. NOTE: Push all circuit breakers in to prevent damage during chair installation. a. Fabricate an armrest removal/installation tool (Ref. Figure 201). b. Lower the chair to its lowest vertical position. c.

Rotate the chair (base first) thru the cabin partitions and position forward of the seat tracks.

d. Align the chair base with the seat tracks and slide the chair aft while holding the locking lever (on the inboard side of the chair) in the up position until the chair engages the seat stop. e. Release the locking lever allowing the lockpin to engage one of the locking holes in the seat track. f.

Install the forward seat stops on the seat tracks by inserting the seat stop pull-pins.

g. Unroll the carpet under the chair and secure in place. h. Replace the outboard armrest by positioning the armrest tool, behind the frame of the chair, above the armrest. Place the pad of the tool against the back of the chair and push towards the chair frame to expose the attaching bolt hole. Replace attaching hardware.

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FLIGHT COMPARTMENT CARPET REMOVAL AND INSTALLATION Carpeting installed in the flight compartment is secured in position by strips of tape (1, Chart 1, 25-00-00) installed on the back of the carpet (Ref. Chapter 25-20-09). If it becomes necessary to install new tape, all surfaces which the tape contacts must be free of dust, oil, fingerprints or other contaminant soils. All metal surfaces should be cleaned with solvent or an approved alkaline cleaning solution (2, 3 or 4, Chart 1, 25-00-00).

COVER MAKE FROM LEATHER BOND TO TOP PLATE USING EC 847 ADHESIVE (P/N 3M CO.) OR EQUIVALENT. 13.87

TOP PLATE MAKE FROM .094 2024-T4 OR 6061-T6 ALUMINUM ALCLAD PLATE. MS27039-1-10 SCREW MS21042-3 NUT AN960-10 WASHER 3.00 REF 1.25 TYP REF .094

2.00 1.00 1.00 .50 R .38 R .63

.21 1.22 .87

.50 .69

ROUND OVER EDGES OF HANDLE TYP

10.50 PAD MAKE FROM .25 THICK PRESSTO-CELL NITRILE PVC EXPANDED RUBBER OR EQUIVALENT. BOND PAD TO TOP PLATE USING EC300L AHESIVE (P/N 3M CO.) OR EQUIVALENT.

R .50 .193 DIA HOLE THRU .200

.50

HOOK MAKE FROM 1.38 O.D. X .188 WALL 7075-T6 ALUMINUM ALLOY TUBE OR EQUIVALENT.OPTIONAL TO TACK WELD OR RIVET HOOK TO HANDLE PER BEST COMMERCIAL PRACTICE.

1.00

SUPPORT 2 PLACES MAKE FROM AND10133-1202 ALUMINUM EXTRUSION OR SHOWN.

HOOK LINER MAKE FROM LEATHER. BOND TO HOOK USING EC847 ADHESIVE (P/N3M CO.) OR EQUIVALENT.

.63

.125

HANDLE MAKE FROM AND10136-1407 ALUMINUM EXTRUSION OR EQUIVALENT TO DIMENSIONS SHOWN.

RIVET 4 PLACES TO ATTACH TOP PLATE TO SUPPORTS TOP PLATE REF SUPPORT REF 3.00 1.25 .63 1.50

.41 TYP .25 TYP 2.00 REF

FL20B 002499AA.AI

Armrest Removal/Installation Tool Figure 201

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FLIGHT COMPARTMENT UPHOLSTERY REMOVAL NOTE: The left sidewall upholstery consists of three panels: One large panel, which covers all of the left side of the flight compartment aft and below the fuel control panel and below the left windows; a small facing panel forward of the fuel control panel, and a carpeted scuff panel below the instrument panel. The right upholstery is similar to the left, except that the large sidewall panel is divided into two separate sections: One panel aft of the circuit breaker panel and below the windows and one panel below the circuit breaker panel. In addition, a narrow trim strip encloses the area just above the fuel control panel on the left side and the circuit breaker panel on the right side. To avoid degrading the performance and reliability of the Ultra Quiet Sound Management System, contact Hawker Beechcraft Corporation, Technical Support, prior to any planned removal, installation and/or refurbishment of the airplane interior. a. Remove the flight compartment chairs, map cases, etc. b. Empty the sidepanel pockets (Ref. Figure 202). c.

Disconnect and remove the ash trays, mic jack and oxygen escutcheons from the sidepanels.

d. On the left side: 1. Remove the 2 screws and washers from the upper forward end of each side pocket. (These screws secure the sidewall panel to the forward scuff panel.) 2. Remove 1 screw and washer from the forward end of the upper pocket (inside of the pocket). 3. Remove 3 screws and washers from the bottom edge of the panel assembly. 4. Pull the bottom edge of the sidepanel away from the airplane sidewall, simultaneously sliding it downward to release the clips at the upper edge of the panel and remove the panel from the airplane. e. On the right side: 1. Remove 1 screw and washer from the forward edge of the aft upholstery panel just below the aft edge of the right circuit breaker panel. 2. Remove 2 screws and washers from the bottom edge of the aft upholstery panel assembly. 3. Pull the bottom edge of the aft sidepanel away from the airplane structure, simultaneously sliding it aft and downward to release the clips at the upper edge and the backing strip at the forward edge of the panel. Remove the panel from the airplane. 4. Remove 2 screws and washers from the upper forward edge of the 2 pockets to release the panel below the right circuit breaker panel from the forward scuff panel. 5. Remove 1 screw and washer from the forward end of the upper pocket (inside of the pocket). 6. Pull the upper edge of the panel assembly away from the airplane sidewall, simultaneously lifting the panel to release the 2 clips at the lower edge of the panel. Remove the panel assembly from the airplane. f.

Remove 1 screw and washer from the lower aft corner and 1 screw approximately in the middle of each of the lower forward scuff panels beneath the instrument panel and remove the scuff panels from the airplane.

g. Remove the small facing panels just forward of the fuel control panel and the right circuit breaker panel by removing 1 screw and washer from each panel.

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FLIGHT COMPARTMENT UPHOLSTERY INSTALLATION NOTE: The left sidewall upholstery consists of 3 panels: 1 large panel, which covers all of the left side of the flight compartment aft and below the fuel control panel and below the left windows; a small facing panel forward of the fuel control panel, and a carpeted scuff panel below the instrument panel. The right upholstery is similar to the left, except that the large sidewall panel is divided into 2 separate sections: 1 panel aft of the circuit breaker panel and below the windows and 1 panel below the circuit breaker panel. In addition, a narrow trim strip encloses the area just above the fuel control panel on the left side and the circuit breaker panel on the right side. To avoid degrading the performance and reliability of the Ultra Quiet Sound Management System, contact Hawker Beechcraft Corporation, Technical Support, prior to any planned removal, installation and/or refurbishment of the airplane interior. a. Install the small facing panels forward of the fuel control panel and the right circuit breaker panel with 1 screw and washer located near the center of each panel (Ref. Figure 202). b. Install the 2 sidewall scuff panels below the instrument panel with 1 screw and washer located near the center of the panels and 1 screw and washer at the lower aft corner. c.

Left Sidewall Panel Installation: 1. Position the panel assembly in place, simultaneously sliding it upward beneath the window frame to engage the clips at the upper edge, and pushing the lower edge outward toward the airplane sidewall. 2. Install 2 screws and washers in the upper forward end of each pocket to attach the sidewall panel to the forward scuff panel below the instrument panel. 3. Install 1 screw and washer inside of the upper pocket and 3 screws and washers at the lower edge of the panel assembly to secure the panel assembly to the airplane sidewall.

d. Right Sidewall Panel Installation: 1. Position the forward upholstery panel assembly below the right circuit breaker panel in place, simultaneously sliding it downward to engage the clips at the bottom edge of the panel. 2. Align and install 2 screws and washers in the upper forward corner of each pocket to secure the sidewall panel to the forward scuff panel. NOTE: The upper forward screw must also secure the tab on the lower end of the facing panel forward of the right circuit breaker panel. 3. Install 1 screw and washer inside of the upper pocket to secure the panel assembly to a clip on the airplane sidewall. 4. Position the aft upholstery panel in place, simultaneously sliding the backing strip at the forward edge beneath the forward sidewall panel and the upper edge of the aft panel assembly beneath the window frame, engaging the clips at the upper edge. Push the lower edge of the aft panel outward against the airplane sidewall. 5. Align the screw holes and install 3 screws and washers: 1 at the upper aft corner of the upper pocket and 2 in the lower edge of the panel assembly to secure the panel to clips on the airplane sidewall. e. Connect and install the ash trays, mic jack and oxygen escutcheons in the sidepanels. f.

Install the flight compartment chairs, map cases etc.

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Flight Compartment Upholstery Figure 202

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FLIGHT COMPARTMENT HEADLINER REMOVAL NOTE: To avoid degrading the performance and reliability of the Ultra Quiet Sound Management System, contact Hawker Beechcraft Corporation, Technical Support, prior to any planned removal, installation and/or refurbishment of the airplane interior. a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Disconnect and remove the overhead electrical and instrument panels (Ref. Chapter 39-10-00).

d. Remove the sun visor assemblies (Ref. Figure 203). e. Remove the window escutcheons (Ref. Chapter 56-10-00). f.

Lower the headliner panel as necessary and disconnect all air, light and oxygen connections from the headliner panel.

g. Remove the headliner panel from the airplane.

FLIGHT COMPARTMENT HEADLINER INSTALLATION NOTE: To avoid degrading the performance and reliability of the Ultra Quiet Sound Management System, contact Hawker Beechcraft Corporation, Technical Support, prior to any planned removal, installation and/or refurbishment of the airplane interior. a. Position the headliner panel in the airplane and connect all air, light and oxygen connections to the panel (Ref. Figure 203). b. Lift the panel assembly into place and install the window escutcheons (Ref. Chapter 56-10-00). c.

Install the sun visor assemblies.

d. Install and connect the overhead electrical and instrument panels (Ref. Chapter 39-10-00). e. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

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FLIGHT COMPARTMENT RIGHT SIDE JEPPESEN CABINET REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Gain access to the flight compartment and electrically disconnect the AC outlet (1) from the Jeppesen cabinet (3) (Ref. Figure 204).

d. Electrically disconnect the Aircell Axxess data port (2) from the Jeppesen cabinet (3). e. Remove four screws (5) securing the Jeppesen cabinet (3) to the forward cabin partition. f.

Remove the Jeppesen cabinet (3) from the airplane.

FLIGHT COMPARTMENT RIGHT SIDE JEPPESEN CABINET INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the Jeppesen cabinet (3) in position on the forward cabin partition and secure using four screws (5) (Ref. Figure 204). b. Electrically connect the AC outlet (1) to the Jeppesen cabinet (3). c.

Electrically connect the Aircell Axxess data port (2) to the Jeppesen cabinet (3).

d. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

FLIGHT COMPARTMENT LEFT SIDE JEPPESEN CABINET REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove four screws (5) securing the Jeppesen cabinet (3) to the forward cabin partition. b. Remove the Jeppesen cabinet (3) from the airplane (Ref. Figure 204).

FLIGHT COMPARTMENT LEFT SIDE JEPPESEN CABINET INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the Jeppesen cabinet (3) in position on the forward cabin partition (Ref. Figure 204). b. Secure the Jeppesen cabinet (3) using four screws (5).

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1

A 2

3 5

5

1. AC OUTLET 2. AIRCELL AXXESS DATA PORT 3. JEPPESEN CABINET 4. HOOK AND LOOP FASTENER 5. SCREWS

RIGHT SIDE SHOWN LEFT SIDE TYPICAL

4 DETAIL

A

FL25B 985689AA.AI

Jeppesen Cabinet - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 204

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PASSENGER COMPARTMENT - DESCRIPTION AND OPERATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) This chapter provides the location and a general description of the furnishings and equipment installed in the passenger compartment (Ref. Figure 3).

ACOUSTIC PROTECTION Acoustic protection is achieved by the following methods: •

Isolation of the rail system from the airframe through the use of vibration isolators.

•

Isolation of all cabinetry from hard contact with the airframe through the use of vibration isolators as part of the mounting system except for hard mounted partitions.

•

Isolation of non structural windows from the airframe through the use of foam grommets and isolated mounts.

•

Skin dampening across the airplane through the use of dynamic tuned vibration absorbers (Ref. Chapter 53-11-00).

•

Insulation bags and over-frame blankets as required (Ref. Chapter 25-80-00).

RAIL SYSTEM Extruded aluminum rails are installed on each side of the passenger cabin for the mounting of all internal panels, furniture and cabinetry (Ref. Chapter 53-40-00). The rails are installed on anti-vibration mountings to maximize acoustic performance and are divided into two main zones, the passenger cabin and the vestibule/baggage compartment.

PASSENGER COMPARTMENT INTERIOR TRIM PANELS The passenger compartment interior trim panels are covered with acoustic damping material and have a decorative finish (Ref. Chart 1). The passenger compartment is divided into two main zones, the passenger cabin and the vestibule/baggage compartment. All passenger compartment interior trim panels are installed on the fuselage rail assemblies and are of a slip fit construction secured with screws or grabber latches for ease of installation.

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Chart 1 Passenger Compartment Interior Trim Panels Construction Method

Panel Title - Location

Figure/Item No.

Outside Skins - 2 layers of fiberglass Core - 1/8 inch airex core Outside Skins - 2 layers of fiberglass

Forward/Center/Aft Lower Sidewall Panel - Cabin Table Closeout Panels - Cabin Headliner Panel - Cabin Headliner Panel - Vestibule Aft Bulkhead Cover - Baggage

Figure 1, Item 5, 7, 10 Figure 1, Item 6, 8 Figure 2, Item 2 Figure 2, Item 4 Figure 2, Item 12

Outside Skins - 2 layers of fiberglass Core - 1/4 inch airex core Outside Skins - 2 layers of fiberglass

Lower Carpet Panel - Cabin Upper Aft Bulkhead Panel - Aft Baggage Window Panel - Cabin Window Panel, Escape Hatch - Cabin Window Panel - Vestibule Window Panel - Aft Baggage

Figure 1, Item 9 Figure 2, Item 11 Figure 1, Item 4 Figure 1, Item 11 Figure 2, Item 7 Figure 1, Item 1 Figure 2, Item 8 Figure 1, Item 10 Figure 2, Item 2

Lower Sidewall Panel - Aft Baggage Skins - Multiple layers of fiberglass

Entry Door Closeout Panel - Vestibule Headliner Closeout Panel - Cabin

Figure 1, Item 3 Figure 2, Item 1, 3, 5, 6

Aluminum Sheet - 0.032 aluminum

Lower Aft Bulkhead Panel - aft Baggage

Figure 2, Item 13

Black Kydex or Lexan

Lower Sidewall Panel - Vestibule

Figure 2, Item 9

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1. WINDOW PANEL - BAGGAGE COMPARTMENT 2. LOWER SIDE WALL PANEL - BAGGAGE COMPARTMENT 3. ENTRY DOOR CLOSEOUT PANEL - VESTIBULE 4. WINDOW PANEL - CABIN 5. AFT LOWER SIDE WALL PANEL - CABIN 6. AFT TABLE CLOSEOUT - CABIN 7. CENTER LOWER SIDE WALL PANEL - CABIN 8. FORWARD TABLE CLOSEOUT - CABIN 9. LOWER CARPET PANEL - CABIN 10. FORWARD LOWER SIDE WALL PANEL - CABIN 11. WINDOW PANEL - ESCAPE HATCH - CABIN 12. CLOSEOUT - ESCAPE HATCH - CABIN

1

12

2

11

3 4 5

6

10

9

7

8

NOTE: ITEMS 4 THRU 12 ARE TYPICAL FOR LEFT AND RIGHT SIDE FM25B 985625AA.AI

Passenger Compartment Interior Trim Panels - Left Side (Right Side Typical) Figure 1

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1. FORWARD RIGHT HEADLINER CLOSEOUT - CABIN 2. HEADLINER - CABIN 3. AFT RIGHT HEADLINER CLOSEOUT - CABIN 4. HEADLINER - VESTIBULE 5. AFT LEFT HEADLINER CLOSEOUT - CABIN 6. FORWARD LEFT HEADLINER CLOSEOUT - CABIN 7. WINDOW PANEL - VESTIBULE 8. WINDOW PANEL - BAGGAGE COMPARTMENT 9. LOWER SIDE WALL PANEL - VESTIBULE 10. LOWER SIDE WALL PANEL - BAGGAGE COMPARTMENT 11. AFT BULKHEAD PANEL UPPER 12. AFT BULKHEAD PANEL COVER 13. AFT BULKHEAD PANEL LOWER

4 3

5

2

1

6

8

7

11 12 10 9

13

FM25B 985626AA.AI

Passenger Compartment Interior Trim Panels - Right Side Figure 2

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CABIN PARTITIONS The forward passenger cabin, aft passenger cabin and baggage compartment partitions separate the flight compartment from the passenger cabin and the passenger cabin from the vestibule/baggage compartment (Ref. Figure 3). The sliding door assemblies and spring loaded closeouts are designed to be frangible for rapid egress from the airplane. FORWARD PASSENGER CABIN PARTITION The left and right forward passenger cabin partitions each encompass a sliding door assembly and are constructed from a lightweight composite material with a Formica laminate layer on the forward surface. AFT PASSENGER CABIN PARTITION The left and right aft passenger cabin partitions each encompass a sliding door assembly and are constructed from a lightweight composite material. RIGHT SIDE BAGGAGE COMPARTMENT PARTITION The right side baggage compartment partition is constructed of a lightweight composite material with a laminate layer on the forward surface. The baggage compartment partition is installed when the optional vanity cabinet is not installed.

CABINETRY The airplane cabinetry is intended for the storage of equipment such as audio/video equipment and carry-on items including refreshment and personal passenger-specific entertainment electronic devices (Ref. Figure 3). FORWARD ENTERTAINMENT CABINET The forward entertainment cabinet is situated aft of the right forward passenger cabin partition and is constructed from a lightweight composite material with a Laminate/Veneer finish on the exterior (Ref. Figure 3). The entertainment cabinet houses a swing-up 15 inch monitor, DVD storage, AC outlet, optional Cabin Management System (CMS) components. FORWARD REFRESHMENT CABINET The forward refreshment cabinet is situated aft of the left forward passenger cabin partition and is constructed from a lightweight composite material with a Laminate/Veneer finish on the exterior (Ref. Figure 3). The refreshment cabinet has various facilities installed (Ref. Chapter 25-30-00). MID-SHIP CABINETS Mid-ship cabinets are constructed from lightweight composite material with an exterior Laminate/Veneer finish (Ref. Figure 3). The left side mid-ship cabinet is installed between the two groups of passenger club seats on the left side of the airplane and is fitted with drawers for general storage and has an iPod docking station or an optional AirCell Axxess II cradle and cordless telephone installed to its upper surface.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL The right side mid-ship cabinet is installed between the two groups of passenger club seats on the right side of the airplane and is fitted with drawers for general storage and may have the optional Aircell Axxess II cradle and cordless telephone installed to its upper surface. ARMCAPS The left and right side armcaps are constructed from a lightweight composite material with a Laminate/Veneer finish on the exterior (Ref. Figure 3). The armcaps are installed on the left and right side passenger cabin ledges adjacent to each facing pair of passenger club seats. The armcaps have cup holders, two programmable switch units and one switch panel for auxiliary input/output. AFT ENTERTAINMENT CABINET (OPTIONAL) The aft entertainment cabinet is an optional installation and is situated forward of the right aft passenger cabin partition and is constructed from a lightweight composite material with a Laminate/Veneer finish to the exterior (Ref. Figure 3). The cabinet houses a swing-up 15 inch monitor, AC outlet, HDMI interface, facility for headset storage and general storage. LOW PROFILE CABINETS The left and right side low profile cabinets are constructed from a lightweight composite material with a Laminate/ Veneer finish to the exterior (Ref. Figure 3). The low profile cabinets contain drawers for general storage and are installed between the rear passenger club seats and the aft passenger cabin partitions. VANITY CABINET (OPTIONAL) The vanity cabinet is an optional installation and is constructed from a lightweight composite material with a Laminate/Veneer finish to the exterior (Ref. Figure 3). The vanity cabinet is installed in place of the right baggage compartment partition and has ordinance signs, a solid state touch switch and the following facilities installed: •

Sink.

•

Removable water tank (with quick disconnect fittings).

•

Overboard drain.

•

Gravity fed water faucet.

•

Mirror.

•

Internal light.

•

Trash container.

•

General storage areas.

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PASSENGER SEATING The passenger cabin can be configured for a maximum of eight passenger club seats. The four forward passenger club seats are of a standard configuration. The aft four passenger club seats can be configured to a FLEX-CABIN CONFIGURATUION. All the passenger club seats recline and swivel with lockable positioning. The cushion seat and backrest (lumbar) have an insert that can be replaced with optional heating packs giving three levels of heat for both the seat and lumbar that are controlled through each individual Programmable Switch (PSW) and armrest mounted switch. Refer to the PSW Graphical User Interface (GUI) flow for the passenger seat heating (Ref. Airplane Maintenance Manual, Chapter 23-30-03).

OTTOMANS (2 EA) (OPTIONAL) The Ottoman, one for each side, can be installed at any of the aft four passenger cabin seating positions (in lieu of seat). The ottoman is stowed against the aft cabinet / partition or forward midship cabinet when not in use. It has a hinged, dampened, upholstered cover with storage space and weighs approximately 10 Kg.

FLEX-CABIN CONFIGURATION The flex-cabin configuration allows for various passenger cabin seating configurations at the aft four passenger club seat positions. Either passenger club seats, ottomans, or neither can be installed in any configuration at the aft four seating positions.

PASSENGER TABLES There are four pull-out passenger tables installed in the passenger cabin side ledge between each pair of adjacent facing passenger seats. The passenger tables are installed to provide table space for each passenger seat (Ref. Figure 3). The passenger tables are of a hinged leaf design and are constructed of a lightweight composite material finished with a layer of Veneer.

LAVATORY The lavatory (Ref. Chapter 38-00-00) is installed in the vestibule of the airplane. The lavatory closeout is constructed from a lightweight composite material with a Veneer finish to the exterior (Ref. Figure 3).

BAGGAGE COMPARTMENT CARGO WEB The right side baggage compartment cargo web is installed between the rear pressure bulkhead and baggage compartment partition or vanity cabinet partition depending on the airplane configuration. The cargo web is secured at ten attachment points; five attachment points use hook and footman loops and five attachment points use anchor plates and quick connection studs. The baggage compartment cargo cross web is installed between the left side of the baggage compartment and right side baggage compartment partition or vanity cabinet partition depending on the airplane configuration. The cargo web is secured at nine attachment points using hook and footman loops.

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1. FORWARD CABIN PARTITION 2. FORWARD RIGHT SIDE ENTERTAINMENT CABINET 3. RIGHT SIDE MID-SHIP CABINET 4. PASSENGER TABLE (EXTENDED) 5. AFT RIGHT SIDE ENTERTAINMENT CABINET OR RIGHT SIDE LOW PROFILE CABINET 6. AFT CABIN PARTITION 7. TOILET 8. AFT RIGHT SIDE VANITY CABINET OR AFT RIGHT SIDE BAGGAGE COMPARTMENT PARTITION 9. LEFT SIDE MID-SHIP CABINET 10. REFRESHMENT CABINET 11. ARMCAP

1 2

11

3

4 11

10

11

9

11

56

7

8

FWD

FM25B 985627AA.AI

Cabinet and Equipment Locations Figure 3

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PASSENGER COMPARTMENT CHAIR AND OTTOMAN - MAINTENANCE PRACTICES Passenger chairs may have an optional seat heater. If the bottom seat cushion with built in heater pad is being replaced, replace the life preserver located in pocket on bottom side of seat cushion.

PASSENGER CHAIR REMOVAL NOTE: The following steps are applicable to all of the passenger chairs (Ref. Figure 201). a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove the shroud from around the base frame of the chair as follows: 1. Remove the two screws which secure the air outlet grill and duct to the forward side of the shroud around the chair base. 2. Slide the chair laterally to its inboard limit. 3. Carefully remove the cover from the top of the outboard side of the shroud beneath the chair assembly. The cover is secured with Dual-Lock (hook-loop) fastener strips engaged by clips bonded to the top of the shroud. 4. Slide the shroud assembly inboard, working the duct assembly loose from the inboard duct outlet on the shroud, and remove the shroud from the airplane.

d. If chair is equipped with seat heater, disconnect the seat heater connector. Cap and stow plug behind lower carpet panel (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). e. Loosen the locking nuts on all four of the chair feet in the seat tracks. f.

Lift the locking retainer on each of the rear feet, slide the chair forward to openings in the seat tracks where the chair feet can be lifted from the tracks and remove the chair from the airplane.

NOTE: The air duct assembly is attached to the chair frame and will be removed from the airplane along with the chair assembly. The duct assembly can be removed from the chair frame by removing the screw which secures the duct assembly to the outboard chair frame.

PASSENGER CHAIR INSTALLATION NOTE: When installing the passenger chairs, the aft feet locking retainers on each chair are to be positioned at the locations in the seat tracks as shown (Ref. Figure 201). a. Install the air duct assembly beneath the chair assembly by installing the locking screw in the outboard chair frame and the duct assembly. b. If chair is equipped with seat heater, remove plug from lower carpet panel and connect plug to seat heater connector (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). c.

Position the chair feet in the seat tracks and slide the chair assembly to its location (Ref. Figure 201).

d. Tighten the locking nuts on all four chair feet to secure the chair in position.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL e. Slide the chair laterally to its inboard limit. NOTE: If the duct assembly has not been disassembled by removing the glass cloth tape wrapping from the duct joint, no adjustment of the duct assembly should be required. If the tape has been removed, reseal the joint by wrapping it with glass cloth tape (6, Chart 1, 25-00-00) after adjusting the duct to fit snugly against the sidewall air outlet. f.

Install the shroud assemblies around the chair base frame. 1. Carefully slide the shroud assembly into position around the chair frame, working the inboard air duct into the duct outlet on the shroud assembly. 2. Align the forward air outlet and grill with the attaching holes in the forward side of the shroud and secure them with the attaching screws. 3. Make sure that the shroud is positioned correctly and install the cover on top of the outboard side of the shroud, engaging the Dual-Lock (hook-loop) fastener strips on each end of the cover with the clips on the shroud. 4. Return the chair to its normal position.

g. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

PASSENGER CHAIR RECLINER ADJUSTMENT If the back reclines without pressure on the reclining button, the cable is adjusted too tightly at the hydrolock. If the button is pressed in all the way and the back will not recline, the cable is adjusted too loosely. All adjustments are made at the hydrolock. Adjust the back recliner as follows: a. Remove the bottom cushion (3) of the chair (Ref. Figure 202). b. Remove the chair pan (4). c.

Locate the recliner cable (7) at the forward end of the hydrolock (10) and loosen the jam nuts (5 and 6). 1. If the chair back will not recline, decrease the threads extending through the bracket (8) by turning both jam nuts (5 and 6) clockwise. 2. If the chair back reclines without pressure on the recliner button (2) increase the amount of threads protruding through the bracket (8) by turning both jam nuts (5 and 6) counterclockwise.

d. Tighten the jam nuts (5 and 6). Do not over-tighten the jam nuts; thread damage could occur. e. Bend the tabs (9) to synchronize the locks so they release at the same time.

PASSENGER CHAIR FORWARD AND AFT TRACKING ADJUSTMENT a. Remove the bottom cushion (3) of the chair (Ref. Figure 203). b. Remove the chair pan (4). c.

Loosen the jam nuts (5 and 20) and turn the jam nut (5) counterclockwise until lockpin (10) will not clear the gear rack when the lever control (1) is lifted.

d. Turn the jam nut (5) clockwise, until the tracking pin clears the gear rack.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL e. Tighten jam nut (20). f.

Check forward and aft tracking adjustment. If not satisfactory, proceed with the following steps:

g. The gear rack (14) must be level with the bracket assembly. If the gear rack (14) is not level, add or remove washers (17) at the attaching point of the gear rack (14). h. Check the alignment of the gear rack (14) to the bracket. If the rack (14) is not perpendicular to the bracket, loosen the four screws (6, 7, and 8) and move the cover plate (9) to let the lock pin (10) align itself with the gear rack slot. i.

Tighten the four screws (6, 7 and 8) and check the forward and aft function.

j.

Check forward and aft tracking adjustment. If not satisfactory, proceed with the following steps:

k.

Remove four screws (6, 7 and 8) and lift the cover plate (9).

l.

Gently move chair frame forward and backward without lifting the lever control (1). If there is movement, replace the shim plate (12) or the shim tape (13).

m. Check the spring (11) for tension and replace if defective. n. Check the lockpin (10) for wear and replace if the wear is excessive. o. Attach the cover plate (9) to the pin block (19) with the screws (6, 7, and 8). p. Attach the chair pan assembly (4). q. Attach the chair bottom cushion (3).

PASSENGER CHAIR LATERAL TRACKING ADJUSTMENT a. Remove the bottom cushion (3) of the chair (Ref. Figure 204). b. Remove the chair pan (4). c.

Loosen the jam nuts (9 and 10) on the lower base assembly and turn the jam nut (9) counterclockwise until the locking pin will not clear the gear rack (14).

d. If the chair will move laterally without lifting the lever control (1), increase the amount of threads protruding through the bracket by turning both jam nuts (9 and 10) clockwise. e. If the chair will not move when the control lever (1) is lifted, decrease the amount of threads protruding through the bracket (11) by turning both jam nuts (9 and 10) counterclockwise. f.

Check the horizontal adjustment and shim as required at the attach point of the rod end (7) by adding or removing washer(s) (6).

g. Loosen the attaching bolts (12 and 13) of the gear rack (14) at the attaching point to make sure that the gear rack (14) is perpendicular to the bracket. h. Tighten the attaching bolts (12 and 13) and check lateral motion. i.

Remove cover plate (15) and inspect inner mechanism for excessive wear.

j.

Replace any worn parts if necessary.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL k.

Reattach cover plate (15) to pin block (16).

NOTE: After adjusting the side-motion tracking, adjust the forward and aft mechanism if necessary. l.

Attach the chair pan (4).

m. Attach the chair bottom cushion (3).

PASSENGER CHAIR SWIVEL ADJUSTMENT The swivel is set at the factory, but is adjustable for excessive up-and-down play. a. With the chair secured in airplane, remove the chair bottom cushion (1) (Ref. Figure 205). b. Remove the chair pan (2). c.

Tighten the screws (3) and bolts (4) to a maximum of 15 inch-pounds.

NOTE: Over tightening can prevent the seat from swiveling and result in damage to the swivel plate. d. Check for up-and-down movement. If up and down movement still exists after the swivel assembly has been adjusted, proceed with the following steps. e. Observe the area where the shaft (5) exits the bearing housing (9) and lift the front of the seat frame. If movement up and down is present, the bearing housing (9) must be removed. f.

Remove two bolts (10) from the bearing housing (9) and remove the bearing housing (9).

g. Remove the outer blind rivets (8) from the bearing housing (9) h. Remove the bearing (7) and wrap additional aluminum foil tape (6) (7, Chart 1, 25-00-00) around the bearing (7). i.

Slide the bearing (7) with the tape (6) into the bearing housing (9) and insert the outer blind rivets (8).

j.

Install two bolts (10) from the bearing housing (9) and replace the bearing housing (9).

k.

Attach the chair pan (2).

l.

Install the chair bottom cushion (1).

SEAT BELT AND SHOULDER HARNESS INSPECTION Contact the manufacturer of the seat belts and shoulder harnesses installed in the airplane for inspection information.

OTTOMAN REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the pedestal cover from the ottoman. b. Loosen the set screw from the two fittings used to secure the ottoman feet in position on the seat tracks. c.

Depress lever and slide the ottoman forward to the openings in the seat track where the ottoman can be lifted from the seat tracks.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL d. Remove the ottoman from the airplane.

OTTOMAN INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Position the ottoman feet in the seat tracks and slide the ottoman to its location. b. Tighten the set screw to the two fittings to secure the ottoman feet in position. c.

Install the pedestal cover to the ottoman.

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Passenger Chair Installation Figure 201

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Passenger Chair Recliner Adjustment Figure 202

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Passenger Chair Forward and Aft Tracking Adjustment Figure 203

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Passenger Chair Lateral Tracking Adjustment Figure 204

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Passenger Chair Swivel Adjustment Figure 205

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 25-20-03

PASSENGER COMPARTMENT PARTITION - MAINTENANCE PRACTICES CABIN PARTITION REMOVAL (FORWARD LEFT AND RIGHT OR LEFT AFT) (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Loosen two locknuts which secure the locking feet to the seat tacks at the base of the partition (Ref. Figure 201). b. Remove the snap-in trim strip on the edge of the partition. c.

Remove the long threaded pin which secures the partition to the headliner. Slide the bottom of the partition to an opening for the locking feet in the seat tracks and remove the partition.

CABIN PARTITION INSTALLATION (FORWARD LEFT AND RIGHT OR LEFT AFT) (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Position the locking feet on the bottom of the partition (Ref. Figure 201) in the seat tracks and slide the partition to its proper location. b. Remove the snap-in trim from the edge of the partition. c.

Align the hole in the upper end of the partition with the hole in the headliner and install the long threaded pin to secure the upper part of the partition in position.

d. Align each half of the partition with the other half so the sliding door will operate properly. e. Tighten the locknuts to secure the locking feet to the seat tracks. f.

Install the snap-in trim strip on the edge of the partition.

RIGHT AFT CABIN PARTITION REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Remove the screws which secure the locking feet to the angle at the base of the partition and to the seat tracks (Ref. Figure 202) b. Pull down on the small lever in the top of the partition to release the spring loaded pin from the headliner, slide the partition assembly inboard and remove the partition from the airplane. NOTE: The locking feet may be left in the seat tracks or removed as felt advisable.

RIGHT AFT CABIN PARTITION INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Position the partition in its location and snap the spring loaded pin at the top of the partition into the hole in the headliner (Ref. Figure 202). b. Install the two screws at the base of the partition into the locking feet in the seat tracks.

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Align the sliding door in the partition with the door in the other partition half and tighten the screws in the locking feet.

AFT RIGHT SIDE BAGGAGE COMPARTMENT PARTITION REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Remove the two screws that that attach the bottom of the partition to the right seat track riser (Ref. Figure 203). b. Remove one screw and capnut at the top of the partition and one screw and capnut from each of the two brackets at the outboard edge of the partition and remove the partition from the airplane.

AFT RIGHT SIDE BAGGAGE COMPARTMENT PARTITION INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Place the partition in the installed position in the airplane (Ref. Figure 203). b. Install one screw and capnut in each of the two attach brackets at the outboard edge of the partition and in the bracket at the top of the partition. c.

Install the two screws at the bottom of the partition to secure the partition to the aft side of the right seat track riser.

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Cabin Partition Removal/Installation (Left Forward, Right Forward and Left Aft) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 201

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Cabin Partition Removal/Installation (Right Aft) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 202

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Aft Right Side Baggage Compartment Partition Removal/Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 203

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LEFT FORWARD CABIN PARTITION REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the forward refreshment cabinet (Ref. REFRESHMENT CABINET REMOVAL, 25-30-00). b. Remove the flight compartment Jeppesen cabinet (Ref. FLIGHT COMPARTMENT LEFT SIDE JEPPESEN CABINET REMOVAL, 25-10-00). c.

Open the cabin partition sliding door to gain access to the cabin partition quick release assembly (1) (Ref. Figure 204).

d. Disengage the quick release pin (2) from the rail assembly located above the cabin partition. NOTE: Support the cabin partition when the quick release pin is disengaged from the rail assembly. e. Close the cabin partition sliding door. f.

Adjust the three nuts (3) on the mounting bracket (4) to lower the cabin partition.

g. Tilt the cabin partition and remove the cabin partition from the mounting bracket (4). h. Remove the three washers (5) from the mounting bracket (4). i.

Remove the cabin partition from the airplane.

LEFT FORWARD CABIN PARTITION INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the three washers (5) on the mounting bracket (4) (Ref. Figure 204). b. Tilt the cabin partition and install the cabin partition on the mounting bracket (4). NOTE: Support the cabin partition until the quick release pin is engaged in the rail assembly. c.

Open the cabin partition sliding door to gain access to the cabin partition quick release assembly (1).

d. Engage the quick release pin (2) in the rail assembly to secure the top of the cabin partition. e. Close the cabin partition sliding door. f.

Adjust the three nuts (3) on the mounting bracket (4) to raise the cabin partition to the desired height.

g. Open and close the cabin partition sliding door to make sure that it aligns correctly. h. Install the flight compartment Jeppesen cabinet (Ref. FLIGHT COMPARTMENT LEFT SIDE JEPPESEN CABINET INSTALLATION, 25-10-00). i.

Install the forward refreshment cabinet (Ref. REFRESHMENT CABINET INSTALLATION, 25-30-00).

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RIGHT FORWARD CABIN PARTITION REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove the forward entertainment cabinet (Ref. FORWARD RIGHT SIDE ENTERTAINMENT CABINET REMOVAL, 25-20-05).

d. Remove the Aircell Axxess II handset and cradle from the cabin partition in the flight compartment (Ref. Airplane Maintenance Manual Supplement, FLIGHT COMPARTMENT HANDSET CRADLE REMOVAL, 23-14-00). e. Remove the flight compartment Jeppesen cabinet (Ref. FLIGHT COMPARTMENT RIGHT SIDE JEPPESEN CABINET REMOVAL, 25-10-00). f.

Open the cabin partition sliding door to gain access to the cabin partition quick release assembly (1) (Ref. Figure 204).

g. Disengage the quick release pin (2) from the rail assembly located above the cabin partition. NOTE: Support the cabin partition when the quick release pin is disengaged from the rail assembly. h. Close the cabin partition sliding door. i.

Adjust the three nuts (3) on the mounting bracket (4) to lower the cabin partition.

j.

Tilt the cabin partition and remove the cabin partition from the mounting bracket (4).

k.

Remove the three washers (5) from the mounting bracket (4).

l.

Remove the cabin partition from the airplane.

RIGHT FORWARD CABIN PARTITION INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the three washers (5) on the mounting bracket (4) (Ref. Figure 204). b. Tilt the cabin partition and install the cabin partition on the mounting bracket (4). NOTE: Support the cabin partition until the quick release pin is engaged in the rail assembly. c.

Open the cabin partition sliding door to gain access to the cabin partition quick release assembly (1).

d. Engage the quick release pin (2) in the rail assembly to secure the top of the cabin partition. e. Close the cabin partition sliding door. f.

Adjust the three nuts (3) on the mounting bracket (4) to raise the cabin partition to the desired height.

g. Open and close the cabin partition sliding door to make sure that it aligns correctly. h. Install the flight compartment Jeppesen cabinet (Ref. FLIGHT COMPARTMENT RIGHT SIDE JEPPESEN CABINET INSTALLATION, 25-10-00).

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Connect the electrical connection for the Aircell Axxess II cordless handset cradle.

j.

Install the Aircell Axxess II handset and cradle (Ref. Airplane Maintenance Manual Supplement, FLIGHT COMPARTMENT HANDSET CRADLE INSTALLATION, 23-14-00).

k.

Install the forward entertainment cabinet (Ref. FORWARD RIGHT SIDE ENTERTAINMENT CABINET INSTALLATION, 25-20-05).

l.

Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

LEFT AFT CABIN PARTITION REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove cabin furnishings as necessary to gain access to the cabin partition. b. Open the cabin partition sliding door to gain access to the cabin partition quick release assembly (1) (Ref. Figure 205). c.

Disengage the quick release pin (2) from the rail assembly located above the cabin partition. NOTE: Support the cabin partition when the quick release pin is disengaged from the rail assembly.

d. Close the cabin partition sliding door. e. Adjust the three nuts (3) on the mounting bracket (4) to lower the cabin partition. f.

Tilt the cabin partition and remove the cabin partition from the mounting bracket (4).

g. Remove the three washers (5) from the mounting bracket (4). h. Remove the cabin partition from the airplane.

LEFT AFT CABIN PARTITION INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the three washers (5) on the mounting bracket (4) (Ref. Figure 205). b. Tilt the cabin partition and install the cabin partition on the mounting bracket (4). NOTE: Support the cabin partition until the quick release pin is engaged in the rail assembly. c.

Open the cabin partition sliding door to gain access to the cabin partition quick release assembly (1).

d. Engage the quick release pin (2) in the rail assembly to secure the top of the cabin partition. e. Close the cabin partition sliding door. f.

Adjust the three nuts (3) on the mounting bracket (4) to raise the cabin partition to the desired height.

g. Open and close the cabin partition sliding door to make sure that it aligns correctly. h. Install all cabin furnishings removed for access.

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RIGHT AFT CABIN PARTITION REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove cabin furnishings as necessary to gain access to the cabin partition.

d. Disconnect the electrical connector for the ordinance sign as necessary. e. Open the cabin partition sliding door to gain access to the cabin partition quick release assemblies (1) (Ref. Figure 206). f.

Disengage the quick release pins (2) from the rail assemblies located above and to the side of the cabin partition. NOTE: Support the cabin partition when the quick release pins are disengaged from the rail assemblies.

g. Close the cabin partition sliding door. h. Adjust the three nuts (3) on the mounting bracket (4) to lower the cabin partition. i.

Tilt the cabin partition and remove the cabin partition from the mounting bracket (4).

j.

Remove the three washers (5) from the mounting bracket (4).

k.

Remove the cabin partition from the airplane.

RIGHT AFT CABIN PARTITION INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the three washers (5) on the mounting bracket (4) (Ref. Figure 206). b. Tilt the cabin partition and install the cabin partition on the mounting bracket (4). NOTE: Support the cabin partition until the quick release pins are engaged in the rail assemblies. c.

Open the cabin partition sliding door to gain access to the cabin partition quick release assemblies (1).

d. Engage the quick release pins (2) in the rail assemblies to secure the top and side of the cabin partition. e. Close the cabin partition sliding door. f.

Adjust the three nuts (3) on the mounting bracket (4) to raise the cabin partition to the desired height.

g. Connect the electrical connector for the ordinance sign as necessary. h. Open and close the cabin partition sliding door to make sure that it aligns correctly. i.

Install all cabin furnishings removed for access.

j.

Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

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RIGHT AFT BAGGAGE COMPARTMENT PARTITION REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove the XM radio receiver (Ref. Airplane Maintenance Manual Supplement, XM RADIO RECEIVER REMOVAL, 23-30-05).

d. Disconnect the electrical connector for the ordinance sign as necessary (Ref. Figure 207). NOTE: Support the baggage compartment partition when bolts are removed from the baggage compartment partition. e. Remove bolt (1), washers (2), nut (3), and spacer (4) from the top bracket on baggage compartment partition (5) (Ref. Figure 207, Detail B). f.

Remove bolt (1), washers (2), nut (3), and spacer (4) from the outboard bracket on baggage compartment partition (5) (Ref. Figure 207, Detail C).

g. Remove five screws (8), washers (2) and nuts (3) from the support brackets at the bottom of the baggage compartment partition (5) (Ref. Figure 207, Detail D). h. Remove the baggage compartment partition from the airplane.

RIGHT AFT BAGGAGE COMPARTMENT PARTITION INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the baggage compartment partition (5) in position (Ref. Figure 207). NOTE: Support the baggage compartment partition until the bolts are installed through the outboard and top brackets. b. Align brackets (6 and 7) with the support and the baggage compartment partition, then Install five screws (8), washers (2) and nuts (3) to secure the support brackets to the bottom of the baggage compartment partition (5) (Ref. Figure 207, Detail D). c.

Install bolt (1), washers (2), nut (3), and spacer (4) to secure the top bracket and baggage compartment partition (5) (Ref. Figure 207, Detail B).

d. Connect the electrical connector for the ordinance sign as necessary. e. Install bolt (1), washers (2), nut (3), and spacer (4) to secure the outboard bracket and baggage compartment partition (5) (Ref. Figure 207, Detail C). f.

Install the XM radio receiver (Ref. Airplane Maintenance Manual Supplement, XM RADIO RECEIVER INSTALLATION, 23-30-05).

g. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

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CABIN PARTITION MOUNTING BRACKET REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the cabin partition as required for access. b. Lift the carpet from around the end of the mounting bracket as necessary for access to the seat track fittings. c.

Remove the two screws from the seat track fitting securing the mounting bracket.

d. Remove the mounting bracket. e. Remove the lock nut from each seat track fitting. f.

Slide the seat track fitting to an open position in the seat track and remove.

CABIN PARTITION MOUNTING BRACKET INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the seat track fittings in the seat track and slide into position. b. Secure each seat track fitting in position with the lock nut. c.

Install the mounting bracket in position and secure using two screws.

d. Install the carpet in position as necessary. e. Install the cabin partition as required.

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1 2

1. 2. 3. 4. 5.

CABIN PARTITION QUICK RELEASE ASSEMBLY QUICK RELEASE PIN ADJUSTING NUT MOUNTING BRACKET WASHER

LEFT FORWARD CABIN PARTITON SHOWN RIGHT FORWARD CABIN PARTITON TYPICAL

5

3

5

4

3

FL25B 985606AA.AI

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1

2

1. 2. 3. 4. 5.

CABIN PARTITION QUICK RELEASE ASSEMBLY QUICK RELEASE PIN ADJUSTING NUT MOUNTING BRACKET WASHER

5

3

5

3

FL25B 985703AA.AI

4

Left Aft Cabin Partition - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 205

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1 2 1. 2. 3. 4. 5.

CABIN PARTITION QUICK RELEASE ASSEMBLY QUICK RELEASE PIN ADJUSTING NUT MOUNTING BRACKET WASHER

1

2

RIGHT AFT CABIN PARTITON SHOWN WITHOUT CABINET

5

3

5

4

3

FL25B 985607AA.AI

Right Aft Cabin Partition - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 206 (Sheet 1 of 2)

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1 2 1. 2. 3. 4. 5.

CABIN PARTITION QUICK RELEASE ASSEMBLY QUICK RELEASE PIN ADJUSTING NUT MOUNTING BRACKET WASHER

1

2

RIGHT AFT CABIN PARTITON SHOWN WITH CABINET

5

3

5

4

3

FL25B 985704AA.AI

Right Aft Cabin Partition - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 206 (Sheet 2 of 2)

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ORDINANCE SIGN

B

1. BOLT 2. WASHER 3. NUT 4. SPACER 5. BAGGAGE COMPARTMENT PARTITION 6. BRACKET 7. BRACKET/PLATE 8. SCREW

C

A

3 BRACKET

2

4 2 5

1

DETAIL

D

A

1 2 DETAIL

BRACKET

C 2 3

5

8 2

1

4

2

8 2 5

7 FLOOR PANEL

2

6

3 SUPPORT

DETAIL

D DETAIL

B

FL25B 985674AA.AI

Right Aft Baggage Compartment Partition - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 207

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 25-20-05

PASSENGER COMPARTMENT CABINET - MAINTENANCE PRACTICES (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) FORWARD RIGHT SIDE ENTERTAINMENT CABINET REMOVAL a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Electrically disconnect and remove the 15 inch monitor, high definition audio visual unit and media center device from the entertainment cabinet (Ref. Pro Line 21 Maintenance Manual Supplement, CABIN MANAGEMENT SYSTEM, 23-30-03)

d. Electrically disconnect the entertainment cabinet. e. Remove the entertainment cabinet bottom drawer (7) (Ref. Figure 201). f.

Remove the four screws (4) and washers (5) securing the base of the entertainment cabinet to the isolator plates (6).

g. Remove the header (3) from the entertainment cabinet to gain access to the quick release pin (2). h. Disengage quick release pin (2) securing entertainment cabinet to the upper rail assembly. i.

Remove the entertainment cabinet from the airplane.

FORWARD RIGHT SIDE ENTERTAINMENT CABINET INSTALLATION a. Install the entertainment cabinet in position on the isolator plates (6) (Ref. Figure 201). b. Engage the quick release pin (2) in the upper rail assembly. c.

Install header (3) to the entertainment cabinet.

d. Install the four screws (4) and washers (5) to secure the base of the entertainment cabinet to the isolator plates (6). e. Install the entertainment cabinet bottom drawer (7). f.

Electrically connect the entertainment cabinet.

g. Install and electrically connect 15 inch monitor, high definition audio visual unit and media center device in the entertainment cabinet (Ref. Pro Line 21 Maintenance Manual Supplement, CABIN MANAGEMENT SYSTEM, 23-30-03). h. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

RIGHT AFT SIDE ENTERTAINMENT CABINET REMOVAL a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Electrically disconnect and remove the 15 inch monitor from the entertainment cabinet (Ref. Pro Line 21Maintenance Manual Supplement, CABIN MANAGEMENT SYSTEM, 23-30-03).

d. Electrically disconnect the entertainment cabinet. e. Remove the entertainment cabinet bottom drawer (7) (Ref. Figure 201). f.

Remove the four screws (4) and washers (5) securing the base of the entertainment cabinet to the isolator plates (6).

g. Remove the header (3) from the entertainment cabinet to gain access to quick release pin (2). h. Disengage quick release pin (2) securing the entertainment cabinet to the upper rail assembly. i.

Remove the entertainment cabinet from the airplane.

RIGHT AFT SIDE ENTERTAINMENT CABINET INSTALLATION a. Install the entertainment cabinet in position on the isolator plates (6) (Ref. Figure 201). b. Engage quick release pin (2) in the upper rail assembly. c.

Install the header (3) to the entertainment cabinet.

d. Install the four screws (4) and washers (5) to secure the base of the entertainment cabinet to the isolator plates (6). e. Install the entertainment cabinet bottom drawer (7). f.

Electrically connect the entertainment cabinet.

g. Install and electrically connect 15 inch monitor from the entertainment cabinet (Ref. Pro Line 21 Maintenance Manual Supplement, CABIN MANAGEMENT SYSTEM, 23-30-03). h. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

MID-SHIP CABINET (LEFT SIDE) REMOVAL a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove the top drawer (6) from the mid-ship cabinet to gain access to electrical connections for the iPod docking station (1) (Ref. Figure 202).

d. Disconnect electrical connections for the iPod docking station (1) and control module (2). e. Remove the bottom drawer (7) from the mid-ship cabinet. f.

Remove the four screws (3) and washers (4) securing the base of the mid-ship cabinet to the isolator plates (5).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL g. Remove the mid-ship cabinet from the airplane.

MID-SHIP CABINET (LEFT SIDE) INSTALLATION a. Install the mid-ship cabinet in position on the isolator plates (5) (Ref. Figure 202). b. Install the four screws (3) and washers (5) to secure the mid-ship cabinet to the isolator plates (5). c.

Connect the electrical connections for the iPod docking station (1) and control module (2).

d. Install the top drawer (7) and bottom drawer (6) to the mid-ship cabinet. e. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

MID-SHIP CABINET (RIGHT SIDE) REMOVAL a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove the top drawer (5) from the mid-ship cabinet to gain access to electrical connections for the Aircell Axxess II cordless handset cradle (1) (Ref. Figure 203).

d. Disconnect electrical connections for the Aircell Axxess II cordless handset cradle (1). e. Remove the bottom drawer (6) from the mid-ship cabinet. f.

Remove the four screws (2) and washers (3) securing the base of the mid-ship cabinet to the isolator plates (4).

g. Remove the mid-ship cabinet from the airplane.

MID-SHIP CABINET (RIGHT SIDE) INSTALLATION a. Install the mid-ship cabinet in position on the isolator plates (4) (Ref. Figure 203). b. Install the four screws (2) and washers (3) to secure the mid-ship cabinet to the isolator plates (4). c.

Connect the electrical connection for the Aircell Axxess II cordless handset cradle (1).

d. Install the top drawer (5) and bottom drawer (6) to the mid-ship cabinet. e. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

AFT LOW PROFILE CABINET REMOVAL NOTE: Removal procedures for the left and right side low profile cabinets are identical. a. Remove the top drawer (6) from the low profile cabinet(1) (Ref. Figure 204). b. Remove the two screws (2) securing the low profile cabinet (1) to the partition. c.

Remove the bottom drawer (7) from the low profile cabinet (1).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL d. Remove the four screws (3) and washers (4) securing the base of the low profile cabinet to the isolator plates (5). e. Remove the low profile cabinet (1) from the airplane.

AFT LOW PROFILE CABINET INSTALLATION NOTE: Installation procedures for the left and right side low profile cabinets are identical. a. Install the low profile cabinet (1) in position on the isolator plates (5) (Ref. Figure 204). b. Install the four screws (3) and washers (4) securing the base of the low profile cabinet to the isolator plates (5). c.

Install the two screws (2) securing the low profile cabinet (1) to the partition.

d. Install the top drawer (6) and bottom drawer (7) to the low profile cabinet (1).

MAGAZINE RACK REMOVAL NOTE: The removal procedure for the left and right side magazine racks is identical. a. Remove the divider (1) to gain access to the four screws (2) (Ref. Figure 205). b. Remove the four screws (2) securing the magazine rack to the partition. c.

Remove the magazine rack from the airplane.

MAGAZINE RACK INSTALLATION NOTE: The installation procedure for the left and right side magazine racks are identical. a. Install the magazine rack in position and secure with the four screw (2) (Ref. Figure 205). b. Install the divider (1) in the magazine rack.

VANITY UNIT REMOVAL a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Drain the 1.5 gallon water tank and remove tank.

d. Electrically disconnect the vanity unit. e. Remove the bottom drawer (9) from the vanity unit (Ref. Figure 206). f.

Disconnect the overboard water drain tube from the drain assembly (Ref. VANITY UNIT, OVERBOARD WATER DRAIN TUBE REMOVAL, 38-30-00).

g. Remove the seven screws (2) and washers (3) securing the base of the vanity unit to the mounting plate (6).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL h. Remove the top drawer (8) to gain access to the two side quick release pins (4) securing the vanity unit to the side rail assembly. i.

Disengage the two quick release pins (4) from the side rail assembly.

j.

Remove the header (7) from the vanity unit to gain access to the two top quick release pins (5) securing the vanity unit to the upper rail assembly.

k.

Disengage the two quick release pins (5) from the upper rail assembly.

l.

Remove the vanity unit from the airplane.

VANITY UNIT INSTALLATION a. Install the vanity unit in position on the mounting plate (6) (Ref. Figure 206). b. Engage the two top quick release pins (5) in the upper rail assembly. c.

Install the header (7) to the vanity unit.

d. Engage the two side quick release pins (4) in the side rail assembly. e. Install the top drawer (8) in the vanity unit. f.

Install the seven screws (2) and washers (3) to secure the base of the vanity unit to the mounting plate (6).

g. Connect the overboard water drain tube to the drain assembly (Ref. VANITY UNIT, OVERBOARD WATER DRAIN TUBE INSTALLATION, 38-30-00). h. Install the bottom drawer (9) in the vanity unit. i.

Electrical connect the vanity unit.

j.

Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

k.

Fill the 1.5 gallon water tank, open the faucet and run the water. Check the overboard drain assembly for leaks.

CABIN ISOLATOR PLATE REMOVAL a. Remove cabin furnishing as required for access to the isolator plate. b. Remove the carpet from the mounting bracket (Ref. PASSENGER COMPARTMENT CARPET REMOVAL AND INSTALLATION, 25-20-09). c.

Remove the screws securing the isolator plate to the seat track fittings.

d. Remove the isolator plate. e. Remove the lock nut from the seat track fitting. f.

Slide the seat track fitting to an open position in the seat track and remove.

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CABIN ISOLATOR PLATE INSTALLATION a. Install the seat track fitting in the seat track and slide into position. b. Secure the seat track fitting in position with the lock nut. c.

Install the isolator plate in position and secure using two screws.

d. Install the carpet over the mounting bracket (Ref. PASSENGER COMPARTMENT CARPET REMOVAL AND INSTALLATION, 25-20-09). e. Install the cabin furnishings as required.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

2 1. 2. 3. 4. 5. 6. 7.

ORDINANCE SIGN QUICK RELEASE PIN HEADER SCREW (4 PLACES) WASHER (4 PLACES) ISOLATOR PLATE (2 PLACES) DRAWER

3

1

7 4

6

5

6 FL25B 985610AA.AI

Aft Entertainment Cabinet - Removal/Installation (Aft Shown, Forward Identical) Figure 201

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

2

1

1. 2. 3. 4. 5. 6. 7.

IPOD DOCKING STATION IPOD ELECTRONIC CONTROL MODULE SCREW (4 PLACES) WASHER (4 PLACES) ISOLATOR PLATE (2 PLACES) TOP DRAWER BOTTOM DRAWER

6

7

5 3

4

5

FL25B 985609AA.AI

Left Side Mid-Ship Cabinet - Removal/Installation Figure 202

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1. 2. 3. 4. 5. 6.

AIRCELL AXXESS II CORDLESS HANDSET AND CRADLE SCREW (4 PLACES) WASHER (4 PLACES) 1 ISOLATOR PLATE (2 PLACES) TOP DRAWER BOTTOM DRAWER

5

6

4 2

3

4

FL25B 985608AA.AI

Right Side Mid-Ship Cabinet - Removal/Installation Figure 203

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1. 2. 3. 4. 5. 6. 7.

LOW PROFILE CABINET SCREW (2 PLACES) SCREW (4 PLACES) WASHER (4 PLACES) ISOLATOR PLATE (2 PLACES) TOP DRAWER BOTTOM DRAWER

2 1

6

7 3 4

5

5 FL25B 985677AA.AI

Left Low Profile Cabinet (Optional) - Removal/Installation (Left Shown, Right Identical) Figure 204 Page 210 Feb 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1

2

2

1 - DIVIDER 2 - SCREW (4 PLACES) FL25B 985605AA.AI

Magazine Rack (Optional) - Removal/Installation Figure 205

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5 1. 2. 3. 4. 5. 6. 7. 8. 9.

ORDINANCE SIGN SCREW (7 PLACES) WASHER (7 PLACES) QUICK RELEASE PIN (SIDE) QUICK RELEASE PIN (TOP) MOUNTING PLATE HEADER TOP DRAWER BOTTOM DRAWER

7

1

4

8 NOTE: AFT FACE QUICK RELEASE PIN NOT SHOWN

2

9

3

6

FL25B 985634AA.AI

Vanity Unit (Optional) - Removal/Installation Figure 206

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 25-20-07

PASSENGER COMPARTMENT TABLE AND ARMREST - MAINTENANCE PRACTICES PASSENGER TABLE CLOSEOUT PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Swivel the two passenger seats, adjacent to the table installation, fully inboard. b. Carefully pull the bottom of the table closeout panel (1) inboard to release the two grabber latches (2) (Ref. Figure 201). c.

Open the table lid and disengage the table closeout panel upper flange (3) from the groove under the armcap assembly.

d. Remove the table closeout panel (1) from the airplane.

PASSENGER TABLE CLOSEOUT PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Open the table lid and install the table closeout panel upper flange (3) in the groove under the armcap assembly (Ref. Figure 201). b. Carefully push the bottom of the table closeout panel (1) outboard until the two grabber latches (2) engage. c.

Close the table lid and swivel the two passenger seats into position.

CABIN SIDEWALL ARMREST REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Remove the passenger chairs. b. Remove the screws from the upright ends of the armrest assembly and the cabin tables (Ref. Figure 202). c.

Pull the armrest away from the cabin sidewall to disengage the extrusion on the base of the armrest assembly from the upper console panel extrusion, and remove the armrest assembly.

CABIN SIDEWALL ARMREST INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Place the armrest into position, engaging the extrusion on the armrest base with the extrusion on the upper console panel (Ref. Figure 202). b. Align the holes in the upright ends of the armrests with the corresponding holes through the cabin tables and secure them in place with the attaching screws. c.

Install the passenger chairs.

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TABLE LID (REF)

ARM CAP (REF)

3

2

SIDE RAIL (REF)

1

2

FWD

1. TABLE CLOSEOUT PANEL 2. GRABBER LATCHES 3. UPPER FLANGE

FL25B 985672AA.AI

Passenger Table Closeout Panel - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 201 Page 202 Feb 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Cabin Sidewall Armrests Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 202

ARMCAP REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Perform the PASSENGER TABLE CLOSEOUT PANEL REMOVAL procedure.

d. Remove the lower sidewall panels (Ref. CABIN LOWER SIDEWALL PANEL REMOVAL, 25-20-11). e. Lift the table from the stowed position to the horizontal (in use) position. f.

Electrically disconnect the programmable switches (PSW) and switch panel (Ref. Pro Line 21 Maintenance Manual Supplement, CABIN MANAGEMENT SYSTEM, 23-30-03).

g. Remove the twenty two screws and washers securing the armcap assembly to the mounting brackets (Ref. Figure 203). h. Place the table in the stowed position.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL i.

Remove the armcap assembly from the airplane.

ARMCAP INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Place the armcap assembly in position and lift the table from the stowed position to the horizontal (in use) position. b. Secure the armcap in position using the twenty two screws and washers (Ref. Figure 203). c.

Electrically connect the programmable switches (PSW) and switch panel (Ref. Pro Line 21 Maintenance Manual Supplement, CABIN MANAGEMENT SYSTEM, 23-30-03).

d. Place the table in the stowed position. e. Install the lower sidewall panels (Ref. CABIN LOWER SIDEWALL PANEL INSTALLATION, 25-20-11). f.

Perform the PASSENGER TABLE CLOSEOUT PANEL INSTALLATION procedure.

g. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

PASSENGER TABLE REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Reposition the passenger chairs as necessary to provide access to the cabin table to be removed. b. Lift the table from the stowed position to the horizontal (in use) position. c.

Remove the four attaching screws from the cabin sidewall beneath the table and remove the table assembly from the airplane.

PASSENGER TABLE INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Make sure that the passenger chairs are positioned as necessary to provide access to the passenger table installation area. b. Lift the table from the stowed position to the horizontal (in use) position. c.

Position the table assembly on the cabin sidewall with the four attach holes aligned with the rivnuts installed in the cabin sidewall.

d. Secure the table to the sidewall with the four attaching screws. e. Place the table in the stowed position. f.

Reposition the passenger chairs for normal seating.

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PASSENGER TABLE REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Perform the PASSENGER TABLE CLOSEOUT PANEL REMOVAL procedure. b. Lift the table from the stowed position to the horizontal (in use) position. c.

Remove the two armcap mounting brackets (4) from the armcap and table frame (Ref. Figure 204).

d. Remove the two mounting brackets (5) from the table frame. e. Remove the two screws (1) and washers (2) from the top of the table frame (3). f.

Place the table in the stowed position.

g. Remove the three screws (1) and washers (2) from the bottom of the table frame (3). h. Remove the table assembly from the airplane. NOTE: When removing the table assembly take care not to damage the monitor wire bundles.

PASSENGER TABLE INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Position the table assembly on the cabin sidewall with the five attach holes aligned with the nutplates installed in the cabin sidewall. b. Lift the table from the stowed position to the horizontal (in use) position. c.

Install the two screws (1) and washers (2) to secure the top of the table frame (3) (Ref. Figure 204).

d. Install the three screws (1) and washers (2) to secure the bottom of the table frame (3). e. Install the two mounting brackets (5) and the two armcap mounting brackets (4). f.

Place the table in the stowed position. NOTE: Make sure the table assembly moves to the fully closed position without interference.

g. Perform the PASSENGER TABLE CLOSEOUT PANEL INSTALLATION procedure.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PROGAMMABLE SWITCH (PSW)

ARMCAP

SWITCH PANEL

PROGAMMABLE SWITCH (PSW)

ARMCAP MOUNTING BRACKETS SIDE RAIL (REF) ARMCAP MOUNTING BRACKET MOUNTING BRACKETS (BASE RECEPTACLE) (REF) ARMCAP MOUNTING BRACKETS

WASHER (22 PLACES) SCREW (22 PLACES)

LEFT AFT ARMCAP SHOWN (LEFT FORWARD ARMCAP AND RIGHT SIDE TYPICAL) (PASSENGER TABLE REMOVED FOR CLARITY)

FL25B 985669AA.AI

Armcap - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 203

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TABLE LEAF (REF)

ARMCAP (REF)

1,2

3

4

5

1. SCREW (5 PLACES) 2. WASHER (5 PLACES) 3. TABLE FRAME 4. ARMCAP MOUNTING BRACKET (2 PLACES) 5. MOUNTING BRACKET (2 PLACES)

FL25B 985643AA.AI

Cabin Table - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 204

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 25-20-09

PASSENGER COMPARTMENT CARPET - MAINTENANCE PRACTICES Before carpet installation is carried out, it will be necessary to remove any furnishings/equipment to gain access to the carpet.

PASSENGER COMPARTMENT CARPET REMOVAL AND INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) All carpet (Ref. Figure 201 and Figure 202) installed in the cabin and aft compartment is secured in place by installation of 2-inch wide double faced tape (1, Chart 1, 25-00-00) to the back of each carpet segment. Carpet is secured to the risers in the aft center aisle by retainers and by adhesive (5, Chart 1, 25-00-00). Should it become necessary to install new tape or adhesive, all surfaces must be free of dust, oil, fingerprints or other contaminant soils. All metal surfaces should be cleaned with solvent (2, 3 or 4, Chart 1, 25-00-00) or an approved alkaline cleaning solution.

PASSENGER COMPARTMENT CARPET REMOVAL AND INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) All carpet (Ref. Figure 203) installed in the cabin and aft compartment is secured in place by installation of 2-inch wide double faced tape (8, Chart 1, 25-00-00) to the back of each carpet segment. Carpet is secured to the risers in the aft center aisle by retainers and by adhesive (5, Chart 1, 25-00-00). The carpet is also secured to the cabin center aisle risers by insertion underneath the front bezels of the floor lighting units (six places). Should it become necessary to install new tape or adhesive, all surfaces must be free of dust, oil, fingerprints or other contaminant soils. All metal surfaces should be cleaned with solvent (2, 3 or 4, Chart 1, 25-00-00) or an approved alkaline cleaning solution.

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350-312-007.AI

Carpet Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) Figure 201

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350-312-010.AI

Carpet Installation (FM-1 and After) Figure 202

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CARPET

CARPET

CARPET

CARPET

CARPET

A

CARPET

CARPET

CARPET

CARPET

CARPET

B

SPAR COVER

CARPET

NOTE: DASHED LINES SHOW LOCATION OF DOUBLE-TACK TAPE

CARPET

D

SPAR COVER (REF)

CARPET

C

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CARPET

CARPET

LIGHT INSTL AISLE AND SPAR (REF)

BIND CARPET TO AISLE ACCENT LIGHTING CHANNEL WITH ADHESIVE

CARPET CL INBD SEAT TRACK DETAIL FLOORBOARD (REF)

DETAIL

A

B

CUTOUT (4 PLACES)

CL INBD SEAT TRACK

CARPET

CL OUTBD SEAT TRACK

CL OUTBD SEAT TRACK

C

DETAIL LH SEAT TRACK SHOWN RH OPPOSITE

CL FWD SEAT TRACK FITTING

DETAIL

D

CL AFT SEAT TRACK FITTING

FL25B 985639AA.AI

Carpet Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 203

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 25-20-11

PASSENGER COMPARTMENT SIDEWALL PANEL - MAINTENANCE PRACTICES LOWER CABIN SIDEWALL CONSOLE PANEL, SCUFF PANEL, INNER PANEL AND UPHOLSTERED PANEL REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) NOTE: To avoid degrading the performance and reliability of the Ultra Quiet Sound Management System, contact Hawker Beechcraft Corporation Technical Support prior to any planned removal, installation and/or refurbishment of the airplane interior. a. Remove the cabin furnishings as required. b. Remove the screws from the angle at the base of the lower sidewall scuff panel (Ref. Figure 201). c.

Carefully pull the lower sidewall scuff panel away from the airplane structure while simultaneously sliding the panel downward until the upper edge is free from the extruded retainer. Remove the panel from the airplane.

d. Remove the cabin sidewall armrest (Ref. CABIN SIDEWALL ARMREST REMOVAL, 25-20-07). e. Remove the screws from the extruded upper caps at the top of the console panels. f.

Lift the console panel assemblies out and remove the panel assemblies from the airplane.

g. Lift the inner panels up and out of the lower extruded retainer and remove the panel from the airplane. h. Remove the screws from the upholstered panels at the cabin table locations, lift the panels up and out and remove the panels from the airplane.

LOWER CABIN SIDEWALL CONSOLE PANEL, SCUFF PANEL, INNER PANEL AND UPHOLSTERED PANEL INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) NOTE: To avoid degrading the performance and reliability of the Ultra Quiet Sound Management System, contact Hawker Beechcraft Corporation Technical Support prior to any planned removal, installation and/or refurbishment of the airplane interior. a. Position the upholstered panels at the cabin table locations and slide them into the extruded retainer. Align the screw holes in the upper portion of the panel and secure with the attaching screws (Ref. Figure 201). b. Position the console panel assemblies in their locations in the airplane and install the attaching screws. c.

Fit the extrusion on the sidewall armrests into the console cap retaining channels and secure the upright ends of the armrests with the attaching screws.

d. Place the lower sidewall scuff panel in position against the airplane structure and slide it upward into the extruded retainer, simultaneously pushing the panel outward into place. e. Align the screw holes in the angle at the base of the panel with the holes in the floor just outboard of the outboard seat track and install the attaching screws. f.

Install the cabin sidewall armrest (Ref. CABIN SIDEWALL ARMREST INSTALLATION, 25-20-07).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL g. Reinstall the cabin tables, partitions, cabinets, chairs, etc. brackets and secure the cap with the attaching screws. h. Fit the extrusion on the sidewall armrests into the console cap retaining channels and secure the upright ends of the armrests with the attaching screws. i.

Install cabin furnishings as required.

Lower Cabin Sidewall Console Panel, Scuff Panel, Inner Panel and Upholstered Panel Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 201

UPPER CABIN SIDEWALL WINDOW PANEL REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) NOTE: To avoid degrading the performance and reliability of the Ultra Quiet Sound Management System, contact Hawker Beechcraft Corporation Technical Support prior to any planned removal, installation and/or refurbishment of the airplane interior. a. Remove cabin furnishings as necessary. b. Carefully remove the color band insert trim panels. These panels are attached below the cabin windows with Dual-Lock (hook-loop) fasteners (Ref. Figure 202). c.

Remove the screws from the lower edge of the window panels, beneath the upper panel fabric.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL d. Above the windows, the upper sidewall panels are secured by seven spring-loaded locking pins (Ref. Figure 203) along each side of the headliner panel. Each locking pin must be released by depressing the spring inboard, working through the space between the upper sidewall panel and the headliner. A special tool to simplify this operation may be fabricated as shown (Ref. Figure 204). After each locking pin is released, the upper sidewall panel may be lowered at the upper edge and lifted from the channel below the windows and removed from the airplane.

UPPER CABIN SIDEWALL WINDOW PANEL INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Position the upper sidewall panel in the channel below the cabin windows (Ref. Figure 202). b. Align the screw holes in the panel and the channel. c.

Secure the upper edge of the panel in place with the seven spring-loaded locking pins (Ref. Figure 203). Use the tool fabricated as shown (Ref. Figure 204) to depress the locking pins as necessary for installation of the panel.

d. Install the attaching screws in the lower edge of the upper sidewall panel to secure the panel to the sidewall channel. e. Install the color band insert trim panels below the cabin windows.

Upper Sidewall Panel - Removal/Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 202

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Upper Sidewall Panel Locking Pin - Removal/Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 203

Locking Pin Depression Tool (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 204 Page 204 Feb 1/10

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CABIN WINDOW PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) CAUTION: Care must be taken not to scratch the window when removing the cabin window panel. a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove the cabin headliner closeout panels (Ref. CABIN HEADLINER CLOSEOUT PANEL REMOVAL, 25-20-13).

d. Remove the cabin headliner (Ref. CABIN HEADLINER REMOVAL, 25-20-13) to gain access to the fourteen screws (1) and washers (2) (Ref. Figure 205). e. Remove the fourteen screws (1) and washers (2) and slide the window panel upwards and inboard from behind the armcap. f.

Remove the window panel from the airplane.

CABIN WINDOW PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) CAUTION: Care must be taken not to scratch the window when installing the cabin window panel. a. Install the window panel in position. b. Slide the bottom of the window panel behind the armcap and align the screw holes. c.

Install the fourteen screws (1) and washers (2) to secure the top of the window panel (Ref. Figure 205).

d. Install the cabin headliner (Ref. CABIN HEADLINER INSTALLATION, 25-20-13). e. Install the cabin headliner closeout panels (Ref. CABIN HEADLINER CLOSEOUT PANEL INSTALLATION, 25-20-13). f.

Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

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CABIN LOWER SIDEWALL PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove all equipment and furnishings required to gain access to the lower sidewall panel.

d. Carefully pull the bottom of the lower sidewall panel inboard to release the two grabber latches. e. Carefully pull the top of the lower sidewall panel downwards and outboard to release the lower sidewall panel upper flange from the groove under the sideledge assembly. f.

Remove the lower sidewall panel from the airplane.

CABIN LOWER SIDEWALL PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the lower sidewall panel upper flange in the groove under the sideledge assembly. b. Carefully push the bottom of the lower side wall panel outboard until the two grabber latches engage. c.

Replace all equipment and furnishings removed.

d. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

LOWER CARPET PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove cabin furnishings as necessary to gain access to the lower carpet panel.

d. Remove the passenger table closeout panel (Ref. PASSENGER TABLE CLOSEOUT PANEL REMOVAL, 25-20-07). e. Perform the CABIN LOWER SIDEWALL PANEL REMOVAL procedure. f.

Remove the eleven screws (1) securing the lower carpet panel (3) to the rail assembly (2) (Ref. Figure 206). NOTE: The number of screws fitted can vary dependent on the interior option fitted.

g. Lift the lower carpet panel (3) out of the J channel (4). h. Electrically disconnect the AC outlet (5). i.

Remove the lower carpet panel (3) from the airplane.

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LOWER CARPET PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the lower carpet panel (3) in position on the J panel (4) (Ref. Figure 206). b. Electrically connect the AC outlet (5). c.

Install and tighten the eleven screws (1) to secure the lower carpet panel. NOTE: The number of screws fitted can vary dependent on the interior option fitted.

d. Perform the CABIN LOWER SIDEWALL PANEL INSTALLATION procedure. e. Install the passenger table closeout panel (Ref. PASSENGER TABLE CLOSEOUT PANEL INSTALLATION, 25-20-07). f.

Install any cabin furnishings removed for access.

g. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

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UPPER RAIL

2

1

UPPER RAIL

2

1

CABIN WINDOW PANEL

1 - SCREW (14 PLACES) 2 - WASHER (14 PLACES)

FL25B 985631AA.AI

Cabin Window Panel - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 205

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12345-

SCREW (11 PLACES) SIDE RAIL LOWER CARPET PANEL J CHANNEL AC OUTLET

5

2

1 1

4

3

5

LH SIDE SHOWN RH SIDE SIMILAR FL25B 985636AA.AI

Lower Carpet Panel - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 206

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EMERGENCY EXIT WINDOW PANEL REMOVAL a. Remove the emergency exit door assembly (Ref. EMERGENCY EXIT DOOR REMOVAL, 52-20-00). b. Using a thin 3/8 inch open-end wrench, turn (counterclockwise) each of the 6 bolts which secure the upholstery panel to the emergency exit door assembly until the panel is released from the door (Ref. Figure 207). NOTE: The two lower bolts have locknuts for securing adjustment of the panel. The locknuts must be loosened and held from turning until the bolts are released from the rivnuts in the door assembly. Do not remove the locknuts from the bolts. c.

Remove the panel assembly from the door assembly. Retain the spacers from each bolt for reinstallation.

EMERGENCY EXIT WINDOW PANEL INSTALLATION a. Position the upholstery panel assembly on each of the 6 bolts and start each bolt into the rivnuts in the door assembly (Ref. Figure 207). b. Using a thin open-end wrench, tighten the 4 upper bolts securely. The 2 lower bolts have locknuts to be used for adjustment of the upholstery panel to fair with cabin upholstery panels. Using the thin open-end wrench, tighten the 2 lower bolts as necessary for correct panel positioning, holding the locknut so it will not turn with the bolt. After adjustment of the panel, the locknut should be tightened against the clip. c.

Install the emergency exit assembly (Ref. EMERGENCY EXIT DOOR INSTALLATION, 52-20-00).

Emergency Exit Window Panel - Removal/Installation Figure 207

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

UPPER RIGHT VESTIBULE UPHOLSTERY PANEL REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Remove the right aft cabin partition (Ref. RIGHT AFT CABIN PARTITION REMOVAL, 25-20-03). b. Remove the side facing toilet (Ref. SIDE FACING TOILET ASSEMBLY REMOVAL (FL-1 AND AFTER), 38-30-00). c.

Remove the three screws at the lower edge of the panel assembly which secure the panel assembly the right sidewall, being careful to support the panel assembly as the screws are removed.

d. Lower the panel assembly, sliding it downward to release the upper mounting tabs and remove the panel assembly from the airplane.

UPPER RIGHT VESTIBULE UPHOLSTERY PANEL INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Position the panel assembly in the airplane, sliding it upward against the sidewall to engage the upper mounting tabs and align the three screw holes in the lower edge of the panel assembly with the corresponding holes in the airplane sidewall. b. Install the three screws in the lower edge of the panel assembly. c.

Reinstall the side facing toilet (Ref. SIDE FACING TOILET ASSEMBLY INSTALLATION (FL-1 AND AFTER), 38-30-00).

d. Install the right aft cabin partition (Ref. RIGHT AFT CABIN PARTITION INSTALLATION, 25-20-03).

VESTIBULE WINDOW PANEL AND LOWER SIDEWALL PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the three screws (1) and washers (2) from the bottom of the vestibule window panel (3) (Ref. Figure 208). b. Pull the bottom of the vestibule window panel (3) inboard for the cut-out to clear the solid state mini switch. CAUTION: Care must be taken not to scratch the window when removing the vestibule window panel. c.

Pull the vestibule window panel downwards to release it from the upper retaining bracket.

d. Remove the vestibule window panel (3) and lower sidewall panel (4) from the airplane.

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VESTIBULE WINDOW PANEL AND LOWER SIDEWALL PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the lower sidewall panel (4) and vestibule window panel (3) in position (Ref. Figure 208). b. Locate the vestibule window panel (3) in the upper retaining bracket. c.

Push the bottom of the vestibule window panel (3) outboard making sure the cut-out clears the solid state mini switch.

d. Install the three screws (1) and washers (2) to secure the vestibule window panel and sidewall panel in position.

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7

3

6

5

1 2

4 1234567-

SCREW (3 PLACES) WASHER (3 PLACES) VESTIBULE WINDOW PANEL VESTIBULE LOWER PANEL LOWER AFT SIDE RAIL UPPER AFT SIDE RAIL RETAINING BRACKETS

LAVATORY, PARTITION AND VANITY UNIT REMOVED FOR CLARITY

FM25B 985641AA.AI

Vestibule Window Panel and Lower Sidewall Panel - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 208

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AFT COMPARTMENT UPPER SIDEWALL PANEL REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Remove the color band trim panels to gain access to the upper sidewall panel attaching screws and remove the screws. The color band panels are attached below the window with hook and loop fasteners (Ref. Figure 209). b. Carefully pull the upper sidewall panel and window assembly away from the airplane sidewall, slide the upper attaching tabs from their respective retainer clips and remove the panel assembly from the airplane.

AFT COMPARTMENT UPPER SIDEWALL PANEL INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Position the upper sidewall panel and window assembly in the installed position and slide the upper attaching tabs into their respective retainers (Ref. Figure 209). b. Install the screws in the lower edge of the upper sidewall panel to secure it in place. c.

Install the color band trim panel below the baggage compartment window.

Aft Compartment Upper Sidewall Panel - Removal/Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 209 Page 214 Feb 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AFT BAGGAGE COMPARTMENT WINDOW PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the decorative panel. Pull the panel to release the hook and loop fasteners. b. Perform the AFT COMPARTMENT LOWER SIDEWALL PANEL REMOVAL procedure. c.

Perform the COAT ROD REMOVAL procedure.

d. Remove the four screws (2) securing the bottom of the window panel (Ref. Figure 210). CAUTION: Care must be taken not to scratch the window when removing the window panel. NOTE: If the optional vanity unit is fitted there are only three screws securing the bottom of the window panel. e. Pull the bottom of the window panel inboard to release the panel from the window. f.

Pull the window panel downwards to release it from the upper retaining brackets.

g. Remove the window panel from the airplane.

AFT BAGGAGE COMPARTMENT WINDOW PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the window panel in position. CAUTION: Care must be taken not to scratch the window when installing the window panel. b. Locate the window panel in the upper retaining bracket. c.

Install the four screws (2) to secure the window panel in position (Ref. Figure 210). NOTE: If the optional vanity unit is fitted there are only three screws securing the bottom of the window panel.

d. Perform the COAT ROD INSTALLATION procedure. e. Perform the AFT COMPARTMENT LOWER SIDEWALL PANEL INSTALLATION procedure. f.

Attach the decorative panel. Align the panel and press to engage the hook and loop fasteners.

AFT COMPARTMENT LOWER SIDEWALL PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the decorative panel. Pull the panel to release the hook and loop fasteners. b. Remove the fire extinguisher from its mounting bracket (left side only). c.

Remove the seven screws (1) securing the lower sidewall panel (Ref. Figure 210).

d. Remove the lower sidewall panel from the airplane.

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AFT COMPARTMENT LOWER SIDEWALL PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the lower sidewall panel in position. b. Install the seven screws (1) to secure the lower sidewall panel (Ref. Figure 210). c.

Install the fire extinguisher in the mounting bracket (left side only).

d. Attach the decorative panel. Align the panel and press to engage the hook and loop fasteners.

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COAT ROD CUTOUT

1 - SCREW (7 PLACES) 2 - SCREW (4 PLACES) 3 - DECORATIVE PANEL

HOOK AND LOOP

3

AFT COMPARTMENT WINDOW PANEL HOOK AND LOOP

A

DETAIL

2

1

LH AFT CABIN RAIL ASSY

FIRE EXTIGUISHER CUTOUT

1

A 2 1 3

AFT COMPARTMENT LOWER SIDEWALL PANEL

FL25B 985632AA.AI

1

Aft Compartment Window Panel and Lower Side Wall Panel - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 210

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AFT BULKHEAD UPHOLSTERY PANEL REMOVAL NOTE: The color band insert trim panels and large upholstered half-moon panel are attached with hook and loop fasteners. These panels should be removed slowly and carefully to avoid damaging them. a. Remove the color band insert trim panels (Ref. Figure 211). b. Remove the upholstered half-moon panel. c.

Remove the four screws which secure the upper upholstery trim panel to the aft bulkhead and remove the panel.

d. Carefully lift the edge of the carpet from the bottom edge of the lower carpeted panel, remove the five screws from the flange and remove the carpeted panel from the airplane. e. Remove the three screws which secure each of the two outer trim panels to the aft bulkhead and remove the panels.

AFT BULKHEAD UPHOLSTERY PANEL INSTALLATION a. Position the two upper outer trim panels in place and install them with three screws in each panel (Ref. Figure 211). b. Install the lower carpeted panel in the airplane and secure it to the floor with five screws through the flange at the bottom edge. c.

Install the upper upholstery trim panel to the aft bulkhead with four screws.

d. Install the upholstered half-moon panel and the color band insert trim panels.

ENTRY DOOR CLOSEOUT PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Gain access to the entry door closeout panel (1) (Ref. Figure 212). b. Remove the six screws (6) from the footman loops (5) and remove the footman loops. c.

Unfasten the hook and loop fastening (2) at the top of the entry door closeout panel (1) and slide the entry door closeout panel from underneath the vestibule headliner.

d. Remove the entry door closeout panel from the airplane.

ENTRY DOOR CLOSEOUT PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the entry door closeout panel (1) (Ref. Figure 212) in position and slide the upper edge underneath the vestibule headliner. b. Fasten the hook and loop fastener at the top of the entry door closeout panel. c.

Install the three footman loops (5) in position and secure using the six screws (6).

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Aft Bulkhead Upholstery Panel - Removal/ Installation Figure 211

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A

1

2

3

6 5

FORWARD

4

1. ENTRY DOOR CLOSEOUT PANEL 2. HOOK AND LOOP FASTENING 3. STRUCTURE (REF) 4. FLOOR (REF) 5. FOOTMAN LOOP (3 PLACES) 6. SCREW (6 PLACES)

FS 339.98 REF

VIEW

A-A

(VIEW LOOKING OUTBOARD)

FS 312.50 REF

FL25B 985680AA.AI

Entry Door Closeout Panel - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 212

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COAT ROD REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the four screws (1) securing the coat rod hinge brackets (5), through the housing (4), to the mounting brackets (2) and (6) (Ref. Figure 213). b. Remove the coat rod assembly (7). c.

Carefully remove the coat rod housing assembly (4) and shim (3) by pulling downward and inboard. NOTE: Care must be taken not to drop the shim (3) mounted between the housing (4) and the aft mounting plate (2) behind the panel when removing the housing.

d. Remove the coat rod assembly from the airplane.

COAT ROD INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Carefully install the coat rod assembly housing (4) and shim (3) in position. Make sure housing orientation is correct (Ref. Figure 213). NOTE: Care must be taken not to drop the shim (3) behind the panel when installing the housing. b. Align the coat rod assembly (7) with the holes in the housing. c.

Install the four screws (1) and secure the coat rod hinge brackets (5), through the housing (4), to the mounting brackets (2) and (6).

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WINDOW PANEL (REF)

A A 2 6

3

5

4

1 1234567-

SCREW MOUNTING PLATE (AFT) SHIM HOUSING HINGE BRACKET MOUNTING BRACKET (FWD) COAT ROD

5 7

A

DETAIL LEFT SIDE SHOWN RIGHT SIDE TYPICAL

1

FL25B 985633AA.AI

Coat Rod - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 213 Page 222 Feb 1/10

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PASSENGER COMPARTMENT HEADLINER PANEL - MAINTENANCE PRACTICES HEADLINER PANEL REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) NOTE: To avoid degrading the performance and reliability of the Ultra Quiet Sound Management System, contact Hawker Beechcraft Corporation Technical Support prior to any planned removal, installation and/or refurbishment of the airplane interior. Most components in the headliner are installed to facilitate servicing without removing the headliner panel. However, if the panel must be removed, it may be accomplished as follows: a. Remove the left and right upper sidewall panels (Ref. UPPER CABIN SIDEWALL WINDOW PANEL REMOVAL, 25-20-11). b. Support the headliner panel and remove the attaching screws from the outer edges of the panel. Gradually lower the panel and disconnect wiring and oxygen lines from the panel. c.

After all electrical and plumbing components, etc. are disconnected from the headliner panel, it may be lowered and removed from the airplane.

HEADLINER PANEL INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) NOTE: To avoid degrading the performance and reliability of the Ultra Quiet Sound Management System, contact Hawker Beechcraft Corporation Technical Support prior to any planned removal, installation and/or refurbishment of the airplane interior. a. Position the headliner panel in the airplane and support it as necessary to gain access behind the panel. Connect all wiring, plumbing, etc., to the panel. b. Secure the panel in place with the attaching screws along the outer edges. c.

Install the upper sidewall panels (Ref. UPPER CABIN SIDEWALL WINDOW PANEL INSTALLATION, 25-20-11).

CABIN HEADLINER REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Perform the CABIN HEADLINER CLOSEOUT PANEL REMOVAL procedure.

d. Remove the five oxygen box covers (1) from the headliner (4) by releasing them from the hook and loop fasteners (5) (Ref. Figure 201).

A27

25-20-13

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL e. Remove the twenty screws (2) and washers (3) securing the headliner (4) to the oxygen box brackets (6). f.

Lower the headliner (4) until it is restrained by the four lanyards.

g. Electrically disconnect the headliner. h. Disconnect the plumbing from the eight gasper assemblies. i.

Disconnect the four lanyards from the headliner.

j.

Remove the headliner from the airplane.

CABIN HEADLINER INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Position the headliner in the passenger cabin and attach the four lanyards. b. Connect the plumbing to the eight gasper assemblies. c.

Electrically connect the headliner.

d. Install the headliner (4) in position (Ref. Figure 201). e. Install the twenty screws (2) and washers (3) to secure the headliner (4). f.

Install the five oxygen box covers (1) by attaching the hook and loop fasteners (5).

g. Perform the CABIN HEADLINER CLOSEOUT PANEL INSTALLATION procedure. h. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

CABIN HEADLINER CLOSEOUT PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) NOTE: Removal procedure is typical for both forward and aft closeout panels. a. Remove three screws and nuts securing the closeout panel to the air conditioning bracket. b. Remove the closeout panel.

CABIN HEADLINER CLOSEOUT PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) NOTE: Installation procedure is typical for both forward and aft closeout panels. a. Install the closeout panel in position. b. Install the three screws and nuts to secure the closeout panel to the air conditioning bracket.

Page 202 Feb 1/10

25-20-13

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

123456-

OXYGEN BOX COVER SCREW (20 PLACES) WASHER (20 PLACES) HEADLINER HOOK AND LOOP FASTENERS (20 PLACES) OXYGEN BOX BRACKET

A

6

6 5

4

3

3

2

2

1 DETAIL

A

FL25B 985640AA.AI

Cabin Headliner - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 201

A27

25-20-13

Page 203 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AFT COMPARTMENT HEADLINER PANEL REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Remove the left and right aft compartment upper sidewall panels. b. Support the headliner panel and remove the attaching screws from the outer edges of the panel. Gradually lower the panel and disconnect wiring, air ducts and oxygen lines from the panel. c.

After all electrical and plumbing components, etc. are disconnected, the headliner panel may be lowered and removed from the airplane.

AFT COMPARTMENT HEADLINER PANEL INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Position the headliner panel in the airplane and support it as necessary to connect all wiring, plumbing, etc. to the panel. b. Secure the panel in place with the attaching screws along the outer edges. c.

Reinstall the upper sidewall panels.

VESTIBULE AND AFT COMPARTMENT HEADLINER REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Perform the CABIN HEADLINER CLOSEOUT PANEL REMOVAL procedure for the aft headliner closeout panel.

d. Remove the four screws and washers securing the headliner to the bulkhead panel. e. Remove the three screws securing the headliner to the air conditioning bracket. f.

Lower the headliner panel to gain access to the electrical connections, the oxygen boxes and the gasper plumbing.

g. Disconnect the plumbing to the oxygen boxes. h. Electrically disconnect the headliner. i.

Disconnect the plumbing to the gasper assembley.

j.

Remove the headliner from the airplane,

Page 204 Feb 1/10

25-20-13

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

VESTIBULE AND AFT COMPARTMENT HEADLINER INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Position the headliner in the vestibule and aft compartment to allow connection of the oxygen plumbing. b. Connect the plumbing to the gasper assembley. c.

Connect the plumbing to the oxygen boxes.

d. Electrically connect the headliner. e. Raise the headliner in position and install the three screws and washers to secure the headliner to the air conditioning bracket. f.

Install the four screws and washers to secure the headliner to the aft bulkhead panel.

g. Perform the CABIN HEADLINER CLOSEOUT PANEL INSTALLATION procedure for the aft headliner closeout panel. h. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

A27

25-20-13

Page 205 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 000 25-30-00

BUFFET/GALLEY - DESCRIPTION AND OPERATION REFRESHMENT CABINET (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) The refreshment cabinet is located at the forward left side of the passenger compartment. The refreshment cabinet consists of six drawers, four of which are illuminated and have optional inserts (Ref. Figure 1) as follows: a. General Storage •

Wine glass insert (standard) (1).

•

Water bottle insert (optional) (2).

•

Mini liquor bottle insert (optional) (3).

•

Mini liquor/water bottle insert (optional) (4).

b. Hot/Cold Liquid Container/Server, Cups, Condiments with Slide Out Beverage Holder. c.

Pull-Out Work Surface.

d. General Storage •

Mini liquor bottle/miscellaneous storage insert (standard) (5).

•

Ice chest insert (optional) (6).

•

Wine bottle insert (optional) (7).

•

Ice drain tray insert (optional) (8).

e. General Storage

f.

•

Dual wine bottle insert (standard) (9).

•

Ice drain tray insert (optional) (10).

•

Ice chest insert (optional) (11).

General Storage •

A27

Trash storage (standard) (12).

25-30-00

Page 1 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

1

a

2 3 4

b c d 6

5

7

8

e f 9 10 11 12

FL25B 985589AA.AI

Refreshment Cabinet (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 1

Page 2 Feb 1/10

25-30-00

A27

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL 200200200

BUFFET/GALLEY - MAINTENANCE PRACTICES REFRESHMENT CABINET REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) NOTE: Nearly all of the various floor mounted refreshment cabinets, regardless of size or location are attached to locator plates which are attached to the floor mounted seat tracks. Upright cabinets are also secured at the top by use of a pin assembly through the upper cabinet and the cabin headliner (Ref. Figure 201). a. Remove the bottom drawer of the cabinet. b. Remove the screws and the countersunk washers from each of the four corner locations in the base of the cabinet. c.

If the cabinet is an upright cabinet: 1. Gain access to the upper cabinet interior. 2. Remove the four screws which secure the pin assembly to the upper cabinet and remove the pin assembly.

d. Remove the cabinet assembly from the airplane. e. Remove the four spacers and plate assemblies from the seat tracks.

REFRESHMENT CABINET INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED; FM-1 AND AFTER) a. Position the four plate assemblies and spacers in their respective locations (Ref. Figure 201) in the seat track to align with the holes in the base of the cabinet assembly. b. Remove the bottom drawer of the cabinet assembly. c.

Position the cabinet assembly over the four spacers in the seat tracks and loosely install the four attaching screws and countersunk in the base of the cabinet.

d.

If the cabinet is an upright cabinet: 1. Fit the T-shaped pin assembly through the hole in the upper cabinet assembly and into the hole in the cabin headliner. 2. Install and tighten the four screws to secure the pin assembly to the inner cabinet.

e. Tighten the four screws in the corners of the base of the cabinet. f.

Reinstall the drawers which were removed for access to the inside of the cabinet.

A27

25-30-00

Page 201 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Refreshment Cabinet Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed; FM-1 and After) Figure 201

Page 202 Feb 1/10

25-30-00

A27

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

REFRESHMENT CABINET REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect battery per BATTERY POWER - DISCONNECT procedure (Ref. 24-30-00, 301) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Disconnect the electrical connector for the internal lights.

d. Remove the bottom drawer of the cabinet (Ref. Figure 202). e. Remove the four screws (2) and washers (3) which secure the base of the cabinet to the isolator plates (4). f.

Remove the header panel (5) to gain access to the upper cabinet interior.

g. Disengage quick release pin (1) which secures upper cabinet to upper rail assembly. h. Remove the refreshment cabinet.

REFRESHMENT CABINET INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Position cabinet on the isolator plates (4) (Ref. Figure 202). b. Align and engage the quick release pin (1) to secure the upper cabinet to the upper rail assembly. c.

Install the header panel (5).

d. Install the four screws (2) and washers (3) to secure the base of the cabinet to the isolator plates (4). e. Install bottom drawer of the cabinet. f.

Connect the electrical connection for the internal lights.

g. Connect the battery per BATTERY POWER - CONNECT procedure (Ref. 24-30-00, 301) and remove the caution tag.

ISOLATOR PLATE REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Perform CABINET ISOLATOR PLATE REMOVAL procedure (Ref. 25-20-00, 201).

ISOLATOR PLATE INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Perform CABINET ISOLATOR PLATE INSTALLATION procedure (Ref. 25-20-00, 201).

A27

25-30-00

Page 203 Feb 1/10

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

1

5

12345-

QUICK RELEASE PIN SCREW (4 PLACES) WASHER (4 PLACES) ISOLATOR PLATE (2 PLACES) HEADER PANEL

2 3

4

FL25B 985630AA.AI

Refreshment Cabinet Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 202

Page 204 Feb 1/10

25-30-00

A27

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EM ERGENCY-DESCRIPTION AND OPERATION

EMERGENCY LOCA TOR TRANSMITTER airplane is equipped with an emergency locator transmitter (ELT) to assist in tracking and recovery of the airplane and crew in the event of a crash or emergency landing. The Dorne and Margolin, DM ELT 8.1 and the Narco ELT 10 transmitters were originally approved for factory installation on this airplane; however, these units are replaced with the Artex ELT 110-4, effective on FL-11, FM-1 and after, or may be replaced by installation of Kit No.

The

101-3127-1S.

fuselage at a point approximately 4 feet aft of the aft pressure bulkhead. airplane, an access hole with a spring-loaded cover is located in the airplane skin adjacent to the transmitter, providing access to a remote switch. An antenna for the ELT is mounted on top of the fuselage under the vertical stabilizer at a point approximately 7 inches aft of the ELT. The ELT is mounted

on

the

right

For manual activation of the ELT

The

side of the on

output frequencies of the ELT

The Narco ELT has Dorne and

Margolin

activate the ELT for

an

the

are

121.5 and 243.0

ON-OFF-ARM switch located

MHz, simultaneously. Range is approximately line of sight. on

the transmitter to control the

operation

of the unit. The

ELT switch is marked AUTO-OFF-ON, and the Artex ELT switch is marked TEST-ARM-ON. To

testing,

switch the Dorne

Margolin

or

the Narco units to ON. The Artex unit has

a

TEST

position

for this purpose. To set the units for automatic operation on impact, switch the Narco or the Artex units to ARM or the Dorne and Margolin unit to AUTO. A reset switch, located on the forward end of the Narco transmitter, resets the transmitter to the ARM position in the event the impact switch is accidentally triggered. The Dorne and Margolin unit is reset

by switching

to OFF and back to AUTO. To reset the Artex

unit,

set the switch to

ON, wait

a

second and

switch to ARMED.

adjacent to the ELT has a placard mounted on the exterior fuselage skin around the springto identify the switch positions. The Dome and Margolin placard indicates TEST-AUTO-XMIT, the Narco ELT placard indicates TEST-ARM-XMIT, and the Artex ELT placard indicates ARMED/RESET-ON. To turn the Narco ELT on for automatic actuation on impact, set the switch to the ARM position. To arm the Artex ELT, set the switch to the ARMED/RESET position. The Dorne and Margolin unit is armed by switching to AUTO. The remote switch loaded

nz4

access cover

25-60-00

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRACTICES

EMERGENCY-MAINTENANCE

EMERGENCY LOCA TOR TRANSMITTER MAINTENANCE Maintenance

on

the ELT is

battery replacement:

a.

Visual

shows

b.

Elapsed replacement

inspection

limited to

normally

which warrant

signs

of

date noted

leakage, the

on

replacing

corrosion

battery

battery is the length of time continuously operate the ELT for 48 hours.

Afterany emergency

d.

After

e.

After operation of unknown duration.

f.

If the transmitter is stored in be

one

The information

placarded

on

battery pack. The following

is

a

list of various conditions

insecure leads.

(this

date represents 50% of the useful life of the

which the

battery

may be stored without

losing

its

battery). ability to

use.

cumulative hour of

replaced

or

case

NOTE: The useful life of the

c.

the

use.

an area

where the temperature is

normally above

38" C

(100" Fl,

the

battery

should

every 12 months. on

the

useful

battery

life and

replacement

is included in the data furnished with each ELT, and is

usually

battery.

accomplished on the ELTs must be done by authorized avionics facilities tin manufacturer). It is also a requirement in most cases that specific antennas be used with and battery packs corresponding ELTs. The ELT manufacturer’s instructions must be whenever adhered and to consulted any maintenance is to be performed on the ELT.

NOTE: ELT manufacturers

require

that all work

most instances, the

BA TTER Y PA CK REPLA CEMENT NARCO ELT BATTERY a.

b.

Place the ON-OFF-ARM switch

the ELT in the OFF

Unlatch the

d.

Extend the

mounting strap

portable

wiring,

if

installed, from the terminals

replacement to Remove the four

battery pack

Remove the old

and

remove

the ELT from the

airplane.

antenna.

extending the portable antenna and handling the control head during battery avoid damage to the antenna or the plastic tab on the antenna.

CAUTION: Exercise extreme

the

position.

the ELT.

c.

f.

on

Disconnect the antenna cable from the ELT. Disconnect the remote switch on

e.

(Ref. Figure 201)

screws case

care

in

attaching

the control head to the

apart. The battery connection leads

battery pack by disconnecting

the

battery pack casing and slide the are approximately 3 inches long.

battery pack terminals from

control head and

the bottom of the transmitter PC

board.

g.

Discardtheold

battery.

WARNING: Do not discard the

battery

in fire.

25-60-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Connect the

h.

NOTE: Do not

battery pack

new

remove

terminals to the bottom of the transmitter PC board.

the sealant

the inside

on

lip

of the

battery pack

or a

watertight

seal will not be made when

the unit is reassembled. i.

Using

a

which is

stick, apply

joined

a

bead of sealant

with the

NOTE: This sealant

battery

provides

a

watertight

Slide the control head into the

j.

screws.

Wipe

NOTE: If the four

Stow the

k.

excess

any

screw

portable

case

(supplied with each battery pack) during assembly.

of the control head

careful not to

battery pack (being

pinch

the

wires)

and install the four

attaching

sealant from the outside of the unit.

battery

180" and reinsert.

antenna. care

in order to avoid

airplane

damage

and latch the

to the antenna

I.

Install the transmitter in the

m.

Connect the fixed antenna cable and connect the remote switch

plastic

Press the RESET button and

o.

A

the

plastic

tab

on

the antenna.

wiring (if installed) to the terminals on the ELT. portable antenna contact and the portable antenna.

the ON-OFF-ARM switch

place

or

mounting strap.

separator is inserted between the

n.

new

area

seal when the unit is assembled.

holes do not line up, rotate the

CAUTION: Exercise extreme

Ensure that the

around the

on

the ELT in the ARM

battery pack replacement date must be marked on the outside of the battery pack as defined by the battery pack manufacturer.

position.

transmitter. The date is 50% of the

useful life of the

DORNE AND MARGOLIN ELT BATTERY Instruction for

battery replacement

on

Dorne and

Margolin

ELTs

are

included with the

replacement battery pack.

ARTEX ELT BATTERY a.

Remove the ELT from the

b.

Remove the four

c.

Disconnect the

d.

Plug

e.

Install the

f.

Replace

the

new

screws

mounting

holding

battery pack

battery pack

cover

the lid of the ELT

screws

cover

connector into the ELT and

and

plate and detach the lid.

connector within the ELT and

assembly, making

the four

bracket.

certain that all

tighten

them

remove

place

gaskets

the

are

the

battery pack.

battery

into the unit.

properly aligned.

equally.

TESTING THE EMERGENCY LOCA TOR TRANSMITTER performed following maintenance or repairs of ELTs, other than battery pack replacement, operational capabilities. Testing the ELT, if improperly done, could trigger false alerts and create frequency jamming and may interfere with the reception of a bonafide emergency transmission. Federal Communications Commissions regulations require that this testing be performed in a screened or shielded test room, or in a test enclosure that will hold the self-contained ELT unit with the antenna fully extended. Generally,

tests will be

to determine their

May

1/0825-60-00

P~Z4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION: The EL T switch should not be turned 50-0hm

of installed ELTs may be

Operational testing

NOTE: Tests should not be

modulating

on

unless the ELT is connected to its associated antenna

or

to a

dummy load.

longer than

the carrier with

an

accomplished

as

follows:

three audio sweeps. One audio sweep may be defined as amplitude frequency sweeping downward over a range of not less than 700Hz,

audio

within the range of 1000 to 300Hz and a sweep repetition rate between two and four Hz. Tests should be conducted only in the first five minutes of any hour. If the operation test must be made at a time not included within the first five minutes after the hour, the tests should be coordinated with the nearest FAA tower

flight a.

Turn COM-1 to ON and tune 121.5 MHz.

b.

Turn COM-1 to the SPEAKER

c.

Turn the ELT ON-OFF-ARM, AUTO-OFF-ON TEST-ARM-ON switch

position.

las applicable) to ON and monitor the ELT signal. On airplanes equipped with a remote switch (located in the aft fuselage on the right side or on the instrument panel), the switch may be momentarily flipped to the XMIT, TEST or ON las applicable) position and the ELT signal monitored.

NOTE: If there is is

d.

or

service station.

no

audible

signal,

the

battery

so

probably disconnected

or

dead, assuming that the VHF transceiver

operational.

Place the ON-OFF-ARM, AUTO-OFF-ON ARM

is

las applicable) position.

or

TEST-ARM-ON switch

las applicable)

on

the ELT to the OFF

or

being utilized to test the unit, the switch should be released applicable) position. The audio signal should disappear

If the remote switch is

it will return to the ARM, AUTO

or

ARMED

las

completely. e.

Place the switch

NOTE: If f.

a

signal

is

on

the ELT to the ARM

or

AUTO

position.

There should be

no

audio

signal present.

heard, the impact switch has probably been activated and should be

Firmly press the reset switch COM-1.

on

the front of the ELT and listen to make

sure

the audio

reset.

signal disappears from

25-60-00Mayl/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTACT SEPARATOR

PORTABLE ANTENNA

PORTABLE

CONTACT

ANTENNA

FINGER

CONTACT FINGER PORTABLE ANTENNA BLADE NOT MAKING CONTACT FIXED ANTENNA

CABLE CONNECTOR TACT

I

8

sEPARATOR

1

-COAX CABLE TO AIRPLANE TO REMOTE

FIXED ANTENNA

SWITCH HANDLE

PORTABLE ANTENNA

RESET

STOP PIN

SWITCH

STD-356-4a

Narco

May 1/08Page

204

25-60-00

Emergency Locator Transmitter (ELT) Figure 201

A24

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 25-80-00

PASSENGER COMPARTMENT ACOUSTICS - DESCRIPTION AND OPERATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) SPECIAL TOOLS AND RECOMMENDED MATERIALS The special tools and recommended materials listed in Chart 1 and Chart 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically prescribed by Hawker Beechcraft Corporation. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

Chart 1 Special Tools and Equipment TOOL NAME

PART No.

1. Cheese Cloth

SUPPLIER

USE

Obtain Locally

Adhesive residue removal

Chart 2 Recommended Materials MATERIAL

SPECIFICATION

PRODUCT

1. Solvent

Isopropyl Alcohol

2. Tape

OT-16A (Replaces OT-6A)

SUPPLIER Obtain Locally Orcon Aerospace 1570 Atlantic Street Union City CA, 94587

3. Tape

(3 x 0.002 inch)

Aluminum Foil

Owens Corning Fiberglas Corporation Fiberglas Tower Toledo, OH 43604

4. Tape

Double Sided

Type 597

Intertape Polymer Group 3647 Cortez Road West Bradenton, FL 34210

A27

25-80-00

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PASSENGER COMPARTMENT ACOUSTICS Acoustic protection and vibration protection for the passenger cabin consists of the following components: •

Skin damping panels (Ref. Chapter 53-11-00).

•

Tuned vibration absorbers (Ref. Chapter 53-11-00).

•

Dynamic vibration absorbers (Ref. Chapter 53-11-00).

•

Sound deadening sealant (Ref. Chapter 53-11-00).

•

Between frame insulation blankets.

•

Over frame insulation blankets.

•

Mass loaded vinyl layer.

BETWEEN FRAME INSULATION BLANKETS Between various frames of the fuselage, insulation blankets are installed using double sided tape to prevent sagging (Ref. Figure 1, Sheet 1). The insulation blankets are installed over the skin damping panels, tuned vibration absorbers and dynamic vibration absorbers.

OVER FRAME INSULATION BLANKETS Over the frames between FS 143.00 and FS 371.25, insulation bags are installed (Ref. Figure 1, Sheet 2). The insulation bags are installed between the fuselage frames and the cabin/vestibule headliner and secured using ball strip and retaining disc type fasteners.

MASS LOADED VINYL LAYER A mass loaded vinyl layer is installed between the cabin sidewall trim panels and cabin frames from FS148.00 to FS 202.40. (Ref. Figure 1, Sheet 1). The mass loaded vinyl is secured to the fuselage using aluminum foil tape.

Page 2 Feb 1/10

25-80-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FS FS FS FS FS FS 299.75 289.875 280.00 270.125 260.250 250.650 REF REF REF REF REF REF

2 2

2

2 2

2

2

2

2

2

2

2

2

2

2

2

FS 241.125 REF

2

FS 232.650 REF

2

FS FS 221.375 211.90 REF REF

2

FS 201.775 REF

2

2

2

2

FS 190.65 REF

FS 179.525 REF

2 2

2

2

FS 168.75 REF

FS FS 148.90 143.00 REF REF

2

2

2

2

2

2

2

2

2

2 2

2 2

2 2

2 2

2 2

2

2

FS 132.80 REF

FS 122.00 REF

B

A

A

C

C

1

2

2

2 2

B

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2 2 FS 381.75 REF

FS 371.25 REF

FS 360.75 REF

FS 350.00 REF

FS FS 339.25 FS FS FS REF FS 325.875 312.50 REF 299.75 290.25 332.562 FS REF FS REF REF REF 319.118 307.52 REF REF

FS 280.75 REF

FS FS FS FS 270.50 261.00 251.200 241.40 REF REF REF REF

This Page Intentionally Left Blank VIEW

1

FS 122.00 REF

FS 132.80 REF

FS FS 143.00 148.90 REF REF

FS 168.75 REF

FS 179.525 REF

2

2

2

2

2

2

2

2

2

2 2

FS 190.65 REF

2 2

2

2

FS 201.775 REF

2

2

2

FS 202.40 REF

FS 191.00 REF

FS 179.525 REF

FS 168.75 REF

FS FS FS FS FS FS FS FS 94.00 158.00 150.00 143.00 134.00 125.00 116.00 107.00 REF REF REF REF REF FS REF REF REF 100.50 REF

FS 84.00 REF

1

FS 241.125 FS FS FS FS FS FS FS REF 232.650 250.650 260.250 270.125 280.00 289.875 299.75 REF REF REF REF REF REF REF

2

2

2 2

2 2

FS FS 221.40 211.90 REF REF

A-A

FS FS 211.90 221.375 REF REF

2

FS 231.40 REF

2

2

2 2

2

2

2 2

2

2

2 2

2

2

2

2

2

2

2

2

2

2

2

2

2

2 1. MASS LOADED VINYL PANEL 2. BETWEEN FRAME INSULATION BLANKET

2

2

2 2 2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2 2

2

2

2

2

2

FS 84.00 REF

FS FS FS FS FS FS FS FS 94.00 107.00 116.00 125.00 134.00 143.00 150.00 158.00 REF REF REF FS REF REF REF REF REF 100.50 REF

FS 168.75 REF

FS 179.525 REF

1

FS 191.00 REF

FS 202.40 REF

FS FS 211.90 221.40 REF REF

VIEW

FS 231.40 REF

B-B

FS FS FS FS 241.40 251.200 261.00 270.50 REF REF REF REF

FS 280.75 REF

FS 290.25 REF

FS FS 339.25 FS 325.875 FS REF 312.50 REF FS 299.75 332.562 REF FS REF FS REF 307.52 319.118 REF REF

FS 350.00 REF

FS 360.75 REF

FS 371.25 REF

FS 381.75 REF

FL25B 985696AA.AI

Passenger Compartment Acoustic Protection Figure 1, (Sheet 1 of 2)

A27

25-80-00

Page 3 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1

2

2

2 2

4

2

2

2

STGR 5L

2

STGR 4L STGR 3L

2 2

2 2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

2

STGR 2L

2

REF 0.00 STGR 1 BL STGR 2R

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3

3 STGR 3R STGR 4R STGR 5R

2

FS 122.00 REF

FS 132.80 REF

FS FS 143.00 148.90 REF REF

FS 158.00 REF

FS 168.75 REF

FS 179.525 REF

FS 190.65 REF

FS 201.775 REF

FS 211.90 REF

FS 221.375 REF

FS 232.65 REF

FS 241.125 REF

FS 250.65 REF

FS 260.25 REF

FS 270.125 REF

1

VIEW

FS 280.00 REF

FS 289.875 REF

FS 299.75 REF

FS 307.52 REF

FS 312.50 REF

2

2

2

FS 319.188 REF

FS FS 332.562 339.25 REF REF

FS 350.00 REF

FS 360.75 REF

FS 371.25 REF

FS 381.75 REF

FS 325.875 REF

C-C 1. 2. 3. 4.

MASS LOADED VINYL PANEL BETWEEN FRAME INSULATION BLANKET OVER FRAME INSULATION BLANKET BALL STRIP AND DISC-INSULATION BLANKET RETAINER (59 PLACES)

FL25B 985697AA.AI

Passenger Compartment Acoustic Protection Figure 1, (Sheet 2 of 2) Page 4 Feb 1/10

25-80-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

PASSENGER COMPARTMENT ACOUSTICS - MAINTENANCE PRACTICES (FL-601, FL672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) MASS LOADED VINYL REMOVAL a. Remove cabin furnishings and trim panels as necessary to gain access (Ref. Chapter 25-20-00). b. Remove the aluminum foil tape (3, Chart 2, 25-80-00). c.

Remove the mass loaded vinyl sheet from the airplane.

MASS LOADED VINYL INSTALLATION a. Clean the area where aluminum foil tape is to be applied with solvent (1, Chart 2, 25-80-00) and a cheese cloth (1, Chart 1, 25-80-00). Allow the area to dry. b. Install the mass loaded vinyl panel in position and secure using aluminum foil tape (3, Chart 2, 25-80-00). c.

Install cabin furnishings removed for access (Ref. Chapter 25-20-00).

BETWEEN FRAME INSULATION BLANKET REMOVAL a. Remove cabin furnishings and trim panels as necessary to gain access (Ref. Chapter 25-20-00). b. Perform the MASS LOADED VINYL REMOVAL procedure, as necessary. c.

Remove the insulation blanket and any residual double sided tape and adhesive as necessary (Ref. Figure 201).

BETWEEN FRAME INSULATION BLANKET INSTALLATION a. Clean the area with solvent (1, Chart 2, 25-80-00) and a cheese cloth (1, Chart 1, 25-80-00). Allow the area to dry. b. Install the insulation blanket in position (Ref. Figure 201) and check for interference with structural items such as support fasteners or footman loops. If interference exists, cut a cross in the inboard cover of the insulation blanket with the center of the cut at the point of interference. Cut away the insulation required to eliminate the interference. Seal the opened area on the inside of the cover of the insulation blanket with tape (2, Chart 2, 25-80-00). c.

Install double sided tape (4, Chart 2, 25-80-00) in position on the skin damping panel.

d. Install the insulation blanket in position and apply firm pressure to adhere the insulation blanket in position. e. Perform the MASS LOADED VINYL INSTALLATION procedure, as necessary. f.

Install cabin furnishings removed for access (Ref. Chapter 25-20-00).

A27

25-80-00

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

3

8

1. CABIN TRIM PANEL 2. MASS LOADED VINYL PANEL 3. BETWEEN FRAME INSULATION BLANKET 4. TUNED VIBRATION ABSORBER 5. FRAME (REF) 6. SOUND DAMPING PANEL 7. SKIN (REF) 8. DOUBLE SIDED TAPE (TYPICAL)

1

2

3

4

5

8

7

6

8 FL25B 985698AA.AI

Between Frame Insulation Blanket - Removal/Installation Figure 201

Page 202 Feb 1/10

25-80-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OVER FRAME INSULATION BLANKET REMOVAL a. Remove cabin furnishings and trim panels as necessary to gain access (Ref. Chapter 25-20-00). b. Perform the MASS LOADED VINYL REMOVAL procedure, as necessary. c.

Remove the ball strip from the retainer discs as necessary (Ref. Figure 202).

d. Remove the over frame insulation blanket.

OVER FRAME INSULATION BLANKET INSTALLATION a. Install the over frame insulation blanket in position. Make sure that the holes on the insulation blanket align with the holes through the frame (Ref. Figure 202). b. Install the retainer discs in position and install the ball strip through the retainer discs as necessary. c.

Perform the MASS LOADED VINYL INSTALLATION procedure, as necessary.

d. Install cabin furnishings removed for access (Ref. Chapter 25-20-00).

A27

25-80-00

Page 203 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1

10

2

3

9

4

5

6

8

7

1. CABIN TRIM PANEL 2. MASS LOADED VINYL PANEL 3. BALL STRIP 4. RETAINER DISC 5. OVER FRAME INSULATION BLANKET 6. RETAINER DISC 7. FRAME (REF) 8. BETWEEN FRAME INSULATION BLANKET 9. SKIN DAMPING PANEL 10. SKIN (REF)

6

5 4 3

FL25B 985699AA.AI

Over Frame Insulation Blanket - Removal/Installation Figure 202

Page 204 Feb 1/10

25-80-00

A27

C H A PTE R

FIRE

PROTECTION

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 26

FIRE PROTECTION

TABLE OF CONTENTS

SUBJECT

PAGE 26-1 0-00

Fire DetectionFire Detection

Description and Operation System. Troubleshooting.

Fire Detection

Maintenance Practices.

...............1

Fire Detection

..101 .........___201

Fire Detection Cable Removal

...201

Fire Detection Cable Installation. Fire Detection

System

........._____

Checkout Procedures.

........._____

.201

..........201

26-11-00

Engine Bleed Air Warning System Description and operation Engine BleedAirWarning System Maintenance Practices. Bleed Air Warning Pressure Switch Removal Bleed AirWarning Pressure Switch Installation

..................1

.201 .201

.........201

26-20-00

Fire

Extinguishing Description and Operation Extinguishing System. Fire Extinguishing Maintenance Practices Supply Cylinder Removal Supply Cylinder Installation. Extinguisher Cartridge Service Life. ExtinguisherSupply CylinderService Life Extinguisher Supply Cylinder Recharging. Extinguisher Activation Check.

............1

Fire

........1 ...............4 .........4 ..............4 .4 ...............4

...............5 .....5

26-21-00

Portable Fire

....1

Portable Fire

.......2

Portable

Portable Portable

Portable

n24

Extinguishers- Descriptionand Operation Extinguishers- Maintenance Practices fire Extinguisher Servicing Fire Extinguisherand Bracket Removal Fire Extinguisherand Bracket Installation Fire Extinguisher Inspection

26-CONTENTS

.2 ..........2 ........2

.3

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

26-LOEP

1

May

1/08

26-CONTENTS

1

May

1/08

1 and 2

May May May

1/08

26-10-00

101 201 and 202

1/08 1/08

1/08

201 thru 203

May May

26-20-00

1 thru 6

Oct 31/04

26-21-00

1 thru 4

Mar 9/01

26-11-00

A24

1

Pages

1/08

26-LOEP

May

1/08Page

1

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIRE DETECTION

DESCRIPTION AND OPERATION

FIRE DETECTION SYSTEM A fire detection

system is installed

to

provide

immediate

warning

in the event of

a

fire in the

engine compartment.

The main element of the system is a temperature sensing cable looped continuously around the engine and terminating in a responder unit. This responder unit is mounted in the engine accessory area on the upper left engine mount truss just forward of the engine firewall. The responder contains two sets of contacts: the integrity switch

circuitry; the responder alarm switch contacts warning system when the detector cable senses an overtemperature condition in critical areas around the engine. Signals from each responder unit are transmitted to a printed circuit card. The printed circuit card activates the master warning flasher on the glareshield through the annunciator fault detector printed circuit card. It also activates a flashing red warning light in the respective firewall fuel shutoff valve pushbutton, which is located on the glareshield just below the warning annunciator panel. These pushbutton type indicators have split lenses of red and green to serve the dual functions of monitoring the position of the firewall fuel shutoff valve and giving a visual warning of an overtemperature condition in either engine area. The green lens, placarded L or R FW VALVE CLOSED, indicates that the firewall fuel shutoff valve pushbutton has been depressed, closing the valve and arming the fire extinguisher pushbutton located on the warning annunciator panel. The light being extinguished indicates that firewall fuel shutoff valve is open. The red lens, placarded L or R ENGINE FIRE, illuminates when the fire detector cable senses an overtemperature condition of sufficient magnitude to activate the alarm switch contacts of the responder unit. contacts

complete

The

are

for the

test functions of the fire detection

continuity

the circuit to activate the fire

sensor

cable consists of

a

hermetically sealed,

corrosion resistant, stainless steel outer tube filled with

an

inert

gas, and an inner hydride core that is filled with an active gas. The gases within the tubes form a pressure barrier that keep the contacts of the responder integrity switch closed for fire alarm continuity test functions. As the

temperature around the sensing cable increases, the gases within the tubes begin to expand. When the pressure from the expanding gases reach a factory preset point, the contacts of the responder alarm switch close, completing a

circuit which

For fire

causes

the red L

detection/protection

or

R ENGINE FIRE

purposes critical

a.

Zone f

The accessory compartment.

b.

Zone 2

The

plenum

c.

Zone 3

The

engine

chamber

exhaust

The fire detector is preset at the i. When any

one

areas

light

in the firewall fuel shutoff valve

around the

have been divided into three zones;

area.

area.

factory

to activate the alarm when any of the

following

conditions

are

met:

temperature of the entire cable reaches 360"F.

3. When the

temperature in

zone

1

(accessory compartment)

4. When the

temperature in

zone

3

(hot

sensor

temperature

~a4

to illuminate.

foot section of the cable is heated to 800"F.

2. When the average

NOTE: The fire

engine

pushbutton

cable section in

in this

zone

is

section

zone

compartment)

2 is two feet

approximately

reaches 545"F.

reaches 540"F.

long

and is not

a

fire/overheat

zone.

Activation

900"F.

26-1 0-00Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIRE DETECTOR CABLE

ENG FIRE TES~

Q_9

PRINTED~-:

CIRCUITi BOARD

DETAIL

B

C

FIRE DhECTOR CABLE

I~ DETAIL

A

SENSOR RESPONDER SIMPLIFIED CIRCUIT /RESPONDER ALARM SW. (N.O.)

ISOLATOR

28 VDC

SW

TSE HGIR

B

SENSOR

SENSOR GABLE

RESPONDER

CABLE

LEFT OR

ENG. FIRE

DETAIL

C

INTEGRITY SWITCH N.C.

HELD CLOSED BY

NORMAL SENSOR PRESSURE

Fire Detection

Figure

May

1/08Page

2

26-1 0-00

ool

System 1

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIRE DETECTION -TROUBLESHOOTING etc, must be in the

All

supporting systems or equipment must be operating. All circuit breakers, switches, required for proper operation before troubleshooting begins.

Performing a fire detection system test should confirm circuitry and components. Refer to Chart 1.

the

integrity

of the detector

sensor

cable,

as

well

position

test the

as

electrical

Chart 101

TROUBLESHOOTING

1. L

or

R ENGINE FIRE indicator

during

CORRECTIVE ACTION

PROBABLE CAUSE

PROBLEM

fails to illuminate

FIRE DETECTION SYSTEM

test.

a.

Defective

lamp.

a.

lamp for proper operation.

Check

b. Check for presence of 28 vdc at

b. Loss of power to fire detector.

contact A of the fire detector connector. If not

Cs 19,

(RH

CB

present, check LH

20)

ENGINE FIRE

DETECTOR circuit breaker and

wiring

for proper

operation

and

condition. c.

Loss of test command

signal.

c.

Check fire detector connector

contacts B to C for

continuity when appropriate ENGINE FIRE TEST switch is placed to DET. If continuity is not present, check switch and for proper operation and

wiring

condition. d. Loss of

signal-out

command from

d. Connect

a

jumper wire

between

fire detector connector contacts A

fire detector.

and D. If ENGINE FIRE indicator

illuminates, replace the fire detector. e.

Circuit card

to

operate properly.

assembly

A 129 fails

e.

Connect

a

jumper

wire between

P 351 LH contacts 26 and 27, contacts 28 and

29).

(RH

Place ENGINE

FIRE TEST switch to DET. If

ENGINE FIRE indicator illuminates,

replace

A 129 Left

Test and

Advisory Light Hydraulic Gear Time Delay

Circuit Card. If ENGINE FIRE indicator does not illuminate,

wiring.

A24

26-1 0-00

repair

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIRE DETECTION

MAINTENANCE PRACTICES

FIRE DETECTION CABLE REMOVAL a.

Pull the FIRE DET circuit breaker

b.

Remove the

c.

Remove the nuts, bolts, screws, and

d.

Disconnect the electrical connector from the fire detector

e.

Remove the fire detector cable from the

engine cowling

as

on

the circuit breaker

outlined under the

panel.

heading

clamps throughout

ENGINE COWLING REMOVAL, 71-10-00.

the

length

of the fire detector cable.

responder

switch in the

engine

accessory

area.

airplane.

FIRE DETECTION CABLE INSTALLA TION a.

Install the fire detector cable cable in

NOTE:

on

the

engine using

the nuts, bolts, screws, and

clamps

to

properly

secure

the

place.

Use

care

when

installing

the fire detector cable. Do not form

loops

or

bends in the cable with less than

2-inch-bend radius. Be certain that clearance is allowed between the cable and the fire detector

b.

Install the electrical connector

c.

Reset the FIRE DET circuit breaker

d.

Perform FIRE DETECTION SYSTEM CHECKOUT PROCEDURES

on

on

responder switch

the circuit breaker

in the

engine

surrounding

accessory

a

structure.

area.

panel. as

outlined in this

Chapter.

FIRE DETECTION SYSTEM CHECKOUT PROCEDURES a.

Remove the

engine cowlings

as

outlined

by

ENGINE COWLING REMOVAL, 71-10-00.

apply heat to any portion of the damage the fire detection system.

CAUTION: Never

b.

Examine the fire detection

Check for contact c.

signs pins.

Connect

an

FIRE TEST

d.

or

With as

n24

an

or

a

functional test of the system,

as

this may

carefully to make sure that the sensor tube has no major damage. pits. Check to see that silicone grommets are suitably based on the

supply to the airplane and turn on electrical power. Place the left or right ENG copilot’s subpanel, in the DET position. Make sure that the corresponding L FIRE annunciator and the flashing MASTER WARNING lights illuminate to make correctly.

procedure on the opposite engine. If all annunciator lights illuminate, faulty lights and proceed with the following continuity test.

above test

If not, check for e.

R ENGINE

that the system is wired

Repeat the

element

element for

external 28-vdc power switch, located on the

ENGINE FIRE sure

sensor

of abrasion, kinks, cuts

sensor

ohmmeter, check for continuity between the pins in the responder connector;

the test is

complete.

readings

should be

meter

follows:

1.

PinAtoB lessthanoneohm.

2.

Pin A to C

greater than

3.

Pin A to D

greater than 100 megohms (open circuit).

100

megohms (open circuit).

26-1 0-00May 1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

f.

greater than 100 megohms (open circuit).

4.

Pin B to C

5.

Pin C to D less than

Any

deviation from the above is

Reinstall the

May

one

engine cowlings

ohm.

as

cause

for

outlined

26-1 0-00

rejection.

by

ENGINE COWLING INSTALLATION, 71-10-00.

P~4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE BLEED AIR WARNING SYSTEM The bleed air

warning system provides a visual pneumatic bleed air lines.

DESCRIPTION AND OPERATION

indication of excessive heat caused

by

a

leak

or

rupture in the

environmental and/or The bleed air

lines

made of

ethylene vinyl acetate (EVA) and are routed next to the environmental and pressurized by air tapped off the bleed air manifold, which is located under the pneumatic They first center floorboard panel forward of the main wing spar. Two pressure switches, located below the floorboard under the copilot’s seat, tap into the warning lines and monitor its pressure. When a rupture or leak occurs in the environmental or pneumatic bleed air lines, the excessive heat will cause the warning system’s EVA tubing to melt. This allows the pressure in the warning system to fall below the required level to keep the pressure switch open. With the pressure switch closed, the electrical circuit to the L BL AIR FAIL or R BL AIR FAIL annunciator light will be completed and the light will illuminate.

warning

are

bleed air lines.

When

a

bleed air line failure is indicated

placed pneumatic bleed must be

A24

are

in the PNEU

by the

ENVIR OFF

air shutoff valves,

stopping

annunciator

position.

right or left BLEED AIR VALVES switch appropriate firewall environmental and the engine firewall.

panel light,

the

This closes the

the bleed air flow at

26-11-00

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

ENGINE BLEED AIR WARNING SYSTEM CAUTION:

Every

time the bleed air

occurred, The bleed air

warning

must be

warning system replaced

lines must maintain the

One to four inches from the

pneumatic

MAINTENANCE PRACTICES is

following

actuated, the EVA tubing in the

area

where

damage

clearances:

bleed air lines.

Three to four inches in the center section from the environmental bleed air lines.

One to three inches in the

NOTE: The bleed air

When

from the environmental bleed air lines.

lines must be located below the horizontal center line of the environmental and

bleed air lines.

pneumatic CAUTION:

warning

fuselage

connecting

the EVA

only water as a lubricant. The use of petroleum or any type of damage to the EVA tubing. Breaks in EVA tubes may be repaired (not to exceed IS inches in length) attached with 130292A4 clamps

tubing,

use

lubricant other than water could cause

by use of P/N 101-970093-1 tubes or by replacing the broken tube section. To confirm correct

operation of the system, a simulated break in the EVA tubing can be accomplished by disconnecting the tubing from the engine bleed air manifold beneath the right cabin floorboard just forward of the aft spar (Ref. Figure 201, Detail B) during operation of the system. When the left tube is disconnected from the left boss on

the bleed air manifold, the left switch should activate and illuminate the L BL AIR FAIL annunciator. Confirmation

of the on

right system operation

can

subsequently

be

accomplished by disconnecting

the

right

tube from the

right

boss

the bleed air manifold.

BLEED AIR WARNING PRESSURE SWITCH RENIOVAL a.

Remove the

b.

Remove the electrical connector from the pressure switch.

c.

Remove the

fitting

d.

Remove the

attaching

access

panel directly

under the

copilot’s

from the pressure switch to be screws

that

secure

seat.

replaced. Cap

the switch in

place

the

and

fitting

remove

to

prevent contamination.

the pressure switch.

BLEED AIR WARNING PRESSURE SWITCH INSTALLATION a.

Position the pressure switch in its

b.

Remove the cap from the

c.

Attach the electrical connector to the pressure switch.

d.

Position and

secure

the

fitting

access

mounting

space and

and install the

fitting

secure

with the

attaching

screws.

to the pressure switch.

panel.

26-11-00Mayl/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

This

Page

yaM202

1/08

26-11-00

Page Intentionally

Left Blank

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RIGHT

LEFT BLEED AIR WARNING

BLEED AIR WARNING SWITCH

SWITCH

FII

i

BLEED AIR

k´•´•´•´•´•

_

Uli~

i .I-i\

pUSH TO ACTUATE

7

FIREWALL FUEL VALVE AND ARM FIRE EXT

li~l RFWVILVE

BLEED AIR

D AMBIENT

7111

I

II

I

AIR

C

AMBIENT

II I

illl

ENVIRONMENTAL BLEED AIR

I

I/

c

Ir ~jcl

PANEL)

PLUGS

ENGINE FIREWALL

HII

~ANNUNCIATOR

AIR

D

WARNING

BLEED AIR SHUTOFF VALVE

A

PLUGS

VALVE

DETAIL

A

ENVIRONMENTAL

SHUTOFF VALVE

PNEUMATIC BLEED AIR SHUTOFF

DETPdL

II I

1

II I

I

Illrd ~IR

:Jlill

I

II I

I

III’

ENGINE FIREVIIALL

~PNEUMATIC BLEED AIR SHUTOFF VALVE

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_

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BLEED AIR WARNING

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ENVIRONMENTAL BLEEDAIR LINES

BRAKE DEICE

I~Sg

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BLEED AIR LINES

MANIFOLD~

DETAIL RUDDER BOOST ELECTRICAL

PRESSURE REGULATOR

RH ENGINE BLEED

C

COPILOT’S SUBPANEL

AIR INLET

CONNECTION PLUGS

DETAIL

B

300456-1

Warning System Figure 201

Bleed Air

26-11-00 A24

Page 203 May 1108

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIRE EXTINGUISHING

DESCRIPTION AND OPERATION

FIRE EXTINGUISHING SYSTEM

Figures

1 and 2

extinguisher supply cylinder is mounted on brackets aft of the main spar in each wheel well of each main landing gear. Each cylinder is charged with approximately 2.50 pounds of Bromotrifluoromethane (CBrF3) pressurized to 450-475 psi at 72"F. The line from the cylinder runs along the side of the nacelle and branches into seven spray tubes strategically located about the engine to diffuse the extinguishing agent in the event of a fire. Four of the nozzles are positioned to discharge into the engine exhaust area and the other three discharge into the accessory area. Once activated, the entire supply of extinguishing agent is discharged. The fire extinguisher control switches used to activate the system are located on the glareshield at each end of the warning annunciator panel. The power for these switches is derived from a 5-amp circuit breaker, placarded LEFT or RIGHT ENGINE FIRE EXT., located on the circuit breaker panel. The push-to-activate switches incorporate two indicator lights. The red lens in the upper half of the light, placarded L or R ENGINE FIRE, indicate that the firewall fuel shutoff valve pushbutton, located on the glareshield and centered under the waming annunciator panel, has been depressed. The amber lens in the lower half of the light monitors the condition of the pyrotechnic cartridge and the status of the cylinder charge. As long as the cartridge is intact and the cylinder is not discharged, the amber light will remain extinguished. When the cartridge is fired, the light is illuminated and will remain illuminated until the cartridge is replaced. The green lens in the firewall fuel shutoff valve push button, placarded L or R FW VALVE indicates that the firewall valve is closed. This light will remain illuminated until the firewall valve push button is depressed a second

A fire

time. Test functions of the fire detection system are accomplished through two toggle switches located on the right instrument subpanel. These switches, placarded ENG FIRE TEST, DET-OFF-EXT, and LEFT RIGHT, are of the

three-position,

center-off type. When either switch is

placed

in the DET

position, electrical

current flows from a 5-

amp circuit breaker located on the right circuit breaker panel, placarded RIGHT or LEFT FIRE DETECTOR, through the engine fire detector circuitry to activate the flashing red L or R ENG FIRE light in the firewall fuel shutoff valve

push-button located on the glareshield directly under the warning annunciator panel. In the EXT position, circuitry for the EXTINGUISHER-PUSH light in the fire extinguisher push-button receives electrical power from 5-amp circuit breaker, placarded L or R ENG FIRE EXT, located on the right circuit breaker panel.

26-20-00

the the

Ra~heon

Aircraft tompany

MAINTENANCE MANUAL SUPER KING AIR B300/B300C

inl

iii

r

A

CIRCUIT CARD ASSY

I

168

j5r/

B!

FIRE EXTINGUISHER SUPPLY CYLINDER ENG FIRE TES’I

’9’

O-´•S, DETAIL

C

PRESSURE GAGE

PUSH TO *CTUITE FDIEW*LL FUEL YIL~E L"’LL"

*NOIRk(FIREEYT

DETAIL

DETAIL

A

350-482-13

Fire

Extinguishing System Figure

tcO2

Page

31/04

26-20-00

B

1

A17

Ral~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O-RING

nii

I\o

CARTRIDGE ASSEMBLY

Al

FITTING END

LOCKWASHER INSULATED TERMINAL

DETAIL

A

CONDITION 1. INSTALLED UNBLOWN SQVIB

FIRE EXTINGUISHER SUPPLY CYLINDER FITTING END

CARTRIDGE ASSEMBLY

CONDITION 2. SCIUIB DETONATED

EXTINGUISHER SUPPLY CYLINDER

CARTRIDGE ASSEMBLY

CONDITION 3. DISCHARGE OF EXTINGUISHING AGENT

Fire

A17

300-482-10

Extinguishing Squib Figure 2

2620I00

Oct

31/04Page

3

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIRE EXTINGUISHING

MAINTENANCE PRACTICES

SUPPL Y CYLINDER REMOVAL a.

Remove electrical power from the

CAUTION: Install

a

shunt

airplane.

(shorting device)

accidental activation from stray

or jumper wire across the contacts of the explosive squib to prevent voltages or static charges whenever the squib is not connected to the

airplane. b.

Working through

the main gear wheel well,

identify, tag

and disconnect the

wiring

to the

supply cylinder

terminals. c.

Disconnect the tube attached to the bottom of the

d.

Remove the

attaching

bolts and

remove

the

supply cylinder.

cylinder from

mounting

the

bracket.

SUPPL Y CYLINDER INSTALLA TION a.

Ensure electrical power has been removed from the are

not

airplane

and that the fire

extinguisher

activation switches

depressed.

b.

Secure the

c.

Remove the shunt and connect the

d.

Connect the tube to the bottom of the

e.

Restore electrical power to the

cylinder to

the

brackets with the

mounting

airplane wiring

attaching

to the

bolts.

supply cylinder terminals.

cylinder.

airplane.

EXTINGUISHER CARTRIDGE SERVICE LIFE

Replace

the

cartridge

at the interval

specified

in

Chapter 5-11-00,

or

sooner

if the

following exceptions

are

exceeded: a.

The storage temperature should not exceed 130"F.

b.

The service temperature

c.

The life of marked

on

a

(installed)

should be

a

nominal 200"F.

cartridge is determined as starting from plastic bag containing the cartridge.

the date

(month/year) stamped

on

the

cartridge body

or

the

EXTINGUISHER SUPPLY CYLINDER SERVICE LIFE Check the

engine

remain in service

fire extinguisher at the interval specified in Chapter 5. The fire extinguisher supply cylinders beyond the period of time stated in Chapter 5-11-00 provided:

cylinder is hydrostatically

a.

The

b.

The pressure gage indicates proper

c.

There is

Oct

tested.

charge (refer to

visible damage, such as dents, deeper deeper than 0.004 inch.

no

scratches

may

31/0426-20-00

Chart

1).

than 1/16 inch per inch of average dent diameter,

nor

any

~7

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

If the fire

extinguisher is removed from the airplane for any reason when it is past the due date for hydrostatic testing, emptied and hydrostatically tested per the DOT specifications prior to reinstallation. If the container is pressurized when removed from the airplane, it can be shipped to a recharge station, still pressurized, providing there is no evidence of damage as noted in step c. The station must then hydrostatically test the container before it is to be

recharging

and

returning

it to the

user.

EXTINGUISHER SUPPLY CYLINDER RECHARGING WARNING: Under

no

period

circumstances should

stated in

Chapter

a

supply cylinder be allowed to hydrostatic testing.

remain in service

more

than the

5-11-00 without

extinguisher supply cylinder is a pressurized container. Refer to the appropriate complete instructions on how to remove, disassemble, and empty the fire Failure to comply with the above and to instructions given in the overhaul manual extinguisher. could cause injury to personnel and/or damage to equipment.

The fire

overhaul manual for

Check the pressure gage on each cylinder prior to flight to ascertain that the pressure limits for the ambient temperatures noted in Chart 1.

cylinders

are

charged

to within the

NOTE: If the

engine has ingested a fire extinguisher agent or compound, then, and only then, should the engine be cleaned, removed and disassembled. If the engine fire extinguisher is discharged, the engine baffling will keep it from being ingested.

Fully discharged cylinders, or any cylinder indicating be returned to a recharging station.

less than the

specified pressure

on

the pressure gage, should

Chart 1

FIRE EXTINGUISHER CYLINDER PRESSURE LIMITS -40

-20

0

20

40

60

80

100

120

140

Indicated

190

220

250

290

340

390

455

525

605

700

Pressure

to

to

to

to

to

to

to

to

to

to

240

275

315

365

420

480

550

635

730

840

Temp

In

In "F

psi

EXTING UISHER A CTI VA TION CHECK a test lamp consisting of one 327 light bulb connected to two 22 gage wires. The wires should be of sufficient length to allow the operator to sit in the cockpit, perform the procedure and view the test lamp connected to wiring in the wheel well. Install an alligator clip on the free end of each wire.

a.

Construct

b.

Remove electrical power from the airplane.

CAUTION: Install

a

shunt

(shorting device) orjumper wire across the contacts of the explosive squib to prevent voltages or static charges whenever the squib is not connected to the

accidental activation from stray

airplane wiring. c.

Working through the extinguisher squibs.

d.

LeftFire

nl7

main gear wheel wells,

identify, tag

and disconnect the

wiring

to the left and

right

fire

ExtinguisherCheck

26-20-00

5

Ral~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1.

Connect the test lamp leads to the wires disconnected from the squib. Position the test lamp be viewed by the operator in the cockpit.

2.

Applyelectrical powertotheairplane.

3.

Press the fire wall valve switch to close the fire wall valve and

Extinguisher

Push"

light

and the test

Press and hold the left fire

4.

test

light

will decrease in

extinguisher intensity.

The "Fire

the fire

extinguisher. intensity.

Extinguisher

Push"

can

The "Fire

light should extinguish

switch. The "Fire

Extinguisher

Push"

light

and the

will illuminate and the test

6.

Repeat the actions in steps

7.

Press the fire wall valve switch to open the fire wall valve and disarm the fire Extinguisher Push" light and the test light should extinguish.

CAUTION: Ensure the left fire

continuing

e.

extinguisher switch. intensity.

light

arm

with low

that it

should increase in

Release the left fire

5.

light

should both

so

4 and 5

an

light

additional five times.

extinguisher switch procedure.

extinguisher.

is not depressed and that the test light is

The "Fire

extinguished before

with this

8.

Remove electrical power from the airplane.

9.

Disconnect the test lamp from the left squib

wiring.

RightFire ExtinguisherCheck 1.

Connect the test lamp leads to the wires disconnected from the squib. Position the test lamp be viewed by the operator in the cockpit.

2.

Apply electrical powerto

3.

Press the fire wall valve switch to close the fire wall valve and

Extinguisher 4.

light

and the test

Press and hold the

right

fire

light

Release the

should

that it

can

airplane.

Push"

the test 5.

the

so

light

extinguisher increase in intensity.

should both

light

switch. The "Fire

right fire extinguisher switch. The intensity.

"Fire

arm

the fire

with low

extinguisher. intensity.

Extinguisher Push" light

Extinguisher

Push"

light will

The "Fire

should

extinguish

illuminate and the test

and

light

will decrease in 6.

Repeat the

7.

Press the fire wall valve switch to open the fire wall valve and disarm the fire Extinguisher Push" light and the test light should extinguish.

actions in steps 4 and 5

CA UTION: Ensure the

continuing

an

additional five times.

with this

procedure.

Remove electrical power from the airplane.

9.

Disconnect the test lamp from the

Remove the shunt.

g.

Restore electrical

Oct

31/04Page

6

The "Fire

right fire extinguisher switch is not depressed and that the test light is extinguished before

8.

f.

extinguisher.

Identify

right squib wiring.

and connect the wires to the left and

right fire extinguisher squibs.

powerto the airplane.

26-20-00

nlr

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PORTABLE FIRE EXTINGUISHERS Two

portable

fire

extinguishers

are

installed in the

side of the door frame. The other

tinguishers The

are

mounted

on

portable extinguishers

Halon 1211 is

red

DESCRIPTION AND OPERATION airplane. One extinguisher is located in the aft cabin on the lower cockpit on the bottom of the co-pilot’s seat. Both ex-

is located in the

extinguisher quick-release brackets.

contain 2

pounds

of 1211

extinguishing agent and

100

psi of nitrogen for pressurization. B), and

chemical agent effective against combustible fires (Class A), flammable liquid fires (Class electrical fires (Class C). However, the smaller size extinguishers do not contain enough agent to qualify for

A

a

a

Class

rating.

Halon 1211 or bromochlorodifluoromethane is in a liquefied gas state while contained under pressure in the fire extinguisher. Upon release, the liquid quickly turns to a vapor that dissipates into the air and leaves no residue to cleanup. As it changes from liquid to vapor, a rapid temperature drop to below freezing occurs. The discharge should not be directed at exposed skin or eyes. When used on fires of intense heat, decomposition of the Halon 1211 vapor may be accompanied by a sharp acrid odor. This odor will serve to warn the operator of excessive exposure to the

products of combustion and

to take evasive action.

WARNING I IWI\RNING

Liquefied

Halon 1211

frostbite. Avoid contact with

exposed skin or eyes. High by-products when applied to fire. Avoid inhalation of the by-products by evacuating and ventilating the area. Do not use in confined spaces with less than 311 cubic feet per extinguisher. can cause

concentrations of Halon 1211

The bottles

can

produce

toxic

equipped with hand-operated actuating valves. The portable extinguishers may be recharged caily approved equipment service shops. Refer to Figure 1 for portable fire extinguisher locations. are

at lo-

fire

nln

26-21-00Page

1

Ray~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PORTABLE FIRE EXTINGUISHERS

MPIINTENANCE PRACTICES

PORTABLE FIRE EXTINGUISHER SERVICING

CAUTION 1 rCAUTION Do not

recharge with any materials except Halon 1211 and Nitrogen. Press lever only in case of discharge will cause pressure loss. Do not recharge extinguisher if damaged or corThis extinguisher must be fitted with a nozzle marked GH- 104.

fire. Partial roded. a.

After use,

b.

Return the

discharge

guisher charge

the

extinguisher to is 2

an

authorized service agency

pounds of Halon 1211

Record recharge date

c.

relieve pressure and

extinguisher completely to

on

pressurized

dealer for

or

to 100

psi

replace

the

ringpin.

recharging immediatel~´•after´•wse:

Extin-

with Nitrogen.

attached tag.

PORTABLE FIRE EXTINGUISHER AND BRACKET REMOVAL 1

Figure

NOTE Removal

procedures for the portable fire extinguishers

and brackets in the cabin and

cockpit

are

typical. To remove the cockpit or cabin fire extinguisher from quick-release latch, and remove the extinguisher. a.

To

b.

remove

securing

the

extinguisher

bracket from the sidewall

the

or

extinguisher bracket,

co-pilot’s chair,

open and unhook the

remove

the four

screws

and washers

the bracket.

PORTABLE FIRE EXTINGUISHER AND BRACKET INSTALLA TION

Figure

1

NOTE Installation procedures for the

typical. Replace a.

To install the

four b.

Mar

screws

the

portable fire extinguishers

extinguisher with

extinguisher bracket to the

an

identical type

sidewall

or

and brackets in the cabin and

cockpit

are

extinguisher.

co-pilot’s chair, align

the bracket with the inserts and install

and washers.

To stow the

extinguisher, position the extinguisher

9/0126-21-00

in the bracket, hook and close the

quick-release

latch.

nln

Rayl~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PORTABLE FIRE EXTINGUISHER INSPECTION

NOTE The

portable

fire

extinguishers

must be

inspected

at the interval

specified

in

Chapter

5.

portable extinguisher inspection consists of checking the gage to verify that normal pressure is maintained and recharging the extinguisher after use or at the required date. During the routine inspections, the following inspection procedures must be performed:

The

Check the gage for cracks, chips and cleanliness. Pointer on the face of the pressure gage must be in the range between the recharge and overcharge marks.

a.

"green" operating

Check that the tamper seal holding the ring-pin is in place. If the tamper seal is broken or missing, the extinguisher may have been discharged or partially discharged. A partially discharged extinguisher will leak, lose presb.

sure on

and become

inoperable. The extinguisher

should be

recharged

in accordance with the

recharge

instructions

the label.

c.

Ensure that the

mounting

d.

Ensure that the

discharge

e.

Make

sure

brackets

are secure

quick

release clamps operate

properly.

nozzle is unobstructed.

operating instructions and replacement schedule tags extinguisher.

the

attached to the

and the

are

in

good condition, legible, and securely

Weigh the extinguisher and record results on the attached replacement schedule tag. The maximum gross weight is 4 pounds 14 oz. and the minimum gross weight is 4 pounds 8 oz. Recharge the extinguisher if the gross weight is less than 4 pounds 8 oz. f.

g.

nln

Record the

inspection

date

on

the attached

replacement schedule tag.

26-21-00Page

3

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Irl!1 C

I

I

"X~

I

VIEY

A

5

B

d~l

Vrm

PRESSURE GAGE DISCHARGE NOZZLE OUICK-RELEASE LATCH EXTINGUISHER BRACKET WASHER SCREW 7.’EXTINGUISHER

I. 2. 3. 4. 5. 6.

B

5

I

c~

11

7

v~C

FL2~8

003571M

Portabie Fire

Extinguisher and Figure

Page

raM4

9/01

26-21100

Bracket Installation

1

A12

CHAPTER

FLIGHT

CONTROLS

REV34, 4/20/07

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 27 - FLIGHT CONTROLS TABLE OF CONTENTS SUBJECT

PAGE 27-00-00

Flight Controls - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Control Cable Tension Inspection Record . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 27-10-00 Aileron and Tab - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Control Wheel Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Control Wheel Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Control Column Cable Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Control Column Cable Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Control Column Bearing Support Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Control Column Bearing Support Repair. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Aileron Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Aileron Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Aileron Cable Removal (Fuselage) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Aileron Cable Installation (Fuselage) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Aileron Cable Removal (Wing) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Aileron Control System Rigging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Aileron Cable Installation (Wing). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Aileron Tab Removal (Left Only). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Aileron Tab Installation (Left Only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Aileron Tab Cable Removal (Wheel Well-To-Tab Control) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .217 Aileron Tab Cable Installation (Wheel Well-To-Tab Control) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .217 Aileron Tab Actuator and Outboard Cable Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .219 Aileron Tab Actuator and Outboard Cable Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .219 Aileron Tab Indicator Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Aileron Tab Rigging. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .223 Checking Aileron Tab Free Play . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .223 27-20-00 Rudder and Tab - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Rudder Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Rudder Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Rudder Cable Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Rudder Cable Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Rudder Control System Rigging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Rudder Pedal and Bellcrank Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Rudder Pedal and Bellcrank Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Rudder Pedal Inspection and Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Magnesium Rudder Pedal Arms. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Aluminum Rudder Pedal Arms (Unbushed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212

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PAGE

Rudder Tab Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Tab Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Forward Rudder Tab Cable Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Forward Rudder Tab Cable Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Tab Actuator And Cable Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Replacing The Rudder Tab Actuator Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Tab Actuator and Cable Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Tab Indicator Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Tab System Rigging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Checking Rudder Tab Free Play . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

212 212 214 214 215 216 219 219 220 224

27-21-00 Rudder Boost - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Rudder Boost - Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 Rudder Boost System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 Rudder Boost - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Rudder Boost Transducer Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Rudder Boost Transducer Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 27-30-00 Elevator and Tab (Pitch Control) - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Control Cable Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Control Cable Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Control System Rigging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Tab Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Tab Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Forward - Elevator Trim Tab Cable Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Forward - Elevator Trim Tab Cable Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Vertical - Elevator Trim Tab Cable Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Vertical - Elevator Trim Tab Cable Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Trim Tab Rigging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Trim Indicator Scale Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Trim Tab Actuator Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Elevator Trim Tab Actuator Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Replacing Elevator Trim Tab Actuator Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electric Elevator Trim Tab Actuator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electric Trim Tab Actuator Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electric Trim Tab Actuator Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electric Trim Tab Actuator Cable Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Magnetic Clutch Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Magnetic Clutch Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Magnetic Clutch Torque Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Page 2 May 1/10

27-CONTENTS

201 201 205 205 206 207 210 210 211 213 216 217 224 224 225 225 226 227 227 228 228 228 228 229

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PAGE

Elevator Tab Indicator Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .229 Checking Elevator Tab Free Play . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .229 27-31-00 Stall Warning-Safe Flight System - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Lift Transducer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Lift Computer. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Stall Warning-Safe Flight System - Troubleshooting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Ground Functional Test. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Stall Warning-Safe Flight System - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Lift Transducer Heaters. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Stall Lift Computer Calibration - On Ground . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Stall Lift Computer Calibration - In Air. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 27-50-00 Flaps - Description And Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Flaps - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flap Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flap Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Flap Drive Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Flap Track Wear Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Flap Track Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Flap Motor and Gearbox Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Flap Motor and Gearbox Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Flap Actuator Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Flap Actuator Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Flap Control System Rigging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Flap Safety Mechanism. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Flap Safety Switch Functional Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Flap Actuator Piston Lubrication (1200 Hours) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Flap Flexible Driveshaft Inspection and Repair. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 27-70-00 Gust Locks and Damper - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Control Locks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Control Lock Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Control Lock Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

27-LOEP

1

May 1/10

27-CONTENTS

1 thru 3

May 1/10

27-00-00

1 thru 8

Nov 1/07

27-10-00

201 thru 225

Feb 1/09

27-20-00

201 thru 225

Feb 1/10

27-21-00

1 101 and 102 201 and 202

May 1/10 May 1/10 May 1/10

27-30-00

201 thru 231

Oct 31/06

27-31-00

1 101 thru 105 201 thru 206

Feb 1/09 May 1/08 May 1/08

27-50-00

1 201 thru 210

Oct 31/06 May 1/10

27-70-00

201 and 202

Oct 31/06

A28

27-LOEP

Page 1 May 1/10

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FLIGHT CONTROLS NOTE: Stall

strips

are

DESCRIPTION AND OPERATION

installed

on

the

wing

deice boots which effect roll characteristics. Refer to

Chapter

30-10-00

for their proper installation.

All

exception of the flaps are cable-operated conventional surfaces which require no power assistance for normal control by the pilot or copilot. The flaps and optional electric elevator trim are electrically powered. An electrically powered rudder boost/yaw dampening system (which is connected directly to the autopilot), designed to aid the pilot during an engine-out condition, is provided to function automatically (when activated) as torquemeter oil pressure drops during an engine failure. flight controls,

with the

All

primary flight control surfaces are manually controlled through cable/bellcrank systems. Dual controls are provided for operation by either the pilot or the copilot. Ailerons and elevators are operated by conventional pushpull control wheels, interconnected by a T shaped control column. Rudder pedals are interconnected by a linkage below the crew compartment floor. Rudder bellcrank arms are adjustable to two positions which move the pedals approximately one inch forward or aft. Surface travel stops and linkage adjustments are incorporated into each cable/bellcrank system.

Ailerons, elevators and rudder may be secured with control locks installed in the

airplane

is

the

on

ground

crew

compartment

when the

and out of service.

operated by an electric motor-driven gearbox mounted on the forward side of airplane. The gearbox drives four flexible drive shafts, each connected to an each at flap. A safety mechanism is provided which will disconnect power to the electric acme-thread-type jackscrew motor in the event of any type of failure which causes any flap to be 3" to 5" out of phase with the other three flaps. The flaps are controlled by a lever mounted in the pedestal. A lever position detent is provided to select 40% flaps extension (14") for approach position. Full flap position is 35" (100%). Wing flap position tin percentage) is shown by an indicator located in the pedestal near the flap control lever. The indicator is actuated by a potentiometer driven by the right inboard flap.

Two the

flaps

rear

installed

on

each

wing

are

spar at the centerline of the

Trim tabs

manually controlled by the pilot adjustable double-end clevis rod assemblies which are capable of removing joint free play. All trim tab actuators used on this airplane are of a dual configuration, providing additional safety control of trim and tab free play. Tab position indicators are provided on the tab controls which are located on the pedestal.

through

The

are

installed

drum-cable

optional

on

the left aileron, the rudder and each elevator. The tabs

systems using dual jackscrew actuators. The dual

electric motor-driven elevator trim tabs

control wheel. A

downspring

and bob

weight

are

are

activated

incorporated

by

a

are

actuators drive

control switch

on

into the elevator control

the outboard handle of each

system for improved stability.

primary flight control surfaces limit their travel while traveling stops secured to the cables limit Figure 208, Chapter 27-10-00, shows the proper method of safetying the trim tab stops to prevent their loosening and moving on the cables. Because the cables are connected together with turnbuckles, each cable has one left-hand- and one right-hand-threaded cable end. Proper winding of the cables on the pedestal and actuator drums as shown in Figure 206, Chapter 27-10-00 ensures against crossing the cables and causing improper trim tab movement. Positive

stops

on

the

trim tab movement.

Refer to the and force,

applicable rigging procedures for details regarding downspring force and system friction.

chain and cable tension, control wheel movement

27-00-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTROL CABLE TENSION INSPECTION RECORD The control cable tension

inspection

record is

provided

to record the

temperature and cable tension of the aileron, can be machine copied without

aileron tab, elevator, elevator tab, rudder, and rudder tab control cables. The record

I constituting

a

violation of the Hawker Beechcraft

Corporation copyrights.

CONTROL CABLE TENSION INSPECTION RECORD A. COCKPIT AND FORWARD FUSELAGE

MECH

INSP

MECH

INSP

MECH

INSP

INSPECT AND RECORD AILERON CABLE TENSIONS: TEMPERATURE:

degrees

F.

Control Column Interconnect Cable Tension:

1/8 inch Aileron Cable Tension at Quadrant: LEFT

RIGHT

B. REAR FUSELAGE AND EMPENNAGE

INSPECT AND RECORD ELEVATOR, ELEVATOR TAB, RUDDER AND RUDDER TAB CABLE TENSIONS: TEMPERATURE:

F.

degrees

DOWN

Elevator Cable Tension: UP Elevator Tab Cable Tension:

RIGHT

Rudder Cable Tension: LEFT Rudder Tab Cable Tension:

C. LEFT WING INSPECT AND RECORD AILERON TAB CABLE TENSIONS: TEMPERATURE:

degrees

F.

Aileron Tab Cable Tension:

Page

voN2

1107

27-00-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

SPECIAL TOOLS AND RECOMMENDED MA TERIALS

special tools and recommended materials listed in Charts 1 and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. I Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance with I the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used. The

Chart 1

Special

Equipment SUPPLIER

PART NUMBER

TOOL NAME 1.

Tools and

810 99-524000

Aileron Travel Board

Hawker Beechcraft

USE

Corp.

Wichita KS 67201

2.

810-1101130001-1

Aileron Trim Tab Travel

3.

Hawker Beechcraft

Corp.

Wichita KS 67201

Board TrimTabCable

StopTool I

TS1171

RudderTravel Board

807 101-630000-1

Hawker Beechcraft

Corp.

ElevatorTravel Board

807 101-610000-1

Hawker Beechcraft

Corp.

Hawker Beechcraft

7.

Hawker Beechcraft

Board

-2

Wichita KS 67201

RudderTrim TabTravel

810 130-630000-1

Corp. Corp.

setting flight

Checking

and

setting flight

I

Checking

and

setting flight

I

Checking

and

setting flight

Checking

and

setting flight

I

control movement.

Hawker Beechcraft

Corp.

Wichita KS 67201

Board

and

control movement.

810 130-610000-11

Elevator Trim Tab Travel

Checking

control movement.

Wichita KS 67201

6.

setting flight

control movement.

Wichita KS 67201 5.

and

control movement.

Wichita KS 67201 4.

Checking

control movement.

Checking

and

setting flight

I

control movement.

NOTE

Special 8.

Tab Deflection Check

810 45-135030-9

(May

Fixture

as

to

9.

Tool l.thru 7.

be fabricated

illustrated

(Ref. Figure 1).

Hawker Beechcraft

Corp.

Checking

and

setting flight

Wichita KS 67201

control movement.

Obtain

locally

Check tension.

Obtain

locally

Burn in clutch.

I

illustrated. Refer

Figure 2.)

Cable Tensiometer

10. Drill Motor

as

(450 Max

RPM) 11. Voltmeter

A23

Fluke Model 8000A

John Fluke

or8100A

Everrett, WA

Manufacturing,

Check

voltage.

27-00-00

Nov

1/07Page

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

Special Tools TOOL NAME 12. Push-Pull Scale

type, 25-pounds

and

Equipment (Continued)

PART NUMBER

SUPPLIER Obtain

(Spring

USE Check control force.

locally

or more

capacity) C81Q

13. Dial Indicator

Federal Products

Tab

free-play

check.

Providence, RI

1

14.

Torque System Calibrator

101-000000/934

Hawker Beechcraft

Corp.

15.

Torque System

Pressure

Model 2311

Barfield instrument

Corp.

4101 N.W. 29th St., Miami,

Tester

Perform Rudder Boost Transducer Check.

Wichita KS 67201

Perform Rudder Boost Transducer Check.

FL 33142

16. Flukemeter

8060Aorequivalent

John Fluke

Manufacturing,

Everrett, WA

Page

voN4

1107

27-00-00

voltage checks that require accuracy of a digital display. Perform

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PIN 0810 130-610000-1-2 ELEVATOR TRIM TAB TRAVEL BOARD

p’’

TS 1171

:Pd %P~

C

(USED TO TIGHTEN CASTELLATED

41

~I

NLIT USED ON FLKIHT CONTROL SYSTEM) ~rmo-l,? PIO

P/N 0807 101-610000-) -2

(00060 807 101-610000-1) ELEVATOR TRAVEL BOARD

63_

PIN 810 98´•524000 AILERON TRAVEL BOARD P/N 0807 101-630000-1 (ORDER 807 101-630000-1)

RUDDER TRAVEL BOARD

Plhl 0810-1 101-130001.1 AILERON TRIM TAB TRAVEL BOARD

~m

(ORDER 810-1101190001-1) PIN 130-630000-1 RUDDER TRIM TAB TRAVEL BOARD

O

FLne

073234AA.TIF

Special Tools Figure 1

A23

27-00-00

Nov

1 07Page

5

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

9

12

io

q78

t3

I

.8 IN

t;

.5 IN

.25 IN

7

O

5/8-)1

TAP

TYP

2.9 IN

I

t

AA TAB

1’4 1.30 IN 2

ITEM

OUANT.

DESCRIPTION

NO.

.68 IN

6 aluminum

1.viuqe 1

21

22

314

3

1

112

4

i

C81Q Indicator"

5

1

3i4

6

1

114 Dia.

7

1

114 Dia. xl corrosion res. stl.

8

1

1/4-28 nut

x

x

x

1-318

x

x

x

7-1/2 2-112

x

x

10 aluminum

or or

14 aluminum or

equiv. equiv.

I

’--+t+

7 1.6 IN

equiv.

2 corrosion res. stl.

x

9

1

318

w

5

x

10 rubber

10

1

3/8

x

2

x

10 rubber

11

1

114

x

2

x

12

2

1/2

x

13

13

2

KN813 Keensert

14

2

118

x

or

1-3/4 aluminum

\.31

IN

10 corrosion res. stl. x

3 VLIER Or

Torque Screw tap 112-13

SECTION A A

1-314 rubber

"PIN of Federal Products

Corp.,

Providence R.I.

THIS GROOVE TO BE A SNUG flT TO THE SCREW BRACKET ON THE DIAL INDICATOR 1900-135-3

Fabricating Check Fixture For Tab Deflection Figure 2

Page

voN6

1/07

27-00-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 Recommended Materials

MATERIAL 1.

Grease, Aircraftand Instrument, Gear and

SPECIFICATION MIL-G-23827*

SUPPLIER

PRODUCT

No. A72823

AMOCO, Inc. 2021 Spring Road, Oak Brook, IL 60521

Aeroshell 7

Shell Oil Co.

Supermil Grease

Actuator Screw

1 Shell Plaza, Houston, TX 77001 2.

3.

Solvent, Dry Cleaning

P-D-680, Type III

MIL-S-8802

Sealer

(Mineral Spirits)

Solvents, Inc. 201 S. Cedar Street, Valley Center, KS 67147

PR1422

Courtaulds

Barton

Stoddard Solvent

Aerospace,

Inc.

P.O. Box 1800

5454 San Fernado Road,

Glendale, CA 91209 Essex Chemical

Pro-Seal 890

Corp. Coast Manufacturing Co., Angeles, CA

Pro Seal Los

Obtain

4.

MaskingTape

5.

Lubricating Grease, Molybdenum Disulfide

MIL-G-21164

Lubricant, AirDrying,

MIL-L-23398

6.

Aeroshell Grease 17

locally

Shell Oil Co. 1 Shell Plaza, Houston, TX 77001

Electrofilm

Lubribond

Manufacturing

Co.

P.O. Box 55669

Solid Film

25395

Rye Canyon Road,

Valencia, CA 91355

Methyl Propyl

7.

Solvent

8.

Epoxy,Wear Resistant

Ketone

Devcon WR-11210

Obtain

Locally

Devcon

Corp.,

30 Endicott Street,

(Liquid)

Danvers, MA 01923 9.

Epoxy,Wear Resistant (Paste)

Devcon WR 11410

Devcon

Corp.,

30 Endicott Street,

Danvers, MA 01923 10.

Retaining Compound

Loctite

Loctite 680

Corp.,

705 N. Mountain Road,

Newington, CT 06111 11. Primer

Loctite Primer Grade T

Loctite

Corp.,

705 N. Mountain Road,

Newington, CT 06111

A23

27-00-00

Nov

1 07Page

7

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 Recommended Materials MATERIAL

Coating

for Aluminum

and Aluminum

MIL-C-81706 per MIL-C-5541

SUPPLIER

PRODUCT

SPECIFICATION

12. Chemical Conversion

(Continued)

1200, 1200S and 1201, 1203 and 600

Alodine

32100

Stephenson Highway, Heights, MI 48071

Madison

Alloys

13. Corrosion Preventive

Parker and Amchem, Inc.

MIL-C-16173

Braycote

Castrol, Inc.

137

16715 Von Karman Ave.

Compound

Suite 230,

Irvine, CA 92714 Vantico A&T US Inc.

Epibond 104A/B

14. Adhesive

5121 San Fernando Road West Los

15. Tedlar

838

Tape

Angeles,

CA 90039

Mining and Manufacturing Co. 3M Minnesota

Tape

Center

St. Paul, MN 55101

1

16.

Naphtha

17.

Lubricating

Obtain

TT-N-95 Oil

SAE-J2360

locally

Hawker Beechcraft Aircraft

101-380016-01

Services Take

precautions when using MIL-G-23827, painted surfaces.

MIL-G-81233 and

engine

oil

as

these lubricants contain chemicals

harmful to

Page

voN8

1107

27-00-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AILERON AND TAB WARNING:

time

Any

MAINTENANCE PRACTICES

push-pull rods

are

installed

or

adjusted,

the

inspection holes near the ends of the rods fittings are visible. the threads must

must be checked to ascertain that the threads of the end

be visible in the holes.

CONTROL WHEEL REMOVAL a.

Disconnect the electrical

b.

Remove the taper pin which secures the control wheel adapter from the control column.

wiring

from the various control wheel switches

adapter

as

necessary.

to the control column and

pull

the control wheel

CONTROL WHEEL INSTALLATION a.

Place the control wheel secures

i.

adapter

Excessive or

2.

the

nylon

adapter

and control wheel in

to the control column while

driving

of the taper

pin

can cause

place on the control column and observing the following precautions:

cracks in the

mallet should be used to set the taper

Make certain that the unthreaded

portion

pin

tubing

insert the taper

of the control column. A

lightweight

pin that

rawhide

when it is installed.

of the small end of the taper

pin

is at least flush with, but not

more

than 0.06 inch above the surface of the control column. 3. 4.

Tighten

the taper

nut to 12 to 15

inch-pounds.

If the taper next size

b.

pin

pin hole has become enlarged larger taper pin.

Connect the electrical

wiring

or

elongated,

it

can

be

from the various control wheel switches

taper reamed

as

as

required

to install the

necessary.

CONTROL COLUMN CABLE REMOVAL a.

Disconnect the

gileron

b.

Paint

on

one

proper c.

tooth

alignment

cables from the control column cable at the turnbuckles.

each of the control column

actuating sprockets

and its

corresponding

chain link to make

sure

of the control wheels at installation of the chain.

Loosen the cable turnbuckle in the center of the control column horizontal

retaining pins, unsafety

the chain from the

sprockets

and

remove

cross

member,

remove

the cable

the control column cable and chain

assembly.

CONTROL COLUMN CABLE INSTALLATION NOTE:

a.

If a uSed cable is installed, the cable should be dipped in corrosion preventive compound (Item No. 13, Chart 2, 27-00-00). The excess should be removed by wiping with a clean rag. Chapter 20-04-00 for control cable and pulley inspection requirements.

Place the control column cable and chain

links of the chains

engaging

wire the chain to the b.

n25

the

Refer to

assembly on the cross member of the control column with the painted corresponding painted sprocket teeth. Install the cable retaining pins and safety

sprocket.

Connect the aileron cables at the turnbuckles

on

the control column.

27-1 0-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: The interior of all turnbuckles should be coated corrosion

Rig

c.

or

filled with grease

(Item

No. 1, Chart 2,

27-00-00)

for

protection.

the cables

as

outlined under AILERON CONTROL SYSTEM RIGGING.

CONTROL COLUMN BEARING SUPPORT INSPECTION Remove

a.

NOTE:

If

located aft of the

panel

access

discrepancies are found during procedure.

nose

the

wheel well

(Ref. Chapter 6-50-00).

inspection, perform the CONTROL COLUMN BEARING SUPPORT

REPAIR

CAUTION: If the gap between the support or

missing

rivets

arm

and the

bearing support exceeds

0.020 inch and/or

found, inspect adjacent attachment intercostal/keel

are

area

loose, working

for deformation and

cracks. b.

Inspect left and right control (Ref. Figure 201, Sheet 1).

c.

Check the gap between left and 0.020 inch.

d.

If

applicable,

install the

column

access

bearing supports

right support

arm

for loose,

and

working

bearing support

or

missing

to make

rivets

sure

the gap does not exceed

panel.

CONTROL COLUMN BEARING SUPPORT REPAIR This

procedure should only

be

performed

to correct

discrepancies found

in the CONTROL COLUMN BEARING

SUPPORT INSPECTION. WARNING: Whenever any part of this system is dismantled, adjusted, repaired or replaced, a detailed investigation must be made on completion to make sure that distortion, tools, rags, or any other loose articles, or foreign matter that could impede the free movement and safe operation of the a.

system

are

Remove all power from the of

airplane

present, and the systems and installation in the work

not

airplane and disconnect

the

battery. Display warning

notices

area are

prohibiting

clean.

connection

electrical power. and any associated cabinets

b.

Remove the forward cabin

c.

Remove the

d.

Remove the extrusion

e.

Remove the control column boot and

f.

Remove the forward

g.

Disconnect the link from the bob

h.

Remove

i.

Working through

partitions

flight compartment

access

the

right

side of the

pedestal.

plates forward of

the

pedestal

and floorboard

and

on

each side of the

pedestal.

panels.

weight.

located aft of the

access

if installed.

(Ref. Chapter 25-10-00).

flight compartment carpet

panel the

on

seats

las required),

nose

wheel well

(Ref. Chapter 6-50-00).

hole, disconnect the push-pull tube and, if applicable, the pitch change transducer

rod end.

Page

beF202

1109

27-1 0-00

nas

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE:

Install.suitable cable blocks forward of floor member at

approximately FS

prior

107

to

disconnecting

the

aileron control column cables.

j.

Disconnect the aileron control column cables.

k.

Remove the left and

NOTE: The radio

panel

right taper pins

in the center of the instrument

Remove the control column

I.

inserted into support

from the aft side of the universal

arm

panel may have

joint

and disconnect the

torque tubes.

to be removed for clearance.

bolts. Raise the control column and support it in place using a dowel rod (i.e. the lower tube) just forward of the bearing supports (Ref. Figure

mounting

crossmember

201,Sheetl). rivets and

the

m.

Carefully

n.

Inspect the bearing supports and the support arms for damage. Inspect for damage in the adjacent make sure that the proper edge margin for the bearing support and support arm is maintained.

o.

If necessary drill the

remove

support

remove

arm

NOTE: It is recommended that the

of the rivet p.

Attach each

on

and

bearing supports.

bearing support

bearing support

bearing support

to the

support

and

attach holes to 0.159 to 0.164 inch diameter.

attach rivets be installed with the manufactured

the inboard side of the support

area

(resultant)

head

arm.

arm on

the control column with six CR3213-5

Cherry

Max rivets

or

MS20470AD5 solid rivets. q.

Make

sure

the gap between the

bearing support

and the support arm does not exceed 0.020 inch.

NOTE: The maximum unshimmed total gap between the bearing supports and the adjacent attachment intercostala/keels measured prior to bolt installation is not to exceed 0.156 inch. Shim as required with

(NAS1149F0516P, NAS1149F0532P, NAS1149F0563P, AN960-516, or AN960-516L) between bearing supports and the adjacent attachment intercostals/keels to reduce the total gap to a maximum of 0.030 inch (0.015 inch maximum per side). Shim equally on each side of the control column. It is acceptable to substitute bolts up to two grip lengths longer as required to allow washers to be added while maintaining at least 1 1/2 thread protrusion through the nut. washers the

NOTE:

It is recommended that control column

mounting

attachment intercostal/keel and the nut

Carefully

lower the control column into

keel and the s.

t.

place

Position the control column to either the

(intercostal/keel). inch-pounds.

On the

bolts be installed with the bolt head

the inside of the support

on

the outside of the

arm.

and insert mount bolts into the left and

right

attachment intercostal/

adjacent bearing support.

attachment to 65

on

On the

left,

same

or

right

side until the

bearing support

side, install the washer and

opposite side, measure the resultant gap (Ref. Figure 201, Sheet 2).

between the

nut

on

the

touches the

mounting

adjacent

bolt and torque 50

support bearing and the adjacent attachment

intercostal/keel

NOTE: A total gap of 0.030 inch maximum (0.015 inch maximum per side) between the bearing supports and adjacent attachment intercostal/keel is acceptable. It is acceptable to reduce gaps of less than 0.030 inch if desired, provided the total interference fit does not exceed 0.020 inch (0.010 inch per side).

A25

27-1 0-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: A total gap of between 0.030 and 0.156 inch must be reduced

by installing washers

as

shims. Use either

NAS1149F0516P, NAS1149F0532P, NAS1149F0563P, AN960-516, or AN960-516L washers as shims. The washers on each side of the column must be of equal thickness, and must reduce the gap of each side to 0.015 inch

or

less. No

than two washers of any thickness may be installed per side. The total (0.010 inch per side).

more

interference fit is not to exceed 0.020 inch

NOTE: If the gap exceeds 0.156 inch call Hawker Beechcraft u.

Shim

equally

as

required

to achieve

to obtain a proper fit. Install v.

Install

a

Technical

maximum gap of 0.030 inch. Make 50 to 65

sure

bolt(s), washer(s), nut(s) and torque

Support

bolts

are

for assessment.

of suitable

grip length

inch-pounds.

cotterpins.

CAUTION: Excessive

driving

of the taper pin

should be used to set the taper w.

Corporation

can cause

pin when

cracks in the

tubing.

A

lightweight rawhide

or

nylon

mallet

it is installed.

taper pins, taper pin washers and nuts to secure the torque tubes to the universal joints. Make sure that taper pin is at least flush with, but not more than 0.06 inch above the surface of the universal joint and torque 15 to 20 inch-pounds. Install

the small end of the

x.

Install

y.

Connect the aileron control column cables and

cotterpins. cable blocks forward of floor member at

remove

approximately

FS 107. tube and if

z.

Connect the

aa.

Connect the link to the bob

ab.

Perform

push-pull

of this

Install the boot and

ad. Install the extrusion

on

the

af.

Install the

right

side of the

partitions

flight compartment

seats

panel located aft of the

aj. Connect

Page

the

battery

and

panel

remove

each side of the

pedestal.

pedestal.

floorboard

ah. Install the

the radio

on

(Ref. Chapter 25-10-00).

flight compartment

applicable, install

procedure. Rig any other systems disturbed during applicable Chapter of this maintenance manual.

and any associated cabinets.

ag. Install the forward access

rod end.

in accordance with the

plates forward of the pedestal and

Install the forward cabin

If

pitch change transducer

weight.

repair

ae.

ai.

the

AILERON CONTROL SYSTEM RIGGING

accomplishment ac.

applicable,

and carpet.

wheel well

(Ref. Chapter 6-50-00).

in the center of the instrument

warning

20427-1 0-00

nose

panels

notices

prohibiting

panel.

connection of

airplane electrical power.

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

f

i:)

´•i

FWD

INBOARD

.\9

.,CONTROL COLUMN BEARING

BEARING

MAXIMUM GAP F....

SUPPORT ARM

INCH

020.0PAG

MAXIMUM

0.030 INCH MAXIMUM

i,

INTERCOSTAL

TOTAL GAP

ii~

j 0.159/0.164 INCH DIA.

6 HOLES

’ib ´•\´•1

VIEW

A

Control Column

Bearing Support Inspection Figure 201 (Sheet 1 of 2)

ORIGiNAI A25

As Received ATP

and

Repair

27-1 0-00

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

H ´•j-´•ii:,:

C;tPX~ iC

sP~:

0.030 INCH MAXIMUM

TOTAL GAP

f FWD

]NBOARD

II~.

Control Column

Bearing Support Inspection Figure 201 (Sheet 2 of 2)

Page

206

Feb 1/09

27-1 0-00

and

Repair

ORIG\NAL A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AILERON REMOVAL

Only

the left aileron

incorporates

an

aileron tab. The aileron tab

actuator which is mounted ahead of the

Each aileron

push-pull

rods connect

directly

bracket is inserted between the aileron skin and spar and is secured with four one hinge bracket to transmit movements to the aileron.

hinge

the cotter

remove

side of the aileron tab to the

b.

push-pull (Ref. Figure 202).

spar

to the twin

screws.

screw

The aileron

rod is connected to

NOTE: On the left aileron,

a.

rear

Support

the aileron in

from the

hinge

appropriate

to

manner

prevent damaging the aileron

the horns

when the

on

the underneath

removed

screws are

brackets.

Remove the four screws on

an

pins, bolts, washers and nuts connecting push-pull rods from the aileron tab actuator.

screws

attaching each hinge.)

aileron

hinge

bracket to the aileron.

(Two

screws on

the

top and

two

the bottom at each

c.

While

d.

Remove the

e.

Move the aileron

providing support screws

for the aileron,

attaching

straight away

CAUTION: On the left aileron, rods

the

through

pull the aileron straight away

use

wing.

cable to the aileron.

bonding jumper

from the

from the

wing.

caution to not

damage the aileron skin while moving the adjustment of the push-pull rods.

aileron tab

push-pull

the aileron. Do not disturb the

AIL ERON INS TALLA TION NOTE: a.

Any repair, modification, painting or~replacement

Support

the aileron in

position

and install the

bonding jumper

NOTE: On the left aileron, the aileron b.

carefully guide the aileron leading edge or skin.

Align the inboard, loosely install two

center and outboard

bolts

tone

bolt in the

of the aileron

hinges top and

tab

or

cables

aileron tab

(Ref. Figure

push-pull rods through

requires~ rebalancing. 202 and

the aileron

Figure 203).

so as

to not

damage

of the aileron in the proper location on the aileron spar, then one in the bottom) through each hinge into the nut on the aileron

spar. c.

Pull

on

the aileron to confirm that the bolts

NOTE: If there is d.

Install the

no

are

properly

movement when the aileron is

remaining

bolts and

NOTE: The clearance noted in

tighten

Figure

pulled,

installed. the bolts

are

203 must be maintained between the aileron and the outboard

apply

flaps.

The gap

to the lower forward area where the

tapers outboard.

e.

Install the bolts, washers, nuts and cotter

f.

Check the aileron and tab for proper travel and attachment.

n25

installed.

all the bolts.

should be constant within 0.06 inch. These dimensions do not aileron

properly

pins securing

the aileron tab

push-pull

rods to the aileron tab horns.

27-1 0-00

Page

beF702

1/09

I

Hawker Beechcraft

Corporation

MANUAL SUPER KING AIR 8300/B300C MAINTENANCE

NOTE ONLY THE LEFT AILERON HAS AN AILERON TRIM TAB.

-4

A

r~a

8

~R

~B

C

DETAIL

A

DETAIL

C

3.

AILERON HINGE ATTACH SCREW (4) AILERON HINGE ATTACH SCREW (4) AILERON HINGE ATTACH SCREW (4)

4.

OUTBOARD HINGE BRACKET

5.

CENTER HINGE BRACKET

6.

INBOARD HINGE BRACKET

i.

2.

DETAIL

B e300-15~-21

Aileron Installation and Removal Figure 202

beF802

Page

1/09

27-1 0-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AILERON TRAVEL

BOARD

NOTE:MOUNT

810 99-524000 AILERON TR~VEL BOARD 3 RIVETS BEYOND IST RIE OUTBO~RD OF THE INBOARD HINGE (WING STATION 236.923)

O. IF

INCH -tO. 21 -0. 09

INCHi j INCH

1). 38

DIMENSIONS TO BE NOTED WHEN INSTALLING THE FLAPS AND/OR AILERONS

INCH

t

TYPICAL

r). 13

BOTH

INCH

~IDES

88278 061 442F1A

Flap Installation Figure 203

Aileron and

ORIGINAL n25

AE Received By ATP

27-1 0-00

Page

209

Feb 1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AILERON CABLE REMOVAL a.

b.

Remove the

pilot’s

seat and the forward passenger seats as necessary.

pilot’s compartment floorboards, panels forward of the rear spar.

Remove the left left cabin floor

c.

(FUSELAGE)

center floorboard

pilot’s compartment

the

access

plate and all

Disconnect the forward ends of the cables at the turnbuckles at the vertical member of the control column

(Ref. Figure 204).

I d.

Disconnect the aileron cable cable

e.

retaining pins

from all

locking plates on pulley brackets.

the

quadrant regulator just

Attach lead lines to the forward ends of the cables and

remove

forward of the

the cables

through

rear

the aft

spar. Remove the

access

openings.

Detach the lead lines from the cables.

AILERON CABLE INSTALLA TION NOTE:

(FUSELAGE)

a used cable is installed, the cable should be dipped in corrosion preventive compound (Item No. 13, Chart 2, 27-00-00). The excess should be removed by wiping with a clean rag. Chapter 20-04-00 for control cable and pulley inspection requirements.

If

a.

Attach the cables to the lead lines and route into

b.

Install the cable

c.

Connect the cables to the aileron

Safety d.

wire the

retaining pins

screws

in the

pulley

position (Ref. Figure 204).

brackets.

quadrant regulator by installing

with 0.032 inch diameter

Connect the cable sections at the turnbuckles

safety

on

Rig

f.

Install all floor

Page

locking plates

and

attaching

screws.

or

filled with grease

(Item

No. i, Chart 2,

27-00-00) for

protection.

the cables

e.

the cable

wire.

the vertical member of the control column.

NOTE: The interior of all turnbuckles should be coated corrosion

Refer to

as

outlined under AILERON CONTROL SYSTEM RIGGING.

panels and

seats.

21027-1 0-00

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

HINGE POINT

3/161N RIG PIN HOLE

WS215

WS209

D

E

TURNBUCKLE SAFTEY CLIPS WS187 D,,,,

B DETAIL

INBOARD BELLCRANK

WS146

C

PRESSURE SEAL

D

STOPBOLTS RIG PIN HOLE

BL108

C

3/16 IN. CABLES

BL27

A)

O FS235

O HINGE POINT

3/16 IN. CABLES

FS125

A

B

i

FS158 FS143

1I81N.CABLES BL108

D,,,,

FS107

E

OUTBOARD BELL CRANK

WS146

WS187 WS209

A

WS215

CONTROL COLUMN CHAIN SAFETYING

TYPICAL 3 PLACES

FL27s 985255A8.A1

Aileron Control

Figure

A25

System

204

27I1 o-oo

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Page

212;e"b"; o’g~

27110100

Page Intentionally Left

Blank

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AILERON CABLE REMOVAL a.

Remove all

(WING)

inspection plates on the underside of the outboard wing panel and rear spar (Ref. Figure 204).

center section

immediately

forward of the b.

Remove the passenger seats just forward of the rear spar as necessary to gain access to the floor remove the floor panels for access to the aileron quadrant regulator and cables.

c.

Remove the pressure seals and cable

d.

Disconnect the cables at the turnbuckles in the wheel well and attach lead lines to the cable ends of both the

panels and

retaining pins.

inboa~d and outboard cables. e.

Disconnect the outboard cables at the bellcrank in the outboard

f.

Disconnect the inboard aileron cable

g.

Pull the cables through the access openings at the outboard wing bellcrank and at the just forward of the rear spar in the fuselage. Detach the lead lines from the cables.

locking plates

NOTE: The aileron cables from the inboard

outboard bellcranks

are

quadrant regulator

interchangeable.

not

from the

wing panel.

quadrant regulator just forward of the aileron

rear

spar.

quadrant regulator

to the turnbuckles and from the turnbuckles to the

Each cable should be identified for correct location

prior

to

removal.

AILERON CONTROL SYSTEM RIGGING NOTE: When

rigged, the push-pull rods.

Disconnect the

a.

of the

rear

threads of the rod end

must be visible in the

autopilot cables from the aileron quadrant regulator below by removing the screws and the cable locking plates.

inspection

holes in the ends of the

the cabin floorboards and

just

forward

spar

Install the aileron travel board

b.

bearings

(Item No. 1, Chart 1,27-00-00)

at

wing

station 236.293

using

the

existing

hardware. c.

With both aileron and

wing cables disconnected from the outboard wing bellcranks, install rig pins in the bellcranks rig the ailerons to neutral position (O" 1/2" up, 1" down from O" on the travel board). Remove the rig pins

and set the surface stops for 24" NOTE: With the

hinge

range without d.

Rig

Rig

a

Install the

f.

must move

on

the travel board.

freely through

the full up and down travel

binding. assembly that interconnects the pilot’s and the copilot’s pounds. The control wheels should align within 1/2".

controls at the control

tension of 10 +15 -0

the control

the cables

2" -1" down from O"

properly tightened, both ailerons

the aileron chain and cable

column to e.

bolts

2" -1" up and 16"

so

column-to-quadrant regulator cables (fuselage) to the proper tension (Ref. Figure 205). Adjust position when proper tension is obtained.

that the control wheels will be in neutral

rig pins in the quadrant regulator and both outboard wing bellcranks. Tighten the four wing cable evenly in small increments until the quadrant regulator pointers are aligned to the correct indications Figure 206.

turnbuckles shown in NOTE:

Rigging

should be

accomplished only

after

a

temperature normalization has been achieved. DO NOT RIG

THE CABLES WHEN THE AIRPLANE IS UNDER DIRECT SUNLIGHT.

n25

27-1 0-00

Page

beF312

1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

g.

wing cable system by strumming the wing cables to remove any circuit friction and to quadrant regulator springs to balance cable tensions. If required, readjust the turnbuckles to realign quadrant regulator pointer.

Vibrate the entire aileron allow the the

h.

wing and apply a side load to move the corresponding quadrant pointer rig position. (This should be smooth and even.) Repeat this loading on approximately the opposite wing cables. Both pointers should realign at the initial rig position. Readjust the turnbuckles as required to eliminate uneven rigging. Grasp both aileron wing

cables of

one

0.25 inch from the initial

i.

quadrant brake mechanism is working properly, remove the rig pins from the system and through the entire aileron travel while simultaneously checking visually that the quadrant regulator pointers do not travel along the compensation scale. Movement would indicate that the quadrant regulator is not compensating (not maintaining constant rig tension). Any quadrant regulator not compensating must be removed from the airplane and returned to the manufacturer.

To make move a

j.

sure

that the

control wheel

Readjust,

if

required,

and

safety wire the

2" -1" up and 1 6" 2" -1" down per step c. The surface stops for 24" on each aileron and the difference between full up and full down

difference between full up and full down travel travel on opposite ailerons should be 8" rt 10. k.

With the

WARNING:

installed and rigged to proper tension, the force of neutral shall not exceed 25 +5 -10 inch-pounds.

system completely

10" to the left

or

right

Visually

check that the aileron movement

i.

Secure all turnbuckles with the

m.

Make

sure

1.

step of

A

corresponds

required

to

move

the control wheel

to the control wheel movement.

safety clips.

that the aileron installation is within the

following

limitations:

up to 0.50 inch is allowable between the outboard

flap

and the aileron at the

trailing edge

with the

flap trailing edge below the aileron trailing edge. 2.

The gap between the edge of the outboard flap and the aileron should be 0.19 +0.21/-0.09 inch constant to within 0.06 inch, except in the forward area where the aileron tapers outboard.

3.

The contour of the aileron may be 0.15 inch above

4.

The aileron and the aileron

rig pin

in the bellcrank and

n.

Install the aileron

o.

Rig the autopilot servo Chapter22-10-01).

NOTE: This

Page

servo

completes

the

or

below the contour of the

wing

on one or

both sides.

linkage may have up to 0.06 inch free play at the aileron trailing edge, 3 to 5-pound force applied perpendicular to the aileron trailing edge.

with the

a

cables for the

applicable autopilot system (Ref. Chapter 22-10-00

cables in accordance with the

rigging procedures

21427-1 0-00

or

Chapter 22-10-01).

applicable autopilot system (Ref. Chapter

for the entire aileron control

22-10-00

or

system.

n25

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

so

40 o

g

so O

alo

lo

20

30

40

70

60

50

90

so

100

TEMPERATURE In ’F

Aileron Cable Tension

Figure

110

300601-10

Graph (Fuselage)

205

HOT MARK .20

i ~;F

.95

lir

.05O .19

a

_

COU) MARK

10

90

30

40

50

90

70

80

90

100

110

fEMPERATUAE IN P

Aileron Ouadrant

A25

Regulator Cable Tension Adjustment Graph Figure 206

27-1 0-00

Page

beF512

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AILERON CABLE INSTALLA TION NOTE:

I

(WING)

a used cable is installed, the cable should be dipped in corrosion preventive compound (Item No. 13, Chart 2, 27-00-00). The excess should be removed by wiping with a clean rag. Refer Chapter 20-04-00 for control cable and pulley inspection requirements.

If

a.

Attach the inboard and outboard cables to the lead lines and route the cables into

b.

Attach the outboard cables to the bellcranks in the outboard

c.

Connect the inboard cables to the inboard

installing

the cable

locking plates

with the

to

position. (Ref. Figure 204).

wing panels.

quadrant regulator in the fuselage just forward attaching screws. Safety the screws with 0.032

of the rear spar by inch diameter safety

wire. d.

Connect the inboard and outboard cable sections at the turnbuckles in the wheel wells.

NOTE: The interior of all turnbuckles should be coated corrosion e.

Install the cable

f.

Using

solvent

Lubricate to g.

or

filled with grease

(Item

No. i, Chart 2,

27-00-00)

for

protection. retaining pins

pulley

brackets.

No. 2, Chart 2, 27-00-00), clean the control cables for the length of travel beyond the cleaned area with grease (Item No. 1, Chart 2, 27-00-00)

(Item

one

in the

through

the seals.

and install the seals in their

respective

inch

Fill the cable seals with

lubricating grease (Item

No. 1, Chart 2,

27-00-00)

locations. the cables

h.

Rig

i.

Replace all

as

outlined under AILERON CONTROL SYSTEM RIGGING in this

plates, floor panels

access

AILERON TAB REMOVAL

Disconnect the dual tab actuator

b.

Remove the 4

c.

Disconnect the

NOTE: If the

same

hinge the

pushrods

upper and 2

bonding jumper

hinge

a new

If

halves from the

a new

tab is

being installed,

respective positions a.

Position the aileron tab

b.

Fit the tab

hinge

on

on

lower)

which

secure

on

the

airplane,

new

hinge

hinge

remove

halves to the tabs.

the tab from the aileron.

halves may remain attached to the aileron halves should be removed from the aileron and

hinge

tab should be installed.

(LEFT ONL Y) remove

the aileron

both

hinge

hinge

position

on

halves from the

new

aileron tab and install them in their

halves.

the aileron and install the

halves into

each of the 2 tab

the tab

tab is to be installed, the tab

AILERON TAB INSTALLA TION NOTE:

from the tab horns.

cables from each end of the tab and

tab is to be reinstalled

halves. If

new

(2

and seats.

(LEFT ONL Y)

a.

screws

chapter.

the tab,

align

bonding jumper the

screw

cables

on

each end of the tab.

holes and install the 4

attaching

screws

in each

hinge.

Page

27-10-00

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

Connect each of the dual actuator

pushrods individually

to the tab horns and

adjust them chapter.

as

instructed under

AILERON TAB RIGGING and CHECKING AILERON TAB FREE PLAY in this

AILERON TAB CABLE REMOVAL.

(WHEEL

WELL-TO-TAB

a.

Remove the

b.

Remove the left

c.

Disconnect the tab cables at the turnbuckles and connect lead lines to the cable ends.

pilot’s

lead lines for d.

seat and left passenger seats forward of the

CONTROL)

cockpit floorboard and

right

or

Remove the cable

left threads

on

the left floor

rear

spar.

panels forward of the

rear

spar.

Identify

the cables and

the cable ends.

retaining pins, fairleads and

pressure seals in the

fuselage

and the grommets from the

inboard wheel well rib. e.

Pull the cable from the

f.

Remove the cable drum support bracket from the

g.

Remove the nut and

h.

Unwind the cable from the drum, drive the cable lock

structure and detach the lead lines.

airplane

bushing

from the drum shaft and

AILERON TAB CABLE INSTALLA TION NOTE:

pedestal. remove

pin from

(WHEEL

the drum from the shaft. the drum and

WELL-TO-TAB

remove

CONTROL)

If a used cable is installed, the cable should be dipped in corrosion preventive compound (Item No. 13, Chart 2, 27-00-00). The excess should be removed by wiping with a clean rag. Refer Chapter 20-04-00 for control cable and pulley inspection requirements.

a.

Place the exact center of the cable in the slot in the cable drum and insert the lock

b.

The cable must be installed

c.

Set the indicator at O, then install the cable

d.

Install the drum support bracket.

e.

Route the cables, connect the turnbuckles and install the

as

shown in

Figure

207.

guide

corrosion

Using

solvent

through

(Item No. 2, Chart 2, 27-00-00) one

inch

Seal the rubber seals to the metal with sealer

h.

Rig

i.

Replace

the tab cables and access

adjust the indicator

covers, floor

or

beyond

g.

n25

pin.

end of the cable around the drum 2

’/4 turns.

or

retaining pins, fairleads

filled with grease

and

grommets.

(Item No. 1, Chart 2, 27-00-00)

for

protection.

the seals. Lubricate to

all

Wrap each

to

and drum with the short shaft and nut.

NOTE: The interior of all turnbuckles should be coated

f.

the cable.

coverings

as

equivalent, the cleaned

clean the control cables for the area

with grease

length of travel (Item No. 1, Chart 2, 27-00-00).

(Item No. 3, Chart 2, 27-00-00) (Ref. Figure 209,

Detail

B).

I

necessary.

and seats.

27-1 0-00

Page

beF712

1/09

Hawker Beechcraft

Corporation

MANUAL SUPER KING AIR B300/B300C MAINTENANCE

PEDESTAL DRUM: RIGHT HAND THREADED TURNBUCKLE STUD END ACTUATOR DRUM: LEFT HAND THREADED

TURNBUCKLE STUD ENDS

CABLE LOCK PIN

PEDESTAL DRUM: LEFT HAND THREADED TURNBUCKLE STUD ENDS

ACTUATOR DRUM: RIGHT HPIND THREADED TURNBUCKLE STUD ENDS

350-151-22

Aileron Tab Cable

Figure

Page

27-1 0-00

Winding

207

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AILERON TAB ACTUA TOR AND OUTBOARD CABLE REMOVAL Remove the

a.

b.

inspection plates

on

the underside of the Left

wing immediately

forward of the

rear

spar.

Disconnect the tab control cables at the turnbuckles in the wheel well and attach lead lines to the cables.

the cables for

right

or

left threads

on

c.

Remove the cable

d.

Disconnect the tab

e.

Remove the bolts

f.

Remove the actuator and tab control cables from the

retaining pins

from the

pulley

brackets.

rods at the actuator.

push-pull

attaching

Identify

the cable ends.

the actuator to the

rear

spar.

wing through

the actuator

access

hole and detach the lead

lines from the cables. g.

h.

Remove the actuator drum from the actuator. 1.

Remove the

2.

Remove the nut and lock.

3.

Removethethree

4.

Removethecapand spacer.

5.

Removethe

6.

Removethedrumand

safety

wire from the

large

nut over the drum.

boltsfromthecap.

bearing.

keyfromtheactuator.

Slide the cable in the drum to

remove

the cable

keeper

from the drum and

remove

the cable from the actuator

drum.

AILERON TAB ACTUA TOR AND OUTBOARD CABLE INSTALLA TION NOTE: If

a used cable is installed, the cable should be dipped in corrosion preventive compound (Item No. 13, Chart 2, 27-00-00). The excess should be removed by wiping with a clean rag. Refer Chapter 20-04-00 for control cable and pulley inspection requirements.

a.

Set the actuator

b.

Place the cable in the sldt in the actuator drum and slide the cable until the

c.

Starting

screws

A25

at 1/2 full travel.

keeper

at each end of the drum wrap the cable toward the center of the drum.

around the drum 4 1/4

is in

Wrap

place

Install the drum and

2.

Install the

3.

Installthecapand spacer.

4.

Install the three bolts in the cap.

5.

Install the nut and lock.

key

into the

into the

in the drum.

each end of the cable

times, then install the drum in the housing.

1.

bearing

to

housing.

housing.

27-1 0-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

6.

Lockwire the nut to the lock.

NOTE: The actuator rod ends may need to be

adjusted

before the rod end bolts will install without

d.

Install the actuator and connect the tab

e.

Connect the lead lines to the cables and route the cables

pulley f.

rods.

push-pull

through

the

wing.

Install the cable

retaining pins

in the

brackets.

Connect the cables at the turnbuckles and

rig

the cables.

NOTE: The interior of all turnbuckles should be coated corrosion g.

binding.

Install the

Adjust

the indicator if necessary.

filled with grease

or

(Item

No. 1, Chart 2,

27-00-00)

for

protection.

inspection plates.

AILERON TAB INDICA TOR ADJUSTMENT

I

a.

Loosen the setscrew in the side of the trim tab

b.

Removethe knobfromtheshaft.

c.

Raise the indicator dial until it turns

d.

Turn the dial to the desired

e.

Replace

knob and

tighten

adjusting

knob

(Ref. Figure 209).

freely.

position and

lower to engage the reduction gears.

the setscrew.

30

20 o

’O a

10

20

30

40

50

60

70

TEMPERATURE

80

90

100

110

F

984495AA

Aileron Tab Cable Tension

Figure

Page

220

Feb 1/09

27-1 0-00

Graph

208

ORIGINAL As Received

ATP

By

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ACTUATOR

AILERON TAB

TURNBUCKLES

DETAIL

C :d

B

AILERON

CENTER LINE

AILERON TAB ACTUATOR ASSEMBLY

F.S. 235

A

DETP~1L

BL27

D

ETONELBAC

CHECK AILERON TRIM TAB TENSION AT W.S.148

W.S.95

b E

W.S.168 F.S. 105

FILL WITH MIL-S-8802

SEALANT BETWEEN SEALS

(BOTH SIDES)

W.S.195

AILERON TRIM TAB CONTROL

TAB CONTROL STOPS OETAIL

A

DETPIIL

E

CABLE PRESSURE SEALS

DETAIL

B

FLPIB

985254/\8.*1

Aileron Tab

Control-System Figure 209

A25

27-1 0-00

Page 221 Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Page

27-1 0-00

Page Intentionally

Left Blank

A25

Hawker Beechcraft Corporation SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AILERON TAB RIGGING NOTE: Do not connect the

actuating components

of the

autopilot until all flight

control

systems have been properly

rigged. Before

the aileron tab, the ailerons must be

rigging

a.

Disconnect the tab horns from both

b.

Install the aileron control lock.

c.

Set the tab control wheel

d.

Adjust

each actuator

so

e.

pushrods of the dual

actuator

(Ref. Figure 209).

1

that the tab indicator reads O.

linkage individually

of the dual actuators. After

properly rigged.

adjustment,

until the tab is in the neutral

connect both actuator

position (O" linkages to the tab

on

the travel

horns

board) for each (Ref. Figure 208).

the aileron tab travel to 15" ~1 1/2" up and 15" f 1 1/2" down from the 0" position on the travel board. adjustments with the cable stops (Ref. Figure 209, Detail E) in the left wheel well. Tighten the cable

Adjust

Make the

to 33-40 inch

pounds and safety with P/N MS24665-5 cotter pins. Refer to Chapter 27-00-00, Figure 1, adapter. A 3/8 inch drive socket can be modified to engage the slots on the cable stop castellated nut allowing the use of a 3/8 inch drive torque wrench for torquing purposes. The modified socket can be used as a torque adapter instead of the tool (Ref. Chapter 27-00-00, Figure 1) stops

for the torque wrench

CAUTION: Make certain the cable stays in the groove in the cable stops while tightening the nut on the stop. Cotter pins must not protrude far enough to snag adjacent components during operation of the cable. f.

Perform

a

visual check to make

tab indicator:

right wing

up, tab

sure

the aileron tab movement

NOTE: With the aileron tab set at neutral, 1/2" of cause

corresponds

to the movement indicated on the

down; left wing up, tab up. servo

the tab to exceed its maximum travel

travel is

acceptable, provided

setting

at full up

or

in

Chapter

5-00-00.

that the

servo

effect does not

full down trim tab and full up

or

full down

aileron.

CHECKING AILERON TAB FREE PLA Y The aileron tab should be A check fixture

push-pull

scale

to the tabs

are

(P/N

at intervals

45-135030-9)

specified

the

equivalent (Ref. Chapter 27-00-00, Figure 2), a dial indicator and a 1,27-00-00) for applying accurate loading inspection for free play of the tabs. or

No. 12, Chart 1, 27-00-00 and Item No. 13, Chart

required

for

making

the

lock the control surfaces to prevent movement of the ailerons. Set the aileron tabs in the neutral

a.

Securely position.

b.

Using hinge

line and

Apply

a

c.

810

(Item

inspected

shot

bags, affix

small

on

the dial indicator check fixture

the outboard

piece

of

edge

so

that the dial indicator

point

is 2.50 inches aft of the tab

of the aileron tab.

masking tape (for paint protection) 2.50 inches aft of the tab hinge line and along point of pressure against the tab by the push-pull scale.

the

centerline of the tab actuator. This will be the

d.

Apply

another

piece of masking tape

in the

corresponding position

on

the bottom surf ace of the tab for the

purpose. e.

n25

Zero the dial indicator at

no

load

initially. Do

not reset

during

the

checking procedure.

27-1 0-00

same

1

Mawker Beechcraft

Corporation

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

f.

With the

reading

push-pull as

point of masking tape, apply

scale at the

g.

Release half the load until

h.

Apply

i.

Release half the load until

a

j.

Enter the recorded values

on a

a

full

a

3-pound-upward

8

load at the

2 and record

3-pound-downward

load. Record the dial

Subtract A from 28 and record

3.

Multiply

4.

Subtract C from 28 and record

2 and record

as

Add X and Y and record

as

as

the bottom surface. Record the dial

is obtained. Record the dial

proceed

as

reading

as

8.

reading

as

C.

D.

follows:

as

X.

28.

can

as

on

reading

28.

2.

by

masking tape

copy of Chart 201 and

NOTE: The results of X and Y

k.

full

load is obtained. Record the dial

1.5-pound-upward load

Multiply

D

by

1.5-pound-downward

1.

5.

a

A.

as

Y.

be

negative

number.

E.

If deflection of the tab is within the allowable limits for both actuator

linkages,

the tab and its

linkages

are

in

good

condition. I.

If the free

play

is excessive, disconnect the trim tab actuator rods and

indications of excessive

Page

beF42

1/09

wear.

Replace excessively

27-1 0-00

worn

visually inspect

the bolts and

bushing

for

parts.

n25

Hawker Beechcraft

Corporation

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

Chart 201 Aileron Tab Free

Play Limits,

E

DESCRIPTION

READING/CALCULATION

A, dial reading with 3-pound downward load applied

on

B, dial reading with 1.5-pound downward load applied C, dial reading with 3-pound upward load applied

on

D, dial reading with 1.5-pound upward load applied

aileron tab.

on

aileron tab.

aileron tab.

on

aileron tab.

A=

8=

C=

D=

28, calculation result of multiplying 8 by 2.

28

X, calculation result of subtracting A from 28.

X

28, calculation result of multiplying D by 2.

28

Y, calculation result of subtracting C from 28.

Y

E, calculation result of adding X and Y.

E=X+Y=

8

x

28

D

28

2=

A

x

2

C

NOTE Maximum Allowable Aileron Tab Free

A25

Play Limits, E~,,

0.053 inch.

27-1 0-00

1/09

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 27-20-00

RUDDER AND TAB - MAINTENANCE PRACTICES WARNING: Any time push-pull rods are installed or adjusted, the inspection holes near the ends of the rods must be checked to ascertain that the threads of the end fittings are visible. The threads MUST be visible in the holes.

RUDDER REMOVAL a. Remove the tail cone. b. Disconnect the push-pull rods at the double clevis ends which connect to the rudder tab horns (Ref. Figure 201). NOTE: The double clevis ends on the tab push-pull rods are designed to tighten the inside clevis with a binding action against the clevis bolt and the outside clevis, which removes free play of the bolt in the hole. Loosen the inner clevis first (the small nut forward of the larger nut) before removing the clevis bolt. c.

Remove the bonding cables.

d. Remove the three bolts, washers and nuts which attach the rudder torque tube to the rudder control horn. NOTE: Observe the number and position of the shims. e. Support the rudder and remove the bolts which attach the two upper hinge brackets to the vertical stabilizer. There are four bolts for each bracket. Remove the rudder from the airplane.

RUDDER INSTALLATION NOTE: Any repair, modification, painting or replacement of the rudder or the rudder tab requires rebalancing. Refer to Chapter 55-40-00 for these procedures. a. Carefully place the rudder in position. The rudder tab actuator rods must be guided through the rudder. Loosely install the bolts in the upper hinge brackets (Ref. Figure 201). b. Install the laminated shims between the rudder torque tube and the rudder control horn. They should be installed in such a manner as to provide a snug fit between the torque tube and the control horn, and maintain the rudder within ±0.06 inch of the true vertical position with respect to the centerline of the rudder hinge supports. NOTE: Any combination of 0.003 or 0.062-inch laminated shims may be used. The maximum total thickness for the shim material should not exceed 0.190 inch. c.

When the conditions noted in step b are obtained, install the bolts, washers and nuts which attach the torque tube to the control horn. Tighten the nuts to 50 to 70 inch-pounds and secure with safety wire. Apply torque paint to the threads and nuts.

NOTE: After tightening, the bolts shall not rotate in their holes under 24-35 inch-pounds of torque applied to the bolt. d. Tighten the bolts on the upper two hinge brackets to 37 to 47 inch-pounds and safety with cotter pins. NOTE: If it was necessary to remove the hinge bracket from the rudder assembly for balancing, the nuts should be tightened to 40 to 50 inch-pounds and safetied with cotter pins. After tightening, the bolts shall not rotate under 15-20 inch-pounds of torque applied to the bolt. It is permissible to tighten up to 60 inch-pounds in order to advance the nut for cotter pin alignment. Do not loosen the nuts for cotter pin alignment. If torque requirements cannot be met, it may be necessary to add or remove washers as required to obtain proper torque values and achieve cotter pin alignment.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL e. Install the bonding cables. f.

Reconnect and tighten the rudder tab push-pull rod clevises.

g. Install the tail cone. NOTE: Tighten the large nut of the double clevis first, then the small nut. h. Check the rudder and tab for proper rigging as outlined in the RUDDER CONTROL SYSTEM RIGGING and RUDDER TAB SYSTEM RIGGING procedures in this chapter, then secure the turn buckles with the safety clips. NOTE: The interior of all turnbuckles should be coated or filled with grease (1, Chart 2, 27-00-00) for corrosion protection. i.

Verify that the installation is within the following limitations. 1. A gap of 0.10 ±0.06 inch should exist between the trailing edge skin of the vertical stabilizer and the rudder nose with the rudder deflected to full travel towards that edge. 2. The minimum gap between the top edge of the rudder and the empennage should be 0.12 inch. 3. The gap between the lower edge of the rudder and tab and the tail cone should be 0.12 to 0.38 inch.

NOTE: It is permissible to trim the edge of the rudder or tab 0.06 inch in order to achieve the distances noted. If trimming is required, the rudder should be checked for balance.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Rudder Installation and Removal Figure 201

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RUDDER CABLE REMOVAL a. Remove all left seats and access panels, aft fuselage access panels and tail cone. b. Remove the rudder servo cables from the forward rudder cables. Refer to Chapter 22-10-00 for the proper procedures. c.

Disconnect the cables at the turnbuckles, tag and identify lead lines and connect lead lines to the aft ends of the forward cables.

d. Remove the cable retaining pins from the pulley brackets and the pressure seals from the aft pressure bulkhead. NOTE: It may be necessary to remove the pulley if cable passage is restricted. e. Disconnect the forward cables from the forward bellcrank and pull the cables out through the crew compartment. f.

Disconnect the lead lines from the forward cables.

g. Disconnect the aft cables from the aft rudder bellcrank and remove them.

RUDDER CABLE INSTALLATION NOTE: If a used cable is installed, the cable should be dipped in corrosion preventive compound (13, Chart 2, 2700-00). The excess should be removed by wiping with a clean rag. Refer to Chapter 20-04-00 for control cable and pulley inspection requirements. a. Identify the forward rudder cables, attach them to the lead lines and pull them into position. b. Attach the forward rudder cables to the forward bellcrank and install the cable retaining pins in the pulley brackets. Reinstall any pulleys that have been taken out to facilitate removal of the cables. NOTE: Refer to Figure 202, Detail G, for the proper cable safetying method. c.

Disconnect the lead lines.

d. Attach the aft rudder cables to the aft rudder bellcrank, route the cables through the aft fuselage and attach the turnbuckles. NOTE: The interior of all turnbuckles should be coated or filled with grease (1, Chart 2, 27-00-00) for corrosion protection. e. Using solvent (2, Chart 2, 27-00-00), clean the control cables for the length of travel through the seals. Lubricate to one inch beyond the cleaned area with grease (1, Chart 2, 27-00-00). f.

Fill the cable seals with (1, Chart 2, 27-00-00) grease and install the seals in their proper location.

g. Rig the rudder control system as outlined in the RUDDER CONTROL SYSTEM RIGGING procedures in this chapter, then secure the turnbuckles with safety clips. h. Connect the rudder servo cable to the forward rudder cable in accordance with the procedures for RUDDER SERVO CABLE INSTALLATION in Chapter 22-10-00. i.

Rig the rudder servo cables in accordance with the procedures for AUTOPILOT CONTROL SYSTEM RIGGING noted in Chapter 22-10-00.

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Rudder Control System Figure 202

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RUDDER CONTROL SYSTEM RIGGING NOTE: Do not connect the actuating components of the autopilot until all flight control systems have been properly rigged. The airplane must be placed on jacks before the rudder can be rigged. This will permit rudder forces to be measured properly. a. Remove the radio antenna from the right side of the vertical stabilizer. b. Install the rudder travel board (P/N 807 101-630000-1, Figure 1, 27-00-00) at vertical canted station 39.289. The travel board is installed in the bolt holes used for the antenna. c.

Install a rig pin in front rudder bellcrank and a rig pin in the rig pin hole in the aft bellcrank torque shaft assembly.

d. Disconnect the rudder tab actuator push-pull rod (do not change adjustment of the rod) and align the tab trailing edge with the rudder trailing edge. NOTE: The double clevis ends on the tab actuator push-pull rods are designed to tighten the inside clevis with a binding action against the clevis bolt and the outside clevis, which removes free play of the bolt in the hole. Loosen the inner clevis first (the small nut forward of the larger nut) before removing the clevis bolt. e. Disconnect rudder push-pull rod from the rudder control horn. f.

Adjust the rudder stops for a deflection of 25° +1 -0 left and right of neutral (or 0 on the travel board). Tighten the locknuts on the stops.

g. Rig the rudder cables to the tension shown in Figure 203. h. Center the rudder at 0 on the travel board, adjust the rudder control horn push-pull rod accordingly, tighten the locknut and reconnect it to the control horn. i.

Remove both rig pins.

j.

Set the rudder stops at the forward bellcrank for a clearance of 0.38 +0.06 -0 inch. Tighten the locknuts.

k.

Using a hand force gage, check for a maximum of 20 pounds of pedal force in the full forward and full aft positions on both rudder pedals.

NOTE: Pedal forces must be measured at the gust lock hole in the rudder pedal arm (7" radius arm). Limits must be met with either pair of rudder pedals in both full forward and full aft adjustment positions. There should be no sudden changes in force due to friction or interferences in the system. l.

Reconnect and tighten the rudder tab clevis.

NOTE: Tighten the large nut of the double clevis first, then the small nut. m. This completes the rigging of the primary portion of the rudder control system. Verify that the rudder installation is within the following limitations: 1. The gap at the leading edge of the rudder measured between the vertical stabilizer skin trailing edge and the nose of the rudder when the rudder is deflected full left and right shall be 0.10 ±0.06 inch. 2. The minimum gap between the top edge of the rudder and the empennage should be 0.12 inch. 3. The gap between the lower edge of the rudder and tab and the tail cone should be 0.12 to 0.38 inch.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Rudder Cable Tension Graph Figure 203 n. Rig the rudder tab system as indicated in the RUDDER TAB SYSTEM RIGGING procedures in this chapter. o. Connect the rudder servo cable to the forward rudder cable in accordance with the procedures for RUDDER SERVO CABLE INSTALLATION in Chapter 22-10-00. p. Rig the rudder servo cables in accordance with the procedures for AUTOPILOT CONTROL SYSTEM RIGGING noted in Chapter 22-10-00. q. Remove the travel board, reinstall the antenna, seats, access panels and tail cone.

RUDDER PEDAL AND BELLCRANK REMOVAL a. Remove the floorboards forward of the pilot’s and copilot’s seats. b. Remove the nonadjustable push-pull tubes connecting the idler arms and bellcranks. c.

Disconnect the nose steering push-pull rod at the arm to the right of the pilot’s right rudder pedal.

d. Remove the bolts securing the inboard collars on both rudder pedal cross-shafts. e. Disconnect the brake master cylinders from the rudder pedals. f.

Remove the taper pins securing the cross-shaft supports (inboard of each shaft).

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A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL g. Pull the cross-shaft inboard until it is free of the outboard supports. h. Lift the rudder pedals up and out. NOTE: Note the proper position of the idler arms, pedals and collars on the shaft before removing the rudder pedals. These positions must be maintained to assure proper operation when the pedals are installed. i.

Release tension on rudder cables and disconnect the cables from the pilot’s bellcrank.

j.

Remove the adjustable push-pull tube connecting the bellcranks.

k.

Remove the bolts attaching the bellcranks to the brackets and remove the bellcranks.

RUDDER PEDAL AND BELLCRANK INSTALLATION a. Place the bellcranks in their respective positions and install the attaching bolts. b. Install the adjustable push-pull tube connecting the bellcranks. c.

Place the pilot’s and copilot’s rudder pedals in position with the collar and idler arms and slide the shafts into their outboard supports.

d. Secure the inboard supports with their attaching screws. e. Replace the taper pins securing the inboard collars on each of the cross-shafts and tighten to 15-20 inchpounds. Make certain that the small end of the taper pin is at least flush with, but not more than 0.06 inch above the surface. CAUTION: Excessive driving of the taper pin can cause cracks in the tubing and/or casing. A lightweight rawhide or nylon mallet should be used to set the taper pin when it is installed. f.

Connect the brake master cylinders.

g. Install the nonadjustable push-pull tubes from the pedals to the bellcranks. h. Connect the nose steering push-pull rod. i.

Connect the cables to the bellcrank. Refer to Figure 202, Detail G, for the proper safetying procedure.

j.

Rig the rudder control system as indicated in the RUDDER CONTROL SYSTEM RIGGING procedures in this chapter.

k.

Depress the adjustment lever adjacent to each pedal and push the pedal forward until contact is made with the stop lug on the idler arm.

l.

Release the pedal and adjustment lever, then check that the spherical end of the adjustment pin enters the index hole in the idler arm.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RUDDER PEDAL INSPECTION AND REPAIR Inspect all four rudder pedal arms at the intervals specified in Chapter 5. MAGNESIUM RUDDER PEDAL ARMS This procedure is applicable to magnesium rudder pedal arms only. If the rudder pedal arms are manufactured of aluminum, “ALUM” will be cast into the side of the rudder pedal arm and this procedure will not be applicable. a. Remove the two bolts that secure the brake pedal to the rudder pedal arm. b. Inspect the bushings in the rudder pedal arm for looseness (Loose is defined as any movement) (Ref. Figure 204). If the bushings are tight proceed to step f. c.

If a bushing is loose, remove the bushing and measure the wall thickness of the casting. If the thickness at any point is less than 0.080 inch, remove and replace the rudder pedal arm. Refer to Detail B of Figure 204.

d. Arms with loose bushings that meet the wall thickness requirements may be reworked if the distance between the bushing and casting wall does not exceed 0.015 inch. If more than 0.015 inch, replace the rudder pedal arm. Refer to Detail C of Figure 204. e. Loose bushings that meet the requirements of steps c and d may be secured in position with Loctite. NOTE: Use retaining compound (10, Chart 2, 27-00-00) and primer (11, Chart 2, 27-00-00) to secure the bushing. Allow the retaining compound to fully cure before assembling the brake pedal to the rudder pedal arm. The minimum cure time is 24 hours at 70 °F or 30 minutes at 250 °F. When the retaining compound is first applied, hold the bushing in place without moving for 5 minutes. f.

If the bushing is tight, the minimum wall thickness of the bushing and casting shall not be less than 0.094 inch. If less than 0.094 inch at any one point, replace the rudder arm.

NOTE: Before assembly lubricate the attaching bolts with a light coat of grease (5, Chart 2, 27-00-00). g. After proper cure of the Loctite (if applicable) reassemble the rudder pedal and brake pedal arm assembly.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Magnesium Rudder Pedal Arm Bushing Inspection and Repair Figure 204

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL ALUMINUM RUDDER PEDAL ARMS (UNBUSHED) This procedure is applicable to aluminum rudder pedal arms (unbushed) only, as indicated by the letters “ALUM” cast into the side of the rudder pedal arm. If the rudder pedal arms are manufactured of magnesium, this procedure will not be applicable. a. Remove the two bolts that secure the brake pedal to the rudder pedal arm. b. Inspect the attach holes for elongation or excessive wear. Measure the wall thickness of the arm casting, if the thickness at any point is less than 0.130 inch, continue with this procedure. Refer to Figure 205, Detail A. If the wall thickness is in tolerance, proceed to step g. c.

Perform the PILOT or CO-PILOT RUDDER PEDAL AND BELLCRANK REMOVAL procedure.

d. Ream the hole out to 0.249 - 0.250 inch diameter. Figure 205, Detail B. e. Install a P/N 105740X-ZF-0250 bushing with retaining compound (10, Chart 2, 27-00-00). Before applying the retaining compound, clean the mating surfaces of the bushing and arm with primer (11, Chart 2, 27-00-00). NOTE: Allow the retaining compound to fully cure before assembling the brake pedal to the rudder pedal arm. The minimum cure time is 24 hours at 70° F or 30 minutes at 250° F. Hold the bushing in place for five minutes after inserting it in position in the rudder pedal arm. f.

Perform the PILOT or CO-PILOT RUDDER PEDAL AND BELLCRANK INSTALLATION procedure.

g. After the retaining compound has cured properly (if applicable), reassemble the rudder pedal and brake pedal arm assembly. NOTE: Before assembly, lubricate the attaching bolts with a light coat of grease (5, Chart 2, 27-00-00).

RUDDER TAB REMOVAL a. Disconnect the dual tab actuator pushrods from the rudder tab horns. b. Push the rudder to one side of the tail cone and disconnect the bond jumper cable from the bottom of the tab. c.

Remove the screw which secures the hinge pin at the bottom of the rudder tab, carefully pull the pin out of the hinge, and remove the tab from the rudder.

RUDDER TAB INSTALLATION a. Lubricate the hinge pin and the hinge with Brayco 300 in accordance with the LUBRICATION CHART in Chapter 12-20-00. b. Position the tab on the rudder and carefully install the hinge pin. c.

Install the screw in the bottom of the rudder tab to secure the hinge pin in place. Install the bonding jumper cable in the bottom of the tab.

d. Reinstall the rudder tab actuator pushrods individually on the tab horns and adjust them as instructed under RUDDER TAB SYSTEM RIGGING and CHECKING RUDDER TAB FREE PLAY in this chapter.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A B RUDDER PEDAL ARM

INSPECT FOR THE CASTING WALL THICKNESS 0.130 INCH MIN.

BUSHING

REAMED HOLE 0.249-0.250 INCH DIA.

DETAIL

A

DETAIL

B

BB27B 985253AA

Aluminum Rudder Pedal Arm (Unbushed) Inspection and Repair Figure 205

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FORWARD RUDDER TAB CABLE REMOVAL a. Remove all left seats and access panels, the toilet, the aft fuselage access panels and the belly access door below the pedestal. b. Remove the cable retaining pins, fairleads and cable seals. c.

Disconnect the cables at the turnbuckles and connect lead lines to the forward cable ends. Tag the lead lines to identify them for left or right tab movement to assure proper rerouting of the cables.

d. Pull the cables forward through the access opening below the pedestal. e. Remove the forward and side access panels from the pedestal. f.

Remove the nut from the rudder tab control shaft, then remove the bolt securing the control wheel to the shaft. Remove the shaft and the indicator drive gear.

NOTE: To prevent “backlash” of the cable around the drum, tape the two cables together before removal or reinstallation of the drum in the pedestal. g. Remove the cable retaining pins from the pedestal pulley brackets, and pull the drum and cable from the pedestal. h. Unwind the cable from the drum and remove the cable lock pin.

FORWARD RUDDER TAB CABLE INSTALLATION NOTE: If a used cable is installed, the cable should be dipped in corrosion preventive compound (13, Chart 2, 2700-00). The excess should be removed by wiping with a clean rag. Refer to Chapter 20-04-00 for control cable and pulley inspection requirements. a. Place the exact center of the cable in the drum slot and install the cable lock pin. Install the cable as shown in Figure 206. Wrap each end of the cable around the drum 2-1/4 turns. b. Set the indicator at 0, position the drum and cable guide and install the control wheel, shaft and indicator drive gear. c.

Identify the cables, attach the lead lines to them and route into position in the fuselage. Install the pulley bracket cable retaining pins, fairleads and seals. Remove the lead lines and connect the turnbuckles.

NOTE: The interior of all turnbuckles should be coated or filled with grease (1, Chart 2, 27-00-00) for corrosion protection. d. Using solvent (2, Chart 2, 27-00-00), clean the control cables for the length of travel through the pressure seals. Lubricate to one inch beyond the cleaned area with grease (1, Chart 2, 27-00-00). e. Fill the cable seals with grease (1, Chart 2, 27-00-00) and install. f.

Seal the rubber seals to the metal with sealer (3, Chart 2, 27-00-00). Refer to Figure 207, Detail C.

g. Rig the rudder tab system as indicated in the RUDDER TAB SYSTEM RIGGING procedures in this chapter, then secure the turnbuckles with the safety clips. h. Replace all seats and access panels.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Rudder Tab Cable Winding Figure 206

RUDDER TAB ACTUATOR AND CABLE REMOVAL a. Remove the aft fuselage access panels and actuator access plate on the vertical stabilizer. b. Disconnect the rudder tab cables at the turnbuckles in the aft fuselage. Identify and attach lead lines to the actuator cable ends. c.

Remove the cable retaining pins in the pulley brackets.

d. Disconnect the double clevises on the push-pull rods at the rudder trim tab. NOTE: The double clevis ends on the tab actuator push-pull rods are designed to tighten the inside clevis with a binding action against the clevis bolt and the outside clevis, which removes free play of the bolt in the hole. Loosen the inner clevis first (the small nut forward of the larger nut) before removing the clevis bolt. e. Remove the actuator mounting bolts and remove the actuator and cables through the access hole. f.

Disconnect the lead lines.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

REPLACING THE RUDDER TAB ACTUATOR CABLES NOTE: If a used cable is installed, the cable should be dipped in corrosion preventive compound (13, Chart 2, 2700-00). The excess should be removed by wiping with a clean rag. Refer to Chapter 20-04-00 for control cable and pulley inspection requirements. a. Remove the cable drum from the actuator as follows: 1. Remove the lockwire from the nut and lock located over the drum. 2. Remove the nut and lock. 3. Remove the three bolts from the cap. 4. Remove the cap and spacer. 5. Remove the bearing. 6. Remove the drum and key. b. Lift the drum from the housing and unwind the cable. c.

Slide the cable in the drum until the keeper is free of the drum and remove the cable.

d. Install the cable in the actuator as follows: 1. Place the cable in the drum and slide the cable until the keeper in place in the drum. 2. Wrap the cable 4 1/4 turns around the drum from the ends to the center. 3. Place the actuator in the center of its travel. 4. Install the drum and key in the housing. 5. Install the bearing. 6. Install the cap and spacer. 7. Install the three bolts which retain the cap. 8. Install the nut and lock. (Do not overtighten). 9. Lockwire the nut to the lock.

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Rudder Tab Control System Figure 207

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27-20-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RUDDER TAB ACTUATOR AND CABLE INSTALLATION a. Working through the vertical stabilizer access hole, mount the actuator with the mounting bolts and secure. b. Identify and connect the lead lines to the cables, route them into position and connect the turnbuckles. NOTE: The interior of all turnbuckles should be coated or filled with grease (1, Chart 2, 27-00-00) for corrosion protection. c.

Reinstall the cable retaining pins in the pulley brackets.

NOTE: Each of the dual actuator push-pull rods must be adjusted individually before connecting permanently to prevent binding. d. Reconnect the rudder tab push-pull rod clevises to the rudder tab horns. NOTE: Tighten the large nut of the double clevis first, then the small nut. e. Rig the rudder tab system as indicated in the RUDDER TAB SYSTEM RIGGING procedures in this chapter, then secure the turnbuckles with the safety clips. f.

Reinstall access covers.

RUDDER TAB INDICATOR ADJUSTMENT Ordinarily the trim tab indicator will correspond to the tab position; however, if proper indication cannot be achieved by adjusting the tab clevis rods, adjustment of the indicator can be accomplished as follows: a. Loosen the setscrew in the side of the trim adjusting knob. b. Remove the knob from the shaft. c.

Raise the indicator dial until it turns freely.

d. Turn the dial to the desired position and reengage the reduction gears. e. Reinstall the knob and tighten the setscrew.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RUDDER TAB SYSTEM RIGGING NOTE: To determine a standard rudder from an improved performance rudder the following observations can be made of the upper trailing edge of the rudder installed. Refer to Figure 209 and Figure 210. •

The standard rudder has a proturbance or bubble extending vertically on the upper side of the trailing edge of the rudder. The bubble is blended into the skin of the rudder and is not riveted.

•

The improved performance rudder has a slightly larger bubble extending vertically on the upper side of the trailing edge of the rudder. The outer edges of the bubble are riveted to the skin of the rudder. A small drain hole is located at the bottom of the bubble. The bubbles trailing edge extends out approximately 1/2 inch from the trailing edge of the rudder.

a. Install a rig pin in the aft rudder bellcrank. b. Disconnect the push-rod clevises from the rudder tab dual actuator. NOTE: The double clevis ends on the tab push-pull rods are designed to tighten the inside clevis with a binding action against the clevis bolt and the outside clevis, which removes the free play of the bolt in the hole. Loosen the inner clevis first (the small nut forward of the larger nut) before removing the clevis bolt. c.

Set the control wheel on the pedestal so the tab indicator reads 0.

d. Rig the cables to the proper tension as shown in Figure 208. e. Actuator screw midpoint travel adjustment. 1.

Standard Rudder (Ref. Figure 209) - Turn the actuator screw until it is positioned at the midpoint of its travel.

2. Improved Performance Rudder (Ref. Figure 210) - Turn the actuator screw until the distance between the actuator housing and the center of the actuator rod end is 2.20 inches (Ref. Figure 207, Detail G). f.

Adjust the clevis rods until the tab is in its neutral position. (Visually align the trim tab trailing edge with the trailing edge of the rudder.) Secure the clevis bolt and tighten the clevis (large nut first, small nut last).

g. Remove the rig pin. h. Using the rudder tab travel board, with the rudder in neutral, adjust the rudder tab travel for a deflection of 15 +1 1/2 - 0° in each direction with the cable stops (See Figure 207, Detail D) in the aft fuselage section. Tighten the nuts on the stops to 35-40 inch-pounds and safety the nuts with P/N MS24665-5 cotter pins. See Figure 1, 27-00-00 for the torque wrench adapter. A 3/8-inch drive socket can be modified to engage the slots on the cable stop castellated nut allowing the use of a 3/8-inch-drive torque wrench for tightening purposes. The modified socket can be used as a torque adapter instead of the tool shown in Figure 1, 27-00-00. CAUTION: Make certain the cable stays in the groove while tightening the nut on the cable stop. Cotter pins must not protrude far enough to snag on adjacent components during cable operation. i.

Visually check that rudder tab movement corresponds to the movements indicated on the tab indicator: “nose left”, tab moves right, “nose right”, tab moves left.

j.

Using the rudder tab travel board, visually check the rudder anti-servo (leading tab) travel as follows:

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A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: A maximum of two (0.040 inch) laminated shims (P/N 130-524031-3) may be used with total thickness reduced to 0.060 inch or less by removing laminations to obtain correct rudder tab travel. Place shim(s) between the adapter and the base of the actuator. Maximum shim thickness is 0.060 inch. Remove laminations from the shim as required. 1.

Standard Rudder (Ref. Figure 209) - The rudder tab should exhibit a 10 ±0.5° anti-servo (leading tab) travel at full right and full left rudder travel with tab set at neutral. If antiservo adjustment is required, laminated shims (P/N 130-524031-3) may be placed between the adapter and the base of the actuator. Adjustment of the actuator is accomplished by removing laminations from the shim as required to obtain the correct antiservo tab position. Maximum shim thickness is 0.060 inch.

2. Improved Performance Rudder (Ref. Figure 210) - The rudder tab should exhibit a 16 ±0.5° anti-servo (leading tab) travel at full right rudder travel with tab set at neutral and 20 ±0.5° anti-servo (leading tab) travel at full left rudder travel with tab set at neutral. If antiservo adjustment is required, laminated shims (P/N 130524031-3) may be placed between the adapter and the base of the actuator. Adjustment of the actuator is accomplished by removing laminations from the shim as required to obtain the correct antiservo tab position. Maximum shim thickness is 0.060 inch.

Rudder Cable Tension Graph Figure 208

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RUDDER TRIM TAB TRAVEL BOARD

RUDDER TRIM TAB

STANDARD RUDDER FL55B 093762AA.AI

Standard Rudder Figure 209

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A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RIVETS

RUDDER TRIM TAB TRAVEL BOARD

DRAIN HOLE

RUDDER TRIM TAB

IMPROVED PERFORMANCE RUDDER

FL55B 093763AA.AI

Improved Performance Rudder Figure 210

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHECKING RUDDER TAB FREE PLAY Visually inspect the rudder tab for any damage, security of hinge attach point and for tightness of the actuating system. Inconsistencies should be remedied prior to checking the free play of the tab. The rudder tab should be inspected as specified in Chapter 5. A check fixture (P/N 810 45-135030-9) or the equivalent as shown in Figure 2 of 27-00-00, dial indicator and a pushpull scale (12 and 13, Chart 1, 27-00-00 for applying accurate loading to the tabs is required for making the inspection for free play of the tab. a. Securely lock the control surfaces to prevent movement of the rudder. Set the rudder tab in the neutral position. b. Tape the dial indicator check fixture to the rudder so that the dial indicator point is positioned 4.50 inches aft of the tab hinge line and at the top edge of the tab. c.

Apply a small piece of masking tape on the left side of the tab (for paint protection) 6.50 inches aft of the tab hinge line and along the centerline of the tab actuator. This will be the point of pressure against the tab by the push-pull scale.

d. Apply another piece of masking tape in the corresponding position on the right surface of the tab for the same purpose. e. Zero the dial indicator at no load initially. Do not reset during the checking procedure. f.

With the push-pull scale at the point of masking tape, apply a full 3-pound-left-side load. Record the dial reading as A.

g. Release half the load until a 1.5-pound-left-side load is obtained. Record the dial reading as B. h. Apply a full 3-pound-right-side load at the masking tape on the right surface. Record the reading as C. i.

Release half the load until a 1.5-pound-right-side load is obtained. Record the reading as D.

j.

Enter the recorded values on a copy of Chart 201 and proceed as follows: 1. Multiply B by 2 and record as 2B. 2. Subtract A from 2B and record as X. 3. Multiply D by 2 and record as 2D. 4. Subtract C from 2D and record as Y. 5. Add X and Y and record as E.

NOTE: The results of X and Y can be negative numbers. k.

If deflection of the tab is within the allowable limit, the tab and its linkage are in good condition.

l.

If the free play is excessive, disconnect the tab actuator rod and visually inspect the bolts and bushings for indications of excessive wear. Replace excessively worn parts.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 Rudder Tab Free Play Limits, E DESCRIPTION

READING/CALCULATION

A, dial reading with 3-pound left-side load applied on rudder tab.

A=

B, dial reading with 1.5-pound left-side load applied on rudder tab.

B=

C, dial reading with 3-pound right-side load applied on rudder tab.

C=

D, dial reading with 1.5-pound right-side load applied on rudder tab.

D=

2B, calculation result of multiplying B by 2.

2B = B x 2 =

X, calculation result of subtracting A from 2B.

X = 2B - A =

2D, calculation result of multiplying D by 2.

2D = D x 2 =

Y, calculation result of subtracting C from 2D.

Y = 2D - C =

E, calculation result of adding X and Y.

E=X+Y= NOTE

Maximum Allowable Rudder Tab Free Play Limits, EMax = 0.020 inch.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 27-21-00

RUDDER BOOST - DESCRIPTION AND OPERATION Rudder boost reduces the rudder pedal force that is required during an “engine out” situation. “Engine out” sensing is based on engine torque from torque transducers on the forward left side of each engine. When differences in engine torque between the engines exceeds a preset level the Flight Control System engages and provides drive voltage to the rudder servo. The drive voltage supplied to the rudder servo is proportional to the differential voltage outputs from the two torque transducers on the engines. This results in the drive voltage increasing proportionally to the split in torque between the two engines. This translates into higher servo torque as the engine torque differential increases. Trimming of the rudder must be achieved by the pilot. The rudder boost is enabled by setting the pedestal mounted control switch, placarded RUDDER BOOST OFF-YAW CONTROL TEST, to the RUDDER BOOST position. The rudder boost system is disabled if the RUDDER BOOST switch is in the OFF position and interrupted when the DISC TRIM/AP YD switch is pushed. An amber caution annunciator, RUD BOOST OFF, is provided on the caution/advisory/status annunciator panel to indicate that the rudder boost control switch is in a position other than RUDDER BOOST (ON).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 100100100 27-21-00

RUDDER BOOST - TROUBLESHOOTING The rudder boost system can be tested by simulating engines running by applying pressure to the torque transducer manifold. A split in voltage outputs from the two rudder boost transducers to the autopilot or rudder boost computer of 0.982 VDC ± 0.08 VDC will cause rudder boost system activation.

RUDDER BOOST SYSTEM a. Remove the engine cowling (Ref. Chapter 71-10-00). b. Connect the torque calibrator (14, Chart 1, 27-00-00) or torque pressure tester (15, Chart 1, 27-00-00) to the rudder boost transducer manifold. c.

Connect a breakout box between the torque transducer and the torque transducer electrical connector.

d. Connect the voltmeter (16, Chart 1, 27-00-00) to the torque transducer via the breakout box (Ref. Figure 101). e. Apply external electrical power to the airplane (Ref. Chapter 24-40-00) f.

Apply pressure to the manifold at a slow steady rate until 60 psi is indicated on the pressure gage. As the pressure rises, record the output voltage for each input pressure setting listed in Chart 101. The output voltage must fall within the range shown in Chart 101 for each specific setting.

g. Slowly reduce the pressure; as the pressure lowers record the output voltage for each input pressure setting listed in Chart 101. The output voltage must fall within the range shown in Chart 101 for each specific setting. Replace any transducer that fails to meet the requirements of this test procedure. h. Bleed the pressure down to 0 psi and disconnect the test equipment. i.

Disconnect external electrical power (Ref. Chapter 24-40-00).

j.

Install the engine cowling (Ref. Chapter 71-10-00).

Chart 101 Rudder Boost Transducer Functional Test Values Reference Pressure (PSI)

A28

Voltmeter Reading (PSI Rising)

Voltmeter Reading (PSI Falling)

Output Tolerance (VDC)

0

+0.450 to +0.550

20

2.116 to 2.216

30

2.950 to 3.050

40

3.783 to 3.883

60

5.450 to 5.550

27-21-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURE GAGE NITROGEN BOTTLE

C + 28 VDC D - 28 VDC (TRANSDUCER GND) A + SIGNAL OUT B - SIGNAL & CASE GND

28 VDC POWER SUPPLY

VOLTMETER FL27B 033708AC.AI

Rudder Boost Transducer Functional Test Schematic Figure 101

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 27-21-00

RUDDER BOOST - MAINTENANCE PRACTICES RUDDER BOOST TRANSDUCER REMOVAL a. Remove all electrical power from the airplane. b. Remove the upper forward engine cowling (Ref. Chapter 71-10-00). c.

Remove the safety wire and disconnect the electrical connector (1) from the torque transducer (3) (Ref. Figure 201).

d. Disconnect the vent line (2) from the transducer (3). e. Remove the torque transducer (3), washer (4) and O-ring (5) from the torque pressure manifold (6).

RUDDER BOOST TRANSDUCER INSTALLATION a. Install a new O-ring (5) and the washer (4) on the torque transducer (3) (Ref. Figure 201). b. Install the torque transducer (3) in the torque pressure manifold (6). c.

Connect the vent line (2) to the torque transducer (3).

d. Connect and safety wire the electrical connector (1) to the torque transducer (3). e. Install the upper forward engine cowling (Ref. Chapter 71-10-00). f.

Restore electrical power to the airplane.

A28

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A

TORQUE PRESSURE MANIFOLD

O-RING

RUDDER BOOST TRANSDUCER

ELECTRICAL CONNECTOR

WASHER

DETAIL

A

VENT LINE FL27B 033685AA.AI

Rudder Boost Transducer Installation Figure 201

Page 202 May 1/10

27-21-00

A28

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELEVATOR AND TAB WARNING:

(PITCH CONTROL)-

MAINTENANCE PRACTICES

Anytime any push-pull rods are installed or adjusted, the inspection hole near the ends of the push-pull rods must be checked to ascertain that the threads of the end fittings are visible. The threads MUST be visible in the holes.

ELEVATOR REMOVAL a.

Remove the

screws

navigation light b.

and

attaching remove

Disconnect the elevator tab

fairing on the vertical stabilizer, disconnect the fairing from the airplane (Ref. Figure 201).

the aft

the

push-pull

electrical

wiring

from the

rods from the tab horns at the aft double devises.

on the tab push-pull rods are designed to tighten the inside clevis with a binding action against the clevis bolt and the outside clevis, which prevents turning of the bolt in the hole. Loosen the inner clevis first (the small nut forward of the larger nut) before removing the clevis bolt.

NOTE: The double clevis ends

c.

Disconnect the elevator push-pull rod from the control horn

d.

Remove the

safety wire, bolt, safety wire

NOTE: Observe the number and

position of

on

the inboard end of the elevator.

bracket and washers which attach the torque tube to support bracket. washers and

position

of the

safety

wire bracket in order to facilitate

reinstallation. e.

f.

Disconnect the bonding cables between the elevator and the horizontal stabilizer.

Support the elevator and remove the nut and washer(s) from the bolt that extends vertically through the portion hinge bracket attached to the elevator. Remove the bolt from each bracket and carefully remove the elevator from the airplane to avoid damage to the elevator or the elevator tab push-pull rod.

of each

NOTE: Removal of the vertical bolt attached to the

while

~21

attaching

the

hinge

clevis to the elevator

hinge bracket will leave pivot point to remain

bracket of the horizontal stabilizer. This will allow the

hinge facilitating removal and

installation

procedures.

27-30-00

the clevis in contact

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELEVATOR CONTROL HORN

BRACKEfELEVATOR HINGE

DETAIL

C

DETAIL

B ’d

BONIDING

DETAIL

CABLES

A 350-(31-5

Elevator Removal and Installation

Figure

Page

tcO202

31106

27-30-00

201

A21

Rayt~eon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTROL

14" 1" O" UP DEFLECTION FROMTHE NEUTRALPOSITION

HORN

.50 INCH

LEFT ELEVATOR CONTROL HORN SVPPORT

MINIMUM

H

fF

LEFT ELEVATOR

CONTROL HORN

INTERCONNECT

~Y

LINK

ELEVATOR CONTROL

A~

HORN STOP BOLTS BALLAST

I

ELEVATOR

WEIGHT DETAIL

D

~JnSINC*BLE

DOWN,

20.+1.-~.00WN

DEFLECTION FROM

STOP BOLT

THE NEUTRAL POSITION

14.75~ .38 INCHES ELEVATORUP

O

j PRESSURE DETAIL

DETAIL

H

BULKHEAD

A

15.12

PROPER CABLE

.06 INCHES

SAFETY METHOD

.12 INCHES

CPIPICAL 4 PLACES)

TURNBUCKLES PUSH ROD

DETAIL

fE

NRNBUCKLES

DETAIL

B

E

ELEVATOR AUTOPILOT

STOP

DETAIL

G

SERVO

RIG PIN

HOLE

BELLCRANK

BOLTS

~CG

STOPS .37~ .08

tINCHES ’1

.37f .06

FS 353

323

STOP BOLTS

INCHES

oO,

~O

ELEVATOR UP

BALLAST ELEVATORDOWN

WEIGHT

FS 301

ELEVATOR FORWARD

BELLCRANK

FS!Og DETAIL

C

~C

B

C

FORWARD

RIG PIN

AFT

BELLCRANK

ELEVATOR UP

HOLE

BELLCRANKS

3/16 IN. CABLE DCTAIL

F

Elevator Control

Figure

A21

System

202

27-30-00

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31/06Page

203

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

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27-30-00

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A21

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELEVA TOR INSTALLA TION NOTE:

a.

Any repair, modification, painting or replacement Chapter 55-20-00 for balancing procedures.

of the elevator

Guide the elevator into

pull

rod. Install the

position on the airplane, taking attaching bolts, washers and nuts.

care

or

require rebalancing. Refer

tab will

to

damage the elevator or the elevator tab pushtighten at this time (Ref. Figure 201). 1

not to

Do not

NOTE: The bolts must be installed with the heads up. b.

Install the bolt, washers and safety wire bracket which secure the torque tube on the inboard end of the elevator support bracket. The safety wire bracket should be installed in the same position as it was removed. A

to the

gap of 0.060 to 0.092 inch must be maintained between the support bracket and the safety wire bracket. Use AN960-516 or AN960-516L washers as required to control the noted gap. It is permissible to install one (1) AN960-516

or

AN960-516L washer between the support bracket and the torque tube. If the latter is done, a place of the NAS1305-22H bolt. When the above conditions are satisfied,

NAS1305-23H bolt must be used in

tighten c.

the bolt to standard torque value.

Safety

the bolt

so

the

safety wire

will

tighten

if the bolt loosens.

If for any reason, the bolts which attach the hinge clevis to the horizontal stabilizer hinge bracket were loosened or replaced (horizontal bolt through the pivot point), they must be tightened to a torque of 40 to 50 inch-pounds.

hinge and work outboard to the outboard hinge. After torquing, the bolt shall not rotate under 15 to 20 inch-pounds of torque applied to the bolt. It is permissible to tighten to 60 inch-pounds if cotter pin holes do not align. Do not loosen the nut to align cotter pin holes. If torque requirements cannot be met, add or remove washers as required and repeat the above procedure.

Start the

d.

procedure

at the inboard

Start the following procedure at the inboard hinge bracket and work outboard to the outboard hinge bracket. Tighten the ve rtical hinge bracket bolts to 50 to 70 inch-pounds. After torquing, the bolt shall not rotate u nder 25 to 35

inch-pounds

of torque

applied

to the bolt.

cables between the elevator and the horizontal stabilizer.

e.

Install the

f.

Connect the elevator

push-pull

rod to the elevator control horn

g.

Connect elevator tab

push-pull

rods to the tab control horns at the double clevis.

bonding

the inboard end of the elevator.

on

Tighten

the

large

nut of the

double clevis first. h.

Rig the elevator control system in accordance with the ELEVATOR in this chapter, then secure the turnbuckles with the safety clips.

i.

Connect the

navigation light wiring

and install the aft

fairing

on

CONTROL SYSTEM RIGGING

the vertical stabilizer with the

procedures

attaching

screws.

ELEVA TOR CONTROL CABLE REMOVAL a.

Remove the

b.

Remove the aft floor

c.

Remove the tail section

d.

Tag

e.

and

identify

all left cabin seats, floor

panels

and the

access

large

panels,

floor

and the

coverings and

panel

floor

retaining pins from (Ref. Figure 202).

Disconnect the elevator

autopilot

all

servo

pulley

panels

on

the left side of the

airplane.

inside of the aft cabin entrance door.

access

plates

from the vertical and horizontal stabilizers.

both forward elevator cable ends in relation to their

Remove the cable bulkhead

f.

pilot’s seat,

brackets and

attaching points

remove

on

the bellcrank.

the cable seals from the aft pressure

1 from the cables in the aft

fuselage

section.

27-30-00

Oct

31/06Page

205

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

g.

Disconnect the elevator cables from the bellcrank and disconnect the front cables from the aft cables at the turnbuckles in the aft

h.

section.

Connect lead lines at the forward ends of the cables and

Tag i.

fuselage

and

identify

remove

the cables

through

the aft

fuselage

section.

the lead lines for proper reinstallation of the cables.

Connect the lead lines at the turnbuckles of the aft elevator cables in the aft

fuselage

section.

Tag

and

identify

the lead lines for proper reinstallation.

j.

Working through the remove

access

openings

in the horizontal stabilizer, disconnect the cables from the bellcrank and

the cables.

NOTE: Take

not to

care

drop the cables

the lead lines with tape

or

or

the lead lines into the vertical stabilizer since recovery is difficult. Secure are disconnected from the lead lines.

ties when the cables

ELEVA TOR CONTROL CABLE INSTALLA TION NOTE: If

used cable is installed, the cable should be dipped in corrosion preventive compound (13, Chart 2, 2700-00). The excess should be removed by wiping with a clean rag. Refer to Chapter 20-04-00 for control cable and pulley inspection requirements.

a.

a

Connect the cables to the lead lines and route the aft down

b. c.

the vertical stabilizer and into the aft

through

(elevator up) cable from the aft slot of the elevator bellcrank fuselage section (Ref. Figure 202).

Connect the cable end to the bellcrank. Route the aft

(elevator down) cable from the fuselage section.

forward slot of the elevator bellcrank down

through

the vertical

stabilizer and into the aft d.

Connect the cable end to the bellcrank.

e.

Attach the foMlard cables to the forward bellcrank, route them aft cables at the turnbuckles.

NOTE: The interior of all turnbuckles should be coated

or

through the pulleys and

filled with grease

(1,

reattach the forward and

Chart 2,

27-00-00) for corrosion

protection. f.

g.

Install the

Using

pulley retaining pins.

solvent

(2,

seals. Lubricate

Chart 2,

one

inch

27-00-00), clean the cables the length of travel through the pressure bulkhead beyond the cleaned area with grease (1, Chart 2, 27-00-00).

h.

Fill the pressure bulkhead cable seals with grease

i.

Rig

j.

Replace

Oct

31/06Page

the cables

206

all

as

(1, Chart 2, 27-00-00) and

cable

install.

outlined in ELEVATOR CONTROL SYSTEM RIGGING.

access

panels, floor coverings and

27-30-00

seats.

nzl

Ray~heon nircraft Company SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELEVATOR CONTROL SYSTEM RIGGING NOTE: Do not connect the

actuating components

of the

autopilot

until all

flight

control systems have been

properly

rigged. a.

Install the elevator travel boards, P/N 807 101-610000-1. Refer to be mounted

b. c.

on

Disconnect the elevator Install

a

Figure 1,

27-00-00. One travel board should

each horizontal stabilizer at station 35.000. rod at the elevator control horn

push-pull

each elevator

on

(Ref. Figure 202).

rig pin in the forward bellcrank and a rig pin in the aft elevator bellcrank. Access to the aft through an access plate in the vertical stabilizer just below the horizontal stabilizer.

elevator

bellcrank is d.

Disconnect the double clevis

edge

NOTE: The double clevis ends action

against

the elevator tab

on

trailing edge

of each tab with the

the tab

on

of its

push-pull rods at respective elevator.

push-pull

the tab control horns; then

e.

With the

f.

Remove the forward

(the

small nut forward of the

rig pins installed, rig

rig pin

are

designed

the cables to the proper tension

and

adjust the right

the

trailing

tighten the inside clevis with a binding removes play of the bolt in the hole. Loosen before removing the clevis bolt. larger nut)

rods

to

free

the clevis bolt and the outside clevis, which

the inner clevis first

align

(Ref. Figure 203).

hand cable until the forward

rig pin

will

slip easily

into the

rig pin

hole.

NOTE: This g.

adjustment

allows the tension of the cables to be

Check the tension of the cables to cable divided

by

verify that the sum

TENSION DOWN CABLE

Example: (57 pounds

75

Adjust on

pounds)i

weight

added to the system.

of the tension of the up cable and the tension of the down Graph in Figure 203.

each elevator travel for

a

2

132

i

2

i

X

2

66

pounds.

pounds.

deflection of 20" +1" -O" up and 14" +1 -0 down measured from the 0"

position

the travel boards.

NOTE: Ensure that the elevators i.

with the bob

2 is within the limitations refer to the Tension

TENSION UP CABLE

h.

rigged

move

freely (without binding) throughout the

Center the elevators and connect the elevator

necessary to obtain NOTE:

00

a

reading

Verify that the threads

are

on

Remove the aft

k.

Attach the elevator

servo

rods to the control horns.

each travel board, then

visible

rig pin. There should

j.

push-pull

through be

no

the

entire travel.

inspection

tighten

Adjust

the rod ends

as

the locknuts.

hole in the end of the rod.

rig pins remaining

in the

system.

cables to the forward elevator control cables,

using

the

procedures

for ELEVATOR

SERVO CABLE INSTALLATION in Chapter 22-10-00. i.

Rig

the elevator

RIGGING in m.

~at

servo

Chapter

cables in accordance with the

procedures

for AUTOPILOT CONTROL SYSTEM

22-10-00.

Use a hand force gage to check for a combined downspring and bob weight force of 29 fl pounds and for elevator system friction of 9 +1 -9 pounds with the flight system (including the autopilot) fully installed. Make these check as follows:

27-30-00Page

207

Ray~heon

AiKraft company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 1.

required to steadily pull the control column aft through neutral from the full forward position. Measure the force required to return the control column from the full aft position forward through neutral. Add the two readings and divide by two. The resultant should indicate a combined downspring and bob weight force of 29 +1 pounds. If this reading is not obtained, readjust the downspring to obtain the Measure the force

proper tension.

Example: (FAft

I

2.

Use the

FFore)

readings

2

obtained in

the system friction of 9

1~

(34

Example: (FAft- FFore)i

2

1 -9

(34

24)

2

i

58

Set the stops at the forward bellcrank for

=10 a

2

29

pounds.

the difference and divide

Step 1., find pounds. 24)’2

i

i

2

5

by

two. The resultant should indicate

pounds.

clearance of 0.37 +0.06 inch. Refer to

Figure 202,

Detail C.

pushrod from the forward bellcrank disconnected at the base of the control column, adjust the bobweight-stop bolt to provide a minimum cushion of 0.50 inch before the interconnecting link between the bobweight bellcrank and control column bracket fails over center. Refer to Figure 202, Detail A.

o.

With the

p.

Adjust the pushrod

until the distance between the centers of the attachment

points on each end of the Figure 202, Detail B.

rod is

15.12 +0.06 -0.12 inches then connect the rod to the control column. Refer to

1 q.

Check that the control column clears the full travel from stop to stop

on

adjacent structure and

all electrical

wiring and components throughout

the forward bellcrank.

NOTE: The elevator control system has three stops. The primary stops are contacted by the control horn to limit elevator movement. The secondary stops are on the forward bellcrank and establish the limits of control

column travel. The final stop in the elevator control system is the stop bolt for the bob weight. r.

Check that the elevator-down stop bolt in the forward bellcrank contacts its stop before the bob weight contacts its stop bolt. The pushrod may be adjusted +.06 to -0.12 inch from its initial setting in Step p. to obtain the proper

stop sequence and clearance between the control column and adjacent equipment. Referto Figure 202, Detail

s.

Verity that the

elevator installation is within the

limitations:

1.

A gap of 0.187 +0.100 -0.050 inch should exist between the trailing edge skin of the horizontal stabilizer and the centerline of the elevator nose with the elevator deflected full travel up or down.

2.

The minimum gap between the inboard

NOTE: It is

permissible to Step 2. If trimming

t.

following

Connect and

NOTE:

Page

Tighten

tighten

the

large

edge

of the elevator and the vertical stabilizer should be 0.12 inch.

edge of the elevator or tab 0.06 inch in order to required, the elevator should be checked for balance.

trim the is

the elevator tab devises nut of the double clevis

27130100

on

each

achieve the distance noted in

elevator tab.

first, then the small

nut.

9~21

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELEVATOR TRAVEL 20-21’ UP IdlP DOWN

NOTE The range shown in this graph is one-hen of the tension load resulting fma cabining 28tension of the up caWe with the tension of tt~edorm cable. EXAMPLE:

20

n

10

’’’’’"’T I r i I

i i Ii

1111 I

I

I

i I

i

i

I

I I

L it

I I

I

I

I

I I

I

I

I

I

I

I

I

I

I 1

(tension of

72

38

up

cable)

pounds

45 (tensron of dorm

CAUTION:

Rig the tension of

other

so

40

50

80

ro

one

cable as nearly eouai to the tension of che

2

20

cable!-

20

so

as

possible.

too

lzo

Ilo

TEMPERATURE IN ´F FU7B D43890AA

Cable Tension

Graph for Figure 203

A21

Elevators

27-30-00

Oct

31/06Page

209

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELEVATOR TAB REMOVAL NOTE: The

following steps

for elevator tab removal and installation

are

applicable

to both the left and

Remove the aft horizontal stabilizer

b.

Disconnect the elevator tab dual actuator

c.

Disconnect the

d.

Remove the

screw

Carefully

the hinge pin from the hinge while simultaneously supporting the airplane.

e.

bonding jumper which

pushrods

from the tab horns.

cable from the inboard end of the tab.

secures

the inboard end of the

hinge pin

to the tab.

remove

tab from the

tabs.

from between the two elevators.

a.

fairing

right

elevator tab, and

remove

the

ELEVATOR TAB INSTALLATION a.

Lubricate the elevator tab CHART in

Chapter

hinge

and the

hinge pin with Brayco

300 in accordance with the LUBRICATION

12-20-00.

b.

Position the elevator tab

c.

Secure the inboard end of the

d.

Install the

e.

Connect the elevator tab dual actuator

on

bonding jumper

the elevator and

hinge pin

cable

on

carefully

install the

to the tab with the

hinge pin.

attaching

screw.

the inboard end of the elevator tab with the

pushrods individually

attaching

to the tab horns and

adjust

screw.

them

as

under ELEVATOR TRIM TAB RIGGING and CHECKING ELEVATOR TAB FREE PLAY in this f.

Oct

Install the aft horizontal stabilizer

fairing.

31/0627-30-00

instructed

chapter.

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELEVATOR TRIM TAB CABLE REMOVAL

FORWARD

CAUTION: If tension in the system is lost during cable maintenance, check the forward cable drum (3) and elevator trim tab actuator cable drums to ensure the cable is not unwound from drums (Ref. Figure 204). a.

Remove the access panel 6 on the left side of the vertical stabilizer, just Chapter 12-20-00, FUSELAGE ACCESS OPENINGS).

b.

Move the elevator surface to neutral

force, try

to

manually

elevators do not c.

Remove

move

position (0") and

(Ref.

rig pin in the aft elevator bellcrank. Using minimum verify that the rig pin is correctly installed. Ensure the

the elevators up and down to

a

move.

fuselage

opening 11 just OPENINGS).

access

FUSELAGE ACCESS

aft of the

d.

Remove both

e.

Remove

f.

Remove the left and

g.

Remove flight compartment OPENINGS).

h.

Remove left passenger compartment carpets

flight compartment

chairs

landing gear

nose

wheel well

(Ref. Chapter 12-20-00,

(Ref. Chapter 25-10-00).

flight compartment carpet (Ref. Chapter 25-10-00). right pedestal

side

access

floorboards 3

Remove the left side passenger seats

i.

install

below the horizontal stabilizer

1

as

and

panels.

4

(Ref. Chapter 12-20-00, FLOORBOARD ACCESS

(Ref. Chapter 25-20-00).

required to gain access to the trim

cables

being removed (Ref. Chapter

25-20-00). Remove cabin floorboards 5; 6, 7, 8, 9, 10, 11, 12, 13, 14, 15 and

j.

k.

Open fuselage

I.

On the left side of the upper cable terminal ends of cable

access

panel

12

Attach

a

Remove

FUSELAGE ACCESS

a

groove at

one

end to

identify

clips

to

OPENINGS).

approximately align

I

to the forward end of the turnbuckle

(2).

and disconnect the left-hand threads terminal end from turnbuckle and attach

terminal end. Label the feed line with the words "Left-hand threads terminal end" o.

Attach

a

a

feed line to the

(Ref. Figure 205,

Detail

D).

(1).

Remove clips and disconnect the

right-hand threads terminal end from turnbuckle and attach a feed line to the "Right-hand threads terminal end" (Ref. Figure 205, Detail D).

terminal end. Label the feed line with the words NOTE: Some of the those q.

n,

I

tag with the words "Forward cable right-hand threads terminal end" to the forward end of the turnbuckle

attached to cable p.

the foMlard

the left-hand threads end.

tag with the words "Forward cable left-hand threads terminal end"

attached to cable n.

(Ref. Chapter 12-20-00,

pedestal, move the elevator trim control wheel (1) and cable (2) (Ref. Figure 205, Detail D).

Note: Each turnbuckle barrel has m.

16(Ref. Chapter 12-20-00, FLOORBOARD

OPENINGS).

ACCESS

pulleys cannot be cleared by the terminal ends even with cable guard pins removed. pulleys where necessary to provide for adequate clearance.

Remove cable

guard pins from pulley brackets.

Refer to

Figure 205,

Detail B for

general

Remove

locations of the

27-30-00

pulleys.

I

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: If cable is to be reused, take than a ten inch diameter.

care

r.

Lubricate the cables with grease pressure seal.

s.

Carefully feed

t.

While

u.

On the left side of the

(1,

to

keep the cable clean and

Chart 2,

the cable terminal ends

27-00-00)

through

as

free from

necessary to

damage. Coil

cable

loosely

no

tighter

pull the cable terminal ends through the

the pressure seals at FS 381.

pulling the feed lines through the fuselage, withdraw both left and right-hand threads terminal ends through the fuselage and out of the belly access panel 11 (Ref. Chapter 12-20-00, FUSELAGE ACCESS OPENINGS). pedestal, loosen two bolts (11) and nuts securing the trim bracket and idler sprocket (10) to relieve tension from the chain (8), and move trim bracket out of the way to facilitate maintenance only (Ref. Figure 204). bracket

NOTE: When bolt

(13) is removed from the left sprocket (12), may fall.

side of the

pedestal,

washer

(14),

located between the

pedestal

frame and the v.

I

(13) and remove bolts (13) at each end of the trim shaft (16). Remove washer (14) between pedestal and sprocket (12). Lift the trim shaft assembly as needed to remove the chain (8) from the sprocket (12), and remove the trim shaft assembly from the pedestal with the forward cable attached. Remove

safety

w.

Remove the

x.

Unwrap

y.

sprocket (12), cable guard (15)

cable from the drum and

remove

Remove the forward cable from the and into the

z.

wire from bolts

(3)

the cable lock

airplane

while

from the trim shaft

(16).

pin (Ref. Figure 206).

routing

the feed lines

through

the

right

side of the

pedestal,

cockpit.

Disconnect the feed lines from both left and

Oct

and drum

31/0627-30-00

right-hand

threads terminal ends.

P~Z1

Raytheon

Aircraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELEVATOR TRIM TAB CABLE INSTALLATION

FORWARD

WARNING: Perform all steps of this procedure, in the order listed. Do not skip any steps of this procedure. Failure to do so may result in injury to personnel and damage to equipment.

CAUTION: If tension in the system is lost during cable maintenance, check the forward cable drum (3) and elevator trim tab actuator cable drums to with

a.

Clean the cable

b.

Check cable for cleanliness and

compound (13, c.

assembly

Chart 2,

a

ensure

the cable is not unwound from drums

a tag labeled "Left-hand threads terminal end" (Ref. Figure 205, Detail D).

Attach

e.

Wrap

a

27-00-00).

to the forward cable left-hand threads terminal end

I

tag labeled "Right-hand threads terminal end"

the forward cable

Chart 2,

damage. Replace cable if necessary. Dip the cable in corrosion preventive 27-00-00). Remove excess corrosion preventative by wiping with a clean cloth.

Attach

d.

(2,

clean cloth saturated with solvent

(Ref. Figure 204).

on

the cable drum

CAUTION: Do not kink the cable while

as

follows

locating

to the forward cable

right-hand threads

terminal end.

(Ref. Figure 206):

1

the middle of the forward cable.

Damage

to the cable will occur.

1.

Align the terminal ends of the forward cable together and mark the middle of the forward cable with ink or paint. Locate the side of the forward cable with the left-hand threads terminal end. Position the middle of the cable in the middle of the cable drum slot (see Detail B). With the left-hand threads terminal end side of the cable, on the flat side of the cable drum, install the cable lock pin in the middle of the cable drum slot (see Detail C).

2.

From the lock pin, wrap each cable 2 1/4 turns around the drum work toward the middle of the drum (see Detail D).

3.

Position the cable

guard

over

the drum and

beginning

with the outside grooves and

tape the forward cables together just outside of the cable guard

to prevent cable backlash at the drum (see Detail E). When applying tape to the cable, make sure the cables are separated so that it is easy to identify which cable end winds off the forward and aft side of the drum.

threads terminal end".

f.

Attach the

g.

Attach the left-hand threads terminal end to the feed line labeled "Left-hand threads terminal end".

right-hand

threads terminal end to the feed line labeled

one person will be and free from damage.

Note: More than

h.

side and then out of the

j.

precautions to keep the cable

clean

belly access panel (11) (Ref. Chapter 12-20-00, FUSELAGE ACCESS OPENINGS). through the right side of the pedestal, and then proceeding inside of pedestal to the left belly access panel until the drum is close to the pedestal.

On the left side of the upper pedestal, move the elevator trim control wheel (7) to approximately 0 maintain the approximate 0 position until the terminal ends are connected (Ref. Figure 204). Install the cable drum

assembly k.

route the forward cable. Take

Pull the feed lines from the Draw the forward cables

i.

required to

"Right-hand

(3) with guard (15) and sprocket (12)

and washer

Install and

safety

(14)

wire bolts

in the

(13),

pedestal, one on

on

the trim shaft

and

(16). Carefully position the trim shaft (8) onto the sprocket (12).

and install the lower end of the chain

each side of the

position

pedestal.

27-30-00

1

Ray~heon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i.

Identify the forward cable with the left-hand threads terminal end (2) and make sure it winds off the forward side (3) as installed. Identify the forward cable with the right-hand threads terminal end (1) and make sure it winds off the aft side of the drum as installed. Route the cable from the drum as follows (Ref. Figures 205): of the drum

I

dna402

NOTE: It is

permissible

to install cable

1.

Route cable

(2)

over

the outboard

2.

Route cable

(1)

over

the inboard

3.

Route cable access

4.

(1) through the

aft

as

pulley (4) (Ist

pulley (4) (Ist

the forward

(2) through panel).

Route cable

guard pins

set of

set of

pulley (5) (2nd

pulley (5) (2nd

being

the cable is

pulleys under the pedestal drum). under the

pulleys

set of

set of

routed.

pedestal drum).

pulleys under the pedestal, just

pulleys

under the

pedestal, just

above the

above the

belly

belly access

panel), 5. 6.

Using

Route cable as

7.

the feed lines,

pull

the cable into the

fuselage.

(2) through the top pulley (6) (3rd set of pulleys at pilot and into the forward cabin.

FS 103 under the

pilot).

This cable continues

the top cable under the

Route cable

continues

(1) though

pulley (6) (3rd set of pulleys at FS 103 pilot and into the forward cabin.

the bottom

under the

pilot). This cable

the bottom cable under the

as

8.

Using

9.

Route cable

(1) through

the bottom

10. Route cable

(2) through

the

11. Route cable

(l)through

the bottom

12. Route cable

(2) through

the top

13. Route cable

(l)through

the bottom

14. Route cable

(2)

15. Route cable

(1) under the

the feed lines route cable

(2) through

pulley (4th

top pulley (51h

pulley (7th

outboard

set of

pulleys

set of

at FS

145).

145).

301).

314).

at FS

at FS

pulleys

pulleys

301).

at FS

at FS

pulleys

set of

at FS

at FS

pulleys

pulleys

set of

pulley (7th

pulleys

pulleys

set of

set of

pulley (6th

pulley (4th

set of

set of

pulley (5th

pulley (6th

under the inboard

the top

314).

342).

at FS

342).

length of cable (2) as necessary with grease (1, through the inboard pressure seal at FS 381.

Chart 2,

16. Lubricate the left-hand threads terminal end and

27-00-00). Carefully

feed the terminal end

right-hand threads terminal end and length of cable (I)as necessary with grease (1, 27-00-00). Carefully feed the terminal end through the outboard pressure seal at FS 381.

17. Lubricate the

18. Route cable

cable

as

the bottom

pulley (8th

(l)through

the top

pulley (8th

21. Remove feed line and attach the

31/06Page

214

pulleys

at FS

404).

This cable becomes the

right

side

set of

pulleys

at FS

404).

This cable becomes the left side cable

it routes aft in the vertical stabilizer.

20. Lubricate all turnbuckles with grease

Oct

set of

it routes aft in the vertical stabilizer.

19. Route cable as

(2) through

Chart 2,

27-30-00

(1,

Chart 2,

right-hand

27-00-00) for corrosion protection prior to installation.

threads terminal end to the tumbuckle.

RBYtheOll

Aircraft Campany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

22. Remove feed line and attach the left-hand threads terminal end to the tumbuckle. 23. Tension the forward cable sufficient to m.

Make

sure

the forward cable is routed

I. Ensure cable is n.

engaged

properly by verifying that the cable has been routed as described in Step pulley grooves and all guard pins are installed (Ref. Figures 204 and 205).

in the

Position the trim bracket and the idler

(8). Remove o.

prevent slack.

Using solvent (2, 381. Lubricate to

bracket

sprocket

slack from tab control chain

(8)

(10) and align idler sprocket (9) tighten the two bolts (11) and nuts.

and

Chart 2, 27-00-00), clean the cables for the length of travel one inch beyond the cleaned area with grease (1, Chart 2,

with tab control chain

the pressure seals at FS

through

27-00-00).

p.

Perform the ELEVATOR TRIM TAB RIGGING

q.

Move the top of the trim control wheel and note that the bottom cable, aft of the 3rd set of pulleys, under the pilot’s seat, moves the same direction as the top of the trim control wheel. No binding is allowed.

procedure.

Move the top of the trim control wheel to position the elevator trim tabs at neutral with the elevators at neutral. If necessary, adjust the indicator in the flight compartment to 0 while the tabs and elevators are at neutral. The 0 mark

If

on

the trim control wheel indicator must

required, perform

s.

Remove the

t.

Ensure turnbuckles have been safetied.

u.

rig pin

align

with the

triangle

mark

on the pedestal edgelighted panel. procedure (Ref. Chapter 27-30-00).

the ELEVATOR TAB INDICATOR ADJUSTMENT

from the elevator aft bellcrank.

Move the top of the trim control wheel forward (airplane nose down) and verify the trim tab trailing edge position. Again verify looking inboard from the pilot side at the trim wheel, turn the wheel

moves

to the full up

counterclockwise and proceed to the tail and v.

verify the

trim tab moved up.

Move the top of the trim control wheel aft (airplane nose up) and verify the trim tab trailing edge moves to the position. Again verify looking inboard from the pilot side at the trim wheel, turn the wheel clockwise

full down and w.

proceed

to the tail and

verify

the trim tab moved down.

Install cabin floorboards 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15 and 16

ACCESS x.

Install left side passenger seats

y.

Install left passenger compartment carpets.

z.

Install

aa.

Install left and

ab. Install ac.

right pedestal side

access

FLOORBOARD ACCESS

OPENINGS).

panels.

flight compartment carpet (Ref. Chapter 25-10-00). flight compartment

fuselage

ae.

Install

af.

Close access

~21

FLOORBOARD

(Ref. Chapter 25-20-00).

flight compartment floorboards (3 and 4) (Ref. Chapter 12-20-00,

Install both

ad. Install

(Ref. Chapter 12-20-00,

OPENINGS).

access

access

seats

(Ref. Chapter 25-10-00).

opening (11) (Ref. Chapter 12-20-00,

FUSELAGE ACCESS

OPENINGS).

panel (6) (Ref. Chapter 12-20-00,

FUSELAGE ACCESS

OPENINGS).

(Ref. Chapter 12-20-00,

FUSELAGE ACCESS

OPENINGS).

panel

12

27-30-00Page

215

Raytheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION: With the control column pulled to the ah position, allowing the control column to free fall to the forward position can cause damage to the elevator system. ag. Pull the pilot’s control wheel aft and make noise or binding. ah. Move the

pilot’s

unusual noise

VERTICAL

sure

that the elevator travels to the full up

control wheel forward and make

or

sure

position

with

that the elevator travels to the full down

no

unusual

with

position

no

binding.

ELEVATOR TRIM TAB CABLE REMOVAL

CAUTION: If tension in the system is lost during cable maintenance, check the forward cable drum (3) and elevator trim tab actuator cable drums to ensure the cable is not unwound from drums (Ref. Figure 204). NOTE: The left vertical cable is connected to the

right

actuator cable and the

right

vertical cable is connected to the

left actuator cable. Removal cable

procedures for the left and right vertical trim tab cables procedure is provided, unless otherwise indicated.

Both terminal ends of the left vertical cable

right

vertical cable

If

electric elevator trim

an

assembly Remove the

a.

with

a

right-hand

panel

6

on

force, try

c.

autopilot

move

servo

is installed, the

trim tab

right

hand vertical cable is

a

two

part

servo.

the left side of the vertical stabilizer,

FUSELAGE ACCESS

manually

to

only the right vertical

left-hand threads terminal ends. Both terminal ends of the

connection located aft of the

Move the elevator surface to neutral

b.

are

the same,

threads terminal ends.

servo or

fork-and-eye

access

Chapter 12-20-00,

are

are

just

below the horizontal stabilizer

(Ref.

OPENINGS).

position (0") and

rig pin in the aft elevator bellcrank. Using minimum verify that the rig pin is correctly installed. Ensure the

install

the elevators up and down to

a

elevators do not

move.

Remove

panels (16 and 18) on the top and bottom of the horizontal stabilizer (Ref. Chapter 12-20-00, OPENINGS).

access

FUSELAGE ACCESS d.

Remove

access

panel

5

on

the left side of the aft

fuselage (Ref. Chapter 12-20-00,

FUSELAGE ACCESS

OPENINGS). e.

Open fuselage

f.

On the left side of the

access

forward and aft cables

I

panel

Attach

h.

Working through on

a

FUSELAGE ACCESS

against

the frame. Do not

position

cable block

OPENINGS).

that the turnbuckles

against

the

connecting the

pulley.

cable block to both ends of the forward cable, aft of FS 404, to prevent the forward cable from

the

access

openings

on

moving.

the top left-hand side of the horizontal stabilizer, attach a cable block against the trim tab actuator housing, to prevent the actuator

both cables of the left elevator trim tab actuator,

drum from

unwinding.

NOTE: Each turnbuckle barrel has i.

(Ref. Chapter 12-20-00,

pedestal, move the elevator trim control wheel so are easily accessible (Ref. Figure 205, Detail D).

NOTE: Position cable block g.

12

Attach

a

a

groove at

one

end to

identity the

tag with the words "Right-hand threads terminal end" (2) in the aft fuselage compartment.

left-hand threads end.

to the aft end of the tumbuckle that is attached

to the cable

Oct

3106Page

216

27-30-00

nzl

NeltltNeen

nircrart

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

j.

Disconnect the

k.

Remove cable locations of

I.

threads terminal end from the turnbuckle and attach

right-hand

guard pins pulleys.

Working through

the

pulley brackets.

from the vertical cable

access

turnbuckle attached to cable

Refer to

a

feed line to the terminal end.

Figure 205,

Detail B for

openings on the top left-hand side of the horizontal stabilizer, (2). Do not disconnect the cross over cable turnbuckle.

NOTE: If cable is to be reused, take than a ten inch diameter.

care

to

keep the

cable clean and free from

damage.

general

I

disconnect the lower

Coil cable

loosely

no

tighter

working with the cables that are strung up through the vertical stabilizer, take precautions to avoid dropping the ends of the cables down into the interior of the vertical stabilizer since recovery is difficult.

While

m.

Working through

the

access

on

n.

the top

openings

on

the top left-hand side of the horizontal stabilizer with the

the cable and feed line up through the vertical stabilizer and out the of the horizontal stabilizer to remove the right vertical cable.

threads terminal end,

pull

Disconnect the feed line from the

right

right-hand opening

access

vertical cable.

ELEVATOR TRIM TAB CABLE INSTALLATION

VERTICAL

CAUTION: If tension in the system is lost during cable maintenance, check the forward cable drum (3) and elevator trim tab actuator cable drums to ensure the cable is not unwound from drums (Ref. Figure 204). NOTE: The left vertical cable is connected to the

right actuator cable

and the

right

vertical cable is connected to the

left actuator cable. Installation

tab cable

procedures for the left and right vertical trim tab cables is provided, unless otherwise indicated.

Both terminal ends of the left vertical cable

If

electric elevator trim

assembly

with

a

are

servo or

with

Clean the cable

b.

Check cable for cleanliness and

compound (13,

assembly

Chart 2,

only

the

right

vertical trim

right vertical cable

stabilizer. The feed line

left-hand threads terminal ends. Both terminal ends of the

autopilot

servo

is installed, the

right

hand vertical cable is

a

two

part

servo.

clean cloth saturated with solvent

(2,

Chart 2,

27-00-00)

damage. Replace cable if necessary. Dip the cable in corrosion preventive 27-00-00). Remove excess corrosion preventative by wiping with a clean cloth.

NOTE: Each turnbuckle barrel has Attach the

a

are

connection located aft of the

fork-and-eye

a.

c.

the same,

threads terminal ends.

right-hand

right

vertical cable

an

are

procedure

was

a

groove at

with the

installed

one

end to

identify the

left-hand threads end.

right-hand threads terminal ends to during the VERTICAL ELEVATOR

the feed line in the horizontal TRIM TAB CABLE REMOVAL

procedure. NOTE: More than

person will be required to route the right vertical cable. Position one person at the access the top left-hand side of the horizontal stabilizer to feed the cable. Position another person in

one

openings on fuselage compartment damage.

the aft

d.

Route the

right vertical

cable

to

pull

through

the

the feed line. Take

pulleys by pulling

precautions

to

keep the cable clean and free from

the feed line forward and down

through

the vertical

stabilizer.

Az~

27-30-00

Oct

31/06Page

217

Ral~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

e.

Lubricate all turnbuckles with grease

f.

Working through the

g.

(Ref. Figure 205,

NOTE: If

installing installed).

h.

Tension the

engaged i.

right-hand

the

right

right vertical pulleys.

Chart 2,

on

27-00-00)

for corrosion

protection prior to installation.

the top left-hand side of the horizontal stabilizer, attach the

right

threads terminal end to the turnbuckle.

Remove the feed line and attach the turnbuckle

I

openings

access

vertical cable with the

(1,

Detail

right vertical

cable with the

right-hand

threads terminal end to the

D).

vertical cable,

cable is

ensure

properly

routed onto electric elevator trim control

cable sufficient to prevent slack. Ensure the

right

vertical cable is routed

properly

(if

and

in the

Install the cable

guard pins removed during the VERTICAL

ELEVATOR TRIM TAB CABLE REMOVAL

procedure. j.

Remove the cable blocks installed

during

the VERTICAL

ELEVATOR TRIM TAB CABLE REMOVAL

procedure. k. I.

Remove all tags from turnbuckles. Move the top of the trim control wheel forward (airplane nose down) and verify the trim tab trailing edge position. Move the top of the trim control wheel aft (airplane nose up) and verify the trim tab

to the full up

edge

moves

to the full down

Perform the ELEVATOR TRIM TAB RIGGING

n.

Ensureallturnbuckles havebeensafetied.

o.

Install

p.

Remove the

q.

Install

access

panel

6

(Ref. Chapter 12-20-00,

Install

access

panel

5

(Ref. Chapter 12-20-00, FUSELAGE ACCESS OPENINGS).

Close

access

panel

12

s.

panels (16

rig pin

and

procedure.

18) (Ref. Chapter 12-20-00,

t.

FUSELAGE ACCESS

(Ref. Chapter 12-20-00,

noise u.

pilot’s control or binding.

Move the

pilot’s

unusual noise

Oct

can cause

Pull the

31/06Page

218

OPENINGS).

pulled to the aft position, allowing damage to the elevator system.

wheel aft and make

sure

binding.

27-30-00

OPENINGS).

FUSELAGE ACCESS

OPENINGS).

the control column to free fall to the forward

that the elevator travels to the full up

control wheel forward and make

or

FUSELAGE ACCESS

from the elevator aft bellcrank.

CAUTION: With the control column

position

trailing

position.

m.

access

moves

sure

position

with

that the elevator travels to the full down

no

unusual

position

with

no

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1~

2

P

D

OUTED JOUTBD)

rO~ B 2

o

FORWARD LOOKING AFT DETAIL

1. FORWARD

(RIGHT

7

B

13

HAND THREADS

9

TERMINAL END) CABLE 2. FORWARD (LEFT HAND THREADS TERMINAL END) CABLE

15

3. DRUM

1~6

b

10

(UNDER PEDESTAL) SET OF PULLEYS (UNDER PEDESTAL) SET OF PULLEYS (FS 103.00)

4. 1ST SET OF PULLEYS

5. 2ND 3. 330 7. TAB CONTROL WHEEL

11

8. CHAIN

12

9. IDLER SPROCKET 10. IDLER SPROCKET BRACKET II. BOLTS 12. SPROCKET 13. BOLTS 14. WASHER 2

15. CABLE GUARD 16. TRIM SHAFT

13

1

DETAILA

F~78

043663A~AI

Fonnrard Elevator Trim Tab Cable

Figure

A21

204

27-3000

Oct

31/06Page

219

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

27130100

Page Intentionally Left Blank

A21

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AFT

SAFETY

FORWARD

(LEFT-HAND THREADS)

(RIGHT-HAND THREADS)

CLIP

TERMINAL END

TERMINALEND

O

DUAL PUSH RODS

3

1

TRIM TAB ACTUATOR

1~.-

,2 GABLE STOPS FORWARD

OUTED louiBo

TERMINAL

END(RIGHT-HAND

THREADS)

SAFE~Y

AFT

CLIP

(LEFT-HAND THREADS!

DETAIL

TURNBUCKLES

a~

F ~O

n

TERMINAL END

B

F

O a

i’

F

’U""""

j

DETAIL

C)

A

TURNBUCKLES

F 2 6 5

j’

I

1

i

DUAL PUSH RODS

ACTUATORTRIM

~Uh

TAB

O

FS 103 2

DETAIL

FILL WITH MIL-S-8802

a

YE

!BOTH SIC)ES)

AFT CABLE

1116 (N.

B i. FORWARD

TERMINAL 2. FORWARD

(RIGHT-HAND THREADS END) CABLE (LEFT-HAND THREADS

PRESSURE SEAL

TERMINAL END) CABLE 3. DRUM

Crop VIEW)

4. FIRST SET OF PULLEYS

DETAIL

(UNDER PEDESTAL)

FS 404

C

C)

5. SECOND SET OF PULLEYS

i’

(UNDER PEDESTAL) 6. THIRD SET OF PULLEYS

~.pr

iFS103)

6~

FS 381

FS 342

FORWARD GABLE

TAB ACTUATOR

FS 301

PUSH-PULL

1/16 IN.

RODS

et

2

b

FS 314

DETAIL

FS 145

ELEVATOR TRIM CONTROL

B

(IF INSTALLED) ELEVATOR TAB ACTUATOR

1

DETAIL

G

TAB CONTROL HORN DETAIL

E

FI~:8 rri?66-"M.JI

Elevator Tab Control

Figure

System

205

ORIGINAL As Recehred

ATP

A2t

6)

27-30-00

Page

221

Oct 31/06

RaYRIGWI

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Page

27130100

Page Intentionally Left

Blank

A21

Ral~heon

AiKraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

oOO SPROCKET

E1

B

1Ce FORWARD CABLE WITH

D,,,

TERMINALENDLEFT

A

HAND THREADS

MIDDLE OF CABLE AND MIDDLE OF

SIDE WITH

CABLE DRUM SLOT

CABLE LOCK PIN

RIGHT-HAND

INSTALLED

THREADS

CABLE LOCK PIN

TERMINAL END FLAT SIDE OFDRUM

FORWARD CABLE WITH HAND THREADS

RIGHT

TERMINAL END SIDE WITH LEFT- HAND THREADS

(CABLE

GUARD NOT

DETAIL

SHOWN)

(DRUM NOT FULLY WRAPPED) (CABLE GUARD NOT SHOWN)

TERMINAL END

B

o,,,,,

C

CABLE WITH RIGHT-HAND THREADS TERMINAL END BEGINNING AT THE SPROCKET SIDE OF THE DRUM

SPROCKETSIDE

OF

DRUM

CABLE GUARD

FORWARD CABLE

FORWARD CABLE WITHLEFT-HAND

-RIGHT

THREADS

HAND THREADS

TERMINAL END

CABLE WITH LEFT-HAND

(TEMPORARY)

THREADS TERMINAL END BEGINNING AT THE FLAT SIDE OF THE DRUM

TERMINAL END TAPE

DETAIL

(DRUM

E

FULLY

WRAPPED)

DETAIL

D

Fonnrard Elevator Trim Tab Cable

Figure

A21

206

27I30-00

Oct

31/06Page

223

NeldNeert

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELEVATOR TRIM TAB RIGGING NOTE: If

a

dipped in corrosion preventive compound (13, Chart 2, 27excess by wiping with a clean rag. Refer to Chapter 20-04-00 for control pulley inspection requirements.

used cable is installed, the cable should be

00-00).

The

cable and

should be removed

The elevator control system must be a.

Place the elevators in neutral and install the bellcrank is

I

properly rigged before the elevator tab system

through

an access

plate

rig pin

be

rigged.

in the aft elevator bellcrank. Access to the aft elevator

in the left side of the vertical stabilizer all turnbuckles

just

below the horizontal stabilizer.

(Ref. Figure 207).

b.

Rig the

c.

Set the control wheel

d.

Adjust the clevis rods on both of the dual actuators as necessary until the tab is in its neutral position. (Visually align the trim tab trailing edge with the trailing edge of the elevator.) Secure the clevis bolts and tighten the devises (large nut first, small nut last).

e.

Adjust the elevator tab for a deflection of 3" +1/2" -0" up from neutral and 15" +1" -O" down from neutral with the cable stops in the aft fuselage section. Refer to Figure 205, Detail F. Tighten the stops to 35-40 inch-pounds and safety with P/N MS24665-5 cotter pins. Refer Figure 1, 27-00-00 for cable stop installation and removal tool.

I

cables to the proper tension and

can

on

the

pedestal

so

safety

the tab indicator reads O.

CAUTION: Make certain the cable stays in the groove while tightening the nuts on the cable stops. The cotter pins must not protrude far enough to snag on adjacent components during cable operation. f.

Check the movement of the elevator tab. The elevator tab should have 3.4" f 1/2" up elevator and 2.4" f 1/2" down elevator servo (trailing tab) travel with the tab set at neutral. Shim as required to obtain the correct servo tab travel.

NOTE: If

required,

a

maximum of

one

laminations to obtain correct

shim 0.040 inch thick may be used as is or may be adjusted tab travel. It is permissible to bond the shim with adhesive

servo

by removing (14, Chart 2,

27-00-00). WARNING: It is not

permissible

to have

one

elevator tab with

servo

action and the other with antiserro

action.

g.

completion of the above rigging procedures, place the control wheel and the elevator in neutral position. trailing edges of the tab and elevator are aligned. The 0 mark on the tab the dial be must triangular indicator mark. (Adjust the dial indicator if necessary.) A red paint position opposite mark, 0.06 inch wide by 0.30 inch long should be present at each full-nose-up or full-nose-down limit of the indicator on the trim wheel (Limits are established by the cable stops). The red marks are painted according to the instructions given by ELEVATOR TRIM INDICATOR SCALE MARKINGS. On

Rotate the elevator tab wheel until the

ELEVA TOR TRIM INDICA TOR SCALE MARKINGS NOTE: This

procedure should only be performed if, during the accomplishment of the ELEVATOR TRIM

RIGGING, it is necessary to do elevator trim indicator scale a.

Move the elevator trim indicator scale to 0 and neutral

CAUTION:

Oct

31/06Page

224

TAB

markings.

visually verify that the

elevator trim tab

trailing edge

is also in

a

position. During

the

following checks,

27-30-00

do not force the elevator trim system past its limits.

nal

RBytheMI

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: The elevator trim control movement should be smooth

roughness

of cable travel

cable that is out of

throughout the entire range of travel. Binding or the control surface movement may be an indication of cable fraying or a within the trim system. If this condition is suspected, the entire length of the cable

during

position

must be checked for condition.

b.

With

one person inside the airplane and one pe mon observing the elevator trim tab trailing edge, manually move the elevator trim control slowly, to the maximum nose up position. Visually verify that the elevator trim tab trailing

edge c.

0.30 inch

Manually

long

move

the entire control movement.

red mark to

align

(maximum nose up with the elevator tab

position) with a highly visible 0.06 position pointer.

trailing edge

moved

by

(1/16 inch)

wide

slowly, to the maximum nose down position and visually verify that the upward throughout the entire control movement.

Mark the elevator trim indicator scale

wide

inch

the elevator trim control

elevator trim tab e.

throughout

Mark the elevator trim indicator scale

by d.

moved downward

0.30 inch

long

red mark to

(maximum nose down position) with a highly align with the elevator tab position pointer.

visible 0.06 inch

(1/16 inch)

ELEVA TOR TRIM TAB ACTUA TOR REMOVAL a.

Remove the

b.

Tag

c.

Disconnect each of the double devises

access

plates

from the top of the horizontal stabilizers.

for identification and disconnect both turnbuckles at each location.

NOTE: The double clevis ends

on

on

the dual tab actuators

the tab actuators

are

designed

to

on

each of the elevator tab hems.

tighten

the inside clevis with

a

binding

action

the clevis bolt and the outside clevis, which removes free play of the bolt in the hole. Loosen the inner clevis first (the small nut forward of the larger nut) before removing the clevis bolt.

against

d.

Remove

mounting

bolts and

remove

the actuator

through

the

access

opening.

ELEVATOR TRIM TAB ACTUATOR INSTALLATION a.

Position the actuator with the cable ends inboard and mount the

NOTE: The b.

push-pull

rod ends of the dual actuator must be

Install the double-clevis ends

on

assembly

with the

adjusted individually

each dual actuator rod at the tab horns.

to

mounting

bolts and

secure.

prevent binding.

Tighten

the inner clevis with the small

nut first.

NOTE: The double clevis ends

on

the tab actuators

are

designed

to

tighten

the inside clevis with

a

binding

action

the clevis bolt and the outside clevis, which removes free play of the bolt in the hole. Loosen the inner clevis first (the small nut forward of the larger nut) before removing the clevis bolt.

against

c.

Remove identification

d.

Rig

e.

Install the

~21

tags and

connect both turnbuckles at each location.

to proper tension and check for correct travel. access

plates

at the

top of the horizontal stabilizer.

27-30-00

NaYIbeeyt

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

30

´•tt

tlfitSi: ~.t i.t~tti

~j m

fi-i

rtt

~´•i´•)-

u.

20 ´•t´•´•~-e T

z

o

y

fi-f(´• tt C t ´•tf+´•~ f´•t+S i-i-i i-i i´•t i i i´•-i i i ´•ti i

~´•I j~i n i-Fr:!´•U´•´•i´• !´•´•i I-I´• F-F´•(

Bfl

i:t to

t’;~T

1

i -i

i ´•i

t:lit

ELEVATOR TAB TRAVEL 3´•

it-tci ~i ii iti~1

’50

00 UP

~20

1

00 DOWN f-´•+i

i’

60

50

40

30

20

80

70

100

90

110 300-601-14 ooi

TEMPERATURE IN OF

Cable Tension

.t´•;

Graph for Elevator Trim Figure 207

Tab

REPLACING ELEVATOR TRIM TAB ACTUATOR CABLES NOTE: If

a

00-00). a.

The

excess

should be removed

Remove the trim tab actuator in this

as

instructed under the

heading

27-

ELEVATOR TRIM TAB ACTUATOR REMOVAL

chapter.

b.

Pull the actuator cables until the

c.

Remove the cable and drum

Oct

dipped in corrosion preventive compound (13, Chart 2, by wiping with a clean rag.

used cable is installed, the cable should be

safety

as

’up"

cable and the "down" cable

hanging

from the drum

are

of

equal length.

follows:

wire from the nut

the actuator drum.

1.

Remove the

2.

Removethe nutandlock.

3.

Removethethree

4.

Removethe

capandspacer.

5.

Removethe

bearing.

6.

Removethedrumand

keyfromtheactuator.

7.

Slide the cable

out of the drum and remove the cable.

over

boltsfromthecap.

keeper

31/0627-30-00

A21

Ral~heon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Install the cable

on

the actuator drum

as

follows:

1.

Place the cable in the drum slot and slide the keeper in

2.

Starting at each

3.

Check to ascertain that the actuator is in the center of its travel.

4.

Install the drum and

5.

Installthebearing

6.

Installthecapand

7.

install the three

8.

Install the nut and lock.

9.

Safety wire

place.

end of the drum wrap the cable 4 1/4 turns around the drum, toward the center of the drum.

key

into the actuator.

intheactuator. spacer.

retaining

bolts in the cap.

the nut to the lock.

ELECTRIC ELEVA TOR TRIM TAB ACTUA TOR ELECTRIC TRIM TAB ACTUATOR REMOVAL a.

Remove the

b.

Disconnect the actuator wire harness at the disconnect

c.

Place

d.

Disconnect the actuator cable at the forward turnbuckle first and then at the aft

fitting.

e.

Remove the three bolts

now

a

access

wood

or

plates from the aft fuselage

below the vertical stabilizer.

splices (Ref. Figure 208).

sheet metal shim between the cable drum and cable

securing

guard

so

the actuator to the bracket. The actuator may

the cable will not unwind.

be removed from the

airplane.

´•06

-.03 -.oa

GAP BETWEEN ARMATURE AND ROTOR HUBS

II

CLUTCH ROTOR-----\

rBEARING

_

CABLE DRUM

MOTOR ASSY J

Ct--COVER SE’T SCREWS

CLUTCH HOUSING

AIR GAP .10 TO .01

UTCH ARMATURE :100-133-4

Electric Trim Tab Actuator

Figure 208

A21

27-30-00

Oct

31/06Page

227

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTRIC TRIM TAB ACTUATOR INSTALLATION

I

bracket with the three

a.

Secure the actuator to its

b.

Connect the actuator cable at the aft

c.

Remove the shim

d.

Connect the actuator wire harness at the disconnect

e.

Install the aft

mounting

previously placed

fuselage

access

fitting

attaching

bolts

(Ref. Figure 208).

and at the turnbuckle.

between the cable drum and the

guard.

splices.

plates.

ELECTRIC TRIM TAB ACTUATOR CABLE REPLACEMENT

I

a.

b.

where it is

at the drum

pinned (Ref. drop paint point .)8piece 02 er ug iF

Mark the old cable with

Mark the

new

of tape

a

or a

of

at the

cable in relation to the old cable and install the

new

cable in the

same

location and

position

as

the

old cable. c.

Secure the cable

retaining pin

and wrap the cable around the drum. The

assembly

is

now

ready to

install in the

airplane. MAGNETIC CLUTCH REMOVAL a.

Remove the lid from the clutch

b.

Loosen the setscrew in the clutch rotor and armature hubs.

c.

Remove the motor from the clutch

d.

Slide the cable drum and shaft assembly from the clutch housing.

e.

Remove the clutch from the clutch

housing.

housing.

housing.

MAGNETIC CLUTCH INSTALLATION a.

Install the clutch in the clutch

b.

Slide the cable drum and shaft

c.

Tighten

housing.

assembly

into the clutch

the clutch armature setscrews until there is

no

housing.

visible end

play

in the cable drum shaft. Slide the clutch

rotor on the motor shaft to obtain 0.010- to 0.015-inch clearance between the friction surfaces of the clutch

before

tightening

the setscrews. Stake both setscrews. the clutch

d.

Install the motor

on

e.

Install the lid

the clutch

Oct

on

housing

with the

attaching

screws.

housing.

27-30-00

A21

Ral~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAGNETIC CLUTCH TORQUE TEST The

following

check should be

performed

any time the

clutch is

magnetic

replaced:

a 28-vdc power source, actuate the magnetic clutch with the red and white electrical leads. Use wrench to check that the clutch will hold with 30 inch-pounds applied at the actuator shaft.

a.

With

b.

If the static torque of the clutch is less than 30 Bolt the actuator to

1.

Fabricate

2.

a

a

a

plate

and

the

in

plate

a

burn in the clutch

as

screwdriver)

torque

follows:

vise.

rod that will fit the hole in the end of the drum shaft. Grind the rod

so

that it has

a

flat end

(like

to fit into the slot in the bottom of the hole.

Fit the other end of the rod to

3.

tighten

inch-pounds,

a

low

a

speed

motor

(450 rpm)

for

a source

of power to burn in the clutch.

14- to 16-vdc power, activate the magnetic clutch and run the motor for 15 seconds. Allow to cool for minute and check torque. When 30 inch-pounds of torque as checked in Step a. is achieved,

Using

4.

one

reassemble the unit and NOTE:

Exceeding

place

it back in service.

the 15-second-burn-in

magnetic clutch in period.

periods

may overheat and damage the magnetic clutch. Always allow the compressed air to prevent damage before doing another burn-

to cool and blow clean with

ELEVA TOR TAB INDICA TOR ADJUSTMENT a.

Loosen and back out the tab wheel

retaining

b.

Pull the tab wheel off the shaft until

stopped by

NOTE:

Removing

the tab wheel

more

screw

the

than 1/4 inch will

from 3/16 to 1/4 inch.

retaining

screw.

disengage

the tab wheel hub from the

sprocket

inside of the

pedestal c.

disengaged at this point, insert a knife blade or small screwdriver between the tab wheel edge of the reduction gear away from the tab wheel. With the reduction gears disengaged, turn the indicator to the desired position. Moving the indicator one tooth will change the indicator reading about 3/4 degree. If the indicator is not

and indicator and hold the

d.

Engage

the reduction gears and

tighten the

tab wheel

retaining

screw.

CHECKING ELEVATOR TAB FREE PLA Y the elevator tabs for any damage, security of hinge attach points and for tightness of the actuating Inconsistencies should be remedied prior to checking the free play of the tabs. The elevator tab should be systems. in as inspected specified Chapter 5.

Visually inspect

A check fixture

scale

(12 play

(P/N

810

45-135030-9) or the equivalent, refer to Figure 2 of 27-00-00, a dial indicator and a spring 27-00-00) for applying accurate loading to the tabs are required for making the inspection

and 13, Chart 1,

for free

of the tabs. lock the control surfaces to prevent movement of the elevators. Set the elevator tabs in neutral

a.

Securely position

b.

Affix the dial indicator check fixture

line and

A21

on

the outboard

edge

so

that the dial indicator

point is positioned

3.00 inches aft of the tab

hinge

of the elevator tab.

27-30-00

Oct

31/06Page

229

RByCheO´•

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

Apply

a

small

piece

of

masking tape (for paint protection)

centerline of the tab actuator. This will be the d.

Apply another piece

of

in the

masking tape

3.50 inches aft of the tab

hinge

line and

along

the

point of pressure against the tab by the push-pull scale.

corresponding position

on

the bottom surface of the tab for the

same

purpose. e.

Zero the dial indicator at

f.

With the

reading

push-pull

as

load

no

Do not reset

during

the

point of the masking tape, apply

scale at the

checking procedure.

a

full

3-pound

Release half the load until

h.

Apply

i.

Release half the load until

a

j.

Enter the recorded values

on a

full 3-pound

downward load is obtained. Record the dial

1.5-pound

a

load at the

upward

masking tape

on

1.5-pound upward load is obtained. Record the reading follows:

k.

Repeat Steps

I.

If deflection of the tab is within the allowable limits, the tab and its

linkage

copy of Chart 201 and

1.

MultiplyBby2and

2.

SubtractAfromeBand recordasX.

3.

Multiply

4.

Subtract C from 2D and record

D

by

2 and record

Add X and Y and record

If the free

m.

play

through j.

31/06Page

230

as

B.

reading

as

C.

D.

2D.

can

as

on

as

be

Y.

negative

numbers.

E.

the

opposite

elevator tab.

is excessive, disconnect the trim tab actuator rods and

for indications of excessive

Oct

proceed

as

as

recordas2B.

NOTE: The results of X and Y

b.

reading

the bottom surface. Record the

as

5.

downward load. Record the dial

A.

g.

a

initially.

wear.

Replace excessively

27-30-00

worn

are

in

good

visually inspect

condition. the bolts and

bushings

parts.

AZ1

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 Elevator Tab Free

Play Limits,

E

READING/CALCULATION

DESCRIPTION

A, dial reading with 3-pound downward load applied

on

8, dial reading with 1.5-pound downward load applied

C, dial reading with 3-pound upward load applied

on

D, dial reading with 1.5-pound upward load applied

elevator tab.

on

elevator tab.

elevator tab.

on

elevator tab.

A=

8=

C=

D=

28, calculation result of multiplying 8 by 2.

28

X, calculation result of subtracting A from 28.

X

28, calculation result of multiplying D by 2.

28

Y, calculation result of subtracting C from 2D.

Y

E, calculation result of adding X and Y.

E=X+Y=

8

28

D

28

2

x

A=

x

2

C

NOTE Maximum Allowable Elevator Tab Free

~al

Play Limits, Ehn,

0.006 inch.

27-30-00

Oct

31/06Page

231

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STALL WARNING-SAFE FLIGHT SYSTEM

DESCRIPTION AND OPERATION

The stall

warning system consists of the following major components: the lift computer, the lift transducer, the aural warning system, left hand landing gear squat switch, a stall warning self test switch, a 5-amp circuit breaker (furnishing power to the system), a heat panel for the transducer, a stall warning heat control relay and a 15-amp circuit breaker toggle switch (providing power to the heat panel). In

the system provides precise prestall warning to the pilot by activating the warning signal when are reached. The activation level of the warning tone is changed by the flap position.

general,

specific

lift coefficients

LIFT TRANSDUCER The transducer has

protruding transmits

0.75 vac, which is provided by the lift computer. A small vane a power requirement of 10 into the airstream responds to the change in lift coefficient of the wing with change in angle of attack, and

a

signal output

to the lift

computer.

LIFT COMPUTER The lift computer is a solid state electronic unit incorporating power distribution, computation, monitoring, test and warning functions. The computer will process signals from the lift transducer, the flap position switches, left hand

safety switch and a crew compartment test switch. The 101-380005-35 lift computer (non Proline 21 airplanes), will supply a modulated output ground signal and the 101-380005-39 lift computer (Proline 21 airplanes), will supply a constant ground signal when the speed ratio decreases below the value indicated for the flap position.

n25

27-31-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STALL WARNING-SAFE FLIGHT SYSTEM The Ground Functional Test is intended to be stall

a

TROUBLESHOOTING

troubleshooting procedure

to determine the proper function of the

warning components.

GROUND FUNCTIONAL TEST NOTE: This GROUND FUNCTIONAL TEST is it is not

a

troubleshooting procedure. Unless the system will not function or procedures, it is not necessary to perform

to calibrate it in accordance to the calibration

possible

this test. The lift computer is equipped with three adjustable potentiometers in the top of the computer. The are marked "O", "1" and "2" for full up, approach and full down flaps. With the a.

airplane

on

the

ground,

Connect the test box

(P/N

Locate the breakout box

a

functional test may be

SK100360

so

or

that the test

performed using

the

potentiometers

following procedure:

equivalent) between the lift computer and jacks are accessible (Ref. Figure 101).

the

airplane wiring

harness.

CAUTION: The anchor tab of the force

mounting plate

is

anchor tab. Refer to b.

applicator can be bent if the knob that applies tension to the transducer tightened. Use care when installing the force applicator to prevent damage to the the data supplied with the force applicator.

over

Install a force applicator with the appropriate gage las indicated in Chart 101), onto the left wing in accordance with the manufactures instructions. Refer to the data supplied with the force applicator. The force arm must be

positioned on

the

sure

that the

so

vane are

that the

applied force is within 1/32 inch of the transducer vane tip. Forces applied forward or up as "minus" and forces applied aft or down on the vane are classified as "plus". Make free to move with the force applicator.

classified

vane

is

NOTE: The 1952-3 gauge must be used when the tip gram values are less than 15 grams. Use the 1952-5 gauge only when it is necessary to exceed 15 tip grams. For the following procedure, start with the -3 gauge. c.

Place the stall

d.

Place the

e.

Apply

f.

Simulate

pins

warning

battery

heat circuit breaker switch in the OFF

switch in the ON

external power to the an

"in

position.

position.

airplane (Ref. Chapter 24-40-00).

flight" condition

as

follows:

Bypass

the

landing

gear safety switch

by placing the jumper

between

2 and 7 of the breakout box.

g.

Should the stall warning tone sound, warning signal (Ref. Figure 102).

h.

Runtheflapstothe FULLUPposition.

press the transducer

vane

aft

or

down with the force

applicator to stop

the

NOTE: Before

removing any component for repair or replacement, make sure that the system is receiving proper voltage, that all wiring checks out, that all connections are making proper contact and that all test equipment is functioning properly. The following voltage checks are made for the purpose of determining if the lift computer and lift transducer are functioning properly. These checks should be made before any adjustments are attempted. If the voltages are not correct, make sure that the correct part number components

an,

are

installed.

27-31-00

1/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Connect

test

The

Should the

i.

a digital voltmeter(ll, Chart 1, 27-00-00) to digital voltmeter should register 10.00 i 0.75 vac.

the lift

remove

range,

Special care

CAUTION:

necessary also

Connect

j.

a

to

computer for repair

approach

reading

the desired value

to observe the gage

voltage

test fail to

register within

the

test box.

specified

replacement.

should be exercised when

important

digital

or

points "24" and "25" (TP-25 is high) of the

the

carefully

straight

on

tip gram

values in the

following

tests. If will be

to minimize the effects of hysteresis in the gage. It is

to avoid parallex.

(TP-26 being low) and compare the voltage tip gram settings. The voltages across 26 and 28 are AC voltages magnitude with the lift transducer position and if they are not correct (assuming the 10 is correct) then the lift transducer should be removed for repair or replacement.

voltmeter to test

points

26 and 28 of the test box

to the values in Chart 101 at the various

in

varying vac

polarity

checked in

and

Step

i.

Con nect the

k.

digital voltmeter to test poi nts 22 and 2 of the test box (TP-2 being low) and compare the DC voltage tip gram settings. If the voltages are not within limits, (assuming that voltages checked in Steps i. and j. are correct) the lift computer should be removed for repair or

to the values in Chart 101 at the various

the AC

replacement. I.

digital voltmeter, check the voltage at test points (pins) 1, 4 and 10 of the test box. Pins 1 and 10 should voltage. Pin 4 should indicate 14 vdc or greater. On FL-I through FL-111 and FL-113 through FL152, FM-1 through FM-9, if there is no voltage at pin 10, confirm that Mandatory Service Bulletin 27-3095 has been complied with. FL-112, FL-153 and after and airplanes in compliance with SE 27-3095 should have bus voltage at pin 10. If not, check the wiring in accordance with the service bulletin or the B300 Wiring Diagram Manual as applicable. If there is voltage at pins 1 and 10, but no output from pin 4, remove the computer for repair or replacement. Using

a

indicate bus

NOTE: When stall

warning is activated, stall warning tone should pulse at a 1 hertz (Hz) rate and the pulse rate linearly to 10 Hz tone as force on the vane is increased in the forward or up direction. Stall activated when the tone is heard pulsing at a 1 Hz rate. is considered warning should increase

that the

m.

Make

n.

applicator. Press the transducer vane aft or down with a force of slowly release to the zero force. Readjust the force applicator and press the vane slowly forward or up. The stall warning tone should activate at a -1 i: 1.25 tip grams of force. Should the stall warning tone fail to sound within the indicated tip grams of force, the system may need to be calibrated (Ref. Stall Lift Computer Calibration).

sure

flaps

Install the 1952-1 gauge

approximately

+3

flaps to applicator,

Run the

p.

on

tip grams,

Return the gauge to 0

o.

are

tip

still in the FULL UP

position.

the force then

grams.

the APPROACH

position. Check

for 14 vdc

or

greater

at

pin

5 and 0 vdc

on

pin

6.

Using

the

press the vane fonnrard or up. The stall warning tone should activate at a -2 i 1.25 tip grams of force. Should the stall warning tone fail to sound within the indicated tip grams of force, the system may need to be calibrated. If either voltage reading is incorrect, reference the wiring diagram manual and check the flap force

wiring (Ref. Stall

I q.

Lift

Computer Calibration).

Return the gauge to 0

tip grams.

Install the 1952-3 gauge. Run the flaps to the FULL DOWN. Check for 14 vdc or greater at pin 6 and 0 vdc 5. Using the force applicator, press the vane forward or up. The stall warning tone should activate at

r.

on

pin

-6 i 1.25 tip grams of force. Should the stall warning tone fail to sound within the indicated tip grams of force, the system may need to be calibrated. If either voltage reading is incorrect, reference the wiring diagram manual and check flap wiring (Ref. Stall Lift Computer Calibration).

May

1/08Page

102

27-31-00

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

s.

Remove the 1952-3 gauge from the force applicator and push the vane full aft warning test switch. The stall warning tone should activate. If the test is

the stall

or

down, by hand, and actuate

positive,

release the switch and

If the

warning tone does not activate, check for a ground potential at pin 8 with the test switch held in test. If there is no ground potential, check the test switch and wiring in accordance with the 8300 Wiring Diagram Manual. If there is good ground potential, remove the lift computer for repair or replacement.

vane.

t.

Remove the electrical

from test

condition. Run the

FULL UP

ground flaps to the

point 7 of the test box. This will reestablish an airplane on ground position. Install the 1952-3 gauge on the force applicator and apply

-10

tip grams of force on the transducer vane with the stall warning test switch in OFF. The stall warning tone should not activate. If the warning tone is activated in this mode, check for a ground potential at pin 7. A ground potential could indicate

7,

remove

a

landing gear safety switch computer for repair or replacement.

fault in the

the lift

or

improper rigging.

If there is

no

ground potential

at

pin

u.

Release the force on the vane and remove the force applicator. Move the stall warning test switch to TEST position. The stall warning should activate. Should the warning tone fail to operate, connect the digital voltmeter to test points 16 and 2 (2 being ground) of the test box. Move the stall warning test switch to TEST and hold it in that position. Make sure the vane moves automatically to the forward or up stop. The digital voltmeter should read 15 f 4 vdc. If the voltmeter reading is not within specified limits, remove the lift computer for repair. Should the voltmeter reflect a correct reading, but the transducer vane fails to move to the forward or up stop, measure the voltage at the transducer. If the voltage is within limits, remove the transducer for repair or replacement.

v.

Remove external power from the

w.

Remove the test box and reconnect the lift computer to the

airplane (Ref. Chapter 24-40-00). Turn the battery switch OFF.

airplane

harness.

Chart 101 Lift Transducer Characteristics

TIP GRAMS

TP-26, TP-28

LT-3701-2

REFERENCE ONLY

TP-22, TP-2

AC MILLIVOLTS DC VOLTS /TOLERANCE

-12

427

9.2

0.75

-6

279

6.00 f 0.50

+6

0.0

0.00 f 0.50

USE 1952-5 GAGE FOR THE FOLLOWING: +18

nns

279

-6.00

0.75

27-31-00May

1/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: THE LOCALLY MANUFACTURED TEST BOX SHOULD BE WIRED AS A STRAIGHT THROUGH BREAKOUT BOX. ONE TEST POINT

(BANANA JACK) SHOULD BE

IN SERIES WITH

EACH PIN AND SOCKET OF THE CONNECTORS

PARTS LIST FOR LOCALLY MANUFACTURED TEST BOX

QUANTITY PER PART NUMBER

DESCRIPTION

AIRPLANE

AMP 205839-3

PLUG

1

AMP 205090-1 OR M39029/63-368

SOCKET FOR PLUG

AS REQUIRED

AMP 205089-1 OR M39029/64-369

PIN, RECEPTACLE

AS REQUIRED

AMP 205840-3

RECEPTACLE FOR TEST BOX

1

AMP 206070-1 OR AMP206322-1

BACKSHELLS

AS REQUIRED

CU-3006A

BUD MINI BOX

1

1506-102

TEST JACKS, RED

AS REQUIRED

1506-103

TEST JACKS, BLACK

AS REQUIRED

13168144-22-9

WIRE

AS REQUIRED

0000 0000

11

/0000 0009 0000 9000

00000

LIFT COMPUTER PLUG AMP 205840-3

DETAIL

A LIFT COMPUTER

SYSTEM WIRING

HARNESS-SEE THE APPROPRIATE WIRING DIAGRAM

MANUAL AMP 205840-3

AMP 205839-3

PLUG

SOCKET FL34B

SAFE FLIGHT P/N SK100360

Breakout Test Box

Figure

May

1/08Page

104

27-31-00

m365~AnAI

Hookup

101

A24

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIR FLOW

WARNING TONE MUST ACTIVATE AT THE CORRECT TIP GRAM SETTING AS THE VANE MOVES FROM THE AFT POSITION TO THE FWD POSITION

NEGATIVE TIP GRAMS

(CRUISE)

1

(STALL).

NVD POSITION

(STALL)

NEUTRAL

uisE)(O

TIP

GRAMS)

AFT POSITION

POSITIVE TIP GRAMS

VIEW LOOKING OUTBOARD ALONG LEADING EDGE OF LEFT WING R348 016J96AA.AI

Lift Transducer Vane Positions

Figure

A24

102

27-31-00

Page

yaM501

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STALL WARNING-SAFE FLIGHT SYSTEM The stall calibration

MAINTENANCE PRACTICES

warning maintenance practices in this chapter include procedure, and a transducer heater functional check.

ground

a

calibration

procedure,

an

in-flight

troubleshooting procedure to determine the proper function I of the stall warning components. Satisfactory completion of this functional test does not necessarily assure proper stall warning margin. (Stall warning margin is the number of knots that the stall warning tone precedes the stall speed.) If a lift computer or lift transducer is replaced, perform the Ground Calibration procedure or the flight check in accordance with the In-flight Calibration Procedure. If the stall warning system has failed in any manner or the stall warning margin has changed without explanation, perform the Ground Functional Check. If only an improper stall warning margin is suspected the functional check would not necessarily be required. The Ground Calibration procedure is recommended before a flight check, however, if it is impractical, an In-flight Calibration procedure may be performed without an initial Ground Calibration. If the flight calibration is not practical, the Ground Calibration check should provide stall warning margins that are within the specified tolerances. In order to set a specific margin, a flight calibration in accordance with the In-flight Calibration procedure would be required. The Pilot conducting the flight check must be experienced in conducting wings level, control column full aft, power idle stalls at entry rates no The GROUND FUNCTIONAL TEST is intended to be

greater than

one

a

knot per second.

LIFT TRANSDUCER HEA TERS a.

Apply

external power to the

airplane (Ref. Chapter 24-40-00).

high surface touching the vane or mounting plate. for extended periods of time could cause damage to the

WARNING: Do not leave the heaters with power

temperatures The

can cause

or

safety

Place the left main

c.

Place the stall

d.

The

e.

Make

f.

Place the stall

g.

Move the left main

h.

Place the stall

warning

i.

The

plate temperatures

j.

Make

k.

Place the stall

I.

Remove external power from the

m.

Return the left main

and

vane

sure

landing

warning

gear

for

more

than ONE minute. Since the

switch in the ON GROUND condition.

heat switch in the ON

position.

plate temperatures will rise noticeably within

that the heaters

and

applied

extreme caution when

of power in still air other parts of the Lift Transducer.

b.

sure

use

application

heaters

vane

burns,

are

warning switch

landing

in the OFF

gear

safety

are

will rise

and allow the

momentarily

vane

with

a

moistened

fingertip.

with

a

moistened

fingertip.

to cool.

dN position. noticeably

within 30 seconds.

operating by touching

switch in the OFF

landing

position

the surface

switch to IN AIR condition.

heat switch in the

that the heaters

warning

operating by touching

30 seconds.

position

the surface

and allow the

momentarily

vane

to cool.

airplane (Ref. Chapter 24-40-00).

gear switch to the ON GROUND condition.

27-31-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STALL LIFT COMPUTER CALIBRA TION

ON GROUND

NOTE: This procedure must be performed in its entirety and in sequence. All of the calibrations The operator should not try to perform only one calibration function. a.

Remove the carpet and cabin center aisle floor board forward of the

b.

Make

c.

Remove the

d.

Disconnect the left main

sure

the stall

heat switch located

warning

potentiometer

access cover

landing

gear

on

the

from the stall

safety

pilot

wing

inboard sub

are

to be

completed.

spar.

panel

is in the OFF

position.

warning computer.

switch rod from the torque link and simulate

an

IN AIR condition.

applicator can be bent if the knob that applies tension to the transducer tightened. Use care when installing the force applicator to prevent damage to the the data supplied with the force applicator

CAUTION: The anchor tab of the force

mounting plate

is

over

anchor tab. Refer to

Install the force

e.

applicator

with gauge number 1952-1 onto the left wing in accordance with the manufacturer’s supplied with the force applicator. The force arm must be positioned so that the

instructions. Refer to the data

applied force

is within 1/32 inch of the transducer

f.

Make

g.

Turn the

h.

Apply

i.

Place the external power switch to the ON

j.

Flaps

sure

that the

vane

airplane battery

is free to

move

with the force

switch to the ON

external electrical power to the

vane

tip (Ref. Figure 201). applicator

installed.

position.

airplane (Ref. Chapter 24-40-00).

position.

retracted calibration:

WARNING: Make

sure

with this

NOTE: When stall

personnel and equipment

that all

are

clear of the

flap

areas

before

proceeding

procedure. warning tone should pulse at a 1 hertz(Hz) rate and the pulse linearly to 10 Hz tone as the force on the vane is increased in the forward or up warning is considered activated when the tone is heard pulsing at a 1 Hz rate.

warning

is activated, the stall

rate should increase

direction. Stall 1.

Run the

2.

Deflect the transducer

3.

warning tone is not sounding, proceed to step 4. If the stall warning tone is sounding, turn the No. 0 potentiometer on the computer counterclockwise (CCW) until the tone just stops sounding. Then tu m the potentiometer clockwise (CW) until the tone just starts to sound. Proceed to step 5.

4.

If the stall

k.

warning sounding.

Reduce force force

6.

vane

position.

forward until the gauge reads -1.0 f 0.2

tip

grams.

on

tone is not

sounding,

the transducer

vane

turn the No. 0

using

the force

potentiometer on

applicator

the computer CW until the tone

until the tone stops

sounding.

just

Increase the

being applied to the vane to allow it to move forward or up until the tone just starts to sound. The gauge

should indicate -1.0 f 0.2

tip grams.

Return the gauge to 0

grams.

Approach flaps

May

to the FULL UP

If the stall

starts

5.

flaps

tip

calibration:

27-31-00

P124

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1.

Run the

2.

Deflect the transducer

3.

If the stall 1

flaps

warning

potentiometer

potentiometer 4.

vane

sounding, proceed

the computer (CW) until the tone

clockwise

Reduce the force

Return

up until the gauge reads -2 f 0.2

on

to

step

counterclockwise

the transducer

just

(CCW)

using

warning tone is sounding, turn the No. just stops sounding. Then turn the

until the tone

starts to sound. Proceed to

turn the No. 1

vane

4. If the stall

tip grams.

potentiometer on

the force

applicator

step 5.

the computer clockwise

until the tone stops

to the vane to allow it to move forward or up until the tone

being applied

gauge should indicate -2

I.

or

warning tone is not sounding, just starts sounding.

the force

6.

forward

tone is not

on

position.

If the stall the tone

5.

to the APPROACH

0.2

just

(CW)

sounding.

until

Increase

starts to sound. The

tip grams.

theforceto0tipgrams.

Flaps down calibration: 1.

Remove the 1952-1 gauge and install the 1952-3 gauge. Run the flaps to the FULL DOWN position.

2.

Deflect the transducer

3.

If the stall

warning

vane

forward

tone is not

or

up until the gauge indicates

sounding, proceed

to

step

a

4. If the stall

-6

0.2

warning

tip grams.

tone is

sounding,

turn the No.

potentiometer on the computer counterclockwise (CCW) until the tone just stops sounding. Then turn the potentiometer clockwise (CW) until the tone just starts to sound. Proceed to step 5.

2

4.

If the stall the tone

5.

warning tone is not sounding, just starts sounding.

Reduce the force the force

on

the transducer

being applied

turn the No. 2

vane

using

potentiometer

the force

gauge should indicate -6 f 0.2

tip

Place the external power switch to the OFF

7.

Remove external power from the airplane (Ref. Chapter

8.

Turn the

9.

Remove the force applicatorfrom the airplane.

airplane battery switch

11. Install the

to the OFF

landing gear safety

potentiometer

access cover on

12. Install the cabin floor board

or

the computer clockwise

until the tone stops

up until the tone

just

(CW)

until

sounding. Increase

starts to sound. The

grams.

6.

10. Connect the left main

applicator

to the vane to allow it to move forward

on

panels

position.

24-40-00).

position.

switch rod to the torque link. the stall

warning computer.

and the carpet.

STALL LIFT COMPUTER C-ALIBRA nON

IN AIR

procedure should result in a stall warning margin that falls within the tolerances procedure. However, flight calibration may produce tip gram values that differ from the ground calibration or may fall outside the acceptable limits of the ground calibration procedure. It is

NOTE: The Ground Calibration

specified

in this

27-31-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

permissible to readjust the computer in the air to achieve the required stall margin or to set a specific margin specified. Any adjustments preformed during the Flight Calibration procedure take precedence over the Ground Calibration procedures.

within the tolerances

a.

Remove the carpet and cabin center aisle floor board

b.

Remove the Prior to

c.

potentiometer

flight, adjust weight

access cover

and C.G.

so

panels forward of

from the stall

the spar.

warning computer.

that the test will be conducted at 12,600

13,000 pounds with the C.G.

at F.S. 197.3 to F.S. 200.4.

d.

When in the test area, at

parameters specified Place the

e.

NOTE:

propeller

During

the

a

safe altitude and in smooth air, check that the

in step

weight

and balance

are

within the

c.

levers full forward.

performance

of the

following steps in this procedure, stall is defined as the moment the control speeds will be within the range shown in Chart 201 if the

column contacts the full aft stop. Actual stall maneuver is executed correctly. f.

Flaps retracted 1.

2.

calibration:

gear UP and the power set to idle, trim the airplane to 135 KIAS. Slowly reduce greater than one knot per second. Record the air speed when the warning tone just starts to sound, then continue to reduce air speed until the airplane stalls. Record the stall speed. The stall warning tone should sound at an airspeed 5 14 knots prior to the stall speed. With the

and

air

rate not

flaps speed at a

airspeed, adjust potentiometer No. 0 until the stall warning prior adjustment increases the air speed at which the stall warning the air speed at which the stall warning tone sounds. One full A decreases CCW sounds. tone adjustment will the air of the turn change speed by approximately 3 knots. potentiometer If the stall

warning

sounds within 5

g.

landing

tone did not sound at proper to stall. A CW

14 knots

Approach flapscalibration: 1.

flaps set to the APPROACH position, landing gear in the UP position, and the power set to idle, airplane to 122 KIAS. Slowly reduce air speed at a rate of no greater than one knot per second. Note the airspeed when the warning tone just starts to sound, then continue to slowly reduce air speed until the airplane stalls. Record the stall speed. The stall warning tone should sound at an airspeed 5 12 knots prior to the stall speed. With the trim the

2.

airspeed, adjust potentiometer No. 1 until the stall adjustment increases the air speed at which the prior warning stall warning tone sounds. A CCW adjustment decreases the air speed at which the stall warning tone sounds. One full turn of the potentiometer will change the air speed by approximately 3 knots. If the stall

warning

tone did not sound at the proper

sounds within 5

h.

12 knots

to the stall. A CW

Full

flaps

1.

flaps and landing gear in the DOWN position, and the power set to idle, trim the airplane to 110 Slowly reduce air speed at a rate no greater than one knot per second. Record the airspeed when the stall warning tone just starts to sound, then continue to slowly reduce air speed until the airplane stalls. Record the stall speed. The stall warning tone should sound at an airspeed 5 11 knots prior to the stall speed.

down calibration:

With the KIAS.

May

1/0827-31-00

n24

Hawker BeeChCraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

2.

airspeed, adjust potentiometer No. 2 until the stall prior to the stall. A CW adjustment increases the air speed at which the stall the stall warning tone sounds. A CCW adjustment decreases the air speed at which the stall warning tone sounds. One full turn of the potentiometer will change the air speed by approximately 3 knots. if the stall

warning

warning

tone did not sound at the proper

sounds within 5 -11 knots

i.

Install the potentiometer

j.

Install the cabin floor board

access cover on

panels

the stall

warning computer.

and carpet.

Chart 201 Stall

Speeds

Required Stall Speeds Flaps Up Position

86 to 94 KIAS

Flaps Approach Position

77 to 85 KIAS

Flaps Down Position

69 to 77 KIAS

(Knots Indicated

Air

Speed)

27-31-00

Page

yaM502

1/08

Hawker BeechcraPt

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

r~7i

/8

I´•

2

a

I

1~ j

i.

INSERT POSITIONER ANCHOR TAB

(3)

INTO VANE

5.

TURN SCREWS

(2)

AND

GAGE PRESSURE ARM

OPENING.

OF VANE

(8)

(6) AS REOUIRED TO BRING (7) TO BEAR ON SURFACE

WITHIN 1/32" OF TIP.

ONTOTHE MOUNTING PLATE.

2.

HOOKANCHORTAB(3)

3.

KEEPING ANCHOR TAB ENGAGED, SHIFT POSITIONER

FOR NEGATIVE

UNTIL CONE POINTS

SURFACE FOR POSITIVE

6.

SCREW HEADS

(4)

ENTER RECESSES IN THE

TURN

(8)

TIP GRAMS AND FORWARD

TIP GRAMS.

(5). 7.

4.

APPLY PRESSURETOAFTSURFACE OFVANE

SCREW(I)

COUNTERCLOCKWISE UNTIL KNOB

TURN SCREW

(6) TO ADJUST FORCE (TIP GRAMS)

AS REC1UIRED.

CLUTCH SLIPS. FW48 016395~/11

Force

Applicator

Figure

May

1/08~9’m"8"

27-31-00

201

A24

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FLAPS The

flaps,

DESCRIPTION AND OPERATION two

on

each

wing,

are

driven

by

an

electric motor

through

a

gearbox

mounted

on

the forward side of the

spar. The motor incorporates a dynamic braking system, through the use of two sets of motor windings, which helps to prevent overtravel of the flaps. The gearbox drives four flexible driveshafts connected to jackscrews at each

rear

flap.

A

cause

safety mechanism is provided to disconnect power to the electric motor flap to be three to six degrees out of phase with the other flaps.

in the event of

a

failure which would

any

The

flaps are operated by a sliding lever located just below the condition levers on the pedestal. Flap travel from O% (full up) to 100% (full down) is registered in percentage on an electric indicator on top of the pedestal near the flap control lever. The flap control has a position detent provided to select 40% flaps for approach. Full flaps is approximately 35". The indicator is operated by a potentiometer driven by the right hand inboard flap. Any of the three flap positions, UP, APPROACH or DOWN may be selected by moving the flap selector lever up or down to the selected switch position indicated on the pedestal. The

flap motor power circuit is protected by a 20-ampere circuit breaker placarded FLAP MOTOR and located on right circuit breaker panel. A 5-ampere circuit breaker, placarded FLAP CONTROL, for the control circuit is also located on this panel.

the

The

landing gear warning system is effected by the position of the flaps. Anytime the flaps are set in the approach position and the landing gear is not extended, a warning horn will sound until the gear is extended or the flaps retracted.

nat

27-50-00

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FLAPS - MAINTENANCE PRACTICES

200200200

FLAP REMOVAL NOTE: Prior to removal of each inboard flap, partially extend the flaps and disconnect the flap safety mechanism from the bracket at the outboard end of the flap. On the right hand inboard flap only, disconnect the linkage to the flap position transmitter from the bracket located on the leading edge of the flap approximately 19 inches outboard of the inboard flap track. a. Place the flap control switch in the DOWN position. When the flaps are fully down, pull the flap motor control circuit breaker located on the fuel panel beside the pilot’s seat. b. Remove the bolt, washers and nut securing the flap actuator to the brackets on the leading edge of the flap. Slide the end of the actuator free of the brackets and remove the bushing from the end of the actuator (Ref. Figure 201 and Figure 202). NOTE: Measure the extension of the flap actuator screw so it can be installed in its original position. c.

Remove the access plugs from the top of the flap on each side of the inboard and outboard roller brackets.

d. Disconnect the end of the bonding cables from the flap brackets. e. Remove the bolts, washers and nuts connecting the forward end of the flap brackets to the forward track of the wing brackets. f.

While providing support for the flap, remove the bolts, washers and nuts securing the flap to the aft track of the wing brackets, then remove the flap from the wing.

g. Remove the rollers and bearings from the tracks of the wing brackets. Note the correct position of the nylon washers with respect to the flanged rollers and the track bearings to facilitate installation. CAUTION: Never operate the flaps with the right hand inboard flap removed as the limit switches will be inoperative and serious damage to the flaps, wings and actuating system can result.

FLAP INSTALLATION a. Position the small flange rollers and nylon washers in the forward tracks of the wing brackets and the wide flange rollers and nylon washers in the rear tracks of the wing brackets (Ref. Figure 201 and Figure 202). CAUTION: To prevent flap track damage, install the flap rollers so that the flanges (with a nylon washer between each flange and the track) are facing each other, that is, to the center of the flap. b. Align the holes in the flap brackets with the rollers in the tracks of the wing brackets and install the bolts, washers and nuts securing the flap to the wing. NOTE: The clearance noted in Figure 201 must be maintained between both flaps and between the outboard flap and the aileron. The gap between the outboard flap and the aileron should be 0.19 inch + 0.21/ -0.09 constant within ± 0.06 from leading edge to trailing edge, except dimensions do not apply where the aileron tapers outboard. c.

Ascertain that the flap actuator screw is extended to the same degree as was marked upon removal, then reinstall the bushing in the end of the screw.

d. Align the end of the actuator screw with holes in the brackets on the flap and install the bolt, washer and nut securing the end of the actuator in place.

A28

27-50-00

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Flap and Aileron Installation Figure 201 e. Partially retract the flaps, then reconnect the safety switch mechanism to the bracket on the outboard end of the flap. On the right hand inboard flap only, reconnect the mechanism of the flap position transmitter to the bracket located on the leading edge of the flap approximately 19 inches outboard of the inboard flap track. f.

Install the access covers on the wings above and below the flap actuators. Install the access plugs on each side of the flap brackets for the flap rollers.

g. Check the flap system for proper rigging.

FLAP DRIVE CABLES To ascertain correct installation, flap drive cables are identified by color bands as well as by part numbers. These bands indicate direction of internal cable twist or lay. The color codes are as follows: a. Red band for right lay cables (right outboard or left inboard flap). b. Green band or no band for left lay cables (left outboard or right inboard cables). NOTE: The rear-mounted cables at the flap gearbox drive the outboard actuators, the forward-mounted cables drive the inboard actuators.

Page 202 May 1/10

27-50-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Flap Control System Figure 202

A28

27-50-00

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FLAP TRACK WEAR LIMITS The allowable track wear on the bearing surfaces of the outboard tracks is 0.032 inch, resulting in a maximum flap track dimension of 0.785 inch. On the inboard flap tracks the allowable wear is 0.038 inch, with a maximum flap track dimension of 1.038 inch. The allowable wear into the track side surface is 0.050 inch (Ref. Figure 203). Track wear within the above limitations may be dressed smooth with light emery cloth to prevent roller binding. To help reduce wear, it is recommended that the tracks and rollers be kept clean and lubricated using a dry spray lubricant (Item 6, Chart 2, 27-00-00). The teflon chafing washers should also be kept in good condition.

FLAP TRACK REPAIR NOTE: New inboard flap track slot dimensions (dimension A) are 0.997 to 1.00 inch with an allowable wear dimension up to 1.038 inch. New outboard flap track slot dimensions (dimension A) are 0.750 to 0.753 inch with an allowable wear dimension up to 0.785. The maximum allowable side wear (dimension B) on any flap track is 0.050 inch below the original surface (track plane) (Ref. Figure 203). WARNING: If the track is worn beyond the maximum allowable dimension, Repair must not be attempted. Replace excessively worn flap tracks. a. Clean the area of the track that is to be repaired with solvent (Item 7, Chart 2, 27-00-00) or equivalent solvent. (Ref. Figure 203). b. Roughen the area to be repaired with 180-grit emery cloth. c.

Clean the roughened area with soap and water, rinse and dry with a lint-free cloth or blow dry with filtered shop air.

B A

A

1900-40-7

Flap Track Wear Limits Figure 203 Page 204 May 1/10

27-50-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL NOTE: Epoxy (Item 8, Chart 2, 27-00-00) should be used in repair areas with less than 0.02 inch wear. Epoxy (Item 9, Chart 2, 27-00-00) should be used in repair areas with 0.02 inch or more wear. d. Select the type of epoxy as dictated by the amount of wear and mix a sufficient amount to perform the repair. e. Apply the epoxy to the worn area and allow it to cure until hard enough to work. f.

When sufficiently hard, work the epoxy repair into the original track dimension.

g. Finish the repair with 320-grit emery cloth. h. Apply coating (Item 12, Chart 2, 27-00-00) to the repair area. i.

Apply one coat of zinc chromate primer.

j.

Do not operate the flaps until the epoxy repair has fully hardened.

NOTE: The epoxy should be fully cured in approximately 6 to 8 hours in an environment of at least 60° F.

FLAP MOTOR AND GEARBOX REMOVAL a. Remove the center aisle floorboard immediately forward of the rear spar. b. With the flap motor control circuit breaker pulled, disconnect the electrical leads from the flap motor and identify with tags to facilitate correct installation. c.

Remove the safety from the retaining nuts securing the flexible shafts to the gearbox, then remove the retaining nuts.

d. Remove the nuts from the studs and remove the motor and gearbox from the airplane. e. Remove the two screws securing the flap motor to the gearbox.

FLAP MOTOR AND GEARBOX INSTALLATION a. Secure the flap motor to the gearbox with the two retaining nuts. b. Install the nuts on the studs to secure the motor and gearbox to the rear spar. c.

Connect the electrical leads to the flap motor and remove the identification tags from the wiring.

d. Connect the flexible shafts to both sides of the gearbox with the retaining nuts, then safety the nuts. e. Cycle the flap system to check the rigging. Ascertain that no rollers bottom out at either end of travel and that the flaps are synchronized. f.

Install the center aisle floorboard over the flap motor and gearbox assembly.

FLAP ACTUATOR REMOVAL a. Fully extend the flaps and disconnect the actuator from the flap. b. Remove the inspection plate from the lower surface of the wing and uncouple the flexible drive shaft. c.

Remove the mounting bolts and actuator from the bracket.

A28

27-50-00

Page 205 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL d. Remove the bushings from the actuator.

FLAP ACTUATOR INSTALLATION a. If a new or overhauled actuator is being installed, ascertain that the tape placed over the vent hole for shipping has been removed. b. Position the actuator with its vent hole up and install the mounting bolts and bushings. c.

Connect the drive shaft and replace the access cover. The cable has squared ends.

d. Extend the actuator until the flap synchronizes with the next flap, then connect the actuator to the flap. e. Check the flap rigging. f.

If a new or overhauled actuator is installed, lift lightly on trailing edge of the flap while running the flaps through a complete extension and retraction cycle. There should be no roughness or indication of binding in actuator.

FLAP CONTROL SYSTEM RIGGING WARNING: A voltage requirement of 28.5 ± 0.25 vdc, using auxiliary power unit, must be maintained during all flap system rigging operations. Do not exceed more than one flap cycle every 10 minutes. More than one cycle every 10 minutes will reduce service life. NOTE: Loosen the switch bracket attach screws (2 per bracket) before attaching the switches by either tightening or loosening the cap screws. Retighten the switch bracket attach screws after adjustment has been made. a. Disconnect the actuators from all four flaps. b. Raise and lower each flap by hand to assure freedom of movement with no binding. c.

Connect the actuator to the right hand inboard flap.

d. Adjust the up-limit switch so the right hand inboard flap is within wing contour limits. e. Adjust the downlimit switch to obtain 35° +1° -2° of flap travel. f.

Individually connect the actuators to each of the other three flaps, and synchronize each flap with the right hand inboard flap. Actuator lengths can be adjusted by screwing the pushrod in or out of the actuators. A finer adjustment can be obtained, if required, by disconnecting the cable at the right angle drive or at the motor gear box and rotating the cable 90° in either direction.

g. After fully up and fully down rigging has been completed, run the flaps down and check the position indicator. If the indicator does not show 100% flaps, loosen the transmitter arm bolt and rotate the transmitter shaft until the reading is correct, then tighten the transmitter arm bolt. h. Run the flaps up and check the position indicator for 0% flaps. If the indicator is not correct, lower the flaps and lengthen (if greater than 0%) or shorten (if less than 0%) the position-transmitter fork to correct approximately one-half of the indication discrepancy. i.

After the indicator travel has been corrected, adjust the transmitter arm as in step g.

j.

Adjust the approach flap limit switches to stop the flaps at 14° ± 1° (40%). Check the position indicator needle to make sure that it is within the white band.

Page 206 May 1/10

27-50-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL NOTE: Do not alter the limit-switch settings to compensate for a faulty indicating system. When the approach downlimit and landing gear warning cam (Ref. Figure 204) is properly adjusted, the landing gear warning horn will sound when the flaps are set in the UP or APPROACH position and the landing gear is not extended. If the flaps are in the UP or APPROACH position, the tone can be silenced by pressing the GEAR WARN SILENCE button adjacent to the landing gear control switch; the in-transit lights in the landing gear control switch handle cannot be extinguished. If the warning tone has been silenced, the landing gear warning system will be rearmed when the power lever(s) are advanced sufficiently. With the flaps beyond the APPROACH position, the warning tone and in-transit lights will be activated regardless of the power lever settings, and can only be cancelled by extending the landing gear.

Flap Limit Adjustment Cams Figure 204

A28

27-50-00

Page 207 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FLAP SAFETY MECHANISM The safety mechanism arms must be detached from the leading edges of the flaps before the flaps are removed from the wings. These arms are adjacent to each other at the area between the inboard and outboard flaps. Detach by removing the nuts from the bolts where the arms attach to the flaps. Note the sequence of hardware removal for later installation (Ref. Figure 205). Split-flap protection is provided by an asymmetrical flap switch system. This switch is rigged to shut off the flap motor for any out-of-phase condition of three to six degrees between flaps. This switch is spring-loaded to the normally closed position, but is rigged so that the roller cam holds the switch in its momentary (normally open) position to provide electrical continuity to the flap motor when the outboard and inboard flaps are parallel and in phase with one another. a. Set the switch so that its actuator is on the roller cam when the flaps are parallel. FLAP SAFETY SWITCH FUNCTIONAL TEST a. Connect the airplane to an external power source. Turn the external power and battery switches ON. b. Extend the flaps to the full down position. c.

Open the flap indicator/control circuit breaker.

d. Disconnect the right hand outboard flap adjustable rod by removing the arm attach bolt. e. Manually reposition the arm until the roller cam has allowed the safety switch roller to move off the cam lobe. Secure disconnected parts to prevent damage if flap moves. f.

Select flaps UP. Reset the circuit breaker. The flaps should not retract.

CAUTION: Be prepared to immediately shut off the Master Switch, should the flaps start to retract. g. If the flaps retract, replace the flap safety switch and re-rig the flap system in accordance with procedures listed in FLAP CONTROL SYSTEM RIGGING. Proceed to step j listed below. h. Select flaps DOWN. Open the flap indicator/control circuit breaker. i.

Connect the flap adjustable rod to the outboard flap.

j.

Perform steps c through i on the left hand side.

k.

Retract the flaps.

l.

Turn OFF all electrical power and disconnect external power.

Page 208 May 1/10

27-50-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Safety Switch Rigging Figure 205

FLAP ACTUATOR PISTON LUBRICATION (1200 HOURS) a. Extend the flaps to full down position. b. Inspect the actuator for any signs of leakage or external damage. If found, replace or repair actuator as required (Ref. Component Maintenance Manual, B300 Series - Flight Controls - Maintenance Practices). c.

Locate the vent hole on upper side of installed actuator (approximately 1/2 inch above from part identification tag). The vent hole diameter is about 0.063 to 0.065 inch.

d. With the actuator extended, apply 1/3 to maximum 1/2 oz. of lubricating oil (Item 17, Chart 2, 27-00-00) using a plastic tube and syringe. Clean the outside of actuator from any oil. CAUTION: Do not use any other type of oil. e. Cycle the actuator a minimum of 3 cycles, observe for any oil overflow from the vent hole. If overflow exhibits, clean and recycle the actuator until clear of overflow. If no overflow is seen, lubrication is completed.

A28

27-50-00

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FLAP FLEXIBLE DRIVESHAFT INSPECTION AND REPAIR Cuts or nicks that penetrate the outer plastic housing may allow moisture to enter, promoting lubrication failure and internal corrosion. Such housing damage within the pressurized compartment may be especially harmful. Any pressurization air leakage through the housing, though minor, may carry significant amounts of moisture, condensing and pooling in the colder outboard portion of the drive-shaft assembly. Inspect the drive-shaft housing for nicks and cuts that penetrate. Replace the drive shaft or patch with tape (Item 15, Chart 2, 27-00-00). If patching, clean the area with naphtha (Item 16, Chart 2, 27-00-00) and wipe dry. Apply the tape with a spiral wrap, tight and wrinkle free, overlapping each wrap by two-thirds. The patch should extend a minimum of two inches on each side of the damaged area. The free end of the tape patch may be additionally secured with one or two small nylon tie wraps. Inspect the condition of the ends of the flexible shafts. Replace the assembly if either square shaft end is frayed or worn to less than 0.172 inch measured between any two adjacent corners.

Page 210 May 1/10

27-50-00

A28

Raylheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

GUST LOCKS AND DAMPER

MAINTENANCE PRACTICES

CONTROL LOCKS The control locks consists of the

U-shaped clamp

and two

pins connected by

a

chain. The

pins lock

the

primary flight

engine power control levers and serves to wam the pilot not to start U-shaped clamp with the control locks installed. It is important that the locks be installed or removed together to preclude

engines possibility of flight controls. the

a

fits around the

controls and the

an

attempt

to taxi or

fly the airplane

with the power levers released and the

pins still installed

in the

1

L_

f~lr

iiC~I

1 i

~----1

lillil 00

Control Lock Installation

Figure

201

27-70-00

Oct

31/06Page

201

Raytheon

AiKraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTROL LOCK REMOVAL WARNING: Before

starting

the

engines,

remove

the control locks.

rudderpin.

a.

Removethe

b.

Remove the control column

c.

Remove the

U-shaped

pin.

power control

clamp.

WARNING: Remove the control locks before is installed, serious

damage

towing the airplane. If towed with steering linkage can result.

a

tug while the rudder lock

to the

CONTROL LOCK INSTALLATION a.

Position the

b.

Move the control column

NOTE: The holes c.

around the

engine

necessary to

align

U-shaped clamp

are

as

aligned

power controls.

the holes in the control column and install small

when the control wheel is full forward and rotated

approximately

pin.

15" to the left.

L-shaped pin through the hole provided in the floor aft of the rudder pedals. The rudder pedals must align the hole in the rudder bellcrank with the hole in the floor. The pin is then inserted until the flange is resting against the floor. This will prevent any rudder movement. Insert the

be centered to

Oct

31/0627-70-00

CHAPTER

FUEL

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 28

FUEL

TABLE OF CONTENTS

SUBJECT

PAGE 28-00-00

Fuel

Descriptionand Operation. SpecialTools and Recommended Fuel- Troubleshooting Fuel

....1

............____

Materials.

................._

................._

.............._

................._

............_6

Maintenance Practices

Servicing

the Fuel

.......1

System

................._

.......1

28-10-00

Storage-

Maintenance Practices

...201

Nacelle Fuel Cell Removal

......201

Nacelle Fuel Cell Installation

.....202

Inboard

Leading Edge Fuel Cell Removal Inboard Leading Edge Fuel Cell Installation Outboard Leading Edge Fuel Cell Removal Outboard Leading Edge Fuel Cell Installation. AftOutboardWing CenterFuel Cell Removal AftOutboardWing CenterFuel Cell Installation Aft Inboard Wing Fuel Cell Removal. Aft Inboard\l\ling Fuel Cell Installation Auxiliary Fuel Cell Removal Auxiliary Fuel Cell Installation. Leakage Checks and Repairs (WetWing Fuel Cells). Fuel Cell LeakageTest. Uniroyal Fuel Cell Repair GoodyearFuel Cell Repair

.............206 ............206 ............209 ..........209 ................._

..........210 .........210 .211

................214

.....214 ...215 ....218 ........219 .......221 ......221

Fuel Cell Preservation. 28-20-00 Fuel Distribution- Maintenance Practices

Fuel

Fittings. Engine Fuel Filters and Screens. Engine-Driven Fuel Boost Pump Removal Engine-Driven Fuel Boost Pump Installation. Standby Boost Pump Removal. Standby Boost Pump Installation JetTransfer Pump Removal JetTransfer Pump Installation

..............201 ........._____

.201 .........__201 .........____

........._201

.........____

.203 .....205 ...205

Firewall Shutoff Valves

.........205

Firewall Shutoff Valve Removal Firewall Shutoff Valve Installation.

..205

Crossfeed Valve Removal.

na,

.205

................._

Firewall Shutoff Valve Functional Check Crossfeed Valve

..203

..........._.206 ................._

................._

28-CONTENTS

......206

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 28 TABLE OF CONTENTS

FUEL

(CONTINUED) PAGE

SUBJECT Crossfeed Valve Installation

206

Fuel

207

Purge

Line CheckValve

Motive FlowValve Motive FlowValve Removal.

207 207

Motive FlowValve Installation Firewall

FilterCleaning Reset Fuel FilterBypass Indicator. Integral FuelTankAccess DoorRemoval Integral FuelTankAccess Doorlnstallation

........209

209 210 210

28-40-00

Indicating Description and Operation Capacitance Fuel Quantity Indicating System Fuel Quantity Sensor Fuel Capacitance Probes. Indicating- Troubleshooting System Insulation Check System Capacitance Check. Indicator Linearity Check(nota system calibration) System Calibration Empty Tanks Calibration (Preferred Procedure) Full in Tank Calibration (Alternate Procedure Only)

1 1

2

......101 101 103 104

110 111

Probes Bench Test

Water Test

Indicating-

Maintenance Practices.

Nacelle Fuel

Quantity Probe Removal. Nacelle Fuel Quantity Probe Installation Fuel Quantity Probe Inspection Fuel Quantity Probe Removal for the Inboard Leading Edge and Inboard Aft Fuel Cells Fuel Quantity Probe Installation for the Inboard Leading Edge and Inboard Aft Fuel Cells. Fuel Quantity Probes Removal forthe Integral (Wet Wing) Fuel Cell Fuel Quantity Probes Installation for the Integral (Wet Wing) Fuel Cell. Fuel Quantity Liquid Level Sensor Removal Fuel Quantity Liquid Level Sensor Installation.

Page

yaM2

1/08

28-CONTENTS

201 201 201 202 202 202 203

203 204 204

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

28-LOEP

1

May

1/08

28-TOC

1 and 2

May

1/08

28-00-00

1 thru 11

Mar 9/01

28-10-00

201 thru 222

May

28-20-00

201 thru 211

Oct 31/06

28-40-00

1 and 2

Oct 31/06

101 thru 115

Oct 31/06

201 thru 205

Oct 31/06

A24

Pages

1/08

28-LOEP

May

1/08Page

1

Raytheon Aircraft BEECH SUPER KING AIR MODEL 8300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

FUEL The fuel

system consists of a series of rubber bladder-type cells and an integral (wet wing) tank in each wing conby a crossfeed line controlled by a valve. The separate fuel system for each engine is further divided into a main and auxiliary fuel system with a total usable fuel capacity of 539 gallons. The main fuel system in each wing consists of a nacelle tank, two wing leading edge tanks, two box section tanks and an integral (wet wing) tank, all interconnected to flow into the nacelle tank by gravity. The total usable fuel capacity of the main fuel system is 380 gallons. The filler cap for this system of tanks is located on the leading edge near the wing tip. The auxiliary fuel system consists of a fuel tank on each side of the center section. Each tank is equipped with its own filler opening and each tank has a usable capacity of 79.5 gallons. When the auxiliary fuel system is being used, fuel is transferred from it to the main fuel system by a jet pump mounted adjacent to the outlet strainer and drain in the auxiliary fuel cell. nected

The main and in each

wing.

auxiliary fuel systems are equipped with five sump drains, a drain manifold and a firewall filter drain The drain valve for the firewall fuel filter is located to the right of the filter at the firewall on the underside

of the nacelle. The nacelle tank has two drains located

on

the bottom center of the nacelle forward of the wheel well.

The inboard drain is for the The

leading edge

fuel tank has drain for the

wing

standby boost pump and the outboard drain is for the nacelle fuel sump and strainer. tank has a drain on the underside of the wing just outboard of the nacelle. The integral (wet wing)

sump drain located approximately midway on the underside of the wing aft of the main spar. The auxiliary tank is at the wing root midway between the main and aft spars. The gravity feed line from the a

tanks to the nacelle tank also has

well to

a

drain valve

just

a

drain line that extends aft

along

the outboard side of the main gear wheel

aft of the wheel well.

The main and

auxiliary fuel systems are vented through a recessed vent coupled to a static vent on the underside wing adjacent to the nacelle. One vent is recessed to prevent icing. The second vent, which is heated to prevent icing, also serves as a backup should the other vent become plugged. The outer wing tanks are cross vented with one another. The wing tanks are then vented through a float operated vent valve installed on the forward outboard side of the integral fuel tank. A line just aft of the float-operated vent valve extends from the integral fuel tank through a suction relief valve and aft to an air inlet on the underside of the wing. Another suction relief valve is installed in the line from the float-operated vent valve to the siphon-break line. Both suction-relief valves are set to operate at 2 inches of water. The line from the float-operated vent valve in the integral fuel tank is routed forward along the leading edge of the wing inboard to the nacelle and aft through a check valve to the recessed vent just outboard of the nacelle and midway between the main and rear spars. Another line tees off from the vent line and extends through a flame arrester to a heated ram vent immediately outboard and aft of the recessed vent. The vent line from the auxiliary fuel cell is routed through a float-operated check valve before teeing into the vent line leading to the recessed and heated ram vents. The auxiliary fuel cell vents into this line until there is sufficient fuel for the float to close the check valve, thus preventing excess fuel from being discharged through the vents. When the check valve closes, the auxiliary fuel cell is vented through a line routed outboard from the check valve and along under the leading edge fuel cells to a point of juncture with the vent line from the integral fuel cell at the outboard end of the cell. The wing tanks gravity feed into the nacelle tank through a line extending from the aft inboard wing tank forward along the outboard side of the nacelle tank aft of the firewall immediately under the motive flow valve. A flapper-type check valve in the end of the gravity feed line prevents any backflow of fuel into the wing tanks. The fuel pressure required to operate the engine is provided by an engine-driven fuel pump mounted in conjunction with the fuel control unit on the accessory case. Fuel is pumped to the engine by an engine-driven boost pump mounted on a drive pad at the aft accessory section of the engine. Any time the gas generator (N1) is turning, this pump operates to provide fuel sufficient for all conditions except operation with crossfeed or operation with hot aviation gasof the

oline at altitudes above 20,000 feet.

nia

28-00-00

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL The

supply

line from the nacelie tank is routed from the inboard side of the nacelle tank forward to the

engine-driven

boost pump through a normally open firewall shutoff valve installed in the fuel line immediately behind the engine firewall. The firewall shutoff valve for each engine fuel system is actuated by its respective FUEL FIREWALL VALVE switch in the instrument

panel glareshield.

When the FUEL FIREWALL VALVE switch is

wall shutoff valve closes to shut off the flow of fuel to the

closed, its respective fire-

From the firewall shutoff valve, fuel is routed to the

engine. engine-driven boost pump, then to the main fuel filter on the lower center of the engine firewall. The 20-micron filter incorporates a bypass valve to permit fuel flow in case of plugging and a drain valve to drain the filter prior to each flight. A pressure switch mounted directly above the filter senses boost pump fuel pressure at the filter. At 9 to 11 psig of decreasing pressure, the switch closes and actuates the red FUEL PRESSURE light in the annunciator panel. At this time the standby boost pump should be switched on.

I

The fuel filter the filter is in

assembly is equipped with a bypass indicator in the form of a red button that will bypass condition. Refer to 28-20-00 for the procedure to reset the indicator.

pop up

indicating

that

a

I CAUTION I Operation

with the fuel pressure

light

ON is limited to 10 hours between overhaul

or

replacement of

engine-driven fuel pump. Windmilling time is not equivalent to operation of the engine at high power with respect to the effects of cavitation on fuel pump components; consequently, windmilling the

time is not to be included in the 10-hour limit

on

engine operation

without

a

boost pump.

The red FUEL PRESSURE

through

routed

light will go out with 9 to 11 psig of increasing fuel pressure. From the main filter, fuel is the fuel flow transmitter which is mounted in the outflow line between the fuel control unit and the

flow divider. Fuel from the transmitter is routed

through

the fuel heater that utilizes heat from the

the fuel. The fuel is then routed to the fuel control unit that monitors the flow of fuel to the

engine oil to warm engine fuel nozzles.

A check valve in the fuel return line

I

along the outboard side of each nacelle immediately aft of the firewall permits high pressure pump to be returned to the main fuel system. One end of the line from the high pressure fuel pump is plumbed into the gravity feed line from the outboard wing tanks at a point just aft of the fitting on the nacelle fuel cell for the gravity feed line. excess

fuel from the

engine-driven fuel pump is mounted on the accessory case in conjunction with the fuel control unit. This pump protected against fuel contamination by an internal 200-mesh strainer. The primary fuel boost pump is also engine-driven and is mounted on a drive pad on the aft accessory section of the engine. This boost pump has an operating capacity of 1,250 pounds per hour at a pressure of 30 psi. The engine-driven boost pump is backed up by

The is

electrically driven standby fuel pump located in the bottom of each nacelle tank. Either the engine-driven pump or its backup unit, the standby boost pump, is capable of supplying fuel to the engine-driven fuel pump minimum pressure requirements of the engine manufacturer.

an

boost at the

CAUTION I rCAUTlON Should the boost pumps fail, suction lift

operation may be employed; however,

suction lift operation engine overhaul periods. If the pump is operated on suc10-hour limit, overhaul or replacement of the pump is necessary.

is restricted to 10 hours total time between

tion lift

beyond

the

In addition to driven

serving as a backup unit in the standby pump provides the additional

to the other. The electrical power with

switches

Mar

on

the fuel control

event of

malfunction in the engine-driven boost pump, the electrically for the crossfeed of fuel from one side of the airplane required pressure which the standby pumps are operated is controlled by lever lock toggle a

panel.

9/0128-00-00

nln

Raythe6n

Aircrafr

BEECH SUPER KING AIR MODEL B300/B300C

MAINTENANCE MANUAL

AVIATION

g8E~

FUEL

AT

FUEL

FUEL

UNDER

PUMP

FUEL

CROSSFEED

FUEL

RETURN

AIR CINE

I

FUEL FLOW

STRAINER

OR

p3

ENGINE FUEL MANIFOLD BLEED AIR

LINE

FUEL

PUMP

ENGINE

FUEL FOR

1~1

FUEL

PURGE

FUEL CONTROL

I

HEATER,

I

_FUEL

AIR

FUEL CONTROL LEFT

PROBES

FUEL

PRESSURE

AN~UNCIATOR

PURGE

PRESSURE

PURGE

LINE

lid

CHECK

RELIEF

VALVE

DRIVEN

BOOST

PUMP

VALVE

GRAVITY FLOW CHECK VALVE

I

FIREWALL

I

STANDBY

BOOST

I~

NACELLE

TANK

SHUTOFF

VALVE

IND;ICATOR

FUEL

FLOW

FUEL

PRESSURE

MAIN- 190

FILTER

SWITCH

CHECK

VALVE

TANK

GRAIN VALVE

ENGINE SUCTION

UNIT

FUEL

FIREWALL

FILLER

O

O

INDICATOR

PRESSURE

IFUEL VENT

O O

TRANSMITTER AND

FILTER

STRATNER

PND

TRANSFER

CONTROL MOTIVE

DEFUELING

DRAIN

VALVE

FLOW

VALVE

I

d~an

_IK

PUMP

ANNUNCIATOR

1 III

GAL NOISE

AUX-79.5 GAL

VENT PRESSURE SWITCH FOR W.S.

NO FUEL

290.92

FUEL

LOW

GALLONS

FLOAT

VALVE

LEFT

TRANSFER ANNUNCIATOR

LEVEL

54

FILTER

~i]

8116~1 g0

CRDSSFEED

VALVE

SENSOR

DRAIN SWITCH

STRAINER. FUEL

23

GALLONS

79.5

RECESSED VENT AIR

INLET

~IEATED RAM VENT

FLOAT

VALVE

VENT

i

IC~II

DRAIN

GALLONS

VALVE

DRAIN ;LAME

ARRESTOR

TRANFER

JET

PUMP

nns mnauw

Fuel

ORIGINAL As Received

By

system

schematic

Figure 1

ATP

A12

28I00-09

Mar

9/01Page

3

Raytheon- Aircraft SEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

THIS PAGE INTENTIONALLY LEFT BLANK

a Mar

9/01Page

4

28-00-00

A12

Raytheon

Aircraft

BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

NOTE To alleviate electrical interference with the avionics

standby boost

pump is installed

on

equipment

of the

the underside of the nacelle

just

airplane,

a

noise filter for the

aft of the firewall

adjacent

to

the pump. Fuel pressure from the engine-driven boost pump provides the motive flow by which the jet transfer pump functions. The fuel line that supplies the motive flow to the jet transfer pump is routed along the outboard side of the nacelle

through the jet pump motive control valve just aft of the firewall to the jet transfer pump installed in the sump of the auxiliary tank. A check valve is installed in the motive flow line immediately aft of the motive flow control valve to prevent the engine from sucking air when the boost pump is not operating. The motive flow valves are opened by actuation of lever-lock toggle switches on the fuel control panel. Fuel is then pumped through the jet transfer pumps to transfer fuel from the sump of the auxiliary tank to the nacelle tanks. This switch may be placed in either the automatic (AUTO) or manual (AUX TRANSFER OVERRIDE) position. When the switch is in the AUTO position, the power is applied to the motive flow valve by the automatic fuel transfer module, a control module of solid state circuitry that is mounted under the center aisle floorboard approximately 30 inches forward of the main spar. A pressure switch set to actuate at 6 ~1 psi is installed in the fuel line between the motive flow valve and the check valve. Should the pressure switch not be actuated and there is fuel in the auxiliary tank, the NO TRANSFER light on the fuel control panel will remain illuminated to indicate that the motive flow valve is still closed. The auxiliary fuel transfer switch can then be placed in the AUX TRANSFER OVERRIDE position to bypass the fuel transfer module and apply power directly to the motive flow valve. Once the motive flow valve has opened, the jet transfer pump will pump fuel from the strainer in the sump of the auxiliary fuel tank into the nacelle fuel cell through the line that is routed to the fitting on the aft side of the nacelle tank for as long as either the engine-driven boost pump or the electrical standby boost pump is operative and there is fuel in the auxiliary tank. When the auxiliary fuel is depleted, the low level float valve de-energizes the motive flow valve to prevent cycling of the motive flow valve due to sloshing fuel. An overflow line is plumbed from the top of the nacelle tank back to the auxiliary tank to provide a retum for excess fuel delivered by the jet transfer pump. This line incorporates a pressure relief valve set at one psi. Two suction relief valves are installed in the siphon break line adjacent to the vent float valve on top of the nacelle tank. One valve is set at 4 inches of water to prevent the fuel cell from collapsing. The other valve is also set at 4 inches of water to prevent fuel from siphoning from the nacelle tank to the auxiliary tank. The siphon break line is routed aft along the inboard side of the wheel well through a flame arrester to an air inlet just outboard and aft of the auxiliary tank. This flame arrester and the one adjacent to the heated ram vent protect the fuel system from ignition through the vent system should lightning strike the airplane. The

auxiliary

fuel system will not feed into the main fuel system if there is a failure of both boost pumps or a failure on the auxiliary tank fuel gage and by the illumination

of the motive flow shutoff valve. This condition will be noted

of the NO TRANSFER

the fuel control

panel. This light is actuated if there is less than 6 fl psi of pressure the pressure switch adjacent to the motive flow valve and if the float switch in the sump of the auxiliary tank is not in the empty position. The automatic fuel control module simultaneously removes the power to close the motive

light

on

on

flow valve to prevent continued operation of the jet transfer pump. The jet transfer pump will not be damaged by operation after the tank is dry, but extended operation with an empty auxiliary tank may tend to draw unnecessary moist air into the main fuel system from the empty, vented auxiliary tanks.

a~a

28-00-00

5

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CAUTION I CAuTIONI system is full and the AUX Transfer system has been operated, the wing and napressurized to approximately 1 psi. DO NOT OPEN the fuel cap located on the leading edge near the wing tip until the pressure has been relieved. Running the engine with the When the main

celle tanks will be

AUX Transfer circuit breaker pressure

drops

Each nacelle tank is connected to the

I

by automatically

a

in the

engine

of the nacelle aft to the center section and controlled

may relieve the pressure.

pulled

Pumping

the

wing tanks

until the

is another alternative.

across

opposite wing by

ignition

is

on or

crossfeed line routed from the inboard side

opposite

nacelle. The crossfeed line is

of the LH nacelle. The transfer system will crossfeed is selected to it’s respective side.

valve connected into the line at the aft inboard

be turned off when

a

to the inboard side of the corner

Operation of the standby boost pump on the side from which crossfeed is desired will ensure an adequate flow of engine and will maintain motive flow ~for the jet transfer pump. When the manually operated crossfeed control switch on the fuel control panel is actuated, power is drawn from a 5-ampere circuit breaker on the fuel control panel to the solenoid that opens the crossfeed valve. The automatic transfer module simultaneously energizes the standby pump on the side from which crossfeed is desired and de-energizes the motive flow valve in the tank system being crossfed. When the crossfeed valve is open, the green FUEL CROSSFEED light on the annunciator panel will illuminate. The crossfeed will not transfer fuel from one cell to another; its primary function is to supply fuel from one side to the opposite engine during and engine-out condition. If the standby boost pumps on both sides are operating and the crossfeed valve is open, fuel will be supplied to the engines in the normal manner because the pressure on each side of the crossfeed valve will be equal. fuel to the

I CAUTION I A

standby boost pump

MUST be in

operation

on

the side from which the fuel is

being supplied.

airplane is equipped with a fuel purge system which is designed to assure that any residual fuel in the engine during engine shutdown. During engine operation, compressor discharge (P3 air) is routed filter and check a valve, pressurizing a small air tank mounted on the engine truss mount. On engine shutthrough down, the pressure differential between the air tank and the fuel manifold causes air to be discharged from the air tank, through a check valve and into the fuel manifold system. The air forces all residual fuel remaining in the fuel This

manifolds is consumed

manifold out

through

consumed, which in

the nozzles and into the combustion chamber. The fuel forced into the combustion chamber is turn

causes a

momentary rise in engine speed.

SPECIAL TOOLS AND RECOMILIENDED II/IA TERIALS

meeting federal, military or supplier specprovided only specifically required by Raytheon Aircraft Company. Any product conforming to the specification listed may be used. The products included in these charts have been tested and I approved for aviation usage by Raytheon Aircraft Company, by the supplier, or by compliance with the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE REQUIREMENTS OF THE SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHARTS. Only the .basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification .I prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

I

The’special ifications

Page

tools and recommended materials listed in Charts 1 and 2

are

for reference

628-00-00

and

are

as

not

ni2

Raytheon Aircraft SEECH SUPER KING AIR MODEL. B3001B30CTC MAINTENANCE MANUAL

CHART1

SPECIAL TOOLS

TOOL NAME 1.

DC-400orDC-400A DC Fuel

Quantity

PART NUMBER

Digital

101-00800

Test Set

with DC-400 Module

Assy

USE

SUPPLIER Barfield Instrument

or

Fuel

Quantity Capacitance Test

Corp.,

101-00850,

1478 Central

101-00802

East Point, Ga. 30344

Ave.,

1-800-241-6769 2.

BarfieldTechnical Manual

TM0800

Barfield

InstrumentCorp.,

I

1478 Central Ave.,

Fuel Quantity Capacitance Test

East Point, Ga. 30344 1-800-241-6769 3.

Raytheon

modified DC-400

TK 2129/935

1

4.

15 Pin

Customer

Raytheon

Test Set

Adapter

Cable

101-00817

Assy.

Fuel

Quantity Capacitance Test

Support, Company

Aircraft

Barfield Instrument

Fuel

Quantity Capacitance Test

Corp.,

1478 Central Ave.,

East Point, Ga. 30344 1-800-241-6769 5.

Probe

AdapterCable

Barfield Instrument

101-00814

1478 Central

East

Corp.,

Ave.,

I

Fuel

Quantity Capacitance Test

Point, Ga. 30344

1-800-241-6769 6.

Barfield Instruction Manual

Barfield Instrument

56-101-00802

1478 Central

East

Corp.,

Ave.,

Fuel Quantity Capacitance Test

Point, Ga. 30344

1-800-241-6769 7.

Probe descrete level

Barfield Instrument

101-01012

interface cable

1478 Central

East

Corp.,

Ave.,

Fuel

Quantity Capacitance Test

Point, Ga. 30344

1-800-241-6769 8.

HarnessAdapterCable

1

TK2129/935

Assy

A

Customer

Raytheon 9.

Harness

AdapterCable

10. Inserter/Extraction Tool

TK2129/935

Assy

M81969/14-11

B

Fuel

Quantity Capacitance Test

Support, Company

from terminal board

Support, Raytheon Company Customer

Fuel Quantity Capacitance Test

Aircraft

Customer

Raytheon

A12

Support, Company

Aircraft

Aircraft

Remove

28-00-00

probe

wires

7

Raytheon Aircraft SEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CHART2 RECOMMENDED MATERIALS

MATERIAL 1.

SPECIFICATION

PRODUCT Permatex No. 2

Gasket Cement

VENDOR Permatex Industrial Div of Locktite

Corp.,

705 N.

Mountain, Newington, Ct 06111-1411 2.

Sealer

Pro-Seal PR890A1/2

Essex Chemical

Corp.,

Pro-Seal Div., 19451 Susana

Compton,

1

3.

Cleaning

Solvent

PD-680, Type III

Stoddard Solvent

RD.,

CA 90221-5713

Obtain

Locally

(Mineral Spirits)

1

4.

Solvent

TT-M-261

Obtain

Locally

5.

Solvent

TT-N-95

Obtain

Locally

6.

Sealer

MIL-S-8802

Pro-Seal PR890B1/2

Essex Chemical

Corp.,

Pro-Seal Div., 19451 Susana RD.,

Compton, 7.

Lubricating

Grease

Plastilube No.

Warren

CA 90221-5713

Refining

Chemical Co., 5551 Penison,

Cleveland, OH 8.

Olytite

Sealant

stir

LA-CO Industries inc., 1201 Pratt Elk Grove

9.

Stop-A-Leak

Sealant

Blvd,

Village,

11160007

LA-CO Industries

inc., Blvd, Elk Grove Billage, 11160007 1201 Pratt

Mar

9/01Page

8

28-00-00

ai2

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FUEL -TROUBLESHOOTING CHART3 TROUBLESHOOTING

FUEL SYSTEM

MAIN BO~ST PUMP INOPERATIVE

STEP 1

Defective

Pump

YES

Repair

replace

or

as

required.

as

required.

CHART4 TROUBLESHOOTING

FUEL SYSTEM

STANDBY BOOST PUMP INOPERATIVE STEP 1

Fuses Blown

YES

Replace

fuses

YES

Replace

diodes

YES

Replace required

NO

Defective Diodes NO

Open

circuit

CHART5 TROUBLESHOOTING

FUEL SYSTEM

FUEL JET TRANSFER PUMP INOPERATIVE STEP 1

Defective boost pump

YES

Repair

YES

Replace

YES

Replace

YES

Repair

or

replace

NO Defective transfer motive flow valve NO Defective fuel control module NO

Open

circuit

as

required

CHARTG TROUBLESHOOTING

FUEL SYSTEM

WING TANKS OVERPRESSURIZING STEP 1

A12

Check valve in nacelle tank

slightly open during fuel transfer operation. (Tanks will pressurize to the 1.5 psi value of the pressure relief valve)

YES

Replace

check valve.

28-00-00

Mar

9/01Page

9

Ray~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL CHART TROUBLESHOOTING

FUEL SYSTEM

NACELLE TANKS OVERPRESSURIZING STEP 1

Pressure relief valve too

high, malfunctioning (stuck closed) or installed backwards. (May cause structural damage to the nacelle tank or

stringers

on

access

Correct

or

replace

as

required.

liner, bent hat sections

sides of nacelle,

and deformation at the top

nacelles at

YES

or

or

leakage

bottom of the

areas)

CHART 8

TROUBLESHOOTING

FUEL SYSTEM

FUEL EXITING OVERBOARD FROM THE OUTBOARD WING AIR VENT STEP 1

Chech valves

malfunctioning

or

installed

YES

Correct

or

replace

as

required.

backward.

CHARTS TROUBLESHOOTING

FUEL SYSTEM

FUEL EXITING OVERBOARD FROM INBOARD WING VENTS STEP 1

Fuel system overserviced

YES

Drain

YES

Repair

excess

fuel if

required.

NO

Cross-feed valve stuck open

(May be opposite engine is fuel Uneven burning can also running. indicate a leaking or open cross-feed valve)

caused when

or

replace

as

required

side

CHART 10 TROUBLESHOOTING

FUEL SYSTEM

COLLAPSED FUEL TANK STEP 1

Possible blocked vent lines valve stuck open.

Mar

28-00-00

or a

vent float

YES

Repair condition and/or replace required.

valve

as

a~z

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FUEL- MAINTENANCE PRACTICES

SERVICING THE FUEL SYSTEM For

complete

fuel system

servicing information,

refer to

Chapter

12-10-00 under the

following

individual

headings:

FUEL HANDLING PRACTICES, FUEL GRADES AND TYPES, FUEL BRANDS AND TYPE DESIGNATIONS,

FUEL HANDLING SAFETY

INFORMATION, FILLING

THE TANKS, DRAINING THE FUEL SYSTEM, FUEL CELL

PRESERVATION AND JET FUEL ADDITIVES.

A12

28-00-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

STORAGE

MAINTENANCE PRACTICES

NACELLE FUEL CELL REMOVAL a.

Make

b.

Drain all fuel from the nacelle and outboard

c.

Remove the

d.

Disconnect and

e.

sure

all electrical power is disconnected from the

access cover

remove

Remove the fuel

wing panel

airplane. fuel cells.

from the top of the nacelle to

the

plumbing

gain

to the nacelle fuel

access

for the valves located above the fuel cell

quantity probe (Ref. Figure 201)

as

described in

Chapter

quantity probe.

cover.

28-40-00 under fuel

quantity

indication. f.

g.

Unsafety

and

remove

Working through

the

the bolts

cover

securing the fuel cell

opening,

remove

cover

the 4 set

to the fuel

cell, then

remove

securing the flapper

screws

the

cover.

check valve to the

gravity

feed line at the outboard side of the nacelle tank. h.

Disconnect the internal at the crossfeed tee

opening i.

on

on

plumbing at the fuel boost pump and fuel strainer in the bottom of the nacelle tank and the inboard side of the tank, then remove the lines and check valves through the cover

top of the nacelle tank.

Remove the

standby

boost pump from the bottom of the fuel cell

as

described in

Chapter

28-20-00 under fuel

distribution.

j.

Working through fasteners, then

k.

the boost pump opening, remove the 3 the strainer from the fuel cell.

safety pins securing

the fuel strainer to the fuel cell

remove

in the wheel well, disconnect the check valve in the line that runs to the transfer pump from the aft fuel cover near the top of the tank. Remove the bolts securing the cover to the cell and remove the cover and

Working cell

gaskets. I.

Remove the

access

panel

on

the inboard side of the nacelle

immediately

forward of the center section

leading

edge. m.

Working through the access opening on the inboard side of the nacelle, disconnect the line to the crossfeed Unsafety and remove the six bolts and washers securing the crossfeed tee in place. Remove the tee and gaskets from the fuel cell installation.

n.

Remove the

o.

Working through the access opening on the outboard side of the nacelle, disconnect the fuel line at the elbow. Unsafety and remove the 6 bolts and washers securing the elbow in place, then remove the elbow and its two gaskets.

p.

Unsnap the Carr fasteners securing the top of

q.

Collapse the

access

panel

fuel cell and

on

the outboard side of the nacelle

remove

it

through

just forward of the leading edge.

the nacelle fuel cell to the

the top

opening.

tee.

Use

care

adjacent

to avoid

structure.

damaging

the fuel cell.

28-1 0-00

Page

201Mayl/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

NACELLE FUEL CELL INSTALLATION NOTE:

Expose

the fuel cell to

temperatures of

at least 60" F for

a

period sufficient

to ensure

flexibility during

installation. the cell and install it

damaging

the fuel cell.

b.

Snap

c.

Working from

d.

Working through the access opening on the outboard side of the nacelle just forward of the wing leading edge, place a gasket between the fuel cell fitting and the skin and elbow when positioning the elbow over the opening. Install and torque the 6 elbow retaining bolts to 45 to 50 inch-pounds, then safety the bolts. Connect the fuel line to the elbow and install the access panel.

e.

flapper check valve on the end of the gravity feed line with (Ref. Figure 201). Secure the valve in place with the 4 set screws.

access

care

the top of the fuel cell to the holes in the

the top of the nacelle,

push

the fuel cell into

position

CAUTION: Make

cover

seep-free

when

the

hinge

at the

bay.

top of the line

O-ring is in place in the flapper check valve. The end of the gravity feed line must beyond the O-ring until it butts up firmly against the shoulder of the flapper Valve to ensure seal.

inside the wheel well,

Working

nacelle structure.

that the

sure

be inse~fed a

adjacent

inside the fuel cell

Install the

I

f.

securing

the

opening.

to avoid

Collapse

the Carr fasteners

through

Use

a.

positioning

g.

Install and torque the

h.

Working

the aft

cover

place

a

between the fuel cell

gasket

cover over

the

opening

bolts to 45 to 50

retaining

near

fitting

and skin and between the skin and

the top of the tank.

inch-pounds then safety

inside the wheel well, connect the line and check valve from the

jet

the bolts.

transfer pump to the aft side of the

cover.

i.

Working through the access opening on the inboard side of the nacelle just forward of the center section leading edge, place a gasket between the fuel cell fitting and the skin and between the skin and crossfeed tee when positioning the tee over the opening. Install and torque the six tee retaining bolts to 45 to 50 inch-pounds, then safety the bolts.

j.

Reconnect the fuel lines to the crossfeed tee, then install the

k.

Working through

the

cover

opening

on

access

panel

on

the inboard side of the nacelle.

top of the nacelle tank, position the boost pump and strainer plumbing

and check valves in the fuel cell. I.

Working through the boost pump opening on the underside of the nacelle, place the fuel strainer in the fuel cell fasteners, then secure the strainer in place with the three safety pins.

NOTE: If the

plug was removed from the plug upon installation.

bottom of the fuel strainer installation,

apply

a

position

over

torque of 35-50 inch-pounds

to the m.

Connect the strainer and boost pump

n.

Install the

o.

Working through strainer

plumbing

NOTE: Take

May

1/08Page

202

standby

care

boost pump

the

cover

as

plumbing

indicated in

opening

on

and check valves to the fuel strainer.

Chapter

28-20-00.

top of the nacelle,

connect the tee

on

the end of the boost pump and

to the crossfeed tee on the inboard side of the nacelle tank.

not to catch threads of bolt on the

28-1 0-00

edges

of the

gasket during

insertion.

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

p.

Place a gasket on each side of the fuel cell cover pan. Align the fuel cell cover with the mounting holes on top of the pan. Install and torque the cover plate retaining bolts to 45 to 50 inch-pounds for serials FL-I thru FL-265, FL-267 thru FL-283; FM-1 thru FM-10 that have not installed Kit 130-9005-5. Install and torque the cover plate

retaining

bolts to 35 to 40

inch-pounds

for serials FL-266, FL-284 and after; FM-11 and after and

prior airplanes

that have Kit No. 130-9005-5 installed.

NOTE:

retaining bolts in the sequence designated by numbers 1 through 36 in Figure 202 to of the cover. On airplanes FL-266, FL-284 and after; FM-I1 and after and prior installation ensure proper have Kit No. 130-9005-5 installed, complete the torque sequence one time only and check that airplanes shown and in re-torque bolt only if torque is lower than 30 inch-pounds. torque sequence Torque

the

cover

CAUTION: Handle the fuel accuracy of the q.

Install the fuel

NOTE:

Torque

quantity probe carefully. Damage probe.

to the surface of the

quantity probe (Ref. Chapter 28-40-00). Torque

the

retaining

bolts in the sequence

designated by

the

probe

probe retaining

through

letters A

F in

tubes will

destroy the

bolts to 30 f 5

Figure 202

to

inch-pounds.

ensure

proper

installation. r.

Install the valves and their attendant

plumbing

CAUTION: Be certain that all check valves s.

Install the

access cover on

are

over

the fuel cell

cover

(Ref. Figure 202).

installed properly for flow direction

(Ref Figure 202).

top of the nacelle.

Goodyear Fuel Cells with construction other than BTC-85, torque fuel cell nipple clamps to 25 -t 5 inchpounds. Goodyear fuel cells constructed with ETC-85 have black nipples, while fuel cells constructed with material prior to ETC-85 have clear yellow nipples.

NOTE: For

28-1 0-00

Page

yaM302

1/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

FUEL QUANTITY PROBE

6

o

A

FLAPPER

CHECK VALVE

CHECK VALVE "i

e

a

e

e e

e

VALVE

B FUEL a

o

e

STRAINER STANDBY BOOST PUMP

DEFUELING VALVE

DET*IL

B

C;d

8 DCTAIL

A

350-281-29

Nacelle Fuel Cell installation

Figure

May 1/08Page

204

28-1000

201

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

SUCTION RELIEF

VALVE

VENT

FLOAT

38

qs

VALVE PRESSURE

lsC~

RELIEF VALVE FUEL LOW

/11

ns~

FUEL

LEVEL

IC’fll

II

SE""""

II~YMh nr I ~b

QUANTITY PROBE

)t

bO

Ic

SUCTION RELIEF

II~II

~h LL

14t

VALVE

leYT ´•t~

I

SUCTION

Y

v+

RELIEF VENT

VALVE

VALVE

~PD1

PRESSURE RELIEF

g

VALVE

1

LH NACELLE

\´•e

FUEL CELL ACCESS

111

I,~e It

FUEL LOW LEVEL

t

t

FUEL QUANTITY PROBE

~IIXUU-

I~WVI,

~16+

SENSOR

O/I-+

SUCTION

I

RELIEF

Ci~

VALVE

I

B

RH NACELLE FUEL CELL ACCESS

FL2BR 002729AA Al

Torquing Fuel Cell Figure 202

A24

Cover

28-1 0-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

INBOARD LEADING EDGE FUEL CELL REMOVAL a.

Make

b.

Drainthe

mainfuelsystem.

c.

Unclamp

and

d.

Remove the outboard

e.

Remove the

f.

Unsafety and remove (Ref. Figure 203).

I

sure

all electrical power to the

is disconnected.

drain valve spacer and washer from the aft inboard bottom of cell

remove

jumper

airplane

access cover on

wire and

the 5

CAUTION: Handle the fuel accuracy of the

top of the wing

unplug the

mounting

to

gain

access

to the fuel

connector of the lead wire to the fuel

screws

and

remove

quantity probe carefully; damage probe as a measuring device.

the fuel

adjacent

to the naceile.

quantity probe.

quantity probe.

quantity probe

to the surface of the

from the fuel cell

probe

tubes will

destroy

the

g.

Remove the

h.

Working through the fuel access opening, disconnect the large interconnect in the aft side of the fuel of the opening by removing the "WWD" clamps securing the interconnect lines to the nipple caps.

cell inboard

i.

Remove inboard

cover

j.

Remove the

k.

Unsafety

attaching

access cover on

jumper

and

bolts and the

wire and the 5

remove

CAUTION: Handle the fuel

accuracy of the

cover

plate

top of wing

to

to the fuel cell access

gain

access

fitting.

to the fuel

quantity probe

the connectors of the two lead wires to the fuel

unplug

mounting

screws

and

remove

quantity probe carefully; damage probe as a measuring device.

the fuel

quantity probe

to the surface of the

and fuel cell

quantity probe.

from the fuel cell.

probe

tubes will

I.

Remove the

m.

Working through the fuel access opening, disconnect the large interconnect line directly aft opening by disconnecting the "WWD" clamp securing the interconnect line to the fuel cell.

n.

Remove the "WWD"

large o.

p.

attaching

bolts and the

clamp

cover

access

panels adjacent

Disconnect the vent line

side of the

wing

to the fuel cell

running

destroy

the

fitting.

access

that connects the small interconnect line to the fuel cell

interconnect line removed in the

Remove the

plate

plate.

of the

access

nipple just inboard of the

preceding step.

to the outboard side of the nacelle.

from the aft inboard side of the

leading edge

fuel cell to the forward inboard

inboard aft fuel cell.

q.

Release the snap fasteners

r.

Collapse

the cell and

securing the

remove

it

through

cell to the upper

the outboard

wing

access

skin.

opening

on

top of the wing leading edge.

INBOARD LEADING EDGE FUEL CELL INSTALLA TION NOTE:

Expose the

fuel cell to temperatures of at least 60" F for

a

period sufficient

to ensure

flexibility during

installation. a.

Collapse

Page

yaM602

1/08

the cell and install it

through

28-1 0-00

the outboard

access

opening

on

top of the wing leading edge.

az4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

b. c.

Secure the snap fasteners that hold the fuel cell

against

the upper

skin.

wing

Install the washer, spacer and drain valve on the inboard aft end of the fuel cell and secure them in place with retaining clamp (Ref. Figure 203). The washer is to be installed between the spacer and cell liner.

the d.

Connect the vent line at the aft inboard end of the fuel cell.

Torque the

"WWD"

clamps to the torque

values listed

under Chart 1. e.

Working through

the inboard

at the aft side of the cell.

f.

access

Torque

opening on top of the wing, connect the large and small nipple clamps to the values listed under Chart 1.

interconnect lines

"WWD"

plate and gasket on the fuel cell with the attaching bolts, then lock the bolts in place with safety Apply gasket cement (Item i, Chart 2, 28-00-00) between the adapter and skin when installing the cover

Install the wire.

cover

plate. NOTE:

g.

Install the free end of the

Insert the fuel

quantity probe

CAUTION: Handle the fuel

bonding jumper into its

opening

under

one

of the

cover

mounting

bolts.

in the fuel cell.

quantity probe carefully; damage to the surface quantity probe as a measuring device.

of the

probe

tubes will

destroy the

accuracy of the fuel h.

Secure the fuel

safety

quantity probe

in

place

with the

attaching bolts. Torque

the bolts to 25 f 5

inch-pounds

NOTE: Install the free end of the

bonding jumper

under

one

in the two connectors of the lead wires to the fuel

i.

Plug

j.

Working through

the outboard

outboard end of the fuel cell.

access

Torque

opening

on

the "WWD"

of the fuel

quantity probe mounting

quantity probe

and reattach the

bolts.

jumper wire

to the

top of the wing, connect the two cell interconnect nipple clamps to the values listed in Chart 1.

k.

Working through the outboard access opening on top of the wing, Connect the large and small at the aft side of the cell. Torque the "WWD" nipple clamps to the values listed in Chart i.

I.

Install the wire.

and

wire them.

probe.

lines at the

interconnect lines

gasket on the fuel cell with the attaching bolts, then lock the bolts in place with safety Apply gasket cement (Item 1, Chart 2, 28-00-00) between the adapter and skin when installing the cover plate

cover

and

plate. NOTE: Install the free end of the m.

Insert the fuel

quantity probe

CAUTION: Handle the fuel

bonding jumper into its

opening

under

one

of the

cover

mounting

bolts.

in the fuel cell.

quantity probe carefully; damage to the surface quantity probe as a measuring device.

of the

probe

tubes will

destroy the

accuracy of the fuel n.

Secure the fuel

safety NOTE:

Install the free end of the

in

place

with the

bonding jumper

attaching

under

in the connector of the lead wire to the fuel

o.

Plug

p.

Install all

nz,

quantity probe

bolts.

Torque

the bolts to 25 f 5

inch-pounds,

then

wire them.

access

plates

on

one

of the

quantity probe

the upper and lower surfaces of the

mounting

bolts of the fuel

and reattach the

jumper

quantity probe.

wire to the

probe.

wing.

28-1 0-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

jso

10

A a

8

-~E D

UPPER

INTERCONNECT i,,,

CRAIN VALVE

DETAIL

A

GASKET

LOWER

FUEL QUANTITY PROBE

INTERCONNECT TUBE

CLAMP DETAIL

DETAIL

~be

CLAMP,,

DETAIL

C

8 D

CLAMP

UPPER

INTERCONNECT TUBE CLAMP

DETAIL

F

LOWER INTERCONNECT TUBE

INTERCONNECT TUBE

DETAIL

8 sso-?al.Jo

Inboard

May

28-1 0-00

Leading Edge Fuel Cell Figure 203

Interconnects

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

Chart 201

Fuel Cell Fuel Cell

Fitting

I.D.

or

Nipple Clamp Torque

Tube

Value

Clamp Torque

Size Inches Diameter

Pound-inches

0.25 thru 0.62

12-15

0.75 thru 1.00

15-20

1.50

25-30

2.00

30-35

3.00

35-40

OUTBOARD LEADING EDGE FUEL CELL REMOVAL all electrical power to the

a.

Make

b.

Drainthe

c.

Remove the center and outboard

sure

airplane

is disconnected.

mainfuelsystem. access covers

and

gaskets

from the lower surface of the

wing leading edge.

opening, disconnect the upper and lower interconnect lines at the inboard end of the "WWD" clamps that secure the lines to the cell nipples (Ref. Figure 204).

the center

Working through the fuel cell by removing d.

e.

Working through the same opening, disconnect the large interconnect removing the "WWD" clamps from the line and cell nipple. Remove the bolts end of the

securing the wing leading edge.

filler neck to the fuel cell and

remove

line

just outboard of the opening by

the filler neck and

gasket from the

outboard

f.

Working through the filler neck opening, disconnect the interconnect line from the aft outboard end of the fuel cell directly behind the filler neck opening by removing the "WWD" clamp that secures the line to the cell nipple.

g.

Working through

the two

h.

Collapse

the cell and

openings wing skin.

access

hold the fuel cell to the upper remove

it

through

on

the underside of the

the inboard

access

wing leading edge,

unsnap the fasteners that

opening.

OUTBOARD LEADING EDGE FUEL CELL INSTALLATION NOTE:

Expose

the fuel cell to temperatures of at least 60" F for

installation. It should be noted that this fuel cell contains

integral

with the cell. This

fuel cell. This

nipple is

nipple

a

period sufficient to ensure flexibility during internal nipple which is covered by a web

an

is located 12.12 inches inboard of the outboard end of the aft side of the

not used in this installation.

the cell and install it

through

the inboard

opening

the underside of the

a.

Collapse

b.

Working through the two access openings on the underside hangers that hold the fuel cell against the upper wing skin.

c.

Working through the filler neck opening, connect the interconnect line at the aft outboard (Ref. Figure 204). Torque the "WWD" nipple clamps to the values listed in Chart 1.

access

of the

on

wing,

secure

wing leading edge.

the snap fasteners

on

the 9

end of the fuel cell

28-1 0-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

d.

Position the filler neck and the filler neck

adapter

gaskets wing

and the

on

the fuel cell.

Apply gasket

cement

skin. Secure the filler neck in

place

(Item 1, Chart 2, 28-00-00) between retaining bolts and safety wire

with the

the bolts. e.

Install the

f.

Working through

access cover

and

the center

gasket access

interconnect line just inboard of the listed in Chart 1.

Working through

g.

the

same access

the aft inboard end of the fuel cell. h.

Install the

access cover

and

on

the outboard

opening opening

on

access

opening

with the

attaching

bolts.

underside of the

to fuel cell

wing leading edge, connect the large nipple. Torque the "WWD" nipple clamps to the value

opening, connect the two small interconnect lines to the fuel cell nipples Torque the "WWD" nipple clamps to the values listed in Chart i.

gasket

on

the center

access

opening

with the

attaching

at

bolts.

AFT OUTBOARD WING CENTER FUEL CELL REI~IOVAL a.

Make

b.

Drainthe

all electrical power to the

sure

is disconnected.

mainfuelsystem.

Remove the second

c.

airplane

access cover

outboard of the nacelle and aft of the main spar from the underside of the

wing. d.

Worki ng th rough this

the "WWD"

openi ng, discon nect the large interconnect line forward of the open ing the line to the cell nipple.

access

clamp securing

by removing

e.

Working through the same opening, disconnect the large interconnect line and the hose at the forward end of the cell by removing the "WWD" clamp securing it in place (Ref. Figure 205).

f.

Disconnect the small interconnect line at the outboard aft end of the fuel cell

holding

it in

the "WWD"

clamp

place.

Disconnect the small and

g.

by removing

outboard

clamps holding

them in

large

h.

Release the snap fasteners

i.

Collapse

the cell and

interconnect lines at the inboard end of the fuel cell

by removing

the "WWD"

place. securing the cell

remove

it

through

the

to the upper

access

skin.

wing

opening

the underside of the

on

wing.

AFT OUTBOARD WING CENTER FUEL CELL INSTALLA TION NOTE:

Expose

the fuel cell to temperatures of at least 600 F for

a

period

sufficient to

ensure

flexibility during

installation. a.

Collapse nacelle

b.

the fuel cell and install it

on

the underside of the

Working through this access opening, the upper skin of the

I

c.

through wing.

May

secure

access

opening aft

the snap fasteners

on

the 1 1

of the main spar and outboard of the

hangers that

hold the fuel cell

against

wing.

Connect the small and "WWD"

the second

nipple clamps

large

interconnect lines at the inboard end of the fuel cell

(Ref. Figure 205). Torque

the

to the values listed in Chart 1.

28-1 0-00

an4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

d.

Connect the small interconnect line at the aft outboard end of the fuel cell.

Torque

the "WWD"

nipple clamp

to

the correct value listed in Chart i. e.

Connect the

large

interconnect line at the forward outboard end of the fuel cell.

Torque the "WWD" nipple clamp

to the correct value listed in Chart 1.

f.

Connect the

Torque g.

large

interconnect line at the forward side of the fuel cell

the "WWD"

Install the

clamp

and

access cover

directly

in front of the

access

opening.

to the correct value listed in Chart i.

gasket

the second

on

access

door outboard of the nacelle and aft of the main spar.

AFTINBOARD WING FUEL CELL REMOVAL all electrical power to the

a.

Make

b.

Drain the main fuel system.

c.

Remove the

access cover over

d.

Remove the

jumper wire

e.

Unsafety

sure

and

remove

the fuel

unplug

and

the 5

airplane

is disconnected.

quantity probe.

the connectors of the two lead wires to the fuel screws, then remove the fuel

mounting

CAUTION: Handle the fuel accuracy of the f.

Remove the

g.

Working through adjacent

large

quantity probe carefully; damage probe as a measuring device.

access cover

this

to the surface of the

remove

the "WWD"

to the tank unit on the inboard side of the fuel cell

NOTE: This plug is

only required

on

Goodyear fuel

cells.

from the fuel cell.

probe

aft of the main spar and outboard of the nacelle

opening,

access

quantity probe

quantity probe.

on

tubes will

the underside of the

clamp and extract the plug (Ref. Figure 205).

Uniroyal

destroy the

from the fuel cell

fuel cells do not have the

wing.

nipple

nipple requiring this

plug. h.

Disconnect the

large interconnect nipple.

line at the forward side of the fuel cell

by removing the

"WWD"

clamp securing

it to the fuel cell i.

j.

Disconnect the small interconnect line outboard of the Remove the "WWD"

clamps

large interconnect

and disconnect the small and

large

line at the foMlard side of the fuel cell.

interconnect lines at the outboard end of the

fuel cell. k. i.

Remove the

access cover

just aft of

the main spar and

Working through this opening, remove leading edge fuel cell.

the "WWD"

adjacent

to the nacelle on the

clamp securing the fuel cell nipple

topside of

the outer

to the vent line

wing.

leading

to

the inboard m.

Release the snap fasteners

n.

Collapse

the cell and

securing

remove

it

the cell to the upper

through

the

access

wing

opening

on

skin. the underside of the

wing.

28-1 0-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MAN UAL

D

A

INNER

INTERCONNECT TUBE

g~

OUTER

k

INTERCONNECT TUBE

DETAIL

A CLAMP

CLAMP

CLAMP

UPPER

INTERCONNECT

CLAMP

TUBE

LOWER

DETAIL

B

INTERCONNECT TUBE

350-281-31

Outboard

May

1/08Page

212

28-1 0-00

Leading Edge Fuel Cell Figure 204

Interconnects

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

o0000 -I

LC!

~i/ A DETna

A

INTEGRAL FUEL CELL

UPPER

CLAMP

INTERCONNECT

UPPER

TUBE

INTERCONNECT TUBE

LOWER

CLAMP

INTERCONNECT

CLAMP

TUBE

LOWER

INTERCONNECT_

~h,

’3b

-~R

TUBE

DETAIL

TUBE.

INTERCONNECT CLAMP

B

CLAMP

CLAMP

INTERCONNECT TUBE

TUBE

DETAIL

C

CLAMP

HOSE

M

I/

’HOSE

TUBE

MTAIL

P

CLAMP 350-281-32

Interconnects for Aft

A24

inboard, Aft Center and Aft Outboard (Integral) Wing Fuel Cells Figure 205

28-1 0-00

Page

yaM312

1/OS

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

A~r INBOARD WING FUEL CELL INSTALLATION NOTE: Expose the fuel cell to temperatures of at least 60" F for installation. a.

Collapse on

b.

Working through of the

c.

d.

the cell and install it

the underside of the this

the

through

flexibility during

ensure

aft of the main spar and outboard of the nacelle

opening

access

sufficient to

wing.

access

opening,

the 6 snap fasteners that hold the fuel cell

secure

against

Connect the small and

large interconnect

"WWD"

to the values listed in Chart 1.

nipple clamps

Connect the small and

large interconnect

lines at the outboard end of the fuel cell

lines at the forward side of the fuel cell.

(Ref. Figure 205). Torque

Insert the

plug in the cell nipple at the (Goodyear fuel cells only).

f.

Install the

access cover

g.

Working through

Torque the "WWD" nipple

the

and

access

gasket

inboard side of the fuel cell.

on

opening

the

on

access

opening

the top of the

on

Torque

the

clamp

the underside of the

wing adjacent

to the correct value listed

wing.

to the outboard side of the nacelle

of the main spar, connect the vent line to the nipple at the forward inboard side of the fuel cell. "WWD" clamps to the values listed in Chart i. Insert the fuel

quantity probe

CAUTION: Handle the fuel

accuracy of the i.

Secure the fuel

safety NOTE:

the

to the values listed in Chart 1.

in Chart 1

h.

the upper skin

wing.

clamps e.

large

period

a

into its

opening

in

Torque

destroy

the

in the fuel cell. to the surface of the

quantity probe carefully; damage probe as a measuring device.

quantity probe

just aft the

Torque

bolts.

place with the attaching

probe

tubes will

the bolts to 25 f 5

inch-pounds,

then

wire them.

Install the free end of the

under

bonding jumper

in the two connectors of the lead wires to the fuel

j.

Plug

k.

Install the

access cover over

the fuel

quantity probe

of the

one

mounting

bolts of the fuel

quantity probe.

quantity probe.

and

secure

in

place

with the

attaching

bolts.

AUXILIARY FUEL CELL REMOVAL a.

Make

b.

DraintheauxiliaryfueI system.

c.

Remove the small round

d.

Disconnect the two electrical leads of the fuel quantity probe (Ref.

e.

Unsafety and remove the 5 mounting remove the probe from the fuel cell.

sure

all electrical power to the

CAUTION: Handle the fuel accuracy of the

Page

cover

airplane

adjacent

is disconnected.

to the

screws

fuselage

securing

to

the

quantify probe carefully; damage probe as a measuring device.

28-1 0-00

gain

access

to the fuel

quantity probe.

Figure 206).

jumper wire and fuel quantity probe

to the surface of the

probe

tubes will

in

place, then

desfroy the

,4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

f.

Remove the

large oblong cover aft quantity probe.

of the main spar

on

top of the

center section to

gain

access

to the

auxiliary

fuel cell and fuel g.

Disconnect the two electrical leads of the fuel

quantity probe.

h.

Unsafety

securing

remove

and

the

remove

mounting

the 5

screws

the

jumper wire and fuel quantity probe in place,

then

the fuel cell.

probe from

CAUTION: Handle the fuel accuracy of the

quantify probe carefully; damage probe as a measuring device.

probe

tubes will

destroy the

from the top of the fuel cell.

i.

Remove the fuel cell

j.

Working through the cover opening on top of the auxiliary fuel cell, remove the "WWD" clamps securing the cell nipples on the outboard side of the fuel cell to the vent line, nacelle fuel return line, and the lines to and from the jet transfer pump.

k.

opening

jet transfer pump at the unions directly under the cover opening on top of the outboard segments of the pump lines from the hanging strap outboard of the cover them from the fuel cell.

Disengage

and

Remove the to the

remove

cover

plate

over

the drain

on

the underside of the center section aft of the main spar and

adjacent

fuselage. and

the drain valve and strainer

m.

Unsafety

n.

Disconnect the internal

remove

the check valve and o.

gaskets

Disconnect the lines to and from the the fuel cell.

I.

cover

and

to the surface of the

Working through

the

retaining

bolts and

plumbing to the jet pump and check valve, the jet transfer pump from the fuel cell. cover

gaskets.

then

remove

the strainer and drain

opening on top of the auxiliary fuel cell, disengage the hanger strap and remove them from the fuel cell.

assembly,

inboard segments of the

jet

transfer pump lines from the p.

Release the

q.

Collapse

hook/loop

fasteners

the fuel cell and

securing

remove

it

the cell to the upper the

through

large

access

wing

skin.

opening

on

top of the

center section.

AUXILIARY FUEL CELL INSTALLA TION NOTE:

Expose

the fuel cell to

temperatures of

at least 60" F for

a

period sufficient

to ensure

flexibility during

installation.

the fuel cell and install it in the

a.

Collapse

b.

Press the

c.

With the check valve installed

hook/loop

fasteners

valve and float switch into the

together on

wing

center section.

to secure the fuel cell to the upper center section skin.

the strainer and drain valve

assembly, insert the assembled strainer, drain the assembly in place with the attaching bolts inch-pounds, then safety them.

in the fuel cell and

opening (Ref. Figure 206). Torque the retaining bolts

to 45 to 50

secure

installing the strainer assembly, place one gasket gasket between the skin and the strainer assembly.

NOTE: When

d.

n24

between the fuel cell

Reconnect the electrical leads of the float switch, then install the

cover over

fitting

and skin and the other

it and the strainer and drain valve.

28-1 0-00

Page

yaM512

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

NOTE: If the float switch

or

the

plug adjacent

to it has been

removed, apply

a

torque of 35

to 50

inch-pounds

upon

installation. e.

Working through the large

oval

faces forward.

pump) f.

opening on top of the auxiliary fuel cell, connect the jet transfer pump to assembly. Install the jet pump so that the motive flow port (large end of the

access

the check valve of the fuel strainer

Insert the inboard segments of the fuel lines to the jet transfer pump through the large oval opening on top of through the support strap just inboard of the aft end of the opening. Connect the motive flow (3/

the fuel cell and 8

g.

line to the forward

inch)

facing

end of the pump and the outlet

(1/2 inch)

line to the aft end of the pump.

Connect the vent, fuel return, motive flow and jet pump outlet lines at the outboard end of the the "WWD" clamps to the values listed in Chart 1.

auxiliary fuel

cell.

Torque h.

Connect the outboard segments of the jet transfer pump lines to the inboard segments at the unions under the cover opening on top of the fuel cell.

i.

Clamp

the hoses in

which connect the two lines from the

place

inboard end of the fuel cell

adjacent

to the cell

nipples.

directly

jet transfer pump to the external fuel lines at the jumper to the connector hose clamps on

Install the bond

each line to the fuel transfer pump.

j.

Place a gasket on each side of the fuel cell cover pan. Align the fuel cell cover with the mounting holes on top of the pan. Install and torque the cover plate retaining bolts to 45 to 50 inch-pounds for serials FL-1 thru FL-265, FL-267 thru FL-283; PM-1 thru FM-10 that have not installed Kit 130-9005-5. Install and torque the cover plate

retaining

bolts to 35 to 40

FL-284 and after; FM-II and after and

inch-pounds for serials FL-266,

prior airplanes

that have Kit No. 130-9005-5 installed.

NOTE:

the cover retaining bolts in the sequence designated by numbers 1 through 36 in Figure 202 to proper installation of the cover. On airplanes FL-266, FL-284 and after; FM-11 and after and prior airplanes that have Kit No. 130-9005-5 installed, complete the torque sequence one time only and check torque in sequence shown and re-torque bolt only if torque is lower than 30 inch-pounds.

Torque ensure

CAUTION: Handle the fuel accuracy of the k.

Insert the fuel

Torque one

quantity probe

the bolts to 25

of the

quantity probe carefully. Damage probe as a measuring device.

5

into its

opening

to the surface of the

in the fuel cell

inch-pounds, then safety

cover

and

secure

probe tubes will destroy the

in

place

attaching bolts. bonding jumper under

with the

the bolts. Install the free end of the

probe mounting bolts.

the connector of the electrical lead of the fuel

quantity probe

into the

airplane wiring.

i.

Plug

m.

Install the

n.

Insert the inboard fuel quantity probe into its opening on top of the center section aft of the main spar and adjacent to the fuselage. Torque the bolts to 25 f 5 inch-pounds, then safety the bolts. Install the free end of the bonding jumper under one of the probe mounting bolts.

access

plate

over

CAUTION: Handle the fuel of the o.

Install the

Page

yaM612

1/08

probe

the fuel cell

cover.

quantity probe carefully; damage measuring device.

to the surface of the

probe

will

destroy the accuracy

as a

access cover over

the fuel

28-1 0-00

quantity probe

and

secure

in

place

with the

attaching

bolts.

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

i; i

D j

F~

I

3

1"

´•o~

a A

C

8~

B JET PUMP

GASKET

~II----

Cj DETAIL

VALVE

FUEL C)UANTITY PROBE FUEL

GASKETS

6

STRAINER

,~iy a

FLOAT SWITCH s

FUEL LINE CLAMP PLUG

D

DRAIN

HOSE CLAMPS

De-lAIL

C

VALVE

BONDING JUMPER

FUEL CAP AND

JUMPER

FILLER

CLAMPS

ii

111 i::

"I´•;´•

i~VO

O

FUEL LINE CLAMPS

FROM

DETAIL

A DETAIL

MOTIVE

B

VALVE 350-281-33

Auxiliary Fuel Cell Installation

Figure

A24

206

28-1000May

1/08

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

LEAKAGE CHECKS AND REPAIRS To

WING FUEL

CELLS)

integral (wet wing) fuel cell, measure the size of the wet area around the by wiping the leakage clean and applying talcum powder in the area of the leak. After 30 minutes, check the area to determine if the leak classifies as a stain, seep, heavy seep, or running leak (Ref. Figure 207). Fuel leaks must also be classified as to whether they occur in an open area or in an enclosed area to differentiate between those that require immediate repair and those not considered potential flight hazards. classify

leak. A

the

(WET

more

degree of leakage

Any leakage

WARNING:

into the a.

Heavy seeps

or

in

an

enclosed area, such as the wheel well, or in an area where the fuel will blow requires grounding the airplane until repair is made.

smaller leaks in

(Item 8, Chart 2, in

an

fuselage,

maintenance. No action sealant

in

accurate measurement may be obtained

an

open

at

repair

required

28-00-00

or

may be repaired any time the airplane is grounded for other stations other than the Maintenance base of operations. An external

area

Item 9, Chart 2,

28-00-00)

may be used.

immediate

grounding

and

b.

Any leakage

c.

Remove any sealant around the leak with a sharp nonmetallic tool, such as a tool of chisel-shaped formica. Scarf the ends of the existing fillet so that the new sealant can form a continuous and smooth tie-in. Sealant

(Item 6,

enclosed

an

area

requires

repair.

Chart 2,

28-00-00) is recommended for fillet and faying seals and sealer (Item 2, Chart 2, 28-00-00) is coating and injection seals. Thoroughly clean the area to be repaired with solvent 28-00-00 or Item 5, Chart 2, 28-00-00) prior to sealing. The following repairs are permissible: 2,

recommended for

(Item 4, 1.

Chart

If the

leakage

is around

a

rivet, restrike the rivet. This

can

only

be done

once.

If the leak

persists, replace

the rivet. 2.

If the or

3.

4.

leakage

is around

a

bolt with

If the

leakage is at the gasket persists, replace the gasket. If

a

gasket type seal, retorque the

bolt. If the leak

persists, replace

the seal

the bolt.

around

leakage is around anchor nuts or (Item 6, Chart 2, 28-00-00).

an access

access

opening

plates

on

or

fitting, retorque

the underside of the

the attachments. If the leak

wing,

seal around the nuts with

sealer

NOTE: If the drain valve the castellated

Page

yaM812

1/08

was

removed

portion down,

during the foregoing

checks and

then torque the nut to 75-100

28-1 0-00

repairs, inch-pounds

install the valve and

retaining

nut with

safety.

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

RUNNING LEAK

3/4" DIA.

~3

i

f

Dln

O

STAIN

j 1

1/2"

i-r’6"

o

DIA

~i

1

SEEP

MAX.

I 3

1/2"-1" D1A ARE9 WHERE FUEL APPEARS TO FLO\N OR

RUN, FOLLOWING CONTOUR OF

SKIN \NHEN THIS AREA IS WIPED

DRY

FUEL WILL USUALLY BEGIN To DRIP~-AFTER REACHING THIS POINT

HEAVY SEEP

A100-231-23

Leakage of Integral (Wet Wing) Figure 207

Fuel Cells

FUEL CELL LEAKAGE TEST Rubber bladder type fuel cells may be bench tested for leakage by sealing off all openings and inflating the empty psi with a mixture of shop air and ammonia gas, then checking for visible indications of leakage on a cloth

cell to 1/4

saturated with a.

phenolphthalein

The following equipment is required and should be hooked up 1.

Closure

plates

sufficient to

opening 2.

Rubber

3.

leakage test, proceed

as

as

follows:

indicated in the schematic in

Figure

208.

for the fuel cell

cover

the cell

opening. Such plates may be fabricated of aluminum sheet cut to a size openings. Drill holes in the closure plate to match the hole pattern around the

in the fuel cell. to plug the fitting openings in the fuel cell. One of the stoppers plastic tubing used to connect the fuel cell into the test setup.

stoppers

insertion of the

A24

solution. To set up and conduct the

A manometer for

differential. The manometer

clear

the illustration shown.

measuring 6 inches of water plastic tubing; frame and scale similar to

can

should have

a

hole for

be fabricated from

28-1 0-00

glass

or

Page

yaM912

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

A

5.

Two flasks

6.

that

regulator

4.

can

be set to

1/4

provide

psi (6

inches of

water)

from

a

supply

of

air.

(or bottles) approximately one liter (or quart) in capacity. A third container may be hooked into the test setup to provide an optional overflow collector if desired. The two containers should be provided with rubber stoppers that have holes for insertion of 1/4-inch tubes (glass or metal) as shown in the schematic in

Figure

Plastic

of

tubing

components

a

208.

shown

as

provide a leak-free fit in Figure 208.

size to

over

the tubes and

a

length

sufficient to interconnect the test

7.

Make up a solution of phenolphthalein as follows: Add 1/3 ounce phenolphthalein 1/2 gallon of ethyl alcohol (obtain locally), mix, then add 1/2 gallon of water.

8.

Make up

an

by adding 100 gallon of water.

ammonia solution

(NH40H) (obtain locally) 9.

shop

per

Place the fuel cell and test

CAUTION: Make

sure

10. Install the closure

equipment

the work

plates

area

over

on a

cc

(3

ounces)

of concentrated ammonium

to

hydroxide

clean work bench.

is clean of metal

the fuel cell

fluid

crystals (obtain locally)

shavings

openings

or

other debris that could

damage

the fuel cell.

and torque the retaining screws as specified in the openings, then insert the rubber stoppers into the

installation section of the Maintenance Manual for the open

fittings.

11. The flask

(or bottle) containing

the ammonium

hydroxide

solution should be 1/3 to 1/2 full

as

shown in the

illustration. 12. Connect as

a

shop air supply to the regulator and Figure 208.

interconnect the

regulator, breakers,

fuel cell and manometer

indicated in

13. Inflate the fuel cell to 1/4

psi

with

a

mixture of

shop

air and ammonium gas. A &inch difference in the two psi. It is not necessary to restrain

water levels of the manometer will indicate that the fuel cell is inflated to 1/4

the cell other than to

keep from rolling off the bench. The filling of

but should not be rushed 14. Saturate

a

large,

as

the cell will be rather slow at the 1/4

psi,

overpressure of the cell could result.

clean cloth with

phenolphthalein. (Immerse

it in

a

container and squeeze out

excess

liquid). CAUTION: Wear rubber gloves to protect against skin irritation when handling the cloth. As a further protection against possible penetration of the phenolphthalein solution through the gloves, wash your hands thoroughly after finishing the test. 15.

Lay

the cloth

With each

over

the various

application

portions

presence of a leak. Encircle the locations of leaks. NOTE: Continued

use

evaporation

of the

area on

testing

pink

stain

the fuel cell beneath such stains with

cloth will

a

on

the cloth to indicate the

chalk mark to

pinpoint the

require repeated saturations with phenolphthalein since rapid progressively reduces the sensitivity of the test unless the

of the alcohol from the cloth

solution in the cloth is

May

of the fuel cell until the entire exterior of the cell has been covered.

of the cloth, watch for the formation of reddish

frequently

28-1 0-00

renewed.

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

EMPTY FUEL CELL

(ALL OPENINGS PLUGGED)

OPTIONAL

OVERFLOW COLLECTOR

SHOP AIR

PLASTIC

AMMONIA GAS

STD. RULER

TUBING

(NH3)

OR YARDSTICK

LEAK PROOF

MOISTURE

STOPPERS

COLLECTOR 6"

REGULATOR SET TO ~d PSI

L-Y1C-~

GLASS

X/

TUBES

AMMONIUM HYDROXIDE

GLASSFLASK

(NH4OH)

OR

SOLUTION

BOTTLE

MANOMETER 6" of WATER

PSI U-28~´•30

Setup

for

Leakage Figure 208

Test

UNIROYAL FUEL CELL REPAIR

pertaining to the repair, handling and storage of Uniroyal fuel cells, refer to Report FC-1473-73 Handling and Storage Procedures for Bladder Type Fuel and Oil Cells", which is published Inc., by Uniroyal Engineered Systems Department, Mishawaka, Indiana. This manual has been included in the Component Maintenance Manual. For information

entitled "Recommended

GOODYEAR FUEL CELL REPAIR For information regarding the repair, handling and storage of BTC-54A, BTC-67, ETC-85 and ETC-99 fuel cell constructions, refer to the manual entitled "Repair and Maintenance Manual for Vithane Fuel Cells" (Publication Number: AP368; Goodyear Aerospace Corporation, Engineered Fabrics Division, Rockmart, Georgia 30153). This manual has been included in the

replaced

A24

rather than

repaired

Component Maintenance damaged.

Manual. ETC-39 and ETC-39-1 type fuel cells should be

when

28-1 0-00

Page

2 1Mayl/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

FUEL CELL PRESERVATION CAUTION: Never store fuel cells in the

vicinity of electrical equipment,

such

as

generators and motors. The

the commutators of these units will result in minute sparks that cause the formation of ozone gas. Ozone has a highly destructive effect on fuel cells. Although it leaves no visible indication, ozone makes the material of which the cells are formed brittle so that the cells will movement of brushes

disintergrate

upon

across

application

of stress.

NOTE: Preservation is not necessary for in-service fuel cells. When the cell is to be empty for an indefinite the fuel cell should not be open to the atmosphere except for the normal vent lines in the airplane. NOTE: If aviation

gasoline

was

empty for any indefinite

Goodyear fuel cells for storage of

yaM2 2

1/08

a

period

prior to emptying, purge

the cell with

jet fuel prior to leaving

the tank

of time.

polyethylene: they need not be treated for storage. The only recommendation they be carefully wrapped for protection against dust, then be stored at room from sunlight.

constructed of

Goodyear

temperatures in

Page

are

in the fuel cell

period,

cells is that

location shielded

28-1 0-00

,4

Raytheon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUEL DISTRIBUTION

MAINTENANCE PRACTICES

FUEL FITTINGS

Any time

the clamp-type fittings connecting the fuel lines are loosened, new O-rings must be installed in the assembly before the fitting is clamped. When installing these fittings, ensure that the safety spring is seated in the clamp lever. Lubricate all AN type fittings and B-nut seats with an approved anti-seize thread compound prior to tightening. Thoroughly inspect all areas of maintenance for leaks and seepage (Ref. Figure 201).

ENGINE FUEL FIL TERS AND SCREENS Refer to the Pratt for the

Whitney Engine Maintenance Manual for The engine-driven fuel pump, screens, and filters.

PT6A-60A

Engine for proper servicing procedures

NOTE: The fuel filters and

screens are cleaned and inspected as specified in Chapter 5. In addition to such precautions, all fuel filters and the tank sumps should be cleaned any time the submerged standby boost

pumps

are

removed.

ENGINE-DRIVEN FUEL BOOST PUMP REMOVAL a.

Disconnect the inlet, outlet and drain lines from the pump.

b.

Remove the four bolts remove

securing the pump airplane.

in

place

on

the

vacuum

pad of the engine

accessory case, then

the pump from the

ENGINE-DRIVEN FUEL BOOST PUMP INSTALLA TION a.

Apply lubricating

b.

Engage the pump drive spline with the pump with the seal drain port down.

c.

Install and torque the four mounting bolts to 65 to 85 inch-pounds.

d.

Reconnect the inlet, outlet and drain lines to the ports of the pump housing.

A21

grease

(7,

Chart 2,

28-00-00) sparingly positioned

to the drive

on

the

spline

vacuum

of the boost pump.

pump

pad of the engine accessory case

28-20-00

201

Ray~heon

AiKlaft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i.

4.

2. RING SEAL ON INSTALL EACH FERRULE (LUBRICATE BEFORE INSTALLING).

INSTALL RETAINER ASSEMBLV ON BODY.

INSTALL BODY ON ONE FERRULE.

3.

PULL BODv BACK OVER OTHER FERRULE.

j

ENGAGE LATCH ASSEMBLY.

RETAINER SAFETY SPRINGASSfMBLV LATCH ASSEMBLY BONDING WIRE

BODY

I~

F~J´•

FERRULE "O~ RING SEAL

(NOT FURNISHED) 1WO-Zlll-29

Fuel Fittings Installation Figure 201

Oct

31/0628-20-00

A21

Raycheon

Aircraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STANDBY BOOST PUMP REMOVAL all electrical power to the

a.

Make

b.

Drain the nacelle and

c.

Remove the oil cooler duct and the scoop

d.

Disconnect the electrical lead from the pump.

e.

Cut the

f.

sure

safety wire

wing

fuel cells

from around the

Pull the pump out far

enough

airplane

is disconnected.

(Ref. Figure 202). over

retaining

the pump.

bolts and

to disconnect the fuel

remove

plumbing

the bolts.

at the pump outlet

fitting,

then

remove

the pump

from the cell.

STANDBY BOOST PUMP INSTALLA TION CAUTION: When

a new

standby boost pump is

to be

installed, submerge it in fuel before performing the bench test

run.

a.

Insert two headless 1/4 UNF bolts, 1-1/2 inches

of the pump

(Ref. Figure 202).

b.

Position

gasket

c.

With the

outlet

one

long,

between the cell and the tank liner and

large plug aft, fitting.

insert the pump far

enough

d.

Fully insert the pump into the mounting opening, bolts to 45 to 50 inch-pounds. Safety the bolts.

e.

Connect the electrical leads to the pump.

f.

Reinstall the scoop

nn

into the pump

over

into the

working

one

mounting ring

gasket

between the tank liner and the pump.

mounting opening

the cell

over

in the cell to aid in installation

to connect the

plumbing

the pump. Install and torque the

to the

retaining

the pump and the oil cooler duct.

28-20-00Page

203

Raytheon

AiKraft Company

SUPER KING A\R B3001B300C MAINTENANCE MANUAL

CHECK

I

~YI

VALVE

CHECK VALVE

FUEL STRAINER STANDBY BOOST PUMP

OW LEVEL SENSOR

DEFUELING VALVE

d DETAIL

A

Components

350-281-35

in the Nacelle Fuel Cell

Figure

Page

tcO402

31/06

28-20-00

202

A21

8aytheon

Aircraft

Company

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

JET TRANSFER PUMP REMOVAL a.

Drain the fuel cells.

b.

Working through the

cover opening on top of the auxiliary fuel cell, disconnect the jet pump from the motive flow line, outlet line and check valve beneath the pump, then remove the pump from the fuel cell (Ref. Figure 203).

JET TRANSFER PUMP INSTALLATION a.

Working through

the

opening

cover

on

top of the auxiliary fuel cell,

the check valve attached to the fuel strainer of the

b.

jet

pump faces

assembly. forward (Ref. Figure 203).

Connect the forward to the fuel outlet

facing end of the (1/2 inch) line.

connect the bottom

Install the pump

pump to the motive flow

so

that the

(3/8 inch) line

port of the jet pump to

large

and the aft

end

(motive

facing end

flow

port)

of the pump

FIREWALL SHUTOFF VALVES

Electrically operated, gate-type Relief valves

are

incorporated

shutoff valves

are

mounted behind the firewall

into valves to relieve thermal

on

the inboard side of each nacelle.

expansion downstream from the valve (Ref. Figure 203).

NREWALL SHUTOFF VAL VE REMOVAL Make

b.

Drain the fuel system to

c.

Remove the

d.

Disconnect the electrical lead from the valve.

e.

Disconnect the inlet and outlet lines from the valve and

f.

Remove the

sure

all electrical power to the

is off.

a.

access

safety

a

door

airplane

level below the shutoff valve on

(Ref. Figure 203).

the inboard side of the nacelle,

wire and four

mounting

bolts and

plug

just

forward of the

leading edge.

the lines.

remove

the valve from the

mounting

bracket.

FIREWALL SHUTOFF VAL VE INSTALLA nON a.

Position the valve in its

b.

Connect the inlet and outlet lines.

c.

Connectthe electrical leads.

d.

Replacetheaccess

nn

mounting bracket,

then install the

mounting

bolts and

safety

wire

(Ref. Figure 203).

cover.

28-20-00

NaYifNeon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIREWALL SHUTOFF VALVE FUNCTIONAL CHECK CAUTION: When the firewall fuel shutoff valve switch is actuated to the closed position, the EXTINGUISHER PUSH annunciator in the

extinguisher is

corresponding fire extinguisher switch illuminates to indicate that the engine fire Actuating the extinguisher push light/switch will release the extinguishing agent.

armed.

NOTE: The firewall fuel shutoff valve switches and

right

of the

warning

annunciator

a.

Start the

b.

Upon engine stabilization, perform 1.

engine

Close the

as

placarded panel.

outlined in the B300/B300C FAA

applicable engine

the

following

FMI VALVE PUSH

located in the

are

Approved Airplane Flight

glareshield

to the left

Manual.

check:

firewall shut-off valve

by pushing

the FMI VALVE PUSH switch.

NOTE: If

engine fuel flow does not decrease to zero (O) within 10 seconds of fuel flow shut-off valve activation, replace the motive flow check valve and repeat this procedure.

2.

Observe that the zero

3. c.

(O)

appropriate FUEL PRESS LO annunciator illuminates and engine following activation of fuel firewall shut-off valve.

fuel flow decreases to

within 10 seconds

Repeatthis procedureforthe otherengine.

If the firewall shut-off valve does not function referenced in

chapter

28 of the

Component

properly, perform

inspection and functional (P/N 101-590097-13).

the

Maintenance Manual

test

procedures

CROSSFEED VALVE The line-mounted crossfeed valve allows crossfeed of fuel from either system to either or both engines when circumstances warrant. The crossfeed valve is located on the inboard side of the left wheel well (Ref. Figure 203).

CROSSFEED VALVE REMOVAL a.

Make

b.

Drain the fuel system to

c.

Disconnect the inlet and outlet lines from the valve and

d.

Disconnect the electrical lead from the valve.

e.

Remove the

sure

all electrical power to the

safety

a

airplane

is off.

level below the crossfeed valve

wire and

mounting

bolts and

(Ref. Figure 203).

plug the

remove

lines.

the valve from the

mounting

brackets.

CROSSFEED VALVE INSTALLATION a.

Place the valve in its

b.

Connect the inlet and outlet lines to the valve.

c.

Connect the electrical lead to the valve.

Oct

mounting

bracket then install the

31/0628-20-00

mounting

bolts and

safety wire (Ref. Figure 203).

na

Rayfhwm

AiKraft

Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

FUEL PURGE LINE CHECK VALVE To

gain access to the fuel purge line check valve, just forward of the wing leading edge.

remove

the

access cover

from the outboard side of each nacelle

MOTIVE FLOW VALVE jet pump that transfers fuel from the auxiliary to the main fuel side of each nacelle. To gain access to this valve, remove is of the the outboard mounted firewall aft on just system the access cover from the outboard side of each nacelle just forward of the wing leading edge (Ref. Figure 203). The valve that controls the motive flow of fuel to the

MOTIVE FLOW VALVE REMOVAL all electrical power to the

a.

Make

b.

Disconnect the

c.

Disconnect the fuel lines from the valve and

d.

Remove the 2

sure

plug

and

receptacle

mounting bolts,

then

airplane on

is off.

top of the valve (Ref. Figure 203).

remove

plug

the lines.

the valve from the

airplane.

MOTIVE FLOW VAL VE INSTALLA TION a.

Position the valve

b.

Connect the inlet and outlet lines to the valve.

c.

Connect the

~31

on

its

mounting

wiring receptacle

bracket and

to the

plug

on

secure

in

place

with the 2

attaching

bolts

(Ref. Figure 203).

top of the valve.

28-20-00Page

207

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A

,b5

I~dl;(L c

i

i_iq3~k3; D MOTIVE FLOW VALVE

OUTLET

JET TRANSFER PUMP

INLET

CHECK

VALVE

FLOAT SWITCH

II

j ~ETAIL A DETAIL

D

FIREWALL

SHUTOFFVALVE ~a

DETAIL

B CROSSFEED

VAL ED TAIL

C aso-2el34

Fuel

Oct

28-20-00

System Pump and Valve Installations Figure 203

A21

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIREWALL FILTER CLEANING Clean the firewall filters at intervals noted in Chapter 5-20-00. a.

Closethefirewall shutoff valve.

b.

Remove the drain hose from the firewall filter and disconnect the drain line.

c.

Cut the iockwire

d.

Removethe

e.

Removethefiltercase assembly.

f.

Remove the two hex nuts

g.

Remove the filter element.

h.

Clean the filter element, filter

i.

Install the filter element and

j.

Install the filter

k.

Install the washer seal and

i.

Safety the retaining

m.

Install the drain hose and connect the drain lines.

n.

Openthefirewall

securing

retaining

case

the filter

case

assembly retaining

nut.

nutandwasherseal.

the filter element.

securing

case

assembly and mounting

secure

hardware with solvent

(3, Chart 2, 28-00-00).

it with two hex nuts.

assembly. retaining

nut.

nut with lockwire.

shutoff valve.

RESET FUEL FILTER BYPASS INDICATOR is equipped with a bypass indicator in the form of bypass condition. Reset the bypass indicator as follows:

The fuel filter

assembly

the filter is in

a

a.

Remove the fuel filter

b.

Press up

c.

Clean and

A21

on

the black

inspect

case

a

red button that will pop up

indicating

that

31/06Page

209

and element.

plunger button and

the filter element and

reset the red

bypass

replace the filter

case

indicator

simultaneously.

and element.

28-20-00

Oct

Ral~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INTEGRAL FUEL TANKACCESS DOOR REMOVAL Remove the fuel tank access door to

CAUTION: Refer to

gain

access to

Chapter 12, FUEL operations on the

maintenance

Drainthefuelsystem. RefertoChapterl2.

b.

Insert

10-32

screw

probes

for maintenance

or

to

stop leakage.

HANDLING SAFEP/ INFORMATION, before fuel system.

a.

a

the fuel

proceeding

with any

into the threaded hole in center of the exterior surface of the door to be removed

(Ref.

Figure 204). c.

Remove the countersunk

d.

Holding

the door with the 10-32

door

necessary to

a.

as

O-ring

Remove the

screws

remove

from the

perimeter

of the door to be removed.

inserted in step b, push in on the door to release the seal and rotate the it from the opening in the wing lower skin. screw

seal from the

perimeter of the

door and discard.

INTEGRAL FUEL TANKACCESS DOOR INSTALLATION a.

Clean the

b.

Insert

a

c.

Install

a new

d.

mating

10-32

surfaces of the

screw

wing

skin and the door. Clean the

O-ring groove

in the door.

into the threaded hole in the exterior surfaces of the door to be installed

AN124029

O-ring

Holding the door by the 10-32 position

skin and rotate it into

into the groove in the

screw

(Ref. Figure 204).

perimeter of the door.

inserted in step b, insert the door into the access opening in the lower wing Ensure that the O-ring is properly positioned in the groove of the

opening.

in the

door.

NOTE: The door should be installed in the

Install the countersunk screws around the

a.

sequence in b.

wing

Tighten

the

Figure screws

with the 10-32

holding

screw

to the outboard side.

perimeter of the door and initially snug the screws using the tightening

204. to 20-25

inch-pounds

in the order

specified by

the

tightening sequence

in

Figure

204.

important to tighten the door screws in a definite pattern to ensure uniform compression of the seal and prevent possible fuel seepage. The example in Figure 204 shows the sequence to be followed when

NOTE: It is

tightening

Oct

31/06Page

210

the

retaining

screws

in these doors.

28-20-00

RBy~heOn

nircraft Campany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

10-32 HOLE 7

3

5 9

I 1

14

15

17

d

1 ~I

16

18

12

10~ 6

2

4

8

C920~213

Integral

A21

Fuel Tank Access Door Tightening Figure 204

Sequence

28-20-00

Page

211

Oct 31/06

Ray~hwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INDICATING

DESCRIPTION AND OPERATION

CAPACITANCE FUEL QUANTIN INDICATING SYSTEM The fuel

compensated for specific gravity and reads in a pounds system processes the signals from the fuel quantity for in various fuel cells readout by the fuel quantity indicators. A selector switch the accurate an (capacitance) probes located between the fuel quantity indicators in the fuel panel beside the pilot may be set in the MAIN or momentarily held in the AUXILIARY position to determine whether the gages indicate the pounds of fuel in the nacelle and wing fuel cells of the main fuel system or the pounds of fuel in the center section fuel cell of the auxiliary fuel system. Each side of the airplane has an independent gaging system consisting of a fuel quantity (capacitance) probe in the nacelle fuel cell, one in the aft inboard fuel cell, two in the integral twet wing) fuel cell, two in the inboard leading edge fuel cell and two in the center section fuel cell. When the fuel selector switch is in the MAIN position, the fuel select relay will not be energized and the input to the indicator from the SIGNAL IN tred) wire will be from the main fuel tank probes. Additionally, the SIGNAL IN (red) and the SIG RETURN tgreen) wires from the auxiliary tank probes will be connected together through the relay, which will prevent the indicator from reading the auxiliary tank fuel quantity. Holding the fuel selector switch in the AUX position will energize the fuel select relay which allows the indicator to receive the signal by the SIGNAL IN tred) wire from the auxiliary tank probes and the SIGNAL IN (red) and the SIG RETURN tgreen) wires from the main tank probes will be connected together so that the indicator will only read the auxiliary fuel quantity.

quantity indicating system

on

is

a

capacitance type

that is

linear scale. An electronic circuit in the

density and electrical dielectric constant vary with respect to temperature, fuel type and fuel batch. The capacitance gaging system is designed to sense and compensate for these variables. The fuel quantity probe is simply a variable capacitor comprised of two concentric tubes. The inner tube is profiled by changing the diameter as a function of height so that the capacitance between the inner and outer tube is proportional to the tank volume. Fuel

The tubes the fuel

serve as

fixed electrodes and the fuel of the tank in the space between the tubes acts as the dielectric of The capacitance of the fuel quantity probe varies with respect to the change in the dielectric

quantity probe.

that results from the ratio of fuel to air in the fuel cell. As the level of fuel between the inner and outer tubes rises, air with a dielectric constant of one is replaced by fuel with a dielectric of approximately two, thus increasing the

capacitance variation that is a linear function of that volume. This function is converted to a linear current that actuates the fuel quantity indicator. Capacitance fuel probes are designed to produce a capacitance variation that is linear in relation to variation in weight, even though weight is nonlinear with respect to the fuel level. By varying the capacitance per inch, the nonlinear level signal is changed to linear function. In addition to its capacitance sensing tubes, each fuel quantity probe contains a small circuit network that produces an output current whose average value is directly proportional to fuel level, while automatically compensating for fuel temperature-density variations. An A-C waveform, whose characteristics are insulated by a regulator from line voltage variations in the incoming +28 VDC, is impressed across the low Z side touter tube) of the fuel quantity probe. The ensuing signal is further processed by a DC amplifier, which contains a potentiometer for adjusting the "Full" and "Empty" settings. The DC amplifier controls response time and drives a servo type meter movement. FUEL QUANTITY SENSOR In addition to the fuel

low fuel

(electro-optic) level sensors are installed in lights in the Caution/Advisory annunciator panel to indicate approximately 300 pounds of fuel remaining in the L or R fuel system. This remaining fuel supply is calculated to provide approximately 1/2 hour of fuel flow at maximum continuous power at 10,000 feet altitude. A time delay is incorporated into the electrical circuitry to reduce the possibility of false low fuel level indications caused by sloshing of fuel in the tanks. A test position on the fuel selector switch on the fuel control panel provides a means of determining that the sensor system is working properly. quantity capacitance indicating system,

each nacelle fuel cell which will illuminate amber L and/or R FUEL QUANTITY

nzl

28-40-00

I

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUEL CAPACITANCE PROBES Each

I

capacitance probe consists of

two concentric tubes. The tubes

serve as

fixed electrodes and the fuel of the

tank in the space between the tubes acts as the dielectric of the probe. The capacitance of the probe varies with respect to the change in the dielectric that results from the ratio of fuel to air in the tank. The capacitance of the probe

changes with variations in the different manufacture’s fuels that may result in density changes, etc. The tubular capacitor elements of each capacitance probe are profiled to match the contour of the tank in which it is installed to provide linear capacitance versus volume in the tank at differing flight attitudes. The nacelle capacitance probe contains an integral compensator installed in the lowest point of the fuel cell so that it will always be covered by fuel. It is located thus to sense any variation in the dielectric constant of the fuel caused by temperature changes. The signal output from the compensator is used as a correction signal for the reference portion of measurement circuit to minimize errors in the indicator section. The nacelle capacitance probe’s integral compensator does sense variations of the dielectric constant of the fuel caused by temperature changes but not changes caused by variations in the different manufactures fuels that is seen by changes in capacitance of the two concentric tubes. also

Oct

31/06Page

2

28-40-00

Ral~heOl

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INDICATING- TROUBLESHOOTING

Troubleshooting of the fuel quantity indicating system requires the use of special tools (Ref. Chart 1, 28-00-00). The DC-400 and DC-400A digital DC Fuel Quantity Test Sets (1, Chart 1, 28-00-00) are manufactured by Barfield Instrument Corp. These two test sets function identically, only difference is that the DC-400A has a greater range than the DC-400. The test set TK2129/935 (3, Chart 1 28-00-00) is a DC-400 test set that has been modified by Raytheon Aircraft Company. They have a 15 pin "D" connector and a shorting switch that has to be set that the DC400 and DC-400A do not have.

One 9-vdc

battery inside the test set provides the power required to read insulation (conductance and capacitance. capacitance in picofarads (pF) and conductance in nano Siemens (nS). The airplanes battery power auxiliary power source is required for indicator checking and calibration.

The LCD shows or an

Troubleshooting

phases: checking the system harness insulation, probe harness insulation, system capacitance, probe capacitance and indicator test. If the indicator does not check or is replaced, checks

carried out in five

are

it must be calibrated.

SYSTEM INSULA TION CHECK NOTE: Connect

a

regulated

28-vdc external power

supply

to the

airplane when troubleshooting

or

calibrating.

This test

procedure may be performed with full, partially full or empty tanks. Display reading are presented in nano (nS), equivalent megohms are derived by dividing 1000 by the LCD display reading: 1000/50 nS= 20 Megohms. These checks are identical for the left and right fuel systems (Ref. Chart 104). Siemens

a.

Locate the test set

b.

Ensure that the test set ON/OFF switch is in the OFF

conveniently for the procedures

that follow.

position.

CAUTION: Power to the

airplane must be off when lowering or raising possibility of shorting any wiring connections to ground.

c.

Disconnect

d.

Ensure that the

e.

Open

f.

Leave the

g.

Gain

h.

Disconnect airplanes harness from the fuel

i.

Connect the test set

panel

to

preclude the

battery.

the fuel

battery

switch is OFF.

quantity system

airplane’s

access to

fuel

circuit breakers.

fuel select switch in the MAIN

quantity

(1

or

position.

indicator.

quantity

quantity

j.

Rotate TEST FUNCTION selector to IND AMP.

k.

Set INSULATION/SYSTEM switch to INSULATION.

I.

Rotate INS TEST POINTS switch to LO-UGND.

m.

Place the

shorting

indicator.

3, Chart 1, 28-00-00) ACFT

NOTE: Do not connect the test set to the fuel

nzl

the fuel control

switch to the NO

connector to the

airplane’s

hamess.

indicator.

position. (On Raytheon Modified

test sets

only.)

28-40-00

101

Raythwm

Aircraft Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

I

n.

Place the ON/OFF switch to ON and allow sufficient time for LCD to stabilize.

o.

The LCD

NOTE:

reading

During

should be less than 50 nS.

the insulation test, it may take

does not read below 50 nS in

p.

one

some

time for the indication to

completely

stabilize. If the indication

minute, the reading is unacceptable.

remaining positions. Allow sufficient time (no more than one position. reading in each position should be less than 50 nS, will show an overrange indication (1

Rotate the INS TEST POINTS selector through the

minute)

for the LCD to stabilize in each

except in the SIG/RTN position which

The LCD

q.

Rotate INS TEST POINTS selector to RTN/SIG.

r.

Connect battery and external power to the plane.

s.

Turnthe

t.

Turn the external power switch ON.

u.

Close the fuel system circuit breakers that ON shall not exceed 10 nS.

v.

Set the

battery masterswitchON.

airplanes

were

opened

in step

e.

The

change

between power OFF and power

fuel select switch to AUX and hold.

remaining positions. Allow sufficient time (no more than one minute) for the LCD to stabilize in each position. The LCD reading in each position should be less than 50 nS. Except in the SIG/RTN position which will show an overrange indication (1 Rotate the INS TEST POINTS selector through the

NOTE: Due to

continuity through

that short will also be

I

x.

y.

the diodes inside the

seen as a

probe,

when the test set detects

a

short from RTN to GND,

short from SIG to GND.

When any of the above checks are out of tolerance, isolate parts of the airplane center section wire harness from the wing wire harnesses by disconnecting the wing break connector (P281).

Repeat steps j through w. Acceptable readings are 50 nS or less. If the insulation readings are acceptable, the wing tank wire harness to the probes. If not, the fault is in the airplane’s wire harness between the indicator in the cockpit out to the wing break connector. fault lies in the

When any faults have been isolated to the 1.

at a time from their

following:

the

respective connectors,

the connectors attached to the harness.

probes disconnected

Repeat the test that indicated the fault after each probe acceptable reading would be 005 nS or less.

3.

If the fault remains disconnect the connectors from the harness

individually, repeat

If the fault still remains, the fault may be in the harness, the J281

wing

panel

is disconnected. With all

the

break connector,

an

procedure. or

the P1/J125 fuel

connector.

Perform the system isolation test when any faults have been isolated to the wire harnesses: 1.

If the fault condition

was

by disconnecting the wing break connector, clean wing break connector and confirm the fault.

corrected

contact cleaner, then connect the

Oct

one

perform

2.

4.

I

center section wire harness

Disconnect the nacelle probe and both auxiliary probes,

leaving

aa.

airplane

28-40-00

the connector with

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

2.

Systematically

disconnect each

probe,

one

at

a

time, from it’s respective matrix connector; leaving the

I

connector attached to the harness.

3.

Both wet

4.

Repeat the test that

5.

may be isolated at the

same

indicated the fault after each

If the fault remains after all the one at a

6.

wing probes

probes

by

time

probe

connector P202.

is disconnected.

have been isolated

systematically disconnect each

matrix connector,

time, and repeat the procedure.

If the fault still remains it may be in the

NOTE: The results of the

preceding checks

limits, repeat the entire

procedure

wing break

connector or the harness itself.

must be within the stated limits. If results are

slightly outside

to ensure that failure of the checks was not due to human

ab. Turn the test set OFF. Disconnect the test set. Turn off external power and airplane’s wire harnesses to the original configuration.

of these

error.

battery switches. Connect

the

I

SYSTEM CAPACITANCE CHECK fuel tanks either

The

following

a.

Locate the test set convenient to the indicator for these checks.

b.

Ensure that the ON/OFF switch

c.

Ensure that the

d.

Open

e.

Gain

f.

Disconnect fuel quantity indicator harness form the

g.

Connect the test set ACFT connector to the indicator harness.

checks must be

the fuel

battery

performed

on

fuel

airplane’s

the test set is in the OFF

master switch is OFF and the

quantity system circuit

access to

with the

full

is disconnected.

quantity indicator. rear

i.

Place the INSULATION/SYSTEM switch to SYSTEM.

j.

Place the MAINTTOI-AUWNAC switch to MAINTTOT.

k.

Place the

I.

Place the 200

m.

Place the test set ON/OFF switch to ON.

switch to the YES

(pF)/1 ,000 (pF)

on

of the indicator.

quantity

Rotate the TEST FUNCTION selector

Depress

completely

position.

battery

h.

n.

or

breakers.

NOTE: Do not connect the IND connector to the fuel

shorting

completely empty

the test set to

PROBE(S).

position. (On Raytheon

switch to 200

(pF) position

and hold test set PRESS TO READ CAP

indicator.

Modified test set TK2129/935

if tanks

are

(pF) pushbutton:

only.)

empty or the 1,000 (pF) if the tanks

the

reading

are

full.

should be within the range

shown in Chart 101.

~al

28-40-00Pagel03

NaytNaatt

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 101 Values

System Capacitance MAIN

(NOM)

AUX

(NOM)

AUX

(MIN)

152.2

186.0

59.4

53.4

65.3

FULL

253.9

228.5

279.2

97.2

87.5

106.9

or

full

capacitance

values in the

o.

Connect

p.

Place the fuel select switch to AUX and hold.

q.

Depress

battery,

connect external power; Turn on the

and hold PRESS TO READ CAP

book for future reference.

log

battery

switch and turn

The

(pF) pushbutton.

(MAX)

on

external power switch.

should be within the range shown in

reading

Chart 101.

NOTE: Record these empty If any test is out of

r.

or

full

capacitance

specifications,

probes and/or airplane’s wiring

at

values in the

log

book for future reference.

isolate fault

by referencing airplane’s wiring connecting junctions.

NOTE: The value must be within tolerances

procedure

I

AUX

(MAX)

169.1

I

I

MAIN

(MIN)

EMPTY

NOTE: Record these empty

I

MAIN

specified

in Chart 101. If results

are

schematics and

slightly

disconnecting

outside limits, repeat entire

to insure test failure is not due to human error.

completes CAPACITANCE TEST.

s.

This

t.

Place the test set ON/OFF switch to OFF

u.

Turn off the external power switch and the

v.

Connect the

battery

wire harnesses to the

airplane’s

and disconnect the test set from the indicator harness.

position

switch.

original configuration.

INDICATOR LINEARITY CHECK (NOTA SYSTEM

off set from the values used in

NOTE: The

pF values used for this test are Linearity check the system must be in this chapter. check may be

calibrated

the fuel

using

the

preferred

a

normal calibration. After

performing this procedures

or altemate system calibration

indicator with the fuel tanks full,

partially

full

The

following

a.

Ensure that the

b.

Locate the test set

c.

Open

d.

Gain

e.

Disconnect

f.

Connect the test set ACFT connector to the indicator wire harness connector and the IND connector to the

the

battery

performed

CALIBRATION)

conveniently to

to the

or

empty.

the fuel control

panel.

circuit breakers.

airplane’s fuel quantity indicator.

airplane’s

indicator. Use the

quantity

master switch is OFF.

appropriate fuel quantity system

access

indicator wire harness connector

adapter cables (8

g.

Set ON/OFF switch to OFF.

Oct

31/06Page

104

on

28-40-00

or

plug

at indicator.

9, Chart 1, 28-00-00) if necessary,

Ral~heon

Aircraft Campany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

h.

Rotate TEST FUNCTION switch to CAP SIM CAL

i.

Set INSULATION/SYSTEM switch to SYSTEM.

j.

Set MAINTTOT-AUWNAC switch to MAINTTOT.

k.

Set 200

i.

Set test set ON/OFF switch to ON.

m.

Set CAP SIM

n.

(pF)/1,000 (pF)

(pF)

switch to 200

(NORM SYS).

(pF).

100’s and 10’s thumbwheels to 1 and 8

Depress and hold PRESS TO display of 189.0 pF.

READ CAP

(pF) pushbutton

respectively. while

adjusting

CAP SIM

(pF)

control knob to obtain

test set o.

Release

p.

Rotate TEST FUNCTION switch to IND AMP.

q.

Connectaircraft

r.

Close circuit breakers.

s.

Connect external power to aircraft. Place the master switch On.

pushbutton.

battery.

battery

CA UTION: Do not tap bezel of instrument to vibrate. To

of indicator before The indicator should read If

results

required

are

zero

pounds. If

not

adjust

Rotate TEST FUNCTION switch to CAP SIM CAL

u.

Set 200

v.

Set CAP SIM

w.

Depress a

switch to 1,000

reading

of 273

y.

Rotate TEST FUNCTION switch to IND AMP.

z.

The indicator should read 1,200

aa.

If

required

results

are

not

(pF)/1,000 (pF)

ad. Set CAP SIM

Depress a

A21

adjustment

at

rear

of indicator.

respectively. while

adjusting CAP

SIM

(pF)

control knob to obtain

pushbutton.

pounds. If not, adjust

attainable, indicator

must be

ab. Rotate TEST FUNCTION switch to CAP SIM CAL

ae.

E

(NORM SYS).

(pF) pushbutton

Release

Set 200

or

pF.

x.

ac.

gently tap adjacent panel or rear housing

replaced.

100’s and 10’s thumbwheels to 2 and 7

(pF)

friction

Turn the external power

(pF).

and hold PRESS TO READ CAP

test set

EMP 1

must be

t.

(pF)/1,000 (pF)

remove

position.

taking readings.

attainable, indicator

not

switch to the On

(pF)

switch to 200

display

100’s and 10’s thumbwheels to

of 60.0

or

FULL"

adjustment

at rear of indicator.

replaced.

(NORM SYS).

(pF).

and hold PRESS TO READ CAP

test set

"F

and 6

respectively.

(pF) pushbutton while adjusting

CAP SIM

(pF)

control knob to obtain

pF.

28-40-00Page

105

Ray~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

af.

Release

pushbutton.

ag. Set MAINTTOT-AUWNAC switch to AUXINAC. ah. Rotate TEST FUNCTION switch to IND AMP. ai.

The indicator should read 0

pounds.

If not,

adjust

EMP 2/E 2 at

rear

of indicator. If

required

results

are

not

attainable, indicator must be replaced.

aj. Repeat steps (h) ak. Set MAINTTOT

thru

(ai)

as

necessary to

ensure

AUWNAC switch to MAINTTOT.

al.

Rotate TEST FUNCTION switch to CAP SIM CAL

am.

Set 200

an.

Set CAP SIM

ao.

(pF)/1,000 (pF)

Depress a

ap. Release

(pF)

switch to 1,000

reading

(NORMSYS).

(pF).

100’s and 10’s thumbwheels to 2 and 1

and hold PRESS 10 READ CAP

test set

adjustment.

accurate gage

of 210

(pF) pushbutton

respectively. while

SIM

(pF)

control knob to obtain

CAP SIM

(pF)

control knob to obtain

CAP SIM

(pF)

control knob to obtain

adjusting CAP

pF.

pushbutton.

aq. Rotate TEST FUNCTION switch to IND AMP. ar.

The indicator should indicate 300 +35

as.

Rotate TEST FUNCTION switch to CAP SIM CAL

at.

Set CAP SIM

au.

Depress

(pF)100’s

pounds.

and 10’s thumbwheels to 2 and 3

and hold PRESS TO READ CAP

a test set

display

of 231

(pF) pushbutton

Release pushbutton.

aw.

Rotate TEST FUNCTION switch to IND AMP.

ax.

The indicator should indicate 600 f35

at.

Set CAP SIM

ba.

Depress and hold PRESS TO test set

display

of 252

while

adjusting

pounds.

ay. Rotate TEST FUNCTION switch to CAP SIM CAL

(pF) 100’s

respectively.

pF.

av.

a

(NORM SYS).

(NORM SYS).

and 10’s thumbwheels to 2 and 5 READ CAP

(pF) pushbutton

respectively. while

adjusting

pF.

bb. Release pushbutton. be. Rotate TEST FUNCTION switch to IND AMP.

bd. The indicator should indicate 900 +35

pounds.

be. Set test set ON/OFF switch to OFF.

Oct

31/0628-40-00

nl~

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

bf.

Place the external power switch and

battery switch

to the off

position.

Remove external power and disconnect

battery. pF values used for this test are off set from the values used in a normal calibration. After performing this Linearity check the system must be calibrated using the preferred or alternate system calibration procedures

NOTE: The

in this

bg.

chapter.

Disconnect test set ACFT connector from aircraft

bh. Disconnect test set IND connector from indicator

adapter cable

bi.

Disconnect

bj.

Connect aircraft

wiring plug

bk. Return aircraft to

wiring

or

or

adapter cable.

adapter cable.

and indicator if

applicable.

to indicator.

original configuration.

NOTE: Follow above

~al

from aircraft

wiring plug

procedures,

if necessary for

opposite

side of

airplane.

28-40-00

RBYtheO´•

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102 Indicator

Linearity

Check Values

DC 400 SETTING

INDICATOR READING

fTOLERANCE

189

0

210

300

35

231

600

35

252

900

35

273

1,200

FUEL CONTROL PANEL

FUEL PANEL

CONNECTOR

I

FUEL PROBE

I

~mNe BREAK CONNECTOR

1~0

FUEL PROBE

BULKHEAD CONNECTOR FUEL PROBE

FUEL PROBE

300´•2804

Tank Unit Locations

Figure

Oct

28-40-00

101

A21

RBy~heOn

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SYSTEM CALISRA TION The fuel

quantity system (Ref. Figure 102) may be calibrated with the fuel level in the fuel tanks at any level using procedure. However the preferred procedure is to calibrate the system with the tanks completely empty undrainable fuel only.

the alternate or

with

While

calibrating

the system with empty tanks is more reliable than the alternate procedure, the accuracy of the procedure (full tanks) can be appreciably enhanced if the empty-tanks value is known. It is recommended that when the empty capacitance value is determined, it should be recorded in the airframe log for future use in calibrating. alternate

NOTE:

Any

time

a

probe

is

changed,

a new

empty tank value will have

to be established.

The

preferred procedure (completely empty or undrainable fuel only) makes use of the actual empty-tank value in adjusting the zero indication. The alternate procedure (full tanks) applies a nominal empty-tank value to the system by the test set for the zero indication. Both is

a

procedures will be outlined in the following test: however, it must be remembered that the alternate procedure stop-gap procedure only and the system should be recalibrated using the preferred procedure at the earliest

convenience of the operator.

4 4

8

2

12-

QTY O

INDICATOR EYPTY SmlNG WITH TANKS DEFUELED THROUGH SUMP DRAINS.

FUEL 16

cg~tt

POINTER SET APPROXIMATELY ONE NEEDLE WIDM BELOW THE ZERO MARK.

14

O

System

Calibration

Figure

ant

Empty

102

28-40-00Page

109

RayNheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EMPTY TANKS CALIBRATION

(888888880 PROCEDURE)

switch is OFF, the fuel

a.

Ensure that the

battery

b.

Defuel

and drain sumps

c.

Locate the test set

d.

Ensure that the ON/OFF switch

e.

Gain accesstoindicator.

f.

Disconnect the indicator

g.

Connect the test set ACTT connector to the indicator

airplane

conveniently

wiring

in the

for

working

on

the test set is OFF.

adapter cables (8

Place the INSULATION/SYSTEM switch to SYSTEM.

j.

Set MAINTTOT-AUX/NAC switch to MANTTOT.

k.

Set the

i.

Place the

switch to the NO

n.

Set the CAP SIM

o.

Place the test set ON/OFF switch to ON.

p.

Depress

I’

(pF)

100’s and 10’s thumbwheels to

and hold PRESS TO READ CAP

only.)

and 9

(pF) pushbutton

respectively.

while

adjusting

CAP SIM

(pF) control

battery

and close circuit breakers.

Connect extemal power. Place the

battery

switch to the ON

position

and the external power ON.

slightly below zero, approximately one needle width. Refer to Figure acceptable, adjust El adjustment on the indicator to set pointer position.

The indicator should indicate

position

is not

u.

SettheTESTFUNCTION switchtoADDCAP.

v.

The indicator should read 1,300

w.

Set the TEST FUNCTION switch to CAP SIM CAL

x.

Set the

position

pounds,

If not,

adjust

F1

adjustment

on

Release AUX switch and

z.

This

repeat Steps

t. thru

w. as

completes CALIBRATION (DRY TANKS).

31/0628-40-00

102. If

the indicator to obtain correct

pointer

reading.

(NORM SYS).

airplanes fuel panel select switch to AUX and hold. The indicator should is not acceptable adjust E2 adjustment on the indicator.

y.

Oct

knob to obtain

of 93.1.

pushbutton.

Connect the s.

Modified test set TK2129m35

switch to 200.

display

Release

(NORM SYS).

position. (On Raytheon

Set the

q.

9, Chart 1, 28-00-00) if necessary,

fuel select switch to MAIN.

m.

LCD

is disconnected.

harness connector and connect the test set IND

wiring or

i.

pF

battery

harness connector from the indicator.

Rotate TEST FUNCTION selector to CAP SIM CAL

shD~ing

open, and

are

cockpit.

h.

airplane’s

circuit breakers

(Ref. 12-10-00).

connector to the indicator. Use the

I

quantity

necessary to

ensure

indicate 0

pounds.

accurate calibration.

If

pointer

RBYHICOII

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

aa.

Turn off external power switch. Turn the battery switch OFF. Turn the test set OFF. Disconnect the test set. Disconnect external power.

ab. Connect the

airplane’s

wire harness to the indicator and return the

FULL IN TANK CALIBRATION

PROCEDURE

(ALTERNATE

airplane

to the

original configuration.

ONLY)

(wet tanks) should only be used as a temporary measure when draining facilities are not available. airplane should be recalibrated using EMPTY TANKS CALIBRATION (PREFERRED PROCEDURE) at the first opportunity.

The Calibration

The

applies nominal empty tank capacitance value to the system by the test set for indicator capacitance value, equal to the combined value of the nominal empty tank and the reading. fuel in the tanks, is applied to system and the indicator is adjusted to indicate substituted fuel of equivalent quantity full indicator for reading. quantity

The Wet tanks calibration A second

zero

NOTE: Accuracies

airplanes

rivalling preferred calibration may

are

be obtained if measured

known and used instead of EMPTY values

(Ref.

Chart

dry capacitances for specific S/N 101). The ADD FOR FULL value 93.1

should be added to known values to obtain CAP SIM value for FULL.

conveniently for working

in the

cockpit.

a.

Locate the test set

b.

Ensure that the ON

c.

Ensure that the battery switch is OFF, the fuel quantity circuit breakers

d.

Gain

e.

Disconnect the indicator wire harness connector from the fuel

f.

Connect the test set ACFT connector to the indicator wire harness connector and connect the test set IND connector to the indicator. Use the adapter cables (8 or 9, Chart 1, 28-00-00) if necessary,

g.

access to

Connect the

OFF switch

the fuel

battery,

quantity

reset circuit

on

the test set is OFF. are

open, and the

battery

is disconnect.

indicator.

breakers,

indicator.

quantity

connect external power,

place battery switch to the ON position

and

the external power switch ON.

(NORM SYS).

h.

Rotate the TEST FUNCTION selector to CAP SIM CAL

i.

Set the test set INSULATION/SYSTEM switch to SYSTEM.

j.

Set MAINTTOT-AUXINAC switch to MAINTTOT.

k.

Set the 200

i.

Place the

m.

Place test set ON/OFF switch to ON.

n.

Set the CAP SIM

o.

shorting

switch to 200

switch to the NO

(pF)

(pF).

position. (On Raytheon Modified

100’s and 1 O’s thumbwheels to

digits

test set TK2129/935

to 1 and 6

only.)

respectively.

Depress and hold PRESS TO READ CAP (pF) pushbutton while adjusting CAP SIM (pF) control knob to obtain a

p.

(pF)/1,000 (pF)

LCD value of 169.1

pF (Ref.

Chart

101).

Release pushbutton.

28-40-00Page

111

I

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: Check the

log

book for

an

empty tank value and, if available,

use

that value in

place

of the values

given

in

Chart 101. q.

slightly below zero, approximately one needle width. Refer to Figure El adjustment on rear of indicator for pointer position. adjust acceptable,

The indicator should indicate

I’ I

RotatetheTESTFUNTION switchto INDAMP.

position

is not

s.

Rotate the test TEST FUNCTION switch to CAP SIM CAL

t.

Set 200

u.

Set CAP SIM

v.

(pF)/1,000 (pF)

Depress

(pF)

switch to 1,000

and hold PRESS TO READ CAP

pF (Ref.

w.

x.

I

Release

push

digits

to 2 and 5

respectively (Ref.

adjusting

while

Chart

the CAP SIM

101).

(pF)

control knob to

101).

button.

pointer position

y.

Rotate TEST FUNCTION switch to CAP SIM CAL

z.

Set 200

aa.

Set MAINTTOT

ac.

(NORMAL SYS).

(pF) pushbutton

Chart

The indicator should read 1,300 pounds. If indicator to obtain 1,300 pounds.

(pF)/1,000 (pF)

ab. Set CAP SIM

pointer

(pF)

100’s and 10’s thumbwheels to

obtain the LCD value of 253.9

102. If

switch to 200

is not

acceptable adjust

F/

adjustment

at the rear of

(NORM SYS).

(pF).

AUWNAC switch to AUWNAC.

(pF)

100’s and 10’s thumbwheels to

digits

to 0 and 5

respectively (Ref. Chart 101).

Depress and hold PRESS TO READ CAP (pF) pushbutton while adjusting the CAP SIM (pF) control knob pF (Ref. Chart 101).

to

obtain the LCD value 59.4

I

ad. Release

pushbutton

ae.

Rotate TEST FUNCTION switch to IND AMP.

af.

The indicator should read

of indicator to obtain ag.

Repeat steps

n

exactly 0 pounds. correct reading.

through

af

as

necessary to

NOTE: The indicator does not have tank

adjusts

the full

setting

a

If

pointer position

ensure

is not

acceptable adjust

Retum the

airplane

to the

aux

tanks.

PROBES BENCH TEST Ensure that the ON

b.

Ensure that the

battery switch

c.

Disconnectthe

battery

Oct

31/06Page

112

OFF switch

at rear

separate adjustment for Aux tank "FULL". The full adjustment for the main

for the main and the

original configuration.

a.

adjustment

accurate calibration.

ah. Set the test set ON/OFF switch to OFF and disconnect the test set. ai.

E 2

on

the test set is OFF.

is OFF and the fuel

28-40-00

quantity

circuit breakers

are

open.

RaytheMI

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Rotate TEST FUNCTION switch to

e.

Set INSULATION/SYSTEM switch to SYSTEM.

f.

Set MAINTTOT-AUWNAC switch to MAIN/TOT.

g.

Set 200

(pF)/1,000 (pF)

PROBE(S).

switch to 200

(pF).

NOTE: Tanks must be from the

completely empty or completely full for capacitance aircraft for empty capacitance checks if desired.

checks. Fuel

(5,

Chart 1,

28-00-00)

to test set

(5,

Chart 1,

28-00-00)

to

be removed

probes may

probes receptacle.

h.

Connect Seech

i.

Connect Seech probe

j.

pin ground lead of probe adapter to ground clip pigtail of probe adapter. Attach ground clip to grounding spot on the probe. For Raytheon Modified test set (TK2129/935) place shorting switch to YES position.

k.

SettestON/OFFswitch toON.

I.

Depress

probe adapter

P/N 101-00814

adapter P/N

101-00814

matching

color of

probe lead

wire

pins.

For DC-400 Connect socket

(pF) pushbutton for probe capacitance display. Probe capacitance value must specified, by part number, in Chart 103. If value is not in tolerance the probe must be

PRESS TO READ CAP

be within tolerances

as

replaced. m.

Set ON/OFF switch to OFF.

n.

Rotate TEST FUNCTION switch to IND AMP.

o.

Set INSULATION/SYSTEM switch to INSULATION.

NOTE: p.

Any fuel

level is

acceptable for the

insulation checks.

FOR DC400 Disconnect pin socket ground lead of probe adapter from ground clip pigtail. (Disconnect small ground clip). For Raytheon Modified test set (TK2129/935) place shorting switch to NO position.

black wire from q.

Rotate INS TEST POINT switch to LO-Z GND.

NOTE:

r.

the insulation test, it may take some time for the indication to completely stabilize. If the indication does not read below 50 nS in one minute, the reading is unacceptable.

During

Set ON/OFF switch to ON. Allow sufficient time for the test

LDC s.

display

Rotate INS TEST POINT switch to each stabilize in each

reading

stabilize

(no

remaining position. Allowing

more

than

one

minute).

The

of between 1,500 and

an

specifications.

insure test failure is not due to human t.

Set ON/OFF switch to OFF.

u.

Disconnect

probe adapter from probe.

v.

Disconnect

probe adapter from

If results

are

display to position, which will show a

sufficient time for test set

shall be less than 50 nS except in SIG/RTN overrange display of (1

position, readings

NOTE: Conductance must be within

A21

display to

shall be less than 50 nS.

slightly

outside limits, repeat

procedure

to

error.

test set.

28-40-00

Oct

31/06Page

113

I

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

w.

This

completes the Probe

x.

Return the

airplane

to the

Bench Test.

original configuration.

Chart 103 Fuel Probe

Capacitance

Values

CAPACITANCE PROBE LOCATION

Leading Edge

Inbd

PROBE NUMBER

MIN

NOM

MAX

24.7

27.5

30.3

40.3

44.8

49.3

21.2

23.3

25.7

32.1

35.7

39.3

15.9

17.7

19.5

24.5

27.2

29.9

52.7

58.6

64.5

74.1

82.3

90.5

100-380006-149, -151 or-167

26.2

29.1

32.0

42.6

47.3

52.0

100-380006 -119, -169

27.3

30.3

33.3

44.9

49.9

54.9

100-380006-93, -121 or-179

20.1

22.2

24.5

31.1

34.6

38.1

100-380006-95, -123

18.0

19.9

22.0

26.5

29.4

32.3

38.1

42.1

46.5

57.6

64.0

70.4

100-380006-139, -143

100-380006-141, -145

Nacelle

100-380006-77, -113

Intergral

I

Inbd

Outbd

Oct

through

-175

or

or

-177 -173

or

or

-171

or

or

Intergral (Total)* *Measured

(pF)

MAX

Inboard Aft

Intergral

FULL

NOM

100-380006-81, -115

Aux Outbd

CAPACITANCE

(pF)

MIN

Leading Edge Outbd

Aux Inbd

EMPTY

-197

-181

bulkhead harness connector

31/0628-40-00

A21

NaVNteon

AiKraft

company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 104

Conductance to

Megohm

Conversion EQUIVALENT MEGOHM

DISPLAY READING

0.5

1

1000

1.

500

2.

200

5.

100

10.

050

20.

020

50.

010

100.

005

200.

002

500.

001

1,000.

000

>1,000. NOTE

Display readings are presented in nS (nano Siemens). Equivalent megohms display reading. Example: 1,000/50 20 Megohms.

are

derived

by dividing 1,000 by test

set

WATER TEST

Every airplane experiencing moisture problems should have a water test performed on system wiring and probes. Fuel does not have to be drained from the tanks for this test. a.

the fuel

quantity

indication

Record the resistance values of the system between any two wires and between any wire and airframe

ground

tall combinations). probe

and its associated

b.

Spray

c.

Check the resistance values

d.

Alternately

e.

Water

water

on one

do

Steps

b. and

again

c.

wiring.

of all different combinations per

until all

probes

and

wiring

Step

a.

have been checked with water.

the resistance to decrease from wire to wire and from wires to ground. Find specific causes for change by alternately applying shop air and water spray to pin-point cuts in the wiring or the area water affects the system. Use appropriate material to make an environmental seal.

causes

resistance where

A21

28-40-00

Oct

31/06Page

115

RayWleon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INDICATING

MAINTENANCE PRACTICES

NACELLE FUEL QUANTITY PROBE REMOVAL NOTE: Any time

a

probe

is

calibration

preferred

replaced with a new or procedures (dry tanks).

rebuilt part, the system should be recalibrated per system

(Ref. Figure 201) from the top of the

Remove the

b.

Using the pin extractor tool (10, Chart 1, 28-00-00) remove the fuel quantity probe wires quantity terminal board. (Label each wire before removing from terminal board.)

c.

Unsafety

d.

Lift fuel

access cover

and

remove e

6 bolts

quantity probe straight

CAUTION: Handle the fuel

securing

the

probe

in

nacelle to

to the fuel

a.

gain

access

quantity probe.

from the nacelle fuel

place.

up until free of support at the bottom of fuel cell and

quantity probe carefully, for damage as a measuring device.

to the surface of the

remove

probe

from the cell.

probe tubes will destroy the

accuracy of the probe

NACELLE FUEL QUANTITY PROBE INSTALLA TION NOTE: Any time

preferred

a

probe

is

calibration

replaced with a new or rebuilt part, the system should be recalibrated per system procedures (dry tanks).

NOTE: It is recommended that the fuel system be drained to facilitate installation of the nacelle capacitance probe. This will enable

opening

to

one

guide

the lower end of the

probe tubes into the support by working through the

for the fuel strainer.

a.

Remove the

b.

Position two spacers between three gaskets under the flange of the probe. With one man lowering the probe tubes into the opening on top of the nacelle, have another man guide the lower end of the probe into the support

standby

boost pump

at the bottom of the cell

tubes of the probe

are

(Ref. 28-20-00).

by reaching through

properly aligned

the

opening

with the support

for the boost pump. Rotate the spacers until the

C~UTION: Handle the fuel quantity probe carefully, damage accuracy of the c.

Install the bolts

Torque

probe

securing

as a

to the surface of the

probe

tubes will

destroy

the

measuring device.

probe in place. New washers (P/N 800-515-1/4) must inch-pounds, then lock them in place with safety wire.

the

the bolts to 30 +5

probe

(Ref. Figure 201).

NOTE: Torque the retaining bolts in the sequence

designated by

letters B

through

F in

be installed with the bolts.

Figure

2 of

Chapter

28-10-

00 to ensure proper installation.

d.

Using

the

pin inserter tool (10, Chart 1, 28-00-00) install the fuel quantity probe applicable 8300 Wiring Diagram Manual.

wires in the nacelle fuel

quantity

terminal board. Refer to e.

Install the

access

f.

Install the

standby

A21

coveroverthe boost pump

probe.

(Ref. 28-20-00).

28-40-00

Oct

31/06Page

201

I

RayWleon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUEL QUANTITY PROBE INSPECTION NOTE: Because the nacelle tank is the lowest

contamination will

biological

usually begin (black

contamination

point

there. Therefore, if the nacelle tank is clean and there is no evidence of sludge) in the sump of the nacelle fuel tank, it may be assumed the

remainder of the fuel system is clear of

biological

Remove the nacelle fuel

b.

Inspect

c.

Inspect the bottom of the nacelle fuel tank for debris

d.

If

no

probe for biological contamination (black film

or

sludge)

or

and evidence of

corrosion.

biological

evidence of

nacelle fuel e.

quantity probe.

contamination.

Refer to NACELLE FUEL QUANTITY PROBE REMOVAL.

a.

the

system debris will collect there and biological

in the fuel

biological contamination (black sludge) in the sump of the quantity probe. Refer to NACELLE FUEL QUANTITY PROBE

contamination.

nacelle fuel tank is found, install the INSTALLATION.

If evidence of

cleaned

as

biological contamination is noted, then all the fuel probes and tanks will have to be inspected required. The fuel probes should be cleaned with a clean cloth and isopropyl alcohol.

f.

Remove any debris from the nacelle tank sump.

g.

Install the fuel

quantity probes

and return the

airplane

and

to service.

FUEL QUANTITY PROBE REMOVAL FOR THE INBOARD LEADING EDGE AND INBOARD AFT FUEL CELLS

I

NOTE:

a.

b.

Any time preferred

Remove the

a

probe

is

calibration

replaced with a new or rebuilt part, the system should be recalibrated per system procedures (dry tanks). the fuel

access cover over

quantity probe (Ref. Figure 201).

Using the pin extractor tool (1 O, Chart 1 28-00-00) remove the fuel quantity probe wires from the probes terminal (Label each wire before removing from the terminal board.)

board. c.

Unsafety

and

remove

the 5

CAUTION: Handle the fuel accuracy of the

mounting

screws

and

remove

the fuel

quantity probe carefully, for damage as a measuring device.

quantity probe

from the fuel cell.

to the surface of the

probe tubes will destroy

the

probe

FUEL QUANTITY PROBE INSTALLATION FOR THE INBOARD LEADING EDGE AND INBOARD AFT FUEL CELLS

I

NOTE:

a.

Any time preferred

a

probe

is

calibration

Insert the fuel

quantity probe

CAUTION: Handle the fuel

accuracy of the b.

Secure the fuel

safety

replaced with a new or rebuilt part, the system should be recalibrated per system procedures (dry tanks).

31/06Page

202

opening

in the fuel cell

(Ref. Figure 201).

quantity probe carefully, for damage probe as a measuring device.

quantity probe

in

place

with the

attaching

to the surface of the

bolts.

Torque the bolts

probe tubes will destroy the

to 25 +5

wire them.

NOTE: Install the free end of the

Oct

into its

bonding jumper

28-40-00

under

one

of the

probe mounting

bolts.

inch-pounds,

then

RaytheMI

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

Using pin inserter tool (10, Chart 1, 28-00-00) install the fuel quantity probe wires Refer to applicable B300 Wiring Diagram Manual.

d.

Install the

cover over

the fuel

quantity probe

and

secure

it in

Any time preferred

a

probe

is

calibration

probes terminal

(WET WING)

FUEL CELL

replaced with a new or rebuilt part, the system should be recalibrated per system procedures (dry tanks).

a.

Drainthe mainfuel system.

b.

Remove the inboard and

c.

Remove the

d.

Working through the access opening, disconnect the aircraft electrical wiring from the R, S, and the top of the fuel quantity probe. Disengage the leads from the strain relief clip on the probe.

access

CAUTION: Take e.

largest

of the 6

access

panels for the integral fuel cell from

panel adjacent to the fuel quantity probe from the underside of

precautions

to avoid

damaging

the

destroy

remove

the

wing (Ref. Figure 201). L terminals

near

quantity probe carefully, for damage to the surface probe as a measuring device.

of the surface of the

probe

fuel

tubes will

the accuracy of the

(WET WING)

FUEL CELL

Any time a probe is replaced with a new or rebuilt part, the system should be recalibrated preferred calibration procedures (dry tanks).

Insert the top of the fuel

a.

the

wing.

retaining clip from the top of the

FUEL QUANTIN PROBES INSTALLA TION FOR THE INTEGRAL NOTE:

the underside of the

shielding around the wiring.

Remove the retaining clamp from the bottom and unsafety and capacitance probe, then remove the probe from the fuel cell.

CA UTION: Handle the fuel

board.

place with the attaching bolts.

FUEL QUANTIN PROBES REMOVAL FOR THE INTEGRAL NOTE:

into the

quantity probe into the retaining clip and safety wire quantity probe in place (Ref. Figure 201).

the

clip.

Install the

per

clamp

system

that

anchors the bottom of the fuel

CAUTION: Handle the fuel accuracy of the b.

quantity probe carefully, for damage probe as a measuring device.

to the surface of the

Connect the electrical leads to the R, S, and L terminals in accordance with the are secured under the strain relief clip of the probe.

probe

tubes will

destroy

wiring diagram. Make

sure

the

that

the R, S, and L cables CAUTION: Take c.

~al

Install the

precautions

access covers

to avoid

and

damaging

gaskets

on

the

shielding around the wiring.

the underside of the

wing.

28-40-00Page

203

I

Raytheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUEL QUANTITY LIQUID LEVEL SENSOR REMOVAL

I

a.

Remove the

b.

Disconnect the electrical connector from the top of the

c.

Disconnect and

d.

Unsafety

and

e.

Carefully

lift the

access cover

remove

remove

from the top of the nacelle to

plumbing

lines and

the bolts which

sensor

straight

fittings

secure

the

as

gain access to the fuel quantity sensor (Ref. Figure

201

sensor.

necessary.

sensor

in

place.

up and out of the fuel cell.

FUEL QUANTITY LIQUID LEVEL SENSOR INSTALLATION position in the nacelle fuel cell (Ref. Figure 201).

a.

Carefully

b.

Install the

c.

Connect the electrical connector to the

d.

Install the

Oct

31/06Page

204

insert the fuel

sensor

attaching bolts

plumbing

into

to secure the sensor in

lines and

fittings

28-40-00

place. Torque the bolts

to 25-30

inch-pounds

sensor.

in the top of the nacelle. Install the nacelle

access cover.

and

safety

wire.

Raylheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

C

A,~

B ’P

o

r

I

C

c

C

i

i

ad

d

F

4

’5

a,

DETAIL

DETAIL

B

A q-

DETAIL

DETAIL DETAIL

E

DETAIL

D

F

~-]ad

C 35azs~-ze

Fuel

A21

Quantity Probe Installation Figure 201

28-40-00

Oct

31/06Page

205

C H A PT E R

ICE AND RAIN

PROTECTION

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 30

ICE AND RAIN PROTECTION

TABLE OF CONTENTS

SUBJECT

PAGE 30-00-00

Iceand Rain Protection-

SpecialToolsand

Description

and

Operation

................._

................._

Recommended Materials.

.......1

.............1

30-10-00

Airfoil Surface Deicet-

Descriptionand Operation System Surface Deicer Indicating System Airfoil Surface Deicer Troubleshooting

.........1

Surface Deicer

Airfoil Surface Deicer Surface Deicer Boot

...1 ...............101

Maintenance Practices

...........201

Cleaning.

...201

Surface Deicer Boot Removal. Surface Deicer Boot Installation Test Control

Strips (FL-1

...201

(FL-1

thru

FL-442; FM-I and After)

thru FL-442; FM-1 and

........._____

........._.202

After)

...206

Adhesion Test....; Boot

..........207

Fastboot

........._207

Acceptability Preparation and Installation Procedures (FL-443 and After) Sealing of Deicer Boot Edges. FASTbootAir Pressure Test (FL-443 and After). Stall Strip Installation. Surface Deicer Boot Age Master and Icex Application Surface DeicerBoot Repairs. Resurfacing Deicer Boots Scuff Damage Tube Area Damage. Loose Surface Ply in Non-lnflatableArea. Loose Surface Ply inTubeArea. Fabric Back Ply Damage During Removal.

...209 ........211

.213 ....213 ....213

.............215 .216

.........216

Surface Deice Pressure SensorSwitch Removal.

.......216

Surface Deicer Pressure SensorSwitch Installation.

.....216

Surface

DeicerOperational Check BleedAir Pressure Regulator Relief Valve Adjustment Vacuum RegulatorValve Adjustment

.........____.

........._____

.216

...217 .217

.........___

DeicerBoot Final Finish

........218

30-20-00

Description andOperation Lip Separation Anti-ice System.

Airlntakes-

..................1

Air IntakeAnti-lce Inertial Air Intakes Anti-ice

................._

................._

Maintenance Practices

................._

Lip Crack Repair Engine InertialAnti-lcing System Servicing Rigging the Engine Inertial Anti-icing System.

................._

................._

........._._..._

n25

................._

................._

................._

.1

.201

................._

.......201

............201

..´•........202

30-CONTENTSPagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 30

ICE AND RAIN PROTECTION

TABLE OF CONTENTS

(CONTINUED) PAGE

SUBJECT

Bypass

Duct

Repair. 30-21-00

Brake Deice

System

Description and Operation

1

30-40-00

Windows andWindshields-

Descriptionand Operation

1

Windshield Anti-ice Windshield Window

Wipers Defog System.

Windowsand Windshield -Maintenance Practices

201

Wiper Motor Removal Windshield Wiper Motor Installation. Windshield WiperConverter Removal. Windshield

Windshield Windshield

201 201 201

Installation

WiperConverter WiperAdjustment Heating Elements

202 202

Resistance Check

203

WindshieldAnti-lce Controller Functional Check.

203

Windshield Window

Defog

Air Filter Removal

(FL-1

thru FL-318, FM-I thru FM-10,

with Kit No. 130-9700-1 Installed; FL-319 and After, FM-11 and Window

Defog

Air Filter Installation

(FL-1

After).

204

thru FL-318, PM-1 thru FM-IO,

with Kit No. 130-9700-1 Installed; FL-319 and After, FM-11 and

After).

204

30-60-00

Propeller Electric Deicers- Description and Operation Propeller Electric Deicer Troubleshooting Propellers Electric Deicers- Maintenance Practices PropellerDeicerBoot Removal Propeller Deicer Boot Installation. Propeller Deicer Brush Replacement.

1 101

201 201 201 204

Timer Check. Heat Test

Continuity

Test

DeicerResistance Check.

Assembly Resistance Slip Ring Alignment Slip Ring Repair. Propeller Deicer System Inspection. Modular Brush

Page

207

Check.

230;CONTENTS

207

208

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

list of Effective CH-SE-SU

PAGE

DATE

30-LOEP

1

Feb 1/09

30-CONTENTS

1 and 2

Feb 1/09

30-00-00

1 thru 5

Feb 1/09

30-10-00

1 thru 3

Nov 1/07

101 thru 103

Nov 1/07

201 thru 218

Feb 1/09

30-20-00

30-21-00

30-40-00

30-60-00

A25

1

Novl/07

201 thru 204

Nov 1/07

1

Novl/07

1 and 2

201 thru 207

May 1/08 May 1/08

1 and 2

Nov 1/07

101 thru 106

Nov 1/07

201 thru 210

Nov 1/07

Pages

30-LOEP

Feb

1/09Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

ICE AND RAIN PROTECTION This

airplane

is

equipped

with

variety

DESCRIPTION AND OPERATION of ice and rain

protection systems that

be utilized

during operation under heating provide adequate protection against the formation of ice while air from the cabin heating systems prevents fogging to ensure visibility during operation under icing conditions. Heavy duty windshield wipers for both the pilot and copilot provide further visibility during rainy flight conditions. Pneumatic deicer boots break off ice which has collected on the leading edge of the wings and horizontal stabilizer. Regulated bleed air pressure and vacuum are cycled to the pneumatic boots for the inflation-deflation cycle. The selector switch that controls the system permits automatic single cycle operation or manual operation. Wing ice lights aid the pilot in detecting the formation of ice on the wing leading edge. The lights are installed on the outboard side of each engine nacelle and are controlled by a 5-amp circuit breaker switch located on the pilot’s inboard subpanel. Ice protection for the engine is provided by an inertial separation system utilizing a dual motor actuator. Should the primary motor on the electrical actuator fail, a standby motor can be engaged to actuate the system. The leading edge lip of each engine air inlet is continuously anti-iced by hot exhaust gases. The propellers are protected against icing by electrothermal boots that automatically cycle upon actuation. a

inclement weather conditions. Electrical

Engine bleed air is

routed

can

elements imbedded in the windshield

line and hose

through

solenoid-operated shutoff valve to a distributor manifold that deicing. cockpit side window defrosting is provided by engine bleed air anytime one or both engines are running. A heating element in each pitot mast prevents the pitot opening from becoming clogged with ice. The heating elements are connected into the airplane electrical system through two 5-ampere circuit breakers. Heating elements in the vane and mounting plate provide ice protection for the stall warning lift transducer. Power for the stall warning transducer heat is taken from a 15-amp circuit breaker switch on the left inboard subpanel. A heated vent on the underside of each wing ensures continued fuel system venting should the recessed vents become obstructed with ice. Fuel vent heater power is provided through two switches on the left inboard subpanel.

by

directs the hot air to the brakes for

a

Cabin window and

SPECIAL TOOLS AND RECOMMENDED MA TERIALS

special tools and recommended materials listed in Charts 1 and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance with the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO The

THE REQUIREMENTS OF THE SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHARTS.

Only

the basic number of each

the latest revision. It is the

specification

is listed. No

of the technician

n25

attempt has been made

to

update

the

listing

to

mechanic to determine the current revision of the

responsibility applicable specification prior to usage of the product listed. This product to be used. or

can

be done

by contacting

the

30-00-00

supplier

of the

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 1

Special Tools and Equipment TOOL NAME

1.

PART NO.

SUPPLIER

Emerson Climate

XW20509

Wrench

(Formerly

USE

Technologies Corp.)

Alco Controls

windshield

Adjust arm

wiper

tension

P.O. Box 411400 St. Louis, MO 63141-1400 2.

SprayGun

Binks No. 7 with

Binks ITW Industrial

No. 63 PB head

195 Internationale Boulevard

JGA 75X

3.

RubberHand Roller,

74-451-74

Finishing

Glendale

Heights,

Goodrich

Corporation

2730 West

Tyvola

cement for deicer

boot installation

IL 60139

Apply

Four Coliseum Centre

Two Inch Wide

Apply

manual pressure

for deicer boot

Road

installation.

Charlotte, NC 28217-4578

Chart 2 Recommended Materials

1.

Product

Specification

Material

Cleaning Solvent

MIL-PRF-680

Type

I

Stoddard Solvent

Supplier (Mineral

Obtained

Locally.

Spirit) 2.

Solvent

Methyl Propyl (MPK)

3.

AbrasivePad

Scotch-Brite MMM-A-121

4.

Adhesive

5.

Superseded

6.

Conductive

Scotch-Grip

Item. Use any SAE-AMS-S-8802 material

Ketone

3M 1300L

(Ref. 25.)

or

A56BR-1

Edge

Company

3M Center

St. Paul, MN 55144-1000 PR1425

(Ref. 26.) Goodrich

as

replacement.

Corporation

Four Coliseum Centre

Sealer

2730 West

Tyvola Road Charlotte, NC 28217-4578

7.

Solvent

8.

Coating

9.

Solvent

A-A-59107

Toluol

(Toluene)

Icex

ASTM-D4080

Trichloroethane

Obtained

Locally.

Goodrich

Corporation

Four Coliseum Centre 2730 West

Tyvola

Road

Charlotte, NC 28217-4578

Page

beF2

1/09

30-00-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 2

Recommended Materials

Product

Specification

Material

I

10. Adhesive,

(Continued)

I

Supplier

Bostik 10088 with

USM

Bostik 1009A

Rubber-to-

A

OR

Rubber; Rubber-

Combi-Bond

to-Metal

Industries Inc.

Coldbonding

Bostik Division

Adhesive with Combi-

211 Boston Street

Bond Hardener

MIL-DTL-81706 per MILDTL-5541

11. Chemical

Conversion

Coating

12.

Corporation subsidiary of Emhart

Middleton, MA 01949-2128 Henkel Corporation Aerospace- Surface

Alodine 1200

Treatments

for

Stephenson Highway Heights, MI 48071

Aluminum and

32100

Aluminum

Madison

Alloys MIL-PRF-23827

Grease, Aircraft and Instrument,

Royco Type 1

1

27

Anderol Inc. 215

Merry

Lane

Gear and Actuator

P.O. Box 518

Screw

East Hanover, NJ 07936

Aeroshell Grease 7

NOTE

Type Do not mix

Type together

Type

II

I and

I

Shell Oil

I

grease

Company

1 Shell Plaza

II

I

P.O. Box 2463

Houston, TX 77001

Aeroshell 33

Typel Mobilgrease Type 1

Exxon Mobil

27

Fairfax, Castrol

Type

Corporation

3225 Gallows Road

Aeroplex

VA 22037

Air BP Lubricants Division

Al

I

BP Products North America

NJ 07054-4406

Parsippany, CAUTION Take

precautions when using MIL-PRF-23827, painted surfaces.

Mil-PRF-8 1322 and

engine oil.

These lubricants contain chemicals

harmful to

13. Primer

Coatings:

Epoxy, High-Solids

MIL-PRF-23377

Type

Akzo Noble

10P8-11

I Class I

East Water Street

Waukegan, 14. Urethane Paint

Aerospace

Coatings

CA 880/F17038

Gloss Black Desothane

IL 60085

PRC Desoto 5430 San Fernando Rd

Glendale, CA 15. Solvent

16. Solvent

Propeller Slip Ring Cleaning

ASTM D-329

Acetone

CRC-2-26

Obtained

91209

Locally.

CRC Industries Inc. 885 Louis Drive

Warminster, PA 18974

A25

30-00-00

Feb

1/09Page

3

Corporation

Hawker Beechcraft

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 2

(Continued)

Recommended Materials

17. Protective

Product

Specification

Material

Age

Coating

Master No. 1

Supplier Goodrich

Corporation

Four Coliseum Centre

Charlotte, NC 28217-4578

18. Solvent, Cleaner

TT-I-735

Isopropyl

19. Weld

AWS A5.9 Class ER347

Type

Rod,

Tyvola Road

2730 West

A-A-52408

Alcohol

347

Obtained

Locally.

Obtained

Locally.

Stainless Steel 20.

Compound

Big Three Industries Tempil Division

Anti-Heat

Heat

Sink

Inc.

2901 Hamilton Boulevard

South Plainfield, NJ 07080 21.

White Star

Aerodynamic

Fibre Glass-Evercoat

Smoother

Company 6600 Cornell Road

Cincinnati, OH 45242 22. Conductive

A56BR-1

Edge

Sealer

(Part

Goodrich

74-451-11)

Part No. 74-451-207

23. Primer, FASTboot 24.Primer

No.

I

I Bostik 1007M

Corporation

Four Coliseum Centre 2730 West

Tyvola Road

Charlotte, NC 28217-4578 Bostik Division 211 Boston Street

Middleton, MA 01949-2128

25.’Edge Filler

SAE-AMS-S-8802

PR1440A-1/2, or PR1440A-2, or PR1440B-1/2, or PR1440B-2, or

PRC-Desoto International Inc. P.O. Box 1800 5454 San Fernando Road

Glendale, CA 91209

PR1440B-4

AC-236A-1/2, or AC-236A-2, or AC-236B-1/2, or AC-236B-2, or

Advanced

Chemistry

Technology

Inc.

7341 Anaconda Avenue

Garden Grove, CA 92841

AC-236B-4

CS-3204A-1/2,

or

CS-3204A-2, or CS-3204B-1/2, or CS-3204B-2

Flamemaster

P.O. Box 1458 11120 Sherman

Sun 26.

*Edge Filler

PR1425B-1/2, PR1425B-2

Corporation

I ChemSeal Division

or

Valley,

Way

CA 91352

PRC-Desoto International Inc.

P.O. Box 1800 5454 San Fernando Road

Glendale, CA 91209

Page

beF4

1/09

30-00-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 2

Recommended Materials

27. Solvent

TT-N-95

28. White Cloth

CCC-C-440

Type

II

Type

II

Naphtha, Aliphatic

Obtained

Locally.

Cheese Cloth. Bleached

Obtained

Locally.

White

Class II 29.

Supplier

Product

Specification

Material

(Continued)

Masking

Tape

3M

200

Company

3M Center

St. Paul, MN 55144-1000 30. Surface

Shinemaster

Cleaner,

Shinemaster

31. Wax, Deicer Boot

32. Cold

Prep

Goodrich

Corporation

Four Coliseum Centre

Deicer Bool

Combi-Bond

combi-bond

Bonding

2730 West

Tyvola Road

Charlotte, NC 28217-4578

Richwood Industries Inc.

Adhesive/

P.O. Box 1298

Hardener

Huntington WV 25714

"25. and 26. PRODUCT identification: The suffix dash number stands for maximum allowable application time (or hour, "-2" for up to 2 hours and "-4" for up to 4 hours. The alphabet preceding assembly time), i.e. "-1/2" for up to the suffix dash number stands for Class, i.e. "A" is Class A (application method by brush) and "B" is Class B

’/2

(application

n25

method

by

extrusion gun

or

spatula).

30-00-00

Feb

1/09Page

5

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRFOIL SURFACE DEICER

DESCRIPTION AND OPERATION

SURFACE DEICER SYSTEM system is operated with pressure obtained by bleeding air from the engine compressors. This air is routed through a regulator valve that is set to maintain the pressure required to inflate the deicer boots on the leading edge of each wing and the horizontal stabilizer. To assure operation of the system should one engine fail, a check valve is incorporated into the bleed air line from each engine to prevent the escape of air pressure into the chamber of the inoperative compressor. The bleed air from the engine is also routed through an ejector that employs the venturi effect to produce vacuum for deflation of the deicer boots and operation of instruments. The inflation and deflation phases of operation are controlled by means of a distributor valve. The deicer system is actuated by a three-way toggle switch on the left subpanel. This switch is spring-loaded to return to the OFF position from either the MAN UAL or the SINGLE position. When the switch is pushed to the SINGLE position, one complete cycle of deicer operation automatically follows as the distributor valve opens to inflate the deicer boots. After an inflation period of approximately 6 seconds for the wings and 4 seconds for the horizontal stabilizer, a timer relay switches the distributor valve to the OFF or VACUUM position for deflation of the deicer boots. When the switch is pushed to the MANUAL position, all the boots will inflate and will continue to hold in the inflated position as long as the switch is held in position. Upon release of the switch, the distributor valve returns to the OFF position and the deicer boots remain deflated until the switch is actuated again (Ref. Figure 1). The deicer and

vacuum

I

I

SURFACE DEICER INDICA TING SYSTEM The surface deicer

indicating system is comprised of three pressure sensor switches, two relays and necessary wiring which interface with the central caution/advisory system and the annunciator panel. 28 vdc for the surface deicer indicating system is supplied by the triple fed bus and SURF DEICE circuit breaker located on the circuit breaker panel, right cockpit side panel.

electrical

wing pressure sensor switches are located just outboard of the left and right engine nacelles and connect to the deicer boot pressure lines with tubing. The left wing pressure sensor switch is mounted with a clamp to a bracket on the strobe power supply mounting bracket. The right wing pressure sensor switch is mounted with a clamp to a

The

(tail) pressure sensor switch is mounted with a clamp right horizontal stabilizer deicer boots on the centerline. All three pressure sensor switches 0.5 psi. When the surface deicer boots receive pneumatic open when the deice system pressure exceeds 14.5 pressure for inflation, the wing pressure sensor switches actuate and complete electrical circuits to energize the two relays. The energized relays complete the electrical circuit to the central caution/advisory system and illuminate the WING DEICE annunciator (green) light. If either one or both of the pressure switches do not actuate, a wing deice fault is probable and the WING DEICE annunciator will not be illuminated. The WING DEICE annunciator will stay illuminated until both pressure switches actuate to the normally closed position, which occurs when the deice system pressure drops below 8 psig at each outboard wing deice boot. Suction will occur after the 6 second pressurization action and constitutes the end of the deice cycle. If both switches do not actuate to the normally closed position the WING DEICE annunciator light will remain illuminated indicating the end of the deice cycle has not been reached and the deice boots have not pulled down properly which may impair ice shedding at the next deicing attempt. bracket

on

the intercostal web. The horizontal stabilizer

between the left and

A2,

30-~ 0-00Page

1

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

The horizontal stabilizer pressure sensor switch, when actuated, completes electrical circuitry directly to the central annunciator panel to illuminate the TAIL DEICE annunciator green light. The horizontal stabilizer pressure switch

0.5 psig at the tee to each deice boot. When the system pressure exceeds 14.5 will illuminate. If the pressure switch doesn’t the annunciator switch actuates, DEICE) light (TAIL green pressure actuate, a horizontal stabilizer fault is probable and the TAIL DEICE annunciator will not be illuminated. The TAIL

will actuate when the deice

I

DEICE annunciator will stay illuminated until the pressure switch actuates to the normally closed position, which will when the deice system pressure drops below 8 psig at the tee leading to the horizontal stabilizer deice boots.

occur

pressurization action and constitutes the end of the deice cycle. If the pressure normally closed position the TAIL DEICE annunciator light will remain illuminated of end the deice the indicating cycle has not been reached and the deice boots have not pulled down properly which the next deiceing attempt. at ice shedding may impair

Suction will

occur

after the 4 second

switch doesn’t actuate to the

Page

30,~ 0,00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

rPNEUMATIC GAGE I

VACUUM REGULATOR VALVE

FWD

1~

F\REWACL,

I PUL--( i: I

SHUTOFF DEICE BOOT

PRESSURE BULKHEAD

VALVE

.FIREWALL

DEICE BOOT

Il i! Il

II ;I ;I

DEICE BOOT

In ,BLEEDAIR CLOS’ SHUTOFF I ii VALVE

DEICE BOOT

MAIN SPAR

IREAR SPAR-I--

DOOR SEAL

AFT PRESSURE

BULKHEAD

PRESSURE VACUUM

1

PRESSURE OR VACUUM

DEICE BOOTS

BLEED AIR PRESSURE

TO WINDOW

REGULATOR

-e

DEFROST

DOOR SEAL

TO VACUUM

I

VALVE

VACUUM LINE

II

DEICE

REGULATOR

DISTRIBUTOR TO DOOR

VALVE

SEAL

TO PNEUMATIC GAGE EJECTOR

HYD POWER PACK PRESSURE PORT

CHECK VALVE

DEICE LINE BLEED AIR

~tnr’

LINE BLEED AIR LINE

FLIGHT METER SWITCH PORT

BLEED AIR LINE

BREAKAGE/

WARNING SYSTEM

BLEEDAIR PRESSURE REGULATOR LINE RUDDER BOOST PRESSURE PORT DEICE

oETnli~

6300-351-124

A

Surface Deicer

Figure

A23

1

30-10-00

Page 3 Nov 1107

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

AIRFOIL SURFACE DEICER

TROUBLESHOOTING

Chart 101 Surface Deicer

Troubleshooting

Deicer Boots Fails To Inflate

STEP 1

Is there

adequate

System

Properly

air pressure to inflate boots?

YES

NO

Proceed to STEP 2

Check pressure regulator valve for proper adjustment (Ref. BLEED AIR PRESSURE REGULATOR REL1EF VALVE STEP 2

ADJUSTMENT, 30-10-00).

Are the pressure lines unrestricted?

YES

NO Check for restrictions in lines

Proceed to STEP 3

to the deicer

Clear lines obstructed.

boot(s) affected. STEP 3

common

Are the pressure lines free of leaks?

YES

NO Check for leaks in lines

common

to the deicer

Proceed to STEP 4

boot(s)

affected. STEP 4

Does the distributor valve function

properly? YES

NO Check for proper opening and closing of the distributor valve. Replace distributor valve.

Chart 102

Surface Deicer

Troubleshooting

Deicer Boots Fails To STEP 1

Do deicer boots go

through complete cycle

System

Cycle

when SINGLE switch is

momentarily actuated? YES

NO

immediately spring loaded switch is released, replace delay printed circuit board assembly. the

STEP 2

Do deicer boots have

an

Proceed to STEP 2

deflate when

If deicer boots inflate OK, but

inflation

period

of

the time

approximately 6

seconds

(wing),

and 4 seconds

(horizontal

stabilizer)? YES

NO If inflation times

replace

A23

are more or

the time

less than the

delay printed

circuit

required time, board assembly.

30-~ 0-00

Page

voN101

1/07

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 103

Troubleshooting

Surface Deicer

Deicer Boots Fails To Deflate STEP 1

Are

vacuum

regulator

Completely

filter and/or lines unobstructed?

YES

NO Are

vacuum

lines

YES

STEP 2

vacuum

or

clear the

Is

vacuum

Proceed to STEP 2

leaking?

NO

Replace

filter andl

vacuum

I Repair or replace

as

required.

lines.

regulator functioning

or

adjusted properly? YES

NO

Clean, adjust

or

System

replace

the

vacuum

regulator (Ref.

Proceed to STEP 3

VACUUM REGULATOR VALVE ADJUSTMENT. 30-

70-00). STEP 3

Is pressure

regulator

valve

adjusted properly? YES

NO valve could affect

of the pressure

regulator regulator adjustment. Adjust or replace pressure regulator valve (Ref. BLEED AIR PRESSURE

Adjustment the

Proceed to STEP 4

vacuum

REGULATOR RELIEF VALVE ADJUSTMENT. 30-10-

00). STEP 4

Does the distributor valve function

properly? YES

NO Perform

an

operational

distributor valve if

check of the

system. Replace

required (Ref. SURFACE DEICE 30-10-00).

OPERATIONAL CHECK,

Page

voN201

1/07

30-~ 0-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

Chart 104

Troubleshooting

Surface Deicer

Deicer Indicator

STEP 1

Is

faulty

System

System Faulty

indication intermittent?

YES

NO

Proceed to STEP 2

Pressure be

sensor

plugged.

switch(es) vent hole may clamp so hole is not

Reinstall

covered. STEP 2

Do the pressure

sensor

switches function

properly? YES

NO

Replace defective STEP 3

Is there

a

problem

switch.

Proceed to STEP 3

with the electrical circuit?

YES

NO Troubleshoot the surface deicer bleed air pressure

Locate and

repair

as

required.

system

A23

30-~ 0-00

Page

voN301

1/07

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRFOIL SURFACE DEICER

MAINTENANCE PRACTICES

Since the deicer boots and related components operate on clean air bled directly from the engine, little is required in the way of servicing the system. The only possible source of contamination is through the air entering the vacuum valve in the

vacuum system. The filter for the vacuum system is installed outside the pressurized area in compartment. This filter should be periodically replaced according to the time limits stated in Chapter 5 of this manual. Other than this, the only servicing required is for the vacuum regulator valve, which prevents the

regulator

the

nose

vacuum

The

system from exceeding operating valve is mounted

regulator

vacuum

valve bleeds outside air into the

regulator Frequency of cleaning

limits

on

by allowing

the proper amount of air to enter the

lines.

vacuum

the pressure bulkhead in the nose compartment. Since the vacuum system, it is essential that the regulator valve filter be kept clean.

vacuum

the filter will vary with the conditions under which the

airplane

is

operated; however,

should

it appear that the valve needs adjustment, especially to lower the vacuum, the filter should be cleaned and the setting rechecked before readjusting the valve. The valve can be removed before cleaning by disconnecting the line from the valve and

30-00-00)

removing the retaining compressed air.

CAUTION: Deicer boots should not be

damage Two

nuts. The valve should be cleaned in MIL-PRF-680

solvent(l,

Chart 2,

and dried with

types of deicer boots

deicer boots;

operated

at

temperatures below -40 "F as this may result in permanent

to the deicer boots.

Airplanes

FASTboot deicer boot

are

in

use.

Airplanes

FL-443 and After

thereafter

are

referred to

FL-1 thru FL-442; FM-I and After

are

installed with conventional

installed with FASTboot deicer boots. as

FASTboot,

a

Trademark of Goodrich

Corporation)

uses a

bonding

system with pressure sensitive adhesive applied to deicer bond side in manufacturing. The pressure sensitive adhesive is activated with FASTboot primer and installation pressure, eliminating the traditional cementing operation for conventional deicer boots installation.

SURFACE DEICER BOOT CLEANING The surface of the deicer boots should be checked for indications of

flight. Any

oil spots that

are

found should be removed with

a

mild

engine oil after servicing and at the end of each detergent soap and a water solution. Care should

during cleaning to avoid scrubbing the surface of the deicer boots, as this will tend to remove the special application. It should also be remembered during servicing of the airplane that the deicer boots are made of soft flexible stock which may be damaged if refuelling hoses are dragged over the surface of the deicer boots or if ladders and platforms are rested against them. be exercised Icex

SURFACE DEICER BOOT REMOVAL a.

Starting at one 2,30-00-00).

b.

Apply

a

of the upper

minimum amount of toluol

tension to c.

corner

peel

trailing edge

t7,

Chart 2,

of the deicer boot, soften the adhesion line with toluol

30-00-00)

to the seam

line, while carefully applying just enough

back the deicer boot.

Using a brush or trigger type oil can to apply toluol (7, Chart 2, 30-00-00), separate the leading edge for a chordwise distance of four inches across the upper trailing edge. NOTE: The

t7, Chart

area

for toluol

deicer boot from the

between the deicer boot and

t7,

Chart 2,

leading edge which has been separated will act as 30-00-00); consequently, the deicer boot may be pulled forward with

a

reservoir

unison

tension. d.

From the center line of the

applied

n25

leading edge,

continue to

apply toluol (7, Chart 2, 30-00´•´•00) while

tension is

being

to undercut the adhesive until the deicer boot is removed.

30-1 0-00

Page

beF102

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

e.

Thoroughly clean all adhesive from the leading edge propyl ketone (2, Chart 2, 30-00-00).

SURFACE DEICER BOOT INSTALLA TION WARNING: Confirm that the

airplane

is

with clean,

(FL-1

grease-free

cloths

dampened with methyl

THRU FL-442; FM-1 AND

electrically grounded

to

AFTER)

prevent static sparks which could ignite

solvent vapors

CAUTION: Check the part identification of the deicer boot before using methyl propyl ketone or acetone (2 or 15, Chart 2, 30-00-00) on the deicer boot. Should the deicer boot be labeled "ESTANE~ toluol (7, Chart 2,

30-00-00) only should be

used

on

the deicer boot. DO NOT allow

methyl propyl ketone

to

come

in

contact with the Estane deicer boot. a.

Clean the

by the deicer boot with a clean, grease-free cloth dampened with solvent (2, 7 30-00-00). Change cloths frequently and never dip a used cloth in the clean supply of solvent.

area

15, Chart 2, b.

the surface

dry

To clean bare metal,

(11, gloss.

Alodine 1200 the

remove

CAUTION: To d.

dampened with clean, grease-free, dry cloth.

Reclean the metal surface with

wipe c.

to be covered

Carefully

with

scour

a

clean cloth

the surface with Scotch-Brite

i, 30-00-00).

assure

clean the

(2,

7 or

15, Chart 2, 30-00-00), then quickly

pad (3, Chart 2, 30-00-00) and then treat the metal with or a 320 grit sandpaper to

good adhesion,

rough

do not

wipe

with solvent after this final

before

NOTE: If the finish

on

sanding.

back surface of the deicer boot at least twice with

(7, Chart 2, 30-00-00). Change

applying

a clean, grease-free cloth, frequently to avoid recontamination of the cleaned too heavily with solvent or scrub repeatedly. Allow to

cloths

of the deicer boot. Do not saturate the back surface

dry thoroughly

solvent

On epoxy primed metal, use Scotch-Brite Use clean air blast or dry cloth to remove sanding particles.

Chart

moistened with toluol areas

a

or

adhesive.

the back of the deicer boot is smooth,

mechanically roughen

the

bonding

surface before

cleaning. e.

Prepare

test

strips

as

instructed under the

heading TEST CONTROL STRIPS (FL-1

THRU

FL-442; FM-1 AND

AFTER). f.

3/, inch masking tape (29, Chart 2, 30-00-00), mask off the area to be covered by the deicer boot, allowing ’/2 to 3/4 inch margin beyond the actual deicer boot area. Mask off accurately to avoid unnecessary clean up of

With

excess

g.

adhesive.

Open the container and thoroughly mix the Scotch-Grip 1300L adhesive (4, Chart 2, 30-00-00) with Do not attempt to use adhesive that has jelled too much to drip from the stick.

Page

20230-1 0-00

a

clean stick.

azs

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: Do not

apply the adhesive at temperatures below 40"F, at a relative humidity higher than 80% or under extremely dusty conditions. The table below will serve as a further guide for application of the adhesive.

Temperature

h.

Either of the i.

Brush

In "F

Drying

Time In Minutes

Above 80

30

60 to 80

45

Below 60

60

following

one even

two methods may be used to

coat of

apply

the adhesive.

Scotch-Grip 1300L adhesive (4, Chart 2, 30-00-00) on both the deicer boot back allowing the adhesive to dry, re-stir adhesive and apply a second even coat to

and the metal surface. After

both surfaces. NOTE:

Brushing

too

long

Allow the second coat to 2.

in

one area

dry for

will

cause

at least 30

the adhesive to "roll"

minutes, preferably

an

or

"ball

up".

hour, before installing the deicer boot.

Using a spray gun (2, Chart i, 30-00-00) spray one even coat of Scotch-Grip 1300L adhesive (4, Chart 2, 30-00-00) on both the deicer boot back and the metal surface. After allowing the adhesive to dry, spray a second even cross coat on both surfaces. Allow the second coat to dry for at least 30 minutes, preferably an hour, before installing the deicer boot. NOTE: For

spraying consistency, dilute the Scotch-Grip 1300L adhesive (4, Chart 2, 30-00-00) with a blend parts petroleum naptha (27, Chart 2, 30-00-00) to one part methyl propyl ketone (2, Chart 2, 30-00-00) until a No. 4 Ford cup will empty in 20 seconds; of two

i.

Snap a chalk line along the center of the leading edge of the airfoil. Snap a corresponding along the centerline of the adhesive side of the deicer boot (Ref. Figure 201).

j.

Attach the inflation hoses to the deicer boot connections without

leaving fingerprints

on

chalk line

lengthwise

the adhesive side of the

deicer boot. k.

Ilsing

clean, lint-free cloth heavily moistened (but

dripping) with toluol (7, Chart 2, 30-00-00), reactivate spanwise strips about 6 inches wide and 24 inches long. Match the deicer boot chalk line to the leading edge chalk line and roll the deicer boot surface spanwise along the leading edge with a rubber roller (3, Chart 1, 30-00-00) to remove all air from between the adjoining surfaces. Rubbing the adhesive surfaces excessively will remove some of the adhesive. If the deicer boot is misaligned, pull it free quickly with a quick motion and reposition it properly. a

the adhesive

NOTE:

n25

on

the airfoil

Applying

leading edge

a vacuum

not

and deicer boot in

to the deicer boot will aid in installation.

30-1 0-00

Hawker Beechcraft S’UPER KING

Corporation

AIR B300/B300C MAINTENANCE MANUAL

CENTERLINE OF

DE-ICER CENTERLINE

AIRFOIL

IWHITE)~

_

LEADING EDGE

DE-ICER AIR

CONNECTION HOSE

~t,´•

:s;r

.I

APPROX

I DETAIL

D

I-la"

srlAPPROX APPROX

D~-ICER

a

INITIAL INSTALLED AREA

DETAIL

A LINE

REACTIVATED AREAS

DETAIL

E

STARTING TRIM

DETAIL

B

B

TRIMMING WITH HOOK KNIFE

DETAIL

F

21-´•´• DETAIL DETAIL

G

C 13300-351-(27

Surface Deicer Boot Installation thru FL-442; FM-I and After)

(FL-1

Figure

Page

beF402

1/09

30-1000

201

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I.

Activate the adhesive surfaces and roll

on each top half and lower half of the deicer boot in sequence. Exerting Chart 1, 30-00-00) on the entire surface of the deicer boot parallel with the (3, pressure, inflatable tubes and use the narrow stitch roller between the tu bes. Take care to avoid entrapping air th roughout the rolling operation. If an air blister does occur, insert a hypodermic needle into the blister so that the air can use

the rubber roller

escape, then press the surface down until the adhesive surface seals.

CAUTION: If the blister is within the inflatable tube area, be careful to insert the needle between the tubes to avoid puncturing them. m.

Using

a

sharp knife, trim

the deicer boot

as

required

between the inflatable tube and the entire surface of the deicer boot.

process. Roll the n.

trailing edge

for proper fit. A 0.75 inch edge distance must be maintained After the trimming process has been completed, reroll the centerline of the deicer boot when initiating the rolling

edge of the trim. Always start at the

of the deicer boot with

exposed adhesive up to within ’/4 inch strips for deicer boot acceptability as instructed FL-442; FM-1 AND AFTER).

a

stitcher roller.

Clean off all

of the deicer boot

Perform

test

under the

CONTROL STRIPS

edges. heading, TEST

an

adhesion test of the

(FL-1

THRU

o.

Install masking tape (29, Chart 2, 30-00-00) around the deicer boot for uniform edge lines, then cover all exposed adhesive and fair around all cut edges and trailing edges of the deicer´• boot with filler compound (5, Chart 2, 30-00-00).

p.

After the adhesive and

adjacent

sealing

com

pound have dried and cu red, (2, Chart 2, 30-00-00).

remove

the maski ng tape and clean the surf ace

to the deicer boot with solvent

NOTE: The deicer boots must not be

provided

operated

until 48 hours after installation. The

relief from the 48 hours of

time recommended for

following instructions Scotch-Grip 1300L

are

supply drying adhesive on pneumatic deicer boots. This applies to the deicers with 1’/4’inch or narrower tubes operating at 20 psi or less pressure. The chart gives the reduced set times after installation for the applicable pneumatic deicers. The airplane may be operated after this set time as long as the deicer system is not used until after the 48 hour period. If the deicers are flexed before a 48 hour set time, the deicer boots must be che’cked for signs of lifting as soon as possible and be reinstalled or replaced if visible signs of lifting are present (Ref. Figure 202). CAUTION:

to

Applying heat externally through the deicers is not recommended to speed up drying time since it important for the bondline to be at the indicated temperature. The deicers will insulate the bondline from the heat being applied through if. Excess heat could cause deterioration of the deicers.

is

NOTE: It is recommended that the actual set time before inflation of the deicer boots be extended

as

much

as

possible. q. r.

Determine the Locate the

side of the s.

If the

room

temperature and humidity.

point on the chart chart) intercept.

where the

temperature (scale

at the

top of the chart) and

intercept point falls within the "lnstallation Not Recommended"

temperature and humidity conditions fall within the acceptable range where the temperature and humidity is within the acceptable range. t.

If the

u.

If the intercept point falls by moving straight down

n25

intercept point

falls within the "24 Hour

below the "24 Hour to the

drying

Dry

humidity

(scale

on

the

area, do not install the deicers until the or

the installation is moved to

Time" area, allow 24 hours of

Dry Time" area on the chart, read (at the bottom of the chart).

drying

an area

time.

the recommended

drying

time

time scale

30-1 0-00

Page

beF502

1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

(F)

TEMPERATURE

’P

100 "O

r

70

"P

T

r

-I-

T

-i

HOUR

24 80

t

-I-

DRY

i

T o

70f-

60

65

i-

T

55

50

i

i-

t

TIME

f

r

i

7

o~ W

i-

-I-

o c

60

Hw

H

T

r

-I-

f

r

HZ--

-I-

C Q

I

O

50

-I--+-1--r-t--l--r-+--I---

-f u

I

c

w

c

cn[~

40 w

I--

C

C

I

t

r

20 I o

H

O

30

_

C

t

C

-l-C -I

L

L

,L

_

_I

_

_

_

_

_

--I--

C

--I L

I

-I-

L

I

_i_

_

_

-I-

C-

L

_

t

_

o w

--I--

--I--

J

_

_

z-

L _1_

_C

L

_C

_

i

_

c O

_

_

I

I

_

ob-t--b-CO

2

6

4

SEi

8 TIME

10

12

AFTER

14

16

18

INSSALLATION

~O

~2

24

26

~8

t95UE3080517

(HRS)

Drying Time for Scotch-Grip 1300L Adhesive (FL-1 thru FL-442; FM-1 and After) Figure 202 TEST CONTROL STRIPS

QFL-1

AFTER)

THRU FL-442; FM- I AND

through the use of test strips applied at the time of deicer boot installation. strip from full thickness pieces of trimmings, scrap or previously rejected deicer boot material. Prepare one test strip for each batch or mixture of adhesive used. The strip should be applied in convenient area adjacent to the deicer boot. The metal and rubber surfaces shall be prepared in the same manner as prescribed Deicer boot adhesion shall be checked

Prepare

a

1 inch

x

8 inch test

for the deicer boot installation.

NOTE: The test strip may be same

surface

run on a

preparations

separate aluminum panel of the same alloy as the leading edge skin. bonding requirements as previously stated shall apply.

applying the test strip, leave approximately one inch of the free end of adhesive for clamp for the adhesion test. Allow the strip to cure for a minimum of 24 hours or more

When a

The

and

the purpose of attaching before testing adhesion.

Refer to ADHESION TEST.

ADHESION TEST

Using a push-pull gage attached to a clamp on the test strip unbonded end, measure the force required to remove strip at a rate of four inches per minute. The pull shall be applied 180" to the surface (strip doubled back on itself). A minimum requirement of seven pounds tension shall be required to remove the test strip. If these adhesion requirements are met, the airplane may be flown after installation of the deicer boot; however, if the deicer boot is activated before the 48 hour set time, it must be inspected for any signs of lifting or debonding at the next maintenance facility or within 10 hours. In the event of failure, the acceptance of the deicer boot installation shall be determined by acceptable requirements. Refer to BOOT ACCEPTABILITY.

the

Page

beF602

1109

30I10-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BOOT ACCEPTABILITY In the event of test a.

Using

toluol

deicer boot

strip failure, acceptability shall be based

(7, Chart 2, 30-00-00)

sufficiently

to attach a

b.

Attach

c.

If

d.

Reattach the deicer boot

to loosen the adhesion

force of

seven

pounds per inch of width corner as

can

a

following:

line, carefully lift

one corner

of the

newly installed

force 180" to the surface in such

instructed in this

Failure of the deicer boot to meet the above

a

direction that the deicer

be exerted under these conditions, the installation is

INSTALLATION (FL-I THRU FL-442; FM-1 AND e.

the

clamp.

push-pull gage to the clamp and pull with boot tends to be removed on a diagonal. a

on

Chapter AFTER).

requirement

heading SURFACE DEICER BOOT

under the

necessitates

satisfactory.

complete

removal and reinstallation of

the deicer boot.

FASTBOOT PREPA RA nON AND INSTALLA TION PROCEDURES

(FL-443 AND AFTER) NOTE: FASTboot should be installed at temperatures above 50"F and a.

With

3/4

beyond

inch

masking tape (29,

the actual FASTboot

Chart 2,

30-00-00), mask off

a

relative

the FASTboot

humidity

area

below 90%.

allowing

’/2 to 3/4

inch

margin

area.

b.

Aluminium surfaces coated with epoxy primer (cured for a minimum of 8 hours at with 400 grit sandpaper or scour pad (3, Chart 2, 30-00-00)

c.

(28, Chart 2, 30-00-00) dampened with toluol (7, Chart 2, 30-00-00), scrub the area FASTboot, followed by scrubbing with a clean dry white cloth (28, Chart 2, 30-00-00) before the solvent evaporates. Repeat this procedure until there is no evidence of contamination on the clean dry white

Using

a

80"F)

shall be scuff sanded

clean white cloth

to be covered

by

the

cloth.

NOTE: Do not pour or spray cleaning solvent on the layers to contaminate the sealing surfaces. d.

Using

e.

Trace the chalk line with

ballpoint

f.

Open

thoroughly

a

carpenter’s chalk line, snap

the container and

a

airplane structure,

line, centrally located

pen, and

remove

on

the

chalk line with

a

otherwise the solvent may

leading edge clean

dry

between

run

of the airfoil section.

white cloth

(28, Chart 2, 30-00-00).

stir the FASTboot

primer (23, Chart 2, 30-00-00) with a clean stick. If the by stirring, a paint shaker can be used. primer that has jelled and/or separated and cannot be blended together.

solids have settled to the bottom of the container and cannot be blended Do not attempt to g.

Apply

use

FASTboot Primer

(23,

Chart 2,

30-00-00)

to masked off

area

and allow to

dry

for 5 minutes.

CAUTION: Do not

remove release paper from FASTboot prematurely, as the exposed bond side will adhere to primed leading edge. When peeling release paper, keep FASTboot from contacting the primed leading edge until ready to roll in proper position.

the

NOTE: h.

Have

Position and

a

sufficient number of

align FASTboot

personnel present

to

effectively

air connection with air connection hole

handle the FASTboot.

on

the

leading edge,

and

apply

vacuum as

follows:

a25

30-1 0-00

Page

beF702

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

If FASTboot is

1.

the

airplane

connection

point

If FASTboot is

2.

being

installed

deicer line

or

leading edge fixed to the airplane, connect FASTboot air connection to Apply vacuum at the nearest connection point with no valve between the

on a

hose.

and the FASTboot.

being installed

on a

leading edge

not fitted to the

airplane,

connect and

apply vacuum directly

to FASTboot air connection.

NOTE: if necessary vacuum application may be deferred, until after the FASTboot centerline and air connection area are bonded on the leading edge. i.

Roll up FASTboot with release paper facing outward to 12-18 inches of inboard end. While an assistant holds the FASTboot in place, peel back 3-4 inches of centerline release paper strip at inboard end and roll FASTboot centerline firmly against the leading edge centerline with rubber roller (3, Chart 1, 30-00-00), anchoring

FASTboot in position. CAUTION: Remove the bond side release paper on FASTboot without on FASTboot which can adversely affect adhesion. CAUTION: Do not touch the exposed bond side adhesion.

j.

to avoid paper slivers

oils and contaminants from the hand

remaining

adversely affect

can

NOTE:

FASTboot adhesive is activated by pressure. Firmly roll FASTboot against primed leading edge with rubber roller (3, Chart 1, 30-00-00).

NOTE:

Make

sure

that

alignment

is correct for the

FASTboot~air connection(s).

peels centerline release paper strip, roll FASTboot firmly against leading edge 30-00-00). Repeat until the entire centerline is installed.

While assistant

(3, k.

as

tearing

Chait 1,

After centerline is bonded, bond the air connection

with rubber roller

area.

NOTE: If the FASTboot has two air connections, bond both of them. Release paper is slit for air connection(s). For cut-outs, install FASTboot up to cut-out area. Use hook knife to trim cut-out to fit leading edge. i.

If

m.

Beginning

vacuum

application on

has been deferred,

n.

strip.

primed leading edge.

Roll outward from the centerline of the

peel next release paper strip, taking care that exposed firmly against the leading edge while peeling the release FASTboot toward the trailing edge to avoid trapping air.

Roll

peel release paper strips, one at a time and roll FASTboot against the leading edge. Finish the air connection side of the FASTboot by peeling the final 1 to 1’/2 inches of release paper strip and rolling FASTboot Continue to

firmly against o.

vacuum now.

the air connection side of the centerline,

bond side does not touch the paper

apply

the

Trim FASTboot

leading.edge.

as

required

with

FASTboot is attached. Make

a

sure

sharp

knife and continue attachment of FASTboot until the total

that FASTboot is trimmed

no

closer than 0.75 inch from the

area

edge

of

of the

inflatable tubes. p.

Roll the entire surface of FASTboot

trailing edges

Page

again, applying pressure, of the FASTboot with steel stitcher roller.

30-1 0-00

starting

at the centerline

area.

Finally,

roll the

nzs

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SEALING OF DEICER BOOT EDGES All cut

edges

and

For epoxy sealed:

a.

trailing

primed

or

tapered edges of the

deicer boot shall be filled and/or sealed

aluminium surfaces and deicer boot surfaces that

are

(Ref. Figure 203).

in the masked off

to be filled and/

area

or

1.

Lightly

scuff with 400

2.

Clean the

3.

Apply

grit sandpaper

or scour

pad (3,

Chart 2,

30-00-00).

area with a clean white cloth (28, Chart 2, 30-00-00) dampened with naphtha (27, Chart 2, 30-0000), followed by wiping with a clean dry white cloth (28, Chart 2, 30-00-00) before the naphtha evaporates. Repeat this process until there is no evidence of contamination.

Bostik 1007M Primer

(24,

Chart 2,

30-00-00)

to bare metal surfaces and allow to

dry

for

a

minimum

of 30 minutes. 4. b.

Remove the

Apply edge

masking tape, previously applied

installed close

Apply

together

as

on

(25, Chart 2, 30-00-00) or PR1425 Class B (26, Chart 2, 30-00-00) to the full edges, cut-outs, recess edges and butt-joints in between two deicer boots that are

surface,’/4 to ’/2

1/16.to 1/, inch from

inch from the deicer boot

narrowest width

30-00-00), bordering th~eedges of the area’to be filled. its edge. Another line to be on the leading edge.

Chart 2,

masking tape (29,

the deicer boot surface,

NOTE: The width between the

c.

masking tape possible.

lines may vary

depending

2.

Apply edge filler between the tape lines, fairing to the adjacent masking tapes as soon as the edge filler has been applied.

3.

Allow

Apply

surface.

follows:

two new lines of

One line to be

edge

leading edge

filler PR1440 Class B

thickness of the deicer boot

1.

to mask off the area, from the

edge

filler to

conductive

edge

fully

for the

cure

sealer

(6,

cure

Chart 2,

time

on

surface for

a

the

area

to be

filled;

use

the

smooth transition. Remove the

specified (Ref. Chad 201).

30-00-00)

to the

trailing edges

of the deicer boot

as

follows:

1.

Apply masking tape (29, Chart 2, 30-00-00) on the deicer boot surface around the deicer boot’s trailing edge, or tapered edge, at least ’/4 inch from the edge. If edge filler has been used, make sure that the masking tape is at least ’/16 to 1/4 inch from the edge filler.

2.

Apply masking tape (29, Chart 2, 30-00-00) on the leading edge,’/8 to 1/, inch outside of the area initially cleaned (approximately 3/4 inch out from the deicer boot edge). Form neat, straight lines to border the edge of the sealer application. NOTE: If the

edge seal is being refurbished, make sure the deicer boot edges wiping with naphtha (27, Chart 2, 30-00-00).

3.

Stir the

edge sealerthoroughly by volume.

to

disperse any

are

free of contamination

solids. If necessary dilute with toluol

by

(7, Chart 2, 30-00-00)

not to exceed 20%

4.

Apply

5.

Remove the

an even

brush coat of conductive

masking tapes

as

edge

the sealer is

sealer

(6,

Chart 2,

30-00-00)

between the

tape lines.

applied.

NOTE: An easy method to remove the masking tapes is to attach ends of the masking tape lines to a cardboard cylinder. Roll the cylinder to take up two lines of tape as the edge sealer is applied.

azs

30-1 0-00

Page

beF902

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

6.

Cure time of the conductive

7.

After the conductive

clean, white cloth

edge

sealer

(6,

Chart 2,

30-00-00)

is 1 hour at 77"F and 50% relative

edge sealer has cured completely, clean the deicer boot and surrounding (28; Chart 2, 30-00-00) dampened with toluol (7, Chart 2, 30-00-00).

humidity.

areas

with

a

EDGE SEALER

DE-ICER BOOT

EDGE SEALER, TAPERED EDGE DE-ICER AIRPLANE

SKIN

EDGE SEALER

DE-ICER BOOT

EDGE

EDGEFILLERAIRPLANE

FILLER/SEALER, FULL THICKNESS

DE-ICERS AND CUTOUTS

SKIN

EDGE SEALER

DE-ICER BOOT

EDGE FILLER/SEALER, RECESSED DE-ICER

EDGE

AIRPLANE

FILLER

SKIN LJ30B985275AAAI

Edge Filler/Sealer Application Figure 203

Page

beF012

1/09

30-1 0-00

A25

Hawker 8eechcraft

Corporation

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

Chart 201

Edge MANUFACTURER’S NO. AND CLASS

APPLICATION TIME

PR1440-84

(25,

Chart 2,

30-00-00)

PR1440-82

(25, Chart 2, 30-00-00) PR1410-B112

(25,

Chart 2,

30-00-00)

PR1425-B112

(26, Chart 2, 30-00-00) PR1425-82

(26,

Chart 2,

30-00-00)

A56BR-1

(6,

Chart 2,

FillerlSealer

(HOURS)

Curing

Times

TACK FREE TIME

CURE TIME

(HOURS)

4

48

96

AIITypes

2

36

72

AIITypes

1/2

10

30

AII

Types

1/2

8

24

Fillet

2

24

48

Fillet

’i,

30-00-00)

TYPE OF SEAL

(HOURS)

Conductive

1

Edge

Sealer

NOTE

Application time is time requirements

are

stated

from 77"8, reduce

application time,

as

minimum

taken at 77"F

requirement,

tack free time and

2"F with 50% f 5% relative

tack free time and

cure

time

application

time

are

maximum

requirements. All

For every 10"F rise in temperature and for every 10" below 77"F one-half

by

double the stated time. Frozen sealants shall have their time reduced material

cure

humidity.

(1/2)

by

45 minutes from the standard two

part

times.

FASTBOOT AIR PRESSURE TEST (FL-443 AIVD AFTER) a.

After installation of the FASTboot, pressure testing and in flight pressurizing may be carried out immediately provided installation occurred above 50"F and with less than 90% relative humidity. Pressure applied during test shall not exceed 18

A25

psig (Ref.

SURFACE DEICER OPERATIONAL

CHECK).

30-1 0-00

Page.al Feb

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STALL STRIP INSTALLATION a.

The stall

strips

are

long and

11 inches

are

164.735 is 17 inches outboard of the end

b.

When

using

wipe

with

thoroughly, removing all old adhesive. Mask methyl propyl ketone (2, Chart 2, 30-00-00).

Combi-Bond Adhesive

deicer boot, mix

one

partlof

(32,

Wing

Station 164.735

(Wing

Station

fillet) (Ref. Figure 204).

Clean the deicer boot surface to be installed and

c.

installed with the inboard ends at

Chart 2,

30-00-00),

a

two

off the

part adhesive,

area

where the

new

to attach the stall

Combi-Bond Hardener with 17 parts of Combi-Bond Cold

Bonding

strip is

strip

to the

Adhesive

by

weight. d.

Apply two coats of well mixed adhesive to both surfaces to be bonded, allowing 15 to 30 minutes between each coat (depending on temperature conditions) and 8 to 12 minutes after the final coat before bonding, then allow to cure for 48 hours. Use the mixture within 8 hours unless it is stored at

NOTE: If surfaces become too

dry

and cannot be solvent reactivated,

temperatures below 65"F.

apply an additional

coat of cement

as

detailed

above.

LEFT

WLNG

20 i .06 "A" is 19.31 end and ourboord end or

stall

.06 Dimension "A" Y i is rnboord end and 18.31 or Inches or ourboord end of

06 stoll

Dimension or

Inboard

inches

or

inches .06

strip.

RIGH~

WING

Sfrip.

Stall

Page

beF212

1/09

30-1 0-00

Inches

981271AI\

Strip Installation Figure 204

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SURFA CE DEICER BOO T A GE I~ASTER AND ICEX APPL ICA TION Master No. 1

Age

(77,

Chart 2,

30-00-00)

is

a

liquid

that

protects rubber products from weathering and

ozone

and

extends the life of these parts. Age Master No.l and Icex compound are both products of Goodrich Corporation. Icex will not harm the deicer boots and offers added ozone protection. When properly applied and renewed at

periodic intervals, Icex provides a smooth, polished film that evens out microscopic irregularities on the rubber surfaces; therefore, ice formations have less chance to cling and are removed faster and cleaner when the deicer boots

are

operated.

a.

Wash the deicer boot with mild soap and water.

b.

Isopropyl alcohol (18, Chart 2, 30-00-00) may be used to remove substances which cannot be removed using soap and water; however, the deicer boot must be washed again with mild soap and water, rinsed with clean water and allowed to dry.

c.

Apply masking tape (29, Chart 2, 30-00-00) adjacent

CAUTION:

To avoid the loss of vital

fire

safety precautions,

Thoroughly

rinse the surface with clean water and allow to

to the deicer boot to be treated to

components needed for the protective agent

do not spray

Age Master No.

to

dry.

prevent staining.

penetrate the rubber and for

i.

d.

Using a brush or three inch trim roller or a two inch by four inch swab of lint-free cloth (wet but not dripping), apply a heavy coat of Age Master No. i. Plastic or rubber gloves should be used with the swab method to prevent staining the skin. Apply at a rate of 0.4 to 0.5 fluid ounces per square foot (130 to 160 mi per square meter). Cover the surface completely and evenly in uniform strokes.

e.

Allow the first coat of

Age

Master No. 1 to

NOTE: A minimum of two coats of f.

Age

dry

from five to ten minutes.

Master No. 1

are

required

for

a

complete

treatment.

Apply a second coat of Age Master No. 1 as outlined in step "d". Apply a total of 0.75 fluid ounces per square foot (240 mi per square meter) for effective protection. Allow the second coat to dry 20 to 30 minutes before handling. NOTE: After

applying

the second coat of

Age Master No. 1 to the deicer boot, it must have dried a maximum applying Icex compound. Without further cleaning, Icex compound is then applied Age Master No. 1.

of 24 hours before

directly

over

the

g.

Allow the two coats of

h.

Thin the Icex

Age

Master No. t to

dry

for 24 hours.

compound (8, Chart 2, 30-00-00) with

trichloroethane

(9, Chart 2, 30-00-00)

to obtain

a

thin coat

application. i.

Use

a

clean cloth saturated with the thinned Icex

compound

for

application.

Hand buff until

a

smooth

glossy

surface is obtained. NOTE: Both the

Age

Master

no.

1 and Icex

compound

should be

reapplied every

150

flight

hours.

SURFACE DEICER BOOT REPAIRS RESURFACING DEICER BOOTS The the

principal surfacing

Ai5

factors involved when has

resurfacing

seems

advisable

are

if the

surfacing

material has abraded off

developed cracks.

30-1 0-00

or

if

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

a.

thoroughly with toluol (7, Chart 2, 30-00-00)

Clean the deicer boot

or

uncontaminated unleaded aviation

gasoline. the entire surface of the deicer boot with fine

b.

Roughen

c.

Clean the surface

again

with

a

sandpaper.

clean lint-free cloth moistened with toluol

or

uncontaminated unleaded aviation

gasoline. d.

Apply masking tape (29,.Chart 2, 30-00-00) beyond

the upper and lower

trailing edges, leaving

a

’/4 inch gap

of bare metal. Brush

e.

one

of conductive

one coat

hour. Then

apply

a

may be flown

airplane

If conductive

NOTE:

edge

30-00) on the deicer boot and allow it to dry for at least dry at least four hours before operating the deicer boots. The conductive edge sealer is dry.

sealer

(6,

Chart 2,

second coat and allow it to as soon as

the

(6, Chart 2, 30-00-00) has aged three months or more it may be necessary (7, Chart 2, 30-00-00) to obtain the proper brushing consistency. Mix thoroughly parts conductive edge sealer to one part toluol.

edge

sealer

to´•dilute it with toluol

approximately

5

SCUFF DAMAGE

commonly encountered and generally will require no repair; however, close visual are cycled may expose deep scuffs and cuts. On those occasions, if the entire ply inspection surface (0.010 inch) has been removed, or if the deicer boot is cut, it is necessary to patch the damage. Goodrich Corporation Kit No. 74-451-C contains cold patches suitable for repairing the damaged area.

This

type of damage is

most

when the dgicer bbots

a.

Clean the or

b.

steel

Using

NOTE: A c.

around the

locally

the buffed

loose

particles.

Select

e.

Apply

area

manufactured area

with

a

with

one even

a

around the

clean, grease-free cloth dampened with toluol (7, Chart 2, 30-00-00)

damage

so

that it is

completely roughened.

material will

assure a

neater

clean, grease-free cloth dampened with toluol (7, Chart 2, 30-00-00) to

coat of No. 4

at least

’/2

inch

beyond

the

damaged

area

repair.

remove

in all directions.

cement, provided in the repair kit, to the patch and the damaged

area.

Allow the

dry until tacky.

patch to the deicer boot with an edge, or the center, adhering pockets. Thoroughly roll the patch down with a stitcher roller.

the

avoid air

but

moderately,

buffing shield, fabricated from any thin sheet

repair patch which will extend

a

cement to

Apply

damage gasoline.

wool, buff the

Wipe

d.

f.

area

unleaded aviation

first. Work the

patch

down

carefully

to

CAUTION: Check the part identification of the deicer boot before using methyl propyl ketone or acetone (2 or 15, Chart 2, 30-00-0b) on the deicer boot. Should the deicer boot be labeled "ESTANE’: toluol (7, Chart 2,

30-00-00) only should be

used

on

the deicer boot. DO NOT allow

methyl propyl ketone

to come in

contact with the Estane deicer boot.

NOTE: The so

run

g.

patches

are

manufactured to stretch in

that stretch is in the widthwise

along

the

length:of

one

(chordwise)

direction

only.

Be

sure

to cut and

direction of the inflatable tubes. The

apply the selected patch length of the patch shall

the tubes.

patch to set for 10 to 15 minutes, then clean the patch and surrounding area with a dampened with methyl propyl ketone (2, Chart 2, 30-00-00) or toluol (7, Chart 2, 30-00-00).

Allow the

Page

30-1 0-00

clean cloth

*25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

h.

adhesion of the

Satisfactory to check the

i.

Apply

a

repair

smooth

after

light

will be reached in about four hours;

patch

however, the deicer boot may be inflated

minimum of 30 minutes.

a

coat of filler

compound (5, Chart 2, 30-00-00)

to seal and feather the

edges

of the

patch

to

the deicer boot.

j.

Apply

one

light coat of conductive edge

sealer

(6, Chart 2, 30-00-00) to the patched area, extending beyond the dry thoroughly (at least on hour) and apply a

buffed area, to restore the conductive surface. Allow the sealer to

light

second k.

coat.

After the filler

00-00)

to the

compound and sealer has dried and cured, apply patch and surrounding area.

a

thin

of Icex

coating

compound (8, Chart 2,

30-

TUBE AREA DAMAGE a.

Clean the

area

around the

damage

with

a

clean, grease-free cloth dampened with toluol

or

unleaded aviation

gasoline. b.

Buff the

c.

Wipe

d.

area

around the

the buffed

Select

with

area

a

with the

buffing stick, provided

NOTE: If

of the

none

or

patches

If’this

patches. Complete

of the cut

edges

in the

repair

clean, grease-free cloth dampened with toluol

patch from the repair kit of ample size

a

the ends and

e.

damage

damaged

remove

loose

particles.

and extend at least

area

5/, inch be;ond

tear.

are

the size

is done, bevel the

the installation of the

to cover the

to

kit.

patch

as

required, cut a patch of the desired size from edges by cutting with shears at an angle.

outlined in the

paragraph

one

of the

SCUFF DAMAGE, steps "e"

larger

through

"k".

LOOSE SURFA CE PL Y IN NON-INFLA TABLE AREA a.

Peel and trim the loose surface

b.

Scrub

(roughen)

parallel c.

the

to the cut

area

edge

ply

to a

point where adhesion of

the surface

ply

is

good.

in which the surface

to the cut

Scrub with steel wool and toluol

edge of

directly

the

over

ply is removed with steel wool. The scrubbing motion ply to prevent the ply from loosening.

all

edges,

but

parallel

to the

edge

of the

ply,

to

must be

taper edges of the

ply. d.

Cut

a

piece

of surface

extend at least e.

Mask off

f.

Apply

one

an area

one even

ply material, provided in the repair kit, large enough beyond the damaged area in all directions.

1’/2

inches

Roll the surface

larger

in

coat of No. 4 cement,

material. Allow the cement to

g.

to

cover

the

damaged

area

and

inch

dry

until

length and width

than the size of the

provided in the repair kit, tacky.

to the

damaged

damaged

area

area.

and the surface

ply

ply to the deicer boot with a two inch rubber roller (3, Chart 1, 30-00-00), applying enough wrinkling. If air blisters appear, remove with a hyperdermic needle-and reroll the area.

tension to prevent h.

Remove the

"g" through

nzs

masking tape

and

complete

the installation

as

outlined in the

paragraph

SCUFF DAMAGE, steps

"k".

30-1 0-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LOOSE SURFACE PLY IN TUBE AREA

starting to flex fail. This type of failure ply when the deicer boot is pressurized. If detected while a small blister (’/4 to 3/, inch in diameter) and immediately patched, service life of the deicer boot will be appreciably extended. Repair of this type damage is the same as SCUFF DAMAGE. Loose surface

in the tubearea is

is

as a

ply easily detected

usually

an

indication of the deicer boot

under the surface

blister~

FABRIC BACK PLY DAMAGE DURING REMOVAL If the adhesive from the

leading edge skin has

adhered to the back surface of the deicer

boot,

remove

the adhesive

with steel wool and

methyl propyl ketone (2, Chart 2, 30-00-00). In spots where the coating has pulled off the fabric, leaving the bare fabric exposed, apply at least two additional coats of Scotch-Grip 1300L adhesive (4, Chart 2, 3000-00). Allow each coat to dry thoroughly. SURFACE DEICE PRESSURE SENSOR SWITCH REMOVAL NOTE:

Removal of the wing and tail deice pressure circuit breaker SURF DEICE

sensor

the circuit breaker

a.

Disengage

b.

Remove the nut, washer,

screw

c.

Hold the pressure

switch and disconnect the

d.

Cap

or cover

sensor

the tube

end

to

and

on

switches is

mounting clamp securing

prevent entry of foreign

panel

typical. in the

cockpit (right

the pressure

sensor

side

panel).

switch to its bracket.

pneumatic pressure tubing. matter.

SURFACE DEICER PRESSURE SENSOR SWITCH INSTALLA TION NOTE: Installation of the a.

Position the pressure

wing and tail sensor

deice pressure

switch and

sensor

mounting clamp

switches is

typical.

with the vent hole

30". The

clamp

must not

cover

the

vent hole of the switch.

b.

Secure the

c.

Hold the pressure

d.

Connect the electrical connector to the pressure

e.

Engage the circuit

mounting clamp sensor

with

a

screw, washer and nut.

switch and connect the

pneumatic

sensor

pressure

tubing.

switch.

breaker SURF DEICE.

SURFACE DEICER OPERA TIONAL CHECK a.

engines operating at 70 to 80 percent RPM gas generator speed, momentarily place the deicer switch single position. Th~ wing deicer boots should inflate for approximately six seconds and the tail deicer boots should inflate for approximately four seconds, then deflate to the vacuum hold down position. During inflation, the pneumatic pressure gage should register approximately 18 psi and the advisory annunciator lights

With both in the

WING DEICE and TAIL DEICE should illuminate. b.

Hold the deicer control switch in MANUAL inflated while the switch is retained in this

heading PRESSURE REGULATOR

Feb

1/09Page

216

30-1 0-00

position for a few seconds. The deicer bootsshould inflate and remain position. Check for correct system pressure as indicated under the

RELIEF VALVE ADJUSTMENT in this

chapter.

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

Release the deicer control switch, the

vacuum

hold down

permitting it to return to the OFF position.The deicer boots should deflate position. The advisory annunciator lights WING DEICE and TAIL DEICE should

to

extinguish. d.

Repeat steps "a" through "c" with each engine operating individually speed. Shut down engine upon completion of checks.

at 70 to 80

percent RPM gas generator

BLEED AIR PRESSURE REGULA TOR RELIEF VAL VE ADJUSTMENT The pressure regulator valve is mounted under the center aisle floorboard just to the right of the airplane centerline immediately forward of the rear spar. It regulates incoming bleed air to approximately 18 psi of pressure. The unit also incorporates a relief valve that is set at approximately 21 psi. Ordinarily, the regulator valve will not require

adjustment since

adjusting a.

Start

screw

each unit is preset at the factory; however, the pressure should it become necessary to reset the valve in the field.

engine

one

and

run

it up until

a

reading

regulator valve is equipped

between 70 to 80 percent RPM is

registered by

the gas

with

an

generator

tachometer. b.

Check the deicer pressure gage for a reading of 18, 1 psi. If necessary loosen the adjusting screw locknut located on top of the valve.

CAUTION: Do not exceed the recommended 18 f 1 excessive c.

Turn the

wear on

adjusting

screw

psi regulator setting

unsafety

because

the lock

retaining

higher settings

washer and

will result in

the relief valve.

clockwise to increase

pressure gage indicates 18+1

or

counter clockwise to decrease the pressure

setting

until the

psi.

NOTE: Check the system vacuum gage for a reading of 5.9 inches Hg., since adjustment of the pressure regulator valve may affect the vacuum system suction enough to necessitate readjusting the vacuum regulator valve. d.

Tighten

and

resafety

the locknut then shut down the

engine.

VA CUUM REGULA TOR VAL VE ADJUSTMENT The

regulator valve is located

vacuum

on

the forward left hand side of the forward pressure bulkhead at

Fuselage

Station 84.00. NOTE:

Prior to and

a.

Start

making any adjustments to the vacuum regulator valve, make certain that the instrument regulator filter are clean and free of lint or other foreign materials.

air filter

vacuum

engine and

one

run

it up until

a

reading between

70 and 80

percent RPM is registered by the gas generator

tachometer. b.

Check the

vacuum

valve

regulator c.

Turn the

d.

When the

adjusting

a

screw

IN

reading

of 5.9 +0/-0.2 inches

the lock

(clockwise)

retaining

Hg. If the indication is incorrect, adjust the loosening the adjusting screw locknut.

vacuum

washer and

to increase or OUT

(counterclockwise)

to decrease the vacuum

setting.

gage registers a reading of 5.9 inches Hg. with the engine operating within the range in step "a" tighten the locknut and resafety it, then shut down the engine.

vacuum

designated

n25

gage for

by unsafetying

30-1 0-00

Page

beF712

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DEICER BOOT FINAL FINISH a.

Clean deicer boot

00-00)

to remove

by using a clean white cloth (28, Chart 2, 30-00-00) dampened with solvent (7, Chart 2, paint ouerspray and heavy contamination.

b.

Apply Shinemaster Prep (30, Chart 2, 30-00-00)

c.

Wipe

off Shinemaster

until all contaminates

d.

Prep are

with

a

clean wet

removed.

with

a

clean lint-free cloth.

(with water) sponge, rinising Wipe dry with a clean, lint-free cloth.

sponge

as

it becomes

Apply Shinemaster (31, Chart 2, 30-00-00) to deicer boot with a clean, lint-free cloth, wiping Apply 2 or 3 coats allowing each coat to dry before applying the next coat.

Page

30-1 0-00

30-

in

dirty. Repeat

one

direction.

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIR INTAKES

DESCRIPTION AND OPERATION

AIR INTAKE ANTI-ICE LIP

lip around each engine air inlet is heated by hot exhaust gases to prevent the formation of ice during inclement weather. A scoop in the LH exhaust stack on each engine diverts a portion of the hot exhaust gases downward through a flex hose into the hollow lip encircling each engine air inlet. The gases are exhausted out of the opposite The

exhaust stack. No shutoff

or

temperature indicator is necessary for this system.

INERTIAL SEPARA TION ANTI-ICE SYS TEM

separation system, consisting of two electrically actuated movable vanes, is built into each engine air inlet to prevent moisture particles from entering the engine inlet plenum during freezing conditions. In normal operation, the vanes are positioned with the forward vane retracted (up) and the aft vane extended (down) to direct all incoming air into the engine air plenum. When icing conditions are encountered, the forward vane is lowered into the inlet airstream and the aft vane is retracted. Repositioning these vanes will cause the velocity of incoming air to increase so that heavy ice laden air will be directed overboard through the lower aft cowling, while lighter incoming air will turn abruptly to enter the engine plenum around the trailing edge of the extended forward vane and the curved fixed An inertial

vane.

positioned simultaneously through a linkage system connected to an electrically operated linear Upon actuation, actuator travel is maximum in direction commanded with no intermediate positions. The electric actuator for each engine consists of a primary and secondary motor with a single actuator rod assembly. The system is normally driven by the primary motor. In the event the primary motor malfunctions, system power is provided through selection of the secondary motor.

The two

vanes are

actuator.

CAUTION: Should the actuator prima~y motor malfunction, the corrected before the next The

primary

cause

of the malfunction must be determined and

flight.

are energized through switches placarded ENG ANTI-ICE, LEFT-RIGHT, ON-OFF subpanel. The secondary system may be activated through a second set of switches primary switches and placarded ACTUATORS-STANDBY-MAIN.

actuator motors

the left outboard

located

on

located

just below

the

fully extended, a position sense switch on each vane linkage will cause advisory (green) light in the caution/advisory annunciator panel to illuminate. When the control switches on the subpanel are activated, a second position sense switch, also located on each forward vane linkage, will energize a 30 to 40 second time delay circuit. If full extension of the vanes is not attained in this time, the L ENG ICE FAIL and/or R ENG ICE FAIL caution (yellow) light in the annunciator panel will illuminate, signaling a fault in the primary motor of the designated actuator. To complete vane extension and extinguish fault light, place corresponding ACTUATORS switch to STANDBY position. When the icing conditions have passed, the ANTI-ICE switches are placed in OFF position. This drives actuators in opposite direction, returning vanes to non-icing position and extinguishing annunciator panel lights. In

operation,

when the forward

vanes are

the L ENG ANTI- ICE and R ENG ANTI-ICE

A23

30-20-00Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIR INTAKES

MAINTENANCE PRACTICES

ANTI-ICE LIP CRA CK REPAIR drill the ends of the crack

a.

Stop

b.

Clean

c.

Using the gas steel weld rod

d.

If it has not been necessary to disassemble the air intake anti- ice lip from the cowling in order to accomplish the repair, then the aluminum skin attached to the anti-ice lip must be protected from the heat generated by

area

to be welded

as

using

a

thoroughly

No. 40 drill bit as

(Ref. Figure 201).

possible, removing

all dirt, oil,

1 or

other contaminants.

tungsten are welding process (heli-arc), weld the crack and stop drill holes shut. Use stainless (19, Chart 2, 30-00-00) for the repair. If the crack is in an area of the air intake anti-ice lip that is of air chamber, or intake or outlet tubes, the anti-ice lip should be purged with argon for fifteen the hot part minutes before welding begins and also throughout welding. If the crack is in an area of the anti-ice lip that is not part of the hot air chamber or tubes, the back side of the area to be welded should be backed with clean copper sheet 0.032 inch thick, or thicker. Under no circumstances should repair welding be performed on an area where the stainless steel anti-ice lip is lapped over the aluminum cowling skin. The two metals must be separated (the lip must be removed from the cowling) prior to repair.

The purging procedure mentioned above will do much to dissipate the heat of welding. In some instances, especially if the area to be repaired is immediately adjacent to, but not lapped over, the aluminum cowling skin, it may be beneficial to also use a protective heat sink compound such as Anti-Heat (20, Chart 2? 30-00-00) to protect the cowling skin.

welding.

e.

After the

welding operation

has been

completed, sand and buff the repaired

area

flush with the

surrounding

area.

ENGINE INERTIAL ANTI-ICING SYSTEM SERVICING To help control wear and keep the inertial anti-icing system of the engines operating freely, the actuating linkage should be periodically lubricated with grease (12, Chart 2, 30-00-00). Beyond lubrication, virtually no servicing of the inertial

anti-icing system

is

required.

NOTE: NOTE: Do not lubricate with oil.

Adjustments may

be made

on

the inertial

anti-icing system

as

outlined in this

chapter

under the

heading

RIGGING

THE ENGINE 1NERTIAL ANTI-ICING SYSTEM.

~u,

30-20-00Page

201

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

RIGGING THE ENGINE INERTIAL ANTI-ICING SYSTEII/I The

following procedure provides

its various a.

I

components

a.

Remove the

to

gain

access

with

rigging of the inertial anti-icing system to ensure another throughout all phases of operation.

for the

respect

to

the proper

adjustment

of

one

cowling as outlined in Chapter 71-10-00 system components.

under the

heading

COWLING REMOVAL,

as

required,

to

b.

b. Disconnect the control rod from the forward

c,

c.

If the control rod is disconnected at the

(No.l)

vane

engine mount,

linkage (Ref. Figure 202).

use

AN960-10 washers

as

required

to

align

the control

rod end. retracted and the aft

d.

d. Ensure that the actuator is

e.

e.

f.

f. Return the actuator to the retracted

g.

g.

Operate

Adjust

vane

h.

fully

the actuator to full extension

(extension

(No.2)

vane

is in the full down

distance of actuator rod should be 4.0

slightly

h. Extend the actuator. The aft

be flush with,

or a

i.

i.

Adjust

j.

j.

Reinstall the

the

vane

0.02

inches).

position.

the control rod to 10.50 inches and reconnect it to the forward

inner surface should be

position.

below the

top of the fixed

vane

linkage.

The

plane

of the forward

vane

should be in the full up position and the plane of the forward below, the bottom of the fixed vane.

vane

should

maximum of 0.060 inch

vane sensor

cowling

switches to

as

outlined in

give 0.100

Chapter

inch minimum overtravel at the limits of actuator

71-10-00 under the

operation

heading COWLING INSTALLATION.

BYPASS DUCT REPAIR The inertial anti-icer will function

effectively only if the inner surface Rough spots, dents or projecting rivets, screws, or other protrusions the bypass duct. To prevent this, make sure there are no protrusions

Page

30-20100

of the

bypass

duct is

aerodynamically clean. building up and block

may allow ice to begin or flaws in the duct.

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXHAUST STACKS

NUT ASHER

BOLT

~O

FLEX HOSE

A

DISCONNECT CLAMPS

NE AIR INLET ANTI-ICE LIP

DETAIL

A

Air Intake Anti-ice

350-258-12

Lip

Figure 201

A23

30-20-00

Page

voN302

1107

Hawker Beet~hcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MAN UAL

BWIGPNAk

as Received By aTB

POSITION OF VANES AND AIR FLOW FOR .DRY AIR I(JON-ICING

CONDITION

ACTUATOR

(ELECTRICALLY OPERATED)

INLET DUCT I_IP HEATED

WITH HOT GASES FROM A COLLECTOR IN THE

:72 VANE

EXHAUST

14~

STACK

r

AIR INLET

if

BYPASS AIR

OIL COOLER INLET

FIXED VANE

-1 VANE

CONTROL ROD OIL COOLER BYPASS ALR

POSITION OF VANES AND AIR FLOW FOR ICING CONDITIONS

ACTUATOR

A’CTUATOR TRAVEL 4.00

1

02"

n2 VANE

AIR INLET

L´•13

BYPASS AIR

OIL COOLER INLET tl VANE

060" MAX

FIXED

VANE

OIL COOLER BYPASS AIR

8300-851-~25

Inertial Anti-ice System

Figure

Page

voN402

1107

30-20-00

202

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BRAKE DEICE SYSTEM Heated air for the brake deice

DESCRIPTION AND OPERATION

system is supplied by the pneumatic bleed air system. Downstream of the pneumatic

bleed air shutoff valves, the brake deice line tees off the

pneumatic bleed air line in each wheel well. Deice bleed solenoid-operated shutoff valve, through a flexible hose, and to the distributor manifold on the assembly. Bleed air is distributed through orifices located on the circumference of both rings of each

air is then routed to

piston and axle

a

distributor manifold. The system is controlled

toggle switch placarded BRAKE DEICE, ON-OFF located on the pilotis inboard position, electrical power is supplied through a 5-amp circuit breaker on the RH circuit breaker panel to a control module located under the center aisle floorboard immediately aft of the cabin forward partition. Current is then supplied to open the deice shutoff valve in each main gear wheel well, allowing hot bleed air to flow through the distributor manifolds and deice the brakes. A switch that is part of each shutoff valve then closes and completes a circuit to illuminate the LH BK DEICE ON and the RH BK DEICE ON advisory (green) lights in the caution/advisory annunciator panel. Refer to Chapter 32-41-00 for further information on the brake deice subpanel.

by

a

When the switch is in the ON

system

~aa

30-21-00

i

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WINDOWS AND WINDSHIELDS

DESCRIPTION AND OPERATION

WINDSHIELD ANTI-ICE The

pilot’s

protected against icing by dual level heating elements imbedded in the by two toggle switches placarded WSHLD ANTI-ICE, NORMAL-OFF-HI, PILOT-COPILOT located on the pilot’s inboard subpanel. and

windshield.

copilot’s windshields

Operation

are

of the windshield heaters is controlled

Each electrothermal windshield is connected to the

airplane

electrical

system through high heat and low heat relays

and temperature controllers located on electrical panels on the aft side of the forward pressure bulkhead just forward of the instrument panel. Each system is protected by a 50-ampere circuit breaker located on the power distribution panel assembly under the center aisle floorboard between FS 158.000 and FS 167.625. Each controller is protected

5-ampere circuit breaker located on the circuit breaker panel on the right hand side of the flight compartment. a temperature sensor element (thermistor) which senses windshield temperature and, through its associated controller, cycles heater power to maintain a desired mean temperature between 90" F and

by

a

The windshields also include 110"F.

WINDSHIELD WIPERS Heavy duty windshield wipers for both the pilot and copilot provide visibility during rainy flight conditions. The wipers are controlled by a rotary switch placarded WINDSHIELD WIPER, PARK-OFF-SLOW-FAST located on the overhead panel. Circuit protection is provided by a 10-ampere circuit breaker located on the circuit breaker panel on the right hand side of the flight compartment. Rotary power for operating the wiper system is provided by a motor driving two converters through flexible shafts located forward of the instrument panel. The motor contains an automatic reset thermoprotector which will temporarily de-energize the motor in the event of an overload. Also included are radio noise filters and a gear train for actuating a cam switch to automatically "park" both wipers when the rotary switch is turned to PARK position. windshield

WINDOW DEFOG SYSTEM cockpit side window defog is provided through the use of engine bleed air anytime one or both engines running. A pressure regulator mounted under the floorboard, right of center and aft of FS 221.375, the bleed air pressure for window defog (Ref. Figure 1). From the regulator the air is routed to the right of regulates center and forward of FS 221.375 where the air lines divide. At this point part of the air is routed to the sides of the airplane and up the sidewall to just below the windows where it tees and runs fore and aft under the cabin windows. Cabin window and are

Beneath each cabin window there is another tee in the system which delivers the air to the inside surface of the through two tubes.

exterior window

CA UTION: Caution must be used when

removing

lines. Make cerfain the bleed air lines

Air for the

cockpit

to the sides of the

installing the emergency exits to a void damaging the are properly connected when installing the hatches. or

side windows is routed forward from FS 221.375 to FS 143.000. At this

airplane and up the sidewall to the windows. The of the windows through a manifold in the window frame.

warm

dry

air is

now

point the

bleed air

line tees,

running

directed to the inside surface

Air filters may be installed inline with the system tubing to prevent grime build-up on the windows. installed in three places. One on each side wall and one under the forward floorboard.

30-40-00

They

will be

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PLUMBING TO COCKPIT

DEFOG PRESSURE REGULATOR

SIDE WINDOW DEFOG

F.S. 143.00

F.S.

F.S.

122.00

143.00

(UNDER

AIR FILTER

EMERGENCY EXIT

FLOORBOARD)

PLUMBING TO CABIN

F.S.

EMERGENCY EXIT

THE

WINDOW DEFOG

221.37

F.S.

F.S. 221.37

312.50

WARM AIR

NOULES

P\ WARM AIR

MANIFOLD

AIR FILTER

FROM DEFOG PRESSURE

REGULATOR

woe 031572AA ~I

Cabin Window and Side Window

Figure

May

1/0830-40-00

Defog

1

A24

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANACE MANUAL

WINDOWS AND WINDSHIELD

MAINTENANCE PRACTICES

WINDSHIELD WIPER MOTOR REMOVAL a.

b.

To

gain floating

access

the radio

quick-release fasteners securing panel (Ref. Figure 201).

to the motor, loosen the

instrument

Tilt the

panel

placing

undue force

aft

sufficiently on

to

permit

removal of the electrical connections and cable drives. Use

any wires, control heads, mounts,

c.

Remove the

d.

Remove the flexible drive shaft

e.

Remove the four

equipment panel

or

to the

care

to avoid

cables.

panel.

attaching

retaining and

screws

nut and disconnect the electrical

disengage

plug.

the motor from the flexible drive shaft.

WINDSHIELD WIPER MOTOR INSTALLATION that the

a.

Make

b.

Connect the electrical

c.

sure

wiper

blades

plug

are

in the

park position. (Ref. Figure 201).

to the motor and

operate the

Connect the flexible drive shaft to the motor with the

attaching

park position.

motor to the

retaining

nut and secure the motor in

place

with the

screws.

d.

Reconnect the mechanical drives and electrical connections to the radio

e.

Carefully position the panel in the floating instrument panel. Use care place undue force on any wire, component, control head, or mount.

f.

Fasten the

quick-release

fasteners

securing

the radio

panel

to the

panel.

not to

floating

pinch

any wire

instrument

or

wire bundles

or

panel.

WINDSHIELD WIPER CONVERTER REMOVAL a.

Remove the

wiper

motor as outlined in this

Chapter

under the

heading

WINDSHIELD WIPER MOTOR REMOVAL.

NOTE: The motor must be removed before the left hand converter must be removed before the

Rotate the

c.

Remove the

wiper

d.

Remove the

screws

e.

Remove the flexible drive shaft

CAUTION: Avoid f.

ns,

Remove the

arm

screw

attaching

can

can

be removed, and both of the

preceding

units

be removed.

on

the

wiper

arm

assembly (Ref. Figure 201).

assembly.

securing

bending

hand converter

clockwise to relax tension

b.

adjustment

right

the drive shaft seal on

assembly

to the

the left hand side of the converter.

the ends of the flexible drive shafts when

bolts

fuselage.

securing

the converter in

removing

the converfer.

place.

30-40-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANACE MANUAL

WINDSHIELD WIPER CONVERTER INSTALLA TION NOTE:

First install the

right

hand converter, then the left hand converter, and

Adjust the right hand converter until

b.

Secure the

c.

Attach the flexible drive shaft to the

d.

Adjust

e.

Connect the flexible drive shaft to the

hand converter in

the converter in

CAUTION: Make

with the

right hand

sure

attaching

g.

Install

assembly

arm

Reinstall the windshield

assembly

bolts.

and

place

adjust wiper

as

it is

placed

into

position,

then

bolts. are

properly engaged upon

with the

arm

attaching

installation.

screws.

tension.

motor as outlined in this

wiper

position.

side of the left hand converter

right hand attaching

in

position (Ref. Figure 201).

converter.

that the flexible drive shafts

Secure the drive shaft seal

wiper

with the

place

f.

h.

place

the left hand converter until the drive shaft is in the extreme clockwise

secure

the motor.

the drive shaft is in the extreme counterclockwise

a.

right

finally

Chapter

under the

heading

WINDSHIELD WIPER MOTOR INSIALLATION.

WINDSHIELD WIPER ADJUSTMENT NOTE:

Never operate the windshield

Run the windshield

wiper

wiper

to the PARK

on a

position.

dry

windshield.

If the

wiper

blades do not

from the center post of the windshield, or if the tension of the within 4.5 to 5.5 pounds, adjustment is required. a.

b.

c.

away from the glass. Insert a 1/3 inch diameter This will relieve blade tension against the glass.

Lift the arm.

wiper arm

wire and loosen the alien

Cut the

safety

enough

for removal.

Lift the

wiper arm

located d.

wiper

on

hub and

reposition

screw on

arm

come

at the

pin through

the hub end of the

wiper

to rest at

wiper

the hole

arm

approximately 2 inches attaching point is not

blade

on

each side of the

until the hub

can

be

wiper

spread

it until blade is 2 inches from windshield center post. An adjustment sleeve tinner teeth) and coarse touter teeth) adjustments.

the converter shaft has both fine

Reinstall the

arm

assembly

on

the drive shaft,

making

sure

that the

arm

is

pulled

up until the washer is in the

counterbore of the hub. e.

Tighten head

the alien head

screw

until the

with 0.032

safety

wire.

screw

from the holes in the

wiper

wiper

arm

is anchored

securely

to the drive shaft.

Safety

wire the alien

f.

Remove the

g.

Set the wiper arm to a tension load of 4.5 to 5.5 pounds at the wiper blade attaching point. Rotate the spring adjusting screw on top of the wiper arm with the wrench tChart 2, 30-00-00) designed for this purpose. Turn the screw clockwise to decrease or counterclockwise to increase the adjusting spring tension.

Page

yaM202

1/08

pin

30-40-00

arm.

a24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANACE MANUAL

WINDSHIELD HEA TING ELEMENTS RESISTANCE CHECK When

a

loss in windshield

heating

area

is

evident, check the dual level heating elements of the suspect windshield

for the proper resistance values. to terminal blocks

lower side of windshield.

a.

Remove

b.

Disconnect power leads from HI and LOW terminals.

c.

low range ohmmeter, measu re the resistance between the g rou nd terminal and the LOW terminal block. The resistance should be 0.89 ohms f 15%. Measure the resistance between the ground terminal and the HI

Using

glareshield,

required,

as

to

gain

access

on

a

on the temperature sensor should be tolerances, replace windshield as outlined in

terminal block. The resistance should be 0.65 ohms f 15%. Resistance 309 ohms

Chapter

15% at 70F. If resistance

56-10-00 under the

headings

readings

are

out of above

WINDSHIELD REMOVAUINSTALLATION.

d.

Reconnect power leads to HI and LOW terminals.

e.

Reinstallthe

glareshield.

WINDSHIELD ANTI-ICE CONTROLLER FUNCTIONAL CHECK WARNING:

Prolonged operation

of the windshield anti-ice heater

can cause

irreparable damage

to the

windshield. NOTE: The

following

checks

can

be made

utilizing

a

locally

manufactured variable rheostat

capable of varying

resistance from 320 ohms to 340 ohms.

the terminal blocks

a.

Remove the

b.

Disconnect the power leads from the LOW

NOTE:

glareshield

Use the windshield

to

gain

access to

ground post (G) for

c.

Disconnect the wires

d.

Turn the BATT switch ON and

e.

Check that the controller

on

the windshield

place

provides

(LP)

the lower outboard side of the windshield.

terminal and install

the test

sensor

on

a

28 VDC test

lamp.

light ground.

terminal block and install

a

variable rheostat.

the windshield anti-ice switch in the NORMAL

power to the windshield

(test lamp

should

position.

illuminate)

when the resistance is

set at 320 ohms.

lamp extinguishes

when the resistance is set at 340 ohms.

f.

Check that the test

g.

Turn the windshield anti-ice switch OFF.

h.

Turnthe BATTswitchOFF.

i.

Remove the 28 VDC test

lamp

from the LOW

(LP)

terminal and windshield

ground post.

Reconnect the power

lead.

j.

Remove the variable rheostat from the windshield

sensor

terminal block and reconnect the temperature

sensor

leads. k.

A24

Reinstall the

glareshield.

30-40-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANACE MANUAL

WINDOW DEFOG AIR FIL TER REI~IIOVAL (FL- I THRU FL-318, FM- I THRU FM- 10, WITH KIT NO. 130-9700-1 INSTALLED; FL-319 AND AFTER, FM- II AND AFTER) Remove electrical power from the

a.

airplane.

Remove aircraft seats, cabin side wall, and floor boards as underneath the cabin floorboards (Ref. Figure 202).

b.

required

to

gain

access

to window

defog pneumatic

tubing

NOTE: Metal

tubing

c.

defog pressure regulator transitions to plastic tubing beneath the plastic tubing then routes to the cockpit D windows and cabin side windows.

from the window

floorboards. The

pressure regulator and trace metal pneumatic tubing to clamped joints with plastic The filter is mounted in the plastic tubing 3 to 6 inches past the end of the metal tubing tone

Locate the window

pneumatic tubing.

defog

filter each side wall and

clamps and

d.

Loosen the

e.

Discard the old filter.

one

filter under forward

remove

floorboard).

the filter from the

airplane.

WINDOW DEFOG AIR FIL TER INSTALLA TION KIT NO. 130-9700- 1 a.

Position the

(FL- I

AFTER)

filter in the plastic tubing so that the directional arrow is pointing plastic tubing leading to the side windows (Ref. Figure 203).

away from the metal

tubing

plastic tubing with clamps.

b.

Install the filter in the

c.

Install the aircraft floor boards, cabin side walls, and seats.

d.

Restore electrical power to the

May

THRU FL-318, FIM- 1 THRU FM- 10, WITH

INSTALLED; FL-319 AND AFTER, FM- 1 I AND

new

and toward the

cabin

airplane.

30-40-00

P~i24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANACE MANUAL

WIPER ARM ARIUSTMENT SCREW

ALLEN HU\D scFlncv

DRIVE SHAR SEAL ASSEMBLY

ADJUSTMEHT SLEEVE

CONVEAtEF~

MOTOR

g03tie-tA Windshield Wiper Instarration

Figure

,,4

201

30-40-00

Page

yaM502

1/08

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANACE MANUAL

PLUMBING TO COCKPIT

DEFOG PRESSURE REGULATOR

SIDE WINDOW DEFOG

AIR FILTER

F.S. 143.00

F.S.

F.S.

122.00

143.00

(UNDER

EMERGENCY EXIT

WINDOW DEFOG

221.37

F.S.

F.S. 221.37

FLOORBOARD)

PLUMBING TO CABIN

F.S.

EMERGENCY EXIT

THE

312.50

WARM AIR

NOZZLES

WARM AIR

MANIFOLD

AIR FILTER FROM DEFOG

PRESSURE REGULATOR

w30e aJI512aaal

Cabin Window and Side Window

Figure

May

1/08Page

206

30´•´•40-00

Defog

202

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANACE MANUAL

PLASTIC

TUBING

PLASTIC

TUBING

METAL

TUBING

CLAMP FILTER LJ30B

031573~8

Window

Defog

Pneumatic Air Filter Installation

Figure

A24

203

30-4000

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

PROPELLER ELECTRIC DEICERS

propeller electric deicer system includes an improved single heating element deicer boot for each propeller blade, slip rings, modular brush assemblies, timer, control switches and an ammeter (refer to Figure 1 for location

The

registers the amount of current (26 beyond the switch limitations, an integral circuit breaker will shut off power to the deicer timer. The current flows from the timer through the brush assemblies to the slip rings, where it is distributed to the individual propeller deicer boots. Deicing is accomplished by raising the deicer boot surface temperature sufficiently to reduce the bond between ice and boot, allowing centrifugal force and scavenging air flow to sling ice from the propeller. To conserve power and effectively remove ice, power is provided to the deicer boots in timed intervals rather than continuously. The time interval between heating cycles is necessary to permit ice to form and build up slightly prior to removal. of the various

switch is turned on, the ammeter

to 32

If the current rises

components). When the AUTO amperes) passing through the system.

heating sequences for the deicer boots noted in the following section are the sequences during the normal operation. However, due to the fact that the timer does not return when the power is turned off, it may restart at any sequence. point

NOTE: The

evidence

Two control switches

are

located

on

the left

subpanel, just to the right of the pilot’s

control column, and

in

which

are

to any

given

are

placarded

PROP-AUTO-MANUAL. When the AUTO switch is activated, power to the deicer boots is cycled in gO-second phases. The first 90-second phase heats all deicer boots on the right propeller. The second phase heats all the deicer boots moves

from

on

the left

one

phase

propeller. The deicer timer completes one full cycle every three minutes. As the deicer timer to the next, a momentary deflection of the propeller ammeter needle may be noted.

propeller deicer system is provided as a back up to the automatic system. When the MANUAL switch is activated, power is applied to all heating elements on both props. The manual override switch is of the momentary type, and must be held in place until the ice has been dislodged from the propeller surface. Although the propeller ammeter will not indicate prop boot load in the manual mode, the loadmeters will indicate approximately a 5%

I

I

A manual

increase in load when the manual

aza

propeller

deicer

system is in operation.

30-60-00

NoPva~leg:Page

1

1

Corporation

Hawker Beechcraft

MANUAL SUPER KING AIR B3001B300C MAINTENANCE

O

oEFnosr 1\IR

LIGHTS LANOING

I ICE

Tlrl

NAV

000000

~up

OFF

ICE

PROTECTION PAOP

NORMI\L

11170

tisa~

~LltL /ENT

MINUIL

O00000 )(I

IEFT

PILOT ~OPILOT UEICE

u.lctO

VF

STPICL

j?iN

DOWN

Locn HEL

O

R

OFF

Q

I.~NUMG Gt~R

P)IOT

N~SE

´•1D~ ir

HICI(T

SVRMCE aAIKf.

STROBE

O O

LDG GEPR CONT

RIGHT

LEFT

O~NT1-ICE

PULL

BEACON

RECOG

WnffN

boo0"00

MWUPII.

LEFT FF

SILENCE

H~LnY

RIGH~T

TEST

o

PROP UMMETER

iOVERHEAD PANEL)

DEICE BOOTS

DEICE BOOTS AUTOMATIC

CONTROL SUBPANEL

SWITCH

SLIP RING´•------’ MODULAR BRUSH

n Y

DEICER TIMER

R-le-iq

/I

I

1

i"

~------SLIP r

MODULAR BRUSH

ASSEMRLY I’I:(CJP AMh4~TEli

RING

ASSEMBLY

MANUAL CONTROL

MANUAL PROP DEICE

CONTROL CIRCUIT BREAKER

SWITCH

MAIN SPAR---AUTO AND MANUAL PROP DEICE CIRCU17

BREAKERS

LEFT DEICE MANUAL OVERRIDE

RIGHT DEICE

OVERRIDE

RELAY

RELAY

H?00-3~1

12!1

Propeller Deicer Figure 1

voN2

Page

1107

30-60-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PROPELLER ELECTRIC DEICER -TROUBLESHOOTING The circuit breakers and ammeter

example, breaker;

a

can

low

reading

on

general nature of many electrical problems. For power-on condition indicates a short circuit or bad circuit high resistance problem in the system. Consequently, it is

be used to indicate the

circuit breaker that is unable to maintain

a

the ammeter indicates

a

a

recommended that the behavior of these items be noted

CAUTION:

Prolonged operation

prior

of the deice boots when the

to

initiating

propellers

the

are

specific troubleshooting procedures.

static may result in

severe

damage

to

the deice boots.

tracing electrical circuits and correct wiring information, refer to the applicable WIRING DIAGRAM MANUAL, Chapter 30 and Figure 101 in this chapter.

NOTE: For

I

Chart 101

Propeller Deicer System

Troubleshooting

Propeller Deice Ammeter Malfunction STEP 1

Is PROP AUTO circuit breaker

engaged?

or

Inoperative

The ammeter will indicate

zero

with the circuit breaker

disengaged. YES

NO

Engage

circuit breaker. If circuit breaker will not remain

check circuit for electrical short and

STEP 2

Does PROP AUTO switch function

through

repair

as

properly?

engaged,

Proceed to STEP 2

necessary.

The ammeter will indicate

zero

with

no

electrical power

the PROP AUTO switch.

YES

NO

PROP AUTO switch. Remove electrical power from the airplane and check continuity through the switch in the ON Check for

faulty

Proceed to STEP 3

position If the PROP AUTO switch is defective

STEP 3

Does

propeller ammeter

replace

indicate correct

the switch.

amperes?

Test electrical power into and out of the ammeter

shunt.

YES

NO

If the ammeter indicates other than the checked electrical power through the shunt, replace the ammeter.

A23

30-60-00

Page

voN101

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102

Propeller

Troubleshooting

Deicer

System

Propeller Deice Ammeter Readings Erratic STEP 1

Is the deice timer

operating correctly? YES

NO If

propeller ammeter indicates normal part time and zero current part time during a 90 second cycle (Ref. HEAT TEST, 30-60-00) to determine if the deicer is not heating (Ref. TIMER CHECK, 30-6000) to verify electrical power at pins on the timer. If 24 vdc is not indicated

on

the affected

pins

of the timer,

Proceed to STEP 2

replace the

timer. Is the electrical circuit between the timer

STEP 2

plug

and the deicer boot OK?

YES

NO

I I

I

Check electrical power at the terminal block located on the spinner bulkhead. If the electrical power is not at the terminal block, check the brush assembly terminals including the ground (Ref. Figure 101, Details C and

D).

Repair defects as necessary and check electrical wiring plug. Correct any loose or corroded connections. STEP 3

Is the resistance normal

to the timer

through the brush and slip ring assembly

and the deicer heaters?

YES

NO

through part of cycle and low current through the other part, perform the deicer resistance check. (Ref. DEICER RESISTANCE CHECK, 30-60-00). If ammeter indicates normal current

If resistance

Proceed to STEP 3

readings

not within

are

acceptable limits,

Proceed to STEP 4

take the

action outlined in the DEICER RESISTANCE CHECK,

appropriate 30-60-00 procedure. STEP 4

Is the resistance normal in the modular brush

assembly? YES

NO RESISTANCE

(Ref. MODULAR CHECK, 30-60-00).

For resistance

readings that are

Perform resistance check.

appropriate

not within

acceptable limits, take

Proceed to STEP 5

the

action outlined in the MODULAR BRUSH ASSEMBLY

RESISTANCE CHECK, 30-60-00

Page

BRUSH ASSEMBLY

30-60-00

procedure.

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

Chart 102

Troubleshooting

Propeller Deicer System (Continued)

Propeller Deice Ammeter Readings Erratic STEP 5

Is

airplane voltage normal? NO

YES Proceed to STEP 6

If amrneter indicates low current

throughout cycle, check for low voltage to the PROP AUTO switch (Ref. Figure 101 Detail B). Check I wiring for partially broken wiring, loose or corroded connections. Correct defects in the STEP 6

wiring

circuits

Are the connections between the

I I

applicable.

as

airplane power supply

and the timer

output OK? YES

NO

Proceed to STEP 7

triple bus power supply, the probable cause could be power input terminal of the switch to the plug at the timer.

Because of the from the

Repair STEP 7

any loose

or

corroded connections in the

area.

Are the electrical connections from the timer to the deicers OK?

YES

NO If

a

"Ricker" of the ammeter

of the

only part cycle, rough or dirty slip rings.

occurs

affected deicers and check for

in

locate the

Correct any loose andlor corroded connections between the timer and the brush assemblies. Clean, repair or replace slip rings.

Chart 103

Troubleshooting Radio Noise STEP 1

Are the brushes

or

Interference With

properly aligned

and not

Deicer

Propeller

System

Propeller

Deicers ON

wearing excessively? YES

NO

Proceed to STEP 2

Check brushes for proper alignment and excessive wear. Check for rough or dirty slip rings.

Realign or replace defective brushes. Clean, repair, adjust or replace the slip ring assembly as required. STEP 2

Is the

wiring

free of loose connections

NO

Repair

A23

or

replace wiring

as

required.

or

partially

broken wires?

YES Proceed to STEP 3

30-60-00

Page

voN301

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 103

Propeller

Troubleshooting Radio Noise STEP 3

or

Deicer

System (Continued)

Interference With Propeller Deicers ON

Are the PROP AUTOIMANUAL switches OK?

NO

YES

present with PROP AUTO switch ON and PROP MANUAL switch OFF, check for faulty PROP

Proceed to STEP 4

If radio noise is

AUTO switch. Reverse

positions

of the switches and if

radio noise is present, check for faulty PROP MANUAL switch Connect

jumper

a

terminals. If this

across

cures

the

suspected switch replace the faulty

the radio noise,

switch STEP 4

wiring routed away from

Is the deicer

the radio

wiring? YES

NO

Separate

Deicer wire bundle should be at least

the deicer and radio wire bundlesl

inches away from radio

components.

wiring

eight

and

components.

Chart 104

Propeller Deicer System

Troubleshooting

Rapid Propeller Deice Brush Wear STEP 1

Is brush

assembly

in

or

Frequent Brush Breakage

alignment? YES

NO Check brush

alignment

as

outlined with

Proceed to STEP 2

procedures

under PROPELLER DEICER SYSTEM INSPECTION, 30-60-00.

Realign STEP 2

Is the

or

replace

slip ring

in

the brush

assembly

as

necessary.

alignment? YES

NO

Check the slip ring

alignment

with

a

dial indicator.

run

To

align

the

slip ring, refer to

SLIP RING

ALIGNMENT,

properly aligned when they a true plane relative to the modular assembly.

Slip rings in

brush

are

30-60-00. To restore

roughened

or

damaged slip rings,

refer to

SLIP RING REPAIR, 30-60-00.

Page

voN401

1/07

30-60-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 105

Troubleshooting Propeller STEP 1

Propeller

Deicer

System

Deicer Boots Fail to Heat with PROP MANUAL Switch

Is MANUAL PROP DEICE CONTROL circuit breaker

engaged? YES

NO

Engage

circuit breaker. If circuit breaker

Proceed to STEP 2

disengages

before actuation of the PROP MANUAL switch,

an

electrical short exists between the circuit breaker and

Repair the

electrical short.

disengages only after

actuation of the

the PROP MANUAL switch.

If circuit breaker

PROP MANUAL switch,

an

electrical short exists

between the PROP MANUAL switch and the manual override

relay. Refer to the airplane WIRING repairs.

DIAGRAM

MANUAL and make STEP 2

Is PROP MANUAL switch OK?

NO

YES Proceed to STEP 3

Remove electrical power from the airplane and check continuity through the switch in the ON position.

Replace faulty STEP 3

switch.

Are the manual override and

relay

and electrical circuits OK?

YES

NO Check

to the

voltage (Ref. Figure 101,

input

terminal of the affected

Details G and

relay

I

H).

If electrical power is not indicated at the open circuit between the switch and the

relay, relay,

If electrical power is not indicated at the

relay output

correct

I I Check voltage at the output terminal of the affected

relay.

terminal, replace the relay.

A23

30-60-00

1/07

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DETAIL

E

DETAIL

TIMER AND PLUG

G 92031C

1

GROUND

IJ

oX2

Q

o

B

o

RH son

oX1 ooA

(IGROUND _

LH

II

II

aoa

MANUAL

O

OVERRIDE RELAY MANUAL PROP DEICE

DETAIL DETAIL

-To~JAIL

B IGROUND( hi I

1^..Uh

Al+

CIRCUIT BREAKERS

H

C

I OX-2

O

O

oX10

O

DETAIL

I

B

SHUNT AUTOMATIC

MANUAL

MODE SWITCH

DETAIL

MANUAL

OVERRIDE RELAY

C

DETAIL

MODE SWITCH

D

BrS~-hA--l

11

CI

I

LH BRUSH MODULE

RH BRUSH MODULE

ASSY

ASSY

GROUND 40A

5A

t~

CI

I

DETAIL F L~ MANUALPROP DEICE CONTROL

P

CIRCUIT BREAKER

GROUND

AUTO PROP

DEICE CIRCUIT 8300-351-130

BREAKER

Propeller Deicer Schematic

Figure

voN601

Page

1107

30-60-00

101

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

PROPELLERS ELECTRIC DEICERS

PROPELLER DEICER BOOT REMOVAL a.

Removethe

b.

Disconnect the deicer boot leads from the

c.

Remove the

propellerspinner.

the lead

clip securing

strap

spinner

to the

bulkhead.

spinner

bulkhead and the

clamp securing

propeller hub.

it to the

NOTE: The lead strap is isolated from the deicer boot by a terminal strip clamp and wire harness to facilitate replacement of the strap or heating element portion separately upon failure of either. d.

Using methyl propyl

ketone

and the blade, loosen

or

CAUTION: Unless the boot

damaging e.

Apply

(2

or

7, Chart 2, 30-00-00) to soften the adhesion line between the boot

of the boot

being

sufficiently to grasp scrapped,

removed is to be

it with vise

cushion

grip pliers

thejaws

similar

or a

of any

pulling

gripping

tool to

tool.

prevent

the boot surface.

slow, steady pull

a

toluol

one corner

on

the boot to

pull

it off the

propeller

surface while

continuing

to

the solvent to

use

soften the adhesive. f.

Remove the Chart 2,

remaining

adhesive from the boot and

propeller

blade with

methyl propyl ketone

or

toluol

(2

or

7,

1

30-00-00).

PROPELLER DEICER BOOT INSTALLA nON a.

on the propeller blade so that its centerline at the inboard end is adjacent to the split in propeller blade clamp and 1 inch outboard of the clamp, and the centerline at the outboard end falls on the blade leading edge. Be sure the lead strap is in the proper position to be clamped to the blade retaining clamp. (Ref. Figure 201, Detail A).

Position the deicer boot the

b.

Maskoff

c.

Remove the deicer boot and Use

a

an

areaapproximately

thoroughly clean the surface within the masked area on the propeller blade area. dampened with solvent (2 or 15, Chart 2, 30-00-00). For final cleaning wipe the solvent off clean, dry, lint free cloth to avoid leaving a film.

clean cloth

quickly

with

a

CAUTION: The metal and d.

Moisten

a

clean cloth with

surface of the deicer boot, e.

Thoroughly

mix adhesive

f.

dry humidity is

rubberparts

must be

thoroughly

clean to

assure

maximum adhesion.

methyl propyl ketone or acetone (2 or 15, Chart 2, 30-00-00) and clean changing the cloth frequently to avoid contaminating the clean area.

(4,

for at least

adhesive to if the

1

Chart 2,

one

30-00-00)

hour at 40"F

or

and

apply one

even

brush coat to the

above when the relative

between 75% and 90%. Do not

apply

humidity

propeller

humidity

is

unglazed

blade. Allow the

is less than 75%,

the adhesive if the relative

the

or

two hours

higher than 90%.

drying time, apply a second brush coat of adhesive to the propeller and one coat of unglazed surface of the deicer boot. It is not necessary to adhesive more than 1/2 inch of the deicer lead strap. Allow the adhesive to dry.

After

allowing

sufficient

adhesive to the

30-60-00

Page

voN102

1/07

I

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

g.

on the propeller, starting 1 inch from blade retaining clamp, making sure the lead strap position to clamp to the blade retaining clamp. Moisten the adhesive lightly with methyl propyl ketone or toluol (2 or 7, Chart 2, 30-00-00) and tack the boot center line to the blade leading edge. If the centerline of the boot deviates from the blade leading edge, pull up with a quick motion and replace properly. Roll firmly along the centerline with a rubber roller (Ref. Figure 201, Detail B).

Position the deicer boot is in

I

I

CAUTION: Never

use a

metal

or

wooden roller for this purpose, for

they

would

damage

the

element in

heating

the deicer boot.

pockets

i.

outwardly from the centerline to the edges of the boot. If excess material at the edges tends to form puckers, work them out smoothly and carefully with the fingers (Ref. Figure 201, Details D and E).

j.

Roll the

k.

Clean the blade with

I

trapping

air

Gradually tilting the roller, work the boot carefully over each under the boot (Ref. Figure 201, Details D and E).

I

Roll

tapered edges of the a

boot with

a narrow

steel stitcher roller.

clean cloth moistened with

careful not to let solvent

I

side of the blade contour. Avoid

h.

run

into the

edge of the

methyl propyl

ketone

or

toluol

(2

or

7, Chart 21 30-00-00). Be

boot.

i.

Apply one even brush coat of conductive edge sealer (6, Chari 2, 30-00-00) around the edges of the boot, allowing ’/16 to 1/8 inch of overlap on the boot and extending to the masking tape. Remove the masking tape after applying the conductive edge sealer to obtain a neater border.

m.

Install the

I

n.

clamp securing

the lead

strap

to the

Connect the lead terminals and install the terminal and the

clip

to

assure

enough

clip

propeller on

the

blade

retaining clamp.

spinner bulkhead. There must be no slack between the clip and the clamp on the blade to allow propeller

slack between the

feathering. curing time for the adhesive before running the engines and turning up curing time before operating the deicers.

CA UTION: Allow 12 hours and 24 hours

Page

30160100

the

propellers

AZ3

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

STRAP CLAMP DEICER BOOT

DETAIL

A

MASKING TAPE

DETAIL B

1

DETAIL

D

DETAIL

E 350-25 1-4

Propeller Deicer Boot Installation

Figure

A23

201

30-60-00

Page

voN302

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

PROPELLER DEICER BRUSH REPLACEMENT is made up of two modules. Each module consists of a plastic housing with an The modular units are stacked with a spacer and are held together with screws. When

The modular brush brush and

spring.

assembly

integral a

brush

out, it may be replaced separate from the entire module. Refer to Goodrich Corporation Report No. 68-04714K or subsequent in the King Air Series Component Maintenance Manual, P/N 101-590097-1;3, Chapter 30.

wears

CAUTION: When

replacing propeller deicer brushes, pounds to avoid damaging the brush

inch

NOTE:

Brush

is determined

must be

brushes with rods a.

hardware must be

attaching

During measurement, 1/16 inch of the brush should protrude from the protrusion of the brush when the module is installed on the airplane.

wear

module)

all

by inserting

a

pin

into

a

torqued

to

no more

brush module. This is the normal

hole in the back of the brush module. A brush

replaced when themeasurement (Ref. Figure 202).

than 18

modules.

is

125/64

Disconnect the wire harness terminals at the terminal

inches, for brushes without rods,

screws

entire ~03’ theinch for

/64

or

of the modular units that make up the brush

assembly. the modular units to the

mounting

bracket.

b.

Remove the screws, nuts and washers

c.

Remove the

d.

Replace each module with another of the same part number. The part number is etched into the surface of the plastic housing. Optionally, the brush alone may be replaced. Refer to Goodrich Corporation Report No. 68-04714K or subsequent in the King Air Series Component Maintenance Manual, P/N 101-590097-13, Chapter 30.

e.

Stack the modules and spacer

I

f.

assembly retaining

screws

securing and

separate the modules and spacer.

(Ref. Figure 203).

assembly screws so that the screw head fits in the recess in the spacer. Place the flat washer between housing and install the retaining nut. Make sure the assembly is "square" before tightening the assembly screws in place. Install the

the star washer and modular

g.

Place the modular units

on

the

mounting

bracket and insert the

bracket. One washer fits under the head of the h.

Before

installing

the retainer nuts, make

sure

screw

and

one

that the brushes

mounting

under the

are

aligned

through retaining nut. screws

with the

the modules and

slip rings such

that the entire

brush face contacts the copper rings. If the brushes do not align with the slip rings throughout the entire 360 degrees of slip ring rotation, install shims (P/N 1E1157) between the brush module spacer and the mounting bracket until the brushes i.

I j.

are

properly aligned

with the

approximate

center of the copper

ring.

retaining washers and nuts, making certain that 1/16 1/32 inch is maintained between slip ring surface. To prevent damage to the brushes, the brush modules should that the brushes contact the slip rings at an angle of approximately 2 degrees from perpendicular, toward the direction of slip ring rotation (Ref. Figure 204). install the

the brush

modules and the

be

angled

as

measured

Connect the terminals of the airplane system wire harness to the brush assembly.

Page

301~0100

same

so

designated terminals of the modular

M3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1-~5/54"

BRUSHES

WITHOUT RODS RODS

~3/5BRUSHESi- WIsH

r NOTE DURING THE MEASUREMENI ONLY 1/16 INCH OF BRUSH SHOULD BE ALLOWED TO PROTRUDE FROM THE BRUSH MODULE.

C96FL3082352

Determining

Brush Wear On Modular Brush

Figure

wlEE

C

Assembly

202

H%RNESS

MOUNIING BRACKET

3E2090 GRUSH

/i

.SSEI´•IG~Y

/:I

IEl 157

ir

;Iv’ BRUSH

MODULE 3E2090-1 (2 REO)

MOUNTING SCREWS

SPACEF? 4E2~18-4 350-351-128

ORIGINAL As Received ATP

A23

By

Modular Brush

Assembly Figure 203

30-60-00

1107

Hawker Beechcraft

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MOUNTING BRACKET

21 [r(

1

II II

I

I

MODULE

al

1 111

/--Q

I

ASSY

FWD

SLIP RING ASSY

-IC

1/32 INCH MIN 3/32 INCH MAX

0300-351-131

Modular Brush

Assembly Figure 204

I

Installation

TIMER CHECK

Experience

in the field has indicated that often the timer is considered defective when the

elsewhere. For this reason, the a.

following

test should be

performed

source

before the timer is removed

of the trouble lies

as

defective.

wiring harness disconnected at the timer and the deicer switch in the AUTO position, check the voltage pin B of the harness plug to ground. If no voltage is present the timer is NOT at fault. If system voltage is present at pin B, check the circuit from harness plug pin G to ground with an ohmmeter. If no circuit is indicated, the fault is in the ground lead rather than the timer. If ground connection is open, the timer step switch will not change position. With the

from

b.

ground and power circuits have been checked, connect a jumper wire between pin B of the timer receptacle and terminal B of the connector plug and from pin G of the timer receptacle to ground. With the deicing switch in the AUTO position, check the voltage at pin B of the timer (referenced to ground). The volt meter should indicate approximately 24 volts when the airplane battery is being used. Check pins D and F referenced to ground. Each pin should read 24 volts in sequence as follows:

After the

1.

Pin D

on

for 90 seconds

(heats right prop).

2.

Pin F

on

for 90 seconds

(heats

left

prop).

battery voltage, the on-time of each deicer boot may slightly exceed sequence time reposition itself to start at a given pin when the system is turned off, but will begin its cycling point where it stopped when the system was shut down. Cycling will then proceed in the order noted above.

NOTE: When

operating

on

noted above. It should also be noted that the timer does not

Nov

107Page

206

30-60-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

After

a

zero

before

voltage reading of 24 volts DC is obtained, hold the voltmeter probe on the pin until the voltage drops to moving the probe on to the next pin in the sequence. After the correctness of the cycling sequence has been established, turn the deicing system switch OFF at the beginning of one of the "on-time" periods and record the letter at which the voltage is present to facilitate performance of the following test.

HEA T TEST Before this test can be performed, the jumper wires installed for the timer test must be removed so the connector plug can be replaced in the timer receptacle. Two persons are required to perform this test: One in the flight compartment to turn the deicer system switch to AUTO while the person outside feels the deicer boots to see if they are heating properly. The deicer control is located on the left subpanel, just to the right of the pilots control panel. I By activating the PROP-AUTO switch, power to the propeller deicer boots is cycled in g0-second phases. The first 90 -second phase heats all the deicer boots on the right propeller. The second phase heats all the boots on the left I propeller. The deicer timer completes one full cycle every three minutes. The person

inspecting the propeller deicer boots must check to be certain all of the boots on the right propeller are heating throughout the first gO-second phase. If it is determined that the right propeller boots are heating properly, repeat the test for the left propeller deicer boots. If any irregularities are detected, a continuity check should be performed on the wiring from the timer to the brush assembly and the propeller terminal connections. CONTINUITY TEST

After

removing

the

plug from

the timer,

use an

continuity from:

ohmmeter to check the

a.

Pin D of the

plug

to terminal B of all of the deicer boots

on

the

b.

Pin F of the

plug

to terminal B of all of the deicer boots

on

the left

c.

Pin G of the

plug

to

d.

Ground to terminal C of all of the deicer boots

on

the

e.

Ground to terminal C of all of the deicer boots

on

the left

right propeller.

I

propeller.

ground. right propeller.

I

propeller.

DEICER RESISTANCE CHECK To check for incorrect resistance

or the presence of a short or open circuit at the brush to slip ring contact, disconnect the harness at the timer and check the resistance from each deicer circuit lead to ground with a low range

ohmmeter. If the resultant

readings are not 0.875 to 1.075 ohms, disconnect the deicer lead straps to measure the individually. Individual boot resistance should measure between 3.26 and 3.60 ohms. If the readings in the first check are not within the accepted limits but those in the second check are, the trouble is probably in the brush-to-slip ring area. If the readings in the second check are also off, the deicer concerned is damaged and must be replaced. heater resistance

MODULAR BRUSH ASSEMBL Y RESISTANCE CHECK To check for

an open circuit or high resistance in the brush assembly, measure the resistance from the face of the brush to its terminal stud or receptacle pin with a low range ohmmeter. If this resistance measures over 0.013 ohms,

locate and

repair the

cause

of the excessive resistance. If the resistance measured is infinite, locate and correct the

open circuit or replace the module. Check resistance between the two terminal studs resistance should not be less than 0.5 megohms.

or

receptacle pins.

30-60-00

This

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MAN UAL

SLIP RING ALIGNMENT properly aligned when they run in a true plane relative to the modular brush assembly. This condition can by attaching a dial indicator gage to the engine reduction gear housing in such a manner that a reading of the slip ring wobble may be obtained. To avoid error in the readings, rotate the slip rings slowly by pushing in on the propeller to take the play out of the thrust bearing. If the total runout over 360 degrees of rotation exceeds 0.008 inch, or 0.002 inch in any 4 inch are, the slip rings should be aligned. The

slip rings

are

be checked

a.

adjustment may be made to correct the slip ring wobble by varying the torque on Using the dial indicator to follow the points of maximum deviation, adjust the slip ring assembly to the prescribed runout limits by varying the torque of the mounting bolts, as required, within a range of 40 to 75 inch-pounds.

Approximately

a

0.012 inch

the attachment bolts.

b.

required for alignment, the slip ring assembly may be shimmed to within prescribed limits for true running by the addition of AN960C416L washers on the mounting bolts between the slip ring assembly and the spinner bulkhead. Install flat steel washers on each side of the star washer used between the slip ring and the spinner bulkhead to protect the bulkhead against damage. The use of aluminum washers or a star washer next to the spinner bulkhead may cause it to crack. If more than 0.012 inch of adjustment is

the

adjustments may affect the clearance between the brush modules and slip rings; consequently, slip ring alignment, a check should be made to ascertain that a distance of from 1/32 to 3/32 inch is maintained between the brush modules and slip ring surface.

NOTE: The above after

SLIP RING REPAIR

Structurally sound slip rings with roughened or damaged surfaces can be restored to serviceability by machining. Thoroughly clean slip rings with methyl ethyl ketone before beginning resurfacing. Mount the slip ring assembly concentrically in the lathe with not more than 0.002 inch wobble or runout over 360 degrees of rotation. Take a light cut for a smooth finish and cut no deeper than is required to remove the surface damage. The contact surfaces of the slip rings must be parallel within 0.008 inch and flat within 0.008 inch overall (not exceeding 0.002 inch from flat over a 4 inch are). If necessary, undercut the insulation between slip rings to a depth of 0.020 to 0.030 inch below the contact surface of the slip rings. The width of the slip ring MUST NOT be reduced by more than 0.005 inch in this operation. The contact surface of the slip rings must have a finish of 29 to 35 microinches. Burr the edges, reinstall and align the slip rings. the thickness of the slip ring at any point must not be less than 0.187 inch. NOTE: If the solder the

slip ring

or

braze connection

must be

on

the underside of the

slip ring

is

exposed by

the

machining operation,

replaced.

PROPELLER DEICER SYSTEM INSPECTION

components of the deicer system should be inspected periodically for incipient defects. The following inspections is to provide a means for detecting and correcting such defects before they deicer system inoperative.

The various the

a.

Check for fuel and oil

excessively b.

leakage

and to cut into the

onto the brush modules and

slip rings. Stop

purpose of render the

slip rings. This will cause the brushes to wear repair the brush modules and slip rings.

all leaks. Clean and

Lock the brakes and operate the engines at near take off power. Turn the deicer system switch to AUTO and observe the ammeter for at least 1 cycle. If the ammeter needle does not rest within the shaded band, except flicker that may occur at programmed intervals when the step switch of the timer troubleshooting chart for the probable source of trouble. for

Page

a

30160100

cycles, refer

to the

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

With the

shut

engines

off,

turn the deicer switch to AUTO and feel the deicer boots

on

the

proper sequence of heater operation. The presence of local hot spots indicates surface heaters, which should be repaired before more serious damage develops. d.

Remove the spinner dome and open all access doors pertaining to the wiring and components of the deicer system. Turn the deicer switch to AUTO and station an assistant in the flight compartment to observe the system ammeter. Flex all accessible wiring, particularly the lead straps, leads from the slip ring assembly and the firewall electrical connectors and their wiring. Any movement of the ammeter, other than the cycling flickers that may

e.

propellers for the damage to the deicer

occur

programmed intervals,

at

indicates

short

a

or

open circuit that must be located and corrected.

To extend the life of the lead strap between the hub clamp and at least inch from the existing location of the bend.

clip, reposition

the bend in the

strap

to

a

point

1/2

f.

Check for

g.

Check for radio noise radio

h.

damaged

gearturned

in AUTO

or

probable

source

on.

springs

and for

worn or

radio compass interference

by operating

If, under these conditions, noise

disappears

damaged brushes.

or

when the

the

interference

at near takeoff power with the when the deicer system is operated

engines

occurs

system is OFF, refer to

the

troubleshooting

chart for the

of trouble.

Check all clamps,

Closely

or

or

MANUAL mode and

for loose, broken i.

brush rods

clips, mountings and electrical missing safety wire.

connectors for

tightness

and electrical soundness. Check also

or

check the deicer boots for wrinkled, loose

or

torn areas,

particularly

at the outboard end and at the

point

where the strap passes under the hub clamp. Look for abrasions or cuts along the leading edge and the flat or thrust face. If the heater wires are exposed in damaged areas or if the rubber is found to be tacky, swollen or

deteriorated

j.

las

from contact with oil

or

solvent

fluids), replace the damaged

deicer boot.

Check that the hub

clamps are tight. Inspect for cracks or other damage. Check to see that the cushioning missing or damaged in the area under the hub clamp or on the edge of the spinner dome. Manually operate the propeller from "low pitch" to "feathering" while checking that the deicer lead straps do

material is not

come

k.

Check the grease

I.

If

or

slip rings for gouges, roughened surfaces, cracks, burned or discolored areas, and for deposits of oil, dirt. Clean greasy or contaminated slip rings with CRC-2-26 solvent(l6, Chart 2, 30-00-00).

uneven wear or

the

not

under tension.

wobble is detected, check the

alignment, push

of rotation is

over

in

on

the

0.008 inch

propeller to or

alignment

of the

slip rings with a dial indicator. While checking bearing end play. If the runout over 360 degrees inch are, refer to the paragraph on SLIP RING

eliminate the thrust

exceeds 0.002 inch in any 4

ALIGNMENT. m.

Examine the modular brush assembly mounting bracket and module housings for cracks, deformation are not chafed or binding.

or

other

indications of damage. Check for tight connections and that the leads n.

Check to

slip ring over 360 degrees of rotation. If the brush is not properly aligned, add shims under the brush modules or elongate the holes in the mounting bracket to raise or lower the the brush modules to the proper position. If the brushes ride BOTH high and low with respect to the slip rings in 360 degrees of rotation, the slip ring assembly is eccentrically mounted and the spinner bulkhead must be replaced.

o.

Check for proper

see

that each brush rides

fully

on

its

spacing between the brush modules and slip rings as indicated in Figure 204. If this distance specified limits, loosen the mounting screws and reposition them in the elongated holes until the modules are properly positioned. If necessary, shims can be added between the thrust bearing plate and mounting bracket until the brush assembly is properly located. is not within the

n23

30-60-00

Page

voN902

1/07

I

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

p.

I

angle of the brush modules in relation to the slip rings. If this angle is not approximately 2 degrees Figure 204, loosen the mounting screws and reposition the brush modules until the proper angle exists between the brush modules and slip rings. It should be noted that the spacing established in the preceding step must also be maintained after the proper angle is established. Estimate the

as

q.

indicated in

system operating and a man in the flight compartment observing the ammeter, visually inspect physically flex the wiring from the brush assemblies to each component of the deicer system and to the airplane power supply. Jumps of the ammeter needle, other than the momentary flicker that may occur when the timer switches at programmed intervals, indicate loose or broken wiring in the area under examination at the moment. In such instances, continue to flex the wiring in the area that first indicated trouble while checking the continuity through the individual wires of the affected harness until the source of trouble is located. Use the wiring diagram to trace the circuitry of the deicer system. With the deicer and

Page

30-60-00

P1~3

CHAPTER

INDICATINGI RECORDING SYSTEMS

Ray~heon Aircraft BEECH SUPER KING AIR MODEL B3bd/B3i)OC MAINTENANCE MANUAL

INDICATING/RECORDING SYSTEMS

CHAPTER 31

TAB~E OF CONTENTS

PAGE

SUBJECT 31-50-00

Central

Warning Systems Description

Annunciator

System

and

1

Operation

1

Power

2

Dim Control Central

Warning Systems-

6

Maintenance Practices

Warning

Annunciator Panel Removal

6

Warning

Annunciator Panel Installation

6

Caution/Advisory/Status

Annunciator Panel Removal

6

Caution/Advisory/Status

Annunciator Panel Installation

6

A12

31 -CONTENTS

Mar

9/01Page

1

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CHAPTER 31

INDICATING/RECORDING SYSTEMS

LIST OF PAGE EFFECTIVIN CHAPTER-SECTION-SUBJECT

31-Effectivity

31-Contents

31-50-00

A12

PAGE

DATE

1

Mar 9/01

2

Mar 9/01

1

Mar 9/01

2

Mar 9/01

1

Mar 9/01

2

Mar 9/01

3

Mar 9/01

4

Mar 9101

5

MarS/O1

6

MarS/O1

7

MarS/O1

8

Mar 9/01

9

Mar 9/01

31-EFFECTIVITY

Mar

9/01Page

1

Raytheon Aircraft SEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CENTRAL WARNING SYSTEMS

Figures 1,

DESCRIPTION AND OPERATION

2 and 3

A central annunciator system is installed in the airplane to alert the crew of any malfunction in critical airplane systems. The annunciator system consists of two master warning light and two master caution light switches in the

glareshield, a warning annunciator panel iri the center of the glareshield panel on the pedestal below the main instrument panel.

and

a

(CAS)

caution/advisory/status

annun-

ciator

The red

warning

annunciators indicate

amber caution annunciators indicate

a

hazard which

a

requires immediate crew alerting requires immediate attention,

diate corrective action. The white status annunciators indicate but does not

initiated

or

and corrective action. The

malfunction which

a

but not

necessarily

condition which could be either normal

or

imme-

abnormal

require immediate crew alerting or action. The green advisory annunciators confirm that an operation by the flight crew is occurring properly and does not require immediate crew alerting or any fur-

selected

ther action.

NOTE The green LH and RH autofeather arm lights are separate from the CAS annunciator panel. Airplanes FL-1 thru FL-119 and FL-121; FM-1 thru FM-8, have the autofeather-arm lights located in the

glareshield

the

pilot’s side. Airplanes FL-120 and FL-122 and after; FM-9 and after have two (AFX) lights mounted adjacent to the engine ITT instruments in lieu of the rectangular autofeather-arm lights in the glareshield. on

round autofeather

arm

The master warning and master caution

panel. warning legends legends Anytime a warning or caution annunciator is illuminated, the master waming or master caution lights are illuminated. The master warning or master caution lights will flash until the legend face on either light (pilot or copilot) is pressed, at which time a signal is applied to the reset input on the A125 annunciator-control pcb and the flashing lights are extinguished. The annunciator will remain illuminated until the fault signal is removed from the annunciator panel and the master warning or caution lights will not flash until another annunciator fault signal is applied to the system. The advisory and status annunciators are not accompanied by a flashing master light when they are illuminated. Charts 1 and 2 provide a list of the warning annunciators and caution/adviso~y/status annunciators in each panel.

The

lights are

mounted in

pairs

on

either side of the

read MASTER WARNING RESET and the Caution

A PRESS-TO-TEST switch located

on

the

copilot’s

side of the

of the annunciators and master

warning

all annunciators in both

and all four master

panels

and caution

warning

annunciator

annunciator

panel

is used to test illumination

the test switch, the operator will illuminate and caution lights. Dim control over the annunciator

lights. By pressing

warning automatically controlled through the ambient-light sensor circuit. information on the light dimming circuit.

panels

warning

read MASTER CAUTION RESET.

is

Refer to DIM CONTROL for

more

detailed

ANNUNCIA TOR SYSTEM POWER The ANN POWER and ANN IND circuit breakers located nunciator

on

the

right

circuit breaker

panel provide

power to the

an-

system.

The ANN POWER circuit breaker

supplies power to the following units: MASTER WARNING indicator, MASTER CAUTION indicator, annunciator control pcb and the annunciator PRESS-TO-TEST switch. When actuated, the PRESS-TO-TEST switch supplies lamp test power to the following: annunciator control pcb, annunciator fault-detect No.l

pcb, annunciator fault-detect

No. 2

pcb,

annunciator fault-detect No. 3

pcb, left

stop pcb, left advisory light test and the hydraulic landing gear pcb. The above pcb’s card rack shown in

aln

Chapter

vane

are

sense, left

located in the

ground-idleprinted circuit

39-21-00.

31-50-00Page

1

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

The ANN IND circuit breaker

provides power to illuminate the annunciators on the CAUTIONI ADVISORY/STATUS panel and the GLARESHIELD panel. When a fault occurs in one of the systems, a signal is sent to the annunciator panel illuminating the annunciator. Refer to the Beech Super King Air B300 Wiring Diagram Manual for detailed schematics of the annunciator system. DIM CONTROL

Transistors 0112, 0113 and 0114, located in the the

printed circuit card rack, are used in the dimming circuit for the CAS annunciators, annunciators, warning landing gear control-handle lights, firewall shutoff valve switch lights,

gear downlock lights and the prop synchrophaser switch lights. The dim mode is automatically selected when the following conditions are met: either generator is on line, the overhead floodlights are OFF, the pilot’s flight instrument lights are ON and the ambient light level in the flight compartment las sensed by an ambient light sensor located in the overhead control

matically

panel)

is below

a

preset value. Unless all these conditions

met, the bright mode is auto-

are

selected.

NbTE The master

warning

and caution

lights

are not

dimmed in the dim mode.

CHART1 WARNING ANNUNCIATORS

NOMENCLATURE

COLOR

CAUSE FOR ILLUMIDJATION

#1 AC BUS

Red

#1 AC bus failure.

#2 AC BUS

Red

#2 AC bus failure.

L FUEL PRES LO

Red

Fuel pressure failure

on

left side.

R FUEL PRES LO

Red

Fuel pressure failure

on

right side.

L OIL PRES LO

Red

Oil pressure failure

on

left side.

R OIL PRES LO

Red

Oil pressure failure

on

right

L BLEED FAIL

Red

Bleed-air line failure

on

left side.

R BLEED FAIL

Red

Bleed-air line failure

on

right

CABIN DIFF HI

Red

Cabin differential pressure exceeds 6.9

CABIN ALT HI

Red

Cabin altitude exceeds 12,000 feet.

’A/P TRIM FAIL

Red

Improper trim

’A/P FAIL

Red

Autopilot

Optional equipment

Mar

or no

side.

side.

trim from

monitor has sensed

autopilot a

psi.

trim command.

failure.

if installed.

9/0131-50-00

A12

Raytheon Aircraft BEECH SUPER KING AIR MODEL

OC

L

L CHIP

L ENG

L BL

GEN

L GEN TIE

L NO FUEL XFR

DETECT

ICE FAIL

L

AIR OFF

FUEL OTY

AUTOFTHER OFF

B3~d/B300C

MAINTENANCE MANUAL

L PITOT HEAT

R PITOT

HYD FLUID LOW

RVS NOT READY

BAT TIE OPEN

DUCT

BATTERY CHARGE

PITCH TRIM OFF

HEAT

OVERTEMP

GEN TIE OPEN

R

NO FUEL

R

EXT PWR

R FUEL OTY

NOT ARMED

OXY

XFR

RUD BOOST

OFF

DC GEN

R

CHIP DETECT

R

R

ENG

R BL

ItE FAIL

AIR OFF

´•´•ri

IGNITION ON

L

L ENG At~TI-ICEIFUEL CROSSFEED

WING OEICE

L

PROP

i

L BK DETCE ON

PITCH

MAN TIES CLOSE

PROP GND SOL

ELEC HEAT ON

CABIN ALTITUDEILDG/TAXI LIGHT

.´•il

L

BK DEICE

IGNITION ON

R

TAIL DEICE

ON

cON1 NI

PROP

a

PITCH

AIRPLANES WITH

BATTERY CHARGE (FL-I THRU FL-214; FM-I THRU LEAVE BLANK (FL-215 THRU FL-228; FM-IO) GND SOL

PROP

(FL-115 THRU FL-288:

L GEN TIE OPEN

CHIP DETECT

L N) FUEL XFR

ENG ICE FAIL

L

ANTI-ICE

OPTIONAL

L DC GEN

L

R

PASS OXY ON

[FL-I THRU FL-228;FM-I THRU FM-IO KIT 130-3017-1 INSTALLED) ´•+i

R ENG

L FUEL

BL AIR OFr

HYD

FLUID LOW

BAT TIE OPEN

FM-9

AND FM-IO)

RVSNOTREADY

EXT

PITCH TRIM OFF

R

R CHIP DETECT

NO FUR XFR

R

PWR

OXYNOTARMED

R DC GEN

RGENTIEOPEN

DUCT OVERTE~P

OTY

AUTOFTHER OFF

FM-91

F~L OPI

RUDBOOSTOFF

R

ENG

ICE FAIL

R

BL AIR OFF

ii

L

PITOT

HEAT

PROP

IGNITION ON

L

LENGANTI-ICE

GND SOL

FL~LCROSSFEED

A

i

WING DEICE

L

PROP PITCH

i

ii

L

ENG ANTI-ICE

R

PITOT HEAT

R

IGNITION ON

t

BK DEICE ON

CABIN ALTITUDE

MAN TIES CLOSE

ELEC HEAT OJ

LOG/TAXI LIGHT

PASS OXY ON

R

BK DEICE ON

AIR COND NI

TAIL DEICE

R

PROP

PITCH

OPTIONAL OPTIONAL FL-289 AND AFTER; KIT 130-3017-5 INSTALLED

FM-II

AND AFTER AND AIRPLANES

WITH mmouu

Caution/Advisory/Status

Annunciator Panel

Figure

A12

Legends

1

31 50-00

Page

3

Mar 9/01

Ral~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL CHART 2

CAUTION/ADVISORY/STATUS NOMENCLATURE

(CAS)

ANNUNCIATORS

COLOR

CAUSE FOR ILLUMINATION

L DC GEN

Yellow

Left generator off the line.

L GEN TIE OPEN

Yellow

Left generator bus isolated from the center bus.

HYD FLUID LOW

Yellow

Hydraulic fluid

RVS NOT READY

Yellow

in the power

pack

is low.

Propeller levers are not in the high landing gear extended.

rpm, low

pitch position

with R GEN TIE OPEN

Yellow

Right generator

bus isolated from the center bus.

R DC GEN

Yellow

Right generator

off the line.

L CHIP DETECT

Yellow

Metal contamination in the left

L NO FUEL XFR

Yellow

No left

BAT TIE OPEN

Yellow

Battery

DUCT OVERTEMP

Yellow

Duct air too hot.

R NO FUEL XFR

Yellow

No

R CHIP DETECT

Yellow

Metal contamination in

L ENG ICE FAIL

Yellow

Left

L FUEL QTY

Yellow

Left fuel

oil is detected.

engine

fuel transfer.

auxiliary

isolated from generator buses.

right auxiliary fuel

engine selected

transfer.

right engine

oil is detected.

anti-ice system is

inoperative.

less than 30 minutes continuous

quantity

power. BATTERY CHARGE

I

Yellow

Battery charge

EXT PWR

Yellow

External power connector is

R FUEL QTY

Yellow

(FL-1

thru FL-214; FM-1 thru

rate is too

high.

FM-9)

Right fuel quantity

plugged

in.

less than 30 minutes

remaining

at

maximum continuous power. R ENG ICE FAIL

Yellow

Right engine

L BL AIR OFF

Yellow

Left bleed-air flow control valve is closed.

AUTOFTHER OFF

Yellow

selected anti-ice system

Autofeather switch is not armed and

inoperative.

landing gear is

ex-

tended. PITCH TRIM OFF

Yellow

Electric trim

de-energized by a trim

disconnect switch

the control wheel with the PITCH TRIM switch

pedestal

turned

Yellow

Oxygen arming handle charge.

RUD BOOST OFF

Yellow

Rudder boost switch OFF.

R BL AIR OFF

Yellow

Right bleed-air flow

I

R PITOT HEAT

Yellow

Right Pitot Heat

I

’L PITOT HEAT

Yellow

Left Pitot Heat is

9/01Page

4

31-50-00

on

the

on.

OXY NOT ARMED

Mar

on

is

not

pulled

or

system failed

to

control valve is closed.

inoperative

inoperative

A12

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL CHART 2

CAUTION/ADVISORY/STATUS NOMENCLATURE L IGNITION ON

(CAS)

ANNUNCIATORS

COLOR Green

(CONTINUED)

CAUSE FOR ILLUMINATION Left

ignition

and

engine

start switch is on,

nition system is armed and left 17%. L ENG ANTI-ICE

Green

Left

FUEL CROSSFEED

Green

Crossfeed is selected.

Yellow

28 vdc is

PROP GND SOL

(FL-115

and

After; FM-9 and After)

R ENG ANTI-ICE

engine

anti-ice

being

vanes

in

delivered to

or

left

engine torque

position

one or

for

both

icing

auto-ig-

is below

conditions.

ground

idle

pitch

stop solenoids. Green

Right engine

anti-ice

in

vanes

position

for

icing condi-

tions. R IGNITION ON

Green

Right ignition and engine start switch is on, or right autoignition system is armed and right engine torque is below 17%.

WING DEICE

Green

Wing

L BK DEICE ON

Green

Left brake deice system in

MAN TIES CLOSE

Green

Manually

ELEC HEAT ON

Green

Electric heat is

Green

Right

TAIL DEICE

Green

Horizontal stabilizer surface deice system in operation.

L PROP PITCH

White

Left

CABIN ALTITUDE

White

Cabin altitude exceeds 10,000 feet.

LDGTTAXI LIGHT

White

Landing light(s)

PASS OXY ON

White

Passenger

AIR COND N1LOW

White

Right engine

R PROP PITCH

White

Right propeller

R BK DEICE ON

’Optional equipment

A12

surface deice system in operation.

operation.

closed generator bus-ties. on.

brake deice system in

propeller is

below the

or

taxi

operation.

flight

light

oxygen system

on

idle stop.

with

landing gear

up.

charged.

N1 too low for air

is below the

conditioning

flight

load.

idle stop.

if installed.

31-50-00

Mar

9/01Page

5

Ral~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CENTRAL WARNING SYSTEMS

MAINTENANCE PRACTICES

WARNING ANNUNCIATOR PANEL REMOVAL

Figures

2 and 3

a.

Remove electrical

b.

Remove the four

powerfrom

screws

the

securing

airplane. the

plates

and the

warning

annunciator

to the brackets in the

panel

glareshield. c.

Swivel the

warning

annunciator

panel

to clear the brackets and

pull the panel

far

enough

out of the

glareshield

to reach the electrical connector.

d.

Disconnect the electrical connector and

remove

the

warning

annunciator

panel

from the

airplane.

WARNING ANNUNCIA TOR PANEL INSTALLA TION

Figures 2 and 3 a.

warning annunciator panel glareshield.

Connect the electrical connector to the

brackets and insert the

in the

panel

b.

Secure the

c.

Restore electrical power to the

plates

and the

warning

annunciator

panel

and swivel the

panel far enough

to clear the

to the brackets with the four screws.

airplane.

CA UTION/AD VISOR Y/STA TUS ANNUNCIA TOR PA NEL REMO VAL

Figure

4

a.

Remove electrical power from the

b.

Remove the six

c.

Remove the four

screws

d.

Pull the panel far

enough

e.

Disconnect the electrical connectors and

screws

securing

airplane.

the face

securing

plate

the CAS

to the CAS annunciator

panel

to the instrument

out to reach the electrical connectors remove

on

panel.

panel. the back of the CAS

the CAS annunciator

panel

from the

panel.

airplane.

CA UTION/AD VISOR Y/STA TUS ANNUNCIA TOR PANEL INSTALLA TION

Figure

4

a.

Connect the electrical connectors to the CAS annunciator panel.

b.

Align

c.

Secure the face

d.

Restore electrical powerto the

Mar

9/0131-50-00

the CAS annunciator

plate

panel with the pedestal

to the CAS annunciator

cutout and secure with four

panel

with six

attaching

attaching

screws.

screws.

airplane.

nln

Raytheon Aircraft SEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

I. 2. 3. 4.

5. 6. 7. 8. 9. 10. II.

12.

MASTER WARNING LIGHT SWITCH MASTER CAUTION LIGHT SWITCH LH AUTOFEATHER ARM LIGHT RH AUTOFEATHER ARM LIGHT EXTINGUISHER PUSH SWITCH PRESS-TO-TEST SWITCH DISCHARGED LIGHT L ENGINE FIRE SWITCH i FW VALVE CLOSED SWITCH PUSH TO ACTUATE FIREWALL ARM FIRE EXT SWITCH FUEL VALVE R FW VALVE CLOSED SWITCH R ENGINE FIRE SWITCH

Xo~

C 2

3

5

4

5

6

t;J

dXoi_m~ 1

7 8

DETAIL

i 9

10

I

1

1 I

1

~110

7 12

A

DETAIL

B

B 5

7

5

1‘2

8

9

Glareshield Panel

A12

7

lOoETAILC

C94FL3181442 t

Assembly (FL-1 thru FL-119, FL-121; Figure 2

PM-1 thru

FM-8)

31 I50-00

Mar

9/01Page

7

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

i.

3. 4.

5. 6. 7. 8. 9. 10.

MASTER WARNING LIGHT SWITCH MASTER CAUTION LIGHT SWITCH EXTINGUISHER PUSH SWITCH PRESS-TO-TEST SWITCH DISCHARGED LIGHT L ENGINE FIRE SWITCH L FW VALVE CLOSED SWITCH R FW VALVE CLOSED SWITCH R ENGINE FIRE SWITCH COCKPIT VOICE RECORDER MIKE

Xo´•s~ d3,

3

2

C

6

"1"11

57

DETAIL

i

H-l"-l--

4

I---l-R

1

3

9

2

Il´•-,u

8510

1

A

DETAIL

B

B 3

6

5

7

DETAIL

3

8

5

9

C

cs4R3lel3as c

Glareshield Panel Assembly (FL-120, FL-122 and After; FM-9 and After)

Figure

Page

raM8

9/01

31-50-00

3

A12

Raytheon Aircraft BEECH SUPER KING AIR MODEL B30b/B~dOC MAINTENANCE MANUAL

DETAIL

DETAIL

II

O

o

DETAIL

B

1.

SCREW(G)

3.

CAUTION/ADVISORY/STATUS ANNUNCIATOR PANEL ELECTF~ICAL CONNECTORS

4

_y

C

MS24693-BB24 FACE PLATE

A

cslolst~

Caution/Advisory/Statu

s

Ann unciator Pane I Rem ova I

Figure

A12

4

31-50-00

Mar

9/01Page

9

CHAPTER

LANDING GEAR

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 32

LANDING GEAR

TABLE OF CONTENTS

PAGE

SUBJECT 32-00-00

Landing Gear Description and Operation SpecialTools and Recommended Materials.

................1 .............2

32-10-00

Main Gearand Doors- Maintenance Practices

Main Gear Shock Absorber

..........201

................._

Servicing.

................201

Lubrication.

........._

Main Landing Gear Removal Main Landing Gear Installation

....202 ...202

GearTorque Knee Removal Main GearTorque Knee Installation Main GearDrag Brace Removal. Main Gear Drag Brace Installation Main

.204 .........____

.204

.........____

.........____

.........___._

........._._._._

........._._._._

.206

........._._._._

206

32-20-00 Nose Gearand Doors

Maintenance Practices

..........201

........._._._._

Nose GearStrut

Servicing Landing GearShimmy Damper.

.......201 ..202

Lubrication. Nose

Landing

........._

Gear Removal

....203

Nose Landing Gear Installation.

..203

Knee Removal

NoseGearTorque NoseGearTorque Knee Installation. Nose Gear Drag Brace Removal NoseGearDrag Brace Installation

.204

.204 .206

.207

32-30-00

Extension and Retraction

Description

and

Operation

......1

Extension and Retraction -Troubleshooting Time Delay PCB

............101

.........____

Hydraulic Power Pack Assembly Gear-up Pressure Switch Gear-up Pressure Check Valve, System Pressure Relief Valve

.........______

.........___________

.........____

Hand

Pump Dump Valve,

........._____

Extension and Retraction -Maintenance Practices.

........._____

........._____

Landing Gear Components in LH Center Hydraulic System Servicing Filling and Bleeding The Landing Gear Hydraulic System. BleedingThe Main GearActuator. Bleeding The Nose Gear Actuator BleedingThe PowerPack.

Section

.........____

........._.____

...............__

.........201

.........___________

.202 .202 .206

..............__

.........__......

........._.

........._____

........._.____

........._.____

........._.____

111

......201

.........___________

a25

.110

....110

Vent Valve and Thermal Relief Valve .....110

.........___.___

Access Provisions for

.........___________

........._.____

207

......208

32-CONTENTSPage

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 32

LANDING GEAR

TABLE OF CONTEIVTS

(CON~NUED) PAGE

SUBJECT Bleeding The

211

Accumulator.

212

Bleeding The Service Valve. BleedingThe Emergency E~ension Hand Pump Hydraulic Landing GearFill ReservoirScreen. Landing GearHydraulicSystem FilterReplacement.

213

214 214

Landing Gear Bleed Air Pressure Overboard Relief Orifice Screen Landing Gear Power Pack Filter Screens Cleaning and/or Replacement Gear-up and Gear-down Port Screens (Sperry-vickers Power Pack) Finger Screen Cleaning (Airight Power Pack) Emergency Extension Hand Pump Suction Line Filter Removal. Emergency Extension Hand Pump Suction Line Filter Installation

........._

215 216 216 217

........._

219

219

Power Pack Removal. PowerPack Installation

........223

224

Power Pack MotorRemoval

224

Power Pack Motorlnstallation

Sperry-Vickers SelectorValve Assembly Sperry-Vickers SelectorValve Assembly Gear-up Pressure Switch Removal Gear-up Pressure Switch!lnstallation.

Removal.

224

Installation

226 226

.........___.....

226

Fluid Level SensorRemoval

227

Fluid Level Sensor Installation.

227

Hydraulic Hydraulic

Fluid Fill ReservoirRemoval

227

Fluid Fill Reservoir Installation.

228 230

Accumulator Removal Accumulator Installation

........230

Service Valve Removal

231

Service Valve Installation.

232

Emergency Emergency

Extension Haand Pump Removal. Extension Hand Pumplnstallation

233 233

NoseGearActuator Removal Nose GearActuatorClevis

235

Inspection.

236

Nose GearActuator Installation.

236

Main GearActuator Removal.

238

Main GearActuatorClevis

240

Inspection

Main GearActuatorlnstallation

240

Main GearActuator

241

Bearing Support Inspection Landing Gear Rigging Operating The Landing Gear with The Emergency Extension OperatingThe Landing Gearwith An External Pump Nose Gear Rigging Main Gear Rigging. Main GearActuatorAdjustment Landing GearDoors. NoseGear Door Rigging. Main GearDoorRigging Hydraulic Landing Gear Plumbing LeakTestAnd Cleaning

Page

beF2

1/09

32-CONTENTS

Hand

Pump

242 243 244 247

252 253 253 255 257

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 32

LANDING GEAR

TABLE OF CONTENTS

(CONTINUED)

SUBJECT Repair

PAGE

of

Hydraulic System Plumbing.

........._____

...........____

................259

32-40-00

Wheels and Brakes

Description

Main Wheel Assemblies Nose Wheel

Assembly

and

Operation

........._____

.............___

........._____

........._____

........._____

...........1

........._____

........._____

Tires

System Assembly Parking Brake Valves Wheels and Brakes -Troubleshooting Brake

Hydraulic

Brake

........._____

.........2

Wheelsand Brakes- Maintenance Practices Wheel and Brake

Servicing.

.101

................._

................._

.........._.......

................._

............201

................._

.....201

Tires

Sealing Minor Leaks Brake System Servicing

of Rim-inflated Tubeless Tires ................._

Brake Fluid Reservoir Pressure

Equalization

..202

................._

Line and Orifice

..............._._

Cleaning .........___

the Brake

Bleeding System. Gravity Bleeding ..........._ Pressure Bleeding Brake Bleeding (Using a Pressure Pot)...: Brake Bleeding (Using an Electric Bleeder). Brake MasterCylinder Removal Brake MasterCylinderlnstallation AdjusZmentof the Brake Master Cylinder Linkage ........._....__

................._

:.......204

................._

’............_205 .....205 .....205 ..207 .207 .207

.‘....209

Parking Parking BrakeValve Installation

Adjusting

the

Parking

................_

Brake Control Cable.

NoseWheel Removal NoseWheel Installation

..209 ............209 ................._

..............__

.........203

................._

................._

Brake Valve Removal

........202

..........210 ........210

Brake Wear Limits.

a25

MainWheel and Brake Removal.

.212

MainWheel and Brake Installation

.213

32-CONTENTSPage

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 32

LANDING GEAR

TABLE OF CONTENTS

(CONTINUED) PAGE

SUBJECT 32-41-00

Description and Operation. -Troubleshooting

1

Brake DeiceBrake Deice

101 201

Brake Deice-Maintenance Practices.

Distributor Manifold Removal.

201

DistributorManifold Instsillation

..202

Brake DeiceShutoff Valve Removal

202

Brake DeiceShutoff Valve Installation.

204

Testingthe

Brake Deice

System

204

32-50-00

Steering Description and Operation. Steering Maintenance Practices Steering Mechanism Removal. Steering Mechanism Installation Steering Link End PlayAdjustment

Nose

1

Nose

201 201

201 203

32-60-00

and\l\larning- Descriptionand Operation Warning -Troubleshooting. Position and\l\larning- Maintenance Practices. NoseGearDrag Brace DownlockSwitch Adjustment. Nose GearActuator Downlock Switch Replacement. Up-PositionSwitch Adjustment (Nose and Main Gear) Main Gear Downlock Switch Adjustment. Main GearSafety Switch Adjustment Power LeverSense Switch Adjustment (Landing GearWarning) Flap Landing Gear Warning Switch Adjustment (Flap Approach Downlimitand Landing GearWarning Cam)

1

Position

Position and

Page

432-CONTENTS

101 201 201 204 204 205

208 ........._...._.._

210

210

n25

Hawker Beechcraft Corporation SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

32-LOEP

1

Feb 1/09

32-CONTENTS

1 thru 4

Feb 1/09

32-00-00

1 thru 10

Apr 28/06

32-10-00

201 thru 207

Feb 1/09

32-20-00

201 thru 208

Apr 28/06

32-30-00

1 thru 13

Apr 28/06

101 thru 111

Apr 28/06

201 thru 259

Apr 28/06

1 thru 3

Apr

101 and 102

Apr 28/06

201 thru 215

Apr

1 and 2

Apr 28/06

101 and 102

Feb 1/09

201 thru 205

Apr 28/06

1

Apr 28/06

201 thru 204

Apr 28/06

1 thru 5

Apr 28/06

101 thru 103

Apr 28/06

201 thru 211

Apr 28/06

32-40-00

32-41-00

32-50-00

32-60-00

A25

Pages

28/06

28/06

32-LOEP

Feb

1/09Pagel

Ral~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LANDING GEAR

DESCRIPTION AND OPERATION

an airplane has experienced abnormal landing gear procedures of any type, as a safety precaution, place the airplane on jacks prior to performing any inspection or maintenance. Ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

WARNING: When

CAUTION:

Jacking of an airplane for the purpose of landing gear operation inspection, servicing or maintenance should be accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary tojack the airplane in the open, wind velocity in any direction and terrain variations, must be compensated for prior to jacking the airplane.

airplane is equipped with a retractable tricycle landing gear system. The nose gear and main gear assemblies incorporate air-oil type shock struts that are filled with both compressed air and hydraulic fluid. The nose gear strut is equipped with a single wheel and tire. Each main gear strut is equipped with two wheels and tires. The nose gear is attached to two longitudinal fuselage members in the fuselage nose and pivots aft into the wheel well when retracted. The main landing gears are attached to the two main structural ribs of the nacelles and pivot forward into the wheel wells when retracted. The landing gear doors consist of one set of nose gear doors and two sets of main gear doors, all hinged at the sides and spring-loaded to the open position. As the landing gear is retracted, two mile rs on each gear engage the door actuating cams and pull the doors closed, covering the wheel well openings and forming a smooth contour with the surrounding airplane structure.

The

landing gear is retracted and extended by individual actuators and drag brace assemblies connected to each landing gear. The actuators are powered by a hydraulic system consisting primarily of the actuator located in each wheel well, a hydraulic power pack (containing a pump, motor, reservoir, and selector valve) located in the LH wing, an accumulator, and hydraulic plumbing routed from the power pack to each landing gear actuator for a normal extend mode, an emergency extend mode, and a normal retract mode. A landing gear control switch, placarded UP DN, is located on the pilot’s inboard subpanel. When the control handle is moved to the UP position, power is supplied to the pump motor and to the gear-up solenoid to allow system fluid under pressure to flow to the retract side of the system. The landing gear is held in the retracted position by hydraulic pressure maintained in the retract plumbing system. A pressure switch in the power pack will activate the pump motor should the system pressure drop to the low pressure limit. When the control handle is placed in the DN position, power is supplied to the pump motor and to the gear-down solenoid to allow system fluid under pressure to flow to the extend side of the system. When the actuator pistons are positioned to fully extend the landing gear, an internal mechanical lock in the nose gear actuator and a mechanical lock on each main gear drag brace will lock the landing gear in the down position.

The

Emergency manual landing gear extension is provided by a hand pump located on the floor between the pilot’s seat pedestal. To extend the landing gear with this system, the pump handle is removed from its securing clip and pumped up and down. As the handle is pumped, hydraulic fluid is drawn from the power pack into the pump and pressurized, then routed from the pump to each landing gear actuator. A service valve in the hydraulic system may be used with the hand pump to retract the landing gear for maintenance. and the

landing gear position is provided by two red in-transit lights located in the landing gear control switch handle and three green gear-down indicator lights on the pilot’s inboard subpanel. The in-transit lights illuminate when the landing gear are in transit. The lights extinguish when the gears are up. The three gear-down

Visual indication of the

lights

illuminate when each

switches, and the

landing

gear is down and locked. The electrical circuits necessary to illuminate the gear-

completed through the lights downlock switches. brace drag

down and in-transit

are

nose

gear actuator

gear-down

pressure switch, the

up-position

A landing gear aural warning system warns the pilot that the landing gear is not down and locked during specific flight regimes. Various warning modes result, depending on the position of the flaps and the throttle switches.

p~o

32-00-00

Apr 28/06Page

1

Nayfbeert

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Nose gear

accomplished by a mechanical linkage system extending from the rudder pedals to a steering assembly. A spring mechanism in the steering linkage permits tow bar or braked steering angles greater than that provided by the rudder pedal system. When the nose gear is retracted, the nose wheel is automatically centered and the steering linkage becomes inoperative. steering

yoke connected

The

airplane

is

is

to the nose gear

with four

hydraulically operated

brake assemblies. Each main

landing gear incorporates assembly contains two with and and back rotate discs the to a pressure plate wheel, a stationary disc, plate attached to the rotating keyed brake housing. When the pilot’s or copilot’s rudder pedals are depressed, hydraulic fluid is pressurized by the master cylinders attached to the back of the pedals. The pressurized fluid is routed to the pistons in the brake housing, forcing the disc stack together and creating friction between the rotating discs and the brake lining on the stationary components of the brake assembly. The brakes are equipped with automatic adjusters to maintain the proper brake clearance and compensate for brake lining wear.

equipped

two multi-disc, metallic-lined brake assemblies,

Brake

deicing

is

provided by an optional engine is routed through

one on

each side of the strut. Each brake

brake deice system which utilizes

engine bleed air

as

the

deicing agent.

tubes and hoses from the bleed air line in each main gear wheel well to a distributor manifold installed between the wheels on each main gear shock strut. A shutoff valve in each main gear

Hot air from the

wheel well controls the flow of heated air to the distributor manifold.

WARNING: Never service the accumulator

landing

gear without first

hydraulic system or do maintenance or rigging of the on jacks (3, Chart i, 32-00-00). Stay clear of the gear doors while the landing gear is in operation. When jacking or

placing

the

the

airplane

landing gears, and airplane in an unsheltered area where winds in excess of 35 knots may be encountered, never jack more than one gear clear of the ground at a time. Any time the landing gear is only partially retracted during maintenance, always cycle the gear with the power pack through at least one complete cycle before removing the airplane from the jacks,

wheel wells, the

SPECIAL TOOLS AND RECOMMENDED MATERIALS The special tools and recommended materials listed in Charts 1 and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Raytheon Aircraft Company. The

products included in these charts have been tested and approved for aviation usage by Raytheon Aircraft Company, or by compliance with the applicable specifications. Generic or locally manufactured products which requirements of specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

by the supplier, conform to the

Page

232-00-00

nzo

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 SPECIAL TOOLS PART TOOL NAME 1.

Main GearStrut

115-590023-1

(Figure 1,

3.

USE

Aircraft Co.

Raytheon

Limit travel of main

9709 E. Central

Limiter

2.

SUPPLIER

NUMBER

Sheet

Wichita, KS 67201

1)

Nose GearStrut

115-590035

Aircraft Co.

Raytheon

Limiter

9709 E. Central

(Figure 1,Sheet 1)

Wichita, KS 67201

Jacks,7,000

Obtain

Limit travel of

nose

landing

gear shock strut.

Support airplane with landing ground.

Locally

gear clear of

pounds capacity (Figure 1, Sheet 1) 4.

landing

gear shock struts.

Functional test

#327 bulb and

equipment

holder

Toggle

Obtain

Function test time

Locally

delay relay

PCB. switch

Alco Electronic Products, Inc.,

MST 105D

North Andover, MA, 01845

2-ampere fuse

Obtain

locally

and holder 5.

Hand-driven

TK229/939

6.

7.

Air-driven

Raytheon

Aircraft Co.

9709 E. Central

hydraulic pump, 3,600 psig (Figure 1, Sheet 2)

Supply hydraulic pressure operate landing gear.

to

Supply hydraulic pressure operate landing gear.

to

Wichita, KS 67201

TK229-1/939

Raytheon

Aircraft Co.

hydraulic pump, 3,600 psig (Figure 1 Sheet 2)

9709 E. Central

Pressure gage,

Obtain

Wichita, KS 67201

Measure

Locally

4,000 psig

the

hydraulic

pressure in

system.

NOTE

hydraulic pump should have a reservoir, or be equipped with fittings which will permit connection to a reshydraulic pump and pressure gage both need valves capable of controlling the application and release of hydraulic fluid to the unit under test. All test equipment should be capable of holding a pressure of at least 3,600 psig without leaks.

The

ervoir. The

Ensure the

servicing equipment

8.

Ohmmeter

9.

Lubricationnozzle

contains clean fluid to avoid

Obtain 2-737

fluid system.

Check circuit

Locally

Stewart-Wamer Alemite Division

Lubricate

Diversey Parkway Chicago, IL 60614

components.

1826

A20

contaminating the airplane

continuity

landing

32-00-00

gear

Apr 28/06Page

3

RaytAeon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

SPECIAL TOOLS

(Continued)

PART TOOL NAME 10. Lubricationnozzle

NUMBER 314150

USE

SUPPLIER Stewart-Warner Alemite Division

Lubricate

Diversey Parkway Chicago, IL 60614

components.

1826

11,

M400

Injector

Aero Seal

(Raytheon

authorized

outlets) Model 4005

12. Pressure pot, hand pump

(Figure 1,

Inject sealant into assembly.

gear

wheel and

tire

Tronair Aircraft Ground

Support

Equipment

Bleed

trapped

air from brake

system.

So. 1740 Eber Rd.

Sheet 3)

Holland, OH 13. Pressure bleeder,

landing

Model 5014

43528

Tronair Aircraft Ground

mechanical pump

Equipment

(Figure 1,Sheet 3)

So. 1740 Eber Rd.

Support

Bleed trapped air from brake

system.

Holland, OH 43528 TK-1763-2/935

14. Test box

Raytheon

Aircraft Co.

9709 E. Central

(Figure 1,Sheet 4)

Wichita, KS

67201

Test

operation of main gear uplock switches and synchronize nose gear downlock switches.

TK-1763-5/935

15. Test box

(Figure 1,

Raytheon

Aircraft Co.

9709 E. Central

Sheet 4)

Wichita, KS 16. Screw driver

tip

Apex Apex

170-8

or

212-8

Obtain

Test operation of main gear downlock and safety switches.

67201

Locally

Removal and installation of upper

hydraulic system access

plate.

Apr

28/06Page

4

32-00-00

A20

RBIfIOMI

nircrart

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

115-590035

NOSE LANDING GEAR SHOCK STRUT LIMITER

DETAIL

A

B

*C

JACK CAPACITY 7000 LB RMUIRED

DETAIL

B

Dq x~

115-590023-1 MAIN LANDING GEAR SHOCK STRUT LIMITER

14, ‘P

DETAIL

C J~o-ol T-nE

Special Tools Figure 1 (Sheet 1 of 4)

A20

32-00-00

Apr 28/06Page

5

Ray~heon

Aircraft

Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

HYMIAUUC PUMP

AIR DRIVPI

P/N TK229-11939

HYDRAUUC HAND PUMP

appD.~

P/N TK229/939

Special Tools Figure 1 (Sheet 2 of 4)

Apr

32-00-00

A20

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MECHANICAL

PUMP

PRESSURE

BLEEDER

HAND

PUMP

PRESSURE

POT

Special Tools Figure 1 (Sheet 3 of 4)

A20

32-00-00

Apr

28/06Page

7

Ral~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAIN GEAR SWITCH TEST BOX

O DS11

CONNECTORS

O DS12

DOWN LOCK

O

O

DS6

DS7

0

0

DS1

DS2

SAFETY SWITCH

O

O

O

I

DSB

DS9

DS10

0

00

I

DS3

054

DS5

TK1763-51935 TEST BOX

00 CHECK

THE MAIN GEAR DOWN LOCK AND SAFETY

SWITCHES)

CONNECTORS

NOSE GEAR POSITION SWITCH TEST BOX

O

O

O

O

DS6

DS2

DS5

DS1

~o

o

o

o

DS4

DS7

053

NOSE ACT

DRAG LEG

DS8

UP LOCK

TK17632/935 TEST BOX

(TO SYNCHRONIZE THE NOSE GEAR DOWN LOCK SWITCHES AND CHECK THE MAIN GEAR UP LOCK SWITCHES) 2002( 1~0

Special Tools Figure 1 (Sheet 4 of 4)

Apr 28/06Page

8

32-00-00

A20

Raytheon

Aircraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 RECOMMENDED MATERIALS MATERIAL 1.

Hydraulic

Fluid

PRODUCT

SPECIFICATION MIL-H-5606

3126

Hydraulic

SUPPLIER

Oil

Exxon Co., USA

P.O.Box2180 800 Bell Street

Houston, TX 77001 FED 3337

Chevron U.S.A. 225 Bush Street

San Francisco, CA 94120 2.

LPS No. 3

Corrosion

Holt

Lloyd Corp. Hugh Howell

4647

Preventive Lubricant

Road

Tucker, GA 30084 3.

Lubricating Grease, Molybdenum

MIL-GP~164

Aeroshell Grease 17

Shell Oil Co. 1 Shell Plaza

P.O. Box 2463

Disulfide

Houston, TX 77001 Castrolease MSA

(C)

Castrol Oils Inc. Raritan Plaza 2

Edison, NJ 08837

Royco

Royal Lubricants Co. Campus Dr. Parsippany, NJ 07054

64C

6

Chevron Aviation

Chevron U.S.A.

Grease 44

225 Bush Street

San Francisco, CA 94120 Texaco Inc.

TG-8173

P.O. Box 509

Beacon, NY 12505 4.

Grease, Aircraft,

MIL-G-81322

Mobiigrease

28

Mobil Oil

Corp.,

150 East 42nd Street

General

Purpose Wide Temperature Range

New York, NY 1 0017

Aeroshell Grease 22

Shell Oil Co. 1 Shell Plaza

P.O. Box 2463

Houston, TX 77001

Royco

22S

Royal 6

Lubricants Co.

Campus

Dr.

Parsippany, 5.

A20

Nitrogen,

Technical

BB-N-411

Obtain

NJ 07054

Locally

32-00-00Page

9

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2

RECOMMENDED MATERIALS MATERIAL 6.

Cleaning

Solvent

PRODUCT

SPECIFICATION

PD680, Type III

(Continued)

Stoddard Solvent

SUPPLIER Obtain

Locally

(Mineral Spirits) 7.

MIL-L-23398

Lubricant, Air

Drying, Solid

Lubribond

Electrofilm Inc.,

Film

7116 Laurel

North 8.

TireSealant

Aero Seal

(Gal.

or

Canyon Blvd., Hollywood, CA 91605

Raytheon

Authorized Outlets

Pint) 9.

Grease, Aircraft,

Aeroshell Grease 5

Shell Oil Co. 1 Shell Plaza

High Temperature

P.O.Box2463

Houston, TX 77001 10. Adhesive

EC2216

Obtain

Locally

11.

Lux, Joy

Obtain

Locally

Liquid Detergent

12. Grease

Molykote

G-N Paste

Dow

Coming Corp.

P.O. Box 997 3901 South

Saginaw

Road

Midland, MI 48602

Page

rpA01

28/06

32-00-00

A20

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAIN GEAR AND DOORS WARNING: When

MAINTENANCE PRACTICES

maintenance

performing

hydraulically operated landing gear system, be aware that hydraulic cylinder can displace hydraulic fluid and cause of other movement actuator unanticipated cylinders in the landing gear retraction system. Servicing of the landing gear hydraulic accumulator can also result in unanticipated movement of an actuator. Either action can result in an unsafe, unlocked landing gear system; therefore, place the airplane on jacks prior to performing any inspection or maintenance. Cycle the landing gear and make sure that all three landing gears are down and locked prior to removing the airplane from jacks. any movement of a

on a

actuator

Never service the accumulator

or

the

hydraulic system

or

do maintenance

or

rigging

of the

landing gear without first placing the airplane on jacks (Item No. 3, Chart 1, 32-00-00). Stay clear of the wheel wells, landing gears, and gear doors while the landing gear is in operation. When

jacking

encountered,

Any time

the

the

airplane in an unsheltered area where winds in excess of jack more than one gear clear of the ground at a time.

35 knots may be

never

landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the

with the power

jacks.

MAIN GEAR SHOCK ABSORBER SERVICING a.

Remove the valve cap and

depress

the valve

core

to release the air. Allow the strut to

WARNING: Release the air pressure entirely before b.

Remove the valve the hose in

c.

Slowly

Cycle

core

and connect

container of clean

one

end of

hydraulic

fluid

expel

the strut

as

install the valve

any

a

No. 1, Chart 2,

hydraulic fluid into the hydraulic fluid and air.

excess

many times

as

the valve

compress.

core.

1/4-inch hose to the valve stem.

(Item

extend the strut to draw

the strut to d.

a

removing

fully

Submerge

the ´•other end of

32-00-00).

strut. When the strut is

necessary to relieve the air. With the strut

fully extended, slowly

compressed,

remove

compress

the hose and

core.

CAUTION: Never tow

or

taxi the

airplane

with

a

flat strut. Even brief towing

or

taxiing

with

a

deflated strut

can cause

damage. e.

With the

until the

airplane on the ground and empty except for full fuel and oil, inflate the main piston is extended 3.23 to 3.49 inches.

strut with

dry

filtered air

LUBRICA nON Lubricate the main gear wheel

a25

bearings

and grease

fittings (Ref. Chapter

12-20-00 LUBRICATION

32-1 0-00

SCHEDULE).

Page

beF102

1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAIN LANDING GEAR REMOVAL a.

b.

as

e.

cams.

Safety

wire the doors in the

drag brace from the main gear by removing the cotter pin (11), nut (10), washers (8 and 9), and disconnecting the drag leg, install the bolt, washers, and nut into the drag leg in the same position installed to facilitate correct installation (Ref. Figure 201).

Disconnect the bolt

d.

landing gear doors by disconnecting them from the actuating position.

Disable the open

c.

(Item No. 1, Chart 1, 32-00-00) and (Item No. 2, Chart 1, 32-00-00) to limit the extension of place the airplane on jacks (Item No. 3, Chart 1, 32-00-00) as instructed in Chapter 7-00-00.

Install strut limiters the struts and

(7).

After

when

Disconnect the On

hydraulic

airplanes equipped

brake flex hose at the top of the

with brake

deicing,

remove

landing

gear and cap the

hydraulic lines.

clamp securing the brake deicer hose just above the torque knees.

the

to the upper end

of the strut. Disconnect the hose at the union in the bracket f.

Disconnect the

g.

Remove the

(2,

4 and

safety

access

5), hinge

switch

wiring from

the

receptacle

at the upper rear of the wheel well.

panels covering the landing gear hinge bolts. Remove the cotter pins (1 1), (1), and bushings (3) and lower the gear away from the airplane.

nuts

(6),

washers

bolts

NOTE: After removing the bolt, position the washers

on

the bolt in the

same

sequence

as

when installed.

MAIN LANDING GEAR INSTALLATION a.

Coat all surfaces of the two bolts installation to protect

b.

against

(1)

and nuts

corrosion

(6)

with lubricant

(Item

No. 2, Chart 2,

32-00-00)

at the time of

(Ref. Figure 201).

hinge bolts (l)through the strut and keel with (4) (a minimum of one on each side of the strut) between the keel and strut as required to provide 0.005 to 0.030-inch total clearance between the keel and strut surfaces before the bolt is torqued. Apply a minimum torque of 800 inch-pounds to the hinge bolt nuts, then tighten the nuts to the next castigation and install the cotter pin. One AN960-1216L washer (5) may be used under the nut to obtain the required torque value. Position the gear in the wheel well. Install the

bushings (3)

and the

the bolt heads toward the center of the strut. Install the 105090CR025-12J washers

c.

d.

Connect the

hydraulic

brake flex hose to the union with brake

on

airplanes equipped

torque knees. Install the clamp securing the hose

Connect the lower

f.

Plug the safety

g.

Install the

drag leg

switch

wiring

move or

h.

Service and inflate the

i,

Connect the

j.

Bleed the brakes

roll.the

landing

landing gear

deicing,

landing

into the

landing gear hinge bolt

CAUTION: Do not

Page

to the

airplane

gear strut

doors to the

gear.

just

above

to the upper end of the strut.

gear with the bolt

receptacle

access

landing

connect the brake deicer hose at the union in the bracket

On the

e.

the

(7),

washers

(8

and

9),

nut

(10),

and cotter

pin.

at the upper rear of the wheel well.

panels.

until the struts

(Ref.

are

properly serviced

and inflated.

MAIN GEAR SHOCK ABSORBER

actuating

SERVICING).

cams.

(Ref. Chapter 32-40-00).

32-1 0-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

k.

Lubricate the main gear hinge points and drag brace joints with the proper lubricant (Ref. Chapter 12-20-00 LUBRICATION SCHEDULE).

I.

Check the switches

m.

landing gear rigging as instructed instructed in Chapter 32-60-00.

in

Chapter

32-30-00 and

adjust

the downlock and

up-position

as

Remove the

airplane from

i.

BOLT

2.

WASTIER

3.

BUSHING

4.

WASHER

5.

WASHER

the

jacks.

a

BOLT 4 8.

11.

WASTIER

1 I

Nvri COT~R PIN

I~

i//

jIii i

i

I 300-201-4

Main

Landing

Gear Installation

Figure

A25

201

32-1 0-00

Page

beF302

1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

MAIN GEAR TORQUE KNEE REMOVAL a.

Place the

b.

Deflate the

c.

Remove the wheels and brakes

NOTE: d;

Cap

f.

g.

landing gear

the

hydraulic

knee

strut

Remove the

32-00-00)

described in

instructed in

Chapter

bolt(l)

and

7-00-00.

32-40-00.

brake line to prevent contamination of the

(14),

Chapter

top of the strut.

at the valve located on

by relieving pressure as

as

hydraulic

fluid.

that attach the

safety switch

arm

to the upper

(3) (Ref. Figure 202). spring securing

the

Remove the cotter pin (7), nut

hydraulic

(6),

position

Cut the

pin (2)

safety

wire from the clevis remove

brake flex hose to the upper torque knee.

washers

and lower torque knees. Note the

knee pin out and h.

No. 3, Chart 1,

jacks (Item

on

Remove the cotter pin (20), nut (19), washer

torque e.

airplane

(5, 8,

9 and

12), bushing (11),

and bolt

(13) that

connect the upper

of the washers to facilitate installation of the torque knees.

and

remove

the lower torque knee

the clevis

pin from

the upper knee

pin (4). Tap

the upper

(3).

Remove the cotter pin (15), washer (16), and clevis pin pin out and remove the lower torque knee (10).

(18)

from the lower knee

pin (17). Tap

the lower knee

MAIN GEAR TORQUE KNEE INSTALLA TION a.

b.

Coat the upper and lower knee (Item No. 3, Chart 2, 32-00-00)

pins (4 and 17), bushing (11), (Ref. Figure 202).

and bolt

(13)

with grease

Position the lower torque knee (10) in place. Tap the lower knee pin (17) through the torque knee and the the landing gear and Secure it with the clevis pin (18), washer (16), and cotter pin (15).

lug

on

c.

Position the upper torque knee (3) in place. landing gear brace and install the clevis

the

in the forward side of the retainer d.

Install the bolt

(13), bushing (1 1),

torque knees. Use

an

Tap the upper knee pin (4) through the torque knee and the lug on pin (2). Safety wire between the clevis pin and the safety wire hole

ring.

washers

(9

and

AN960-816, AN960-816L,

minimum end play. Use AN960-616L washers a

e.

12), or

(5)

nut

(6), and

pin (7) that connect the upper and lower (6) under the nut as required to obtain proper cotter pin engagement. Do not cause

cotter

AN960D816L washer

under the nut for

tight joint.

Install the bolt

(1),

washer

(14),

nut

(19),

and cotter

pin (20)

that attach the

safety

switch

arm

to the upper

torque

knee. f.

Install the

g.

Install the wheels and brakes

h.

Lubricate the torque knee joints

i.

Remove the airplane from the jacks.

j.

Service and inflate the

spring securing

hydraulic

the

as

landing

brake flex hose to the upper torque knee.

described in

Chapter

(Ref. Chapter

gear strut

(Ref.

32-40-00.

12-20-00 LUBRICATION

SCHEDULE).

MAIN GEAR SHOCK ABSORBER

SERVICING).

CAUTION: DO NOT MOVE OR ROLL THE AIRPLANE UNTIL THE STRUTS ARE PROPERL Y INFLA TED AND SERVICED.

Page

20432-1 0-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BOLT 2. CLEVIS PIN

3. UPPER TOROUE KNEE 4. UPPER KNEE PIN

5 6

I 1

1

5. WASHER 6. NUT 9

7. COTTER PIN

6. WASHER I

45

I/

9. WASHER

it

4

i

1!

~1

1

10. LOWER TORCIUE KNEE

7

i?.

.1 REHSAW

.41ONIHSU

13. 80Lf WASHER

15. COTTER PIN

10

(6. WASHER

P

17. LOWER KNEE PIN ~i

(6. CLEVIS PIN

lvl \:!I I II

I

14. NUT

1

20. COTTER PIN

10

13 16 15

Main Gear

A25

Torque Knee Installation Figure 202

32-1 0-00

Page

beF502

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAIN GEAR DRAG BRACE REMOVAL No. 3, Chart 1,

32-00-00) (Ref. Chapter 7-00-00).

a.

Place the

b.

Disconnect the landing gear doors from the

c.

Disconnect the downlock switch

d.

Disconnect the drag brace from the main gear by removing the cotter pin (1), nut (2), washers 13, 4, and 5), and bolt (6). After disconnecting the lower drag leg (7), install the bolt, washers and nut into the drag leg to facilitate

airplane

correct installation e.

on

jacks (Item

wiring

actuating

from the

cams

receptacle

and

safety

wire in the open

position.

at the upper rear of the wheel well.

(Ref. Figure 203).

Remove the cotter pin (22), nut (23), bolt (10), washers (9, 16, and 17), and stops (25) securing the actuator (24) to the idlers (11) and lock link (26). Note the locations of the washers and stops to facilitate correct

clevis

installation. f.

Remove the cotter pin 121), nut (20), bolt (12), and washers (13, 14, 18, and 19) securing the upper drag leg

(15)

to the wheel well attach

fitting.

NOTE: Note the number of washers

(14)

on

each side of the upper drag leg (15) to facilitate installation of the on the landing gear strut.

drag

brace in alignment with the attachment fitting

MAIN GEAR DRAG BRACE INSTALLA nON a.

Inspect the stop plate (8) atop the upper drag leg (15) for evidence of scoring or gouging by the stops. Replace plate if any such evidence is found. If the stop plate is gouged through so that the upper drag leg is scored or gouged, replace the upper drag leg (Ref. Figure 203).

the

NOTE: If the stop plate is scored or gouged, the square corners of the stops (25) may be rounded to radius of 0.030 inch to prevent reoccurrence after the new plate is installed.

a

maximum

b.

Lubricate bolt (6 and 12) with grease (Item No. 3, Chart 2, 32-00-00).

c.

(12) through the wheel well fitting and upper drag leg (15). Install the washers (13, 14, 18, and positions as when removed. Make sure that at least one AN960-1216L washer (14) is installed between each side of the upper drag leg and the wheel well fitting. Use at least one AN960-1216L washer (18) under the nut (20). Use additional washers (18) as required to obtain minimum end play, but do not cause a tight joint. Use at least one AN960-1016 or AN960-1016L washer (19) under the nut to allow engagement of the nut (20) and cotter pin (21). Install the nut and tighten finger tight. Secure with the cotter pin. Insert the bolt

19) in

the

same

drag leg (7) with the attachment fitting on the landing gear strut; there shall landing gear is in the extended or retracted position. Correct any drag leg the AN960-1216L washers (14) from side to side of the upper drag leg. A minimum misalignment by shifting of one washer must be installed on each side of the upper drag leg.

NOTE: Check the

be

d.

no

alignment of the

side loads

Attach the lower cotter

pin (1).

on

drag leg (7)

Make

lower

when the

the

sure

to the

landing gear

that the washers

are

strut with the attach bolt

installed in the

same

(6),

order

CAUTION: Prior to installation, inspect the bolt (10) for evidence of scoring

as

or

washers

(3, 4,

and

5),

nut

(2)

and

when removed.

galling. Replace

the bolt if any

evidence is found.

I

e.

Lubricate bolt

Page

(10)

with grease

(Item

20632-1 0-00

No. 4, Chart 2,

32-00-00).

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

f.

Check the

alignment

of the actuator clevis

(24)

with the

drag

brace

as

instructed in

MAIN GEAR

RIGGING, 32-30-00. When the two are properly aligned, connect the actuator clevis to the upper drag leg (15) with the bolt (10), washers (9, 16, and 17), stops (25), nut (23), and cotter pin (22). Arrange the washers and stops in the same order as when they were removed. Tighten the nut (23) finger-tight and install the cotter pin (22). Use AN960-816 and/or AN960-816L washers (17) under the nut for proper cotter pin engagement. Make sure that the nut and washers allow 0.030 to 0.060 inch end play for the bolt and that the stops (25) pivot freely enough on the bolt to be moved by the fingers. g.

Connect the downlock switch

h.

Lubricate the

i.

Connect the

j.

Check the switches

k.

drag

brace

wiring

to the

receptacle

joints (Ref. Chapter

landing gear

doors to the

rear

12-20-00 LUBRICATION

actuating

landing gear rigging as instructed instructed in Chapter 32-60-00.

at the upper

in

of the wheel well.

SCHEDULE).

cams.

Chapter

32-30-00 and

adjust

the downlock and

up-position

as

Remove the

airplane

from the

jacks.

1. COTTER PIN

2. NUT

3. WASHER 4. WASHER 5. WASHER

1------c~

g~ BOLT 7. LOWER DRAG LEG 8. STOP PLATE 5

O.WASHER BOLT

.01REHSAW

11. IDLER

4

12. BOLT 13. WASHER 14. WASHER

14

15. UPPER DRAG LEO 16. 17. WASHER 18. WASHER

29\ ~D

19. WASHER 20.NUT

i

21. COTTER PIN 22. COTTER PIN

21--7,

23. NUT 25.

•´42POTSACTUATOR

CLEVIS

26. LOCK LINK 27. DOWNLOCK SWITCH

20 19 14 If

16

15

14

13

350-201-12

Main Gear Brace Installation

Figure

A25

203

32-1 0-00

1/09

Ralfheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

NOSE GEAR AND DOORS

hydraulically operated landing gear system, be aware that a hydraulic cylinder can displace hydraulic fluid and cause of other movement actuator cylinders in the landing gear retraction system. unanticipated accumulator of the can also result in unanticipated movement Servicing landing gear hydraulic Either action result in of an actuator. can an unsafe, unlocked landing gear system; therefore, place the airplane on jacks prior to performing any inspection or maintenance. Cycle the landing gear and ensure that all three landing gears are down and locked prior to removing the airplane from jacks.

WARNING: When

performing

maintenance

on a

any movement of

actuator

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart i, 32-00-00). Stay clear of landing placing wheel wells, landing gears, and gear doors while the landing gear is in operation. Never service the accumulator

or

the

the

gear without first

of 35 knots may be

airplane in an unsheltered area where winds in excess encountered, never jack more than one gear clear of the ground at a time. Any

the

jacking

When

only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the

landing

time the

with the power

the

the

gear is

jacks. NOSE GEAR STRUT SERVICING a.

Remove the valve cap

b.

Depress

c.

Allowthe

the valve

on

core

struttofully

the top of the

and

slowly

nose

gear strut.

release the air.

compress.

WARNING: All air pressure must be released from the the valve stem. d.

Remove the valve

e.

Connect

f.

Submerge

g.

Slowly

h.

When the

one

core

end of

a

nose

gear strut before

removing

the valve

core

from

from the valve stem.

1/4-inch I.D. hose to the valve stem.

the other end of the hose in

extend the

nose

nose

landing

a

container of clean

gear strut to draw

hydraulic

hydraulic fluid (1, Chart 2, 32-00-00). fluid into the

landing gear strut is fully extended, slowly compress the

nose

strut to

landing expel

gear strut.

any

excess

hydraulic fluid

and air. i.

Recycle

the

j.

With the

nose

nose

landing

landing

gear strut

gear strut

as

many times

compressed

as

necessary to relieve the air.

and all of the air removed,

remove

the hose and install the valve

core.

k.

airplane on the ground and empty, except for full piston is extended 3.77 to 4.06 inches.

With the

until the

CA UTION: Never tow or tawi the

airplane

with

a

fuel and oil, inflate the

flat strut. Even brief towing

or

taxiing

nose

with

a

strut with

dry filtered

deflated strut can

air

cause

damage

32-20-00Page

201

Raytheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LANDING GEAR SHIMMY DAMPER shimmy damper, insert a wire, approximately 1/16 inch in diameter, through the hole piston rod until the wire touches the bottom of the hole in the floating piston. Mark the wire, remove it and measure the depth of insertion. Inserting the wire in the hole in the floating piston, rather than letting it rest against the face of the piston, will give a more accurate check. The wire can be inserted approximately

To check the fluid level in the

in the washer at the aft end of the

5.25 inches when the reservoir is

empty.

NOTE: To determine if the wire is inserted in the hole of the each insertion

depth.

When the wire is in the hole, the

floating piston, insert the wire several times, noting depth will be approximately 1/2-inch greater.

When the shimmy damper is full, the distance from the end of the piston rod to the bottom of the hole in the aft floating piston is 2.63 to 2.88 inches. When the distance is 3.125 to 3.375 inches, the shimmy damper lacks a half inch of being full and should be serviced. To add hydraulic fluid (1, Chart 2, 32-00-00), proceed as follows: a.

Removethe shimmydamper.

b.

Remove the clevis bolt from the piston rod end fitting and

fitting c.

end of the

piston

snap-ring, disc

Remove the

the

secure

and

spring from

the aft end of the

piston

CA UTION: The spring in the piston rod assembly is under compression. d.

Remove the aft

e.

Fillthepiston

f.

Insert the 10-32 bolt

piston

shimmy damper in

a

fixed

position

with the

rod down.

floating piston

from the

piston

rod

by screwing

a

rod.

Carefully remove the snap-ring and washer.

long

10-32 bolt into the

piston

and

pulling

it out.

rodwithfluid.

through the fitting end of the piston rod and engage the forward floating piston. Pull the fitting end of the piston; at the same time, insert the aft floating piston and spring and install snap-ring.

toward the

the disc and g.

Remove the bolt from the forward

h.

After initial installation of the

floating piston

and install the

piston rod end fitting.

piston rod end fitting, adjust to allow no more than 1.13 inches of length as piston to the center of the fitting clevis. After initial adjustment of end fitting, shimmy damper to the strut assembly and carefully check the adjustment as follows:

measured from the end of the connect the

1.

Check the piston rod end fitting for equal travel of the piston in either direction through the full turning radius (from stop to stop). Ensure that there is adequate clearance during piston travel to prevent overtravel on either side of the damper barrel.

i.

Disconnect and readjust the piston rod end fitting

as

necessary.

LUBRICATION

I

Lubricate the

Page

rpA202

28/06

nose

gear wheel

bearings

32-20-00

and grease

fittings (Ref.

Lubrication Schedule in

Chapter 12).

Ray~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOSE LANDING GEAR REMOVAL a.

Place the

b.

Disconnect the

c.

Retract the gear

d.

Remove the

e.

Disconnect the electrical

f.

airplane on jacks (3, Chart 1, 32-00-00) 1, 32-00-00) to limit the extension of the struts.

h.

slightly

drag

Remove the

brace from the

Place

a

nose

gear

wiring

nose

for the

hinge

Remove the cotter lower the

nose

NOTE: Note the

gear

drag

cams

and

Chapter 7.

safety

Install strut limiters

wire in the open

(1

and 2, Chart

position.

brace and to unlock the actuator.

instructed in NOSE GEAR DRAG BRACE REMOVAL.

as

landing

from the

bolt

block under the wheel to are

actuating

to take the load off the

steering yoke (12) (11) (Ref. Figure 201).

when the bolts i.

gear doors from the

Disconnect the bolt

g.

landing

instructed in

as

and taxi

nose

gear

lights

at the LH nose wheel well keel.

by removing the

cotter

pin (13),

nut

(9),

washer

(10),

and

access covers.

remove

part of the load

the

on

attaching

bolts and to support the

nose

gear

removed.

pins (7),

nuts

(8), washers (2, 4, airplane.

5 and

6), bushings (3)

and

nose

gear attach bolts

(1),

then

gear away from the

of the washers to facilitate installation.

original position

NOSE LANDING GEAR INSTALLA TION a.

At the time of installation, lubricate the bolts

(3,

Position the

b.

gear brace Install the

c.

the on

and

bushings (3

and

15)

with Aeroshell Grease 17

nose

gear in the wheel well and install the

drag

brace lower

legs (16) through

the web in the

nose

hinge

bolts

(1)

with at least

one

100951-X-031-UC

or

100951-X-064-UC washer

(4)

on

each side of

gear brace to fill the gap between the nose gear brace and the keel. Install a countersink washer (2) each bolt with the countersink towards the bolt head. Install the bushings (3) over the bolts and into the nose

casting

when the

nose

gear is in

position.

Install the remaining washers (5 and 6) and the nuts (8) on the bolts. Torque the hinge attach bolts to 400 to 700 inch-pounds and secure the nuts (8) with the cotter pins (7). Use AN960-1016 and/ or AN960-1016L washers (6) under the nut as required to obtain proper torque and engagement of the nut and cotter pin. same

sequence

as

noted

during

removal

procedures.

Connect the

steering yoke (12) to the nose gear with the bolt (1 1), washer (10), nut (9) and cotter pin (13). finger-tight. Use AN960-516 or AN960-516L washers (10) under the nut as required for proper engagement of the cotter pin.

Tighten

the nut

f.

Install the

g.

Connect the

h.

Lubricate the

p~o

22)

(21).

NOTE: Position the washers in the e.

and

nose

gear d.

(1, 11,

32-00-00) (Ref. Figure 201).

Chart 2,

drag

brace

landing

on

the

and taxi

nose

gear

as

light wiring

instructed in NOSE GEAR DRAG BRACE INSTALLATION.

at the LH nose wheel well keel.

nose gear and drag brace hinge joints and the instructed in the Lubrication Schedule in Chapter 12.

steering linkage

with the proper lubricant

32-20-00

as

Apr 28/06Page

203

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i.

j.

Connect the

Check the the

k.

landing

gear doors to the

actuating

cams.

landing gear and door rigging as instructed in Chapter 32-30-00. Adjust the actuator downlock switch, and the drag brace downlock switch as instructed in Chapter 32-60-00.

up-position switch,

Install the

nose

Remove the

gear

bolt

hinge

airplane

from the

access covers.

jacks.

NOSE GEAR TORQUE KNEE REMOVAL

airplane

a.

Place the

b.

b. Deflate the

c.

on

landing

Remove the cotter

jacks (3, Chart 1, 32-00-00) gear strut

pin (6),

Remove the cotter pin knee

e.

pin

out and

remove

Remove the cotter

torque knee pin

(4),

instructed in

Chapter

7.

the pressure at the valve located

on

top of the

strut.

(8), washers (7 and 9), bushing (10), and bolt (Il)that connect the upper and position of the washers on the attach bolt to facilitate installation (Ref. Figure 202).

nut

lower torque knees. Note the d.

by releasing

as

washer

(3),

the upper

pin (16),

washer

and clevis

torque knee

(15),

pin (1 (5).

pin (13) from

and clevis

out and remove the lower

from the upper torque knee

the lower

pin (2). Tap the

upper torque

torque knee pin (14). Tap the lower

torque knee (12).

NOSE GEAR TORQUE KNEE INSTALLATION a.

Position the lower torque knee (12) on the lower shock absorber and tap the lower torque knee place. Install the clevis pin (13), washer (15), and cotter pin (16) (Ref. Figure 202).

b.

Position the upper torque knee (5) on the upper shock absorber and tap the upper torque knee Install the clevis pin (1), washer (3), and cotter pin (4). Install the bolt

c.

to the lower

(1 1

bushing (10),

washers

(7 and 9),

torque knee. Install the washers in the

nut

pin (2)

into

into

place.

(8), and cotter pin (6) that attach the upper torque knee positions from which they were removed.

same

d.

Lubricate the torque knee joints with the proper lubricant

e.

Removethe

Apr

pin (14)

as

instructed in the Lubrication Schedule in

Chapter 12.

airplanefromthejacks.

28/0632-20-00

A20

RaYReOn

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

\O

9

11

2

14

13

22

16 17

’17

16 15

14 20

21

1

BOLT

P.WASHER 3. BUSHING

4. WASHER 5. WASHER

6.WASHER 7 COTTER PIN 8. NUT 9

NUT

10. WASHER 11. BOLT 12. STEERING YOKE

13 14

COTTER PIN WASHER

15. BUSHING

16 17

DRAG BRACE LOWER LEGS WASHER

18. WASHER 19

NUT

20

COTTER PIOJ

21

NOSE GEAR BRACE

22

BOLT

8360-351-96

Nose

Landing

Gear fnstallation

figure

A20

201

32-20-00

Page 205 Apr 28/06

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i. CLEVIS PIN 2. UPPER TORQUE KNEE PIN

1

3. WASHER

2

4. COTTER PIN

5. UPPER TORQUE KNEE 8. COTTER PIN

4

7. WASHER

8. NUT 9. WASHER

I;;

10. BUSHING 11. BOLT

ii

12. LOWER TORQUE KNEE 13. CLEVIS PIN 14. LOWER TOROUE KNEE PIN 15. WASHER

16. COTTER PIN

89 10 12

13

\\\\l’i

16

Nose Gear torque Knee Installation Figure 202

NOSE GEAR DRAG BRACE REMOVAL Place the

b.

Disable the open

I

airplane

a.

c.

on

landing position.

Remove the

Chart 1,

jacks (3,

gear doors

clamps securing

32-00-00)

by disconnecting

as

them from the

the downlock switch

CAUTION: To maintain the downlock switch

wiring

(9)

d.

Remove the nut

e.

Retract the

nose

gear

slightly

to take the load off the

f.

Remove the bolt

(32),

washer

(35),

g.

Remove the cotter

(14)

and

nose

pin (15) and

gear brace

(22).

nut

and nut

(16)

Chapter

actuating

to the upper

7.

wire the doors in the

drag leg (6) (Ref. Figure 203). the aft side of the

to the forward side of the upper

drag

drag leg

to turn.

drag leg.

brace and to unlock the actuator.

(34) connecting

from the lower

Safety

cams.

adjustment, do not allow the nut on

the downlock switch

(24) securing

instructed in

the actuator clevis

hinge

bolt

Note the location of the washers

(33)

(21). Drive the (17, 19, and 20)

to the

yoke (30).

bolt out of the lower

and

bushings (13)

drag legs

to facilitate

installation. h.

Apr

Retract the actuator to avoid interference when

32-20-00

removing

the

drag

brace

assembly.

A20

Ral~hwm

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i.

(1), washers (4), and nuts (5) securing the two pins (3) to the upper drag leg (6). Remove pins with Vise-Grips or equivalent pliers and retain the washers (2) located between the upper drag leg and attachment fittings. Remove the drag brace assembly.

Remove the two bolts

the the

NOSE GEAR DRAG BRACE INSTALLA TION

hinge (Ref. Figure 203).

Coat the lower

b.

Place the lower ends of the lower

c.

bolt

(21)

a.

and

bushings (18)

with Aeroshell Grease 17

drag legs (14) through the web

in the

(3, Chart 2, 32-00-00)

gear brace

nose

(22).

drag leg (6) in the attachment fittings. rnstall one AN960-1016L washer (2) fitting and drag leg on each side of the drag leg. Use care to align the holes through the drag leg with the holes through the fittings and secure the drag leg to the fittings with the two pins (3). Secure the pins to the drag leg with the two bolts (1), washers (4), and nuts (5). Ensure that the grease fittings are accessible for Position the upper end of the upper

between the

future d.

use.

bushings (18) and washers (17, 19, and 20) on the lower drag legs (14) in the same positions from they were removed. Insert the lower hinge bolt (21)through the nose gear brace (22) and the lower drag legs. Install the nut (16) and torque it to 200 to 400 inch-pounds, then install the cotter pin (15). Use an AN9601016 and/or AN960-1016L washer (17) under the nut as required to obtain the proper torque and engagement of the nut and cotter pin. Install the

which

e.

Extend the actuator to the clevis to the

yoke

align

(33) (34).

the bolt hole in the actuator clevis

with the bolt

(32),

washer

(35),

and nut

with the bolt hole in the

CAUTION: To maintain the downlock switch adjustment, do not allow the nut f.

Install the downlock switch

the upper

Lubricate the

h.

Connect the

i.

Check the

switch, the

the upper

drag leg

and

secure

it with the nut

(24).

Install the

drag leg

to turn.

wiring clamps

on

drag

brace with the proper lubricant

landing

gear doors to the

actuating

(Ref. Lubrication

Schedule in

Chapter 12).

1

cams.

landing gear and door rigging as instructed in Chapter 32-30-00 and adjust the actuator downlock drag brace downlock switch, and the up-position switch as instructed in Chapter 32-60-00.

Remove the

A20

on

the aft side of the

drag leg.

g.

j.

(9)

on

yoke (30). Secure

airplane

from the

jacks.

32-20-00

Apr 28/06Page

207

Raytheon

Aireraft

Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

35

31

25

1

25 11

3

29

22

24’

.11

23

12 14

17

13

1~

2YO

~L--15 19

18 17 16 1

2

BOLT WASHER

18

BUSHING

19

WASHER

3. PIN

20. WASHER

4. WASHER

21

5

NUT

22. BRACE

6

UPPER DRAG LEG

23

7

BUSHING

24. NUT

BOLT BRACKET

8

WASHER DOWNLOCK SWITCH 10 BUSHING 11 WASHER 12. BOLT

25

9

26

13. BOLT

30. YOKE

14. LOWER DRAG LEO

31. WASHER

15. COTTER PIN

32. BOLT

18. NUT

33

17. WASHER

34

Nose Gear

27

COTTER PIN NUT NUT

28. COTTER PIN

29

WASHER

ACTUATOR CLEVIS NUT 35. WASHER

Drag

8300-351-92

Brace Installation

Figure 203

Apr 28/06Page

208

32-20-00

A20

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXTENSION AND RETRACTION

DESCRIPTION AND OPERATION

airplane has experienced abnormal landing gear procedures of any type, as a safety precaution, place the airplane on jacks prior to performing any inspection or maintenance. Ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

WARNING: When

CAUTION:

an

Jacking

of an

airplane for the purpose of landing gear operation, inspection, servicing or maintenance, accomplished within an enclosed building or hangar. In the interest of safety, should it necessary to jack the airplane in the open, wind velocity in any direction and terrain variations compensated for prior to jacking the airplane.

should be become must be

hydraulically operated landing gear system, be aware that cylinder can displace hydraulic fluid and cause unanticipated movement of other actuator cylinders in the landing gear retraction system. Servicing of the landing gear hydraulic accumulator can also result in unanticipated movement of an actuator. Either action can result in an unsafe unlocked landing gear system. Therefore, place the airplane on jacks prior to performing any inspection or maintenance. Cycle the landing gear and ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

WARNING: When

performing

maintenance

any movement of

a

on a

hydraulic

actuator

nose and main landing gear assemblies are extended and retracted by a hydraulic power pack, located inboard of the LH nacelle and forward of the main spar. The hydraulic power pack consists primarily of a 28-vdc motor, pump, two-section reservoir, filter, four-way solenoid selector valve, relief valves, lock valves, gear-up pressure switch and

The

low fluid level sensor. To prevent cavitation of the pump, engine bleed air regulated to 18 to 20 psi is plumbed into the system fill reservoir and the power pack reservoir. A capped cross, adjacent to the service valve, is plumbed into the bleed air line to the fill reservoir as a connection point for pressurized air during ground operation of the power Associated plumbing for-a normal extend mode, emergency extend mode and normal retract mode is routed from the power pack to each main gear actuator and the nose gear actuator. The plumbing for the normal extend mode and the emergency extend mode is fitted separately to the shuttle valve in each actuator. The shuttle

pack assembly.

spring-loaded to a position which allows hydraulic fluid from the normal extend plumbing to flow into and cylinder. The retract mode plumbing is fitted to the opposite end of each actuator. The system plumbing, shown in Figure 1, is color coded as follows:

valves

are

out of the actuator

Regulated engine

Orange

bleed air

Normal extend

White

Normal retract

Blue

Hydraulic

Purple

fluid fill

Yellow

Hand pump suction

BrownNVhite

Hand pump pressure

Brown

Emergency extend

landing gear control handle, placarded UP-UN, is located on the pilot’s inboard subpanel. A downlock latch prevents the landing gear control handle from being raised while the airplane is A

solenoid-operated the ground; the

on

RH main gear safety switch releases the latch when the plane leaves the ground. If necessary, the latch manually overridden by pressing down the red button placarded DN LOCK REL.

CAUTION: Never

rely on the safety switch to keep the gear down position of the landing gear handle.

while

taxiing

or on

landing

or

takeoff roll.

can

be

Always

check the

~ao

32-30-00Page

1

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

To prevent accidental gear retraction whenever the strut is compressed.

on

the

ground,

a

safety switch

on

the

right

main strut breaks the control circuit

landing gear control circuit is protected by a two ampere circuit breaker on the pilot’s inboard subpanel. Power for the pump motor is supplied through the landing gear motor relay and the 00-ampere circuit breaker in the center section leading edge forward of the power pack. The motor relay is energized through the time delay PCB and the

The

logic relay PCB

under the center aisle floorboard

just aft of the flight compartment. These PCBs will interrupt

current

gear control circuit breaker if continuous motor operation exceeds approximately 14 seconds. When the control handle is placed in the UP position, a circuit is completed from the landing gear control

trip

switch to the time

delay PCB through the RH safety switch and the gear-up pressure switch. When the control handle position, a circuit is completed from the landing gear control switch to the time delay PCB through

is

placed

the

nose

the

landing

to the motor and

in the DN

gear actuator downlock switch and the main gear downiock switches.

landing gear control handle is moved to the UP position, the gear-up solenoid on the selector valve is energized, actuating the gear selector valve to allow system fluid under pressure from the pump to flow to the retract side of the system. The nose gear actuator requires 200 to 400 psi of hydraulic pressure at the retract port to unlock the internal mechanical downlock mechanism. As the actuator pistons move to retract the landing gear, the fluid in the actuators exits through the normal extend ports and flows back to the power pack through the normal extend plumbing. When the hydraulic fluid enters the power pack, the gear selector valve directs the return fluid to the primary reservoir. The landing gear is held in the retracted position by hydraulic pressure maintained in the retract plumbing system. When the system pressure reaches the high pressure limit (2,775 +55 psig), the gear-up pressure switch on the power pack assembly will interrupt current to the pump motor. This same pressure switch will activate the pump motor should the system pressure drop to 300 to 400 psig below the high pressure limit. An accumulator, precharged to 800 psi and located next to the power pack, helps to maintain the system pressure in the gear-up When the

mode. NOTE: After the

landing gear is retracted, it is normal for the pump motor to run momentarily, once during the first five minutes after retraction and again approximately 30 minutes later. This is caused by temperature changes

in the

hydraulic fluid, by slight

internal fluid

leakage,

or

by

air in the

hydraulic system.

landing gear control handle is moved to the DN position, the gear-down solenoid is energized, actuating the selector valve to allow system fluid under pressure from the pump to flow to the extend side of the system. As When the

pistons move to extend the landing gear, the fluid in the actuators exits through the normal retract ports and flows back to the power pack through the normal retract plumbing. Fluid from the pump opens a pressure check valve in the power pack to allow the return fluid to flow into the primary reservoir. When the actuators have fully

the actuator

extended the

landing

gear,

an

internal mechanical lock in the

nose

gear actuator and

a

mechanical lock

on

each

main gear drag brace engage to hold the landing gear in the down position. The pump motor will continue to run until all three landing gears are down and locked. A low pressure vent valve in the power pack (open below 80 psid and closed above 80 psid) relieves any thermal expansion in the retract side of the system when the landing gear

is down and locked.

yellow HYD FLUID LOW annunciator located in the CAUTION/ADVISORY panel will illuminate in the event the hydraulic fluid level in the landing gear power pack becomes low. A sensing unit mounted on the motor end of the power pack provides the necessary switching circuitry to illuminate the low fluid light. The optically operated sensing unit has an integrated self-test circuit, energized by a switch on the instrument panel, to function-test the sensing unit’s internal circuitry.

A

Apr

28/0632-30-00

~o

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION ADVISORY PANEL

o PILOT’S INBOARD SUBPANEL

DETAIL

A

NOSE GEAR

ACTUATOR

PLUMBING INSTL

EXTENSION HAND PUMP

TIME DELAY ASSEMBLY

(FOR DETAIL. SEE

PRINTED

CIRCUIT CARD RACK. CHAPTER 39-21-00)

SERVICE VALVE

LOGIC RELAY

LEADING EDGE ELECTRICAL EQUIPMENT PANEL (FOR DETAIL SEE CHAPTER

LH MAIN

(FOR DETAIL.

SEE

PRINTED CIRCUIT

39-20-00)

CARD BOX. CHAPTER

B

BO-AMP aRculT BREAKER

~I 11

39-21-00)

-11#1

11

I

L

-RH MAIN

GEAR ACTUATOR

GEAR ACTUATOR

MAIN SPAR

MOTOR

RELAY FILL RESERVOIR

ACCUMULAT

POWER

BLEED AIR FROM ENGINES

PACK ASSEMBLY 350-23(-11

AIR REGULATOR

Hydraulic Landing Gear System Figure 1 (Sheet 1 of 2)

A20

32-30-00

3

~ytheon

nircraft

Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

~1

’SPERRY-VICKERS POWER PACKS HAVE THE GEAR-UP PRESSURE SWITCH MOUNTED ON THE SELECTOR VALVE END OF THE POWER PACK

I

REGULATEDENGINE BLEEDAIR

I

NORMALEXTEND LINE NORMAL RETRACTLINE

FILLLINE

I

;I

HANDPUMPSUCTIONLINE HANDPUMP PRESSURELINE EMERGENCY EXTEND LINE

TO NOSE GEAR AND RH MAIN

GEAR ACTUATORS

TO NOSE GEAR AND RH

F?AIN

GEAR ACTUATORS

SERVICE VALVE

FROM HAND

SELECTOR VALVE

PUMP

AND SOLENOIDS

TO LH MAIN GEAR

POWER PACK

o:

ASSEMBLY

ACTUATOR

FROM FILL

(A

RESERVOIR

GEAR-DOWN

’GEAR-UP

PORT

.PRESSURE SWITCH

GEAR-UP PORT TOACCUMULATOR

FLUID

--7~i

LEVEL

TO NOSE GEAR

SENSOR

AND RH MAIN

f

GEARACTUATORS TO LH MAIN

/~Y,MOTOR

HAND PUMP

GEAR ACTUATOR

PRESSVRE

PORT TO LH MAIN

GEARACTUATOR

TOH\ANDPUMP

PRESSURIZATION

CONNECTION POINT FOR GROUND OPERATION OF POWER PACK OVERBOARD TO FILL

FROM FILL

HAND PUMP SUCTION

RESERVOIR

LINE

FILL PORT

RESERVOIR

DETAIL

B

FL32B ahus2~u

Hydraulic lauding Gear System Figure 1 (Sheet 2 of 2)

Apr 28/06Page

4

32-30-00

A20

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURE

REGULATED BLEED AIR

FLUID

ENGINE

VENT PORT

(18 TO 20 PSI) CHECK

VALVE 1

I

I

I

AUXILIARY RETURN PORT (PLUGGED) PACK

POWER

ASSEMBLY

r--

RETURNFLUID

I

NOTE:

n

FILL RESERVOIRI

ORIFICE

-5A

I

I

I

I

I

RETURN OVERBOARD VENT

28VDC 60A PUMP MOTOR RELAY

PUMP

FILL

MOTOR

VALVE FILTER RELIEF

HAND I

D

I

i

SECONDARY RESERVOIR

~f

SOLENOID

I

RESISTOR

OUT

IN

SERVICE VALVE SWITCHES

TIME

PUMP

LOGIC RELAY

DELAY

HAND PUMP PRESSURE PORT

I I

VALVE

nAUXILIARY rlPRESSURE

ISUCTION PORT

HAND

SELECTOR

t

PUMP CHECK VALVE

VALVE

PUMP

SYSTEM RELIEF

PUMP

PORT

SWITCH CIRCUIT OPENS ON INCREASING PRESSURE AT 2775 55 PSIG AND CLOSES ON DECREASING PRESSURE AT A DIFFERENTIAL OF 300-400 PSIG

CVRRENT n LIMITI~G

PRIMARY RESERVOIR

FILTER

THE INTERNAL SHUTTLE VALVE IS SPRING LOADED TO A POSITION WHICH ALLOWS FLUID Ihl THE ACTUATOR TO FLOW OUT THE NORMAL EXTEND PORT PRESSURE

n

I

i

UP

DOWN

tI

PORT

(PLUGGED)

SOLENOID

GEAR DOWN PORT

HAND PUMP PRESSURE

CHECK VALVE

PRESSURE SWITCH

ii~-l

FILTER

VENT

VALVE

.I RH

SAFETY.--.

SWITCH

o! I

I’

.I

L__J L__J

FILTER

THERMAL

RELIEF

VALVE

L____----_____----___

UP -r

I

I

UP

ACCUMULATOR

ol

28VDC 2A

GEAR PORT

RH MAIN I V~

r

I

L---J

NOSE ACT

i-_ J

:D_OW~1: CONTROL SWITCH

SERVICE VALVE

r---~

LH

MATNI ol

SWITCHESL__J

DOWNLOCK

ol I---I

LH SAFETY SWITCH

n

LH MAIN ACTUATOR

n

NOSE ACTUATOR

n

MAIN ACTUATOR RH

FL328

9837i5MAI

Hydraulic Landing Gear Schematic (Normal Retract Mode) Figure 2

A20

32-30-00

Rayt~eon

Aircraft

Company

SUPER KING AIR 6300/B300C MAINTENANCE MANUAL

This

Apr

28106~Z"2861os

32’30’00

Page Intentionally

Left Blank

AZO

RaytReo~

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

HAND PUMP PRESSURE

FLUID

REGULATED BLEED AIR

ENGINE (18 TO 20

VENT PORT

PSI) CHECK

VALVE I

I

I

I

AUXILIARY RETURN PORT PLUGGED)

PACK

POWER

ASSEMBLY

r--

REIURNFLUID

I

I’

HAND

SUClrON

PUMP

RETURN

5A

FILTER OVERBOARD VENT

CONDITIONS:

28VDC 60A

I

I.LANDING GEAR CONTROL HANDLE IN "DOWN" POSITION 2.2-AMPERE CONTROL CIRCUIT BREAKER PULLED

n

PRIMARY RESERVOIR

FILL RESERVOIR

ORIFICE

PUMP MOTOR

PUMP

VALVE FILTER RELIEF

HAND PUMP o

i

SELECTOR

SECONDARY RESERVOIR

RESISTOR

SERVICE VALVE SWITCHES

SUCTION PORT

HAND

OUT

IN

SOLENOID

ITME

DELAY

PUMP

LOGIC

HAND

RELAY

PUMP

PRESSURE PORT

f

PUMP CHECK

VALVE

_J __J

VALVE

AUXILIARY

I\ I

I~ n

1

VALVE

HAND PUMP PRESSURE FLUID UNSEATS VALVE

SYSTEM RELIEF

PUMP

NOTES: PRESSURE FLUID FROM HAND PUMP SHUTTLES INTERNAL SHUTTLE VALVE TO ALLOW FLUID TO FLOW INTO ACTUATOR

CURRENT LIMIIING

MOTOR

FILL PORT

RELAY

j

I

UP

DOWN

tj

X

PORT

(PLUGGED)

SOLENOID

GEAR DOWN

HAND

PORT

PUMP DUMP

VALVE PRESSURE SWITCH

IPRESSURE

PRESSURE CHECK

VALVE

1

FILTER

VENT

VALVE

ol RH SAFETY SWITCH

ol

II

I

ol

L_

FILTER

UP r

RELIEF

VALVE

UP

PORT

MAIN I

ACCUMULATOR ol

28VDC

L__J

2A NOSE ACT

SERVICE VALVE

r--,

._´•i

LD_ow_N_I CONTROL SWITCH

THERMAL

GEAR

RH r--

c~

LH

MAIN I

61

ol L_-J

DOWNLOCK SWITCHES

L__J

SAFETY SWITCH

LH

n

MAIN ACTUATOR

LH

n

NOSE ACTUATOR

n

RH MAIN ACTUATOR

FL328 983768~A.Al

Hydraulic Landing Gear Schematic (Emergency Extend Mode) Figure 3

A20

32-30-00

Ra~heon Aircraft Company SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Apr

32-30-00

Page Intentionally

Left Blank

A20

Baytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURE

HAND PUMP

REGULATED BLEED AIR

FLUID

ENGINE (18 TO 20

VENT PORT

PSI) CHECK

VALVE I

I

I

I

AUXILIARY RETURN PORT (PLUGGED)

POWER

PACK

ASSEMBLY

r--

RETURNFLUID PRIMARY RESERVOIR

FILL

I

-:::I

HPINDPUMPSUCTION

RETURN FILTER

5A

I,

CONDITIONS: I.AIRPLANE 2.2-AMPERE

RESERVOIR

ORIFICE

28VOC

ON JACKS CONTROL CIRCUIT

I

OVERBOARD VENT

~o-L´•

60A PUMP MOTOR

BREAKER

PULLED

PUMP

KNOB ON SERVICE VALVE PULLED UP 4.LANDING GEAR CONTROL HANDLE IN "UP" 3.RED

VALVE

FILTERRELIEF

POSITION

HAND PUMP I I

O

SELECTOR

SECONDARY RESERVOIR

SUCTION

I

IPORT

I

ISOLENOID

I

CURRENT LIMITING

n

RESISTOR

SERVICE VALVE

HAND PUMP

OUT

IN IIME

LOGIC RELAY

DELAY

SWITCHES

RH SAFETY SWITCH

j

PUMP PRESSURE PORT

_J

I UP

DOWN

X

1/

I I

nAUXILIARY PRESSURE PORT

(PLUGGED)

SOLENOID

GEAR DOWN PORT

HAND PUMP DUMP

PRESSURE

PRESSURE CHECK

SWITCH

VALVE

HAND

VALVE

I I

VALVE

_

t

PUMP CHECK

1

VALVE

THE INTERNAL SHUTTLE VALVE IS SPRING LOADED TO A POSITION WHICH ALLOWS FLUID IN THE ACTUATOR TO FLOW OUT THE NORMAL EXTEND PORT

SYSTEM RELIEF

PUMP

NOTE:

n

MOTOR

FILL PORT

RELAY

VALVE

J

I

FILTER

_J

VENT VALVE

r-

ol L--J

THERMAL

FILTER L---------------------I

UP

I I I

I

I

MAIN I

VALVE

C-------------------~

GEAR PORT

RH

RELIEF

UP

ACCUMULATOR

ol

28VDC

L__J

2A

NOSE ACT

Lo~ CONTROL SWITCH

i

SERVICE VALVE

r-

i_ i LH

MAINI ol DOWNLOCK SWITCHES

ol LH SAFETY SWITCH

n

LH MAIN ACTUATOR

n

NOSE ACTUATOR

n

RH MAIN ACTUATOR

FU2B

Hydraulic Landing Gear Schematic (Hand Pump Retract Mode) Figure 4

A20

32-30-08

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Apr

32130100

Page Intentionally

Left Blank

A20

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURE

REGULATED BLEED AIR

FLUID

AUXILIARY RETURN PLUGGED) PORT

ENGINE (18

TO

20

POWER

PSI) CHECK

VALVE I

I

I

PACK

ASSEMBLY

r--

RETURNFLUID

FILL

NOTE:

I

THE

n ~i

INTERNAL SPRING LOADED TO A ALLOWS FLUID FROM GEAR PORT OF POWER PACK TO FLOW INTO ACTUATOR

PUMP

~5A

SHUTTLE

VALVE IS POSITION WHICH

FLUIDPRESBURE

RESERVOIRI

ORIFICE

I

I

I

I

I

I RETURN FILTER

OVERBOARD VENT 28VDC~

DOWN

1

F90M

i-U

60A PUMP MOTOR "E’*’

PUMP

FILL

MOTOR

SECONDARY

HAND PUMP

i

E~j

PORT

SELECTOR

RESISTOR

TIME

SOLENOID

HAND PUMP

OUT

LOGIC RELAY

DELAY

j

HaNo PUMP

PRESSURE

I

SYSTEM RELIEF

1

t

PUMP CHECK

VALVE

VALVE

I I

RESERVOIR

SUCTION

IN

I

VALVE FILTER RELIEF

SERYICE VALVE SWITCHES

I

PORI

VALVE

n

I

PUMP

UNLOCKS YALVE

CURRENT LIMITING

PRIMARY RESERVOIR

UP

DOWN

t1 f~

VALVE

PORT

PRESSURE PORT

I

GEAR DOWN

PUMP

PRESSURE CHECK

AUXILIARY

I

(PLUGGED)

SOLENOID

HAND

PRESSURE SWITCH

n

1

I I

nPORT

FILTER

VENT VALVE

.I SAFETY SWITCH

RH

o! I

I’

.I

L__J

FILTER

THERMAL RELIEF

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L_-

GEAR UP T

RH

:uP:

MAIN I

v

2A

I

I

ACCUMULATOR

ol

28VDC Y,

I

L---J

NOSE ACT

SERVICE VALVE

r

LD_OW_N I CONTROL SWITCH

LH

MAINI

~I

ol I_-J

DOWNLOCK SWITCHES

LH

SAFETY

SWITCH

n

LH MAIN ACTUATOR

n

NOSE ACTUATOR

n

RH MAIN ACTUATOR

FL3ZB 9a3768AA.AI

Hydraulic Landing Gear Schematic (Normal Extend Mode) Figure 5

A20

32-30-00

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Apr

2810632-30-00

Page Intentionally Left

Blank

A20

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Emergency

manual

gear extension is provided by a hand pump, placarded LANDING GEAR ALTERNATE the floor between the pilot’s seat and the pedestal. To extend the gear with this system,

landing

EXTENSION, located

on

pull the landing gear control circuit breaker on the pilot’s inboard subpanel and place the landing gear control handle in the DN position. Remove the pump handle from its securing clip and pump the handle up and down to extend the gear. As the handle is pumped, hydraulic fluid is drawn from the hand pump suction port of the power pack into the pump and pressurized. Fluid from the pump is routed to the power pack hand pump pressure port and to the shuttle valve in each actuator. The fluid routed to the shuttle valves actuates the valves, allowing fluid to flow into the actuator cylinders. As the actuator pistons move to extend the landing gear, the fluid in the actuators exits through the normal retract ports and flows back to the power pack through the normal retract plumbing. The fluid routed from the hand pump to the power pack hand pump pressure port unseats the internal hand pump dump valve, allowing the return fluid to flow into the prima~y reservoir. Continue to pump the handle up and down until the three green GEAR DOWN indicator lights on the pilot’s inboard subpanel illuminate. Ensure that the pump handle is in the full down position, then place the pump handle in the securing clip. When the pump handle is stowed, an internal relief valve opens to relieve the hydraulic pressure in the pump. WARNING: After

an

controls

landing

emergency nor

gear extension has been made, do not move any landing gear or circuit breakers until the cause of the malfunction has been

reset any switches

determined and corrected. A service valve

adjacent to the

maintenance. A flush-mounted nacelle allows

access

power

may be used with the hand pump to raise and lower the landing gear for door on top of the center section between the fuselage and the left engine

pack

access

to the service valve. With the

airplane

on

jacks, pull

the detent

pin,

move

the

plunger

retainer

pull up plunger. The hand pump can then be pumped to raise the gear to the desired covering has been performed, push the plunger down and use the hand pump to After the maintenance required position. lower the gear. To ensure proper positioning of the service valve plunger, the plunger is safety wired in the down the

plunger and

on

position. Before returning

the

the

airplane

to service make sure that the

plunger

is

pushed

down and

safety wired

to the

service valve bracket. CAUTION: If the plunger on the service valve is pushed down while the is

on

and the

landing

landing gear is retracted, the electrical power position, the landing gear will extend

gear control handle is in the down

immediately. pack contains a cap and dipstick assembly graduated in in maintaining the system fluid level. The fill reservoir is accessible temperature for convenience inboard of LH nacelle. the access door A fill reservoir

adjacent

to the power

32-30-00

degrees through

of fluid a

small

Rayfheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXTENSION AND RETRACTION -TROUBLESHOOTING

airplane has experienced abnormal landing gear procedures of any type, as a safety precaution, place the airplane on jacks prior to performing any inspection or maintenance. Ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

WARNING: When

CAUTION:

an

of an airplane for the purpose of landing gear operation, inspection, servicing or maintenance, should be accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary to jack the airplane in the open, wind velocity in any direction and terrain variations,

Jacking

must be

compensated for prior to jacking

the

airplane.

damage to the airplane in case of accidental landing gear retraction, place the airplane jacks (3, Chart 1,32-00-00) as instructed in Chapter 7 when troubleshooting the landing gear

WARNING: To avoid on

system.

hydraulic system or do maintenance or rigging of the airplane on jacks (3, Chart 1, 32-00-00). Stay clear of the wheel wells, landing gears and gear doors while the landing gear is in operation. Never service the accumulator

landing

When

gear without first

jacking

encountered,

Any

time the

the

or

placing

the

the

airplane in an unsheltered area jack more than one gear clear

never

landing

gear is only

where winds in of the

ground

excess

of 35 knots may be

at a time.

partially retracted during maintenance, always cycle the gear one complete cycle before removing the airplane from the

with the power pack through at least Jacks.

landing gear system using Charts 101 through 104 in this section and items 3 through 8, 14 and 15 in Chart 1, 32-00-00. Before using the troubleshooting charts, ensure that the auxiliary ground power unit is set

Troubleshoot the

at 28 VDC and that the

battery has

a

charge

of at least 20 VDC.

a loose or damaged electrical connection. Ensure that all connectors are clean and Repair or replace any damaged or loose connector pins. Refer to the applicable wiring diagram manual for specific pin and plug locations.

Many faults

can

be traced to

free of corrosion.

Follow the steps in the troubleshooting charts sequentially unless otherwise instructed. For next step when there are no instructions immediately following a NO condition.

example, proceed to the

32-30-00Page

101

Raldheon

Aircraft

Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

Chart 101

TROUBLESHOOTING

Landing STEP 1

Gear Takes

LANDING GEAR RETRACTION AND EXTENSION

Longer That

10 Seconds To Retract Or Extend

Does the landing gear take longer that 10 seconds both to retract and extend?

YES

Go to

Step

4.

NO STEP 2

Does the

landing gear take seconds to extend only?

longer than

10

YES

Refer to Chart 102.

longer than

10

YES

Go to

YES

Replace

YES

Refer to Chart 102.

NO

STEP 3

Does the landing gear take seconds to retract only?

Step

5.

NO

Refer to Chart 102. STEP 4

The power

pack

is not

developing full operating

the power

pack.

power, possibly due to a defective valve. Check the power pack as instructed in

TROUBLESHOOTING HYDRAULIC POWER PACK ASSEMBLY. Is the power

pack

defective? NO

Refer to Chart 102. STEP 5

Is the emergency extension hand pump handle stowed properly?’

NO Stow the hand pump handle in the NOTE

securing clip.

If the hand pump handle is not in the stowed position, the hand pump internal relief valve is not open.

Apr

28/0632130-00

A20

Raytheon

AiKraft

company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102 LANDING GEAR RETRACTION AND EXTENSION

TROUBLESHOOTING Power STEP 1

Pump

Motor Runs

Longer Than

Does the pump motor run between 10 and 20 seconds without tripping the landing gear

10 Seconds

YES

Go to

YES

The gear-up pressure switch is not

Step

6.

control circuit breaker? NO STEP 2

Does the pump motor run 10 to 15 seconds on the retraction cycle only, with the landing gear control circuit breaker tripping after the gear is

high pressure (2,720 Replace the switch.

at

to

opening

2,830 psig).

retracted? NO

STEP 3

Does the pump motor run 10 to 15 seconds on the extension cycle only, with the landing gear control circuit breaker tripping after the gear is

YES

nose gear downlock switch or the main gear drag brace downlock switches are out of adjustment or defective. Adjust the

The

switch(es) as instructed in 32-60-00. Replace any defective switch.

extended?

NO STEP 4

Does the pump motor run 10 to 15 seconds longer on both the extension and retraction

cycles,

with the

breaker

tripping

or

YES

Go to

Step

9.

YES

Go to

Step

11.

YES

Find and correct the

gear control circuit after the gear is retracted or

landing

extended? NO STEP 5

Does the pump motor cycle excessively when landing gear is in the retracted position?’

the

*NOTE

After the

landing gear

is retracted, it is normal

for the pump motor to run momentarily, once during the first five minutes after retraction and

again approximately 30 minutes later. This is caused by temperature changes in the hydraulic fluid, by slight internal fluid leakage, or by air in the hydraulic system. STEP 6

Is the pump motor

receiving

less than 28 VDC?

cause

of the low

voltage. NO STEP 7

Is the

fluid?

landing

gear system low

on

hydraulic

YES

the fluid. Check the system for leaks and correct any faults. If the low fluid

Replenish level level

light did sensing

not

illuminate, check the fluid

circuit and correct any

defects.

A20

32-30-00

Zr~Page

103

RBYtheOn

AsKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102 LANDING GEAR RETRACTION AND EXTENSION

TROUBLESHOOTING Power

Pump

Motor Runs

Longer

(Continued)

Than 10 Seconds

1~SO STEP 8 STEP 9

The pump motor is weak. Is the time the time

delay circuit malfunctioning? Check

delay assembly as

YES

Replace

the motor.

YES

Replace

the time

YES

Replace

the pump motor

delay

PCB.

instructed in TIME

DELAY PCB. NO

STEP 10

Are the pump motor

relay

contacts stuck

or

relay.

fused? STEP 11

Charge the accumulator as instructed in Chapter 12-10-00. Check the charging

Is the accumulator pressure less than 750 PSI?

valve for leaks. NO STEP 12

Is there excessive fluid actuator

piston

leakage past the

YES

Replace

the seals.

YES

Replace

the power

seals? NO

STEP 13

defective valve in the power pack assembly? Check the power pack as instructed Is there

a

pack.

in TROUBLESHOOTING THE HYDRAULIC POWER PACK ASSEMBLY.

Apr

28/06Page

104

32-30-00

A20

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 103

TROUBLESHOOTING

LANDING GEAR RETRACTION AND EXTENSION Gear Will Not Extend

Landing STEP 1

Is the

landing

gear control circuit breaker

open?

YES

Reset the circuit breaker. Go to

Step

6.

YES

Reset the circuit breaker. Go to

Step

12.

YES

Push the knob down and

NO STEP 2

Is the power

pack pump

motor circuit breaker

open? NO STEP 3

Is the red knob

on

the service valve in the up

safety

position?

wire. Place the

the knob and

secure

secure

it with

safety device pin.

over

it with the

NO

STEP 4

Are the service valve switches defective?

the switches.

YES

Replace

YES

If there is

NO

STEP 5

Does the pump motor relay coil receive power from the nose gear actuator downlock switch and the main gear downlock switches? Check for continuity through the switches with the

airplane

on

retracted

and the landing gear instructed in 32-60-00.

jacks

as

no

switch(es)

continuity, adjust

the

instructed in 32-60-00. If

as

switch is defective,

a

replace it.

partially

NO Go to STEP 6 STEP 7

Step

16.

Does the circuit breaker open

Is the time

delay

circuit

again?

tripping

the breaker in

less than 15 seconds? Check the circuit

YES

Go to

YES

Replace

YES

Check each circuit and correct any faults.

YES

Replace

the

relay.

YES

Replace

the

solenoid(s).

Step

7.

the PCB.

as

instructed in TROUBLESHOOTING THE TIME DELAY PCB.

NO STEP 8

Is the control circuit

(up

or

down)

shorted to

ground? NO

STEP 9

Is the pump motor

relay coil shorted

to

ground?

NO STEP 10

A20

Are the gear-up or gear-down selector solenoids shorted to ground?

32-30-00Page

105

RBytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 103

TROUBLESHOOTING

LANDING GEAR RETRACTION AND EXTENSION

Landing

(Continued)

Gear Will Not Extend

NO STEP 11

Is the circuit breaker defective?

STEP 12

Does the circuit breaker open

STEP 13

Is the power circuit shorted to structure?

again?

YES

Replace

the circuit breaker.

YES

Go to

YES

Check the circuit and correct any faults.

YES

Replace

the pump motor.

Replace

the circuit breaker.

Step

13.

NO STEP 14

Are the pump motor

windings

shorted to

ground? NO STEP 15

Is the circuit breaker defective?

YES

STEP 16

Is there an open circuit between the selector valve gear down solenoid and the three downlock switches?

YES

Check for loose

continuity.

broken wires and loss of

or

Correct any faults.

NO

STEP 17

Is the gear selector solenoid valve stuck in the up mode? Listen for an audible click (to indicate the valve is

shifting)

YES

If there is

no

click, replace the valve.

when the

control handle is moved to

landing gear gear-down position.

NO STEP 18

an open circuit between the landing control circuit breaker and the gear gear selector switch?

Is there

YES

Check for loose

or

broken wires and loss of

continuity. Correct any

faults.

NO STEP 19

Is the pump motor relay coil open or improperly Check for continuity between the

YES

grounded?

power terminal of the coil and

Ground the coil motor

correctly. Replace relay if the coil is open.

the

ground.

NO

STEP 20

windings open or improperly grounded? Check for continuity between the positive terminal of the pump motor and ground.

Are the pump motor

YES

Ground the motor if the

windings correctly. Replace the windings are open.

NO STEP 21

Is the time delay assembly opening the circuit prematurely? Check the assembly as instructed

YES

Replace

the time

delay

PCB.

in TROUBLESHOOTING THE TIME DELAY

PCB.

Apr

28/06Page

106

32-30-00

A20

ROYntlOOn

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 104

TROUBLESHOOTING

LANDING GEAR RETRACTION AND EXTENSION

Landing STEP 1

Is the

landing

Gear Will Not Retract

gear control circuit breaker

open?

YES

Reset the circuit breaker. Go to

Step

7.

YES

Reset the circuit breaker. Go to

Step

13.

NO STEP 2

Is the power

pack

pump motor circuit breaker

open? NO STEP 3

Is the emergency extension hand pump handle out of its stowed

YES

Correctly stow the hand pump securing clip.

handle under

the

position?’ NO

NOTE

STEP 4

If the hand pump handle is not stowed, the hand pump internal relief valve is not open. Is the red knob

on

the service valve in the up

YES

Push the knob down and

safety

position?

wire. Place the

the knob and

secure

secure

safety

it with

device

it with the

over

pin.

NO STEP 5

Are the service valve switches defective?

YES

Replace

the switches.

NO

STEP 6

landing gear safety switch close Check for continuity through the

Does the RH

improperly? switch with

weight

off the gear

as

YES

If there is the switch

no

continuity, adjust

or

replace

instructed in 32-60-00.

as

instructed in

32-60-00.

NO STEP 7

Does the circuit breaker open

STEP 8

Is the time

again?

delay circuit tripping the breaker

less than 15 seconds? Check the circuit

in

YES

Go to

YES

Replace

YES

Check each circuit and correct any faults.

YES

Replace

the

relay.

YES

Replace

the

solenoid(s).

Step

8.

the PCB.

as

instructed in TROUBLESHOOTING THE TIME DELAY PCB.

NO STEP 9

Is the control circuit

(up

or

down) shorted

to

ground? NO STEP 10

Is the pump motor

relay

coil shorted to

ground?

NO STEP 11

A20

Is the gear-up or gear-down selector solenoid shorted to ground?

32-30-00

Apr

28/06Page

107

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 104 LANDING GEAR RETRACTION AND EXTENSION

TROUBLESHOOTING

Landing Gear

(Continued)

Will Not Retract

NO STEP 12

Is the circuit breaker defective?

STEP 13

Does the circuit breaker open

STEP 14

Is the power circuit shorted to structure?

again?

the circuit breaker.

YES

Replace

YES

Go to

YES

Check the circuit and correct any faults.

YES

Replace

the pump motor.

the circuit breaker.

Step

14.

NO STEP 15

Are the pump motor

windings

shorted to

ground? NO STEP 16

Is the circuit breaker defective?

YES

Replace

STEP 17

Does the pressure switch close improperly at Iow pressure? Check for continuity between

YES

If there is

no

continuity, replace

the switch.

If there is

no

continuity, adjust

replace

pins B and C

as

instructed in 32-30-00. NO

STEP 18

Does the gear-up solenoid energize improperly? Check for continuity through the LH

safety

switch with

weight

off the gear

YES

the switch

as

or

instructed in 32-60-00.

as

instructed in 32-60-00. NO

STEP 19

Is the gear selector solenoid valve stuck in the an audible click (to

YES

If there is

no

click, replace the valve.

down mode? Listen for

indicate the valve is

shifting)

when the

landing

gear control handle is moved to the gear-up

position. NO STEP 20

an open circuit between the landing circuit breaker and the gear control gear selector switch?

Is there

YES

Check the circuit for loose and loss of

continuity.

or

broken wires

Correct any faults.

NO

STEP 21

Is the pump motor relay coil open or improperly Check for continuity between the

YES

power terminal of the coil and STEP 22

correctly. Replace

the

relay if the coil is open.

ground.

windings open or improperly grounded? Check for continuity between the positive terminal of the coil and ground.

Are the pump motor

Ground the coil motor

grounded?

YES

Ground the motor if the

windings correctly. Replace the windings are open.

NO

Page

10832-30-00

A20

Raytheon

nircrart Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 104

TROUBLESHOOTING

LANDING GEAR RETRACTION AND EXTENSION

Landing Gear STEP 23

(Continued)

Will Not Retract YES

delay assembly opening the circuit prematurely? Check the assembly as instructed Is the time

Replace

the time

delay

PCB.

in TROUBLESHOOTING THE TIME DELAY PCB.

TIME DELA Y PCB

delay assembly will energize the logic relay anytime the power pack pump motor continues to run longer than approximately 14 seconds. When the logic relay is energized, it will interrupt current to the pump motor and apply ground to the 2-ampere control circuit breaker, causing it to open. Should the time delay circuit malfunction The time

for any reason, and should the gear-up pressure switch or the nose gear actuator downlock switch or the main gear drag brace downlock switches fail to interrupt power to the power pack motor, serious damage to the motor could result. Check the time

delay assembly

for proper

PCB from the

operation

as

follows:

airplane.

a.

Remove the time

b.

Assemble and connect the components of the functional test equipment (4, Chart 1,

assembly

as

delay

shown in

Figure

32-00-00)

to the time

delay

101.

ON

S1

P------

as

os

25 VDC

Fl

OFF

L1

327 BULB IN APPROPRIATE LAMP HOLDER

S1

ALCOSWITCH TOGGLE SWITCH MST 105D 2´•AMP FUSE AND HOLDER

Fl

UNIT UNDER TEST

300-603-35

Time

Delay Relay Functional

Figure

A20

Check Circuit

101

32-30-00

Apr 28/06Page

109

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

switch.

c.

Apply powertothe

d.

Turn switch S1 ON. After asse

e.

a

time

delay of

14 f3

seconds, lamp L1 should illuminate; if not, replace the time delay

mbly.

Remove the test

and install the time

equipment

delay

PCB in the

airplane.

HYDRA ULIC POWER PACK ASSEMBL Y GEAR-UP PRESSURE SWITCH a.

Connect the

hydraulic

up port of the power

pump

(5

or

6, Chart 1, 32-00-00) and pressure gage (7, Chart 1, 32-00-00) to the gear-

pack.

NOTE: Connect the

hydraulic pump and pressure gage to the gear-up port of the power the pump at any other location in the hydraulic system.

b.

Slowly apply

c.

Connect the circuit checker

do not connect

pressure with the hydraulic pump while monitoring the circuit checker and the pressure gage. The switch should actuate (indicated by a loss of continuity) at a pressure of 2,720 to 2,830 psig. pressure or

ohmmeter

(8,

Chart 1,

connector. The circuit checker should indicate

d.

pack only;

32-00-00) to pins B and C of the pressure switch continuity between the pins.

electrical

Decrease the pressure slowly while monitoring the circuit checker and the pressure gage. The pressure switch should deactuate (indicated by regaining continuity) at 300 to 400 psig below the pressure at which the switch actuated.

GEAR-UP PRESSURE CHECK VALVE, HAND PUMP DUMP VALVE, VENT VALVE AND THERMAL RELIEF VALVE

Connect the

a.

hydraulic pump (5 pack.

or

6, Chart i, 32-00-00) and pressure gage (7, Chart 1, 32-00-00)

to the gear-

up port of the power

NOTE: Connect the

hydraulic pump and pressure gage to the gear-up port of the power the pump at any other location in the hydraulic system.

b.

Apply

a

valve is

pressure of 50 to 60

psig

and stop

pumping;

the pressure should

drop

to

Apply

d.

Slowly

the pressure decreases. The pressure indication should stabilize at 3,150 pressure at which the thermal relief valve has closed.

Apr

(indicating

that the vent

open). a

loss of

increase the pressure while monitoring the pressure gage. The thermal relief valve should relieve at a pressure of 3,500 ~50 psig. Stop pumping after the thermal relief valve has cracked and monitor the pressure

gage

f.

zero

do not connect

a pressure of 2,800 psig. Allow the pressure gage to stabilize. The gage should not indicate pressure due to an internal leakage.

c.

e.

pack only;

as

psig minimum, indicating

the

Relieve the pressure to 100 to 110 psig; the pressure should hold (indicating that the vent valve is closed). Continue to bleed off the pressure; when the pressure reaches 80 psig, the vent valve should open and drop the pressure to

zero.

Disconnect the

equipment.

32-30-00

a2o

Ral~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SYSTEM PRESSURE RELIEF VALVE

6, Chart 1, 32-00-00) and pressure

a.

If the power pack is out of the airplane, connect the hydraulic pump (5 gage (7, Chart 1, 32-00-00) to the power pack auxiliary pressure port.

b.

If the power pack is in the airplane, connect the hydraulic pump (5 or 6, Chart 1, 32-00-00) and pressure gage (7, Chart 1, 32-00-00) to the gear-down port of the power pack, pull the 60-amp motor circuit breaker, place the landing gear control switch in the down position, and connect an external power supply (28 f0.25 volts) to the

or

airplane. hydraulic pump and the pressure gage to the gear-down or auxiliary pressure port of the power do not connect the pump at any other location in the hydraulic system.

NOTE: Connect the

pack only; c.

pressure. Some leakage through the gear select valve is normal. Increase the pressure while monitoring the pressure gage. The pressure relief valve should relieve at a pressure of 3,250 f50 psig. Stop pumping after the system pressure relief valve has cracked and monitor the pressure gage as the pressure decreases. The pressure indication should stabilize at 2,900 psig minimum, indicating the pressure at which the valve has

Apply

closed. d.

Disconnectthe

testequipment.

32-30-00Page

111

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXTENSION AND RETRACTION WARNING: When

MAINTENANCE PRACTICES

maintenance

performing

hydraulically operated landing gear system, be aware that hydraulic cylinder can displace hydraulic fluid and cause any other movement of actuator unanticipated cylinders in the landing gear retraction system. of the accumulator can also result in unanticipated movement Servicing landing gear hydraulic of an actuator. Either action can result in an unsafe unlocked landing gear system. Therefore, place the airplane on jacks prior to performing any inspection or maintenance, Cycle the landing gear and ensure that all three landing gears are down and locked prior to removing the aircraft from jacks. movement of

When

maintenance

performing

on a

actuator

a

the

on

hydraulic system,

cleanliness is essential for

maintaining

a

functional and

trouble-free system. Any foreign materials that are allowed to enter the system are damaging to the O-rings, seals, valves and moving parts within the system. Such damage can result in fluid leakage and/or failure of the system

components. Observe the following guidelines when working seal

hydraulic storage

on

the

hydraulic system:

containers to prevent contamination of the

fluid

a.

Completely

b.

Use

only

clean

hydraulic

c.

Use

only

clean

hydraulic fluid when flushing the system

d.

When any lines or hoses are disconnected and/or any components are removed from the system, all openings to prevent the entry of foreign material into the system.

e.

When the system is open,

f.

Keep

g.

If the system becomes contaminated, drain and flush the system with clean

h.

To reduce the

fluid when

filling

hydraulic

during storage.

the system. or

testing any of the system components.

prevent contamination of the hydraulic fluid with other oils

hands and tools free of contaminants

(grease, oil, dirt, etc.)

while

working

on

or

the

hydraulic

plug

or

cap

water.

hydraulic system.

fluid.

possibility of leaks in the hydraulic system, take care when installing hydraulic fittings or components. Anytime a fitting or component is loosened or removed, discard the O-ring and install the fitting or component with a new O-ring. To prevent damage to the O-ring, coat the O-ring and the threads of the fitting or component with hydraulic fluid before installing the O-ring; do not contaminate the O-ring after it is lubricated.

WARNING: Never service the accumulator

landing

gear without first

wheel wells, When

landing

jacking

encountered,

Any time

the

the

gears, and

airplane in

never

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart 1,32-00-00). Stay clear of gear doors while the landing gear is in operation.

jack more

the

or

placing

an

the

unsheltered

than

one

area

where winds in

gear clear of the

ground

at

excess a

the

the

of 35 knots may be

time.

landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the

with the power

jacks. ACCESS PROVISIONS FOR LANDING GEAR COMPONENTS IN LH CENTER SECTION access panels tone upper and two lower) in the LH center section cover the landing gear power pack and related components. The panels extend forward from the main spar to the aft edge of the center section leading edge. A hinged door for the fill reservoir and accumulator is provided in the upper wing panel so that access to either

Three

will not

require removal of the

accumulator, The upper

one or

panel

upper panel. For any maintenance work other than filling the system or charging the all of the center section access panels and/or the center section leading edge must be removed.

can

be removed after

removing

the

screws

from its

perimeter. The

lower

panels

32-30-00

can

be removed

Apr

28/06Page

201

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

removing the screws from the perimeter and the center of each panel. A guard attached to the underside of the upper panel will prevent installation of the panel if the plunger on the service valve is not pushed down. If any difficulty is experienced installing the upper panel, check to ensure that the knob on the service valve is pushed down I and safety wired, and that the plunger retainer is in position and pinned. Refer to Figure 201. after

HYDRAULIC SYSTEM SERVICING

hydraulic landing gear system consists primarily of maintaining the correct fluid level and maintaining precharge. Charge the accumulator, located forward of the power pack, to 800 +50 psi with dry bottled nitrogen (5, Chart 2, 32-00-00) as instructed in Chapter 12. A charging gage is mounted on the accumulator. A fill reservoir, located above the power pack, contains a cap and dipstick assembly graduated in degrees of fluid temperature. Add hydraulic fluid (1, Chart 2, 32-00-00) as required to fill the system. Servicing

the

the correct accumulator

WARNING: Never service the accumulator

landing

gear without first

or

placing

the

the

hydraulic system or do maintenance airplane on jacks (3, Chart 1, 32-00-00).

or

rigging

of the

Stay clear of the wheel wells, landing gears and gear doors while the landing gear is in operation. When jacking the airplane in an unsheltered area where winds in excess of 35 knots may be encountered, never jack more than one gear clear of the ground at a time. Any time

the

landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the

with the power

jacks. Replace the hydraulic system filter at the intervals specified in Chapter 5-1 1-00. Clean the filter screens or the finger in the power pack gear-up and gear-down ports, the filter screen in the fill reservoir outlet port, and the bleed air overboard orifice at the intervals specified in Chapter 5-11-00. screens

FILLING AND BLEEDING THE LANDING GEAR HYDRAULIC SYSTEM The

landing gear system should not need to be filled and bled unless the are opened at the actuators, resulting in a considerable loss of

system lines

jacks (3, Chart 1, 32-00-00)

a.

Place the

b.

Connect

c.

Remove the upper and lower

airplane

an

on

external power

supply

to the

access

as

instructed in

airplane and adjust

panels

as

shown in

Figure

WARNING: Never service the accumulator without first

Never do maintenance

the

power pack is removed or any of the fluid and entry of air into the system.

Chapter

voltage

7.

to 28 ~0.25 volts.

201.

placing

the

airplane

on

jacks (3, Chart 1, 32-00placing the airplane on

rigging of the system without first jacking the airplane in an unsheltered area where winds in excess of 35 knots may be encountered, never jack more than one gear clear of the ground at a time. Any time the landing gear is only partially retracted during maintenance, always cycle the gear with the power pack through at least one complete cycle before removing the airplane from the jacks.

00). jacks (3,

d.

Charge the

Chart 1,

32-00-00).

accumulator to 800 +50

12-10-00.

Apr 28/06Page

202

32-30-00

or

When

psig with

bottled

dry nitrogen (5,

Chart 2,

32-00-00)

as

instructed in

Chapter

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: SCREWS IN THIS PANEL REOUIRE A SPECIAL SCREWDRIVER TIP. SEE CHART i. SPECIAL TOOLS IN CHAPTER 32-0)-00.

/SCAEW

FILLRESERVOIR AND ACCUMULATOR o

o

ACCESS DOOR

t I

o

o,~

UPPER ACCESS

o

PANEL

U

~a

A

MAIN SPAR

LOWERINBOARD ACCESS PANEL

LOWER OUTBOARD ACCESS PANEL

DETAIL

A

d

SCREW 350-1M

Access Provisions for

A20

Landing Gear Components Figure 201

in LH Center Section

32-30-00Page~

203

Ray~heMI

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL NOTE: The

regulated power pack.

e.

Locate the

supply f.

cross

power

fitting forward psi dry air to

of 18 to 20

Pull the

00-ampere power pack

raise it to the full up g.

supply

position.

should

incorporate

of the power the fitting.

pack,

a

shutoff valve to control the flow of

remove

the cap from the

fitting

pressurized

and connect

a

air to the

regulated

motor circuit breaker. Unstow the emergency extension hand pump handle and

Place the

plunger

on

the service valve in the down

Bleed the hand pump suction and pressure lines to the service valve

as

position.

follows:

1.

Disconnect the hand pump suction line at the hand pump. Disconnect the hand pump pressure line at the service valve. Disconnect the line at the service valve gear-up port and cap the open gear-up port.

2.

With the air pressure shut off, turn the electrical power down position.

CAUTION: Do not exceed

a

fluid

depth

of

one

on

and

place the landing gear control switch

inch above the reservoir outlet. Add

hydraulic

in the

fluid to the fill

reservoir only; do not add fluid to the power pack primary reservoir. 3.

approximately three quarts of hydraulic fluid (1, Chart 2, 32-00-00) to the fill reservoir as fast as the system will accept it while maintaining a fluid depth of approximately one inch above the reservoir outlet.

Add

Connect the suction line to the hand pump when fluid appears at the end of the line.

h.

the hand pump through full strokes as fast as possible until fluid appears at the end of the hand pump pressure line. Stop pumping and connect the hand pump pressure line to the service valve.

4.

Operate

5.

Install and lock the fill reservoir cap.

Bleed the emergency extend lines to the actuators

NOTE: The emergency extend port

on

Stowthe hand pump handle.

2.

Disconnect the emergency extend line from the air

follows:

each actuator is identified with

1.

regulated

as

nose

an

gear actuator.

S.

Quickly pressurize

the system with the

supply. gear actuator when fluid appears at the end of the line.

3.

Connect the emergency extend line to the

4.

fitting in the nose gear actuator emergency extend port just enough to allow a fitting. Operate the hand pump to pressurize the system until hydraulic fluid appears at the fitting and all indications of air have been bled from the line. Tighten the B nut and ensure the fitting is tight in the port.

nose

Loosen the B nut at the

restricted flow of air from the

5.

6.

Apr

28/06Page

Repeat step

4 at each of the

following

locations:

a)

The RH main gear actuator emergency extend line at the actuator emergency extend port.

b)

The LH main gear actuator emergency extend line at the actuator emergency extend port.

c)

The power

d)

The service valve gear-up port

pack hand

pump pressure port.

Shutoff the airsupply.

204

32-30-00

(this will

bleed the retum line from the fill reservoir to the service

valve).

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

7.

Remove the cap and connect the line to the service valve gear-up port.

Bleed the

i.

primary

retract lines as follows:

1.

Disconnect the

2.

Add 4 to 5 quarts of hydraulic fluid to the fill reservoir and pressurize the system.

3.

Connect the retract line to the

4.

Loosen the B nut at the

nose

gear retract line at the

nose

nose

gear actuator.

replace

the cap.

Operate

the hand pump to

gear actuator when fluid appears at the end of the line.

nose gear actuator retract port just enough to allow a restricted flow of hand pump to pressurize the system until hydraulic fluid appears at the fitting and all indications of air have been bled from the line. Tighten the B nut and ensure the fitting is tight in the

air from the

fitting

in the

fitting. Operate the

port.

Repeat step 4

5.

locations:

The RH main gear actuator retract line at the inboard nacelle bulkhead.

b)

The LH main gear actuator retract line at the inboard nacelle bulkhead.

c)

The service valve gear-up port.

d)

The accumulator.

Do not shut off the air supply. Proceed to step j.

Bleed the primary extend lines NOTE: The

primary

as

extend port

follows:

on

each actuator is identified with

a

p.

primary extend port.

i.

Disconnect the line at the

2.

Place the landing gear control switch in the up position.

3.

Connect the primary extend line to the

4.

Loosen the B nut at the fitting in the nose gear actuator primary extend port just enough to allow a restricted flow of air from the fitting. Operate the hand pump to pressurize the system until hydraulic fluid appears at the fitting and all indications of air have been bled from the line. Tighten the B nut and ensure the fitting is

tight 5.

k.

in the

nose

gear actuator

nose

gear actuator when fluid appears at the end of the line.

port.

Repeat step

4 at each of the

following

locations:

a)

The RH main gear

primary

extend line at the inboard nacelle bulkhead.

b)

The LH main gear

primary

extend line at the inboard nacelle bulkhead.

Place the and

I.

following

a)

6.

j.

at each of the

pull

landing gear control switch in the down position. Shut off the air supply, turn off the electrical 2-ampere landing gear control circuit breaker on the pilot’s inboard subpanel.

power

the

Using the emergency extension hand pump, retract and extend the landing gear through several cycles. After cycle, add hydraulic fluid as required until the fluid level in the reservoir stabilizes at the appropriate temperature mark on the dipstick. While cycling the landing gear, check for any signs of hydraulic fluid leakage. Check the pressure in the accumulator with the gear fully retracted and fully extended. The gage should indicate approximately 800 psi with the gear extended and approximately 1,500 psi with the gear retracted. each

n,o

32-30-00

Apr 28/06Page

205

Raytheon

nircraff

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

m.

Cycle the gear several times with the emergency extension properly and that all air is removed from the system.

hand pump to

verify that the landing

gear operates

NOTE: The pressures specified above are approximate indications subject to the size and accuracy of the gage used. The difference between the pressures is more meaningful than the actual pressure indications. n.

2-ampere control circuit breaker and

Reset the

turn the electrical power

on.

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying IS to 20 of regulated dry air to the power pack reservoir during ground operation of the power pack. the

When

cycling

and

five minute

a

landing gear with the power pack, cooling period every five cycles.

Ensure the

the service valve is

plunger on

minute

a one

cooling period between cycles

be careful not to overfill the system,

adding hydraulic fluid to the reservoir, dumped overboard. Place a bucket under the

NOTE: When

o.

allow

overboard drain tube to catch the down and

pushed

safety wired,

the

psi

as excess

excess

plunger

fluid will be

fluid.

retainer is in

position

and

the hand pump handle is in the stowed position and the system is pressurized with air. Operate the gear a minimum of ten complete cycles with the hydraulic power pack. Every third or fourth cycle of the

pinned, landing landing gear, shut off the air supply, check the fluid level in the reservoir, and add fluid as required until the fluid level stabilizes at the appropriate temperature mark on the dipstick. While cycling the landing gear, check for any signs of hydraulic fluid leakage. Check the pressure in the accumulator with the gear fully retracted and fully extended. The gage should indicate approximately 800 psi with the gear extended and 2,600 to 2,700 psi with the gear retracted. NOTE: The pressures specified above are approximate indications subject to the size and accuracy of the gage used. The difference between the pressures is more meaningful than the actual pressure indications.

supply.

Disconnect the air

p.

Shut off the air

q.

Install the upper and lower

access

Disconnect the external power

supply

panels

supply

as

line from the

shown in

from the

Figure

cross

fitting

and

replace

the cap

on

the

fitting.

201.

airplane.

removing the airplane from the jacks, make sure that the hand pump handle is in the stowed position; that the plungeron the service valve is pushed down and safety wired with the plunger retainer in position and pinned; that the landing gear control handle is in the down position; and that the landing

CAUTION: Before

gear is down and locked. s.

Remove the

airplane from

the

jacks.

BLEEDING THE MAIN GEAR ACTUA TOR trapped air from the main gear actuator after the system lines are opened at the actuator. Bleed

airplane

jacks (3,

a.

Place the

b.

Connect

c.

Remove the upper and lower

Apr

28/06Page

206

an

on

external power

Chart 1,

supply

32-00-00)

to the

access

32-30-00

airplane

panels

as

as

actuator has been

instructed in

and

adjust

shown in

the

Figure

replaced

or

when any of the

Chapter 7.

voltage 201.

to 28 ~0.25 volts.

hydraulic

Ralfheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart i, 32-00-00). Stay clear of doors while the landing gear is in operation.

WARNING: Never service the accumulator of the

landing

gear without first

wheel wells, When

landing

jacking

encountered,

the

placing

the

gears and gear

airplane in an unsheltered area where winds in excess jack more than one gear clear of the ground at a time.

the the

of 35 knots may be

never

Any time the landing gear is only partially retracted during maintenance, always cycle the gear with the power pack through at least one complete cycle before removing the airplane from the jacks. d.

Ensure the accumulator is

Chapter

regulated power pack.

NOTE: The

e.

charged

to 800 f50

with bottled

psig

nitrogen (5,

Chart 2, 32-00-00)

instructed in

as

12-10-00.

Locate the

supply of

cross

power

supply

fitting forward psi dry air to

18 to 20

should

incorporate

of the power

the

pack,

a

shutoff valve to control the flow of

the cap from the

remove

fitting

air to the

pressurized

and connect

a

regulated

fitting.

2-ampere landing gear control circuit breaker.

f.

Pull the

g.

Bleed the retract line and the nacelle bulkhead

fitting

as

SYSTEM. Bleed the lines

primary and emergency extend lines at the actuator fittings and at the inboard instructed in FILLING AND BLEEDING THE HYDRAULIC LANDING GEAR

individually

until fluid appears at the

and all indications of air

fittings

are

eliminated

from the lines.

airsupply.

h.

Shutoff the

i.

Fill the fluid reservoir

j.

Reset the

landing

as

required

to

replace the fluid

lost in

bleeding.

gear control circuit breaker and restore the air

supply.

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psi of regulated dry air to the power pack reservoir during ground operation of the power pack. When cycling the landing gear with the power pack, allow a one minute cooling period between cycles and a five minute

cooling period every five cycles.

air that may have been

landing gear with trapped.

I.

Shut off the air

Disconnect the air

m.

Fill the fluid reservoir

k.

Extend and retract the

supply.

as

required

to

the power

supply

replace any

pack through

from the

cross

ten

complete cycles

fitting

fluid lost from the

and

to

displace

replace the cap

displacement of trapped

on

the

any residual

fitting.

air.

BLEEDING THE NOSE GEAR ACTUATOR Bleed

trapped

system lines

air from the

are

opened

nose

gear actuator after the actuator has been

jacks (3, Chart 1, 32-00-00)

a.

Place the

b.

Connect

c.

Remove the upper and lower

p~o

airplane

an

replaced

or

when any of the

hydraulic

at the actuator.

on

external power

supply to access

the

airplane

panels

as

as

instructed in

and

adjust

shown in

the

Figure

Chapter 7.

voltage

to 28 ~0.25 volts.

201.

32-30-00

Apr

28/06Page

207

Ral~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WARNING: Never service the accumulator

landing

gear without first

wheel wells,

placing

hydraulic system or do maintenance or rigging of the airplane on jacks (3, Chart 1, 32-00-00). Stay clear of the doors while the landing gear is in operation. When jacking

the

or

the

landing

gears and gear unsheltered area where winds in

the

excess of 35 knots may be encountered, airplane in an than of the clear one gear never jack more ground at a time. Any time the landing gear is only retracted during maintenance, always cycle the gear with the power pack through at partially least one complete cycle before removing the airplane from the jacks.

d.

Ensure the accumulator is

Chapter

charged

to 800 +50

with bottled

psig

NOTE: The

regulated power supply should incorporate power pack.

e.

Locate the

supply f. g.

cross

fitting forward psi dry air to

of 18 to 20

Pull the

Chart 2,

nitrogen (5,

32-00-00)

instructed in

as

12-10-00.

e-ampere landing

of the power the fitting.

pack,

shutoff valve to control the flow of

a

the cap from the

remove

fitting

pressurized

and connect

a

air to the

regulated

gear control circuit breaker.

primary and emergency extend lines at the actuator fittings as instructed in filling hydraulic landing gear system. Bleed the lines individually until fluid appears at the fittings and

Bleed the retract line and the and

bleeding

the

all indications of air

are

h.

Shutoff the

i.

Fill the fluid reservoir

j.

Reset the

eliminated from the lines.

airsupply.

landing

as

required

to

replace

the fluid lost in

bleeding.

gear control circuit breaker and restore the air

supply.

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psi of regulated dry air to the power pack reservoir during ground operation of the power pack. When cycling the

landing gear with the power pack, allow cooling period every five cycles.

a one

minute

cooling period between cycles

and

a

five

minute

Extend and retract the air that may have been

landing gear with trapped.

i.

Shut off the air

Disconnect the air

m.

Fill the fluid reservoir

k.

supply.

as

required

to

the power

pack through

supply from

replace

the

cross

ten

complete cycles

fitting

any fluid lost from the

and

replace

to

displace

the cap

displacement of trapped

on

the

any residual

fitting.

air.

BLEEDING THE POWER PACK

trapped air from the power pack after the power pack or the power pack filter (refer to Figure 202) has been replaced or when any of the hydraulic system lines are opened at the power pack.

Bleed

a.

Place the

b.

Connect

c.

Remove the upper and lower

Apr

28/06Page

208

airplane

an

on

jacks (3, Chart 1, 32-00-00)

external power supply to the access

32-30-00

airplane

panels

as

as

instructed in

and

adjust

shown in

the

Figure

Chapter

voltage

7.

to 28 ~0.25 volts.

201.

A20

RaytheOn

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POWER PACK MOTOR

PRESSURE SWITCH

D

O-RING

HAND PUMP

t

FILTER ELEMENT

PRESSURE FILTER HOUSING

O-RING

FILTER HOUSING GEAR DOWN

--L

GEAR UP

AIRIGHT POWER PACK FILTER

GEAR DOWN

HAND PUMP PRESSURE

rGEAR UP

I

i

I O-RING FILTER ELEMENT

MODE SELECTOR VALVE

FILTER HOUSING CAP

FILTER HOUSING CAP

POWER PACK MOTOR

V~CKERS POWER PACK FILTER

Hydraulic System Figure 202

A20

2m2cl-te

Filter

32-30-00

209

Rayfheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart 1, 32-00-00). Stay clear of landing placing wheel wells, landing gears and gear doors while the landing gear is in operation.

WARNING: Never service the accumulator gear without first

When

jacking

encountered,

the

the

or

the

airplane in an unsheltered area where winds in excess jack more than one gear clear of the ground at a time.

the the

of 35 knots may be

never

Any time the landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the jacks.

with the power

d.

Ensure the accumulator is

Chapter NOTE: The

charged

to 800 f50

psig

with bottled

nitrogen (5, Chart 2, 32-00-00)

instructed in

as

12.

regulated pack.

power

supply

should

incorporate

a

shutoff valve to control the flow of

pressurized air

to the

power e.

Locate the

supply

cross

fitting forward of the power pack, remove the cap from the fitting and psi dry air to the fitting. Shut off the air supply.

connect

a

regulated

of 18 to 20

f.

Pull the 2-ampere

g.

Add

h.

Reset the landing gear control circuit breaker and restore the air supply.

landing

gear control circuit breaker.

hydraulic fluid (1, Chart 2, 32-00-00) to the appropriate temperature mark on the dipstick.

fill reservoir

as

required

until the fluid level stabilizes at the

damage to the pump, never operate the power pack without supplying 18 to 20 psi of regulated dry air to the power pack reservoir during ground operation of the power pack. When cycling the landing gear with the power pack, allow a one minute cooling period between cycles and a five

CAUTION: To prevent serious

minute

cooling period every five cycles.

i.

Extend and retract the landing gear through 10 complete cycles with the power pack to bleed the primary section of the power pack. After every cycle, shut off the air supply and add fluid to the fill reservoiras required to replace any fluid lost from the displacement of trapped air.

j.

Extend and retract the landing gear through several cycles with the emergency extension hand pump to bleed the emergency extend section of the power pack. After every cycle, shut off the air supply and add fluid to the fill reservoir as required to replace any fluid lost from the displacement of trapped air.

k.

If necessary, continue

NOTE: The

Page

hydraulic

cycling

the gear and

adding

fluid level will stabilize when all

32-30-00

fluid to the fill reservoir until the fluid level stabilizes.

trapped

air has been eliminated from the power

pack.

Raytheon

AiKraft Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

BLEEDING THE ACCUMULATOR hydraulically operated landing gear system, be aware that any movement of a hydraulic actuator cylinder can displace hydraulic fluid and cause unanticipated movement of other actuator cylinders in the landing gear retraction system. Servicing of the landing gear hydraulic accumulator can also result in unanticipated movement of an actuator. Either action can result in an unsafe, unlocked landing gear system. Therefore, place the airplane on jacks prior to performing any inspection or maintenance. Cycle the landing gear and ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

WARNING: When

CA UTION:

performing

Jacking

maintenance

on a

airplane for the purpose of landing gear operation, inspection, servicing or maintenance, accomplished within an enclosed building or hangar. In the interest of safety, should it necessary to jack the airplane in the open, wind velocity in any direction and terrain variations, compensated for prior to jacking the airplane.

of an

should be become must be

trapped air from the accumulator after the opened at the accumulator.

Bleed is

airplane

jacks (3,

a.

Place the

b.

Connect

c.

Remove the upper and lower

on

external power

an

Chart 1,

supply

32-00-00)

to the

access

accumulator has been

as

instructed in

airplane and adjust

panels

as

shown in

the

Figure

replaced

Chapter

voltage

or

when the

hydraulic system

7.

to 28 f0.25 volts.

201.

hydraulic system or do maintenance or rigging of landing gear without first placing the airplane on jacks (3, Chart 1, 32-00-00). Stay clear of wheel wells, landing gears and gear doors while the landing gear is in operation,

WARNING: Never service the accumulator

When

jacking

encountered,

the

or

line

the

airplane in an unsheltered area where winds in excess jack more than one gear clear of the ground at a time.

the the

of 35 knots may be

never

Any time the landing gear is only partially retracted during maintenance, always cycle the gear with the power pack through at least one complete cycle before removing the airplane from the jacks. d.

Ensure the accumulator is in

Chapter

regulated power pack.

NOTE: The

e.

Locate the

supply

charged to

800 +50

psig

with bottled

dry nitrogen (5,

Chart 2,

32-00-00)

as

instructed

12-10-00.

cross

power

supply

fitting foMlard psi dry air to

of 18 to 20

should

incorporate

of the power the

pack,

a

shutoff valve to control the flow of

remove

the cap from the

fitting

pressurized

and connect

a

air to the

regulated

fitting.

2-ampere landing gear control circuit breaker.

f.

Pull the

g.

Loosen the

fitting at the bottom of the accumulator and trapped air are eliminated.

allow the

trapped

air to escape.

Tighten

the

fitting

when

all indications of h.

Reset the

landing

gear control circuit breaker.

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psi of regulated dry air to the powerpack reservoir during ground operation of the power pack. When cycling the landing gear with the power pack, allow a one minute cooling period between cycles and a five minute

~ao

cooling period every five cycles.

32-30-00

Apr

28/06Page

211

Rnl(theon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

landing gear with the power pack through ten complete cycles. After every third or fourth supply and add fluid to the fill reservoir as required to replace any fluid lost from the

Extend and retract the

i.

shut off the air

cycle, displacement

of

trapped

air.

Disconnect the air

supply.

j.

Shut off the air

k.

Install the upper and lower

access

from the

supply

panels

shown in

as

fitting

cross

Figure

replace

and

the cap

on

the

fitting.

201.

BLEEDING THE SERVICE VALVE Bleed

air from the service valve after the service valve has been

trapped

system lines is

opened

jacks (3, Chart 1, 32-00-00)

a.

Place the

b.

Connect

c.

Remove the upper and lower

airplane

on

external power

an

supply

to the

access

airplane

panels

WARNING: Never service the accumulator

landing

gear without first

wheel wells, When

landing

jacking

encountered,

Any

replaced

or

when any of the

hydraulic

at the service valve.

time the

the

as

instructed in

and

adjust

shown in

the

Figure

Chapter

voltage

7.

to 28 f0.25 volts.

201.

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart 1, 32-00-00). Stay clear of doors while the landing gear is in operation.

the

the

or

placing

as

the

the

gears and gear

airplane in an unsheltered area jack more than one gear clear

never

where winds in

of the

ground

excess

of 35 knots may be

at a time.

landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the

with the power

jacks. d.

Ensure the accumulator is in

Chapter

regulated power pack.

NOTE: The

e.

Locate the

supply f. g.

cross

power

supply

fitting forward psi dry air to

of 18 to 20

Pull the 2-ampere

landing

Remove the detent Cut the

charged to

800 f50

psig

with bottled

dry nitrogen (5,

Chart 2,

32-00-00)

as

safety

should

incorporate

a

shutoff valve to control the flow of

of the power pack, remove the cap from the the fitting. Shut off the air supply.

fitting

pressurized

and connect

a

gear control circuit breaker.

pin from the service valve plunger pull up the plunger.

retainer and rotate the retainer away from the

landing

gear retract line at the service valve retract port.

i.

Unstow the emergency extension hand pump handle and pump the handle until fluid appears at the all indications of trapped air are eliminated. Tighten the retract line fitting. Push the service valve

plunger down and safety

landing

plunger

retainer

over

the

plunger

and

and install

gear extend line at the service valve extend port.

Loosen the

i.

Pump the hand pump handle until Tighten the extend line fitting.

212

wire. Rotate the

fitting

pin.

k.

Apr 28/06Page

plunger.

wire and

Loosen the

the detent

air to the

regulated

h.

j.

instructed

12-10-00.

fluid appears at the

32-30-00

fitting

and all indications of

trapped

air

are

eliminated.

RaytheMI

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

m.

Reset the

gear control circuit breaker and restore the air

landing

supply.

damage to the pump, never operate the power pack without supplying 18 to 20 psi of regulated d~y air to the powerpack reservoir during ground operation of the power pack. When cycling

CAUTION: To prevent serious

landing gear with the power pack, allow cooling period every five cycles.

the

a one

cooling period

minute

between

cycles

and

a

five

minute n.

Extend and retract the landing gear with the powe r pack through ten complete cycles. After every third or fou rth cycle, shut off the air supply and add fluid to the fill reservoir as required to replace any fluid lost from the displacement of trapped air.

o.

Shut off the air

p.

Install the upper and lower

supply.

supply from

Disconnect the air access

panels

as

the

shown in

cross

Figure

fitting

and

replace the

cap

on

the

fitting.

201.

BLEEDING THE EMERGENCY EXTENSION HAND PUMP Bleed of the

trapped air from the emergency extension hand pump hydraulic system lines is opened at the hand pump.

a.

Place the

b.

Connect

c.

Remove the upper and lower

airplane

an

on

jacks (3,

external power

Chart 1,

supply to

32-00-00)

the

access

airplane

panels

as

as

after the hand pump has been

instructed in

and

adjust

shown in

voltage

the

Figure

Chapter

replaced

or

when any

7.

to 28 f0.25 volts.

201.

or the hydraulic system or do maintenance or rigging of landing gear without first placing the airplane on jacks (3, Chart 1, 32-00-00). Stay clear of wheel wells, landing gears and gear doors while the landing gear is in operation.

WARNING: Never service the accumulator

When

jacking

encountered,

the

airplane in an unsheltered area where winds in excess jack more than one gear clear of the ground at a time.

the the

of 35 knots may be

never

Any time the landing gear is only partially retracted during maintenance, always cycle the gear with the power pack through at least one complete cycle before removing the airplane from the

jacks. d.

Ensure the accumulator is

Chapter NOTE: The

charged to

800 +50

psig

with bottled

nitrogen (5, Chart 2, 32-00-00)

as

instructed in

12-10-00.

regulated pack.

power

supply

should

incorporate

a

shutoff valve to control the flow of

pressurized

air to the

power e.

Locate the

supply

cross

fitting forward of the power pack, remove the cap psi dry air to the fitting. Shut off the air supply.

from the

f.

Pull the 2-ampere

g.

Loosen the hand pump pressure line at the sen/ice valve hand pump port.

h.

and connect

a

regulated

landing

gear control circuit breaker.

Unstow the extension hand pump handle and pump the handle until fluid appears at the fitting and all indications of

i.

fitting

of 18 to 20

trapped

Reset the

air

are

landing

eliminated.

Tighten

the hand pump pressure line

gear control circuit breaker and restore the air

fitting.

supply.

32-30-00Page

213

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psi of regula ted d~y air to the power pack reservoir during ground operation of the power pack. When cycling the

landing gear with the power pack, allow cooling period every five cycles.

a one

minute

cooling period

between

cycles

and

a

five

minute

landing gear with the power pack through ten complete cycles. After every third or fourth supply and add fluid to the fill reservoir as required to replace any fluid lost from the trapped air.

Extend and retract the

j.

shut off the air

cycle, displacement

of

k.

Shut off the air

i.

Install the upper and lower

supply. Disconnect access

the air

supply from

panels

as

the

shown in

cross

Figure

fitting

and

replace

the cap

on

the

fitting.

201.

HYDRAULIC LANDING GEAR FILL RESERVOIR SCREEN The fill reservoir

screen

should be cleaned and

a.

Remove the forward inboard

b.

Disconnect the power pack

access

supply

panel

inspected on

at interval

specified

the bottom of the left

wing

in

Chapter

5.

center section.

line from the lower fill reservoir port and cap the

supply

line to minimize fluid

loss.

NOTE: Place

container under the reservoir and

a

supply

line to catch the

hydraulic

fluid when the

supply

line is

disconnected from the fill reservoir. c.

Remove the union from the lower reservoir port.

d.

Remove the

e.

Clean the

screen

with solvent

f.

Place the

screen

in the reservoir port and install the union.

g.

Install

h.

finger screen

O-ring

a new

Remove the

access

from the lower reservoir port.

(6, Chart 2, 32-00-00)

and connect the power

panel

on

and blow

pack supply line

dry

with

shop

to the reservoir

air.

port.

top of the left wing center section and add hydraulic fluid (1, Chart 2, 32-00-00)

to

the reservoir.

instructed in

i.

Pressurize the landing gear

j.

Loosen the nut at the service valve gear-up port and bleed the air out of the system.

k.

Tighten

i.

Install the upper and lower

hydraulic system

as

Chapter

32-00-00.

the nut at the service valve gear-up port. access

panels.

LANDING GEAR HYDRAULIC SYSTEM FILTER REPLACEMENT Replace

the filter at interval

specified

in

Chapter

5.

NOTE: All filters and

screens in the hydraulic landing gear system must be replaced or cleaned any time any landing hydraulic gear system component (other than filters or screens) is replaced, and at the first after inspection component replacement.

Apr

28/06Page

214

32-30-00

nao

RBYtheMI

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

procedures for the landing gear hydraulic system filter installed on the Vickers and SperryAlright power packs are the same; however, the O-rings for the filter housings have different part numbers. For the Alright power pack, the filter housing O-ring part number is MS28778-

CAUTION: The removal and installation

226. For the

the filter housing

Sper~y- Vickers power pack, O-ring is installed.

O-ring part number is

M528775-122. Ensure

that the correct

NOTE: To minimize fluid loss and prevent system contamination, temporarily plug the filter element port until the new filter is ready to install. Shop towels will be needed to absorb the system fluid that will escape when the filter is removed. a.

Remove the upper and lower

b.

Cut the

c.

Discard the filter element, the filter

d.

Lubricate the

e.

Insert the filter element, the filter element

f.

safety

Lubricate the the filter

wire and

new

new

access

filter

as

shown in

the filter from the power

unscrew

filter element

panels

housing O-ring

O-ring

housing O-ring

with clean

spring

Figure

201.

pack. Refer to Figure

and the filter element

hydraulic

fluid

(1,

with clean

hydraulic fluid (1,

1

ring.

Chart 2,

and the filter element

202.

32-00-00).

O-ring into the

Chart 2,

filter

housing.

32-00-00) and install the O-ring

on

housing. housing into

the power

and

safety

wire.

g.

Install the filter

h.

Fill the reservoir to the proper level and bleed the system LANDING GEAR HYDRAULIC SYSTEM.

pack

as

instructed in FILLING AND BLEEDING THE

LANDING GEAR BLEED AIR PRESSURE OVERBOARD RELIEF ORIFICE SCREEN The bleed air orifice overboard relief

specified

in

Chapter

screen

(refer

to

Figure 203)

should be cleaned and

inspected

at interval

screens in the hydraulic landing gear system must be replaced or cleaned any time hydraulic landing gear system component (other than filters or screens) is replaced, and at the inspection after component replacement.

NOTE: All filters and

a.

Remove the forward inboard

b.

Remove the orifice and the short tubing section from the overboard bleed air line just forward of the

power c.

I

5.

access

panel from

the lower left

wing

any first

center section surface.

landing

gear

pack.

Remove the orifice from the short

tubing

section and blow

through

the orifice with

shop air to

remove

any

possible restrictions. d.

Install the orifice with the hex

on

the overboard side and the short

tubing

section.

Torque

the

inch-pounds. e.

Install the lower

wing

center section

access

panel.

32-30-00

fittings to

40-65

1

RBYtheon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BLEED AIR OMRBOARD RELIEF ORIFICE SCREEN

LOWER WING SKIN CENTER SECTION

rYL~MO

Bleed Air Pressure Overboard Relief Orifice Screen

Figure

203

LANDING GEAR POWER PACK FILTER SCREENS CLEANING AND/OR REPLACEMENT GEAR-UP AND GEAR-DOWN PORT SCREENS

I

The gear-up and

inspected

(SPERRY-VICKERS

gear-down ports of the Sper~y-Vickers specified in Chapter 5-11-00.

power

POWER

pack (refer

to

PACK)

Figure 204)

should be cleaned and

at intervals

hydraulic landing gear system must be replaced or cleaned any time hydraulic landing gear system component (other than filters or screens) is replaced, and at the inspection after component replacement.

NOTE: All filters and

a.

screens

in the

Remove the upper and lower

NOTE: Make

provisions

access

to collect the

panels

hydraulic

Remove the

c.

Remove the unions from the gear-up and

d.

Using

Apr

28/06Page

216

an

shown in

Figure

alien wrench,

remove

gear-down ports

plumbing

is disconnected.

of the power

pack.

gear-down ports.

the permanent

32-30-00

201.

fluid which will be lost when the

lines connected to the gear-up and

b.

hydraulic

as

any first

screens

from the gear-up and

gear-down ports.

A20

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

M)WN PORT

UP PORT

UNION PERMANENT SCREEN QRING

I.

2. 3.

~900´•231-(5

Sperry-Vickers

Power Pack Filter Screens

Figure the ports after the

have been removed.

e.

Plug

f.

Clean the

screens

with solvent

g.

Install the

screens

into the gear-up and

h.

Install

new

204

screens

(6, Chart 2, 32-00-00) and blow dry

O-rings (MS28778-6)

on

gear-down ports

with

of the power

shop

air.

pack.

the unions, and install the unions in the gear-up and

gear-down ports

of the

power pack.

hydraulic

lines to the gear-up and

i.

Install the

j.

Check the system fluid level and add

k.

Install the upper and lower LH

FINGER SCREEN CLEANING

wing

NOTE: All filters and

hydraulic

access

(AIRIGHT

The gear-up and gear-down ports of the at interval specified in Chapter 5.

gear-down ports

(1, Chart 2, 32-00-00)

pack. as

required.

panels.

POWER

Alright

fluid

of the power

PACK)

power

pack (refer

to

Figure 205)

should be cleaned and

inspected

in the

hydraulic landing gear system must be replaced or cleaned any time any hydraulic landing gear system component (other than filters or screens) is replaced, and at the first inspection after component replacement.

A20

screens

32-30-00

Apr

28/06Page

217

RaytheMI

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

a.

Remove the upper and lower

NOTE: Make

provisions

b.

Remove the

c.

Cap

d.

the

to collect the

panels

hydraulic

as

shown in

Figure

201.

fluid which will be lost when the

plumbing and unions from the gear-up and gear-down ports of

plumbing

is disconnected.

the power

pack.

lines.

plumbing

Remove the filter at the

access

screen

with

a

magnet that

can

be inserted into the port,

or

with

a

small wire with

a

45x bend

tip.

the ports after the

have been removed.

e.

Plug

f.

Clean the

screens

g.

Insert the

finger screens

h.

Install

i.

Reconnect the

j.

Install the upper and lower LH

wing

k.

Replace

the fluid that

during

new

screens

with solvent

(6,

32-00-00) and

into the gear-up and

O-rings (MS28778-6) plumbing

Chart 2,

on

blow

dry

with

shop

air.

gear-down ports.

the unions, and install the unions in the gear-up and

gear-down ports.

lines.

was

lost

access

the

panels.

screen

removal with

hydraulic fluid (1, Chart 2, 32-00-00)

as

required.

GEAR DOWN PORT

Power Pack Filter Screens

(AlrigM)

GEAR UP PORT

1

i.

3

UNION

2. SCREEN 3. O-RING

300234-4

Alright

Power Pack Filter Screen

Figure

Apr

28/06Page

218

32-30-00

205

A20

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EMERGENCY EXTENSION HAND PUMP SUCTION LINE FILTER REMOVAL

safety reasons, pull the 5-ampere landing gear relay circuit breaker subpanel and place a note on the circuit breaker panel that WORK IS

WARNING: For

on

the

pilot’s right

IN PROGRESS ON

LANDING GEAR HYDRAULIC SYSTEM. The

landing gear control handle should airplane is on the ground.

never

be moved from the down-and-locked

position

while the

It is recommended that the

area

be

roped off during extension

a.

Remove all power from the airplane and disconnect the reconnecting of airplane electrical power.

b.

Jack the

c.

airplane

hydraulic

Remove the to

Figure

in accordance with

power

Chapter

or

retraction of the

battery. Display warning

notices

landing

gear.

prohibiting

7-00-00.

pack access cover from

the lower left hand side of the

wing

center section. Refer

201.

d.

Remove the hand pump suction line

e.

To minimize fluid lose,

immediately

(B)

nut from the 90" elbow. Refer to

Figure

cap the emergency extension hand pump suction line and the 90" elbow.

NOTE: Provisions should be made to collect the fluid which will be lost when the power

206.

plumbing

is disconnected from the

pack.

(B)

nut at the first

fitting

f.

Loosen the emergency extension hand pump suction line

g.

Move the emergency extension hand pump suction line as necessary to have element, P/N 30579, from the suction line. Refer to Figure 206.

inboard of the power

enough

pack.

the filter

room

to

room

and insert the filter

remove

EMERGENCY EXTENSION HAND PUMP SUCTION LINE FILTER INSTALLATION a.

Move the emergency extension hand pump suction line

element, P/N 30579, into the suction line. Refer

to

as

Figure

b.

Connect the emergency extension hand pump suction line

c.

Tighten

d.

Torque (B)

e.

Service the

f.

Manually

g.

Connect the

the emergency extension hand suction line nuts to 230 to 260

battery

landing gear and

cycle

enough

(B)

to the 90x elbow tube.

nut to the first

fitting

inboard of the power

pack.

inch-pounds.

hydraulic system with hydraulic fluid (1,

extend the

(B)

necessary to have

206.

the

once

Chart 2,

32-00-00)

as

required.

with the emergency extension hand pump.

landing

gear

normally

once

to check for leaks in the

landing gear hydraulic

system. h.

A2a

Bleed the

hydraulic system

as

instructed in BLEEDING THE EMERGENCY EXTENSION HAND PUMP.

32-30-00

219

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

00

O00

HAND PUMP SUCTION LINE

ia~;e ~jJ

POWER PACK

DETAIL A 30579 FILTER ELEMENT. PUMP SUCTION LINE

HAND

FILL LINE

DETAIL

o

B

II

II

DETAIL

"B"NUT~

B

FW2B

003190M

Hand

Pump

Inlet Filter Installation

Figure

Apr

28/06Page

220

32-30-00

206

A20

Ral~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

airplane from the jacks, ensure that the emergency extension hand pump handle position, that the service valve plunger is pushed down and safety-wired with the plunger retainer in position and pinned, that the landing gear control handle is in the DN position and that the landing gear is down and locked.

CAUTION: Before

removing

the

is in the stowed

i.

airplane from jacks airplane to service.

Remove the return

in accordance with

Chapter

7. Remove

warning notices,

restore power, and

POWER PACK REMOVAL a.

Place the

b.

Remove the upper and lower

c.

Remove and

airplane

gear-up and

on

jacks (3,

Chart 1,

access

32-00-00)

panels

as

instructed in

shown in

as

Figure

Chapter 7.

201.

identi~y the electrical wiring from the motor, fluid level gear-down solenoids. Refer to Figure 207.

sensor, gear-up pressure switch and the

hydraulic lines are disconnected from the power pack, plug foreign material into the lines or power pack.

CAUTION: As the of d.

e.

f. g.

1

Remove the

cap all

openings

to

prevent entry

following:

1.

The line from the fill reservoir to the fill port of the power

2.

The line to the hand pump pressure port of the power

3.

The rib channel below the power

4.

The line to the gear-up port of the power

5.

The line to the seal drain port of the power

Disconnect the

following

pack filter to

from the power

pack possible.

pack.

pack:

2.

The line to the

3.

The line to the vent port of the power

bonding jumper from

pack.

pack.

The line to the hand pump suction port of the power

gear-down port

pack.

make removal of the power

1.

Remove the

or

of the power

pack.

pack.

pack.

the motor end of the power

pack.

Supporting the power pack from underneath the wing, cut the safety wire and remove the three bolts and attaching each end of the power pack to the mounting brackets, then lower the power pack away from the airplane. washers

32-30-00

Apr 28/06Page

221

RayBeon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SELECTOR VALVE SOLENOID CONNECTOR

Qbd/:

GEAR-DOWN PORT

MOUNTING BRACKETS

BOLT

WASHER

POWER PACK WASHER BOLT

RETURN FILTER

MOTOR HAND PUMP

PRESSURE PORT

II

GEAR-UP PORT

r

FLUID LEVEL SENSOR

IIC

GEAR-UP PRESSURE

INBOARD

AFT

SWITCH

NEOAT~E TERMINAL

IY-~-2POSITIVE

SEAL DRAIN PORT FILL PORT’ HAND PUMP

-~/j

~WASHER

TERMINAL

SUCTION PORT

JUMPER WASHER LOCK WASHER BOLT

AIRIGM POWER PACK GEAR-UP

PRESSURE SWITCH

~5v/

,POWER PACK VENT PORT

GEAR-DOWN PORT

~ga

HAND

MOTOR

E

PUMP PRESSURE PORT GEAR-UP PORT

II It

FLUID LEVEL

SENSOR

I

NEGATIVE TERMINAL

//dbaOgiI

POSITIVE

TERMINAL

(IC

SEAL DRAIN PORT

WASHER

~h

FILL PORT

INBOARD

)~,BONDINO

JUMPER

WASHER LOCK WASHER

AFT

HAND PUMP SUCTION PORT

SPERRY-VICKERS POWER PACK

Hydraulic

3nrP*a

Power Pack

Figure 207

Page

22232-30-00

A20

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POWER PACK INSTALLA TION a.

Install the power pack through the underside of the wing and position between the mounting brackets. Install three bolts and washers in each end of the power pack and safety wire. Refer to Figure 207.

b.

Secure the

c.

Connect the

d.

e.

bonding jumper to following

the power

pack

with the bolt and washers.

pack:

to the power

1.

The line to the hand pump suction port of the power

2.

The line to the

3.

The line to the vent port of the power

Install

gear-down port

of the power

pack.

pack.

pack.

thefollowing: to the fill

port of the power pack.

1.

The line from the fill

2.

The line from the power extend line.

3.

The rib channel below the power

4.

The line to the gear-up port of the power

5.

The line to the seal drain port of the power

Connect the electrical

can

pack

wiring

hand pump pressure port to the tee in the

nose

gear actuator emergency

pack filter. pack. pack.

to the motor, fluid level sensor, gear-up pressure switch and the gear-up and down

selector valve solenoids. f.

Connect

an

external power

supply

to the

airplane

WARNING: Never service the accumulator

landing

gear without first

wheel wells,

landing

adjust

the

voltage

to 28 ~0.25 volts.

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart 1, 32-00-00). Stay clear of gear doors while the landing gear is in operation. or

placing

gears and

and

the

the

airplane in an unsheltered area where winds in excess encountered, never jack more than one gear clear of the ground at a time. When

jacking

the

the the

of 35 knots may be

Any time the landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the jacks. with the power

g.

Charge the

accumulator to 800 f50

psig

with bottled

dry nitrogen (5,

Chart 2,

32-00-00)

as

instructed in

Chapter

12-10-00.

h.

Fill and bleed the landing gear GEAR HYDRAULIC SYSTEM.

i.

Install the upper and lower

hydraulic system

access

panels

as

as

instructed in FILLING AND BLEEDING THE LANDING

shown in

Figure

201.

32-30-00

Apr

28/06Page

223

1

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Disconnect the external power

j.

supply

from the

airplane.

removing the airplane from the jacks, make sure that the hand pump handle is in the stowed position; that the plunger on the service valve is pushed down and safety wired with the plunger retainer in position and pinned; that the landing gear control handle is in the down position; and that the landing gear is in the down and locked position.

CAUTION: Before

k.

Remove the

airplane

from the

jacks.

POWER PACK MOTOR REMOVAL

jacks (3, Chart 1, 32-00-00)

a.

Place the

b.

Remove the lower

c.

Disconnect the electrical

airplane

on

access

panels

as

shown in

instructed in

as

Figure

Chapter

7.

201.

from the motor. Note the location of the motor terminals

be installed in this

wiring position.

d.

Remove the bolts

securing

e.

Remove the motor from the power

the motor to the power

so

that the motor

(3,

Chart 2,

can

pack.

pack.

POWER PA CK MOTOR INSTALLA TION a.

Coat the motor drive shaft

b.

Mate the motor to the drive shaft

position as positioning of the same

coupling

chamber and the

coupling

shaft

splines

with grease

32-00-00).

coupling splines. Install the motor with the electrical terminals located was removed. Alignment pins on the motor are provided to aid in the the bolts securing the motorto the power pack.

in the

when the motor motor. Install

c.

Connect the electrical

d.

Install the lower

e.

Remove the

wiring

access

airplane

to the motor.

panels

from the

as

shown in

Figure

201.

jacks.

SPERRY-VICKERS SELECTOR VALVE ASSEMBLY REMOVAL NOTE: The

assembly area should be void of materials and equipment not directly associated with assembly of these room temperature/humidity conditions should prevail. Ventilation should be such that outside

units. Normal small

I

a.

particle

debris is not allowed to settle in the

area.

from the filter bowl. Refer

O-ring (2) (1) er uhousing. giF ot

Remove the filter bowl

from the valve

Remove the

208.

(3)

b.

Remove the filter element

c.

Remove the selector valve

from the valve

screws

(5

and

6)

housing.

Remove the

and washers

O-ring (4) from

(7) securing

the filter element.

the selector valve

(8)

to the valve

housing. d.

Remove the selector valve and

e.

Remove the pressure switch

Apr

O-rings (9) from the

(10)

from the valve

28/0632-30-00

valve

housing.

housing. Remove the

O-ring (11)

from the pressure switch.

Raytheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

11

10

13

16

15 17

DETAIL

A

DETAIL

B

11

B

108

16

j

b--t´•

7~ d

5.

I´• X-

~A O

7

3

n~o-nel

Sperry-Vickers

Selector Valve

Figure

A20

Assembly

208

32-30-00

Apr 28/06Page

225

Ra~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL f.

Remove the 14 and

(13,

pressure-operated check valve (hand pump and 15) and the O-ring retainers (16 and 17) from the

gear-up check check valves.

valve) (12). Remove

the

O-rings

SPERRY-VICKERS SELECTOR VALVE ASSEMBLY INSTALLATION NOTE: The

should be void of mate rials and

assembly area

units. Normal

room

small

debris is not allowed to settle in the

particle

temperature/humidity

equipment not directly associated with assembly of these prevail. Ventilation should be such that outside

conditions should area.

a.

Clean and lubricate all parts in clean hydraulic fluid (1, Chart 2, 32-00-00) just prior to lubrication and, in the case of screws to assure more accurate torque readings.

b.

Install the Refer to

I c.

O-rings (13, Figure 208.

14 and

15)

(12) in

Install two check valves

O-ring

and

the valve

retainers

(16

housing. Torque

and

assembly to provide

initial

17)on two pressure-operated check valves (12).

valves to 55

60

inch-pounds.

Secure check valves

to each other with lockwire.

d.

Install the

e.

Position the selector valve

f.

Torque

g.

Install the

O-ring (4)

on

filter element

h.

Install the

O-ring (2)

on

filter bowl

i.

Install the filter bowl

(1)

in the valve

O-ring (9)

the

screws

for the selector valve in valve

to 45

(8) 50

on

the valve

housing.

housing.

Secure with

screws

(5

and

6) and washers (7)

inch-pounds.

(3).

Install the

filter element in the valve

new

housing.

(1).

housing (hand tight).

GEAR-UP PRESSURE SWITCH REMOVAL a.

Place the

b.

Remove the lower

airplane

on

jacks (3, Chart 1, 32-00-00)

access

panels

as

shown in

as

instructed in

Figure

Chapter 7.

201.

NOTE: The pressure switch is located on the motor end of the Alright power pack. The pressure switch is located on the end opposite the motor on the Sperry-Vickers power pack. c.

Disconnect the electrical

d.

Unscrew the gear-up pressure switch from the power

wiring

from the switch.

pack

and

plug the port.

NOTE: Shop towels will be needed to absorb the system fluid which will escape from the port when the switch is removed.

GEAR-UP PRESSURE SWITCH INSTALLATION

O-ring (MS28778-4)

a.

Install

b.

Install the pressure switch

c.

Connect the electrical

d.

Add

Apr

a new

hydraulic fluid (1,

28/065"2~

on

the pressure switch.

by screwing it

wiring

into the power

pack. Torque

to 50

60

inch-pounds.

to the switch.

Chart 2,

32-00-00)

32-30-00

to the fill reservoir up to the

appropriate

fill mark

on

the

dipstick.

A20

Ray~hwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

e.

Install the lower

f.

Remove the

access

airplane

panels

from the

shown in

as

Figure

201.

jacks.

FLUID LEVEL SENSOR REMOVAL a.

Place the

b.

Remove the lower access

c.

Disconnect the electrical

d.

Place

a

down to e.

airplane

on

panels

wiring

container under the a

sensor

as

32-00-00)

shown in

from the

instructed in

as

Figure

Chapter

7.

201.

sensor.

airplane. Open the

level lower than the

Disconnect the

Chart 1,

jacks (3,

line at the power pack fill port and drain fluid from the fill reservoir

sensor.

from the power

pack.

FLUID LEVEL SENSOR INSTALLATION

O-ring (MS28778-8)

a.

Install

b.

Install the

c.

Connect the electrical

d.

Add

e.

Test the sensor’s electrical circuit

a new

sensor

hydraulic

into the power

fluid

wiring

on

the

pack.

sensor.

The

should be installed hand

sensor

tight only.

to the sensor.

(1, Chart 2, 32-00-00)

to the fill reservoir up to the

by pressing

the

hydraulic fluid

appropriate

sensor

fill mark

test switch

on

on

the

the

pilot’s

dipstick. inboard

subpanel. f.

Install the lower

g.

Removethe

access

panels

as

shown in

Figure

201.

airplanefromthejacks.

HYDRAULIC FLUID FILL RESERVOIR REMOVAL a.

b.

Place the

airplane

on

jacks (3, Chart 1, 32-00-00)

Remove the upper and lower

access

as

instructed in

Chapter

panels and the leading edge of the

7.

left center section

as

shown in

Figure

201. c.

Disconnect and cap the two upper tube assemblies reservoir (1). Refer to Figure 209.

d.

Disconnect and cap the fluid

NOTE: Place

a

f.

Drain the

T-fitting

screw

11) from

from the port

the ports

on

on

the inboard side of the

the inboard side of the reservoir sump.

supply/return T-fitting

to catch the

hydraulic fluid

is disconnected from the fill reservoir.

hydraulic fluid

Remove the

supply/return T-fitting (5)

and

suitable container under the reservoir and fluid

when the e.

(10

(18),

from the reservoir into washer

(10)

and

a

suitable container.

nut(l5)securing the

cap

assembly chain terminal (17) to the airplane

structure.

~ao

32-30-00Page

227

Ral~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

g.

Remove the bolts remove

(14),

washers

the reservoir from the

(6 and 13) airplane.

and nuts

(7) securing

the reservoir to the

airplane

structure and

HYDRAULIC FLUID FILL RESERVOIR INSTALLATION a.

Position the reservoir

(7).

1 b.

Refer to

Figure

Secure the cap

(1)

the

on

structure and secure with the bolts

airplane

(14),

washers

(6

and

13) and

nuts

209.

assembly chain terminal (17)

to the

(18),

structure with the screw

airplane

washer

(16)

and nut

(1 5). c.

Install

new

O-rings (3

and

8)

on

the

T-fitting (5)

the tube assemblies to the reservoir ports

d.

Pressure-check the installation for leaks 1.

3.

as

and the tube assemblies

shown in

Figure

(10

and

Ilj. Connect the T-fitting

and

209.

follows:

Disconnect and cap the tube assembly (11) from the vent port of the power pack. Disconnect and cap the power pack end of the tube assembly leading from the lower port of the T-fitting (5) to the fill port of the power

2.

as

pack. Cap the open ports

in the power

pack.

Disconnect and cap the tube assemblies from the inboard and lower ports of the power pack. Cap the open ports of the cross fitting. Remove the cap from the upper port of the the

cross

fitting

and connect

a

cross

fitting

regulated supply

forward of the

of 30

psi dry

air to

fitting.

NOTE: The

regulated

air

supply

should

incorporate

a

shutoff valve to control the flow of

pressurized air

to the

reservoi r. is installed and locked. Pressurize the reservoir and tube

4.

Ensure the reservoir cap assembly assemblies with the air supply.

5.

Check the cap

assembly

6.

Shut off the air

supply

7.

Remove the caps from the inboard and lower tube assemblies to the open ports.

8.

Install

a new

(12)

fittings

and

for leaks. No leaks

and disconnect it from the

cross

are

permissible.

fitting. Cap

ports of the

cross

the open port

fitting.

O-ring on the tube assembly (11) and remove the cap assembly (11) to the vent port of the power pack.

Install

on

new

the

cross

O-rings

fitting.

and connect the

from the vent port of the power

pack.

connect the tube

9.

Install

a new

O-ring

on

e.

Fill the reservoir with

assembly leading from the lower port of the T-fitting (5). Remove pack and connect the tube assembly to the fill port.

the tube

from the fill port of the power

hydraulic

fluid and bleed the system

as

the cap

instructed in FILLING AND BLEEDING THE

LANDING GEAR HYDRAULIC SYSTEM. f.

Install the upper and lower access

g.

Removethe

Apr

28/06Page

228

covers

and the

leading edge of the left center section

as

shown in

Figure

201.

airplanefromthejacks.

32-30-00

nno

Ral~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AFT

OUTBOARD

3:::::"

12

17

P 14

13

B76

8

f

9 10

TO SERVICE VALVE RETURN PORT

54P3

2

TO POWER PACK FILL PORT I. 2. 3. 4. 5. 6.

8. 9.

FILL RESERVOIR FILTER SCREEN O-RING UNION FLUIO SUPPLY/RETURN WASHER NUT O-RING UNION

10. Ii. 12. 13. T-FITTING

4.

15. 16. 17. 18.

BLEED AIR INLET POWER PACK VENT CAP ASSEMBLY WASHER BOLT NUT WASHER CHAIN TERMINAL SCREW

TUBE TUBE

ASSEMBLY ASSEMBLY

3ao-3s I-III

Hydraulic Fluid Fill Reservoir Figure 209

A20

32-30-00Page

229

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ACCUMULATOR REMOVAL

I

airplane

a.

Place the

b.

Remove the upper

c.

Relieve the accumulator pressure 210.

d.

Disconnect and cap the tube

e.

Remove bolts

on

jacks (3, Chart 1, 32-00-00)

access

panel and

the

as

instructed in

leading edge

Chapter

7.

of the left center section at the

as

shown in

Figure

of the accumulator

201.

Refer

(1) (2). by depressing top eru gi F o t

(6)

from

the valve

assembly (5)

from the port at the bottom of the accumulator.

clamps (3) securing accumulator to

the

mounting

bracket

(4)

and

remove

accumulator.

ACCUMULATOR INSTALLATION WARNING: When

performing maintenance on a hydraulically operated landing gear system, be aware that a hydraulic actuator cylinder can displace hydraulic fluid and cause any of other actuator cylinders in the landing gear retraction system. movement unanticipated of the landing gear hydraulic accumulatot can also result in unanticipated movement Servicing of an actuator. Either action can result in an unsafe, unlocked landing gear system. Therefore, place the airplane on jacks prior to performing any inspection or maintenance. Cycle the landing gear and ensure that all three landing gears are down and locked prior to removing the aircraft from jacks. movement of

CAUTION:

airplane for the purpose of landing gear operation, inspection, servicing or maintenance, accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary tojack the airplane in the open, wind velocity in any direction and terrain variations, must be compensated for prior to jacking the airplane.

Jacking

of an

should be

a.

Place the accumulator

b.

Remove the cap from the tube accumulator.

(2)

in the

clamps (3)

assembly (5)

CA UTION: If the accumulator pressure gage is

charged.

damage c.

Charge the

If the

and

(7)

secure

with two bolts

and connect the tube

(6).

Refer to

assembly

to the

Figure port

at the bottom of the

reads less than 400 psi, observe the

gear unlocks while and should be replaced. nose

charging

nose gear as the accumulator the accumulator, the accumulator may have internal

psi with bottled dry nitrogen (5, Chart 2, 32-00-00)

accumulator to 800 +50

210.

as

instructed in

12-10-00.

d.

Inspect the installation for any leaks.

e.

Install the upper

f.

Remove the

Apr

28/06Page

230

access cover

airplane from

the

and

leading edge

jacks.

32-30-00

of the left center section

as

shown in

Figure

201.

Chapter

RBythwm

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

6

7

~´•D

g

U

X ~3

2

s

REMOVE LEADING EDGE AND UPPER ACCESS

i.

VALVE ASSEMBLY

2. 3.

ACCUMULATOR CLAMP

4.

MOUNTING BRACKET

5.

TUBE ASSEMBLY

6.

BOLT

7.

PRESSURE GAGE

PLATE

350-35(-105

DETAIL

A Hydraulic Landing Gear System Figure 210

Accumulator

SERVICE VAL VE REMOVAL jacks (3, Chart 1, 32-00-00)

instructed in

a.

Place the

b.

Remove the upper

c.

Disconnect the service valve electrical connector

(2)

d.

Remove the four tube assemblies

from the service valve

e.

Cut the

airplane

on

access cover

safety wire securing

Remove the bolts and f.

Remove two unions and

one

from the left center section

(4, 6,

8 and

the two bolts

remove

as

9)

as

from the

(5) attaching

Chapter 7.

shown in

Figure

201.

airplane wiring harness. Refer to Figure

(7)

the service valve

211.

and cap the lines.

assembly to the airplane

structure.

the service valve.

elbow from the ports

on

the service valve. Do not

remove

union from

landing gear

up port. g.

A20

Ensure the

preformed packings

are

removed from the service valve ports.

32-30-00

Apr

28/06Page

231

Raytheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

2

io

4

NOTE:

SAFETY WIRE BOLTS AND PLUNGER WITH MS20995C32 SAFETY WIRE PER MS33540

6

8

DETAIL A

9

PLUNGER RETAINER ELECTRICAL CONNECTOR DETENT PTN LANDING GEAR RETRACT TUBE ASSEMBLY BOLT EMERGENCY EXTEND TUBE ASSEMBLY SERVICE VALVE HAND PUMP PRESSURE TUBE ASSEMBLY RETURN TUBE ASSEMBLY JM)-~l-IDb PLUNGER

I. 2. 3. 4. 5. 6. 7. 8. 9. 10.

Service Valve

Figure

211

SERVICE VALVE INSTALLATION a.

b.

assembly (7) Figure 211.

Place the service valve bolts

as

shown in

on

the

Remove the caps from the tube assemblies shown in Figure 211.

airplane

(4, 6,

structure and

8 and

9)

secure

with two bolts

(5). Safety

wire the

and connect the tube assemblies to the correct

ports

as

c.

Ensure the accumulator is

Chapter

charged

to 800 f50

psi

with bottled

nitrogen (5, Chart 2, 32-00-00)

instructed in

fluid lost and bleed the system in accordance with BLEEDING THE SERVICE VALVE.

d.

Replace any hydraulic

e.

Connect the service valve electrical connector

f.

Inspect

g.

Install the upper

h.

If necessary,

i.

Remove the

Apr

28/06Page

(2)

to the

airplane wiring

harness.

all connections for leaks. access cover on

the left center section

as

shown in

push down the service valve plunger (10) and safety plunger retainer(l) inboard and secure with the detent pin (3).

232

as

12.

airplane

from the

Figure

wire

as

201.

shown in

Figure

211. Rotate the

jacks.

32-30-00

A20

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EMERGENCY EXTENSION HAND PUMP REMOVAL instructed in

a.

Place the

b.

Remove the center aisle carpet forward of the main spar

c.

Remove the floorboard

d.

airplane

Remove the nuts and

remove

on

jacks (3,

(27),

Chart 1, 32-00-00)

washers

(23 and 25) Figure 212. and

pin (9), washer (8)

and spacers

Remove the cotter

f.

Disconnect and cap the hand pump pressure tube (15) from the reducers (13 and 19).

(22),

Remove nuts

washers

cover.

(17)

and bolts

(24) securing

pin (7) connecting

e.

g.

Chapter 7.

to the emergency extension hand pump.

adjacent

the shield. Refer to

as

the link

assembly (12)

(16) securing

the shield

(26)

assembly (10)

to the hand pump

to the

pivot (3).

and the hand pump suction tube

the hand pump to the

airplane

(21)

assembly

structure and remove

the hand pump. h. i.

If necessary, If the

remove

O-rings (14

and

the reducers

20)

were

(13

and

19)

not removed

from the hand pump ports.

along

with the

reducers,

remove

and discard the

O-rings

from the

hand pump ports.

EMERGENCY EXTENSION HAND PUMP INSTALLATION a.

If the reducers

hydraulic

fluid

(13 and 19) were removed from the hand pump ports, lubricate new O-rings (14 and 20) (1, Chart 2, 32-00-00) and install the O-rings on the reducers. Refer to Figure 212.

b.

Install the reducers in the ports

c.

Place the hand pump on the airplane structure and secure with the bolts (16), washers Ensure that the washers are installed between the hand pump and the structure.

d.

Connect the link

on

the hand pump

with

1

(21).

(17)

and nuts

(22).

pin (7), washer (8) and cotter pin (9). Check hand misalignment in the connecting linkage. Check handle binding in position clip. The hand pump should go into detent just prior to the connection stow Adjust linkage to obtain proper handle stow positions, then tighten jam reaching position. nut of link assembly, insuring tang of key washer is in slot. The link may not exceed 1.90 inch length from assembly (10)

to the

pivot (3)

with the clevis

pump handle movement to assure there is no stow position by moving handle towards stow

or

centerline of other hole.

assembly (12)

and the hand pump suction tube

assembly (15)

e.

Connect the hand pump pressure tube hand pump reducers (13 and 19).

f.

Operate

g.

Check the hand pump handle stow position by slowly lowering the handle to the level of its stow clip (29). The handle should go into detent and a pressure release in the pump should be felt just prior to reaching the stow position. Stow the handle under the clip.

the pump handle (33) to ensure there is the pump and its plumbing for fluid leaks.

A20

no

binding

or

misalignment

in the

to the

connecting linkage. Inspect

32-30-00

Apr

28/06Page

233

Raytheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

23

3*-~ 39

~c5 31

i

ii i

e,-

Vi

I i

29

28

27

13

2 24

R-

23--/\C

A1I

~f

I

I 15

W~

16

i. CLEVIS PIN 2. STOP 3. PIVOT 4. WASHER 5. COTTER PIN 6. NUT 7. CLEVIS PIN 8. WASHER

9. COTTER PIN 10. LINK ASSEMBLY 11. JAM NUT

12. HAND PUMP PRESSURE TUBE ASSEMBLY 13. REDUCER

14. O-RING 15. HAND PUMP SUCTION TUBE ASSEMBLY 16. BOLT 17. WASHER 18. SWIVEL ELBOW 19. REDUCER 20. O-RINO 21. HAND PUMP

22. NUT 23.WASHER

24. 25. 26. 27. 28. 29.

30. 31. 32.

33. 34.

SPACER WASHER SHIELD NUT STOW BLOCK STOW CLIP STOP BLOCK COTTER PIN WASHER HANDLE PIVOT BOLT

8300-351-l07

Emergency Extension Hand Pump Figure 212

Page

2343230-00

A20

Ral~heon

Aircraft Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

h.

If the handle goes into detent out of 1.

Remove the cotter

2.

Loosen the

jam

pin, washer and clevis pin connecting

nut

(11)

i.

attaching

the link

on

CAUTION: The final adjusted of the

shorten the link

4.

Ensure that the tang of the

5.

Connect the link

the link

assembly (10)

to the

pivot.

assembly.

assembly

key

charged

as

required by rotating

washer is in the

the

assembly to

key

slot and

the clevis.

tighten

the

pivot with the clevis pin, washer and

to 800 ~50

with bottled

psi

Chapter

12-10-00.

j.

Replace

any

k.

Install spacers

I.

Install the floorboard and the center aisle carpet.

m.

Remove the

hydraulic

follows:

of the link assembly must not exceed 1.90 inches between the center-line

length

Lengthen

Ensure the accumulator is

as

holes of the link and its clevis.

3.

or

linkage

the

position, adjust

jam

cotter

nut.

pin.

nitrogen (5, Chart 2, 32-00-00)

as

instructed in

fluid lost and bleed the system in accordance with BLEEDING THE HAND PUMP.

(24) and

washers

airplane from

the

(23

and

25)

on

the bolts

(16).

Install shield

(26)

and

secure

with the nuts

(27).

jacks.

NOSE GEAR ACTUA TOR REMOVAL

jacks (3,

Chart 1,

32-00-00)

a.

Place the

b.

Disconnect the actuator downlock switch

c.

To

d.

Working through

airplane

on

provide working

room

the

in the wheel

access

instructed in

receptacle plug

well,

panel just

as

remove

aft of the

the

Chapter

7.

located in the LH keel of the

drag

nose cone

brace

assembly as

nose

instructed in

and above the actuator

(17),

wheel well.

Chapter 32-20-00.

remove

the

primary

and emergency extend hydraulic hoses (19 and 20) from the actuator. Identify the hoses to facilitate later installation. Disconnect the retract hydraulic hose (21) from the swivel fitting (22) in the actuator trunnion. Cut the

safety

wire and

CAUTION: As the

hydraulic

foreign e.

remove

fitting from

the swivel

hoses

(19

20 and

material into the hoses

or

Remove each actuator support bracket 1.

2.

Working inside the wheel well, support bracket (2). Remove the

row

of five bolts

are

disconnected, plug

Figure or

213.

cap all

openings

to

prevent entry of

actuator.

(2)

remove

(11)

21)

the actuator. Refer to

as

follows:

the five bolts

and washers

(4)

and washers

(12) attaching

(3) securing

the aft end of the actuator

the actuator support bracket to the actuator

support (1) and the actuator support plate (16). 3.

Remove the shim

4.

Remove the bolt the bracket

(13)

between the actuator support bracket and the actuator support

(14) and washer (15) securing the forward end of the from the airplane.

plate.

actuator support bracket and

remove

32-30-00Page

235

Ral~heon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

f.

Remove the four bolts

(8)

supports (1). Remove

the

and washers

bearing

(7) attaching

each actuator support bearing assembly (6) to the actuator (5) from the actuator trunnions. Note the order of

assemblies and the shims

the shims and retain them in that order for later installation.

g.

Support

the actuator and

plates (16)

remove

to the actuator

the four

remaining

(9) and washers (10) securing the actuator support plates and actuator out of the wheel well.

bolts

supports. Lower the support

NOSE GEAR ACTUA TOR CLEVIS INSPECTION

I

Inspect the nose gear actuator clevis for excessive wear at the inte rval specified i n Chapte r 5-00-00. If the maxi mum diameter of either hole in the clevis exceeds 0.3260 inch in any direction, replace the clevis. Refer to Figure 213.

NOSE GEAR A CTUA TOR INSTALLA TION NOTE: The wire bundle of the downlock switch must be

inserting

to a.

Place

one

the actuator into

actuator

run

support plate (16)

over

b.

the hole in the actuator

mounting

each of the actuator trunnions. Position the actuator

the actuator supports (1) and each side of the actuator. Refer to Figure 213.

support plates between

I

through

bracket

prior

position.

Install each actuator support bracket

(2)

as

secure

with four bolts

(9)

and washers

2.

Position the shim

3.

Secure the actuator support bracket to the actuator support, shim and support (Il)and washers (12).

4.

Working

secure

the actuator

secure

the forward end with

support bracket and the

a

bolt

(14)

Position the actuator support bracket and

inside the wheel well,

and actuator two each on

follows:

1.

(13) between

(17) (10),

actuator

and washer

(15).

support plate (16).

plate

with

the aft end of the support bracket with five bolts

(4)

a row

of five bolts

and washers

(3).

c.

(5) over the actuator trunnions in the same positions from which they were removed. Install the actuator support bearing assemblies (6) over the actuator trunnions with the bearings toward the actuator. Secure the bearing assemblies to the actuator supports with four bolts (8) and washers (7).

d.

Manually push

Install the shims

the landing gear to the retracted position and check that the actuator clevis is centered with the gear. If it is not centered, add or remove shims (5) between the actuator supports and the actuator support bearing assemblies to correct the misalignment. The allowable side play of the actuator with respect to the nose

support bearing assemblies is 0.005 Install

e.

a new

to 0.040 inch.

O-ring (23) on the swivel fitting (22). Install the swivel fitting hydraulic hose (21) to the swivel fitting.

in the actuator trunnion and

safety wire.

connect the retract

f.

Working through the

access

panel just

aft of the

emergency extend hydraulic hoses (19 and loosened, install new O-rings (26 and 27). g.

Connect the actuator downlock switch

h.

Install the

i.

Bleed the actuator

Apr

28/0632-30-00

drag brace assembly as

as

20)

wiring

nose cone

and above the actuator, connect the primary and (24 and 29). If the elbows were removed or

to the elbows

in the LH keel of the

instructed in

Chapter

nose

wheel well.

32-20-00.

instructed in FILLING AND BLEEDING THE LANDING GEAR HYDRAULIC SYSTEM.

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A

COMPARTMENT FORWARD BULKHEAD

2?

24

23

25

).1

26

17

1

29

D

"Ile 21

i,

i

I 20

19

(I

II

16

1.

2.3.

18

ACTUATOR SUPPORT ACTUATOR SUPPORT

r’ 17

REITSAWTEKCARB

4.

BOLT

5. 6.

SHIM ACTUATOR SUPPORT BEARING ASSEMBLY

7.

WASHER

8.

BOLT

9.

BOLT

16

~II

,5

14

1212

8 a

too 109

Mr*a 13.

WASHER SHIM

22.

14.

BOLT

23.

15.

WASHER

24.

16.

25. 26.

18.

ACTUATOR SUPPORT PLATE ACTUATOR DOWNLOCK INDICATOR SWITCH

27.

19.

PRIMARY U(TEND HYDRAULIC HOSE

28.

20.

EMERGENCY UCTEND HYDRAULIC HOSE

29.

12.

17.

21.

A

RETRACT HYDRAULIC HOSE SWIVEL FITTING O-RING ELBOW NUf O-RING O-RING NUT ELBOW

aso-35~-los

Nose Gear Actuator Installation

Figure

A20

213

32-30-00

Apr

28/06Page

237

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

j.

Check the

landing

gear

rigging

as

instructed in

nose

k.

Connect the

landing

gear doors and check the

rigging

instructed in

as

as

Chapter, and adjust th~ drag Chapter 32-60-00.

in this

rigging

gear

downlock, up-position and actuator downlock switches

instructed in this

brace

Chapter.

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psi of regulated dry air to pressurize the power pack reservoir during ground operation of the power pack assembly. When cycling the landing gear with the power pack, allow a one minute cooling period

between

five minute

cycles and a

cooling period after five cycles. Before removing the airplane

from the

that the hand pump handle is in the stowed position, that the plunger on the service valve is pushed down and safety wired with the plunger retainer in position and pinned, that the landing

jacks,

make

sure

gear control handle is in the down i.

Remove the

airplane

from the

position,

and that the

landing gear is

down and locked.

jacks.

MAIN GEAR ACTUATOR REMOVAL a.

Place the

b.

Working

airplane

jacks (3,

on

Chart 1,

32-00-00)

as

instructed in

Chapter

in the wheel well, disconnect the gear doors from the actuation secure with safety wire.

7.

connecting links. Swing

the doors out

of the way and

I

c.

Disconnect the actuator clevis

d.

After the actuator is

(32)

disengaged

from the

from the

drag

brace. Refer to

drag brace, fully

Figure 214.

retract the actuator

piston with the emergency

extension hand pump. e.

Disconnect and cap the ends of the three hydraulic hoses (6, 21 and 22) connected to the actuator (26). Cap the actuator fittings as the hoses are removed. Remove the hoses from the brackets (7) attached to the actuator

mounting brackets (10). f.

Disconnect, cap and across

the stiffener

remove

the

pneumatic hose,

the

hydraulic

lines and the fire

extinguisher

lines routed

plate (20).

g.

Remove the two bolts

h.

Remove the two bolts

washers and nuts

(17), (12),

washers

(9) and

securing

nuts

each brace

(8) securing

each

(15)to

the stiffener

T-angle (13)to

plate (20).

its actuator

mounting

bracket

(10). the

plate (14).

i.

Disconnect the wire bundle

plug from the up-position switch (16)

j.

Remove the four bolts

washers and nuts from the strap (31) atop the actuator remove the bolts (29) from the spar cap.

remove

k.

the

strap.

remove

mounting brackets (10)

and

It is not necessary to

Remove the six bolts

mounting bracket

(30),

and

(4)

and washers

(3) along

the side of each actuator

mounting

bracket

(10) securing

the

to the spar.

i.

Stow all lines out of the way. Pull the actuator/mounting bracket in the spar, then remove it from the wheel well.

m.

Remove the six bolts

assembly straight

forward and out of the slots

(1 8), washers (1 9) and nuts and remove the stiffener plate (20) from the actuator mou nting long bolt (5), washers (11), nut (24), cotter pin (25) and spacer (23) located behind the

brackets. Remove the

plate.

Apr

28/06Page

238

32-30-00

nzo

Ral~heon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

28

2

31

’XO. A

23

22

7

19

11 I

13

b

C) 7

16 10 ’5 DRIIL

9

8

A Ig~ WASTIER 20. STIFFENER PLATE

i. WASHER 2. NUf 3. WASHER 4. BOLT BOLT 8. EMERGENCY UCTEND HYDRAULIC HOSE 7. HOSE BRACKET 8. NUT g. WASHER 10. ACTUATOR MOUNTING BRACKET

21. RETRACT HYDRAULIC HOSE 22. PRIMARY U(TEND HYDRAULIC HOSE 23. SPACER 24. NUT

25. 28. 27. 28.

COTTER PIN

iS. BRACE 18. UP-POSITION SWITCH 17. BOLT

ACTUATOR O-RINII UNION 29. BOLT 30. BOLT 31. STRAP 32. ACTUATOR CLEVIS 33. BEARING 34. BOLT 35. BEARING SUPPORT

18. BOLT~

38. SHIM

11. WASHER 12. BOLT 13. T-ANGLE 14. PLATE

sso-2~6a2

Main Gear Actuator Installation

Figure

A20

214

32-30-00

Apr

28/06Page

239

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

n.

Remove three bolts

(34),

and nuts

(1)

washers

(2)

and

each

remove

mounting

NOTE: If the shims are to be removed, mark the number and

position

(10) and bearing support bearings (33), do not remove

bracket

(35) from the actuator. If it is not necessary to replace or to clean and repack the the bearing supports (35) and the shims (36) from the mounting brackets.

for later installation.

MAIN GEAR ACTUATOR CLEVIS INSPECTION

I

Inspect the main gear actuator clevis (32) for excessive wear at the interval specified in Chapter 5. If the maximum diameter of either hole in the clevis exceeds 0.5800 inch in any direction, replace the clevis. Refer to Figure 214. MAIN GEAR ACTUATOR INSTALLATION a.

If the

bearings were removed, press the bearings (33) into the bearing supports (35). Install the same number (36) that were removed and secure each bearing support to its actuator mounting bracket (10) with bolts (34), washers (1) and nuts (2). Refer to Figure 214.

of shims three

I b.

Install the

bearing

brackets

mounting

(10)

each side of the actuator

on

and the actuator is 0.005 to 0.025 inch. Add

or remove

(26). Ensure that the clearance between each shims (36) as required to obtain the proper

clearance. c.

Install the spacer (23) and washers (1 1) between the two actuator mounting brackets and (5) and washers (11). Install the nut (24) loosely and hold it in place temporarily with

bolt

Do not bend the cotter NOTE: The nut

(24)

pin

the

on

secure a new

it with the cotter

long pin (25).

at this time.

long

(5)

bolt

will be

torqued

after the actuator is

properly aligned

instructed in MAIN

as

GEAR RIGGING.

d.

Lubricate bolt

e.

Install

new

hoses

(6,

f.

(5)

with grease

O-rings

21 and

on

22)

Chart 2,

(12,

all of the hose

to the actuator

or

32-00-00)

tube

fittings

at time of installation.

that

were

loosened

or

removed. Connect the

hydraulic

(26).

Position the actuator and support structure in the wheel well and insert the actuator rod end

through the

hole in

the spar. g.

Install the washers

NOTE: The

mounting (3).

attaching

brackets

bolts

Install the forward stiffener

(19) and

angles

on

mounting rigging.

plate (20) on the

the spar. Secure each bracket

brackets will be

actuator

tightened after

mounting

brackets and

brackets

(10)

loosely

with six bolts

the actuator is

secure

(4) and

properly aligned

with four bolts

(18),

as

washers

nuts.

Install the strap

i.

the

for the

(4)

instructed in main gear h.

on

(31)

on

top of the

actuator

mounting

and

secure

with four bolts

(30), washers

and

nuts.

plate (14) on the forward stiffener plate (20) (17), washers and nuts.

Position the

j.

two bolts

T-angle (13)

k.

Secure each

I.

Connect the wire bundle connectors.

m.

Route and connect all

Apr

28/06Page

240

to its actuator

hydraulic,

fire

32-30-00

and

secure

mounting bracket (10) with

extinguisher

and

pneumatic

each brace

two bolts

(15)

(12),

to the stiffener

washers

(9)

plate with

and nuts

lines and hoses. Secure with proper

(8).

clamps.

nno

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: When

the actuator

installing

hydraulic

lines to the hose brackets

(7),

install the 3/8-inch line in the forward

hole and the 1/4-inch line in the aft hole. n.

Check the the two

alignment of the actuator clevis with the drag brace as instructed properly aligned, connect the actuator clevis to the drag brace.

o.

Bleed the actuator

p.

Check the

switches q.

in MAIN GEAR RIGGING. When

are

instructed in FILLING AND BLEEDING THE LANDING GEAR HYDRAULIC SYSTEM.

gear rigging as instructed in MAIN GEAR RIGGING. instructed in Chapter 32-60-00.

Adjust the up-position

landing

as

When the

as

landing

to the spar.

gear is

Torque the

and downlock

rigged properly, tighten the six bolts (4) securing each actuator mounting bracket (10) (24) on the long bolt (5) to 30 to 40 inch-pounds and secure it with the new cotter pin

nut

(25). Connect the

landing

gear doors and check the

rigging

instructed in MAIN GEAR DOOR RIGGING.

as

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psi of regulated d~y air to pressurize the power pack reservoir during ground operation of the power pack assembly. When cycling the landing gear with the power pack, allow a one minute cooling period

between cycles and a five minute cooling period after five cycles. Before removing the airplane from the jacks, make sure that the hand pump handle is in the stowed position, that the plunger on the service valve is pushed down and safety wired with the plunger retainer in position and pinned, that the landing gear control handle is in the down position, and that the landing gear is down and locked. s.

Remove the

airplane from the jacks.

MAIN GEAR ACTUA TOR BEARING SUPPORT INSPECTION a.

Place the

b.

Ensure the

airplane

on

landing

jacks (3,

Chart 1,

32-00-00)

gear control circuit breaker is

as

instructed in Chapter 7.

pulled,

then

place

the

landing gear control handle

in the up

position. c.

Remove the detent

pin and the safety wire from the plunger on the service valve,

then

move

the

plunger retainer

away from the valve. d.

Pull the service valve

e.

Remove the emergency extension hand pump handle from its

plunger

up into the retract

position.

CAUTION: Do not lower the handle to the level of the securing relief Valve to open and depressurize the system. f.

Pump the

g.

Once the main

placing

handle

it in its

sufficiently

landing

clip

while

and pump the handle up and down.

pumping,

as

this will

the internal

cause

gear.

landing gear is unlocked, lower the emergency extension hand pump handle and stow securing clip. A release in pressure will be felt as the handle is lowered into the clip.

h.

Place the service valve

i.

Grasp

plunger

in the extend

each main gear, in tum and

support (35). Refer

~ao

to unlock the main

securing clip

to

Figure

move

(down) position

fore and aft while

to relieve the pressure in the

checking

it

by

system.

for movement of the actuator

bearing

214.

1

32-30-00

Apr 28/06Page

241

Raytheon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

If any movement is detected, remove the actuator (26) and inspect the bearing (33) for condition and the bearing support (35) and mounting bracket (10) for bolt hole elongation. k.

Install the actuator After the

(26)

inspection

if necessary.

pump handle and stow it m.

When the

pushed n.

completed, extend the landing gear and by placing it in its securing clip.

has been

lower the emergency extension hand

landing gear is extended to the down and locked position, ensure the plunger on the service safety wired with the plunger retainer in position and the detent pin installed.

valve is

down and

Remove the

airplane

from the

jacks.

LANDING GEAR RIGGING WARNING: For

safety reasons, pull the 2-ampere rigging the landing gear.

control circuit breaker

on

the

pilot’s inboard subpanel

while

cycled with the power pack until the landing gear is properly rigged. To raise and rigging, use a TK229/939 manual or TK229-1/939 air-driven extemal hydraulic pump (5 or 6, Chart 1, 32-00-00) or the equivalent, or use the emergency extension hand pump. The emergency extension hand pump can be used to raise and lower the landing gear by selecting the retract or extend mode of the service valve, located adjacent to the power pack beneath an access panel in the top skin of the LH center section, just inboard of the LH nacelle and forward of the main spar. The mode is selected by pulling up or pushing down the plunger at the top of the se rvice valve. The valve is normally secured in the mode to extend the landi ng gear (plunger pushed down). The plunger cannot be pulled up to select the retract mode until the detent pin is pulled, the plunger retainer over the service valve is moved, and the safety wire securing the knob in the down position is removed. When the plunger is pulled up, the two switches mounted on the service valve are actuated to open the circuit to the power pack motor. This same action positions the service valve to route pressurized fluid from the hand pump

The

landing gear landing

lower the

should not be

gear for

through the normal

retract mode

plumbing

to the actuators.

OPERATING THE LANDING GEAR WITH THE EMERGENCY EXTENSION HAND PUMP a.

Place the

b.

Ensure the landing gear control circuit breaker is

airplane

on

jacks (3,

Chart 1,

32-00-00)

as

instructed in

pulled,

then

Chapter

7.

place the landing gear

control handle in the up

position. c.

Retract the landing gear

follows:

Remove the detent pin and the retainer away from the valve.

2.

Pull up the plunger

3.

Remove the emergency extension hand pump handle from its securing clip and pump the handle up and down. Do not lower the handle to the level of its securing clip while pumping, as this will cause the internal

4.

When the

placing

28/06Page

242

on

plunger

on

move

the

plunger

the service valve.

resulting

in

a

loss of pressure.

Pump

the handle until the gear is retracted.

gear is retracted, lower the emergency extension hand pump handle and stow it securing clip. A release in pressure will be felt as the handle is lowered to the clip.

landing

it in its

safety wire

from the

the service valve, then

1.

relief valve to open,

Apr

as

32-30-00

by

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Extend the

landing

CAUTION: If the

gear

as

follows:

the service valve is pushed down while the landing gear is retracted, the electrical is the on, landing gear control circuit breaker is reset, and the landing gear control handle is power in the down position, the gear will extend immediately.

plunger on

1.

Push the

plunger

2.

Place the

landing

3.

Remove the emergency extension hand pump handle from its securing clip and pump the handle up and down. Do not lower the handle to the level of its securing clip while pumping, as this will cause the internal

on

the service valve down.

gear control handle in the down

relief valve to open, resulting in indicating the gear is extended. 4.

loss of pressure.

Pump

the handle until resistance to movement is felt,

landing gear is extended, lower the emergency extension hand pump handle and stow securing clip. A release in pressure will be felt as the handle is lowered to the clip.

Afterthe it in its

e.

a

position.

When

is

rigging

it

by placing

completed, extend the landing gear to the down and locked position. Ensure the plunger on the pushed down and safety wired, with the plunger retainer in position and the detent pin installed.

service valve is

OPERATING THE LANDING GEAR WITH AN EXTERNAL PUMP a.

Place the

b.

Ensure the and the

c.

airplane

To operate all three

landing gears,

1.

Remove the upper and lower

2.

Remove the first

as

instructed in

Chapter

to

connect the pump

access

panels

as

as

7.

follows:

shown in

hydraulic tubes connected to the

Figure

gear-up and

201.

gear-down ports of the

Connect the external pump hoses to the open extend and retract

4.

Operate

To operate

pack. Cap the

hydraulic

tubes.

the external pump in accordance with the vendor’s instructions.

one

landing

Working inside hoses from the

gear

individually,

connect the pump

as

follows:

the wheel well, disconnect the landing gear actuator flexible primary extend and retract rigid hydraulic tubes. Cap the open tubes to prevent contamination.

2.

Connect the external pump hoses to the open extend and retract actuator hoses.

3.

Operate

When

power

prevent contamination.

3.

1.

e.

jacks (3, Chart 1, 32-00-00)

landing gear control handle is in the down position, the landing gear control circuit breaker is pulled, plunger on the service valve is secured in the down position.

open ports

d.

on

the external pump in accordance with the vendor’s instructions.

rigging

is

completed, extend the landing gear to the down and locked position. Disconnect landing gear system hoses or tubes. Install the access panels.

the external

pump hoses and connect the

32-30-00

Apr

28/06Page

243

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psi of regulated dry air to pressurize the power pack reservoir during ground operation. A capped cross, adjacent to the service valve, is plumbed into the bleed air line to the fill reservoir as a connection point for pressurized air during ground operation of the power pack assembly. To pressurize the system, remove

When

the cap and connect the air supply to the

cross

cycling the landing gear with the power pack, cycles, allow a five minute cooling period.

fitting.

allow a

one

minute

cooling period between cycles,

after five

Before removing the airplane from the jacks, make sure that the hand pump handle is in the stowed position, that the plunger on the service valve is pushed down and safety wired with the plunger retainer in position and pinned, that the landing gear control handle is in the down position and that the landing gear is down and locked. NOSE GEAR RIGGING

CA UTION: Do not

cycle the landing gear with the power pack until the gear is properly rigged. Use the emergency extension hand pump, a TK229/939 or TK229-1/939 external pump (5 or 6, Chart i, 32-00-00), or the equivalent for initial rigging as instructed in LANDING GEAR RIGGING.

a.

Place the

b.

Disable the

c.

airplane nose

on

jacks (3,

gear doors

Chart 1,

32-00-00)

by disconnecting

as

instructed in

the doors from the

Chapter cam

7.

assemblies.

Remove the nut, washer and bolt attaching the actuator clevis to the yoke. Loosen the actuator clevis jam nut piston rod counterclockwise several turns to retract the clevis. Refer to Figure 215.

and rotate the actuator

I d.

Connect

Chapter

a

TK1763-2/935 test box

(14, Chart 1, 32-00-00)

to the actuator downlock switch as instructed in

32-60-00.

NOTE: While

rigging the landing gear, observe the components and hydraulic lines for any indication of binding, dragging, interference, leakage, or questionable operation. Correct any problems as necessary.

e.

Apply a pressure of 500 700 psi to ensure that the actuator is fully down and locked and that the appropriate lights on the test box are illuminated. Release the pressure and disconnect the test box from the downlock switch.

I’

With the

yoke.

drag

brace

leg against

the stop bolts, rotate the clevis out until the clevis

Rotate the clevis 112 additional turn to extend the clevis for

g.

Connect the actuator clevis to the

h.

Cycle

the

landing gear

yoke

a

aligns

with the hole in the

slight preload.

with the bolt.

and check that the lower

drag legs

make contact with the stop

bushings

when the gear

is down and locked. i.

Hold the actuator

key j.

Check the rod to

rod in

position. Tighten

the clevis

jam

nut to 15

20

foot-pounds

and

safety

wire to the

hole in the

piston rod to ensure that the clevis threads are sufficiently engaged in the piston piston rod lacks an inspection hole, check for a maximum distance of 2.15 inches of the clevis attaching hole to the end of the piston rod.

inspection

cover

the hole. If the

from the center

Apr

piston

washer.

32-30-00

Ray~heon

Aircraft Company

MANUAL SUPER KING AIR B300/B300C MAINTENANCE

ACTUATOR END CAP ACTUATOR BEARING SUPPORT

UPPER DRAG LEG

STOP BOLT

STOP BUSHING STOP BUSHING"

r~

Y--WASHERS

vOKE LOWER DRAG LEG

MTAIL

A

i

Rigging Figure 215

Nose Gear

32-30-00 A20

Apr

28/06Page

245

Raylheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

k.

To eliminate any side load on the actuator, the alignment of the actuator and yoke assembly to the drag brace assembly must be checked. Remove the stop bolt and bushings attaching the yoke to the upper drag leg, and check for proper

alignment

as

follows:

yoke is offset to facilitate alignment and may be installed with the short leg on either side. If it is necessary to change the position of the yoke for proper alignment, rotate the yoke and piston rod to the desired position as a unit. Do not change the clevis adjustment set in step g.

NOTE: The

I.

m.

1.

With the actuator fully extended, position the yoke for installation on the upper drag leg. Measure the space between the yoke and the upper drag leg on each side of the yoke.

2.

Retract the actuator to its fully retracted position. Manually push the nose gear to the retracted position and locate the yoke assembly for installation on the upper drag leg. Measure the space between the yoke and the upper drag leg on each side of the yoke.

3.

position and extend the actuator. Install AN960-616 and/or AN960-6161 washers on each side of the yoke to obtain the alignment as determined in steps 1 and 2. A minimum of one AN960-616 or AN960-6161 washer must be installed on each side of the yoke. Install the stop bolt, bushings, washer and nut. If the misalignment between the yoke and drag leg is such that at least one washer will not fit on each side of the yoke, remove the actuator as instructed in nose gear actuator removal, and add or remove shims from under the actuator bearing supports to correct actuator misalignment.

Manually pull

the

drag

brace to the extended

Apply clay in the upper wheel well panel depression that is above the shimmy damper piston gear is fully retracted. Fully the

rod when the

retract the nose gear, then extend the gear and measure the thickness of the

shimmy damper piston

damper piston

rod and the

the actuator stroke

as

clay at the impression left by (represented by the thickness of the clay) between the shimmy upper wheel well panel should be approximately 0.5 inch. Adjust

rod. The clearance

depression

in the

instructed in step

o

if necessary.

NOTE: Following any adjustment, clearance should also be verified (with the gear in the retracted between the

upper n.

nose

nose actuator

drag leg ton legs

brackets and the upper

next to the up

switch)

drag leg by applying clay

position)

to the lower end of the

to confirm that clearance exists.

adjustable between 11.04 and 11.30 inches. It is preset by the supplier at require adjustment; however, if the clearance measured in step n is not within from the the airplane as instructed in NOSE GEAR ACTUATOR REMOVAL and actuator tolerance, remove stroke follows: adjust the actuator length as

The stroke

length of the

actuator is

1 1.17 ~0.03 inches and should not

CAUTION: Before adjusting the nose gear actuator, determine the manufacturer of the unit. Actuators manufactured by Phoenix Controls, Inc., must be adjusted while in the unlocked condition or the internal lock mechanism may be damaged. To unlock the actuator, 400 psi to the retract port of the actuator.

apply

fluid pressure at 200 to

NOTE: When the actuator end-cap is rotated out, the stroke length is increased, which will decrease the clearance between the shimmy damper piston rod and the upper wheel well panel. Rotating the endcap in will decrease the stroke length and increase the clearance. Each full turn of the end-cap will

change To

the stroke

ensure

end-cap

Apr

proper

length by

0.06 inch.

alignment of the hydraulic plumbing 360-degree rotations only.

must be rotated in

32-30-00

to the shuttle valve located in the end cap, the

Raythwm

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1.

safety wire and loosen the end-cap jam nut. Rotate the end-cap one full turn at a time until the proper adjustment is obtained. The end-cap may be rotated a maximum of two rotations in or out; measure the actuator stroke length to ensure that the stroke length is within the range of 11.04 to 11.30 inches.

2.

After the stroke

3.

Remove the

length

Install the actuator actuator

as

is

the

properly adjusted, tighten

jam

nut to 30

40

foot-pounds

and

safety wire.

instructed in NOSE GEAR ACTUATOR INSTALLATION. Install the shims under the

bearing supports

in the

positions

same

as

determined in step k. bleed the actuator

as

instructed in

FILLING AND BLEEDING THE LANDING GEAR HYDRAULIC SYSTEM. o.

Lubricate the

gear and

landing

drag

brace

hinge points

as

instructed in

Chapter

12-10-00.

p.

Adjust the drag brace downlock, up-position and actuator downlock switches as instructed in Chapter 32-60-00, and cycle the landing gear to check for proper operation of the in-transit and gear-down lights.

q.

Connect the

gear door

nose

cams

to the doors. Check the

rigging

of the doors

as

instructed in NOSE GEAR

DOOR RIGGING. r.

Remove the

airplane

from the

jacks.

MAIN GEAR RIGGING

cycle the landing gear with the power pack until the gear is properly rigged. Use the emergency extension hand pump, a TK229/939 or TK229-1/939 external pump (5 or 6, Chart i, 32-00-00), or the equivalent for initial rigging as instructed in landing gear rigging.

CAUTION: Do not

airplane

a.

Place the

b.

Disable the

c.

For

on

jacks (3,

landing gear

doors

Chart 1,

32-00-00)

by disconnecting

safety purposes, pull the 2-ampere landing

as

instructed in

Chapter

the doors from their

gear

7.

actuating

relay circuit breaker located

cams.

on

the

pilot’s

inboard

subpanel.

rigging the landing gear, observe the components and hydraulic lines for any indication of binding, dragging, interference, leakage, or questionable operation. Correct any problems as necessary.

NOTE: While

d.

Remove the nut, stops, washers and bolt

e.

Remove the cotter

f.

With the

pin, nut,

attaching

washers and bolt

the actuator clevis to the

attaching

the lower

drag leg

drag

to the

brace. Refer to

landing

Figure

216.

gear strut.

drag brace locked and the upper and lower drag legs butted together, check for a minimum clearance of 0.007 inch between each lock hook and the lock pin. The maximum clearance allowed is an average of 0.020 inch per side; to determine the average clearance, add the clearance on the right side to the clearance on the left side and divide

by

two. For

example,

if the clearance

on one

side is 0.010 inch and the clearance

on

the

other side is 0.030 inch, the average clearance would be 0.020 inch. Material may be removed from the flat inside surface of the lock hooks as required (up to the average maximum of 0.020 inch) to maintain the 0.007 inch clearance; do not remove any material from the radius in the lock hook. The inside surface of each lock hook must be

parallel

to the flat surface of the lock

pin to

ensure

full surface contact. Refer to

Figure 216,

Detail

pin has been established, turn the clevis (7200), or altematively rotate the piston rod two full turns to achieve the positive down-lock before the piston bottoms out in the actuator.

NOTE: After the 0.007 inch clearance between the lock hook and the lock clockwise same

~30

an

additional two turns

effect. This will

ensure

32-30-00Page

247

RayfheMI

Aircraft

Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

a

ACTUATOR END CAP ACTUATOR BEARING SUPPORT

d

A ACTUATOR CtEVIS

iii

I

IDLER

DETAIL

~r

B

LOCK LINK

C

~/--LOCKHOOK

IDLER or

ION~-LOCK PIN

ooooool~ IDLER STOP BLOCK

DRAG BRACE ASSEMBLY

DETAIL

A

350-201-10

Main Gear

Figure

Page

24832-30-00

216

Rigging (Sheet 1 of 2)

A20

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LOCK LINK CLEVIS ACTUATOR CLEVIS STOP

STOP

COTTER PIN

I

I

WASHER

NOTE: TIGHTEN NUT FINGER TIGHTAND SAFETY

BOLT

NUT

WASHER(S)AS REQUIRED

NOTE:

TO

REPLACE BOLT IF INSPECTION REVEALS

OBTAIN COTTER PIN ENGAGEMENT

SCORING OR GALLING. LUBRICATE ENTIRE

WASHER(S)AS

BOLT WITH GREASE MlL-G-21164

IDLERS

REQUIRED TO

BEFORE INSTALLING.

OBTAIN 0.030 TO 0.060 INCH

BOLT END PLAY DETAIL

C

APPLY SOLID FILM LUBRICANT MlL-L-23398 TO CONTACT AREAS

LOCK PIN

CAUTION:

O

DONOTREMOVEANY MATERIAL FROM THIS RADIUS

O

LOCK HOOK

O

O O

O O

APPLY SOLID FILM LUBRICANT

CAUTION:

MlL-L-23398 TO CONTACT AREAS

THESE TWO SURFACES MUST

BE PARALLEL FOR FULL CONTACT

0.007 INCH MINIMUM CLEARANCE

(EACH SIDE) (AVERAGE OF

0.020 INCH MAXIMUM CLEARANCE

TWO

SIDES)

ROUND THIS POINT TO

0.06-0.09 (0.06

0.03) INCH RADIUS OETAIL

D

FL328

91YMBU

Rigging (Sheet 2 of 2)

Main Gear

Figure

A20

216

32-30-00

Apr 28/06Page

249

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL CAUTION: If the lock

pin on the drag brace is grooved in replace both lock hooks and the lock pin.

g.

Note how the lock hooks slide

over

Install the clevis

attaching

bolt

or

if the lock hooks

are

worn,

the lock

Chart 2, 32-00-00). Round off the minimize pin wear.

(7,

h.

the hook contact areas,

pins prior to locking. Treat the contact areas with solid film lubricant point of the hook to a radius of 0.06 to 0.09 inch (0.06 +0.03 inch) to

through

the idlers and rotate the idlers toward the idler stop blocks; both idlers same time and be in full contact. File the stop blocks as necessary to

should contact the idler stop blocks at the obtain full contact. i.

Check the

alignment of the lower drag leg with the attachment lug on the landing gear strut; there shall be no on the drag leg when the landing gear is in the extended or retracted position. Correct any misalignment by shifting the AN960-1216L washers from side to side of the upper drag leg attach point. A minimum of one washer must be installed on each side of the upper drag leg. After the proper alignment is obtained, connect the lower drag leg to the landing gear strut as instructed in MAIN GEAR DRAG BRACE

side loads

INSTALLATION.

j.

With the

drag brace in the down and locked position and the full weight of the landing gear on the drag brace, verify that the lock hooks are in full contact with the flat surfaces of the lock pin. Pull down on the drag brace until the upper and lower drag legs are butted together, then check for a minimum clearance of 0.007 inch between each lock hook and the lock pin.

k.

With the actuator

fully

extended and the

actuator clevis with the

any side loads I.

drag

the actuator

on

landing

gear in the extended position, check the alignment of the brace. The actuator clevis must slip between the drag brace idlers without causing

piston

rod.

With the actuator fully retracted, unlock the drag brace, manually push the landing gear to the retracted position and again check for any side loads on the actuator piston rod. If any misalignment is found in either position, remove the actuator as instructed in MAIN GEAR ACTUATOR REMOVAL, then shift the shims under the actuator

bearing supports as required to correct the misalignment. Ensure that the proper clearance between bearings is maintained as instructed in MAIN GEAR ACTUATOR INSTALLATION.

the actuator and the m.

With the actuator mounted in the structure, the landing gear in the down and locked position and the actuator clevis disconnected from the drag brace, use the hand pump to apply and maintain sufficient hydraulic pressure to

fully

NOTE: For

extend the actuator.

airplanes

FL-1

through FL-159; FM-1 through n through q.

FM-9 that have not

complied

with Beech Service Bulletin

2728, perform rigging steps Remove the

n.

on

spring-loaded lock leg.

Loosen the actuator clevis

o.

link

assembly

and

position the drag brace idlers against

the down stop blocks

the sides of the upper

jam

holding the drag brace idlers fully against the stop blocks, adjust the aligned with the idler holes, then extend the clevis an additional two full proper gear-up clearance or to align the slot of the clevis with the actuator

nut. While

actuator clevis until the clevis holes are

turns

(720").

If necessary to obtain

rod slot, the clevis may be extended up to Ensure that the

p.

jam q.

To

nut to 15

ensure

key washer properly foot-pounds.

additional full turn

(360").

engages the slots of the clevis and the actuator rod and torque the clevis

20

that the clevis threads

through the inspection

sufficiently engaged in the piston rod, check that a stiff wire will not pass piston rod. If the piston rod lacks an inspection hole, check for a maximum center of the clevis attaching hole to the end of the piston rod. are

hole in the

distance of 3.41 inches from the

Apr

one

28/0632-30-00

n2o

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: For airplanes FL-160 and After; FM-10 and After and airplanes that have complied with Beech Service Bulletin 2728 perform rigging steps r through u. r.

Adjust the

actuator rod

so

the actuator clevis holes

align

with the

drag leg

idler holes when the idlers

are

fully

idler stop blocks. Refer to Figure 206. If this is possible, proceed with substep 1. If the clevis shoulder meets the end of the rod before the holes are aligned, proceed with substep b.

against the drag brace

1.

Install and adjust clevis

a)

as

follows:

Extend the actuator clevis two

complete

(720")

turns

NOTE: If necessary, the actuator clevis may be extended gear up clearance.

b)

one

additional turn

(360")

to obtain

Measure the distance between the end of the actuator rod and the shoulder of the clevis to determine the number of washers

c)

maximum of

a

required

as

spacers. Take in to consideration the thickness of the

Remove the clevis and install with the

key

washer and spacers

aligning

key washer.

the tab washer with slot in the

actuator rod. 2.

Remove the clevis and install with the

key

washer

aligning the

tab in the

key washer

with the slot in the

actuator rod. s.

Tighten

t.

Check the clevis thread engagement in the piston rod at the inspection hole in the rod.

u.

Safety wire

v.

Secure the jam nut to the key washer with safety wire.

w.

When the actuator clevis is adjusted properly, there should be 0.10 to 0.20 inch overtravel. Check the overtravel as follows: 1.

the clevis to 35

foot-pounds

the clevis to the

Ensure that the

landing

key

of torque.

washer with MS20995C32

gear is in the down and locked

safety-wire.

position

and that the idlers

are

in full contact with the

stop blocks. the hand pump,

2.

Using

3.

Check that the clevis holes

4.

Relieve dny

hydraulic

apply

and maintain sufficient

are

hydraulic

pressure to

fully

extend the actuator.

0.10 to 0.20 inch past the idler holes.

pressure in the actuator.

x.

Rotate the clevis and the actuator piston rod as a unit to align the clevis with the idlers. Ensure that the clevis lubrication fittings are on top to provide access for future servicing.

y.

Install the

z.

Connect the actuator clevis to the 1.

spring-loaded

lock link

assembly. drag

brace

Coat the bolt with grease (3, Chart 2, one AN960-916L

216, Detail C. Use 2.

as

follows:

32-00-00) or

Add AN960-816 and/or AN960-816L washers

the nut

finger tight

and

secure

it with

and insert it

through the

idlers and clevis

as

shown in

AN960-916 washer to obtain 0.030 to 0.060 inch bolt end

a new

as

required pin.

to obtain proper cotter

Figure play.

pin engagement. Tighten

cotter

32-30-00

Apr 28/06Page

251

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Ensure that the bolt has 0.030 to 0.060 inch end play (inboard/outboard). Ensure that the stops rotate on the bolt (within their limits). Check the stops for proper orientation.

3.

aa.

Using

a

lubrication nozzle

the bolt while ab. Retract the

drag brace ac.

the

joint

with grease

landing

gear and

brace

drag

hinge points

Adjust the up-position and downlock switches

operation

as

airplane from

as

32-00-00). Turn

instructed in MAIN

instructed in Chapter 32-60-00, then cycle gear-down lights. as

gear strut and the

12-10-00.

as

of the in-transit and

the

landing

length

Chapter

instructed in

Connect the landing gear doors. Check the rigging of the doors

ag. Remove the

Chart 2,

(3,

0.25 +0.12 inch clearance between the

If proper clearance or alignment cannot be obtained, adjust the actuator stroke GEAR ACTUATOR ADJUSTMENT, then repeat steps k through x.

check for proper af.

(10, Chart 1, 32-00-00), lubricate properly distribute the grease.

to

landing gear fully and check for spar fitting.

ad. Lubricate the ae.

lubricating

free to

are

the

landing

gear to

instructed in MAIN GEAR DOOR RIGGING.

jacks.

MAIN GEAR ACTUATOR ADJUSTMENT

NOTE: The stroke

adjustable between 8.01 and 8.51 inches. It is preset by the supplier at require adjustment; however, increasing the stroke length of the actuator will clearance between the landing gear brace and the drag brace spar fitting. Decreasing the

length

of the actuator is

8.15 inches and should not

decrease the stroke

length

will increase the clearance. 7.

Place the

b.

Disable the landing gear doors by disconnecting the doors from their actuating

c.

For

d.

Retract the landing gear fully and

airplane

on

jacks (3,

Chart 1,

32-00-00)

as

instructed in

Chapter

a.

cams.

safety purposes, pull the e-ampere landing gear relay circuit breaker located on the pilot’s inboard subpanel.

spar fitting.

measure

the clearance between the

If the clearance is not 0.25 M.12 inch

actuator from the

airplane

as

or

if the idlers

are

landing

gear brace and the

not free of the idler

instructed in MAIN GEAR ACTUATOR REMOVAL and

stops,

drag

remove

brace

the

adjust the stroke length

as

follows:

NOTE: The end-cap is retained

on

In either case, the rotation of the end-cap.

screw.

1.

the actuator

safety

cylinder by

one

of two methods: with

wire must be removed and the

jam

a

jam

nut or with a set

nut or set screw loosened to allow

Rotate the end-cap one full turn at a time until the proper adjustment is obtained. When the end-cap is rotated out, the stroke length is increased, and when rotated in, the stroke length is decreased. Each full turn of the

end-cap

will

change

three rotations in

the stroke

or out; measure range of 8.01 to 8.51 inches.

NOTE: To

ensure

length by

0.06 inch. The end cap may be rotated a maximum of length to ensure that the stroke length is within the

the actuator stroke

proper alignment of the hydraulic plumbing with the shuttle valve in the end-cap, the end-cap 360-degree rotations only.

must be rotated in 2.

After the stroke length is properly adjusted, tighten the jam nut to 30 screw

Apr

28/06Page

252

is

used)

and

safety

wire.

32-30-00

40

foot-pounds (or

until snug if

a set

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

3.

Install the actuator actuator as

instructed in MAIN GEAR ACTUATOR INSTALLATION. Install the shims under the

as

bearing supports

in the

same

position

as

determined in MAIN GEAR RIGGING. Bleed the actuator

instructed in FILLING AND BLEEDING THE LANDING GEAR HYDRAULIC SYSTEM.

the gear as instructed in MAIN GEAR RIGGING. When 15 20 foot-pounds and safety wire it to the key washer.

e.

Rig

f.

Connect the

landing

g.

Removethe

airplanefromthejacks.

gear doors. Check the

rigging

rigging

of the doors

as

is

complete, torque the clevis jam

nut to

instructed in MAIN GEAR DOOR RIGGING.

LANDING GEAR DOORS landing gear doors consist of two nose gear doors and two sets of main gear doors. The gear doors are hinged sides and spring-loaded to the open position. As the gears are retracted, two rollers on each landing gear the at engage the door actuating cams and pull the doors closed.

The

NOSE GEAR DOOR RIGGING Prior to

rigging

the

nose

gear doors, the

landing

gear must be

properly rigged

as

instructed in NOSE GEAR

RIGGING. the landing gear with the power pack until the gear doors are properly rigged. Use the extension hand pump, a TK229/939 or TK229- 1/939 extemal pump (5 or 6, Chart 1, 32-00emergency 00), or the equivalent for initial rigging as instructed in LANDING GEAR RIGGING.

CAUTION: Do not

a.

Place the

cycle

airplane

on

jacks (3, Chart 1, 32-00-00)

Disconnect the gear doors from the

b.

actuating

as

cams

instructed in

and

move

Chapter

7.

them out of the way, then

fully

retract the

nose

gear. c.

Push the doors up

d.

Check the

cam

by

hand to check for fit and clearance.

and rollers for proper clearance and freedom of

operation. See Figure

217 for

cam

and roller

clearance. e.

Extend the gear and connect the door attach linkage so that the doors are held in an overcenter position. The linkage should be adjusted so that the doors are in a slight ove rcenter position when the nose gear is down

door

and locked.

Apply

a

force of

remain in the overcenter

f.

approximately

25

pounds

at the center of the door. The door mechanism should

position.

Retract the gears and apply a force of approximately 25 pounds at the center of the door during the retraction door should maintain an overcenter position and clear the fork by a minimum of 0.43 inch during the

cycle. The retraction g.

If further

Lubricate the door

Chapter h.

cycle.

hinges

adjustment and

is

actuating

required, the

door attach

linkage

mechanism with the lubricants

should be

specified

adjusted

1/4 turn at

a

time.

in the Lubrication Schedule in

12-20-00.

Cycle the landing gear several landing gear is retracted.

times with the power

pack, checking

each time that the doors close

snugly when

the

nno

32-30-00

Apr

28/06Page

253

Ray~heon

AiKraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

959299-95

NOTE:

INSTALLANC11 BOLTWITH HEAD ON AFT SIDE OF LINK ON RH SIDE

OF AIRPLANE. BOLT HEAD DIRECTION ON LH SIDE OF AIRPLANE IS OPTIONAL

A CAM ASSY

ROLLER

SHOCK STRUT CASTING

(0540 RETRACTED)

AIRCRAFT

BOLT NUT WASHER

AN4-l1 BOLT

I/ ,I

NUT

AN960-416 WASTIER

"-\U\\\\\\\\\\\\\X‘"\\\\\\\\\U

N,\NN COTTER PINPN\\ \ \ NX BUSHING

COTTER PIN

LINK ASSY

~h

I

BUSHING BOLT

-IWVt~ I

I

I

V

AN960-416 WASHER

I

NUT

BOLT

-i

NUT WASHER COTTER

I

I~INOTE:

I

U/

PIN

1

ROLLER

(GEAR UCTENDED)

I

-II-

\IY

.03 TO

INCH OAF

I

ONRIGHTHANDREAR HINGE ONLY, OMIT NUT AND PLACE AN960-416 WASHER UNDER BOLT HEAD ON INSTALLATION

HOLE.250 TO .254 INCH DIAMETER THROUGH PLATE AND

1TEKCAAB

.032 TO .125 INCH OAF AFTER

RIGGING

DEtAa

A NOTE:

NOTE:

TRIMLEADING EDGE OF DOORS fO GIVE -.060 INCH CLEARANCE TO NOSE CONE

Nose Gear Door

Figure

Apr

28/06Page

254

32I30-00

LOCATE HOLE BY ADJUSTING 50-410012-389 PLATE ON BOTH SIDES OF BRACKET. TO OBTAIN OAF SHOWN BETWEEN CAM ASSY AND ROLLER ON SHOCK STRUT CASTING. DRILL THROUGH PILOT HOLE IN PLATE. LINK ASSY BETWEEN CAM ASSEMBLY AND DOOR ASSEMBLY MUST BE OVER CENTER WHEN DOOR IS FULLY OPEN

Rigging

217

A20

Ral~heon

nircrart

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psi of regulated dry air to pressurize the power pack reservoir in place of the engine bleed air. A capped

adjacent to the service valve, is plumbed into the bleed air line to the fill reservoir as a connection point forpressurized air during ground operation of the powerpack assembly. To pressurize the system, remove the cap and connect the air supply to the cross fitting. cross,

the

When

cycling

and

five minute

a

landing gear with the power pack, cooling period every five cycles.

allow

a one

minute

cooling period between cycles

Before removing the airplane from the jacks, make sure that the hand pump handle is in the stowed position, that the plunger on the sen/ice valve is pushed down and safety wired with the plunger retainer in position and pinned, that the landing gear control handle is in the down position and that the landing gear is down and locked. MAIN GEAR DOOR RIGGING

Prior to

rigging the main gear doors, the landing gear must be properly rigged as instructed in MAIN GEAR RIGGING. The following adjustments are to be done in the sequence given. Each time the door linkage is readjusted, the overcenter dimension, the tire clearance and the snug fit of closed doors must be checked. CAUTION: Do not

cycle the landing gear with the power pack until the gear doors are properly rigged. Use the emergency extension hand pump, a TK229/939 or TK229- 1/939 extemal pump (5 or 6, Chart 1, 32-0000), or the equivalent for initial rigging as instructed in LANDING GEAR RIGGING.

a.

b.

Place the airplane

on

jacks (3, Chart 1, 32-00-00). Refer to Chapter

7.

Disconnect the lower clevis from the plate attached to the door by removing the bolt, washer, nut and cotter pin from the clevis. Refer to

Figure

218. Check the cam, link and both devises for freedom of

operation throughout

Adjust the torque of the pivot bolts and lubricate the linkage joints if there is any indication of Refer to the Lubrication Schedule. Refer to Chapter 12 for the proper lubricant.

normal travel.

binding. c.

d.

Make the following check with the gears

extended and the

cam

resting against

the door

hinge

extrusion:

1.

Place the upper edge of a straightedge at the centerline of the link mounting bolt and the lower centerline of the bolt attaching the lower clevis to the plate on the door.

2.

Check that the centerline of the upper clevis bolt is overcenter by no more than 0.06 inch with respect to the attaching point of the bottom clevis to the link when each door locks in the open position.

With the a

e.

fully

landing

gear retracted,

adjust the clevis connecting the upper

link to the

cam

edge

at the

until the door closes for

snug fit.

Check for

a

clearance of 0.04 to 0.08 inch between the door actuator roller and the

adjusting

block of the

cam.

If necessary, loosen the two bolts securing the adjusting block in place and reposition them with respect to the slotted mounting holes in the adjusting block until the proper clearance is obtained, then tighten the two bolts to

lock the f.

adjusting

block in

place.

Check the cams, link and pivots for proper alignment and freedom of movement; the out on the actuator roller when the gear is cycled.

NOTE:

Adjust the

door

linkage only

114 turn at

a

cam

slot must not bottom

time.

32-30-00

Apr

28/06Page

255

Ray~heon

AiKraft Company

MANUAL SUPER KING AIR B300/B300C MAINTENANCE

DOOR HINGE EXTRUSION

n)~l?rcSPRINO STRAIGHT EDGE CAM

ADJUSTING r\

BLOCK

(d ’,O

I/

.04 TO .08 INCH

CLEARANCE BETWEEN

Y:,

7 ADJUSTING ~O

LINK

I

BLOCK

OF CAM AND ROLLER

Y\

UPPER

ADJUSTING CLEVIS

MAXIMUM OF .06 INCH

LOWER ADJUSTING CLEVIS

LINK PLATE

MAIN GEAR DOOR

20420+7

Rigging Figure 218

Main Gear Door

28/06Page Apr

256

32-30-00

A20

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

g.

Retract the gear and apply 25 pounds of pressure to the lower center edge of the door during retraction. The door should clear the tire by a minimum of 0.62 inch during the cycle. If the door clearance is sufficient, retract the gear and check that the doors are properly closed. If the doors do not close flush or are too tight, adjust the door linkage to obtain a proper fit by adjusting the upper and lower pivots or by moving the slotted link plate on the door. To move the slotted link plate, remove the center bolt and loosen the two outside bolts.

h.

If it is necessary to

move

pilot

to drill a new center hole in the

NOTE: The link plate

can

plate on the door to obtain a proper fit of the door during rigging, tighten plate in its new position and use the existing hole in the door bracket as a link plate.

the slotted link

the two outside bolts to hold the link

(such

be reused if the redrilled center hole

as a

hole in the

shape of

a

figure eight)

will

retention. However, if the circumference of the new hole in the link plate overlaps the circumference of the old hole by two-thirds or more, replace the link plate and drill a new hole for positive

provide positive retention.

i.

Check that the door linkage is properly overcenter in the open position by applying 25 pou nds of pressure toward the gear at the lower center edge of the door. This is to ensure that each door is sufficiently locked open to withstand the air load present during takeoff and landing. Rig the door if it folds under this 25-pound load.

j.

Lubricate the door

Chapter k.

hinges

and the

actuating

mechanism

as

instructed in the Lubrication Schedule. Refer to

12.

gear several times with the power pack, checking each time that the doors close is retracted and that they stay open when the landing gear is extended.

Cycle the landing the

landing gear

snugly when

CAUTION: To prevent serious

damage to the pump, never operate the power pack without supplying 18 to 20 psi regulated dry air to pressurize the power pack reservoir in place of the engine bleed air. A capped cross, adjacent to the service valve, is plumbed into the bleed air line to the fill reservoir as a connection point for pressurized air during ground operation of the power pack assembly. When pressurizing the system, remove the cap and connect the air supply to the cross fitting. of

When

cycling

and

five-minute

a

the

landing gear with the power pack, cooling period every five cycles.

allow

a

one-minute

cooling period between cycles

Before removing the airplane from the jacks, make sure that the hand pump handle is in the stowed position, that the plunger on the service valve is pushed down and safety wired with the plunger retainer in position and pinned, that the landing gear control handle is in the down position and that the landing gear is down and locked. i.

Remove the

airplane from the jacks.

HYDRAULIC LANDING GEAR PLUMBING LEAK TEST AND CLEANING a.

Low PressureTest:

Attach

Nitrogen

power

pack.

2.

Apply

150

3.

There shall be

4.

Apply

1.

A20

psi

cart to the

extend, emergency extend, retract line, and the hand pump suction line at the

pressure and close valve no

pressure

trapping pressure

for 5 minutes.

drop.

leak detector fluid to connection to locate leaks.

32-30-00Page

257

Ral~heMI

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

b.

c.

Cleaningand Flushing: 1.

Bleed off pressure.

2.

Disconnect the nitrogen cart and hook up the

3.

Open

one

4.

Pump

1.5

5.

Do notreusethefluid.

line at

a

time and

measure

pints of fluid through each

High Pressure

hydraulic test

pump

(5 or 6,

Chart 1,

32-00-00)

to the manifold.

from the downstream side.

line.

Test:

Disconnect the extend line at the gear down port of the power pack and connect it to the test pump pressure hose.

1.

Disconnect the retract line assembly at the gear up port of the power pack, and connect it to the return hose

2.

of the test pump.

pressure to the main extend lines for three minutes.

3.

Apply 1,850 psi

4.

Visually inspect each leakage.

NOTE: A

drop

connection

in pressure may

or

occur

fitting

in the

landing

gear extend lines

due to allowable internal

leakage

Change the test pump selector valve so that the landing gear retract lines landing gear extend lines are the return to the reservoir of the test pump.

6.

Apply

7.

The

8.

Visually inspect

9.

If

no

1,850 psi pressure

landing gear

leaks

are

to the

landing

actuators will retract

each connection

found, relieve the

10. Disconnect the tube

or

as

fitting

to

verify

there is

no

in the actuators.

5.

a

(white)

are now

pressurized

and the

gear retract lines for three minutes.

the pressure is in the

applied.

landing gear

retract lines to

verify

there is

no

leakage.

test pressure.

assembly from pack.

the return to the reservoir of the test pump and reconnect it to the gear

down port of the power 11.

Change the

test pump selector valve so that the

landing gear

retract lines are the return to the reservoir of

the test pump. 12. With service valve knob in the down

position

and the hand pump in the stowed

pressure hose to the section line at the power 13. Disconnect the

secondary extend

fluid flows from the 14. Connect

15. The 16.

Visually inspect and

line at the

nose

apply 1,850 psi

actuators will extend

each connection

white)

connect the

gear actuator and pump fluid

through the system

until the

gear line.

gear actuator and

landing gear

(brown

Page

nose

nose

position,

pack.

or

as

25832-30-00

the pressure is

fitting in

lines to insure there is

pressure to the

no

seconda~y

extend system for 5 minutes.

applied.

the emergency extend lines and the hand pump pressure

leakage.

neo

RBytheOn

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

17. If

no

leakage

is found,

remove

hydraulic

test pump and connect all

components that

were

removed.

leakage is discovered, relieve the test pressure and insure there is no pressure in the hydraulic lines. repairing the leak, periorm the part of the pressure test again that showed leakage.

18. If

After

REPAIR OF HYDRAULIC SYSTEM PLUMBING

repair of damaged hydraulic plumbing lines used in the landing gear retraction and extension system may accomplished using CryoFit couplings, manufactured by Advanced Metal Components Incorporated, 1374 Willow Road Menlo Park, CA 94025. Should such repair be required, contact the Technical Support Department, Raytheon Aircraft Company, Wichita, KS 67201. You will be advised of procedures for obtaining repair parts and personnel to train and guide your service staff in the correct technique for installation of the CryoFit couplings. Effective

be

repairing hydraulic plumbing lines with CryoFit couplings are detailed in Chapter 29 of the King Air Component Maintenance Manual. These procedures, however, should only be used by properly trained and qualified personnel. Procedures for Series

32-30-00Page

259

Raythwm

AiKraft

Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

WHEELS AND BRAKES

DESCRIPTION AND OPERATION

airplane has experienced abnormal landing gear procedures of any type, as a safety precaution, place the airplane on jacks prior to performing any inspection or maintenance. Ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

WARNING: When

CAUTION:

an

Jacking of an airplane for the purpose of landing gear operation, inspection, servicing or maintenance, should be accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary to jack the airplane in the open, wind velocity in any direction and terrain variations, must be compensated for prior to jacking the airplane

MAIN WHEEL ASSEMBLIES each main landing gear (Ref. TIRES for size and type). Each I together with eight bolts and nuts, with one washer under each bolt head and nut to prevent galling and stress concentration. An O-ring mounted in a groove on the inner wheel half seals the wheel against air leakage when the wheel halves are joined together. Eight keyway liners bolted to each inboard wheel half protect the wheel flange from damage that would be caused by the tangs on the rotating brake

Two

forged

aluminum 6.50 X 8 wheels

wheel consists of

an

discs. The wheels rotate installed

seals

are

and

cotter

a

are

installed

on

inner and outer wheel half held

over

on

tapered

each wheel

roller

bearings seated in bearing cups shrink-fitted into each wheel half. Grease bearing. The wheel assemblies are retained on each axle with washers, a nut

pin.

NOSE WHEEL ASSEMBLY One cast aluminum 6.50 X 10 wheel is installed

the nose landing gear (Ref. TIRES for size and type). The wheel I together with eight bolts and nuts, with one washer under each bolt head and nut to prevent galling and stress concentration. An O-ring mounted in a groove on the inner wheel half seals the wheel against air leakage when the wheel halves are joined together. The wheel rotates on tapered roller bearings seated in bearing cups shrink-fitted into each wheel half. Grease seals are installed over each wheel bearing. The wheel is retained on the axle by a washer, a spacer, a nut and a cotter pin. consists of

an

inner and

an

on

outer wheel half held

TIRES nose landing gear wheel is equipped with a 22 X 6.75 X 10, 8-ply rated, tubeless, rim-inflated landing gear wheel is equipped with a 19.5 X 6.75 X 8, 10-ply rated, tubeless, rim-inflated tire.

The

tire. Each main

HYDRAULIC BRAKE SYSTEM

hydraulic brakes are applied by depressing the toe portion of either the pilot’s or copilot’s rudder pedals, thereby moving the piston rod in the master cylinder attached to each pedal. The resulting hydraulic pressure is transmitted through flexible hoses and rigid aluminum tubes to the two disc brake assemblies between each pair of main landing gear wheels. Hydraulic fluid is supplied to the master cylinders from a reservoir accessible through the The dual

nose

avionics compartment door.

(Ref. Figure 1).

I

parking brakes use the main brake system and two additional valves to hold the airplane in place while on the ground. The parking brakes are applied by pressurizing the brake lines in the normal manner with the main brakes, then pulling out the parking brake knob (located below the pilot’s subpanel), which closes both parking brake valves simultaneously. The valves retain the pressure in the brake lines, keeping the brakes locked. The parking brake is released by depressing the brake pedals to equalize the pressure on both sides of the valves, then pushing in the parking brake knob to open the valves.

The

32-40-00

Apr

28/06Pagel

Raythwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BRAKE ASSEMBLY The

airplane is equipped

side of each main

with four

hydraulically-operated,

multi-disc, metallic-lined brake assemblies,

one on

each

gear hub and axle assembly. A hydraulic inlet swivel fitting interconnects the two brake assemblies in each pair. Each brake assembly contains two inlet ports; a bleeder valve is installed in one and an inlet fitting is installed in the other. The brake assemblies can be interchanged by reversing the locations of the inlet

landing

and bleeder

fittings.

Each brake

assembly

keyed to rotate with the wheel, a stationary carrier and lining and piston housing. Braking occurs when hydraulic pressure is applied to the three pistons in the piston housing. The pistons compress the disc stack, creating friction between the rotating discs and the brake lining attached to the stationary components of the brake. Three automatic adjuster assemblies are installed in each piston housing to maintain the proper brake clearance and compensate for brake lining wear.

a

torque plate bolted

contains two stacked discs

to the

PARKING BRAKE VALVES

hydraulic lines from the copilot’s master cylinders are pilot’s rudder pedals on the aft side of the pressure bulkhead. The valves are operated simultaneously by a push-pull control cable connected between the valve levers and the parking brake knob below the pilot’s outboard subpanel. The knob is pulled out to close the valves and pushed in to open them. Parking

brakes

are

provided by

two

lever-operated valves

to the wheel brakes. The two valves

Apr 28/06Page

2

32-40-00

in the

located forward of the

Ray~hwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURE VENT RESERVOIR

PILOT’S MASTER CYLINDER

II II

_II_COP1LOT’S IP ~IMASTER

II

L~ r41 CYLINDER

OVERBOARD DRAIN

FWD

TO LER BRAKE

J

AR

PARKING BRAKE VALVES

L To RIGHT

BRAKE

BRAKE SCHEMATIC

-hl II~/ PARKING

BRAKE

CONTROL KNOB

BRAKE FLUIO RESERVOIR

MASTER CYLINDERS

PRESSURE WUAUZATION LINE PARKING BRAKE VALVE BRAKE ASSEMBLY 35021bl(

Hydraulic Brake System Figure 1

A20

32-40-00

Raytheon

AiKraft

Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

WHEELS AND BRAKES

TROUBLESHOOTING

Troubleshoot the brake system using Chart 101. Follow the steps in the chart sequentially unless otherwise instructed. For example, proceed to the next step when there are no instructions immediately following a NO condition.

WARNING: Never service the accumulator

landing

gear without first

wheel wells,

landing

jacking

When

encountered,

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart 1, 32-00-00). Stay clear of gear doors while the landing gear is in operation. or

placing

gears and

the

the

airplane in an unsheltered area where winds in excess jack more than one gear clear of the ground at a time.

the

the the

of 35 knots may be

never

Any time the landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the jacks.

with the power

Chart 101

Troubleshooting STEP 1

Do the brake

fail to

pedals operate?

feel solid, but the brakes

Brake

System

YES

Go to

YES

Bleedthe

YES

GotoStep8.

YES

GotoSteplO.

YES

Go to

YES

Replacethe brakelining.

YES

Clean

YES

Removetheforeign

YES

Replacethe

Step

6.

NO

STEP 2

Do the brake

pedals

feel

spongy?

brakesystem.

NO STEP 3

Do the brakes

grab? NO

STEP 4

Are the brakes unable to hold

pressure?

NO STEP 5

Does the

brake fail to hold

parking

properly?

Step

12.

NO *NOTE:

New brakes may not hold the

moving are

STEP 6

at

high

power

settings

airplane from until the brakes

broken in.

Is the brake

lining

worn

beyond

allowable

limits? NO STEP 7

Is the brake

lining

contaminated with oil,

or

replace the

brake

lining.

grease, etc.?

STEP 8

Is

a

stone

or

other

foreign

matter

locking

the

matter.

brake disc?

NO STEP 9

A20

Is the brake dise

warped

or

bent?

disc.

32-40-00

Apr

28/06Page

101

I

Raycheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 101 Brake

Troubleshooting STEP 10

fluid leak in the brake

system?

is there

a

Visually

check the entire system.

System (Continued) YES

Correct any faults.

NO STEP 11

Are the master

cylinder seals leaking? scoring or damage.

YES

STEP 12

Is there air in the brake

system?

If the seals

are

scored

or

damaged, replace

them.

Check the seals for

YES

Bleed the brake system.

YES

Replacethe valve.

YES

Adjust

NO STEP 13

Is the

parking

brake valve defective? NO

STEP 14

Is the control cable out of

adjustment

or

or

replace

the cable.

broken?

Page

10232-40-00

A20

Ral~heon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

WHEELS AND BRAKES

performing

WARNING: When

maintenance

on a

hydraulically operated landing

gear system, be

aware

that

any movement of a hydraulic actuator cylinder can displace hydraulic fluid and cause unanticipated movement of other actuator cylinders in the landing gear retraction system.

Servicing of the landing

hydraulic accumulator can

also result in

unanticipated movement landing gear system. Therefore, place the airplane on jacks prior to performing any inspection or maintenance. Cycle the landing gear and ensure that all three landing gears are down and locked prior to removing the aircraft from jacks. of

an

gear

actuator. Either action can result in

an

unsafe, unlocked

hydraulic system or do maintenance or rigging of landing placing airplane on jacks (3, chart i, 32-00-00). Stay clear of wheel wells, landing gear is in operation. Never service the accumulator

or

gear without first

the

the

airplane in an unsheltered area where winds in excess encountered, never jack more than one gear clear of the ground at a time.

When

Any

jacking

time the

the

the

the

of 35 knots may be

landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the

with the power

jacks. WHEEL AND BRAKE SERVICING For detailed information

the

applicable

to the proper inspection and repair maintenance manual. component

relating

procedures

for the wheels and brakes, refer to

TIRES

airplane is equipped with 10-ply, 19.5 x 6.75 x 8, rim-inflated tubeless 8-ply, 22 x 6.75 x 10, rim-inflated tubeless tire on the nose landing gear.

The

CAUTION: If the tires

detergent

come

in contact with fuel,

hydraulic fluid,

or

tires

on

the main

oil, wash them down

landing

as soon as

gears and

possible

an

with

a

solution to prevent deterioration of the rubber.

Maintaining proper tire inflation will help to avoid damage from landing shock and contact with sharp stones and ruts, and will minimize tread wear. When inflating the tires, inspect for cuts, cracks, breaks and tread wear. The pressure of a serviceable tire that is fully inflated should not drop more than 5% over a 24-hour period. CAUTION:

Recapped tires may swell due to increased temperature at takeoff. Increased tire size may damage the landing gear doors and retract mechanism during retraction or extension of the landing gear.

NOTE: While

repair

Raytheon

Company cannot recommend recapped tires, tires retreaded by specialized service limitation rating for TSO-C62c may be used.

Aircraft

station with

a

an

FAA-approved

daily for proper inflation on airplanes performing more than one flight a day. Check the tires on other flight and at least once a week. Check the tire pressure only when the tires are cool; airplanes wait at least two hours (three hours in hot weather) after a flight before checking tire pressure. consequently, Check the tires

before each

together on dual wheels only tires that are equally inflated, with inflated diameters recommended (but not required) to be within 0.25 inch of matching, for equal load distribution on the tires. Measure the diameters after the tires have been mounted and kept fully inflated for a recommended (but not required) period of 12 hours at room temperature to allow for normal tire growth. If the inflated diameters of the tires on a set of dual wheels do not match Pair

n2o

32-40-00

201

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

within 0.25 inch, install the tire with the larger diameter on the outside wheel. It is permissible to reverse the direction of rotation of a wheel/tire assy. It is further recommended that the same tire brand and tread style be used on a set of dual wheels.

Inflate the main gear tires to 90 ~t2 psi loaded.

loaded

psi

or

psi

to 85 ~2

if the

airplane

is

on

jacks. Inflate the

nose

gear tire to

55-60

SEALING MINOR LEAKS OF RIM-INFLATED TUBELESS TIRES

(8, Chart 2, 32-00-00)

Aero Seal tire sealant

is recommended

as an

effective

means

of

controlling

the

gradual

loss

of tire inflation pressure when the leakage rate does not exceed five percent over a 24-hour period. The tire sealant and an M400 injector (11, Chart 1, 32-00-00) for applying it are available in either pint or gallon quantities from a

Raytheon Apply a.

Company

the tire sealant

Place the

psi b.

Aircraft

or

When

as

airplane

authorized outlet.

follows:

on

jacks (3, Chart 1,32-00-00)

as

instructed in

Chapter 7

and reduce the tire pressure to 35

less.

using

the M400

and

adapter (furnished

1.

Screw the

2.

Place the M400

3.

Prime the

4.

Pull the handle

CA UTION:

injector

gallon

container:

with the

injector)

injector squarely

injector with fully

on

the

into the container.

adapter

in

a

vertical

position.

several slow strokes of the handle.

back to fill the

Keep out of line

with the

injector

with tire sealant

injector handle and remove

(the injector will hold the

injector from the

two

ounces

of

sealant).

valve stem before

releasing

the handle. 5.

c.

Place the tip of the injector squarely on the valve stem and inject the tire sealant by pushing the handle completely in. The valve core does not need to be removed. One injection will be sufficient for each tire.

When

using

the

pint container and the attached

1.

Install the pump

2.

Screw the

3.

on

the

pint container

adapter firmly

Operate the

and

pump:

tighten firmly.

onto the tire valve stem.

pump until two

ounces

of tire sealant

las

indicated

on

the

container)

has been

pumped

into the

tire. 4.

d.

Removethe

adapterfromthevalve

stem.

Inflate the tire to the proper pressure to distribute the tire sealant and

remove

the

airplane

from the

jacks.

BRAKE SYSTEM SERVICING Brake system servicing is limited primarily to maintaining the hydraulic fluid level in the reservoir mounted in the upper LH comer of the aft bulkhead of the nose avionics compartment. When checking the level after performing maintenance

on

the brake system, add

a

within 1.0 inch of the top of the reservoir

Page

rpA202

28/06

32-40-00

sufficient

quantity of hydraulic fluid (1, on the dipstick).

Chart 2,

32-00-00) to fill

the reservoir

(see level marked

nzo

Ralfheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BRAKE FLUID RESERVOIR PRESSURE EQUALIZATION LINE AND ORIFICE CLEANING

Contaminants in cabin air

(fuzz, lint, nicotine, tar, etc.) can find their way into the orifice installed in the pressure equalization line and eventually reduce the orifice so that excessive air is diverted into the brake fluid reservoir, causing excessive pressure to be applied to the master cylinders. The orifice should be cleaned at the interval specified. Refer to Chapter 5-00-00. a.

Disconnect the pressure

b.

Select

a

length

of rubber

equalization

line from the brake fluid reservoir

that will slide

tubing

over

the pressure

(Ref. Figure 201).

equalization

line. Ensure that the

1 tubing

fits

tightly. NOTE: The bottom drain is located c.

Inject

a

immediately

small amount of solvent

(6,

Chart 2,

forward of the forward pressure bulkhead.

32-00-00)

into the rubber

tubing and blow out the line with low air Repeat as necessary until clean

pressure. Check the solvent flowing from the bottom drain for cleanliness. solvent flows from the bottom drain. d.

After clean solvent flows from the bottom drain,

e.

Remove the rubber

tubing

from the pressure

dry

the line

equalization

thoroughly with

low air pressure.

line. Connect the line to the brake fluid reservoir.

INLET TUBE

PRESSURE

MUAUZATION LINE

BRAKE

RESERVOIR

EQUALIZATION ORIFICE

FORWARD PRESSURE BULKHEAD

3002(98

Brake Fluid Reservoir

A20

Equalization Figure 201

Line Orifice

Cleaning

32-40-00

Apr 28/06Page

203

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BLEEDING THE BRAKE SYSTEM at any point between the master cylinder in and the wheel brake assembly, whenever the brakes become spongy service, or whenever the parking brakes will no longer hold. In the latter instance, the system should be checked for leakage.

Brake

Use to

system bleeding will be required whenever the system is opened

only hydraulic fluid (1,

Chart 2,

get into the brake system. Dirt

cylinders

and

cause

32-00-00)

can

in the brake

get under seals and

system and

ensure

leaks

cause

or

clog

that the

dirt or foreign matter is allowed compensating ports in the master no

the brakes to lock.

recommends the use of pressure pot brake bleeding. If the pressure pot bleeding method is not available, electric bleeding is recommended. Use the gravity method only if the other two methods are not available. If the gravity system is used, pressure bleed the brakes at the earliest possible time. Using any method, the parking brake control and toe brake pedals must both be fully released to open the compensating ports

Raytheon Aircraft Company

in the brake master

cylinders.

or spongy after the bleeding operation, air may be trapped in the cylinders. Remove the brake lay it on its side. Add brake fluid as needed through the bleed port and tap the brake lightly with a rubber hammer to dislodge any air bubbles. When air bubbles no longer appear at the port, install the brake and repeat the bleeding procedure.

If the brakes feel soft

and

GRAVITY BLEEDING

bleeding is done from the master cylinder down to the brake assembly. The brake fluid reservoir during the bleeding operation. The entire system may be bled by operating the pilot’s brake pedals kept because the pilot’s and copilot’s master cylinders are plumbed in series. Bleed the system as follows:

This method of

full

must be

the bleeder valve

brake

assembly sufficiently

a.

Open

b.

Slowly depress the pilot’s brake pedal corresponding steadily to eliminate air trapped in the system.

c.

Hold the brake

pedal

on one

in the

depressed position and

to allow air to escape from the brake

to the brake

being

bled.

Depress

the

assembly.

pedal slowly

close the bleeder valve. Ensure there is

no

leakage

and

at the

brake bleeder.

d.

Release the brake

e.

Repeat steps

f.

Open the no more

a

pedal.

through

bleeder valves

d until on

no more

air bubbles appear in the drained fluid.

the other brake and repeat steps

a

through d, depressing the

other brake

pedal

until

air bubbles appear in the drained fluid. the bleeder valve and

there is

g.

Tighten

h.

Check the brake reservoir fluid level and add

ensure

no

leakage

at any bleeder valve.

hydraulic fluid (1,

Chart 2,

32-00-00)

as

required

to obtain

a

full

reading. i.

Apr

Check the brakes for proper operation. When the brake pedals and the pedal pressure should be equal for both brakes.

28/0632-40-00

are

depressed there should

be

no

spongy feeling

Raytheon

AiKraft Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

PRESSURE BLEEDING

bleeding is the most efficient method of bleeding the brake system. This procedure involves attaching a hand-pump pressure pot (12, Chart 1, 32-00-00) or a mechanical-pump pressure bleeder (13, Chart 1, 32-00-00) to the bleeder assembly and back bleeding the system to the fluid reservoir. Pressure

BRAKE BLEEDING (USING A PRESSURE POT) a.

Disconnect and cap the pressure equalization line from the brake fluid reservoir. Attach an extension line approximately three feet in length to the open port. Place the end of the extension line in a clean receptacle to collect the brake fluid overflow

b.

(Ref. Figure 202).

Remove the bleeder valve and the

fitting

on

each bleeder

c.

Connect the pressure

d.

Apply

a

an

AN815-4

fitting

into the open

assembly. line(s)

from the pressure pot to the AN815-4

constant pressure of 15

observe the fluid

adapter from each bleeder assembly. Install

draining

fitting(s).

pounds maximum to the pressure pot. Open the pressure pot control valve and

from the extension line. is free of air bubbles, then close the pressure pot valve.

e.

Bleed the system until the

f.

Disconnect the pressure line(s) from the AN815-4 fitting(s). Remove the AN815-4 fitting from each bleeder assembly and install a new O-ring, the bleeder valve and the adapter in each bleeder assembly.

g.

Remove the extension line from the brake fluid reservoir. Connect pressure

h.

draining fluid

equalization

line to the open port.

Remove the cap from the hydraulic fluid reservoir and add hydraulic fluid (1, Chart 2, 32-00-00) as required to the fluid level within 1.0 inch of the top of the reservoir (see the level marked on the dipstick). Install the

bring cap i.

on

the reservoir.

Check the

operation of the brakes. There should be no equal on the LH and RH brakes.

soft

or

spongy

feeling

at the brake

pedals and the pedal

pressure should be

BRAKE BLEEDING

(USING

AN ELECTRIC

BLEEDER)

a.

Disconnect and cap the pressure equalization line from the brake fluid reservoir. Attach the electric bleeder fluid return line to the open port (Ref. Figure 202).

b.

Remove the bleeder valve and the

fitting

on

each bleeder

adapter from each

bleeder

c.

Connect the infusion lines

d.

Activate the electric bleeder and set the relief valve to 15

observing the

assembly.

Install

an

AN815-4

fitting

into the open

assembly. on

pressure gage

the electric bleeder to the AN815-4

prior to opening

pounds

fittings. maximum

the electric bleeder control

(this valve).

may be ascertained

by

e.

Open the electric bleeder control valve and observe the returning fluid through the inline sight glass. Pumping the pilot’s and copilot’s pedals during the bleeding process may help to dislodge any air bubbles trapped in the master cylinders.

f.

When the

A20

returning

fluid shows

no

further evidence of air bubbles, close the electric bleeder control valve.

32-40-00

Apr

28/06Page

205

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRESSURE TION

FITTING

RETURN

/RESERVO1A

LINE,

I io~ i~--

PRESSURE BULKHEAD

L

TO ANB15-4

FITTING

LINES

TD PIN81511

FITTING

i

i PRESSURE BLEEDER

I

,j

USING THE MECHANICAL PUMP PRESSURE BLEEDER

BRAKE HYDRAULIC INLET LINE

ASSEMBLY PRESSURE TION

FITTING EXTENSION LINE FORWARD

PRESSURE BULKHEAD

RECEPTACLE BLEEDER ADAPTER (REMOVE TO ATTACH AN815-4 FITTING)

DNAEVLAV

TO AN815-4

FITTING

LINE

POT

USING THE HAND PUMP PRESSURE POT 35o-2te-to

Pressure

Apr

28/06Ze28~

32-40-00

Bleeding the Brake System Figure 202

A20

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

g.

Disconnect the fluid infusion lines from the AN815-4

assembly h.

and install

a new

O-ring,

fittings.

Remove the AN815-4

fitting from each assembly.

bleeder

the bleeder valve and the adapter in each bleeder

Disconnect the fluid return line from the brake fluid resen/oir. Connect the pressure

equalization line

to the open

port. i.

Remove the cap from the hydraulic fluid reservoir and add hydraulic fluid (1, Chart 2, 32-00-00) as required to bring the fluid level within 1.0 inch of the top of the reservoir (see the level marked on the dipstick). Install the

cap

j.

on

the reservoir.

operation of the brakes. When the brake pedals pedal pressure should be equal on both brakes.

Check the and the

depressed

are

there should be

no

spongy

feeling

BRAKE MASTER CYLINDER REMOVAL

hydraulic fluid

from the brake system

(Ref. Figure 203).

a.

Bleed the

b.

Remove the floorboards from around the master

c.

Disconnect and

d.

Remove the Remove the

plug

the brake lines at the

attaching cylinder.

cotter

pins,

cylinder.

cylinder. Tag

washers and clevis

the lines for identification.

pins

at the upper and lower end of the master

cylinder.

BRAKE MASTER CYLINDER INSTALLATION a.

cylinder in position pins (Ref. Figure 203).

Place the brake master and cotter

on

the rudder

pedal

and install the

clevis

pins,

washers

1

b.

Connect the brake lines to the master cylinder. Position the upper brake line friction against the rudder pedal.

c.

Install the floorboards.

d.

Bleed the brake system

as

attaching

so as

to cause the least amount of

instructed in BLEEDING THE BRAKE SYSTEM.

ADJUSTMENT OF THE BRAKE MASTER CYLINDER LINKAGE a.

b.

Loosen the locknut

the

piston shaft (Ref. Figure 203).

pin, washer and clevis pin attaching lug on the rudder pedal.

Remove the cotter clevis free of the

c.

on

The so

length

of the

cylinder assembly can

be

1

the master

cylinder clevis

to the rudder

pedal.

Slide the

adjusted by turning the clevis on the piston shaft. Adjust the clevis points at the top and bottom of the cylinder is 9.00 that the piston does not bottom when the brake is applied.

that the distance between the centers of the attachment

inches.

Adjust

the

CAUTION: The above

length

of the

cylinder so

adjustment must be

maintained for correct

operation

of the master cylinder. Do not

readjust

the overall dimension between the centers of the clevis hole and the master cylinder mounting pivot hole to accommodate the

physical stature of operating personnel.

32-40-00Page

207

RBytheoH

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MASTER CYLINDER COTTER PIN

PIN

WASHER

STATIONARY

A

SHAFT

DETAIL

B

MASTER CYLINDER

HYDRAULIC

FITTINGS7 II

II u----cc\elru INLET PRESSURE EQUALIZA

TUBE

LINE

FLUID

RESERVOIR

FORWARD PRESSURE

BULKHEAD

TTER PIN AMER

LOCKNUT

FORW

PRESSURE BULKHEAD PRESSURE EQUALIZATION ORIFICE

DETAIL

A

350-351-l(g

Brake Master

Figure

Page

rpA802

28/06

32-40-00

Cylinder

203

A20

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Move the master

into

position

to mate with the

washer and

cylinder clevis cotter pin.

e.

Tighten the

clevis locknut.

f.

Check the upper and lower attachment points of the master the attachment lugs on the rudder pedal.

lug

on

the rudder

cylinder to

ensure

pedal

and install the clevis

that there is

no

pin,

interference with

PARKING BRAKE VAL VE REMOVAL a.

Bleed the

b.

Remove the floorboard located

c.

Remove the

fluid from the brake system.

hydraulic

adjacent

to the

pilot’s

safety wire (Ref. Figure 204).

and disconnect the link

d.

Disconnect and cap the

hydraulic

e.

Remove the two bolts

rudder

pedals

assembly from

to

gain

access

the control cable

to the brake valves.

by removing

the two

screws

1 lines from the valves.

securing the

valves to the forward pressure bulkhead and

remove

the valves from the

airplane. f.

Cut the

safety wire

and disconnect the link

assembly

from the valve control levers

by removing

the two

screws

and four washers.

PARKING BRAKE VALVE INSTALLATION a.

Connect the link

assembly to the (Ref. Figure 204).

valve control levers with two

the forward pressure bulkhead and

Position the valves

c.

Insert the end of the control cable into the link

d.

Connect the

e.

Bleed the brake system

f.

Adjust the parking brake control cable

g.

Install thefloorboard.

hydraulic

and four washers. Secure with

safety wire

1

b.

on

screws

assembly.

secure

the valves with the two bolts.

Secure with the two

screws

and

safety wire.

lines to the valves. as

instructed in BLEEDING THE BRAKE SYSTEM. as

instructed in ADJUSTING THE PARKING BRAKE CONTROL CABLE.

ADJUSTING THE PARKING BRAKE CONTROL CABLE parking brake valves is not recommended. If leakage is encountered, replace the valve. the proper operation of the parking brake valves, the full travel of the valves in both directions must be

NOTE: Overhaul of the To

ensure

maintained. a.

Remove the floorboard

b.

Loosen the two

Move the cable

stop. Tighten

n2o

housing

the

to the

pilot’s

securing the parking (Ref. Figure 204).

screws

pressure bulkhead c.

adjacent

rudder

pedals.

brake control cable

in the blocks until the valves

housing

in the

phenolic blocks

on

the forward

1 are

fully opened

when the control knob is

pushed

in to its

screws.

32-40-00

Apr 28/06Page

209

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINIENANCE MANUAL

CONTROL,

PHENOLIC

CABLE

BLOCK,

P~ ~-\LoCK

CABLE HOUSING

FORWARD PRESSURE

SCREW

BULKHEAD

SCREW :o

TO LH BRAKE

NUT

SCREW

WHEEL

PARKING VALVE

PILOT’S MASTER CYLINDER FROM

BRAKE

LINK

~Y

FROM COPILaT’S’ MASTER CYLINDER

~P SCREW

SCREW

BOLT

CONTROL LEVERS WASHER

TO RH BRAKE

WHEEL sao-3sl-lla

Parking

Brakes Valves and Control Cable

Figure d.

Pull the control knob out to its stop and check that the valves close

e.

If necessary, repeat steps b

f.

Install the floorboard

through

adjacent

to the

Adjustment

204

fully.

d until the valves open and close

pilot’s

rudder

fully

at the control knob

stops.

pedals.

NOSE WHEEL REMOVAL

I

a.

Remove the cotter

CAUTION: Use

care

pin,

when

axle nut, washer and spacer from the axle

removing all internal and external nose

(Ref. Figure 205).

wheel components to avoid

damaging

the axle

surface and/or nicking the axle threads.

b.

Remove the outer grease seal and the

c.

Remove the inner

bearing

cone

bearing

cone

and

remove

the wheel and tire from the axle.

and the grease seal from the axle.

NOSE WHEEL INSTALLATION

I

CAUTION: Aeroshell Grease 5 SHC 100, and MIL-G-81322 grease are not compatible; DO NOT MIX. If the grease is changed, make certain that all the affected components are thoroughly cleaned before lubrication. To avoid the

Apr

possibility of mixing incompatible greases,

28/0632-40-00

use

the

same

grease

throughout

this installation.

A20

Raytheon

Aircraft

company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

a.

Pack grease (9, Chart 2, 32-00-00) or (4, Chart 2, 32-00-00) into the inner and outer bearing cones and smear grease on the ends of the rollers. Spread an adequate coat of grease on the surface of the bearing cups

I

(Ref. Figure 205).

1

b.

Check the axle and nut for burrs

c.

Carefully place the inner grease seal on the axle against the axle shoulder with the lips of the seal facing the bearing. Place the inner bearing cone on the axle against the seal, place the wheel and tire on the axle and seat the bearing cone in the cup. Install the outer bearing cone on the axle and seat the cone in the outer bearing cup.

d.

Install the outer grease seal

e.

Apply

on

or

rough

threads.

the axle with the

lips of the

seal

facing

the

bearing.

adequate coat of grease (9, Chart 2, 32-00-00) or (4, Chart 2, 32-00-00) to the threads of the axle and bearing surfaces of the spacer, washer and axle nut. This grease must be identical to the used on the wheel bearings. Install the axle nut, washer and spacer on the axle.

an

the nut and to the

grease f.

g.

Tighten the bearings.

Back off the axle nut to see

h.

axle nut to 150

that there is

Install the cotter

no

200

inch-pounds torque

while

rotating the

wheel to

ensure

proper

inch-pounds

while

If the holes in the axle and the nut do not

align, tighten

the nut to the next available

torque, then torque the

of the

the wheel. Check to

nut to 30

zero

rotating

seating

side motion of the wheel.

pin.

keying

position.

NOSE GEAR AXLE

OUTER BEARING CONE

GREASE SEAL--

r

GREASE SEAL

SPACER

INNER BEARING CONE

COTTER PIN

Y’~´•

NUT

WASHER 3oo-x4-s

Nose Wheel

Figure 205

n?o

32-40-00Page

211

Ray~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BRAKE WEAR LIMITS To check the total disc wear, apply the parking brakes, then measure the distance between the pressure plate and the brake housing as shown in Figure 206. If this dimension is 0.200 inch or greater, remove the brake assembly

landing gear and check the individual discs for wear manual. Overhaul the brake assembly if required.

from the

as

instructed in the

applicable component maintenance

SEGMENTED CARRIER AND LINING

PRESSURE PLATE

.200 INCH

BRAKE HOUSING

DIRECTION OF MOVEMENT PISTON

300-2186

NOTE: APPLY BRAKES BEFORE CHECKING WEAR TOLERANCE

Brake Wear Limits

Figure

206

MAIN WHEEL AND BRAKE REMOVAL a.

Remove the three

screws

securing

the

hubcaps

to the wheels and remove the

hubcaps

and

gaskets

(Ref. Figure 207). CA UTIOIV: Use

care

when

removing all internal and external wheel components to avoid damaging the axle surface

and/or nicking the axle threads. b.

Remove the cotter

wheel and tire to the axle. Remove the wheels and tires

from the

grease seals and

pin, nut and washers securing each axle, being careful not to drop or damage the

c.

Disconnect the brake

d.

On

hydraulic

airplanes equipped

line from the inlet swivel

with the brake deice system,

fitting

remove

bearing

cones.

and cap the line and

the deice manifold

as

fitting.

instructed in

Chapter 32-41-

00.

Apr

28/0632-40-00

A20

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

e.

Remove the inboard and outboard brake assemblies, being careful not to drop and the bleeder

or

damage

the inlet swivel

fitting

assembly.

MAIN WHEEL AND BRAKE INSTALLATION CAUTION: Aeroshell Grease 5 SHC 100, and MIL-G-81322 grease are not compatible; DO NOT MIX. If the grease is changed, make certain that all the affected components are thoroughly cleaned before lubrication. To avoid the a.

Apply

an

possibility of mixing incompatible

greases,

use

the

same

grease

throughout

this installation.

coat of grease (9, Chart 2, 32-00-00) or (4, Chart 2, 32-00-00) to the inside diameter of the housing and to the axle prior to installation (Ref. Figure 207).

adequate

inboard brake

the shock strut axle. Ensure that the brake spacer bottoms

Position the inboard brake assembly

c.

Using hydraulic fluid (1, Chart 2, 32-00-00), lubricate the inlet swivel fitting O-rings, the bleeder assembly Orings and the grooves in the inlet swivel fitting and bleeder assembly. Lightly lubricate the surfaces next to the

on

I

the strut.

b.

on

I

grooves. d.

Install the inlet

damage e.

Apply

an

the

fitting and O-rings.

the bleeder

assembly

on

the inboard brake

adequate coat of grease (9, Chart 2, 32-00-00) housing and to the axle.

or

assembly, being

Chart 2,

(4,

32-00-00)

careful not to

displace

or

to the inside diameter of the

outboard brake f.

Position the spacer and the outboard brake assembly on

the g.

the outboard brake with the inlet

Ensure that both brake assemblies

On

are

correctly

seated

on

the

piston

and axle

assembly

and that the

fitting

freely.

airplanes equipped with the brake deice system, install the deice manifold

Connect the

j.

piston and axle assembly. Carefully mate the inlets assembly, being careful not to displace or damage

the

O-rings.

swivels h.

fitting

on

and the bleeder

hydraulic

brake fluid line to the inlet

as

instructed in

Chapter 32-41-00.

fitting.

Pack grease (9, Chart 2, 32-00-00) or (4, Chart 2, 32-00-00) into the bearing cones and smear grease on the ends of the rollers. Spread an adequate coat of bearing grease on the surface of the bearing cups and the lips

of the grease seals. k.

Check the axle and nut for burrs

i.

Apply grease ~9, Chart 2, 32-00-00)

or

rough

threads.

(4,

Chart 2,

or

32-00-00)

washer, spacers and nut. This grease must be identical m.

Install the

n.

Place the wheel and tire

o.

bearing

cone on

the axle. The

on

lips

Install the spacers and washer

on

on

bearing surfaces bearings.

of the

the wheel

of the grease seal must be toward the wheel.

the axle and install the outer

torque while rotating the wheel

to the axle threads and all

to the grease used

bearing

the axle. Place the axle nut

to ensure proper

seating

on

of the

cone

and grease seal.

the axle and

tighten to

150

200

inch-pounds

bearings.

32-40-00Page

213

I

Ral~heon

Aircraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

HYDFIAULIC INLET LINE

FITTING

BRAKE HOUSING

O-RING BLEEDER ASSEMBLY

O-RING

OUTER BEARING CONE SPACERS INNER BEARING CONE

WASHER

NUT

HUBCAP r#2~2

Main Wheels and Brakes

Figure

Apr 28/06Page

214

32-40-00

207

A20

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION: Ascertain that the grease seals the wheel. p.

q.

Back off the axle nut to

Install the cotter

pin.

are

not

damaged and are properly

against

the

bearing

nut to 40

inch-pounds

while

If the holes in the nut and the axle do not

align, tighten

the nut to the next available

zero

torque, then torque the

seated

rotating

cups in

the wheel.

keying

position. r.

Secure the

s.

Repeat steps j through

t.

Bleed the brake system

hubcap

and

gasket r

to the wheel with the three screws.

to install the as

opposite

wheel and tire.

instructed in BLEEDING THE BRAKE SYSTEM.

32-40-00

Apr 28/06Page

215

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BRAKE DEICE WARNING: When

DESCRIPTION AND OPERATION

airplane has experienced abnormal landing gear procedures of any type, as a safety precaution, place the airplane on jacks prior to performing any inspection or maintenance. Ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

CAUTION:

an

airplane for the purpose of landing gear operation, inspection, servicing or maintenance, accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary to jack the airplane in the open, wind velocity in any direction and terrain variations, must be compensated for prior to jacking the airplane.

Jacking

of an

should be

The brake deice system uses hot air to melt ice from the main landing gear wheels (Ref. Figure 1). The hot air flows from each engine compressor through the pneumatic bleed air system to a tee fitting in each main gear wheel well. From there, the hot air flows

through the

the aft side of the

brake deice line to

a

solenoid-operated shutoff valve,

gear strut to

a

then

through a flexible

distributor manifold attached to the

assembly along landing assembly. The distributor manifold consists of two hollow tubes, one on each side into rings. Hot air blows onto the wheels and brakes through orifices located around hose

piston and axle assembly, formed the circumference of each ring. of the brake

The system is controlled by an on-off toggle switch on the pilot’s inboard subpanel. When the switch is in the on position, electrical power is supplied through a 5-amp circuit breaker on the RH circuit breaker panel to a control

module located under the center aisle floorboard

applies

immediately

aft of the cabin forward

partition. The

control module

solenoid-operated deice shutoff valve in each main gear wheel well, allowing hot bleed the distributor manifold and deice the brakes. An internal switch in each shutoff valve then closes,

power to open the

air to flow

through completing a circuit advisory panel.

to illuminate the green LH BK DEICE ON and RH BK DEICE ON annunciators in the cautionl

When the

landing gear is retracted, the LH main gear up-position switch closes, activating a timing circuit in the brake deice control module. If the brake deice control switch is not moved to the off position within 10 minutes, the

timing circuit will the timing circuit

close the deice shutoff valves to avoid

overheating

has closed the valves, the brake deice

system

the components inside the wheel wells. Once again until the landing gear is

cannot be turned on

extended.

32-41-00Page

1

I

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i

L BK DEICE ON

I

R BK DEICE ON

GAUTIONIADVISORY ANNUNCIATOR PANEL

LH ENGINE

RH ENGINE

BLEED AIR

BLEED AIR

BRAKE DEICE CONTROL MODULE

LH

RH

SHUTOFF VALVE

20

2

28

26

1

24

I

I

I

I

I

I

I I

1 I

I I

LH DISTRIBUTION MANIFOLD

I I

SHUTOFF VALVE

RH DISTRIBUTION

MANIFOLD

5 AMP CONTROL

CIRCUIT BREAKER

28VDC

L95A BRAKE DEICE ON DOWN o

OFF

I

I

1

4---1

UP

BRAKE DEICE LINE

BRAKE DEICE

LH MAIN GEAR

CONTROL SWITCH

UP POSITION SWITCH

FU28 06i3W4AAI

Brake Deice

Apr

28106Page

2

32-41-00

System Schematic (System On) Figure 1

A20

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BRAKE DEICE -TROUBLESHOOTING WARNING: When

an airplane precaution, place

has

experienced abnormal landing gear procedures of any type, as a safety airplane on jacks prior to performing any inspection or maintenance. landing gears are down and locked prior to removing the aircraft from

the

Ensure that all three

jacks. CAUTION:

airplane for the purpose of landing gear operation, inspection, servicing or maintenance, accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary to jack the airplane in the open, wind velocity in any direction and terrain variations, must be compensated for prior to jacking the airplane. Jacking

of an

should be

Troubleshoot the brake deice system using Chart 101. Follow the steps in the chart sequentially unless otherwise instructed. For example, proceed to the next step when there are no instructions immediately following a NO condition. Before

using

battery

has

Many faults

a

the

troubleshooting chart, charge of at least 20 vdc.

ensure

that the

auxiliary ground

power unit is set at 28 vdc and that the

be traced to a loose or damaged electrical connection, ensure that all connectors are clean and free Repair or replace any damaged or loose connector pins. Refer to the applicable wiring diagram manual specific pin and plug locations. can

of corrosion. for

WARNING: Never service the accumulator

landing

gear without first

wheel wells, When

jacking the

the

the

the

of the

landing gears,

encountered,

Any time

or

placing

the

and

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart 1, 32-00-00). Stay clear gear doors while the landing gear is in operation.

airplane in an unsheltered area where winds in excess of jack more than one gear clear of the ground at a time.

35 knots may be

never

landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the

with the power

jacks.

a25

32-41-00

Page

beF101

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 101

Troubleshooting STEP 1

Brake Deice

System

YES

Go to

Step

4.

main gear wheel

YES

Go to

Step

7.

Does the system fail to shut off automatically approximately ten minutes after the main gears

YES

Go to Step 10.

YES

Reset the circuit breaker. Go to

Isthe nosegearuplockswitch outof adjustment faulty? Check the circuit for continuity.

YES

Adjust

Does the circuit breaker open again?

YES

Check the circuit for

Does hot air fail to reach both main gear wheel brakes? NO

STEP 2

Does hot air fail to reach

one

brake? NO STEP 3

are

up and locked?

NO The

STEP 4

system is operating normally.

Is the brake deice circuit breaker

open?

Step

6.

NO STEP 5

or

the switch.

replace

or

STEP 6

Repair any STEP 7

Is the solenoid control valve defective? Check the valve circuit for

YES

Replace

YES

Tighten

a

short to

ground.

faults.

the valve.

continuity.

NO STEP 8

Are the bleed air lines

leaking?

or

replace

the lines.

NO

replace

the lines.

STEP 9

Are the bleed air lines blocked?

YES

Clear

STEP 10

Is the time

YES

Replace the time delay PCB.

delay PCB defective? Check the (Ref. Testing the Brake Diece System 32-41-00).

or

PCB

NO STEP 11

Is the left gear up and lock switch out of adjustment or defective? Check the switch

circuit for

Page

beF201

1/09

continuity.

32-41-00

A25

Raldheon

AiKraft

Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

BRAKE DEICE

MAINTENANCE PRACTICES

hydraulically operated landing gear system, be aware that cylinder can displace hydraulic fluid and cause hydraulic any of other movement actuator unanticipated cylinders in the landing gear retraction system. accumulator of the can also result in unanticipated movement Servicing landing gear hydraulic of an actuator. Either action can result in an unsafe, unlocked landing gear system. Therefore, place the airplane on jacks prior to performing any inspection or maintenance. Cycle the landing gear and ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

WARNING: When

performing

maintenance

on a

movement of a

actuator

Never service the accumulator

landing

gear without first

wheel wells,

landing

or

placing

hydraulic system or do maintenance or rigging airplane on jacks (3, chart 1, 32-00-00). Stay clear doors while the landing gear is in operation.

the

the

gears and gear

airplane in an unsheltered area where winds in excess encountered, never jack more than one gear clear of the ground at a time. When

jacking

the

of the of the

of 35 knots may be

Any time the landing gear is only partially retracted during maintenance, always cycle the gear with the power pack through at least one complete cycle before removing the airplane from the jacks. NOTE: Ensure that the two flexible hose assemblies for each brake deice manifold the

same

airplane

supplier.

The Flexfab

when maintenance is

(gray color) performed.

and the Bemco

(red color)

are

of the

same

color and from

hoses must not be mixed

on

any

one

DISTRIBUTOR MANIFOLD REMOVAL

jacks (3,

Chart 1,

a.

Place the

b.

Remove the main

c.

Disconnect the lower brake deice hose

d.

Remove the bolt, washer and nut

e.

airplane

on

landing

gear wheels

32-00-00)

as

instructed in

Chapter

7.

(Ref. Chapter 32-40-00).

assembly

securing

from the

journal

on

the distributor manifold

the manifold top bracket to the hub and axle

(Ref. Figure 201).

assembly.

Remove the bolt, washers and nut securing the static discharger assembly and the manifold support assembly. Remove the static discharger assembly and the manifold.

assembly

to the hub and axle

~ao

32-41-00Page

201

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DISTRIBUTOR MANIFOLD INSTALLATION NOTE: Ensure that the orifices in the distributor manifold

are

clean and unobstructed

prior

to installation of the

manifold. a.

discharger assembly has been removed from its mounting bracket, prepare the mounting surfaces bonding (Ref. Chapter 20-03-00). Secure the static discharger assembly to the bracket with two safety wire (Ref. Figure 201).

If the static

for electrical nuts and

b.

Prepare the mounting surfaces for electrical bonding (Ref. Chapter 20-03-00). Install the manifold support assembly and static discharger assembly on the hub and axle assembly and secure with the attaching bolt, washers and nut.

c.

Secure the manifold top bracket to the hub and axle assembly with the bolt, washer and nut. Install the bolt with its head on the side nearest the torque knee. Seal under the nut, washer, bolt head and top bracket with adhesive can

(10,

Chart 2,

be turned with the

32-00-00), fingers.

then

d.

Connect the lower brake deice hose

e.

Install the main

landing

gear wheels

tighten

the bolt until snug. Do not torque the bolt. Ensure that the washer

assembly to

the

journal

on

the distributor manifold.

(Ref. Chapter 32-40-00).

BRAKE DEICE SHUTOFF VAL VE REMOVAL a.

I

Working inside the main gear whedl well, disconnect the valve. Identify and tag the wires (Ref. Figure 201).

CAUTION: When

two electrical connectors from the brake deice shutoff

disconnecting the bleed air line, upper brake deice hose assembly and removing the shutoff valve, (i.e., do not break the torque paint on) the inlet and outlet fittings installed in the shutoff

do not disturb valve. b.

Disconnect the bleed air line from the inlet side of the shutoff valve.

c.

Disconnect the upper brake deice hose

d.

Remove the nut and washer

securing

valve from the bracket.

Apr

28/0632-41-00

assembly from the

outlet side of the shutoff valve.

the shutoff valve to the firewall

mounting

bracket. Remove the shutoff

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTRICAL CONNECTOR

UPPER BRAKE DEICE HOSE

~o

ASSEMBLY WASHER NUT

~O

BR*KE

U

I

VALVE

it

A

o

FIREWALL

MOUNTING BRACKET

LOWER BRAKE DEICE HOSE ASSEMBLY

BLEED AIR LINE

ELECTRICAL CONNECTOR

+NOTE INSTALL BOLT WITH HEAD TOWARD TORQUE KNEE. SEAL UNDER BOLT HEAD. NUT. WASHER, AND TOP BRACKET WITH EC2216 ADHESIVE.

IW

WASHER BOLT *BOLT

NUTNUT

*TOP BRACKET

5/

´•IWASHER~J

i

/STATIC DISCI´•IAROER

NI

BRACKET

JOURNAL DETAIL

STATIC DISCHAROER ASSEMBLY

A

WASHER

SUPPORT

NUT

ASSEMBLY

(I

HUB AND AXLE ASSEMBLY

UO-2(1112

DISTRIBUTOR MANIFOLD

Brake Deice Distributor and Shutoff Valve

Figure 201

A20

32-41-00

203

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BRAKE DEICE SHUTOFF VALVE INSTALLATION CAUTION: When

connecting the bleed air line, upper brake deice hose assembly and installing the shutoff valve, (i.e., do not break the torque paint on) the inlet and outlet fittings installed in the shutoff

do not disturb valve. a.

Install the shutoff valve

on

the firewall

mounting

bracket

the valve to the bracket with the nut and washer

I

that the FLOW

so

arrow on

the valve

points aft. Secure

(Ref. Figure 201).

b.

Connect the bleed air line to the inlet side of the shutoff valve.

c.

Connect the upper brake deice hose

d.

Connect the two electrical connectors to the shutoff valve.

assembly to

the outlet side of the shutoff valve.

TESTING THE BRAKE DEICE SYSTEM Pressure test and/or functional test the brake deice system when any component is maintenance is performed. a.

Pressure test all

plumbing connections, unions, lines, etc.,

valve to the distributor manifold

as

from each

solenoid-operated

Disconnect and cap the lower brake deice hose assembly at the journal open journal to prevent contamination (Ref. Figure 201).

2.

Disconnect and cap the bleed air line at the brake deice shutoff valve.

3.

Connect

an

air

supply regulated

CAUTION: Leave the

at 80

5.

Apply a fittings.

leak-check solution of mild

6.

Inspect

the connections and

7.

Turn the brake deice, bus tie and

8.

Shut off the

Apr

master

regulated

system

brake deice shutoff

on

the distributor manifold.

Cap the

to the inlet of the brake deice shutoff valve.

on

the wheels when the

air

detergent (1 1,

fittings

Chart 2,

for leaks. No leaks

battery

battery master switch

is turned ON.

as

32-00-00)

are

allowed, except

drop

2.

Turn the brake deice, bus tie and

3.

Turnonthe

regulatedairsupply.

4.

Ensure that

none

32-41-00

minute leak in the valve.

follows:

Remove the caps from the lower brake deice hose assembly and the Connect the hose assembly to the distributor manifold.

battery

on

a

to zero.

1.

of the orifices

and water to the connections and

master switches OFF.

and let the pressure

supply

Functional test the brake deice system

28/06Z;~B

when

switch, bus tie switch and brake deice switch ON.

Turn the

b.

psi

weight of the airplane

4.

battery

or

follows:

1.

I

replaced

journal

on

the distributor manifold.

master switches ON.

the inner surfaces of the distributor manifolds

are

blocked

or

restricted.

~D

Raytheon

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

5.

Turn the brake deice switch OFF, then ON. Ensure that each valve solenoid is functioning properly. Ensure that the green LH and RH BK DEICE ON annunciators extinguish when the system is off and illuminate when the system is

6.

on.

Actuate and hold the LH main gear up-position switch for ten minutes. Ensure that the brake deice system shuts off automatically after ten minutes. Turn the brake deice switch OFF, then ON. Ensure that the brake deice system does not activate. Turn the brake deice switch OFF.

7.

Release the LH main gear

up-position

switch. Turn the brake deice switch ON and

ensure

that the deice

system activates. 8.

Turn the brake deice, bus tie and

9.

Let the pressure drop to zero, then air line to each shutoff valve inlet.

nlo

battery

master switches OFF.

remove

the

regulated

air

supply.

Remove the cap and connect the bleed

32-41-00

Apr 28/06Page

205

Ray~heon

Aircraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOSE STEERING

DESCRIPTION AND OPERATION

WARNING: Place the airplane

on

jacks prior to performing

any

inspection

or

maintenance. After

performing

maintenance of any type on the landing gear system and before releasing the aircraft to service the landing gear must be cycled from the fully extended to fully retracted and back to fully extended at least once,

checking

for proper

operation

and

rigging.

CAU~ION: Jacking of an airplane for the purpose of landing gear operation, inspection, servicing or maintenance, should be accomplished within an enclosed building or hangar. In the interest of safety, should if become necessary to jack the airplane in the open, wind must be compensated for prior to jacking the airplane.

Direct

linkage

of the

nose

to the rudder

pedals

allows the

be increased

nose

velocity in

any direction and terrain variations,

wheel to be turned 14" to the left and 12" to of the wheel brakes while

right.

The deflection

steering pedals. A by engaging the transmission of excessive the loads to shock rudder spring steering linkage dampens the allowed the braked that exceeds control rudder also and or pedals by engaging only permits towing steering pedals. When the nose wheel is retracted, the steering yoke and the attaching bolt rotate, making nose steering inoperative. The steering mechanism is located on the LH side of the nose wheel well. wheel

can

one

with the rudder

mechanism in the forward

32-50-00

Apr

28/06Pagel

Raythwm

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOSE STEERING

MAINTENANCE PRACTICES

performing

hydraulically operated landing gear system, be aware that a hydraulic actuator cylinder can displace hydraulic fluid and cause unanticipated movement of other actuator cylinders in the landing gear retraction system. Servicing of the landing gear hydraulic accumulator can also result in unanticipated movement of an actuator. Either action can result in an unsafe, unlocked landing gear system. Therefore, place the airplane on jacks prior to performing any inspection or maintenance. Cycle the landing gear and ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

WARNING: When

maintenance

on a

any movement of

Never service the accumulator

landing

gear without first

wheel wells, When

landing the

jacking

encountered,

Any time

the

or

placing

hydraulic system or do maintenance or rigging of airplane on jacks (3, chart 1, 32-00-00). Stay clear of doors while the landing gear is in operation.

the

the

gears and gear

airplane in an unsheltered area where winds in excess jack more than one gear clear of the ground at a time.

the

the

of 35 knots may be

never

landing

with the power

gear is

pack through

only partially retracted during maintenance, always cycle the gear at least one complete cycle before removing the airplane from the

jacks. STEERING MECHANISM REMOVAL a.

Turn the

nose

wheel

b.

Working

in the

nose

steering

wheel well,

aft link tubes to the idler c.

Remove the

yoke d.

yoke

from the

mechanism to the full left remove

the two bolts, nuts, washers and cotter

pins securing

the forward and

arm.

attach bolt, washer, nut and cotter

nose

position.

landing

pin from

the

steering yoke (Ref. Figure 201).

Remove the

gear.

Remove the four bolts, washers and nuts securing the remove the forward linkage from the airplane.

steering support bracket to the

LH side of the wheel well

and

securing the forward link tube to the support adjustment of the forward link tube.

Remove the bolt, washers and nut

e.

the support link to allow for later

f.

Remove the floor from the LH side of the

nose

compartment

to

gain

access

link. Remove the link tube from

to the outboard bolt

securing

the

idler shaft to the wheel well structure. g.

Remove the two bolts, nuts and washers

shaft and the idler h.

i.

from the

Remove the

ring

eight

studs

securing

the idler shaft to the wheel well structure. Remove the idler

airplane.

Remove the bolt, washer, nut and cotter rudder pedal torque tube.

boot

,o

arm

securing

pin securing

the boot and boot

and aft link tube from the

the aft link tube to the

ring

nose

steering torque

arm on

to the forward pressure bulkhead. Remove the

the

boot,

airplane.

32-50-00Page

201

I

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STEERING MECHANISM INSTALLATION a.

Move the

b.

Position the

nose

landing

gear to the full left turn

steering support bracket on the

position.

LH

nose

wheel well bulkhead. Secure the bracket with the two short

bolts and washers in the forward holes, and with the two

long bolt,

nuts and four washers in the aft holes

(Ref. Figure 201). c.

Center the

nose landing gear. Lubricate the steering yoke attach bolt with grease (3, Chart 2, 32-00-00) and steering yoke to the nose gear with the attach bolt, washer and nut. Use an AN960-516 or AN916516L washer under the nut as required for proper engagement of the cotter pin. Tighten the nut finger tight, then loosen it to the nearest keying position and install the cotter pin. Ensure the yoke rotates freely on its eye assembly without binding.

secure

d.

the

Position the idler the

bearings

of the idler

arm

between the two

and the idler to

arm

arm.

Install

a

bearings

in the

nose

wheel well structure. Insert the idler shaft

maximum of three 100951X032-XT washers

prevent side play. Secure each end of the idler shaft

to the

as

required

bearings with

a

on

through

either side

bolt, washer and

nut. e.

Secure the aft end of the aft link tube to the torque nut, and cotter pin.

f.

Install the boot and boot

g.

Check the forward link tube for excessive end

(Ref. STEERING LINK

ring

on

arm on

the rudder

the forward pressure bulkhead and

END PLAY

play. If ADJUSTMENT).

the end

play

pedal torque tube with the bolt, washer,

secure

is

more

with the

eight attaching

than.030 inch,

adjust

studs.

the link tube

h.

Install the aft end of the forward link tube to the idler

arm

and

secure

with the bolt, nut, washer and cotter

pin.

i.

Install the forward end of the aft link tube to the idler

arm

and

secure

with the bolt, nut, washer and cotter

pin.

j.

Set the rudder

panel k.

Adjust 1.

2.

the

in the neutral

pedals

under the

pilot’s

length

Loosen the

position and center the nose wheel (aim straight ahead). Open the rig pin in the bellcrank to hold the rudder pedals in neutral.

of the forward link tube

assembly

the

rod end.

jam

access

seat and install the

nut

on

adjustable

as

follows:

length of the link tube assembly by mating the rod end with the support link. Lengthen the link assembly by threading the rod end out of the link tube, or shorten the assembly by threading the rod

Check the tube

end into the tube. 3.

Adjust the length

of the tube until the

nose

wheel remains centered when the rod end is installed

on

the

support link. 4.

Tighten

the

jam

nut to

secure

the rod end.

I.

Secure the link tube to the support link with the bolt, washers and nut. Install the AN960-416 washer under the nut. Install the AN960-616 washer under the link tube fitting.

m.

Ensure that the

n.

Remove the

o.

Lubricate the

Apr

nose

rig pin

wheel is aimed

straight

ahead when the rudder

pedals

are

in the neutral

position.

from the bellcrank.

steering

mechanism with grease

28/0632-50-00

(3,

Chart 2,

32-00-00)

as

instructed in

Chapter

12.

Ra~hwm

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

steering

mechanism

p.

Move the

q.

Install the LH floor of the

nose

through

its entire range of travel to

ensure

there is

no

binding

in the

system.

compartment.

STEERING LINK END PLA YADJUSTMENT a.

Remove the forward link tube

b.

Remove the retainer

Inspect

ring

(Ref.

STEERING MECHANISM

from the link barrel and slide the

the retainer slots in the link barrel for cracks

or

REMOVAL).

spring cartridge

(Ref. Figure 201, Detail C). damage is found, replace the

I

out

distortion. If any such

link

barrel. c.

Ensure that the

d.

Add

a

spring

has

no

breakage

or

stacking. Inspect

the

retaining

nut for

security.

(P/N 1 0095-DD-032WT for the aft end and (P/N 10095-DD-032WK for the forward end) and check play should be 0.030 inch or less without binding. Add washers as required.

washer

for end

play

up to three

between the rod end and the collar. The end

e.

Lubricate the barrel bore and

f.

Slide the

g.

Install the forward link tube

spring cartridge

spring

with grease

into the barrel and

(Ref.

(4,

secure

Chart i,

32-00-00).

with the retainer

STEERING MECHANISM

ring.

INSTALLATION).

32-50-00

I

Apr

28/06Page

203

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

An ROD END

008

RETAINER RING

O00

WASHEREI

(END PLAY) WASHERS

(END PLAY)

C"

A

ATTACH BOLT

BARREL AINER NUT

JAM

NUT

DETAIL

C

Kc/

ADJUSTABLE ROD END

WHEEL WELL STRUCTURE

~ka IDLER ARM

DETAIL

(SIDE PLAY) FORWARD TUBE

A

TORQUE ARM (INSTALLED ON RUDDER PEDAL TORQUE

IDLER SHAFT

dl

On:

I:

Ia.&"

C

PINS ST YOKE ATTACH

BOLT

i

BOLT

Th!

j dS

BOOT

BOOT RING

YOKE

rE’LI

AFT LINK TUBE

~b´•

SUPPORT LINK STEERING SUPPORT BRACKET

DETAIL

B

(ROTATED CLOCKWISE) 350´•351-111

Nose Wheel

Steering

Mechanism and Link

Adjustment

Figure 201

Page

20432-50-00

A20

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POSITION AND WARNING

DESCRIPTION AND OPERATION

an airplane has experienced abnormal landing gear procedures of any type, as a safety precaution, place the airplane on jacks prior to performing any inspection or maintenance. Ensure that all three landing gears are down and locked prior to removing the aircraft from jacks.

WARNING: When

CAUTION:

Jacking of an airplane for the purpose of landing gear operation, inspection, servicing or maintenance, should be accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary tojack the airplane in the open, wind velocity in any direction and terrain variations, must be compensated for prior to jacking the airplane.

Visual indication of

landing gear position is provided by two red in-transit lights, located in the landing gear control pilot’s inboard subpanel, and by a GEAR DOWN indicator light assembly containing three green lamps placarded NOSE L R, located adjacent to the landing gear control switch. In-transit lights illuminate when landing gear is extending or retracting, and extinguish when the gear is up. When the gear is down and locked, the in-transit lights extinguish and GEAR DOWN lights illuminate. To check in-transit lights, press the HDL LT TEST switch located to the right of the landing gear control switch. To check GEAR DOWN lights, press the light assembly case. Power for the in-transit and GEAR DOWN lights is drawn from a 5-ampere LANDING GEAR-IND circuit breaker on the RH circuit breaker panel. The in-transit circuit is completed through the downlock switch on each landing gear drag brace and up-position switch in the upper part of each wheel well. The GEAR DOWN circuit is completed through each drag brace downlock switch. When the landing gear is fully retracted, each landing gear strut actuates its up-position switch to open the circuit and extinguish the in-transit lights (the lights will not extinguish until all three gears are fully retracted). As soon as the landing gear moves from the fully retracted position, each up-position switch actuates to complete the circuit and illuminate the in-transit lights. The lights will remain illuminated until each drag brace moves into the down and locked position, actuating its downlock switch to open the in-transit circuit and complete the GEAR DOWN circuit. In-transit lights will then extinguish and the GEAR DOWN lights will illuminate (Ref. Figure i). switch handle

on

the

NOTE: In order for the

nose

gear-down light

to

illuminate, the

nose

gear actuator downlock switch must also be

actuated.

landing gear aural warning system is provided to warn the pilot when the landing gear is not down and locked during specific flight regimes. If either or both power levers are retarded below 84% to 86% N1, the warning tone will sound intermittently and the in-transit lights will illuminate. If the flaps are in the UP or APPROACH position, the tone can be silenced by pressing the GEAR WARN SILENCE button adjacent to the landing gear control switch; the in-transit lights in the landing gear control switch handle cannot be extinguished. If the warning tone has been silenced, the landing gear warning system will be rearmed when the power lever(s) are advanced sufficiently. With the flaps beyond the APPROACH position, the waming tone and in-transit lights will be activated regardless of the power lever settings, and can only be cancelled by extending the landing gear. To test the landing gear warning system, set the WARN TEST switch on the copilot’s inboard subpanel to the LDG GEAR position. The warning tone will sound and the in-transit lights will illuminate (Ref. Figure 2). A

CAUTION: Never

rely on the safety switch to keep the gear down while taxiing position of the landing gear control switch handle.

or on

landing

or

takeoff roll.

Always

check the

To prevent accidental gear retraction on the ground, the the control circuit when ever the strut is compressed.

~ao

safety

switch

on

the

right

main

landing

32-60-00

gear strut breaks

Apr 28/06Page

f

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

safety switch also actuates a solenoid-latched downlock hook that prevents the landing gear handle from being placed in the UP position when the airplane is on the ground. The hook automatically unlocks when the airplane leaves the ground, but can manually overridden by pressing down on the red button placarded DN LCK REL. The right hand safety switch will ground the in-transit light relay to illuminate the in-transit lights and ground the gear warning PCB to sound the warning tone any time the landing gear control handle is moved to the UP position while the airplane is on the ground with the shock strut compressed.

The RH

Apr

28/06Page

2

32-60-00

A20

Ray~hwm

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

;\L

3

’’,´•~d

I’.

~´•"""J:

i

I,~:x 6$

C"D

LANDING GEAR WARNING TONE

\j/

SWITCHES

P ~"IIIIIII r~SilG

(allllllll~

PEDESTAL

DETAIL

A

~SU

O

O

PI~OT’S INBOARD SUBPANEL

ACTUATOR DOWNLOCK SWITCH.

DETAIL

DOWNLOCK SWIT

B

SAFETY SWITCH

MAIN SPAR

~I

MOUNTING BRACKET MAIN GEAR UP

POSITION SWITCH

DRAG

POSITION SWITCH ’I

1Q’i

DOWNLOCK SWITCH

NOSE LANDING GEAR

DETAIL

MAIN LANDING GEAR

C

DETAIL

D

350-35(-1(6

Landing Gear Position and Warning System

Figure

A20

1

32-60-00

Apr

28106Page

3

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Page

32’60’00

Page Intentionally Left

Blank

A20

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

up 2 Iro

r

I

1

LANDING

POSITION

PUSH TO TEST IN-TRANSIT LIGHTS

DOWN

RH

CB2

o--

LIFT COMPUTER

7>-

3

MAIN GEAR SAFETY SWITCH

up

fir

I

5A

IN-TRANSIT LIGHTS

CBI

LANDING GEAR CONTROL SWITCH

LANDING GEAR WARN TONE

P~75

JI

31

DOWN

28

LANDING GEAR AND STALL WARN TEST SWITCH

FLAP CONTROL SWITCH

GEAR

36 29

INDICATOR

30

r2

P

DOWN

DOWN

I

I

I

I

SP 150

1

I

I

t llK4

34

RH THROTTLE SENSE SWITCH

40

3

44

UP

NOSE GEAR UP-POSITION SWITCH

42

GEAR UPPOSITION SWITCH LH

FLAP IIEnIT SWITCH

43

3

39

GEAR WARN TONE SILENCE SWITCH

5

L

’t-o

45 38

2br

3

4

37

THROTTLE SENSE SWITCH

LH

6~---

5

41

d ´•e

2

r~11

I

2

,3 ;P"

r

I

T

I

5AT

K5

43

6

*6 NOSE GEAR DOWNLOCK SWITCH

LH GEAR DOWNLOCK

A121

RELAY

PANEL

ASSY

SWITCH

4ro

DOWN 6

RH GEAR UP-POSITION SWITCH

3, UP

NOSE GEAR ACTUATOR DOWNLOCK SWITCH

PRESS

TO

I

I

I

I

I

4

8

I

I

1

I

I

I

1

141~

1

I

I

I

1

113

I

I

I

I

5

TEST 3~

NOSE,

I

5;_

LEFT

RIGHT

GEAR DOWN LIGHTS

RH GEAR DOWNLOCK

SWITCH

FLAP CONTROL SWITCH APPROACH POSITION

CLOSES

WHEN

Q

B

GEAR WARNING FLAP LIMIT SWITCH BEYOND THE APPROACH POSITION

SCHEMATIC

SHOWN

IS

IN

THE

UP

WHEN

WITH

POWER

GEAR

ARE

LEVERS

CLOSES

DOWN

WHEN

AND

SET

FLAPS

LOCKED

I

i

11K1

OR

A122

THROTTLE SWITCHES CLOSE BELOW 84% TO 86% NI

NOTE:

SWITCH

I

RELAY

PANEL

EXTEND AUDIO SYSTEMS CONTROL BOX

350-351-115

Landing Gear

Position and

Warning System

Electrical Schematic

Figure

A20

ASSY

WARNING TONE

2

32-60-00

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POSITION AND WARNING

TROUBLESHOOTING

lights, the downlock lights, and the landing gear warning system using Charts troubleshooting charts, ensure that the auxiliary ground power unit is set at 28 VDC using has a charge of at least 20 VDC. battery

Troubleshoot the in-transit the

102. Before

the

Many

101 and

and that

a loose or damaged electrical connection. Ensure that all connectors are clean and Repair or replace any damaged or loose connector pins. Refer to the applicable wiring diagram specific pin and plug locations.

faults

can

be traced to

free of corrosion. manual for

Follow the steps in the troubleshooting charts sequentially unless otherwise instructed. For next step when there are no instructions immediately following a NO condition. WARNING: Never service the accumulator

landing

gear without first

wheel wells, When

landing

jacking

encountered,

the

or

placing

example, proceed

to the

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart 1, 32-00-00). Stay clear of doors while the landing gear is in operation.

the the

gears, end gear

airplane in an unsheltered area where winds in excess jack more than one gear clear of the ground at a time.

the

the

of 35 knots may be

never

Any time the landing gear is only partially retracted during maintenance, always cycle the gear pack through at least one complete cycle before removing the airplane from the jacks. with the power

32-60-00Page

101

RBYtheOn

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 101

TROUBLESHOOTING

Landing STEP 1

Gear

LANDING GEAR POSITION AND WARNING SYSTEM

Warning

Tone Does Not Sound When

Appropriate

tone circuit breaker

YES

Reset the circuit breaker. Go to

Is the landing gear warning circuit malfunctioning? Set the stall warning/landing gear warning switch to LDG GEAR WARN and check the circuit for continuity to the audio

YES

Correct any faults

YES

Adjust

or

replace any defective

YES

Adjust

or

replace

YES

Repair

YES

Check the circuit for

Is the landing open?

gear

warning

Step

6.

NO STEP 2

control box. NO STEP 3

flap adjustment, Are the

or

throttle switches out of

worn,

or

switch.

burned out? NO

STEP 4

Are the downlock switches out of

adjustment,

any defective switch.

worn, or burned out?

NO STEP 5

Troubleshoot the audio control box

instructed in the

supplier

as

or

replace the

box.

manual. Is the box

malfunctioning? NO STEP 6

Does the circuit breaker open

again?

a

short to

ground.

Correct any faults.

Apr

28/06Page

102

32-60-00

A20

Raytheon

Aircraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102

TROUBLESHOOTING

LANDING GEAR IN-TRANSIT AND DOWNLOCK LAMPS

Lamps Do STEP 1

lamps burned out? push-to-test switches.

Are the indicator

pressing

the

Not Illuminate

Check

by

Properly

YES

Replace

the

bulb(s).

NO STEP 2

Is the

landing

gear indicator circuit breaker

YES

Reset the circuit breaker. Check the circuit for

open?

a

short. Correct any faults.

NO STEP 3

the

out of

YES

Adjust

open circuit between the landing gear indicator circuit breaker and the in-transit

YES

Check the circuit for loose

up-position or downlock switches adjustment, worn, or burned out?

Are the

or

replace

switch(es).

NO

STEP 4

Is there

an

or

broken wires.

or

broken wires.

Correct any faults.

lamps? NO STEP 5

A20

open circuit between the landing gear indicator circuit breaker and the geardown lamps? Is there

an

YES

Check the circuit for loose Correct any faults.

32-60-00Page

103

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POSITION AND WARNING WARNING: When

performing

MAINTENANCE PRACTICES

maintenance

hydraulically operated landing gear system, beaware that hydraulic cylinder can displace hydraulic fluid and cause any of other actuator cylinders in the landing gear retraction system, unanticipated movement of the Servicing landing gear hydraulic accumulator can also result in unanticipated movement of an actuator. Either action can result in an unsafe, unlocked landing gear system. Therefore, place the airplane on jacks prior to performing any inspection or maintenance. Cycle the landing gear and ensure that all three landing gears are down and locked prior to removing the aircraft from jacks. on a

movement of a

actuator

Place the airplane

on jacks prior to performing any inspection or maintenance. After performing maintenance of any type on the landing gear system and before releasing the aircraft to service the landing gear must be cycled from the fully extended to fully retracted and back to fully

extended at least once,

checking

for proper

operation

and

rigging.

operation of the downlock and up-position switches installed on all three landing gear. (14, Chart 1, 32-00-00) to test the nose gear actuator downlock switch the nose gear brace and the switch, up-position switches. Use TK1763-5/935 test box (15, Chart 1, 32-00-00) to test the main drag switches the safety switches. Schematics and materials required to build the test circuits are and downlock gear shown in Figures 201 and 203. Use

a

test circuit to check the

Use the TK1763-2/95 test box

WARNING: Never service the accumulator

landing

gear without first

wheel wells,

landing

or

placing

the

hydraulic system or do maintenance or rigging of airplane on jacks (3, Chart 1, 32-00-00). Stay clear of doors while the landing gear is in operation,

the

gears, and gear

airplane in an unsheltered area where winds in excess encountered, never jack more than one gear clear of the ground at a time. When

jacking

the

the the

of 35 knots may be

Any time the landing gear is only partially retracted during maintenance, always cycle the gear with the power pack through at least one complete cycle before removing the airplane from the jacks. NOSE GEAR DRAG BRACE DOWNLOCK SWITCH ADJUSTMENT CAUTION: While

adjusting the drag brace downlock switch,

the emergency extension hand pump, TK 229/939 the equivalent to retract or extend the landing gear instructed in LANDING GEAR RIGGING IN CHAPTER 32-30-00.

TK229-/935 pump,

or

as

(5

or

use

6 Chart 1, 32-00-00),

or

NOTE: Before

attempting any adjustment of the switch, the landing gear must be rigged correctly as instructed in Chapter 32-30-00. When the landing gear is rigged correctly and the nose gear downlock switches are adjusted correctly, the drag brace downlock switch will actuate before the actuator downlock switch actuates.

a.

Place the

b.

Disable the

c.

Disconnect the to the

airplane

on

landing

jacks (3, Chart 1, 32-00-00)

gear doors

by disconnecting

as

the

instructed in

actuating

Chapter

7.

cams.

drag brace downlock switch connector and the actuator downlock switch applicable TK1763-2/935 test box connectors shown in Figure 201.

d.

The green NOSE ACT and locked position.

e.

Position the

lights

adjustable stop

on

the test box should illuminate

with

approximately 0.25

as

the actuator

inch of threads

exposed

piston

as

connector and connect

is extended to the down

shown in

Figure

32-60-00

202.

Apr 28/06Page

201

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

that the head of the

f.

Install the switch

g.

Secure the switch with the

h.

Set the switch

i.

Turn the indicate

so

(S1)

on

locking

adjusting

nuts and

safety

bolt contacts the

plunger,

wire.

the test box to DRAG LEG.

adjusting bolt out until the green lights on the test box illuminate. continuity after connecting the wire leads to pins D and F. adjusting

but does not compress it.

bolt out two additional full turns

(0.071 inch)

If

using

an

ohmmeter, it should

for switch overtravel.

j.

Turn the

k.

hand pump, cycle the gear to unlock and back to lock while monitoring the lights on the test box. Adjust bolt the stop as required to ensure that the drag brace downlock lights (green) on the test box illuminate before the actuator downlock lights (green) illuminate. If using two ohmmeters, connect the wire leads to pins B and C on the actuator downlock switch connector. The ohmmeter connected to the drag brace switch connector should

Using the

indicate open before the ohmmeter connected to the actuator switch connector. NOTE: The to

i.

nose

gear downlock switches must actuate in the proper sequence to allow the downlock indicator to allow the pump motor on the hydraulic power pack to shut off correctly.

As the gear is cycled to unlock, the red indicate an open circuit.

NOTE: Excessive m.

compression

Disconnect the test box

Page

lights

operate and

or

or

lights

bottoming

on

the test box should illuminate. If

out of the switch

plunger

may

cause

using

damage

an

ohmmeter, it should

to the switch.

the oh mmeters from the switch connectors and install the connectors in the ai rplane.

20232-60-00

n20

Ray~heon

nircrart

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONNECTORS

NOSE GEAR POSITION SWITCH TEST BOX NOSE

ACTO

O

O

O

DS6

DS2

DS5

DS1

DRAG LEG

FRONT PANEL

O

O

O

O

DSB

054

DS7

DS3

(4x5x. 185)

ALUMINVM

UP LOCK J1

I

C NOSE ACT

BATTERY

DS1 DS5 DS2 DS6 P1

NOSE GEAR ACTUATOR DOWNLOCK CONNECTOR

DRAG LEG

E

B

DS3

A P2

DS7

DRAG LEG DOWNLOCK CONNECTOR

DS4

S1

F

DS8 UP LOCK

C

_j

CON ECTORUP POSITION SWITCH TK1763-2-935 TEST BOX

LIST OF MATERIALS DESIGNATOR

QUANTITY

S1 DS5-DS8 DS1-DS4 P1 6 82 J1

2 1 1 4 4 2 1 1

ITEM DESCRIPTION BATTERY "D" SIZE, DRY CELL, WIRED IN PARALLEL BATTERY HOLDER KEYSTONE TYPE #2176 SWITCH ALCO MST405N LAMP HOLDER (GREEN) MS 25256-4 AND GE #331 LAMP LAMP HOLDER (880) MS 25256-6 AND GE #331 LAMP SOCKET- MS3121E10-6S CONNECTOR- MS3122E-12-10S CABINET- BUD #CU-2105B (5x4x3) 22 AWG WIRE WITH PROTECTIVE SLEEVING (8 FT)

FL32B 985218MAI

Nose Gear Downlock and

UP-Position Figure 201

A20

Switch Test Circuit

32-60-00Page

203

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psig of regulated dry air to pressurize the power pack reservoir during ground operation of the power pack

assembly. five

Chapter 32-30-00. When cycling the landing gear with cooling period between cycles and a five minute cooling period after

Connect the air source as instructed in

the power pack, allow a

one

minute

cycles.

n.

Cycle the gear and check for proper ope ration of the GEAR DOWN light, located on the pilot’s and the landing gear warning tone. Operate the gear through at least one complete cycle.

o.

Connect the

landing gear

doors to the

actuating

cams

and

remove

the

airplane from

the

inboard

subpanel,

jacks.

NOSE GEAR ACTUA TOR DOWNLOCK SWITCH REPLACEMENT The actuator downlock switch is actuator and

preadjusted.

If the switch must be

repeat the landing gear rigging procedure

as

replaced for any reason, replace Chapter 32-30-00.

UP-POSITION SWITCH ADJUSTMENT (NOSE AND MAIN Before

adjusting

the

position switch,

the

landing

gear must be

GEAR)

rigged correctly

as

instructed in

adjusting the up-position switch, use the emergency hand pump, hydraulic pump (5 or 6 Chart i, 32-00-00), or the equivalent to retract instructed in LANDING GEAR RIGGING in Chapter 32-30-00.

CAUTION: While

a.

b.

Place the

airplane

Disable the

on

jacks (3,

landing gear

doors

Chart 1,

32-00-00)

by disconnecting

as

the entire

instructed in

instructed in

them from the

Chapter

actuating

Chapter

32-30-00.

a

TK229/939

or

or

extend the

TK229-1/939

landing

gear

as

7.

cams.

Safety

wire the doors in the

open position. c.

Ensure that the

landing gear is fully

d.

Disconnect switch connector and install it

e.

Set the switch

f.

Loosen the

(S1)

on

retracted before on

the

adjusting

the switch.

applicable plug on TK1763-2/935 test

box shown in

Figure

201.

the test box to UPLOCK.

locking nut that holds the switch in position. Adjust the switch so that the green lights on the test box using an ohmmeter, it should indicate continuity when the wire leads are connected to pins A and C.

illuminate. If

nose gear up-position switch, turn the adjusting nut an additional two turns and secure the switch with the locking nuts and safety wire.

(0.083 inch)

for overtravel

g.

On the

h.

On the main gear up-position switches, turn the adjusting nut an additional two to five turns (0.083 inch to 0.21 inch) for overtravel. This adjustment will expose 0.30 to 0.15 inch of the switch plunger when the landing gear is

fully

retracted. Secure the switch with the

NOTE: Excessive i.

compression

Disconnect the test box

or

or

bottoming

locking

nuts and

out of the switch

safety

plunger

wire.

may

cause

damage

to the switch.

the ohmmeter from the switch connector and install the connector in the

airplane.

CAUTION: To prevent serious

damage to the pump, never operate the power pack without supplying 18 to 20 psig regulated dry air to pressurize the power pack reservoir during ground operation of the power pack assembly. Connect the air source as instructed in Chapter 32-30-00. When cycling the landing gear with the power pack, allow a one minute cooling period between cycles and a five minute cooling period after five cycles. of

Apr

28/06Page

204

32-60-00

aso

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

j.

Check for proper operation of the in-transit gear through at least one complete cycle.

k.

Connect the

landing

gear doors to the

lights

actuating

located in the

cams

and

gear control switch handle.

landing

remove

the

airplane

li~lADJUSTABLE

from the

Operate

the

jacks.

STOP

.25 INCH

LOCK NUTS

NOSE GEAR DRAG BRACE ASSEMBLY

SWITCH

(80~212-1

Nose Gear

Drag

Brace Downlock Switch

Figure

Adjustment

202

MAIN GEAR DOWNLOCK SWITCH ADJUSTMENT Before

adjusting

the downlock switch, the

landing

gear must be

rigged correctly

as

instructed in

Chapter 32-30-00.

adjusting the downlock switch, use the emergency hand pump, TK229/939 or TK229-1/939 hydraulic pump (5 or 6 Chart i, 32-00-00), or the equivalent to retract or extend the landing gear as

CAUTION: While

instructed in LANDING GEAR RIGGING in a.

b.

Place the

Disable the

open c.

~ao

on

jacks (3, Chart 1, 32-00-00)

landing gear position.

doors

by disconnecting

as

instructed in

them from the

Disconnect the switch connector and connect it to the

Figure d.

airplane

Chapter 32-30-00.

Chapter

actuating

7.

cams.

applicable TK1763-5/935

Safety wire

the doors in the

test box connector

as

shown in

203.

Ensure that the

landing gear

is down and locked.

32-60-00Page

205

RBl~heMI

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

e.

Loosen the locknut

on

the switch and back the switch out to the

point

that the

is contacted, but not

plunger

compressed. f.

Adjust the switch until the green lights on the test box illuminate. continuity when the wire leads are connected to pins T and D.

g.

Turn the

adjusting

NOTE: Excessive

nut three additional full turns

compression

or

bottoming

(0.125 inch)

out of the switch

using

an

ohmmeter, it should indicate

for switch overtravel.

plunger

may

cause

damage

to the switch.

h.

Secure the switch with the

locking

i.

Disconnect the test box

the ohmmeter from the switch connector and install the connector in the

or

nuts and

If

safety

wire.

airplane.

CAUTION: To prevent serious damage to the pump, never operate the power pack without supplying 18 to 20 psig of regulated dry air to pressurize the power pack reservoir during ground operation of the power pack

assembly.

Connect the air source

the power pack, allow a

five

j.

Operate and the

k.

28/06Page

206

instructed in Chapter 32-30-00. When cycling the landing gear with cooling period between cycles and a five minute cooling period after

as

minute

cycles.

the gear through at least one landing gear warning horn.

Connect the

Apr

one

landing

gear doors to the

32-60-00

complete cycle and check for proper operation of the GEAR DOWN light

actuating

cams, and remove the

airplane from

the

jacks.

RByRleon

AiKraft

tompany

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

MAIN GEAR SWITCH TEST BOX

oDOWN OSll

U)CK

O

SSAW~

DS12

00000 057

DS6

OS9

DSB

DS10’~

FRONTPANEL(4xSx3) ALUMINUM

00000 DSt

DS2

DS4

DS3

DS5

J2

~--_I

SAFETY SWITCH CONNECTOR

V

W~

I

I

I

Z

J1~1

I

1

I

I

I

I

I

1

I

MAIN GEAR

DS7

I DSs

DS1

D

I

BATTERY

DS12

DSI1

WWNLOCK LIGHTS

DOWNLOCK SWITCH CONNECTOR

I

L--l

DSB

L---~

DS9

I

IDS10

SAFETY SWITCH LIGHTS

DS3

DS2

DS4

DS5

E

i

JK TK1763-5/935 TEST BOX LIST OF MATERIALS

DESIGNATOR

DS6-DS12 DS1-DSS J2 J1

QUANTITY 2 f 7 5 1 1 1

ITEM DECRIPTION BATTERY "D" SIZE, DRY CELL, WIRED IN PARALLEL BATTERY HOLDER KEYSTONE TYPE #2176 LAMP HOLDER (RED) MS25256-6 AND GE #331 LAMP LAMP HOLDER (GREEN) MS25256-4 AND GE #331 LAMP CONNECTOR MS3474L16-26S CONNECTOR MS3474L14-19S CABINET BUD CU-2105B (5 x 4 x 3) 22 AWG WIRE WITH PROTECTIVE SLEEVING (8 FT) FLpB OBYIIAL.

Safety Figure 203

Main Gear Downlock and

A20

Switch Test Circuit

32-60-00

Apr 28/06Page

207

Raylheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAIN GEAR SAFEN SWITCH ADJUSTMENT This

to both the RH and LH

procedure is applicable

jacks (3,

a.

Place the

b.

Deflate the shock strut

c.

Remove the

retaining

airplane

on

safety

Chart 1,

32-00-00)

instructed in

as

safety

Chapter

switch actuator rod from the

as

switches.

instructed in

Chapter 7.

All tires must be clear of the floor.

12-10-00.

attaching bracket on the (Ref. Figure 204).

upper torque knee, then

remove

the

nut and the switch arm from the switch shaft

cycle the landing gear with the power pack if low on fluid or if the landing gear system is not properly rigged. Use the emergency extension hand pump to extend and retract the landing gear for maintenance and rigging.

CAUTION: Do not

NOTE: Use

a

gear-type puller obtained locally

to remove the switch arm from the switch shaft to

prevent damage

to the internal mechanism of the switch.

d. e.

Jack the

g.

connector

on

safety switches) continuity.

or

Install the switch

align

if

using

arm on

with the

an

j.

Remove the

bracket

fully

from the

T and S

landing

LH

(for

position.

wiring

to the

both RH and LH

gear wheel well.

until the red

lights

of the test

on

a position parallel to the upper torque knee and adjust the actuator the torque knee. Install the actuator rod connecting bolt.

extended

locking

position.

screw on

The red test

the switch

lights

arm

should remain illuminated.

and back off the

locking

screw.

that it is 2 inches from the

fully extended position. At some point between 0.75 and fully position, lights will extinguish and the green test lights will illuminate. Adjust the switch shaft counterclockwise (same for both RH or LH installations) at the adjusting screw until the green lights illuminate and the red lights extinguish within the above limits. If using an ohmmeter, turn the adjusting screw counterclockwise until the ohmmeter indicates an open circuit. When satisfactory adjustment is reached, tighten the locking screw and retaining nut. so

2.00 inches from the

I.

or

pins

of each main

extended

the switch shaft in

Lower the shock strut to the

Position the shock strut

for both the RH

ohmmeter, until it indicates

attaching

safety wire

(same

rear

thefully

Connect the switch

Rotate the switch shaft clockwise

i.

1

(Ref. Figure 204). (Ref. Figure 203).

switch

the TK1763-5/935 test box

ohmmeter to

rod to

k.

safety

0.38 to 0.62 inch from

If not using the test box, connect the wire leads from an installations) of the receptacle plug located in the upper

box illuminate, h.

compressed from

Disconnect the electrical connector from the

applicable f.

the shock strut is

landing gear so

Before 1.

safety wiring

Compress

extended

the

locking

screw

to the switch arm, recheck the

continuously

as

position

switch

rigging

as

follows:

lights will extinguish and the green lights illuminate when the using an ohmmeter, it will indicate an open circuit compressed to the fully compressed position.

as

the shock strut is

shock

in step k. If

Extend the shock strut from the

fully compressed position. The green test lights should remain illuminated position 0.38 to 0.62 inch from full extension. At this position the green light will extinguish and the red lights will illuminate. If using an ohmmeter, it will indicate an open circuit until the strut reaches 0.38 to 0.62 inch from full extension, then will indicate continuity from there to full extension. until the strut reaches

NOTE: The

point

a

at which the switch is actuated

during compression and extension of linkage on the landing gear.

because of tolerances in the switch and its attendant

Page

safety

the shock strut. The red test

strut reaches the same

2.

the red test

20832-60-00

the shock strut differs

Raythwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

m.

n.

Safety wire

the

locking

Disconnect the test box

screw

or

to the switch arm.

the ohmmeter from the

switch and reconnect the

safety

safety switch

to the

airplane

power connector. o.

Inflate the shock strut

as

instructed in

Chapter

12-10-00.

LH STRUT

LA SWITCH ARM

\j

,L’

SWITCH

RETAINING NUT

LOCKING SCREW

ADJUSTING SCREW

J~fACTUATOR

(UNDERSIDE)

hi G

,Q

ROD

T

UPPER TOROUE KNEE

NVT

WASHER

CO

300202-8

Main Gear

A20

Safety Switch Adjustment Figure 204

32-60-00

Apr 28/06Page

209

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POWER LEVER SENSE SWITCH ADJUSTMENT

(LANDING

GEAR

WARNING)

Cam-operated switches are installed on brackets on a pedestal structure. If either power lever is retarded below a safe flight setting when the gear is not down and locked, a cam installed on the power lever linkage will close the throttle sense switch and sound a warning tone intermittently. The airplane must be in flight when determining the position of the power levers that corresponds to 84% to 86% N1 (gas generator speed), because ram air effect will cause the lever position to differ from the position observed during ground operation. in

advance the power levers until 84% to 86%

a.

With the

b.

Mark the

c.

Remove the lower

d.

Place the power levers in

e.

Adjust the landing in this position.

f.

Move the power levers and listen for

g.

Remove the tape and install the

h.

Flight

airplane

flight,

position of the

on

the

upholstery panels from alignment

pedestal

with the

with

an

with

a

both sides of the

tape

gear warning horn switches

airplane N1.

test the

84% to 86%

power levers

on

the

by moving

piece

N1

is attained

of tape. Land the

on

each

engine.

airplane.

pedestal.

pedestal. them in their slotted

audible click when the power levers

mounting

are

brackets to

just actuate

moved aft of the tape.

pedestal upholstery.

landing

gear retracted and the power levers retarded until

warning

horn sounds at

FLAP LANDING GEAR WARNING SWITCH ADJUSTMENT

(FL9P APPROACH DOWNLIMITAND

LANDING GEAR WARNING

CAM)

landing gear warning switch is a cam-operated switch mounted on the back of the RH aft wing spar with the flap limit switches. The adjustment cam is accessed through a door forward of the RH inboard flap. Adjustment

The

procedures downlimit

Apr

28/06Page

210

are

cam

Chapter 27-50-00, FLAP CONTROL SYSTEM RIGGING. properly adjusted, the landing gear warning switch is also adjusted.

described in

is

32-60-00

When the

flap approach

nna

Raytheon

nircraft Campany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

/PEDESTAL

ed

It LANOING GEAA WARNIWG POWER LEVER SWITCHES

1

’‘C~

STRUCTURE MOUNTING BRACKETS

POWERLEVER~ CAM

-FY~r\

DETAIL

A DETAIL

Landing

Gear

Warning

350-1585

Power Lever Switch

Figure

A20

B Adjustment

205

32160100

211

CHAPTER

LIGHTS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 33 - LIGHTS TABLE OF CONTENTS SUBJECT

PAGE 33-00-00

Lights Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 33-10-00 Flight Compartment - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Annunciator Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Instrument Indirect Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Side Panel Lights and Overhead Floodlights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Flight and Gyro Instrument Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Overhead, Subpanel and Console Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Engine Instrument Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Flight Compartment - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Edgelighted Panel Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Edgelighted Panel Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Etched Circuit Board Edgelights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Printed Circuit Board (PCB) Repair Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Printed Circuit Board Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Printed Circuit Board - Conformal Coating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Annunciator Lamp Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Master Caution/Warning Lights Lamp Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Engine Fire F/W Valve Switch Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Engine Fire Extinguisher Switch Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Control Wheel Map Light Replacement (Not Applicable to FL-711 and After; FM-37 and After) . . . . . . . . . .210 Instrument Indirect Lights Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Landing Gear Control Handle Lights Lamp replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Magnetic Compass Light Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Overhead Floodlights Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 33-20-00 Passenger Compartment - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Reading Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Entry and Loading Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Vestibule, Aft Compartment Lights and Exit Signs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Lighting Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .4 Passenger Compartment - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 No Smoking/Fasten Seat Belts Light Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Cabin Fluorescent Light Tube Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Reading, Table, Vestibule and Baggage Compartment Lights Lamp Replacement . . . . . . . . . . . . . . . . . . . .202 Step Lights Lamp Replacement (Optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Exit Sign Light Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Spar Light Tube Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Threshold Light Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206

A28

33-CONTENTS

Page 1 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 33 - LIGHTS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE

Handle Position Observation Light Lamp replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Door Hook Observation Light Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Exterior Entry Light Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Assembly and Potting of High Voltage Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

208 208 210 210

33-40-00 Exterior - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Anti-Collision Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Recognition Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Tail Floodlights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Landing and Taxi Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Navigation Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Wing Ice Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 Exterior - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Wing Tip Light Assembly Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Wing Tip Light Assembly Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Wing Tip Strobe/Aft Navigation Lights Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Forward Wing Tip Navigation Light Lamp Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Wing Tip Recognition Light Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Tail Strobe Light Flashtube and Socket Assembly Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Tail Navigation Light Lamps Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 206 Wing Ice Light Lamps Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 206 Landing Light Lamps Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 207 Taxi Light Lamps Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 207 Focusing the Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 209 Anti-Collision (Flashing Beacon) Light Lamps Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 209 Tail Floodlight Lamps Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 211 Strobe Power Supplies Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 211 33-50-00 Emergency Lighting - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Emergency Lighting - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Self-Illuminated Exit Sign Brightness Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

Page 2 May 1/10

33-CONTENTS

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

33-LOEP

1

May 1/10

33-CONTENTS

1 and 2

May 1/10

33-00-00

1 and 2

Mar 9/01

33-10-00

1 thru 7 201 thru 214

Feb 1/09 May 1/10

33-20-00

1 thru 7 201 thru 210

Feb 1/09 Feb 1/09

33-40-00

1 thru 7 201 thru 213

Oct 31/06 Oct 31/06

33-50-00

1 and 2

Mar 9/01

A28

33-LOEP

Page 1 May 1/10

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

LIGHTS DESCRIPTION AND OPERATION This on

chapter contains airplane.

all

lighting systems

and

sub-systems required

for both interior and exterior illumination used

the

SPECIAL TOOLS AND RECOMMENDED MATERIALS

Special tools are listed in Chart 1 and recommended materials are listed in Chart 2. Those listed as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Raytheon Aircraft Company. The products included in these charts have been tested and approved for aviation usage by Raytheon Aircraft Company, by supplier or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of specification may by used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to using the product listed. This can be done by contacting the supplier of the product to be used.

CHART1 SPECIAL TOOLS Tool Name

1.T-light Comparator

Part Number

CAN/DB/45-1

Use

Supplier Self-Lighting, Inc., 169 Western Highway W. Nyack, NY 10994 Ph. 1-800-777-9399

checking illuminated sign brightness. For

or

914-353-0235

nll

33-00-00Pagel

Ral~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CHARTP

RECOMMENDED MATERIALS MATERIAL 1.

Coating

SPECIFICATION MIL-I-46058

PRODUCT Conothane CE-1155

SUPPLIER

Conap Inc., 1405 Buffalo St.

Olean, NY 14706 2.

Coating

MIL-I-46058

Conothane CE-1164

Conap Inc., 1405 Buffalo St.

Olean, NY 14706 3.

Solvent

Product S8

Conap Inc., 1405 Buffalo St.

Olean, NY 14706 4.

Battery

Alkaline NEDA 14a

Conap Inc., 1405 Buffalo St.

Olean, NY 14706 5.

Adhesive

EA-901

Conap Inc., 1405 Buffalo St.

Olean, NY 14706 6.

Sealant

EC1239B1/2

Minnesota

Mining

and

Mfg. Co.,

3M Center

St. Paul, MN. 55101 7.

Sealant

Pro-Seal 89081/2

Coast Paint and Chemical

Company

1507 Grande Vista Ave.

Los 8.

Liquid

Mar

9/0133-00-00

detergent,non-abrasive

Lux, Joy

Angeles,

Obtain

CA. 90023

locally

I

A12

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FLIGHT COMPARTMENT

DESCRIPTION AND OPERATION

ANNUNCIA TOR LIGHTS The annunciator

lights

consist of the

lights associated with the central warning system described in Chapter lights include a warning annunciator panel (with red readout) centrally located in the annunciator panel (caution-yellow, advisory-green, status-white) located glareshield, and a caution/advisory/status below the center of the instrument panel. Adjacent to the warning annunciator panel on the glareshield is a pressto-test switch to test the annunciator lights and the pilot’s and copilot’s red warning and yellow caution flashers. 31-50-00. The annunciator

INSTRUMENT INDIRECT LIGHTS The instrument indirect

lights

consist of ten

lamps mounted under the glareshield to illuminate the instrument panel. in-flight operation, lights are powered from the triple fed bus through the INSTR INDIRECT circuit breaker (Ref. Figure 1) located on the right hand circuit breaker panel. The lights can be dimmed through the INSTR INDIRECT potentiometer located on the overhead control panel. In normal

the instrument indirect

Four of the instrument indireci

also be controlled by the INSTRUMENT EMERGENCY LIGHTS switch panel. Emergency power is furnished through the ENTRY LIGHTS circuit breaker located on the fuel control panel. The power source can be either the hot battery bus or the triple fed bus through the FUEL PANEL circuit breaker located on the main power distribution panel. located

on

lights

can

the overhead instrument

SIDE PANEL LIGHTS AND OVERHEAD FLOODLIGHTS

panel lights and the overhead floodlights are powered from the R GEN bus t~rough the SIDE PANEL circuit (Ref. Figure 2) located on the right hand circuit breaker panel. Power to the overhead floodlights is direct from the dimmer control. Power to the side panel lights is switched through the MASTER PANEL LIGHTS switch located on the overhead control panel. The side breaker

The dimness of the

pilot

COPILOT OVHD FLOOD

and copilot overhead floodlights is controlled through potentiometers located on the overhead control panel.

the PILOT OVHD FLOOD and

The side

panel lights can be dimmed through the SIDE PANEL potentiometer located on the overhead control panel. panel lights include the right hand circuit breaker panel edgelight, the upper and lower fuel panel edgelights lights which illuminate the fuel quantity gages.

The side and the

FLIGHT AND GYRO INSTRUMENT LIGHTS The

flight and gyro instrument lights are powered from the L GEN bus through the FLIGHT INSTR circuit breaker (Ref. Figure 3) located on the right hand circuit breaker panel. The lights are switched through the MASTER PANEL LIGHTS switch located on the overhead control panel.

The

instrument installations, the turn and

indicator

flight lights consist of the various flight lights as determined by the light and the lights in the control wheels. Dimness of the lights FLIGHT INSTR potentiometers located on the overhead control panel.

is controlled

The gyro lights control panel.

n25

can

be dimmed

by

the PILOT and COPILOT GYRO INSTR

by

slip

the PILOT and COPILOT

potentiometers located

on

the overhead

33-1 0-00Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OVERHEAD, SUBPANEL AND CONSOLE LIGHTS lights are powered from the R GEN bus through the SUB PNL OVHD (Ref. Figure 4) located on the right hand circuit breaker panel. Power is switched to the MASTER PANEL LIGHTS switch located on the overhead control panel. The lights can be dimmed by the lights by SUBPANEL potentiometer located on the overhead control panel. Lights controlled by this system the OVHD FED include edgelights on the overhead control panel, overhead instrument panel, pedestal switch panel, landing gear extension handle, engine control panel, and on the subpanels. In addition, the system controls the magnetic compass light, the instruments on the overhead instrument panel, the instruments on the pedestal/console, and various avionics lights as determined by the particular airplane equipment.

The overhead,

subpanel

and console

CONSOLE circuit breaker

ENGINE INSTRUMENT LIGHTS

engine instrument lights are powered from the L GEN bus through the AVIONICS ENG circuit breaker (Ref. Figure 5) located on the right hand circuit breaker panel. The lights are switched through the MASTER PANEL LIGHTS switch located on the overhead control panel. Dimness of the radio control panel lights and the edgelight on the glareshield placard is controlled through the AVIONICS PANEL potentiometer located on the overhead control panel. Dimness of the engine instrument lights is controlled through the ENGINE INSTR potentiometer located on the overhead control panel. An engine instrument light power supply located on the AC power distribution panel supplies 0 to 5 vdc to th~ engine instrument lights located on the pilot’s instrument panel.

The

Feb

1/09Page

2

33-1 0-00

aae

Hawker Beechcraft SUPER KING AIR B300/B300C

10

A

OVERHEAD

CONTROL

Corporation

F31AINTENANCE

MANUAL

PANEL

INSTR INDIRECT DIM&

V

i IIYLCJOI;S~I

TRIPLE FED

I

BUS A146 RH BREAKER

OFF

LIGHT _h SENSOR

I

I I I

I I

AMBIENT LIGHT SENSOR

INSTR INDIRECT DIM CONTROL

CIRCUIT PANEL

A125 ANNUNCIATOR CONTROL PCB

DS A133 OVERHEAD INSTRUMENT PANEL

ENTRY LIGHTS

a 5~

I/

I

I

I

I

DS

5

DS

7

DS

9

OS

A124 FUEL CONTROL PANEL

I

FUEL PANEL FEEDER NO 2

A145TRIPLEMAIN POWERPANEL FED

3

OFF

INSTRUMENT EMERGENCY I LIGHTS SW

BATTERY BUS

DS

DN

BUS

DISTRIBUTION

I

L k105

10

DS

8

DS

b

DS

4

DS

2

GLARESHIELD 360-603-100

Instrument Indirect

Lights Schematic Figure 1

ORIGINAL BY

A25

As Received AIP

33-1 0-00

Page

3

Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A110

OVERHEAD

CONTROL

PANEL

Al

R6 ON

5A R

GEN BUS

A146 RH BREAKER

d

SIDE PANEL CIRCIJIT PANEL

R26

SIDE PANEL DIM CONTROL

´•r 06

MASTER PANEL LIGHTS SI

I

LIGHT SENSOR

L_

IT1

R9

R29

PILOT OVERHEAD FLOOD DIM CONTROL

09

RI I

R31

COPILOT OVERHEAD 011

L___~i

FLOOD DIM CONTROL

DS197 PILOT OVERHEAD FLOODLIGI-1T

AMBIENT LIGHT

SENSOR

OVHDLIGHTSFL000 A125 ANNUNCIATOR CONTROL PCB

DS197 PILOT OVERHEAD FLOODLIGHT

OS124 UPPER FUEL PANEL EDGELIGHT

DS234 R CIRCUIT BREAKER PANEL EDGELIGHT

OS3

DS4

DS 1 23

PANEL

A124

FUEL

CONTROL

PANEL

L.OWER FUEL EOGELIGHT

ASSY sao-sos-lol

Side Panel

Lights

and Overhead

Figure

Page

4

Feb 1/09

c

Floodlights Schematic

2

ORIGINA’L

33I10I00

As Received By ATP

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A110

OVERHEAD

CONTROL

PANEL

Al R4

FLIGHT INSTR L

GEN BUS

ON

7.5A

CIRCUII PANEL

COPILOT GYRO INSTR DIM CONTROL

04

MASTER PANEL LIGHTS SI

A146 RH BREAKER

R24

LIGHT SENSOR

L_

R2

R22

COPILOT FLIGHT INSTR DIM CONTROL

02 L_

R3

R23

PILOT GYRO INSIR DIM CONTROL

03 L_

RI

Fi21

PILOT FLIGHT INSTR DIM CONTROL

01 L_

AMBIENT LIGHT SENSOR

PILOT

FLIGHT

LIGHTS

M139II\IDICATORTURN&

-----l

Flight

and

Gyro

PILOT

CONTROL

PILOT

GYRO

SLIP

PILOT FLIGHT LIGHTS A125 ANNUNCIATOR CONTROL PCB

WHEEL

LIGHTS

COPILOT

FLIGHT

COPILOT

CONTROL

COPILOT

GYRO

LIGHTS WHEEL

LIGHTS 3BO-~03-IM

Instrument

Figure

Lights

C

Schematic

3

ORIGINAL, As

A25

Recelved~ By: AfP

33I10I00

Page

5

Feb 1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A110

OVERHEAD

SUBPNL OVHO& CONSOLE

CONTROL

PANEL R8

R28

ON 08 Al

a

I’

7.5

R

A146

GEN BUS RH

CIRCUIT

01

BREAKER PANEL DS215

LIGHT SENSOR

MASTER SI PANEL LIGHTS

MAG

OVHD FED SUBPANEL DIM CONTROL

COMPASS´•LAMP

CR3

L_

DS167 OVERHEAD INSTR EDGELIGHT

DS250 OVERHEAD CONT EDGE LIGHT

VIONICS

AMBIENT LIGHT SENSOR A125

ANNUNCIATOR PCB

CONTROL A230

PEDESTAL/CONSOLE

A133 OVERHEAD INSTRUMENT PANEL E

22 CABIN PRESSURE

SW

7_"

ONTROLLER 1 M4

D~ICE

M2

AMMETER

DS225 I I

I

VOLTMETER

I

I

I

I/

I

PEDESTAL PANEL Ai13 ENG CONT EDGELIGHT

LOG

GEAR EXTENSION HANDLE EDGELIGHT

ITBi23

B FLAP POSITION INDICATOR

M114

R.LOADMETER

+I

I

I

i

R.LOADMETER

M128 DIFF PRESSURE INDICATOR

M129 RATE OF CLIMB INDICATOR

L___---------------------------_--J

A220 M2

A245

PROP

I

M3

DS245 FED PNL EDGELIGHT

SUBPANEL

DS220 R INBDI EDGELIGHT

T

DS223 L INBDI i EDGELIGHT

I

ASSY R OUTED EDGELIGHT

IDS222

1DS22 I L OUTED EDGELIGHT 1

:3~0-603-103

C

L_

Overhead, Subpanel

and Console

Figure

Page

beF6

1/09

33-1 0-00

Lights

Schematic

4

As Received ATP

BLORrGINA

A25

Hawker Beechcraft Corporation SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A136 COCKPIT INSTRUMENT PANEL A110

AVIONICS&I

I

ENG_ INSTR/

I

OVERHEAD

CONTROL

PANEL

ON

R7

ENG TURBINE TACH R

AVIONICS PANEL DIM CONTROL

I

I

I M1O3

R27 ENG OIL TEMP &PRESS R

ISI ,GEN A146

07

eus RH

LIGWT SEI\ISOR

DIM

CIRCUIT BREAKER PANEL

I

I

I

M107

Al

L---

ILIGHTS

R

OFF

ENG

r--I------------’ M1O5 RADIO

PANEL

LIGHTS

Mi13 GLARESHIELD PLACARD EDGELIGHT

I

ENG TURBINE GAS TEMP R

I

ENG PROP TACH R

MIOI

RFUELENG

L_

ENGINE INSTR DIM CONTROL

nIM OFF

MI I I

FLOW

Fi5

M116

I

I

tC~--J

I

r---------

POT

I

I

I

r

w

M;-;O

I

28vDC

ENG

PROP M1O0

TO

L ENG FUEL FLOW

L

POT

o

ENG PROP SYNCHRO SCOPE

5VDC

TACH

L

M;1(2

PSI ENGINE INSTR LIGHT POWER SUPPLY

AMBIENT LIGHT SENSOR

L_______

A263 AC POWER DISTRIBUTION PANEL

I

A1~5 ANNUNCIATOR CONTROL PCB

I

I

M104

I

ENG

GASTURBINETEMP ENG TOROUE PRESS

L ENG OIL TEMP

I

PRESS

M1O6

ENG TURBINE TACH

L

M1O2

L_______________~

350-~03-104

Engine

C

Instrument

Lights Schematic Figure 5

ORIGINAL A25

As Received By ATP

33I10I00

Feb

1/09Page

7

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

FLIGHT COMPARTMENT - MAINTENANCE PRACTICES EDGELIGHTED PANEL ASSEMBLIES The edgelighted panel assemblies consist of an outer plastic panel and a printed circuit board to which wheat lights are soldered (Ref. Figure 201). These panel assemblies are mounted strategically throughout the crew compartment to identify the function and mode of the various switches and systems. The inscriptions on the outer, counterbored, plastic panel of the edgelighted assemblies are illuminated by wheat light lamps soldered in parallel to a printed circuit board and powered by 28 vdc. Due to the fact that edgelighted panels can be damaged by inappropriate maintenance practices and contamination, usually moisture resulting from spills or storm windows left open in moist environments, they must be removed and visually inspected at the interval specified in Chapter 5-00-00.

Edgelight Replacement Figure 201

A28

33-10-00

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EDGELIGHTED PANEL INSPECTION a. Disconnect the airplane power. b. Remove any switch or rheostat knobs that may interfere with the removal of the panel assemblies. c.

Remove the attaching screws (Ref. Figure 201) and lift the edgelighted panel away from the structure.

NOTE: Exercise care not to scratch or damage the panel assemblies. d. Inspect the outer, plastic panel for cracking, scratches, etc. If damaged, the plastic panel must be replaced. Refer to the appropriate Hawker Beechcraft Parts Catalog for the component part numbers. e. Inspect the printed circuit board for delamination, cracks, abrasions, arcing, and discoloration. If any damage of the type noted in this step is found, the PCB must be replaced. f.

Utilizing a regulated 28-vdc power source, check the wheat lights to make sure proper illumination of all the lamps. All lamps that fail to illuminate properly must be replaced and the PCB cleaned and recoated as outlined in PRINTED CIRCUIT BOARD (PCB) REPAIR PROCEDURES.

g. If no damage is found, no further action is required and the panel may be replaced.

ETCHED CIRCUIT BOARD EDGELIGHTS Switch identification letters on the different panel sections are illuminated at night by edgelights. An edgelight is an etched circuit board (Ref. Figure 201) with several lamps soldered to the etched circuit. An edgelight is seated in the individual panel sections. The solder position of each lamp after installation must align with its respective cover indentation to allow the etched circuit edgelight to seat properly in its cover panel. The different edgelighted panel sections can be tested by the applicable potentiometer on the overhead control panel. If the print in a particular panel area is not lighted or is dim in contrast to other edgelights, the defective lamps should be replaced as follows: a. Remove the panel mounting screws and clips. b. Remove the panel. c.

Remove the screws holding the etched circuit edgelight in the panel.

d. Separate the etched circuit edgelight from the panel. e. Unsolder the defective lamps. Solder the new lamps in place. f.

Assemble the edgelight in the panel.

PRINTED CIRCUIT BOARD (PCB) REPAIR PROCEDURES Because of the bonded type construction of the board, repair of the PCB assembly is limited to replacement or repair of the wheat light lamps. The following steps should be observed when replacement or repair of a lamp (or lamps) becomes necessary. a. Utilizing a low wattage soldering iron, heat the solder holding each of the lamp leads to the PCB (Ref. Figure 202). As the solder begins to soften, lift the lead away from its mounting pad.

Page 202 May 1/10

33-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL CAUTION: The lamp mounting pads and leads may lift away from the board if excessive heat is applied to the solder attaching the lamp leads to the mounting pads. If this occurs, the PCB must be replaced. b. Solder the new wheat light lamp to the appropriate pads on the PCB. Do not apply excessive solder to the assembly, and make sure that each connection has a good fillet between the pad and the lead. The contour of each lamp lead should be visible in the solder. c.

After completing repairs, check that all lamps match the counterbores in the outer plastic panel.

d. Connect a regulated 28-vdc power source to the PCB and make sure that all lamps illuminate. When normal panel function is attained, the panel must be cleaned and a conformal coating applied before final assembly. PRINTED CIRCUIT BOARD CLEANING a. Immerse the entire PCB in a container of isopropyl alcohol. NOTE: The PCB may be lightly scrubbed with a soft bristled brush as necessary to remove stubborn contaminants. b. Make sure that all traces of flux and other contaminants are washed away. c.

Remove the PCB from the container and rinse it by pouring clean isopropyl alcohol over the panel assembly.

d. Immediately after rinsing, place the assembly in a vertical position (to draw off any residual moisture) and allow to dry. NOTE: After cleaning, care must be exercised to prevent contamination of the PCB through handling or from the environment. All traces of oil, moisture or any other contaminants must be kept away from the PCB. Clean, lint-free, white gloves or clean rubber gloves must be worn at all times during and after the cleaning of a PCB assembly. PRINTED CIRCUIT BOARD - CONFORMAL COATING a. As soon as possible after the PCB is fully dry, the conformal coating should be applied. The coating must completely cover the side of the PCB on which the light lamps are installed. NOTE: Hawker Beechcraft Corporation (HBC) recommends Conothane CE1155 or CE1164 (Item No. 1, Chart 2, 33-00-00 or Item No. 2, Chart 2, 33-00-00) thinned 25% with Product S8 (Item No. 3, Chart 2, 33-00-00). CE1155 is a two part product and should be mixed in a ratio of 10 parts of component “A” to 7 parts component “B” by weight. CE1155 is the preferred coating agent; however, any coating that conforms to MIL-I-46058 may be used. b. The coating may be applied by dipping, brush or spray. Whichever coating method is used, care must be taken to avoid getting any coating in the area of the electrical connector. After application, the coating must be cured as recommended in the manufacturer’s instructions. c.

Inspect the coating for complete coverage, fisheyes, bubbles, dry spots, peeling, blisters, wrinkles, and cracks. If any coating defects are found, the panel must be recleaned and recoated.

d. When the conformal coating has been satisfactorily applied and cured, the edgelighted panel may be reassembled and installed. Replace any knobs that were removed and reconnect the airplane power.

A28

33-10-00

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Edgelighted Panel Printed Circuit Board Repair Figure 202

Page 204 May 1/10

33-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ANNUNCIATOR LAMP REPLACEMENT a. Remove all electrical power from the airplane. CAUTION: Failure to remove power from the airplane prior to removing or installing annunciator legends could result in an arc that could damage an annunciator printed circuit board. b. Push in on the legend plate (Ref. Figure 203). It should pop out when released, but will be retained by a wire clip. NOTE: Pull on the legend plate with fingers only. Damage to the legend plate may occur if tools such as pliers are used for removal. c.

Swivel the legend plate to gain access to the lamps.

d. Extract both lamps from the lamp holder with fingers or a small screwdriver. Always replace the lamps as a set. e. Install the new lamps. f.

Make sure that the top of the lamp holder and the legend plate are facing up.

g. Slide the lamp holder into the annunciator panel and push on the legend plate until the lamp holder snaps into place. h. Restore electrical power to the airplane. i.

Check for illumination of the new lamps by pressing the test switch located adjacent to the warning annunciator panel.

1. DEPRESS LEFT SIDE OF INDICATOR PANEL TO ROTATE IN DIRECTION SHOWN.

2. PULL BULB FROM REAR OF INDICATOR PANEL.

FA33B 985404AA.AI

Annunciator Lamp Replacement Figure 203

A28

33-10-00

Page 205 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MASTER CAUTION/WARNING LIGHTS LAMP REPLACEMENT a. Remove all electrical power from the airplane. CAUTION: Failure to remove power from the airplane prior to removing or installing annunciator legends could result in an arc that could damage an annunciator printed circuit board. b. Grasp the finger grips on the side of the legend face and pull outward to remove the lamp holder (Ref. Figure 204). Damage to the legend face can occur if tools, such as pliers or channel locks, are used to remove the legend face. c.

Extract lamps from the unit by using a finger nail or small screwdriver blade. It is recommended that all lamps in a given cap be replaced at the same time, regardless of the number of lamps burned out. This will make sure that all lamps in the cap have approximately the same service life in the future.

NOTE: Be certain that the correct replacement lamp is used. The lamp number can usually be obtained from the base of the lamp itself, or check the LAMP REPLACEMENT GUIDE in this chapter. Visually inspect the new lamp for quality manufacture. Lamps should be discarded if the glass envelope is distorted or not aligned with the lamp base. d. To reinsert the cap assembly into the base of the unit, it is necessary to "cock" the cap prior to insertion into the base assembly. This is done by pulling the two halves of the cap assembly apart until the unit snaps into a locked, extended position. This usually has already occurred when the cap was removed from the base assembly; however, it can snap back to the closed position when the lamps are being replaced. e. With the cap ready to install, check for proper orientation by looking into the base assembly for any indexing lugs, and match them to the index grooves in the base of the cap assembly. Install the cap with a firm action. The cap should snap into the base and be positively locked into position. Check the unit for proper operation and restore power to the system.

Master Caution/Warning Lights Lamp Replacement Figure 204

Page 206 May 1/10

33-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 LAMP REPLACEMENT GUIDE - FLIGHT COMPARTMENT LOCATION Glareshield Indirect Lamps

REF. DES A105DS1 thru A105DS10

Landing Gear Control Handle Lamps A100DS1, A100DS2

PART NO. 1864 327

Master Warning Lamps

A105DS15DS1 thru A105DS15DS4 387 A105DS16DS1 thru A105DS16DS4

Master Caution Lamp

A105DS17DS1 thru A105DS17DS4 387 A105DS18DS1 thru A105DS18DS4

Engine Control Edgelight

A113

D158-100-5

Fuel Quantity Indicator Light Tray

A124DS3, A124DS4

6838

Engine Fire Ext. Sw. Lamp

A161S1DS1 thru A161S1DS4 A162S1DS1 thru A161S1DS4

MS25327-327

Firewall Shutoff Sw. Lamp

A163S1DS1 thru A163S1DS4 A164S1DS1 thru A164S1DS4

MS25327-327

Clock Edgelight

A211A1DS1, A212A1DS1

D158-100-5

Map Light (Not applicable to FL-711 and After; and FM-37 and After)

A211DS1, A212DS1

MS25069-1495

Lower Fuel Panel Edgelight

A124DS123

D158-100-5

Upper Fuel Panel Edgelight

A124DS124

D158-100-5

Overhead Flood Lights

DS197, DS198

303

Magnetic Compass Light

DS215

327

R Inboard Subpanel Edgelight

DS220

D158-100-5

L Outboard Subpanel Edgelight

DS221

D158-100-5

R Outboard Subpanel Edgelight

DS222

D158-100-5

L Inboard Subpanel Edgelight

DS223

D158-100-5

Glareshield Placard Edgelight

DS224

D158-100-5

R CB Panel Edgelight

DS234

D158-100-5

Pedestal Sw. Panel Edgelight

DS245

D158-100-5

Ovhd. Cont. Edgelight

DS250

D158-100-5

Cabin Press Cont. Lights

E122DS1, E122DS2

327

A28

33-10-00

Page 207 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE FIRE F/W VALVE SWITCH LAMP REPLACEMENT a. Remove all electrical power from the airplane. CAUTION: Failure to disconnect the battery from the hot battery bus before lamp removal may result in accidental closing of the firewall valves. b. Remove the copper safety wire from the clear plastic guard (Ref. Figure 205). Flip the clear plastic guard up, grasp the finger grips on the sides of the legend face, and pull outward. c.

While fully extended, rotate the legend face 1/4 turn in either direction.

d. Push in on the legend face to release the lamp holder tabs from their slots. e. Pull the lamp holder out and swivel it down to access the lamps. f.

Remove colored boots from the lamps as required.

g. Extract the four lamps from the lamp holder with fingers or a small screwdriver. Always replace the lamps as a set. h. Install the new lamps. i.

Install any colored boots previously removed.

j.

Fully extend the legend face to engage the tab cam.

k.

Retract the tabs with the tab cam by rotating the legend face 1/4 turn in either direction.

l.

Once the tabs are retracted, swivel the lamp holder up and slide it all the way into the switch body.

NOTE: Install the legend face with the nomenclature facing upright. The lamp holder will not seat properly if the legend face is inverted. m. Extend the tabs by rotating the legend face 1/4 turn. The lamp holder will lock into place as the tabs extend. n. Push the legend face into the switch body until it clicks. An audible click indicates that the legend face has locked in place. o. Safety wire the clear plastic guard closed with 30-SF copper safety wire. p. Restore electrical power to the airplane.

ENGINE FIRE EXTINGUISHER SWITCH LAMP REPLACEMENT a. Remove all electrical power from the airplane. CAUTION: Failure to disconnect the battery from the hot battery bus before lamp removal may result in accidental discharge of the fire extinguishers. b. Remove the copper safety wire from the clear plastic guard (Ref. Figure 206). Flip the clear plastic guard up, grasp the finger grips on the sides of the legend face, and pull outward. c.

Extract the four lamps from the lamp holder with fingers or a small screwdriver. Always replace the lamps as a set.

Page 208 May 1/10

33-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL d. Install the new lamps. e. To reinsert the cap assembly into the base of the unit, it is necessary to "cock" the cap prior to insertion into the base assembly. This is done by pulling the two halves of the cap assembly apart until the unit snaps into a locked, extended position. This usually has already occurred when the cap was removed from the base assembly; however, it can snap back to the closed position when the lamps are being replaced. f.

With the cap ready to install, check for proper orientation by looking into the base assembly for any indexing lugs, and match them to the index grooves in the base of the cap assembly. Install the cap with a firm action. The cap should snap into the base and be positively locked into position. Check the unit for proper operation and restore power to the system.

g. Safety wire the clear plastic guard closed with 30-SF copper safety wire. h. Restore electrical power to the airplane.

Engine Fire F/W Valve Switch Lamp Replacement Figure 205

A28

33-10-00

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Fire Extinguisher Switch Lamp Replacement Figure 206

CONTROL WHEEL MAP LIGHT REPLACEMENT (NOT APPLICABLE TO FL-711 AND AFTER; FM-37 AND AFTER) a. Remove all electrical power from the airplane. b. Remove the two screws in the center piece of the control wheel (Ref. Figure 207). c.

Remove the map light lamp from the lamp holder in the interior of the control wheel.

d. Insert a new map light lamp. e. Replace the two screws in the center piece of the control wheel. f.

Restore electrical power to the airplane.

INSTRUMENT INDIRECT LIGHTS LAMP REPLACEMENT a. Remove all electrical power from the airplane. b. Locate the faulty lamp under the glareshield (Ref. Figure 208). c.

Remove the lamp from its socket and replace with a new lamp.

d. Restore electrical power to the airplane.

Page 210 May 1/10

33-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONTROL WHEEL

BULB

A 1. REMOVE TWO SCREWS IN CENTER PIECE. SCREW

2. REMOVE MAP LIGHT FROM INTERIOR. 3. UNSOLDER WHEAT LIGHT, AND RESOLDER REPLACEMENT.

DETAIL

A FA33B 985406AA.AI

Control Wheel Map Light Lamp Replacement (Not applicable to FL-711 and After; and FM-37 and After) Figure 207

GLARESHIELD

BULB 1. LOCATE FAULTY BULB UNDER GLARESHIELD. 2. REMOVE BULB FROM SOCKET. FA33B 985405AA.AI

Instrument Indirect Lights Lamp Replacement Figure 208

A28

33-10-00

Page 211 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LANDING GEAR CONTROL HANDLE LIGHTS LAMP REPLACEMENT a. Remove all electrical power from the airplane. b. Unscrew the retainer from the knob assembly and remove the defective lamp (Ref. Figure 209). c.

Install a new lamp in the knob assembly.

d. Screw the retainer back on the knob assembly. e. Restore electrical power to the airplane.

MAGNETIC COMPASS LIGHT LAMP REPLACEMENT a. Remove all electrical power from the airplane. b. Swivel the shield over the lamp upward and remove the defective lamp (Ref. Figure 210). c.

Install a new lamp in the knob assembly.

d. Swivel the shield down over the lamp. e. Restore electrical power to the airplane.

OVERHEAD FLOODLIGHTS LAMP REPLACEMENT a. Remove all electrical power from the airplane. b. Pull the lens and lens holder out of the light assembly (Ref. Figure 211). c.

Remove the old lamp and insert a new lamp.

d. Insert the lens and lens holder in the light assembly and push it into place. e. Restore electrical power to the airplane.

Page 212 May 1/10

33-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Landing Gear Control Handle Lights Lamp Replacement Figure 209

SHIELD

LAMP

1. SWING SHIELD UP. 2. REMOVE LAMP. FA33B 985407AA.AI

Magnetic Compass Light Lamp Replacement Figure 210

A28

33-10-00

Page 213 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Overhead Floodlights Lamp Replacement Figure 211

Page 214 May 1/10

33-10-00

A28

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

PASSENGER COMPARTMENT

DESCRIPTION AND OPERATION

READING LIGHTS The passenger compartment reading lights (Ref. Figure 1) are powered from the R GEN bus through the READING circuit breaker located on the right hand circuit breaker panel. Each of the eight reading lights are controlled by an individual

switch located in the sidewall armrest. There

light

are

four table

lights

controlled

by individual

pressure

actuated switches.

ENTRYAND LOADING LIGHTS The entry and loading lights (Ref. Figure 2) are powered from the hot battery bus or from the the FUEL PANEL FEEDER NO.2 located on the main power distribution panel. Both sources

triple fed bus through supply power through the ENTRY LIGHTS circuit breaker located on the fuel control panel. Two cabin door observer lights are controlled by a single push-on, push-off switch. When the cabin door is open, power is provided to the exterior entry light to illuminate the ground in front of the cabin door. When the cabin door is open and the left seat riser threshold switch is closed, power is provided to the seat-riser threshold light, the three step lights, and the two spar light tubes. None of these lights will illuminate when the cabin door is locked. A

momentary-push

switch is

provided adjacent

to the cabin door to illuminate the

handle-position

When any of the cabin door switches are not closed, a red DOOR UNLOCKED signal is annunciator panel when external power or generator power is applied to the airplane.

observer

displayed

on

the

light. warning

VESTIBULE, AFT COMPARTMENT LIGHTS AND EXIT SIGNS The vestibule, aft NO SMK FSB control

panel

compartment lights and exit signs (Ref. Figure 3)

BAGGAGE circuit breaker

in the

The two overhead

during

normal

operation.

are

powered

from the L GEN bus

The NO SMK FSB/FSB switch

on

through the

the overhead

flight compartment controls the power to the three no-smoke/fasten-seat-belts signs lights in the aft compartment are illuminated by closing the switch in the headliner.

in the cabin.

The aft

baggage compartment lights can also be controlled by the aft baggage compartment light switch. Power is provided through the ENTRY LIGHTS circuit breaker located on the fuel control panel. In normal operation, the ENTRY LIGHTS circuit breaker is fed by the triple fed bus from the FUEL PANEL FEEDER NO.2 circuit breaker located on the main power distribution panel. The ENTRY LIGHTS circuit breaker is also fed by the hot battery bus for operation of the aft baggage compartment lights when there is no power on the triple fed bus. The two emergency exit signs in this airplane are located in the center aisle headliner adjacent to the cabin door and emergency exit hatches. During normal operation, they are powered by the airplane electrical system. During

emergency power off conditions, they are self-activating and internally powered by four "C" size dry batteries located in each unit. A three-position rocker switch, labeled ON-TEST, OFF-RESET, allows for testing of each unit before and

during maintenance by momentarily selecting the ON-TEST position. The switch should be placed in the position and then in the center position before flight. In the center position, an internal inertia switch illuminate the light if 1.5 g’s are sustained for more than 1/30th of one second.

flight

OFF-RESET will

NOTE:

Exit

sign

batteries should be checked at interval

specified in Chapter 5-00-00. Replace the batteries (Item 33-00-00) specified in Chapter 5-11-00. The lamps must also be checked on an annual basis as they may become loose over a period of time. To prevent lamp loosening, make a small slippage mark between the lamp and holder. The paint will hold the lamp and still allow fast replacement if required. No. 4, Chart 2,

n25

at interval

33-20-00

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

READING

A520

R GEN BUS A146 RH BREAKER

CIRCUIT PANEL

I

CABIN

HEADLINER

I

I

I LIGHT

DS31 FWD

NO

DS33

NO

TABLE SW

READING

I

LT A281

SWITCH

I

I LIGHT

NO

ASSY

TABLE

1

FWD~ DS35 FWD

28VDC GND GND

3

READING 1

A283

28VDC GND GNI!

SWITCH

ASSY

LEFT LIGHT DS~7

NO

READING

1

AFT, NO

I

TABLE SW

LT

A285

SWITCH

LIGHT

NO

3

READING

1

A287

NO

DS~4

NO

2

TABLE SW

READING

LT

I A282

2

I

I

READING

I

I A284

RIGHT

NO

2

READING

I

TABLE SW

LT A286

_

DS40

NO

2

28VDC GND GND

SWITCH

I LIGHT

READING

I

I

AFT

NOTE:

ASSY

ASSY

TABLE I

4

ASSY

28VDC GND GND

SWITCH

LIGHT DS38 AFT

28VDC GND GND

SWITCH

LIGHT 4

ASSY

TABLE

FWD, DS36NO FWD

28VDC GND GND

SWITCH

LIGHT DS32 FWD

ASSY

TABLE

1

I DS41 AFT

28VDC GND FND

A288

THE TABLE LIGHT SWITCHES ARE SHOWN WITH THE TABLES STOWED.

28VDC GND GND

SWITCH

ASSY

FL33B 08524877

Reading Lights Schematic Figure 1

Page

beF2

1/09

33-20-00

A25 ATP

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

DOOR _L

ENTRY LIGHTS

5"

1

i

S

DOOR

OPEN DOOR

BATTERY BUS

DOOR

CLOSE

SI

S227 CABIN DOOR ENTRY LT CUTOFF A124 FUEL CONTROL PANEL

I

I

II

FUEL PANEL FEEDER I´•JO 2

UNLOCKED

I

o

1S301 IHOOK

I

S302 AFT FWD HOOK SW SW

I I

I I

I I

I

IDS207 UPPER STEP LT I

A145 MAIN POWER DIS~RUBUTION PANEL

I

I

I

I

IDS208

FED

LT

DSI

TRIPLEI 6USI

20"’

OS260 CABIN OBSERVATION FWD

A202 SEAT RISER THRESHOLD LT LEFT

II

I

L7

5307 CABIN DOOR HOOK OBSERVER SW

83 CABIN DOOR LATCH SENSE o

DS260 CABIN OBSERVATION AFT

5185 HANDLE POSITION SENSE SW

CENTER STEP LT

DS209 LOWER STEP LT

CABIN DOOR OPEN SIGNAL

I I

I

5184 OBS LT SW

I I

I I

Ai25 ANNUNCIATOR CONTROL PCB

DS203 HANDLE POSITION OBSERVATION LT

I I

L______________J

A186

CABIN

AIRSTAIR

DOOR

DS201 FWD SPAR LIGHT TUBE

OSI 18 EXTERIOR ENTRY iT

DS202 AFT SPAR LIGHT TUBE

3ao-60s-los

Entry

A25

and

ORIGINAL By

As Received ATP

c

Loading Schematic Figure 2

33-20-00

Page3 Feb 1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

LIGHTING PANELS are powered from the triple fed bus through the CABIN LIGHTS circuit right hand circuit breaker panel. The lighting panels are controlled through the CABIN LIGHTS BRIGHT/DIM/OFF switch located on the overhead control panel. When the CABIN LIGHTS switch is set to BRIGHT, relay K1 is energized, allowing power to flow to power supplies PS1 through PS6 located in the cabin lighting panel. The light tubes in the cabin, vestibule and baggage headliners are then illuminated.

The cabin

lighting panels (Ref. Figure 4)

breaker located

I

the

on

On FL-I thru FL-8l,the aft and After, all

lights

baggage indirect lights together.

controlled

are

by

a

switch

just

aft of the cabin door. On FL-82

illuminate

NOTE: When passenger oxygen pressure activates the passenger oxygen-pressure- sense switch (Ref. Chapter 35-00-00), 28 vdc is applied to energize K1 regardless of the position of the CABIN LIGHTS

switch. This enables the passengers to When the CABIN LIGHTS switch is set to

PS1 the

PS4 and illuminate the

through light tubes

light

clearly

see

DIM, relay K1 is de-energized, allowing power

tubes in the cabin headliner. The two aft

EL LIGHT PANELS circuit

dimming touch switch installed operation of the dimming touch switch

the

to flow to power

light tubes

supplies

in the cabin headliner,

baggage compartment headliner will not be energized, allowing power from the AC TEST breaker on the ac power distribution and stall warning computer panel to flow to in the cabin headliner. The cabin headliner light tubes can then be dimmed by

in the vestibule headliner and the

light

tubes in the

illuminated when the CABIN LIGHTS switch is set to DIM.

JACK

their oxygen masks.

Relay

K2 is

in the headliner.

Chart 1

Lamp Replacement Guide

Sign Lamp Tray

Fasten Seat Belt Threshold Exit

Lamp Tray

Lamp

Sign Lamp

Fluorescent

Light

Tubes

PART NO.

REF. DES

LOCATION

No Smoke

Passenger Compartment

A107DS1,A108DS1, A1OSDS1

1202-300

A107DS1, A108DS1, Al 09DS1

1202-300

A202DS1

MS252314-313

A520A1DS1,A521A1DS1 A520A1DS2, A520A1DS3 A521 A1DS2, A521A1DS3

425

A520DS1 thru A520DS30

PW-3500-D10

56NG5-0137

A521DS1 thru A521DS4

123.2 E-A

A522DS1 thru A522DS8

D-A,

ReadingTTable Lamps

A520DS31 thru A520DS42

1495)(

Vestibule

A521DS5

1495)(

Baggage Compt. Lamps

A520DS11,A522DS512

1495>(

Exterior

Entry Lamp

DS118

MS24513-4174

Tubes

DS201

Lamp

Spar Light

Handle Position Obsv.

Lamp

1864

DS207 thru DS209

1864

E122DS1, E1220S2

327

Page

beF4

1/09

Lamps

33-20-00

J-A

TT1 003-SMOKE-2-EP-M P-TVLN

DS203

Step Lamps Cabin Door OBSV.

DS202

or

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NO SMK 5A

LEFT GEN BUS

NO FSB

8

FSB

(FASTEN SEAT BELT)

SMK BAGGAGE

DS2

I

A146 RH CIRCUIT BREAKER PANEL

I

I Ds~

S2

I

I

DS2

"G"

FSB

F~110 OVERHEAD CONTROL PANEL

I

I

T

I r

I

I

I-

I

(NO SMOKE)

SWITCH

DS1 I c

I

I

I

I

I

I

I

t

DSL A109

SIGN ASSY-CABIN ORDINANCE FWD

S1

SWITCHTEST K1 DS12

(FASTEN SEAT BELT)

R) )I(R

Al A520

SIGN ASSY-EXIT HEADLINER

DSll

ASSEMBLY-CABIN

I

I

I

I

I

I

S1

~--113

DS2

6

1

S2

CR4 CRiS

2

(NO SMOKE) CI/

IIC

DSj

I

DS2

T

I

I

IIIII

I

Iltn

r:

CR2

_L

1

S2

"G"

I I

I

IblDSI

CR 1

A1OP

SIGN ASSY-CABIN ORDINANCE FWD

SWITCH S1

DSI

DS5

DIODE

Al A522

sl

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

ASSY

HEADLINER ASSEMBLY-COMPARTMENT AFT BAGGAGE

(FASTEN SEAT SWITCH TEST

K1

I

I

S181 AFT COMPARTMENT BAGGAGE LT.

Al 6521

SIGN ASSY-EXIT ASSEMBLY-VESTIBULE

I

I

I

I

I

I

I

I

I

I

I I

I

I

DS2

5A

(No SMOKE)

I

I BATTERY BUS

FUEL PFlNEL FEEDER N0.2

ENTRY LIGHTS

2_00 TRIPLE ENTRY LIGHTS

FED BUS

A124 FUEL CONTROL PANEL

DS1 A109

SIGN ASSY-CABIN ORDINANCE FWD 350-603-107

A145 MAIN POWER DISTRIBUTION PANEL

Vestibule, Aft Compartment Lights Exit

A25

and

Schematic

Signs Figure

3

33-20-00

Page

5

Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

This

Page

33120100

Page Intentionally

Left Blank

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

150

TRIPLE FED BUS

CABIN LIGHTS

3A

BRIGHT

AC EL

DIM

OFF

TEST JACK LIGHTS PANEL

K2

I

I

I

I

I

I

I

I

I

I

A263 AC POWER STALL WARNING

I

DIST. AND COMPUTER PANEL

S8 CABIN LIGHTS +28VDC A110

OVERHEAD

CONTROL PANEL

S209 PASS. OXYGEN PRESSURE SENSE SWITCH (CH 35-20-00)

K1U T

I

I o

S181 AFT COMPT BAGGAGE LT. SW.

I

I

I

I I I I I

I I I

A520

CABIN HERDLINER

28VDC POT

GND

PS 1

I I I I

I

DS1

´•DS~

DS5

DS7

DSP

DS11

DS1~

28VDC POT

GND

PS2

I I I I

I

DS2

DS4

DS6

DSs

DSIO

DS12

DS14

I I I I

I

DS 15

DS17

DS1P

DS21

DS23

DS25

DS27

28VDC

I

I

I

GND

I

I

I

28VDC

~---1 GND

28VDC POT GND

PS3

DIMMER CONTROL

SP DIMMING TOUCH SW-

28VDC POT GND

PS4

DS 16

DS18

DS2D

DS29

DSI

DS30

DS2

DS22

DS24

DS26

DS28

DS3

DS1

DS~

DS5

DS7

DS4

DS2

DS4

DS6

DS8

El

28VDC POT

GND

PSS

I I

´•I

28VDC POT

GND

PS6

I

A519 CABIN LIGHTING PANEL

A521

VESTIBULE

HEADLINER

A522

35~603-108

BAGGAGE

HEADLINER

Lighting

Panels Schematic

Figure

A25

4

33-20-00

Feb

1/09Page

7

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

PASSENGER COMPARTMENT

MAINTENANCE PRACTICES

NO SMOKING/FASTEN SEA T EEL TS LIGHT REPLACEMENT a.

Remove electrical power from the

b.

Snap

c.

Remove the two

d.

Disconnect electrical

e.

Replace

off the

screws

f.

the

cover to

the

screws

sign (Ref. Figure 201). holding

the

lamp tray

in

position.

wiring.

lamp tray

and snap-on

airplane.

with

a new

lamp tray assembly,

connect electrical

wiring,

then reinstall the

cover.

Restore electrical power to the

airplane.

SNAP-ON COVER

No

Smoking/Fasten

Seat Belts

Figure

,2,

30032s-1~

Lights Replacement

201

33-20-00

retaining

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

CABIN FL UORESCENT LIGHT TUBE REPLACEMENT WARNING: Do not operate the lighting system with any high voltage connectors disconnected electrical shock hazard exists and damage to personnel can occur. CAOTION: Do not

operate the lighting system with any high voltage

electrical connectors and

airplane

connectors disconnected

as

as an

damage

to the

can occur.

Precautions should be taken to avoid been in contact with bare

touching the connectors with bare fingers. If the connectors have fingers, they should be cleaned with alcohol before being put into service.

NOTE: Should it become necessary to operate the fluorescent lighting system with a high voltage electrical connection disconnected, the de power should be removed from the respective power supply. a.

Remove electrical power from the

b.

Carefully

c.

Remove the fluorescent

d.

Lower the tube and

e.

Reach

f.

Continue to withdraw the

g.

Remove the two

h.

Install

i.

Stow the electrical

j.

Install the

k.

Carefully replace

I.

Restore electrical power to the

remove

through

a new

the

upholstered

light

carefully

the headliner

screws

cover

plate (Ref. Figure 202).

tube from the

holding clips by pulling straight

withdraw the electrical

panel opening

wiring

to

airplane.

new

as

far

as

possible.

until the electrical connector is accessible.

separate the electrical

connector

airplane

(Ref. Figure 202, Detail A).

connector and

tighten

the

securing

screws.

inside the headliner and attach the electrical connector to the Velcro fastener.

fluorescent the

from inside of the headliner

and pry the electrical connector loose from its Velcro fastener.

fluorescent tube connector into the

wiring

wiring

down.

light

tube into the

upholstered

cover

holding clips.

plate.

airplane.

READING, TABLE, VESTIBULE AND BAGGAGE COMPARTMENT LIGHTS LAMP REPLACEMENT a.

Pull the lens and lens holder out of the

light assembly (Ref. Figure 203).

b.

Remove the old

a new

c.

Insert the lens and lens holder in the

Page

lamp and replace

with

20233-20-00

lamp.

light assembly

and

push

it into

place.

nzs

Corporation

Hawker Beechcraft

SUPER KING AIR 8300/8300C SERIES MAINTENANCE MANUAL

HEADLINER ASSY.

~I

T

ELECTRICAL CONNECTOR

BULB CLIPS

A-’

VELCRO FASTENER REFLECTOR

oQ

is

DETAIL

A

FLUORESCENT 8UL8

COVER PLATE

30~352-11

Cabin Fluorescent Light Tube Replacement

Figure

A25

202

33-20-00

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

LAMP LEI\IS

HOLDER 350-352-031

Typical Reading, Table,

Vestibule and

STEP LIGHTS LAMP REPLACEMENT

Baggage Compartment Lights Lamps Replacement Figure 203

(OPTIONAL)

a.

Remove the four screws, the retainer, and the lens from the step

b.

Remove the defective

c.

Install the lens and retainer and

lamp

and

replace with secure

C

a new

light (Ref. Figure 204).

lamp.

with the four

attaching

screws.

EXIT SIGN LIGHT LAMP REPLACEMENT a.

Carefully pull electrical

I

the lens

cover

loose from the headliner while

supporting

the lens

cover

to avoid

straining

the

wifing (Ref. Figure 205).

b.

Remove the defective

c.

Install the lens

lamp

and

replace

with

new

lamp.

cover.

ORIGINAL

Page

204

Feb 1/09

33-20-00

As Received By ATP

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

FILL HOLE WITH RTV-108 SILICONE ADHESIVE BEFORE TNSTALLING SCREWS

BOTTOM STEP

I

OF

LAMP

LENS

RETAINER

j

SCREW

Isa-~s2-ma

Step Lights Lamp Replacement Figure 204

n25

33-20-00

Page

beF502

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

LAMP (14

BATTERIES

(4)

LAMP 1425)

$1

7~

COVEROSPACER WI

hi

SWITCH

MOUNTING PLATE

)i SCREW

Y

350-352-28

Exit

Sign Light Lamp Replacement Figure 205

SPAR LIGHT ~UBE REPLACEMENT a.

Remove all electrical power from the

b.

Remove the electrical connector from the

c.

Carefully

d.

Connect the electrical connector to

e.

Apply three drops of EA-901 adhesive (Item No. 5, Chart 2, 33-00-00) light tube and insert the light tube into the retainer.

f.

Restore electrical power to the

pry the

light

airplane.

light

tube

(Ref. Figure 206).

tube out of the retainer. a new

light

tube. at three locations on the back side of the

airplane.

THRESHOLD LIGHT LAMP REPLACEMENT

I

a.

Remove the three

b.

Remove the defective

c.

Install the lens and

Page

beF602

1109

screws

securing

lamp

cover on

and the

cover

replace

light

33-20-00

and lens to the

with

and

a new

secure

light (Ref. Figure 207).

lamp.

with the three

attaching

screws.

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

LTGHT

TUBE

’84;m~’ir"

3W-3~2-032

Spar Light Tube Replacement Figure 206

8--

SCREW

IAMP

SOCMEI

SCREW

CO~ER

LAMP

Threshold

Light Lamp Replacement Figure 207

ORIGIMAL A25

As Received By ATP

33-20-00

Page

207

Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

HANDLE POSITION OBSERVA nON LIGHT LAMP REPLACEMENT

I

a.

Remove the snap caps from the

b.

Remove the

c.

Remove the defective

d.

Install the placard

e.

Install the snap caps

screws

securing

on

lamp

the

placard

placard

from the

the door and on

the

on

(Ref. Figure 208).

to the cabin door.

lamp holder and replace

secure

placard

the cabin door

on

with the

retaining

with

a new

lamp.

screws.

the cabin door.

PLACARD

LAMP CABIN

DOOR

355-352-535

Handle Position Observation

Figure

Light Lamp Replacement 208

CABIN DOOR HOOK OBSERVA TION LIGHT LAMP REPLACEMENT a.

Remove the upholstery panel above the cabin door by removing the two snap caps and the two screws (Ref. Figure 209), then pulling the mounting tabs on the upholstery panel out of the brackets on the headliner

intercostal. b.

I

Remove the defective lamp and

Install the

upholstery panel

replace

with

a new

above the cabin door

headliner intercostal and installing the two

lamp.

by inserting

screws

the

mounting

tabs into the brackets

on

the

and snap caps.

ORIGINAL.

Page 208 Feb 1/09

33-20-00

As Received By ATP

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

SWITCH

r FORWARD CABIN DOOR HOOK OBSERVATION LIGHT

7

UPHOLSTERY PANEL

LENS SCREW

CAB I N DOOR HOOK A FT

DBSERVAIICN LIGHT

~SNAP

CAP

SCREW

SNAP

CAP-----/ 380-36~-057

Cabin Door Hook Observation

Figure

C

Light Lamp Replacement

209

LAMP BONDING

LENS

JUMPER

HOLDER

SCREW 80-3~1-031

C

~SCREW

Exterior

A25

Entry Light Lamp Replacement Figure 210

As Received

ATP

ByORIGNAL

33-20-00

Page

beF902

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

EXTERIOR ENTRY LIGHT LAMP REPLACEMENT a.

Remove the

supporting b.

I"

eight

screws

Remove the defective

Install the shown in

securing the access door over the light to the bottom straining the electrical wiring (Ref. Figure 210).

of the left hand

wing

while

the door to avoid

access

Figure

lamp and replace

door and

with

with the

secure

a new

lamp.

attaching

screws,

making

sure

to install the

bonding jumper

as

210.

ASSEMBL Y AND POTTING OF HIGH VOLTAGE CONNECTORS WARNING:

Do not

damage

to

personnel

operate the lighting system with any high voltage airplane can occur.

CAUTION: Do not

connectors disconnected

operate the lighting system with any high voltage

electrical shock hazard exists and

as an

can occur.

connectors disconnected

as

damage

to the

electrical connectors and

touching the connectors with bare fingers. If the connectors have fingers, they should be cleaned with alcohol before being put into service.

Precautions should be taken to avoid been in contact with bare

I

NOTE:

Should it become necessary to operate the fluorescent lighting system with a high voltage electrical connection disconnected, the de power should be removed from the respective power supply.

The

following

a.

Strip

b.

Crimp

the

is the

insulation pins crimp

the

from the

appropriate potting procedures for high voltage

c.

Apply Super

d.

Insert the

to

3/16-inch

wiring

and

being

careful not to nick the conductor

positioner. Crimp the

sockets to the

or

wiring.

flaring

the wires.

Be careful not to let any wires

(Locktite)

Bond 409

to the

pin/socket,

for

setting

the

pin

and socket into connector.

pin/socket into connector until the device is completely seated in the connector orifice. pin/socket into the connector or install a mating connector or install a mating connector to make

pin/socket.

e.

Allow

one

f.

Pot the connectors with HYSOL 9309

hour for the

Super

reach the bottom of the Let the HYSOL 9309

Page

protrude

barrel.

of the

g.

connectors:

bond to

cavity.

cure

Start

a mating alignment

cure.

using a medical syringe with needle, or suitable extension as required filling the wire leaving no voids. Fill the cavity until completely full.

for 24 hours at 77" F before

21033-20-00

Insert sure

to

using part.

a25

Ral~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXTERIOR

DESCRIPTION AND OPERATION

ANTI-COLLISION LIGHTS The standard anti-collision

light installation consists of an upper anti-collision light mounted in the upper ernpennage light mounted on the bottom of the fuselage. The anti-collision lights are the flashing beacon type of light. The anti-collision lights are controlled by a 10-ampere circuit breaker type switch placarded "BEACON" located on the pilot’s inboard subpanel (Ref. Figure land 2).

and

a

lower anti-collision

An

optional high-intensity anti-collision light installation consists of a strobe light mounted in each wing tip and a assembly mounted in the tail. The pulsating strobe high-intensity lights provide a means of recognition for the airplane during night flights. The strobe lights are controlled by a 5-ampere circuit breaker type switch placarded "STROBE" located on the pilot’s inboard subpanel.

flashtube and socket

The strobe

lights are powered by separate power supplies for each light. The wing strobe light power supplies are just outboard of each nacelle near the wing leading edge. The wing tips incorporate the navigation, recognition and strobe light systems. The separate power supply for the tail strobe light (flashtube) is located within the tail fairing, just forward of the tail strobe light. installed

The strobe

light

power

NOTE: The left and

supply

right

units

hand

are

wing

wired to operate the strobe

strobe

light

lights (wing tips

assemblies have to be of the

and

same

tail) synchronously.

part number for the system

to

operate properly. WARNING:

Complete observance of safety precautions when performing any maintenance to the light system is an absolute necessity due to the high voltage present in the system.

strobe

RECOGNITION LIGHTS The are

optional recognition lights

are

The

recognition lights are pilot’s inboard subpanel.

A21

wing tip just forward and inboard of the strobe lights. The lights airplane (Ref. Figure 3).

installed in each

focused to the front and outboard of the controlled

by

a

7.5-amp circuit breaker type switch placarded "RECOG" located

33-40-00

on

the

.,Pa3~b:Pagel

Ray~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TAIL FLOODLIGHTS The on

optional tail floodlights

are

the vertical stabilizer. The

FLOOD" located

on

the

mounted

floodlights

on

the underside of the horizontal stabilizer and illuminate the identification

controlled by a 15-ampere circuit breaker type switch placarded ’7AIL pilot’s inboard subpanel (Ref. Figure 4). are

IOA TRIPLE FED

BEACON DSI A223 PILOT’S INBOARD SUBPANEL

A524 UPPER FLASHING BEACON

OSI A523 LOWER FLASHING BEACON

Anti-Collision

Oct

31/06Page

2

33-40-00

(Flashing Beacon) Lights Figure 1

Schematic

A21

Ray~hwm

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ANODE

5A R GEN 9US

28VDC STROBE

I

I

I

TRIGGER SYNC

A223 PILOT’S INBOARD SUBPANEL

CATHODE

GND DS2 PS104 R. HIGH INTENSITY LT POWER SUPPLY

HIGH

DSI NAV INTENSITY A266

R.

WING

TIP

LT

ANODE 28VDC TRIGGER SYNC

CATHODE DSI

GND

A267 TAIL

TAIL HIGH INTENSITY LT POWER SUPPLY

PS100

UPPER LT

ANODE

28VOC TRIGGER SYNC

CATHODE

GND

DS2 PS103 L. HIGH INTENSITY LT POWER SUPPLY

DSI

NAV

HIGH

INTENSITY A265

L.

WING

TIP

LT

3ao-so3-l to

Anti-Collision

A21

(High Intensity) Lights Figure 2

c

Schematic

33-40-00

Oct

31/06Page

3

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RECOG DS

3

7.5

RIGHT GEN BUS A223 PILOT’S INBOARD SUBPANEL A266 RIGHT TIP LIGHT

DS

WING

3

A265 LEFT TIP LIGHT

WING

3ao-soJ-l~l

Recognition Lights Schematic Figure 3

TAIL FLOOD

DS

7.5

LEFT GEN BUS A223 PILOT’S INBOARD SUBPANEL DS 159 RIGHT FLOOD LIGHT

TAIL

DS

DS 158 LEFT FLOOD LIGHT

TAIL

sao-M)3-lln

Tail

Oct

31/06Page

4

33-40-00

Floodlights Schematic Figure 4

A21

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LANDING AND TAXI LIGHTS Two

landing lights and one taxi light are mounted on the nose landing gear. The landing lights are controlled by two 10-ampere circuit breaker type switches placarded "LEFT LANDING" and "RIGHT LANDING". The taxi light is controlled by a 15-ampere circuit breaker type switch placarded 7AXI". All three switches are located on the pilot’s inboard subpanel (Ref. Figure 5). NA VIGA TION LIGHTS

navigation light installation consists of two red lights installed in the left wing tip, two green lights right wing tip, and a light installed in the aft end of the empennage. The navigation lights are controlled by a 7.5ampere circuit breaker type switch placarded "NAV" located on the pilot’s inboard subpanel (Ref. Figure 6).

The standard

installed in the

When the

optional high intensity anti-collision lights assembly as the flashtube.

are

installed, the tail navigation light is

a

halogen lamp

mounted

in the same

R

GEN BUS

RIGHT LANDING

10

L

2EN BUS

R

DS 110 LANDING

LT

i

DS 109 LANDING

LT

S507 NOSE GEAR UPLOCK SWITCH

LEFT LANDING

10

TRIPLE FED BUS

A129 ADVISORY LIGHT TEST &HYDR GR TIME DELAY PCB

TAXI

LOG/TAXI 15

LIGHT

DS TAXI A223

INBOARD

106

T

A511 DIODE ASSY

(WHITE)

LIGHT E193 CAUTION/ ADVISORY ANNUNCIATOR PANEL

PILOTS SUBPANEL

(CH 33-10-00) C

Landing

A21

and Taxi

Lights Figure 5

Schematic

33-40-00

Oct

31/06Page

5

Iaytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NAV L

GEN BUS

IOPTIONALI DSI

NAV&HIGH

INTENSITY

7.5 L_____

A223 PILOTS INBOARD SUBPANEL

DS2 A266

R

AFT

NAV

TIP

WING

DSI

FWD

NAV

DS2

AFT

NAV

A266

R

TIP

WING

LIGHT

LIGHT

DSI

A267

DSI

FWD

NAV

DS2

AFT

NAV

A265

L

iT

TAIL

UPPER

WING

TIP

LT

(OPTIONAL] DSI NAV&HIGH INTENSITY

DS2

A265

L

AFT

WING

NAV

TIP

LIGHT

Navigation Lights Schematic Figure 6

Page

tcO6

31/06

33-40-00

A21

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WING ICE LIGHTS of

The

the

the

circuit breaker type

optional wing ice lights are installed in the outboard side of each nacelle and are aimed at wing to illuminate any ice accumulation. The wing ice lights are controlled by a 5-ampere switch placarded "ICE" located on the pilot’s inboard subpanel (Ref. Figure 7).

leading edge

ICE

TRIPLE BUS

FED

A223 PILOTS INBOARD SUBPANEL

DS112 R. ICE

LT.

DSi I I ICE L.

LT.

360-603-111

Wing

A21

Ice

Lights Schematic Figure 7

33-40-00

Oct

31/06Page

7

Nayffmaa

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXTERIOR

MAINTENANCE PRACTICES

WING TIP LIGHT ASSEMBL Y REMOVAL bleed-off resistor is incorporated in the strobe power supply circuit, high voltage is in involved the circuit between the strobe power supplies and the strobe light assemblies. For this reason, turn the control switch for the strobe lights OFF and wait for at least ten minutes

Warning: Although

to

a

at the power supply and before handling or in units Failure to observe these precautions may result in these any way. or shock.

elapse before disconnecting the cables

disassembling physical injury a.

Remove electrical power from the

b.

Remove the transparent

c.

Remove the

d.

Disconnect the electrical connector and

attaching

airplane (Ref. Figure 201).

wing tip light assembly

screws,

1

cover.

washers, lock washers and bonding jumper and lift remove

the

complete

unit from the

out the

light assembly.

airplane.

WING TIP LIGHT ASSEMBL Y INSTALLA TION a.

Install the sure

new

wing tip light assembly and secure with bonding jumper (Ref. Figure 201).

the

attaching

screws, washers and lock

washers, being

to install the

b.

Connectthe electricalconnector.

c.

Reinstall the transparent

d.

Restore electrical powerto the

e.

Apply EROSION

wing tip light

1

cover.

airplane.

PREVENTION SEALANT

(Ref. Chapter 20-08-00).

WING TIP STROBE/AFT NA VIGA TION LIGHTS REPLACEMENT WARNING:

Although

a

bleed-off resistor is

incorporated

in the strobe power

supply circuit, high voltage

is

involved in the circuit between the strobe power supplies and the strobe light assemblies. For this reason, turn the control switch for the strobe lights OFF and wait for at least ten minutes to

elapse

disassembling physical injury a.

Remove the

disconnecting the cables at the power supply and before handling or these units in any way. Failure to observe these precautions may result in or shock.

before

wing tip light assembly

from the

airplane

as

described in REMOVAL OF WING TIP LIGHT

ASSEMBLY in this section. b.

201).Remove

c.

Remove the upper, lower and aft

d.

Remove the strobe

e.

Place new

a

the two

screws

from the aft

light wiring

navigation light

screws

lens retainer and

from the strobe

light

a new

flashtube to

if

applicable (Ref. Figure

base.

from the electrical connector and

clean, lint-free cloth around

replace the lamp

remove

the strobe

light

from the

assembly.

keep fingers from contacting the glass and install the

flashtube.

33-40-00Page

201

I

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I

CAUTION: If fingers should contact the flashtube, clean the isopropyl alcohol and allow to air dry. f.

Install the

g.

Install the base

h.

Install the lens retainer

Install the

i.

new

strobe

light wiring

over

assembly

the aft

wing tip light assembly

with

clean, lint-free cloth and

a

in the electrical connector.

the flashtube

over

thoroughly

area

and

secure

navigation light

in the

airplane

as

and

with the four

secure

attaching

with the two

screws.

attaching

screws.

described in INSTALLATION OF WING TIP LIGHT

ASSEMBLY in this section.

Chart 201

Lamp replacement Guide LOCATION

Nose

Landing Light Beacon)

Anti-Collision (Flashing

Navigation Light

Tail LH

REF. DES.

Lights

Ice

Exterior

Wing Navigation Lights

PART NO.

DS111, DS112

A70798-24

DS109, DS110

4596

A523DS1,A5204DS1

34-0226010-91

A267DS 1

1683

A265DS1, A265DS2,

MS35309-7512

A265DS1 DS1 1\11835309-7512

A266DS1, A266DS2,

Wing Navigation Lights

RH

A266DS1 DS1 Nose Taxi

Lights

Wing Recognition Lights (Optional) Floodlights

Tail

Anti-Collision

(optional wing strobe)

DS106, DS107

4596

A265DS3, A266DS3

130-381001-1

DS159DS1, DS158DS1

1982

A266DS1DS2,

MS25309-7512

or

1982SP

A265DS1 DS2 Anti-Collision Tail

(optional

tail flashtube and socket

Navigation Light) optional halogen lamp)

assy)

A267DS1

A506

A267DS1

A508-28

FORWARD WING TIP NA VIGA TION LIGHT LAMP REPLACEMENT a.

Remove the transparent

b.

Remove the

c.

Press the

lamp

d.

Install the

new

e.

Install the transparent

Oct

31/06Page

202

screw

wing tip light

securing

cover

(Ref. Figure 201).

the lens retainer and lens to the base.

into the socket and turn counterclockwise to

lamp

and

secure

remove.

the lens and lens retainer to the base with the

wing tip light

33-40-00

attaching

screw.

cover.

A21

Ray~hwm

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WING TIP RECOGNITION LIGHT REPLACEMENT a.

Remove the

wing tip light assembly from

the

airplane

as

described in REMOVAL OF WING TIP LIGHT

ASSEMBLY in this section. b.

Remove the tool

c.

ground wire from (Ref. Figure 201).

stud and

remove

attaching screws and washers securing recognition light assembly.

d.

install

e.

Install the

ground

Install the

wing tip light assembly

a new

recognition light assembly wire

the

on

the "hot" wire from the wire

with

splice

an

insertion

1

Remove the two discard the old

f.

ground

the

on

ground lug as

the

the bracket and

recognition light assembly

secure

with the two

and insert the "hot" wire into the wire

to the bracket and

attaching splice

screws

with

an

and washers.

insertion tool.

described in INSTALLATION OF WING TIP LIGHT ASSEMBLY in this

chapter. TAIL STROBE LIGHT FLASHTUBE AND SOCKET ASSEMBL Y REPLACEMENT WARNING:

a bleed-off resistor is incorporated in the power supply circuit, high voltage is involved in the circuit between the power supply and light assemblies. For this reason, turn the control switch for the strobe lights OFF and wait for at least ten minutes to elapse before

Although

disconnecting

the cables at the power supply and before handling or disassembling these units in any way. Failure to observe these precautions may result in physical injury or shock. a.

b.

Removeelectrical Remove the aft tail strobe

light

powerfromtheairplane. plate from supply.

cover

power

Disconnect the tail strobe

c.

from the tail

Remove the

connector from the power

wire harness. Secure the harness

light

vertical stabilizer d.

light

the top surface of the horizontal/vertical stabilizer fairing to

screws

to the

and disconnect the

as necessary to

prevent it from

navigation light connector dropping from reach into the

which attach the

the

navigation/strobe light assembly to the tail fairing and remove the complete airplane, carefully pulling the wiring and connectors completely out of the tail fairing.

Disassemble the lens retainer, the lens and

halogen lamp

access

(Ref. Figure 202).

light assembly from e.

supply

gain

and shield from the

gasket assembly.

from the flashtube and socket

assembly

and

remove

the

CAUTIOIV: Use

care not to contact the halogen lamp or the new flashtube with the fingers. If fingers should contact halogen lamp or the flashtube, clean the lamp or the flashtube thoroughly with a clean, lint-free cloth and isopropyl alcohol and allow to air dry.

the

f.

Remove the connectors from the flashtube and socket

g.

Assemble the socket

h.

existing halogen lamp assembly.

Insert the

existing i.

na

respective

wiring and connectors

screws

which

Connect the strobe

wires and install them

on

the

corresponding

wires of

a new

assembly.

were

light

and shield, and the

into the

removed in

and

opening Step c.

navigation light

gasket,

in the tail

lens and retainer to the

fairing and

connectors to the

reinstall the

respective

power

new

flashtube and

complete light assembly with

supply

and wire harness.

33-40-00

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

j.

Reinstall the

k.

Restore electrical power to the

cover on

top of the tail fairing.

airplane.

ELECTRICAL CONNECIOR WASHER LOCKWASHER

GROUND STUD

BONDING STRAP

SCREW

CREW SHER

"j

d

WA WASHER LOCKWASHE SCREW ANTI-COLLISION STROBE LIGHT

Y,

a COGNITION LIGHT OPTIONAL)

B

(OPTIONAL) AFT

WASHER

SCREW

FWD

NAVIGATION LIGHT

NAVIGATION LIGHT

DETAIL A 350-352-030

C

Wing Tip Light Replacement Figure 201 (Sheet 1 of 2)

Oct

31/06Page

204

33-4000

A21

Raytheon

Aircraft Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

SCREW

ANTI-COLLISION STROBE LIGHT ~S

LAMP

HOLDER NAVIGATION LIGHT BULB

COVER

SCREW

GASKET

LENS RETAINER

SCREW LENS

BASE

DETAIL

LAMP

SCREW

C

HOLDER

NAVIGATION LIGHT BULB COVER GROUND STRAP

V

,LENS

O

OUND

uD

I

SPLICE

GASKET

DETAIL

B

LENS RETAIN

9´•kSCREW

RECOGNITION LIGHT

DETAIL D

Wing Tip Light Replacement Figure 201 (Sheet 2 of 2)

A21

33-4000

Oct

31/06Page

205

Ral~heon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SCREW

LENS RETAINER

LENS

GASKET

HALOGEN NAVIGATION LAMP

SHIELD TUBE

DETAI1 A FLASH TUBE AND SOCKET ASSY

350-382-12

Tail Strobe and

Navigation Light Replacement Figure 202

TAIL NA VIGA TION LIGHT LAMPS REPLACEMENT

I

the lens retainer

a.

Remove the

b.

Remove the lens from the socket and reflector

c.

Press the

lamp into the socket and

d.

Install the

new

screws

securing

lamp, lens,

(Ref. Figure 203).

assembly.

turn counterclockwise to

lens retainer and the

remove.

screws.

WING ICE LIGHT LAMPS REPLACEMENT

I

door located

a.

Remove the

access

b.

Remove the

light lamp

c.

Replace

Oct

the

access

on

the outboard side of the nacelle

from the fixture and

replace

with

a new

(Ref. Figure 204).

light lamp.

door.

31/0633-40-00

A21

Raytheon

nireraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

9

SOCKET AND REFLECTOR ASSY

LAMP LENS

"5""

LENS LENS RETAINER

SCREW

I

I 350-362-11

Tail

Navigation Light Replacement Figure 203

LANDING LIGHT LAMPS REPLACEMENT a.

Remove the

retaining ring

b.

Remove the

light lamp

c.

Install the

from the

from the

1

landing light (Ref. Figure 204).

airplane

and

replace

retaining ring securing the landing light

with

to the

a new

light lamp.

airplane.

TAXI LIGHT LAMPS REPLACEMENT a.

Remove the

retaining ring

b.

Remove the

light lamp

c.

Install the

A21

from the taxi

from the

light (Ref. Figure 204).

airplane and replace with

retaining ring securing

the taxi

light

to the

a new

1 light lamp.

airplane.

33-40-00

Oct

31/06Page

207

Raytheon

Aircraft

tompany

SUPER KING AIR B300/B300C MAINIENANCE MANUAL

LANDING

REMOVE

RETAINING

TAXI

LIGHTS

2.

RING.

REMOVE OLD SEALED BEAM UNIT ANO REPLACE WITH NEW UNIT.

I

LIGHT

WING

ICE

LIGHT

j!

i.

2.

REMOVE REMOVE

RETAINING RING (I) SEALED BEAM UNIT (2)

I 1

I. 2.

REMOVE REMOVE

ACCESS BULB

DOOR

FL338971631

Landing,

Oct

33-4000

Taxi and

Wing Ice Light Figure 204

Bulb

Replacement

A21

Raythwm

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FOCUSING THE LANDING LIGHTS airplane level, its

With a.

b.

Park the

airplane

Loosen the

struts so

that the

mounting

and its lateral axis

properly inflated,

is at

landing light

a

parallel

to the

distance of 25 feet from

wall, focus landing lights

a

follows:

wall.

landing light mounting brackets until the (Ref. Figure 205).

bolts and rotate the

as

centerline of each

concentrated beam is 3 feet 9 inches above the floor c.

landing lights on their mounting retighten all the mounting bolts.

Rotate the then

(FLASHING BEACON)

ANTI-COLLISION a.

b.

Carefully

Loosen the cover.

c.

remove

the sealant around the

screw

glass

are

7 feet 6 inches

apart,

LIGHT LAMPS REPLACEMENT cover

(Ref. Figure 206).

securing the clamp ring around the glass replace the lamps as required.

cover on

the beacon

light

and

remove

the

glass

/I1.Remove and

Reinstall the

glass

cover

CAUTION: Ensure that the d.

brackets until the centerlines of each beam

Fillet seal around the

and the

clamp ring.

lamps do

not contact the

perimeter of the glass

glass cover at any point during oscillation.

cover

with sealant

(7,

Chart 1,

33-10-00).

TED LIGHT

I I

-e

FADED LIGHT

IENDS NOT TOO DISTrNCT)

FLOOR 6"

L3’ 9´•~

Landing Light Adjustment Figure 205

~al

33-40-00Page

209

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A

LENS SCREW

XQ_ FILLET SEAL

PERIPHERY WITH PRO SEAL 8908%

UPPER ANTI-COLLISION LIGHT

DETAII

A

FILLET SEAL PERIPHERY WITH PRO SEAL 8908’/2

CLAMP

LENS

SCREW

RING

LOWER ANTI-COLLISION LIGHT

DETAIL

B 350-3614

Anti-Collision

Page

tcO31106 012

33-40-00

(Flashing Beacon) Light Figure 206

Bulb

Replacement

A21

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TAIL FLOODLIGHT LAMPS REPLACEMENT a.

Carefully

b.

Remove the four

c.

Remove and

d.

Install the lens and lens retainer

e.

Fillet seal around the

remove

the sealant around the screws

replace

periphery

of the lens retainer

securing

the lens retainer and

lamp

required.

the

as

periphery

on

the

airplane with

remove

the

the lens from the

attaching

of the lens retainer with sealer

(Ref. Figure 207).

airplane.

screws.

(6, Chart 2, 33-00-00).

STROBE POWER SUPPLIES REPLACEMENT WARNING:

a bleed-oft resistor is incorporated in the strobe power supply circuit, high voltage is involved in the circuit between the strobe power supplies and the strobe light assemblies. For this reason, turn the control switch for the strobe lights OFF and wait for at least ten minutes

Although

elapse before disconnecting the cables at the power supply and before handling or disassembling these units in any way. Failure to observe these precautions may result physical injury or shock.

to

a.

in

applicable power supply. Access to the tail strobe power supply is gained by removing the from the top surface of the horizontal/vertical stabilizer fairing to gain access to the tail strobe cover plate light power supply. Access to either wing power supply is gained by removing the fairing on the leading edge of

Gain

access

to the

aft

the b. c.

wing just

outboard of the nacelle

(Ref. Figure 208).

Disconnect the electrical connectors from the power

Remove the the

screws

and washers

securing

the power

supply to the

structure and

remove

the power

supply from

airplane. to the structure with the

d.

Install

e.

Connect the electrical connectors to the power

f.

Replace

n21

supply.

new

power

the

supply

fairing

and

secure

removed to

gain

access to

attaching

screws.

supply. the power

supply.

33-40-00

Oct

31/06Page

211

Raytheon

AiKlaft Cc~mpany

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

HOVSING

A

’e GASKET

PIVOT BRACKET

r LAMP SOCKET

REFLECTOR HAL

U FILLET SEAL PERIPHERY

WITH EC-12398-’/~ SEALER

LENS RET

DEtAIL

A 350-353-6

Tail

Page

tcO212

31/06

33-40-00

Floodlight Bulb Replacement Figure 207

A21

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

B

WING STROBE

POWER SUPPLY BRACKET

’X~P

WASTIER

SCREW

NUTWASHER LOCK WASHER

DETAIL

A

PIN HOUSING

TAIL STROBE

PLUG

POWER SUPPLY

I WASHER SCREW

DETAIL

B 350-362´•13

Supplies Replacement Figure 208

Strobe Power

A21

33I40-00

Oct

31/06Page

213

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

EMERGENCY LIGHTING

Emergency

door exit

signs

are

DESCRIPTION AND OPERATION manufactured to be

self-illuminating by

use

of

a

phosphor

coated tube and tritium

gas. No exposure to daylight is necessary. They have a useful life of many years that is determined by the level of luminosity at time of manufacture, the decay rate of the tritium and the minimum acceptable luminosity requirements in the Code of Federal

Regulations

and Federal Aviation

Regulations

or

other national airwo~thiness

authority.

CAUTION 1 I CAUTION While

no

primary radiation is emitted by this style of light, damaged or defective lights and outdated sources must be properly disposed of. Contact the manufacturer or supplier for instruc-

calibration tions.

FAA

requirements call for

the

microlamberts. Handles and

luminosity of handles and signs on the airplane to be equal signs should be replaced at intervals specified in Chapter 4.

EMERGENCY LIGHTING When

testing

handles

or

signs,

to

or

greater than 100

MAINTENANCE PRACTICES ensure

the

T-light Comparator

has

a

current calibration. See the manufacturer’s

specification for this information. Replacement calibrated sources are available from the manufacturer and may be installed by the user. This type of instrument is calibrated only at the luminosity shown and cannot be used to compare the values. Checks should be made at several points across the face of the component under test. If it appears less bright than the calibrated source at any point, it should be replaced. Other brand test instruments traceable to

nl2

a

are

acceptable if they meet the following tolerance luminosity of 100 microlamberts +15 or -O.

are

within calibration intervals and

national standard for

33-50-00

Ray~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

SELF-ILLUMINATED EXIT SIGN BRIGHTNESS CHECK

inspected on the airplane, under all types of lighting conditions, without the need for brightness requires the use of a T-light Comparator (1, Chart 1, 33-00-00). The test is per-

Self-illuminated devices removal.

formed a.

Checking

as

for

be

follows:

Clean the device to be tested with

00-00), wipe dry with b.

can

a

a

mixture of

warm

water and

liquid detergent,

non-abrasive

(3,

Chart 2, 33-

clean soft cloth.

Ensure the calibration is current

on

the test instrument.

Place the comparator base flat on the surface of the device to be tested and aperture is over the area to be tested. c.

move

it

gently

until the

viewing

Compare the brightness of the device portion seen through the aperture and the calibrated source. If the device is as bright or brighter than the calibrated source, the selected point of measurement meets the specification. Several measurements should be made across the surface of the sign or handle. d.

e.

If any

point

appears less

bright than

the comparator, the device must be

replaced.

NOTE

T-light Comparators

used for

ed reference

installed within the

source

checking

illuminated

preceding

sign brightness

must have had

twelve months for the

a

brightness

newly calibrattest to be

con-

sidered valid.

T-light Comparator Figure 1

O Mar

9/0133-50-00

mn

CHAPTER

NAVIGATION

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 34

NAVIGATION

PITOT/STATIC

TABLE OF CONTENTS

SUBJECT

PAGE 34-00-00

Navigation 4 Pitot/Static- Description and Operation Digital Outside Air Temperature Indicator Pitotand Static Pressure Systems Special Tools. Navigation 4 Pitot/Static -Troubleshooting. Navigation 4 Pitot/Static- Maintenance Practices. Pitot System Pressure Test. Inspecting PitotSystem Hoses. Static System Check. Static System LeakTest.

......1 ................1 ..1

............101 .......201 .....201 ..201

.......202

34-01-00

Navigational Components- Description

and

Operation

.....1

Publication List

Navigational Components

Maintenance Practices

......201

Removaland Installation of

Flight Instruments. Navigational Component Arrangement. Navigational Component Removal Navigational Component installation.

.........201 .201 .201 .201

Radarlndicator Removal

.......201

Radar Indicator Installation

......202

RadarAntenna Removal.

.......202

RadarAntenna Installation

GlideslopeAntenna GlideslopeAntenna

......202

Removal

....202

Installation.

.205

34-10-00

Air Data

System (For

RVSM

(FL-352

Compliant Airplanes)-

and After; FM-11 and After; and if Equippedwith Collins EflS-85B(14))

Airplanes

Airworthiness RVSM

Inspection Requirements Region Inspection

Maintenance Practices

that have

complied

with Service Bulletin No. 34-3507, .1

.................1 .........2

Static Portlnspection Air Data system and

Transponder Check In-flight Autopilot (Altitude Hold) Check Painting RVSM Critical Region Comer Markings

nit

...............10

................13 .........15

34-CONTENTS

1

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 34

NAVIGATION

TABLE OF CONTENTS

SUBJECT

PITOT/STATIC

(Continued) PAGE

34-20-00

Attitudeand Direction

MaintenancePractices

Standby Compass Calibration AvionicsCooling BlowerOperational Check Airplaneswith EFIS KA-33 Cooling Blower.

Page

tcO2

31/06

34-CONTENTS

201

201 202

202

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

34-LOEP

1

Feb 1/10

34-CONTENTS

1 and 2

Oct 31/06

34-00-00

1 thru 5 101 201 and 202

Oct 31/06 Oct 31/06 Oct 31/06

34-01-00

1 thru 3 201 thru 206

Oct 31/06 Oct 31/06

34-10-00

1 thru 15

Feb 1/10

34-20-00

201 and 202

Oct 31/06

A27

34-LOEP

Page 1 Feb 1/10

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NAVIGATION

DESCRIPTION AND OPERATION

PITOT/STATIC

DIGITAL OUTSIDE AIR TEMPERATURE INDICATOR

digital outside air temperature indicator system consists of a temperature probe, a remote processor, digital display unit, associated wiring and a 5-amp circuit breaker. The temperature probe is located on the belly of the airplane forward of F.S. 107.00 at L.B.L. 17.00. The temperature probe is a semiconductor device that generates a signal for the processor to translate. The remote processor is mounted on a panel assembly located beneath the center aisle floor aft of F.S. 168.75. The processor receives a signal from the temperature probe, translates it and sends a signal to the digital display unit. The digital display unit is mounted in the left hand side panel in the crew compartment. The display unit presents a digital, numeric indication of outside air temperature. The primary indication is in degrees Celsius, with a momentary push-button switch to display degrees Fahrenheit.

The

The range of the display unit is -55 to 80 degrees Celsius or -67 to a provision for automatic dimming as the ambient light declines.

176

degrees

Fahrenheit. The

display

unit has

PITOTAND STATIC PRESSURE SYSTEMS systems provide a source of impact pressure and static air for operation of the of the system is composed of two mast-mounted pitot tubes, one on each side of the pitot portion lower nose, electrical wiring for each pitot heater and tubing for instrument connection. The impact pressure entering the pitot tubes is transmitted to the dual airspeed indicators mounted on the instrument panel through separate

The

pitot

and static pressure

instruments. The

tubing

routed

Since the

along

pitot

each upper side of the

tube is the lowest

point

nose

compartment.

in each line from the

airspeed indicators,

eliminates the need for drain valves. Two circuit breaker switches

heating

on

the left inboard

the resultant natural

subpanel control

the

drainage pitot tube

elements.

of the system includes two static ports on each side of the fuselage just forward of F.S. 402.75. Lines connect the static ports to the instruments in the crew compartment. The static lines are routed from the static ports to the top center of the fuselage, then over to the right side of the fuselage. They are then routed forward in

The static

portion

sidewall beneath the windows, to the rate-of-climb indicator, altimeter and airspeed indicator on the instrument panel. The static line drain valves are located behind an access door located in the lower right hand crew compartment sidewall adjacent to the instrument panel. The static lines should be drained anytime the airplane has

the

fuselage

or erratic instrument readings indicate that the normal static source is be utilized. The alternate system supplies static air from the interior of the restricted, the alternate air source may aft fuselage. The alternate static air line is routed through the aft pressure bulkhead forward along the right side of

been

exposed

to rain. Should abnormal

fuselage to the static air selector valve. This selector valve is located below the right circuit breaker panel adjacent to the instrument panel. The static air, selector valve is held in the normal position by a clip, the alternate air source is selected by raising the clip and moving the toggle from NORMAL to ALTERNATE. The instruments

the

then function

nn

on

the alternate air

source.

34-00-00

1

NaYPheapl

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SPECIAL TOOLS

I

Each tool listed in Chart 1 is provided as generic or locally manufactured tools that

an are

example of the equipment designed to perform a specific function. the equivalent with respect to accuracy, function and craftmanship

may be used in lieu of those listed.

Chart 1

Special Tool Name 1.

Tools

Part No.

Surgical Tubing long

Supplier

Use

Obtain

Locally

Leak check

pitot system.

112 in. I.D., 3 ft.

1

2.

Locking Pliers (or Hemostat)

Obtain

Locally

Leak check

pitot system.

3.

VacuumPump

Obtain

Locally

Leak check

pitot system.

4.

Altimeter

Obtain

Locally

Leak check

pitot system.

Page

234-00-00

Raylheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DATA

9

SWITCH

8

B

7

D

6

F

IOVDC DISPLAY

GND

CLOCK/ASC

II

5

PROBE

(BLACK)

4

PROBE

(RED)

3

28

A

VDC

H

i?

INDICATOR

2

GROUND PROCESSOR

REMOTE

WHITE 5 C849

OUTSIDE

AIR

BLACK RED

BLUE

TEMP

RIGHT CIRCUIT BREAKER PANEL

3o0-390-01*

Digital Outside

A21

1 PROBE

Air

Temperature Wiring Figure 1

34-00-00

Oct

31/06Page

3

RaytheOn

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I

I

ca~

f

01´•

nEi ..~.iss4 mJ

sl

la

n´•

ra~

O

O

C´•~,o

.YI

B (El)

FREE AIR TEMP

REMOTE PROCESSOR

DETAIL

C

AC POWER DISTRIBUTION AND STALL WARNING COMPUTER

PANEL

01 1/

Uld

ESCUTCHEON

r

I~ I/

DETAIL

FUSELAGE BELLY SKIN

II

UNDER CREW

I; II

COMPARTMENT

I: II

i

L----~

II

B

PROBE

I

I

LOOKING AFT LEFT SIDE AT FS

ii

107 BULKHEAD

FREE AIR TEMP

i

II

1 e

---~i

I i

I o

23C

PUSHb

i

I; i o

""’’´•´•´•’’II

FOR OF

J

1

DETaa

A

PILOT’S LEFT SIDEWALL

DIGITAL DISPLAY

INDICATOR C9201706

Digital

Outside Air

Temperature Indicator

Figure

Oct

31/06~’314,

34-00-00

2

A21

Raydheon

nircraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PILOT’S STATIC AIR

COPILOTS STATLC AIR,

TOPILOT’S INSTRUMENTS

PRESSURE

i.

i’-´•

TO COPILOT’S INSTRUMENTS

I

PILOT’S ALTERNATE

STATIC AIR ’O

CDPILOTB PITOT

STATIC

AIR

STATIC AIR

PILOTS ALTERNATE STATIC AIR

TO COPILOT’S INSTRUMENTS TO PILOT’S INSTRUMENTS

PILOT’S PITOT

DETAIL

A

~e

DRAIN VALVE 300-394-1

Digital

A21

Outside Air

Temperature Wiring Figure 3

34-00-00

Oct

31/06Page

5

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NAVIGATION

PITOT/STATIC -TROUBLESHOOTING

Chart 101

Troubleshooting Instruments

Step

1.

Lines

Pitot/Static Pressure

Inoperative

clogged

or

Erratic

System

Operation

YES

Drain lines at drain valves, disconnect lines at instruments and blow out with low pressure air.

YES

Repair

NO

Step

2.

Cleek lines for leaks

or

loose

connections.

as

required.

Chart 102

Troubleshooting Pitot

Pitot/Static Pressure

Heating Element(s) Inoperative Check

Step

1.

Circuit breaker switches

System

tripped

YES

wiring continuity for grounded or open Repair as required and reset circuit

circuits.

breaker switches.

StepP.

Circuitbreakertrips again

YES

Step

Defective

YES

A21

3.

heating

element

Check for defective circuit breaker and as

replace

required.

Replace heating

element.

34-00-00

Oct

31/06Page

101

Ray~heon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NAVIGATION

MAINTENANCE PRACTICES

PITOT/STATIC

PITOT SYSTEM PRESSURE TEST Connect

a.

low pressure air

a

CAUTION: To avoid

source

the

rupturing

(3,

Chart 1,

diaphragm

34-00-00), equipped

of the

with

an

on-off valve, to the

airspeed indicator, apply pressure slowly

pitot

head inlet.

and do not build up

excessive pressure in the line. b.

pressure SLOWLY until the valve off.

Apply

NOTE: As

airspeed indicator registers

90

percent of its maximum reading, then

turn the

equipment noted above not be available, clamp a rubber tube ~1, Chart pitot head inlet so that the tube connection is airtight. Crimp the end of the tube with locking pliers (2, Chart 1, 34-00-00) and roll the tube up SLOWLY until the airspeed indicator registers 90 percent of its maximum reading. alternate method should the

an

1, 34-00-00)

over

the

If the system retains the pressure required to maintain the are no leaks in the pitot lines. If the airspeed indicator

c.

there

reading just obtained for a period of five minutes, reading declines, check the system for leaky hoses

and loose connections.

CAUTION: Release pressure

slowly to

avoid

damaging

the

airspeed indicator.

INSPECTING PITOT SYSTEM HOSES After the

pitot system is checked for leaks, inspect the hoses for signs of deterioration, particularly at bends and at points to the pitot mast and airspeed indicator. Hoses that are cracked or hardened should be with rubber hose conforming to Military Specification MIL-G-5593. Any time a hose is replaced, repeat a replaced

the connection the

preceding

pressure check.

STATIC SYSTEM CHECK The amount of attention

a.

static system depends largely on operating conditions. Foreign matter is ports and lines during times of high humidity, excessive precipitation, and dry

required by the

likely dusty weather; consequently, specified in Chapter 5. most

to accumulate in the static

the system should be checked

Disconnect the line at the

frequently

under such circumstances

or

at the interval

airspeed indicator and blow LOW pressure airthrough the lines to the static ports. during this procedure to ensure that each line is cleai; since even one clogged

Cover each static port separately port causes instrument error. CAUTION:

Never blow air

through the line toward the instrument panel; to do so may seriously damage blowing back through the line from the instrument panel, make sure that

instruments. When

instrument lines have been disconnected so

no

pressure

NOTE: It is essential that the static air system be drained after the b.

Drain the static air line

drain valve is

placed

by opening

the

access

~PZ1

airplane

door located in the lower

flight or

Close the alternate static air valve to prevent air from

has been

right

when the cabin is

being

the

reach the instruments.

exposed

hand

crew

to rain.

compartment wall. A

in the line at this location to facilitate the removal of moisture.

CAUTION: Do not drain the static air system while in c.

can

the

pressurized.

blown into the cabin

during

the

following step.

34-00-00

I

Ra~hwm AiKraft Company SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Disconnect the line from the valve at the point where it connects to the airspeed indicator and blow the alternate static air line clear.

readings may result if wax or polish is applied to the static air buttons. Clean the static air periodically with isopropyl alcohol, or equivalent, to ensure that no film has formed on them.

NOTE: Erratic instrument

buttons

STA TIC SYSTEM LEAK TEST The

following leak test accomplishes specified in Chapter 5. CAUTION: To avoid

damaging

the

the

airspeed indicators,

the lines capped, or an equal the system for leakage. a.

Connect

an

external

requirements

vacuum source

vacuum

of Federal Aviation

Regulations

91.411 at the interval

the indicators should be disconnected from the system and applied to the pitot side of the indicators while testing

should be

to the static air

system

test

ports in the aft compartment behind the aft

pressure bulkhead. b.

Place

an

altimeter

(4, Chart 1, 34-00-00)

in the

vacuum

line when

connecting

the

vacuum source

to the static

port. c.

Apply

a vacuum

equivalent

of vacuum sealed, the loss

Oct

to

16,200 feet plus field elevation

over a one

31/0634-00-00

minute

period

at the time and

place of the

must not exceed 2% of the vacuum

test. With the source

equivalent.

ul

Ral~heOl

AiKraft

Company

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

NAVIGATIONAL CORIIPONENTS The

navigation

installations under

Navigational Components

Maintenance Practices

(Ref. 34-01-00)

are

typical

of

Because of the many variations of equipment and installations, an airplane may differ somewhat from the illustrations, however, reference to the approximate locations shown may be benficial for

the installations in the

maintenance

airplane.

operations.

For

specific information applicable to individual systems, refer to the Wiring Diagram Wiring Diagram Manual P/N 130-590031-197 (FL-381, FL-383 and After, appropriate vendor equipment operators manuals which are furnished with each

more

Manual P/N 130-590031-7C and Avionics FM-12 and

After)

and to the

airplane. For maintenance of individual components, refer to the latest revision of the appropriate manual for further information. The following Chart 1 is a list of the various navigation equipment manuals which may be applicable to the

navigation system

installed in the

airplane.

PUBLICATION LIST

Chart 1

Navigation Equipment

Manuals in

Alphabetical

Order of

and Title

Title

Company KA-138 Nav

Switching

Bendix/King

KCP-420 AP/FD

Bendix/King

KCS-305

Bendix/King

KCU-567/KCU-568 Control

Bend ix/l
KDA-430 Data

Bendix/King

KDC-481 Air Data

Bendix/King

KDF-806 ADF Receiver 066-05511-0004

Bendix/King

KDI-573B DME Indicator 006-05595-0000

Bend ix/King

KDL-589 Data Loader 006-0561 6-0001

Bendix/King

KDM-706/KDM-706A/KDM-706E

Bendix/King

KEA-130A

Bendix/King

KEA-346

Encoding

Bendix/King

KFC-100

Autopilot Flight

Computer Adapter

Compass System

Adapter

Encoding

KNC-667 Power

Module 006-05664-0000

006-05116-0002

Display

006-05665-0000

Computer

006-05653-0001

DME Receiver 006-05177-0005

Altimeter 006-05563-0000

Altimeter 006-05514-0001

Director

System

006-05668-0000

Supply

006-05644-0002

006-05697-0001 006-05698-0001 006-05699-0000

Bendix/King

KNI-582 RM1006-05193-0001

Bendix/King

KNR-634 Nav Receiver 006-05188-0007

Bendix/King

KNS-660

~al

Flight Management System

I

It

Kit 006-00533-0000

Bendix/King

Bendix/King

Company

006-8407-00

(Includes Self Test)

34-01-00

RBytheMI

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

Navigation Equipment Manuals

in

Order of

Alphabetical

Company

and Title

(Continued)

Title

Company Bendix/King

KPI-552/KPI-553HSI 006-05601-0001

Bendix/King

KRA-405 Radio Altimeter 006-05104-0000

Bendix/King

KXP-756

Bendix/King

Long Range

Bendix/King

RDS-86 Radar 006-05966-0004

Collins

331A-3G Course Indicator Overhaul Manual

Transponder Nav

006-05198-0005

System

006-05645-0002

(Repair) (with

illustrated parts

list)

331A-3G Course Indicator 522-0762672 Collins

ADF60 Automatic Direction Finder Instruction Book ADF-60 Automatic Direction

Collins

Finding System

ADS-65 Air Data Sensor Instruction Book

(Installation

and

Repair)

523-0766184

(Repair)

ADS-65 Air Data Sensor 523-0771884

Collins

ADS-80 Air Data ADS-80 Air Data

Collins

System System

ALT-50 Radio Altimeter ALTdO Radio Altimeter

Collins

ALT-55 Radio Altimeter ALT-55 Radio Altimeter

55A/55B)

Instruction Book

(Installation)

523-0767654

System System

Instruction Book

(Installation

and

Repair)

523-0764281

System Instruction Book (Installation and Repair) System (with ALT-55B for 2500-foot operation and

ALT 55/

523-0766793

Collins

CAD-62 Control Adapter Instruction Book (Repair) CAD-31/CAD-62 Control Adapter 523-0773216

Collins

DME-42 Transceiver Instruction Book

(Repair)

DME-42 DME Transceiver 523-0772458

Collins

EFD-74 Electronic EFD-74 Electronic

Collins

EFIS-85B EFIS-85B

Flight Display Flight Display

(4/14)

Electronic

(4/14)

and EFIS-86B

DPU-85N/MPU-85N Collins

or

Flight Information Systems Installation Manual (4/14) Electronic Flight Information Systems (Using DPU-86N/MPU-86N) 523-0775353

EHSI-74n4B Electronic HSI

EHSI-74n4B Electronic HSI Collins

Collins

System System

Instruction Book

Flight

Instrument

System

Instruction Book

FIS-84

Flight

Instrument

System

523-0768867

FIS-85

Flight Flight

Instrument

System System

523-0769151

Instrument

(Installation)

523-0772693

FIS-84

FIS-85 Collins

Instruction Book 523-0772699

Instruction Book

HCP-74 HSI Control Panel Instruction Book

(Installation) (Installation)

(Repair)

HCP-74 HSI Control Panel 523-0772704 Collins

HPU-74 HSI Processor Unit Instruction Book

(Repair)

HPU-74 HSI Processor Unit 523-0772709

Oct

31/06Page

2

34-01-00

A21

NayMmae

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

Navigation Equipment

Manuals in

Alphabetical

Order of

Company

(Continued)

and Title

Title

Company Collins

IND 42

()DME

Indicator Instruction Book

DME Indicator 523-0772463

INC 42

Magnetic Compass System Instruction Book (Installation) MCS-65 Magnetic Compass System (covers DGS-65, CCU/RCP-65

Collins

MCS-65

and

FDU-70)

523-0771835

RMI-30 Radio

Collins

RMI-30 Radio

Collins

SSS-65

Slip/Skid Slip/Skid

SSS-65 Collins

Magnetic Magnetic

TDR-90

VIR-32 VIR-32

Instruction Book

Navigation Receiver Navigation Receiver

Systems

WX-1000

(Installation

Stormscope

System System

Instruction Book

WXR-220/270/300 Weather Radar L-3 Avionics

(Installation

and

Repair)

and

Repair)

Installation Manual 523-0774651

(Repair)

523-0772819

WXR-220/270/300 Weather Radar

Collins

Repair)

523-0765128

TWR-850 Turbulence Weather Radar Collins

and

Sensor 523-0771647

TWR-850 Turbulance Weather Radar

Collins

(Installation

Indicator 523-076976

Sensor Instruction Book

Transponder Transponder

TDR-90

Indicator Instruction Book

System System

Instruction Book

(Installation)

523-0772443

78-8060-5820-8

Universal Avionics

Corp.

2214UNS-1A Flight Management System

Technical Manual

Report

No. 2206, 2207,

Universal Avionics

Corp.

UNS-1D

Flight Management System

Technical Manual

Report

No. 34-60-09

1 I

Universal Avionics

Corp.

UNS-1K

Flight Management System

Technical Manual

Report

No. 34-60-12

1 I

Universal Avionics

Corp.

UNS-1L

Super Flight Management System Technical Manual Report

Universal Avionics

Corp.

UNS-1M

Navigation Management System

Technical Manual

Report

or

No. 34-60-25

No. 34-60-05

34-01-00

1 I

1 I

Ray~heon

nircraft

Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

NAVIGATIONAL COMPONENTS

REMOVAL AND INSTALLA TION OF FLIGHT INSTRUMENTS Instructions for removal and installation of all

Chapter

flight

instruments in the

floating

instrument

panel

are

outlined in

39-10-00 of this manual.

NA VIGA TIONAL COMPONENT ARRANGEMENT all avionics components pressure bulkhead, except for

Nearly

are

installed in the

autopilot

servos

nose

which

compartment

are

or

covered in

the aft avionics shelves

Chapter

just aft

of the aft

22 of this manual and the radio

amplifier, which is mounted beneath the cabin center aisle floor in line with the aft cabin window. typical installation of components which can be used as a reference for approximate component Figure locations. Figure 202 shows typical component installations.

altimeter dual radio 201 shows

a

NA VIGA TIONAL COMPONENT REMOVAL The avionics units installed in the

trays and

can

nose

compartment and the aft avionics shelves

be removed and reinstalled in the

same

are

nearly

all installed in

mounting

manner, as follows.

a.

Remove all electrical power from the

b.

Loosen the thumbscrew retainer and allow it to fall away from the

c.

Carefully slide the unit from its mounting tray. disengage as the unit is removed.

airplane.

retaining

bracket.

The electrical connector located

on

the back of the unit will

NA VIGA TIONAL COMPONENT INSTALLA TION a.

Ensure that all electrical power is OFF.

b.

Carefully engage

I

mounting rack. The electrical position.

slide the unit into the

as

the unit slides into

c.

Position the thumbscrews and

tighten.

d.

Restore electrical powerto the

airplane.

connector on the end of the unit will

automatically

RADAR INDICA TOR REMOVAL a.

Remove all electrical power from the

b.

Locate the radar indicator in the center of the instrument radar indicator and

disengage

airplane.

c.

Slide the radar indicator aft and out of the

d.

Tag, identify

na

panel.

Turn the two

locking pawls

at the bottom of the

the indicator.

mounting tray.

and disconnect the electrical connectors

on

the back of the indicator.

34-01-00Page

201

Raytheon

AiKlaft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RADAR INDICA TOR INSTALLA TION a.

Ensure that all electrical power is OFF.

b.

Connect the electrical connectors

c.

Slide the indicator into the

d.

Lightly

e.

Restore electrical power to the

press forward

on

on

the back of the indicator.

mounting tray

in the instrument

panel.

the radar indicator and rotate the two

locking pawls

to secure it.

airplane.

RADAR ANTENNA REMOVAL NOTE: Refer to

Figure 1,

23-00-00 for radar antenna location.

a.

Remove all electrical power from the

b.

Remove the

c.

Remove the radome.

d.

Tag, identify

and disconnect the electrical connectors from the radar antenna.

e.

Remove the

attaching

attaching

airplane.

from the radome.

screws

hardware and the radar antenna from the

airplane.

RADAR ANTENNA INSTALLATION

I

a.

Ensure that all electrical power is OFF.

b.

Perform antenna

c.

Secure the radar antenna

d.

Connect the electrical connectors to the radar antenna.

e.

Install the radome with

f.

Restore electrical power to the

bonding procedures (Ref. 23-00-00). on

the

attaching

nose

bulkhead with the

attaching

hardware.

screws.

airplane.

GLIDESLOPE ANTENNA REMOVAL

I

NOTE: Refer to on

Figure 1,

the forward

23-00-00 for

nose

glideslope

antenna location. The antennas are located on the lower stiffener

bulkhead. Either antenna may be removed

a.

Removeelectrical

powerfromtheairplane.

b.

Remove the

radome.

c.

Disconnect the coaxial connector from the antenna.

d.

Remove the the

Oct

31/06Page

nose

mounting

screws

which attach the antenna

as

housing to the

follows:

bulkhead and

remove

the antenna from

airplane.

202

34-01-00

A21

Ray2heon

Aircraft Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

loeaoo

*URIL W~N

~I TWEGEN

los24a

I I

#2 DB-418

1

#1 DB-418

I 1

I

B

I~IJ

APC-65

RELAY BOX

ADC-BOO~AP/FD CMPTR AIR DATA

(TOP)

CMPTR

GYRO DGS-65

1

O

I

J-BOX #1

os 204

I

PISSENDER

ELEC BOX

DGS-65

OXYGEN

COMPASS

COMPASS #2#1

BO1TLE

VOICE RECD

HF

HF

HF

ANT

HMTR

POWER

COUPL

REC

FLT

DATARECD

SUPPLY

TDR-

TDR-

#2

#1

#1

DME

VHF-22A COMM #2

#1

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VHF-22A COMM VIR-32 COMM #2

#1

VIR-32 COMM

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KNS-660

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LNS-

FLIGHT

RNAV

PHONE

#2

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RADIO AFT FUSELAGE AVIONICS SHELVES NOSE CAMPARTMENT AVIONICS SHELVES

D~AILA

ALTM FL348

OEIAIIB

062135AA.AI

Typical

Avionics

Component Locations

Figure

A21

201

34-01-00

Page 203 Oct 31/06

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

34-01 -00

Page Intentionally Left

Blank

A21

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

GLIDESLOPE ANTENNA INSTALLA TION a.

Ensure that electrical power is OFF.

b.

Perform antenna

c.

Attach the antenna

bonding procedures (Ref. 23-00-00). housing to the

bulkhead

using the mounting screws housing.

and insert the antenna ends

through the

antenna holders located on either side of the antenna

d.

Connect the coaxial cable to the antenna

e.

Reinstallthenose radome.

f.

Restore electrical power to the

nal

housing.

airplane.

34-01-00

Oct

31/06Page

205

Ral~heMI

nircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DIRECTIONAL GYRO

DIRECTIONAL GYRO NO

#1

b!l I

OCP~O d,

Q

MOUNTING TRAY

THUMBSCREW MOUNT

350-480-26

Typical

Oct

31/06Page

206

34-01100

Avionics

Component Installations Figure 202

A21

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 34-10-00

AIR DATA SYSTEM (FOR RVSM COMPLIANT AIRPLANES) - MAINTENANCE PRACTICES (FL-352 AND AFTER; FM-11 AND AFTER; AND AIRPLANES THAT HAVE COMPLIED WITH SERVICE BULLETIN NO. 34-3507, IF EQUIPPED WITH COLLINS EFIS-85B(14)) AIRWORTHINESS INSPECTION REQUIREMENTS The airworthiness inspections are required every 24 months or upon removal and installation of a static port or if damage to the RVSM region is observed or if the area within the RVSM region is repaired or painted. NOTE: All inspections must be conducted at ambient temperature with the airplane resting on its landing gear. There are no jacking or leveling requirements to conduct these inspections. a. Verify that the avionics and air data components listed in Table 1, REQUIRED AVIONICS AND AIR DATA COMPONENTS FOR RVSM OPERATION are installed and operational. b. Perform the AIR DATA SYSTEM AND TRANSPONDER CHECK. Verify the air data system errors are within specified RVSM tolerances called out in Charts 1 and 2. c.

Perform the RVSM REGION INSPECTION. Verify the corner markings identifying the RVSM Critical Region are discernible and in good condition. Re-mark the RVSM critical region as required (refer to PAINTING RVSM CRITICAL REGION CORNER MARKINGS).

d. Perform the STATIC PORT INSPECTION. Verify that the static ports are within the specified RVSM tolerances listed in the Static Port Inspection procedure. e. Conduct the IN-FLIGHT AUTOPILOT (ALTITUDE HOLD) CHECK. Verify that the airplane can maintain the specified RVSM tolerances listed.

Special Tools and Equipment Tool Name Gauging Equipment

A27

Part Number SPF-4 (A1M-BCH-GE)

Supplier

Use

Hawker Beechcraft To determine static port step height depth Parts and and make RVSM region measurements Distribution

34-10-00

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RVSM REGION INSPECTION The RVSM Region encompasses an area approximately 24” x 24” surrounding the static ports on each side of the airplane. Small markings must be painted on the corners of the RVSM Region to aid in identification of the area as shown in Figure 1. All repairs required within the RVSM Region must remain internal. If internal repairs are not possible, a RVSM specific analysis must be conducted to verify air data system integrity. Contact Raytheon Aircraft Customer Support at 1-800-429-5372. a. Inspect the RVSM critical region for obvious damage, deformation, creases, dents or bulges in the skin. Inspect for anomalies such as paint runs, non-flush application of aerodynamic sealant, dimples, dents, blisters, etc. The static port orifices must be inspected for corrosion, elongation, deformation, and/or obstruction and the operator must ensure that no foreign matter is found within the port orifice. b. Inspect the RVSM Critical region for incorrect type or oversized fasteners that may have been installed. c.

Inspect the oxygen servicing door on the right hand side for deformation and damage. Ensure the door functions normally and the door closes tightly with minimal mis-match relative to the airplane skin.

d.

If visual inspection of the RVSM Region indicates that damage, deformation, repair, etc. exists, then a special instrumented inspection of the RVSM Region must be conducted. Contact Raytheon Aircraft Customer Support at 1-800-429-5372.

e. In all cases, damage and repair within the RVSM Critical Region will necessitate a special instrumented inspection of the skin contour and surface geometry near the static ports, to determine RVSM compliance status.

STATIC PORT INSPECTION The static port must remain free of deformation, dents, obstructions, and foreign matter. If the static ports are found to be elongated, deformed, or obstructed in any way, the static ports must be replaced, and the STATIC PORT INSPECTION must be accomplished. a. Refer to Figure 4 and use the gauge block as a tooling reference and initialize the SPF-4 as follows: NOTE: Make sure the dial indicator reads negative when the plunger is depressed and positive when the plunger is elongated. 1. Inspect the SPF-4 for evidence of damage and/or contamination. 2. Clean the gauging assembly, gauge block, and dial indicator, as required, using a clean cotton cheesecloth moistened with solvent such as methyl propyl ketone, aliphatic naptha, isopropyl alcohol, or acetone. 3. Place the gauging assembly on the gauge block. 4. Ensure the smaller needle is at approximately 0.100. 5. Rotate the dial indicator to set the large needle at zero (0.0). 6. Remove the gauging assembly from the gauge block. CAUTION: After initialization, use caution to ensure the dial indicator adjustment is not offset. Erroneous indications may result. If the dial indicator adjustment is inadvertently offset, reinitialize the dial indicator.

Page 2 Feb 1/10

34-10-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL b. Inspect the static ports for flushness (step height) and angularity. The step height measurements are obtained at four (4) locations on each static port. These measurements are averaged to determine a Static Port Flushness (SPF) value for each of the four static ports. Refer to Figure 3 for measurement locations and calculation of SPF. The Static Port Angularity (SPA) value must be determined for each static port and is calculated by subtracting the minimum measurement from the maximum measurement value. Figure 3 shows the calculation of SPA for each system static port. The calculated port angularity values must fall within the range shown in Figure 3. Perform the step height and angularity measurement of the pilot’s and copilot’s static ports as follows: 1. Enter the airplane information (airplane serial number, owner, and date) on a copy of Figure 3. 2. Clean the surface of static ports and fuselage in the measurement region. 3. Place the gauging assembly onto the static port surface as shown in Figure 2. NOTE: Since the gauge is nominally set to 0.100 inch, you must add or subtract the readings from 0.100 inch to determine actual flushness measurement value. This should be completed before calculating any averages. All measurements should have a positive sign. 4. Move to a measurement point as shown in Figure 3 and record the calculated dial indicator reading. Repeat the measurement on all four positions of the static port. Record the maximum and minimum calculated step heights measured. 5. Record the measurements for the other static ports (pilot and copilot). 6. Calculate the step height average (SPF) for each port using the measurements from the four (4) measurement points (add all measurements and divide by four). Enter the SPF values (upper left, lower left, upper right, lower right) as noted in Figure 3. 7. Ensure the SPF values are within the specified tolerance. If not, remove and reinstall the static ports as necessary to ensure RVSM system flushness tolerances are met. 8. Calculate the Static Port Angularity (SPA) value for each port by subtracting the minimum step height recorded from the maximum step height recorded. Enter these SPA values (upper left, lower left, upper right, lower right) as noted in Figure 3. 9. Ensure the SPA values are within the specified tolerance. If not, remove and install the static ports as necessary to ensure the RVSM system angularity tolerances are met.

A27

34-10-00

Page 3 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Table 1 Required Avionics and Air Data Components for RVSM Operation Part Number

Component, Manufacturer and Model

822-0370-461

Air Data Computer (Pilot) ADC-85A

622-3975-004 or -014

Barometric Altimeter (Pilot) Collins ALI-80A

9D-80130-31

Air Data Display Unit (ADDU) IS&S

9B-03508-49

Installation Configuration Module (ICM) IS&S

P/O 9D-80130-31

Alert Annunciator (IS&S)

9B-81040-20

Analogue Interface Unit (Copilot) IS&S

622-9210-005/-006

# 1 and # 2 Transponder Collins TDR-94D

622-9352-003/-004/-005

# 1 and # 2 Transponder Collins TDR-94

622-1270-001

# 1 and # 2 Transponder Collins TDR-90

622-2923-004/-024

Alerter/Preselector, Collins PRE-80A

622-9462-024

Alerter/Preselector, PRE-80C

622-6684-002/-005

Autopilot Panel, Collins APP-65A

622-9785-032/-432

Autopilot Computer(s), Collins APC-65J

622-9724-032

Autopilot Computer, Collins APC-65J

CAUTION: Replacement of the listed components must be accomplished with units of the identical part number except that subsequent dash number components with equivalent functionality are acceptable provided that the change(s) do not affect RVSM capability. The installer must review applicable FAA approved data to determine equivalency of new dash number unit prior to installation.

Page 4 Feb 1/10

34-10-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A NO SCALE

RVSM CRITICAL REGION

B 2 INCHES

1/2 INCH

12 INCHES STATIC PORTS

2 INCHES

CORNER MARKING (EXAMPLE ONLY) DETAIL

12 INCHES

B

NOTE: THE CORNER MARKING MUST BE VISIBLE TO THE PERSON CONDUCTING THE VISUAL INSPECTION. ANY CONTRASTING COLOR OF THE CORNER MARKING IS ACCEPTABLE.

14 INCHES FWD

10 INCHES

DETAIL

A

NOTE: DIMENSIONS SHOWN ARE MINIMUM DIMENSIONS

FL34B 031159AA.AI

RVSM Region Figure 1 (Sheet 1 of 2)

A27

34-10-00

Page 5 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

F.S. 381.75 REF

F.S. 402.75 REF

F.S. 392.25 REF

OXYGEN SERVICE DOOR R.H. SIDE

SHADED AREA UNIVERSAL (PROTRUDING) HEAD RIVETS

FL34B 031271AA.AI

RVSM Region Figure 1 (Sheet 2 of 2)

Page 6 Feb 1/10

34-10-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Static Port Step Height Measurement Figure 2

A27

34-10-00

Page 7 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRPLANE SERIAL #: OWNER: DATE:

NOTES/COMMENTS:

MEASUREMENT POINT U P

U P

FWD

FWD

LHS

RHS

MAX VALUE = MIN VALUE =

MAX VALUE = MIN VALUE =

MAX VALUE = MIN VALUE =

MAX VALUE = MIN VALUE =

SPF UPPER LEFT AVERAGE=

SPF UPPER RIGHT AVERAGE=

SPF LOWER LEFT AVERAGE=

SPF LOWER RIGHT AVERAGE=

REQUIREMENT FOR EACH STATIC PORT: UPPER LEFT (MAX-MIN) =

UPPER RIGHT (MAX-MIN) =

LOWER LEFT (MAX-MIN) =

LOWER RIGHT (MAX-MIN) = REQUIREMENT FOR EACH STATIC PORT: FL34B 031160AA.AI

Static Port Step Height Measurement Log Figure 3

Page 8 Feb 1/10

34-10-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DIAL INDICATOR

GAUGING ASSEMBLY

GAUGE BLOCK

-109 GAUGE BLOCK (4 INCHES x 1/2 INCH x 1/2 INCH)

.001" DIAL INDICATOR

FL34B 031233AA.AI

Step Height Measurement Tool and Dial Indicator Reading Figure 4

A27

34-10-00

Page 9 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIR DATA SYSTEM AND TRANSPONDER CHECK The ADC, Altimeter, and Air Data Display Unit (ADDU) must be maintained in accordance with the applicable Component Maintenance Manual, Airplane Maintenance Manual and Federal Aviation Regulations. However, these components must also meet RVSM specific system accuracy tolerances. The accuracy tolerances for the Pilot’s system are provided in Chart 1. The accuracy tolerances for the Copilot’s system are provided in Chart 2. The transponder output must be checked to ensure accurate reporting of the displayed altitude. It is noted that this requirement to check the air data system and transponder output is in addition to the test specification identified in 14 CFR Part 43, Appendix E. NOTE: To avoid damage to the airplane instruments, follow all cautions and warnings in Chapter 34. This test must be performed on the airplane using calibrated digital test equipment. This test must be performed on both pilot and copilot systems with an Air Data Test Set with an accuracy of 0.003 in. Hg (0.1 mbar ±25 ft). The air data and transponder test should be conducted concurrently. Refer to Charts 1 and 2. a. Perform pitot static system leak check and record leak rate of each system on Chart 1 and 2 as applicable. Refer to 34-00-00. b. Verify that the altimeter Barometric Pressure Counter is set to 29.92 in. Hg. (1013 mb). c.

Apply the reference altitude and Mach (or airspeed) for the condition as shown in Charts 1 and 2.

d. Record the altitude displayed by the pilot and copilot altimeters on Chart 1 and 2 as applicable. Ensure that indicated altitudes are within allowable tolerances shown. e. Verify the reported altitude from the transponder test equipment for the pilot’s and copilot’s transponders. 1. Set ENCD ALTM 1/2 switch to ALTM 1. If equipped with dual transponders set the transponder 1/2 switch to 1. Record the #1 transponder output in Chart 1. 2. Set ENCD ALTM 1/2 switch to ALTM 2. If equipped with dual transponders set the transponder 1/2 switch to 2. Record the #2 transponder output in Chart 2. f.

Repeat steps c through e for all conditions listed in Charts 1 and 2.

Page 10 Feb 1/10

34-10-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 Air Data System Accuracy Test Specifications (Pilot’s System) Test Point

Mach Number

Airspeed (kts)

Applied Altitude (feet)

1

0.270

100.0

2

0.349

3

Pilot’s Altitude (feet)

Nominal Altitude (feet)

Allowable Altitude Tolerance

29000

29000

28947 to 29053

130.0

29000

29000

28947 to 29053

0.428

160.0

29000

28987

28934 to 29040

4

0.505

190.0

29000

28957

28904 to 29010

5

0.289

100.0

32000

32000

31943 to 32057

6

0.345

120.0

32000

32000

31943 to 32057

7

0.401

140.0

32000

31995

31938 to 32052

8

0.457

160.0

32000

31976

31919 to 32033

9

0.538

190.0

32000

31944

31887 to 32001

10

0.309

100.0

35000

35000

34939 to 35061

11

0.399

130.0

35000

34996

34935 to 35057

12

0.459

150.0

35000

34976

34915 to 35037

13

0.517

170.0

35000

34954

34893 to 35015

AIR DATA TEST SET INFORMATION

Transponder #1/ Encd Alt #1 Reported Altitude (feet)

LEAK RATE:________________________________

MANUFACTURER:_____________________________ MODEL:___________________________________ SERIAL NUMBER:_____________________________

DATE OF CALIBRATION:______________________

ACCURACY SPECIFICATION:____________________________________________________________

A27

34-10-00

Page 11 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 Air Data System Accuracy Test Specifications (Copilot’s System) Test Point

Mach Number

Airspeed (kts)

Applied Altitude (feet)

1

0.270

100.0

2

0.349

3

Copilot’s Altitude (feet)

Nominal Altitude (feet)

Allowable Altitude Tolerance

29000

29000

28946 to 29054

130.0

29000

29000

28946 to 29054

0.428

160.0

29000

28987

28933 to 29041

4

0.505

190.0

29000

28957

28902 to 29011

5

0.289

100.0

32000

32000

31946 to 32054

6

0.345

120.0

32000

32000

31946 to 32054

7

0.401

140.0

32000

31995

31941 to 32049

8

0.457

160.0

32000

31976

31923 to 32031

9

0.538

190.0

32000

31944

31890 to 31999

10

0.309

100.0

35000

35000

34945 to 35055

11

0.399

130.0

35000

34996

34941 to 35050

12

0.459

150.0

35000

34976

34922 to 35032

13

0.517

170.0

35000

34954

34899 to 35009

Transponder #2/Encd Alt #2 Reported Altitude (feet)

AIR DATA TEST SET INFORMATION

LEAK RATE:________________________________

MANUFACTURER:__________________________

MODEL:___________________________________

SERIAL NUMBER:__________________________

DATE OF CALIBRATION:______________________

ACCURACY SPECIFICATION:____________________________________________________________

Page 12 Feb 1/10

34-10-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

IN-FLIGHT AUTOPILOT (ALTITUDE HOLD) CHECK a. During normal cruise flight at an altitude between FL250 and FL350 (Baro 29.92 In.Hg. or 1013 mb), press the ALT HOLD PUSH ALTM1/ALTM2 switch to select ALTM2. Engage the autopilot in altitude hold mode and any appropriate lateral mode. Allow the airplane to stabilize on the selected altitude. The air must be stable (no turbulence) during this check. b. With the airplane in the normal (cruise) mode and autopilot altitude hold engaged, record the data from primary displays (using Chart 3) every 5 minutes for a flight segment up to 1 hour in length. On longer flights, the data may be recorded every 10 minutes. The maximum altitude deviation shown on the display should not exceed ±70 feet. c.

If the autopilot does not maintain altitude to within ±70 feet from the selected cruise altitude, repeat the autopilot check once again, ensuring the Mach/Airspeed remains constant during the test and the air remains stable during the entire check. If the check still fails, conduct autopilot component and/or servicing checks as specified by Rockwell Collins. Repeat steps a and b as required, ensuring compliance with RVSM altitude hold requirements.

A27

34-10-00

Page 13 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 3 RVSM AUTOPILOT PERFORMANCE TRACKING FORM - CRUISE TEST TIME (MINUTES)

PILOT’S ALTIMETER

COPILOT’S ALTIMETER

PILOT’S MACH

COPILOT’S MACH

PILOT’S KCAS

COPILOT’S KCAS

0:00 0:05 0:10 0:15 0:20 0:25 0:30 0:35 0:40 0:45 0:50 0:55 1:00 AIRPLANE SERIAL #:______________________

DATE:______________________________

ENROUTE TO:____________________________

PILOT:______________________________

NOTES:

Page 14 Feb 1/10

34-10-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PAINTING RVSM CRITICAL REGION CORNER MARKINGS NOTE: The corner marking must be visible to the person performing the visual inspection. Any contrasting color of the corner marking is acceptable. a. Measure a 24-inch X 24-inch area surrounding the static ports on each side of the airplane. Refer to Figure 1 (Sheet 1 of 2), DETAIL A. This is the RVSM critical region. b. Mask the area surrounding the static ports to protect from solvent and paint overspray using a barrier material and adhesive tape. c.

Clean the area to be painted with a clean cloth dampened with isopropyl alcohol.

d. Make a template by cutting L-shaped notches in card stock or similar material to the dimensions referenced in Figure 1 (Sheet 1 of 2), DETAIL B. Tape the template to the side of the fuselage (to identify the RVSM critical region) using adhesive tape. Apply adhesive tape and barrier material as required to prevent overspray. e. Apply urethane paint (MIL-C-83286) to the L-shaped cutout notch areas. Allow adequate drying time.

A27

34-10-00

Page 15 Feb 1/10

Raythwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ATTITUDE AND DIRECTION

MAINTENANCE PRACTICES

STANDBY COMPASS CALIBRATION compass card for magnetic error is accomplished by removing the correction card plate the compensator with a brass or other nonmagnetic screwdriver. Calibrate the standby compass to a

Correction of the

and

adjusting

rose or

compass a.

b.

standby

by

use

of

a

performed

calibration is

Compass

precision

calibrated under the

1.

Both

2.

All avionics ON

3.

Both

4.

Windshield electric heat OFF

5.

Windshieldwipers

6.

Pitot heatOFF

7.

Stallwarning

8.

Air-conditionerand blowerOFF

Set the

lining

sight

compass.

following

conditions:

engines running

generatorsON

heatOFF

adjustment

up the dot

on

OFF

screws

of the compensator

Zero

on zero.

position of the adjustment

screws

is obtained

by

the compensator frame.

CAUTION: The North-South and East-West

adjustment screws will stop after approximately 3/4 rotation. DO NOT misalign the magnets until compass compensation is

FORCE BEYOND THE STOPS, since this would

impossible. Align the aircraft to actly NORTH.

c.

d.

a

magnetic

Align the aircraft to a magnetic

NORTH

EAST

heading. Adjust the N-S adjustment

heading. Adjust the

E-W adjustment

screw

screw

until the compass reads

until the compass reads

ex-

exactly

EAST. e.

Align

screw

f.

the aircraft to

until this

error

a

magnetic SOUTH heading. by one half.

Align the aircraft to a magnetic WEST heading.

until the

error

Note the

resulting

SOUTH

error.

Adjust

the N-S

adjustment

is reduced

is reduced to

one

Note the

resulting WEST error. Adjust the

E-W

adjustment screw

half.

g. Align the aircraft in successive magnetic 30" headings and record all errors on the inner ring of the deviation 10" of the actual aircraft card of the compass. In each position the standby magnetic compass should read within

magnetic heading. NOTE:

A21

Steps

c.

through

g. may be

repeated

as

necessary to obtain

an

accuracy of

10" at each 30"

34-20-00

heading.

Oct

31/06Page

201

Raltheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AVIONICS COOLING BLOWER OPERATIONAL CHECK AIRPLANES WITH EFIS KA-33 COOLING BLOWER Perform

an

operational

test as follows:

a.

Applyexternal powertotheairplane.

b.

Turn BA~TswitchtoON.

c.

Place EXT PWR switch to ON.

d.

Place the INVERTER select switch to the No. 1

e.

PlaceAVIONICS masterswitchtoON.

f.

Place EFIS power switches to ON.

g.

Visually verify the KA-33 cooling blower,

h.

Place EFIS power switches to OFF.

i.

Place AVIONICS master switch to OFF.

j.

Place the INVERTER select switch to OFF.

k.

Place EXT PWR switch to OFF.

I.

Turn BATT switch to OFF.

m.

Remove external power from the

Oct

or

No. 2

position.

located behind instrument

panel

on

the

pilot’s side, is operating.

airplane.

34-20-00

A21

C H A PT E R

OXYG IE N

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 35 - OXYGEN TABLE OF CONTENTS SUBJECT

PAGE 35-00-00

Oxygen - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Oxygen - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Oxygen System Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Oxygen System Purging . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Oxygen Cylinder Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Oxygen Cylinder Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Passenger Oxygen Shutoff Valve Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Passenger Oxygen Shutoff Valve Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Passenger Cabin Oxygen Mask Container Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .206 Passenger Cabin Oxygen Mask Container Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .206 Passenger Cabin Oxygen Box Housing Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .207 Passenger Cabin Oxygen Box Housing Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .207 Oxygen System Low Pressure Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Oxygen System High Pressure Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Passenger Oxygen Shutoff Valve O-Ring Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Oxygen Mask Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Cabin Section Oxygen Mask Flow Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Barometric Pressure Switch Check. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Method 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Method 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Method 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213

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35-CONTENTS

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

35-LOEP

1

Feb 1/10

35-CONTENTS

1

Feb 1/10

35-00-00

1 thru 8 201 thru 215

Feb 1/10 Feb 1/10

A27

35-LOEP

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 35-00-00

OXYGEN - DESCRIPTION AND OPERATION The oxygen cylinder is serviced through a fill valve located in the oxygen service panel on the right side of the aft fuselage. The high pressure system has two pressure gages, one gage is located in the copilots lower instrument panel for in-flight use and the other is located in the oxygen service panel for checking oxygen pressure when filling the system. Oxygen cylinders are available in three sizes, 50, 77 and 115 cubic feet (Ref. Figure 1, Figure 2, Sheet 1, Figure 2, Sheet 2, Figure 3, and Figure 4). There are two oxygen-operated pressure switches in the system. One switch is located in the panel above and aft of the copilots position. This switch operates the OXY NOT ARMED annunciator on the instrument panel and advises the pilot to pull the PULL ON SYSTEM READY control knob to arm the system and extinguish the annunciator. The other oxygen pressure switch is located in the ceiling in the aft passenger compartment. Oxygen pressure activates the switch and illuminates PASS OXY ON annunciator on the instrument panel, advising the crew that the masks are deployed and the oxygen is available to the passengers. The shutoff valve and regulator attached to the end of the oxygen cylinder regulates the oxygen flow by a push/pull control lever. To arm the oxygen system, pull the PULL ON SYSTEM READY control knob located on the left side of the pedestal. The regulator is constant flow and supplies low pressure oxygen through tubing to the outlets. The barometric pressure switch located in the upper sidewall, forward of the right hand emergency exit (F.S. 158.0 and W.L. 135.5), automatically deploys the passenger oxygen masks when the cabin altitude reaches 12,500 feet. When activated, oxygen pressure is released to the container boxes and a plunger extends, opening the doors and dropping the masks. After the masks are deployed, pull the oxygen valve lanyard pin for oxygen to flow to each mask. When the masks are no longer required, reinsert the lanyard pin to stop the flow of oxygen. In the event of cabin depressurization, the barometric pressure switch is automatically activated and oxygen is supplied to the passenger masks. If the barometric pressure switch malfunctions, the pilot may arm the system by pulling out on the PASSENGER MANUAL DROP OUT control knob located on the right side of the pedestal. The PULL ON SYSTEM READY control in the crew compartment must be on to supply oxygen to the crew. A first aid oxygen mask is provided in the toilet compartment in the aft fuselage. Oxygen is released to the mask by a manual ON/OFF valve located in the overhead container box. Pull out on the PULL ON SYSTEM READY control knob located on the pedestal to supply oxygen to the first aid mask.

SPECIAL TOOLS AND RECOMMENDED MATERIALS The special tools and recommended materials listed in Chart 1 and Chart 2 meet federal, military and/or supplier specifications and are provided for reference only. The materials listed are not specifically require by Hawker Beechcraft Corporation. Any product conforming to the specification may be used subject to availability. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

A27

35-00-00

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 Special Tools and equipment Tool Name 1. Shutoff Valve and Test Harness

Specification

Supplier

TK1738-5 or 3712G4B Hawker Beechcraft Corporation 9709 E. Central Wichita KS 67201

Use Perform system check.

2. Pressure Gage (0-100 psi) TK1738-6

Hawker Beechcraft Corporation 9709 E. Central Wichita KS 67201

Perform system check.

3. Jumper Hose (2) and Adapter

Size 6

Local

Oxygen low pressure test harness.

4. Tool

4460102-2

Hawker Beechcraft Corporation Authorized Outlets

To install O-rings in passenger oxygen shutoff valve.

Chart 2 Recommended Materials Material

Specification

Product

Supplier

1. Oxygen

MIL-O-27210

Obtain Locally

2. Anti-Seize Tape

A-A-58092

Obtain Locally

3. Lubricant

Silicone 4 Compound

4. Oxygen Leak Detector Kit MIL-L-25567 5. Disinfectant

6. Isopropyl Alcohol

8. Lubricant

Page 2 Feb 1/10

Obtain Locally QS4

TT-I-735 or MIL-I-10428A

7. Parts and Instructions Kit

35-00-00

Brulin and Company P.O. Box 270 Indianapolis, IN 46206 Obtain Locally

4460102-1

Krytox 240AC

Dow Corning 3901 S. Saginaw Rd. Midland, MI 48641

Hawker Beechcraft Corporation Authorized Outlets

RAPID 4460102-5 BOC Edwards (supersedes 4460102-3) 301 Ballardvale Street Wilmington, MA 01887

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CABIN OXYGEN PRESSURE SENSE SWITCH D

D

D

D

D

S

D

1000 500

1500

USE NO OIL

OXYGEN SYSTEM FILL PORT

0

(B300C ONLY)

2000 OXYGEN SUPPLY PRESSURE

PSI

DIAL PRESSURE GAGE

CABIN HEADLINER OXYGEN COMPARTMENTS OXYGEN CONTROL

TRIPLE FED BUS

PASS OXY ON

BAROMETRIC PRESSURE SWITCH NO

OXY NOT ARMED

2 1000 500

1500

USE NO OIL 0

2000 OXYGEN SUPPLY PRESSURE

COPILOT'S PRESSURE GAGE

NC TRIPLE FED BUS

PSI

5A CB S

OXYGEN SUPPLY CYLINDER

SUPPLY PRESSURE REGULATOR

HIGH PRESSURE

ANNUNCIATOR PANEL

5A

This Page Intentionally Left Blank HIGH PRESSURE OVERBOARD DISCHARGE

CABIN OXYGEN SHUT-OFF VALVE (MANUAL AND SOLENOID OPERATED)

COPILOT'S OXYGEN OUTLET VALVE

FIRST AID MASK AND CONTAINER

PASSENGER MAUAL DROPOUT CONTROL KNOB (PUSH/PULL CONTROL)

LOW PRESSURE D

PULL ON SYSTEM READY CONTROL KNOB (PUSH/PULL CONTROL)

DOUBLE MASK BOX S

PILOT'S OXYGEN OUTLET VALVE

SINGLE MASK BOX

FL35B 985665AA.AI

Oxygen System Functional Schematic Figure 1

A27

35-00-00

Page 3 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This Page Intentionally Left Blank

Page 4 Feb 1/10

35-00-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SINGLE MASK CONTAINER

PASSENGER OVERRIDE CONTROL CABLE

COCKPIT OXYGEN GAGE

OXYGEN CREW MASK (DILUTER DEMAND)

E

FIRST AID MASK AND CONTAINER COCKPIT GAGE LINE AND FILLER PORT

PRESS SWITCH ASSY

B C

OXYGEN CONTROL CABLE

D

FS 143.00

A FS 158.00

HIGH PRESSURE OVERBOARD RELIEF

FS 299.75

FS 168.75

PASSENGER DOUBLE MASK CONTAINER OXYGEN PRESSURE SWITCH

FILLER VALVE ASSY OXYGEN GAGE

SHUTOFF VALVE MANUAL OVERRIDE

FS 381.75 OXYGEN CYLINDER GAGE LINE

LOW PRESSURE

FILL LINE OFF

DETAIL

DETAIL

A

B

HIGH PRESSURE OVERBOARD RELIEF ON

CABIN LOW PRESSURE

BAROMETRIC PRESSURE SWITCH

DETAIL

C

CONSOLE

OXYGEN ON/OFF CONTROL

CONSOLE

MANUAL OVERRIDE

DETAIL

D

DETAIL

E

FL35B 985666AA.AI

Oxygen System (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) Figure 2 (Sheet 1 of 2)

A27

35-00-00

Page 5 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SINGLE MASK CONTAINER

PASSENGER OVERRIDE CONTROL CABLE

COCKPIT OXYGEN GAGE

OXYGEN CREW MASK (DILUTER DEMAND)

E

FIRST AID MASK AND CONTAINER COCKPIT GAGE LINE & FILLER PORT

PRESS SWITCH ASSY

B C

A D OXYGEN

FS 143.00

CONTROL CABLE

FS 158.00

FS 289.87

FS 168.75

PASSENGER DOUBLE MASK CONTAINER FILLER VALVE ASSY

OXYGEN PRESSURE SWITCH

SHUTOFF VALVE MANUAL OVERRIDE

OXYGEN GAGE

HIGH PRESSURE OVERBOARD RELIEF

FS 381.75 OXYGEN CYLINDER GAGE LINE

LOW PRESSURE

FILL LINE OFF

DETAIL

B

HIGH PRESSURE OVERBOARD RELIEF

CABIN LOW PRESSURE

ON DETAIL

BAROMETRIC PRESSURE SWITCH

A

DETAIL

C

CONSOLE

OXYGEN ON/OFF CONTROL

CONSOLE

MANUAL OVERRIDE

DETAIL

D

DETAIL

E FL35B 985667AA.AI

Oxygen System (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 2 (Sheet 2 of 2)

Page 6 Feb 1/10

35-00-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SINGLE MASK CONTAINER

PASSENGER OVERRIDE CONTROL CABLE

COCKPIT OXYGEN GAGE

OXYGEN CREW MASK (DILUTER DEMAND)

E

FIRST AID MASK AND CONTAINER COCKPIT GAGE LINE & FILLER PORT

PRESS SWITCH ASSY

B C A

D OXYGEN

FS 143.00

CONTROL CABLE

FS 158.00

PASSENGER DOUBLE MASK CONTAINER

OXYGEN PRESSURE SWITCH

SHUTOFF VALVE MANUAL OVERRIDE

HIGH PRESSURE OVERBOARD RELIEF

FS 299.75

FS 168.75

FILLER VALVE ASSY

FS 381.75 OXYGEN CYLINDER GAGE LINE

LOW PRESSURE

OXYGEN GAGE

FILL LINE OFF

DETAIL

B

HIGH PRESSURE OVERBOARD RELIEF

CABIN LOW PRESSURE

ON DETAIL

BAROMETRIC PRESSURE SWITCH

A

DETAIL

C

CONSOLE

OXYGEN ON/OFF CONTROL

CONSOLE

MANUAL OVERRIDE

DETAIL

D

DETAIL

E FL35B 985679AA.AI

Oxygen System (FM-1 and After) Figure 3

A27

35-00-00

Page 7 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Oxygen System Masks Figure 4

Page 8 Feb 1/10

35-00-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OXYGEN - MAINTENANCE PRACTICES

200200200

OXYGEN SYSTEM SERVICING WARNING: Avoid making sparks and keep all burning cigarettes or fire away from the vicinity of the airplane. Make sure that the oxygen shutoff valve control is in the closed position. Inspect both the airplane and charging cart filler connections for cleanliness before attaching the filler valve of the charging cart. Make certain that your hands, tools and clothing are clean, particularly of grease or oil, for these contaminants will ignite upon contact with pure oxygen under pressure. As a further precaution against fire, open and close all oxygen valves slowly during filling. CAUTION: Use only aviators breathing oxygen (1, Chart 2, 35-00-00) for servicing the oxygen system. Do not use oxygen intended for medical purposes or such industrial uses as welding. Such oxygen may contain excessive moisture that could freeze in the valves and lines of the oxygen system. Access to the pressure indicator and filler valve of the oxygen system may be gained through an access door located on the right side of the aft fuselage (Ref. Figure 3 and Figure 4, 35-00-00, Detail B). To recharge the oxygen system, remove the protective cap from the filler valve and attach the hose from an oxygen recharging unit to the filler valve. Make sure that the airplane oxygen system and the servicing equipment are properly grounded before servicing the system. To prevent overheating, fill the oxygen system slowly by adjusting the recharging rate with the pressure regulating valve on the recharging unit. All oxygen cylinders should be filled to 1850 ± 50 psi at a temperature of 70° F. This pressure may be increased an additional 3.5 psi for each degree of increase in temperature; similarly, for each degree of drop in temperature, reduce the pressure for the cylinder by 3.5 psi. When the oxygen system is properly charged, turn off the oxygen, disconnect the filler hose from the filler valve and replace the protective cap on the filler valve. If at any time, in the process of servicing and purging the system or replacing the oxygen cylinder, it becomes necessary to disconnect a fitting, the threads of the fitting should be wrapped with anti seize tape (2, Chart 2, 35-00-00) prior to being connected back into the system. NOTE: Refer to Advisory Circular 43.13-1A for the additional servicing precautions recommended by the FAA on the oxygen systems.

OXYGEN SYSTEM PURGING Offensive odors may be removed from the oxygen system by purging. The system should also be purged any time system pressure drops below 50 psi or the lines are left open. Purging is accomplished by connecting a recharging unit into the system and permitting oxygen to flow through the lines and outlets until any offensive odors have been carried away. WARNING: Avoid making sparks and keep all burning cigarettes or fire away from the vicinity of the airplane when the outlets are in use. Inspect the filler connections for cleanliness before attaching the filler valve. Make certain that your hands, tools and clothing are clean, particularly of grease or oil, for these contaminants will ignite upon contact with pure oxygen under pressure. As a further precaution against fire, open and close all oxygen valves slowly during filling. a. Open the cabin door to provide air circulation through the airplane. b. Open the access panel for the filler valve, remove the protective cap and attach the hose from the oxygen recharging unit to the filler valve. c.

Pull out the PULL ON SYSTEM READY control knob located on the left side of the pedestal.

A27

35-00-00

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL NOTE: The O-ring in the control cable may be lubricated with Silicone (3, Chart 2, 35-00-00) to reduce friction during operation of the cable. d. Pull out the PASSENGER MANUAL DROP OUT control knob to automatically drop the oxygen masks from their containers. e. Pull the lanyard pin to open the oxygen flow valve in each of the oxygen mask outlets to vent the line. f.

Adjust the recharging unit pressure regulator to deliver 50 psi of pressure to the system.

g. Allow the system to purge for one hour. h. If any offensive odor still lingers, continue purging the system for an additional hour. i.

If such odors still remain, replace the supply cylinder.

j.

After the system has been adequately purged, push the PASSENGER MANUAL DROP OUT control knob back to the OFF position.

k.

Rotate the valve actuator arm aft to the armed position and insert the lanyard pin.

l.

Pack the oxygen masks back into their containers and latch the mask container doors.

m. Position the door so that the plunger can strike the block on the door when activated.

OXYGEN CYLINDER REMOVAL a. Access to the cylinder may be gained by removal of the access panel on the right side of the airplanes belly, immediately aft of the aft pressure bulkhead. WARNING: Avoid making sparks and keep all burning cigarettes or fire away from the vicinity of the oxygen cylinder. Make sure that your hands, tools and clothing are clean, particularly with respect to oil or grease, for those contaminants will ignite upon contact with pure oxygen under pressure. b. Close the oxygen supply cylinder valve by pushing in on the PULL ON SYSTEM READY control cable knob. c.

Disconnect the oxygen line fittings (2) from the regulator valve assembly (4) (Ref. Figure 201).

d. Cap the open lines immediately with clean metal fittings to prevent contaminants in the lines. e. Disconnect the control cable (6) from the regulator valve control lever (3). f.

Loosen the two wing nuts connected to the T-bolts (5) on the cylinder brackets (7).

g. Raise the cylinder brackets (7) and remove the cylinder (1) from the brackets.

OXYGEN CYLINDER INSTALLATION a. Place the new cylinder (1) in the brackets (7) and again with fittings (Ref. Figure 201). b. Tighten the two T-bolt wing nuts on the mounting brackets. c.

Carefully inspect the fittings for cleanliness and freedom from contaminants.

d. Connect the oxygen line fittings (2) to the regulator valve assembly (4). Page 202 Feb 1/10

35-00-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL e. Connect the control cable (6) to the regulator control lever (3). f.

Open the regulator valve assembly (4) on the oxygen cylinder (1).

g. Test the connections for leaks with the oxygen leak detector kit (4, Chart 2, 35-00-00). h. Safety wire the wing nuts to the T-bolts (5). i.

Install access panel.

PASSENGER OXYGEN SHUTOFF VALVE REMOVAL a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Pull the OXY circuit breaker to disarm the passenger oxygen valve.

d. Close the oxygen regulator valve on the oxygen supply cylinder by pushing in on the PASSENGER MANUAL DROP OUT control handle. e. Push in on the PULL ON SYSTEM READY control knob. f.

Remove the sidewall panels between F.S. 158 and F.S. 168.75 (Ref. UPPER CABIN SIDEWALL WINDOW PANEL REMOVAL, 25-20-11).

g. Disconnect electrical wires from the shutoff valve (3) (Ref. Figure 202). h. Loosen the nut (16), bushing (14) and washer (15) on the retaining pin (12) holding the control cable (9) and remove the cable from the pin. i.

Disconnect the oxygen tube assembly (6) from the cabin shutoff valve and cap all lines immediately to prevent contaminants from entering the oxygen system.

j.

Remove the cabin shutoff valve (3) from the mounting bracket by removing the screws (4).

k.

Remove tee-fitting (8) and union (1) from the shutoff valve (3). Remove and replace all O-rings (2).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1. OXYGEN CYLINDER 2. FITTINGS-OXYGEN LINES 3. REGULATOR CONTROL LEVER 4. REGULATOR VALVE ASSEMBLY 5. WING NUTS/T-BOLT 6. CONTROL CABLE 7. MOUNTING BRACKETS

2

A

1

3

4

5 7

6

1

2 1

6

6

2

4 3

2

3

4

DETAIL

A

2

FL35B 985587AA.AI

Oxygen Cylinder and Regulator Replacement Figure 201

Page 204 Feb 1/10

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A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1. UNION 2. O-RING 3. SHUTOFF VALVE 4. SCREW 5. NUT 6. TUBE ASSEMBLY 7. SCREW 8. TEE 9. CONTROL CABLE 10. ATTACHMENT CLAMP 11. CONTROL CABLE 12. PIN 13. SHUTOFF VALVE LEVER 14. BUSHING 15. WASHER 16. NUT

3 2

1

13

A

4 2 11

5

10 12

6

16 15

9 7

13 14

8 12

3

9

DETAIL

A FL35B 985602AA.AI

Passenger Oxygen Shutoff Valve Figure 202

A27

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PASSENGER OXYGEN SHUTOFF VALVE INSTALLATION a. Push in on the PULL ON SYSTEM READY control knob to confirm oxygen supply regulator valve is off. b. Install the tee-fitting (8) on the cabin shutoff valve (3). Install new O-rings (2) on the unions. Connect the union (1) to the oxygen supply lines (Ref. Figure 202). c.

Secure the cabin shutoff valve to the mounting bracket with screws (4).

d. Remove the caps from the oxygen lines and reconnect the tube assembly (6) to the cabin shutoff valve (3). e. The PASSENGER MANUAL DROP OUT lever should be in the off position prior to connecting the control cable. Connect the control cable (9) to the pin (12) by inserting the cable in the pin hole and then tightening the nut (16). f.

Perform the leak test procedures after installation of the cabin shutoff valve (Ref. OXYGEN SYSTEM LOW PRESSURE TEST).

g. Connect electrical wires to the solenoid on the cabin shutoff valve. h. Install the sidewall panel between F.S. 158 and 168.75 (Ref. UPPER CABIN SIDEWALL WINDOW PANEL INSTALLATION, 25-20-11). i.

Place the oxygen system in the off position upon completion of cabin shutoff valve installation.

j.

Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

PASSENGER CABIN OXYGEN MASK CONTAINER REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Open the cabin door to provide air circulation through the airplane. b. Pull out the PULL ON SYSTEM READY control knob located on the left side of the pedestal. c.

Pull out the PASSENGER MANUAL DROP OUT control knob located on the right side of the pedestal. The passenger oxygen masks should drop out from their containers.

d. Push in the PASSENGER MANUAL DROP OUT control knob. e. Push in the PULL ON SYSTEM READY control knob. f.

Pull the lanyard pins to open the oxygen flow valves in both of the oxygen masks of the container to be removed to vent the supply line.

g. Disconnect the oxygen supply line from the door actuator valve. h. Remove the four plastic screws and remove the oxygen mask container. i.

Cap the open line immediately with an oxygen clean fitting to prevent contaminants in the line.

PASSENGER CABIN OXYGEN MASK CONTAINER INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the cap from the oxygen supply line. b. Carefully inspect the oxygen supply line fitting for cleanliness and freedom from contaminants.

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A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL c.

Place the oxygen mask container in position and install the four plastic screws.

d. Connect the oxygen supply line to the oxygen mask container door actuator valve. e. Rotate the valve actuator arm aft to the ARMED position and insert the two lanyard pins f.

Pack the oxygen masks and latch the oxygen mask container door.

g. Perform the OXYGEN SYSTEM LOW PRESSURE TEST.

PASSENGER CABIN OXYGEN BOX HOUSING REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Perform the PASSENGER CABIN OXYGEN MASK CONTAINER REMOVAL procedure. b. Remove the four screws and spacers from the oxygen box housing and remove the oxygen box housing. NOTE: Make a note of the spacer positions as the spacers are different sizes.

PASSENGER CABIN OXYGEN BOX HOUSING INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Place the oxygen box housing in position and install the four screws and spacers, make sure that the spacers are installed in the same position that they were removed from. b. Perform the PASSENGER CABIN OXYGEN MASK CONTAINER INSTALLATION procedure.

OXYGEN SYSTEM LOW PRESSURE TEST NOTE: Oxygen used for testing or recharging must be aviator’s breathing oxygen (1, Chart 2, 35-00-00). The following equipment is needed to perform this test: •

The test harness and shutoff valve (1, Chart 1, 35-00-00), a pressure gage (2, Chart 1, 35-00-00), and attaching adapters (3, Chart 1, 35-00-00) may be used for this test. Other equipment of equal testing capabilities may also be used.

•

Pressure gage 0 to 100 psig (1 psig increments and oxygen clean).

•

Tee connector (oxygen clean).

•

Shutoff valve (oxygen clean).

•

Two jumper hoses (3, Chart 1, 35-00-00) (oxygen clean).

•

Leak detector fluid (4, Chart 2, 35-00-00).

A27

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Page 207 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL WARNING: Parts and materials used to assemble the oxygen low pressure test apparatus must be free of contaminants or foreign material. Some contaminants coming in contact with oxygen could cause spontaneous combustion resulting in damage to property and possible injury. Make certain materials used to assemble the test apparatus is oxygen clean. The fabrication of test equipment into a test apparatus is one method of testing the low pressure side of the oxygen system. Connect the test apparatus to the low pressure port on the oxygen system supply regulator and pressurize the system. Pressure leaks in the oxygen system can be monitored on the pressure gauge. Once the leak has been isolated, a more detailed check can be accomplished by using the oxygen leak detector kit (4, Chart 1, 35-00-00). a. Install the oxygen test harness with the test shutoff valve in the open position (Ref. Figure 203). b. Pull out on the PULL ON SYSTEM READY control knob. c.

Allow 10 minuets for the oxygen system to stabilize.

d. Monitor the test system’s pressure gage for pressure increase. e. Close the shutoff valve on the test apparatus. NOTE: When the shutoff valve is closed, oxygen pressure is held in the emergency and crew outlets system. This tests the emergency mask, crew masks and shutoff valve for possible leakage. f.

Monitor the pressure gauge on the test apparatus for pressure loss not to exceed 5 psi within 15 minuets.

g. If leakage exceeds 5 psi in 15 minutes, apply oxygen leak detector solution (4, Chart 2, 35-00-00) to suspected area. After locating the leak, make the necessary repairs and retest the system. h. Pull out on the PASSENGER MANUAL DROP OUT control knob. i.

Open the test shutoff valve and recharge the oxygen system to 70 psi and allow pressure to stabilize for 3 minutes. The oxygen mask container doors should open and the masks dropped down for use. NOTE: When the passenger shutoff valve is opened, oxygen flows to the passenger stations causing the test gage to drop momentarily, then stabilize.

j.

Close the test apparatus shutoff valve. NOTE: This procedure checks the passenger oxygen mask containers, passenger oxygen solenoid shutoff valve and associated plumbing.

k.

Monitor the pressure gage on the test apparatus for pressure loss not to exceed 5 psi within 15 minuets.

l.

If leakage exceeds 5 psi within 15 minuets, apply oxygen leak detector solution (4, Chart 2, 35-00-00) to the suspected area. After locating the leak, make the necessary repairs and retest the system.

m. Push in on the PULL ON SYSTEM READY control knob. n. Open the shutoff valve on the test apparatus to allow the pressure to bleed down. o. Push in on the PASSENGER MANUAL DROP OUT control knob. p. Release any residual system line pressure by activating one of the passenger masks (pull the lanyard pin out and then replace it several seconds later). q. Repack the oxygen mask, latch the mask container doors and remove the test apparatus from the pilot’s oxygen outlet.

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35-00-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL r.

Position the door so that the plunger can strike the block on the door when activated.

s.

Remove the oxygen test harness.

t.

Reconnect the oxygen supply line to the cabin low pressure fitting.

Oxygen Leak Detection Kit Figure 203

OXYGEN SYSTEM HIGH PRESSURE TEST NOTE: Oxygen used for testing or recharging must be aviators breathing oxygen (1, Chart 2, 35-00-00). a. With a pressure of 1,500 to 1,800 psi in the oxygen cylinder, observe that there is NO pressure loss in 30 minuets. b. If leakage is noted, apply leak detector solution to the area. After locating the leak, make the necessary repairs and retest the system. Wipe the area clean and dry after using leak test solution.

PASSENGER OXYGEN SHUTOFF VALVE O-RING REPLACEMENT NOTE: The solenoid-operated oxygen shutoff valve with manual override is located behind the forward right cabin window panel just above the window between F.S. 158.00 and 168.75. a. Remove the valve for O-ring replacement (Ref. PASSENGER OXYGEN SHUTOFF VALVE REMOVAL). b. At the intervals specified, disassemble the passenger oxygen shutoff valve and replace the O-rings (Ref. Chapter 5-00-00).

A27

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 1. Because this valve is actuated so infrequently in normal service, there is the possibility of the O-rings deteriorating, which could cause the valve to leak oxygen (O-ring deterioration does not hinder valve operation). 2. The following kits are required when replacing the O-rings: O-rings and instructions (7, Chart 2, 35-00-00), lubricant (8, Chart 2, 35-00-00) and reusable tool (4, Chart 1, 35-00-00). c.

Install the valve after O-ring replacement (Ref. PASSENGER OXYGEN SHUTOFF VALVE INSTALLATION).

OXYGEN MASK CLEANING To open the lid to the passenger oxygen mask container, pull out on the PULL ON SYSTEM READY and the PASSENGER MANUAL DROP OUT controls. To gain access to the crew masks reach overhead and pull the crew masks from their stowed position. a. Wear protective gloves throughout the cleaning procedure. b. Prepare a cleaning solution by mixing one ounce of disinfectant (5, Chart 2, 35-00-00) with 2 gallons of hot distilled water (140° F maximum) or isopropyl alcohol (6, Chart 2, 35-00-00). Any disinfectant compatible with oxygen and plastic may be used. c.

Dip a soft cotton cloth or gauze pad in cleaning solution and wipe the inside and outside of the mask face piece. CAUTION: Do not allow any cleaning solution to enter the reservoir bag or flow indicator. Be careful that the dilution valve diaphragm on the crew masks is not damaged.

d. Using a soft cotton cloth dampened with cleaning solution, wipe the reservoir bag, flow indicator and oxygen tubing. e. Dip a soft cotton cloth in room temperature distilled water and rinse all areas which were previously cleaned. f.

Release any residual system line pressure by activating one of the passenger masks (pull the lanyard pin out and then replace it several seconds later).

g. Allow the masks to thoroughly dry, stow the masks, and close the containers. h. Position the door so that the plunger can strike the block on the door when activated.

CABIN SECTION OXYGEN MASK FLOW CHECK a. Pull out the PULL ON SYSTEM READY control knob located on the left side of the pedestal. b. Wait 25 to 30 seconds for the system to load. Then pull out the PASSENGER MANUAL DROP OUT control knob located on the right side of the pedestal. The passenger oxygen masks should drop out of their containers. c.

Individually check each passenger mask for flow by removing the lanyard pin located in the mask container assembly and observing the mask flow indicator. If flow is indicated reinstall the lanyard pin and check the next mask. If flow is not indicated mark the mask for replacement.

d. After each passenger mask has been checked, remove the cover from the first-aid oxygen-mask container located overhead in the toilet compartment of the aft fuselage. e. Remove the first-aid oxygen mask from its container.

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35-00-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL f.

Place the ON/OFF valve located in the first-aid oxygen-mask container in the ON position. Check for flow in the first-aid mask by observing the flow indicator. If flow is not indicated mark the mask for replacement. Place the ON/OFF valve in the OFF position.

g. Push in the PASSENGER MANUAL DROP OUT control knob. h. Push in the PULL ON SYSTEM READY control knob. i.

Replace any oxygen masks that have been marked for replacement.

j.

Release any residual system line pressure by activating one of the passenger masks (pull the lanyard pin out and then replace it several seconds later).

k.

Stow the masks and close the containers.

l.

Position the door so that the plunger can strike the block on the door when activated.

BAROMETRIC PRESSURE SWITCH CHECK NOTE: If this procedure is being performed due to a Special Inspection requirement of Chapter 5-21-05, METHOD 1 or 2 must be performed. If the procedure is being performed solely to check the operation of the pressure switch, then METHOD 1, 2 or 3 may be performed. If this procedure is being performed due to a Special Inspection requirement of Chapter 5-21-05, perform the CABIN ALTITUDE WARNING PRESSURE SWITCH CHECK, 21-30-00, in conjunction with this procedure. METHOD 1 WARNING: Comply with standard FAA regulations for oxygen usage when performing this check. NOTE: It is not necessary to exceed an altitude of 13,000 feet while performing this check. NOTE: The oxygen system must be on and armed while performing this check. a. Fly the unpressurized airplane to the altitude at which the oxygen masks deploy. b. As airplane altitude increases, note the altitude on a certified altimeter static test set or hand held certified altimeter set to 29.92 inch Hg. Make sure the following events occur at 12,000 to 15,000 feet: 1. PASS OXY ON annunciator illuminates. 2. Cabin oxygen masks deploy. c.

If this procedure is being performed due to a Special Inspection requirement of Chapter 5-21-05, pull the lanyard pin out and make sure oxygen flows, then replace the lanyard pin every oxygen mask.

d. The pilot shall then descend to an altitude below 10,500 ft. e. As the airplane descends, note the altitude at which the advisory annunciator extinguishes. The annunciator light shall extinguish at 10,500 feet or higher. f.

If the requirements of b and e are met, the barometric switch is operating properly and the system is operating as designed.

g. Release any residual system line pressure by activating one of the passenger masks (pull the lanyard pin out and then replace it several seconds later).

A27

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL h. Repack the masks and latch the mask container doors. i.

Position the door so that the plunger can strike the block on the door when activated.

j.

If required, refill the oxygen tank (Ref. SERVICING - MAINTENANCE PRACTICES, 12-10-00).

METHOD 2 a. Fabricate a vacuum chamber from 3 inch schedule 40 PVC plumbing pipe or suitable equivalent, 4 to 8 inches long with two end caps. One end cap is permanently attached to the plumbing pipe with PVC cement then drilled and tapped for an AN816-4D fitting. The other end cap is a removable closure. Material required for the vacuum chambers may be obtained locally. Refer to Figure 204 or Figure 205 for an example of a fabricated vacuum chamber. b. Remove the attaching hardware and the barometric pressure switch from the airplane. Do not disconnect the wires from the pressure switch. Cut the tie wraps from the wire harness to allow adequate length to place the pressure switch in the vacuum chamber. NOTE: The barometric pressure switch is located in the upper sidewall, forward of the RH emergency exit (F.S. 158.0 and W.L 135.5) c.

Suspend the chamber from the airplane structure to eliminate strain on the pressure switch wires. Place the pressure switch inside the vacuum chamber with the wires exiting the chamber from the locations referenced in Figure 204 or Figure 205. Install the end cap then apply plumbers putty or equivalent around the wires to seal the chamber.

d. Apply electrical power to the airplane. NOTE: The oxygen system must be on and armed while performing this check. e. Connect an altimeter test unit or similar device with a certified altimeter to the fitting on vacuum chamber. f.

Slowly increase the vacuum in the chamber and check for leaks. Make adjustments to the end cap and apply plumbers putty or equivalent as required to reduce leak rate to a manageable amount. Total sealing may not be possible.

g. Slowly increase the vacuum in the chamber and note the altitude on the test unit at which the following events occur at 12,000 to 12,500 feet: 1. PASS OXY ON annunciator illuminates. 2. Cabin oxygen masks deploy. h. If this procedure is being performed due to a Special Inspection requirement of Chapter 5-21-05, pull the lanyard pin out and make sure oxygen flows, then replace the lanyard pin in every oxygen mask. i.

Slowly decrease the vacuum in the chamber and note the altitude on the test unit at which the PASS OXY ON annunciator light extinguishes. The annunciator light shall extinguish at 10,500 feet or higher. Allow the vacuum chamber to return to atmospheric pressure.

j.

The switch must be replaced if it does not meet these specifications.

k.

Disconnect the test unit from the fitting on the vacuum chamber.

l.

Disconnect electrical power from the airplane.

Page 212 Feb 1/10

35-00-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL m. Remove the pressure switch from the vacuum chamber. n. Install the barometric pressure switch with attaching hardware and secure wire harness with tie wraps. o. Release any residual system line pressure by activating one of the passenger masks (pull the lanyard pin out and then replace it several seconds later). p. Repack the masks and latch the mask container doors. q. Position the door so that the plunger can strike the block on the door when activated. r.

If required, refill the oxygen tank (Ref. SERVICING - MAINTENANCE PRACTICES,12-10-00).

METHOD 3 a. Fabricate a vacuum chamber from 3 inch schedule 40 PVC plumbing pipe or suitable equivalent, 4 to 8 inches long with two end caps. One end cap is permanently attached to the plumbing pipe with PVC cement then drilled and tapped for an AN816-4D fitting. The other end cap is a removable closure. Material required for the vacuum chambers may be obtained locally. Refer to Figure 204 or Figure 205 for an example of a fabricated vacuum chamber. b. Remove the barometric pressure switch from the airplane, if required. The barometric pressure switch is located in the upper sidewall, forward of the RH emergency exit (F.S. 158.0 and W.L 135.5). c.

Place the pressure switch inside the vacuum chamber with wires connected to the terminals (COM and NO) of the switch. Route the wires out of the chamber from the location referenced in Figure 204 or Figure 205. Connect an ohmmeter to these wires for the test. Install the end cap then apply plumbers putty or equivalent around the wires to seal the chamber.

d. Connect an altimeter test unit or similar device with a certified altimeter to the fitting on vacuum chamber. e. Slowly increase the vacuum in the chamber and check for leaks. Make adjustments to the end cap and apply plumbers putty or equivalent as required to reduce leak rate to a manageable amount. Total sealing may not be possible. f.

Slowly increase the vacuum in the chamber and check for continuity at the increasing altitude activation point (12,500 +000/-500 feet).

g. After continuity is acquired, slowly decrease the vacuum in the chamber and check for termination of continuity at the decreasing altitude point (10,500 feet minimum). Allow the vacuum chamber to return to atmospheric pressure. h. Disconnect the test unit from the fitting on the vacuum chamber. i.

The switch must be replaced if it does not meet these specifications.

j.

Remove the pressure switch from the vacuum chamber.

k.

Install the barometric pressure switch in the airplane, if required.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

THE END CAP IS PERMANENTLY ATTACHED WITH PVC CEMENT. END CAP IS DRILLED AND TAPPED FOR AN AN816-4D FITTING.

RELIEFS PROVIDED FOR THE PRESSURE SWITCH WIRES AS THEY EXIT.

THIS IS A COMMON PLUMBING CLEAN OUT PLUG. BEFORE USING CLEAN THE RUBBER SEAL AND APPLY SILICONE LUBE.

CLEAN EDGES AND SMOOTH WITH FINE SANDPAPER.

PRESSURE SWITCH WIRES

AN816-4D FITTING PLUMBERS PUTTY

FL21B 032864AA.AI

Vacuum Chamber (Sample) Figure 204

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A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

APPLY PLUMBERS PUTTY TO SEAL AROUND WIRES.

APPLY TAPE TO SEAL THE SLOT AFTER SWITCH IS PLACED INTO VACUUM CHAMBER .

LATCH

WATER TANK TO TOILET BOWL SEAL, CHOOSE ONE THAT FITS INSIDE END CAP. APPLY SMALL BEAD OF PUTTY TO BASE OF SEAL BEFORE INSERTING INTO CAP. COAT FACE OF SEAL WITH SILICONE LUBE.

THE END CAP IS PERMANENTLY ATTACHED WITH PVC CEMENT. END CAP IS DRILLED AND TAPPED FOR AN AN816-4D FITTING FOR ALTIMETER TESTER CONNECTION.

AN816-4D FITTING

FL21B 032865AA.AI

Vacuum Chamber (Sample) Figure 205

A27

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Page 215 Feb 1/10

CHAPTER

PNEUMATIC

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 36

PNEUMATIC

TABLE OF CONTENTS PAGE

SUBJECT 36-00-00

Pneumatic

Description

and

Operation

..................1 .201

Pneumatic- Maintenance Practices Pressure

RegulatorValve Adjustment

................201

36-CONTENTS

1/08Page May

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

36-LOEP

1

May 1/08

36-CONTENTS

1

May 1/08

1

May 1/08 May 1/08

36-00-00

201

A24

Pages

36-LOEP

1/08Page May

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PNEUMATIC Bleed air at

DESCRIPTION AND OPERATION

psi pressure is obtained from both engines and flows fuselage. Check valves (Ref. Figure 1) are installed to prevent reverse flow during single engine operation. Downstream from the tee all bleed air passes through an 18 psi regulator which incorporates a relief valve set to operate at 21 psi in case of regulator failure. This regulated bleed air is manifolded to supply pneumatic pressure to the surface deicers, door seal, bleed air failure warning system and the cabin window defrost system, and to provide forcing flow and pressure for the vacuum ejector. Bleed air is extracted from the third stage of the engine compressor at a maximum temperature of 650" F and is cooled approximately 70" above ambient temperature at the tee in the fuselage due to heat transfer in the pneumatic a

maximum flow rate of 1 to 1-112 Ib/min at 90-120

through pneumatic

lines to

a common

tee located in the

plumbing.

PNEUMATIC PRESSURE GAGE

WECTOR LH ENGINE BLEED AIR

RH ENGINE

TO VACUUM REG AND

BLEED AIR

INSTRUMENT PLUMBING

N

L-,--

SOLENOID DOOR SEAL

L

DEICE VALVE

REGULATOR

REGULATOR AND RELIEF VALVE

CHECK VALVES TO RH WING

TO LH WING

DEICER BOOTS

DEICER 800TS TO EMPENNAGE DEICER BOOTS

Pneumatic Pressure

System Schematic

Figure

A24

350-190-5

1

36-00-00

MaPya~leg:Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

PNEUMATIC

PRESSURE REGULA TOR VAL VE ADJUSTMENT the pressure regulator valve, which is mounted under the right seat deck immediately forward of the aft will not require adjustment. The unit is preset at the factory; however, the pressure regulator valve is equipped spar, with an adjusting screw should it become necessary to reset the valve in the field. Readjustment may be

Ordinarily,

accomplished

as

follows:

engine

until

reading

between 70 to 80 percent is

registered by the

a.

Run up the

b.

Check the deicer pressure gage for a reading of 18 f 1 psi. If necessary, unsafety the lock loosen the adjusting screw locknut located on top of the valve (Ref. Figure 201).

c.

Turn the

adjusting

a

screw

Tighten

and

resafety

tachometer.

retaining

washer and

clockwise to increase, and counterclockwise to decrease, the pressure

pressure gage indicates 18f1 d.

(N1)

gas generator

setting

until the

psi.

the locknut, then shut down the

engine.

NOTE: Check the system vacuum gage for a reading of 5.9 in. Hg., for adjustment of the pressure may affect system suction enough to necessitate readjusting the vacuum regulator.

regulator valve

ADJUSTING SCREW

pc~

LOCKNUT

o

PRESSURE REGULATOR

c

300-1 90-1

Pressure

Regulator Adjustment Figure 201

36-00-00May

1/08

CHAPTER

VACUUM

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

CHAPTER 37

VACUUM

TAB~E OF CONTENTS

SUBJECT

PAGE 37-00-00

Vacuum

System

Description

and

Operation

1

Recommended Materials Vacuum

System

Vacuum

Vacuum

Maintenance Pracitices

1

Regulator

Valve Filter

1

Regulator

Valve

2

Instrument Air Filter

A12

1

Adjustment

Replacement

2

37-CONTENTS

Mar

9/01Pagel

Ray~heon Aircraft BEECH SUPER KING AIR MODEL B300lB300C MAINTENANCE MANUAL

CHAPTER 37

VACUUM

LIST OF PAGE EFFECTIVIP/ CHAPTER-SECTION-SUBJECT

PAGE

DATE

37-Effectivity

1

Mar 9/01

37-Contanta

1

Mar 9/01

37-00-00

A12

1

Mar 9/01

2

Mar 9/01

3

MarS/O1

37-EFFECTIVITY

Mar

9/01Pagel

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

VACUUM SYSTEM

DESCRIPTION AND OPERATION

Vacuum is obtained from the bleed-air-driven

vacuum ejector. The ejector is capable of supplying vacuum ranging Hg at sea level to 6 inches of Hg at 31,000 feet. The ejector supplies vacuum for the pressurization control system at a regulated 4.3 to 5.9 inches of Hg through a regulator valve located in the nose compartment. A filter located on the regulator provides a filtered and sheltered air source. 0.3- micron, 99.7-percent-efficient

from 15 inches of

An instrument air filter is also mounted in the

nose compartment on the upper center portion of the forward pressure provide additional protection for the instruments from dust and other foreign particles in the air. The filter is a disposable unit which should be checked for cleanliness at the interval specified in Chapter 5-00-00 and replaced at the interval specified in Chapter 5-11-00 or at shorter intervals during operation in dusty conditions.

bulkhead. It is

incorporated

in the lines to

RECOMMENDED MATERIALS The recommended materials listed in Chart 1

as meeting federal, military or supplier specifications are provided for specifically required by Raytheon Aircraft Company. Any product conforming to the specification may be used subject to availability. The products included in these charts have been tested and approved for aviation usage by Raytheon Aircraft Company by the supplier, or by compliance to the applicable specifications. I

reference

only and

are

I

not

G ENERIC OR LOCALLY MAN UFACTU R ED PRODUCTS WHICH CONFORM TO THE REQU IREMENTS OF TH E

SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsi-

bility of the the

technician

or

product listed. This

mechanic to determine the current revision of the

can

be done

by contacting

the

supplier

of the

applicable specification prior to product to be used.

usage of

CHPIRT1 RECOMMENDED MATERIALS MATERIAL 1.

Cleaning

Solvent

SPECIFICATION PD-680

Type VACUUM SYSTEM

cleaning

III

PRODUCT Stoddard Solvent

SUPPLIER Obtain

Locally

(Mineral Spirits)

MAINTENANCE PRACTICES

VA CUUM REGULA TOR 1/AL VE FIL TER The

vacuum

regulator is mounted

in the

nose

compartment

on

the left side of the pressure bulkhead. The valve is

protected by a foam type filter that should be cleaned with solvent (1, Chart 1, 37-00-00) at the interval specified in Chapter 5-20-00. If the vacuum in the system exceeds 6.4 inches of Hg, clean the filter and recheck vacuum before attempting to adjust the regulator valve.

A12

37-00-00Pagel

Raythean Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

VA CUUM REG ULA TOR VAL VE ADJUSTMENT The

vacuum

Adjust

valve is mounted

regulator

the lower left side of the pressure bulkhead in the nose vacuum for proper operation of the instruments:

on

follows to

provide

sufficient

that the Pneumatic

System

pressure is

the valve

as

a.

Verify

b.

Check instrument and

c.

Start

engine and

one

regulator filters

run

it up until

a

correctly

compartment.

set.

for cleanliness.

reading

of 70 to 80 percent is

registered by the

gas generator

(N1) tachom-

eter

d.

Check the

adjust

the

gage for a reading of approximately 5.9 +0 -.2 inches of Hg. If the indication is incorrect, regulator valve by unsafetying the retaining lock washer and loosening the adjusting screw

vacuum

vacuum

locknut. e.

f.

Turn the

’When

ignated

adjusting

screw

in

(clockwise)

to

increase, br

out

(counterclockwise),

to decrease the vacuum

gage registers a reading of 5.9 inches of Hg with the engine in step a, tighten and safety wire the locknut, then shut down the engine. the

vacuum

operating within the

setting.

range des-

INSTRUMENTAIR FILTER REPLACEMENT the

compartment right door.

a.

Open

b.

Remove the instrument air filter at its

c.

Install the

new

d.

Close the

nose

nose

fitting.

instrument air filter.

compartment right door.

FILTER

VACUUM

REGULATING VALVE

ADJUSTING SCREW BEND TABS TO LOCK

ADJUSTING SCREW

Vacuum

Mar

9/0137-00-00

3W-190-3

Regulator Adjustment Figure 1

aln

Raytheon Aircraft MOdEi B300/8360~ MAINTENANCE

BEECH SUPER KING AIR

II

BULKHEAD ES.

INSTRUMENT

VACUUM REGULATOR

FORWARDPRESSURE

MANUAL

AIR FILTER

JVALVE

84.00)

_.

TO PRESSURIZATION

FIS. 84.00

FILTERED AIR MANIFOLD

MANIFOLD

VAC GYRO TO

1N

HORIZON

WECTOR

VAC~

sSLIP

DIR

GYRO

IN

INDICATOR

P~V

GYRO SUCTION GAGE 300(404

Vacuum

A12

System Schematic Figure 2

37-0000

Mar

9/01Page

3

CHAPTER

VVAT ERI

VVAST E

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 38 - WATER/WASTE TABLE OF CONTENTS SUBJECT

PAGE 38-30-00

Waste Disposal - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Toilet - Standard Airplane (FL-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Toilet - Cargo Door Equipped Airplane (FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Vanity Unit Waste Water Drain (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . .1 Waste Disposal - Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .101 Waste Disposal - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Servicing the Toilet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Side Facing Toilet Assembly Removal (FL-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Side Facing Toilet Assembly Installation (FL-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Forward Facing Toilet Assembly Removal and Installation (FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . .201 Vanity Unit, Overboard Water Drain Tube Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .203 Vanity Unit, Overboard Water Drain Tube Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .203

A27

38-CONTENTS

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

38-LOEP

1

Feb 1/10

38-CONTENTS

1

Feb 1/10

38-30-00

1 101 and 102 201 thru 204

Feb 1/10 Feb 1/10 Feb 1/10

A27

38-LOEP

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 38-30-00

WASTE DISPOSAL - DESCRIPTION AND OPERATION SPECIAL TOOLS AND RECOMMENDED MATERIALS The special tools and recommended materials listed in Chart 1 as meeting federal, military or supplier specifications are provided for reference only and are not specifically prescribed by Hawker Beechcraft Corporation. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

Chart 1 Recommended Materials MATERIAL

SPECIFICATION

PRODUCT

1. Lock Wire

SUPPLIER Obtain Locally

2. Tape

Scotch Brand 33

Obtain Locally

3. Coating Adhesive

Scotch-Grip EC776 SR

Obtain Locally

TOILET - STANDARD AIRPLANE (FL-1 AND AFTER) The standard version of the airplane is equipped with a side facing electric toilet located in the aft vestibule, just inside of the cabin door. Either the Monogram recirculating flush toilet or the Alamo "Clean-Flush" toilet may be used in the standard side facing configuration. Total waste container capacity of the Monogram toilet is 2.9 gallons. Total waste container capacity of the Alamo toilet is 2 gallons. Both toilets are flushed by pressing a button on the top surface of the toilet assembly. The Monogram toilet will flush continuously while the button is pressed. The Alamo toilet operates on a flushing cycle of approximately 6 to 10 seconds. A 10-ampere circuit breaker located on the right subpanel protects the motor/pump circuit.

TOILET - CARGO DOOR EQUIPPED AIRPLANE (FM-1 AND AFTER) The cargo door version of the airplane is equipped with a forward facing toilet located in the left aft compartment aft of the cargo/entrance door opening. Either a dry nonflushing type or a Monogram electric recirculating flush toilet may be installed in cargo door version of the airplane. Total waste container capacity of the Monogram toilet is 2.9 gallons. The Monogram recirculating flush toilet is flushed by pressing a button on the top surface of the toilet assembly, and will flush continuously while the button is pressed. A 10-ampere circuit breaker located on the right subpanel protects the motor/pump circuit.

VANITY UNIT WASTE WATER DRAIN (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) The vanity unit (Ref. Chapter 25-20-00) is equipped with an overboard waste water drain and is controlled using a touch switch located above the vanity sink bowl. The overboard drain valve is protected by a 5 amp circuit breaker.

A27

38-30-00

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WASTE DISPOSAL - TROUBLESHOOTING

100100100

Chart 101 Troubleshooting - Electrical Flush Toilet TOILET WILL NOT FLUSH STEP 1

STEP 2

STEP 3

STEP 4

Circuit breaker tripped.

YES

Check toilet electrical system for shorted circuits or weak circuit breaker. Repair or replace components as required.

NO

Proceed to Step 2.

Inadequate flush fluid charge.

YES

Recharge as required.

NO

Proceed to Step 3.

Motor or pump failed.

YES

Repair or replace motor or pump as required.

NO

Proceed to Step 4.

YES

Repair or replace as required.

Check timer on Alamo toilet.

Chart 102 Troubleshooting - Electrical Flush Toilet TOILET FLUSHES CONTINUOUSLY STEP 1

STEP 2

A27

Flush switch malfunctions. YES

Check timer on Alamo toilet.

Replace switch.

NO

Proceed to Step 2.

YES

Repair or replace as required.

38-30-00

Page 101 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 103 Troubleshooting - Electrical Flush Toilet EXCESSIVE NOISE AND/OR CURRENT DRAIN STEP 1

STEP 2

Tank strainer clogged.

Motor and/or pump failed.

YES

Clean strainer.

NO

Proceed to Step 2.

YES

Repair or replace motor or pump as required.

Chart 104 Troubleshooting - Electrical Flush Toilet OFFENSIVE ODOR STEP 1

Page 102 Feb 1/10

Inadequate/lack of chemical mix in initial tank charge or excessive usage between service periods.

38-30-00

YES

Empty and reservice toilet with correct mix.

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

WASTE DISPOSAL - MAINTENANCE PRACTICES SERVICING THE TOILET Refer to Chapter 12-20-00 for servicing information for all toilets which may be used in the airplane.

SIDE FACING TOILET ASSEMBLY REMOVAL (FL-1 AND AFTER) a. Open the door on front of the toilet cabinet and remove the tank (Ref. Figure 201) (Ref. SERVICING THE TOILET, 12-20-00). b. Remove the four jam nuts from the seat track studs located at each corner of the base of the toilet frame. c.

Carefully lift the complete toilet assembly up and out from its position in the airplane.

d. Remove the seat track studs from the track and retain them with the jam nuts removed in step "b" for later reinstallation. e. For disassembly, maintenance and subsequent reassembly of the toilet unit, refer to the appropriate supplier manual in the Hawker Beechcraft Corporation Component Maintenance Manual, P/N 101-590097-13 or subsequent.

SIDE FACING TOILET ASSEMBLY INSTALLATION (FL-1 AND AFTER) a. Position the four seat track studs in the seat tracks at the approximate location of the attach holes in the corners of the toilet assembly frame. b. Position the toilet assembly in the airplane, guiding the four seat track studs into the four holes in the corners of the base of the toilet assembly frame. c.

Install and tighten the four jam nuts on the seat track studs.

FORWARD FACING TOILET ASSEMBLY REMOVAL AND INSTALLATION (FM-1 AND AFTER) The forward facing toilet cabinet is riveted in place in the aft compartment and should not necessarily require removal for normal maintenance. The toilet units within the cabinet may be removed by first observing servicing requirements (Ref. SERVICING THE TOILET, 12-20-00), then removing the screws which secure the toilet to the cabinet. For disassembly, maintenance and subsequent reassembly of the toilet unit, refer to the appropriate supplier manual in the Hawker Beechcraft Corporation Component Maintenance Manual, P/N 101-590097-13 or subsequent. Reinstallation of the toilet unit is accomplished by positioning the toilet unit into the cabinet and securing it with the attaching screws. The servicing instructions (Ref. SERVICING THE TOILET, 12-20-00) should be reviewed during this reinstallation.

A27

38-30-00

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Side Facing Electric Flush Toilet (FL-1 and After) Figure 201 Page 202 Feb 1/10

38-30-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

VANITY UNIT, OVERBOARD WATER DRAIN TUBE REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the vanity unit overboard water drain tube is empty of waste water. b. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. c.

Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”.

d. Remove the middle and bottom drawers of the vanity unit. e. Remove the coating adhesive, tape and lockwire from the overboard water drain tube connected at the fuselage drain assembly (Ref. Figure 202). f.

Disconnect the overboard water drain tube from the fuselage drain assembly.

VANITY UNIT, OVERBOARD WATER DRAIN TUBE INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Connect the vanity unit overboard water drain tube to the fuselage drain assembly (Ref. Figure 202). b. Install four coils of lockwire (1, Chart 1, 38-30-00) around the overboard water drain tube at the fuselage drain assembly. c.

Wrap the joint between the overboard water drain tube and fuselage drain assembly with tape (2, Chart 1, 38-30-00). Apply coating adhesive (3, Chart 1, 38-30-00) over the tape to seal to seal the joint.

d. Install the middle and lower drawers of the vanity unit. e. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

A27

38-30-00

Page 203 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FS 316.00 REF

A A

1. OVERBOARD WATER DRAIN TUBE 2. FUSELAGE DRAIN ASSEMBLY 3. SKIN (REF) 4. LOCKWIRE 5. TAPE 6. COATING ADHESIVE

4 1

6 5 2

B 2 DETAIL

3

VIEW

B

A-A FL38B 985701AA.AI

Vanity Unit, Overboard Water Drain Assembly (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 202 Page 204 Feb 1/10

38-30-00

A27

CHAPTER

ELECTRICAL PAN ELS, PARTS

AN D I N ST RU M E N TS

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTRICAL PANELS, PARTS AND INSTRUMENTS

CHAPTER 39

TABLE OF CONTENTS

PAGE

SUBJECT 39-00-00

Electrical Panelsand

Components

Description

and

Operation

.................1

39-10-00 ..201

Instrumentand Control Panels- Maintenance Practices

....201

Instrument Panel -Zone248. Removal of

.201

Flight Instruments Flight Instruments.

.201

Installationof

.207

Removal of theAvionics Instrument Panel. Installation of the Avionics Instrument

........208

panel

Engine Instruments Engine Instruments InstrumentSubpanel Zones244and 245. InstrumentSubpanel Section and Component Removal InstrumentSubpanel Section and Component Installation. Pedestal Panels and Components -Zone243. Upper Pedestal Panel Components Removal Zone 243 Upper Pedestal Panel Components Installation. Lower Pedestal Panel Components Removal Zone 243 Lower Pedestal Panel Components Installation. Circuit Breaker Panel (A146) Zone 246

.208

Removal of the

.208

Installation of the

............208 .209 ................209 .........209 209

.....209 .211 .....211 ..............211 ....211

Circuit Breaker Removal.

...212

Circuit Breaker Installation Fuel Control Panel

(A124) Zone 247 Removal of Toggle Switches Installation of Toggle Switches.

................215

.215 .215

....218

Circuit Breaker Removal.

...218

Circuit Breaker Installation

.218

Removal of Fuel Installation of

Quantity Gages Fuel Quantity Gages

...............219

....219

Overhead Panels -Zone253 Overhead

LightControl

Panel

(A110)

.............219 ...219

Removal of Rheostats

.219

Installation of Rheostats.

Light Dimming Transistors Installation of Light DimmingTransistors. Overhead Instrument Panel (A133)

.........220

Removal of

,4

.......220 ...............220

Removal of Instruments.

.220

Installation of Instruments

.220

39-CONTENTS

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTRICAL PANELS, PARTS AND INSTRUMENTS

CHAPTER 39

TABLE OF CONTENTS

(CONTINUED)

SUBJECT

PAGE 39-20-00

Center Section and

Wing

Electrical Panels

Maintenance Practices

201

Variable Heat Control and Stall

Warning Panel (A150) Location Zone 522 Variable Heat Control and Stall Warning Panel Removal Variable HeatControl and Stall Warning Panel Installation Leading Edge Electrical Equipment Panel (A227) Location Zone 511 Leading Edge Electrical Equipment Panel Removal. Leading Edge Electrical Equipment Panel Installation Standby Fuel Pump Radio Frequency (RF) Filters (A231 and A232) Location Zones 521, 621......... Standby Fuel Pump Radio Frequency (RF) Filters Removal Standby Fuel Pump Radio Frequency (RF) Filters Installation Inboard Nacelle Power Distribution Electrical Panels (A251 and A252) Location Zones 521, 621 Inboard Nacelle PowerDistribution Electrical Panels Inboard Nacelle PowerDistribution Electrical Panel

201 201 201 203 203 203 204 204 204 205

Removal

205

Installation.

206

Battery Power and Distribution Equipment Panel (A228) Location Battery Powerand Distribution Equipment Panel Removal Battery Powerand Distribution Equipment Panel Installation. External Power Receptacle (J112) Location Zone 611 External Power Receptacle Removal External Power Receptacle Installation.

Zone 611

209 209 209 211

211 211

39-21-00

Fuselage Electrical

Panels- Maintenance Practices

Left Hand Forward

Flight Compartment Equipment

201

Panel

(A225)

Location

Zone 221

201

Removal Installation

Right

Hand Forward

Flight Compartment Equipment

Panel

(A226)

Location

Zone 222............... 201

Removal Installation AC Power Distribution and Lift

Computer

Panel

(A263)

Location

Zone143

204

Removal Installation

Main Power Distribution Panel

(A145)

Location -Zone 143

204

Removal Main Power Distribution Panel

Components (Sheet2, Components (Sheet2,

Detail Detail

Components (Sheet 1). A) B)

................._

208 208 209

Installation Printed Circuit Card Rack Location

Zone 143

211

Removal Installation Printed Circuit Card Rack

Page

yaM2

1/08

39-CONTENTS

213

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 39

ELECTRICAL PANELS, PARTS AND INSTRUMENTS TABLE OF CONTENTS

(CONTINUED) PAGE

SUBJECT

..........213

PrinterCircuitCard Box Location -Zone 143.

Removal Installation

Aft Electric Heat

Equipment

(A216) Location

Panel

...............215

-Zone 163.

Removal

Installation Forward Electrical Heat

Panel

(A215)

Supply

Panel

Equipment

Location

Zone 132

..........218

Removal

Installation Cabin Fluorescent

Lighting

Power

(A519)

Location

.....218

Zone 163

Removal Installation Interturbine

Temperature Gage

Balance Resistors

(R100

and

R101)

Location

Zones 141 and 142......222

Removal Installation

Flap

Motor

.224

Relay (K105) -Zonel51.

Removal Installation

A24

39-CONTENTS

1/08Page May

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

39-LOEP

1

May 1/08

39-CONTENTS

1 thru 3

May

1/08

39-00-00

1 thru 5

May

1/08

39-10-00

201 thru 224

May

1/08

39-20-00

201 thru 212

May

1/08

39-21-00

201 thru 224

May

1/08

A24

Pages

39-LOEP

May

1/0bPage

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTRICAL PANELS AND COMPONENTS This

contains information

chapter

operation

the

on

DESCRIPTION AND OPERATION

and maintenance of the

airplane electrical systems and are contained in the applicable this chapter. Refer to Chapter 20-03-00 for

components. The wiring diagrams which show the electrical circuitry for this airplane

wiring diagram manual, information This

on

chapter

electrical

and should

bonding

always be used in conjunction grounding procedures.

is divided into four sections:

Section 39-00-00 contains the

zone

locations with

Section 39-10-00 contains information

indicating achieved section

instruments and

through

are

with

and

the

use

located in the

primary

descriptions

to enable

panel

location in the

airplane.

the location and basic maintenance of

panels containing the various Airplane system performance and total airplane system control is panels and instruments; therefore, all the electrical panels covered in this

on

controls.

of these various

flight compartment

and

are

accessible to the

Sections 39-20-00 and 39-21-00 each contain information

on

flight

crew.

the location and maintenance of those

panels

which

secondary controls and electrical components. Access to these panels and components is during maintenance, and is gained through access openings and floorboards located throughout the

contain most of the

necessary only Section 39-20-00

airplane. the

airplane.

n24

covers

Section 39-21-00

the

covers

panels and electrical components located in the center section and wing of panels and electrical components located in the fuselage of the airplane.

the

39-00-00

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FS

.CO

F/

6

!AT

j(BO.TTEF?Y

n

ACCE’S) es

61

i

WS

i

.735

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WS

29

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650 643

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400

(1~0)

300

(6

0)

POWER

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ORrGINAL As

ENGINE SECTION. FIRE WALL FORWARD

(600)

WING

WING

CENTER

ATP

CENTER

ANO

SECTION

WING

FRO~

520

[520)

NACELLE

530

[630)

WS

23.309

10

WS

196.198

340

[540)

WS

96.198

TO

WS

~91.735

350

[550)

WING

OUTBOARD

OF

WS

AFT

OF

Received By

SECTIONS

FUSELAGE

TO

WS

23.309

FIREWALL

291.735 350-603-129

Top

Zone View of

Figure

May

1/08Page

2

39-00-00

C

Airplane

1

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

/FS\ i

O. CO

t--t

II

’~ES/

RIGHT

C

FS 30.00

710 1

i

227~121 FS 84.00

32 1 131

S

14~.00

143

740

142

730

;41

cS

i ’I

133

i

--151

7r,

152

t

162

b

163

.90

FS 312.50

L,,

72 1 17

FS 381 .75

ORIGINAL As Recelvad

By

ATP

ci==-

LONE

00 10 20

30 40 150 160 170

RADOME AND AREA BELOW THE FLOOR RADOME FORWARD OF FS30.00 FS30.00 TO 84.00

LONE

700

LANDING GEAR ODORS AND WHEELWELLS

710

NOSE

LANDING GEAR LEFT MAIN LANDING GEAR RIGHT MAIN LANDING GEAR

730 740

FS84.00 TO FS 43.00 FS 43.00 TO FS~04.40 FS204.40 TO 239.90 FS239.90 TG FS312.50 FS312.50 TO FS38 .75

3eo-soa-IJo

Bottom Zone View of

Figure

A24

c

Airplane

2

39-0000

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

82 L~>

FS

FS a~.oc

30.00

FS 381 .50

FS 143.00 FS 312.50

FS 107.00

FS 57.50

IDI

/340

3

010100000

33

~b

i-(

/330

I

2, (~82)

(2623

(2 FS

ai i

i231

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(a12i 221

(2221

ZONE

200: 0:

FS30.00

10

220: 230: 240: 250:

’S84.00

10

2

260: 270:

FOR

LONE

300: 310:

360:

EMPENNAGE FUSELAGE AFT OF PRESSURE ~ULKHEAD ~ORSAL FIN VERTICAL STA~ILIZER ~UDDER ~ORIZONTAL STABILIZER ELEVATORS

LONE

100:

POWER

ZONE

aoo:

DOORS

FS84.00 FS91.00 FS107.00 4

320: 330:

FS94.00 10 SEE FIGURE SEE FIGURE 4 ’Sid3.00 iO FS312.50 (BELOW LOWER LONGERON) ’5143.00

(ABOVE 280:

LONE

ABOVE FLOOR, FS30.00 TO F5347.50 INCLUSIVE

FS3

100 SEE

2.50

340: 350:

TO

FS312.50 LOWER LONGERON) TO

PLANT

FS381.50

BREAKDOWN,

811

FIGURE

82

2.

(8 2,: i822): 830

Avro~Ics COMPART~ENT EMERGENCY EXI? CASIN ENTRY

ORIGINAL As Received

By

ATP

380-603-131

Left Hand Side Zone View of

Figure

May

1/08Page

4

39-00-00

C

Airplane

3

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ZONE

~00 240 241 242 243 244

2L5 246 2d7

ORIGINAL As Received By ATP

248 249 250 25 252 253 254 255

Z~EW COMPARTMENT aELOW LOWER WI~COW LONGERON, LEFT FUSELAGE SIDE WALL RIGHT FUSELAGE SIDE WALL PEDESTAL AND CONSOLE RIGHT SUBPANEL LEFT SUBPANEL CIRCUIT BREAKER PA~EL FUEL CONTRCL PANEL INSTRUMENT PANEL GLARESHIELD ABOVE LOWER WINDOW LONGERON. LEFT CAaIN SIDE WALL RIGHT CABIN SIDE WAL! OVERHEA~ CONTROL PANELS PILOT’S CONTROL WEEEL COPILOT’S CONTROL

iS107.00

TO

FSiL3.00

FS107.00

TO

FS143.00

251

252 253

Q1100C

O

3

\UOUI

1/"

-n-

8~N\

2aS3~01

241

/K/

‘-oVar44

I

I

254

255

247

X~

242

246 243

C

Flight Compartment Zone Figure 4

A24

View of

Airplane

39-00-00Page

5

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSTRUMENT AND CONTROL PANELS INSTRUIMENT PANEL

MAINTENANCE PRACTICES

ZONE 248

The instrument instrument

panel is divided into three sections: the flight instruments (pilot’s and copilot’s), the avionics panel, and the engine instruments (Ref. Figure 201, Figure 202 and Figure 203).

REMOVAL OF FLIGHT INSTRUMENTS a.

Access the

the NOTE:

panel

flight

instruments

the

quick-release

fasteners which hold the

Wrap padding around the control column just below the panel section control column and the panel section.

b.

Loosen the fasteners

c.

Tilt the

d.

Disconnect the

plumbing

Disconnect and

remove

e.

by loosening

panel sections, then tilt

sections aft for removal.

panel

securing

section aft,

the

using

panel

care

section in

to avoid

to avoid

marring

the finish of the

place.

placing

undue force

on

any wires

or

plumbing

of the instruments.

and/or electrical connections from the instrument to be removed.

any post

lamps.

Remove the

mounting

screws

securing

the instrument to the

panel

section. f.

Remove the instrument.

INSTALLATION OF FLIGHT INSTRUMENTS

WARNING: To avoid

possible confusion, the displays of the pilot’s and copilot’s altimeters must be of matching types (either drum and pointer or three-needle). The brands and/or the signal source lair or electric) need not match.

a.

Place the instrument in

b.

Secure the instrument

position

using

the

in the

panel section.

mounting

screws

and post

lights (if installed).

Connect the post

light

wires

(if

used). c.

Connect the

d.

Carefully position the panel section in its proper place, taking precautions to prevent pinching the electrical wiring or bending the plumbing too sharply. Avoid placing undue force on any wires, plumbing, or instruments.

e.

Secure the

f.

Remove the

,4

plumbing

panel

and/or electrical connections to the instrument.

section with the

padding

quick-release fasteners.

used to protect the finish.

39-1 0-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

May

1/0839-1 0-00

Page Intentionally

Left Blank

an4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

_

I´• ~,s

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350

TYPICAL

INSTRCIMENT

350-391-013

PANEL

ORIGINAL As Received ATP

Instrument Panel

By

(FM-1

thru

Figure

A24

(Typical)

FM-8, FL-1 thru FL-119 and FL-121) 201

39-1 0-00

PMa 9ye~3sMay

1/OS

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

May

39-1 0-00

Page Intentionally

Left Blank

a?,

Hawker Beechcraft

Corporation

SUPER KING AIR B30018300C MAINTENANCE MANUAL

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C04RJPB081J

Instrument Panel

(Typical)

(FM-9 and After, FL-120, FL-122 and After) Figure 202

39-10-00 A24

Page 205 May 1/08

Hawker Beechcraft

Corporation

SUPER KING AIA B300/B300C MAINTENANCE MANUAL

This

May

39-1 0-00

Page Intentionally

Left Blank

nnd

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

GLARESHIELD

r

ENGINE INSTRUMENTS AVIONICS SECTION

PILOT’S FLIGHT

PANEL

INSTRUMENT PANEL SECTION

COPILOT’S FLIGHT INSTRUMENT PANEL SECTION

00 00 00 00 00

LEFT OUTBOARD SUBPANEL

LEFT

J

RIGHT OUIBOARD SUBPANEL

RIGHT INBOARD SUBPANEL

INBOARD SUBPANEL

350-390-015

Instrument and Control Panels

Figure

203

REMOVAL OF THE AVIONICS INSTRUMENT PANEL NOTE: Certain

optional

avionics installations

require

the

use

of

a

solid

panel

and cannot be removed

as a

panel

section. a.

Remove the radar instrument

or

any

avionics

heavy

equipment requiring special mounting supports forward of the

panel.

b.

padding as necessary to protect the radio controls and the airplane engine and propeller controls.

c.

Loosen the

d.

Tilt the avionics

panel

to avoid

undue force

e.

A24

Use

quick-release

placing

aft

securing

fasteners

sufficiently on

to

the radio

permit

and to

panel

or

to the

floating

instrument

panel.

removal of the electrical connections and cable drives. Use

any wires, control heads,

Remove the avionics instrument

prevent marring the finish of the avionics panels

care

mounts or cables.

control head.

39-1 0-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSTALLATION OF THE AVIONICS INSTRUMENT PANEL a.

Install any control head

b.

Connect the mechanical drives and electrical connections

c.

Carefully position bundles

or

or

instruments removed from the avionics

the avionics instrument

place undue force

d.

Secure the avionics

e.

Install the radar

f.

Remove any

or

panel

any

on

to the

heavy

in the

required.

floating panel

Use

floating panel.

any wire, component, control head

avionics

used for

padding

panel

as

with the

section.

panel

quick-release

care

not to

any wire

pinch

or

wire

mount.

or

fasteners.

equipment requiring special mounting supports.

protection.

REMOVAL OF THE ENGINE INSTRUMENTS The

engine instruments

are

mounted in the center section of the

floating

instrument

panel.

a.

Remove the lens cap from the post lamps adjacent to the instrument to be removed. This permit pulling the instrument straight out of the instrument clamp.

b.

Loosen, but do

c.

Press the screw

d.

not remove, the screw below and to the left of the

lightly

Pull the instrument

to loosen the

straight

clamps around

out of the

engine

provides

clearance to

instrument to be removed.

the instrument.

clamp securing

provided

it. Sufficient wire is

to

permit

removal of the

instrument. e.

Disconnect the

engine

instrument electrical connectors from the

airplane

wire harness connectors.

INSTALLATION OF THE ENGINE INSTRUMENTS a.

Connect the

b.

Insert the

against c.

engine

the

Carefully

airplane

wire harness electrical connectors to the

instrument into its which

screw

tightens

damaging

the

instrument connectors.

mounting clamp in the panel. It may permit the insertion of the

the clamp to

rotate the instrument in the

CAUTION: To avoid

engine

clamp

to obtain the desired

be necessary to hold instrument.

alignment

light pressure

of the dial.

instrument, tighten the mounting clamp only enough

to hold the instrument in

place. the

d.

Tighten

e.

Replace the post lamp

screw

below and to the left of the instrument to

(Zone 245)

subpanels

and the

Page

clamp.

are

ZONES 244 AND 245

located

just

below the main instrument

copilot’s subpanel (Zone 244),

(Ref. Figure 201, Figure

the

lens caps.

INSTRUMENT SUBPANEL The instrument

tighten

202 and

panel

and consist of the

pilot’s subpanel

each divided into two sections, inboard and outboard

Figure 203).

39-1 0-00

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSTRUMENT SUBPANEL SECTION AND COMPONENT REMOVAL a.

Remove the

CAUTION:

b.

screws

securing

the

edgelit panel

to the

subpanel

performing maintenance around edgelit panels, panels, as they cannot always be repaired. When

Remove the

screws

securing

the

subpanel

section to the

section and

precautions

take

subpanel

carefully

it from the

remove

not to scratch or

the

damage

lift it from the

carefully

structure and

panel.

panel

structure. c.

Tag or

and disconnect all

fasteners

the

securing

plumbing

and/or electrical connections from the

the component to the front of the

panel and

panel components.

remove

Remove the

jam

nut

the component from the backside of

panel.

INSTRUMENT SUBPANEL SECTION AND COMPONENT INSTALLATION a.

Position the component in the

b.

Connect all

c.

subpanel

B300

plumbing and/or electrical Wiring Diagram Manual.

Align

the

subpanel

section with the

and

secure

jam

according

connections

panel

with it’s

to

performing maintenance around edgelit panels, panels, as they cannot always be repaired.

Align

the

edgelit panel

with the

subpanel

and

secure

with

or

tags

structure and secure with

CAUTION: When

d.

nut

fake

attaching

fasteners.

or

the Hawker Beechcraft

attaching

Super King

Air

screws.

precautions

not to scratch or

damage

the

screws.

ZONE 243

PEDESTAL PANELS AND COMPONENTS

pedestal panels (Ref. Figure 204) and components are located below the annunciator/caution advisory light panel between the pilot’s and copilot’s seats. They are divided into upper and lower panels.

The

UPPER PEDESTAL PANEL COMPONENTS REMOVAL

panel assembly

a.

Remove the

screws

securing

the upper

b.

Remove the

screws

securing

the instrument to the

c.

Tag

and disconnect all

plumbing and/or

ZONE 243 to the

pedestal

panel and carefully

and lift the

remove

panel

out.

it from the backside of the

panel.

electrical connections from the back of the instrument.

UPPER PEDESTAL PANEL COMPONENTS INSTALLATION a.

Connect all

plumbing and/or electrical connections to the back of the Super King Air 8300 Wiring Diagram Manual.

instrument

according

to

tags

or

the

Hawker Beechcraft

the backside of the

b.

Carefully position

the instrument

on

c.

Secure the

to the

with the

P~4

panel

pedestal

attaching

panel

and

secure

with the

attaching

screws.

screws.

39-1 0-00

Page

yaM902

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

F C~

glVI

I1U

FEPTLIR

OKI

1I1*

EI´•G:YLS

FLIP

X\IERSE

I

IIRP ~pp?0*3( 00*"

Ruooin r,s ;rrr

am,

Nly

*ao*_r

Q

IILY

vs

Its

~Ei

WARNIUP car

CIBIU

0

~1003 "’::~s-´•a

ajb

ORIGINAL By

As Recerved ATP

C94FL39B1513 C

Pedestal and Console Assembly

Figure

May

1/08Page

210

39-1 0-00

204

nno

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LOWER PEDESTAL PANEL COMPONENTS REMOVAL

ZONE 243

performing maintenance around edgelitpanels, they cannot always be repaired.

CAUTION: When

a.

Remove the

screws

securing

the

to the upper

edgelit panel

use care

not to scratch

and

panel assembly

or

damage the panels as

carefully

remove

it from the

panel. b.

Pry

c.

Remove the

d.

out the

panels jam

on

nut

By reaching through

the sides of the

or screws

the side,

and disconnect the electrical

pedestal.

securing

the component to the face of the lower

pedestal.

carefully remove the component from the underside of the pedestal panel wiring from the back of the instrument being removed.

and

tag

LOWER PEDESTAL PANEL COMPONENTS INSTALLATION a.

Con nect all electrical wi ring to the back of the instru ment Air 8300

Wiring Diagram

By reaching through the side, carefully position secure with the jam nut or screws.

c.

Place the

CA UTION: When

they d.

Align

the

to

tags

or

the Hawker Beechcraft

Super King

Manual.

b.

panels

according

at the sides of the

the component

the underside of the

on

pedestal panel

and

pedestal.

performing maintenance around edgelit panels, always be repaired.

use care

not to scratch

or

damage

the

panels as

cannot

edgelit panel

with the

CIRCUIT BREAKER PANEL

pedestal panel

and

secure

with the

attaching

screws.

(A 146) ZONE 246

right hand circuit breaker panel (Ref. Figure 205 and Figure 206) is located on the right interior sidewall airplane adjacent to the copilot. The panel is hinged at the bottom to provide access to the circuit breakers.

The

of the

CIRCUIT BREAKER REMOVAL CA UTION: When

they

performing maintenance around edgelit panels, always be repaired.

a.

Remove the five

b.

Carefully

c.

Use

remove

padding

use care

not to scratch

or

damage

the

panels as

cannot

screws

securing

the

edgelit panel

the

to avoid

damage

edgelit panel

to the circuit breaker

from the circuit breaker

to the circuit breaker

panel,

panel.

panel. as

it could contact the control wheel

or

other

or

electrical

obstacles. at the

top of the circuit breaker panel.

d.

Remove the three

e.

Lean the top of the panel away from the sidewall while using components behind the panel.

f.

Tag

g.

Remove the

~a4

screws

and disconnect the electrical

jam

nut

on

wiring from

care

to avoid

damaging

the wires

the circuit breakers.

the front side of the circuit breaker

panel

for the circuit breaker

being

removed.

39-1 0-00Mayl/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

h.

Remove the circuit breaker from the backside of the

i.

Reinstall the

jam

nut

panel.

the circuit breaker to prevent loss.

on

CIRCUIT BREAKER INSTALLATION nut from the circuit breaker.

a.

Remove the

b.

Insert the circuit breaker in the

c.

Install the

d.

jam

jam

Connect electrical

Raise the

from the backside.

nut on the circuit breaker.

Wiring Diagram e.

panel

wiring

to the circuit breaker

according

to

tags

or

the Hawker Beechcraft

Super King

Air B300

Manual.

panel and panel.

secure

it to the sidewall with three screws, then

remove

the

padding

that

was

used to

protect the

CA UTION: When

they f.

Install the

Page

yaM212

1/08

performing maintenance around edgelit panels, always be repaired.

use care

not to scratch or damage the

panels as

cannot

edgelit panel

and

secure

39-1 0-00

with five

screws.

nz4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

IJARNINGS

TPL

FEC

5

AVIONICS

ENGINES

7-------

VOICE RCOR

POWER

LEFT

LEFT

AUTO

LEFT

LEFT

LErT

LEFT

LEFT

#7~#

5

5

s

#7~#

5

5

5

j

BLEED AIR WARN

OIL PRESS WARN

IGNITOR

OIL PRESS

OIL IEMP

FIRE

FUEL

OETR

FLOW

WARN

T IANOI~G

i-(

5

~1

T

FEATHER

ANN

GEAR

LE’~

COS

POWER

~j

5 IN3

tl

j

RI;HI

INO

5 WARN

NORMAL

RIGHT

~3

RIGHT

5

t3

RIGHT

FLAP

GEN d 20

ALT

ALT

ALERT

FLIGHT

iND g CONT~OL

RIGHT

RIGHT

N(1

RIGH1

AUDIO

GEN ~I

LEFT

NCSHK

IURN

INSTR

E~G INSTR SIDE

CONSOLE

TRI

CHIP DETR

READING

PROP

5

5

ifl

PANEL

PILCT

SLIP

ENC3

g

’ILCT

j

OUTSIDE AIR z

Fi

SPEED

p

LEFT

CABIN

INDIRECI

IIGHTS

ENG

KN

L_-T

TEMP

5

5 L

3LE"O AiR CONTROL

PRESS

T~i _

5

GEN

j

RIGHT

CABIN

OXY

~1

CABIN

NO.2

AUDIO

N0.2

RMI

DME

NAV

XPONOER

RADIO

N0.3

NO.I

NO.i

NO.Z

NO.I

PHONE

IND

LEFT

PILOT

OSPL

MULTI FCTN

EAOI

>RCSR

BUS

IO~OUE METER

(eGl AVIONICS

RIGHT

ELECTRICAL GE~I

DEICE

RESET

ALT HIGH

CIFF

ANTI ICE

Ti~ PRO"

a

to

WIPER

5

a

RIGHT

HIGH

I

AN/F#

CONTRCL

0

COMPASS

CIGAR

tl

STEREO

5

LEFT

LEFT

~fl

COLTROL

?~CSR

N3.2

RVOOER

PILOT

RlriI

AP

EHSI

NO.2

SERVO

NO.I

BOOST

CAT PROBE

RADAR

RADIO

DUIE

ALTM

NO.2

ELEK

MULTI

FZ5

RADIO

CSPL

FCTN

POWER

IUNE

CONTR

PRCS~

I;

DEICE CONTROL

CONTROL

RIGHT

BUS TIE

POWER

FSTBYHRZN?

s#s~j2

IIGHTER ANTI

5

ICE

R

RIGHT

5

AUX

’ILOT WSHLD ANTI ICE

STSY ENG

VEN1

GEN

EMSI

’CS ’OWEI?

’I)WER

io tl

COPILCT~EAOING

5

FURNISHING

FUEL

R

TEST

-r

SURF

WSHLO

Si~

5

CONTROL

MASTER

L

X~ONOER

~i=

5

WARN

TEMP

ALT

INSTR

PROP

RIGHT

WEATHER

AIR

ENVIRONMENTAL~

iFL

NO

GND COPILOT

AVIONICS ADF

GOV

SYNC:

SLIP TURNB

5

AUDIO

NAV

COI"M

L_FT

NO.2

FS3 B BAGGAGE

5

1

FEDFI

NO.i

I

AYIO#IZS

SUB PNI OVHD

PITCH

ILOT

;_

PILOT

5

MOTOR

R

COPILPT ENCD

COMM

5

IGHTS FLAP

MASTER

Na.

IAVIONICS COYM 5

5

RIGHT

AYIONICS

3

I

POWER

START STALL

ED

O~PASS

BUS TIE ’OWER

BRAKE

~i

RIGHT

IND

HEAT

FLi

MGTSYS

BAT r

LRN

5

1

~O

17

DEICE

DSPL

NC.2

350-351-050

C

ORIGINAL As Received

By

ATP

Circuit Breaker Panel

(FM-1

thru

FM-8, FL-1 thru FL-119 and FL-121)

Figure

A24

205

39-1 0-00

Page 213 May 1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WARNINGS WARN

POWER

FED

LEFT

5

ANN

LEF~

LEFT

LEFT

OIL ?RESS WARN

FED

~j

5 INC

START CONT

cIRE

IGNITOR POWER

DETR

FLAP

5

5

5

INC

RIGH~

RIGHT

WARN

FLAP

MOTOR

5

ALT

r

I

Ir9 g COYTRCL

A!

RIGHT

RIGHT

RIGHT

ILOT

GEI\1~

T

FLIGHT

AVIONICS 5

1

ALERT

INSTR

I~´•ISTR

FSB 5 BAGGAGE

B b

CJNSOLE

TRIM

SLIP

PL

FEG 01

PILOT ENCD

OUTSICIE AI?

5

5

TEMP

LEFT

iEYIP

PRESS

INSTR

WARN

LEFi

CABIN

INCIRECTL!MTS

OXY

TER

L

GEN

~j

5

~i

RIGHT

10

20NT?3L

AM/FM IO

STEREO

ANTI ICE

*LT

OIFF HIGH

WIPER

HIGH

CIGAR

LEFT

LEFT

CONTROL

POWER

5

5

/2

/2

5

WSHLD

RIGHT

COHM

COPILOT

N3.2

AUDIO

N0.2

IND

CME

NAV

XPONDR

PROP

5

NO.I

NC.I

LEFT

PILOT

DSPL

ANTI ICE

~1

XPONOER

RIGHI

OilC~

ANTI

PILOT

,12

5

COilTROL

RIGHT

EHSI

6US TIE POWER L

BUS

ICE

5

5

RIGHT

DEICE

r

STBY

HRZN

(2)

AL’X SAT

iiE POVER

BRAKE

NO.i

PHONE

COPILOT HEADING

COMPASS

9 PRCSR

EMSI

PRCSR

NO2

AP

FCS POWER

RUDDER

SERVO

NO.I

e005i

RADAR

RADIO

OME

FCTN PRCSR

;i--i~iji

PILOT WSHLD

NC.2

RACIO

3

MULTI

I

T STBY ENG

RIGHT

~O

1=1

2

EADI

RESET

~3NTR3i

VENT

RI~I

NO.3

3

LIG~TER

GEN

AVIONICS

BUS TIE

6

FUEL

R

AUDIO

ELECTRICAL GEN

OEICE

CABIN

j~=(

NO.2

5

FUR>JISHING

CONTROL

ADe

5

5 CONT ROL

AIR

SURF

t=I

EI~IG

TEST

T

CABIN

5

BLEED

RIGHT

WEATHER

SPEED

NO.i

PROP GOY

SYliC

PANEL

AIR

MN

;´•ii Fl

AUDIO

525 a

~n

5 ALT

I

CHI~ DETR

5

PILOT

NO

IAVIONICS

I

1

SLIP TURN

PILOT

5

5

READING I PROP

SIDE

117~#

N4V

COMM

O

RIGHT

LEFT

NOSMK

~j

E~G

5

OVHC b

PITCH

5

TURN

COMM

I

SUB PNL

3

NO?MAl

I VIONICS

i

LIGHTS

ENCO

t~

O

POWER

FV:L FLOW

COPILOT

GEN f( 20 IJ

AYIONICS

3

#_:5j)

5

FLIGHT

L

COMPASS

RCDR

r

i

STALL

ri

LEFT

(5i(S

FEATHER

3LE_D AI~ WARN

VOICE

LEFT

5

r

fEIR

LEFT

AUTO

AVIONICS

ENGINES

7------

LEFT

r

RMI

O NOD*T2 PROBE

~15R5A2

IND

HEAT

FLT

METSYS

LRN

ALTM

NO.2

ELEK

MULTI

RADIO

DSPL

FCTN

FCS POWER

TUNE

CONTR

DSPL

~7’2

dC

N0.2

C9~FL3980812

ORIGINAL As

Received BY ATP

(FM-9

Page 214 May 1/08

39-1 0-00

Circuit Breaker Panel and After, FL-120, FL-122 and Figure 206

After)

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

(A 124) ZONE 247

FUEL CONTROL PANEL The fuel control the

pilot. Toggle

panel (Ref. Figure

Figure 208) is located in the left interior sidewall of the airplane next to are provided on the panel to control the standby fuel pump, auxiliary circuits. Gages are provided on the panel to monitor the quantity of fuel gaging

207 and

switches and circuit breakers

fuel transfer, fuel crossfeed, and fuel in the fuel tanks.

REMOVAL OF TOGGLE SWITCHES a.

Wrap padding

CA UTION: When

they b.

around the

pilot’s

control column to protect the finish of the fuel control

performing maintenance around edgelit panels, always be repaired.

use care

not to scratch

panel. or

damage

the panels

as

cannot

Remove the six

screws

securing

the upper

edgelit panel

to the control

panel and carefully

remove

it from the

airplane. and washers at the top of the fuel control

c.

Remove the three

d.

Lean the top of the

e.

Tag

f.

Remove the

g.

Remove the switch from the backside of the

and

screws

panel

electrical

remove

jam

wiring

securing

nut

gain

away from the sidewall to

access

panel.

to the

toggle

switches.

from the switch to be removed.

the switch to the front side of the

panel.

panel.

INSTALLATION OF TOGGLE SWITCHES a.

Insert the switch into the

panel

from the backside of the

b.

Secure the switch to the

panel

with the

c.

Connect electrical

to the switch

d.

Manual.

Push the

top of the panel back

avoid

damaging

CAUTION: When

they e.

Install the

f.

Remove the

~a4

wiring

Diagram

the

wiring

or

jam

panel.

nut.

according

to

tags

or

the Hawker Beechcraft

to the sidewall and install the three

attaching

Super King

screws

Air B300

and washers. Use

Wiring

care

to

panels

as

other components.

performing maintenance around edgelit panels, always be repaired.

use care

not to scratch or

damage

the

cannot

edgelit panel padding

and

which

secure

was

with six

screws.

used to protect the finish

on

the

panel.

39-1 0-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ON

O

ENG

CROSSFEEC FLOW

ENGINEf

STANO~Y PUMP

T;

STANCBY PUMP

o

OFF O’F AUX

O-F

iFIA~SiER

PUX

OVERRIDE

s

s

a USABLC

4

NEL

1273

2

iBS

533

12-

EACH

AUX

AUTa

239 FUEL

L4S.100

12-

MANUAL

14

OTY

OVERRIDE

s

4

HAIN´•2 ~/FUU

EA3LI

LBS

SEE

ACITO O

cU_L

10

CUANTITY

all,

TRANSFER

14

LBS´•130

PY1

TEST

MaI~ MAIN/AUX

O

TANK

MAIN/AUX

TANK

RIGHT

LEF~ AUXILIARY

LEFT~FUEL FIRE WALI

VALVE

AUX

SIANOBY

TRANS

PUMP

FER

~TY

PR

IND

WAN

SS

RIGHT

SYSTEM

OTY

CR~SS

OTY

PRESS

OTY

WARN

FEED

WARN

WARN

IND

AUX

TRANS FER

STANCBY PUMP

FIRE WALL VALVE

5

AC ~o

26VAZ

BATTERY

BUS NO

I I5VAC 26VAC

2

AZ

i ISVAC

BUS

EBG

CONI

FIRE

LEFT

EX~

_NTRY

RIG-:T LIGHIS

GND COM

BUS

AVI\1CS

9AT

eus

RELAY

CONT

1

io

I

ORIGINAL As Received ATP

By

399-391-991

(FM-1

Fuel Control Panel thru FM-8, FL-1 thru FL-119 and

Figure

Page May

216

1/08

39-1 0-00

C

FL-121)

207

A24

Hawker 8eechcraft

Corporation

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

CRCSSFEED FLCW

ENGI~E

STANDBY PUMP Chi

ENG

STANDBY DUMP

i,

0"

O

OFF OFF

OFF

’Is

n´•NsiEa ilx OVERRIDE

f

AUIO

LBS

2

BS

~33

12

SEE

LBS´•

FU~L

1273USABLE

FUEL

EAC~

CUANTITY

O ~AIN/AUX

10

~Ciwv 1412-

X’JTf

LBS-IDO

TEST

p,

O

FUEL

AUX

MANUAL

FUEL

00

4

lyAIN

AUX IRANSiER OVERRIOE

e,

IJAIN MAIN/AUX TANK RI~HT

TANK

LEFT

O

AUXILIARY

FIRE WALL VALVE

O

SIANDBY PUMP

AUX

OiY INC

FUECO :ER

~RESS WARN

LEFT

AC

i,~"

OTY WARN

CROSS FEED

FUEL

OTY WARN

PRESS WARN

~1

AUX

OFUiC FER

STANDBY PUMP

FIRE WALI

O

VALVE

RIGHT

SYSTEM

ENGINE

BUS --7

I;?

OTY IND

INSTRUMENTS

""X""

sss 33333 26

VAC

rENG

5

FIRE

VA3 26

EXT

VAC

ENTRY

115

VAC

GND

CONT Iir

BUS~ AVNCS BPT BUS

ToRouF

PRO’ IACLI

TURBINE TbC-I

;LiEL rLOW

OIL PRESS

OIL T_MP

Csos9 LEFT

RIGHT

LI;~TS

COM

RELAY

CLINT

RIGHT

O

O

O

i

ORIGINAL As Received

By

ATP

C94FL39B08

(FM-9

Fuel Control Panel and After, FL-120, FL-122 and

Figure

A24

After)

208

39-1 0-00

Page 217 May 1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CIRCUIT BREAKER REMOVAL a.

Wrap padding

around the

pilot’s control column

to

protect the finish of the fuel control panel.

CAUTION: When

performing maintenance around edgelit panels, they cannot always be repaired.

b.

Remove the six

screws

securing

the upper

edgelit panel

not to scratch or

use care

panel

to the control

and

damage

carefully

the

remove

panels as

it from the

airplane. and washers at the top of the fuel control

c.

Remove the three

d.

Lean the top of the

e.

Pull apart the

f.

Tag

g.

Remove the jam nut

h.

Remove the circuit breaker from the backside of the

i.

Reinstall the jam nut

screws

panel away from the sidewall

hook-and-loop

and disconnect

wiring

fastener

securing

to

gain

the

plastic

from the circuit breaker

being

the front side of the fuel control

on

access

panel.

to the circuit breakers.

cover over

the circuit breakers and

the

remove

cover.

removed.

panel for the

circuit breaker

being

removed.

panel.

the circuit breaker to prevent loss.

on

CIRCUIT BREAKER INSTALLATION a.

Remove the jam nut from the circuit breaker.

b.

Insert the circuit breaker from the backside of the

c.

Install the

d.

jam

nut on the circuit breaker.

Connect electrical

Wiring Diagram e.

f.

Place the

panel.

wiring

to the circuit breaker

according

to

tags

or

the Hawker Beechcraft

Super King

Air 8300

Manual.

plastic

cover over

the circuit breakers and

secure

by pressing

Push the top of the panel back to the sidewall and install the three damaging the wiring or other components.

the

attaching

hook-and-loop screws

fastener

together.

and washers. Use

care to

avoid

CA UTION: When

performing maintenance around edgelit panels, they cannot always be repaired.

g.

Install the

h.

Remove the

edgelit panel padding

and

which

secure

was

with six

use care

not to scratch or damage the

panels as

screws.

used to protect the finish

on

the

panel.

REMOVAL OF FUEL QUANTITY GAGES instructed in REMOVAL OF TOGGLE SWITCHES to

a.

Lower the fuel control

b.

Remove the connector from the back of the fuel gage.

c.

Remove the four

Page

panel

attaching

as

screws on

21839-1 0-00

the front of the gage and

remove

gain

access to

the gages.

the fuel gage from the front of the

panel.

az4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INSTALLATION OF FUEL QUANTITY GAGES the fuel control

from the front and

a.

Insert the gage

b.

Connect the connector to the back of the gage.

c.

through

Push the top of the wires

panel

back to the sidewall and

panel

secure

secure

with three

with the four

screws.

Use

attaching

care

to avoid

screws.

damaging

the

components.

or

performing maintenance around edgelit panels, they cannot always be repaired.

CAUTION: When

edgelit panel

d.

Install the

e.

Remove the

and

padding from

OVERHEAD PANELS

secure

the

with six

pilot’s

use care

not to scratch

or

damage

the

panels as

screws.

control wheel.

ZONE 253

panels (Ref. Figure 209, Figure 210 and Figure 211) are located in the ceiling above the pedestal are two panels: the overhead light control panel and the overhead instrument panel. The light dimming transistors are exposed when the overhead light control panel is hinged open.

The overhead

controls. There

OVERHEAD LIGHT CONTROL PANEL

(A110)

REMOVAL OF RHEOSTA TS a.

Loosen the set

tone per knob)

screws

and

remove

the knobs from the rheostats.

CAUTION: When

performing maintenance around edgelit panels, they cannot always be repaired.

b.

Remove the six

screws

NOTE: Remove the the

panel

securing

screws

drop

to

the

edgelit panel

at the bottom of the

use care

to the overhead

panel

first.

Removing

not to scratch

or

damage

the

panels as

panel. the

screws

at the

top of the panel will allow

down away from the headliner.

edgelit panel.

c.

Remove the

d.

Remove the wires from the rheostat.

e.

Remove the

f.

Remove the rheostat.

jam

nut which attaches the rheostat to the

panel.

INSTALLA TION OF RHEOSTA TS a.

Insert the rheostat into the

b.

Secure the rheostat with the

c.

Install the wires

on

panel jam

from the back of the

panel.

nut on the front of the

panel.

the rheostat.

performing maintenance around edgelit panels, they cannot always be repaired.

CA UTION: When

d.

n24

Align

the

edgelit panel

with the

panel. While holding

the

panel

use care

in

not to scratch

or

damage

the

place, push it up against the airplane

39-1 0-00

panels as

structure.

Page

yaM912

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: When

pushing

the

panel

up

against

the

airplane structure,

use care

to avoid

damaging

the wires

or

components. e.

Secure the

f.

Install the knobs

panel

to the on

airplane

structure with

the rheostats and

tighten

screws.

the set

screws.

REMOVAL OF LIGHT DIMMING TRANSISTORS a.

Remove the top three

b.

Remove the two

c.

Remove the transistor.

screws

screws

from the overhead

and nuts

securing

light

control

panel

and lower it to

gain

access

to the transistors.

the transistor to the bracket.

INSTALLA TION OF LIGHT DIMMING TRANSISTORS a.

Place the transistor in the bracket.

b.

Secure the transistor to the bracket with two

c.

Push the overhead

panel

up

against

OVERHEAD INSTRUMENT PANEL

the

screws

airplane

and nuts.

structure and secure with three screws.

(A133)

REMOVAL OF INSTRUMENTS a.

Remove the four

b.

Pull the instrument out of the

c.

Remove the wires from the instrument.

d.

Removethe instrument.

screws

securing

the instrument to the

panel sufficiently

to

gain

panel (Ref. Figure 211).

access

to the wires.

INSTALLA TION OF INSTRUMENTS

Hold the instrument close

b.

Attachthewirestothe instrument.

c.

Push the instrument into the

panel being careful

d.

Secure the instrument to the

panel

Page

yaM02

1/08

enough

to the

to allow installation of the wires.

a.

39-10-00

panel

with four

not to

damage

wires

or

components.

screws.

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CDoNoToPEnnrE

DYHD

OFF

PARK

MPILOTOYHD

PILOT

ONDRYGLASS

WINDSHIELDWIPER

FLOOD

INDIRECT

FLOOD

OFF

OFF

OFF

SLOW

O

Fasr

BRT

snT

BRT

MASTER PANEL

PILOT

PILOT

COPILOT

COPILOT

LGKIS

FLIGHI

GYRO

ENGINE

I\YIONICS

OYHD FED

SDE

GYRO

FLIGHI

ON

INSTR

INSSR

INSTR

PANEL

LSUBPANEL

PANEL

INSTR

INSTR

OFF

OFF

OFF

OFF

OFF

OFF

OFF

OFF

B,,,m,RT,RT,m,,,RT,m OFF

OPERATION LIMITATIONS TM MARKINGSAND PLACARDS IN THIS AIRPLANE CONTAIN OFERATING

LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING TH(S AIRPLANE IN THE NORMAL

CABIN

PILOT

COPILOT

MIC

LIGHT

FUWI

NOSMK

MIC

NORMAL

BRIGHT

ON

FSB

NORMAL

CATEGORY AND IN COMPLIANCE WnH THE OPERATING LIMIT~TIONS

cQI

SIPITED IN THE FORM OF PLPIU\RDS

V

MARKINGS AND MANUALS NO ACROBATIC MANEUVERS INCLUDING SPINS ARE APPROVED

OXYGEN

CAUTION STALL WARNING IS INOPERATIVE

o

WHEN MASTER SWITCH IS OFF M

OFF

STANDBY COMPASS IS ERRATIC

F OFF

OXYGEN

FSB

MASK

MASK

WHEN WINDSHIELD I\~I-ICE ANDOR AIR CONDITIONER IS ON

THIS AIRPLANE APPROVED FOR VFR. IFR DAY

I

NIGHI OPERATIONS

FL39B98541SAA.AI

Overhead

´•´•-rP A24

Light Control Figure 209

Panel

ORIGi´•;:.i As Received By ATP

´•iZ

39-1000

Page 221 May 1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

o

,~´•TT 018

q

h~4 CR/

´•´•S

c

b´•~´•i CR6

GSI

S3

GS2

a/

isi Is)

O s4 SI

CR5

ca~

o

pe

S5

Sb

C;B1

A-; S7

Is)

~J

S8

S9

U

CR3

SO

ri

R3

8E

aRI~

n

R30

R20R28 R26R27

n

JIJ2

R2L aI 1

R23 aDI

R22

A o

Fi2 i

350-368-015

C

Overhead

Light Control Panel Components Figure 210 (Sheet 1 of 2)

ORIGINAL

Page 222 May 1/08

39-1 O 00

As Received ATP

By A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RI

R~ R3 R4

PILOT’S

FLIGHT

-COPILOT’S

GYRO

PILOT’S

INSTRUMENT

COPILOT’S

INSTRUMENT

GYRO

-ENGINE

RS

-SIDEPANEL

R7

-AVIONICS

RS

-OVERHEAD.

LIGHT PANEL

R9

PILOT’S

RIO

INSTRUMENT

R~I

COPILOT’S

R12

-WINDSHIELD

RESISTOR

LIGHT

LIGHT

INSTRUMENT

INSTRUMENT

R3

LIGHT

INSTRUMENT

FLIGHT

RESISTOR

-FURNISHINGS

57

-NO

S9

-COPILOT’S

SIO

-CABIN

RESISTOR

LIGHT

RESISTOR

RESISTOR

LIGHT

SS

RESISTOR LIGHT

PEDESTAL

OVERHEAD

OVERHEAD WIPER

SWITCH

SEAT

MICROPHONE

BELT

SWITCH

ALTITUDE WARNING BAROMETRIC PRESSURE SWITCH

RESISTOR

AND

SU3PANEL

FLOODLIGHT

INDIRECT

CONTROL

SMOKING/FASTEN LIGHT SWITCH

LIGHT

LIGHT

RESISTOR

RESISTOR

FLOODLIGHT

RESISTOR

RESISTOR

AND

J2

-PTN

Ai

-AMBIENT

BLOCKS LIGHT

01

-?ILOT’S

FLIGHT

SENSOR

ASSEMBLY

INSTRUMENT

LIGHT

TRANSISTOR

RESISTOR 02

-COPILGi’S FLIGHT INSTRUMENT LIGHT TRANSISTOR

03

-PILOT’S LIGHT

04

-COPILOT’S GYRO INSTRUMENT LIGHT TRANSISTOR

~R3

06

-STDEPANEL

IHRU

07

-AVIONICS

R21 THRU R21

-9IM

CONTROL

BIAS

RESISTORS

DI~

CONTROL

SIAS

RESISTORS

R~S THRU R3

CR6

-OIODES

08

S

-MkSTER

S~

-WINDSHIELD

PANEL

53

PILOT’S

53

CABIN

LIGHT

WIPER

SWITCH

MICROPHONE

LIGHT

LIGHT PANEL

TRANSISTOR

LIGHT

SUBPANEL TRANSISTOR

OVERHEAD TRANSISTOR

-PILOT’S

OI0

-INDIRECT INSTRUMENT TRANSISTOR -COPILOT’S OVERHEAD TRANSISTOR

OI8

AND TRANSISTOR

TRANSISTOR

AND

PEDESTAL

FLOODLIGHT

09

SWITCH

SWITCH

INSTRUMENT TRANSISTOR

OVERHEAD. LIGHT

SWITCH

GYRO

LIGHT

FLOODLIGH?

PEDESTAL

LIG~7

GS

AND GS2

-GROUNC

STUDS

ORIGINAL As Received

By

AfP

C9~3981514 C

Overhead

A24

Light Control Panel Components Figure 210 (Sheet 2 of 2)

39-1 0-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

W3J1

A

A

S2

S1

I

OFF

I

OFF

I

2ml I HANEUYERING EMERGENCY

LIGHTS

m~o

S2J1

M4 M1

Mi

M3

W3J2

Slj,

MAGNETIC COMPASS

COMPONENTS M1 M2 M3 M4 S1 S2 A

LEFT DC LOADMETER RIGHT DC LOADMETER DC VOLTMETER AND BATTERY AMMETER PROPELLER AMMETER EMERGENCY LIGHT SWITCH VOLTMETER BUS SELECT SWITCH JUMPER ASSEMBLIES

W3J1 W3J2 S1J1 S2J1

OVERHEAD INSTRUMENT LIGHT WIRE CONNECTOR MAGNETIC COMPASS LIGHT MATING WIRE CONNECTOR EMERGENCY LIGHT WIRE CONNECTOR WIRE RECEPTACLE

FA33B 985422AA.AI

Overhead Instrument Panel

Figure

211

ORIGINAL

Page 224 May 1/OS

39-1 0-00

As Received By ATP

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CENTER SECTION AND WING ELECTRICAL PANELS The center section and

wing

electrical

panels

are

located

on

MAINTENANCE PRACTICES

the left and

right

sides of the

airplane

in the

wings

and

center section.

The electrical

panels

components of the fuselage

and

are

listed in

Chapter 39-21-00, FUSELAGE ELECTRICAL

PANELS.

VARIABLE HEAT CONTROL AND STALL WARNING PANEL

(A 150) LOCA TION ZONE 522

panel is located (Ref. Figure 201).

drag

The

in the LH nacelle wheel well, behind the

landing

VARIABLE HEAT CONTROL AND STALL WARNING PANEL a.

Turn off the electrical power to the

b.

Removethe

c.

Mark to

d.

brace and behind the mud

guard,

REMOVAL

airplane.

mudguard.

identify

all wires and disconnect them.

Remove the five bolts and washers from the

gear

(three

on

the forward end and two

on

the aft

end)

and

remove

the

panel

airplane.

VARIABLE HEAT CONTROL AND STALL WARNING PANEL Position the

b.

Connect all the wires to the

c.

Connect the wire

d.

Install the mud

e.

Turntheelectrical poweron.

panel

on

the

mounting

a.

bracket and

secure

INSTALLATION

with five bolts and washers.

panel.

plug.

guard.

39-20-00

Page

yaM102

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Fdnwano

0-

R1

OU

LL_II

I"~

-0-

A

CR1

QP~ R2

K1

-O

AFT

J1 300-355-12

Variable Heat Control and Stall

Figure

May

1/0839-20-00

Warning

Panel

201

nz4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LEADING EDGE ELECTRICAL EQUIPNIENT PANEL The

panel is located approximately leading edge, (Ref. Figure 202).

(A227) LOCA TION ZONE 51 1

24 inches from the left side of the

fuselage,

inboard of the nacelle, inside the

LEADING EDGE ELECTRICAL EQUIPMENT PANEL- REMOVAL a.

Shut off all electrical power to the

b.

Remove the

c.

Mark to

d.

Disconnectthe

e.

Remove the four

airplane

leading edge assembly

identify

electrical system.

between the nacelle and

and disconnect the wires connected to the

fuselage.

panel assembly.

jumperassembly. attaching

bolts and washers and

LEADING EDGE ELECTRICAL EQUIPMENT PANEL in

and

Position the

panel

b.

Connect the

jumper assembly.

c.

Connect the wires to the proper marked terminals.

secure

the

panel.

INSTALLATION

with four bolts and washers.

a.

place

remove

Refer to

Chapter 20-03-00, Torque

ELECTRICAL BONDING. the nuts

on

the

relay

terminals to 127 to 159 inch-

pounds. d.

Installtheleading edgeassembly.

e.

Turn

on

the electrical power to the

airplane.

TB

KtOl

W120

COMPONENTS K101

HYDRAULIC LANDING GEAR POWER RELAY

W120

CB101

Telos,

-BUSBAR LANDING GEAR MOTOR CIRCUIT BREAKER (60 AMPS)

CB102

LANDING GEAR TIMER POWER CIRCUIT

I/

I,

W

_I

BREAKER(5AMPS) JUMPER ASSEMBL~ TB102

TERMINAL BOARD

TB103

TERMINAL BOARD

E235

LEFT GENERATOR BUS TIE CURRENT SENSOR

CB102

Leading Edge

Electrical

Figure

A24

350-65-23

Equipment

Panel

202

39-20-00

Page

yaM302

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STANDBY FUEL PUII/IP RADIO FREQUENCY

(RF) FILTERS (A23 I

AND

A232) LOCA nON

ZONES 521, 621. One filter is located

the bottom side of each nacelle, aft of the firewall, at

on

Fuselage

Station 154 and Buttock Line

103, (Ref. Figure 203). STANDBY FUEL PUMP RADIO FREQUENCY

I

a.

Remove the

b.

Mark to

c.

Remove the nut and washer

FILTERS

REMOVAL

the bottom of the nacelle.

access cover on

identify

(06)

and disconnect the wires connected to the ends of the filter.

securing

the filter to the bulkhead and

STANDBY FUEL PUMP RADIO FREQUENCY a.

Place the filter in the proper

b.

Connect the wires to the ends of the filter.

position

on

(RF)

FILTERS

the bulkhead and

o

INSTALLATION

secure

o\

with the washer and nut.

O

O

o/U~o\ I

o

o

the filter.

RIGHT STANDBY FUEL PUMP

n

O

remove

o

/O olS~

O

I /o~H\o AFT

O

O

O

O

O

O

O O)

O

O

O

LEFT STANDBY PUMP

~o

FU5L

FL106

FL105

O

O

O

O O

O

ol lo~ X ~o

~cl

o/

I I

ion

x ~ol to

I I

\O 0.

I I

VIEW LOOKING UP AT RIGHT NACELLE

VIEW LOOKING UP AT LEFT NACELLE

Standby Fuel Pump

RF Filter

FL105

Left

F1106

Riaht Standby Fuel Pump RF Filter

350-64-15

Standby Pump Radio Frequency Filters Figure 203

May

1/08Page

204

39-20-00

an4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INBOARD NACELLE POWER DISTRIBUTION ELECTRICAL PANELS LOCA TION

panels are located (Ref. Figure 204).

on

the inboard sides of the nacelle. One above and

INBOARD NACELLE POWER DISTRIBUTION ELECTRICAL PANELS a.

Remove the two

b.

Turn off all electrical power.

c.

Remove the forward

access

doors

panel

as

on

the inboard side of the

one

forward of the

wing leading edge

follows:

Disconnect the feed-thru

assembly

from the forward terminal of the R1 shunt.

3.

Disconnect the feed-thru

assembly

from the forward terminal of the K2

4.

Mark to

5.

Disconnect the

Remove the aft

2.

Mark to Make

screws

remaining

from the

and washers

wires to the

on

relay.

relay.

panel.

panel.

(three

upper and three

lower)

that

secure

the

panel

and

remove

the

airplane.

panel

identify

sure

and disconnect all

jumper assembly

Remove the six the

panel

interconnect bus bar

the aft terminal of the K1

2.

identify

wing leading edge,

above the LH nacelle.

Disconnect the forward and aft

1.

A252)

REMOVAL

1.

panel from d.

AND

ZONES 521, 621

The

6.

(A251

as

follows:

and disconnect all wires connected to the

the forward and aft

panel

panel.

interconnect bus bar to the forward

panel

is disconnected,

or

disconnect the bus bar from the upper terminal of the F1 limiter. 3.

Remove the six

screws

and washers

(three

upper and three

lower)

that

secure

the

panel

and

remove

the

panel from the airplane.

~a4

39-20-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I

INBOARD NACELLE POWER DISTRIBUTION ELECTRICAL PANEL- INSTALLATION Install the aft

a.

panel

as

follows: in the aft

1.

Position the

2.

Connect all wires to the

panel

Installtheforward

b.

access

opening

on

the nacelle and

secure

the aft

and

with six

screws

and washers.

panel.

panelasfollows: in the

opening forward of

panel

with six

and washers.

i.

Position the

2.

Connect the wires to the

panel assembly. Refer to Chapter 20-03-00, ELECTRICAL BONDING.

3.

Connect the wires to the

panel assembly.

4.

Connect the feed-thru

assembly

terminal to the forward terminal of the K2

5.

Connect the feed-thru

assembly

terminal to the forward terminal of the R1 shunt.

6.

panel

access

Connect the forward and aft

panel

interconnect bus to the aft K1

secure

screws

relay.

relay terminal and,

if

required,

to the upper

terminal of the F1 limiter. c.

Install the two

d.

Turn

May

on

access

doors

covering

the electrical power to the

the two

panels.

airplane.

1/0839-20-00

n2i

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

F8

F7

F6

F5

~V

F4

11(0)1~ Fi2

AFT

O O

O

O

K1

2

Oug

w

AFT PANEL

i

CB1

CB3

CB2

CB4

I

K1

O

CB5

I~R1

O

350-355-24

FORWARD PANEL

Inboard Nacelle Power Distribution Electrical Panels

Figure 204 (Sheet

A24

1 of

2)

39-20-00

Page

yaM702

1/08

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

COMPONENTS

(AFT PANEL)

K1

GENERATOR

BUS

TIE

F1

GENERATOR

BUS

TIE

LIMITER

F2

GENERATOR

SUB

BUS

LIMITER

F4

SPARE

LIMITER

F5

SPARE

LIMITER

F6

SUBPANEL

F7

CIRCUIT

F8

TRIPLE

W

BUS

COMPONENTS

RELAY

LIMITER BREAKER

BUS

PANEL

LIMITER

BAR

(FORWARD PANEL)

CBI

LOAD

METER

NEGATIVE

CIRCUIT

BREAKER

CB2

LOAD

METER

POSITIVE

CIRCUIT

BREAKER

CB3

GENERATOR

FIELD

CB4

GENERATOR

CONTROL

PANEL

CIRCUIT

BREAKER

CB5

GENERATOR

CONTROL

PANEL

CIRCUIT

BREAKER

K1

LINE

K2

START

R1

SHUNT

CONTRACTOR

A

JUMPER

W

BUS

AND

SENSE

CIRCUIT

BREAKER

RELAY

RELAY

ASSEMBLY

BAR

350-355-038

Inboard Nacelle Power Distribution Electrical Panels

Figure

May

39-20-00

204

(Sheet

2 of

2)

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BA TTER Y PO WER AND DISTRIBUTION EQUIPMENT PANEL The

panel is located (Ref. Figure 205).

on

the RH

wing,

inboard of the nacelle, forward of the

BATTERY POWER AND DISTRIBUTION EQUIPMENT PANEL a.

Remove the RH

b.

Lift and

leading edge

between the

back to

disengage the three button gain access to the panel.

c.

Mark to

identify

d.

Disconnectthejumper assemblies.

e.

Remove the four bolts and washers that

snaps

fuselage

securing

the

the fabric

Position the

panel

b.

Connect the

jumper

c.

Connect the wires to the

panel.

d.

Install the

cover over

panel

e.

Install the

leading edge assembly.

on

the

mounting

brackets and

assemblies. Refer to

the

and

leading edge,

REMOVAL

panel

secure

cover

assembly

and

remove

the

over

panel

the

panel. Move the

cover

from the

airplane.

INSTALLATION

with four bolts and washers.

Chapter 20-03-00, ELECTRICAL

secure

box and under the

panel.

BATTERY POWER AND DISTRIBUTION EQUIPMENT PANEL a.

battery

and nacelle.

and disconnect the wires connected to the

secure

(A228) LOCA TION ZONE 6 1 I

BONDING.

with the three button snaps.

39-20-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AF1

K

K135

24

F

Oi

CR180

Wi

E~34

CRI

b

A

A

7-

o

o

FLOW

CalSk 236

Te13~

Klr"l

COMPONENTS KI~I CRI K1~4 1(135 CR 80 CB 54 E~34 E~36 F 01 TB 04 W 16

BATTERY

BUS

iIE

RELAY

IRANSLORB

EXTERNAL BATTERY

POWER

RELAY

RELAY

TRANSZORB

REMOTE

CONTROL

BATTERY

6US

GENERATOR

BUS

AND

SPARE

TERMINAL

BOARD

FUSE BUS

CIRCUIT

TIE

CURRENT

TIE

BREAKER ASSEMBLY

SENSOR

CURRENT

SENSOR

ASSEMBL\I

BAR

JUMPER

ASSEMBLY

W0-355-025

Battery

Power and Distribution

Figure

Equipment

C

Panel

205

ORIGINAL As Received

Page

210

May 1/08

39-20-00

By

ATP

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXTERNAL POWER RECEPTACLE

(JI 12) LOCA nON ZONE 61 1

The external power

receptacle is located along leading edge, (Ref. Figure 206). EXTERNAL POWER RECEPTACLE Remove the leading edge fairing

b.

Remove the top and bottom forward

c.

Mark to

d.

edge of

the

REMOVAL

a.

identify

the outboard side of the RH nacelle, at the aft bottom

on

the outboard side of the nacelle. access

panel along

the outboard side of the nacelle.

and disconnect the wires from the external power

receptacle.

Remove the bolt, washer, nut, and lock washer securing the aft bus bar to the airplane structure. Remove the securing the aft bus bar to the external power receptacle and remove the bus bar.

nut and washer e.

Remove the two screws, washers, and nuts securing the external power receptacle and from its

mounting

EXTERNAL POWER RECEPTACLE a.

b.

Position the external power Place the aft bus bar

over

receptacle

on

its

mounting

bracket and

the aft terminal of the external power

(refer to Chapter 20-03-00, ELECTRICAL BONDING) Torque the nut to 270 to 300 inch-pounds.

c.

Secure the bus bar to the aft terminal with the nut and washer.

d.

Connect the wires to the external power receptacle and on

the

receptacle

INSTALLATION

structure

washer.

remove

bracket.

the center terminal to 115 to 144

secure

inch-pounds. Torque

secure

with two screws, washers, and nuts.

receptacle. and

secure

Torque

Bond the bus bar to the with the bolt,

airplane washer, nut, and lock

the nut to 115 to 144

inch-pounds.

each with the nut and washer.

the nut

on

Torque

the nut

the forward terminal to 15 to 10 inch-

pounds. e.

Apply inspection lacquer to

f.

Install the

access

g.

Install the

fairing

aa~

all

torqued

nuts.

panels.

over

the

leading edge.

39-20-00May

1/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

J282

CB205

5

GS149

O

CB204

((i

OOo

O

J112

~QRWARD

CB205

C8204 300-351-14

External Power

Figure

Page

yaM212

1/08

39-20-00

Receptacle 206

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

FUSELAGE ELECTRICAL PANELS

fuselage electrical panels assembly of the airplane.

The

The electrical

are

MAINTENANCE PRACTICES

located inside the

fuselage

panels and components of the center section Wing Electrical Panels, 39-20-00.

and

from the

wing

are

flight compartment

to the empennage

listed in

Center Section and

LEFT HAND FORWARD FLIGHT COI~1PARTMENT EQUIPMENT PANEL

(A225)

LOCA TION

ZONE 221 The

panel (Ref. Figure 201)

is located forward of the instrument

panel

above the rudder

pedals

on

the forward

pressure bulkhead. REMOVAL

identify

a.

Mark to

b.

Disconnect

c.

Remove the

and disconnect all wires and wire

clamps connected

to the

panel.

thejumperassembly. eight

screws

and washers that

secure

the

panel

and

remove

the

panel.

INSTALLATION a.

Position the

b.

Connect the jumper

c.

Connect all wires and wire

panel

in

place

and

assembly.

secure

Bond

clamps

with

as

eight

instructed in

to the

and washers.

screws

(Ref. Chapter 20-03-00).

panel.

RIGHT HAND FORWARD FLIGHT COMPARTMENT EQUIPMENT PANEL

(A226)

LOCA TION

ZONE 222 The

panel (Ref. Figure 202)

is located forward of the instrument

panel

above the rudder

pedals

on

the forward

pressure bulkhead.

REMOVAL

identify

a.

Mark to

b.

Disconnectthe

c.

Remove the

and disconnect all wires and wire

clamps

connected to the

panel.

jumper assembly.

eight

screws

and washers that

secure

the

panel

and

remove

the

panel.

INSTALLATION in

a.

Position the

panel

b.

Connect the

jumper assembly.

c.

Connect all wires and wire

nw

place

and

secure

Bond

clamps

with

as

eight

screws

instructed in

to the

and washers.

(Ref. Chapter 20-03-00).

panel.

39-21-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

I

FWD

ha:

I\

E241

K

,J B

:9’\K119

CB194

II

o

CR12

124

E16

o

O

0)~

0)1-~

I

’-L(O

\B ~II

I

W117

B

CI\ COMPONENTS K118 K119

CR124 CR128 W117 E116

PILOT’S PILOT’S DIODE DIODE BUS BAR PILOT’S

WINDSHIELD WINDSHIELD

ANTI-ICE ANTI-ICE

WINDSHIELD ANTI-ICE ASSEMBLY PILOT’S WINDSHIELD ANTI-ICE CIRCUIT BREAKER (5 AMP) JUMPER ASSEMBLY OPTIONAL PITOT HEAT CURRENT (FL-289 AND AFTER: FM-II AND

HIGH HEAT RELAY LOW HEAT RELAY

TEMPERATURE

CONTROL

CB194 A E241

Left Hand Forward

Page

20239-21-00

CONTROL

SENSOR

AFTER)

Flight Compartment Equipment Figure 201

Panel

A24

Corporation

Hawker Beechcraft

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

FWD~ I

f Z

I

I

,:IIf I

I

Z

I

f II K

I I

I

1

II

I

B

I,

rI ,I

II

Il

K120/Io)~ ~(Ont<123/ o

I

II

I

E124

:RI

125

,I

BI~ O) J-’

111 (II

III

~-L 10

O

I 1 U

1 i

W118

O

I

I

I

~b

I 1

E242

a I m

/I/

cru IO;II

9

D

COMPONENTS K120 K123 CR125 CR129 W118 E124 C8193

COPILOT’S WINDSHIELD COPILOT’S WINDSHIELD DIODE DIODE BUS BAR COPILOT’S WINDSHIELD CONTROL ASSEMBLY COPILOT’S WINDSHIELD

CIRCUIT BREAKER A

E242

Right

A24

JUMPER

ANTI-ICE LOW HEAT RELAY ANTI-ICE HIGH HEAT RELAY

ANTI-ICE

TEMPERATURE

ANTI-ICE CONTROL (5 AMP)

ASSEMBLY

OPTIONAL PITOT HEAT CURRENT SENSOR (FL-289 AND AFTER: FM-II AND AFTER)

Hand Forward

Compartment Equipment Figure 202

Panel

39-21-00

Page

yaM302

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

AC POWER DISTRIBUTION AND LIFT COMPUTER PANEL This

panel (Ref. Figure 203) is located

under the floorboard

just

(A263) LOCA TION ZONE143

ahead of the emergency exit doors,

on

the

airplane

centerline between FS 168 and FS f 80.

REMOVAL a.

Remove the carpet

runner

and the forward floorboard from the center aisle.

WARNING: Use caution when

removing

hot to the touch for Mark to

c.

Disconnect the

d.

Remove the six

time after

some

(61 through R5),

as

they

may be

use.

all wires and disconnect them from the

identify

b.

the wires from the resistors

panel assembly.

jumper assembly. screws

and washers and

remove

the

panel

from the

airplane.

INSTALLATION the

airplane

a.

Position the

panel

b.

Connect the

jumper assembly and

c.

Connect all wires to the

d.

on

structure and

bond

as

Install the floorboard and the carpet

panel is located

with six

instructed in

screws

and washers.

(Ref. Chapter 20-03-00).

panel assembly. runner.

MAIN POWER DISTRIBUTION PANEL The

secure

(A 145) LOCA TION ZONE

143

below the first center aisle floorboard, between the emergency exit doors

(Ref. Figure 204).

REMOVAL a.

Remove the center aisle carpet forward of the main spar.

b.

Remove the floorboard forward of the main spar.

c.

Mark to

identify

and disconnect all wires to the

d.

Mark to

identify

and disconnect all the wire

e.

Disconnect the

f.

Page

panel from

plug

assemblies.

jumper assembly.

Remove the six the

panel assembly.

screws

the

and washers

tone

in each

corner

and

one

each

by

the K5 and K6

relays)

and

remove

airplane.

39-21-00

P124

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

COMPONENTS JI

J2 CBI CB2 CB3 CB4 CB5 E196 GSI TBI GS2 El RI R2

R3 R4 R5 GS3 PSI A

II

RECEPTACLE RECEPTACLE ND.I INVERTER MONITOR ND.I INVERTER MONITOR N0.2 INVERTER MONITOR

[115 VACI [26 VACI [115 VAC) [26 VAC)

NO.2 INVERTER MONITOR AC TEST JACK AND ELECTRIC LIFT COMPUTER GROUND STUD TERMINAL BOARD

LIGHT

PANELS

GROUND STUD FREE AIR TEMPERATURE REMOTE PROCESSOR GROUND IDLE STOP RESISTOR GROUND IDLE STOP RESISTOR GROUND IDLE STOP RESISTOR GROUND IDLE STOP RESISTOR HYDRAULIC LANDING GEAR SHUTOFF RESISTOR GROUND STUD ENGINE INSTRUMENT LIGHT DIMMER JUMPER ASSEMBLY

43~

I~

as

I

I

O

I

FS

168.75

o6e

98

REF

JI

CBI

C82 CB3

C~4

J2

CB~

E196

FORWARD

aR71

O

TBI

GS2

GSI 234

678 PSI

GS3

I

i

/F

S

179.

U

A

REF

~Y

BL 00.00 REF c

AC Power Distribution and Lift

Figure

A24

Computer

Panel

203

39-21-00

Page

yaM502

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

O

O

wi

O

CR9\

CR6

o;I

CR7

KI

K2

K3

K4

CR8

O K6

CR I I ’--UC

GS I GS3

K71~

VR I

CR12

332 334

K8 CR13

~---1

VR2

PI

W125

(Typical) 2)

Main Power Distribution Panel

Figure

Page

20639-21-00

204

(Sheet

1 of

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

B

~i‘7i

O

O

B

w

I I i

i i

(i~I

I

T’T’7

i

fiBys c fi

i I

II I I

130I

CB47

I1

Il

O

fi

/I

1

CBag

Ca48

I

ii i I

r

A

DETAIL

CENTER L

PROP

OC

TEST

OEICE

JACK

Cs I

CB9

SUB

NC.

PANEL

C) C) CB7 L

GEN

SUB

BAR

C821

VENi BLCWER

OEISE

ANEL

CB17

PANEL

j~ C837

C935

2833

D_I=E

3U5

BUS

1814 FE3

SUB

BUS

CB

3

CB

8

i O

Cs

AC

CLUTCH

CBaO

i

2

BUS

’3~ CB22

CB2a

NC.2 INVERTER

CB26

sUS

FUEL AVIONICS

CONTROL"ANEI

C88

GEN

EVAP BLOWER

2316

C

B

C

B

PANEL

PANEL

CB28

CB30

PANEL

B PANEL

0832

CB34

C

B

TOILET/

C

VANITY

~Z CB31

Cs29

C827

C346

n2

CB36

CB3B

-CT~3

(IIjl:

O

ROTATED

83"

DETAIL

ORIGINAL

A24

CB6 R

~O

CBi3

-W

As Recerved ATP

CB4

/RWSHDAVIONICSAFT

TRLLE

FU_I

C82

ri 5

R PROP\ DEICE

C) C)

CBC5

AVIONICS BUS 2

CB

TIE

POWER

C) CB

~j: CBi9

4SUB

AUTC’ROP

ii~ 1

BUS scis

BUS

(3 ~1 28~3

CB3

CB5

L

CB25

0

i

INVERTER

By

FOR

O

CLARITY

B

350-354-028.~1

Main Power Distribution Panel

Figure

204

(Sheet

2 of

(Typical) 2)

39-21-00

Page 207 May 1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

MAIN POWER DISTRIBUTION PANEL COMPONENTS

NOTE:

Typical installation,

K1

Condenser Blower

K2

#1 Avionics Power Bus

Relay

K3

#2 Avionics Power Bus

Relay

K4

#3 Avionics Power Bus

Relay

CR6 THRU CR9 K6-

Furnishings

Bus

K7

Left

K8

Right Propeller

R1

Propeller

Propeller

W125

Deice Manual Override

on

airplane

serial number.

Relay

Deice Manual Override

Relay

Transzorb Assemblies

Deice Timer

Deice Timer

Plug

VR2

Right Generator Control

Panel

Bus Bar

GS1 Thru GS4

Ground Studs

Jumper Assembly

COMPONENTS

I

serial number.

Relay

Left Generator Control Panel

A

airplane

Relay

VR1

W1

on

Deice Ammeter Shunt

Propeller

Propeller

P1

depending

occur

Transzorb Assemblies

CR11 THRU CR13

I

variations will

(SHEET 1)

NOTE:

(SHEET 2,

Typical installation,

DETAIL

A)

variations will

occur

depending

CB47

Air-Conditioner Condenser Blower Circuit Breaker

CB48

Aft Electric Heat Circuit Breaker! Electric Heat Circuit Breaker

CB49

Forward Electric Heat Circuit Breaker

W1

Bus Bar

Page

20839-21-00

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

COMPONENTS NOTE:

(SHEET 2,

Typical installation,

DETAIL

B)

variations will

CB1

No. 1 Inverter Circuit Breaker

CB2

Condenser Blower Circuit Breaker

CB7

Subpanel

CB9

DC Test Jack Circuit Breaker

occur

depending

on

airplane

serial number.

Feeder Circuit Breaker

CB10

Bus Tie Power circuit Breaker

CBII

Left Manual

CB12

Right

CB13

Radiant Heat Circuit Breaker

CB14

Copilot

CB15

No. 2 Avionics Bus Feeder Circuit Breaker

CB16

No. 3 Avionics Bus Feeder Circuit Breaker

CB17

Ventilation Blower Power Circuit Breaker i FWD Cabin Blower Power Circuit Breaker

CB18

Aft Evaporator Blower Power Circuit Breaker

CB19

Left Refreshment Bar Circuit Breaker

CB20

SMS Circuit Breaker

CB22

Cockpit

CB24

Air-Conditioner Clutch Circuit Breaker

CB25

115 VAC Inverter Power Circuit Breaker

CB26

No. 2 inverter Circuit Breaker

CB27

Fuel Panel Feeder No. 2 Circuit Breaker

CB28

Circuit Breaker Panel Feeder No. 1 Circuit Breaker

CB29

Bus Tie Control Circuit Breaker

CB30

Circuit Breaker Panel Feeder No. 2 Circuit Breaker

CB31

No. 2 Fuel Panel Feeder Circuit Breaker

CB32

Circuit Breaker Panel Feeder No. 3 Circuit Breaker

CB33

Subpanel Feeder Circuit

CB34

Circuit Breaker Panel Feeder No. 4 Circuit Breaker

A24

Propeller Deice Circuit

Manual

Breaker

Propeller Deice Circuit

Breaker

Windshield Deice Circuit Breaker

AFT Cabin Blower Power Circuit Breaker

Blower Circuit Breaker

Breaker

39-21-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

CB37- Auto

I

Propeller

Deice Circuit Breaker

CB38

Toilet/Vanity

CB46

Avionics Feeder Triple Fed Bus Circuit Breaker

Circuit Breaker

CRI THRU CR3 Diodes

INSTALLATION a.

Position the

panel

b.

Connect the

jumper assembly. Bond

c.

Connect all the wire

d.

Connect all the wires to the

e.

Install thefloorboard.

f.

Install the carpet.

Page

on

the

plug

mounting

brackets and as

secure

instructed

with six

screws

and washers.

(Ref. Chapter 20-03-00).

assemblies.

panel.

39-21-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

PRINTED CIRCUIT CARD RACK LOCA TION The

ZONE 143

printed circuit card rack is located under the floorboard in the pedestal, between FS 143 and FS 158 (Ref. Figure 205).

center of the

airplane, approximately

one

foot aft

of the

REMOVAL a.

Remove the carpet at the

b.

Remove the center aisle floorboard forward of the

c.

Remove the

d.

Mark to

e.

Disengage

f.

Mark to

g.

Disconnect

h.

plastic

identify

securing

the

quick-release

flight compartment partition.

to the terminal board.

fasteners that

secure

the

cover

to the rack and remove the cover.

the circuit card connectors and disconnect the connector from each card.

thejumper assembly.

Remove the six bolts and washers the

cover

seats.

the wires and disconnect the wires from the terminal board.

the four

identify

nuts

flight compartment

(three

forward and three

aft)

that

secure

the rack and

remove

the rack from

airplane.

INSTALLATION a.

b.

Position the rack in

Connect the

place

on

the

mounting

jumper assembly. Bond

as

c.

Connect the card connectors to the

d.

Install the

e.

Connect the wires to the terminal board.

f.

Install the

g.

Install thefloorboard.

h.

Installthe carpet.

a24

cover on

cover on

brackets and

instructed

printed circuit

secure

with six

attaching

bolts and washers.

(Ref. Chapter 20-03-00).

cards.

the rack.

the terminal board.

39-21-00

PMa Sye$~May

1/08

Hawker Beechcraff

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

O

L~-i-

O

’.j P"’

S510

12

AC POWER

10

BAT.

MARGE

9

MONITOR

MON/BRAKE DI

A320

TIMER/AMBIENT AIR TD

AUTO FUEL TRANSFER

A170

A149

I B

BUS TIE

7 ANN FIULT

N,

5

4

L

R

SPEED/R In

VANE SENSE

TIHER/R GND

AFNUNCIATOR FAULT DETECT

NO.

A319

A130

ADVISORY LT TEST/HYDR LDG GEAR TD

ADVISORY LT TEST/SURF DI

3

A257

DETECT NO 3/L ICE VANE SENSEIL GNO IOLE STOP TO

6

0114

CONTROL

A129

IDLE STOP TO

A140

I

A127

Q113 2

ANNUNCIATOR

FALCT

ANNWCIAT(FI

DETECT

A126

CONTROL

A125

7218T2.0N

0112

00 O

9E

i __

__

350-354-025

C

Printed Circuit Card Rack

Figure

May

1/0839-21-00

205

A24

Hawker Beechcraff

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

PRINTED CIRCUIT CARD RACK A125

Annunciator Control PCB

A126

Annunciator Fault Detect No. 2 PCB

A127

Annunciator Fault Detect No. 1 PCB

Al 29

Left

A130

N1

A140

Right Advisory Light

A149

Auto Fuel Transfer PCB

Al 70

Battery Charge

A257

Bus Tie Control PCB

A319

Annunciator Fault Detect No. 3/Left Ice Vane Sense/Left Ground Idle

A320

AC Power Monitor PCB

0112

Advisory Lights

0113

Caution

0114

Warning Lights

S510

Cabin Altitude

A

Advisory Light Test/Hydraulic Landing

Gear Time

Delay

PCB

Ice Vane Sense PCB

Speed/Right

Test/Surface Deice

Timer/Right

Ground Idle

Monitor/Brake Deice Timer/Ambient Air Time

Stop

Time

Delay PCB

Delay PCB

Stop

Time

Delay

PCB

Dim Control Transistor

Dim Control Transistor

Lights

Dim Control Transistor

(10,000 FT.)

Caution Switch

Jumper Assembly ZONE 143

PRINTER CIRCUIT CARD BOX LOCA TION The

printed circuit

card box

is located between FS 158 and FS 167, under the second floorboard

(Ref. Figure 206)

forward of the front spar. REMOVAL a.

Remove the carpet forward of the front spar.

b.

Remove the first center floorboard forward of the front spar.

c.

Pull up

d.

Loosen the two

e.

Mark to

f.

Disconnect the

g.

Remove the six

Ms

on

the four

plungers

and

quick-release

identify

and

remove

remove

fasteners

the

cover

securing

assembly

from the

printed

circuit card box.

each circuit card retainer and

remove

the retainers.

all card connectors

jumper assembly. screws

and washers and

remove

the

printed circuit card box from

the

airplane.

39-21-00

PMa 9yel~:May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

RELEASE

~UIeK

FASTENER

CIRCUIT

CARD

RETAINER

--------7

1

I

e=o:~s

~B,s

8

A

~I

Al~Oi

A~59

A~66

A~60

A

A~7a

19

A123

CIRCUIT

CARD

CIRCUIT

CARD

CIRCUIT

CARD

PRINTED CIRCUIT RELAY PANEL PRINTED CIRCUIT RELAY PANEL PRINTED CIRCUIT EXTERNAL POWER CONTROL PRINTED CIRCUIT CARD

CARD

8

R~LAY

PANEL

A119

RELAY

PANEL

Ai~a

R~LAY

A121

RELAY

PANEL PANEL

Al

A12~ A260

PRINTED PRINTED PRINTED

CARD

A264

FIRE EXTINGUISHER TEST PRINTED ~IRCUIT CARD

AZ69

PROP

INDICATOR CIRCUIT CARD

PITCH

~RINTED A~78

ELECTRIC

PRINTED

CARD A

JUMPER

HEAT CONTRGL CIRCUIT CARD

ASSEMBLY

350-354-026

5

ORIGINAL As Recalvad By ATP

Printed Circuit Card Box

Figure

Page

yaM412

1/08

39-21-00

206

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

INSTALLATION a.

Position the

panel

b.

Connect the

jumper assembly.

c.

Connect the card connectors.

d.

Place the two circuit card retainers

on

e.

Position the

f.

Install the floorboard.

g.

Install the carpet.

cover

the

mounting

assembly

brackets and

Bond

in

as

over

place

secure

instructed

and

secure

screws

and washers.

(Ref. Chapter 20-03-00).

the circuit cards and

AFT ELECTRIC HEA T EQUIPI~ENT PANEL The

with six

by pushing

secure

by tightening

down the four

the

quick-release

fasteners.

plungers.

(A2 16) LOCA TION ZONE

163

panel (Ref. Figure 207 and Figure 208) is located under the center aisle floorboard even panel is between FS 251 and FS 261,just right of the center line of the airplane.

with the fifth cabin

window. The

REMOVAL a.

b.

Disconnect all electrical power to the Remove the center aisle carpet.

c.

Remove the third floorboard aft of the

d.

Tag identify assembly.

e.

airplane.

and disconnect all

Disconnect the

wiring

rear

spar.

from the electrical components

on

the aft electric heat

equipment panel

jumper assembly.

f.

Remove the four bolts and washers that

g.

Removethe

secure

the

panel

to the

mounting

brackets

panel.

INSTALLATION a.

Position the

b.

Cdnnect

c.

Connect all

panel

on

mounting

brackets and

secure

with four bolts and washers.

thejumperassembly. wiring

to the

d.

Install the floorboard.

e.

Install the carpet.

f.

the

respective electrical components.

Restore electrical power to the

airplane.

39-21-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

rQ,

o

O

J1

CB1 K3

(O)

GS18

)@)KI

COMPONENTS K1 K3 CB1 J1 GS1 A

-AFT ELECTRIC HEATER EMERGENCY SHUTDOWN RELAY -AFT EVAPORATOR BLOWER POWER RELAY -AFT ELECTRIC HEATER POWER CIRCUIT BREAKER -RECEPTACLE -GROUND STUD -JUMPER ASSEMBLY

FL39B 005814RA

Aft Electrical Heat Equipment Panel (FL-1 Thru FL-81)

Figure

Page

yaM612

1/08

39I2100

207

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

GS1 K1

:I

o

P1-P6

K3

~R P13 O

CR1

R2

P7

CR3

ol ’I1P~

ph(

1 J10

TB1 P12

K4

El

59

CRit

olll

I

1

1

I

111

K2

o

CB1

J1 HEFlTER

ELECTRIC

EMERGENCY

K1

-~FT

K2

-CFlBIN LIGHTING

REL~Y

K3

-FlFT

BLOWING POWER

K4

-C~BIN LIGHTING

CBI

-~FT

51

-ELECTRIC

GS1

-GROUND

STUD

-JUMPER

FISSEMBLY

EVFlPORATCR

SHUTDOWN

REL~Y

HEAT

POWER

P~NEL

-C~BIN LIGHTING

PLUG

P12-Pi3

-CFlBIN

LIGHTING

PLUG

CRI-CR4

-CFlBIN LIGHTING

DIODE

38

-CABIN LIGHTING

RELAY

-C~BIN LIGHTING

RECEPTFlCLE

TB1

-CRBIN LIGHTING

TERMINFlL BOFlRDS

El

-DIMMER

10

THRU

THRU

FL-492.

FL-492.

FL-494

FL-494

THRU

THRU

FL-499)

FL-499)

OREFlKER

RECEPTFlCLE

P1-P7

59-5

(FL-82

(FL-82

RELFlY

HEFlTER POWER CIRCUIT

ELECTRIC

RELF)Y

SOCKET

CONTROL FL21B 002980F18

ORIGINAL As Received

By

Aft Electrical Heat Equipment Panel (FL-82 and After; FM-1 and After)

Figure

208

ATP

A24

39-21-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

FORWARD ELECTRICAL HEA T EQUIPI~ENT PANEL The

panel (Ref. Figure 209)

is located under the

(A215) LOCA TION ZONE

cockpit floorboard, just

to the

right

132

of the centerline of the

airplane

between F.S. 125.0 and 134.0. REMOVAL a.

Disconnect all electrical power from the

b.

Remove the

copilot’s

c.

Remove the

right

d.

Remove the

copilot’s

e.

Remove the

right

airplane.

seat.

hand

cockpit carpet.

seat track.

hand

cockpit

floorboard

Tag identify all wires and disconnect equipment panel assembly.

all

just forward

wiring

of the

copilot’s

seat

position.

from the electrical components

on

the forward electric heat

jumper assembly.

g.

Disconnect the

h.

Remove the four bolts and washers which

panel assembly

from the

secure

the

panel assembly

to the

airplane

structure and

remove

the

airplane.

INSTALLATION Position the forward electric heat

a.

equipment panel assembly

in the

airplane and

secure

with four bolts and

washers b.

Connectthejumper assembly. Connect all

c.

wiring

to the

respective electrical component.

d.

Install the

cockpit floorboard,

e.

Install the

copilot’s

f.

Restore electrical power to the

seat

tracks, and carpet.

seat.

airplane.

CABIN FLUORESCENT LIGHTING POWER SUPPL Y PANEL (A519) LOCA TION Panel

(A519) (Ref. Figure 210) is located

Forairplane

in two different

serial numbers FL-1 to FL-8l,the

floorboard aft of the

rear

positions, depending

panel (A519) is located at the edge of the cabin

spar and forward of the forward

on

airplane

center of the

ZONE 163

serial number:

airplane

door. This location is

below the fourth

fuselage

station

299 at waterline 79.

For

airplane serial

panel

May

aft of the

numbers FL-82 and

rear

after, and FM-1 and after, the panel (A519) is located

spar. This location is

39-21-00

fuselage

station 241 at waterline 79.

at first center aisle floor

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

O JI

CBI

GSI

O

KI

COMPONENTS KI

CBI JI GSI

A

-FORWARD ELECTRIC HEATER EMERGENCY SHUTDOWN RELAY -FORWARD ELECTRIC HEATER POWER CIRCUIT BREAKER -RECEPTACLE -GROUND STUD -JUMPER ASSEMBLY

FL398

003815AA

Forward Electric Heat

Figure

A24

Equipment

Panel

209

39-21-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

0

PS6

IARN HIGH

A

ps\g~K1 ~I

O

Q ps

FI

PS4

HH cR

A

D

P2

PS2

~AG E

O

CR2

o

P4

o

K2

I RFT)

FwD

A

PS5

IARNI

Ps

C(I~C( P7

TB1

O A

PS3

El

A

IARNI psi

J10 pr

P11

P12

COMPONENTS

El PS1 THRU PS6 K1 AND K2 TB1 CR1 THRU CR~ P1 THRU P8 P11 THRU P13 J9 THRU 310 A

-DIMMER CONTROL -POWER SUPPLIES -RELAYS -TERMINAL BOARD -DIODES -PLUGS -PLUGS -CONNECTORS -FUSE HOLDER WITH

Cabin Fluorescent

3

AMP

Lighting Power Supply Figure 210

AGC

3

FL398

FUSE

003523RA

Panel

ORIGINAL As Received

Page 220 May 1/08

39I21 I00

By

ATP

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

REMOVAL WARNING: Make

sure

all electrical power to the

a.

Turn off all electrical power to the

b.

Removethe

c.

For

fuselage

numbers FL-1 to FL-81

d.

For

fuselage

numbers FL-82 and after,

e.

Tag identify

f.

Remove

g.

Tag identify

h.

NOTE: The

and disconnect all wire

screw

screw

j.

this

panel

electrical system.

remove

the fourth floorboard aft of the

remove

from

plugs

the first center aisle floor

rear

panel

spar.

aft of the

rear

spar.

panel components.

nuts and remove cover from the terminal board.

and two washers

and washers

securing

securing

the

the

jumper assembly

jumper assembly

to the

to the

panel and

panel

also

remove

help

the

secure

jumper assembly.

the

panel

to the

structure.

Remove the six power

removing

and disconnect all wires from the terminal board.

airplane i.

is turned off before

centeraislecarpet.

plastic

Remove

airplane

panel

remaining attaching screws and washers (three forward, one just aft of the El dimmer control.

one

each just aft of the PS1 and PS6

supplies, and

Remove the

panel

from the

panel

on

airplane.

INSTALLATION a.

Position the

just aft of b.

the

mounting brackets and secure with six screws and washers (three forward, supplies, and one just aft of the El dimmer control).

secure the jumper assembly with (Ref. Chapter 20-03-00).

Connect and

c.

Connect all wires to the terminal board.

d.

Install the terminal board

e.

f.

one

each

the PSI and PS6 power

Connect all wire

plugs

cover

to the

and

secure

the

longest attaching

with the

plastic

screw

and two washers. Bond

as

instructed

nuts.

panel components.

Install the floorboard.

g.

Installthecarpet panels.

h.

Restore electrical power to the

airplane.

39-21 -00

Page

yaM12

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

INTERTURBINE TEMPERA TURE GA GE BALANCE RESISTORS

(R 100 AND

R10 I)

LOCATION- ZONES 141 AND 142 The interturbine

window,

one

temperature gage balance resistors

each left and

right of

are

located below the floorboard forward of the first cabin

airplane. In addition, one terminal board aft of Fuselage Station 158 (Ref. Figure 211).

the center of the

resistor. The resistors and terminal boards

are

is

adjacent

to each

REMOVAL Remove the carpet behind the

a.

flight compartment

seats.

Remove the center aisle floorboard forward of the front spar.

b.

Mark to

c.

identify

the wires and disconnect them from the resistor.

Remove the two

d.

and washers that

secure

the resistor and

remove

the resistor.

the wires and disconnect them from the terminal board.

e.

Mark to

f.

Remove the two

identify

screws

screws

that

secure

the terminal board and

remove

the terminal board.

INSTALLATION the

support and install the

a.

Position the resistor

b.

Connect the wires to the resistor.

on

Position the terminal board

c.

on

two

attaching

the support and install the two

d.

Connect the wires to the terminal board.

e.

Install the center aisle floorboard.

f.

Install the carpet.

May

1/0839-21-00

screws

attaching

and washers.

screws.

A24

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

13C~ ´•~1

Ilol~ ~ol DETAIL

rara~

R1(II

,,1, 78163

DETAIL

A

(ROTATED 90~ CCW)

COMPONENTS R100

-RESISTOR

R101

-RESISTOR

TB163

TERMINAL BOARD

TB164

-TERMINAL BOARD

B

(ROTATED 90D CW)

Interturbine Temperature Gage Balance Resistors Figure 211

n24

39-21-00

350-352-39

Hawker Beechcraft

Corporation

SUPER KING AIR MODEL B300/300C MAINTENANCE MANUAL

FLAP MOTOR RELA Y The

wing flap

motor

floorboard aft of the

(K105) ZONE

151

relay (Ref. Figure 212) is located above the wing flap spar and just to the right of the airplane centerline.

motor at FS

225, below the second

rear

REMOVAL a.

Remove the center aisle carpet

runner.

b.

Remove the second center aisle floorboard aft of the

c.

Mark to

d. e.

identify

Disconnect the

rear

the wires and disconnect them from the

spar.

relay.

jumper assembly.

Remove the two

screws

and washers

securing

the

to its

mounting

secure

with two

relay

bracket. Remove the

relay

from the

airplane. INSTALLATION a.

Place the

flap

motor

relay

on

its

b.

Connect the

c.

Connect the wires to the

d.

Install the center aisle floorboard.

e.

Install the carpet

mounting

bracket and

screws

and washers.

jumper assembly.

relay.

runner.

Ki05 FLAP MOTCR RELAY CR107 IRANSZOR3 TRANSZORB CRlOa GSI 9 GROUND STUD JUMPER ASSEMBLY A 8102 FLAP MOTOR

05 CR107 CR108 K

-i

’I

--GS 1 19

ORIGINAL

’1

As Received

I!_.I

ATP 810;!

225FS FWC

35a353ooeAI

Flap Motor Relay Figure 212

Page

yalN42

1/08

39-21-00

A24

By

CHAPTER

STANDARD PRACTICESSTRUCTURES

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 51

STRUCTURES

TABLE OF CONTENTS

PAGE

SUBJECT 51-00-00

Structures-

Description

and

..................1

Operation

.........1

Recommended Materials

....2

Primary Structural Components Secondary Structural Components.

.2

.201

Structures- Maintenance Practices. Structural

Wing

Repair. UpperSkin Inspection Repairin Primary Structure. Dent Repair in Secondary Structure

Metal Skin Metal Skin

Skin Dent Limitations Skin Dent Limitations

...............202 .........203 ......203

Both Sides Accessible.

Repair when Both Sides

are

Accessible.

...........204 ........204

One Side Accessible

Repair when One Side is Accessible Skin Dent Filler Repair Sealing

,,4

.201

CenterSection Bonded Panel

.............204 ......204

51-CONTENTS

1/08Page May

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

51-LOEP

1

May

1/08

51-CONTENTS

1

May

1/08

1 and 2

May 1/08 May 1/08

51-00-00

201 thru 205

A24

Pages

51-LOEP

May 1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STRUCTURES Being

of

DESCRIPTION AND OPERATION

semimonocoque construction,

the

fuselage

of this

airplane

is

pressurized

to the skin between bulkheads

at FS 84.00 and FS 381.75. All

skin, bulkheads and structure joints, plumbing and wiring connections passing through pressure bulkheads, access doors, windows, control cables and torque shafts are sealed to minimize air leakage. Although the wing center section is an integral part of the fuselage, the wing panels outboard of the nacelles

are

removable. To

left side of the

provide

fuselage swings

a

down.

convenient

stairway

Emergency exits

are

for

boarding

installed

on

the

airplane,

the cabin entrance door

both sides of the

fuselage just

on

aft of the

the

crew

compartment partition.

RECOMMENDED I~ATERIALS as meeting federal, military or supplier specifications are provided for only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance to the applicable specifications. GENERIC OR

The recommended materials listed in Chart 1

reference

MANUFACTURED PRODUCTS WHICH CONFORM TO THE REQUIREMENTS OF THE SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART. Only the basic number of LOCALLY

specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used. each

Chart 1

Recommended Materials MATERIAL 1.Solvent 2. Primer

SPECIFICATION A-A-59282

SUPPLIER

PRODUCT

Methyl Propyl EC3911

Ketone

Obtain

Locally

Minnesota

Mining

Mfg.

Co.

St. Paul, MN 55144-1000 3.

Aerodynamic Smoother

EA960F

Hysol. Aerospace

Products

2850 Willow pass Rd. Pittsburg, CA 94565 4.

Sandpaper

~as

No. 400

Obtain

Locally

51-00-00

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PRIMARY STRUCTURAL COMPONENTS The

structural components are essential to the proper function of the airplane. Failure components would seriously endanger the safety of the airplane and/or the passengers:

following primary

to any of the a.

Control systems.

b.

Engine

c.

Attach

d.

Coverings

e.

Wing,tail

f.

Landing

g.

Auxiliary

h.

Seat and seat support structure.

occurring

mounts.

fittings. of the

fuselage, wings,

surfaceand

tail surfaces and control surfaces.

controlsurfacespars.

gears and support structure. members used to

strengthen

or

support other members carrying direct loads.

SECONDARY STRUCTURAL COMPONENTS

not

following secondary structural components would require necessarily endanger the safety of the airplane and/or the passengers.

a.

Wingtips.

b.

Aerodynamic fairings.

c.

Nose

d.

Furnishings

e.

Non-structural doors and

In the event of failure, the

May

immediate attention, but would

cone.

and

upholstery (excluding seating). covers.

1/0851-00-00

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STRUCTURES- MAINTENANCE PRACTICES STRUCTURAL REPAIR WARNING:

Drilling,

modification

considered the

or

any type of work which creates a break in the pressure vessel is of the owner or facility performing the work. Obtaining approval

responsibility

of the work is, therefore, their

responsibility.

repair to chem-milled skins may be accomplished, provided proper edge distances (twice the rivet diameter plus 0.06-inch) are maintained between repair rivets and all points of change in skin thickness at points of transition between the original skin thickness and the etched portions of the skin. Minor

general, structural repair methods used on this airplane may be in accordance with AC 43.13-1A, AIRCRAFT INSPECTION AND REPAIR MANUAL and AC 43.13-2, AIRCRAFT ALTERATIONS MANUAL. In addition, the In

following should

be considered:

pressurized area, all skins, formers and stringers are structural members, and it is essential strength of the pressure vessel be maintained. A cabin pressurization test must be after performed any structural repair to the pressure vessel.

CAUTION: In the

that

the structure

a.

Never make

b.

All

lap joints, including patches,

c.

All

repair

d.

Never

e.

Do not countersink

f.

Scratches in the outer windows of

a

skin

replacement

or

patch from

a

material thinner than the

must have at least two

material must be free of any defects such

dimple

a

structural member

deeper than

by driving

as

staggered

rows

original

skin.

of rivets.

nicks, gouges and/or scratches.

the rivet head into the part.

75% of the material thickness.

acrylic plastic

may be removed with 400 to

600-grit sandpaper, providing

that

than 0.003-inch of material is removed. Polish the repaired area smooth with buffing compound. The minimum thickness of the crew compartment side windows is 9/32 inch and for the cabin and baggage not

more

compartment windows, 7/32 inch. No crazing

NOTE: The window over

repair

above is for localized

or

cracks

are

permitted

repair of individual

on

the windows in the pressure vessel.

scratches

only

and should not be

performed

the entire window.

WING CENTER SECTION BONDED PANEL UPPER SKIN INSPECTION Inspect

the

NOTE:

right

For this

hand and left hand

inspection,

coin. Make

sure

wing

center section bonded

panel

upper skin

(Ref. Figure 201)

closed end of a pocket knife, rounded edge of a smooth instrument or testing instrument is smooth and free from any sharp or rough edges.

Use the test instrument to tap the wing center section bonded panel upper skin located left hand upper wing center section between the fuselage and the nacelle.

b.

Tap

wing

demonstrate c.

Tap

the

wing

panel aft of the row rivets hollow sound showing a separated bond.

center section bonded a

a

solid

shown in Test Zone lof

panel 3/4 inch forward of the row of rivets ringing sound showing a bonded panel.

center section bonded

201. It should demonstrate

n24

follows:

use a

that the

a.

the

as

on

the

Figure

right

a

heavy

hand and

201. It will

shown in Test Zone 2 of

51-00-00

Figure

Page

yaM102

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Starting at the edge of the nacelle 2 inches fuselage to wing center section fairing.

aft of the forward spar web, tap every two inches inboard to the side

of

I

tapping process until the entire surface

of the

e.

Move 2 inches aft and repeat the panel upper skin is covered.

f.

Visually inspect the wing center section bonded panel upper a separation of the wing center section panel upper skin.

g.

If separation of the wing center section bonded panel upper skin is detected, Corporation Customer Support.

skin surface for

a

wing

center section bonded

slight raise

or

bubbles

indicating

contact Hawker Beechcraft

FORWARD

L FRONT

INBOARD

SPAR WEB

NACELLE FAIRING

%I

CENTERLINE

O

OF NACELLE

FUSELAGE

i FUSELAGE FAIRING

DRIVEN RIVET LINE FOR

TEST

ZONE 2

TESTING REAR SPAR

Wing

Center Section Bonded Panel

Figure

TEST

ZONE

Upper Skin Inspection

Area

201

METAL SKIN REPAIR IN PRIMARY STRUCTURE Isolated dents to

a

depth of

except for the 10% of the

aerodynamic

Page

are permissible on wing upper skins providing all requirements are met, rule of SKIN DENT LIMITATIONS-BOTH SIDES ACCESSIBLE. Fill the dents with

0.250 inch

area

smoother per REPAIR WHEN ONE SIDE IS

20251-00-00

ACCESSIBLE, this Chapter.

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

METAL SKIN DENT REPAIR IN SECONDARY STRUCTURE The

following

dent

repairs

can

be made

only

to

structural skins

seconda~y

specified

under

SECONDARY STRUCTURAL COMPONENTS, 51-00-00. SKIN DENT LIMITATIONS These limitations and

BOTH SIDES ACCESSIBLE

following repairs apply only

SKIN DENT LIMITATIONS

to aluminum skins. For

see

depth (Ref. Figure 202, Detail A).

a.

Dents do not exceed 0.100 inch in

b.

Dents do not exceed 10% of total surface

c.

Dents

are no

d.

Sharp

dents

area

in

closer than 0.50 inch to any rivet

or

or

magnesium skins,

ONE SIDE ACCESSIBLE, this Section.

penetration

of skin not

one

square foot.

structural

area

(Ref. Figure 202).

permitted.

STRUCTURAL

O

AREA

i,,, O .50

O

InCH

DENT 100

CA. 50

RIVET~

II\ICH

INC’I

_L

DETAIL

A

350-13-0%0

Skin Dent Limitations

Figure

A24

202

51-00-00

Page

yaM302

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

REPAIR WHEN BOTH SIDES ARE ACCESSIBLE be made to

The

following repairs

a.

Remove finish from

b.

Use

c.

Inspect

d.

Dye penetrant inspectforcracks.

e.

When

discrepant

for cracks and

a

secondary

area

per

structural aluminum skins.

Chapter

backup support and form-out dents

solid

a

can

uneven

These limitations

apply

accessible from either

apply

filler per SKIN DENT FILLER REPAIR, this Section.

to aluminum skins that are accessible from

one or

only

one

side and

skins that

are

skins when

one

magnesium

both sides.

Dents do not exceed 0.100 inch in

b.

Dents do not exceed 10% of total surface

c.

Sharp

or

a

ONE SIDE ACCESSIBLE

a.

dent

to skin contour.

surfaces.

smoother surface is desired,

SKIN DENT LIMITATIONS

20-08-00.

penetration of skin

depth (Ref. Figure 202,

is not

area

in

one

Detail

A).

square foot.

permitted.

REPAIR WHEN ONE SIDE IS ACCESSIBLE This

is

procedure

applicable to aluminum

or

a.

Prepare

b.

After dent has been filled,

are

skins when

only

one

side is accessible and to

magnesium

accessible.

both sides

and fill dent per SKIN DENT FILLER REPAIR, this Section.

inspect

for smoothness.

SKIN DENT FILLER REPAIR

I

a.

Sand

b.

Clean

area

c.

Apply

EC3911

area

lightly with

with No. 400

Methyl Propyl

primer(ltem

No. 4, Chart

sandpaper (Item Ketone

1).

(MPK) (Item No. 1,Chart l)and dry completely.

No. 2, Chart

1)

and

dry

a

minimum of 5 minutes.

Wipe the

area

clean with

a

dry

cheesecloth. d.

Fill dented

area

with EA960F

aerodynamic

smoother

(Item

No. 3, Chart

1) mixed

and

applied per

the

manufacturer’s instructions. e.

After four hours at

f.

Apply

Page

finish

as

room

required

temperature, sand for the

area

smooth.

area.

20451-00-00

Pi24

Hawker Beechcraft

Corporatian

MAINTENANCE MANUAL SUPER KING AIR 8300/B300C

SEi5LINC

etc. is of the windows, doors,

prime

seams. tke slcio and bulkhead structural ~epa,r or is pressuilzed, sealing seals. When making a rubber Becausc3 ~his airplane r~movab\e have shafts with the proper cables and torque must be sealed importance Control vessel, the mating suci~ces the p~essure in break withthe proper sealers modgication which creates a attached to it must be seated I;urfaces, ~he pressure vessel or mating all clean penetrating sealer. All other components seaters, be sure to thoroughly bonding eftective For described in Chapter 20-10-00. seals, matil?g parts and rubber

5t-00-00 A24

Page 205 May flOB

C H A PT E R

DOORS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 52 - DOORS TABLE OF CONTENTS SUBJECT

PAGE 52-00-00

Doors - General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 52-10-00 Passenger/Crew Doors - Description and Operation (FL-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Passenger/Crew Entrance Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Passenger/Crew Doors - Maintenance Practices (FL-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Cabin Entrance Door Damper. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Entrance Door Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Entrance Door Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Fitting and Mounting a New Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Cabin Entrance Door Adjustment (New Door) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Latch Mechanism Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Upper Latch Hook and Pin Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Folding Step Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .209 Handrail Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Cabin Door Seal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Cabin Door Seal Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Pneumatic Valve Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Main Cabin Door Hinge Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 52-11-00 Cargo and Airstair Door - Description and Operation (FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Cargo and Airstair Door - Maintenance Practices (FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Cargo Door Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Cargo Door Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Adjustment of Cargo Door Latching Mechanism. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Gas Spring Assembly Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Cargo Door Seal Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Fitting a New Airstair Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Airstair Door Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Airstair Door Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .215 Adjustment of Airstair Door Latching Mechanism . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .216 Folding Step Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .217 Airstair Door Damper Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .218 Airstair Door Seal Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .221 Cargo Door Lower Attachment Lug Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .221

A28

52-CONTENTS

Page 1 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 52 - DOORS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 52-20-00

Emergency Exit Doors - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Emergency Exit Doors - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Emergency Exit Door Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Emergency Exit Door Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Latching Mechanism Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Emergency Exit Door Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 52-70-00 Passenger/Crew Door Warning - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Passenger/Crew Door Warning - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cabin-Door-Unlocked Switch Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cabin-Door-Unlocked Switch Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cabin-Door-Locked Switch Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Hook-Sense Switch Adjustment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 52-71-00 Cargo and Airstair Door Warning - Description and Operation (FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Cargo and Airstair Door Warning - Maintenance Practices (FM-1 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Adjustment of Cargo and Airstair Door Warning Switches. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Airstair Doorsill Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cargo Door Upper Handle Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cargo Door Lower Handle Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 202 Cargo Door Forward and Aft Latch Switches. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Cargo Door Lower Latch Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 Airstair Door Forward and Aft Latch Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Cargo Doorsill Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Cabin/Cargo Door Annunciator Circuitry Check. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205

Page 2 May 1/10

52-CONTENTS

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

52-LOEP

1

May 1/10

52-CONTENTS

1 and 2

May 1/10

52-00-00

1 thru 4

Nov 1/07

52-10-00

1 201 thru 213

Nov 1/07 May 1/10

52-11-00

1 and 2 201 thru 223

May 1/08 May 1/08

52-20-00

1 201 thru 206

Feb 1/10 Feb 1/10

52-70-00

1 201

May 1/08 May 1/08

52-71-00

1 and 2 201 thru 206

May 1/08 May 1/08

A28

52-LOEP

Page 1 May 1/10

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DOORS-GENERAL SPECIAL TOOLS AND RECOMII/IENDED IWA TERIALS The

special tools and recommended materials listed in Charts 1 and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. I Any product conforming to the specification listed may be used. The products included in this chart have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance with the I applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the Charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to the usage of the product listed. This can be done by contacting the supplier of the product to be used.

52-00-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

Special Tools (FWI-1)

1.

Hawker Beechcraft

101-590052-1

Adjustment

USE

SUPPLIER

PART NO.

TOOL NAME

Corporation

Adjusting

Corporation

To aid in

cargo door latch

post.

9709 East Central

Wrench

Wichita, KS 67201 2.

Hawker Beechcraft

101-590053-1

ClosingAid

9709 East Central

and Stabilizer

stabilizing cargo door an extended period

opened for

when

of time.

Wichita, KS 67201

O

00

86~

00

gQ~

3 101-590052-1

Cargo Door Latch Adjustment Wrench

D

101-590053-1 Cargo Door Closing Aid and Stabilizer 350-17-30

Special Tools (FM-1) Figure 1

Page

voN2

1107

52-00-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 Recommended Materials

MATERIAL

1.

SPECIFICATION

MIL-PRF-5606 Hydraulic Fluid (Brakes and Shock Struts) I

SUPPLIER

PRODUCT

Mobil Aero HF

Exxon Mobil

Corporation

3225 Gallows Road

I Fairfax,

I

VA 22037

Shell Oil

Aeroshell Fluid 41

Company

P.O. Box 2463 One Shell Plaza

Houston, TX 77001

Brayco 756

Air BP Lubricants

Parsippany, 2.

LubricantSolidFilm, Heat Cured, Corrosion

3.

MIL-PRF-46010

Everlube Products

Lube-Lok 5306

100

Cooper Circle City, GA

Peachtree

Inhibiting

Sealer

NJ 07054

SAE-AMS-S-8802

*PR1440B-1/2

or

PR1440B-2

30269

PRC-Desoto International Inc. P.O. Box 1800 5454 San Fernando Road

Glendale, CA 91209 4.

Lubricating Oil, General Purpose Low Temperature

MIL-PRF-7870

Air BP Lubricants

Brayco 363

Division of BP Products North America

Parsippany,

NJ 07054-4406

Anderol Inc.

Royco 363

215

Merry

Lane

P.O. Box 518 East Hanover, NJ 07936 5.

Adhesive, Gap

Huntsman Advanced Materials

104-A/B

Epibond

Filling Epoxy 6.

Sealer

SAE-AMS-S-8802

PRC-Desoto International Inc.

*PR1440

P.O. Box 1800

5454 San Fernando Road

Glendale, CA 91209 7.

Thread

Locking Compound

Loctite 290 Threadlocker

Wicking

Grade

Henkel

Corporation Crossing

1001 Trout Brook

Rocky Hill, CT

A23

52-00-00

06067

Nov

1 07Page

3

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

Chart 2

Recommended Materials

MATERIAL

SPECIFICATION

8.

Solvent

A-A-59282

9.

Solvent

TT-N-95

(Continued) SUPPLIER

PRODUCT

Methyl Propyl

Ketone

Obtained

Type

II

Locally.

Naphtha, Aliphatic

10. Adhesive

Scotch-Weld 2216

3M

Company

3M Center

St. Paul, MN 55144-1000 11. Translucent

Momentive Performance

RTV108

Adhesive

Materials/Holdings Hudson River Road

Waterford, NY 12188 12. Cement

D. Aircraft Products

Dapco 3300

Company

1191 Hawk Circle

Anaheim, CA 92708 13. Adhesive

Scotch-Grip

1300L

3M

Company

3M Center

St. Paul, MN 55144-1000 14. Thread

Locking Compound

Loctite 271 for stud diameter under 2 inches.

Henkel

Corporation Crossing

1001 Trout Brook

Loctite 277 for stud diameter

Rocky Hill, CT 06067

over2 inches.

15.

Superseded

Item. Use Item No. 3

16. Lubricant, Air

Drying, Solid

or

MIL-L-23398

6

as

replacement. Perma-Slik G

Electrofilm

Manufacturing

Co.

P.O. Box 55669

Film

25395

Rye Canyon Road

Valencia, CA 91355 *Use PR1440B-1/2 when

assembly

time is within 30 minutes after sealer is mixed, PR1440B-2 when

assembly by

time will take from 30 minutes up to 2 hours. The letter "B" in the name stands for Class B, for application extrusion gun or spatula. The product is also available in Class A, i.e. PR1440A, for application by brush.

Page

voN4

1107

52-00-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PASSENGERICREW DOORS

(FL-1

AND

DESCRIPTION AND OPERATION

AFTER)

PASSENGER/CREW ENTRANCE DOOR swing-down entrance door, located in the left aft section of the fuselage, provides a convenient stairway for entry plastic covered cable provides support for the door in the open position. This cable can also be used as a handhold for entering and exiting the aircraft, and it can be used as a means for pulling the door shut from the inside of the airplane. A pneumatically inflated rubber seal around the cabin door seals the pressure vessel during flight. A hydraulic damper permits the door to lower gradually during opening.

A

and exit. A

The entrance door

locking

mechanism has two handles

tone

outside and

one

inside)

which

are

interconnected.

When either handle is rotated, two latches hook into the doorframe at the top and two latch pins on each side of the door lock into the frame on the sides. There are four sight openings on the inner facing of the door, one opening

stripe, painted on each latch pin, aligns with a pointer in the sight opening when the door is internally lighted sight openings are provided above the door for viewing the two latch hooks to ensure upper proper engagement, and next to the inner door handle for viewing the door safety switch actuation. The lights at these locations are illuminated by actuating momentary push-button switches near each sight opening.

over

each latch

pin.

A

closed and latched. In addition,

A button

adjacent

to the door handle, both inside and

outside, must be pressed and held before the handle

rotated to open the door. When the cabin is pressurized, cabin internal pressure inflates to help prevent accidental opening of the door. An annunciator

of the

A23

airplane

light

on

cockpit illuminates if the door is not closed ground, the door can be locked with a key.

in the

the

and all latches

are

a

can

be

bellows behind the button

not

fully

locked. For

52-10-00

security

1

I I

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

PASSENGER/CREW DOORS - MAINTENANCE PRACTICES (FL-1 AND AFTER) CABIN ENTRANCE DOOR DAMPER a. When installing the damper assembly, attach the rod end to the cabin door and the barrel end to the supports on the cabin doorframe. Shim as necessary with AN960-416 washers to eliminate side play between the damper rod end, damper barrel end and the damper attach supports (Ref. Figure 201). b. Service the cabin door damper by removing the damper assembly from the airplane, then place the damper barrel down and loosen the three screws securing the cap end to the barrel. Push down on the piston rod end until the piston head is at the bottom of the barrel. Slide the cap end up the piston rod and fill the cylinder barrel with maximum of 215cc (7.2 ounces) of hydraulic fluid (1, Chart 2, 52-00-00). Replace the O-Rings on the cap end. Secure the cap end on the barrel by tightening the three set screws.

Cabin Entrance Door Damper (FL-1 and After) Figure 201

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52-10-00

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENTRANCE DOOR REMOVAL a. Pull the cabin door circuit breaker, located in the crew compartment. b. Remove the cotter pin, washers and pin attaching the folding step cable under the doorsill step (Ref. Figure 202). c.

Disconnect the wiring from the two cabin door switches.

d. Disconnect the inflation tube from the door seal. e. Disconnect the damper assembly. f.

Disconnect the handrail cable.

g. Remove the hinge retainer. h. Support the door and remove hinge pin. i.

Remove the door.

NOTE: Lubricate the entrance door locking mechanism, handle assembly and rollers with solid film lubricant (2, Chart 2, 52-00-00).

ENTRANCE DOOR INSTALLATION a. Position the door and match up the hinge halves (Ref. Figure 202). b. Install the hinge pin. c.

Connect the cable to the doorframe.

d. Connect the damper assembly. e. Connect the cabin door seal to the inflation tube. f.

Connect the door wiring.

g. Connect the folding step cable. h. Install the hinge seal retaining strip. i.

Engage the cabin door circuit breaker.

NOTE: If the nut on the bolt securing the base of the door cable was removed, then ensure that the head of the bolt is placed outboard to prevent the handrail from catching under the bolt.

Page 202 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Airstair Door (FL-1 and After) Figure 202

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52-10-00

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FITTING AND MOUNTING A NEW DOOR a. Prepare the door as follows before fitting it to the fuselage: NOTE: A new entrance door is supplied with a new door hinge half, seal retainer, and seal separate from the door. Do not rivet the hinge half or seal retainer to the new door until after the new door has been fitted. 1. Trim the lower corners of the door skin. To prevent the door from riding on the fuselage upon installation, taper the door skin IN to the first hinge segment. 2. Loosen the latch rods (tubes) for the upper latch pins in the sides of the door to allow for adjustment of the pins when the door is being fitted to the fuselage. 3. Adjust the hooks on top of the door by turning the eccentric bolt on the forward side of the door until the flat is UP and turning the eccentric bolt on the aft side until the flat is DOWN. 4. Work the inner tubes (located inside the door seal at the lower part of the door) around the inside seal until the greater length of the inner tube on the forward side of the door is at the bottom side of the door and the greater length of the aft inner tube is at the aft side of the door. Since there is less mass to compress when the door is closed and locked with the inner seal stiffeners located thus, maximum sealing is assured. 5. If the new door is not already equipped with an outside door handle, turn the inside door handle to the fully locked position, and lock the outside door handle with the key before installing it. Seal the base of the outside door lock with sealer (3, Chart 2, 52-00-00) before installing the attaching screws. 6. Dust the door seal liberally with soapstone before fitting it to the fuselage. 7. Remove all covering from the fuselage hinge half where it is riveted to the fuselage. This material may be folded back inside the fuselage over the doorframe. 8. Check that the lower portion of the openings in the fuselage, where the top door hooks engage, are tapered for easy entrance of the hooks. 9. Remove the upper and lower latch pins on each side of the door prior to fitting the door to the fuselage. Only the hooks on top of the door are to be engaged during the initial fitting of a new door. 10. After lubricating the door hinge with lubricating oil (4, Chart 2, 52-00-00), work the pin through the fuselage hinge half. 11. Install one 1/4 inch spacer against the forward side of the fuselage doorframe just below the cutout for the lower latch pin and another 1/4 inch spacer just above the upper latch pin cutout. 12. Install an 0.080 inch spacer on top of the fuselage hinge half at a point approximately five inches inboard from each side of the lower doorframe. These spacers will shim up the door enough to clear the upholstery material. Trim off all excess door seal so that the door rests on the shims, not on the seal. b. Secure the hinge half to the new door with a minimum of five sheet metal screws, then position the door in the fuselage doorframe and install the hinge wire. c.

Close the door and check that the top hooks are centered and fully engaged. Lock the door and remove the sheet metal screws from the lower door hinge half.

d. Working from inside the fuselage, shift the door so that it is squared in the doorframe and fits tightly against the 1/ inch spacers on the forward doorframe and the 0.080 inch spacers on the hinge half riveted to the fuselage. 4

Page 204 May 1/10

52-10-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL e. With the door centered and the hinge half on the door mated with the hinge half on the fuselage, install the five sheet metal screws, using the five existing pilot holes or drilling new #40 holes if necessary. f.

Open the door and trim its upper skin to clear the fuselage skin by 3/32 inch along and below the drop channel above the door. Close the door and recheck the door for fit and proper engagement of the upper hooks.

g. Once the door has been fitted and trimmed so that the clearance between the door and forward frame is 1/4 inch and between the door bottom and fuselage is 0.080 inch, remove the door and drill 23 evenly spaced pilot holes through the door skin and hinge half. h. After cleaning all drill cuttings from between the hinge and door skin, coat both sides of the door hinge with sealer (3, Chart 2, 52-00-00). With the hinge wire installed to prevent warping and maintain alignment, rivet the hinge to the door. i.

Install the door on the fuselage, but do not cut the hinge wire at this time.

j.

Trim the door as required to prevent the skin from butting against the fuselage (trim the aft door skin first). Check the hooks on top of the door for proper adjustment as indicated under LATCH MECHANISM ADJUSTMENT.

k.

Install and adjust the upper and lower latch pins on each side of the door in accordance with the procedure under LATCH MECHANISM ADJUSTMENT.

l.

After the door is completely rigged, lock the jam nuts on the upper hook adjustment rods.

m. Cut the hinge wire; then install the hinge seal and retainer. n. Rig the steps as outlined under FOLDING STEP ADJUSTMENT. o. After the door has been installed and painted to match the fuselage, lubricate the door seal with a silicone lubricant.

CABIN ENTRANCE DOOR ADJUSTMENT (NEW DOOR) Check the doorframe for irregular surfaces, particularly at the front and aft top corners and between the striker plate and side frame. Grind down the high spots. Fill in the low spots with Epibond 104-A/B gap filling epoxy adhesive (5, Chart 2, 52-00-00), modified with aluminum powder or paste to give an aluminum color finish. To prepare the resin thoroughly mix 10 parts of Epibond 104B to 100 parts of Epibond 104A by weight, and add 10% flexibilizer by weight to the resin. Application time is 30 to 45 minutes, cure time is 4 to 6 hours depending on temperature and humidity. After cure, sand smooth. NOTE: A frequent source of leaks is improperly adjusted latch pins that allow the door to move when the cabin is pressurized. The following adjustment will aid in preventing leakage during pressurized flight. a. Remove the seal and panels from the door. Lift the sill rubber on the door half only. b. Back the top latch hooks off until they no longer latch. c.

Remove the aft left cabin chair and loosen the side upholstery panels to gain access to the inside of the doorframe. Loosen the frame of the window aft of the door, and peel back the upholstery side panel for access to the back side of the doorframe. Spray or paint the underside of the upper latch pin on each side of the door with D-check developer or Blue Dykem. This is the portion of the pin that makes contact with the roller in the door-opening frame. Close and lock the door, then open the door and turn the handle to the locked position. Check that the roller contacts the flat of the latch pin. If the roller contacts the latch pin taper or taper radius, reposition the latch pin until the roller contacts the flat of the latch pin.

A28

52-10-00

Page 205 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL NOTE: If the shoulder of the latch pin strikes the adapter because there are not enough threads to adjust the pin for proper engagement, the following procedure will be necessary: 1) Mark the position of the roller on the doorframe with masking tape. 2) Remove the roller plate and make a shim from 0.050 aluminum to fit behind it. 3) After drilling the shim to match the roller plate, install the shim and roller assembly with the two inboard screws. Do not install the two outboard screws at this time. 4) Close and lock the door and check that the roller is on the flat of the latch pin. 5) Shim the roller plate as necessary to obtain proper engagement. 6) Install the outboard screws. d. With the door closed and latched, turn the door handle and carefully observe the movement of each latch pin and roller with a flashlight. Minute movements of the latch pin should move both the roller in the doorframe and the roller inside the door. The door should also move slightly outboard as the pins are retracted into the door when the roller hits the tapered portion of the latch pin. If the roller fails to move as described, reposition it inboard by removing the two outboard screws and loosening the inboard screws that fit in the slotted holes. Move the roller inboard and check that it is not cocked. After checking that the surfaces of the roller and latch pin are in the same plane when in the locked position, tighten the retaining screws in the slotted holes. Since the roller plate has been shifted, the outboard mounting holes will no longer be in alignment. To maintain the metal-to-metal contact required for the latch roller and pins when the door is under a pressurized load, enlarge the two outboard screw holes to a diameter of 1/4 inch. Countersink the holes to fit a flat head AN screw 1/4 inch in diameter. Secure the roller plate in place with these screws, washers and elastic hex head nuts. e. Adjust the two top latch hooks until they can be moved sideways by finger pressure when in the latched position. Observe hook movement through the inspection holes in the cabin headliner. Insert an 0.065 inch diameter wire through the door structure and the matching holes in each hook to ascertain that the hook is past center on its cam. With the hooks adjusted in this manner, check the latch-hook actuating rods for a slight free end play. Apply Loctite to the threads before final adjustment of the top latch hooks. f.

Lay back the loosened sill rubber and remove the cement from the front and rear corners of the fuselage doorframe. Fill the corners with sealer (6, Chart 2, 52-00-00), then make a radius in the sealer that extends 3/ 4 inch in either direction from the corner. Let the sealer cure while installing the door seal on the door; this permits the formation of a channel in the sealer when the door is closed.

g. Install the door seal on the door. Cement the front and back of the door seal in the door extrusion for an area approximately three inches outboard from the hinge end, using silicone cement. Install the wood grain fairing and sill rubber on the door. h. Allow the sealer applied in step f to set up until it is no longer sticky to the touch, but is still pliable. Powder the sealer generously with soapstone or talc powder. Wax the contact areas of the door seal. Leave the door closed overnight if possible; if not, open the door but let the sealer cure (this takes three to four hours at 70°F). i.

Check the door for chafing or wear where it contacts the fuselage doorframe. If localized wear is evident, check the fuselage doorframe for a latch plate positioned too far outboard. If this is the case, grind the latch plate until it fairs with the contour of the doorframe.

LATCH MECHANISM ADJUSTMENT a. With the door open, place the handle in the “LOCKED” position. The latching hooks must clear the door structure. Adjust the turnbuckle to obtain the proper overcenter alignment of each hook latching mechanism (Ref. Figure 203). b. Remove the two plug buttons from the hook inspection holes on the inside upper doorway frame.

Page 206 May 1/10

52-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Latch Mechanism Adjustment (FL-1 and After) Figure 203

A28

52-10-00

Page 207 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

As the door is pulled closed from the inside, the hooks should enter the holes in the upper doorframe regardless of the handle position. Check the hook clearance in all of the handle positions. Adjust the hooks as necessary with the eccentric bolt. The hooks should fully engage the latch pins. Adjust the eccentric bolt and/or the hook length to obtain proper engagement.

NOTE: The full range of adjustment of the eccentric bolt is accomplished in 360° of rotation. Do not turn the bolt more than 360° in either direction. Hook adjustment must be checked in all handle positions each time the eccentric bolt is rotated. d. Turn the handle to the “OPEN” position. If the hooks do not release and allow the door to open, adjust the eccentric bolt. Repeat step c. NOTE: Insert a 0.076 inch diameter check pin into the rigging pin hole shown in Figure 203 to determine if the hook is engaged and correctly rigged. If rigging pin hole is not present, remove latch mechanism cover and visually confirm the latch mechanism goes into an over-center position when the door is closed. After adjusting the latch-hooks, apply thread locking compound (7, Chart 2, 52-00-00) to the hook threads and tighten down the lock nuts on the adjusting rods. e. Close and lock the door. Check for proper hook engagement, hook release and door seal contact. Adjust the hook length as required and check for overcenter alignment per step a. NOTE: Check the hook engagement to determine that the hooks may be moved slightly with the fingers. If no movement is perceptible, unscrew the hook(s) one full turn and recheck. f.

Check the upper and lower latch pins on each side to ensure they have at least one inch of travel. Travel limits on the four latch pins should be reached simultaneously. When rotating the handle to the open position, the latch pin must begin retracting simultaneously. If the travel of any latch pin is limited or if the upper and lower latch pins are not synchronized, the upholstery and access panels on the steps should be removed for a check of the upper and lower latch chains, which transfer movement from the door handle to the latch rods. Adjust the chains that are attached to the latch rods, by removing the locking clips on the turnbuckles and adjusting the turnbuckles as necessary.

NOTE: Check the latch pins for proper thread engagement by inserting a piece of safety wire into the check hole after latch adjustment. The safety wire should not pass through, indicating that the grip length is satisfactory. g. The upper latch pins must extend far enough to ride on the latch rollers and at least 0.12 inch past the tangent point of the latch pin when the door is locked. The flat of the lower latch pin must extend 0. 38 +0.06/-0.25 inch past the centerline of the rollers, when the door is locked (Ref. Figure 204). NOTE: Each latch pointer, which is visible through the inspection opening in the door, should point at the line on the latch rod when the door is in the locked position. The chamfered end of the 50-430018-11 latch pin must always be placed on opposite side of roller assembly. h. Coat the four latch rollers with lubricant, air drying solid film (16, Chart 2, 52-00-00) and install the upholstery. i.

With the door closed, the torque required to rotate the handle to the locked position must not exceed 150 inchpounds.

Page 208 May 1/10

52-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL UPPER LATCH HOOK AND PIN INSPECTION Inspect the complete upper latch hook mechanism to include hooks, latch pins, hook arms, levers and clevis pins for cracks, fractures, damage and excessive wear. Replace all parts worn beyond serviceable limits. Check wear limits as follows (Ref. Figure 203): a. Remove clevis pin and pivot pin to inspect for fatigue fractures and measure wear, replace when wear reaches 10% of original diameter. b. Prior to installation lubricate rotating and sliding pins and bolts with lubricating oil (4, Chart 2, 52-00-00), wipe off excess lubricating oil.

FOLDING STEP ADJUSTMENT a. Start the adjustment procedure with the door open (Ref. Figure 205). b. Remove the upholstery panel behind the step. c.

Raise the door until the step interconnect rod is accessible through the lightening holes in the door structure.

d. Adjust the step interconnect rod to obtain 0.01 to 0.05 inch gap at the down-stop. e. Raise the door slightly until the step extending cable is slack. f.

Remove the turnbuckle locking clips.

g. With the door open and the handrail installed, adjust the step extending cable as necessary to maintain a gap of 0.01 to 0.05 inch between the upper step and its stop when the lower step contacts its stop. NOTE: Stand on the bottom fixed-step while checking step clearance after adjusting the step-extending cable.

A28

52-10-00

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DOOR ASSEMBLY

FUSELAGE DOOR FRAME

0.12 INCH MINIMUM WITH LATCH IN LOCK POSITION

UPPER LATCH PIN ADJUSTMENT

DOOR ASSEMBLY

FUSELAGE DOOR FRAME

CHAMFERED END MUST ALWAYS BE PLACED ON OPPOSITE SIDE OF ROLLER ASSEMBLY. 0.38 + 0.06 - 0.25 INCH WITH LATCH IN LOCK POSITION

ROLLER ASSEMBLY DOOR ASSEMBLY

FUSELAGE DOOR FRAME LOWER LATCH PIN ADJUSTMENT (50-430018-11)

0.38 + 0.06 - 0.25 INCH WITH LATCH IN LOCK POSITION ROLLER ASSEMBLY

LOWER LATCH PIN ADJUSTMENT (50-430018-9)

LJ52B 050689AA.AI

Latch Pin Adjustment (FL-1 and After) Figure 204

Page 210 May 1/10

52-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Folding Step Adjustment (FL-1 and After) Figure 205

A28

52-10-00

Page 211 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL h. Secure the turnbuckle in place with the locking clips. i.

Replace the upholstery panel.

j.

Check that the stainless steel bumper pads on each aft corner of each step are securely attached to the step. If the bumper pads are loose or missing, install the bumper pads as follows: 1. Fabricate a replacement pad out of 1/16 inch thick stainless steel if necessary. The replacement should measure 0.56 by 0.76 inch. 2. Scuff the bonding surface of the bumper pad and the underside of the door with coarse grit sandpaper. 3. Clean the bonding surfaces with solvent (8 or 9, Chart 2, 52-00-00). 4. Wipe the surface clean with a clean dry rag before the solvent can evaporate. 5. Apply adhesive (10, Chart 2, 52-00-00) to both surfaces. 6. Place a layer of clean gauze or cheesecloth between the step and bumper pad. 7. Clamp the bumper pad to the step until the adhesive has cured per manufacturer’s recommendations.

HANDRAIL ADJUSTMENT a. Ascertain that the spring-loaded post for the handrail is fully extended when in the down position. If it is not, reduce the tension of the spring until the post extends far enough for the weight of the door to rest on the support cable. b. With the door closed, hook a spring scale into the cable attach fitting at the upper end of the handrail post. The spring scale should indicate that the handrail post is being held against the door with a force of 21/2 to 31/2 pounds.

CABIN DOOR SEAL The cabin door seal is inflated by engine bleed air tapped from the deice manifold located under the right side of the center aisle floorboard. Air is routed from the manifold through a normally open solenoid valve that receives power from the landing gear safety switch and shuts off the air supply to the door seal during ground operations when energized. During pressurized flight, the solenoid valve is energized by placing the pressurization dump switch in the “DUMP” position.

CABIN DOOR SEAL REPLACEMENT a. Remove the old seal and wash all traces of old adhesive from the door with solvent (8, Chart 2, 52-00-00) b. Wash the new seal thoroughly with solvent (8, Chart 2, 52-00-00) to remove the soapstone powder preservative. c.

Apply translucent adhesive (11, Chart 2, 52-00-00) to the end of the channel and up approximately 11/2 inches on each side of the lower door.

d. Place the seal ends in place and wrap the split flat ends around the bottom of the door and bond them into place with cement (12, Chart 2, 52-00-00). Ensure that the support inserts in the ends of the seal are positioned on the side of the door and there is no excessive build-up of cement. e. Clamp the seal to assure full contact until the adhesive has cured for 24 hours.

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52-10-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL f.

After the curing has been completed, stretch the seal evenly over the top of the door.

g. Slide the corner stiffeners (located inside the seal) into place and install the seal into the seal retaining channel. h. Apply soapstone powder to the seal as needed to ensure that the seal will slide into the proper place when closing the door.

PNEUMATIC VALVE ADJUSTMENT The pneumatic valve may be adjusted as follows: a. Remove the cabin floorboard aft of the main spar. b. Attach a 0 to 50 psi pressure gage to the door seal side of the valve. c.

Apply a pressure of 18.5 psi to the solenoid side of the valve.

d. Back off the locknut and adjust the spindle on the top of the valve to obtain a reading of 4.1 psi on the pressure gage. e. Tighten the locknut and install the necessary plumbing to the valve. f.

Install the cabin floorboard.

MAIN CABIN DOOR HINGE REPLACEMENT The hinge should be replaced on the main cabin door (standard airstair door), when consecutive lugs are missing (on single or both hinges) or more than one lug is missing in an 8.0 inch span along a single hinge. Ignore the partial lugs on each end in the lug count.

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52-10-00

Page 213 May 1/10

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CARGO AND AIRSTAIR DOOR The cargo door (Ref. Figure 1) is

top and incorporates

an

airstair door and window. Gas

on

each side of the door for

with

opening

the door after the initial

and

on

the

fuselage

are

(FM-1 AND AFTER)

attached to the door frame and to brackets

charged

nitrogen

DESCRIPTION AND OPERATION

hinged

opening

at the

applied.

force is

structure above the door, cushion the

springs automatically

Four small gas springs, attached to brackets on the door closing force of the large gas springs on the sides of the

door. The door is counterbalanced to remain in the open position; however, a support rod P/N 101-590053-1, (Item No. 2, Chart 1, 52-00-00) is available for additional support and to hold the door open during gusty conditions. The gas springs also apply a closing force to assist in closing and latching the door. A rubber seal is held in place retainers around the periphery of the door to effectively seal the pressure vessel when the cabin is pressurized.

by

The latching mechanism for the cargo door is operated by two handles, one at the bottom forward corner and the other at the upper aft side of the door. The rotary handle on the aft side of the door is attached to cable drums. When the handle is rotated, cables attached to the drums wind or unwind in response to the direction of handle movement. The cables from the handle are routed around splined drums at each of the camlock latches on the forward and aft

sides of the door. The splines in the drums engage splines on the camlock shafts of the latch so that the rotation of the drum, when actuated by the cable from the handle, rotates the face of the latch to engage the latch post in the door frame. The latch cables are adjusted by turnbuckles to a tension (25-30 pounds) sufficient to allow proper

latching

and

unlatching

in response to handle movement. A splined cam on the ends of the camlock shafts opposite on brackets at the upper latches to indicate when the door is closed and

the latch faces actuate switches mounted

latched. The movement of the lower latch handle fore and aft is transferred door to four latch

pins

that engage latch brackets

on

the door with

lugs

by

a

tube

running

the width of the cargo

attached to the doorsill of the

fuselage.

The latching mechanism for the airstair door is similar to the cable-camlock latching mechanism. Cables from the handles of the airstair door

are

routed around

splined

portion of the cargo door drums at the three camlock

latches on each side of the airstair door for latching and unlatching the camlock latches at latch posts on the cargo door in response to handle movement. Switches at the lower door, in conjunction with a switch adjacent to the pressure lock, switches at the latches and handles of the cargo door and switches at the doorsills of both doors, are connected into

doors

az,

are

a

warning

circuit with

a

readout

on

the annunciator

panel

to indicate when the airstair and cargo

closed and latched.

52-11-00

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

2

1

3

ii cf~s

i

22

I

1

16

I4

25 27

26

\i; 15

7

29

\;\CT

30

i-i

Q,/

QK

1

\t:

o 111I~

1

13

i.

2. 3. 4.

5. 6. 7.

8. 9. 10. 11. 12.

13. 14.

IS.

GAS SPRING BRACKETS DOORSILL SWITCH

200-107-15

CARGO DOOR UPPER AFT HANDLE

17.

21.

CARGO DOOR CAMLOCK LATCHES (4) DOOR ROLLER GUIDE BRACKET (2) SAFETY LATCH CATCH (OPEN POSITION) OPEN POSITION STOP BOLT FOLDING STEP MECHANISM

22.

AIRSTAIR DOOR INSIDE HANDLE

23.

CARGO DOOR HANDLE SAFETY LATCH SAFETY LATCH STOP (CLOSED POSITION) CAMLOCK LATCHES AND POSTS (6) TURNBUCKLE (AIRSTAIR DOOR FORWARD LATCH] FOLDING STEPS CARGO DOOR HANDLE WARNING SWITCH

19. 20.

24.

HANDLEHOOK LOWER HANDLE WARNING SWITCH DOORSILL SWITCH LOWER LATCH SWITCH LOWER LATCH PINS (4) AIRSTAIR DOOR LATCH SWITCHES (2) TURNBUCKLE (AIRSTAIR DOOR AFT LATCHES)

1/0852-11-00

16. 18.

TURNBUCKLE (04000 DOOR FORWARD LATCHES) CAMLOCK LATCH SWITCHES (2) GAS SPRING BRACKETS (2) DOOR SUPPORT ROD BRACKET CARGO DOOR LOWER HANDLE LOWER LATCH ROD

25. 26. 27.

28. 29.

30.

CARGO DOOR ALIGNMENT GUIDE

ALIGNMENT GUIDE STRIKER PLATE

and Airstair Door Latching Mechanism (FM-1 and After)

Figure

May

9

12

(4)

Cargo

1

1

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

CARGO AND AIRSTAIR DOOR

(FM-1

AND

AFTER)

CARGO DOOR REIWOVAL CAUTION: Avoid

operating

the cargo door with the airstair open. To do

so

may

damage

the

hinges

and

adjacent

structure.

a.

Disengage the cabin door and

b.

To open the cargo

door, proceed

NOTE: The cargo door 1.

radiant heat circuit breakers. as

follows:

mechanism

latching

can

only

be

from inside the

operated

airplane.

Release the fasteners and open the hinged door on the lower forward corner of the cargo door. move the handle to the open position. Secure the hinged door.

Trip

the

hook and 2.

Release the fasteners and open the hinged door on the upper aft corner of the cargo door. Press the button move the handle to the OPEN position. Secure the hinged door.

and 3.

Attach

one

end of the door stabilizer

of the door. Make

sure

CA UTION: Avoid side

c.

d.

the detent

loading

assembly (door support rod)

of the gas

spring assemblies

to

the airstair doorsill step and allow the door to

4.

Push out

5.

Attach the free end of the door support rod to the ball stud

on

to the ball stud located on the forward side

is installed.

pin

fuselage

Disconnect the electrical connector at the upper

prevent damage

swing on

to the internal mechanisms.

open.

the forward

fuselage

door frame.

door frame.

retaining clips and detach the six gas cylinder assemblies at the bracket mounted ball fuselage door frame (4 places), and on the lower forward and aft door surface (2 places).

Remove the upper

e.

Remove the

f.

Support

g.

Remove the

screws

and the

the forward and aft

hinge pin

hinge pin

portions

from the

retainers

on

each end of the

studs

on

the

hinge.

of the door. Remove the door support rod.

hinge

halves and

carefully

remove

the door.

CARGO DOOR INSTALLA TION (Ref. Chapter 12-20-00).

If necessary, lubricate the cargo door

b.

Carefully

c.

Attach the door

d.

Install the

e.

Attach the gas spring assemblies to the bracket mounted ball studs on the upper the lower forward and aft sides of the door. Secure with the retaining clips.

f.

Connect the door electrical connector at the upper

g.

With the electrical power on, engage the cabin door circuit breaker. Observe that the CABIN DOOR

an,

move

the door into

support rod

hinge pin

position,

as

shown

the lubrication Chart

a.

mate the

to the door and

retainers

on

on

hinge halves, and

fuselage

each end of the

install the

ball studs. Make

hinge

with

fuselage

sure

hinge pin.

the detent

pin

is installed.

screws.

fuselage

door frame and

on

door frame.

52-11-00

light

is ON.

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

h.

i.

to observe for

Station two maintenance

personnel outside the airplane at each end of the hinge pin retainers and the edge of the door skin as

door

condition between the

the door is closed.

Close the cargo door,

proceed

as

hinge

a

binding

follows: the detent

pin is

1.

Detach the lower end of the door support rod. Make

2.

Firmly grasp the free end of the door support rod while exerting a downward force to overcome the pressure of the gas spring assemblies. Remove the door support rod after the gas spring assemblies pass the overcenter

3.

sure

installed.

position.

If necessary, apply an inward force against the lower the latching mechanism to engage.

portion of

the door to compress the door seal,

permitting

NOTE: The airstair door lower fixed step the cargo door closed. 4.

Open

the

hinged

(door closed) incorporates

door

on

the upper aft

door

on

the lower forward

corner

a

finger

hold cap which may be used to

of the door. Press the button and

move

pull

the handle to the

closed position. 5.

j.

Open the hinged position.

corner

of the cargo door. Move the handle to the CLOSED

With electrical power ON, observe that the CABIN DOOR

light

is out.

ADJUSTMENT OF CARGO DOOR LA TCHING MECHANISM CAUTION:

Adjustment mechanism

of the two cargo door

alignment guides complete. rigging requirements

a.

Make

b.

Remove all

c.

Remove the seal from its retainer around the

d.

upholstery panels from the cargo

Remove the

retaining clip

Remove the

retaining clip

door.

periphery of

from the end of each of the four small gas spring assemblies at the point where the door frame above the cargo door, then disengage each of the gas spring on

each bracket.

from the end of each of the two

anchored to the brackets the ball stud

on

taped

to the door at the four latch

NOTE: An undercontour of 0.06 inch between the door and

NEVER be outside that of the

Adjust the

h.

Adjust the

open position stop bolt handle when the handle is rotary

the

Page

large gas spring assemblies at the point where disengage each of the gas spring assemblies from

on the side of the cargo door, then each door bracket.

Shim the cargo door with spacer blocks the door matches that of the fuselage.

g.

the cargo door.

on

assemblies from the ball stud

f.

not to be made until all other cargo door

that the airstair door is closed and latched.

sure

anchored to the brackets

e.

are

are

closed

position stop

fuselage

is

points

acceptable,

so

that the outside contour of

but the door contour must

fuselage.

(Ref. Figure 201) to obtain a clearance of 0.09 to 0.12 inch between it positioned with the safety latch engaged by its open position catch.

bolt

and the

(Ref. Figure 201) to obtain a clearance of 0.06 to 0.09 inch between it and positioned with the safety latch engaged by its closed position catch.

rotary handle when the handle is

52-11-00

a24

Hawker Beechcraft Corporation SUPER KING AIR B300/8300C MAINTENANCE MANUAL

!1,

OPEN POSITION S70P BOLf

OPEN POSITION--~_ SAFETY LATC)-t CATCH

all

"R SAFETY LATCH--4--´•cC~h

B

LOSED POSITION STOP BOLT’

CtOSED POSITION SAFETY

HCIACHCTAL

if 200-107-7

Rotary Latch Adjustment (FM-1 and After) Figure 201

a24

52-11-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CAMtOCt( SHA~-r SPLINES

i~si oi

´•"~::StOP

PIN

ALIGN SLOT IN DRUM WITH GUIDE RETA)NER

I

LATCtJ CAM 200-107-10

Cable Drum and Camlock Shaft Assembly (FM-1 and After)

Figure

Page

52111100

202

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE:

requires replacement, wrap the cable around each latch drum and the rotary handle drum retaining pin slot in the drum is aligned with the drum guide retaining screw (Ref. Figure 202), on the inboard side of the latch housing. This will allow adequate rotation of the camlock shaft to complete the latching and unlatching movements of the latching mechanism. If

door cable

a

so

that the

i.

Rig the latch cables to the required tension (Ref. Figure 203). Cable tension for the two forward camlock latches is adjusted with the turnbuckle at the top of the door. The turnbuckle just below the rotary door handle is for adjusting the cable to the latches on the aft side of the door.

j.

After proper cable tension is set,

k.

With the rotary handle in the open position, insert the splines of each camlock shaft into the splines of its respective cable drum so that the cutout in the latch face of the shaft is centered with respect to the are made

by I.

the latch when the door is

safety

the turnbuckles

as

indicated

(Ref. Figure 204).

closing (Ref. Figure 205).

splines of each latch cam (Ref. Figure 202) with the splines on the small end of the camlock shaft just contacts its stop pin. On the top latch on each side of the door where the electrical switches are located, back the cam off one spline from the point where it contacts the stop pin, then install the washer and nut securing it in place. On the bottom latch on each side of the cargo door, back the cam off two splines from the point where it contacts the stop pin, then install the washer and nut securing the cam in place.

Engage

so

NOTE:

the

that the

cam

Any time the camlock shafts

are

repositioned

with respect to the cable drums, the latch

cams

must be

reindexed to the camlock shaft to allow full travel of the latch handle.

5

B ~e;

g Zi cl

20

30

U)

BO

~O

m

so

so

la,

~to

TDIRRA’RRE N r LBS. A~ SET

25f:

Door Cable Tension Graph (FM-1 and After)

Figure

A24

203

52-11-00

Page

yaM502

1/OS

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CLIPS

fURNBUCKLE SAFETV CLIPS 200-1 07-11 Safetying

Cable Turnbuckles

(FM-1 and After)

Figure

204

LATCH CLOSING ARC FROM CENTERLINE OF HINGE CAMLOCK SHAFT LATCH FACE

TO

CLOSE

APPROXIMATE EQUAL SPACE

200-107-12

Camlock Latch Adjustment (FM-1 and After)

Figure

Page

52-11-00

205

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

m.

Adjust the latch rod to a length of 6.15 inch as measured from the centerline of its attachment points (Ref. Figure 206) to the latch pin guide and the latch handle. The rod end that is attached to the handle is adjustable.

n.

With the lower latch handle in the hooked a

position, check that the untapered shoulder of each latch pin extends respective latch pin brackets (Ref. Figure 207). If necessary, shim the latch beyond AN960-616L washers (Ref. Figure 206) to obtain the 0.10 inch dimension.

minimum of 0.10 inch with AN960-616

pin

NOTE: The cabin

or

its

upholstery panels

adjustment of the latch posts o.

With the door closed and held in

on

each side of the door frame must be removed to

provide

access

for

following step.

in the

place by the bottom latches, adjust

each latch

post

on

the sides of the door

of contact with the latch face of the camlock shaft

aligns with the closing are made by the latch when the door is fully closed (Ref. Figure 208). To make this adjustment, rotate the eccentric bushing, in conjunction with the eccentric latch post, until the post is properly aligned with the latch, then tighten and safety the nut securing the post in place. A special latch post wrench (Item No. 1, Chart 1, 52-00-00) is required to adjust the eccentric bushing. frame until the

post’s point

CA UTION: The gas

spring assemblies accomplished.

NOTE:

Coating

the latch

post with "Blue Dykem",

the face of the latch p.

the eccentric

Adjust

II/1UST be disconnected for the

or

the

equivalent,

adjustment in the following procedures

will facilitate

pinpointing

its

area

to be

of contact with

(Ref. Figure 208).

bushing (Ref. Figure 209)

of the roller

guide assembly

in the door frame

on

each side of the

cargo door adjacent to the upper latches until the roller just contacts the guide bracket on the door when the door is fully latched. After the roller is properly positioned on the door frame with respect to the guide bracket on

q.

the door,

the nut

securing the roller

in

place.

Close the door and check that the camlock latches when actuated

properly r.

tighten

Adjust make

by

the

latching

on

the sides of the cargo door and the bottom latches ope rate

handles.

the doorsill, lower latch, latch handle, rotary handle, and forward and aft latch switches as necessary to that the cabin door warning system functions properly. Adjust the switches (Ref. 52-71-00, CARGO

sure

AND AIRSTAIR DOOR WARNING

SWITCHES). to the door at the forward and aft latch

s.

Remove spacer blocks and shims that

t.

Work the door seal into the retainer channel around the

were

taped

perimeter

of the door with

a

points.

tongue depressor

or

its

equivalent. u.

v.

the ends of the gas spring assemblies with the ball studs securing them to the brackets over the cargo door, then lock each in place with a retaining clip.

Engage and

Check the latch mechanism for proper

CAUTION:

operation

in the open and closed

Adjustment of the two cargo door alignment guides rigging requirements are completed.

are

on

the sides

positions.

not to be made until all other cargo door

mechanism w.

Center the cargo door lower latch mechanism with the lower doorsill lugs. Adjust the striker plates on the forward and aft fuselage doorframe, using shims (P/N 101-514190-11) as required to maintain a 0.06 to 0.03 inch clearance between the roller and striker

x.

,4

Install all

upholstery

that

was

removed

plate.

during

the

adjustment procedure.

52-11-00

Page

yaM702

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: When the cargo door is closed and latched, the white index marks on the upper rotary camlock latches should align with the calypso orange stripes on the gas spring assemblies on the sides of the door. The orange marks

on

the lower rotary camlock latches should

align

with the black

stripes

on

the cargo door

upholstery. GAS SPRING ASSEI~BL Y REPLACEI1IENT CAUTION: Under The a.

following

no

circumstances shall any attempt be made to service the gas

criterion may be used to determine

The door opens

sluggishly

or

b.

During

door

fully

the gas

spring

assemblies.

assemblies:

open.

sluggish operation of the gas springs need for replacement of~the part.

NOTE: It should be noted that and does not indicate

fails to

replacement of

spring

is normal

during exceptionally

cold weather

a

closing, after the gas spring

assemblies pass overcenter

position,

the downward force is sufficient

to close the door. c.

Gas spring rods

are

nicked

or

bent.

CARGO DOOR SEAL REPLACEI~ENT a.

Open

the cargo door and install the door support rod.

CAUTION: The door support rod will have to be detached cargo door shall be supported.

temporarily during seal replacement. During

the cabin door circuit breaker.

b.

Disengage

c.

Disconnect the electrical connector at the upper

d.

Detach the gas

e.

Index mark the seal

f.

Remove the old seal from the door seal retainer.

g.

Apply soapstone powder to

h.

Starting with the seal splice at the marked location on the door frame, work strip of phenolic or plexiglass with a rounded end will facilitate installation.

i.

Clean off the soapstone

j.

Attach the gas

k.

Connect the electrical connector at the top of the door frame.

I.

Engage

May

this time the

spring

door frame.

assemblies at the door.

splice

at the

the

top of the door frame.

new

powder

as

spring assemblies

the cabin

fuselage

seal and the seal retainer. the seal into the retainer. A thin flat

necessary.

to the door.

lights circuit breaker,

52-11-00

with power

ON, observe that the CABIN LIGHT is

on.

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

6.t5 1N.

LATCH ROD

AN 9~0-616 WASHER

(MINIMUM OF ONE) AN 960-616 WASHERS

AS F~EQUIRED

OPEN POSITION OF BOTTOM LATCHES

200-107-8

Adjustment of Bottom Latches (FM-1 and After) Figure 206

A24

52-11 -00

PMaa9ye~t

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OPEN POSITION STOP BRACKET

OPEN POSITION STOP

C~OSED POSITION HOOK

LATCH ROD

LATCH PIN

BRACKETS

rl .10 IN. Q I

LATCH PIN CLOSED POSITION OF BOTTOM ~ATCHES 200-107-9

Latch Pin

Adjustments (FM-1 and After) Figure 207

Page

52-11-00

aas

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LATCH FACE OF

CONTACT AREA~ (COAT W\TH F3LUE

CAMLOCK SHAFT

DY KEM)

TO CLOSE

LATCH CLOS1NG ARC FROM CENTER OF

HINGE

LATCH POST

CARGO DOOR LATCH POST

ECCENTRIC BUSHING 200-107-22

Camlock Latch and Post Alignment (FIM-1 and After)

Figure

aw

208

52-11-00

Page

yaM1 2

1/OS

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ECCENTRIC BUSYrNG

1 ij ROLtER

200-1 07-14

Roller Guide Adjustment (FM-1 and After)

Figure

Page

52111100

209

A24

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FITTING A NEW AIRSTAIR DOOR A

new

airstair door is

not rivet the

hinge

supplied

half

or

hinge half,

with the door

seal retainers to the

new

the seal retainer, and the seal

separate from the door. Do

door until after the door has been fitted.

door, (Ref. Chapter 52-11-00, CARGO DOOR REMOVAL).

a.

Remove the cargo

b.

Remove the airstair door,

c.

Place the cargo door on a padded work bench with the outside skin of the door up. The cargo door should be secured to the work bench if possible, to prevent movement during the fitting procedures.

d.

Place the

e.

Using

new

airstair door

straightedge,

a

(Ref. Chapter 52-11-00,

on a

padded

AIRSTAIR DOOR

work bench with the outside skin of the door up.

draw two horizontal reference lines

through

the centerline of the

the lower outside skin of the airstair door. The lines should be drawn side and f.

through

the upper

screws on

Draw two horizontal reference lines

adjacent

opposite

the

through edges

side to the outside

head

phillips

the lower set of

screws on

screws on one

of the door.

the cargo door the airstair door. The lines should extend to the recessed airstair door

through

to the lines that were drawn on

REMOVAL).

the centerline of the

phillips-head

screws on

frame. NOTE: The horizontal reference lines may not match when the new airstair door is first placed into the frame; however, they should begin to align more closely as the door is trimmed and begins to fit into place. g.

Place

a

frame

adjacent

shim, approximately 0.038 to the

existing

door

to 0.050-inch thick and 8 to 10-inches

hinge

long,

into the recessed airstair door

half.

NOTE: This shim will hold the outside skin of the airstair door flush with the outside skin of the cargo door airstair door is properly trimmed. h.

i.

Place the handle of the airstair door to the full open the posts in the cargo door.

position.

This will allow the six camlock latches to

once

align

the

with

Position the airstair door in the cargo door. The excess skin on the door will not allow it to fit into the recessed center the camlock latches on the post as close as possible.

frame; however,

CAUTION: Extreme caution must be used

during

skin removal to prevent

removing

excess

material and

creating

between the cargo and airstair doors. The gap between the airstair and cargo door is to be 0. 060 inch maximum.

an

j.

enlarged gap

at the bottom of the airstai r doo r, determine where excess ski n needs to be removed to allow the bottom

Starting

end of the door to fit into the recessed frame. Remove the airstair door from the cargo door.

disc attached to

sanding k.

an

electric motor,

remove excess

skin from the bottom of the door

Using a 40-grit required.

as

Position the airstair door in the cargo door and center the forward and aft cam latches on the post. Determine excess skin needs to be removed from the sides of the door so it will fit into the recessed frame. Remove

where

excess

NOTE:

i.

skin from the sides of the door

required.

many times as requ ired unti I the sides of the door fit into the recessed frame. The horizontal reference lines should begin to line up as the sides of the door are trimmed to fit.

Repeat the above proced u re as

begins to fit into the opening, place four 3/8- to 1/2-inch shims, support the door flush with the outside skin of the cargo door.

As the door

opening

n24

as

to

two on each

side, into the recessed

52-11-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

m.

begin removing excess skin material from the top of the door. This is best accomplished by leaving opening and raising the top up for sanding. Repeat this procedure, as required, until the top of door will fit into the recessed opening. Place three 3/8 to 1/2-inch shims into the recessed opening to support

Mark and

the door in the the

the top of the door flush with the outside skin of the cargo door.

NOTE: The top of the door will continue to grow n.

as

the door fits further into the recessed

opening.

opening, check that the camlock latches are centered on the post and latch the door closed. Mate the new hinge half (P/N 101-430196-3) to the existing hinge half on the cargo door and install the hinge pin. Use shims as required all around the door to keep it from moving while drilling hinge Once the door fits

into the

completely

holes. o.

twenty-three 0.128- 0.133-inch-diameter holes through the door, using the first row of pilot holes adjacent hinge pin as guides. Countersink the twenty-three holes 100 degrees X 0.230-inch diameter on the hinge

Drill

to the

half. p.

Install #30

five 0.176 the

pull

(minimum of seven) equally spaced to hold the door to the hinge half. Drill thirtyholes, using the remainder of the holes in the hinge half as guides. Countersink degrees X 0.286-inch diameter on the hinge half.

cleco fasteners

0.180-inch diameter

thirty-five

holes 100

CAUTION: Do not exceed the maximum gap of 0. 060 inch between the airstair and cargo door. q.

The door

can now

be

opened

and closed

freely

on

the

hinge,

Remove the

remaining

excess

skin material until

the desired gap of 0.040 inch is obtained between the airstair and cargo door. r.

hinge pin and the 52-00-00) A

Remove the

No. 6, Chart 2, s.

t.

Position the

new

hinge

half and the lower seal retainer

twenty-three

door with sealer

No. 15, Chart 2,

Install

(P/N 101-430142-27)

holes drilled, refer to

in the retainer with the

(Item

sealer

(Item

align the pilot

holes

cleco fasteners. Remove the airstair door from the cargo door. B between the hinge half and the lower seal. on

the door and

Apply

step "o". Seal between the lower seal retainer and the

52-00-00).

twenty-three rivets (P/N MS20426AD4) through the hinge half, door skin, (P/N NAS1739B5-5) through the remaining holes in the hinge half.

and the retainer. Install

thirty-

five rivets u.

the door. The outside

0.096-inch diameter holes holes 100 v.

w.

(P/N 101-430142-29) and the top retainer(P/N 101-430142-31) along the inside edge of the retainers should be 0.025 inch from the outside edge of the door. Drill through the door, using the pilot holes in the retainers as guides. Countersink the

Position the two side retainers

edge of

degrees

X 0.230-inch diameter

the outside skin.

Seal between the retainers and the door with sealer

MS20426AD3)

to secure the retainers to the door.

Carefully place

the airstair door into

retainers

on

each end of the

hinge

position,

with

(Item

mate the

No. 15, Chart 2,

52-00-00). Install rivets (P/N

halves, and install the hinge pin. Install the hinge pin

screws.

(Ref. Chapter 52-11-00, CARGO DOOR INSTALLATION).

x.

Install the cargo door,

y.

Install the bushi ng, spacer, washer, and

z.

on

screw

attaching the

handrail cable eye to the cargo door

pin, washers, and

cotter

pin attaching

Adjust folding step mechanism, (Ref. 52-11-00, FOLDING

STEP

ADJUSTMENTS).

Fold the sill step outboard and install the

the

folding step

mou nt

bracket.

cable under the

doorsill step. aa.

May

1/0852-11-00

P~24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ab.

Adjust

latching mechanism, (Ref. Chapter 52-11-00, ADJUSTMENT MECHANISM).

the airstair door

LATCHING ac.

warning switches located under the doorsill step adjacent warning switches, (Ref. Chapter 52-71-00, ADJUSTMENT OF WARNING SWITCHES).

Connect the electrical connector for the airstair door to the door

hinge. Adjust

the airstair door

CARGO AND AIRSTAIR DOOR ad.

Starting with the strip of phenolic or plexiglass soapstone powder as necessary.

Apply soapstone powder to

the

new

seal and retainer.

work the seal into the retainer. A thin flat installation. Clean off the ae.

af.

OF AIRSTAIR DOOR

Remove

upholstery

from the old door and install it

Install the bolt and washer

ag. Paint the

new

Corporation,

attaching

door to match the

the door

fuselage.

the

on

damper to

new

or

with

a

install

the airstair door

painted

to match the

paint applied

new

upholstery

the door,

as

required.

Support, Hawker Beechcraft airplanes.

to individual

lubricate the door

fuselage,

on

rounded end will facilitate

support bracket.

Refer to the Commercial Product

Wichita, for color and color number of exterior

ah. After the door has been installed and

door,

seal at the marked location

(Ref. Chapter 12-20-00).

AIRSTAIR DOOR REMOVAL a.

b.

Disengage

the cabin door circuit breaker.

Remove the cotter

pin attaching

and

pin, washers,

folding step

the

cable under the doorsill

step. Fold the step

inboard. c.

Disconnect the electrical connector

d.

Support

the door and

cargo door mount

adjacent

to the door

hinge.

the screw, washer, spacer and

remove

bushing attaching

the handrail cable eye to the

assembly.

e.

Remove the bolt and washers

f.

Remove the

g.

Support

screw

and

the door and

hinge

remove

attaching retainer the

the door

plate

damper

to the airstair door

at each end of the

hinge pin. Carefully

remove

support bracket.

hinge pin. the door.

AIRSTAIR DOOR INSTALLATION a.

If necessary, lubricate the airstair door

b.

Carefully

c.

Install the

hinge pin

d.

Install the

bushing,

move

the door into retainers

shown

as

on

the Lubrication Chart

(Ref. Chapter 12-20-00).

position and support the door. Mate the hinge halves, and install on

each end of the

spacer, washer, and

screw

hinge

with

attaching

the

hinge pin.

screws.

the handrail cable eye to the cargo door mount

assembly. e.

Install the bolt and washer

f.

Connect the electrical connector

g.

attaching

the door

adjacent

Fold the doorsill step outboard. Install the

damper to the

to the door

na,

support bracket.

hinge.

pin, washers, and

door sill step. The cable will have to be extended

airstair door

against

cotter

the

pin attaching the folding step

spring

cable underthe

load.

52-11-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

the cabin door circuit breaker.

h.

Engage

i.

Close and lock the airstair door. With electrical power ON, observe that the CABIN DOOR Unlock the door and check the time

j.

time

required

required

light

is out.

for the door to free fall from the full closed to full open

shall not be less than 5 seconds

position.

The

(Minimum).

ADJUSTn/lENT OF AIRSTAIR DOOR LA TCHING NIECHANISM a.

Remove the

b.

Remove the seal from its retainer around the

c.

Shim the airstair door with spacer blocks the door matches that of the cargo door.

upholstery panels

as

necessary to

gain

access

periphery

taped

to the

latching

mechanism.

of the airstair door.

to the door at the six latch

points

so

NOTE: An undercontour of 0.06 inch between the airstair door and the cargo door is door contour must NEVER be outside that of the cargo door. d.

that the outside contour of

acceptable, but

the airstair

position and the pressure lock engaged by the arm assembly, the handle support into the cable drum, then adjust the handle rod to fit between the arm

With the outside and inside handles in the closed insert

a

rig pin through

of the inside handle and the NOTE:

Only

arm

of the outside handle

(Ref. Figure 210).

the rod end that attaches to the inside handle of the door is

adjustable. After the handle rod is adjusted length, check that the threads of adjustable end are visible in the inspection hole of the rod tightening the jam nut and attaching the rod to the handle arm.

to the proper

before

Remove the

e.

rig pin from

the support of the inside

arm.

requires replacement, wrap the cable around each latch drum and handle drum so that the retaining pin aligned with the drum guide retaining screw (Ref. Figure 202) on the inboard will of latch This allow adequate rotation of the camlock shaft to complete the latching and side the housing. of the unlatching movements latching mechanism. If

NOTE:

a

door cable

slot in the drum is

f.

Rig

the latch cables to the tension

turnbuckles

on

(Ref. Figure 203). Cable

tension for the camlock latches is

adjusted with the

each side of the door.

g.

After the proper cable tension is set,

h.

With the door handles in the open position, insert the splines of each camlock shaft into the splines of its respective cable drum so that the cutout in the latch face of the shaft is centered with respect to the are made

by i.

the latch when the door is

safety

the turnbuckles

(Ref. Figure 204).

closing (Ref. Figure 205).

splines of each latch cam (Ref. Figure 202) with the splines on the small end of the camlock shaft cam just contacts its stop pin. On the bottom latch on each side of the door where the electrical so switches are located, back the cam off one spline from the point where it contacts the stop pin, then install the washer and nut securing it in place. On the other four latches, back the cam off two splines from the point where it contacts the stop pin, then install the washer and nut securing the cam in place.

Engage

the

that the

NOTE: Any time the camlock shafts are repositioned with respect to the cable drums, the latch reindexed to the camlock shaft to allow full travel (90 degrees) of the latch handles.

cams

must be

NOTE: The

following step can not be accomplished unless the cargo door has been completely rigged, (Ref. Chapter 52-11-00, ADJUSTMENT OF CARGO DOOR LATCHING MECHANISM).

May

52-11-00

nn4

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Adjust each latch post

adjacent to the latches of the airstair door until the post’s point of aligns with the closing are made by the latch when the door is fully closed (Ref. Figure 211). To make this adjustment, rotate the eccentric bushing, in conjunction with the eccentric latch post, until the post is properly aligned with the latch, then tighten and safety the nut securing the post in place. A special latch post wrench (Item No. 1, Chart 2, 52-00-00) is required to adjust the eccentric bushing.

j.

on

the cargo door

contact with the latch face of the camlock shaft

NOTE:

Coating

the latch post with "Blue

the face of the latch

k.

For the

Dykem", (Ref. Figure 211).

adjustment of switches SWITCHES).

on

or

its

the airstair door.

equivalent,

will facilitate

(Ref. Chapter 52-71-00,

pinpointing

its

area

of contact with

CARGO AND AIRSTAIR DOOR

WARNING I.

Remove spacer blocks

m.

Work the door seal into the retainer channel around the

to door at 6 latch

taped

points.

periphery

of the door with

a

tongue depressor

or

its

equivalent. n.

Attach

a

closing

pull gage to the

the door. The

torque required NOTE:

Multiply reading

outside handle and check the torque required to operate the latching mechanism while torque required to start rotation of the handle should not exceed 250 inch-pounds and the

to continue the

latching

movement should not exceed 100

inch-pounds.

the distance in inches from the handle shaft to the attachment in

pounds

on

the gage to

measure

the

inch-pounds

of torque

point of the pull gage times the required for actuation of the latch

mechanism. If the

o.

actuating torque does not fall within readings can be obtained.

the

prescribed limits, readjust

the door posts and cable

rigging

until

the proper

Reinstall all

p.

upholstery

that

was

removed to facilitate latch

adjustment.

FOLDING STEP ADJUSTMENT This

adjustment (Ref. Figure 212) supported by the handrail cable.

is to be

performed

with the cargo door latched and the airstair door down and

a.

Adjust the tu mbuckle for the top step cables until cable tension (approximately 50-60 pounds) firmly against its stop, then safety the turnbuckle.

b.

Adjust the turnbuckle for the then

c.

safety

Adjust the remaining turnbuckle

safety

NOTE: When the step cables are

step cables until cable tension holds the

center

step firmly against its stop,

the tu mbuckle.

off their stops, then

nnl

center

holds the top step

being

until all slack is removed but cable tension is insufficient to

pull

the

folding steps

the turnbuckle. are

properly rigged,

there is

no

play

between the

steps and their stops while the steps

used.

52-11-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRSTAIR DOOR DAMPER REPLACEMENT a.

Remove the bolts and washers

b.

Service the

c.

Attach the barrel end of the

attaching

replacement damper,

if

the door

damper to

the cargo and airstair door support brackets.

required, (Ref. Chapter 12-10-00).

damper to the cargo door support bracket and the piston rod end to the airstair door bracket with bolts and washers; shim as necessary, with AN960-416 washers, to align the damper ends support and eliminate side play.

NOTE: If the piston end

requires adjustment,

lock the threads with thread

locking compound (Item

No. 14, Chart 2,

52-00-00).

Page

52-11-00

nz4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

"00

:~SMEMBLY(: 12-

\(I

I

DETAIL

I-ii rl~7

A

r:

I

nJ

,gy

t

INSIDE

HANDLE IN CLOSED

RIG PIN HOLE

POSITION

ej

B ii

if$

DETAIL

HANDLE ROD

.r.,:.

B

200105-4

Latching Mechanism (FM-1 and After) Figure 210

Airstair Door

A24

52-11 -00

Page

yaM912

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

r~ LATCH

CONTACT AREA

FACE OF

CAMLOCK S)SAt

(COAT WITH BLUE ov KEM)

I

TO C=LOSE

LATCH CtOSING ARC

FROM~ CENTER OF LATCH

POSfJ

HINGE

ECCENTR1C BUSHING

DOOR FRAME LAfCH POST 206-107-13

Latch Post Adjustment (FM-1 and After)

Figure

May

52-11-00

211

na4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRS-TAIR DOOR SEAL REPLACER/1ENT a.

b.

Open

the airstair door and

disengage

Remove the cotter pin, washers, and pin attaching the inboard. The cable is

spring

Disconnect the electrical connector

d.

Remove the bolt and washers

Support

the door and

cargo door mount

remove

adjacent

attaching the screw,

to the

the door

hinge

door.

damper to

the cargo door

g.

Remove the old seal from the door seal retainer.

h.

Apply soapstone powder

splice

at the

or

to the

to the

top of the door frame.

new

seal and the retainer.

splice at the marked location on the door, work the plexiglass with a rounded end will facilitate installation.

with the seal

of phenolic

support bracket.

washer, spacer, and bushing attaching the hand rail cable eye

Index mark the seal

Starting

cable under the doorsill step. Fold the step

assembly.

f.

i.

folding step

loaded.

c.

e.

the cabin door circuit breaker.

j.

Clean off soapstone powder

k.

Install the bushing, spacer, washer, and

I.

Install the bolt and washer attaching the door

m.

Connect the electrical connector and install the

as

seal into the retainer. A thin flat

strip

necessary. screw

attaching

damper

the hand rail eye to the cargo door mount

assembly.

to the cargo door mount bracket

pin, washers, and cotter pin attaching against the spring load.

the

folding step

cable

under the doorsill step. The cable will have to be extended n.

Engage

the cabin

lights circuit breaker,

with power

ON; observe that the CABIN LIGHT is

on.

CARGO DOOR LOWER A TTACHII/1ENT LUG INSPECTION The cargo door lower attachment lugs should be inspected after each intervals specified in Chapter 5-00-00. The wear dimension of 0.290 inch

~as

heavy equipment cargo operation and at (Ref. Figure 213), must not be exceeded.

52-11-00

PMa Syel:~:May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ATTACHED TO BRACKET ON SILL

STEP ON CARGO DOOR

Ij

CABLE TURNBUCKLE AND

TURNBUCKLE

CABLE TURNBUCKLE

j j

AND STOP FOR

CENTER STEP

A:

TURNBUCKLE SAFETY CLIPS

DETAIL

A

j’ malos-e

Folding Step Adjustment (FM-1 and After) Figure 212

Page

52-11 -00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

.290

-t .290

MINIMUM

~I

t

MINIMUM

C9201955

Lower Attachment Lug Inspection (FM-1 and After)

Figure

p~,

213

52-11-00May

1/08

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 52-20-00

EMERGENCY EXIT DOORS - DESCRIPTION AND OPERATION The two inward opening, plug type, emergency exit doors, placarded EXIT-PULL, are located on the right and left sides of the cabin over the wings. From the inside, the doors are released with a pull-down handle, and on the outside the doors may be released by a flush mounted pull-out handle. The doors are of the nonhinged type which remove completely from the frame when the latches are released. The door can be locked so that it can not be removed or opened from the outside using the flush-mounted pull-out handle. The door is locked when the locklever (inside) is in the down or locked position. Locking the door is for security when the airplane is parked. The locklever should be in the up or unlocked position prior to flight, to allow removal of the door from the outside in the event of an emergency. Removal of the door from the inside is possible at all times using the EXIT-PULL handle, since this handle is not locked by the lock-lever. An exit lock placard is placed on the lock-lever so that it can be read when the lever is in the locked position. Emergency exit lights located in the overhead upholstery panels adjacent to each door provide for easy location of all exits in the event that evacuation of the airplane is necessary (Ref. Chapter 33-20-00).

A27

52-20-00

Page 1 Feb 1/10

SUPER KING AIR B300/B330C MAINTENANCE MANUAL 200200200

EMERGENCY EXIT DOORS - MAINTENANCE PRACTICES On the lower frame of the emergency exit are two adjustable lugs which hold the lower section of the door in place. On each side of the frame are three adjustable lugs set to engage three stationary lugs on each side of the door to prevent the door from being pushed out past the airplane contour when the cabin pressurization is turned on. NOTE: When replacing the emergency exit door seal, clean all traces of the old adhesive from the door with solvent (8, Chart 2, 52-00-00). Use adhesive (13, Chart 2, 52-00-00) to bond the new seal to the door.

EMERGENCY EXIT DOOR REMOVAL WARNING: Never open the emergency exit door when the cabin is pressurized. a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Pull the release handle out and pull down on the emergency exit door.

d. Electrically disconnect the emergency exit door (Ref. Figure 201) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). e. Remove the emergency exit door from the airplane.

EMERGENCY EXIT DOOR INSTALLATION WARNING: Never open the emergency exit door when the cabin is pressurized. a. Electrically connect the emergency exit door (Ref. Figure 201) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). b. Place the lower edge of the door to the outboard side of the two adjustable lugs on the emergency exit lower frame. Push the handle in until the latches have closed completely. NOTE: When installing a new emergency exit door, the adjustable side lugs will have to be adjusted with the cabin pressurization on. This must be done to achieve proper matching of the door with the airplane contour. c.

Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

LATCHING MECHANISM ADJUSTMENT NOTE: The following adjustment steps may have to be made more than once to obtain proper operation of the door. a. Adjust the linkage assembly to make sure that the slide lock assembly clears the pushrod in the unlocked position (Ref. Figure 202). b. Adjust the AN 3 stop bolt so the handle is flush with the upholstery panel. c.

Adjust the turnbuckle to increase or decrease door-to-seal pressure (Ref. Figure 203). When proper sealing is obtained and the release handle is fully against the closure stops, install the locking clips on the turnbuckle. The door must release and be opened with the application of 15 ± 5 pounds of pull.

A27

52-20-00

Page 201 Feb 1/10

SUPER KING AIR B300/B330C MAINTENANCE MANUAL

A

A OUTBOARD

SCREW

A

CONNECTOR

WASHER

VIEW

A-A

NUT

DETAIL

A

FL52B 985658AA.AI

Emergency Exit Door Electrical Connector (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 201

Page 202 Feb 1/10

52-20-00

A27

SUPER KING AIR B300/B330C MAINTENANCE MANUAL

Emergency Exit Door Latching Adjustment Figure 202

A27

52-20-00

Page 203 Feb 1/10

SUPER KING AIR B300/B330C MAINTENANCE MANUAL

Emergency Exit Door Figure 203

Page 204 Feb 1/10

52-20-00

A27

SUPER KING AIR B300/B330C MAINTENANCE MANUAL

EMERGENCY EXIT DOOR INSPECTION Cracks can be formed by rough finishing (ridges) or a thin skin flexing situation, possibly caused by the use of cleanup grinders on the corner. Inspect for cracks in the curvature between the seal and the outer skin face near the corners (Ref. Figure 204, Sheet 1, Sheet 2, Sheet 3). Inspect three inches to either side of the corners at the curvature. A 5 to 10 power magnifier may be used to better check the area. The area should be smooth and exhibit no undercutting.

Emergency Exit Door Inspection Figure 204 (Sheet 1 of 3)

A27

52-20-00

Page 205 Feb 1/10

SUPER KING AIR B300/B330C MAINTENANCE MANUAL

Emergency Exit Door Inspection Figure 204 (Sheet 2 of 3)

Emergency Exit Door Inspection Figure 204 (Sheet 3 of 3)

Page 206 Feb 1/10

52-20-00

A27

Hawker Beechcraft

Corporation

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

PASSENGER/CREW DOOR WARNING The DOOR UNLOCKED

light

in the annunciator

DESCRIPTION AND OPERATION

panel remains

illuminated until the cabin door is closed and latched,

then the lower forward latch bolt compresses the spring tab that actuates the switch mounted on the cabin bulkhead behind the latch plate in the doorway. When the handle is rotated to the locked position, the latch arm actuates the switch mounted in the door

through

adjacent

the forward and aft hook

to the lock

sense

assembly.

With these switches

switch to bias the annunciator

panel

actuated, the circuit is grounded that current no longer flows fully engaged, depress the switch illuminates a light at the

transistor

so

to the DOOR UNLOCKED

check that the lock mechanism is

momentary switch

on

point

the inside of the door. This

engages the plunger of the lock assembly. The cabin door-closed-switch, cabin-doorand the hook-sense switch will not normally require adjustment except when a new switch is installed.

where the latch

locked switch,

~124

light. For a further visual adjacent to the transparent panel arm

52-70-00

1/08Page May

f

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PASSENGER/CREW DOOR WARNING

MAINTENANCE PRACTICES

CABIN-DOOR-UNLOCKED SWITCH ADJUSTMENT a.

Remove the

b.

Loosen the two

light c.

upholstery panel

attaching

at the lower forward corner of the

screws

and

goes out when the cabin door is

the switch in the

mounting

slots

so

that the DOOR UNLOCKED

closed, LATCHED and LOCKED.

to the lower forward corner of the

upholstery panel

Attach the

position

doorway.

doorway.

CABIN-DOOR-UNLOCKED SWITCH INSPECTION a.

Remove the

b.

Inspect the spring tab behind

c.

Make

d.

Install the

sure

upholstery panel

at the lower forward corner of the

the latch

cabin-door-unlocked switch

upholstery panel

plate in

the

doorway

doorway.

to make

sure

it is not cracked

or

broken.

adjustment.

at the lower forward corner of the

doorway.

CABIN-DOOR-LOCKED SWITCH ADJUSTMENT a.

Remove the

b.

Loosen the two

upholstery panel mou

nting

over

screws

the lock

assembly.

and

position the switch on the door lock arm so that the annunciator panel lig ht position with the door closed and latched, The bracket for the switch has mounting screw for modifying the position of the switch.

is out when the handle is in the locked an

c.

adjustment slot

at the inboard

With the door closed and latched when the door mechanism is locked and the

the DOOR UNLOCKED

light

in the annunciator

panel

plunger is in the down position, applied to the handle in the

must illuminate when force is

unlock direction. d.

Fasten the

upholstery panel

over

the lock

assembly.

HOOK-SENSE SWITCH ADJUSTMENT a.

Remove the forward

b.

Close, latch and lock the cabin door.

c.

Loosen the two

or

aft handrail

panel from

the cabin door.

attaching screws on the switch assembly plate and position the switch assembly light goes out when the cabin door is closed, LATCHED and LOCKED.

so

that the

DOOR UNLOCKED d.

Tighten

the two

e.

Open

f.

Attach the foMlard

attaching

screws on

the switch

assembly plate.

the cabin door and check that the DOOR UNLOCKED or

aft handrail

panel

light

illuminates.

to the cabin door.

52-70-00

Page

yaM102

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CARGO AND AIRSTAIR DOOR WARNING

(FM-1

AND

DESCRIPTION AND OPERATION

AFTER)

warning system for the cargo and airstair doors utilizes ten switches to indicate that all door handles and latches are safety positioned when the door is closed and latched (Ref. Figure 1). Two separate switch circuits are used to illuminate a CABIN DOOR warning light in the annunciator panel to indicate that the cargo and/or airstair doors are not properly secured. The one circuit is a ground-seeking circuit wired through the airstair doorsill switch, the cargo

The

switches, and the airstair door handle switch. This circuit holds a transistor in the off condition until the circuit is opened by a broken wire or actuated switch, then the transistor applies power to the warning lights in the annunciator panel. The other circuit includes the airstair doorsill switch; the cargo doorsill switch; the cargo door lower latch switch; and the cargo door and airstair door forward and aft camlock switches. This circuit applies aft and lower handle

power directly to the annunciator panel when the cargo and/or airstair doors are not closed and locked. The camlock latch switches utilized in this circuit are actuated by a cam attached to the shaft of the camlock latch that is rotated

consequently, these switches sense the rotating motion of the handle along the cable when the door is being locked. If the cable breaks during the locking cycle, these switches will still indicate an unlocked condition. In the event that any switch actuator or cam fails, the switch will return to the normally closed position to indicate an unlocked condition.

by

the cable and handle drums;

nz~

52-71-00

May 1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRSTAIR DOOR

DOORSILL SWITCH

jl

a

I´•iB

it

I

CARGO DOOR FORWARD LATCH SWITCH

CARGO DOOR UPPER HANDLE

SWITCH

~hW o

o\\i

B

\i\\n

ElrY~6\

AIRSTAIR DOOR LATCH

HANDLE

CARGO~P

SWITCH

AFT

LATCH

AIRSTAIR DOOR FORWARD LATCH SWITCH

SWITCH c’

SWITCH TEST RECEPTACLE

AIRSTAIRDOOR

AFT LATCH SWITCH

a

~J,,

i I

LOL?ER HANDLE SWITCH

CARGO DOOR DOORSILL SWITCH LOWER LATCH SWITCH 200107-18

Cargo

and Airstair Door Warning Switches (FM-1 and After)

Figure

Page

252-71-00

1

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CARGO AND AIRSTAIR DOOR WARNING

(FM-1

AND

MAINTENANCE PRACTICES

AFTER)

ADJUSTMENT OF CARGO AND AIRSTAIR DOOR WARNING SWITCHES A test

receptacle for functionally testing the ten switches used in the cabin door warning circuit is provided portion of the cargo door adjacent to the handle for the lower latch mechanism.

in the

lower forward

NOTE: With the airstair door open so that the doorsill switch is not actuated, check the test connector for 24 volts at pin "E" and ground at pin "N" with a voltmeter prior to adjusting any of the door switches.

AIRSTAIR DOORSILL SWITCH the cargo door directly above the airstair door where it when the airstair door is closed. step

This switch is mounted

support a.

b.

for the fixed

Turn ON the

on

battery

master switch and the circuit breaker for the

Unfasten and open the warning switch.

by

the forward

reading lights.

the lower latch handle of the cargo door to

cover over

be actuated

can

gain

access

to the test

receptacle

for the c.

Loosen the locknuts and of the test

tighten

receptacle

the other locknut

d.

Close and fasten the

e.

Turn OFF the

adjust

the switch in its mount until the voltmeter indicates

when the airstair door is closed, then rotate the

securing

cover over

battery

the switch in

adjustment

a

loss of

voltage

at

pin

"E"

nuts 1.5 turns farther and

place.

the lower latch handle.

master switch and

disengage

the circuit breaker for the

reading lights.

CARGO DOOR UPPER HANDLE SWITCH The upper handle switch is mounted upper handle (Ref. Figure 201).

on

the forward side of the

NOTE: The airstair door must be closed and latched

so

fully

open

safety

latch catch,

that its doorsill switch is actuated

immediately

above the

during the following

switch

adjustment. a.

b.

Turn ON the

battery

master switch and the circuit breaker for the

Unfasten and open the hinged access the switch for adjustment.

cover over

the handle

on

reading lights.

the upper aft

corner

of the cargo door to

gain

access to

c.

Unfasten and open the hinged access cover on the lower forward receptacle used for this adjustment procedure.

corner

of the cargo door to

gain

access

to the

test

d.

Move the handle switch latch

on

its slotted

mounting

bracket until the voltmeter indicates

when the catch of the handle

of the test

receptacle (Ref. Figure 201); tighten

the

safety latch rides on mounting screws locking the handle

Close and fasten the

hinged

f.

Turn OFF the

master switch and the circuit breaker for the

n24

lip

a

loss of

of the striker

switch in

ground at pin "M" plate for the safety

place.

door.

e.

battery

the

reading lights.

52-71-00

1/08

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

UPPER HANDLE I

(OPEN

SAFETY LATCH

i

SAFETY LATCH CATCH

MOUNTING BAR

SWITCH

POSITION)7r

Qso=

1

q´•30

ROLLER CATCH

IIYC~-l

i

P~

o. OF SAFETY

´•iii/

LATCH CATCH

t

i

UPPER HANDLE

ri SAFETY LATCH

i STRIKE PLATE DOOR

AFT

SAFETY LATCH CATCH

LATCH

Cargo

Door

Upper

"RoLLER CATCH

(CLOsED POSITION)

SWITCH

2W-107-20

Handle and Forward and Aft Latch Switches

Adjustment

Figure i01 CARGO DOOR LOWER HANDLE SWITCH The lower handle switch is mounted

on

the handle

support immediately aft of the handle.

NOTE: The airstair door must be closed and latched

so

that its doorsill switch is actuated

during the following

switch

adjustment. master switch and the circuit breaker for the

a.

Turn ON the

b.

Unfasten and open the hinged access used for this adjustment procedure.

c.

battery

cover over

reading lights.

the lower latch handle to

gain

access

to the test

receptacle

mounting bracket until the voltmeter indicates a loss of ground on pin "A" of the approaches the point where the pin on the handle just touches the hook prior locked position (Ref. Figure 202, View A); tighten the mounting screws locking the fully

Move the switch in its slotted to

the lower handle

receptacle engagement in the

test

switch in

as

place.

d.

Closeandfastenthe

hingeddoor.

e.

Turn OFF the

master switch and the circuit breaker for the

Page

yaM202

1/08

battery

52-71-00

reading lights.

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LOWER HANDLE

HOOK LOCKING PIN

SWITCH

HqOK

VIEW

A

ADJUST SWITCH TO ACTUATE WITH PIN AND HOOK POSITIONED THUS

Q;

i

LOWER HANDLE

HOOK LOCKING PIN

CLOSED POSITION

VIEWB Cargo

Door Lower Handle and Latch Switches

Figure

Adjustments

202

CARGO DOOR FORWARD AND AFT LA TCH SWITCHES A switch is mounted

rotates, its

on a

respective

bracket

adjacent to the upper camlock latch on each side of the cargo door. As each latch by a cam attached to the end of the camlock shaft opposite the latch face.

switch is actuated

NOTE: The airstair door must be closed and latched switch

so

that the doorsill switch is actuated

a.

Turn ON the

b.

Unfasten and open the hinged door over the lower latch handle of the cargo door to receptacle used for this adjustment procedure.

c.

Unfasten and open the

d.

Remove

battery

upholstery

camlock latches e.

during

the

following

adjustment.

on

master switch and the circuit breaker for the

door

over

the door handle

as necessary to the cargo door.

gain

access

hinged

on

reading lights.

the upper aft

to the switches mounted

corner

gain

access

to the test

of the cargo door.

adjacent to the

upper forward and aft

Move each switch

on its slotted mounting bracket until the voltmeter indicates 24 volts on pin "K" (for the forward switch) and pin "D" (for the aft latch switch) when the safety latch mounting bar is .50 f .30 inch from the striker plate of the safety latch catch as the handle approaches the closed position (Ref. Figure 201). Tighten the mounting screws securing the switch in place.

latch

f.

A24

Reinstall all covers, the

hinged

door and

upholstery panels

that

were

removed for this

adjustment.

52-71-00

Page

yaM302

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

g.

Turn OFF the

battery

master switch and the circuit breaker for the

reading light.

CARGO DOOR LOWER LA TCH SWITCH A switch is mounted

rotates, its

bracket

on a

respective

adjacent to the lower camlock latch on each side of the airstair door. As by a cam attached to the end of the camlock shaft opposite the

switch is actuated

NOTE: The airstair door must be closed and latched

so

that the doorsill switch is actuated

during

the

each latch

latch face.

following

adjustments. a.

b.

Turn ON the

battery

master switch and the circuit breaker for the

Unfasten and open the hinged access receptacle for the warning switch.

cover over

reading lights.

the lower latch handle of the cargo door to

gain

access

to the

test

c.

Remove

upholstery from

the airstair door

as

necessary to

gain

access

to the switch

adjacent

to the pressure

lock. d.

Turn ON the

e.

While

battery

master switch and the circuit breaker for the

reading lights.

position, move the switch in its slotted mounting holes pin "L" of the test receptacle when the pressure lock plunger rides in the keyway at a point .04 inch or less from where the plunger drops into the keyhole (Ref. Figure 203, View A). Tighten the mounting screws securing the switch in place on its mounting bracket. rotating

the airstair door handle toward the locked

until the voltmeter indicates the loss of

f.

Reinstall

g.

Turn OFF the

upholstery

and close and

battery

ground

secure

the

at

hinged

access cover.

master switch and the circuit breaker for the

reading lights.

ACTUATING ARM

KN HOLE-(I RII~-KEYWAY MAX

nEwA PRESSURE LOCK PLUNGER

o

d~0

C

i~KEYWAY .W MAX .01 MIN.

ACTUATING

vww

B

KM

~oo-lat´•n

Airstair Door Handle and Forward and Aft Latch Switches

Figure

Page

yaM402

1/08

52-71-00

Adjustment

203

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AIRSTAIR DOOR FORWARD AND AFT LATCH SWITCHES nted

A switch is

mou

rotates, its

respective

bracket

on a

adjacent to the lower camlock latch on each side of the airstair door. As by a cam attached to the end of the camlock shaft opposite the

switch is actuated

NOTE: The airstair door must be closed and latched

so

that the doorsill switch is actuated

during

the

each latch latch face.

following

adjustments. master switch and the circuit breaker for the

a.

Turn ON the

b.

Unfasten and open the hinged access test receptacle for the warning switch.

c.

Remove

battery

cover over

reading lights.

the lower latch handle of the cargo door to

upholstery from the airstair door as necessary to gain access to adjacent to the lower forward and aft camlock latches.

the pressure lock

gain

access

plunger

to the

and to the

switches mounted

rotating the handle of the airstair door toward the locked position, move each latch switch in its slotted mounting bracket until the voltmeter indicates 24 volts at pin "H" (for the forward latch switch) and pin "J" (for the aft latch switch) of the test receptacle when the pressure lock plunger rides in the keyway at a point .01 to .40 inch from where the plunger drops in the keyhole (Ref. Figure 203, View B). Tighten the mounting bracket.

d.

While

e.

Close and

f.

Turn OFF the

secure

the

battery

hinged

access cover

and reinstall

upholstery.

master switch and the circuit breaker for the

reading lights.

CARGO DOORSILL SWITCH

latching mechanism structure of the cargo door directly under the airstair door where it doorsill when the cargo door is closed. Both the cargo and airstair doors must be locked and latched and all of the other warning switches must be properly adjusted before the cargo doorsill switch is adjusted.

This switch is attached to can

be actuated

a.

Remove the lower

b.

Turn ON the

c.

by the

upholstery panel

battery

from the cargo door to

Loosen the locknuts and

Reinstall the lower

e.

Turn OFF the

access

master switch and the circuit breaker for the

adjust

upholstery panel

battery

to the switch.

reading lights.

the switch in its mounts until the CABIN DOOR

goes out when the cargo door is closed and

d.

gain

on

warning light

in the annunciator

latched, then tighten the locknut securing the switch in place.

the cargo door.

master switch and the circuit breaker for the

reading light.

CABIN/CARGO DOOR ANNUNCIA TOR CIRCUITRY CHECK following inspection and adjusted:

The

a.

b.

nn,

Make

sure

test should be

that the cabin door is closed and latched

Lift the door

2.

Check that the orange index marks sure

after any of the door latches

by

the

step and check the position of the safety

i.

Make

performed

on

by

arm

the

switches

are

replaced

or

following: and pressure lock

each of the six rotary

that the cargo door is closed and latched

or

cam

locks

align

plunger. within the indicator windows.

following:

52-71-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

1.

Observe

2.

Check that the orange index marks

3.

Observe

through

Observe

through the window in the aft stripe on the carrier rod.

4.

through

the

hinged

the handle

access cover

on

window that the upper handle is in the latched

each of the four rotary

access cover

cam

locks

position.

align within the indicator windows.

window that the lower latch handle is in the latched

lower

corner

position.

of the door that the orange colored indicator

aligns

with

the orange NOTE: The

untapered shoulder that the

of the

latching pins

must extend

past each attachment lug.

switch is OFF.

c.

Make

d.

Check that with the cargo door closed and latched and the cabin door closed but not latched, the cabin door annunciator light illuminates.

e.

Open

f.

Turn the battery switch ON and check that the cabin door annunciator

light

g.

Close and latch the cabin door. Check that the cabin door annunciator

extinguishes.

Page

sure

battery

the cabin door and check that the cabin door annunciator

52-71-00

light extinguishes. illuminates.

nn4

CHAPTER

FUSELAGE

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 53 - FUSELAGE TABLE OF CONTENTS SUBJECT

PAGE 53-00-00

Fuselage - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Fuselage Access Openings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Fuselage - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Aft Fuselage Moisture Drainage System Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 53-10-00 Main Frame - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Recommended Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Fuselage Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Recurring Stringer Inspection (FL-1 thru FL-103, FM-1 thru FM-8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Recurring Forward Side of Aft Pressure Bulkhead Inspection (FL-1 thru FL-110, FM-1 thru FM-8) . . . .204 Fuselage Stringer Reinforcement/Repair (FL-1 thru FL-103, FM-1 thru FM-8) . . . . . . . . . . . . . . . . . . . . . . .205 External Doublers (FL-1 thru FL-103, FM-1 thru FM-8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Internal Reinforcement Kit (FL-1 thru FL-103, FM-1 thru FM-8). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 External Doubler Removal for Installation of Internal Stringer Reinforcement Kit (FL-1 thru FL-103, FM-1 thru FM-8) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 53-11-00 Cabin and Cockpit Vibration Absorbtion - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Dynamic Vibration Absorbers (FL-475 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Dynamic Vibration Absorber Tuning Frequency (FL-475 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) . . . . . . . . . . . . . . . .2 Dynamic Vibration Absorber Tuning Frequency (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Tuned Vibration Absorbers (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . .3 Skin Damping Panels (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). . . . . . .5 Skin Damping Panel, Damage Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Main Landing Gear, Nose Wheel Well, Avionic Compartment and Main Spar Cover, Skin Damping Panels . .7 Main Landing Gear, Nose Wheel Well, Sound Deadener Coating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 Cabin and Cockpit Vibration Absorption - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Dynamic Vibration Absorber Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Dynamic Vibration Absorber Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Dynamic Vibration Absorber Tuning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Tuned Vibration Absorber Mount Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .205 Tuned Vibration Absorber Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .205 Tuned Vibration Absorber Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .206 Skin Damping Panel Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . .206

A27

53-CONTENTS

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 53 - FUSELAGE TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE

Skin Damping Panel Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 206 Main Landing Gear, Nose Wheel Well Sound Deadening Coating Installation . . . . . . . . . . . . . . . . . . . . . . . 207 53-30-00 Plates and Skin - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 53-40-00 Attach Fittings - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Cockpit Seat Tracks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Cabin Seat Tracks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Cabin Rail System (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . 1 Attach Fittings - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cockpit Seat Track Wear Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cockpit Seat Lockpin Wear Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cockpit Seat Support Channel Wear Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Corrosion on the Cockpit Seat Track . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cabin Seat Track Wear Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Corrosion on the Cabin Seat Track . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Cabin Rail and Aft Cabin Rail System Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 204 Cabin Rail and Aft Cabin Rail System Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 204

Page 2 Feb 1/10

53-CONTENTS

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

53-LOEP

1

Feb 1/10

53-CONTENTS

1 and 2

Feb 1/10

53-00-00

1 thru 5 201 and 202

May 1/08 May 1/08

53-10-00

201 thru 216

May 1/07

53-11-00

1 thru 9 201 thru 211

Feb 1/10 Feb 1/10

53-30-00

1 and 2

May 1/08

53-40-00

1 and 2 201 thru 206

Feb 1/10 Feb 1/10

A27

53-LOEP

Page 1 Feb 1/10

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUSELAGE

DESCRIPTION AND OPERATION

This

Chapter describes the fuselage, which is comprised of compartments for the crew, passengers, cargo and equipment. Included is the inspection and repair of the fuselage main frame. Also provided is the wear limit criteria for the cockpit seat tracks, cockpit seat lock pins and cockpit seat support channels. The

fuselage

is of

a

semimonocoque

construction that consists of frames,

aluminum skins. The main bulkheads

stringers, bulkheads, keels enclosed with

the forward pressure bulkhead (FS 84.00) and the aft pressure bulkhead between the forward and aft pressure bulkheads forms the pressure vessel. To minimize are

(FS 381.75). The fuselage loss of pressurization, all skin, doors, bundles and control cables the cabin section is

are

designed

windows and structure

routed

as

the

joints

are

sealed. In

the pressure vessel with seals and

through baggage compartment.

addition, the plumbing, wire

plug

connectors. The aft end of

FUSELA GE ACCESS OPENINGS A

swing-down entrance door is located on the aft left side of the cabin at FS 325.87. The entrance door incorporates steps for boarding the airplane. Emergency exit doors are located on the left and right sides of the cabin at FS 191.00 to expedite egress from the airplane during emergency evacuation. For information concerning the doors, refer to Chapter 52. Windows are incorporated on both sides of the fuselage, including a window in each of the emergency exit doors. For information concerning the windows, refer to Chapter 56.

Fuselage radome

access

on

the

moisture. Access refer to

nz~

Figures

openings provide access to components within the fuselage. Avionic compartment doors and the of the airplane allow access to avionic equipment and incorporate seals to prevent entry of to the rudder control horn and stops is by removal of the tailcone. For additional access openings,

nose

1 and 2.

53-00-00

May

1/08Page

1

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i.

RADAR

GEAR

1.

NOSE

3.

AIR

4.

AVIONICS

5.

RUDDER

6.

ELEVATOR

POIN7

CONDITIONER

8.

RUDDER

CONTROL

9.

NOSE

ACTU.r?TO~.

LANDING

GEAR

CONTROL AFT

SElsVICh

CA3IES

FUSELAGE

OXYGEN

4.

AIR

5.

HORIZONTAL

6.

ELEVATOR

ELEVATOR

19.

AIR

AND

Rn13S.

COMPASS

(BELOW AND

SERVICE

PEDESTAL) SAFETY

V~LVES.

OXYGEN

BOTTLE.

VALVE.

TAB

DELZE

’RESSURE

SWITCH.

CABLES.

ATTACHMENT.

CRUER

FLUX

TAIL

ATTACHMENT,

PULLEYS,

ACIU~IORS

ZONDITICNER

SWITCH,

-ONDENSER.

STAG~LILER

TA3

~ESET

DOOR.

OUIFLOW

STABILIZER

PUSl-

CONDITION~R

VALVE.

PULLEYS

GAGE

CONDITIONER

HORIZONTAL

DUAL

kN3

STOPS.

A-R

AYCESS

A~CESS.

FILLER

18.

DOORS,

ACILATC>

3.

20.

RUDDER

GEAR

REFRIGERATICI\I

i~.

BLOWER.

BELLSRANK.

TAe

NOSE

CONDENSER

BELLCRANK.

RUDDER

O.

GLPOE~CCPE.

ANTEUNA,

STOPS.

AND

AND

VALVES

PLUMBING AND

FITTINGS

COMPENSATORS

3eo-ola-olo

c

ORIGINAL As

Received´•By AfP

Fuselage

Page

2530000

Access

Openings (FL-1 Figure 1 (Sheet 1 of 2)

and

After)

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

~0000

r

(j

588

30TT3K

3F

FUSELAGE

-i 4

9

2

i 1

i

i

1

8

10

h\

*rr 9

ii

TOP OF USELAGE

5-

U33EK H~RIIZSNTAL ST/’j:I: _IZER

4

~r,

C

Oo~S,

O O iC) ~i

i 350-013-009

8

5

C

13

ORIGINAL As Received

By

ATP

Fuselage

Access

Figure

A24

Openings (FL-1 1 (Sheet 2 of 2)

and

After)

53-00-00

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I.

RADAR

~iIDESCOPE.

ANTENNA.

AT-ACt

GEAR

’CINT.

2.

NOSE

3.

AI~

a.

AVIONICS

5.

RJDDERBELLCRk~K.

6.

ELEVATOR

COMPAR-YE~1

BEL_CRANK.

RUDDER

TAB

8.

RUDDER

CONT~OL

9.

NOSE

ACTUAICR

LANDTN,

II.

NOSE

CONTROL AFT

3. 14.

FUSELAGE

OXYGEN AIR

FILLER

5.

HORIZONTAL

6.

ELEVATOR

HORIZONTAL

18.

ELEVATOR

~O.

AIR DUAL

OUTFLOW

SAFETY

VALVES.

OXYGEN

BOTTLE.

VALVE.

PRESSURE

SWITCH.

CAB_ES

STOPS.

AND

FLUX

TAB

UEZC~

ATTAC~MENT.

TAB

CRYER

TAIL

ATTACHMENT.

PULLEYS,

STABILIZER

COMPASS

?ECESTA_)

~ONDENSER.

R03S.

CGNDITI3NER

AND

SERVICE

AND

STABIILER

PUSH

17.

9.

~AGE

CONDITIONE~

(BELOW

PULLEYS

ACCESS.

SWITCH.

DOOR.

ACCESS

kN7

4E’EI

VALVE.

SERVICE

CA3LES

AIR

30CRS.

ACTUATOR

GEAR

STOPS.

RUDDER

~ORN.

G~AR

REFRIGERATTON O.

GLOWER.

CONDITIO~ER

AND

VALVES

PLUMBING AND

FITTZ~GS.

COMPENSA-ORS.

360-013-010

ORIGINAL As Received

By

ATP

Fuselage

Access

Figure

Page

yaM4

1/08

53-00-00

Openings (FM-1 2 (Sheet 1 of 2)

and

After)

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

34

.n/ ji~j

lo o o o i

o’J_I

a

588

GOiTOi~

9

4

OF

FUSELAGE

1 i

8

J~.--

e

01~>1

’3

OP

OF ;USELAGE

j

U‘FE I3EIZONTAL jTA ZER n

a

19

C

O

00 C~

C’iC>4ii i

g

Y,

8

ORIGINAL By

As Received ATP

350-013-019

13

5

Fuselage

Access

Figure

A24

Openings (FM-1 2 (Sheet 2 of 2)

and

After)

53-00-00

5

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUSELAGE

MAINTENANCE PRACTICES

AFT FUSELAGE I1IIOISTURE DRAINAGE SYSTEIM INSPECTION a.

Visually

b.

Open

c.

ensure

the aft

that all drain holes in the ventral fin

fuselage

access

clear of debris.

door.

Ensure that the O.1g-inch-diameter drain holes in the four clear of debris. One

of the centerline d.

are

At the

stringer is located (Ref. Figure 201).

airplane lower centerline,

to the

right

stringers just aft of the rear pressure bulkhead are of the centerline and the other three stringers are to the left

locate the channel that

parallels the

access

door.

Visually inspect the

drain hole

at the lower forward end of the channel. Ensure that it is 0.50 inch in diameter and is clear of debris. Ensure the

"KEEP DRAIN HOLE OPEN" decal is located e.

n24

Close the aft

fuselage

access

on

the channel

(Ref. Figure 201).

door.

53-00-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A

,li?´•

Ci;

Ei7 STRINGERS i~IT HOLES IN

GASE11

~ROSS-FLOW DRAIN HOLE

i

E,LI"iICAL vR%Ii~ HOLE

C

7*

I7PIA,

Ajj;;/jd

Ir!

lic~

BRIIGIIRilAL. i9s Rece[vscl By

i

A1’P

i,

DOOR

(SHOWN

RICHI

OPEN)

STRINGER ~DLE

LOC~ING DOWN ON AFT PRESSUFi_ 3ULKHEAD AREA

VIEW

DETAIL

Aft

Page

Fuselage

53100100

A

C95FL5380

26

Drainage System Inspection Figure 201

Moisture

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

MAIN FRAME The information structural

inspection schedule will form the basis for ensuring structural requested that Hawker Beechcraft Corporation be notified of any indications of I the total airplane time be included when such indications occurred. Please forward this Beechcraft Corporation Technical Support, Wichita, Kansas 67201.

compiled fuselage. fatigue and that

integrity of

the

information to Hawker

from the results of the

It is

RECOMMENDED MA TERIALS as meeting federal, military or supplier specifications are provided specifically recommended by Hawker Beechcraft Corporation. The products included in this chart have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance to the applicable specification. Generic or locally manufactured products which conform to the requirements of the specifications listed may be used even though not included in Chart 201. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to use of the product. This can be done by contacting the supplier of the product to be used.

The recommended materials listed in Chart 202

for reference

only

and

are

not

Chart 201 Recommended Materials NAME

Methyl Propyl

1.

Solvent

2.

Solvent

A-A-59107

Toluol

3.

Chemical

MIL-DTL-81706 per MILDTL-5541

Alodine 1200

Conversion

SUPPLIER

PRODUCT

SPECIFICATION

Ketone

(Toluene)

or

1201

Obtained

Locally.

Obtained

Locally.

Henkel Corporation Aerospace- Surface Treatments

Coating

32100

Stephenson Highway Heights,

Madison

M148071 4.

Sealer

SAE-AMS-S-8802

PRC-Desoto International

PR-1 440

ne

ii

5454 San Fernando Road

Glendale, CA 91209 5.

EpoxyPrimer

MIL-PRF-23377

AKZO Nobel

10P8-11

(for Type I,

Class

C)

Coating

Aerospace

Inc.

East Water Street

Waukegan, 6.

WashPrimer

MIL-PRF-8514

M3225/M3226

IL 60085

Sterling Lacquer

MFG. CO.

Inc. 3150 Brannon Ave

St. Louis, MO 63139

A22

53-1 0-00

Page

yaM102

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUSELAGE INSPECTION of the fuselage as indicated in Chart 202 or the applicable recurring stringer inspection, to integrity of the component parts. The inspection schedule that follows has been devised to ensure the total safety of the pressure vessel. These inspections were derived from the results of extensive testing. Should damage be detected in any structural component during this inspection, all adjacent structures must be carefully investigated for indications of related damage. All damage to non-pressurized areas must be repaired or replaced in compliance with the standard repair practices defined in AC 43.13-1A AIRCRAFT INSPECTION AND REPAIR MAN UAL, or AC 43.1 3-2 AIRCRAFT ALTERATIONS MANUAL. Damage to pressurized structure requires reference to the Structural Inspection and Repair Manual (SIRM) when applicable. Additional area repairs may require documentation from the Repair Design Office (RDO) or other approved sources.

I Inspect priority ensure

areas

the structural

Should there be

a

visual

inspection

NOTE: Do not

efficiency of the pressure vessel, these additional inspections should plates, upholstery panels, floorboards and insulation as necessary to permit a careful skin and underlying structure in the areas noted in the following procedure:

noticeable decrease in the

be made. Remove

access

of the

permanently

remove

any of the

upholstery support strips

riveted to the bulkheads

or

basic airframe

structure. a.

Carefully inspect the floor for cracks, loose rivets in the

damage

or

area near

line of the pressure vessel at all points of juncture with the adjacent support structure fasteners. Check all bulkhead flanges and web lightening holes for cracks or other

points of

intersection with the floor line of the

fuselage. Inspect for

cracks and loose

rivets in splice plates, support doublers, stringers, clips and angles adjacent to, or tying into, the floor and its substructure throughout the length of the pressure vessel. Check the floor rail support structure, the floor

support channels and the stringer ties b.

Inspect the

rivet

to the floorboards for

pattern for indications of sheared

at FS 84. Check for cracks in the skin bulkhead web and stiffener

or

for cracks

flanges

c.

Check for cracks

d.

Inspect the fuselage for damage and

or

supporting or

damage

loose rivets

or

stretched rivets.

each side of the forward pressure bulkhead the attaching rivets. Inspect the

emanating from structural damage.

structure

other

on

and sheared, loose

or evidence of other damage to the keel web, stiffener flanges and the angles enclosing and supporting the evaporator pressure box under the floor on the right side of the avionics compartment immediately in front of the forward pressure bulkhead. Check for loose rivets in the pressure box skin and in the supporting structure adjacent to the pressure box enclosure.

points of juncture with the instrument panel support brackets adjacent to the instrument panel for cracks and of bulkheads and frames for damage or loose rivets near the flanges

loose rivets at

located between FS 100 and FS 107. Check the intercostal

sheared

or

stretched rivets.

Inspect

the

the instrument panel substructure. e.

Inspect

for loose rivets and cracks

under the crew

f.

finger

doublers and

Inspect

damage

at the upper and lower

gussets

for loose rivets and cracks

loose, sheared structure structural

in the bulkheads and

corners

longerons

of the storm windows

on

that intersect each side of the

or

finger

or

other structural

doublers and

gussets

damage

in the bulkheads,

at the upper and lower

corners

clips, and longerons

that

of each windshield. Check for

points and doublers. Check for cracks in the skin or supporting Inspect the bulkhead web and stiffener flanges for cracks or other

stretched rivets at attachment

emanating from

the

attaching

rivets.

damage.

The

inspection in Step f. requires removal of windshields interior upholstery and instrument panel glareshield to access structure for inspection. Removal of the windshield is not required.

Page

yaM202

other structural

compartment.

intersect under the

NOTE:

or

1107

53-10-00

oz

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Inspect the escape hatch, the blocks supporting it, the fuselage frame encompassing it and the cap strips at the of the hatch opening for cracks or other indications of structural damage. Check bulkheads, longerons, doublers, clips, straps, angles and other structural members adjacent to the escape hatch for damage and loose

g.

corner

rivets h.

fuselage and the nearby supporting members for evidence of and the stringer adjacent to it immediately above the doorway plate damage. for cracks or other signs of damage. Check all door hooks, latch bolts and their striker plates in the doorframe for indications of damage. Inspect the bulkhead, bulkhead flanges, support doublers, stringers, clips and angles adjacent to the doorframe for cracked or loose rivets. Inspect the cabin door, the doorframe

in the

Check the hook catch

structural

Inspect each side of the rear pressure bulkhead for evidence of structural damage. Inspect the webs and their supporting stiffeners, clips, angles and plates for cracks and loose rivets. Check the bulkhead flanges and the stringers at the cutouts in the bulkhead flanges for cracks and loose rivets. Check the mounting brackets for the oxygen bottle and the box for the outflow and safety valves for cracks and loose rivets at their points of

i.

attachment to the pressure bulkhead. The

NOTE:

or

stringers

are

numbered

consecutively down each side top of the fuselage.

of the

fuselage from

the first

stringer

to the

right

left of the centerline at the

Chart 202

Priority

Inspection Guide For Fuselage Stringers (FL-1 thru FL-110; FM-1 thru FM-8)

Area

PRIORITY AREA OF INSPECTION

(FL-1 thru FL-103; FM-1 thru FM-8) stringers 5 thru 11 (both left and right)

Inspect for

FUSELAGE INSPECTION cracks

on

non-reworked

pressure bulkhead at the to the stringers with 6 rivets. of the

rear

on

point where the zee stiffeners

the aft side

are

if

on

(FL-1 thru FL-103; FM-1 thru FM-8) Inspect for stringers on the aft side of the rear pressure bulkhead (both left and right) have internal reinforcement kits

non-reworked

stringers 8, 9,

and 10

INITIAL

SUBSEQUENT

INSPECTION

INSPECTION

2,500

500 CYCLES

CYCLES

I I

attached

FUSELAGE INSPECTION cracks

5 thru 11

2,500

500 CYCLES

CYCLES

installed. FUSELAGE INSPECTION

(FL-1

thru FL-103; FM-1 thru

FM-8, with

external

CYCLES

(FL-1 thru FL-103; FM-1 thru FM-8, with internal Inspect for cracks above and below the stringer cutouts in the bend of the rear pressure bulkhead flange.

CYCLES

doublers)

Inspect

radius of the

rear

pressure bulkhead

stringer

FUSELAGE INSPECTION

FUSELAGE INSPECTION below the

stringer

500 CYCLES

(FL-104 thru

FL-1

10) Inspect for cracks

cutouts in the bend radius of the

rear

above and

pressure bulkhead

2,500

10,000

2,500 CYCLES

2,500 CYCLES

CYCLES

flange.

n~z

I

flange.

doublers) radius

2,500

cutouts in the bend

for cracks above and below the

53-1 0-00

1107

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RECURRING STRINGER INSPECTION

(FL-1

THRU

FL-103, FM-1 THRU FM-8)

If the airplane has accumulated 2,500 cycles, inspect inspection, cracked stringers are to be repaired. All cracks

to be

are

repaired

for cracked

stringers.

If cracks

are

discovered

during

the

in accordance with FUSELAGE STRINGER REINFORREEMENIRREPIR in this

chapter.

I

NOTE: If stringers 8, 9, and 10 (left or right) are reworked by installing external doublers, the 500 inspection remains in effect for non-reworked stringers on that side.

cycles recurring

airplanes with stringers without external doublers or internal reinforcement kits must have the originally installed stringers inspected in the area aft of the rear pressure bulkhead at 2,500 cycles (initial) and 500 cycles (recurring).

All

I Inspect stringers are

through No. 11 (both left and right) (Ref. Figures 206, 207 and 208) where the zee stiffeners stringers. The zee stiffeners are attached to each stringer with six rivets. The six rivets attach of the zee stiffener (next to the inboard side of the fuselage skin) to the flat horizontal web of the

No. 5

attached to the

the outboard end

stringer. NOTE: The six rivets To

are

inspect the stringers,

vertically through

the

stringer

web and

zee

stiffener.

stringers from below. Look up at the flat, narrow web of the stringer which is located fuselage skin and the rounded J-section of the stringer. Check the six rivets that are stringer immediately aft of the rear pressure bulkhead. Look for cracks in the stringer,

view the

between the inside of the

installed in the web of the

emanating

installed

from any of the six rivets.

Ensure that the rivets

are

rounded J-section of the

positioned correctly

stringer.

stringer: the rivets should be pulled or stretched.

in the web of the

The rivet shanks should not

not be installed

stringer must be inspected at 500 cycle intervals unless internal reinforcement kits are stringers 8, 9, and 10 on both sides of the airplane. When installed, inspection intervals are extended cycles for non-reworked stringers.

the

Each non-reworked

installed

on

to

inspection schedule on airplanes with either external stringers 5 through 11 on both sides as outlined below.

Resume the current Maintenance Manual reinforcements kits installed

on

all

RECURRING FORWARD SIDE OF AFT PRESSURE BULKHEAD INSPECTION

THRU

If external doublers

Remove the a.

rear

b.

rear

or

internal reinforcements kits have been installed,

inspect

the forward side of

shown

Inspect

reworked

as necessary to permit a careful visual noted in the following procedure:

upholstery panels and insulation areas

rear

FL-110, FM-1

stringers

on

the forward

pressure bulkhead between both left and

inspection of the forward

right stringers

No. 5

through

side of

No. 11

(Ref. Figure 209).

Remove sealer that surrounds

Page

THRU

internal

or

pressure bulkhead.

pressure bulkhead in the

Inspect as

(FL-1

doublers

1,000

FM-8)

side of the

I

on

stringers which pass through the stringer cutouts in the rear pressure bulkhead. stringers cutouts in the bend rad i us of the rear pressure bulkhead fla nge.

for cracks above and below the

53-~ 0-00

~22

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

NOTE:

It is

notify Hawker Beechcraft Corporation of any indications of cracks in the pressure bulkhead, the total time on the airplane and the total number of landings when such indications were noted. Forward this information to the Technical Support

requested that

forward side of the

customers

rear

the airplane Department, Hawker Beechcraft Corporation, Wichita, Kansas 67201, FAX No. (316)-676-8027.

on

c.

Apply sealer (4, Chart 201)

d.

Install insulation and

around

stringers

which pass

through stringer

This

procedure is to extend the life of the structure in the area of the longitudinal stringers intersect the zee channel bulkhead stiffeners. are

discovered

during the inspection,

two different

repairs

rear

on

the

same

FI~-8)

side of the airplane.

pressure bulkhead at the

point

where the

procedures are available to reinforce the stringers. Install each stringer that shows any indication of cracking.

external doubler

or an

internal reinforcement kit

EXTERNAL DOUBLERS

(FL-I

THRU FL-103, PM-1 THRU

an

pressure bulkhead.

THRU FL-103, FM-? THRU

(FL-?

CAUTION: Do not mix internal reinforcement kits and external doubler

If cracks

rear

upholstery panels.

FUSELAGE STRINGER REINFORCEMENTIREPAIR

either

cutouts in the

on

FM-8)

Figures 206, 207 and 208 inspect both left and right stringers No. 5 through No. 11 per Chart 202, along I length immediately aft of the rear pressure bulkhead. If any of these stringers indicate signs of the cracked stringers are to be made. This repair procedure is accomplished by installing an to cracking, repairs external doubler to the affected stringer on the rear pressure bulkhead at the point where the stringers intersect the zee channel bulkhead stiffeners. The following steps are for the repair of stringers 5 through 11 as shown (Ref. Figures 201 thru 205). Referring

an area

a.

b.

to

six rivets in

Remove the rivets from the

stringer and the pressure bulkhead requirements (Ref. Figures 201 thru 205).

in the

area

of the

repair for the

individual

Fabricate all doublers from 2024T3 alclad material. The gage and width of the doublers and shims may be found Figures 201 thru 205. The length of a given doubler or shim is determined by picking up the required number

in

of rivets at the

existing locations. Keep

in mind that

a

0.31-inch

edge

distance

on

I

the end rivets must be

maintained. Shim thicknesses may be varied to obtain the best fit. c.

Place the doubler and shim in

position

on

the skin and drill the rivet holes

as

required

for the individual

string

repair. d.

After the

drilling operation

has been

NOTE: Before installation, smooth all

completed,

remove

all debris and burrs.

sharp edges and apply a

coat of epoxy

primer (5, Chart 201)

to the shims and

I

doublers. e.

If the

stringer is not cracked all the Coating (3, Chart 201)

Conversion

way across, stop drill the crack with a number 40 drill bit. Apply chemical to the crack and stop drill hole. Prime the crack with epoxy primer (5:

.)102trahC

f.

Apply

a

thin coat of sealer

(4,

Chart

201)

NOTE: If any of the sealed interior surfaces

g.

Rivet the doublers and shims in remove

~a?

the

excess

place

sealer with solvent

to all

mating surfaces

of the doublers and shims.

pull loose, during the drilling operation, reseal with sealer (4,

on

(2

the exterior side of the skin or

2, Chart

las

shown in

Figures

Chart

201 thru

205),

201). and

201).

53-~ 0-00

Page

yaM502

1107

I

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

INTERNAL REINFORCEMENT KIT

NOTE:

If

(FL-1

THRU

external doubler has been installed

an

FL-103, FM-1 THRU FM-8)

on a

stringer that

is to be reinforced with

an

internal reinforcement

kit, refer to EXTERNAL DOUBLER REMOVAL FOR INSTALLATION OF INTERNAL STRINGER REINFORCEMENT KIT for instructions

on

removing

the external doublers.

CAUTION: Do not mix internal reinforcement kits and external doubler

I

Inspect

repairs

on

the

same

side of the

airplane.

right stringers No. 5 through No. 11 per Chart 202 along an area six rivets in length immediately pressure bulkhead as shown in Figures 206, 207 and 208. If any of these stringers indicate signs of repairs to the cracked stringers are to be made. This repair procedure is accomplished by installing an

both left and

aft of the

cracking,

rear

stringer on the rear pressure bulkhead at the point where the stringers channel bulkhead stiffeners. Reference Charts 203 and 204, to determine the appropriate internal

internal reinforcement kit to the affected

I

intersect the

zee

reinforcement kit for are

stringer repairs.

The parts and instructions

required

to install the internal

contained within the internal reinforcement kits listed under "MATERIAL"

on

the included

stringer reinforcement drawing.

EXTERNAL DOUBLER REMOVAL FOR INSTALLATION OF INTERNAL STRINGER REINFORCEMENT KIT

(FL-1

THRU FL-103, FM-1 THRU

If the external doublers doublers a.

b.

as

to be removed and

on

the exterior

Remove the aft cabin interior and sidewall rear

replaced

with internal

reinforcement

stringer

kits,

remove

the

follows:

Locate the external doublers

the

fuselage

panels

as

skin aft of the cabin.

required

pressure bulkhead where the external doublers

CAUTION: Use c.

are

FM-8)

a

drill

set to 0. 25 inch

stop

or

less when

are

to

removing

Remove the rivets that attach the doublers and shims to the

gain

access

to the

area on

the forward side of

attached.

the external doubler rivets.

fuselage skin,

rear

pressure bulkhead and

fuselage

stringers. d.

Remove the external doublers and shims from the surface of the

e.

Remove any loose

f.

Apply epoxy primer (5, primer to dry.

Chart

201)

g.

Use

small brush and

apply

sealer

NOTE:

a

paint, primer

Dip

each rivet in sealer

h.

Installthe rivets.

i.

Treat the bare

j.

Treat the

k.

Install the cabin interior

area on

area on

(4,

area

(4,

length Chart

Chart

201)

around the rivet holes.

to each hole.

prior to installing

components

201) before

that

were

with urethane

53-~ 0-00

new

rivets in the open rivet holes. Use P/N

is to be determined upon installation. installation.

and around each rivet head with epoxy

area

skin.

to each rivet hole and to the area around the rivet holes. Allow the epoxy

and around each rivet head with wash

Finish the modified exterior

Page

material from the

Internal reinforcement kits should be installed MS20470-B4 rivets. Rivet

I

sealing

or

fuselage

primer (6,

primer (5,

Chart

Chart

201)

201)

and allow time to

and allow time to

dry.

dry.

removed.

paint

to match the

airplane paint

scheme.

nzz

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 203 Internal Reinforcement Kits

(FL-1

thru

PART NUMBER 101-4064-1

Reinforcement Kit for

Reinforcement Kit for

101-4064-4

side

(left

Up

to 3

as

required.

#1 1

Up

to 4

as

required.

#10

Up

to 3

as

required.

(right

Up

to 2

as

required.

side

1 if

required.

1 if

required.

or

Stringer #5, #6,

#7

or

only) Stringer #8, #9,

or

only)

Reinforcement Kit for side

101-4064-5

side

Reinforcement Kit for

(left

#7

Stringer #5, #6,

only)

(right 101-4064-3

QUANTITY PER AIRPLANE

DESCRIPTION

side 101-4064-2

FL-103; PM-1 thru FM-8)

Stringer #8

or

#9

only)

Reinforcement Kit for

Stringer #11 (left

only) 101-4064-7

Reinforcement Kit for

Stringer

#10

(right

side

only)

Chart 204 Individual

Stringer Internal Reinforcement (FL-1 thru FL-103; PM-1 thru FM-8)

STRINGER NUMBER

nz?

KIT NUMBER

(LEFT SIDE)

Kits

KIT NUMBER

(RIGHT SIDE)

No. 5

101-4064-1

101-4064-2

No. 6

101-4064-1

101-4064-2

No. 7

101-4064-1

101-4064-2

No. 8

101-4064-3

101-4064-4

No. 9

101-4064-3

101-4064-4

No. 10

101-4064-3

101-4064-7

No. 11

101-4064-5

101-4064-2

53-~ 0-00

Page

yaM702

1107

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A

NOTE STRII\IGE~ 5 AI\ID RH IDE~I_Ca

6

LH

SHOWN.

NOTE IN DETAIL A SKIi~S HAVE BEEN DELETED IN ORDER -O DELINEATE TEE POSITION OF THF SIR ’GER ´•ND BULKHEAD. ,OUSLER AND SHIM IN VIEW A-A s-iol~ls PLACE ON SKIN.

A

1

NOTE SHORT

EDGE

PO~SIBLE,

3UT~ SHIMS AFT END OF

ADD

AGAINS1 FWD SKIN

DISTANCE Ii\l 51-11~1 DUE TO EXISTING h3iE.

FLA1

ADD 3 CR35~4-; RIVETS

AF PRESSURE ~ULKHEAD iS 1 .75

SHIM ALC

i ADD CR3jL42 RI~ETS

2

CR35~4-2RIVETS

rA

Ao:_1

J

INSIALL h cn´•sanJ

RIVET~

/I

0.85

ITYP!

t

I-~io

10U~LER AND INSTAI CR3c~42 RIVETS IN ~XISTIN; RIV~T 3CAIIONS

OIMDLE

T 7~00

(MAX.!

o c

L80

\I;

RI:jETS

SKIT\

DETAIL

c.

ALC FLAT

4

AUD

0.80

DIMPLE DOUBLER AND INSTALL G CR3524-2 RIVETS IN EXISTING LOCATIONS

DOUBLER

0.30

(IYP: SHEE~

F~24

~IVCTS

RIVETSAOD

RIV;T A~JACENI TO CRAC": INSTLI CR3524-3 RIVET

A

LOOKING INBO

LAP -rr

I

1-

I-´•-/III´•I-I´•´•

i" VIEW

A-A

DDU"L-R

Number S and 6 Left and Right Stringer Repair (FL-1 thru FL-103; FM-1 thru FM-8)

Figure

201

SHIM

C93FL53e

659

ORIGINAL As Received ATP

Page

53-~ 0-00

A22

By

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SHIM .050/2024

NOTE I-1-7----

j

C,~jl

-G

1B

A

F

la,

Y:E,IA-A

DOIIBLERi

EDGE

POSSIGIE.

L~I

DJ~iAI\ICE Ti\J SEIM DUE TO EXT~TING HOLE FLAT

F~D

.nFT

~KIN

ADD

PRESSURE

"LC

CR35;24-’

BULKHEAD.75 38 i i

~O

-O

~O

00

11 i II

R

II\ISIA_L

i

1O

~O

O

I~

ADD 7 CR35~4-2 RIVETS

O..-A’A_-l

_L\

rA

SHII~

3

FS ADD CR3524-~ RI~ETS

0.85

SI’IN

VIEWB-B

NOTE SHORT

(TYP)

~iC

NOTE DETAIL A SKINS HAVE 3EEN DELETED ORDER 10 DELINEATE THE FOS:I:TTON STRINGER AND BULKHEsC:. IN SHOI´•IS DOUBLER ~ND ’_~CE DN SKIN. I~ TN

BUTT SHI~S AFT END OF

73

VIEW OF DOUBLER DELETE3 TROM VIEW Or EXTER~L S~IIS. IN ORDER TO CLP.RIFY LAYOUOF FILLERS FOR STRINGE; RH I=_I\I-ICAL NO. 7. LH SHOWN.

Jh-";.,i RI~ETS

‘O

Q

i. ii

Cre

‘O

UIMPLE

COUBLER II\1S~TALL CP35; RI\JETS IN r~-STING RI~-I LOCATIONS

-ND´•:

3

I

CO

,i~ c

0.5d4

1--I

(IYP) ~c

iMAX.)

CR35~a-2 RIvEIS

0.80

ADD 3 CR3524-2

RIVETS

1.80

DIMPLE DOUBLER AND TNSTALI b RI~ETS IN EXISTLNG LOCATIONS

SKIN

-1

DETAIL

A

DOUBLER 17

.040/~034PLC FLAT

StlEE1

P.DD 7 CR352L-~ RIVETS

RI~_T ACJACENT TO Ci??’l‘K INSiALL 3 RIVET

LOOKING INBD

LAP

SHli-l

VIEW

ORIGINAL As Received By

A-A

DOufi

_R

C93FLE´•3e

’58

Number 7 Left and Right Stringer Repair (FL-1 thru FL-103; FM-1 thru FM-8)

Figure

202

ATP

A22

53-1 0-00

Page

yaM902

1/07

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE SHOWN

STRINGEi~ L RH IDEN ICAI

NOTE

I

IN DETAIL A ~KINS HAVE BEEN DELETEC ,ELIN_.TE THE POSITION IN ORDER Tn OF THE STRINGER AND BULKHEAD. VIEW A-A SHO~S DOUBLER AND SHIM IN PLACE ON S´•(Ii\l.

A

NOTE SHORT EDGE DIS;AI~CE IN SHI~ FOSSIeLi DUE TO EXISTING HOLE. EUTT SHIMS AFT END O; aDD

5

OR

AGAINST FWD SKI~

6

3

ADO ni-T PRESSURE @CILI*HEAD .75

FLAT SHIM .050/2024-73

RZVEIY AUU 7 3R35~4-2

,IVETS

~IVETS

A

~=II;

0-

j

O

j

i.OO

I I

INSTALL 8 CR35~i-3 RIVETS

i

II to Drni-´•L_ ocut~i,r; AND INSTA_L

,o.so

RIV_TS IN EXI~TZN, RIVE1 LOC~TION’

(IYP)

3. CO MAX.); AUD CR35

-DD

6

i?r

KI~EIS

0.60 1 .80

RIvrTS

SKIN

DIMPLE D~UGLER AND INSTALL 6 CR3524-2 R:I:vETS IN EXISTING LOCATIONS

FWD

DETAIL LOM
A

DOUBLER 13 .040/2024 ALC SHEE~r FLAT ADD 7 CR3524-~ RIVETS

RIVET ADJaCEN TO CRACK INTALI CR352d-3 RIVET

INBD

SHIM

?1 j i

WINC’OW

VIEW

SKIN

Number 8 Left and

(FL-1

thru

A

A

00""_’"

AFT

SHIM

C93FL538

i 65:

Right Stringer Repair

FL-~03; FM-1 thru FM-8)

Figure

203

ORIGINAL As Received

By

ATP

Page

yaM012

1107

53-~ 0-00

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE

o _r

I~ H RH

A

SHOWN IDENTICAI

AFT

DU FS

PRESSURE K~EAD

TO RIVET CRACK. DRAW DTMPLE DOU3LE’Z AND ~1-1:1:lil. INSTALL C1~35 2 RIVET IN EXTS-II´•IG LOCATION

A

1

v,

ii

~O

SiRINGERR

ADD 3 CR3524-2 RIVETS

INSTALL 6 CR3524-2 RIVEIS IN EXISTING LOCATIOI\IS

ADD 2 CR3524-2 RIVETS

1

DETAIL A S~:l:NS HAVE BEEN OELEIEC ORDER ~r0 C´•I_II\IE\TE THE POSITION THE STR NG_I: iiND BULKHEAD

IN IN OF

:I’

ii

1 D.E’;

~Y

‘iF

-c:

P

‘O

0~

0-0

I

Ir:0.80

~IMPLE DOUBLER iND 6 CR352a-2 ii-iSTL! PZ~ETS IN EXISTING L’I)CATIONS

1 .80

DETAIL ADD 3 CR3524-2 RIVETS

.._

DIMPLE DOUBLE~ kND INSTALL 8 CR35~4-3 RIVETS I~ EXZ~TING LOCATIONS

LOOKING

kDD a CR35~4-2 RIVETS

A

INBD

DOUS_ER

ALC FLAi

SHEET

SKIN

VIEYA-A

COUBLER C93FL53B

i

(1"6

Number 9 and 10 Left and Right Stringer Repair (FL-1 thru FL-I03; FM-I thru FM-8)

Figure

ORIGINAL As Received BY n2n

ATP

204

53-1 0-00

Page 211 May 1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MAN UAL

j

j NOTE IN IN OF

A

DETAIL ORDER T~

THE

SI/INS HBvE BEEN DELETED DELII~EATE IHE POSITION STRINGER AN3 GJLKHEAD

A Li-l

Sli3WI\1

RI--l

IDEI~TICAL ADD 3 CR3524-2 RIVETS

AFT

PRESSURE 3ULKHEAD FS 381.75

8 RIVETS IN LCUATIONS

--i.80 0.80

CR3524-~ EXISTING

knD RI~

:;I_,

r3

’r

STRII\IGER

ADJACENT TD DRAW DIIVIPI_E CRACI~. DOUBLER AND S~-1IM. INSTALL CR352a-3 RIVET IN EXISTING LOCATION RIVET

A ii

0.85

O

(TYP)

O

U" :liLC FLAT

O

C~ i

I\

O

0-

ii

73.CO

Si-EET 3.~0

DIMPLE DOUBLER AN~ INSTALL 8 CR35~4-2 RIVETS IN EXISTING LOCATIONS

(MAX. DIM?L_ UOUELE~ AND INST~_L 5 CR3524-~ IN ExISIING LOCBIIONS

i ADD

ADD

2

RIVETS

OETAIL LOOKING

A

INBD SKII\I

-rr

VIEWA-A

DOUBLER

Number 11 Left and

(FL-1

thru

Right Stringer Repair FL-103; PM-1 thru FM-8) Figure

205

ORIGINAL As Received

By

ATP

Page

yaM212

1107

53-~ 0-00

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CENTER LINE RNO. 1 STRINGER NO. 2 NO.3 NO. 4

STRINGER NO. 5 NO. 6 STRINGER NO. 7

J7

D

NO. 8 STRINGER NO. 9

STRINGER NO. 10

\--STRINGER NO. 11

200-98-34

OR\GINAL As Received BY

Fuselage Stringers Figure 206

AT P

A22

53-1 0-00

yaM312

Page

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CENTERLINE STRINGER NO.

STRINGER NO.

2

I

LH

STRINGER NO.

2

RH

STRINGER NO.

3

RH

STRINGER NO.

4

RH

STRINGER NO.

5

RH

STRINGER NO.

6

RH

STRINGER NO.

7

RH

STRINGER NO.

8

RH

STRINGER NO.

9

RH

~O

FRAME

~f ZEE STIFFENERS

O

REAR PRESSURE BULKHEAD

NOTE:

ONLY STRINGERS NO. TIED TO THE RH

VIEW:

SIDE

REAR

SHOWN.

LH

5

THROUGH NO.

LH

BULKHEAD ZEE

PRESSURE SIDE

II

STRINGER NO.

10

RH

STRINGER NO.

II

Rt-f

AND RH ARE

STIFFENERS.

TYPICAL.

LOOKING FORWARD AT THE REAR PRESSURE BULKHEAD FROM

AFT

THE

SIDE

OF

THE

BULKHEAD.

C93885381724

(FL-1

Affected Stringers thru FL-103; FM-1 thru

Figure

May 107Page

214

53-10-00

FM-8)

207

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ZEE

STIFFENER

O UP

STRINGER

ZEE

00

q

I

STIFFENERS

FUSELAGE SKIN LH

f--~g! REAR PRESSURE BULKHEAD

I STRINGER CRACK

o~

Y,~

I

(TYPICAL)

INSPECT THE STRINGERS FOR CRACKS WHERE ZEE STIFFENERS ARE ATTACHED TO

THE

STRINGERS WITH 6 RIVETS. (STRINGER J-SECTION REMOVED FOR

THE

STRINGERS

DETAIL RIVETS

CLARITY)

A

(6]/

o

O

O

O REAR

PRESSURE

REAR

PRESSURE BULKHEAO

BULKHEAD

CRACK

INSPECTION AREA (STRINGER J-SECTION REMOVED FOR CLARITY)

A

STRINGER

INSPECT FOR AROUND THE 6

I/

CRACKS RIVETS

~o

0\0

o

LH FUSELAGE SKIN

VIEW LOOKING

OF

THE

FORWARD

LH

STRINGERS

AND

TO

THE

AND

REAR

PRESSURE

LEFT

FROM

INSIDE

BULKHEAD

THE

FUSELAGE 593855381725

Stringer

Crack Aft of the Rear Pressure Bulkhead thru FL-103; FM-1 thru FM-8)

(FL-1

Figure

A22

208

53-~ 0-00

Page

yaM512

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MAN UAL

/~*o

c

111

h

~f;b

~ei

_OL)O

GZ;.

j

r~

j/ j

:i

i-e

n

A

?,d r;

k

ii

REAR FRESSIIRE BULI´•c;-IEAn

DETAIL

A

RH

FUSELAGE

9!´•: IN

r-

P\

9’

b;?-

R

ii

iFOR

REMOVE S;ALE’> INSPECT13N

O

~I

INSPEZT FOR CRACI~S

J

O

jI

i, Cc PRESSURE BULI~HEAD

--tC--RER

~ii ;11---11

o

ii

Ij

I~

ilI~ Ilo

ijoo U!

I~

DETAIL

C

S’~INGER

C93FLj3e1632

DETAIL

C

B

Forward Side of Aft Pressure Bulkhead Inspection (FL-I thru FL-110; FM-1 thru FM-8)

Figure

209

ORIGINAL As Received By ATP

May 107Page

216

53-~ 0-00

A22

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 53-11-00

CABIN AND COCKPIT VIBRATION ABSORBTION - DESCRIPTION AND OPERATION SPECIAL TOOLS AND RECOMMENDED MATERIALS The special tools and recommended materials listed in Charts 1 and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically prescribed by Hawker Beechcraft Corporation. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

Chart 1 Special Tools and Equipment TOOL NAME

PART No.

SUPPLIER

1. Soft Durometer Roller

Obtain Locally

2. Teflon Scraper

Obtain Locally

3. Needle Nose Pliers

Obtain Locally

4. Rubber Squeegee

Obtain Locally

5. Heat Gun

Obtain Locally

6. Cheese Cloth

Obtain Locally

A27

USE Skin damping panel removal, installation and repair.

53-11-00

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 Recommended Materials MATERIAL

SPECIFICATION

PRODUCT

SUPPLIER

1. Solvent

Naphtha

Obtain Locally

2. Solvent

Isopropyl Alcohol

Obtain Locally

3. Solvent

Methyl Propyl Ketone (MPK)

Obtain Locally

4. Activator

Loctite7387

Epoxy

Loctite Corporation 1001 Trout Brook Crossing Rocky Hill, CT 06067

5. Adhesive

Loctite 330

Epoxy

Loctite Corporation 1001 Trout Brook Crossing Rocky Hill, CT 06067

6. Adhesive

Loctite 242

Thread locker

Loctite Corporation 1001 Trout Brook Crossing Rocky Hill, CT 06067

7. Sealant

Tectyl 351S

Sound Deadener

Daubert Chemical Company Inc. 4700 South Central Ave. Chicago, IL 60638

DYNAMIC VIBRATION ABSORBERS (FL-475 AND AFTER) Dynamic vibration absorbers are installed for vibration and sound reduction in the flight compartment and forward cabin area. The absorbers are installed above and below the cabin and cockpit windows on each side of the fuselage between FS 134.00 and FS 290.25. The absorbers are mounted on the airplane frame and consist of spacers, mounts, weights and leaf springs. The weights are secured to the leaf springs with bolts, washers and nuts; the leaf springs are secured to the mounts with bolts, washers and nuts. DYNAMIC VIBRATION ABSORBER TUNING FREQUENCY (FL-475 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED) At the time of installation, each absorber is tuned to the frequency of 100.00 Hz (-3 and -21 leaf springs) or 195.00 Hz (-23 leaf spring). This frequency is determined by the specific propeller speed at which a vibration or noise exists. DYNAMIC VIBRATION ABSORBER TUNING FREQUENCY (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) At the time of installation, each absorber is tuned to the frequency of 101.30 Hz (-35 leaf springs). This frequency is determined by the specific propeller speed at which a vibration or noise exists.

Page 2 Feb 1/10

53-11-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TUNED VIBRATION ABSORBERS (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) Tuned vibration absorbers (TVA’s) (Ref. Figure 1) are installed for vibration and sound reduction in the flight compartment and passenger cabin area. The absorbers are installed below the cabin and cockpit windows on each side of the fuselage internal surfaces between FS 107.00 and FS 312.5. The TVA’s are attached to the airplane skin, through holes in the skin damping panels using a two part epoxy adhesive mix. The TVA is a self contained mass and spring system that is tuned at the time of manufacture to a narrow frequency range to match specific propeller speed at which noise or vibration exists.

A27

53-11-00

Page 3 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1

2

3 4

5

1 2 3 4 5

- FUSELAGE SKIN (REF) - SKIN DAMPING PANEL - TUNED VIBRATION ABSORBER MOUNT - THREADLOCK (REF) - TUNED VIBRATION ABSORBER FL25B 985646AA.AI

Skin Damping Panel and Tuned Vibration Absorber Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 1

Page 4 Feb 1/10

53-11-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SKIN DAMPING PANELS (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) Skin damping panels are installed for vibration, sound and vibration reduction in the flight compartment and passenger cabin area. The skin damping panels are installed on the majority of the fuselage skin internal surfaces between FS 84.00 and FS 381.75. The skin damping panels are attached to the airplane skin with a pressure sensitive adhesive layer (on the panel) protected by a peel off release liner prior to installation. SKIN DAMPING PANEL, DAMAGE LIMITS Damage classified as “Not Acceptable” can be repaired using the skin damping removal/installation procedures (Ref. Chapter 53-11-00), removing only the damaged skin damping panel. NOTE: Any damage to damping panels must be evaluated. On the fuselage side and top above floor level, all damaged sods must be replaced. Below floor level it is permissible to leave five total damaged sods. Replace sods with first priority being the cabin area, followed by the cockpit, vestibule and baggage areas. Damage classification for skin damping panels is as follows:

Chart 3 Flight Compartment and Passenger Compartment Skin Damping Panel Conditioning PANEL CONDITION

FIGURE, DETAIL

EXPLANATION

Ideal Panel Condition - Acceptable.

Figure 2, Detail A

A slight pattern or ripple may be present on the aluminum cap but no other form of damage should be visible.

Creased Aluminum Cap - Acceptable.

Figure 2, Detail B

Creases caused in manufacture of the panel but does not reduce panel performance.

Dented Aluminum Cap - Acceptable.

Figure 2, Detail C Slight indentations that do not pierce the aluminum cap are acceptable as long as the stand-off material does not protrude or appear damaged.

Dented Corner (Aluminum Cap and Stand-Off Material) - Acceptable.

Figure 2, Detail D Deformation of the aluminum cap and stand-off layer must not extend further than 0.5 inch from the corner.

Missing Stand-Off Material from the Corner - Acceptable/Not Acceptable.

Figure 2 Detail E

If any piece of stand-off material other than the corner is missing or the aluminum cap is severely delaminated then the panel is not acceptable.

Pierced or Punctured Aluminum Cap Not Acceptable

Figure 2, Detail F

A pierced or punctured aluminum cap where the stand-off material is visible is not acceptable.

Severe Deformation - Not Acceptable

Figure 2, Detail G If the stand-off layer is deformed so that the thin web is broken or creases and delamination are obvious throughout the panel then the panel is not acceptable.

A27

53-11-00

Page 5 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CREASE

A

DETAIL IDEAL PART CONDITION - ACCEPTABLE CREASES

B

DETAIL CREASED ALUMINUM CAP - ACCEPTABLE

DENTS DELAMINATION STAND-OFF MATERIAL BROKEN THIN WEB

G

DETAIL SEVERE DEFORMATION OF PART NOT ACCEPTABLE

STAND-OFF MATERIAL

C

DETAIL DENTED ALUMINUM CAP - ACCEPTABLE STAND-OFF MATERIAL

PUNCTURED ALUMINUM CAP

F

DETAIL PUNCTURED ALUMINUM CAP - NOT ACCEPTABLE

AREA LIMIT 0.5 INCH

D

E

DETAIL MISSING STAND-OFF ON CORNER ACCEPTABLE/UNACCEPTABLE

MISSING STAND-OFF MATERIAL

DETAIL DENTED CORNER (ALUMINUM AND STAND-OFF) - ACCEPTABLE

FL53B 985691AA.AI

Skin Damping Panel Conditioning (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 2 Page 6 Feb 1/10

53-11-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAIN LANDING GEAR, NOSE WHEEL WELL, AVIONIC COMPARTMENT AND MAIN SPAR COVER, SKIN DAMPING PANELS Skin damping panels are installed on the nose wheel well (in the flight compartment), the upper inboard skin of the avionics compartment between FS 84.00 and FS 57.50 and the main spar cover for sound and vibration reduction (Ref. Figure 3). The skin damping panels are attached to the nose wheel well skin and avionic compartment skin with a pressure sensitive adhesive (on the damping panel) that is protected by a peel off release layer prior to installation.

MAIN LANDING GEAR, NOSE WHEEL WELL, SOUND DEADENER COATING The sound deadener is a single mix, waterborne, asphalt emulsion, corrosion preventative compound. A uniform layer of sound deadener coating is applied to the lower and inboard surfaces of the nose wheel well that recede into the nose compartment and flight compartment area to reduce noise in the flight compartment.

A27

53-11-00

Page 7 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This Page Intentionally Left Blank

Page 8 Feb 1/10

53-11-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FS 57.50 (REF)

FS 84.00 (REF)

FS 70.75 (REF)

STGR 7R (REF) 1 STGR C (REF)

A

A

1

2

STGR R (REF)

D

3 WL 87.00 (REF)

CL ACFT (REF)

B

STGR B (REF) STGR C (REF)

D FS 57.50 (REF)

1234-

STGR 7L (REF)

4

FS 84.00 (REF)

FS 143.00 (REF)

SKIN DAMPING PANEL CARPET This MAIN SPAR COVER SOUND DEADENER COATING

VIEW

A-A

CL ACFT (REF)

1

Page Intentionally Left Blank

DETAIL

B

1

C

E 1

1 1

1

WL 93.875 (REF)

WL 93.875 (REF)

WL 93.875 (REF)

WL 92.00 (REF)

WL 92.00 (REF)

WL 92.00 (REF)

1

E WL 87.00 (REF)

FS 95.50 (REF)

AFT

VIEW

E-E

FS 84.00 (REF)

RBL 8.00 (REF)

C 1

D-D

VIEW (MAIN LANDING GEAR NOSE WHEEL WELL)

LBL 8.00 (REF)

FS 84.00 (REF)

FS 95.50 (REF)

AFT VIEW

C-C

WL 87.00 (REF)

FL53B 985692AA.AI

Main Landing Gear, Nose Wheel Well, Avionics Compartment and Main Spar Cover Skin Damping Panels Figure 3

A27

53-11-00

Page 9 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

CABIN AND COCKPIT VIBRATION ABSORPTION - MAINTENANCE PRACTICES DYNAMIC VIBRATION ABSORBER REMOVAL NOTE: Both halves of the weights are marked with an ink stamp that denote the resonant frequency at which the absorber is tuned. Torque paint, applied to the ends of the weights, leaf spring(s) assembly hardware, indicates any disturbance of the weights, leaf spring(s) assembly hardware. Any indication of movement requires retuning the absorber. a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove any equipment, furnishings and panels (Ref. Chapter 25-20-00) necessary to gain access to the dynamic vibration absorbers (Ref. Figure 201 and Figure 202).

d. Mark the location of each dynamic vibration absorber and identify each weight so they can be reinstalled in the same position. e. Remove four nuts, washers and bolts used to secure the dynamic vibration absorber mount to the airplane frame. f.

Carefully remove the absorber assembly from the airplane frame, taking care not to disturb the weights or leaf spring position.

DYNAMIC VIBRATION ABSORBER INSTALLATION NOTE: Make sure that areas where the spacers and leaf springs mate are free of primer. Check cadmium plating for damage. Clean the surface and apply a new coat of cadmium plating (per Specification QQ-P-416) in areas where damage has occurred. Check the mounting surface for a smooth, flat surface. A change in the mating surface necessitates retuning the absorber. a. Align the dynamic vibration absorber (Ref. Figure 201 and Figure 202) with the mating surface. DO NOT INVERT ANY ABSORBER ASSEMBLY. b. Install four bolts, washers, and nuts to secure the dynamic vibration absorber mount to the airplane frame. c.

After installation, check the condition of the ink stamp indicating the absorber part number and resonant frequency. Make sure that the frequency ink stamp is installed and legible on the leaf spring. NOTE: Make sure that the dynamic vibration absorbers do not contact insulation, wiring or other objects after insulation.

d. Replace any equipment, furnishings and panels (Ref. Chapter 25-20-00) removed to gain access to the dynamic vibration absorbers. e. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

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DYNAMIC VIBRATION ABSORBER TUNING Tuning of the absorbers must be performed by properly trained personnel using special equipment. If tuning becomes necessary, contact Hawker Beechcraft Corporation Technical Support for instruction. The absorbers are tuned to a specific frequency and a bead of torque paint (Ref. Figure 201 and Figure 202) is applied to the ends of the weights and leaf springs. Any breakage of the torque seals necessitates retuning the absorber.

Page 202 Feb 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INK STAMP IN APPROXIMATE LOCATION SHOWN AFTER TUNING. STAMP MARKING SHALL READ: "130-420059-21" (100.00 HZ)

INK STAMP IN APPROXIMATE LOCATION SHOWN AFTER TUNING. STAMP MARKING SHALL READ: "130-420059-3" (100.00 HZ)

-21 REF

FS 339.25

FS 307.520

FS 299.750

FS 290.250

FS 280.750

FS 270.500

FS 251.200

FS 261.000

FS 241.400

FS 231.400

FS 221.400

FS 211.900

FS 202.400

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FS 179.525

FS 168.750

FS 158.000

FS 143.000 FS 147.600

FS 134.000

FS 125.000

FS 116.000

FS 94.000 FS 100.500 FS 107.000

RIGHT SIDE ONLY

INK STAMP IN APPROXIMATE LOCATION SHOWN AFTER TUNING. STAMP MARKING SHALL READ: "130-420059-23" (195.00 HZ)

-3 REF -23 REF

FL53B 053266AA.AI

Dynamic Vibration Absorbers (FL-475 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687) Figure 201

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FS 339.25

FS 307.520

FS 299.750

FS 290.250

FS 280.750

FS 270.500

FS 261.000

FS 251.200

FS 241.400

FS 231.400

FS 221.400

FS 211.900

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FS 191.000

FS 179.525

FS 168.750

RIGHT SIDE ONLY

FS 158.000

FS 143.000 FS 147.600

FS 134.000

FS 125.000

FS 116.000

FS 94.000 FS 100.500 FS 107.000

LEFT SIDE ONLY

INK STAMP IN APPROXIMATE LOCATION SHOWN AFTER TUNING. STAMP MARKING SHALL READ: "130-420059-35" (101.30 HZ)

TORQUE SEAL (REF)

-31 ASSY

FL53B 985598AA.AI

Tuned Vibration Absorbers (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 202

Page 204 Feb 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TUNED VIBRATION ABSORBER MOUNT INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove all equipment, furnishings and panels (Ref. Chapter 25-20-00) necessary to gain access to the required tuned vibration absorber (Ref. Figure 203, Sheet 1, Sheet 2 or Sheet 3).

d. Clean the bonding surface of the airplane skin with solvent (1, 2, 3 Chart 2, 53-11-00) and cheese cloth (6, Chart 2, 53-11-00). e. Apply activator (4, Chart 2, 53-11-00) on the base of the tuned vibration absorber mount and the prepared airplane skin. f.

Place an adequate amount of epoxy adhesive (5, Chart 2, 53-11-00) on the base of the tuned vibration absorber mount to allow for a small fillet of epoxy to be squeezed from between the base and the airplane skin when initially installed.

g. Place the tuned vibration absorber mount in the installed position with enough pressure to create a fillet of epoxy adhesive around the absorber mount. h. Hold the tuned vibration absorber mount in the installed position for 1.5 minutes or until the epoxy adhesive can support the weight of the tuned vibration absorber mount. i.

Allow epoxy to cure for 12 hrs. Perform the TUNED VIBRATION ABSORBER INSTALLATION procedure (if required).

j.

Install all equipment, furnishings and panels removed for access (Ref. Chapter 25-20-00).

k.

Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

TUNED VIBRATION ABSORBER REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove any equipment, furnishings and panels (Ref. Chapter 25-20-00) necessary to gain access to the tuned vibration absorber required (Ref. Figure 203, Sheet 1, Sheet 2 or Sheet 3).

d. Rotate the tuned vibration absorber counterclockwise and remove it from the tuned vibration absorber mount. NOTE: The tuned vibration absorber is secured to the tuned vibration absorber mount using a threadlock adhesive.

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TUNED VIBRATION ABSORBER INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Clean the threads of the tuned vibration absorber mounting with a clean cheese cloth dampened with solvent and allow to dry thoroughly. Bonding surface must be free of dust, oil, finger prints and other surface contaminates. b. Apply threadlock adhesive (6, Chart 2, 53-11-00) to the mounting threads. CAUTION: Overtightening can cause damage to the bond between the tuned vibration absorber mount and the airplane skin. c.

Install the tuned vibration absorber on the tuned vibration absorber mountand firmly tighten by hand. Tighten tuned vibration absorber until snug, then tighten an additional 1/4 turn.

d. Install all equipment, furnishings and panels removed for access (Ref. Chapter 25-20-00). e. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

SKIN DAMPING PANEL REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove any equipment, furnishings and panels (Ref. Chapter 25-20-00) necessary to gain access to the skin damping panel required (Ref. Figure 203, Sheet 1, Sheet 2 or Sheet 3).

d. Perform TUNED VIBRATION ABSORBER REMOVAL procedure (if required). e. Using needle nose pliers (3, Chart 2, 53-11-00), remove the aluminum cap from panel to be removed. f.

Using a heat gun (5, Chart 2, 53-11-00), heat the stand-off layer and remove with scraper (2, Chart 2, 53-11-00).

g. Remove remaining viscoelastic material from the airplane skin using solvent (1, 2 or 3, Chart 2, 53-11-00) and cheese cloth (6, Chart 2, 53-11-00).

SKIN DAMPING PANEL INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) CAUTION: The panel when installed must not overlap chemi-mill edges, rivets, sealer or any obstructions. a. Clean area where skin damping panel is to be installed with a clean cheese cloth (6, Chart 2, 53-11-00) dampened with solvent (1, 2 or 3, Chart 2, 53-11-00). Bonding surface must be free of dust, oil, finger prints and other surface contaminants. CAUTION: Once the release liner has been removed, handle the skin damping panel by the edges to prevent contamination of the pressure sensitive adhesive. b. Peel off the release liner from the skin damping panel, place the panel over the installed position without allowing the skin damping panel to touch the airplane skin. Page 206 Feb 1/10

53-11-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL c.

Press the skin damping panel firmly into position and roll over the entire area of the skin damping panel with a roller (1, Chart 2, 53-11-00) or rubber squeegee (4, Chart 2, 53-11-00) NOTE: If pressure is to be applied by hand make sure that a firm and even pressure all over the skin damping panel is used taking care not to mark the panel in any way.

d. Perform the TUNED VIBRATION ABSORBER INSTALLATION procedure (if required). e. Install all equipment, furnishings and panels removed for access (Ref. Chapter 25-20-00). f.

Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

MAIN LANDING GEAR, NOSE WHEEL WELL SOUND DEADENING COATING INSTALLATION a. Gain access to the main landing gear, nose wheel bay. b. Clean all wheel well surfaces that recede into the nose compartment and flight compartment area to be sealed with solvent (1, 2, or 3, Chart 2, 53-11-00) and cheese cloth (6, Chart 2, 53-11-00). Make sure all surfaces are clean, dry and oil free. c.

Apply sealant (7, Chart 2, 53-11-00) in an even coat 0.10 to 0.12 inch thick, feathering the edges to zero.

d. Leave the sealant to cure. Dry to touch time is 30 to 45 minutes and total cure time is 16 to 34 hours dependant upon ambient temperature.

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FS 241.125 REF

FS FS FS FS FS FS 299.75 289.875 280.00 270.125 260.250 250.650 REF REF REF REF REF REF

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FS FS 148.90 143.00 REF REF

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FS FS 221.375 211.90 REF REF

FS 232.650 REF

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FS 371.25 REF

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FS 290.25 REF

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FS FS FS 261.00 251.200 241.40 REF REF REF

FS 179.525 REF

FS 190.65 REF

FS 201.775 REF

FS 231.40 REF

FS FS 221.40 211.90 REF REF

FS 202.40 REF

FS 191.00 REF

FS 179.525 REF

DETAIL

FS 241.125 FS FS FS FS REF 232.650 250.650 260.250 270.125 REF REF REF REF

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1 - TUNED VIBRATION ABSORBER (TVA) 2 - SKIN DAMPING PANEL

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VIEW

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FS FS FS FS FS FS FS FS 94.00 158.00 150.00 143.00 134.00 125.00 116.0 0 107.00 REF REF REF REF REF FS REF REF REF 100.50 REF

FS 168.75 REF

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B

G FE

2

FS FS 339.25 FS FS REF FS 325.875 312.50 REF 299.75 332.562 FS REF FS REF REF 319.118 307.52 REF REF

FS 132.80 REF

G

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B

FS 122.00 REF

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FS 132.80 REF

FS FS 339.25 FS FS 325.875 REF 312.50 FS 299.75 REF REF FS 332.562 REF FS 319.118 REF 307.52 REF REF

2

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FS 350.00 REF

2

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FS 360.75 REF

FS 371.25 REF

FS 381.75 REF

FL25B 985650AA.AI

Skin Damping Panel and Tuned Vibration Absorber (FL-601, FL-672, FL-688 and After With CMS Installed) Figure 203 (Sheet 1 of 3)

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STGR 14L

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FS 381.75 REF

FL25B 985651AA.AI

Skin Damping Panel and Tuned Vibration Absorber (FL-601, FL-672, FL-688 and After With CMS Installed) Figure 203 (Sheet 2 of 3) Page 210 Feb 1/10

53-11-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

2 2

WL 129.52 (REF)

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FWD VIEW

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VIEW

FS FS 312.50 307.52 (REF) (REF)

F-F

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2

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K 1

VIEW

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3

VIEW

1. TUNED VIBRATION ABSORBER 2. SKIN DAMPING PANEL 3. SKIN (REF)

TYPICAL SKIN DAMPING PANEL/FUSELAGE INSTALLATION

J

2

J-J

H

DETAIL TYPICAL SKIN DAMPING INSTALLATION WITH TUNED VIBRATION ABSORBER

4. TUNED VIBRATION ABSORBER MOUNT

FL53B 985688AA.AI

Skin Damping Panel and Tuned Vibration Absorber (FL-601, FL-672, FL-688 and After With CMS Installed) Figure 203 (Sheet 3 of 3)

A27

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Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

PLATES AND SKIN

This section is concerned with the skin formed to the structure of the of the skin is necessary, the thickness. or

repair

WARNING:

same

fuselage.

Drilling, modification or any work which creates a break the responsibility of the owner or facility performing the is, therefore, their responsibility.

It is recommended that

repair

It is essential that when

material and material thickness be utilized. Refer to

methods used

on

the

airplane

replacement Figure 1 for skin

in the pressure vessel is considered Obtaining approval of the work

work.

be in accordance with

AC43.13A, AIRCRAFT

INSPECTIQN AND REPAIR MANUAL and AC43.13-2, AIRCRAFT ALTERATIONS MANUAL. In addition, the

following should

be considered:

fuselage, all skin, formers, frames and stringers are structural members and it is essential that the structural strength of the pressure vessel is maintained. A cabin pressurization test must be performed after any structural repair to the pressure vessel.

CAUTION: In the pressure

area

of the

a.

Never make

b.

All

lap joints, including patches,

c.

All

repair material

d.

Never

e.

Do not countersink

Minor

a

dimple

repair

skin

a

replacement

patch from

material thinner than the

must be free of any defects such as

structure member

deeper than

plus 0.006-inch) portion of the

and the etched

a

must have at least two

by driving

75

a

staggered

rows

original

skin.

of rivets.

nicks, gouges, and/or scratches.

rivet head into the part.

percent of the material thickness.

to chem-milled skins may be are

n24

or

maintained between

accomplished, providing proper edge distances (twice the rivet diameter repair rivets and all points of transition between the original skin thickness

skin.

53-30-00

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

3

3

I

DI 0!011 3

3

2

0! ii-

13

7

4

2

k~S

2

3

2 3

33

3

~CO

3

lj

9

3

3

3

i

B

b

?I

3

~7

II

3

3

1

ooooooo

3

3

3

I

13

222

0

2

3

3

8

E~

2

MATERIAL

2

1

I

IV

SS IhC~ES

_t

ITEM

202413

.n25

9.

2024T3

.04~

10.

202413

.n5

I

202673

.071

S.

202473

.090

6.

202473

.03~

202473

053

1.

MATERIA

3.

202473

IHICKNESS IN INCHES .025

20241?

.050 81 LA~INAirZ ~3. nLIES MIL C qOfid ARCU~C ’T

12.

H.

13

3

I

a

LAK:~AiED GLASS 606

Tb

CLOTH-PEi 4 ADOIII7~8 AliACH APEP.

GLASfi FLU

.030 RC, iSI P~R ~IL-C9084

3

PLIES

.025 350-13-012

.OLD

C

Fuselage Skin Thickness Figure 1 ORIGINAL As Received

By

ATP

May

1/0853-30-00

A24

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 53-40-00

ATTACH FITTINGS - DESCRIPTION AND OPERATION COCKPIT SEAT TRACKS The cockpit seats (pilot and copilot) are mounted on seat tracks. The seat tracks allow movement of the seats forward and aft between seat stops. Lock pins are controlled by the seat occupant to adjust and secure the seat in a particular position on the tracks. The pilot and copilot seats have seat support channels that are designed to move on the tracks while preventing seat and track separation. Four cockpit seat tracks extend from FS 118.00 to FS 142.00 along L/RBL 11.00 and L/RBL 21.00. Each seat track is secured to a track support with 18 screws into nutplates on the track support structure.

CABIN SEAT TRACKS The cabin seats (passenger) are mounted on seat tracks in the fixed position. Movement of the seats is accomplished within the seat base (Ref. Chapter 25-20-01). Four cabin seat tracks extend aft from FS 143.00 (except at the cabin entrance door) along L/RBL 9.32 and L/RBL 22.94. Each seat track is secured to track support assemblies with countersink screws and nuts.

CABIN RAIL SYSTEM (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) The cabin rail system is used to support internal furnishings (Ref. Chart 1) and is divided into two areas, the main cabin and the aft cabin. The main cabin consists of 14 fuselage mounted rails, (two upper and twelve lower rails), eight hat sections (table supports), and the aft cabin has four rails, two upper and two lower (Ref. Figure 1). The rails are installed on anti vibration mounts secured to mounting brackets, the mounting brackets being attached to the fuselage.

Chart 1 Cabin Rail Installed Components MAIN CABIN

AFT CABIN

Interior Panels

Interior Panels

Headliners

Headliners

Partitions

Partitions

Cabinetry Passenger Tables Armcaps

A27

53-40-00

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AFT CABIN UPPER RAIL CABIN UPPER RAIL

AFT CABIN LOWER RAIL

CABIN LOWER RAILS

NOTE: LEFT SIDE SHOWN - RIGHT SIDE TYPICAL

FL53B 985645AA.AI

Cabin Rail System Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 1 Page 2 Feb 1/10

53-40-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

ATTACH FITTINGS - MAINTENANCE PRACTICES As the seat attach fittings wear with use, their strength is reduced. Excessive wear of the seat attach fittings may cause the crew seat to become unstable. Wear for the seat attach fittings have been established to determine when replacement is necessary (Ref. Figure 201). Wear Limits are checked at the intervals specified in Chapter 5. Replacement of worn seat attach fittings must be accomplished if wear limits are exceeded. Inspect the entire length of each seat track for wear. If gouging or chaffing is present and the depth and width does not exceed the limits shown in Figure 201 proceed with the following repair procedure. a. Remove any sharp edges using aluminum oxide sandpaper. CAUTION: Do not sand any deeper than the initial gouge or chafe. b. Apply coating (3, Chart 201, 53-10-00) on any exposed surface.

COCKPIT SEAT TRACK WEAR LIMITS The seat track must be replaced if wear limits shown in Figure 201 are exceeded. A slight gouge in the forward and aft direction of the upper seat track surface caused by the lock pin while sliding the crew seat, is not detrimental to the operation of the seat provided the gouge does not exceed wear limits.

COCKPIT SEAT LOCKPIN WEAR LIMITS Replace the lock pin if the diameter of the pin engagement into the seat track is less than the minimum dimension shown in Figure 201, Detail B.

COCKPIT SEAT SUPPORT CHANNEL WEAR LIMITS Check each seat support channel for wear. Replace the seat support channel if any measurement is less than the minimum dimension shown in Figure 201, Detail C.

CORROSION ON THE COCKPIT SEAT TRACK Inspect the entire length of each seat track for corrosion. Refer to Figure 201 for wear limits which have been established for the flight compartment seat tracks. If corrosion is found on the seat tracks, refer to Chapter 20-0900 for corrosion removal and treatment. If the limits shown in Figure 201 cannot be met, contact Hawker Beechcraft Corporation Technical Support.

CABIN SEAT TRACK WEAR LIMITS As the seat tracks wear with use, their strength is reduced. Wear limits for the seat tracks have been established to determine when replacement is necessary. Wear limits are checked at the intervals specified in Chapter 5. For maximum wear limits which have been established for the seat track refer to Figure 202. Replacement of a worn seat track must be accomplished if any wear limit is exceeded. Inspect the entire length of each seat track for wear. If gouging or chaffing is present and the depth and width does not exceed the limits shown in Figure 202, proceed with the following repair procedure.

A27

53-40-00

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Cockpit Seat Attach Fittings Wear Limits Figure 201

Page 202 Feb 1/10

53-40-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CORROSION ON THE CABIN SEAT TRACK Inspect the entire length of each seat track for corrosion. Refer to Figure 202 for wear limits which have been established for the passenger seat tracks. If corrosion is found on the seat tracks, refer to Chapter 20-09-00 for information on corrosion removal and treatment. If the limits shown in Figure 202 cannot be met, contact Hawker Beechcraft Technical Support.

Cabin Seat Track Wear Limits Figure 202

A27

53-40-00

Page 203 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CABIN RAIL AND AFT CABIN RAIL SYSTEM REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove panels, equipment and furnishings (Ref. Chapter 25-20-00) as required to get access to the cabin rail assembly.

d. Remove the screws (1) and washers (2) securing the rail (3) to the isolator brackets (4) (Ref. Figure 203) from the locations shown in Chart 201. e. Remove the rail (3) from the airplane.

CABIN RAIL AND AFT CABIN RAIL SYSTEM INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Place the rail assembly (3) in the installed position on the isolator brackets (4) (Ref. Figure 203). If rail assembly slots do not exist for mounting, drill 0.194 to 0.190 inch hole thru rail assembly to match isolator brackets. b. Install the screws (1) and washers (2), and tighten the screws (1) to secure the rail (3) at the locations shown in Chart 201. c.

Install the panels, equipment and furnishings (Ref. Chapter 25-20-00) removed for access to the cabin rail assembly.

d. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tags.

Page 204 Feb 1/10

53-40-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

4

1234-

SCREW WASHER RAIL ISOLATOR BRACKET

2

3

1 FL53B 985644AA.AI

Rail System Removal/Installation (Typical) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 203

A27

53-40-00

Page 205 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 Rail System Isolator Bracket Locations

F.S. Number

Main Cabin Upper

Main Cabin Middle

Main Cabin Lower

148.9

X

158

X

X

X

X

X

X

X

211.9

X

X

231.4

X

X

251.2

X

X

261

X

X

X

X

168.75 179.525

X

201.775

X

232.65

Aft Cabin Upper Left

Aft Cabin Upper Right

Aft Cabin Middle Left

Aft Cabin Middle Right

X

241.125 250.625

X

270.125

X

289.875

X

290.25 307.52

X

312.5

Page 206 Feb 1/10

X X

325.88

X

X

332.56

X

X

339.25

X

X

350

X

X

360.75

X

X

X

X

371.25

X

X

X

X

53-40-00

X

A27

C H A PT E R

STABILIZERS

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 55

STABILIZERS

TABLE OF CONTENTS

PAGE

SUBJECT 55-10-00

..........201

Horizontal Stabilizers- Maintenance Practices

.......201

Recommended Materials

.201

Horizontal Stabilizer Removal

..202

Horizontal Stabilizer Installation 55-20-00

....1

Elevator- Maintenance Practices

Balancing Checking Balance Elevator

Balancing Procedures Equipment Required

to Perform Check

Balancing by

Force Measurement Method ..................1 ...1

Force Measurement Method

Equipment Required to Perform Check Balancing by Counterbalancing Counterbalancing Method

.2

Method

.....2

55-30-00 .............201

Vertical Stabilizer- Maintenance Practices.

......201

Vertical Stabilizer Removal

....201

Vertical Stabilizer Installation 55-40-00

...201

Rudder- Maintenance Practices

Balancing Checking Balance Equipment Requiredto Perform Check Balancing Balancing Procedure. Counterbalancing Method Rudder Trim Moisture Drain Inspection Rudder

A24

.......201 ..........201 ...201 ...............203

55-CONTENTS

1/08Page May

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

55-LOEP

1

May

1/08

53-CONTENTS

1

May

1/08

55-10-00

201 thru 203

May 1/08

55-20-00

1 thru 5

Oct 31/04

55-30-00

201 thru 203

May

55-40-00

201 thru 205

May 1/08

A24

Pages

1/08

55-LOEP

May 1/08Page

1

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

HORIZONTAL STABILIZERS

MAINTENANCE PRACTICES

RECOMMENDED MATERIALS The recommended materials listed

(Ref. Chart 201) as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification may be used subject to availability. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance to the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE REQUIREMENTS OF THE SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART.

Only

the basic number of each

specification

revision. It is the

responsibility

specification prior

to usage of the

is listed. No

of the technician

product

attempt has been made

to

update

the

listing

to the latest

mechanic to determine the current revision of the

or

listed. This

can

be done

by contacting

the

supplier

applicable

of the product to be

used.

Chart 201

Recommended Materials Material

Specification

i. Methyl Propyl Ketone (Supersedes Methyl Ethyl Ketone)

Product

Supplier

A-A-59282

2. Sealer

Devcon "F"

Obtain

Locally

Devon

Corp

59 Endicott St

Danvers, MA 01923

HORIZONTAL STABILIZER REMOVAL a.

Remove the

screws

which attach the center

access

plates

fairings

to the left and

right

sides of the horizontal and vertical

stabilizers. b.

Remove the

c.

Remove the elevators

d.

Remove the

rotating e.

f.

cover

(Ref. Chapter 27-30-00,

plates from

the

beacon and the upper tail

Remove the

access

plates,

Disconnect the left and and

from the left hand side of the vertical stabilizer

secure

them to

the

right

top

ELEVATOR AND

just below the horizontal

TAB).

center of the horizontal stabilizer and disconnect the

wiring

from the

fairing navigation light.

fairing

and the tail

cone

from the horizontal stabilizer.

elevator trim tab cables from the turnbuckles in the horizontal stabilizer

assembly

prevent them from falling into the vertical stabilizer.

g.

Remove the

h.

Drill out the rivets which attach the forward

i.

Drill out the rivets which attach the

j.

Remove the 8 bolts which attach the horizontal stabilizer to the vertical stabilizer.

screws

stabilizer.

which attach the aft

fairing

to the horizontal stabilizers and

fairing

fairing angles

remove

the

fairing.

to the vertical and horizontal stabilizers and remove the

fairing.

to the horizontal and vertical stabilizer intersection.

55-1 0-00

Page

yaM102

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE: When attach

k.

removing the bolts, carefully remove the shims from between the points so they will not be inadvertently dropped into the vertical

Remove the horizontal stabilizer

assembly

from the

horizontal and vertical stabilizer stabilizer.

airplane (Ref. Figure 201).

HORIZONTAL STABILIZER INSTALLA TION a.

Position the horizontal stabilizer stabilizer to the

on

the vertical stabilizer and install the 8 bolts which attach the horizontal

airplane.

NOTE: Before the bolts

are tightened, measure the gap at the attach points. If the gap exceeds .014 inch, install P/N 101-600012-3 laminated shims at the forward vertical stabilizer spar and P/N 101-600012-5

b.

c.

d.

laminated shims at the

rear

Torque the forward bolts to 205 pounds of torque applied to the

bolt.

Install and rivet the

g.

necessary.

inch-pounds. Aftertorquing,

fairing angles

the bolts must not rotate under 100

the bolts must not rotate under 175

160 inch-

215 inch-

to the horizontal and vertical stabilizer intersection with MS20426AD3 rivets

appropriate length.

Install and rivet the forward

Cherrylock f.

as

Torque the rear bolts to 350 430 inch-pounds. After torquing, pounds of torque applied to the bolt.

of e.

245

spar

rivets

fairing to the horizontal and vertical stabilizers with NAS1739-1 (or equivalent Cherrymax rivets) of the appropriate length.

Install and attach the

rear

Route the trim tab cables

fairing over

to the horizontal and vertical stabilizers with the

the

pulleys

and into the left and

right

existing

or

NAS17388

screws.

horizontal stabilizers and connect them to

turnbuckles. h.

Install the elevators

i.

Rig

j.

the elevators and elevator trim tabs

Install cover,

Figure

May 1/08Page

(Ref. Chapter 27-30-00,

202

access

ELEVATOR AND

TAB).

(Ref. Chapter 27-30-00, ELEVATOR

plates and fairings and

the tail

cone

to

complete

AND

TAB).

the horizontal stabilizer installation

(Ref.

20 1

55-1 0-00

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

4

DETAIL

s

A

A 1. FORWARD

SHIM

2. AFT SHIM 3. BOLT 4. WASHER 5. NUT

I

B 8

cn~laza

Horizontal Stabilizer Removal and Installation

Figure

A24

201

55-1 0-00

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C ~AINTENANCE MANUAL

ELEVATOR

MAINTENANCE PRACTICES

ELEVA TOR BALANCING After

repainting and/or repair, the finished elevator must be check balanced to ensure that its static moment about hinge line is within the prescribed limits. The static moment for all completed elevator assemblies must fall within the range of 1.60 inch-pounds nose heavy to 0.80 inch-pounds tail heavy at the measured moment about the hinge line (Ref. Figure 1). The static moment of the elevator is determined by multiplying the unbalanced weight of the elevator assembly times the perpendicular distance from the hinge centerline to the center of gravity when the chord line is horizontally level. The weight is measured in pounds and the distance in inches. The static moment of a 100 percent balanced elevator assembly is 0.0 inch-pounds. Tail heaviness indicates static underbalance while nose the

heaviness indicates static overbalance.

CHECKING BALANCE completely assembled in flying condition. All painting, including stripes and touch-up, must be completed. The tab, tab pushrod, static wicks, and hinge bolts must be attached. The chord line must be horizontally level and the hinge line must be properly supported when the static moment is measured. Although many different methods of check balancing exist, they can be categorized under the following two headings:

The balance must be checked in

a.

Counterbalancing

The

draft-free

a

application

of

a

known force

counter the unbalance moment of the elevator

b.

Actual Force Measurement a

Counterbalancing

is the

weight

or

simplest

at a measured distance from the

hinge

line to

assembly.

Measurement of the force

known distance from the centerline of the

NOTE:

with the elevator

area

applied by the

elevator surface

on a

single support

at

hinge.

method of check

balancing.

BALANCING PROCEDURES WARNING:

Airplanes using adjustment weight attachment screws must replace them with adjustment weight attachment bolts while performing these procedures (Ref. Figure 1). Refer to Chart 1 for appropriate adjustment weight attachment bolts.

EQUIPMENT REQUIRED TO PERFORM CHECK BALANCING BY FORCE MEASUREMENT METHOD a.

A stand with knife

b.

A certified beam balance calibrated in units of 0.01 Ibs

and its

capacity

c.

A support

d.

A

edge supports (Ref. Figure 1).

should

equal

tare

plus

The knife or

edges

rule and

spirit

same

less. The balance should have

a

horizontal flat

plane.

weighing platform

2.0 Ibs minimum.

spindle similar to the illustration and leveling blocks,

straight edge,

should be in the

as

required (blocks

spindle

tare).

level.

FORCE MEASUREMENT METHOD a.

Locate the chord line on

the

hinge

marker, such

A17

by placing

a

straightedge

at the inboard end of the elevator

centerline and the other end is centered as

grease

pencil,

then

remove

the

trailing edge. the straightedge. on

assembly

so

that

Mark the chord line with

55-20-00

one a

end is

suitable

I

Ray~heon

nircrart

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

hinge centerline is not openly visible, it can be located as follows: With the hinge clevis properly aligned and tightened, locate the center of the clevis mounting bolt on the top of the elevator (covered with a plug button) as a reference point. The hinge line is 1.13 inches forward of this reference point. Mark the hinge line with a grease pencil.

NOTE: While the

b.

Fit correct size bolts in the outboard and center Ensure that it is free to rotate about the

c.

Place if it is

d.

hinge

brackets and mount the elevator

hinge

a small platform scale under the trailing edge if the control surface nose-heavy.

e.

spirit

line and level it

the knife

level and rule

are

edges.

tail-heavy or under the leading edge

by extending

or

contracting

the

under the leading edge of procedure. Hold a spirit level spindle, or by using blocks and shims or

perpendicular distance from the hinge centerline to the point supported by the spindle.

Measure the the

f.

is

Place the upper end of the spindle under the trailing edge of tail-heavy surfaces nose-heavy surfaces. The spindle must be vertical throughout the balancing

the

against the marked chord under the spindle.

on

line.

removed from the surface and read the reaction

on

Ensure that

the beam balance.

Calculate the static unbalance moment M from the formula: M

D(R-T) inch-pounds where,

D

Perpendicular distance from the hinge centerline

R

Reaction

T

Tare, i.e. spindle plus leveling blocks

(pounds)

to the

spindle point (inches).

read from the beam balance. or

shims

on

the scale

platform (pounds).

EXAMPLE

D is 10.0 inches, R is 1.100 M

10.0

(1.100-1.000);

pounds

M =1.00

and T

1.000

pound

inch-pound.

M is within the prescribed range which is satisfactory. If M is not within the the COUNTERBALANCING METHOD procedures in this chapter.

prescribed

range, refer to

Step j.

of

EQUIPMENT REQUIRED TO PERFORM CHECK BALANCING BY COUNTERBALANCING METHOD

edge supports (Ref. Figure 1).

a.

A stand with knife

b.

A paper cup

c.

Approximately0.5 poundof

d.

A certified beam balance

e.

A

or

similar

straight edge, ruler,

light weight

edges

must be in the same horizontal

plane.

container.

leadshot.

weighing

and

The knife

device calibrated in units of 0.01

pound

or

less.

spirit level.

COUNTERBALANCING METHOD a.

by placing a straightedge at the inboard end of the elevator assembly so that one end is hinge centerline and the other end is centered on the trailing edge. Mark the chord line with a suitable marker, such as grease pencil, then remove the straightedge.

Locate the chord line on

Oct

31/04Page

the

2

55-20-00

nl7

Raytheon

AiKraft

Company

SUPER KING AIR B3GO/B3OGC MAINTENANCE MANUAL

NOTE: While the

hinge centerline is not openly visible, it can be located as follows: With the hinge clevis properly aligned and tightened, locate the center of the clevis mounting bolt on the top of the elevator (covered with a plug button) as a reference point. The hinge line is 1.13 inches forward of this reference point. Mark the hinge line with a grease pencil.

b.

Secure the trim tab in its neutral

c.

Fit the correct size bolts in the

1). Ascertain d.

position

with

a

small

hinge devises and

piece

of

masking tape.

mount the elevator

that the elevator is free to rotate about the

hinge

on

the knife

edge supports (Ref. Figure

line.

To determine if

adjustment weights should be added or removed, suspend a paper cup from a point near the trailing edge if the balance is nose down or near the inboard end of the balance weight assembly on the elevator leading edge if the balance is tail down. Use a short length of small diameter string secured to the surface with a small piece of masking tape (Ref. Figure 1). The cup must be free to hang vertically.

center of the elevator

e.

Add small

holding f.

quantities of lead shot

the

Carefully

spirit

level

measure

aligned

the

to the cup until the elevator balances with the chord line level. Check this

by

with the marked chord line.

perpendicular

distance D within 0.1 inch from the

hinge

centerline to the

point

of

suspension of the cup. g.

Remove the cup, contents, and NOTE: Since any

carefully h.

weighing

on

error

scales that

then

string,

weigh

them to within 0.05

magnified by the

is

are

distance D,

pound.

weighing

is most

important

and must be done

certified for accuracy.

Calculatethestatic balanceasfollows: The

weight of

the cup and contents is

designated by W.

The distance between the centerline of the The

over or

underbalance moment is

hinge

and the

designated by

suspension point of the cup is designated by D.

M.

M=WxD i.

The

following (nose-heavy)

is

a

typical example

of

and the paper cup was line level at W O.lGO-pound and D M

0.100 x13.8

M

1.38

balancing calculation: Assume the elevator is slightly overbalance suspended from the trailing edge. If the elevator balances with the chord

a

13.8

inches, then...

inch-pounds (The product of W x D must be accurate to within required static balance range and is therefore acceptable.

0.05

inch-pounds).

In this instance M

I

is within the

j.

If the static balance does not fall within the range of 1.60 inch-pounds nose-heavy (overbalance) to 0.80 inch-pounds tail-heavy (underbalance), adjustment weights must be added or removed and the balance

rechecked. NOTE: A maximum of four small

adjustment weights (P/N 101-610026-5)

and

seven

large adjustment weights

(P/N 101-610026-7) may be added or removed from the balance weight assembly on the outboard leading edge of the elevator. The steel cover plate must be installed over the adjustment weights with NAS6703HUXX bolts (Ref. SE 27-3187). Bolt

lengths vary with the number of weights installed. Refer plates are located inside the elevator assemblies to inch-pounds then safety wired with MS20995C32 wire.

to Chart 1 for the proper attachment bolts. Nut

anchor the bolts. Bolts

m7

are

torqued

20 to 30

55-20-00

oS~X:

I

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BALANCE WEIGHT ASSEMBLY PLATE

COVER

MASKING

TAPE

(PLACE NEAR ELEVATOR HINGE LINE)

DETAIL

MASKING TAPE

B

e-

DETAIL

CONTAINER

A

SMALL ADJUSTMENT WEIGHTS iOi-610026-5 ATTACHMENT BOLTS LARGE ADJUSTMENT WEIGHTS 101-610026-7

MASKING

C F

TAPE

ONTAINER

(NEAR ELEVATOR HINGE LINE)

KNIFE

DETAIL

F1

U

C

/EDGE O

ED

U

ELEVATOR HINGE CLEVIS

B E MASKING

TAPE

(TO SECURE TAB IN NEUTRAL)

I~

MUST

ACTUAL

BE

FORCE

HORIZONTALLY

LEVEL

MEASUREMENT

METHOD

JIG

MUST BE HORIZONTALLY LEVEL FOR OVERBALANCE CHECK

VIEW

D

-´•´•4s~-

I

I JIG

JIG

DETAIL

E-E

MUST BE HORIZONTALLY LEVEL FOR UNDERBALANCE CHECK

VIEW

F-F

Elevator

Balancing Figure 1

Oct

55-20-00

A17

Raytheon

Aireraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

Adjustment Weights No. of

Weights Peg. for Balancing

Combination

Attachment Bolts

Combination

Weights Beg. P/N I Weights Peg.

Number of

P/N

Number of

Part Number of

Washers

Bolts for Each

Per Elevator

Peg. Per Bolt

Elevator

Bolts

Beg.

101-610026-5

101-610026-7

(Small Weight)

(Large Weight)

1

1

O

2

0

NAS6703HU12

2

2

0

2

0

NAS6703HU13

I

I

2

2

0

2

1

NAS6703HU14

I

I

3

3

0

2

0

NAS6703HU14

I

I

4

4

0

2

0

NAS6703HU15

I

4

4

0

2

1

NAS6703HU16

I

5

4

1

2

0

NAS6703HU16

6

4

2

2

0

NAS6703HU17

I

6

4

2

2

1

NAS6703HU18

I

7

4

3

2

O

NAS6703HU18

I

8

4

4

2

0

NAS6703HU19

I

I

8

4

4

2

1

NAS6703HU20

I

I

9

4

5

2

0

NAS6703HU20

10

4

6

2

0

NAS6703HU21

10

4

6

2

1

NAS6703HU22

I

I

11

4

7

2

0

NAS6703HU22

I

I

NOTE: Based

on

availability

it is

permissible to

use

1

the next

I

I

P/N NAS 1 149C0363R

grip length bolt and add one using the odd part numbered

washer under the head of the attachment bolts, instead of

A17

I

55-20-00

I

bolts.

Oct

31/04Page

5

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

VERTICAL STABILIZER

VERTICAL STABILIZER REn/lOVAL

navigation light.

and disconnect the tail

a.

Remove the tail

b.

Remove the rudder

c.

Remove the elevators and the horizontal stabilizer

d.

Remove the

e.

Disconnect the rudder tab, elevator and elevator tab cables from the turnbuckles in the tail section.

f.

Remove the rudder

g.

Drill out the rivets which attach the short aft dorsal fin section to the main dorsal fin

fuselage; h. i.

access

then

(Ref. Chapter 27-20-00).

plates

push

remove

from the left and

it from the

Remove the vertical stabilizer remove

Carefully

right

assembly (Ref. Chapters

27-30-00 and

sides of the vertical stabilizer

rods from the control horns and the torque shaft

55-10-00).

assembly (Ref. Figure 201).

assembly. assembly

and the aft

airplane.

Drill out the rivets which attach the

and

j.

cone

fuselage/vertical

attaching

stabilizer fillet to the

bolts from the main and

rear

fuselage.

spars and from the aft

fuselage

structure

the shims.

lift the vertical stabilizer

assembly

from the

fuselage.

VERTICAL STABILIZER INSTALLATION a.

b.

Using methyl propyl ketone (Item No. 1, Chart 1, 55-10-00), clean all existing sealer from the vertical stabilizer fillet, the aft fuselage area of attachment of the vertical stabilizer, and from the area around each rivet hole in the fairing. Position the vertical stabilizer

on

the aft

fuselage (Ref. Figure 201)

and install the

attaching

bolts

through

the

main and rear spars and the fuselage structure. Shim the attach points as necessary with laminated shims (P/N 101-600012-1) to a maximum gap of .020 inch between the spars and their respective attach points.

Torque c.

all bolts to 100

inch-pounds.

Attach the vertical stabilizer fillet to the size and

d.

140

fuselage with

MS20426AD and MS20470AD rivets of the

appropriate

length. assembly and the aft fuselage with CR2248-4 appropriate length. Install each Cherrylock rivet with

Install and rivet the small dorsal fin section to the main dorsal fin

Cherrylock

rivets

(or the equivalent Cherrymax rivets)

of the

Devcon "F" while Devcon is still wet.

assembly and the elevators (Ref. Chapters

55-10-00 and

e.

Install the horizontal stabilizer

f.

Install the rudder

push rods

g.

Install the rudder

(Ref. Chapter 27-20-00).

h.

Connect all elevator, elevator trim and rudder trim cables to the turnbuckles in the

i.

Rig the elevators, 27-20-00).

~a4

on

the rudder control horns and the

elevator trim tabs, rudder and rudder trim tab

27-30-00).

torque shaft assembly.

(Ref. Chapters

fuselage

tail.

27-30-00 and

55-30-00

1/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

j.

Connect the tail

fuselage

Page

navigation light

and insta\\ the tail

cone

and the

access

plates

on

the left and

right

side of the

tail.

55-30-00

a24

Corporation

Hawker Beechcraft

MAINTENANCE MANUAL SUPER KING AIR B300iB300C

f ’A

00

9

00

000 14

O

14 1 10

15 16

11

B DETAIL

DETAIL

C

A

3 2

3

1

BOLT

2

WASHER

3. NUT 4. UPPER AFT SHIM 5

C

UPPEA FORWARD SHIM

2

3

6. LOWER AFT SHIM 7

LOWER FORWARD SHIM

8. DRAIN INSTRUCTION DECAL 9

u,

DORSAL FIN RIVETS

10

AF;T DORSAL FIN

11

FILLET

12

FILLET RIVETS

1 2 6

13. VERTICAL STABILIZER 14

HORIZONTAL STABILIZER

15. RUDDER

16

2 3

3

2

MAIN DORSAL FIN

DETAIL

B

300´•134-8

Installation Vertical Stabilizer Removal and 201 Figure

55-30-00 A24

yaM302

Page

1108

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RUDDER

MAINTENANCE PRACTICES

RUDDER BALANCING After

repair, the finished rudder (Ref. Figure 201), must be check balanced to make sure that its hinge line is within the prescribed limits. The static moment for all completed rudder assemblies must fall within the range of 3.00 pound-inches nose heavy to 3.00 pound-inches tail heavy at the measured moment about the hinge line. The static moment of the rudder is determined by multiplying the unbalanced weight of the rudder assembly times the perpendicular distance from the hinge centerline to the center of gravity when the chord line is horizontally level. The weight is measured in pounds and the distance in inches. The static moment of a 100% balanced rudder assembly is 0.0 pound-inches. Tail heaviness indicates static

repainting

and/or

static moment about the

underbalance while

nose

heaviness indicates static overbalance.

CHECKING BALANCE a draft-free area with the rudder completely assembled in flying condition. All touch-up must be completed. The tab, tab pushrod, static wicks and hinge bolts must be attached. The chord line must be horizontally level and the hinge line must be properly supported when the static moment is measured. Although many different methods of check balancing exist, they can be categorized under the following two headings:

The balance must be checked in

painting, including stripes

a.

Counterbalancing

and

The

application

of

a

known force

counter the unbalance moment of the rudder

b.

Actual Force Measurement

Measurement of the force

known distance from the centerline of the

NOTE:

Counterbalancing

is the

or

simplest

weight

at

measured distance from the

a

hinge

line to

assembly. applied by

the rudder surface

on a

single support

at a

hinge.

method of check

balancing.

EQUIPMENT REQUIRED TO PERFORM CHECK BALANCING a.

A stand with

knife-edge supports (Ref. Figure 201).

b.

A paper cup

or

c.

Approximately

d.

A certified beam balance

e.

A

similar

1/2

straightedge,

light weight

pound

ruler and

The knife

edge

must be in the

same

horizontal plane

container.

of lead shot.

weighing spirit

device calibrated in units of 0.01

pounds

or

less.

level.

BALANCING PROCEDURE COUNTERBALANCING METHOD a.

Locate chord line

by placing

a

straightedge

at the lower closure rib of the rudder so that

the center of the torque tube while the other end is centered on the trailing suitable marker, such as a grease pencil, then remove the straightedge. NOTE: While the

hinge

centerline is not

openly visible,

it

can

be located

as

edge.

follows: Use

of rivets adjacent to the bottom hinge line as a reference line. The forward of this reference line. Mark the hinge line with a grease pencil. the center

nz4

row

one

end is

aligned

Mark the chord line with

with a

grease pencil to mark hinge line is 0.89 inch

a

55-40-00

Page

yaM102

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

b.

Secure the trim tab in its neutral

position

c.

Fit the correct-sized bolts in the

hinge

201).

with

a

small

piece

of

masking tape.

brackets and mount the rudder

Ascertain that the rudder is free to rotate about the

hinge

on

the

knife-edge supports (Ref. Figure

line.

d.

adjustment weights should be added or removed, suspend a paper cup from a point near the center of the rudder trailing edge if the balance is nose down or near the center of the leading edge if the balance is tail down. Use a short length of small diameter string secured to the surface with a small piece of masking tape (Ref. Figure 201). The cup must be free to hang vertically.

e.

Add small

To determine if

holding

a

quantities of lead shot to the cup until the rudder balances with spirit level aligned with the marked chord line.

f.

Carefully measure the perpendicular suspension of the cup.

g.

Remove the cup, contents and

distance "D" within 0.1 inch from the

string,

then

weigh

them to within 0.05

the chord line level. Check this

hinge

centerline to the

point

by

of

pounds.

Chart 201 ADJUSTMENT WEIGHTS ATTACHMENT SRCREWS Number of

Number of Screws

Weights Necessary for Balancing

weights

0

1

or

2

2

AN3-4A

3

or

4

2

AN3-5A

5

or

6

2

AN3-6A

7

or

8

2

AN3-7A

identical. Read

are

NOTE: Since any

carefully h.

Part Number of Screws for each Installation

0

All

Required

weighing

on

across

error

scales that

is

are

from the left column to determine number and type of

magnified by

the distance "D"

weighing

is most

screws

important and

for installation.

must be done

certified for accuracy.

Calculatethestatic balanceasfollows: of the cup and contents is

designated by

1.

The

2.

The distance between the centerline of the

3.

The

4.

M=WxD.

5.

The

M

0.150

weight

over or

and the

designated by

suspension point of

the cup is

designated by

"D".

"M".

following is a typical example of a balancing calculation: Assume the rudder was slightly underbalance (tail heavy) and the paper cup was suspended from the leading edge. If the rudder balances with the chord 8.3 inches", then: 0.150 pound" and "D line level at "W

M =1.25

Page

yaM202

underbalance moment is

hinge

"VV".

1/08

x

8.3

pounds-inches

55-40-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

In this

(The product of "W" x "D" must be accurate to within 0.05 pounds-inches). required static balance range and is therefore acceptable. i.

If the static balance does not fall within the range of 3.00

inches tail

heavy (underbalance), adjustment weights

pound-inches

nose

instance, "M" is within the

heavy (overbalance)

to 3.00

pound-

must be added or removed and the balance rechecked.

NOTE: Balance may be adjusted by adding or removing P/N 101-630017-1 weights. A maximum of 16 adjustment weights are allowed. Eight of the adjustment weights are secured to the forward end of the lower closure rib with two screws, the last

weight

to be

a

P/N 101-630015-1. Nut

plates

are

located

on

the rib to anchor

the screws. if necessary, an additional eight adjustment weights may be installed on the rib at Canted Station 34.59, with the last weight being P/N 101-630015-1 (Ref. Chart 201) for screw sizes.

RUDDER TRIM MOISTURE DRAIN INSPECTION a.

Deflect the rudder trim tab

b.

Visually inspect

opening at trailing edge of the

Make

sure

rudder

nn~

the trim tab control.

trailing edge of the closure rudder (Ref. Figure 202). remove

any

excess

rib. The

triangular opening

sealant, adhesive,

or

foreign

should extend

material which

drainage.

of proper drainage by introducing approximately 1/2 cup of water into the opening at the top of the with a squeeze bottle. Confirm that water flows freely from the triangular opening at the

trailing edge

bottom of the rudder e.

using

the

Inspect the opening for obstructions and interferes with proper

d.

to one side

the drain

3/8 inch from the c.

fully

trailing edge.

Return the rudder trim tab to the neutral

position.

55-40-00

PMa 9ye:10 ~May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

C~

MASKING TAPE (NEAR RUDDER HINGE LINE)

1

ATTACH SCREWS

101-630015-1 ADJUSTMENT WEIGHTS (8 MAXIMUM)

DETAIL

A

CONTAINER KNIFE EDGE

D MASKING TAPE TO SECURE TAB 1N NEUTRAL

MASKING RUDDER HINGE

RAEN(EPAT

LINE)

RUDDER HINGE CLEVIS

CONTAINER

~e DETAIL

DETAIL

C

B

CONTAINER

CONTAINER

JIG MUST BE HORIZONTALLY LEVEL

JIG MUST BE HORIZONTALLY LEVEL

STATIC OVERBALANCE

nan

STATIC UNDERBALANCE ITAIL HEAVY)

(NOSE HEAVY)

D~D

lnea

20013~(

E-E

Balancing Figure 201

Rudder

Page

yaM402

1/08

55-40-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SKIN

OF!IUZn~

-RIANGULAR FC~ DRAINAGE

i’

RUDG_R TRAIING EDGE

~2:x-r

3/8

I)UDCc?

VIEW

INCH

SKIN

LOO~INZ

JP

AT

IM~EDIATELY

RIB

AGCV~

iA3 295’27831 %5

Rudder Trim Tab Moisture Drain

Figure

Inspection

202

ORIGINAL As Received

By

ATP

A24

55-40-00

1/08

C H A PT E R

VVINDOVVS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 56 - WINDOWS TABLE OF CONTENTS SUBJECT

PAGE 56-00-00

Windows - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Cleaning Plastic Windows. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Cleaning Electrochromic Window Shades . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Precautions Required when Stripping, Painting or Degreasing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Removing Paint from Windshields . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Cleaning Windshields . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Wedge Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Hollow Drill Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Drill Bushing Fabrication. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 56-10-00 Windows - Crew Compartment Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Windshield Seal Inspection and Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Windshield Antistatic Coating and Tab Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .202 Bonded Antistatic Tab Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Antistatic Tab Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205 Windshield Replacement Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Windshield Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Windshield Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .207 Storm Window Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Storm Window Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .212 Storm Window Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Storm Window Seal Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Storm Window Seal Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Storm Window Stop Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Crew Compartment Side Window Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 Crew Compartment Side Window Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .214 56-15-00 Window Inspection and Repair Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Crew Compartment, Cabin, and Baggage Windows. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Acrylic Window Refurbishing Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Inspection and Repair of Window Attach Frames . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .205

A27

56-CONTENTS

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 56 - WINDOWS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 56-20-00

Cabin Windows - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Electrochromic Window Shades (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . . 1 Cabin Windows - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cabin Outer Window Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Cabin Outer Window Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Polarized Window Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Polarized Window Disassembly (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Polarized Window Assembly (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205 Polarized Window Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 207 Electrochromic Window Shade Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 207 Electrochromic Window Shade Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 208 Electrochromic Window Shade Controller Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 208 Electrochromic Window Shade Controller Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 208 Emergency Exit Polarized Window Removal (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) . . . . . . . . . . . . . . . . . 210 Emergency Exit Polarized Window Installation (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed) . . . . . . . . . . . . . . . . 211 Emergency Exit Electrochromic Window Shade Removal (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 211 Emergency Exit Electrochromic Window Shade Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) . . . . . . . . . . . . . . . . . . . . . . 211 Vestibule Window Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 212 Vestibule Window Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 213 Baggage Compartment Window Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 214 Baggage Compartment Window Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 214

Page 2 Feb 1/10

56-CONTENTS

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

56-LOEP

1

Feb 1/10

56-CONTENTS

1 and 2

Feb 1/10

56-00-00

201 thru 206

Feb 1/10

56-10-00

201 thru 216

Nov 1/07

56-15-00

201 thru 206

May 1/07

56-20-00

1 and 2 201 thru 216

Feb 1/10 Feb 1/10

A27

56-LOEP

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200 56-00-00

WINDOWS - MAINTENANCE PRACTICES CLEANING PLASTIC WINDOWS CAUTION: To avoid obstruction of vision or damage to the clear urethane anti-fog coating, do not use plexiglass cleaners on the inner surfaces of the crew compartment side windows. Use only glass cleaner (1, Chart 202, 56-00-00) or a solution of warm water and mild, non-abrasive liquid detergent (2, Chart 202, 5600-00) and wipe with a clean, soft cloth or a clean, damp chamois. Do not use these cleaners on the uncoated exterior surfaces of the crew compartment side windows or on either surface of the cabin outer windows. Keep the plastic cabin windows and the exterior surfaces of the crew compartment windows clean and waxed at all times. Use only approved plexiglass cleaners (3, Chart 202, 56-00-00). To prevent scratches and crazing, wash the windows carefully with plenty of mild detergent and water. Use the palm of the hand to feel and dislodge dirt and mud. A soft cloth, chamois, or sponge may be used, but only to carry water to the window surface. Rinse the window thoroughly, then dry it with a clean, moist chamois. Rubbing the surface of the plastic window with a dry cloth will serve only to build up an electrostatic charge that attracts dust. Remove oil and grease with a cloth moistened with kerosene (4, Chart 202, 56-00-00). Never use gasoline, benzine, alcohol, acetone, carbon tetrachloride, fire extinguisher, anti-ice fluid, lacquer thinner, or glass cleaner. These liquids will soften the plastic and may cause crazing. After all dirt and grease have been removed from the window, apply a good grade of paste wax (5, Chart 202, 5600-00) or the preferred polish (3, Chart 202, 56-00-00) to the window to fill in minor scratches and help prevent additional scratches or chemical damage. Apply a thin, even coat of polish or wax and bring it to a high polish by rubbing lightly with a clean, dry, soft flannel cloth. Change the cloth frequently to avoid a buildup of gritty particles. Never use a power buffer; the heat generated by the buffing pad may soften the plastic. Acrylic windows are extremely susceptible to damage during painting, stripping, and fuselage cleaning operations. Improper protection of the acrylic windows can cause severe chemical damage which will result in reduced service life and structural failure of the acrylic. Functional fluids, such as deicing, hydraulic, etc., are also detrimental to the acrylic windows. Depending on the type of chemical involved, the damage to the window which results from such contacts may not be evident for months; therefore, it must be stressed that all recommended cleaning procedures be complied with and that only the approved window cleaning products be utilized.

CLEANING ELECTROCHROMIC WINDOW SHADES To clean the outer glass surface of the electrochromic window shades use a 50/50 mix of isopropyl alcohol and water solution with a soft clean cloth. Use only approved plexiglass cleaners (3, Chart 202, 56-00-00) to clean the inside frost pane.

PRECAUTIONS REQUIRED WHEN STRIPPING, PAINTING OR DEGREASING Paint, paint strippers, degreasing compounds, and most solvents will seriously damage acrylic windows. If any of these functions are to be performed in the vicinity of the windows, the windows must be completely sealed against the chemical compounds and fumes. Pressure sensitive polyester film (mylar) and pressure sensitive painting/ stripping masks of polyester, aluminum, and other composite materials are commercially available for this purpose. When installed, the mask must extend beyond the window cutouts in the skin. This will prevent the chemical compounds from attacking the window edges. If paint is inadvertently applied to the windshield glass during airplane repainting, remove the paint as instructed in REMOVING PAINT FROM WINDSHIELDS.

A27

56-00-00

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

REMOVING PAINT FROM WINDSHIELDS a. Mask the acrylic crew compartment side windows and the paint on the airplane skin to prevent damage from the solvent. CAUTION: The acrylic side windows are extremely susceptible to damage from solvents. To prevent damage, use care not to contact the acrylic windows or the airplane paint with the methyl propyl ketone or other solvent. To avoid damage to the windshield anti-static coating, never use any rubbing compound or polish, or any substance containing acid, on the windshield. b. If the paint on the windshield is dry, contact the Hawker Beechcraft Corporation Technical Support for consultation. c.

If the paint on the windshield is still wet, use a clean, soft cloth dampened with solvent (9, Chart 202, 56-00-00) to remove the paint. Wipe the glass surface in a straight rubbing motion. Never use any abrasive materials or acids to remove the paint.

d. Rinse the glass thoroughly and dry, but do not apply wax.

CLEANING WINDSHIELDS a. Wash excessive dirt and other substances from the glass with clean water. b. Wash the windshield clean with mild soap and water or with a 50/50 solution of isopropyl alcohol (6, Chart 202, 56-00-00) and water or Prist acrylic plastic and glass cleaner (24, Chart 202, 56-00-00). Wipe the glass surface in a straight rubbing motion with a soft cloth or sponge. Never use any abrasive materials or strong acids to clean the glass. c.

Rinse the glass thoroughly and dry, but do not apply wax.

NOTE: It is essential that windshield wipers be kept clean. Grit trapped by the wipers is the most common source of scratches in the glass. Do not attempt to polish such nicks and scratches out of the glass surface.

SPECIAL TOOLS AND RECOMMENDED MATERIALS The special tools and recommended materials listed in Charts 201 and 202 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used. WEDGE FABRICATION A plastic wedge is used to pry up the fiberglass cover tab over the windshield anti-static tab. Make the wedge from stretched acrylic or plexiglass stock at least 1/2 inch thick. Bevel one end sharply enough to slip under the fiberglass cover tab.

Page 202 Feb 1/10

56-00-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL HOLLOW DRILL FABRICATION A hollow drill is used to cut clearance holes for screws through the sponge rubber strips attached to the windshield. Make the drill from a 3-inch length of steel tubing of 0.064-inch inner diameter. Sharpen the outer edge of one end to cut the rubber. DRILL BUSHING FABRICATION A drill bushing is used to act as a support and guide for the hollow drill. Make the bushing from aluminum tubing slightly shorter than the 3-inch hollow drill, with an inner diameter sufficient for insertion and rotation of the hollow drill and an outer diameter which will fit freely into the screw holes in the windshield. Insert the drill and bushing into a windshield screw hole as a test to ensure that the drill will not bind in the holes.

Chart 201 Special Tools ITEM

TOOL NAME

PART NO.

USE

Barfield

Test resistance of windshield anti-static coating.

Plastic wedge

Fabricate locally

Pry up fiberglass cover over anti-static tab.

3.

Pencil type soldering iron (40 watt)

Obtain locally

Apply solder to anti-static tab wires

4.

Hollow drill

Fabricate locally

Cut screw holes in windshield sponge rubber seal.

5.

Drill bushing

Fabricate locally

Support and guide hollow drill.

6.

Orbital sander

Obtain locally

Refurbish acrylic cabin windows.

1.

Ohmmeter (capable of registering over 100 million ohms (100 megohms))

2.

A27

2548H

SUPPLIER

56-00-00

Page 203 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 202 Recommended Materials ITEM

MATERIAL

SPECIFICATION

PRODUCT

SUPPLIER

1.

Glass Cleaner

Windex

Drackett Products Co. Cincinnati, OH 45232

2.

Liquid Detergent, NonAbrasive

Lux, Joy

Obtain Locally

3.

Acrylic Plastic Polish and Cleaner

Part No. 403D

Permatex, Inc. Kansas City, KS 66115

Clearview AVL-CV-16

Aviation Laboratories 5401 Mitchelldale #B6 Houston, TX 77092

Meguiars MGH-10

Meguiar’s Inc. P.O. Box 17177 Irvine, CA 92614

4.

Kerosene

5.

Paste Wax

Fed. Spec. P-P-560

VV-K-211

Obtain Locally Johnson’s J-Wax Paste

S. C. Johnson & Son, Inc. 1521 Howe St. Racine, WI 53403

Simonex

Simonex Co. P.O. Box 368 Greenville, SC 29602

6.

Isopropyl Alcohol

TT-I-735 or MIL-I-10428A

Obtain locally

7.

Naphtha

TT-N-95

Obtain locally

8.

Sealer

9.

Methyl Propyl Ketone

10.

Copper Foil Tape

3M1181

3M Industrial Adhesives & Tape Division 3M Centre 900 Bush Ave St. Paul, MN 55144

11.

Primer

SS4179

Momentire Performance Materials Co. Silicone Products Waterford, NY 12188

Page 204 Feb 1/10

56-00-00

RTV-732

Dow Corning 3901 S. Saginaw Rd. Midland, MI 48641 Obtain locally

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 202 Recommended Materials (Continued) ITEM

MATERIAL

SPECIFICATION

PRODUCT

SUPPLIER

12.

Electric Grade Silicone Rubber

RTV-162

Momentire Performance Materials Co. Silicone Products Waterford, NY 12188

13.

Tape, Conductive Adhesive MIL-T-47012 Foil

1126

3M Industrial Adhesives & Tape Division 3M Centre 900 Bush Ave St. Paul, MN 55144

14.

Sealer

Technit 72-00002

Technical Wire Products, Inc. 129 Dermody St. Crawford, NY 07016

15.

Adhesive

RTV-732

Dow Corning 3901 S. Saginaw Rd. Midland, MI 48641

16.

Sealer

PR-1425B-1/2 (PR-1425B-2 acceptable as an alternative)

PRC-Desoto International, Inc. P.O. Box 1800 5454 San Fernando Road Glendale, CA 91209

17.

Paint Stripper

18.

Urethane Primer

10P8-11

Akzo Noble Aerospace Coatings E. Water Street Waukegan, IL 60085

19.

Adhesive

Scotch-Grip 1300L

3M Industrial Adhesives & Tape Division 3M Centre 900 Bush Ave St. Paul, MN 55144

20.

Plastic Window Scratch Remover

MA-1Kit

MicroSurface Finishing Products 1217 W. 3rd Street Wilton, IA 52778

21.

Epoxy Adhesive

EA9309 PT

Hysol Div. of The Dexter Corp. P.O. Box 312 2850 Willow Pass Rd. Pittsburg, CA 94565

22.

Lubricant, Stainless Stick

Door-Ease

American Grease Stick Company 2651 Hoyt Muskegon, MI 49443

A27

D-Zolve GE15-33R

Solvent Kleene 1311/2 Lynnfield Street Peabody, MA 01960

56-00-00

Page 205 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL Chart 202 Recommended Materials (Continued) ITEM 23.

MATERIAL Sealer

SPECIFICATION

PRODUCT

SAE-AMS-S-8802 PR-1440B-1/2

SUPPLIER PRC-Desoto International, Inc. P.O. Box 1800 5454 San Fernando Road Glendale, CA 91209

NOTE Any alternate products certified to SAE-AMS-S-8802 requirements are acceptable. 24.

Prist Acrylic Plastic and Glass Cleaner

Prist #84830 13 oz. can

Prist Aerospace Products PO Box 3087 Conroe, TX 77305

25.

Primer Solution

SS4120

Regal Plastics 329 N. Indiana Wichita, 67214

26.

Adhesive/Sealer

RTV103

Regal Plastics 329 N. Indiana Wichita, 67214

27.

Adhesion Promoter

PR-142

PRC-DeSoto International, Inc. 5454 San Fernando Road Glendale, CA 91203

Page 206 Feb 1/10

56-00-00

A27

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WINDOWS

CREW COMPARTMENT MAINTENANCE PRACTICES

NOTE: Refer to DEFROST AND FLIGHT COMPARTMENT HEAT, Chapter 21-20-00 for information compartment window defogging system.

on

the

crew

WINDSHIELD SEAL INSPECTION AND REPAIR NOTE:

(translucent or milky white) or earlier type polysulfide PR-1829 (gray) weather seal is installed at replace it with the polysulfide PR-1425 ~black) weather seal according to Kit No. 101-5172. procedure that follows is applicable to the polysulfide PR-1425 weather seal only.

If silicone

the windshield, The

Inspect

the weather seal between the windshield

INSPECTION AND MAINTENANCE Tlr~lETABLE, inch

or

less, it may be repaired.

a.

Turn off all electrical power.

b.

Inspect

c.

If necessary,

the weather seal for

CAUTION:

d.

Clean the the

glass and the windshield retainer at the interval specified (Ref. Chapter 5-00-00). If the seal is damaged in areas extending 1/2

remove

debonding, cracks,

or wear

(Ref. Figure 201).

any loose material.

To prevent scratches, nicks, or cracks removing old sealant material.

damaged area naphtha evaporates.

of the seal with

to the

windshield, do not

use a

naphtha (7, Chart 202, 56-00-00). Wipe

metallic scraper when

with

a

clean, dry cloth before

OUTBOARD ALUMINUM WEATHER SEAL

GLASS

RETAINER

GLASS

PLASTIC

sssss ss530snnnl

Windshield Seal

Figure

nz3

201

56-~ 0-00Nov

1/07

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

e.

f.

To

repair the damaged

Allow the sealant to

time/temperature specified by Chapter 56-00-30).

cure

for the

Allow the sealer to NOTE: A

thoroughly

cure

before

layer of sealer 1/16-inch thick

damaged area overlapping original hump contour.

to the

to 0.250 inch. Smooth sealant to match the

by 0.125

CLEANING VidlNDSHIELD, g.

apply sealer (16, Chart 202, 56-00-00)

weather seal,

the windshield and retainer

the manufacturer. Clean the windshield

(Ref.

flight.

will

cure

in 24 hours. Thicker

layers

will

cure

in 48 to 100 hours.

WINDSHIELD ANTISTA TIC COA TING AND TAB INSPECTION

(Utilizing Inspect

an

Ohmmeter

Barfield Fuel Calibration Instrumentation P/N 2548H

or

the windshields antistatic

and tab

coating

bonding

at intervals

(Ref.

or

Equivalent.)

INSPECTION AND MAINTENANCE

TIMETABLE, Chapter 5-00-00). a.

I"

Turn off all electrical power.

00-00)

or

Prist

CAUTION:

acrylic plastic

To

If necessary,

and

to the

prevent damage

WINDSHIELDS c.

glass with a 50/50 solution of isopropyl alcohol and glass cleaner (24, Chart 202, 56-00-00).

Clean the exterior of the windshield

remove

windshield, clean the windshield

(1, Chart 201 56-00-0 0) capable of reading required for the following inspection.

Set the ohmmeter range dial

e.

Attach

f.

a

one

Chart 202, 56-

instructed in CLEANING

the finish from the windshield frame to expose bare metal.

d.

to

(6,

(Ref. Chapter 56-00-00).

NOTE: An ohm meter will be

as

water

100 megohms and

on

ohmmeter test lead to the bare metal

copper wire mesh

pad, such

Contact the windshield

glass

as a

on

Brillo scrub

with the wire mesh

adjust

in

excess

the needle

of 100 million ohms

reading

to

(1 00 megohms)

zero.

the windshield frame. Attach the other ohmmeter test lead

pad.

pad. Check the

ohmmeter

reading. If the

ohmmeter

reading

is

100 megohms or less, but more than 0 ohms in at least 10 different locations, no further action is required. If the finish was removed from a spot on the windshield frame for this test, repaint the spot to match the surrounding finish. NOTE: Do not touch the

I

pad

with

one

hand and the frame with the other hand

as erroneous

readings will

occur.

Resistance between the windshield and windshield frame should range from 5000 ohms to 100,000,000 ohms (5K ohms to 100 megohms).

g.

If the ohmmeter NOTE:

Do not

reading

remove

Beechcraft h.

If

some

of the

readings,

Page

is

more

megohms, proceed

the windshield from the

Corporation

readings

than 100

Technical

were more

20256-~ 0-00

following steps:

airplane as a result of this inspection. Support for consultation.

Contact Hawker

megohms, draw a diagram noting the locations of the Corporation Technical Support for consultation.

than 100

and contact Hawker Beechcraft

with the

excessive

n23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i.

If all the ohmmeter 1.

2.

than 100

more

megohms, perform the following

Remove the ohmmeter test lead from the wire mesh Place the ohmmeter test lead down

3.

readings were

the antistatic tab

on

the windshield

on

inspection steps:

pad.

glass

within 0.50 inch of the antistatic tab. Do not press

inspection.

this

during

antistatic tab

reading is 10 megohms or less as the lead is drawn around the antistatic tab, the antistatic providing sufficient electrical continuity between the windshield retainer and the antistatic coating on windshield glass. If the ohmmeter reading is more than 10 megohms, continue with the following steps.

If the ohmmeter

tab is the

NOTE:

4.

j.

During the following test, airplane, windshield, and

meter

that the hands and

If

probes.

Place the other wire mesh

10 different locations

If the 10 resistance

100

If intermittent

pad in readings are

megohms

on

less,

or

body

than

more

pads. Place

Connect the ohmmeter test leads to wire mesh

more

1.

ensure

one

one

are

from the

completely insulated

antistatic tab is installed, check each tab.

pad

within 0.50 inch of the antistatic tab.

the windshield and note the resistance

a new

readings.

antistatic tab must be installed.

readings of 100 megohms or less were indicated, repeat step megohms, proceed with the following steps:

"i". If all resistance

readings

were

than 100

Move the ohmmeter test lead and

pad approximately four inches away from the edge of the antistatic pad stationary on the windshield glass.

tab

and within 0.25 inch of the windshield retainer. Hold the

2.

Place the other

pad

and test lead in 10 different locations

on

the windshield and note the resistance

readings. 3.

Place

a

mark

of resistance

less, install 4.

5.

on

the windshield retainer in the

readings

a new

If ten resistance

that

were

100

antistatic tab. Center the

readings

of 100

four inches from the

the wire mesh

pad.

new

of the

stationary pad. At the mark, write the number readings were 100 megohms or

less. If all ten resistance

tab

on

the mark made

on

move

the windshield retainer.

the ohmmeter test lead

additional ten resistance

readings

with

The other ohmmeter test lead must remain within 0.25 inch of the windshield retainer.

readings of 100 readings of 100 megohms or less, install a new antistatic tab If only intermittent readings of 100 megohms or less were found, repeat step "i".

point,

megohms

less. If

NOTE:

or

mark the windshield retainer and record the number of ohmmeter

At each test

at that mark.

vicinity

megohms or less were not found, previous test point and take an

approximately

or

megohms

a

If ohmmeter

point

has ten resistance

readings of 100 megohms were not indicated at any test point, do not remove the airplane until contacting Hawker Beechcraft Corporation Technical Support for

windshield from the consultation.

BONDED ANTISTA TIC TAB REPAIR a.

Tape

off

an area

around the

fiberglass

cover

tab. The

area

should be

large enough

to

protect

the

glass

and

contain excessive sealant flow. b.

Using

the

plastic wedge (2, Chart 201 56-00-00), gently pry the fiberglass tab away from the windshield edge attachment. 1

surface.

Do not disconnect the tab from the metal c.

A23

Fold the

fiberglass

cover

tab back

over

the metal

edge

attachment and

tape

it down out of the work

56-1 0-00

area.

Page

voN302

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MAN UAL

d.

Using the plastic wedge, pry the copper tab away from the windshield surface. attaching the copper tab. Tape the tab out of the work area.

Do not break

or sever

the braided

wire

scrape the sealant from the windshield surface with the

plastic wedge.

e.

Gently

f.

Remove any residual sealant by rubbing the area with a soft cloth dampened with solvent (9, Chart 202, 56-0000). The glass may exhibit some staining that cannot be removed; however, it is not detrimental to the tape bond.

Using

pencil type soldering iron (3. Chart 201, 56-00-00), wire and separate the wire from the tab.

40-watt

a

the braided

melt the solder

attaching

the copper tab to

piece of copper foil tape (10, Chart 202. 56-00-00) 1/2 inch long.

h.

Cut

i.

Remove the tape backing, being careful not to contaminate the adhesive with body oils or dirt. Place the copper tape over the area originally used for tab bonding. Rub the tape down to the surface of the windshield with the plastic wedge.

j.

a

Position of the

a

section of wire solder

pencil soldering

of 1/8 inch. Remove the k.

I.

the center of the copper tape (installed in the previous step). Apply the tip just long enough to melt a puddle of solder with a maximum diameter

soldering

iron and the solder

tweezers

Remove any

or some

excess

taped-off

area

flux with with

a

dampened with solvent (9, Chart 202, 56-00-00). Wipe (6; Chart 202. 56-00-00).

cotton swab

isopropyl

alcohol

the interior

Thoroughly clean the bond surface of the fiberglass cover tab with isopropyl alcohol (6, Chart 202, 56-00-00). Using a cotton swab, apply a moderate coat of primer (11, Chart 202, 56-00-00) to the bond surface of the fiberglass cover tab. Allow the primer to dry for approximately two minutes. CAUTION: Use

only minimal

amounts of methyl

the adhesive bond of the copper n.

simultaneously.

other suitable tool, hold the braided wire to the top of the solder spot. Apply the tip of the soldering iron to the braided wire at the solder spot. Remove the soldering iron as soon as the solder has blended with the braided wire.

Using

of the m.

on

iron to the solder

Apply

a

1116- to 1/8-inch thick

propyl tape.

layer of electronic grade taped off area.

ketone and

isopropyl alcohol,

silicone rubber

(12:

Chart 202,

as

either could

destroy

56-00-00) over the

copper

tab and inner boundaries of the o.

Fold the cover

fiberglass

tab with the

original position and tape it in place. Apply sufficient pressure to the weather-proof seal. Allow the sealant to cure for 24 hours before removing

tab back to its

cover

tape

to

assure a

the tape. p.

Remove excessive sealant flow from the tape remove the tape.

by gently rubbing

it with the

plastic wedge. After the excessive

sealant has been removed,

q.

Clean the windshield

Page

as

instructed in this

56-~ 0-00

chapter.

n2a

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

BVS BAR

WINDSHIELD GLASS

WEATHERSEAL BVMPER

HEATED AREA

~II

I

WINDSHIELD RETAINER sus BAR ANTI STATIC TAB

ANTI-STATIC TAB F90-365-7

Windshield Antistatic Tab

Figure 202 ANTISTA TIC TAB INSTALLA TION NOTE:

Beech Kit No. 90-5048-1 removable

a.

or

provides

the

parts

to install two

new

removable

type antistatic

tabs

on

the

bonded tab windshields.

existing antistatic tab from windshields that have removable tabs (Ref. Figure 203). Clean the glass with isopropyl alcohol (6, Chart 202, 56-00-00). A wood or plastic scraper may be used to aid removing the sealer.

Remove the

windshield in

b.

Center the

new

antistatic tab

on

the mark

on

the windshield retainer that tested 100

different locations. A 0.59-inch section of the antistatic tab must

cover

megohms or less in ten glass (Ref. Figure 203).

the windshield

top end at a point 0.5 inch from the outer side of the windshield retainer. through each side of the tab (Ref. Figure 203).

Mark the antistatic tab inch diameter hole

two holes drilled in the antistatic tab

c.

Using the

d.

Drill two 0.0935-inch-diameter holes at the marks

debris created e.

Tap

the

guide,

on

a

0.0980-

mark the windshield retainer.

the windshield retainer. Vacuum the

area

to

remove

the

drilling operation.

the two holes in the windshield retainer with

NOTE:

A23

by

as a

Drill

a

No. 4-48 flat bottom tap.

If the windshield frame is buffed, buff the antistatic tabs before installation.

56-1 0-00

Page

voN502

1/07

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

0980 INCH DIAMETER

ANTI-STATIC TAB ATTACH SCREW HOLES

12 REQ.) .0935 INCH DIA. HOLE TAP 4-48 (2 REO.)

.50 INCH

i

WINDSHiELD

09

RETAINER

INCr-7(

ANIISTATIC

TAB

ii

ELECTRICI1L

INCH

TECHNIT 72-00002

-t

CONDUCTIVE SILICONE

CONDUCTIVE TAPE 1 125

OR EQUIv. (AS REO.)

1

,i

INCHES LONG

I,,,

541NCH ANTI-STATIC TAB

WINDSHIELD .12 INCH

GLASS

TAB TO BE FLUSH WITH GLASS IN

SILASTIC 140 SEALANT

THIS AREA WITHIN

OR EOUIV. (AS

005 INCH

REQ.) 350-l~C-2j

Windshield Antistatic Tab Installation

Figure

f.

Attach the antistatic tab to the windshield with two MS35207-212 antistatic tab with outlined

by

the

so

screws

furnished with the kit. Mask off the

that, when the tab is removed, the periphery of the tab location will be

antistatic tab and

lightly

sand the bottom end. Sand the windshield retainer

exposed.

Clean inside the masked-off conductive area.

area with isopropyl alcohol (6, Chart 202, 56-00-00) and apply a strip of electrical tape (13, Chart 202, 56-00-00) approximately 1.125 inches long. Center the tape in the masked-off

Install 0.47 inch of the conductive

conductive h.

masking tape

tape. Remove the

until bare metal is

g.

203

tape

on

the windshield

glass (Re´•f. Figure 203).

Press the electrical

tape down with finger pressure only.

Clean the bottom surface of the antistatic tab and the top surface of the electrical conductive tape with isopropyl Apply an electrical conductive sealer (14, Chart 202, 56-00-00), to the top surface of the electrical

alcohol.

conductive i.

tape.

Install the antistatic tab

on

the windshield retainer. The sealant should flow from under the

the sealant does not flow out around the tab,

NOTE: Do not press

j.

on

top of the tab

in

an

remove

attempt

the tab and

apply

edges of the

tab. If

additional sealer.

to squeeze out the sealer.

Remove the tape from around the antistatic tab and allow the sealant to

cure as

recommended

by

the

product

instructions.

Page

voN602

1107

56-i 0-00

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

k.

Mask off the four sides of the tab, leaving 0.0937 inch clearance between the edge of the masking tape and the edge of the tab. Mask off the top surface of the antistatic tab. Do not mask the area between the masking tape and the tab.

I.

Apply

adhesive

(15.

Chart 202,

weather seal. Remove the

56-00-00),

or

equivalent,

to the four sides of the antistatic tab to

masking tape and allow the adhesive

to cure

as

provide a by the manufacturer’s

recommended

instructions. m.

If necessa ry, paint the antistatic ta b to match the finish installation on the airplane.

on

the windshield retainer frame. Do not buff the tab after

WINDSHIELD REPLACEMENT CRITERIA glass and plastic windshield is subject to a gradual process of delamination due temperature and pressure incurred during pressurized flights at This delamination is not detrimental to the structural integrity altitudes and under weather conditions. varying varying of the windshield, but may significantly decrease visibility or the deicing capability of the windshield. Beyond certain limits, either of these effects will require replacement of the windshield. The following guidelines are provided as an aid to determine when a windshield should be replaced: The

heated laminated

electrically

to the effects of chemical action and differentials of

a.

VISIBILITY IMPAIRMENT:

vision, whether are no cause

windshield b.

or

for

Replace

not these

concern.

areas

the windshield when

extend to the

The rate of

areas

of delamination

edge of the glass. Smaller

growth of delaminated

areas

enlarge

should be used

point of impairing appearing as bubbles guide for scheduling

to the

delamination as a

replacement.

HEATING IMPAIRMENT LIMITS: total heated

Replace

the windshield when the lost

heating

area

exceeds 1/4 to 1/3 of the

area.

WINDSHIELD REMOVAL a.

Cut the

b.

Remove the

c.

Inside the

sealing compound screws

crew

free from the retainer

strip and

window frame.

at the front of the windshield.

compartment,

remove

the windshield and detach the power one at a time.

the

screw

supply

that

secures

lead at the

corner

ground jumper wire at the outboard corner of post. Gently push the windshield panels outward

the

d.

Pull the rubber seal and rubber filler free from the window frame and channel.

e.

Scrape away any remaining sealing compound, filler,

f.

Wash the window frame and channel clean with solvent

or

seal that may have adhered to the window frame.

(9,

Chart 202.

56-00-00).

WINDSHIELD INSTALLA TION

Proper performance of this procedure should ensure a stress-free windshield installation. Beech Kit No. 101-50411 provides the parts and detailed instructions for installation of both windshields. Beech Kit No. 101-5041-3 provides the

parts and detailed instructions for installation of either windshield.

procedures

in this manual and the instructions

provided

In the event of

with the windshield kits,

a

conflict between the

the kit instructions should be

followed

A23

56-1 0-00

Page

voN702

1107

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MAN UAL

Prior to

installing

the

windshield to bind are

in

of the

new

or

and

alignment

windshield, inspect the windshield frames for old sealer

other

or

objects

that could

cause

the

that all

nutplates improperly. Check all windshield mounting holes with a screw to ensure undamaged. It is recommended that the heating element and temperature sensor resistance

seat

window be checked is instructed under WINDSHIELD HEATING ELEP\I1ENTS RESISTANCE CHECK

(Ref. Chapter 30-30-00) before

installation.

will be completely cured in 30 hours higher temperatures and humidities. As the temperature varies up or down from the optimum 77"F, the pot life and cure time of the sealant may be expected to either double or be halved for each 10" of change. For example, if the ambient temperature is 67"F, the sealant will have a pot life of approximately one hour and a complete cure time of 60 hours. Always mix the sealant thoroughly. This procedure will require two maintenance personnel working constantly to complete installation before the sealer sets up.

CAUTION: The sealer provided with the kits has at 77"F with

a.

Mask off the exterior screw

b.

a

holes

on

Remove the

exposed

humidity of 50%.

area

c.

d.

excess

windshield

Trim the

excess

around the windshields with

reactive at

masking tape. Mask masking tape.

off the

nutplates by covering

the

protective paper from the metal retaining ring of the windshields. Cover any retaining ring with masking tape. Press the masking tape around each the masking tape from the countersink of each screw hole with a sharp knife. All

windshield

glass

and the metal

on

the inside of the windshield

protective paper from

Insert AN3-15A bolts

(10 places) through

each side of the windshield

the bolt heads Fabricate four

against the

as

holes

guide pins by cutting the top and bottom of the

"5", "7" and "12"

along

on

the

the raised

lip.

top and bottom and through holes

Tape the bolt shanks to hold windshield (Ref. Figure 204, View A-A).

shown in

inside surface of the

in hole "1" at the

f.

are more

holes must be open.

and "10"

e.

pot life of one-half hour and

the inside of the windshield frames with

of the countersunk holes. Cut screw

a

Sealants

204.

Figure

heads from 3-inch

long AN3 bolts. Insert a guide pin (Ref. Figure 204).

them in

and

place

secure

in

"4" with

place

frame for each windshield half

guide pins for alignment, carefully center the windshield in its frame as evenly as possible (Ref. Figure 204, A-A). Check for a minimum clearance of 0.020 inch between the inside glass and the lower frame member. If necessary place a shim (drill rod or drill shank of sufficient diameter) between the edge of the inside glass and the frame near the lower guide pin. Mark the location of the shim for future reference. If the required clearance cannot be maintained or interference between the windshield and adjacent structure is encountered,

Using

the

View

contact Hawker Beechcraft

Corporation

Technical

Support for

consultation.

NOTE: The purpose of the following step is to establish the best plane in which the windshield can be mounted. Therefore, it is desirable that the best contour match should be marked near the four corners of the windshield.

g.

use a 3-inch-long straightedge to match the contour of the windshield with that of (Ref. Figure 204, View B-B). If the windshield rocks on the bolt heads, center the windshield as evenly as possible to equalize the free play. Mark at least four places tone or more on at least three edges) where the exterior surface of the airplane is level with the metal retaining ring of the windshield (Ref. Figure 204, View B-B). If there are not four places that are level, mark the places where the contours most nearly match and mark them as high or low in inches as measured.

With the windshield centered, the windshield frame

h.

Remove the windshield from the windshield frame;

shims, if installed. Do not

Page

remove

the

56-~ 0-00

remove

guide pins from the

the 10 bolts

taped

to the

windshield; and

remove

the

windshield frame.

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i.

Clean the

contacting surfaces

of the silicone seals and the windshield frame with solvent

The 50-420066-341 silicone seals

00).

to be

are

applied

(9,

Chart 202: 56-00-

to the sides and centers of the windshield

frame, the

50-420066-343 seals to the bottom, and the 50-420066-345 seals to the top of the frame.

j.

kit) (Ref. Figure 204, together snugly. in the

k.

periphery of the windshield frame with Dapcotac cement (included C-C). The ends of the dam material used at the corners should be butted

Glue the silicone seals flush with the inside View

The 50-420066-347 sponge rubber strips are to be applied to the sides and center of the windshield, the 50420066-349 strips to the bottom, and the 50-420066-351 strips to the top. Apply a 0.25-inch wide strip of

(included

EC1 300L cement

in the

kit) to the

of cement to the windshield between the thickens. Allow the cement to cement

dry until tacky. Glue the sponge rubber strips to the windshield by matching the strip on the windshield glass (Ref. Figure 204, View D-D). Press firmly

the rubber to the cement

strip strips. on

periphery of the sponge rubber strips and apply a similar strip holes and the inside periphery of the windshield where the glass

inside

screw

to bond the

i.

Trim the sponge rubber strips on the ends so that the ends are butted one against the other. Trim the outer of the sponge rubber strips until an overlap of 0.064 inch is present around the periphery of the windshield

m.

D-D).

View

Figure 204.

edge (Ref.

Using the hollow drill (4, backup, drill all the

as a

56-00-00) and the drill bushing (5, Chart 201, 56-00-00) with a block of wood mounting holes through the sponge rubber strips. It may be necessary to punch

Chart 201, screw

out the accumulated rubber from inside the drill. n.

approximately 1200 grams of sealer(l6, Chart 202, 56-00-00) from the kit in accordance with the manufacturer’s instructions. Apply a 0.25-inch-deep bead of sealer around the periphery of the windshield frame Mix

in the

between the silicone rubber seals and the frame

valley

CAUTION: Once the sealer is mixed, if is

imperative

(Ref. Figure 204,

View

C-C).

that the windshield installation be

completed

without

interruption. o.

p.

Using

the

guide pins previously step

completely

cured.

Start, but do not tighten, installation

installed for

alignment, position

the windshield in the frame.

"h" between the windshield and frame. The shims

removed in

through

screws

in all the

mounting holes. Lubricate

are to remain in

all

screw

place

threads with

Replace

the shims

until the sealer is

liquid

soap to facilitate

the rubber seals.

installing the screws, carefully note the depth to which the screws penetrate the frame before actually entering the nutplates. In areas where the windshield will remain high after installation, screws with a longer grip will be required. This can be gaged by visually comparing the amount these screws protrude above the frame after the screws in the locations marked in step "g" are tightened.

NOTE: When

q.

Tighten the

r.

the marked

remaining

screws

until the windshield is

positioned

for the contour match

as

marked. Do not

guide pins and install screws in the holes. Beginning with the 13 screws along the bottom of the following the torque sequences shown (Ref. Figure 204). Tighten all the screws just enough to seat the screw heads in the countersunk holes in the retainer. Do not torque the screws any tighter as this could create windshield stress by pulling the windshield into the frame. After these screws have been seated into the countersinks, the screws tightened in the previous step should be seated and snugged against the retainer. Remove the

windshield and

nzJ

tighten

screws.

56-1 0-00

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I~

7

S

c?

10

1

6

3

34 io

idj

I

,6,

I I

I

i

rIi

J4

,5~ 4,

,5

oi

ii.j

blfS8 ’F:

,7

0-

---9

;iJII

----i-´•I

;il

i"-

i

1.

-i´•i

i

3

I

7"

c~

,4

-3.L-

IL’

s

13

8

f

2

3

WII\I

5

5

b MOUNTING

SI-I:Lsl_lI

io

3o

4

SCREW

’1 2

HOLES 13

_

AN3

i 5~

_I(

E31

Ir

,TAP_

I

FKAME7

___

I

li~jIj

r

i/i

I

A~A

i!

GLAc-31I

B

c-1

---1 VIEW i-1.2iS;I

.0;20

INCI

i

1/

A-A --r

i~iCkL

~it(-

1;1

EDGE

i_

IHROUGH

TOF.

F3R

1

IGLASS

SIDE

GOOD

MAICH

kuD

OF

B-B

TYPIC11 kid~

-R´•’-IE.

EDGE

r C---

VIEW

D-0

FOTIOM. CENTER. EOTH WINDSHIELD

,~ST’´•Trl-IT i

~3

L~

-\u

C--l

~,STRAIGHI

MARKS

I

u

1

cp i

iOir!

STRAIGHT

i

COUTCIIR

EDGE

1/16

INCH

OVERLkP

SEAIANi

i,SEAL

GL~SS HIG~-:

CONTOUR SPOI´•~T,I

I)I!CI:EF

;IRJF

RAME

VIEW

VIEW

C-C

D-D

LJ56R 973636bA

Windshield Installation

Figure

Page

voN012

1107

56-~ 0-00

204

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Mask off all

s.

screw

windshield frame. clean the t.

heads with

and smooth and fair the sealer between the windshield and the

masking tape

soap may be used to facilitate

Liquid

smoothing

the sealer. Remove the

masking tape

and

area.

Allow the sealer to

cure

undisturbed for at least 30 hours at

a

temperature of 77"F with

an

accompanying

humidity of 50%. CAUTION: Do not

attempt to pressurize the cabin, fly the airplane, completely cured.

NOTE: For every 10"F rise in temperature above double the cure time. u.

After the

13

torquing, If shims v.

time has

cure

screws

along

elapsed, torque

check all

screws

to

ensure

use

brighteners used

as

with

area

Mask the windshield and

CAUTION: Never

that the

paint

as

surrounding

required.

for every 10"F below 77"F,

coating

on

3.

Sand the windshield retainer with 120- to

4.

Clean the sanded retainer with solvent

5.

Prime the retainer with urethane

6.

Paint the windshield retainer with urethane

7.

Attach the

with

paint stripper(l7,

ground jumper wire

prevention

Paint the windshield retainer in the or

following

manner:

pasteboard masking material.

during painting. Most metal hydrogen gas that eats away the stannous oxide

will combine with aluminum to form

the antistatic

paint

them and fill the gap with sealer.

remove

structure with paper

Remove the old

erosion

by half;

until the sealer has

mounting screws to 20 inch-pounds, beginning with the following the torque sequences (Ref. Figure 204). After countersunk heads are properly seated and that all screws are tight.

2.

Apply

screws

aluminum foil to mask electrothermal windshields

at the windshield corner

w.

time

the

the windshield

used between the windshield and frame,

were

cure

tighten

the bottom of the windshield and

Touch up the windshield 1.

77"F, reduce the

or

the windshields. Chart 202,

280-grit

(9,

56-00-00)

paper to

Chart 202,

remove

equivalent epoxy paint stripper.

or an

the

original

anodized

coating.

56-00-00).

primer (18, Chart 202, 56-00-00) paint of the appropriate color.

at the outboard corner of the windshield and connect the power

supply lead

post.

sealant

(Ref. EROSION

PREVENTION SEALANT,

Chapter 20-08-00).

STORM WINDOW REMOVAL the storm window until it is secured

a.

Open

b.

Remove the five screws, nuts, and washers

c.

Remove the two screws, washers, and cap nuts which

d.

If necessary,

remove

the three bolts

by

the

hold-open

securing

securing

catch.

the storm window to the secure

hinge

bracket

the latch base and rubber

the storm window

hinge

to the

airplane

(Ref. Figure 205).

gasket to

structure and

the window. the

remove

hinge.

A23

56-1 0-00

Page

voN1 2

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MAN UAL

STORI~ WINDOWINSPECTION the window for cracks

crazing of the surface.

a.

Inspect

b.

Determine that the latch,

c.

Inspect

d.

Check the adjustment of the storm window. There should be

e.

Inspect

or

hinge,

and

hold-open

catch work

properly.

the seal for deterioration and proper fit to the frame and the window.

the storm window frame for evidence of corrosion

or

no

wind noise

trapped

n

or

water

leakage.

water.

SEAL

n STORM WINDOW HINGE

1

HALVES

SCREW

(2 PLACES) BOLT

GASKET

(3 PLACES) WASHER

LATCH

(2PLACES)

BASE SCREW

(5 PLACES)

IP~ CAP NUT

BOLT

(2 PLACES)

WASHER

(2 PLACES)

(5 PLACES)

WINDOW LATCH

WASHER

NUT

(2 PLACES)

(5 PLACES)

WINDOW

FL56B985296AA.AI

STOP

Crew

Compartment Storm Window

Figure

Page

voN212

1107

56-i 0-00

205

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STORM WINDOW INSTALLA nON a.

b.

If necessary,

position the

storm window

Install the rubber gasket and latch base

hinge on

on

the

airplane

structure and

the storm window and

secure

secure

with three bolts.

with two screws, washers, and cap

nuts.

Install the window

c.

the

screws

required

on

the

hinge half

and

until the nuts contact the

to turn the nuts

against

the

secure

with five screws, washers, and nuts

hinge. Torque hinge.

the

screws

to 2 to 4

(Ref. Figure 205). Tighten inch-pounds more than the torque

CAUTION: When attaching the acrylic storm window to the hinge half, torque the attaching screws only to torque 2 to 4 inch-pounds above that required to turn the nut with the screw. Exceeding the recommended torque values will d.

Close and latch the storm window.

e.

Inspect

f.

the storm window for

If the storm window is not

a

a

tight

fit

cause

against

the window to crack at the

a

hinge attach points.

the window frame seal.

tight seal (water leakage

or

wind

noise), adjust

the

stop

as

instructed in STORM

WINDOW STOP ADJUSTMENT.

STORM WINDOW SEAL REMOVAL a.

Openthe

b.

Pull the rubber seal and adhesive from the window frame.

c.

Remove any remnants of the seal

(9,

stormwindow.

Chart 202,

or

adhesive from the window frame with

a

rotary brush

or

solvent

56-00-00).

STORM WINDOW SEAL INSTALLA TION a.

Insure the storm window frame is completely free of any traces of the old adhesive.

b.

Apply adhesive (19, Chart 202, 56-00-00) to the window seal in the area it will the mating area of the window frame. Allow the adhesive to dry until tacky. Install the window seal. Ensure the seal fits flush

c.

against

contact the window frame and to

the storm window. Press the seal

firmly

to bond the

seal to the window frame. If the storm window is not

a

382002-1, adjust the stop

as

d.

tight

seal

(water leakage

or

wind

noise),

make

sure

that the seal is of Part No. 101-

instructed in STORM WINDOW STOP ADJUSTMENT.

STORM WINDOW STOP ADJUSTMENT a.

Open

b.

Loosen the two bolts securing the window stop in its slotted mounts (Ref. Figure 205).

c.

Slide the window stop outboard to obtain

thestormwindow.

NOTE: If the window a

/us

tighter

stop

a

tighter seal.

is at the end of its travel

adjustment,

the window

stop may

be bent outboard to obtain

seal.

56-1 0-00

PNaoSyB:l~:

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

Tighten

the two window

stop

mount bolts.

CREW COMPARTMENT SIDE WINDOW REMO VAL a.

Remove the headliner from its retainer

b.

Remove the

NOTE:

strip

its retainer

upholstery panel from

top of the window frame.

at the

strip

If the RH window frame is to be removed, move

it

slightly

away from the

upholstery

at the bottom of the window frame.

remove

before

Remove the four

d.

Remove the two bolts and washers from the storm window

e.

Work the

screws

from the RH circuit breaker

screws

removing

c.

attaching

the

the

upholstery panel

from both the upper and lower retainer

plastic window frame away from

the

airplane

stop and

strips

remove

and

the

and

panel

from its retainer.

remove

the retainer

strips.

stop.

structure.

NOTE: The inner window will be removed along with the window frame. If the inner window requires removal, it may be pressed out of its retaining groove in the plastic window frame with hand pressure. f.

If necessary, loosen the of the window.

clamp

and disconnect the

plastic pneumatic

tube from the steel tube at the lower aft

corner

g. h.

Remove the

screws

from the outer window retainer and

Remove the window from the

fuselage.

remove

the retainer.

Remove the old seal from the window. Remove any residual sealer from

the window and the outer window frame.

CREW COMPARTMENT SIDE WINDOW INSTALLA TION a.

Lightly scuff all 202, 56-01-00)

surfaces of the will be

new

seal

(P/N 101-384246-3)

with 400

grit sandpaper where sealer (16, Chart

applied.

b.

Wipe the seal surface with naphtha (7, Chart 202, 56-00-00) and wipe it dry immediately with a clean (lint free) dry cloth. Do not allow the naphtha to evaporate dry because it will leave a film on the area where sealant will be applied.

c.

Apply

a

light

(16, Chart 202, 56-00-00) in the seal. Install the seal (with sealing ridges on the window) around the rim of the window pane. All surfaces of the seal must lay flat against

coat of sealer

outboard side of the the window. d.

Lightly

e.

Apply a light coat of sealer (1S, Chart 202, 56-00-00) assembly to the airframe.

f.

scuff the airframe cutout with 400

Center the seal/window

attaching

Page

assembly

grit sandpaper where

sealer

(16,

Chart

202, 56-00-00)

will be

applied.

inside the airframe cutout to bond the seal/window

in the airframe cutout, then install the metal retainer

ring

and

secure

with

screws.

561~ 0100

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AtllA

I-

PLASTIC PNEUMATIC TUBE

CLAMP

OUTER PANE

STEEL TUBE

I

PLASTIC WINDOW FRAME

SEALING RIDGES

101-384246-3 SEAL OUTER SKIN

STEEL TUBE INNER PANE

j~--------PLASTIC

RETAINING GROOVE

WINDOW FRAME

OOW FRAME SGF~EW

(IOP~AGESI

jj

DETAI1

’WINOOW RETAINER

A-A

350-~10-24

Crew Compartment Side Window Installation Figure 206

A23

56-1 0-00

Page 215 Nov 1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

plastic fairing tool,

g.

Using

h.

Remove the

a

smooth

protective paper from

excess

sealer which may squeeze out in the milled radius

the outer window pane.

Thoroughly

area.

clean the outer window pane and the

inner window.

damage to the clear urethane anti-fog coating, do not use cleaners compartment side windows. Use only glass cleaner (I; Cha~it 202. 56-00-00) or a solution of warm water and non-abrasive liquid detergent (21 Chart 202. 56-00-00) and wipe with a clean, soft cloth or a clean, damp chamois. Do not use these cleaners on the uncoated exterior surfaces of the crew compartment side windows. For those surfaces, use acrylic plastic cleaner (3, Chart 202, 56-80-00).

CAUTION: To avoid obstruction of vision on

i.

If necessary,

the inner surfaces of the

place

or

crew

the inner window in the groove in the

plastic

window frame and snap it into

place

with hand

pressure.

j.

k.

If necessary, connect the secure with the clamp.

plastic pneumatic

tube to the steel tube at the lower aft

corner

of the window and

Install the plastic window frame in place around the side window. Position the upper and lower strips in place on the window frame and secure each with four screws.

upholstery

retainer I.

If necessary, install the RH circuit breaker

m.

Install the upholstery

n.

Apply

Page

voN612

1107

erosion

panel and the

prevention

sealant

and

headliner in their

(Ref.

56-~ 0-00

panel

secure

it with the

respective

attaching

retainer

screws.

strips.

EROSION PREVENTION SEALANT, Chapter

20-08-00).

n2a

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WINDOW INSPECTION AND REPAIR PROCEDURES CREW COMPARTMENT, CABIN, AND BAGGAGE WINDOWS airplane are made of a fail-safe, multi-ply stretched acrylic material. Inspect these windows (Ref. Figure 201) specified (Ref, INSPECTION AND MAINTENANCE TIMETABLE, Chapter 5-00-00) and the by pilot during preflight inspections.

The side windows of the

at interval

I

ACRYLIC WINDOW REFURBISHING PROCEDURE which may be repaired utilizing this procedure. If any Chart not covered in 201, contact Hawker Beechcraft Corporation Technical

Chart 201 outlines the

types and

limits of window

unusual conditions

found that

are

are

damage

Support for consultation. Use of this procedure is prohibited, except Hawker Beechcraft Corporation Technical Support. NOTE:

New window does not have the milled

a.

Mask off any

b.

Usewet abrasives

c.

Flush the window surface with

d.

Use

e.

f.

major portions

Gradually lighten force

on

Work

a

before

of the window which

the

a

not involved in the

motion and alternate the line of

Chart 202

or

by

refurbishing.

working

pressure

on

the abrasive

as

using

sanding

each abrasive at

each finer

right angles grade

grade.

to

cross

the sanding pattern.

is utilized. Do not exert excessive

the window pane.

marginally larger area as each finer abrasive moving to the next finer abrasive.

Do not overheat the acrylic window.

h.

Start the

i.

by

in old window.

liberal amount of water after

g.

(6,

are

instructed

specifically

only.

straight-line sanding

a

edge found

as

is used.

Completely

remove

each

previous sanding pattern

refurbishing procedure with 240-grit wet/dry silicone carbide cloth, or equivalent, and an orbital 56-00-00). Use this combination until all traces of the damage have been removed.

sander

Chart 201,

Use

a

320-grit wetldry silicone carbide cloth with the orbital

sander and work the window until the

240-grit pattern

has been removed.

j.

Repeat step

"i"

using 400-grit, 600-grit, 1800-grit, 2400-grit, 3200-grit, 4000-grit,

and

6000-grit

silicone carbide

cloth in succession. cushioned abrasive cloth

k.

Finish the

i.

Inspect the finished window following the inspection procedure damage and grit patterns have been removed.

m.

When satisfied that the window has been

refurbishing procedure using

an

8000-grit

shown

or

cerium oxide.

(Ref. Figure 201)

to ensure that all

I

properly refurbished, apply a small amount of antistatic cleaner or wax high luster. For removal of minor crazing or scratches, the plastic window scratch (20, Chart 202, 56-00-00) is recommended.

to the window and buff to a remover

56-1 5-00

PMa Sye:l~:May

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

A

A

1

1

1"

VIEW

B9’i LAMP

VIEW

LAMP

C].

OF FUSELAGE

FUSELAGE SKIN

VIEW

(V-h?

’*"’7a

FUSELAGE SKIN

LAMP~

LAMP

VIEW

A-A

VIEW

B-B

THE WINDOW INSPECTION PROCEDURE SHOWN IN THIS FIGURE SHOULD BE PERFORMED

AREA, OR AT NIGHT. USE A GOOD LIGHT SOURCE AND MOVE IT AROUND THE WINDOW AT VARIOUS ANGLES WHILE VIEWING THROUGH THE WINDOW FROM DIFFERENT DIRECTIONS. INSPECT ALL OF THE FUSELAGE SIDE WINDOWS IN THIS MANNER. SEE CHART 201 FOR DAMAGE DESCRIPTION AND RECOMMENDED ACTION. IN A DARKENED

Window

May

1/0756-~ 5~00

Inspection Procedure Figure 201

A22

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 WINDOW DAMAGE

Scratches, abrasions, gouges and

chips with depth of 0.015

a

Inner

excess

with

a

depth

a

Inner

ply

ply

in

of 0.015 inch.

Crazing with

Improper maintenance cleaning procedures.

Recommended Action or

inch.

Scratches, abrasions, gouges

chips

ply

maximum

Outer

and

Probable Cause

Location

Damage Type

maximum

Outer

depth

Inner

ply

ply

of 0.015 inch.

Improper maintenance, cleaning procedures or object impact. Improper maintenance cleaning procedures.

Damage may

PROCEDURES. or

window is

Contact with

Airplane may be operated unpressurized only until the replaced.

window is

unapproved or

compounds; fatigue.

Contact with unapproved

cleaners, solvents,

or

chemical stress

in

excess

Inner

ply

of 0.015 inch.

replacement of the window mandatory before further flight.

Immediate is

Airplane may be operated unpressurized only until the replaced.

stress

Crazingwith amaximumdepth

be worked out. Refer to

ACRYLIC WINDOW REFURBISHING

chemical

ply

window is

Improper maintenance or cleaning procedures or object impact. cleaners, solvents,

Outer

Airplane may be operated unpressurized only, until the replaced.

compounds; fatigue.

Contact with

unapproved

cleaners, solvents,

Damage may be worked out. Refer to ACRYLIC WINDOW REFURBISHING PROCEDURES.

replacement of the window mandatory before further flight.

Immediate is

or

chemical stress

Outer

ply

compounds; fatigue.

Contact with

unapproved

cleaners, solvents, chemical stress

Haziness and cloudiness.

Inner

ply

or

compounds;

unapproved

cleaners, solvents,

or

chemical

Outer

ply

compounds; fatigue.

Contact with unapproved

cleaners, solvents,

or

chemical compounds; stress

Pane delamination

nz2

Airplane may be operated unpressurized only until the window is replaced.

Airplane may be operated unpressurized only until the replaced.

window is

Airplane may be operated unpressurized only until the replaced.

window is

fatigue.

Stress; extreme heat

high

window is

fatigue.

Contact with

stress

Airplane may be operated unpressurized only until the replaced.

humidities.

at

56-1 5-00

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 WINDOW DAMAGE

Damage Type

Probable Cause

Location

Out of contour

(Continued)

High humidity; water absorption, excessive heat or pressurization; chemical or

Distortion

solvent

Recommended Action

replacement of the window mandatory before further flight.

Immediate

is

absorption.

Improper restoration when removing damage from outer ply, chemical or solvent damage.

If distortion is caused

by poor techniques, the window replaced at will with no flight

restoration

may be limitations. However, if the distortion is the result of chemical

or

solvent

damage, the airplane may be operated unpressurized only until the window is replaced. Circumferential cracks

at

Inner

ply

least 2 inches from the window

Improper maintenance; stress

fatigue.

fra me. Outer

ply

Circumferential cracks

within

Inner

ply

ply

maximum of 20 hours at

a

reduced

pressure of 4.6 psid with altitude of 25,000 feet.

a

maximum

Improper maintenance;

Airplane may be operated unpressurized only until the replaced.

window is

Airplane may be operated unpressurized only until the replaced.

window is

fatigue,

Improper maintenance; stress

fatigue; object

impact.

Clamshell-typechips 1/4-inch edge, 3132- inch deep, and l.O-inch long (Ref. Figure 203).

Outer

from milled

ply

for

Airplane may

fatigue; object impact.

stress

Outer

window is

Improper maintenance; stress

2 inches of the window frame.

Airplane may be operated unpressurized only until the replaced.

Improper maintenance; fatigue; object impact, compression damage. stress

Blend out

polish

to

operated

be

a

damage with sandpaper,

a

and

clear, scratchless finish with

plastic window scratch remover (20, Chart 202, 56-00-00) or equivalent. Break edge to 0.03-inch radius.

NOTE If cracks, from the

Page

yaM402

1/07

56-1 5-00

known

chip,

no

as

"vents", radiate

repairs

are

allowed.

Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

INSPECTION AND REPAIR OF WINDOW A TTACH FRAMES Perform the

of the window attach frames

following inspection

INSPECTION AND MAINTENANCE TIMETABLE, a.

Press

on

the cabin windows and

is observed,

no

on

further action will be

on

all

airplanes

specified (Ref.

at the intervals

Chapter 5-00-00).

I

the

flight compartment side window from the exterior side. If no movement required; however, if there is any indication of looseness, proceed with the

following steps. b.

Remove each loose window

c.

With the frame

pressed

as

back

the frame and skin in the

indicated under the proper

against

areas

heading

in this

chapter.

the outer skin, drill 0.098-inch diameter holes, six inches

where the frame has

separated from

apart, through

the skin. Drill the holes 0.20 inch from the

edge of the frame (Ref. Figure 202). d.

Countersink the holes 100"

enough e.

on

to hold the frame in

both sides. The holes

place

the frame

on

while the epoxy adhesive

Pry the frame far enough from the skin to allow the mating mating surfaces of the skin and

all the adhesive from the

CAUTION:

Pry

g.

and

a

mating

only

made flush.

380-grit sand

paper. Sand

frame.

surfaces of the skin and frame with

surfaces

(21, Chart 202, 56-00-00) (Ref. Figure 202).

to

separate the

two from

one

naphtha (7, Chart 202,

in accordance with the manufacturer’s directions and

h.

Install NAS1097 rivets and flatten the rivet butts until the countersink

i.

If necessary,

use a

j.

Remove any

excess

k.

Install the windows

A22

are

clean cloth.

Mix the epoxy adhesive

it to the

mating

to be countersunk

surfaces to be sanded with

only enough to permit repair. Any attempt damage to either or both.

Clean the adhesive residue from the

56-00-00)

assembly need

and the rivet butts

the frame and skin apart

another may result in f.

cures

mill to flush any rivet butt

epoxy adhesive with

as

protruding

above the frame

naphtha using

indicated under the proper

area

a

heading

apply

is filled.

assembly.

clean cloth. in this

chapter.

56-~ 5-00

Page

yaM502

1/07

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MAN UAL

ORIGINAL As Received

ATP OLITER

.~O

SKIN

INL^H-iUiEF

WIUCO~J

j

i

EPOXY SIVE

r´•

FRAIL´•i_7

j

i.b

j

AREA SEPARATION

?NCHES

‘i i

i, i,

DRILI .098-INCti HOLES AS REQUIRE~ TH?OUG~ WINDO:nl FRAME AND SKI~ OCi" COUNTERSINK tiC~TH SIDES

WINDOW FRAME

LNAS1097 RIVET

/A ::’IEW

A-A

VIEIN’ LOOKING OIITBOAF~D THROUGH WINDOW SUTOU1

350-110-030

Window Attach Frame

Figure

C

Repair

202

1/41N

3/32 IN

t

I I~

B

p

-I

Y=´•hB VIEW

VENT

NOTE:

A

SECTION

B-B

APPLICABLETO MILLED EDGE WINDOW ONLY.

~L

THIS DOES NOT APPLY TO

A

NON-MILLED EDGE WINDOW.

FL568985297AAAI

Clamshell-Type Chip Damage Limits Figure 203

Page

yaM602

1107

56-1 5-00

A22

By

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 56-20-00

CABIN WINDOWS - DESCRIPTION AND OPERATION ELECTROCHROMIC WINDOW SHADES (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) The passenger cabin has fifteen electrochromic window shades that are controlled with the individual Programmable Switch (PSW) (Ref. Figure 1). The window shade has selectable levels of transparency between dark and clear. The cabin PSW provides single action command inputs for control of the window shade transparency for the following groups: •

All Window shades

•

All Right Side shades

•

All Left Side shades

•

Right Side Forward Club shades

•

Right Side Aft Club shades

•

Left Side Forward Club shades

•

Left Side Aft Club shades

Each individual PSW controls the paired and club electrochromic window shades at each individual passenger seat position. Refer to the PSW Graphical User Interface (GUI) flow for the electrochromic window shades (Ref. Pro Line 21 Maintenance Manual Supplement, Chapter 23-30-03).

A27

56-20-00

Page 1 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ALL RIGHT SIDE ALL

RIGHT SIDE FORWARD CLUB PAIR

PAIR

RIGHT SIDE AFT CLUB

PAIR

PAIR

PAIR

PAIR

LEFT SIDE FORWARD CLUB

PAIR

PAIR LEFT SIDE AFT CLUB

FWD

LEFT SIDE ALL ALL

FM56B 985687AA.AI

Electrochromic Window Shade Control Groups Figure 1 Page 2 Feb 1/10

56-20-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

CABIN WINDOWS - MAINTENANCE PRACTICES NOTE: Refer to WINDOW DEFOG SYSTEM, 30-40-00 for information on the cabin window defogging system.

CABIN OUTER WINDOW REMOVAL a. Remove the polarized window (Ref. POLARIZED WINDOW REMOVAL) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed). b. Remove the electrochromic window shade (Ref. ELECTROCHROMIC WINDOW SHADE REMOVAL) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). c.

Remove the screw and clamp securing each of the two stainless steel pneumatic tubes to the window frame (Ref. Figure 201, Sheet 1, Detail B-B or Figure 201, Sheet 2, Detail B-B). Remove the tubes from the frame.

d. Remove the eight screws and washers securing the window retainer to the window frame (Ref. Figure 201, Sheet 1, Detail A-A or Figure 201, Sheet 2, Detail A-A). Remove the retainer from the airplane. e. Remove the window outer pane from the window frame. f.

Remove the old seal from the window pane. NOTE: If a frost seal is installed, exercise care not to tear or loosen the seal during removal of the window retainer and window.

g. If the window pane is to be reinstalled, use paper to protect the surfaces from scratches or other damage. h. Clean all residual sealer from the window frame and retainer.

CABIN OUTER WINDOW INSTALLATION Caution: To avoid scratches and other damage when installing a new window pane, leave the protective paper attached to the window until the window is secured. NOTE: A new window pane without a milled edge (Ref. Figure 201, Sheet 1) has superseded the old window pane. Milled edge exists only in an old window pane (Ref. Figure 201, Sheet 2). When installing the new window pane, replace the seal. The retainer must also be replaced, or modified by elongating the mounting holes in the retainer ring, to accommodate for the thicker edge of the new window pane. a. Lightly scuff all surfaces of the new seal (P/N 101-384139-5 or 101-384139-7) with 400 grit sandpaper where sealer (16, Chart 202, 56-00-00) will be applied. b. Wipe the seal surface with naphtha (7, Chart 202, 56-00-00) and wipe it dry immediately with a clean (lint free) dry cloth. Do not allow the naphtha to evaporate dry because it will leave a film on the area where sealant will be applied. c.

Apply a light coat of sealer (16, Chart 202, 56-00-00) in the seal. Install the seal (with sealing ridges on the outboard side of the window) around the rim of the window pane. All surfaces of the seal must lay flat against the window (Ref. Figure 201, Sheet 1, Detail A-A or Figure 201, Sheet 2, Detail A-A).

d. Lightly scuff the airframe cutout with 400 grit sandpaper where sealer (16, Chart 202, 56-00-00) will be applied. e. Apply a light coat of sealer (16, Chart 202, 56-00-00) inside the airframe cutout to bond the seal/window assembly to the airframe.

A27

56-20-00

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL f.

Bond the seal to the outer edge of the window with sealer (16, Chart 202, 56-00-00). All surfaces of the seal must lay flat against the window when installed. Do not remove the center portion of the window seal until instructed.

g. Position and center the window in the window frame. h. Install the window retainer against the window pane and secure it with eight screws and washers (Ref. Figure 201, Sheet 1, Detail A-A or Figure 201, Sheet 2, Detail A-A). i.

Using a plastic fairing tool, smooth excess sealer which may squeeze out in the milled radius area.

j.

Place the two stainless steel pneumatic tubes and clamps on the window frame (Ref. Figure 201, Sheet 1, Detail B-B or Figure 201, Sheet 2, Detail B-B). Secure each clamp to the frame with one screw. CAUTION: Use care not to cut or scratch the window pane when cutting away the center portion of the window seal.

k.

Using a single edge razor blade, carefully cut away the center portion of the window seal covering the outer surface of the window pane. Cut the seal flush with cutout in the airplane skin.

l.

Apply erosion prevention sealant (Ref. EROSION PREVENTATIVE SEALANT, 20-08-00).

m. Remove the protective paper from the window pane and thoroughly clean the window pane (Ref. CLEANING PLASTIC WINDOWS, 56-00-00) using a lint free cloth and acrylic plastic cleaner (3, Chart 202, 56-00-00). n. Install the polarized window (Ref. POLARIZED WINDOW INSTALLATION) (FL-1 thru FL-600, FL-602 thru FL671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed). o. Install the electrochromic window shade (Ref. ELECTROCHROMIC WINDOW SHADE INSTALLATION) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed).

Page 202 Feb 1/10

56-20-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Cabin Outer Window Installation (Un-Milled Edge) Figure 201 (Sheet 1 of 2)

A27

56-20-00

Page 203 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OUTER SKIN WINDOW FRAME

B A

A EPOXY ADHESIVE

B

WINDOW FRAME OUTER SKIN

101-530899-3 SEAL BOND TO WINDOW FRAME USING EC 1300L ADHESIVE

SEALING RIDGES

WASHER (8 PLACES)

101-384139-5 SEAL

SCREW (8 PLACES)

WINDOW PANE

DETAIL

A-A

WINDOW RETAINER

(VESTIBULE WINDOW ONLY) WINDOW PANE

OUTER SKIN

STAINLESS STEEL PNEUMATIC TUBE (2 PLACES)

EPOXY ADHESIVE

WINDOW RETAINER

WINDOW FRAME OUTER SKIN

SEALING RIDGES

CLAMP

WINDOW FRAME

101-384139-5 SEAL

SCREW WASHER (8 PLACES)

OUTER SKIN

SCREW (8 PLACES)

WINDOW PANE

WINDOW RETAINER

DETAIL

A-A

DETAIL

B-B

FL56B985294AA.AI

Cabin Outer Window Installation (Milled Edge) Figure 201 (Sheet 2 of 2)

Page 204 Feb 1/10

56-20-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POLARIZED WINDOW REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED) NOTE: The following steps are not applicable to the emergency exit window. Refer to EMERGENCY EXIT POLARIZED WINDOW REMOVAL for removal procedures for that window. a. Remove the upper sidewall panel (Ref. UPPER CABIN SIDEWALL WINDOW PANEL REMOVAL, 25-20-11). b. The attaching screws are covered by a flat rubber seal bonded to the upper sidewall panel. To gain access to the screws, carefully stretch the seal over and off of the three glide assemblies and work the seal off of the polarized window shroud. The tubular outer seal will remain attached to the polarized window assembly (Ref. Figure 202). c.

Remove the four attaching screws and washers and remove the polarized window assembly from the upper sidewall panel.

POLARIZED WINDOW DISASSEMBLY (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the retainer and inner polarized window pane from the shroud by depressing the three spring-loaded guides (Ref. Figure 202) outward from the center of the window to release the retainer from the shroud. b. Carefully spread the retainer and remove the inner window pane from the retainer. c.

Remove the outer polarized window pane from the shroud.

POLARIZED WINDOW ASSEMBLY (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED) CAUTION: If possible, assemble the window in a dust free environment to prevent scratches and the accumulation of foreign material on the window components. Wear white gloves while assembling the window. Clean the window panes using a lint free cloth and acrylic plastic cleaner (3, Chart 202, 56-00-00). Blow the panes clear of dust with filtered air (not to exceed a pressure of 30 psi). a. Insert the outer polarized window pane into the shroud with the flat portion of the pane at the top of the shroud and the trademark facing the installer (Ref. Figure 202). NOTE: If the movable pane binds in operation, lubricant (22, Chart 202, 56-00-00) may be applied to the edge of the pane. Clean any excess lubricant from all surfaces of the pane. Do not substitute any other lubricant. b. Spread the retainer. With the knob on the pane facing the installer, insert the movable pane into the retainer. c.

Position the retainer on the shroud with the split in the retainer at the top. Align the cutouts in the retainer with the three glide assemblies, then depress the three spring-loaded glides outward from the center of the window and snap the retainer and movable pane into the shroud.

d. Check the movable pane for smooth rotation in the retainer. If necessary, adjust the screws in the glide assemblies until the pane rotates smoothly on the bearing surfaces of the glides.

A27

56-20-00

Page 205 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MOUNTING TABS SHROUD OUTER POLARIZED PANE RETAINER INNER POLARIZED PANE

OUTER SEAL

GLIDE ASSEMBLY

FL56B 985593AA.AI

Polarized Window Assembly (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687) Figure 202

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POLARIZED WINDOW INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED) NOTE: The following steps are not applicable to the emergency exit window. Refer to EMERGENCY EXIT POLARIZED WINDOW INSTALLATION for installation procedures for that window. CAUTION: When the airplane is parked in an area exposed to intensive sunlight, the polarized windows should be in the open position (positioned to permit the entry of sunlight) to prevent deterioration of the window polarization. The windows are designed to provide sufficient ultraviolet protection when in the open position to prevent fading of the interior fabrics and upholstery. If possible, assemble the window in a dust free environment to prevent scratches and the accumulation of foreign material on the window components. Wear white gloves while installing the window assembly and clean the window panes with a lint free cloth and acrylic plastic cleaner (3, Chart 202, 56-00-00). Blow the panes clear of dust with filtered air (not to exceed a pressure of 30 psi). a. Align the mounting holes in the shroud with those in the window panel and install the four attaching screws and washers (Ref. Figure 202). b. Carefully stretch the flat rubber seal over the three glide assemblies. Make sure that the seal lies flat all around the shroud. Make sure that the four vent holes in the top half of the shroud (two each at the two o’clock and the ten o’clock positions) are not blocked. c.

Repeat steps “a” and “b” for each window to be assembled and/or installed.

d. Install the upper sidewall panel (Ref. UPPER CABIN SIDEWALL WINDOW PANEL INSTALLATION, 25-20-11).

ELECTROCHROMIC WINDOW SHADE REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) NOTE: The following steps are not applicable to the emergency exit window. Refer to EMERGENCY EXIT ELECTROCHROMIC WINDOW SHADE REMOVAL for installation procedures for that window a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove cabin furnishings as required for access to the required electrochromic window shade (Ref. Chapter 25-20-00).

d. Electrically disconnect the electrochromic window shade. e. Remove the four screws (4) and four washers (3) securing the electrochromic window shade assembly to the window doubler (8) (Ref. Figure 203). f.

Remove the electrochromic window shade assembly.

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ELECTROCHROMIC WINDOW SHADE INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the electrochromic window shade assembly in position on the window doubler (8) and secure using four screws (4) and four washers (3) (Ref. Figure 203). b. Electrically connect the electrochromic window shade. c.

Install any cabin furnishings removed for access as required (Ref. Chapter 25-20-00).

d. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

ELECTROCHROMIC WINDOW SHADE CONTROLLER REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) NOTE: Each passenger cabin electrochromic window shade controller is located below the applicable passenger cabin window behind the cabin lower sidewall panel. The lavatory electrochromic window shade controller is located adjacent to the lavatory window in the aft position behind the vestibule window sidewall panel. a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Remove cabin furnishings as required for access to the required electrochromic window shade controller (Ref. Chapter 25-20-00).

d. Electrically disconnect the electrochromic window shade controller. e. Remove the electrochromic window shade controllerfrom bracket assembly.

ELECTROCHROMIC WINDOW SHADE CONTROLLER INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the electrochromic window shade controller in the bracket assembly. b. Electrically connect the electrochromic window shade controller. c.

Install any cabin furnishings removed for access as required (Ref. Chapter 25-20-00).

d. Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1

A A 1

2

9 1. 2. 3. 4. 5. 6. 7. 8. 9.

3

8

ELECTROCHROMIC WINDOW SHADE SEAL WASHER (4 PLACES) SCREW (4 PLACES) FRAME (REF) ANTI-VIBRATION ISOLATOR GROMMET NUT PLATE WINDOW DOUBLER WINDOW

4

7

5

6 DETAIL

A-A

TYPICAL

FL56B 985695AA.AI

Electrochromic Window Shade - Removal/Installation (FL-601, FL-672, FL-688 and After With Cabin Management System Installed) Figure 203

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EMERGENCY EXIT POLARIZED WINDOW REMOVAL (FL-1 THRU FL-600, FL-602 THRU FL671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED) a. Remove the emergency exit door assembly from the fuselage. Disconnect the emergency exit door from the window defogging system by pulling the air tube straight off the exit door tee fitting. b. Remove the emergency exit door assembly from the airplane. c.

Measure and record the distance between each of the six attach brackets on the door assembly and the clips on the window panel, to provide a flush installation of the window panel upon installation of the door assembly in the airplane.

d. Loosen the lock nut on each of the six bolts which attach the window panel assembly to the door assembly and turn the bolts to release them from the rivnuts in the door assembly. Retain all spacer washers for installation. NOTE: The bolts will remain in the clips attached to the window panel (Ref. Figure 204). e. The attaching screws are covered by a flat rubber seal bonded to the window panel. To gain access to the screws, carefully stretch the seal over and off of the three glide assemblies and work the seal off of the polarized window shroud. The tubular outer seal will remain attached to the polarized window assembly. f.

Remove the four attaching screws and washers and remove the polarized window assembly from the window panel.

BOLT LOCKNUT WASHER

CLIP

BRACKET (ATTACHED TO EMERGENCY EXIT DOOR ASSEMBLY)

EMERGENCY EXIT WINDOW PANEL

RIVNUT SPACER WASHER TYPICAL 6 PLACES

FL56B 985594AA.AI

Emergency Exit Door Window Panel Attach Brackets (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687) Figure 204

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EMERGENCY EXIT POLARIZED WINDOW INSTALLATION (FL-1 THRU FL-600, FL-602 THRU FL-671, FL-673 THRU FL-687, FL-689 AND AFTER WITHOUT CABIN MANAGEMENT SYSTEM INSTALLED) a. Align the mounting holes in the shroud with those in the window panel and install the four attaching screws and washers. Carefully stretch the flat rubber seal over the three glide assemblies. Make sure that the seal lies flat all around the shroud. Make sure that the four vent holes in the top half of the shroud (two each at the two o’clock and ten o’clock positions) are not blocked. b. Position and install the window panel and window assembly on the emergency exit door assembly using the six attaching bolts, washers, spacer washers and lock nuts (Ref. Figure 204). c.

Obtain the proper distance (measured and recorded during disassembly) between each of the six brackets on the door assembly and the six clips on the window panel by adjusting the lock nuts. Make sure that the window panel is mounted flush with the panels in the airplane.

d. Push the air tube for the window defogging system onto the emergency exit door tee fitting. Do not use any kind of clamp or adhesive to secure the tube to the tee fitting. WARNING: Use care when installing the emergency exit door so as not to pinch the air tube for the window defogging system. A pinched air tube will cut off air flow to the window and could hamper proper function of the door in an emergency. e. Install the emergency exit door in the airplane. f.

Apply erosion prevention sealant (Ref. EROSION PREVENTION SEALANT, 20-08-00).

EMERGENCY EXIT ELECTROCHROMIC WINDOW SHADE REMOVAL (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Make sure the BAT switch is set to the OFF position and tag the switch with a caution tag indicating “DO NOT APPLY POWER”. b. Disconnect the airplane battery (Ref. BATTERY POWER - DISCONNECT, 24-31-00) and tag the connector with a caution tag “DO NOT RECONNECT”. c.

Electrically disconnect the electrochromic window shade.

d. Remove the emergency exit door assembly from the fuselage. Disconnect the emergency exit door from the window defogging system by pulling the air tube straight off the exit door tee fitting. e. Remove the emergency exit window panel (Ref. EMERGENCY EXIT WINDOW PANEL REMOVAL, 25-20-11). f.

Remove the four screws (4) and four washers (3) securing the electrochromic window shade to the window doubler (8) (Ref. Figure 203).

g. Remove the electrochromic window shade.

EMERGENCY EXIT ELECTROCHROMIC WINDOW SHADE INSTALLATION (FL-601, FL-672, FL-688 AND AFTER WITH CABIN MANAGEMENT SYSTEM INSTALLED) a. Install the electrochromic window shade in position on the window doubler (8) and secure with four screws (4) and four washers (3) (Ref. Figure 203).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL b. Install the emergency exit window panel (Ref. EMERGENCY EXIT WINDOW PANEL INSTALLATION, 25-20-11). c.

Push the air tube for the window defogging system onto the emergency exit door tee fitting. Do not use any kind of clamp or adhesive to secure the tube to the tee fitting. WARNING: Use care when installing the emergency exit door so as not to pinch the air tube for the window defogging system. A pinched air tube will cut off air flow to the window and could hamper proper function of the door in an emergency.

d. Electrically connect the electrochromic window shade. e. Install the emergency exit door (Ref. EMERGENCY EXIT DOOR INSTALLATION, 52-20-00). f.

Connect the airplane battery (Ref. BATTERY POWER - CONNECT, 24-31-00) and remove the caution tag.

VESTIBULE WINDOW REMOVAL a. Remove the vestibule upper sidewall panel (Ref. UPPER RIGHT VESTIBULE UPHOLSTERY PANEL REMOVAL, 25-20-11) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed). b. If necessary remove the polarized window (Ref. POLARIZED WINDOW REMOVAL) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed). NOTE: Normally, it will not be necessary to remove the flat rubber seal from the window frame when removing the outer window. Therefore, disregard step “e” unless it is necessary to remove the seal. c.

Remove the vestibule window panel (Ref. VESTIBULE WINDOW PANEL REMOVAL, 25-20-11) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed).

d. If necessary remove the electrochromic window shade (Ref. ELECTROCHROMIC WINDOW SHADE REMOVAL) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). NOTE: Normally, it will not be necessary to remove the flat rubber seal from the window frame when removing the outer window. Therefore, disregard step “e” unless it is necessary to remove the seal. e. Carefully remove the flat rubber seal from around the window frame (Ref. Figure 201, Sheet1, Detail A-A or Figure 201, Sheet 2, Detail A-A). Remove any residual adhesive from the frame and the seal with solvent (9, Chart 202, 56-00-00). f.

Remove the screw and clamp securing each of the stainless steel pneumatic tubes to the window frame (Ref. Figure 201, Sheet 1, Detail B-B or Figure 201, Sheet 2, Detail B-B). Work the tubes out from under the flat rubber seal and remove the tubes from the frame.

g. Remove the eight screws and washers securing the window retainer to the window frame. Carefully pull the retainer through the flat rubber seal and remove retainer from the airplane. h. Remove the window pane from the window frame. Carefully pull the pane through the flat rubber seal and remove the pane from the airplane. Remove the seal from the rim of the window pane. i.

If the window pane is to be reinstalled, use paper to protect the surfaces from scratches or other damage.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

VESTIBULE WINDOW INSTALLATION CAUTION: To avoid scratches and other damage when installing a new window pane, leave the protective paper attached to the window until the window is secured. a. Lightly scuff all surfaces of the new seal (P/N 101-384246-5) with 400 grit sandpaper where sealer (16, Chart 202, 56-00-00) will be applied. b. Wipe the seal surface with naphtha (7, Chart 202, 56-00-00) and wipe it dry immediately with a clean (lint free) dry cloth. Do not allow the naphtha to evaporate dry because it will leave a film on the area where the sealant will be applied. c.

Apply a light coat of sealer (16, Chart 202, 56-00-00) in the seal. Install the seal (with sealing ridges on the outboard side of the window) around the rim of the window pane. All surfaces of the seal must lay flat against the window (Ref. Figure 201, Sheet 1, Detail A-A or Figure 201, Sheet 2, Detail A-A).

d. Lightly scuff the airframe cutout with 400 grit sandpaper where sealer (16, Chart 202, 56-00-00) will be applied. e. Apply a light coat of sealer (16, Chart 202, 56-00-00) inside the airframe cutout to bond the seal/window assembly to the airframe. f.

Bond the seal to the outer edge of the window with sealer (16, Chart 202, 56-00-00). All surfaces of the seal must lay flat against the window when installed. Do not remove the center portion of the window seal until instructed.

g. Carefully insert the window pane through the flat rubber seal and position the pane in place in the window frame. center the window pane in the frame. h. Carefully insert the window retainer through the flat rubber seal and position the retainer against the window pane. Secure it with eight screws and washers (Ref. Figure 201, Sheet 1, Detail A-A or Figure 201, Sheet 2, Detail A-A). i.

Work the two stainless steel pneumatic tubes under the flat rubber seal and position the tubes and clamps on the window frame (Ref. Figure 201, Sheet 1, Detail B-B or Figure 201, Sheet 2, Detail B-B). Secure each clamp to the frame with one screw. CAUTION: Use care not to cut or scratch the window pane when cutting away the center portion of the window seal.

j.

Using a single edge razor blade, carefully cut away the center portion of the seal covering the outer surface of the window pane. Cut the seal flush with the cutout in the airplane skin.

k.

Bond the flat rubber seal (P/N 101-530899-3) to the window frame as follows: CAUTION: Before installing the flat rubber seal (P/N 101-530899-3), inspect it for tears, cuts, or punctures. If any damage is found, install a new seal. NOTE: Normally it will not be necessary to install the flat rubber seal when installing the outer window. Therefore, disregard step “k” unless it is necessary to install the seal. 1. Make sure that the surfaces to be bonded are clean, dry, and free from oil or grease. 2. Using a brush, apply a thin, even coat of adhesive (19, Chart 202, 56-00-00) around the outer periphery of the seal and the window frame. Do not apply adhesive to the frame in the area of the two stainless steel pneumatic tubes, nor to the areas of the seal that will fit over the tubes.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 3. Allow the adhesive to dry until tacky. 4. Position the seal on the window frame so that the flats are at the top and bottom and the uncemented areas are over the pneumatic tubes. Press the cemented mating surfaces firmly together. l.

Remove the protective paper from the window pane. Thoroughly clean the window pane and the polarized window using a lint free cloth and acrylic plastic cleaner (3, Chart 202, 56-00-00).

m. If necessary install the polarized window (Ref. POLARIZED WINDOW INSTALLATION) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed). n. If necessary install the electrochromic window shade (Ref. ELECTROCHROMIC WINDOW SHADE INSTALLATION) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). o. Place the upper sidewall panel and window assembly in position and stretch the flat rubber seal around the window shroud. Make sure that the seal lies flat all around the shroud. Make sure that the four vent holes in the top half of the shroud (two each at the two o’clock and the ten o’clock positions) are not blocked. p. Install the upper sidewall panel and window assembly (Ref. UPPER RIGHT VESTIBULE UPHOLSTERY PANEL INSTALLATION, 25-20-11) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed). q. Install the vestibule window panel (Ref. VESTIBULE WINDOW PANEL INSTALLATION, 25-20-11) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed).

BAGGAGE COMPARTMENT WINDOW REMOVAL a. Remove the baggage compartment upper sidewall panels (Ref. AFT COMPARTMENT UPPER SIDEWALL PANEL REMOVAL, 25-20-11) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed). b. Remove the baggage compartment sidewall panels (Ref. AFT BAGGAGE COMPARTMENT WINDOW PANEL REMOVAL, 25-20-11) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed). c.

If necessary, remove the four attaching screws which secure the inner window pane and shroud to the upper sidewall panel and remove the shroud and window pane (Ref. Figure 205).

d. Drill out the rivets attaching the window retainer to the window doubler (Ref. Figure 205, Detail A), and remove the retainer. e. Remove the outer window pane from the airplane. f.

Remove the old seal from the rim of the window pane.

BAGGAGE COMPARTMENT WINDOW INSTALLATION a. Lightly scuff all surfaces of the new seal (P/N 101-384246-5) with 400 grit sandpaper where sealer (16, Chart 202, 56-00-00) will be applied. b. Wipe the seal surface with solvent (7, Chart 202, 56-00-00) and wipe it dry immediately with a clean (lint free) dry cloth. Do not allow the naphtha to evaporate dry because it will leave a film on the area where sealant will be applied.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL c.

Apply a light coat of sealer (16, Chart 202, 56-00-00) in the seal. Install the seal (with sealing ridges on the outboard side of the window) around the rim of the window pane (Ref. Figure 205, Detail A). All surfaces of the seal must lay flat against the window.

d. Lightly scuff the doubler in the airframe cutout with 400 grit sandpaper where sealer (16, Chart 202, 56-00-00) will be applied. e. Apply a light coat of sealer (16, Chart 202, 56-00-00) on the doubler inside the airframe cutout to the bond the seal/window assembly to the airframe. f.

Center the seal/window assembly in place against the window doubler, then install the metal retainer ring and secure with attaching rivets (Ref. Figure 205, Detail A). Make sure the rivet holes in the retainer are aligned with those in the doubler.

g. Using a plastic fairing tool, smooth excess sealer which may squeeze out in the milled radius area. CAUTION: Use care not to cut or scratch the window pane when cutting away the center portion of the window seal. h. Using a single-edge razor blade, carefully cut away the center portion of the seal covering the outer surface of the window pane. Cut the seal flush with the cutout in the airplane skin. i.

If necessary, install the inner window pane and shroud on the upper sidewall panel (Ref. Figure 205, Detail B), and secure with the four attaching screws.

j.

Thoroughly clean the outer and inner window panes with a lint-free cloth and acrylic plastic cleaner (3, Chart 202, 56-00-00).

k.

Install the upper sidewall panel (Ref. AFT COMPARTMENT UPPER SIDEWALL PANEL INSTALLATION, 25-20-11) (FL-1 thru FL-600, FL-602 thru FL-671, FL-673 thru FL-687, FL-689 and After Without Cabin Management System Installed).

l.

Install the baggage compartment sidewall panels (Ref. AFT BAGGAGE COMPARTMENT WINDOW PANEL INSTALLATION, 25-20-11) (FL-601, FL-672, FL-688 and After With Cabin Management System Installed).

m. Apply erosion prevention sealant (Ref. EROSION PREVENTION SEALANT, 20-08-00).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OUTER SKIN

SEAL SHROUD

WINDOW DOUBLER

ATTACHING SCREW (4 PLACES) NAS1097 ATTACHING RIVETS

A

101-384246-5 SEAL

OUTER WINDOW PANE

UPPER SIDEWALL PANEL

SEALING RIDGES OUTER WINDOW PANE

B

WINDOW RETAINER

INNER WINDOW PANE

DETAIL

INSTALLATION TABS

A

UPPER SIDEWALL PANEL ATTACHING SCREW (4 PLACES) SHROUD

SEAL

INNER WINDOW PANE

WINDOW PANE AND SHROUD ATTACH POINTS

DETAIL

B

FL56B 985595AA.AI

Baggage Compartment Window Installation Figure 205

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C H A PT E R

VVINGS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 57 - WINGS TABLE OF CONTENTS SUBJECT

PAGE 57-00-00

Wings - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Wing Center Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Attach Fittings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Wings - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Wing Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Wing Disassembly. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .204 Wing Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .208 Wing Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .213 Wing Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .219 Wing Bolt Maintenance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Wing Bolt Nut and Spar Fitting Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Outboard Wing Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 Wing Center Section Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .220 57-30-00 Plates/Skin - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 57-50-00 Aileron - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Aileron Balancing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Checking Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Equipment Required to Perform Check Balancing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Balancing Procedure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Counterbalancing Method . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201

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List of Effective Pages CH-SE-SU

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1 thru 4

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Hawker Beechcraft

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

WINGS

airplane consists of the center section and two outboard wing assemblies. The center section is fuselage and forms an integral part thereof, providing structural support for the engine nacelles and the outboard wing assemblies. Each outboard wing assembly is attached to the center section with three tension bolts and one shear bolt. The three tension bolts are located at the upper and lower aft spar attach points and at the upper forward main spar attach point. The shear bolt is installed at the lower forward main spar attach point. The

wing

on

this

riveted to the

The center section and outboard

wing

assemblies

are

of

semimonocoque

box construction. Both center section

I-beam sections built up from aluminum extruded tee caps, webbing and stiffeners. Similar construction spars is used in the outboard wing spars, except that a combination of aluminum extruded cap and extruded U-channel members comprise the main spar caps while those of the rear spar are composed of formed aluminum angles and are

cap

strips.

leading edge assembly and the main outboard wing assembly are joined together at the main spar by continuous hinges. A subspar is installed at the aft end of the leading edge. The space forward of this subspar is utilized to route wiring and plumbing. Between the subspar and the main spar, bladder fuel tanks are installed the full span of the outboard leading edge. The

faying-surface-sealed integral (wet wing) fuel tank is installed in the outboard end of each outboard wing assembly. The tank interior is coated for corrosion protection and is accessible through o-ring sealed doors in the lower wing skin. Inboard of the integral tanks, bladder fuel tanks are installed.

A

WING CENTER SECTION rear spars are parallel and are continuous from one outboard wing attach joint to the joint. A subspar is installed forward of the main spar between the fuselage and each nacelle to which a removable leading edge is attached. The area within the removable leading edge and forward of the subspar is used to route engine controls, plumbing and wiring, etc. A subspar located forward of the rear spar provides a tunnel for control cables and flap drive shafts and serves as a fuel wall for the bladder tanks from the root rib to the nacelle. Landing gear hinge point structural supports in the nacelles are made of machined alloy plate. Formed sheet metal formers and stringers establish the nacelle fairing and a cavity for a bladder fuel tank above

The center section main and other outboard

wing

attach

and forward of the wheel well.

A TTA CH FITTINGS

major fittings in each wing and center section are the supporting structures adjacent to the attachment points flap actuator, flap tracks and flap, the aileron hinge brackets and hinges, the main landing gear, drag legs and landing gear doors. Minor fittings include brackets to support cable pulleys, bellcranks and similar components. The main gear is bolted to heavy aluminum alloy fittings attached to the main rib assembly at the aft end of the wheel well. The main gear drag leg is bolted to an aluminum alloy forging attached to the main spar of the center section. If the landing gear support channels are warped or buckled, or if the landing gear hinge bolt extrusions are cracked, The

for the

replacement

is necessary.

SPECIAL TOOLS AND RECOMMENDED MATERIALS

special tools and recommended materials listed in Charts 1 and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. I Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance with I the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO The

THE REQUIREMENTS OF THE SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE

CHARTS.

az2

Only

the basic number of each

specification

is listed. No attempt has been made to

update

the

listing

57-00-00Page

to

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

the latest revision. It is the

responsibility applicable specification prior to usage of product to be used.

of the technician the

product

or

mechanic to determine the current revision of the

listed. This

can

be done

by contacting

supplier of

the

the

Chart 1

Special TOOL NAME

II’

Aligning

Pin

or

101-120125-1 D943

USE

SUPPLIER

PART NUMBER

101996 PIN

Tools

Hawker Beechcraft

Corporation Wichita, KS 67201

For

installing

removing the wing bolt in the clevis-type spar fitting at the wing attach

2.

GreaseGun

3.

Alemite grease nozzle

Obtained

314150

Locally.

Stewart-Warner Alemite Sales Co., Inc. 10901 Ist St.

Omaha, NE 68137-01206

4.

GreaseGun-Lever Action

500141

(LG445)

Lubrication 3851

Engineers Airport Freeway

Fort Worth, TX 76111

Page

yaM2

1/07

57-00-00

and

lower forward

point.

injecting corrosion preventive compound into the lubrication fittings in the barrel nuts in the upper forward wing attach point fittings. For

For fitting to grease gun for injecting corrosion preventive compound into the lubrication fittings in the barrel nuts in the upper forward wing attach point fittings. For

lubricating

the

wing

bolts.

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 Recommended Materials

Lubricating Oil, Special Preservative

1.

Air BP Lubricants Division

300

Brayco

MIL-PRF-32033

SUPPLIER

PRODUCT

SPECIFICATION

MATERIAL

BP Products North America NJ 07054-4406

Parsippany, Royco

Anderol Inc.

308CA

215

Merry

Lane

P.O. Box 518 East Hanover, NJ 07936 Nor Rust 518

(Code

R-62-

I

Daubed Chemical Co. 4700 S Central Ave.

2103-1)

Chicago,

IL 60638-1531

CRC Chemicals, U.S.A Warmister, PA

*CEC3-36

LPS No. 1

Holt

Lloyd Corp. Hugh Howell

4647

Rd.

Tucker, GA 30084-5004 WD40

WD40

1061 San 2.

American Grease Stick Co.

Door-Ease

Lubricant

Company Cudahy PI. Diego, CA 92138

2651

Hoyt, Muskegon,

3.

Solvent

TT-N-95

4.

Solvent

5.

Corrosion Preventive

MIL-PRF-16173

Compound

Grade 2

Naphtha Methyl Propyl

Ketone

NOX-RUST 502-LS

MI 49443

Obtained

Locally.

Obtained

Locally.

Daubed Chemical Co. 4700 S. Central Ave.

Chicago, MIL-PRF-16173

Braycote

194

IL 60638

Air BP Lubricants Division

BP Products North America

Grade 4

Parsippany,

May

be used

as a

field substitute for

Brayco

300 for

use

in trim tab

hinges; however, Brayco

NJ 07054-4406

300 is the

preferred

product.

A22

57-00-00

May 1 07Page

3

Hawker Beechcraft Corporation SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TS1222-5 OR TS1 222-4 WRENCHES TO BE USED ON THE BOLT SIDE OF THE BOLT/NUT ASSEMBLY AT THE UPPER AND LOWER AFT WING ATTACH PO)NTS

TS1176-11 TOROUE

oO

WRENCH ADAPTER TO BE USED ON THE NUT SIDE OF THE BOLTINUT ASSEMBLY AT THE UPPER AND LOWER AFT WING POINT

I/

,o

\ATTACH

11001 A 1-1/1S-INCH BOX END WRENCH ADAPTER FOR USE WlTH A TORQUE WRENCH. TO BE USED ON THE NUT SIDE OF THE LOWER FORWARD WING ATTACH POINT

10996 OR 101-120125-10943

ALIGNING PIN

350-17-20

Wing

Bolt Installation Tools

Figure

May

1/07Page

4

57-00-00

TS 1176-6 TORQUE WRENCH ADAPTER TO BE USED ON THE BOLT SIDE OF THE BOLTI BARREL NUT ASSEMBLY AT THE UPPER FORWARD WING ATTACH POINT

1

A22

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WINGS - MAINTENANCE PRACTICES

200200200

WING REMOVAL The following procedure outlines the removal of the outboard section of the wing from the center section (Ref. Figure 201): CAUTION: If the wing is to be disassembled after removal, liberally apply an aerosol spray of penetrating lubricant (1, Chart 2, 57-00-00) to the entire accessible length of each spar hinge as soon as possible after the airplane is turned over for maintenance. Allow the lubricant to soak in as long as possible (at least 12 hours) before attempting to remove the hinge pins. NOTE: When plumbing lines are disconnected, they must be capped immediately to prevent contamination of the respective system. a. Disconnect the electrical leads from the battery. b. Drain and purge the wing fuel cells. CAUTION: Fuel must be purged from all fuel tanks in both wings. c.

Position a tail stand under the tail of the airplane and support both wings to ensure stability of the airplane during and after removal of the wing.

d. Remove the skin plate located on the upper and lower center section immediately outboard of the nacelles and over the wing attach bolts (1). e. Disconnect the aileron cables (both wings) and the trim tab cables (left wing only) (7) at the turnbuckles in the wheel well (Ref. AILERON REMOVAL, 27-10-00). f.

Disconnect the split-flap safety mechanism at the wing break (Ref. FLAP SAFETY MECHANISM, 27-50-00).

g. If the wing is to be disassembled after removal, remove the fuel cells (Ref. INBOARD LEADING EDGE FUEL CELL REMOVAL, 28-10-00). Remove the aileron (Ref. AILERON REMOVAL, 27-10-00). Carefully peel back the deicer boot (Ref. SURFACE DEICER BOOT REMOVAL, 30-10-00) to expose the wing tip. Remove the wing tip as follows: 1. Disconnect the wing-tip light electrical leads at the fixtures. NOTE: When plumbing lines are disconnected, they must be capped immediately to prevent contamination of the system. 2. Remove 47 screws securing the winglet to the wing. 3. Support the winglet and pull it away from the wing. CAUTION: Remove the strobe light lead pins with a matrix tool only. Other tools will damage the pins, sockets or leads. 4. Disassemble the strobe light electrical connector and mark the pin locations of the leads to aid later installation. Remove the lead pins with a matrix tool. NOTE: Leave the outboard leading edge fuel cell in place until the spar is removed from the leading edge. h. Remove the inverter access door (2).

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57-00-00

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL i.

Remove the wing bolt access covers (3).

j.

Remove the inboard access cover from the lower side of the outboard wing (5).

k.

Disconnect the flexible drive shaft from the flap actuator (6).

l.

Disconnect the pneumatic line from the deicer boot hose (8). NOTE: When plumbing lines are disconnected, they must be capped immediately to prevent contamination of the system.

m. Disconnect all electrical connectors between the wing and the center section. n. Disconnect the fuel and vent lines from the wing center section (9). o. Remove the electrical bonding cables and disconnect the fuel cell interconnect tube (10). p. Support the wing being removed with a suitable cradle. Support the opposite wing in order to assure airplane stability during and after removal of the wing. NOTE: Prior to removing the wing attach bolts, mark (but do not scribe or scratch) the wing and center section fittings to determine their positions relative to one another to aid in wing realignment. q. Loosen the upper forward and upper and lower aft attach bolts. r.

Remove the lower forward attach bolt.

CAUTION: The lower forward wing bolt must be carefully driven out with an aligning pin and a rawhide mallet. The aligning pin is available from Hawker Beechcraft Global Customer Support Parts and Distribution Division as P/N 10996 PIN or P/N 101-120125-1D943. Care must be exercised not to damage the bolt threads or the interior surface of the bolt bore in the wing attach fittings during the driving operation. There should be no binding of the bolts during removal of the upper forward or the upper or lower aft wing attach bolts. The wing must be repositioned as necessary to alleviate any possible binding of the bolts during removal. s.

Remove the remaining wing attach bolts. Pull the wing straight away from the airplane until clear of all plumbing, cables and wiring.

Page 202 May 1/10

57-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Wing Removal Figure 201

A28

57-00-00

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WING DISASSEMBLY a. Support the wing on a suitable cradle. b. Remove the screws around the spar caps at the root and root tip ribs. c.

At the outboard end of the wing, free the ends of the hinge pins. Remove the hinge pins as follows (Ref. Figure 202 Sheet 1, 2, and 3): CAUTION: Never use a drill motor to spin a hinge pin in or out of the hinge. The resulting friction heat will cause the pin to expand and seize in the hinge. NOTE: Before removing any single hinge pin, pull all hinge pins out 1 inch (2 hinge lugs) to break any adhesion or binding caused by corrosion or buildup of dust. Remove the hinge pins from the wing section first, then from the leading edge. Support the leading edge/spar assembly while the second main wing hinge pin is being removed to prevent the assembly from falling away from the wing. 1. Method 1 a) Clamp locking pliers (or equivalent) tightly on the pin. b) Place a board in a suitable position on the wing spar to use as a fulcrum for a lever. CAUTION: Use slow, steady pressure on the lever to avoid breaking the hinge pin. c) Bring the lever to bear against the locking pliers and pry the hinge pin out of the hinge. d) Use thicker boards and shift the position of the locking pliers as the hinge pin is pulled out of the spar. 2. Method 2 a) Fabricate a support bracket and crank (Ref. Figure 202 Sheet 3). b) Attach the bracket to the end stiffener of the spar with two screws (Ref. Figure 202 Sheet 2). c) Insert the crank through the bracket. Align the hole in the crank so the tension will be applied to the hinge pin in as straight a line as possible. d) Insert the free end of the hinge pin through the hole in the crank. WARNING: Keep clear of the hinge pin end when the hinge pin is nearly removed. The sudden release of tension may cause the pin to spring free at high velocity. CAUTION: Use slow, steady rotation of the crank to avoid breaking the hinge pin. e) Turn the crank to pull the hinge pin out of the hinge. f)

Remove the support bracket when the hinge pin has been removed.

d. After the spar is separated from the leading edge, install a temporary hinge pin into each open hinge to prevent damage, distortion or blockage of the hinge lugs during handling. e. If the spar is to be replaced, remove the fuel vent line from the spar. Retain the line for reinstallation on the new spar. f.

Remove the outboard leading edge fuel cell from the leading edge.

Page 204 May 1/10

57-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL g. Inspect the interior of each fuel cell bay for loose, torn, cracked or missing anti-chafing tape. Apply tape as shown over any exposed rivets, fasteners, sheet metal edges or protrusions which might scuff the fuel cell (Ref. Figure 203). h. Pressure-check each fuel cell for leaks (Ref. FUEL CELL LEAKAGE TEST, 28-10-00). i.

Inspect the entire interior and structure of the wing and leading edge for corrosion or damage.

Wing Hinge Pin Removal Figure 202 (Sheet 1 of 3)

A28

57-00-00

Page 205 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Wing Hinge Pin Removal Figure 202 (Sheet 2 of 3)

Page 206 May 1/10

57-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Wing Hinge Pin Removal Figure 202 (Sheet 3 of 3)

A28

57-00-00

Page 207 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Anti-Chafing Tape Application Figure 203

WING ASSEMBLY a. Place the leading edge in locally fabricated cradles (Ref. Figure 204). b. Install the outboard leading edge fuel cell into its bay in the leading edge and secure all retaining buttons to the inner top surface of the leading edge. NOTE: Ensure that the fuel cell is pressure-checked for leaks before installation. c.

Install the fuel cell (Ref. INBOARD LEADING EDGE FUEL CELL INSTALLATION, 28-10-00).

d. Apply anti-chafing tape around the lip of the outboard leading edge fuel cell bay, so that the tape will seal to the spar when it is installed (Ref. Figure 203). e. Grind a conical point on one end of each new hinge pin to ease installation. NOTE: Use only new hinge pins. Provide several extra pins in case any are damaged or bent during installation. Never attempt to install a bent or distorted hinge pin. f.

Remove the temporary pins from the hinges of the leading edge and the forward hinges of the spar. Leave in place the temporary pins in the aft hinges of the spar.

g. Lubricate each open hinge lug and new pin with water-displacing lubricant (1, Chart 2, 57-00-00).

Page 208 May 1/10

57-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL h. Position the spar on the leading edge and align the hinge sections. Ensure that the antichafing tape around the edge of the outboard leading edge fuel cell bay seals properly on the spar. NOTE: If necessary, gently tap the spar into alignment with a rawhide mallet. i.

Insert the pointed end of the pin into the spar and slide it into the hinge as far as possible by hand. Slide the telescoping tubes of Repair Kit 35-5885 over the pin. NOTE: If necessary, apply lubricant (2, Chart 2, 57-00-00) or an equivalent beeswax preparation to the hinge pins to ease installation.

j.

Place supports at a suitable height to align the telescoping tubes to the hinge. Clamp a stout bungee cord or spring to the larger tube and attach it to the spar (Ref. Figure 205), so that the tube is held firmly against the hinge throughout the pin installation. Use the longest tubes at the beginning of the installation and change the tubes as necessary as the pin is driven into the hinge. CAUTION: Do not allow the hinge pin to strike the wing attach fitting. Measure the hinge and the hinge pin before installation to determine the proper installation distance. Mark the hinge pin to indicate a safe stopping point. NOTE: Always keep the end of the inner (smaller) tube tight against the spar to avoid bending or kinking the pin in the intervening gap. If a bungee cord or spring is not available, station a person at the end of the tube to hold it firmly against the spar with locking pliers.

k.

Drive the pin in the hinge, using an E-4 rivet gun or equivalent and a rivet set with a 3/32 inch hole. Replace the telescoping tubes as necessary to properly support the hinge pin until the hinge pin is completely driven, then remove the tubes. Continue driving the hinge pin until it is completely through the last hinge loop, but not in contact with the wing attach fitting. NOTE: If necessary, vibrate the spar with a rawhide mallet or another rivet gun to aid installation. If a rivet gun is used, place a phenolic block between the spar and the gun to protect the spar.

l.

Insert the free end of the hinge pin into a convenient hole in the end of the spar, or tape it to the end of the spar, to keep it from interfering during the installation of the remaining pins.

m. Repeat steps i thru l for the remaining hinge. n. If a new spar is installed, install the fuel vent line on the new spar in the same manner and location as on the old spar. Ensure that the vertical stiffeners have flat, smooth edges near the line and that they provide adequate clearance for the line. o. Remove the temporary pins from the hinges of the main wing and the aft hinges of the spar/leading edge assembly. p. Lubricate each open hinge lug and new pin with water-displacing lubricant (1, Chart 2, 57-00-00). NOTE: If necessary, apply lubricant (2, Chart 2, 57-00-00) or equivalent beeswax preparation to the hinge pins to ease installation. q. Position the assembled spar and leading edge on the main wing section and align the hinge sections. NOTE: If necessary, a strap or belt of webbing may be used to cinch the spar into place (Ref. Figure 206), and a rawhide mallet may be used to gently tap the spar into alignment. If a strap is used, locate it over a stiffener or other structure to avoid damage to sheet metal. r.

Repeat steps i thru l for the remaining hinges.

A28

57-00-00

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL s.

Trim the excess length of the pins to 4.88 ± 0.12 inches. Loop both ends clockwise around the nearest screw on the spar end stiffener and tighten. Allow the washer to retain the loops.

t.

Install the screws around the spar caps at the root and root tip rib.

u. Paint the wing and spar as required.

Leading Edge Cradle Figure 204

Page 210 May 1/10

57-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Hinge Pin Installation Figure 205

A28

57-00-00

Page 211 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Wing Assembly Strap Figure 206

Page 212 May 1/10

57-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WING INSTALLATION WARNING: Upper forward and upper and lower aft wing bolts and nuts that have reached their life limit (10 years of installed time) must be replaced with new components. Clean all wing attach fittings and hardware (bolts, washers and nuts) thoroughly using a nonmetallic brush and solvent (3 or 4, Chart 2, 57-00-00). Inspect all wing attach components in accordance with WING BOLT, NUT AND SPAR FITTING INSPECTION in this chapter. a. Coat the bolt bores and washer/nut bearing surfaces of each fitting, each bolt, washer and nut with corrosion preventive compound (5, Chart 2, 57-00-00). WARNING: The soft aluminum washer between each upper fitting must be replaced any time the fittings are separated or repositioned. All washers having countersinks must mate with the head of the bolt on the upper forward and the upper and lower aft wing bolts. b. With the wing supported on a suitable cradle, carefully move the wing into mating position with the center section, route and position all of the various cables, plumbing and wiring as necessary to prevent damage to them. c.

Install the upper forward, the upper and lower aft wing attach bolts, washers and nuts in their respective locations, but do not tighten the bolts at this time.

CAUTION: Each bolt must be inserted by hand without binding. If a bolt cannot be easily inserted, reposition the wing until the bolt moves freely. Be certain that the lubrication fitting on the barrel nut (Ref. Figure 211) in the upper forward wing attach position is accessible. d. Position the wing so that the lower forward wing attach bolt hole in the wing aligns perfectly with the bolt hole in the center section. e. Install a special aligning pin (P/N 10996 PIN or P/N 101-120125-1/D943) coated with corrosion preventive compound (5, Chart 2, 57-00-00) into the lower forward wing attach bolt hole from the forward side of the wing. Care should be exercised when driving the pin so the bolt bore is not damaged. f.

Insert the lower forward wing attach bolt, with one AN960PD1416L washer and one NAS1515H14 nylon washer under the bolt head, into the forward side of the bolt hole and carefully drive it into the hole with a rawhide mallet, simultaneously driving out the aligning pin. The washers and bolt head must seat firmly against the surface of the fitting (Ref. Figure 207).

g. Install one NAS1515H14 nylon washer under the nut and install the nut. Should the slot in the nut not align with the lockwire hole in the bolt, install one AN960PD-1416L washer between the nylon washer and the nut and torque the nut at 30 inch pounds to 50 inch pounds (Ref. Figure 207). The slot in the nut must align with the lockwire hole in the bolt after torquing. Safety the bolt with MS20995C41 safety wire. h. Position the wing as necessary so the other three bolts which were installed in step c can be turned freely without binding. CAUTION: Ensure that the wing bolt wrenches do not bottom out on the wing fittings during the following torquing procedure to prevent damage to the fittings and/or false torque readings. i.

Tighten the upper forward and the upper and lower aft wing attach bolts per the applicable illustrations (Ref. Figures 208, 209 and 210). Torque the upper aft bolt first, then the upper forward and finally the lower aft bolt. Torque the upper forward bolt at the bolt head and the upper and lower aft bolts at the nut. When a torque wrench adapter is used, the length of the adapter must be added to the length of the torque wrench for adjustment of the torque requirements (Ref. TORQUE WRENCHES, 20-01-00).

A28

57-00-00

Page 213 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL j.

When torquing procedures have been completed, inject additional corrosion preventive compound (5, Chart 2, 57-00-00) into the lubrication fitting of the barrel nut (Ref. Figure 211) on the upper forward attach fitting with a high quality grease gun fitted with an Alemite 314150 nozzle. Sufficient corrosion preventive compound has been added when one of the following criteria has been met: 1. The corrosion preventive compound emerges from between the two portions of the barrel nut assembly. 2. The compound emerges from the threaded portion of the bolt. NOTE: If the lubrication fitting fails to accept additional compound when the grease gun is repeatedly pumped, the fitting is clogged and should be replaced with a new NAS516-1 fitting.

k.

Coat the exposed threads of the wing bolts with corrosion preventive compound (5, Chart 2, 57-00-00).

l.

Connect the wing fuel cell interconnect tube and attach the electrical bonding cables.

m. Connect the fuel vent lines. n. Support the winglet and place it next to the wing tip. o. Connect the winglet to the wing tip with the attaching screws. p. Mate the electrical connectors. q. Connect the aileron and trim tab control cables at the turnbuckles in the wheel well. r.

Connect the flap flexible shaft to the outboard flap actuator.

s.

Connect the pneumatic line to the deicer boot hose.

t.

Rig the aileron and trim tab control cables (Ref. AILERON CONTROL SYSTEM RIGGING and AILERON TAB RIGGING, 27-10-00).

u. Rig the flaps (Ref. FLAP CONTROL SYSTEM RIGGING, 27-50-00). v.

Secure the wing-to-nacelle fairing to the center section with the attaching screws.

w. Connect the wing-tip lights and install the wing tip. x.

Seal the deice boot at the wing tip (Ref. Sealing of Deicer Boot Edges, 30-10-00).

y.

Remove the tail stand and wing supports.

z.

Refuel the airplane (Ref. FUEL HANDLING PRACTICES, 12-20-00).

aa. Check all connections for leakage and correct as necessary. ab. When it has been ascertained that there is no fuel leakage, connect the electrical power. ac. Check for proper operation of the fuel quantity transmitters, strobe lights and navigation light. ad. Install all access covers and doors. ae. Test fly the airplane to ensure proper wing and stall warning vane adjustment.

Page 214 May 1/10

57-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FL57B985320AA.AI

Lower Forward Wing Bolt Installation Figure 207

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57-00-00

Page 215 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NAS578-12B RETAINER

80691CF-1216 BARREL NUT ASSEMBLY

LUBRICATION FITTING 101-100011-1 WASHER

81784-12-32 OR VCC0025 BOLT (USE TS1176-6 TORQUE WRENCH ADAPTER)

101-110023-3 WASHER

WING FITTING OUTBOARD

WING FITTING CENTER SECTION

BOLT TORQUE: 2380 TO 2500 INCH-POUNDS. COAT THE COMPLETE BOLT, NUT, WASHER, AND WING FITTING BOLT BORES WITH MIL-PRF-16173, GRADE 2 CORROSION PREVENTIVE COMPOUND. AFTER TORQUING THE BOLT USE A HIGH QUALITY GREASE GUN AND AN ALEMITE P/N 314150 GREASE NOZZLE TO INJECT MIL-PRF-16173, GRADE 2 CORROSION PREVENTIVE COMPOUND INTO THE BARREL NUT LUBRICATION FITTING. COAT THE EXPOSED THREADS WITH CORROSION PREVENTIVE COMPOUND. POSITION THE 101-100011-1 WASHER WITH THE COUNTERSINK AGAINST THE BOLT HEAD RADIUS AND THE OUTER RADIUS AGAINST THE RADIUS IN THE WING FITTING; CHECK THE WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS.

REFER TO CHART 201 FOR THE WING BOLT WRENCHES AND TORQUE ADAPTERS USED WITH THIS WING BOLT AND NUT.

FL57B 985322AA.AI

Upper Forward Wing Bolt Installation Figure 208

Page 216 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

95-110025-3 WASHER (POSITION WITH RADIUS TOWARD THE WING FITTING)

35-105111-3 WASHER (INSTALL WITH COUNTERSINK TOWARD BOLT HEAD)

81783-1018 NUT

81786-10-20 OR VCN0018 BOLT

WING FITTING OUTBOARD MS20002-10 WASHER DRAIN HOLE

101-110023-1 WASHER

DRAIN HOLE

WING FITTING CENTER SECTION

BOLT TORQUE: 1180 TO 1300 INCH-POUNDS. COAT THE COMPLETE BOLT, NUT, WASHERS, WING FITTING BOLT BORES, AND EXPOSED BOLT THREADS WITH MILPRF-16173, GRADE 2 CORROSION PREVENTIVE COMPOUND. CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS. AN MS20002-10 WASHER MAY BE USED BETWEEN THE NUT AND THE RADIUSED WASHER TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT.

REFER TO CHART 201 FOR THE WING BOLT WRENCHES AND TORQUE ADAPTERS USED WITH THIS WING BOLT AND NUT.

CAUTION INSPECT THE WING ATTACH FITTINGS TO ENSURE THAT THE DRAIN HOLES ARE CLEAR

FL57B 985321AA.AI

Upper Aft Wing Bolt Installation Figure 209

A28

57-00-00

Page 217 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

REFER TO CHART 201 FOR THE WING BOLT WRENCHES AND TORQUE ADAPTERS USED WITH THIS WING BOLT AND NUT.

95-110025-3 WASHER (POSITION WITH RADIUS TOWARD THE WING FITTING)

81783-1018 NUT

35-105111-3 WASHER (INSTALL WITH COUNTERSINK TOWARD BOLT HEAD)

81786-10-20 OR VCN0018 BOLT

WING FITTING OUTBOARD

WING FITTING CENTER SECTION MS20002-10 WASHER

BOLT TORQUE: 1180 TO 1300 INCH-POUNDS. COAT THE COMPLETE BOLT, NUT, WASHERS, WING FITTING BOLT BORES, AND EXPOSED BOLT THREADS WITH MILPRF-16173, GRADE 2 CORROSION PREVENTIVE COMPOUND. CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS. AN MS20002-10 WASHER MAY BE USED BETWEEN THE NUT AND THE RADIUSED WASHER TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT.

FL57B 985323AA.AI

Lower Aft Wing Bolt Installation Figure 210

Page 218 May 1/10

57-00-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 Wing Bolt Tools BOLT POSITION

BOLT PART No.

WRENCH PART No.

NUT PART No.

NUT TORQUE ADAPTER

Upper Forward

81784-12-32 or VCC0025

TS1176-6

80691CF-1216 (Barrel Nut)

None Required.

Lower Forward

130909B175

11/4 inch box-end wrench

130909N46

11001

Upper and Lower Aft

81786-10-20 or VCN0018

TS1222-5

81783-1018

TS1176-11

WING ADJUSTMENT Adjustment of the outer wing panel angle of incidence is not ordinarily necessary. Most prevailing wing-heavy conditions can be traced to improperly rigged ailerons or flaps. If, however, the ailerons and flaps are properly rigged, change the angle of incidence of one of the wings slightly. It is desirable to have the trailing edges of both wings as high as possible to minimize fuselage drag; consequently, when one wing is heavy, the trailing edge of the opposite wing should be raised, decreasing its lift relative to the heavy wing. Only if this is not possible should the trailing edge of the heavy wing be lowered. If this combination does not correct the wing-heavy condition, rig the flaps of the heavy wing slightly down. Do this only as a last resort since it will result in additional drag on the airplane. Wing adjustment can be accomplished without loosening the lower forward wing attach bolt. Loosen only the upper forward and the upper and lower aft wing attach bolts. Before loosening the wing attaching bolts to adjust the wing incidence angle, mark (but do not scribe or scratch) the position of the wing fittings on the center section fittings for a reference point. Replace both soft aluminum washers between the upper forward and the upper rear fittings. CAUTION: Ensure that the wing bolt wrenches do not bottom out on the wing fittings during the following torquing procedure to prevent damage to the fittings and/or false torque readings. a. Tighten the wing bolts to the torque specified for each respective bolt in the applicable illustration (Ref. Figures 208, 209 or 210). Torque the upper forward bolt at the bolt head and the upper and lower aft bolts at the nut. When a torque wrench adapter is used, the length of the adapter must be added to the length of the torque wrench for adjustment of the torque requirements (Ref. TORQUE WRENCHES, 20-01-00). b. When torquing procedures have been completed, inject additional corrosion preventive compound (5, Chart 2, 57-00-00) into the lubrication fitting of the barrel nut (Ref. Figure 211) in the upper forward wing bolt position with a high quality grease gun fitted with an Alemite 314150 nozzle. Sufficient corrosion preventive compound has been added when one of the following criteria has been met: 1. The corrosion preventive compound emerges from between the two portions of the barrel nut assembly. 2. The compound emerges from the threaded portion of the bolt. NOTE: If the lubrication fitting fails to accept additional compound when the grease gun is repeatedly pumped, the fitting is clogged and should be replaced with a new NAS516-1 fitting. c.

Coat the exposed threads of the wing bolts with corrosion preventive compound (5, Chart 2, 57-00-00).

A28

57-00-00

Page 219 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL WARNING: When adjusting the wing, always replace both soft aluminum washers. Check all upper forward and upper and lower aft wing bolts for proper torque at the first scheduled inspection of the airplane.

Barrel Nut Assembly Figure 211

WING BOLT MAINTENANCE Refer to Structural Inspection and Repair Manual (P/N 98-39006C or subsequent) for maintenance procedures and intervals.

WING BOLT NUT AND SPAR FITTING INSPECTION Refer to Structural Inspection and Repair Manual (P/N 98-39006C or subsequent) for maintenance procedures and intervals.

OUTBOARD WING INSPECTION Refer to Structural Inspection and Repair Manual (P/N 98-39006C or subsequent) for maintenance procedures and intervals.

WING CENTER SECTION INSPECTION Refer to the Structural Inspection and Repair Manual (P/N 98-39006C or subsequent) for maintenance procedures and intervals. Inspect the left and right wing center section bonded panel upper skin (Ref. WING CENTER SECTION BONDED PANEL UPPER SKIN INSPECTION, 51-00-00).

Page 220 May 1/10

57-00-00

A28

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PLATES/SKIN The

following

illustrations indicate

maintenance and

na,

MAINTENANCE PRACTICES

repair procedures

access as

locations to various components of the airplane in order to perform for scheduled and unscheduled maintenance of the airplane.

required

57-30-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

?6 23

5 6

4

4

7 26 6 5

3

O MAIN SPAR

I

1

II Ift-----1

21----cb

1

8

I

II

I\

9

P

24

---21

I

9

8

RH UPPER

LH UPPER

11

12

25 13

14

26

26

14

13

11

1? 25

O 18 19

19

MAIN SPAR 17

20

20

22

15

16

16

RH LOWER

15 LH tOWER 300-14-1

Wing

Center Section Access

Figure

May

1/0857-30-00

201

(Sheet

1 of

Openings 2)

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1,

2.

3.

Landing Gear Attach Bolts, Deicer Plumbing, Electrical Wiring, Fuel Line, External Power Relay(RH o~ly). Fuel Pressure Switch IMotive Flow Valve). Check Valve, Wing Bolt, Deice Plumbing, External Power Receptacle (RH only). Fuel Control Purge Valve, Transfer

Printed Circuit Board (RH only). 14.

Bleed Air

Control Motive Flow Valve, Fire Ex-

tinguisher Plumbing, Engine Control Cables, Firewall Electrical Connec-

15,

tor, Pneumatic Line and Solenoid

18.

Valve (LH 4.

engine).

ACcess to Nacelle Fuel Cell, Fuel

Quantity Probe, Fuel Plumbing, Check 17.

Valve. 5,

Check Valves, Check Valves, Transfer

Forward Electrical Power DiStri-

Jet

bution Panel. 6.

7. 8. 9.

10. ii.

12.

Aft Electrical Power Distribution

18.

Panel.

19.

Battery. Auxiliary Fuel System Filler. Auxiliary FuelGell Access, Fuel Quantity Probe. Fuel Quantity Probe, Wheel Well-Hydraulic, Fuel and Pneumatic Plumbing, Power Control Cables, Engine Fire Extinguisher Cylinders, Electrical Wiring, Flap Rigging Terminals (RH only).

Pump, Fuel

Switch,

Receptacle. Wiring and Connectors, Fuel Line, Lower Forward Wing Bolts, External Power Relay (RH only). External Power Electrical

Wing Bolts.

20.

Lower Aft

21.

UpperAftWing Bolts. Plumbing fittings, pressure

22.

seals

and aileron cable seals. Gear Service.

24,

HydraulicLanding Flap Switches.

25.

Fuel Firewall Shutoff Valve,

23.

Fire

Extinguisher Plumbing,

Engine Pneu-

Outlet Strainer and Drain, Standby

matic Line and Solenoid Valve,

Boost

Pump Inlet Strainer, Pump Drain, Radio Filter, Fuel Quantity

(RH engine).

Support. Heat Exchanger, Bleed Air Plumbing, Bleed Air Bypass Valve Micro Switch (LH only), Fuse Panel with Spare Fuses, Hydraulic Landing Gear Pump and Motor (LH only). Compressor Clutch Control Panel, Compressor Clutch Voltage Drop Resistor, Electronic Time Delay

Wiring, Air Conditioner Plumbing JRH only). Engine Control Cables, Deicer Plumbing, Hydraulic Plumbing, Wire Bundles, Instrument Air Lines, Refrigerant Lines (RH only),

Firewall Electrical Connector and

Probe 13.

Exchanger, Bleed

Air Plumbing, Bypass Valve, Bleed Air Bypass Valve Micro Switch (LH only), Compressor Clutch Control Panel, Compressor Clutch Voltage Drop Resistor, Electronic Time Delay Printed Gircuit Board, Battery Air Vent Line (RH only), Starter Solenoids, Bleed Air Plumbing. Landing Gear Bolts. Bleed Air Plumbing Flap Torque Shaft, Aileron Control Cables, nap Actuator Aileron Tab Cables (LH only), Emergency Bus Fuses(RH only). Fuel Outlet Strainer and Drain,

Heat

26,

Air Conditioner

High

Pressure Switches

and Low

(RH only).

FL57B 991542AA

Wing Center Section Access Openings Figure 201 (Sheet 2 of 2)

A24

57-30-00

Page

203Mayl/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1

5

5

4

3

2

4

3

j

7

2

1

7

8

9

8

UPPER

14

11

10-7

re

12

Ip

n

I

I

17

Ip

IS

24

16

24

14

j

1~

Ip

12

18

11

I

I

I

A

I

20 21

12

~j

12

21

16

20

17

25

LOWER

i.

FUEL PLUMBING. STROBE LIGHT WIRING

15.

EXTERNAL POWER RECEPTACLE

2.

FUELFILLER

16.

LOWER FWD. WING BOLTS

3.

FUEL QUANTITY PROBE

17.

INTEGRAL

4.

FUEL QUANTITY PROBE

18.

FUEL OUANTITY PROBES

5.

FUEL CELL. FUEL QUANTITY PROBE AND

19.

FUEL VENT LINE

(WET WING) FUEL CELL

FUEL SYSTEM PLUMBING AND ELECTRICAL

CONNECTORS. AILERON TRIM TAB

6.

UPPER FWD. WING BOLT

7.

AILERON BELL CRANK, PUSH ROD AND STOPS

ACTUATOR 20.

(LH ONLY)

AILERON BELL CRANK AND STOPS

8.

FUEL VENTS AND DRAINS

21.

AILERON PULLEY AND FAIRLEAD

9.

UPPER AFT WING BOLT

22.

AILERON PULLEY

10.

FUEL CELL PLUMBING AND SUCTION RELIEF VALVE

23.

OUTBOARD FLAP ACTUATOR

11.

LEADING EDGE FUEL CELL AND PLUMBING

24.

FUEL VENTS, FLAME ARRESTER AND VER-

12.

LEADING EDGE FUEL CELL AND PLUMBING

13.

AFT OUTBOARD FUEL CELL

25.

LOWER AFT WING BOLTS

14.

AFT INBOARD FUEL CELL

26.

AILERON TRIM TAB ACTUATOR (LH ONLY)

TICAL LINE CHECK VALVE

350-)2-3

Wing

Access

Figure

May

57-30-00

Openings 202

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AILERON

MAINTENANCE PRACTICES

AILERON BALANCING After

repainting and/or repair, the finished aileron must be checked to makes sure that its static moment about the line is within the prescribed limits. The prescribed limits are 8.80 to 10.00 pound-inches nose heavy. The static moment of aileron is determined by multiplying the unbalanced weight of the aileron assembly times the perpendicular distance from the hinge center line to the center of gravity when the chord line is horizontally level. The weight is measured in pounds and the distance in inches.

hinge

CHECKING BALANCE The balance must be checked in

a draft free area with the aileron completely assembled in flying condition. All touch-up must be completed. The tab, tab pushrod, static wicks and hinge bolts must be attached. The chord line must be horizontally level and the hinge line must be properly supported when the static moment is measured. Although many different methods of check balancing exist, they can be categorized under the following two headings:

painting, including stripes

a.

Counterbalancing

and

The

of

application

a

known force

counter the unbalanced moment of aileron

b.

Actual Force Measurement

Counterbalancing

is the

weight

at a measured distance from the

hinge

line to

assembly.

Measurement of the force

known distance from the centerline of the NOTE:

or

applied by

the aileron surface

on a

single support

at a

hinge.

simplest method of check balancing.

EQUIPMENT REQUIRED TO PERFORM CHECK BALANCING a.

A stand with

knife-edge supports as

illustrated

(Ref. Figure 201).

The knife

edges

must be in the

same

horizontal

plane. b.

A paper cup

c.

Approximately

d.

A certified beam balance

weighing

e.

A

spirit

or

straightedge,

similar

lightweight

pound of lead

1

ruler and

container.

shot.

device calibrated in units of 0.01

pound

or

less.

level.

BALANCING PROCEDURE COUNTERBALANCING METHOD a.

Locate the chord line the

trailing edge.

by placing

a

straightedge

Mark the chord line with

a

at the inboard end of the aileron

suitable marker, such

as a

grease

assembly so that one end pencil, then remove the

is

on

straightedge. b. c.

Secure the trim tab

(left

hand

only)

Fit the correct sized bolts in the

in its neutral

hinge

the aileron is free to rotate about the

nas

position

with

a

small

brackets and mount the aileron

hinge

piece of masking tape. on

the

knife-edge supports.

Ascertain that

line.

57-50-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

adjustment weights should be added or removed, suspend a paper cup from a point near the trailing edge. Use a short length of small diameter string secured to the surface with a small masking tape as illustrated (Ref. Figure 201). The cup must be free to hang vertically.

To determine if

center of the aileron

piece e.

of

Add small

holding f.

quantities of lead shot to the cup until the aileron balances with the chord line level. Check spirit level aligned with the marked chord line.

this

by

the

Carefully

measure

the

perpendicular

distance "D" within 0.1 inch from the

hinge

line to the

point

of

suspension

of the cup. Remove the cup, contents and

g.

NOTE: Since any

carefully h.

weighing

on

weight of

error

scales that

Calculate the static balance

string

as

is

are

then

weigh

magnified by the

distance "D",

pounds.

weighing

is most

important and

must be done

certified for accuracy.

follows:

the cup and contents id

designated by

1.

The

2.

The distance between the centerline of the

3.

The

over or

them to within 0.05

underbalance moment is

hinge

"W".

and

designated by

suspension point

of the cup is

designated by

"D".

"M".

Thus: M=WxD 4.

following is a typical example of a balancing calculation: Assume the aileron is overbalance (nose heavy) and the paper cup was suspended from the trailing edge. Assume that the aileron balances with the chord line level at "W .900 pound" and "D 10.0 inches", then:

The

M

.900

x

10.0.

M

9.00

pound-inches pound-inches). acceptable.

In this instance, "M" is within the

Adjustment weights must be added or removed and the balance rechecked prescribed limits (8.80 to 10.00 pound-inches nose heavy).

if the static balance does not fall

(The product of "W x D" must required static balance range i.

be accurate to within 0.05 and is therefore

within the

NOTE: If the balance condition is not within the limits stated above, lead adjustment weights (P/N 101-130001201) may be added or removed from the forward end of the inboard closure rib to attain the required balanced condition. A steel

cover

plate (P/N 101-130001-219)

must be installed over the

adjustment

If necessary to meet the conditions of balancing, one or two cover plates may be used without the addition of weights, or two cover plates in addition to the weights may be used.

weights.

May

57-50-00

nn4

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201

Adjustment Weights No. of

Weights Necessary Balancing

For

and Screws

No. of Screws

Part No. of Screws

Part No. of Screws With

Required

With One Cover

Two Covers

None

4

MS27039-1-08

MS27039-1-09

1

4

MS27039-1-09

MS27039-1-10

2

4

MS27039-1-10

MS27039-1-11

3

4

MS27039-1-11

MS27039-1-12

4

4

MS27039-1-12

MS27039-1-13

5

4

MS27039-1-13

MS27039-1-14

6

4

MS27039-1-14

MS27039-1-15

A24

57-50-00

Page

yaM302

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

gl

MASIINO ~IPE rO srcuat I*e IN ~EUIPIL

MPISI(ING I*PP PL*tE NE*I1*116110N HINGE LINE i

COVLI PL~TI

I

D

ONI 011 TWO *5 BEOVIRED FOB PIOPEII BI\LANCE

coNlnlNEa

.~9"

DETAIL

B

101-130QOI-101 IDJUSTMENTWEIO

(mnximuM

0161 In*LH

DETAIL

A HNOE BIIACYn I(NIH EDGE

SUPPOI(T

r_o---e

116 MUS~ BE WOIIIZON~ALLI LEVEL

DETAIL C VIEW

D-D

2DD(Bbl

Balancing Figure 201

Aileron

Page

20457-5000

A24

C H A PT E R

PROPELLERS/ PROPU LSO RS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 61 - PROPELLERS TABLE OF CONTENTS SUBJECT

PAGE 61-00-00

Propellers - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Special Tools and Recommended Materials. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Breakout Box Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 61-10-00 propellers - Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Propeller assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Propeller settings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Propeller Assembly - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Lubrication. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Cleaning Propeller Reversing Hardware. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Propeller Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .201 Propeller Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .203 Propeller Shaft Oil Seal Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .206 Propeller Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Dynamic Balancing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Test Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .210 Test Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Ground Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 Flight Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .211 61-20-00 Controlling - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Primary Governor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Overspeed Governor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1 Flight Idle Low Pitch Stop . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Ground Idle Stop System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2 Low Pitch Warning Sensor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Propeller Reversing System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3 Controlling - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Primary Governor Removal. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Primary Governor Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5 Feathering Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .8 Overspeed Governor Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .8 Overspeed Governor Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9 Overspeed Governor Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .9

A28

61-CONTENTS

Page 1 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 61 - PROPELLERS TABLE OF CONTENTS (CONTINUED) SUBJECT

PAGE 61-21-00

Autofeathering - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Autofeathering - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Autofeather Pressure Switch Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Autofeather Pressure Switch Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Autofeather Power Lever Switch Adjustment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203 Autofeather System Operational Check. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 61-22-00 Synchrophasing - Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 Synchrophasing - Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 Synchrophaser System Functional Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102 Synchrophaser Continuity Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103 Propeller Governor Operational Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104 Pickup Output Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 Synchrophasing - Maintenance Practices . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Magnetic Pickup Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201 Magnetic Pickup Installation and Adjustment (Without Elliot Noise Reduction System) . . . . . . . . . . . . . . . . 201 Magnetic Pickup Installation and Adjustment (With Elliot Noise reduction System) . . . . . . . . . . . . . . . . . . . 203 61-40-00 Indicating - Maintenance Practices. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ground Idle Stop Switch Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Annunciator Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Annunciator Switch Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

201 201 201 201

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61-CONTENTS

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

61-LOEP

1

May 1/10

61-CONTENTS

1 and 2

May 1/10

61-00-00

1 thru 6

May 1/10

61-10-00

1 and 2 201 thru 212

May 1/10 May 1/10

61-20-00

1 thru 9

Sep 28/01

61-21-00

1 thru 3 201 thru 204

May 1/10 May 1/10

61-22-00

1 101 thru 106 201 thru 205

Nov 1/07 Nov 1/07 May 1/10

61-40-00

201 and 202

May 1/08

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61-LOEP

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 61-00-00

PROPELLERS - DESCRIPTION AND OPERATION SPECIAL TOOLS AND RECOMMENDED MATERIALS The special tools and recommended materials listed in Chart 1 and Chart 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

BREAKOUT BOX FABRICATION A breakout box is used to functionally test the propeller synchrophaser. Make the box using two connectors with backshells, two CCT-L strain relief assemblies, ten banana-plug or equivalent jacks, a project box of suitable size, and 22-gauge wire as required (Ref. Figure 1, Sheet 2).

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61-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1 Special Tools and Equipment TOOL NAME

PART NO.

SUPPLIER

USE

1. Feedback Ring Puller (Ref. Figure 1, Sheet 1)

TK1573-918-1 Hawker Beechcraft Corporation Remove feedback ring from PO Box 85 propeller. Wichita, KS 67201

2. Torque Adapter (Ref. Figure 1, Sheet 1)

10113

Hawker Beechcraft Corporation Apply torque to propeller PO Box 85 mounting bolts. Wichita, KS 67201

3. Dial Indicator w/base (Ref. Figure 1, Sheet 1)

Obtain Locally

Measure runout of low pitch stop collar.

4. Breakout Box (Ref. Figure 1, Sheet 2)

Fabricate Locally

Test propeller synchrophaser.

5. Volt/Ohmmeter (Ref. Figure 1, Sheet 3)

Obtain Locally

Test propeller synchrophaser.

6. Oscilloscope (Ref. Figure 1, Sheet 3)

Model 434

Tektronix Inc. PO Box 500 Beaverton, OR 97005

Test propeller synchrophaser.

7. Dynamic Balancer

Model 8500

Chadwick-Helmuth Aviation Products Co. Inc. 4601 N. Ardan Dr. El Monte, CA 91731 Telephone (818) 576-6161

Propeller Dynamic Balancing.

8. Adapter Cable (FL-1 thru FL-35)

10390

Chadwick-Helmuth Aviation Products Co. Inc. 4601 N. Ardan Dr. El Monte, CA 91731 Telephone (818) 576-6161

Propeller Dynamic Balancing.

9. Junction Box

9110

Chadwick-Helmuth Aviation Products Co. Inc. 4601 N. Ardan Dr. El Monte, CA 91731 Telephone (818) 576-6161

Propeller Dynamic Balancing.

10. Adapter cable (FL-36 and after; FM-1 and After)

8461

Chadwick-Helmuth Aviation Products Co. Inc. 4601 N. Ardan Dr. El Monte, CA 91731 Telephone (818) 576-6161

Propeller Dynamic Balancing.

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61-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2 Recommended Materials MATERIALS

SPECIFICATION

PRODUCT

SUPPLIER

1. Steel Wool

A-A-1043

Obtain Locally

2. Lacquer, Clear, Aerosol Spray

TT-L-58E

Obtain Locally

3. Petrolated Graphite

MIL-T-5544B or MIL-T-83434

Obtain Locally

4. Lubricating Grease

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Plastilube No. 3

Warren Refining Div. Parr Inc. 5151 Denison Ave. Cleveland, OH 44102

61-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Special Tools Figure 1 (Sheet 1 of 3)

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Special Tools Figure 1 (Sheet 2 of 3)

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61-00-00

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Special Tools Figure 1 (Sheet 3 of 3) Page 6 May 1/10

61-00-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 61-10-00

PROPELLERS - DESCRIPTION AND OPERATION PROPELLER ASSEMBLY The HC-B4-MP-3, all-metal, four-bladed propeller on this airplane is hydraulically controlled by engine oil, and is reversible, constant-speed, and full-feathering (Ref. Figure 1). Speed control is accomplished by a single-acting engine-driven governor. Backing up the engine-driven governor is an overspeed governor and a power turbine (N2) governor which is integral to the normal or primary governor. A servo piston mounted on the front of the propeller spider hub moves the propeller blades through links connected to the trailing edges. Centrifugal counterweights on each blade, in conjunction with a feathering spring on the servo piston, increase pitch (decrease rpm) toward the feathered position as governor oil pressure is relieved. The feathering spring completes the feathering operation when centrifugal twisting moment is lost as the propeller stops rotating. The autofeather system also provides a means of immediately dumping oil from the propeller governor to enable the feathering springs to start feathering the propeller blades as soon as the engine torquemeter oil pressure drops below 4.7 psi at power settings above 87 to 89% N1. The servo piston of the reversing propeller is connected by four spring-loaded sliding rods to a low pitch stop collar located behind the propeller. The movement of the low pitch stop collar is transmitted by one carbon block through a reversing lever and connecting linkage to a beta valve, which is positioned to maintain the blade angle while propeller rpm is lower than that of the governor pilot valve as selected by the control. The reversing lever is also connected to the power turbine governor to limit propeller rpm in the reverse position. A push-pull cable extends from the reversing lever aft to a control beta cam box connected to the power lever control and fuel control unit. Movement of the control is transmitted through the beta cam box and interconnecting linkage to the fuel control unit and governor to regulate propeller speed and pitch.

PROPELLER SETTINGS Refer to Chart 1 for the proper settings of the propeller. NOTE: The synchrophaser must be turned OFF while making these settings.

Chart 1 Propeller Settings

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Full Feathered Angle

79.3° at the 42 inch station

Mechanical Reverse Pitch Stop

-14° at the 42 inch station

Mechanical Pickup of the Beta Ring

15.4° at the 42 inch station

Maximum RPM

1700 RPM (at takeoff)

61-10-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Propeller Control Figure 1

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61-10-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

PROPELLER ASSEMBLY - MAINTENANCE PRACTICES WARNING: Prior to performing maintenance on an engine, pull and tag the start control and igniter power circuit breakers.

LUBRICATION Lubricate the propeller hub and low pitch stop rods (Ref. Figure 201) at 200-hour intervals (Ref. Chapter 12-20-00).

Propeller Assembly Figure 201

CLEANING PROPELLER REVERSING HARDWARE The non-aluminum components of the propeller reversing hardware may be rubbed clean with steel wool (1, Chart 2, 61-00-00) and coated with aerosol clear lacquer spray (2, Chart 2, 61-00-00).

PROPELLER REMOVAL a. Remove the upper forward cowling from the engine nacelle (Ref. Chapter 71-10-00). CAUTION: To prevent damage to the deice slip ring brushes during and after removal, tape them in place before removing the brush block.

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61-10-00

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL b. Remove the two nuts, thin washers, and screws securing the propeller deice brush block assembly to the engine bracket (Ref. Chapter 30-60-00). c.

Remove the spinner dome by removing the attaching screws from around the aft circumference.

d. Disconnect the propeller reversing lever from its top end at the propeller control linkage (Ref. Figure 202). CAUTION: Make sure that the feedback ring puller is centered and straight to avoid damaging the propeller. Take care not to bend or otherwise damage the spring-loaded rods or the low pitch stop collar (the brass ring). e. Install the feedback ring puller (1, Chart 1, 61-00-00) (Ref. Figure 203). Pull the low pitch stop fully forward. f.

Remove the safety wire from the propeller mounting bolts.

CAUTION: The propeller weighs 187 pounds, make sure that it is properly supported by an engine hoist or other means before removing the mounting bolts. g. Remove the eight bolts securing the propeller in place and remove the propeller from the engine.

Propeller Control Linkage Figure 202

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Feedback Ring Puller Figure 203

PROPELLER INSTALLATION CAUTION: Handle the propeller with special care at all times during installation. Do not allow the low pitch stop collar (the brass ring) or the stop rods to be bent or damaged. NOTE: Refer to Chapter 61-22-00 for correct propeller synchrophaser pickup installation for the left side and right side synchrophasers. a. Make sure that the engine and propeller flanges are clean. b. Place a new O-Ring seal over the engine shaft. NOTE: The low pitch stop collar is not installed on new propellers delivered from the factory as a precaution against damage during shipment. Only one of the four jamnuts is installed on one of the stop rods. This nut is locked in position on the rod with loctite for proper positioning of the collar. If the collar is already installed on the propeller, disregard steps c and h. c.

When a new propeller is being installed, install the low pitch stop collar as follows: 1. Install the three jamnuts on the three stop rods (#4 is already in position)

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61-10-00

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 2. Loosen the nut on the front end of each rod. 3. Install the low pitch stop collar on the ends of the four rods. The rods can be screwed into the collar by applying a thin wrench to the flats provided on the rods. Do not tighten the jamnuts at this time. d. Install the propeller on the engine by inserting the mounting studs on the propeller into the mounting holes on the engine propeller shaft. Make sure that complete and true contact is made between the mating surfaces. e. Apply petrolated graphite (3, Chart 2, 61-00-00) to the surfaces of the eight B-3339 bolts and A-2048-2 washers. Install the eight propeller mounting bolts with the chamfered (beveled) edge of each washer toward the bolt head, through the engine mount flange into the propeller mount flange. f.

Using the torque adapter (2, Chart 1, 61-00-00), torque all bolts to 40 foot-pounds, then to 80 foot-pounds using torque sequence A (Ref. Figure 204).

g.

Final torque all bolts to 100 to 105 foot-pounds using torque sequence B (Ref. Figure 204). Safety all bolts as instructed in the Federal Aviation Administration Aircraft Inspection and Repair Manual, AC (43.13-1).

h. When a new propeller is being installed, check the runout of the low pitch stop collar as follows: NOTE: Refer to Chapter 20-01-00 for torque wrench usage and extension formulas. All torques in this procedure are “wet” torques. 1. Tighten the one jamnut that is locked in position on the low pitch stop rod to 12 foot-pounds. 2. Attach a dial indicator (3, Chart 1, 61-00-00) to the reduction gear housing so that the runout of the forward inner surface of the low pitch stop collar can be measured (Ref. Figure 205). To avoid error in the measurement, rotate the stop collar slowly while pushing in on the propeller to take the play out of the thrust bearings. If the total runout exceeds .010 inch, adjust the three remaining rods and jamnuts as required to obtain the specified runout. 3. Torque the three remaining jamnuts to 12 foot-pounds. 4. Torque the nut on the front end of each rod to 12 foot-pounds. i.

Connect the propeller reversing lever to the propeller control linkage (Ref. Figure 202).

CAUTION: Hold the carbon brush block against the low pitch stop collar and the metal retaining clip of the carbon block. If the clearance is less than 0.005 inch at any point, replace the carbon block. j.

Install the deicer brush block assembly (Ref. Chapter 30-60-00).

k.

Check the propeller reversing linkage on the front of the engine for proper rigging.

l.

Install the engine cowling (Ref. Chapter 71-10-00) and spinner dome.

m. Perform the necessary engine run-up checks as instructed in the pilots operating handbook (POH) and FAA Approved Airplane Flight Manual.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TORQUE SEQUENCE A

TORQUE SEQUENCE B

USE THIS TORQUING SEQUENCE FOR THE INITIAL AND SECONDARY TORQUING PORCEDURE

USE THIS TORQUING SEQUENCE FOR THE FINAL TORQUING FA61B PROCEDURE 100136AA.AI

Torque Sequence Figure 204

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61-10-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Measuring Runout of Low Pitch Stop Collar Figure 205

PROPELLER SHAFT OIL SEAL REPLACEMENT A propeller shaft oil seal of a nonsplit configuration is installed on all new or overhauled engines. Should it become necessary to replace the propeller shaft oil seal between overhauls, the same nonsplit type may be installed as follows: a. Remove the upper and lower forward engine cowlings (Ref. Chapter 71-10-00). b. Remove the propeller as per PROPELLER REMOVAL. c.

Remove the eight bolts securing the seal retaining plate to the thrust bearing cover and slide the seal retaining plate forward against the propeller shaft flange.

d. Remove and discard the gasket. e. Remove the seal from the cavity in the thrust bearing cover. Take care not to damage the bore of the thrust bearing cover assembly or the surface of the oil seal race. f.

Remove the garter spring from the back of the seal. Cut and discard the seal.

g. Coat the new seal with clean engine oil and remove the garter spring. h. Gently work the seal over the propeller mounting flange and the seal retaining ring onto the propeller shaft.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL CAUTION: Avoid applying loads locally to the lip of the oil seal. The seal element is soft and subject to damage unless handled carefully at all times. i.

Install the garter spring by grasping with both hands and rotating each end counterclockwise two turns. Push the ends together and rotate each end clockwise two turns to lock them together (Ref. Figure 206).

j.

Place the spring into the slot on the back side of the seal.

k.

Press the seal gently into its cavity. The garter spring will not be visible with the seal installed properly.

l.

Check to see that the seal is pushed evenly in place.

m. Align the gasket profile with the bolt pattern and install it over the propeller flange and seal retaining ring. Do not bend the gasket. NOTE: The gasket may be split at right angles between the upper pair of bolt holes. Install the gasket over the propeller flange and seal retaining ring (Ref. Figure 207). n. Place the seal retaining ring in position and secure it to the thrust bearing cover with the bolts removed in step c. Torque the bolts to 36 to 40 inch-pounds and secure them in pairs with safety wire. o. Install the propeller as per PROPELLER INSTALLATION. p. Install the upper and lower forward cowling (Ref. Chapter 71-10-00).

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61-10-00

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Garter Spring Installation Figure 206

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Gasket Replacement Figure 207

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61-10-00

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PROPELLER INSPECTION a. Check the propellers for condition and attachment. b. Check the condition of the mechanical feedback ring, the stop rods and the springs. c.

Check the reversing linkage for evidence of binding and security of attachment.

d. Check the valve and plumbing for security of attachment and leakage.

DYNAMIC BALANCING Airplane serials FL-36 and after and FM-1 and after are hard wired at the factory for field connection of the Chadwick-Helmuth Model 8500 Balancer (7, Chart 1, 61-00-00). The connector for the balancer is located on the right fuselage sidepanel behind the copilot seat. Several other brands of dynamic balancing equipment are available for purchase and may be used as directed by the manufacturer of the equipment. For airplanes not prewired at the factory, refer to the applicable instructions furnished by the equipment manufacturer. Dynamic balancing of the propellers must be accomplished ONLY by personnel who have available to them, and who are totally familiar with, the applicable service equipment and data. Personnel must be thoroughly instructed as to the use and care of the test equipment being used. TEST PREPARATION NOTE: The following test procedure has been developed for use with the Chadwick-Helmuth Model 8500 Balancer. a. Remove the upper engine cowling nearest the propeller (Ref. Chapter 71-10-00). b. Install the vibration sensor brackets on the lower stud of the tach generator nearest the propeller, if not previously installed. Index mark the spinner and the spinner bulkhead. c.

Install vibration sensors on the brackets. Make sure that the vibration sensor is vertical with respect to the plane of the propeller.

d. On airplanes that HAVE NOT been wired for dynamic balancing, accomplish step e. For airplanes that Have been wired for dynamic balancing, proceed to step f. e. Connect the vibration sensor wires to the sensor and route them along the fuselage through the overwing emergency escape window. Secure the vibration sensor wires to the nacelle, wing and fuselage so they will not come loose during the balancing operation. f.

Gain access to the synchrophaser control box. Remove the connector from the synchrophaser control box and plug in the adapter cables (8, Chart 1, 61-00-00 or 10, Chart 1, 61-00-00).

g. Plug the adapter cable leads and the vibration sensor leads into the 9110 junction box (9, Chart 1, 91-00-00): LH engine wiring to channel one (1) and RH engine wiring to channel two (2). Select position one (1) on the junction box. Turn the synchrophaser power switch OFF. NOTE: Propeller should be lubricated before dynamic balancing to make sure that each blade has equal amounts of grease. h. Record the number and position of all balance weights in the propeller logbook to provide baseline information. i.

Perform a normal engine start. Taxi to the run-up pad and position the airplane headed into the wind. Shut down the right side engine.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL TEST PROCEDURE GROUND CHECK a. Turn ON the synchrophaser power switch and note that the 8500 balancer completes the SELF TEST function. Increase the LH propeller speed to cruise RPM, minimum torque. Press the BALANCE button. b. When the propeller speed has stabilized at cruise RPM, press the START button. When the measurement is complete, make a note of the vibration level and phase angle. Press the RE DO button and when the measurement is complete, note the vibration level and phase angle. Repeat the above sequence until confident of the results. Press PRINT and the 8500 balancer will print the results of the last reading. c.

Increase power to approximately 80% torque at the same RPM as before. Repeat step b. Compare the results of the readings taken at both power settings. If they differ more than 0.2 IPS (inches per second) the propeller should be tracked or sent to the propeller shop for blade angle check and/or static balance. Reduce power to IDLE.

d. Perform a normal start on the RH engine, then shut down the LH engine. e. Select position 2 on the junction box. Increase RH propeller speed to cruise RPM, minimum torque. Perform the tests in steps b, and c on the RH propeller. When the tests are complete, shut down the RH engine. If the vibration levels are 0.1 IPS or less, go to step a. under FLIGHT TEST PROCEDURE. If the vibration levels are above 0.1 IPS, proceed to step f. f.

Compute the weight amount and location, using the balance charts (Ref. Figure 208). Attach the weights as computed per the propeller manufacturer’s service instructions.

g. Perform a normal start on the LH engine. Repeat steps a through e until balance is acceptable. FLIGHT TEST a. Establish the following flight conditions: 1. ALTITUDE - 16,000 ft., CRUISE POWER, CRUISE SPEED. 2. Perform a normal shutdown on the RH engine. b. When the propeller speed has stabilized at cruise RPM, press the START button. When the measurement is complete, make a note of the vibration level and phase angle. Press the RE DO button and when the measurement is complete, note the vibration level and phase angle. Repeat the above sequence until confident of the results. Press PRINT and the 8500 balancer will print the results of the last reading. c.

Restart the RH engine and when cruise power has been established, perform a shutdown of the LH engine. Repeat step b above on the RH engine.

d. Make balance corrections on the ground per step f under GROUND CHECK. If the vibration levels are 0.1 IPS or less, no corrections are needed and the test is complete. e. Make appropriate logbook entries denoting that the propellers have been dynamically balanced.

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61-10-00

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Balance Chart Figure 208

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Raythean Aircraft BEECH SUPER KING AIR MODEL~ B300/B300C MAINTENANCE MANUAL

CONTROLLING

DESCRIPTION AND OPERATION.

PRIMARY GOVERNOR

single-acting govemormoves the prdpeller blades towards the low pitch thigh rpm) hydraulic stop and reverse positions by passing oil to the propeller through the oil transfer housing and the hollow center of´•the propeller shaft. The primary govemor, mounted on top of the gear:reduction housing, controls the power turbine (N2) Speed by varying propeller blade pitch. The governor consists of a gear-type oil pump with a pressure relief valve, a pair of pivoted flyweights mounted on a rotating head, and aspring-loaded pilot valve that regulates the flow of oil to and from the propeller servo piston. The position of the pilot valve is controlled by the combination of rotating flyweights (engine speed), the spring load imposed by the externally mounted speed control lever through the central cable from the propeller control lever in the crew compartment, and the synchrophaser magnetic force (when the synchrophaser is on). When the propeller rpm drops to an underspeed condition below the control setting, the speeder spn~ng force overcomes the flyweight force to lower the pilot valve plunger and open the portin the governor drive gear shaft, through which oil flows to the propeller servo piston and decreases blade angle. The decrease in pitch reduces the load on the engine. The resulting increase in propeller rpm also increases the centrifugal force of the rotating flyweights, which then lift the pilot valve plunger to cover the’ port in the govemor drive gear shaft and shut off the flow of oil to the propeller; The forces exerted on the pilot valve plunger by the flyweights and speeder spring then balance, causing a state of´•equilibrium to exist between the spring and flyweights (on´•speed condition). An overspeed condition occurs with a decrease in propeller load or with movement of the propeller control to decrease rpm. The flyweight force then overcomes the speeder spring force and raises the pilot valve plunger to open the port through which oil drains from the propeller through the governor to the sump. The load on the engine increases and the rpm drops as the countennreights and feathering spring increase propeller pitch. The pilot valve then centers in the govemor drive gear shaft to block the flow of oil to and from the propeller as the governor flyweight and the speeder spring force reach a state of equilibrium.

The

governor contains a fuel section designed to protect the engine against oveispeeding in the event of a malfunction, such as sticking propeller blades. During reverse thrust operation, the fuel section is set below the

The

primary

by the governor to permit control of governor speed by the FCU (fuel coritrol unit) servo system. As is increased, a pneumatic orifice is opened by a yoked bellcrank, operated off the flyweight head, to reduce the fuel metered to the engine.The speed of governor fuel section operation is determined bythe speed selected by the governor, and the position of the reset lever, which is normally set so that the fuel section fully regulates power speed speed

selected

(N2) speed at approximately 6% higher than the maximum setting of the governor, and at 4% lower than the minimum speed position. The reset lever causes the yoke to contact the pilot valve. The resulting spring load, in addition to the speeder spring force, must be overcome by the flyweights in order for them to control propeller speed.

turbine

This effect increases

govemed speed by

about 1%

over

that

normally

selected.

OVERSPEED GOVERNOR A

propeller overspeed governor, mounted on the left side of the reduction gear housing, acts as a safeguard against propeller overspeed should the primary governor fail. The overspeed governor regulates the flow of oil to the propeller pitch-change mechanism by means of a flyweight and speeder spring arrangement similar to that of the primary governor. The overspeed unit governs at 104% N2 Speed (approximately 1,768 rpm). Since it has no mechanical controls, the overspeed governor is equipped with a testing solenoid which resets the normal overspeed setting to approximately 1,560 rpm for ground testing.

*IjPage

1´•

Ral~heon ~rcraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FLIGHT IDLE LOln/ PITCH S7~P position thrcJ~dhrthe solenoid clevis. The propeller servo flight idle low pitch stop operates in the rods to the low pitch stop four mounted behind the propeller. A is connected spring-loaded by piston the of the block the latter transfers movement car~bon brush through the propeller reversing lever riding on slip ring motion fonnrard iliitial of the valve of the beta blocks off the flow of oil to the propeller. to the beta valve governor.Tlse from the pro~.er into the reduction gearbox sump. A mechanical stop limits Further motion forward dumps the i~l the forward motion of the beta valve. Rearward movement of the beta valve does not affect normal propeller control. When the propeller is rotating at a speed lower than that selected on´•the governor, the govemor pump provides oil pressure to the servo piston and´•decreases the pitch of the propeller blades until the feedback of motion from the low;pitch stop collar pulls the beta´•valve into a position blocking the supply of oil to the propeller, thus preventing further pitch changes.

The

GROUND IDLE STOP SYSTEM ground idle stop system, using an electrical solenoid mounteb on the front of the reversing push/pull cable, is designed to operate on the ground only by resetting the propeller blades to maintain an angle of 2 at ground idle. The solenoid is connected to the~propeller reversing lever by means of a slotted clevis which allows the reversing lever to be pulled aft, resetting the tjeta valve.

The

through the RH landing gear squat’Switch. As the airplane lands, the squat switch activates the solenoid, which in tum pulls the reverse lever back to reset the beta valve. This enables the propeller blades to reset to a lower blade angle (2), increasing propeller rpm. The travel on the reverse lever is limited by the

The electrical solenoid is wired

slot in the clevis. While the

airplane

is

on

the

ground,

the system remains activated. When the squat switch deactireverse lever forward to its original position. If a

vat~s the solenoid, the spring force from the beta valve pushes the failure

occurs

28 volts for

in the system during flight such that one or both of the ground idle low pitch solenoids are receiving than 10 seconds, the yellow PROP GRND SOL annunciator (FL-115 and after, FM-9 and after,

more

FN-2 and after) located

on

the CAUTION/ADVISORY ANNUNCIATOR

tions the PROP GND SOL annunciator

(if installed)

is inhibited

by

panel

will illuminate.

Dur/ng ground

opera-

the left squat switch.

pitch stop switch is provided in the pedestal to ensure operation of the ground idle stop sSistem under Iow gross weight operation of the airplane. The switch is activated by a linkage to the throttle~levers. Lifting either throttle lever to the beta range will cause the throttle lever detent pin to contact the linkage to actuate the low pitch A propeller low

stop switch. Returning both’throttle lelers

Rig

and

adjust

the

ground

to the idle

idle stop system. Refer to

Sep~28/0161-20-00

position will deactivate

Chapter

the switch.

76-00-00.

als

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

LOW PITCH WARNING SENSOR propeller low pitch warning sensor is mounted on the RH side of each engine, adjacent to the beta ring. The senpositioned to transmit an electrical signal to illuminate white L PROP PITCH and R PROP PITCH lights in the CAUTION/ADVISORY ANNUNCIATOR panel as the aft flange of the beta ring travels aft past the center of the sensor. The L or R PROP PITCH annunciators are provided to inform the pilot of a blade angle more than 8 degrees below the flight idle low pitch stop. The difference between the flight idle and ground idle blade angle is approximately 10 degrees. Therefore, in normal ground operation, these annunciators will be illuminated. The blade angles will be automatically reset from ground idle low pitch stop to the flight idle low pitch stop as the power levers are advanced above 68 70% N1 speed, and the L and R PROP PITCH annunciators will extinguish. A ground idle test switch is located on the lower left outboard subpanel to provide a means of checking the operation of the sensors during ground operation. A

sors are

To test and

adjust

the low

pitch warning

sensor, refer to

Chapter 76-00-00.

PROPELLER REVERSING SYSTEM

Propeller reversing is accomplished by moving the power lever controls into the reverse range. This enables the propeller servo piston to reverse the pitch of the propeller blades with engine oil pressure from the governor pump. The power lever controls are connected to the engine control beta cam box, which is also linked to the fuel control unit. A push-pull cable extends from the beta cam box forward to the reversing lever which is attached to the brush that rides in the propeller brass or low pitch stop collar. Movement of the power lever controls is transmitted through the beta cam box and interconnecting linkage to the fuel control unit.

ma

61-20-00

3

Ral~heon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

SPEED CONTROL 011 DUMP

W

BETA VALVE

Governor Nomenclature

Figure

Sep

28/0161-20-00

1

A13

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

MAINTENANCE PRACTICES

CONTROLLING

PRIMARY GOVERNOR REMOVAL

Figure

I

NOTE The power turbine governor is a.

Remove the upper forward

b.

Remove the cotter

an

integral part

of the

primary

governor.

engine cowling.

pin,

castellated nut, washers, and bolt

pin,

castellated nut, washer, and bolt

pin,

castellated nut, washer, bolt, and spacer

securing

the governor control lever to the

propeller

cable rod end. c.

Remove the cotter

securing

the fuel governor

interconnecting rod

to the

fuel governor controllever. d.

Remove the cotter

reversing

securing the front clevis

end to the

propeller

lever.

e.

Remove the cotter

f.

Remove the

and clevis

pin, washer,

safety wire

pin securing

and disconnect the

the

lever to the beta valve.

propeller reversing

propeller synchrophaser

electrical

plug

from the solenoid

on

the

governor. g. Remove the safety wire and disconnect the lines and ports as shown in Figure 1. h.

Remove the four nuts and washers

i.

Remove the govemor and governor

Py

line and oil

anchoring the

dump

governor to the

line from the govemor.

mounting pad

on

Cap

or

the reduction

plug

any open

gearbox

case.

mounting pad gasket.

PRIMARY GOVERNOR INSTALLA TION

Figure 2 NOTE Refer to

Chapter

70-06-00

3032842, for procedures

gasket

(Standard Practices) of the Pratt 8 Whitney Maintenance Manual, linkage assembly and adjustments to the linkage assembly.

the four studs

a.

Install

b.

Lightly

c.

Position the governor on the mounting pad and the nuts to 170 to 100 inch-pounds.

a new

coat the

over

splined

P/N

on

on

the governor

shaft of the governor with

mounting pad.

lubricating

secure

it in

grease

place

(4,

Chart 2,

with the four

61-00-00).

attaching

washers and nuts.

Torque d.

Secure the

propeller reversing

lever to the beta valve with the

attaching bushing, clevis pin, washer,

and cotter

pin. e.

Secure the front clevis end to the

propeller reversing lever with

the

attaching

spacer, bolt, washers, castellated

nut, and cotter pin. f.

Secure the fuel governor interconnecting rod to the fuel governor control lever with the castellated nut, and cotter pin.

nls

attaching bolt, washer,

61-20-00

Sep 28/01Page

5

Raythean Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

g. Secure the governor control lever to the and cotter pin.

propeller speed control with the attaching bolt, washers,

h.

Connect the

Py

i.

Connect the

propeller synchrophaser electrical plug

and oil

dump

lines to the governor and

castellated nut,

safety wire.

to the solenoid and

safety

wire.

NOTE Start the

in the normal

engine

manner

and

perform steps j through

n

before

retuming

the

airplane

to service.

j.

Check for interference with the

overspeed

governor

as

instructed in OVERSPEED GOVERNOR INTERFER-

ENCE CHECK. k.

I.

m.

n.

Check the propeller 1.

Set the power lever to 60 to 62%

2.

Featherthe

3.

Verify

Check the

N1.

N1 speed

does not

change.

underspeed fuel governing system

as

1.

Disconnect and hold the

propeller

2.

Set the

lever to MAXIMUM.

3.

Accelerate the

propeller control

engine slowly

Check the maximum 1.

Set

2.

Adjust

propeller

governor reset lever

as

speed stop

propeller governor play.

screw as

Np speed obtained is 1,598

necessary

fuel governor

reset lever is

as

as

3.

Set the power control to obtain 77% torque and observe

4.

Activate the

5.

Check that the propeller governor reset lever is still

6.

An increase in

Ng

of

Install the upper forward

shown in

contacting the

Set the

overspeed

Figure

2 of 76-00-00.

MAXIMUM.

than 1/2%

engine

1,632 rpm.

MAXIMUM stop and that the lost motion link has

Ng.

governor test solenoid to obtain 95%

more

to

follows:

2.

propeller control lever to

the MINIMUM stop.

Np (1,700 rpm).

overspeed

Ensure the

against

follows:

control to obtain 100%

the maximum

follows:

and check that the

propeller speed

Check for interference with the 1.

Sep

follows:

as

propellers.

that the

0.100 inch of free

o.

feathering system

(150 rpm)

is

Np (1,615 rpm).

contacting

the MAXIMUM stop.

unacceptable.

cowl.

61-20-00

a~s

Raytheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

PRESSURE SWITCH

OVERSPEED GOVERNOR AUTOFEATHER

ARM-OFF-TEST UNFEATHER FEATHER RPM

SVNCHROPHASER TARGET

PICKUP

BOX

GOVERNOR

ON-OFF

UNFEATHER FEATHER- RPM

RESET AUTOFEATHER

OVERSPEED GOVERNOR

PRESSURE SWITCH ENGINE OIL

300-254-~

Propeller Control Figure 2

A13

61-20-00

7

Raldheon Aircraft BEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

FEA THERING ADJUSTMENT

Figure

3

a.

Position the

b.

Pull the

propeller

lever in the full

lever back

propeller

against

high-rpm position the detent, then

and advance the power lever to obtain 1,700 rpm. the detent

adjust

as

required

to obtain

1,390 rpm

~(at detent).

I To check this the c.

Pull the

diately

engine,

adjustment,

CAUTION cA~moN

it is sufficient that the

do not allow the

propeller to

move

1

propellerjust begin

to feather. To avoid

damage

to

into the feathered position.

propeller lever past the detent (feather position) and observe that the propeller begins to feather. propeller to the high-rpm region to avoid damage to the engine.

Imme-

return the

OVERSPEED GOVERNOR REMOVAL a.

Remove the upper forward

b.

Remove the

c.

Remove the four

safety

engine cowling

as

instructed in

wire and disconnect the electrical

self-locking nuts and plain housing.

washers

Chapter 71.

plugs

from the governor solenoids.

securing

the governor and

remove

the governor from the

left side of the reduction gear

AUTOFEATHER POWER SWTTCHES

a

FEATHERING

omMs 993117

Feathering Adjustment Figure 3

Sep

28/01Page

8

61-20-00

nla

Raytheon Aircraft SEECH SUPER KING AIR MODEL B300/B300C MAINTENANCE MANUAL

OVERSPEED GOVERNOR INSTALLATION a.

Install

b.

Apply lubricating

c.

Position the govemor on the mounting pad and install the four 170 to 190 inch-pounds to the mounting nuts.

a new

gasket

on

the

(4,

grease

mounting pad. Chart 2,

61-00-00) sparingly

to the governor

plain

splined

washers and

drive.

self-locking

nuts.

Apply

a

torque of d.

Con nect the electrical

used to test governor e.

plugs to the governor. The solenoid with the receptacle on top is the speed reset solenoid operation and the remaining solenoid is used for autofeathering. Safety wire the plugs.

Install the upper forward

engine cowling

as

instructed in

Chapter 71.

OVERSPEED GOVERNOR CHECK overspeed unit, mounted on the left side of the reduction gear housing, is preset at the factory to govern at 104% NS Speed (approximately 1,768 rpm) and should not normally require readjusting. This setting can be reduced to 1,520 to 1,610 rpm for testing purposes by means of a testing solenoid valve. A second solenoid valve attached to the governor provides a means of immediately dumping oil from the unit for autofeathering. Check the overspeed The

governor

as

follows:

a.

Move the

b.

Increase

propeller

levers full forward.

powerto obtain 1,500 rpm.

cAvnoN I I CAUTION Be c.

Hold the

extremely careful.

propeller test

switch

on

DO NOT exceed the

the left

subpanel

limits

in the PROP GOV TEST

Advance the power levers until the rpm stabilizes. A rpm indication of 1,520 to 1,610 rpm.

d.

engine torque

during

this test.

position.

correctly operating overspeed

governor will hold

a

stable

NOTE

Overspeed units that fail to govern qualified service station for repair. e.

Set the power lever in the idle

f.

Repeat steps

als

a

through

e

position,

for the

at the

prescribed settings

then release the

should be

propeller test

replaced

and returned to

a

switch.

opposite engine.

~1-20-00

Sep

28/01Page

9

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 000 61-21-00

AUTOFEATHERING - DESCRIPTION AND OPERATION The automatic feathering system provides a means of immediately dumping oil from the propeller governor to feather the propeller blades when engine torquemeter oil pressure drops to 7 to 13% torque at engine power settings of 87% to 89% N1 or greater (Ref. Figure 1). The system is primarily intended for use during takeoff and landing. It should be ARMED until the airplane has gained enough altitude that the loss of one engine and its resultant drag will not present an immediate problem to the pilot. The autofeathering system is controlled by a four-pole, doublethrow switch with three functional positions: ARM (up position), OFF (center position) and TEST (momentary down position). When the autofeather arming switch, located on the pilots outboard subpanel, is placed in the ARM position, voltage is routed from a 5-ampere circuit breaker on the RH circuit breaker panel to the power lever switches mounted on a bracket in the control section of the pedestal. The autofeathering system remains inoperative as long as the power levers are retarded below the 87 to 89% N1 position. When the power levers are advanced to 87 to 89% N1 position, a mechanical actuator on each power lever closes its respective power lever switch. Voltage is then routed to the autofeather high pressure switches and a ground is applied to the autofeather low pressure switches. These switches are located adjacent to the torque pressure transmitter above and just forward of the LH exhaust outlet on each engine. The LH autofeather high pressure switch will actuate to its normally open position at 6.1 psi, connecting voltage to the contacts of the A122K3 solenoid-control relay. Under these conditions the RH autofeather low pressure switch is actuated to its normally open position (4.0 psi) and the ground is removed from the A122K3 relay and autofeather solenoid dump valve. Voltage is applied through the de-energized contacts of the A122K3 relay to the autofeather-arm light relay (A122K2) coil. With the RH power lever also advance to 87 to 89% N1, a ground is applied to the autofeather-arm light relay coil, thereby energizing the arm light relay to illuminate the RH autofeatherarm light. All of the control relays are mounted on two relay panels located under the center aisle floorboard forward of the main spar. The LH autofeather-arm light is illuminated by a circuit identical to that described for the RH side. NOTE: The green LH and RH autofeather-arm lights are located separate from the caution/advisory/status (CAS) panel. Airplanes FM-1 thru FM-8, FL-1 thru FL-119 and FL-121 have the green autofeather-arm lights located in the glareshield on the pilots side. Airplanes FM-9 and after, FL-120 and after have two green autofeather-arm lights, labeled AFX, mounted adjacent to the engine ITT instruments instead of in the glareshield. FL-381, FL-383 and FM-12 and After (Proline 21) will have AFX illuminated on the MFD. Should an engine fail or lose power while the system is armed, engine torque will begin to drop off until the high pressure switch deactuates to the normally closed position (4.7 psi). This removes voltage from the autofeather-arm light relay coil and applies it to the coil of the autofeather solenoid-control relay. Consequently, the autofeather-arm light for the opposite side is extinguished when its arm light relay de-energizes. As the engine continues to experience a decrease in power, torquemeter oil pressure decreases to the low pressure switch deaction point (3.1 psi). When the low pressure switch deactuates to the normally closed position, a ground is applied to the autofeather solenoid dump valve and autofeather solenoid-control relay. The autofeather solenoid control relay is then energized to apply voltage to the autofeather solenoid dump valve of the failed engine. The solenoid dump valve opens and immediately reduces propeller governor oil pressure to zero, permitting the propeller blades on the affected engine to quickly move to the feathered position. The circuit is such that the autofeather system for the opposite engine is disarmed through the pressure switch connections to prevent feathering of both propellers during flight. The system includes a yellow AUTOFEATHER OFF caution annunciator, located in the caution/advisory/status panel, that informs the pilot he has not armed the autofeather system before takeoff or landing. The annunciation circuit receives power from the triple-fed bus through the annunciator warning indicator circuit breaker (A146CB4). When the autofeather arming switch is in the OFF position, voltage is routed through the de-energized A120K5 control relay and LH gear down-and-locked switch to illuminate the annunciator. When the autofeathering arming

A28

61-21-00

Page 1 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL switch is placed in the ARM position, it supplies a ground and voltage to the relay coil to open the annunciator circuit and extinguish the annunciator. After takeoff, when the landing gear is retracted, power is removed from the annunciator circuit to extinguish the annunciator when the LH gear down-and-locked switch opens. When the autofeather arm switch is placed in the TEST position, the power lever switches are bypassed and both a ground and voltage are applied through the high and low pressure switches to energize the autofeather-arm light relays. Both autofeather-arm lights should illuminate if the system is functioning properly. NOTE: Engine torque must be approximately 13 to 20% (6.11 psi torquemeter oil pressure) to actuate the high pressure switches for this test. Selecting the test position permits the pilot to verify operation of the autofeather circuit without advancing the power levers to 87 to 89% N1.

Page 2 May 1/10

61-21-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Autofeather System Functional Schematic Figure 1

A28

61-21-00

Page 3 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

AUTOFEATHERING - MAINTENANCE PRACTICES AUTOFEATHER PRESSURE SWITCH REMOVAL NOTE: Removal procedures for the high and low pressure switches are identical. Each high pressure switch is mounted adjacent to the torque pressure transmitter above and just forward of the LH exhaust outlet on the respective engine. Each low pressure switch is mounted just below and to the left of the respective high pressure switch (Ref. Figure 201). a. With the battery and generator switches OFF and external power disconnected, remove the upper forward cowling (Ref. Chapter 71-10-00). b. Unsafety and disconnect the electrical connector (1) from the switch (2 or 4) (Ref. Figure 201, Detail A). c.

Unsafety the mounting nut at the base of the switch (2 or 4), then remove the switch (2 or 4) from the torque pressure manifold (5).

d. Remove and discard the O-ring (3). CAUTION: Install a protective plug in the torque pressure manifold (5) to prevent contamination of the torquemeter chamber oil supply.

AUTOFEATHER PRESSURE SWITCH INSTALLATION CAUTION: Do not apply more than 30 inch-pounds of torque to the switch mounting nut. a. Install a new O-ring (3) on the switch (2 or 4) (Ref. Figure 201). b. Remove the protective plug from the torque pressure manifold mounting hole and install the switch (2 or 4). c.

Tighten the switch mounting nut and secure with safety wire.

d. Connect the electrical connector (1) to the switch and secure with safety wire. e. Install the engine cowling (Ref. Chapter 71-10-00).

A28

61-21-00

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Autofeather Pressure Switch Installation Figure 201

Page 202 May 1/10

61-21-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AUTOFEATHER POWER LEVER SWITCH ADJUSTMENT NOTE: The autofeather power switches are accessed through the cover on the LH side of the pedestal. a. Start both engines according to procedures outlined in the Hawker Beechcraft Corporation B300 Pilots Operating Handbook and FAA Approved Airplane Flight Manual. b. Advance the power levers until the engines are running at 87 to 89% N1, then mark a reference line on the pedestal with masking tape. NOTE: It is recommended that the reference line be as close to 89% N1 as possible. c.

Shut both engines off with procedures outlined in the Hawker Beechcraft Corporation B300, Pilots Operating Handbook and FAA Approved Flight Manual.

d. Set the power levers to the reference line marked in step b. and adjust each power lever autofeather switch until an audible click is heard (Ref. Figure 202). e. Repeat steps a. and b. to verify the autofeather system activates at the proper N1 speed. f.

Do the AUTOFEATHER SYSTEM OPERATIONAL CHECK.

NOTE: The green LH and RH autofeather-arm lights are located separate from the caution/advisory/status (CAS) panel. Airplanes FM-1 thru FM-8, FL-1 thru FL-119 and FL-121 have the green autofeather arm lights located in the glareshield on the pilots side. Airplanes FM-9 and after, FL-120 and FL-122 and after have two green autofeather-arm lights mounted adjacent to the engine ITT instrument labeled AFX instead of in the glareshield.

Autofeather Power Lever Switch Adjustment Figure 202

A28

61-21-00

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

AUTOFEATHER SYSTEM OPERATIONAL CHECK a. With both engines running, set both power levers at idle and place the autofeather-arm switch in the TEST position. Verify that the autofeather-arm lights remain extinguished. This confirms that the high pressure switches are not actuated. NOTE: The autofeather-arm switch remains in the TEST position through step e. b. Advance both power levers until the autofeather-arm lights illuminate, then verify that engine torque is at 14 to 20%. Illumination of the arm lights indicates that the high pressure switches have actuated to the normally open position. c.

Slowly retard the RH engine power lever until the LH arm light extinguishes and verify that the RH engine torque is approximately in the range of 14 to 20%. This indicates that the interlock circuit between the RH and LH systems has functioned properly and that the RH high pressure switch has deactuated.

d. Retard the RH engine power lever until the RH arm light extinguishes and the RH propeller feathers. Verify that torque of the RH engine is approximately in the range of 7 to 13%. This will confirm that the RH low pressure switch has deactuated and that the circuit to the autofeather solenoid dump valve for the RH propeller is working properly. Failure of the propellers to feather indicates that the low pressure switches have failed to deactuate. NOTE: The RH autofeather-arm light may blink or flash intermittently as the propeller fluctuates. This is due to the low pressure switch opening and closing with small fluctuations in torque. e. SLOWLY advance the RH power lever until the LH arm light illuminates. Using the LH power lever, repeat steps c and d to verify proper operation of the opposite side of the system. NOTE: It is normal for the autofeather-arm lights to blink or flash, as the high and low pressure switch actuation points are slightly different, and therefore, do not actuate and deactuate at the same pressures; consequently, illumination of the LH and RH arm lights does not occur at the same moment. By moving the power levers SLOWLY during test, the technician is able to observe the sequence of switch actuations as the arm lights illuminate or extinguish. The schematic in Figure 1, Chapter 61-21-00 provides detailed information on the actuation pressures to help explain this effect. f.

With both power levers set at idle, place the autofeather arming switch in the ARM position.

g. SLOWLY advance both power levers until both autofeather-arm lights illuminate. Verify that the power levers are approximately in the range of 87 to 89% N1. (Refer to AUTOFEATHER POWER LEVER SWITCH ADJUSTMENT procedures to mark the actuation point if performing this check in conjunction with switch adjustment). Illumination of both arm lights within the proper power setting indicates that the power levers and pressure switches are properly adjusted and actuating within the intended range. h. SLOWLY retard the RH engine power lever until both autofeather-arm lights extinguish. If the arm lights extinguish in the range of 87 to 89% N1, this verifies the proper operation of the RH power lever switch. i.

Advance the RH power lever until the both arm lights illuminate, then repeat the preceding step with the LH power lever to verify proper operation of the LH power lever switch.

Page 204 May 1/10

61-21-00

A28

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SYNCHROPHASING

DESCRIPTION AND OPERATION

propeller synchrophaser automatically matches the rpm of both propellers as a result of maintaining a specific phase relationship between the blades of the left and right propellers. The control box senses pulses generated by magnetic pickups mounted at identical locations relative to the centerline of each engine. Targets mounted on the propeller spinner bulkheads provide the pulse reference for the pickups.

The

magnetic pickups operate on the magneto electric induction principle: once each propeller revolution, when the target passes in close proximity to the magnetic field of the pickup, an alternating current is induced in the pickup. Normal peak-to-peak voltage is between 4 vac and 110 vac. The

Maintaining a time-phase relationship is the only priority of the control box. It does not respond to the amplitude input signals, but to the phasing of the waveforms, although a voltage change of approximately 0.7 volts necessary to trigger the control box. It senses the rate and phase of the pulses from each pickup and attempts superimpose the waveforms by increasing or decreasing the speed of each propeller.

of is

the

to

ground potential to each governor. The governors receive a constant voltage from the controller. The variable ground potential controls current flow through an electromagnet in each governor, therefore controlling its strength. The electromagnet influences the flyweights and the pilot valve in the governor to increase or decrease the prop blade angle. The approximate range of authority for the governor control is 23 to 27 The command from the controller is

a

rpm.

speed of one propeller will follow the changes of the other propeller. The holding range of the governor will prevent a propeller from losing too much speed if that of the other propeller is manually reduced (such as in power changes or propeller feathering) while the synchrophaser is on. Because the governor can increase, but never decrease, the speed selected by the propeller control lever, the propeller rpm will never follow below that speed. The

synchrophaser system may be left on during takeoff and landing, although the synchrophasing range will be reduced at maximum rpm. The system cannot synchronize the propellers when the blades are against the low pitch stops, as is normal for final approach and landing. The system cannot synchronize propellers when their difference

The

in rpm is outside a limited range, termed the capture range, typically that the synchrophaser be turned off if one propeller is feathered.

equal

to the

holding range.

It is recommended

synchrophaser system is controlled through a push switch placarded PROP SYNCH-ON-OFF. To operate the system, synchronize the propellers in the normal manner and turn the synchrophaser on. To change rpm, adjust both propellers at the same time. This will keep the setting within the holding range of the system. If the synchrophaser is on, but will not synchronize the propellers, the propeller speeds are not within the capture range required for the system to assume control. Turn the synchrophaser off, synchronize the propellers manually, then turn the synchrophaser on. The

n23

61-22-00

,~slp,:Page

1

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SYNCHROPHASING- TROUBLESHOOTING A

logical sequence of

in the a.

system

are

For the first

tests is

provided

in Chart 101 to aid the technician.

phase of troubleshooting, perform

a

functional test of the

SYNCHROPHASER FUNCTIONAL TEST in order to faults within the b.

For the second as

the most

probable

causes

of faults

gain

synchrophaser

as

instructed in

information which may be essential to

differentiating

system.

phase

of trou blesh ooting,

perform

continuity test of th e synchrophaser wiring and components (4, Chart 1, 61-00-00) can be the various circuits of the synchrophaser system.

a

instructed in SYNCHROPHASER CONTINUITY TEST. A breakout box

fabricated c.

Only

listed in the chart.

locally

For the third

to

provide

convenient

phase, if the continuity

access

to

test fails to reveal the

fault, perform

a

functional test of the propeller

governors as instructed in PROPELLER GOVERNOR FUNCTIONAL TEST. The breakout box used in the second phase can also be used for this test. d.

For the fourth from the

e.

If

none

phase, if no faults magnetic pickups.

of the

known to be

np8

preceding tests operational.

are

revealed

reveals

a

by the first three phases,

evaluate the character of the

fault, the control box may be assumed

to be

faulty. Replace

61-22-00

outputs

it with

one

Page

voN101

1107

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MAN UAL

Chart 101

Troubleshooting STEP 1

Do the

Propellers synchronize after

a

Propeller Synchrophaser

few

STEP 2

The

YES

seconds?

NO

Is the circuit breaker

Go to

YES

open?

Are the

within the

propellers

Go to

STEP 4

Perform the control box Does the box

STEP 5

I

Perform the

continuity

test.

pass?

propeller governor test. Can manually operated?

STEP 6

I

Is the

output of the magnetic pickups. peak-to-peak voltage within

Are the AC waveform

Step

4.

YES

Go to

Step

5.

symmetrical

Correct any Go to

NO

tolerance?

STEP 7

Go to

YES

Check the

7.

NO

Go to

Step

8.

governor.

system is operating normally.

Adjust

YES

voltage be changed by adjusting pickup-to-target gap?

The

NO Is the face of each of its

faulty

Go to Step 8.

Can the

STEP 9

the

Step

NO

the

6.

Go to

The

on.

wiring faults.

YES

identical?

STEP 8

Step

Replace

YES

and

3.

NO

NO

both governors be

Step

Turn the

range3

I

2.

system off, synchronize the propellers manually and turn the system

YES

capture

Step

Reset the circuit breaker.

NO STEP 3

system is operating normally.

target parallel

to the face

YES

pickup?

replace the targets.

or

system is operating normally.

Go to

Step

9.

Go to

Step

9.

The system is

NO

Align

the

operating normally.

targets properly.

SYNCHROPHASER SYSTEM FUNCTIONAL TEST a.

Start the

engines high

levers in the

CAUTION: When b.

Using

c.

Turn the

d.

Using

the

and increase power until the rpm

reducing

the

propeller levers,

propeller speed,

reduce both

synchrophaser switch

the

If the

propeller lever, increase the right propeller to match

synchrophaser fails steps b through d.

Page

of both

propellers

to match the

102~1-22-00

do not exceed the

propellers

to the ON

the rpm of the e.

speed

is 1700 rpm, with the

propeller

control

position.

to as

nearly

torque redline.

1500 rpm

as

possible.

position.

rpm of the left propeller that of the left.

propellers

on

the first

slightly. Verify that

attempt,

turn the

the

synchrophaser

increases

synchrophaser off and repeat

nls

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

f.

If the

synchrophaser is operating properly, continue to increase synchronization is lost. Record the rpm at that point.

the left

propeller

rpm with the

propeller control

lever until

g.

Using the propeller control lever, slowly decrease the left propeller synchronization is again lost. Record the rpm at that point.

rpm below that of the

right propeller

until

propeller speeds at which synchronization is lost in the holding range, should be 23 to 27 rpm. This test evaluates the ability of the right propeller governor to respond to correction commands from the control box, as well as the ability of the control box to issue commands

NOTE: The difference between the two

properly. b

If the

synchrophaser system fails

through g, changing

the rpm of the

to pass this test,

right propeller

perform

the

synchrophaser continuity

observing the synchronization

and

test.

of the left

h.

Repeat steps propeller.

i.

During this functional test, verify that the communications and navigation equipment is not adversely affected by the synchrophaser operation, and that synchrophaser operation is not adversely affected by the operation of other electrical equipment.

SYNCHROPHASER CONTINUITY TEST A sensitive volt/ohmmeter

(5?

Chart 11

61-c0-00)

a.

Ensure that the

b.

Remove the connector from the control box.

c.

Check the

d.

Test the

e.

Close the between

battery

master switch is OFF.

synchrophaser system wiring

synchrophaser pins A and B.

the

If

no

Open

the

conformity

circuit breaker. Turn the

test.

synchrophaser

to the schematic

circuit breaker.

(Ref. Figure 101).

synchrophaser

plug

faults

were

revealed

battery

master switch ON and check for

to the control box before

turning

the

battery voltage

battery master switch OFF and opening

circuit breaker.

Correct any wiring faults revealed resistance. Restore the system to

g.

for

required for this

continuity (Ref. Chart 102).

CAUTION: DO NOT connect the

f.

is

by

by this test. Replace any component which fails to operational status and repeat the functional test.

this test, check the

propeller governor

as

meet the

specified

instructed in PROPELLER GOVERNOR

OPERATIONAL CHECK.

A23

61-22-00

Page

voN301

1107

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OWHGIMBL B~s Receivedl

By

~TP ---_7 6LUE ~RIMARV C;O~

PROP

------i;lfi

SION.

PICKUF

10

PICKUF:

HI

l-------- W~-IITE

FICKUP

BLUE

VOI-kGE

GOL’

PEIMARV F~OP GO~ SIGNL

WilITE

r

PIZKUP

LO

GLUE

>ICKUP

’-II

WHITE

VDC

2"

BLUE G

PROP OUi

P"IM%RY

~8

tO"

v

I

1´•

PICKUP

I

IN

CDi-!TT~I_

C95FL618159?1

CONTROI SWITCH

60j(

Synchrophaser Box Wiring Figure 101

C

Schematic

PROPELLER GOVERNOR OPERA TIONAL CHECK Perform the following test before a.

Connect the breakout box

evaluating

the

outputs of the magnetic pickups:

(4! Chart 1, 61-00-00)

between

plug

P151 of the

airplane wiring harness and the

control box.

b.

Start the

engines

and increase the

propeller rpm

to 1700 rpm with the

propeller control levers in the high rpm

position CAUTION: When c.

Using

Install

a

the

propeller rpm,

do not exceed the

propeller levers, reduce the speed of

the

controlled d.

reducing

by

both

torque

propellers

redline.

to 1500 rpm to

ensure

that

they

are

being

the governors.

jumper

between test

points

R and A. The

speed

of the

right propeller should noticeably

increase. If the

governor does not increase the speed of the propeller, check for 28 vdc from the control box at test point K. Refer to (4. Chart 1, 61-00-00), SPECIAL TOOLS illustrations. Remove the jumper and the speed of the

propeller e.

Install

a

should

noticeably

jumper between

decrease.

test

points

L and A. The

speed of the left propeller should

noticeable increase. If the

governor does not increase the speed of the propeller, check for 28 vdc from control box at test point J. Refer to (4, Chart 1, 61-00-00), SPECIAL TOOLS illustrations. Remove the jumper and the speed of propeller should

f.

noticeably

decrease.

Shut down

engines

Page

voN401

1107

and

remove

electrical power.

61-22-00

A23

Hawker Beechcraff

Corporation

SUPER KING AIR B3001B300C MAINTENANCE MANUAL

g.

If

propeller speed operation

was

not

acceptable,

determine whether the 3.9-ohm resistor in control box is open. points B and J for

Set volt/ohmmeter to diode function and check for 700-1000 ohms resistance between test

the left governor, or between test points B and K for the right governor. Airplanes that have a control box with an F following the serial number or the part number, will have a thermistor instead of a 3.9 ohm resistor. h.

If resistance checks

were

acceptable, perform the

PICKUP OUTPUT CHECK before

condemning

the control

box.

i.

If all

system operations

were

normal,

remove

breakout box from

airplane

and connect P151 wire harness to

control box.

PICKUP OUTPUT CHECK

pickup outputs and to make adjustments as necessary, an oscilloscope display the output waveform and measure the peak-to-peak voltages.

In order to evaluate the character of the

(61

61-00-00)

Chart 11

required

to

master switch is turned off and the

synchrophaser

a.

Be

b.

The control box must be connected to the wire harness P151 when

sure

the

is

battery

circuit breaker is open.

performing voltage

checks of the

magnetic

pickups. c.

Connect

oscilloscope

d.

Start the

engines

CAUTION: e.

When

leads between

and

adjust

reducing

the

the

pins C

and G for the

propeller speeds

propeller rpm,

to

right pickup

as near

and between

1,700 rpm

do not exceed the

as

pins

D and E for left

pickup.

possible.

torque redline.

generated by the pickups should depart smoothly from the baseline, rise smoothly to the positive peak, drop off to the negative peak, and return to the baseline (Ref. Figure 102). There should be no secondary peak at either the positive or negative peak of the waveform. The ascending and descending sides of the peaks should be symmetrical. Deviations in the waveform may indicate the following faults:

The ideal waveform

ragged

1.

A

2.

An

3.

A

f.

asymmetrical waveform

secondary peak

Record the

If the

vac

an

intermittent fault in the

may indicate that the

target is

in the waveform may indicate that the

peak-to-peak voltage

be between 4

g.

waveform may indicate

and 110

peak-to-peak voltage

pickup.

not

parallel

to the

tip of the pickup.

target has been damaged.

of the waveforms from each

pickup. Ideally,

the

peak-to-peak voltage

should

vac.

of the

pickups

does not match, check the

magnetic pickup

as

instructed in

NIAGNETIC PICKUP INSTALLATION AND ADJUSTMENT. h.

A23

If all

system operations

were

normal, shutdown engines and

remove

all test

equipment.

61-22-00

Page

voN501

1/07

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 102

Synchrophaser Continuity

Checks

Ohmmeter Indication

Component

A and Ground

0 Ohms

A and B

A and B

Open Circuit

Test Between

Receptacle Pins

C and G

52

68 Ohms

D and E

52

68 Ohms

K and R

115

205 Ohms

Right Governor

J and L

115

205 Ohms

Left Governor

Resistance may be

as

much

as

20%

higher during

O

heat soak

Right Pickup Left

following engine

MINIKUM’EAK-TO

vee

Pickup

shutdown.

PEEK

1 360’ (J\L

i:lO’t~LtF

SH*;I

As V31XTION

t~P_´•s ~gaHGWNAe BBecfeivec% By Typical Pickup Waveform Figure 102

Page

voN601

1107

61-22-00

A23

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

SYNCHROPHASING - MAINTENANCE PRACTICES MAGNETIC PICKUP REMOVAL a. Remove the lower forward engine cowl to gain access to the pickup. b. Unplug the electrical leads of the pickup from the fire seal receptacle. c.

Unsafety and remove the pickup from its mounting bracket.

MAGNETIC PICKUP INSTALLATION AND ADJUSTMENT (WITHOUT ELLIOT NOISE REDUCTION SYSTEM) The synchrophaser pickups are located in a bracket adjacent to each propeller deicer brush block. NOTE: For proper function of the propeller synchrophaser, the pickup must be installed 5° behind the blade for the right and left propeller. a. Remove the lower forward engine cowl to provide access to the pickup. Target should pass across the center of the magnetic pickup. The face of target and pickup should be parallel. b. Screw the pickup into the mounting bracket. c.

Adjust the pickup to provide an initial clearance between the pickup and the target (Ref. Figure 201). NOTE: This is an initial setting only. Adjust the pickup properly as instructed in steps d. through h. prior to placing the airplane back in service.

d. Tighten the pickup locknut to a maximum torque of 25 inch-pounds. e. Connect the two electrical leads. NOTE: Install the lower forward engine cowl and extend ice vanes before running the engine. f.

Measure the output of the pickup according to the synchrophaser PICKUP OUTPUT CHECK procedure.

g. If necessary, adjust the gap between the pickup and target. Move the pickup away from the target to decrease voltage output, and move it closer to the target to increase the voltage output. Altering gap by 0.007 inch will increase/decrease voltage by approximately 0.5 volt. h. Torque the locknut on the pickup to a maximum of 25 inch-pounds and safety wire the locknut. i.

Repeat steps f and g as required to obtain matching voltage outputs from each pickup.

j.

If the connector plug was previously disconnected, connect the plug to the control box.

NOTE: Install the lower forward engine cowl and extend ice vanes before running the engine. k.

Perform the synchrophaser FUNCTIONAL CHECK procedure.

A28

61-22-00

Page 201 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CL BLADE NO.1

CL BLADE NO.1 BALANCE WEIGHT

5 DEGREES REF

5 DEGREES REF

CL BLADE CL BLADE SPINNER BULKHEAD

CL BLADE

TARGET BRACKET

LEFT PROPELLER SPINNER BULKHEAD (VIEW LOOKING FORWARD)

PICKUP BRACKET

CL BLADE RIGHT PROPELLER SPINNER BULKHEAD (VIEW LOOKING FORWARD)

BALANCE WEIGHT

BALANCE WEIGHT

SPINNER BULKHEAD

SPINNER BULKHEAD

PICKUP BRACKET

SYNCHROPHASER PICKUP SYNCHROPHASER PICKUP 0.10 INCH GAP 0.04 INCH GAP

METAL FERROUS TARGET

MAGNETIC TARGET FL-1 THRU FL-35

FL-36 THRU FL-248 FM-1 AND AFTER

FL61B985310AA.AI

Propeller Synchrophaser Installation (Without Elliot Noise Reduction System) Figure 201

Page 202 May 1/10

61-22-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MAGNETIC PICKUP INSTALLATION AND ADJUSTMENT (WITH ELLIOT NOISE REDUCTION SYSTEM) The synchrophaser pickups are located in a bracket adjacent to each propeller deicer brush block. NOTE: For proper function of the propeller synchrophaser, the pickup must be installed as follows: 5° behind the blade for the left propeller and 25° in front of the blade for the right propeller (FL-249 thru FL-474) (Ref. Figure 202). 5° behind the blade for the left propeller and 27.5° behind the blade for the right propeller (FL-475 and After; FM-13 and After) (Ref. Figure 203). a. Remove the lower forward engine cowl to provide access to the pickup. Target should pass across the center of the magnetic pickup. The face of target and pickup should be parallel. b. Screw the pickup into the mounting bracket. c.

Adjust the pickup to provide an initial clearance between the pickup and the target (Ref. Figure 202). NOTE: This is an initial setting only. Adjust the pickup properly as instructed in steps d through h prior to placing the airplane back in service.

d. Tighten the pickup locknut to a maximum torque of 25 inch-pounds. e. Connect the two electrical leads. NOTE: Install the lower forward engine cowl and extend ice vanes before running the engine. f.

Measure the output of the pickup according to the synchrophaser PICKUP OUTPUT CHECK procedure.

g. If necessary, adjust the gap between the pickup and target. Move the pickup away from the target to decrease voltage output, and move it closer to the target to increase the voltage output. Altering gap by 0.007 inch will increase/decrease voltage by approximately 0.5 volt. h. Torque the locknut on the pickup to a maximum of 25 inch-pounds and safety wire the locknut. i.

Repeat steps f and g as required to obtain matching voltage outputs from each pickup.

j.

If the connector plug was previously disconnected, connect the plug to the control box.

NOTE: Install the lower forward engine cowl and extend ice vanes before running the engine. k.

Perform the synchrophaser FUNCTIONAL CHECK procedure.

A28

61-22-00

Page 203 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CL BLADE

CL BLADE TARGET BRACKET

25 DEGREES REF

5 DEGREES REF

CL BLADE

CL BLADE

SPINNER BULKHEAD

CL BLADE

CL BLADE

BALANCE WEIGHT

RIGHT PROPELLER SPINNER BULKHEAD (VIEW LOOKING FORWARD)

LEFT PROPELLER SPINNER BULKHEAD (VIEW LOOKING FORWARD)

BALANCE WEIGHT SPINNER BULKHEAD PICKUP BRACKET

SYNCHROPHASER PICKUP

0.10 INCH GAP

MAGNETIC TARGET

SPINNER DOME FL-249 THRU FL-474

FL61B985309AB.AI

Propeller Synchrophaser Installation (With Elliot Noise Reduction System) (FL-249 thru FL-474) Figure 202

Page 204 May 1/10

61-22-00

A28

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CL BLADE

BALANCE WEIGHT

CL BLADE 27.5 REF

5o REF

o

CL BLADE

CL BLADE SPINNER BULKHEAD

BRACKET LEFT PROPELLER SPINNER BULKHEAD (VIEW LOOKING FORWARD)

RIGHT PROPELLER SPINNER BULKHEAD (VIEW LOOKING FORWARD)

FL61B 985576AA.AI

Propeller Synchrophaser Installation (FL-475 and After; FM-13 and After) Figure 203

A28

61-22-00

Page 205 May 1/10

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INDICATING

MAINTENANCE PRACTICES

GROUND IDLE STOP SWITCH ADJUSTMENT Power to the low

pitch stop system (set by the power levers.

and is activated

at 1050

rpm)

is

provided through

the

squat switch

to the power lever switch

panel from the left side of the pedestal.

a.

Remove the

b.

Adjust the power lever switch in its mounting slots (Ref. Figure 201) until it is in the full overtravel position (approximately 0.60 inch beyond the point of actuation) with the power levers in the forward position. Lift either power lever and check that the switch clicks at a point approximately 0.20 inch before the end of travel by the lever attached to the

c.

Install the

panel

on

actuating

arm.

the left side of the

pedestal.

ANNUNCIATOR SWITCHES To prevent incorrect governing of the engines or the development of asymmetrical thrust, a yellow PROP RVS NOT READY light in the pedestal annunciator panel warns not to reverse either of the propeller blades while in the high to the warning light switches is provided through the landing gear control switch warning light switches are mounted in the pedestal adjacent to the propeller lever bell cranks. When either propeller lever is moved from the high rpm (iow pitch) position, its respective warning switch closes to illuminate the PROP RVS NOT READY light in the annunciator panel. When both propeller levers are in the high rpm (low pitch) position, the switches are open and the warning light should be extinguished.

pitch (low rpm) position. Power

when "DOWN" is selected. The

ANNUNCIA TOR SWITCH ADJUSTMENT a.

Remove the

panel

from the left side of the

NOTE: The

following adjustment requires

b.

engines.

Start the

Position the

pedestal.

that the

landing

gear be down and locked.

propeller control lever in the full high

rpm

position and advance the

power lever

to 1700 rpm. c.

Adjust

the annunciator switch in its

retarded to d.

approximately

nno

slots

(Ref. Figure 201)

until it actuates when the

Stop

the

above

engines

propeller

lever is

1675 rpm.

propeller lever slightly and check that the yellow PROP RVS NOT approximately 1 675 rpm and illuminates at approximately 1675 rpm.

Advance and retard the

extinguishes e.

mounting

and install the

panel

on

the left side of the

READY annunciator

pedestal.

61-40-00

Page

yaM102

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

REVERSE NOT READY SWITCHES

THROTTLE SWITCHES

QB

THROTTLE SWITCH

THROTTLE CONTROL BEUCRANK misw

ADJUST BY MOVING

SWITCH IN SLOTTED MOUNTING HOLES

Pedestal Switch

Figure

Page

20261-40-00

Adjustment

201

A24

CHAPTER

POVVERPLANT

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 71

POWER PLANT

TABLE OF CONTENTS

PAGE

SUBJECT 71-00-00 Power Plant-

Descriptionand Operation

.................1

Recommended Materials

.........2

Power Plant- Maintenance Practices

.201

Engine Removal Engine Build-up. Engine Return Engine Installation. FUEL Control Unit

.214

Purge Procedure. Handling Procedures. EngineWashing Procedures. Engine Cold WeatherPrecautions Engine Ground Operating Procedures Airplaneand Engine Prestartlnspection Starting Engines EitherEngine First Engine Shutdown Motoring the Engine Windmilling onthe Ground. Fuel Nozzles

.214 ....214 .216 ................216 ...........216

.............218 ..........218 ........218 ..218

71-10-00

Cowling- Descriptionand Operation (Effectivity: All). Cowling

......1 ..........1

Maintenance Practices

(Effectivity: All) Cowling Removal (Effectivity: All) Cowling Installation (Effectivity: All) UpperCowiing DoorLatch Adjustment (Effectivity: All)

...1

.4 .....6

71-20-00

Mounts-

..1

Descriptionand Operation Engine Mount Engine Mount Isolators

................._

Mounts- Maintenance Practices

...201

Engine Mount Reconditioning Engine MountAssembly Installation

....201 .201

71-30-00

Fireseals-

Description

Engine

Heat Shields

and

.1

Operation.

71-50-00

Electrical Harness

n?s

Description

and

Operation

............1

71-CONTENTS

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 71

POWER PLANT

TABLE OF CONTENTS

(CONTINUED) PAGE

SUBJECT 71-70-00

Engine Drains Description and Operation Engine Fuel Purge System Engine Drains- Maintenance Practices. Fuel PurgeTank Removal Fuel PurgeTank Installation Fuel PurgeTankCleaning Fuel Purge System airfilter Inspection and Cleaning Fuel Purge System Check valve Inspection, Cleaning and Leakage Fuel Purge System Flow Divider/Purge Valve LeakageTest

Page

yaM2

1/08

71-CONTENTS

1 1

201 201 ....201 ......201 201 test

203 204

a24

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective Pages CH-SE-SU

PAGE

DATE

71-LOEP

1

May 1/10

71-CONTENTS

1 and 2

May 1/08

71-00-00

1 thru 3 201 thru 226

Nov 1/07 May 1/10

71-10-00

1 thru 6

Jul 31/95

71-20-00

1 and 2 201 and 202

May 1/08 May 1/08

71-30-00

1 and 2

May 1/08

71-50-00

1

May 1/08

71-70-00

1 201 thru 204

May 1/08 Feb 1/10

A28

71-LOEP

Page 1 May 1/10

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POWER PLANT

DESCRIPTION AND OPERATION

The PT6A-60A

engines installed on these airplanes are of the "free turbine" type. Each engine utilizes two independent turbine sections, one driving the compressor in the gas generator section and the other (a two-stage power turbine) driving the propeller shaft through a reduction gear box. Each engine is self sufficient since its gas generator driven oil system provides lubrication for all areas of the engine, pressure for the torquemeter and power for the propeller pitch control. Inlet air enters the engine through an annular plenum chamber, formed by the compressor inlet case where it is directed forward to the compressor. The PT6A-60A engine compressor consists of three axial stages, combined with a single centrifugal stage, assembled as an integral unit. A row of stater vanes, located between each stage of compression, diffuses the air, raises its static pressure and directs it to the next stage of compression. The compressed air passes through diffuser tubes which turn the airthrough 90 degrees in direction and convert velocity to static pressure. The diffused air then passes through straightening vanes to the annulus surrounding the combustion chamber liner assembly. The combustion chamber liner consists of two annular wrappers bolted together at the front dome shaped end. The outer wrapper incorporates an integral large exit duct. The liner assembly has perforations of various sizes that allow entry of compressor delivery air. The flow of air changes direction 180 degrees as it enters and mixes with fuel. The fuellair mixture is ignited and the resultant expanding gases are directed to the turbines (Ref. Figure i). I

supplied by a dual manifold consisting of primary and secondary transfer tubes and adapters. The fuel is then injected into the combustion chamber liner through 14 individual nozzles arranged in two sets of seven. The fuel/air mixture is ignited by two spark igniters which protrude into the liner. The resultant gases expand from the liner, reverse direction in the exit duct zone and pass through the compressor turbine inlet guide vanes to the single stage compressor turbine. The guide vanes ensure that the expanding gases contact the turbine blades at the correct angle, with minimum loss of energy. The still expanding gases are then directed forward to drive the power turbine, consisting of the first stage guide vane and turbine and the second stage inlet guide vane and turbine, drives the propeller shaft through a reduction gearbox. Fuel is

The compressor and power turbines are located in the approximate center of the engine with their respective shafts extending in opposite directions. The exhaust gas from the power turbine is collected, routed into the exhaust duct

assembly and directed to the atmosphere by twin opposed exhaust stubs. Interturbine temperature (T5) is monitored by an integral bus-bar, probe and harness assembly installed between the compressor and power turbines with the probes projecting into the gas path. A terminal block mounted on the gas generator case provides a connection point to the flight compartment instrumentation. All engine driven accessories, with the exception of the propeller governor, overspeed governor and tachometer generator are mounted on the accessory gearbox at the rear of the engine. These components are driven by the compressor by means of a coupling shaft which extends the drive through a tube at the center of the oil tank. The engine oil supply is contained in an integral oil tank which forms the rear section of the compressor inlet case. The tank has a total capacity of 2.5 U.S. gallons and is provided with a dipstick. Refer to the

Engine

Maintenance Manual for

complete description and maintenance information

on

the

engine

and

accessories.

A23

71-00-00

NO’V"~Jb:

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RECOMMENDED MA TERIALS

I I

The recommended materials listed in Chart 1

as meeting federal, military or supplier specifications are provided for only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification may be used, subject to availability. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or by compliance to the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE

reference

REQUIREMENTS OF THE SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART.

Only

the basic number of each

revision. It is the

I specification prior

responsibility

specification

is listed. No

of the technician

to usage of the

or

attempt has been made

to

update

the

listing

to the latest

mechanic to determine the current revision of the

product listed. This

can

be done

by contacting

the

supplier

applicable

of the product to be

used.

Chart 1 Recommended Materials

MATERIAL

I

I

i.

Cleaning Solvent

SPECIFICATION MIL-PRF-680

Type I,

or

British Standard BS245:1976

Page

voN2

1107

71-00-00

PRODUCT Stoddard Solvent

SUPPLIER Obtained

Locally

(Mineral Spirit)

A23

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OW’IGlhNBah as ~eceived BY ~VP

ASSEMBLY GEARBO

AFT FIRESEAL FLANGE

FORWARD FIRESEAL FLANGE

COMBUSTION

CHAMBERGAS

AIR INLET SCREEN

GENERATOR CASE

´•a´•

POWER TURBINE INTERSTAGE

b

EXHAUST DUCT AND

t

C

INSULATION BLANKET

rt

g

d4t1e:j9;

PROPELLER

GOVERNOR

t~

i´•

B

IGNITION EXCITEf

COMPRESSOR TURBINE

SPARK‘IGNITORS

SCAVENGE OIL TUBES PROPELLER GEARBOX ASSEMBLY

COMPRESSOR INTERSTAGE AIR INTAKE

COMPRESSOR TURBINE INLET

I

6I

COMBUSTION CHAMBER INLET

EXHAUST DUCT

BEARINGS BEIRINGS

EXHAUST OUTLET

O

INTERTURBINE

O

I~

X

COMPRESSOR INLET

ACCESSORY DRIVE ROLLER BEARINGS

´•1_1~---?e

II ’r;F

II

i

4

~i I

X

REDUCTION GEARBOX

REAR CASE TO POWER TURBINE HOUSING

EXHAUST DUCT TO POWER TURBINE SHROUD HOUSING

FLANGE

FLANGE

REDUCTION GEARBOX TO EXHAUST DUCT FLANGE

POWER SECTION TO GAS GENERATOR CASE FLANGE

GAS GENERATOR CASE TO COMPRESSOR INLET CASE FLANGE

SMALL EXIT DuCn COMPRESSOR TURBINE SHROUD HOUSING TO COMPRESSOR TURBINE VANE RING FLANGE

COMPRESSOR INLET CASE TO ACCESSORY GEARBOX FU\NGE 300-2416

Engine Figure 1

PT6A-60A

A23

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Page 3 Nov 1107

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POWER PLANT - MAINTENANCE PRACTICES 200200200

ENGINE REMOVAL a. Disconnect the electrical power to the engine as follows: 1. Turn the Battery Master switch ON. 2. Press the appropriate switch(es) located on the glareshield to close the fuel firewall shutoff valve(s) to the engine(s). Wait at least 30 seconds (Ref. Figure 201 or 202). 3. Turn the Battery Master switch to OFF. 4. Open all engine circuit breakers. 5. Disconnect all external electrical power to the airplane. 6. Disconnect the airplane’s battery. b. Position a suitable stand under the tail of the airplane. c.

Remove the engine cowling (Ref. ENGINE COWLING REMOVAL, 71-10-00). The lower aft cowling does not need to be removed.

d. Remove the propeller (Ref. PROPELLER REMOVAL, 61-10-00). e. Place a suitable cover over the engine air inlet screen and propeller shaft to prevent the entry of foreign matter. f.

Remove the two center panel aft attaching flanges and the upper section of the baffle from the engine baffle assembly (Ref. Figure 203).

g. Position a suitable drip pan under the engine to catch fuel and oil. h. Drain the engine oil (Ref. OIL SYSTEM, 12-10-00). i.

Disconnect the following items from the engine: NOTE: Tag and identify all hoses, plumbing and electrical connections to ensure correct reinstallation. Cap or cover all open hoses, plumbing, engine ports and electrical connections to prevent contamination. Note all securing clamps and stand off locations for correct reinstallation on the new engine. 1. Disconnect the forward electrical wire harness connection from the chip detector (Ref. Figure 204). 2. Remove the vent (torque transmitter) hose from the engine (Ref. Figure 204). 3. Remove the autofeather switches lubrication hose and snubber from the engine (Ref. Figure 204). 4. Remove the torque transmitter and autofeather switches mounting bracket assembly from the engine flanges (Ref. Figure 204). 5. Disconnect and remove the overspeed governor and solenoid from the engine (Ref. Figure 204). 6. Disconnect and remove the forward electrical wire harness standoffs from the engine. 7. Remove the deicer brush block assembly from the engine (Ref. Figure 204).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 8. Disconnect the propeller control cable from the propeller governor linkage and the forward mounting bracket and pull the cable back to the forward heat shield (Ref. Figures 205 and 212). 9. Remove the propeller control cable mounting bracket from the engine flange (Ref. Figure 212). 10. Disconnect and remove the propeller reversing lever and its bushings from the beta valve and front end clevis (Ref. Figure 206). 11. Disconnect the bleed air line and fitting from the engine (Ref. Figure 207). 12. Disconnect the forward electrical wire harness plug from the left aft wire harness plug in the forward heat shield (Ref. Figure 207). 13. Disconnect the forward electrical wire harness connection from the prop tach generator (Ref. Figure 208). 14. Remove the prop secondary low pitch warning assembly from the engine (Ref. Figure 208). 15. Remove the ground idle stop solenoid and mounting bracket from the engine (Ref. Figure 208). 16. Remove the fire detector wire and its standoffs from the forward section of the engine (Ref. Figure 212). NOTE: The fire detector wire secured to the engine mount between the forward heat shield and the engine baffle assembly does not need to be removed. 17. Remove the upper aft engine fire detector wire and standoffs from the engine (Ref. Figure 209). 18. Disconnect the fire detector wire plug located on the aft top left side of the engine mount and pull the fire detector wire and plug clear of the engine (Ref. Figure 209). 19. Disconnect the aft left electrical wire harness connector from the forward end of the ignition exciter (Ref. Figure 209). 20. Remove the two cable clamps that secure the aft ignition exciter electrical wires to the engine mount (Ref. Figure 209). 21. Disconnect the ignition exciter from the engine mount and leave with the engine (Ref. Figure 209). 22. Disconnect the aft bonding strap from the engine (Ref. Figure 209). 23. Disconnect the two oil lines from the engine (Ref. Figure 209 and 215). 24. Carefully remove the aft right electrical harness wire connections from the ITT component (Ref. Figure 210). 25. Disconnect the fire extinguisher line and standoffs from the engine and let hang from its attach point at the forward heat shield (Ref. Figure 211). 26. Disconnect the combustion case overboard vent line from the engine and let hang from its attach point at the forward heat shield (Ref. Figure 211). 27. Disconnect the overboard fuel dump hose from the underside of the engine between the forward heat shield and the baffle assembly. 28. Disconnect the two fuel lines from the aft side of the forward heat shield (Ref. Figure 211).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Annunciator Panel (FL-1 thru FL-119, FL-121 and FM-1 thru FM-8) Figure 201

Annunciator Panel (FL-120, FL-122 and After, and FM-9 and After) Figure 202

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

29. Disconnect the fuel flow lines from the forward heat shield and fuel manifold assembly (Ref. Figure 211). 30. Disconnect the two halves of the forward heat shield from itself and the engine fire seal flange and set off to the side of the engine (Ref. Figure 1, 71-30-00). 31. Disconnect the fuel line from the fuel heater (Ref. Figure 213). 32. Disconnect the aft right electrical wire harness connection from the turbine tach generator (Ref. Figure 213). 33. Disconnect the aft right electrical wire harness connections from the oil pressure warning switch and oil temperature sensor (Ref. Figure 213). 34. Disconnect the aft right electrical wire harness connection from the fuel flow transmitter (Ref. Figure 213). 35. Disconnect the aft right electrical wire harness connection from the oil pressure transmitter (Ref. Figure 213). 36. Disconnect the condition control cable mounting bracket, linkage and securing clamp at the engine and remove them (Ref. Figures 214 and 216). 37. Disconnect the power control cable mounting bracket and linkage (green arm) at the engine and remove them (Ref. Figures 214 and 216). NOTE: The green linkage arm stays with the control cable. 38. Disconnect the oil drain line and fitting from the engine (Ref. Figure 215). 39. Disconnect the two fuel lines from the engine driven fuel boost pump (Ref. Figure 215). 40. Disconnect the two drain lines from the engine driven fuel boost pump (Ref. Figure 215). 41. Disconnect the drain line from the starter-generator mounting bracket (Ref. Figure 215). 42. FOR THE RIGHT ENGINE ONLY! Disconnect the drain line from the air conditioner compressor. 43. Disconnect the drain line from the engine fuel control. 44. Disconnect the air intake duct at the starter-generator and the lower aft cowling (Ref. Figure 215). Pull the duct out through the top. WARNING: Make sure the battery and external power to the airplane are disconnected before removing the starter-generator. 45. Disconnect all electrical connections from the starter-generator. Be sure to label all wires to facilitate correct reinstallation (Ref. Figure 209). 46. Disconnect and remove the starter-generator from its mounting bracket (Ref. Figure 215). 47. FOR THE RIGHT ENGINE ONLY! Disconnect the air conditioner compressor from the engine (Ref. COMPRESSOR REMOVAL, 21-50-00). NOTE: Do not disconnect the refrigerant lines or discharge the refrigerant system when performing an engine change.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Baffle Assembly Figure 203

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL 48. Disconnect the oil vent hose and fitting from the engine (Ref. Figure 216). 49. Disconnect the fuel purge line and elbow fitting from the top of the fuel control unit (Ref. Figure 216). j.

Attach an engine sling to the forward and aft engine hoisting lugs and position a suitable hoist directly over the eye of the engine sling (Ref. Figure 1, 71-20-00).

k.

Raise the engine sling sufficiently to relieve the weight on the engine mount isolator.

l.

With the engine supported by a hoist, remove the four bolts that secure the engine and engine mount isolators to the engine mount, removing lower bolts first (Ref. Figure 1, 71-20-00). NOTE: Identify and retain all engine mounting bolts, washers and nuts to ensure correct installation on the new engine.

CAUTION: Before pulling the engine clear of the engine mount, check that all wiring, cables, tube and hose assemblies are disconnected and free from snagging. m. Pull the engine clear of the engine mount and install in a suitable floor stand. Be sure the engine is lifted clear of the baffle (Ref. Figure 217).

ENGINE BUILD-UP The preparation of a new engine for installation consists of removing from the old engine ALL components not found on the new engine, and installing them on the new engine, noting the following peculiarities: a. Position and secure the starter-generator mounting bracket on the new engine in the same position it was installed on the old engine. CAUTION: Consult the Engine Maintenance Manual before attempting to remove the new engine from the shipping container. b. Install the air conditioner compressor mounting bracket on the right engine (Ref. COMPRESSOR INSTALLATION, 21-50-00). c.

Refer to the Engine Maintenance Manual for specific torque values.

NOTE: Tag and identify all hoses, bolts, nuts, washers and electrical connectors; note harness clamp and standoff locations for reinstallation on the new engine. Cap all open hoses and engine ports to prevent contamination.

ENGINE RETURN When an engine is being returned, the following must be done to or enclosed with the engine. NOTE: Refer to the Engine Maintenance Manual for specific instructions on preparing the engine for shipping. a. All openings, bosses and lines must be plugged, capped or covered. b. All electrical connections must be covered. c.

The propeller hub must be covered.

d. The exhaust ports and engine air inlet screen must be covered.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Forward Left Section Figure 204

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Page 207 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL e. All linkage and loose parts must be secured to the engine to prevent movement. f.

The IGNITION EXCITER must be returned with the engine.

g. The ENGINE LOG BOOK must be returned with the engine. h. Use the new engine shipping container to return the old engine. Be sure the engine is secured to the shipping bracket.

ENGINE INSTALLATION a. Attach an engine sling to the forward and aft engine hoisting lugs. Position a suitable hoist directly over the eye of the engine sling (Ref. Figure 1, 71-20-00). CAUTION: Take care to prevent damage to the engine components, plumbing and electrical wiring while the engine is being lowered into position. b. Hoist the engine from the floor stand and position it over the engine mount. Slowly lower it into the mount, being sure that the aft heat shield is lowered behind the engine baffle assembly. c.

With the engine supported by the hoist, install the four bolts that secure each of the four engine mount isolators to the engine mount pads on the engine. Torque the bolts to 275-300 inch-pounds.

CAUTION: Attach the upper engine mount isolators to the engine mount first. When this has been completed, relax the hoist and attach the lower engine mount isolators to the engine mount. Torque each bolt to 450-500 inch-pounds. d. Remove the hoist and sling from the engine. e. Install the following items and components to the engine: 1. Connect the fuel purge line and elbow fitting to the top of the fuel control unit (Ref. Figure 216). 2. Connect the oil vent hose and fitting to the engine (Ref. Figure 216). 3. Connect the drain line to the engine to the engine fuel control. 4. Connect the drain line to the starter-generator mounting bracket (Ref. Figure 215). 5. Connect the two drain lines to the engine driven fuel boost pump (Ref. Figure 215). 6. Connect the two fuel lines to the engine driven fuel boost pump (Ref. Figure 215). 7. Connect the oil drain line and fitting to the engine (Ref. Figure 215). 8. Connect the fuel line to the fuel heater (Ref. Figure 213). 9. Connect the two oil lines to the engine (Ref. Figures 209 and 215). The oil line shown in Figures 209 has an aluminum lower fitting; tighten it to 300 to 500 inch-pounds. The upper fitting is steel; tighten it to 900 to 1,000 inch-pounds. 10. FOR THE RIGHT ENGINE ONLY! Connect the air conditioner compressor to the engine (Ref. COMPRESSOR INSTALLATION, 21-50-00). 11. FOR THE RIGHT ENGINE ONLY! Connect the drain line to the air conditioner compressor.

Page 208 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Propeller Control Cable and Linkage Figure 205

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71-00-00

Page 209 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 12. Connect the aft bonding strap to the engine (Ref. Figure 209). 13. Position the ignition exciter to the engine mount and secure (Ref. Figure 209). 14. Secure the aft ignition exciter electrical wires to the engine mount with the two cable clamps (Ref. Figure 209). 15. Connect the aft right electrical wire harness connection to the oil pressure transmitter (Ref. Figure 213). 16. Connect the aft right electrical wire harness connection to the fuel flow transmitter (Ref. Figure 213). 17. Connect the aft right electrical wire harness connections to the oil pressure warning switch and the oil temperature sensor (Ref. Figure 213). 18. Connect the aft right electrical wire harness connection to the turbine tach generator (Ref. Figure 213). 19. Connect the aft left electrical wire harness connector to the forward end of the ignition exciter (Ref. Figure 209). 20. Position the power control cable mounting bracket and linkage (green arm) to the engine and secure them in place (Ref. Figures 214 and 216). 21. Connect the condition control cable linkage and cable support mounting bracket to the engine and secure them in place (Ref. Figures 214 and 216)). 22. Position and secure the starter-generator to its mounting bracket (Ref. Figure 215). 23. Install the air intake duct to the starter-generator and lower aft cowling (Ref. Figure 215). 24. Reconnect all electrical connections to the starter-generator (Ref. Figure 209). 25. Connect the two halves of the forward heat shield to itself and the engine fire seal flange (Ref. Figure 1, 7130-00). 26. Connect the two fuel lines to the aft side of the forward heat shield (Ref. Figure 211). 27. Connect the fuel flow lines to the forward heat shield and the fuel manifold assembly (Ref. Figure 211). 28. Connect the overboard fuel dump hose to the underside of the engine between the forward heat shield and the baffle assembly. 29. Connect the combustion case overboard vent line to the engine (Ref. Figure 211). 30. Connect the fire extinguisher line and standoffs to the engine (Ref. Figure 211). 31. Connect the aft right electrical wire harness connections to the ITT component (Ref. Figure 210). CAUTION: Tighten the ITT thermocouple harness connections according to the ENGINE MAINTENANCE MANUAL. To prevent damage to the ceramic portion of the thermocouple harness block, hold the bolts rigid while installing and tightening the attaching nuts. DO NOT exceed the recommended torque when tightening the attaching nuts. 32. Connect the upper aft engine fire detector wire and standoffs to the engine (Ref. Figure 209). 33. Connect the fire detector wire plug located on the aft top left side of the engine mount and secure it to the engine mount with the two clamps (Ref. Figure 209).

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Propeller Reversing Lever Figure 206

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

34. Connect the forward fire detector wire and its standoffs to the forward section of the engine (Ref. Figure 212). 35. Connect the forward electrical wire harness connection to the prop tach generator (Ref. Figure 208). 36. Position and secure the prop secondary low pitch warning assembly to the engine (Ref. Figure 208). 37. Attach the ground idle stop solenoid and mounting bracket to the engine (Ref. Figure 208). 38. Connect the forward electrical wiring harness plug to the aft electrical wire harness receptacle in the forward heat shield (Ref. Figure 207). 39. Install the bleed air line and fitting to the engine (Ref. Figure 207). 40. Install the propeller reversing lever and its bushings to the beta valve and front end clevis (Ref. Figure 206). 41. Install the propeller control cable forward mounting bracket to the engine flange (Ref. Figure 212). 42. Pull the propeller control cable forward from the forward heat shield and secure to the forward mounting bracket and propeller governor linkage (Ref. Figures 205 and 212). 43. Connect the deicer brush block assembly to the engine (Ref. Figure 204). 44. Install the forward electrical wire harness and standoffs to the engine (Ref. Figure 204). 45. Connect the overspeed governor and solenoid to the engine (Ref. Figure 204). 46. Install the torque transmitter/autofeather switches mounting bracket assembly to the engine flange (Ref. Figure 204). 47. Install the autofeather switches, lubrication hoses and snubber to the engine (Ref. Figure 204). 48. Connect the vent (torque transmitter) hose to the engine (Ref. Figure 204). 49. Connect the forward electrical wire harness connection to the chip detector (Ref. Figure 204). f.

Add oil to the engine (Ref: OIL SYSTEM, 12-10-00).

g. Position and secure the two center panel aft attaching flanges and the upper section of the baffle to the baffle assembly (Ref. Figure 203). h. Install the propeller to the engine (Ref. PROPELLER INSTALLATION, 61-10-00). i.

Install the engine cowling (Ref. ENGINE COWLING INSTALLATION, 71-10-00).

j.

Remove the cover from the engine air inlet screen.

k.

Remove the drip pan and tail stand.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Bleed Air Connection Figure 207

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71-00-00

Page 213 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL l.

Connect the electrical power to the engine and airplane as follows: 1. Connect the airplane’s battery. 2. Connect the engine’s circuit breakers. 3. Turn the Battery Master switch ON. 4. Press the appropriate switch(es) located on the glareshield to open the fuel firewall shutoff valve(s) to the engine(s). Wait at least 30 seconds (Ref. Figure 201 or 202). 5. Turn the Battery Master switch OFF. 6. Connect the external electrical power to the airplane at this time if needed.

FUEL CONTROL UNIT PURGE PROCEDURE CAUTION: Throughout the following procedure, observe the starter operating limits of 40 seconds ON, 60 seconds OFF,40 seconds ON, 60 seconds OFF, 40 seconds ON then 30 Minutes OFF. a. To purge the fuel control unit of preservation oil, install the unit on the engine and connect it to the airplane fuel supply. Install a suitable line between the fuel control outlet and a clean container. b. With the ignition OFF, and the fuel control lever in the IDLE position, motor the engine until clean fuel flows from the fuel outlet. During the motoring run, move the fuel lever from the IDLE to the CUTOFF position to ascertain fuel shut off. c.

Remove the line used to purge the fuel control unit and connect the engine plumbing to the fuel control outlet. Check the installation for leakage.

CAUTION: Before attempting a start, motor the engine with the fuel shut off to ensure that all fuel has been purged from the engine.

FUEL NOZZLES HANDLING PROCEDURES Extreme care should be exercised when handling fuel nozzles; even fingerprints on the orifice may produce a poor spray pattern. If fuel nozzles are not to be reinstalled in the engine immediately, they should be placed in a covered container to prevent exposure to dirt. If nozzles are to be shipped or stored, they must be separately and securely wrapped. Packing nozzles together in a single container which allows relative movement will damage orifice faces.

ENGINE WASHING PROCEDURES For engine washing, refer to ENGINE WASHING PROCEDURES,12-20-00.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Forward Right Section Figure 208

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE COLD WEATHER PRECAUTIONS Frozen precipitation may be blown into the exhaust stacks if windy conditions exist and particularly if the airplane is parked down wind without covers installed. Ice ingestion, coupled with residual engine heat following engine shut down may allow water to seep by gravity flow into the compressor section and refreeze as the engine cools down and becomes cold soaked in subfreezing temperatures. In cold weather conditions, park the airplane into the wind if possible and install exhaust stack covers. CAUTION: If turbine wheel ice is suspected, monitor N1 closely during the engine start. If no N1 spool up occurs, abort the start in order to avoid over temp of the starter-generator.

ENGINE GROUND OPERATING PROCEDURES NOTE: The airplane ground crew must be familiar with equipment and proper operating procedures, including emergency procedures. AIRPLANE AND ENGINE PRESTART INSPECTION a. Check the airplane documentation to make sure that no discrepancies or removed parts exist that will affect engine or airplane operation. b. Make sure that all engine accessory equipment is installed, plumbing and wiring is properly secured and no engine leaks exist. c.

Inspect engine inlets and exhaust for obvious damage and foreign object debris (FOD).

d. Visually inspect the airplane and surrounding area for the following: 1. Adequate oil, fuel and hydraulic fluid quantity. Replenish if necessary. 2. Fuel, oil or hydraulic leakage. 3. Make sure that all protective covers are removed from the exterior of the airplane. 4. Make sure that no loose equipment or tools are in the immediate area. e. Position the airplane into the prevailing wind and clear of other airplanes or objects. f.

Install main landing gear wheel chocks.

g. Visually inspect runup pad and remove all foreign object debris (FOD). h. Check all ground support equipment and position fire extinguisher equipment nearby.

Page 216 May 1/10

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Aft Left Section Figure 209

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Page 217 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL STARTING ENGINES - EITHER ENGINE FIRST WARNING: Ensure all personnel are familiar with the intake and exhaust operating area dangers during engine start and while engines are running. Make sure that ground personnel are not wearing loose clothing (coats, jackets, scarves etc.) near the engine while it operates. Make sure that hoods on parkas are not loose. CAUTION: Do not move the power levers forward and back quickly unless an acceleration/deceleration test is being performed. Fast movement of the power levers can cause the engine temperature to change quickly. a. Start engine in accordance with the applicable model B300/B300C Pilot’s Operating Handbook and FAA approved Airplane Flight manual. ENGINE SHUTDOWN a. Shutdown engine in accordance with the applicable model B300/B300C Pilot’s Operating Handbook and FAA approved Airplane Flight manual. MOTORING THE ENGINE a. Set the Condition lever to FUEL CUTOFF. b. Set the Ignition and Engine Start switch to OFF. c.

Select Master switch ON.

CAUTION: Do not exceed the following starter-generator starting limitations: 30 seconds ON, 5 minutes OFF, 30 seconds ON, 5 minutes OFF, 30 seconds ON, 30 minutes OFF. d. Set the Ignition and Engine Start switch to STARTER ONLY. e. Release the switch to OFF before the start cycle duration exceeded. WINDMILLING ON THE GROUND it is highly recommended that while the airplane is unattended, the inlet and propeller and exhaust covers are installed to prevent windmilling.

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Center Right Section Figure 210

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Page 219 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Forward Lower Section Figure 211

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Forward Upper Section Figure 212

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Page 221 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Aft Right Section Figure 213

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Power and Control Condition Cables Figure 214

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Page 223 May 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Aft Left Section Figure 215

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SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Aft Right Section Figure 216

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Engine and Typical Floor Stand Figure 217 Page 226 May 1/10

71-00-00

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aeechcraft MODEL 8300

MAINTENANCE MANUAL

COWLING DESCRIPTION AND OPERATION (Effectivity: AIl)

b.

ing

cowling encloses each power plant and is composed of six sections. The upper forward cowling is readily removed by releasing the four cam-type fasteners (two on each side of the cowling). The two cowling center panels are located on both sides of the cowling just aft of the forward upper and lower cowlings and are secured with quick-release fasteners. The lower forward cowling is bolted to the lower aft cowling and incorporates an air inlet scoop which provides an air flow to the engine compressor. An inertial ice vane is installed in the forward lower cowling to prevent the entry of freezing rain and snow into the engine compressor air inlet screen. The upper aft cowling is secured to the lower aft cowling and to the firewall. The upper aft cowling has two hinged access doors located on both sides of the cowling and one The

hinged

access

door located

position by

on

top, each secured in

on

Remove the upper forward cam-type fasteners

cowling (1) by releas_ (com.

Remove the cowling center

panels (2),

each side of the

d.

2.

MAINTENANCE PRACTICES

from the 3.

~igure

right cowling).

from the the

vane.

Disconnect the upper flex hose clamps (6, 3) that connect the anti-ice lip ducts (5, Figure

Figure 3) to the

exhaust stacks

(1, Figure 3).

Working through the cowling center panels (2), remove the four bolts that attach the lower forward cowling (8) to the lower aft cowling (7). 4.

Carefully

5.

Open

1. on

lower and

Remove the upper aft

e.

remove

the

cowling (3)

cowling.

as

follows.

the upper aft

each side of the

cowling access doors (5) cowling by releasing the latches

(6). Remove the two bolts that

end of the

(Effecfivity: All) f.

cowling

to the lower aft

secure

cowling

to the

Carefully

engine

lift the

secure

the aft end

mount.

cowling

Remove the lower aft

the forward

cowling (7).

Remove the two bolts that

4.

I

follows.

engine and cowling cowling center access openings and disconnect the forward ice vane linkage (3, Figure 2)

of the

COWLING REMOVAL

bonding strap engine (leave attached to

as

at the

3.

(Effectivity: All)

found

Reach between each side of the

the

2.

COWLING

cowling (8)

Disconnect the

1.

one

cowling.

Remove the lower forward

side of each

latches. The lower aft

cowling is secured to the upper aft cowling and the engine mount. The lower aft cowling incorporates an engine oil cooler and a by-pass door that provides an outlet for ice particles. the closed

e.

the four

clear of the

cowling (7)

as

engine.

follows:

NOTE CAUTION

damage to the propeller spincowling edges, and the exterior painted surfaces, it is imperative that the cowling be kept level throughout the removal procedure. This may be accomplished by employing two men, one on each side of the cowling.

When the engine is being removed, the lower aft cowling does not need to be removed.

To prevent

ner, the

Disconnectthefollowing

1.

a) engine. b)

The two oil cooler lines

The two

each side of the

NOTE

identify

and

c)

tag all cowling attaching

right

atthecowling.

The

precooler engine.

on

the left side of

bleed air lines,

starter-generator cooling duct

side of the

one

on

on

the

engine.

parts.

´•I

a.

fairings (10) by (11), (six on each

Remove the exhaust stack

ing the cam-type fasteners c;owling for FL-127 and

the

after).

after and

on

releas-

d)

The aft ice

vane

from its

linkage (2, Figure

2).

side of

FM-9 and

2.

of the

Remove the four bolts that

cowling

to the

engine

secure

the aft end

mount.

71-1 0-00

Page A7

1

Jul 31/95

Bee~hcraft MODEL B300 MAINTENANCE MANUAL

I.

2. 3. b.

5. 6. 7. 8. 9. 10. II.

UPPER FORWARD COWLING COWLING CENTER PANEL UPPER AFT COWLING HINGE UPPER AFT COWLING ACESS DOORS LATCHES LOWER AFT COWLING LOWER FORWARD COWLING ANTI-ICE LIP EXHAUST STACK FAIRING (EFFECTIVITY: CAM-TYPE FASTENERS

FL-127 AND AFTERI

FM-9 AND AFTER)

4

2

I 1

10

000 o

o

I I----

O

O

0

O

O

O

0

0

0

0

0

O

O O

O

O

000

1

8

6

csn71alz(n c

Cowling

Installation

Figure

(Effectivity: All) 1

71-10-00

Page 2 Jul 31/95

A7

Qeechcraft MODEL 8300

MAINTENANCE MANUAL

i.

2. 3.

ENGINE MOUNT TRUSS AFT ICE VANE LINKAGE FORWARD ICE VANE LINKAGE

t

Ice Vane and

Linkage (Effectivity: All) Figure 2 71-1 0-00

Page A7

3

Jul 31195

aeechcraft MODEL 8300

MAINTENANCE MANUAL

Carefully lower and engine mount. 3.

the

remove

the

cowling

from

COWLING INSTALLATION

(Effectivity: All)

(Figure I) Install the lower aft

a.

cowling (7)

as

d) b.

damage to the propeller spincowling edges, and the exterior painted surfaces, it is imperative that the cowling be kept level throughout the installation procedure. This may be accomplished by employing two men, one on each side of the cowling. To prevent

two

ner, the

Position the

secure

cowling

the aft end with the four

engine mount attaching bolts.

The starter-generator side of the engine.

a)

6~

cooling

duct

(1, Figure 2)

vane

the left side of

linkage (2, Figure 2).

cowling (3)

cowling

and

on

secure

on

as

follows:

the

engine

2.

Secure the forward end of the

3.

cowling (7)

with the two

Close the upper aft with the latches

cowling to the attaching bolts.

and

secure

cowling (6).

c.

Install the lower forward

cowling (8)

and

1.

aft

mount

it at the aft end with the

attaching bolts.

lower aft

Position the

cowling

to the

access

as

engine

doors

(5)

follows:

and lower

cowling (7).

Connectthefollowing atthecowling.

2.

right

to the

The aft ice

Position the

1.

one on

engine.

Install the upper aft

truss

bleed air lines,

precooler

The two oil cooler lines

c) engine.

follows:

CAUTION

1.

The two

b)

each side of of the

Working through the cowling center panel (2), cowling to the lower aft cowling (7) with the attaching bolts.

2. on

the

secure

four

MI

the

,Ix

D_ A

5

i. 2. 3. 4. 5. 6.

EXHAUST STACKS NUT WASHER BOLT ANTI-ICE LIP FLEX HOSE DISCONNECT

CLAMPS C95FL7181207 C

Anti-ice

Lip and Ducts (Effectivity: All) Figure 3

71-10-00

Page

4

Jul 31/95

A7

43eechrraft MODEL 8300 MAINTENANCE MANUAL 3.

lip ducts (5, Figure 3) to (1, Figure 3) with the flex hose

Connect the anti-ice

the exhaust stacks

4.

the

at the

cowling

connect the forward ice

clamps (6, Figure 3).

d.

NOTE

Torque the T-bolts on

the

Position and

secure

one for each side of

special clamps

e.

and

to 30 inch-lbs.

i. 2. 3. 4. 5. 6.

Reach between each side of the

cowling

CLEVIS ASSEMBLY NUT (LOOSEN TO ADJUST DOUBLER LONGERON WASHER PIN

CLEVIS

the

engine and openings and linkage (3, Figure 2).

center access

vane

cowling cowling.

the

center

panels (2),

Place the upper forward cowling (1) in position secure with the four cam-type fasteners (11).

ASSY.)

C95FL7181206 C

Upper Cowling

Adjustment (Effectivity: All) Figure 4

Door Latch

71-10-00

Page A7

5

Jul 31/95

Y3eechcraft MODEL 8300 MAINTENANCE MANUAL f.

Install the exhaust stack

fairings (10) by securing

the cam-type fasteners (11), (six cowling for FL-127 and after and

CRAFT P/N

45-590074-7) can be used for the force push-pull gage can be ordered

on

each side of the

measurement. The

on

FM-9 and

through

after).

a

BEECHCRAFT authorized outlet.

NOTE

UPPER COWLING DOOR LATCH ADJUSTMENT

latching force, thread assembly into the longeron as required. To decrease the latching force, thread the clevis assembly out of the longeron. Use only half or full turns to

(Effectivity: All)

To increase the

the clevis

(Figure I) keep the upper cowling door securely during flight, the door latches should be adjusted to operate by moderate hand force. While not easily released or secured with the fingers, the latches must be operable without the use of tools or shop In order to

closed

aids. a.

Release the latches

cowling b.

access

doors

Loosen the nut

(6)

and open the upper aft

assembly. the nut

Tighten bly (1, Figure 4).

d.

(2, Figure 4)

on

Ensure that the

the clevis remains

parallel

to the

the clevis

assem-

pin (6, Figure 4) in longeron (4, Figure

4).

(5).

(2, Figure 4)

maintain the proper orientation of the clevis

on

the clevis

assem-

e´•

Close the upper aft cowling access doors (5). securing the latches (6), check that the force

While

bly (1, Figure 4).

Starting with the forward latch, adjust the height of the clevis (1, Figure 4) on the longeron (4, Figure 4) so that a force of 12 to 14 inch pounds is required to close the latch. Adjust the aft latch as previously outc.

lined, then recheck the forward latch. Forces should

required is moderate and approximately equal for both (6).

latches f.

Release the latches is moderate and

required (6).

latches

Close the upper aft cowling

be measured within .50 inch of the lower end of the

g.

latch handle. A

secure

push-pull gage (such

as

BEECH-

(6) and check that the force approximately equal for both

the latches

access

doors

(5)

and

(6).

71-1~00

Page

6

Jul 31/95

A7

Hawker Beechcraft

Corporation

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

MOUNTS

ENGINE MOUNT supported by a welded tubular mount of 4130 chrome molybdenum steel, which is bolted to the nacelle attaching points. If the engine mounts are removed from the engine firewall, bolts are to be torqued to 365-390 inch-pounds on reinstallation. Various brackets are welded to the engine mount to attach cowling and components adjacent to the engine (Ref. Figure 1). The

engine

is

firewall at four

ENGINE MOUNT ISOLA TORS Four

engine

mount isolators are utilized to secure the

the airframe structure. Each

anchored to the without

engine

engine

engine

to the

engine mount engine by

and

dampen engine

vibration to

mount isolator is attached to the

mount with one bolt. Individual

four bolts, and each isolator is mount isolators may be replaced or overhauled

engine removing the engine from the engine mount, provided the weight of the engine 1).

is

supported erugiF.feadequately R (

CAUTION: All

engine

For instructions

on

mount isolators on an

engine

the removal and installation of

must be of the same manufacturer and

engine

mount

type.

isolators, refer to ENGINE REMOVAL and ENGINE

INSTALLATION, 71-00-00.

nn4

71-20-00

Ma~85:

Hawker Beechcraft

Corporation

MANUAL SUPER KING AIR B300/B300C MAINTENANCE

An~ HOISTING LUG

FORWARD HO1ST\NG LUG

aa

~S;i’C´•

i/

h~;

:a

ENGINE MOUNT ISOLATOR

ENGINE MOUNT ISOLAT04 ATTACH F’OINTS ENGINE MOUNT

\I DETAII

A

300260-4

Engine

Mount and Isolators

Figure

Page

27120-00

1

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

MOUNTS- MAINTENANCE PRACTICES ENGINE MOUNT RECONDITIONING Since the

engine mount is a reconditioning of this type mount

assembly fabricated

welded

would be

as

from 4130 chrome

molybdenum steel,

normal

follows:

NOTE: Some cracks may be repaired by approved heliarc welding. Hawker Beechcraft Corporation Technical Support should be consulted on an individual engine mount basis to determine if welding is possible or

feasible. a.

b.

Strip paint If cracks

from the

are

to be

engine

mount and

magnaflux inspect

welded, preheat the section

to be

the mounts for cracks.

repaired

to 400 to 800"F and

post-heat after repair to

700

to 8000F for stress relief.

c.

Check the tubes for

d.

Clean the

bushing e.

engine

straightness.

mount for

painting

and

cover

all

bushings

to

prevent paint from adhering

to the inside of the

ends.

Prime the

engine

mount and cover with aluminium

paint.

ENGINE MOUNT ASSEMBL Y INSTALLA TION Should the engine mount assembly be removed for any reason, or following steps should be followed to ensure proper alignment with a.

a new

engine

assembly be installed, the engine cowling:

mount

the firewall and the

Position the

engine mount assembly up to the firewall and install bolts only where the engine mount assembly points are flush with the firewall. Torque these bolts to 365 to 390 inch-pounds. If at least one thread does protrude through the barrel nut, remove the AN960-616 washer from the bolt and torque the bolts as above.

attach not

b.

Check the

remaining attach points. If all attach points torqued 365 to 390 inch-pounds.

are

flush with the firewall, the

remaining

attach bolts may

be installed and c.

If the

points are not flush with the firewall, measure the gap. If the gap does not exceed (Ref. Chart 201) of the proper thickness may be installed between the engine mount assembly and the firewall, then the bolts may be installed and torqued as above. If the gap exceeds 0.100 inch between the engine mount assembly and the firewall, contact Hawker Beechcraft Corporation Technical remaining

0.100

inch,

Support d.

a

attach

shim

for evaluation and recommended action.

If the

engine mount assembly is removed from the firewall to install the engine (after alignment of the engine assembly with the firewall), install the engine into the engine mount assembly. Then reinstall the engine mount assembly and engine up to the firewall assembly using the shims that were established for proper alignment on the engine mount assembly to the firewall. mount

e.

If the

engine and engine mount assembly were built up off the airplane without proper alignment with the firewall, position the engine and engine mount assembly up to the firewall, then install the bolts at the engine mount assembly points flush with the firewall. Remove the attach bolts to the engine isolator and the engine mount assembly. Lift the engine clear of the engine mount assembly and check for proper alignment with the firewall as

f.

noted above.

Check the

engine cowling to procedure.

ensure

that

no

binding

or

twisting

is evident. If any

binding

or

twisting

is noticed,

repeat the above

71-20-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201

Shims for

I

Engine

Mount

Assembly

to Firewall

SUPPLIER

SPECIFICATION

MATERIAL THICKNESS

NOTE

0.020 inch

Alloy 4130 (formerly of MIL-S-18729) specified according to the different conditions: Shim is made of

0.025 inch

Condition A 0.032 inch

0.040 inch

Page

yaM202

1/08

(Annealed)

SAE-AMS-6350

by

71-20-00

MA

(Modified Annealed),

Locally

Fabricated.

SAE-AMS-6351

(Normalized or otherwise producer), SAE-AMS-6345

Condition N the

or

or

heat treated

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIRESEALS

DESCRIPTION AND OPERATION

ENGINE HEA T SHIELDS The two

engine

heat shields

(fireseals) (Ref. Figure i)

are

attached to the

engine, just

forward and aft of the

engine

compressor intake. Each heat shield is constructed of semicircular sections, which are bolted to the engine fireseal flanges and to each other to form a complete seal between the engine and cowlings. The heat shields also provide

support for all lines, controls and ducts that pass from

na~

one

engine

fire

zone

to another.

71-30-00

MaP;I~:Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

O

ATTACHING BOLTS (16)

0‘

A~ISACnlNG BOCTS C18)

AFT HEAT SHIELD

FORWARD HEAT SHIELD 300-241-7

Engine Heat Shields Figure 1

Page

271-30-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ELECTRICAL HARNESS

DESCRIPTION AND OPERATION

The three power plant electrical harnesses connect the various engine electrical components with the firewall electrical plugs. The left aft harness is routed along the left side of the engine mount, connecting various aft engine

components. It is routed through the baffle assembly to

a

plug assembly

in the forward heat shield where it connects

with the left forward harness. The left forward harness continues from this

plug

to various forward

engine

electrical

components and the propeller’s electrical systems. The right harness is routed along the right side of the engine mount to various engine components, the ITT component and to a plug assembly in the baffle assembly. From this plug it connects to the ice vane electrical components.

nn,

71-50-00

May

1/08Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE DRAINS

DESCRIPTION AND OPERATION

ENGINE FUEL PURGE SYSTEM The fuel purge system is designed to ensure that any residual fuel in the fuel manifolds is consumed during engine shutdown. During engine operation, compressor discharge air (P3 air) is routed through a filter and check valve

pressurizing

a

small air tank mounted

on

between the air tank and fuel manifolds

the

engine

causes

engine shutdown the pressure differential discharged from the air tank, through a check valve and fuel, remaining in the fuel manifolds, out through the nozzles

truss mount. On

air to be

into the fuel manifold system. The air forces all residual

and into the combustion chamber. The fuel forced into the combustion chamber is consumed, which in turn a

causes

momentary rise in engine speed.

71-70-00Page

1

SUPER KING AIR B300/B300C MAINTENANCE MANUAL 200200200

ENGINE DRAINS - MAINTENANCE PRACTICES FUEL PURGE TANK REMOVAL a. Remove the bleed air line, filter and check valve from the inlet port of the tank (Ref. Figure 201). b. Remove the check valve and tube from the outlet port of the tank. c.

Remove the four bolts, nuts and clamps which secure the tank to the mounting plate.

d. Remove the tank from the airplane.

FUEL PURGE TANK INSTALLATION NOTE: Anytime the O-rings are removed, replace them with new O-rings a. Install the fitting and O-ring (if installed) in the outlet port of the tank. Install the check valve at the outlet port (Ref. Figure 201). b. Install the check valve and O-ring in the inlet port of the air tank. Install the O-ring and filter in the inlet port of the check valve. c.

Position the air tank on the mounting plate in the original position. Secure the air tank to the mounting plate with the two clamps, four bolts, washers and nuts.

d. Connect the bleed air line to the filter on the inlet side of the air tank. e. Connect the tube leading to the flow divider to the check valve on the outlet side of the air tank.

FUEL PURGE TANK CLEANING Refer to Chapter 5-00-00 for inspection and cleaning intervals. a. Refer to FUEL PURGE TANK REMOVAL and remove the tank from the airplane. b. Flush the tank with solvent (1, Chart 1, 71-00-00) and blow dry with shop air. c.

Refer to FUEL PURGE TANK INSTALLATION and install the tank.

FUEL PURGE SYSTEM AIR FILTER INSPECTION AND CLEANING Refer to Chapter 5-00-00 for inspection and cleaning intervals. a. Remove the bleed air line from the filter. b. Remove the filter from the check valve. The O-ring that is installed between the check valve and filter should be replaced if damaged. c.

Inspect filter for rust and corrosion, clean with shop air. If the filter is rusted or corroded, replace filter.

d. Install the O-ring between the filter and the check valve. Connect the filter to the check valve. e. Connect the bleed air line to the filter.

A27

71-70-00

Page 201 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Engine Fuel Purge System Figure 201

Check Valve Pressure Flush Figure 202

Page 202 Feb 1/10

71-70-00

A27

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUEL PURGE SYSTEM CHECK VALVE INSPECTION, CLEANING AND LEAKAGE TEST CAUTION: Do not disassemble check valve. Refer to Chapter 5-00-00 for inspection and cleaning intervals. a. Remove check valve (Ref. Figure 201). b. Inspect for any foreign material and corrosion. CAUTION: Wear rubber gloves and eye protection when using solvents. c.

Pressure flush the check valve using solvent (1, Chart 1, 71-00-00) to remove carbon particles or sludge residue (Ref. Figure 202).

d. After all solvent is drained out of check valve, blow dry with shop air (80 - 120 psi). e. After cleaning, test the check valve for leakage (Ref. Figure 203). 1. Apply a filtered regulated air source (40 - 100 psi) to the downstream side of the check valve. 2. Fill the upstream side of the check valve with water and look for signs of leakage (bubbles). No leakage is allowed. If leakage is detected repeat steps c. through e. Replace the check valve if leakage is detected. f.

After all water is drained out of the check valve, blow dry with shop air (80 - 120 psi).

Check Valve Leakage Test Figure 203

A27

71-70-00

Page 203 Feb 1/10

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUEL PURGE SYSTEM FLOW DIVIDER/PURGE VALVE LEAKAGE TEST a. Disconnect the fuel purge line (P3 air) from the engine flow divider purge valve. b. Connect a fuel resistant collection hose and bottle to the flow divider purge valve. c.

Perform an engine start and allow the engine temperature to stabilize.

d. No fuel leakage is allowed. If fuel leakage is detected from the flow divider purge valve while the engine is running, replace the flow divider purge valve. Refer to the applicable Pratt and Whitney Engine Maintenance Manual. e. Shut down the engine. NOTE: Drops of fuel may exit the flow divider purge valve shortly after shutdown. This is considered normal because the P3 line was disconnected, and the fuel in the fuel manifold lines was not purged on shutdown and will be free to exit. f.

Disconnect the collection hose and bottle from the flow divider purge valve.

g. Connect the fuel purge line (P3 air) to the engine flow divider purge valve. h. Perform a dry motoring cycle prior to the next engine start.

Page 204 Feb 1/10

71-70-00

A27

%HAPTE R

ENGINES

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE

CHAPTER 72

TABLE OF CONTENTS

SUBJECT

PAGE 72-00-00

Engine-

A25

General

72-CONTENTS

Feb

1/09Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE

List of Effective cH-SE-SU

PAGE

DATE

72-LOEP

1

Feb 1/09

72-CONTEWTS

1

Feb 1/09

72-00-00

1

Feb 1 109

A25

MA~UAL

Pages

72-LOEP

Feb

1/09Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300~B300C MAINTENANCE MANUAL

ENGINE- GENERAL NOTE: Refer to the PT6A-60A

Engine

Maintenance Manual P/N 3034342 for detailed information

on

these

subjects.

n25

72-00-00

Feb

1109Pagel

CHAPTER

IGNITION

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 74

IGNITION

TABLE OF CONTENTS

SUBJEC T

PA GE 74-00-00

Ignition Description and Operation Ignition System Auto-ignition System Ignition- Maintenance Practices Spark Igniters Auto-ignition System Auto-ignition Pressure Switch Removal. Auto-ignition Pressure Switch Installation Auto-ignition Check Ignition ExciterControl Box Removal. Ignition ExciterControl Box Installation

..1

........._._._._

........._201

........._._._._

..........201 ........201

................_.

n25

...201

.........._.......

..........._202

................._

............203

74-CONTENTSPagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

74-LOEP

1

Feb 1/09

74-CONTENTS

1

Feb 1/09

1 and 2

Feb 1/09

201 thru 204

Feb 1/09

74-00-00

A25

Pages

74-LOEP

Feb

1/09Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

IGNITION

DESCRIPTION AND OPERATION

IGNITION SYSTEM

spark ignition system of the PT6A-60A engine provides quick light-ups over a wide temperature range. The system includes a solid state ignition exciter designed to be mounted on the airframe, two individual high tension cable assemblies, and two spark igniters. Although designed to be energized by the 28-VDC electrical system of the airplane, the ignition system will function effectively over a range of 9 to 30 volts.

The

ignition exciter encases in epoxy resin the solid state circuitry, transformer, and diodes required to transform the DC input to a high voltage output. When the ignition exciter is energized, a capacitor is progressively charged until the energy stored is sufficient to ionize a spark gap in the unit and discharge the capacitor across the two spark igniters through a dividing and step-up transformer network. The network is designed so that one igniter will continue to function even though the other is open or shorted. The network also enables the capacitor to discharge automatically should either or both igniters become inoperative, or should input voltage be

The sealed unit of the

switched off.

engine is delivered by two ignition braiding. The cables are equipped with coupling nuts at each end for connection to the ignition exciter and spark igniter. The spark igniters are mounted adjacent to the fuel manifold at the 4 and 9 o’clock positions on the gas generator case. Each spark igniter is a double-ended, threaded plug with a central positive electrode enclosed in annular semiconducting material. The electrical potential produced by the ignition exciter is applied across the gap between the central conductor and the igniter shell (ground). A small current passes across the semiconducting material of the spark igniter as the potential developed by the ignition exciter increases. This current increases until the air between the central conductor and the shell ionizes into a high energy discharge between the electrodes. The resultant spark always occurs at some point in the annular space between the central conductor and its shell.

The electrical energy output from the ignition exciter to the spark igniters on the cable assemblies, each consisting of an electrical lead contained in flexible metal

AUTO-IGNITION SYSTEM

auto-ignition system (Ref. Figure 1) is designed to provide automatic ignition when engine torque falls too low. system ensures ignition during take-off, landing, turbulence, and during adverse conditions of icing weather. The auto-ignition control switch on the left subpanel is wired to a pressure switch mounted adjacent to the torque pressure transmitter just forward and above the exhaust outlet on each engine. This switch monitors torque oil pressure. When the control switch is in the ARM position and engine torque drops below 16 percent, the pressure switch closes to provide power from a 5-ampere circuit breaker on the right circuit breaker panel to energize the engine igniter and illuminate the IGNITION ON light (green) in the annunciator panel located forward of the pedestal. The igniter will continue to function until engine torque increases enough to actuate the pressure switch and break the circuit to the igniter and annunciator lights. For extended ground operation, the auto-ignition system should be turned off to prolong the service life of the igniter units. The

This

n25

74-00-00

Hawker Beechcraft

Corporation

MANUAL SUPER KING AIR B300/B300C SERIES MAINTENANCE

AUTO IGNITION ARM SWITCHES AUTO IGNITION/AUTO FEATHER PRESSURE SWITCII

D1P

AU~TO IGNITIONIAUTO FEATHER PRESSURE SWITCH

IGNITOR

SUB PANE~

IGNITOR

D

h A

B

a,

RH CIRCUIT BREAKER PANEL

IGNITOR POWER CIRCUIT BREAKERS (C g RJ

ENGINES LEFT

DETAIL

C

VIEW LOOKING UP BELOW ENGINE

O

0: ENG AUTO IGNITION

IGNITOR POWER

ARM~

I

OFF

RIGHT

DETAIL

A DETAIL

B

DETAIL

D

350-2((´•37

Auto-ignition System Figure 1

Page

beF2

1/09

74-00-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

MAINTENANCE PRACTICES

IGNITION

SPARK IGNITERS WARNING: If

a

the

spark igniter is to be removed within six minutes of the last operation, ground the lead engine to dissipate possible residual voltage of the ignition exciter.

to

spark igniters (Ref. Figure 201) for proper operation, disconnect one lead at the ignition exciter and discharge of the spark igniter that is still connected, then repeat the procedure for the other spark igniter. The igniters will spark at a rate of 0.8 to 1.0 spark.per second with 9 volts applied and up to a rate of 1.4 to 4.0 sparks per second with 30 volts applied.

To check the

listen for the

AUTO-IGNITION SYSTEM AUTO-IGNITION PRESSURE SWITCH REMOVAL This switch is mounted

outlet

on

each

NOTE: A

adjacent

torque pressure transmitter just forward

and above the left hand exhaust

engine.

double-pole,

double-throw switch functions both

pressure switch for the Place the

b.

Be certain the external power

c.

Remove the upper forward

d.

Unsafety

and

remove

e.

Unsafety

the

mounting

f.

Install

battery

and

as

the

auto-ignition pressure

switch and the

high

autofeathering system.

a.

a

to the

generator switches located source

cowling

on

the left hand

subpanel

in the OFF

position.

is disconnected.

as

outlined under the

heading

COWLING REMOVAL, 71-10-00.

the electrical connector from the switch. nut at the base of the switch. Remove the switch from the

protective plug

in the switch

mounting

airplane.

hole to prevent contamination of the governor oil

supply.

AUTO-IGNITION PRESSURE SWITCH INSTALLATION a.

Remove the

b.

Position the

c.

Safety

d.

Connect the electrical

e.

Install the upper forward

protective plug new

O-ring

wire the nut

on

from the switch

mounting pole.

and install the switch in the hole.

Tighten the

switch

mounting

nut to seat the

O-ring

seal.

the switch.

plug.

The

cowling

plug as

is to be

tightened finger tight

outlined under the

and then

safety

wired.

heading COWLING INSTALLATION,

71-10-00.

AUTO-IGNITION CHECK a.

b.

c.

With both

engines running,

set the power levers at idle.

in the annunciator

Place the left hand and

right hand auto-ignition switches in the ARM position. Both IGNITION ON (green) lights panel should illuminate. The annunciator panel is located forward of the pedestal.

Advance the

hand power lever until 20% of torque is indicated and the R IGNITION ON

right

extinguished.

n25

74-00-00

light

is

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

I

d.

Retard the

e.

Pull the

f.

Press the

g.

Repeat

right

right

hand power lever until the R INGNITION ON

light

hand circuit breaker and ascertain that the R IGNITION ON

right hand ignition circuit breaker and ascertain that

the

illuminates at

procedures

in

light

approximately

16%

torque.

goes out.

the R IGNITION ON

light

illuminates.

steps "b" through "f" with the left hand engine auto-ignition system.

IGNITION EXCITER CONTROL BOX REMOVAL

spark igniter is to be removed within six minutes of the last operation, ground the lead to engine to dissipate possible residual voltage of the ignition exciter. Always disconnect couplings at the exciter first and use insulated tools to remove the nuts. Do not touch output connectors or coupling nuts with bare hands.

WARNING: If

a

the

NOTE: The The

ignition

following procedure

is

applicable

to both

engines.

exciter control box is located to the left hand side of the

engine

and is accessed

by opening

the left hand

cowl door.

battery and generator switches

a.

Place the

b.

Make

sure

c.

Open

the left hand cowl door.

d.

Tag

e.

Disconnect the electrical power

f.

Cap

g.

Remove the

the

the external power

igniter

source

located

supply

wire from the

connector from the

igniter

CAUTION: When

loosening or tightening braiding or ferrules turn at the

damage

in the OFF

position.

the

damage

and contamination.

Cap

lead connectors to protect from

j.

Remove the bolts

k.

Remove the

I.

Place the battery and generator switches located

and nuts

control box from the

20274-00-00

nuts do not let the

exciter control box.

i.

ignition exciter

coupling

ignition

lead connectors from the

(sixteen)

connector

ignition

cable

time.

igniter

washers

exciter control box.

and contamination.

igniter lead

same

Disconnect the

(four),

ignition

lead connectors.

h.

Page

subpanel

leads to facilitate installation.

safety

igniter

the left hand

is disconnected.

the electrical connector to protect from

the

on

(four)

from the

ignition

exciter control box.

airplane. on

the left hand

subpanel

to the ON

position.

A25

Hawker Beechcraft

Corporation

SUPER KING AIR 8300/B300C SERIES MAINTENANCE MANUAL

IGNITION EXCITER CONTROL BOX INSTALLATION

spark igniter is to be removed within six minutes of the last operation, ground the lead to engine to dissipate possible residual voltage of the ignition exciter. Always disconnect couplings at the exciter first and use insulated tools to remove the nuts. Do not touch output connectors or coupling nuts with bare hands.

WARNING: If

a

the

NOTE: The The

ignition

following procedure

applicable

is

to both

engines.

exciter control box is located to the left hand side of the

engine

and is accessed

by opening

the left hand

cowl door.

battery

and generator switches located

a.

Place the

b.

Make

sure

the external power

c.

Make

sure

the surface of the firewall/baffle is

d.

Locate the

e.

Install the bolts

NOTE: Make f.

ignition

sure

Remove the

source

washers

(sixteen)

the two wire harness

protective

subpanel

in the OFF

position.

properly prepared

to

provide adequate electrical bonding.

position.

and nuts

clamps

caps from the

the left hand

is disconnected.

exciter control box in to

(four),

on

are

(four)

to secure the

ignition

exciter control box in to

position.

installed with the bottom bolts, washers and nuts.

igniter lead

connectors.

CA UTION: Do not let lubricant contact the center conductor of the exciter connectors. Contact may result in resistance which could generate heat and oxidation. g.

Lightly

CAUTION:

coat the threads of the

ignition exciter

connector

coupling

nuts do not let the

h.

Observing the identification tags, connect the igniter leads to the ignition exciter control connector coupling nuts finger tight plus 45" and safety wire.

i.

Remove the

j.

Connect the electrical power

k.

Closethelefthand

I.

Place the

n25

battery

caps from the electrical power

supply

cable to the

supply

ignition

box.

ignition

generator switches located

on

connector.

exciter control box.

the left hand

subpanel

to the ON

cable

Tighten igniter lead

enginecowling.

and

high

control box connectors with lubricant.

When loosening or tightening the igniter lead braiding or ferrules turn at the same time.

protective

a

position.

74-00-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C SERIES MAINTENANCE MANUAL

1

B

:I,´•op

PI o

I.IGNITION EXCITER BOX

s~3

1

2. IGNITION EXCITER FLANGE 3. WASHER

//_nllv

II,I_

1

4. BRACKET

1

5. BOLT

G.WASHER 7. SHOULDER WASHER

8. WASHER

DETAIL

A

Ir;Ic~j ;T

7

BIa"l_IU"a DETAIL

9

OETIILC

B FM74e 9854231\*./Ll

Ignition

Exciter Control Box Installation

Figure

Page

beF402

1/09

74I00I00

201

A25

CHAPTER

ENGINE

CONTROLS

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 76

ENGINE CONTROLS

TABLE OF CONTENTS

SUBJECT

PAGE 76-00-00

EngineControls- Description and Operation SpecialTools and Recommended Materials. Engine Controls Maintenance Practices Power Control Rigging Propeller Control Rigging Reversing System Rigging Governor Control Rigging.

.............1 .............1 ...............201 .........201

................._

................._

...205 ................._

................._

Condition Control Catch Gate Removal

Condition Control

...209

..............211

Condition ControlCatch Gate Installation. Condition Control Catch Gate

.......205

.............211

Inspection

..............212

Rigging

.......215

PropellerBeta Rod LengthAdjustment. Ground Run Rigging Check

...............215

.....216

Low Idle Check. Deadband Check

High

Idle Check

..........217

................._

Maximum Reverse Check

...218

Power LeverMismatch Check

.218

RPM Check.

Governing Feathering Check TorqueCheck...

.....219 ..........219

....219

Solenoid ReleaseCheck

....221

Ground Idle Solenoid Check.

..221

Adjustment Check PitchWarning Check

BetaValve Low

.221 ...222

Maximum PowerCheck

Ground

.....222

IdleStop SwitchAdjustment

Inspectionof

.222

PowerLeverDetent Pin.

................223

EngineControls Removal (Power, Propellerand Condition Levers) Engine Controls Installation (Power, Propellerand Condition Levers) Engine Control CableTestand RepairProcedures Equipment Required forTesting, Purging and Repair of Engine Control Cables.

................._

........._.226

................._

LeakTestof

EngineConirol

Cables.

Nitrogen Purge of Cables. Inspection and Repairof Damaged EngineControl

n25

...........226 ......229

.229 ..............229 ...229

Cables.

...............229

76-CONTENTS

~X:Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

76-LOEP

1

Feb 1/09

76-CONTENTS

1

Feb 1/09

1 and 2

Feb 1/09

201 thru 230

Feb 1/09

76-00-00

A25

Pages

76-LOEP

Feb

1/09Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

ENGINE CONTROLS

Control cables connect the control levers in the each

engine.

pedestal

to the

linkage that operates the various components on provide for rigging adjustments at the pedestal cables are anchored to the brackets in the pedestal

Each cable conduit terminates in threaded rod ends to

linkage on the engine. The conduits for the engines. The cables are routed from the pedestal aft under the crew compartment floorboards in groups to each engine. At a point just aft of the partition between the cabin and crew compartment, a set of controls for each engine branches outboard along the leading edge of the center section to the nacelles, then forward through the firewall to the engine linkage. The cables are protected from the adjacent structure by spacers and grommets. Each control cable is interconnected through bellcranks and push rods to its respective control lever in the pedestal. levers and at the

and at the

The

propulsion system

is

operated by three

sets of controls: the power

The power levers and the condition levers control and control constant speed propellers through the

levers, propeller levers and condition levers.

engine power. The propeller levers are operated primary governor located on each engine.

conventionally

The power levers control engine power from idle through takeoff power by operation of the gas generator (N1) governor in the fuel control unit. Increasing N, rpm results in increased engine power. When the power levers are lifted over the IDLE detent, they control engine power through the beta and reverse ranges.

speeder spring inside the primary governor to reposition the pilot valve, which propeller rpm. When the propeller lever is pulled into the feathering range, the feather dump valve plunger on the governor is depressed, which causes complete dumping of high pressure oil. Detents at the rear of lever travel prevent inadvertent movement into the feathering range. Each

propeller

results in

an

lever

increase

operates or

a

decrease of

The condition lever has three

positions,

FUEL CUTOFF, LOW IDLE and HIGH IDLE. This lever controls the idle

cutoff function of the fuel control unit. When the condition lever is set in the LOW IDLE

unit)

control is set to the

for 70

72%

N1

to obtain

a

position, the FCU (fuel control position

The condition levers may be set in the HIGH IDLE faster response when maximum reverse thrust has been selected.

(normally)

62

64%

N1 position.

SPECIAL TOOLS AND RECOMMENDED MA TERIALS

special tools and recommended materials listed in Chart 1 and Chart 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier or by compliance with the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO The

THE REQUIREMENTS OF THE SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE

CHARTS.

Only

the basic number of each

responsibility applicable specification prior to usage of product to be used. the latest revision. It is the

n25

specification

is listed. No

of the technician the

product

or

attempt has been made

to

update the listing

to

mechanic to determine the current revision of the

listed. This

can

be done

by contacting the supplier

76-00-00

of the

I I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

Special Tool Name 1.

Engine Inletprotective

Tools

Part No.

Supplier

CPWA 32350A

Screen

Use

Kell-Strom Tool Co.

Prevent

214 Church St.

damage

foreign object to engine.

Wethersfield, CT 06109 2.

MaximumN1

Shim

WT-107901

Bauer Howden inc.

Tool

50 Tower Lane

Adjust maximum N1 on engine.

power

Avon, CT 06001-4228 3.

Obtain

HeatGun

Locally

Shrink

tubing.

Chart 2

Recommended Materials Material

Specification

Product

Supplier Obtain Locally

1.

DryNitrogen

2.

Isopropyl Alcohol

TT-1-735

3.

Trichloroethane

O-T-634

Obtain

Locally

B.F. Goodrich

Akron, OH 4.

TeflonTape

0.005 inch thick, 3/4 inch wide, pressure sensitive,

extruded

TFE

Minnesota

Mining and Manufacturing Co. 3M Center

type.

St. Paul, MN 55144 5.

Heat

ShrinkableTubing

TFE

Minnesota

Mining and Manufacturing Co. 3M Center St. Paul, MN 55144

6.

Lubricant

Door Ease

American Grease Stick Co.

Hoyt Muskegon,

2651

7.

Adhesive

EC1300L

MI 49443

Mining and Manufacturing Co.. Minnesota

3M Center

St. Paul, MN 55144

Page

beF2

1109

76-00-00

nzs

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE CONTROLS

MAINTENANCE PRACTICES

POWER CONTROL RIGGING a.

Move the power levers to the IDLE detent. Install the 0.25-inch rig pin through the hand side of the pedestal and through the two power lever bellcranks.

rigging

NOTE: If the bellcrank holes do not line up, adjust the pedestal interconnect rods until ready cable clear as required to install the rig pin. b. c.

Disconnect the Loosen the

the d.

rigging

Make

sure

clevis of the

rear

screw

reversing

cable from the cambox

they do. Move the oxygen

(Ref. Figure 202).

input lever clamp and install the rig pin (a (Ref. Figure 202).

in the cambox

hole in the cambox

hole in the lower left

that the threaded end of the power control cable extends through the check hole).

#41 drill bit, 2.5 inches

past the check hole

long) through

in the rod end

(safety

wire should not pass e.

Position the cambox

input

input lever is horizontal and the top edge of the bearing rod input lever tightening bolt (Ref. Figure 202). If the power control cable placement of the input lever, move the u-bolt up to the next set of holes on the

lever

so

that the cambox

end is flush with the head of the cambox

is too short to allow horizontal cable support bracket. f.

Adjust

the interconnect rod until the distance between the center of the attach hole in each rod end is 8.28

inches. Connect the rod to the top hole in both the FCU

g.

Remove the

h.

Adjustthedeadband asfollows: 1.

Make

rig pin

sure

from the cambox and the

that the

rear

clevis of the

pedestal

reversing

arm

and the cambox

arm

(Ref. Figure 202).

bellcranks.

cable is disconnected from the cambox.

CAUTION: If the power lever does not move easily into full reverse, do not force it. Check that the reversing cable is disconnected or that the overcenter link is properly oriented with respect to the fuel control lever. 2.

Pull the

pedestal

power lever into

reverse

far

enough

to

move

the FCU fuel control lever off the deadband

stop surface (Ref. Figure 202, Detail A). cambox, slowly move the input lever clockwise until the deadband stop screw just hits the stop (Ref. Figure 202, Detail B). (The screw should be against the stop such that a piece of paper between the screw and the stop will be held tightly and any further motion in the reverse direction will release the paper.) At this position, the pedestal power lever should be approximately 0.25 inch aft of the GND FINE detent. Temporarily mark this position with a piece of tape labelled "MARK 1".

3.

At the

4.

At the cambox,

slowly move the input lever clockwise until the deadband stop screw is about to lift off the stop, but still grips the paper. At this position, the pedestal power lever should be approximately 0.25 inch forward of the IDLE detent. Temporarily mark this position with a piece of tape labelled "MARK 2". CAUTION: To avoid loss of sequence, do not rotate the serrated washer by a

more

than 2

or

3 serrations at

time.

NOTE: Fine adjustments to the deadband position should be made with the interconnect rod. If more than two turns of the rod are required, the adjustment should be made with the serrated washer.

,2,

76-00-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

5.

If necessary, adjust the deadband position forward or aft in the pedestal by changing the length of the interconnect rod or by rotating the serrated washer on the FCU arm shaft (Ref. Figure 202, Detail B). Make

the first washer.

adjustments with Rotating the rod

either counterclockwise

approximately 6.

the interconnect rod; if these shaft

or

moves

adjustments

the serrated washer clockwise

the deadband aft. Each serration

are

insufficient, then rotate the serrated the deadband forward; rotating

moves on

the washer

moves

the deadband

by

1/16 inch.

If necessary, adjust the deadband width by rotating the deadband stop screw on the FCU (Ref. Figure 202, Detail A). Rotate the screw clockwise to widen the deadband or counterclockwise to narrow the deadband. If it is impossible to position the deadband between the IDLE and GROUND FINE detents (because of cable play, for example), it is permissible to slightly widen the deadband. However, the deadband should not exceed more than approximately 0.25 inch of pedestal power lever travel forward of MARK 2

or

aft of MARK 1.

REVERSING CABLE

BETA VALVE

FUEL CONTROL UNIT

(FCU)

j

GOVERNOR AND REVERSING SYSTEM

CAM BOX

PT-6A-60A

Page

beF202

1/09

76-00-00

Engine and Major Controls Figure 201

n25

Hawker Beechcraft

Corporation

SUPER KING AIR 8300/8300(3 MAINTENANCE MANUAL

DEADBAND STOP SURFACE

DEADBAND

NOTE:

STOP SCREW MAXIMUM N

i

AFTER ALL FINAL RIGGING

(D

STOP SCREW

TORQUE TO VALUES SHOWN ADJUSTMENTS ARE MADE.

FCU ARM STOP TAB

POINT "A"

TORQUE TO 20-30 REAR CLEVIS

INCH-POUNDS HIGH HIGH IDLE

REVERSING CABLE

IDLE

STOP SCREW

ROLLER

O

O MAXIMUM REVERSE

O

STOP SCREW RIBBED TAB

SERRATED

O

O O

CONDITION

WASHER

O

CABLE TORQUE TO 20-30

DETAIL

B

O~Y

8.28

INCH POUNDS

RIG PIN HOLE

INCHES INTERCONNECT ROD CLAMP SCREW HORIZONTAL (REF)

B

DEADBI\ND TOROUE TO 12-18

STOP SCREW

INCH-POUNDS

TORCIUE TO 20-30 INCH POUNDS

HIGH IDLE ROLLER

MAXIMUM N

POWER

I-XnXa

STOP SCREW

INPUT LEVEL

CONTROL CABLE

HIGH

HIGH IDLE STOP SCREW

MAXIMUM REVERSE

~II-I

O

CAM BOX

CAM

FUEL CONTROL

TT

r

IDLESELECT

LEVEL

STOPSCREW

LOW IDLE

ADJUSTMENT SCREWS o

OVERCENTER LINK

,´•119

00

O0

FUEL CONTROL UNIT

(FCU) OET*I~

A

A

CLAMP SCREW

DETAIL

C

Fuel Control Unit and Cambox

Figure

A25

Rigging

202

760000

Page

203

~Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/6300C MAINTENANCE MANUAL

This

Page

beF402

1/09

76-00-00

Page Intentionally

Left Blank

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

PROPELLER CONTROL RIGGING REVERSING SYSTEM RIGGING a.

Make

sure

that the forward end of the

reversing

cable

just

covers

the check hole in the link terminal

(Ref. Figure 203, Detail B). b.

If

c.

Make

required, file sure

that the two washers

(Ref. Figure d.

Make

the

sure

the inside walls of the clevis to make

203, Detail

in

are

Set the torque

on

are

smooth.

spacers and the side walls of the clevis

adjusting

screw so

203, Detail B. At this

completely into the clevis. Make sure that the beta lever, when prior to reaching the terminal thread-end the clevis counterclockwise. not, adjust

that it

penetrates 0.55 inch into the clevis from the outside face

point,

the end of the

the forward

Nf link

(Ref. Figure 203, Detail A, Point A). Make

edge

of the solenoid bracket

binding. Tighten

support bracket

to

and

secure

so

screw

should be visible in the slot of the clevis.

that it is 2.5 inches from the center of the

sure

that the hardware

the bracket about the

prevent the solenoid from rotating about

attaching

the beta

reversing cable. Adjust the reversing cable.

the

screw

holding

Using light movement

h.

pressure, rock the solenoid slightly back and forth around the on the bearing (Ref. Figure 203, Detail D).

bearing

to the clevis is

bearing

in the solenoid

and check for freedom of

arm in its full forward position (the notch firmly against the torque adjusting screw), set the solenoid pull-in distance (the distance between the forward face of the solenoid and the aft face of the AN960 washer on the plunger) to 0.34 to 0.36 inch (Ref. Figure 203, Detail A). Adjust the pull-in distance by loosening the solenoid bracket screws and moving the solenoid within the bracket to obtain the proper position. Retighten the hardware secure.

CAUTION: Once the to

nzs

sure

With the beta

and

i.

the

arm

NOTE: It may be necessary to sand or file the spacers between the clevis and the saddle bracket to make that the clevis slides freely with no binding.

g.

in

the clevis slot-end

Adjust

free from

they

that the link terminal is threaded

retarded

(Ref. Figure f.

place between the

that

D).

position, stops fully (Ref. Figure 203, Detail B). If it does

e.

sure

Connect the

reversing cable is connected to both the cambox cam and place the power lever(s) in reverse without the engine(s) running.

rear

clevis of the

reversing

cable to the first hole from the

top of the

the beta arm, do not attempt

cambox

cam

(Ref. Figure 202).

76-00-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Page

76-00-00

Page Intentionally

Left Blank

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

WASHERS~

CLEVIS BOLT TO BE

I

LINK

LINK

CLEVIS

INSTALLED FINGER TIGHT

A~ ~SADDLE BRACKET

TO PREVENT BINDING

~-SPACEAS

TERMINAL

BETA ARM TORQUE ADJUSTING SCREW

REVERSINGCABLE ~_

~L----C

1

O I.INK

SOLENOID

CT\;

C

6CBa

‘´•1

TERMINAL

CLEVIS

.Ir.l\

SADDLE BR.4CKET

DETAIL

SOLENOID BRACKET

TO

B

BETA ARM

(POSITION IN SLOT TO SUPPORT SOLENOID AND PREVENT BINDING IN CLEVIS)

’X~

BRACKET

SOLENOID SUPPORT BRACKET

(j

NOTE

TORQUE TO VALUES SHOWN AFTER ALL FINAL RIGGING

ADJUSTMENTS ARE MADE

DETAIL

PROXIMITY SWITCH BRACKET

i

SOLENOID

SADDLE BRACKET

090 TO

110 INCH

CLEVIS 25

WASHER

C~V/

I

ATTACH TO

LINK

REVERSING CABLE LINK TERMINAL (SEE DETAIL A.

TORQUE ADJUSTING

INCHES

SCREW

JAM NUT ATTACH TO

BETA AAM

SOLENOID BRACKET

"B"

II I

IR=-=71

1

1111

IUlli

11

I 1

Y

I

ii

~i(l

I

I

44 TO

SWITCH

POINT ’A") TOROUE TO 12-18

INCH-POUNDS

GOVERNOR N I ARM (SEE DETAIL A. POINT’B’)

BETA RING NOTE

INCH-POUNDS

46

281NCH

,PROXIMITY

TORQUE TO 12-18

POINT

_;rj

T

POINT

AN960

PROXIMITY SWITCH

10 INCH

BETA RING

"A"

D

U/ UJ/

OIMENSIONS ARE TO THE STEEL

SURFACE OF THE BETA RING

II

INCH

NfLINK--*

DETAIL

PROP MOUNTING

C

DETAIL

F

FLANGE

BRACKET ATTACH BOLTS ADJUST

DETA(L A BETA VALVE

(ADJUST AS SHOWN IN FIGURE 4)

y

SWITCH

F

POSITION) ENGINE NOSE CASE

DETAIL

E

FV68985288M.M

Propeller Reversing Rigging Figure 203

A25

76-0000

Page

207

Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

~Page

beF802

1109

76-00-00

Page Intentionally

Left Blank

azs

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

WARNING:

Make certain that the forward

nut is between the two chamfered faces

of the beta valve

of the beta valve

as

shown in

edge of the conical cap Figure 204 and that none

the cap nut, Misadjustment of the beta valve leading to overtorquing of the engine and a

piston is visible outside unplanned feathering of the propeller, possible hazard to airplane operation.

can

result in

j.

Adjust the rear clevis of the reversing cable so that the forward edge of the conical cap housing is between the two chamfer faces of the beta valve (Ref. Figure 204).

k.

Remove the Nf link from the governor Nf

I.

Adjust

the Nf link to

rod end

provide a 0.090 (Ref. Figure 203, Detail C).

and the

arm

reversing

cable.

to 0.110 inch gap between the bottom of the Nf link and the

m.

Connect and

n.

Position the low pitch warning proximity switch so that it extends 0.28 inch aft (Ref. Figure 203, Details E and Fl. The sensing surface of the switch should the closest point (Ref. Figure 203, Detail Fl.

secure

the Nf link to the governor

NOTE: The dimensions

given

are

nut on the beta valve

arm

and to the

reversing

to the steel surface of the beta

cable

jam

nut on the

(Ref. Figure 203, Detail C).

of the

rear

surface of the beta

be 0.10 inch from the beta

ring ring at

ring.

WARNING

AFTER THE BETA VALVE IS ADJUSTED. MAKE CERTAIN THAT THE FORWARD EDGE OF THE CONICAL CAP NUT IS BETWEEN THE TWD CHAMFER FACES OF THE BETA VALVE AND THAT NONE OF THE BETA VALVE PISTON IS VISIBLE OUTSIDE THE CAP NUT. MISADJUSTMENT OF THE BETA VALVE CAN CAUSE UNPLANNED FEATHERING OF THE PROPELLER. RESULTING IN A POSSIBLE HAZARD TO AIRPLANE OPERATION AND OVERTDROUE DAMAGE TO THE ENGINE.

BETA

VALVE

CONICAL

CAP

FORWARD EDGE OF CAP NUT

NUT

CHAMFER FACE 2

--OJ)

1/)1

~II Ili)ii CHAMFER FACE

VALVE

o CHAMFER FACE

PISTON

EDGE OF CAP NUT

CHAMFER

-FACE

VALVE SHOWN IN FULL FORWARD (UNADJUSTED) POSITION FOR CLARITY BETA

ARM

2

VALVE SHOWN IN ADJUSTED POSITION NOT

SHOWN

FDR

CLARITY

SOD-2M-O~

Beta Valve

Adjustment Figure 204

GOVERNOR CONTROL RIGGING a.

Place the

b.

Adjust

the

propeller lever propeller

in the FEATHER

control cable rod end

position. so

that the feather

bottomed out when the cable is connected to the

ORIGINAL By

As Received

A25

ATP

speed

dump

control lever

valve on

the

plunger is fully compressed and propeller governor (Ref. Figure 205).

76I00I00

Page

209

Feb 1109

Hawker Beechcraft

Corporation

MANUAL SUPER KING AIR B300!B300C MAINTENANCE

PROPELLER GOVERNOR SPEED CONTROL FEATHER DUMP

SCREW,

FEATHER DUMP VALVE PLUNGER

NOTE: TORQUE TO VALUE SHOWN AFTER ALL FINAL RIQOING ADJUSTMENTS ARE MADE.

TORQUE TO 20-30 INCH-POUNDS PROPELLER GOVERNOR SPEED CONTROL LEVER

PROPELLER CABLE

MAXIMUM SPEED STOP

Propeller

beF012

Page

1109

76-00-00

Adjustment Figure 205

Governor

Screws

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONDITION CONTROL CA TCH GA TE REMOVAL a.

Set both the aileron and rudder trim tab allow the

adjusting

b.

Loosen the set

c.

Remove the

d.

Remove the indicator dials

(8).

e.

Loosen the set

remove

Remove the

f.

adjusting

knobs

knobs to be reinstalled in the proper in the side of the trim

screw

knobs

(7 and 10) and

remove

read O. This will

the knobs.

under each knob.

grip ring

screws

screws

adjusting

(7 and 10) so that the tab indicators (8) position (Ref. Figure 206).

and

attaching

the friction lock knobs

the electroluminescent

(3).

panel (2)

that is installed

over

the

POWER, PROP and

CONDITION levers. Position the electroluminescent panel (2) to gain

g.

access to

the

area

where the condition control catch

gate is

located.

Peel back the rubber

h.

cover

in the

(1)

area

of the condition control catch

gate. Two

screw

heads will become

visible. i.

Remove

screws

attaching

the escutcheon

(9). Lift

the escutcheon and disconnect the wires to the

electroluminescent panel (6). Remove the escutcheon. the

flap

switch

j.

Remove

screws

attaching

k.

Remove

screws

attaching the flap switch

i.

Gain

access

gate (5). The gate may be allowed cover

to the condition control catch

plate (4)

gate and

and

remove

remove

the

to

hang

from the

flap

switch lever.

plate.

the two screws, washers and nuts

attaching

the

catch to the pedestal. m.

Discard the old catch.

CONDITION CONTROL CA TCH GA TE INSTALLA nON lubricant (Item No. 6, Chart 2, 76-00-00) to the condition lever (Ref. Figure 206).

a.

Apply

b.

Install the

new

catch

gate with

areas

of the

new

catch

gate that will

the screws, washers and nuts. Locate the catch

gate

rub

against

the

at the low idle end of the

lever travel.

plate (4)

c.

Install the flap switch

d.

Install the flap switch gate (5) with

e.

Connect the wires to the electroluminescent

f.

Secure the rubber

g.

Install the electroluminescent panel

h.

Install the friction lock knobs

i.

Install the indicator dials (8)

a25

cover

cover

(1)

that

(3) so

with

screws.

screws.

was

that

and install the escutcheon

peeled back during

(2)

and

panel (6)

with

tighten

they

removal with adhesive

(9) with

screws.

(Item No. 7, Chart 2, 76-00-00).

screws.

the set

screws.

read O.

76-00-00

Page

beF1 2

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

j.

Install the

k.

Install the trim tab

grip rings. adjusting

knobs

(7

and

10)

and

tighten

the set

screws.

CONDITION CONTROL CATCH GATE INSPECTION The condition control catch

gates

are

designed

to

stop the aft travel of the condition levers

gates worn, the condition levers may not stop at their low idle to the fuel cut-off position. Inspect the catch gates for wear (Ref. Figure 207). If the catch

are

catches should be

replaced

as soon as

CAUTION: Use caution in the

possible.

operation

of the condition levers

idle catch gates until the catch gates

Page

212~b"el:db?

76-00-00

at their low-idle position. position and be inadvertently moved Any worn or non-functioning low-idle

are

on

any

airplane

with

worn or

non-functioning

low-

replaced.

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DN

FUEL FE*THER

1

tUTOFF

3

CIUIION

3

I

(I

151

LU/

sU~*r

Vj

i

_

Up O.

I

F

L

17’

e

10

8

II

Lll/o

4

/11

5

IILE~ON IFIY

/\l-je C~ VI~IY"\I/I

RLDDER1RIII

I\I

c~

v\

1.

RUBBER COVER

2.

ELECTROLUMINESCENT PANEL

i

7

3. FRICTION LOCK KNOBS 4.

FLAP SWITCH COVER PLATE

5.

FLAP SWITCH GATE

6. ELECTROLUMINESCENT PANEL RUDDER TRIM TAB ADJUSTING KNOB

7.

8. TRIM TAB INDICATOR DIALS ESCUTCHEON

9. 10.

AILERON TRIM TAB ADJUSTING KNOB

Condition Control Catch Gate Installation

Figure

206

ORIGINAL A25

As Received ATP

By~

76-00-00

Page

213

Feb 1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OUTBOARD

HIGH

IDLE

HIGH

HIGH

OUTBOARD

HIGH

IDLE

RPM

RPM

CI I OI I

1 I I

D Ii Ti

I

i 1 I

i~

II l~i 01 1~1 1\11 I

I LOW

I I

i

I I

I

I I /M1 j 1~111 1 I~iil I l~il i lydl I

IDLEI1’

i

I I I I I 1 I

C O

LEVERS"

SHOWN

n I

IN LOW IDLE

POSITION

T

7 O I~

I

FUEU /CWTOFF

"CONDITION

i I

~Y

LOW

’r\ IDL_E

FUEU /CUTOFF

WORN

"CATCH GATE"

CATCH

(TYPICAL)

GATE

NOTE: DIFFERENT STYLES MAY BE INSTALLED

HOWEVER THEIR

FUNCTION IS THE SAME.

PEDESTAL SHOWN WITH RUBBER SLOT SEAL REMOVED FOR CLARITY L*7SB 002457AA.AI

Condition Control Catch Gate

Figure

207

ORIGINAL

Page

214

Feb 1/09

76-00 00

As Received By ATP

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONDITION CONTROL RIGGING a.

Place the condition lever in the LOW IDLE

b.

Connect the condition control cable to the ribbed tab of the fuel condition lever

c.

Check the fuel flow and fuel cutoff system

position.

as

follows:

1.

Disconnect the

2.

Place

3.

Motor the

4.

Move the condition lever forward and confirm that fuel flows from the line.

5.

Move the condition lever to the FUEL CUTOFF

engine generator case).

lever is

fuel line at the fuel flow divider

engine by placing

at the six o’clock

pumped

approximately halfway

position

on

the gas

from the open line.

the start control switch in the STARTER ONLY

position.

position. Confirm that the fuel

flow

stops when the condition

between the LOW IDLE and the FUEL CUTOFF detents. If it does not,

the condition control cable rod end 6.

(located

suitable container under the fuel line to catch fuel

a

(Ref. Figure 202).

necessary to meet these

as

adjust

requirements.

Connect the fuel line at the fuel flow divider.

PROPELLER BETA ROD LENGTH ADJUSTMENT a.

Remove the

screws

securing

the

propeller spinner

dome and

caliper,

the distance from the

remove

the

spinner

dome from the

airplane

(Ref. Figure 208). b.

Using

a

standard six inch scale

elastic stop nut as

c.

nzs

necessary

on

all four

using

If the beta rods

are

(4)

or

measure

beta rods. The distance should be

the beta rod

the correct

stop

length,

a

piston

flat surface to the aft end of the

nominal 2.00 inches.

Adjust the beta rod(s)

nuts. no

further

adjustment is required.

76-00-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1 .970 INCHES

STOP NUT

BETA

ROD

PROPELLER VO PISTON

Propeller Beta Rods Figure 208 GROUND RUN RIGGING CHECK This check is to make are

sure

interdependent, adjusting ground run check

Perform the

CAUTION: Before the first

engine and propeller systems. Because require adjusting another and repeating all system may the following sequence:

the proper

rigging

of all

one

in

engine start,

make

sure

that the fuel cutoff

of the systems part of this check.

some or

is operating properly in accordance dump valve plunger on each propeller the feather position.

system

with CONDITION CONTROL RIGGING and that the feather

governor is a.

b.

Position the Install the

damage

airplane heading

when its

propeller lever is

in

into the wind.

engine inlet protective screens (Item No. 1, Chart 1, 76-00-00), if available, engines. If the screens are not available, deploy the ice vanes.

to

prevent foreign object

to the

CAUTION: Unless the c.

fully compressed

Start and

run

the

propellers

engines

are

feathered, maintain

until the oil

at least

1,050 propeller rpm at all times.

temperature is well into the operating range.

LOW IDLE CHECK a.

Place the power lever at the IDLE detent and the condition lever at the LOW IDLE detent.

b.

Confirm that 1.

N1 speed

is 62 to 64%. If it is not, set the low idle

Loosen the FCU lever

clamp

screw

speed

as

follows:

(Ref. Figure 202).

ORIGINAL

Page

216

Feb 1/09

76-00-00

As Received

ATP

By A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

2.

Two low idle

tighten

adjustment

the lower

the upper

screw an

provided.

screws are

screw an

equal

equal

To increase the idle

speed, loosen the upper screw and speed, loosen the lower screw and tighten screw changes N, speed by approximately

amount. To decrease the idle

amount. One-sixth of

a

turn of each

3.5%. NOTE:

3.

Adjusting the low idle speed may sufficiently to require resetting.

affect the maximum forward and maximum

reverse

N1 speed

Tightenthe FCUleverclampscrew.

DEADBAND CHECK a.

Move the power levers aft of MARK 2 toward MARK 1 propeller rpm (N2) increases between the marks.

(Ref. Figure 209). Confirm that N,

NOTE: Since the fuel flow (Wf) must increase before the gas generator speed and more accurate indicator for the deadband check. b.

Move the power levers aft of MARK 1. Confirm that Wf

c.

Move the power levers forward of MARK 2. Confirm that Wf

d.

If the as

engines

or

propellers

do not

respond properly

in

(fuel flow)

step

a,

or

N1

(fuel flow) b,

or

c,

(N1)

can

remains constant and

increase, Wf is

a

faster

increases. or

N1

adjust

increases.

the deadband

position and/or width

instructed in POWER CONTROL RIGGING.

REVERSE

RANGE

GROUND

FINE

DEIENT

PDWER

L~ .25 INCH (APPROXIMATE)

MARK

.25 INCH LAPPROXIMATE)

GROUND

FINE

LEVER

INCREASE

POWER

r-11~ MARK

i_

RANGE

FLIGHT

2

IDLE

OETENT

FWD 300-161-011

Power Lever

Positioning Figure 209

ORIGINAL sy

A25

As Recalvad ATP

76-0000

Page

217

Feb 1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

HIGH IDLE CHECK a.

Place the power levers at the IDLE detent and advance the fuel condition lever to the HI-IDLE N, increases to 70 to 72% rpm.

position. Confirm

that

b.

If the 1.

engine

does not

respond properly

step

a, set the

high

idle

as

follows:

are not mismatched, adjust the high idle roller position by loosening the lock nuts roller(Ref. Figure 202). Move the roller toward the high idle select cam to increase N1 speed the cam to decrease N1 speed.

If the fuel condition levers and or

the

moving

away from

CAUTION: Do not set the roller not

far out toward the

so

more

If the condition levers

high

idle select

cam

that the deadband reset the

deadband stop happens, rotation of the condition lever shaft, then readjust the surface. If this

riding against the

allow 2.

in

are

mismatched, make

sure

high

that the control cable rod ends

stop

idle stop idle roller.

are

high

installed

screw

is

screw to

properly, then N1 speed.

adjust high idle stop by turning the stop screw in to increase N, speed or out to decrease Each half-turn of the stop screw changes N1 speed by approximately 1.5%. the

MAXIMUM REVERSE CHECK a.

Move the power lever to the full

b.

Confirm that

stop

position.

adjust the maximum reverse N1 speed by turning the maximum reverse N1 speed and out to decrease N1 speed (Ref. Figure 202). Each half-turn of the stop changes N1 speed by approximately 2.7%.

screw

screw

reverse

is 84 to 86%. If not,

N1

in to increase

POWER LEVER MISMATCH CHECK a.

While

observing N1 speed

FINE detent into the b.

and all other limits,

reverse

move

the power levers to full forward and aft of the GROUND

range.

Confirm that the power lever handles are within 1/8 inch of each other when both engines are at the speed. If the power lever handles do not match within this limit, adjust the power levers as follows: NOTE:

1.

same

N1

inconsistent amount of power lever mismatch is present (for example, if the power levers are together at idle and maximum, but mismatched in between), one fuel control unit may be suspect and should be tested or replaced. If

Make

an

sure

that the power control cables have been

properly rigged

as

instructed in

POWER CONTROL RIGGING. In particular, check that the cambox rigging holes are properly aligned. Make sure that the interconnect rods are the same length, all rod ends are in the proper holes, and the cambox 2.

Make

sure

properly 3.

If all

input

levers

are

horizontal.

that the cables in the control

with its hole in the

rigging

pedestal,

pedestal are correctly rigged, that each bellcrank hole aligns they are identical left and right.

and that

is correct and the power levers

are

still mismatched,

inspect the FCU and the engine for faults.

engine to an old one, it may be necessary to alter the adjustment pedestal or to alter the adjustment of the cables in the control pedestal engine-to-engine rigging of the camboxes in order to match the power levers.

NOTE: When attempting to match

a new

of the cables in the control or

to alter the

Fuel flow rates and ITT will not match between

Page

2187~-00-00

engines

with

differing

amounts of

use.

a25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

GOVERNING RPM CHECK a.

Place the

then

propeller lever full forward,

the power lever forward. Confirm that the

propeller maintains

forward of the FEATHER detent. Confirm that the

propeller maintains

move

1,700 rpm. b.

Move the

1,400 c.

to

propeller

lever aft until it is

just

1,420 rpm.

If either the minimum

or

the maximum

propeller

rpm is out of tolerance, set the

propeller

rpm

as

follows:

To

adjust the maximum rpm, rotate the maximum rpm stop screw located to the right of the propeller governor speed control (Ref. Figure 205). Rotate the screw clockwise to decrease or counterclockwise to increase the maximum rpm. One turn of the stop screw changes the maximum speed by approximately 50

1.

rpm.

To

2.

adjust the

to increase

minimum rpm, adjust the position of the detent in the control aft to decrease the minimum rpm.

pedestal. Move the

detent forward

or

FEATHERING CHECK a.

Place the

propeller lever

full forward, then

move

the power lever forward until the

propeller

reaches

approximately 1,500 rpm. Slowly move the propeller lever aft past the FEATHER detent and observe the torque and N2 gages for indications that the propeller begins to feather smoothly at 1,350 to 1,400 rpm. b.

Allow the the

c.

propeller to decrease to approximately 1,000 rpm, propeller unfeathers smoothly.

then

move

the

propeller

lever forward. Confirm that

begin to feather within the rpm limits, adjust the feather dump valve stop screw located propeller governor speed control (Ref. Figure 205). Rotate the stop screw clockwise to decrease counterclockwise to increase the rpm at which the propeller begins to feather.

If the

does not

propeller

to the left of the or

TORQUE CHECK a.

Place the

b.

Advance the power lever forward to obtain altitude.

propeller lever

WARNING: After

adjusting

full forward.

exactly 1,500 propeller

rpm. Record the torque,

OAT, and pressure

the torque, make certain that the forward

edge of the conical cap nut is between (Ref. Figure 204) and that none of the beta valve piston is visible outside the cap nut. Misadjustment of the beta valve can result in unplanned feathering of the propeller, leading to overtorquing of the engine and a possible hazard to airplane operation. the two chamfer faces of the beta valve

c.

The torque recorded should be within 2.0% of the value for the recorded OAT and pressure altitude (Ref. Figure 210). The maximum allowable difference between left and right propeller torque is 1.0%. If the

torque is

out of

tolerance, adjust it with the torque adjusting

(Ref. Figure 203, Detail B). Rotate the One half-turn of the

n25

screw

changes

screw

screw on

clockwise to decrease

the torque

by approximately

or

the beta

arm

clevis

counterclockwise to increase the

1%.

76-00-00

torque.

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

6o

L

C~--J 1l

L

55

I

f

C

C

Ct

/--I--I i

-I

i-

t

C tl--l~

i

t- f

C

t

tl--Ji

-I -I

;bf

t-t+tt-;:r 50

[L

45

L1

I~h! I i~il

I

y

a

40

8 L

L?

-i

35

ri

Ti

31)

1

I

I

172VI I~

C

r r r

25

ET

20

-50

-40

-30

-20

-O

OUTSIDE

0 AIR

20

10

TEMPERATURE

30

40

50

(’Ci 3m-601-2n

c

Flight Idle Graph Figure 210

Page

220

Feb 1/09

76-00-00

ORIGINAL AB Received ATP

By

A25

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

SOLENOID RELEASE CHECK a.

Move the power levers to the IDLE detent.

b.

Advance the power lever forward from the IDLE detent until the solenoid releases. Make sure that the solenoid releases at 68 70% N,, indicated by a decrease in propeller rpm. If no rpm decrease occurs, adjust the ground idle solenoid

switches in the

dropout

1.

Loosen the

2.

Move

3.

Tighten

cams

the

pedestal

which contact the

cams

as

ground

follows:

idle solenoid

forward to increase solenoid release cams

which contact the

N,;

dropout switches (Ref. Figure 211,

Detail

aft to decrease solenoid release

move cams

C).

N1.

ground idle solenoid stop switches.

GROUND IDLE SOLENOID CHECK

CAUTION: Unless feathered, a.

Place the condition levers to stabilized

b.

ground

operate the propellers below 1,050 rpm.

never

high

idle and the

idle RPM of each

propeller control engine (Ref. Figure 203).

Hold the GRND IDLE STOP switch in the TEST

lights

position.

levers in the full forward

position.

Note the

The L PROP PITCH and R PROP PITCH annunciator

should be illuminated.

c.

Advance the power levers forward until each

d.

Release the GRD IDLE STOP switch. The L PROP PITCH and R PROP PITCH annunciator

engine

RPM reaches 1,500 RPM and stabilizes.

lights

should

extinguish. e.

f.

Make

sure

that each

engine

RPM decreases to 1,150 to 1,250 RPM and stabilizes.

Return the power levers to the ground idle position and make sure both engine RPMs return and stabilize to the step a. The L PROP PITCH and R PROP PITCH annunciators should illuminate. If the decrease in RPM

value in

is not within limits,

adjust

the solenoid

as

follows:

1.

Loosen the lower

2.

Move the solenoid aft to increase rpm

3.

Tighten the lower

4.

Repeat the solenoid check procedure

screws on

screws on

the solenoid bracket

drop;

(Ref. Figure 203).

move

the solenoid forward to decrease rpm

drop.

the solenoid bracket. to make sure of the correct

operation.

BETA VALVE ADJUSTMENT CHECK a.

Move the

b.

Advance the power lever until the propeller rpm reaches 1,700 rpm and stabilizes at a minimum (There must be sufficient torque to make sure that the governor is controlling the propeller.)

c.

Hold the GND IDLE STOP switch in the TEST

n25

propeller lever

to the full forward

position.

position

and make

sure

that there is

no

change

7~-00-00

in

torque of

propeller

90%.

rpm.

Page

beF12

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

edge of the conical cap nut is between (Ref. Figure 204) and that none of the beta valve piston is visible outside the cap nut. Misadjustment of the beta valve can result in unplanned feathering of the propeller, leading to overtorquing of the engine and a possible hazard to airplane operation.

WARNING: After

adjusting the torque,

make certain that the forward

the two chamfer faces of the beta valve

d.

If there is

observable

an

in

change

propeller rpm, the readjust the beta

REVERSING SYSTEM RIGGING to

beta valve is

misadjusted.

Return to

valve.

LOW PITCH WARNING CHECK a.

Move the power levers to the IDLE detent

b.

Advance the power levers forward from the IDLE detent.

c.

Confirm that the L and R PROP PITCH

simultaneously d.

If 1.

one or

when the power levers

both PROP PITCH

lights

securing

Loosen the bolts

lights

are

do not

the

(Ref. Figure 203).

on

caution/advisory annunciator panel extinguish beyond the solenoid release point (68 to 70% N,).

the

moved

extinguish properly, adjust the

proximity

switch bracket to the

affected

engine

proximity switch(es)

nose case

as

follows:

bracket

(Ref. Figure 203, Details E and Fl. 2.

Move the if it

proximity

extinguishes rigging.

switch bracket forward if the

too late. The

mounting

respective

PROP PITCH

light extinguishes

holes in the bracket may be slotted

as

too soon

or

aft

necessary to achieve proper

switch 3.

Tighten

securing

the bolts

the bracket to the

engine

nose case

bracket.

MAXIMUM POWER CHECK a.

Install the maximum

N1

shim tool

(Item

No. 2, Chart 1,

76-00-00) on the FCU arm stop tab so that (Ref. Figure 202, Detail B, Point A).

the left hand

side of the tool is flush with the left hand side of the stop tab

far forward

b.

Move the power lever

c.

Confirm that the maximum

as

as

possible with the shim tool installed.

N1 is 95%. If it is not, adjust the Nt speed with the maximum N1 stop screw located (Ref. Figure 202, Detail B). Rotate the stop screw clockwise to increase or stop counterclockwise to decrease the N, speed. One half-turn of the screw changes the N1 speed by approximately above the FCU

tab

arm

1.4%.

d.

Shut down the

rigging

tools

Return the

engines and

are

remove

the shim tool.

removed, all cables and rods

airplane

Inspect both engines to make sure that all test equipment and properly connected, and all fasteners are properly safetied.

are

to service.

GROUND IDLE STOP SWITCH ADJUSTIMENT

pedestal side panel.

a.

Remove the left hand

b.

With the power lever in the forward position, adjust the ground idle stop switch. on the bracket to be actuated to full overtravel position (approximately 0.06-inch beyond the actuating point) (Ref. Figure 211).

Page

2227~-00-00

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

c.

With the power levers in the IDLE detent, lift either power lever and check the travel of the lever arm after the switch de-actuates. The switch should de-actuate approximately 0.20-inch before the end of travel of the lever arm.

d.

Install the

pedestal

side

panel.

INSPECTION OF POWER LEVER DETENT PIN a.

Disconnect all electrical power.

b.

Remove the

pedestal overlay panel

and rubber closeout to

NOTE: Inspect the power lever detent

pins through

gain

access

to the power lever detent

the power lever travel slot in the

pins.

top of the pedestal.

a mirror and flashlight or alternatively a boroscope, inspect the upper power lever detent pin on each power lever for excessive wear where the pin rides in the groove in the idle/reverse stop assembly between the levers. Wear of one third or more of the diameter of the pin is considered excessive (Ref. Figure 211).

c.

Using

d.

If excessive

wear

of the

pin

is indicated, the power lever

assembly

must be

replaced

1.

Remove the

copilot’s

2.

Remove the

engine

3.

Remove the

edgelight panel

Remove the

upholstery panel from the right hand side of the pedestal and pedestal control levers. Retain all attaching parts.

4.

panel 5.

assembly.

control lever knobs, the and the

printed

engine

control friction brake knobs and the

circuit board from the

flap

control knob.

pedestal. Retain all attaching parts. remove

the small instrument

forward of the

Remove the four

Note the

screws

Retain the

pedestal. 6.

seat

follows:

as

quantity

that

secure

the

right

hand end of the control lever

pivot shaft

to the

right

side of the

screws.

of washers and spacers between the

engine control lever assemblies for reassembly

purposes. NOTE: A drop cloth should be used to keep items dropped from the 7.

Fabricate

8.

Insert the

a

dummy engine

pedestal

from

falling

control shaft 0.495-inch in diameter and at least nine inches

below the floor.

long.

dummy shaft into the control shaft opening in the left side of the pedestal, pushing the control lever pivot shaft to the right until the dummy shaft is ready to enter the right hand or left hand power lever which is to be removed.

NOTE: If both power levers

are

to be

replaced,

it is best to

remove

and

replace them individually, right hand

first, then left hand. 9.

Disconnect the

push rod from

the lower connection to the power lever to be removed. Retain the

attaching

parts. 10.

Catching control

the spacer washers that fall, pull the dummy shaft back to the left until the power lever, power and friction brake arm are released, then remove the assembly from the pedestal.

arm

1 1. Disassemble the power lever from the arm assembly by disconnecting the tension spring, removing the two nuts and washers and one cotter pin and washer from the three pins in the slotted holes.

n25

76-00-00

Page

beF32

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

new power lever to the MS24665-132 cotter pin.

12. Assemble the a new

arm

assembly

with the nuts and washers removed in

substep

11 and

complete power lever, power control arm and friction arm assembly in the pedestal and push pivot shaft through the power lever assembly (reinstall the spacer washers as noted in substep 6) until contact is made with the dummy shaft.

13. Position the

the control lever

14. Connect the

15.

push rod

Repeat substeps

9

to the lower end of the power lever with the

through

14

existing attaching parts.

the left hand power lever if both power levers

on

pivot shaft, installing the spacer washers noted pedestal.

16. Install the control lever is

pushed

out of the

17. Install the four screws which secure the

18. Install the left hand and e.

g.

hand

screw

secure

printed circuit board breakage.

just

and

edgelight panel

on

the

as

noted in

pedestal. Make

to avoid

h.

Install all

engine

i.

Check for proper operation of all switches and controls in the

control lever knobs, friction brake knobs and the

2247~-00-00

to the

dummy shaft

pedestal.

step

pivot shaft

c.

forward of the control levers.

properly

Page

pivot shaft

6 until the

it and the left hand end of the control lever

and washer. Position the control wheel

Install the small instrument panel Install the

hand end of the

substep

being replaced.

pedestal upholstery panels.

Install the manual elevator trim control wheel and with the attaching

f.

right

right

in

are

flap

pedestal

certain that all

lights

are

positioned

control knob. area.

n25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POWER LEVER LH---

DETENT PIN

----RH

´•P

POWER LEVERS

A

i

e

ASSEMBLYLEVER DETAIL

B

LINK

LEVER ARM

GROUND IDLE STOP SWITCH

SPRING

MT*IL

A

8 Cg

cnouNo IDLE

_

SOLENOID DROPOUT

PUSH ROD

PUSH

D BELL CRANK

CAM

AUTOFEATHER

SWITCHES

(REF.) DETAIL

DETAIL

C

D 35o-lsa-14

Ground Idle

A25

Switches

Stop Figure

Adjustment

211

76I00-00

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE CONTROLS REMOVAL a.

Disconnect electrical power from the

b.

Remove the

pilot’s and copilot’s

Remove the

screw

control lever

pivot shaft

c.

(POWER,

LEVERS)

airplane.

seats

and washer that

PROPELLER AND CONDITION

(Ref. Chapter 25-10-00). the elevator trim tab control wheel and the left end of the

secures

to the left side of the

pedestal. Note

the

position

engine

of the elevator trim tab control wheel

for installation. and condition lever

knobs, friction brake knobs, and flap control knob.

d.

Remove the power,

e.

Remove the edgelight panel and the printed circuit board from the pedestal. (Ref. Chapter 39-10-00).

f.

j.

screws

pedestal. Retain the

Note the

NOTE: A i.

upholstery panels from the left hand and right hand side of the pedestal panel forward of the pedestal control levers. Retain all attaching parts.

Remove the four the

h.

Retain all

Remove the

instrument g.

propeller

the right hand (Ref. Figure 212).

secure

end of the control lever

cloth should be used to

keep

items

dummy control lever pivot shaft

dropped

from the

pedestal

and

pivot shaft

of washers and spacers between the control lever assemblies for

quantity

drop

that

screws

from

attaching parts

remove

to the

right

reassembly

falling

the small

hand side of

purposes.

below the floor.

that is 0.495 inch in diameter and at least nine inches

long.

Fabricate

a

Insert the

dummy shaft into the control shaft opening in the left side of the pedestal, pushing the control lever right until the dummy shaft is ready to enter the left hand or right hand control lever which is to

pivot

shaft to the

be removed. NOTE: If

more

than

one

control lever is to be

replaced,

it is best to

remove

and

replace

them

individually, right

hand

first, then left hand. k. I.

Disconnect the

Catching the

push rod from the lower

spacers and washers that fall,

to be removed is released. Remove the

m.

end of the control lever to be removed. Retain the

Disassemble the

engine

nuts and washers and

pull the dummy shaft back assembly from the pedestal.

control lever from the

one

cotter

ENGINE CONTROLS INSTALLA TION a.

Assemble the in

b.

Steps

I. and

new

m.

engine

arm

pin and washer

to the left until the control lever

arm

assembly

assembly by disconnecting the tension spring, removing pins in the slotted holes.

the

from the three

(POWER, PROPELLER AND

control lever to the

attaching parts.

assembly

with the tension

under ENGINE CONTROLS REMOVAL. Install

a new

CONDITION

spring, nuts pin.

LEVERS)

and washers removed

cotter

complete control lever assembly and the arm and brake assembly in the pedestal and push the pivot shaft through the control lever assembly. Install the spacers and washers as noted in Step h., ENGINE CONTROLS REMOVAL, until the contact is made with the dummy shaft (Ref. Figure 212).

Position the

control lever under

push rod

to the lower end of the control lever with the

c.

Connect the

d.

Install the control lever

ENGINE CONTROLS

Page

pivot shaft. Install the spacers and washers REMOVAL, until the dummy shaft is pushed

22676-00-00

existing attaching parts. noted in

Step h. under pedestal.

out of the

a?s

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Install the four

e.

the

screws

which

f.

Install the left hand and

g.

Install the small instrument

h.

Install the

properly i.

secure

the

right

hand end of the control lever

pivot

shaft to the

right

hand side of

pedestal.

right

hand

pedestal upholstery panels.

panel just

printed circuit board breakage.

and

forward of the

edgelight panel

pedestal control levers (Ref. Chapter 39-10-00).

to the

pedestal.

Make certain that all

lights

are

positioned

to avoid

Install the manual elevator trim tab control wheel and

shaft with the

attaching

screw

secure

it and the left end of the

and washer. Position the elevator trim tab control wheel

engine as

control lever

noted in

Step

c.

pivot

under

ENGINE CONTROLS REMOVAL.

j.

_Install the

k.

Install the

I.

Check for proper

n25

power,

propeller

and condition lever

pilot’s and copilot’s operation

seats

knobs, friction brake knobs, and flap control knob.

(Ref. Chapter 25-10-00).

of all switches and controls in the

pedestal

area.

76-00-00

Page

beF72

1109

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CONDITION

LEVERS PROPELLER LEVERS

POWER LEVERS CONTROL LEVER PIVOT SHAFT

8~

DETENT PIN

FRICTION BRAKE ARM ASSEMBLY

‘O

POWER CONTROL

FRICTION BRAKE ARM

PUSH ROD

L

ARM

POWER CONTROL ARM

ASSEMBLY

PUSH ROD 300-lse-7

Engine Control Levers Figure 212

Page

beF82

1109

76-00-00

A25

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE CONTROL CABLE TEST AND REPAIR PROCEDURES The

engine

control cables used in this

airplane are pre-lubricated by the cable manufacturer and the ends are sealed ingress of moisture or contaminants into the cable housings. If problems are encountered operation or freezing of the cables, the following procedures should be followed:

to reduce the

possibility

with

stiff

binding,

of

EQUIPMENT REQUIRED FOR TESTING, PURGING AND REPAIR OF ENGINE CONTROL CABLES a.

A

regulated

b.

A

regulated dry nitrogen

c.

Airsource.

d.

Snap ring pliers.

vacuum source.

source.

LEAK TEST OF ENGINE CONTROL CABLES a.

Visually inspect

the cable assemblies for evidence of

bends and installation b.

Disconnect the power,

c.

Using

snap nacelle.

ring pliers,

damage, such

damage. propeller remove

and condition control cables from the

the snap

rings,

washers and

Connect each of the three control cables in each nacelle to

d.

to

apply

20

should be

in.-Hg.

no

vacuum

loss of

crimps, cuts, abrasions, unusually tight

as

o-rings from

a

regulated

to each cable. Shut off the valves to

vacuum

engine

trap

in each nacelle.

each of the three control cables in each

vacuum source

the

vacuum

and

adjust the regulator housings. There

in the cable

for two minutes.

NITROGEN PURGE OF CABLES a.

With the

rings

vacuum source

from each of the

(Item psig.

source

18

b.

Purge

still connected to the cables in

cables in the

corresponding 76-00-00)

No. 1, Chart 2,

the cables for

a

rings

in the

Remove the test

equipment,

crew

install

nacelle,

remove

new

the snap

rings, washers and Oa regulated nitrogen regulator output pressure to

compartment pedestal. Connect

new

pedestal

and

adjust

P/N 561-571-106

the

O-rings

in condition and

in power cables (P/Ns of Cablecraft, Tacoma, compartment ends of the cables and repeat the

O-rings

LEAK TEST OF ENGINE CONTROL CABLES in this c.

one

to the cables in the

minimum of 15 minutes. Install

control cables and P/N 561-571-104

the washers and snap

crew

propeller Washington). Install

chapter.

O-rings (per step b)

and install the washers and snap

rings

on

the

nacelle ends of the cables. d.

Repeat steps

a, b and c on the

opposite engine control cables.

INSPECTION AND REPAIR OF DAMAGED ENGINE CONTROL CABLES a.

Visually

examine the affected cable

assembly

to determine the extent of

discarded if it has been crushed, has the binder

or

strand wires cut

damage. The assembly shouldbe through, or has been contaminated (by

petroleum products, dirt, etc.).

n25

76-00-00

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

NOTE:

If there is reason to believe that

accumulated in the cable b.

If examination indicates that

a

substantial

assembly,

damage

quantity

of moisture

it should be baked

dry

(water

vapor

or

condensation)

has

at 125" Celsius for four hours.

is confined to the Teflon cover,

proceed

with the

following steps:

NOTE: The purpose of this repair is to seal the damaged area to reduce the possibility of entry of moisture or other contaminants into the cable housing, and to protect the assembly from further damage or wear from abrasion. 1.

Clean the

area, plus three inches on either side, using a clean cloth which has been dampened (Item No. 2, Chart 2, 76-00-00) or trichloroethane (Item No. 3, Chart 2, 76-00-00). Wipe clean dry cloth.

damaged

with 100% alcohol

dry 2.

with

a

Starting

at a

two inches from the

point

around the cable

housing

to

a

point

damaged

area, wrap Teflon

tape (Item No. 4, Chart 2, 76-00-00) damaged area. Wrap the tape so it

two inches on the other side of the

overlaps itself by one-half width. NOTE: Make 3.

In

areas

sure to

subject to

select Teflon tape with

abrasive

direction from the first tape

NOTE:

temperature range suitable for use

damage (e.g. clamp points), apply layer.

a

second

in the

area

layer of Teflon tape

being repaired. in

theopposite

protection is required, heat-shrinkable tubing (Item No. 5, Chart 2, 76-00-00) may be applied tape. The largest size possible should be used to achieve maximum shrinkage, and tubing should be cut to at least 0.25-inch longer than the taped area to be covered. To properly shrink the tubing, If additional

over

the Teflon

heat to above the heated

tubing

crystalline

(327" Fl with a forced air heat gun (Item No. 3, Chart 1,76-00-00). As the shrinkage, remove the heat source and allow the tubing to cool. The over the existing cable housing should be equal to, or greater than 0.010 inch.

melt

reaches 20 to 30%

thickness of the covered

Page

a

area

76-00-00

n25

CHAPTER

ENGINE

RBYtheOn

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER n

ENGINE INDICATING

TABLE OF CONTENTS

PAGE

SUBJECT 77-00-00

Engine Indicating- Descriptionand Operation SpecialToolsand Recommended Materials. Engine Indicating- Troubleshooting. Enginelndicating- Maintenance Practices. Engine Ground PerformanceChecks.

............1 .............1

.101 .............201

................201

General Information Power Check Power Check

........201

(without JETCAL). (with JETCAL)

.202 .205

Estimated Field Barometric PressureCalculation

Indicating System Test Equipment IndicatorSystemCheck ITT Indicating System Checks (FM-1

....209

209

N1 and N2

.209

thru FM-8; FL-1 thru FL-119 and

Airframe ITT Wi re-Harness-Resistance

(FM-1

Check and

FL-121)

thru FM-8; FL-1 thru FL-11Sand

Balance Resistor

FL-121) Adjustment (FM-I thru FM-8; FL-1

.....211

thru FL-119 and

FL-121)

.212

ITT

thru FL-119 and

ITT

FL-119 and

Check (FM-1 thru FM-8; FL-1 Thermocouple-lnsulation-Resistance Check (FM-I thru FM-8; FL-1 thru Thermocouple-Loop-Resistance ITT Indicator Check (FM-1 thru FM-8; FL-1 thru FL-119 and FL-121) ITT

...211

Adjustment

FL-121).

FL-121)

.213 .213 .213

......214 (FM-9 and After; FL-120, FL-122 and After). .214 and FL-122 and After; FL-120, After) (FM-9 Airframe ITT Wire Harness Continuity Check (FM-9 and After; FL-120, FL-122 and After).......... .216 ITT Thermocouple-Loop-Resistance Check (FM-9 and After; FL-120, FL-122 and After)............ 216 .217 ITT Thermocouple-lnsulation-Resistance Check (FM-9 and After; FL-120, FL-122 and After) FL-1 and Checks thru thru FL-119 ............,.217 FM-8; Torquemeter-lndicating (FM-1 System FL-121) .218 Torque Indicator Check (JETCAL) (FM-1 thru FM-8; FL-1 thru FL-119 and FL-121). IndicationandCalibration ...............218 Torque (Priorto FL-232; FM-10). .221 Torque Indication and Calibration (Meggitt) (FL-232 and After; FM-10 and After)

Indicating System

Checks

ITT Indicator Calibration Check

Torque Transmitter Removal Torque Transmitter Installation Fuel FlowSystem Check

net

....223 ...223 .......224

77-CONTENTS

.~:Pagel

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 77

ENGINE INDICATING

LIST OF EFFECTIVE PAGES OR-SE-SD

PAGE

DATE

77-LOEP

1

Oct 31/06

77-CONTENTS

1

Oct 31/06

77-00-00

1 thru 5

Oct 31/06

101

Oct 31/06

201 thru 226

Oct 31/06

A21

77-LOEP

Oct

31/06Page

1

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE INDICATING

DESCRIPTION AND OPERATION

engine indicating instruments consist of twelve instruments grouped in two vertical rows on the pilot’s side of panel. Each engine is monitored with six instruments which are briefly described by the following 1 and 2): (Ref. Figures

The

the main instrument

Interstage Turbine Temperature is generated by signals from the engine thermocouple over a range of 0-1,200"C. Airplanes FM-1 thru FM-8, FL-1 thru FL-119 and FL-121 utilize an 8-ohm balance resistor in the airframe thermocouple wire harness. ITT

Oil pressure from the torquemeter of the propeller reduction gearbox is converted to an electrical signal transmitter and displayed as a percent torque value. This value is representative of the torque applied to the propeller shaft. Torque indicators installed on FM-9 and after, FL-120 and FL-122 and after incorporate a digital

TORQUE

by the torque

display

to

the standard

complement

PROP RPM

Propeller

RPM

(N,)

analog pointer.

is read from

Instrument range is from 0 to 120%.

signals generated by the propeller tachometer generator.

Instrument

range is from 0-2,000 RPM.

(N1) signals generated by PERCENT RPM

FL-122 and after

A ratio of the actual

operating gas turbine shaft RPM (N1) as read from installed on FM-9 and after, FL-120 and Tachometers generator. to complement the standard analog pointer. Instrument range is from

versus

maximum

the turbine tachometer

incorporate

a

digital display

0-110%.

FUEL FLOW

Fuel flow in

pounds-per-hour (PPH)

is read from

signals generated by

the fuel flow transmitter.

Instrument range is from 0-750 PPH. OIL TEMP/PSI

Temperature

of the

engine

oil is

displayed according

to

signals generated by the oil temperature according to signals

bulb. Instrument range is from -20"0 to +1400C for oil temperature. Oil pressure is displayed received from the oil pressure transmitter. Instrument range is from 0-200 psi for oil pressure.

SPECIAL TOOLS AND RECOMMENDED MA TERIALS special tools and recommended materials listed in Charts 1 and 2 as meeting federal, military or supplier specifications are provided for reference only and are not specifically required by Raytheon Aircraft Company. Any product conforming to the specification listed may be used. The products included in these charts have been tested and approved for aviation usage by Raytheon Aircraft Company, by the supplier, or by compliance with the applicable specifications. Generic or locally manufactured products which conform to the requirements of the specification may be used even though not included in the charts. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

The

nz,

77-00-00

Raytheon

nilcraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

II 9

Ii

ITT’’CX

6(Bch~Tt 5

11

4

3

3

54

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o

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(brhnn *o~B/l

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71) so

PROP

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PROP

RPM

Oa~

15 too

xloo

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(Brhnh

10

n´• O;o 20~11

00

lt~4

20 30

RPM

RPM

40

00 sp

7

IP

FUELFLOW

-~JI

P~HX100

~FUEL FLOW

PPHX100

I

_w~12

~o

rr~P´•C\k

-20

200~

JIPSI

140

~I

P’.\Y/

200

BPSI

~GU,

C´•UFLTIBIII~ C

(FM-1

Engine Indicating Instruments thru FM-8; FL-1 thru FL-119 and Figure

Oct

31/06Page

2

77-00-00

FL-121)

1

A21

RBYtheon

Aircraft

Company

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

0~ I1PI

9

19

12

ITT

ITT 2

2 ’CX100

’CY100

i

7

1

7 b

5

5

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\YB 80 60

60

8‘

6

\20PROP

5/,\\

5

I/-~POPROP

9A V

Is

ia;ll

\\-Is \\c~7RRIX100

1615

1615

14

0~ ~less.ei \\BiBO

X RPM

BO

bO

a

7

O,

PPWX100

3

40

60

B

7

Z RPM

10

II=‘6FUEL

FUEL FLOY

a

O

O~\

I~CTURBIN

/j

\\-~,d

FLOW

O

PPHXIW

3

2

2

lil\~U 9

OIL Ido

O

~5

20

/’C

2001~

D

a

OIL

/1~160

200

O

O

-20

/’C

PS

C94FL77B0704

Engine Indicating Instruments (FM-9 thru FM-11; FL-120, FL-122 thru FL-382, except FL-381) Figure 2

A21

77-00-00

Oct

31/06Page

3

Raythwm

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 1

Special Tool Name 1.

JETCAL

Analyzer

Tools and

Equipment Use

Supplier

Part Number

Howell Instruments Inc., 3479 W. Vickery Blvd.,

BH112JD

Performance

Testing

Fort Worth, TX 76107 2.

Torque SystemCalibrator

101-000000/934

Aircraft Co.,

Raytheon

3.

Torque System

Pressure

Barfield Instrument

Model 2311

Torque

Perform

Indicator

Check

PO. Box 85, Wichita, KS 67201

Corp.,

Performance

Testing

4101 N.W 29th. St.,

Tester

Miami, FL 33142 4.

5.

CalibratorTThermometer

Ohmmeter

Omega

Must

CL23

measure

at

Omega Engineering,

Perform ITT Calibration

PO. Box 4047, Stamford, CT. 06907

Check

Obtain

Perform Resistance and

Locally

Continuity

least 5,000 ohms of resistance. 6.

ITTTestSet

Barfield 2312-G

Barfield Instrument

Corp.,

Checks

Perform ITT Calibration Check.

4101 N.W. 29th. St.,

Miami, FL 33142 7.

Fuel Flowmeter

10A455S with

Fischer and Porter, 125 E.

Perform Fuel Flow

Specific Gravity,

County

Line Rd., Warminster, PA 18974

Transmitter Check.

Fluke

Perform

0.808 1.1

Centistokes,

80 to 800 PPH

8.

Flukemeter

8060A

or

equivalent

Corporation

09090909

Blvd.

Seaway Everett, Washington,

6920

9.

Nitrogen SupplyCart

99-55500

Raytheon

Adapter Test

130-380042-1/935

11. Calibration

Adapter Nitrogen Supply Hoses

Oct

31/06Page

4

1 Raytheon

101-380091-2/939

77-00-00

i Raytheon

Aircraft Co.,

Aircraft Co.,

Aircraft Co.,

P.O. Box 85, Wichita, KS 67201

a

digital

98206-

PO. Box 85, Wichita, KS 67201

Box

checks that

display.

PO. Box 85, Wichita, KS 67201 10. Calibration

voltage

require accuracy of

P.O. Box

Torque Indicator Calibrating.

Perform

Testing

and

Perform

Testing

Torque Indicator

and

Perform

Testing

Calibrating.

Torque Indicator Calibrating.

and

aal

Raldheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 2

Recommended Materials Material 1.

RedVarnish

Specification

Product

Glyptol

1201

Supplier General Electric Co., Insulating Materials Dept.,

Campbell Rd., Schenectady, NY.

A21

12306

77-00-00

Oct

31/06Page

5

Raytheon

Aircraft

Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

ENGINE INDICATING- TROUBLESHOOTING

engine indicating systems may need to be performed would be that the performance parameters of the PT6A-60A Ground Performance Check Graphs MAINTENANCE PRACTICES, Figure 201) or that engine performance parameters I

The first indication that checks

on

the

failed to meet the

airplane engine (Ref. ENGINE INDICATING have changed.

engine ground performance check graphs are presented as constant torque versus ambient temperature so that engine performance can be checked over a wide range of ambient temperatures without overtorquing the reduction gearbox. Periodic engine performance checks must be carried out and changes in engine performance noted. All forms of engine deterioration will be accompanied by an increase in interstage turbine temperature and fuel flow at a given power. Compressor deterioration will, in some cases, be due to dirt deposits and will cause an increase in gas generator speed to obtain a given power setting. This form of deterioration can be remedied by compressor washing as described in the engine maintenance manual. Hot-section deterioration will cause a decrease in the gas generator speed required for a given power setting.

The

Usually, when only one engine performance parameter is suspect, it can be assumed that the problem is with the indicating system. Normally, when the fault is in the engine, at least two of the performance parameters will be outside of the expected limits. In either case, the engine should never be automatically condemned without a thorough investigation of the appropriate engine indicating systems. When propeller pitch at low idle is out of adjustment, the ITT reading will be too high. Refer to the engine rigging procedures in 76-00-00 for specific rigging instructions on the engine controls.

n21

77-00-00Page

101

RB~heOn

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE INDICATING

MAINTENANCE PRACTICES

Checks

performed on the engine indicating systems include interstage speed (N1), torque, fuel flow and propeller speed (N2)´• The

in this

procedures

chapter

Some modifications of these

supplemental supplied with the

are

P/N 3032842, and to the instructions

turbine temperature

the instructions in the

to

test

equipment being

Engine

(ITT), gas generator

Maintenance

Manual,

used.

procedures may be necessary if test equipment not specified in this chapter is used. voltages are standard values and will remain unaffected, regardless of the type of

All pressures, resistances and equipment being used.

Factors affecting the accuracy of the equipment, such as calibration, frequency of certification or misuse, must be taken into consideration before any equipment may be used to check or calibrate the engine indicating systems.

ENGINE GROUND PERFORMANCE CHECKS NOTE:

Engine ground performance check data may be used by maintenance personnel to evaluate the effects of component replacement, inaccuracies in the engine instruments or progressive hot section deterioration, but such data should never be used as the sole criterion for determining the airworthiness of an engine. Refer to the MINIMUM TAKEOFF POWER chart and procedures in the appropriate Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual to determine if the engines are producing sufficient power for airworthy operation.

GENERAL INFORMATION The

engine ground performance checks are presented as torque versus ambienttemperature and engine parameters can be checked over a wide range of conditions without overtorquing the gearbox. Periodic engine checks must be carried out and changes in engine parameters noted.

graphs

pressure reduction

so

for

that

engine deterioration will be accompanied by an increase in interstage turbine temperature and fuel flow given power. Compressor deterioration will, in most cases, be due to dirt deposits and will effect an increase in gas generator speed to obtain a given power setting. This form of deterioration can be remedied by compressor washing as described in Chapter 12-20-00 of this maintenance manual. Hot-section deterioration will cause a decrease in the gas generator speed, an increase in fuel flow and an increase in ITT for a given power setting.

All forms of at a

a.

All systems that

b.

The generator for the

c.

Let the power

d.

Always

e.

look

use

runs

bleed air from the

engine being

engine being tested

tested should be tumed off.

must be off

during

stabilize for at least two minutes before

directly

into the instrument

Recheck the instruments

being

the

reading

read to eliminate

constantly during engine power by the instruments.

ground

test.

the instruments.

parallax

error.

checks. Hold all power

settings

as

close

as

possible

to the desired values as indicated

f.

Use extreme

care

in

calculating

air inlet temperature. Air inlet temperature is obtained by adding 4"C to the discrepancy in the recorded air inlet temperature results in a large ITT

outside air temperature (OAT). A small error when correlated with chart data. g.

nn

The

following

charts and information

1.

Power Check Data Worksheet

(without JETCAL) (Chart 201).

2.

Power Check Data Worksheet

(with JETCAL) (Chart 202).

are

required

to

perform

the

engine

power check:

I 77-00-00Page

201

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

h.

3.

PT6A-60A Ground Performance Check

4.

Temperature

Conversion Chart

Perform the

engine performance JETCAL) procedures.

Graphs (Ref. Figure 201).

(Ref. Figure 202).

check

as

outlined

the

by

respective

POWER CHECK

performing the following checks, the engine cowling must be engine check parameters. F.O.D. screens must not be installed.

NOTE: Prior to

of

POWER CHECK

in

place

(WITH

in orderto

or

WITHOUT

ensure

consistency

(WITHOUT JETCAL)

a.

Record the outside air temperature temperature in Chart 201.

b.

Determine barometric pressure by setting the altimeter at zero and noting the field barometric pressure indicated in the Kollsman window. Average the readings of the pilot’s and copilot’s altimeters when they differ. The

I

(OAT)

in

degrees

Celsius. Add 4"C to this

reading

and record

as

air inlet

preferred procedure is to set the altimeter to zero and read the pressure from the Kollsman window or to contact Flight Service for an uncorrected pressure reading. Do not use the sea level pressure normally reported Refer to ESTIMATED FIELD BAROMETRIC PRESSURE CALCULATION procedure only if the the tower. by

the local

Kollsman window is off scale. c.

I~ e.

Using the barometric pressure reading obtained in the preceding step, determine the target torque value, fuel flow, ITT and N1 speed from the PT6A-60A Ground Performance Check Graphs (Ref. Figure 201). Start the

engines as outlined by procedures Airplane Flight Manual.

f.

airplane velocity.

Position the wind

crosswind

(90"

in the

to the wind

appropriate

direction)

Power-up the airplane. (Turn on an inverter for airplanes ac engine instruments).

Pilot’s

Operating

Handbook and FAA

to eliminate variation in

parameters due

to

Approved

changing

FM-1 thru FM-8, FL-1 thru FL-1 19 and FL-121 to power

the

g.

Ensure that the

air-conditioning,

h.

Position the ice

vanes

i.

Verify

that the

j.

Bring

the power levers foMlard to establish

step

I

in the retracted

propeller levers

are

that the

engine propeller

Verify

I.

Record the fuel flow,

m.

Shut down the

all off

on

the

engine being

checked.

position (OFF).

in the

high a

rpm mode.

torque indication equal

N1

is

governing

at

approximately

to the

target torque value determined in

engines as outlined by procedures Approved Airplane Flight Manual.

Compare ground

1700 RPM. DO NOT exceed limitations.

and ITT indications in Chart 201. in the

appropriate

Pilot’s

the actual values recorded in Chart 201 with the target values

The actual values recorded should also be used

Oct

are

c.

k.

n.

bleed air and generator

test

runs.

31/0677-00-00

as a

Operating

Handbook and FAA

plotted from the graphs in Figure 201. performance history to compare with the results of futu re

galfthaoa

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Graphs (Ref. Figure 201) are based on a typical new installation. Minor engines and installations may produce results that are slightly different from the reference values represented by the graphs; therefore, should the engine meet the minimum takeoff power criteria as stated in the appropriate Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual, large variations of fuel flow and ITT from the graph reference values may be indicative of faults within the engine’s indicating systems. Should an engine parameter begin to drift progressively up or down during subsequent checks, a trend toward engine deterioration may be assumed. A minimum takeoff power check should be performed before the engine is declared nonairworthy. The real value of the graphs in Figure 201 is in giving the technician an approximation of where the engine parameters should be for a typical new installation.

The PT6A-60A Ground Performance Check differences between

Detailed record

keeping

of

engine performance parameters

is

all-important

performance.

For that purpose, a good system of engine-condition-trend maintenance personnel so that preventive maintenance measures may be

development of

more

detecting early trends of change in monitoring should be employed by accomplished well in advance of the

in

serious conditions.

Chart 201 Power Check Data Worksheet

FIELD BAROMETRIC PRESSURE:

(without JETCAL)

AIR INLET TEMP

(OAT

4"C)

TORQUE FROM FIGURE 201:

INDICATED LH

RH

PROPELLER SPEED:

INDICATED LH

RH

FUEL FLOW FROM FIGURE 201:

INDICATED LH

RH

ENGINE

INDICATED LH

RH

INDICATED LH

RH

(TARGET 1,700 RPM)

N1

FROM FIGURE 201:

ITT FROM FIGURE 201:

ENGINE SHUTDOWN COMMENTS:

LH

RH

nn,

77-00-00

Oct

31/06Page

203

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FIELD BAROMETRIC PRESSURE

B m

(IN Hg)

7

’1

700

FIELDI 29.92

800 LUD

29

~4SW I

I

1

I

I

I

I

I

I

1

Y~-26

%~i´•´• 102

NG

I~ tooss ~8 %[n 0

96

92 820

800 780 760

NOTES: STATIC INSTALLED 1700 RPM PROP RPM

740 720

700

X

INSTALLATION ASSUMES

8801

I

I

I

I

I

640

v

/L

I

I

I

I

I

I

1

I

I

I

I

I

I

I

1

0

10

20

30

40

50

4

SHPEX

2 Ib/min

Pg

BLEED

620

B

800

-40

-30

-20

-10

ENGINE A)R INLET TEMPERATURE

(’C)

3810.259.2

PT6A-60A Ground Performance Check Graphs

Figure

Page

tcO402

31/06

77-00-00

201

A21

Ral~heon

Aircraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

POWER CHECK

(WITH JETCAL)

manual may be used to set up engine power as a reference for inflight checks. The PT6A-60A Ground Performance Check Graphs (Ref. Figure 201) should be used as a reference when

Performance

performing

graphs

static

in the

ground

appropriate flight

checks.

following procedure provides the basic instructions needed to set up the airplane for test and compare the airplane’s engine instrument readings with those of the JETCAL Analyzer (1, Chart 1, 77-00-00). All supplemental information on adapter cable connection and operation of the JETCAL Analyzer should be obtained from the manufacturer’s operating instructions.

The

Ensure that all switches

b.

Start the

engines with procedures Airplane Flight Manual.

c.

Power-up the airplane. (Turn engine instruments.)

d.

Determine the barometric pressure by setting the altimeters at zero and noting the field barometric pressure indicated in the Kollsman window. Average the readings of the pilot’s and copilot’s altimeters when they differ.

on

the JETCAL

off.

a.

are

outlined in the

on an

appropriate

Pilot’s

Operating

Handbook and FAA

Approved

inverter for FM-1 thru FM-8, FL-1 thru FL-119 and FL-121 power to the

ac

preferred procedure is to set the altimeter to zero and read the pressure from the Kollsman window or to Flight Service for an uncorrected pressure reading. Do not use the sea level pressure normally reported by the tower. Refer to ESTIMATED FIELD BAROMETRIC PRESSURE CALCULATION procedure only if the Kollsman window is off scale.

The

contact the local

e.

Using the barometric pressure reading obtained graph in Figure 201.

in the

preceding step,

determine the target torque value from

1

the f.

Set the JETCAL

Analyzer

propeller speed (N2)

to

set at 77.3

1,700 rpm

on

percent in accordance with the operating manual instructions. Adjust the

engine

to be tested.

NOTE: The 77.3 percent setting on the JETCAL Analyzer correlates to 1,700 rpm and for each engine in case the engine instruments are not in agreement. g.

Approximate

air inlet temperature

by adding 4"C

to outside air

provides

a common

temperature. Record this value

on

setting

the Power

Check Data Worksheet in Chart 202. h.

After as

i.

operating the engine for at least two on the engine instruments.

1 minutes to stabilize all

engine parameters,

record fuel flow and torque

indicated

Record the gas generator speed (N1), propeller speed (N2) and ITT as read from the airplane engine instruments.

on

the Power Check Data Worksheet in

Chart 202

j.

before k.

N1, N2 and ITT on the recording a final value.

Record

After all

data sheet

as

required readings have been taken,

read from the JETCAL

reduce

engine

displays.

Ensure that ITT has stabilized

power to idle and repeat steps h thru

j

for the

opposite engine.

na

77-00-00

205

I

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 202 Power Check Data Worksheet

(with JETCAL)

AIRCRAFT SERIAL NO.

DATE

RUN BY

INSPECTOR LEFT ENGINE

ENGINE SERIAL NO.

"C

O.A.T. IN.

FIELD BAROMETRIC PRESSURE Run Data

Chart Data

Hg

Inst. Corr.

INLET AIR TEMP

"C

(T1)

Corr.

Devia-

Reading

tion

Tolerance

Remarks

TORQUE

TORQUE

"C

PANEL

"C

I.T.T.

J.C.

"C

FUEL LB./HR.

FLOW

I

LB./HR. PANEL

N1

J.C. PANEL

1,700 RPM

N2

1

RPM

IJ.C.

(77.3%)

RIGHT ENGINE "C

O.A.T.

ENGINE SERIAL NO. FIELD BAROMETRIC PRESSURE

IN.

Inst.

Run Data

Chart Data

Hg

Corr.

INLET AIR TEMP

(T1)

Corr.

Devia-

Reading

tion

Tolerance

"C

Remarks

TORQUE

TORQUE

PANEL

"C

I.T.T.

J.C.

"C

"C

FUEL FLOW

LB./HR.

LB./HR.

I PANEL

N1

N8

Oct

J.C.

1,700 RPM

PANEL

(77.356)

J.C.

77-00-00

RPM

A21

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i2o 115 I io

105

ioo 95 90 85 80

75 73 65 w

E

60

55 LL

cn

50 45 40

Z5

35 30 25

20 15 10

0

-15-10-5

0

c5

10

DEGREES

15

20

25

30

35

40

45

50

CELSIUS C94887781288

Temperature Conversion Chart

Figure

A21

202

77-00-00

Oct

31/06Page

207

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I

Using the recorded air inlet temperature plotted against the graphs in Figure 201, determine the target torque, fuel flow rate, ITT and N1 speed for the test conditions of each engine. Record each of these values on the Power Check Data Worksheet in Chart 202.

i.

that the indicated fuel flow rate is at

below

graph

value.

1.

Verify

2.

Verify that the JETCAL ITT reading does not exceed the maximum value designated by the graphs in Figure 201 when adjusted for the recorded air inlet temperature. If the reading is more than 75"C below the temperature designated by the graph, perform a check of the airplane’s ITT indicating system.

3.

Verify that the N, and N2 readings recorded from the airplane indicators when compared to the JETCAL readings throughout their entire range.

I

a)

Airplanes

or

FM-1 thru FM-8, FL-1 thru FL-119 and FL-121 have the

N1

in Percent

Nz

40 to 110:

b)

Airplanes FM-9

airplane’s

If the

N,

in Percent

The

graphs

in

Figure201

are

outlined in this

based

on

a

tolerances:

readings chapter.

typical

new

following

tolerances:

in RPM

0 to 1,700:

indicators do not match the JETCAL as

tolerances

1400 to 1,700: f 5

0.8

0 to 110: f 1.2

suspect airplane indicating system

following

following

100

and After, FL-120, FL-122 and After have the

N,

within the

in RPM

500 to 1,000:

0 to 30: f 1

are

20.2

within the established limits,

perform

installation. Minor differences between

a

test of the

engines

and

installations may produce results that are slightly different from the reference values represented by the graphs; therefore, should the engine meet the minimum takeoff power criteria as stated in the appropriate Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual, large variations of fuel flow and ITT from the graph reference values may be indicative of faults within the engine’s indicating systems. Should an engine parameter begin to drift progressively up or down during subsequent checks, a trend toward engine deterioration may be assumed. A minimum takeoff power check should be performed before the engine is declared nonairworthy. The real value of

graphs in Figure 201 is typical new installation.

the a

Detailed record

keeping

of

in

giving

the technician

an

approximation

engine performance parameters

is

of where the

all-important

performance. For that purpose, a good system of engine-condition-trend maintenance personnel so that preventive maintenance measures may be development of

Oct

31/06Page

208

more

engine parameters

should be for

detecting early trends of change in monitoring should be employed by accomplished well in advance of the

in

serious conditions.

77-00-00

n2e

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ESTIMATED FIELD BAROMETRIC PRESSURE CALCULATION NOTE: This is

alternate method of

an

field barometric pressure and should be used

obtaining

only

in instances

where the Kollsman window is off scale. a.

Set the altimeter to field elevation. Record the elevation and the barometric pressure from the Kollsman window. 1.

b.

Use 1.0 inch 1.

c.

1820 ft. MSL at 29.84 inches

Hg

1820 ft. MSU1000

Example:

Hg

29.84 inches

Example:

Hg

per 1,000 ft. MSL of altitude to determine the estimated field barometric pressure.

Subtract the 1.82 inches 1.

d.

Example:

1.82 inches

Hg

from the barometric pressure recorded in

Hg

1.82 inches

Hg

a.

28.02 inches Estimated Field Barometric Pressure

proper charts. Ref er to POWER CH ECK

Apply 28.02 inches Hg to the as applicable.

Step

(WITH

or

WITHOUT J ETCAL)

procedu re

INDICATING SYSTEM TEST EQUIPMENT and equipment are available for the purpose of checking and calibrating the engine indicating The listed in Chart 1, 77-00-00 and referenced in the following steps are recommended for checking tools systems. engine performance, although any equipment that meets the specified accuracy requirements may be used.

Various

analyzers

Figure 203 provides during the test. Test

an

engine

instruments outside the instrument

panel

Equipment Accuracy Requirements:

N1

RPM within

NP

RPM within f 0.1%

ITT within

N1

illustration of the bracket used to mount the

AND

0.1%

5.0"C

N2

INDICATOR SYSTEM CHECK

Gas generator

speed (N2)

speed (N1)

is indicated

as a

percentage of the maximum allowable gas generator rpm. Propeller

is indicated in rpm.

Analyzer (1, Chart 1, 77-00-00) is capable of measuring rotating speeds within f 0.1%; therefore, it being used as a calibrating standard. It can also be programmed to read percent rpm or straight The tachometer generators are connected to the test set and drive the test set and airplane indicator in parallel. rpm. The connecting cables provided with the JETCAL allow the user to splice into the system in the cockpit or on the engine at the tachometer generators.

The JETCAL

lends itself well to

The

N1

and

N2

indicators have

indicator and JETCAL indicator

no adjustment and must be replaced if out of tolerance. Should the airplane RPM readings disagree, replace the indicator first, then replace the tachometer generator

if necessary. a.

Place the JETCAL

perform

n21

Analyzer

in

a

convenient location in the

the rpm indicator system check

as

outlined

by

airplane

the JETCAL

and connect the necessary cables to operator’s manual instructions.

77-00-00

I

Raytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

2.0

ROLL THIS END TO APPROX 2 1/8 DIA. 1 .5

ROLL CENTER TO 7/8 DIA.

5.5 ROLL THIS END TO APPROX 7/8 DIA.

2.0

1/4 RAD

TYP.

I .87

2.33

2.62

5.82

FABRICATE FROM ALUMINUM SHEET OR TUBING. THIS DRAWING MAY BE USED AS A TEMPLATE.

C94FLTIB1278 t

Engine

Page

tcO012

31106

77-00-00

Testing Support Figure 203

Instrument

Bracket

A21

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

b.

Use the test set

operator’s

manual to program the test set to read percent

or

rpm

as

required

to check the

indicator. c.

Start the

d.

Compare the Nt

applicable engine according Airplane Flight Manual. or

N2 reading

on

to the

appropriate Pilot’s Operating Handbook and

the indicator with the

reading

on

the JETCAL

FAA

Approved

Analyzer through

I

the full

deflection of the indicator.

The tolerances for

through

N1

0

Nz

500

through 1,000

N1-0 through 0

and

Np

30%: +1%, 40

The tolerances for

N2

N1

through

airplanes

N2

indicators for

are as

follows:

RPM:

are as

follows:

25 RPM.

FM-9 and After, FL-120 and FL-122 and After

110%: f1.2%.

through 1,700

ITT

following

through 1,700

airplanes

RPM: f 20.2 RPM

17T INDICATING SYSTEM CHECKS The

FM-1 thru FM-8, FL-1 thru FL-119 and FL-121

110%: f 0.8%.

RPM: f 100 RPM, 1,400

and

N1

indicators for

(FM-1

THRU FM-8; FL-I THRU FL- 119 AND

system checks should be made anytime indicating system.

a new

indicator

or

thermocouple

FL-121)

is installed

or

when

a

fault is suspected in the

performing any of the following electrical checks, Chapter 71-10-00 to remove the engine cowling. When all Prior to

the indicator if all other

areas

of the system

were

all electrical power from the airplane and refer to checks of the ITT indicating system are complete, replace remove

within tolerance,

or

replace other components

as

necessary.

The ITT system checks may be performed with a JETCAL Analyzer (1, Chart 1, 77-00-00), Barfield ITT Test Set (6, Chart 1, 77-00-00) or an ohmmeter (5, Chart 1, 77-00-00). Connect the desired test equipment to the indicating circuit in accordance with instructions

instructions

test unit

checks.

along

with the

NOTE: When

supplied with each test unit. Use the operating following procedures to accomplish the ITT indicating system

installing

the nuts for the

thermocouple leads,

refer to the

applicable

Pratt and

provided

with the

Whitney Engine

Maintenance Manual for the correct torque value for the chromel and alumel nuts. When

testing is complete, connect all wiring that was disconnected for airplane and install the engine cowling as outlined in Chapter 71-10-00. AIRFRAME iTT WIRE-HARNESS-RESISTANCE

FL-119 AND

the test, restore electrical power to the

CHECK AND ADJUSTMENT

(FM-1

THRU FM-8; FL-1 THRU

FL-121)

perform these checks until the internal engine components have cooled to ambient temperature. The engine components and thermocouple will require at least ten hours of cool-down time to reach ambient temperature.

NOTE: Do not

internal

a.

b.

Remove the ITT indicator from instru ment

panel and disconnect the ai rplane wire harness leads at the indicator.

(6, Chart 1, 77-00-00) to check resistance of the airframe wire harness. The Barfield to read resistance of an 8-ohm ITT indicating system and should be operated in the operator’s manual instructions.

Use the Barfield ITT test set test set is

specifically designed

accordance with

77-00-00

I

Raytheon

AiKraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

1.

Resistance of the airframe wire harness shall be within 8 each wire harness lead to locate

2.

If wire hamess resistance is

procedures

to

bring

short

a

only slightly

or

wiring

out of

0.05 ohms. If not,

a

continuity

check of

tolerance, perform BALANCE RESISTOR ADJUSTMENT

resistance within tolerance.

BALANCE RESISTOR ADJUSTMENT(FM-1 THRU FM-8; FL-1 THRU FL-119 AND a.

perform

break.

FL-121)

Remove the center aisle carpet and floorboard just aft of the forward cabin partition to Figure 204 for an illustration of the balance resistor.

gain

access

to the ITT

balance resistors. Refer to

NOTE: The balance resistors

b.

Adjust 1.

To

are

located

the balance resistor until

adjust

a

on

support brackets suspended from the left and right

resistance of 8 It 0.05 ohms is obtained for the wire harness

harness resistance, disconnect the

terminal and reconnect it

so

seat track risers.

thermocouple-lead-spool (to reduce resistance)

that there is less

wire

on

or more

as

follows:

the balance resistor from the

(to

increase

resistance) spool

wire in the circuit with the harness. 2.

Remove the insulated

incorporates

a

second

NOTE: Do not cut off the

coating at the point where the new solder connection is made. The thermocouple-lead spool for additional resistance if required.

excess

wire. The best

procedure

is to insulate the

excess

the proper resistance has been obtained. This will facilitate later resistance necessitating replacement of the balance resistor.

(FM-1

Balance Resistor thru FM-8; FL-1 thru FL-119 and

Figure

Oct

31/06Page

212

77-00-00

204

FL-121)

balance resistor

wire with tape and stow it after adjustments without

Ra~heon AiKraft Company SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ITT THERMOCOUPLE-INSU LATION-RESISTANCE CHECK

(FM-1

THRU FM-8; FL-1 THRU FL-1 19 AND

FL-1 21) If the

thermocouple-loop

acceptable limits, perform

resistance is out of

the

following

check to determine harness

insulation resistance: NOTE: A conventional ohmmeter

Analyzer Follow the

a.

or

applicable

ohmmeter. If

an

(5,

Chart i,

77-00-00)

may be used to

perform

this check instead of the JETCAL

manual to

perform

this check without

Barfield ITT Test Set. instructions in the test set

ohmmeter is

being used,

operator’s

turn it on,

zero

a

conventional

the meter and select the proper scale before

making

is not within tolerance,

suspect

the resistance check. The ohmmeter should indicate 5,000 ohms or more. If either resistance a break in the insulation that is causing a short.

b.

CHECK(FM-1

ITT THERMOCOUPLE-LOOP-RESISTANCE Disconnect the trim

a.

generator With the

b.

thermocouple

THRU

reading

FM-8; FL-1 THRU FL-119 AND FL-121)

leads and the airframe wire harness from the

T, terminal

block

on

the gas

case.

(6, Chart 1, 77-00-00) or ohmmeter (5, Chart 1, 77-00-00) test polarity of the connections (alumel to negative and chromel to

harness intact, connect the test set

Tg

leads to the terminal block.

Carefully

observe

positive). Measure

c.

loop

resistance of the

Tg system

at the terminal block leads. Resistance must be between 1.30 and

1.55 ohms.

NOTE: It is

condition may exist where several probes are broken or damaged and resistance still accepted limits. This condition may cause erroneous temperature indications due to reduced although the loop check resistance was within tolerance during test.

possible

that

a

falls within the

samplings,

Chapter 77 of the applicable Pratt 8 Whitney Engine Maintenance Manual for the procedures to be remove the engine power section assembly and check the harness leads and system probes.

Refer to

d.

to

ITT INDICATOR CHECK The or

If

(FM-1

THRU FM-8; FL-1 THRU FL-119 AND

following check on the ITT indicator should be performed performing checks of other indicating instruments.

used

FL-121)

any time it is

suspected that the

indicator is

erroneous

when

thermocouple

harness resistances

indicator may be nonfunctional or shock damage. An

adjustment

screw on

or

are

simply

within need

acceptable limits, the fault is most likely in the ITT indicator. The recalibration adjustment due to aging of the internal components

a

the back of the indicator is used to

the temperature indications

on

the JETCAL

Analyzer (1,

align

Chart 1,

the temperature indications

on

the indicator with

77-00-00).

Analyzer is not available, the Omega CalibratorTThermometer (4, Chart 1 77-00-00) or Barfield (6, Chart 1 77-00-00) may be used to apply a millivolt signal to the ITT indicator representative of specific temperature test points. In the event the indicator has lost its linear response to changes in thermocouple resistance, no adjustment can be made to correct this condition and the indicator must be

NOTE: If

a

JETCAL

ITT Test Set

77-00-00Page

213

Raytheon

AiKraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

replaced.

Chapter

cool-down is not

Engine a.

Refer to

39-10-00 for removal and installation

required

b.

Perform the

c.

The ITT indicator

settings

Adjustthe

e.

Seal the

access

in the test unit

panel

to

operator’s

instruments.

the electrical connector. Disconnect the electrical

access

manual for temperature indicator calibration. listed

on

the worksheet

as

compared to temperature

ITT indicatoras necessary.

adjusting

screw

with red varnish

following ITT system checks should be suspected in the indicating system.

(1,

Chart 2,

77-00-00)

after calibration.

(FM-9 AND AFTER; FL-120, FL-122 AND AFTER)

ITT INDICATING SYSTEM CHECKS The

engine

the leads.

readings should be within the tolerances applicable test unit. Refer to Chart 203.

the

on

d.

procedures

of the

for this check.

Remove the indicator from the instrument connector from the indicator to

procedures

made

anytime

a new

indicator

or

thermocouple

is installed

or

when

a

fault is

NOTE:

Engine cool-down is not required to perform a calibration check of the engine indicator, but is required checks. The internal engine components and thermocouple will perform the thermocouple-resistance require at least ten hours of cool-down time to reach ambient temperature.

Prior to

performing

71-10-00 to

any of the following checks, remove all electrical power from the airplane and refer to Chapter the engine cowling. When all checks of the ITT indicating system are complete, replace the

remove

indicator if all other

I

to

NOTE: When

areas

installing

of the system

the nuts for the

were

within tolerance,

or

replace

thermocouple leads, refer

to the

other components

as

found necessary.

applicable Pratt and Whitney Engine

Maintenance Manual for the correct torque value for the chromel and alumel nuts.

testing is complete, connect all wiring that was disconnected for the test, airplane and install the engine cowling. Refer to Chapter 71-10-00. When

ITT INDICATOR CALIBRATION CHECK a.

Disconnect the gas generator

(FM-9

restore electrical power to the

AND AFTER; FL-120, FL-122 AND

AFTER)

engine Tg and trim thermocouple wire harnesses at the Tg terminal block mou nted The airplane wire harness remains connected to the terminal block.

on

the

engine

case.

NOTE: If the millivolt

signal generator

is not ambient temperature

compensated, use the graph (FM-9 and After; FL-120,

in

Figure

209

trahC(ot

convert to millivolt and subtract from ITT Indicator Test Points

FL-122 and

After)

204).

b.

Chart

I

capable of generating a millivolt signal relative to the temperature test points. Refer to 204. The JETCAL Analyzer (1, Chart 1, 77-00-00) or Omega CalibratorTThermometer (4, Chart 1, 77-00suitable for this test. Follow the test unit operator’s manual instructions as applicable to this check.

Connect

00)

is

a

device

NOTE: Ensure that the

polarity of

the alumel and chromel wires

are

strictly

observed when

making

the test

connections. c.

Oct

Apply

31/06Page

214

28 vdc to the

airplane

and

apply

77-00-00

power to the ITT indicator.

,1

Raytheon

Aircraft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 203 ITT

(FM-1

System

Check Worksheet

thru FM-8; FL-1 thru FL-119 and

FL-121)

AIRPLANE S/N DATE

CHECKED BY

INSPECTOR

HARNESS RESISTANCE

LEFT

8f0.050HMS

RIGHT

8

0.05 OHMS

INSULATION CHECK LEFT

MUST BE OVER 5,000 OHMS

RIGHT

MUST BE OVER 5,000 OHMS

INDICATOR CHECK LEFT S/N

JETCAL

TOL.

TEST

"C

TEMP "C

RIGHT S/N INDICATOR READING

JETCAL

TOL.

TEST TEMP "C

200

50

200

50

400

35

400

35

600

25

600

25

700

15

700

15

750

10

750

10

800

5

800

5

850

10

850

10

900

15

900

15

1000

25

1000

25

1200

50

1200

50

A21

INDICATOR READING

"C

77-00-00

Oct

31/06Page

215

Raytheon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

d.

on

indicator reads between 183" and 217"C, it is within tolerance for the 200"C

Repeat f.

the test unit to

Select the 200"C calibration point

thermocouple wire harness. If the test point. Refer to Chart 204. the

previous step

for each test

apply

the

equivalent

millivolt

signal

to the airframe

Refer to Chart 204.

point.

readings fall within tolerance for all test points, perform the remaining ITT system checks to verify integrity of the thermocouple and thermocouple wire harness. If the indicator readings do not fall within tolerance, always perform a check of the thermocouple wire harness before replacing the indicator. If the indicator

Chart 204 ITT Indicator Test Points

(FM-9 TEST POINT

and After; FL-120, FL-122 and

("C)

MILLIVOLTS

INDICATOR TOLERANCE

200

8.137

183-217

400

16.395

383-417

600

24.902

588-612

800

33.277

793-807

1000

41.269

988-1012

1200

48.828

1183-1217

AIRFRAME ITT WIRE HARNESS CONTINUITY CHECK

(FM-9

AND AFTER; FL-120, FL-122 AND

a.

Disconnect the

airplane

wire harness at the

b.

Disconnect the

airplane

wire harness at the ITT indicator connector.

c.

Use

an

ohmmeter

continuity

After)

on

(5,

Chart 1,

77-00-00)

T, terminal

block

on

to check each lead for

each lead if the harness is

in the ITT wire harness is

responsible

Disconnect the trim

b.

With the

c.

Measure

CHECK

thermocouple

continuity.

good. If resistance is indicated, for any erroneous ITT indicator

ITT THERMOCOUPLE´•LOOP-RESISTANCE a.

the gas generator

leads and

(FM-9

airplane

AND

the

Tg system

AFTER)

case.

The ohmmeter should indicate

suspect that a short or break somewhere readings.

AFTER; FL-120, FL-122 AND AFTER)

wire hamess from the

Tg terminal

Tg harness intact, connect an ohmmeter (5, Chart 1, 77-00-00) to the terminal observing the polarity of the connections (negative to alumel and positive to chromel). loop resistance of

("C)

at the terminal block leads. Resistance for

a

block.

block while

carefully

normal system should

be between 1.30 and 1.55 ohms.

condition may exist where several probes are broken or damaged and resistance accepted limits. This condition may cause erroneous temperature indications due to reduced samplings, although the loop check resistance was in tolerance during test.

NOTE: It is

possible

that

a

still falls within the

d.

Referto to

Oct

Chapter 77 of the applicable Pratt Whitney Engine Maintenance Manual forthe procedures to be the engine power section assembly and check the hamess leads and system probes.

used

remove

31/0677-00-00

~1

Raytheon

AiKraft

Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

ITT THERMOCOUPLE-INSULATION-RESISTANCE a.

Connect the ohmmeter

(5,

CHECK

Chart 1,

77-00-00)

(FM-9

to the alumel lead

AND AFTER; FL-120, FL-122 AND on

the

T, terminal

block and to

AFTER)

ground

(gas generator case). b.

Measure resistance of the circuit. A functional indicated

c.

d.

on

thermocouple

should have at least 5,000 ohms of resistance

the ohmmeter.

Repeat steps

a

and b for the

thermocouple’s

chromel lead.

If either lead check does not meet the resistance and the system components tested and Whitney Engine Maintenance Manual.

repaired

requirements specified,

the

engine

must be

split at the C-flange applicable Pratt

in accordance with instructions found in the

TORQUEMETER-INDICA TING SYSTEM CHECKS (FM- 1 THRU FM-8; FL- I THRU FL- 1 19 AND

FL-121)

The torque transmitter, attached to the torque pressure manifold on the propeller reduction gearbox, senses oil pressure from the torquemeter. This oil pressure is converted to an electrical signal by the torque transmitter and displayed as a percent torque value. This value is representative of the torque applied to the propeller shaft. The

torque indicator displays torque applied

to the

propeller

shaft in percent of allowable torque.

The torque indicator may be checked by using the JETCAL connects directly into the torque-transmitter manifold on the

Analyzer (1, Chart 1, 77-00-00). The JETCAL Analyzer engine and incorporates it’s own transducer to drive the

indicator. An alternate method to

functionally

test the

torque indicating system is

to simulate

pressure. Shop air pressure may be applied to the torque pressure manifold by Chart 1, 77-00-00) or a torque system pressure tester (3, Chart 1, 77-00-00). Use Chart 205 to compare

acceptable

pressure

readings

to the test pressure

propeller reduction gearbox oil using a torque system calibrator (2,

inputs,

then record the instrument

performance. Adjustments to the torque indicating system a plug on the indicator.

nn

may be

accomplished by adjusting the adjustment

screw

located under

77-00-00Page

217

I

Raytheon

AiKraft company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 205

Torque System Check (FM-1 TEST

TORQUE

P.S.I.

PERCENT

TOLERANCE

25.7

1.1

20

51.5

0.9

25

64.34

0.75

30

77.2

0.6

38.85

100.0

0.3

40

102.9

0.3

45

115.8

0.6

TORQUE INDICATOR CHECK

starting a.

the

engine

(JETCAL) (FM-1

RIGHT INSTRUMENT SIN

THRU

FM-8; FL-1 THRU FL-119 AND FL-121)

connecting a JETCAL oil line adapter and transducer to the propeller reduction gearbox, comparing the JETCAL readings to the respective engine torque indicator.

instructions.

b.

Use the test unit

operator’s

c.

Start the

in accordance with the

engine

manual to program the JETCAL to read percent torque.

appropriate

Pilot’s

Operating

Handbook and FAA

Approved Airplane

Manual.

Flight d.

LEFT INSTRUMENT S/N

Disconnect the lower oil line from the torque pressure manifold where the torque transmitter and autofeather pressure switches are mounted, then connect the JETCAL test equipment as outlined by the test unit’s

operating

I

and

FL-121)

PERCENT

10

This check consists of

Worksheet

thru FM-8; FL-1 thru FL-119 and

Compare the readings

of the

cockpit indicator to the JETCAL Analyzer at each torque value adjust or replace the indicator as necessary.

listed in Chart 205.

If the indicator does not fall within tolerance,

TORQUE INDICATION AND CALIBRATION

(PRIOR

TO FL-232;

PM-10)

require starting the engines. Compressed air or compressed nitrogen is used to simulate propeller gearbox oil pressure. The torque system calibrator (2, Chart 1, 77-00-00) or torque system pressure tester 1, 77-00-00) is used as the reference pressure source.

This test does not reduction

(3,

Chart

The torque system calibrator is a precision pressure calibrated in pounds per square inch.

Page

tcO31/06 812

77-00-00

regulator and valve assembly. The face of the instrument

is

,1

Ray~heon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL NOTE: The torque indicating system response to gearbox pressure is linear and translates to percent of torque for every 1 psi of gearbox pressure. a.

b.

Disconnect the vent line from the Disconnect the lower AN

fitting

approximately

2.58

of the torque transmitter.

rear

from the torque pressure manifold and connect the torque calibrator

or

torque

pressure tester to the manifold. c.

Turn both valves

d.

Apply

e.

Turn the

f.

Turn the pressure

on

the

torque calibrator

external power to the

battery

airplane

switch ON and source

valve

On serials FM-1 thru FM-8; FL-1

as

bring on

or

torque pressure

outlined in

one

tester off and connect

Chapter 24-40-00.

of the inverters

on

line to power the torque transmitter.

the torque system calibrator

through

air to the unit.

shop

FL-119 and FL-121

or

pressure tester

perform steps

g, h,

n

on.

and

o.

pressure to each test pressure listed in Chart 205 and record the indicated torque

g.

Adjust

h.

Make any necessary adjustments to the torque transmitter by adjusting the screw under the adjustment plug until the system is properly calibrated. Replace the torque transmitter if the tolerances cannot be met.

On serials FM-9, FL-120, FL-122 i.

through

Disconnect both oil lines from the

FL-231

tee-fitting

perform steps i through

at the

reading.

I

o.

torque pressure manifold and cap the port that is

not used

during test. j.

Connect the nitrogen pressure

k.

Connect the voltmeter (8, Chart 1, 77-00-00) and power supply to the transmitter(Ref. Figure 205).

i.

Apply

m.

Slowly

source

and pressure gauge to the

uncapped port

on

the

tee-fitting.

pressure to the manifold at a slow steady rate until 85 psi is indicated on the pressure gage. As the pressure rises, record the output voltage for each input pressure setting listed in Chart 206. The output voltage must fall within the range shown in the Chart for each specific setting. reduce the pressure; as the pressure lowers record the output voltage for each input pressure setting listed in Chart 206. The output voltage must fall within the range shown in the Chart for each specific setting. Replace any transmitter that fails to meet the requirements of this test procedure.

CAUTION: Bleed the pressure down to O psi before disconnecting the pressure

source

from the torque pressure

manifold. n.

Bleed the pressure down to 0 psi and disconnect the test equipment. Remove cap and connect both oil lines to the

o.

tee-fitting

at the

torque pressure manifold.

Connect the vent line to the

rear

of torque transmitter and the AN

fitting

to the

torque pressure manifold.

77-00-00

I

Ral~heon

AiKlaft Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 206

Torque Transmitter Functional (FM-9 and After; FL-120, FL-122

Test Values thru

FL-231) OUTPUT

REFERENCE PRESSURE

TOLERANCE IN VDC

(PSI)

0

-0.050 to +0.050

20

1.126to1.226

40

2.303 to 2.403

60

3.479 to 3.579

80

4.656 to 4.756

85

4.950 to 5.050

PRESSURE

GAGE

NITROGEN BOTTLE

Al 28VDC

BI-

COMMON

C

OUTPUT

SIGNAL

D

OUTPUT

SIGNAL

E

SPARE

Fl SPARE

28 VDC POWER SUPPLY

VOLTMETER

Torque Transmitter Functional Test Schematic (FM-9; FL-120, FL-122 thru FL-231) Figure 205

Oct

31/0677-00-00

A21

Raytheoa

AiKraft

tompany

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TORQUE INDICATION AND CALIBRATION

(MEGGITT) (FL-232

This system functional test

of

provides

a means

testing

and

calibrating

On each

b.

Remove torque transmitter from torque pressure manifold.

c.

Connect the

d.

Connect

e.

Connect the

f.

Remove torque indicators from the instrument

g.

Connect the calibration

a

nitrogen adapter

hoses

(11, Chart 1, 77-00-00)

to the

calibrated pressure indicator capable of 100 PSI to the

nitrogen adapter

hose to the

on

external electrical power to the

Apply

i.

On the

j.

Perform the

pilot’s subpanel,

nitrogen supply panel.

cart

(9,

Meggitt torque

indicator and transmitter.

torque transmitter.

nitrogen adapter Chart 1,

hose.

77-00-00).

Note the location of torque indicators for installation.

adapter test box (10, Chart 1, 77-00-00)

indicators. Ensure that all switches h.

the

AFTER)

disconnect the oil pressure line connected to the torque transmitter.

a.

engine

AND ARER; FM-10 AND

to the electrical harness and to the

test box are turned to OFF. Refer to

Figure

torque

206 for test box schematic.

airplane.

turn the BATTERY and EXT POWER switch to ON.

Torque Indicator Test Procedure. Refer

to Chart

207, Testing and Calibration Procedure.

Chart 207

Testing

and Calibration Procedure Result

Action Circuit Breaker Test

On the circuit breaker panel, check that CB34 R TORQUE METER and CB19 L TORQUE METER CBs are

On the instrument meters

are

panel,

both left and

right torque

off.

OPEN.

On the circuit breaker

panel,

close CB34 R TORQUE

METER. On the circuit breaker

On the instrument on

panel,

close CB19 L TORQUE

METER.

and the

digital

On the instrument and the

digital

panel, the right torque light.

meter comes

readout will

panel,

the left torque meter

readout will

comes on

light.

Calibration Procedure

On the PSI meter, make sure 0 PSI is displayed. If not release pressure from the nitrogen hoses.

On the calibration test box, hold S1 in the CAL ZERO position for 5 seconds then release. On the

PSI

as

nitrogen supply cart, adjust the pressure to 38.91 displayed on the PSI digital display.

On the calibration test box, hold S1 in the CAL FS position for 5 seconds then release.

p~,

On the instrument 0%

panel, both torque

meters will

display

torque.

No leaks shall be detected in any of the oil pressure

systems fittings. On the instrument

panel, both torque

meters will

display

100% of torque.

77-00-00

221

I

Rayfheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

k.

On the

nitrogen supply cart, slowly adjust

I.

On the

pilot’s subpanel,

m.

Disconnect the

n.

Install torque transmitter into torque pressure manifold.

o.

the pressure to 0 PSI.

turn the EXT POWER switch to OFF.

hoses from the torque transmitter.

nitrogen adapter

Connect the oil pressure lines to the torque transmitter.

p.

Torque and seal all fittings that

q.

Remove the calibration

disturbed

were

during

the

performance

of this test to 30-foot

pounds.

box from electrical harness and torque indicators.

adapter test

Connect electrical harness to torque indicators. s.

Install the torque indicators into their NOT SWITCH SIDES.

respective locations

t.

Disconnect electrical power from the

airplane.

P120 J1

MS 3476W1 4-19SW

in the instrument

panel

as

noted

during

removal. DO

P120 P1

I

MS3474W14-19SW CABLE

(REF)

F/S S1

ZERO

I

F/S ZERO

CABLE

(REF) TORQUE METER TEST BOX

MS3474W14-19SW L__.

P119J2

k2 FEET~

_~I

SCHEMATICVIEW NO SCALE

-1

P119P2

~C2 FEET-pi

MS 3476W1 4-19SW

FATIB9914~AB.AI

Calibration

Adapter Test Box (Meggitt) Schematic (FL-232 and After; PM-10 and After) Figure 206

Page

tcO2 2

31/06

77-00-00

A21

Raytheon

nircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TORQUE TRANSMITTER REMOVAL a.

Remove all electrical power from the

b.

Remove the

engine cowling

c.

Remove the

safety wire

as

airplane.

outlined in

Chapter 71-10-00.

and disconnect the electrical connector

(1) from the torque

transmitter

(3) (Ref.

Figure 207). d.

Disconnect the vent line

(2)

e.

Remove the transmitter

(3),

from the transmitter washer

(4)

and

(3).

O-ring (5)

from the torque pressure manifold

(6).

TORQUE TRANSMITTER INSTALLA TION Install

b.

Install the transmitter

(3)

in the torque pressure manifold

c.

Connect the vent line

(2)

to the transmitter

d.

Connect and

e.

Install the

f.

Restore electrical power to the

a new

O-ring (5)

safety

and the washer

the transmitter

a.

(4)

on

4_

as

outlined in

(6).

(3).

wire the electrical connector

engine cowling

(3) (Ref. Figure 207).

Chapter

(1)

to the transmitter

(3).

71-10-00.

airplane.

,6

2~

A

1.ELECTRICALCONNECTOR 2. VENT LINE

VIEW

bTORQUE TRANSMITTER 4.WASHER 5. O-RING 6. TORQUE PRESSURE MANIFOLD

A

Torque Transmitter Installation

Figure

A21

207

77-00-00

Oct

31/06Page

223

RByH~eOn

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

FUEL FLOW SYS~EM CHECK

I

a.

Disconnect the fuel flex line from the fuel heat

b.

Disconnect the fuel lines from the fuel-flow transmitter, then cap the lines and

exchanger

inlet

(Ref. Figure 208). remove

the transmitter from the

airplane. c.

Connect the flex line which

d.

Connect

I e.

Turn

f.

Open

on

test flowmeter

a

discharge

was

(7,

disconnected in step

Chart 1,

77-00-00)

a

to the inlet

to the outlet

line to return the fuel to the main fuel tank

as

port of the fuel-flow transmitter.

port of the fuel flow transmitter and

shown

Check each fuel flow transmitter

System

h.

against

no

bubbles

are

the flowmeter indication and rates shown in Chart 208, Fuel Flow

Check Worksheet. Remove the test equipment, install the fuel flow transmitter and connect the fuel lines

install

or

a

the fuel boost pump and open the firewall shutoff valve.

the needle valve in the test system and let the fuel recirculate at the full flow rate until present in the flowmeter glass before starting the system check.

I"

connect

(Ref. Figure 208).

a new

Repeat steps

a

transmitter

through g

as

on

necessary.

the

opposite fuel flow transmitter,

then

replace

any

faulty components

as

necessary.

Chart 208 Fuel Flow

INDICATOR

TOLERANCE

100

8

200

8

300

8

400

8

450

8

500

8

550

8

600

8

700

8

750

8

tcO42

31/06

LEFTINSTRUMENTS S/N

RIGHT INSTRUMENTS S/N

PPH

PPH

Page

System Check Worksheet

77-00-00

A21

gaYtheotr

AiKraR

Company

SUPER KING AIR 8300/B300C MAINTENANCE MANUAL

FLOWMETER FLOW

NEEDLE

DIRECTION

VALVE

MAIN

FUEL

CONNECT TO FLEXIBLE HOSE FUEL FLOW TRANSMITTER OUTLET.

TANK

DISCONNECT FUEL LINES. CAP AND REMOVE TRANSMITTER

L--__J

I

I

FUEL

III

FLOW

LINES

TRANSMITTER

DISCONNECT FUEL LINE FROM HERE

ANO

CONNECT TO FUEL INLET

TRANSMITTER

LFYO

FUEL

HEAT

EXCHANGER

VIEW

LOOKING

AT

RH

SIDE OF

ENGINE C94FL77B1277

Fuel Flow Transmitter and Test

Figure

A21

Equipment Configuration

208

77-00-00

Oct

31/06Page

225

RBytheon

Aircraft

Company

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

y=0.004x-0.7191 RZ~i 1.6

1.4

1.2

0.8

MI111 VOLTS 0.6

0.4

0.2

-0.2

.0

10

30

20

40

50

60

70

80

90

1M)

AMBIENTTEMPERATURE ’F

esns 00Y194~Y

Ambient

Page

tcO62

31/06

77-00-00

Temperature Conversion Graph Figure 209

A21

C~A PTER

EXHAUST

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 78

EXHAUST

TABLE OF CONTENTS

SUBJECT

PAGE 78-00-00

Exhaust-

Descriptionand Operation

........._._.__

Recommended Materials Exhaust-Maintenance Practices.

.........__._._

........._._._.._

.1

.........1 ................_

..201

ExhaustStacks. Exhaust Stack Removal

Exhaust stack installation ExhaustStackCrack Repair.

n25

.....201

....202 .202

78-CONTENTSPagel

Hawker Beechcraft

Corporation

SUPER KING AIR 8300/8300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

78-LOEP

1

Feb 1/09

78-CONTENTS

1

Feb 1/09

1

Feb 1/09

201 and 202

Feb 1/09

78-00-00

A25

Pages

78-LOEP

Feb

1/09Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

EXHAUST The exhaust an

"L"

system consists

shaped

and away from the The

engine anti-ice lip to

engine directly

exhaust stacks and the to the

engine

air inlet anti-ice

engine

and channels hot

engine

lip.

The exhaust stack is

exhaust gases past the

cowlings

engine.

stack around the front

lip is

of the

tube that is mounted

is

a

continuous duct that channels hot

edge

of the

prevent the formation

engine

of ice in and

engine exhaust gases from the engine’s left exhaust opening engine’s right exhaust stack. The purpose of this around the engine air intake during inclement weather.

air inlet

to the

RECOMMENDED MA TERIALS The recommended materials listed

(Ref. Chart i) as meeting federal, military or supplier specifications are provided only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification may be used subject availability. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance to the applicable specifications. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE REQUIREMENTS OF SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART. Only the basic number of each specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

for reference

Chart 1 Recommended Materials

Material i.

Methyl Propyl

2.

Welding Rod

Ketone

Specification

Supplier

Product

A-A-59282

Obtain Inconel 82

Locally

Huntingdon Alloys Incorporated 11750 Chesterdale Road

Atkinson

Square

Cincinnati, Ohio 45246

n25

78-00-00

Feb

1/09Page

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXHAUST

MAINTENANCE PRACTICES

EXHA UST STA CKS The exhaust stacks

by

the

use

of the

mounted

the

directly to following procedure. are

engine exhaust ports and

can

be removed for service

or

replacement

EXHAUST STACK REMOVAL Remove the upper forward and lower forward

a.

engine cowlings

in that order

(Ref: Chapter 71-10-00, COWLING

REMOVAL). NOTE: The

engine

air inlet anti-ice

the lower forward b.

lip flex hoses must be disconnected from the exhaust stacks prior to removing engine cowling (Ref: Chapter 71-10-00, COWLING REMOVAL).

Remove the brackets for the fire detection

sensor

cable and note their

placement (Ref: Chapter 26-10-00, FIRE

DETECTION). Remove the twelve

c.

remove

bolts, washers and

the exhaust stack

nuts that secure the exhaust stack to the

engine

exhaust port and

(Ref: Figure 201).

EXHAUSi STACKS

ASHER

U~

P" FLEX HOSE

DISCONNECT

V"i

V;-

rl

A

i i

CLAMPS

NE AIR INLET

_c~----le

DEfAIL

Engine

A

350-25812

Exhaust Stacks and Air Inlet Anti-ice

Figure

A25

ANTI-ICE LIP

Lip

201

78-00-00

1/09

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

EXHAUST STACK INSTALLATION a.

NOTE: The attached bolts b.

I

I

exhaust

Position the exhaust stack to the engine previously removed (Ref: Figure 201). are

to be

torqued

Install the lower forward

cowling

(Ref: Chapter 71-10-00,

COWLING

port and

to 50-70

with the twelve bolts, washers and nuts

secure

inch-pounds. flex hoses to the exhaust stacks

engine air inlet anti-ice lip INSTALLATION).

and connect the

c.

Install the brackets for the fire detection

d.

Install the upper forward

sensor

cable

(Ref: Chapter 26-10-00,

engine cowling (Ref: Chapter 71-10-00,

COWLING

FIRE

DETECTION).

INSTALLATION).

EXHAUST STACK CRACK REPAIR

Repair Do not

cracks less than three inches in

repair

cracks

greater

the

length using

than three inches in

procedure

length.

If

a

outlined in this section. of this

repair

significance

is

required, replace the

exhaust stack.

Repair a.

b.

cracks to

exhaust stack

an

follows:

Remove the exhaust stack from the

engine

as

instructed in EXHAUST STACK REMOVAL.

Remove all carbon from the interior and exterior surfaces

exhaust stack to c.

as

using

hot soapy water and

a

suitable brush. Allow the

dry thoroughly.

Wire brush both the inside and outside of the

area

which

requires

a

weld, using

a

brush with fine stainless steel

bristles d.

Rinse the

e.

Prior to

area

to be

welding

repaired

the crack,

1.

Place

2.

Cap the openings

a

copper sheet,

Introduce

is

an

with

Methyl Propyl

accomplish a

one

of the

Ketone

(Item

No. 1, Chart 1,

and allow to

dry.

following procedures;

minimum of 0.063 inch thick,

against

the inside surface of the crack.

in the exhaust stack with wooden blocks and seal the

remaining small crevices with tape. welding. Continue until the repair

argon purge, at 10 cubic feet per hour, five minutes before

complete. the crack

using

the tungsten inert gas process and

welding

rod

(Item

f.

Repair

g.

Install the exhaust stackas instructed in EXHAUST STACK INSTALLATION.

Page

78-00-00)

20278-00-00

a

No. 2, Chart 1,

78-00-00).

a25

C H A PT E R

OIL

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 79

OIL

TABLE OF CONTENTS

PAGE

SUBJECT 79-00-00

Oil

System

Descriptionand Operation

..................1 .........5

Recommended Materials

OilSystem Maintenance Oil System Servicing. Engine Oil Changing.

.201

Practices

Oil Cooler Removal.

Oil Cooler Installation ................205

Oil CoolerThermostat Valve Removal

.............205

Oil CoolerThermostat Valve installation.

.....205

Oil BreatherTube Removal.

....207

Oil Breather Tube Installation

................207

OilTank Drain Shutoff Valve Removal

..............207

OilTank Drain Shutoff Valve Installation. 79-30-00

Indicating- Descriptionand Operation OilTemperature Indicating System. Oil Pressure Indicating System Oil System Chip Detectors Indicating- Troubleshooting Indicating- Maintenance Practices Chip Detector Removal. Chip Detector Installation

..................1 .1

.....1 ........1

......101 .201

........201 .......201 203

Oil Pressure Transducer Removal

.203

Oil Pressure Transducer Installation. Low Oil Pressure Switch Removal

..........203 .205

Low Oil Pressure Switch Installation. Oil Oil Oil

Temperature Temperature Temperature

Bulb FunctionalTest

PressureWarning Chip Detector Inspection

nz4

.205

Bulb Installation

Oil Pressure Transducer Functional Test

LowOil

..205

Bulb Removal.

................205 ..............206 ......208

Switch FunctionalTest.

........209

79-CONTENTS

1/08Page May

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/8300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

79-LOEP

1

May

1/08

79-CONTENTS

1

May

1/08

1 thru 5

May May

1/08

May May May

1/08

79-00-00

201 thru 208 79-30-00

1 thru 6 101 and 102 201 thru 209

A24

Pages

1/08

1/08 1/08

79-LOEP

May

1/08Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

OIL SYSTEM

oil system (Ref. Figure 1) is a closed system consisting basically of a pressure system, a scavenge and a breather system, (Ref. Figure 2) all of which are supplied as part of the engine by the engine system manufacturer. Added to the closed engine system is an oil cooling system, an overboard breather line and an

The

engine

indicating system. components

are

Refer to

Chapter

mounted within

or on

79-30-00 for information the

engine

with the

on

the

exception

indicating system.

All of the oil

system

of the oil cooler which is mounted below the

engine. NOTE: Refer to the Pratt

engine

Whitney PT6A-60A Engine Maintenance supplied components of the system.

Manual for detail information

relating

to the

manufacturer

supply for the engine is contained in an oil tank which is an integral part of the engine compressor inlet case. through a filler neck located at the 11 o’clock position on the accessory gearbox housing and accessed through a hinged access door on the top surface of the upper forward engine cowling. A cap and dipstick extends down through the filler neck into the oil tank. The dipstick is marked in US quarts to indicate the amount of oil required to fill the engine oil tank to the full mark. The tank has a capacity of 2.5 gallons (10 quarts) of which 1.5 gallons (6 quarts) are usable, with a total system capacity of 16.3 quarts. The oil system is serviced with the oil type specified in the latest revision of Pratt Whitney Service Bulletin No. 13001.The tank is vented through a breather boss on the accessory gearbox housing. A breather tu be from the breather boss is routed aft of the engine and exits through the bottom of the nacelle. The oil

Oil is added to the tank

picked up from the oil tank and routed through the pressure side of the oil system by an internal pressure pump mounted at the bottom of the oil tank. A pressure regulating valve and a cold pressure relief valve are mounted at the top of the pump housing. A filter assembly, consisting of a filter element and a filter bypass valve downstream of the oil pump, filters the oil before it is delivered to the engine components. The filter assembly is accessible

The oil is

through

a cover

at the 3 o’clock

position

on

the compressor inlet

case.

by two double-element scavenge pumps, one mounted within the accessory gearbox externally on the accessory gearbox. The rear element of the external scavenge pump forces the oil from the reduction gearbox to the oil cooler inlet port. The oil cooler incorporates a thermostatic control valve which will allow some oil to bypass the cooler core when the oil temperature is below 160" F. At 160" F the valve will direct all of the oil flow through the cooler core. Oil from the cooler is then returned to the oil tank through a hose from the oil cooler outlet port to a fitting at the 12 o’clock position on the compressor inlet case. The rear element of the internal pump scavenges oil from the accessory gearbox sump and forces it through the oil-to-fuel heater. Oil from the heater is returned to the oil tank by one of two paths, dependent upon the temperature of the oil as it leaves the heater. A thermostatic bypass/check and diverter valve, positioned between the heater and oil tank, will prevent oil that is too hot from returning directly to the oil tank without first flowing to the oil cooler. This valve will divert the hot oil to join the oil flowing to the oil cooler from the external scavenge pump. Oil is returned to the oil tank and another mounted

The oil system can be drained at the following locations: the reduction gearbox, the oil tank, the accessory gearbox and the oil cooler. The oil tank is drained through a drain tube and shutoff valve mounted at the 6 o’clock position on

the compressor inlet

case.

To

CAUTION: The shutoff valve is make

nz4

sure

operate the drain

safety

remove

the cap and open the shutoff valve.

wired in the closed position, after the

that the valve is in the closed

position

and

safety

draining operation

is

complete, always

wired.

79-00-00Page

1

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INLETFROM

u

c

O o

OIL COOLER

BREATHER TUBE BOSS o

OIL FILLER Q’

AND DIPSTICK

t

o

h

u ACCESSORY GEARBOX

t

COMPRESSOR INLET CASE

r

OIL FILTER

THERMOSTATIC BYPASS CHECK AND DIVERTER

EXTERNAL SCAVENGE PUMP

I

VALVE

OUTLET

OIL-TO-FUEL

TO OIC COOLER

HEATER

350-257-17

Engine Oil System Figure 1

May

1/08Page

2

79-00-00

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

THERMOSTAT VALVE WHEN FULLY OPEN ALLOWS DIVIDED FLOW THRU fHE COOLER CORE AND BY-PASS GALLERY. ~--O(L TANK BREATHER

WHEN FULLY CLOSED IT ALLOWS

FLOW THRU THE COOLER CORE ONLY

OIL FILLER AND DIPSTICK

SPLINES. BEARINGS AND

DETAIL

FIRST STAGE REDUCTION GEARS

A

THERMOSTATIC CONTROL AND DIVERTER VALVE

TOFIQUEMETER OIL PROPELLER SHAFT

CENTRIFUGAL BREATHER

CONTROL VALVE

RETURN FROM COOLER

OIL TRANSFER TUBE

PROPELLER GOVERNOR AND BETA CONTROL THRUST ROLLER

OIL-TO-FUEL HEATER NO

-ff~s,,;

4

BEARING

BEARING--7

NO

sVJI11IG

NO

2

Is~.

BEARING

3 BEARING

I

OIL FIITER ANt)

fO COOLER

ML TI\NKIIX~W

’´•I~ I

CHECK VALVE ASSEMBLY

OIL SUPPLY TO PROPeLLER

ffiHIfI

I I/ NO

B

I I

LI

NO

_I

~C1 I

L~

t%LI

I

PRESSURE

COMPRESSOR BEARINGS

4 BEARING

NOZZLE

FILTER BYPASS VALVE

POWER TURBINE BEARINGS

OIL TRANSFER SLEEVE

RELIEF VALVE

O(L PRESSURE PUMP

REDUCTION CASE

SCAVENGE PUMP

(REAR ELEMENT)

POWER TURBINE BEARINGS TOROUE LIMITER

REDUCTION GEARBO~ CW)P

(IF FITTED)

I

IOROLlEMETER

U

SCAVENGE PUMP

INDICATOR

(FRONT ELEMENT)

A

TORQUEMETER PRESSURE SUCTION

PRfSSUREO(L

AND

TANK DRAIN

INDICATOR

ACCESSORY CASE

I

I

a

SCAVENGE PUMP

(REAR ELEMENT)

~j I

IB

PROPELLER SUWLY OK TO OIL PRESSURE

~ACCESSORY

I~L"Y;REc3uLATINo

SCAVENGEOIL BREATHER AIR

L~3 i

PRESSURE --I

GEARBOX GRAIN

oc~ cowR

fO OL TEMPERATURE

INDICATOR

I

I

TOIIQUEMErrR PRESSURE

NO n BEARING

SCAVENGE PUMP

(FRONT ELEMENT)

300´•2571

Engine

A24

Oil

System Schematic Figure 2

79-00-00

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

This

Page

79100100

Page Intentionally

Left Blank

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

RECOMMENDED MATERIALS as meeting federal, military or supplier specifications are provided for only and are not specifically required by Hawker Beechcraft Corporation. Any product conforming to the specification may be used. The products included in these charts have been tested and approved for aviation usage by Hawker Beechcraft Corporation, by the supplier, or by compliance to the applicable specifications. GENERIC OR

The recommended materials listed in Chart 1 reference

LOCALLY

MANUFACTURED

PRODUCTS

WHICH

CONFORM

TO

THE

REQUIREMENTS

SPECIFICATION MAY BE USED EVEN THOUGH NOT INCLUDED IN THE CHART.

Only

OF

THE

the basic number of

specification is listed. No attempt has been made to update the listing to the latest revision. It is the responsibility of the technician or mechanic to determine the current revision of the applicable specification prior to usage of the product listed. This can be done by contacting the supplier of the product to be used.

each

Chart 1 RECOMMENDED MATERIALS MATERIALS

Lubricating

Grease

PRODUCT

SPECIFICATION MIL-G-6032

L-237

or

CE-1155

SUPPLIER

Lehigh

Chemicals

Nuddix Div.

Tennaco Chemicals Inc.

Chestertown, MD 21620 Rockwell 950

Rockwell

Mfg.

Co.

4207 First Ave.

Brooklyn, Royce

A24

32

NY 07981

Royal Engineering Co. Whippany, NJ 07981

79-00-00

May

1/08Page

5

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OIL SYSTEM

MAINTENANCE PRACTICES

OIL SYSTEII/I SERVICING

Servicing the engine oil system primarily involves maintaining the engine oil at the proper level, inspecting and cleaning the engine oil filter and changing the engine oil when the oil becomes contaminated. Refer to Chapter 12-10-00 for the oil system filling procedure. The oil filter should be cleaned and inspected at each engine oil change and at interval specified in Chapter 5-00-00. The filter is replaced at inten/al specified in Chapter 5-00-00. ENGINE OIL CHANGING CAUTION: When

changing to a different brand of oil, completely drain the engine oil system as indicated in the procedure below. Remove the oil filter and immerse it in the new brand of oil to be used. Install the oil filter and drain plugs. Fill the system to the proper level, and ground run the engine for 20 minutes to thoroughly circulate the new brand of oil throughout the system. Completely drain the engine oil system and again remove the oil filter and immerse it in the new brand of oil. Fill the engine oil system as indicated below. This procedure will thoroughly purge the system of the old oil to prevent chemical interaction between it and the

a.

b.

Remove the upper

forward,

new

brand of oil.

center and aft and the lower forward

engine cowling (Ref. Chapter 71-10-00).

Provide suitable containers, funnels, and drain hoses to facilitate oil

drainage

and to

prevent unnecessary oil

spillage. c.

Remove the dust cap compressor inlet

(Ref. Figure 201) from the oil tank drain shutoff

case.

Remove the

safety

d.

Remove the drain

e.

Release the Dzus fasteners which

f.

Remove the

g.

Disconnect the unions from the inlet and outlet ports of the oil cooler.

h.

Remove the oil filter element

i.

Remove the

j.

Remove the drain

k.

With all the drain

plug

safety

chip

located at the 6 o’clock secure

wire from the drain

as

plug

position

the lower aft

plug

and

on

position

the

rear

cowling

remove

detailed in the Pratt

detector at the 6 o’clock

valve at the 6 o’clock

position of the engine oil tank.

wire and open the shutoff valve to drain the

on

cover

the drain

Whitney

face of the accessory to the

plug

below the oil cooler.

from the oil cooler.

PT6A-60A

the reduction

cowling

gearbox housing.

Engine

gearbox

front

Maintenance Manual.

case.

from the oil-to-fuel heater.

plugs removed, engine of oil.

motor the

engine

with the starter

only (no ignition)

to

permit the scavenge

pumps to clear the CA UTION:

Limit the to the

in the

motoring to the time required to accomplish the above due to the limited lubrication available engine during this operation. To prevent damage to the fuel control unit, leave the condition lever FUEL CUT OFFposition while motoring the engine.

Observe the starter operating limits of 30 seconds ON, 5 minutes OFF, 30 seconds ON, 5 minutes OFF, 30 seconds

ON,

30 minutes OFF.

I.

Install the oil filter element

m.

Install

nas

new

O-rings

on

as

detailed in the Pratt

the drain

plugs

and the

chip

Whitney

PT6A-60A

Engine

Maintenance Manual.

detector.

79-00-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DETAIL

B

A

b

10

4

3

OIL-TO-FUEL

OIL COOLER

HEATER

1. ACCESSORY GEARBOX DRA~N PLUG

2. O-RING

B

3. O-TO-FUEL HEATER DRAIN PLUG 4. O-RING

DETAIL

A

5. CHIP DETECTOR 6. O-RING

7. OIL TANK DRAIN SHUTOFF VALVE 8. DUST CAP

9. DRAIN PLUG 10. O-RING 350-257-12

Engine

Oil

System

Figure

Page

79-00I00

Drains

201

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

n.

o.

Install the

chip

detector in the reduction

Install the drain

safety

the

gearbox

face of the accessory

plug

on

plug

in the oil cooler and

rear

Torque

case.

to 45-55

gearbox housing. Torque

and

safety

to 215-240

wire.

inch-pounds

and

wire.

p.

Install the drain

q.

Connect the unions to the inlet and outlet ports of the oil cooler.

r.

Install the drain

s.

Place the shutoff valve in the closed

t.

inch-pounds

Fill the

safety

wire.

in the oil-to-fuel heater and

plug

to 65-70

torque

inch-pounds,

then

position and safety wire. Install the dust cap

engine with the correct amou nt and type

of oil

as

specified

safety

on

wire.

the shutoff valve.

in the latest revision of Pratt

Whitney Service

Bulletin No. 13001. NOTE: The oil tank

capacity of each engine is 2.5 gallons (10 quarts), of which only 1.5 gallons (6 quarts), are Additionally, approximately 6 quarts of oil are required to fill the lines and oil cooler, giving a total system capacity of 16.3 quarts. However, because of the residual oil trapped in the system, no more than 13 quarts should be added during an oil change. usable.

u.

Motor the

engine

over, with the starter

only, long enough

to

get

an

oil pressure

reading.

CA UTION: Observe the sta~fer operating limits of 30 seconds ON, 5 minutes OFF, 30 seconds ON, 5 minutes OFF, 30 seconds v.

Check the

w.

Check the of Pratt

ON, then 30 minutes OFF.

engine for

oil leaks.

engine oil level and add oil as required to fill the tank to the proper Whitney Service Bulletin No. 13001 for the correct type of oil.

x.

Install the lower

y.

Install the

cover on

the

engine cowling

below the oil cooler and

secure

level. Refer to the latest revision

the Dzus fasteners.

engine cowling (Ref. Chapter 71-10-00).

OIL COOLER REI~OVAL CAUTION: To prevent contamination of the oil system, cap are disconnected or removed. a.

Release the Dzus fasteners which

secure

or

the lower center

plug

all

openings

engine cowling

in the

cover

system

to the

as

the components

cowling

below the oil

cooler. b.

Place

c.

Cut the

d.

Disconnect the unions from the oil inlet and outlet ports a suitable container.

e.

Remove the 8 bolts, washers and nuts

NOTE:

a

drip

pan under the

safety

wire and

engine

remove

the oil cooler drain

If the elbow tube assemblies

positions.

to catch any oil

are

securing

removed,

spillage.

plug

and drain the oil into on

the oil cooler

a

suitable container.

(Ref. Figure 202)

and drain the oil into

the oil cooler to the outlet and inlet ducts.

note their

Install the unions in the oil cooler with

new

positions O-rings.

so

they

can

be reinstalled in the

79-00-00

same

Page

yaM302

1108

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

TUGE

ASSY

UNION

EOSE

ASSEMBLY

(OUTI

s ASSEMBL

HOSE

OIL

COOLER

(INj

THERMOSTAT WASHER

ORIGINAL As INTAKE DUCT

OIL COOLER

OUTLE1 DUC1

Received By A’TP

WIGGIIUS COUPLII\IG

CLAMPS

---TUBE

ASSY

‘UNION MOUNTING BOLT

CETAIL A

~50-257-011

C

Oil Cooler Installation

Figure

May

1/0879-00-00

202

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OIL COOLER INSTALLATION a.

Install the drain

b.

Position the oil cooler between the inlet and outlet ducts and install the 8 bolts, washers and nuts.

c.

plug

in the oil cooler with

a new

O-ring

safety

and

Connect the unions to the inlet and outlet ports in the oil cooler

wire the

plug.

(Ref. Figure 202).

Reinstall the elbow tube

assemblies if removed. d.

Refill the oil system

e.

Motor the

engine

as

over

necessary per with the starter

Chapter

12-10-00 and check the oil level.

only (no ignition) long enough

to obtain an oil pressure

readi3g.

CA UTION: Obsen/e the starter operating limits of 30 seconds ON, 5 minutes OFF, 30 seconds ON, 5 minutes OFF, 30 seconds ON, then 30 minutes OFF. f.

Check for leaks around the oil cooler inlet and outlet

fittings

g.

If

cover

no

leaks

are

found, install the lower

center

cowling

and the drain

plug.

below the oil cooler.

O1L COOLER THERMOSTAT VAL VE REMOVAL a.

Disconnect the Dzus fasteners in the lower aft

b.

Drain and

c.

With

a

remove

the oil cooler

as

wrench of the proper size,

specified

remove

cowling

cover

below the oil cooler and

remove

the

cover.

under OIL COOLER REMOVAL.

the thermostat valve from the oil cooler.

OIL COOLER THERMOSTA T VAL VE INSTALLA TION a.

Install the thermostat valve in the oil cooler with

b.

Reinstall the drain

c.

plug

in the oil cooler and

a new

safety

washer.

wire the

plug.

Reinstall the oil cooler between the inlet and outlet ducts and refill the oil system

as

specified

under

OIL COOLER INSTALLATION.

O1L BREA THER TUBE REMOVAL a.

Remove all electrical power from the

b.

Remove the

c.

Loosen the on

the

airplane.

engine cowling (Ref. Chapter 71-10-00).

clamps and

engine

remove

accessory

the oil vent hose from the elbow

(Ref. Figure 203)

and the oil breather

adapter

gearbox housing.

d.

Remove nut, washer, bolt and

e.

Remove the oil vent hose from the

f.

Remove the bolts and washers

g.

Remove the oil breather

clamps

that

secure

the oil vent hose to the

engine

truss mount.

airplane.

securing

adapter from

the oil breather

the

airplane

adapter to

the breather tube boss

and discard the old

on

the

engine.

O-ring.

79-00-00May

1/08

I

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

BOLT

WASHER

MI

OIL VENT HOSE

a

´•sZ

SCREW CLAMP

B

OIL BREATHER ADAPTER

O-RING

v ~U"B

ELBOW

CLAMP DETAIL

A

RIGHT HAND ENGINE

BOLT

WASHER

Rg~i OIL VENT HOSE

t CLAMP~

OIL BREATHER ADAPTER

SCREW

DETAIL

B

LEFT HAND ENGINE

CLAMP

ELBOW

350-257-9

Oil Breather Tube Installation

Figure

Page

79-00-00

203

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OIL BREA THER TUBE INSTALLA TION a.

Install the

new

engine

O-ring

on

with the

the oil breather

attaching

engine

b.

Secure oil vent hose to the

c.

Install the oil vent hose

d.

Install the

e.

Restore electrical power to the

on

adapter

and

secure

the oil breather

adapter to

the breather tube boss

on

bolts and washers. truss mount with

the oil breather

adapter

attaching bolt, washer,

and elbow and

secure

nut and

with

clamps (Ref. Figure 203).

1

attaching clamps.

engine cowling (Ref. Chapter 71-10-00). airplane.

OIL TANK DRAIN SHUTOFF VAL VE REMOVAL a.

Remove the

engine cowling (Ref. Chapter 71-10-00).

b.

Place

pan under the

c.

a

drip

spillage.

to catch any oil

(Ref. Figure 204) engine oil tank.

Remove the dust cap valve to drain the

d.

engine

from the shutoff valve. Remove the

safety

wire and open the shutoff

Remove the drain tube from the union and the shutoff valve.

CAUTION: To prevent contamination of the oil system after the drain tube is removed, cap the union. e.

Remove nut from the shutoff valve and

remove

the shutoff valve and washers from the bracket.

OIL TANK DRAIN SHUTOFF VALVE INSTALLA TION a.

Install the shutoff valve and washers into the bracket.

b.

Install nut

c.

Connect the drain tube to the shutoff valve and union

d.

Place the shutoff valve in the closed

e.

Install the dust cap

f.

Refer to

on

the shutoff valve to

Chapter

on

secure

the shutoff valve to the bracket.

position

and

(Ref. Figure 204).

safety wire.

the shutoff valve.

12-10-00 and check the oil level and add oil

as

necessary to

replace

the oil drained from the

tank.

g.

Motor the

engine

over

with the starter

only (no ignition) long enough

to obtain an oil pressure

reading.

CAUTION: Observe the starter operating limits of 30 seconds ON, 5 minutes OFF, 30 seconds ON, 5 minutes OFF, 30 seconds ON, then 30 minutes OFF. h.

Check the

area

i.

If

are

~a4

no

leaks

around the shutoff valve for leaks.

found, install the engine cowling (Ref. Chapter 71-10-00).

79-00-00

Page

207Mayl/08

I

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

i. DUST CAP

2. SHUTOFF VALVE S.WASHER

4. BOLT 5. WASHER 6

BRACKET

7. NUT 8

DRAIN TUBE

9. UNION 10

O-RING

A

15 ENGINE AIR

INTAKE PLENUM

10

7

.9

K~-

3

V

VIEWA

550´•257-11)

Oil Tank Drain Shutoff Valve

Figure

Page

yaM802

1/08

79-0000

204

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

DESCRIPTION AND OPERATION

INDICATING

OIL TEMPERA TURE INDICA TING SYSTEM oil temperature is monitored by an oil temperature bulb mounted on the accessory gearbox housing of each and is displayed on the oil temperature gage in the instrument panel (Ref. Figure 1) (Ref. Figure 2). A constant power source is supplied to the resistance-type temperature bulbs by the L and R OIL TEMP circuit

Engine engine

beakers located

The

engine

on

the

right

hand circuit breaker

oil temperature gage, in the

engine

panel (Ref. Figure 3)

in the

cockpit.

instruments section of the instrument

panel,

is

graduated

from

20" C to 140" C in increments of 10" C.

OIL PRESSURE INDICATING SYSTEM

engine oil pressure is monitored by an oil pressure transducer (Ref. Figure i) (Ref. Figure 2) mounted on the accessory gearbox housing of each engine and is displayed on the oil pressure gage in the instrument panel. Electrical power for the transducers is through the L and R OIL PRESS circuit breakers on the right hand circuit breaker panel in the cockpit. Engine oil pressure is sensed by the transducer and converted by the transducer into an electrical signal that is transmitted to the appropriate oil pressure gage (Ref. Figure 3). The input signal to the oil pressure gage will range from O to 5 vdc, with 0 volts being equal to 0 psi and 5 volts being equal to 200 psi. The

The

engine oil pressure gage, psi psi increments.

in the

engine

instruments section of the instrument

panel,

is

graduated

from 0 to 200

in 10

engine oil pressure in either engine drops below approximately 40 psi, the crew is notified by the low oil pressure warning system. The system consists of a low oil pressure switch mounted on the accessory gearbox housing of each engine, 5-amp L and R OIL PRESS WARN circuit breakers on the right hand circuit breaker panel

When the

in the

cockpit,

and L and R OIL PRESS LO annunciators located in the

glareshield warning

annunciator

panel.

The

oil pressure warning switches close at a decreasing pressure of 40 2 psi and open at an increasing pressure that is a maximum of 30 percent above the closing pressure (Ref. Figure 4). When one of the switches closes, a circuit

is

completed between

the

appropriate circuit breaker and the warning annunciator panel to illuminate the L or R OIL Chapter 31-50-00 for additional information on the warning annunciator system.

PRESS LO annunciator. Refer to

O1L SYSTEM CHIP DETECTORS

engines is contaminated with metal particles, L CHIP DETECT or R CHIP the caution/advisory annunciator panel (Ref. Figure 5). The presence of metal particles in the oil is disclosed by a magnetic chip detector installed in the reduction gearbox housing of each engine. The chip detector consists of two parts, the valve housing and the detector body. The valve housing is threaded to accept the detector body and is installed into an adapter mounted to the gearbox housing. The valve housing contains a spring loaded valve which is self-closing when the detector body is removed, allowing removal of the chip detector body without the loss of engine oil from the gearbox housing. The chip detector body has two magnetic poles on one end (which are in contact with the engine oil when the detector is installed in the engine) and an electrical connector on the other end. Electrical power to the chip detectors is through the 5-amp LEFT and RIGHT CHIP DETR circuit breakers on the right hand circuit breaker panel in the cockpit (Ref. Figure 4). Metal particles in the engine oil are attracted to the magnetic poles. When enough particles are present to bridge the gap between the poles, an electrical circuit through the chip detector will be completed to the appropriate caution When the

lubricating

oil in

DETECT annunciators

are

one or

both

illuminated

on

annunciator.

CAUTION:

Anytime

the oil system is contaminated

by metal particles,

the oil cooler must be

replaced and

the oil

prevent engine damage. In addition, all airplane components and associated plumbing utilizing the engine oil system, such as propeller governors, must be flushed until free of system flushed

to

contamination.

79-30-00Page

1

Hawker Beechcraft

Corporation ORIGINAL

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

As Received

By

ATP

L

OIL

PRESSURE

R

LO

OIL

"RESSURE

~´•-A’J oo "V/ oo~

C GLARESHIELD

WARNING

ANN~NCIATOR

A

DETAIL

X ~8’:

, I,

I, s-, , ,I,

yi C

o

30

;ao

60 50

FUELFLCY

5-aC) OpH

LEFT ENGINE OIL TE~PERAIUR’ AND PRESSURE INDICATOR

i?i

PANEI

X

00

50

60

FUELFLOW

,_

~3 4

1 501

P"H

taoI

XiOO

Lo20

RIGHT ENGINE OIL TEMPERATURE AND PRESSURE INDICATOR

a

OIL PRESSURE TRANSDUCER

200

50

OIL PRESSURE LOW

DETAIL

B

WARNING

S’rlITCH

OIL TEMPERATURE BULB

DETAIL DETAIL

D

D

C C9dFL798

Engine

608

C

Oil Pressure and Temperature Indicating System thru FL-119 and FL-121; FM-1 thru FM-8)

(FL-1

Figure

May

1/0879I30-00

1

A24

Hawker Beechcraft

Corporation ORIGINAL

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

As Received ATP

i

OIL

?RESSURE

By

LC R

OIL

PRESSURE

LO

i..Y

ARESHIELD

ANNUNCIATORnO FANEL

WARNING

DETAIL

Ao

3j´•C1~ C

o

k´•: B B 8.8

8 B 88

ll~ii!

Ii:

~Cr3 ~I

OIL PRESSURE TRANSDUCER P

LEFT ENGINE OIL TEM?ERATURE ANC PRESSURE INCICAIOR

DETAIL

RIGHT ENGINE OIL TEMPERATURE AND PRESSURE INDICATOR

B

iOW OIL PRESSURE WARNING SWITCHH

OIL TEMPERATURE eUL6

0 DETAIL

DETAIL

C

D

C94FL79B13Bb

Engine

C

Oil Pressure and Temperature Indicating System FL-122 and After; FM-9 and After)

(FL-120,

Figure

A24

2

79-30-00Page

3

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

5A

TRIPLE FED BUS

A R

OIL

O

t--t--------~-l

IA

CI

t-i--t--i

IB

IEI´•1P

5 TRIPLE FED SUS

F R

OIL

?RESS ENGINE TEMP BULB

RH

El

121

GI

i--i---------~

HI

t-i--c---l

B

n

IISVDC

IN

OU7

IAICOl~ivlON D

RH ENGINE OIL TEMP ?RES ING

+28VDC

OI1

CASE

GND

n

RH eNGINE OII PRESSURE IRANS~UZER

5A

TRIPLE FED aus

Al OIL

I

I

A

TEMP

5A

TRIPLE FED BUS L

OIL

PRESS L~ ENGINE TEMP BULB

Ei

l-t------(

Gi

H

ORIGINAL As

Recelvad BY LH ENGINE TEM? S PRES

OILIi\lG

ATP

I

IC

+28VDC

IBi

+5VDC

OIL

IN

OUT

A

eOMMON

D

EASE

GND

LH ENGINE OII P4ESSURE TRANSCUC-R

350603-098

Engine

May

1/08Page

4

Oil Pressure and

79I30-00

C

Temperature Indicating System Schematic Figure 3

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ENGINE OIL CHIP DETECTOR L

5A

B

GEN BUS L

CHIP DETECT

L CHI? DETR L OIL PRES LO

5k

IRIPLE FED BU’

h

OIL WARN L

PRESS

CAUTION/ADVISORY ANNUNCIATOR PANEL

ANN FAULT DET. PCB

iOW OIL PRESSURE SWITCH LH

R DIL PRES LO

5P.

TRIFLE FED

eus

R

OIL WARN

PRESS

RH iOW OIL PRESSURE SWITCH

ANN FAUL1 DET. 2 FCB

B

5A R

_

G_N 3US

A

R CHIP DETR

WARNING ANNUNCIATOR PANEL

R

ENGINE OIL CHIP DETECTOR

R

CHIP DETECT

CAUTION/ADVISORY ANNUNCIATOR PANEL

i

350-603-097

C

ORIGINAL As Received

By

ATP

Chip

A24

Detector and Low

Engine Oil Pressure System Figure 4

Schematic

79-30-00

May

1/08Page

5

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ORIGIMAL As Received BY ATP

U

O

A

B

i

DETAIL

MAGNETIC POLE

A

VALVE HOUSING

DETECTORBODY

MAGNETIC POLE

CHIP

DETAIL

i

CHIP OEIECI, ANNUNCIATGR

CHIP

IF

DETECI

R

CHIP

DETECI

~J

CHIP DETECT ANNUNCIATOR

INSTALLED CAUTION/ADVISORY

ANNUNeIATOK

DETAIL

Engine

1/08~"ms

B

,R

~/L

OPIIONAL

May

DETECTOR

79-30-00

Oil

PANEL

C

C94FL798

387

C

Chip Detector System Figure 5

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INDICATING- TROUBLESHOOTING

Chart 101

Engine ENGINE STEP 1

Is there

Oil

Temperature

Bulb

OPERATING, BUT NO OIL TEMPERATURE INDICATED

continuity

between the

temperature bulb and the oil temperature gage?

YES

Replace

the temperature bulb.

NO

Restore

continuity.

Chart 102

Indicating System

Oil Pressure

ENGINE OPERATING, BUT NO OIL PRESSURE INDICATED STEP 1

Is the left

or right OIL open?

breaker

STEP 2

STEP 3

Is the

engine oil level

Is there

PRESS circuit

low?

continuity between the

left

or

011 PRESS circuit breaker and

right appropriate

the

STEP 4

Is there

oil pressure

continuity

gage?

between the

transducer and the oil pressure

gage? STEP 5

Perform

a

functional check of the

transducer

as

YES

Close the circuit breaker.

NO

Proceed to

YES

Replenish (Ref. 12-10-00).

NO

Proceed to

Step

3.

YES

Proceed to

Step

4.

NO

Restore

YES

Proceed to

NO

Restore

continuity.

NO

Replace

the transducer.

Step

2.

continuity. Step

5.

outlined under OIL

PRESSURE TRANSDUCER FUNCTIONAL TEST. Is the transducer

A24

functioning properly

79-30-00

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 103

Chip Detectors CHIP DETECTORS NOT PROVIDING ANNUNCIATION SIGNAL STEP 1

IstheleftorrightCHIP open?

DETRcircuit

breaker

STEP 2

Is there

INO

continuity between the

left

or

CHIP DETR circuit breaker and

right appropriate chip

the

STEP 3

Is there

continuity

detector?

between the

chip

detector and the annuciator fault detection STEP 4

Is there

pcb?

continuity

between

annunciator fault detector the

caution/advisory panel?

STEP 5

Inspect the chip

pcb

and

annuciator

detector

as

outlined

under CHIP DETECTOR INSPECTION procedures. Does the chip meet the inspection requirement?

Page

10279-30-00

YES

Close the circuit breaker.

i

Proceed to Step 2.

YES

Proceed to

NO

Restore

YES

Proceed to

NO

Restore

YES

Proceed to

NO

Restore

NO

Replace faulty chip

Step

3.

continuity. Step

4.

continuity. Step

5.

continuity.

detector.

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

INDICATING

MAINTENANCE PRACTICES

CHIP DETECTOR REIVIOVAL chip detector (Ref. Figure 201) consists of two parts; the body (2) and the valve housing (5). These parts are procurable individually. If one part of the chip detector requires replacement, replace both parts. Never mix parts from one chip detector with those from another. The not

a.

Remove all electrical power from the

b.

Remove the lower aft

c.

Disconnect the electrical connector

d.

Cut the

airplane.

engine cowling (Ref. Chapter 71-10-00). (1) from

the

chip

detector

body (2).

safetb wire and remove the chip detector body (2) from the valve housing (5). The spring-loaded valve housing (5) will close when the chip detector body (2) is removed, thereby preventing the loss of from the gearbox. Discard the O-rings (3 and 4).

in the valve

any oil e.

If 1.

required, Place

(5) 2.

the valve

remove

a

housing (5)

suitable container under the

as

follows;

gearbox

to catch the oil that will be released when the valve

housing

is removed.

Cut the

safety

wire and

remove

the valve

housing (5)

from the

adapter (7).

Discard the

O-ring (6).

CHIP DETECTOR INSTALLA TION

chip detector (Ref. Figure 201) consists of two parts, the body (2) and the valve housing (5). These parts are procurable individually. If one part of the chip detector requires replacement, replace both parts; do not mix parts from one chip detector with those from another.

The not

a.

If 1.

2.

required, install Install

a new

housing (5)

as

O-ring (6)

in the valve

housing (5).

Install the valve

safety

housing (5)

in the

adapter (7). Torque the valve housing (5)

to 175 to 200

inch-pounds

and

inch-pounds

and

wire.

b.

Install

c.

Install the detector

safety

follows;

the valve

new

O-rings (3

and

4)

body (2)

on

the

chip detector body (2).

in the valve

housing (5). Torque

the detector

body (2)

to 45 to 55

wire.

required to fit the chip detector wrench flats, overtightening can result in fracturing of the chip detector bodywith just "normal" hand wrenching pressure. Therefore, only tighten the chip detector body with a calibrated torque wrench and apply no more than 45 to 55 inchpounds of torque to the detector body.

CAUTION: Due to the size of the wrench the

d.

Connect the electrical connector

(1)

e.

Check the oil level in the

oil tank and add oil

engine

to the

chip

detector as

body (2).

required (Ref. Chapter 12-10-00).

79-30-00

1/08

Hawker BeeChCraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

I.

ELEC~RICAL CHIP

~ONNECTOR

DETCZTR

3.

O-RIUG

~t3

BODY

A

C´•\

i.

O-RING:VALV~

5.

VAL\/_

6.

O-RI~IG

SEAT)

EOUSING

ADAPT ER

PTAL NIGROyB

"li~

As Received

i

a

5

DETAIL

A

34 1

csan79e1390 c

Chip

Detector Installation

Figure

May

79-30-00

201

A24

Corporation

Hawker Beechcraft

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

OIL PRESSURE TRANSDUCER REMOVAL a.

Remove all electrical power from the

b.

Remove the

c.

Cut the

d.

Cut the

e.

engine cowling (Ref. Chapter 71-10-00).

safety

safety O-ring (3). If

required,

airplane.

wire and disconnect the electrical connector from the transducer wire and

remove

from the boss

on

remove

the reducer

the accessory

the transducer

(4) from

the reducer

(4).

bushing (2) (Ref. Figure 202).

Discard the

the reducer

bushing (2)

bushing (2) as follows: cut the safety wire and gearbox housing and discard the O-ring (1).

remove

OIL PRESSURE TRANSDUCER INSTALLATION a.

If

bushing (2) (Ref. Figure 202)

install the reducer

required,

O-ring (1)

1.

Install

a new

2.

Apply (2).

a

3.

Thread the reducer

on

the reducer

thin coat of lubricant

bushing

i2) to 40

O-ring (3)

Install

a new

c.

Apply

a

d.

Thread the transducer

on

No. 1, Chart 1,

the transducer

thin coat of lubricant

(Item

(4) into the bushing (2).

Connect the electrical connector to the transducer

f.

Restore electrical power to the

Motor the

engine with the

gearbox housing. Torque

bushing

the reducer

79-00-00)

to the external threads of the transducer

the transducer

(4), tighten hand-tight

and

(4)

to 40

safety

inch-pounds

(4).

and

safety

wire.

airplane.

long enough (4).

starter

for oil leaks at the transducer

to the external threads of the reducer

the accessory

bushing (2). Torque

e.

g.

79-00-00)

(4).

No. 1, Chart 1, reducer

follows:

bushing (2).

bushing (2) into the boss on inch-pounds and safety wire.

b.

wire it to the reducer

(Item

as

to obtain

an

oil pressure

reading. Shut the engine down

and check

CAUTION: Obsen/e the sfa~ter operating limits of 30 seconds ON, 5 minutes OFF; 30 seconds ON, 5 minutes OFF; 30 seconds ON, then 30 minutes OFF. h.

Install the

engine cowling (Ref. Chapter 71-10-00).

LOW OIL PRESSURE SWITCH REMOVAL a.

Remove all electrical power from the

b.

Remove the

c.

Cut the

safety wire and

d.

Cut the

safety wire and O-ring (8).

airplane.

engine cowling (Ref. Chapter 71-10-00). disconnect the electrical connector from the low oil pressure switch remove

the switch

(9)

from the tee

(5)

mounted

on

the accessory

(9) (Ref. Figure 202).

gearbox housing.

Discard the

n24

79-30-00

Page

yaM302

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

ORIGINAL By

As Received ATP

3

A

I.

O-RING RECUCER

3. d.

5.

3USHING O-RING OIL PR~SSURE TRANSDUCER TEE

~i

5

,i´•

6. aULB

9.B. Lowo-RINeOIL

FRESSURE

SWITCH 1´•~2

9

DETAIL

7

A

C94’L79B

Oil Pressure Transducer, Low Oil Pressure Switch and Oil Figure 202

Page

yaM402

1/08

79-30-00

Temperature

39

Bulb Installation

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LOW OIL PRESSURE SWITCH INSTALLA TION

O-ring (8)

a.

Install

b.

Thread the switch

a new

inch-pounds

and

on

the low oil pressure switch

(9) into the tee (5) mounted safety wire to the tee (5).

c.

Connect the electrical connector to the switch

d.

Restore electrical power to the

e.

Motor the

engine with the

for oil leaks at the switch

on

(9) (Ref. Figure 202).

the accessory

gearbox housing. Torque

and

(9), tighten hand-tight

safety

the switch

(9)

to 30

wire.

airplane.

starter

long enough to obtain

an

oil pressure

reading.

Shut the

engine down and check

(9).

CA UTION: Observe the stalfer operating limits of 30 seconds ON, 5 minutes OFF; 30 seconds ON, 5 minutes OFF; 30 seconds

f.

Install the

ON, then 30 minutes OFF.

engine cowling (Ref. Chapter 71-10-00).

OIL TEMPERATURE BULB REMOVAL a.

Remove all electrical power from the

b.

Remove the

c.

Cut the

d.

Cut the

airplane.

engine cowling (Ref. Chapter 71-10-00).

safety

wire and disconnect the electrical connector from the

safety wi re and disconnect the temperatu re Discard the gasket (6).

bulb

(7)

the tee

temperature bulb (7) (Ref. Figure 202).

mou nted on

the accessory

gearbox

housi ng.

OIL TEMPERA TURE BULB INSTALLA TION a.

b.

Install

a new

Install the

the tee

gasket (6)

on

the temperature bulb

temperature bulb (7) into the

tee

(5)

(7) (Ref. Figure 202).

mounted

on

c.

Connect the electrical connector to the temperature bulb

d.

Restore electrical power to the

e.

the accessory

gearbox housing

and

safety

wire to

(5).

Motor the

engine with the

(7), tighten hand-tight

and

safety

wire.

airplane.

starter

long enough to obtain (7).

an

oil pressure

reading.

Shut the

engine down

and check

for oil leaks at the temperature bulb

CA UTION: Obsen/e the starter operating limits of 30 seconds ON, 5 minutes OFF; 30 seconds ON, 5 minutes OFF; 30 seconds f.

Install the

ON, then 30 minutes OFF.

engine cowling (Ref. Chapter 71-10-00).

OIL TEMPERA TURE BULB FUNCTIONAL TEST a.

Remove all electrical power from the

b.

Remove the

airplane.

engine cowling (Ref. Chapter 71-10-00).

79-30-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

wire and disconnect the electrical connector from the

c.

Cut the

safety

d.

With

ohmmeter make

an

ohms to 140.9 ohms for

sure

that resistance between

temperatures from

20" C to

pins

temperature bulb (7) (Ref. Figure 202).

A and B of the

temperature bulb (7) is from 82.2

140" C.

e.

Connect the electrical connector to the temperature bulb

f.

Install the

(7), tighten hand-tight

and

safety

wire.

engine cowling (Ref. Chapter 71-10-00).

OIL PRESSURE TRANSDUCER FUNCTIONAL TEST a.

items

required

perform

this test:

The

following

1.

Regulated supply of dry, filtered, compressed nitrogen

2.

Pressure gage.

3.

Plumbing necessary

4.

Digital

voltmeter calibrated in .01-volt increments.

5.

28vdc

powersupply.

are

to

to connect transducer to pressure

Remove the transducer

c.

Connect the

d.

Connect the voltmeter, resistor and power

e.

Apply

f.

Slowly

nitrogen

no

less than 200

psi.

supply.

instructed under OIL PRESSURE TRANSDUCER REMOVAL.

b.

as

at

pressure

source

and pressure gage to the transducer

supply

to the transducer

(Ref. Figure 203).

(Ref. Figure 203).

pressure to the transducer at a slow steady rate until 200 psi is indicated on the pressure gage. As the pressure rises, record the output voltage for each input pressure interval listed in Chart 201 The output voltage must fall within the range shown in Chart 201 for each specific interval. reduce the pressure, as the pressure lowers record the output voltage for each input pressure interval listed in Chart 201. The output voltage must fall within the range shown in the chart for each specific interval.

CAUTION: Bleed the pressure down to O g.

Disconnect all of the test

h.

Install transducer in the

Replace

Page

psi before disconnecting

equipment from

airplane

as

source.

the transducer.

instructed under OIL PRESSURE TRANSDUCER INSTALLATION.

any transducer that fails to meet the

79-30-00

the transducer from the pressure

requirements of this

test

procedure.

P~24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

Chart 201 Oil Pressure Transducer

Output Voltages

INPUT PRESSURE IN PSI

OUTPUT VOLTAGE IN VDC

I

0

.10 to .10

25

.53 to .73

50

1.15to 1.35

75

1.78 to 1.98

100

2.40 to 2.60

125

3.03 to 3.23

150

3.65 to 3.85

175

4.28 to 4.48

200

4.90 to 5.10

PRESSURE

GAGE

ORIGINAL As Received

By

NIIROGEI\1 BOTTLE

ATP

-_:i-~~8 VDC POWER SUPPLY

A

COMMON

ei´•

5

Ci+

28

c

CASE

voc

our

VOC

IN

GNO

IRANSDUCER UNDER TES7

C94FL7781aBI

Oil Pressure Transducer Functional Test Schematic

Figure

A24

203

79-30-00May

1/08

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

LOW OIL PRESSURE WARNING SWITCH FUNCTIONAL TEST a.

The

following

items

1.

Regulated supply

2.

Air pressure gage calibrated in .01

3.

Plumbing

4.

Continuity tester.

are

required

of

perform

this test:

dry, filtered, compressed psi

air at

airplane

as

no

less than 50

psi.

increments.

necessary to connect switch to pressure

Remove the switch from the

b.

to

supply.

instructed under LOW OIL PRESSURE WARNING SWITCH

REMOVAL. c.

Connect the pressure

d.

Connect the

e.

With

f.

Apply pressure to the switch at a slow steady rate until 50 psi is indicated on the pressure gage. There should be no continuity across the normally closed contacts; if there is, replace the switch.

no

source

continuity

pressure

tester to the

applied

Reduce the pressure at

g.

a

to the

normally

closed contacts of the switch

switch, check for continuity. If

slow

actuate between 38 and 42

h.

and pressure gage to the switch.

steady rate, noting at what psi; if not, replace the switch.

no

(pins

continuity

pressure

A and

B).

is indicated

continuity

replace

the switch.

is indicated. The switch should

Slowly increase the pressure, noting at what pressure there is no longer continuity. The difference between decreasing and increasing actuation points shall be a maximum of 30% of the actual decreasing point.

NOTE: To find the maximum

increasing point for a specific decreasing point (Ref.

Chart

202) locate

the

the

decreasing

point Step g, under ACTUATE ON DECREASE PSI and read across under ACTUATE ON INCREASE PSI. The increasing actuation pressure noted in Step h, must not be higher than this value. If it noted in

is, replace switch.

Chart 202 Low Oil Pressure

Warning

ACTUATE ON DECREASE PSI

ACTUATE ON INCREASE PSI

40.5

52.65

40.0

52.00

39.5

51.35

39.0

50.70

38.5

50.05

38.0

49.40

the check four times to confirm

i.

Repeat

j.

Disconnect the test equipment from the switch.

consistency.

CAUTION: Bleed the air pressure down to O

May

1/08Page

208

Switch Actuation Points

79-30-00

psi before disconnecting

the air

supply from

the switch.

A24

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

k.

Install the switch in the

INSTALLATION.

airplane as instructed under LOW OIL PRESSURE WARNING SWITCH Replace any switch that does not meet the requirements of this test procedure.

CHIP DETECTOR INSPECTION The

chip detector consists of two parts, the body and the valve housing (Ref. Figure 201). These parts are not procurable individually. If one part of the chip detector requires replacement, replace both parts; do not mix parts from one chip detector with those from another. a.

b.

Remove the

Inspect Pratt

c.

With

a

chip

the chip Whitney

d.

Inspect

body

as

described under CHIP DETECTOR REMOVAL.

detector for metal material

PT6A-60A

continuity

magnetic poles

detector

Engine

on the magnetic poles. If any metal material is found, refer to the Maintenance Manual for the proper action to be taken.

tester connected to the electrical

and check for

the threads

on

the

continuity.

chip

detector

If there is

body

pins on the chip detector body, place a steel no continuity, replace the chip detector.

and valve

housing

and

replace

any

chip

bar

across

detector with

the

damaged

threads. e.

Check the electrical connector for bent, broken

f.

Check for

signs

or

burned

pins.

of excessive oil

leakage in the valve housing, which would indicate a deteriorated or damaged functioning properly. If required, remove the valve housing as instructed under CHIP DETECTOR REMOVAL. The O-ring valve seat can then be replaced. If the valve is sticking or has a broken spring, replace the complete chip detector. Install the valve housing or new chip detector as instructed O-ring

valve seat

or a

valve that is not

under CHIP DETECTOR INSTALLATION.

g.

Install

a new

O-ring

on

the

chip

detector

body

and install the

chip

detector

body

in the valve

housing

as

instructed under CHIP DETECTOR INSTALLATION. h.

n24

Check the oil level in the

engine

oil tank and add oil

as

required (Ref. Chapter 12-10-00).

79-30-00

Page

yaM902

1/08

C H A PT E R

STARTING

Hawker Beechcraff

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

CHAPTER 80

STARTING

TABLE OF CONTENTS

SUBJECT

PAGE 80-00-00

Starting- Description

A24

and

Operation.

.1

80-CONTENTS

1/08Page May

1

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

List of Effective CH-SE-SU

PAGE

DATE

80-LOEP

1

May

1/08

80-CONTENTS

1

May

1/08

80-00-00

1

May 1/08

A24

Pages

80- LO E P

May

1/08Pagel

Hawker Beechcraft

Corporation

SUPER KING AIR B300/B300C MAINTENANCE MANUAL

STARTING

DESCRIPTION AND OPERATION

The

engine is equipped with a starter/generatorwhich serves as a starter during engine cranking and as a generator engine is started. Under adverse starting conditions, a ground power unit (GPU) may be utilized. The GPU should have a capacity of 600 amperes (minimum intermittent) output and should be adjusted to produce 28.25 f 0.25 volts. A GPU should not be used unless the airplane battery has an indicated charge of at least 20 volts, and the battery should be ON to absorb transients present in some GPUS. If the battery does not indicate at least 20 volts, it must be charged or replaced before connecting the GPU to the airplane. The starter has operating limitations after the

of 30 seconds on, 5 minutes off, 30 seconds on, 5 minutes off, 30 seconds on, then 30 minutes off. Refer to the Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual for complete starting instructions. When

operating as a generator; the unit is capable of delivering 300 amps at 28.25 f 0.25 volts. For a more complete description and operation or for maintenance of the system refer to Chapter 24-30-00 or to the appropriate supplier publication.

~a4

80-00-00Page

1

SUPER KRVG

AI~350

AND 350C

(MODEL B300 AND B300C)

R´•IIAINTENANCE M[ANUAL SUPPLEIMENT for B300 AND B300C AIRPLANES OPERATED IN CANADA

This and 350C (Model Manual part number

P/N 130-590031-49B

the

Super King

8300C

130-590031-11

Air 350

Maintenance and subsequent.

Reissued:

September,

1992

PUBLISHED BY COMMERCIAL PUBLICATIONS

BEECH A~IRCRAFT CORPORATION WICEI~IIA. KANSAS 61301 U. S. k

ci3eechcraft A~ylkanCompany

M´•mb´•rslOlM*

1’1 ~I

G´•n´•rollri~an

C H A PT E R

SERVICING

BEECHCRAFT MODEL B300 MAINTENANCE MANUAL SUPPLEMENT

12

SERVICING

TABLE OF CONTENTS CHAPTER

SUBJECT

PAGE

12-00-00

Servicing

....´•´•´•´•´•´•´•..1

General 12-20-00

.1

Schedule;d Servicing :Interior Care Cleaning Leather

or

Vjn;l’´•

I

Carpets Wool 6r Wool Blends and Cotton

I 1

"END"

I2-CONTENTS

Page 1 September, 92

BEECHCRAFT MODEL 8300 MAINTENANCE MANUAL SUPPLEMENT

CHAPTER 12 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT

PAGE

DATE

12-Effectivity

1

September,

1992

12-Contents

1

September,

1992

12-00-00

1

September, 1992

12-20-00

1

September, 1992

"END"

12-EFFECTIVITY

Page 1 September, 92

BEECHCRAFT MODEL B300 MAINTENANCE MANUAL SUPPLEMENT

SERVICING

GENERAL

in which the airplanes conforming the requirements for export to Canada differ from the standard Model B300 and B300C airplanes. Refer to the basic maintenance for the manual servicing and maintenance procedures common to both the export version and the standard version of the Model 0300 and 03000 airplanes. to

NOTE This

supplement is

to be used in the BEECHCRAFT Model B300 and B300C Maintenance Manual Part Number 130-590031-11. ´•The information contained herein is confined to those particulars

conjunction

with

"END"

12-00-00

Page 1 September, 92

8EECHCRAFT MODEL 8300 MAINTENANCE MANUAL SUPPLEMENT

d. Apply the suds to the stained of the material.

SCHEDULED SERVICING

area

INTERIOR CARE

The

certification

basis of the Models 8300/83000 requires that interior materials be fire resistant. In order to assure that these materials retain their fireresistant capability, the following procedures mustbe observed.

CLEANING LEATHER OR VINYL

Use a piece of cheese cloth e. e"ed in clean water to remove the SUdS film. Use a dry, soft piece of f. cloth to dry the dampened area.

After

The color of leather may be a surface finish only. Do not rub the leather materials with hard When working or course materials. in the cabin, use protective covUse only the upholstery. ers on mild detergent and soft damp cloths to clean soiled leather. remove

10

occasional any stain can a

soft, damp

cloth,

NOTE Never water

saddle

use

polish,

oil,

or

leather

furniture ammonia any kind on

soap,

of

Dust has impurities which may affect fabrics, therefore vacuum at regular intervals. Dry clean at regular intervals accumulated. has before excessive soil of and Actual draperies cleaning dry upholstery must be performed by a professional dry cleaner only.

After 10 dry cleanings, wool or wool blend fabrics must be replaced or retreated to of fire-resistive ensure their retention properties in accordance with FAR 23.853.

varnish,

solvent

or

vinyl.

a.

Use lukewarm

b.

Do not dry clean

or

cool water or

After 5 dry cleanings, cotton fabrics must be replaced or retreated to ensure their retention of fire-resistive properties in accordance with FAR 23.853.

only.

steam clean,

Using Castile, Ivory or any other work up a thin layer of suds of cheesecloth. piece

c.

mild on

a

cleanings,

or

WOOL OR WOOL BLENDS AND COTTON

light film of grit and dust, dusting is required. Almost be removed by washing with

a

cheese

the carpet must be retreated to ensure retention of fire-resistive properties in accordance with FAR 23.853. Cleaning is to be accomplished with a water basesolution. Dry cleaning of the carpet is not recommended.

CAUTION

an

soap

CARPETS

replaced

To

damp-

CAUTION

soap,

Do not wash fabrics with water.

"END"

12-20-00

Page

1

September, 92