ATP INDEX COPYRIGHT
2002
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ATP Grid Index to Manufacturer’s Publications:
Raytheon Aircraft Co. Bonanza V35B; F33A;
F33C; A36; A36TC; B36TC
Maintenance Manual Section
Topic
General Information
Title Page Manufacturer’s Introduction Record of Revisions Record of
Temporary Revisions Letter of Transmittal (Highlights
of Changes)
Aircraft General
05.00.00
Time Limits/Maintenance Checks
05.00.00
List of Effective
05.10.00 05.10.00 05.20.00
Pages
Time Limits
Overhaul and
Replacement
Scheduled Maintenance Checks
06.00.00
Dimensions and Areas
06.00.00
List of Effective
06.00.00 07.00.00 07.00.00
07,00.00
Pages
General
Lifting and Shoring List of Effective Pages General
08.00.00
Leveling and Weighing
08.00.00
List of Effective
08.00.00
Pages
General
09.00.00
Towing and Taxiing
09.00.00
List of Effective
08/19/2002
Schedule
Pages
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
1 of
6
Section
09.00.00
10.00.00 10.00.00 10.00.00
Topic General
Parking, Mooring, Storage, and Return List of Effective Pages General
11.00,00
Placards and Markings
11.00.00
List of Effective Pages
11.00.00
General
11.20.00
Exterior Placards and
12.00.00
Servicing
12.00.00
List of Effective Pages
12.00.00
General
12.10.00
Replenishing
12.20.00
Scheduled Service
Airframe
Markings
Systems Airframe
20.00.00
Standard Practices
20.00.00
List of Effective Pages
20.00.00
to Service
General
20.01.00
Torque Wrenches
20.02.00
Electrostatic Discharge Sensitivity
20.03.00
Electrical Bonding
20.04.00
Control Cables and Pulleys
20.05.00
Bearings
20.06.00
Tube and Hose Assemblies and Fittings
20.07.00
Locking
20.08.00
Airplane
20.09.00
Corrosion
Devices
Finish Care
Conditioning
21.00.00
Air
21.00.00
List of Effective Pages
21.40.00 21.50.00
Heating and Ventilating System Cooling
23.00.00
Communications
23.00.00
List of Effective Pages
23.10.00 23.10.00
08/19/2002
Speech
Communication
Ground Communication System
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
2 of
6
Section
23.60.00
Topic Static Discharging
24.00.00
Electrical Power
24.00.00
List of Effective Pages
24.30.00
DC Generation
Standby Generator
24.31.00 24.40.00
External Power
24.50.00
AC Electrical Load Distribution
25.00.00
Equipment/Furnishings
25.00.00
List of Effective Pages
25.00.00
General
25.60.00
Emergency
27.00.00
Flight Controls Record of Temporary Revisions
27.00.00
List of Effective Pages
27.00.00
27.00.00
General
27.10.00
Aileron and Tab
CE-748,CE-772 and After;CJ´•149 and After;D-10097,D-10120
27.10.00
and After;E-I111,E-1241 Thru E-21111 Except E-1946 and
E-2104;EA-1 Thru EA-388 Except EA-320 After, EA-320, EA389 E-1946, E-2104, E-2111
27.11.00 27.20.00
Rudder and Tab
27.20.00
F33A, F33C, A36, A36TC AMD B36TC
27.21.00
V35B
27.30.00
Elevator and Tab
Stall Warning/Safe Flight System
27.31.00 27.50.00
Flaps
27.70.00
Gust Lock and
Dampener
28.00,00
Fuel
28.00.00
List of Effective Pages
28.00.00
General
28.10.00
Storage
28.20.00
Distribution
28.40.00
Indicating
30.00.00
Ice and Rain Protection
30.00.00
List of Effective Pages
30.00.00
08/19/2002
After
General
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
3 of
6
Section
Topic
Propellers/Rotors
30.60.00
32.00.00
Landing Gear
32.00.00
List of Effective
Pages
32.00.00
General
32.10.00
Main Gear and Doors
32.20.00
Nose Gear and Doors
32.30.00
Extension and Retraction
32.40.00
Wheels and Brakes
32.50.00
Steering
32.60.00
Position and Warning
33.00.00
Lights
33.00.00
List of Effective
Pages
33.20.00
Interior
33.40.00
Exterior
34.00.00
Navigation
34.00.00
List of Effective Pages
34.10.00
Flight Environmental
34.40.00
Independent
Position Determining
35.00.00
Oxygen
35.00.00
List of Effective
35.00.00
General
36.00.00
Pneumatic
36.00.00
List of Effective
36.00.00
Data
Pages
Pages
General
39.00.00
Electric Panels Parts and Instruments
39.00.00
List of Effective
Pages
39.00.00
General
39.10.00
Instrument and Control Panels
39.20.00
Electrical and Electronic Equipment Racks
Structures
51.00.00
Standard Practices
51.00.00
List of Effective
51.00.00
08/19/2002
Structures
Pages
General
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
4 of
6
Section
Topic
52.00.00
Doors
52.00.00
List of Effective Pages
52.00.00
General
52.10.00
Passenger/Crew Cargo
52.30.00
53.00.00
Fuselage
53.00.00
List of Effective Pages
Plates/Skin
53.30.00 55.00.00
Stabilizers
55.00.00
List of Effective Pages
55.00.00
General
55.10.00
Horizontal Stabilizer
55.20.00
Elevator and Rudder
55.30.00
Vertical Stabilizer
55.40.00
Rudder
56.00.00
Windows
56.00.00
List of Effective
General
56.10.00
Flight Compartment Passenger Compartment
57.00.00
Wings
57.00.00
List of Effective Pages
57.00.00
General
57.30.00
Plates/Skins
57.40.00
Attach Fittings
57.50.00
Flight Surfaces
Canard
Pages
56.00.00
56.20.00
or
Propeller/Rotor 61.00.00
Propellers/Propulsors
61.00.00
List of Effective Pages
61.10.00
Propeller Assembly
61.20.00
Controlling
Power Plant
08/19/2002
Copyright
Aircraft Technical Publishers BC
0220
MM
Page
5 of
6
Section
Topic
71.00.00
Power Plant
71.00.00
List of Effective Pages
71.00.00
General
71.10.00
Cowling to Continental Aircraft
72.00.00
Engine (Refer
73.00.00 73.30.00
Engine Fuel and Control List of Effective Pages Fuel Flow Indicating
74.00.00
Ignition
74.00.00
List of Effective Pages
73.00.00
74.00.00
General
74.20.00
Distribution
77.00.00
Engine Indicating
77.00.00
List of Effective Pages
77.00.00
General
79.00.00
Oil
99.00.00
List of Effective Pages
99.00.00
General
80.00.00
Starting
80.00.00
List of Effective Pages
80.10.00
Cranking
81.00.00
Turbines
81.00.00
List of Effective Pages
81.00.00
Engine Manuals)
General
91.00.00
Charts
91.00.00
List of Effective Pages
91.00.00
Chart 1 Consumable Materials
91.00.00
Charts 2, 4 and 5
91.00.00
Installation of Flared Fittings
91.00.00
Chart 3 Thread Lubricants
End of Index
08/19/2002
Copyright
Aircraft Technical BC
0220
MM
Publishers
Page
6 of
6
NIFGI INTRO
Ral~heon Aircraft BEECH BONANZA SERIES
V35B F33A F33C A36
A36TC B36TC
(D-10097, D-10120 and After) (CE-748, CE-772 and After) (CJ-149 and After) (E-llll, E-1241 and After) (EA-I thru EA-272 Except EA-242) (EA-242, EA-273 and After)
Nlaintenance Manual
NOTE: This manual
was
formerly
called the Beechcraft Bonanza Series
Maintenance Manual.
Copyright P/N: 36-590001-9 Issued:
May
9, 1980
0
Raytheon
Aircraft
Company 2002 P/N: 36-590001-9A23 Revised: june 28, 2002
Published
By
RAVTH EO N AIRCRAFT COM PANY
P.O. Box 85
Wichita, Kansas 67201 U.S.A
NOTE Where Beech Aircraft
Corporation is referred to in this publication, Raytheon Aircraft Company.
it will be taken to read
EXPORT STATEMENT
Exported under the authority of license exception: TSU. ’7hese commodities, technology or software were exported from the United States in accordance with Export Administration Regulations. Diversion contrary to U.S. law
prohibited.
i
Raytheon Ai
rcraatRaytheon
Company
Member of GAMA General Aviation
CAIIA
Manufacturers Association
RECORD OF REVISIONS
MFG REV
DESCRIPTION
NO
ISSUEDATE
ATPREVDATE
INSERTEDBY
A22
See
Highlights
11/10/00
3/5/01
ATP/RCL
A23
See
Highlights
6/28/02
9/4/02
ATPNDR
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
LIST OF EFFECTIVE REVISIONS
Always destroy superseded pages when you
insert revised pages.
Title Page
June 28, 2002
"A"
Page
A23
"B"
Page
A23
PART NUMBER
DATE
CHAPTERS AFFECTED
36-590001-9A
May 9, 1980
Original
36-590001 -9A 1
October 10, 1980
Introduction, 5, 6, 11,24, 25, 30,34,36,73
36-590001-9A2
January 28,
36-590001 -9A3
March 12, 1981
36-590001-9A4
January 20,
1981
1982
Introduction, 12, 21, 25, 33, 35, 61,71,73, 77, 81 5, 11,32, 57
Introduction, 6, 12, 21, 23, 24, 25, 27, 28, 34, 39, 57, 61,81, 91
36-590001 -9A5
February 18,
36-590001-9A6
October 27, 1983
1983
Introduction, 5, 6, 27 Introduction, 5, 6, 12, 21, 24,
27,28,30,32,33,39,61,71, 72, 79, 91 36-590001-9A7
December 21, 1983
71
36-590001 -9A8
January 18, 1984
5, 12, 20, 28, 57, 91
36-590001-9A9
September 27, 1984
Introduction, 5, 12, 21,23, 25, 27, 33, 35, 36, 71, 74, 91
1985
36-590001-9A10
May 31,
36-590001-9A11
August 29,
36-590001-9A12
August 28, 1987
1985
Introduction, 27 12, 28
Introduction, 5, 11, 12, 25, 27, 28, 32, 36, 51, 55, 71,74
NOTE: A List of Effective pages will be in the front of each chapter. a part number which appears on the title page with the date of the issue. Subsequent revisions are identified by the addition of a part number Al after a part number denotes the first revision to the basic publication, A2 the second, etc Occasionally, it is necessary to reissue and reprint a publication for the purpose of obsoleting a previous issue and outstanding revisions thereto As these replacement reisstles are the code will also change to the next successive letter of the alphabet at each issues For example, B for the first reissue, C for the second, etc
publications
are
assigned
code after the
ordering a handbook, give the basic number, and the reissue code when applicable, if a complete up-to-date publication be required, give the basic number and revision code for the particular set of revision pages you desire
Is
desired Should only revision
A23
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
LIST OF EFFECTIVE PAGES
Always destroy superseded pages when
A23
(Continued)
you insert revised pages.
PART NUMBER
DATE
CHAPTERS AFFECTED
36-590001-9A13
March 30, 1990
Introduction, 7, 32
36-590001-9A14
June 20, 1991
Introduction, 5, 12, 20, 27, 55, 71, 91
36-590001-9A15
December 20, 1991
Introduction, 52
36-590001 -9A 16
October 16, 1992
5, 9, 11,12, 21,25, 27, 28, 51, 55, 56, 91
36-590001 -9A 17
November 16, 1994
Introduction, 32, 74
36-590001 -9A 18
August 18,
36-590001-9A19
March 29, 1996
5, 27
36-590001 -9A20
February 26,
27
36-590001 -9A21
December 23, 1999
5, 32, 52
36-590001 -9A22
November 10, 2000
20, 25, 57
36-590001-9A23
June 28, 2002
5
1995
1999
Introduction, 12, 21, 23, 27, 32, 91
RECORD OF TEMPORARY REVISIONS
ia~b´• TEMP REV NO
DESCRIPTION
ATP REV
INSERT
DATE
REI
REMOVE
DATE
BY
REMOVED
INCOR
BY
ISSUE DATE
27-1
27-50-00:4
12/1 1/92
27-2
27-50-00:4
1 1
/1 5/93
12/1 5/97
ATP/M B
1
2/1 5/97
27-2
2/1 5/97
ATP/M B
8/09/99
A20
1
ATP/M B /JRS
Raytheon
Aircraft
BEECH BONANZA SERIES MAINTENANCE MANUAL
RECORD OF TEIIlIFORARY REVISIONS Affected
emporary Revision No.
Removed
Inserted
By Chapter
Page(s)
Date
By
Revision No.
Date
inserting or removing a temporary revision, the applicable revision number and the initials of the person(s) inserting and/or removing these revisions should be recorded on these pages.
When
NOTE: Insert the Record of
Temporary
Revisions after the
Log
of
Temporary Revisions page(s).
Pagel
Rayeheon
Aircraft
SEECH BONANZA SERIES MAINTENANCE MANUAL
RECORD OF TEMPORARY REVISIONS
No.
Page
2
Removed
I
Inserted
Affected
emporary Revision
By Chapter
Page(s)
By
Date
Revision No.
Date
Raytheon
Aircraft
BEECH BONANZA SERIES MAINTENANCE MANUAL
LOG OF TEMPORARY REVISIONS Revision No.
Date
27-1
Dec 11/92
27-2
Nov 15/93
Subject drive cable connection
Flap Flap drive cable connection
Incorporated TR 27-2 A20
Page 1 Feb 26/99 NOTE: Insert this
Log
of Temporary Revisions after the Record of Revisions page.
Ral~heMI Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
P/N 36-590001-9, REVISION A23, JUNE 28, 2002 HIGHLIGHTS The
chapters
which have been revised
are
listed below with the
Highlights
of each
change.
Remove the affected
pages and insert the A23 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.
Description
Chapter/Section
5-10-00
Added data
5-20-00
data from 1000 hours to
Changed
references for Hartzell
Pressure
Pump
to
Magneto
Flap Motor
Added data
Changed
Change
Nose Gear Retract Rod Rod-ends from
on
Changed shimmy damper
Added
of
supplier
and
on
Chapter
5-20-00.
condition.
propellers, Woodward Propeller Governor
and Air
data.
Standby
Air Pressure
Brush check removed
System
replacing
motor
Check Valve data. on
condition
covers
the brushes.
the FACTS program.
on
references from FAR to 14 CFR.
Added data for
Standby Alternator/Generator,
Instrument Air
System
and
Standby
Instrument Air. Revised Added
Landing Gear Gearbox inspection.
inspection
of Fuel Strainer and Control Column. Revised Fuel Cell,
Caps
and
Vents data.
Added
Inspection
Revised Nose
of
Landing
Revised Cable and
Added
Flapper
inspection
Valve data.
Gear Retract Rod data.
Pulleys
data.
of Rudder Forward
Soar and other chages.
Page A23
1
Jun 28/02
Raytheon Aircraft REVISION 36-590001-9A23 to the
BEECH BONANZA SERIES MAINTENANCE MANUAL
P/N 36-590001-9
Title
MAV 9,
1980)
INSERT
REMOVE PAGE
(ISSUED:
CHAPTER
PAGE
Title
Page
CHAPTER
DATED
Jun 28/02
Page
Logo Page
Logo Page
"A"
Page
"A"
Page
A23
"B"
Page
"B"
Page
A23
All
5EFF
1
5-EFF
Jun 28/02
All
5-TOC
1 and 2
5-TOC
Jun 28/02
All
5-10-00
1 thru 6
5-10-00
Jun 28/02
All
5-20-00
1 thru 20
5-20-00
Jun 28/02
NOTE
These instruction pages may be discarded after the above revision has been properly incorporated into the Maintenance Manual.
Page
1 of 1
MAINTENANCE MANUAL INTRODUCTION LIST OF PAGE EFFECTIVIP/ CHA PTER-SECTION-SUBJECT
Introductian-Effectivity Introduction
PAGE
DATE
1
Aug 18/95
1
2
Sep 27/84 Sep 27/84
3
Jan 20/82
4
Jan 20/82
5
May 9/80
6
Oct7/83
7
Sep 27/84 Sep 27/84 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95 Aug 18/95
8 9 10 11 12 13 14 15 16 17
18 19 20 21
22 23 24 25
26 27
28 29
30 31 32
33
Introduction-Effectivity A18
Page 1 Aug 18/95
BEECHCRAFT BONAN;LA SERIES
MAINTENANCE MANUAL
WARNING
INTRODUCTION
only genuine BEECHCRAFT or BEECHCRAFT approved parts obtained from BEECHCRAFT approved sources, in Use
NOTE Service Publication reissues
automatically provided
manual. For information reissues
or
revisions
or
revisions
connection with the maintenance and
are not
to the holders of this on
how
applicable
to
to this
Beech
Genuine BEECHCPAFT parts and inspected under rigorous
are produced procedures to insure airworthiness and suitability for use in Beech airplane applications. Parts purchased
Service Bulletin No. 2001.
from The BEECHCRAFT Bonanza Series Maintenance Manual is in accordance with GAMA (General Manufacturers Association) Specification No. 2 also meets the intent of the requirements of Specification 100 (Air Transport Association of
prepared
Aviation
format. It the ATA
America)
with respect to the arrangement and content of the SystemlChapters within the designated chapter´•numbering
system.
The Maintenance Manual is
of
obtain
manual,
refer to the latest revision of BEECHCRAFT
I
repair
airplanes.
supplemented by
the
sources
Salvaged airplane parts,
even
reworked
parts
obtained from non-BEECHCRAFT approved or parts, components, or structural assemblies, the service history of which is unknown or cannot be authenticated, may have
following publications: (1)
The BEECHCRAFT Bonanza 36 Series Parts Catalog, P/N 36-590001-1 (2) BEECHCRAFT Bonanza 35 Series Parts Catalog, P/N 35-590102-5 (3) BEECHCRAFT Bonanza 33 Series Parts Catalog, P/N 33-
sources,
(4) BEECHCRAFT Bonanza Wiring Diagram Manual, P/N 35-590102-9 (5) BEECHCRAFT Bonanza 33, 35, 36 Series Continuing Care Inspection Guide PIN 9836711 and (6) BEECHCRAFT Approved Model 33, 35 and 36 Inspection Guide P/N 98-32227.
temperatures
590010-7
other than BEECHCAAFT,
though outwardly identical in appearance, may not have had the required tests and inspections perfor~ed, may be different in fabrication techniques and materials, and may be dangerous when installed in an airplane.
been
subjected or
unacceptable
stresses
have other hidden
damage,
to
or
not
through routine visual or usual nondestructive testing techniques. This may render the part, component or structural
discernible
assembly, even though originally manufactured by BEECHCAAFT, unsuitable and unsafe for ~airplane use.
NOTICE
BEEC)~1CRAFT expressly
Corporation expressly reserves supersede, cancel and/or declare
Seech Aircraft the
right
to
obsolete any part, part numbers, kits or publication that may be referenced in this manual without
prior
disclaims
any
respon!jibility for maifunctions, failures, damage or injury caused by use of non-BEECHCRAFT approved parts.
notice.
ASSIGNMENT OF SUBJECT MA TERIAL It
shall
be
owner/operator
the
responsibility
of
the
to ensure that the latest revision
publications referenced in this manual utilized during operation, servicing,
of
maintenance of the
are
and
publication is organized at four levels: Group, System/Chapter, Sub-System/Section, and Unit/Subject.
airplane.
CORRESPONDENCE
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 (see Chapter 11 for placard If
The content of this
Identified by different colored divider tabs. Group are primary divisions of the manual that enable separation of content. Typical of this division separation between Airframe Systems and the Power
These
broad is the Plant.
a
location).
System/Chapter
The various groups
are
broken down into
major systems such as Environmental Systems, Electrical Power, Landing Gear, etc. The systems are arranged more or less alphabetically rather than by precedence or
INt~ODUCTION A9
Page 1 Sep 27/84
BEECHCRAFT BONANZA SEAIES MAINTENANCE MANUAL
importance. They the first element of
a
assigned
a
number, which becomes
standardized
numbering system. Thus,
are
the element "28" of the number 28-00-00 refers to the
chapter "Fuel". Everything concerning the fuel system be covered in this
CHAPTER SECTION SUBJECT
SUBJECT
FUEL
28
chapter.
Indicating
28-40
broken down into sub-systems. These sub-systems are identified by the second element of a standard numbering
Fuel
28-40-00
system. The number "40" of the number 28-40-00 is for the indicating portion of the fuel system.
The material is
Sub-System/Section
The
major systems of
The individual units within
Unit/Subject be identified
by
system, such
an
airplane
are
sub-system may numbering is assigned by the
a
the third element of the standard
as
28-40-01. This number
manufacturer and may,
or
PAGE
will
Uuantity Indicators arranged
within the
1
chapter
in
ascending
numerical sequence. The Chapter-Section Subject number and page number are found at the lower outside corner of each page.
may not, be used and will vary in
usage.
EFFECTI1~N LOG OF EFFECTIVE REVISIONS
APPLICATION The to the GAMA
or ATA format will
Any publication conforming use the same basic numbering system. Thus, whether manual be
the
Log of Effective
Revisions
the manual lists the revisions
following the title page of currently effective for the
manual.
BEECHCRAFT Bonanza Series Maintenance a BEECHCRAFT Bonanza Wiring Diagram
a
Manual, or Manual, the person wishing information concerning the
indicating portion of
the fuel
system, would refer
to the
Tab "28, Fuel". The table of contents in the front of this chapter will provide a list of sub-systems covered in this chapter.
AEROFICNE
System/Chapter
(GAMA) has specification for microfiche and registered the Aerofiche for use by all GAMA Members. Consult the
The General Aircraft Manufactures Association
developed For
example:
name
a
28-00
General
issue of the Publications Price List for an enumeration of the maintenance information available in
28-10
Storage
Aerofiche form for order from Seech Aircraft Corporation.
current
(Tanks, cells, necks, caps, instruments, etc.) 28-20
Distribution
(Fuel lines, pumps, valves, controls, etc.) 28-30
28-40
Dump (If in-flight dumping system is installed, it would appear here.) Indicating (Quantity, temperature, pressure, etc., does not include engine fuel flow
or
pressure.)
ALPHABETICAL INDEX An
alphabetical index,
page 9 of this assistance in
alphabetical
which may be found beginning on is also provided as an
Introduction,
locating the desired provides the chapter
index
information. and
The
sub-chapter
in
which any given information may be found. Reference to the Table of Contents in the front of the indicated chapter will
provide
the exact page
on
which the information
can
be found.
LIST Of EFFECTIVE PAGES this example further, by turning to the Table of Contents for Chapter 28, the following information might be
Carrying
found within the list:
Pages following each Chapter GividerTab, lists the issue date of each page that is effective for that chapter.
The list of Effective
INTRODUCTION
Page2 Sep 27/84
ASi
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL SVSTEM/CHAPTER INDEX GUIDE
following System/Chapter, Sub-System/Section Index Guide is prepared in Specification No. 100 and GAMA Specification No. 2 for use with Maintenance Manuals, Parts Catalogs and Wiring Diagram Manuals. The following chapters are not applicable to this Maintenance Manual: 4, 22, 26, 29, 31, 37, 38, 49, 60, The
accordance with both ATA
70, 75, 76, 77, 78, 83, and 95.
SYSTEMI
SUB-SYSTEMI
CHAPTER
SECTION
TITLE
INTRODUCTION 5
TIME LIMITS/MAINTENANCE CHECKS 10
Time Limits
20
Scheduled Maintenance Checks
6
DIMENSIONS AND AREAS
7
LIFTING AND SHORING General
00 8
LEVELING AND WEIGHING 00
j 9
TOWING AND TAXIING 00
10
12
00
General
20
Exterior Placards and
Markings
SERVICING General
10
Replenishing
20
Scheduled Servicing
STANDARD PRACTICES 20
21
General
REQUIRED PLACARDS
00
20
General
PARKING AND MOORING 00
11
General
AIRFRAME General
ENVIRONMENTAL SYSTEMS 40
Heating
60
Cooling
INTRODUCTION
Page A4
3
Jan 20182
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
23
COMMUNICATIONS 60
24
25
30
DC Generation
40
External Power
50
Electrical Load Distribution
EQUIPMENT/FURNISHINGS 00
General
10
Flight Compartment Passenger Compartment Emergency
60
FLIGHT CONTROLS
00
General
10
Aileron and Tab
20
Rudder and Tab
21
Ruddervator and Tab
30
Elevator and Tab
31
Warning/Safe Flight System Flaps Gust Lock and Damper
50 70
28
30
32
33
Discharging
ELECTRICAL POWER
20
27
Static
Stall
FUEL 00
General
10
Storage
20
Distribution
40
Indicating
ICE AND RAIN PROTECTION
00
General
60
Propellers
LANDING GEAR 00
General
10
Main Gear and Doors
20
Nose Gear and Doors
30
Extension and Retraction
40
Wheels and Brakes
50
Steering
60
Position and
Warning
LIGHTS 20
Interior
40
Exterior
INTRODUCTION
Page4 Jan 20/82
A4
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
34
NAVIGATION AND PITOT STATIC 10
35
OXVGEN 00
36
General
10
instrument 3 Control Panels Electrical 5 Electronic Equipment Racks
STRUCTURES
53
00
General
10
Passenger/Crew Cargo Doors
56
10
Horizontal Stabilizers
20
30
Elevator and Ruddervator Veriical Stabilizer
40
Rudder
WINDOWS
General
10
Flight Compartment
20
Cabin
WINGS
30
General Plates/Skin
40
Attach
Fittings
50
Flight
Surfaces
00
61
Plates/Skin
STABILIZERS
00
57
Doors
FUSELAGE 30
55
General
DOORS
30
j
MULTIPURPOSE PARTS
00
00
52
General
ELECTRICIELECTRONIC PANELS
20 51
General
PNEUMATIC 00
39
Flight Environmental Data/Pitot Static
PROPELLERS 10 20
Propeller Assembly Controlling
INTRODUCTION
Page 5 May 9180
BEECHCRAFI BONANZA SERIES MAINTENANCE MANUAL
71
POWER PLANT 00
General
10
Cowling
72
ENGINE
73
ENGINE FUEL AND CONTROL
Indicating
30 74
IGNITION 00
General
20
Distribution
77
ENGINE INDICATING
General
00
OIL
79
General
00 80
STARTING
Cranking
10
TURBINES
81
General
00
91
CHARTS
SUPPLEMENTARY PUBLICATIONS
Following
is
a
list
of
VENDOR PUBLICATIONS
publications providing servicing,
overhaul and parts information on various components of the BEECHCRAFT Bonanza which you may obtain to supplementthe Maintenance Manual. In most instances,
ENGINE
1
10-520
you should obtain the publications directly from the manufacturer or his distributor. Only a few, vendor manuals
Service Parts
supplementary publications, are available from Commercial Products Support, Beech Aircraft Corporation.
Mobile, Alabama 36601.
and Beech
Those
which
are
Publications Price
available List.
Since
are a
listed
wide
in the current
variety
of
radio
equipment is available and because radio manufacturers normally supply parts and a servicing manual with each set, radio publications have not been included in the list.
Motors
Catalog Form X-30040. Teledyne Continental
Aircraft
Maintenance
Teledyne
publications
on
additional
available, they will be added
components become
to this list of
and
Division, Post Office Box 90
Overhaul
Continental
Motors
Manual Aircraft
Form
X-30039.
Products
Division,
Post Office Box 90 Mobile, Alabama 36601.
Operators Handbook Motors Aircraft
As
Products
Form X-30041,
Products
Teledyne
Continental
Division, Post Office Box 90
Mobile, Alabama 36601.
publications.
INTRODUCTION
Page6 Oct7/83
A6
BEECHCRAFT BONANZA SEAIES NIAINTENANCE MANAUL
TSIO-520
Overhaul Manual with Parts List Bulletin No. 33080 for the 35-380088-1 Propeller Governor, Woodward Governor
Manual for TSIO-520 Series Aircraft Engines Teledyne Continental Motors Aircraft Products Division, Post Office Box 90, Mobile, Alabama
Company, Rockford,
36601.
MAGNETOS
Operators Manual for TSIO-520-U and -UB Engines Form No. X-30044, Teledyne Continental Motors Aircraft Products
Overhaul Instructions for Bendix S-1200 Series
Overhaul
Illinois.
Form No. X-30042,
Division, Post Office Box 90, Mobile, Alabama 36601.
Magnetos Corporation,
Form L-609, Scintilia Division, Bendix Aviation Sidney, New York.
10-550
Service Parts List for Bendix 8-1200 Series Magnetos, Form L-608, Scintilla Division, Bendix Aviation Corporation,
Illustrated Parts Catalog Form X-30569, Teledyne Continental Motors Aircraft Products Division, Post Office Box 90, Mobile, Alabama 36601.
Sidney,
New York.
Installation, Maintenance and Operation Instructions, SGRNand S6AN-205 Magnetos, Form L-526, Scintilla
201
Overhaul Manual Form X-30568, Teledyne Continental Motors Aircraft Products Division, Post Office Box 90,
Division, Bendix Aviation Corporation, Sidney, New York.
Mobile, Alabama 36601.
Ovemaul Instructions, S-600 Series Magnetos, Form L-551, Scintilla Division, Bendix Aviation Corporation, Sidney, New
Continued Airworthiness Maintenance and Operators Manual Form X-30565, Teledyne Continental Motors
York.
Aircraft
Division,
Products
Post Office Box 90, Mobile,
Alabama 36601.
Service Parts List, S-600 Series Scintilla Division, Bendix Aviation
Magnetos, Form L-552-1, Corporation, Sidney, New
York.
TURBOCHARGER Series Aircraft Magnetos Maintenance and Overhaul Instructions, Form No. 1037-A, Slick Electro, Inc., Rockford, Illinois 61101.
4200/6200
Overhaul Manual and Parts Catalog Fonn No. X-30055, Teledyne Continental Motors Aircraft Products Division, Post Office Box 90, Mobile, Alabama 36601.
FUEL INJECTION
STARTING MOTOR
Overhaul Manual and Parts Catalog Form No. X-30052, Teledyne Continental Motors Corporation, Aircraft Products
Parts and
Division, Post Office Box 90, Mobile, Alabama 36601.
Ohio 43694.
Equipment List, Service Parts and Technical Data OE-A1, Equipment Section Service Department, Toledo,
PROPELLER ALTERNATOR Overhaul Manual and Parts
McCauley
Industrial
Catalog Manual No. 720415, Corporation, Dayton, Ohio.
Equipment List,
Service Parts and Technical Data OE-A1,
Prestolite Service Owner’s
Manual, 115H, or Overhaul Manual No. 1138, Hartzell Propeller, Inc., Piqua, Ohio. Hartzell
Propeller
Service
Manual
Service with
overhaul
and
parts for McCauley
propellers, Manual No. 761001 or McCauley propeller Operators Manual No. MPC-11, McCauley Accessory Division, Cessna Aircraft Company, 1840 Howell Ave., Dayton, Ohio 45417. 3A32C406-X
Department,
Parts
and
Equipment
Section, Toledo, Ohio 43601.
642056A1
Teledyne
and
Overhaul
Instructions for Continental
P/N
642051 Alternator, Publication No. X-30531, Continental Motors, Aircraft Products Division, or
Post Office Box 90, Mobile, Alabama 36601.
ELECTRIC PROPELLER DEICER
PROPELLER GOVERNOR
Report 70-04-700, Maintenance Report 68-04-7128, B.F. Goodrich Engineered Systems Company Division, B.F. Goodrich Company, Installation of Deicer Boots,
McCauley Service Manual No. 78041 for the 35-380088-3 Propeller Governor, 3535 McCauley Drive, Vandalia, Ohio
Manual
45377.
Akron, Ohio 44318. Introduction
A9
Pege7 Sep 27164
BEECHCRAFT BONAEnA SEAIES MAINTENANCE MANAUL
BATTERY
AUTOPILOT
King KFC-P00
Installation
Manual
No. 006-0203-00 for
Models F33C, M3A, A36, and A36TC or No. 006-0201-00 for Model V35B, King Radio Corporation, 400 N. Rogers
Service Manual, Publication Number: GSM-12n, Teledyne Battery Products, P.O. Box 431, 840 W. BrocMon Ave.,
Redlands, CA 92373.
Road, Olathe, Kansas 66061. Service Manual CB12-9, Edo-Aire Mitchell Service and Overhaul Manual for Century III PIN 68854 or Century IV P/N 68889, P.O. Box 610,
Concorde
Battery Corp.,
for Concorde
Aircraft
2009 San Bemadino
Battery,
Rd., West
Covina, CA 01790.
Mineral Wells, Texas 76067.
STROBE LIGHT RADAR Overhaul Power
Manual with
Supply),
Illustrated
Parts List
(60-1750-3
Publication Number: 33-40-58; Grimes Div. Corp., 515 North Russel Street, Urbana,
of Midland Ross
WeatherScout
description
Digital
Weather
Radar
and Installation Manual,
System, System
Publication Number:
188023100, R.C.A., Avionics Systems, 8500 Balboa Blvd.,
Ohio 43078.
Van
Nuys, CA
91409.
AIR CONDITIONER COMPRESSOR Model 508
Compressor, Abacus International,
P. O. Box
327, Dallas, Texas 75221.
SUPPLEMENTARY BEECHCRAFT PUBLICAT)ONS FLIGHT CONTROLS 98-35012
ELECTRIC ELEVATOR TRIM TA8
Brake
Edo-Aire Mitchell, Automatic Right Control Systems, AK563 Bulletin No. 686 or AK669 Bulletin No. 798, EDO-AIRE MITCHELL, P.O. Box 610, Mineral ~lells, Texas 76067.
Servicing
Maintenance Instructions and Illustrated
Parts Breakdown for the Main Wheel, Nose Wheel and
Assembly.
32-31-24 Maintenance Information and Breakdown for EM 27-8
Landing Gear
Illustrated
Parts
Motor.
Introduction
PageB Sep 27/84
A9
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL
INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
ACCESS OPENINGS, FUSELAGE AND A36TC ACCESS OPENINGS, FUSELAGE F33A AND F33C ACCESS OPENINGS, FUSELAGE V35B) ACRYLIC LACqUER (INTERIOR COLORS) ACT ASSY, ELEV TRIM TAB (E-llll) ACT BRUSH REPLACE SCHED, ELEC TRIM TAB ACT DISASSEMBLY, ELEV TRIM TAB (E-llll) ACT INST, ELEC TRIM TAB (F33A, F33C, V35B) ACT REM, ELEC TRIM TAB (F33A, F33C, V35B) ACTUATOR ASSEMBLY INSTL, LANDING GEAR ACTUATOR ASSEMBLY REMOVAL, LANDING GEAR ACTUATOR ASSEMBLY, ELEVATOR TRIM TAB ACTUATOR ASSEMBLY, LANDING GEAR RETRACT ACTUATOR CLEANING AND PARTS REP, LANDING GEAR RETRACT ACTUATOR DISASSEMBLY, ELEV TRIM TAB ACTUATOR DISASSEMBLY, LANDING GEAR RETRACT ACTUATOR FUNCTIONAL TEST, LANDING GEAR RETRACT ACTUATOR INSTALLATION, FLAP ACTUATOR INSTALLATION TRIM TAB ACTUATOR INSTALLATION 33 and 36), ELEV TRIM TAB ACTUATOR INSTALLATION, AILERON TRIM TAB ACTUATOR REMOVAL, FLAP ACTUATOR REMOVAL V35B), TRIM TAB ACTUATOR REMOVAL 33 and 36), ELEV TRIM TAB ACTUATOR REMOVAL, AILERON TRIM TAB ACTUATOR REMOVAL (33 and 36), ELEV TRIM TAB ACTUATOR, FLAP DISASSEMBLY AND ASSEMBLY ADJUSTING THE WING AEROFICHE AILERON AND TAB-MAINTENANCE PRACTICES AILERON AND TAB-MAINTENANCE PRACTICES AILERON CONTROL CABLE INSTALLATION AILERON CONTROL CABLE REMOVAL AILERON CONTROL SYSTEM RIGGING AILERON CONTROL TRIMMER AILERON INSTALLATION AILERON INSTALLATION AILERON REMOVAL AILERON REMOVAL AILERON RIGGING AILERON TAB ACTUATOR INSTALLATION AILERON TAB ACTUATOR REMOVAL AILERON TAB AILERON TAB
jA36
IV35B),
I
PAGE
53-30-00 53-30-00 53-30-00 20-00-00 27-30-00 27-30-00 27-30-00 27-30-00 27-30-00 32-30-00 32-30-00 27-30-00 32-30-00 32-30-00 27-30-00 32-30-00 32-30-00 27-50-00 27-21-00 27-30-00 27-11-00 27-50-00 27-21-00 27-30-00 27-11-00 27-30-00 27-50-00 57-00-00 IN-TR-OD 27-10-00 27-11-00 27-11-00 27-11-00 27-11-00 27-10-00 27-10-00 27-11-00 27-10-00 27-11-00 27-10-00 27-11-00 27-11-00 27-10-00
3 1 2 3 8 13 7 12A 12A 1 1 6 6 6 6 6 9 4 8 12 6 4 7 11 6 11 5 4 2 1 1 3 3 4 6 4 3 4 2 4 8 8 6
27-11-00
7
INTRODUCTION Page 9 A18
Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAC INDEX
CHAPTER AND SUB CHAPTER
COMPONENT ITEM OR SUB SYSTEM
AILERON TRIM TAB CABLE INSTALLATION AILERON TRIM TAB CABLE REMOVAL AILERON TRIM TAB FREE PLAY INSPECTION AILERON TRIM TAB RIGGING AIR CONDITIONER BELT AIR CONDITIONER CONDENSER AIR CONDITIONER LEAK DETECTION AIR CONDITIONER MAINTENANCE AIR CONDITIONER TORQUES AIR CONDITIONER PRECAUTIONS AIR CONDITIONER TROUBLESHOOTING AIR CONDITIONING FUNCTIONAL TEST AIR CONDITIONING SYSTEM AIR CONDITIONING SYSTEM CHARGING AIR CONDITIONING SYSTEM DEPRESSURIZING AIR CONDITIONING SYSTEM PURGING AIR FILTER INSTALLATIONINLINE INTAKE AIR FILTER INSTALLATION AIR FILTER REMOVAL AIR FILTER REMOVAL INTAKE AIR PRESSURE PUMP INSTALLATION AIR PRESSURE PUMP REMOVAL AIR SYSTEM, INSTRUMENT AIRPLANE DIMENSIONS MODEL A36TC AIRPLANE DIMENSIONS MODEL A36 AIRPLANE DIMENSIONS MODEL B36TC AIRPLANE DIMENSIONS MODEL 33 AIRPLANE DIMENSIONS MODEL 35 AIRPLANE FINISH CARE AIRPLANE FINISH CLEANING ALCAL CALIBRATION UNIT ALPHABETICAL INDEX ALTERNATOR DRIVE GEAR AND COUPLING INSTL ALTERNATOR INSTALLATION ALTERNATOR REMOVAL ALUMINUM CORROSION REMOVAL ALUMINUM CORROSION TREATMENT
IINLINE
ALUMINUM ELECTRICAL BONDING ALUMINUM SURFACES ASSIGNMENT OF SUBJECT MATERIAL ATA APPLICATION AUXILIARY FUEL PUMP INSTALLATION AUXILIARY FUEL PUMP REMOVAL AUXILIARY OR FUEL BOOST PUMP AVIONICS/RADIO EQUIPMENT INSTALLATION AVIONICS/RADIO EQUIPMENT REMOVAL
27-11-00 27-11-00 27-11-00 27-11-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00
12-10-00 12-10-00 12-10-00 12-10-00 36-00-00 36-00-00 36-00-00 36-00-00 71-00-00 71-00-00 36-00-00
06-00-00 06-00-00 06-00-00 06-00-00 06-00-00 20-08-00 20-08-00 77-00-00 IN-TR-OD 24-30-00 24-30-00 24-30-00
20-09-00 20-09-00 20-03-00 20-03-00 IN-TR-OD IN-TR-OD 28-20-00 28-20-00 28-00-00 39-10-00 39-10-00
PAGE 7 7 8 7 7 8 7 5 7 5 4 5 2 3 3 3 5 5 5 5 6 6 1 4 3 5 1 2 2 3 1 2 6 6 6 3 4 7 2 1 2 1 1 1 1 1
INTRODUCTION
Page 10 Aug 18/95
A18
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL ALPHABETICAL
COMPONENT OR SUB
INDEX
ITEM
SYSTEM
BAGGAGE DOOR INSTALLATION BAGGAGE DOOR REMOVAL BAGGAGE DOORS (MODELS F33A, F33C, AND V35B) BALANCING PROCEDURE BALANCING THE AILERON BALANCING THE ELEVATOR BALANCING THE RUDDER BALANCING THE RUDDERVATOR BATTERY BOX AND LID PAINTING BATTERY BOX CLEANING BATTERY CLEANING BATTERY INSTALLATION BATTERY MAINTENANCE PROGRAM BATTERY REMOVAL BATTERY REPLACEMENT, ELT BATTERY SERVICING BATTERY BEARING HOUSING INSPECTION BEARING INSTALLATION USING RETAINING COMPOUND BEARING INSTALLATION BY STAKING BELT TENSION ADJUSTMENT, COMPRESSOR BLEEDING THE BRAKE SYSTEM BLEEDING THE BRAKE SYSTEM, GRAVITY BLEEDING THE BRAKE SYSTEM, PRESSURE INSTALLATION BLOWER, FRESH AIR REMOVAL BLOWER, FRESH AIR BOLTS, TOR9UING COARSE THREAD IN SMEAR BOLTS, TORQUING FINE THREAD IN SMEAR BONDING JUMPER ACROSS TUBING CLAMP ELECTRICAL BONDING BOOST PUMP, AUXILIARY BRAKE ADJUSTMENT, PARKING BRAKE ASSEMBLY BRAKE ASSY AND MAIN WHEEL INSTALLATION BRAKE ASSY AND MAIN WHEEL REMOVAL BRAKE ASSY INSPECTION AND CLEANING BRAKE CLEANING AND PARTS REPLACE, PARKING BRAKE MASTER CYLINDER ASSEMBLY BRAKE MASTER CYLINDER CLEANING AND PARTS RPLACEMENT BRAKE MASTER CYLINDER DISASSEMBLY BRAKE MASTER CYLINDER INSTALLATION BRAKE MASTER CYLINDER LINKAGE ADJUSTMENT BRAKE MASTER CYLINDER REMOVAL BRAKE RELAY CHECK, DYNAMIC BRAKE RELINING
CHAPTER AND SUB CHAPTER
52-30-00 52-30-00 52-00-00 57-50-00 57-50-00 55-20-00 55-40-00 55-20-00 20-08-00 24-30-00 24-30-00 24-30-00 24-30-00 24-30-00 25-60-00 24-30-00 12-20-00 20-05-00 20-05-00 20-05-00 12-10-00 32-40-00 32-40-00 32-40-00 21-50-00 21-50-00 91-00-00 91-00-00 20-03-00 28-00-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-30-00 32-40-00
PAGE
1 1
1 1 1 1 1 3 7 9 8 8 7 8 1 9 1 2 2 3 7 8 10 9
11 11 11 11 8 1 7 1 1 3 4 8 7 6 6 6 6 6 3 6
INTRODUCTION A18
Page 11 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND
BRAKE SHUTTLE VALVE BRAKE SYSTEM BRAKE SYSTEM BLEEDING BRAKE SYSTEM BLEEDING, ELECTRIC BRAKE SYSTEM BLEEDING, GRAVITY BRAKE SYSTEM BLEEDING, PRESSURE POT BRAKE SYSTEM, HYDRAULIC BRAKE SYSTEM BRAKE SYSTEM TROUBLESHOOTING BRAKE VALVE ASSEMBLY, PARKING BRAKE VALVE DISASSEMBLY, PARKING BRAKE VALVE INSTALLATION, PARKING BRAKE VALVE REMOVAL, PARKING BRAKE WEAR AND WEAR LIMITS BRAKES, RELINING BREAK-IN ENGINE OIL BRUSH BLOCK CLEANING SLIP RING BRUSH BLOCK INSTALLATION BRUSH BLOCK REMOVAL BRUSH MODULE REPLACEMENT BRUSH MODULE RESISTANCE CHECK BRUSH REPLACEMENT BRUSH WEAR LIMITS
32-40-00 12-10-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 12-10-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 79-00-00 30-60-00 30-60-00 30-60-00 30-60-00 30-60-00 30-60-00 30-60-00
1 6 1 13 13 13 9 10 11 11
CABIN DOOR ADJUSTMENT CABIN DOOR INSTALLATION (MODEL F33C) CABIN DOOR INSTL (F33A, V35B, A36, A36TC) CABIN DOOR LOCK, FITTING TUMBLER TO KEY CABIN DOOR QUICK RELEASE MECHANISM CABIN DOOR REMOVE (F33A, V35B, A36, A36TC) CABIN DOOR REMOVAL (MODEL F33C) CABIN DOOR TELEFLEX CABLE REMOVE AND INSTL CABIN DOOR WINDOW INSTALLATION CABIN DOOR WINDOW REMOVAL CABIN DOOR CABIN HEATING
52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 52-10-00 56-10-00 56-10-00 52-00-00 21-40-00 33-20-00 33-20-00 27-21-00 21-40-00 27-00-00 28-40-00 28-10-00 28-10-00
2 2 1 3 1 1 2 7 2 2 1 1 2 2 5 1 1 1 1 1
CABIN OVERHEAD LIGHT BULB INSTALLATION CABIN OVERHEAD LIGHT BULB REMOVAL CABIN REPL, ELEVATOR TAB INDICATOR CABIN VENTILATION CABLE TENSION, EFFECTS OF TEMPERATURE CALIBRATION OF FUEL QUANTITY INDICATOR CELL INSTALLATION, FUEL CELL REMOVAL, FUEL
SUB CHAPTER
PAGE 1 4 8 12 9 12 1 4 3 7 7 7
7
INTRODUCTION
Page 12 Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT
CHAPTER AND
OR SUB
SUB CHAPTER
ITEM SYSTEM
CHARGING THE AIR CONDITIONING SYSTEM CHART 1, SERVICING CHART 2, LUBRICATION SCHEDULE CHECKING BALANCE CHECKING BALANCE CLEANING AND PARTS REPL, MAIN LANDING GEAR CLEANING AND PARTS REPL, NOSE LANDING GEAR CLEANING AND WAXING THE AIRPLANE CLEANING AND WAXING THE AIRPLANE FINISH CLEANING FUEL STRAINERS CLEANING INTERIOR CABIN TRIM CLEANING PLASTIC WINDOWS CLEANING PLASTIC WINDOWS CLEANING THE STATIC AIR SYSTEM CLUTCH INSTALLATION, MAGNETIC CLUTCH REMOVAL, MAGNETIC CLUTCH TOROUE TEST, MAGNETIC COLUMN, CONTROL RIGGING CHAIN COLUMN, CONTROL RIGGING CHAIN COLUMN, CONTROL, ARM INSTALLATION COLUMN, CONTROL, ARM REMOVAL COLUMN, SINGLE CONTROL COMMUNICATION COMPASS LIGHT BULB INSTALLATION COMPASS LIGHT BULB REMOVAL COMPONENTS LOCATION ZONES, ELECTRICAL COMPRESSOR BELT INSTALLATION COMPRESSOR BELT PULLEY ALIGNMENT COMPRESSOR BELT REMOVAL COMPRESSOR BELT TENSION ADJUSTMENT COMPRESSOR INSTALLATION AND ALIGNMENT COMPRESSOR MOUNTING TORQUES COMPRESSOR OIL LEVEL CHECKING COMPRESSOR REMOVAL CONDENSER, AIR CONDITIONER CONDENSER CONTROL RIGGING CONSUMABLE MATERIALS CONTROL CABLE PULLEY INSPECTION CONTROL CABLE STORAGE CONTROL CABLE SYSTEM INSPECTION CONTROL COLUMN ARM INSTALLATION CONTROL COLUMN ARM REMOVAL CONTROL COLUMN CHAIN RIGGING CONTROL COLUMN CHAIN INSTALLATION CONTROL COLUMN CHAIN REMOVAL CONTROL COLUMN CHAIN RIGGING
12-10-00 12-20-00 12-20-00 55-20-00 57-50-00 32-10-00 32-20-00 20-00-00 12-20-00 28-00-00 12-20-00 56-00-00 12-20-00 34-10-00 27-30-00 27-30-00 27-30-00 27-10-00 27-11-00 27-10-00 27-10-00 27-10-00 23-10-00 33-20-00 33-20-00 39-20-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00 21-50-00
12-10-00 21-50-00 21-50-00 21-50-00 91-00-00 20-04-00 20-04-00 20-04-00 27-10-00 27-10-00 27-10-00 27-11-00 27-11-00 27-11-00
PAGE 3 6 7 1 1 2 2 2 4 2 5 1 4 2 12A 12A 13 1 1 1 1 1 1 1 1 1 7 7 7 7 9 7 3 9 8 8 1 3 3 2 1 1 1 1 1 1
INTRODUCTION A18
Page 13 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT ITEM
CHAPTER AND
OR SUB SYSTEM
SUB CHAPTER
CONTROL COLUMN ROLLER ADJUSTMENT CONTROL COLUMN SUPPORT ROLLER ADJUSTMENT CONTROL COLUMN, SINGLE CONTROL LOCKS CONTROL SYSTEM, AILERON, RIGGING CONTROL TRIMMER, AILERON CONTROLLING STATIC CHARGE BUILDUP COOLING DESCRIPTION AND OPERATION CORRESPONDENCE CORROSION CONTROL CORROSION PROTECTION CORROSION-RESISTANT (CRES) STEEL SURFACES COTTER PIN INSTALLATION COURTESY LIGHT BULB INSTALLATION COURTESY LIGHT BULB REMOVAL COWL FLAP RIGGING COWLING INSTALLATION COWLING LATCH RIGGING COWLING REMOVAL CRES STEEL OR TITANIUM ELECTRICAL BONDING CYLINDER ASSEMBLY, BRAKE MASTER CYLINDER CLEANING AND PARTS RPL, BRAKE MASTER CYLINDER DISASSEMBLY, BRAKE MASTER CYLINDER INSTALLATION, BRAKE MASTER CYLINDER LINKAGE ADJUSTMENT, BRAKE MASTER CYLINDER REMOVAL, BRAKE MASTER
27-11-00 27-11-00 27-10-00 10-00-00 27-10-00 27-10-00 20-02-00 21-50-00 IN-TR-OD 20-09-00 20-09-00 20-03-00 20-07-00 33-20-00 33-20-00 71-10-00 71-10-00 71-10-00 71-10-00 20-03-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00
2 2 1 1 1 4 6 1 1 1 3 6 4 2 2 1 1 1 1 6 7 7 7 7 7 6
DAMPENER ASSEMBLY, NOSE GEAR SHIMMY DAMPENER CLEANING/PARTS REP, NOSE GEAR SHIMMY DAMPENER DISASSEMBLY, NOSE GEAR SHIMMY DAMPENER INSTALLATION, NOSE GEAR SHIMMY DAMPENER OVERHAUL, NOSE GEAR SHIMMY DAMPENER REMOVAL, NOSE GEAR SHIMMY DEFUELING, AIRPLANE DEICER BOOT DEICER HEAT TEST DEICER TIMER CHECK DIMENSIONS AND AREAS DIRECT ELECTRICAL BONDING DOOR, UTILITY REMOVAL DRAINING THE FUEL SYSTEM DRAINS, FUEL SYSTEM DUAL CONTROL COLUMN DYNAMIC BRAKE RELAY CHECK
32-20-00 32-20-00
7 2 9 9 9 7 4 5 10 9 1 1 1 1 2 1 2
32-20-00 32-20-00
32-20-00 32-20-00 28-00-00 30-60-00 30-60-00 30-60-00 06-00-00 20-03-00 52-30-00 12-10-00 28-00-00 27-11-00 32-30-00
PAGE
INTRODUCTION
Page 14 Aug 18/95
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BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL
INDEX
CHAPTER AND
COMPONENT ITEM OR
SUB CHAPTER
SUB SYSTEM
DYNAMIC BRAKE RELAY DYNAMIC BRAKE RELAY
INSTL, LANDING GEAR REMOVAL, LANDING GEAR
EFFECT OF TEMPERATURE UPON CABLE TENSION ELECTRIC BLEEDING HR GUIDE ELECTRIC PROPELLER DEICER 100 HR GUIDE ELECTRIC PROPELLER DEICER 50 HR GUIDE) ELECTRIC PROPELLER DEICER ELECTRIC PROPELLER DEICING ELECTRICAL BONDING METHODS ELECTRICAL BONDING OF TUBES ELECTRICAL BONDING EXAMPLES ELECTRICAL BONDING OF GROUND TABS ELECTRICAL COMPONENTS LOCATION ZONES ELECTRICAL LOAD CONTINUOUS STANDARD ELECTRICAL LOAD CONTINUOUS ELECTRICAL LOAD INTERMITTENT OPTIONAL ELECTRICAL LOAD INTERMITTENT ELECTRICAL POWER RETURNS
j100
IOPTIONAL ISTANDARD
ELECTRICAL SYSTEM ELECTRICAL SYSTEM TROUBLESHOOTING ELECTRICAL UTILIZATION CHART
ELECTROLUMINESCENT PANEL INSTALLATION, LIGHTS ELECTROLUMINESCENT PANEL REMOVAL ELECTROSTATIC DISCHARGE SENSITIVITY CLASSIFICATION ELEV TAB FREE PLAY, CHECKING ELEV TRIM TAB SERVO INST, ELECTRIC ELEV TRIM TAB SERVO REMOVAL, ELECTRIC ELEVATOR AND TAB MAINTENANCE PRACTICES ELEVATOR AND TAB MODEL V35B ELEVATOR BALANCING ELEVATOR INSTALLATION ELEVATOR REMOVAL ELEVATOR RIGGING PROCEDURE ELEVATOR STABILIZER INSTALLATION, V35 ELEVATOR STABILIZER REMOVAL, V35 ELEVATOR TAB INDICATOR CABLE REPL ELEVATOR TAB INDICATOR CABLE REPL ELEVATOR TAB RIGGING ELEVATOR TAB RIGGING ELEVATOR TAB RIGGING, V35 ELEVATOR TAB RIGGING TO CORRECT FOR YAW, V35 ELEVATOR TABS, INSPECTION (V35B) ELEVATOR TRIM TAB ACTUATOR
PAGE
32-30-00 32-30-00
2 2
27-00-00 32-40-00 05-20-00 05-20-00 05-20-00 30-60-00 20-03-00 20-03-00 20-03-00 20-03-00 39-20-00 24-50-00 24-50-00 24-50-00 24-50-00 20-03-00 24-30-00 24-30-00 24-50-00 33-20-00 33-20-00 20-02-00 27-30-00 27-30-00 27-30-00 27-30-00 27-21-00 55-20-00 27-30-00 27-30-00 27-21-00 55-10-00 55-10-00 27-21-00 27-30-00 27-21-00 27-30-00 27-21-00 27-21-00 27-21-00 27-30-00
2 10 1 1 1 1 1 1 6 11 1 2 1 2 3 1 1 1 1 1 1 1 11 12 12 1 5 1 1 1
1,5 1 1 9 6 7 6B 7 9 7 6B
INTRODUCTION
Page 15 A18
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COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
ELEVATOR TRIM TAB ACTUATOR ASSEMBLY ELEVATOR TRIM TAB ACTUATOR INSTAL, V35 ELEVATOR TRIM TAB ACTUATOR REMOVAL, V35 ELEVATOR TRIM TAB ACTUATOR DISASSEMBLY ELEVATOR TRIM TAB INDICATOR CABLE REPL ELEVATOR TRIM TAB INDICATOR CABLE REPL ELEVATOR TRIM TAB HINGE INSPECTION ELECTRIC ELEVATOR TRIM,OPTIONAL OPTIONAL ELECTRIC ELEVATOR TRIM, ELEVATOR TRIM, ELEC GROUND CHECKS EMERGENCY LOCATOR TRANSMITTER BATTERY REPLACEMENT EMERGENCY LOCATOR TRANSMITTER MAINTENANCE EMERGENCY LOCATOR TRANSMITTER EMERGENCY LOCATOR TRANSMITTER TESTING EMPENNAGE SKIN THICK (F33A A36, A36TC) EMPENNAGE SKIN THICKNESS ENCLOSED AREAS SUBJECT TO HIGH HUMIDITY ENGINE AIR INDUCTION SYSTEM ENGINE AND FLIGHT INSTRUMENT INSTL ENGINE AND FLIGHT INSTRUMENT REMOVAL ENGINE BUILD-UP
27-30-00 27-21-00 27-21-00 27-30-00 27-21-00 27-30-00 27-21-00 27-30-00 27-21-00 27-30-00 25-60-00 25-60-00 25-60-00 25-60-00 55-00-00 55-00-00 20-08-00 71-00-00
(~358)
ENGINE CLEANING ENGINE DRIVEN FUEL PUMP INSTALLATION ENGINE DRIVEN FUEL PUMP REMOVAL ENGINE FUEL FILTERS AND SCREENS ENGINE INSTALLATION (TURBOCHARGED) ENGINE INSTL (NORMALLY ASPIRATED) ENGINE INSTRUMENT CLUSTER INSTALLATION
ENGINE INSTRUMENT CLUSTER REMOVAL ENGINE OIL, RECOMMENDED ENGINE REMOVA~NORMALCY ASPIRATED) ENGINE REMOVAL TURBOCHARGED) ENGINE TROUBLESHOOTING ENGINE ENVIRONMENTAL FALLOUT (ACID RAIN) EPOXY POLYAMIDE PRIMER FOR URETHANE EQUIP REQUIRED TO PERFORM CHECK BALANCE EVAPORATOR FILTER REPLACEMENT EVAPORATOR INSTALLATION EVAPORATOR REMOVAL EXTENDED STORAGE AND HIGH WIND EXTENSION SYSTEM, MANUAL LANDING GEAR EXTERIOR AND INTERIOR FINISHES EXTERIOR AND INTERIOR PRIMERS EXTERIOR LIGHTS, TROUBLESHOOTING EXTERIOR
39-10-00 39-10-00 71-00-00 12-20-00 71-00-00 71-00-00 12-10-00 71-00-00 71-00-00 39-10-00 39-10-00 79-00-00 71-00-00 71-00-00 71-00-00 72-00-00 20-08-00 20-00-00 57-50-00 21-50-00
21-50-00 21-50-00 10-00-00 32-30-00 20-00-00 20-00-00 33-40-00 11-20-00
PAGE
6C,8,9 12 11
6B,7,8 9 6A 10 12 7 12A 1 1 1 3 2 5 7 1 1 1 6 5 6 6 1 5 5 1 1 2 5 5 2 1 3 4 1 12 12 12 1 1 2 2 2 1
INTRODUCTION
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COMPONENT OR SUB
ITEM
SYSTEM
CHAPTER AND SUB CHAPTER
PAGE
EXTERNAL POWER EXTERNAL POWER
12-20-00 24-40-00
1 1
FAA REQUIRED PLACARDS AND MARKINGS FILLER CAPS AND VENT LINES INSP, FUEL CELL FILLING THE FUEL CELLS INLINE AIR FILTER INSTALLATION FILTER INSTALLATION INTAKE AIR FILTER REMOVAL INLINE), AIR AIR FILTER REMOVAL FITTING TORQUE, FLARE FITTINGS, FLARED FLAP ACTUATOR DISASSEMBLY FLAP ACTUATOR ASSEMBLY FLAP ACTUATOR INSTALLATION FLAP ACTUATOR REMOVAL FLAP INNER FLEX SHAFT INSTALLATION FLAP INNER FLEX SHAFT REMOVAL FLAP INSTALLATION FLAP LIMIT SWITCH ADJUSTMENT FLAP MOTOR INSTALLATION FLAP MOTOR REMOVAL FLAP POSITION INDICATOR AND ADJUSTMENT FLAP REMOVAL FLAP SHAFT INSTALLATION FLAP SHAFT REMOVAL FLAP TRACK WEAR LIMITS FLAPPER VALVE INSPECTION, FUEL CELL FLAPS DESCRIPTION AND OPERATION FLAPS MAINTENANCE PRACTICES FLAPS, THREE POSITION FLAPS, TWO POSITION FLARE FITTING TORQUE FLARED FITTINGS FLIGHT AND ENGINE INSTRUMENT INSTALLATION FLIGHT AND ENGINE INSTRUMENT REMOVAL FLIGHT ENVIRONMENT DATA FLUID LINE FITTING INSTALLATION FLYABLE STORAGE FUEL CELL FLAPPER VALVE, INSPECTION FUEL CELL INSTALLATION FUEL CELL LEAKAGE TEST FUEL CELL PRESERVATION (GOODYEAR) FUEL CELL PRESERVATION (UNIROYAL) FUEL CELL REMOVAL
11-00-00 28-20-00 12-10-00 36-00-00 36-00-00 36-00-00 36-00-00 91-00-00 28-20-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00
1 3 1 5 5 5 4 11 4 7 7 6 5 6 6 1 1 4 4 3 1 4 4 1 6 1 1 3 3 11 4 1 1 1 2 2 6 1 6 9 9 1
j tINTAKE)I
27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 27-50-00 28-10-00 27-50-00 27-50-00 27-50-00
27-50-00 91-00-00 28-20-00 39-10-00 39-10-00 34-10-00 20-06-00 10-00-00 28-10-00 28-10-00 28-10-00 28-10-00 28-10-00 28-10-00
INTRODUCTION Page 17 A18
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BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
CHAPTER AND SUB CHAPTER
COMPONENT ITEM OR SUB SYSTEM
FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL FUEL
CELL CELL CELL CELL FLOW FLOW FLOW
REPAI RGOODYEARUNIROYAL REPAIR
RESERVOIR (CJ-149 AND AFTER) VENT LINESAND FILLER CAPS, INSP INDICATING INDICATOR SYSTEM CALIBRTION AND CORRECTION FLOW TRANSMITTER INSTALLATION FLOW TRANSMITTER REMOVAL HANDLING PRACTICES PUMP ADJUSTMENT, ENGINE DRIVEN PUMP INSTALLATION, AUXILIARY PUMP INSTALLATION, ENGINE DRIVEN PUMP REMOVAL, AUXILIARY PUMP REMOVAL, ENGINE DRIVEN
QUANTITY QUANTITY FUEL QUANTITY FUEL QUANTITY FUEL QUANTITY
INDICATORS INDICATOR CALIBRATION SENSORS SENSOR INSTALLATION SENSOR REMOVAL
28-10-00 ’28-10-00 12-10-00 28-20-00 73-30-00 73-30-00 71-00-00 73-30-00 73-30-00 28-00-00 28-20-00 28-20-00 28-20-00 28-20-00 28-20-00 28-40-00 28-40-00 28-40-00 28-40-00
28-40-00
REMOVAL SELECTOR VALVE INSTALLATION SELECTOR VALVE REMOVAL STRAINER INSTL VALVE) FUEL STRAINER INSTL WING FUEL CELLS) SELECTOR VALVE) FUEL STRAINER REMOVAL FUEL CELL) FUEL STRAINER REMOVAL FUEL STRAINERS, CLEANING FUEL SYSTEM ADJUSTMENT (EA-l AND AFTER) FUEL SYSTEM ADJUSTMENT (TURBOCHARGED) FUEL SYSTEM DRAINS FUEL SYSTEM FULL THROTTLE ADJUSTMENT FUSELAGE ACCESS OPENINGS (A36 AND A36TC) FUSELAGE ACCESS OPENINGS (F33A AND F33C) FUSELAGE ACCESS OPENINGS (V35B) FUSELAGE SKIN THICKNESS (A36 AND A36TC) FUSELAGE SKIN THICKNESS (F33A AND F33C) FUSELAGE SKIN THICKNESS (V35B)
28-00-00 28-20-00 28-20-00 28-20-00
GALVANIC CORROSION
20-09-00 IN-TR-OD 32-10-00
FUEL FUEL FUEL FUEL
tSELECTOR IWING
GAMA APPLICATION GEAR ASSEMBLY, MAIN LANDING GEAR ASSEMBLY, NOSE LANDING
28-20-00 28-20-00 28-20-00 28-00-00 71-00-00 71-00-00 28-00-00 28-00-00 71-00-00 53-30-00 53-30-00 53-30-00 53-30-00 53-30-00 53-30-00
32-20-00
PAGE 9 9 1 3 1 1 11 1 1 2 1 1 1 1 1 1 1 1 1 1 4 2
2 2 3 2 3 2 12 12 2 1
7 3 1 1 8 4 6
1 2 5 7
INTRODUCTION
Page 18 Aug 18/95
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BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL
COMPONENT OR
SUB
INDEX
CHAPTER AND
ITEM
SUB CHAPTER
SYSTEM
32-10-00 32-20-00 32-10-00 32-20-00 32-60-00 32-10-00 32-20-00 32-00-00 32-10-00 32-20-00 33-20-00
PAGE
2 1 1
GEAR DISASSEMBLY, MAIN LANDING GEAR GEAR DISASSEMBLY, NOSE LANDING GEAR INSTALLATION, MAIN LANDING GEAR INSTALLATION, NOSE GEAR POSITION LIGHT ADJ, LANDING GEAR REMOVAL, MAIN LANDING GEAR REMOVAL, NOSE GEAR SYSTEM, LANDING GEAR WEAR TOLERANCE, MAIN GEAR WEAR TOLERANCE, NOSE GLARESHIELD FLOODLIGHT BULB REMOVAL GLARESHIELD FLOODLIGHT BULB INSTL GLARESHIELD INSTALLATION GLARESHIELD REMOVAL GRAVITY BLEEDING GROUND COMMUNICATION GROUND RUNNING AND WARM-UP GUST LOCK AND DAMPER
33-20-00 39-10-00 39-10-00 32-40-00 23-10-00 71-00-00 27-70-00
1 1 1 1 1 7 4 1 1 1 1 9 1 6 1
HANDLING OF ESDS COMPONENTS AND EQUIPMENT HANDLING PRACTICES, FUEL HEADLINER INSTALLATION HEADLINER REMOVAL HEAT AND VENT SYSTEM INSPECTION HEATER AND DEFROSTER OPERATION HEATER MUFF INSTALLATION HEATER MUFF PRESSURE TEST HEATER MUFF REMOVAL HEATING AND VENTILATION, INSPECTION OF HOISTING HORIZONTAL STABILIZER INSTALLATION HORIZONTAL STABILIZER REMOVAL HORN SYSTEM, THROTTLE WARNING HOSE ASSEMBLY INSTALLATION HUMIDITY AND DUST EFFECTS ON ESDS COMPONENTS AND HYDRAULIC BRAKE SYSTEM HYDRAULIC PRESS BEARING REMOVAL
20-02-00 28-00-00 25-00-00 25-00-00 21-40-00 21-40-00 21-40-00 21-40-00 21-40-00 21-40-00 07-00-00 55-10-00 55-10-00 32-60-00 20-06-00 20-02-00 32-40-00 20-05-00
3 2 5 5 7 1 7 7 7 7 1 1 1 1 1 8 1 1
30-00-00 71-00-00 71-00-00
1 7 8
ICE AND RAIN PROTECTION IDLE SPEED AND MIXTURE ADJUSTMENT IDLE SPEED AND MIXTURE ADJUSTMENT
EQUIPMENT
(EXCEPT 10-550 ENG) (10-550 ENG)
INTRODUCTION
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COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
IGNITION AND STARTER SWITCH IGNITION SYSTEM IGNITION TROUBLESHOOTING INDEFINITE STORAGE INDEX GUIDE INDICATOR CALIBRATION, FUEL QUANTITY INDICATORS, FUEL QUANTITY INDIRECT ELECTRICAL BONDING INDUCTION AIR FILTER INSP OF FUEL CELL VENT LINE/FILLER CAPS INSPECTING PITOT SYSTEM HOSES INSPECTION GUIDE 100-HOUR INSPECTION OF FUEL CELL FLAPPER VALVE INSPECTION OF HEATING AND VENTILATION INSPECTION OF THE HINGES INSPECTION OF THE OUTSIDE AIR TEMP GAGE INSPECTION, OUTBOARD WING MAIN SPAR CAP INSTRUMENT AIR PRESSURE, LOW INSTRUMENT AIR SYSTEM INSTRUMENT AIR SYSTEM SERVICING INSTRUMENT CLUSTER INSTt,
74-00-00 74-00-00 74-00-00 10-00-00 IN-TR-OD 28-40-00 28-40-00 20-03-00
INSTRUMENT CLUSTER
REMOVAL, ENGINE ENGINE AND FLIGHT POST LIGHT INSTALLATION POST LIGHT REMOVAL REMOVAL, ENGINE AND FLIGHT WEDGE LIGHT TRAY INSTL WEDGE LIGHT TRAY REMOVAL
INSTRUMENT INSTL, INSTRUMENT INSTRUMENT INSTRUMENT INSTRUMENT INSTRUMENT
JACKING
KEYWASHERS
LANDING LANDING LANDING LANDING LANDING LANDING LANDING
(TAB
GEAR GEAR GEAR GEAR GEAR GEAR GEAR
AND CUP
TYPES)
INSTALLATION
ACTUATOR ASSEMBLY INSTL ACTUATOR ASSEMBLY REMOVAL ASSEMBLY, MAIN ASSEMBLY, NOSE CLEANING AND PARTS REPL, MAIN CLEANING AND PARTS REPL, NOSE DISASSEMBLY, MAIN
PAGE
1 1 1 1 3 1 1 1 3
12-20-00 28-20-00 34-10-00 05-20-00 28-10-00 21-40-00 27-21-00 34-10-00 57-00-00 36-00-00 36-00-00 36-00-00 39-10-00 39-10-00 39-10-00 33-20-00 33-20-00 39-10-00 33-20-00 33-20-00
3 2 5 6 7 7 3 11 3 1 3 1 1 1 1 1 1 1 1
07-00-00
1
20-07-00
5
32-30-00
1 1 5 7 4 2 2
32-30-00 32-10-00 32-20-00 32-10-00 32-20-00 32-10-00
INTRODUCTION
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COMPONENT OR
CHAPTER AND
ITEM
SUB
SUB SYSTEM
LANDING GEAR DISASSEMBLY, NOSE LANDING GEAR DYNAMIC BRAKE RELAY CHECK LANDING GEAR DYNAMIC BRAKE RELAY INSTL LANDING GEAR DYNAMIC BRAKE RELAY REMVL LANDING GEAR ENGINE COMPARTMENT-LOCATED RETRACTAND PREVENT SWITCH ADJUSTMENT AFTER,AND CJ-180 AND LANDING GEAR ENGINE COMPARTMENT-LOCATED WARNING SWITCH ADJUSTMENT (CE-748,CE-772,iHRU CE-1300,CE-1302 THRU CE-1306,CJ-149 THRU CJ-179,D10097,D-10120 AND AFTER,E-1111,E-1241 THRU 2110,EXCEPT E-1946 AND E-2104,AND EA-1 THRU EA-388,
CHAPTER
PAGE
32-20-00 32-30-00 32-30-00 32-30-00 32-60-00
1 2 2 2 6
32-60-00
1
32-60-00
1
32-60-00
2
32-30-00 32-10-00 32-20-00 32-10-00 32-20-00 32-10-00 32-20-00 32-30-00 32-30-00 32-60-00
1 1 1 1 1 2 1 2 2 3
32-60-00
7
32-40-00 32-30-00 32-20-00 32-30-00 32-30-00
1 1 1 8 8
32-30-00 32-30-00 32-30-00 32-30-00 32-30-00 32-30-00 32-30-00 32-30-00
7 9 2 2 1 4 9 11
AFTERjCE1301.CE-1307
EXCEPT EA-320) LANDING GEAR ENGINE COMPARTMENT-LOCATED WARNING SWITCH ADJUSTMENT (CE-1301,CE-1307 AND AFTER,AND CJ-180 AND AFTER) LANDING GEAR EXTENSION SYSTEM, MANUAL LANDING GEAR INSTALLATION, MAIN LANDING GEAR INSTALLATION, NOSE LANDING GEAR LUBRICATION, MAIN LANDING GEAR LUBRICATION, NOSE LANDING GEAR OVERHAUL, MAIN LANDING GEAR OVERHAUL, NOSE LANDING GEAR MOTOR INSTALLATION LANDING GEAR MOTOR REMOVAL LANDING GEAR PEDESTAL-LOCATED WARNING SWITCH ADJUSTMENT (E-1946,E-2104,E-2111 AND AFTER,AND EA-320,EA-389 AND AFTER) LANDING GEAR PEDESTAL-LOCATED RETRACTPREVENT SWITCH ADJUSTMENT (E-2458,E-2468 AND AFTER, AND EA-320, EA-389 AND AFTER) LANDING GEAR POSITION LIGHT ADJUSTMENT LANDING GEAR REMOVAL, MAIN LANDING GEAR REMOVAL, NOSE LANDING GEAR RETRACT ACTUATOR ASSEMBLY LANDING GEAR RETRACT ACTUATOR CLEANING AND PARTS REPLACEMENT LANDING GEAR RETRACT ACTUATOR DISASSEMBLY LANDING GEAR RETRACT ACTUATOR FUNCTIONAL TEST LANDING GEAR RETRACT ROD INSTL, MAIN LANDING GEAR RETRACT ROD REMOVAL, MAIN LANDING GEAR RETRACT SYSTEM LUBRICATION LANDING GEAR RIGGING LANDING GEAR SAFETY SYS MAIN AND ADJUST LANDING GEAR SAFETY SYS MICROSWITCH ADJUST
INTRODUCTION Page 21 A18
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BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
32-30-00 LANDING GEAR SAFETY SYS PRESS SWITCH ADJ 32-30-00 LANDING GEAR SAFETY SYS SAFETY SWITCH CHECK 32-30-00 LANDING GEAR SAFETY SYS SAFETY SWITCH CHECK 32-20-00 LANDING GEAR SHIMMY DAMPER 32-20-00 LANDING GEAR SHIMMY DAMPER OVERHAUL 32-20-00 LANDING GEAR SHIMMY DAMPER WEAR TOLERANCE 12-20-00 LANDING GEAR SHOCK STRUTS 32-00-00 LANDING GEAR SYSTEM 32-00-00 LANDING GEAR WEAR TOLERANCE, MAIN 32-00-00 LANDING GEAR WEAR TOLERANCE, NOSE 33-40-00 LANDING LIGHT INSTALLATION 33-40-00 LANDING LIGHT REMOVAL 28-10-00 LEAKAGE TEST, FUEL CELL 08-00-00 LEVELING 33-20-00 AND/OR POSITION) LIGHT BULB INSTL 33-20-00 LIGHT BULB REMVL WARNING AND/OR POSITION)LIGHTS 33-40-00 LIGHT BULB REPLACEMENT CHART-1 33-40-00 LIGHT, STEP 32-60-00 LNDG GR RETRACT-PREVENT SW-ENG COMPT-LOCATED (CE-1301, CE-1307 AND AFTER;CJ-180 AND AFTER) 32-60-00 LNDG GR WARN SW ADJUST-ENG COMPT-LOCATED (CE-748, CE-772 THRU CE-1300, CE-1302 THRU CE-1306; CJ-149 THRU C3-179, D-10097, D-10120, AND AFTER; E-llll, E-1241 THRU E-2110, EXCEPT E-1946 AND E-2104; EA-1 THRU EA-388, EXCEPT EA-320 32-60-00 LNDG GR WARN SW ADJUST-ENG COMPT-LOCATED (CE-1301 CE-1307 AND AFTER; CJ-180 AND AFTER) 33-40-00 LIGHT, STEP 20-07-00 LOCKWIRE AND COTTER PIN REQUIREMENTS 20-07-00 LOCKWIRE HOLE ALIGNMENT 20-07-00 LOCKWIRE INSTALLATION PROCEDURES 20-07-00 LOCKWIRE TWISTING IN-TR-OD LOG OF EFFECTIVE REVISIONS 33-40-00 LOWER ROTATING BEACON INSTALLATION 33-40-00 LOWER ROTATING BEACON REMOVAL 91-00-00 LUBRICANTS, THREAD 32-30-00 LUBRICATION LANDING GEAR RETRACT SYSTEM 12-20-00 LUBRICATION OF LANDING GEAR UPLOCK ROLLERS 32-10-00 LUBRICATION, MAIN LANDING GEAR 32-20-00 LUBR~CATION, NOSE LANDING GEAR 12-20-00 LUBRICATION
IWARN
MAGNESIUM CORROSION REMOVAL MAGNESIUM CORROSION TREATMENT MAGNETO DROP-OFF CHECK
20-09-00 20-09-00 74-00-00
PAGE 11 9 9 9 9 12 2 1
7 4 5 5 6 1 1 1 6 1 6 1
2
1 1 4 1 4 2 5 4 11 1 5 1 1 5
4 4
2
INTRODUCTION Page 22
Aug 18/95
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BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT OR SUB
ITEM
SYSTEM
CHAPTER AND SUB CHAPTER
PAGE
MAGNETO INSTALLATION AND TIMING MAGNETO POINT GAP AND TIMING MAGNETO PREPARATION FOR INSTL MAGNETO PREPARATION MAGNETO PRESSURIZATION AIR FILTER MAGNETO REMOVAL MAGNETO TIMING MAIN LANDING GEAR ASSEMBLY MAIN LANDING GEAR CLEANING AND PARTS REPL MAIN LANDING GEAR DISASSEMBLY MAIN LANDING GEAR INSTALLATION MAIN LANDING GEAR LUBRICATION MAIN LANDING GEAR REMOVAL MAIN LANDING GEAR RETRACT ROD INSTALLATION MAIN LANDING GEAR RETRACT ROD REMOVAL MAIN LANDING GEAR SHOCK STRUTS SERVICING MAIN WHEEL AND BRAKE ASSY INSTALLATION MAIN WHEEL AND BRAKE ASSEMBLY REMOVAL MAIN WHEEL ASSEMBLIES MAIN WHEEL INSPECTION AND CLEANING MAIN WHEEL JACKING MANIFOLD PRESSURE ADJUSTMENT MANIFOLD PRESSURE ADJUSTMENT MAP LIGHT BULB INSTALLATION MAP LIGHT BULB REMOVAL MARKING OF ESDS COMPONENTS AND EQUIPMENT MASTER CYLINDER ASSEMBLY, BRAKE MASTER CYLINDER CLEANING AND PARTS RPL, BRAKE MASTER CYLINDER DISASSEMBLY, BRAKE MASTER CYLINDER INSTALLATION, BRAKE MASTER CYLINDER LINKAGE ADJUST, BRAKE MASTER CYLINDER REMOVAL, BRAKE MECHANICAL PRESS BEARING REMOVAL METAL SURFACE PREPARATION AND ELECTRICAL BONDING MODEL DESIGNATION PLACARD MOORING MOTOR INSTALLATION, FLAP MOTOR INSTALLATION, LANDING GEAR MOTOR REMOVAL, FLAP MOTOR REMOVAL, LANDING GEAR
74-00-00 74-00-00 74-00-00 74-00-00 74-00-00 74-00-00 74-00-00 32-10-00 32-10-00 32-10-00 32-10-00 32-10-00 32-10-00 32-30-00 32-30-00 12-20-00 32-40-00 32-40-00 32-40-00 32-40-00 07-00-00 71-00-00 81-00-00 33-20-00 33-20-00 20-02-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 20-05-00 20-03-00 11-00-00 10-00-00 27-50-00 32-30-00 27-50-00 32-30-00
4 3 3 4 3 3 4 5 4 2 1 1 1 3 3 2 4 3 1 4 1 15 1 2 2 11 7 7 7 7 7 6 1 3 1 1 4 1 3 1
NONPOSITIONING TYPE FITTING INSTALLATION NOSE GEAR INSTALLATION NOSE GEAR LUBRICATION NOSE GEAR REMOVAL
20-06-00 32-20-00 32-20-00 32-20-00
2 1 1 1
INTRODUCTION
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COMPONENT ITEM OR SUB SYSTEM
NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE NOSE
NOSE
GEAR SHIMMY DAMPENER ASSEMBLY GEAR SHIMMY DAMPENER CLEANING/PARTS REPL GEAR SHIMMY DAMPENER DISASSEMBLY GEAR SHIMMY DAMPENER INSTALLATION GEAR SHIMMY DAMPENER MFG WEAR TOLERANCE GEAR SHIMMY DAMPENER REMOVAL LANDING GEAR ASSEMBLY LANDING GEAR CLEANING AND PARTS REPL LANDING GEAR DISASSEMBLY LANDING GEAR MFG WEAR TOLERANCE LANDING GEAR SHOCK STRUT WHEEL ASSEMBLY WHEEL INSPECTION AND CLEANING WHEEL INSTALLATION WHEEL REMOVAL WHEEL STEERING WHEEL TRAVEL STOP ADJUSTMENT
OIL BREAK-IN OIL COOLER INSTALLATION OIL COOLER REMOVAL OIL FILTER INSTALLATION OIL FILTER REMOVAL OIL GRADES OIL HIGH TEMPERATURE OIL PRESSURE ADJUSTMENT OIL SYSTEM OIL SYSTEM OPENABLE WINDOW INSTALLATION OPENABLE WINDOW REMOVAL OUTSIDE AIR TEMPERATURE GAGE REMOVAL OUTSIDE AIR TEMPERATURE GAGE OUTSIDE AIR TEMPERATURE GAGE INSTL OVERHAUL AND REPLACEMENT SCHEDULE OXYGEN CYLINDER INSTALLATION OXYGEN CONTROL CABLE ADJUSTMENT OXYGEN CYLINDER REMOVAL OXYGEN CYLINDER RETESTING OXYGEN HIGH PRESSURE TEST PROCEDURE OXYGEN LOW PRESSURE TEST PROCEDURE
OXYGEN SERVICING OXYGEN SYSTEM PURGING OXYGEN SYSTEM
CHAPTER AND SUB CHAPTER 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 12-20-00 32-40-00 32-40-00 32-40-00 32-40-00 32-50-00 32-50-00
79-00-00 79-00-00 79-00-00 12-10-00 12-10-00 79-00-00 79-00-00
71-00-00 12-10-00 79-00-00 56-20-00 56-20-00 34-10-00 34-10-00 34-10-00 05-10-00 35-00-00 35-00-00 35-00-00 35-00-00 35-00-00 35-00-00 12-10-00 35-00-00 12-10-00
PAGE
10 9 1 9
12 7 7 2 1 4 2 1 5 5 5 1 1
1 1 1 2 2 1 1 17 2 1 1 1 3 2 3 1 6 7 6 8
2 2 5 3 4
INTRODUCTION Page 24
Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT
ITEM OR SUB SYSTEM
PACKAGING OF ESDS COMPONENTS AND EQUIPMENT PAINT FREE AREAS PAINT FREE AREAS PAINT REMOVAL FROM MAGNESIUM PAINT REMOVAL FROM MAGNESIUM SURFACES PAINTING AREAS OF HIGH HUMIDITY PAINTING BATTERY BOX AND LID PAINTING MAGNESIUM S.URFACES PAINTING MAGNESIUM PAINTING MUD AND SPRAY AREAS PAINTING PROCEDURES, SPECIAL PAINTING RUBBER SEALS PAINTING, PROPELLER BLADE PARKING BRAKE ADJUSTMENT PARKING BRAKE CLEANING AND PARTS REPLACEMENT PARKING BRAKE VALVE ASSEMBLY PARKING BRAKE VALVE DISASSEMBLY PARKING BRAKE VALVE INSTALLATION PARKING BRAKE VALVE REMOVAL PARKING PASSENGER READING LIGHT BULB INSTL PASSENGER READING LIGHT BULB REMOVAL PERMANENT STATIC CONTROL WORKSTATION PINS, TAPER PIPE THREAD FITTING INSTALLATION PITOT AND STATIC PRESSURE SYSTEM PITOT AND STATIC SYSTEM TROUBLESHOOTING PITOT SYSTEM PRESSURE TEST PITOT SYSTEM PLACARD REPLACEMENT
PLATES/SKIN PORTABLE STATIC CONTROL WORKSTATION POSITION LIGHT ADJ, LANDING GEAR POST LIGHTS POWER PLANT POWER SUPPLY UNIT INSTALLATION POWER SUPPLY UNIT REMOVAL PREPARATION FOR PRESERVATION OF FUEL CELL (GOODYEAR) PRESERVATION OF FUEL CELL (UNIROYAL) PRESSURE POT BLEEDING PRESSURE REGULATOR ADJUSTMENT PRESSURE REGULATOR INSTALLATION PRESSURE REGULATOR REMOVAL PRESSURE, LOW INSTRUMENT AIR
CHAPTER AND SUB CHAPTER
20-02-00 20-08-00 20-00-00 20-00-00 20-08-00 20-00-00 20-00-00 20-08-00 20-08-00 20-00-00 20-00-00 20-00-00 20-00-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00 10-00-00 33-20-00 33-20-00 20-02-00 27-00-00 20-06-00 34-10-00 34-10-00 34-10-00 34-10-00 20-08-00 53-30-00 20-02-00 32-60-00 33-20-00 71-00-00 33-40-00 33-40-00 10-00-00 28-10-00 28-10-00 32-40-00 36-00-00 36-00-00 36-00-00 36-00-00
PAGE
10 7 6 3 5 5 6 6 5 5 5 5 5 7 7 7 7
7 7 1 1 1
4,6 2 2 1 1 1 1 3 1
5,8 1 1 1 2 2 4 9 9 10 7 6 6 2
INTRODUCTION
A18
Page 25 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
PRETREATMENT (WASH) PRIMER FOR URETHANE PAINT PRIMARY STRUCTURAL COMPONENTS PROPELLER ADJUSTMENT PROPELLER BLADE MAINTENANCE PROPELLER BLADES PAINTING PROPELLER DEICE BOOTS PROPELLER DEICER BOOT INSTALLATION PROPELLER DEICER BOOT REMOVAL PROPELLER DEICER TROUBLESHOOTING PROPELLER GOVERNOR ADJUSTMENT PROPELLER GOVERNOR INSTALLATION PROPELLER GOVERNOR REMOVAL PROPELLER INSTALLATION PROPELLER REMOVAL PROPELLER REPAIR, MINOR PROPELLERS PUMP INSTALLATION, AUXILIARY FUEL PUMP INSTALLATION, ENGINE DRIVEN FUEL PUMP REMOVAL, AUXILIARY FUEL
20-08-00 51-00-00 61-10-00 12-20-00
RADAR ANTENNA INSTALLATION RADAR ANTENNA REMOVAL
34-40-00 34-40-00 34-40-00 39-10-00 39-10-00 20-03-00 36-00-00 36-00-00 36-00-00 32-30-00 32-30-00 32-30-00 32-40-00 20-09-00 20-06-00 20-02-00 51-00-00 28-10-00
RADAR, WEATHER RADIO/AVIONICS EQUIPMENT INSTALLATION RADIO/AVIONICS EQUIPMENT REMOVAL RECOMMENDED MATERIALS REGULATOR ADJUSTMENT, PRESSURE REGULATOR INSTALLATION, PRESSURE REGULATOR REMOVAL, PRESSURE RELAY CHECK, DYNAMIC BRAKE RELAY INSTL, LANDING GEAR DYNAMIC BRAKE RELAY REMOVAL, LANDING GEAR DYNAMIC BRAKE RELINING THE BRAKES REMOVAL OF CORROSION FROM ALUMINUM SURFACES REMOVAL OF TUBE AND HOSE ASSEMBLIES REMOVAL/INSTALLATION OF ESDS EQUIPMENT REPAIR OF FIBERGLASS COMPONENTS REPAIR OF FUEL CELL (GOOOYEAR REPAIR OF FUEL CELL (UNIROYAL REPLACING ELEVATOR TRIM TAB RESERVOIR INSTL, FUEL (CJ-149 AND AFT) RETAINING RINGS (SPIROLOX, ETC.) INSTALLATION RETRACT ACTUATOR CLEANING AND PARTS REPL, LANDING GEAR RETRACT ACTUATOR FUNCTIONAL TEST, LANDING GEAR
20-08-00 12-20-00 30-60-00 30-60-00 30-60-00 61-20-00 61-20-00 61-20-00 61-10-00 61-10-00 61-10-00 61-10-00
28-20-00 28-20-00 28-20-00
28-10-00 27-30-00 28-10-00 20-07-00 32-30-00 32-30-00
PACE 4 1 1 3 7 1 5
5 1 1 1 1 1 1 2 1 1 1 1
1 1 1 2 1 2 7 6 6 3 3 3 6 3 1 1 2 9 9 6 1 5 8 9
INTRODUCTION Page 26
Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
ALPHABETICAL INDEX
COMPONENT OR SUB
ITEM
SYSTEM
RETRACT RETRACT RETRACT RETRACT RETRACT RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING RIGGING
ACTUATOR ASSY, LANDING GEAR ACTUATOR DISASSY, LANDING GEAR ROD TNSTL, MAIN LANDING GEAR ROD REMOVAL, MAIN LANDING GEAR SYSTEM LUBRICATION, LANDING GEAR AILERON CONTROL SYSTEM AILERON CONTROL SYSTEM ELEV TAB, COMPENSATE YAW TO LEFT EtEV TAB, COMPENSATE YAW r0 RH ELEVATOR CONTROL SYSTEM ELEVATOR TAB ELEVATOR TRIM TAB RUDDER CONTROL SYSTEM THE CONTROL COLUMN CHAIN T~E LANDING GEAR RIGGING, ELEVATOR TAB, CORRECT FOR YAW ROTATING BEACON
CHAPTER AND SUB CHAPTER
32-30-00 32-30-00 32-30-00 32-30-00 32-30-00 27-10-00 27-11-00 27-21-00 27-21-00 27-30-00 27-21-00 27-30-00 27-20-00 27-10-00 32-30-00 27-21-00 33-40-00 12-20-00
ROTCN LOCKS RUBBER SEALS RUDDER BALANCING RUDDER CONTROL SYSTEM RIGGING RUDDER INSTALLATION RUDDER REMOVAL RUDDER RIGGING PROCEDURE RUDDER-MAINTENANCE PRACTICES RUDDER, MODELS F33A, F33C, A36 AND A36TC RUDDER, V35B RUDDERVATOR BALANCING RUDOERVATOR INSTALLATION RUDDERVATOR REMOVAL RUDOERVATOR Rigging PRACTICES RUDDERVATOR-MAINTENANCE
27-20-00 27-21-00 55-20-00 27-21-00 27-21-00 27-21-00 27-21-00
SAFETY SWITCH CHECKING IN TEST POSITION, LANDING GEAR SAFETY SYS MAINT AND ADJ, LANDING GEAR SAFETY SYSTEM OPTIONAL LANDING GEAR SCHEDULED MAINTENANCE CHECKS SEAT INSTALLATION, PASSENGER SEAT INSTALLATION, PILOT AND COPILOT SEAT INSTL, FIFTH AND SIXTH, (A36 ANO A36SC) SEAT INSTL, FIFTH (MODEL F33A AND V35B) SEAT REMOVAL, FIFTH AND SIXTH (A36 AND A36TC) SEAT REMOVAL, FIFTH (MODELS F33A AND V35B) SEAT REMOVAL, PASSENGER
32-30-00 32-30-00 32-00-00 05-20-00 25-00-00 25-00-00 25-00-00 25-00-00 25-00-00 25-00-00 25-00-00
20-08-00 55-40-00 27-20-00
27-20-00 27-20-00 27-21-00 27-20-00
PA
8 7 3 3
1 4
4
9 9
1
7 6 1 1 4 7 4 4 7 1 1 1 1 1 1 1 1 3 3 3 5 1
9 9 1 1 3 1 4 4 4 4
3
INTRODU
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
ALPHABETICAL INDEX
COMPONENT
ITEM OR SUB SYSTEM
CHAPTER AND
SEAT REMOVAL, PILOT AND COPILOT SEAT STOWAGE, FIFTH AND SIXTH (A36 AND A36TC) SEAT STOWAGE, FIFTH (F33A, F33C AND V35B) SEATING SECONDARY STRUCTURAL COMPONENTS SELECTOR VALVE INSTALLATION, FUEL SELECTOR VALVE REMOVAL, FUEL SELF-LOCKING NUTS SENSOR INSTALLATION, FUEL QUANTITY SENSOR REMOVAL, FUEL QUANTITY SHAFT INSTALLATION, FLAP SHAFT INSTALLATION, FLAP INNER FLEX SHAFT REMOVAL, FLAP SHAFT REMOVAL, FLAP INNER FLEX SHIMMY DAMPER SHIMMY DAMPER SHIMMY DAMPENER ASSEMBLY, NOSE GEAR SHIMMY DAMPENER CLEANING/PARTS REP NOSE GEAR SHIMMY DAMPENER DISASSEMBLY, NOSE GEAR SHIMMY DAMPENER INSTALLATION, NOSE GEAR SHIMMY DAMPENER OVERHAUL, NOSE GEAR SHIMMY DAMPENER REMOVAL, NOSE GEAR SHIMMY DAMPENER WEAR TOLERANCE SHOCK STRUT SHOCK STRUT, NOSE LANDING GEAR SHOCK STRUTS, MAIN LANDING GEAR SHUTTLE VALVE, BRAKE SKIN THICK, EMP (F33A, F33C, A36, A36TC) SKIN THICKNESS, EMPENNAGE (V35B) SKIN THICKNESS, FUSELAGE (A36 AND A36TC) SKIN THICKNESS, FUSELAGE (F33A AND F33C) SKIN THICKNESS, FUSELAGE (V35B) SLIP RING ALIGNMENT SLIP RING MACHINING SLIP RING SLOTTED, STEEL LOCKNUTS (PREVAILING TORQUE TYPE) SPARK PLUGS SPECIAL CONDITIONS CAUTIONARY NOTICE SPECIAL PAINT PROCEDURES SPECIAL TOOLS STABILIZER INSIALLATION, HORIZONTAL STABILIZER INSTALLATION, RUDDERVATOR STABILIZER INSTALLATION, VERTICAL STABILIZER REMOVAL, HORIZONTAL STABILIZER REMOVAL, V35 ELEVATOR STABILIZER REMOVAL, VERTICAL
25-00-00 25-00-00 25-00-00 25-00-00 51-00-00 28-20-00 28-20-00 20-07-00 28-40-00 28-40-00 27-50-00 27-50-00 27-50-00 27-50-00 12-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 32-20-00 12-20-00 32-20-00
SUB CHAPTER
32-10-00 32-40-00 55-00-00 55-00-00
53-30-00 53-30-00 53-30-00 30-60-00 30-60-00 30-60-00 20-07-00 12-20-00 05-10-00 20-08-00 12-20-00 55-10-00 55-10-00 55-30-00 55-10-00 55-10-00 55-30-00
PAGE 1 4 4 1 1 1 1 1 1 1 4 5 4 5 2 7 10 9 9 9 9 9 12 2 1 1 1 2 5 8 4 6 10 11 13 1 3 1 7 19 1 1 1 1 1 1
INTRODUCTION
Page 28 Aug 18/95
A18
BEECHCRAFT BONANZA SERIES
MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT
ITEM
CHAPTER AND
OR SUB SYSTEM
SUB CHAPTER
STAINLESS STEEL AND TITANIUM SURFACES STALL WARNING SYSTEM ADJUSTMENTS STALL WARNING SYSTEM DESC AND OPER STALL WARNING SYSTEM MAINT PRACTICES STALL WARNING/SAFE FLIGHT SYS DESC/OPER STALL WARNING STALL WARNING/SAFE FLIGHT SYS MAINT PRAC STANDBY AIR FILTER INSTL (INTAKE) STANDBY AIR FILTER REMOVAL (INTAKE) STANDBY AIR FILTER INSTL (INLINE) STANDBY AIR FILTER REMOVAL (INLINE) STANDBY GENERATOR-DESC AND OPER STANDBY GENERATOR-MAINTENANCE PRAC STANDBY INSTRUMENT AIR SYSTEM STARTER BRUSHES STARTER INSTALLATION STARTER LUBRICATION STARTER OVERHAUL STARTER REMOVAL STARTER TROUBLESHOOTING STARTING STATIC AIR SYSTEM-EMERGENCY STATIC AIR SYSTEM-NORMAL STATIC SYSTEM CHECKS STATIC WICK INSTALLATION STATIC WICK REMOVAL STATIC WICKS STATION DIAGRAMS (MODEL A36 AND A36TC) STATION DIAGRAMS (MODEL STATION DIAGRAMS (MODEL 35 STEEL CORROSION REMOVAL STEERING, NOSE WHEEL STEP LIGHT´•L STORAGE AND TRANSIT OF ESDS COMPONENTS AND STORAGE, EXTENDED STORAGE, TEMPORARY STORAGE STORM WINDOW INSTALLATION STORM WINDOW REMOVAL STRAINER INSTL (SELECTOR VALVE), FUEL STRAINER INSTL (WING FUEL CELLS), FUEL STRAINER REMOVAL (SELECTOR VALVE), FUEL STRAINER REMOVAL (WING FUEL CELLS), FUEL STRAINERS, CLEANING FUEL STRIPPING AND CLEANING URETHANE PAINT STROBE LIGHT POWER SUPPLY INSTL
20-03-00 27-31-00 27-31-00 27-31-00 27-31-00 27-31-00 27-31-00
36-00-00 36-00-00 36-00-00 36-00-00 24-31-00 24-31-00 36-00-00 80-10-00 80-10-00 80-10-00 80-10-00 80-10-00 80-10-00 80-10-00 34-10-00 34-10-00 34-10-00 23-60-00 23-60-00 23-60-00 06-00-00 06-00-00 06-00-00 20-09-00 32-50-00 33-40-00
33j
EQUIPMENT
20-02-00 10-00-00 10-00-00 10-00-00 56-10-00 56-10-00 28-20-00 28-20-00 28-20-00 28-20-00 28-00-00 20-08-00 33-40-00
PAGE 6 1 1 1 1 1 1 5 5 5 5 1 1 1 2 1 1 1 1 1 1 1 1 2 1 1 1 8 6 7 5 1 1
12 1 2 1 2 2 2 3 2 3 2 4
2
INTRODUCTION
A18
Page 29 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
ALPHABETICAL INDEX
COMPONENT ITEM OR SUB SYSTEM
CHAPTER AND SUB CHAPTER
STROBE LIGHT POWER SUPPLY REMOVAL STROBE LIGHT STRUCTURAL REPAIR SUBPANEL, RIGHT AND LEFT SUPPLEMENTARY PUBLICATIONS SURFACES SUSCEPTIBLE TO MUO AND SPRAY SURFACES, CONTROL
33-40-00 33-40-00 51-00-00 39-10-00 IN-TR-OD 20-08-00 27-00-00
2 1 1 2 6 7 1
TAB FREE PLAY, CHECKING ELEVATOR TAB HINGES, INSPECTION TAIL NAVIGATION LIGHT INSTALLATION TAIL NAVIGATION LIGHT REMOVAL TAIL STROBE/NAV LIGHT INSTALLATION TAIL STROBE/NAV LIGHT REMOVAL TAPER PINS, FLIGHT CONTROLS TAXI LIGHTINSTALLATION TAXI LIGHT REMOVAL TAXIING TEMPORARY STORAGE TEST FOR FUEL CELL LEAKAGE TESTING THE STATIC SYSTEM FOR LEAKS THREAD LUBRICANTS THROTTLE ADJUSTMENT THROTTLE WARNING HORN SYSTEM TIE-DOWN, NORMAL TIME LIMITS TIRE AND WHEEL MAINTENANCE TIRES TIRES TIT INDICATOR CALIBRATION TIT INDICATOR CALIBRATION
27-30-00 27-21-00 33-40-00 33-40-00 33-40-00 33-40-00 27-00-00 33-40-00 33-40-00 09-00-00 10-00-00 28-10-00 34-10-00 91-00-00 71-00-00 32-60-00 10-00-00 05-10-00 32-40-00 12-20-00 32-40-00 77-00-00 81-00-00 20-00-00 91-00-00 91-00-00 09-00-00 32-50-00 27-30-00 27-30-00 27-30-00 27-30-00 33-20-00 33-20-00 27-30-00 27-30-00
11 10
TORQUE WRENCHES TORQUING COARSE THREAD BOLTS IN SMEAR TORQUING FINE THREAD BOLTS IN SMEAR TOWING TRAVEL STOP ADJUSTMENT, NOSE WHEEL TRIM TAB ACTUATOR BRUSH REPLACE SCHED, ELEC TRIM TAB ACTUATOR INSTL, ELEC, (F33A, F33C, V35B) TRIM TAB ACTUATOR REMOVAL, ELEC, (F33A, F33C, V35B) TRIM TAB ACTUATOR, ELEVATOR TRIM TAB LIGHT BULB INSTALLATION TRIM TAB LIGHT BULB REMOVAL TRIM TAB SERVO INSTL, ELECTRIC ELEVATOR TRIM TAB SERVO REM, ELECTRIC ELEVATOR
PAGE
5 5 4 4 2
5 5 2 2 6
2 11 8 1 1 1 3 1 1 1 8 1 11 11 1 1’ 13 12 12 6 2 2 11 11
INTRODUCTION
Page 30 Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT ITEM
CHAPTER AND
OR SUB
SUB
SYSTEM
TROUBLESHOOTING LANDING GEAR ELECTRICAL SYSTEM IROUBLESHOOTING-PITOT AND STATIC SYSTEM
CHAPTER
PAGE
TROUBLESHOOTING TUBE DAMAGE LIMITS TUBE INSTALLATION TUBING CLAMP TO BONDING JUMPER ELECTRICAL BONDING TURBOCHARGER ADJUSTMENT AND TEST TURBOCHARGER CONTROLLER INSTALLATION TURBOCHARGER CONTROLLER REMOVAL TURBOCHARGER INSPECTION TURBOCHARGER INSTALLATION TURBOCHARGER LEAK TEST TURBOCHARGER REMOVAL TURBOCHARGER SHAFT FREEING TURBOCHARGER SYSTEM TURBOCHARGER TROUBLESHOOTING TURNBUCKLE LOCK CLIP INSTALLATION TYPICAL BLIND GROUND STUD TYPICAL GROUND STUD ELECTRICAL BONDING
32-00-00 34-10-00 36-00-00 21-50-00 32-40-00 20-06-00 20-06-00 20-03-00 81-00-00 81-00-00 81-00-00 05-20-00 81-00-00 81-00-00 81-00-00 81-00-00 81-00-00 81-00-00 20-07-00 20-03-00 20-03-00
2 1 1 4 3 4 2 8 5 8 8 2 7 5 7 7 1 1 5 6 6
UPPER ROTATING BEACON INSTALLATION UPPER ROTATING BEACON REMOVAL URETHANE (EXTERIOR COLORS) URETHANE PAINT PROCEDURES (ALUMINUM) URETHANE PAINT REPAIR PROCEDURES URETHANE PAINTS URETHANE PRIMER URETHANE TOPCOATS URETHANE TOUCH-UP REPAIR UTILITY DOOR ADJUSTMENT UTILITY DOOR INSTL (MODEL A36 AND A36TC) UTILITY DOOR LATCH PIN ADJUSTMENT UTILITY DOOR REMOVAL (MODEL A36 AND A36TC) UTILITY DOOR WINDOW INSTALLATION UTILITY DOOR WINDOW REMOVAL UTILITY DOORS (MODEL A36 AND A36TC)
33-40-00 33-40-00 20-00-00 20-00-00 20-08-00 20-08-00 20-08-00 20-08-00 20-08-00 52-30-00 52-30-00 52-30-00 52-30-00 56-20-00 56-20-00 52-00-00
5 5 2 4 4 3 5 5 5 1 1 1 1 1 1 1
VALVE ASSEMBLY, PARKING BRAKE VALVE DISASSEMBLY, PARKING BRAKE VALVE INSTALLATION, PARKING
32-40-00 32-40-00 32-40-00
7 7 7
TROUBLESHOOTING, INSTRUMENT AIR SYSTEM TROUBLESHOOTING, AIR-CONDITIONING
INTRODUCTION
A18
Page 31 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MAN UAL ALPHABETICAL INDEX
COMPONENT
ITEM
OR SUB SYSTEM
VALVE VALVE VALVE VALVE VALVE
REMOVAL, PARKING
INSTALLATION,
FUEL SELECTOR INSTALLATION, PARKING BRAKE REMOVAL, FUEL SELECTOR REMOVAL, PARKING BRAKE VALVE, BRAKE SHUTTLE VENDOR PUBLICATIONS FILLER CAPS INSP, FUEL CELL VENT LINES VENTILATION BLOWER INSTALLATION VENTILATION BLOWER REMOVAL VERTICAL STABILIZER INSTALLATION VERTICAL STABILIZER REMOVAL VOLTAGE REGULATOR ADJUSTMENTS VOLTAGE REGULATOR INSTALLATION VOLTAGE REGULATOR REMOVAL
WARNING AND POSITION LIGHT BULB INSTL WARNING AND POSITION LIGHT BULB REMOVAL WARNING HORN SYSTEM, THROTTLE WAXING AIRPLANE FINISHES WEAR AND WEAR LIMITS, BRAKE WEATHER RADAR WHEEL AND TIRE MAINTENANCE WHEEL ASSEMBLIES, MAIN WHEEL ASSEMBLY AND BRAKE INSTALLATION WHEEL ASSEMBLY AND BRAKE REMOVAL WHEEL ASSEMBLY, NOSE WHEEL INSPECTION AND CLEANING MAIN WHEEL INSPECTION AND CLEANING, NOSE WHEEL INSTALLATION, NOSE WHEEL REMOVAL, NOSE WHEEL TRAVEL STOP ADJUSTMENT, NOSE WICKS, STATIC WINDOW CLEANING WINDOW INSTALLATION (FORWARD LEFT) WINDOW REMOVAL (FORWARD LEFT) WINDOWS AFT OF OPENABLE WINDOW INSTL WINDOWS AFT OF OPENABLE WINDOWS REMOVAL WINDSHIELD INSTALLATION WINDSHIELD REMOVAL WING ACCESS OPENINGS WING ADJUSTMENT WING ATTACH FITTINGS WING BOLT, NUT AND FITTING INSPECTION
CHAPTER AND SUB CHAPTER
32-40-00 ’28-20-00 32-40-00 28-20-00 32-40-00 32-40-00 IN-TR-OD 28-20-00 21-50-00 21-50-00 55-30-00 55-30-00 24-30-00 24-30-00 24-30-00
33-20-00 33-20-00 32-60-00 20-08-00 32-40-00 34-40-00 32-40-00 32-40-00 32-40-00 32-40-00 32-40-00
32-40-00 32-40-00 32-40-00 32-40-00 32-50-00 23-60-00 56-00-00 56-10-00 56-10-00 56-20-00 56-20-00 56-10-00 56-10-00 57-30-00 57-00-00 57-40-00 57-00-00
PAGE 7 2 7 2 7 1 6 3 11 11 1 1 7 7 6
1 1 1 3 1 1 3 1 4 3 1 4 5 6 5 1 1 1 1 1 1 1 1 1 1 4 1 7
INTRODUCTION Page 32
Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX
COMPONENT OR SUB
WING WING WING WING WING WING WING WING WING WING WING WING
ITEM
CHAPTER AND
SYSTEM
SUB CHAPTER
INSTALLATION LEADING EDGE AND MAIN SPAR REMOVAL LEADING EDGE AND MAIN SPAR INSTL MAIN SPAR CAP INSPECTION, OUTBOARD NAVIGATION LIGHT INSTALLATION NAVIGATION LIGHT REMOVAL REMOVAL SKIN THICKNESS STROBE LIGHT INSTALLATION STROBE LIGHT REMOVAL TIP INSTALLATION TIP REMOVAL
57-00-00 57-00-00 57-00-00 57-00-00 33-40-00 33-40-00 57-00-00 57-30-00 33-40-00 33-40-00 57-00-00 57-00-00
PAGE 2 1 2 11 4 4 1 2 4 3 1 1
"END"
INTRODUCTION
A18
Page 33 Aug 18/95
CHAPTER
TIME LIMITS/
MAINTENANCE CH EC KS
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
TIME LIMITS/MAINTENANCE CHECKS
CHAPTER 5
TABLE OF CONTENTS
PAGE
SOBJECT
5-1 0-00
Special Landing
1
Replacement Schedule
Overhaul and
Conditions
Cautionary
1
Notice
2
Gear
3
Power Plant
Flaps Fuel
4
Controls
Flight
and
4
System
4
Instruments Electrical
5
System
5
Miscellaneous
5-20-00
Scheduled Maintenance Checks
1
Maintenance Practices
Electric
Propeller
Deicer
(EiO-Hour Guide)
1
Electric
Propeller
Deicer
(100-Hour Guide)
1
Turbocharger(EA-l
3
and After)
25 Hours
3
50 Hours
3
100 Hours
3 3
E33C, F33C Spin Inspection (Acrobatic Category) 100-Hour
or
Annual
Inspection
A36 and
Program (Models
Special
Conditions Cautionary Notice
A.
or
Annual
6
B36TC)
FACTS
1GO-Hour
6
Guide
7 9
Inspection
9
Operational Inspection
10
B. Power Plant
C. Cabin and D.
A23
Wings
and
Baggage Compartment
13
Carry-Through Structure
15
E. Nose Gear
16
F. Main Gear and Brakes
17
G. Main Gear
Operation
18
H. Nose Gear
Operation
19
5-CONTENTS
Jun
28/02Page
1
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 5
TIME LIMITS/MAINTENANCE CHECKS
TABLE OF CONTENTS (CONTINUED)
SUBJECT
I. Rear
PAGE
Fuselage
and
Empennage
J. General
Jun
28/0Page
2
5-CONTENTS
19 20
A23
Ray~eon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 5
TIME LIMITS/MAINTENANCE CHECKS
LIST OF PAGE EFFECTIVITY
CI-IAPTER-SECnON-SUBJECT
PAGE
DATE
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5-EFFECTIVITY
Jun
28/02Pagel
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
OVERHAUL AND REPLACEMENT SCHEDULE replacement must be performed not later than the recommended period. The condition period can be used as a criterion for determining subsequent periods applicable individual airplane or fleet operation, provided the operator has an approved monitoring system.
The first overhaul
or
item at the end of the first
The time
periods
for
inspections noted in
this manual
are
based
on
of the to the
average usage and average environmental
con-
ditions.
NOTE The recommended function
as
periods
do not constitute
a
guarantee the item will reach the period without malby the manufacturer.
the aforementioned factors cannot be controlled
SPECIAL CONDITIONS CAUTIONARY NOTICE
WARNING I WARNIEIO)
performing maintenance on an engine or the Airframe, ALWAYS pull the starter conLanding Gear circuit breaker. This will remove power to the control as well as the igniter power relay and Landing Gear Control relay.
Prior to
trol circuit breakers and the starter
for Air Taxi, or other than normal operation, and airplanes operated in humid tropics, or cold and damp climates, etc., may need more frequent inspections for wear, corrosion and/or lack of lubrication. In these areas, periodic inspections should be performed until the operator can set his own inspection periods based on ex-
Airplanes operated
perience. NOTE The date noted
on
the "STANDARD AIRWORTHINESS CERTIFICATE", FAA Form No. 8100-2,
which is issued with each
ponents listed in the An
engine cycle
new
following
is defined
as
airplane,
is to be used
as
the basis for all TBO
or
replacement
com-
schedule.
the
period
of time from the initial start to shutdown of the
engine. This
encompasses start-up, increase to full or partial power las required during a flight regime) and back to complete engine shutdown. Normal operation results in the number of landings being equivalent to
azs
engine cycles.
5-1 0-00
Jun
28/02Pagel
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
OVERHAUL AND REPLACEMENT SCHEDULE
OVERHAUL OR REPLACE
ITEM
NOTE All items not listed
are
to be overhauled or
replaced
"on condition". "On condition" items
are to
be overhauled
or
unserviceable condition, if they are worn, inoperative, potentially replaced inspection normal maintenance. Primarily items that are calender, cycle not intermittent and inaccurate, repairable through or hour limited are included in the following list. reveals
if
unsafe
a
or
LANDING GEAR Main Gear
On condition
(Leaking or collapsed struts that cannot be by replacement will constitute the "On condition" requirement. Any pitting, corrosion, cracking,
Assembly
corrected
distortion
seal
or
visible
replacement will overhaul.) Nose Gear
wear
noted
during the seal requirement for
also constitute the
an
On condition
(Leaking or collapsed struts that cannot be by seal replacement will constitute the "On condition" requirement. Any pitting, corrosion, cracking, distortion or visible wear noted during the seal replacement will also constitute the requirement for an overhaul.)
Assembly
corrected
Nose Gear Retract Rod Rod-Ends
(All)
2000 hours
Actuator
4000 hours
Retract Motor
2000 hours
Retract Motor Brushes
500 hours
Shimmy Damper
On condition
Wheels and Tires
On condition
or on
Brake
Assembly
On condition
Brake
Lining
On condition
Cylinder
On condition
Shuttle Valve Assembly
On condition
Master
Parking
Brake Valve
All Hoses
Jun
28/025-10-00
I
condition
I
On condition
On condition
als
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE ITEM
(CONTINUED)
OVERHAUL OR REPLACE
POWER PLANT
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. Cabin Heater Muff
On condition
*Engine (Non-turbocharged)
1700 hours
*Engine (EA-I
1600 hours
*Reference
and
after)
Teledyne Continental Motors Corporation Service Bulletin M91-8,
Engine
Controls
On condition
Engine
Vibration Isolator Mounts
Engine
Exhaust
System
overhaul
dated
or on
July 10, 1991
or
subsequent.
condition
On condition
Starter
Inspect
at
engine overhaul,
overhaul
or
replace
on
condition
Standby Generator Standby Generator
1500 hours
Brushes
500 hours
Alternator
On condition
Oil Cooler
On condition,
Propeller (McCauley)
Refer to
Propeller (Hartzell)
replace
if contaminated
McCauley Service
Bulletin 1378
or
subsequent
Refer to the latest revision of Hartzell Service Letter 61 for TBO
Propeller Controls
On condition
Propeller Governor (McCauley)
At
engine
overhaul
condition but not to exceed
or on
1800 hours
Propeller Governor (Woodward)
At
engine overhaul
or on
condition. Refer to Woodward
I
Service Bulletin 3350. Air Pressure
Standby
Refer to
Pump
Air Pressure
All Hoses
Pump
Replacement Schedule
Every 600 hours Hoses
of pump
in Airborne SI 300-16
operation
carrying flammable liquids
at
engine
overhaul
or
every 5 years, whichever occurs first since the last replacement or delivery date of the airplane from the
factory; all other Engine
Air Filter
hoses
on
condition
Clean every 50 hours of operation (10 times max.). Replace every 500 hours or 1 year, whichever occurs first.
A23
5-1 0-00
Jun
28/02Page
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
OVERHAUL AND REPLACEMENT SCHEDULE ITEM
(CONTINUED)
OVERHAUL OR REPLACE
POWER PLANT
Engine
(Continued)
Baffle Seals
Replace Teledyne Continental
Magneto (Bendix
(TCM))
Motors
as
necessary
or
every 10 years of service.
Engine overhaul or every four years, whichever first. Refer to TCM Service Bulletin 643.
comes
FLAPS AND FLIGHT CONTROLS Aileron Trim and
Flight
Linkage
On condition On condition
Controls
Elevator Tab Actuator
On condition
Flap Motor and Gearbox
Replace
Flap Actuators
2000 hours
Flap Flexible Shaft
2000 hours
on
condition
FUEL SYSTEM On condition
Fuel Cells
Wing
Fuel
Quantity
Transmitters
Fuel Cell Drain Valve
Fuel
System Check
Valves
On condition On condition On condition every 10 years
Fuel Selector Valve
Replace
Fuel Boost
Overhaul every 10 years
Pump
Hoses
All Hoses
carrying
flammable
liquids
at
engine overhaul
or
every 5 years, whichever occurs first since the last replacement or delivery of the airplane from the factory; all other hoses
Fuel Cell Reservoir Kit (If installed)
Replace
on
condition
foam insert every 10 years
INSTRUMENTS Turn Coordinator
On condition
Altimeter
Every 24 months calibrate)
Directional
Gyro
Horizon
Gyro
Pressure
nuJ4
28/02
(inspect and
On condition
On condition
Gyro
Page
per FAA directive
Gage
5-1 0-00
On condition
A23
I
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE ITEM
(CONTINUED)
OVERHAUL OR REPLACE
INSTRUMENTS (Continued) Units
Engine Gage
On condition
Airspeed Indicator
On condition
Rate-Of-Climb
On condition
Fuel Flow/Manifold Pressure Indicator
On condition
Tachometer
On condition
Clock
On condition
Flap Position indicator
On condition
Free Air
On condition
Temperature Indicator
Pressure
System
Standby
Pressure
Air Pressure
Filter
(In-line
System
Regulator
and
Filters
Intake)
(In-line
and
300 hours of
Every
300 hours of pump operation
airplane operation
On condition
Valve
On condition
All Hoses
Standby
Intake)
Every
Air Pressure
System
Check Valve
Replace
every 10 years
ELECTRICAL SYSTEM
Battery Master Relay
On condition
All Other
On condition
Relays
Voltage Regulator
On condition
Starter
On condition
Relay
Battery (Emergency
Locator
Transmitter)
Replace
at 50% of useful life
las
any time transmitter is used cumulative hour or
stated
more
on
than
the
battery)
one
MISCELLANEOUS Hand Fire Cabin
Extinguisher
Heating
and
Ventilating
Ducts
Inspect
every 12 months,
Inspect
every 12 months
Oxygen Regulator
On condition
Air Conditioner Filter
On condition
Air Conditioner
On condition
Seat Belts
or
Compressor
Inspect every
Shoulder Harnesses
Oxygen Cylinder (Lightweight
3HT
Type)
12 months
Hydrostatically years
or
recharge
as
necessary
or on
condition
or on
condition
test every 3 years.
Replace every
4,380 refills (ICC regulation), whichever
24
occurs
first.
A23
5-1 0-00
Jun
28/02Page
5
Ray~hean Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE
(CONTINUED)
OVERHAUL OR REPLACE
ITEM
MISCELLANEOUS (Continued)
Oxygen Cylinder (Standard Weight Wing-Attach Bolts
3AA
Type)
Hydrostatically Replace Refer to
Jun
28/0Page
6
5-1 0-00
test every 5 years
10 years after initial Chapter 57.
inspection
or on
condition.
n?s
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
SCHEDULED MAINTENANCE CHECKS
ELECTRIC PROPELLER DNCER
MAINTENANCE PRACTICES
(50 HOUR GUIDE)
of the propeller deicer system should be inspected every 50 hours for the appearance of following inspections may provide means for detecting and correcting such defects before they render system inoperative:
The various
components
defects. The the deicer a.
Lock the brakes and
operate the engine
at near takeoff power. Turn the deicer
systems switch ON and observe
the ammeter for at least 3 minutes. If the ammeter needle does not indicate amperage (reference ELECTRIC PROPELLER DEICING in Chapter 30-60-00 for proper amperagej for 90 seconds at 90 second intervals, refer to the
troubleshooting
chart for the
probable
sources
of trouble.
WARNING IWdRNINO) Before moving propeller, make certain that ignition switch is OFF and that engine has cooled completely. There is always some danger of a cylinder firing when propeller is moved.
CAUTION I IcnuTloN While
following
the instructions of step b,
tween the brushes and
b.
With the
engine
move
the
forth to
propeller back and
prevent arcing be-
slip ring.
shut off, turn the deicer switch ON and feel the deicer boots
quence of heater operation. The presence of local hot spots indicates service should be repaired before more serious damage develops.
on
the
damage
propeller for
to the deicer
the proper
se-
heaters, which
Remove the spinner and open all access doors pertaining to the wiring and components of the deicer system. Turn the deicer switch ON and station an assistant in the cockpit 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 c.
wiring. Any short d.
or
movement of the ammeter, other than the
To extend the life of the lead
at least 1/2 inch from the e.
flicker that
occurs
at 90 second
intervals, indicates
Check for
damaged
existing
strap between the hub clamp and clip, reposition the bend in the strap
a
brush rods
Check for radio noise
or
at
a
point
location of the bend. or
springs
ELECTRIC PROPELLER DNCER a.
cycling
open circuit that must be located and corrected.
and for
worn or
damaged
brushes.
(100 HOUR GUIDE)
radio compass interference
at near takeoff power with the radio
by operating the engine
If, under these conditions, noise or interference occurs when the deicer switch is ON and disappears when the switch is OFF, refer to the troubleshooting chart for the probable source of trouble. gear turned
on.
WARNING IWARNINOI Before
moving propeller,
completely.
nza
There is
make certain that
always
some
ignition switch
is OFF and that
danger of a cylinder firing when
a
engine has cooled
propeller is moved.
5-20-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL b.
Check all
ness.
clamps, clips, mountings, electrical connections or missing safety wire.
and connectors for
tightness
and electrical sound-
Check also for loose, broken
Closely check the
deicer boots for wrinkles, loose or torn areas, particularly around the outboard end and at the the strap passes under the hub clamp. Look for abrasion or cuts along the leading edge of 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 detec.
point where riorated
d.
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 mamissing or damaged in the area under the hub clamp or on the edge of the spinner dome. Manually oppropeller from "high pitch" to "low pitch" while checking that the deicer lead straps do not come under
teria\ is not erate the
tension. e.
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 (23, Chart i, 91-00-00). After such a allow a run-in time of 5 hours of engine operation before turning on the deicer system.
Check the
grease
or
cleaning,
wobble is detected, check the alignment of the slip rings to the prop shaft with a dial indicator. the turning prop to check the slip ring alignment, push in on the prop to eliminate play in the propeller thrust If the out over 360" of rotation is over 0.005 inch or if over any 4-inch are it exceeds 0.002 inch, refer run bearing. to the paragraph on SLIP RING ALIGNMENT in Chapter 30-60-00. f.
If
uneven wear or
While
g.
Examine the brush
sure
that connections
mounting bracket and housing for cracks, deformation, tight and that the leads are not chafed or binding.
or
other indications of
damage. Make
are
fully on its slip ring over 360" of rotation. If the brush is not properly aligned, elongate the holes in the mounting bracket to raise or lower the brush block to the proper position. If the brushes ride BOTH high and low with respect to the slip rings in 360" of rotation, the slip ring assembly is eccentrically mounted and the spinner bulkhead must be replaced. For the correct angular location of the brushes to the slip ring, refer to the illustrations in Chapter 30-60-00. h.
Check to
that each brush rides
see
add shims under the brush block
or
Check for proper spacing between the brush block and slip rings as indicated in DEICER BRUSH REPLACEMENT, Chapter 30-60-00. If this distance is not within the specified limits, loosen the mounting screws and reposi-
i.
tion them in the
bearing plate
elongated holes until the block is properly positioned. If necessary, mounting bracket until the brush block is properly located.
add shims between the thrust
and
angle of the brush block in relation to the slip rings. If this angle is not approximately 2", as indicated in DEICER BRUSH REPLACEMENT, Chapter 30-60-00, loosen the mounting screws and reposition the brush block until the proper angle exists between the brush block and slip rings. The spacing established in Figure 3, Chapter 30-60-00 must also be maintained after the proper contact angle is established.
j.
Estimate the contact
CAUTION 1 [CAVTION While
following
the instructions of
tween the brushes and
k.
step k,
move
the
propeller back
and forth to
prevent arcing be-
slip ring.
With the deicer system operating and a man in the cockpit observing the ammeter, visually inspect and physifrom the brush blocks to each component of the deicer system and to the aircraft power supply.
cally flex the wiring
Movement of the ammeter needle indicate loose
wiring
in the
or
area
harness until the
Jun
28/0Page
2
(other than
the
cycling that occurs
when the timer switches at 90-second
intervals)
under examination at the moment. In such instances, continue to flex the that first indicated trouble while checking the continuity through the individual wires of the affected in the
broken
wiring
source
of trouble is located. Use the
5-20-00
area
wiring diagram
to trace the
circuitry
of the deicer
system.
Ray)heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
TURBOCHARGER
(EA-1
AND
AFTER)
25 HOURS a.
Visually inspect
oil leaks, exhaust system leaks and
general
condition.
oil leaks, exhaust system leaks and
general
condition.
50 HOURS a.
Visually inspect
100 HOURS
Inspect turbocharger system per a.
following method:
assembly. Inspect the compressor wheel for nicks, cracks or broken blades. Turn excess bearing drag or wheel rubbing against housing. Reinstall air inlet duct.
Remove compressor inlet duct
wheel b.
the
by hand and feel
for
Check the oil inlet and outlet ports in center
housing
for leaks, and the turbine heat blanket for condition and
security. Check for any interference with tion and security. c.
d.
Inspect
all exhaust system
linkage
between the
components for
worn or
bypass
valve
damaged
(wastegate)
areas, loose
clamps, cracks and
Inspect lubrication system components for worn or damaged areas, loose clamps and should be given to the ducts downstream (pressure side) of the compressor. e.
f.
Inspect
the fuel
injection
general
and actuator, its
leaks.
condi-
leaks.
Special
attention
nozzle pressure reference manifold, for deteriorated hose, loose connections, leaks
or
obstructions
g.
All fluid power lines should be checked for leaks and
security.
The compressor discharge reference line from the throttle air valve to the controller should be spected for oil leakage from the controller. Any leakage is cause for replacement of the controller. h.
opened
and in-
E33C, F33C SPIN INSPECTION (ACROBATIC CATEGORY) inspection is required on all E33C and F33C (CJ-1 and after) airplanes which are being acrobatically spun is (even if the spin time is only a small part of total time). This inspection is NOT required if an airplane performing acrobatic maneuvers other than spins (no spins at all). The regular 109-Hour Inspection (P/N 98-322276 or subseGuide (P/N quent), Intermediate 1 GO-Hour inspection (P/N 98-38999 or subsequent) or Continuing Care Inspection
This
98-36711D
n?s
or
subsequent)
MUST also be
complied
with.
5-20-00
JunPa2~egi:Page
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
E33C, F33C SPIN INSPECTION (ACROBATIC CATEGORY) FREQUENCY 1. 50 Hours
PART Rudder
INSPECTION
pedal
CORRECTIVE ACTION
Check for cracks.
If cracks
MECH
bellcrank
Technical
found, contact the Support Department of
support
Raytheon
Aircraft
INSP
are
Company.
assembly 2. 50 Hours
Elevator to
Check
Elevator
(4
torque fitting casting joint
proper hole diameter.
per
screw
holes
elevator)
If hole diameter is
for
inch,
ream
more
hole to 0.208
than 0.194 rt
0.002 inch
diameter and install NAS 2903-4
or
NAS 6203-4)( oversize bolt. If hole
diameter exceeds 0.210 inch for oversize bolts, contact the Technical
Support Department of Raytheon Company. Torque bolt or
Aircraft screw
to 30 to 40 inch-tbs.
Check hole size in
If hole diameter is greater than 0.251
elevator inboard
inch, replace elevator torque fitting.
hinge
mount hole in center of
elevator torque
fitting.
Check elevator rod end
mounting
3. 50 Hours
hole in the
If hole diameter is
inch,
ream
greater than 0.379
to 0.436
~t
elevator torque fitting for
install
proper diameter.
bushing.
Horizontaland
Horizontal stabilizer
If bolt holes
are more
vertical
in diameter
or
stabilizer
forward spar: Check diameter of 4 outboard
attachment
bolt holes
bolt holes
(2 upper and
on
each side 2
lower).
(stabilizer spars and
bulkheads)
one
bushings
0.001 inch and
BS 105740-X-XC-0500
than 0.253 inch
elongated,
to 0.270
ream
the
0.002 inch
diameter and install NAS 2904-14 oversize bolts. If hole diameter exceeds 0.272 inch for oversize
Horizontal stabilizer rear spar: Check diameter of 2 outboard bolt holes on
each side 1
(1
upper and
I bolts, contact the Technical Support Department of Raytheon Aircraft Company. Torque the nuts to 85 to 100 inch-lbs.
lower).
If any of these holes
are
oversize, check all other horizontal stabilizer holes and vertical stabilizer bolt holes for correct diameter.
Page
nu28102 J4
5-20-00
A23
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
E33C, F33C SPIN INSPECTION (ACROBATIC CATEGORY) (CONTINUED) FREQUENCY
CORRECTIVE ACTION
INSPECTION
PART
Check torque
4. 50 Hours
on
all
nuts.
Inboard
Check for
elevatorhinge
and
straightness
Torque the pounds.
MECH
INSP
nuts to 85 to 100 inch
Replace
if bent
or worn.
Replace
if bent
or worn
wear.
bolts Elevator
push- I
rods to
Check for and
straightness
smaller than
0.370 inch diameter.
wear.
elevator
torque fitting bolt 5. 50 Hours
Upper
and
Inspect
tor
cracks,
middle rudder
corrosion andexcessive
hinges
wear.
cracks,
Lower rudder
Inspect
hinge
corrosion andexcessive
tor
Replace
if any of noted conditions
exist.
Replace
if any of noted conditions
exist.
wear.
6. 50 Hours
Elevatorhinge joint
Checkbearing for looseness and bearing bracket for cracks,
Replace
if noted conditions exist.
corrosion and excessive wear.
Check
If I.D. is
bushing
over
under 0.310
diameters.
Replace Check elevator
hinge
brackets hole diameter.
Check elevator
hinge
0.191 inch
or
O.D. is
inch, replace bushings.
if noted conditions exist.
If greater than 0.200 inch, replace
bracket.
Replace
if noted conditions exist.
Replace
if
bracket for cracks, corrosion and excessive wear.
Check bolts for
wear.
plating
is
worn or
corroded.
Check reassembled
joint 7. 50 Hours
straightness,
Elevator
Check for
pushrods
and cracks.
Check rod end
new
parts
as
bearing play.
Replace pushrod Replace
required.
excessive free
Check rod end
If
hole diameter.
more
I replace
if bent
or
cracked.
bearing if play is noted.
rod end
for excessive free
mounting
A23
Install
for looseness.
than 0.378 inch in diameter,
rod end.
5-20-00
Jun
28/02Page
5
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
E33C, F33C SPIN INSPECTION (ACROBATIC CATEGORY) (CONTINUED) FREQUENCY
PART
INSPECTION
CORRECTIVE ACTION
8. 50 Hours
Trim Tab
Check for cracks.
Replace if noted conditions
Check free indicated in
play as Chapter
Replace
tab
bushing
10. 50 Hours
Elevator
Trim tab
and/or trim tab
pushrod ends and/or trim excessive free
Check for cracks,
If cracks
especially between outboard hinge and
Technical
elevator balance horn.
repair.
Check
Replace
straightness.
are
play
INSP
exist.
tab
actuator shaft and/or trim tab
27-30-00.
9. 50 Hours
MECH
hinge
if
is noted.
found, contact the
Support Department of Raytheon Aircraft Company for if bent.
pushrod assemblies 11. 50 Hours
Trim tab
Check output shaft for
actuator
straightness.
Replace
if bent.
Check attach bolts for proper torque.
Check actuator installation for
looseness. 12. 50 Hours
Elevator
bellcrank
Check pushrod mounting hole for proper diameter.
If more than 0.379 inch, press out and press in one
existing bushing
BS105740X-XC0968 drill 0.377
hole 13. 50 Hours
14. 50 Hours
(elevator pushrod to bellcrank)
Check for
Inboard
Checkforcracks. Check
elevatorhinge casting
hinge bearingsfor
Bolt
and
straightness
rt
bushing
and
0.002-inch diameter
through bushing.
Replace
if bent
or worn
smaller than
0.370 inch.
wear.
Replace
if noted condition exists.
looseness.
100-HOUR ORANNUAL INSPECTION GUIDE operator is responsible for maintaining the airplane in an airworthy condition, including compliance applicable Airworthiness Directives as specified in Part 39 of Title 14 Code of Federal Regulations (14 CFR). It is further the responsibiiity of the owner or operator to ensure that the airplane is inspected in conformity with the I requirements covered in 14 CFR Parts 43 and S1.These 14 CFR Parts cover the requirements concerning the Inspection Guide. This Inspection Guide is not intended to be all inclusive, for no such guide can replace the good judgement of a certified airframe and power plant mechanic in the performance of his duties. As the one primarily responsible for the airworthiness of the airplane, the owner or operator should select only qualified personnel to maintain the airplane. The
owner or
with all
I
FACTS PROGRAIVI ~ODELS A36 AND
B36TC)
Airplanes delivered from the factory after August 1, 2001 will use the Factory Aircraft Comprehensive Tracking System (FACTS) which becomes the factory computerized maintenance tracking and forecasting system for the Model A36/B36TC series airplanes. The FACTS program for the Model A36/B36TC adheres to the guidelines es-
Jun 28/0 Page
:6
5-20-00
A23
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL tablished in this
chapter of the
maintenance manual. The Raytheon Aircraft approved inspection program contained Raytheon factory computerized maintenance inspection program (FACTS), is specifically for the Model A36/B36TC series airplanes. Any variation to the inspection program must be approved in writing by the FAA Flight Standards District Office (FSDO), or Airworthiness Authority. The FACTS program meets the requirement of both 14 CFR 91 and 14 CFR 135. in this
and within the
chapter,
SPECIAL CONDITIONS CAUTIONARY NOTICE The time
periods for the inspections noted in this schedule are based on normal usage under average environmental 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. conditions.
NOTE The
required periods do not constitute a guarantee that the item will reach the period function, as the aforementioned factors cannot be controlled by the manufacturer.
without mal-
This inspection program, in accordance with 14 CFR Parts 43 and 91, consists of, but is not limited to, inspection items listed in this Inspection Guide, any applicable Airworthiness Directives issued
against Sheet
the airframe
as
or
any
equipment
installed therein and
conformity
to
Type Certificate Data
applicable.
Material contained in this
guide, including
the
inspection intervals, may
be
changed
at any time
by
the
owner/oper-
ator, with prior notification and approval of the local FAA General Aviation District Office, when warranted by service
experience or engineering recommendations. Information planes covered in this maintenance manual except where
contained herein is differences
are
applicable to all Bonanza by serial effectivity.
series air-
indicated
Inspection Guide may be used as an outline, detailed information of the many systems and components airplane will be found in the various sections of this maintenance manual and the pertinent supplier publications. It is also recommended that reference be made to the applicable maintenance handbooks, service instructions, Beech and Raytheon Aircraft service bulletins, applicable FAA regulations and publications, and supplier bulletins and specifications for torque values, clearances, settings, tolerances, and other requirements. In the final analysis, it is the responsibility of the owner/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. While the in the
NOTE
Any time are
an
airplane
not covered with
that have been
repainted or touched up, inspect all placards and decals to assure that they paint, are easily readable, and are securely attached. Replace any placards
is
inadvertently
defaced
or
removed.
In addition to the inspections prescribed by this schedule, the altimeter system and all ATC transponders MUST be tested and inspected at 24-month intervals in compliance with the requirements specified in 14 CFR Parts 91.411, and 91.70.
1
airplane must be accomplished within each 12-month period for compliance with the Regulations. The time periods for inspections stated in this inspection guide should NEVER be exceeded by more than 10 hours, and then only if the additional time is required to reach a place where the inspection can be satisfactorily accomplished. However, the additional time used must be deducted from the next inspection time. If 10 hours were used to reach the inspection facility, the next inspection would be due in 90 hours for the next 100-hour inspection with no extension allowed. A
complete inspection
of the
Title 14 Code of Federal
nu
5-20-00
JunPa2ggl~):Page
7
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
airplane must receive a complete (100-hour, annual, or complete continuing care inspection) inspection every 12 months regardless of the hours flown. The inspections completed during a 12-month period can be deleted from the items to be inspected. Rubber goods such as fuel lines are recommended to be changed at five year periods An
regardless
of
airplane time. NOTE
Additional
publications
For information
on
listed in the current Publications Price List CD ROM
are
these
1-800-796-2665, fax
publications (316) 676-4824,
(P/N 994-32808). (TMDC) at our web site at http:/l ray-
contact the Technical Manual Distribution Center
E-mail TMDC 8 rac.ray.con
or
visit
theonaircraft.com.
NOTE All electrical systems operational inspections are to be made using pable of delivering and maintaining 28.25 volts 0.25 volts DC.
I
Raytheon
Aircraft
Company issues
service information for the benefit of
classes of Service Bulletins. MANDATORY
(Red Border)
an
external power
source ca-
and operators in the form of two changes, inspections or modifica-
owners
Service Bulletins
are
factory considers compliance with these Service Bulletins mandatory. OPTIONAL Service Bulletins cover changes, modifications, improvements or inspections which may benefit the (No Border) of information covered by the OPTIONAL Service Bulletin, each owner or operator is the wide range owner. Due to responsible for conducting a thorough review of each OPTIONAL Service Bulletin to determine if compliance is required based on the applicability of the OPTIONAL Service Bulletin to his particular set of operating conditions. It is the responsibility of the owner or operator to ensure that all Beech and Raytheon Aircraft Service Bulletins which are pertinent to his particular operation are complied with. tions that could affect
safety.
The
NOTE Model E33C and F33C airplanes 50 hours.
being
spun MUST also have the AEROBATIC INSPECTION at
WARNING I I W~RNINO
During
I
the
Ensure the
Jun
28/0Page
8
performance landing gear
of this
inspection
the
airplane will be placed on three-point jacks. removing the airplane from the jacks.
is down and locked before
5-20-00
nns
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
100-HOUR OR ANNUAL INSPECTION A.
OPERATIONAL INSPECTION 1.
STARTER
energized
MECH
INSP
Check for proper operation, unusual noise and dragging. Check starter light (if installed) and/or load meter to ensure starter disengagement when
starter switch is released.
2.
3.
Check for proper fuel pressure limits and fluctuations.
FUEL FLOW
CYLINDER HEAD TEMPERATURE
I
I
I I
Check for proper operation, temperature and
fluctuations. Check for proper output and unusual noises.
4.
ALTERNATOR
5.
STANDBY ALTEWVATOR/ GENERATOR Perform
a
functional test
as
outlined in
Check for proper operation in test mode. 24-31-00 of P/N 36-590001-9A (or
Chapter
the Bonanza Series Maintenance Manual. Check
subsequent),
wiring
security
for
and
condition 6.
INSTRUMENT AIR SYSTEM
Check for proper
7.
STANDBY INSTRUMENT AIR
(If installed)
and
plumbing
wiring
for
operation
and output pressure.
Check far proper
and condition. Refer to AFM
security
operation. Check Supplement 36-590006-
23. 3.
PROPELLER OPERATION smoothness of
9.
Cycle propeller and
check for proper rpm
drop and
operation.
PROPELLER DEICER
Check for proper
operation
and amperage drawn
on
ammeter.
Check for proper pressure, temperature limits
10. OIL PRESSURE AND TEMPERATURE and unusual fluctuations. 11. MAGNETOS
Check the performance of the
NORMAL PROCEDURES in the 12. POWER CHECK
Operating
appropriate
Pilot’s
as
outlined under the
Operating
Refer to NORMAL PROCEDURES in the
heading
Handbook.
appropriate
Pilot’s
Handbook.
13. AMMETER
Check for proper indication and unusual fluctuations.
14. HEATING AND VENTILATING SYSTEM
15. FIREWALL SHUTOFF VALVE
Check for proper
16. IDLE RPM AND MIXTURE SETTINGS
Check controls for freedom of
17. IDLE CUT-OFF
Check for proper
18. IGNITION SWITCH
Rotate the
Check for proper operation, heat and airflow
of movement.
output. Check controls for freedom
settings.
magneto
operation
and freedom of movement.
Check for both proper rpm and mixture
operation.
operation
and freedom of movement.
ignition switch through
the OFF
position
to the extreme
limit of switch travel; if the engine stops firing, the switch is normal. If the engine continues to run with the switch held against the OFF stop, it is an indication that magneto is still "hot" or ungrounded. When the switch is released, it should
automatically
return to OFF and the
engine should stop running. However, replaced.
any
one
ignition
switch exhibiting this abnormal condition should be
ana
5-20-00
9
Ra~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
100-HOUR OR ANNUAL INSPECTION A. OPERATIONAL INSPECTION
(CONTINUED) MECH
(Continued)
INSP
With the engine running, check for proper operational limits, engine response and rigging. Check friction locks for proper operation.
19. ALL ENGINE CONTROLS
Check for proper operation and unusual fiuctuations.
20. FUEL QUANTITY GAGES 21. AUXILIARY FUEL PUMP
Check pump for proper
operation,
unusual noise and
fluctuations. 22. FUEL TANK SELECTOR
Check for proper placarding, proper
operation and
feel for
detent.
positive
Check for condition, attachment, cracked
23. ALL LIGHTS
switches, knobs and circuit breakers for looseness and 24. STALL WARNING SYSTEM
Check for proper
Check for proper
25. RADIO OPERATION
or
broken lenses. Check
operation.
operation
and
heating
of the unit.
operation, security of switches and
knobs.
Check for noisy operation, full travel and proper indication.
26. FLAPS
27. PITOT HEAT
Check for amperage drawn
on
ammeter and for proper
heating of
the
unit. 28. FLIGHT INSTRUMENTS
Check for condition and proper
operation.
Check for condition and wear, ease of operation and proper release of the brake. Check for unusual brake chatter.
29. BRAKES
parking
30. EMERGENCY LOCATOR TRANSMITTER Check for proper operation. Tune radio to 121.5 MHz on VHF or 243 MHz on UHF, then turn ELT switch to ON and monitor for
I
one
signal.
Turn ELT switch OFF, then place in ARM airplane is returned to service.
position.
Ensure that the ELT is
armed when the
31. AIR-CONDITIONER
condenser retracted
moves to
position
Operate the air conditioner and verify that the retractable ground extended position when turned on and returns to
the
when turned off. Check for proper
32. OXYGEN SYSTEM
operation
the
and unusual noise.
Functionally check the oxygen system for proper operation. Check operation.
the oxygen bottle shutoff valve for proper 33. SWITCHES, CIRCUIT BREAKERS
Check for proper operation.
CONTROLS, TRIM CONTROLS AND TRIM INDICATOR Check freedom movement and proper operation through full travel with and without flaps extended. Check electric trim controls for operation.
34. FLIGHT
B.
of
POWERPLANT 1.
NACELLE SKiN loose
2.
or
Page
cracks. Check for
COWL FLAPS
Open
the upper
for cracks.
Check for travel, deformation and
5-20-00
or
damage.
Check for condition, security and adjustment of latches.
cowling and clean. Inspect 4.
or
Check for cracks and deformation. Check for loose
rivets and concealed
COWLING
damage
rivets.
NACELLE STRUCTURE
missing 3.
missing
Check for deformation and obvious
security. Inspect for cracks.
Pi23
Ray~hean Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 1OO-HOUR OR ANNUAL INSPECTION B. POWER PLANT
5.
(CONTINUED)
(Continued)
MECH
INSP
Clean, inspect, regap, test and replace as necessary. Tighten spark torque and check ignition harness condition and for proper attachment.
SPARK PLUGS
plugs
to proper
6.
COMPRESSION
7.
BATTERY
Perform differential
compression
test.
tight connections and add distilled water to maintain a top of separators. Inspect the vents and overflow tube for obstructions. Check for security and proper attachment. Check for corrosion. Make certain the battery is clean. Water or dirt on battery surface can cause the battery to discharge. Inspect
for clean,
level of 3/8-inch above
8.
Inspect plumbing and associated accessories for condition (such as fraying) and attachment. Check plumbing clearance and secure against
PLUMBING cracks and
possible chafing. 9.
Check reservoir for
BRAKE FLUID RESERVOIR
security,
open vent, proper fluid level
and for leaks. 10. ENGINE OIL TANK OR SUMP and
Check for cracks, leaks, proper fluid level, deformation
security.
11. CRANKCASE
security
Check security of crankcase-thru bolts. inspect the
and that the tabs
are
dipstick tabs
for
not bent.
12. OIL SUMP DRAINS AND SCREENS
and for obstructions. Check for metal
Clean screens, check for holes in the screens particles or foreign matter on screens and filters.
Check for proper torque after installation. 13. OIL COOLER
Check oil cooler, lines and fittings for condition,
security, chafing
and
leaks. Check for condition and security. Check the lightning strikes. If there is evidence of lightning strikes, consult the propeller manufacturer, the engine manufacturer and Raytheon Aircraft Company. Inspect the blades for cracks, dents, nicks, scratches, erosion, corrosion, security and movement in the hub.
14. PROPELLER AND MOUNTING BOLTS
tip
of the blades for evidence of
15. PROPELLER SPINNER 16. PROPELLER HUB 17. ALTERNATOR
attachment and 18. ALTERNATOR
Check for deformation, security and cracks.
Check for cracks,
excessively leaking seals
Check for condition and attachment. Check
possible
and condition.
wiring
for proper
chafing. Check for unusual noise.
(Prestolite
or
Delco
Remy only) Remove and disassemble
the
necessary to inspect the rotor shaft bearings for condition and replace if necessary. Refer to Beech Service Instructions No. 0546-359 Rev II or subsequent.
alternator
as
19. STARTER
Check for condition, attachment and chafed
20. STANDBY GENERATOR/ALTERNATOR wires and for
n23
or
loose wires.
Check for condition, attachment, security of
chafing.
5-20-00
11
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION B. POWER PLANT
MECH
(Continued)
21. MAGNETOS
excessively
(CONTINUED) INSP
Check contact points for proper clearance. Points with deep pits or areas must be discarded. Inspect the cam follower felt pad for
burned
proper lubrication and clean the compartment with harness for proper connection,
security
and
22. MAGNETO PRESSURIZATION FILTER
a
fraying.
clean, dry cloth. Check ignition Check
timing.
Check for condition, cleanliness and
security.
Check cylinders and exhaust manifold for obvious leaks, security and cracks, check baffles for cracks and security. Check cylinders for broken cooling fins and loose or missing base nuts.
23. CYLINDERS AND BAFFLES
Check for deformation, security, cracks, leaks, loose or missing occur due to normal internal
24. EXHAUST SYSTEM
clamps. Check for thin wall condition which may erosion on stacks which have long service time. nuts and
25. FIREWALL access
Check for wrinkles, damage
holes for proper
or
cracks. Check all electrical and control
sealing.
Check all fuel, oil and air hose or duct for damage. Check fittings for security.
26. HOSE AND DUCTS
deterioration and
Check for condition,
27. ENGINE ACCESSORIES
and tubes for
chafing, security
28. ENGINE MOUNTS
security and leaks. Check wiring,
Check for cracks, corrosion and security. grounding straps for condition and
21-40-00.
Check for leaks and corrosion and control
30. PROPELLER GOVERNOR
31. ENGINE CONTROLS
attachment, alignment
Inspect rubber cushions, security.
Check for cracks, distortion, corrosion, leaks and
29. CABIN HEATER SYSTEM
Chapter
hoses
and leaks.
mount bolts and nuts, and
obstructions per
leakage, cracks,
Check controls and associated and
rigging.
equipment
arm
for
security.
for condition,
Remove cable connection bolts and check for wear
each 300 hours. 32. IGNITION HARNESS
Inspect
for
fraying and
attachment.
33. ELECTRICAL WIRING AND EQUIPMENT Inspect electrical equipment and accessories for fraying and attachment. Check for condition,
34. ALL DRAINS AND PLUGS leaks and correct
security
wiring
and associated
and obstructions. Check for
tightness.
35. PRESSURE PUMP INTAKE FILTER
Inspect
filter for
condition, cleanliness and
security. Check filter container for leaks. Replace filter every 300 hours
or more
often
as
necessary. 36. AIR-CONDITIONER COMPRESSOR
refrigerant level and for oil leaks. and worn or frayed condition.
security and attachment. Check Chapters 12 and 21. Check belt for tension
Check for
Refer to
Check for condition, cleanliness and security.
37. INDUCTION AIR FILTER
38. INDUCTION SYSTEM AND ALTERNATE AIR
delamination of the inner
cracks, operation and
dun
28/0Page
12
lining.
Check hot and cold flexible air ducts for
Check the alternate air valve for
blockage, security,
wear.
5-20-00
~23
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
100-HOUR OR ANNUAL INSPECTION B. POWER PLANT
MECH
(Continued)
39. FUEL INJECTION CONTROL VALVE screen
(CONTINUED)
Clean the
screen
and check for
damage.
Install
and check for leaks.
Inspect all fuel injection components, lines and fittings for fuel leaks, fraying and cracking.
40. FUEL INJECTION SYSTEM
evidence of 41
FUEL RETURN LINE
(EA-I
drain line, particularly in the fitting of the fuel return line.
thru
EA-439) Check for chafing against the wastegate seal approximately six inches from the fire wall bulkhead
area
42. ELECTRIC PROPELLER DEICER a.
Check for service
damage
Check for attachment and
to the deicer
heaters, brush rods, springs and brushes.
security.
b.
Check the lead strap and all other clamps, connectors and wiring for electrical soundness, security and attachment.
c.
Check the
deposits d.
slip rings
for
of oil, grease
roughness, cracks, burned or discolored areas and for dirt. Check for security and attachment of all components.
or
Check deicer boots for wrinkles, loose
or
torn
areas.
43. TURBOCHARGER SYSTEM a.
Inspect the system
b.
Inspect the
for oil leaks, exhaust system
compressor wheel for nicks, cracks
leaks, cracks and attachment.
or
broken blades and freedom of
movement. c.
Inspect the bypass valve (wastegate) for proper operation and inspect all linkage for interference, condition, security and attachment.
d.
Inspect all
exhaust system components for
worn or
damaged
areas, loose
clamps,
worn or
damaged
areas, loose
clamps,
cracks and leaks. e.
Inspect
lubrication system components for
cracks and leaks.
injection
reference
f.
Inspect the upper deck pressure reference lines and the fuel manifold for loose connections, leaks and possible chafing.
g.
Check and calibrate the turbine inlet temperature indicator in accordance with Chapter 77-00-00.
h.
Check manifold pressure controller
44. ENGINE BAFFLE SEALS
annual
inspection. Replace
linkage
for
wear.
Inspect for security and condition as
necessary
or
at each 100-hour
or
every 10 years of service.
Inspect pressure system in-line filter for condition, cleanliness and security. Replace pressure system in-line filter in accordance with the Overhaul and Replacement Schedule in Chapter 5-10-00.
45. FILTERS
C.
CABIN AND BAGGAGE COMPARTMENT 1.
ana
SKIN Inspect skins for deformation, cracks and loose found, check adjacent structure.
or
missing
rivets. If
damage
is
5-20-00
INSP
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL IOO-HOUR OR ANNUAL INSPECTION C. CABIN AND BAGGAGE COMPARTMENT 2.
STRUCTURE concealed
3.
(CONTINUED)
I
(Continued)
Check for cracks and def ormation. Check for loose
or
missing
MECH
INSP
rivets and
damage.
CABLES, PULLEYS AND TURNBUCKLES Check the flight control components, pulleys. Replace control system components (pushrods, turnbuckles, end fittings, castings, etc.) that have bulges, splits, bends, or cracks. Check control cables, pulleys, and associated equipment for condition, attachment, alignment, clearance and
cables and
proper
operation. Replace
length
of cable
important
pulleys
cables that have
than 3 broken strands in any 9-foot
more
evidence of corrosion. Check cables for proper tension. NOTE It is to operate controls through their full range so that the cables move away from
and all
or
portions
of the cables
are
exposed
for
inspection.
LANDING GEAR GEARBOX AND ACTUATING LINKAGE
4.
Check for
condition and attachment. Check for unusual noise. Remove oil filler
leakage, wear, plug and check oil
by engaging and turning the emergency hand crank 1/2 turn to determine that oil being picked up on the worm gear. The oil level should be maintained no more than necessary to cover 112 of the diameter of the worm gear. Install oil filler plug. level
is
I 5.
6.
security
and check
signs
of
chafing
security and wear at jam nuts for tightness.
Check for condition,
all
security
points. and leaks.
cracks.
or
BRAKE MASTER CYLINDER AND PARKING BRAKE VALVE
security 8.
housing
for
AUXILIARY FUEL PUMP AND FUEL LINES
Check lines for 7.
Check for condition,
FLAP MOTOR AND SHAFTS
Check drive shaft
and leaks. Check lines for
signs
of
chafing
or
Check for condition,
cracks.
Check for freedom of movement. Check cables, push/pull rods, bellcranks, pulleys, turnbuckles and fair leads for proper routing, condition and security. RUDDER PEDALS
Check rudder
positive
positions for wear. Check locks and pins to ensure important to operate controls through their full range so that away from pulleys and all portions of the cables are exposed for
pedal fore
lock. NOTE
the cables move
and aft
It is
inspection. 9.
CONTROL COLUMN, TRIM CONTROL AND INDICATOR (Electric and Manual) Check for freedom of movement. Inspect pulleys, sprockets, bearings, actuators, chains and turnbuckles for condition,
security
operation. Check trim indicator for proper
and
indication. 10. ENGINE CONTROLS locks for proper
Check for
ease
of
operation through full
travel. Check friction
operation.
11. ELECTRICAL WIRING AND EQUIPMENT
Check for condition,
security
and
signs
of
chafing. 12. PLUMBING
Check all plumbing and connections for security, leakage and
general
condition. 13. WINDOWS AND DOORS
Inspect windows for scratches, crazing and general Inspect doors for security of attachment. Check latching mechanism for proper engagement and ease of operation. Check that rotation of the interior door handle without depressing the handle lock release button does not unlatch the door. condition.
Jun
28/0Page
14
5-20-00
nns
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION C. CABIN AND BAGGAGE COMPARTMENT
(CONTINUED) MECH
(Continued)
INSP
14. INSTRUMENTS AND INSTRUMENT PANEL
Inspect instrument panel, sub panels, placards and instruments for condition and attachment. Check all knobs for security. Inspect shock mounts and ground straps for cracks and security.
15.
SEATS, SEAT BELTS AND SHOULDER HARNESSES Inspect cabin seats,
seat belts
and shoulder harnesses for proper operation, condition and security of attachment. Inspect floorboards for condition and seat attachment. Check for operation of the seat
stops. Check condition of the oxygen system and check the oxygen
16. OXYGEN SYSTEM
masks for cleanliness and stowage. 17. VENTILATING SYSTEM and
Check all fresh air and heat outlet vents for proper movement
operation.
18. FUEL SELECTOR VALVE
Inspect for leakage, security, freedom of movement, proper
detent feel and condition. Clean strainer and check for condition. Check for proper
placarding. Check emergency release handle and latch assembly for Check that the hatch moves out freely. Check the complete latch
19. EMERGENCY EXIT HATCH
operation. assembly for condition proper
and all moving parts for proper operation. With the hatch installed, check for proper latching and seal. Safety the emergency exit with 0.020
inch-diameter copper wire after 20. STATIC SYSTEM
opening.
Check and drain water from the static lines. Check for condition, mounting
21. CABIN AIR BLOWER
security
and
wear
at all
points.
Drain and clean. On fuel cells with foam inserts, check for brown foam material. Refer to Safety Communique No. 67 and Service Bulletin No. 2109.
22. FUEL STRAINER
23. CONTROL COLUMN
D.
(E-1946, E-2104, E-2111 and After; EA-320, EA-389 and After) U-joint roll pins and ensure they are not backing out.
I
control column
Inspect the
MECH
WINGS AND CARRY-THROUGH STRUCTURE
LH 1.
SKIN
Check for deformation and obvious damage. Check for cracks, loose
or
INSP
RH
missing
rivets. If damage is found, check adjacent structure. Check for indications of hard landing or excessive flight loading. 2.
STRUCTURE or
missing
Check for cracks, deformation and concealed damage. Check for loose
rivets. for cracks, proper fit and attachment.
3.
ACCESS DOORS AND PANELS
4.
CABLES, PULLEYS AND TURNBUCKLES Check the flight control components, cables and pulleys. Replace control system components (pushrods, turnbuckles, end fittings, castings, etc.) that have bulges, splits, bends, or cracks. Check control cables, pulleys, and associated equipment for condition, attachment, alignment, clearance and
Inspect
than 3 broken strands in any 3-foot length of cable or evidence of corrosion. Check cables for proper tension. NOTE It is important to operate controls through their full range so that the Gables move away from
proper
operation. Replace
pulleys and
nns
all
portions
cables that have
of the cables
are
more
exposed
for
inspection.
5-20-00
15
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL IOO-HOUR OR ANNUAL INSPECTION D. WINGS AND CARRY-THROUGH STRUCTURE
(CONTINUED) MECH
(Continued)
LH 5.
AILERONS
Check for condition and security. Check for cracks, loose
and freedom of movement. Check
rods for
security
hinge bearings
RH
missing rivets push/pull
and brackets for condition,
and rod ends for corrosion.
6.
FUEL CELLS, CAPS AND VENTS Inspect fuel cells, caps and Chapter 28. Refer to Service Instruction Number 0632-280.
7.
PLUMBING
8.
ELECTRICAL WIRING AND EQUIPMENT
I
or
INSP
Check for
leakage, chafing,
condition and
Inspect
for
vent lines. Refer to
security.
chafing, damage, security
and
attachment. 9.
FLAP LIMIT SWITCHES
Check for condition, security and freedom of operation. Check for condition, security, binding
10. FLAPS AN D ACTUATORS drive shafts. Check
roller
bearings
flap skin and
structure for
and tracks for condition. Check
11. FLAP POSITION TRANSMITTER
cracks, loose
stop
area
or
or
chafing of actuator
missing
are
Check the drain holes in the upper wing attach fittings to open and free of obstruction.
13. WING SPAR CAP
damage.
Check for security and operation.
12. DRAIN HOLES
they
rivets. Check
for condition and
Inspect the wing spar cap
for corrosion. Refer to
ensure
Chapter
that
57. See
Service Bulletin 2538. 14. WING BOLTS
wing bolts for proper torque at the first 1 GO-hour inspection and inspection after each reinstallation of the wing attach bolts. Refer to maintenance manual for wing bolt, nut and fitting inspection criterion
Check
at the first 1 GO-hour
Chapter 57 of this and frequency.
15. RADAR ANTENNA COVER
Check the fiberglass for security, attachment and cracks.
16. FUEL VENTS AND AIR INLETS, PITOT TUBE AND STALL WARNING VANE
Check
for condition and obstruction. 17. Perform the INSPECTION OF FUEL CELL FLAPPER VALVE
Refer
procedure. retpahC ot
I
28-10-00.
E.
MECH
NOSEGEAR WHEEL AND TIRE
1.
Check wheel for cracks and tire for wear, damage and proper
inflation. Check wheel
bearings
LANDING GEAR STRUT
2.
for condition and
Inspect
leakage.
Check for wear at attach
3.
ACTUATING LINKAGE
4.
GEAR DOORS AND LINKAGE
wear.
the shock strut and components for cracks,
attachment, proper inflation and evidence of
points. Check for cracks and security.
Check doors for damage and cracks to the structure and skins. Check linkage for wear and cracks at the attach points. Check for condition and
security.
NOSE GEAR STEERING LINKAGE
5.
security. Inspect linkage
Jun
INSP
28/02PagelG
Inspect linkage
for
tightness,
condition and
boots for condition.
5-20-00
A23
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION
(Continued)
E. NOSE GEAR 6.
(CONTINUED)
SHIMMY DAMPER
MECH
INSP
Check for condition and attachment. Check attach points for Chapter 12-20-00.
cracks. Check fluid level per 7.
in 8.
Check and maintain the proper fluid level in the strut as outlined
STRUT FLUID LEVEL
Chapter
12-20-00.
STRUT AND A-FRAME HINGE BOLTS
Inspect
for corrosion and
security of
attachment. 9.
STATIC CABLE
(If installed)
Inspect for condition, proper
clearances and attachment.
Check for condition.
10. VISUAL INDICATOR
11. NOSE LANDING GEAR DRAG BRACE
(P/N 002-820016-31, P/N 002-820018-3, or Installed) Check that the two drag brace bracket attachment bolts (Item 22, Figure 4, Chapter 32-20-00) are secure. Check drag brace assembly for shear stress, wear and corrosion. At 2,000 hours, remove and inspect the two bracket
with Kit 35-4012-1
attachment bolts.
Replace
all hardware with evidence of shear stress,
wear
and/or
corrosion. 12. NOSE LANDING GEAR RETRACT ROD ROD-ENDS
for F.
signs
of
cracking,
sheer stress,
wear
Check the retract rod rod-ends
I
and corrosion.
I MECH
MAIN GEAR AND BRAKES
LH 1.
BRAKES, LINES, LINING AND DISCS lines for
chafing
and
signs
of
leakage
or
Check for condition,
wear
and
cracks. Check discs for wear
or
I I INSP
RH
security. Check
warping.
Check
brake discs for cracks. 2.
Check wheels for cracks and tires for wear, damage, condition
WHEELS AND TIRES
and proper inflation. Check wheel 3.
bearings
for condition and
ACTUATOR GEARBOX, MOTOR AND SWITCHES
wear.
Check for
leakage, condition
and
security. 4.
LANDING GEAR STRUTS Inspect the shock struts and components for cracks, attachment, corrosion, proper inflation and evidence of leakage.
5.
ACTUATING LINKAGE condition and
6.
Check for
GEAR DOORS AND LINKAGE
linkage
for
STRUT FLUID LEVEL
8.
outlined in
points.
Check for
Chapter
Check doors for damage and cracks to the structure and cracks at the attach points. Check for condition
wear
security. Determine that all pins. and
as
and cracks at attach
security,
and skins. Check
7.
wear
clevis
retaining pins are
in
place and secured with
cotter
Check and maintain the proper hydraulic fluid level in the struts 12-20-00.
STRUT AND A-FRAME HINGE BOLTS
Inspect
for corrosion and
security of
attachment.
A23
5-20-00
17
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION G.
(CONTINUED)
MAIN GEAR OPERATION
MECH LH
INSP
RH
WARNING circumstances should the landing gear be operated electrically while the hand engaged. In the event of such an operation, a tear down and magnetic inspection should be performed to determine damage to the engagement slot in the worm shaft. Under
no
crank is
CAUTION
battery voltage is not sufficient to properly cycle the landing gear for this inspection, only an external power source capable of delivering and maintaining 28.25 0.25 VDC to the airplane’s electrical system throughout the extension and retraction cycles when performing the landing gear retraction inspection. Refer to Chapter 32 for more specific information on the following items. Since the use
fit and fair. Check for unusual noise.
1.
DOORS
2.
POSITION LIGHTS Check for security, adjustment and wiring for breaks, condition of insulation, loose connections and proper indication.
3.
WARNING HORN
4.
UPLOCK CABLE TENSION
Check
security. Check 5.
operation,
Check for proper operation.
uplock cable
Check
uplock
cable mechanism for condition and
for proper tension and for
EMERGENCY EXTENSION
possible fraying.
Check system for freedom of
operation. Check for engagement of the
unusual noise. With the spar cover installed, check for proper emergency extension handle and proper system operation. 6.
DOWNLOCI( TENSION
Check for proper deflection force
on
the main gear knee
joints. 7.
UPLOCK ROLLERS indicated in
Chapter
Check condition and clearance of 12-20-00. Check for
uplock
rollers and lubricate
as
binding.
8.
LIMIT SWITCH RIGGING Check for security and proper adjustment of the limit switches. Refer to RIGGING THE LANDING GEAR in Chapter 32-30-00 of this maintenance manual for correct landing gear gearbox internal clearance.
9.
SAFETY SWITCH
Check for security, proper
rigging
and
operation.
airplane on jacks and cycle the landing gear while position light switches operate in conjunction with the condition and operation of the complete landing gear the Check position.
10. GENERAL OPERATION
Place the
to ascertain that the
checking landing gear system.
11. DYNAMIC BRAKING ACTION 12.
of
dynamic
brake
relay.
(If Installed) Inspect the retractable step for cable and safety link condition, proper adjustment and operation. Check fixed link condition, proper adjustment and operation. Check fixed steps for security. ASSIST STEP
Page
nuJ81
Verify proper operation
28/02
5-20-00
nzs
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION H.
(CONTINUED) MECH
NOSE GEAR OPERATION
INSP
WARNING Under
circumstances should the landing gear be operated electrically while the hand engaged. In the event of such an operation, a tear down and magnetic inspection be performed to determine damage to the engagement slot in the worm shaft.
no
crank is should
CAUTION
I
I
II
voltage is not sufficient to properly cycle the landing gear for this inspection, 0.25 VDC to external power source capable of delivering and maintaining 28.25 the airplane ’s electrical system throughout the extension and retraction cycles when performing
Since the battery use
only an
Refer to
the landing gear retraction inspection. following items.
for
more
specific information
on
the
fit and fair. Check for unusual noise.
i.
DOORS
2.
NOSE GEAR UP TENSION
Check
Chapter 32
operation,
Check the up tension
on
the nose gear as indicated in
RIGGING THE LANDING GEAR in Chapter 32-30-00. 3.
DOWNLOCK TENSION Check the downlock tension RIGGING THE LANDING GEAR in 32-30-00.
4.
GENERAL OPERATION
on
the nose gear
as
indicated in
Place the airplane on jacks and cycle the landing gear while checking to ascertain that the position light switches operate in conjunction with the landing gear position. Check the condition and operation of the complete landing gear
system.
I.
Inspect for
5.
VISUAL INDICATOR
6.
NOSE GEAR STEERING
proper
adjustment
and operation.
Check for condition and security.
REAR FUSELAGE AND EMPENNAGE i.
Check for deformation, cracks and obvious damage. Check for loose damage is found, check adjacent structure.
SKIN
or
missing
rivets. If 2.
INTERNAL FUSELAGE STRUCTURE loose
or
missing
Check for cracks and deformation. Check for
rivets. Check bulkheads, door
posts, stringers and doublers for
corrosion, cracks and buckles. 3.
STRUCTURE other obvious
4.
Inspect the two damage.
most aft bulkheads for
cracks, distortion, loose rivets
or
CABLES, PULLEYS AND TURNBUCKLES Check the flight control components, pulleys. Replace control system components (pushrods, turnbuckles, end fittings, castings, etc.) that have bulges, splits, bends, or cracks. Check control cables, pulleys, and associated equipment for condition, attachment, alignment, clearance and
cables and
have more than 3 broken strands in any 3foot Check cables for proper tension. NOTE It is of corrosion. evidence length their full range so that the cables move away from controls to through important operate for inspection. of the cables are and all exposed portions pulleys
proper
operation. Replace cables that
of cable
~123
or
5-20-00
Jun
28/02PagelS
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 100-HOUR OR ANNUAL INSPECTION (CONTINUED) I. REAR FUSELAGE AND EMPENNAGE
5.
CONTROL SURFACES or
missing
(Continued)
6.
Check for deformation, cracks and security. Check for loose security of hinges and
hinge casting ton
the aft
bulkhead)
for cracks
mounting bolt holes.
TRIM TABS AND ACTUATORS
Chapter
27-30-00. Check
hinges
Check for security and
Check free play per security and wear. Check
wear.
and trim tab actuators for
trim tabs for cracks and control rods for attachment. Lubricate trim tab
Chapter
hinges per
12-20-00.
7.
STATIC PORTS
8.
PLUMBING
9.
INSP
rivets. Check for freedom of movement. Check for
bond cables. Check the inboard elevator in
MECH
Check for obstruction and clean
Check for
leakage, cracks, chafing,
ELECTRICAL WIRING AND EQUIPMENT
as
necessary.
condition and
security.
Inspect for chafing, damage, security
and
attachment. 10. STATIC LINES 11. ANTENNAS
12.
Check condition of static lines and drain.
Check for condition and
ELEVATOR/RUDDER
security.
(Ruddervators)open and clean.
a.
Check that the drain holes
b.
Check that the ruddervator trim tab and ELEVATOR TRIM IAB
are
hinge pin are correctly INSTALLATION, Chapter 27-21-00.
the trim tab
c.
Check for cracks
d.
Check the stabilizer front and
on
hinge support
rear
mated. Refer to
channel.
spar attach points for cracks and looseness.
(CE-I thru CE-1425; CJ-I thru CJ-179; E-l airp\anes that have not installed Kit No. 33-6001-1 2333 every 500 flight hours or annually.
13. RUDDER FORWARD SPAR EA-1 thru EA-500 and
Service Bulletin No.
thru E-2518; S Refer to
(CE-1426 and After; CJ-180 and After; E-2519 and After; airplanes that have installed Kit No. 33-6001-1 S Open inspection covers adjacent to the upper and center hinges. Inspect ribs, spar, hinges and all rudder components in area of the hinges for attachment security, cracks and general condition using a flashlight and mirror. Install covers.
14. RUDDER FORWARD SPAR
EA-501 and After and
J.
GENERAL
Airplane
2.
Airplane lubricated,
3.
Inspect
4.
5.
Jun
28/0Page
20
all
placards
after
cleaning,
to ensure that
Ensure that all Airworthiness and
I
cleaned and serviced.
1.
previously
in accordance with
they
are
Chapter
easily readable
and
securely attached.
Directives, Beech and Raytheon Aircraft Service Bulletins are reviewed and complied with as required.
issued Service Instructions
complete or annual inspection of the airplane, all noted in this guide should be inspected. For
12-20-00.
a
5-20-00
items
on
the
airplane
that
are
nns
CHAPTER
DIMENSIONS AND AREAS
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 6
LIST OF PAGE EFFECTIVITY CHAPTER SECTION PAGE
SUBJECT 6-EFFECTIVITY/CONTENTS
DATE ........,,,.Oct 7/83
1
6-00-00
1
CHAPTER 6
.........,._
Feb 18/83
2
Oct 10/80
2A
Feb 18/83
3
................Oct 7/83
4
...............Jan 20/82
5
.........,.,..Oct 7/83
6
..............Jan 20/82
7
............,Jan 20/82
8
..............Jan 20/82
DIMENSIONS AND AREAS
TABLE OF CONTENTS CHAPTER SECTION
SUBJECT
SUBJECT ..6-00-00
DIMENSIONS AND AREAS
(CE-748, CE-772 and after; CJ-149 thru CJ-155 Without Kit 33-4002-1) Airplane Dimensions (D-10097, D-10120 and after) Airplane Dimensions (CJ-156 and after, and CJ-149 thru CJ-155 with Kit 33-4002-1) Airplane
PAGE
Dimensions
........1
........2 ......2A
Airplane Dimensions (E-llll, E-1241 and after) Airplane Dimensions (EA-1 thru EA-272 except EA-242) Airplane Dimensions (EA-242, EA-273 and after) Stations Diagram (CE-748, CE-772 and after; CJ-149 and after) Stations Diagram (D-10097, D-10120 and after) Stations Diagram (E-llll, E-1241 and after; EA-1 and after)
i................
.......3 .......4 .......5 .......6
.......7 ............8
"END"
&EFFECTIVrTYICONTENTS
P~g´•l Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
26’8
i3
8’3" i
6’7"
7.5" MINIMUM CLEARANCE 33’6"
I
O
h\
o
’OPTIONAL RADAR
12’2"
7’ DIA
9’7"
1
113´•607.1(
Altplene Dimalmions (CE-748, CE´•772 and after; CJ-149 thru CJ-155 Without Kit 33-4002-1) Figure 1 6´•00-00
Pegei A5
Febi8/83
BEECHCRAFT BONANZA SERIES MAINtENANCE MANUAL
26’5"
T 6’7" c:r
i
I
7’7"
6´•8" MINIMUM CLEARANCE
33’6"
o
I
h\
o
´•OPTIONAL RADAR
10’6"
7’ DIA
9’7"----------1
Airplane
6-0090
Page2 Oct 10/80
Dimensions
(D-10097, P´•10120 Figure 2
v,r.~or.is
and
after)
BEECHCRAFF
BONANtA SERIES MAINTENANCE MANUAL
26’8
i3 8’3"
j
6’!"
7.5" MINIMVM CLEARANCE 33’6"
WING AREA: 181.0 SO.FT.
I
O
h\
lL111
o
12’2"
7’ ~DIA
9’7"
Airplane
Dimensions (CJ-150 and after, and CJ-149 thru CJ-155 With Kit 339002-1)
133-607.29
Figure 2A 6-00-00
Page 2 A A5
Feb18183
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
8’5"
6.6"
CI~
CLEARANCE, 9.5" E-1946, E-2104, E-2111 AND
7.5" MINIMUM
4FTER
~k
33’6"-
t
IQ
t
~Ck
*OPTIONAL RADAR
tAT SERIALS E´•1946, 6-2104, 6-2111 AND ~k AFTER, VORTEX GENERATORS WERE ADDED TO tHE WING LEADING EDGE. AT THE SAME SERIALS A CONTROLLABLE TAB REPLACED THE FIXED fAB ON THE LEFT AILERON.
12’2"
L~-
80" DIA 3 BLADE PROPELLER USED 6-1946,
6-2104, 6-2111 AND AFTER.
7’ DIA
t
t
j-9’7" A38-M)7- 33
Airptane
(8-1111, Figure 3
Dimensions
6-1241 and
atter)
6-00-00
Page3 A6
Oc17/83
YLL~)
ICI~ 1~,
BONANtA SERIES MAINTENANCE MANUAL
29.5
8 FT. 5 IN.
sFT:elN.
--W,L. I0oon
f-
9.5 IN. (MIN. CLEARANCE WITH TIRE AND SHOCK STRUT DEFLATED)
3"56 MIN.
2.5"
33 FT. 6 IN.
VERTICAL STABILIZER
’OPTIONAL RADAR
12 FT. 2 IN.
80 IN. DIA.
9 FT. 7 IN. A36TC-607-20
Airplane Dlmanalona (EA-l’thru Figure 4
EA-212
Except EA-242)
6-00-00
Page
4
Jan 20/82
A4
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
2.5’
L~pt
t t THE FIXED TAB IS REPLACED BY A CONTAOLLABLE TAB ON LEFT AILERON AT SERIALS EA-320, EA-389 AND AFTER
1
VERTICAL STABILIZER
12 FT. 2 IN.
078
~----9 FT. 7 IN.
29.5
Z> 6 FT. 6 IN.
~D ~D
(MIN. CLEARANCE WITH TIRE AND SHOCK STRUT DEFLATED)
10.5 IN.
8 FT. 5 IN.
-;-__1
--W.L. 100.00
r 3"56 MIN.
Airplane Dlmanaiona (EA-242, Figun, 5
EA-273 and
836TC-607-23
a’fter)
6-00-00
Page5 A6
Oct 7/83
BEECHCRA~ BONANZA SERIES MAINTENANCE MANUAL
14.96
’M
41.~72
..75
116.50
1I~qi
104.90
27200
292.00
257.649.00 19.812
174.50
151.00
33.345
ii om w.L111 I
82.53;1.W.L. 88.1
248.30
149~W
18.25 39.50 4.50 12125 29.25
68.00 58.50
83.090100.00
233.50
207.00
i
17.8;1 112138 131.00
256.90
170.00 179.00
291.00
FUSELAGE
152.250
HORIZONTAL STABILIZER
VERTICAL STABILIZER
272.000 257.806
3.500 1.245
15.250 38.403 25.500 35.750 ~CC----I
Y~-- 36.15 36.900
j
46.000
58.250 56.550 72.500
148.815
175.837
191.00
182563
123.1 82 39.375 86.000 113.172 59.000 135´•30 09.305 83.547 23.881 95.483 73.000
136.188
i~i
n WING
Ir 175.294
0.00
80.647 108.281 44.164 122.750
53.d00 I 45.000
131~
J3sow
36.030
Stations
Diagram (CE-748, CE-TIP Figura
and
after; CJ-149 and after)
8
6-00-00
Paga6 Jan 20/82
A4
BEECHCRAFT
BONIVJZASERIES MANmNANCE MANUAL,
82.960 94.75
116.25r
MIo4.so I ID1F~3.812 ~I IX(1B
41.172
14.96
27200
118´•50
I
33.545
257.609 151.M)
292.00
277.00
174.50
11_1
w.L. w.l
as.J-~--Clz(z
I
I
248.30 233.50
Mj.OO 18.25
\491W
39.50 12125 29,25
4.50
i
68.00 58.50
85.090100.00
LI
lir.87 131.00 112.138
256.90
297.00
FUSELAGE
170.00 1’19.00 152.250
CLOFAIRPLANE
:I
0.000
12500 56.250 35.750‘15.250 46.000
MLFRONT SPAR
STABIUZER
M REAR
38.15 3.900
39.315 66.000 135´•30 59.000
1 23.182
113.172
148.175136.1
175.837 191.00
162.563
rjg305 83.54173.0001. n~ rl
23.881
95.463
88
0.00
WING
175.294
80.b47 108.281 94.864 122=750
Stations Diagram
(0-10097, F~gure 7
53.d00 45.000 38.030
.i~´•7
I)-10120 and after)
6-00´•00
Page 7 Jan 20/82 A~
BEECHCRAFT BONAE~A SERIES MAINTENANCE MANUAL
58.00
1M).00
148.15
Ile.M
124.75 23.345 -10.00
174.00
48.50
I3~.!72
8.25
Iq.aol 155.00
20!.00
233.50
1257.606272.00
100.00
0.~00
’9´•25
170.00 39.00 29.50
83:00
58.00
112:138
131.00
12;.55
14j.00
FUSELAGE 495 .245
38.
39.375 83.547 66.00 122.75 103.641 146.875 73.M)S9 ~.091 113.1n (36.188 1gW83
175.281 181W
53:00 47.m
31.75
yu.se~
13.218~/
83.00
1
11~--23.06
VERTICAL STABIUZER
272.00
257.608
r
162563 7
136.168 i
108.261
MODELS F33A. F33C. V35B. A38. A36TC
3.M
I
BO.C17
25.50
45.00 23.at
35.75
WING
36.15 36.90
3’1.75
218.18
198.000
usloml iogsml~
122.7$ 148.875 175.281 136.188 162.563
103.641
83.541 66,00 73.M)
113.172IglpB(
580039.875123;881
56.25
47.00 66.55 .525
83.00
HORUOHTAL STABIUZER
162363 136.188 108.281
80.047
qjDD
MODEL B36TC
23.81
366038
Stations Diagram (E-llll. E-1241 and after; EA-1 and after) FIE(un, g 6QO-00
PegeB
"END"
3en ~0/82 A4
C H A PT E R
LIFTING AND
SHORING
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER I
LITTINC AND SHORING
TABLE OF CONTENTS SUBJECT
CHAPTER
CHAPTER
PACE
SECTION
7-00-00
Lifting and Shoring
Jacking Main
Maintenance Practices
SUBJECT ....7-00-00
1 I 2
Wheel ja;k:Ing
Hoisting "END"
7-CONTENTS Page 1 A13
Mar 30/90
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 7 LIST OF PAGE EFFECTIVITY
CHAPTER SECTION SUBJECT
PAGE
DATE
7-EFFECTIVITY
1
Mar 30/90
7-CONTENTS
1
Mar 30/90
7-00-00
1 2
Mar 30/90 Mar 30/90
"END"
7-EFFECT1V1TY A13
Page 1 Mar 30/90
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
LIFTING AND SHORING PRACTICES
MAINTENANCE
JACKING
WARN ING
The
landing
gear
struts
do
incorporate internal stops. the
aiplane
attempt
to
is
jacks,
on
remove
the
knees, the torque knee pins bolt connecting the torque
not
When do
not
torque or
the
knees the shock
without first aeflating absorber assembly and supporting the gear. The torque knees provide the extension stop for the lower shock absorber When assembly. they are disconnected, the cylinder is free to slide out of the upper
assembly. CAUTION
Jacking only
the
be
landing gear should accomplished within an or building hangar.
enclosed 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, wind
velocity in considered
any direction must be
prior
to
jacking
airplane.
the
35-590006 Main Wheel Jack Figure 2
Adapter
A three point jack (Figure 1) is used to ii ft the airplane off the ground. Each jack pad is identified and located on the underside of the fuselage. One jack pad is located on each of the lower wing-tofuselage attachment fittings along the front spar. The rear jack fitting consists of an eye bolt that is screwed completely into the airplane. WARNING
Be
sure
the
rear
jack point safety
place and safetied to prethe vent airplane from nosing over. As an additional precaution against nosing over, attach, but not suspend, a weight of approximately 200 pounds to the aft tiedown lug. is
in
When one wing is to be removed, a stand should be placed under the opposite wing and the tail to counteract the resulting unbalanced condition of the airplane. MAIN WHEEL JACKING
jack adapter (Figure 2) is optional equipment. Before raising the airplane, be sure the shock strut is properly inflated to the correct If the strut is not inflated to height. the recommended height, it will be impos-
The main wheel
supplied
Model 300 Service Jack
figure 1
as
sible to insert thejack adapter into the wheel axle. A scissor type jack is recommended for Individual wheel jacking.
main
7-00-00 A13
Page 1 Mar 30/90
BEECHCRAFT BONANZA SERIES MA1NTENANCE MANUAL
HOISTING
airplane
The
Install
a.
be
may
the
ting, P/N 35-590067, wing attach bolt. b. the c.
the
u
a
far
hoisting on
sling fiteach upper forward
Attach the hoisting 35-590064-1 shown
~n
hoisting sling fittings. Install the strap assembly aroung blade shanks.
propeller d.
Hoist the
airplane
ETON.ylhto ms
Adjust the strap assembly ai rp lane
the
slightly e.
may
mainte-
follows:
as
P/N
bly, to
hoisted
parts replacement
or
nance
be
nose
to
keep
level down attitude. in
or
a
As added precaution, an installed under the tail
a
stand the
of
airplane. 35-590064-1
Hoisting Sling Assembly Figure 3
If
the
airplane
must
be
hoisted
and
the
P/N 35-590064-1 When lowering the airplane, caution should be exercised to prevent the shock strut from becoming compressed and forcing the
landing
gear door
against the jack adapt-
er.
hoisting sling assembly available, remove the cabin door,
is not the left front window and the front seats. Attach a sling to the front wing spar in the fuselage and a line to the hoist fitting on the engine.
CAUTION
CAUTION
Do not walk on the wing walk with the airplane on the main wheel
A spreader must be used above the cabin to prevent damaging the door molding and window frame.
jack. "END"
1-00-00 Page 2 Mar 30/90
A13
CHAPTER
LEVELING AND VV EIGHING
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 8
LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT
DATE
PAGE
8-EFFECTIVITY/CONTENTS
1
.........,,,May 9/80
8-00-00
1
...............May 9/80
CHAPTER 8
LEVELING AND WEIGHING
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
GENERAL
8-00-00
Maintenance Practices
PAGE
........1
Leveling
.......1
"END"
&EFFECTIVltYICONTENTS
Plg´•l Mly 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
GENERAL
MAINTENANCE PRACTICES
the center of
a
second
Suspending the plumb assist in stabilizing it.
LEVELING
a can
screw
below.
of
oil will
directly light engine
leveling is accomplished by removing the front seat(s) placing a bubble level on the spar carry thru structure. Deflate the tire or strut on the high side of the airplane to
To level the
Lateral
bob to the
and
airplane longitudinally, attach a cord and plumb phillips head screw, located beneath the rear window on the left side of the airplane. Inflate or deflate the nose gear shock strut as necessary to pass the cord through
phillips head bob in
center the bubble.
"END"
8-00QO
Page May
1
9/80
CHAPTER
TOVVING AND
TAXIING
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 9-TOWING AND TAXIING TABLF OF CONT~NTS CHAPTER
SUBJECT
PACE
9-00-00
Towing and Taxiing
1
Maintenance Practices
1
Towing One Person
Towing With Taxiing
i
Towing a
1
TractororTug
i
"END"
0-CONTENTS
Page 1 A16
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 9 LIS T OF FACE EFFECTIVITY CHAPTER SECTION SUBJECT
PAGE
DATE
9-EFFECTIVITY
1
Oct 16/92
9-CONTENTS
1
Oct 16/92
9-00-00
1
Oct 16/92
"END"
0-EFFECTIVITY
Page Ale
1
Oct 16192
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
TOWING AND PRACTICES
CAUTION
MAINTENANCE
TAXIING
After
moving
the tow bar.
TO WING
the
airplane, always remove propeller with
Never turn the
the tow bar attached to the the
WARNING
nose
gear
as
hit the tow bar.
engine is warm, and it is necessary the propeller to attach the tow bar,
If the to
propeller will
move
stand
clear of the
move
the
Make
of rotation.
direction
of rotation
area
propeller against
the
and
normal
certain
the
magneto switch is off. While the engine is warm, residual fuel in the intake ports and injectors may ignite and cause the engine to kick.
CAUTION When
airplane is being towed,
an
a
quali-
fied person must be in the pilot’s seat to operate the brakes in case of an emerWhen the
gency.
is
airplane
being
moved
backward, do not apply the brakes abrupt-
ly.
Hand Tow Bar
airplane slowly, avoiding sudor taxi the airplane strut. Even brief towing or taxi-
Tow the
den
stops.
with
a
flat
ing with damage
a
Figure
Never tow
deflated strut
can cause severe
used
as
a
handhold
tow bar
while
entering
closing
or
the door.
Always
to the care
Never leave the cabin
door open on the ramp damage the door.
as
wind
tractor
the tow
tug, attach the pins on the nose
or
Always observe the turn gear lower torque knee. Turns limits of the nose gear when making turns. geater than these limits can cause extensive damage
not be
open the storm window to relieve internal pressure when the cabin.
airplane with a ~P/N 45-590075) to
To tow the
top of the cabin door should
leaving
I
TOWING WITH A TRACTOR OR TUG
to the strut.
NOTE The
1
lower
gusts may
gear and shimmy damper. Also, exercise removing the tow bar from the nose gear torque knee to prevent damage to the lubrifittings on the torque knee.
nose
when
cation
NOTE ONE PERSON TOWING
attempt to tow the airplane backby the fitting in the tail skid. The tail skid was designed only to protect the tail in the tail-low landing and to provide Do not
ward
CAUTION The Hand Tow Bar used with
a
~Figure 1)
must not be
attachment for the tail tie-down.
tow vehicle.
TAXIING One
person smooth and
can
move
the
airplane easily
on
a
level surface with the tow bar (P/N 36-590015) furnished with the airplane. Attach the tow bar to the tow pins on the nose gear lower torque knee and push or pull gently to move the airplane.
airplane must be taxied with the wing flaps up, engine cowl flaps open. Turning may be accomplished by the use of the nose wheel steering
The
and the
mechanism.
"END"
9-00-00
Page A16
1
Oct 16/92
CHAPTER
PA RKING,
MOORING, STO RAG E, RTN TO SVC.
BEECHCRAFT
BONANZA SiRjES MAINTENANCE MANUAL
CHAPTER 10
LIST OF PAGE EFFECTIVITY CHAPTER SECTION DATE
PAGE
SUBJECT
10-EFFECTIVITY/CONTENTS
1
10-00-00
1
May 9/80 May ...............May ...............May ....May
2 3 4
CHAPTER 10
9/80
9/80 9/80 9/80
PARKING AND MOORING
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
GENERAL
10-00-00
.......1
Maintenance Practices
Parking. Mooring
........1 ........1
Normal Tie-Down
Extended
PAGE
Storage
and
High
........1
Wind
........1
Control Lock
Storage Flyable Storage 7 Temporary Storage Indefinite Storage
to 30
.........2
Days
30 to 90
.........2
Days
.........3
.........4
Preparation for Service
L’END"
1 O-EFFECtlVITYICONTENTS
p´•a´•1 Mly 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
surfaces must then be secured to prevent banging against the stops. The controls should be secured in position with
MAINTENANCE PRACTICES
GENERAL
control locks that
PARKING
mooring, parking by pulling out the parking brake control, then pressing the pilot’s brake pedals until firm. Do not attempt to lock the parking brake by applying force to the parking brake handle; it controls a valve only and cannot apply pressure to the brake master cylinders.
The brakes
for
are set
installed in the control column. When
properly.
Pitot-static tubes should be covered. EXTENDED STORAGE AND HIGH WIND
mooring the Bonanza, the following method is recommended: Place chocks fore and ah of each main wheel. Position a tail stand under the tail skid, adjusting the When
slightly compress the nose gear shock through each wing mooring lug, fastening each end to a ground point, one forward and one ah of the wing. Run a line through the hole in the tail skid and anchor at the sides of the airplane approximately 5 feet from the base of the stand. If a storm is anticipated, two lines may be secured to each main landing gear strut barrel near the
height of
CAUTION
are
be sure to fasten all doors and windows
the stand to
strut. Run a line
Do not set the brakes
are
parking
hot from
temperature when
brake control when the
severe use or
an
during
low
accumulation of moisture
may cause the brakes to freeze. An increase in outside air temperature can build up excessive pressure in the system. In addition, the parking brake should be left OFF and wheel chocks installed if the
airplane is
to be left unattended.
V-brace and also
a
line may be attached around the nose
gear strut near the lower torque knee. It is recommended that the airplane be tied down headed into the wind, with the control lock installed.
MOORING
CONTROL LOCK
designed to provide guidelines which can be mooring and securing Bonanza series airplanes. Mooring procedures for normal tie-down operations as well as mooring for extended storage and high
A control column lock pin is provided for the control column and the aileron control wheel. The lock pin secures both the aileron control wheel and the elevator control. A cover is
This section is
followed when
wind conditions follow:
on the control lock to cover the throttle control, boost pump, and the propeller control. Install the control lock assembly in the following sequence:
provided
NORMAL TIE-DOWN Rotate the control wheel to the right and move the so the hole in the bracket and the column
a.
On Bonanza series airplanes, a tie-down lug is installed.on each wing, and on the ah fuselage. The tie-downs should be nylon or dacron ropes or chains with sufficient strength to
column forward
gusty winds. Manila or high airplane hemp ropes should never be used. The tie-downs should allow very little or no movement when tightened, too much
provided
restrain the
in
or
slack will allow the airplane to jerk against the tie-downs. When securing the tail section of the airplane, the tie-down should have a slight slack so that the nose of the airplane will
align
to
accept the pin.
b.
pin through
and into the control
causes more pressure to be placed on the wing tie-down ropes and anchors. Adequate antislip knots such as bowlines or square knots should be used when securing the
guide
column. Ensure positive retention of the lock pin by placing assembly over the throttle control, boost pump, and propeller control. c.
the the
cover
not be raised off the ground. In a strong headwind, a tail tie-down that is too tight will increase the angle between the wing and the oncoming air. This creates an additional lifting
force, which
the hole
Push the control column lock in the control column
WARNING
Always completely remove the control lock assembly before engine start, taxiing, and flight.
lines.
STORAGE
Securing operations should be planned so the airplane is tied down facing the prevailing wind, if the ground attachment permits.
Once the
airplane
has been
positioned
into the wind,
the wheels should be checked fore and ah. The
flight
control
The storage procedures listed are intended to protect the airplane from deterioration while it is not in use. The primaly objectives of these measures are to prevent corrosion and
10-OMW)
Pagel May 9/80
BEECHCRAFT BONA~UA SERIES MAINTENANCE MANUAL
damage from exposure storage
are
to the elements. Three
f.
types of and
considered:
a.
FLYABLE STORAGE
b.
TEMPORARY STORAGE
c.
INDEFINITE STORAGE.
7 to 30
days.
up to 90
PITOT TUBE
h.
WINDSHIELD AND WINDOWS
days,
PREPARATION FOR SERVICE
line to the nose gear. ENGINE PREPARATiON FOR STORAGE a
Engines in airplanes that are flown only occasionally tend to exhibit cylinder wall corrosion much more than engines that flown
Iftheengine hasatotaltimeofmorethan25 consumption has stabilized, drain break-in oil after a ground warm-up and install oil Teledyne Continental Motors Specification MHS-24C. 2. Preflight the airplane. 1.
the per
30 to 90 DAYS
TEMPORARY STORAGE
frequently. 1.
Check for correct oil level and add oil if
2.
Run
engine
1500 rpm with oil and normal operating range.
at least five minutes at 1200 to
cylinder head temperatures
DURING FLYABLE STORAGE
Each
in the
seven
days
during fiyable storage, the propeller shall be rotated by hand. After rotating the engine six revolutions, stop the propeller 45" to 90" from the position it was in.
WARNING Before rotation of propeller blades, ascertain magnetoswitch is OFF, throttle in CLOSED position and mixture control is in the IDLE CUTOFF position. Always stand in the clear while turning propeller.
1.
airplane flown
Arrangements
should be made to have the
at least 30 minutes each week in order to
keep
the internal parts of the engine lubricated. Ground running of the engine will not provide proper heating of the oil without
possible damage
to other
cylinder/crankshaft
MOORING
b.
ENGINE PREPARATION FOR STORAGE
flyable storage. in
flight)
until oil
temperature
reaches normal range. Drain oil supplyfrom sump while engine is still warm and replace djain plug. 1. Fill the sump to the full mark on the dipstick lubricating oil meeting the requirements of MIL-C6529, Type 11 (3, Chart 1, 91-00-00), which will mix with normal oil and provide protection against conosion. 2. Removethetopsparkplug andatomizespray preservative oil MlL-L-46002, Grade 1 (4, Chart 1,9190-00) at room temperature, through the upper spark plug hole of each cylinder with piston in the down position. Rotate crankshaft as each pair of cylinders is sprayed. Stop crankshaft with no piston at top position, and thoroughly respray each cylinder. Reinstall spark plugs. 3. Apply preservative to engine interior by spraying the above specified oil (approximately two ounces) through the oil filler tube. Seal all engine openings exposed to the atmosphere using suitable plugs, or moisture resistant tape, and attach red streamen at each point. Affix a tag to the propeller in a conspicious place with the following
gage with
notation; DO NOT TURN PROPELLER, ENGINE PRESERVED. Seal the propeller blade spinner cutouts with
tape.
engine compartment components
due to lack of air flow, and will result in condensation of
moisture in the oil
See
a.
Operate engine (Preferably
necessary to bring level to full mark.
c.
Remove all
covers
hours and the oil
are
Close all
and tape, clean the airplane and give it a thorough inspection, particularly wheel wells, flaps, and control
7 to 30 DAYS
manila rope. It is recommended a tail support be used to compress the nose strut and reduce the angle of attack of the b.
cover.
be installed over windshield and windows.
openings.
Attach
Install
windows and window vents. It is recommended that covers
MOORING If the airplane cannot be placed in a a. hanger, install the control lock and tie the airplane down securely at the three points provided. Do not use hemp or
wings.
Static ground airplane securely
g.
i.
FLYABLE STORAGE
GROUNDING
effectively.
supply, increasing
the
possibility
of
rust.
c.
Fill to
FUEL CELLS
capacity
to minimize fuel
vapor and protect cell inner liners. FLIGHT CONTROL SURFACES d.
Lock with
internal and external locks. d.
FUEL CELLS
Fill to
capacity
to minimize fuel
vapor and protect cell inner linen, FLIGHT CONTROL SURFACES e. internal and extemal locks.
1040´•00
Page2 May 9/80
e.
and
Lock with
GROUNDING
Static
ground airplane securely
effectively. f.
PITOT TUBE
g.
WINDSHIELD AND WINDOWS
Install
cover.
Close all
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
windows and window vents. It is recommended
installed
over
h.
BATTERY
standard
cover
be
Remove and store
according
to
covers, tape, and
thorough inspection, particularly wheel wells, flaps, and control openings. With bottom spark plugs removed, hand turn propeller several revolutions to clear excess preservative oil, then reinstall plugs. Preflight the airplane and
flight
a
ENGINE PRESERVED.
NOT TURN PROPELLER
practices. Remove all PREPARATION FOR SERVICE and Clean the airplane give it a tags.
i.
propeller has not been removed, affix a conspicuous place with the following notation: DO if the
10.
tag in
windshield and windows.
The cylinder DURING INDEFINITE STORAGE c. protex plugs shall be inspected weekly. The plugs should be
changed
as soon as
their color indicates unsafe conditions of
storage. If the dehydrator plugs have changed color in half
engine
cylinders, replaced.
of the
or more
should be
all desiccant material
one-
on
the
test.
The cylinder bores should be resprayed with preventive mixture every six months or more frequently it bore inspection indicates corrosion has started. Replace all desiccant and protex plugs. Before spraying, the engine shall be inspected for corrosion as follows: Inspect the interior of at least one cylinder on the engine through a spark plug hole. If cylinder shows start of rust, spray cylinder corrosion preventive oil MIL-C6529, Type 11 (3, Chart 1, 91-00-00) and turn prop over five or six times, then respray. Remove the rocker box cover from the engine and inspect 1.
INDEFINITE STORAGE
corrosion
See FLYABLE STORAGE.
a.
MOORING
b.
ENGINE PREPARATION FOR INDEFINITE
Drain the engine oil and service with
STORAGE
lubricating
oil, MlL-C-6529, Type 11 (3, Chart 1, 91-00-00). 1. Immediately after servicing with the corrosion preventive mixture, fly the airplane for a period of time not to
exceed
a
the valve mechanism.
maximum of 30 minutes,
propeller be removed and the engine removed from the airplane. The propeller shaft should be coated with preservative oil and wrapped with moisture proof material and tape, 2.
It is recommended the
Coat blades with preservative oil
PROPELLER
d.
and wrap with moisture proof material and tape. If propeller has been removed, coat all paris with protective material to
exclude dust, and then tape. FUEL CELLS Drain fuel cells. e.
NOTE
engine is removed from the airplane, mooring stand must be used. If
a
tail
engine
oil
Remove the top spark plug from each’ and spray thoroughly with corrosion preventive
cylinder
mixture MlL-C-6529, Type 11 (3, Chart 1, 91-00-00), at a temperature range of 221" to 250"F. 4. install protex plugs in each of the top spark plug holes, making sure that each plug is blue in color when installed. Protect and support the spark plug leads with AN4060-1 protectors. 5. Place a bag of desiccant in the exhaust pipes and seel openings with moisture resistant tape. 6.
contained
gasoline.
according
to standard
by inserting a protex plug in the breather hose and damping in place. 8. Wrap engine with moisture proof material and tape after desiccant bags have been installed. 9. Attach a red streamer to each place on the engine where bags of desiccant are placed. Either attach red tape or to the with safety wire to prevent wicking of
streamers outside of the sealed area with
inside of sealed
area
moisture into sealed
area,
or
After 24 hours,
practices.
a
remove
Do not
fuel cells until 24 hours after oil has been f.
of
coating
light
cells and store remove or
handle
applied.
FLIGHT CONTROL SURFACES
Lubricate all
hinge pins, bearings, bell cranks, chains, control rods and quadrants and coat lightly with corrosion preventive compound MlL-C-16173 (5, Chart 1, 91-00-00). flight
control surface
1.
Seal cold air inlet to the heater muff with
moisture resistant tape, 7. Seal engine breather
thin
Flush, spray,
the inner liners of all fuel cells which have
2. 3.
rub
1. on
g. and
Lock with internal and external control locks.
GROUNDING
Static
ground airplane securely
effectively.
PITOT TUBE h. Apply a thin coating of grease, MlL-G-10924 (6, Chart 1, 91-000-00), and install cover. Close all WINDSHIELD AND WINDOWS i. windows and window vents and install covers over
windshield and windows. LANDING GEAR i’. the shock struts with k.
TIRES
periodically.
Inflate
Coat the extended portion of
light weight
Install as
oil.
covers.
Check air pressure
necessary.
10´•0090
Page3 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
WING FLAP TRACKS AND ROLLERS
I.
corrosion
preventive compound.
Place
flaps
Coat with
PREPARATION FOR SERVICE
in retracted
position.
a.
standard
according
to
b.
INSTRUMENT PANEL
material and
secure
SEATS
p.
LANDING LIGHTS
c.
protective
according
with tape,
to standard
practices. Tape connections.
store in a
dry temperate AIRFRAME
s.
Remove and
room,
Cover static ports and all openings secure with tape to exclude rain,
foreign
matter.
propeller if it was removed. Rotate preservative oil from the cylinders. Install the spark plugs, battery, and rotate propeller a. by hand through all compressions of the engine to check for liquid lock. Reinstall cowling and start engine in the normal
Page 4 May 9/80
clear excess
manner.
f.
inspection
"END"
1090´•00
Reinstall the
propeller to
with barrier material and sun, and
lubricating oil, Per Teledyne Continental
Motors MHS-24C. d.
Remove and store
LOOSE TOOLS AND EQUIPMENT
r.
cylinder plugs and all paper, tape, and used to presen/e engine. Drain corrosion preventive mixture and reservice
with recommended
covers.
Cover with barrier material
STALL WARNING UNIT
q.
Remove all
dehydrating agent
with tape,
Install
o.
secure
Cover with barrier
Remove all covers, tape, and tags from the
airplane.
practices.
n.
and
Remove and store
BATTERY
m.
Give the airplane a thorough and test fly the airplane.
cleaning,
visual
C H A PT E R
PLACARDS AND MAR KI NGS
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER ~1-PLACARDS TABLE OF CONTENTS CHAPTER
SUBJECT
PAGE
11-00-00
Required FAA
Placards
Description and Operation
1
Required Placards and Markings Designation Placard
1
Model
1 11-20-00
Exterior Placards and
Markings
Description and Operation
1
"END"
11-CONTENTS
Page A16
1
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 11 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT
PAGE
DATE
11-EFFECTIVITY
1
Oct 16/92
11-CONTENTS
1
Oct 16/92
11-00-00
1
Oct 16/92
11-20-00
1
May
2
Oct 16/92
3
Oct 16/92
4
Oct 16/92
9/80
5
Oct 16/92
6
Oct 16/92
"END"
11-EFFECTIVIM
Page A16
1
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
DESCRIPTION AND
REQUIRED PLACARDS OPERATION
MOD~L D~SIGNA TION PLACARD
designation placard identifies the airplan by its model number and serial number. Should a question arise concerning the care of this airplane, i is important to include the airplane serial number in any correspondence to Beech Aircraft Corporation. Refer to Chapter 11-20-00 for illustration of the plac ard. On airplanes 0-10097, D-10120 and after; EA-1 The model
FAA REQUIRED MARKINGS
PLACARDS
AND
markings are listed Operating Handbook and FAA Approved Airplane Flight Manual. Refer to Section II of the applicable Pilot’s Operating Handbook for these placards and markings. For the acrobatic Bonanza (CJ-149 and after), also refer to the LOG OF SUPPLEMENTS in the Pilot’s Operating
All
required
interior
placards
and
in the Limitations of the Pilot’s
Handbook.
CAUTION Any time an airplane is repainted, inspect all placards to assure that they are not covered with paint, are easily readable, and are securely attached,
thru EA-272 except EA-242; CJ-149 and after; CE-748, CE-772 thru CE-1200; E-llll, E-1241 thiu E-2399; and
EA-242, EA-273 thru EA-472, the model designation
placard is located on the right side of adjacent to the inboard end of the flap. On
airplanes
the
fuselage
CE-1201 and after, E-2400 and after, and
EA-473 and after, the model designation placard is located on the right side of the fuselage under the
leading edge
of the horizontal stabilizer.
is mounted .50-inch below the skin
forward of the tail
lap
The
placard
and 12-inches
cone.
"END"
11-00-00
Page A16
1
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
EXTERIOR PLACARDS AND DESCRIPTION AND OPERATION
Shown in this which
are
Chapter
are
essential for
r
markings, practices,
are
information for that model.
i
DOORIACK
IINSTALL
WITH
and
maintenance
r~ RTANT
by location/description of each. The placards which shown for location only and may or may not bear identical information to the placards installed on the various individual models. Note the specific information on the placards installed on each model to determine current
followed
follow
placards
exterior
good
ILINK
MARKINGS
BOLT;
ROD
HEAD
ATTACH POIN
-----------~1-I
AFTI
L_______11 LOCATED IN THE CENTER OF THE UNDERSIDE OF THE FUSELAGE AT APPROXIMATELY FS 131.00 LOCATED ON THE OUTBOARD SIDE OF THE ROOT RIB IN THE WHEEL WELL, VISIBLE ABOVE THE INBOARD DOOR
-CAVTIONTVRN LIMITS REACHED
WHEN RED LINES ALIGN
Do NOTEXCEED
I
TOW
r--
I
IJACK PADI L---_____J
LOCATED DIRECTLY ABOVE THE NOSE LANDING GEAR TORQUE KNEE
’c-~
I
iL__T_I
LOCATED ON THE LH SIDE OF THE FUSELAGE AT APPROXIMATELY FS 151.00 (2 PLACES)
LOCATED AT WING ROOT ON CENTER SECTION SPAR, FORWARD OF THE INBOARD WHEEL WELL DOOR
IMPORTANT INSTALL UPLOCK CABLE A~TACH BOLT WITH HEAD AFT
LOCATED AT APPROXIMATELY WS 60.00 IN EACH WHEEL WELL, DIRECTLY ABOVE THE UPLOCK ASSEMBLY
1I-2MK)
Page 1 May 9/80
BEECHCRAFT
BONANZA SERIES
MAINTENANCE MANUAL
I
(ilrechcralt
(I)cechfraft
OIL AIR STRUT
OIL AIR STRUT
FART NO. 36´•825(85 sEECH L~IRCR*FI UWIWRITK~N
.tKH *IIClln EOllollllON
I
I
I I
I I
(31cchcrzli OIL AIR STRUT ru~ a
s*IINO
I
*c*n* ulaui. u~u
I
Ib´•~10010
*rrl~
INSTRUCTIONS
r´•*w~
I.C* YCUII m*TUra
ul~
IrrsrRucnow
INSTRUCTIONS
TO CHECK FLUID AND Flu REMOVE VALVE C*P. DEPRESS VALVE CORE AND ALLOW STRUT TO FULLY COMPRESS. THEN RAISE AND BLOCK
STRUT n INCH FROM COMPRESSED POSITIDN- REMOVE VALVE BODY ASSEMBLY AND F11l WITH HYDRAULIC OIL CONFORMING TO INSTRUCTION MANUAL SPECIFICATIONS. SLOWLY EXTEND STRUT FROM BLOCKED POSITION AND REPLACE VALVE BODY ASSEMBLY. DEPRESS VALVE CORE AND COMPLETELY COMPRESS STRLIT TO RELEASE EXCESS AIR AND OIL. WITH AIRPLANE EMPTY EXCEPT FOR FUu FUEL AND OIL KEEP STRUT INFLATED TO3W INCHES OF PISTON SHOWING.
I
I
I
I
I
I
rO CHIEI ilUIO 1NO nit 1111811 VILYI C*). DHnI V*LVI COll LINO ALLOW IIIUT r0 IULL* CD*n~ll. ~nm I*lw ~No UOC* (IIUI INCH 11811 COMI(IIIYD ~OllnOH llMOVI V*LVI 11)81 UBMIL* ANO lII1 WIIH H*DI*ULIC 011 CONIOIUING 10 INIIIUCIION n*Null IICIrIC*lIlNr ~II oIIrl*ct lrsrAl UNrlL IDDlrlON IL 011 C*NNOI 11 10010 WIIH I1~Ur IXIINOID II)LICIV*LVIIODI 1III
CML~
~Onu. rlOY
*c* .011110*
COYIII´•(lrO
~uru* uo rli
nm
..Y01(
I1IYr
*muuc a mas ~o
IY~IIUCltO* YI*Y~L
ua´• rm*o
IM Al LrmD *Ma
I...Y1LI
V1LY(
IVYT mi
CORT
mnla mvr ro
1*o
CWCLTlr~r
111
uo a.na
I
I
1IU tym TIC~n U* rUlrUlwOOl U.r.M
I
I
´•TURLI m i car or Ala wrr.
I
I
DI~I(IIVLLVl(Olt
WARNING
I
LIULYU
IND COM)LIIIL’I CDMIIII~ I11UI ~O 11111I1 IXCIII *N 1NO O(L
I
I
I
IlaOW’NG
I
I I
WPH *lm*llI wm txcHI lot ruu lull IND 011 110 IIIUI INIUnD 10 I INCHIlOr nllOH
)(~’1
LOCATED ON THE RIGHT MAIN LANDING GEAR STRUT
WARNING RELEASE
AIR
IN
STRUT
BEFORE
I
DISASSEMBLINO BUILT UNDER ONE OR MORE OF THE FOLLOWING BEECH PATENTS: 2388137. 24708(61 OTHER P*TENTS
~lrll
CE-748 THRU CE-979;
CJ-143 THRU
WARNING III(~II*IIINI1)UI IKH~DI1*II(MILING
D-10397 AND AFTER;
CJ-156 AND AFTER;
E-1970 AND AFTER;
CE-980 AND AFTER.
(i)eechcrall OIL AIR STRUT a
~wlu,*
*Ic*uclulcoaula
EA-273 AND AFTER;
INSTRUCTIONS ~o wo; ato uo ru
CJ-155;
E-llll, E-1241 THRU 0.1969;
D-10097, D-10120 THRU D-10396;
LOCATED ON THE NOSE
LANDING GEAR STRUT
EA-1 THRU EA-272.
rloY
laYlalAn arru nr*nusr lo Im mn 1 r*
COYIl(llIO W)IIIIM
ITYOlr
11I1(
U)D’
uurUI 410 ru
*n* nouuc a moruc ro I*II(IUCII~* Y**UIL II´•rS´•UIO*S X~I. rma lIW rrY *arro *um uc´•ruu ao*
ISIIYI)LI
caarar
LOCATED ON THE NOSE LANDING GEAR STRUT
lo
Df~lr6r
IIM
uu~rr
*4111
r0 aLf*Y
Call flUII
111 CWILIIlL’ U UO a
I~*
unu rvn
SEE CHAPTER 12 OR 32 FOR CORRECT EXTENSION
I’U"D’O’ ´•rllll
LOCATED ON THE LEFT MAIN LANDING GEAR STRUT C9101542
11-20-00
Page
2
Oct 16/92
Ale
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
NOTICE WING BOLTS ARE LUBRICATED
SEE MAINTENANCE MANUAL FOR CORRECT TORQUE VALUES
ON AIRPLANES CE-950 AND AFTER, CJ-156 AND AFTER, D-10372 AND AFTER, E-1847 AND AFTER, EA-221 AND AFTER.
LOCATED ON THE LEFT WING NEAR THE FOUR WING ATTACH BOLTS AND ON THE RIGHT WING NEAR THE TWO´• LOWER ATTACH BOLTS. ALSO LOCATED ON THE RIGHT SIDE OF THE FUSELAGE NEAR THE TWO UPPER WING ATTACH BOLTS.
r EMERGENCY LOCATOR TRANSMITTER SWITCH
I
r
-I
EMERGENCY LOCATO~ TRANSMITTER
i
SWITCH
I
ON
OFF
ARM
REARM
XMIT
O
O FOR AVIATION EMERGENCY USE ONLY.
FOR AVIATION EMERGENCY USE ONLY.
UNLICENSED OPERATION UNLAWFUL.
i
OPERATION IN VIOLATION OF FCC
I
OPERATION IN VIOLATION OF FCC
I
RULES SUBJECT TO FINE OR LICENSE
I
RULES SUBJECT TO FINE OR LICENSE
UNLICENSED OPERATION UNLAWFUL.
REVOCATION.
L
ARM
REVOCATION.
L_______________-_J _
_
_
_
_
_
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
FORWARD AND BELOW THE STABILIZER
FORWARD AND BELOW THE STABILIZER ON
ON AIRPLANES: EA-1 AND EA-2; CE-748, CE-772 THRU CE-828; E-llll, E-1241 THRU
AIRPLANES: D-10197 THRU D-10346; EA-3 THRU
E-1406, D-10097, D-10120 THRU D-10196 AND
EA-80; E-1407 THRU E-1686: CE-829 THRU CE-905 AND CJ-150 THRU CJ-155 EXCEPT
CJ-149 EXCEPT AIRPLANES WITH
AIRPLANES WITH KITS 101-3046 OR 101-3127 INSTALLED.
KITS 101-3046 OR 101-3127 INSTALLED.
r
--I
EMERGENCY LOCATOR TRANSMITTER
EMERGENCY LOCATOR TRANSMITTER
I
SWITCH XMIT
SWITCH
I
ARM
TEST
AUTO
XMIT
O FOR AVIATION EMERGENCY USE ONLY.
I
I
FOR AVIATION EMERGENCY USE ONLY.
UNLICENSED OPERATION UNLAWFUL.
I
I
UNLICENSED OPERATION UNLAWFUL.
OPERATION IN VIOLATION OF FCC
I
OPERATION IN VIOLATION OF FCC
RULES SUBJECT TO FINE OR LICENSE
i
RULES SUBJECT TO FINE OR LICENSE
REVOCATION.
i
I J
_
_
_
_
I
L
REVOCATION. _
_
_
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
LOCATED ON THE RIGHT SIDE OF THE
FORWARD AND BELOW THE STABILIZER
FUSELAGE FORWARD AND BELOW THE STABILIZER
ON AIRPLANES D;10347 AND AFTER;
ON AIRPLANES: E-2148 THRU E-2423; EA-412
EA-81 THRU EA-411: E-1687 THRU E-2147;
THRU EA-479; CE-1033 THRU CE-1240 AND
CE-906 THRU CE-1032 AND AIRPLANES WITH
CJ-156 THRU CJ-179 EXCEPT AIRPLANES
KIT NO. 101-3046 EXCEPT AIRPLANES WITH
WITH KITS 101-3046 OR 101-3127 INSTALLED.
KIT NO. 101-3127 INSTALLED.
C9200973
11-20-00
Page A16
3
Oct 16192
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
r--------------------------~
EMERGENCY LOCATOR TRANSMITTER SWITCH
r----------------------------~ i EMERGENCY LOCATOR TRANSMITTER I
SWITCH ARMED/
TEST
ARM
XMIT
ON
RESET
1
O
i FOR AVIATION EMERGENCY USE ONLY.
FOR AVIATION EMERGENCY USE ONLY.
UNLICENSED OPERATION UNLAWFUL.
UNLICENSED OPERATION UNLAWFUL.
I
OPERATION IN VIOLATION OF FCC
I
j
OPERATION IN VIOLATION OF FCC
RULES SUBJECT TO FINE OR LICENSE
I
I
RULES SUBJECT TO FINE OR LICENSE
REVOCATION.
REVOCATION.
L
L--______________~
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
FORWARD AND BELOW THE STABILIZER ON
FORWARD AND BELOW THE STABILIZER ON
AIRPLANES: CE-1241 THRU CE-)646; E-2424
AIRPLANES: CE-1647 AND AFTER; E-2694
THRU E-2693 AND EA-480 THRU EA-530
AND AFTER; EA-531 AND AFTER AND
EXCEPT AIRPLANES WITH KIT 101-3127
AIRPLANES WITH KIT 101-3127 INSTALLED.
INSTALLED.
r
r
AVGAS ONLY
AVGAS ONLY
s~B" ~I GRADE
GRADE
100LL
lIIS
1~9" ~a"
I
I
GRADE
GRADE
(M)LL
100
FOR ALTERNATE FUELS SEE
FOR ALTERNATE FUELS SEE
PILOTS OPERATING HANDBOOK
PILOTS OPERATING HANDBOOK
CAPACITY 40 US GALLONS tar USABLE) WITH WINGS LEVEL
DEPRESS FLAPPER CHECK QUANTITY
CAP. TO TAB BOTTOM 30 GAL (27 USABLE) CAP. TO TAB SLOT 35 GAL (32
USP~BLE)i
SECURE CAP
CAUTION DO NOT INSERT FUEL NOZZLE
i
MORE THAN 1%" INTO TANK
i
PLACE INBOARD OF FILLER CAP
rcnuTnow DO NOT INSERT
r------------------------1
FUEL NOZZLE
FUEL
MORE THAN 3"
L
INTO TANK
~1
1
54 US GAL CAPACITY
(51 US GAL USABLE) L__--_,-----~
80 GALLON FUEL SYSTEM ON AIRPLANES D-10303 AND AFTER; EA-33 THRU EA-272 EXCEPT EA-242;
PLACE DECAL AFT OF FILLER CAP 108 GALLON FUEL SYSTEM
CE-884 AND AFTER;
ON AIRPLANES EA-242,
CJ-156 AND AFTER; AND E-1594 AND AFTER
EA-273 AND AFTER C92M)97~
11-20-00
Page
4
Oct 16192
A16
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
FUEL AVIATION GASOLINE GRADE 100LL
or
100
FOR ALTERNATE FUELS SEE
PILOTS OPERATING MANUAL
CAPACITY 25 US GALLONS (22 USABLE)
CAUTION DO NOT INSERT FUEL NOZZLE MORE THAN 3" INTO TANK 50 GALLON FUEL SYSTEM ON AIRPLANES D-10097; 0-10120 THRU D-10302, EA-1 THRU EA-32, CE-748, CE-772 THRU CE-883;
CJ-149 THRU CJ-155; AND E-llll, E-1241 THRU E-1593
11-20-00
A16
Page
5
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
EXTERNAL
POWER 24 VOLT
THE MODEL DESIGNATION PLACARD IS LOCATED ON THE RIGHT SIDE OF THE FUSELAGE
LOCATED ON THE RIGHT SIDE OF THE
ADJACENT TO THE INBOARD END OF THE FLAP ON AIRPLANES
ENGINE COMPARTMENT, JUST BELOW THE
D-10097,
COWLING DOOR
D-10120 AND AFTER; EA-1 THRU EA-272; CORPORATION
CJ-149 AND AFTER; CE-748, CE-772
MODEL
SERIAL
THRU CE-1200, E-llll, E-1241 THRU PC
~VSE ONLY MS20392-X25 OR ISHEAR PIN WITH THIS PLVNGER
E-2399; AND EA-273 THRU EA-472.
TC B
LOCATED ON THE NOSE LANDING
THE MODEL DESIGNATION
PLACARD IS LOCATED ON THE
GEAR RETRACT LINK ROD
RIGHT SIDE OF THE FUSELAGE UNDER THE LEADING EDGE r_-
OF THE HORIZONTAL STABILIZER
i STATIC AIR.
ON AIRPLANES
I KEEP CLEAN I
CE-1201 AND AFTER, E-2400 AND AFTER,
LOCATED ON THE LEFT SIDE OF THE FUSELAGE
AND EA-473 AND AFTER.
JUST AFT AND BELOW THE REAR WINDOW
USE SAE 50 ABOVE 40" F
I USE SAE 30 BELOW 40" F
L
I
rl~l
LOCATED ON THE INSIDE OF THE LEFT COWLING
DOOR, ON THE FORWARD SIDE. THE PLACARD IS r-
VISIBLE WHEN THE DOOR IS OPEN
PULL TO
I CHECK LATCH L ------I
r--------------------~
FUEL CELL SUMPI DRAIN DAILV I_ I
LOCATED NEAR THE FORWARD HANDLE OF EACH COWLING DOOR
rI I
__
_
_
_
_
_
_
LOCATED ON THE UNDERSIDE OF EACH WING NEAR THE FUSELAGE
CAUTION
MCAiNETO tS NOT INTERNALLY GROUNOEII. COHSULT OWNEAS BEFORE
.ONI-TCENNOCSID LMANUAL
_
I
.J
DRAIN DAILY _I
LOCATED ON THE INSIDE OF EACH COWLING DOOR, ON THE AFT SIDE, THIS PLACARD IS
LOCATED ON THE LEFT SIDE OF THE FUSELAGE
VISIBLE WHEN EITHER DOOR IS OPEN
JUST BELOW THE LEADING EDGE OF THE WING
r---~ NO HANDLE L,-,~J INBOARD END LEFT FLAP, JUST OUTBOARD
ON TOP SURFACE NEAR OUTBOARD
WALKWAY ON RIGHT FLAP, 4 INCHES
END OF EACH HORIZONTAL
OUTBOARD OF FUSELAGE NEAR WING LEADING EDGE.
STABILIZER. C92009;2
"END"
11-20-00
Page
6
Oct 16/92
A16
CHAPTER
SERVICING
c5deechcraft BONANZA SERIES MAINTENANCE MANUAL CHAPTER 12-SERVICING TABLE OF CONTENTS PAGE
SUSJECT
12100-00 General
Description
And
1
Operation 12-1 0-00
Replenishing Maintenance Practices (Effectlvity: All) Filling The Fuel Cells (Effectivity: All) Draining The Fuel System (Effectivity: All) Fuel Cell Reservoir (Effectivity: CJ-149 And After) Engine Fuel Filters And Screens (Effectivity: All) Oil System (Effectivi~y: Ail) Oil Filter Removal (Effectivity: All) Oil Filter Installation (Effectivity: All) Air-Conditioning System (Effectivity: All) Depressurizing the Air-Conditioning System (Effectivity: All) Purging The Air-Conditioning System (Effectivity: All) Charging The Air-Conditioning System (Effectivi~: All) Checking Compressor Oil Level (Effectivity: All) Brake System (Effectivity: All) Oxygen System (Effectivity: All) Oxygen Servicing (Effectivity: All except E-1946, E-2104, E-2111 and after, EA-320, after) Oxygen Servicing (Effectivity: E-1946, E-2104, E-2111 and after, EA-389 thru EA-439) Oxygen Servicing (Effectivity: EA-320, EA-440 And After)
1
1 1 1
1 2 2 2 2
3 3 3 3 4 4
..........................................................................................1....,....................
EA-389 and 5 5
6
12120100 Scheduled
Servicing
Maintenance Practices
1 1
Tires
E>
Battery Propeller
1 1
Deice Boots
Shock Struts
2
Shimmy Damper Propeller Blade Maintenance
2
Induction Air Filter
3
Spark Plugs
3
3
3
Roton Locks
Cleaning And Waxing The Airplane Cleaning Plastic Windows Cleaning Interior Cabin Trim Engine Cleaning
Finish
4
5 5 5
Lubrication Lubrication Of Chart 1,
3
Landing
Servicing
Gear
Uplock
Rollers
5 6
12-00ntents A18
Page 1 Aug 18/95
aeechcraft BONANZA SERIES MAINTENANCE MANUAL CHAPTER 12-SERVICING TABLE OF CONTENTS SUBJECT
(Confinued) PAGE
Chart 2, Lubrication Schedule
Special
Tools
7 19
1 2-Contents
Page 2 Aug 18/95
A18
Beechcr~aft BONANZA SERIES MAINTENANCE MANUAL CHAPTER 12-SERVICING LIST OF PAGE EFFECTIVITY CHAPTER-SECTION-SUBJECT
15-Effectivity 1 BContents
12-00-00
12-1 0-00
PAGE 1
Aug 18/95
1
2
Aug 18/95 Aug 18/95
1
May 9/80
1 2
3 4 5
6 1220-00
Aug Aug Aug Aug Aug Aug
18/95 18/95 18/95 18/95 18/95 18/95
1
May 9/80
2
Jun 20/91
3
Aug Aug Aug Sep Sep
4 5
6 6A 7 8
9 10
10A 11
12 13 14
15 16 17
18 19 20 21 22
A18
DA~E
28/87 28/87 28/87 27/84 27/84 Oct7/83 May 9/80 Aug 29/85 Aug 29/85 Aug 29/85 oct 7/83 May 9/80 May 9/80 May 9/80 Oct 7/83 oct 7/83 Oct 7/83 Oct 7/83 Jan 18/84 Jan i 8/84 Jan 18/84 Aug 29/85
12-8ffectlvity Page 1 Aug 18/95
BEECHCRAFT BONANtA SERIES MAINTENANCE MANUAL
GENERAL
Detailed maintenance information
DESCRIPTION AND OPERATION
The information contained within this chapter pertains to the general servicing procedures and maintenance practices used when
servicing
the various systems of the
airplane.
pertaining
to these
systems will be found in the applicable chapters. Overhaul information for components of several systems will be contained within this manual. For electrical wiring diagrams refer to the BONANZA F33A, F33C, V35B 8 A36 Wiring
Diagram Manual,
P/N 35-590102-9.
"END"
1260-00
Page 1 May 9/80
BONANZA SERIES MAINTENANCE MANUAL
Normally the fuel strainers should be inspected and cleaned every 100 hours. However, the strainers should be inspected and cleaned at more frequent intervals in response to unknown fuel handling areas
conditions of service, practices, and operation in
severe
should be used; below 40"F, SAE 30 is recommended. Any aviation grade engine oil which meets Continental Motors Corporation Specification MHS248 is
acceptable
of excessive sand or dust.
OIL SYSTEM
for
use.
I
CAUTION
(Effectivity: All) If metal contamination of the oil system
airplane is equipped with a wet sump oil system with a capacity of 12 quarts of oil. The oil filler cap is accessible through an access door in the left engine cowling. The
is detected and the cause is corrected the oil cooler should be replaced. In
addition, flush out the system through the interconnected oil system plumbing and replace or clean any other accessories that will remain with the engine.
right hand access plate and unscrew the sump drain plug in the lower right hand side of the engine aankcase. An oil drain trough, furnished with each airplane is used to convey the oil through the bottom of the engine cowl prior to CJ-156, CE-922, D-10364, E-1752 and
OIL FILTER REMOVAL
EA-129. At CJ-156 and after, CE-922 and after, D-10364 and after, E-1752 and after and EA-129 and
b.
Remove the
a quick attach, snap-type fuel/oil drain adapter (see sheet 4 of special tools, 12-20-00) and approximately 18 inches of hose will be used to drain the oil
c.
Loosen the
sump.
a.
Under normal
operating conditions, the recommended operating hours between oil changes is 100 hours. The oil filter should be removed and replaced at each oil change. When operating under adverse weather conditions or continuous high power settings, the oil should be changed more frequently. Before draining the oil, run up the engine until the oil reaches operating temperature to assure complete draining of the oil. Oil grades, (2, Chart 1, 91-00-00) are general recommendations only, and will vary with individual circumstances. Check oil inlet temperature during flight in determining use of the correct grade of oil. inlet temperatures consistently near the maximum
ine oil.
number of
b.
To drain the
engine sump,
remove
the
after,
allowable indicates a heavier oil is needed. The new airplane is delivered with Rustband oil (Mll-C-6529, in the engine. This is a corrosion preventive oil and should be removed at 20 hours of operation, but no later than 25 hours of operation. If the Rust-
Type II)
band oil is not removed at the proper time, varnish may form in the engine. Oil conforming to Mll-L-6082 may be added to the Rustband oil as necessary. After
removing
the Rustband oil, refill with MIL-L-6082 min-
eral oil, which should be used until oil consumption has stabilized (until after engine break-in). After the
dispersant (AD) aviation grade weight that will give satisfactory starting. Above 40"F, SAE 50 viscosity break-in
period,
use an
ashless
oil in the heaviest
a.
LH
Gain
access
engine
to the
(Effectivity: All) oil filter
engine
by opening
the
cowl access door.
engine
oil filter
spin-off filter
and
011 FILTER INSTALLATION
Clean and lubricate the
Position the
new
safety wire. filter.
(Effectlvity: All) filter
new
filter
remove
on
the
gasket
with eng-
engine mounting
torque of 18-20 footIf a torque wrench is not available, tighten the filter with a suitable wrench for three-quarters to one
adapter pounds.
and
tighten
full turn after
gasket
the filter to
a
contact.
wire the filter to the
c.
Safety
d.
Securetheleftengine
engine adapter.
cowl accessdoor.
AIR-CONDITIONING SYSTEM
(Effectivity:
All) Servicing the air-conditioning system consists of periodically checking the refrigerant level, checking compresser oil level, checking the compressor belt tension, and changing the system air filter, Recharge the as outlined under CHARGING THE AIRCONDITIONING SYSTEM whenever the refrigerant level is low, air has entered the system, or compo-
system
nents
carrying refrigerant
are
replaced. Aefrlgerant
leaks may be detected by inspection with a flameless leak detector. When working on a refrigerant air cool-
ing system, observe the following special servicing precautions: a.
Due to the air
quality control regulations enacted refrigerant cannot be
in the United States, R-12
12-1 0-00
Page 2 Aug 18/95
A18
I
aeechcraft BONANZA SERIES MAINTENANCE MANUAL vented into the atmosphere. When performing maintenance on the air-conditioning system where R-12 can
escape from the system, evacuate the system with a recovery or recycle servicing unit that will salvage the refrigerant.
only
The
air-conditioning system is a high pressure system. Before disconnecting a refrigerant line, the system must be discharged with a recovery servicing unit. Purge the entire system to a 125-micron level. b.
c.
After the system is
depressurized, check
PURGING THE AIR-CONDITIONING SYSTEM
(Effectlvity: All) To purge the system, connect
recycle servicing unit air-conditioning system (located under the copilot’s seat). See AirConditioning System Schematic in Chapter 21-50-00, a
to the low pressure side of the
and purge the entire system with the operating at the 125-micron level.
I -´•I´•´•I ARNING
the oil
level in the compressor per CHECKING COMPRESSOR OIL LEVEL.
vacuum
pump
CHARGING THE AIR-CONDITIONING SYSTEM
(Effectlvlty: All)
A face shield should be worn when performing maintenance on the lines
I
because refrigerant coming In with the eyes can cause loss af
tcat-noc
WARNING WIIUIWO
I
sight. A face shield should be
when the lines coming In con-
maintenance
performing because rsfrlgerent
servicing the with system refrigerant because It converts to a highly toxic gas when exposed to an open flame. Do not smoke when
tact with the eyes
can cause
loss of
sight. Do not smoke when
system
DEPRESSURIZING THE AIR-CONDITIONING SYSTEM
worn
on
converts to
(Eftectlvity: All)
exposed The
I --I´•´•I
servicing the refrigerant because It a highly toxic gas when
with to
an
open flame.
servicing points for charging copilot’s seat.
the system
are
located under the
WARNING
airplane serials prior to CE-1792, E-2945 and use refrigerant R-12 (7, Chart 1, 91-00-00). For airplane serials CE-1792 and after, E-2945 and after, and EA-579 and after, use refrigerant R-134a (54, Chart 1, 91-00-00). Other refrigerants, particularly those containing methyl chloride, will cause rapid a.
A face shield should be worn when
performing maintenance on the because refrigerant coming In
For
EA-579
lines con-
tact with the eyes can cause loss ot
sight.
deterioration of the aluminum compressor components.
Do not smoke when
servicing
the
b. Connect the recycle/recovery service unit to the connections located under the copilot’s seat. When
system with refrigerant because It converts to a
exposed
highly toxic
gas when
servicing points for discharging copilot’s seat,
The
charging a completely purged system, charge pound of refrigerant.
to an open flame.
the system
are
Connect
a
service unit that
recycles
the
refriger-
ant to the service valves and open the low pressure
CHECKING COMPRESSOR OIL LEVEL
valve. When the pressure is depleted, open the pressure valve and operate the vacuum pump to completely b.
remove
After charging, start the engine in accordance with applicable Pilot’s Operating Handbook and run the air-conditioning system. Slowly add only enough additional refrigerant so that the system cools effectively. c´•
the
located under the a.
with 1
the
refrigerant
from the
system,
(Etfectivity: All) The air-conditioner compressor oil level should be checked by a qualified air-conditioner service man if 12-1 0-00
A18
Page 3 Aug 18/95
aeechcraft BONANZA SERIES MAINTENANCE MANUAL refrigerant charge is lost (evidenced by oil loss). airplane serials prior to CE-1792, E-2945 and EA-579, the air-conditioner system requires 4 to 5 ounces of 500-viscosity oil (8, Chart 1, 91-00-00). For airplane serials CE-1792 and after, E-2945 and after, the
BRAKE SYSTEM
(Effectivity: All)
For
and EA-579 and after, the air-conditioner system requires 4 to 5 ounces of Ester Oil (65, Chart 1, 91-00-
00). Check the compressor oil level
as
hydraulic brakes are self-compensating and require no adjustment. Linings should be checked for small nicks or sharp edges which could damage the The
brake discs. Worn, dished or distorted brake discs replaced. The brake fluid is supplied to the
should be
brake system from the reservoir tank located in the engine accessory section and is accessible by raising
follows:
the Fabricate
a.
angle
so
a
dipstick by bending
a
wire to
a
90"
that 1-112 inches of the wire will insert into
the compressor. b.
only
dipstick with a flat for the paint to dry.
Paint the
ficient time
Start the
black
paint. Allow suf-
of the
engine
cowl. The reservior should
hydraulic fluid (9, Chart 1, 91-00-00) system. Ensure that no dirt or foreign is allowed to enter the brake system.
MIL-H-5606
in the brake matter
in accordance with the
applicable engine Operating Handbook and run the airconditioning system for 15 minutes with the engine running at low rpm to allow oil to accumulate in the compressor. Observe the engine operating limitations as noted in the applicable Pilot’s Operating Handbook. Shut down´• the engine in accordance with the applicable Pilot’s Operating Handbook. c.
right side
be filled to within 1-112 inches of the top and a visible fluid level maintained on the dip stick at all times. Use
Pilot’s
OXYGEN SYSTEM
(Effectivity: All)
In general, the oxygen system on the Bonanzas may be serviced in accordance with FAA AC43.13-1A.
Relieve the air-conditioner system pressure by evacuating the system with a recycle servicing unit. d.
e.
After the system pressure is relieved,
oil filler
remove
the
plug.
dipstick through
the oil filler
port, slowly
rotate the clutch shaft until the
dipstick will
insert to the
f.
Insert the
ENGINE
bottom of the compressor. g.
Withdraw the
dipstick
at
dipstick;
COMPRESSOR
LIA
FIREWALL
oil should
register
on
5/8 inch below the filler port. Add oil
the as c
necessary to maintain this measurement. H
h.
Install the oil filler
plug
with
O-ring
and
secure
plug. NOTE Make sure that the O-ring is not twisted and that dirt or particles ARE NOT ON the O-ring seat. The plug should be snug. Do not
overtighten
the
COMPRESSOR FUSE (NOT APPLICABLE TO E-2104, E-2111 AND AFTER; EA-BX), EA-440 AND AFTER)
FILLER FLVG
;T
I
BAFFLE I
plug.
35-425-1
i. Charge the air-conditioning system as noted in CHARGING THE AIR CONDITIONING SYSTEM.
j.
Check the
area
around the filler
plug for leaks.’lf
leaks exist, do not overtighten the filler plug. Remove the plug as noted in step "e" and install a new O-ring
depressurizing the system with a recycle servicing unit. Secure the plug and recharge the system as
after
noted in steps "h" and "i".
Servicing Compressor (Effectlvlty: All) Figure 1
12-1 0´•00
Page 4 Aug 18/95
A18
aeechcraft BONANZA SERIES MAINTENANCE MANUAL
I
WARNING w*awlm
This pressure may be increased an additional 3.5 psi for each degree of increase in temperature; similarly,
I
Keep fire and sparks away and never smoke In the proximity of oxygen. Tools, equipment and hands must also be kept clean when servicing the oxygen system, since deposits of oil or other hydrocarbons are highly flammable when exposed to high concentrations of oxygen. Furthermore, the presence of other foreign particles In the oxygen lines may result In leaks that will both exhaust the o~gen supply and present a fire harard. As an additional safety precaution, use only the antlselze compounds and leak-testing soaps recommended for breathing oxygen systems,
pressure for the
Breathing Oxygen (10, Chart 1,91-00-00) when recharging only
Aviator’s
the oxygen bottle.
Close the shutoff valve, disconnect the supply cylinder, and replace the filler valve cap.
OXYGEN SERVICING
(Effectivlty:
and
Ensure that all
airplane electrical power
is off. Do
operate electrical switches, or connect or disconnect ground power generators during the oxygen charging operation. not
b.
Make
servicing
sure
that
no
fueling or other flammable fluid servicing the oxygen sys-
is in process when
Observe the guidelines under the heading OXYGEN SYSTEM in this Chapter and service the system as follows: Remove the access opening over the oxygen cylinder shutoff valve and check that the valve is off.
a.
copilot’s
Slide the
b.
seat to the rear until the filler
valve is clear, then remove the cap from the filler valve and connect the supply cylinder to the filler valve.
Open
the valve
on
Always ground the servicing equipment and the system to be serviced before connecting the filler adapter.
Close the valve
e.
Close the valve
g. Disconnect the filler valve cap.
Replace the
h. i.
WARNING
Do not use oxygen Intended for medlcal purposes, or such Industrial uses as welding. Such oxygen may contain excessive moisture that could free~e up the valves and lines of the oxygen
system,
Open system to d.
cylinder shutoff valve and slowly fill the 1850 ~50 psi at 70"F, ambient temperature.
the
oxygen
cylinder.
on on
Slide the
airplane
the
the
oxygen
copilot’s
cylinder.
charging cylinder.
supply cylinder
access
and
and
replace
the
panel.
seat forward to its normal
posi-
tion. OXYGEN SERVICING
(Effectlvlty: E-1946, E-2104, EA-439)
E´•2111 and after, EA-389 thru
Observe the
guidelines under the heading OXYGEN Chapter and service the system as
SYSTEM in this follows: a.
I--~I
airplane
the
d. Open the valve on the charging cylinder slowly fill the airplane cylinder.
tem c.
EA-320, EA-389
after)
The
a.
All except
E-1946, E-2104, E-2111 and after,
f.
following procedures should be followed prior to, and during the oxygen servicing operation:
of drop in temperature, reduce the cylinder by 3.5 psi.
e.
c.
NOTE Use
degree
for each
Check that the oxygen system is turned off.
(Check
the
push-pull knob.)
b. Slide the copilot’s seat to the valve is accessmedi. c.
rear
until the filler
Remove the filler valve cap and connect the sup-
ply cylinder. d.
Open
the valve
on
the
supply cylinder and slowly
the
supply cylinder and discon-
fill the system. e.
Close the valve
nect the f.
on
supply cylinder.
Install the filler valve cap. 12-1 0-00
Page A18
5
Aug 18/95
I
aeechc~slft BONANZA SERIES MAINTENANCE MANUAL g.
Slide the
copilot’s
seat to its normal
OXYGEN SERVICING And
position.
(Etfectivity: EA-320,
EA-440
Locate and
the
Open the charging cylinder airplane cylinder(s).
d.
After
e.
Reinstall the
c.
Observe the guidelines under the heading OXYGEN SYSTEM in this Chapter and service the system as follows: a.
remove
wing, outboard
Remove the cap from the filler supply cylinder to the filler
nect the
After)
the left
b.
the of
access panel on the top of wing station 66, and aft of
opening opening.
valve and
and
con-
slowly
fill
filling the airplane cylinder(s), close the supply cylinder shutoff valve, disconnect the supply cylinde’l and replace the filler valve cap. access cover.
the front spar.
12-1 0-00
Page 6 Aug 18/95
A18
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
SCHEDULED SERVICING PRACTICES
MAINTENANCE
a.
Before
connecting an external power unit, turn equipment switches, all radio equipment, alternator switch. The battery switch in the airplane
OFF all electrical and the
should be ON.
T/RES nose
wheel tire is
a
5.00-5
4-ply
tire. The main wheel
are 7.00-6 6-ply tires. Inflate the nose wheel tires to 40 pounds and the main wheel tires to 33 to 40 pounds, Maintaining proper tire inflation will minimize tread wear and aid in preventing tire rupture caused from running over sharp stones and ruts. When inflating tires, visually inspect for cuts,
tires
arcing, make certain no power is being the external power unit when the connection is
To prevent
b. The
applied by made.
Leave the
c.
battery ON during
CAUTION
cracks, breaks, and tread wear. The pressure of a serviceable tire that is fully inflated should not drop more than 4
percent
over a
24-hour
the entire external
power operation.
The
period.
may be damaged if than 30 volts.
battery
exposed
to
voltages higher NOTE
BATTERY Oil and other
hydrocarbons spilled
on
tires not
only weaken the rubber but may cause it to swell. Avoid spilling oil, fuel or solvents on tires and clean off any accidental spillage as soon as possible.
of
tendency
is located
battery
on
the
right
side of the
engine
Corporation cannot recommend recapped tires. Recapped tires have a
The fluid level of the battery should be checked every 25 hours and maintained 3/8 inch above the top of the
to swell as a result of the increased
separators. Add only distilled
Beech Aircraft use
The
compartment, just forward of the firewall. The battery is accessible for servicing by raising the right engine cowl door and removing the battery box cover.
CAUTION
the
A 24-volt, 1 10 ampere hour Teledyne Battery Products leadacid battery is provided for operation of the electrical system.
temperature generated during
takeoff. Increased
gravity
specific
water to maintain the
of between 1.275 and 1.295.
can jeopardize proper function of the landing gear retract system, with the possibility of damage to the landing gear doors and retract
tire size
NOTE
mechanism. Do not overfill the are
overfilled,
lower
EXTERNAL POWER
battery.
When the
water and acid will
of the
portions fuselage.
engine
battery spill
cells
on
the
accessory section
and lower An external power unit with a negative ground may be used to supply power for ground checks, starting and battery
charging. The power unit may be connected directly to the battery or to an optional external power receptacle, located on the lower engine cowling. The receptacle is designed for use with a standard AN type plug.
For further servicing information, detailed instructions are furnished with each battery from Teledyne Battery Products.
optional external power circuit is equipped with a relay diode to protect the airplane electrical system against damage from an external power source with reversed polarity.
The surface of the deice boots should be checked for
The
and
a
Observe the following precautions when using power
source.
an
external
PROPELLER DEICE BOOTS
oil after
Any
servicing
oil found
on
Removal of oil
the
airplane
engine flight.
and at the end of each
the surface of the boots should be removed.
can
accomplished by the use of a neutral Special care should be used on cleaning, to avoid damaging the surfacing. be
soap and water solution. electric deice boots, while
special conductive
12-2M)0
Page
May
1
9/80
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CAUTION
NOTE Because the deicer boots
flexible
stock,
are
a bottle containing compressed air nitrogen under extremely high pressure
If
made of soft
be
must
care
exercised
used,
care
is
should be taken not to overin-
against dragging gasoline hoses over them resting ladders or platforms against the
flate the strut.
surface of the boots.
be used with
or
or
A pressure regulator must high pressure bottled air or
nitrogen. SHOCK STRUTS Remove all the air-
To check the fluid level and fill the strut, jack plane, remove the valve cap and depress the valve core
to release the air pressure from the strut.
WARNING The
strut
removal
be
should
of the valve
pressure may result in
before
deflated
body
or
excessive
personal injury
or
property damage. Compress and block the strut 1/4-inch from the fully Remove the valve body compressed position. assembly and fill with MIL-H-5606 hydraulic fluid (9, Chart 1, 91-00-00). After filling the strut, slowly extend the strut from the blocked position and replace the valve body assembly. Completely conipress the strut to release excess air and oil, then reinstall the valve core.
material from the
foreign
of the shock struts with
hydraulic
a
exposed piston
cloth moistened with
fluid.
SHIMMY DAMPER To check the fluid level in the shimmy damper, insert a wire of approximately 1/16-inch diameter through the hole in the disc at the end of the
piston
rod until
it touches the bottom of the hole in the floating piston. Mark the wire, remove and measure the depth of insertion. Inserting the wire in the hole of the floating
piston, rather than letting it rest against the piston, will give a more accurate check.
face of
the
NOTE To determine if the wire is inserted in the hole of the floating piston, insert the wire several times, noting each insertion depth. wire is correctly inserted, the be will approximately 1/4-inch length
When the
CAUTION
greater.
Do not inflate the struts with the jacks since sudden extension
on
inflation
damage
of the
strut
may
on
the
shimmy damper is full, the insertion depth The empty reading is 3-1/16 inches. If the wire enters the piston rod over 2-3/8 inches, hydraulic fluid should be added. When hydraulic fluid is needed, remove the shimmy damper and add MIL-H-5606 hydrau;.e fluid (9, Chart 1, 12-20-00) as
airplane
When the
or over-
is 2-3/16 inches.
cause
internal
to the strut.
With the airplane resting
ground
and the fuel
nitrogen airplane D-10,397
follows:
after, E-1,970 and after, and EA-273 and after,
position
cells full, inflate the nose strut with dry air or until 3-1/2 inches of piston is exposed. On serials CE-980 and after, CJ-156 and after, and
area
gear strut until 5 inches of the strut exposed. Rock the airplane gently to prepiston vent possible binding of the piston in the barrel when inflate the is
inflating.
a.
Secure
the
shimmy damper
in
a
fixed
with the clevis end down.
nose
b.
Remove the cotter
piston rod. is compressed.
from the
pin, washer,
Remove with
and
care as
the
spring, spring
12-20-00
Page 2 Jun 20/91
A14
BEECHCRAFT BONANZA SERIES MAIN-TENANCE MANUAL
c.
scraper of end
internal Remove the ring, snap ring and the end seal from the aft the barrel (opposite the clevis
end),
PLUGS
the proper spark plug and spark plug refer to Continental Service Bulletin No. M77-10. The spark plugs should be installed with no lubrication and torqued to 300 to 360 inch-pounds (25 to 30 footFor
gap,
d. the
SPARK
Insert
a
6-32 threaded rod into and remove the piston.
floating piston
pounds). Push the piston rod to the clevis end and fill the barrel with MIL-H-5606 hydraulic fluid (9, Chart i, 91-00-00). e.
f. Slowly actuate the piston rod, allowing the fluid to flow into the clevis end chamber, then return the piston to the
clevis end of the barrel, g.
Refill
replace the internal
the
displaced
end
snap
seal, ring.
h.
Fill
the
i.
Reinstall
fluid
and
ring
and
scraper
piston rod with fluid,
ROTON
Usually,
Roton locks will not need service. If there is a grinding and binding in the lock as the seat reclines or if the becomes action return jerky, a small amount of grease properly applied as follows should improve the operation.
Use only ENCO ANDOK-B grease (12, a. Chart 1, 91-00-00) on the threads as shown in Figure i. Too much grease in the wrong
place floating piston, spring washer and cotter pin. Spread the cotter pin to allow clearance for the measuring wire. it
Reinstall
can
cause
improper operation.
the
Release the i. from the floating
k.
LOCKS
(Figure 1)
the
PROPELLER BLADE
6-32
rod
and
b. co un
the
Compress
te rba 1 ance
guide approximately
spring
spring
and one
inch. c.
remove
Remove the retaining ring.
piston. Relax pressure on the spring guide d. and counterbalance spring slowly until the spring is fully extended.
shimmy damper,
MALNTENANCE
Remove the lock from the fixture the spring guide, count~rbalspring and spring guide tube.
e.
Due
to
the
high
stresses
to
which
blades their are subjected, maintenance is vitally important, the leading edpe of each on lade from the tip inboard to Just beyond 33-inch All nicks and station. the scratches be must repaired before the airplane is flown. Nicks and scratches set of concentrations which can stress up exceed the strength of the blade material; the result will be a crack and premature failure of the blade. The method and limits for this type of repair, as outlined the in applicable Propeller Handbo~ok,
propeller
and
remove
ance
careful
garticularly
Apply a small completely (see Figure 1). f.
quantity
of
grease
Reassemble the lock. For service g. other than lubrication, return the Roton lock to the manufacturer. CLEANING FINISH
AND
WAXING
THE
AIRPLANE
should be followed carefully.
Prior to
INDUCTION AIR FLLTER
wheels, making certain the brake discs are covered; attach pitot cover securely; install
The induction air filter should be cleaned periodically and replaced every 500 hours of service. Clean the filter as described in the manufacturer’s instructions on the filter.
cleaning plugs
in
the exterior,
or
mask
off
cover
all
openings. Be particularly careful
the
other to mask
off both static air buttons before washing or
waxing.
72-20-00 Page 3 A12
Aug 28/87
BEECHCRAFT BONANZA
SERIES
MAINTENANCE MANUAL
RETAINING RING
FULLY EXTENDED
SPRING GUIDE
(APPROX) APPLY (LIGHTLY HERE ONLY)
3/4"
GREASE
SPRING GUIDE TUBE
ABSOLUTELY NO GREASE
MAIN ASSY
IN THIS AREA
COUNTERBALANCE SPRING
Lock Figure 1
Roton
The
urethane
the finish
with
a
wax
paint finish cleans easily and mild detergent solution, sponge white clean A Rinse with clear water. cloth, saturated with either MEK (31, Chart 1, 91-00-00) or toluol (19, Chart 1, 91-00-00) may be used to remove accuand dried mulations of oil or grease, insects. Flush the surface with plenty of cool water to remove all traces of soap and dry with a chamois to prevent water marks.
is
yellowed
a
appearance.
removed before
be
should
a
The old coat
new
applied.
Airplanes with be polished to
aluminum
skin
surfaces may
high gloss with any warranted aluminum polish. Soft clean cloths a
chamois should be used to prevent scratching the aluminum when cleaning and
or
a
polishing. CLEANING
PLASTIC
WINDOWS
CAUTION CAUTION
When mild care
from
airplane use special avoid washing away grease
washing soap to
with
any
and
the
Do
water,
lubricated
washing with solvent
area.
not
an
use
ice
scraper
to
windows because this practice may cause scratches To avoid to the window surface. scratches, any cleaning of the windows should be done with care. remove
After
in the wheel
lubriareas, lubricate all cation points. Premature wear of lubricated surfaces may result if above the precautions are not taken.
well
ice
from
commercial cleaning compound made specifically for acrylic plastic windows may be used. When using a commercial cleaner,
A
For better protection, a non-abrasive wax may be used on airplanes exposed to cormoisture with rosive atmospheres condensation.
follow the instructions on the container. If a commercial cleaner is not available, the following instructions should be followed:
Wax application procedures are important and will vary in accordance with the type being used. For best results, follow the A manufacturers wax specifications.
of the acrylic plastic windows The should never be attempted when dry. window should first be flushed with water
build-up
of
several
coats
of
wax
may
give
Cleaning or
a
mild
lightty with
solution, then grit-free cloth,
soap a
rubbed chamois
12-20-00
Page 4 Aug 28/87
A12
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
or are or
sponge. Stubborn grease or oil deposits readily removed with aliphatic naphtha hexane. Rinse with clear water.
thinner or aromatic cleaners clean the to they will damage the windows; surface of the plastic. Aliphatic naphtha and similar solvents are and extreme highly flammable, be taken when must care using them. CLEANING
use
INTERIOR
CABIN
TRIM
Proper care and cleaning of the interior cabin trim (Noryl and Kydex plastics) is of to maintain a primary importance desirable appearance. Clean the interior trim with cabin a detergent soap and water, and brush scrub with a soft bristle brush will dislodge most dirt. Wet wipe with clean water and wipe dry. Alcohol may be used to remove foreign material that is alcohol soluble, CAUTION
The
interior cabin trim if contaminated
easily
methyl
engine solvent, or
may any
be cleaned with Stoddard standard neutral solvent
engine. Compressed air speed up drying time.
may
be
used
to
LUBRICATION
Lubrication charts and diagrams within information that contain this section ensure the proper operation and preservation of the airplane. Location, interval
Avoi;l and lubricant required are given. excessive application of lubricants. LUBRICATION OF ROLLERS
LANDING
GEAR
UPLOCK
uplock roller bearings should be lubricated with MIL-G-2382f grease (11, Chart i, 91-00-00) every 100 hours or any the time after cleaning the wheel we 11 bearings are subjected to degreasing with solvent under pressure. Using a pressure the uplock bearing is lubricated gun, through a grease fitting installed in the uplock bearing bolt. The
NOTE
ethyl
thinner and other types of thinners. Sharp edges or cuts on the edge of the interior cabin trim material may cause it to crack.
gasoline,
The
be can cleaned
ketone, naphtha, Mufti, standard solvent,
with
CLEANING
for recommended cleaning engines. The cleaner may be sprayed or brushed on the
CAUTION
Do not abrasive
ENGINE
lacquer
The
grease Fitting on the drag the di rectly above upl ock roller bearing, does not supply lubrication for the uplock roller
leg,
bearing.
12-20-00
Page 5 A12
Aug 28/87
BEECHCRAFT BONAMIA SERIES MAINTENANCE MANUAL
CHART 1 SERVICING
LOCATION
ITEM
SERVICE WITH
INTERVAL
See Consumable
Preflight
Check
Engine Battery
Oil Level
Access door
Water
upper cowl (1) RH rear side of
Air Conditioner
Compressor
Oil Level
Air Conditioner
Refrigerant Magneto Pressure-
on
Materials Chart
See Chapter 21 for location and special instructions Between
25 hrs.
Distilled Water
engine compartment (1) See Chapter 21 for location and special instructions
Suniso No. 5GS
Tex_a~WF
or
As
required
As
required
100
500 Viscosity Oil Rehigeranr No. 12
50 hrs.
Magnetos
ization Air Filter
Change Engine Oil
Lower
rear
See Consumable
side of
Engine
Left
Oil Filter
rear
100 hrs.
Materials Chart
engine (1)
100 hrs.
side of
engine ~1) Clean Induction Air Filter Fuel
Injection Control
Fuselage nose section grill (1) Fuel injection control valve
Valve Screen
of the Fuel Selector Valve
Strainer
on
the lower side
engine (1)
Fuel selector valve inboard left wing root (1)
Clean on
as
described
50 hrs.
the filter
Clean with solvent and blow dry with air
pressure Clean with solvent and blow
dry
100 hrs.
100 hrs.
with air
pressure Pressure
Pump
Intake
Rear
engine
baffle
(1)
Replace
300 hours on
Fliter
or
condition
Drain Fuel
Sump Drain
Fuel Cell Drains Static Drain
Preflight Preflight
Inboard left wing root (1)
wings (2) Behind the ah upholstery panel (1) Under both
50 hrs.
Replace Induction Air Filter Pressure System Inline Filter
Fuselage grill (1)
nose
section
Between pressure and instruments
500 hrs. on
regulator (1)
300 hn. on
or
condition or
condition
12-20-00
PageG Sep 21/84
A9
BEECHCRAFT BONANZA SERIES MAIMENANCE MANUAL
CHART 1
SERVICING (CONT’D) SERVICE WITH
LOCA TION
ITEM
INTERVAL
Sen/ice
Brake Fluid Aeservoir
Upper
forward side of the
firewall
Under front seats
Oxygen Cylinder
MIL-H-5606
hydraulic
(1) (1)
As
required
As
required
As
required annually
fluid
Mil-0-27210 aviator’s
breathing oxygen
except EA-320 EA-440 and after.
EA-320, EA-440 and after in left Main and Nose
Landing
Top
wing (1)
of each strut
(3)
Shimmy Damper
Mll-H-5606
hydraulic fluid and dry compressed air
Gear Struts Nose
landing gear (1)
Denotes
As
MIL-H-5606
hydraulic
or
fiuid
or
required annually
quantity of servicing points.
12-20-00
Ag
Page 6A Sept 27/84
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHART 2 LUBRICATION SCHEDULE
G
J
;&I~,PO
A
i
c
L
~inl I DH
N
Q
~1)7 R R 36804´•120
NOTES
i.
The
following details. (A
lubrication points B36TC. 2.
3. 4.
are
the V-tail
T) constitute a lubrication san/icing schedule. Major differences between model types relative to configuration, exdu8ively for the V358, and the cargo doors provided only on the model A36. A36TC.
thru
~k
operational application may dictate more frequent san/icing. Landing gear components may require lubrication every 25 or 50 hours, depending on operation. MIL´•G´•81322 grease may be used in place of MIL-G-23827 grease in warm climates: however. Environmental conditions and
in
extremely
cold climates
MIL-G-23827 grease should be used. Care should be taken when using greases MIL-G-81322 and MIL-G-23827, since they contain synthetic lubricants which will 5. discolor painted surfaces, and will soften rubber products.
3&604´•121
12-20-00
Page7 A6
Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHART 2
(Cont’d)
LUBRICAT)ON SCHEDULE
INDEX
LOCATION
POINTS(
LUBRICANT
INTERVAL
(5)
MIL´•Gd1322
100 hfs
NOSE WHEEL WELL
n
Nose wheel
steering
m
o DETAIL
A
35-604-12
L~3
O
m
DETAIL
B INTERVAL
INDEX
LOCATION NOSE LANDING GEAR
POINTS(
LUBRICANT
O
Nose shock strut
(1)
Mll-H-5608
AR
O
Shimmy damper
(1)
MIL-H-5806
AR
Nose gear
hinge points
(2)
MIL-G-81322
100 hrs
m
Nose gear
linkage
(2)
MIL-G-B1322
100 hrs
O
Nose gear torque knees
(6)
MILO-81322
100 hr3
MIL-G-B1322
100 hrs
(2)
Ae,oshell 5 Prefened or MII-Gg1 322
100 hrs
(2)
M~L´•G-81322
100 hrS
MIL-0-81322
100 hrs
"A" Frame
O
pivot points
Nose wheel
bearings
Nose gear swivel 9
12-20-00
Page 8 May 9/80
Rod end fittino
3580e’3
BEECHCRAFT BONANZA SER\ES
MAINTENANCE MANUAL
CHART 2 (Cont’d) LUBRICAflON SCHEDULE
i’
~K r IZI
DETAIL
INDEX
LOCATION
C .POINTS(
LUBRICANT
INTERVAL
SAE 20 or SAE 10W30
100 hrs
NOSE GEAR DOORS
O
Nose wheel door hinges
(4)
35804´•14
DETAIL
INDEX
LOCATION
D
POINTS(
LUBRICANT
INTERVAL
(10)
SAE 20 or SAE 10W30
100 hrs
RUDDER PEDALS
O
Rudder
pedal linkage
35-804-15
12-20-00
All
Page 9 Aug 29185
BEECHCRA~I BONANtA SERIES MAINTENANCE MANUAL
CHART 2 (Cont’d)
LUBRICATION SCHEDULE
INDEX
LOCATION FORWARD CABIN DOOR
POINT(
LUBRICANT
INTERVAL
O
Forward cabin door handle
(1)
SAE 20 or SAE 10W30
100 hrs
Forward cabin door latch
(3)
SAE 20 or SAE 10W30
100 hrs
Forward cabin door
(2)
SAE 20 or SAE 10W30
100 hrs
O
hinges
O
DETAIL
E 35601-18
Detail F applies only to serials E-lll1, E-1241 and after; EA-1 and after.
k O NOTE Lubricate all internal moving parts of the latching mechanism with Aeroshell 17,
~Et
as
required.
o DETAIL INDEX
LOCATION AFT CABIN DOOR
O O
F
POINTS(
LUBRICANT
INTERVAL
AH cabin door handle
SAE 20
100 hrs
Ah cabin door latch
SAE 10W30 SAE 20 or
(3)
or
100 hrs
SAE 10W30
O
’AH cabin door
’Mix MIL´•M-7866 with
naphtha
hinges
and
apply
(2) with
a
brush.
MlL-M-7866
AR 35-804-17
12-20-00
Page 10 Aug 29/85
All
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
CHART 2 (Cont’d) LUBRICATION SCHEDULE
POINTS(
LUBRICANT
INTERVAL
(18)
SAE 20 or SAE 10W30
100 hrs
LOCATION
INDEX
CONTROL COLUMN
linkage
O
Control column
O
Control column head
(3)
SAE 20 or SAE 10W30
100 hrs
Control column torque knees
(6)
SAE 20 or SAE 10W30
100 hrs
O O
~C C: PRIOR TO D-10404, CE-1037, 8-2111 EXCEPT 8-1946 AND 8-2104, EA-389 EXCEPT 84-320
DETAIL
G 36604((8
‘-o
55 DETAIL
GG
E-1946, D´•2104, E´•2111 AND AFTER, EA-320, EA-389 AND AFTER. INDEX
LOCATION CONTROL COLUMN
m m"" 1~3
Control column chains Ball
bearings (without seals)
Torque Shafts W’p"
tllli
length
POINTS()
LUBRICANT
INTERVAL
(4) (10)
SAE20
100 hrs.
MIL-L-7870 Oil
100 hrs.
(2)
MEK Solvent
100 hrs.
a
of square shafts with MEK, these surfaces to remain
dry
or
10W30 Oil
and free of oil.
Remove one of the nonadjustable rollers (27-00-00). If it is a sealed roller with the seals intact, rainstall the roller and make a maintenance record that the rollers are sealed and do not need lubrication. If the rollers are not sealed, or the seals are not intact, they may be replaced with sealed rollers and a maintenance record made that the rollers do not need lubrication. If the adjustable rollers are removed for lubrication or replacement, refer to Chapter 27-00-00 for adjustment. 36-604-(17 001
12-20-00
All
Page 10A Aug 29/85
BEECHCRAF~ BONANZA SERIES
MAINTENANCE MANUAL
CHART 2 (Cant’d) LUBRICATION SCHEDULE
NOTE At series D-10380 and after. CJ-1Stj and after. CE-960 and after, E-1886 and
after, EA-249 and after, sealed bearings were
installed
and
no
lubrication
is
required.
8~
I
DETAIL INDEX
LOCATION
H
POINTS(
LUBRICANT
INTERVAL
(2)
SAE 20
100 hrs
TRIM TAB CONTROL
O
Elevator trim control
or
SAE 10W30 3escw´•,cs
t2-2eoo
Psgsli Oc17/83
A6
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHART 2 (Cont’d) LUBRICATION SCHEDULE
INDEX
POINTS(
LUBRICANT
INTEAVAL
(1)
MIL-G-B1322
600 hn
gear actuator gear box
(1)
MIL-L-2105 Mobil 636
300 hrs
gear system retract
(5)
SAE 20 or SAE 10W30
LOCATION LANDING GEAR ACTUATOR
O
Landing gear
O
’Landing
O
"Landing
motor gear box
arms
or
100 hrs
properly filled, the oil level on apip stick inserted through the filler hole will be approximately 1/4 inch.
’When
jl
2]
"The
nose
gear retract
arm
is located beneath the gear box.
l~J
DETAIL
I 35604-47.
DETAIL
J
INDEX
LOCATION FLAP MOTOR
POINTS(
LUBRICANT
INTERVAL
111
Flap flexible drive shaft (inside of cable housing)
(1)
MIL-G-23827
900 hrs
12-20-00
Page 12 May 9/80
3CgOC48
BEECHCRAFF BONANZA SERIES MAINTENANCE MANUAL
CHART 2 (Cont’d) LUBRICATION SCHEDULE
INDEX
LOCATION
POINTS(
LUBRICANT
INTERVAL
(2)
Mll-L-10324A OR MlL-L-2105C 75W OR 101-380016-1
900 hrs
FLAP ACTUATOR
m
Flap
actuator
~ETAIL K 3caocso
O
U
DETAIL
L
Detail L depicts the Bonanza 33 and 36 Series airplanes. The Bonanza 35 Series does not incorporate Index 2.
INDEX
n
O O
LOCATION ELEVATOR TRIM ’Elevator trim tab
hinge
"Elevator him tab actuator
tTab control horn pivot
POINTS(
LUBRICANT
INTERVAL
(2)
MlL-M-7866
100 hrs
(2)
MlL-G-23827
AR
(t)
SAE 20
AR
or
SAE 10W30 ’Mix MlL-M-7868 with naphtha and apply with a brush. series 35 Bonanza used "The actuator is not airplanes. on the tOn the Bonanza 35 series, lubricate both the upper and lower tab control horn pivots (Index 3). On the Bonanza 33 and 36 series airplanes, only the upper tab control horn
pivot lubrication
is
required.
3ssoc49
12-20´•00
Page 13 May 9/80
BEECHCRAFF BONANZA SERIES IAINTENANCE MANUAL
CHART 2 (Cont’d) LUBRICATION SCHEDULE
INDEX
LOCATION
POINTS(
LUBRICANT
INTERVAL
(6)
SAE 20 or SAE 10W30
100 hrs
COWL FLAPS Cowl
flap hinges
O
DETAIL
M 355555(
~3
~ETAIL
N
INDEX
LOCATION MAIN LANDING GEAR
POINTS(
LUBRICANT
INTERVAL
O
Main shock struts
(2)
MIL´•H-5606
AR
I~
Hinge paints
and retract
(1 4)
MlL-G-81322
100 hn
O
Main gear torque knees
(10)
MIL-G-8~ 322
100 hrs
O
Main wheel
(4)
Aeroshell 5
100 hrs
links
bearings
Preferredor MlL-G-81 322
O
Landing gear uplock rollen
12-20´•00
Rage 14 May 9/80
(2)
MIL-G-23827 See Lubrication of Landing Gear Uplock Rollers In this chapter.
35604´•52
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHART 2 (Cont’d) LUBRICATION SCHEDULE
o
m LI
DETAIL
P
*Lubricata the aileron pushipull rod ends tin place) at 100 hr intervals using SAE 20 or 10W30 oil. or remove the aileron push/pull rad assembly and clean 8 lubricate rod ends using MIL-G-23827 grease. Rotate the rod end eye balls to assure adeguate lubrication coverage. Check aileron rigging after reinstallation of the rod end
INDEX
LOCATION AILE RON
O
Aileron control
O
assembly.
linkage
*Aileron push/pull rods ends
POINTS(
LUBRICANT
INTERVAL
(6)
SAE 20 or SAE 10W30
100 hn
(4)
MIL-G-23827 or SAE 20 or SAE 10W30
100 hrs
(1)
MIL-G-23827
AR
Ot
Aileron trim tab actuator
~t
Aileron trim tab
hinge
(1)
VV´•LBOO Preferred. LPS-1. CRC 3-36. WD-40
100 hrs
Ot
Aileron trim tab
push-pull linkage
(5)
VV-L-BOO Preferred. LPS-1, CRC 3-36. WO-40
100 hrs
IZb
EA-389 and t Enactive 6-1946, E´•2104. E-2111 and after: EA-320, after. 366M-ln
12-2M)O
Page 1G Oct 7/83
A6
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHART 2 (Cont’d) LUBRICATION SCHEDULE
INDEX
LOCATION BAGGAGE DOOR
POINTS(
LUBRICANT
INTERVAL
O
Largedoor
latch mechanism
(3)
100 hrs
O
Small door latch mechanism
(1)
SAE 20 or SAE 10W30 SAE 20 or SAE 10W30 MIL-M-7866
’Door
hinge
(1)
’Mix MIL-M-7866 with naphtha and
apply
with
a
100 hrs
AR
brush.
1
O
3
DETAIL
Q
Detail Q includes serials CE-748. CE-172 and after; CJ-149 and after: and D-10097, 0-10120 and after. 35-604-55
~I DETAIL
R
INDEX
LOCATION ELEVATOR TAB
POINTS(
LUBRICANT
INTERVAL
n
Elevator tab actuator
(1)
MIL´•G-81322
100 hrs
O
Elevator tab
(4)
SAE 20 or SAE 10W30
~00 hrs
linkage Detail R includes
only
serials 0-10097, 0-10120 and after.
35-eo4-5s
12-20-00
Page 17 A6
Oc17183
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHART 2 (Cont’d) LUBRICATION SCHEDULE
INDEX
LOCATION DIFFERENTIAL CONTROL
POINTS(
LUBRICANT
INTERVAL
O
Elevator cable reduction
(2)
SAE 20 or SAE 10W30
100 hrs
O
Differential control assy
(4)
MlL-G-81322
100 hrs
an
I
i?lg
45‘
DETAIL Detail S includes
only
S
Bonanza 35 series
airplanes. 35-604´•57
;i
\s_n
DETAIL T INDEX
LOCATION ELEVATOR CONTROL
POINTS(
LUBRICANT
INTERVAL
O
Elevator bell crank
(2)
SAE 20 or SAE 10W30
100 hrs
n
Elevator control push
SAE 20 or SAE 10W30 Detail T includes only serials CE-748. CE-n2 and after; CJ-149 and after: E-l 111. E´•1241 and after: and EA-1 and after.
pull
(2)
100 hrs
35-604-58
12-20-00
Rage
18
Oct7/83
A6
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
0.
50-590014
TS1222-5 50-590012
TS1222-3 TS1222-4
TS1222-8
50-590013 TS1171-1 TS1171-2 TSI 176-1
TS1176-10
TS1171-10
TS1176-2 UPPER FORWARD WING BOLT WRENCHES: TS1222-3 TS1222-5 50-590012 TS1222-4 TS12228
(FOR NAS152-37 (FOR MS20012-20 (FOR MS20012-20 (FOR MS20012-20 (FOR MS20012-20
BOLTS) AND 131790-1 AND 131790-1 AND 131790-1 AND 131790-1
BOLTS) BOLTS) BOLTS) BOLTS)
UPPER FORWARD WING NUT TORQUE WRENCH ADAPTERS: TS1171-2 TS1176-2 TS1176-10 TS1171-10
(PRIOR TO CE-928, CJ-156, D-10353, E-1758 AND EA-150) (PRIOR TO CE-928, CJ-156, D-13053, E-1758, AND EA-150) (CE-928 AND AFTER, CJ-156 AND AFTER, D-10353 AND AFTER, E-1758 AND AFTER, EA-150 AND AFTER) (CE-928 AND AFTER, CJ-156 AND AFTER, D-10353 AND AFTER, E-1758 AND AFTER, EA-150 AND AFTER)
LOWER FORWARD WING BOLT WRENCHES: TS1222-5
(CE-748, CE-772 AND AFTER; CJ-149
AND AFTER;
E-llll,
E-1241 AND AFTER; D-10097, D-10120 AND AFTER; EA-1 THRU EA-272 EXCEPT EA-242)
50-590012
(CE-748, CE-772
AND AFTER;
CJ-149 AND AFTER;
E-llll,
E-1241 AND AFTER; D-10097, D-10120 AND AFTER; EA-1 THRU EA-272 EXCEPT EA-242)
(CE-748, CE-772
TS1222-8
AND AFTER; CJ-149 AND AFTER; E-llll, E-1241 AND AFTER; D-10097, D-10120 AND AFTER; EA-1 THRU EA-272 EXCEPT EA-242) (CE-748, CE-772 AND AFTER; CJ-149 AND AFTER; E-llll,
TS1222-3
E-1241 AND AFTER; D-10097, D-10120 AND AFTER; EA-1 THRU EA-272 EXCEPT EA-242) (EA-242, EA-273 AND AFTER)
TS1222-4
Special Tools (Sheet Figure 2
1 of
36-17-15
4)
12-20-00
Page A8
19
Jan 18/84
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
LOWER FORWARD WING NUT TORQUE WRENCH ADAPTERS: TS1171-2
TS1176-2 TS1176-10
(PRIOR TO CE-928, CJ-156, E-1758, D-10353, AND EA-150) (PRIOR TO CE-928, CJ-156, E-1758, D-10353, AND EA-150) (CE-928 AND AFTER, CJ-156 AND AFTER, E-175B AND AFTER, 0-10353 AND AFTER, EA-150 THRU EA-272 EXCEPT EA-242)
50-590014
(EA-242,
EA-273 AND
AFTER)
UPPER AFT WING BOLT WRENCHES: 50-590012 TS1222-5 TS1222-4 TS1222-8
UPPER AFT WING NUT TORQUE WRENCH ADAPTERS: 50-590013 TS1171-1 TS1176-1
LOWER AFT WING BOLT WRENCHES: 50-590012 TS1222-5 TS1222-4 TS1222-8
LOWER AFT WING NUT TORQUE WRENCHES:
TS1171-1 TS1176-1 50-590013
35-590064-1 HOISTING SLING ASSEMBLY
35-590006 MAIN WHEEL JACK ADAPTER
MODEL 300 SERVICE JACK MAX. CAPACITY 5000 LBS
35-590009 THROTTLE RETAINING NUT WRENCH
Special Tools (Sheet
Figure
2 of
36-17-22
4)
2
12-20-00
Page
20
Jan 18/84
A8
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
SPECIAL TOOLS 35-590087
DIFFERENTIAL MECHANISM USED ON THE BONANZA 35 SERIES AIRPLANES ONLY 810-5 35660040 LH
810-5 35660040-1
RH
ELEVATOR CHECK FIXTURE USED ON MODEL SERIALS D-10097, D-10120 AND AFTER 810-3 35660040 LH
810-3 35660040-1 RH ELEVATOR CHECK FIXTURE USED ON MODEL SERIALS CE-748, CE-772 AND
35-590087-9 STOP
AFTER; CJ-149 AND AFTER, E-llll,
USED WITH 35-590087 ASSEMBLY WHEN
E-1241 AND AFTER; AND EA-1 AND AFTER
RIGGING THE MODEL SERIALS D-10097, D-10120 AND AFTER
C
810 35660043-2
TRIM TAB JIG
36-590015-1 TOW BAR
j
g
C~F 35-590021 TAIL TIE-DOWN SUPPORT ASSEMBLY
810 33524000
RUDDER CHECK FIXTURE
810-1 50590091
45-590074-7
AILERON TRAVEL GAGE
LANDING GEAR TENSION GAGE 36-17-16
Special
Tools (Sheet 3 of 4) figure 2
d
12-20-00 A8
Page
21
Jan 18/84
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
PREFLIGHT FUEL DRAIN TOOL ON 836TC AIRPLANES OR FUEL SELECTOR VALVE DRAIN TOOL ON A36TC AIRPLANES WITH KIT NO. 36-9008-15 INSTALLED
B36TC FUEL/OIL DRAIN ADAPTER PIN107B
36-17-~7 001
Special
Tools
(Sheet Figure 2
4 of
4)
"END"
12-20-00
Page 22 Aug 29/85
All
C H A PT E R
STANDARD PRACTICES
(AIRFRAME)
Ci~echcraft BONANZA SERIES MAINTENANCE MANUAL.
CHAPTER 20
STANDARD PRACTICES
AIRFRAME
TABLE OF CONTENTS
Subject
Page 20-00-00
Standard Practices
Airframe
1
20-01-00 1
Torque Wrenches 20-02-00 Electrostatic
Discharge Sensitivity
Electrostatic
Discharge Sensitivity
Electrostatic Discharge
Sensitivity
Description and Operation
1
Classification
1
Maintenance Practices
1
of ESDS
Removal/installation Equipment Handling of ESDS Components and Equipment Controlling Static Charge Buildup
3
Permanent Static Control Workstation
6
1
6
Portable Static Control Workstation and Dust Effects
8
ESDS
on Humidity Components Equipment................................ Packaging of ESDS Components and Equipment Marking of ESDS Components and Equipment Storage and Transit of ESDS Components and Equipment
8
and
10 11
12
20-03-00 Electrical
Bonding
Electrical
Bonding
Direct Electrical
Description
and
1
Operation
Methods
1
Bonding Bonding
1
of Tubes
1
1
Indirect Electrical
Electrical
Bonding
Electrical Power Returns
1
Recommended Materials
2
Electrical Bonding
Metal Surface
3
Maintenance Practices
Preparation
and Electrical
3
Bonding
3
Aluminum Surfaces
Corrosion-Resistant
(CRES)
6
Steel Surfaces
6
Stainless Steel and Titanium Surfaces Electrical
Typical
Bonding Examples
6
Blind Ground Stud
6
CRES Steel
or
Titanium Electrical
6
Bonding
7
Aluminum Electrical
Bonding Tubing Clamp to Bonding Jumper Electrical Bonding Bonding Jumper Across Tubing Clamp Electrical Bonding Typical Ground Stud Electrical Bonding Electrical Bonding of Ground Tabs
8 8 11 11
20-Contents
Page A14
1
Jun 20/91
Ci3eechcraft BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 20
STANDARD PRACtlCES
TABLE OF CONTENTS
AIRFRAME
(Continued) Page
Subject 20-04-00
Description and Operation
Control Cables and Pulleys
1 1
Recommended Materials Maintenance Practices
Control Cables and Pulleys
2
Control Cable
2
Control Cable
3
System Inspection Storage Cable Pulley Inspection
Control
3
20-05-00 1
Description and Operation
Bearings
1
Recommended Materials
1
Maintenance Practices
Bearings
Hydraulic
Press
Removal
Bearing Bearing
1
................................................i.......................................
1
Removal
Mechanical Press
2
Bearing Housing Inspection
Be~ring
Instailation Using Retaining Compound Bearing Installation By Staking
2 3
20-06-00 Tube and Hose Assemblies and
Tubing, Hose and Fittings
Fittings
Description and Operation
Maintenance Practices
Assembly
1 1
Removal of Tube and Hose Assemblies Hose
1
1
Installation
Tube Installation
2
Fitting Installation Nonpositioning Type Fitting Installation Pipe Thread Fitting Installation Tube Damage Limits
2
Fluid Line
2 2 4
20-07-00
Locking Devices
Self-Locking
Description
and
Operation
Slotted, Steel Locknuts (Prev~ailing Torque Lockwire and Cotter Pin Requirements Locking Devices
1 1
Nuts
Type)
Maintenance Practices
Lockwire Installation Procedures
1 1 1 1
Lockwire Hole
4
Lockwire
4
Alignment Twisting
Cotter Pin Installation
4
Keywashers (Tab and Cup Types) Installation Retaining Rings (Spirolox, Etc.) Installation Turnbuckle Lock Clip Installation
5 5
5
PO-Contents
Page 2 Jun 20/91
A14
C~eechcraft BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 20
STANDARD PRACTICES
TABLE OF CONTENTS
AIRFRAME
(Continued) Page
Subject 20-08-00
Airplane Finish Care
1
Description
1
Recommended Materials
3
Maintenance Practices
Airplane Finish Care
3
Airplane Finish Cleaning Environmental Fallout (Acid Rain) Waxing Airplane Finishes Placard Replacement
3 3
3 3
Urethane Paints Urethane Paint
Stripping
And
Pretreatment
4
Repair Procedures
Cleaning’Urethane (Wash)
4
Paint
Primer For Urethane Pairit
4
Urethane Primer
5
Topcoats Urethane Touch-Up Repair Painting Magnesium Paint Removal From Magnesium Surfaces Painting Magnesium Surfaces Special Procedures Propeller Blades Surfaces Susceptible to Mud and Spray
5
Urethane
5 5 5
6 7 7 7 7
Rubber Seals
Enclosed Areas
Battery
Subject
To
7
High Humidity
7
Box and Lid
7
Paint Free Areas
20-09-00 Corrosion
Description
1
Galvanic Corrosion
1
Recommended Materials
1
Corrosion
Maintenance Practices
1
Corrosion Control
1
Corrosion Protection
3
Aluminum Corrosion Removal
3
Removal of Corrosion from Aluminum Surfaces
3
Aluminum Corrosion Treatment
4
Corrosion Removal
4
Corrosion Treatment
4
Magnesium Magnesium
Steel Corrosion Removal
5
20-Contents
Page 3 A14
Jun 20/91
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 20
STANDARD PRACTICES
AIRFRAME
LIST OF PAGE EFFECTIVIP/
CHAPTER-SECTION-SUBJECT
P0-Effectivity
20-Contents
20-00-00
20-01-00
20-02-00
20-03-00
A22
PAGE
DATE
1
Nov 10/00
2
Nov 10/00
3
Nov 10/00
1
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2
Jun 20/91
3
Jun 20/91
1
Nov 10/00
2
Nov 10/00
1
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2
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3
Jun 20/91
4
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5
Jun 20/91
1
Jun 20(91
2
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3
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4
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5
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6
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7
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8
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2
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3
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4
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5
Jun 20/91
201EFFECTIVITY
Nov
10/0 Page
1
RaylIheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 20
STANDARD PRACTICES
AIRFRAME
LIS T OF PA GE EFFECTIVITY(CONTINU ED) CHA PTER-SECTION-SUBJEC T
20-04-00
20-05-00
20-06-00
20-07-00
Nov
10/Page
2
20-EFFECTIVITY
PAGE
DATE
6
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7
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8
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9
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10
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11
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12
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2
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3
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4
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4
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5
Jun 20/91
6
Jun 20/91
7
Jun 20/91
A22
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 20
STANDARD PRACTICES
AIRFRAME
LIST OF PAGE EFFECTIVIN (CONTINUED) CHA PTER-SECTION-SUBJECT 20-08-00
20-09-00
A22
PAGE
DATE
1
Jun 20/91
2
Jun 20/91
3
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4
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5
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6
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7
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3
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4
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5
Jun 20/91
20-EFFECTIVITY
Nov
10/0 Page
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
AIRFRAME
STANDARD PRACTICES
WARNING I W*RNING)
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 reconnection of any component, remove all identification tags. Check all associated systems for correct function prior to returning the airplane to service. practices used in maintaining the airplane in an airworthy condition. The information in this 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. This
chapter describes
the standard maintenance
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 Bolt
Torque Information
unit/subject contains the general information for installation of torqued fasteners. It has information adapters and torque charts showing the torque of different types of nuts and bolts.
on
the
use
of torque
20-02-00
Electrostatic
Discharge Sensitivity
Information
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- Electrical
This
unit/subject
Bonding
contains the
Information
general
information for installation of electrical
wiring grounding,
tube
grounding
and
electrical power returns. 20-04-00
This
unit/subject
20-05-00This
by pound
contains the
Bearing
unit/subject
the
Pulley Information
general
information for maintenance and
of control cables and
contains the
general
information for installation and removal of
of the
Tubing
pulleys.
Information
bearings. The by use
removal is described of the
retaining
com-
Information
unit/subject contains the general
information for maintenance of hoses,
identified, but the information is basic and applies
~p
inspection
use hydraulic and mechanical press method. The installation is described and the staking method.
20-06-00-
This
Control Cable and
to most
tubing
and
fittings. Components are
not
applications.
20-00-00
NovP:9~
Ralkheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 20-07-00
Fastener
Locking
Information
This
unit/subject contains the general information for the installation of washers, retaining rings and turnbuckle locking clips. 20-08-00-
This
Airplane
cotter
pins, lockwire,
tab and cup type
key-
Finish Information
unit/subject contains application.
the
general information for maintenance of
the finishes used
on
the
airplane
and
paint
removal and
20-09-00- Corrosion Removal and Control Information
This
unit/subject
Page
contains the
general information for the control,
20-00-00
treatment and removal of corrosion.
na?
ci3~eechcraft BONANZA SERIES MAINTENANCE MANUAL
TORQUE WRENCHES
(FIGURES
1 AND
Formula for increased effective
2) Y
Threads of nuts and bolts to be
135
specified. The
loss of normal friction
by
10
1350
1.5
11.5
117.39
must be
torqued
10
clean and free of all lubricants unless otherwise tion may result in
x
length:
contamina-
overtorquing.
Y
117 inch-lbs.
NOTE
A measurable to initiate the
Y
torque may of
turning
Formula for decreased effective
be exercised
Torque wrenches should before they are used.
be
some
10 Y
setting. For example; a requires 20 inch-pounds
proper torque of
force
torqued
to at 20
should
freely
turn
must
If
the
100
inch-pounds
desired
to
This
torque.
method compensates for the friction of or fastener.
an
1),
ure
increased
adapter
compensation or lost leverage.
figure
a
must
ment must be
To
is used with
calculated
the
between the center of the bolt and the scale attach-
torque require-
ing point. For example, if the specified torque is 200 inch-pounds and the distance is 15 inches, a pull of 13.3 pounds must be applied.
made
for
before the final
torquing. actually give
T L
x
L or
Y E
When
Y L
E EXAMPLE:
(Desired) Torque Apparent (Indicated) Torque Effective Lever Length Effective Length of Extension
Actual
T
135 inch-lbs.
Y
Unknown
L
10.0 inches
E
1.5 inches
a
torque wrench adapter is used, the length
of the
adapter
flex
"T" handle wrench and
or
must be added to the a
length
of the
value calculated for
particular combination. The following example in finding a desired value.
that
cal T=
pounds (scale reading)
torque wrench (Figbe
the desired torque which will specified, use the following formula:
LEGEND:
torque wrench is
a
required to obtain the specified torque, divide the torque in inch-pounds by the distance in inches
A new
Torque Formula:
159 inch-lbs.
To calculate the force in
the torque Basic
8.5
1.5
method of
the locknut
When
158.82
1350
not available, an acceptable checking the torque is to attach a spring scale (Figure 2) to a conventional flex or "T" handle inserted into an adapter. Force should be applied in direction perpendicular to an imaginary line a extending from the center of the bolt through the spring scale attaching point.
be
inch-pounds above the
indicate
10
8T01039
desired torque. If the desired torque is 80 inch-pounds, the torque wrench achieve
x
locknuts.
This initial torque must then be added to the desired torque to attain the locknut that
135
required
length:
is
a
typi-
Effective length of flex or "T" ................12 inches Handle wrench Length of adapter ...............3 inches ..................1 5 inches Total length Desired torque on bolt ........2000 inch-lbs.
(2000 inch-lbs.)
(15 inches)
133.3 Ibs.
BT01038
20-01-00
Page A14
1
Jun 20/91
C~3eechrraft BONANZA SERIES MAINTENANCE MANUAL
TORQUE WRENCH DRIVE CENTERLINE
II I i
C-
ADAPTER DRIVE CENTERLINE
HANDGRIP CENTERLINE
(PREDETERMINED)
200001 i
O I
Torque Wrench and Adapter
Figure
1
20-01-00 Page 2
Jun 20/91
A14
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
(LB)
TORQUE
(IN-LBS.) 90’
OTAL LENGTH 2000-017-02
Computing Torque with Figure 2
A14
a
Spring Scale 20-01-00 Page 3 Jun 20/91
C~3eechcraft BONANZA SERIES MAINTENANCE MANUAL
CHART 1 FINE THREAD
SERIES, CLASS 3, CADMIUM PLATED (EXCEPT AS NOTED)
AND NONLUBRICATED
Maximum Allowable
Torque Limits Recommended for Installation
MS21042
Dry-Film
AN310
Lub Nut
Nuts
12-15
5/32-36 3/1 6-32 1/4-28 5/1 6-24 3/8-24 7/1 6-20 1/2-20 9/1 6-18
1* 15-19 37-47
20-25 50-70 100-140
160-190 450-500 480-690 800-1 000
56-78 72-1 08
1 1 1
5/8-18 3/4-16
2300-2500
1--1---
7/8-14
2500-3000
1---
*This is
1100-1300
MS20364
MS21245
AN320
1 7-9 12-15
30-40 60-85 95-110 1 270-300 1 290-410 1 480-600 660-780 13001500
Lub Nut
1
1 20
1
1 40
1 1 1
1100 1 225 1 390
1
Lub Nut
Nuts
1*
1 840
30 70 135 200
MS21245
MS20364 AN320
Dry-Film
AN310
Dry-Film
Nuts
Column 4
MS2 i 042
MS20365
Dry-Film Lub Nut
Nuts
1 12 25 60 140 240
1
1 500
210-230 310-430 485-605 1090-
1100
1
1 660
415
1600 2400 5000
1 1 1
1 960 11400 1 3000
660 1060 2500
1800-
1250 1640-
7000
1
1 4200
3740
2400
2100
thread (.1640-32) with recommended torque tightening torque of 14 inch-pounds.
a coarse
allowable
Column 3
Column 2
Column 1 MS20365
Size
Tightening
Torque (Inch-Pounds)
(Inch-Pounds)
limits of 9-11
inch-pounds
and
a
maximum
BT03021
20-01-00 4 Jun 20/91
Page
A14
’13eechcraft BONANZA SERIES MAINTENANCE MANUAL
CHART 2
TORQUING COARSE THREADED BOLTS LOADED IN SMEAR
Size
9-32 10-24
1/4-20 5/1 6-18 3/8-16 7/16 1/2-13 9/1 6-12 5/8-11 3/4-10 7/8-9 1-8 1 1
1/8-8 1/4-8
The above values
Torque Limits REcommended
Maximum Allowable
(Inch-Pounds)
Torque (Inch-Pounds)
AN365
AN364
8 AN310
6 AN320
Nuts
Nuts
Nuts
12-15 20-25 40-50 80-90 160-185 235-255 400-480 500-700 700-900 1150-1600 2200-3000 3700-5000 5500-6500 6500-8000
7-9 12-15 25-30 48-55 95-110 140-155 240-290
20 35 75 160 275 475
300-420 420-540 700-950 1300-1800 2200-3000 3300-4000 4000-5000
1100 1500 2500 4600 7600 12000 46000
apply
to Class 3
AN365 AN310
880
AN364 6 AN320 Nuts
12 21 45
100 170 280
520 650 900 1500 2700 4500 7200 1000
threads, cadmium plated and nonlubricated.
8T03022
20-01-00
Page A14
5
Jun 20/91
Cil)eechcraft BONANZA SERIES MAINTENANCE MANUAL
charge, while materials at the bottom of the 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
ELECTROSTATIC DISCHARGE SENSITIVITY
static
DESCRIPTION AND OPERATION
list
Some types of electronic components are easily damaged by electrostatic discharge (ESD), and
require special handling ESD is
a
release
and
of stored
storage procedures. electrostatic charge
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. which has been
are
constant, and will vary with ambient conditions. A
greater possibility of ESD exists when the positions of listed items in Table 1 are farther apart. For
example,
individual
an
using his/her
hands to
pick
up a PVC pipe has more potential for producing ESD than does an aluminum part contacting a steel
pa’t. Table 2 identifies
some
typical electrostatic charge can produce the electro-
levels and the actions that static
charge.
ELECTROSTA TIC DISCHARGE SENSITIVITY CLASSIFICA TION Three levels of
sensitivity classification are estabdischarge sensitivity devices.
lished for electrostatic Personnel
who
remove, inspect, test or install equipment containing ESDS combe aware of the possibility of ESD
instruments and must
ponents damage,
and should handle ESDS components in procedures covered in this chap-
accordance with ter.
Proper procedures
and
policies for the handling equipment should be
of ESDS components and adhered to for the following Control of ESD
reasons:
damage,
Class 1
from time of compo-
nent manufacture to time of actual
installation,
must be verifiable and must be maintained use
of established
Classification is used to aid the manufacturer
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:
Class 2
Sensitivity Sensitivity
range is from 0 to 1,999 volts. range is from 2,000 to 3,999
volts.
by
industry standards.
Class 3
policy dictates that all personnel procedures to prevent damage ESDS components and equipment.
Established
Sensitivity range
is from 4,000 to 15,999
volts.
follow certain to
Interacting aware
areas
of their
of
responsibility
obligation
must
be
to maintain proper
ESD-controlled environments. Table 1
REMOVAL/INSTALLA TION
lists several materials and the associated
electrostatic
charge polarity
and
OF ESDS
EQUIPMENT
magnitude for
each. Materials at the top of the list are capable of producing the greatest amount of positive electro-
A14
ELECTROSTATIC DISCHARGE SENSITIVITY MAINTENANCE PRACTICES
Observe the or
installing
following procedures when removing equipment at the airplane:
ESDS
20-02-00 Page 1 Jun 20/91
L~3eechcraft BONANZA SERIES MAINTENANCE MANUAL
TABLE 1 MATERIAL POLARITY
CHARGE MATERIALS
(Relative Magnitude and
Polarity)
Air
Pos~ive
Human Hands
Positive
Asbestos Rabbit Fur Glass Mica Human Hair
Positive Positive Positive Positive
Positive Positive
Nylon Wool
Positive Positive
Fur Lead Silk Aluminum
Positive Positive Positive
Paper
Positive
Cotton Steel Wood Amber
--Neutral--
Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative Negative
................._
Sealing
Wax Hard Rubber
................._
Nickel, Copper Brass, Silver Gold, Platinum
................._
Sulfur
Acetate, Rayon
Polyester Celluloid/ Orlon/ Saran/ Polyurethane Polyethylene Polypropylene PVC (Vinyl) KEL-F (CTFE)
i.....
SILICON
TEFLON/ BT01D30
during CAUTION
tems
power-on to
prevent
maintenance
Tools with should
plastic
not
be
or
used
devices. These tools
charge which charge during Insulated
20-02-00 Page 2 Jun 20/91
insulated handles
does
ESDS
around
can
carry
a
static
readily disthe grounding process, tools should be used only not
of aircraft sysshock to
testing
electrical
personnel performing the
tests.
Some circuit board assemblies may be
protected covers
by
charge. Use tion
to
plastic store
can a
covers. an
These
electrostatic
static control work sta-
neutralize
any
electrostatic
A14
BONANZA SERIES MAINTENANCE MANUAL
TABLE 2
TYPICAL ELECTROSTATIC VOLTAGES
ACTIONS OF PERSONS
Walking Walking
across
MOST COMMON
HIGHEST
READING (VOLTS)
READING (VOLTS)
12,000 4,000 1,800 1,500
39,000 13,000 18,000 20,000 7,000
carpet
vinyl tile floor Seated in polyurethane foam chair Picking up poly bag Inserting paperwork into vinyl envelopes across
Data based
on
ambient relative
800
humidity
15% to 36%
BT01031
charge on the covers before touching a printed circuit board. Store the covers
safe
a
from
distance
the
work
When
a.
using test equipment, discharge all test ground prior to connection to the ESDS cir-
cult under test, b.
a portable static control work station removing ESDS circuit boards from card cages and enclosures at the airplane.
when
Place removed ESDS
equipment
on
the work
station static
dissipative work surface before openstatic shielding container holding the
ing the replacement ESDS equipment, d, its
Just prior to engaging mating receptacle, touch
the
receptacle charge on the e.
Maintain
d. Always opening any Avoid
e.
Use
c.
a
cable connector with
the connector shell to
shell to neutralize any electrostatic connector or the installer’s body.
protective coverings
on
stored ESDS
equipment.
to’
pins
HANDLING OF ESDS COMPONENTS AND
All
personnel handling ESDS components and equipment should receive instruction in the proper handling of such items. Observe the following handling rules to prevent damage to ESDS components and equipment: Keep
ESDS
components
protective packaging
and until
equipment opened at a
static control work station. b.
place
Before the
unsealing packages on
control work station.
A14
ESD
protective packages,~
the work surface of
a
static
wear
ESD
grounding
a
wrist
strap when
protective package.
touching circuit components or connechandling ESDS components or equip-
when
f.
Never
place any ESDS component, before or assembly, on a nonconductive surface or in a container not specifically designed for storage of after
ESDS devices. g. with
Protect
h.
ESDS
components
protective containers,
pin-shorting
and
equipment and/or
conductive caps,
devices.
Store and transport ESDS components and containers. Seal all ESD warning label
equipment in ESD protective protective containers with an prior to shipment. i.
EQUIP~WENT
a.
remove
me"t.
ment
inside ESD
pressure air nozzles to
use
printed circuit boards. Rapid movement of air, combined with airborne dust particles, can create an electrostatic charge that will destroy ESDS components.
area.
leads to
Do not
c.
dust from ESDS
Place all loose ESDS components and equipinto ESD protective containers BEFORE
removing
a
grounding
wrist strap.
j. Keep the work station free of any material required to accomplish the assigned task. k.
Follow established ESD
protection
not
rules and
p’ocedures. I´• Always use a static control work station, either permanent or portable, when removing ESDS components and equipment from protective packaging.
Use only grounded, electrically isolated, and m. temperature controlled soldering irons that have been rated for use with ESDS components and
equipment. tive
or
Use
static
equipment,
only hand tools that have conducdissipative handles or grips. Test
such
as
scopes and meters, must be 20-02-00 Page 3 Jun 20/91
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
11
7
2
10~
9
1~1 STATIC WORK
CONTRDLLED STATION
1
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. Apol*lae
Permanent Static Control Work Station
Figure 1 20-02-00
Page
4
Jun 20/91
A14
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
,19
1
dl
3
V2
i. ALLIGATOR CLIP TO
RELIABLE GROUND CONNECTION 2. SNUG-TO-SKIN PERSONNEL
WRIST STRAP 3. STATIC DISSIPATIVE
WORK SURFACE
AP014~89
Portable Static Control Work Station
Figure
2
20-02-00
Page A14
5
Jun 20/91
Cj~eechcraR BONANZA SERIES MAINTENANCE MANUAL
rated for
use
around ESDS
components and equip-
exposing ESDS components and equiplarge electromagnetic or electrostatic fields transformers or transmitting antennas.
Avoid
n.
ment to
such
as
A
Four basic These
following
CAUTION
techniques
are
Never
in ESD control.
employed
Minimize
charge. sonnel
human
is
body
a
good
The
electrical conductor and for the
body grounding device such as a wrist or ankle strap. Always wear a grounding wrist strap when opening ESD containers or handling exposed ESDS components and equipment. reason
electrostatic
dissipated by skin
c.
charges
contact
on
with
NEUTRALIZE THE CHARGE
can
a
Nonconductors,
polystyrene coffee cups, plastic bags, and some clothing develop electrostatic charges that cannot be neutralized by grounding, lonized air flow will neutralize an electrostatic charge on a nonconductor as long as the ionized air blower puts out both positive and negative ions. such
d.
as
MINIMIZE
THE
EFFECTS
rounding ESDS components be free of electrostatic fields static
shielding
OF
ELECTRO-
The immediate environment
STATIC FIELDS
to
mlnlmlze
and or
equipment
sur-
must
must have suitable
induced effects from
electrostatic fields.
Under certain conditions, pera grounding wrist strap
using
may need to
a
use
a
moisture enhancer to
grounding ankle strap to dissipate body charge buildup. Wear cotton clothing instead of wool or synthetics. Use an ionized air blower to dissipate charges from nonconductive items. DRAIN OFF THE CHARGE TO GROUND
wrist strap
The strap must be in contact with the wearer’s skin to adequately dissipate any electrostatic
charge buildup by using conductive or dissipative flooring and static-dissipative work
surfaces. Wear leather shoes, cotton socks, and
grounding
a
wear
clothing.
over
static
be
con-
I C~UIION(
are:
MINIMIZE THE CHARGE BUILDUP
that
on
items:
electrostatic
b.
charges
permanent static control work station consists of
the
CONTROLLING STATIC CHARGE BUILDUP
a.
electrostatic
diverting, to ground, objects.
ductive
ment.
resistance
skin
lotion-type provide a
low-
between
the
connection
wrist and the wrist strap.
a´•
GROUNDING WRIST STRAP
Each person and
ESDS
equipment components grounding wrist strap to dissipate bodily electrostatic charges. The wrist strap must fit firm against the skin and release quickly in case of an emergency. The wrist strap incorporates a 1 megohm current-limiting resistor, in series with the ground cord, to protect the wearer from electrical
that
handles
must wear
a
shock hazards. SURFACE STATIC-DISSIPATIVE WORK b. Conductive mats on the work bench surface are designed to remove electrostatic charges from conductive items c.
placed
on
the mat.
Conductive floor-
CONDUCTIVE FLOORING
ing is used required. To
when
additional
control
maintain total control
of
over
ESD
ESD,
is
use
conductive chairs, a grounding heel strap, and conductive shoes. Conductive flooring in ESD control areas must
tive
be free of all
wax or
other nonconduc-
coatings.
HARD GROUND CONNECTION Grounding of the static control work station is accomplished through one or more copper ground rods driven
d.
PERMANENT STA TIC CONTROL
into moist earth to
WORKSTATION
low
(FIGURE I)
ground. All work station connections to ground are made through a one megohm resistor to protect work station personnel from electrical shock hazards by limiting current flow to ground.
A static control work station
handling
provides for static-free equipment by
of ESDS components and
20-02-00 Page 6 Jun 20/91
resistance
a
depth
path
from
sufficient to the
work
provide station
a
to
A14
BONANZA SERIES MAINTENANCE MANUAL
f.
NOTE Some
building grounds
checked to
ensure
from
rent looping grounds.
need
that there is other
to
be
and if
no cur-
nearby
external and not static.
e.
IONIZED
AIR
provides negative ions over blower tralize
a
The
BLOWER
constant flow of
CONDUCTIVE CONTAINERS
ESDS devices
transported in approved containers to prevent ESD damage. These 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 must be
of current is
source
Chairs used
protected work stations must be conductive, padded, must be covered with static dissipa-
tive material.
g.
Ensure that the
STATIC DISSIPATIVE SEATING
at ESD
ionized
positive
air
and
the work station surface to neunonconductive on electrostatic charges
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
work station. Conductive boxes, kit trays, and similar types of approved containers provide complete
charge accumulators
A grounding h. GROUNDING HEEL STRAP 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 foot-
possible to eliminate all (styrofoa, plastic, etc.)
static
work area, the ionized air blower is used to provide additional protection by flooding the work area with balanced negativelpositive ionized air. Static charge accumulators from
a
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 inadvertent buildup. should
always
be
ESD
protection
to
ESDS components and
equip-
ment while in transit.
wear to
make contact with
ductive
flooring.
used in combination
provide
a
conductive mat
or con-
grounding heel strap can be with a grounding wrist strap to
The
maximum ESD
protection.
CLOTHING ANTISTATIC/CONDUCTIVE electrostatic of clothing generate Many types i.
CAUTION THIS EQUIPMENT CONTAINS DEVICES SENSITIVE TO DAMAGE BY ELECTROSTATIC DISCHARGE (ESD) USE ESD PRECAUTIONARY PROCEDURES WHEN TOUCHING, REMOVING, OR INSERTING PARTS OR ASSEMBLIES
C
Equipment Enclosure Cautionary Placards Figure 3 20-02-00 Page 7 A14
Jun 20/91
Cj~echcraR BONANZA SERIES MAINTENANCE MANUAL
charges. To remove some of this buildup, work stapersonnel 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
tion
devices,
as
these
fabrics
retain
electrostatic
of emergency. The wrist strap incorporates a megohm current-limiting resistor, in series with
case
1
the
ground cord,
to
b´•
designed
static
WORKSTATION
items contact the mat. c.
provides for handling of ESDS components and equipment during maintenance operations at the airplane. The typical portable work station is available as a field service kit that is used to dissipate electrostatic charges before the charges can damage ESDS components and equipment. portable
static control work station
static-free
static control work station
typical portable following
A
sists of the
con-
Each person GROUNDING WRIST STRAP who handles ESDS components and equipment
grounding wrist strap to dissipate bodcharges. The wrist strap must fit against the skin and should release quickly in
must wear a
electrostatic
firm
to remove electro-
HARD GROUND CONNECTION
Ground the
portable work station to the airframe or to a common ground as shown in Figure 2. All portable work station connections to ground are made through 1 megohm current-limiting resistors to protect maintenance personnel from electrical shock hazards. HUMIDITY AND DUST EFFECTS ON ESDS COMPONENTS AND EQUIPMENT
items:
a.
ily
charges
A
from conductive items when those
PORTABLE STA TIC CONTROL
A
from electri-
integral part of the portable
an
work station, and is
(FIGURE 2)
wearer
STATIC-DISSIPATIVE WORK SURFACE
conductive mat is
charges.
protect the
,,I shock hazards.
Humidity is a humidity,
the
factor in the control of ESD. The lower the
greater the chance of damage
to
ESDS components and equipment. Humidity at the work station should be maintained between 30 and 65 percent.
CAUTION ELECTROSTATIC DISCHARGE SENSITIVE ELECTRONIC DEVICES SPECIAL HANDLING REQUIRED AP014191
ESDS Drawing Note
Figure 20-02-00 Page 8 Jun 20/91
4
A14
~eechcraR BONANZA SERIES MAINTENANCE MANUAL
RS-471
MIL-STD-1285 ESD SYMBOL
ESD SYMBOL
MIL-STD-129H ESD SYMBOL AP014193
ESDS Symbols
Figure
A14
5
20-02-00 Page 9 Jun 20/91
Cil)eechcraR BONANZA SERIES
MAINTENANCE MANUAL
Repair
of ESDS circuit boards, including replacecomponents, should be performed in
ment of ESDS a
ESD protective erwise defined
packaging requirements, unless othby specification, shall conform to the
following:
dust-free environment,
Class 1
PACKAGING OF ESDS COMPONENTS AND
EQUIPMENT All ESDS components and equipment require special ESD protective packaging. Seal all ESDS pack-
ages with in
Figures
appropriate cautionary label
an
3
through
as
Package
in
multi-layer
conductive
type bags consisting of an inner and outer layer of antistatic (surface resistivity of 109 to 10’4 ohms per square inch) or static dissipative (surface resistivity of 10" to 109 ohms per square inch) material with a middle layer of conductive material (surface resistivity of 10 ohms or less).
shown
8.
Class 2
Package in a static dissipative matepossessing a surface resistivity of 105 to 109 ohms per square inch. Materials specified
rial
i ,,,,,-t Do not
for Class 1 may also be used.
clips or staples when sealing any ESDS package. Do
not
use
use
Class 3
Package
possessing
carbon-filled, conductive
a
surface
in
an
antistatic
resistivity
material of 109 to 1014
ohms per square inch.
bags. Remove ESDS components and equipment from protective, static-shielded containers
ONLY at
a
static control
work station after
attaching a grounding wrist strap and verifying that ESD producing items are not on the static dissipative work surface.
Place all ESDS devices in
approved static shielding in shipper’s normal exterior containers. Use antistatic cushioning or fill materials. Do not use static generating materials, such as polyethylene, styrofoam, or paper. containers before
Antistatic
packing
packaging
is
generally pink
color. The material differs from
CAUTION
or
common
blue in
plastic
in
ATTENTION
SENSITIVE ELECTRONIC DEVICES. SPECIAL HANDLING REQUIRED, DO NOT OPEN EXCEPT AT AN APPROVE WORK STATION.
CONTENTS STATIC SENSITIVE HANDLING PRECAUTIONS
(PREFERRED)
REQUIRED
CONTENTS
(ACCEPTABLE) APOld192
ESD Unit Container Notice
Figure 6 20-02-00
Page 10 Jun 20/91
A14
Ci~echcraR BONANZA SERIES MAINTENANCE MANUAL
Cd ATTENTION CONTENTS STATIC SENSITIVE HANDLING PRECAUTIONS
REQUIRED AP01419d
Protective Container Notice
Figure 7
positions or a hand inside of a triangle with an angling bar across the triangle) are yellow on a black background or black on a yellow background.
incorporated into the manufacturing process. This during NOT provide static shieldDOES of type packaging ing, and is generally used to package instruction that
an
antistatic compound is the
material
sheets, data sheets, and other non-ESDS materials
prior
to introduction into
All non-ESDS items, that
a
static-free environment. enter an ESD work
are to
station, require repackaging in antistatic materials.
Mark unit containers with the ESDS caution label the outside of the ers
shielding packaging differs from packaging, in that it has the ability to
Conductive static antistatic shield static
devices,
contained
within,
from
external
charges. Conductive static shielding packagbags and rigid con-
is available in the form of
ing
with
Apply
an
package.
ESD caution label
marks
directly
board, assembly
Figure 8. printed circuit
shown in
equipment enclosure,
or
door that would expose ESDS devices, if removed. Mark appropriately using decal transfer,
access
stencil, silk screen,
tainers.
as
to each ESDS
cover,
on
Mark exterior contain-
or
any other method meeting
permanent legibility requirements. MARKING OF ESDS COMPONENTS AND
EQUIPMENT All
ESDS components and appropriately with
marked
shown in
Figure
equipment should ESDS symbol
an
5.
be as
Display
ESDS
that
attached to circuit boards should contrast
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" in diameter. ESDS symbols are
with the circuit board base color. Enclosures that contain ESDS circuit boards should be identified
NOTE ESDS
pointing
symbols
(circle
with
into the circle from
arrows
equidistant
bright orange paint
on
by
the outer face of the enclo-
sure.
20-02-00
Page A14
11
Jun 20/91
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
STORAGE AND TRANSIT OF ESDS
against
COMPONENTS AND EQUIPMENT
controlled work stations.
ESD
ESDS CAUTION
NEVER
preparing
equipment
transfer
in
conductive
static-
Shipping information and other instructions, accompanying ESDprotected packages, shall be contained in anti-static
materials when
ESDS devices for
and
dissipative,
use
all assemblies and
packages, which have been properly in protective packages, require proper
storage
ordinary plastic containers packing transporting ESDS components or equipment.
When
at static
enclosed
1~--11´•´• t or
through appropriate handling
or
static-free containers.
materials. ESDS components, that
shipment, ensure protected
have been
are
received in
damaged or opened packing containers, are not acceptable, and should be returned for replacement.
CAUTION SENSITIVE DO
NOT
SHIP
ELECTRONIC OR
STORE
DEVICES
NEAR
ELECTROSTITIC.ELECTROnAGNETIC, NAGNETIC, OR RADIOACTIVE
STRONG
FIELDS.
AP014195
In-House
20-02-00 Page 12 Jun 20/91
Storage Container Figure 8
Label
A14
Ci~eechcraft BONANZA SERIES MAINTENANCE MANUAL
ELECTRICAL BONDING
INDIRECT ELECTRICAL BONDING
DESCRIPTION AND
OPERATION The
When direct electrical
following terms description:
tem
defined
are
used in the sys-
as
ELECTRICAL BOND: A reliable electrical
con-
nection between conductive parts which provides electrical
conductivity.
ELECTRICAL BONDING: Conductive parts electrically bonded when they
are
considered
interconnected
mechanically common
are
maintain
a
potential.
electrical
conducting connection, whether accidental, by which an electrical
GROUND: A intentional
or
current or
equipment
a common
to
and
uses
is connected to maintain
I or
Whether
direct
must reflect
or
high
are
commonly
indirect,
all
surface
This includes but is not limited to, all films such as anodize, grease, oil, paint, other finishes with
resistance
protective lacquer, or properties. Once
high bonding surface is cleaned, and the necessary protective coatings applied, the compo-
the electrical
nent
is
installed and
formed to
the wire should not be bent or as this has a tendency to the
jumper and reduce its "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.
bonding
electrical
the
performed on bonding jump-
maintenance standards to main-
integrity. Many times, an illprepared 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.
tain
maintenance is
effectiveness.
used.
electrical
CAUTION --II´•´•
around these flexible
weaken
Bolts, rivets, conductive laminates, flashing
bonding jumpers
a
damaged
of electrical
mechanical methods to attach the electrical conducand
Indirect
always as short as single jumper. Two bonding 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 joi"ts. possible jumpers
ers,
tors.
imprac-
and washers. The connection is
bonding; types Both are accomplished by using
direct and indirect.
are
used.
nection. These flexible metal straps are attached to a prepared metal surface using screws, studs, nuts
electrical potential.
basic
two
are
bonding is most commonly accomplished by using bonding jumpers to make the desired con-
Anytime
are
methods
electrical
ELECTRICAL BONDING METHODS There
bonding
tical, indirect bonding methods
a
resistance check is
verify continuity
perof the electrical bond.
Indirect electrical
bonding
is also used to connect
shielding terminals to a braiding attaches to the electrical connectors with clamps and shields the airplane wi’e harness for its entire length.
the
airplane ground. The
wire harness
tubular
ELECTRICAL BONDING OF TUBES All metallic tubes that carry
other fluids,
cally static
including gases,
petroleum products must have
a
or
mechani-
connection to the ground plane for dissipation. Plumbing sections must be elec-
secure
trically
bonded to each other to eliminate a potential charge on the individual segments. Conti-
electrical
plumbing segments is achieved 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. nuity
between the
with electrical DIRECT ELECTRICAL BONDING
Direct
are
bonds
electrical
metal-to-metal
joints.
frequently assembly,
used the
for
joints
conductive film that prevents corbonding surface. Most direct electrical
treated with
rosion of the
are
Before
a
bonds involve the installation of components minum.
on
alu-
ELECTRICAL POWER RETURNS Electrical power returns should be direct with the possible path from the operating equip-
shortest
20-03-00 Page 1 A14
Jun 20/91
Cil)eechcraR BONANZA SERIES MAINTENANCE MANUAL
CHART 1
RECOMMENDED MATERIALS SPECIFICATION
MATERIAL
1.
PRODUCT
TT-M-261
Cleaner
VENDOR
Obtain
Methyl Ethyl
locally
Ketone 2.
Alodine 1200
Coating
Amchem Products Inc., Spring Garden St.,
Ambler, PA 19002 3.
Conformal
Conothane CE-1155
MIL-I-46058
Coating
Conap Inc., 1405 Buffalo St., Olean, NY 14706
4.
5.
MIL-P-2337
Primer
MIL-S-8802
Sealant
Advanced
1-lv-12/1-1H-7
Type
1
PR1422
Coatings
8 Chemicals, 4343 Temple
City Blvd.,
Temple City,
CA 91780
Products Research and Chemical
Corp.,
5426 San Fernando Rd., Glendale, CA 91203 6.
0-T-634
Cleaner
1,1,1, Trichlorothane
BF Goodrich,
500 S. Main Street, Akron, OH 44318
BT03019
ground when practical. Current return leads 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 conment to
4 AWG
or
nection. A maximum of four wire terminals may be on an individual grounding stud. If two or
installed
grounded to an individual stud, each a mechanically sound connection and meet applicable maximum resistance values. Component case electrical bonding and current more
wires are
wire must form
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
right configuration
a
component, and
is used
ensure
the
during installation.
20-03-00 Page 2 Jun 20/91
vendor
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
of
or
the
mechanic to determine the current
applicable specification prior
to
usage of the product listed. This can be done by contacting the vendor of the product to be used.
The recommended materials listed in Chart 1 or
cations. GENERIC OR LOCALLY MANUFACTURED
revision
RECOMMENDED MA TERIALS
meeting federal, military
provided for reference only and are not specifiearly required by Beech Aircraft 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 Beech Aircraft Corporation, by the vendor or compliance to the applicable specifiare
as
specifications
A14
ci~echcraft BONANZA SERIES MAINTENANCE MANUAL
2000-610-32
Use of Stainless Steel Wire Brush On Aluminum (With Pilot)
Figure
1
provide
MAINTENANCE
ELECTRICAL BONDING
tion
PRACTICES
a
to
means
prevent
of
adequate
a
concentration
ventila-
of that
harmful vapors. The procedures follow describe preparation of the vari-
METAL SURFACE PREPARATION AND
ous
ELECTRICAL BONDING
cal
preparation for electrical bonding requires 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.
types of bonding.
metal surfaces for electri-
Surface the
ALUMINUM SURFACES
Remove any nonsoluble protective finishes or a. corrosion from an area slightly larger than the area to be bonded
(minimum of fine sandpaper.
.25
inch) by sanding with
NOTE Do not
use
sandpaper. or
emery cloth Use
or
NOTE
iron oxide
aluminum oxide
silicon carbide
only sandpaper.
A stainless steel wire brush with
may be used to clean small ure
a
areas
pilot (Fig-
1).
WARNING
b. When with
working solvents,
in
an
enclosed
cleaners
or
area
finishes,
Clean
MEK
the
bonding
(1, Chart 1) to
surface
remove
thoroughly
any oils
or
with
contami-
nants.
20-03-00 A14
Page 3 Jun 20/91
Ci;)eechcraR BONANZA SERIES MAINTENANCE MANUAL
BLIND GROUNDING STUD
NUT
LOCK
WASHER
WASHER
TERMINAL (LIMIT TO 4)
STRUCTURE 2000-610-41
Typical Blind Ground Stud Figure 2 NOTE Do not touch the
e.
bonding surface
with
dry.
acids may prevent adhesion of the alodine film or cause corrosion, bare hands.
c.
Body
oils
area
or
Shake the alodine solution
ously just prior to application, bonding surface with a clean sponge, brush
or
After the alodine has
bonding surface. Care must be taken not to damage the alodine coating as it is still soft when bonding.
(2, Chart 1) vigorapply to the Scotch Brite pad,
NOTE The
cloth.
bonding
bled within ment.
surfaces must be
one
Once
assem-
hour of alodine treat-
dried,
softened before it
NOTE
alodine can
be
must
be
effectively
bonding. If more than an hour passed, soften the alodine by applying wet alodine to the dried surused in
an
has
amber color. If the solution is coffee colored, it has been contaminated.
face.
cleaning procedure if conalodine has been applied to taminated the bonding surface. Repeat
rinse the
not cover the
then
The alodine solution should have
changed color,
with clean, deionized water and gently wipe Touch up any areas where the alodine does
the
f.
Install
the
component
being
electrically
bonded. d.
Keep
the treated
area
wet with
alodine for color
approximately 3 to 5 minutes until a yellow develops. Should the alodine not change color, it is an indication that the surface was not properly cleaned.
g. Seal around the edges of the electrical bond with conformal coat per MIL-I-46058 (3, Chart 1). If
assembly was originally protected by primer, prime the assembly with primer (4, Chart 1) and reapply the original finish as required.
the
20-03-00
Page
4
Jun 20/91
A14
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
CHART 1 HARDWARE USED WITH GROUND STUDS
Structure
Screw,
bolt
Lock-Nut
Plain
Washer
Washer
Washer
Lock Washer
Lock Washer
Nut
A
B
C&D
E
F
MS35338
MS35338
Tinned
Copper
Terminal and
Alum.
Aluminum
Cad.
Cad.
Alloys
Plated
Plated
Steel
Steel
Alloy
Jumper
Alum.
Cad.
Cad.
Cad.
Alloy
Plated
Plated
Plated
Steel
Steel
Steel
Cad.
Steel,
Cad.
Cad.
Cad.
Cad.
Cadmium
Plated
Plated
Plated
Plated
Plated
Plated
Steel
Steel
Steel
Steel
Steel
Steel,
CRES
CRES
Cad.
Cad.
CRES
CRES
Steel
Steel
Plated
Plated
Steel
Steel
Steel
None
None
None
None
(corrosionresistant)
8T03020
USE TITANIUM OR CRES STEEL SCXEW OR BOLT ABOVE 330’ F.
USE CAD. PLATED STEEL SCREW OR BOLT BELOW 330’ F.
WASHER STEEL LIGHT SERIES PLATED
SEAL AFTER INSTALLATION 1-1/2 DIAMETER CLEANED AREA
CLEAN TO BASE METAL AREA 1-1/2 DIAMETER OF TERMINAL
LOCK-WASHER
BONDING JUMPER
PLATED STEEL, CRES STEEL OR TITANIUM STRUCTURE
SELF-LOCKING NUT OR SELF-LOCKING PLATE NUT
2000-610-33
CRES Steel
or
Titanium Electrical Bonding
Figure 3 20-03-00 A14
Page 5 Jun 20/91
Ci~eechcraft BONANZA SERIES MAINTENANCE MANUAL
NOTE The
bond
must
area
refinished
be
within 24 hours of electrical
bonding
to
preserve the integrity of the bond. If the bond involves a structural compoit must
nent,
be fillet sealed
the
at
edges or seams with sealant (5, Chart 1) 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 Remove all grease and oil from the electrical bonding surface with cleaner (6, Chart 1). Remove all
bonding
paint
surface with
Lightly
e.
Use cleaner solvent
electrical
bonding
cadmium
lacquer from the electrical MEK (1, Chart 1). or
f.
Install
the
a
electrically
edges or seams with sealant (5, Chart 1) to prevent moisture from entering and deteriorating
the electrical
surfaces.
bonding
TYPICAL BLIND GROUND STUD
(FIGURE 2) Installation of
a
accomplished
as
blind
typical
stud may be
ground
follows:
MS35338
Use
sur-
being
component
washers
on
all
bonding/grounding
Their
function
is
to
tight connection with plain or self-locking nuts under conditions
ensure a
surfaces time to
bonding
lock
electrical
where thermal
the
with
at the
thoroughly dry. Install
being
component
connections.
d.
wipe dry
g. After a good bond has been verified with the resistance check procedures, it must be fillet sealed
bolted
Allow the electrical
to clean the
bonded.
faces.
c.
1)
NOTE
from the steel
plating
and
surface.
clean rag.
not to remove any zinc or
care
Chart
(6,
surfaces
NOTE Use
bonding
ELECTRICAL BONDING EXAMPLES
a.
b.
sand the electrical
d.
electrically
may
expansion of
the
screw
occur.
bonded. The sidewalls of the
a.
NOTE The
bond
area
within 24 hours of the
integrity
involves
a
must
refinished
be
bonding
to preserve
of the bond. if the bond
structural
component,
must be fillet sealed at the
it
edges or 1) to pre-
(5, Chart entering and detethe electrical bonding surriorating faces. Refer to Chapter 20-08-00 for information on airplane finishes. seams
with sealer
vent moisture from
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.
Ensure the blind
ground
stud is of sufficient
size to distribute the current it will be
subjected
to.
CRES STEEL OR TITANIUM ELECTRICAL
BONDING
(FIGURE 3) a.
Prepare
the
electrical
surfaces
bonding
as
outlined under METAL SURFACE PREPARATION STAINLESS STEEL AND TITANIUM SURFACES
AND ELECTRICAL BONDING in this chapter.
Remove all oil and grease from the electrical bonding surface with cleaner solvent (6, Chart 1).
distance will
b. a.
b.
Remove all
bonding c.
paint
or
from the electrical
lacquer (1, Chart 1).
surface with MEK
Allow the electrical
oughly dry. 20-03-00 Page 6 Jun 20/91
bonding
surface to thor-
Screw size: Use
permit.
a
substituted for the No. meet
edge
CRES steel c.
Use
a
distance
10
or
screw
No. 6
screw
requirements.
screw must
1/4-inch
No. 10
A No. 8
where
screw
edge
may be
if necessary to A Titanium or
be used.
diameter fastener for
100-amp
current returns.
A14
~3eechcraft BONANZA SERIES MAINTENANCE MANUAL
SEAL AFTER INSTALLATION 1-1/2 DIAMETER OF CLEANED AREA
CAD. PLATED STEEL SCREW OR BOLT STEEL WASHER PLATED
CLEAN TO BASIC METAL AREA 1-1/2 DIAMETER OF WASHER
LOCK-WASHER ALUMINUM WASHER
BONDING JUMPER
ALUMINUM STRUCTURE
WASHER (ALCLAD) NOT USED WITH PLATE NUT
SELF-LOCKING NUT OR SELF-LOCKING PLATE NUT
2000-610-35
Aluminum Electrical Bonding
Figure d.
Use
5/16-inch diameter fastener for 200-
a
amp current returns. e.
Use
an
Use
screw
for
an
h.
MS35206
plated
or
steel
screw
steel
or
titanium
lock
electrical
connections.
Their
where the maximum
(FIGURE 4)
washers
on
all
bonding/grounding function
Prepare
the
electrical
surfaces
bonding
as
outlined under METAL SURFACE PREPARATION
is
to
tight connection with plain or self-locking nuts under conditions where thermal expansion of the screw ensure a
may
required
F.. a.
MS35338
is
exceeds 6000 F..
ALUMINUM ELECTRICAL BONDING
CRES
NOTE Use
sealing
for
F..
applications above 330"
bolted
No
temperature
MS35206 cad
applications below 3300 f.
4
occur.
AND ELECTRICAL BONDING in this b.
Screw size: Use
distance will
permit.
a
c.
distance
edge Use
a
l/binch
10
chapter.
screw
A No. 8 or No. 6
substituted for the No. meet
No. 10
screw
where
screw
edge
may be
if necessary to
requirements. diameter fastener for
100-amp
current returns.
g. Use an MS21042L self-locking nut, or a selflocking nutplate (MS21047L or MS21069L) to retain the
screw.
d.
Use
a
5/16-inch
diameter fastener for 200-
amp current returns.
20-03-00
Page A14
7
Jun 20/91
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
CLEAN TO BASE METAL 1-1/2 CLAMP WIDTH AND INSIDE OF CLAMP
SEAL AFTER INSTALLATION 1-1/2 DIAMETER
CLEANED AREA
STRUCTURE
CLEAN AREA OF CLAMP TAB THAT TOUCHES TERMINAL TO BASIC METAL
WASHER
NUT AND WASHER SEAL AFTER INSTALLATION 1-1/2 DIAMETER CLEANED AREA 2000-610-36
Tubing Clamp to Bonding Jumper Electrical Bonding Figure 5 NOTE
c.
MS35336 lock washers on all bolted electrical bondinglgrounding Their function is to connections. ensure a tight connection with plain or self-locking nuts under conditions where thermal expansion of the screw Use
e.
Use
d.
MS35206 CRES steel
screw
above
Use
clamps of
the
same
tube material to avoid
BONDING JUMPER ACROSS TUBING CLAMP ELECTRICAL BONDING
(FIGURE 6)
an
MS21042L
self-locking nut, or a selfor MS21069L) to retain
locking nutplate (MS21047L the
an
dissimilar metal contact.
occur.
may
Use
3300 F..
Accomplish with
screw,
a.
electrical
bonding jumpers Prepare
the
bonding across
electrical
of
tubing segments
clamps
as
follows:
surfaces
bonding
as
TUBING CLAMP TO BONDING JUMPER
outlined under METAL SURFACE PREPARATION
ELECTRICAL BONDING
AND ELECTRICAL BONDING in this
(FIGURE 5)
b.
Accomplish electrical bonding
bonding jumpers
as
of
tubing clamps
with
follows:
b.
Use
an
below 3300 F..
MS35206
cad
plated
steel
screw
an
MS35206
cad
plated
steel
screw
screw
above
below 3300 F.. c.
a. Prepare the electrical bonding surfaces as outlined under METAL SURFACE PREPARATION AND ELECTRICAL BONDING in this chapter.
Use
chapter.
Use
an
MS35206 CRES steel
330" F.. d´•
Install
screw e.
an
AN960 cad
plated
washer under the
head and nut.
Use
an
MS21042L
self-locking
cad
plated
steel nuts.
20-03-00
Page 8 Jun 20/91
A14
’~)eed´•lcraft BONANZA SERIES MAINTENANCE MANUAL
TAB WELDED OR BRAZED TO TUBING
CLEAN TAB TO BASIC METAL AND SEAL AFTER
INSTALLATION.
O
I
II
O
CLEAN TAB TO BASIC METAL AND SEAL AFTER INSTALLATION. 2000-610-37
Bonding Jumper Across Tubing Clamp Electrical Bonding Figure 6
A14
20-03-00 Page 9 Jun 20/91
~)eechcraft BONANZA SERIES MAINTENANCE MANUAL
LOCK WASHER F
LOCK NUT TERMINAL (LIMIT TO 4)
WASHER D
I
WASHER C
I
PLAIN NUT
r
WASHER B STRUCTURE
WASHER
A
I
LOCK
WASHER E
SCREW OR BOLT
2000-610-39
Typical Ground Stud Electrical Bonding Figure 7
CLEAN TO BASE METAL BONDING/GROUNDING AREA AND CHEMICALLY TREAT
THIS AREA OF STRUCTURE AND BACK OF TAB MUST BE CLEANED AND CHEMICALLY TREATED BEFORE RIVETING TAB TO STRUCTURE. SEAL AREA AFTER ASSEMBLY.
4
4
NAS
1919M04S RIVET
(MAINTAIN 60 RIVET SPACING; RIVETS TO PENETRATE SHEET ONLY.)
FACE 2000-610-42
Electrical Bonding of Ground Tabs Figure 8 20-03-00
Page 10 Jun 20/91
A14
~)eechcraft BONANZA SERIES MAINTENANCE MANUAL
where thermal
TYPICAL GROUND STUD ELECTRICAL BONDING
(FIGURE 7)
may electrical
Accomplish
current returns
as
Screw size: Use
a.
distance will
bonding
permit.
a
No. 10
A No. 8
substituted for the No. 10 meet
b.
edge Use
of
ground
studs for
follows:
or
screw
No. 6
screw
where
screw
1/4-inch
if necessary to
diameter fastener for
100-amp
current returns. c.
Use
a
5/16-inch diameter
fastener for 200-
ELECTRICAL BONDING OF GROUND TABS
a. Prepare the electrical bonding surfaces as outlined under METAL SURFACE PREPARATION AND ELECTRICAL BONDING in this chapter.
b.
Use
washers
on
an
NAS1919M04S
rivet
to
attach
the
tab.
Use
ground
NOTE lock
compatible
(FIGURE 8)
c.
MS35338
screw
Refer to Chart 2 for a listing of d. hardware used with grounding studs.
ground
amp current returns.
Use
the
edge
may be
distance requirements.
a
expansion of
occur.
a
minimum of three rivets to attach the
tab.
ail
NOTE
electrical bolted bondinglgrounding Their function is to connections.
If it is necessary to remove the tab for any reason, the surface must be recleaned to remove all films.
tight connection with plain or self-locking nuts under conditions ensure a
ITEM TO BE BONDED THROUGH MOUNTING FEET
LOCK WASHER CLEAN MOUNTING STRUCTURE 1/4 TO BASE METAL TIMES THE AREA OF THE CLEAN MOUNTING FEET. THE PORTION OF THE FEET IN CONTACT WITH THE MOUNTING STRUCTURE. REFINISH AFTER INSTALLATION 1/4 TIMES THE AREA CLEANED.
NOTE ON
ITEMS THAT HAVE THE BOLTS SPACED MORE THAN 6 INCHES IT IS ONLY NECESSARY TO CLEAN THE AREA 2 INCHES ON EACH SIDE OF THE ATTACH BOLTS OR SCREWS.
APART,
2000-610-43
Electrical Bonding of
A14
Equipment Installed Figure 9
With
Mounting Feet
20-03-00 Page 11 Jun 20/91
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
REFINISHED AREA MOUNTING
LOCK
BA~E
WAS~ER
BONDING STRAP
SHOCK MOUNT
CLEANED AREA
-,i I
LOCK WASHER
MOUNTING STRUCTURE
CLEAN THE MOUNTING STRUCTURE TO THE BASE METAL 1/2 TIMES THE WIDTH OF THE BONDING STRAP AND THE ATTACHING BONDING STRAP SCREWS. REFINISH AFTER INSTALLATION 1/2 TIMES THE AREA CLEANED.
NOTE INSTALL BONDING STRAP UNDER SHOCK MOUNT PAD IN SUCH A MANNER THAT THE STRAP DOES NOT ALTER SHOCK MOUNT FUNCTION.
Electrical
20-03-00 12 Jun 20/91
2000-610-44
Bonding of Equipment Installed With Shock Mounts Figure 10
Page
A14
CST)eechcraft BONANZA SERIES MAINTENANCE MANUAL
used
DESCRIPTION AND OPERATION This
airplane uses carbon steel control cables of multiple wire construction with the number of strands varying according to the diameter of the cable. The carbon steel wire is helically twisted into strands and the strands wound about other strands
forming
the flexible carbon steel cable.
The
PRODUCTS WHICH CONFORM TO THE REQUIREOF
MENTS
A
SPECIFICATION
MAY
BE
USED
EVEN THOUGH NOT INCLUDED IN THE CHART. 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
RECOMMENDED MA TERIALS The recommended materials listed in Chart 1
as
specifications provided for reference only and are not specifically required by Beech Aircraft Corporation. Any or
to
to
cations. GENERIC OR LOCALLY MANUFACTURED
Only
meeting federal, military
the
specification may be availability. products included subject in these charts have been tested and approved for aviation usage by Beech Aircraft Corporation, by the vendor or compliance to the applicable specifiproduct conforming
CONTROL CABLES AND PULLEYS
vendor
are
the technician revision
of
or
the
mechanic to determine the current
applicable specification prior
to
usage of the product listed. This can be done by contacting the vendor of the product to be used.
CHART 1
RECOMMENDED MATERIALS MATERIAL
1.
Lubricant
SPECIFICATION
MIL-G-23827
PRODUCT
VENDOR
Grease
American Oil Co., 165 N. Canal,
Supermil A722823
Chicago, Royco
27A
Royal
IL 60606
Lubricants Co.,
River Road, Hanover, NJ 07936
Aeroshell Grease 7
Shell Oil Co., 1 Shell Plaza, P.O. Box 2463, Houston, TX 77001
BP Aero Grease 318
BP
Trading Limited,
Moore Lane, Britannic House, London E.C. 2 2.
Corrosion
MIL-C-16173
Petrotect Grade 2
England
Pennsylvania Refining
Preventive
Co.,
Compound
1686 Lisbon Road, Cleveland, OH 44104
Braycote
130
Bray Oil Co., Los Angeles,
CA
8T01241
Ai4
20-04-00 Page 1 Jun 20/91
Ci~echcraR BONANZA SERIES MAINTENANCE MANUAL
CONTROL CABLES AND PULLEYS MAINTENANCE PRACTICES
CONTROL CABLE SYSTEM INSPECTION
(FIGURE I)
Inspect the control cables for incorrect routing, fraying and twisting. Look for interference with adjacent airplane structure, equipment, wiring, plumbing and other control cables. a.
b. Monitor control cable movement for freedom, looseness and full travel.
Visually inspect
c.
tion, cracks
WARNING
When
control cables, inspecting always wear gloves to avoid injury from frayed or broken wires,
When
a
control cable is removed from
the
airplane, the cable should be dipped in MIL-C-16173 corrosion preventive (2, Chart 1). Excess corrosion preventive may be removed by wiping with
a
e.
wires
fdllows:
swaged fittings for fitting.
Locate any control cable broken as follows:
1. Inspect the pulleys by passing a
distor-
control cables
or
corroded
near
fairlead
cloth
along the length of the cable. If a snag is found, closely examine the cable to determine the extent of the damage as shown in
Figure and
as
all
broken wires at the
d. Turnbuckles should have the proper thread exposure and be correctly safety wired.
clean cloth.
Inspect the control cable system
or
1.
2. Any suspect cable should be removed placed in a loop position and checked for addi-
tional broken wires
as
shown in
Figure
1.
BROKEN WIRES ARE VISIBLE WHEN CABLE IS REMOVED AND BENT
BROKEN WIRES ARE NORMALLY DETECTABLE BY WIPING A CLOTH ALONG THE CABLE
DO NOT BEND THE CABLE INTO A LOOP SMALLER THAN 50 TIMES THE CABLE DIAMETER 2000-610-61
Typical Control Cable With Broken Wires Figure 1
20-04-00
Page
2
Jun 20/91
A14
ci3~echcraft BONANZA SERIES MAINTENANCE MANUAL
cable is installed in its normal position in the airplane. If only a part of the control cable is installed
NOTE Individual broken wires in
and
primary
are
acceptable
secondary
in
control
cables at random locations when there are no on
for
remove
of
corrosion.
with If
the control cable, form it into
(FIGURE 2) broken
Inspect all control
a
loop,
and
The interior of all turnbuckles should grease tection.
(1, Chart 1) for corrosion pro-
When stored in coil
Control cable pulleys are installed along the control cables where a change of direction is needed.
b. Inspect all control cable pulley bearings for smooth rotation, freedom from flat spots and foreign material. or
in
a
coil.
form, the coil inside diameter
should not be less than 150 times the control cable diameter, or bent in a radius of not less than 75 times the control cable diameter. Coils should not be flattened, twisted or folded during storage. Storage requirements should apply until the control
A14
follows:
embedded in the grooves.
CONTROL CABLE STORAGE
straight
as
a. Inspect all control cable pulleys for roughness, sharp edges and the presence of foreign material
filled with MIL-G-23827
Control cables should be stored
pulleys
NOTE
NOTE
or
cable
necessary,
check the center strand for corrosion. Replace any control cable that shows evidence of corrosion.
be coated
control cable storage requirements portion of the control cable.
to the uninstalled
CONTROL CABLE PULLEY INSPECTION
any three foot segment of cable.
evidence
assembly,
than three broken wires
Inspect the control cables
3. wires
more
an
apply
c. Inspect alignment.
all
control
cable
pulleys
for proper
I"spect the control cable pulley brackets and guards for damage, misalignment and looseness. d´•
e.
Control cable
pulleys
which turn for
a
short
distance must be rotated periodically to provide new bearing surface for the control cable.
a
20-04-00 Page 3 Jun 20/91
aeschcraft BONANZA SERIES MAINTENANCE MANUAL
WEAR MARK
EXCESSIVE CABLE
TENSION
PULLEY MISALIGNMENT
WEAR MARK
PULLEY TOO LARGE FOR CABLE
CABLE MISALIGNMENT
FROZEN BEARING
NORMAL CONDITION 2000-610-60
Control Cable Pulley Wear Patterns
Figure 2
20-04-00 4
Page
Jun 20/91
A14
Ci~eechcraft BONANZA SERIES MAINTENANCE MANUAL
DESCRIPTION AND OPERATION
BEARINGS
b.
Place
two
table under the This
contains
chapter
bearing
installation
and
removal information.
1. The
RECOMMENDED MATERIALS
on
the
bearing
at least
hydraulic press Figure 1/2-inch thicker
shown in
removal and installation tool
bearing
a
as
width.
bearing
Center
the
on
bearing housing
supports should be
than the c.
supports
bearing and installaapproximately 1/8-inch smaller diameter of the bearing outer race.
outer race. The
tion tool should be
The recommended materials listed in Chart 1
as
than the outside
vendor
specifications are provided for reference only and are not specifically required by Beech Aircraft 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 Beech Aircraft Corporation, by the vendor or compliance to the applicable specifimeeting federal, military
or
1~7 CAUTION
The
ing
OF
A
SPECIFICATION
MAY
BE
USED
in
remain
direct
bearing being
cations. GENERIC OR LOCALLY MANUFACTURED PRODUCTS WHICH CONFORM TO THE REQUIREMENTS
hydraulic press plunger and bearremoval and installation tool should
d´•
Align
the
bearing
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
apply pressure ing housing.
of
the
applicable specification prior to usage of the product listed. This can be done by contacting the vendor of the product to be used.
the
bearing removal and hydraulic press plunger and force the bearing from the bear-
installation tool with the
revision
with
and the
EVEN THOUGH NOT INCLUDED IN THE CHART.
Only
alignment
removed at all times.
to
MECHANICAL PRESS BEARING REMOVAL
(FIGURE 1) Remove the
bearing housing
from
the
air-
plane. BEARINGS
MAINTENANCE PRACTICES
b.
HYDRAULIC PRESS REARING REMOVAL
Remove
the
bearing housing
from the
the
bearing outer bearing width.
air-
c.
Center
a
an
race
center
inner diameter
and
bearing
diameter than the the
plane.
a bearing larger than 1/2-inch deeper than the
bearing housing,
the
(FIGURE 1) a.
On
removal socket with
removal socket smaller in
bearing
outer race.
CHART 1 RECOMMENDED MATERIALS MATERIAL
1.
Cleaner
SPECIFICATION
TT-M-261
VENDOR
PRODUCT
Methyl Ethyl
Obtain
locally
Loctite
Corp.,
Ketone 2.
Primer
Locquic
Primer "T"
705 N. Mountain Rd., Newington, CT 06111
3.
Retaining Compound
609
Loctite
Corp.,
705 N. Mountain Rd., Newington, CT 06111
BT01240
20-05-00
Page A14
1
Jun 20/91
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
LOAD MUST BE APPLIED TO OUTER
REMOVAL AND INSTALLATION
BEARING
TOOL
ONLY.
RACE
NUT WASHER HOUSING
W
--7
SOCKET
BEARING
SUPPORT HOUSING SOCKET
WASHER
BEARING
BOLT APPLY THE INSTALLING OR REMOVAL LOAD TO THE OUTER RACE OF THE BEARING. HYDRAULIC
REMOVAL
OR
INSTALLATION
TOOL
MECHANICAL PRESS METHOD
PRESS METHOD
2000-6 i 0-49
Bearing Removal Figure 1 d.
Install
washer and bolt
a
through
one
of the
I
sockets, through the center of the bearing, then
through e.
f.
opposite socket
the
Install
washer and nut
a
Tighten
as
the nut
on
shown in
on
Figure
CIUI1ON
I
1.
When cleaning bearing surfaces, never allow solvent to enter the bearing. Never touch the bearing or bearing housing surfaces with bare hands. Use a clean cloth to cover the bearing to prevent contamination after they have been cleaned.
the bolt threads.
the bolt until the pressure bearing from the bearing
is sufficient to release the
housing. BEARING HOUSING INSPECTION
Coat the surfaces where a retaining comis to be applied with primer (2, Chart i). This includes the bearing outer surface, bearing housing mating surface and the bearing housing retention b.
Inspect
the
bearing
cracks, warpage
or
housingto-bearing
housing for any grooves, hole elongation. The bearing
contact surface must be smooth
pound
flange
and uniform,
if
applicable. CAUTION I U-´•-I
REARING INSTALLATION USING RETAINING COMPOUND a.
Clean the outer surface of the
with MEK
(1, Chart 1) and wipe dry.
bearing
race
Ensure that oil
bearing
no
primer is applied
grooves
or
to the lubrication
ports.
20-05-00
Page 2 Jun 20/91
A14
Ci3~echcraft BONANZA SERIES MAINTENANCE MANUAL
BEARING INSTALLATION BY STAKING
NOTE
(FIGURE 2)
All cadmium, zinc, corrosion-resistant and anodized steel, including plastic
items,
be
must
b.
proper adhesion pound (3, Chart 1). e.
Allow the
primer (2,
least 30 minutes at
room
Chart
1)
to air
dry
for at
temperature.
on
the
d.
g. area
h.
bearing housing.
Apply retaining compound (3, Chart 1) to the bearing and the bearing housing, retaining compound
must cure before the
is put into service. Curing may be one of the following:
accom-
with
Allow the
1.
remain at
to be
are
the
supports.
bearing housing
was
previously staked,
stakes should be centered between the
new
stakes. If
existing
a new
bearing housing
used, the stake pattern should be the the old
one on
between the
bearing plished
and bearing housing on two Figure 2, if both sides of the staked. The inner bearing race
bearing
shown in
is
being
same as
the
bearing housing.
the
Using
The
as
If the
hydraulic or mechanical pressure method shown in Figure 1, 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. f.
or
must not touch the
applied.
bearing housing.
mechanical pressure 1, apply pressure to the
hydraulic Figure is firmly seated
Place the
bearing
Apply a thin coat of the retaining compound (3, Chart l)to the bearing and the bearing housing mating surfaces where the primer (2, Chart 1) was
the
in the bearing housbearing until it ing. Pressure must be applied in direct alignment to the bearing housing for the bearing to seat properly.
supports,
d.
bearing
on
the
Using
c.
retaining compound (3, Chart 1) may be applied before or after bearing installation in the bearing housing.
The
Center the
bearing
method shown in
NOTE
e.
Center the
a.
primed to assure of the retaining com-
room
bearing
and
bearing housing
to
temperature for 24 hours without parts,
any movement of the
2. Heat the bearing and bearing housing to 275" ~100 F. and maintain that temperature for 15 minutes only. CHART 2 RECOMMENDED STAKES FOR BEARINGS
Bearing O.D.
NOTE a ring stake is used, combined length should be 25 percent of bearing circumference.
When
total the
pi,,takes should be located .030 .010-inch
from the outer diameter of the
bearing
on
the bear-
ing housing. f.
deep
Pin stakes should to retain
staked
g.
on
bearings
be .010 to .032-inch
bearing housing
is
both sides.
The number of
housing
only
when the
should be
pin
as
stakes around
a
bearing
indicated in Chart 2.
bearing has been secured in the housing by staking or by the use of a retaining compound,
After the
relubricate with the proper lubrication and reinstall in the airplane.
Number of Stakes
I ´•´•´•ll~1 CAUTION
up to .734-inch
4
.735-inch to .984-inch
6
.985-inch to 1.234-inches
8
bearing should slip or move in bearing housing, the bearing must
If the
BT01160
A14
the
be removed and recleaned. The bear-
ing housing must be recleaned. Examine the bearing for any damage and reinstall in the bearing housing.
20-05-00 Page 3 Jun 20/91
’i3eechcraft BONANZA SERIES MAINTENANCE MANUAL
OUTER BEARING RACE
HOUSING TO .025 R
.030
.010
~.OIO-INCH
-iiJ
.010 TO .032 INCH
SUPPORT INNER BEARING RACE
STAKE
NOTE DO
NOT
SUPPORT AGAINST
INNER BEARING RACE
DURING
STAKING. 2000-610-50
Bearing Staking Figure 2
20-05-00
Page 4 Jun 20/91
414
Cil)eechcraft BONANZA SERIES MAINTENANCE MANUAL
TUBE AND HOSE ASSEMBLIES AND
e.
DESCRIPTION AND OPERATION
FITTINGS
Never stretch
a
hose to make
connection.
a
The hose material must be compatible with applicable system fluids. Substitution of a hose material that is not compatible with the system fluid f.
the This chapter contains information to remove, maintain and install hose and tube assemblies and fit-
tings. 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
of tube assemblies used in the airaluminum or steel machine formed tubing
majority
plane
are
assemblies. used in areas of the airplane where a flexible line is more suitable for installations and Hoses
are
freedom of movement is necessary.
will contaminate the system.
REMOVAL OF TUBE AND HOSE
ASSEMBLIES Tube and hose assemblies may be removed lows: a.
Relieve all
b.
Disconnect both
d.
MAINTENANCE PRACTICES
ing maintenance, repair or servicing pneumatic operated system.
on
any fluid
clamps securing
hose
or
tube
the tube
plug
the hose
or
or
tube
Remove the tube
or
hose
assembly
and tag
both ends to aid in reinstallation.
HOSE ASSEMBL Y INSTALLA TION Hose assemblies may be installed
as
follows:
NOTE
CAUTION
systems
or
or
CAMON1 that
Remove all
identify
Observe all WARNINGS, CAUTIONS and NOTES throughout this maintenance manual when perform-
Verify
pressure. ends of the
assembly and immediately cap hose ends and fittings. c.
fol-
assembly.
TUBING, HOSE AND FITTINGS
If
which
a
hose
new
assembly
is
be
to
installed, the hose assembly must be clean, the correct length, clear of
operate
pneumatics under pressure are fully depressurized before opening or disconnecting a tubing or
from fluids
system
as
or
obstructions and material with the
compatible
system fluid.
hose. a.
The and
list of maintenance
following
vided
as
aid for
an
practices is prohandling, removing, installing
repairing tubing and
hoses.
Cap
plug all disconnected tubing and hose and fittings immediately to prevent con-
or
assemblies
tamination of the system. b.
Visually
check
for
cleanliness, evidence of
contamination and obstructions tion of tube
or
prior
this
have
Any hose protective
and checked for obstruction d.
When
prior
connecting tube assemblies, do not assembly to the installed position. If
mismatch between the male and female fittings should result, see Figure 1 for the allowable mismatch.
e.
f.
to installation,
force the tube a
After
ensure
and tube assemblies that did not covers installed must be cleaned
outlined
assembly
to
fittings.
Torque the "B" nuts to torque specified in Chart 1.
no c.
Connect the "8" nuts of the hose
e.
d.
practices
maintenance
TUBE AND HOSE ASSEMBLIES MAINTENANCE PRACTICES in
chapter.
th, proper
to reconnec-
hose assemblies.
heading
AND FITTINGS
b. a.
Observe the
under the
torquing
the
the "B" nuts,
fittings using
inspect
the
the hose to
that the hose is not under tension and that
indication of
twisting
is present.
Inspect
the hose for proper
Inspect
the hose for freedom to
length. expand
and
Co"t’act.
Inspectthe hose forclearance to all structure. inadequate clearance exists between the hose and structure, protection must be provided for the hose to prevent damage from chafing. g.
If
20-06-00
Page A14
1
Jun 20/91
BONANZA SERIES MAINTENANCE MANUAL
TUBE INSTALLA TION
d.
Install the
packing (O-ring)
is
assembly
tube
new
a
The
be
to
the
installed, the tube assembly must be clean, the correct length, clear of obstructions and manufactured of the
e.
correct material.
under the AND
MAINTENANCE PRACTICES in
FlTTINGS
this
chapter.
b.
Inspect
tube
ends, Make
fittings
Check
d.
alignment
1.
and fit of the tube
Place the tube
and
the tube
2.
tighten assembly.
assembly
1.
The free tubing end must 1/32-inch of the fitting per every length as shown in Figure 1. 4.
e.
to
aligned
antiseize
apply the proper
com-
fittings. assembly
the
on
the "B" nuts to the torque values Chart 1.
tighten
and
fittings specified
in
fittings
Lubricate
may be installed
the
male
as
follows: the
fitting, system
of
backup ring packing sparingly or petrolatum (AN-P-51, Vaseline).
fluid
by
a
sud-
Holding turning,
the nut with
in
turning
a
rotate the
wrench to prevent it in an additional 1-1/2
fitting fitting in the
than
no more
one
by
proper direction 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.
NONPOSITIONING TYPE FITTING INSTALLATION may be installed
Nonpositioning type fittings
fol-
as
Install the nut
(AN6289)
on
the
Install the teflon backup
bore of the nut.
20-06-00 Page 2 Jun 20/91
packing with petrolatum (AN-P-51, Vaseline). a´•
Lubricate the
b´•
Install the
c.
Thread the
tightly d.
on
in the
packing
fitting
the system fluid
fitting
or
thread relief.
into the boss until it bottoms
the boss.
Tighten
the
fitting
to
the
specified torque
fitting
Pipe
thread
a.
Apply 1.
be installed
fittings may
as
teflon tape to the threads
Start tape at
or
close to
follows:
as
follows:
narrow
end of
threads. until the
nut is clear of the thread relief, c.
be detected
PIPE THREAD FITTING INSTALLATION
with the
threads
and
b.
can
value.
FLUID LINE FITTING INSTALLATION
a.
point
lows:
lengthwise within 1/32-inch per every 10 tube length as shown in Figure 1.
Install the tube
Fluid line
the
The free end of the tube must match the
If necessary,
pound f.
be
10 inches of
cone
inches of
nut
den increase in torque.
g.
assembly in the proper coupling nut at one end of
3.
fitting
fitting into the boss with the fitting until the packing contacts
turns. Position the
within
tube
with the
This
from
opposite end of the tube must be degrees of parallel with the fitting as
Figure
pushed
NOTE
properly assembly.
The
within two
shown in
one
is
are
follows before installation:
position
packing
boss.
bends.
that the
certain
with
compatible
the lower threaded section of the fit-
Install the
turning
damage, particularly at Damaged tube replaced or repaired.
and
installed before connection of the tube
as
f.
be
Turn the nut down until the
the tube for
fittings,
assemblies should be c.
packing must system fluid.
firmly against ting.
Observe the maintenance practices outlined heading TUBE AND HOSE ASSEMBLIES
a.
the thread relief.
NOTE
NOTE If
on
Wrap the tape around the fitting in the Wrap clockwise for right hand threaded fittings. Wrap counterclockwise for left hand threaded fittings. 2.
direction of the threads.
ring
in the counter-
A14
’~-)eecEacraft BONANZA SERIES MAINTENANCE MANUAL
ra
MAXIMUM ALLOWABLE 1/32 INCH PER 10 INCHES OF TUBE LENGTH
MEASURE MISMATCH WITH FREE END CLEAR OF FITTING
MAXIMUM ALLOWABLE 1/32 INCH PER lo INCHES OF
TUBE LENGTH
MAXIMUM ALLOWABLE 1/32 INCH PER 10 INCHES OF TUBE LENGTH
I t 2 DEG MAX
ANGULAR MISMATCH
RADIAL MISMATCH
LENGTH MISMATCH 2000-610-63
Tubing Installation Mismatch Figure 1 CHART 1 FLARED FITTING TORQUE CHART (INCH-POUNDS) Hose
Tubing
Aluminum
Steel
Size
O.D.
Tubing
Tubing
Tubing
Tubing
Fitting
(Inches)
Flare
Flare
Flareless
Flareless
(Aluminum)
-8 -10 -12
Min
Max
80 125 250 350 500 700
90 135 180 270 450 700 1100 1200
900 900
1300 1350
100 150 200 300 500 800 1150 1400 1450 1500
75 80 100 100 200 360 390 600 600
90 100 130 130 240 400 430 900 900 900
90 135 180 270 450 700 1100 1200 1300
100 150 120 300 500 800 1150 1400 1450
1350
1500
1/4
11/2
600
3/4
-16 -20 -24
Max
65
1/4 5/16 3/8 1/2 5/8
-5 -6
Min
40 60 75 150 200 300 500 600
3/16
1
1
Oxygen
Max
Max
-4
Steel
Min
Min
-3
Aluminum
600
Min
Line
Max
Hose End
Fitting Min
70 100
125
Max
70 85 100 210 300 500 700
100 120 180 250 420 480 850 1150
and
tighten
BT01080
3.
tape
Apply tension to the tape shape of the threads.
to conform the
to the
4.
The
b.
Thread the
until it bottoms
fitting into the boss tightly on the boss.
tape should overlap the previous pipe thread
wrap of tape up to one-half inch to seal fittings up to two inches in diameter.
A14
20-06-00 Page 3 Jun 20/91
~3eechcraft. BONANZA SERIES MAINTENANCE MANUAL
TUBE OUTSIDE DIAMETER (D)
ADII IS MEASURED BEND TO TUBE CENTERLINE
TUBE CENTER LINE
2000-610-64
Tube
Bending Figure 2
TUBE DAMAGE LIMITS
a.
Replace steel tubes which have nicks or deeper than 10 percent of tubing wall
scratches
thickness.
NOTE Nicks and scratches not
exceeding
the
following limitations may be repaired by polishing out the damaged area, using Finish
fine
grade polishing
of emery cloth and oil. with crocus cloth and
oil. Flush and clean all
grit from line
b. or
Replace any aluminum tube which has nicks scratches deeper than 20 percent of the tube
wall thickness. c. Replace any tubes which have dents deeper than 5 percent of the tube outside diameter.
assembly.
20-06-00
Page 4 Jun 20/91
A14
Cj~eechcraR BONANZA SERIES MAINTENANCE MANUAL
CHART 2 TUBING BENDING LIMITS
DIAMETER
RADII
RADII
(D)
1/8 3/16 1/4 5/16 3/8 7/16 1/2 5/8 3/4 7/8 1
1-1/8 1-1/4
1-3/8 1-1/2 1-5/8 1-3/4 1-7/8 2
2-1/4 2-1/2 3
MILLIMETER
3.175 4.762
6.350 7.937 9.525 11.112 12.700 15.875 19.050 22.225 25.400 28.575 31.750 34.925 38.100 41.275 44.450 47.625 50.800 57.150 63.500 76.200
INCH
.375 .563 .750 .938 1.125 1.312 1.500 1.875 2.250 2.625 3.000 3.375 3.750 4.125 4.500 4.875 5.250 5.625 6.000 6.750 7.500 9.000
6D
4D
3D
INCH
ADDITIONAL BEND
RECOMMENDED BEND
TUBE OUTSIDE
MILLIMETER
9.525 14.286 19.050 23.811 28.575 33.336 38.100 47.625 57.150 66.675 76.200 85.725 95.250 104.775 114.300 123.825 133.350 142.875 152.400 171.450 190.500 228.600
INCH
MILLIMETER
.500 .750 1.000 1.250 1.500 1.750 2.000 2.500 3.000 3.500 4.000 4.500 5.000 5.500 6.000 6.500 7.000 7.500 8.000 9.000 10.000 12.000
12.700 19.048 25.400 31.748 38.100 44.448 50.800 63.500 76.200 88.900 101.600 114.300 127.000 139.700 152.400 165.100 177.800 189.500 203.200 228.600 254.000 304.800
INCH
.750 1 .1 25
1.500
1.875 2.250 2.625 3.000 3.750 4.500 5.250 6.000 6.750 7.500 8.250 9.000 9.750 10.500 11.250 12.000 13.500 15.000 18.000
MILLIMETER
19.050 28.572 38.100 47.622 57.150 66.672 76.200 95.250 114.300 133.350 152.400 171.450 190.500 209.550 228.600 147.650 266.700 285.750 304.800 342.900 381.000 457.200
079
A14
20-06-00 Page 5 Jun 20/91
ci~eechcraft BONANZA SERIES MAINTENANCE MANUAL
LOCKING DEVICES
DESCRIPTION AND
cent
plug.
OPERATION
boss
casing. Never lockwire bushing to pins should be installed so that the
or
Cotter
head fits into the slot of the castellated nut and,
Except for specific instructions required to satisfy a certain application, the following procedures are standard methods used to install various locking devices used in conjunction with bolts, screws and
unless
otherwise
should be bent end flat
specified, the stud
over
or
of
end
one
the
pin
bolt and the other
the flat of the nut.
against
nuts.
MAINTENANCE
LOCKING DEVICES PRACTICES
SELF-LOCKING NUTS Where cedure
self-locking applies:
nuts
are
used, the following pro-
LOCKWIRE INSTALLA TION PROCEDURES
2)
self-locking nuts, note the torque necesturn the self-locking nut before the self-
For
a.
sary to
locking
NOTE
nut is seated.
Figure 1 illustrates a typical lockwire procedure. Although there are numerous lockwire operations performed on the airplane, practically all are derived from the basic examples shown in Fig-
Add the above torque to the value detailed in the assembly instruction for the application. Use b.
this
I AND
(FIGURES
new
value
the total
as
applied torque,
SLOTTED, STEEL LOCKNUTS (PREVAILING
ure
2.
TORQUE TYPE) Effective
requires
locking the full
of slotted, steel locknuts on bolts engagement of all locknut threads.
Observe the
when
following guidelines
installing
lockwire:
The chamfered section of the locknut ID does not exert force on the bolt. It is not necessary that the bolt be flush with or protrude from the outer face of
the locknut,
a.
Newlockwire mustbe used.
b.
Use the
same
type and diameter
of lockwire
LOCKWIRE AND COTTER PIN
assembly. Except employed during the wire used on the airspecified, and corrosion resistant is heat plane power plant
REQUIREMENTS
steel wire of 0.025-inch diameter.
as
the initial
that
where otherwise
c.
tightening a castellated nut for cotter pin installation, alignment of the slot must be obtained without exceeding the maximum torque. If this is not possible, replace the nut. After tightening the
When
nut to the recommended
be loosened to slot in the nut is not
torque, the
permit insertion or
of
a
nut must not
cotter
lockwire hole in the bolt
correctly aligned
at the minimum
pin.
If the
torque value
the nut, screw or bolt should be further tightened to the next alignment position, but the maxi-
torque value given must not be exceeded.
Should
alignment still be impossible exceeding the maximum torque, back off one-half turn and retorque.
pins must never be reused. Ail pins must fit snugly into drilled holes in the bolts and studs for locking purposes. Bushings and plugs must be lockwired to the adjaLockwire and cotter
manner
a
that
tighten and keep a part locked in place, thus counteracting the natural tendency of the part to loosen. e.
Lockwire must
never
be overstressed. It will
break under vibrations if twisted too lockwire shall be
pulled
tightly. The being twisted, but
taut when
shall have minimum tension, if any, when secured. f.
without the nut
Lockwire must be installed in
to pre-
tends to
or screw
given, mum
d´•
tight after installation rubbing or vibration.
Lockwire must be
vent failure due to
Lockwire
engine,
or
ends which
ends
must
be
bent
structure, to avoid sharp
might present
a
safety
toward
the
projecting
or
hazard
or
vibrate
in the air stream.
lockwire and cotter
a
9´• Internal wiring must not cross overorobstruct flow passage when an alternate method can be
used.
20-07-00
Page A14
1
Jun 20/91
~eechcraR BONANZA SERIES MAINTENANCE MANUAL
INSERT
THE UPPERMOST WHICH POINTS TOWARD THE SECOND BOLT, THROUGH THE HOLE WHICH LIES BETWEEN THE NINE AND TWELVE O’CLOCK POSITIONS, GRASP THE END OF THE WIRE WITH A PAIR OF
WIRE,
POSITION THE HOLES.
PLIERS AND PULL THE WIRE TIGHT.
O
INSERT PROPER GAGE WIRE.
BRING THE FREE END OF THE WIRE AROUND THE BOLT HEAD IN A COUNTER-CLOCKWISE DIRECTION AND UNDER THE END PROTRUDING FROM THE BOLT HOLE. TWIST THE WIRE IN A COUNTER-CLOCKWISE DIRECTION.
WRAP UPPER END OF WIRE AND BEND IT AROUND THE HEAD THEN OF THE BOLT. UNDER THE OTHER END OF THE WIRE. BE SURE WIRE IS TIGHT AROUND HEAD.
GRASP THE WIRE BEYOND THE TWISTED PORTION AND TWIST THE WIRE ENDS COUNTER-CLOCKWISE UNTIL TIGHT.
DURING THE FINAL TWISTING MOTION OF THE PLIERS, BEND THE WIRE DOWN AND UNDER THE HEAD OF THE BOLT.
TWIST WIRE UNTIL WIRE IS JUST SHORT OF HOLE IN THE SECOND BOLT.
KEEPING WIRE UNDER TENSION, TWIST IN A CLOCKWISE DIRECTION UNTIL THE WIRE TIGHT. TIGHTENED THE WIRE SHALL HAVE APPROXIMATELY 7 TO 10 TWISTS PER INCH.
NEHWSI
CUT OFF EXCESS WIRE WITH DIAGONAL CUTTERS
g 2000-6011- 18
RH Thread
20-07-00 Page 2 Jun 20/91
Lockwiring Procedure Figure 1
A~4
~)eechcraft BONANZA SERIES MAINTENANCE MANUAL
EXAMPLE
EXAMPLE
EXAMPLE 3
2
EXAMPLE
4
FILLISTER HEAD SCREWS, SQUARE HEAD PLUGS, AND OTHER SIMILAR PARTS ARE WIRED SO THAT THE LOOSENING TENDENCY OF EITHER PART IS COUNTERACTED BY THE TIGHTENING OF THE OTHER PART. THE DIRECTION OF TWIST FROM THE SECOND TO THE THIRD UNIT IS COUNTER-CLOCKWISE TO KEEP THE LOOP IN POSITION AGAINST THE HEAD OF THE BOLT. THE WIRE ENTERING THE HOLE IN THE THIRD UNIT WILL BE THE LOWER WIRE AND BY MAKING A COUNTER-CLOCKWISE TWIST AFTER IT LEAVES THE HOLE, THE LOOP WILL BE SECURED IN PLACE AROUND THE HEAD OF THAT BOLT.
BOLTS,
EXAMPLE
5
EXAMPLE
EXAMPLE
6
7
EXAMPLE
8
METHODS FOR WIRING VARIOUS STANDARD ITEMS. WIRE MAY BE WRAPPED OVER THE UNIT RATHER THAN AROUND IT WHEN WIRING CASTELLATED NUTS OR ON OTHER ITEMS WHEN THERE IS A CLEARANCE PROBLEM.
6X~ EXAMPLE 9 THE METHOD FOR WIRING BOLTS IN DIFFERENT PLANES. NOTE THAT WIRE SHOULD ALWAYS BE APPLIED SO THAT TENSION IS IN THE TIGHTENING DIRECTION.
EXAMPLE
RH Thread
A14
10
HOLLOW HEAD PLUGS WIRED WITH THE TAB BENT INSIDE THE HOLE TO AVOID SNAGS AND POSSIBLE INJURY TO PERSONNEL.
EXAMPLE
II
CORRECT APPLICATION OF SINGLE WIRE TO CLOSELY SPACED MULTIPLE GROUP. 2000-604-19
Lockwiring Examples Figure 2 20-07-00 Page 3 Jun 20/91
Ci3~echcraft BONANZA SERIES MAINTENANCE MANUAL
LOCKWIRE HOLE ALIGNMENT
When nuts
c.
to be secured to a fastener
are
pins, tighten the fastener to the low side (minimum) of the applicable specified or selected torque range, unless otherwise specified, and if necessary, continue tightening until the nut slot aligns with the fastener hole. Maximum torque must with cotter
Check the units to be lockwired to make sure that they have been correctly torqued and that the wiring holes are properly positioned in relation to each other. When there are two or more units, it is desirable that the holes in the units be in the same rela-
tionship
to each other. Never
units to obtain
proper
loosen of the holes. It
overtorque
alignment
possible to align the wiring holes when torqued within the specified limits. if it is However, 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, should be
the
units
be exceeded.
never
or
are
Castellated
d´•
nuts
safetied with cotter
installed
fasteners
on
are
preferred method is with the cotter pin bent parallel to the axis of the fastener. The alternate method, where the cotter pin is mounted perpendicular to the axis of the fastener, may be used when the cotter pin in the prepins.
The
ferred method is apt to become
a
snag.
If 50 percent or more of the cotter pin diameter is above the nut castellation, a washer should be e.
LOCKWIRE TWISTING
used under the nut
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 To
falling into damage. marginal.
ends from hazard
a
is
or
areas
The
where
strength
they might
create
of lockwire holes
or a
shorter fastener should be
installed. A maximum of two washers may be permitted under a nut. f´•
Use the
listed
in
largest
MS24665
nominal diameter cotter
that
the
hole
and
slots
application of a cotter pin to any permitted if the fastener hole size required hole and slot size for the
accommodate. No nut or fastener is
is less than the cotter
pin.
Install the cotter pin head firmly in the slot of g. the nut with the axis of the cotter pin eye at right
COTTER PIN INSTALLA TION
angles
to the fastener shank. Bend the cotter
(FIGURE 3)
prongs
so
are
Use the the
following to select desired application:
a.
Install
b.
Select cotter
new
cotter
pin
and install cotter
pins
for
firmly
that the cotter seated
against
pin
head and upper prong the fastener and the lower
pin
prong against the nut.
pin or rod end applications, install the pin with the axis of the eye parallel to the shank of the clevis pin or rod end. Bend the prongs around the shank of the clevis pin or rod end as shown in Figure 3. h.
pins.
In clevis
cotter
material in accordance with
temperature, atmosphere and service limitations
specified
pin will
as
in Chart 1.
CHART 1
COTTER PIN INFORMATION MATERIAL
TEMPERATURE
SERVICE
MS24665 Cotter Pins Carbon Steel
Ambient
Normal atmosphere cotter pins contacting cadimum plated bolts
Temperature
up to 4600F
or nuts.
MS24665 Cotter Pins
Ambient
Corrosion-Resistant Steel
up to 6000F
Temperature
Nonmagnetic requirements cotter pins contacting corrosion-resistant steel bolts
or
nuts in
a
corrosive
atmosphere. BT01083
20-07-00
Page
4
Jun 20/91
A14
(i~eechcraft BONANZA SERIES MAINTENANCE MANUAL
plated cotter pins should not be applications bringing them in contact with fuel, hydraulic fluid or synthetic lubricants. i.
Cadmium
used in
KEYWASHERS (TAB AND CUP INS TA L LA TION
TYPES)
c.
External type rings must be to allow installation without
enough
expanded only becoming bent.
After installation, ensure each retaining ring is completely seated in its groove, without looseness d.
or
distortion.
TURNBUCKLE LOCK CLIP INSTALLA TION
keywasher, interchangeable.
The terms are
tabwasher and
Observe the following when installing washers, tabwashers and cupwashers: a.
Always
use new
washers for each
cupwasher new
assembly.
(SPIROLOX, ETC.)
Internal
point
rings
Safety
turnbuckles with lock
clips
as
a.
New lock
b.
Screw both threaded terminals
clips
be
installed
compressed beyond ring meet.
must not be
where ends of the
using
follows:
must be used.
so
than three threads of either terminal is side the body.
a. Retaining rings must approved retaining ring pliers.
into
threaded terminals are screwed the turnbuckle barrel.
tance into the turnbuckle barrel
INSTALLA TION
b.
The turnbuckle barrel must be filled MIL-G-23827 grease before the
with
When
RETAINING RINGS
the
NOTE
key-
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. b.
(FIGURE 4)
equal dis-
an
that
no
more
exposed
out-
if necessary, adjust the terminals until the c. 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
TO PROVIDE CLEARANCE PRONG MAY BE CUT HERE
PRONG MUST BE OF SUFFICIENT LENGTH AS SHOWN.
PRONGS MUST BE OF SUFFICIENT LENGTH TO EXTEND 90’ BEYOND HOLE AS SHOWN.
CASTELLATED NUT ON BOLT PREFERRED METHOD
PIN APPLICATION 2000-610-46
Cotter Pin Installation
Figure 3 20-07-00 Page 5 A14
Jun 20/91
Ci3eechcraR BONANZA SERIES MAINTENANCE MANUAL
HOOK LOOP HOOK LIP
LOCKING CLIP
´•---------~6-´•
SWAGED TERMINAL
SWAGED TERMINAL
TURNBUCKLE BARREL
2000-610-47
Turnbuckle Safetying Using Lock Clips
Figure 20-07-00 Page 6
Jun 20/91
4
A14
aeechcraft BONANZA SERIES NIAINTENANCE MANUAL
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 in the center of
turnbuckle barrel
using fingers only. clip installation
tool to check the lock
clip
Do not as
the
use a
locking
could be distorted.
the turnbuckle barrel.
d.
Press the
locking clip
in the hole in the center
of the turnbuckle barrel to its full extent. e.
The curved end of the
locking clip
f.
To check proper to remove the
Repeat the previous steps locking clip on the opposite
for installation of end of the turn-
buckle barrel.
will latch in
the hole in in the center of the turnbuckle barrel.
attempt
g. the
seating of the locking clip, pressed "U" end from the
h´• Both locking clips may be inserted in the same side of the turnbuckle barrel center hole or in oppo-
site sides of the turnbuckle barrel center hole.
20-07-00 Page 7 A14
Jun 20/91
BONANZA SERIES MAINTENANCE MANUAL
AIRPLANE FINISH CARE
RECOMMENDED MA TERIALS
DESCRIPTION and
following cleaning, waxing, placarding painting information provides finish care information needed to maintain the airplane in an approved
The
condition.
NOTE When
interior
or
refer to the
paint is airplane log book
exterior
required, paint part number. This number will identify the type of paint used on the airplane as it was delivered new. On older airplanes which do not have the paint part number listed on the airplane log book, contact the Commercial Service Department of BEECH Aircraft Corporation to determine the paint used on the airplane as it was for the
delivered,
The recommended materials listed in Chart 1
as
meeting federal, military or vendor specifications are provided for reference only and are not specifically required by Beech Aircraft 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 Beech Aircraft Corporation, by the vendor 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 revision
or
of the
mechanic to determine the current
applicable specification prior
to
usage of the product listed. This can be done by contacting the vendor of the product to be used.
CHART 1
RECOMMENDED MATERIALS SPECIFICATION
MATERIAL
VENDOR
PRODUCT
1.
Cleaner
0-A-51
Acetone
Obtain
locally
2.
Cleaner
TT-M-261
Methyl Ethyl
Obtain
locally
Obtain
locally
Obtain
locally
Ketone 3.
Cleaner
4.
Acid
5.
Base Primer
Etching
TT-N-95 Primer
Naphtha
MIL-C-8514 EX2016G
Pratt 8 Lambert
Coatings Div., P.O. Box 2153,
Wichita, KS 67201 6.
Catalyst
T607
Pratt 8 Lambert
Coatings Div., P.O. Box 2153,
Wichita, KS 67201 7.
Urethane Primer
38-Y-3
U.S. Paint,
Lacquer
and Chemicals Co.,
St. Louis, MO. 8.
Cleaner
Lacquer Thinner
Obtain
locally
20-08-00
Page A14
1
Jun 20/91
BONANZA SERIES MAINTENANCE MANUAL
CHART 1
RECOMMENDED MATERIALS (Continued)
9.
Anti-static
528-104
Coating
VENDOR
PRODUCT
SPECIFICATION
MATERIAL
or
528-306
DeSoto Inc., Southwestern Plant, Forrest Ln. and Shiloh
Rd., P.O. Box 401268
Garland, TX 75042 10.
M-213
Elastomeric
Lord Chemical Products
Group,
Polyurethane (white base)
2000 W. Grandview
Blvd., Erie, PA 16514 11.
M-200
Curing Solution (elastomeric polyurethane)
Lord Chemical Products
Group, 2000 W. Grandview
Blvd., Erie, PA 16154 12.
EC750
Sealer
Minnesota
Mining
and
Mfg. Co., St. Paul, MN 13.
Oakite No. 6
14.
Sanding Surfacer
Oakite Products Inc., Berkeley Hts., N.J. 07922 F900 Primer Surfacer
Andrew Brown Co., 801 E. Lee,
Irving, 15.
Toluol
16.
Isopropyl
17.
(toluene) Alcohol
Alodine 1200S
TX
TT-T-548
Obtain
locally
TT-I-735
Obtain
locally
MIL-C-5541
Amchem Products Inc.
Ambler, PA 19002 18.
Primer, Epoxy-
U.S. Paint,
MIL-P-23377
Lacquer
and
Chemical Co.
Polyamide
St. Louis, MO 19.
Urethane Paint
6160 Matterhorn White
U.S. Paint, Lacquer and Chemical Co. St. Louis, MO
BT01239
20-08-00
Page
2
Jun 20/91
A14
Cj~echcraff BONANZA SERIES MAINTENANCE MANUAL
AIRPLANE FINISH CARE
ENVIRONMENTAL
MAINTENANCE
PRACTICES
After the specified curing period of new paint, avoid outside storage when conditions exist where moisture may collect on 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.
AIRPLANE FINISH CLEANING
´•´•´•11´•´•1 CAUTION
Since
paint
films do not obtain
hard
a
considerable time after
drying, airplanes that have been recently painted should not be polished or
finish for
a
WAXING AIRPLANE FINISHES
good coat of wax will protect the airplane finish from the sun’s rays and protect the surface against oxidation. Any good automotive polish or wax may be used. A
waxed until the finish has cured for at least 60
a
b. with
days. painted surfaces
Remove dust and dirt from
a.
with
cellulose sponge and cool tap water.
Remove oil and grease with
a
cloth
PLACARD REPLACEMENT
dampened placards must be in place and legible. Whenever airplane has been repainted or touched up after repairs, replace any placard that has been defaced or is missing.
All
naphtha.
the CAUTION i CIUnOK~I
URE~HANE PAINTS
airplane with mild soap and water, use special care to avoid washing away grease from any lubricated area. After washing the
When
wheel well
areas
points.
of
surfaces
lubricated
Ivory
or
NOTE
Any time the paint on the airplane is stripped for repainting, whether the repaint is to be on a localized area of the airplane or on the entire airplane, a thorough inspection for possible hidden corrosion should be conducted.
with solvent, lubricate
all lubrication
precautions
Remove insects with
c.
mild
the
washing
these
Premature
are
a
may not
wear
result
if
observed,
cellulose sponge and
a an extremely hard finish for protection against sandblast during takeoff and landings led to the development of urethane coatings for airplanes. Urethane paint dries to a high gloss and retains
The need for
Lux soap and water solution.
I"rU~1 CAUTION
color much better than standard finishes. It is unaffected by the chemicals in hydraulic fluids, deicer fluids and fuels and requires less care and maintenance than standard finishes.
Harsh soaps and detergents will damage the airplane finish. d.
Carefully
rinse
the
surface to
remove
ALL
soap. e.
NOTE After
Dry
the
FALLOUT(ACID RAIN)
cleaned
surface
thoroughly
chamois to prevent water marks.
with
a
any
placards
painting
repairs,
inspect
to ascertain that none have
been covered with
paint.
20-08-00 A14
Page 3 Jun 20/91
Ci~eechcraft. BONANZA SERIES MAINTENANCE MANUAL
URETHANE PAIN~ REPAIR PROCEDURES
The
normally required for urepaint to cure must be extended temperatures below 700F. The paint time
thane at
will
not cure
temperatures below
at
a
applications
working
brush
NOTE
60"F.
substitute will
finish with such or
while
require several stripper in with a stiff
the
wooden scraper.
Mask around the edge of the skin or skins a. containing the damaged area. Use a double thickness of heavy paper to prevent accidental splashes of paint stripper from penetrating the masking. b.
stripper as instructed by the Stay 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
Apply
urethane
manufacture.
This
airplane is finished with pretreatment (wash) primer, 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
the affected area with water.
maximum life.
CAUTION
Urethane
NOTE
stripe, numeral and letter pat-
Precut
terns are available
Rinse the
c.
NOT
USE
OF
ANY
good
pletely
clean.
Paint
be
must
removed from these surfaces with fine care not
to sand into
the material. Never use aluminum foil to
electrothermal
mask
during painting, eners
form
hydrogen
a
coating
on
shields. If metal cover
bright-
gas that eats away
the
as
an
anti-
electrothermal windare used,
brighteners
windshield
pasteboard masking
with
paper material.
or
Because of their resistance to chemicals and sol-
vents, urethane paints and
paint stripper. a
good
stripped
area
aluminum wool
surface with
a
as
f.
Thoroughly rinse fully dry the affected includes several joints
with clean water and of
care-
If the
stripped area skin laps, let the airplane
area.
sit until all moisture has dried. This may be accelerated by blowing the skin laps and seams with com-
pressed
air. Wet
masking
should be
replaced.
will combine with aluminum to
the stannous oxide used
static
windshields
for most metal
dry.
Bon Ami, Ajar, Comet cleaner, scouring will leave the surface com-
cleanser such etc. A
sandpaper, using
with water and
acetone, methyl
as
FIBERGLASS, NYLON OR COMPOSSURFACES.
area
Using a nylon scratch pad or dipped in clean water, clean the
STRIPPER
skin.
carefully with a solethyl ketone or lacquer thinner. This will prevent tiny particles of loose paint from adhering to the stripped area. Wash the
d.
vent such
TYPE FOR REMOVING PAINT FROM ITE
the
burn
e.
CAUTION
DO
contain
usually
or
gloves and eye protection when using stripper.
through Modagra-
PAINT
irritate
Wear rubber
fics of Kansas, 1720 S. 151 St. West, Rt. 1 Goddard Ks. 67052.
STRIPPING AND CLEANING URETHANE
strippers
acids that
primers require a special stripper is not available, stripper may be used. Removing the
If
enamel
a
urethane
PRETREATMENT
(WASH)
PRIMER FOR
URETHANE PAINT
etching primer (4, Chart 1) should be improve the adhesion of the finishing applied coats. A base primer (5, Chart 1) and catalyst (6, Chart 1) are used in equal parts as a pretreatment wash primer at the factory. An
acid
to
a.
Mix the
primer
as
instructed
by
the manufac-
turer.
20-08-00
Page
4
Jun 20/91
A14
BONANZA SERIES MAINTENANCE MANUAL
Apply a thin wet coat of primer. permitted to dry for at least an hour, b.
It should be
but not over six hours, before the next coat of urethane primer is applied.
eliminate the scratches left
Take is
Mix
instructed
the
urethane
Chart
primer 17,
1)
as
the manufacturer.
by
removing
Wash the sanded
e.
coarse
paper. metal than
more
any
with
area
Change often to sanding dirt will
cleaner
a
clean wash cloths be
picked
(2
or
so
8,
that
up.
up has been cleaned until all traces of discoloration are gone, apply a thin coat of pretreatment primer (4, Chart I) f.
a.
the
by
absolutely necessary.
Chart 1). all of the
URETHANE PRIMER
avoid
care to
After the
damaged
to the
to
area
be touched
area.
NOTE For the best results these directions
NOTE
carefully, for some manufacturers require that the primer be allowed to set for 1/2 hour after the catalyst and base have been mixed must be followed
while
others
after
use
recommend
If
metal conversion
a
iridite
or
alodine
primer coating
is
can
coating
be
immediate
a
mixing,
conversion
metal
wash
dispensed
is
primer
coating
available,
clean the surface to
Apply a coat of urethane primer with a spray gun using 35 to 40 psi of air pressure. A spotted appearance only indicates that the coat is thin. c.
If the initial
primer
primer slightly to roughen the surface and Wipe off the sanding dust with a cloth dampened with a cleaner (8, Chart 1), then apply the topcoat. adhesion.
paint
and
catalyst
Apply
the
topcoat with
a
as
instructed
by
the
spray gun at 35 to 45
psi of air pressure. Two coats are normally required to fully conceal the primer and build up the topcoat film necessary for adequate service life and beauty. The urethane finish will normally cure to approxi-
mately 85% of its full hardness peratures of 800F or higher.
Mask around the skin
h.
Spray
high tack damaged
d.
Do not
on
damaged
joint,
use an
paint strippers that may
immediate corrosive effect
magnesium and/or
faces.
Acid
base
strippers
are
and
aluminum some
not recommended.
if the
stripper
is not listed in the
sumable materials chart of this
edge use
of the a
fine
the
edge
of the
paint begins to fair into grade of sandpaper to
sur-
phenol
Consult the manufacturer for cautions
area.
When the
smooth
urethane topcoats.
WARNING
of
e. Using a coarse sandpaper, fair damaged area with the metal.
a
on two
I --´•~´•´•I
base
edges
meet
PAINT REMOVAL FROM MAGNESIUM SURFACES
paint by using a adhesive tape around the edge of the
Remove all loose
paint
If
cause
the
has cured for 24
PAINTING IMAGNESIUM
area.
b.
up
necessary, apply additional urethane until the juncture of old paint with metal is no visible.
gone.
in 24 hours at tem-
containing
primer
the indentation where the metal and old
URETHANE TOUCH-UP REPAIR a.
apply
After the urethane
g.
man uf actu re r.
b.
be touched
urethane
hours, sand the area under repair with medium fine sandpaper. Sand the edge of the repair area until
primer longer
URETHANE TOPCOATS Mix the
no
area.
is
a.
but
carefully
topcoat is applied,
sand the
assure
with.
primer (7, Chart 1) to the bare metal. This should produce a satisfactory undercoat for the repair and
coat is allowed to cure for
than 24 hours before the
as
wash
If the metal has not been treated with
b.
more
such
the
used,
conman-
ual.
a. more
Mask
areas
not
thicknesses of
being stripped with two or masking tape and aluminum 20-08-00
Page A14
5
Jun 20/91
~i3eechcraft BONANZA SERIES MAINTENANCE MANUAL
foil to prevent accidental
the b.
spillage
from
exposure to high concentrates of vapor may irritate the eyes and lungs.
penetrating
masking. Apply paint stripper (27, Chart 1, 91-00-00) to being stripped with a brush or non-
the surface
atomizing gun.
plane paint loose remain
strippers
on
are
with
the
allowed to
neutralized with surface being stripped must be thoroughly dry before any application of the stripper. Magneslum surfaces are treated at the factory with a brown to amber Dow #19 primer coat. Any magnesium surfaces not displaying this color should be resprayed with a primer coat before application of paint. Most
to remain
on
the air-
for 20 to 30 minutes, then work the
NOTE
water;
paint stripper
Allow the
c.
bristle brush. The
a
airplane
dry
remaining stripper may
for 2 hours but must not be
the surface.
on
the
therefore,
1 Never
use a
wire brush when remov-
from
ing paint it may
CAUTION
cause
magnesium damage to
surfaces for the surface.
masking paper and wash the area thoroughly with water under high pressure. Remove all remnants of paint with lacRemove
d.
the
affected
NOTE Dow #19 is used in the field to restore the original anti-corrosion surface treatment that may have been penetrated in service. The chemicals for Dow #19 formula may be purchased from a BEECHCRAFT Authorized Outlet in powder form or may be procured
locally 1. water in
gallon
and
produced
as
quer thinner.
PAINTING MAGNESIUM SURFACES
NOTE
Any time an airplane is repainted, inspect all placards to assure that they are not covered with paint, are easily readable, and are securely attached.
follows:
approximately 3/4 gallon of distilled plastic container which will measure one
Place a
of fluid. The water should be at
a
tempera-
2.
Add
3.
Add 1
1-1/3 oz.
oz,
(H2CT04)´• sulphate (CaS04)to
of chromic acid
of calcium
Prepare
a.
ture of between 70"F and 90"F.
the surface to be
SURFACES. with
the water.
lacquer
Clean thinner
the
water and
Apply
liberal
a
corrosion resistant
I
coating
of
after
assembly. Any
ings which will bearings shall
epoxy-based
primer.
unreduced corrosion
thoroughly
or grease holes in the cast-
receive be
zinc
bushings
coated
chromate
with
or
wet,
primer
or
preventative compound
at
the time of installation.
w,,,, WARNING
Stripping should be accomplished in a well ventilated area, since prolonged
area
equivalent solvent.
will come in contact with oil
dry by
exposure to hot air blast, 7.
indi-
Unprimed areas of magnesium castings are to be coated with MIL-M-3171 corrosion preventative compound (28, Chart 1, 91-00-00) unless these areas
Brush the solution in and around the bare surfaces of the magnesium, keeping the area wet with the solution for one to three minutes to produce a brown film. Do not exceed three minutes.
running
as
NOTE
5.
Rinse with cold
affected
or an
4. Add distilled water to make one gallon of solution and stir vigorously for at least 15 minutes.
6.
repainted
cated under PAINT REMOVAL FROM MAGNESIUM
b. tative
Prime the affected
compound
and
area
apply
with corrosion preventhe urethane topcoat.
20-08-00
Page 6 Jun 20/91
A14
Ci3~echcraft BONANZA SERIES MAINTENANCE MANUAL
NOTE
a.
application of the primer base, the magnesium surface should be thoroughly dried. Drying may be accomplished by subjecting the magPrior to
nesium to
b.
hour. Allow
a
minimum of four hours
time between
application
of the
and topcoat.
propeller
blades
instructed
as
by
the pro-
SURFACES SUSCEPTIBLE TO MUD AND SPRAY coat of white epoxy
paint
to the
following
areas:
a.
b. c.
nose
landing
Interior surface of Main and
nose
gear wheel wells.
landing
gear doors.
following
areas
landing gear
assemblies.
kept free from paint:
Fright
c.
Exhaust manifolds and exhaust stacks.
controls.
control cables and chains.
1. Aluminum parts attached firewall shall be primed in detail.
directly
to
the
Aluminum flexible conduit. All
tubing except unplated steel, which primer on the exterior, on
receive two coats of
shall
inte-
riors where the color scheme must be maintained, and except as note, on the interior of the engine
one coat
of
a
thoroughly
dissolved solution of
part Oakite No. 6 (13, Chart 1, 91-00-00) and two parts water to all rubber surfaces that are to into contact with metal
or
g.
Stall
h.
Chromium
i.
one
other rubber
sur-
faces.
warning
vane.
plated portions
magnesium parts and assembliss which are enclosed and subject to high humidity should be protected against corrosion by coating with either epoxy primer, MIL-C-16173 corrosion preventative compound, light grease or heavy oil (5, Chart 1, 91-00-00). Steel, aluminum
or
BATTERY BOX AND LID
Finish the interior of the
battery
box and lid
as
fol-
landing gear
Rubber and "rubberlike" surfaces.
j. Electrical wiring, unless otherwise noted specific requirement. k´• i. m. n.
ENCLOSED AREAS SUBJECT TO HIGH HUMIDITY
of the
tubes.
Glide path antenna
as a
(if installed).
Pitot mast and static buttons.
Cabin door sill and upper latch.
Utility
door
opening threshold (E-llll,
and after; EA-1 and
lows:
shall be
b.
piston
RUBBER SEALS
come
(57, Chart 1, 91-00-00).
compartment.
Main and
Apply
91-00-00).
Engine
f.
one
(2)
Epoxy-Polyamide
coats of Matterhorn White ure-
No. 6160
paint
of
Chart 1,
a.
e.
manufactures owner’s manual,
Apply
two
(56,
Firewalls and wrought aluminum surfaces forward of the firewall, with the following exception:
PROPELLER BLADES
peller
coats
d.
SPECIAL PROCEDURES
Paint the
(2)
two
PAINT FREE AREAS
The
1300 to 140"F for
drying primer
Apply
thane
elevated temperature of a minimum of one
an
Apply
Primer per MIL-P-23377
E-1241
after).
overhead console escutchharness escutcheon, lower utility ,,,1 door escutcheon, window latch escutcheon, OAT escutcheon, ignition panel escutcheon, circuit o.
Window
moldings,
shoulder
breaker panel escutcheon, upper utility door latch escutcheon, wing bolt cover escutcheons, and sidewall air valve escutcheons.
surfaces subject to rotation or slidelevator trim tab linkage joints.
bearing
p.
All
ing,
such
as
q. All exterior placards. See manual for placard locations.
Chapter
II
in this
20-08-00
Page A14
7
Jun 20/91
BONANZA SERIES MAINTENANCE MANUAL
RECOMMENDED MA TERIALS
CORROSION
DESCRIPTION
Corrosion is the
gradual eating away
of material
by
chemical action,
Corrosion may develop at areas where the proteccoating has been damaged. When this hap-
tive
pens, it is important to restore the protective coating. Corrosion also occurs when dissimilar metals in
moisture
present. High any humidity, high levels of environmental impurities (such as salt spray, acid rain, exhaust deposits, or chemical fumes), or high ambient temare
levels
contact
with
of
peratures
will increase the rate of corrosion. Some
of the more common
types
of corrosion
are
surface
corrosion, intergranular corrosion, pitting, exfoliation, and electrolytic or galvanic corrosion.
The recommended materials listed in Chart 1
in these charts have been tested and
The als
galvanic
series shown below shows which met-
attacked when in contact with
are
metal. The wider the
separation
a
PRODUCTS WHICH CONFORM TO THE REQUIREMENTS
BE
USED
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 resposibility of the or
of
mechanic to determine the current
applicable specification prior
the
to
usage of the product listed. This can be done by contacting the vendor of the product to be used. CORROSION
MAINTENANCE PRACTICES
damage requires inspection to determine depth of penetration and the cross-sectional area change. The 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 and refinished treated as applicable. In all instances, good preventive maintenance and reguCorrosion
the
alloys 5052, 5056, 5356, 6061, 6063
All other aluminum
MAY
CORROSION CONTROL
Magnesium alloys Aluminum
SPECIFICATION
corro-
corroded end of series
or
A
OF
EVEN THOUGH NOT INCLUDED IN THE CHART.
dissimilar
in the series, from
the top to the bottom, the faster the rate of sion. A partial galvanic series list follows:
Anodic,
for
cations. GENERIC OR LOCALLY MANUFACTURED
revision
(FIGURE I)
approved
aviation usage by Beech Aircraft Corporation, by the vendor or compliance to the applicable specifi-
technician
GALVANIC CORROSION
as
meeting federal, military or vendor specifications are provided for reference only and are not specifically required by Beech Aircraft Corporation. Any product conforming to the specification may be used subject to availability. The products included
alloys
Zinc
Cadmium
lar
Lead
cleaning
will be the most effective corrosion
con-
trol. Tin
following solvents may be used to remove grease, oil, stains and other surface contaminants on most materials. The
Steel
Copper alloys Specification
Product
Nickel
alloys
Titanium
Cathodic,
or
protected end
num
alloys
corrode when
in
example:
alumi-
with
steel;
contact
steels corrode when in contactwith copper.
A14
0-T-634
Perchloroethylene
O-T-236 TT-T-548
Toluene
of series
Note that corrosion is relative. For
Trichloroethylene
TT-X-916
Xylene
Methyl ethyl
ketone........... TT-M-261
Dry cleaning
solvent
...........P-D-680
20-09-00 Page 1 Jun 20/91
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
TABLE I GALVANIC COUPLES EMP
METALLURGICAL CATEGORY SOLID
GOLD,
AND T
O
+0.05
GRAPHITE
RHODIUM:
3
SILVER
SOLID
OR
PLATED:
HIGH
4
NICKEL,
SOLID
OR
PLATED;
MONEL;
R
ALLOYS:
SILVER HIGH
ALLOYS
NICKEL-
COPPER, SOLID OR PLATED; LOW BRASSES OR BRONZES; SILVER SOLDER; GERMAN SILVER; HIGH COPPER-NICKEL ALLOYS; NICKEL-CHROME ALLOYS; AUSTENITIC STAINLESS STEELS (301, 302, 304, 316 321 347) 309
6
COMMERCIAL
7
HIGH
8
18% CHROMIUM 0- 3
9
CHROMIUM,
YELLOW AND
BRASSES
BRONZES;
TIN-PLATE
II
LEAD
PLATED;
12
ALUMINUM,
13
IRON,
14
TYPE CAST 15
OR
PLATED; T
12%
OR
OF
-0.20
-0.25 MUNTZ
CHROMIUM
-0.30 -0.35 -0.45
410
TIN-LEAD HIGH
ALLOYS
GRAY,
BRASS,
RESISTANT STEELS
ST
PLATED
WROUGHT
WROUGHT,
1 ALUMINUM,
NAVAL
TIN,
TERNEPLATE:
SOLID
AND BRONZES
TYPE CORROSION 6 -RES
10
O
-0.15
TITANIUM
5
BRASSES
PERMISSIBLE COUPLES*
+0.15
GOLD-PLATINUM
PLATED;
2
C
(VOLT
LEAD THE
SOLDERS
-0.50
ALLOYS
-0.55
DURALUMIN
MALLEABLE;
-0.60
PLAIN
-0.70
ALLOYS OTHER THAN DURALUMIN; 7075, 5052, 5056, 1100, 3003. ALLOYS OF THE SILICON TYPE 355 356. WROUGHT
-0.75
6061,
1 ALUMINUM,
THAN SILICON
TYPE;
PLATE: GALVANIZED STEEL ZINC-BASE DIE CAST ALLOYS;
ZINC-
-1.10
OR
-1.60
CAST
16
HOT-DIP-ZINC
17
ZINC
18
MAGNESIUM
WROUGHT; AND
ALLOYS
OTHER
MAGNESIUM-BASE
ALLOYS CAST
-0.80 -1.05
OF GROUPS CONNECTED BY LINES ARE CONSIDERED AS PERMISSIBLE COUPLES; THIS SHOULD NOT BE CONSTRUED AS BEING DEVOID OF GALVANIC ACTION. PERMISSIBLE COUPLES REPRESENT A LOW GALVANIC EFFECT. INDICATES THE MOST CATHODIC MEMBER OF THE SERIES. AN ANODIC MEMBER, AND THE ARROWS INDICATE THE ANODIC DIRECTION. REFER TO TABLE II, MIL-STD-I86, FOR GROUP AMPLIFICATION OF GALVANIC COUPLES.
MEMBERS
HOWEVER,
o
**TAKEN
FROM
MIL-STD-1250(MI),
31
MARCH
1967
2000-slo-*a
Galvanic Coupies List
Figure 1 20-09-00 2
Page
Jun 20/91
A14
~S3eechcraft BONANZA SERIES MAINTENANCE MANUAL
CHART 1 RECOMMENDED MATERIALS
MATERIAL
SPECIFICATION
Coating
1.
PRODUCT
MIL-C-5541
VENDOR
Alodine 1200
Amchem Products Inc.,
Garden St., Ambler, PA 19002
Spring
Amchem Products Inc., St. Joseph, MO 2.
MIL-P-23377
Primer
Epoxy
Primer
Ameron Industrial,
Coatings Div., P.O. Box 2153, Wichita, KS 67201 3.
MIL-M-10578
Rust Remover
8T01237
VV-K-211
Kerosene
ute
of parts may be used when the
Vapor degreasing proper equipment
chlorides
titanium. Do
on
any solvents in
aluminum
areas
close
system,
similar metals
as
well
cleaner with
to corrosion in
are
corrosion num
alloy
by
as
all cracks and sheet
laps. thoroughly compressed air.
soft brush. Rinse
dry
with
WARNING
are
several methods. Most aircraft alumi-
sheet have
a
thin
Always wear rubber gloves and protective clothing when working with acids. A face mask may be necessary,
of pure at the mill. Other alumi-
cladding layer
(ALCLAD) applied alloy parts may be protected with an anodic coating system or a chromate treatment. Many steel parts are protected by cadmium plating. Most parts have protective primer. aluminum num
ALUMINUM CORROSION REMOVAL Corrosion may be removed
mechanically
or
chemi-
cally.
cles that could
depending upon ventilation in the area. if acid accidentally contacts skin or eyes, immediately flush with fresh water and seek medical advice.
REMOVAL OF CORROSION FROM ALUMINUM SURFACES a.
In mechanical removal, it is essential that the abrasive materials
on
the tool leave
on
no
residue
or
parti-.
future corrosion. An abrasive ferrous metals will contain min-
cause
previously used
A14
a
with clean water and
subject g ni-parts y ra v protected degrees. against Aircraft
corrosion is best removed or aluminum
On clad aluminum alloys, use a chemical alkaline cleaner. Mix and store alkaline solutions in plastic, stainless steel, or glass containers. Mask off all dis-
composites,
CORROSION PROTECTION metals
alloy parts,
with aluminum oxide abrasive paper
Apply
common
alloys
of corrosion. A steel wire
wo l.On
to the oxygen
All
cycle
I w-´•~´•´•I use
use
new
brush used on aluminum alloys will leave tiny particles sufficient to initiate corrosion of the aluminum.
not use exotic solvents on
Do not
a
is available,
WARNING
Do not
which will imbed in aluminum
particles
and start
Strip all paint from the surface
u"de’
STRIPPING
PAINT in
Chapter
AND
CLEANING
as
directed
URETHANE
20-08-00.
b. Mechanically remove rubbing as necessary.
corrosion
by sanding
or
20-09-00 Page 3 Jun 20/91
CJT)eechcraR BONANZA SERIES MAINTENANCE MANUAL
the surface
Inspect
c.
sufficient
material
carefully to ensure that to satisfy structural
any such
remains
dry without
that
materials
washed.
being
requirements. Clean the corrosion d. chemical alkaline cleaner.
removed
with
area
I
a
Treat all aluminum surfaces with MIL-C-5541
e.
in the Alodine solution.
Rinse the treated
water and
dry
in an oven
area
in COLD
by exposure
or
running
They should be immediately after use. If such are left to dry in the open air,
washed
to hot air
items
blast,
they could NOTE If cold
available,
and the
a.
area
Strip
all
paint from
the
surface
directed
as
under PArNT REMOVAL FROM IWAGNESIUM SUR-
stated above.
as
create a fire hazard.
MAGNESIUM CORROSION REMOVAL
water is not
running rinsing may be eliminated dried
I
Brushes and cloths should not be left
(1, Chart 1). 1.
WARNING w-.,.,
FACES. 2.
minimum of 30 minutes
Brush 2 coats
(a apart) of epoxy primer (2, Chart 1) on and around the reworked area. Assure adequate penetration of primer into the treated area.
Mechanically remove corrosion by sanding or rubbing as necessary. If sanding, use aluminum sandpaper. Start with 240 grit and finish with 400 grit.
ALUMINUM CORROSION TREA TMENT
sufficient
b.
c.
the surface
Inspect
material
carefully to ensure that to satisfy structural
remains
requirements. After corrosion removal and surface
als
should
be
given
protective
cleaning,
met-
treatment
and
painted. Alodine treatment of aluminum alloys forms protective coating which resists corrosion and provides a good surface for adhesion of the paint primer. a
Alodine 1200, 1200S, 1201 (1, Chart 1), or equivalent, when mixed 2 ounces per gallon of water, will be an 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 epoxy polyamide primer (2, Chart l)and allow to dry.
d.
ethyl
Clean the corrosion removed ketone or naphtha.
e´• Apply corrosion magensium.
area
treatment to the
with
methyl
unprotected
MAGNESIUM CORROSION TREATMENT
Any
bare
magnesium component which will be should be lightly sanded to any oxide coatings and coated with Dow
returned to service remove
#19 formula. The chemicals for Dow #19 formula may be purchased from a BEECHCRAFT Authorized Outlet in
powder duced a.
form
as
or may be follows:
Place
water in
a
procured locally
approximately 3/4 gallon plastic
container which will
nofofluid. llag.F009
distilled
of
measure one
The water should be at
CAUTION
and pro-
a
tempera-
ture of between 70"F and
Keep the Alodine solution confined the
affected
cracks
and
area.
Mask
or
seal
to
all
crevices, all steel parts, mechanical components.
and any Wash all brushes and cloths immediafter
use to prevent inadvertent ately contact with the acid solution and to
eliminate
a
possible
fire hazard from
b.
Add
c.
Add 1
1-1/3 oz.
oz.
of chromic acid
of calcium
(H2CT04)´•
sulphate (CaS04)
to the
water.
d.
Add distilled water to make
tion and stir e.
vigorously
one
gallon
of solu-
for at least 15 minutes.
Brush the solution in and around the bare
faces of the
magnesium, keeping
the
area
sur-
wet with
20-09-00
Page
4
Jun 20/91
A14
Cil)eechcraR BONANZA SERIES MAINTENANCE MANUAL
the solution for one to three minutes to produce brown film. Do not exceed three minutes, f.
Rinse
with
cold
running
water
and
a
dry by
Apply solution
to the corroded area
resistant brush. Allow to stand
thoroughly
using
one
rinse with hot water and
an
acid-
minute, then
wipe dry.
exposure to hot air blast. g.
Apply
a
sion resistant
liberal
coating
of epoxy based
I
corro-
primer.
Always STEEL CORROSION REMOVAL
tective rust
Remove corrosion from steel parts by mechanical means. Use a steel wire brush, a steel scraper, steel wool, or 400-grit abrasive paper.
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 I)with one part of clean water in a stainless steel, plastic or glass container.
wear
WARNING
rubber
clothing
removal.
when A
I
gloves working
face
mask
and prowith with
may be
depending upon ventilation in the area. If acid accidentally contacts the skin or eyes, immediately necessary,
flush with fresh water and seek medi-
If acid
cal advice. In most cases, steel that has been cleaned shall be treated with a minimum of one coat of epoxy primer
(2,
Chart
1)
to
protect against future corrosion.
20-09-00
Page A14
5
Jun 20/91
CHAPTER
AIR
CONDITIONING
BONANZA SERIES MAINTENANCE MANUAL CHAPTER 21
ENVIRONMENTAL SYSTEMS
TABLE OF CONTENTS SUBJECT
PAGE
21140-00
Heating and Ventilating System Description Cabin Heating Heater and Defroster Operation
and
Operation
1
1 1
Cabin Ventilation
1
Pilot’s Fresh Air Ventilation Overhead Fresh Air Ventilation Cabin Air Exhaust Fresh Air Blower
1 1 1 1
Heating and Ventilating Maintenance Practices Inspection of Heating and Ventilating System 100-Hour Inspection of Heating and Ventilating System 100-Hour Inspection of The Exhaust System Heater Removal (F33A, F33C, V35B and A36) Heater Installation (F33A, F33C, V35B and A36) Heater Removal (A36TC and B36TC) Heater Installation (A36TC and B36TC) Heater Pressure Testing
7 7
7 7
7 7 7
7 8
Fresh Air Blower Removal
10
Fresh Air Blower Installation
10
21150100
Cooling Description and Operation (Effectlvlty: Optional) (Effectivity: All serials except E-2104, E-2111 and after and except EA-320, (Effectivity: Serials E-2104, E-2111 and after, EA-320, EA-389 and after) Troubleshooting
Air-Conditioning System (Effectlvlty: Optional)
Maintenance Practices (Effectivlty: Maintenance Of Air-Conditioner Precautionary Service Measures Air-Conditioning FunctionalTest
Cooling
Optional)
1
EA-389 and
after)
1 2 4 5 5 5 5
System Leak Detection Compressor Belt Removal Compressor Belt Installation Compressor Belt Tension Adjustment Compressor Mounting Torques Compressor Belt Pulley Alignment
7
Condenser Removal
8
Condenser Installation Condenser Control Rigging
8
Condenser Condenser
7 7
7 7
8
Uplimit and Downlimit Rigging Flight-Extension Limit Rigging
Compressor Removal Installation and Alignment
7
8 8 9
of
Compressor
9
21-Contents A18
Page 1 Aug 18/95
aeechcraft BONANZA SERIES MAINTENANCE MANUAL CHAPTER 21
ENVIRONMENTAL SYSTEMS
TABLE OF CONTENTS SUBJECT
(Continued) PAGE
Ventilation Blower Removal
11
Ventilation Blower Installation
11
Evaporator Evaporator Evaporator
Removal
12
Installation
12
Filter
12
Replacement
21 -Contents
Page
2
Aug 18/95
A18
aeechcraft BONANZA SERIES MAINTENANCE MANUAL CHAPTER 21
ENVIRONMENTAL SYSTEMS
LIST OF PAGE EFFECTIVITY CHAPTER-SECTION-SUBJECT
21-Etfectlvity
PAGE
DATE
1
Aug 18/95
1
Aug 18/95 Aug 18/95
21-Contents 2
21-40-00 1 2 3 4
5 6 7
8 9 10
Oct 16192 oct 16/92 oct 16/92 Oct 16/92
Oct 16/92 Oct16/92 oct 16/92 Oct 16/92 oct 16/92 Oct 16/92
21-50-00 1 2
3 4
5
6 7
8 9 10
11 12
A18
Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug
18/95 18/95 18/95 18/95 18/95 18/95 18/95 18/95 18/95 18/95 18/95 18/95
21-Effectivity Page 1 Aug 18/95
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
HEATING AND VENTILATING SYSTEM DESCRIPTION AND OPERATION (Figures 1,2,3,4 and 5)
CABIN VENTILATION In
moderate
temperatures, ventilation air
obtained from the in
ever,
heat exchanger connected to the right exhaust stack provides for heated air to five outlets in the forward and ah areas of the cabin. The two forward A
outlets are located above and forward of each set of The two aft outlets are installed rudder pedals. behind the right front seat and the right rear seat. The fifth outlet provides heated air for windshield
defrosting, In
flight,
can
desirable
extremely high temperatures, to pull the red FIREWALL AIR
be
heating by it
How-
may
be
control and
only the fresh air ventilation described in the following paragraphs. use
PILOT’S FRESH AIR VENTILATION A duct in each
wing root is connected directly to an adjustable outlet in the upholstery panel forward of each front seat. Airflow from each outlet is controlled
ram
air enters
through the heater air intake
and passes through the heater, then into a mixer valve on the forward side of the firewall. The heater air intake on Models F33A, F33C, V35B and A36 is from the right side of the nose. Models A36TC and B36TC have an airscoop on the left side of the engine compartment that furnishes air to the heater. In the mixer valve, the heated air is combined with a controlled quantity of unheated ram air picked up at the fresh air intake. The fresh air intake on Models F33A, F33C, V35B and A36 is in the engine rear baffle. The fresh air intake on Models A36TC and B36TC is from the right side of the nose. Air of the desired temperature is then ducted from the mixer valve to the outlets in the cabin. When the forward cabin control is in the cold
outlets used for
the CABIN HEAT control full forward.
pushing
CABIN HEA TING
same
position, unheated air circulates through
by
a
center knob.
The~direction of airflow is
trolled by rotating the louvered knob on the rim.
cover
con-
with the small
OVERHEAD FRESH AIR VENTILATION Fresh
ram
of the
air from the air intake
on
the upper side
aft
fuselage is ducted to individual outlets above each seat, including the optional 5th seat on Models F33A and V35B and the optional 5th and 6th seats on Models A36, A36TC and B36TC. Each outlet can be positioned to direct the Row of air as desired. The volume of incoming air can be regulated by rotating the outlet. A shutoff va’lve is installed in the I fresh air duct ah of the cabin compartment panel. I The valve is operated by turning a knob on the overhead panel.
the cabin.
CABIN AIR EXHAUST
HEATER AND DEFROSTER OPERATION The
heater controls
are
located
on
the
lower leff
pilot’s subpanel. To obtain heated air to the cabin outlets, pull the CABIN HEAT control. The control regulates the amount of cold air that is mixed with the air from the heater. When the control is pulled fully out, the cold air is directed overboard and only heated
air enters
located
on
the
cabin.
The
forward
the firewall forward of the rudder
deliver heated air to the forward cabin CABIN HEAT control is
pulled
out.
To
vents,
pedals,
when
the
provide heated
air to the aft seat outlets, pull out the AFT CABIN For maximum heat, the control is HEAT control.
pulled fully
out.
To obtain heated air for
defrosting
the windshield, pull the DEFROST control out. It may be necessary to vary or close the AFT CABIN HEAT control to obtain maximum air flow for
close off all air from the heater
defrosting. system, pull the
To red
FIREWALL AIR control located to the extreme leff of the
pilot’s lower subpanel.
Since the cabin is sealed, an air exhaust is required provide for circulation of cabin ventilation air. A
to
Cabin air outlet is installed in the cabin aft
panel
and is connected to
in the left side of the
an
upholstery
exhaust vent installed
fuselage.
FRESH AIR BLOWER
An optional fresh air blower may be installed on airplanes CE-941 and after, CJ-156 and after, D-10348, D-10364 and after, E-1809 and after and EA-192 and The fresh air blower utilizes the same ducts after.
and air outlets as the overhead fresh air system. The blower is located aft of the baggage compartment wall at the aft end of the overhead fresh air plenum. The blower’s circuit breaker/switch is located on the console
near
planes.
On
the fuel
mixture
lever
on
early
air-
and after, CJ-156 and E-1954, E-1988 and after and
airplanes CE-990
affer, D-10390 and after, EA-243, EA-273 and after, the circuit breaker/switch is located in the center of the
subpanel.
21-40-00
Page 1 A16
Oct 16~92
L
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
HEATER AIR INTAKE (NOSE)
MIXER VALVE (COLD POSITION
HEATER FRESH AIR INTAKE
(ENGINE BAFFLE) LEFT FORWARD
-HEATED AIR
"h
i
~R\ ~J
I
-OVERBOARD VENT
OUTLET FRESH AIR
1
Lln
~U
L
,RIGHT FORWARD OUTLET
(LEFTWING FRESH AIR
FIREWALL AIR
(RIGHT WING ROOT)
t
CONTROL OVERHEAD FRESH AIR SHUTOFF CONTROL DEFROSTER
I~H
CABIN
II
ni´•i
I
AFT OUTLET
I
(RIGHT FRONT SEAT)
/YJ
AFT CABIN HEAT CONTROL
INDIVIDUAL OVERHEAD FRESH AIR OUTLETS AFT OUTLET
t
(RIGHT REAR SEAT)
r;l
OUTrPTSj
-~-------CONTROL
CABLE
OPTIONAL 5TH AND 6TH SEAT
INDIVIDUAL OVERHEAD FRESH AIR
t
CABIN AIR OUTLET
CABIN AIR EXHAUST WATER DRAIN THROUGH
BOTTOM OF FUSELAGE
t
OVERHEAD FRESH AIR SHUT OFF VALVE OVERHEAD FRESH AIR SCOOP
(V35B) OVERHEAD FRESH AIR SCOOP
(F33A. F33C,
B
and
A36)
CE-831 AND AFTER. D-10200
AND AFTER AND E-1408 AND AFTER.
Heating
(CE-748,
and
Ventilating System
CE-772 thru CE-918, CE-920 thru CE-922, CE-924,
C9200100
CE-926 and CE-928; CJ-149 thru CJ-155; 0-10097, 0-10120 thru 0-10347; and E-llll, E-1241 thru E-1421, E-1423 thru E-1550, E-1552 thru E-1568, E-1570 thru E-1580 and E-1582
E-1593) Figure 1
thru
21-40-00
Page 2 Oct 16/92
A16
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
n/
HEATER AIR INTAKE
(NOSE)
FRESH AIR INT
(ENGINE BAFFLE) HEATER MIXER VALVE
(COLD
POSITI
OVERBOARD VENT HEATED AIR
FRESH AIR (LEFT WING
ROOT)
-I II
AIR
_t~
(RIGHT WING ROOT)
LEFT FORWARD OUTLET
RIGHT FORWARD OUTLET
FIREWALL AIR CONTROL DEFROSTER CONTROL
CABIN HEAT CONTROL
~SP
OVERHEAD FRESH AIR CONTROL
AFT CABIN HEAT CONTROL
AFT OUTLET (RIGHT FRONT SEAT)
AFT OUTLET (RIGHT REAR
SEAT)
INDIVIDUAL OVERHEAD
FRESH AIR OUTLETS
CONTROL CABLE
........i
OPTIONAL 5TH AND 6TH SEAT INDIVIDUAL OVERHEAD FRESH AIR OUTLETS
AIR SCOOP
(V35B)
CABIN AIR OUTLET CABIN AIR EXHAUST
rWATER DRAIN THROUGH BOTTOM OF FUSELAGE
F~--- ------I r------~
i
OVERHEAD FRESH AIR
OPTIONAL CABIN FRESH AIRBLOWER
g
SHUT OFF VALVE
OVERHEAD FRESH AIR SCOOP
(F33A.
F33C and
A-36)
CE-941 AND AFTER. CJ-156 AND AFTER, D-10348, D-10364 AND AFTER AND E-1809 AND AFTER. C9200101
Heating and Ventilating System (CE-919, CE-923, CE-925, CE-927, E-929 and after; CJ-156 and after; D-10348, D-10353 and after; and E-1422, E-1551, E-1569, E-1581, E-1594 thru E-1945, E-1947 thru E-2103, and E-2105 thru E-2110)
Figure
2
21-40-00
Page A16
3
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL OVERBOARD
VENT~
(NOSE)
HEATER AIR INTAKE
MIXER VALVE
(COLD POSITION)
FRESH AIR INTAKE
I
I
HEATER
(ENGINE BAFFLE) HEATED AIR RIGHT FORWARD OUTLET
LEFT FORWARD OUTLET
FRESH AIR INLET
I
(RIGHT WING ROOT)
FRESH AIR INLET
(LEFT WING ROOT)
OVERHEAD FRESH AIR DEFROST DUCT OUTLET
CONTROL
FIREWALL AIR CONTROL AFT OUTLET
ln\ H/ I"
CABIN HEAT CONTROL
I
(3RD
a 4TH
SEATS)
AFT CABIN HEAT CONTROL
DEFROSTER CONTROL
AFT OUTLET
(5TH
6TH
SEATS)
INDIVIDUAL OVERHEAD FRESH AIR OUTLETS
CONTROL CABLE
CABIN AIR OUTLET
OVERHEAD FRESH AIR
SHUT OFF VALVE CABIN AIR EXHAIIST-’
I
I I
I
OPTIONAL CABIN
FRESH AIR BLOWER WATER DRAIN THROUGH
BOTTOM OF FUSELAGE
(gZ
~Rf
OVERHEAD FRESH AIR INLET
C9200102
Heating and Ventilating (E-1946, E-2104 and E-2111 and after) Figure 3
21-40-00
Page 4 Oct 16/92
n16
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL EXHAUST GASES FROM ENGINE
(RIGHT SIDE ONLY)
(NOSE)
FRESH AIR INTAKE
HEAT EXCHANGER
HEATER HEATER AIR INLET
AIR EXHAUST
AIREXHAUST AIR-SCOOP
,111
(OUTLET BELOW)
´•e
MIXER VALVE
MIXER VALVE
FRESH AIR
-e
I~Llt
EXHAUST GASES TO
(LEFT WING ROOT) t
LEFT FORWARD OUTLET
FRESH AIR
(RIGHT
DEFROST OUTLET
WING ROOT)
TURBOCHARGER AND OVERBOARD
’RIGHT FORWARDOUTLET
FIREWALL AIR CONTROL ~b63F
DEFROSTER CONTROL CABIN HEAT CONTROL AFT CABIN HEAT CONTROL
I
//II
I I IIL~---E- AFT OUTLET
(RIGHT FRONT SEAT)
INDIVIDUAL
FRESH AIR OUTLET
I
YU 2C~----t 111 I
INDIVIDUAL OVERHEAD FRESH AIR OUTLETS AFT OUTLET
(RIGHT
REAR
SEAT)
24
CABIN AIR OUTLET
II OVERHEAD FRESH AIR SCOOP
CABIN AIR EXHAUST
a
WATER DRAIN THROUGH BOTTOM OF FUSELAGE
j
~EPI-BANDAFIER
CP2W1(13
Heating and Ventilating (EA-1 thru EA-20, EA-22 thru EA-21 and EA-29 through EA-32) Figure 4 21-40-00
Page Ale
5
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE WIANUAL FRESH AIR INTAKE
(NOSE)
EXHAUST GASES FROM ENGINE
(RIGHT SIDE ONLY)
HEATER MUFF EXHAUST GASES
I
TO TURBOCHARGER--\
I
(/-AIREXHAUST
AND OVERBOARD
MIXER VALVE HEATER AIR INLET RIGHT FORWARD OUTLET c
LEFT FORWARD OUTLET~II
c
FRESH AIR INLET
FRESH AIR INLET
r
(LEFT WING ROOT)
(RIGHT
WING
ROOT)
OVERHEAD FRESH AIR
DEFROST DUCT OUTLET
CONTROL
AS
FIREWALL AIR CONTROL AFT OUTLET
CONTROLI//
DEFROSTER
I
/n\
r-´•-T- (3RD
4TH
SEATS)
CABIN HEAT CONTROL
AFT CABIN HEAT CONTROL
AFT OUTLET
(5TH
INDIVIDUAL OVERHEAD
g 6TH
SEATS)
i
FRESH AIR OUTLETS
I
t~
CONTROL CABLE
CABIN AIR OUTLET
OVERHEAD FRESH AIR SHUT OFF VALVE CABIN AIR EXHAUST--/ WATER DRAIN
THROUGH~
j(
I
I
(Ba
OPTIONAL CABIN FRESH AIR BLOWER
BOTTOM OF FUSELAGE
OVERHEAD FRESH AIR INLET
~EA-21. FIREWALL AIR CONTROL
EA-28. EA-33 THRU
EA-319. EA-321 THRU EA-388.
CABIN HEAT CONTROI.
EA-320, EA-389
ANO AFTER
AFT CABIN HE*~ CONTROL EA-192 AND AFTER
OEFROSTERCONTROL~’
~DETAIL
A
C92o010~
Heating and Ventilating (EA-21, EA-28, EA-33 and after) Figure 5
21-40-00
Page
6
Oct 16/92
A16
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
MAINTE-
HEATING AND VENTILATING NANCE PRACTICES
INSPECTION OF HEATING AND VENTILATING SYSTEM
Inspect the air intake ducts leading to the heater; check all clamps and connections for tightness and Check the duct for the duct for holes and cracks. Check the internal restrictions and/or collapsing. screen at the intake duct; remove and clean as nec-
H~ArrR INSTALLATION AND A36) a.
cabin
and
heat
outlets.
Seal
cables
or
or
tape
heater
shroud
and
retaining
b.
install the heater in the
c.
Connect the
engine
airplane.
exhaust
to the
system
heater.
Inspect the heater control box for full stop-to-stop travel and proper sealing of the valve. Inspect the condition of the air ducts leading to the windshield
openings around wires, tubes, through the firewall.
the
screws.
essary.
defroster
Install
V35BJ
(F33A. F33C,
d.
Connect the heater ducts to the heater.
e.
Install the heater
HEATER REMOVAL
access
panel.
I
836TCJ
AND
(A36TC
passing Remove the heater
access
b.
Remove the heater
ducting.
c.
Remove four bolts
a.
panel from the
right side. Inspect around
the removable web
the lower half
on
leaks.
Openings, stringer cutouts, or cracks must be kept sealed with sealing compound (17, Chart 1, 91-00-00) between the bulkhead and the skin by removing the upper upholstery panel of the bulkhead. Also plug the leveling lug holes in the baggage doorframe to prevent entry of the
cabin
rear
bulkhead
for
the
on
heater which attach it to the exhaust
d.
of cold air.
Loosen the
clamp
right side system.
of the
the left side of the
on
heate r.
100-HOUR INSPECTION OF HEATING AND VENTILA TING SYSTEM
the
heater
through
the
e.
Remove
f.
Remove the heater shroud from the heater.
access
hole. Check for corrosion, cracks
clamps,
loose
obstructions.
sealing
loose
Check for
or worn
areas
in
ducts,
missing fasteners or proper operation, travel and or
Pressure test the heater g. HEATER PRESSURE TESTING in this
of valves,
100-HOUR INSPECTION OF THE EXHAUST SYSTEM
INS TALLA TION
HEA TER
as
indicated
(A36TC
B36TC) Check per POWER Chapter 5-20-00.
PLANT
REMOVPIL nLIVIVVnL
F33C, jF33A, (I
Remove the heater
a.
EXHAUST SYSTEM
access
V35B vu~u
nlru
panel from the
Remove both heat ducts from the heater.
a.
Install the heater shroud
b~
Installthe
c.
Tighten
on
system
Disconnect the and
remove
heater from the
it from the
exhaust
the heater.
heaterthroughthe accesshole
the
clamp
on
the left side of the
heater.
d.
Install the four bolts
on
the
heater which attach it to the exhaust c.
AND(
in
right side. b.
in
Chapter.
to 100 to 110
right side of the system. Tighten
inch-pounds.
airplane.
Remove the screws from the heater shroud d. and slide the shroud off the heater,
e.
Install the ducts to the heater.
f.
Install the heater
access
panel. 21-40-00
Page A16
I
Oct 16/92
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
HEA TER PRESSUR~ T~STING The heater should be which
could
inspected for cracks and leaks
introduce
carbon
monoxide
into
the
heating system. On
all
(EA-1 hours
any leaks are apparent, replace the heater. This test is also recommended for the heater at every engine
Bonanzas
and
except after), perform a
and
planes, pressurize the heater to 25 psig. On A36TC and B36TC, pressurize the heater to 5 psig. Pressurize the heater with air or nitrogen and either immerse in water or "paint" with a soap solution. If
pressure test
the
turbocharged models inspection each 100
change.
visual
each 500 hours.
NOTE
On the
turbocharged models (EA-1 and after), visually inspect and pressure test each 100 hours. The pressure test can be accomplished as follows:
The
heat transfer
internal
place for a.
Remove the heater
as
indicated in HEATER
baffle a
warpage is
studs
and/or
correct cause
along
cone
with
must
supply of heat. for replacement.
the
be
in
Any
REMOVAL. b.
Itest
Inspect
for leaks.
the heater
On
F33A,
visually and
pressure F33C, V35B and A36 air-
If the inspection indicates a good heater, c. reinstall the heater as indicated in HEATER INSTALLATION.
21-40-00
Page
8
Oct 16/92
Ale
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
A
DUCT TO AIR INTAKE
ADAPTER
MOUNTING BRACKET NUT
SCREW
(4)
’Be SCREW (4)
WASH\ER (3) DUCT TO
OVERHEADOUTLETS
NUT
SPACER
WASHER (3) CLAMP
d SAFETY
CLAMP(2)/ A~ ~I(
SPACER
(2) OWER
SCREW BOLT
OETIIL
A~
~ETAIL
CE-941 THRU CE-1555; CJ-156 THRU CJ-179; D-10348, D-10364 THRU D-10403; E-1809 THRU E-2592; EA-192 THRU EA-514.
A~
I~
CE-1457 THRU CE-1555, E-2532 THRU E-2592, EA-505 THRU EA-514.
[4)
SAFETY CLAMPS AND SAFETY WIRE INSTALLED PER SERVICE BULLETIN NO. 2380.
CE-1556 AND AFTER, E-2593 AND AFTER, EA-515 AND AFTER.
C9200124
Fresh Air Blower Installation
Figure
6
21-40-00
Page A16
9
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
FRESH AIR BLOWER REMOVAL
FRESH AIR BLO WER INS TALLA TION
(Figure 6)
(Figure 6)
a.
Remove
the
fifth
and
sixth
seats
when
a.
installed.
screws
Place the blower in
attaching
the
position adapter and
and install four blower
to
the
mounting bracket. b.
Remove the cabin
c.
Disconnect the electrical connector.
d.
Remove the
rear
upholstery panel. b.
c.
clamps securing the ducts
to
through
Connect the air ducts with
clamps.
Install the screw, or boit(s), and nange and brackets.
spacer(s)
the blower
the fan inlet and outlet. e.
Remove the
comply with Service f.
safety wire from airplanes that
Bulletin No. 2380.
Remove the
screw (or bolt/bolts) through flange and mounting bracket. Observe spacer and washer installation so they can be installed in the original locations.
the blower
d. Blowers that have the safety clamps must safety wired. Use a minimum of three strands of .041-inch safety wire looped through the safety clamps. The safety wire should be installed with a slight tension and each strand should have equal be
tension.
Remove four screws through the adapter, g. mounting bracket and the blower housing. Remove the blower from the airplane.
e.
Connect the electrical connector.
f.
Install the
g.
Install the fifth and sixth seats if used.
rear
upholstery panel.
"END"
CONTINUEB
21-40-00
Page 10 Oct16/92
A16
aeeca~craft BONANZA SERIES MAINTENANCE MANUAL COOLING DESCRIPTION AND OPERATION (EffectSvity: Optional) optional air-conditioning system is a recirculating 12,000-BTU cooling system. The air-conditioner is
The
wired
through
the
right landing gear upiock position
switch, the left landing gear safety switch, and the
nor-
mally closed full throttle switch. With the airconditioner operating on the ground, the control circuit is wired through the left landing gear safety switch, which fully opens the condenser air scoop door located under the airplane. With the gear extended and the throttle fully opened, action of the full throttle switch will
remove
power from the compressor clutch
coil, and drive the condenser air scoop door closed.
landing gear is retracted, power is transmitted from the normally open contacts of the full throttle switch (actuated closed when the throttle is fully open), through the right landing gear uplock-position switch (actuated closed when When the
airplane
is airborne and the
the gear is up and locked) to the condenser air scoop door actuator. Power is then conducted through the
flight-position-limit switch located at the end of the door (actuated closed when the door is closed), causing the actuator to open the door to the Right position. When the door flightposition-limit switch is actuated, the power is then normally open
contacts of the door
directed to the compressor clutch coil,
light, independent of the air-conditioner circuit, is by the condenser air scoop door, through the left landing gear uplock-position switch’s normally closed contacts (closed with the landing gear extended), which will indicate a door-open condition
A
actuated
while the gear is extended.
high-pressure-sensing switch monitors the presof the refrigerant from the compressor to the expansion valve. The normally closed high pressure switch will actuate, causing an open circuit to the com-
The
sure
presser clutch coil when the pressure in the line 10 psi, (340 ~t 10 psi on serials E-2121 reaches 390 and after; EA-320, EA-440 and after; CE-1030 and after) which disables the compressor. The high pressure switch automatically resets to the normally
closed
position
when the
pressure. There is also
valve, located
on
a
refrigerant falls to a safe high-pressurreppoppe relief
the forward side of the firewall,
which will relieve the system if the pressure reaches 450 psi, and will reseal again at 360 psi. The low pressure switch, closed when the system is senses
refrigerant line drops to a pressure low enough to indirefrigerant and/or oil loss (below 7 psi), the switch will open and prevent further operation of the compresser. When the refrigerant system is properly charged (approximately 7 psi or more), the switch will b,,,tivated closed allowing the compressor clutch cate
normally open (actuated charged with refrigerant)
system pressure. When the pressure in the
coil to be activated so the air-conditioner may operate. Th, purpose of the switch is to prevent damage to the compressor should oil and/or refrigerant loss occur. The condenser air scoop door under the airplane automatically opens when the air-conditioner is turned on´•
On the
ground, the door opens
to
approximately
3
flight, the door opens to approximately 3/4 inch. The air scoop door-actuator-limit switches
inches. In
1/2 are
preset; however if adjustment becomes
neces-
sary, refer to CONDENSER CONTROL RIGGING in
this
chapter.
The belt-driven compressor, which is coupled with a magnetic clutch, compresses the refrigerant to a high
pressure, high temperature gas. This gas passes the condenser where cooling air removes heat from the gas, condensing it to a liquid state. The
through
liquid
then passes
through the expansion valve
where
it is metered into the evaporator at a rate of 55 psi, (30 psi on serials E-2104, E-2111 and after; EA-320,
EA-440 and after;and CE-1037 and
liquid evaporation
allows most of the
after)
which
to return to a gas. The heat is absorbed from cabin air
required for passing over the evaporator coils. After passing through the evaporator, the refrigerant returns to the compressor at
a
reduced pressure.
A time
delay relay has been added to the compressor circuit at serials E-2104, E-2111 and after; U~-320, EA-440 and after; CE-1037 and after. The time delay
relay prevents the compressor from being energized a high head pressure exists, which would cause
while
unnecessary stress on the belt and other components. The time delay relay is located on the forward side of
the front spar
carry-through
on
the
right side
of the
airplane.
(Effectivity:
All Serials
except E-2104, EA-320,
E-2111 and after and except Cq-389 and after)
The optional air-conditioning system is controlled by a switch on the powerplant control panel and by both high- and low-pressure-sensing switches. The switch which controls the system is located on the powerplant control panel (console) and is placarded ArR
21-50-00 Al8
Page 1 Aug 18195
BONANZA SERIES MAINTENANCE MANUAL and are
placarded AIC OFF and BLOWER HI LO protect the
COND OFF HI LO. The system circuit breaker, located on the right hand subpanel, is placarded AJC
umn
CIR BKR.
system
The entire system is protected by a 15-amp circuit breaker. The compressor and condenser air scoop door are protected by two separate ti-amp fuses. The
panel. One circuit breaker (5 amps) protects the compresser wiring, while the other (15 amps) protects the blower wiring.
fuses are located front of the
on
the forward side of the firewall in
This allows the evaporator fan to after the compressor has been removed
copilot.
operated from the system by be
a
blown fuse.
Serials E-2104, 8-2111 and after, EA-320, t4-389 and after)
(Effectivity:
optional air-conditioning system is a recirculating cooling system. The two switches which control the system are located to the left of the pilots control colThe
and OFF. The two circuit breakers which are
located in the left sidewall circuit breaker
If the air-conditioner switch is in the A/C air-conditioner will
come on
position,
the
with the blower at low
speed, even if the blower switch is off; however, moving the blower switch from OFF or LO to HI will result in blower speed increasing to its maximum. With the air-conditioner switch off, the blower will operate at either high or low speed according to the switch position.
21-50´•00
Page 2 Aug 18/95
A18
~Rchcraft BONANZA SERIES MAINTENANCE MANUAL
I
i
15
9
8 16
6 10
‘i
17
=1
Compressor 2. Htah Pressure Line 3. High Pressure Relter Valve 4. Htgh Pressure Sense Switch i.
5. 6. 7. 8. 9. 10. I.
12. 13. 14. 15. 16. 17. Is.
4
Condenser Recetver-Drrer and Sight Class High Pressure Service Valve
Expanston Valve Evaporator Pressure Service Valve Pressure Limit Switch Low Pressure Line Louvers-Atr Duct Air Duct
Low Low
1
i
I
Fan Fan
I
Meter
Condenser Actuator Compressor Clutch and Puller
c~leoon c
Air-Conditioner System
Figure
1
21-50-00 A~t8
Page 3 Aug 1.8185
BONANZA SERIES MAINTENANCE MANUAL CHART 1 TROUBLESHOOTING AIR-CONDITIONING SYSTEM (Effectivity: PROBABLE CAUSE
PROBLEM 1. Insufficient
cooling.
a.
Blower not
functioning.
b. Obstructed
or
disconnected air
Optional) I
CORRECTIVE ACTION a.
Repair.
b. Remove obstruction
or
repair.
duct.
Compressor slipping.
clutch
c.
d.
Evaporator
filter
e.
Refrigerant
level low.
f. 2. No
cooling.
or
a.
Expansion
belt
clogged.
valve malfunction.
Blown fuse, loose connection.
adjust.
c.
Repair
d.
Replace.
e.
Leak-test and recharge.
f. a.
or
Replace. Check connections, fuse,
continuity. b. Blower not
3. Excessive vibration of unit.
d.
Compressor valves inoperative.
d.
Repair
a.
Correct
a.
Overcharged.
a.
)b. Purge
system.
Mount
or
compressor bolts loose.
pulley
c.
d. Fan
Hissing
6. Chatter module. 7. Belt
recharge.
replace.
refrigerant charge.
and
recharge system.
Ic. Tighten. d.
Tighten.
oil level low.
a.
Add oil.
b.
Replace.
refrigerant level.
c.
Add
hitting shroud.
d.
Align
Compressor Low
or
loose.
b. Defective belt,
5.
Leak-test and
c.
d. Drive unit.
Repair.
Leak in system.
c.
Noisy
b.
c.
b. Air in
4.
functioning.
refrigerant. and
e.
Defective compressor.
e.
Replace.
a.
Add
a.
Replace. Adjust.
tighten
shroud.
in
evaporator module.
a.
Low
or
knock in
a.
Defective
a.
Loose.
a.
b.
Overcharged.
b. Correct
c.
Air in system.
c.
Evacuate and recharge.
a.
Pulleys
not in line,
a.
Align pulleys.
tight,
b.
Adjust
c.
Replace.
d.
Replace.
slipping.
8.Excessive belt
wear,
evaporator
charge,
b. Belt too c.
expansion
valve,
Pulley groove wrong size.
d. Belt width wrong. 9. Broken belt.
a.
Check all
causes
listed.
refrigerant.
refrigerant level.
or
la. Replace
replace.
or correct.
21-50-00
Page 4 Aug 18/95
A18
aeechcraft BONANZA SERIES MAINTENANCE MANUAL
COOLING
MAINTENANCE PRACTICES
(Effectivity: Optional)
freeze into ice at the expansion valve, but can also cause the formation of hydrochloric or hydrofiuoric acids in the
MAINTENANCE OF AIR-CONDITIONER
be
system. The air-conditioning system must foreign material or
if contaminated with
purged
moisture.
Servicing the air-conditioning system consists of periodically checking the refrigerant level, checking compresser oil level and changing the system air filter. Recharge 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. PRECAUTIONARY SERVICE MEASURES Due to the air
a.
in the United
quality
control
regulations
States, R-12 refrigerant
enacted
cannot be
vented into the nance on
the
atmosphere. When performing mainteair-conditioning system where R-12 can
escape from the system, evacuate the system with only a recovery or recycle servicing unit that will salvage the b.
refrigerant.
The
air-conditioning system is a high pressure disconnecting a refrigerant line, the discharged with a recovery servicing the entire Purge system to a 125-micron level.
system. Before system must be unit.
precautions should be taken to prevent damfittings or connections. Even minute damage to connection could cause it to leak. Any fittings getting a dirt on them should be wiped clean with a grease or cloth dampened with alcohol. Do not use chlorinated solvents such as trichloroethylene for a cleaning agent, for they are contaminants. If dirt, grease or e.
All
age to
I
mo’sfu’e gets inside lines and cannot be removed, the line will have to be replaced. f.
For
serials
airplane
EA-579,
use a
prior
to
CE-1792, E-2945 and
small amount of clean 500
refrigeration (8, Chart 1, 91-00-00) and dip the o-ring in this oil before oil
on
viscosity
I
all tube joints
assembling
the
joint. g. For airplane serials CE-1792 and after, E-2945 and after, and EA-579 and after, use a small amount of Ester Oil (65, Chart 1, 91-00-00) on all tube joints and
dip
joint.
the
o-ring in this oil before assembling help in making a leak-proof joint.
1
the
This will
CAUTION owrloN1
I --´•-´•I WARNING
A face shield should be
worn
performing maintenance on the because refrigerant coming In
Insufficiently torqued tubing connections result in loose joints while excessively torqued connections can cause deformed joint parts. Either condition can result in refrigerant leakage. can
when lines con-
tact with the eyes can cause loss of
sight.
h.
When
connecting aluminum fittings
in the
reftiger-
system, torque all 5/8-inch fittings to 18 21 footpounds and all 1/2-inch fittings to 11 13 foot-pounds.
ant
servicing the system with refrigerant because It converts to a highly toxic gas when exposed to an open flame Do not smoke when
NOTE The
doing
the work should be on
tioning order.
I
major reasons for these measures are for and to prevent dirt and moisture from entering safety the system. Dirt contaminants may cause leaky valves or wear in the compressor, Moisture may not only d.
The
is the last
assembly
moisture into the lines.
throughly familiar with
servicing the system. They should follow very carefully these instructions when performing the task that will maintain this system in a proper funcinstructions
receiver-dryer
to be connected. This is necessary to reduce and/or eliminate the entry of
Before any service is attempted which requires opening of refrigeration plumbing or units, the person c.
For
charging the air-conditioner Chapter 12-10-00.
or
checking
the oil,
refer to
AIR-CONDITIONING FUNCTIONAL TEST With the
engine running
on, observe the
milky
or
bubbles
at 1,000 rpm and the
system
sight glass. If refrigerant appears appear, charge the system as noted 21-50-00
A18
Page 5 Aug 18/95
I
~Beechcraft BONANZA SERIES MAINTENANCE MANUAL
ELECTRIC CLUTCH SUCTION
ENGINE-DRIVEN DISCHARGE COMPRESSOR
HIGH PRESSURE SWITCH LOW PRESSURE SWITCH
PRESSURE RELIEF
II
VALVE
SERVICE VALVE (SUCTION) UNDER COPILOT’S SEAT
II
RECYCLE/ RECOVERY UNIT
SERVICE VALVE (HIGH PRESSURE) UNDER COPILOT’S SEAT
O EXPANSION VALVE
IN
t
RECEIVER DRYER 5 SIGHT GLASS UNDER COPILOT’S SEAT
OUT
CONDENSER IN
OUT
EVAPORATOR
C9*E1~183118
C
Air-Conditioning System Schematic Figure 2 21-50-00
Page 6 Aug18/95
A~8
~eechcraft BONANZA SERIES MAINTENANCE MANUAL under the heading CHARGING THE AIRCONDITIONING SYSTEM in Chapter 12-10-00.
Check the system for leaks
using
a
flameless leak
detector.
SYSTEM LEAK DETECTION A reduction of
system cooling ability
of bubbles in the
refrigerant, may
or
the presence
indicate
partial loss of refrigerant. Check for bubbles in the sight glass on the receiver-dryer located under the copilot’s seat. The sight glass should be checked during operation at maximum available ambient and cabin temperatures, Streams of bubbles past the glass and/or milky appearance in the glass indicate an inadequate quantity of refrigerant. If a loss of refrigerant is suspected, an inspection of the system plumbing should be carried out to locate the source of the leak. Large leaks may be located by the appearance of oily spots where oil has been carried out by escaping refrigerant. a
Smaller leaks, which are much more difficult to locate, may be detected by detergent bubbles, or an elec-
belt should be retensioned to 50 to 65 pounds and maintained at this tension. To check the compressor belt tension, use a Burrough’s Model BT-33-73F-50 belt tension gage or equivalent. Position the belt tension gage as shown in Figure 3. If a belt tension gage is not available, a properly tensioned new belt will
require 4.1 to 5.0 pounds force for a midspan deflection of 0.14 inch. After 5 hours operating time, the belt should be retensioned. After 5 hours, a properly tenrequire a force of 3.3 to 4.1 pounds for a midspan deflection of 0.14 inch. The belt should be
sioned belt will
maintained at this tension. See by midspan deflection.
Mounting
Nut................................................275
Compressor
COMPRESSOR BELT REMOVAL
(Figure 4)
Drive
engine cowling
to
gain
to the
access
compressor belt. b.
Loosen the
c.
Loosentheself-locking
jamnut
on
the
e.
remove
on
to 325 in.lbs.
to Bracket
Bolt
Pulley
Bolt
Pulley
Nut
tension from the
Adjusting
Bolt Jamnut .................275 to 325 in. Ibs.
Idler Arm
Self-Locking Nut..........300
If it is determined that the compressor belt pulleys are alignment, they may be adjusted as follows:
NOTE An
Install the compressor belt over the compressor pulley, idler pulley, and drive pulley.
rough’s No.
to increase belt tension as
the idler
bracket indicated in COMPRES-
on
alignment.
pulley
SOR BELT TENSION ADJUSTMENT in this
chapter.
Torque the self-locking nut on the idler arm to 350 inch pounds. d. Torque the jam nut on the adjusting bolt to 325 inch pounds. e. Closetheengine cowling, c.
to 300
a.
Opentheengine cowling.
b.
Remove the belt
,f
Determine if the idler
d.
shims
as
e.
Reinstall the
ure
5.
65 to 80
pounds.
After 5 hours of
static tension of
operating
time, the
pulley
or
drive
Remove the
remove
COMPRESSOR BELT TENSION
a
indicated in COMPRESSOR
pulley is
out
and add
or
alignment.
ADJUSTMENT New belts should be installed with
as
BELT REMOVAL. c.
275 to
alignment gage is available (Bur-
8082 for 0.38 pulleys and No. 8082A for 0.50 pulleys) to check belt
a.
bolt
to 350 in. Ibs.
COMPRESSOR BELT PULLEY ALIGNMENT
(Figure 4)
adjusting
to 800 in Ibs.
...........................700
out of
Remove the compressor belt.
Use the
to 850 in. Ibs.
...........................800
COMPRESSOR BELT INSTALLA TION
b.
to 325 in. Ibs.
..................................275
bolt.
adjusting
nutontheidlerarm.
d. Use the adjusting bolt to compressor belt.
Engine 220 to 260 in. Ibs.
Idler
the
Bracket to
Bolts
tronic detector.
Open
4 for belt ten-
COMPRESSOR MOUNTING TORQUES
Nut
a.
Figure
sion
f.
If the drive
appropriate pulley required per Figure 5.
pulley
pulley
and
was
torque
as
indicated in
Fig-
removed, install the cotter
pin. 21-50-00
A18
Page 7 Aug 18/95
aeechcraft BONANZA SERIES MAINTENANCE MANUAL NOTE
d.
Connect the hoses to the condenser.
If the cotter pin holes do not align within the prescribed torque range, a new nut may be installed or one AN960-C916L washer may be used under the nut.
e.
Install the
f.
Install the beacon
light.
CONDENSER CONTROL RIGGING The condenser is located
CONDENSER REMOVAL The condenser is located beneath the the main spar
fairing.
airplane
aft of
carry-through. light.
on
a.
Removethe beacon
b.
Removethefairing
c.
Disconnectthe hosesatthecondenser.
conditioner turned
d.
Remove actuator bolts.
e.
Removetheattach bolts.
flight position any time flight.
f.
aft of thecondenser.
the bottom side of the
airplane fuselage approximately even with the 3rd and 4th seats. With the airplane on the ground and the airconditioner turned on, the condenser will be fully open. Any tine the air-conditioner is turned off or the engine is at full throttle with the air-conditioner turned on, the condenser will be fully closed. With the airon
the
the condenser will be open to the airplane is in normal
The condenser is controlled
Remove the condenser.
by the electrical circuitry air-scoop actuator. Check the conproper operation. If the condenser fails to
that controls the denser for
CONDENSER INSTALLAT/ON
an open circuit between the PRESS AIR COOL switch and control actuator.
operate, check for
position.
a.
Place the condenser in
b.
Secure condenser with attaching bolts.
CONDENSER UPLIMIT AND DOWNLIMIT RIGGING
c.
Installthe actuator bolt.
For
complete condenser rigging, full up travel of the condenser should first be checked. a.
COMPRESSOR PULLEY
With the condenser actuator motor attached to the
condenser, and the condenser in the upper limit of travel, the forward edge of the condenser fairing should be b.
If the
approximately flush fairing
is not Rush,
with the lower skin.
operate the condenser
motor to ´•lower the condenser.
V BELT
With the condenser lowered, disconnect the bolt c. that attaches the actuator to the condenser and screw the actuator eye bolt in to raise, or out to lower, the condenser.
~__J_
O
d.
Reconnect the condenser attach bolt, operate the and recheck for flush uptravel of the con-
denser.motor, IDLER PULLEY
When the proper uptravel of the condenser is attained, the fully down travel (full extension), is autoe.
BELT TENSION GAGE
DRIVE PULLEY 36-425-3
matically set through the action of the internal limit switch of the actuator and need not be adjusted. In the fully extended position, the forward edge of the condenser fairing is approximately 3 inches beneath the
fuselage skin. CONDENSER FLIGHT-UCTENSION LIMIT RIGGING Belt Tension Measurement
Figure
3
Both the extended
flight-extension limit and the condenserwarning-light switches are located on a
21-50-00
Page 8 Aug 18/95
A18
aeechcraft BONANZA SERIES MAINTENANCE MANUAL bracket denser as
a.
ing
the aft end
near
assembly.
To
rig
the
on
right side
of the
both of the switches,
con-
proceed
wUN,,, WARNING
follows:
The air-conditioning system Is a high pressure system. Before dlsconnectIng a refrigerant line, the system must be discharged with a recovery senrlcIng unit. Purge the entire system to a 125-micron level.
Remove the 12 screws and washers from the fair-
which
the switches and pressure hoses aft
covers
of the condenser. b.
Remove the
fairing.
Disconnect each of the two pressure hoses c. located on each side of the condenser assembly.
A face shield should be
Con nect
screw.
a
Do not make connection with the center
f.
at the
as
indicated in step
c
to the
switch
condenser-extended warning-light (inboard the switch actuating bolt on the condenser to actuate the switch when the forward edge of
switch). Adjust
the condenser is lowered 1.5 inches the
skin at the
fuselage
perpendicular
to
airplane centerline.
con-
servicing the refrigerant because It a highly toxic gas when
Do not smoke when
system with converts to
exposed
airplane centerline.
Connect the voltmeter
lines
sight
screw.
Adjust the
fuselage skin
when
tact with the eyes can cause loss of
bolt on the end of the condenser to actuate the switch when the forward edge of the condenser is lowered 1.25 inches perpendicular to the e.
worn
performing maintenance on the because refrigerant coming In
voltm eter to the R ig ht-extensio n-li m it switch (outboard switch), by attaching one lead to the top screw on the switch and one lead to the bottom d.
i
to an open flame.
a.
Open
b.
Remove electrical leads from compressor clutch
the
right engine cowling.
terminals. Disconnect refrigerant lines at the compressor. Cap refrigerant lines and compressor fittings. c.
d.
Remove the compressor belt as noted in COMPRESSOR BELT REMOVAL in this chapter.
NOTE
Using a voltmeter to adjust the above switches is not necessary if the click of switches upon actuation is audible. g. Connect and the aft condenser
washers and
tighten the pressure hoses, place fairing in position and install the 12
screws.
Purge and charge the air-conditioning system as indicated in CHARGING THE A\R-CONDIT\ONING h.
SYSTEM in
Chapter
12.
e.
Remove the compressor mounting bolts and nuts
and
remove
compressor.
INSTALU\TION AND ALIGNMENT OF COMPRESSOR The starter drive pulley nut is torqued to 700 800 inch-pounds. If the cotter pin holes will not align, change the nut and/or use a washer under the nut. Do not overtorque the drive pulley nut. Install the cotter pin. a.
NOTE
COMPRESSOR REMOVAL
The use of AN960-C916L washer, or equivalent, as required for cotter pin
NOTE Due to the air
quality
control
When performing maintethe air-conditioning system where R-12 can escape from the system, evacuate the system only with a recovery or recycle servicing unit that will salvage the refrigerant.
atmosphere. nance on
alignment,
regulations
enacted in the United States, R-12 refrigerant cannot be vented into the
b.
is
permissible.
Remove the spacer from the bolt through the Inspect the o-ring for damage and replace if
case.
necessary. c.
Install the compressor bracket assembly and align pulley with the drive pulley. The idler should
the idler be
tightened snug within track. Install the existing nut on the through bolt, then install the two
and washer
21-50-00 A18
Page 9 Aug 18!95
I
~eechcraft BONANZA SERIES MAINTENANCE MANUAL
COMPRESSOR
ACCESSORY DRIVE PADS
BRACKET
G
I
MIDSPAN DEFLECTION CHECK
~YY/
COMPRESSOR O
I
ADJUSTING BOLT
II~
STARTER
JAM NUT IDLER PULLEY
DRIVE PULLEY IDLER ARM SELF
LOCKING NUT
UP
ENGINE
CENTER LINE
LEFT~
I)
RIGHT
LOOKING FORWARD AT THE REAR OF THE ENGINE 36-425-5
Belt Tension
By Midspan Deflection Figure 4
21-50-00
Page 10 Aug 18/95
A18
~echcraft BONANZA SERIES MAINTENANCE MANUAL .375-inch-diameter, 2-inch-long bolts with their wash-
j.
tighten all 3 bolts finger-tight. Beginning through bolt, tighten the bolts to 220-260 inchpounds in sequence counterclockwise.
ers, and
Chapter
the
I
d. and
e.
k.
Install the compressor utilizing the bolts, washers, self-locking nuts that are supplied with the bracket
equipment kit. Torque the Loosen the
locking
nut
on
jam
nut
the idler
the idler outward
nuts 275
on
the
arm.
325
a.
Adjust
by rotating the adjusting bolt inward Adjust the V-be\t to
to obtain the proper belt tension.
Torque
self-locking
I
the
jam
inch-pounds, inch-pounds.
nut 275 to 325
nut 300 to 350
12-10-00.
Closethe
engine cowling.
Remove the
pilot’s
and
copilot’s
seats per
b´•
Remove the spar
c.
Disconnect the electrical leads from the motor.
cover.
VENTILATION BLOWER INSTALLATION
and
a.
Position the blower
g. Remove caps from lines and compressor and install lines to the fittings on the compressor.
b.
Install the bolts
magnetic clutch.
c´•
Connect the electrical leads to the motor.
d.
Install the spar
e.
Installtheseats
I:
Install the electrical leads to the
Chap-
Remove the bolts which attach the blower to the evaporator and remove the blower.
SION ADJUSTMENT in this chapter. t.
in
d.
the tension outlined in COMPRESSOR BELT TEN-
I
specified
ter 25.
and self-
Install the V-belt.
as
VENT/LATION BLOWER REMOVAL
inch-pounds.
adjusting bolt
Charge the system with refrigerant
CHARGING THE AIR-CONDITIONING SYSTEM in
with
on
the evaporator.
attaching
the blower to the evapo-
rater.
Service the system with oil as specified in CHECKING COMPRESSOR OIL LEVEL in Chapter 12-10-00.
cover.
perChapter25.
IDLER PULLEY ASSEMBLY BOLT
(800 TO
850 IN. LBS.
TORQUE)
ADD OR REMOVE CONTINENTAL PIN 643956-20 SHIMS BETWEEN
BEARING AND SPACER FOR P*OPERWONMEN7
SPACER
DETAIL
A
~iy
SPACER
STARTEWACCESSORY DRIVER
o
DRIVE PULLEY NUT
(700
TO 800 IN. LBS.
TORQUE)
A
PIN
ADD OR REMOVE CONTINENTAL PIN
646064-20 SH~MS BE~WEEN PULLEY AND SPACER AS REQUIRED FOR
DETAIL
B
PROPER ALIGNMENT 36-425-4
Belt
Pulley Alignment Figure 5 21-50-00
A18
Page 11 Aug 18/95
Q3eechcraft BONANZA SERIES MAINTENANCE MANUAL EVAPORATOR REMOVAL
b.
Connectthe refrigerant lines.
Depressurize the air-conditioning system with a recycle servicing unit as specified in DEPRESSURIZING THE AIR-CONDITIONING SYSTEM in Chapter
c.
Connect the electrical leads to the motor.
a.
12.
b.
Remove the
pilot’s and copilot’s
seats per
Chap-
ter 25.
Remove the filter
d.
Remove the
cover
cover
from
over
Chapter
the ducts.
Disconnect the drain tubes and between the evaporator and duct.
remove the
tape
Removethe sparcover.
g.
Removethe ducts.
h.
Disconnect the electrical leads from the motor. Disconnect the
refrigerant
Charge
the
system with refrigerant
as
specified
in
CHARGING THE AIR-CONDITIONER SYSTEM in
and filter.
e.
i.
tubes. e.
c.
f.
Install the ducts and tape with duct tape (29, Chart 1, 91-00-00) to the evaporator and connect the drain
d.
lines and cap the open
f´•
12-10-00.
I"stall the spar
cover.
g.
Install the filter and filter
h.
installthecover overtheducts.
i.
Install the seats per
cover.
Chapter
25.
EVAPORATOR FILTER REPLACEMENT
ports. Remove the bolts attaching the evaporator to the floorboard. Remove the evaporator from the airplane,
j.
The evaporator filter should be dirty or defective. Remove the cover
EVAPORATOR INSTALLAT/ON a.
located
copilot’s
on
side to
replaced
if
clogged,
screws in the spar the underside of the airplane on the
gain
access to
the filter.
Position the evaporator in the airplane and install attaching it to the floorboard.
the bolts
21 -50-00
Page 12 Aug 18/95
A18
I
CHAPTER
COMMUNICATIONS
BONANZA SERIES MAINTENANCE MANUAL CHAPTER 23
COMMUNICATIONS
TABLE OF CONTENTS SUBJEC~
PAGE
2311 0-00 Ground Communication System Description and Operation Ground Communication (E-2104, E-2111 and after, EA-320, EA-389 and
1
after)
1
23~-60-00
Operation
Static
Discharging
Description
Static
Discharging
Maintenance Practices
and
1 1
Static Wick Removal (Plior to D-10383, CJ-156, CE-978, E-1932, EA-273 Static Wick Installation (Plior to D-10383, CJ-156, CE-978, E-1992, EA-273 Static Wick Removal (D-10383, CJ-156, CE-978, E-1932, EA-273 and after)
1
Static Wick Installation
1
(D-10383, CJ-156, CE-978, E-1932,
EA-273 and
after)
1 1
P3Contents A18
Page 1 Aug 18/95
BONANZA SERIES MAINTENANCE MANUAL CHAPTER 23
COMMUNICATIONS
LIST OF PAGE EFFECTIVITY CHAPTER-SECTION-SUBJECT
PSEffectlvlty P~-Contents
23-1 0-00
23-60-00
A18
PAGE
DATE
1
Aug 18/95
1
Aug 18/95
1
Sep 27/84
1
Jan 20/82
23-83eetlvlty Page 1 Aug 18/95
BEECHCRAFT BONANPA SERIES MAINTENANCE MANUAL
GROUND COMMUNICATION DESCRIPTION AND OPERATION
SYSTEM
communication while all other electrical
GROUND COMMUNICATION (E-2104, E-2111 and after; EA-320, EA-389 and after)
center. The
below the
after, this may be equipped with an optional ground communication system. This system allows radio
The
equipment
is turned
off. The switch for this system is a push-on, push-off switch located near the top of the instrument panel to the right of
system’s two 5-amp circuit breakers are located battery box. On airplane serials CE-1037 and optional equipment is available on the model
F33A; however, there
airplane
are
no
standard locations for the
equipment.
"END"
23-1 090
99
Pegs 1 Sep 27184
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
STATIC DISCHARGING OPERATION
DESCRIPTION AND
aluminum
or
and the
magnesium
Dow treatment of
preventive to use airplane surface.
corrosion
is
a
suitable
between the static wick base
A static electrical
airplane while
charge may build up in the surface of the is in flight. This electrical charge, if retained,
it
NOTE
interference in radio and avionics
equipment operation. Therefore, static wicks are installed on the trailing edges of the flight surfaces to aid in the dissipation of the electrical charge. can
cause
STATIC DISCHARGING PRACTICES
elevator, five
one on
(four
on
model
35)
one on
static wicks
the rudder. These
are
contact
two
(none
on
b.
Install the wick,
using the
two screws and lock
removed and
the
B36TC) on
on
each aileron, three
on
NOTE
Check the
each
continuity
between the static wick
base and the surface to which it is attached. There should be a resistance of 2.5 miliiohms or
the rudder. These fifteen (twelve on are removed and installed in the
V35B) static wicks
flight
Whenever it is
washers.
less.
The base of the later static wicks is riveted to surface and need not be removed in normal
same manner.
the
in
same manner.
elevator, and three the
be used
suitably protected
necessary that any combination of such metals be assembled, an interposing material compatible to each should be used.
On seriils 0-10383, CJ-156, CE-976, E-1932, and EA-273 and after, the static wicks are installed with one (three on the 836TC) on each wing tip, installed in the
not to
are
unless
against electrolylic corrosion.
MAINTENANCE
On serials prior to 0-10363, CJ-156, CE-978, E-1932 and EA-2j3, the static wicks are installed with one on each each aileron, and
Dissimilar materials intimate
service. c.
Refinish
attachment
(Prior to EA-2M)
STATIC WICK REMOI/AL 156, CE-978, E-1932 and a.
securing b.
Remove the
two
screws
and
lock
washers
No.
the wick
point.
STATIC WICK REMCVAL (0-10383, 9781 E-1932, EA-273 and after) a.
Remove the wick from the surface.
Clean around the static wick
3M
around
CJ-156, CE-
the wick to the surface.
STATIC WICKINSTALL9TION (Prior to CJ-156, CE-978, E-193Y and EA-213)
finishes
area
0-10383, CJ-
b.
a.
the surface
area
Unscrew the static wick from the base. Remove the static wick and lock washer.
0-10383, STATIC WICK INSTALLATION (0-10383, CJ-156, CE-978, E-1932, EA-273 and after)
by:
Removing all grease, oil, paints, lacquer, metal or other high resistance properties with Minnesota 600 grit sandpaper, or equivalent. The mating
surfaces must be smooth and contoured so that maximum surface area is in actual contact. Alodine treatment for
The threads must be clean and free of grease, oil, and
paint. a.
Install the static wick and lock washer.
b.
Torque the static wick
to 4.7
inch-pounds.
"END"
2360-00
page A4
1
Jan 20/82
CHAPTER
ELECTRICAL POVVER
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 24
ELECTRICAL POWER
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
DC GENERATION
Description Electrical
PAGE
..........24-30-00
......1
Operation System
and
......1
Troubleshooting Electrical System
......1
Maintenance Practices
......6
Alternator Removal
......6
Alternator Installation
......6
Drive Gear and on
Coupling Installation ......6
New Alternators
......6
Voltage Regulator Removal Voltage Regulator Installation Voltage Regulator Adjustments Battery Maintenance Program Battery Removal Battery Installation Battery Cleaning Battery Box Cleaning Battery Servicing
......7 ......7
......7 ......8
......8 ......8
......9 ......9 .....24-31-00
STANDBY GENERATOR
Description and Operation
.....1
Maintenance Practices
.....1 ........24-40-00
EXTERNAL POWER
.....1
Maintenance Practices
ELECTRICAL LOAD DISTRIBUTION
24-50-00 .....1
Maintenance Practices Electrical Utilization Chart
.....1
Continuous Load (Standard Equipment) Continuous Load (Optional Equipment)
.....1
(Standard Equipment) Intermittent Loads (Optional Equipment).
.....2
.....2
Intermittent Loads
.....3
"END"
2eCONfENTS
FaO´•1 Oct 7/83
BEECHCRAFT BONANZA SERIES MAINIENANCE MANUAL
CHAPTER 24 LIST OF PAGE EFFECTIVITY CHAPTER SECTlON SUBJECT
PAGE
DATE
PCEFFECTIVITY
1
Oct 7/83
24-CONTENTS
1
Oct 7/83
1
24-30-00
Oct 7/83 9/80
2
May
3
Oct 10/80 Oct 10/80
4
5
Oct 10/80
6
Oct 10/80
7 8
Oct 10/80 Oct 10/80
9
Oct 10i80
24-31-00
1
Oct 7/83
24-40-00
1
May
1 2
May 9i80 May 9180
3
Jan 20/82
24-50-00
9/80
"END"
P4-EFFECTIVITY
Page A6
1
Oct 7183
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
DC GENERATION OPERATION
DESCRIPTION
AND
alternator is
designed
magnetism.
In the event the
to have
a
small amount of residual
battery is discharged
extent that it will not excite the alternator
ELECTRICAL SYSTEM
magnetism
is strong
enough
to the
field, the residual
to excite the alternator field if
all load is removed from the
airplane electrical system includes a 28-volt, 50-amp (prior to CJ-156, CE-929, D-10354, EA-159, E-1766) or 60amp (CJ-156 and after, CE-929 and after, D-10354 and after, EA-159 and after, E-1766 and after) alternator. A 100amp alternator is optional. The alternator and one 11.0ampere-hour lead acid battery supply all the de power to the airplane. The battery supplies power for the airplane starter system and electrical system when the engine is not operating. The alternator provides the do voltage to the electrical system during engine operation. The
airplane electrical system until the bus is brought up to the proper voltage. When attempting to excite the alternator and develop output without battery power, turn off all electrical load and operate the engine at near cruise speed. In the event the alternator is not producing electrical power, the alternator sensor will illuminate an annunciator light.
Electrical system
repair methods
alternator output is controlled
by
"Aircraft Alterations" manual AC 43.13-2.
combined
a
airplane
bus
through
a
Any components
and any wire, cable, or terminals used in the maintenance of the electrical system must be of aircraft
transistorized voltage regulator/overvoitage relay. Current to excite the alternator field is normally derived from the the
Agency’s "Aircraft
manual AC 43.13-1A and/or the
Inspection and Repair" The
used must be made in
accordance with the Federal Aviation
replaced
10 amp switch/circuit breaker and relay. The self excited
voltage regulator/overvoltage
quality. Any solderless terminals or splices used applied with tooling specified by the vendor.
must be
TROUBLESHOOTING ELECTRICAL SYSTEM
TROUBLE
PROBABLE CAUSE
REMARKS
ALTERNATOR SYSTEM 1.
No ammeter indication.
a.
Loose connection.
a.
Check connections
b.
No alternator output.
b.
Check alternator output.
c.
Defective voltage regulator,
c.
Replace regulator.
d.
Overvoltage relay tripped,
d.
Check
throughout system.
reguratorlovervoltage
relay for
proper output.
2.
No alternator output.
a.
Defective ammeter.
e.
Replace
a.
Circuit breaker
a.
Reset.
b.
Open
b.
Check
c.
Defective control switch.
c.
Replace
d.
Brushes
d.
Replace brushes.
e.
Dirty slid rings.
a.
With alternator
tripped.
circuit,
worn out,
ammeter.
continuity switch.
with No. 400
jet f.
Brushes not
rings.
contacting slip
f.
of circuit.
to remove
running, clean slip rings finer sandpaper. Use air grit.
or
Clean brushes and holders with
a
clean,
lint-free, dry cloth. Replace weak springs.
24-30-00
Pagel A6
Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
TROUBLESHOOTING ELECTRICAL SYSTEM
TROUBLE 2.
PROBABLE CAUSE
No alternator output.
g.
(Continued)
Open
REMARKS
shorted circuit in
or
g.
h.
Open
shorted circuit in
or
h.
Alternator output low.
Replace
if
Test
resistance
of stater.
Replace
if
Replace
if
defective.
stater.
3.
Test resistance of rotor.
defective.
rotor.
i.
Defective
a.
Defective rectifier diode.
i.
Replace regulator.
a.
Replace diode.
or
a.
Test.
battery
b.
Check
c.
Check switch for operation.
voltage regulator.
BATTERY SYSTEM
i.
No
power
battery
indicated
with
a.
master switch "ON".
Battery discharged defective.
b.
Open
circuit between
continuity.
and master switch.
c.
Master switch defective.
necessary. d.
Defective
d.
relay.
Check relay for operation.
Replace if
necessary. 2.
Power
3.
with master switch
on
in "OFF"
a.
Master switch defective.
Complete failure
to
operate.
b.
Relay
contacts stuck.
a.
Loose
or
Loose
broken lead. or
terminals in
Excessive
Check switch for operation.
spewage
(crystalline deposits outside of battery).
c.
Battery
a.
Excessive
not
disengaged battery.
charged.
charge
rate.
b.
Replace relay.
a.
Secure lead.
b.
Secure terminals.
c.
Charge battery.
a.
Clean
on
b.
Excessive
ambient
b.
temperature during charge.
No
Output.
a.
Output voltage adjustment too low.
24-30-00
Page 2 May 9/80
if
the battery electrolyte level.
and
adjust the
Clean
and
adjust
the
electrolyte
battery
level.
VOLTAGE REGULATOR SYSTEM
i.
Replace
necessary.
b.
4.
a.
position.
set
a.
Readjust output voltage.
the
BEECHCRAFT BONANtA SERIES MAINTENANCE MANUAL
TROUBLESHOOTING ELECTRICAL SYSTEM
1.
REMARKS
PROBABLE CAUSE
TROUBLE No output.
b.
Field circuit fuse open.
b.
Replace fuse.
’c.
Transistor 07 open.
*c.
Replace 07.
d.
Overvoltage protection circuit tripped.
d.
Reset
e.
Relay
e.
Clean relay contacts.
a.
Overvoltage circuit
set too
a.
Readjust overvoltage circuit.
high,
b.
Readjust output voltages.
(Continued)
2.
Output is normal when engine is started but ceases after
3.
a
dirty.
circuit.
low.
short time.
Overvoltage inoperative
4.
contacts
overvoltage protection
circuit at any
b.
Output voltage
’a.
Transistor Q1 and 02 open.
’a.
Replace Q1
’b.
Diode CR3 shotted.
’b.
Replace CR3.
c.
External pin connections not properly made.
c.
Check external pin connections.
’d.
Zener diode CR2 open.
’d.
Replace CR2.
’e.
Relay
*e.
Repair
a.
Readjust output voltage.
’b.
Replace 06
set too
or
02.
voltage.
Continuous high output.
K1 stuck.
Output voltage adjustment high.
a.
or
replace relay.
set too
5.
Indicator
lamp fails
to
light.
07 shorted.
07.
*b.
Transistor 06
*c.
Transistor 05 shotted.
’c.
Replace 05.
’d.
Transistor 04 open.
’d.
Replace Q4.
’e.
Transistor 03 open.
’e.
Replace 03.
a.
Lamp
burned out.
a.
Replace lamp.
b.
Relay
contacts
b.
Clean
relay
c.
Check
ground connection.
c.
Bad
or
dirty,
ground connection
at
or
contacts.
indicator lamp.
OECO Voltage
regulator/Overvoltage
relay only
24-30-00
Page 3 Oct 10/80
BEECHCRAFT BONANtA SERIES MAINtENANCE MANUAL
TO BUSS DASHED LINES INDICATE t TYPICAL CONNECTIONS
r--
WARNING LIGHT
tT~ I 1 1
1
F
D
H
J
r GRD
E
201334 CR6 IN4004
G To FIELD
.47-2W~
C6 20
-_- -_
r
1
R14
j
C41
)2.4K
I
lr
TQ7 2N3055
A
04
r
2N2905A
t
C2
T
R1
R13
R8
640
1.6K-1W
3K
140
R10
CR2 IN751A
Q1
953
MPS-
06 2N3055
R15 T1
6517
2.4K
L-l-
57
5 R7
R2
03 2N3053
2K
100
-I
R4 330 R11 100
CR1
R9
Ti57
3.9K
I
R5
I
05 2N2905A
I
I
I
I
I
CR5
I
I
MR1032A
1.5K
I
C1
C3
~Q2
I
20
1.0
2N3053 1
I
I
I
C5 0.01
CR4 IN753A Re
I
I
R12
1K
I
1
249
I
I
R16
I
47K
J
R17 2.4K
R3 820
2W
GR41 L,,
TERMINAL IDENTIFICATION
UNLESS OTHERWISE SPECIFIED ALL RESISTORS ARE 112 WATT CARBON, 5% EXCEPT "BJ" RESISTORS WHICH ARE 3 WATT WIREWOUND. ALL RESISTORS ARE EXPRESSED IN OHMS.
A B
C D E
cBATTERY FIELD GROUND TRIPOUT INDICATOR LIGHT NORMALLY CLOSED TO TERM "H"
F
G H I.
J
TRIPOUT INDICATOR LIGHT LATCH CONTACTS NORM, OPEN REGULATOR INPUT +RELAY COIL 36-351-1
Voltage Regulator System Prior to CE-898, CJ-156, D-10332,
E-1644, EA-58
Figure
24-30-00
Page
4
Oct 10/80
1
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
K1
500
R18 R19
7.1
4.7~
1N936
8.2K
C121e
VOLTS
47
02 07 a 08
I
\jf~ j
~(7K
MPS8599
2NS063
R20 3.OK
I
I
j
I R16 22K
R21 470 R22 470-~
I
)R13
I
<4.7K
1
\NOTES i. DESIGNATORS USED:
R23 (NOTE 2) 3301(
1.0
TC3
C3-C5, Cf-C13, R5R23, 02-08, D1, 21-22
(S/N 97 a ON)
2. MAY BE CtlPPED OUT IN
(SIN 97 a ON)
I
IIJ-BLKS,
I
C
GND
YELS, G A
O
04
03
R5 2.4K
2N4036
R15
J(SIN 97’
2N3055
05
C5 .01
22 1P1936 C11 10
O.V. INDICATOR
ORNS, B
FIELD
R9
IN4003
J1
MS3102A-18-1P
150K
18K
Q6~1‘
IBUS
WHTS, D
R,,
MPS8099
LATCH
D1
R8 15K
R6 470
&ON)
TEST.
I‘ 1‘ C7 a C8 1.0
R14 330K
(NOTE 2)
(S/N 97
a
ON)
IREG VOLTS I
R11IADJUST
C9 a C10
1K
4.7
12
A7
8.2K
4.7K
36-3’´•1-7
Voltage Regulator System CE-898 and after, CJ-156 and after D-10332 and after, E-1644 and after EA-58 and after
Figure
2
24-30-00
Page5 Oct 10/80
BEECHCRAFT BONANLA SERIES MAINTENANCE MANVAL
DC GENERATION
MAINTENANCE PRACTICES
proper operation.
AL TERNA TOR REMOVAL a.
right
NOTE
Access to the alternator is
cowl door and
through
the forward
If
gained through the opening of the cowl.
a
alternator is to be installed, refer to
new
GEAR
DRIVE
AND
COUPLING
INSTALLATION ON NEW ALTERNATORS to
change CAUTION The
the drive gear and
coupling
output terminal of the alternator is
directly to the battery. Make sure the battery switch is "OFF" before removing the wires at the alternator or serious damage to the wiring harness and alternator may result from accidental grounding of the output stud. connected
DRIVE GEAR AND COUPLING INSTALLATION ON NEW AL TERNA TORS alternator will be received without the drive gear The drive gear and coupling from the old
The
new
and
coupling.
alternator will need to be installed b.
to the new
alternator.
Disconnect the electrical
wiring
harness from the
the
on
alternator.
new
changed by following
the
Remove the shipping spacer and washer
(if
The drive and
coupling
procedures
follows.
as
may be
alternator. c.
Remove the four
attaching bolts. Remove the
alternator.
a.
installed~ from the replacement alternator. Install the woodruff key (if not already installed), and thrust washer. Ensure the bearing assembly coupling surface (copper color) of the thrust washer is installed b.
AL TERNA TOR INSTALLA TION a.
Install
a new
gasket
on
the alternator
flange.
toward the alternator. Install the nut and
c.
pounds. CAUTION
pin
the cotter
further, but Do
not
force
the
alternator into
position
or
to the alternator or drive gears could
d. ensure
alternator
pilot enters
squarely, and engine pad.
the
the alternator is
crankcase bore
resting flat
on
to a
torque of 400 inch-
hole in the shaft, the nut should be
not to exceed 500
align
the nut to
result. Care must be taken to assure that the
damage
tighten
If the slots of the castellated nut do not
Install
inch-pounds.
align with tightened
Do not back off
holes. an
MS24665-302 cotter pin
carefully
to
clearance when the alternator is installed in the
engine.
the
NOTE on the mounting pad. attaching nuts and washers bringing to a snug condition. Torque the nuts to 150 to 180 inch-pounds in diagonally opposite pairs. d. Connect the electrical wiring to the alternator.
b.
Position the alternator
Do not
c.
Install the
flange
clamp the alternator body or mounting a vise. The cotter pin must be installed and then trimmed. The portion bent toward the in
alternator
housing
must NOT touch the thrust
washer when bent
over
the nut. The
away from the alternator NOT reach beyond the threads bent
CAUTION Never turn the battery switch "ON" until all wiring harness connections have been made and properly tightened or serious damage to the wiring harness and alternator may result from accidental grounding.
portion
housing on
must
the end of
the shaft.
VOL TAGE REGULA TOR REMOVAL
is
Ensure that the battery switch is OFF, the battery a. disconnected, and the external power source is
disconnected. b. e.
24-30-00
Page6 Oct 1 0160
Start the
engine
and check for oil seepage and
Locate the voltage regulator installed
aft side of the firewall in the
on
flight compartment.
the
right
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
Tag
c.
and
remove
wires from
all
the
voltage
adjustments.
screws
be
f.
regulator. and
voltage regulator attaching voltage regulator.
Remove the
d.
remove
the
For final check and adjustment, the engine should operated at cruise rpm (2500 rpm) with the alternator "ON" and carrying approximately 50% load.
VOL TAGE REGULA TOR INSTALLA TION BATTERY MAINTENANCE PROGRAM Ensure that the
a.
is
battery
switch is OFF, the
disconnected, and the external power
battery
source
is
Place the
b. with
attaching
remove
voltage regulator
in
and
position
secure
screws.
Install electrical wires
c.
battery is accessible for servicing by raising the right engine cowl and removing the battery box cover. A systematic battery maintenance program should be The
disconnected.
on
the
voltage regulator
and
established
follows:
as
tags.
d.
Reconnect the
e.
Operate
regulator setting
the
battery, engine and confirm
A
a.
the
voltage
b.
under various loads,
The
battery
on
the
should be removed from the
and serviced after 100 occurs
VOLTAGE REGULATOR ADJUSTMENTS
performed
in the services
log
battery
should be maintained.
flight
hours
or
30
days,
airplane
whichever
first. If the ambient temperatures are above 90"F or between engine starts averages less than 30
the time
minutes, the time between san/icing may be reduced. c.
be
should be checked
sure the electrolyte level is sufficient to maintain a specific gravity of 1.285. If the specific gravity drops below this point add electrolyte (3 parts water to 1 part electrolyte) instead of distilled water and charge the battery. Recheck
limitations voids the warranty. Should it become necessary to adjust the voltage regulator, may
battery
fill. Be
voltage regulator is set and sealed at the factory. Breaking the seal prior to the warranty The
adjustments
The fluid level of the
every 25 hours and maintained at 318 inch above the top of the separators. If the fluid level is low, add distilled water to
NOTE
made in
the
following
the
battery
after
charging for
a
proper
specific gravity.
manner.
NOTE
CA UTION
battery. When the battery spill on the lower portions of the engine accessory section and lower fuselage. Neutralize the acid spillage immediately with a water solution of sodium bicarbonate (baking soda). Do not overfill the
Observe
engine operating
cells
limitations.
a. Bring the voltage regulator and the alternator up operating temperature (preferably by flying), by operating the engine at 1800 rpm with approximately 50% load for a
to
are
overfilled,
water and acid will
minimum of 15 minutes.
Connect
b.
a
precision
voltmeter to the circuit
breaker bus.
Operate
c.
the
engine
at cruise rpm
(2500 rpm)
with
the alternator "ON", and the electrical load reduced to
a
minimum. d.
Check the bus voltage. If it is not 28.50 -C .25 vdc, should be made as indicated in the following
During periods when the ambient temperature is below 32"F, the battery should be maintained in a fully charged state to prevent freezing. When distilled water is added, the battery should be charged sufficiently to thoroughly mix the water with the electrolyte as a precaution against freezing.
adjustment
peak performance, the battery must be kept dry. If foreign materials are present in sufficient quantities, the resultant deposits may form conductive paths that permit a rapid self discharge of the battery. To prevent the collection of such deposits, the battery should be d.
step. Remove the
labeled "REG" from the
plastic plug regulator and adjust the regulator by turning the potentiometer clockwise to increase the voltage and counterclockwise to decrease the voltage. Make any adjustments in small increments and allow 2 or 3 minutes operation time for the system to stabilize between e.
corner
of the
For
clean and
cleaned after each 100 hours of service whichever
occurs
or
every 30
days,
first.
24-30-00
Page 7 Oct 10/80
BEECHCRAFT BONANtA SERIES MAINTENANCE MANUAL
CAUTION
e.
Position the positive cable
on
the
battery and
Position the negative cable
on
the
battery and
secure.
f.
Excessive spewage may result if the cell vents are not
kept
clean and open.
secure.
Remove g. terminals. The
e.
log
of
battery service performed should
justified. Accurate
consumption data is a valid barometer to use for adjustment of the servicing intervals. For further servicing, information instructions are furnished with each battery.
Place the
Position the
petroleum jelly from the
excess
box lid
battery
on
the
battery
box and
secure.
Secure the aft fuselage
i.
panel.
access
water
BA fTERY REMOVAL a.
h.
be
evaluated to determine the need to service the battery at the above recommended inten/als or to extend the intervals if
any
battery switch
in the OFF
BA~ERY CLEANING Remove the battery as described under the a. heading BATTERY REMOVAL in this chapter. Ensure that the battery cell filler caps are in place b. and tight. Brush dirt off with a stiff bristle brush.
position and
that the external power unit is disconnected. b. Locate the battery in the engine compartment
ensure
right
the upper
Remove
c.
CA UTION
on
hand side of the firewall. the
negative battery
cable from
the
Never
wire brush
use a
or
brush with
construction for this purpose or other damage may result.
battery.
as
short
a
metal
circuiting
CA UTION
Always
remove
the
ground
cable terminal first
c.
Disconnect the
d.
position battery.
it
so
positive
cable from the
battery
f.
a
solution of ammonia
or
gallon of water). any electrolyte sprayed or spilled out.
This will neutralize
tone part of soda
to a
CA UTION
and
it will not interfere with the removal of the
Entrance of ammonia
Remove the battery box from the firewall. Remove the battery from the airplane.
e.
Scrub the battery with
bicarbonate of soda
and install it last to prevent accidental short circuits.
battery Never
or
soda solution into
cell will neutralize the cell
solvents to clean the
use
these may
damage
the
battery
a
electrolyte. battery, for
case.
BA ~TERY INSTALLA TION
b.
battery switch in the OFF position and ground power unit is disconnected. Position the battery in the battery box.
c.
Install the
d.
Coat the
with
a
d.
Place the
a. ensure
that the external
light
coat of
box at the firewall.
battery battery terminals petroleum jelly.
the
e.
with clear water, then sponge off
Wash the
battery to air-dry. battery filler caps with clean
no
f. Inspect the battery for cracks, holes, spots. Replace if necessary.
g.
CAUTION If the
battery
Allow the
in
positive battery terminal is
hot water
soap, then examine the vent holes in the filler caps to make sure they are clear. and
and cable terminals
Rinse the
excess water.
good
Make
sure
that all
battery hardware
battery
or
is clean and
mechanical condition.
not marked
POS, or painted red and the negative NEG, or battery terminal is not marked
NOTE
painted black, use a voltmeter to determine the battery polarity before connecting the battery in
battery terminals required, use a battery terminal cleaning tool and brighten up the terminals to ensure a good electrical
the
airplane.
Reverse
polarity
will
destroy
the
diodes and other electronic components in the electrical system.
24-30-00
Pages Oct 10/80
If additional
cleaning
and cable terminal is
connections.
of the
burn
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
BA ’ITERY BOX CLEANING The
battery box is vented overboard to dispose of electrolyte and hydrogen gas fumes discharged during normal charging operation. To ensure the disposal of these fumes, the vent hose connections at the battery box should be checked frequently far obstructions. The battery box should be washed out thoroughly and dried each time the battery is removed and cleaned.
performance. Never add anything but distilled water when adjusting the electrolyte level of the battery. If electrolyte is added each time the level in the battery is low, a high concentration of electrolyte may cause dissolution of the plates. Under high temperature conditions, this may be indicated by the presence of black particles in the electrolyte of the affected cells.
NOTE
BA TTERY SERVICING Do not fill the
battery
over
one-half inch above
separators. Only lead-acid equipment should be used when servicing lead-acid type
The battery should be maintained in a fully charged state at all times and the electrolyte level checked at regular
the
intervals. A clean fully charged battery will provide peak
batteries.
"END"
24-30-00
Page9 Oct 10180
BEECHCRAFT BONANZA SERIES IAINTENANCE ~ANUAL
STANDBY GENERATOR OPERATION
DESCRIPTION AND
standby generator system is provided to power essential equipment in the event of loss of electrical power on the
The switch is
placarded OFF-ON-GENIRESET. The voltage regulator/overvoltage relay is mounted aft of the firewall and controls the generator output.
A
The
standby generator
is self
exciting
and
requires
no
main system,
external electrical power for it to function, although it does require 2925 to 4050 rpm (engine rpm is 1950 to 2700) to
standby generator system is an independent electrical system incorporated into the main system in such a manner as
function
The
only to essential engine instruments fuel lights, turn coordinator, fuel quantity, quantity, certain lights, and navigation and communication system. A diode in the circuit from the battery to the standby generator system prevents the generator from furnishing any power to the battery, but allows the battery (if serviceable) to supply power to the essential equipment in the event of inadequate output or failure of the standby generator, to furnish power
certain
properly. At a minimum engine speed of 1950 rpm, the generator will produce a continuous 6.5 amps at 28 volts or for intermittent (1 minute on 2 minutes off) operation 11 amps at 24 volts.
The
standby generator system is controlled and protected voltage regulator/oven/oltage relay. The regulator will control the voltage at 28.50 -e .50 volts. The overvoltage relay will remove the standby generator from the ~circuit should the voltage reach 32.0 0.5 volts. Although the overvoltage relay is set to trip and remove the generator by
a
from the circuit at 32.0
voltage spikes (at
NOTE
Should The circuits from the
battery
to the
standby
to
the
The
battery
switch may be in the OFF
standby generator system should only
flight by moving
the switch
momentarily
to the
position.
be used when
to
the
if
main system
a
picked
save
up from the
STANDBY GENERATOR PRACTICES
STANDBY GENERATOR ~UNCTIONAL TEST
b.
Turn the generator switch OFF. Turn the battery switch OFF.
c.
Turn the
a.
are
located
on
the
right side
of the
panel prior to E-2111 (except E-1946 and E(except EA-320). At the noted serials the the left subpanel and the standard to is moved switch voltmeter near the pedestal is used.
volts. a.
instrument
and EA-389
standby generator switch ON (do not position). The volt meter should register approximately 24
contact the GEN/RESET
engine baffle.
d.
The switch and voltmeter
MAINTENANCE
short exists
battery power for lowering the flaps and if the problem is determined to be only a faulty gear alternator). After turning the switches OFF, turn the standby generator on. This optional generator is mounted aft of the right magneto aft of the engine baffle and is cooled by air therein, and to
2104),
seconds).
a
possible damage
that is
50 mill
GEN/RESET position.
loss of electrical power on the main electrical system. As soon as’ a loss of electrical power is evident, turn the alternator and battery switches OFF (this is to prevent there is
trip
trip for
transient voltage spike cause the overvoltage relay removing the generator from the system, it may be a
reset in
generator system and the battery to the stall warning system are always alive, even though
0.5 volts it is not sensitive to small
33 volts it will not
Place the switch
momentarily
in the GENIRESET
position. f.
The volt meter should register approximately 28 at 1950 rpm.
volts, with the engine operating
"END"
24-3190
Pagel A6
Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
EXTERNAL POWER
MAINTENANCE PRACTICES
b.
airplane electrical system is protected against damage reverse polarity by a relay and diodes in the external power circuit. The external power receptacle is located just outboard of the left engine nacelle. The receptacle is designed for a standard AN type plug. To supply power for ground checks and for ground power unit assisted engine starts, a ground power unit capable of supplying a The
from
battery master switch on to protect transistorized equipment against transient voltage spikes. the
CA’UTION
battery switch is turned off for ground power operation, place an external battery in parallel with the output of the external power unit before operating any transistorized avionics equipment.
When
continuous load of 300 amperes at 24 to 30 volts is required. Use of an inadequate ground power unit can cause a voltage drop below the drop-out voltage of the starter
By
the
relay, resulting same
token,
a
of 350 amperes will power cables of the
in
relay
damage the airplane,
external power
excess
relay and c.
AN
Observe the power
following precautions when using
an
external
plug,
from the
ground power unit does not have a standard polarity of the plug. The positive lead ground power unit must connect to the center post, If the
check the
negative lead must connect to the front post and a positive voltage of 24 to 28 vdc must be applied to the small polarizing pin of the airplane’s external power receptacle. The power output of the external power receptacle must be the
source:
auxiliary power source that is polarity of the power source is unknown, determine the polarity with a voltmeter before connecting the unit to the airplane. Use only a. negatively grounded.
the
extended
chatter and welded contacts.
maximum continuous load in
connecting the external power unit, turn equipment and alternator Switches, but leave
Before
OFF all radio
an
If the
capable checked
of
.25 maintaining 28.5 periodically with a voltmeter
vdc and should be of known accuracy.
"END"
24-40-00
Page 1 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
ELECTRICAL LOAD DISTRIBUTION MAINTENANCE PRACTICES ELECTRICAL UTILIZATION CHART
following specifies
the electrical load for each
piece of
equipment, either standard or optional, available on the airplane. Based on this information, the electrical load for the airplane may be determined. Intermittent items should not be figured into the total figure when computing continuous load since the short duration of their usage will not significantly alter the standard load. The electrical load has been divided into 4
Intermittent load
d.
Intermittent load
Under be
The
c.
categories
follows:
as
no
more
(standard equipment) Continuous load (optional equipment)
b.
CONTINUOUS LOAD
condition shall the total continuous electrical load than 80% of the total alternator
continuous load consists of loads listed the avionics
receiving
as
loads. Transient loads
capacity. Total continuous and are
intermittent
loads.
NOTE The loads listed
as
continuous loads
are
for
equipment which will be operated for periods of 15 minutes or longer; however, the intermittent loads and the avionics transmitting loads should considered for
determining possible overloading during shorter periods of time, i.e., takeoff and landing. be
Continuous load
a.
(standard equipment) (optional equipment)
(STANDARD EQUIPMENT)
NUMBER PER AIRPLANE
EQUIPMENT
AMPS
EACH
TOTAL
1
.06
.06
2
.02
.04
Inverter, Electroluminescent Instruments, Engine Clock, Panel
1
.50
.50
1
.32
.32
1
.01
.01
Potentiometer, Light Dim
4
.03
.12
Relay, Annunciator Dim Relay, Battery Master
1
.04
.04
1
.50
.50
Sensor, Alternator Out
1
.04
.04
Turn Coordinator
1
.40
.40
Voltage Regulator
1
3.00
3.00
Passenger Reading Light Compass
2
.30
.60
2
.17
.34
1
.04
.04
Elevator Tab
1
.04
.04
Flap Position
1
.04
.04
Fuel Select
2
.04
.08
12
.17
2.04
Flap Indicator System Fuel Indicator System
LIGHTING
3rd
4th
Cabin
Glareshield Flood
.04
OAT
1
.04
Tail Position
1
1.02
1.02
2
.93
1.86
Wing Tip
Nav
Light
24-50-00
Page 1 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CONTINUOUS LOAD
(Optional Equipment) AMPS
NUMBER PER AIRPLANE
EQUIPMENT Air
EACH
TOTAL
Conditioning
Actuator, Condenser Door
1
.86
.86
Compressor Clutch Evaporator Blower Clock, Digital Electrothermal Prop Anti-ice (2 Blade) (3 Blade)
1
1.70
1.70
1
13.50
13.50
1
.20
.20
1
10.00
10.00
1
15.00
15.00 .01
Ammeter
1
.01
Timer
1
.10
.10
1
5.00
5.00
1
4.60
4.60
2
.30
.60
1
.04
.04
26
.04
1.04
37
.04
1.48
14
.024
.67
16
.024
.77
Power
Supply,
Strobe
Heater, Pitot
(1)
LIGHTING 5th 8 6th Seat
Reading
Clock, Control Wheel 8-Day Instrument, Post Light (Single) Instrument, Post Light (Dual) Instrument, Wedge Light (Single) Instrument, Wedge Light (Dual)
Map Rotating Beacon, Lower Rotating Beacon, Upper
1
.30
.30
1
3.22
3.22
1
3.22
3.22
Tail Nav/Strobe
1
1.02
1.02
INTERMITTENT LOADS
(Standard Equipment)
EQUIPMENT
Cigarette Lighter Flap Motor Flasher, Gear Warning Horn, Gear Warning Horn, Stall Warning Landing Gear Motor Pump, Auxiliary Fuel Pump, Auxiliary Fuel Pump, Auxiliary Fuel Relay, Dynamic Brake Relay, Starter Starter, Engine
2
6.00
12.00
1
11.00
11.00
1
.04
.04
1
.20
.20
1
.20
1
40.00
1
3.00
3.00
1
3.00
3.00
1
4.00
Starter Vibrator
.20 40.00 (3)
~2) (4) 4.00 (5j
1
1.25
1.25
1
3.30
3.30
1
100.00
100.00
1
2.00
Alternator Out
1
.04
.04
Condenser Door
1
.04
.04
2
.17
.34
1
.04
.04
2.00 (5)
LIGHTING
Courtesy Light Door Ajar
24-50´•00
Page 2 May 9/80
Open
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
INTERMITTENT LOADS
(Srandard Equipment Continued) NUMBER PER
LIGHTING (Continued)
Landing Gear Landing Light
AIRPLANE
Indicator
AMPS EACH
TOTAL
4
.04
.16
1
8.93
8.93
Actuator
f
.85
.85
Resistor, Shunt
1
.37
.31
1
.08
.08
1
8.93
’8.93
INTERMITTENT LOADS
(Optional Equipment)
EQUIPMENT Elevator Trim
Relay, Ldg
Gear Latch
LIGHTING Taxi
Light
NOTES:
(1) (2) (3) (4) (5)
Intermittent Operation. only on Models A38, V35B, F33A and F33C. Peak current after initial start-up load. Used
Used only Used only
on
Model F33C.
on
Models A36TC and B38TC.
"END"
24-50-00
Page A4
3
Jan´• 20/82
C H A PT E R
EQUIPMENTI FU RN ISH I NGS
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 25
EQUIPMENT/FURNISHINGS
TABLE OF CONTENTS
PAGE
SUBJECT 25-00-00
Description
and
Operation
1
Flight Compartment
and
Passenger Compartment Seating
1
General
Maintenance Practices
2
Pilot and
Copilot Seat Removal
2
Pilot and
Copilot
General
Seat Installation
2
Passenger
Seat Removal
2
Passenger
Seat Installation
4
Fith Seat Removal
(CE-748,
Pith Seat Installation Fith Seat
CE-772 and After; D-10097, D-10120 and
(CE-748,
Stowage (CE-748,
(E-llll,
Fith and Sixth Seat Installation
Fith and Sixth Seat
CE-772 and After; D-10097, D-10120 and
CE-772 and After; 0-10097, D-10120 and
Pith and Sixth Seat Removal
After)
E-1241 and After; EA-1 and
(E-llll,
Stowage (E-llll,
After)
4
After)
5
After)
E-1241 and After; EA-1 and
E-1241 and After; EA-1 and
4
5
After)
5
After)
5
Vertical Position
5
Horizontal Position
5
Headliner Removal CE-929 and After; CJ-156 and After; D-10348, E-1551, E-1569, E-1594 and After; EA-21, EA-28, EA-33 and After)
(CE-919, CE-923, CE-925, CE-927, D-10353 and After; E-1422,
6
Header Installation
(CE-919, CE-923, CE-925, CE-927,
CE-929 and After; CJ-156 and After; D-10348,
D-10353 and After; E-1422, E-1551, E-1569, E-1594 and After; EA-21, EA-28, EA-33 and
Forward Forward
A22
After)
6
Carry-Through Spar
Cover Removal
7
Carry-Through Soar
Cover Installation
7
25-CONTENTS
Nov
10/00Pagel
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 25
EQUIPMENT/FURNISHINGS
TABLE OF CONTENTS (CONTINUED) PAGE
SUBJEC7 25-60-00
Emergency Description
and
1
Operation
1
Locator Transmitter
Emergency
Communications
Components Corporation ELT TR70-17
and TR70-13
1
Narco ELT 10 Dorne and
Margolin
1
ELT
2
Artex ELT 110-4
Emergency-
Components Corporation Battery Replacement
Battery
Pack
Testing
the
Testing
the Communications
Emergency
Testing the Narco
9
Replacement
11
Locator Transmitter
Components Corporation
the Dorne and
Testing
the Artex ELT 110-4
Margolin
ELT TR70-13 and TR70-17
11
11
ELT 10
Testing
2Nov10/00
7
Margolin Battery Replacement
Atrex ELT 110-4
3 5
Battery Replacement
Dome and
Page
3
Locator Transmitter Maintenance
Communications Narco
3
Maintenance Practices
Emergency
1
ELT
25-CONTENTS
12
12
A22
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 25
EQUIPMENT/FURNISHINGS
LIST OF PA GE EFFECTIVITY
CHA PTER-SECTION-SUBJECT
PAGE
DATE
P&Effectivity
1
Nov 10/00
25-Contents
1
Nov 10/00
2
Nov10/00
1
Nov 10/00
2
Nov 10/00
3
Nov 10/00
4
Nov 10/00
5
Nov 10/00
6
Nov 10/00
7
Nov 10/00
1
Oct 16/92
2
Oct16/92
3
Oct 16/92
4
Oct 16/92
5
Oct 16/92
6
Oct16/92
7
Oct 16/92
8
Oct 16/92
9
Oct 16/92
10
Oct 16/92
11
Oct 16/92
12
Oct 16/92
13
Oct 16/92
25-00-00
25-60-00
A22
25-EFFECT~VITY
Nov
10/0 Page
1
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
GENERAL
DESCRIPTION AND OPERATION
FLIGHT COMPARTMENTAND PASSENGER COMPARTMENT SEA TING On all serials except CJ-149 and after, the pilot and copilot seat backs fold forward to facilitate passengers entering and leaving the airplane. Airplane serials CJ-149 and after have locking seat backs on the pilot and copilot seats which
can
be folded forward
by rotating the seat back release lever, located on the lower inboard side of each seat. copilot’s seat on the upper right corner is also used to fold the copilots seat for-
An additional lever located behind ward for
access
to the passenger seats.
The passenger seat backs can be folded forward by rotating the seat back release lever located side of each seat. All passenger seats have locking backs.
To
adjust the pilot, copilot,
on
the lower inboard
and passenger seats forward or aft, an adjustment lever, located beneath the front of the can then be slid to the desired position.
seats, must be pulled up. The seat A seat back
adjustment lever, located on the lower inboard side of the pilot, copilot, passenger, and on the fifth and (A36 Series), enables the seat back to be adjusted to several positions. It is controlled by a mechanical, three position cam lock. An optional seat installation is available whereby the adjustment of the copilot and passenger seat backs are controlled by a loton lock lever located on the forward inboard side of the seat bottom. sixth seats
Airplane serials E-2104, E-2111 and after, and EA-389 and after are equipped with vertically adjusting seats in the flight compartment (copilot’s seat is optional). The seat is raised and lowered by gas springs mounted underneath the seat. The seat is adjustable through a arrange of 1.3 inches for improved visibility and crew comfort. The raising and lowering action is initiated by pulling up on a release lever located on the front RH side of the seat. When the release lever is raised, two ratchet type camlocks are disengaged from sector gears attached to the gas springs mounted on each side undeneath the seat, allowing the gas spring piston rods to extend or retract to raise or lower the seat. To raise the seat the pilot’s weight must be shifted forward. To lower the seat the weight must be shifted to the rear to overcome the gas spring tension.
P~2
25-00-00
Raytheon Aircraft BEECH BONANZA SERIES MAIN’TENANCE MANUAL
GENERAL
MAINTENANCE PRACTICES
PILOT AND COPILOT SEA T REMOVAL a.
Remove the seat stops at the aft end of the
b.
Pull up on the fore and aft mounting tracks.
adjustment
mounting
tracks..
lever located beneath the front of each seat, and slide the seat off the
PILOTAND COPILOT SEA T INSTALLA TION
NOTE If shims which a.
were
installed in the seat support, they should be reinstalled in the same location from removed to achieve proper seat locking engagement with the seat track.
they were
Align the seat guide
in the
same
location
b.
Pull up
and
ensure
c.
If the lock
on
as
with the seat track. If shims
that from which
they
were
the fore and aft
that the seat is
pin
does not
with shims. Use shims
as
adjustment lever and securely in place.
align
were
installed in the front seat
guide, they
should be reinstalled
removed. slide the seat onto the seat track. Release the
with the holes in the center seat track, it will be necessary to locking pin with the holes in the seat track.
adjustment lever
reposition the guides
needed to center the
NOTE Shims
(three
The shims
d.
Pull up
that the e.
on
inches
are
long X 0.3 inch wide) may be fabricated form 0.016 6061-T6 Sheet aluminum. placed inside the seat guide and formed around the guide. Refer to Figure 2.
the fore and aft
locking pin
has
adjustment lever and slide the seat through the full positive engagement in all holes of the seat track.
travel of seat
adjustment.
Ensure
Install the seat stops at the aft end of the seat track.
NOTE When
airplane serials CJ-149 and after are used for aerobatics and parachutes are worn, the headpilot and copilot seats must be removed and the seat back cushions rotated over the
rests for the
seat backs and reattached to the bottom of the seat backs. The headrest
can
then be reinstalled.
PASSENGER SEA T REMOVAL a.
When
airplane serials CJ-149 and afterare being operated in the aerobatics category, the passenger seats gravity requirements.
may
need to be removed in order to meet the center of b.
Remove the seat stops at the aft end of the seat tracks.
c.
Pull up
mounting
Page
on
the fore and aft
adjustment lever, located beneath the front
track.
2Nov10/00
25-00-00
of each seat, and slide the seat off the
Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
~I
SECTOR GEAR
GAS SPRING
iB
RELEASE
ACTUATOR
LEVER
ROD
,o
TORQUE TUBE
ADJUSTIING LEVER
EA258 om~man.nl
Vertically Adjusting Figure 1
A22
Seat
25I00-00
Nov
10/0 Page
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
SHIMS
MAKE FROM .016 6061-T6 ALUMINUM .3 INCHES
I
SUIOUIOE
T~----´•
NMES
CENTER SEAT TRACK EA258
CENTER FRONT SEAT LEG
SHIM
VIEW FROM FRONT
Seat Track Shims
Figure
2
PA SSENGER SEA T INSTALLA TION
Align
b.
Pull up on the fore and aft adjustment lever and slide the seat onto the that the seat is securely in place.
the seat
guides
with the slots in the
a.
mounting
tracks.
mounting
tracks. Release the lever and
ensure
c.
Reinstall the seat stops at the aft end of the
FIFTH SEA T REMOVAL
(CE-748,
a.
Remove the two bolts at the lower aft
b.
Remove the seat
by removing
mounting
tracks.
CE-772 AND AFTER; D-10097, 0-10120 AND
portion
AFTER)
of the seat bottom.
the extrusion at the forward top side of the hatshelf. Reinstall the extrusion
on
the hatshelf.
FIFTH SEA T INSTALLA TION
(CE-748
CE-772 AND AFTER; D- 1 0097 0-10120 AND
a.
Remove the extrusion from the hatshelf.
b.
Instail the extrusion along with the seat back
c.
Install the seat bottom, seat belts, and the two
Nov
25-00-00
retaining strap
securing
on
AFTER)
the hatshelf.
bolts.
A22
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
FIFTH SEA T STOWAGE a.
Pull forward
forward side
on
on
the lower
(CE-748, CE-772 AND AFTER;
D- 10097 0-10120 AND
of the seat back until the seat back is in
portion
the seat bottom, rotate the seat bottom to
a
horizontal
position,
and
position
retaining strap
into
position.
vertical
a
AFTER)
position. Lift up the seat bottom
on
the
legs par-
allel with the seat bottom. b.
Lower the seat back into
a
vertical
position and snap
FIFTH AND SIXTH SEA T REMOVAL a.
Fold the bottom of the seat up to
b.
Remove the seat attach
a
(E- 1 I 1 1,
vertical
position
the
E- 1241 AND
AFTER; EA-1 AND AFTER)
and fold the seat support in the retract
position.
pins.
FIFTH AND SIXTH SEA T INSTALLA TION
(E- 1 I 1 I,
E- 124 1 AND AFTER; EA- I AND
a.
Positionthe seats.
b.
Install the seat attach
c.
Fold the seat bottom and seat support down and snap the support into the floor base.
AFTER)
pins.
FIFTH AND SIXTH SEA T STOWAGE
(E- I 1 I I,
The fifth and sixth seats may be folded either in This may be accomplished as follows:
a
E-124 I AND AFTER; EA-1 AND
horizontal
or
vertical
position
to
provide
AFTER)
additional cargo space.
VERTICAL POSITION vertical position.
a.
Fold the seat bottom up to
b.
Fold the seat support into the retract
c.
Position the seat
a
against the
rear
position.
bulkhead in
a
vertical
position.
HORIZONTAL POSITION
support into
a.
Fold the seat
b.
Fold the seat back forward and
retract
position
position
and
on
position
the seat bottom
on
the floorboard.
top of the seat bottom.
NOTE
seating arrangement is available (A36 and A36TC series only) that enables the third and fourth passenger seats to be turned facing aft. When this arrangement is used, the fifth and sixth seats must be moved four (4) inches forward to maintain proper weight and balance. If the seats are returned to a standard seating arrangement (facing forward), the fifth and sixth seats MUST be A club
moved back to their
original position. Holes are located in the floorboard under the carpeting to famounting brackets and the seat support base. Is is recommended that
cilitate installation of the side
both the third and fourth passenger seats face the
~n
same
direction at all times.
25-00-00
5
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CE-929 AND AFTER; CJ- 156 E-1569, E-1594 AND AFTER; E-1422, E-1551, AFTER;
(CE-919, CE-923, CE-925, CE-927,
HEADLINER REMOVAL
AND AFTER; D-10348, D-10353 AND EA-21, EA-28, EA-33 AND AFTER)
described in this
a.
Remove the seat backs
b.
Removethe aftbulkheadclosure.
c.
Working through
as
the aft bulkhead,
remove
Chapter.
the tape from around the air ducts that connects the air duct to the
headliner duct. which hold the overhead console in
d.
Remove the
e.
Disconnect the wires to the
f.
Remove the window
g.
Removethe doortrim.
h.
Remove the
screws
light
and
remove
place.
the console.
moldings.
glareshield.
Refer to
Chapter
39-10-00.
Remove the windshield trim.
j.
Remove the garment
loop fasteners. These hook and loop fasteners together.
the headliner to disconnect the fabric hook and
k.
Gently pull
are
located wherever the
I.
Separate
on
hanger.
airplane
frame and headliner
come
the forward air ducts from the air duct in the headliner. A
spatula
or
similar tool may be used to work
between the ducts to work the sealer loose. m.
Disconnect the electrical
toward the front, n.
or
aft of the
Remove the headliner
wiring to the headliner lights. (This connector is located pilot’s side window.)
through
near
the center of the headliner
the door.
HEADLINER INSTALLA TION
(CE-919, CE-923, CE-925, CE-927, CE-929 AND AFTER; CJ- 156
AND AFTER; D- 1034$ D-1 0353 AND
AFTER; E- 1422, E- 1551, E-1569, E- 1594 AND AFTER;
EA-21, EA-28, EA-33 AND AFTER) airplane
a.
Place the headliner in the
b.
Connect the electrical
c.
Connect the forward ventilation ducts. Seal ducts with adhesive
d.
Engage
e.
Install the garment
f.
Install the windshield trim.
g.
Install the
h.
Install
Nov
10100~t,
the hook and
wiring
loop
to the headliner
lights.
fasteners to hold headliner in
(54,
Chart 1,
91-00-00).
place.
hanger.
glareshield.
Refer to
Chapter
39-10-00.
thedoormoldings.
25-00-00
A22
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL i.
Install the window
j.
Connect the wires to the console
k.
Connect the duct aft of the
I.
Install the bulkhead closure.
m.
Install the seats
molding.
rear
light
bulkhead closure.
described in this
as
and install the console.
Tape the joint with two-inch wide tape (55,
Chart 1,
91-00-00).
Chapter.
FORWARD CARRY-THROUGH SPAR COVER REMOVAL a.
Remove the
b.
Remove emergency
c.
On aft side of spar cover,
d.
On forward side of spar cover,
e.
Remove RHaccesscover.
f.
From inside of RH
g.
Lift spar
pilot
cover
and
copilot
landing
gear crank
pull
access
and
seats.
from spar
back carpet and
pull
cover.
remove screws
back carpet and
cover, loosen
remove
cover
clamp
from spar
remove screws
and
from spar
air duct from
remove
cover.
cover.
plenum
and
grill
assembly.
from forward spar.
FORWARD CARRY-THROUGH SPAR COVER INSTALLATION
I CAUTION 1 Improper installation of the forward carry-through emergency hand crank operation. Ensure the without interference with the spar cover.
Centersparcoveron
b.
From inside of RH
c.
Install RH
d.
On forward side of spar cover, install
e.
On aft side of spar cover, Install
f.
Check the emergency
access cover
g.
Install emergency
h.
Install the
a2ln
pilot
cover, install air duct on
access
carry-through
plenum
and
grill assembly
and
tighten clamp.
assembly.
landing spar
landing
and
may interfere with the landing gear gear hand crank will engage and rotate
cover
theforward spar.
a.
the forward
spar
landing
copilot
screws to secure
screws to secure
gear hand crank to
forward end of spar
aft end of spar
ensure
cover
cover
and install carpet.
and install carpet.
handle will engage and rotate without interference with
cover.
gear crank
cover
to spar
cover.
seats.
25-00-00
NoVP:~Page
7
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
DESCRIPTION AND OPERA-
EMERGENCY TION
EMERGENCY LOCATOR TRANSMITT~R The
airplane
is
with
equipped
an
automatically
actu-
ated emergency locator transmitter (ELT) to assist in the tracking and recovery of the airplane and crew in the event of a crash or emergency landing. The ELT a battery-powered emergency (ELT), an antenna and a switch accessible through a spring-loaded door in the right side of the fuselage adjacent to the ELT. The output frequencies of the ELT are 121.5 and 243.0 MHz, simultaneously. Range is approximately line of sight. The ELT is mounted near the right side of the fuselage, at approximate, F. S. 230.00.
of
consists
system
impact switch which will actuate the ELT automatically upon impact of the airplane. The TR70-13 also has a remote switch which is accessible through a small door in the right side of the fuselage. The placarded switch positions are REARM-ARM-XMIT. The XMIT position is momentary and is used to test the operation of the ELT. The ARM position is used to arm the impact switch for automatic actuation upon impact of the airplane. The REARM position is used to reset the impact switch after testing the ELT.
locator transmitter
NARCO ELT 10
(Figure 2) The
Narco ELT
remote switch
EA-81
after,
10
is
EA-411,
thru
CE-906 thru CE-1032.
The antenna for th’e ELT is mounted
top of the fuselage at F.S. 195 on airplanes D-10097, D-10120 and after; E-llll, E-1241 thru E-2147; CE-748, CE-772 thru CE-1032; EA-1 thru EA-411 and CJ-149 thru
the XMIT
on
installed
(XMIT-ARM)
on
with a two-position airplanes D-10347 and
to test the ELT
position
tion for automatic
or
The Narco ELT 10 is installed with remote switch
CJ-156 and after, CE-1033 and after and EA-412 and after.
thru
CORPORATION
placed in posi-
in the ARM
operation upon impact of the air-
CJ-155. The antenna is mounted under the dorsal fin forward of the vertical stabilizer on airplanes
COMPONENTS
and
plane.
just
COMMUNICATIONS
E-2147
thru
E-1687
The remote switch is
~TEST-ARM-XMIT)
on
a three-position airplanes E-2424
E-2693, EA-480 thru EA-530 and CE-1241 thru
CE-1646.
The TEST and XMIT position are used for testing the ELT. The ARM position is used for automatic operation upon impact of the airplane.
ELT TR70-17 AND TR70-13 The
(Figure 1)
Narco
ELT
ON-OFF-ARM. There ration on
are
two
Communication
ELT~ being
used.
Component Corpo-
The TR70-17 ELT is installed
D-10120 thru D-10196; E-llll, E-1406; EA-1 and EA-2; CE-748, CE-772
airplanes D-10097,
E-1241
thru
thru CE-828 and CJ-149.
The TR70-13 ELT is installed
thru D-10346, E-1407 thru E-~686, EA-3 thru EA-80, CE-829 thru CE-905 and CJ-150 thru CJ-155. can be Both, the TR70-17 and TR70-13,
on
airplanes 0-10197
replaced or
with the Narco ELT 10
the Artex ELT 110-4
by Kit
by
Kit No. 101-3046-1
10
has
The ELT
airplane and used
a
control
can
switch
decaled
be removed from the
portable unit. In this event, placed in the ON position to transmit continuously. The OFF position on the ELT prevents operation of the unit and the ARM position is used to arm the impact switch for automatic actuation upon impact of the airplane. as a
the ELT control switch would be
The Narco ELT 10 110-4
can be replaced with the Artex ELT by Kit No. 101-3127-1.
No. 101-3127-1.
DORNE AND MARGOLIN ELT The TR70-17 ELT is mounted in the
the
airplane through a small door in the right side of the fuselage. The placarded switch positions are ARM-OFF-ON. The OFF position preThe ON position is vents operation of the ELT. momentary and is used to test the operation of the ELT. The ARM position arms an impact switch which will actuate the ELT automatically upon impact of the airplane. so
(Figure 3)
control switch is accessible
The TR70-13 has
a
control switch which is not
acces-
It is placarded airplane. OFF-ON-ARM. The OFF position prevents operation of the ELT. The ON position can be used for manual operation of the ELT. The ARM position arms an sible
from
outside
the
The Dorne and
Margolin
ELT is installed
on
airplanes
CE-1033 thru CE-1240, CJ-156 and after, E-2148 thru E-2423 and EA-412 thru EA-479. An AUTO-OFF-ON control switch located
controls the
of the unit.
on
the ELT
When the switch is
operation position, the ELT will transmit for testing The AUTO position arms an or manual operation. impact switch which will actuate the ELT automatically upon impact of the airplane. The OFF position A remote prevents operation of the ELT. TEST-AUTO-XMIT switch is used for testing and manual actuation of the ELT. The TEST position is a on
the ON
25-60-00
Page A16
1
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
momentary switch which will mit.
The XMIT
position
the AUTO
operation and
cause
the ELT to trans-
turns the unit
position
on
arms
for manual the
unit to
operate when the impact switch is actuated upon
impact of the airplane. The Dorne and
Margolin ELT can be replaced with the by Kit No. 101-3127-1.
Artex ELT 110-4
ARTEX ELT 110-4
(Figure 4) The Artex ELT 110-4 is installed
on
airplanes
CE-1647
and after, E-2694 and after and EA-531 and after.
An ON-OFF control switch
on
the ELT controls the
operation of the unit. When the switch is in the ON position, the ELT will transmit for testing or manual operation. Place the switch in the OFF position to An internal impact discontinue the transmission. switch will actuate the ELT automatically upon impact The remote ARMED/RESET-ON of the airplane. switch is used to arm the ELT or to manually actuate the ELT. When placed in the ON position, the ELT will transmit. The ARMED/RESET position arms the ELT to operate automatically upon impact of the airplane. To reset the ELT, cycle the control svi~itch on the ELT to the ON position, then to the OFF position, and cycle the remote switch to the ON position, then to the ARMED/RESET position.
25-60-00
Page
2
Oct 16/92
A16
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
MAINTENANCE PRACTICES
EMERGENCY
or
TR A NS MI TT~R
LOCA TOR EMERGENC Y MAINTENANCE
counter
replacing
life
useful
and
batteries, such
of
over-the-
those sold for
as
flashlights, portable radios, etc., ally unknown.
the ELT is normally limited to battery. The following is a list of the various conditions which warrant battery replaceMaintenance
the
acceptable suppliers, since
other
condition
are
usu-
on
CAUTION
the
The ELT switch should not be turned ON
ment:
unless the ELT is connected to its associ-
Visual
a.
corrosion
shows
case
life of the
signs
of
leakage,
ated antenna
or a
50-ohm
dummy
load.
unsecured leads. noted
date
Elapsed replacement
b.
battery
or
inspection
on
the
CORCOMPONENTS COMMUNICA TIONS PORA TION BA TTER Y REPLACEMENT
(this date represents 50% of the useful
battery).
NOTE NOTE
(Artex ELT 110-4) or Kit (Narco ELT 10) may be installed on these airplanes. Referto the appropriate procedure when one of these kits is installed on your airplane. Kit No. 101-3127-1
battery is the length battery may be stored without losing its ability to continuously
The useful life of the of time which the
No.
101-3046-1
a.
Remove the cabin aft
operate the ELT for 48 hours. c.
After any emergency
d.
After
one
use,
gain
cumulative hour of
operation of
use.
After
f.
If the transmitter is stored in
an area
where
temperature is normally above 100"F (380C), the battery life will be shortened.
the
I
Avoid
in
storing
excess
the batteries at
of 1300F
d.
on
temperatures
(550C).
battery
life
and
replacement
to
on
the ELT
position.
On the TR70-17 ELT, the ELT to the
remove
mounting
four
bracket.
screws
On the
TR70-13 ELT, rotate the release knob on the base to release the ELT. Remove the ELT from the airplane. e.
Information
upholstery panel
fuselage.
Disconnect the antenna cable. On the c. TR70-13 ELT, disconnect the remote switch wiring.
attaching
CAUTION
to the aft
Place the ARM-OFF-ON switch
b.
in the OFF
unknown duration.
e.
access
is
included in the data furnished with each ELT, and is usually placarded on the battery,
i"g
base f.
Remove the on
screws
which hold the mount-
the transmitter and
Remove the old
electrical connector.
remove
the base.
battery and disconnect battery.
the
Discard the old
NOTE
WARNING Replacement batteries should be obtained only from ELT and aircraft manufacturers
DO NOT discard the
battery in
a
fire.
25-60-00
Page 3 A16
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
TR70-13 ELT
CONTROL
SWITCH
A RELEASE KNOB
d
DETAIL
B
SWITCH ACCESS CONTROL
SWITCH
SWITCH
TR70-17 ELT
(REMOTE)
DOOR
POSITION PLACARD
SWITCH
POSITION PLACARD
REMOTE
I
SWITCH
cbi~
REMOTE SWITCH FOR TR70-13 ELT
DETAIL
C
SWITCH
ACCESS DOOR
DETAIL
A C9101610
Communications
Components Corporation Installation Figure 1
25-60-00
Page 4 Oct 16/92
A16
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
Inspect for, and properly treat, any corrog. that may be indicated in the area where the battery was installed.
Ision
h.
Connect
a
fresh
battery
and install it in the
compartment. the base and
j.
Install the transmitter in the airplane and On the TR70-13 ELT, con-
screws.
na
attach the antenna cable.
wiring.
nect the remote switch
The
future
on
To avoid
to the
damage
antenna
replacement
new
the ELT in
a
visible
of the ELT.
inspections
useful life of the
battery
as
should
date
area.
tab
the
and
on
handling
the control head.
the four screws attaching battery casing and slide the trol head and battery case apart. The battery nection leads are approximately 3-inches long.
f.
Remove
control head to the
This date is 50% of the defined by the battery
Do not
remove
the sealant
battery pack
or a
on
the inside
watertight seal
not be made when the ELT unit as
con-
NOTE
of the
Test the ELT
the con-
be
This will aid in
manufacturer. I.
or
the upper end, care must be exercised in extending the portable anten-
Replace
k.
antenna.
portable
CAUTION
plastic
i.
marked
Extend the
e.
instructed in TESTING THE
is
lip
will
reas-
sembled.
EMERGENCY LOCATOR TRANSMITTER. m.
Install the cabin aft
g.
upholstery panel.
Disconnect the
battery terminals
PC board. Discard the old
NARCO B A TTER Y REPLA CEMENT
(Figure 2)
DO NOT discard the
(Artex ELT 110-4) may airplanes. Refer to the Artar ELT 110-4 procedure when this kit is installed on your airplane. be installed
b.
on
to the ah
c.
upholstery panel
to
the
antenna
cable
from
i.
fire.
Unlatch the mounting strap and
ELT from the
airplane.
remove
for and
properly
treat any area
Connect the terminals of the
on
corro-
where the
new
battery
the
Using a spatula, apply a bead of sealant j. (supplied with each battery pack) around the area of the control head which is joined with the battery case when reassembied.
ELT. Disconnect the remote switch wiring from the terminals on the ELT. d.
a
to the bottom of the transmitter PC board.
position.
Disconnect
Inspect
sion that may be indicated in the battery was installed.
fuselage.
Place the ARM-OFF-ON control switch
the ELT in the OFF
h.
these
Remove the cabin ah
access
battery in
101-3127-1
Kit No.
gain
battery.
WARNING NOTE
a.
battery by unsnapping the
from the bottom of the transmitter
the
NOTE This
sealant
provides
a
watertight
seal
when the unit is assembled.
25-60-00
Page A16
5
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
SWITCH ACCESS DOOR REMOTE SWITCH
SWITCH POSITION
PLACARD
A
CONTACT SEPARATOR
CONTROL HEAD
MOUNTING
ATTACHING SCREW
(4)
STRAP PORTABLE
LATCH
PORTABLE
ANTENNA
ANTENNA
CONTACT
CONTACT
FINGER
B
DETAIL
FINGER
PORTABLE ANTENNA BLADE NOT MAKING CONTACT
FIXED ANTENNA CABLE CONNECTOR
CONTACT SEPARATOR
CONTROL SWITCH
COAX CABLE TO AIRPLANE
TO
ANTENNAPORTABLE STOP PIN
RESET
REMOTElrg
FIXED ANTENNA
HANDLE
SWITCH C9101611
DETAIL
A
Narco ELT 10 Installation
Figure 2
25-60-00
Page
6
Oct 16/92
A16
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
k.
head
control
Insert the
battery
section
into the
being careful not to pinch the wires and four attaching screws. Wipe any excess
Install the cabin aft
s.
upholstery panel.
case,
install the
DORNE
AND
MARGOLIN
BA TTER Y
sealant from the outside of the unit.
(Figure 3) NOTE NOTE If the four the
screw
battery
case
Stow the
I.
holes do not line up, rotate 1800 and reinsert.
portable
Kit No. 101-3127-1
(Artex ELT 110-4) or Kit (Narco ELT 10) may be installed on these airplanes. Refer to the appropriate procedure when one of these kits is installed on your airplane.
antenna.
CAUTION Exercise extreme
in order to avoid the
or
plastic tab
gain
101-3046-1
a.
Remove the cabin ah
access
to the aft
upholstery panel
to
fuselage.
the upper end.
on
Install the transmitter in the
m. secure
care
to the antenna
damage
No.
the
b.
Make certain the ELT is turned off.
c.
Disconnect the antenna cable.
d.
Disconnect the remote switch.
e.
Remove
airplane and
mounting strap.
Connect the fixed antenna cable to the ELT. (plastic) separator is inserted between the portable antenna contact and the portn.
Ensure that the contact
I
able antenna
as
shown in
Figure
NOTE With the contact
f. not in
be
place, a transmitted,
for
a
separator
very weak signal may which is strong enough
on
h.
wiring
Remove the remove
screws
Disconnect the
from the bottom of the
battery
and discard it.
WARNING DO NOT discard the
battery
The
in
a
fire.
the
Inspect for
i.
and
properly
sion that may be indicated new
replacement
the ELT in
a
visible
date
area.
should
be
battery
treat any corroarea
where the
replaced.
Connect the
j. k.
manufacturer.
marked as instructed in TESTING THE LOCATOR TRANSMITTER in this chap-
Test the ELT
was
in the
This will aid in
inspections of the ELT. This date is 50% of the useful life of the battery as defined by the battery
future
r.
in
the bottom.
to the
RESET button and place the p. ARM-OFF-ON switch on the ELT in the ARM position.
on
ELT
the ELT.
Press
q. marked
the
Remove the ELT from the airplane.
g. ELT and
use.
Connect the remote switch
o.
holding
screws
functional
test, but too weak for emergency
terminals
the
place.
2.
future
The on
new
the ELT in
inspections
useful life of the
new
battery.
replacement a
visible
date
area.
should
be
This will aid in
of the ELT.
This date is 50% of the
battery
defined
the
.rerutcafunamyrebyttab as
25-60-00
Page Ale
7
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
A
SWITCH ACCESS DOOR REMOTE
CABLE TO ANTENNA
SWITCH
DORNE AND MARGOLIN ELT
SWITCH POSITION
PLACARD
CONTROL SWITCH
(AUTO
OFF
ON)
REMOTE SWITCH WIRING
DETAIL
A C9101612
Dorne And
Margolin Figure
ELT Installation 3
25-60-00
Page
8
Oct 16/92
Ale
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
i.
Install
bottom
the
of the
ELT
and
WARNING
the
screws.
Do not discard Install the ELT in the
m.
the
screws
which hold it in
Test the ELT
n.
as
airplane
battery pack in
fire.
a
and install
NOTE
place.
Replacement battery packs should be only from ELT and airplane manufacturers or from other acceptable sup-
instructed in TESTING THE
EMERGENCY LOCATOR TRANSMITTER in this
obtained
chap-
ter.
since the condition and useful life over-the-counter batteries, such as those sold for flashlights, portable radios,
pliers,
Install the cabin aft
o.
ARTEX ~LT REPLAC~MENT
of
upholstery panel.
1 10-4
BA TTER Y
NOTE
procedure
must be used for
that have Kit No.
101-3127-1
installed
on
defined
Remove the cabin aft
a.
to the ah
access
b.
the OFF
usually unknown.
A new battery pack replacement date must i. be marked on the outside of the transmitter. The date is 50% of the useful life of the battery pack as
airplanes
them.
gain
are
i. Inspect for and properly treat any corrosion that may be indicated in the area where the battery was installed.
(Figure 4)
This
etc.,
PACK
upholstery panel
to
fuselage.
k.
nector
Place the control switch
(12)
on
Connect the
battery pack
electrical
con-
(10).
i.
the ELT in
position,
by the battery pack manufacturer.
screws
Secure the
(8).
battery pack to the gaskets
Make certain that all
ELT with the are
properly
aligned and in good condition. c.
the
Loosen the two thumb screws (1) securing frame cap (2) to the mounting frame
mounting base ~5). d.
Disconnect the antenna cable
(4) from the
ELT.
e.
Disconnect the remote switch harness
from the ELT
(3)
(11).
o.
base
Remove the ELT
frame base
(11) from the mounting
h.
Remove the to the ELT
screws
(11).
connector
(10)
(8) securing the bat-
remote
switch
harness
(3)
connect to
Install the ELT
(11) in the mounting frame Position the ELT in the mounting frame that the arrow on the top of the ELT is pointed
so
in the direction of p.
battery pack
the
(4) through the (11).
(5).
(5).
Disconnect the g. from the ELT.
tery pack
Insert
n.
cable
connect to the ELT
through the mounting frame cap (2) and the ELT (11).
base
f.
Insert the antenna
m.
mounting frame cap (2) and
flight.
Install the
mounting screws (1).
mounting (5) and
frame base
q. the OFF
frame cap (2) onto the with the thumb
secure
Place the control switch
~12)
on
the ELT in
position.
2,60-00
Page Ale
9
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL 14
15
A
DETAIL
B
11
12
(4
o
/Ilrl~
3
4
"O ~I
j 10
B
i.
THUMBSCREW
2.
MOUNTING FRAMECAP
3.
REMOTE SWITCH HARNESS
4.
ANTENNA CABLE
5.
MOUNTING FRAME BASE
6.
SCREW
7.
WASHER
3.
SCREW
9.
BATTERY PACK
10.
BATTERY PACK CONNECTOR
11.
ELT
12.
CONTROL SWITCH
13.
SWITCH POSITION PLACARD
14.
ACCESSDOOR
15.
REMOTE SWITCH
7
~tl
s-
s
Q
r‘‘ 5
2
DETAIL
A
1
C9101613
Artex Elt 110-4 Installation Figure 4
25-60-00
Page 10 Oct 16/92
A16
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
Test the ELT
r.
as
instructed in TESTING THE
EMERGENCY TRANSMITTER in this Install the cabin aft
s.
THE TES TING TR A NS MI TTER
chapter.
upholstery panel. LOCA TOR
EMERGENCY
TESTING THE COMMUNICATIONS COMPONENTS CORPORATION ELT TR70-13 AND TR 70-1 7
(Figure 1) Turn
a.
the
on
airplane’s COMM-1
and tune
it to 121.5 MHz.
Any time maintenance is performed on the ELT, the following operational test must be performed. The FAA/DOT allows free space transmission tests from airplane anytime within five minutes after each
b.
Turn
SPEAKER
the
COMM-1
position and place
audio
switch
to
the
the volume control in
the center of its range.
the
hour.
The test time is
warble
tone,
or
generally approximately
The control tower should be notified that about to be
NOTE
three sweeps of the a one-second test. a
test is
Monitor
frequency on COMM operating.
a
1
to
be
certain the radio is
performed.
Improper testing of the ELT could trigger false alerts create frequency jamming of real emergency Be certain that all procedures are transmissions. closely followed and that monitoring of frequencies occurs to ensure the ELT switches are placed in the proper positions after testing is complete. if the test is performed with the ELT removed from the airplane, Federal Communications Commission regulations require the testing be done in a screened or shielded and
test room, or in a test enclosure that will self-contained ELT and an antenna.
hold the
placed
ON
connected to
or a
50-ohm
or
approximately the ELT signal.
the one
NOTE A
distinctive
downward
sweeping
tone
should have been heard from the monitor-
ing receiver during
the test.
if the tone
was
heard, the ELT is functioning properly.
If
~assuming that the VHF transceiver is operating properly), the battery is probably disconnected, outdated or discharged.
The ELT switch must not be its associated antenna
second and monitor
there
CAUTION
position unless the ELT is
Place the TR70-17 ELT switch to ON
c.
TR70-13 remote switch to XMIT for
was no
audible tone
in the
dummy
d. to the OFF
After the test, place the TR70-17 ELT switch position or the TR70-13 ELT remote switch
to the REARM
load,
appear
position. completely.
The audio
signal
should dis-
NOTE e.
Tests
should
not
be
longer than
three
audio sweeps. One audio sweep may be defined as amplitude modulating the carrier
with
an
downward
audio
frequency
sweeping
range of not less than 700 Hz, within the range 1600 to 300 Hz, and a sweep repetition rate between two over
should
be conducted
in the first five minutes of any hour. If the operational tests must be made at a
only
time not included within the first five minafter the
audible
position.
signal present.
If the ELT continues to
the remote switch is in the ARM
operate, position.
check that
On the g. switch to ON, then
TR70-17 ELT, place the control place it firmly in the ARM position. On the TR70-13 ELT, gain access to the ELT control switch and place it in the OFF position. The audio signal should stop. Reset the.TR70-13 ELT to the ARM position.
hour, the tests should be
coordinated with the nearest FAA tower
flight
f.
no
a
and four Hz. Tests
utes
Place the ELT switch in the ARM
There should be
or
service station.
Operational testing of installed ELTs must be accomplished by the following appropriate procedure:
TESTING TI-IE NARCO ELT 10
(Figure 2) a.
Turn
on
the
airplane’s
COMM-1 and tune
it to 121.5 MHz. 2160-00
Page 11 A16
Oct 16/92
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
b.
audio
COMM-1
the
Turn
SPEAKER position and e center of its range,
switch
to’the
the volume control in
place
Place the remote TEST-AUTO-XMIT switch
c.
in the TEST
mately
position and hold the switch for approxi second.
one
NOTE
NOTE Monitor
frequency on COMM radio is operating,
a
certain the
1
to
A
be
econd and monitor the ELT
distinctive
(TEST-AUTO-XMIT, approximately one signal.
the
tone
heard, the ELT is functioning properly. audible tone
the
place
test,
the
or
the
the
place
test,
remote
position.
If the ELT continues to operate, be certain Gain switch is in the AUTO position.
to the ELT and check that the control switch
remote
position or the position. The audio disappear completely,
ensure
remote
access
XMIT-ARM switch to the ARM should
out-
discharged.
After
f. the
TEST-AUTO-XMIT switch to the AUTO
signal
If
was no
is in the AUTO After
was
Monitor the emergency channel to e. the ELT has discontinued operation.
If
the VHF transceiver is
d.
if the tone
TEST-AUTO-XMIT switch in the AUTO
(assuming that operating properly), the battery is probably disconnected, outdated or discharged. was no
the test,
battery is probably disconnected,
d.
sweeping
should have been heard from the monitoring receiver during the test, if the tone was there
tone
audible tone (assuming that the VHF transceiver is operating properly), there
dated
downward
sweeping
heard, the ELT is functioning properly.
NOTE A
downward
ing receiver during
Place the remote ELT MIT-ARM) switch to XMIT for c.
distinctive
should have been heard from the monitor-
cycle
position
also.
If the ELT still continues to send a signal, g. the control switch on the ELT to the ON position
and then to the AUTO
to reset the ELT
position
impact
switch. e.
e
or
If the ELT continues to
operate, check that
remote XMIT- ARM switch is in the ARM
position posi-
the TEST-AUTO-XMIT switch is in the AUTO
TESTING THE ARTEX ELT 110-4
(Figure 4)
tion.
Turn
a.
If the ELT continues to send
f.
a
signal, gain
on
the
airplane’s
COMM 1 and tune
it to 121.5 MHz.
to the ELT and firmly press the reset switch the front of the ELT and listen to ensure that the
access on
audio
signal disappears
control switch
must
be in the ARM
position when
b.
the
audio
COMM-1
switch
to
the
the volume control in
position and place
the center of its range.
NOTE
TESTING THE DORNE AND MARGOLIN ELT
Monitor
(Figure 3) a.
Turn
SPEAKER
procedure.
the test
completing
from the COMM 1. The ELT’s
a
frequency on COMM operating.
1
to be
certain the radio is
Turn
on
the
airplane’s COMM 1 and
tune
the
Place
c.
it to 121.5 MHz.
switch in the ON
remote
position
for
ARMED/RESET-ON
approximately
one sec-
end. b. SPEAKER
Turn
the
position
COMM-1 and
place
audio
switch
to
the
the volume control in
NOTE
the center of its range.
distinctive downward sweeping tone should have been heard from the monitor-
A
NOTE
ing Monitor
a
certain the
frequency on COMM radio is operating.
1
to
be
receiver
during the
test.
If the tone
was
heard, the ELT is functioning properly. there
was no
audible tone
(assuming
If
that
25-60-00
Page 12 Oct 16/92
A16
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
f.
the VHF transceiver is
operating properly), battery is probably disconnected, outdated or discharged.
If the ELT continues to
Gain
access
to the ELT and check that the control
switch is in the OFF d.
After
the
ARMED/RESET-ON
place
test,
switch
in
the
the
ARMED/RESET
Monitor the emergency channel to that the ELT has discontinued operation,
position also.
remote
position. e.
operate, be certain position.
the remote switch is in the ARMED/RESET
the
ensure
If the ELT still continues to send a signal, g. the control switch on the ELT to the ON and cycle then OFF
position
and then
ARMED/RESET
and the remote switch to the ON
position
to
reset the
ELT
impact switch. "END"
25-60-00
Page A16
13
Oct 16/92
C H A PT E
FLIGHT
CONTROLS
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
FLIGHT CONTROLS
CHAPTER 27
TABLE OF CONTENTS
PAGE
SUBJECT
27-00-00
Flight
Controls
Description
and
1
Operation
1
Control Surfaces Effect of
2
Temperature Upon Cable Tension
2
Taper Pins 27-1 0-00
Maintenance Practices
Aileron and Tab
CE-772 and After; CJ-149 and After; D-10097, D-10120 and After; E-llll, E-1241 thru 2111 except E-1946 and E-2104; EA-1 thru EA-388 except EA-320)
(CE-748,
Single
1
1
Throw-Over Control Column
Control Column Arm Removal
1
Control Column Arm Installation
1
Rigging
1
the Control Column Arm Chain
1
Dual Control Arm Dual Control Arm Removal
1
Dual Control Arm Installation
1
Rigging
4
The Dual Control Arm Chain
Aileron Removal
4
Aileron Installation
4
Rigging the Aileron
Control
Aileron Control Trimmer
4
System
(Single
Control Column
6
Airplanes)
Trimmer Removal
6
Trimmer Installation
6 6
Aileron Tabs
27-11-00
Aileron and Tabs
(E-1946, E-2104,
1
Maintenance Practices
E-2111 and After; EA-320, EA-389 and
After) 1
Dual Control Column
A20
Control Column Chain Removal
1
Control Column Chain Installation
2
27-CONTENTS
Feb
26/9 Page
1
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 27
FLIGHT CONTROLS
TABLE OF CONTENTS (CONTINUED) PAGE
SUBJECT
Rigging
2
Adjustment
3
Control Column Chain Control Column Roller
FoMlard Outer Tube Rollers
(Roil
on
the Inner
Control Column Support Roller Adjustment
3
Square Shaft)
(Attached
to the Instrument
Subpanel)
4
Aileron Removal
5
Aileron Installation
5
Aileron Control Cable Removal
5
Aileron Control Cable Installation
9
Rigging
the Aileron Control
9
System
11
Aileron Tab Aileron Trim Tab Cable Removal
11
Aileron Trim Tab Cable Installation
11
Aileron Trim Tab
12
Rigging
Aileron Trim Tab Actuator Removal
12
Aileron Trim Tab Actuator Installation
12
Aileron Trim Tab Actuator
Disassembly
13
Aileron Trim Tab Actuator
Assembly
14
Checking
Aileron Trim Tab Free
Aileron Trim Tab Free
14
Play
15
Play Inspection 27-20-00
Maintenance Practices
1
(F33A, F33C, A36, A36TC and B36TC)
1
Rudder and Tab Rudder
1
Rudder Removal
1
Rudder Installation
Rigging
the Rudder Control
6
System 27-21 -00
Ruddervator and Tab Maintenance Practices
1
Rudder(V35B) Rudder
Rigging
1
Procedure
1
Ruddervator Removal
3
Ruddervator Installation
4
Page
beF2
26/99
27-CONTENTS
A20
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 27
FLIGHT CONTROLS
TABLE OF CONTENTS (CONTINUED)
SUBJECT
PAGE
Elevator Trim Tab Removal
4
Elevator Trim Tab Installation
6
Elevator and Tab
6
Elevator
(V35B)
Rigging
Inspection
Procedure
Electric Elevator Trim Elevator Tab
Rigging For
6
of Elevator Tabs
10
(Optional)
10 10
Rigging
12
Elevator Trim Tabs to Correct for Yaw
Right
Yaw
For Left Yaw
(Nose
(Nose
of
of
airplane
airplane
Elevator Tab Indicator Cable
Inspection
of Tab
tends to
tends to
move to the
move
right
with
to the left with
12
wings level)
wings level)
12
Replacement
12
Hinges
14
Trim Tab Actuator Removal
(V35B)
Trim Tab Actuator Installation
14
(V35B)
14
27-30-00
Elevator and Tab
Maintenance Practices
(F33A, F33C, A36, A36TC, B36TC)
1
Elevator Removal
1
Elevator Installation
Rigging
1
the Elevator Control
System (CE-748,
CE-772 and After; CJ-149 and After; Prior to E-211 1
except E-1946 and E-2104; Prior to EA-389 except EA-320)
Rigging
the Elevator Control
Elevator Tab Indicator Cable
System (E-1946, E-2104,
1
E-2111 and After; EA-320, EA-389 and
Replacement (CE-748, CE-772 and After; EA-320)
After)
6
CJ-149 and After; Prior to
E-2111 except E-1946 and E-2104; Prior to EA-389 except Elevator Trim Tab Fonnrard Cable
(E-1946, E-2104, Rigging
6
Replacement
E-2111 and After; EA-320, EA-389 and
6A
After)
the Elevator Trim Tab
6B
Elevator Trim Tab Actuator
6B
Elevator Trim Tab Actuator to CJ-156
except those
Disassembly (F33A, B36TC, A36TC airplanes with Kit 33-4002-1 installed)
Elevator Trim Tab Actuator CJ-156 except those
A20
Assembly (F33A, B36TC, A36TC airplanes with Kit 33-4002-1 installed)
and A36 except E-llll; F33C
and A36 except E-llll; F33C
prior 6B
prior to 6C
Elevator Trim Tab Actuator
Disassembly (E-l 11 1 only)
7
Elevator Trim Tab Actuator
Assembly (E-llll only). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8
27-CONTENTS
Feb
26/99Page
3
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 27
FLIGHT CONTROLS
TABLE OF CONTENTS (CONTINUED) PAGE
SUBJECT
Model F33C
Elevator Trim Tab Actuator
incorporating
Kit
Disassembly 33-4002-1)
Elevator Trim Tab Actuator
rating
Kit
Checking After)
and After, and earlier
airplanes 8
Model F33C
Assembly
(CJ-156
(CJ-156
and After, and earlier
airplanes incorpo9
33-4002-1)
Elevator Tab Free
Play (CE-748,
CE-772 and After; E-l 111, E-1241 and After; CJ-149 and 11
Elevator Trim Tab Actuator Removal
(F33A, F33C, A36, A36TC
Elevator Trim Tab Actuator Installation
Elevator Trim Tab Actuator Color Electric Elevator Trim
and
(F33A, F33C, A36, A36TC
Coding (F33A, F33C, A36,
B36TC)
and
B36TC)
A36TC and
B36TC)
11 12 12 12
(Optional)
12A
Model A36, A36TC and B36TC Electric Elevator Trim Tab Servo Removal
12A
Electric Elevator Trim Tab Servo Installation
12A
Electric Elevator Trim Ground Checks
without
(Airplanes
Autopilot)
12A 128
Model F33A, F33C and V35B Electric Trim Tab Actuator Removal
128
Electric Trim Tab Actuator Installation
128
New Tab Cable Installation
12B
Magnetic Clutch Removal
128
Magnetic
12B
Clutch Installation
Electric Trim Tab Actuator Brush
Replacement
Schedule
13
13
Magnetic Clutch Torque Test 27-31 -00
Stall
Warning/Safe Flight System Description
Stall Stall
Operation
Warning System
Warning
Stall
and
1 1
Maintenance Practices
1
Warning System
1 1
Adjustments 27-50-00
Description
Flaps
Maintenance Practices
1
Removal
1
Flap
Page
beF4
26/99
and
Operation
1
Flaps
27-CO NTE NTS
A20
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 27
FLIGHT CONTROLS
TABLE OF CONTENTS (CONTINUED) PAGE
SUBJECT
1
Flap Installation Flap
Track Wear Limits
1
Flap
Limit Switch
2
Two-Position
Adjustment
Flaps (CE-748,
CE-722 thru CE-815; CJ-149; D-10097, D-10120 thru D-10178; 2
E-llll, E-1241 thru E-1370)
Flaps (CE-816 After)
Three-Position EA-1 and
Flap
Position Indicator and
and After, CJ-150 and After; D-10179 and After; E-1371 and After; 2 5
Adjustment
5
Flap Motor Removal
Connecting
Flexible
Flap
Drive Shaft to
Flap
5
Motor Shaft
7
Flap Motor Installation
Flap
7
Shaft Removal
8
Flap Shaft Installation Flap
Actuator Removal
8
Flap
Actuator Installation
8
Flap
Inner Flex Shaft Removal
9
Flap
Inner Flex Shaft Installation
9
Flap Actuator Disassembly
10
Flap Actuator Assembly
11
27-70-00
Gust Lock And
1
Damper
1
Control Lock
A20
27-CONTENTS
Feb
26/99Page
5
Qeec~craft BONANZA SERIES MAINTENANCE MANUAL CHAPTER 27 RECORD OF TEMPORARY REVISIONS REVISION NUMBER
DATE INSERTED
DATE REMOVED
REASON REMOVED
PAGE NUMBER
27-1
Dec 11/92
Nov 15/93
Temporary
27-50-00 Page 4
Revision 27-2 27-2
27-50-00
Nov 15/93
NOTE: Insert this Record of
Temporary
Revisions after the
Chapter
27 divider tab.
Page 1 Nov 15/93
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 27
FLIGHT CONTROLS
LIST OF PA GE EFFECTIVITY
CHA PTER-SECTION-SUBJECT
27-Effectivity
Pir-Contents
27-00-00
27-10-00
27-11-00
A20
DATE
PAGE
1
Feb 26/99
2
Feb 26/99
3
Feb 26/99
1
Feb 26/99
2
Feb 26/99
3
Feb 26/99
4
Feb 26/99
5
Feb 26/99
1
Aug
28/87
2
Aug
28/87
1
Mar 29/96
2
Aug 18/95
3
Aug
4
Mar 29/96
5
Mar 29/96
6
Mar 29/96
7
Aug18/95
1
Feb 26/99
2
Feb 26/99
3
Feb 26/99
4
Feb 26/99
5
Feb 26/99
6
Feb 26/99
7
Feb 26/99
8
Feb 26/99
9
Feb 26/99
10
Feb 26/99
11
Feb 26/99
12
Feb 26/99
13
Feb 26/99
27-EFFECTIVITY
18/95
Feb
26/99Page
1
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 27
FLIGHT CONTROLS
LIST OF PAGE EFFECTIVITY (CONTINUED) CHAPTER-SECTION-SUBJECT
PAGE
27-20-00
27-21-00
27-30-00
Page
beF2
26/99
27-EFFECTIVITY
DATE
14
Feb 26/99
15
Feb 26/99
16
Feb 26/99
17
Feb 26/99
1
Feb 26/99
2
Feb 26/99
3
Feb 26/99
4
Feb 26/99
5
Feb 26/99
6
Feb 26/99
1
Mar 29/96
2
Aug 18/95
3
Mar 29/96
4
Mar 29/96
5
Mar 29/96
6
Mar 29/96
7
Mar 29/96
8
Mar 29/96
9
Mar 29/96
10
Mar29/96
11
Mar 29/96
12
Mar 29/96
13
Mar 29/96
14
Mar 29/96
15
Mar 29/96
1
Aug 18/95
2
Aug 18/95
3
Aug 18/95
4
Aug 18/95
5
Aug
6
Aug 18/95
18/95
A20
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 27
FLIGHT CONTROLS
LIST OF PAGE EFFECTIVIN (CONTINUED)
CHAPTER-SECTION-SUBJECT
PAGE
DATE
6A
Aug 18/95
6B
Aug 18/95
6C
Aug 18/95
7
Jun 20/91
8
May 31/85
9
May 31/85
10
Oct 7/83
11
May 31/85
12
Jun 20/91
12A
Jun 20/91
12B
Jun 20/91
13
Oct 7/83
27-31-00
1
May 9/80
27-50-00
1
Feb 26/99
2
Feb 26/99
3
Feb 26/99
4
Feb 26/99
5
Feb 26/99
6
Feb 26/99
7
Feb 26/99
8
Feb 26/99
9
Feb 26/99
10
Feb 26/99
11
Feb 26/99
12
Feb 26/99
13
Feb 26/99
27-70-00
A20
1
27-EFFECTIVITY
May
9/80
Feb
26/99Page
3
BEECHCRAFT BONANZA SERIES MA\NTENANCE MANUAL
DESCRIPTION AND
FLIGHT CONTROLS OPERATION
position. The switch is placarded UP, OFF, DOWN. The markings on this position
and
indicator will CONTROL
be UP
100, 200 and DN,
SURFACES NOTE
V35B and A36TC air-
Model
F33A, F33C, planes and earler Model A36 and B3GPC airplanes are e~uipped with either a single "throw-over or dual "T" control colE-2111 and umn. At serials E-1946, E-2104, after; EA-320, EA-389 and after, dual All
control columns equipment. The
operated require
installed as standard flight controls are cable were
surfaces conventional for no power assistance
control by the pilot or copilot. and optional electric elevator electrically driven.
which norma’l
The flaps trim are
primary flight control surfaces are manually controlled through cable bell Each system incorporates crank systems. survace travel stops and linkage adjustments. The ailerons, elevators, and rudder All
secured with control locks (qust ~hen the flight compartment. these locks are installed, the elevator is at approximately 110 down and the control wheel is approximately 120 to the The rudder pedals are interconright. nected by a linkage below the flight compartment floor. -~he rudder pedals are
may
be
locks)
in
adjustable
to
two
positions by pressing
the spring-loaded lever
pedal.
If brakes
are
the side of the installed on the lever may be same on
not
On serials E-1946, E-2104, E-2111 and after, the approach position is 120
serials CJ-150 On Airplane CE-8~6 and after, D-10179 E-1371 through E-2110 except
and and
after, after,
E-1946
and
E-2104, and EA-1 and after, the flaps have three positions; UP (O"), APPROACH (150), and DOWN (300). The switch is placarded UP, APPROACH and DOWN. There is no way to stop the flaps in other positions without using the circuit breaker. The flap position transmitter (if installed) is located near the left flap actuator.
On airplane serials E-1946, E-2104, E-2111 and after, EA-320, and EA-389 and after, the position of the flaps is indicated by three lights, located near the flap control handle, in the subpanel. The lights indicate down, wi 11 approach, and intransit positions. All lights are out wheri the flaps are up.
Trim tabs The tabs
pilot
are are
installed
each elevator. by the systems using
drum-cable Tab position indicaprovided on the tab controls.
through
jackscrew
on
manually controlled
actuators.
copilot’s pedals, this used to place the copilot’s pedals against
tors
the floor.
optional electric elevator trim tab operated by a control switch on the outboard handle of the pilot’s control A down spring and bob weight are wheel. incorporated into the elevator control system for improved stability.
One flap installed on each wing is operated byan electric motor-driven gearbox the forward side of the rear spar at on of The the centerl i ne the ai rplane. gearbox drives two flexible drive shafts, connected to an acme thread type each jackscrew at each flap. The flaps are controlled by a lever in the subpanel, and their position indicated by an instrument The the left of the control column. to lever (switch) must be pulled out of a detent to change positions. On airplane serials CJ-149, C’E-748, CE-772, through
CE-815, 0-10097, D-10120 through D-10178, E-llll, and E-1241 through E-1370, the flaps may be stopped at any desired position by moving the flap switch to the OFF position when the flaps are at the desired
are
The is
On
earlier serials, aileron trimming was by bendable tabs on each aileron and a spring tension trimmer in the control column. The bendable tabs were adjustable only while on the ground. The spring tension trimmer was ad~justable in flight. The spring tension trimmer and left bendable
tab were replaced by an inflight adjusta-l ble trim tab at serials E-2111 and after,l except E-1946 and E-2104, and on serialsl This system is a EA-321 through EA-388. cable control a jacksrew system with actuator and a trim wheel in the pedesal.
27-00-00 Page 1 A12
Aug 28/87
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
the primary flight conand limit their travel. traveling stops secured to the cables the tab limit Because trim movement. cables are connected at turnbuckles, each cable has one left hand and one right hand threaded cable end. Proper routing of the cables shown in the applicable subas chapter will aid against crossing the cables and improper movement causing after Ehe cables have been removed and reinstalled.
TAPER
applicable riyyiny procedures
of tile
Positive stops trol surfaces
on
PINS
Refer to the applicable rigging procedures cable for and details regarding chain tension, control wheel movement and force, and system friction. Any time the control column has been removed and disassembled, be should the following precautions observed: a.
When
installed,
nylon mallet Refer to the for details
regarding
chain
and
cable
tension, control wheel movement and force, and down spring force and system friction.
a
to
tapered
extend surface.
or
be to are pins light weight rawhide or
taper
use
no
set the pin. The small end shank should be flush with,
more
than 0.06 inch
over
the
CAUTION EFFECT
OF
TEMPERATURE
UPON
CABLE
The taper pin may crack the torque tube if driven excessively.
TENSION
Graphs specifying the
correct maximum and minimum cable tension permissible for the various controls appear on the individual rigging control system illustrations. The graphs provide rigging limits at temperatures varying from OOF to 1100F. The horizontal scale on the graphs disignates the temperature in degrees Fahrenheit at which the control cables may be rigged, and the vertical scale designates the correct tension in pounds for each tem-
perature reading,
WARNING On
airplane
serials
E-1946,
E-2104, E-2111 and after; EA-320, the EA-389 and observe after, color coding on all parts when
replacing
or
reinstalling control
cranks and/or other system components. DO NOT
cables, bell control
connect coded parts of one color to coded parts of different color.
"END"
27-00-00 Page 2
Aug 28/87
A12
rZ~eechcraft BONANZA SERIES MAINTENANCE MANUAL
AILERON AND TAB MAINTENANCE PRACTICES (EffectiVity: CE1748, CE1772
link. The turnbuckles must be near the access opening. The slot in the lower sprocket should be approxi-
and after; CJ-149 and after; 0-10097, 0-10120 and after; Elllll, E11241 thru E-2111 except E´•1946 and 0-2104; EA-1
mately parallel
thru EA1388 except
b.
theturnbucklesand Removethesafetywirefrom or tighten the chain as necessary.
loose"
EA1320)
NOTE the chain until friction or binding is felt on the control wheel, then loosen the chain just enough to remove the binding or friction from the control wheel.
Tighten
SINGLE 7HROW-OVER CONTROL COLUMN
(Figure
I c.
CONTROL COLUMN ARM REMOVAL
Check the control wheel and control surfaces for
proper a.
Remove the four
collar
assembly
to the sides of the arm.
that
screws
secure
to the control column
the retainer
housing.
Disconnect any electrical
c.
Remove the aileron trimmer
indicated in AILE-
as
After the
and freedom of movement.
adiustments
are
complete, check
that
the location of the control wheel, sprockets, and turnbuckles are as shown. Refer to Figure 1.
wiring.
b.
d~
operation
e.
Safety
wirethe turnbuckles.
RON CONTROL TRIMMER.
I
Pull the "T" handle located
d.
the control
the forward side of
arm.
Rotate the control column
e.
on
cal
position housing.
arm
to the
nearly verti-
and slide the control column
arm
DUAL CONTROL ARM
(f~igure 2) DUAL CONTROL ARM REMOVAL
off the a.
Remove the four
collar
assembly
screws
Position the control
ure
1. Make
sure
approximately parallel
I
as
each other
near
the
shown in
b.
The ailerons MUST be in the neutral
e.
Pull the "T" handle located
the control d.
on
position.
the forward side of
arm on
the control ool-
housing.
Connect all electrical
omit the following step. b.
assembly
Install the retainer collar and attach it with the four
as
indicated in AILE-
Check the control column forfull movement and
the control surfaces for proper direction of movement.
RIGGING THE CONTROL ARM CHAIN
screw
right
and washer
retaining
the
forward side of hub of the
c.
Disconnect all electrical
d.
Slidethecontrolarm off ofthehousing.
pin
con-
wiring.
Position the control arm, control wheel, and as shown in Figure i. The long and short on
the
sprockets
Position the control
arm as
shown. Refer to
Figure
2.
Make sure the slot in the center sprocket is b. approximately vertical and the turnbuckles between the long chains and the short chains are are opposite each other near the access openings. Th,,ilerons MUST be in neutral.
NOTE
sprockets
chains must be centered
the
DUAL CONTROL ARM INSTALLATION
g. Install the aileron trimmer RON CONTROL TRIMMER.
a.
on
arm.
wiring.
screws.
h.
Remove the
trol
a.
f.
housing.
Some installations may have a "T" handle on the right forward side of the the control arm. Pull the "T" handle and
are
arm.
Slide the control column
umn e.
Figsprocket is
long and short chains access opening,
the retainer
NOTE
to the sides of the arm and that
the turnbuchles between the
opposite
vertical
arm
that the slot in the lower
secure
to the control column
CONTROL COLUMN ARM INSTALLATION a.
that
within one
Some installations may have a "T" handle on the right forward side of the the control arm. Pull the "T" handle. 27-1 0-00
Page A19
1
Mar 29/96
aeechcraft BONANZA SERIES MAINTENANCE MANUAL
I
’4
r
I
i i/ \r
z-li
1
I
111
LONG CHAIN
ACCESS OPENING
TURNBUCKLE
SHORT CHAIN
SLOT
IN SPROCKET
C9201 73~
Single
Throw-over Control Column
Figure
1
27-1 0-00
Page 2 Aug 18/95
A18
aeechcrraft BONANZA SERIES MAINTENANCE MANUAL
TURNBUCKLES MUST BE OPPOSITE SLOT LONG CHAIN
ii
IN SPROCKET
I
LONG CHAIN
Arl
3
r
8
A
TURNBUCKLES MUST BE OPPOSITE
SHORT CHAIN
RIGHT
LEFT VIEW LOOKING AFT
I
RIGHT
DETAIL
LEFT
A
FWD
C9201739 9
Dual Control with
Single Control Figure 2
Column
27-1 0-00
A18
Page 3 Aug 18/95
aeechc~ft BONANZA SERIES MAINTENANCE MANUAL d.
Slide the control column
umn
the control col-
arm on
NOTE On installations with
the
"T" handle, omit
a
following step.
Install the pin e. control arm hub. f.
Place the aileron in
hinge brackplace between the aileron skin and the reinforcing structure. b.
ets. The
housing,
assembly
on
the
right
side of the
Install the retainer collar and attach it with the four
screws.
g. Check for full control movement and for proper direction of movement.
hinge brackets
position
on
the
must be in the correct
c.
Install the upper and lower hinge bracket
d.
Pull
screws.
the aileron in a direction straight away wing to make sure that the hinge brackets are positioned correctly. If there is any movement of the aileron, recheck the position of all hinge brackets. on
from the
RIGGING THE AILERON CONTROL SYSTEM
(Figure 3)
RIGGING THE DUAL CONTROL ARM CHAIN
NOTE
Position the control arm, control wheel, and sprocket as shown. Refer to Figure 2. a.
b.
Center the
ets within c.
e.
and short chains
on
their sprock-
link.
one
The slot in the center
mately vertical d.
long
BEECHCRAFT recommends the use of the aileron travel gage shown in the SPECIAL TOOLS in Chapter 12-20-00.
as
Remove the
Adjust the
shown.
be 2.
wing
as
necessary. a.
Aileron and
flap
outboard of the inboard
surfaces must
upper and lower surfaces of the
properly adjusted by chains until binding is
wing
align
with the
within 1/16 inch.
are
Adjust the aileron downstops in the wing until the just clears the gusset on the wing rib. Set the aileron upstep in the wing so that the aileron bellcrank just misses the aileron pushrod. b.
the the control wheel; then loosen the chains just enough to remove the binding or friction from the control
tightening noticed
(just hinge).
rib
aileron
NOTE The chains
The front of the travel gage should be located over the leading edge skin splice with the aft portion over the number 8
approxi-
wire from the turnbuckles.
safety
chains
sprocket must Refer to Figure
bellcrank
on
wheel c.
complete, check that the location of the control arm, control wheels, sprockets and turnbuckles are as shown. Refer to Figure 2.
f.
g.
After the
Safety
adjustments
are
the
screws
b.
remove
damage
to
attaching hinge bracket.
the two
from the top and bottom of each
straight away from the attaching areas.
Pull the aileron
avoid c.
and
Remove the screws
attaching
the
the
AILERON INSTALLATION Attach the
bonding
wing
bonding
to the aileron.
a.
connecting the
aileron to the bell-
upstep and the downstop.
The aileron is in neutral when the aileron
trailing edge aligns with the trailing edge of the wing, and its inboard end is parallel with the outboard end of the flap.
AILERON REMOVAL
Support the aileron
the link
NOTE
wire the turnbuckles.
h. Check the controls for freedom of movement and the control surfaces for proper direction of movement,
a.
Adjust
crank to allow full travel of the aileron surface between
cable to the aileron.
to
cable
d.
Adjust the cables from
the
cables. The turnbuckles
wing
are
to the control col-
in the wheel wells.
Secure the control column wheel in neutral by e. securing a bar across the top of the control wheel and leveling the control wheel with a bubble level. Onlith the control locks installed, the control wheel is rotated 12" to the right.) Adjust the tension as shown on the aileron temperature cable tension ure 3.
graph. Refer
to
Fig-
27-1 0-00
Page
4
Mar 29/96
A~9
BONANZA SERIES IVIAINTENANCE MANUAL
AILERON CONTROL SYSTEM TEMPERATURE CABLE TENSION GRAPH
ALL SINGLE CONTROL COLUWIN
BONANZAS so
s40
I
CABLES
I
CABLE TENSION
I
SURFACE TRAVEL
~30 20" 40LBS
AILERON
+2 -2
UP
~5LBSAT
59"F BUNGEE SPRINGS CONNECTED
20"
+2DOWN -2
10
10
20
40
30
50
60
70
80
90
100
110
120
TEMPERATURE -~F
RIGHT AILERON
UP CABLE
IN WHEEL
WEUTURNBUCKLES
C
DOWNSTOP
UPSTOP
oo’
’:i:iSas-::-::-:::::
LEFT UP
SPAR TURNBUCKLES
RIGHT UP
CARRY THROUGH
1N WHEEL WELL
-Y
LEFT AILERON
BALANCE CABLE
UP CABLE
36-151-17
6
!1
~i
001
_Y, RUDDER INTERCONNECT BUNGEE
Rigging The Aileron Control System (Effectlvity: CE-748, CE-T72 and after; CJ-149 and after; D-10097, D-10120 and after; E-lll1, E-1241 thru E-2111 except E-1946 and
E-2104; EA-1 thru EA-388 except EA-320)
Figure 3
27-10-00
Page A19
5
Mar 29/96
CJ;)eechcraft BONANZA SERIES MAINTENANCE MANUAL NOTE The control wheel must be level in relation to the airplane. If the airplane is not level, make a corresponding change to the position of the control wheel using a
spirit
Check the allerons for correct directlon of movement. When the control wheel Is moved to the left, the left alleron must move up and the right
level protractor.
Take the cable reading in the wheel well where the control column cables attach to the
alleron must move down. When the control wheel Is moved to the right, the right alleron must move up and left alleron must move down.
wing cables.
f.
Rotate the control wheel to ascertain
the
wing bellcranks
by
feel that
reach their stops before the trol column reaches its stops.
con-
g. If there is less travel of the control wheel in one direction than in the other direction, loosen one turn-
AILERON CONTROL TRIMMER (SINGLE CONTROL COLUMN AIRPLANES)
tighten the opposite
The aileron control system is equipped with an aileron control trimmer which functions by applying tension on
lower cable turnbuckle, depending on which way the travel is off. Maintain the correct cable tension.
the aileron control cables to level the wings as needed. The holding pressure exerted by the aileron
buckle
h.
on
the lower cable and
Secure the control wheel in neutral after the
control trimmer cor-
rect travel of the wheel is obtained.
connecting
the aileron in
determined
Adjust the link wing bellcrank to obtain neutral. Neutral position of the aileron is
the aileron to the
by aligning
the inboard end of the aileron
with the outboard end of the
flap with the flap
in the up
position
tem
the cable tension.
TRIMMER REMOVAL
(Figure
give Figure
a
deflection of 3.
NOTE The aileron bellcrank stops should make contact 1/16 inch before the control column stops are reached.
body halves by holding the body housing touter half) and turning the clutch nut body (inner half) counterclockwise. b. Separate the two body halves by pulling out on the clutch body housing. clutch
TRIMMER INSTALLATION
(FIgure 4) a´•
Carefully insert the shaft through the felt seal into bearing, being careful not to sheer the felt
each aileron bellcrank contacts its upstep at the same time the bellcrank in the opposite wing
the hub
contacts its
seal.
j.
sure
downstop.
Check the control stop (secondary stop) in the control column for 1/16-inch clearance in each direction. If the clearance is not correct, recheck the entire k.
aileron control system for correct chain and cable
rig-
ging. NOTE The control stop clearance provides a slight movement of the control wheel (a "cushion") after the travel stops on the aileron bellcranks make contact. i.
Recheck cable tension and
buckles. m.
Tighten alljamnuts.
safety
4
Unscrew the two
a.
Set the bellcrank stop bolts to 20" ~2" up and/or down. Refer to i.
Be
can be easily overriden at the discrepilot. The trimmer does not change the sysrigging but should be removed before checking
tion of the
wire the turn-
b. Screw the two halves of the unit together by holding the clutch body and turning the clutch body nut. Hand-tightening the two halves should be sufficient.
Check that the tangs of the drive shaft engage properly with the sprocket as the unit is being tightened by hand. Also note that the position indicator on the face of the unit is right side up as the shaft c´•
engages with the
sprocket.
AILERON TABS The ailerons
equipped with sheet metal tabs which airplane is on the ground. bending them in opposite directions to each other. Bend the tabs only a small amount each time and check the setting by flight test. are
may be adjusted while the The tabs are adjusted by
27-1 0-00
Page
6
Mat 29/96
A19
aeechcraft BONANZA SERIES MAINTENANCE MANUAL
3
2
i.
THROW-OVER CONTROL ARM "T"
CONTROL
2.
DUAL
3.
AILERON TRIMMER
ARM
;f~C
Alleron Trimmer
(Slngle Control Column) Figure 4 27-1 0-00
A18
Page 7 Aug 18/95
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
AILERON AND TAB
(E-1946, E12104,
MAINTENANCE PRACTICES AFTER, EA-320, EA-389 AND
E12111 AND
AFTER)
WARNING I WARNING) Make certain that insulation, tie wraps, etc. do not interfere with control components such as
cables, chains,
etc.
DUAL CONTROL COLUMN
WARNING I WARNING) On
airplane serials
CE-1566 and after; E-1946, E-2104, E-2111 and after; EA-320, EA-389 and on all parts when replacing or installing control cables,
after, observe the color coding
bellcranks an~or other control system components. DO NOT connect parts of one color to coded parts of a different color. CONTROL COLUMN CHAIN REMOVAL
FIGURE 1 a.
Paint
one
tooth of each control column’s sprocket and its
corresponding
chain link to
ensure
proper alignment
of the control wheels at installation. b.
Loosen the turnbuckles of the control column chain and the aileron turnbuckles in the wheel well.
TURNBUCKLE
STOP
TORQUE SHAFT
GUARD PIN
LINK
ASSEMBLY
CHAIN ASSEMBLY
I
CONNECTOR LINK
SPROCKET ASSEMBLY
AILERON CABLE ASSEMBLY
Q AIRCRAFT 36-155-6
Dual Control Column Chain
Figure
A20
Adjustment
1
27-11-00
Feb
26/9 Page
1
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL c.
Remove the
safety
wire from the 4 bolts
(2
on
each
end),
and
remove
the 6 bolts from the channel between the
control columns.
d.
Remove the channel from the
e.
Disconnect the turnbuckles from the chain of the control column.
f.
Remove the 4 connector links from the stop link
airplane.
assembly,
then
remove
the stop link
assembly.
NOTE It may be necessary to g.
Slide the
remove
the stop block before
sprocket support assembly aft
over
the
joint
removing
then
remove
the stop link
assembly.
the chains from the control columns.
CONTROL COLUMN CHAIN INSTALLATION
FIGURE 1 a.
Install the chains
b.
Install the stop link
c.
Install the aileron cable chains. The inboard holes of the stop link
over
the control column
assembly.
sprockets.
The outboard holes
are
used with the control column chain.
assembly
are
used with the aileron cable
chains.
NOTE Make certain the connector links d.
Install the stop block if removed.
e.
Connect the turnbuckles
f.
Slide the
(do
not
are
properly
installed.
tighten).
sprocket support assemblies forward and install the channel between the control columns. Safety wire
the bolts. g.
Tighten
the control column chains
as
indicated in CONTROL COLUMN CHAIN RIGGING.
WARNING IWARNINO) Check the ailerons for proper motion, When the control column is turned to the aileron should move down and the
right aileron
move
right,
the left
up.
CONTROL COLUMN CHAIN RIGGING FIGURE 1
Rigging a.
Rig
of the control column chain may be neutral
on
the control wheels
may be ~0.06 inch off the b.
accomplished by
by placing straightedge.
a
straightedge
the
across
Assure that the ends of the control column chain around the
from the centerline of the
Page
following: the top of the control wheels. One of the
right sprocket
are
within
one
link of
grips
equidistance
sprocket.
27-11-00
A20
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL If the stop link assembly is not centered within ~0.02 inch with respect to its stop, the link. c.
d.
Place
a
vertical load of two
+0.06 inches. e.
the
pounds
the turnbuckles
Adjust
adjust the turnbuckles to center
the top chain near the airplane centerline. The chain should deflect 0.25 necessary to obtain this deflection.
on
as
rigging the control column chain, refer to ailerons are properly rigged. After
RIGGING THE AILERON CONTROL SYSTEM and make certain
CONTROL COLUMN ROLLER ADJUSTMENT
FIGURES 2 AND 3 FORWARD OUTER TUBE ROLLERS
(ROLL
ON THE INNER SQUARE
SHAFT)
FIGURE 2 There
are
four rollers
on
the forward end of each control column which transmit torque to the square inner shaft. are installed with eccentric bolts which allow for adjustment of roller clear-
Two of the rollers of each control column ance.
These two bolts may be identified the shafts clean and
by their
Wipe
b.
Hold
c.
The roller
d.
If the conditions of step
e.
Turn the bolt until the conditions of step
f.
Tighten
g.
Check the other
h.
If the
of the on
firmly against the
shaft.
side of the shaft should turn
freely
nonadjustable
the
opposite
Adjust
the rollers
as
follows:
dry.
a.
one
10-32 threads.
c are
rollers
while
having
no more
not met, loosen the nut on the roller which has the bolt with 10-32 threads. c are
complied
with.
the nut, then recheck the roller clearance in accordance with steps b and
pair
than 0.002 inch clearance.
of rollers
as
indicated in steps b and
adjustment is needed, follow steps d,
e
c.
c.
and f for the second set of rollers.
Repeat this procedure for the other control column.
nzo
27-11-00
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
1?
FORCE
f~lS ROLLER SHOUCD ROLL FREE .002 0~7 LESS
34´•t50-*
Forward Control Column Rollers
Figure CONTROL COLUMN SUPPORT ROLLER ADJUSTMENT
2
(ATTACHED TO
THE INSTRUMENT
SUBPANEL)
FIGURE 3 The
top
two rollers of each control column
support
are
installed with eccentric bolts which may be used for adjust-
ment as follows:
Pull the control column fore and aft until the ers
position of
least clearance between the control column and
Keep the control column in this position while checking probably have its own position of least clearance.
is located.
column will
firmly against the
and/or
adjusting
top rollers.
a.
Hold the control column
b.
The clearance between the control column tube and the lower roller should be 0.005 ~0.002 inch.
c.
If the correct clearance is not indicated, loosen the nuts
d.
Rotate the bolts to obtain the proper clearance.
e.
Tightenthe
f.
Recheck for proper clearance
g.
Repeatforthe
Page
beF4
26/99
nuts.
(step b).
othercontrol column.
27-11-00
two
on
the two top rollers.
support
roil-
the clearance. Each control
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
AILERON REMOVAL a.
Lower the
b.
Support
c.
Pull the aileron
d.
Remove the
flaps
and disconnect the
the aileron and
straight
screws
remove
push-pull
the two
away from the
rod to the aileron tab.
attaching
to avoid
wing
attaching the bonding
screws
from the top and bottom of each
damage
to the
attaching
hinge
bracket.
areas.
cables to the aileron.
AILERON INSTALLATION a.
Attach the
b.
Place the aileron in
bonding
aileron skin and the c.
cables to the aileron.
position on the hinge reinforcing structure.
Install the upper and lower
hinge
brackets. Be
bracket
sure
the
hinge
bracket is in the proper
place
screws.
Pull on the aileron in a direction straight away from the wing to assure that the hinge brackets sitioned. If any movement of the aileron is noted, recheck the position of all hinge brackets. d.
e.
Lower the
flap
between the
and connect the aileron tab
push-pull
rod and install the cotter
are
properly
po-
pin.
AILERON CONTROL CABLE REMOVAL FIGURE 4 and the floorboards in the
pilot’s compartment.
Remove the
b.
Remove the forward passenger seats and the floorboards between the main and
c.
Remove the
trailing edge
pilot’s
and
copilot’s seat,
a.
plates wings.
access
of the
as
gain
necessary to
access
to the aileron cables and
from the cable
pulley
d.
Remove all necessary cable
e.
Disconnect the forward aileron cables from the chain and cable
retaining pins
rear
spars.
pulley brackets
on
the lower
brackets.
assembly at the connector link below the control
column. Install lead lines to both aileron cables. f.
Disconnect the forward aileron cables and the forward outboard
Connect g.
a
lead line to
one
end of the cable and
remove
Disconnect the balance cable at the turnbuckle in each
remove
h.
wing
cable at the turnbuckles in each
wing.
the cable.
wing.
Connect
a
lead line to
one
end of the cable and
the cable.
Disconnect the forward outboard and the aft outboard cables at the bellcrank in each
wing. Identify and
remove
the cables.
~20
27-11-00
Feb
26/9 Page
5
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
i. WHEEL 2. COLLAR ASSEMBLY 3. COLUMN TORQUE TUBE 4. ELEVATOR TORQUE ARM 5. ELEVATOR TORQUE TUBE 6. ELEVATOR BELLCRANK 7. ELEVATOR TORQUE TUBE SUPPORT 8. 808 WEIGHT ASSEMBLY S.CQUAR 10. COLLAR ASSEMBLY 11. ELEVATOR PUSHROD 12. CONNECTOR 13. INNER COLUMN GUIDE 14. INNER COLUMN TORQUE TUBE
.SU-JOIM iTROPPUS
16. SPROCKET 17. TAPER PIN 18. SPROCKFT
q 21
19 18
.91TUNFORWARD SUPPORT
1
16
20. 21. COTTER PIN 22. SUPPORT. ROLLERS
Ip
11
;I
15
17
110
4
7--,
~1 17
4
~’B
I
3
8
I
5 22 17
2
17 c
111\\ t
1
36155-\4
Control Column
Figure
Page 6 Feb 26/99
27-11-00
3
A20
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
O
F.S. 96.00
Q
F.S. 84.358
DETAIL
C
DETAIL
RIGHT AILERON UP
B
RIGHT AILERON
BALANCE CABLE
LEFT AILERON UP
F.S´• 117.187
BALANCE CABLE~ I
D
A
C
DETAILD F.S. 112000
LEFT A1LERON VP
AILERON TAB
ACTUATOR
B BALANCE CABLE
i a
TEMPERATURE CABLE rr#SIOIJ GRAPH
TTRAVEL
STOPS
AILERON CABLE
I
I
SURFACETFIA~EL
DETAILE DETAIL
A
AILERON
35~5LBS AT 59~F BUNGEE
SPREKiS CONNECTED
20" 20"
~I a
g
BEUCRANK
I’
2" UP 2’ DOWrl 10
20
.30
-40
50
60
TEMPERAfURE AIIlRON TAB
F.S.
APPROXIMATE FUSiLAGE STATION
10 LBS +-5 LBS -0 LBS AT
9"~ 0 9"t 0
70
80
90
100
110
120
"F
1" UP 1´ WWN
59"F
36151-18
Aileron
(E-1946,
A20
System
E-2104 and After, EA-320 and Figure 4
27-11-00
EA-389)
Feb
26/99Page
7
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
THIS PAGE INTENTIONALLY LEFT BLANK
Page
8
Feb 26/99
27-11-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
AILERON CONTROL CABLE INSTALLATION FIGURE 4 a.
Connect the forward outboard and the aft outboard cables to the bellcrank in each
wing.
Route the cables in-
board and disconnect the lead lines. b.
Route the balance cable
through
wing,
one
the
fuselage,
then
through
the
opposite wing. Disconnect the wing.
lead
line and connect the balance cable and the aft outboard cables to the turnbuckles in each c.
Route
one
end of the aileron cables outboard in each
wing,
and the other end forward to the control column.
Connect the cables to the turnbuckles at the forward outboard cable in each
both aileron cables at the connector link below the control column.
d.
Connect the chain and cable
assembly to
e.
Install all
pulley
f.
Rig
g.
Install the
h.
Install the floorboards and the forward passenger seats.
i.
Install the floorboards and the
retaining pins
the aileron control access
in the
wing.
brackets.
system.
plates
on
the lower
pilot’s
trailing edge
and
copilot’s
of the
wings.
seats.
WAANINO I I WARNING Make certain that as
cables, chains,
insulation, tie wraps,
etc. do not interfere with control
components such
etc.
Check for correct direction of movement
by moving
the control wheel. When the control
wheel is moved to the left, the left aileron should move up and the right aileron move down. When the control wheel is turned to the right, the right aileron should move up and the left aileron down.
RIGGING THE AILERON CONTROL SYSTEM NOTE
Company recommends the use of the aileron travel gage shown in the SPECIAL Chapter 12-20-00. The front of the travel gage should be located over the leading edge skin splice with the aft portion over the number 8 wing rib (just outboard of the inboard aileron hinge). Raytheon
I
Aircraft
TOOLS in
a.
Aileron and tab surfaces must
b.
Place the aft
the locknuts
on
c.
Tightenthe
d.
Rig
neutral
arm
with the upper and lower surfaces of the
of both aileron bellcranks
both ends of the
push-pull
wing
within 1/16 inch.
parallel to the adjacent wing rib. If the aileron is adjust the push-pull tube until the aileron
tube and
not in
neutral, loosen
is in neutral.
locknuts. on
the control wheels
may be ~0.06 inch off of the
nm
align
by placing straightedge.
a
straightedge
across
the top of the two control wheels. One
27-11-00
grip
9
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL e.
Assure that the ends of the chain around the
centerline of the
are
within
one
link of
equidistance
from the
sprocket.
if the link stop
f.
control column
right
assembly
is not centered with respect to its stop,
adjust the
turnbuckles to center the link.
Place a vertical load of two pounds on the top chain near the airplane centerline. The chain should deflect 0.25 g. ~0.06 inch. Adjust the turnbuckles as necessary to obtain this deflection. h.
Connectthe
bungeesprings.
With a straight rig pin installed between the pilot’s rudder pedals and with a simulated (10 Ibs.) cable tension, i. adjust the turnbuckle above the forward aileron bungee spring until both bungee springs are extended equally ~0.06
inch.
j.
Adjust the turnbuckles
k.
Remove the
i.
Adjust
m.
Tighten
n.
Rig
o.
Be
in the wheel wells to
straightedge
on
(primary stops)
(00).
for
a
deflection of 20 ~2" up, and 20 lt2" down from neutral.
the bellcrank stop bolts.
the aileron cables to the tension indicated in sure
the ailerons to neutral
from the control wheels.
the aileron bellcrank stops the locknuts
bring
each bellcrank contacts its upstep at the
Figure same
4. Use the turnbuckles in the wheel wells.
time the bellcrank in the
opposite wing contacts
its down-
stop. p. Set the secondary stop bolts (the stop link at the forward end of the control clearance from the stop with the ailerons at full travel (both right and left).
column) to
maintain 0.06 to 0.12 inch
q. With a straight rig pin installed between the pilot’s rudder pedals, the control wheels should center within 5" of neutral. If necessary, readjust the vertical turnbuckle above the forward bungee spring and the aft turnbuckle in the
wheel well
as
required
to center the control wheels.
r.
Recheck cable tension and
s.
With the ailerons
10"
right
t.
Connect the
or
left of
safety the turnbuckles.
Make certain all locknuts
fully rigged (bungee springs disconnected), neutral shall not exceed 15 inch-pounds.
the torque
are
required
tight. to move either control wheel
bungee springs.
WARNING IWI\RNINO
by moving the control wheel. When the control wheel is moved to the left, the left aileron should move up and the right aileron move down. When the control wheel is turned to the right, the right aileron should move up and the left
Check for correct direction of movement
aileron down. u.
Removeall
Page
rigging pins.
27-11-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
AILERON TAB A trim tab has been installed in the left aileron which is controllable from inside the
tab is controlled
through
normal cable and chain
linkage to
a
airplane while in flight. The aileron pedestal with the indicator.
control wheel located in the
AILERON TRIM TAB CABLE REMOVAL seat and the left floorboard.
a.
Remove the
b.
Remove the lower forward
c.
Remove the forward left passenger seat and the floorboard.
d.
Remove necessary
e.
Remove the cable
f.
Disconnect the tab cables at the turnbuckles in the left
g.
Remove the cable
h.
Remove the outboard cable from the actuator sprocket. Remove the cable
through the
actuator
i.
Remove chain master link at the
Remove cable
through the
actuator
pilot’s
upholstery panel
access
plates
retaining pins
stops
at
wing
to
gain
at the
on
the left side of the
access
pulley
to the trim tab
pedestal.
cables, actuator, and cable pulley brackets.
brackets.
wing. Identify
and connect lead lines
on
the cable ends.
station 43.375.
sprocket
on
the
pedestal.
access
opening.
access
opening.
AILERON TRIM TAB CABLE INSTALLATION
pedestal sprocket
a.
Position the chain of the forward tab cable around the
b.
Route the cable ends aft in the
c.
Position the chain of the outboard cable around the actuator
d.
Install the cable stops at
e.
Install the cable
f.
Rig
g.
Install all
h.
Install the floorboard and the left forward passenger seat.
i.
Install the floorboard and the
j.
Install the
and outboard into the left
wing
sprocket
and disconnect the lead lines.
and route the cable ends inboard.
station 43.375 and connect the cables at the turnbuckles in the
wing
retaining pins
the aileron trim tab control access
fuselage
and install the chain master link.
in the
pulley
wing.
brackets.
system per AILERON TRIM TAB RIGGING in this chapter.
plates in the left wing.
upholstery panel
pilot’s
on
seat.
the left side of the
pedestal.
WARNING IWARNINOI Make certain that insulation, tie wraps, etc. do not interfere with control components such as cables, chains, etc.
plane with respect to the aileron when the aileron is moved. When the tab control wheel is turned to indicate left wing up, the aileron tab should move up. If the aileron and aileron tab do not move in the proper direction, recheck rigging. The aileron tab should stay in the
same
27-11-00Page
11
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
AILERON TRIM TAB RIGGING
NOTE Place the aileron in neutral. a.
Place the aileron trim tab control in neutral
b.
Place the aileron in neutral
position
position.
and connect the trim tab to the tab actuator.
By turning the sprocket on the actuator, adjust the trim tab to both extremes of travel; measure both settings return the tab to the midpoint of the two extremes of travel. This will place the actuator in the neutral position.
c.
d.
If the trim tab is not in the neutral
tral
position.
e.
Center the chain
f.
Set the aileron tab stop
stops
to 40 to 60
on
the
sprocket W.S.
(at inch-pounds.
g.
Rig
h.
Check trim tab travel,
cable tension and
position
and
safety all
tighten the
43.375)
adjust travel
completion
upon
as
adjust the pushrod
to
place
the tab in
neu-
cable.
to obtain
noted in
of step c,
and
a
surface deflection of 9" +0" -1" up and down.
Figure
Torque
the
4.
turnbuckles and stops.
WARNING I I wnrc#l~a After rigging the aileron and aileron tab control system, check for correct movement of the control surfaces with respect to the movement of the controls. The aileron tab should stay in the same plane with respect to the aileron when the aileron is moved. When the tab control wheel is turned to indicate left wing up, the aileron tab should move up. If the aileron and
aileron tab do not move in the proper direction, recheck the
rigging.
AILERON TRIM TAB ACTUATOR REMOVAL a.
Remove the
b.
Disconnect the outboard cable at the turnbuckles in the
c.
Remove the outboard cable from the actuator
d.
Disconnect the actuator from the trim tab
e.
Remove the bolts
access
plates
at the actuator.
attaching
wing.
sprocket.
linkage.
the actuator to the
wing
structure. Remove the actuator.
AILERON TRIM TAB ACTUATOR INSTALLATION a.
Position the actuator
b.
Connect the actuator to the tab
c.
Install the outboard cable
d.
Connect the cables at the turnbuckles in the wing.
Page
beF21
26/99
against the wing
on
structure and install the
attaching
bolts.
linkage.
the actuator
27-11-00
sprocket.
nzo
Ral(theon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL the ai\eron trim tab control system.
e.
Rig
f.
Install the
access
plates
at the actuator.
AILERON TRIM TAB ACTUATOR DISASSEMBLY FIGURE 5 a.
Remove the pins from the nut
assembly (5) and sprocket (1)
and
the
remove
sprocket (1)
from the actuator
as-
sembly. b.
Remove the snap
c.
Remove the actuator
d.
Remove the
(Il)from
the
ring (10)
from the actuator
(8) from
screw
the nut
housing (6), and pull
the nut
assembly (5)
out of the
housing.
assembly.
pins from the actuator screw (8) and the actuator rod end (11) and remove the actuator rod end screw (8). The bearing (4) and the bushing (9) can now be removed from the screw.
1.
Sprocket
8. 9. 10. 11. 12. 13.
2. Check Nut 3. AdSustinO Bushing 4. Bearing 5. Nut Asselhbly 6. Actuator Housing 7. Bracket
3
4
Actuator Screw
I
Bushing
Snap Ring
7
8
Actuator Rod End Tube End Actuator Tube
5
I 13
"e
12
~fi io 3
ii
4
THns as4es9AA
Aileron Trim Tab Actuator
Figure 5
A20
27-11 -00
Feb
26/9 Page
13
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL e.
Remove the check nut
f.
Remove the
and
(2),
screw out
from the nut
bearing (4)
the
with
adjusting bushing (3)
a
spanner wrench.
assembly.
AILERON TRIM TAB ACTUATOR ASSEMBLY
NOTE lubricate all
During assembly bearing (4)
a.
Install the
b.
Install the other
c.
Install the actuator
d.
Push the nut
e.
Use
housing
the nut
on
bearing (4)
and
bushing (9)
(11,
Chart 1,
91-00-00).
on
the actuator
screw
ring (10)
in the
(8).
assembly.
into the actuator
assembly
with grease
assembly (5).
in the nut
screw
moving parts
housing (6),
and install the snap
housing.
spanner wrench to install the adjusting bushing (3) into the housing until the end play between the screw and nut assembly is less than 0.025 inch. If the end play cannot be reduced to within limits, replace the a
actuator.
f.
Install the check nut
g.
Install the actuator rod end
h.
Align the
i.
Install the
j.
Align the
(2)
holes in the
the
on
adjusting bushing.
(11)
screw
sprocket (1)
holes in the
on
(8)
the
on
screw.
with those of the actuator rod end
the actuator
sprocket (1)
(11)
and install the two
pins.
assembly.
assembly (5)
with those in the nut
and install the two
pins.
CHECKING AILERON TRIM TAB FREE PLAY FIGURE 6
Visually inspect
the aileron trim tab for
damage, security of hinge attach points, and checking the free play of the tab.
for
tightness
of the
actuating
system. Inconsistencies must be corrected before
(P/N 45-135030-9/810) or equivalent, a dial indicator, and a push-pull scale loading to the tab are required for making the inspection for tab free play. Refer to Figure 6.
A check fixture
applying
for
accurate
a.
Securely lock the
control surfaces to prevent movement of the ailerons. Set the aileron trim tab in neutral.
b.
Use shot
hold the dial indicator check fixture
bags to
tab
hinge
line and
c.
Apply
a
small
on
the outboard
edge
so
that the
point of the dial
indicator is 2.0 inches aft of the
of the aileron tab.
piece of masking tape (for paint protection) 4.0 inches aft of the tab hinge line point of pressure against the tab by the push-pull scale.
and
along the
cen-
terline of the tab actuator. This is the
Apply
e.
Set the dial indicator at
f.
With the
g.
Release half of the load to obtain
Page
another
piece of masking tape
d.
zero.
push-pull scale
on
in the
corresponding
location
on
during
the
Do not reset the dial indicator
the
masking tape, apply a
27-11-00
1.5
a
3.0
pound downward
pound
the bottom surface of the tab.
checking procedure.
downward load. Record the dial
load. Record the dial
reading
as
reading
as
A.
B.
nzo
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL h.
On the
masking tape
on
the bottom surface,
Release half of the load to obtain
Enter the recorded
j.
readings
on a
a
1.5
3.0
copy of Chart 1 and
SubtractAfromBand recordasX.
2.
Multiply Bby2and
3.
Multiply
4.
SubtractCfrom2Dand recordasY.
pound upward
load. Record the
proceed
as
load. Record the dial
reading
as
reading
as
C.
D.
follows:
recordas2B.
2 and record
by
a
pound upward
1.
D
apply
as
2D.
NOTE X and Y 5.
Add X and Y and record
(E
I.
If the free
play
determine the
be
negative
numbers.
E.
as
MAXIMUM)
0.094 INCH
k.
can
is
over
cause.
All
the maximum
worn
parts
specified in Chart 1, inspect replaced.
all components of the tab actuator system to
must be
AILERON TRIM TAB FREE PLAY INSPECTION
1
FIGURE 6 This check should be
performed
at least once
a
year to
ensure
that the trim tab free
play falls
within the
prescribed
limits.
(P/N 45-135030-9/810) or equivalent as shown in Figure 6, a dial indicator, and a push-pull scale for I applying accurate loading to the tab are required for making the inspection for free play of the tab.
A check fixture
a.
Securely
lock the control surfaces to
prevent
movement of the ailerons. Set the aileron tab in the neutral
posi-
tion.
Using shot bags, affix the dial indicator check fixture hinge line and on the outboard edge of the aileron tab. b.
c.
Apply
a
small
d.
that the dial indicator
point
is 2.00 inches aft of the tab
masking tape (for paint protection) 4.00 inches aft of the tab hinge line and along actuator. This will be the point of pressure against the tab by the push-pull scale.
piece
centerline of the tab
so
of
Apply another piece of masking tape in the corresponding position on the
bottom surface of the tab for the
the
same
purpose. e.
Zero the dial indicator at
f.
With the
ing
as
push-pull
no
scale at the
initially.
Do not reset
during
the
checking procedure.
point of masking tape, apply a full £
downward load. Record the dial read-
A.
g.
Release half the load until
h.
Apply
i.
Release half the load until
~2(1
load
a
full
a
3-pound upward a
1.5-pound downward load at the
load is obtained. Record the dial
masking tape
l.£ upward
on
reading
as
the bottom surface. Record the dial
load is obtained. Record the dial
reading
as
B.
reading
D.
27-11-00
as
C.
Rayeheen Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
Enter the recorded values
j.
on a
copy of Chart 1 and
proceed
as
follows:
recordas2B.
1.
MultiplyBby2and
2.
SubtractAfrom 28 and record
3.
MultiplyDby2and recordas2D.
4.
Subtract C from 2D and record
as
as
X.
Y.
NOTE The results of X and Y 5.
k. All
Add X and Y and record
If the free worn
play
as
be
negative
numbers.
E.
inspect
exceeds 0.094 inch,
parts should be
can
all components of the tab actuator system to determine the
cause.
replaced.
CHART1 AILERON TAB FREE PLAY LIMITS 3-POUND
I.5-POUND READING
READING
2B
-A
=X
2D
-C
=Y
X
+Y
=E
(E=O.Og4-inch maximum)
Page
bef61
26/99
27-11-00
A20
RRyliheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
9
to\i
12
678
13
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.5 IN
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--1-!5
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25 IN
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mM
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1
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NO. .68 IN 8 aluminum or
2
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1/2
3
x
x
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x
10 aluminum
4
1
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5
1
3/4
6
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1
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10
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3/8 1/4
x
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11
i
12
2
13
2
14
2
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x
2 1/2 x 14 aluminum x
equiv.
or
equlv.
stl. 56.
II
I
II
1
1.6~
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10 rubber
x
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13
equhr.
or
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13
SECTION A
A
THIS GROOVE TO BE A SNUG FIT To THC 5CR5W 8840881 ON THE DIAL INDICATOR
R. I.
loo-lss.a
Fabricating Clamp for Tab
Deflection
Figure 6
A20
27-1100
Feb
26/99Pagel7
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
MAINTENANCE PRACTICES
RUDDER AND TAB
RUDDER
(F33A, F33C, A36, A36TC,
AND
B36TC)
WARNING I WARNING) On
CE-1566 and after; E-1946, E-2104, E-2111 and after; EA-320, EA-389 and coding on all parts when replacing or installing control cables,
airplane serials
after,
observe the color
bellcranks and /or other control system components. DO NOT connect parts of parts of a different color.
one
color to
coded
RUDDER REMOVAL a.
Detach the tail cone, disconnect the tail
b.
Remove the tail section
c.
Remove the four attach bolts from the rudder bellcrank.
d.
Disconnect the rudder
e.
Removethe rudder.
access
hinges
doors
navigation light
wire and
remove
the left hand side of the aft
on
and rudder
bonding
the tail
cone.
fuselage.
cable.
RUDDER INSTALLATION a.
Placethe
b.
Connect the rudder
c.
Install the rudder bellcrank attach bolts
d.
Installtheaccess doors.
e.
Connect the
f.
Install the tail
A20
rudderinposition. hinges
and
navigation light
bonding
cable.
(torque
to 50 to 70
inch-pounds).
wires.
cone.
27-20-00
Feb
26/99Page
1
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
Rig
Pin
CL
CL 0.38’’ to 0.45"
8-8
t
s,
8
i
A-A
Rig Pinr: 3/8" dio. x 2-1/8" Long 8loc1(: 1/2" w 1" x 2" Long
Rudder Pedal
Figure
Page
be26/99 F2
27I20-00
Rig
Tool
1
A20
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
OETAILA
LEFT RU]DER CABLE
F~3A lCE-lAE, AH) AFTER) FEED A)c~) AFTER) RUDDER PEDAL STOPS
RUDDER BELLCRAM< STOPS
RIGHT RUDDER CABLE
D
A
LEFT RUDDER CABLE
RIGHT RUDDER
CABLE
RMOER PEDAL STOPS
i~B
A36 (E-IIIl. E-12~1 AHI AFTERI A5~6n: TEA-I TCIRII u-nr. pceEm 99-262) B;HTC (EA-UZ´• AH9 AFTER) ATTACH BOLTS
OETAIL E
DETADL D
mA4B
mAILc
/I Rudder
System
Figure
A20
2
27-20-00
Feb
26/99Page
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
THIS PAGE INTENTIONALLY LEFT BLANK
Page
beF4
26/99
27-20-00
A20
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CABLES
CABLE
RUDDER
25
TENSION
5 LBS LBS AT 59’ F
SURFACE 25 AND
LEFT RIGHT
TRAVEL
ALL F33A AND A36TC. F33C PRIOR TO CJ-156 WITHOUT KIT 33-4002-1,
A36 PRIOR TO E-2111 EXCEPT E-1946 AND E-2104 20
+0 AND
-1 LEFT RIGHT
B36TC
25 +1 20 +O
LEFT -I RIGHT
F33C,
23 +O -1 LEFT AND RIGHT OF NEUTRAL
TEMPERATURE
CABLE
CJ-156 AND AFTER. AND EARLIER F33C’S WITH KIT 33-4002-1
E-1946. E-2104 AND E-2111 AND AFTER
TENSION GRAPH
50
40
g 5 g H
30
20
10
10
20
30
40
50 60 70 TEMPERATURE- ’F
80
90
100
110
120
EA278 984801AA
Rudder Cable Tension and Surface Travel Data
Figure
A20
3
27-20-00
Feb
26/99Page
5
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL RIGGING THE RUDDER CONTROL SYSTEM
I
FIGURES 2 AND 3
NOTE
rigging of the rudder pedals a rigging tool may be fabricated from a steel block 1/2 inch X 1 inch X 2 inches; and two 3/8-inch- x 2-1/8-inch-long pins. The rig pins are located parallel and forward of the block, one on each side, and welded. The rig pins should be spaced as noted in To facilitate
Figure
1.
a.
Place the rudder
b.
Install
c.
With the bellcrank in the neutral
graph
in
a
rig
pedals
in the aft
tool in the holes
Figure
3, then
remove
position.
provided
the
in the
pilot’s rudder pedals.
position, rig the rig pin.
cables to the tension shown
on
the temperature cable tension
NOTE Installation of the
justment The d.
right
Adjust the
as
the
rig pin in the pilot’s pilot’s pedals.
hand rudder
pedals
are
rudder
rigged
pedals
0.38
as
Adjust the rudder pedal travel at the rudder pedal stops immediately prior to contact with the rudder pedal stops.
f.
Make
Page
sure
that the rudder movement
27120100
corresponds
bring
the
copilot’s pedals
0.45 inch forward of the neutral
rudder travel at the rudder bellcrank stops
e.
will
indicated in so
Figure
to the same ad-
position.
2.
that contact with the rudder bellcrank stops
to the movement of the rudder
occurs
pedals.
A20
~eechcraft BONANZA SERIES
MAINTENANCE MANUAL RUDDERVATOR AND TAB MAINTENANCE PRACTICES
jig assembly Figure 1, Detail E) to position the differential mechanism in the neutral position. The jig assembly will position the differential mechanism of the right tail e.
I
RUDDER
I
Install the differential mechanism
(refer
(V35B)
to
RUDDER RIGGING PROCEDURE
control arm aft of the differential mechanism for the left tail control arm with the elevator and rudder sys-
(Flgure
tems in neutral.
1
NOTE
NOTE
All rudder
rigging should be accomwith a travel board installed. A plished bubble protractor should not be used for any rudder rigging procedure.
jig assembly is
The rudder system and elevator system are separate systems forward of the
tems
The 35-590087 differential mechanism to be used with the 35-590087-9 stop installed.
With the rudder, elevator and tab syscorrectly adjusted and in neutral,
the differential mechanism tail control
empennage. The control surfaces for both the rudder and elevator are the same
(rudder)
parts. The rudder and elevator
control surfaces will be referred to
Adjust the stops on the aft fuselage bulkhead to permit a maximum combined ruddervator travel as shown on the overall travel tables. Refer to Figure 1. With the
adjusting
on
the
nose
link at the rudder
wheel and
jig assembly,
are
per
Figure
d.
Position the control column in the neutral position with 4-112 inches (4-3/4 inches on D-10359 and after) between the collar on the instrument panel and split collar on the control column. This can be accom-
plished by cutting a block 4-1/2 (or 4-3/4 for D-10359 after) inches long and taping it to the control col-
umn.
rig tool and the
are
installed with
position with tempera-
ture cable tension
graph.
The trim tab
system is in neutral when the cockpit indicator is at 0", the cable tensions are
1, 27-20-00.
and
the rudder
the cable tensions set to the
tool in
each side, and
spaced
positioned jig assembly.
the ruddervators in the 0"
the rudder
pins. See Figure 1, 27-20-00. The rig pins are located parallel and forward on oneon
is to be
control column block
set to the
The left rudder pedal is rigged .38 to .45 inch aft of the neutral position. To facilitate rigging of the rudder pedals to these dimensions, a rigging tool may be fabricated from a steel block 1/2 x 1 x 2 inches, and two 3/8 x 2-1/8-inch-long rig
pins
arm
The elevator and rudder system are in neutral when the differential mechanism
NOTE
the block, welded. Rig
(center)
inside the hole in the
aft of the rudder
Straighten position pedals in neutral position with an aligning (rig) the pedals. Refer to Figure 1, 27-20-00. c.
the differential mechanism elevator
control
quadrant, pedals, lengthen or shorten as necessary to align the copilot’s pedals with the pilot’s pedals. When aligning the pedals, be sure both sets of pedals are in the same position. just
the
jig assembly and the out(legs) of the jig assembly are lightly contacting the forward side of the fuselage station 256.9 bulkhead. The nut
a.
b.
lightly contacting
mechanism board ends
as
ruddervator.
located
arms are
aft side of the 35-590087 differential
temperature cable tension
are at O" or symgraph metrically split. The tabs are at 00 when their trailing edges align with the trailing edges of the ruddervators.
and the tabs
Adjust the short, lower elevator cable to a total length of 23.62 ~.06 inches as measured from the center of its attachment points at the reduction bellcrank and the differential mechanism. Refer to Figure
f.
5. No threads on the turnbuckle should be visible out-
adjustment. Safety the turnadjustment of this cable is required.
side of the barrel after buckle. No further
g. Adjust the main rudder cable tensions to the tension shown on the temperature cable tension graph. Refer to Figure 1. (The cables can be adjusted simul-
taneously with the rudder balance cable.) The balance cable is adjusted by adding or removing washers 27-21-00
Page A19
1
Mar 29/96
I
BONANZA SERIES MAINTENANCE MANUAL
TEMPERATURE CABLE TENSION GRAPH 60
I
RUDDER TRAVEL
OVER-ALL TRAVEL
(COMBINE RUDDER AND ELEVATOR)
50
I
40
LEFT 23"
i
10 UP
260
~1" DOWN
LEFT
RIGHT 26" i 23"
10 UP
10 DOWN
RIGHT
440
20 UP
35"
20 UP
370
+2" DOWN
40"
+20 DOWN
i;
Z
O
n
i
a
t
-~if"i
H
30
4
H
o
H
cci
s
BALANCE CABLE
LH. PEDAL
R.H. PEDAL w
RUDDER
I
RUDDER PEDAL SETTINGS
3
H
NEUTRI\L POSITION
20
.38 TO .45
r:
INCHES AFT OF
c~Lj
NEUTRAL POSITION L:
-tct
10 20
30
40
50
60
70
80
90
100
110
TEMPERATURE-F"
35-590087 AND 35-590087-9 DIFFERENTIAL MECHANISM
JIG ASSEMBLY FUSELAGE STATION 151.0
FUSELAGE
STOP BOLTS
DETAIL
STATION 170.0
A RIGHT RUDDER
PEDAL
CABLE
POSITION LEFT RUDDER
ADJUSTING
CABLE
LINK
B DETAIL
LA
D DIFFERENTIAL MECHANISM
DETAIL
/I ~71
DETAIL
DETAIL
E
C
B: 35-153-17 003
Rudder
System (V35B) Figure 1
27-21-00
Page 2 Aug 18/95
A18
BONANZA SERIES MAINTENANCE MANUAL
pulley bracket. and rudcolumn control The differential mechanism, neutral in their der pedals are still to be positions after behind swivel bolt
cable tensions
on
are
the balance cable
RUDDERVATOR REMOVAL
(Figure 2) NOTE
adjusted.
The rudder system and elevator system are separate systems forward of the empennage. The control surfaces for both the rudder and elevator are the same parts. The rudder and elevator
Set the ruddervators in the neutral position (O") by adjusting the length of the control push-pull rods. Make sure the rod ends remain screwed the required length into the push-pull tubes. They should extend h.
past the inspection hole, i.e.
though
the
inspection
a
wire should not pass
control surfaces will be referred to ruddervator.
hole.
Remove the differential mechanism jig assembly remove the rudder pedal rig tool. Leave the control column 4-1/2- (or 4-3/4- for D-10359 and after) inch-long block in place to prevent elevator system i.
Before
and
influence
on
rudder
When ruddervator travels are correct, tighten the jamnuts, the rudder stop jamnuts, safety the turnbuckles, safety the nut on the swivel bolt on the pulley bracket of the balance cable and recheck travel. rod end
Remove the elevator column 4-1/2-
after) inch-long
Changing rudder rigging ging. Check elevator rigging ging. i.
hinge the
line. If any movement exists, find of the looseness. If any hinge
cause
bolt, bearing
k.
D-10359 and
disassembly check the ruddervaperpendicular to the
tor for movement
rigging.
j. Set the rudder travel by adjusting the stop bolts (refer to Figure 1, Detail A) just aft of the pilot’s rudder pedals. Refer to Figure 1 for the applicable table of travels and the appropriate rudden/ator travel values. Steps b through h should result in the ruddervator travel being correct or nearly correct. Make any final minor adjustments by lengthening or shortening the control push-pull tubes. Make sure the rod ends remain screwed the required length into the push-pull tubes. They should extend past the inspection hole, i.e. a wire should not pass through the inspection hole.
(or 4-3/4-
wear,
I -´•I´•´•I WARNING
Remove the
a.
or
bushing shows signs replaced.
of
must be screws
holding the tail
cone
Remove the tail
b.
in
posi-
cone
and disconnect the
naviga-
side and bottom
panels.
wire.
tion
light
c.
Remove the aft
d.
Remove the 5/16-inch bolt from the
fuselage
push-pull
tube. e.
inspection hole,
the open left side
Working inside
release the tab cable tension, then fasten the ruddervator tab cables so that no slack in the cables will be
transmitted
beyond
the affected tab.
NOTE
for
change elevator rigchanging rudder rig-
they
tion.
Identify the cables so that they may be reinstalled in the proper location.
block.
may after
as
f.
g.
Disconnect the elevator tab cables at the tab. Remove the
guide
block located
on
the tab cable
at the front of the ruddervator.
h. i.
Remove the cotter
pins
from the
Remove the nuts from the three
hinge
bolts.
hinge bolts.
NOTE Check the ruddervator for the correct direction of movement by working the rudder pedals. When the left rudder pedal is depressed, the left ruddervator should move down and the right
Support the
twist when the
fall or removed.
down.
so
that it will not
hinge bolts
are
position of the washers in each hinge assembly. Tag each hinge assembly as to the location of the washers. Refer to Figure 2. Note the
ruddervator should move up. When the right rudder pedal is depressed, the left ruddervator should move up, and the right ruddervator should move
ruddervator
j.
Remove the bolts from the
hinges. 27-21 -00
Page A19
3
Mar 29/96
aeechcrrdt BONANZA SERIES MAINTENANCE MANUAL k. Remove the two bonding attached near the hinges.
i.
jumpers which
are
Install the nuts bolts. d.
hinge
NOTE The center and outboard
require
(Figore 2)
hinge bolt each
two AN960-10 washers under
the nut. If the bolt
1´•U´•1~1WARNING
grip length,
Torque the nuts to tightened up to cotter pin holes.
one
inch-pounds; they inch-pounds to align the
e.
20 to 25
may be
40
f.
h.
The elevator/rudder control surfaces will be refered to as ruddervator.
Install the cotter
pins
in the
hinge bolts.
Connect the tab cables to their
NOTE
the ruddervator in its proper position. Make sure the hinge bushings are installed in the hinge halves on the stabilizer.
The bolt connecting the cable to the tab horn should be tight enough to prevent rattle, but loose enough to swivel. If the bolt is too tight, the tab control system will bind.
NOTE or
must be
bushing replaced.
The maximum wear for the inboard bearing is.001-inch radial and .025-inch axial. Install the
bonding jumpers at the center and outboard hinges (two 105090D032-1D washers go between the screw head and skin).
respective tab
horn.
Support
showing signs of wear
long
g. Install the guide block for the tab cable at the front of the ruddervator.
NOTE
Any hinge bolt, bearing
is too
additional washer may be added under the nut.
Airframe vibration may be caused by worn elevator hinges, mlsthreaded trim tab hinges, loose stabilizer attachment or any Improper Installation which will allow free play.
b.
the center and outboard
Remove the ruddervator.
RUDDERVATOR INSTALLATION
a.
on
i.
Remove the fasteners which were installed to prebeing transmitted to the rest of
vent cable slack from
the tab system.
j. k´• i.
Using the notes made during removal (refer to Figure 2), install the proper washers and bolts in the hinges as follows:
Install the 5/16-inch
install the aft
push-pull tube
bolt.
fuselage inspection panels.
Connect the tail
light
wire and install the tail
cone.
c.
NOTE Check for proper ruddervator and trim tab travel after installation is complete. When the control column is pulled back, the correct ruddervator movement is up. When the elevator trim tab control is moved toward the nose-up position, the trim tab should move DOWN. When the elevator trim tab control is moved toward the nose-down position, the trim tab should move UP.
NOTE Install the bolts with the nuts toward the
fuselage. The inboard hinge requires two AN960-416L AN960-416 washers. Install one AN960-416L washer under the bolt head and one between the torque fitting and the ruddervator inboard hinge support. One AN960-416 washer should be installed under the 1,
and
one
nut.
ELEVATOR TRIM TAB REMOVAL
Torque the be tightened up to pin holes. 2.
inch-pounds, It may inch-pounds to align the cotter
nut to 30 to 40
70
(Figure 3) a.
Remove the
screws
from the tail
cone.
27-21-00
Page
4
Mat 29/96
A19
BONANZA SERIES MAINTENANCE MANUAL
2 3 4 5 6 7 8
2
STABILIZER BOLT WASHER ELEVATOR (RUDDERVATOR) NUT WASHER WASHER TORQUE FITTTNG
INBOARD
HINGE SUPPORT
3
ao I
a
:o: J
a a
8
7
6
5
O
4 C95012783131
Ruddervator Installation
Figure
2
27-21-00
Page A19
5
Mar 29/96
’iS)eechcraft BONANZA SERIES MAINTENANCE MANUAL Disconnectthe electricalwiresand removethetail
b.
ELEVATOR RIGGING PROCEDURE
cone.
NOTE
pin from
Remove the cotter
c.
the control cables
rigging must be accomplished with a travel board installed. A bubble protractor should not be used for any elevator rigging procedure. All elevator
devises and trim tab. Remove the nuts, washers and bolts from the
d.
control cable devises.
Support the trim tab so that hinge pin is removed.
e.
it will not fall
or
twist
when the f.
Remove the
Adjust the stops on the aft fuselage bulkhead to permit maximum combined elevator/rudder (rudden/a-
a.
wire from the trim tab
safety
hinge
pin.
as shown in the table of travels under OVERALL TRAVEL in Figure 4.
torj travel the
g.
Unclip
h.
Pull the
hinge pin.
hinge pin
out and remove the elevator
b´•
Position the control column in the neutral
position
trim tab.
with 4-1/2 inches (4-3/4 inches on D-10359 and after) between the collar on the instrument panel and the
ELEVATOR TRIM TAB INSTALLATION
split collar on the control column. This can be accomplished by cutting a block 4-1/2- (or 4-3/4- for D-10359 and after) inches long as applicable and taping it to
(Figure 3) a.
Support
the elevator trim tabin
position
on
the
ruddervator.
Install the trim tab
hinge pin. Refer
c.
Clip
in
d.
Connect the control cable devises to the trim tab
hinge pin
position
and
to
Figure
safety
3.
wire.
with the bolts, washers and nuts.
NOTE The devises should be tight enoi~gh that they will not rattle but loose enough so that they will swivel. If the devises are too e.
f.
Straighten the nose wheel and adjust the pilot’s rudder pedals (fore and aft) to the same position. Install the rudder pedal rig tool in the pilot’s rudder
c.
b.
the
the control column.
tight, binding may
Install the cotter
pins
occur.
in the clevis bolts.
Connect the electrical wires and install the tail
cone.
NOTE Check that the trim tab moves in the correct direction as indicated by movement of the controls.
ELEVATOR AND TAB
(V35B)
NOTE The rudder system and elevator system are separate systems forward of the empennage. The control surfaces for both the rudder and elevator are the same parts. The rudder and elevator control surfaces will be referred to as ruddervator.
pedals
to
place
them in the neutral
position
and to
prevent rudder system influence on´•elevator rigging. The left rudder
pedal
is aft of the
right
rudder
with the system in neutral. Use an offset shown in Figure 1, Chapter 21-20-00. d.
Install the differential mechanism
position
rig
pedal
tool
as
jig assembly to posi-
the differential mechanism in the neutral
accomplished with the 35-590087 differjig assembly with the 35-590087-9 stop (refer to Figure 1, Detail E) installed. This will position the right tail control arm of the differential tion. This is
ential mechanism
mechanism aft of the left tail control arm with the elevator system and rudder system in neutral.
Adjust the short, lower elevator cable to a total length of 23.62 ~.06 inches as measured from the center of its attachment points at the reduction bellcrank and the differential mechanism. Refer to Figure e.
5. No threads
on
turnbuckle ends should be visible
adjustment. Safety the turnadjustment of this cable is required.
outside of the barrel after buckle. No further
Adjust the upper and lower (forward of the reducbellcrank) elevator cable turnbuckles simultaneously until cable tensions are as shown on the temperature cable tension graph in Figure 4. The
f.
tion
differential mechanism, the control column and rudder pedals are still to be in their neutral positions after cable tensions
are
adiusted.
27-21-00
Page
6
Mar 29/96
A19
BONANZA SERIES
MAINTENANCE MANUAL
i. 2. /I
DETAIL A
TAB HINGE PIN TAB HORN CABLE BOLT
DETAIL B O
RIGHT\
./Q\IJ
f--
OII
IO
o
o
o
o RIGHT
DETAIL D
DETAilLC
_
~Yc----fAB HINGE PIN RUDDERVATOR
#TAIL H
DETAIL G O WRONG
O
O
O
O
O
O
O
WRONG
DETAIL E
DETAIL
F C9CID127831JS C
Elevator Trim Tab Installation
Figure
3
27-21-00
Page A19
7
Mar 29/96
BONANZA SERIES
MAINTENANCE MANUAL 50
I ’",~K
io I
ELEVATOR TRAVEL
i
UP TR*VEL
cr,
WWH
o 2
tnYs~
B
oR
19"
Pv?+O,
OVERALL TRAVEL T~UVELCOMBINED ELEVATOR AND RUDDER)
tP’,
c
1"
(L.H.) 44~ (R.H.) 3P
r
20 UP 2~ UP
37. 40~
r
G
2. DOWN 2~ DOWN
o
tE D iLL(~
’’~’’;I
20
30
50
40
60
70
TEMPERATURE
80
90
100
110
-"F
ELEVATOR TAB TRAVEL ELEVATOR DOWN CABLE UP TRAVEL
ELEVATOR TAB NEUTRAL POSmON FROII O" ELEVATOR
DOWN TRAVEL
LEFT TAB
51/2"
+1/20
--10
23~
-t
20
I
ELEVATOR
FAIRLEAD
ELEVATOR UP CABLE
HINGE LINE
RIG~T TAB
DETAIL
OC 0"
Il"
0"
1"
G
TAB CABLE STOPS
STOP PLATE
-C9o~SPRING TAB "UP~’ CABLES AB "DOWN" CABLES
C
FWD
A
STA. 272
B
ELEVATOR DOWN~ ADJUST ACTUATOR SCREW TO 23~ g RIG WITH TAB DOWN
.44
i
.06
2
0
SPRING
O
DETAIL
E
ELEVATOR DOWN SPRING
UP ELEVATOR r~ UP CI\BLE
TAB DOWN CABLE
U r
ELEVATOR DOWN
~a
I
--~III
DOWN ELEVATOR CABLE
ELEVATOR UP~ NOSE DOWN
DETAIL
A
TAB NOSE UP~
DETAIL
B
DETAIL
MECHANISM
C i DETAIL
D
DETAIL
F 35-152-38 001
Elevator
System (V35B) Figure 4
27-21-00
Page
8
Illar 29/96
A19
Qeechc~ft BONANZA SERIES MAINTENANCE MANUAL NOTE
the
With the rudder, elevator and tab cable systems correctly adjusted and in neutral, the differential mechanism is in its neutral position when its tail control (rudder arms) are lightly contacting the aft side of the 35-390087 differential mechanism jig assembly (with -9 stop installed) and the outboard ends (legs) of the jig assembly are lightly contacting the forward side of the fuselage station 256.9 bulkhead. The nut on the differential mechanism elevator (center) control arm is to be positioned inside the hole in the jig assembly. The elevator and rudder system is in neutral when the differential mechanism
jig assembly, the rudder rig tool control column block
are
and the
installed with
the ruddervators in the 0"
position and temperature cable tension graph. Refer to Figure 4. The trim tab system is in neutral when the cable tensions set to the
cockpit indicator is
tensions
at
0", the cable
set to the
temperature graph and the tabs are at symmetrically split to correct for are
cable tension 0"
or
yaw. The tabs
ing edges align
are
at O" when their trail-
with the
trailing edges
of
the ruddervators. Set the ruddervators in the neutral
position (O") by lengths. Make sure the rod ends remain screwed the required length into the push-pull tubes. They should extend past the inspection hole, i.e. a wire should not pass through the inspection hole. g.
adjusting
the control
push-pull
tube
h.
Remove the differential mechanism
and
remove
jig assemblies 4-1/2-inch-long block (4-3/4-inch-long on D-10359 and after) on the control column. Recheck (reset if necessary) the elevator cable tensions. The elevator trim system may be repositioned to minimize the downspring/bob weight effect on the elevator arm and elevator cable tensions. After the downspring effect is minimized, the up-and-down cable tension the
average must fall within the maximum and minimum
llrB DIFFERENTIAL MECHANISM
ELEVATOR REDUCTION BELL CRANK
23.62 f- .08
INCHES
FS 256.9
FS 233.5
SHORT. LOWER ELEVATOR CABLE
35-152-41
Elevator Short Lower Cable
Adjustment
I 27-21 -00
Page A19
9
Mar 29/96
~eechcraft BONANZA SERIES MAINTENANCE MANUAL values
designated by the temperature cable tension graph. Figure 4. Refer to
Check the elevators for correct up-and-down travel limits: 22-1/2 degrees ~O -1 degree up and 19 +2 -1 degrees down. The stops are nonadjustable stops forward of the instrument panel and underneath the control column. Steps b through h should result in the i.
ruddervator travel
being correct or close to correct. Make any final minor adjustments by lengthening or shortening the ruddervator push-pull tubes, but make sure
the rod ends remain screwed the
required length
into the
push-pull tubes. They should extend past the inspection hole, i.e. a wire should not pass through the inspection j.
hole.
Adjust the elevator downspring cable turnbuckle
Check the up and down travel of the elevator tabs. a. The travel should be 5-1/2" +1/2" -1" up and 23" +2" ‘00 down. b.
Check the main and the aft tab cables for proper as shown on the temperature cable tension
tension
graph.
Refer to Figure 4. The same number of terminal threads should be visible on each end of the turnbuckle barrels (a maximum of three threads may be
visible). ELECTRIC ELEVATOR TRIM
For the Model F33A, E33C and V35B electric trim syst,,t see Chapter 27-30-00.
ELEVATOR TAB RIGGING
with the ruddervators 9" up and the tabs 20" down (nose up) to remove all slack from this cable system; then check the force
on
pounds applied
on
NOTE The
the elevator control column.
With the trim tabs set at neutral
k.
tab travel. are
correct, Elevator tabs should be
the rod-end jam nuts, safety the turnbuckles and recheck the travels. Remove the rudder rig tool.
rigged with the bubble protractor perpendicular to the chord plane of the stabiiizer or tab respectively.
travel board
i.
Changing elevator rigging maychange rudder rigging. Check rudder rigging after changing elevator rigging,
a. on
ARNING WULIING
bubble protractor is not
However, with the ruddervator set at neutral, a tab travel board or a bubble protractor may be used to set elevator
tighten
I
a
to set the ruddervator travels.
A travel board must be used for this.
the ruddervators
When the elevator travels and forces
of
use
adequate
(O"), force of 19 ~3 the control column is required to a
through neutral. If necessary, the elevator adjust downspring cable turnbuckle to obtain the value. move
(OPTIONAL)
I
Install
or
4-1/2-inch-long block (or 4-3/4-inch-long after) on the control column and rudder pedal rig tool (Figure 1, 27-20-00) to a
D-10359 and
install the
maintain the ruddervators in neutral. Rotate the elevator tab wheel in the cabin so the indicator dial is set on
Check for correct direction of ruddervator travel by moving the control column. When the control column Is
pushed forward,
zero.
NOTE
the correct rudder-
Both elevator trim tabs should be at neutral (tab trailing edge aligned with ruddervator trailing edge; see the procedure for RIGGING ELEVATOR TRIM TABS TO CORRECT FOR YAW). Trim tab actuator stops on the cables should be moved away from the stops in the fuse-
vator movement is down. When the
control column Is
pulled back,
the
correct ruddervator movement Is up.
When the elevator trim tab control Is moved toward the nose-up position, the trim tab should move DOWN.
When the elevator trim tab control is moved toward the nose-down posltlon, the trim tab should move UP. INSPECTION OF ELEVATOR TABS
NOTE The trim tabs have surface,
an
upper contoured
lage. b.
Rotate the elevator trim tab control wheel to full up on the indicator (tabs down). Check the tab actuator at F.S. 233.5. for a distance of.38 to .50 inch between the face of the actuator and the centerline of nose
the bolt in the clevis end of the actuator shown in
Figure
screw as
6.
27-21-00
Page
10
Mar 29/96
A19
aeechcraft BONANZA SERIES
MAINTENANCE MANUAL Move the tab system to neutral (00) position. readjust cable tension per the temperature
Adjust the length of the actuator screw by disconnecting the bellcrank at the actuator bolt and turning the screw to the dimension shown in Figure 6. Recon-
f.
nect the bellcrank to the tab actuator,
g. Move the tab control wheel toward nose-down a"d establish trim tab up-travel per the chart on Figure
c.
Check and
cable tension
Adjust the four trim tab cables aft of the bellcrank
d.
to obtain 23" +2" -0" tab down
position,
the fixed h.
maximum of 3
preceding procedure has established
of the elevator tab actuator to
Check the clevis bolts which attach the tab cables
stop against the fixed stop in the fuselage. Move the
(O") on the indicator. The trailing edge of the trim tabs should align with the traili"g edge of the ruddervators. tab control wheel to neutral
capabilthrough its correctly oriented the
j.
move
maximum available range and has the tab indicator, the tab actuator and trim tabs to
Reinspect
and
safety
and cable stops affected tab cable stops are to be
one
another.
pounds
CLEVIS
enough to allow free binding the tab cables.
i. Move the trim tab wheel toward nose-up and establish the trim tab down-travel per the chart on Figure 4, and move the trim tab cable adjustable down
to obtain these dimensions.
ity
adjustable upstep against
stop in the fuselage.
movement of the horn without
fully nose down on the indicator (tabs up). The trim tab up-position should be 5-1/2" +1/2" -1" without altering the tab cable adjustment. Loosen the tab cable stop, if necessary, The
4 if necessary.
rosion and dirt and be loose
threads),
Move the tab control wheel to
e.
Figure
to the tab horn. The clevis bolts should be free of cor-
stop if necessary. The same number of terminal threads should be visible on each end of the turn-
(a
in
4. Move the trim tab cable
and establish
the initial trim tab cable tension per the temperature cable tension graph on figure 4. Loosen the tab cable
buckle barrel
graph
of
all turnbuckles, nuts, bolts during this procedure. The
tightened
to 20 +5 -0 inch-
torque and safetied.
END
BELLCRANK
ACTUATOR
BELLCRANK LINKAGE
O
SCREW
ACTUATOR
FACE OF
~BOLT
ACTUATOR CABLE OPENING
ACTUATOR
.50.38
1
BOLT
ACTUATOR
CENTERLINE
\O
TO
ACTUATOR BOLT CENTERLINE TO ACTUATOR FACE DISTANCE 35-152-040
Trim Tab Actuator and Bellcrank
Figure
I
01358)
6 27-21-00
Page A19
11
Mar 29/96
C~3eechcraft BONANZA SERIES MAINTENANCE MANUAL
i After
b. Adjust the left elevator tab down approximately 1 by lengthening the upper left cable and shortening the
rewol"
WARNING
left cable.
rigging
the ruddervator and
c.
Figure
elevator trim tab control system, check for correct movement of the control surfaces with respect to the movement of the controls. When the control column Is moved forward, the ruddervators should move DOWN. When the control column Is moved ah, the ruddervators should move UP. When the elevator trim tab control Is moved toward the nose up position, the trim tab should move DOWN. When the elevator trim tab control Is moved toward the nose down position, the trim tab should move UP. k.
inspection panels
Close all
and test
d.
if
yawing
occurs
in level
flight,
graph specifications
on
4.
Safety
the two turnbuckles, close fly the airplane.
inspection
pan-
els and test
NOTE In the event the above procedure results in overcorrecting, partial readjustment to reduce the rudder effect can be accomplished on one tab only. The maximum allowable amount of split between trim tabs is 6". The average degree of tab travel at fully up or down cannot exceed the limit of travel.
fly the air-
plane. i.
Set cable tension to the
with the ailerons in
ELEVATOR TAB INDICATOR CABLE REPLACEMENT
(Flgure 7)
neutral, adjust the tabs per the instructions under RIG-
a.
GING ELEVATOR TRIM TABS TO CORRECT FOR
neutral
YAW.
tion 185 should be
RIGGING ELEVATOR TRIM TABS TO CORRECT
To install the dial indicator cable, thread the cable through the hole in the head of the cotter pin and out
FOR YAW The elevator tabs
be
rigged to function as a rudder tab by making minor adjustments up and down from neutral position. can
FOR RIGHT YAW
(NOSE OF
LEVEL)
Adjust the right elevator tab down approximately by lengthening the upper right trim tab cable and shortening the lower right trim tab cable. a.
1"
left elevator tab up approximately 1" by shortening the upper left trim tab cable and lengthening the lower left cable. b.
c.
Adjust the
Set cable tensions to the
Figure d.
graph specifications
on
4.
Safety
the two turnbuckles, close fly the airplane.
inspection
pan-
els and test
FOR LEFT YAW
(NOSE
OF AIRPLANE TENDS TO
MOVE LEFT WITH WINGS
LEVEL)
Adjust the right elevator tab up approximately 1" by lengthening the lower right tab cable and shortening the upper right tab cable.
a.
approximately
even.
b.
through the holes c.
in the indicator drum.
With the dial at 0
both ends of the cable
degrees, slip are
of
the cable
so
that
equal length.
Wrap the cable around the drum one full turn in each direction. The end that wraps to the right will be wrapped clockwise around the drum, and the end that d.
AIRPLANE TENDS
TO MOVE TO RIGHT WITH WINGS
Place the proper tension on the trim cables in position. Both turnbuckles aft of Fuselage Sta-
wraps to the left will be wrapped counterclockwise, viewed from the left side. e.
Route the cable
over
the
appropriate
idler
as
pulley
down to the shaft of the tab control wheel. With the dial still in 0 degrees position, take the cable coming off the top of the elevator tab dial sheave and bring it down to the forward side of the tab wheel shaft to the left of the small hole. f.
g. Wrap the cable (counterclockwise) around the shaft toward the hole three turns. Insert the cable through the hole. Wrap the surplus cable around the shaft. h.
With the dial set at 0
take the cable
com-
ing
off the bottom of the trim tab dial sheave and
bring
degrees,
it down to the aft side of the tab wheel shaft, to the
27-21-00
Page
12
Mar 29196
A19
aeechc~rt BONANZA SERIES MAINTENANCE MANUAL
COTTER PIN WRAP ONE FULL TURN IN BOTH DIRECTIONS
I I
lili~
INDICATOR
(SHEAVE)
R~ATEDV 90"
DETAIL
A
O
ANDIDLER
PULLEY
TIE
SOLDERI
A
I
INDICATOR DRUM (SHEAVE)
r-
1
IIN/
na
r-
WRAP 3 FULL TURNS-/
DETAIL
TRIM TAB CONTROL WHEEL SHAFT ROTATED 90´
TRIM CONTROL WHEEL
B
.36-152-39
Elevator Trim Tab Indicator Cable
Figure
Replacement
7
27-21-00
Page A19
13
Mar 29/96
BONANZA SERIES
MAINTENANCE MANUAL
right of the hole in the shaft, and wrap the cable (clockwise as viewed from the left end of the shaft)
b. Remove the access panel on the left side fuselage, just forward of the ruddervator.
three turns toward the hole in the shaft.
Install identification tags to the cables and disconare routed aft to the elevator trim tabs.
i.
Insert the cable
through
c.
the hole in the shaft and
wrap it around the shaft.
j. Twist the cables together and only rosin core solder. Check the tab dial to stop to the other. k.
see
solder them. Use
nect the cables which
d.
Install identification tags to the cables
one
Set the tab dial at 0 degrees. Place tension on the tab cables in the tail section to hold the tabs in line with rudden/ators. i.
ward
pulleys. Secure the cables to the
actuator screw
position
Safety the turnbuckles and set the stops fuselage cables to maintain proper travel in dance with the travel table in Figure 4. m.
Do not cables. e. so
on
the
accor-
Identify the
cables
the bracket and
move
remove
the actuator to
airplane.
(V35B)
above
Position the actuator assembly in the bracket and attaching bolts.
install the three or
below the
the cable to the elevator tab horn
should swivel in the horn at all times, if the bolt binds, it will cause cracks to develop in the tab horn. The bolt
just tight enough to prevent rattle, but tight enough to cause binding in the horn. should be
TRIM TAB ACTUATOR REMOVAL
b.
Rotate the actuator drum upward until the pin c. securing the cable to the drum is no longer visible through the actuator cable opening.
NOTE
not
flight compartfully nose-up posi-
of the actuator
drum travel.
If the bellcrank-to-actuator
screw
linkage
is disconnected, install the actuator bolt, washers, nut and cotter pin to attach the
(V35B)
the trim control to the on the elevator trim tab indicator,
Using the cable at the forward side
drum, be certain the cable is at the end of its actuator
bellcrank to the actuator.
the trim tab control in the
noted
securing
the actuator and attached
UP.
recommended limits, will cause excessive wear on the tab hinges. if excessive wear is noted on the ruddervator half of the hinge, it should be replaced,
move
being removed replacement actuator are
the actuator
TRIM TAB ACTUATOR INSTALLATION
a.
as
put bends in the
It may be necessary to remove the two tab cable pulleys located directly below the actuator, in order to provide cleatance for the cable ends on the actuator cables through the pulley bracket.
INSPECTION OF TAB HINGES
ment,
or
NOTE
After rigging the elevator and elevator trim tab control system, check for correct movement of the control surfaces with respect to the movement of the controls. When the elevator trim tab control wheel Is moved toward the NOSE DOWN position, the
tion
actuator so the
be maintained.
correctly.
WARNING
Using
on
Remove the three bolts
I w~´•´•I
a.
kink
that the cables on the
’eco""ected f.
damage,
bellcrank from the
securing
can
CAUTION
With the ruddervators set in the neutral position, the left elevator tab should be set at 2" ~1" above neutral ruddervator position. The right elevator tab should be set at O" ~1" ruddervator position.
The bolt
each
cables routed forward to the flight compartment. Secure the cables so they do not come off of the for-
NOTE
improper cable tensions, either
on
side of the first turnbuckle and disconnect the actuator
that it will roll from
elevator trim tab should
of the
d.
With the actuator bolt
actuator screw
connecting
the bellcrank to
linkage installed, position the trim tab
27-21-00
Page
14
Mar 29/96
A~9
aeechcraft BONANZA SERIES MAINTENANCE MANUAL actuator screw by rotating the actuator drum to obtain the actuator bolt-centerline-to-actuator-face distance
h.
of.38 to .50
in
e.
as
shown in
Figure
6.
degrees
as
Connect the actuator cables to the cables routed
aft from the
Do not
kink
or
are
hooked up
correctly. Operate system through the full travel to ensure complete and proper degrees of travel of the the elevator
trim tabs. Check for proper direction of travel. For a nose-up condition on the airplane, the trim tab should move down. For a full nose-down condition, the trim tab should move up.
put bends in the
cables. 9´• Connect the bellcrank cables routed aft to the elevator trim tabs,
4.
Be certain that all cables
CAUTION
damage,
Figure
CAUTION
at this time.
t
noted in
r~7
flight compartment.
f. If the two tab cable pulleys, located directly below the actuators, were removed to provide clearance for the ends of the actuator cable, install the two pulleys
I
The elevator trim tab indicator on the pilot’s instrupanel should indicate the fully nose-up position
ment
i.
Install the
lage, just
access
panel
on
the left side of the fuse-
forward of the ruddervator.
27-21-00
Page A19
15
Mar 29/96
BONANZA SERIES MAINTENANCE MANUAL ELEVATOR AND TAB MAINTENANCE PRACTICES (F33A, F33C, A36, A36TC AND B36TC)
WARNING
airplane
d.
Connect the
for the elevator.
e.
Connect the tail
access
doors.
downstop bolt so the aft side of the belltouches a straightedge held vertically just the back of the bulkhead (or is .62 ´•1 .05 inch against forward of the straightedge on F33A).
~t
the elevator
c.
actuator will be coded with
d.
on
push-pull rod
Adjust
the elevator upstep bolt for (25" ~tl" on F33A).
Disconnect the elevator
Detach the tail cone, disconnect the tail light and remove the tail cone,
b.
Remove the tail section access doors hand side of the aft fuselage,
push-pull
navigation
on
2´•00
the left-
f´•
tension
as
tubes from the
With the elevators
B36TC
bolts.
i.
cable and
remove
Connect the elevator bonding cable and position on the stabilizer, install the hinge bolts
b.
and
adjust a
the
cable
1.
downsprings.
fully rigged
on
A36, A36TC,
Employing
a
hand-held force gage
on
the control
as
follows:
A36, A36TC and B36TC: 23 maximum
pounds
of breakout force at
20" DOWN elevator.
b)
25to26
poundsofforcethrough NEUTRAL
23 to 24
pounds
elevator.
safety,
Connect the rod to the trim tab actuator elevator.
only,
a)
the elevator
tighten
Figure
wheel, adjust the elevator downsprings 1.
ELEVATOR INSTALLATION
and nuts then
by
the control column should have a 1/16- to 1/8-inch cushion when in the full forward position.
elevator trim tab.
a.
the control column so
indicated in Sheet 2 of
h´•
Disconnect the actuator rod at the actuator for the
bonding
25"
deflection of
With the column fastened at neutral
d.
Disconnect the elevator the elevator.
a
turnbuckles to obtain neutral elevators with
Connect the elevator
f.
or
support.
g.
hinge
A36,
the gust lock hole is 0.03 inches aft of the hole in the control column
torque tube fittings of the elevator.
Remove the
downward
a
on
downspring.
Rig neutral elevators on positioning the control column e.
a.
for
F33A, 20" ~tl"
i" on B36TC.
23"~ 1" up
red.
Disconnect the elevator
Adjust
deflection of 15" ~1"
ELEVATOR REMOVAL
e.
EA-320)
crank
uator will be coded with a blue color,
c.
wires and install the tail
Set the
a.
actuators may have colored stripes or may be of a solid color. The left act-
or
Install the
TO EA-389 U(CEPT
preceding airplane serials and airplanes In compliance with
right
torque tube fit-
CJ-149 AND ATTER, PRIOR TO E-21 I I EXCEPT E-1946 AND E-2104, AND PRIOR
b.
The
at the
RIGGING THE ELEVATOR CONTROL SYSTEM (CE-748, CE-772 AND AFTER,
Service Bulletin No. 2399, the elevator tab actuators are color-coded. The
black
push-pull tubes
light
point for the
inch-pounds.
serials 08-1566 and after;
different color. On the
nut at the inboard
to 50-70
cone.
8-1948, 8-2104, E-2111 and after; EA-320, EA-389 and after, observe the color coding on allpark when replacing or installing control cables, bellcranks, and/or other control system components. DO NOT connect parts of one color to coded parts of a
earlier
attaching
torque
ting
f.
On
Install the
c.
elevator and
on
the
c)
of force
as
23" UP elevator
is reached.
27-30-00
A18
Page 1 Aug 18/95
e~edtcraft BONANZA SERIES MAINTENANCE MANUAL CABLE
CABLES
ELEVATOR
22
5
SURFACE
TENSION
LBS.
TOP
CABLE
(DOWN ELEVATOR) AT
23
25"~
UP
F33A
I
15’~
1’
DOWN
F33C
I
I
59"F 5 LBS.
MODEL
TRAVEL
1"
I
NOTE
I
I
ON SERIALS CE-881 AND AFTER. CJ-156 AND AFTER. E-1588 THRU E-2111 EXCEPT E-1946 AND E-2104. EA-I THRU EA-388 EXCEPT EA320. THE IN-LINE FORCE REOUIRED TO MOVE THE TRIM TAB SYSTEM CABLES SHALL NOT EXCEED 20 POUNDS. WITH OR WITHOUT ELECTRIC TRIM.
ELEVATOR DOWN STOP
LOWER CABLE
(UP ELEVATORI 24
5
TOP
LBS.
CABLE
(DOWN ELEVATOR) AT
26
(UP 25
15
1"
UP
A36
20"~
1’
DOWN
A36TC
(I II
nayi
I
I
ON MODELS F33A. F33C. A36. A36TC AND B36TC WHERE THE TAB CABLES DIVIDE INTO TWO CABLES EACH. THE TWO CABLES SHALL BE ADJUSTED FOR EOUAL TENSION WITHIN TWO POUNDS OF TOTAL VARIATION.
59"F 5 LBS.
LOWER CABLE
ELEVATOR) 5
TOP
LBS.
CABLE
(DOWN ELEVATOR) AT
I
23"~
23’~
1"
UP
25"+
1’
DOWN
C,
B36TC
o\ O O
59’F
LOWER CABLE
5 LBS.
(UP ELEVATOR) ELEVATOR TABS
15 AT
LBS.
5
LBS.
10"+
1"
UP
O
LBS.
27’~
1"
DOWN
I
I 1
F33A A36
II II 1111
A36TC
59"F
ELEVATOR
ELEVATOR DOWN
II IY /II II
ELEVATOR
UPSTOP
DOWN
D(!
B36TC
AT
59"F
10’+
1’
UP
21"+
1’
DOWN
ELEVATOR
UY
V
DETAIL
E
ELEVATOR UP
UP
D
O
8
000
8
O
C C DETAI~LA
I´•,
B
~´•s
a
ELEVATOR
UP
ELEVATOR DOWN TAB
ElevatorSy~tem (CE-748, CE-M and an.r; W-149and 8Rer; prior to E-2111, except E-1946 and E-2104; prior to EA-389, except EA-320) (Sheet 1 of 2) Figure 1
NOSE DOWN
TAB
NOSE
UP
DETAIL
B
DETAIL
C
DETAIL
E
C9~E*2783DIO
27-30-00
Page 2 Aug 18l95
A18
aeechcraft BONANZA SERIES MAINTENANCE MANUAL TEMPERATURE CABLE TENSION GRAPH ALL ELEVATOR TAB CABLES
8~
z
41
0
10
20
40
30
50
70
60
TEMPERATUAE-
80
90
100
110
120
110
120
OF
50
40
AND~
"i
ToPELEV_AToR
F
0
10
20
30
40
50
MuFn
60
70
TEMPERATURE-
80
90
100
"F
Ti-a3b AND,
z
a
M~UM 16 i
´•i
i1 0
10
20
30
40
50
60
70
BO
90
100
110
120
TEMPERATURE- "F
Elevator
System (CE-748, CE-n2 and after; CJ-149 and after; prior to E-2111, except E-1948 and E-2104; prior to EA-389, except EA-320) (Sheet 2 of 2) Figure 1 27-30-00
A18
Page 3 Aug 18/95
Beeehcr~t BONANZA SERIES MAINTENANCE MANUAL
ELEVATOR
ELEV.
UP
ELEV.
DOWN
ELEV.
UP
ELEV. NOSE
NEUTRAL RIG PLN
TOOL
FABRICATE FROM 5/16-INCH-DIAMETER STEEL ROD
DOWN DOWN
1.35"
r
NOSE UP \‘NOSE
NOSE
DETAIL
DOWN
UP
C aJa
a.sa;03 rNLH68 B36TC 3.45 r.03 INCHES
L
ELEVATOR DOWN
TAB
DETAIL
CABLE STOPS
~c.95..
OETAILB
A F.S.
ELEVATOR
179
UP
CABLE
TOP
5 LBS.
24
(OOWN ELEVATOR) AT
E
5
(UP
I
LBS.
LOWER
5
AT
59’F
26
r
[UP
LBS.
A
AT
DOWN
I’
UP
I’
DOWN
TDP
CABLE
23’
5
LBS.
r
25"
5 O
LBS. LBS.
25’
I’
DOWN RH
27"
I"
DOWN LH
A36 B36TC
59"F c
8"
UP
836TC
LOWER CABLE
10"
ELEV.
UP
ELEVATOR) LBS
15
ELEVATOR TABS
i’
CABLE
(DOWNELEVATOR)
ELEVATOR BELLCRANK STOPS
I"-0
20"
ELEVATOR)
24
B
25´
MODEL
A36
59"F
26
C
TRAVEL
SURFACE
TENSION
CABLE
CABLES ELEVATOR
I"
UP RH
I"
UP
LH
E-2104. E-2111 AND AFTER: EA-320. EA-389 AND AFTER. THE REOUIRED TO MOVE THE TRIM TAB SYSTEM CABLES SHALL NOT
ON SERIALS E-1946.
ELEV. NOSE
DOWN
DOWN\\
NOSE
L=i
c
ELEV.
IN-LINE DOWN
EXCEED ON
UP
FORCE 16
MODELS
THE POUNDS.
EACH.
C~3
ELEV.
E D
AND
OR
B36TC
TWO CABLES SHALL
TENSIONMETER
BLES WITH
DETAIL
A36.
WITH
WITHOUT ELECTRIC WHERE BE
TAB CABLES
DIVIDE
ADJUSTED FOR EOUAL
THE
READINGS SHALL BE
ELEVATOR
IN
THE
TAKEN
ON
TWO CABLES
INTO
TENSION WITHIN 2
THE
NEUTRAL POSITION.
THE DOWN-SPRINGS DISCONNECTED. F.S.
THE
TRIM.
.5
UP *THE
DETAIL
POUNDS.
TOP
AND
AGAINST
BOTTOM
THE
STOPS
CAAND
C9aEn2783nM9
233.50
Elevator System (8-1948, E-2104, E-2111 and after; EA-320, EA-389 and after)
(Sheet 1 of 2) Figure 1A 27-3090
Page
4
Aug 18/95
A18
aeechct~ft BONANZA SERIES MAINTENANCE MANUAL
TEUPERATURE CABLE TENSION GRAPH ALL ELEVATOR TAB CABLES
tffRRtFmfft-KHitF;tffttmtt+ttr-:: TAe
3~ 210
0
l0
20
30
40
50
60
TEMPERATURE
70
80
90
100
liO
120
"F
40
530
B
a 420
0
to.
20
30
40
50
60
70
8b
9~
100
liO
liO
110
120
TEMPERAfURE- "F
f .A3~
z
O
0 0
l0
20
30
40
50
60
70
80
50
100
TEMPERATURE- OF
Elevator
System (E-1946, E-2104,
E-2111 and after;
EA-320, EA-389 and after)
(Sheet 2 of 2) Figure 1 27-30-00 A18
Page 5 Aug 18/95
aeechc~ft BONANZA SERIES MAINTENANCE MANUAL F33A and F33C:
2.
a)
17 to 13
pounds of force
through
15 to 16
of force as 25"
pounds
fully
UP
elevator is reached.
reading at NEUTRAL elevator and 23" (A36, A36TC, and B36TC) or 25" (F33A, F33C) UP elevator (.06 inch off fully upstep) must be taken while The gage
1´•
Removethe
h.
Connect the elevator
NEUTRAL
elevator.
b)
g.
the control wheel is in motion.
Adjust each spring by transferring the upper end spring-attaching hole providing increased or decreased tension, as applicable. The elevator sysk.
to a
rigtool.
downsprings.
i. With the elevators fully rigged (including autopilot and electric trim if installed), the force required to pull the control wheelaft through neutral must be 25 to 29
POU"dS. The force required to return the wheel through neutral shall be 20 to 24 pounds. The difference (friction of the system) between the two readings shall never exceed 9 pounds (7 pounds is desired) nor be less than 4 pounds. j´•
Maintain
a
minimum clearance of.06 inch between
tem should have sufficient freedom to allow free return
adapter and the inner control column guide assembly (both the pilot’s and copilot’s) at fully
of the elevator from
down elevator
fully UP
to
fully
DOWN.
the control wheel
on
the A36 and B36TC.
NOTE
NOTE After
After rigging the elevator and elevator trim tab control system, check for correct movement of the control surfaces with respect to the movement of the controls.
NOSE DOWN position, the trim tab should move UP.
AFTER, EA-320, E1-389 AND AFTER) Set the
downstop
bolt
so
hole in the bellcrank is .38 inch
straightedge
held
against
that the center of the .05 inch forward of
a
the back of the bulkhead at
F.S. 257.606. b. Adjust the elevator push-pull rod for an elevator deflection of 20" ~1" down ton B36TC 25" ~1"),
Adjust
c.
the elevator upstep bolt for
25" +1" -O" on A36 and 23" ~1" up
Disconnectthe
d.
on
a
deflection of
B36TC.
elevatordownsprings.
Rig neutral elevators on the control column by positioning the pilot’s control column so the gust lock hole is 2.50 ~.03 ton B36TO 3.45 ~.03) inches aft of the hole in the control column support and install rig tool (Sheet 1 of Figure 1A). e.
NOTE The short end of the tool is inserted into the control column support and the long end is inserted into the control column. The weight of the control column will hold the tool in place. f.
the turnbuckles to obtain neutral elevators cable tension as indicated in Sheet 2 of Figure
Adjust
with
a
1A.
the elevator and trim tab
correct movement of the control surfaces with respect to the movement of the controls. When the trim tab control wheel is moved toward the
RIGGING THE ELEVATOR CONTROL SYSTEM (8-1946 E-2104, E-2fll AND
a.
rigging
system, check for
ELEVATOR TAB INDICATOR CABLE REPLACEMENT (CE-748, CE-772 AND CJ-149 AND AFTER, PRIOR TO E-2111 EXCEPT E-1946, AND E-2104, PRIOR TO EA-389 EXCEPT EA-320) a.
Place the proper tension
"eut’al b.
on
the trim cables in
position.
To install the dial indicator cable, thread the cable
through the hole in the head of the cotter pin and through the holes in the indicator drum. c.
With the dial at 0
both ends of the cable
degrees, slip the cable are equal length.
so
out
that
d. Wrap the cable around the drum one full turn in each direction. The end that wraps to the right will be wrapped clockwise around the drum, and the end that
wraps to the left will be wrapped counterclockwise, viewed from the left side. e.
Route the cable
over
the
appropriate
idler
as
pulley
down to the shaft of the tab control wheel.
With the dial still in O degrees position, take the cable coming off the top of the elevator tab dial sheave and bring it down to the forward side of the tab
f.
wheel shaft to the left of the small hole.
27-30-00
Page 6 Aug 18/95
A18
cjaeechcraft BONANZA SERIES MAINTENANCE MANUAL g. Wrap the cable (counterclockwise) around the shaft toward the hole three turns. insert the cable
through the hole. Wrap the surplus cable around
the
shaft. h.
Remove the
c.
upholstery panel
baggage
area.
d.
identifying
After
and
tagging
from the back of the
the cables for rein-
stallation, disconnect the forward trim tab cables at the takethecablecom-
WiththedialsetatOdegrees,
ing off the bottom
of the trim tab dial sheave and
bring
turnbuckles in the aft
it down to the aft side of the tab wheel shaft to the
Tie nylon e. small knot.
right of the hole in the shaft, and wrap the cable (clockwise as viewed from the left end of the shaft)
f.
strings
fuselage. to each of the cable ends. Use a
three turns toward the hole in the shaft.
Remove the access panel (actuator door) which is located under the pulleys below the pedestal.
i.
g.
Remov~ the
h.
Remove the
Insert the cable
through
the hole in the shaft and
wrap it around the shaft.
j.
Twist the cables
only k.
rosin
core
together and
solder them. Use
engine
pedestal.
autopilot panel (if installed) propeller controls.
below the
solder.
on
NOTE
Check the tab dial to to the other.
see
that it will roll from
Station a man in the aft fuselage to keep small amount of tension on the strings as they are pulled through the fuselage.
one
stop i.
and
the left side of the
panel
Set the tab dial at O
degrees.
a
Place tension
on
the
tab cables in the tail section to hold the tabs in line
i.
with the elevators.
the neutral
j.
NOTE
Place the elevator tab control in neutral and mark
position
on
the
sprocket
and chain.
Count the number of chain links
on
each side of
the mark and note the number for later reference. With the elevators set in the neutral position, the left elevator tab should be set at 2" rt~lo above neutral elevator position. The
right elevator tab should position.
k.
Pull the cables and
strings
from the
fuselage
out
through the pedestal.
be set
NOTE
at O" ~1" elevator
Safety the turnbuckles and set the stops fuselage cables to maintain proper travel in m.
on
Note which color (blue and black) goes the top, forward side of the
the
over
accor-
dance with the travel table.
sprocket. i.
Tie the
new
cable to the
NOTE
strings.
NOTE
After rigging the elevator and elevator trim tab control system, check for correct movement of the control surfaces with respect to the movement of the controls. When the elevator trim tab control wheel is moved toward the NOSE DOWN posi-
tion, the elevator trim tab should
(color coded blue) cable the tap forward side of the
The shorter
goes
over
sprocket. Pull the
m.
strings and cables back through
move
NOTE
UP.
Make sure that the trim tab cables do not interfere with the engine and propeller controls located adjacent to them.
ELEVATOR TRIM TAB FORWARD CABLE
REPLACEMENT(E-1946, E-210L~,
the fuse-
lage.
E-2111
AND A~TtR, EA-320, EA-339 AND
AFTER)
n.
Check the
pulleys below the pedestal are properly installed.
to deter-
mine that the cables Remove the fifth and sixth seats (if installed) as a. shown in FIFTH AND SIXTH SEAT REMOVAL in
Chapter b.
screws
and remove the floor,
Make certain that the correct number of chain
links
25-00-00.
Remove the
O´•
from the
baggage
area
floor
are on
each side of the mark
on
p.
Co""ect the turnbuckles in the aft
q.
Tensionthecables
the
sprocket.
fuselage.
perSheeteof Figure
1A.
27-30-00 A18
Page 6A Aug 18/95
aeechcraft BONANZA SERIES MAINTENANCE MANUAL Check for proper elevator tab travel.
r.
Set the tab travel
s.
indicated in Sheet 1 of
as
Figure
Installtheaft
upholsterypanel. floor
u.
Install the
v.
Install the back seats. See FIFTH AND SIXTH
baggage
Install the
w.
access
panel.
Chapter
SEAT INSTALLATION in
Sheet 1 of
25-00-00.
panel (actuator door)
panel(s)
on
the
The
4.
below the
d.
1A.
cockpit
indicator is to read 9" f2Q Up and
2rb,
pedestal.
as
with the serials listed in the
planes e.
the stops on the cables to allow surface shown in Sheet 1 of Figure 1 except on air-
Adjust
travel
Install the access
Figure
26" ~t20 down.
pedestal. x.
Torque
as
respect to the movement of the controls. When the elevator tab control is moved toward the "NOSE DOWN" position, the tab should move up.
cables,
ELEVATOR TRIM TAB ACTUATOR
tab control system, check for correct movement of the control surfaces
ELEVATOR TRIFI TAB ACTUATOR
with respect to the movement of the controls. When the elevator tab con-
DISASSEMBLY
the tab should
move
RIGGING THE ELEVATOR TRIM TAB
a.
Place the elevator tab indicator in the neutral
posi-
tion. b.
the cables to the tension shown
temperature cable tension ure 1 or 1A, as applicable.
tor
c.
ing b.
Rig
graph
pushrod
to
bring
on
the eleva-
in Sheet 2 of
Remove the snap ring (6) from the actuator houspull the nut assembly (1 0) out of the housing.
and
Remove the actuator
screw
(9)
from the nut
assembly.
FigCAUTION i ,,,,-r
Place the elevator in neutral
the trim tab
A36TC AND A36,
INSTALLED) (Flgure 2)
up.
a.
(F33A, B36TC,
EXCEPT E-llll, F33C PRIOR TO CJ-156 EXCEPT THOSE AIRPLANES WITH KIT 33-4002-1
trol Is moved toward the "NOSE
position,
inch-pounds.
After rigging the elevator and elevator tab control system, check for correct movement of the control surfaces with
After rigging the elevator and elevator
DOWIV"
note.
NOTE
Make certain that insulation, tie wraps, etc. do not Interfere with con-
components such chains, etc.
preceding
the stop bolts to 40 to 60
WARNING
trol
positions.
3. Set the cable stops to provide 8" ~1" up on LH tab and 10" ~1" up on RH tab, and 27" ~1" down on LH tab and 25" ~1" down on RH tab as indicated in
1A. t.
The normal total difference between the tab
2.
surfaces is to be 2"+ .5" for all
position
and
adjust
the tab into the neutral
Do not damage the rod end when
position.
drilling
out rivets.
NOTE c.
To improve elevator centering, the LH and RH trim tabs ate rigged to a different setting in the neutral position on serials E-1946, E-2104, E-2111 and after, EA-320 and EA-389 and after. Rig these
airplanes per steps 1.
Rig
1
through
and RH up 1"
.5" with indicator at O",
(2), washer (3) and shoulder pin (5) (1). Remove actuator rod end (4) The bearing (7) and the bushing (8)
from the
screw.
can now
be removed from the
d.
4.
neutral tab surfaces with LH down 1"
Remove nut
then drill out rivet
Remove check nut
adjusting bushing (14) ~t
.5"
(15)
screw.
and
with
screw out
the end
appropriate spanner
wrench. e.
RemovetheO-ring (13).
27-30-00
Page 66 Aug 18/95
A18
aeechcraft BONANZA SERIES MAINTENANCE IVIANUAL f.
Remove the
bearing (12)
from the
housing (11).
ELEVATOR TRIM TAB ACTUATOR ASSEMBLY
(F33A, B367C, A367C
deterioration. Lubricate all parts with MIL-G-23827 grease (11, Chart 1, 91-00-00) prior to assembly.
AND A36, U
F33C PRIOR TO CJ-156, U
(Flgure 2) (16, Chart 1, 91-0000) and inspect for cracks, corrosion, and distortion. Replace bushings and any parts showing evidence of
Clean all parts in PD680 solvent
27-30-00 A18
Page 6C Aug 18/95
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
1
14
15
12
13
o
11
9
s 9.
a
ActuatorScrew
i.
Rivet
2.
Nut
10.
3.
Washer
11.
4.
Actuator Rod End
12.
5.
ShoulderPin
13´•
a.
14.
7.
Snap Ring Bearing
NutAssembly Housing Bearing O-Ring Adjusting Bushing
15.
CheckNut
8.
Bushing
33-164-3
Elevator Tab Actuator Figure 2 Install
a.
bearing (12)
into
clockwise
housing (11).
when
screwed
into
the
nut
assembly (10). b.
Install
O-ring (13)
into
adjusting bushing
(14).
Install nut
g. secure
Install
c.
~15). (Do
not
d.
ring (6) e.
adjusting bushing (14) and check tighten.) bushing (8), bearing (7)
Install on
actuator screw
Install
(9) and ~5), washer (3) screw
end
rod
with rivet
and nut
(1)
(4)
on
actuator
(2). NOTE
all
parts
into
housing (11);
pin
h. Screw adjusting bushing (14) into housing (11) until the end play has been removed from the nut assembly, and tighten the check nut(l5). An end play of 0.003 inch is permissible.
ELEVATOR
TRIM
TAB
ACTUATOR
DISASSEMBLY
(E-llll ONLY) (Figure 3) Remove
a.
except O-ring with (11, Chart 1, 91-00-00) prior to assembly. Lubricate the O-ring with MIL-S-8660 (50, Chart 1, 91-00-00). Lubricate
snap
and shoulder
assembly (10) ring (6).
nut
(9).
actuator
secure
and
with snap
the
housing (5) and pull housing.
ring (2) from the assembly (6) out of the
retainer
the nut
MIL-G-23827 grease
f.
Install
screw
(9) into
nut
(10).
WARNING
b.
Remove the actuator
screw
(4) from
the nut
assembly (6). c.
Drill out rivet (12).
d.
Remove nut
pin (9). The collar ~3)
(10), washer~ll) and shoulder can now
be removed.
The trim tab actuator that will be installed on
the left hand horizonal stabilizer shall
its actuator screw ~9) that will rotate clockwise when screwed into the nut assembly (10). The trim tab actuahave threads
on
tor that will be installed on the
right hand
horizontal stabilizer shall have threads
the actuator
screw
(9)
on
that rotate counter-
Remove check nut (8) and
e.
ing (7)
with the
appropriate
screw
out bush-
spanner wrench.
Clean all parts with solvent (16, Chart 1, 91-00-00) and replace parts that are cracked, corroded and distorted.
Chart 1,
Lubricate all
parts with lubricating grease(ll,
91-00-00) prior
to
assembly. 27-30-00
Page A14
7
Jun 20/91
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL 1.
Actuator Rod End
7.
Bushing
2.
Retainer
8.
Check Nut
9.
Ring
3.
Collar
4.
Actuator Screw
10.
Shoulder Pin Nut
5.
Housing Nut Assembly
11.
Washer
12.
Rivet
6.
;st~
i
38133-8
Elevator Tab Actuator Figure 3
(E-llll Only)
Install
g.
ELEVATOR TRIM TAB ACTUATOR ASSEMBLY
bushing (7)
(E-llll only) (Figure 3) (3)
and retainer
ring (2)
on
b.
(1)
Install actuator rod end
align
on
actuator
screw
(4) 1
the holes.
pin (9) washer (11) and (12), P/N MS20613-3C10.
c.
Install shoulder
d.
Install rivet
nut
(10).
assembling the actuator, screw the bushing (7) into the assembly (5) until end play of the nut assembly (6) has been removed, then lock in place by tightening the check nut (8). The nut assembly (6) must be free to rotate and provide smooth operation through its full travel with a maximum end play of 0.0015 inch.
NOTE
lubricating grease (11, 91-00-00) prior assembly.
Lubricate all parts with Chart 1,
to
Install actuator
e.
screw
(4)
into nut
assembly (6).
ELEVATOR TRIM TAB ACTUATOR DISASSEMBLV Model F33C (CJ-158 and after, and earlier airplanes incorporating Kit 33-4002-1)
(Figure3A)
WARNING
a.
housing The trim tab actuator that will be installed
on
its actuator
screw
(4)
b.
the
left hand horizontal stabilizer shall have threads on
Remove the snap ring pull the nut assembly
and
Remove the actuator
assembly.
assembly (6). The trim on the right hand
CAUTION
tab actuator that will be installed
horizontal stabilizer shall have threads tuator
screw
(4)
assembly (6) ring (2).
Install nut
on
the
ac-
Do not
that rotate counterclockwise
when screwed into the nut
with retainer
(4) from the actuator (7) out of the housing. screw (6) from the nut
that will rotate clockwise
when screwed into the nut
f.
(8).
threaded
careful to
being
withi check nut
When
actuator
(4).
screw
secure
NOTE
Place collar
a.
and
damage
rod end when
drilling
out rivet.
assembly (6).
into
housing (5) and
c.
secure
The
Remove nut
bushing (5)
(1), washer (2)
can now
and shoulder
be removed from the
pin (3).
screw.
27-30-00
Page8 May 31/85
A10
BEECHCRAFT BONANtA SERIES MAINTENANCE MANUAL
112
It
bl
6
1
s
4
10
I. Nut
Assembly Housing Bearing 10. O-Ring it. Adjusting Bushing 7. Nut
2. Washer
8. 9.
3. Shoulder Pin 4.
5.
Snap Ring Bushing
12. Check Nut
6. Actuator Screw
F33C-164-6
Elevator Tab Actuator
Figure
3A
(12) and screw out the end adjusting bushing (11) appropriate spanner wrench. Remove O-ring (10). e. f. Remove the bearing (9) from housing (8).
Install adjusting bushing (11) and check nut (12). tighten.) d. Install bearing (5) and snap ring (4) on actuator screw (6). Install shoulder pin (3), washer (2) and nut (1) on e.
Clean all parts in PD680 solvent (16, Chart i, 91-00-00) and inspect for cracks, corrosion, and distortion. Replace bushings and any parts showing evidence of deterioration. Lubricate all parts with MlL-G-23827 grease (11, Chart 1, 91-00-00) prior to assembly.
actuator screw (6).
d.
Remove check nut
with
ELEVATOR TRIM TAB ACTUATOR ASSEMBLY Model F33C (CJ´•ISB and after, and earlier Kit
airplanes
33-4002-1)
Install
Install
Install
f.
screw
(6)
into nut
bearing (9) O-ring (10)
into
into
housing (8). adjusting bushing (11).
(7).
WARNING The trim tab actuator that will be installed on the left hand horizontal stabilizer shall have threads its actuator
screw
(6)
that will rotate clockwise
when screwed into the nut
Clean all parts in PD680 solvent (16, Chart 1, 91-00-00) and inspect for cracks, corrosion, and distortion. Replace bushings and any parts showing evidence of deterioration, Lubricate all parts with MIL-G-23827 grease (11, Chart 1, 91-00-00) prior to assembly. a.
not
on
(Rgure 3A).
b.
c.
(Do
assembly (7). The trim right hand
tab actuator that will be installed on the horizontal stabilizer shall have threads tuator screw
(6)
when screwed into the nut
Install nut g. with snap ring (4).
on
the
ac-
that rotate counterclockwise
assembly (7).
assembly (7) into housing (8),
secure
27-30-00
A10
PageS May 31/85
BEECHCRAFT BONANZA SERIES MAlNTENANCE MANUAL
9
12
io
678
13
5
1I
.8 IN
’+C.5
IN
~-c---------.25
Tnp 5/8-11
1
1.25 IN!
0_ _
k
IN
_
__
_
_
_
-TYP~C
I
2.9 IN
i~H
i
TAB
’/Ciso
14
t~
1.30 IN
ITEM
QUANT.
DESCRIPTION
NO. 1
6 aluminum
equiv.
1
2
3/4
2
2
1
3
1
1/2
4
1
C81Q Indicator*’
5
1
3/4
6
1
1/4 Dia.
7
1
1/4 Dia. xl corrosion res, stl,
8
1
1/4-28 nut
9
1
3/8
10
1
3/8
x
11
1
1/4
x
12
2
1/2
x
13
13
2
KN813 Keensert
14
2
1/8
x
x
x
1 3/8 x
x
x
x
x
7 1/2
2 1/2
5
x
x
10 aluminum
.6811N
res.
equiv.
stl.
II
I
II
1
1.6’
IN
.31 IN
10 rubber
2
x
10 rubber
2
x
x
equiv. equiv.
rnt
x
1
or
14 aluminum or
2 corrosion
x
or
1 3/4 aluminum or
10 corrosion x
3 VLIER or
res.
Torque
stl.
C
screw
tap 1/2
3/4 rubber
13
SECTION A A THIS GROOVE TO BE A SNUG FIT TO THE SCREW BRACKET ON
’*P/N of Federal Products
Corp., Providence, R. I.
THE DIAL INDICATOR
100-135-8
Fabricating Clamp tor Tab Detlection Figure 4
27-3090
PegelO Oct 7183
A6
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
NOTE Lubricate
all
parts
O-ring
except
with
MI L-G-23827 g rease prior to assemb ly. Lubri cate
the
O-ring
with
MIL-S-8660
(50, Chart 1,
"B"
"28".
Multiply
Subtract "A" from "28" and record
3.
Multiply
"D"
by
2 and record
1.
2.
by
as
2 and record
as
"X".
"2D".
as
4.
Subtract "C" from "2D" and record
5.
Add "X" and "Y" and record
as
"Y".
"E".
as
91-00-00). CHART 1 ELEVATOR TAB FREE PLAV LIMITS h.
the end
Screw
play
adjusting bushing (11)
into
housing (8) until assembly, and
has been removed from the nut
tighten the check permissible.
nut
(12).
An end
play
of 0.003 inch is
CHECKING ELEVATOR TAB FREE PLAY (CE-748, CE-772 and after; E-llll, E-1241 and after; CJ-149 and after)
1.5-FOUND
SPOUND
READING
READING
28
-A
=X
+Y
=E
D
2D X
security of actuating corrected prior to
Visually inspect the elevator tabs for any damage, hinge attach points, and for tightness of the systems. Inconsistencies should be checking the free play of the tabs.
(E
0.050 inch
NOTE
(P/N 810 4~135030-9) or equivalent, a dial indicator, and a push-pull scale for applying accurate loading to the tabs are required for making the inspection for
A check fixture t
free
play
The results of "X" and "Y"
can
be
negative
numbers.
of the tabs.
Lock the control surface to prevent movement of the elevators. Set the elevator tabs in the neutral position. b. Using shot bags and tape, affix the dial indicator
maximum)
a.
so that the dial indicator point is positioned on edge of the elevator tab at a point 3.30 inches aft of the hinge line as measured along the top of the tab. c. Apply a sman piece of masking tape to the upper surface (for paint protection) 4.50 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 settle. d. Apply another piece of masking tape in the corresponding position on the bottom surface of the tab for
check fixture the outboard
the
same e.
purpose, Zero the dial indicator at
during
the
no
load
initially. Do
not
Repeat steps
"b"
through "j"
the
on
opposite
ELEVATOR TRIM TAB ACTUATOR REMOVAL F33C, A36, A36TC AND B36TC) a.
Remove the
access
the horizontal stabilizer to
panel
gain
near
access to
the
(F33A,
trailing edge
of
the elevator trim tab
actuator
b.
light
Detach the tail cone, disconnect the tail remove the tail cone.
navigation
wire and c.
the
checking procedure, With the push-pull scale at the point of the f. masking tape, apply 9-pound downward load. Record the dial reading as "A". Release half the load until a l.£ downward g. load is obtained. Record the dial reading as "B". h. Apply a full 9pound upward load at the masking tape on the bottom surface. Record the dial reading as "C". i. Release half the load until a 1.Bpound upward load is obtained. Record the dial reading as "D". Enter the recorded values on a copy of CHART 1 j. and proceed as follows: reset
k.
elevator tab.
Remove the
fuselage just d.
access
Remove the
access
the horizontal stabilizer to actuator e.
on
the left hand side of
panel
gain
near
access to
the
leading edge of
the elevator trim tab
sprocket. Remove the elevator
00 under the f.
panel
forward of the horizontal stabilizer.
heading
as
outlined in
Chapter
27-30-
ELEVATOR REMOVAL.
Disconnect the elevator trim tab cables at the turn-
buckles in the aft
fuselage.
Secure the forward elevator trim
t,b cables to prevent them from
unwinding
at the universal.
CAUTION Do not damage the cables. Use a material such phenolic to protect the cables.
as
27-30-00
Page ’A10
11
;May31/851
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
Remove the chain and cable assembly g. from the elevator trim tab actuator sprocket.
Install the access panel located g. leading edge of the horizontal stabilizer.
near
the
the eleva-
Install the access panel located h. trailing edge of the horizontal stabilizer.
near
the
Remove the hardware
h. tor
trim
tab
to
actuator
Remove the actuator from the
attaching
horizontal
the
stabilizer.
airplane. access panel on the left hand fuselage just forward of the horizontal
Install the
i.
ELEVATOR TRIM TAB ACTUATOR INSTALLATION (F33A, F33C, A36, A36TC AND
side of the stabilizer.
B36TC) install the tail
The elevator trim tab actuators must not be interchanged between the right and left
B36TC) airplanes serials CE-1566 and after, CJ-180 and after, E-2111 and after, and EA-389 and after, elevator On
trim tab actuators have been color coded LH blue and
uncontrollable airplane attitude. Refer to ELEVATOR TRIM TAB ACTUATOR COLOR CODING to reduce the probability of unintentionally switching the actuators upon installation. an
installation cover
On earlier
airplanes,
not color coded. actuators
Position the chain and cable
sprocket equidistant within
the actuator
assembly
(LH
appropriate
blue
and
RH
black).
horizontal
b.
that the
visually inspecting
and
color coded actuator is installed
hardware,
are
Actuators may be inspected for proper by removing the actuator inspection hole
RH black.
Position the elevator trim tab actuator in stabilizer and install the attaching
a.
the
navigation light wire and
cone.
ELEVATOR TRIM TAB ACTUATOR COLOR CODING (F33A, F33C, A36, A36TC AND.
horizontal stabilizers when they are reinstalled after removal. Reversing the actuators reverses the direction, and plane nose-up trim would actually resiilt in an inadvertent nose-down trim condition that could result in
Connect the tail
j.
WARNING
on
that the ends of the chain +.20 inch at the sprocket cen-
so
terline.
installed
can or
elevator trim tab actuators
were
coding of the elevator trim tab accomplished with the actuators
Color
be
This will reduce the
before installation.
unintentionally switching the actuators. probability Use BEECHCRAFT Mandatory Service Bulletin No. of
2399 for
painting
instructions
how to color code
on
elevator trim tab actuators. c.
Install the elevator as outlined under the OF THE ELEVATOR.
WARNING
heading INSTALLATION d.
Connect the elevator trim tab cables to the
turnbuckles in the ah e.
Remove
Do not install
fuselage.
material
used
to
protect
the
cables.
a
blue-coded actuator
black-coded
stabilizer
actuator
blue-coded stabilizer.
on a
or
a
ELECTRIC ELEVATOR TRIM
Rig the elevator trim tab control system as outlined under the heading RIGGING THE ELEVATOR f.
on
a
black-coded
(OPTIONAL)
When the elevator trim tab control wheel
optional electric trim system offered on the airplanes allows the pilot to correct the elevator trim without removing his hands from the controlwheel. The switch requires 2 actions before it will actuate the system: first depressed ~enable switch), then moved forward (down-trim) or rearward (up-trim). On the control wheel left hand grip is a quick-interrupt switch (placarded TRIM INTER) which opens the circuit to the servo and stops the action of The PITCH TRIM OFF-ON the electric trim system.
is moved toward the NOSE DOWN
position,
switch is located in the lower left
the elevator trim tab should
UP.
ing instrument panel and the circuit breaker ~plac-
TRIM TAB.
NOTE After tab
rigging the elevator and elevator trim system, check for correct
control
movement
respect
of the
to the
control
surfaces
with
movement of the controls.
move
The
Bonanza
corner
of the float-
27-30-00
Page 12 Jun 20/91
A14
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
is
TRIM)
arded
circuit breaker
located
electroluminescent
the
in
below the instrument
panel
panel.
TRIM ELEVA TOR GROUND ELECTRIC CHECKS (AIRPLANES WITHOUT
AUTOPI-I
LOT) A36TC, AND
MODEL A36,
B36TC
access
to the
SIXTH
AND
by removing the (refer to Chapter 25 REMOVAL
SEAT
INSTALLATION) and the partition gage compartment and ah section
ON
bagairplane.
the
left trim
(make a note reinstallation)
and dia-
the turnbuckle
Unsafety
on
the
trim
switch
master
and
system circuit breaker.
AND
between the
of the
Turn
b.
engage the "TRIM" c.
and
move
Simultaneously press the pilot’s control wheel switch
that the trim wheel b.
of the electric trim instal-
wires, obstructions safetied cables,
lation for loose
servo
sixth seat
(if installed)
FIFTH
under
SERVO
etc., turn "ON" airplane master switch.
Gain
a.
fifth and
TAB
TRIM
inspection
After
a.
ELEVATOR
ELECTRIC REMOVAL
moves
enable
switch
forward.
toward "DOWN" trim
Note
posi-
cable and loosen the cable. d. c.
Remove the cable
gram of the cable routing for pulleys and capstan.
from the
Remove the 4 bolts, nuts, and 8 washers which secure the servo to the brackets in the aird.
plane.
With
manual override
e.
and
e.
Remove the servo
(note on which side of mounted) from the airplane.
servo
is
TAB
TRIM
ELECTRIC ELEVATOR INS TALLA TION
SERVO
a.
Place the
servo
in
position
and install the
4 bolts, 8 washers, and 4 nuts (make certain the servo is installed in the same position from which it was
removed). Install the cables on the ~outboard) trim cable should be b.
servo.
routed
The left
forward
around the outside groove of the capstan and back to the aft pulley, then forward to the other pulley; wrap around the forward pulley and aft around the inside groove of the
capstan
Install
c.
cable to the
d.
the
pulley
as
and forward to the turnbuckle.
right
(inboard)
elevator
switch
still
capability;
the clutch will
slip.
Simultaneously press the enable switchl p’ilot’s control wheel switch rearward. Note trim wheel moves toward the "UP" trim posi-
that the
With
f.
Adjust the capstan cable guard to within capstan and secure with the attaching Tighten the attaching bolts of the 2 idler
screws.
pulleys. e. Adjust the cable tension per RIGGING THE ELEVATOR CONTROL SYSTEM and Figure 1.
restrictions.
control
wheel
Press the enable switch
must not
switch
still
only;
trim
system
run.
Move the trim switch fore and aft
h.
system
must not
only;
trim
run.
The control wheel mounting includes an I trim-interrupt switch. This switch has the primary purpose of stopping all trim action by interand ground. The interrupt rupting both the trim A switch is a momentary type pushbutton, which may i.
electric
be checked
as
1.
follows:
With the trim system still turned on,
actuate the trim switch to drive the trim
system. While system is being driven, push the interrupt switch and note that the trim system stops running while the switch is
depressed.
If the trim system operates while the 2. interrupt switch is depressed, the trouble should be located and corrected before flying the airplane.
j. Operate the elevator trim system through complete range of of travel to check for any bindf.
pilot’s
grasp the trim wheel and check for manual Ove"ide capability; the clutch will slip.
engaged,
trim
indicated in step "b".
1/32 inch of the
or
wheel
move
g.
ing
control
tion.
the brackets the
its
pilot’s
the manual trim wheel and check for
engaged, grasp
without
If the circuit breaker
both
the
switch actuated,
enable
pull
trips
switch
or
and
the trim
the
runs
direction
the trim circuit breaker, turn the
trim master switch OFF and leave disconnected until 27-30-00
Page 12A A14
Jun 20/91
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
the trouble is located.
breaker out, do not k. the
If the trim
runs
with the circuit
N~W TAB CABLE INSTALLATION
fly the airplane.
After the
electric trim
airplane manual trim system
system check-out, should be free of
excessive friction and should function
Note the position of the old cable in relation to the cable drum and forward end cable fittings. Install the new cable in the same positions
normally. MAGNETIC CLUTCH REMOVAL
MODEL
F33C AND V35B
F33A,
(Figure 5)
ELECTRIC TRIM TAB ACTUATOR REMOVAL Remove the
a.
just
below the
b.
access
leading edge of
on
actuator wire
Disconnect the
the disconnect
door
the
fuselage
the L.H. stablizer.
harness
at
splices.
buckle.
Tape the cable unwinding of the cable.
to the actuator to
Remove the lid from the clutch
b.
Loosen the set
ator
to
Remove the three bolts
prevent
the
bracket.
removed from the
ELECTRIC LATION
The
securing the
actuator
may
actu-
now
be
airplane.
TRIM
TAB ACTUATOR INSTAL-
a.
Place the actuator in its
b.
Install the bolts
mounting location.
securing
the
actuator
place.
Remove the motor from the clutch
d.
Slide the cable drum and shaft
from the clutch
Connect the cables at the turnbuckles
d.
Connect the wire harness.
rotor
in
housing.
assembly
housing.
Remove the clutch from the clutch
housing.
MAGNETIC CLUTCH INS TA LLA nON
(Figure 5) a.
Install the clutch in the clutch
b.
Slide the cable drum and shaft
into the clutch
c.
housing. assembly
housing.
Tighten
until there is
c.
in the clutch
c.
e.
d.
screw
housing.
and armature hubs.
Disconnect the actuator cable at the turn-
c.
a.
no
the
clutch
visible end
armature
play
set
screws
in the cable drum
shaft. Slide the clutch rotor on the motor shaft to obtain .010 to .015 inch clearance between the friction
surfaces screws.
of the
clutch
Stake both set
before
tightening
the
set
screws.
27-30-00
Page
128
Jun 20/91
A14
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CLUTCH ROTOR
CLUTCH HOUSING
.010 to .015
I II CLUTCH
CLUTCH
ASSEMBLYrlL~ SETSCREW
CABLE DRUM SHAFT
CABLE RETAINING PIN
CABLE DRUM Bo-3ael
Electric Trim Tab Actuator Figure 5
CAUTION
tool
that will
shaft
fit the
the
which
on
cable drum is
mounted. With
no
visible end
play
in the cable drum shaft,
the clutch is
de-energized
or
damage
fabricate
to the
450
similar tool
a
’/2
rpm)
TAB
ELECTRIC TRIM REPLACEMENT SCHEDULE
ACTUATOR
the brushes at intervals of 2000
flight
BFIUSH
hours,
performed
check should be
following magnetic clutch
is
drill
any time the
28 vdc power source, connect the red Using lead of the magnetic clutch to ground and the white lead to the power source. Using a torque wrench, check that the
inch-pounds
of torque
applied
at the
be
attached
to
the
5.
Remove the
access
plate
from the clutch
and clutch clean with clean
and blow the
16 vdc,
connect the red electrical lead of the clutch to
ground clips.
Using
housing
a
regulated
power
and the white lead to the power
drill off and
source set at 14 to
source
with
alligator
With the screwdriver in the slot in the drum
unclip
on
and
run
for 15 seconds. Turn the
the leads to the clutch.
8. Let the clutch cool for approximately one minute before reattaching the lead for another 15 second interval. Repeat the foregoing sequence until the clutch will
inch-pounds of torque as indicated in step "a", housing clean with clean dry compressed air. Install the access plate on the clutch housing. hold with 30
actuator shaft.
If the static torque of the clutch is less than 30 inch-pounds, burn the clutch as follows: b.
Find
a
metal
plate
then
blow the clutch and
of sufficient thickness for
to fit in a vise with the actuator
and
large enough rigidity assembly attached. Anchor
the
plate
holes in the plate to match the actuator the actuator to the plate. 2.
may
or
speed (approximately
Secure the screwdriver in the 1/2 inch drill
7.
a
1.
motor
low
housing dry air.
replaced.
clutch holds with 30
a
4.
shaft turn the drill motor a.
that
motor.
6.
MAGNETIC CLUTCH TORQUE TEST The
inch
so
screwdriver or similar tool.
clutch will result.
Replace
Remove the handle from the screwdriver
3.
the clutch faces must not make contact while
Locate
a
CAUTION
in a vise and drill 3
mounting holes. Bolt
blade type screwdriver
or
similar
Exceeding the 15 second burn-in periods may damage the magnetic clutch.
overheat and
"END" 27-30-00
Page A6
13
Oct7/83
EEECHCRAFT BONA~UA SERIES MAINTENANCE MANUAL
STALL WARNING/SAFE FLIGHT SYSTEM DESCRIPTION AND OPERATION
As
rule of thumb,
moving the vane 1/4 inch will change the warning actuates by about 5 mph of indicated airspeed. The only way to test the accuracy of the setting is to fly the airplane into a stall, noting the speed at which the warning horn comes on and the speed at which the full stall a
time the stall
STALL WARNING SYSTEM
occurs.
The stall
warning system is designed to give the pilot advance warning of an impending stall. The stall warning switch is located on the bottom leading edge of the left wing. Air moving over the vane of the switch will cause the switch to open or close depending an the air velocity. The opening or closing of the stall warning switch indicates the lift capabilities of the wing and subsequently indicates to the pilot the approaching of a stall condition.
STALL WARNING
ADJUST UP TO ACTUATE SOONER
O
i
o
MAINTENANCE PRACTICES
STALL WARNING SYSTEM
ADJUSTMENTO SCREWS?
ADJUSTMENTS
O
\O
The stall warning switch is carefully adjusted when the airplane is test flown at the factory. Should it require
readjusting, proceed installation the two
as
follows:
Locate
the under surface of the left
on
Phillips-head
vane.
If the stall
move
the
vane
O
O
(Flgure 1)
one
screws,
warning has
been
on
the
O
O
switch
ADJUST DOWN TO ACTUATE LATER
wing and loosen
60-251-1~
either side of the
coming
back and down. If the stall
on
too
early,
warning
Stall Vane Adjustment
has
Figure
coming on too late, move the vane up and forward. Moving the vane, with the Phillips-head screws loosened, moves the entire unit up or down inside the wing causing the switch to be closed earlier or later. Retighten the screws after making each adjustment. NEVER TRY TO been
1
ADJUST THE SWITCH BY BENDING THE VANE. The stall should be made with the
flaps and gear up and power off. Prior to stalling decelerate no faster than one mph per second. It may be necessary to make several
NOTE
alternate
If
a new
(lift detector) is being installed it positioned (with vane full down) so
switch
should be that the
upper surface of the vane is in with the index line on the cover
alignment plate. The airplane should then be flown the switch adjusted as indicated in following procedure,
i
setting ideally,
adjustments
can
at 7 to 9
switch
and test
mph
setting should
necessary whenever
and
replaced
the
installed.
flights before the desired warning should actuate,
be reached. The stall
ahead of the
a wing or extensively repaired, The switch should require or
complete stall. The adjusted as wing leading edge is
be checked and or no
if
a
switch
new
adjustment
is
in normal
service.
"END"
27-31 -00
Page 1 May 9/80
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
FLAPS
DESCRIPTION AND OPERATION
This
flaps are hinged in specially designed tracks. When extended, the flap moves gives a large, effective wing area, which produces additional lift and drag.
One
flap
The
is installed
on
each
wing.
The
flaps
are
operated by
an
rearward
electric-motor-driven
as
it
pivots
gearbox on the
downward.
aft side of the
front spar at the centerline of the airplane. The gearbox drives two flexible drive shafts, each connected to an acmethread-type jackscrew at each flap. The flaps are controlled by a lever in the subpanel, and the flap position is indi-
by an instrument to the left of the control column. The lever (switch) must be pulled out of a detent to change positions. On airplane serials E-llll, E-1241,though E-1370; CJ-149; CE-748, CE-772 though CE-815; D-10097, and D-10120 through 0-10178, the flaps may be stopped at any position by moving the flap switch to OFF when the flaps reach the desired position. The switch is placarded UP, OFF, and DOWN. The markings on the position indicator will be UP, 10", 20", and DN. On airplane serials CJ-150 and after; CE-816 and after; D-10179 and after; E1371 though E-2110 except E-1946 and E-2104; EA-1 though EA-388 except EA-320, the indicator is marked UP, 15", and DN. Serials E-1946, E-2104 and E-2111 and after; EA-320 and EA-389 and after, have lights to indicate flap position. These lights are marked to indicate the down, in-transit, and approach positions of the flaps. All lights are out when the flaps are up. The flaps can be stopped only on the up, approach, or down position as indicated by the flap switch.
cated
The
flap position transmitter (if installed) is located near the left flap by the flap relay and limit switches.
actuator. Power to
operate the indicator lights
of later serials is controlled
NOTE After
an
damage FLAPS
emergency extension at speeds above the normal extension speeds, or distortion before the next flight.
inspect the flaps for
MAINTENANCE PRACTICES
FLAP REMOVAL a.
Remove the bolt from the
b.
Remove the
c.
Remove the bolts from the
flap actuating
bonding cable
from the
flap
flap
arm.
tracks.
track brackets and
remove
the
flaps.
FLAP INSTALLATION a.
Hold the
flap
in
position
and install the rollers and the bolts in the
flap track
bracket.
NOTE flap track rollers (four rollers per flap and two rollers per track) in the flap track brackets flanges of the rollers in one track facing the flanges of the rollers in other track.
Install the with the b.
Connect the
bonding
cable and install the bolt in the
flap actuating
arm.
FLAP TRACK WEAR LIMITS The allowable track
wear on
the track slot. The allowable
the
bearing
wear
surface is 0.032-inch
resulting
in
a
maximum dimension of 0.785-inch in
into the track side surface is 0.050-inch. Track
wear
within the
preceding limita(49 and
tions may be dressed smooth with light emery cloth to prevent roller binding. Lubricant mixed with solvent 26, Chart 1, 91-00-00) may be brushed on the flap tracks during servicing of the airplane.
n20
27-50-00
Feb
26/99Page~
Rayeheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
FLAP LIMIT SWITCH ADJUSTMENT
NOTE
Battery voltage is not sufficient to properly cycle the flaps during rigging. An auxiliaty power supply capable of maintaining 28.25 ~t0.25 volts should be used. If an external power receptacle is not available on the airplane, jumper cables may be used between the battery and the power supply. Be sure of the polarity before making the connection.
I CAUTION I Excessive a
The
flap
short
operation of the flap motor without proper cooling may cause damage to the motor. Allow cooling time after each extension and retraction cycle.
limit switches
left wing
panel.
limits of travel.
are
mounted
on a
bracket and installed
on
the outboard side of the inboard
The limit switches control the travel of the
They
are
accessible
by lowering
the
flaps by breaking the circuit to the flap flaps.
flap
track in the
motor at the extreme
TWO-POSITION FLAPS
(CE-748, There
CE-772 THRU
CE-815; CJ-149; D-10097, D-10120 THRU D-10178; E-llll, E-1241 THRU E-1370)
two limit switches for this
for the
uplimit position, and one for the downlimit position. To adjust position, assembly so that the assembly can pivot on the foMlard hole. the switch to the as elongated Adjust flaps in neutral position. Actuate the flap switch to the stop necessary down position and measure the degrees of travel (proper degree of travel is 30" +0" -2"). Adjustment of the down position of the flaps is made on the downlimit switch.
the
are
flaps to
neutral
system,
loosen the
one
screws
of the switch
THREE-POSITION FLAPS
(CE-816
AND
AFTER; CJ-150 AND AFTER; D-10179
AND
AFTER; E-1371 AND AFTER; EA-1 AND AFTER)
The limit switches, one for up, two for the approach position and one for the down travel, control the travel of the flaps by breaking the circuit to the flap motor at the extreme limits of selected travel. The switches are accessible by
lowering The
the
flaps.
flap travel is adjusted by moving the Rig as follows:
limit switches. The left
flap
is
rigged first, then
the
right flap is synchronized
with it.
NOTE
Rig the flaps
under
a
simulated
flight load to
reduce overtravel to
a
minimum after the limit switches
have been actuated. When the tween the a.
Adjust
Page
the
flaps are in the 00 position, a clearance of 1/16-inch +1/1Fj-inch flap roller and the forward edge of the flap track slot.
uplimit
switch
so
the
flaps
27’50-00
will
stop
at the 0"
-1/32-inch must exist be-
position.
A2D
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE At serials E-1946, E-2104, E-2111 and
limit
after, the flap switch approach position
is 12".
Adjust the
11"
flaps (outboard) flaps are positioned fully up position to the approach position. Adjust the 13" limit switch (inboard) switch until the flaps are at the 13" to 12.50 position after the flaps have been actuated from fully down to the approach position. switch until the
at 11" to 11.5" after the
have been actu-
ated from
b.
Adjust
(inboard) in its mounting slot until the flap is positioned at 14" to 14.5" after the flap fully up to the takeoff position (15" range). Adjust the 16" limit switch (outboard) in its mountpositioned at 16" to 15.50 after the flap has been actuated from fully down to the takeoff po-
the 14" limit switch
has been actuated from
ing
slot until the
sition
flap (15" range).
is
c.
Adjust the downlimit switch
d.
Remove the bolt
e.
Turn the
f.
Install the bolt
in its
mounting slot until
attaching the right
jackscrew
on
the
connecting
right
actuator to the
actuator in
or
the actuator to the
it actuates at 28" to 30" of
flap
travel.
right flap.
out to
align
the
right flap
with the left
flap.
flap.
CAUTION I I CAUTION If the
flaps
are
removed for any
reason
the main power switch should be in the OFF position.
NOTE After the
flap is completely rigged, adjust the rubber bumper (flap down) installed on the flap and dividing rib. Turn the adjusting screw in or out, as required, to take out play or stop vibration when the flap is in the up position. A distinct change in the sound of the flap motor near the completion of the flap-up travel may indicate an excessive outward adjustment of the bumper. aileron
g. Operate the rubber bumper.
~20
flaps through
full travel to
ensure
that the
flaps
contact the limit switches before
they contact
27-50-00
Feb
the
26/9 Page
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
FLAP SVSTEM FLAP SETTING FLAP ACTUATOR
CE-748, CE-772 THROUGH CE-815; 01-149 D-10097, D-10120 THROUGH P101Z8;
FLAP SHAFT
E-llll, 6-1241 THROUGH E-1370
d FULL UP FULL DOWN
0"
30"
AND HOUSING
2"
FLAP ACTUATOR MOTOR
CE-816 AND AFTER, CJ-150 AND AFTER 0-10179 AND AFTER, E-1371 THRU E-2110 EXCEPT 6-1946 AND 5-2104 EA-1 AND AFTER FULL UP
LIMIT SWITCHES FLAP SHAFT AND HOUSING
O"
APPROACH FULL DOWN
15" 30"
0’
ACTUATOR
2"
6-1946 5-2104, E-2111 AND AFTER FLAP POSITION INDICATOR
FULL LR O" 12" APPROACH FULL DOWN 30"+ 0"- 2"
L
FLAP POSITION fftANSMTT~R
INDICATOR
INDICATOR
FLAP ACTUATOR
TRANSMITTER
CE-748, CE-772 THROUGH
:o
CE-BIBANDAFTER CJ-1SOANDAFTER D-10179 AND AFTER D-10~20 THROUGH D-10178 E-llll, 6-1241 THROUGH 6-1370 G1371 THRU E-2110 EXCEPT E-1946 AND E-2104 EA-1 THRU EA-388 EXCEPT EA-320’
CE-815; CJ-149, 0-10097,
TO ADJUST, LOOSEN MOUNTING BOLTS ANO MOVE FORE AND AFT, OR ROTATE SLIGHTLY.
WHICH HAVE LIGHTS TO INDICATE POSITION
POSTTION SWITCHES SWITCHES DOWNLIMIT SWITCH
o~/or UPLIMTT SWITCHES
UPLIMIT SWITCH
CE;748, CE-n2 THROUGH CE-815, 01-149; D-10097, 0-10120 THROUGH D-10178; E-llll, E´•1241 THROUGH E-1370
FLAP LIMTr SWITCHES
CE-816 AND AFTER CJ-150 AND AFTER D-10179 AND AFTER 5-1371 AND AFTER EA-1 AND AFTER 33-161-15
Flap System Figure 1
Page
4
Feb 26/99
27-5000
A20
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
FLAP POSITION INDICA TOR AND ADJUSTMENT The
flap position
is installed a.
on
indicator gage is installed in the instrument panel. An adjustable flap position indicator transmitter the flap actuator in the left wing just forward of the rear spar to coordinate gage reading with flap travel.
Adjust the flap travel limit ADJUSTMENT.)
switches to
provide
the correct up and down travel of the
flaps. (See
FLAP LIMIT
SWITCH b. not
Run the flaps down and check the pilot’s compartment flap position indicator for 100% flaps. If down flaps are indicated, loosen the transmitter attachment bolts and adjust transmitter fore and aft or rotate slightly until the
reading c.
is correct, then
Run the
flaps
tighten
the transmitter
attaching
up and check the indicator for up
bolts.
flaps reading.
FLAP MOTOR REMOVAL
CAVTION I I CAUTION If the
be
flap motor fails orif major overhaul is required for it to operate properly, the flap motor should replaced. No attempt should be made to overhaul the motor in the field.
a.
Remove the front seat assemblies.
b.
Removethe sparcover.
c.
Detach the
d.
Disconnect the motor electrical
e.
Loosen the two set
f.
Rotate the cable retainers 90".
g.
Loosen the nuts
h.
Pull the flexible drive shafts from the
i.
Remove the
clamp supporting
screws on
wiring
wiring
at the
motor
from the
quick
right-hand flap-shaft housing.
disconnect.
each cable retainer.
the inboard side of the
on
flap
the electrical
attaching
flap
mounting supports.
motor shafts and retainers.
bolts and
remove
the
flap
motor.
CONNECTING FLEXIBLE FLAP DRIVE SHAFT TO FLAP MOTOR SHAFT FIGURE 2 Connect the LH and RH flexible
flap drive shafts
to the
flap
drive motor shaft
as
follows, using the illustration for
component locations: a.
Install the outboard nut and washer
b.
Start setscrews
shaft
as
far
c.
Align
d.
While
~uo
as
as
far
as
they
will go onto the threaded
(2) into retainer. Insert the retainer through
the
flap
shaft
portion
of the
flap
mounting support
shaft
housing.
and onto the motor
it will go.
retainer
keyway with key slot
inserting
the
flap
shaft
in
through
flap the
motor drive shaft and
mounting support,
tighten
one
setscrew
temporarily.
install the inboard washer and nut.
27-50-00
5
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL e.
Install the
flap
shaft
through
the retainer and into the motor drive shaft until the
keyway
is
just past the key slot
in the retainer. f.
Loosen the set
g.
Ensure that the retainer is still installed
h.
Keep inboard
i.
Secure the
screw
that
pressure
flap
on
was
tightened
in step
c.
the motor shaft
on
the retainer and
tighten
as
far is it will go and rotate retainer 9(P.
both retainer set
screws.
drive shaft to the
mounting support by tightening the nuts (2). Tighten inboard nut to ensure that edge of the retainer and the cable housing to allow the retainer to rotate without coming into contact with the cable housing. In threaded part of cable housing is not long enough to install the two nuts and washer, use a die to add 5/8-24 UNEF threads until 0.88 inch thread length is attained. there is sufficient clearance between the outboard
j.
Tighten
outboard nut
against the mounting support.
FORWARD TAINER
(50-361131)
MOUNTING SUPPORT OUIBOARD
FLAP MOTOR
SET OUTBOARD NUT
SET SCREW
KEY SLOT IN MOTOR SHAFT
SET
SCREW
SCREW
RETAINER
KEYWAY
OUTBOARD WASHER INBOARD INBOARD WASHER
NUT
ENSURE THAT THERE IS SUFFICIENT CLEARANCE BETWEEN THE OUTBOARD EDGE OF RETAINER AND THE CABLE HOUSING TO THE RETAINER TO ROTATE WITHOUT COMING INTO CONTACT WITH THE HOUSING.
INBOARD END VIEW RETAINER (50-361
OF
OUTBOARD
31]
RETAINER
END
VIEW
OF
[50-361131) C93D*0480116 C
Flap
Cable Retainer
Figure
Page
be26/99 F6
27-50-00
2
A20
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
FLAP MOTOR INSTALLATION
CAMON 1 I CAUTION Should the
erly,
flap
motor fail or should
it should be
a.
Place the
b.
Connect the
c.
Install flexible
flap
motor in
flap
and
position
motor electrical
secure
wiring
drive shafts into the
flap
major overhaul be required
for the
flap
motor to
operate prop-
No attempt should be made to overhaul the motor in the field.
replaced.
with the
at the
flap
quick
flap
motor attach bolts.
disconnect.
motor shafts in accordance with CONNECTING FLEXIBLE FLAP
DRIVE SHAFT TO FLAP MOTOR SHAFT.
supports the electrical wiring from the right flap shaft housing.
d.
Attach the
e.
Run the
f.
Install the spar
g.
Install the front seat assemblies.
clamp
that
flaps through
full travel, up and down, to check
flap rigging.
cover.
FLAP SHAFT REMOVAL a.
Place the
airplane
on
jacks
and
use
the circuit breaker to retract the
landing
gear until the inboard doors
are
open. b.
Remove the front seat assemblies.
c.
Remove the spar
d.
Loosen the two set
e.
Rotatethecable retainer90".
f.
Remove the nut
g.
Pull the flexible drive shaft from the
h.
Disconnect all
i.
Remove the dust
j.
Disconnect the
k.
Pull the actuator and flexible shaft
A20
cover.
on
screws on
each cable retainer.
the inboard side of the
clamps securing cover
flap
in the
flap
motor shaft and retainer.
the shaft
rear
mounting support.
housing
to the
wing
structure.
section of the wheel well.
actuator from the
wing flap
housing
and the
out of the
wing
spar section.
wing.
27-50-00
Feb
26/9 Page
7
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
FLAP SHAFT INSTALLA TION a.
Pull the flexible shaft and
the
housing through
and attach the actuator to the
wing
wing flap and wing
spar
sec-
tion. b.
Set the
c.
Push the flexible shaft into the
d.
Rotatethe retainer90".
e.
While
f.
Tighten
g.
Install the
h.
Install the dust
i.
Run the
j.
Lower the
k.
Install the spar
i.
Install the front seat assemblies.
flaps
in the up
holding
position.
flap
motor shaft and retainer.
the retainer onto the motor shaft
the nut
on
the inboard side of the
in the
flaps through
to the
wing
the two set
screws
in each retainer.
structure.
section of the wheel well.
full travel, up and down, to check
gear and
landing
rear
possible, tighten
as
mounting support.
clamps securing the shaft housing cover
far
as
remove
the
flap rigging.
airplane from the jacks.
cover.
FLAP ACTUA TOR REMO VAL a.
Place the
b.
Remove the dust
c.
Lower the
airplane
flaps
on
jacks
cover
and retract the
in the
rear
landing
section of the wheel well to
and disconnect the actuator from the
gain
access
the circuit
(use
gear until the inboard door is open
breaker).
to the actuator.
flap.
NOTE To retain the so
original rigging
of the
that it may be installed in the
flaps, mark the extension of the flap actuator before position.
flap position transmitter from
d.
Remove the
e.
Remove the snap
ring
f.
Remove the
bolts from the
pivot
the
flap
actuator.
and disconnect the flexible drive
flap
it is removed
same
mounting
actuator
housing. bracket and
remove
the
flap
actuator.
FLAP ACTUA TOR INSTALLA TION
flap
position
a.
Place the
actuator in
b.
Connect the flexible drive
c.
Install the
flap position
housing
and
secure
it to the
flap
and install the snap
transmitter to the
flap
actuator
mounting bracket
with the
pivot
bolts.
ring.
actuator.
NOTE The
Page
flap position transmitter
27-50’00
is
on
the left-hand
flap
actuator
only.
A20
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
flap
actuator to the
d.
Connect the
e.
Install the dust
f.
Check the
flap rigging.
g.
Lower the
landing
cover
in the
flaps
position
marked
during
removal.
section of the wheel well.
rear
gear and
in the extended
remove
airplane from
the
the
jacks.
FLAP INNER FLEX SHAFT REMOVAL
FIGURE 2
jacks and
retract the
a.
Place the
b.
Remove the front seat assemblies.
c.
Remove the spar
d.
Loosen the two set
e.
Rotatethecable retainer90".
f.
Remove the dust
g.
Remove the two bolts
airplane
on
landing
gear
(using the
circuit
breaker)
until the inboard door is open.
cover.
the cable retainer.
screws on
cover
in the
rear
holding
of the wheel well to
gain
access
the forward end of the actuator in
to the actuator.
place.
NOTE The first
clamp which
ibility to
the flex drive.
The h.
position
secures
transmitter
Remove the snap
on
ring holding
the flex drive to the
the left
flap
wing
may have to be removed to allow
more
flex-
may need to be removed.
the flex drive to the actuator
NOTE Do not lose the spacers located under the i.
To facilitate installation, note how far the shaft
j.
Pull the flex inner shaft from the
flange
of the flex drive.
protrudes past the flange of
the
housing.
housing.
FLAP INNER FLEX SHAFT INSTALLA TION
NG URE 2 a.
Lubricate the inner flex shaft with grease
b.
Install the inner flex shaft into its
c.
Rotate the inner flex shaft until the
plished,
Chart 1,
91-00-00).
housing. key
on
the inner end of the shaft slides into
the measurement noted in FLAP INNER SHAFT REMOVAL step i should
flap
shaft into the
d.
Push the
e.
Rotatethe retainer900.
nu,
(11,
flap
place. (When this is accomagain be noted at this time.)
motor shaft and retainer.
27-50-00
9
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL f.
While
holding
the retainer onto the motor shafts
as
far
possible, tighten
as
the two set
screws
in the retainer.
NOTE Be certain the spacers
g.
Install the
flap
are
in
shaft into the actuator and install the snap
place
in the actuator.
ring.
NOTE A screwdriver may be used to make small adjustments to the actuator does not align with the key of the flex shaft. h.
Secure the actuator in
screw
of the actuator if the slot in the
with the two bolts, washers, and nuts.
place
NOTE The on
position transmitter will have
the shaft if it
i.
Install the dust
j.
Lower the
k.
Cycle
the
flap if it
was
removed. Install the clamp
removed.
cover.
landing
flaps
was
to be installed on the left
gear and
remove
to determine that
the
they
airplane
are
from the
jacks.
properly rigged. NOTE
For correct
adjustment
and
rigging
of the
DICATOR AND ADJUSTMENT in this
flap position
transmitter refer to the FLAP POSITION IN-
chapter.
FLAP ACTUA TOR DISASSEMBL Y
ring (2)
a.
Remove the snap
b.
Tap
c.
Slide the
d.
Check that the end
pounds
e.
on
the
to disconnect the flexible shaft
piston plug (Il)to
piston (6)
of force in both
out of the
drive out the seal
(3)
and
bearings (4).
Withtheactuatorscrew 1/2extended.
3.
With the actuator
screw
screw
fully extended
If the 0.012-inch tolerance is exceeded, screw.
0.012 inch under 25-50
full in and backed out 1 turn.
2.
Page
spacers
play between the piston (6) and the screw (5) does not exceed compression and tension at any of the following positions:
With the actuator
the
from the actuator.
housing (8).
1.
acceptable replace
(17)
(1)
replace the piston and plug with a new one. If the tolerance play of the new piston and screw per the preceding step.
Check the end
1027-50-00
and backed in 1 turn. is still
un-
Raytheon Aircraft SEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE Mark the are
piston and
that the
screw so
same
threads will be in contact when the piston and
screw
assembled.
f.
Remove the
O-ring (12)
g.
Remove the
flap
housing.
from the
(5)
actuator screw
from the
piston (6). NOTE
following step should damage or wear.
The
accomplished only if the piston (6)
be
or
piston plug (11)
is to be
replaced
due to h.
Drill out the
out of the
plug (11)
and take the
pin (14)
piston (6).
FLAP ACTUA TOR ASSEMBL Y Clean all parts with solvent (16, Chart 1, 91-00-00) and wear. Refer to Chart 1 for tolerances and wear limits. a.
the
O-ring (12)
and seal
b.
Replace
c.
Coat the plug
d.
Peen the
pin (14) and file it flush
e.
Pack the
bearings (4)
(11)
pin (14)
and
and excessive
(17). primer (20,
with
Chart 1,
91-00-00) before assembly.
piston (6).
with the
lubricating
with
inspect for cracks, corrosion, distortion,
grease
(50,
Chart 1,
91-00-00)
before
inserting
the
piston (6)
in the hous-
ing (8). f.
Pour
lubricating
g.
Slide
a
oil
bearing (4)
(51, on
Chart 1,
the
screw
91-00-00)
into the
piston
until it is about two inches from
being
full.
(5). NOTE
When the
screw
and
piston
are
disassembled. Check the
were
assembled, be and
piston
sure
screw
the
same
assembly
threads
end
are
in contact
play per step
as
when
they
d of FLAP ACTUA-
TOR DISASSEMBLY. h.
Start the
i.
Install the
pressure,
screw
in the
(5)
remaining bearing (4)
or use a
and slide the
and seal
suitable drift and mallet if
(3),
j.
Install the spacers
k.
Tap
i.
Check that the end
the
piston (6)
shaft
piston plug (11)
play
with
(1) a
into the
housing (8)
with
approximately
100 Ibs.
ring (2).
rawhide mallet to seat the parts
between the
housing (8).
Seat these parts in the press is not available.
(17).
a
and snap
piston
piston (6) and housing (8)
against the
snap
ring (2).
is between 0.002-inch and 0.010-inch.
27-50-00Pagell
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE piston (6)-to-screw (5) plus the end play between the housing (8)piston-to-screw end play (determined in step to-piston (6) the total to get the piston-to-housing end play. from d of FLAP ACTUATOR DISASSEMBLY) The total end
play
between the
shall not exceed 0.022-inch. Subtract the
piston-to-housing end play is correct the end play.
If the to
not within
tolerance, the spacers (3) may be removed
or
installed
made up of 3 different spacers (35-251230-2, 35-251230-4 and 35-251230). A maximum of one 35-251230-2, five 35-251230-4 and seven 35-251230 spacers may be used to make up spacers (3).
Spacers (3)
m.
are
Run the actuator in and out several times to
assure
forced out of the vent hole the first time the actuator is n.
proper operation in its full travel. Excess lubricant will be all the way up.
run
Install the actuator with the vent hole up.
CHART1 FLAP ACTUATOR MANUFACTURING TOLERANCES AND WEAR LIMITS
MANUFACTURED AND/OR
ITEM
(Refer to Figure Piston
3 for Item
No.)
ALLOWABLE WEAR LIMITS
ACCEPTABLE DIMENSIONS
(6)
Pivot Bolt Holes
Inside Diameter 0.3432 to 0.3442
(7)
0.3452
Housing (8) Inside Barrel Dimension
Piston
Plug Hole (10)
Piston
Plug (11)
Housing
End Hole
Piston Shaft Piston Collar
Page
(9)
(13)
(15) (16)
27150100
Inside Diameter 0.875 to 0.878
Inside Diameter 0.3120 to 0.3130
0.879 0.3140
Inside Diameter 0.688 to 0.690
0.694
Outside Diameter 0.685 to 0.687
0.684
Outside Diameter
0.861 to 0.864
0.859
P120
Ray~heon Aircraft SEECH BONANUI\ SERIES MAINTENANCE MANUAL
4
I.
FLEXIBLE
2.
SNAP
3.
SPACERS
SHAFT
RING
4.
BEARINGS
5.
ACTUATOR
6.
PISTON
7.
HOUSING
8.
HOUSING
9.
HOUSING
SCREW
PIVOT
BARREL PLUG
PISTON
ii.
PISTON PLUG
12.
O-RING
13.
HOUSING
14.
PIN
15.
PISTON
SHAFT
16.
PISTON
COLLAR
17.
SEAL
HOLES
INSIDE
HOLE
10.
END
BOLT
DIMENSION
(CONNECTS FLAP TO ACTUATOR)
HOLE
17
16 10
I I
15
12
t
14
13 C94EA2782829
Flap Actuator
Figure
A20
3
27-50-00
Feb
26/9 Page
13
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
b.
GCIST LOCK AND DAMPER hole
provided c.
pin
is
provided
for the control column
and the aileron control wheel. The lock
pin
secures
the aileron control wheel and the elevator control. A
is
provided
on
a.
column
the control lock to
cover
placing
pump, and the
both
to
so
positive retention of the lock pin by assembly over the throttle control, boost propeller control.
cover
cover
the throttle control,
Rotate the control wheel to the
align
the the
Ensure the
boost pump, and the propeller control. Install the control lock assembly in the following sequence:
the column forward
pin through guide and into
column lock
in the control column
control column.
CONTROL LOCK A control column lock
Push the control
right
and
move
the hole in the bracket and the
WARNING
Always completely remove the control lock assembly before engine start, taxiing, and
flight.
accept the pin.
"END"
27-70-00
Page 1 May 9180
CHAPTER
FUEL
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 28
FUEL
TABLE OF CONTENTS PAGE
CHAPTER
SUBJECT
28-00-00 General
1
Description And Operation
System Auxiliary Or Fuel
Fuel
Boost Pump E-2104) except E-1946 Auxiliary OrFuel Boost Pump Auxiliary Or Fuel Boost Pump Auxiliary OF Fuel Boost Pump Fuel System Drains General
(CE-748, CE-772
after, D-10097, D-10120
after, E-llll, E-1241 thru E-2110 1
(CJ-149 and after) (EA-~ thru EA-272 except EA-242) (E-1946, E-2104, E-2111 and after, EA-242,
1 1
2
EA-273 and after)
2 2
Maintenance Practices
2
Handling Practices Cleaning Fuel Strainers Airplane Defueling (Priorto EA-273 exceptEA-242) Airplane Defueling (EA-242, EA-273 and after)
Fuel
2 4
5
28-1C-00
Storage
1
Maintenance Practices
1
(Prior To EA-273 Except EA-242) ~Prior To EA-273 Except EA-242) Reservoir Installation (CJ-149 and after) Fuel Cell Removal (40 Gallon) (EA-242, EA-273 and after) Fuel Cell Installation ~40 Gallon) (EA-242, EA-273 and after) Fuel Cell Removal (14 Gallon) Fuel Cell Installation (14 Gallon) Inspection Of Fuel Cell Flapper Valve Fuel Cell Leakage Test Fuel Cell Removal
1
Fuel Cell Installation
2 3
3 4
4
6 6 9
Fuel Cell Preservation
9
Goodyear Uniroyal
9
Repair
9
Goodyear Fuel Cells Uniroyal Fuel Cells
9
Fuel Cell
9
28-20-00 1
Distribution- Maintenance Practices
Auxiliary Auxiliary Auxiliary Auxiliary
Fuel Pump Removal (CE-748, CE-772 and after, CJ-149 and after, D-10097, D-10120 and after) Fuel Pump Installation (CE-748, CE-772 and after, CJ-149 and after, D-10097, D-10120 and after) Fuel Pump Removal (E-llll, E-1241 and after, EA-l and after) Fuel Pump Installation (E-llll, E-1241 and after, EA-1 and after) I
1 1 1
Fuel Selector Valve Removal
2
Fuel Selector Valve Installation
2
Fuel Strainer Removal
2
~Selector Valve)
ZI-CONTENTS
Page 1 A16
Oct 16192
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
TABLE OF CONTENTS
(Cont’d) PACE
CHAPTER
SUBJECT
(Selector Valve) (Wing Fuel Cells) Installation ~Wing Fuel Cells)
Fuel strainer Installation
i
2
Fuel Strainer Removal
4
Fuel Strainer
4
Of Fuel Cell Vent Lines And Fuel
Inspection Flared Fittings
FillerCaps
4
5 28-40-00
indicating
1
Maintenance Practices
Fuel
1
Fuel
1
Quantity Sensors -(80 Gallon System) Quantity Sensors -(108 Gallon System) Fuel Quantity Indicators (80 Gallon System) Fuel Quantity Sensor Removal Fuel quantity Sensor Installation Fuel Quantity Indicator Calibration
1 1
1
2 "END"
28-CONTENTS
Page 2 Oct 16/92
A16
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 28 LIST OF PAGE EFFECnVITY CHAPTER SECTION SUBJECT
28-EFFECTIVITY 28-CONTENTS
28-00-00
DATE
PAGE
1
Oct 16/92
:1
Oct 16/92
2
Oct 16/92
1
Aug 29/85 Aug 29/85 Aug 29/85 Aug 28/87 Aug 28/87
2 3 4
5 28-10-00
1
2A
Aug 28/87 Aug 28/87 Aug 28/87
2
28-20-00
28-40-00
3
Jan 20/82
4
Jan 20/82
5
Jan 20/82
6
Jan 20/82
7
Jan 20/82
8
Jan 20/82
9
Jan 20/82
1
r
Oct 16/92
2
Oct 16/92
3
Oct 16/92
4
Oct 16/92
5
Oct 16/92
1
Aug 28/87 Aug 28/87
2 "END"
28-EFFECTIVITY
Page Ale
1
Oct 16/92
BEECHCRAFT
BONANZA SERIES ~AINTENANCE MANUAL
DESCRIPTION AND OPERATION
GENERAL
AUXILIARY OR FUEL BOOST PUMP
(CJ-149
and
after)
The fuel boost pump system utilizes 2 separate boost pumps (a high pressure and a low pressure pump) mounted in front of
FUEL SYSTEM
(Figure 1)
the forward spar carry-through. The switch which controls these pumps is located on the fuel control panel and is plaThe standard fuel system
CE-748, CE-772 thru CE-883;
on
CJ-149 thru CJ-155; 0-10097, D-10120 thru D-10302; E-ll11, E-1241 thru E-1593; and EA-1 thru EA-32 consists of a 25
carded HIGH BOOST, OFF, and ACROBATIC BOOST. The high boost pump may be used if the engine driven pump fails,
starting the engine during high ambient temperatures or if engine is hot. The switch must be in the acrobatic boost position during acrobatic maneuvers. Both pumps are for intermittent use only. The boost pump pressures should be as if
gallon (22 gallons usable) edge, which provides the airplane with 50 gallons (44 gallons usable) of fuel. The
the
tem
indicated in Chart 1.
leading a total fuel capacity of
fuel cell located in each wing
standard fuel sysCE-884 and after; CJ-166 and after; D-10303 and after; E-1594 and after, and EA-33 thru EA-272 except EA-242 conon
sists of a 40 gallon (37 gallons usable) fuel cell in each wing leading edge which provides the airplane with an 80 gallon (74 gallons usable) fuel capacity. On EA-242 and EA-273 and after, the fuel system consists of a 40 gallon and a 14 gallon cell in each wing. This provides the airplane with 108 gallons (102 gallons usable) of fuel.
Chart 1 Fuel Boost Pump Pressures
High
23.0
Boost
psi.
16.0
at
I
Acrobatic Boost
1
psi.
11.5
psi.
at
gph.
42
No Flow
1 7.0 psi. at 55 gph.
at
No Flow
The cells located
are
on
filled through
each
an
after, each wing contains
uninterrupted
independent flush type filler cap airplanes except CJ-149 and
On all
wing.
a
an
The
by-pass cracking pressure of each
The fuel selector
with
a
baffled fuel cell to deliver
flow of fuel to the
engine.
maximum
pump is 3.0 in, of water
by-pass pressure drop of 0.35 psi.
at 40
gph.
handle, located forward and to the left of the pilot’s seat, is
placarded OFF-LH TANK-RH TANK for fuel management. Float operated sensors located in each wing tank system measure
fuel
A visual
quantity.
attached to the filler neck of the
of the tab indicates 27
gallons
measuring tab in 80 gallon system.
AUXILIARY OR FUEL BOOST PUMP
(EA-1
thru EA-272
Except EA-242)
each cell is The bottom
NOTE
of usable fuel in each tank and
the detent on the tab indicates 32 gallons of usable fuel in each
On
tank.
airplanes equipped with
kit
no.
36-9008-16 the
EMERGENCY FUEL PUMP switch is removed
after, a sight gage is installed 113.172) to aid in taking on a partial wing (inboard load of fuel. This gage will indicate a partial load of 25, 30, or 35 gallons in its respective wing. When the gage is indicating in At EA-242 and EA-273 and of
station
the black zone, do not
use
and after; D-10097, 0-10120 and after; E-llll, E-1241 thru E-2110 except E-1946 and E-2104) The
single speed auxiliary fuel pump is mounted in front of the forward spar carry´•through on the left side of the airplane. The auxiliary fuel pump provides pressure for starting and emergency operation in case the engine-driven pump fails. Immediately after starting, the auxiliary fuel pump can be used to purge the system of vapor caused by an extremely high ambient temperature or a start with the engine hot. The auxiliary
OFF:
board is removed and the manifold pressure switch in the manifold pressure gage line has the
unplugged
and the
exposed
terminals covered with electrical tape. The vent plumbing outboard of the fuel cell has not been
(CE-748, CE-772
fuel pump is controlled by a switch located panel and placarded AUX FUEL PUMP
placard covered with black paint. The relay under the pilots floor-
boost fuel boost
electrical connector
the gage,
AUXILIARY OR FUEL BOOST PUMP
I
and the
high
on
the fuel control
OPERATION, ON
changed but the fuel supply system is essentially that of a B36TC (EA-242, EA-273 and after). The fuel selector valve drain requires the use of the same type tool (see special toolsj as the B36TC. Refer to the B36TC (EA-242, EA-273 and af ter) for the description and operation. NOTE The
auxiliary
Fuel
Pump
Switch is
placarded
OFF-LOW-AUTO on Serials EA-1 thru EA-53. The
auxiliary Fuel Pump Switch on Serials
EA-54 and
after, and airplanes prior to EA-54 complying with
28-00-00 All
Page 1 Aug 29/85
8EECHCRAFT
BONANZA SERIES
MAIMENAMCE MANUAL
BEECHCRAFT Service Instructions No. 1093 is
placarded
OFF-LOW-HIILOW.
check for contaminants in the fuel; the other drain with its Adapter, P/N 1078, is for draining the fuel system. Each fuel cell drain is located
on
the lower surface of the
forward spar carry-through on the left side of the airplane. The pump is controlled by three switches located in the cabin. One
the main spar, just outboard of the root. The system low spot drain at the bottom of the fuel selector valve is accessible through a door inboard of the left wing
of the switches is located
root.
The two
speed auxiliary fuel pump is located
on
the fuel control
in front of the
panel and pla-
wing, forward of
carded AUX FUEL PUMP OFF, LOW, AUTO or HIILOW. In the AUTO or HIILOW position the pump is operating at all times. At low power power
settings it operates at low boost, and at higher settings (27 to 30 in. Hg manifold pressure) it operates
MAINTENANCE PRACTICES
GENERAL
boost. The mode at which the boost pump operates in the AUTO or HIILOW position is determined by a switch actu-
FUEL HANDLING PRACTICES
ated by manifold pressure. Another switch is located in the subpanel just to the left of the fuel control panel and placarded
When
at
high
EMERGENCY FUEL PUMP OFF ON. This switch will override high pressure side of the
the other switches and actuate the
pump for emergency operation, such as with a failed engine driven fuel pump. The third switch´• is located forward of the instrument panel and plumbed into the manifold pressure gage line. This switch is actuated by manifold pressure, and closes between 29 to 30 in. Hg on increasing pressure (to
high pressure side of the pump), and opens beHg on decreasing pressure (to return the pump to low pressure operation). This switch actuates the high pressure side of the pump, but only functions if the switch on the fuel control panel is in the AUTO or HI/LOW position. actuate the
filling following:
airplane
the
and after;
Do not fill fuel cells
c.
within 100
Care should be exercised while
case
or a
or
NOTE
cell to prevent scratching, damaging the surface or
wings. Do
filling the fuel denting, or otherwise leading edge of the
not allow the fuel nozzle to come in
contact with the rubber fuel cell.
the engine-driven pump fails. Immedi-
ately after starting, the auxiliary fuel pump can be used to purge the system of vapor caused by an extremely high ambitemperature
open flame
EA-242, EA-273
speed auxiliary fuel pump is mounted in front of the forward spar carry-through on the left side of the airplane. The auxiliary fuel pump provides pressure for starting and emer-
ant
near
producing sparks.
The two
gency operation in
observe the
feet of any open energized electrical equipment capable of
AUXILIARY OR FUEL BOOST PUMP 8-2111
always
Service the airplane fuel tanks with Grade 100LL a. (Blue) aviation gasoline, or Grade 100/130 (Green) aviation gasoline (1, Chart 1, 91-00-00). If these fuels are not available, Grade 116/145 (Purple) aviation gasoline (1, Chart 1, 91-00-00) may be used. b. Be certain the airplane is statically grounded to the servicing unit.
tween 27 to 30 in.
(E-1946, 8-2104, and after)
fuel tanks,
CLEANING FUEL STRAINERS
start with the
engine hot. The auxiliary switch located on the subpanel
fuel pump is controlled by a and placarded AUX FUEL PUMP HI LO OFFI
Most fuel injection system malfunctions can be attributed to contaminated fuel. Inspecting and cleaning the fuel strainers should be considered to be of the utmost
regular part
of
preventive
importance
as a
maintenance.
FUEL SYSTEM DRAINS
Normally the fuel strainers should The fuel system prior to EA-273, except EA-242, is equipped with one snap-type drain in each wing. At serial EA-242 and EA-273 and after, there are two drains in each
wing. One drain with its tool is
to be used in a
prefllght
every
100
inspected
hours.
be
Inspected and cleaned
However, the strainers should be
and cleaned at more
frequent
intervals
depending
service conditions, fuel handling equipment and when operating in localities where there is an excessive amount of
on
28-00-00
Page 2 Aug 29/85
Atl
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
THIS LINE IS REPLACED BY A FUEL TRANSDUCER ON SERIALS AFTER CE´•928. CJ-(55. 0-(0353 ANO E-(765 FUEL
MANIFOLD
,~FUEL
V I
FUEL
I-
FILTER DRAIN
E-13~3
AND AFTER EOUIPPED Wllil
I
I\IITOMATIC POWER CONTROL
TAANSDUCER METERING
CONTROL UNIT
SUPPLY RETURN
FUEL
I
VENT
I
)FLOW
I
GAGE
I
I
DRAIN
IINJECTION PUMP
I
FUELTRANSMITTER FWD
FILLER
~t)
SEAL
t
DRAIN
TRANSMITTER USED WHEN OPTIONAL FUEL CELLS
,B CHECKVALVE
ARE INSTALLED
AT SERIALS E´•1946. E´•2104. ANO E´•2111 AND AFTER A DUAL PRESSURE AUXILIARY
PUMP IS INSTALLED S+CJ SERIALS ARE EQUIPPED WITH AN
ADDISIONAL BOOST PUMP PLUMBED IN SERIES WITH THIS PUMP
’1
´•i
b--i~
c,
1
AUx.
i c
PUMP
4
---------I
KB
ii
LH
[L
FUEL T*NK
VALVE
I
137 GPIL. USABLEI OPT
I
ISTRAINER
01111
DA*IN
VLNI
A n, rUEI
~sEIEcron
2SGAL.(220PIL.VSABLEI 40 GAL
1;
T~NK
25GAL.IZZGP~L.VSAALEI 40 GAL. (37 GAL
USAB L E I OPT
I IODR*IN
7DR~INI
STRAINER
IC I....’.".(XI´•´•´•´•
STRAINER
VALVE
SEAL
i FLUSH VENT
YENI
CHECK
5
DRAIN
VENT
VENT
FLUSH VENT
I6,al not
end after; CJ-149 and after; 0-10097, D-10120 and after; E-llll, E-1241 and after)
(00-748, 00-772
RETURN
FUEL MANIFOLD
VENT
CONTROL
DRAIN
UNIT
FUEL TRANSMITTER FILLER
II
TRANSMITTER USED WHEN OPTIONAL FUEL CELLS ARE INSTALLED
SEAL
I
´•SC´•lllll AUX.
I
RELIEF VALVE c´•
I
L.H. FUEL TANK 25 GAL. (22 GAL. USABLE) 40 GAL. (37 GAL. USABLE) OPT
FUEL
FLOW GAGE
I
t
PRESSURE RELIEF VALVE
I
511´•1;ii FND
1
iCHECK
PVMP
INJECTION PUMP CHECK VALVE
i
I DRAIN O
Ae
VENT1
IVALVE
1
L
t
DRAIN
PRESSURE
I--e
I
´•s
SELECTORVALVE (STRAINER
i
&DRAIN)
P,D_R,A!~,_,
:lr
B
I
B
I
VENT
I
(I
CHECK VALVE
R.H. FUEL TANK
i ILSEAL i "DRAIN
(22 GAL. USABLE) (37 GAL. USABLE) OPT
25 GAL.
i
40 GAL.
VENT
VENT
A36TC´•281-32
(EA-1
thru 0A-272
Except EA442)
System Figure 1
Fuel
28-00-00
All
Page 3 Aug 29/85
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
FUEL FLOW TRANSDUCER ENGINE FUEL DISTRIBUTOR VALVE FNC~INF THROTTIE RODY
ENGINE DRIVEN FUFI. SUPPLY LINE 7
FUEL OUANTITY
PUMP
SIGHT GAGE I
I
BOTTOM MOUNTED FUEL QUANTITY TRANSMITTER
/-FUEL RETURNLINE FIREWALL
STA FUELCAPX ANTI´•SIPHON ASSY
SYSTEM OUICK DRAIN IFOR M~INTENANCE
STA
1?1
I
i
STA
I
Y
23
1
t
DUAL PRESSURE ELECTRIC
I
I
I/
ROOST PUMP
ONLYI FUEL SELECTOR VALVE. STRAINER R DRAIN VALVE ng GALLON
14 GALLON CELL
CELL
VENT LINE
SHUTOFF VALVE
O
.r
FROM RH
WING
\-t~ FUEL RETURN TO AH WING
VENT’ PRESSURE
FUEL RETURN TO LH WING
RELIEF VALVE
INTERCONNECT R ANTI-SUAGEVALVE
FLUSHALTERNATE FLAME n ARRESTOR
EXTEkNAL
I
VENT
VACUUM RELIEF VALVE
TOP MOUNTED FUEL QUANTITY TRANSMITTERS
MAIN VENT
Fuel System
tor
or
dust.
It
is
recommended
that
the
strainer, located in the fuel selecvalve, be inspected and cleaned at
intervals of 50 hours of operation and under no condition should the period be extended 100 The hours. over finger strainers in the fuel cell outlets should be removed and cleaned whenever solid materials are found in the cells, or if the airplane has been in storage for an extended period of time. CAUT I ON
The strainer of the non-baffled cell and reservoir with the baffled cell are not interchangeable: Ensure that the correct fuel the stra~ners are reinstalled in proper cells after cleaning and
inspection.
SUMP STRAINER R FUEL CELL OUTLET CHECK VALVE
FUEL CELL ANTI-SLOSH BAFFLE B36TC-603-40
(EA-242, EA-273 and after)
Figure sand fuel
’FLUSH FUEL DRAIN VALVE
2 AIRPLANE DEFUELING
(PRIOR
TO EA-273 EXCEPT
EA-242) WARNING Do not defuel near an open within 100 feet of any or gized electrical equipment ble of producing sparks.
flame ener-
capa-
To ensure tha’t all fuel is removed from the system and to expedite the defueling the should be draineEI fuel operation through ’~he boost pump. The following steps must be accomplished before energizing the pump: a.
plane
Apply external power electrical system.
to
b. Place the fuel selector the ON position and the mixture IDLE CUT-OFF.
the
air-
valve lever
in in
28-00-00 Page 4
Aug 28/87
A12
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
Remove the filler caps to vent the
c.
gized ble of
system. d. Disconnect the fuel line at the firewall and attach a drain hose. Provide suitable container for the fuel. a
Energize the
e.
electrical
equipment producing sparks.
Provide a. the fuel.
a
suitable
capa-
container
for
b. Remove the access cover under the drain valve located under the wing near the fuselage.
boost pump,
f. When the fuel is no longer pumped from the airplane, open the sump drains to complete the defueling operation.
Remove the filler caps to vent the
c.
system. d.
CAUTION
plied
as
Insert loose
the
tool)
drain adapter (supinto the drain valve.
After
defueling or replacement, operate
fuel cell the engine each fuel tank with the airon plane on the ground to ensure that all air has been purged from the fuel cells and the fuel lines to the engine upon refueling.
After draining the fuel, e. the drain adapter and install the
remove access
cover.
CAUTION
After
AIRPLANE
DEFUELING
(EA-242,
EA-273
AND
AFTER) WA.RNING Do or
not defuel within 100
near
an
feet
of
open any
flame
fuel cell the engine each fuel tank with the airon plane on the ground to ensure that all air has been purged from the fuel cells and the fuel lines to the engine upon refueling. or defueling replacement, operate
ener-
"END"
28-00-00 A12
Page 5 Aug 28/87
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
STORAGE
incorporate a fuel cell with collapsible fuel cell reservoir in place of a baffled fuel cell. To avoid damage to the fuel cells,
MAINTENANCE PRACTICES
after
a
CAUTION
proper assured.
installing
Return the a. outboard fuel cell it into place.
Pilot’ s the to Manual before starting and operating the engine,
(PRIOR
b.
the closing zipper, inspect the fuel cell for any foreign material. If the cell is not thoroughly clean, it should
Remove
Remove
c.
fuel d.
the
a lint-free cloth alcohol or water, kerosene. No other solvent should be used to clean the fuel cell.
cells.
the outboard fuel cell and fuel quantity sensor, (The outboard fuel quantity sensor is installed only in the optional 80 gallon fuel system).
and
be cleaned with moi stened
plate
access
inboard
quantity
sensor.
Disconnect
all
access
fuel
cover
and
vent
i.
e. Unsnap the fuel cell and through the outboard fuel cell
remove
the
edge of the access damage to the
prevent
hole fuel
cell. FUEL
I NS TALLATI ON CELL EXCEPT EA-242)
into the the tube
Locate the hose clamp on the 2. fabric-reinforced area of the nipple; it should clear the end of the fitting by 1/4 inch.
CAUTION
to
Insert the flow tube
fitting until 3/8 inch or more of extends through the fitting.
access
hole.
Tape
in
the The molded nipple fittings used on fuel cell are lightweight fittings developed for ease of installation in certain locations in the airplane. To get the best it is service from this type fitting, exercise to certain procedures necessary at the time of installation. The specific precautions other than the general care in handling are as follows:
plumbing. it
cell through the hole and snap
access
Before
EA-273
TO
Drain and purge the fuel
a.
fuel
CAUTION
Operating
FUEL CELL REMOVAL EXCEPT EA-242)
a
is
operation
eng~ne Refer
MUST be before replacement cell.
the fuel cell cavities of clean debris any
the fuel is ti me system drained or a fuel cell replaced, air may enter the system. If the possibility that air has entered the system does exist, start and operate the engine on the ground until all air is removed from the for system. Operate the engine several minutes on each tank until
Any
(PRIOR
EA-273
TO
3. Torque hose clamps as indicated in Chart 1 in this chapter. They should be drawn up in one operation; if the is ret i ghten i ng n ece s sa ry re 1 ea s e 15 and least wait at clamp completely minutes before retightening.
CAUTION
4. Care
should be taken when replacing fuel cells to ensure that the correct type fuel cell is used as a replacement. All Bonanza Series Airplanes except CJ-149 and after use baffled fuel cells. CJ-149 and
Use
no
sealing paste
or
gasket
compounds. 5. Apply a thin film of Simonize metal flow tubes as a lubricant. No other lubricant should be used.
wax
to
28-10-00 Page 1 A12
Aug 28/87
BEECHCRAF-T BONANZA SERIES MAINTENANCE MANUAL
the connector Insert d. assembly into the reservoir while tilting both the reservoir and connector assembly upward.
Chart 1 Fuel Cell
Nipple Cramp Torques of
Inside diameter
Inch-pounds
tin inches) nipple.
torque for fuel
of
CAUTION
nipple clamps. should be exercised to avoid the connector threading Also avoid the reservoir, into bending or di storti ng the fuel strainer which is attached to the end of the connector, for it may foam the in become e nta ngl ed inside the reservoir. Care
Outside diameter
tin inches)
cross
of tube.
.25 thru .62 .75 and 1.00 1.00 1.50 3.00
12 15 25 30 35
16 20 to 30 to 35
to to
to
40
Tighten the nipple clamp.
e.
nector
If fuel Goodyear replacement cells have clear/yellow nipples, torque the fuel cell nipple clamps to 25 +5 inch-pounds. RESERVOIR INSTALLATION
(CJ-149
Install the reservoir after the fuel cell is in the wing and before the access plate is installed. Installation may be accompi i shed as fol lows:
Tape the reservoir flapper valve installing the reservoir.
shut before b.
Compress into
pass it the fuel
through
c.
to
a
the reservoir (squeeze small circumference and the fuel access ring into
cell, Release the reservoir its original shape,
assume
h.
AND is the
by hand)
con-
assembly.
Remove the tape from the flapeer g. valve and check the valve for free play and good sealing.
AFTER) (Fieure 1)
a.
line to the
Connect the fuel
f.
CAUTION
allowing
it
Check to make
positioned properly fuel i.
sure on
the the
reservoir bottom of
cell.
Close all access openings used for reservoir.
installing the
CAUTION
The parts of the non-baffled fuel cells and the baffled fuel cells not to be interchanged. When are installing a new fuel cell, use only those items pertaining to cell that being particular installed. The strainer for the non-baffled cell with reservoir, is for considerably example, longer that the one for baffled if cell and may damage the cell installed in the baffled cell.
28-10-00 Page 2
Aug 28/87
A12
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
FUEL RETAINING MODULE WITH SPECIAL
SPONGE CORE
FLAPPER ::::::i´•::´•::
.::.´•::´•:i-:i-::´•_VALVE
TOIJ FUEL EXISTING FUEL CELL
LINE
FUEL CELL
NIPPLE
CLAM P 36-281-33
Non-Collapsible Fuel Cell Reservoir (CJ-149 Figure 1
and
after)
28-10-00 Page 2A A12
Aug 28/87
BEECHCRAFT BONAN;LA SERIES MAINTENANCE MANUAL
FUEL CELL REMOVAL 213 and after) a.
b.
quantity
Remove
the inboard
access
cover
and fuel
Remove the
e.
Remove the
Before any
closing the zipper inspect the fuel cell for foreign material. If the cell is not thoroughly
clean, it should be cleaned with a lint-free cloth moistened in water, alcohol or kerosene. No other solvent should be used to clean the fuel
sensor.
d.
sump in f.
CAUTION
Drain and purge the fuel cells. Remove the outboard fuel cell access cover, fuel sensor, and fuel sight gage and mounting plate,
c.
quantity
(40 GALLON) (EA-24~ E4-
under the fuel sump, wire and bolts holding the
access cover
safety
cell.
place.
Lower the sump assembly and disconnect the hose from the fuel outlet. Remove the sump and hose
Close zipper in fuel cell dam.
b.
assembly. g. h.
Remove the
clamp from
the drain valve
nipple. CAUTION
Remove the drain valve. Remove the
pilot’s and copilot’s
seats as outlined
in PILOT AND COPILOT SEAT REMOVAL
(Chapter 25-10-
k.
Remove the royalite cover over the main spar. Disconnect the fuel line from the fuel cell fitting.
I.
Remove the two bolts
i.
wing
The
access cover
and fuel quantity
have to be removed from the 14
00).
holding
the fuel cell to the
root db.
Remove the cotter pin from the flapper valve and m; interconnect tube at the outboard end of the fuel cell. n.
remove o.
Loosen the bolt to the napper valve clamp, and flapper valve, Remove the clamps from the two interconnect
the
sensor
gallon fuel
may cell
the small interconnect nipple may be held inplace during installation of the 40 gallon cell. A light film of petrolatum tech (VV-P-236) 142, Chart 1, 91-00-00) may be used as a lubricant on the nipples and under the clamps.
so
Install the fuel cell
c.
tubes.
Torque
the
nipples on the interconnect nipple clamps per Chart 1 in this chapter.
tubes.
Unsnap the fuel cell and p. outboard fuel cell access hole.
remove
it
through the CAUTION
CAUTION
nipple fittings used on the fuel ceil lightweight fittings developed for ease of installation in certain locations in the airplane. To gel the best service from this type fitting, it is necessary to exercise certain procedures at the time of installation. The specific precautions other than the general care in handling are as The molded are
Tape the edge of the access hole damage to the fuel cell.
to
pevent
FUEL CELL INSTALLATION (40 GALLON) (EA-242, EA-2M and afterl
follows: 1. Insert the flow tube into the
CAUTION
inch
or
more
fitting until through
of the tube extends
318 the
fitting. Care should be taken when replacing fuel cells to ensure that the correct type fuel cell is used as a
replacement, to avoid damage
to the fuel
cells, the fuel cell cavities MUST be clean of any debris before
a.
access
installing
Install the fuel cell hole and snap it into
a
replacement cell.
through place.
the outboard fuel cell
2. Locate the
hose
clamp
on
the fabric-
of the nipple; it should clear the end of the fitting by 1/4 inch. 3. Torque hose clamps as indicated in Chart 1 reinforced
area
in this chapter. The hose clamps should be tightened in one operation; if retightening is necessary, release the clamp completely and wait at least 15 minutes before retightening. 4. Use no sealing paste or gasket compounds.
28-1090
Page A4
3
Jan 20182
BEECHCRAFT BONANtA SERIES MAINTENANCE MANUAL
Install the flapper valve.
d.
1.
Install the cotter
pin through the interconnect
flapper valve clamp, 2. Tighten the flapper
tube and
the interconnect
nipples from the tubes. Unsnap the fuel cell and remove it through the
h.
remove the
outboard fuel cell valve
nipple clamps from
Remove the
g.
tubes, and
access
hole.
clamp. CAUTION
CAU~ION Use
new
Tape the edge of the access hole damage to the fuel cell.
gaskets.
to
prevent
NOTE
FUEL CELL INSTALLA~ION On
Uniroyal cells
remove two screws to
installation of the bolts which to the
wing
secure
(14 Gallon)
allow
the fuel cell
CAUTION
root rib.
Care should be taken to avoid damage to the Install the two bolts which
e.
the
root rib.
wing f.
Torque
secure
fuel cells, the fuel cell cavities MUST be clean of any debris before installing a replacement
the fuel cell to
to 20 to 30 in.-lbs. and lockwire.
Instail the drain valve in the fuel cell
cell.
nipple (make
certain the hat section support is in place). Install the nipple clamp. Torque per Chart 1 in this g. Section.
Connectthe sump assembly hose to the fuel outlet. Torque per Chart 2 (91-00-00). h.
i.
Ibs. and
Return the fuel cell through the outboard fuel cell
a.
1
access
hole and snap it into
Install the sump. Torque the bolts to 45 to 55 in.safety wire the bolts and drain valve assembly.
Install the fuel quantity transmitters (2 in the 40 j. gallon fuel cell and 1 in the 14 gallon cell if removed), Torque the transmitters to 20 to 30 inch-pounds and the transmitter mounting plate to 45 to 55 in.-lbs. k.
Connect the electrical wire to the transmitter,
i.
Install the fuel cell
cover
plates
and fuel
CAUTIOIV i
If the cell is not
i
cleaned with alcohol
or
thoroughly clean,
it should be
lint-free cloth moistened in water, kerosene. No other solvent should be a
used to clean the fuel cell.
sight
gage mounting plate. Torque to 45 to 55 in.-lbs. Install the access covers. m. and
nipples on the interconnect tubes, nipple clamps per Chart 1 in this chapter.
Install the cell
b.
Connect the fuel line to the fuel outlet. Torque per
n.
place.
tighten
the
Chart 2 (91-00-00). Install the o.
j
royalite cover over the main spar. Install the pilot’s and copilot’s seats as outlined in p. PILOT AND COPILOT SEAT INSTALLAT\ONl;in Chapter 25-10-00.
CAUTION i
nipple fittings used on the fuel cell lightweight fittings developed for ease of installation in certain locations in the airplane. To get the best service from this type fitting, it is necessary to exercise certain procedures at the time of installation. The specific precautions other than the general care in handling are as The molded are
FUEL CELL REMOVAL (14 Gal/on) a..
b. c.
d.
Drain and purge the fuel cells. Remove the access cover under the
wing tip,
Disconnect the vent plumbing from the fuel cell. Remove the filler cap, adapter assembly, and
1. Insert the interconnect tube into the
anti-siphon assembly. e.
Remove the two
access
covers
under the 14
Remove the two
until 3/8
through
gallon fuel cell, f.
follows:
cover
assemblies from the fuel
the
2. Locate
reinforced
cell.
inch
or
more
fitting
of the tube extends
fitting. the
hose
area
of the
clamp on the fabricnipple; it should clear the
28-10-00
Page
4
Jan 20/82
44
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
fitting by 1/4 inch. Torque hose clamps as indicated in Chart 1 in this chapter. This should be drawn up in one operation; if retightening is necessary, release the clamp completely and wait at least 15 minutes before retightening. 4. Use no sealing paste or gasket compounds, 5. A light film of petrolatum tech (VV-P-235) end of the
NOTE
3.
(42, Chart 1, 91-00-00) may be used lubricant under the clamps and nipples.
as
Use all d.
Install the
to 45 to 55 e.
in.:lbs.
Install the
new
gaskets.
anti-siphon assembly. Torque the
bolts
and lodtwire.
adapter assembly. adapter.
Use Permatex No. 2
between the skin and
f.
Install the fuel cap. Install the two cover assemblies, the one with the g. fuel quantity transmitter is the inboard one. Torque to 45 to
a
55 in.-lbs. and lockwire. c.
the
Connect the vent
clamps per Chart 1
plumbing in the wing tip. Torque in this chapter.
i
h.
Connect the electrical wire to the transmitter.
i.
Install the three
access covers.
28-10-a0
Page A4
5
Jan 20/82
BEECHCRAFT
BONANLA SERIES MAIHTENANCE MANUAL
/NSPECT/ON OF FUEL CELL FLAPPER VALVE
full travel. There should be no binding and the element should seat securely against the valve plate. 2. If the flapper element binds and/or does not
On airplanes that are equipped with baffled fuel cells, the flapper valves (metal or phenolic) should be inspected
properly, the upper rear side of the flapper element binding against the valve plate. 3. The flapper valve element may be relieved from binding by filing a small radius on the upper rear side seat
may be
periodically (Beech Aircraft recommends that the inspection be accomplished at each 100 hr. inspection) for freedom of operation and proper seating.
of the element. The
inspection may
be
accomplished
a.
Drain all fuel from the
b.
Remove the
as
follows:
airplane. rectangular access plate located just outboard of the fuselage on the upper skin of each wing leading edge. Cut the safety wire and remove the attaching bolts c. from the fuel cell access plate.
NOTE
area
around the
shop towel saturated with light oil may be placed directly below the flapper valve to absorb the phenolic dust during rework.
1
4. After determining that the flapper valve is functioning properly, thoroughly wipe the area in the vicinity of the flapper valve with an oil saturated shop towel.
NOTE Cleanthe
A
i
access
plate before h.
removing the plate.
fuel cell i.
Remove the fuel cell
d.
access
plate
in the baffle.
zipper
Locate the
e.
access
flapper
k.
valve in the lower outboard
section of the baffle and determine if the metal
i.
and open the
flapper
phenolic. If the flapper valve is metal, it should and repaired, if necessary, as follows:
to
valve is
1.
Move the
no
binding
in
plate
place.
Tighten
the fuel cell
access plate attaching bolts inch-pounds and safety wire. rectangular access plate on the wing
to 50
Reinstall the skin.
FUEL CELL LEAKAGE TEET
(Figure 2)
and the
element should seat securely against the valve plate. 2. If the flapper element binds and/or does not seat properly, the flapper element arm could be bent. The
the fuel cell and
Close the zipper in the baffle. Install a new gasket and secure the fuel cell
leading edge
inspected
element of the valve
flapper
its full travel. Them should be
through
be
area on
plate.
torque of 45 i.
or
f.
a
Clean the gasket contact access
i
Rubber bladder type fuel cells may be bench tested for
the closed position. 3. If after straightening the am~, the flapper element still binds and/or does not seat properly, the flapper
i f
leakage by sealing off all openings and inflating the empty cell to 1/4 psi with a mixture of shop air and ammonia gas, then checking for visible indications of leakage on a cloth saturated with phenolphthalein solution. To set up and conduct the leakage test, proceed as follows:
replaced with a new flapper element assembly assembly. flapper may be replaced by removing the two attaching bolts from the upper part of the flapper valve. The same attaching parts should be used to install the new flapper element assembly. The new flapper element assembly should be inspected after installation to determine that the assembly did not receive damage during installation that could cause it to bind and/or not seat properly.
j
straightened by placing
arm can
be
the
and the element and
arm
element should be
If the
inspected
screwdriver between
removed and The
element
g.
a
pressing the element toward
fapper
valve
is
phenolic,
it
should be
Move the
flapper
valve element
through
The
following equipment as
its
is
required
indicated in the schematic in
and should
Figure
2.
1. Closure plates for the fuel cell openings. Such plates may be fabricated of aluminum sheet cut to a size sufficient to cover the cell openings. Drill holes in the
closure
plate
to match the hole
pattern around the opening
in the fuel cell. 2.
Rubber stoppers to
plug the fitting openings
in the fuel cell. One of the stoppers should have a hole for insertion of the plastic tubing used to connect the fuel cell into the test setup. 3. A manometer for
and reworked, if necessary,-as follows: 1.
a.
be hooked up
measuring
6
inches of
water differential. The manometer can be fabricated from
2810´•00
page
8
Jan 20/82
A4
BEECHCRAFT BONANZA SERIES MAIMENANOE MANUAL
EMPTY FUEL CELL
(ALL OPENINGS PLUGGED)
OPTIONAL OVERFLOW COLLECTOR
AMMONIA GAS
PLASTIC
STD. RULER
I I
(NH3)
TU~ING
SHOP AIR
OR
YARDSTICK
LEAK PROOF
Irtm
STOPPERS
MOISTURE
COLLECTOR REGULATOR
s´• GLASS
SET TO 1/4 PSI
i
TUBES
AMMONIUM HYDROXIDE
GLASS FLASK
(NH4OH)
OR
SOLUTION
BOTTLE
MANOMETER 6" of WATER
(/4 PSI 33-281-30
glass
or
Test
Leakage Figure 2
Setup
for
4.
A
regulator
that
can
be set to
provide
1/4
psi
The Pressure Test Baffle Restrainer
9.
clear plastic tubing; frame and scale similar to the
illustration shown.
(6 inches of water) from a supply of shop air, 5. Two flasks (or bottles) approximately one liter (or quart) in capacity. A third container may be hooked
fuel cell.
into the test setup to provide an optional overflow collector if desired, The two containers should be provided with rubber
work bench.
b.
Place the fuel cell and test
or
metal)
as
shown in the schematic in
Figure
over
Plastic
the tubes and of
on a
clean
2.
tubing of a size to provide a leak-free a length sufficient to interconnect the test components as shown in figure 2. 7. Make up a solution of phenolphthalein as follows: Add 1/3 ounce phenolphthalein crystals to 112 gallon ethyl alcohol, mix, then add 1/2 gallon water. 6, Make up an ammonia solution by adding 100 cc (3 fluid ounces) of concentrated ammonium hydroxide (NHqOH) per gallon of water, 6.
fit
equipment
CAUTION
stoppers that have holes for the insertion of 1/4-inch tubes
(glass
(Figure
3) is made of 314 inch thick plywood. Sand all edges to remove sharp corners and/or splinters that may damage the
Make
sure
shavings
or
the work
area
is clean of metal
other debris that could
damage
the
fuel cell.
Install the closure plates over the fuel cell c. openings and torque the retaining screws as specified in this chapter of this manual.for the openings, then insert the rubber stoppers into the open fittings.
28-10-00
Page A4
7
Jan 20/82
BEECHCRAFT BOEIANZA SERIES MAINTENANCE MANUAL
8.0"
20.0"
6.00(NP)
TYP-1----15.,.27.0" 6.0"
LOCATE BAFFLE RESTRAINER OVER VELCRO TAPE AREA PRIOR TO INFLATING TO MAXIMUM 1/4 PSI.
INBD
\N
IV~
Pressure Test Baffle Restrainer
Figure
AFT
36-281-34
3
28-10-88
Fags
8
Jan 20/82
A4
BEECHCAAFT BONANZA SERIES MAINTENANCE MANUAL
d.
hydroxide
NOTE
The flask (or bottle) containing the ammonium solution should be 1/3 to 1/2 full as shown in the
Refer to BEECHCRAFT Service Instruction No.
illustration.
Connect
e.
supply
air
shop
a
to the
regulator
and
0632-280, Rev. I
or subsequent and Goodyear Aerospace Corporation Fuel Tank Repair
interconnect the regulator, beakers, fuel cell, and manometer as indicated in Figure 2. Place the baffle restrainer prior to inflation as indicated in
f. area
over
Manual AP368 for further information
Figure
3.
FUEL CELL PRESERVA 7/ON
WARNING
GOOOYEAR
inflation of the fuel cell without the baffle restrainer
result in
can
on
inspection of fuel cells for leakage.
the velcro tape
irrepairable damage
to
Goodyear fuel cells (Construction No. BTC-39, BTC-54A ETC-67) installed in the airplane do not require
the baffle.
and
preservation when the cell is to be empty for an indefinite period of time. The fuel cell should not be open to the atmosphere except for the normal vent lines in the airplane. The cell is assumed wet from a previous filling.
Inflate the fuel cell to 114 psi with a mixture of g. shop air and ammonium gas. A d-inch difference in the two water levels of the manometer will indicate that the fuel cell psi. It is not necessary to restrain the cell
is inflated to 1/4
other than to keep it from
rolling off
the bench. The
the ceil will be rather slow at the 1/4 rushed
psi,
filling
of UNI#OYAL
but should not be
overpressure of the cell could result. Saturat~i a large, clean cloth with phenolphthalein.
as
h.
(Immerse
it in
a
container and squeeze out excess
Uniroyal
fuel cells must be filled every 10 days or the wails a thin coat of light engineoil if they are to be
coated with
liquid.)
preserved for periods of up to one year. Liniroyal fuel cells are to be stored for periods of one year or longer should be coated with a thin coat of light engine oil and then removed from the airplane as outlined under FUEL CELL REMOVAL in this chapter. After the fuel cell is removed from the airplane, it should be wrapped in plaljtic, placed in a box, and stored in a cool dry area.
that
CAUTION
gloves to protect against skin handling the cloth. As a further possible penetration of the against protection phenolphthalein solution through the gloves, wash your hands thoroughly after finishing the Wear
rubber
irritation when
NOTE
test.
The fuel cell should not be removed
Lay
i.
the cloth
over
the various
portions of the fuel
or
until 24 hours after the oil has been
handled
applied.
cell until the entire exterior of the cell has been covered. With each
application
a
reddish
a
leak. Encircle the
with
a
pink
stain
of the cloth, watch for the formation of the cloth to indicate the presence of
area on
chalk mark to
the fuel cell beneath such stains
pinpoint
the locations of leaks.
use
of the testing cloth will require
repeated saturations rapid evaporation of
progressively
with
phenolphthalein
since
UNIROYAL FUEL CELLS
the alcohol from the cloth
reduces the sensitivity of the test
unless the solution in the cloth is renewed.
GOODYEAR FUEL CELLS For repairs of Goodyear fuel cells, refer to Goodyear Fuel Cell Repair Manual AP368, Vithane Fuel Cells.
NOTE
Continued
FUEL CELL ~EPAIR
on
frequently
For repairs of Uniroyal fuel cells, refer to Uniroyal Handbook "Recommended Handling and Storage Procedures for Bladder Type and Oil Cells" PIN FC 1473-73.
"END" 2&1 040
Page A9
9
Jan 20/82
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
DISTRIBUTION- MAINTENANCE PRACTICES
Secure
c.
mounting
fuel
the
selector
valve
to
the
to the
fuel
bracket with the four attach bolts.
CAUTION d.
AUXILIARY FUEL PUMP REMOVAL CE-772 AND AFTER, CJ-149 AND D-10097, D-10120 AND AFTER) Drain and purge the fuel system.
b.
Remove the
lined
PILOT
in
pilot
and
copilot
COPILOT
AND
f.
royalite
as
unscrew
Remove the
the
postlight
fuel
covers
the
g.
Replace the royalite
h.
Reinstall
cover over
the main
TION
the
pilot
and
copilot
seats
as
PILOT AND COPILOT SEAT INSTALLA-
(25-10-00).
out-
the main
Drain and purge the fuel system.
a.
lined
Remove the
PILOT
in
AND
pilot
and
copilot
COPILOT
seats
SEAT
as
out-
REMOVAL
(25-10-00).
spar. d.
truss cover.
covers.
outlined in
REMOVAL
cover over
royalite
spar.
b. Remove the
the
Replace the fuel selector handle and
post light
(25-10-00). c.
plumbing
AUXILIARY FUEL PUMP REMOVAL (E-Illl, E-1241 AND AFTER, EA-1 AND AFTER)
seats
SEAT
Replace
e.
’CnE-748,FT~R,
a.
Reconnect the fuel
selector valve.
Any time the fuel system plumbing is opened, air may enter the system. This condition may cause rough engine operation or loss of power. If the possibility that air has entered the system does exist, start and operate the engine for several minutes on each tank until proper engine operation is assured. Refer to the Pilot’s Operating Handbook and Airplane Flight Manual before starting and operating the engine.
selector from the
handle
royalite
truss
Remove the
c.
and
royalite
cover over
the main
SPa’.
cover, then remove the truss cover.
d. e.
Disconnect the fuel
plumbing
from the fuel
auxiliary
the
Disconnect
fuel
plumbing from
the
fuel pump.
selector valve. f.
Remove the bolts
tor valve to the
securing the fuel selecmounting bracket and remove the fuel
selector valve.
g.
auxiliary
Disconnect
the
fuel
plumbing from the
fuel pump.
Remove the four bolts securing the auxiliary fuel pump to the mounting bracket and remove the auxiliary fuel pump.
Remove the four bolts securing the auxile. ia’y fuel pump to the mounting bracket and remove the auxiliary fuel pump. The pump is located in front of the spar carry-through on the pilot’s side.
AUXILIARY
FUEL PUMP INS TA LLA TION AND AFTER, AND
AFTER)
h.
AUXILIARY FUEL PUMP INS TALLA TION (CE-748, CE-772 AND AFTER, CJ-149 AND AFTER, D-10097, 0-10120 AND AFTER) Secure the auxiliary fuel pump and mounting bracket to the airplane with the attach bolts. a.
b.
Reconnect the fuel plumbing to the auxil-
iary fuel pump.
a.
to the
b.
iary
auxiliary fuel pump and bracket with the four attach bolts.
Secure the
airplane
Reconnect the fuel plumbing to the auxil-
fuel pump. c.
Replace
d.
Install the
the
royalite
cover over
the main
spar.
pilot
and
copilot
seats
as
out-
lined in PILOT AND COPILOT SEAT INSTALLATION
(25-10-00). 28-20-00
Page 1 A16
Oct 16192
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
FUEL SELECTOR VALVE REIMOVAL Drain and purge the fuel
a.
b.
pilot and copilot
Remove the in
lined
PILOT
system.
AND
COPILOT
seats
SEAT
as
out-
REMOVAL
(25-10-00). Remove the
c.
royalite
the main
cover over
spar. d.
post light
the
selector
handle
and
from the
royalite
truss
fuel
the
Remove
unscrew
covers
cover, then remove the truss cover.
the
Disconnect
e.
I
plumbing from
fuel
’1.75
the
I
selector valve.
f.
bolts
Remove the
valve to the
mounting bracket
the
securing and
remove
I\
selector
the selec-
tor valve.
\45"
L I
31
FUEL SELECTOR VALVE INSTALLATION
100
L-
36-2802
Fuel Vent
Lub ricate
a.
VV-P-236
the
petroiatum (42,
fuel
line
Chart
threads
1, 91-00-00) before
installation. Secure the selector valve to the
b.
mounting
bracket with the attach bolts. Connect
c.
the
fuel
plumbing
to
the
fuel
selector valve. d.
Replace
the
royalite
truss
cover
around the
fuel selector valve.
e.
valve and
royalite
Replace the handle on the fuel selector screw the post light covers back on the
truss
f.
cover.
Replace
the
royalite
cover over
Figure
with
the main
FUEL
STRAINER
1
R~R´•IOVAL
VALVE) (Figure 2)
Access to the fuel selector valve fuel strainer may be made by opening the access door located under the airplane below the front edge of the pilot’s side window.
Remove the safety wire around the two mounted on the bottom of the fuel selector valve, then remove the screws. a.
screws
b. and
pull
Remove the bottom of the selector valve the fuel strainer screen from the fuel selector
valve.
FUEL STRAINER TOR VALVE)
INSTALLATION
spar.
(Figure 2)
Install the seats as outlined in PILOT AND g. COPILOT SEAT INSTALLATION (25-10-00).
Install the screen in a. selector valve with the flange
Test the fuel selector valve to
h. it
functions
detents
properly correspond to
28-20-00 Page 2 Oct 16/92
in the
ensure
that
positions and that placard markings.
the
all
(SELECTOR
up.the
b. valve and c.
(SELEC-
bottom
of
the)
the bottom of the fuel selector with the two attach screws.
Replace secure
Safety wire
the
screws.
A16
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
FUEL STRAINER SPRING AND
ATTACHING HARDWARE FIT INTO BOTTOM OF FUEL STRAINER HOUSING
FLANGE
FUEL STRAINER
s~
,p,,,,
UP~GASKET
LOCK PLATE
~IQD
o%
C9201514
Fuel Strainer
Figure
2
28-20-00
Page A16
3
Oct16/92
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
LUBRICATE
LUBRICATE
LUBRICATE
TAPERED PIPE THREADS
b
"i’
DO NOT LUBRICATE
FEMALE THREADS
STRAIGHT THREADS
NEVER ALLOW LUBRICANT 60-604-5
TO CONTACT TH IS SU R FACE
Lubrication of Flared
Figure FUEL
REMOVAL
STRAINER
FUEL
(WING
CELLS) Drain and purge the fuel
a.
Fittings
3
Remove the access plate for each wing a. fuel cell from the lower wing surface. b.
system.
Disconnect the fuel cell vent line from the
fuel cell. b.
Remove the
finger strainer portion of
located between the lower
access
the
cover
wing and
fuselage, Disconnect the fuel line from the connector
c.
assembly.
to the fuel cell end of
Alternately
d.
plug
each
vent
opening
to
that air is passing through all branches of the vent system for the cell. Continue to blow air through assure
d.
Loosen the fuel cell
the
finger strainer
nect
Apply air pressure
c.
the vent line.
and
nipple clamp; disconslide the fuel finger
each
branch
until
any
obstructions
have
been
removed.
strainer from the fuel cell.
STRAINER
INS TALLA nON
(WING
CELLS) tighten
b.
the
assembly in nipple clamp.
Connect
the
fuel
line
to
the
the fuel
through
the
f.
Reconnect the fuel cell vent line to the fuel
g.
Reinstall the
h.
Visually check
cell.
connector
access
plate below each fuel
cell.
assembly, c.
blow air
valve end, then reinstall the valve.
Install the connector
a.
cell and
siphon break check valve and siphon break line from the check
Remove the
e.
FUEL FUEL
Install the
access cover on
the
airplane.
looseness
INSPECTION OF FUEL CELL AND FUEL FILLER CAPS
VENT LINES
cause
or
each fuel cell filler cap for deterioration of the seal which could
leakage. If seals
are
deteriorated
or
damaged
in any way, they should be replaced.
(Figure 1) Check the extended vent to ascertain that a minimum of 1.75 inches below the lower wing skin surface. The vent tube should be i.
following procedure is recommended inspection of fuel tank vent lines and filler caps: The
for
the vent extends
28-20-00
Page
4
Oct 16/92
A16
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
scarfed at
a
450
angle
on
the forward side and should
be canted forward 100 from
perpendicular
to the skin.
FLARED FITTINGS
(Figure 3) fittings and hoses, make sure properly (see Figure 2) with VV-P-236 petrolatum (42, Chart 1, 91-00-00). When previously installed fittings are removed, they should be wiped clean and relubricated before they are reinstalled. Torque all fittings in accordance with the FLARE FITTING TORQUE CHART (Chart 2, 91-00-00). When
NOTE
installing
the threads
Any configuration of the noted
in
step "i"
vent other than as
may create
a
negative
pressure. A negative vent pressure will pull the air, or air and fuel from the fuel vent
tank.
are
hared
lubricated
"END"
28-20-00
Page A16
5
Oct 16192
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
MA IN TENANCE
INDICATING TICES
PRAC-
resistance will be 3 t3 ohms empty and 140 46 ohms full. FUEL QUANTITY LON SYSTEM)
CAUTION is the fuel time system drained air may enter the system. has If the possibility that air entered the system does exist, start and operate the engine on all is air the ground until removed from the system. Operate the engine for several minutes on tank until each engine proper operation is assured. Refer to the Pilot’ s Operating Handbook and before Manual Flight Airplane and the starting operating
(80
INDICATORS
GAL-
Any
eng~ne.
FUEL
QUANTITY
SENSORS
(80
GALLON
the airplane in a level flight with the tanks filled as indicated in Chart 1. Measure the input voltEach terminals. the indicator at age reading should be within +2 millivolts of the value shown in Chart 1, except that +1 the empty reading should be within millivolt of the chart value. Position
attitude
CHART 1 Fuel
Quantity
E
1/4
1/2
3/4
F
Millivolts
6
36
60
86
103
SYSTEM) Fuel
is measured by float type units located in each wing tank system. Electrical signals are transmitted from the sensors to the individual indicators, which indicate fuel remaining in the tank. Resistance between the stud and case of each fuel sensor must be O to 0.5 ohms in the empty position and 43 +2 ohms in the full position for the outboard fuel sensor and 0 to 0.5 ohms in the empty position and 76 +2 ohms in the full position for the inboard fuel sensor.
quantity
sensor
FUEL QUANTITY
SENSORS
(108
GALLON
FUEL QUANTITY SENSOR REMOVAL a.
Turn off electrical
b.
Drain and purge the fuel
c.
Remove the access panel which is to be removed.
sensor
d.
Disconnect
e.
Cut
transmitter
sensor
wire
safety support
power.
system. at
the
remove
the
wiring. and
screws.
SYSTEM) NOTE
Fuel
measured by float type units located in each wing tank sensor system. Electrical signals are transmitted from the sensors to the individual indicators, which indicate fuel remaining in the tank. Resistance between the stud and case of each fuel sensor must be O to 0.5 ohms in the empty position and 43 +2
quantity
is
ohms in the full position for the outboard fuel sensor and O to 0.5 ohms in the empty position and 76 +2 ohms in the full posithe tion for the inboard fuel sensor of resistance cell. The 40 fuel gallon fuel between the stud and case of the cell is O to sensor in the 14 gallon fuel 5 ohms in the empty position and 19 +2 in the ohms full position. The total
Clean the area around the before removing the sensor. f. Remove the the fuel cell. FUEL
sensor
and
sensor
gasket
from
QUANTITY SENSOR INSTALLATION
a. Inspect the fuel cell for wrinkles other obstructions that might impede sensor float travel.
or
Set the new gasket and sensor in is float and ensure that the unrestricted through its full travel from The float arm may be bent, stop to stop. if necessary, to provide clearance. b.
position
28-40-00 Page 1
A12
Aug 28/87
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
Install
c.
torque
screws,
to
the 25
sensor
support
inch-pounds,
safety.
QUANTITY INDICATOR CALIBRATION
Remove the a. instrument panel.
d. power
FUEL
and
on
Connect sensor and check fuel
wiring. gage
Turn the for empty
reading.
b. boards
over
the
the two printed ci rcui t the back of the instrujust to the left of center.
Locate located
panel
ment
glareshield
on
NOTE If
Locate the calibration screw in c. the back of each printed circuit board.
the
gage does not read empty, reinspect the sensors to ensure the float arm is on the down stop and the float clears the bottom
of the fuel cell. Check all for faulty connections.
d. cater
as
Calibrate the fuel follows:
quantity indi-
wiring Ensure that the fuel tank that fuel the to quantity being calibrated is full. 1.
corresponds e.
gages
Fill the tanks and check the fuel for full readings.
NOTE See
Instructions No. Service I or subsequent for Rev. information on more replacement of fuel quantity sensors.
0925,
Turn the calibration screw in 2. back of the corresponding printed circuit board until the needle on the fuel quantity indicator points to the "F" (full) mark. e.
Reinstall
the
glareshield.
"END"
28-40-00
Page 2
Aug 28/87
A12
CHAPTER
ICE AND RAIN
PROTECTION
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 30
ICE
RAIN PROTECTION
TABLE OF CONTENTS CHAPTER SECTION SUBJECT
SUBJECT
PAGE
30-00-00
GENERAL
Description
and
..................1
Operation
30-60-00
PROPELLERS
..................1
and
Operation Electric Propeller Deicing Troubleshooting
Description
.................1 ........1
........5
Maintenance Practices
.................5
Propeller Deicer Boot Removal Propeller Deicer Boot installation Brush Module Replacement (B.F. Goodrich)
.................5 ........9
Deicer Timer Check
........9
Heat Test
.......10
Brush Module Resistance Check (B.F. Goodrich) Slip Ring Alignment (B.F. Goodrich) Slip Ring Machining (B.F. Goodrich).
.......10
Brush Wear
On the
........11
Airplane
..............11 ........11
Replacement (McCauley)
........13
Brush Block Removal Brush Block Installation
Slip Slip Slip Slip
......11
................11
Limits(McCauley)
Removed from the Airplane Brush
.......10
........13
~McCauley)
........13
Ring (McCauley) Ring Alignment (McCauley) Ring or Brush Block Cleaning fMcCauley). Ring Machining (McCauley)
13
´•13 13
’LEND"
30-CONTENTS A6
Page 1 Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 30 LIST O~ PAGE EFFECTIVITY CHAPTER
SECTION SUBJECT
PAGE
DATE
30-EFFECTIVITY
1
Oct 7/83
90-CONTENTS
1
Oct 7/83
30-00-00
1
Oct 10/80
30-60-00
1
Oct 7/83
2
May 9/80 May 9/80
3 4
5
Oct 7/83 Oct 7/83
6
Oct 7/83
7
Oct7/83
8
Oct 7183
9
Oct 7/83
10 11
Oct 7/83 Oct 7/83
12
Oct 7/83
13
Oct 7/83
14
Oct 7/83
"END"
30-EFFECTIVITV
Page A6
1
Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
GENERAL
DESCRIPT1ON AND OPERATION
The airplane is equipped with
protection systems
that
can
a
the airplane electrical system for protecting the opening from becoming clogged with ice.
variety of ice and rain during operation
be utilized
under inclement weather conditions.
Air from the cabin
heating system prevents the windshield from fagging. The propellers are protected against icing by optional electrothermal boots
automatically cycle
an
each blade that, when activated, dispersing the formation of ice.
to aid in
The pitot mast contains
a
heating
element connected to
pitot
optional weather radar system is available for the Bonanza series airplanes starting at serials CD-878 and after, D-10264 and after, E-1534, E-1537 and after, and EA-11 and after. The indicator is located in the radio
An
section of the instrument in the outboard
panel and the antenna is located leading edge of the right wing. (See 34-40-
00.)
"END"
30-00-00
Page
1
Oct 10/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
PROPELLERS
DESCRIPTION AND OPERATION
the timer is in.
phase
PROPELLER SYSTEM
TROUBLESHOOTING
DEICER
ELEC7C~C PROPELLER DEICING propeller deicer system includes an on-off the LH instrument subpanel), an ammeter, a
The electric switch
timer,
ton a
brush
heated boot
assembly, slip rings, and an electrically for each propeller blade. When the on-off
switch is turned ON, the ammeter (near the center of the instrument panel) registers the amount of current (2-bladed, 8-12 amps; 8bladed, 14-18 system. If the current rises
amps) passing through
beyond
the switch limit,
the an
circuit breaker will cut off the power to the timer. The current flows from the timer (forward of instrument
integral
panel) to the brush assembly (mounted in front of the engine case) and is conducted by the brush assembly to the slip rings installed on the spinner backing plate. At serials Dafter, and slip rings became part of an assembly attached between the engine hub and the propeller. The slip rings distribute current to the deicer boots on the propeller blades. Heat from the boots reduces the grip of the ice, which is then removed by the centrifugal effect of propeller rotation and by the blast of the airstream. The timer cycles 10404 and after, CE-1024 and after, E-2069 and
EA-378 and after, the
power to the heating element on each blade. It takes 3 minutes for the timer to complete a cycle of 90 seconds on, 90 seconds off. Whenever the
I
ammeter in the instrument
the proper amerage,
panel
or zero
system is turned on, the or subpanel and registers
amperage,
depending
on
the
The ammeter of the deicer system can be used to indicate the general nature of most electrical problems. it is recommended that, to determine which involved, troubleshooting be preceded by the ammeter test outlined in step "a." of the 60-hour inspection (Chapter 5), and the HEAT TEST described in this chapter.
Consequently, circuits
A
are
reading of two-thirds
one-half
on
two-bladed
(or
the normal amount of current
props)
is
an
indication that
the circuits is open between the slip deicer heater. If the ammeter registers
one
ring assembly excess
of
and
current, the
power lead is shorted to ground. It is possible that the excess current has welded the timer contacts in one phase. Under these circumstances, the timer will either feed current continuously, or not cycle. If the
to the welded contacts
former is true, the heat test will show heating throughout the two phases. Unless the grounded power lead is located and corrected, any new timer that is installed may suffer the same
internal damage during the first use of the system. In most effective use of the troubleshooting chart,
general, for
all of the "indication" entries should be read to locate that which matches conditions of the particular system being checked. The numbered "probable cause" and "remarks" then indicate the proper sequence of checks. It should be noted, however, that such numbers are assigned with
respect
to the
approximate usefulness of the check rather likely sequence of occurance.
than to the most
30-60-00
Page A6
1
Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
TROUBLESHOOLlNG PROPELLER DEICER SYSTEM INDICA TION i.
Ammeter shows
(Both phases cycle.)
PROBABLE CAUSE zero current,
a.
Switch circuit breaker
REMARKS
tripped,
a.
of the 3 minute
Locate and correct short before
resetting by turning switch OFF,
circuit breaker then ON.
b.
c.
Switch
faulty.
No power from
b.
airplane.
~c.
If
voltage
at switch output with voltage input, replace the switch. If voltage is OK at switch output, go to step no
at
switch
If
no
voltage into switch, locate
and
correct open circuit.
d.
Ammeter
faulty. (If
some or
all
d.
Deicers heat with ammeter at
If low
replace ammeter.)
zero,
Test for
voltage
or
replace
zero
up to and out of ammeter. output but proper input,
ammeter.
If
voltage
no
to
ammeter, locate and fix open between switch and ammeter.
e.
Open circuit between
e.
ammeter and timer,
Disconnect harness at timer and check
voltage pin
B
(of harness)
ground.
to
If
none, locate and correct open circuit.
i
t
Open
in
wiring between limer
i.
and firewall connector.
Re(erto Ihepatagraphon heattesttolind Deicers not heating and test for voltage on that pin of firewall connector. If zero over
3 minutes,
wiring from g.
Open
between firewall and
g.
Deicer lead straps,
2.
Ammeter
shows
normal
h.
No
a.
Open in Deicer assembly.
part of cycle, low current rest of cycle. current
ground
If
voltage OK to firewall plug, try voltage junction of Deicer lead and slip ring lead. If no voltage, find and correct open in wiring to brush block, open within brush block, or no contact brush to slip ring. at
h.
circuit.
or
locate and fix open in
timer to firewall.
slip ring
a.
if voltage at Deicer bads, locate and fix open from Deicer to ground.
Disconnect Deicer straps to check heater resistance. If resistance is within
specified
limits, locate and fix open in slip ring leads.
It not,
replace Deicer
with open
circuit. b.
High
resistance in circuit with
low current.
b.
If not in contact of brush to
(including ground brush), Deicer and to timer to fix
wire, loose
3060-00
Page 2 May 9/80
or
slip ring wiring to partially broken trace
corroded connection.
BEECHCRA~ BONANZA SERIES MAINTENANCE MANUAL
TROUBLESHOOTING PROPELLER DEICER SYSTEM (Continued) INDICA TION 3.
PROBABLE CAUSE
Ammeter shows low current.
a.
Airplane voltage
b.
Ammeter
c.
High
REMARKS
low,
faulty.
resistance up to timer,
a.
Check bus
b.
Refer to step "l-d."
c.
Check for
partially
corroded
connection
voltage.
airplane supply 4.
Ammeter
shows
excess
a.
Ammeter
faulty.
Ground
between
broken wire, loose or in
to timer
wiring input.
from
a.
Refer to step "l-d."
b.
Disconnect harness at timer and, with ohmmeter, check from pin B (of harness) to ground. If ground is indicated, locate
current.
b.
ammeter
and timer.
and correct.
c.
Ground between brush block
c.
and timer.
Disconnect leads at brush block and check from power leads to ground with ohmmeter. If ground is indicated, locate and correct.
d.
Ground between brush block and
d.
Deicers.
If
no
short
exists
at
brush-slip ring
contact, check for ground from slip ring lead to prop while flexing slip ring and Deicer leads. If a ground is indicated,
(Excluding ground brush circuit.)
locate and correct.
a.
Timer
faulty.
a.
Test timer
as
indicated in
paragraph
on
timer check. 5.
Ammeter
does
not
"flick"
a.
Timer
ground open,
a.
each 90 seconds.
Disconnect harness at timer and check with ohmmeter from
pin G (of harness) to ground. If no circuit, refer to Bonanza Wiring Diagram Manual PIN 35-590012-9. b.
Timer contacts
are
welded
(caused by short circuit
b.
in
Test timer
as
in
paragraph on timer cycle with voltage
check. If timer does not at pin B, replace timer causing original failure
system.)
but be
sure
short
has been located
and corrected.
5.
Ammeter flicks between 90
second phase
a.
periods.
Loose connection between
airplane power supply timer input, b.
a.
and
Loose or poor connection timer to Deicers.
If trouble
occurs over
Timer cycles
erratically.
cycle,
trace
power source to timer input to locate and tighten loose connection.
b.
Check for brush to
rough or dirty slip rings causing "skip." If not this, trace circuits to
locate and fix loose c.
entire
wiring from
c.
Test timer
as
or
poor connection.
indicated in
paragraph
on
timer check. d.
Electrical
wiring breakdown.
d.
Replace
the
faulty
deicer boot.
3060-00
Page 3 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
TROUBLESHOOTING PROPELLER DEICER SYSTEM (Continued)
7.
Radio noise with Deicers
REMARKS
PROBABLE CAUSE
INDICA TION
or
interference
a.
Brushes
"arcing."
a.
Check brush alignment
as
in step "h" of
inspection (Chapter 5). Look for rough or dirty slip rings. If this is the cause, clean, machine or replace slip ring assembly. Check for slip ring alignment. 100-hour
on.
b.
b.
Loose connection,
Refer to step
"g",
of 100-hour
inspection
(Chapter 5). c.
Switch
d.
Wiring located than
faulty.
8
within
inches
of
less
c.
Try jumper wire across switch. If radio noise disappears, replace the switch.
d.
Replace wiring to
radio
at
least 8 inches from
radio
input
equipment.
equipment wiring. 8.
Rapid brush breakage.
wear or
frequent
a.
Brush block out of
alignment.
a.
alignment as in step inspection (Chapter 5).
Check brush 100-hour
b.
Slip ring
wobbles.
b.
Check
slip ring alignment
"h." of
with
dial
indicator.
c.
Replace
Dirty slip rings.
d.
Clean the
Brushes
e.
See "8a".
c.
Rough slip ring
d.
a.
arcing,
surfaces.
or
machine.
slip rings,
3060-00
Page
4
Oct7183
A6
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
PROPELLERS
AIIAINTENANCE PRACTICES
h.
Remove the
propeller blade with 31, Chart i, 91-00-00). and
PROPELLER DNCER BOOT REMOVAL
propeller spinner.
a.
Remove the
b.
Disconnect the deicer boot leads from the
bulkhead and c.
remaining adhesive from the boot toluol or methyl ethyl ketone (19 or
spinner
PROPELLER DEICER BOOT INSTALLATION
slip ring.
Remove the clip securing the lead strap to the and the clamp securing it to the propeller
NOTE
spinner bulkhead hub.
If
a new
CAUTION Place the blade
so
drying time of (52, Chart 1, 91-00-00)
is installed, the
must be extended per B. F. Goodrich Service Bulletin No. E-75-51.
the solvent will
from the hub. The solvent may propeller seals.
propeller
1300L adhesive
the
run
away
damage the a.
boot
on
On 8.F. Goodrich installations position the deicer propeller blade so that its center line at the
the
split in the propeller blade clamp, and the center line 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 inboard end is
clamp and NOTE If the lead strap is retained by a strap rather by a clamp, remove the boot lead strap
adjacent
to the
1 inch outboard of the
blade retaining clamp.
than
retaining strap as follows: 1. Using methyl ethyl ketone of
toluol
(31
or
19, Chart 1, 91-00-00) to soften the adhesive of the strap, loosen one corner of the strap
NOTE
sufficiently to grasp it with pliers or similar tool. 2. Apply a slow’steady pull to the strap while using the solvent to soften the adhesive.
d.
If
applicable
remove
the boot lead strap
McCauley
place the center line leading edge of the propeller. For other McCauley installation dimensions refer to Figure iA. On
installations
of the deicer boot
on
the
retaining
strap. Using methyl ethyl ketone or toluol (31 or 19, Chart 1, 91-00-00) to soften the adhesive of the strap, loosen one corner of the strap sufficiently to grasp it with pliers or
b.
Mask off
an area
approximately 1/2 inch from (See Figure 1).
the
outer end and each side of the boot.
similar tool.
CAUTION Unless the
boot
scrapped, cushion prevent damaging
being removed is jaws of any pulling
the
to
be
NOTE
tool to
the boot surface.
On installations
off
an area
using rubber lead straps mask approximately 1/2 inch from the area
which will be e.
Apply
a
slow, steady pull to the strap while using
the solvent to soften the adhesive. f. Using methyl ethyl ketone or toluol (31 or 19, Chart 1, 91-00-00) to soften the adhesion line between the boot and the blade, loosen one corner of the boot sufficiently to grasp it with vise grip pliers or a similar tool. the
Apply a slow, -steady pull on the boot to pull it off g. propeller surface while continuing to use the solvent to
soften the adhesive.
occupied by
the lead strap retainer
strap (around the blade shank).
c.
Remove the deicer boot and clean the blade in
the masked area from the
retaining clamp outboard. Clean thoroughly with methyl ethyl ketone or toluol, (31 or 19, Chart 1, 91-00-00). For final cleaning, wipe the solvent off quickly with a clean, dry, lint-free cloth to avoid leaving a the
area
film.
3060-00
PageB Ad
Oct7/a3
BONANZA SERIES MAINTENANCE MANUAL
8\
DEICERBOOT
O Xi-’g
t
n
ililiiiiii~iiiiiiiiiiiiiiiiiillii:::,::::
:i
I. l: . ’1: :if.l : . :. .
1/2"
ii
1/2"
MASKlNG TAPE
ssat´•l~
Deicer Boot Installation
Figure
1
CAUTION
NOTE
If the blade is painted with laquer remove all paint within the masked off area. If the blade is painted with polyurethane, lightly sand within the masked off area, using 400 grit sand paper.
When solvent is used to soften cement, methyl ethyl ketone (MEK) provides approximately 10 seconds time for de-icer application, while Toluol will provide approximately 40 seconds working time.
CA UT/ON The metal and rubber parts must be
clean to
assure
Position the deicer boot on the propeller, starting g. f inch from the blade retaining clamp, making sure the lead
thoroughly
maximum adhesion,
strap is in position Moisten the cement
(31
damp to the blade retaining clamp. lightly with methyl ethyl ketone or tolud
to
19, Chart 1,91-00-00) and tack the boot
or
center line to
leading edge. If the center line of the boot deviates from the blade leading edge, pull up with a quick motion and replace properly. Poll firmly along the center line with a rubber roller (see Figure 2). the blade
d. toluol
(31
Moisten or
a
clean cloth with
methyl ethyl
ketone
or
19, Chart 1, 91-00-00) and clean the unglazed
surface of the deicer boot and both sides of the rubber retainer strap if applicable, changing the cloth avoid contamination of the clean area.
frequently
to
CAUNON
mix EC-1403 cement
(EC apply one even brush coat to the propeller blade and to the unglared back side of the boot. Allow the cement to dry for at least one hour at 40PF or e.
Thoroughly
cement may also be
hours if the
humidity
humidity
is less than 75%,
or
is between 75% and 90%. Do not
the cement if the relative
Never use a metal or wooden roller for this purpose, for they would damage the heating elements in the deicer boot.
and
used)
above when the relative
1300L
humidity is higher
than 90%
two
apply or
the
temperature is below 50"F. f.
After
allowing
sufficient
drying time, apply
a
second brush coat of cement to the propeller and to the unglazed surface of the deicer boot. Apply cement to the necessary to cement the strap to the up to the hub. Allow the cement to dry, lead strap
as
propeller,
h. over
Gradually tilting
pockets
under the boot
carefully trapping air
the roller, work the boot
each side of the blade contour. Avoid
(see Figure 3).
30-60-00
Page6 Oct1/63
As
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
START IN THIS AREA (APPROX. 90 FROM THE DE-ICE BOOT LEAD STRAP) AND WRAP AROUND PROP BLADE SO THAT A DOUBLE THICKNESS WILL COVER THE DE-ICE BOOT LE’AD STAP. TRIM RETAINER STRAP SO THAT IT WIILEND APPROX.
:i
i:
:::::::~j::::.-
AS SHOWN.
"7~´•
A--A
j-.50" P(PICAL I OVERLAP EDGE OF BOOT AND STRAP WITH SEALANT BY ~s"
llc--.12Y’
AS SHOWN.
SEALER
r
II
A
DE-ICE BOOT
A .375
RETAINERSTRAP~
t
.125
I
36-251-8
Boot Deicer Installation Figure 1A
(McCauley)
~SI
30-6090
Page7 As
Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
outwardly from the center line to the edges of (see Figure 4). If excess material at the edges tends to farm puckers, work them out smoothly and carefully with the fingers. Roll the tapered edges of the boot with a narrow i. Roll
i.
the boot
steel stitcher roller.
Clean the blade with
k.
a
clean cloth moistened with
ketone (19 or 31, Chart i, 91-00-00). Be careful not to let solvent run into the edge of the boot. i. Apply one even brush coat of sealer around the
toluol
or
methyl ethyl
of the boot,
edges
boot but and -2 1003
extending
on
allowing 1/16 to 1/8 inch overlap on the masking tape. Use BFG 82-076-1
B.F. Goodrich installations and Sunbrite 78-U-
installations.
Side
McCauiey Remove the masking tape after applying the
enamel
U-1001-C
and
catalyst
on
cement to obtain a neat border.
clamp securing the lead strap propeller blade retaining clamps, m.
60~251-4
to the
Install the
to the
Rolling
Figure
3
Connect the lead terminals and install the clip on n. spinner bulkhead. There must be no slack between the terminal and the clip to assure enough slack between the clip and the clamp on the blade to allow full propeller travel.
the
NOTE
CAUTION
The rubber retainer strap should wrap around over the inboard 1/4 inch of
After deicer boot installation allow at least 12
the blade shank
the deice boot on B.F. Goodrich McCauley installations,
or
1/2 inch on
hours for the 1300L
or EC-1403 cement to dry before starting the engine, and 12 hours more
before
energizing
the deicers.
6~251´•10 60261-8
Rolling Figure%
Center
Edge Rolling Figure 4
3060-00
Page8 Oct 7/83
A6
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
RND
Disconnect the
a.
wire
harness
terminals at the
terminal screws of the modular units that make up the
k colbhsurb assembly. Remove the screws, nuts, and washers securing assembly to it’s mounting bracket.
b.
SLIP RINa ASSY
the modular brush
Remove the
c.
assembly retaining
and
screws
separate the modules and spacer.
t-
4
I
~I
Replace
d.
1132 MIN
3/32 MAx
II
each module with another of the
same
part number, The part number is etched into the surface of the
plastic housing. Restack the modules and spacers
e,
as
necessary.
If there is interference between
adjacent ring terminals, reposition one module with the terminal on the opposite side of the brush module assembly. f. Install the assembly screws so that the screwhead in the recess in the spacer, place the flat washer between the star washer and modular housing and install
fits THRUST BEARING PLATE
assembly is square before in place. Place the modular brush assembly on the g. mounting bracket and insert the mounting screws through
the
eRusn MODULE ASSY
Propeller Deicer Brush Module (B. Figure 5
F.
retaining
tightening
3e240´•e
of the
screw
REPLACEMENT(B.F. Goodrlchl
assembly is made up of two modules, consisting of a plastic housing with an integral brush and spring. These modular units are stacked with a spacer held together by screws to produce the modular brush assembly, The modular brush each
and
Before
one
brush
a
wears
only 3/8 inch of brush containing the brush should
where
to
material remains, the module be replaced. When 1/4 inch of brush remains, the brush
NOTE
During
measurement
being
only
1/16 inch of brush
from the brush module, this the normal protrusion when the brush is
should
protrude
installed
on
the
retaining
nut.
retainer nuts, make
am
sure
that
the
between the brush module spacer and the mounting bracket until the brushes are properly aligned with the approximate center of the
i.
slip ring. retaining washers and nuts, making
Install the t
1/32 inch is maintained between the
slip ring surface. To prevent damage brushes, the modular brush assembly should be
brush modules and the to the
angled so that the brushes contact the slip rings at an angle approximately two degrees from perpendicular, as measured toward the direction of slip ring rotation as shown in Figure 5. Reconnect the "B", and "C" terminals of the j. airplane system wire harness to the same designated terminals of the modular brush assembly. Ensure that the adjacent ring terminals are not touching. of
replaced,
module MUST be
under the
installing the aligned with
certain that 1/16 When
screws
slip rings such that the entire brush face contacts the copper ring. If the brushes do not align with the slip rings throughout the entire 360 degrees of slip ring rotation, install shims (P/N 1E1157) the brushes
BRUSH IIAODULE
assembly
both the block and bracket. One washer fits under the head
Goodrich)
h.
I
nut. Make sure the
the
airplane. DEICEFI TIME~ CHECK
Brush wear is determined by inserting a pin into a hole in the back of the brush module, On all modules having brushes with rods, the brush module should be replaced when the
replaced
pin
be inserted 15/64 inch and MUST be
can
when the
pin
can
brushes,
pin
can
proceed
be inserted 1 9/64 inches. To as
in the field has indicated that often the timer is source
of the trouble lies
elsewhere. For this reason, the following test should be performed before the timer is removed as defective:
be inserted 19/64 inch. On the
rodless brushes, the module should be replaced when the pin can be inserted 1-5/64 inches and MUST be replaced when the
Experience
considered defective when the
follows:
replace
the
a.
With the
wiring
harness disconnected at the timer,
and the deicer switch in the ON from
pin
B of the harness
plug
present, the timer is NOT
at
position, check the voltage to ground. if no voltage is fault; however, if system
3060-00
Page9 A6
Oct7/63
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
I
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 in the timer. If ground connection is open, the timer step switch will not change position, After the ground and power circuits have been b. checked, connect a jumper wire from pin B of the timer receptacle to terminal B of the connector plug and from pin G of the timer receptacle to ground. With the deicing system switch ON, check the voltage to ground from pin B of the timer. The voltmeter should indicate bus voltage. Next, check the DC voltage to ground from pin C or pin O on serials 0-10404 and after, CE-1024and after, E-2069 and after, and EA-378 and after; it should indicate bus voltage for 90 seconds,
seconds,
zero
volts for 90 seconds, bus
voltage
90
Before this test
can
be
performed,
the
jumper
so
replaced in perform this
ON while the
they
are
wire installed
test: one in the
outside feels the deicer boots to see if properly. The man in the cabin observes
man
heating
needle should deflect every 90 seconds in response to the switching action of the timer. Each time this occurs, the man in the cockpit must notify the man’ ammeter
the
propeller deicer boots
so
that the latter
can
check the proper heating sequence of the propeller deicer boots (the entire boot will either heat or cool, depending on
sequence). If any irregularities are detected, a continuity check should be performed on the wiring from the timer to the brush module holder and the propeller deicer
the timer
terminal connections.
CAUTION While
following
TEST" section, forth to prevent
slip ring.
(B.F.
Goodrich) To check for
module, to
a
short circuit,
measure
or
high
resistance in the brush
the resistance from the face of the brush
its terminal studs
or
receptacle pin
If this resistance measures
the
locate and
repair
resistance
measures
cause
zero,
with
a
over
low range
0.013 ohm,
of excessive resistance. If the locate
and correct the open
replace the module. Check the resistance between the terminal studs or receptacle pins. This resistance should not be less than 0.5 meg-ohm. or
the timer
the ammeter for the proper readings (2-bladed: 8-12 amps, 3-bladed: 14-80 amps) throughout the timing sequence. The
inspecting
BF~USH MODULE I~ESISTANCE CHECK
that the connector
receptacle. Two men are cockpit to monitor the ammeter; the other outside by the prop to check the deicer boots. The man in the cockpit turns the deicer system be
moved.
circuit
for the timer test must be removed to
moving the propeller, make certain that ignition switch is off and that the engine has cooled completely. There is always some danger of a cylinder firing when the propeller is Before
the
ohmmeter.
etc.
NEA T TEST
plug can required
WARNING
the instructions of the "HEAT move
arcing
the
propeller
back and
between the brushes and
SL/P R/NG ALIGNMENT
(BF. Goodr~h)
slip rings- are properly aligned when they run in a true plane relative to the brush module. This condition may be checked by attaching a dial indicator gage to the front of the engine crankshaft housing in such a manner that a reading of the slip ring wobble may be obtained. To avoid error in readings, rotate the slip rings slowly while pushing in on the propeller to take the play out of the thrust bearings. If the total run-out over 360 degrees of rotation exceeds 0.005 inch, or 0.002 inch for any 4-inch are, the slip rings should be aligned as follows:
The
Approximately a 0.012 inch adjustment may be slip ring wobble by varying the torque on the attachment bolts. Using the dial indicator to follow the points of maximum deviation, adjust the slip ring assembly to the prescribed run-out limits by varying the torque of the mounting bolts as required within a range of 40 to 100 inchpounds. If more than 0.012 inch of adjustment is required b. for alignment, the slip ring assembly may be shimmed to within the prescribed limits for true running by the addition of AN960C416L washers on the mounting bolts between the slip ring assembly and the spinner bulkhead. If necessary, fabricate thinner shims to the AN960 size. Again the torque a.
made to correct the
may be varied
as
in step "a".
30-60-00
page
10
Oct 7/83
A6
I
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
TORQUE 12-14 IN-LB
NOTE
TORQUE TO 20 TO 30 IN-LB AN960-PD10L WASHER (USE AS REQUIRED FOR
If, in machining, the solder or braze connection the underside of the slip ring is exposed, replacement of the slip ring assembly will be
CORRECT SPACING) TORQUE 8 TO 10 IN-LB
.01
on
necessary.
AIRCRAFT WIRING
BRUSH BLOCK BRACKET
sdUSH
BLOCK ASSY
,LENclNE
BRUSH WEAR LIMITS
(McCauleyl
(FigUre 7) CFIANK CASE
The brushes may be checked for methods.
wear
by
of the
one
following PROPELLER MOUNTING BOLT SLIP RING ASSY PROPELLER HUB
ON THE AIRPLANE 36-251-5
insert
a.
a
thin stiff feeler gage into the slot
on
the
side of the brush block.
Propeller Deicer
Brush Module
Figure
(McCauley)
If it goes
b´•
~dS1 need
6
past the back of the brushes the brushes
replaced.
REMOVED FROM tHE AIRPLANE NOTE
Insert
a.
a
thin stiff feeler gage into the slot on the past the back of the brushes.
side of the brush block The
adjustments may affect the slip rings; consequently, after slip ring alignment, a above
clearance between the brush module and
check should
be
made to ascertain
that
a
Gently push
b. c.
outside
the brushes into the brush block.
If any brush has .094 inch brush the brush block, that brush
less remaining assembly needs
or
replaced.
distance of from 1/32 to 3/32 inch is maintained between the brush module and
slip ring surface BRUSH REPL4CEMEN~
(see Figure 5).
(McCauleyl
(Figure 7) SLIP FIING MACHINING ie.F Good~ch) a.
Slip rings
which have
damaged surfaces, but
roughened structurally sound, can be machined and restored to serviceability. Remove the slip ring assembly from the airplane’ and mount it in a lathe. Position it concentrically in
which
or
are
the lathe, with not bver 0.002 inch wobble 360
or run-out over
degrees rotation. Take light cuts for a smooth finish and deeper than required to remove surface damage, contact surfaces of the slip rings must be parallel within
cut no
The
0.005 inch, and flat within 0.005 inch overall. Deviation from flat is not to exceed 0.002 inch over a 4 inch are. If necessary, undercut the insulation between the slip rings to a depth of 0.020 to 0.030 inch below the contact surface of the
slip rings.
In this
NOT be reduced
operation, width of the slip ring MUST
more
than 0.005 inch. Contact surfaces of
slip rings must have a finish of 29-35 microinches. slip n’ng edges and reinstall in the airplane and align. the
Deburr the
Remove the
brush
block from the
engine
as
indicated in BRUSH BLOCK REMOVAL. b.
Remove the two
screws
in the back of the brush
block.
Pull the brush holder and brushes from the brush c. block. Discard the brush holder and brushes. d.
sliding sliding e.
Replace
the brush holder into
Install the two
place. Torque f. ensure
g.
the brushes and brush holder
the brushes into the slots of the brush
by first
block,then
place.
screws
which hold the holders in
the screws to 20 to 24
inch-pounds.
Push the brushes back into the brush block to that they spring back freely. If
the
brushes bind, loosen the
screws
reposition the brush holders so the brushes ride freely slots. Torque the screws to 20 to 24 inch-pounds. h. Install the brush block BLOCK INSTALLATION.
as
and
in the
indicated in BRUSH
30-60-00
Page A6
11
Oct7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
.094 1 NCH MINIMUM
I
j
\O
a
a FEELER GAGE
BRUSH WEAR MEASUREMENT
~T43 BRUSH BLOCK
DISASSEMBLY
BRUSH AND HOLDER ASSEMBLY
TORQUE 20 to 24 INCH POUNDS
36-251-6
Brush Block
Assembly (NlcCauley) Figure 7
30-60-00
Page
la
Oct7/83
As
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
(McCauleyl
BRUSH BLOCK REMOVAL
SLIP RING MACHINING
a.
Disconnect the lead wires from the terminal
b.
Disconnect the brush block
remove
the brush block from the
mounting engine.
strip.
screws
and
sound
Structurally
(McCauley)
slip rings with damaged surfaces may serviceability.
be
machined to restore a.
ring assembly with methyl ethyl machining. Check the assembly mounting surface flatness. It Clean the slip
ketone before
BRUSH BLOCK INSTALLATION
(McCauleyl
b.
must be flat within .005 inch overall.
(Figure B)
c.
a.
Install the brush block
screws, but do not
b.
Add
block with
the
engine with
the two
(see Figure 6)
to the brush
until each entire brush is in contact
Position the brush block
of rotation. on
the
mounting
bracket
that the distance between the brush block and the face of .015 inch, slip rings is .064
the
d.
Tighten
SLIP RING
the
assembly concentrically
Locate the
that there is
than .002 inch wobble
no more
in
a
lathe
so
or run-out over
360" of rotation. The assembly should be fixed in the lathe in
screws.
shims
mounting it’s slip ring throughout 360~ screws
c. so
the
tighten
or remove
on
the
This will
assembly. the assembly propeller. d.
as
manner
same
it
ensure
was
attached to the
that run-out held while
propeller machining
will be transferred when it is mounted
Take
a
light
cut for a smooth finish
(25
on
the
to 20 micro
inches).
screws.
(McCauley) NOTE
retorqued slip rings the mounting shims added to correct wobble or nonconcentric rotation. Wear or slight wobble may be removed by machining. bolts
On these
can not
be
or
The
spindle speed
should
be
500
rpm
greater. If machine vibration is noticed, it
or
must
be corrected. Machine vibration which is not corrected will result in a chattered finish. Feed rate is to be .002 inch or less with a final pass of
NOTE
.005 inch to .010 inch.
Friction from the brushes will wear
pattern
on
the
cause a concave
slip rings.
This does not Ensure that the face surface of the slip rings are and flat within .008 overall. f. The slip ring holder face and the insulation around and between the slip rings must be undercut to .050 inch to
necessitate replacement or machining unless rapid brush wear is encountered. When a new brush assembly is installed on dip rings with normal wear, without
the brushes will
degradation
SLIP RING ALIGNMENT
of
operation
rapidly or
a.
parallel
seat
.060 inch
service life.
(McCauley)
chattering or screeching noise is heard coming from the block/slip ring area, the probable cause is improper brush block-to´•slip ring alignment. A chattering or screeching detected while turning the propeller tin the normal direction of rotation) by hand should be corrected immediately. If the chattering or screeching is heard above idling engine noise;the problem is severe. Repositioning the brush block as indicated in Figure 7 should correct the problem. If
(Figure 8).
CAUTION
a
brush
SLIP RING OR BRUSH BLOCK CLEANING
(McCauley)
undercutting the insulation between the slip rings, do not cut the inside diameters or the outside diameters of the slip rings more than .003 inch past the original diameters.
When
g. h.
a
clean
Polish the
slip ring edges. ring faces with crocus
cloth to obtain
a
finish of 16 to 22 microinches. i.
slip rings and brush block may be cleaned with cloth dampened with methyl ethyl ketone. The
Deburr the
Check the electrical resistance between each ring ring. The resistance
and the holder .and between each should be
a
minimum of 50K ohms.
30-60-00
Page A6
13
Oct 7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
MACHINE EPOXY AND SLIP RING HOLDER IN AREAS SHOWN TO OBTAIN A TOTAL UNDERCUT OF .050" TO .060".
I
rCI-: 050
.060
,-Z1
.435
f-
AFTER MACHINING OF SLIP RING FACES
CA IjTION WHEN UNDERCUTTING INSULATION BETWEEN RINGS, DO NOT CUT INSIDE AND OUTSIDE DIAMETERS OF SLIP RINGS MORE THAN .003" PAST THE ORIGINAL UNDERCUT DIAMETERS. 36-251-7
Slip Ring Machining (McCauley) Figure 8
~SI
"END"
3060-00
Page
14
Oc17/83
A6
CHAPTER
LANDING GEAR
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 32
LANDING GEAR
TABLE OF CONTENTS
SUBJECT
PAGE
32-00-00
Description
General
Landing
Gear
and
Operation
1
System
1
Optional Landing Gear Safety System
Troubleshooting
Landing
1
Gear Electrical
System
2
32-1 0-00
Main Gear and Doors Main
Gear
Landing
Maintenance Practices
1
Servicing
1
Lubrication
1
Main
Landing
Main
Landing Gear
Main
Landing
Main
Gear Removal Installation
1
Gear Overhaul
Landing
Main Gear
1
Gear
2
Disassembly
Cleaning, Replacement
3
Parts and
Repairs
5
Cleaning
5
Replacement
Parts
5
Repairs Main
6
Landing Gear Assembly
7
32-20-00
Nose Gear and Doors
Maintenance Practices
1
Nose Gear Shock Strut
1
Lubrication
1
Nose Gear Removal
1
Nose Gear Installation
1
Nose Gear Overhaul
2
Nose Gear
Disassembly
Nose Gear
Cleaning, Replacement
2
Parts and
Repairs
3
Cleaning Replacement
A21
3
Parts
4
32-CONTENTS
Dec
23/99Page
1
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 32
LANDING GEAR
TABLE OF CONTENTS (CONTINUED) SUBJECT
PAGE
Repairs
4
Nose Gear
10
Shimmy Damper Servicing
Nose Gear Nose Gear
Assembly
12
Shimmy Damper
Removal
12
Nose Gear
Shimmy Damper
Installation
12
Nose Gear
Shimmy Damper Overhaul
12
Nose Gear
Shimmy Damper Disassembly
Nose Gear
Shimmy Damper Cleaning, Replacement
12
Parts and
Repairs
Cleaning
13
13
Replacement
Parts
13
Repairs
15
Nose Gear
Shimmy Damper Assembly
Nose Gear Retract Mechanism Nose Gear Retract Brace
16
Servicing
Assembly
Check
18
(E-1103
and After; E-l thru E-l 102 With Kit 35-4012-1
Installed)
18
32-30-00
Extension and Retraction
Maintenance Practices
Lubrication
Manual
1 1
Gear Extension
Landing
System
1
Landing
Gear Actuator
Landing
Gear Actuator
Landing
Gear Motor Removal
2
Landing
Gear Motor Installation
2
Dynamic
Brake
Landing
Gear
Landing
Gear
Relay
Assembly
Removal
1
Assembly
Installation
2
Check
Dynamic
Brake
Dynamic
Brake
Landing
Main
Landing Gear Retract
Rigging
Landing
Cleaning
Retract Actuator
Assembly
23/99
Relay
Installation
3 3 5
5
Retract Actuator
ceD2
3
Rod Installation
Disassembly
Page
Relay
Gear
Retract Actuator
Landing
3
Removal
Gear Retract Rod Removal
Main
the
.......................................................................................i........................
and Parts
10
Replacement
Gear Retract Actuator Functional Test
32 -CO NTE NTS
12 12 13
A21
RayiIhcoM Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 32
LANDING GEAR
TABLE OF CONTENTS (CONTI1JUED) SUBJECT
Landing
PAGE
Gear
Check of
Safety System
Landing
Gear
Maintenance and
Safety System
With
Adjustment
Safety
Landing
Gear
Safety System
Microcircuit
Landing
Gear
Safety System
Pressure Switch
14
Switch in Test Position
14
Adjustment
14
Adjustment
14
32-40-00
Wheels and Brakes
Description
and
Operation
1
Main Wheel Assemblies
1
Nose Wheel
1
Assembly
Tires
Brake
1
Assembly
1
Shuttle Valve
1
Brake Wear and Wear Limits
t
Hydraulic
Brake
Troubleshooting
System
Brake
Wheels and Brakes
1
System
3
Maintenance Practices
3
Wheel And Tire Maintenance
3
Main Wheel And Brake
Assembly
Main Wheel
And
Brake
Inspection
Assembly Inspection
Main Wheel And Brake
Removal
3
Cleaning
4
And
4
Cleaning
Assembly
Installation
4
Nose Wheel Removal Nose Wheel
5
Inspection
And
Cleaning
5
Nose Wheel Installation
Relining
5
The Brakes
6
Cylinder
Removal
6
Brake Master
Cylinder
Installation
6
.Brake Master
Cylinder Linkage Adjustment
6
Brake Master
Cylinder Disassembly
6
Brake Master
Cylinder Cleaning
Brake Master
Cylinder Assembly
A21
Brake Master
And Parts
Replacement
6 7
Parking
Brake Valve Removal
7
Parking
Brake Valve Installation
7
32-CONTENTS
Dec
23/9 Page
3
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 32
LANDING GEAR
TABLE OF CONTENTS (CONTINUED) PAGE
SUBJECT
Parking
Brake Valve
Adjustment
7
Parking
Brake Valve
Disassembly
7
Parking
Brake
Parking
Brake Valve
Bleeding
Cleaning
The Brake
And Parts
Replacement
7
Assembly
7
System
8
Gravity Bleeding Pressure Pot Electric
9
Bleeding’
12
Bleeding
12
32-50-00
Steering
Maintenance Practices
Nose Wheel Travel
1
Stop Adjustment
1
32-60-00
Position And
Landing
Warning
Gear Position
Maintenance Practices
1
1
Light Adjustment
Main Gear
1
Nose Gear
1
Landing Gear Warning Switch Adjustment (CE-748,
Engine-Compartment-Located
CE-772 thru
CE-1300, CE-1302 thru CE-1306; CJ-149 thru CJ-179; D-10097, D-10120 and After; E-llll, E-l 241 thru E-2110, Except E-1946 and E-2104; EA-1 thru EA-388, Except EA-320)
Landing Gear Warning
Engine-Compartment-Located
Switch
Adjustment (CE-1301, CE-1307
and
After; CJ-180 and After) Pedestal-Located
Landing
2
Gear
Warning
Switch
Adjustment (E-1946, E-2104,
E-2111 and After;
EA-320, EA-389 and After)
3
Engine-Compartment-Located After)
Landing
Gear Retract-Prevent Switch
Adjustment (CE-1301,
Landing
Gear
Warning
Switch
Adjustment (E-2458,
EA-320, EA-389 and After)
Page
ceD4
23/99
CE-1307 6
and After; CJ-180 and Pedestal-Located
1
32-CO NTE NTS
E-2468 and After; 7
A21
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 32
LANDING GEAR
LIST OF PA GE EFFECTIVITY
CHAPTER-SECTION-SUBJECT
32-Effectivity
32-Contents
32-00-00
32-10-00
32-20-00
A21
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32-EFFECTIVITY
Dec
23/9 Page
1
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 32
LANDING GEAR
LIST OF PAGE EFFECTIVITY (CONTINUED) CHAPTER-SECTION-SUBJECT
PAGE
32-30-00
32-40-00
Dec
23/9Page
2
32-EFFECTIVITY
DATE
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A21
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 32
LANDING GEAR
LIST OF PAGE EFFECTIVln/ (CONTINUED) CHAPTER-SECTION-SUBJECT
32-50-00
32-60-00
A21
PAGE
DATE
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6
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7
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8
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32-EFFECTIVITY
Dec
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3
Qeec~craR BONANZA SERIES MAINTENANCE MANUAL
GENERAL-DESCRIPTION AND OPERATION LANDING GEAR SYSTEM The
landing gears are operated through adjustable linkage connected to an actuator assembly mounted beneath the front seats. The actuator assembly is driven by an electric motor controlled by the landing gear position switch mounted on the right or left subpanel
and limit switches mounted
assembly.
uator
The
switches and actuator
removing The
adjacent
landing assembly
landing gear may be used to drag. Should disorientation occur under instrument conditions, the lowering of the landing gear will reduce the tendency for excessive speed buildup. This procedure would also be appropriate for a noninstrument-rated rated pilot who unavoidably In
emergency, the
an
create additional
to the act-
gear motor, limit are accessible by
encounters instrument conditions
cies such
as severe
tion of the gear doors is
essa’y.
CAUTION
Never tow
landing
brief
gear position switch, limit switches, safety switches, and motor circuit breaker. The push button for resetting the landing gear motor circuit breaker is located in the When the
position,
right subpanel.
gear switch is placed in the UP the circuit is completed to two safety
located
one
on
the
right
up-winding jacks,
if the
of the
the left main gear, the other main gear. If the safety switches on
complete
the circuit to the
landing
airplane
gear motor, as would be the were airborne or supported on
the
landing gear motor will run until the landing gear is fully retracted and the uplimit switch is actuated, breaking the circuit to the landing gear motor. When the landing gear position switch is placed in the DOWN position, the circuit is completed to the downwindings of the landing gear motor, and the motor will operate until the landinggear has been fully extended and the downlimit switch actuated, breaking the circuit to the landing gear motor. To prevent overtravel of the gear, the dynamic brake relay simultaneously breaks the power to the motor and makes a complete circuit through the armature and the opposite field winding. The motor then acts as a generator and the resulting electrical load
on
strut
or
towing
taxi with or
a
flat strut. Even a deflated
with
taxiing
damage.
can cause severe
OPTIONAL LANDING GEAR SAFETY
landing
have been actuated to case
speeds higher special inspecrequired, with repair as nec-
the front seats.
gear may be electrically retracted and extended and may also be lowered manually in an emergency. The landing gear circuit consists of the
located
in other emergen-
Should the landing gear be used at than the maximum extension speed, a
landing
switches,
or
turbulence.
the armature stops the gear almost
instantly.
SYSTEM
optional landing gear safety system functions through the action of a solenoid in the landing gear position switch in conjunction with a three-position safety system switch, a relay and diode, two pressure The
switches mounted wheel well, and throttle position
a
on
the inboard side of the left main
adjacent to the existing engine compart-
microswitch
warning
switch in the
me"t.
Each pressure switch is connected into the pitot and static system. The pressure switch in the gear-up circult is actuated by the pressure differential that exists
pitot and static air system and will close increasing pressure at approximately 90 mph
between the with
IAS. When
speed of 90 mph landing gear position
an
with the
air
IAS has been attained switch in the UP
posi-
tion, the pressure switch in the gear-up circuit closes and actuates
a
relay
mounted
on
the
right-hand
instru-
panel support, thus completing the circuit and retracting the landing gear. A diode locks the relay in ment
position until the retraction cycle is compreceding to occur, the microswitch in pleted. the engine compartment must also be in the open position. This microswitch is actuated by the throttle control when the throttle is advanced sufficiently for the manifold pressure gage to register approximately 18 inches Hg. Conversely, if the throttle is retarded beyond the position corresponding to approximately
the closed CAUTION
Do not
change
switch to
the
position
For the
of the control
the direction of the landing gear while the gear is in transit as this could cause damage to the reverse
retract mechanism.
32-00-00
Page A17
1
Nov 16/94
~echcraft BONANZA SERIES MAINTENANCE MANUAL 18 inches of
Hg
NOTE
in manifold pressure, the microswitch speed has dropped below 120 mph
will close. If the air
IAS at the
The throttle switch is set at the
time the microswitch closes, the resultant pressure differential between the pitot and static system will actuate the pressure switch in the gear-down circuit. When both the microswitch and the same
thus
completing the
to
token, the landing gear will automatically
The
airspeed
following conditions: must have
dropped below
120
mph
IAS.
landing gear position switch is placed in the UP position while the landing gear safety system is in the ON position, the landing gear will retract only when the following conditions are mutually fulfilled: The
airplane must have attained least 90 mph IAS.
an
air
The throttle
enough approximately
must have been
18 inches
retarded
dropped
below
Hg.
safety system switch is a three-position switch normally ON or OFF positions. The switch also contains a momentary or test position for checking that the system is functioning properly. When released from the test position, the switch returns to the ON position.
The
of at
speed
setting
for manifold pressure to have
with
The throttle
ficiently mately 18
same
extend under the
If the
to
the
By
pressure switch close, the current flow through the solenoid will cause the landing gear position switch to
drop into the DOWN position, gear-down circuit.
factory
close when an approximate manifold pressure of 18 inches Hg is produced at about 3000 feet of altitude.
setting must have been advanced sufproduce a manifold pressure of approxiinches Hg.
TROUBLESHOOTING LANDING GEAR ELECTRICAL SYSTEM INDICATION 1. Motor fails to shut off when gear is retracted.
fails to retract.
2.
REMARKS
PROBABLE CAUSE a.
Uplimit
a.
b. Defective switch.
b.
switch not
a.
a.
Saf
b. U 3. Motor fails to shut off when gear
switch is out of
Readjust
switch.
ustment
a.
switch.
switch.
R
limit switch.
b. R
it switch
Downlimit switch does not open.
a.
limit switch.
Readjust
extended. b. Defective Downlimit switch, 4.
Landing
gear actuator is
hitting
a.
Limit switch out of
switch.
b.
adjustment.
a.
working.
c.
limit switch.
Readjust
internal
c.
Dynamic
switch.
b.
b. Limit switch is i brake is not
Check for
brake
rela 5.
Warning
horn
inoperative
or
a.
Open
or
grounded
circuit.
a.
Tri
circuit breaker.
b.t)ownlimit switches open.
7.
Landing gear
extend.
will not retract
or
c.
Open circuit
d.
Landing gear
a.
Bad electrical connection.
motor
inoperative dynamic high resistence in
or
circuit.
Check
continuity.
b. Check and
b. Throttle switches i
fails to extend,
6.
a.
relay
inoperative.
a.
ust as
Reset circuit breaker.
b. Check downlimit switch. The downlimit switch should be closed retracted. with the c. Run a continuity check on the downlimit switch. d. Check brushes, overhaul motor.
or
a continuity check from to switch. breaker circuit a.
Run
32-00-00
Page
2
Nov 16/94
A17
Qeeclact~ft BONANZA SERIES MAINTENANCE MANUAL TROUBLESHOOTING LANDING GEAR ELECTRICAL SYSTEM
(Continued) RENIARKS
PROBABLE CAUSE
INDICATION b.
Landing
gear motor not
b. Check motor
ground.
rounded. c.
Defective control circuit.
d.
Landing
gear motor
inoperative.
c.
Check items 1 thr
3.
d. Check brushes overhaul
or
replace.
32-00-00
Page A17
3
Nov 16/94
Rayllheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
MAIN GEAR AND DOORS
MAINTENANCE PRACTICES
MAIN LANDING GEAR SERVICING Service the main
gear. Refer to
landing
Chapter 12-20-00,
SHOCK STRUTS.
LUBRICATION Lubricate the main wheel
bearings
and grease
fittings. Refer to Chapter 12-20-00,
LUBRICATION SCHEDULE.
MAIN LANDING GEAR REMOVAL When
removing reassembly.
the
landing
gear, take
a.
With the
b.
Disconnect the outboard
c.
Disconnect the inboard
d.
Unsnap
e.
Open
f.
Disconnect the
hydraulic
g.
Disconnect the
safety
h.
Remove the bolt
i.
Remove the
taining
airplane
the
jacks,
landing
cylinder
remove
Remove the brace
k.
Lower the main gear
landing
at the rod-end
original adjustments
gear until the inboard door is in the
door from the
gear door
actuating
landing
fittings
to facilitate
fully open position.
gear strut.
rod at the forward door
uplock assembly
hinge.
from the strut.
bleed ports and pump all fluid from the system. lines where the flexible hose
couples
to the
tubing
on
the
landing
gear.
switch wire. the lift
leg
to the strut.
door in the lower surface of the
the nut. The
j.
to preserve the
and disconnect the
attaching
access
retract the
landing gear
canvas cover
the brake
nut and
on
care
hinge
rear
strut brace
wing leading edge for access to the forward hinge hinge bolt is accessible by lowering the flap.
bolts and associated hardware which attach the main gear to the front and
assembly from the airplane, being careful
not to bend the skin at the
rear
bolt
re-
spars.
edge of the wheel well.
MAIN LANDING GEAR INSTALLA TION a.
Carefully position
the main
landing
gear
assembly
in
place against
b.
Align the hinge bolt holes and install the bushings, bolts, pounds. Install new cotter pins.
the front and
washers and nuts.
rear
spars.
Torque each
nut to 250-690 inch-
NOTE Install 100951-S-016-XF the front and
or
100951-S-032-XF washers
as
required
between the
landing gear and placement of
spars to maintain a maximum total clearance of 0.016 inch. The these washers at the front or rear may help align the lift leg. c.
Install the
d.
Install the bolt
nzl
access
rear
door in the lower
attaching
the lift
leg
wing leading edge.
to the strut.
32-10-00
Ral~heon Aircraft SEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE the nut
Overtightening
on
the bolt that connects the lift
attaching point. Torque
distort the strut
leg to the shock inch-pounds.
strut
can
bind the strut
or
the nut to 25 to 75
landing gearsafetyswitchwire.
e.
Connectthe
f.
Connect the brake
g.
Connect the
line.
hydraulic
uplock assembly to the
strut and snap the
canvas cover
in
place.
CAUTION 1 IcnuTloN The
bolt must be installed with the head of the bolt pointing aft. This is to avoid
uplock cable attach
interference between the bolt and the
stringer
in the main gear wheel well
as
the
landing
gear is
refracted. h.
Connect the inboard Install the outboard
j.
landing
landing
gear door
actuating rod
gear door to the
landing
to the forward door
hinge.
gear strut.
Bleed the brake.
CAUTION I I cnuTlon Excessive
landing k.
operation of
the
gear motor. Allow
Operate the landing
a
landing short
gear motor without proper cooling may cause damage to the time after each extension and retraction cycle.
cooling
gear and check for proper
rigging
of the
uplock
and doors.
MAIN LANDING GEAR OVERHAUL
NOTE Refer to the OVERHAUL AND REPLACEMENT SCHEDULE in maintenance checks of the main
landing
Chapter 5-10-00 for time
limits and
gear.
Experience in the field indicates the points of greatest wear on the main landing gear are the upper and lower bearings in the cylinder assembly. The wear caused on the bearings during takeoff, landing and taxiing tend to result in an oversized condition. The oversized condition of the upper bearing in the cylinder assembly will result in leakage of hydraulic fluid through the upper bearing and O-ring. This will eventually cause fluid to seep down through the felt pad and out the lower bearing. replacement of the scraper ring and all O-rings in the cylinder assembly fails to stop leaks, the oversized condition of the bearings is probable. In such instances the landing gear should be overhauled. The following information will aid in determining the extent of landing gear wear and whether it is possible to overhaul or necessary to replace critical landing gear components. When
Page
32-10-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL MAIN LANDING GEAR ~ISASSEMBLY FIGURE 1
WARNING JW~RNINO)
begin
Do not
any
disassembly
of the main
landing
gear until all air pressure has been
re-
leased.
gear in
vertical
a.
Place the
b.
Release the air pressure from the
c.
To prevent
d.
Remove the main wheel and brake
landing
damage,
a
remove
all
position
to
prevent hydraulic fluid from spilling.
cylinder assembly (9) by depressing
hydraulic plumbing, safety assembly.
Refer to
the valve
core
switch components, and
Chapter 32-40-00,
(2).
clamps.
MAIN WHEEL AND BRAKE ASSEM-
BLY REMOVAL. Remove the retaining ring (5) e. cylinder assembly (9). f.
Invert the
g.
Remove the air valve
landing
and retract the lower shock
gear and drain the
push
the orifice tube
(6)
O-ring (7) from
the orifice tube
(6).
assembly (35)
to
out of the
hydraulic fluid.
assembly (3), O-ring (4), piston ring (8)
and
WARNING IWARNINO) Do not disconnect the torque knees (23 and 34) without first deflating the cylinder assembly (9). The torque knees provide the extension stop for the lower shock assembly, and when disconnected, the shock assembly is free to slide out of the cylinder assembly (9). h.
Remove the nut, washers, and bolt
i.
and
Remove the upper and lower torque knees 31), retaining pins and cotter pins.
j.
Slide the lower shock
(32) connecting
assembly (35)
(23
out of the
and
the upper torque knee
34) by removing
(23)
to the lower
torque knee (34).
the upper and lower torque knee
pins (21
cylinder assembly (9).
CAUTION 1 I cnuTlon The scraper seal (27) may become sharp during normal operation of the gear; ercised to avoid possible injury when removing the scraper seal.
care
should be
ex-
Remove the scraper seal (27), felt pad (26), O-ring and retainer rings (17). The O-ring is located between two retainers within the cylinder assembly (9). Removal of the O-ring may be simplified by using a hook, manufactured
k.
from music wire. Refer to i.
(15) (11).
Disconnect the columns
ings (12)
nn
Figure
from the brace
2.
and brace
(11) from the cylinder assembly (9)
and from each other. Remove bush-
32-10-00
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
I.
AIR
3.
AIR
4.
5. 6. 8. 9. 10. i I
12. 13. 14.
VALVE
O-RINGVALVE COREASSEMBLY VALVE
RETAINER RING ORIFICE TUBE 0-RING PISTON RING CYLINDER ASSEMBLY
BOLT,
CONNECTOR,
BRACE BUSHINGS BUSHING MAIN LANDING BRACE
15. 16. 17.
CAP
3 4
NUT
GEAR
BOLT
7
COLUMN UPPER BEARING
8
O-RING, RETAINER
18.
UPPER LOWER UPPER UPPER
RINGS TOROUE KNEE BUSHING RETAINER RING TORQUE KNEE BORE TORQUE KNEE PIN
9
O
2 .19. POTS,GNIRAEB 20.
21. 23.
A
---n o
24. 25. 26. 27.
UPPER TORQUE KNEE CENTER TORQUE KNEE BUSHING UPPER TORQUE KNEE BORE FELT PAD RETAINER RING/ SCRAPER SEAL
28.
PISTON
29.
(CHROME PORTION) LOWER TORQUE KNEE BUSHING
14
15 i
10
16
1’
’3~7 18
14
4
28
15
30.
31. 32. 33. 34. 35. 36. 37.
OWER TOR~UE KNEE SORE LOWER TORQUE KNEE PIN BOLT, WASHERS, NUT, LOWER TORQUE KNEE BORE LOWER TORQUE KNEE LOWER SHOCK ASSEMBLY BRAZED RETAINING BOLT AXLE
19
1 24
1
21
b
32 34
23
22
11"9 30
DETAIL
A
o
3637 35
DETAIL
B
csarcossPosa c
Main
Dec
32-10-00
31
Landing Gear Assembly Figure 1
A21
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
.Oba
NuiIC
wlR~ i~3/32 BT
P-
14
----1
DOWEL
5/i6
ROD
BRAZED BEARING
O-RING
CYLINDER
~DOWEL
ROD C
C94TC0582194
O-Ring
Removal and Installation
Figure
2
MAIN GEAR CLEANING, REPLACEMENT PARTS AND REPAIRS FIGURE 1
CLEANING Remove all
(16, Chart 1, 91-00-00).
a.
Clean all parts with solvent
b.
Immerse all internal parts in clean
hydraulic fluid (9,
Chart 1,
excess
solvent and
91-00-00) prior
to
wipe dry
after
cleaning.
assembly.
REPLACEE/IENT PARTS FIGURE 1 a.
Inspect all parts
and assemblies for damage
or
Wear which is greater than the allowable
Damage which Screws that Parts that
cannot be corrected
are
are
severely damaged
cracked, chipped
Parts that have corrosion b.
Replace
the
Cotter
A21
following parts
or
or
or
or
excessive
wear
wear.
following conditions are cause for rejection:
tolerances. Refer to Chart 1.
repaired.
have
stripped, severely
worn or
scored threads.
broken.
other defects that cannot be
when main
The
landing
repaired.
gear is overhauled:
pins
32-1 0-00
Dec
23/9 Page
5
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL DU
Bushings (12)
Felt Pad Piston
(26)
Ring (8)
O-Rings (4, 7, 17) Retainer
Safety
Wire
Scraper c.
Replace
Rings (5, 17, 19)
the
Seal
(27)
following parts
on
condition when main
landing
gear is overhauled:
Bearings (16, 19)
Bushings (13, 18, 24, 29) Grease
I
Fittings
Grommets Huck Bolt and Collar
Hydraulic
if removed from the upper
(Replace
bearing (16).)
Hoses
Hydraulic Tubing
Safety
Switch
Valve Core
Components
(2)
Wiring REPAIRS FIGURE 1 a.
Visually inspect castings for cracks
and
wear.
sively b.
and
pitting;
Refer to Chart 1 for tolerances to aid in
worn
pitting, nicks, cracks, distortion Replace all defective and exces-
and finished surfaces for scoring,
determining
the extent of
wear.
parts.
If fluid leaks have been observed
on
top of the air valve assembly (3), check the small O-ring (4) of the valve;
then look for defects in the valve. c.
If the leak is from the
ring (7) d.
All
in the orifice tube
parts
or
junction of the orifice (6).
assemblies may be
Slight scoring
repaired
tube
ii the
of shafts may be corrected
assembly (6)
following
with the
cylinder assembly (9) walls,
check the 0-
conditions exist:
by lapping carefully
with
a
flat oil stone.
NOTE Do not exceed 10% of the
component material thickness when removing nicks, burrs
es.
Page
632-1 0-00
and scratch-
NaylINeMM Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
Smooth minor nicks, burrs and scratches.
Those parts that
plating
as
that removed
Minor thread
scratched
are
be
or
replaced
damage,
or
have
with
new
chase to clean
or
may be
plating
worn
stripped
and
replated
with the
same
type of
parts. smooth.
NOTE
damage requires inspection to determine the depth of penetration and the cross-sectionchange. The damaged area must be thoroughly cleaned and the corrosion must be re(Refer to Chapter 20 for CORROSION MAINTENANCE PRACTICES.) The deterioration by corrosion or removal of corrosion must not reduce the material thickness of any compo-
Corrosion al
area
moved. caused nent
by
than 10%. Refer to Chart 1 for MAIN LANDING GEAR WEAR TOLERANCES AND
more
INSPECTION PROCEDURES
on
components. For additional information contact the Technical Company, P.O. Box 85, Wichita, KS 67201.
Support Department
of
Remove corrosion if
applicable, and apply corrosion prevention materials Type II.
cadmium
plate
Raytheon
Aircraft
as
necessary per MIL-C-5541
or
per Fed QQ-P-416,
Bushings
that check within allowable
When evidence of
damage
wear
tolerances may be reused.
exists to steel parts,
magnetic particle inspect
per MIL-STD-1949.
NOTE Do not remove paint or primer from the area to be fluorescent or dye penetrant inspected per MILSTD-68~6. If the finish absorbs the penetrant so that bleed out prevents satisfactory inspection or if a new finish has not cured for at least 30 days, contact the Technical Support Department of Raytheon Aircraft
Company,
When evidence of
P.O. Box 85,
damage
Wichita, KS 67201.
exists to metal parts other than steel, fluorescent penetrant inspect per
MIL-STD-6866, Type I.
Replace damaged
or
unserviceable parts with
new or
serviceable parts.
MAIN LANDING GEAR ASSEMBLY FIGURE 1
NOTE Prior to
assembly,
immerse all internal parts
(except
felt
pad (26))
in
hydraulic
fluid
(9,
Chart 1,
91-00-00). a.
Install the
O-ring
may be used to work
b.
Soak the felt
and
19).
and retainer
O-ring
pad (26)
rings (17)
bearing (16) of the cylinder assembly (9). position. Refer to Figure 2.
in the upper
and retainers into
in SAE 10W30 oil and install in the
cylinder (9)
between the upper and lower
Slide the scraper seal (27) over the piston (28) and insert the lower shock assembly Work the scraper seal (27) into the lower end of the cylinder assembly (9) until seated. c.
pa~
Two dowel rods
(35)
into the
32-10-00
bearings (16 cylinder (9).
7
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL d.
Install upper torque knee (23) to the cylinder assembly (9) and lower torque knee (34) to the lower shock assembly. (35) using torque knee pins (21 and 31), retaining pins and cotter pins. Install stop (22) to the upper torque knee
pin (21). Insert the center torque knee bushing (24) (32).
and connect the torque knees
(23
and
34) using bolt,
wash-
ers, nut e.
Lubricate
f.
Install
and nut
bearings
bushings (12)
new
(10).
bly fluid). h.
into brace
hydraulic
Install
ring (8)
with grease
(11).
(46, Chart 1, 91-00-00).
Install brace
(15)
(11)
to the brace
onto the
(11)
and
cylinder assembly (9) with bolt, connector cylinder assembly (9) using main landing
(14).
Raise and block lower shock with
fittings
Install forward and aft columns
gear brace bolts g.
at grease
fluid
O-ring (4),
(9,
Chart 1,
valve
core
assembly (35) 1/4 inch from the fully compressed position and fill cylinder assem91-00-00) until the top of piston (28) is covered (approximately 2 pints of hydraulic
(2)
and valve
assembly (3) into orifice tube (6). Assemble the O-ring (7) and piston cylinder assembly (9). Slowly extend lower shock assembly (35) allowing the the cylinder assembly (9), then install retainer ring (5).
to orifice tube and install into
suction to
pull orifice
tube down into
WARNING IWI\RNINO) As with all
forming i.
Inflate the
tube
j.
(6)
operations involving equipment under high pressure, exercise areas directly above and below the strut.
caution when per-
the leak test; avoid the
cylinder assembly (9) to approximately 100 psi using dry air assembly (3) with soap suds and check for air leaks.
or
nitrogen.
Coat the top of the orifice
and air valve
Release the air pressure; clean the
fresh water and
soapsuds off
the
top of the orifice tube (6) and air valve assembly (3) with
wipe dry.
k.
Install air valve cap
I.
Install all
m.
Install main wheel and brake
(1)
to air valve
assembly.
hydraulic plumbing, safety
switch components and
Refer to
assembly.
clamps.
Chapter 32-40-00,
MAIN WHEEL AND BRAKE ASSEMBLY
INSTALLATION. n.
Install main
o.
Service the main
Page
landing
gear to the
landing
airplane.
gear. Refer to
32-1 0-00
Refer to MAIN LANDING GEAR INSTALLATION in this
Chapter.
Chapter 12-20-00, SHOCK STRUTS.
nn~
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHART1 MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES ITEM
I.D.
O.D.
WEAR TOLERANCES AND INSPECTION
PROCEDURES NOTE: Listed below
the tolerances used to
are
determine the extent of
wear
in the main land-
ing gear components. Where pertinent, the permissible wear limits are given for those components. All inside-diameter (I.D.) and outside-diameter (O.D.) dimensions are given in inches. Refer to Figure 1. Lower Shock
Piston
Assembly (35)
(28)
Chrome Portion
Axle
Visually inspect piston (28), axle (37) and brazed retaining bolt (36) wear, damage and corrosion. Any sign of scratches and worn areas which can not be repaired is cause for rejection. Conduct a magnetic-particle inspection per MIL-STD-1949. Any sign of cracking is cause for rejection.
1.602
1.8635
1.593
1.8600
(37)
1.498
1.497
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded. Visually inspect for wear, damage and corrosion. Strip and cadmium plate axle as necessary, per Fed QQ-P-416, Type II, Class 2, on scratched
Upper
and Lower
Knees
(23
and
Torque
or worn areas.
Visually inspect
for wear,
damage and corromagnetic particle inspection MIL-STD-1949. Any sign of cracks,
34)
sion. Conduct per scratches
a
or worn areas
which
can
not be
repaired is cause for rejection. Remove all bushings and inspect bores for corrosion. Replace bushings as needed and cadmium plate per FED QQ-P-416, Type II, Class 2.
Torque 30)
Knee Bore
(20
and
Bushings (18
and
29)
0.6255
Visually inspect
0.6245
sion.
0.5015
Visually inspect for wear, damage and corrosion. if bushings exceed wear tolerances, replace with new bushings. Alignment ream new bushings to specified wear tolerances. Drill out lubricator holes through bushings and
0.4995
Replace
if
for wear, damage and corrowear tolerances are exceeded.
install lubricators.
nnl
32-1 0-00
Dec
23/9 Page
9
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL CHART1 MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES ITEM
I.D.
O.D.
WEAR TOLERANCES AND INSPECTION PROCEDURES
Knee Pins
(21
and
31)
0.4990 0.4980
Visually inspect for wear, damage and corrosion. Any sign of scratches or worn areas which can not be repaired is cause for rejection. If
no
visible
wear
is evident, conduct mag-
particle inspection per MIL-STD-1949. Any sign of cracks is cause for rejection. Replace if wear tolerances are exceeded. netic
Torque Knee Center Hinge Joint
Bore
(Upper) (25)
0.4440
Inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
0.4370
Bushing (24) Bore
(Lower) (33)
0.3150
0.4360
0.3120
0.4330
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
0.3195 0.3125
Orifice
Assembly (6)
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
1.560 1.557
Visually inspect for wear, damage and corrosion. Any sign of scratches or worn areas which can not be repaired is cause for rejection. Check the orifice O.D. does not exceed wear
tolerances. Check that orifice hole does
not exceed 0.187/0.177 inch. Cadmium
plate
necessary except for ring groove in orifice head, per Fed QQ-P-416, Type I, Class 2.
as
Cylinder Assembly (9)
Visually inspect for wear, damage and corrosion. Any sign of cracks, scratches or worn areas which can not be repaired is cause for rejection.
If
fluorescent
no
visible
wear
is evident, conduct
dye penetrant inspection per MIL-STD-6866. Corrosion proof per MIL-C5541 and paint touch up as required.
Internal
Bearings
Page
ceD01
23/99
32-1 0-00
or
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHART1 MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES ITEM
I.D.
O.D.
WEAR TOLERANCES AND INSPECTION
PROCEDURES
Upper (16)
1.8695
1.8650
Visually inspect for wear, damage and corrosion. Replace bearing if wear tolerances are exceeded. If replacement is required, remove the bearing from the cylinder assembly (9) and measure
the O.D.. Select from the O.D. dimen-
sions below to determine the correct ment
replace-
bearing.
2.3225/2.3215 inches, Standard
(P/N 35-815246-13,
Bearing)
2.3345/2.3335 inches, Oversize Bearing)
(P/N 35-815246-23,
2.3425/2.3415 inches, Oversize Bearing)
(P/N 35-815246-25,
If the O.D. dimensions of the
bearing
is greater
than the
replace
replacement dimensions above, the cylinder assembly (9). If additional
information is
required contact the Technical Support Department of the Raytheon Aircraft Company, P.O. Box 85, Wichita, KS 67201. Lower
(19)
1.8695 1.8650
Visually inspect for wear, damage and corrosion. Replace bearing if wear tolerances are exceeded. If replacement is required, remove the bearing from the cylinder assembly (9) and measure
the O.D.. Select from the O.D. dimen-
sions below to determine the correct ment
replace-
bearing.
2.0035/2.0025 inches, Standard Bearing)
(P/N 35-815246-9,
2.0185/2.0170 inches,
(P/N 35-815246-27,
Oversize
Bearing)
If the O.D. dimensions of the
bearing is greater replacement dimensions above, replace the cylinder assembly (9). If additional information is required contact the Technical Support Department of Raytheon Aircraft Com-
than the
pany, P.O. Box 85, Wichita, KS 67201.
32-10100
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL CHART1 MAIN LANDING GEAR WEAR TOLERANCES AN13 INSPECTION PROCEDURES I.D.
ITEM
O.D.
WEAR TOLERANCES AND INSPECTION
PROCEDURES If
replacement of bearing is required, coat bore primer (67, Chart 1,91-00-00) and install
with
new bearing using 91-00-00).
Upper Torque
Knee Attach-
Do not
Instruction Placards
for
Brace Assembly
adhesive
(66,
Chart 1,
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
0.5010 0.4995
ment Hole
an
remove
inspection
purposes
Visually inspect
(11)
sion. Conduct
cylinder assembly except
from
a
or
replacement.
for wear, damage and corrofluorescent or dye penetrant
inspection per MIL-STD-6866. Any sign cracks, scratches be
repaired
is
or worn areas
cause
for
which
of
can
not
rejection.
Hinge Bushings Outer
Inner
Hinge (12) Hinge (13)
0.7192
Replace bearings
0.7184
overhauled.
when main
landing
gear is
when main
landing
gear is
0.6240
Replace bearings
0.6230
overhauled.
0.4395
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
Brace Bores
(14)
Forward Bolt
Bore
0.4370
Center Bolt
(10)
Bore
0.2520 0.2495
Aft Bolt
(14)
Bore
0.4395 0.4370
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
Forward and Aft Columns
(1 5)
Upper and Lower Attachment Forward bores
(14)
0.4395
0.4370 Aft bores
(14)
0.4395
0.4370
Safety
Switch
Components
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded. Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
nents on condition.
Page
ceDP1
23/99
32-10-00
continuity when Replace wiring and compo-
Ensure there is electrical
switch is activated.
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOSE GEAR AND DOORS
MAINTENANCE PRACTICES
NOSE GEAR SHOCK STRUT Se~vice the
nose
gear. Refer to
Chapter 12-20-00,
SHOCK STRUTS.
LUBRICATION Lubricate the
nose
wheel
bearings
and grease. Refer to
Chapter 12-20-00, LUBRICATION SCHEDULE.
NOSE GEAR REMOVAL When
removing the sembly.
gear, take
nose
care
to retain the
original adjustment
a.
Jack the
b.
Disconnect the
drag leg
at its
the
nose
gear brace
c.
Disconnect the
steering
mechanism at the
nose
gear.
d.
Disconnectthe
landing lightwiring.
e.
Remove the cotter
airplane
and
partially
retract the
fitting
on
landing
pins, nuts, washers, bolts,
gear to relieve the load
and
bushings
at the rod end
on
fittings
the retract rod
to facilitate reas-
compression springs.
assembly.
which connect the
nose
gear upper brace to the
wheel well structure. f.
Lower the
nose
gear
assembly
from the
wheel well.
nose
NOSE GEAR INSTALLA TION a.
Carefully position
b.
Align
new
the
nose
bolt holes and install
cotter
gear
assembly against
the
bushings, bolts, washers,
nose
wheel well structure.
and nuts.
Torque the
nuts to 150
200
inch-pounds.
Install
pins. NOTE
Use 100951S016YP washers
between the
nose
gear
(maximum of two per side) assembly and supports.
c.
Connect the
landing light wire.
d.
Connect the
drag leg
of the
e.
Connect the
steering
mechanism to the
nose
gear brace nose
to obtain total end
play
of 0 to 0.015 inch
assembly. gear.
CAUTION I I CAUTION Excessive operation of the landing gear motor without proper cooling may cause damage to the landing gear motor. Allow a short cooling time after each extension and retraction cycle. f.
Operate the landing gear and complete cycles.)
check for proper
rigging
and
nose
gear
adjustment. (Cycle the landing
imum of six
32-20-00
gear
a
min-
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOSE GEAR OVERHAUL
NOTE Refer to the OVERHAUL AND REPLACEMENT SCHEDULE in maintenance checks of the nose gear.
Experience in the field indicates assembly. The forces
the barrel
the
points
exerted
limits and
of greatest wear on the nose gear are the upper and lower bearings in the bearings during takeoff and landing tend to result in an oversized
on
condition. The oversized condition of the upper through the upper bearing and O-ring. This will lower
Chapter 5-10-00 for time
bearing in the barrel assembly will result in leakage of hydraulic fluid eventually cause fluid to seep down through the felt pad and out the
bearing.
When
replacement of the scraper ring and all O-rings in the landing gear fails to stop leaks, the oversized condition bearings is probable. In such instances the landing gear should be overhauled. The following information will aid in determining the extent of landing gear wear and whether it is possible to overhaul or necessary to replace critical landing gear components. of the
NOSE GEAR DISASSEMBLY
FIGURES 1 AND 2
WARNING I WARhllNO) Do not
begin
of the
disassembly
any
nose
landing
gear until all air pressure has been
re-
leased. a.
(1)
Place the strut in
a near
vertical
position
to
prevent the hydraulic fluid from spilling when the air valve assembly
is removed.
b.
Depress the valve
core to
c.
Remove the
wheel. Refer to
d.
Remove the snap
e.
Retract the piston and fork assembly
f.
Remove the orifice tube
g.
Invert the
nose
nose
deflate the strut and
the air valve
Chapter 32-40-00, NOSE
ring (4) retaining
(6).
remove
the orifice tube
(48)
Remove the
gear and drain out the
to
push
WHEEL REMOVAL.
(6).
the orifice tube
O-ring (5)
hydraulic
assembly (1).
and
out of the barrel
(6)
(23).
piston ring (7).
fluid.
WARNING I IWARNINO Do not disconnect the torque knees (37 and 46) without first deflating the torque knees provide the extension stop for the piston and fork assembly
connected, the piston and fork assembly (48) is free to slide h.
Remove the cotter pin
(40),
nut
i.
Remove the cotter pin
(36),
and
j.
Remove the cotter
Page
2~"2f,
(41),
washers
pins (25
pin (50), pins (42
32-20-00
and
and
47),
(39
34)
and
gear. The When dis-
(48). assembly (23).
out of the barrel
44), bushing (45),
and bolt
to disconnect the upper
and washers
nose
(49 and 51)
(43).
torque knee (37).
to disconnect the lower torque knee
(46).
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL and fork
k.
Slide the
i.
Remove the lower snap
piston
assembly (48)
ring (33),
out of the barrel
scraper
(31),
the collar
(23). Remove
Remove the
n.
Remove the nut
brace o.
washers
(30),
washers
(17
and
(3).
19), bushing (18),
and bolt
Removal of the
O-ring
may be
(21) attaching the shimmy damper (20) to the
(15).
Remove the nut
from the barrel p.
(16),
and shim
adapter (32).
and
O-ring (38) and remove the felt pad (24) from inside the barrel (23). simplified by using a hook manufactured from music wire. Refer to Figure 1. m.
(2)
(27
and
29), bushing (28), and
bolt
(26)
to disconnect the
shimmy damper (20)
(23).
Pull the barrel
(23)
out of the brace
(15).
.064 MLISII‘
WIR~ ~I3/32 -i~
DOWEL
E~/
b
ROD
BRAZED BEARING
O-RING
CYLINDER
DOWEL
ROD C94TC05B219d
O-Ring
C
Removal and Installation
Figure
1
NOSE GEAR CLEANING, REPLACEMENT PARTS AND REPAIRS CLEANING a.
Clean all parts with solvent
b.
Immerse all internal parts in clean
A21
(16,
Chart 1,
91-00-00).
hydraulic fluid (9,
Remove all
Chart 1,
excess
solvent and
wipe dry
after
cleaning.
91-00-00) prior to assembly.
32-20-00
Dec
23/99Page
3
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL REPLACEMENT PARTS NGUREP a.
Inspect all parts
and assemblies for damage
or
Wear which is greater than the allowable which cannot be corrected
Damage
Screws that Parts that
are
are
severely damaged
cracked, chipped
Parts that have corrosion
b.
Replace
the
following parts
or
or
or
or
excessive
wear
wear.
nose
following conditions are cause for rejection:
tolerances. Refer to Chart 1.
repaired.
have
stripped, severely
worn or
scored threads.
broken.
other defects that cannot be
when
The
repaired.
gear is overhauled:
Adapter (32)
Bushing(l2) Cotter Pins Felt Pad
Piston
(24)
Ring (7)
O-Rings (5, 38) Safety
Wire
Scraper(31) Snap Rings (4, 33) c.
Replace
the
following parts
on
condition when
nose
gear is overhauled:
Bearings (8, 22) Bushings (18, 28, 35, 45) Grease
I
Fittings
Placards
Valve Core
(1)
REPAIRS NGUREP
Visually inspect castings for cracks and pitting; and finished surfaces for scoring, pitting, nicks, cracks, distortion wear. Chart 1 lists wear tolerances to aid in determining the extent of wear. Replace all defective and excessively worn parts.
a.
and
b.
If fluid leaks have been observed
on
look for defects in the valve.
Page
32-20-00
top of the air valve assembly (1), check the small O-ring of the valve; then
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL c.
If the leak is from the’
orifice tube d.
of the orifice tube
junction
assembly (6)
and the barrel
(23),
check the
O-ring (5)
on
the
(6).
All parts
or
assemblies may be
repaired if
the
of shafts may be corrected
Slight scoring
following
conditions exist:
by lapping carefully with
a
flat oil stone.
NOTE Do not exceed 10% of the component material thickness when
removing nicks,
burrs and scratch-
es.
Those parts that
plating
as
that removed
are
or
scratched
be
replaced
or
have
with
worn
new
plating
may be
stripped
and
replated
with the
same
type of
parts.
Smooth minor nicks, burrs, and scratches. Minor thread
chase to clean
damage,
or
smooth.
NOTE Corrosion al
damage requires inspection to determine the depth of penetration and the cross-sectionchange. The damaged area must be thoroughly cleaned and the corrosion must be re(Refer to Chapter 20 for CORROSION MAINTENANCE PRACTICES.) The deterioration by corrosion or removal of corrosion must not reduce the material thickness of any compo-
area
moved. caused nent
by
more
than 10%. Refer to Chart 1 for NOSE GEAR WEAR TOLERANCES AND INSPEC-
TION PROCEDURES
Department
of
Remove corrosion if cadmium
plate
on
components. For additional information contact the Technical Support P.O. Box 85, Wichita, KS 67201.
I
Raytheon Aircraft Company,
applicable and apply corrosion prevention Type II.
materials
as
necessary per MIL-C-5541
or
per Fed QQ-P-416,
Bushings
that check within allowable
When evidence of
damage
wear
tolerances may be reused.
exists to steel parts,
magnetic particle inspect
per MIL-STD-1949.
NOTE Do not remove paint or primer from the area to be fluorescent or dye penetrant inspected per MILSTD-6866. If the finish absorbs the penetrant so that bleed out prevents satisfactory inspection or if a new finish has not cured for at least 30 days, contact the Technical Support Department of Raytheon Aircraft
Company,
When evidence of
P.O. Box 85, Wichita, KS 67201.
damage
exists to metal parts other than steel, fluorescent penetrant
inspect
per MIL-
STD-6866, Type I.
Replace damaged
or
unserviceable parts with
new or
serviceable parts.
32-20-00
dZ~
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL e.
p,
I.
2. 3. 4. 5.
‘J
6. 8.
2
9. 10. II. 12. 13.
31~9 4
5
--J
AIR VALVE COLLAR
(AS
25
25.
27
~h--t--
36
28. 29. 30. 31.
32. 33. 34.
35. 36 37. 38. 39.
REQUIRED)*
40.
SHIMMY DAMPER BOLT LOWER BEARING BARREL FELT PAD PIN
~4.
26
27.
BOLT BRACE NUT WASHER BUSHING WASHER
15. 16. 17. 18. 19. 20. 21. 22. 23.
b
26.
SHIM *x SNAP RING O-RING ORIFICE TUBE PISTON RING UPPER BEARING COTTER PIN NUT WASHER BUSHING WASHER
23
24
ASSEMBLY
BOLT WASHERS BUSHING WASHER NUT SCRAPER
ADAPTER LOWER SNAP RING PIN BUSHINGS COTTER PIN UPPER TORQUE KNEE a-RING WASHERS COTTER PIN
41. 42. 43. 44. 45. 46. 47. 48.
NUT PIN BOLT WASHER
49.
WASHER COTTER
50. 51. 52.
BUSHING LOWER TOROUE KNEE PIN PISTON AND FORK ASSEMBLY PIN
WASHER
AXLE
29
30 37
38
]C~L "t-- 3 1
329 39
F--
42
33
40
01
1
41
12
4344
i~
15 47
45
t~
46
4950
\o
16 17 18
i
51
5;!
O USE 100951S016YP WASHERS AS REOUIRED PER SIDE TO OBTAIN MAXIMUM TOTAL END CLEARANCE OF .015 INCH. *r
PEEL LAMINATIONS AS NECESSARY FOR OPERATION. MAXIMUM CLEARANCE IS .012
FREEINCH.
22
i,
C94EA3282228
C
Nose Gear
Assembly Figure 2
Dec
32-20-00
A21
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL CHART1
NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES ITEM
I.D.
O.D.
WEAR TOLERANCES AND INSPECTION
PROCEDURES NOTE Listed below
are
the tolerances used to determine the extent of
nent, the permissible
wear
limits
(O.D.) Collar
(2)
wear in the nose gear components. Where pertifor those components. All inside-diameter (I.D.) and outside-diameter dimensions are given in inches. (Refer to Figure 2.)
are
given
Visually inspect for wear, damage and corrosion. Any scratches or worn areas which can not be repaired is cause for rejection. Conduct magnetic particle inspection per MIL-STD1949. Any crack is cause for rejection. Replace
0.3150 0.3120
if
wear
plate
tolerances
as
are
exceeded. Cadmium
necessary per Fed QQ-P-416,
Type II,
Class 2.
Torque and 46)
Knee
Visually inspect for wear, damage and corrosion. Any scratches or worn areas which can
Assembly (37
not be
repaired is cause for rejection. Remove bushing and inspect bores for corrosion. Corrosion proof as necessary per MIL-C-5541. Any crack is cause for rejection. Replace bushall
ing Knee
Upper Torque
as
needed.
(37)
-Bore
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
0.4380 0.4370
Bushing (35)
Visually inspect for wear, damage and corrosion. If bushings exceed 0.3775 inches I.D., replace with new bushings. Alignment ream new bushings to specified wear tolerances. Drill out lubricator holes through bushings and
0.3775
0.3745
install lubricators. Knee Pin
(34)
0.3735
Visually inspect for wear, damage
and
0.3725
sion.
which
scratches
not
Any be repaired
are
exceeded.
corrocan
rejection. If no visible wear is evident, conduct a magnetic particle inspection per MIL-STD-1949. Any crack is cause for rejection. Replace if wear tolerances
Torque Knee
is
or worn areas
cause
for
Center Hinge
Joint Bore
(Upper)
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
0.3150 0.3120
Bushing (45)
na
0.2505
0.311
0.2495
0.310
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
32-20-00
Dec
23/9 Page
7
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL CHART1 NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES ITEM
I.D.
O.D.
WEAR TOLERANCES AND INSPECTION PROCEDURES
Bore
0.3150
(Lower)
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
0.3120
Lower
Torque Knee (46) 0.3775
-Bore
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
0.3745
Knee Pin
(42)
0.374 0.373
Visually inspect for wear, damage and corrosion. Any scratches or worn areas which ~can not be repaired is cause for rejection. If no visible wear is evident, conduct a magnetic particle inspection per MIL-STD-1949. Any crack is cause for rejection. Replace if wear tolerances are
Orifice
Assembly (6)
P/N 35-825195
1.449 1.436
CE-772 thru
(CE-748, CE-979,
CJ-149 thru CJ-155,
D-10097, D-10120 thru D-10396,
exceeded.
Visually inspect for wear, damage and corrosion. Any sign of scratches or worn areas which can not be repaired is cause for rejection. Conduct a magnetic-particle inspection per MIL-STD-1949. Any sign of cracking is cause for rejection. Check the orifice O.D. does not exceed wear tolerances. Check that orifice
E-l 111, E-1241 thru E-1969
hole does not exceed 0.185/0.180 inches. Cad-
EA-1 thru
mium plate as necessary per Fed QQ-P-416, Type I, Class 2.
EA-272)
NOTE: If the orifice exceeds
wear
tolerances,
P/N 36-820021
Orifice
Assembly (6)
P/N 36-820021
(CE-980
and after,
CJ-156 and after, D-10397 and after,
E-l 970 and after, EA-273 and after)
1.449 1.436
assembly
as a
use
P/N 35-825195 Orifice
replacement
Assembly
spare.
Visually inspect for wear, damage and corrosion. Any sign of scratches or worn areas which can not be repaired is cause for rejection. Conduct a magnetic-particle inspection per MIL-STD-1949. Any sign of cracking is cause
for
rejection. Check the orifice O.D. does
not exceed
wear
tolerances. Check that orifice
hole does not exceed 0.142/0.140 inches. Cad-
mium
plate
as
necessary per Fed QQ-P-416,
Type I, Class 2. Barrel
Assembly (23)
Visually inspect for wear, damage and corrosion. Any sign of scratches or worn areas which can not be repaired is cause for rejection. Conduct
a
magnetic-particle inspection Any sign of cracking is
per MIL-STD-1949. cause for rejection.
Bearings
Page
ce23/99 D8
32-20-00
A21
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL CHART1 NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES ITEM
I.D.
O.D.
WEAR TOLERANCES AND INSPECTION PROCEDURES
-Upper
Visually inspect for wear, damage and corrosion. Replace barrel assembly if wear toler-
1.755 1.751
ances are
-Lower
1.755
Visually inspect for wear, damage and corrosion. Replace barrel assembly if wear toler-
1.751
ances are
Upper Torque
Knee Attach-
ment Hole
0.3755
exceeded.
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
0.3745
Piston and Fork
exceeded.
Assembly
(48) Chrome Portion
(topl
1.490
Visually inspect for wear, damage and corrosion. Any sign of scratches and worn areas which can not be repaired is cause for rejection. Conduct a magnetic-particle inspection per MIL-STD-1949. Any sign of cracking is cause for rejection. Replace if wear tolerances
1.482
are
Axle
1.249 1.248
exceeded.
Visually inspect for wear, damage and corrosion. Any sign of scratches and worn areas which can not be repaired is cause for rejection. Conduct a magnetic-particle inspection per MIL-STD-1949. Any sign of cracking is cause for rejection. Strip and cadmium plate axle as necessary, per Fed QQ-P-416, Type II, Class 2
Brace
scratched
or worn areas.
Visually inspect for wear, damage and corrosion. Any scratches or worn areas which can not be repaired is cause for rejection. Remove all bearings and inspect for corrosion. Conduct fluorescent or dye penetrant inspection per MIL-STD-6866. Any crack is cause for rejection. Coat interior of brace and hinge bearing holes with corrosion preventative compound per MIL-C-16173, Grade 1 or 2. Replace all bearings when nose gear is overhauled.
Assembly (15)
Hinge Bushings (12)
on
0.4692 0.4682
Replace bearings when Alignment ream
hauled. fied
wear
nose new
gear is
over-
bearings to speci-
tolerances. Drill out lubricator holes
through bearings
and install lubricators.
Internal Bearings
A21
32-20-00
Dec
23/99Page
9
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHART1 NOSE GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES ITEM
I.D.
O.D.
WEAR TOLERANCES AND INSPECTION
PROCEDURES
Upper
and Lower
(8
and
22)
2.252
Replace bearings when Alignment ream
hauled.
2.250
fied
wear
Do not
gear is
new
bearings
over-
to
speci-
tolerances Drill out lubricator holes
through bearings Instruction Placards
nose
remove
inspection
and install lubricators.
assembly except for replacement.
from brace
purposes
or
NOSE GEAR ASSEMBLY
FIGURES 1 AND 2
NOTE Prior to
assembly, 91-00-00).
immerse all internal parts
Install new O-ring (38) into the upper bearing position. Refer to Figure 1. a.
b.
Saturate felt
c.
Install
d.
Install barrel
(23)
e.
Install shims
(3)
new
pad (24)
scraper
of the barrel
pad (24))
(23).
in
(31), adapter (32)
and
with snap
secure
hydraulic
fluid
(9,
Chart 1,
Two dowel rods may be used to work
with SAE 10W30 oil before installation. Install felt
into the brace
as
felt
(except
pad (24)
in the barrel
O-ring
into
(23).
ring (33).
(15).
necessary.
NOTE Add
or remove
lamination from shims
0.012 between collar f.
Install collar
after
tightening
(2) to
bolts.
(2)
and brace
brace
(15)
Adjust
shims
g.
Install air valve
h.
Install upper torque knee
(3)
as
necessary for free
operation.
Maximum clearance is
(15).
tighten two bolts securing collar. Rotate collar to ensure freedom of movement (3) as necessary to allow collar to rotate freely. Secure bolts with safety wire.
and
valve
assembly (1) excluding (37)
with the
core.
pins (25
and
34),
and cotter
pin (36).
NOTE
(17 and 19) above or below the bushing (18) damper (20) with the lug on the barrel (23)
Install the washers
my
shimmy damper (20)
i.
Position
j.
Install the
k.
Slide the
Dec
bushing (28),
piston
bolt
and fork
and install the
(26),
washer
assembly (48)
32-20-00
bushing (18),
(27
and
29)
into the barrel
bolt
and nut
(21), (30)
on
the brace
washers
(15)
(17
to connect the
and
to
align the
19)
shim-
and nut
(16).
shimmy damper (20).
(23).
A21
Rtylheon Aircraft SEECH BONANZA SERIES MAINTENANCE MANUAL I.
Connect the lower torque knee
m.
Install the
(46)
bushing (45), bolt (43), (37 and 46).
with the
washers
pins (42
(39
and
and
44),
47),
nut
washers
(41)
(49
and cotter
and
51)
pin (40),
and cotter
pin (50).
to connect the upper and
lower torque knees n.
Install
secure
new O-ring (5) and piston ring (7) to orifice tube (6). by attaching snap ring (4) to the top of collar (2).
o.
Lubricate
p.
With the strut in the vertical
assembly (1)
bearings
with
at grease
fittings with
grease
(46,
Push orifice tube
Chart 1,
(6)
down into the barrel
With the
position and approximately 1/4 inch from fully compressed, approximately 500/550 cc of hydraulic fluid (9, Chart 1, 91-00-00).
piston
and fork
assembly (48) compressed,
and
91-00-00).
q. Fully extend and recompress the piston and fork assembly (48) three times or until added. Add additional fluid as required with the strut in the compressed position. r.
(23)
install the valve
core
no
fill
through
the air valve
additional fluid
into air valve
can
be
assembly (1).
WARNING IwnRNI~OI As with all
forming s.
To leak test, inflate the
and air valve t.
operations involving equipment under high pressure, exercise areas directly above and below the strut.
caution when per-
the leak test; avoid the
assembly (1)
approximately 90 psi using dry air or nitrogen. soapsuds and test for air leaks.
nose
with
gear to
Release the air pressure by depressing the valve core in the air valve (2) and air valve assembly (1) with fresh water.
Coat the top of the collar
assembly (1).
Clean the
soapsuds
(2)
from
the top of the collar u.
Install the air valve cap to the air valve
v.
Install
nose
wheel onto the axle. Refer to
w.
Install
nose
gear onto the
x.
Service the
nose
airplane.
gear. Refer to
assembly (1).
Chapter 32-40-00,
Refer to
NOSE WHEEL INSTALLATION.
Chapter 32-20-00,
Chapter 12-20-00,
NOSE GEAR INSTALLATION.
SHOCK STRUTS.
32-20-00
O.Peaileu~
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOSE GEAR SHIMMY DAMPER SERVICING Service the
shimmy damper.
Chapter 12-20-00, SHIMMY DAMPER.
Refer to
NOSE GEAR SHIMMY DAMPER REMOVAL~
FIGURE 2 a.
Remove the nut
the brace b.
(16),
washers
(17
(30),
washers
(27
and
19), bushing (18),
and bolt
(21) which
attach the
shimmy damper (20)
to
(15).
Remove the nut
and
29), bushing (28),
bolt
(26)
and
remove
the
shimmy damper (20)
from
(23).
the barrel
NOSE GEAR SHIMMY DAMPER INSTALLATION FIGURE 2 a.
Install the
barrel
bushing (28),
washers
(27
and
29),
nut
(30)
and bolt
(26) attaching
the
shimmy damper (20)
to the
(23).
bushing (18), washers (17 and 19), nut (16) and bolt (21) attaching the shimmy damper (20) to the nose gear brace (15). For alignment purposes, attach a 100951-X031-YN washer (19) between the damper and the lug on the brace, and a 100951-X031-YM washer (17) under the nut.
b.
Install the
c.
Swivel the
nose
wheel to check the
turning
radius of the strut and for freedom of movement without
gear steering travel inch from maximum travel in both directions.
rough spots. Adjust
the
nose
bolts to stop
adjustment
shimmy damper piston
binding
or
1/32 inch to 1/4
NOSE GEAR SHIMMY DAMPER OVERHAUL
NOTE Refer to the OVERHAUL AND REPLACEMENT SCHEDULE in maintenance checks of the
nose
gear
shimmy bamper.
Chapter 5-10-00 for time
limits and
NOSE GEAR SHIMMY DAMPER DISASSEMBLY
Fli;URE a.
Remove cotter
or screw
b. the c.
3
driver
so
pin (1),
washer
(8)
compression spring (9) by holding the washer (8) spring out when the cotter pin (1) is removed.
and
that the parts will not
floating piston (10) by engaging floating piston (10). Remove the
it with
a
long
6-32
screw or
down with
threaded rod. Remove
Remove the snap ring (2) and piston scraper (3). Force the barrel end (5) out of the barrel rod (12) back and forth. Remove O-rings (4) from the barrel end (5).
a
small rod
O-ring (1 1)
(6) by working
from
the
piston
remaining hydraulic fluid by inverting shimmy damper
d.
Remove all
e.
Remove the snap
f.
Insert
a
the forward
ring (23)
and slide the
piston
rod
(12)
with the
and
pumping
the
remaining parts
piston
rod
(12).
out of the barrel
(6).
long 6-32 screw or threaded rod into the hole at the clevis (24) end of the piston rod (12) and engage floating piston (17). Pull floating piston (17) toward clevis (24) so that the piston retaining pin (15) can
be driven-out.
Dec
23/9 Pagel2
32-20-00
nzl
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL g. Remove the piston retaining and remove O-ring (16). h.
Remove the
O-rings (13)
pin (15)
and
the
push
remaining compression spring (18) damper piston (14).
floating piston (17)
and slide the
out the open end of the
off the
damper piston (14)
piston
piston
rod
(12).
rod
(12)
Remove
from the
i.
Remove
(21)
from the barrel end
remaining
barrel end
(19)
and
piston
scraper
(22)
from the
piston
rod
(12).
Remove
O-rings (20
and
19).
NOSE GEAR SHIMMY DAMPER
CLEANING, REPLACEMENT PARTS AND REPAIRS
CLEANING Clean all parts with
cleaning
solvent
(16,
Chart 1,
91-00-00).
Rinse and
dry thoroughly
after
cleaning.
CAUTION 1 I cnu´•non For
replacement,
use
O-rings approved for use
Lubricate all internal parts with
hydraulic
fluid
with mineral base
Chart 1,
(9,
hydraulic
fluid.
91-00-00) prior to assembly.
REPLACEMENT PARTS FIGURE3 a.
Inspect all parts
and assemblies for damage
or
Wear which is greater than the allowable
Damage
which cannot be corrected
Parts that
are
cracked, chipped
Parts that have corrosion b.
Replace
the
following parts
Cotter Pin
(1)
Retaining
Pin
or
or
or
excessive
wear
wear.
nose
following conditions are cause for rejection:
tolerances. Refer to Chart 2.
repaired.
broken.
other defects that cannot be
when
The
gear
shimmy damper
repaired. is overhauled:
(15)
O-Rings (4, 11, 13, 16, 20, 21) Safety
Wire
Snap Ring (2) Springs (9, 18) Piston
Scrapers (3, 22)
Washer
(8)
32-20-00
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
3
12
9 14 10
16 17
13
I.
2. 3. 4. 5. 6. 7. 8. 9. 10. I I 12. 13. 14. 15.
16. 17. 18. 19.
20. 21
22.
23. 24.
COTTER PIN SNAP RING PISTON SCRAPER O-RINGS BARREL END BARREL ATTACHMENT HOLE WASHER COMPRESSION SPRING PISTON O-RING PISTON ROD O-RINGS DAMPER PISTON RETAINING PIN O-RING FLOATING PISTON COMPRESSION SPRING BARREL END O-RING O-RING PISTON SCRAPER SNAP RING CLEVIS
j 15
FLOATING
19
5~
20 21
23 24
C94E03282874
C
Shimmy Damper Figure 3
Page
ceD41
23/99
32-20-00
A21
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL REPAIRS a.
Visually inspect casting for cracks
and
wear.
sively b.
and
pitting;
Refer to Chart 2 for tolerances to aid in
worn
and finished surfaces for
determining
scoring, pitting, nicks, cracks, distortion wear. Replace all defective and exces-
the extent of
parts.
All parts
or
assemblies may be
repaired
if any of the
of shafts may be corrected
Slight scoring
following problems
by lapping carefully
with
a
exist: flat oil stone.
NOTE Do not exceed 10% of the
component material thickness when removing nicks, burrs and scratches.
Smooth minor nicks, burrs, and scratches.
plating
Those parts that are scratched or have worn plating may be that removed or be replaced with new parts.
stripped and replated
with the
same
type of
as
Minor thread
damage,
chase to clean
or
smooth.
NOTE
damage requires inspection to determine the depth of penetration and the cross-sectionchange. The damaged area must be thoroughly cleaned and the corrosion must be removed. The deterioration caused by corrosion or removal of corrosion must not reduce the material thickness of any component by more than 10%. Refer to Chart 2 for NOSE GEAR SHIMMY DAMPCorrosion al
area
ER WEAR TOLERANCES AND INSPECTION PROCEDURES formation contact the Technical
Support Department
of
on
Raytheon
components. For additional in-
Aircraft
Company,
P.O. Box 85,
1
Wichita, KS 67201. Remove corrosion if cadmium
plate
applicable, and apply corrosion prevention Type II.
materials
as
necessary per MIL-C-5541
or
per Fed QQ-P-416,
Bushings
that check within allowable
When evidence of
damage
wear
tolerances may be reused.
exists to steel parts,
magnetic particle inspect
per MIL-STD-1949.
NOTE Do not remove paint or primer from the area to be fluorescent or dye penetrant inspected per MILSTD-6866. If the finish absorbs the penetrant so that bleed out prevents satisfactory inspection or if a new finish has not cured for at least 30 days, contact the Technical Support Department of Raytheon Aircraft
Company,
When evidence of
P.O. Box 85, Wichita, KS 67201.
damage
exists to metal parts other than steel, fluorescent
penetrant inspect per
MIL-STD-6866, Type I.
Replace damaged
nnl
or
unserviceable parts with
new or
serviceable parts.
32-20-00
I
Raytheon Aircraft SEECH BONANZA SERIES MAINTENANCE MANVUAL NOSE GEAR SHIMMY DAMPER ASSEMBLY FIGURE 3 a.
Replace the O-rings (20 and 21)
rod
(12).
on
the barrel end
(19).
Slide the
piston scraper (22)
and barrel end onto
piston
Replace the O-ring (16) on the floating piston (17) and insert the compression spring (18) and the floating piston piston rod (12). With a long 6-32 screw or threaded rod, engage the floating piston (17) by pulling it toward the clevis (24) so that the retaining pin (15) can be inserted. Install the damper piston (14) on the piston rod (12) and insert the retaining pin (15). Replace the O-rings (13) on the damper piston (14). b.
into the
Insert the
c.
piston
rod
(12)
and components into the barrel
(6)
and
place the
snap
ring (23)
into
position.
(6) in a vise with the open end up and fill the barrel (6) and piston rod (12) with hydraulic fluid 91-00-00). Work the piston rod (12) up and down until bubbles stop appearing in the fluid, then refill the (9, barrel (6) and the piston rqd (12). To eliminate the possibility of an air pocket under the barrel end (5), ensure that the barrel (6) is completely full of hydraulic fluid. Any excess fluid will be forced into the piston rod (12) as the barrel end (5) is inserted. Place the barrel
d.
Chart 1,
e.
Replace
and
secure
f.
O-rings (4) on ring (2).
the barrel end
(5).
Insert the barrel end
piston
scraper
(3)
into the barrel
(6)
piston rod (12) with hydraulic fluid (9, Chart 1, 91-00-00). Engage the floating piston (17) with a 6-32 long pull towards the clevis (24). At the same time, insert and push the floating piston (10) down into the piston (12). This will cause hydraulic fluid to be sucked into the piston rod (12) and preventing the entry of air.
Install compression spring (9), washer (8) and (17) and remove from the assembly. Check the fluid level in the
wire into the
(10)
i.
Install
in this
piston
(12).
shimmy damper on Chapter.
Service the
Page
rod
secure
with cotter
pin (1).
Release the 6-32 rod from the
piston
pin (1) and inserting a 1/16-inch-diameter top of the floating piston (10). If the distance to the piston floating piston (10) and add more fluid to the piston rod (12).
shimmy damper by spreading
the cotter
Measure the distance to the
exceeds 2-3/16 inches,
rod
j.
and
and
g.
h.
(5)
Fill the
screw
rod
the
with snap
remove
nose
shimmy damper
as
the
gear of the
airplane, refer to NOSE GEAR SHIMMY
described under the
32120-00
heading SHIMMY
DAMPER in
DAMPER INSTALLATION
Chapter
12-20-00.
P~21
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHART2 NOSE GEAR SHIMMY DAMPER WEAR TOLERANCES AND INSPECTION PROCEDURES
I.D.
ITEM
O.D.
WEAR TOLERANCES AND INSPECTION PROCEDURES
NOTE
Listed below nents. Where
Barrel
wear in the nose gear shimmy damper compopermissible wear limits are given for those components. All inside-diameter (I.D.) and outside-diameter (O.D.) dimensions are given in inches. (Refer to Figure 3.)
the tolerances used to determine the extent of
are
pertinent,
the
Visually inspect for wear, damage and corrosion. Any sign of scratches or worn areas which can not be repaired is cause for rejection. If localized damage exists, conduct a fluorescent or dye penetrant inspection per MILSTD-6866. Any sign of cracking is cause for rejection. Replace if wear tolerances are
0.865
(6)
0.860
exceeded. Attachment Hole
(7)
Visually inspect for wear, damage and corrosion. Replace if wear tolerances are exceeded.
0.3765 0.3745
Damper Piston (14)
0.857
0.850
Visually inspect for wear, damage and corrosion. Replace if there is any noticeable ridges or grooves at O-ring seats. Replace if wear tolerances are
Floating
Pistons
(10
and
17)
0.240
Visually inspect
0.232
sion. or
(12)
0.253
0.3745
0.246
0.3725
for wear,
damage
and
corro-
Replace if there is any noticeable ridges grooves at O-ring seat. Replace if wear tolerexceeded.
ances are
Piston Rod
exceeded.
Visually inspect for straightness, cracks, scratches, corrosion or worn areas. Any signs of wear which can not be repaired is cause for rejection. Replace if wear tolerances are exceeded.
Clevis
Visually inspect for wear, damage and sion, cadmium plate as necessary per P-416, Type II, Class 2.
(24)
-Bore
-Slot
Visually inspect for
0.190
wear
0.198
Visually inspect for any sign
0.193
Barrel Ends
(5
Hole Diameter
b~
and
any sign of wear. exceeded.
0.196
wear
tolerances
tolerances
corro-
Fed QQ-
Replace
if
Replace
if
are
are
of
wear.
exceeded.
Visually inspect for wear, damage and corrosion. Corrosion proof with coating (53, Chart 1, 91-00-00) as required.
19)
0.379
Visually inspect for wear or damage. Replace
0.376
wear
tolerances
are
if
exceeded.
32-20-00
,%~Pagel7
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOSE GEAR RETRACT MECHANISM SERVICING NOSE GEAR RETRACT BRACE ASSEMBLY CHECK WITH KIT 35-4012-1
(E-1103
AND AFTER; E-l THRU E-1102
INSTALLED)
FIGURE 4
(20), inboard arm (21), attachment bolts (22), washers (23) and nuts (24) for security. Check retract rod rod-ends (58) and (88) for indications of cracking and the mechanism assembly for shear stress, wear and/or corrosion. Refer to Chapter 5-20-00 for scheduled service and maintenance checks. a.
Check outboard
b.
Tighten
arm
any loose hardware and replace all hardware that show area of any corrosion before installing hardware.
signs
of shear stress, wear, corrosion and/
or
cracking. Clean
Dec
32-20-00
A21
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
36
34Z35
31
30
33
32 40 39
38 41~
A
111 20
37
21
38
41 37 41 29 40
28
13
39
22, 23, 24
38
41 38
19
18 14 15
DETAILB
25 11
26
s~//M
8
10 4
7
DETAIL
A
25. BOLT
26. WASHER
3
5~
27.BUSHING
"~r’
28. WASHER 29. NUT J~DOORACTUATOR SHAFT ASSEMBLY
i. RETRACT BRACE ASSEMBLY
13. AFT DRAG BRACE ASSEMBLY
31. SCREW
2. RETRACT DRAG LEG ASSEMBLY
14. DOOR ACTUATOR BRACKET AND PIN SUPPORT
32. NUT
3. BOLT
15.
33. SPRING
5. NUT
SCREW, WASHER, NUT 16. BOLT, WASHER, NUT 17. BOLT, WASHER, NUT
6. COTTER PIN
18. DOOR ACTUATOR PIN ASSEMBLY
36. ROD END
7. LUBE FITTING AND BUSHING
19. BUMPER
37. DOOR ACTUATOR
8. BOLT
20. OUTBOARD ARM
9. BUSHING
21. INBOARD ART
4. WASHER
34. SCREW 35. NUT
ROD ASSEMBLY 38. BALL JOINTS
10. BUSHING
22. DRAG BRACE ATTACHMENT BOLT
39. WASHER
ii. WASHER
23. WASHER
40. NUT
iZ.NUT
24.NUT
41. NUT
EA32B
993~L9AAAI
Nose Gear Retract Mechanism
(E-1103
and
After;
E-1 thru E-1102 with Kit 35-4012-1
Figure
A21
4,
(Sheet
1 of
Installed)
3)
32-20-00
Dec
23/9 Page
19
Rayeheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
42. RETRACT ROD BOOT ASSEMBLY 43. BOOT RETAINING RING 44.STUD 45. CABLE TIE 46. RETRACT ROD BOOT 47.STRIP
48. STUD 49.CABLETIE 50. COVER 51. SCREW AND WASHER
~A
52. RETRACT AFT ROD ASSEMBLY
52
53. BOLT 54. WASHER
55. NUT 56. COTTER PIN 57. TUBE
58.ROOEND 59. NUT 60. WASHER 61. NUT 62. RETRACT IDLER ARM ASSEMBLY 63. BOLT 64. WASHER 65. NUT
71
66. COTTER PIN 67
67. BRACI
1
68. COLLAR 73
69.WASHER
74
70. FLATHEAD PIN 62
71. COTTER PIN
69
T1.IDLERARMa 73. BUSHING 74.8EARINGI
68 70
67 72
75.
9166 64
65
~i i""’ 64
49
45
i
46
4!
H
42
64
43
6’1
Qr~- 55 Q-C~54
57
60~ BL--53
50 48
DETAILA Nose Gear Retract Mechanism
(E-1103
and
After; E-l thru E-1102 with Kit 35-4012-1 Installed)
Figure
Page
ceD02
23/99
3220-00
4.
(Sheet
2 of
3)
A21
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
76. RETRACT FORWARD LINK ROD ASSEMBLY 77. BOLT
78. NUT 79. COTTER PIN 80. ROD 81. PLUNGER ASSEMBLY 82. SPRING 83. SMEAR PIN
84. WASHER
B
85.COTTERPIN
86. NUT
/LiE~-n ~5*11
87. WASHER
76
88. ROD END 89. WASHER
90. WASHER 91. RETRACT ROD LINK DECAL
79
78
i",
88 77
ys,g’ fi
se 87 90
89 so
as
76
DETAIL
82//I
A a;
o-
P DETAIL
B
Q EA32B as34nAA.n,
Nose Gear Retract Mechanism
(E1103
A21
and
After; E-l thru E-1102 with Kit 35-4012-1 Installed) Figure 4. (Sheet 3 of 3)
32-2000
Dec
23/9 Page
21
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
EXTENSION AND RETRACTION
MAINTENANCE PRACTICES
LUBRICATION
landing gear and retract system as detailed in the Lubrication Chart in CATION OF LANDING GEAR UPLOCK ROLLERS in Chapter 12-20-00. Lubricate the
Chapter 12-20-00.
Note LUBRI-
MANUAL LANDING GEAR EXTENSION SYSTEM In the event of landing gear malfunction in flight, the gear may be the front spar between the pilot’s and copilot’s seats.
manually extended by a
hand crank located behind
WARNING i IWdRNING If the
gear’has been
jacks
and
inspected
extended
manually for emergency
before the gear controls
are
airplane must be put normal position.
reasons, the
returned to their
on
CAUTION I I cnvnou Do not attempt to retract the landing gear using the hand crank. The manual extension system is designed to lower the landing gear only. Refer to the appropriate Pilot’s Operating Handbook for
emergency
operating instructions.
landing gear should not be operated electrically with the hand crank engaged. In the event such operation, a teardown and magnetic inspection should be performed to check for damage the engagement slot in the worm shaft of the landing gear actuator. The
of to
LANDING GEAR A CTUA TOR ASSEMBL Y REMO VAL a.
Remove the cabin front seats.
b.
Remove the
c.
Disconnect the main
d.
Remove the
e.
Remove the four
and
move
f.
Disconnect the electrical
access cover on
flap
the switch
landing
motor
top and directly behind the front carry-through
structure.
gear retract rods at the actuator.
attaching
bolts and disconnect the
landing
gear door
screws securing the landing gear limit switch assembly assembly aside to permit removal of the actuator.
wiring
to the
landing
gear motor.
Identify the
on
attaching
rods at the actuator.
the left-hand side of the actuator
wires for
ease
of reinstallation.
CAUTION 1 rCAUTION remove the shaft from the sector gear of the actuator. If the shaft is removed, teardown of the actuator is necessary for reinstallation of the shaft.
Do not
32-30-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE For g.
of reinstallation, note the index marks
ease
Remove the and
landing gear actuator access linkage from the actuator.
ator
arm
h.
Remove the four actuator
attaching
door
nuts and
on
on
the
the bottom of the
remove
arm
and actuator.
fuselage,
and
remove
the
nose
gear actu-
the actuator.
LANDING GEAR A CTUA TOR A SSEMBL Y INSTALLA TION a.
Position the actuator and install the four
b.
Connect the
coincides with the index mark
landing
bolts.
gear rod and linkage to the actuator. Make certain that the index mark the actuator shaft.
landing
nose
attaching
door
the bottom of the
c.
Install the
d.
Connect the
e.
Attach the
f.
Connect the
g.
Connect the main gear retract rods at the actuator.
h.
Install cotter
gear actuator
landing
landing
access
gear motor electrical
gear limit switch door
landing gear
pins
and
on
the
arm
on
safety
fuselage.
wiring.
assembly
attaching
on
to its bracket.
rods at the actuator. Attach the
flap
motor
attaching
bolts.
wire.
CAUTION I I cnlmou
operation
Excessive
landing
of the
gear motor. Allow of
gear system. When minimum of six times.
Check
Cycle
j.
Install the
k.
Install the cabin front seats.
rigging
a
landing gear motor without proper cooling may cause damage P-minute-cooling time after each extension and retraction cycle.
landing
i. tor.
the gear
a
access covers on
cycling
to the
the gear, listen for unusual noises at the motor and actua-
top and directly behind the front carry-through
structure.
LANDING GEAR MOTOR REMOVAL a.
Removethe
rightfrontseat.
b.
Remove the
access
plate
over
wiring. Identify
the motor and disconnect the electrical
the wires for
ease
of
re-
installation. c.
Remove the three
landing gear
motor
attaching
bolts and
remove
the
landing
gear motor.
LANDING GEAR MOTOR INSTALLA TION the actuator and install the
a.
Position the
landing
gear motor
b.
Connect the
landing
gear motor electrical
Dec
23/9Page
2
on
32-30-00
wiring
and install the
attaching access
bolts.
plate
Safety
over
wire the
attaching
bolts.
the motor.
a?l
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL c.
Install the
right
hand seat.
DYNAMIC BRAKE RELA Y CHECK is operated by a split-field, series-wound motor located on the forward side of the main spar carOne field is used to drive the motor in each direction. To prevent overtravel of the gear, a dynamic brake ry-through. into the landing gear circuit and acts as a brake on the motor. When either the up or downlimit is relay incorporated
The
landing gear
switches activate, the relay simultaneously breaks the power circuit to the motor and makes a complete circuit through the armature and the unused field windings, turning the motor onto a generator. The resulting electrical load
applied
to the armature
To check the
dynamic
stops the gear almost instantly.
brake
relay for
proper
it is necessary to
operation,
remove
the spar
cover
to
gain
access
to
the actuator and limit switches.
landing gear with the landing gear handle (either up or down). When the actuator reaches midtravel poappropriate limit switch in the direction the actuator is traveling. The landing gear motor should without stop immediately any noticeable coast.
Actuate the
sition,
actuate the
LANDING GEAR DYNAMIC BRAKE RELA Y REMOVAL a.
Removethe
rightfrontseat.
b.
Remove the
access
plate
which
covers
both the
landing
dynamic brake relay is located slightly outboard to the dynamic brake relay.
c.
The
the
wiring
d.
Remove the two
e.
Remove the
screws
dynamic
which
brake
secure
the
dynamic
gear motor and the
and below the
brake
landing
brake
dynamic
gear motor.
relay assembly to
its
relay.
Identify
attaching
and disconnect
bracket.
relay.
LANDING GEAR DYNAMIC BRAKE RELA Y INSTALLA TION brake
a.
Position the
dynamic
b.
Connect the
wiring
c.
Install the
access cover
d.
Installthe
rightfrontseat.
which
relay
was
which
on
its
attaching
disconnected covers
the
bracket and install the two
during
attaching
screws.
removal.
landing gear
motor and the
dynamic
brake
relay.
MAIN LANDING GEAR RETRACT ROD REMOVAL FIGURE 1 and the
right
front seat.
a.
Remove the
pilot’s
b.
Remove the
access covers
c.
With the
d.
Remove the
attaching
bolts and disconnect the retract rod from the
e.
Remove the
attaching
bolt and disconnect the retract rod from the main
f.
Remove the retract rod
A21
airplane
on
directly
jacks, partially
through
aft of the front retract the
carry-through
landing
spar.
gear until the inboard door is
landing gear landing
fully
open.
actuator retract
arm.
gear V-brace.
the wheel well.
32-30-00
3
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
4
F~Y
i
o
GEAR INBOARD ADJUSTMENT
WHEEL TRAV~L’ V1’"~
GEAR
MAIN GEAR RETRACT RODS
NOSE WHEEL SHIMMY
Q
o~,
(2
O GEAR DOOR L
1C O MAIN GEAR
DOWNLOCK TENSION
.010-.020
E GEAR UP i. UPLOCK UPLOCK BLOCK
SAFETY ~ITCH 36-211--1
Landing Gear System Figure 1
Page
ceD4
23/99
32-30-00
A21
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
MAIN LANDING GEAR RETRACT ROD INSTALLA TION
FIGURE 1 a.
Position the
b.
Install the
c.
Position the main
landing
attaching
gear retract rod in the main
bolt in the main
landing
landing
landing
gear V-brace located in the wheel well.
gear V-brace and the main
gear retract rod in the main
landing
landing
gear retract rod.
gear actuator retract
arm
and install the
attaching
bolts. d.
Install the
access covers
e.
Install the
pilot’s
and the
immediately right
aft of the front
carry-through
spar.
front seat.
RIGGING THE LANDING GEAR Read the entire
landing gear rigging procedure before any attempt to rig the landing gear system. Physically locate reading through the rigging instructions. When any part of the landing gear system requires rigging, recommended that ALL of the rigging steps be accomplished in the order shown.
each item while it is
CAUTION I I cnlmoN Do not the
After the
change the position of the control switch to reverse the direction of the landing gear while landing gear is in transit, as this could cause damage to the landing gear retract mechanism.
airplane
jacks, but before beginning to rig the landing gear, start the retraction cycle enough Apply a sharp load by hand against the nose landing gear strut. Approximately a half to one inch of movement under this load by the main landing gear wheels is a good indication that the landing gear actuator needs to be overhauled and/or adjusted. is
placed
on
to break the downlock tension.
CAUTION I Icnlmou is not sufficient to properly cycle the landing gear during the rigging procedure. A 0.25 volt power supply should be utilized for the landing gear during rigging. If an external power supply is not available on the airplane, jumper cables may be used between the batte~y and
Battery voltage
28.25
the power supply. Be
Excessive
landing Whenever the
the
rigging.
ing
gear is out
operation
sure
of the
polarity before connecting
the power supply to the
battery.
of the
gear motor. Allow
landing gear motor without proper cooling may cause damage a 2-minute-cooling time after each extension and retraction cycle.
to the
landing gear mechanism or doors are removed or disconnected, retract the landing gear and check following procedure for rigging the landing gear was written on the assumption that the entire landof rig.
The
WARNING IWI\RNINO To prevent
possible injury, the emergency landing gear actuator disengaged when operating the landing gear electrically.
nnl
hand crank must
always
32-30-00
be
Ray~heon Aiucraft BEECH BONANZA SERIES MAINTENANCE MANUAL
I CAUTION I Overtightening distort the strut a.
Place the
b.
Lengthen the
airplane
the nut
on
the bolt
jacks
as
instructed in
connecting the drag leg to the shock strut attaching points. Torque the nut to 25 to 75 inch-pounds.
on
main and
Chapter
can
bind the strut
or
7-00-00.
landing gear retract rods sufficiently to prevent excessive tension on the nose gear danger of the V-brace on the main landing gears damaging the skin when the landing gear is retracted. Damage to vital parts may result if abnormal loads are applied to the landing gear retract system. By lengthening the main and nose gear retract rods, such danger is removed. nose
retract rods and to eliminate the
c.
Insert the
d.
Disconnect the
uplock
may
Lengthen
e.
f. the
arm
landing
the
landing
pointing
aft.
uplock cables at the brackets, leaving the springs attached. If the springs are disconnected, the damage the wing skin upon retraction of the gear. Place the uplock block in the lower position. nose
Disconnect the nose
gear retract arm/retract rod attach bolt
landing
nose
gear retract rod.
landing
gear door
linkage
at the
gear door links from the upper ball
attaching point
on
the
nose
landing
gear door. Unscrew
joint.
Remove the bolts attaching the main landing gear outboard door links at the main strut. Remove the actuator g. rod to the inboard main landing gear door by unscrewing from the inboard rod ends and removing the bolt in the door bracket. h.
Screw the stop bolts into the main gear V-brace
assembly
until
approximately
four
or
five threads
are
showing.
CAUTION I ICAUTlON When
running the landing gear electrically before the switches are reset, or for the first time after resetting the switches, run the landing gear with extreme care to make sure the switches open the electrical circuits before the sector gear hits the internal stops in the gearbox. The sector gear should not be touching the stop when the motor stops. Serious damage may result if the internal stops are hit by the sector gear. When checking the dynamic brake system, actuate one of the limit switches and the motor should stop immediately. On
airplanes with a 5-amp push-pull landing gear control circuit breaker, use this circuit breaker to "bump the landing gear. On earlier airplanes without the damp push-pull circuit breaker, manually operate the limit switches and use the 30-amp landing gear motor circuit breaker to ’Ibump" the landing gear. When using the 30-amp circuit breaker, use extreme care because the dynamic brake is inoperative. i.
Run the gear about two thirds up, then stop and "bump" the landing gear the remaining distance to either the setting or to the internal stop by intermittent operation of the LDG GEAR circuit breaker. With the actuator
limit switch
in the retracted
ators)
Dec
23/9Page
before
6
position, check that the
reaching
hand crank will rotate 1/8 to 1/4 turn
the internal stop of the actuator.
32-30-00
(5/8 to
3/4 turn
on
new, or white actu-
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE A
new
by
airplanes as a spare. The new actuator may be identified the upper actuator arm, and the upper and lower actuator housing. When actuator is installed as a spare on earlier airplanes, the actuator should be adjusted by us-
actuator may be installed on earlier
white epoxy
paint
on
the
new
ing
the 5/8 to 3/4 hand crank turns
after the motor has
remaining
stopped.
If this clearance is not
obtained, adjust the uplimit switch. To adjust the uplimit switch, lower the landing gear 5/8 to 3/4 turns of the emergency hand crank, and adjust the switch by turning the screw in the actuator in or out to increase or decrease travel so that it
just breaks the circuit.
Extend the landing gear and check the hand crank. There should be 1/8 to 1/4 turn (or 5/8’ to 3/4 turn on the new j. (or white) actuators) between the extended position and the internal stop. The downlimit switch adjustment is accomplished by bending the switch actuator arm tab so that it just breaks the circuit. On newer actuators, there is an adjustment screw for use when adjusting the downlimit switch.
NOTE On
airplane
serials CE-959 and after, CJ-156 and after, D-10380 and after, E-1879 and after, and slightly slower than on previous serials because the
EA-247 and after, the landing gear will retract motor used runs slower in the retract cycle. Allow 2 minutes of k.
cooling
time between each extend and retract
Extend and retract the
namic brake is
landing operating correctly.
cycle
gear two or three times to assure that the switches are correctly set and the Check the hand crank each time to ensure proper adjustment.
dy-
NOTE It may be necessary to make a closer setting of the limit switches, but there should never be less than 118 of a turn (5/8 of a turn with the new (or white) actuators) on the hand crank in either the
extended
or
retracted
position.
Adjust the main landing gear retract rod (either right or left) to maintain a minimum of 1/16-inch clearance between the joint (knee) of the V-brace and the lift leg and the top wing skin with the landing gear fully retracted. The main landing gear should retract only far enough to clear the inboard door while maintaining the minimum clearance of 1/16-inch. To decrease the clearance between the knee and the top wing skin, shorten the retract rod; to increase clearance, lengthen the retract rod. i.
m.
When the proper setling is obtained, leave the landing gear in the retracted position and screw the upper stop against the main strut. To assure a firm seating, insert a O.OOSinch feeler gage under the bolt head and
bolt down
adjust
the bolt until
gage removed,
a
firm, steady effort is required
screw
the bolt down
an
to
pull
the feeler gage from under the bolt head. With the feeler Tighten the locknut securely.
additional 3/4 turn.
NOTE Refer to service instructions No. 0448-211, Rev, 1, entitled Landing Gear Mechanism installation of Uplock Roller Lubricating Bolt Assembly. n.
Check the
uplock roller for free
movement and
a
Main Gear Retract
maximum clearance of 0.010 to 0.020 inch between the roller
uplock block. If this clearance is not correct, the uplock block must be adjusted. To adjust, loosen the block retaining bolts and adjust the clearance between the roller and the uplock block. The uplock bracket and the block
and the
are
bar
serrated and the serrations must be interlocked.
32-30-00
7
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL o.
Extend the
landing
gear and attach the
uplock
cable to the bracket.
CAUTION i IcnuTloN The attach bolt
uplock cable must be installed with the head of the bolt pointing aft. The bolt position to avoid interference between the bolt and the stringer in the wheel landing gear is fully retracted. on
the
must be installed in this
well when the Retract the
landing gear intermittently as in step i and observe the locking action of the uplock bracket. Starting is an indication that the uplock cable is too tight. The cable should be adjusted for a tension of 52.5 10 0 pounds in the up position. The tension is adjusted at the outboard end of the cable. If sufficient adjustment is not obtainable at the cable eye, additional adjustment may also be made at No. 3 wing rib by moving the cable housing inboard or outboard.
p.
to lock too
soon
Extend the landing gear and check the force required to deflect the main landing gear knee joint. With the landgear in the down position, it should take 45 to 60 pounds of force to deflect the knee joint. To increase tension, add 100951S063XP washers under the inboard end of the spring as required. Maintain a total minimum gap of 0.06 q.
ing
inch between the
spring coils. (The
total gap is the
of all the gaps between the
sum
coils.)
NOTE If unable to obtain
adequate spring tension, check for worn spherical bearing in the retract linkage. spherical bearing has the effect of shortening the entire linkage, causing the rod end spring to compress and stack, leaving nothing for spring adjustments. New bushings will shorten the linkage, again permitting adjustment of the spring. Wear in the
A minimum of 55 on
the 1.
wheels 2.
nose
pounds of deflection force is required at the union of the V-brace and the drag leg assembly landing gear in the fully down position. To obtain the required force, adjust as follows:
gear with the
Lower the
clearing
landing
gear to
just
short of the
fully
down
position
with
no
tension
on
the V-brace and with the
the floor.
A maximum of three 100951DD064XM washers may be added to the end of the
spring
on
the forward
re-
tract rod.
3.
If the additional washers did not
retract rod may be 4.
After the
adjusted (shortened
adjustment,
provide the required minimum deflection force, the rod lengthened) to obtain the required deflection force.
end
on
the forward
or
check that the retract
spring
does not stack at any
point during
full travel of the
nose
gear.
CAUTION I ~cnuTloru Do not adjust the rod end bearing out more than nut and the end of the threads on the rod end
maximum of 0.25 inch
as
measured between the
landing gear in the fully retracted position and the landing gear doors disconnected, a force of 30 pounds applied downward at the center line of the tow pin shall be required to move the strut off the bumper. If this force is not obtained, adjust the rod ends on the aft nose gear retract rod. With the nose wheel in the fully
s.
With the
a
bearing.
nose
to 35
Page
32-30-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL retracted
.quired
to
position move
and both doors
the strut 0.12 inch
fully rigged, a minimum force of 20 pounds, applied as noted above, (at the tow pin) measured along the line of force application.
shall be
re-
landing gear on the outboard door to ensure that the door is not damaged when retracted. Connect outboard door linkage and retract landing gear slowly, checking to ensure that clearance is maintained between the door and the landing gear. After checking to see that the door is not too tight, run the landing gear down and adjust the linkage as required; continue this procedure until a snug, firm fit is obtained when the door is completely closed.
t.
Unscrew the
attaching
link of the main
landing gear inboard door linkage, retract the landing gear slowly and check for clearance linkage and the root rib. Run the landing gear to the 3/4 extended position and adjust to maintain 114 inch of maximum clearance between the tire and the inboard door with slack removed from the door linkage. Continue this procedure until the door closes tightly in both the up and down positions. Adjust doors by varying the length of the push-pull linkage rods. Disconnect the rods at the clevis fittings to make this adjustment. u.
Connect the main
between the door
CAUTION I cnlmolll Install the pushrod attaching bolt for the main landing gear door in the door linkage bracket with the head to the aft. If installed wrong, the bolt may catch on the fuselage skin and root rib of the wing, causing damage to the landing gear retract mechanism or preventing the landing gear from retract-
ing. landing gear door linkage and rig the nose door. Check closely to see that the right hand aft Adjust the nose landing gear doors by varying the length of the push-pull linkage rods in the hinge nose wheel well. With the landing gear retracted, the doors should have a slight tension on them from the actuator rods to keep the doors from vibrating.
v.
Connect the
nose
clears the tire.
landing gear safety switch for the proper adjustment on the right and left main landing gear. Measure the piston from the bottom of the shock strut cylinder and mark the piston with a piece of tape Detail D). Raise the wheel with a small jack, compressing the shock strut, until the tape is even with the (Figure 1, lower edge of the cylinder. Adjust the switch actuating arm at the clevis so the switch is actuated as the tape touches the end of the cylinder. Remove the small jack from the wheel. Pull Landing Gear Motor circuit breaker. Disconnect the left safety switch operating arm at the torque link and position to simulate an "on ground" position. Select "Gear Up", check for audible warning. Select "Gear Down". Connect the safety switch operating arm. Repeat the process with the right landing gear safety switch. On airplane serials CJ-180 and after, CE-1301, CE-1307 and after, E-2458, E-2468 and after and EA-488 and after, check the landing gear retract-prevent switch for proper operation per Chapw.
Check the
314 inch down
on
ter 32-60-00.
Check the landing gear position lights. The lights are mounted on the sub panel. Three green lights, one for each gear, are illuminated whenever the landing gears are down and locked. The red light illuminates any time one or all of the landing gears are in transit or in any intermediate position. All of the lights will be out when the gears are up and locked.
x.
y.
Recheck the
light
switch
adjustment.
CE-1307 and after, CJ-180 and after, E-2458, E-2468 and after, EA-488 and after, check the throttle retract-prevent switch for proper operation as instructed in Chapter 32-60-00.
airplane serials CE-1301,
z.
On
aa.
Safety
p~l
all bolts,
tighten
all lock nuts and
remove
the
airplane
from the
jacks.
32-30-00
Dec
23/9 Page
9
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
RETRACT ACTUA TOR DISASSEMBL Y FIGURE 2
safety wire and remove the bolts (34) and washers attaching the retract housing (35). Remove the spur and pinion gear (2) from the landing gear motor.
a.
Cut the
b.
Remove the snap
c.
Remove the cotter
actuator drive shaft
ring (3),
(7).
Remove the snap
e.
Remove the cotter
f.
the lower
and the woodruff
h.
Cut the
upper
(25)
and the
actuator retract arm
a
from the
(28)
to the upper actuator
worm
from the actuator drive shaft
spanner wrench,
the
remove
screws
remove
remove
(15)
and washers
the retainer nut
(17)
and
attaching
remove
the
the
the actuator
from the upper and lower actuator
bearings (26)
safety wire and remove actuator housing (35).
Using
key (39)
(1)
gear shaft
pin, nut, washers, support plate (37), snap ring (5) and the actuator retract arm (6) Push the shaft out of the actuator assembly in the direction of the arrows.
housings. Caref ully separate both housings and stop assembly (32) and the spacer (33).
Remove the seal
j.
(4)
pin, nut, washers and bolt (9). Cut the safety wire and actuator housing (36) to the upper actuator housing (35).
g.
i.
drive gear
Index mark both
tor gear
the
worm
ring (27) and the
d.
attaching
the
motor
(8)
screws
and washers
sector
worm
and
housings (35
gear shaft
from the
(7).
the hand crankshaft
worm
(19).
(1 0),
the
36).
housing (16)
(19)
sec-
to the
in the direction of
arrows.
Remove the cotter
gear shaft
(19)
and
pin
and loosen the locknut
remove
the
bearing (20)
k.
Remove the
I.
Remove the seal
m.
Remove the
(22)
and the locknut
and the
bearing (29)
(21) enough
to enable the
bearing (20)
to slide down the
worm
split bushing (18). (21)
bearings (23
and the grease fill
from the
and
24)
worm
gear shaft
from the upper
plug (30), with
(19).
housing (35).
the ball check
(31),
from the upper actuator
housing
(35). n.
Remove the
screw
(11),
washer and the nut
attaching
the actuator hand crank
(12)
to the
engaging
shaft
(38)
for the hand crank. Remove the spacer (13) and the O-ring seal from the hand crank shaft housing (16). o.
Page
32-30-00
(14)
from the hand crank
engaging shaft (38)
and
remove
the shaft
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
14. O-RING SEAL 15. SCREW
16. HAND CRANKSHAFT HOUSING 17. RETAINER NUT
5\
18. SPLIT BUSHING
r\
19. WORM GEAR SHAFT
10‘d~6’;
20. BEARING
ri’"
21. LOCKNUT
SEAL
.2GNIRAEB
23.
24. BEARING
~Zh
25. SEAL
,19
26. BEARING 27. SNAP RING 39
28. ACTUATOR RETRACT ARM
30
11\
29. BEARING 30. GREASE FITTING PLUG 35
3~
31. BALL CHECK
N~q
SECTC)R GEAR STOP ASSEMBLY 26
34
33. SPACER 34. BOLT
~h
35. UPPER ACTUATOR HOUSING
36. LOWER ACTUATOR HOUSING
a~
32
aI 1. MOTOR
37. UPPER LANDING GEAR
SUPPORT PLATE ~o
33
J
25
2. SPUR AND PINION GEAR 26
23
38. HAND CRANK ENGAGING
SHAFT AND SPRING
22
’9\
39. WOODRUF KEY
3. SNAP RING
4. WORM DRIVE GEAR 5. SNAP RING 6. ACTUATOR RETRACT ARM 7. ACTUATOR DRIVE SHAFT
8.SCREW 9. BOLT
10. ACTUATOR WORM SECTOR
11. SCREW 12. ACTUATOR HAND CRANK
27
13. SPACER
Landing
Gear Actuator
Figure
A21
Assembly
2
32-30-00
Dec
23/9 Page
11
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
RETRACT ACTUA TOR CLEANING AND PARTS REPLACEMENT with PD680 solvent
(16,
Clean all
parts
sive
Check all gears for cracks, chips, missing teeth, nicks and wear. Check the Replace all worn or damaged parts and seals during assembly.
Chart 1,
91-00-00).
Check all
bearings
and
wear.
damage.
bushings for cracks and exceshousing for cracks, wear and
RETRACTACTUATOR ASSEMBLY FIG URE 2 a.
thread the locknut
(21) on the worm gear shaft (19) and slip the bearing (20) on the shaft with the shield toward the slotted end of the worm gear shaft. Install the split bushing (18) on the shaft and tightbearing the locknut ~21) against the bearing (20) and install a new coffer pin.
Fully
side of the en
NOTE Cut the ends of the coffer the cotter
pin ends tightly
pin
so
across
Install the
bearings (23
and
c.
Install the
bearing (29)
in the upper actuator
d.
Slide the
gear shaft
(19)
protrude beyond the locknut (21). Bend
the nut.
b.
worm
24)
that 0.12 to 0.19 inch will
and the seal
(22)
into the upper actuator
housing (35).
housing (35).
into the upper actuator
housing (35)
in the
opposite
direction of the
arrows.
CAUTION I cnlmohll Do not e.
ring
the seal
Lubricate the threads of the retainer nut
in the upper actuator
f.
damage
housing (35)
with
a
(22)
(17)
while
with
a
installing
light coating
the
worm
gear shaft
of thread lube
spanner wrench. Stake the nut in three
Place the hand crank engagement shaft and seal (14).
spring (38)
(19).
(43, Chart 1, 91-00-00) places.
in the hand crank shaft
housing(l6)
and install
and install the O-
housing (16) in the mounted position. Maintain a clearance of 0.001 to 0.015 inch beengaging shaft (38) and the worm gear shaft (19) with the worm gear fully seated in its thrust bearing in the direction of the arrows. Coat the mating surfaces of the hand crank housing (16) and the upper actuator housing (35) with sealer (44, Chart 1, 91-00-00) and secure with screws (15) and safety wire. g.
Position the hand crank
tween the hand crank
NOTE To maintain the
spacer h.
Dec
specified clearance, the actuator hand crank (12)
may be added
or
Position the actuator hand crank
with the i.
(1 3)
screw
Install the
23/9Page
12
(11),
may be faced off and/or additional
removed.
(12)
and the spacer
(13)
on
the hand crank
engaging
shaft
(38)
and
secure
washer and nut.
bearings (26)
and the seals
32-30-00
(25)
in the upper and lower actuator
housings (35
and
36).
nal
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE Coat the outside diameters of the seals
j.
the double tooth of the
Align
drive shaft
(7).
Install the
spline
(25)
sealing compound (45, Chart 1, 91-00-00).
of the actuator retract
the shaft with the snap
arm on
with
arm
(28)
with the space
on
the
spline
on
the actuator
ring (27).
NOTE If the
landing gear retract actuator is to be installed in the airplane, the retract actuator arm (28) and the snap ring (27) should be sacked and tied until after the installation of the landing gear actuator in the airplane. Slide the actuator drive shaft
k.
stall the spacer
I.
Align
tuator
(7)
into the lower actuator
housing (36)
actuator
to the arrows. In-
the space of the spline on the actuator drive shaft (7) with the double center tooth of the sector (10). Install the actuator worm sector (10) on the shaft.
mating surfaces, and the machined surfaces where the housings (35 and 36) with sealer (44, Chart 1, 91-00-00).
Insert bolt
n.
opposite
spline
of the
ac-
worm
Coat the
m.
in the direction
(33).
(9) through
the lower actuator
housing (36)
and
bolt
position
(9)
is installed,
on
the sector gear stop
the upper and lower
assembly (32)
over
the
bolt.
Align the index marks made during the disassembly, and position the upperactuator housing (35) housing (36). Install washers and screws (8) and safety wire.
o.
over
the lower
actuator
Install the washer and nut
p.
on
the bolt
(9)
and
tighten. Secure
the nut with
a new
cotter
pin.
the space of the spline of the actuator drive shaft (7) with the double tooth of the spline on the actuator retract arm (6). Install the arm on the shaft with the snap ring (5). Install washers, upper landing gear support plate
Align
q.
(37),
nut and a new cotter
Install the woodruff Install the
s.
(2)
worm
pin.
key (39)
in the
(4) on the worm housing (35), making
drive gear
in the upper actuator
keyway
of the
worm
gear shaft
(19).
snap
ring (3). Install the spur and gear shaft (19) with the sure the teeth engage those of the worm drive gear (4).
pinion
Lubricate that portion of the upper actuator housing (35) containing the spur and pinion gear (2) and the drive gear (4) with approximately one ounce of MIL-G-81322 grease (46, Chart 1, 91-00-00). Fill to within 0 inch of the housing center line.
t.
u.
Install the retract motor
v.
Lubricate the actuator assembly,
When
properly filled,
the upper actuator
the oil level
Install the ball check
w.
on
(31)
housing (35)
with bolts
(34)
and washers, and
gear
worm
0.10
safety wire.
through the grease fill port, with one half pint of grease (47, Chart 1, 91-00-00). dip stick inserted through the filler port will be approximately 1/4 inch.
on a
and the grease fill
plug (30)
in the upper actuator
housing (35).
LANDING GEAR RETRACTACTUATOR FUNCTIONAL TEST To
proper operation and break-in of the actuator, the to installation of a newly overhauled actuator in the
ensure
with
p~zl
prior
following airplane.
functional test
procedure
must be
32-30-00
complied
Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
Operate the landing gear retract actuator for five retract and extend cycles with the actuator mechanically loaded an equivalent of 20 amps in both directions. The motor terminal voltage shall be maintained at 28 0.03 volts.
to
The stop distance of the dynamic brake, as measured in revolutions of the hand crank, must not vary from the total maximum-to-minimum stop distance by more than 1/16 of a revolution. The noise output shall not deviate and frequency.
After the functional test
excessively from the
have been
procedures
average of other
performed, place
a
accepted
actuators in
functional test stamp
respect
to
approximately
amplitude
1.5 inches
inboard of center line of the lubrication fill hole.
LANDING GEAR SAFEN SYSTEM MAINTENANCE AND ADJUSTMENT No maintenance is required for the landing gear safety system, other than replacing defective units or checking the electrical wiring for condition, security of attachment, and tightness of electrical connections. The switches are preset and adjustment will not normally be required; however, should the system fail to function properly, the following checks and
adjustments
may be
accomplished.
CHECK OF LANDING GEAR SAFETY SYSTEM WITH SAFETY SWITCH IN TEST POSITION a.
Place the throttle in the closed
b.
Place the
battery
or
retarded
master switch ON. The
position.
landing
gear circuit breaker may be either IN
or
OUT.
Place the
landing gear safety system switch in the momentary fully up (test) position. Noise or movement of the landing gear position switch indicates that the automatic landing gear extension part of the system is functioning properly. The on-off switch returns normally to the ON position unless the pilot intentionally places the switch in the OFF position. c.
solenoid in the
LANDING GEAR SAFETY SYSTEM MICROSWITCH ADJUSTMENT
FIGURE 3 The microswitch cannot be must
be
ascertained
accurately adjusted on the ground. the throttle warning horn
Before the
that
switch
is
safety system microswitch is adjusted, it properly adjusted. See ENGINE-
COMPARTMENT-LOCATED LANDING GEAR WARNING SWITCH ADJUSTMENT LANDING GEAR WARNING SWITCH ADJUSTMENT in this
chapter for
switch. The
as
safety system
microswitch may then be
ters
airplane in flight, mark the approximately 18 inches of Hg.
b.
With the
a.
With the
it
airplane
just
as
c.
Adjust the
was
on
the
when the mark
ground, was
move
the throttle until the mark
cam
airplane
was
setting
or
PEDESTAL-LOCATED
of the throttle
warning
horn
follows:
throttle control at the control
made while the
microswitch until the
adjusted
proper
in
panel when
on
the manifold pressure gage
the control is
aligned
with the control
regis-
panel
flight.
clicks the switch closed with the throttle in the
position indicated
in the pre-
ceding step. LANDING GEAR SAFETY SYSTEM PRESSURE SWITCH ADJUSTMENT
The pressure switches are preset and will not normally require adjustment. Because of the built-in tolerance of these switches, they should not be tampered with unless radically out of adjustment, that is unless the switch in question fails to actuate at an airspeed within 2 mph above or below the setting recommended for it. Even then the system
plumbing and electrical wiring should be checked improper adjustment of the pressure switches.
Dec
32-30-00
to ascertain that the source of trouble is not
something
other than
an
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL a.
Placetheairplane onjacks.
b.
With the master switch ON, the
landing
OFF, advance the throttle to its maximum c.
Place the
landing
d.
Place the
landing gear position
e.
Clamp
a
gear
safety position
gear circuit breaker ON, and the
warning
gear
circuit breaker
position. switch in the ON
switch in the UP
section of soft rubber hose
landing
over
the
position.
position.
pitot head inlet, making certain
f.
Crimp the end of the tubing and roll it up until the airspeed indicator registers retracting immediately if the pressure switch is properly adjusted.
that the connection is
90
mph.
The
landing
airtight.
gear will start
CAUTION ICAVTIONI To avoid
rupturing the diaphragm of the airspeed indicator,
tubing must be
the rubber
g. If the landing gear failed to retract in the preceding step, turn the master switch OFF and switch (upper switch of the two installed in the left main wheel well) as follows: 1.
Secure the rolled up
2.
Connect
a
tubing
so
that it will hold the
airspeed
indicator
reading
continuity tester across the contacts of the pressure switch, mph´•reading on the airspeed indicator.
at 90
rolled slowly.
adjust
the pressure
mph.
then turn the
adjustment
screw
until
the switch closes at the 90 h.
Turn the master switch
cure
i.
the
tubing
so
that the
and roll up the rubber tubing until the airspeed indicator will hold that reading. on
airspeed
indicator
registers
130
mph,
then
se-
Retard the throttle.
Slowly bleed off pressure until the airspeed indicator registers j. ately if the pressure switch is properly adjusted.
120
mph.
k. Should the landing gear fail to extend, turn the master switch OFF and of the two in the left main wheel well) as follows: 1.
Secure the rolled up
2.
Connect
a
tubing
so
that it will hold the
airspeed
The
landing
adjust the
indicator
reading
continuity tester across the contacts of the pressure switch, mph reading on the airspeed indicator.
gear will extend immedi-
pressure switch
at 120
then turn the
(lower switch
mph. adjustment
screw
until
the pressure switch closes at the 120 I.
n21
Turn the master switch ON and check the
landing gear safety system through
the
complete cycle
of
operation.
32-30-00Pagel5
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
THROTTLE CONTROL SHAFT THROTTLE WARNING HORN SWITCH
THROTTLE WARNING HORN SWITCH
1
THROTTLE CONTROL SHAFT
OQ
Ig P
LANDING GEAR SAFFPI SWITCH THAN EA-1 AND AFTER)
(SERIALS OTHER
1
8
LOPTIONAL LANDING GEAR SAFETY SWITCH
(EA-1 AND AFTER)
35-223-5
Landing
Gear
Safety System
and Throttle
Figure
Dec
23/9Page
16
32-30-00
Warning
Horn Microswitch
3
A21
QeechcraR BONANZA SERIES
MAINTENANCE MANUAL
WHEELS AND BRAKES AND OPERATION
DESCRIPTION
piston housing forces the two brake linings against the rotating brake assemblies. The pistons are sealed against leakage with O-rings.
tons in the
MAIN WHEEL ASSEMBLIES The
airplanes
are
equipped
SHUTTLE VALVE
with two Cleveland 6:00 X
Each wheel consists of wheel half held
inner and outer
an
together
magnesium
with bolts, washers, and nuts.
The cup bearings for the inner halves and cone bearings for the outer wheel halves, as well as seals, are installed in the hub assemblies
are
area
of the wheels. The brake disc
bolted to the inner wheel half. A snap wheel
ring is used on each side of the complete assembly to retain the bearings and seals. NOSE WHEEL ASSEMBLY The
airplane is equipped with nose wheel assembly. The
nose
wheel consist of
slum wheel half held
an
a
x
cone
lining MUST be replaced before the metal exposed through the abrasive surface. backplate This can be checked visually without disassembling
The brake
is
inner and outer magneand
assembly has an inner bearing assembly, outside of wheel
and outer cup a felt grease seal with
which is
a ring grease seal on each side of the felt seal. A snap ring is used on each side of the complete wheel assembly to retain the bearings and seals,
th, brake. The minimum allowable thickness for the abrasive surface is 3/32 inch above the rivet. The
brake disc should be measures.450 inch.
I,,,,i,,l the brakes disc will color
as
assume a
the result of heat. These
normal and need not be
a cause
appearance of the brake
changes for
light
straw
incolor
concern.
A
are
glazed
also is normal; the the effectiveness of the
linings
brakes.
The main wheel tires
on
the
airplane
7:00 X 6
are
tires. An inflation pressure of 33 to 40 should be maintained on these tires.
tube-type
wheel tire
nose
tube-type
the
on
airplane
is
5:00 X 5
a
tire. An inflation pressure of 40 on the tire.
psi
psi
should
be maintained
HYDRAULIC BRAKE SYSTEM Fill the fluid reservoir, located
BRAKE ASSEMBL Y
(Figure
The
1
A Cleveland brake
assembly
is installed
on
each main
wheel. The brake assemblies with MIL-H-5606
are designed for use hydraulic fluid (9, Chart 1, 91-00-00).
Each Cleveland brake
assembly contains
a
piston
pistons. The brake assembly contains a pressure plate, a lining, and a backing plate with a brake lining. The brake assembly torque plate is attached to the flange of the wheel axle. Braking action occurs when hydraulic pressure to the two piswith two
on
the forward side of
the firewall, to within 1-1/2 inches of the tap and maintain a visible fluid level on the dip stick at all times by
adding MIL-H-5606 hydraulic 00) as necessary.
housing
when its thickness
replaced
glaze actually improves
TIRES
The
dual brakes are plumbed in series without a shuttle valve. The parking brakes may be set with either the pilot’s or copilot’s brake pedals on the new system.
5
together with bolts, washers,
nose
serials CE-839 and after, CJ-150 and after, D-10209 and after, E-1432 and after, and EA-3 and after, the
BRAKE WEAR AND WEAR LIMITS Cleveland 5:00
nuts.
Each side of the
airplanes with dual brake systems, the earlier airplanes (prior to CE-839, CJ-150, D-10209, E-1432 and EA-3) use a shuttle valve in the hydraulic plumbing of each brake. The shuttle valve prevents the presSU’e from flowing from one master cylinder through the opposite master cylinder of the same brake. At On
6 main wheel assemblies.
hydraulic
brake system is
fluid
(9,
Chart 1, 91-00-
operated by depressing
the pilot’s rudder pedals to compress the piston rods of the attached master cylinders. The hydraulic pressure resulting from the movement of the master cylinder pistons is transmitted through flexible hoses and fixed aluminum
tubing
to the brake disc assemblies
landing gear. This pressure forces the brake pistons to press against the linings and the disc of the brake assembly. Upon release of mounted
each main
against the piston, the brakes disc will tendency to drag against the stationary liners.
pressure a
on
have
32-40-00
Page 1 A17
Nov 16/94
BONANZA SERIES MAINTENANCE MANUAL
f~hff,
INLET
A--LINING
RIVETSTORQUE
PLATE
INSULATOR
OUTLET
BRAKE MASTER CYLINDER
DISC
DETAIL A
i(/
PRESSURE PLATE PISTON
CY\-\Nt3ERS
BRAKE ASSEMBLY
DErAI1 C PARKING BRAKE VALVES
DETA1L B
BRAKE RESERVOIR
PARKING BRAKE VALVES
jj PRESSURE LINE
BLEEDER HOSE
i (I SOURCE OF COMPRESSED AIR FOR PRESSURE BLEEDING
C
PRESSURE POT C94CE32B1990
Brake
System Figure 1
32-40-00
Page
2
Nov 16/94
A~7
Beecbcraft BONANZA SERIES MAINTENANCE MANUAL TROUBLESHOOTING BRAKE SYSTEM
1. Solid
pedal
no
REMARKS
PROBABLE CAUSE
INDICATION
Brake \inings allowable limits
brakes
a.
worn
beyond
a.
Replace linings.
brake.
a.
Air in
a.
Bleed brake
3. Unable to hold pressure.
a.
Leak in brake system.
a.
Visually
2.
b. Defective master 4. Parki
brake will not hold.
a.
a.
Stones or brake disc.
grab
a.
b. A
parking
b. Check master
cylinder.
Air in
Warped
foreign
or
matter
locking
bent disc.
hydraulic lines, the parking brake is parking brake handle. This
closed
Clean brake disc and
b.
Replace
linings.
disc.
NOTE While Beech Aircraft Corporation cannot recommend the use of recapped tires, tires retreaded by an FAA approved
by pulling
closes the valve
repair
station with
a
specialized
service-
limited rating per TSO-C62e may be
and retains the pressure in the brake lines. The parking brake is released when the parking brake handle
pushed in. The optional dual brake system provides the hydraulic breaking action from the copilot’s position as well as the pilot’s position.
seals
valve.
a.
brake valve is installed under the floor-
boards, forward of the pilot’s seat. After the pilot’s pedals have been depressed to build pressure in the out the
cylinder
Bleed brake
b. R
brake valve.
b. Defective 5. Brakes
check entire brake for leaks.
used.
is
MAIN WHEEL AND BRAKE ASSEMBLY REMOVAL a.
WHEELS AND BRAKES
MAINTENANCE
PRACTICES
Place the
Smooth wheel abrasions, nicks and burrs with a fine file and retouch with zinc chromate primer and a\umi-
ters
or
backplate assembly.
hydraulic line, and remove the cylinder assembly by sliding the two guide pins out ,f the torque plate. c.
Disconnect the brake
NOTE
slightly due to shock loads during landings. Normally, this growth is balanced by wear so
Removal of the wheel only does not necessitate disconnection of the line.
wear,
Tires in service grow
tread
the
to
excessive
there is
no
increase in tire diameter.
Remove the cotter pin, wheel retaining nut, washer and spacer. Slide the wheel and inner spacer d.
off the axle. e.
Corporation cannot recommend the use of recapped tires. The tires may pass the retraction test when first installed; however, recapped tires have a tendency to swell after use and may cause malfunctions of the retract system or damage the landing gear doors. Beech Aircraft
jacks.
Remove the four bolts which attach the brake backplate and inner linings to the cylinders, then
prevent corrosion. Replace any damwheel aged parts. Replace tires showing breaks, blis-
lacquer
num
on
b.
remove
WHEEL AND TIRE MAINTENANCE
airplane
The brake disc
removing
assembly can join the
the six bolts which
be removed
by
wheel halves.
NOTE
linings and cylinder assembly removing the wheel by utilizing steps a, b, and c.
The brake can
be removed without
32-40-00
Page A17
3
Nov 16/94
aeechcraft BONANZA SERIES MAINTENANCE MANUAL MAIN WHEEL INSPECTION AND
Inspect the brake disc assembly for cracks, g. excessive wear, or scoring, rust and corrosion. Remove rust and blend out small nicks with a fine
CLEANING
I
-´•I´•´• WARNING
emery cloth. The brake disc should be its thickness measures .450 inch.
I
Inspect the wheel bolts for cracks, corrosion damage. Replace any cracked bolts.
h.
dry cleaning solutions are toxic and volatile, use in a wellventilated area, avoid contact with skin or clothing and do not inhale the
BRAKE ASSEMBL Y INSPECTION AND
CLEANING
vapors,
Clean
a.
Degrease parts and dry bristled brush may be used to all
thoroughly. remove
or
other
Because
a.
replaced when
A soft
hardened
O-rings
in clean
91-00-00) aged or excessively or
hydraulic fluid (9, Chart 1, O-rings are damshould be replaced. they
denatured alcohol. If worn
grease, dust, and dirt. CAUTION
1
t
Do not
spin
the
pressed
air
this will
as
bearings cause
with
Gasoline and dry cleaning fluids are unsuitable as cleaning agents because they will damage O-rings.
com-
damage.
b. Visually inspect bearing cups and cones for nicks, scratches, water stains, galling, heat discoloration, roller wear, cage damage, and cracks Replace if damaged or worn.
Inspect
or
distortion.
inspection,
Inspect wheel halves for cracks, corrosion and other damage. Cracked and badly corroded castings should be replaced. Small nicks, scratches or pits can be blended out using fine (400-grit) sandpaper. e. Inspect snap rings and grease seals for deterioration and wear; replace if damaged or deformed. Lightly saturate the felt seals with 10W30 oil (remove
by pressing lightly). Coat
diameter with
same
the sides and outer
type of grease
as
that used
on
and greasy surfaces with denatured
Inspect entire brake assembly for cracking, nicks, corrosion, damaged threads, etc. Check cylinder walls for scoring or excessive wear. Carefully inspect pistons for nicks or burrs which might damage the O-rings. Remove nicks and burrs with fine crocus cloth, then thoroughly clean. e.
be ets.
MAIN WHEEL AND BRAKE ASSEMBLY
INSTALLA 710N a.
f. Inspect bearing cups for looseness, scratches, pitting, corrosion, or evidence of overheating. Coat the bearing cups with bearing grease. Repack with either Aero Shell No. 5 Chart 1,
or
other greases per MIL-G-81322
91-00-00).
Inspect all brake iinings for cracks. Linings should replaced if they are worn 3/32 inch above the riv-
the
bearing,
(46,
dirty
d.
d.
excess
Clean
c.
the wheel
bearing grease for contamination and solidification at each periodic maintenance c.
b.
alcohol.
Clean and
repack wheel bearings
as
indicated in
MAIN WHEEL INSPECTION AND CLEANING in this
chapter. Replace
any damaged grease seals, and be the grease seal retaining rings and snap rings in place before reinstalling the wheel.
sure are
b.
Install inner spacer, wheel, outer spacer, washer, retaining nut and cotter pin.
NOTE least one 100951X100VY or 100951X050VY washer shall be installed between the outer spacer and wheel retaining nut to permit free rotation of the wheel At
Aero Shell No. 5 grease is not compatible with other greases covered by MILG-81322. Use one
only Aero Shell No. 5 of the other greases; do not mix.
or
32-40-00
Page
4
Nov 16/94
A17
aeechcraft BONANZA SERIES MAINTENANCE MANUAL c.
Install the brake
the two guide
cylinder assembly by inserting pins into the torque plate.
roller wear, cage damage, and cracks Replace if damaged or worn.
NOTE If the torque plate has been removed, it should be reinstalled so that the guide pin holes are positioned aft and centered above and below the horizontal centerline of the axle. The torque plate nuts are
to be
c.
Torque the axle 1.
d.
and
retaining
nut.
rough threads Apply bearing grease or
on
the axle
to the axle
threads and the 2.
While
retaining nut the bearings 3.
4.
bearing surface of the nut. rotating the wheel, tighten
to 180 to 240 are
properly
seated.
Back off the axle
retaining nut to nut with fingers to
Retighten the bearings.
the axle
to ensure that
zero
torque,
remove
end
5.
Torque
the axle
ing position and install
retaining
the cotter
Inspect
wheel halves for cracks, corrosion, and
Inspect the snap rings and grease seals for deterioration and wear; replace if damaged or deformed. Lightly saturate felt seals with 10W30 oil (remove excess by pressing lightly). Coat the sides and outer
e.
diameter with the
same
bearings.
f´•
Inspect the bearing cups
scratches, pitting, corrosion,
b.
Remove the cotter
nose
nut to the next
key-
pin.
c.
Remove the
nose
on
and cones for looseness, or evidence of overheat-
CAUTION
pin, nut, and bushing assembly on the axle. wheel
that used
UIUTlOhl( Aero Shell IVo. 5 grease is not compatible with other greases covered with MIL-G-81322. Use only Aero Shell No. 5 or one of the other greases; do not mix.
wheel.
retain the nose wheel
as
cups and cones with bearing grease. Aero Shell No. 5 grease or other with either Repack MIL-G-81322 (46, Chart 1, 91-00-00), greases per
NOSE WHEEL REMOVAL Jack the
type grease
the
Bleedthebrake systemif necessary.
a.
grease for contaminaperiodic maintenance
ing. Coat the
in the
play
e.
inch-pounds
distortion.
other damage. Cracked or badly corroded castings should be replaced. Small nicks, scratches, or pits can be blended out using fine (400-grit) sandpaper.
nut as follows:
Check for burrs
bearing
the wheel
or
inspection.
pounds. d.
Inspect
tion and solidification at each
to 100 to 140 inch-
torqued
Visually inspect bearing cups and cones for nicks, scratches, water staining, galling, heat discoloration,
b.
which
assembly by sliding
it off
the axle.
Inspect the wheel bolts for cracks, corrosion g. other damage. Replace any cracked bolts.
NOSE WHEEL INSPECTION AND
CLEANING
or
NOSE WHEEL INSTALLATION WARNING
Clean and repack wheel bearings as indicated in NOSE WHEEL INSPECTION AND CLEANING in this chapter. Replace any damaged grease seals, and be a.
Dry cleaning
solutions are toxic and volatile. Use In a well ventilated area, Avoid contact with skin or clothing. Do not inhale the vapors. a.
Degrease all parts and dry thoroughly,
bristle brush may be used to grease, dust, and di~.
remove
sure
are
snap
rings
NOTE a
soft A bushing is permanently installed on the inboard end of the axle. No other hardware is required between the wheel and the inboard end of the axle.
hardened
CAUTION
b. Do not spin the bearings with compressed air. This will cause damage.
retaining rings and place before reinstalling the wheel.
the grease seal
in
Install the wheel, outer spacer,
cotter c.
retaining
nut and
pin.
Torque the axle
nut as follows:
32-40-00
Page A17
5
Nov 16/94
BONANZA SERIES MAINTENANCE MANUAL 1. Check for burrs or rough threads on the axle and retaining nut. Apply bearing grease to the axle threads and bearing surface of the nut,
While
2.
retaining bearings
rotating
nut to 150
the
properly
are
3.
Back off the axle
4.
While
retaining
locking
If not at
5.
a
retaining
cylinder
master
hydraulic
and mark the lines to
lines at each
assure
correct
reinstallation.
d.
Remove the master
nuts and
remove
cylinder attaching cylinder.
bolts and
the master
BRAKE MASTER CYLINDER nut to
zero
torque.
INSTALLA TION
wheel, retorque the axle
inch-pounds
nut to 30
ment of the
inch-pounds
to insure that
Disconnect the two brake
seated.
the
rotating
wheel, tighten the axle
the
200
c.
and check for
align-
a´•
Place the
pedal
holes.
locking position, continue tightening locking locking position and
the axle nut to the first install the cotter pin.
b´•
cylinder in position beneath the attaching bolts and nuts.
brake
and install the
Connect the two
hydraulic
lines to the
cylinder.
The inlet port is the upper port. c.
Replenish
the
hydraulic fluid
and bleed the brake
system.
RELINING THE BRAKES
d.
Install the floorboard and floor mat.
BRAKE MASTER CYLINDER LINKAGE ADJUSTMENT Do not have the while
parking brake engaged
removing the
pedals
Remove the four bolts that attach the to the cylinder assembly.
a.
backplate
assembly
NOTE The
hydraulic
brake line does not have remove the brake
to be disconnected to
linings. b.
backplate
assemblies from the
inboard side of the brake disc and seperate the pressure plate assembly from the cylinder assembly. Place the
backplate assembly
on a
lining facing down and punch or-drill attach the linings to the backp\ate. d.
The
linings
by using plate.
the
Place the
e.
on
the pressure
same
new
procedure
linings
on
firmly against
f.
The rivets
using
the
the
table with the
out the rivets that
a
as
the
used
be removed
on
the back-
backplate and install punch until the lining
backplate.
the pressure plate may be set by procedure as used on the backplate.
on
same
BRAKE MASTER CYLINDER REMOVAL a.
Close the
ing
brake handle.
b.
Unsnapthe
parking
brake valve
floor mat and
section below the brake
by pulling
remove
pedals,
DISASSEMBL Y
(Figure 2) a.
the
park-
thefloorboard
Remove the snap ring (1) and pull the assembled out of the brake cylinder (2).
piston b.
plate may
the rivets. Set the rivets with the is
to
BRAKE MASTER CYLINDER
Remove the
c.
linkage adjustment will adjust the brake straight upright position. This is considered the best adjustment since it will prevent the pedals from hitting the firewall in their extreme forward position. Linkage adjustment is obtained by removing the clevis from the rudder pedal and turning the clevis on or off the piston rod as required. After both pistons are adjusted to the same length, tighten the jam nuts.
The proper
brakes,
Remove the clevis
(3)
from the
piston (14) and the (5), piston
this will free the washer
(4); guide bushing (6), retainer O-ring (7) washer (8) from the piston (14). check nut
c.
Remove the cotter
pull
the collar from the
d.
Remove the cotter
of
pin (9) from piston.
and the
the collar
rear
seat
(10)
and
pin (11) from the plunger end piston (12). The return of the cylinder with the piston
to free the flow lock
piston spring (13)
will fall free
removed.
BRAKE MASTER CYLINDER CLEANING
AND PARTS REPLACEMENT Clean all parts with PD680 Solvent (16, Chart 1, 91-00-00). Check all parts for cracks, corrosion, distortion and wear. Replace all washers and seals at
32-40-00
Page 6 Nov 16/94
A17
Qeechcraft BONANZA SERIES MAINTENANCE MANUAL
reassembly. Lubricate all parts with MIC-H-5606 hydraulic fluid (9, Chart 1, 91-00-00) prior to assembly. Reassemble the cylinder. BRAKE MASTER CYLINDER ASSEMBLY
(Figure 2) a.
Place the return
b.
Slide the flow lock
spring (13)
piston (14) through the piston and
end of the
c.
in the brake
piston (12),
cylinder.
into the
plunger pin (11)
and install the cotter the flow lock
piston.
Place the collar
cotter
(10) on the piston and place pin (9) through the collar and piston,
the
(8), retainer O-ring (7), piston guide bushing (6), and washer (5), on the piston (14). Install the check nut (4) and clevis (3) on the piston. d.
Install the
rear
seat washer
e.
Slide the assembled
piston into snap ring (1).
(2).
Install the
the brake
cylinder
b.
Remove the f\oorboards forward of the
pilots
seats. screw in the cable attach fitting cable and adjust the housing through the mounting of travel between the cable inch 1-1/2 block to obtain the attach fitting. The 1-1/2 inch clearhousing and the parking brake valve with made be ance should
c.
Loosen the set
lever in the OPEN
position.
mounting block, insert the cable in cable attach fitting, tighten and safety wire the screw in the attach fitting.
d´•
e.
Tighten
the
Test the
parking
brake
parking
the set
adjustment by pulling the operating the brake ped-
brake handle out and
als. If the brake pedals are not solid, place the parking brake control in the OFF position and recheck the rig-
f.
ging. Inspect the g. loss.
parking
brake valve for
hydraulic fluid
PARKING BRAKE VALVE REMOVAL a.
Bleed the brake system of all
b.
Remove the floorboards forward of the
copilot’s
PARKING BRAKE VALVE DISASSEMBLY
hydraulic fluid. pilot’s and
seats.
Disconnect he parking brake cable from the parking brake valve by loosening the set screw and pulling the cable free of the cable attach fitting. Disconnect and cap the hydraulic lines from the parking brake valve. Identify hydraulic lines for ease of
d.
installation. Remove the attach bolts, and
remove
the valve.
Place the
parking
brake valve in
the floorboards, forward of the seats. Install the attach bolts. b.
Connect the
which c.
they
were
Connect the
ing brake
as
MENT in this
hydraulic
position under
pilot’s
lines to the
and
ports from
brake cable.
Adjust
the
park-
covered in PARKING BRAKE ADJUST-
chapter.
Bleed the brake system.
e.
Install the floorboards forward of the
pilot’s-and
seats.
Place the
parking OPEN) position.
each of the two
Disconnect and remove the retaining b. from the end of the cam lever assembly (4).
ring (10)
assembly (4) by grasping lever assembly counterrotating clockwise while pulling outward to prevent scoring of the cam lever assembly surface. c.
Remove the
cam
lever
the
cam
PARKING BRAKE CLEANING AND PARTS
brake control in the OFF
Clean all parts with PD680 Solvent (16, Chart 1, 91-00-00). Check all parts foy cracks, corrosion, distortion and wear. Replace all washers and seals at reassembly. Lubricate all parts with hydraulic fluid (9, Chart 1, 91-00-00) prior to assembly. Reassemble the parking brake valve.
PARKING BRAKE VAL VE ASSEMBL Y a.
PARKING BRAKE ADJUSTMENT a.
remove
from the valve
REPLACEMENT same
d.
copilot’s
copilot’s
removed.
parking
Disconnect and
side
the lever and
PARKING BRAKE VALVE INSTALLATION a.
side-bythe Remove body. fittings (13) seal ball steel (2), O-ring (8), (6), O-ring (7), spring (1), and pin (3) from each of the two orifices from which the fittings were removed. a.
e.
e.
(Figure 3)
Install the
cam
lever
(4)
(valve
with the
new
O-rings (9)
clockwise while
rotating by grasping pushing inward to prevent scoring of assembly surface the lever and
the cam lever
32-40-00
Page 7 A17
Nov 16/94
~;)eechcraR BONANZA SERIES
MAINTENANCE MANUAL b.
Connect the
cam
lever
retaining ring (10), assembly (4).
to the end of the
Install the pin
(3), seal (2), O-ring (8), steel ball spring (1) in each of the two side-by-side fit(6), orifices on the valve body. Install an O-ring (7), on ting each fitting (13), and install the fittings. c.
and
BLEEDING THE BRAKE SYSTEM
WARNING
Whenever the brakes
are
to
be
released, make sure the airplane is on level ground and the wheels are checked.
Use only MIL-H-5606 hydraulic fluid (9, Chart 1, 91-00-00) in the brake system, and ensure that no dirt or foreign matter is allowed to get into the brake system. Dirt under seals results in leaks or clogging of the
c0mpensating ports in the master cylinders resulting in brake locking. Beech Aircraft recommends the use of a pressure pot for bleeding the brakes. 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 method 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 in the master cylinders.
instance, the system must be further checked for leak-
"spongy" after the bleeding operation, trapped in the brake cylinders. Remove the brake assembly and 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 bubbies. When air bubbles no longer appear at the port, install the brake and repeat the bleeding proce-
age.
dure.
If the brakes feel soft
Brake system bleeding will be required whenever the system is opened at any point between the master
cylinder
and the wheel brake
assembly,
whenever the
brakes become spongy in service, or whenever the parking brakes will no longer hold. In the latter
16
7
or
air is
14
12
10
2
456
i’1’1 3
15
1
7. RETAINER O-RING
8. REAR SEAT WASHER
9. COTTER PIN
B
10. COLLAR 1. SNAP RING
11. COTTER PIN
2. CYLINDER
12. FLOW LOCK PISTON
3. CLEVIS
13. RETURN SPRING
4. CHECK NUT
14. PISTON
WASHER
15. O-RING
5.
6. PISTON GUIDE BUSHING
16. VALVE SPRING
Brake Master
Figure
Cylinder 2
32-40-00
Page
8
Nov 16/94
A17
aeechcraft BONANZA SERIES MAINTENANCE MANUAL
I
GRAVITY BLEEDING
Depress the pilot’s corresponding brake pedal slowly and smoothly to eliminate air trapped in the b.
WARNING
.mpedal etsy sdna depressed position
I
in the
Hold the
.c.ylbmessa
close the bleeder port at the brake Whenever the brakes are to be released, make sure the airplane is on level ground and the wheels are checked.
d.
Release the brake
e.
Repeat steps
bleeding
is done from the master
pedal.
through
d until
no more
bubbles
appear in the drained fluid. f.
This method of
a
cyl-
Open the bleeder port of the brake assembly on landing gear and repeat steps b through e.
the other
inder down to the brake
assembly. The brake fluid kept full during the bleeding operation. Since the pilot’s and copilot’s master cylinders are plumbed in series (except on EA-1 and EA-2), the entire system is bled by operating the pilot’s brake pedals in the following manner:
NOTE
reservoir must be
On serials prior to CE-839, CJ-150, D-10209, E-1432 and EA-3, the copilot’s master cylinder will have to be bled separately. Repeat steps a through f for the
NOTE Make
provision hydraulic fluid. Open
a.
one
the bleeder
landing
for
catching
port
copilot’s
brakes.
the bleeder ports of the brake assemblies.
g.
Tighten
h.
Check the brake reservoir fluid level and add
the drained
of the brake
assembly
on
gear.
hydraulic fluid MIL-H-5606 (9, Chart 1, 91-00-00) required to obtain a full reading.
i.
as
Spring
2. Seal
3. Pin
i
4. Cam Lever
/i
7.
,d,s
8.
9.
9
,2
C!
10.
11
-i11.
Assembly
O-Ring O-Ring O-Ring Retaining Ring Roll Pin
60222´•lA
Parking Brake Figure 3
Valve
32-40-00
Page A17
9
Nov 16/94
~eechcraft BONANZA SERIES
MAINTENANCE MANUAL
TO BRAKE
TO BRAKE
i. RESERVOIR 2. SHUTTLE VALVE 3..PARKING BRAKE VALVE 4. MASTER CYLINDER
Brake
C93EA3280011
System Plumbing Figure
with Shuttle Valves 4
32-40-00
Page
10
Nov 16/94
A17
~eechcraR BONANZA SERIES MAINTENANCE MANUAL
~Ba
.1BRAKE REDNILYFLUID C RESERVOIR
2. MASTER
3. PARKING BRAKE VALVE
SINGLE BRAKE SYSTEM
1
I’
v
j
Ifi-I i
iX
~wi \´•-h,)) 1.1
DUAL BRAKE SYSTEM
35-21924
Brake System Plumbing without Shuttle Valves
Figure
5
32-40-00
Page 11 A17
Nov 16/94
aeec~craft BONANZA SERIES MAINTENANCE MANUAL i.
Check the brakes for proper operation. When the brake pedals are depressed, there must be no spongy feeling and the pedal pressure equal on both brakes.
PRESSURE P0T BLEED(NG
(Figure 1)
k.
Remove the bleeder hose from each
i.
Close the bleeder port of each brake
Connect the fluid reservoir m. ervoir.
supply
landing
gear.
assembly.
line to the
res-
hydraulic fluid reservoir and add MILhydraulic fluid (9, Chart 1 91-00-00) as required to obtain a full reading. Check the
n.
H-5606
I -´•I´•´•I WARNING
Install the cap
o.
operation of the brakes. There must be feeling at the brake pedals and the pedal pressure must be equal on both brakes. Check the
p. Whenever the brakes are to be released, make sure the airplane is on
level ground and the wheels checked.
the reservoir.
on
no
soft
or
spongy
are
ELECTRIC BLEEDING
hookup for electric bleeding is nearly the same as pressure pot bleeding except the pressure pot bleeder is,,placed with an electric bleeder (refer to Figure 1).
The Pressure
bleeding
is the most efficient method of
bleeding the brakes. This procedure involves attaching a pressure pot to the brake assembly bleeder port and back bleeding the system to the fluid reservoir. a.
Remove the cap from the brake fluid reservoir.
b.
Remove the brake fluid from the reservoir.
c.
Disconnect the fluid
and attach d.
hose to
a
supply line from the supply line.
Place the end of the hose in
a
WARNING
Whenever the brakes are to be released, make sure the airplane is on
the reservoir,
level ground and the wheels checked.
clean container to
collect the brake fluid overflow. e.
f.
Open the bleeder port of install
a
bleeder hose
each brake
(shown
in
assembly.
Figure 1)
onto
each brake bleeder port.
g.
Connect the bleeder hose assemblies (shown in the pressure lines of the pressure pot,
Figure l)to
NOTE On serials
prior to Cf-839, CJ-150, D-10209, E-1432 and EA-3 (airplanes
with shuttle valves in the brake
system)
pilot’s
to actu-
depress
the
brake
pedals
ate the shuttle valve to bleed the
are
a.
Remove the cap from the brake fluid reservoir.
b.
Remove the brake fluid from the reservoir.
Disconnect the fluid supply line from the reservoir, and attach the electric bleeder fluid return line to the c.
supply
line. the bleeder
port of each brake assembly.
d~
Open
e.
Connect the infusion line
each brake bleeder port
on
the electric bleeder to
(Figure 1).
NOTE
prior to CE-839, CJ-150, D-10209, E-1432 and EA-3 (airplanes
On serials
pilot’s
with shuttle valves in the brake system) depress the pilot’s brake pedals to actuate the shuttle valve to bleed the pilot’s brakes, then proceed through step h.
brakes, then proceed through step j. After the pilot’s brakes are bled, depress the copilot’s brake pedals to actuate the shuttle valve to bleed the copilot’s brakes and follow steps g through j.
pilot’s brakes are bled, depress copilot’s brake pedals to actuate the shuttle valve to bleed the copilot’s brakes and follow steps f through i.
After the the
h.
Apply a constant pressure of not more than 30 pounds to the pressure pot. Open the pressure pot
control valve. f.
Bleed the system until the bubbles. i.
j.
draining fluid
Close the pressure pot valve.
is free of
Activate the bleeder and set the relief valve to
approximately 15 pounds; this may be ascertained by observing the pressure gage prior to opening the electric bleeder control valve.
32-40-00
Page
12
Nov 16/94
A17
BONANZA SERIES MAINTENANCE MANUAL g. Open the electric bleeder control valve and observe the returning fluid through the in-line sight
glass.
returning
fluid shows
no
further evi-
dence of air bubbles, close the electric bleeder control valve. i.
line.
Connect the fluid reservoir
supply
line to the
res-
i.
Check the brake fluid level and add MIL-H-5606
hydraulic obtain m.
a
(9. Chart 1, 91-00-00) reading
fluid
full
installthe
caponthe
as
required
to
reservoir.
operation of the brakes. When the pedals are depressed there should be no spongy feeling and the pedal pressure should be equal on both brakes. n.
Check the
brake
Disconnect the fluid infusion line from the bleeder
port. Close
supply
ervoir.
Pumping the pilot’s and copilot’s pedals during the bleeding process may help to dislodge any air bubbles trapped in the master cylinders. When the
Disconnect the fluid return line from the brake fluid
reservoir k.
NOTE
h.
j.
the bleeder
port valves,
32-40-00
Page A17
13
Nov 16/94
aeechcraft BONANZA SERIES MAINTENANCE MANUAL STEERING The
nose
MAINTENANCE PRACTICES
wheel should be
centerline of the
parallel
to the fore and aft
pedals in the neutral position. Loosen the nose gear steering actuator arm at the aft end and screw the end fitting either in or out to make the adjustment, airplane
with the rudder
b.
Turn the
tion: the
with the c,
nose
wheel to the extreme left turn
adjustment nose
wheel in this
Place tape around the aft end of the shimmy at a point 1/32 to 1/4 inch from the
d.
Turn the locknuts
ADJUSTI1IIENT
the
nose
1/32 to 1/4 inch from its maximum travel. If
adjustment
is
required,
the
following procedure is
recommended: a.
that
Loosen the locknuts
on
the
adjustment bolts
clear the stops
on
the
nose
they
wheel
on
the
adjustment bolts
so
that
wheel is turned and the tape on the piston contacts the scraper ring. Tighten the locknuts
rod
stop must be adjusted so that the nose wheel travel is stopped when the shimmy damper is
position.
damper piston rod scraper ring.
NOSE WHEEL TRAVEL STOP
The travel
posi-
bolts must be clear of the stops
just securely. e.
Repeat preceding steps b,
the
nose
tape
on
the forward end of the
and d, except turn right, and place the
c
wheel to the extreme
piston
rod.
so
straight-
ener.
32-50-00
Page A17
1
Nov 16/94
~eechcraR BONANZA SERIES MAINTENANCE MANUAL
POSITION AND WARNING MAINTENANCE PRACTICES
TED ENGINE-COMPARTMENT-LOCA LANDING GEAR WARNING SWITCH
AoJusTnnENr(CE-748, CE-772 THRU CE-1300, CE-1302 THRU CE-1306; CJ-149
LANDING GEAR POSITION LIGHT ADJUSTMENT The
landing gear position lights are mounted on the right subpanel on early serial number airplanes. On airplane serials E-1946, E-2104, E-2111 and after and EA-320, EA-389 and after, the landing gear position lights were moved to the panel. Three green lights,
left side of the
pilot’s
landing gear position lights on are operated by the up-indicator switches
the instrument
panel
down-indicator switches
on
EXCEPT E-1946 AND E-2104; EA-1 THRU EA-388 EXCEPT EA-320) NOTE
sub-
one for each gear, are illuminated whenever the landing gear is down and locked. The red light illuminates any time any portion of the landing gear is in transit or at any intermediate position. All of the lights will be extinguished when the landing gear is up and locked.
The
THRU CJ-179; D-10097, 0-10120 AND AFT;ER; E- IIII, E- 1241 THRU E-2110,
The following steps must be made by pulling the throttle control back. Incorrect settings may occur if the throttle control is pushed forward to check the switch
adjustment. If the altitude referenced in the
be obtained,
and
each gear.
a.
use
With the
following step cannot settings.
Table 1 for alternate altitude
airplane
in
flight
at 100 to 110 knots with
100 feet of pressure altitude (5,000’ 100 feet with the altitude at 2,400 propeller pressure rpm on EA serials) and the landing gear retracted, retard the
3,000
Before
making the following adjustments, place the airplane on jacks as instructed in Chapter 7-00-00
throttle to obtain 12 MAIN GEAR
sure
(15
gear-up With the
landing gear down and locked, adjust the downswitch, located on the forward side of the main gear V-brace, so that the overtravel of the switch plunger is .050 inch after the switch is actuated to the "ON" position. With the landing gear in fully up position, adjust the up-switch, located inboard of the forward side of the main landing gear V-brace, so that the overtravel of the switch plunger is .050 inch after
1 inches of
1 inches of
warning
Hg
on
EA
Hg in manifold presserials). The landing-
horn should sound at this manifold
pressure, but not before. b.
If the horn did not sound under the conditions
established in step a, measure and note the distance from the throttle to the subpanel. c.
Land the
d.
Set the throttle at the
airplane
and shut down the
position
engine.
noted in step b.
the switch is actuated td the "ON" position,
Open the engine cowling and locate the gear warning (throttle) switch as shown in Figure 3 of
NOSE GEAR
Chapter
e.
32-30-00.
f.
With the
Loosen the upper switch bracket and slide the bracket until the gear warning switch closes as indicated by a clicking sound.
is .050 inch after the switch is actuated to the "ON" position. With the landing gear in the fully up position,
g.
landing gear down and locked, adjust the down-switch, located on the right hand side of the wheel well, so that the overtravel of the switch plunger
adjust
the
upswitch, located
on
the
right-hand
lights correspond
to the
landing gear
position. Recheck the switch
plane from the jacks.
adjustment
and
remove
the air-
position.
NOTE
side of
the wheel well, so that the overtravel of the switch plunger is .050 inch after the switch is actuated to the "ON" position. Check the instrument panel to be sure the indicator
Anchor the switch bracket at this
warning horn adjustment is incorrect, repeat steps a through g.
Repeat step adjustment. h.
Working
a
to check the
If the
with the throttle control, check that the
switch actuator roller rides up smoothly on the throttle control actuator and operates without catching or
hanging
on
the
tapered end. Readjust if the switch 32-60-00
Page A17
1
Nov 16/94
Beechcraft BONANZA SERIES
MAINTENANCE MANUAL roller
up or does not operate smoothly during the throttle control movement from idle to full power travel. Ensure full throttle travel and ease of move-
hangs
actuator uator
Close the
engine cowling.
ENGINE-COMPARTMENT-LOCA
not
touching
(CE-1301, CE- 1307 AND AFTER)
NOTE
following checks must be made by pulling the throttle control back. Incorrect settings may occur if the throttle control is pushed forward to check the switch adjustment.
The
landing gear retract-prevent switch may be checked and/or adjusted at the same time the landing gear warning
The
being adjusted because of the similarity of the adjustment. Accomplish switch is
If the altitude referenced in the
the instructions under the ENGINEC O M P A R T M E N T LOCATED SWITCH RETRACT-PREVENT
Gain
access
be obtained, f.
heading.
to the throttle
Inspect
installation
landing
linkage
in the
retard the throttle to obtain
engine
is NOT to be under the
warning switch for proper Figure 1. The switch plunger dimple in the switch actuator
Push the throttle to the
d.
Inspect
the switch
The switch
plunger
fully
plunger
forward
g.
touching
manifold pressure of 12
If the switch
adjustment
is wrong, retard the Hg manifold pres-
1 inches of
sure.
position,
h.
and switch actuator
should be
a
The
and below this manifold pressure, but not above it.
arm.
arm.
Hg.
throttle to obtain 12
c.
at 100 to 110 knots with
landing-gear-up warning horn should sound and the annunciator light should flash at
gear
shown in
following step cannot settings.
Table 1 for alternate altitude
airplane flying
1 inches of
the as
With the
use
3,000 feet altitude and the landing gear retracted,
compartment. b.
plunger.
If removed, return the upper switch bracket to the position noted in step d.
NOTE
a.
the switch
e.
AFTER; CJ-1BO AND
ADJUSTMENT
and the switch act-
the position of the the throttle control housing
actuator arm will be
TED
LANDING GEAR WARNING SWITCH ADJUSTMENT
arm are
plunger touching, mark
upper switch bracket on (shown in Figure 1).Remove the switch actuator assembly from the upper switch bracket and bend the switch actuator arm so that, when installed, the switch
ment.
i.
If the switch
arm.
Measure and note the distance from the
subpanel
to the throttle control.
the switch
TABLE i ALTITUDE COMPENSATION PRESSURE ALTITUBE
1,000 A 2,000 A 3,000 ft 4,000 ft 5,000 ft 6,000 ft 7,000 A 8,000 ft 9,000 ft 10,000 ft
GEAR WARNING FOR EA SERIALS
GEAR WARNING FOR E, CE, CJ SERIALS
19 in.
14 in.
18 in.
13 in.
17 in.
12 in.
16 in.
11 in.
15 in.
10 in.
14 in. H
9 in.
13 in.
8 in.
12.5 in.
7.5 in.
11.5 in.
6.5 in.
11 in.
Hg
6 in.
Hg
32-60-00
Page
2
Nov 16/94
A17
aeechc~nft BONANZA SERIES
MAINTENANCE MANUAL NOTE The
landing-gear-up warning
sound
and the GEAR
NOTE
horn will
UP
warning annunciator light will flash at full flaps with the landing‘gear in the up position. i.
Land the
airplane
and shut down the
following checks must be made by pulling the throttle control back. Incorrect settings may occur if the throttle control is pushed forward to check the switch
The
engine,
Position the throttle control at the measurement noted in step h.
adjustment.
j.
k.
Open
switch
as
the
engine cowling shown in Figure 1.
and locate the
warning
Loosen the upper switch bracket and slide the bracket until the switch closes as indicated by a clicking sound. i.
Tighten
m.
the upper switch bracket at this
position.
n. Working with the throttle control, check that the switch actuator roller rides up smoothly on the throttle control actuator and operates without catching or
the
hanging up on tapered end as shown in Figure 1. Readjust if the switch roller hangs up or does not operate smoothly during the throttle control movement from idle to full power. Ensure full throttle travel and ease of movement. o.
Close the
p.
Repeat
engine cowling.
the
flight
If the altitude referenced in the
be obtained,
following steps cannot settings.
Table 1 for alternate
use
airplane flying at 100 to 110 knots with (propeller at 2,400 rpm on serials and EA-389 EA-320, after) and the landing gear With the
a.
3,000 feet altitude
to obtain 12
retracted, retard the throttle
1 inches of
Hg manifold pressure (15 1 inches of Hg on serials EA-320, EA-389 and after). The landing gear up warning horn should sound (the gear warning annunciator
light
should flash also
after and EA-488 and
serials E-2458, E-2468 and after) at and below this manifold on
pressure. Mark this throttle b.
position
on
the
pedestal.
On serials E-2761 and after, advance the throttle Hg (above 16 in. Hg on serials
to above 13 in.
EA-320, EA-389 and after). Lower the flaps
to fully warning horn should sound and GEAR UP annunciator light should flash.
down and the
check of the switch
setting
at the
airspeed and altitude of the first check. The landing gear warning horn should sound and the gear warning annunciator light on the instrument panel should flash
settings below the manifold pressure being used to adjust the switch. If necessary, readjust the switch as previously instructed. at
After landing the airplane and shutting down engine, set the throttle at the position marked on pedestal in step a. c.
d´•
Remove the
e.
Loosen the
warning switch
(E-1946, E-2104,
f.
NOTE
retaining
side
Adjust
the
as
shown in
cam so
covers.
arm
for the
Figure
a
the
landing
gear
2.
that the switch closes, indicated
click, with the throttle control noted in step a.
by
the
nuts on the cam located on
the end of the actuator rod
PEDESTAL-LOCA TED LANDING GEAR WARNING SWITCH ADJUSTMENT E-2111 AND AFTER; EA-320, EA-389 AND AFTER)
pedestal
the
top position
g.
Retighten
h.
Ensure full throttle control travel and
cam
retaining
at the
nuts.
The
landing gear warning switch may be checked and/or adjusted at the same time as the landing gear retract-prevent switch because of the
adjustment. Accomplish under
the
similarity
of the
the instructions
PEDESTAL-LOCATED LANDING GEAR RETRACT-PREVENT SWITCH ADJUSTMENT heading.
ease
of
movement.
i.
Reinstall the
pedestal
side
covers.
j. Repeat the check of the switch setting at the airspeed and altitude stated in step a. If necessary, readjust the switch as previously instructed.
32-60-00
Page A17
3
Nov 16/94
~eechclTlft BONANZA SERIES MAINTENANCE MANUAL
SWITCH ACTUATOR ARM
INCORRECT CONFIGURATION
DIMPLE
IN ARM
ROLLER
SWITCH ARM
ACTUATOP
SWITCH PLUNGER
CORRECT CONFIGURATION
SWITCH DIMPLE
IN ARM
ROLLER
UPPER SWITCH BRACKET
SWITCH PLUNGER
SWITCH
DETAIL
THROTTLE CONTROL HOUSING
A
TYPICAL FOR BOTH SWITCHES
UPPER SWITCH
(GEAR WARNING)
bD
LOWER SWITCH BRACKET
e ACTUATOR
O
a
O T
LOWER SWITCH
A
Y
SWITCH PLUNGER
35-IW-001
C
(RETRACT -PREVENT)
Englne-Compartment-located
Landing Gear Warning Switches Figure 1
32-60-00
Page
4
Nov 16/94
A17
BONANZA SERIES MAINTENANCE MANUAL
LANDING GEAR RETRACT-PREVENT SWITCH CAM ROD
AFT%B
LANDING GEAR WARNING HORN AND ANNUNCIATOR LIGHT SWITCH CAM ROD
LANDING GEAR RETRACT-PREVENT SWITCH
LANDING GEAR WARNING HORN AND ANNUNCIATOR LIGHT SWITCH OPTIONAL AIR CONDITIONING SWITCH
LANDING RETRACTPREVENT SWITCH CAM
GEAR
LANDING GEAR WARNING HORN AND L~GHT SWITCH
CAM
LOOKING DOWN
33-158-002
Pedestal-located
Landing Gear Warning Figure 2
Switches
32-60-00
Page A17
5
Nov 16/94
BONANZA SERIES MAINTENANCE MANUAL NOTE
TED
ENGINE-COMPAR7MENT-LOCA
LANDING GEAR RETRACT-PREVENT
SWITCH ADJUSTMENT
following checks must be made by pulling the throttle control back. Incorrect settings may occur if the throttle control
The
(CE- 1301,
CE-1307 AND AFTER; CJ-180 AND
is pushed forward adjustment.
AFTER) NOTE
If the altitude referenced in the following step cannot use Table 2 for alternate altitude settings.
be obtained,
The
warning switch may be adjusted at the same time the landing gear retract-prevent switch is being adjusted because of the similarity of the adjustment. Accomplish landing gear checked and/or
f.
Gain
Hg
gear
to the throttle
linkage
in the
Inspect the switch for proper installation in Figure 1. The switch plunger is NOT to be dimple in the switch actuator arm, b.
c.
Push the throttle to the full forward
d.
Inspect
the switch
The switch
plunger
shown
manifold pressure.
under the
and the switch act-
the
plunger touching, mark
the throttle
arm so
There is
the switch
plunger.
If removed, return the upper switch bracket to the position noted in step d.
e.
a
latching relay in the circuit landing gear to fully
which allows the
retract once retraction starts. Retarding the throttle should not stop the landing gear in midtravel.
actuator
bend the
that, when installed, the switch
touching
subpanel
NOTE
position of the control housing
(shown in Figure 1). Remove the switch assembly from the lower switch bracket and actuator arm will be
Measure and note the distance from the
the switch
uator arm are not
switch actuator
h.
to the throttle control.
position.
touching
position.
switch in the up
g. If the retract-prevent switch adjustment is wrong, 1 inches of Hg retard the throttle control to obtain 17
and switch actuator
should be
on
position
initially
a
engine
actuator arm. If the switch
lower switch bracket
I
plunger
as
to
throttle from
compartment.
arm.
check this by advancing the manifold pressure below 17 inches of with the landing gear down and the cockpit landing
acceptable
heading.
access
at 100 to 110 knots with
100. feet of pressure altitude and the landing the landing gear must not retract at extended, gear manifold pressure below 17 f 1 inches of Hg It is any
COMPARTMENT-LOCATED LANDING GEAR WARNING SWITCH ADJUST-
a.
airplane flying
With the
3,000
the instructions under the ENGINE-
MENT
to check the switch
i.
j.
Land the
Open
shown in k.
airplane and
shut down the
engine cowling Figure 1.
the
engine.
and locate the switch
as
Place the throttle at the distance from the sub-
panel
measured in step h.
TABLE 2 ALTITUDE COMPENSATION PRESSURE ALTITUDE
1,000 ft 2,000 ft 3,000 ft 4,000 ft 5,000 ft 6,000 ft 7,000 ft 8,000 ft 9,000 ft 10,000 ft
GEAR RETRACT FOR
C
CJ. EA SERIALS
19 in. 18 in. 17 in.
16 in. H
15 in. 14 in. 13 in. 12.5 in. 11.5 in. H 11 in.
Hg
32-60-00
Page
6
Nov 16/94
A17
Qeechc~ft BONANZA SERIES MAINTENANCE MANUAL Loosen the lower switch bracket and slide the
I.
bracket until the switch closes
ing m.
as
indicated
by
a
click-
sound.
Tighten
the lower switch bracket at this
position.
with the throttle control, check that the actuator relier for the retract-prevents switch rides up n.
Working
smoothly on the throttle control actuator and operates catching or hanging up on the tapered end as shown in Figure 1. Readjust if the switch roller hangs up or does not operate smoothly during the throttle without
control travel from idle to full power. Ensure full throttle travel and ease of movement. o.
Closetheengine cowling.
a.
airplane flying
With the
at 100 to 110 knots with
100 feet of pressure altitude (5,000 f 100 feet pressure altitude with propeller at 2,400 rpm on seri-
3,000
als EA-320, EA-369 and
and the
after)
extended, the landing gear
landing
gear
must not retract at
or
manifold pressure of 16 inches Hg. It is acceptable to initially check this by advancing the below
a
throttle from
manifold pressure below 16 fl inches
a
Hg with the landing gear down and the landing gear position switch in the cockpit in the gear-down position.
b.
of the throttle control
position
Mark the
pedestal
with the throttle retarded to the
on
the
appropriate
manifold pressure.
Repeat the flight check of the retract-prevent switch setting at the airspeed and altitude stated in step f. If necessary, readjust the switch as previously p.
NOTE There is a latching relay in the circuit which allows the landing gear to fully retract once retraction starts. Retarding the throttle should not stop the landing
instructed.
PEDESTAL-LOCA TED LANDING GEAR
RETRACT-PREVENT SWITCH
I
(E-2458, E-2468, AND AFTER; EA-320, EA-389 AND AFTER)
gear in midtravel.
AD3USTMENT
NOTE
d.
Place the throttle control at the mark made
pedestal
f.
the PEDESTAL-LOCATED LANDING GEAR WARNING SWITCH ADJUSTMENT heading,
g.
NOTE
following checks must be made by pulling the throttle control back. Incorrect settings may occur if the throttle control is pushed forward to check the switch adjustment. The
following steps cannot alternate altitude settings.
If the altitude referenced in the be obtained,
use
Table 2 for
engine.
Land the
The landing gear warning switch may be checked and/or adjusted at the same time as the landing gear retract-prevent switch because of the similarity of the adjustment. Accomplish the instructions under
and shut down the
c.
e.
airplane
on
the
in step b.
Remove the
Loosen the
pedestal
retaining
side nuts
covers. on
the
cam
located
on
the end of the actuator rod for the gear retract-prevent switch shown in Figure 2.
Adjust the
cam so
that the switch closes, indicated at the position noted
click, with the throttle control in step b.
by
a
h.
Retighten the
i.
Ensure full throttle travel and
i.
Reinstall the
cam
retaining
pedestal
side
nuts. ease
of movement.
covers.
Repeat the flight check of the switch setting at the airspeed and altitude stated in step a. If necessary, readjust the switch as previously instructed.
k.
32-60-00
Page A17
7
Nov 16/94
CHAPTER
LIGHTS
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
INTERIOR
33-20-00
PAGE
t
Maintenance Practices
Light Bulb Removal Post Light Bulb Installation Wedge Light Tray Removal Wedge Light Tray Installation
Instrument Post instrument
Instrument Instrument
........1
............1 ............1
............1
Electroluminescent Panel Removal
............1
Electroluminescent Panel Installation
..............1 ......1
Individual Warning and Position Light Bulb Removal Warning and Position Light Bulb Removal (Landing Gear, Alternator, and Baggage Door) Warning and Position Light Bulb Installation (Landing Gear, Alternator, and Baggage Door) Glareshield Glareshield
Floodlight Floodlight
............1
8ulb Installation
Light
CJ-156 and after, EA-171 and
.....1
Bulb Removal
Passenger Reading Light Bulb Removal Passenger Reading Light Bulb Installation Compass Light Bulb Removal Compass Light Bulb Installation Trim Tab Light Bulb Removal Trim Tab Light Bulb installation L"ourtesy Light Bulb Removal Courtesy Light Bulb Installation Map Light Bulb Removal Map Light Bulblnstallation Cabin Overhead Light Bulb Removal (Prior to C-993, CJ-156, C-10347, 8-1783, EA-171) Cabin Overhead Light Bulb Installation (Prior to CE-933, CJ-146, D-10347, 8-1783, EA-171) Cabin Overhead
...........1
Bulb Removal
............1 ............1 _
............2 .........2 ............2 ...2
............2 .....2 ...........2 ......2 .2
................2
(CE-933and after,
D-10357 and after, E-1783 and after,
after) Light Bulb Installation (CE-933
Cabin Overhead
........2 and
after,
CJ-156 and after, D-10347 and after, E-1783 and after, EA-171 and after)
............2
Cabin Overhead
Bulb Removal
............2
Cabin
Bulb Installation
..........,2
Light Overhead Light
EXTERIOR.....
Description Strobe
..................................................33-40-00
and
Operation
..........1
............1
Lights
Step Light Optional. Troubleshooting Exterior Lights
............1.
Maintenance Practices
............3
............3
Lights Power
Power
´•2
Supply Supply
Unit Removal Unit Installation
...........3
............3
33-CONTENTS
Page Sep
t
27/84
BEEC~CRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 33
LIGHTS
TABLE OF CONTENTS
(Cont’d) CHAPTER SECTION
SUBJECT
SUBJECT EXTERIOR
(Cont’d)
Maintenance Practices
,,,,,,,..33-40-00
(Cont’d)
Lights (Cont’d) Wing Strobe Light Removal Wing Strobe Light Installation Wing Navigation Light Removal Wing Navigation Light Installation Tail Strobe/Nav Light Removal Tail Strobe/Nav Light Iristallation Tail Naviation Light Removal Tail Navigation Light Installation Taxi Light Removal Taxi Light Installation Landing Light Removal Landing Light Installation Upper Rotating Beacon Removal
...,,,,.,,,,3 ,,.,,,.,,,.,,4 .,,,,,,4 ,,,,.,,,,,,,.4 ,,,,4
.............4
,,.,,,,,,,.,.5 ,,,,,,,,,,.,.5 ,,,,,,,,.,5
,,,,,,,,,,5 ,,,,,.,,,,.,.5
.............5 .............5
.............5
Upper Rotating Beacon installation Lower Rotating Beacon Removal Lower Rotating Beacon Installation Lower Rotating Beacon Bulb Removal Lower Rotating Beacon Bulb Installation, Step Light Bulb Replacement Step Light 8ulb Installation Light Bulb Replacement Chart 1
.............5 ,,,,,,5
,,.,,,,,,,,,.5
,.,,,,,,5 ...,,.,,,..,6 .............6
.............6
IEND"
33-C ONTENTS
Page
2
Sec, 27’84
PAGE
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL CHAPTER 33 LIST OF PAGE EFFECTIVIN CHAPTER SECTION
SU&IECf
PACE
33-EFFECTIVITY 33-CONTENTS
33-20-00
33-40-00
DATE
i
Sep
27184
1
Sep
27/84
2
Sep
27/84
9/80
1
May
2
Jan 28/81
1
Sep Sep Sep Sep Sep Sep
2
3 4
5 6
27/84 27/84 27/84 27/80 27/8(: 27/8r,
"END"
33-EffECTIVITY Ag
Page 1 Sep 213/84
BEECHCRAFT BONANZA SERIES MAINtENANCE MANUAL
INTERIOR
acrylic face panel or the printed circuit damaged, the whole unit must be replaced.
If the
separately.
MAINTENANCE PRACTICES
board becomes
INSTRUMENT POST LIGHT BULB REMOVAL Remove the
a.
Individual post lights, located adjacent to the instruments on the instrument panel may have bulbs removed as follows:
side of the face
attaching
screws
located
on
each
panel. wiring running from the printed splice. assembly from the subpanel.
Disconnect the
b´•
circuit board at the from the post light assembly, Remove the bulb from the post light assembly.
Pull the
a.
b.
light shield
Pull the
c.
ELECTROLUMINESCENT PANEL INSTALLA TION INSTRUMENT POST LIGHT BULB INSTALLA TION and
Install the bulb in the post light assembly. Insert the shield to the instrument post
a.
b.
wiring at the splice. panel assembly in place in the attaching screws.
a.
Reconnect the
b.
Place the
secure
it with
subpanel
the
light WARNING AND POSITION LIGHT BULB REMOVAL
assembly.
(LANDING GEAR, ALTERNATOR, BAGGAGE DOOR)
INSTRUMENT WEDGE LIGHT TRA Y REMOVAL Internal
lighting
of the
instruments
illumination across each instrument. A
provides additional light tray mounted on
the top side of the bezei of each instrument holds two bulbs wired in parallel. If the light bulbs are damaged or burn out the
light tray
Remove the
a.
in
panel
with bulbs must be
place and
screws
that
secure
Remove the
b.
Remove the bulb.
light
shield.
WARNING AND POSITION LIGHT BULB INSTALL9TION (LANDING GEAR ALTERNATOR, BAGGAGE
DOOR)
replaced.
tilt the instrument
a.
the instrument
panel aft
to
gain
the bulb in the
a.
Replace
b.
Install the
light
shield
on
light assembly. the light assembly.
the instruments.
access to
GLARESHIELD FLOODLIGHT BULB REMOVAL NOTE Locate the defective bulb.
a.
Instruments located at the lower
edge
of the
panel may be removed if necessary, to access to the light tray at the top of
gain
up on
the
glareshield attach gain access to glareshield
Remove the
b.
the
to
and
screws
push
the bulb.
Remove the bulb.
c.
instruments.
GLARESHIELD FLOODLIGHT BULB INSTALL4 TION b.
Remove the
screws
that attach the
light tray
to the
instrument bezel.
light assembly.
the bulb in the
a.
Replace
b.
Install the
glareshield
and secure with the attach
screws.
INSTRUMENT INSTALLA TION a.
Install the
the attach
new
WEDGE
light tray
and
LIGHT
secure
in
TRA Y
place
with
PASSENGER READING LIGHT BULB REMOVAL a.
Remove the aluminum
b.
Remove the bulb.
light
cover.
screws.
ELECTROLUMINESCENT PANEL REMOVAL
PASSENGER INSTALLA TION
Three electroluminescent
a.
Replace
instrument
b.
Install
panels provide lighting for the subpanel. The electroluminescent lamp is an integral part of the finished panel and cannot be replaced
READING
the bulb in the the
aluminum
LIGHT BULB
light assembly. light cover on
the
light
assembly.
33-20-00
Page 1 May 9/80
BEECHCRAFT BONANtA SERIES MAINtENANCE MANUAL
COMPASS LIGHT BULB REMOVAL
the control wheel. Pull out center
b. the bulb shield
a.
Flip
b.
Bulb will pop out.
over
the
to one side,
plate and
remove
the bulb from
light assembly.
MAP LIGHT BULB INSTALLA TION
COMPASS LIGHT BULB INSTALLA TION
Replace the bulb in the light assembly. Flip the bulb shield back over ´•the bulb.
a.
b.
Replace the bulb
b.
Reinstall the center
and securewith the
(Prior a.
instrument
light assembly
screws.
to
CE-933 C~-156, 0-10357 E-1783, EA-171)
I
away from the back of the
panel.
a.
access to
Remove the bulb,
b.
attaching
CABIN OVERHEAD LIGHT BULB REMOVAL
TRIM TAB LIGHTBULB REMOVAL Pull the
light assembly. plate in the control wheel
in the
a.
panel assembly
Remove the overhead the bulb.
(Fresh air
to
gain
vents and vent knob must be
removed also.) b. Remove the bulb from the
light assembly.
TRIM TAB LIGHT BULB INSTALLATION a.
Replace
b.
Install
light assembly. light assembly into the instrument
CABIN OVERHEAD LIGHT BULB INSTALLATION
the bulb in the
the
(Plio~toCE-933,
CJ-156, D-10951, E-17B3, EA´•I/1J
panel.
COURTESY LIGHT BULB REMOVAL a.
moulding b.
Remove the
screws
light assembly. panel assembly.
in the
a.
Replace the bulb
b.
Reinstall the overhead
c.
Reinstall the fresh air vents and vent knob.
attaching the upper door
to the door.
Bend door
moulding
over
to
gain
access to
CABIN OVERHEAD LIGHT BULB REMOVAL and after, CJ-156 and after, 0-10357 and
the
(CE-933
bulb. c.
Remove the bulb from the
after, E-1783 and after, EA-171 and after!
light asseri~bly.
a.
COURTESY LIGHT BULB INSTALLATION
b. a.
b.
Squeeze the lens sufficiently to release the pull the lens away from the light assembly. Remove the inoperative light bulb.
catches and
Replace the bulb in the light assembly. Secure the moulding to the door with the
attach
CABIN OVERHEAD LIGHT BULB INSTALLATION (CE-933 and after, CJ-156 and after, 0-10357 and after, E-1783 and after, EA-171 and after)
screws.
MAP LIGHT BULB REMOVAL a.
Remove the
screws
securing
the center
plate
to
"END"
33-20-00
Page2 Jan 28/81
light
bulb.
a.
Install
b.
Install the lens into the
a new
light assembly.
I
BEECHCRAFT BONAN;LA SERIES MAIMENANCE MANUAL
DESCRIPTION AND OPERATION
EXTERIOR
sufficiently, the lamp will go out recharging for the next cycle.
while the
capacitor begins
STROBE LIGHTS
Flashing
strobe
lights
are
mounted
on
each
wing tip
and
are
The system is activated by a circuit breaker switch mounted on the instrument subpanel. The strobe lights are powered by a power supply unit available
on
the tail
baggage compartment. A transistorized circuit in the power supply unit steps up the voltage of the airplane electrical system to the level (approximately 400 volts) required to operate the strobe lights. The stepped-upvoltage is stored in a capacitor until released to the strobe lights. The current from the power supply unit is conducted to the flashtube of the strobe light by a specially shielded power cable. A charge of high voltage electricity is momentarily released to a coil in the flashtube assembly. The coil further steps up the charge to a point where it ionizes the xenon gas in the flashtube. The high voltage stored in the capacit3r then surges through the gas to produce the brilliant burst of light energy that characterizes the strobe light. When the capacitor voltage drops located in the
STEP LIGHT
OPTIONAL
cone.
On serials E-2104, E-2111, and after; and EA-320, EA-389 a step light may be mounted in the fuselage just forward of the step and aft of the right wing trailing edge. The switch is mounted in the top of the forward ~door frame.
and after,
ajar switch will activate perform its annunciator function.
In some installations, the aft door
the
step light
as
well
The timer is located
on
as
the forward side of the forward spar on the right
carry through, and the five amp fuse is located side forward of the firewall.
This system is wired directly to the battery through a five amp fuse and will operate any time the doors are opened.
lights are a part of the same system and operate simultaneously with the step light. Once the step light has been activated the timer will turn the light off in The courtesy
approximately
15 minutes.
33-40-00
A9
Pegs 1 Sep 27/04
BEECHCRAFT BONAN;LA SERIES MAINTENANCE MANUAL
TROUBLESMOOTIMO EXTERIOR LIGHTS REMARKS
PROBABLE CAUSE
TROUBLE
STROBE LIGHTS i.
Lights inoperative.
a.
Circuit breaker
tripped.
a.
Check for short circuit.
Reset circuit
breaker.
2.
One bulb does not
light,
electrical connections.
b.
Loo:se connection.
b.
Check and
c.
Battery defective.
c.
Replace battery
d.
Power
d.
Replace.
a.
Bulb burned out,
a.
Replace bulb.’
b,
fixture not
b.
Check for good bonding between fixture
supply inoperative,
grounded,
tighten
and structure.
c.
Loose connection.
d.
Defective fixture
or
switch,
or use
external power.
Tighten mounting
c.
Check all connections in circuit.
d.
Replace
fixture
or
screws.
switch.
TAIL LIGHT, TAIL NAV/STROBE LIGHT, LANDING LIGHT, AND TAXI LIGHT 1.
Lamp fails
to
light.
a.
Circuit breaker switch
tripped.
a.
Check for short circuit.
Reset circuit
breaker. b.
Circuit
breaker
switch
b.
c.
Larrp burned
d.
Loose connection
wiring.
Check
continuity through
switch.
Replace
if necessary.
defective. out,
or
defective
c.
Replace lamp.
d.
Tighten connections and check wire circuit continuity. Replace or repair wire if necessary.
3343-00
PageP Sep 27/84
A9
BEECHCRATT BONANZA SERIES MAINTENANCE MANUAL
POWER SUPPLY UNIT INSTALLATION
MAINTENANCE PRACTICES
EXTERIOR
CE-748, CE-772 and after; CJ-149 and after, 0-10097, D10120 and after; E- 1111, E- l~i?41 to E- 1370
LIGHfS
CA UTION POWER SUPPLY UNIT REMOVAL
hook-up of
An incorrect
the wires in either the
power input or between the strobe light assemblies and the power supply will cause a reversal of polarity that results in serious
CE-748, CE-772 and after; CJ-149 and after: 0-10097, D10120 and a~ter; E-llll, E-1241 to E-1370
component damage and failure. Care must be taken to ensure that the red wire is connected to
WARNING
power and the black wire is connected to ground. Make sure that the
positive
connectors
High voltage is involved in the circuit between supply and strobe light assemblies. Although a bleed-off resistor is incorporated in the power supply circuit, turn the control switch for the strobe lights OFF and allow at least 10 minutes to elapse prior to disconnecting the cables at the power supply or strobe light assemblies and before units
in
handling
assembled and that
properly. The shields for the wing light cables should be grounded to the airplane structure at the power supply. Refer to
are
connected
and tail
WIRING
the
DIAGRAM
components in
either of these
way. Failure to observe these may result in physical injury from
MANUAL P/N
35-
hook-up of the strobe light system.
59()102-9 to ensure
correct
a
the
any
precautions
Position the power supply unit in the airplane and with the screws, washers, and nuts. Connect the electrical wiring to the power supply. b. a.
electrical shock.
secure
Install
c. a.
properly
are
whiteired, whiteiblack, and whiteiyellow wires
the power
Remove the floorboard on the RH side of the
floorboard
the
the
on
RH
side
of the
baggage compartment.
baggage compartment. b.
Disconnect
the
wiring
electrical
to
the
power
E- 1371 and afler.´• EA-I and after
supply. c.
Remove the screws,
washers, and
nuts
the module to the support structure. d. Remove the power supply from the
anchoring
Place the power supply in its proper location and screws which hold it in place.
a.
install
airplane.
Connect the electrical
b.
adhering
the
to
caution
to the power supply for the above earlier
wiring
indicated
serializations.
8-1371 and after; EA-1 and after
c.
screws
d.
Place the
access
cover
in
place
and install the
and washers.
Reinstall the carpet.
WARNING WING STROBE LIGHT REMOVAL Observe the removal
warning precautions given
instructions
for
the
in the
WARNING
earlier
serializations.
High voltage is involved in the circuit between supply and strobe light assemblies.
the power a.
Locate the access
station 170,
fuselage baggage compartment. b.
and
Remove the 4
remove c.
on
the
the
cover
screws
in the
floorboard, aft of
airplane,
in the
and washers from the
cover
right
side of the
Disconnect the electrical
in
place and
remove
bleed-off resistor is
minutes to elapse
wiring
from the power
screws
which hold the power
the power
supply,
supply
incorporated
in
prior to disconnecting the supply or strobe light handling either of these
power assemblies and before units
Remove the
a
the power supply circuit, turn the control switch for the strobe lights OFF and allow at least 10
cables at the
cover.
supply, d.
Although
in
any
way.
precautions may
Failure
result in
to
these
observe
physical injury
from
electrical shock.
33-40-00
A9
Page 3 Sep 21/84
BEECHCRAFF BONANZA SERIES MAINTENANCE MANUAL
Remove the transparent shield
a.
covering the wing
retainer and
tip lights. b.
Detach the strobe
light assembly
the retainer.
remove
Rotate the bulb counterclockwise to remove.
c.
from the
wing by securing the mounting bracket to the strobe light assembly. Disconnect the electrical wiring. c. d. Remove the screws securing the end plate assemblies to the light assembly. Remove the end plate the alien head screws. Remove the nuts
removing
assemblies. Remove the clear filter
e.
cover
from the strobe
WING NAVIGATION LIGHT INSTALLATION
Replace
b.
Install the retainer
secure
with the
c.
install
light
housing assembly.
the bulb.
a.
Place
a
the
and
navigation light bulb
the
transparent shield and
with
secure
screws.
NOTE
fingers
on
screw.
NOTE
clean cloth around the flashtube to
Before
from
wing, apply
keep coming in,contact with the glass.
installing
shield to
the
transparent shield
Presstite
ensure
on
the
176 sealer around the
moisture cannot enter the
light
compartment.
Carefully
f.
remove
the flashtube from the contact
assemblies. TAIL STROBE/NAV LIGHT REMOVAL WING STROBE LIGHT INSTALLATION
WARNING CA U~ION Observe the
procedure stated
caution
High voltage is involved in the circuit between supply and strobe light assemblies. Although a bleed-off resistor is incorporated in the power supply circuit, turn the control switch for the strobe lights OFF and allow at least 10 minutes to elapse prior to disconnecting the cables at the power supply or strobe light assemblies and before handling either of these units in any way’. F.3ilure to observe these precautions may resu t in physical inlury from
in
the power
POWER SUPPLY UNIT INSTALLATION in this
chapter.
Replace
a.
the flashtube if necessary.
NOTE
electrical shock. Place
a
fingers
clean cloth around the flashtube to from
coming in
contact
keep with the glass. Remove the tail
:one and light shield to gain light assembly. b. Disconnect the strobeinav light assembly from the airplane electrical system. a.
access
Reinstall the clear filter
b.
cover
in the strobe
light
housing. Install the end
c.
bracket screws
on
the strobe
plate assemblies
light housing and
and
secure
mounting with the
c.
d.
Reconnect the
assembly e.
to the
airplane
wiring
and
secure
the strobe
with the alien head
light
If
the
remove
remove
replaced.
flashtube
assembly needs replacement, light assembly the light assembly from the tail cone.
remove the screws on
and
screws,
Reattach the transparent shield to the
Rotate the nav bulb counterclockwise and
the bulb if it needs to be
and nuts,
d.
to the strobe
the backside of the
wing tip. TAIL STROBEINAV LIGHT INSTALLATION
WING NAVIGATION LIGHT REMOVAL a. a.
Remove
the
transparent shield and b.
Remove the
attaching
remove screw
screws
from
the
tip, navigation light
cone
Replace the flashtube assembly and with
the
screws
in
the
backside
secure to
of the
the
light
assembly.
from the wing
from the
tail
bulb
b.
Replace
the bulb if necessary.
33-40-00
Page4 Sep 27/84
A9
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
Reconnect the strobe/nav lignt assemoly
c.
airplane d.
electrical system. Reinstall the light shield
over
to tne
the strobe/nav
light
assembly. e.
LANDING LIGHT INSTALLATION
Reinstall the tail
cone an
TAIL NAVIGATION LIGHT REMOVAL
Remove the outer
with
light shield
gain
to
with
d.
access to
Remove the inner bulb shield from the bulb.
c.
Rotate the bulb counterclockwise to
around the
light
and
wiring
to the back of the
light
and
screws.
Install the
the nose
b.
retaining ring
screws.
Reconnect the
c.
secure a.
install the
b. secure
the bulb.
and install the seal back around
light
the
light.
airplane.
the
Replace
a.
the
bug and
light assembly
secure
with
the lower
on
portion
of
screws.
UPPER ROTATING BEACON REMOVAL
remove.
TAIL NAVIGATION LIGHT INSTALLATION
Remove the
a.
from the lens
screw
retaining clamp.
Remove the lens. the bulb in the holder.
a.
Replace
b.
Place the inner bulb shield
c.
Reinstall the outer
over
light shield
on
the tail
cone.
Remove the
b.
Remove the
from the
screws
screws on
by rotating
counterclockwise.
UPPER ROTATING BEACON INSTALLATION
TAXI LIGHT REMOVAL a.
Remove the bulb
b. the bulb.
light retaining ring.
the back of the
light
Replace
b.
Install the lens
black "mask" is
to
the bulb in the holder.
a.
facing
Secure the lens
c.
the
on
plane making
sure
that the
forward.
clamp
with the
screw.
wiring.
disconnect the
LOWER ROTATING BEACON REMOVAL TAXI LIGHT INSTALLATION
(Prior to E-2050, CE-1014, P10404, EA-320)
Replace the light and place the retaining ring light. Secure the retaining ring with screws. Properly index the light bulb.
and EA-324 except
a.
around the b.
Reconnect the
wiring
to
light and
secure
Remove the
a.
screw
from the lens
retaining clamp.
Remove the lens.
with
Remove the bulb
b.
by rotating counterclockwise.
screws.
LOWER ROTATING BEACON INSTALLATION
(Prior
LANDING LIGHT REMOVAL
to
E-a050, CE-1014, D-10404, EA-324
except EA-
320) a.
Remove the outer retaining screws to detach the lower portion of the nose bug.
light from the b.
assembly c.
removing d.
the bulb in the holder.
a.
Replace
light
b.
Install the lens
retaining ring. Disconnect the wiring from the light assembly by
c.
Secure the lens
Remove the and
the
pull
screws
from the back of the
off the
the plane. clamp with the
on
screw.
LOWER ROTATING BEACON BULB REMOVAL
screws.
Remove the seal from between the
light
and the
retaining ring.
(E-2050 and after; EA-320, EA-324 and after; P´•10404 and after) a.
Remove the
b.’
Remove the lens.
c.
Remove the bulb.
screw
end after; CE-1014
from the lens.
NOTE LOWER ROTATING BEACON BULB INSTALLATION The beam
adjustment
screws
should not be
during removal or installation of the landing light. This will ensure that no further adjustment of the light will be moved
needed.
in
either direction
(E-2050
and after; EA-320, EA-324 and after; CE-1014
and after; Di0404 and after) a.
Install the bulb.
b.
Install the lens and
secure
with the screw.
33-40-00
PageS A8
Sep
27/84
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
STEP LIGHT BULB REPLACEMENT
d.
Remove the
light
bulb.
STEP LIGHT BULB INSTALLATION Locate the small
a.
upholstery
side
panel
the
over
step light. b.
panel
in
c.
Remove the screws upholstery place and remove the panel. Pull the light assembly from its mounting bracket. which hold the
a.
install
b.
Install the
c.
Place the
bulb (1495 G E) in the light socket. light assembly in its mounting bracket. upholstery panel in place and install the
a new
screws.
CHART 1 LIGHT BULB REPLACEMENT
(0-10097, 0-10120 and after; CE-748, CE-TIP and after; CJ-149 and after; E-lill, E-1241 through E-2110 except E-1946 end E-2104; EA-1 through EA-388 except
EA-320)
BULB REPLACEMENT
LOCATION Alternator Out
E-2111 and after; EA-320, EA-389 end after)
(E-1946, E-2104,
Alternator Out
327
Light
BULB REPLACEMENT
LOCATION
327
Light
303 327
Light Compass Light
267
Cabin Overhead Light Cabin Reading
327
Clock Light
Condenser Door
327
Compass Light
327
Condenser Door
327
Cabin Overhead
1864
Light
Clock
Open Light
Courtesy Light Door Ajar Light
1864
Light Flight Compartment Floodlights Fuel Select Light
1819
Lights Instrument Wedge Lights Landing Gear Intransit Lights Landing Gear Uplock Light Landing Light Light Tray Assembly Map Light Navigation Light (Tail) Instrument Post
Light Reading Light Rotating Beacon (Lower) (Prior
313
Elevator Trim Tab
327
Indicator
267 327
Glareshield
327
Lights Instrument Wedge Lights Landing Gear Transit Light Landing Gear Downlock Lights Landing Light Map Light Navigation Light (Tail) Navigation (Wing) OAT Light Oxygen Post Light Pedestal Post Lights Reading Light Rotating Beacon (Lower) Rotating Beacon (Upper) Rotating Beacon (Tail) Step Light Strobe Light (Tail) Strobe Light (Wing) fail Light Taxi Light
327 313 327
Light
313AM 327
Instrument Post
267 A7512-24 327 303 to
thru EA-388; CE-1014 and after)
1819
Light
Fuel Select
E-2050, CE-1014, 0-1404 and
Rotating Beacon (Upper) Subpanel Post Lights Strobe Light (Tail) Strobe Light (Wing) Tail Light
1864
Flap Flight Compartment Floodlights
1495
EA-324 except EA-320) Rotating Beacon (Lower) (E-2050 thru E-210 except E-1946 and E-2104; EA-324
1864
327
4596
OAT
Open Light
Courtesy Light Door Ajar Light
327
Elevator Trim Tab
303
D7080A5-24
WRM1939 D7080A1 -24 327
30-0815-1
30-1467-1 1683
58-380022-13
Light Tray 327
327 4596
1495 A508 A7512-24
327 334 334
303 A707-98-24 WRM1939 WRM1939 1495
A506 30-1467-1
1683 4313
"END"
33-40-00
PageG Sep 27/84
69
Bsl
C H A PT E R
NAVIGATION
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 34
LIST OF PAGE EFFECTIVITY CHAPTER
SECTION DATE
PAGE
SUBJECT
34-EFFECTIVITY/CONTENTS
1
Jan 20/82
34-10-00
1
.....Jan 20/82
2
May
9/80
................Jan 20/82
3
1´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´• ´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•Oct 10/80
34-40-00
............´•´•Oct 10/80
2
CHAPTER 34
NAVIGATION
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
SUBJECT
.34-10-00
FLIGHT ENVIRONMENTAL DATA/PITOT STATIC.
~..........1
Operation Description Pitot System Normal Static Air System Emergency Static Air System Troubleshooting Pitot and Static Pressure System and
............1 .........,f ............1 ............1 ............1 ............1
Maintenance Practices
......1
Pressure Test
System Inspecting Pitot System Hoses Static System Checks Cleaning the Static Air System Testing the Static System for Leaks Outside Air Temperature Gage Removal of the Outside Air Temperature Gage Inspection of the Outside Air Temperature Gage Installation of the Outside Air Temperature Gage............... Pitot
PAGE
............2 ............2
............2
............2 ............2 ............3 .........3 .........,.3
........34-40-00
INDEPENDENT POSITION DETERMINING
..........1
Description and Operation
............1
Weather Radar
............1
Maintenance Practices
............1
Weather Radar
Radar Antenna Removal
............1
Radar Antenna Installation
............1
"END"
34-EFFECTIVITY/CONTENTS
Page
1
J´•n 20%~
BEECNCRAFT BONANZA SERIES
MAINTENANCE MANUAL
FLIGHT ENVIRONMENTAL DATA/PITOT STATIC DESCRIPTION AND OPERATION
I
PITOT SYSTEM
I
side of the
airplane
aft
fuselage.
Ah of the
closure
rear
bulkhead (rear seat panel) is a drain plug, located at the low point of the normal static system. It is provided to drain moisture accumulations from the system. The drain plug should be removed and the moisture drained from the
The
I
of
air for
pitot system provides a source impact operation of the airspeed indicator. The pitot mast is located under the leading edge of the left wing outboard of wing
station 122.75 except EA-242, EA-PM and after. At serials EA-242, EA-273 and after the pitot mast is moved to
outboard of with
an
with
a
on
on
the instrument panel. The switch should be in visible moisture. It is not advisable to
operate the pitot heating element or
on
for short intervals of time to
the
ground except for
remove
ice and
snow.
NORMAL STATIC AIR SYSTEM The normal static system provides a source of static air to the flight instruments through a flush static fitting on each
sand and dust, either in the air
or on
to visible
the
ground.
An
I
flying
or
EMERGENCY STATIC AIR SYSTEM
i
wing station 191.0. The pitot head is provided heating element which is turned on and off i
switch
testing
moisture
electric
when
plastic line every 100 hours and/or after exposure
i
I
optional emergency static air source may be installed to provide air for instrument operation, should the static ports become clogged. The emergency static air control switch is located on the lan side pend below the Instrument subpanel at approximately FS 65. The static air control switch is a two-position switch with both an OFF NORMAL and an ON EMERGENCV position. The switch handle is red in color ~and operation instructions are on a placard near the switch. For further information regarding the emergency static air source system, refer to the respective Pilot’s Operating Handbook,
TROUBLESHOOTING PrTOT AND STATIC PRESSURE SVSTEM PROBABLE CAUSE
INDICA TION 1.
Heating element inoperative.
REMARKS
a.
Defective switch.
a.
Replace switch.
b.
Grounded
b.
Check
or
open circuit,
continuity. Repair
and
replace
as
necessary. c.
Defective
pitot 2.
3.
Circuit breaker keeps
Inoperative operation.
Instruments
erratic in
tripping. or
heating element
in
c.
Replace heating element.
head.
a.
Grounded wire,
a.
Remove
a.
Lines
a.
Open
clogged.
ground from positive lead.
drain valve, allow lines to drain.
Disconnect the lines at the instrument
panel and blow
out
lines with
low air
pressure. b.
b.
Lines leak,
Check lines for loose connection and
c.
Leak in instruments.
FLIGHT ENVIRONMENTAL DATA/PTTOT STATIC MAINTENANCE PRACTICES
PITOT SYSTEM PRESSURE TEST A functional test of the an
pitot system
can
observer in the cabin to watch the
be made by using airspeed indicator
I
c.
points
tighten.
Check instrument
case.
while air pressure is built up artificially soft rubber tubing as follows:
by using
a
section of
a. Clamp the rubber tubing over the pitot head inlet, making certain that the connection is airtight. b. Crimp the end of the tubing and slowly roll it up until the airspeed indicator registers approximately 100
miles per hour.
34´•1090
Page A4
1
Jan 20/82
BEECHCRAn BONANZA SERIES MAINTENANCE MANUAL
CAUTION
Instrument
error or
possible damage could result if or foreign matter.
even one
port is clogged with dirt To avoid
rupturing the diaphragm of the airspeed
indicator, roll up the rubber tubing slowly.
CAUTION c.
Secure the rolled up tubing
so
that it will hold the
d.
If there is
minutes, there is a.
If
a
no
decline in the
reading after
several
leak in the
no
pitot system. reading of the airspeed indicator pitot system plumbing for leaky hoses
decline in the
is observed, check the
Never blow air
the line toward the
through
to do so will
seriously damage blowing back through the line from the instrument panel, make sure that no instrument
airspeed indicator reading.
panel;
the instruments. When
air is blown into the instruments.
and loose connections. NOTE
CAUTION
Wax
buttons should be cleaned periodically with a solvent to insure that no film exists on
Release the air pressure slowly by unrolling the tubing; a sudden release of the air
rubber
pressure may
damage
the
polish applied to the static air buttons can wrong instrument readings. The static air
or
cause
cleaning
the static air buttons.
airspeed indicator.
Drain the static air system
by opening the static drain panel in the tail section.
INSPECTING PITOT SYSTEM HOSES
located ah of the
pitot system is checked for leaks, the hosi~ visually inspected for signs of deterioration. There are two sections of hose in the pitot system: one hose at the pitot mast, accessible by removing the inspection door adjacent to the mast, and the other hose behind the floating instrument panel which connects the pitot line to the airspeed indicator, accessible through the access
TESTING THE STATIC SYSTEM FOR LEAKS
Before the
rear seat
valve
sections should be
cracked
or
replaced with hose conforming Military Specification MIL-H-5593. Anytime a hose replaced, repeat the preceding pressure check.
to
door in the left side of the firewall. Hoses that hardened should be
are
The static system, altimeter instrument, and all ATC transponders must be tested and inspected at twenty four
month intervals in
specified
compliance
the Code of Federal
CAUTION To avoid
Proper functioning of the static air system is vital to safety of flight, particularly on instrument flight. Correct maintenance of the system should be performed as required. The amount of attention required by the static system will depend largely on operating conditions. Extremes of humidity or precipitation, or of dry, dusty conditions, should be signals for increased emphasis on static systems check, since both are favorable to accumulations of foreign matter in the ports
requirements
Regulations.
is
STATIC SYSTEM CHECKS
with the
in FAR Parts 91.170 and 91.177 under Title 14 of
damaging
the
airspeed indicator,
the
indicator should be removed from the system and the lines capped or an equal pressure should be
while leak
applied to the pitot side of the indicator testing the system.
Check the hoses connecting the static air line to the plumbing and the tygon tubing which forms the
instrument
static air line drain. Hoses which
the bends
or
should be
connection
are
cracked, particularly
at
which have become hard, with rubber hose conforming to
points,
or
replaced (14, Chart 1, 91-00-00).
and lines.
MILH-5593
CLEANING THE STA TIC AIR SYSTEM
OUTSIDE AIR TEMPERATURE GAGE
81ow LOW air pressure air through the lines from the disconnected lines at the airspeed indicator, altimeter, and
The outside air temperature gage is mounted in the left side panel beneath the storm window. The pointer registers on a
speed indicator to the static ports. Cover each static port separately when blowing to insure that each line is clear.
dial calibrated in
vertical
34-1090
Page 2 May 9/80
degrees
-50"C to +60"C.
over a
range of
70"8 to
1
50"8,
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
Inspect Inspect
REMOVAL OF THE OUTSIDE AIR TEMPERATURE GAGE
rubber washers for
the pointer for
CAUTION
parts. INSTALLATION QF THE OUTSIDE AIR TEMPERATURE
the gage to the molding or have an assistant hold the gage to prevent it from falling.
Tape
GAGE
a.
Remove the sunshield, boss and washers from the
a.
peeling, cracking, and resiliency. markings on the gage for legibility. Inspect chipped or peeling paint. Replace defective
the index
Install the
the left side
mounting washer, boss, and gage panel molding.
into
stem.
When
b.
damaging
removing the gage,
use
care to
avoid
CAUTION
the stem.
INSPECTION OF THE OUTSIDE AIR TEMPERATURE
Tape the gage
GAGE
assistant hold the gage to
Inspect
the sunshield for dents,
misalignment
plugged openings
stripped
or
damaged
molding
or
have
an
prevent it from falling.
and any
Inspect
b.
Install the outer washers and boss.
threads.
c.
Install the sunshield.
that would allow contact with the stem.
the nut and stem base for
to the
STATIC LINE
AIRSPEED INDICATOR
OPTIONAL EMERGENCY Al~ SOURCE
STATIC
i
ALTIMETER
STATIC LINE DRAIN
VERTICAL SPEED INDICATOR PITOT LINE PITOT MAST AND HEAD
NOTE On serials EA-242, EA-273 and after the pitot mast is moved to outboard of wing station 191.
36-341-9
Pitct and Static
Figure
System
1
"END"
34-10-00
Page 3 A4
Jan 20/82
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
INDEPENDENT POSITION DETERMINING DESCRIPTION AND OPERATION WEATHER RADAR The weather scout 1 consists
primarily of
two items: the
panel, and right wing. There is also supporting equipment, such as a larger capacity engine driven air pump, electrical wiring, plumbing, etc. When the radar unit is turned on, there is a 30 to 40 second warm-up period with the word WAIT displayed on the screen. After WAIT disappears from the screen, there is a delay of approximately four minutes before the radar will function. ~lt is required that ventilation air be pumped through the antenna bay for approximately 4.5 minutes before the antenna will energize.) indicator in the radio section of the instrument the antenna in the outboard section of the
bay of all fuel fumes before the antenna comes special fiberglass covering of the radar antenna is manufactured of three layers of 181 Volan, Epon 828 resin, Furane 951 hardener, Flex-T flexolizer. Any area of the fiberglass through which the radar will either transmit or receive should NOT be repaired. antenna on.
The
DETERMINING
INDEPENDENT POSITION MAINTENANCE PRACTICES WEA THER RADAR RADAR ANTENNA REMOVAL
Locate the antenna in the outboard leading
a.
of the
edge
right wing.
b.
Remove the
fiberglass
antenna cover from the
wing leading edge. c.
WARNING
Remove the four bolts (2
d.
the outboard end
When the radar is on, personnel should not be within three feet of the radar antenna. This
complete 180" are in front of the reproductive and other vital organs of the body are particularly vunerable to radiation damage.
disconnect the air line connector.
includes the
e.
f.
end) from the
on
Disconnect
the
are
accessible.
electrical connector, then
Remove the antenna.
RADAR ANTENNA INSTALLATION a.
delay of 4.5 minutes starts upon completion of two actions: (1) the radar is turned on, 12) there is air pressure equal to approximately two inches of water in the air supply line to the antenna. (The sense switch is located in the air line near the antenna.) This air flow purges the The time
each
Pull the inboard end of the antenna forward untir
the connectors
antenna. The eyes,
on
antenna.
b.
Place the antenna in the wing. Connect the airline connector, then connect the
electrical connector. c.
mounting location place. Install the fiberglass cover on the wing. Place the antenna in its
install the four bolts which
d.
secure
and
it in
34-40-00
Pagel Oct 1 0/8a
BEECHCRAFT BONANtA SERIES MAINTENANCE MANUAL
RADAR
_I
INDICATOR
I
I_
I
I
INSTRUMENT
I
AIR PUMP
STA. 66.00
POLYETHYLENE TUBING AROUND RADAR WIRE BUNDLE
L---+tt~-- STA.122.750
8 VENT TUBE
RADAR ANTENNA
STA. 148.875
r
38´•83-34
Radar Schematic Figure 1
"EPID"
34-40-00
Page2 Oct 10/80
CHAPTER
OXYGEN
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 35
OXVGEN
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
SUBJECT
35-00-00
GENERAL
Description
and
........1
Operation
............2
Maintenance Practices
(0-10097, D-10120 and after; CE-748, CE-772 and after, E-llll, E-1241 through E-2110 except E-1945 and E-2104; EA-1 through EA-388 except EA-320 Oyxgen High Pressure Test Procedure (D-10097, D-10129 and after; CE-748, CE-772 and after, E-1111,E-1241 through E-2110 Except E-1945 and E-2104; EA-1 through EA-388 except EA-320) Oxygen Low Pressure Test Procedure (E-1946, E-2104, E-2111 and after; EA-320, EA-389 and after) Oxygen High Pressure Test Procedure (E-1946, E-2104, E-2111 and after; EA-320, EA-389 and after) Oxygen System Purging Oxygen Cylinder Removal (D-10097, D-10129 and after; CE-748, CE-772 and after; E-llll, E-1241 through E-2110 except E-1946 and E-2104; EA-1 through
Oxygen
PAGE
Low Pressure Test Procedure
EA-388 except EA-320) Oxygen Cylinder Installation (D-10097,
.........2
.............2 ............2 ............3
..........6 D-10120 and after;
CE-748, CE-772 and after, E-llll, E-1241 through E-2110 except E-1946 and E-2104; EA-1 through EA-388 except EA-320) Oxygen Cylinder Removal (E-1946, E-2104, E-2111 and after; EA-320, EA-389 through EA-439) Oxygen Cylinder Installation (E-1946, E-2104, E-2111 and after; EA-320, EA-389 through EA-439)
after)............. (EA-320, Oxygen Cylinder Oxygen Cylinder Installation (EA-320, EA-440 and after) Oxygen Control Cable Adjustment (E-1946, E-2104, E-2111 and after; EA-389 through EA-439) Oxygen Control Cable Adjustment (EA-320, EA-440 and after) Oxygen Cylinder Retesting Removal
........2
EA-440 and
........6
.........6
................6 .........7 ............7
:............7 ............8 .......8
"END"
35-CONTENTS
Page 1 S´•p 27184
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 35 LIST OF PAGE EFFECTIVITY CHAPTER SECTION PAGE
SUBJECT
DATE
35-EFFECTIVIN
1
Sep
27184
35-CONIENTS
1
Sep
27184
1
Sep Sep Sep Sep Sep Sep Sep Sep
35-00-00
2 3 4 5
6 7 8
27184 27/84 27/84
27/’84 27/84 27/84 27184 27/84
"END"
35-EFFECTIVITY
Page A9
Sep
1
27184
BEECHCRRR~ BONANZA SERIES MAIMENANCE MANAUL
DESCRIPTION AND OPERATION
GENERAL
optional oxygen system in the Bonanza series airplanes (except EA-320, EA-440 and after) has an oxygen cylinder attached to the floor in front of the spar carry through. The filler valve is attached to the spar cover below the copilots seat. The oxygen console to the left of the pilot contains the pilot’s outlet and the pressure gage. On some airplanes (prior to E-2111, except E-1946, E-2104; and prior to EA389 except EA-320), the oxygen console also contains a shutoff valve and the pressure regulator mounted on the The
back of the console. This system also has a shutoff valve mounted on the oxygen cylinder. On serials E-1946: E-
2104, E-2111 and after; and EA-320, EA-389 and after, cable operated shutoff valve mounted on the oxygen cylinder. The push-pull knob for this shutoff valve is in the subpanel below the pilot’s control column. On serials there is
one
EA-320, the
and after the oxygen filler valve, shutoff valve(s), and reSlulator(s) are mounted in outboard of wing station 66.
EA-440
cylinder(s), wing(s)
automatically dump the oxygen any time the cylinder pressure reaches between 2500 and 2775 psi. There is an indicator (placarded OXY, H.P. Relief) under each wing which will rupture any time the
is activated.
dump system
The shut-off valves(valve) are(is) controlled by a push-pull knob (Figure 4) in the pilots subpanel. The oxygen pressure gage and pilots outlet are located in the pilots left side panel while the
copilots
outlet is located in the
right
side
stowed in
box under their seats. At serials EA-320, EA-
a
pilot may be stowed place he considers convenient. The third and fourth
389 and after, the mask for the
arrangement. The oxygen masks for the fifth and sixth are
stowed in
Access to the filler valve and pressure gage is gained by removing the access panel located on top of the left wing aft
passengers and the pilot. On earlier airplanes the oxygen outlets are all in the sidewalls of the airplane. On serials CE919, CE-923, CE-925, CE-927, CE-929 and after; CJ-156
system
and after; D-10348, D-10353 and after; E-1422, E-1551, E1569, E-1581, E-1594 and after; EA-21, EA-28, EA-33 and
76.5-cubic foot
airplane. The oxygen
of the
masks for the
pilot
on E-1946, E-2104, E-2111, and after; EA-320, EA389, and after) and the copilot are stowed in a box under their seats. At serials E-1946, E-2104, E-2111, and after;
(except
EA-320, EA-289, and after, the mask for the pilot may be stowed in
a
place
he considers convenient. The third and
fourth seat oxygen masks are stowed in a box attached either to the front or rear of the rear spar, depending upon the seating arrangement. The oxygen masks for the fifth and sixth seats
are
stowed in
a
box attached to the bottom
of their seats,
Starting
with
serials
EA-320 and
A 49.8-cubic foot oxygen cylinder is the normal optional on all Bonanza’s except EA-320, EA-440 and after.
At serial E-1241
and after, and EA-2
optional cylinder
320, EA-440 and after, either foot system is offered. The 50 psi at pressure of 1850
its
49-cubic foot
cylinder
or
98-cubic
should be filled to
a
a
element
sensing
meets
increases
in
altitude with
increased oxygen flow. When the system is not in use, shut off the control valve to prevent oxygen loss. For system servicing refer to Chapter 12.
mounted in the left
WARNING
sparks away when and close all oxygen Make sure the oxygen shut-off
Keep fires, cigarettes are
Mounted on the end of each cylinder is the altitude compensating regulator, overboard dump, and the shut-off valve. The cylinders are mounted in the wing aft of the main spar outboard of wing station 66. The filler valve and a pressure gage are mounted in the top of the wing outboard of wing station 66 and aft of the main spar. There is an ov’erboard dump system on each cylinder which will
valves
slowly,
cylinder
a
of oxygen available. The altitude compensated pressure regulator limits system operation to above 8,000 feet, where
outlets
49-cubic foot
a
through EA-388,
is offered. At serials EA-
temperature of 70 degrees F. This pressure may be increased 3.5 psi, for each degree of temperature increase, or lowered 3.5 psi, for each degree of temperature decrease. The pressure gage is connected directly to the oxygen cylinder and indicates the supply (psi.)
wing only.
one
access
EA-440 and after, the
B36TC oxygen system (Figure 3) has wing mounted oxygen cylinders. The 98-cubic foot system has one 49-cubic foot cylinder mounted in each wing. The 49-cubic foot system has
seats
box attached to the bottom of their seats.
a
of the main spar outboard of Wing Station 66. The panel is held in place by six Dzus fasteners.
center
in a seat
oxygen masks are stowed in a box attached either to the front or rear of the rear spar, depending on the seating
The oxygen system in the Bonanza Series airplanes may be equipped with oxygen outlets for either 3, 4, or 5
after, the oxygen outlets for the pilot and copilot are in the sidewall, while the other outlets are in the headliner near the
panel.
The five passenger outlets are located in the headliner near the center of the airplane. The oxygen masks for the pilot (except on EA-320, EA-389, and after) and copilot are
in use.
and
Open
position. Inspect the filler attaching it to the filler valve. Keep tools, hands and components clean, as fire or explosion may valve is in the closed
connection for cleanliness before
occur
when pure oxygen comes in contact with material such as grease or oil.
organic
35-00-00
A9
Pagal Sep 27/84
BEECHCRAFT BONANZA SERIES MAINTENANCE MANAUL
MAINTENANCE PRACTICES
GENERAL
Observe the pressure gage on the oxygen d. console; there should be a pressure drop of no more than 400
CAUTION Ail
persons
handling
and
Circular
43.13-1A
If the test was satisfactory, turn on the oxygen supply at the oxygen cylinder. If a leak was detected, check the suspected areas with leak test compound, (13, Chart 1, 91-00-00) and repeat steps "c" through "e". f. After the test, wipe the area clean and dry.
servicing oxygen
during servicing. contains
in 5 minutes.
a.
systems should review proper precautions observed
psi.
to be
FAA
Advisory
the
necessary
iniormation.
OXYGEN LOW PRESSURE TEST PROCEDURE (E-
I
OXYGEN LOW PRESSURE TEST PROCEDURE (D10097 0-10120 and after; CE-748, CE-772 and afte~´• E-llll, E-1241 through E-2110 except E-1946an~j E-2104; EA-1 through EA-388 except EA-320)
‘WARNINO
Keep fire, cigarettes and sparks away from the vicinity of the oxygen cylinder. Hands, clothing
WARNING
and tools should be clean. Oil and grease will ignite upon contact with pure oxygen under
sparks away from the oxygen cylinder. Oil and grease
Keep fire, cigarettes vicinity of the will ignite upon
EA-320, EA-389,
1948 E-2104, E-2111, and after)
and
and
contact with oxygen
pressure.
under
pressure. a.
Turn the oxygen to the full off position (use the
push-pull knob). Turn the valve
a.
off
on
the oxygen
cylinder
to the full
position.
Disconnect the oxygen cylinder from the regulator regulator and cap the open lines. c. Plug a 0 to 100 psi. pressure gage into any outlet except the pilot’s outlet. d. Pressurize the system 50 to 55 psi. and allow the b.
at the
system
to stabilize for 2 minutes.
should not
the
following exceed 5.0 psi.
During
e.
drop
if the pressure test is satisfactory, reconnect the pressure lines disconnected in step "b".
Pressure test the connections made in step "f"
g.
using cylinder pressure (1500 psi. or higher), compound, (13, Chart 1, 91-00-00). h. After the test, wipe the area clean
I
Disconnect the oxygen low pressure lines from cap the open lines.
regulator(s) and c. Plug a O to
100 psi. pressure gage into any outlet. Pressurize the system to 50 to 55 psi and allow the system to stabilize for 2 minutes.
d.
e.
During the
ncmt 15 minutes the pressure
should not exceed 5.0
drop
psi.
If the pressure test is
f.
15 minutes the pressure
f.
high
b. the
satisfactory,
reconnect the
lines disconnected in sl:ep "b". Pressure test the connections made in step "f" g. using cylinder pressure (1500 psi, or higher in the cylinder),
and leak test h.
compound, (13, Chart 1, 91-00-00). wipe the area clean and dry.
After the test,
and leak test and
OXYGEN HIGH PRESSURE TEST PROCEDURE (E1946, E-2104, E-2111, and after; EA-320, EA-389,
dry.
OXYGEN HIGH PRESSURE TEST PROCEDURE (D10097 0-10120 and after; CE-748, CE772 and after E-llll, E-1241 through E-2110 except E-1946 E-2104; EA-1 through EA-388 except EA-320)
and after)
ancj
Check to make certain the system is charged to
a.
1500
psi.
or
higher.
Make
b.
sure
the shut-off valve
on
the oxygen
Turn off the oxygen
Keep fire, cigarettes and sparks away from the vicinity of the oxygen cylinder. Hands, clothing and tools should be clean. Oil and grease will upon contact with pure oxygen under
ignite
console is turned oft. c.
WARNING
supply
at the oxygen
cylinder.
pressure.
3540-00
Pagea Sep 27/54
Ag
BEECHCRAFI BONANZA SERIES MAINTENANCE NIANAUL
CENTER SEAT OUTLET AFT SEAT
PRESSUREOXYGEN
OUTLETS
GAGE
PILOT’S OUTLET
PRESSURE REGULATOR
(BACK SIDE)
7
?i
OXYGEN ~i SHUT-OFF
VALVE
GEN CYLINDER COVER ASSEMBLY
CENTER SEAT OUTLET i´•i
RH FRONT SEAT
_i~X-´•
RECHARGE NOZZLE
OUTLET
38-452-1
Oxygen System (Prlor to 02-929 except 02-919, CE´•9S3, 06-925, 06-927; to 01-156; prior to 0-16353 except 0-10348; prior to 2-1594 except 2-1422, 2-1551, 2-1569 and 2-1581; prior to EA9S except EA-21 and EA-28) Figure 1
prior
a.
1500
psi. b.
the
Check to make certain the system is or
charged
to
OXYGEN SYSTEM PURGING
higher.
Make
sure
the shut-off
valve(s) is(are) off (check WARNING
push-pull knob).
c. one of the pressure gages, there should be no pressure drop in 30 minutes. d. If the leak test is not satisfactory, use leak test
Observe
compound (13, Chart 1, 91-00-00)
on
the
system
connections until the leak is located. e.
Make the necessary repairs and repeat step "c".
f.
Wipe
the tested areas clean and
dry.
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
Do
oxygen system. When filling the oxygen system, use only MIL-0-27210 Aviator’s Breathing
Oxygen (10, Chart 1, 91-00-00).
35-00-00
A9
Page3 Sep 27/84
BEECHCRAFT BONANZA SERIES MAINTENANCE MANAUL
OXYGEN
PRESSUREPILOTS OUTLET GAGE
E-1946. E-2104, E-2111, and after; EA-389 thru EA-439
VALVE
~ETAIL E
OXYGEN CYL)NDER COVER ASSEMBLY
C~
B RECHARGE NOZZLE
MANIFOLD OUTLET
DETAIL
A
DETAIL
C
b D
OUTLET
DETAIL
B
TO PUSH-PULL
KNOB
E-1946, E-2104, E-2111, and after; EA-389 thru EA-439
DETAIL
D 836TC´•a41-35
Oxygen System (00-919, CE-923, CE´•925, CE-927, CE-929
and after; CJ-155 and after;
0-10348, 0-10353 and after; 0-1422, 0-1551, 0-1589, 0-1581, 0-1594 and after; EA-21, EA-28, EA-33 through EA-439 except EA-320)
Figure
2
351)0-00
Page4 Sep 27/84
A9
BEECHCRATT BONANZA SERIES MAINTENANCE MANAOL
CONTROL KNOB, PILOTS
I
OUTLET--\
I
L
/iSUBPANEL
\rCOPILOTS
OUTLET
PRESSURE 94.094
66
66
94.094
49 CU. FT. OXYGEN
FILLER
49 CU. FT:
]VALVE
OXYGEN CYLINDER
I.´•GAGE
CYLINDER
GAGE
OVERBOARD DUMP
OVERBOARD DUMP 3rd,4th 51h,6th SEAT OUTLETS
B36TC340-~
Oxygen System (EA-320, EA940 and after) Rgure 3
Offensive odors may be removed from the oxygen system
by purging. The system should also be purged any time the lines are left open and subject to contamination. Purging is accomplished by connecting a recharging cart into the system and permitting oxygen to flow through the lines and outlets until any offensive odors have been carried away, The following steps outline the procedures recommended for
purging the oxygen system.
grease and oil stains, for these contaminants will ignite upon contact with oxygen.
Connect
a.
a
line
from
a
recharging
cart
to the
oxygen filler valve. b. Slowly open the oxygen supply. c. Slowly open the valve which allows oxygen to flow through the mask outlets d.
e.
Plug in an oxygen cockpit. Open all doors and
f.
Set the cart pressure
mask at each outlet in the
cabin and
WARNING
making sparks and keep all burning cigarettes or fire away from the vicinity of the airplane when the outlets are in use. Inspect the Avoid
filler connection for cleanliness before
tools, and clothing
are
attaching
that your hands, clean, particularly from
it to the filler valve, Make
sure
windows.
regulator
to deliver 50
psi
to
the system.
Allow system to purge for one hour and check for g. the presence of odor. If the odor is still present, continue
purging after
for
the
one
additional hour. If the odor is still present hour of purging, replace the supply
second
cylinder.
35-0040
Ag
Page5 Sep 27184
BEECHCRAFT BONANLA SERIES
MAINTENANCE MANAUL
OXYGEN CYLINDER REMOVAL (0-10097, 0-10120 and after; CE-748, CE-772 and after; E-l I 11, E-1241 through E-2110 except E-1946 and E-2104; EA-I tlA-388 except
through
OXYGEN CYLINDER REMOVAL
EA-330)
Remove the
AND COPILOT SEAT REMOVAL in
Chapter 25-00-00.)
Remove the spar cover. Disconnect the control cable from the oxygen
c.
d.
Keep fire, cigarettes and sparks away from the vicinity of the oxygen cylinder. Mands, clothing
E-
Make certain the system is turned off. pilot’s and copilot’s seat. (See PILOT
a.
b.
WARNING
(E-1946, E-2104,
and after; EA-389 through EA-439)
2111
valve.
and tools should be clean. Oil and grease will ignite upon contact with pure oxygen under
WARNING
pressure.
Keep fire, cigarettes and sparks away from the vicinity of the oxygen cylinder. Hands, clothing
close the oxygen supply cylinder valve. Remove the pilot’s and copilot’s seat. (See PILOT
Slowly
a.
b.
AND COPILOT SEAT REMOVAL in
and tools should be clean. Oil and grease will ignite upon contact with pure oxygen under
Chapter 25-00-00.)
Remove the spar cover. Disconnect the line from the supply cylinder. Cap the open line immediately with a clean metal
c.
d. e.
pressure.
fitting. clamp wing nuts. cylinder clamps and remove
f.
Loosen the bracket
g.
Unhook the
cylinder
CAUTION the
Care must be exercised to prevent accidentally turning the oxygen on. Some oxygen will be lost
from the brackets.
OXYGEN CYLINDER INSTALLATION (0-10097, D10120 and after; CE-748, CE-772 and after; E- 1111, through E-2110 except E-1946 and E-2104;
when the lines
high
are
disconnected, especially the
pressure line.
1421-E)023-AE
through EA-388 except
EA-1
a.
cap
or
f.
WARNING
Disconnect the lines from the oxygen cylinder and the openings.
plug
Loosen the wing nuts
disconnect the
Keep fire, cigarettes‘ and sparks away from the the oxygen cylinder. Hands, clothing
g.
on
the
cylinder clamps
and
clamps.
Remove the oxygen
cylinder.
vicinity of
and tools should be clean. Oil and grease will ignite upon contact with pure oxygen under
OXYGEN CYLINDER INSTALLATION
pressure.
2104, E-2111 and after; EA-389 through EA-439) a.
Place the
a.
the
new
cylinder
in the brackets and close
c.
and the
Tighten the bracket clamp wing nuts. Carefully inspect the fittings on both the cylinder line for cleanliness and the presence of foreign
cylinder
in the proper
position
in the
airplane. b.
Connect the
cylinder clamps
c.
Remove the
plugs
cylinder clamps. b.
Place the
(E-1946,
and tighten the
wing
nuts. or
caps and install the oxygen
lines.
matter, which may contaminate the oxygen until it is unfit for
breathing. d. e.
f.
Connect the line fitting to the cylinder fitting. Slowly open the supply cylinder valve. Test the connections for leaks with Oxygen
System Leak-Test Compound, (13, Chart i, 91-00-00). g. h.
Install the spar cover, Install the seats. (See PILOT AND COPILOT
SEAT INSTALLATION in Chapter 25-00-00.)
WARNING
Keep fire, cigarettes and sparks away from the vicinity of the oxygen cylinder. Hands, clothing and tools should be clean. Oil and grease will ignite upon contact with pure oxygen under pressure.
35-00-00
PageG Sep 27/84
A9
BEECHCRAFt BONANZA SERIES MAINTENANCE MANAUL
OXYGEN CYLINDER INSTALLATION (EA-320, EA-
CAUTION
alter)
440 and Care must be exercised to prevent accidentally turning the oxygen on. Some oxygen will be lost when the lines are connected,
high
especially
the
a.
wing
cylinder
Position the oxygen
in
in the
position
clamps.
and connect the
Check to be certain the cylinder is in the proper position and tighten the clamp wing nuts. Safety wire the b.
pressure line,
nuts.
Connect the control cable to the oxygen valve, Check for leaks as indicated in OXYGEN LOW
d. e.
c.
Remove the caps or plugs from the connection install the oxygen lines.
points and
PRESSURE TEST PROCEDURE (E-1946, E-2104, E-2111 and after; EA-320, EA-389, and after) and in OXYGEN
HIGH PRESSURE TEST PROCEDURE (E-1946, E-2104, E-2111, and after; EA-320, EA-389 and after). f. Install the spar cover.
CAUTION
(See PILOT g. AND COPILOT SEAT INSTALLATION in Chapter 25-0000.)
If there is oxygen in the cylinder, there will be some oxygen lost when the high pressure lines
Install the
pilot’s and copilot’s
seats.
are
connected, particularly the pressure gage
line.
OXYGEN CYLINDER REMOVAL (EA-320, EA-440 and
after) Turn the oxygen off. Locate the oyxgen cylinder
a.
b.
under the
wing
ah of the main
Station 66. Remove the c. remove
d.
cylinder
the
screws
WARNING
panel located spar and outboard of Wing access
from the access
Keep fire, cigarettes and sparks away from the vicinity of the oxygen cylinder. Hands, clothing and tools should be clean. Oil and grease will upon contact with pure oxygen under
panel and
ignite
panel.
Disconnect the control cable from the oxygen valve.
pressure.
d.
WARNING
Connect the control cable to the oxygen
cylinder
valve. a.
Check for leaks
as
indicated in OXYGEN LOW
Keep fire, cigarettes and sparks away from the vicinity of the oxygen cylinder. Hands, clothing
PRESSURE TEST PROCEDURE (EA-320, EA-440 and after) and OXYGEN HIGH PRESSURE TEST
and tools should be dean. Oil and grease will ignite upon contact with pure oxygen under
PROCEDURE
pressure.
(EA-320,
If the pressure tests access cover under the wing.
OXYGEN CONTROL
CAUTION
EA-440 and
f.
are
after).
satisfactory,
install the
CABLE ADJUSTMENT
(E-
1946, E-2104, E-2111, and after; EA-389 through EA-
439) Care must be exercised to prevent accidentally turning the oxygen on. Some oxygen will be lost when the lines are disconnected, especially the
high
a.
b.
Disconnect the lines from the oxygen regulator and cap or plug the openings. Loosen the wing nuts on the cylinder clamps. f. Position a suitable cradle under the oxygen g. e.
and disconnect the
pilot’s and copilot’s seats. (See Chapter 25-00-
00.)
pressure line.
clamps.
Remove the spar carry through cover. control cable by repositioning
Adjust the cable, cable housing c.
cylinder
Remove the
PILOT AND COPILOT SEAT REMOVAL in
d. e.
or
the
both.
Install the spar carry Install the pilot’s and
through copilot’s
cover.
(See Chapter
seats.
AND COPILOT SEAT INSTALLATION in
PILOT 25-00-
00.) 35-00-00
A9
Page7 Sep 27/84
BEECHCRAFt BONANZA SERIES
YAINTENANCE MANAUL
OXYGEN CONTROL CABLE ADJUSTMENT
(EA-
320, EA-440 and after)
4,380 pressurizations, whichever service life of the
cylinder
is
occurs
complete,
the
first. When the
cylinder
must be
discarded. The control cablets) may be adjusted either in the wing(s) at the valvets) or at the push-pull knob (Figure 4) just fomard
SUB PANEL
subpanel. Coarse adjustments may be made at the velvets) by repositioning the cable, cable housing, or both. The velvets) is located on the cylinder of the instrument
above
an access
panel
outboard of
Wing Station
66 and ah
of the main spar. Finer adjustment of the system cables may be made at the push-pull knob tFigure 4) just forward
of the instrument
subpanel. On the two cylinder system or on simultaneously.
both
valves should turn off
CONTROL CABLES
OXYGEN CYLINDER RETESTING
airplanes are the light weight plate on the side of each cylinder. Each oxygen cylinder must be hydrostatically tested every three years and the test date stamped on the cylinder. The cylinder has a service life of 24 years and/or
Oxygen cylinders
used in the
type, stamped "3 HT"
on
836TC-340-3
a
Oxygen Shut-Otf Cs~ntrol
Figure
4
"END"
35-00-00
Page8 Sep 27/84
A9
CHAPTER
PNEUMATIC
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 36
PNEUMATIC
’T~ABLE OF COWTENTS
CHAPTER SECTION SUBJECT
SUBJECT
36-00-00
PNEUMATIC
Description
and
EA-443 and after, CJ
airplanes
Troubleshooting
.......1
System
Instrument Air
and earlier
..................1
Operation
Instrument Air
Standby
PAGE
System (E-2217
and after,
-156 and after, CE-1056 and after, with Kit No. 35-5009
Instrument Air
installed)
.......1
3
System
..3
Maintenance Practices
Servicing
.......3
Low Instrument Air Pressure
.......3
Air Filter Removal
Standby Standby
.......4
(Intake)
Air Filter Removal
........5
(Intake) (Intake)
.......5
Air Filter Installation
Air Filter Removal
(Inline) (Inline)
.......5
Air Filter Installation
Standby Standby Pressure
Air Filter Removal
(]nline) (Inline)
........5
Air Filter Installation
...............6
Removal
Regulator Regulator Installation Pressure Standby Regulator Removal Pressure Standby Regulator Installation Pressure Standby Regulator Adjustment (E-2164 and after, EA-422 and after) Pressure RegulatorAdjustment
........6
Pressure
........6 ........6
..........6 ...........7
’LEND"
36-CONTENTS
Page A12
1
Aug 28/87
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 36 LIST OF
PAGE EFFECTIVITY
CHAPTER SECTION SUBJECT
PAGE
DATE
36-EFFECTIVITY
1
Aug 28/87
36-CONTENTS
1
Aug 28-87
1 2 2A 3 4
Aug 28/87 Sep 27/84
36-00-00
5 6 7
Aug 28/87 Sep 27/84 Sep 27/84 Sep 27/84
Aug 28/87 Aug 28/87
"END"
36-EFFECTIVITY
Page A12
Aug 28/87
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
PNEUMATIC ATION INSTRUMENT
gage is in instrument panel.)
DESCRIPTION AND OPER-
pressure
the
left side of the
SYSTEM
AIR
SYSTEM AIR INSTKUMENT AND EA- 443 AND AFTER, CE-1056 AND AFTER, AFTER, CJ-156 AND AFTER, AND EARLIER AIRPLANES WITH KIT NO. 35-5009 INSTALLED) STANDDY
(E-2217
instrument air pressure system provides air for operation of the directional and the horizon gyro. Air is drawn gyro through an inlet air filter mounted on the baffle by the dry air pump. rear eng~ne The air is then routed through the air filter to pressure regulator and inline the gyros. The regulator, which is located nearthe inline filter on the rear engine baffle, should be adjusted to a pressure 5.0 Hg. The 5.0 Hg pressure setting is taken between the regulator and the inline filter (see Figure i).
The
CAUTION
Never been
lof
use
an
dropped
air pump which mishandled.
has
or
standby instrument air pressure system provided to supply instrument air in the the event primary instrument air
A
is
The system incorpump which is driven by an electric motor, a pump intake filter which is mounted on the underside of the engine, an inline filter and a pressure
Instrument air pressure is monitored by located in the instrument air gage the of the instrument side panel. upper right (At serials E-1946, E-2104, E-2111 and after; EA-320, EA-389 and after, the
system
pressure
porates
fails.
pressure
a
------r
1/’
I/
OVERBOARD GYRO PRESSURE INDICATOR CTION GYRO
CHECK VALVE
HORIZON GYRO
CHECK VALVE VENT LINE PRESSURE LINE
MANIFOLD
INLINE( FILTER
)INLINE
Y
Y
TEST GAGE
PRESSURE REGULATOR
PRESSURE
TEST GAGE
~PRESSURE
Y
Y
PUMP(
(ENGINE DRIVEN)
FILTER
t----( INTAKE
INTAKE
FILTER
FILTER
REGULATOR
)STANDBY
PRESSURE PUMP
(ELECTRIC) 36-603-50
Pressure
System Schematic Figure 1
36-00-00 P´•age 1
A´•ug 28/87
BEECHCRAFT BONANZA SERIES MA i NTENANCE MAN UAL
:Oo
n FIL’TER
I
;´•C
NOSE LANDING GEAR KEEL
;f FILTER
REGULATOR
CHECK VALVE ASSBWBLY
PUMP
MOTOR
36-194-10
Standby
Instrument Air Figure 2
System
36-00-00 Page 2
Sep 27/84
A9
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
regulator. The standby system is controlled by an ON/OFF toggle switch, placLH arded STANDBY GYRO P, located on the subpanel. When the system is activated, a solenoid valve, mounted in the pressure supply line just aft of the firewall fit-
all air isolates automatically ting, driven instruments except the directional gyro and the horizon gyro. The standby air pressure system is plumbed into the pri-
system ducting by use of a manifold with check valves to prevent backflow. mary
36-00-00 Page 2A
A12
Aug 28/87
BEECHGRAFT BONANZA SERIES MAINTENANCE MAN UAL
CHART 1 TROUBLESHOOTING INSTRUMENT AIR SYSTEM PROBABLE CAUSE
INDICATION
Zero
i.
indication
on
a.
instrument gage,
b.
REMARKS
Hole in gyro plumbing, line plugged, filter plugged or disconplumbing nected. Defective
Inspect plumbing, replace or lines connect or replace
a.
filter
b.
instrument
Replace
as
necessary.
gage.
pressure gage. c.
Defective gyro horidirection ton or
Inspect replace as
c.
instrument
and
necessary.
gyro.
d. Defective pump. e.
Defective
regulator.
d.
Replace
e.
Replace regulator.
pump.
NOTE
Troubleshooting pressure systems
GENERAL
procedures are
the
for
the
primary
and
standby
air
same.
MAINTENANCE PRACTICES
structure.
RH
the
SERVICING
,ressure
The inline filter is mounted in
engine compartment between the regulator and the instruments, at
The stations 28.25 and 30.75. filter should be replaced every 500 ours or on condition and the inline filter should be replaced every 300 hours or ~n condition.
~uselage
Impurities and foreign matter are removed from the air by two pressure system filintake filter is located on the ahead of the pressure pump. This filter;hould be replaced annually or every 300 to 500 hours of service time depending upon operating conditions. The filter element must not be subjected to solvents and must be replaced if this occurs. Always reinstall the filter cover with the opening facing down. The inline filter is located between the pressure regulator and the instruments. The frequency of replacing this air filter will ters.
The
top of the engine
se rv i ce conditions; depend upon however,they should be checked approximately every 100 hours of operation and replaced every 300 hours of operation, or
sooner
if conditions warrant.
intake filter for the standby instruair system is located on the underof the engine attached to the keel side
The
ment
intake
localities where there dust or sand in the air, the filters should be replaced at more frequent intervals. Under extremely dusty conditions, it may be necessary to inspect the filters daily. A clogged filreduces air flow and slows up the ter rotor, causing improper gyro indication due to a loss of gyroscopic inertia. When
is
a
operating
great
in
amount
of
LOW INSTRUMENT AIR PRESSURE If the pressure pump has failed or operation of the instruments indicates a flucof the tuation or a system pressure
36-00-00 Page 3 A9
Sep
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
decrease in system excessive pressure, the in lines,
pressure, a
partial
a
filter
check for restriction
from
or
may be checked
by: the and
Removing
a.
the system obstructions to flow with
inline
checking by comparing the a
new
for
bends,
kinks
partially
loss resulting pressure loose connections. These conditions
obstructed,
Check the lines c. and excessive carbon.
filter it
from for
resistance
the
or whendiscrepancy repaired in the are replaced any components system, adjust the pressure as pressure indicated under the heading PRESSURE REGULATOR ADJUSTMENT in this Chapter.
With
ever
AIR FILTER REMOVAL
(INTAKE)
(Figure 3)
filter. NOTE
a.
Gain
access
to the filter
by open-
ing the left engine cowling. Use
a
dry, low
pressure air source for this test. If
(10 psi maximum)
Remove the nut, b. from the filter.
flow resistance in the filter removed from the airplane exceeds that of the new filter by more than 1.0 psi, replace the filter, air
Check
b.
all
connections
for
c.
secures
tight-
d.
the Remove the filter.
washers, and
cover
and
which
spacer
nut
Remove the filter.
ness.
FILTER CARTRIDGE
(FOR REPLACEMENT ORDER P/N 09-14-1)
NAS43003-24 SPACER
AN315-3R NUT
NUT
I
I
1j/I I;
.1.....
AN936AIO
LOCK WASHER 970-3 WASHER
AN960PD1716 WASHER
L
FILTER RETAINER NUT AND WASHER 570-190-19
Intake Air Filter Figure 3
3S-00-00
Page 4 Sep 27/84
A9
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
AIR FILTER INSTALLATION
(INTAKE)
d.
Close the engine
I
cowling.
(Figure 3) a.
Install
the filter and
with
secure
the nut. AIR FILTER REMOVAL
Install the spacer and cover should be installed with opening facing down. b.
c.
Secure the
cover
cover.
the
cover
a.
the the
Open
filter
engine
the engine attached to baffle.
b. Remove the from the filter.
Close the
cowling and locate bracket below
the
with the washers
and nut,
d.
(INLINE)
the
inlet and outlet hoses
Remove the nut and washer which c. hold the filter in place.
engine cowling.
(INTAKE)
STANDBY AIR FILTER REMOVAL
d.
(Figure 3)
Remove the filter.
Gain access to the filter by opene. RH the engine cowling. ing
(INLINE)
AIR FILTER INSTALLATION a.
NOTE
secure
b. hoses.
standby system intake filter
The
the underside of the engine attached to the keel strucis mounted
on
ture.
c.
Place the filter in with washer and nut.
position and and
Install
the
Close the
engine cowling
inlet
STANDBY AIR FILTER REMOVAL
f. Remove the nut, from the filter. g. secures
h.
Remove the the filter.
washers, and
spacer
and
nut
AIR
FILTER
(INLINE)
cover
which
a. Open the RH engine covling and locate the filter attached to the bracket below the engine baffle.
b. Remove the inlet and outlet hoses from the filter.
Remove the filter.
STANDBY
outlet
INSTALLATION
the nut and Remove c. hold the filter in place. d.
was7er
which
Remove the filter.
STANDBY
AIR
FILTER
INSTALLATION
(INLINE) a.
Install
the filter and
with
secure
the nut.
a. secure
Install the spacer and should be installed with opening facing down. b.
cover
c.
Secure the
cover
cover.
position and
The
cover
b. hoses.
with the washers
c.
the
Place the filter in with washer and nut. In stall
the
Close the
engine cowling
inlet
and
outlet
and nut.
36-00-00 A9
Page 5 Sep 27/84
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
REGULATOR
PRESSURE
REMOVAL
Gain
a.
the
to
access
regulator by
opening the engine cowling.
Open the engine cowling and regulator.
a.
locate
the pressure
Install a test gage (0-10 psi) in side of the pressure regulator.
b.
the
"out"
Remove the inlet and outlet hoses.
b.
NOTE c.
secure
Remove the nut and washer the regulator in position.
d.
Remove the
which
During this voltage must +0.3 volts.
regulator.
auxiliary
an
REGULATOR
PRESSURE
Place the
a.
position.
in
Install
the nut and washer,
With
c.
the b.
power
primary ON
turn
the engine instrument
the
standby
breaker in the LH Install
c.
the
inlet
and
d.
provide Close the
REGULATOR
air
and
running, system
OFF,
circuit
pump
subpanel.
Adjust the pressure regulator 5.0 +.1 -.2 psi as indicated
the instrument air pressure in the instrument panel.
engine cowling.
PRESSURE
STANDBY
NOT air
regube used.
outlet
hoses. d.
battery
supply,
lated to 28.5 ~.25 vdc,
INSTALLATION
regulator
procedure,
be maintained at 28.5 It is recommended that
gage
to on
mounted
REMOVAL
NOTE
Open
a.
the
RH
locate the pressure
engine cowling regulator.
and
Remove the inlet and outlet hoses.
b.
Rotate the adjusting screw clockwise to increase the pressure and counterclockwise to decrease the pressure.
c.
secure
Remove the nut and washer which the regulator in position.
Remove the regulator.
d.
STANDBY PRESSURE
REGULATOR
INSTAL-
LATION a.
Place the
b.
Install
c.
Install
regulator
in
position.
the nut and washer.
NOTE At should the time no gage installed in the "out" side of the pressure regulator indicate more than 5.0. If this is not enough for air satisfactory pressure instrument operation, the system has or a leak, blockage be restriction which must
repaired immediately. the
inlet
and
outlet
hoses.
e.
breaker Close the engine
d.
cowling. f.
STANDBY PRESSURE
REGULATOR
AFTERMENT jE-2164
AFTER,
AND
Turn the standby air pump circuit to OFF. on the LH subpanel
ADJUSTEA-422 AND
Remove
g.
Close
pri
procedure is performed with engine NOT running and the
ma
ry
instrument
turned off.
test
gage
from
the
the
engine cowling. NOTE
NOTE
This the
the
airplane.
air
system
When this procedure is completed, adjust the primary instrument air system as detailed under PRESSURE REGULATOR ADJUSTMENT in this
chapter. 36-00-00 Page 6
Aug 28/87
A12
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
NOTE
clockwi se the to regulator pressure increase the pressure and counterclockwise to decrease the pressure.
performing this procedure on airplane serials E-2164 and after and EA-422 and after, ensure that the standby air pressure system
Check the instrument air pressure With the the instrument panel engine operating at 800 rpm, the pressure should remain in the green are.
PRESSURE
REGULATOR ADJUSTMENT
d.
When
in
gage
is turned OFF.
NOTE Gain
a.
lator
access
to
the pressure regushould the ti me At no gage installed in the "out" side of the pressure regulator indicate more than 5.0 psi.
by opening the engine cowling.
Install a test gage (0-10 psi) at b. the "out" side of the pressure regulator. c.
4.5 psi
Adjust the pressure regulator on
regulator 2300 rpm.
to
the test gage at the pressure with the engine operating at Rotate the adjusting screw on
e.
Remove
the
test
gage
from
the
airplane. f.
Close the engine
cowling.
"END"
36-00-00 Page 7
A12
Aug 28/87
CHAPTER
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 39
ELECTRIC PANELS PARTS
INSTRUMENTS
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
SUBJECT
GENERAL
39-00-00
Description
and
PAGE
.......1
Operation ........´•.39-10-00
INSTRUMENT AND CONTROL PANELS Maintenance Practices
.......1
Glareshield Removal
.......1
Glareshield Installation
.......1
Engine and Flight Instruments Installation of Engine and Flight Instruments Removal of Engine Instrument Cluster Panel...... installation of Engine Instrument Cluster Removal of Radio/Avionics Equipment Installation of Radio/Avionics Equipment Right and Left Subpanel
.......1
Removal of
.......1
.......1 I..............
ELECTRICAL AND ELECTRONIC EQUIPMENT RACKS
.......1 .......1 .......2 .......2
39-20-00
Maintenance Practices
.......1
COMPONENT LOCATION ZONES
.......1
Area Between the Firewall and Instrument Panel
Airplane Zones
.......3
231 and 232
Side of
Forward, Right Firewall, the Engine compartment, and the
Area Which Includes the
Nose Landing Gear Well Airplane Zones 222/410/710
.......6
Area Beneath the Floor From the Firewall to the
Spar and From the Main Spat to the Rear Spar Airplane Zones 140 and 150 Area Which Includes the Wings and Main Landing Gears Airplane Zones 531 thru 650 and Main
.......9
;.....11
Zones 730 and 740
"END"
39-CONTENTS
Page
1
M´•y 9180
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 39 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT
PAGE
DATE
39-EFFECTIVITY
1
Oct 7/83
39-CONTENTS
1
May 9180
39-00-00 39-10-00
1
39-20-00
May
9i80
May
9180
2
Oct 7/83
3
Oct 7183
1
2 3 4
May May May May
9180 9180 9/80 9180
5
Jan 20/82
6
11
May 9180 May 9180 May 9180 May 9180 May 9180 May 9/80
12
Jan 20/82
7 8
9 10
"END"
~QEFFECTIVITY
Page A6
1
Oct 7/83
BEECHCRAFF BONANZA SERIES MAINTENANCE MANUAL
GENERAL
DESCRIPTION AND OPERATION
receiving equipment. (4) The stationary right panel which switching, and the glove box. (5) The upper left subpanel, located below the left floating panel and above the left subpanel contains autopilot control switching, OMNI indicators, and the flap position indicator. (6) The lower left subpanel contains the heater and air controls for cabin temperature, ignition switch, circuit breaker switches, light controls, flap control, and fuel pump controls. (7) The lower right subpanel contains the landing gear control and indicating lights, and the standard and optional circuit
contains indicators, The instrument
panel general groupings: (1)
on
the
airplane
is divided into seven
A
floating panel, located on the upper left corner of the instrument panel, which contains those instruments necessary to sustain flight. (2) The center stationary panel which contains instruments that indicate the monitoring systems of the engine. (3) The avionics and radio rack, located to the right of the engine instrument panel, which contains various optional avionics and radio various
breakers.
"END"
3400´•00
page t May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
INSTRUMENT AND CONTROL MAINTENANCE PRACTICES
CAUTION
PANELS
if any screws are replaced upon reinstallation of any instrument, be sure they are the same length as the original screws.
WARNING To avoid personal injury, shut off all electrical power,
both
removing components,
battery or
and
before
c.
electrical
d.
external,
installing
any
Connect the post lights as necessary. Connect the plumbing and/or electrical
connections to the a.
Install the
flight instruments. glareshield.
GLARESHIELD REMOVAL a.
Remove the attach screws at each end of the
REMOVAL OF THE ENGINE INSTRUMENT CLUSTER PANEL
glareshield. b.
Lift the
velcro hook and c.
glareshield gently pile which secures
to detach it from the
a.
Remove the
it at its
b.
Disconnect the harness connector
top side,
Disconnect the electrical
quick disconnects glareshield lights,
for
both the compass and the d. Disconnect the defroster heat duct, e.
Remove the
the
glareshield. on
the back of
engine instrument cluster. Remove the
securing the instrument panel. Support the cluster assembly while removing the screws to prevent dropping it. Remove the cluster from the panel. d. c.
screws
cluster to the instrument
glareshield.
GLARESHIELD INSTALLA TION a.
Place the
glareshield
in
position
and connect the
INSTALLATION OF THE ENGINE INSTRUMENT CLUSTER PANEL
defroster heat duct. b.
Connect the electrical
quick
disconnects for both
the compass and the glareshield lights. Install the attach screws at each end c.
a.
proper of the
b.
Place the engine instrument cluster in the instrument panel.
Press downward on the top side of the to secure the velcro hook and pile.
in the
Secure the instrument cluster to the instrument
panel with the
glareshield.
panel
position
screws.
glareshield
d.
CAUTION
REMOVAL OF INSTRUMENTS
ENGINE AND
glareshield. b. Disconnect the plumbing connections from the flight instruments. a.
Disconnect and
d.
Remove
instrument to the
the
remove
mounting
If
replacement of
screws
of the
screws
to
the screws is
same
avoid
length
internal
required,
as
the
damage
use
original to
the
instrument cluster.
Remove the
c.
e.
FLIGHT
and/or
any post screws
electrical
lights. securing
c.
the
d.
panel section.
Connect the engine harness connector to the
back of the instrument cluster.
Install the
glareshield.
Remove the instrument.
REMOVAL OF RADIO/A VIONICS EQUIPMENT
INSTALLATION OF ENGINE AND FLIGHT INSTRUMENTS
a.
Locate the component you wish to
remove
from
the radio/avionics rack. a.
Place the instrument in the proper
position
in the
panel. b.
attaching
Secure the instrument to the screws.
panel
with
the
b.
Loosen the Alien
screw
which
secures
the
piece
of gear in the rack. Slide the required piece of gear from the shelf c. the radio/avionics rack.
on
39-1090
Pagel May 9/80
BEECHCFIAFT BONANZA SERIES MAINTENANCE MANUAL
FLIGHT INSTRUMENT PANEL
ENGINE INSTRUMENT PANEL
RADIO AND AVIONICS RACK
I
RIGHT PANEL AND GLOVEBOX
LEFT UPPER SUBPANEL
RIGHT SUBPANEL
LEFT SUBPANEL
35-392-256
Instrument and Control Panel (except serials E-1946, E-2104, E-2111 and after and EA-320, EA-389 and after)
Figure
INSTALLA TION OF RADIO/A VIONICS EQUIPMENT
1
RIGHT AND LEFT SUBPANEL Access to
a.
install
on
b.
Slide the radio/avionics component you wish to its proper shelf, Make sure the component is seated all the way
back in the shelf to make its electrical connection. c. Tighten the Alien screw which retains the
component in the shelf.
the
individually
mounted
circuit
breakers
is
panel. Before starting any removal or installation procedures, ensure that the battery switch is in the OFF position, the battery is obtained from the underside of the instrument
disconnected, and that the external ground power unit is disconnected. When removing any of the components for maintenance purposes, tag and identify any wires removed to facilitate reinstallation of the components.
39-1 0-00
Page
2
Oct71S3
A6
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
~uHmR
eRspslo
X
eQOO, ~x
larrruar
:O O
~mps
1~31
umR
i;-loo OURR
o
OUTIEI
r~
00
O
0000
00000000000Q0000000 Cm
cm PEDESTPIL
A36-390-22
TYPICIL INSTRUaENT PINEL
Instrument and Control Panel 2111 and after and EA-320, EA-389 and after) Figure 2
(Serlals E-1946, E-2104,
"688"
39-1 090
90993 A6
Oct 7/83
BEECHCRAFT BONA1~IZA SERIES MAINTENANCE MANUAL
ELECTRICAL AND ELECTRONIC EQUIPMENT RACKS MAINTENANCE PRACTICES
diagrams and the accompanying equipment lists Wiring Diagram Manual identify each electrical component with a reference designator. Further, the equipment list identifies the area in which the component is
The circuit in
the
by a zone number. The airplane zoning diagram, repeated in Figure 1, shows the various zones of the airplane. The lists of components, and the illustrations showing their installation on the following pages, identify these components by the reference designator, shown in parenthesis assigned each component in the Wiring Manual, (P/N 35-590102-9). Diagram installed
which is
COMPONENT LOCATION ZONES
Indicates 100
Right
Side
BELOW FLOOR 140
Firewall to Main
150
Main
160
Aft of Rear
Spar
Spar Spar
300
340
Rudder
351
Conventional Tail) Horizontal Stabilizer
(352)
with
AFT FUSELAGE AND EMPENNAGE
(Cont’d)
to Rear
Spar
361
(362)
370 200
(Aircraft
Elevator Tail Cone
FORWARD FUSELAGE 221
(222)
231
(232)
Firewall
(Attached
Accessible from fon~vard
240
251
(252)
410
ENGINE COMPARTMENT
500
(600) WING AND CONTROL SURFACES
to or
Side)
Firewall to Instrument Panel
531
Instrument Panel and
532
Subpanel Cabin (Floor Headliner)
Line to
253
Cabin Headliner Area
270
Main
533(633) 541 (641) 542 (642)
Spar Carry-Through
StruCture 280
Rear
(631) (632)
Wing, Inboard Leading Edge Wing, Inboard-Aft of Main Spar Flap Wing, Outboard-Leading Edge
Wing, Outboard-Aft Spar
of Main
543(643) Aileron 550 (650) Wing Tip
Spar Carry-Through
Structure 700
300
AFT FUSELAGE AND EMPENNAGE
GEAR DOORS AND WHEEL WELLS 710
730 310
Aft
320
Dorsal Fin
330
Fuselage (Aircraft with Conventional Tail) Vertical Stabilizer (Air-
800
craft with Conventional Tail)
Nose
(740)
Main
Landing Landing
Gear Gear
DOORS 820
Cabin
830
Baggage
Entry Door or
Cargo
Door
Airplane Zoning Diagram Figure 1 (Sheet 1 of 2)
3420-00
Pager May 0/60
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
710
531
532
631
541
632 641
550
650
542
543
642
643 533
730
740
351
240
361
362
253
820
633
352
330
251 830
(252)
310
320
340
221 410
(222)
(232) 370 I-
-I
()lndicates Right
Side
140
270
150
280
160
35-607-22
Airplane Zoning Dlegrem Figure 1 (Sheet 2 of 2)
342MW)
PaeaS May 9/80
BEECHCRAFT BONAEUA SERIES MAINTENANCE MANUAL
AREA BETWEEN INSTRUMENT PANEL AND 232
FIREWALL AND AIRPLANE ZONES 231
THE
For maintenance coverage of the voltage regulator, refer to Chapter 24 of the Maintenance Manual. The electrical
equipment junction
(Figure 2) components located between the firewall and instrument panel (zones 231 and 232) are individually
The electrical
contains the
flap position PC
and an externally mounted flasher. The following components are located in airplane zones 231 and 232:
Equipment Junction Box (231) (A19) Landing Gear Warning Horn (231) (LS11) Stall Warning Horn (231) (LS12) Voltage Regulator (232) (VR11) Manifold Pressure Switch (231) (S54) LH Fuel Quantity PCB (231) (A13) RH Fuel Quantity PCB (231) (A14) Electrical
or bolts. Prior to performing any these components, ensure that the battery switch is OFF, the battery is disconnected, and that the external power source (if installed) is disconnected. When removing these components for maintenance purposes, tag and identify any wires removed to facilitate the
mounted with maintenance
box
board, the annunciator dimming PC board, relays, diodes,
screws
on
reinstallation of the components.
r-’l
’I
o
o
II
1\
~--VOLTAGE R"ULATOR
CONNECTOR
O
DETAIL
Right
A
Area Between Firewall and Instrument Panel figure 2 (Sheet 1 ot 3)
35-351-6
Zone 232
39-20-00
Paged May 9/80
BEECHCRAFT BONANZA SERIES YAIWTENANCE MANUAL
CONNECTORS AND SOCKETS
STALL WARNING HORN WIRE
HOUSING
ELECTRICAL EQUIPMENT JUNCTION BOX
LANDING GEAR WARNING HORN
35-3513
DETAIL A
Left Area f~etween Firewall and Instrument Panel Figure 2 (Sheet 2 of 3)
392090
Page4 May 990
Zone 231
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
FUEL QUANTITY PCB’S MANIFOLD PRESSURE SWITCH (EA-1 THRU EA-272
excepi EA-242)
i/
MANIFOLD PRESSURE
I/
i//
I
(INSTRUMENT)
DETAIL B
35´•351 -j
Left Center Area Between Firewall and Instrument Panel Figure 2 (Shset 3 of 3)
Zone 231
39-20´•00
Page S A4
Jan 20182
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
AREA WHICH INCLUDES THE FORWARD, RIGHT SIDE OF THE FIREWALL, THE ENGINE
these switches is found in
OOMPARTMENT, AND THE NOSE LANDING GEAR
Manual. Al
WELL
alternator, starter, etc., will be shown in the 10-520 or TSIO-520 Series Aircraft Engines Overhaul Manual, FORM
AIRFLANE ZONES 222/410/710
(Figure 3)
located in
X-30039A The electrical components located in the above areas and zones are mounted with nuts, bolts, screws, or clamps. Prior to performing any maintenance on these components, that
ensure
the
battery
switch is OFF, the
battery
is
disconnected, and that the external power source (if installed) is disconnected. When removing these components for maintenance purposes, tag and identify any wires removed to facilitate the reinstallation of the
components. The
landing gear uplock and downlock switches
nose
located in the
are
wheel well, and are mounted on the right, outboard side of the wheel well keel. These switches work in conjunction with the indicator lights on the right
subpanel
nose
to indicate
nose
landing
gear
position.
For maintenance coverage of the battery, refer to Chapter 12 of the Maintenance Manual. The throttle warning horn switch
(S34)
(S41) and are
38-20-00
Pagee May 9/80
located
the on
optional landing gear safety switch the throttle control shaft and
are
located in
Adjustment and pictorial coverage of Chapter 32 of the Maintenance maior engine electrical components i.e.,
zone
or
410.
X-30042.
airplane
tones
The
following components
222 and 410:
Fuse blocks, both Standard and
optional (222) (F15, F16, XF15) Battery (222) (BT10) Shunt (222 (R34) Current Limiters (222) (Ft, F2, XF1, XF2) Capacitor Filter (222) (C11) Optional External Power Relay (222) (K12) Optional External Power Receptacle (410) (J32) Starter Relay (222) (K14) Battery Master Relay (222) (K15) Alternator Out Sensor (222) (A16) Throttle Warning Horn Switch (410) (S41) Chapter 32 Optional Landing Gear Safety Switch (410) (S34) Chapter 32 Avionics Master Relay (222) Switch, Nose Landing Gear Uplock (710) (S82) Switch, Nose Landing Gear Downlock (710) (S63)
are
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
FUSE BLOCK
SPARE FUSE BLOCK
STANDARD FUSE BLOCK
STACKED CURRENT LIMITERS STARTER RELAY
SMUNT
EXTERNAL POWER RELAY
BATTERY~
/-BATTERY
MASTER RELAY
~ALTERNATOR OUT SENSOR
AVIONICS MASTER RELAY
CAPACITOR CURRENT
LIMITERS
DETAIL
A
EXTERNAL POWER RECEPTACLE 35-351-2
Fomard, Right Side of Rrewall and Engine Compettment Figure 3 (Sheet 1 of 2)
Zones 222/410
3929´•00
Pege7 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
MAGNETOS
1 LANDING LIGHT
THROTTLE WARNING HORN SWITCH
I
i
EXTERNAL POWER
RECEPTACLE TO CYLINDER HEAD TEMP BULB TO TAXI LIGHT
__
I
LANDING GEAR DOWNLOCK SWITCH LANDING GEAR UPLOCK SWITCH 35-351-5
Engine Compartment
3920-00
PagaB May 9180
and Nose Landing Osar Well Figure 3 (Sheet 2 ot 2)
Zones 410/710
BEECHCRAFT BONANZA SERIES UAINTENANCE MANUAL
AREA BENEATH THE FLOOR FROM THE FIREWALL TO THE MAIN SPAR AND FROM THE MAIN SPAR TO THE REAR SPAR AIRPLANE ZONES 140 AND 150
(Figure 4) The electrical components located from the firewall to the main spar, and from the main spar to the rear spar are mounted with nuts, bolts, screws, and clamps. Prior to
performing any that the battery and
that the
maintenance on these components, ensure switch is Off, the battery is disconnected, external
disconnected. When
power
removing
maintenance purposes, tag and
source
(if installed)
is
these
components for
identify
any wires removed
to facilitate the reinstallation of the
components.
CAUTION Make
sure
the grommets are installed in the
of the main spar through which the wire harness passes, so chafing of the harness will
area
not occur.
The
auxiliary fuel pumps are located forward of the main spar; all other components in this figure are located aft of the main spar. There are three different auxiliary fuel pumps used in the Bonanza Series airplanes: On serials CE-743, CE-n2 and after; D-10097, D-10120 and after; E1111, E-1241 and after, a reference designator (811) is
used for
high boost pump. On serials 01-149 and after, auxiliary boost pumps are used: Reference designator (B11) for high boost and reference designator (812) for low boost. On serials EA-1 and after, a single pump with both high and low speeds is used. The pump used on EA-1 and after is reference designator (813). two
The
four
flight dimming transistor dimming transistors and
side). For adjustment of
bracket
the
landing Chapter 32
downlimit switches, refer to Manual. The following components zones
assembly
is located in
are
zone
contains 150
(left
gear uplimit and of the Maintenance located in
airplane
140 and 150:
Auxiliary Fuel Boost Pump (140) (811, 812, or 813) See above. Light Dimming Transistor Bracket Assembly (150) (A21) Glareshield Light Dimming Transistor (150) (Q1) Subpanel Light Dimming Transistor (150) (02) Eng Inst and Avionics Console Light Dimming Transistor (150) (03) Flight Instrument Light Dimming Transistor (150) (04) Inverter (150) (MG1) Flap Motor (150) (822) Landing Gear Motor (150) (821) Dynamic Brake Landing Gear Relay (150) (K17) Landing Gear Uplimit Switch (150) (839) Landing Gear Downlimit Switch (150) (840)
3420-00
PageS May 8/80
BEECHCRAFT BONANZA SERIES FAAINTENANCE MANUAL
AUXILIARY FUEL BOOST PUMP [B1~ OR 813)
LANDING GEAR UPLIMIT AND DOWNLIMIT SWITCHES
LANDING GEAR MOTOR AUXILIARY FUEL BOOST PUMP (812)
I
FLAP MOTOR
rFRONT
y
INVERTER
SPAR
i
j
jY
-t -r~
rt
I
’I
II
I
II
------I\
~"*I
LIGHT DIMMING TRANSISTOR BRACKET ASSEMBLY
II
L-
DYNAMIC BRAKE LANDING GEAR RELAY
35--352--~
Area Bencbath the Floor From the Arewall to the Rear Figure 4
3920´•00
PagelO Mey 9/80
Soar
Zones 140/150
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
AREA WHICH INCLUDES THE WINGS AND MAIN AIRPLANE ZONES 531 THRU LANDING GEARS 650, AND ZONES 730 AND 740
(Figure 5) components located within the~wings and landing gear wheel wells are mounted with nuts, bolts, screws, clamps, and rivets. Prior to performing any maintenance on the components, ensure that the battery switch is OFF, the battery is disconnected, and that the external power source (if installed) is disconnected. When removing the components for maintenance purposes, tag and identify any wires removed to facilitate the reinstallation of the components.
approximately WS landing gear wheel flap limit switches
40.00.
It is
accessible
through
the
spar. The are accessible forward of the left flap and may be serviced with the flaps lowered. The flap switches are located at approximately WS 33.00. For flap switch
The electrical
limit
main
Maintenance
well forward of the
wing
rear
adjustment refer to Chapter 27 of the At airplane serials D-10179 and
Manual.
after, CJ-I50 and after, CE-816 and after, E-1371 and after, and EA-1 and after the airplanes are equipped with 14
degree and
addition to the
degree approach flap uplimit and downlimit flap 16
limit switches in
switches of
prior
airplane serials. (squat switch) is located on landing gear. The safety switches are provided to prevent inadvertent retraction of the landing gear on the ground. The switches open the control circuit when the struts are compressed. The landing gear safety switches also serve to control the position of the A
landing gear safety
switch
the strut of each main
Each wing contains two fuel level transmitters which provide fuel quantity information to their respective fuel quantity indicator on the engine instrument panel. The inboard fuel quantity transmitter for each wing is located at approximately WS 43.00, and the outboard transmitter is located at approximately WS 97.00.
retractable air conditioner condenser. When the airplane is the ground and the air conditioner is turned on, the
on
condenser extends to the
pitot tube is mounted on approximately WS 125.00.
The heated rib
at
the left outboard
wing
tube
heat
The
pitot
element wires are routed with the tube air line. When the pitot tube is removed for maintenance purposes, be sure to cap the end of the air line to prevent entry of foreign material. Remove the cap upon reinstallation of the tube.
warning switch is located on the left outboard wing leading edge at approximately WS 140.00. Adjustment coverage of the stall warning system is located in Chapter 27 of the Maintenance Manual. The stall warning switch is removable by screws located around the perimeter of the mounting bracket. The stall
The
landing gear uplock and downlock switches, a pair for landing gear, are located in the wheel well on aft side of the front wing spat at WS 45.00 for the gear
each main the
up switch, and at WS 52.00 for the gear down switch. These switches work in conjunction with the indicator lights on the right subpanel to indicate landing gear position. The electrical
switches
indicator
flap position
transmitter and the
flap
limit
located within the left wing. The flap position is mounted at the left flap actuator at
are
ground
extension
position.
The following electrical components are located in the area which includes the wings and main landing gear. This area includes airplane zones 531 thru 650, and zones 730 and 740:
Warning Switch (531) (543) (531) (HR23) Transmitter, LH Inboard Fuel (531) (R20) Transmitter, LH OutboardFuel (531) (R21) Transmitter, RH Inboard Fuel (631) (R22) Transmitter, RH Outboard Fuel (631) (R23) Switch, LH Landing Gear Uplock (730) (560) Switch, LH Landing Gear Downlock (730) (S61) Switch, RH Landing Gear Uplock (740) (564) Switch, RH Landing Gear Downlock (740) (S65) Flap Position Transmitter (730) (MT2) Switch, Flap Uplimit (533) (S50) Switch, Flap Downlimit (533) (551) Switch, 14 Degree Flap Limit (533) (S76) Switch, 16 Degree Flap Limit (533) (S47) Switch, RH Landing Gear Safety (740) (S36) Switch, LH Landing Gear Safety (730) (S37) Stall
Heated Pitot Tube
342090
Pagelf May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
UPLIMIT FLAP SWITCH LH ONLY
STALL
WARNING SWITCH LH ONLY
HEATED PITOT TUBE LH ONLY
APPROACH FLAP SWITCHES CHONLY
FUEL TRANSMITTERS
FUEL TRANSMITTER EA-242. EA-273 AND´• AFTER
i
LANDING GEAR DOWNLOCK SWITCH NOTE
LANDING GEAR UPLOCK SWITCH
DOTTED LINES INDICATE EA-242, EA-273 AND AFTER. AT THE SAME EFFECTIVITY THE PITOT MAST IS MOVED TO THE WING TIP.
FLAP POSITION TRANSMITTER LH ONLY
LDOWNL1MIT FLAP
SWITCH LH ONLY
35-355´•11
Area Which Includes the Wings and Main Landing Gear (Lett Shown) Zones 531 thru 650 and Zones 730 and 740 Figure 5
Wing
"END"
392090
Page 1Z Jin 3900
A4
CHAPTER
STANDARD PRACTICESSTRU C~U RES
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 51
STRUCTURES
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
GENERAL
SUBJECT
........._,,,
PAGE
.........,.,._51 -00-00
Description and Operation Primary Structural Components
..................1 ...........1
Secondary Structural Components
........1
Maintenance Practices
........1
Structural Repair Repair of Fiberglass Components
........1 ........2
IEND"
51-CONTENTS A12
Page 1 Aug 28/87
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 51 LIS T OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT
PAGE
DATE
51-EFFECTIVITY
1
Oct 16/92
51-CONTENTS
1
Aug 28/87
1
Oct 16/92
2
Oct 16/92
51-00-00
"END"
51-EFFECTIVITY
Page A16
1
Oct16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
DESCRIPTION AND OPERATION
GENERAL
airplane is all metal with a semimonocoque type construction. Stresses are carried by both the skin and stiffener members of the fuselage, wings, and empennage. The airplane has primarily a riveted
The
structure. Field
repairs
to skins and stiffener mem-
bers may be accomplished with standard materials and hand tools. The basic structure of the airplane is
fuselage, which is constructed of bulkheads strengthened with longerons, stringers, and skin panels,
Seats and seat structure.
h.
Integrity of V35B and V35B-TC airplanes is improved by installation of Kit No. 35-4016-7 S. The kit will provide additional support to the leading edge
Structural
of
the
and
stabilizers,
be
can
installed
without
removal of the stabilizer.
SECONDARY STRUCTURAL COMPONENTS
the
In
the
event
structural
of
damage,
attention, but would
wing sections are attached to the fuselage carry-through structure by front main and rear spars. The leading edge and rear panel (box section) of each wing are attached to the -main spar by continThe
safety
piano-type hinges. The wing tip is attached to wing rib. The horizontal and vertical
uous
the
following secondary require immediate necessarily endanger the
would
components not
airplane and/or
of the
the passengers.
a.
Wing tips
b.
Fairings
c.
Nonstructural doors and
d.
Furnishings
the last outboard stabilizers
con stru cted
each
are
around
two
channel-section spars and are covered with a skin stiffened by internal beads. Each is attached to the
fuselage
at the front and rear spars. The elevators
and rudder both have
a
main spar and ribs.
The
following
structural
primary
components
of the
airplane and/or
Control systems
b.
Engine
c.
Fittings
the
general, structural repair methods airplane may be in accordance with In
thinner th~n the the
next
ations
thicker
Wing,
tail
surface,
and
tail surfaces
control
the
recommended in addition to AC 43.13-1
are
a.
and control surfaces
e.
on
43.13-1A
original skin. Patches should be of material. The following consider-
and AC 43.13-2 for
fuselage, wings,
AC
AC 43.13-2 AIRCRAFT ALTERATIONS MAN UAL. Never make a skin replacement or patch from a material
mounts
Skins of the
used
AIRCRAFT INSPECTION AND REPAIR MANUAL and
surface
of the
airplane.
joints, including patches, staggered rows of rivets.
b.
All
defects
such
cause
repair
All lap
at least two d.
MAINTENANCE PRACTICES
are
passengers. a.
(excluding
STRUCTURAL REPAIR
essential to the proper function of the airplane. Damage, occurring to any of the components, would seri-
ously endanger the safety
upholstery
seating) STRUCTURES
PRIMARY STRUCTURAL COMPONENTS
and
covers
repair as
material
must
be
must have
free
of any
nicks, scratches, etc., which
can
stress rises.
spars
f.
g.
support
Landing Auxiliary
gears and
support
members used to
other members
carrying
Never dimple a structural member by c. ing the rivet head into the part.
structure
strengthen
direct loads
or
d.
Do not countersink
deeper
driv-
than 75% of the
material thickness.
51-00-00
Page A16
1
Oct 16/92
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
REPAIR OF FIBERGLASS COMPONENTS
Apply an even coat of resin to the sanded Impregnate all three laminated glass cloth patches by laying the patches on clean waxed paper and working the resin through the fabric with a 2-inch d.
area.
Large holes and cracks require that the be cut out and trimmed just beyond the area of damage. If the parts are painted, remove the paint and sand that portion of the part extending at least 2 inches beyond the cutout, a.
damaged
b. such
as
area
Prepare 3 patches of laminated glass cloth, Trevano, Uniglas, or their equivalent. Cut the
patch to the dimensions of the sanded area, the patch 1/2-inch smaller than the first, and the third patch 1/2-inch smaller than the second, first
second
brush.
Place the large patch over the cutout area, bubbles and wrinkles. If the patch starts to sag, place a support behind the repair area. Coat the support with automobile wax or waxed paper to prevent the resin from adhering to the support. Work out all air bubbles and wrinkles while installing the second patch over the first. Install the third patch over the second in the same manner. e.
working
f.
Prepare the MIL-R-7575 resin (24, Chart 1, 91-00-00) for the patch in accordance with the manc.
ufacturer’s instructions.
Make
sure
that your hands handling the
free of oil, grease, and dirt when resin.
are
out all
repaired area with an even coat patches have cured for 24 hours at temperatures between 230C (750F) and 660C (1500F), blend the patch into the contour of the part with fine sandpaper. Paint the repair to match the rest of the Brush the
of resin. After the
part. "END"
51-00-00
Page
2
Oct 16/92
A16
C H A PT E R
DOORS
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 52
DOORS
TABLE OF CONTENTS
SUBJECT
PAGE
52-00-00
General
Description
and
Operation
1
Cabin Door
1
Cabin Door Quick Release Mechanism
Utility
Doors
Baggage
(E-llll,
Doors
(CJ-149
and After
E-1241 and After; EA-1 and
(CE-748,
Only)
1
After)
1
CE-772 and After; CJ-149 and After; D-10097, D-10120 and
After)
1
52-10-00
Cabin
Passenger/Crew
Cabin Door Removal
Door
Maintenance Practices..........
1
E-1241 and After; EA-1 and After; CE-748, CE-772 and After;
(E-llll,
D-10097, D-10120 and After) Cabin Door Installation
1
(E-llll,
E-1241 and
After; EA-1 and After; CE-748, CE-772 and After;
D-10097, D-10120 and After) Cabin Door Removal
(CJ-149
Cabin Door Installation Cabin Door
Installing
2
and
(CJ-149
3
After)
3 3
Adjustment
Cabin Door Lock and
Removing
After)
and
and
Installing
Fitting
Tumbler to
8
Key
the Cabin Door Teleflex Cable
9
10
Interior Cabin Door Handle
Interior Cabin Door Handle Removal and Installation
10
52-30-00
Cargo
Doors
Maintenance Practices.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Utility
Door Removal
Utility
Door Installation
Utility
Door
A21
(E-llll,
After)
E-1241 and After; EA-I and
of the Aft Half of the
Adjustment of
1
After)
1 1
Utility
Utility
the Fomard Half of the
Door Latch Pin
Interior
E-1241 and After; EA-1 and
Adjustment
Adjustment
Utility
(E-llll,
1
Door
Utility
1 1
Door
Adjustment
1
Door Handle Removal and Installation
2
52-CONTENTS
Dec
23/99Pagel
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 52 TABLE OF
000RS
CONTENTS(CONTINUED)
SUBIECT
PAGE
(CE-748,
Large Baggage After)
Door Removal
Large Baggage After)
Door installation
Small
Door Removal
CE-772 and After; CJ-149 and After; D-10097, D-l 0120 and 2
(CE-748, CE-772 and After; CJ-149
and After; D-)0097, D-10120
and
Baggage
2
(CE-748,
CE-772 and After; CJ-149 and After; D-) 0097, D-)0120 and
After)
2
Small and
Baggage After)
Baggage Aner)
Page
ce23199 D2
Door
Door Installation
(CE-748,
Adjustment (CE-748,
CE-772 and After; CJ-149 and After; D-10097, D-10120 2
CE-772 and After; CJ-149 and After; D-10097, D-10120 and 2
52-CONTENTS
A21
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 52
DOORS
LIST OF PAGE EFFECTIVln/
CHAPTER-SECTION-SUBJECT
52-Effectivity SP-Contents
52-00-00
52-10-00
52-30-00
A21
PAGE
1
DATE
Dec 23/99
1
Dec 23/99
2
Dec 23/99
1
May
9/80
1
Dec 23/99
2
Dec 23/99
3
Dec 23/99
4
Dec 23/99
5
Dec 23/99
6
Dec 23/99
7
Dec 23/99
8
Dec 23/99
9
Dec 23/99
10
Dec 23/99
11
Dec 23/99
1
Dec 23/99
2
Dec 23/99
3
Dec 23/99
52-EFFECTIVITY
Dec
23/99Page
1
BEECHCRAFI BONANZA SERIES MAINTENANCE MANUAL
DESCRIPTION AND OPERATION
GENERAL
on
the
right
The doors
located
access to
the cabin
area.
side of the
fuselage
between FS 124.55 and FS
which furnish
are
utility door contains a window, with the forward being hinged on the forward side and the aft door being hinged on the aft side. Each utility door has a folding door stop located at the bottom edge of each door.
CABIN DOOR
170.00. Each
door
The
airplane
is
provided with
a
cabin door which furnishes
flight compartment. The door is located on the right side of the fuselage between FS 58.00 and FS 100.00 on the Model A36 series airplanes, and between FS 68.00
The forward
utility
and FS 104.90
handle with
lock and tumbler
access to
the
Each door is
points, and
on
the Model 33 and 35 series
hinged
a
on
airplanes,
the forward side of the door at two
door stop is located
on
the bottom
a
door contains
an
outside
assembly
and
inside latch
handle. The forward door contains three latches: two
edge of
latch
D-ring
an
pin-type
latches, one on the top and one on the bottom edges of the door, and a bayonet latch which makes contact with the
each door.
striker
plate
on
the sit door. The movement of the three
by a bell crank assembly. The ah utility type handle on the front edge, inside of
latches is controlled
The cabin door is provided with an aft outside and forward inside door handle. The outside handle contains the cabin
door contains
door lock and tumbler assembly. The door contains three latches: a hook latch on the upper edge of the door, a sliding
the door. The door contains two hook type latches which each engage a striker plate lip at the top and bottom of the
bolt latch
door sill. The movement of the two latches is controlled
the lower
the aft side of the door, and a pin type latch on edge of the door. A cable assembly connects the
on
bell crank
a
lever
by
a
assembly.
movement of the upper latch, and a bell crank assembly controls the movement of both the aft and lower pin latches.
An
optional courtesy light is installed in the door above the wiring for the courtesy light exits the door above the upper door hinge.
BAGGAGE DOORS (CE-748, CE-772 and aHer; CJ-149 and after; D-
window. The
19997 0-10120 and after) CABIN DOOR QUICK RELEASE MECHANISM (CJ-149 and after onlyl
airplanes other than the A36 series are provided optional (small or large) baggage door for cargo storage. The doors ate located on the right side of the fuselage. The small door is located between FS 131.00 and FS 151.00, and the large door is located between FS Bonanza
with
The cabin door
can
be
instantaneously jettisoned by
a
quick
release mechanism in the event Of an emergency. The quick release mechanism actuates the door latches through a lever and
cam
131.00 and FS 170.00. tither door is
arrangement. To prevent accidental activation of
the mechanism the red handle that actuates the release is
secured to the escutcheon and
on
the door
by an
side. The small
baggage
single strand of safety wire. The wire breaks and the straightens out to release the handle when latter is pulled. The cam on the lever to which the handle
door has
a
a
door sill to
door has
a
hinged stop rod
on
the forward
on
the forward
hinge, and the large scissors type door stop connecting the top of the the top of the baggage door.
inboard side of the door
aluminum catch
aluminum catch the
an
near
the door
is attached then rotates to actuate the link that unlatches the upper and lower door latches. Simultaneously, an actuator each end of the quick release lever rotates and, through
The small
baggage
door contains
on
lock mechanism located
interconnecting links, withdraws the retainers that lock the upper and lower hinges in place around the hinge pins. This completely releases the door from the fuselage,
only latching device
makes contact with
baggage
a
on
striker on
door contains
plate
the small an
a
combination latch and
the aft side of the door. The latch on
the door sill. This is the
baggage
door. The
large
D-ring
latch
outside and inside
handle. A lock assembly is provided and is located beside the
UTILIjY DOORS
(E-llll,
handle. The
E-1241 and after; EA-I and
affer)
large baggage door contains three pin type on the aft edge and the top and bottom edges
latches located
of the door. The movement of the three latches is controlled
The A36 series airplanes
are
provided
with two
utility
doors
by
a
bell crank
assembly.
"END"
52-00-00
Pagel May 9180
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CABIN PASSENGEWCREW DOOR CABIN DOOR REMOVAL
(E- 1111,
E- 1241 AND
AND AFTER; D- 10097, D- 10120 AND a.
Remove the inboard door handle.
b.
Removethewindow
c.
Remove the armrest,
d.
If the
MAINTENANCE PRACTICES
AFTER; EA-I AND AFTER; CE-748, CE-772
AFTER)
uppermoldingtrim. upholstery panel
optional courtesy light panel.
and the ash tray.
is installed, disconnect the wire
splice
which is located behind the
right
side of the
instrument e.
With the door open, insert
door while
applying
a
f.
Remove the two
g.
Remove the
a
screwdriver between the door stop and the bottom of the door. Slowly close the on the door stop until the stop is released from the door.
downward pressure
phillips
remaining
screws
screws
from each
which
hinge
secure
cover.
the door frame to the
hinges.
NOTE At the upper hinge, four screws are aft of the hinge cover. h.
Carefully
remove
the door
are
by pulling
located aft of the
the door
directly
hinge
cover;
away from the
on
the lower
hinge,
three
screws
hinges.
NOTE Shims have been installed between the
be retained and the
same
hinges and the door to obtain a proper fit. The shims should number of shims installed, where removed, under each hinge when the
door is reinstalled.
nnl
52-10-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
i
a
55-101-9
Cabin Door
Figure CABIN DOOR INSTALLA TION
CE-772 AND AFTER;
n
Stop
1
(E- 1 I I I,
E- 124 1 AND AFTER; EA- 1 AND AFTER; CE-748, D- 10007 D- 10120 AND AFTER)
If the door is new, place the door in position and mark the door hinge tab and perimeter of the door frame where any excess material needs to be removed. Remove the excess material to obtain the best fit prior to installing the seal a.
b.
On
to
a new
c.
a new
door, install
Place the door in
door flush to the d.
door seals around the inside
Check the old door for reference
phillips
on
sure the upper and lower door hinge shims are in place. The same number installation of the door as when the door was removed. The shims serve to keep the
fuselage.
Attach the four
phillips
screws
screws
aft of the upper door
aft of the lower door
f.
Install the door stop in the channel located
cover
52-10-00
secure
plates; each is attached with
Attach the upper and lower
hinge
hinge which
the door frame to the
hinge.
e.
Dec
edge of the door frame.
position, making
of shims should be used
three
new
door seal location.
on
the bottom
edge of
two
phillips
the door.
screws.
hinge.
Attach the
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE The upper door hook latch bracket, located in the door sill above the door, should be preset flush with the door sill. If the door contains the optional courtesy light installation, feed the wire from the courtesy light to the location g. behind the right side of the instrument panel by routing the wire above the door hinge to behind the panel. Splice the courtesy
light
wire to its
connecting wire.
upholstery panel, ashtray,
h.
Install the
i.
Install the window upper
j.
Install the inboard door handle.
k.
If
molding
CABIN DOOR REMOVAL To
remove
trim.
to the installed door
adjustments
the door, cut
and armrest.
are
required,
refer to CABIN DOOR ADJUSTMENT in this
chapter.
(CJ- 149 AND AFTER ONL Y)
safety wire securing the quick release handle (red) in place and straighten out the disengages the hinge pin retainers and remove the door.
aluminum
catch. Pull the handle that
CAUTION Icnvnoirl
Support the door carefully to avoid damaging CABIN DOOR INSTALLA TION To install the door,
position
the door
the
wing when
(CJ- 149 AND AFTER
so
that the
hinge pins
the
quick release frees
the door.
ONL Y)
slide into the
hinge slots,
then
push
in the
quick
release
handle (red) until the retainers engage the holes in the hinge to lock the hinges in place around the hinge pins. Bend the aluminum catch back in place over the handle and secure the handle to the catch with one wrap of 0.020 inch diameter copper wire per QQ-W-343
Type
S.
CABIN DOOR ADJUSTMENT If any of the
following
conditions exist, check and
adjust the cabin
door
latching
mechanism:
The door is difficult to close. There is excessive wind noise around the door. The door is not The door is
opening
The door has a.
airtight in
recently
or
watertight.
flight. been removed
or
repaired.
Ensure that the door’s internal latch mechanism is not
With the door in the open position, operate the mechanism is operating smoothly and properly. 1.
2.
binding
and/or
preventing
latching mechanism
proper door
several times to
closing
ensure
as
follows:
that the internal
position, rotate the inside door handle counterclockwise as far as possible. plate at the edge of the blade protruding from the inner forward end of the handle.
With the door still in the open
Mark the inside handle escutcheon
1\21Page
3
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 3. to the
Place the latch in the open position and then close and latch the door. Check to see that the handle rotates that was marked in the previous step. If the handle does not line up with the mark, open the door and the door upholstery. Inspect the latching mechanism to determine the reason for the interference and make
position
remove
the necessary
adjustments. NOTE
The
areas
of
possible interference
are
where the lower
pin,
the upper latch hook, and the aft latch
bolt engage in the door frame. b.
The latches may 1.
require adjustment
UPPER LATCH
There
are
to ensure
three
points
positive door locking
that should be
as
inspected
follows: and/or
adjusted
on
the upper latch.
Referring to Figure 2 (Sheet 1 of 3), checkto ensure that the upper latch mechanism is over center when can be accomplished by using a small inspection mirror to see that the upper operating link is against the adjustment screw and the forward edge of the upper operating link is forward of the forward edge of the lower operating link. If the latch mechanism is not over center when the door is latched, adjust the over center a)
the door is latched. This
stop
screw.
b)
Referring
to
Figure
2
1 of
(Sheet
3),
check to
ensure
that the upper latch hook
it is almost touching the aft the
pin,
move
the
pin
portion of the hook without riding on the hook. If the upper hook does pin forward or aft tit has four positions) to obtain proper adjustment.
is
positioned so that properly engage
not
Check for proper adjustment of the door upper latch bracket in the door sill above the door. If the door properly in the frame (inboard/outboard) when closed and latched, leaving a noticeable gap between the door and the frame, the upper latch bracket needs to be adjusted "in" to create more tension on the door. This can be accomplished by adjusting the forward tension screw. Refer to Figure 2 (Sheet 1 of 3).
c)
does not fit
2.
LOWER LATCH
The lower aft latch
pin should
be adjusted in the latched (closed) position so that the through both the striker plate and the door opening frame to a minimum of 0.05 inch below the lower surface of the door opening frame, as shown in Figure 2 (Sheet 2 of 3). Adjust the pin as follows, so that it just clears the striker plate when the latch is in the unlatched (open) position, and does not interfere with door opening.
shoulder
(straight sided) portion
of the
pin
has extended
NOTE The amount of the
pin protruding
from the door with the latch open will
the bottom of the door and the door frame in the
a)
Remove the
safety wire
b)
Turn the barrel to extend
depend
on
the gap between
fuselage.
in the turnbuckle. or
retract the
pin
as
necessary.
NOTE It may be necessary to shorten the pin guide by grinding a maximum of 0.2 inch off the top of the as shown in Figure 2 (Sheet 2 of 3), in order to obtain enough travel to make this adjust-
pin guide ment.
c)
Page
Safety
the turnbuckle.
52-10-00
nzl
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL 3. et
on
AFT LATCH
BOLi Check to ensure that the aft latch bolt provides a pre-catch and protrudes into the sockas far as possible without bottoming out. If adjustment is required, proceed as follows, re-
the aft door frame
ferring
to
Figure
a)
2
3 of
(Sheet
Disconnect the
3).
operating tube
at the inside door handle.
mechanism from the
b)
Disconnect the lower aft latch
c)
Rotate the tube to allow the bolt to
pin
protrude the
operating
tube.
proper distance.
NOTE When this is done the outside handle may
protrude
up to 0.25 inch into the air stream, which is
ac-
ceptable. d)
Connect the lower aft latch
pin
mechanism to the
operating
tube. Connect the
operating
tube to the in-
side door handle.
NOTE The aft latch bolt
can
be
aft side of the door and four c.
moving
inboard
or
outboard
the bolt inboard
or
by loosening the four retaining screws on the as necessary, and then tightening the
outboard
screws.
Install any
A21
adjusted
upholstery
and/or
equipment
that
was
removed.
52-10-00
5
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
A
A
WARNING VERIFY DOOR IS PROPERLY LATCHED BEFORE TAKEOFF
VIEW LOOKING OUT AT RH SIDE OF CAB
C R--,
DOOR
UPPER
HOOK
LATCH
_1,
FORWARD
r/
I
DOOR UPPER LATCH BRACKET
TENSION SCREW
UPPER LATCH HOOK PIN SHOULD TOUCHING THE AFT PORTION OF WITHOUT RIDING ON IT.
BE ALMOST THE HOOK
FWD c~
OVERCENTER UPPER
OPERATING
O LOWER
OPERATING
ADJUSTABLE
STOP
SCREW
LINK
WHEN DOOR IS LATCHED. THE FORWARD EDGE OF THE UPPER OPERATING LINK SHOULD BE AGAINST THE OVERCENTER ADJUSTABLE STOP SCREW AND FORWARD OF THE FORWARD EDGE OF THE LOWER OPERATING LINK.
LINK
VIEW LOOKING VIEW
A-A FROM
ROTATED
C9101555
ABOVE 180"
Cabin Door Latch Points
Figure 2 (Sheet
Dec
52-10-00
1 of
3)
A21
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
O
o
TURNBUCKLE
SAFETY
WIRE
CUTOUT
IN DOOR
PIN
D
STRIKER
LOWER
AFT
PAN
GUIDE
PLATE
LATCH
PIN
AFT
VIEW CLEVIS
LOOKING
GRIND OFF TOP REOUIRED TO A
\I
~CUTOUT
TRIKER
B
PIN
PLATE
IN
OUTBOARD
OF PIN GUIDE, IF MAXIMUM OF 0.2 INCH DOOR
PAN
DOOR OPENING FRAME
PIN/ GUIDE
.05 INCH MINIMUM ENGAGEMENT ABOVE TAPERED AREA OF THE PIN IS RECJUIRED
VIEW
D
csioais56
Cabin Door Latch Points
Figure
A21
2
(Sheet
2 of
3)
52-1 0-00
Dec
23/9 Page
7
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
ADJUST LATCH BOLi BY LOOSENING THESE SCREWS (d)
ROTATE THE OPERATING TUBE TO ADJUST BOLT PROTRUSION
BOLT
I
I
I
I
-I
r7
I
I
I
I
I
I
OPERATING TUBE
VIEW INSIDE
DOOR
C
LOOKING
C9101557
OUTBOARD
C
Cabin Door Latch Points
Figure 2 (Sheet 3
of
3)
INSTALLING CABIN DOOR LOCKAND FITTING TUMBLER TO KEY When a
a
lock
full set of To fit
key.
baggage compartment door, cabin door or ignition is broken or worn, it is not necessary to install locks with a new key. A new tumbler can be readily converted tone time), for use with a old new tumbler to a key proceed as follows: on
a
a.
Insert the
b.
With
c.
Note that
d.
With
key
a
To install e.
the
replacement
key
to be used into the new lock.
in the unlocked one or more
fine file,
a new
Loosen the
position,
tumblers
remove
examine the top of the lock barrel where the slots for the tumbler
are
lock in the cabin door,
of each of these tumblers. The
proceed
upholstery panel on the assembly.
as
located.
the slot.
protruding through
portion
the raised
are
key
will
now
operate the
new
lock.
follows:
cabin door to
gain
access to
the handle mechanism
through
the cutout in
the channel under the latch
f.
Remove the lower aft
move
the
screw
from the external door handle
pin from the handle through
fairing directly
under the lock mechanism, and
re-
the cutout in the door channel.
NOTE Both the extreme aft The extreme aft the
Dec
screw
and the lower aft
screw secures
sliding bolt latch pin
in
screw
the door handle
of the outside latch
spring
in
position,
housing
serve as
and the lower aft
retainers.
screw
retains
position.
52-10-00
A21
Ray~heon
Aircraft
BEECH BONANZA SERIES MAINTENANCE MANUAL g.
Remove the aft
disengaged
to be
h.
After
i.
Bevel the
fitting
screw
from the external door handle
from the
the
new
lock to the
key,
install the lock
of the square hole in the end of the lock barrel. The locking lug on the Cover a i. locking cam k.
fairing.
This will free the handle
spring
and allow the handle
actuating assembly.
edges
steel
cloth to
is
in
plate with firmly riveted
locking cam
barrel, in the unlocked position, into
cam
(beveled edge
must face
the handle.
out), and place
the
cam on
the
must be in line with the handle.
prevent marring
the latch handle and peen the end of the lock barrel until the
place.
Install the handle in the door.
REMOVING AND INSTALLING THE CABIN DOOR TELEFLEX CABLE Remove the inside door handle and the machine
b.
Remove the door
c.
Remove the bolt
securing
the teleflex cable to the upper door latch.
d.
Remove the bolt
securing
the lower end of the cable to the lower
screws on
facing.
the upper door
a.
upholstery panels.
actuating
arm.
NOTE Attach
a
length of safety
wire to the lower end of the cable before
leave the wire in the cable track e.
the
Grasp the upper end of the safety wire from the cable.
as a means
cable with vise
of positioning the
grip pliers
and
pull
new
it out
removing
it from the door and
cable.
through
the upper latch
opening.
Remove
NOTE Braze f.
or
silver solder two AN340-832 nuts to two
new
AN742-4
clamps.
installing the upper clevis, place one of the newly prepa;ed clamps between the shoulders on the lower housing and attach the safety wire remaining in the door to the upper end of the cable housing.
Prior to
end of the cable g.
Pull the
safety
housing
into
position by gripping it with vise grip pliers below the shoulder at the lower end. Pull on the tapping on the vise grip pliers to drive the housing through the door chan-
wire attached to the upper end while
nel.
Align the lower clamp with clamp in place on the housing h.
the hole in the door and
secure
it in the
facing
and
secure
it with
a
machine screw, then install the upper
same manner.
i.
Install the upper clevis and attach the cables to the upper and lower latch connections.
j.
Adjust
nai
cable tension
by varying
the cable
length
at either latch connection.
52-1 0-00
Dec
23/9 Page
9
Ray~heon Aircraft BEECH BONANZA SERIES MAINIENANCE MANUAL
INTERIOR CABIN DOOR HANDLE INTERIOR CABIN DOOR HANDLE REMOVAL AND INSTALLATION
NOTE It may be necessary to place the interior cabin door handle in the unlatched that secure the door handle.
position
to access both
screws
that
the interior door handle base
a.
Remove the two
b.
Slide the interior door handle from the shaft,
to the shaft. Refer to
c.
screws
Figure
secure
maintaining
the
plate.
same
orientation of the door handle with respect
3.
Rotate the door handle 90" clockwise,
maintaining
the base
plate
in the
same
position
as
shown in
Figure
3.
NOTE Interior door handle
configuration
d.
Slide the interior door handle
e.
Latch the door
by rotating
over
of
some
the shaft and secure,
f.
to
ceD01
23/99
screws
removed in step
3.
a.
I
depressing the
handle lock release button should not
depressing
the handle lock release button. If the door remains
step g. If the door becomes unlatched, repeat steps
With the door latched, g. should unlatch.
Page
the
Figure
of the door.
Rotate the interior door handle clockwise without
latched, proceed
using
CAUIION cnvnoN
Rotation of the interior door handle without
unlatching
may differ from that shown in
the interior door handle counterclockwise.
I result in
airplanes
depress the handle lock
52-1 0-00
release button while
a
through
rotating
e.
the door handle clockwise. The door
nll
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
STEP
CORRECT INSTALLATION
INCORRECT INSTALLATION
BASE FLAT
UP
FREE-PLAY* up
STEP
DETAIL
FWD
I
A
R
FWD FREE-PLAY+
A FORWARD DOOR EDGE NOTE: FREE-PLAY TRAVEL OF THE COPILOT’S DOOR HANDLE WHEN IN LATCHED POSITION
FORWARD DOOR EDGE
COPILOT’S
CORRECT INSTALLATION
II
DOOR
HANDLE
INCORRECT INSTALLATION
AFT DOOR EDGE
II II
AFT DOOR
EDGE
UP
II
UP
BASE
STEPPLATE STEP
FWD
DETAIL FREE-PLAY*
B
II
AFI
B
NOTE:
FREE-PLAY TRAVEL OF THE UTILITY DOOR HANDLE WHEN IN LATCHED POSITION
r
UTILITY
Interior Crew Door Handle and Interior
A21
DOOR
FREE-PLAYr
HANDLE
Utility Door Figure 3
TH528
9925721\1\
Handle Installation and Orientation
52I10-00
Dec
23/99Pagell
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CARGO DOORS
MAINTENANCE PRACTICES
UTILITY DOOR REMOVAL a.
With the doors open,
b.
Support
remove
the doors and
(E- I II 1,
E- 1241 AND
the
that attach the scissors door stop to the door sill.
remove
screws
the
hinge pins by pulling straight
UTILITY DOOR INSTALLA TION a.
Support
b.
Install the
the doors and install the
AFTER; EA-1 AND AFTER)
(E- I I 1 I,
up.
E- 124 1 AND AFTER; EA- I AND
AFTER)
hinge pins.
that attach the scissors door stop to the door sill.
screws
UTILITY DOOR ADJUSTMENT If the
utility
made to
door does not close
properly or permits air leaks while completely closed, several adjustments may be of the door. After determining the origin of the air leakage as to whether it is from sealing proper forward half of the utility door or the aft half of the door, make the following adjustments as necessary:
assure
around the
ADJUSTMENT OF THE AFT HALF OF THE UTILITY DOOR
Adjustments of the aft door may be performed by removing ening the door latch connecting tube assembly. a.
the
upholstery paneling
and
shortening
or
length-
NOTE
By shortening b.
To
the
connecting
tube
assemblies, the door will be pulled tighter against the door seal.
adjust the length of the connecting tube assembly, remove the cotter key, washers and pin. assembly and turn the pin eye "out" to lengthen the tube assembly.
Turn the
pin
eye
"in" to shorten the tube c.
After the desired
d.
Replacethe upholstery paneling.
length
has been set, install the
pin,
washers and cotter
key.
ADJUSTMENT OF THE FORWARD HALF OF THE UTILITY DOOR a.
If air
leakage
door latch striker For
is found around the forward half of the door, the necessary adjustments may be made at the aft located slightly above and below the upper and lower door sill of the aft door.
plates,
tighter fit, loosen the screws on the upper and lower striker plates on the aft door and move them inboard. By moving the plates inboard, the aft door will adjust inboard thus pulling inward the forward door when it is latched. b.
a
UTILITY DOOR LA TCH PIN ADJUSTMENT If the forward door does not open by the following adjustments: a.
Removethe
b.
Remove the cotter
c.
Loosen the
lengthen
n21
freely,
the door latch
pins
may not be
retracting enough. This
may be corrected
upholsterypaneling. keys, pins
and washers.
pin eye jam nut and turn the the tube assemblies.
pin
eye "in" to shorten the tube assemblies; turn the
pin
52-30-00
eye "out" to
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL d.
After the desired
e.
Replacethe upholstery paneling.
length
has been set,
tighten
the
pin
eye
jam
nut. Install the
pins,
washers and cotter
keys.
INTERIOR UTILITY DOOR HANDLE REMOVAL AND INSTALLATION Refer to Section 52-10-00, INTERIOR CABIN DOOR HANDLE for the removal, installation and checkout instrucutility door handle.
tions for the interior
LARGE BAGGAGE DOOR REMOVAL
0-10097, 0-10120 AND
(CE-746,
CE-772 AND AFTER; CJ- 149 AND AFTER;
AFTER)
a.
On the
b.
Removethedoorhinge pin.
large type door, unlatch the door and
remove
the scissors
type door stop
at the
top of the door.
LARGE BAGGAGE DOOR INSTALLA TION (CE-748 CE-772 AND AFTER; CJ- 149 AND AFTER; D- 10097 0-10120 AND AFTER) a.
Installthedoorhinge pin.
b.
Install the scissors type door stop at the top of the door.
SMALL BAGGAGE DOOR REMOVAL D- 10097 D- 10120 AND AFTER)
(CE-746, CE-772 AND AFTER; CJ- 149 AND AFTER;
a.
On the small door, unlatch the door and
b.
Disconnect the door stop rod from the door at the door.
remove
the door
hinge pin
while
carefully holding
the door in
position.
SMALL BAGGAGE DOOR INSTALLA TION
(CE-748 CE-772 AND AFTER; CJ- 149 AND AFTER; 0-10097, 0-10120 AND AFTER) a.
Connectthestop
b.
While
rodtothedoor.
carefully holding
the door in
position,
install the
hinge pin.
BAGGAGE DOOR ADJUSTMENT(CE-748 CE-772 AND AFTER; CJ- 149 AND AFTER; D- 10097 0-10120 AND AFTER) If the
large baggage door does not open freely, by the following adjustments:
the door latch
pins
may not be
retracting enough.
This may be
cor-
rected a.
Removethe
b.
Remove the cotter
c.
Loosen the
lengthen
upholsterypaneling. keys, pins,
and washers.
pin eye jam nut and turn the the tube assemblies.
d.
After the desired
e.
Replacethe upholstery paneling.
Dec
23/99~e2jSgg
length
has been set,
52-30-00
pin eye
tighten
"in" to shorten the tube assemblies; turn the
the
pin
eye
jam
nut. Install the
pins,
pin
eye "out" to
washers and cotter
keys.
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL If additional inward tension for
sill
(large door),
A21
or
inward
on
a
the
tighter fit of the door is required, adjust inward the three striker plates single latch mechanism contact plate on the door sill (small door).
52-30-00
on
the door
Dec
23/99Page
3
CHAPTER
FUSELAGE
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 53 LIST OF PAGE EFFECTIVITY
CHAPTER SECTION
SUBJECT
PAGE
DATE
53-EFFECTIVITY/CONTENTS
1
.,.,....._,,May 9/80
53-30-00
1
6
May ...............May ...............May ...............May ...............May ...............May
7
....,..........May
9/80
8
...............May ............_May
9/80
2 3 4 5
9
CHAPTER 53
9/80 9/80 9/80 9/80 9/80 9/80
9/80
FUSELAGE
TABLE OF CONTENTS CHAPTER
SECTION SUBJECT
SUBJECT
PAGE
PLATES/SKIN Maintenance Practices
Fuselage
Access
......1
........._.,.,.,
Openings (CE-728, CE-772
and after;
CJ-149 and after). Access Openings
......t
Fuselage Fuselage
(D-10097, D-10120 and after).......... Access Openings (E-llll, E-1241 and after, EA-1 and after) Fuselage Skin Thickness (CE-748, CE-772 and after; CJ-149 and after)
......3
:......4
Fuselage Skin Thickness (D-10097, D-10129 and after)............ Fuselage Skin Thickness ~E-llll, E-1241 and after, EA-1 and
......2
after)
....,..6 .......8
I’END"
53-EFf ECTIVTTYICQNTENTS
paaa 1 May 9/1)0
BEECHCRAFT BONANZA SERIES MAINtENANCE MANUAL
PLATES/SKIN
MAINTENANCE PRACTICES
FUSELAGE ACCESS OPENINGS
81
3
456
2
7
i.
2
Engine
5
Cowl
5.
Empennage Utility Access
Engine
6.
Empennage Control Linkage
Receptacle
7.
Fuel Strainer
8.
Landing Gear
2. Access Plates for 3.
External Power
4.
Empennage Utility Access
Actuator
33-13-15
Fuselage
Access
Openings (CE-748, CE-772
Figure
and after; CJ-149 and
after)
1
53-30-00
Page 1 May 9/80
BEECNCRAFT BONANZA SERIES MAINTENANCE MANUAL
r‘5
4
3
77
O s
3
i.
7
5. External Power
Engine Cowl
2. Access Plates for
Engine
3. Differential Mechanism 4.
Empennage
Page 2 May 9/80
(LH)
Control Linkage
Fuselage
53-30-00
2
Access
Receptacle
6. Differential Mechanism 7.
(Lower)
Landing Gear Actuator ssts~e
a. Fue~ Strainer
Openings (0-10097, 0-10120 and after) Figure 2
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
1
~O 0~5
CI
i
456
5.
Empennage Utility Access
Engine
g.
Empennage Control Linkage
Receptacle
7.
Fuel Strainer
5.
Landing Gear Actuator
i.
Engine Cowl
2.
Access Plates for
3.
Extemal Power
4.
Empennage Utility Access
36-13-17
Fuselage Access Openings (E-llll, E-1241 Figure 3
and after; EA-1 and
after)
53-30-00
Page 3 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
FUSELAGE SKIN THICKNESS
THICNESS MA TERIAL
ININCHES
1.
2024-73
.020
2.
2024-73
.025
3.
2024-73
.032
4.
2024-742
.020
5.
2024-742
.032
6.
6061-76
.020
7.
6061-76
.025
8.
6061-76
.040
9.
COMP 301 CRES
.016
NUMBLFR
Fuselage Skin Thickness (CE-748, CE-TI2 and after; CJ-149 and after) Figure 4 (Sheet 1 of 2)
53´•30-00
Page 4 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
3
7
i
8
i
3
7
1
e
3
1
7
4
3
6
7
~86 3
8
8
8
1~
1
3
7
iT7
j
32 2
2
93
9
f
i 1
1
i 33-1 3-18
Fuselage
Skin Thickness
(CE-748, CE-7M and after; CJ-149 Figure 4 (Sheet 2 of 2)
and
after)
53-30-00
Page 5 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
THICKNESS MA TERIAL
ININCHES
1.
2024-73
.020
2.
2024-73
.025
3.
2024-73
.032
4.
2024-742
.020
5.
6061-76
.020
6.
6061-76
.025
7.
6061-T6
.040
6.
COMP 301 CRES
.016
NUMBER
Fuselage Skin Thickness (D-10097, 0-10120 Figure 5 (Sheet 1 of 2)
53-30-00
Page 6 May 9/80
and
after)
BEECHCRAFI BONANZA SERIES MAINTENANCE MANUAL
s
5
6
2 4
7
3
2
3
3
3
3
3
3
3
3
3
i
3 3
3
6
1
i
3
3
ii 3
3
4
32
3
1
223
1
f
8
3
8
36-13-19
Fuselage
Skin Thickness (0-10097, 0-10120 and after) Figure 5 (Sheet 2 of 2)
53-3090
Page
7
May 9/80
BEECHCRAFT BONAEIZA SERIES
MAINTENANCE MANUAL
THICKNESS MA TERIAL
ININCHES
1.
2024-T3
.020
2.
2024-T3
.025
3.
2024-T3
.032
4.
2024-T3
.040
5.
2024-T3
.063
6.
2024-T4
.032
7.
2024-T42
.020
8.
2024-f42
.032
9.
6061-T4
.025
10.
6061-T4
.040
11.
6061-T6
.020
12.
6061-f6
.025
13.
COMP 301 CRES
.016
NUMBER
Fuselage Skin
Thickness
(E-llll, E-1241 and after; EA-1 and after) 6 (Sheet i of 2)
Figure
53-30-00
Page 8 May 9/80
BEECHCRAFT BONA~ZA SERIES MAINTENANCE MANUAL
’P
1
9
5
7
3
3
i
1.2
1
i5)0
1
s
9
9
4
s
3
3
i
11
3
Fuselage
i
5
2
5
3
2
o 1~
i
6
13
1
lp
a
3
5
3
1
1
3
1
3
1
3
13
2
i
3
Skin Thickness (E-llll, E-1241 and after; EA-1 and Figure 6 (Sheet 2 of 2)
10
12
after)
"END" 53-3090
Page 9 May 9/80
CHAPTER
STABILIZERS
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 55
STABILIZERS
TABLE OF CONTENTS CHAPTER
SUBJECT
PACE
55-00-00 General
1
Maintenance Practices
3
Empennage Skin Thickness 55-10-00
1
Maintenance Practices
Horizontal Stabilizers
Horizontal Stabilizer Removal
(CE-748, CE-772
and after; CJ-149 and after; E-llll, E-1241 and
after, EA-1 and 1
after) Horizontal Stabilizer Installation and
(CE-748,
CE-772 and after; CJ-149 and after; E-llll, E-1241 and after; EA-1
after)
Stabilizer Removal
1
(D-10097, D-10120 and after) (D-10097, D-10120 and after)
1
Stabilizer Installation
55-20-00 Elevator and Ruddervator
1
Maintenance Practices and after; E-llll, E-1241 and after: EA-1 and
Balancing The Elevator (CE-748, CE-772 and after; CJ-149 Checking Balance CheckBalance By Force Measurement Balancing Procedure Force Measurement Method Check Balance By Counterbalancing Balancing Procedure Counterbalancing Method Balancing the Ruddervator ~D-10097, D-10120 and after) Checking Balance Checking Balance By Force Measurement Balancing Procedure Force MeasurementMethod Check Balance By Counterbalancing Balancing Procedure Counterbalancing Method
after) 1 1 1 1
_
3 3 4 4 4 4
5 5
55-30-00.
1
Vertical Stabilizer- Maintenance Practices Vertical Stabilizer Removal
(CE-748, CE-772
and
after; CJ-149 and after; E-llll, E-1241 and after; EA-1 and 1
after) Vertical Stabilizer installation
(CE-748,
CE-772 and after; CJ-149 and after; E-???l, E-1241 and after; EA-1 and 1
after) 55-40-00
1
Rudder- Maintenance Practices
Balancing The Rudder (CE-748, CE-772 and after, CJ-149 Checking Balance Checking Balance By Force Measurement
and after, E-llll, E-1241 and after; EA-1 and
after)
1
1 1
55-CONTENTS Page 1 A16
Oct 16/92
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
TABLE OF
CHAPTER
SUBJECT
Balancing
CON’TENTS (Cont’d)
Procedure Force MeasurementMethod
By Counterbalancing Equipment Required To Perform Check Balancing By Counterbalancing Balancing Procedure Counterbalancing Method
Check Balance
PAGE 1
1 1 3
"END"
55-CONTENTS
Page 2 Oct 16/92
A16
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 55 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT
55-EFFECTIVITY 55-CONTENTS
55-00-00
PAGE
1
Oct 16/92
1
Oct 16/92
2
Oct 16/92
1
5
May May May May May
1
Oct 16/92
2
Oct 16/92
1
Oct 16/92
2 3 4
55-10-00
55-20-00
DATE
9/80 9/80
9/80 9/80 9/80
2
May 9/80
3
Oct 16/92
4
Oct 16/92
5
Oct 16/92
6
Oct 16/92
55-30-00
1
May 9/80
55-40-00
1
May 9/80 May 9/80 May 9/80
2
3 "END"
55-EFFECTIVITV
Page A16
1
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL GENERAL
MAINTENANCE PRACTICES
a
:I
II_
9
12d
2
1.
VERTICAL STABILIZER
2
HORIZONTAL STABILIZER ELEVATOR BONDING JUMPER RUDDERTAB RUDDER
3. 4.
5. 6.
ELEVATOR CENTER HINGE ELEVATORTAB 9. ELEVATOR TORQUE FITTING ’10. ROTATING BEACON 11. DORSAL FIN FAIRING 12. DORSAL FIN SADDLE 7.
8.
’THIS ROTATING BEACON IS OPTIONAL ON E-llll. E´•1241 AND AFTER; EA-1 AND AFTER.
36-131-8
Empennage (CE-748, CE-n2 and after; CJ-149 and after; E-llll, E-1241 and after; EA-1 and after)
Figure
i
55-09-00
Page 1 May 9480
BEECHCRAFT BONANtA SERIES MAINTENANCE MANUAL
io
j
I
5
(BOTH SIDES)
6 (UPPER AND LOWER)
(COVER)
1
6
(UPPER AND LOWER)
36-131-7
Empennage Skin and
Thickness (CE-748, CE-T~S and after; CJ-149 after; E-llll, E-1241 and after; EA-1 and after)
Frgure
554090
Page 2 May 9/80
2
(Sheet
1 of
2)
BEECHCRAFF BONANZA SERIES MAINTENANCE MANUAL
EMPENNAGE SKIN THICKNESS THICKNESS MA TERIAL
IN INCHES
1.
Royalite
3/32 inch
2.
181 Glass Cloth and
3.
Acrylic P.V.C. Alloy Sheet
4.
Magnesium Alloy
5.
2024-T
.020
6.
2024-73
.020
7.
6061-74
.020
8.
2024-7
.032
9.
2024-’73
.032
10.
2024-T
.040
11.
6061 -T6
.040
12.
6061-T6
.050
NUMBE~
Polyester
Resin .090
Condition H
.020
NOTE
Skin thickness for the left side of the empennage
are
the
same as
the
right
side.
’This skin used "This skin used
only only
on
CJ-149 and after.
on
CE-748, CE-772 and after; E-llll,
E-1241 and after; EA-1 and after.
Empennage Skin Thickness (CE-748, CE-n2 and after; CJ-149 and after; E-llll, E-1241 and after; EA-1 and after) Figure 2 (Sheet 2 of 2)
5590-00
Page-3 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
O
o
Q
;II~--
1
.´•,´•J
I
1. Stabilizer
2. Stabilizer
Tip
3. Ruddervator Worn 4. Ruddervator 5. Stabilizer
Hinge
6. Ruddervator Tab 7. Stabilizer Rear Soar 8. Stabilizer Front
Spar 38-131´•6
Empennage (0-10097, 0-10120 and after) Figure 3
55-0040
page 4 May 9/80
BEECHCRAFT BONAkUA SERIES MAINTENANCE MANUAL
F~oY o
a
(BOTH SIDES)
1 4
(COVER)
3g131-5
EMPENNAGE SKIN THICKNESS THICKNESS IN INCHES
NUMBER
MATERIAL
1.
MAONESIUM ALLOY
2.
2024-T3
.020
3.
2024-T4
.020
4.
2024-T3
.025
5.
2024-T3
.040
6.
6061-T6
.040
7.
6061-T6
.050
COND H
.020
Empennage Skin Thickness (D-10097, 0-10120 and after) Figure 4
"END"
55-00-00
Page 5 May 9/80
BEECHCRAFT
BONANZA SERIES
MAINTENANCE MANUAL
STABILIZERS HORIZONTAL NANCE PRACTICES
MAINTE-
STABILIZER
REMOVAL
HORIZONTAL
(CE-748, CE-772 AND AFTER; CJ-149 AND ;4FTER, ~-1111, E-1241 AND AFTER; EA-1 AND
Install the inboard elevator hinge bracket d. the aft side of the ah spar with four bolts with heads on the aft side of the hinge bracket. Place one MS20002C4 washer under the head of each bolt and
on
two AN960-416 washers under each nut. nuts to 85-100
e.
applicable elevator. ELEVATOR REMOVAL in Chapter 27-30-00. Remove the
Refer to
the
on
Connect the trim tab
ble
Connect the elevator tab cables, accessithe left side fuselage access openings.
through
Install the
g. Disconnect the elevator tab cables,
c.
through
the left side
fuselage
access
openings.
raereht spar.
Disconnect the trim tab
HORIZONTAL
STABILIZER E-1241
remove
already installed, kits are available provide additional support to the stabilizer leading edge on V-tail Bonanzas. ’Refer to Chapter 51-00-00. Remove the applicable elevator. Refer to a. ELEVATOR REMOVAL in Chapter 27-21-00.
AFTER; EA-I b.
position
Remove the rear
panels fuselage.
access
of the
located
on
the
and install c.
attaching bolts.
spar
D-10120)
io-loos7.
to
left side, at the
Place the stabilizer in
a.
to
If not
the
INSTALLATION
AND
Refer
elevator.
Chapter 27-30-00.
NOTE
(CE-748, CE-772 AND AFTER; CJ-149 AND
;4FTER; AND AFTER)
REnnovaL
STABILIZ~RAND AFT~R)
Remove the stabilizer.
g.
rear
Install the applicable h. INSTALLATION OF ELEVATOR in
pushrods.
While supporting the stabilizer, f. attach bolts at the front spar.
panels.
access
acces-
Remove the elevator rear spar attaching d. bolts and the elevator center hinge bracket on
e.
to the sta-
pushrods
bilizer. f.
Remove’the access panels located b. left side at the rear of the fuselage.
the
the
AFTER) a.
sible
Torque
inch-pounds.
Disconnect the elevator tab cables,
through the left side fuselage
sible
access
acces-
openings.
NOTE When
installing the horizontal stabilizer, rear spar attaching bolts the placed on the forward side of the
the nuts for the must
avoid
to
spar center
contact
with
the
nuts
on
the
bolts to
85-100
a.
the
stabilizer spar attaching bolts through the inboard holes in each spar with the bolt heads on the aft side of the spar. Place one
Install
four
MS20002C4 washer under the head of each bolt and AN960-416 washer under each nut. Torque the nuts to 85-100
rear
b.
aft
one
inch-pounds,
supporting
the stabilizer, rear
remove
the
spar.
Remove the stabilizer.
STABILIZER 0-10120 AND
inch-
pounds, c.
While
f.
hinge assembly.
the
e.
elevator
Install the forward stabilizer spar attaching bolts. Place one MS20002C4 washer under the head of each bolt and two AN960-416 washers under each
Torque
Remove the attach bolts at the front spar.
stabilizer attach bolts at the
b.
nut.
d.
INSTALLATION
/D-10097,
AFTER)
Place the stabilizer in position and install attaching bolts.
stabilizer
Install the forward stabilizer spar
attaching
bolts.
Torque the front spar attaching nuts to pounds and the rear spar attaching bolts 85-100 inch pounds. c.
200-225 inch to
55-10-00
Page A16
1
Oct 16/92
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
d. ble
e.
f.
Connect the elevator tab cables, accessi-
through the left side fuselage Install the
access
access
openings.
Install
the
applicable elevator.
Refer
to
ELEVATOR INSTALLATION in Chapter 27-21-00.
panels. "END"
5110-00
Page 2 Oct 16/92
A16
BEECHCRAFT
BONANZA SERIES
MAINTENANCE MANUAL
ELEVATOR AND RUDDERVATOR NANCE PRACTICES
MAINTE-
A stand with knife-edge supports as illusFigure 1. The knife edges should be in the horizontal plane.
a.
trated in same
TH~ BALANCING ELEVATOR~-748, CE-772 AND AFTER; CJ-149 AND FTER; ~-1111, E-1241 AND AFTER; EA-1 AND
AFTER) (Figure 1) it
the
by
being repainted, trailing edge so that excess paint the leading edge. AFTER ANY
WITHIN THE
MANUFACTURER’S PRESCRIBED LIMelevator assembly, includ-
the control
arm
and the tab control rod should not
maximum moment of 7.8 inchtail-heavy pounds. The static moment is the total unbalanced weight of the elevator control surface multiplied by the perpendicular distance from its hinge centerline to the center of gravity, when the chord line is horizontally level. The weight is measured in pounds and over a
the distance in
inches. The static moment of
a
100
percent balanced elevator control surface is 0.0 Ib. A tail-heavy surface exhibits static underbalance. A nose-heavy surface exhibits static overbalance. CHECKING BALANCE
with the elevator
completely
a
draft-free
assembled in
flying
condidtion. ALL PAINTING, INCLUDING STRIPES AND TOUCH-UP, MUST BE COMPLETED. The tab, tab static wicks, and hinge bolts must be attached. The chord line must be horizontally level and the hinge line must be properly supported when
pushrod,
the static moment is measured.
Although many different methods of check balancing exist, they can be categorized under the following two headings:
Actual Force Measurement- Measurement a. of the force applied by the elevator surface on a single support at a known distance from the centerline
hinge.
d.
its
capacity should equal
a
in
flat
tare
A
straightedge,
ruler and
spirit level.
Balancing Procedure Force Measurement Method Locate the chord line by placing a straightedge at the inboard end of the elevator so that one end is aligned with the center of the torque tube and the other end is centered on the trailing edge. Mark the chord line by grease pencil or other means on the rib. Remove the straightedge. Fit correct size bolts in the outboard and center hinge brackets and mount the elevator on the knife edges. Ensure that it is free to rotate about the hinge line. Support the trailing edge behind the
hinge point with a spindle resting on a leveled balance platform as illustrated. The spindle must be vertical throughout the balancing procedure. Hold a spirit level against the marked chord line and
center
beam
b.
The application of a Counterbalancing or weight at a measured distance from
hinge
line to counter the unbalance moment of
it
by extending
or
contracting
spindle.
the
Measure the perpendicular distance from the hinge centerline to the point supported by the spindle. Ensure that the spirit level and rule are removed from th,,urface and read the reaction on the beam balance.
Calculate the static underbalance moment "M" from the formula:
M
D(R-T) inch-pounds where,
Perpendicular distance from the hinge centerline to the spindle point (inches). D
R
known force the
calibrated
A support spindle similar to the illustration c. leveling blocks, as required (blocks spindle tare).
level The elevator balance must be checked in
of the
balance
complete painted
be
area
beam
less. The balance should have
and
drain toward REPAINTING OR REPAIR, THE FINISHED SURFACE SHOULD BE CHECK BALANCED TO ENSURE THAT ITS STATIC MOMENT ABOUT THE HINGE LINE IS
ing
or
plus 2.0 Ibs. minimum.
will
ITS. The
certified
weighing platform and
When the elevator control surface is
suspend
A
b.
units of.Ol Ib.
Reaction
Tare, i.e. spindle plus leveling blocks
T 0"
from the beam balance.
(pounds)read
the scale
or
shims
platform (pounds).
the elevator assembly. The
following
is
an
example:
CHECK BALANCE BY FORCE MEASUREMENT
D is 13.5 inches, R is 1.49 Ib. and T The
by
equipment required
to
force measurement is
perform the
as
follows:
1.00 Ib.
check balance
M
13.5
(1.49 -1.00);
M
6.6
inch-pounds.
55-20-00
Page Ale
1
Oct 16/92
BEECHCRAFT BONANZA SERIES klAINTENANCE MANUAL
COUNTERBALANCING
MASKING TAPE
(PLACE NEAR ELEVATOR HINGE LINE)
CONTAINER
VIEW,A-A TOP FORWARD SCREW JIG MUST BE HORIZONTALLY
LEVEL FOR UNDERBALANCE CHECK
A
B MASKING TAPE
DETAIL
B
’CONTAINER
MASKING TAPE
(TO SECURE TAB IN NEUTRAL)
ELEVATOR
HINGE CLEVIS
7 8
KNIFE EDGE
E
55-1528
JIG MUST BE HORIZONTALLY1LEVEL
ACTUAL
Balancing
55-20-00
Page 2 May 9/80
FORCE MEASUREMENT
the Elevator, Ruddervator Figure 1
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
M is within the range which is
CAUTION
satisfactory.
Be certain the forward top screw on the leading edge tip is secured after the elevator has been balanced.
If M is not within the
prescribed range, refer to step i under BALANCING PROCEDURE COUNTERBALANC-
elevator
ING METHOD.
Add small
e.
CHECK BALANCE BY COUNTERBALANCING until The
equipment required to perform check balancing by counterbalancing is as follows:
the
Check this
knife-edge supports as illustrated in Figure 1. The knife edges must be in the same horizontal plane. A paper cup
c.
Approximately
d.
A certified beam balance
or
similar
lightweight contain-
by holding
the
with
shot to the cup chord level.
the
spirit level aligned with
The distance "D" must be
the
hinge line. Measure suspension point of the
"D" from the
the
perpendicular to hinge line to the
cup.
Remove the cup, contents, and
g. b.
quantities of lead
balances
marked chord line. f.
A stand with
a.
elevator
string, then
weigh them.
er.
NOTE
calibrated in units of.Ol
2
pounds of
pound
lead shot.
Since any weighing error is magnified by the distance "D", weighing is most impor-
weighing device
tant and must be done
lesS.
or
that A
e.
Balancing a.
straightedge, ruler,
Procedure Locate
straightedge assembly so
that
the one
chord
line
inboard end is
end
Mark the chord line with grease
pencil,
then
spirit
a
on
h.
the
Calculate the static balance
by
1.
placing
of the
a
elevator
hinge centerline the trailing edge.
The
designated by
with
a
2.
as
position
weight of the
ises and mount the elevator
on
the
hinge knife-edge
ports. Ascertain that the elevator is free about the hinge line. d.
The
3.
a
over or
M
W
The
balancing
to
clev-
suprotate
weight should be added or length of small diameter string secured to the surface with a small piece of masking tape and a paper cup hanging vertically as illustrated in Figure 1. Slightly loosen the forward top screw on the elevator leading edge tip. Suspend the paper cup on the inboard side of the tip and wrap the string with
0´•60
x
small
D.
following
is
a
typical example of
calculation:
screw.
Secure the
string
to the surface
pound" and
M
underbalanced
(tail-heavy)
0.60
x
"D
12.6 inches", then:
12.6
M 7.6 inch-pounds. In this instance, "M" is within the required static balance range and is therefore acceptable.
short
piece of masking tape aft of the top forward screw and near the hinge centerline as shown in Figure 1. The cup must be free to hange vertically. a
underbalance moment is
and the paper cup was suspended from the horn. If the elevator balances with the chord line level at "W
To determine if
use a
around the
cup and contents is
"W".
Assume the elevator is
removed,
follows:
piece of masking tape.
Fit the correct size bolts in the
c.
as
straightedge.
Secure the trim tab in its neutral small
scales
designated by "M".
4. b.
on
Method
suitable marker, such
remove
carefully
certified for accuracy.
level.
the
on
and the other end is centered
a
a
Counterbalancing
the
at
and
are
i.
The complete
including
the control
must not be
7.8
ply,
tail-heavy inch-pounds. If the
remove
elevator
assembly,
and the tab control rod, over a maximum moment of
static balance does not comelevator horn cover and add or solder to bring the elevator balance within
remove
required
painted
arm
the
limits. 55-20-00
Page 3 A16
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
NOTE Coat the
weight
with
tive material such
(20,
Chart 1,
as
CHECKING BALANCE BY FORCE MEASUREMENT
a corrosion prevenzinc chromate primer
equipment required to perform the by force measurement is as follows:
The
91-00-00) to insulate the disReplace the elevator horn
similar metals.
trated in same
BALANCING THE RUDDERVATOR 0-10120 AND AFTER)
ruddervator
the
control
is
surface
being
ENSURE THAT ITS STATIC MOMENT ABOUT THE HINGE LINE IS WITHIN THE MANUFACTURER’S PREThe SCRIBED LIMITS. painted complete rudddervator assembly, including the control arm and the tab control cable attach bolt, nut and washer for both sides of the tab, must not be tail-heavy over a
maximum moment of 14.4 to 17.4 inch-pounds. The static moment is the total underbalance weight ot the ruddervator control surface multiplied by the perpendicular distance from its hinge centerline to the center of gravity when the chord line is horizontally level.
weight is measured in pounds and the distance in inches. The static moment of a 100 percent balanced ruddervator control surface is 0.0 Ib. A tailThe
heavy surface exhibits static underbalance. nose-heavy surface exhibits static overbalance.
A
CHECKING BALANCE The balance must be checked in the
a
draft free in
area
a
with
flying
condition. ALL PAINTING, INCLUDING STRIPES AND The tab, tab TOUCH-UP, MUST BE COMPLETED. control cable attach bolt, nut and washer for both sides of the tab, static wicks and hinge bolts must be The chord line must be horizontally level 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:
attached. and the
a.
c.
d.
Actual Force Measurement
Measurement
The application of a Counterbalancing or weight at a measured distance from
spirit level.
Measurement Method
by placing
a
straightedge
at the
other end is centered on the trailing edge. Mark the chord line by grease pencil or other means on the rib. Remove the straightedge. Fit correct size bolts in the
outboard and center hinge brackets and mount the ruddervator on the knife edges. Ensure that it is free to rotate about the hinge line. Support the trailing edge behind the center hinge point with a spindle resting on a leveled beam balance platform as illustrated. The spindle must be vertical throughout the
spirit level against the by extending or contracting the spindle. Measure the perpendicular distance from the hinge centerline to the point supported by the spindle. Ensure that the spirit level and rule Hold
a
marked chord line and level it
are
on
removed from the surface and read the reaction
the beam balance.
Calculate the static underbalance moment "M" from the formula: M
D(R-T) inch-pounds where,
D
Perpendicular distance from spindle point (inches).
R
known force
ruler and
spindle
inboard end of the ruddervator so that one end is aligned with the center of the torque tube and the
line of the
hinge.
to the illustration
required (blqcks
straightedge,
Locate the chord line
applied by the ruddervator surface on a single support at a known distance from the center-
hinge line
A
as
Balancing Procedure Force
of the force
the
support spindle similar
leveling blocks, tare).
line to the
b.
A
and
balancing procedure.
completely assembled
ruddervator
plane.
b. A certified beam balance calibrated in units of.Ol Ib. or less. The balance should have a flat weighing platform and its capacity should equal tare plus 2.0 Ibs. minimum.
repainted, suspend it by the trailing edge so that excess paint will drain toward the leading edge. AFTER ANY REPAINTING OR REPAIR, THE FINISHED BALANCED TO SURFACE SHOULD BE CHECK
knife-edge supports as illusedges should be in the
The knife
Figure
horizontal
(0-10097,
(Figure 1) When
A stand with
a.
and recheck the balance,
cover
check balance
Reaction
from the beam balance.
Tare, i.e. spindle plus leveling blocks
T on
(pounds)read
the hinge center-
the scale
or
shims
platform (pounds).
to counter the unbalance moment of
the ruddervator
assembly.
The
following is
an
example:
5120-00
Page
4
Oct 16/92
A16
BEECHCRAFT
BONANZA SERIES
MAINTENANCE MANUAL
D is 13.5 inches, R is 2.26 Ib. and T
13.5 (2.26
M
M
-1.00);
inch-pounds.
17.0
M is within the range which is
CAUTION
1.00 Ib.
Be certain the forward top screw on the ruddervator leading edge tip is secured
satisfactory.
after the ruddervator has been balanced.
If M is not within the prescribed range, refer to step i under BALANCING PROCEDURE COUNTERBALANCING METHOD.
Add small
e.
until the
quantities
of lead shot to the cup line
ruddervator balances with the chord
level. Check this
by holding
a
spirit
level
aligned with
the marked chord line.
CHECK BALANCE BY COUNTERBALANCING
equipment required to perform by counterbalancing is as follows:
The
A stand with
a.
trated in
Figure 1. The horizontal plane.
same
check
balancing
knife-edge supports as illusknife edges must be in the
The distance "D" must be perpendicular to f. hinge line. Measure "D" from the hinge line to the suspension point of the cup.
the
Remove the cup, contents, and g. them.
string, then
weigh
NOTE b.
A paper cup
similar
or
lightweight
contain-
er.
3.5
Approximately
c.
pounds
Since any weighing error is magnified by the distance "D", weighing is most impor-
of lead shot,
tant and must be done
that A certified beam balance
d.
calibrated in units of.Ol
straightedge, ruler,
A
e.
Balancing
Procedure Locate
a.
straightedge ruddervator
pound
so
the
that
weighing device
less,
and
spirit level.
a
line
chord lower
one
end is
aligned
1.
placing
by
rib
a´•
of
the
remove
marker, the
with the
cen-
a
as
small
c.
ises and
grease
position
piece of masking tape,
Fit the correct size bolts in the mount the
ruddervator
To determine if
on
the
clev-
hinge knife-edge
weight
weight
should be added
or
leading edge tip, slightly
screw.
underbalance moment is
M
W
x
D.
4. The following balancing calculation:
the
Assume
ruddervator
is
was
typical example
a
underbalance
to
(tail-
from the
heavy) and the paper cup was suspended leading edg‘e. if the ruddervator balances 2.83 pounds" and chord line level as "W
with the "D
6.0
inches", then: 6.0
M
2.83
x
M
17.0
inch-pounds. The product
of "W
x
D". In this
instance, "M" is within the required static balance
acceptable.
loosen
Suspend a paper cup on the tip and wrap the string around the screw. Secure the string to the surface with a small piece of masking tape aft of the forward top screw and near the hinge centerline as shown in Figure 1. The cup must be free to hang vertically, top
inboard side of the
follows:
of the cup and contents is
over or
range and is therefore the forward
as
ruddervator is free to
removed, if the balance is tail-down: On the ruddervator
scales
"M".
3.
pencil, then
straightedge.
The
2.
a
supports. Ascertain that the rotate about the hinge line. d.
a
Secure the trim tab in its neutral
b. with
such
The
designated by
terline of the torque tube and the other end is centered on the trailing edge. Mark the chord line with a
suitable
on
designated by "W".
Method
closure
carefully
certified for accuracy.
Calculate the static balance
h.
Counterbalancing
the
at
or
are
i.
The
bly, including
complete painted the control
arm
ruddervator
assem-
and the tab
control
cable attach bolt, nut and washer for both sides of the tab, should not be tail-heavy over a maximum of 14.4 to 17.4
comply,
inch-pounds. If the static balance does remove
the ruddervator horn
cover
not
and add 55-20-00
Page A16
5
Oct 16/92
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
or
remove
within the
solder to bring the ruddervator balance required limits.
(20, Chart 1, 91-00-00) to insulate the dissimilar metals. Replace the ruddervator horn
NOTE
cover
and recheck the balance.
Coat the weight with a corrosion preventive material such as zinc chromate primer
"END"
5120-00
Page
6
Oct 16/92
A16
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
VERTICAL STABILIZER PRACTICES
MAINTENANCE
Pull the stabilizer
e.
straight
up to
remove
VERTICAL STABILIZER REMOVAL
(CE-748 CE-772 and af2er; CJ- 149 and after; E-l 111, E-1241 and after; EA-1 and after)
VERTICAL STABILIZEF~ INSTALLATION CJ- 149 and aiter; E- 1 II I, E-1241 and after; EA-I and after)
(CE-748, CE-772 and after;
Carefully place
a.
the vertical stabilizer in
Remove the elevators, horizontal stabilizers, and the rudder. Refer to the applicable chapters for removal
and install the bolts in the front and
instructions.
50-70
a.
b.
Torque all inch-pounds.
rear
AN4 vertical stabilizer
b.
Remove the stabilizer saddle and
c.
Connect the
c.
Disconnect the
d.
Install the stabilizer saddle and
applicable). d. Support front and
rear
fairings. rotating beacon wires (if
e.
the stabilizer and
it from the
fuselage.
remove
the bolts at the
rudder.
rotating beacon
position
spars.
attaching
bolts to
(if applicable). fairings.
wires
Install the elevators, horizontal stabilizers, and
Refer to the
applicable chapters for installation
procedures.
spars.
"END"
55-30-00
Page 1 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
RUDDER
MAINTENANCE PRACTICES
tare).
spindle levelling blocks as required. (8locks d. A straight edge, rule and spirit level.
BALANCING THE RUDDER (CE-748, CE-712 and after; CJ- 149 and after; E- I II 1, E-1241 and after; EA-1 and after)
BALANCING PROCEDURE FORCE MEASUREMENT METHOD
(Figure I) Locate the chord line
being repainted, suspend it by that excess paint will drain toward the any repainting or repair, the finished
by placing
When the rudder surface is
inboard end of the rudder
trailing edge so leading edge. After
center of the
the
surface must be check balanced to ensure that its static moment about the hinge line is within the manufacturers
prescribed including
limits. The
the control
complete painted
arm
should not be
assembly, tail-heavy over a
rudder
inch-pounds. The static moment of the by multiplying the unbalanced weight of the rudder 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 maximum of 8.4
rudder is deternined
pounds and the distance in inches. The static moment of a 100 percent balanced rudder assembly is 0.0 inch-pounds, Tail heaviness indicates static underbalance while
nose
heaviness indicates static overbalance,
so
that
straight edge at aligned with
a
one
end is
torque tube and the other end is centered
the
the on
Mark the chord line
by grease pencil or other means on the rib. Remove the straight edge. Fit correct size bolts in the outboard and center hinge brackets and mount the rudder on the knife edges. Ensure that it is free to rotate about the hinge line. Support the trailing edge behind the center hinge point with a spindle resting on a levelled beam balance platform as illustrated. The spindle must be vertical throughout the balancing procedure. Hold a spirit level against the marked chord line and level it by extending or contracting the spindle, or by using blocks and shims under the spindle. Measure the perpendicular distance from the hinge center line to the point supported by the spindle. Ensure that the spirit level and rule are removed the
trailing edge.
from
the
and
surface
read
the
reaction
on
the beam
balance. Calculate the static underbalance moment "M"
from the formula: CHECKING BALANCE M The rudder balance must be checked in
a
draft free
area
completely assembled in flying condition. All painting, including stripes and touch-up, must be completed. The tab, 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: with the rudder
D the
D(R-T) inch-pounds where, Perpendicular distance from spindle point (inches).
R
(Pounds) read from
Reaction
scale
a.
force
applied by
force
or
the rudder surface
Measurement of the
single support at a known distance from the center line of the hinge. The application of a known b. Counterbalancing
weight
on a
at a measured distance from the
to counter the unbalance moment of the rudder
hinge line assembly.
M
center line to
the beam balance. or
shims
on
the
platform (Pounds).
following
is
an
example: 1.49 Ib. and T is 1.00 fb.
D is 13.8 inches, R
Actual Force Measurement
hinge
Tare, i.e. spindle plus levelling blocks
T
The
the
13.8
(1.49
M
1.00);
6.8
inch-pounds.
M is within the range which is satisfactory. If M is not within the prescribed range, refer to step h, under BALANCING PROCEDURE COUNTERBALANCING
METHOD.
CHECK BALANCE BY COUNTERBALANCING CHECK BALANCE BY FORCE MEASUREMENT EQUIPMENT The
equipment required
force measurement is
as
to
perform
the check balance
by
BALANCING BY
Figure plane. b.
Ib.
or
A stand with knife 1. The knife
edge supports
edges should
be in the
c.
as
illustrated in
same
horizontal
A certified beam balance calibrated in units of.Ol a flat weighing platform capacity should equal tare plus 2.0 Ibs. minimum, A support spindle similar to the illustration and
less. The balance should have
and its
PERFORM
CHECK
COUNTERBALANCING
follows: a.
a.
REQUIRED TO
Figure plane.
A stand with knife 1. The knife
edges
b.
A paper cup
c.
Approximately
a.
A
edge supports
as
illustrated in
must be in the same horizontal
light weight container. pounds of lead shot. A certified beam balance weighing device d. calibrated in units of .01 pound or less. or
similar
2
straight edge, ruler,
and
spirit
level.
55´•40-00
Page 1 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
MASKING TAPE
A,C A~
IPLdEI
NIAR RUDDEP HINGI
LINT)
I-,
TAIL
CCoNrAINER
CONTAI
CI\
KNIFE EDGE
I‘
O
~i
ONTAINER
\II
JIO MUST BE HORIZONTALLY LEVEL
ACTUAL FORCE MEASUREMENT
II
J
-uL~
JIO MUST BE HORIZONTALLY LEVEL STATIC OVERBALANCE (NOSE HEAVY)
VIEW
B-B
CONTAINER
VIEW
A-A
JIG MUST BE HORIZONTALLY LEVEL STATIC UNDERBALANCE
(TAIL HEAVY) 36-153´•6Pl
Balancing the Rudder Figure 1
5540-00
Page 2 Mey 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
COUNTERBALANCING
BALANCING PROCEDURE
g.
Calculate the static balance
as
follows:
METHOD The
1.
Locate the chord line
straight edge at that one end is aligned
designated by
with the center of the torque tube while the other end is centered on the trailing edge. Mark the chord line with a
designated by
a.
by placing
the lower closure rib of the rudder so
suitable marker, such
as a
grease
pencil,
a
then
remove
The
2.
the
M
4.
The
hinge brackets and edge supports. Ascertain that the rudder is free to rotate about the hinge line, To determine if weight should be added or c. 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 hom 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 as illustrated in Figure i. The cup must be free to hang vertically. Add small quantities of lead shot to the cup until d. the rudder balances with the chord line level. Check this by holding a spirit level aligned with the marked chord line. The distance "D" must be perpendicular to the a. hinge line. Measure "D" from the hinge line to the suspension point of the cup. f. Remove the cup, contents, and string, then weigh
underbalance
Fit the correct size bolts in the
cup and contents is
over
or
underbalance
suspended
W
is
D
x
following
is
a
typical example of a was slightly
(tail-heavy)
from the horn
and
the
paper cup was If the rudder
leading edge.
balances with the chord line level at "W
"D
moment
calculation: Assume the rudder
balancing
b.
the
"M".
3.
straight edge. mount the rudder on the knife
of
weight
"W".
.65
pound"
and
12.5 inches", then M
.65
M
8.1
x
12.5
inch-pounds. In this instance, required static balance range therefore acceptable.
"M" is
within the
and is
The
complete painted rudder assembly, including must not be tail-heavy over a maximum of 8.4 inch-pounds. If the static balance does not comply, remove the weight in the rudder horn and add or remove solder to bring the rudder balance within required limits. h.
the control
arm
them.
NOTE NOTE
Coat the weight with
weighing error distance "D", weighing is must be done carefully Since any
is
magnified by important
and
scales that
are
most on
material such
the
as
a
corrosion
insulate the dissimilar metals.
weight
in
the
preventative primer to Replace the
zinc chromate
rudder horn and
recheck the
rudder balance.
certified for accuracy,
"END"
55-40-00
Page 3 May 9/80
C H A PT E R
VVIN DOVVS
BEECHCRAFT BONANZA SERIES
MAINfENANCE MANUAL
CHAPTER 56
WINDOWS
TABLE OF CONTENTS CHAPTER
SECTION SUBJECT
SUBJECT
56-00-00
GENERAL
Description
and
......1
Operation
......1
Maintenance Practices
Cleaning
PAGE
...,..1
Plastic Windows
....56-10-00
FLIGHT COMPARTMENT Maintenance Practices
......1
Windshield Removal
......1
Windshield Installation
,.....1
Forward Left Window Removal
,.....1
Forward Left Window Installation
......1
Storm Window Removal
......2
Storm Window Installation
...,..2
Cabin Door Window Removal
......2
Cabin Door Window Installation
......2
.56-20-00
CABIN
,.,...1
Maintenance Practices
Window Removal
Openable Openable Window Installation Utility Doors Window Removal (E-llll, E-1241 and after; EA-1 and after) Utility Doors Window Installation (E-llll, E-1241 and after; EA-1 and after) Windows Aft of Openable Windows Removal Windows Aft of Openable Windows Installation
......1 .......1
,......1 .......1 ,......1 ..........1
"END"
5&CONTtNTS PaPe 1 May 9/80
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 56 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT
PAGE
DATE
56-EFFECTIVITY
1
Oct 16/92
56-CONTENTS
1
May
56-00-00
1
Oct 16/92
1 2
May 9/80 May 9/80
1
May 9/80
56-10-00
56-20-00
9/80
"END"
SE-EFFECTIVITY
Page 1 A1E
Oct 16/92
BEECHCRAFT
BONANZA SERIES
MAINTENANCE MANUAL
GENERAL
DESCRIPTION AND OPERATION
moist chamois.
The windshield and windows for the Bonanza Series
airplanes
are
made of cast
openable window
an
are
windows
of the Model A36
the left side. The cabin
on
area
33 and 35 series each side of
airplanes contains an the airplane, just behind
Never
tone,
of the Model
ah window the
GENERAL
openable
flammable
If it is desirable to
scratches to the window surface. To
avoid
scratches, any cleaning of the wincare.
clean and waxed at
water.
of these
extreme
care
be
must
using these chemicals.
use a
commercial cleaner to clean
washing plastic windows with soap and water, apply a good grade of commercial wax (61, Chart 1, 91-00-00). The wax will fill in minor scratches and help prevent further scratches. Apply a thin, even coat of wax and bring it to a high polish by rubbing lightly with a clean, dry, soft flannel cloth. Never use a power buffer, as the heat generated by the buffing pad may soften the plastic.
When
washing the windows, do not use a bucket or pail. Sand, dirt particles or other debris may collect in the standing water and cause scratches in the plastic.
water from
to feel and
However, it has been discovered that some of these cleaners cause acrylic plastic to craze. Therefore, only the following products are approved as cleaners for acrylic plastic windows: Federal Specification P´•P-560, Part No. 403D; Parko Anti-Static Plastic Polish; and McGuiar’s MGH-10 (60, Chart 1, 91-00-00). Follow the directions on the container. After
CAUTION
dislodge dirt
and
mud. A soft cloth, chamois or sponge may be used only for the purpose of carrying water to the surface with
base
plastic windows, use only cleaners that are approved by Beech Aircraft Corporation. There are several cleaners available commercially that state that they are approved for use on acrylic surfaces.
all times. To prevent scratches and crazing, wash the windows carefully with plenty of soap and running
oughly
a
the
cause
of the window. After
and
exercised when
Do not use an ice scraper to remove ice from windows because this practice may
palm of the hand
with
plastic and may cause crazing. Aliphatic naphtha and similar solvents are highly
CAUTION
kept
ace-
tetrachloride, fire extinanti-ice fluid, lacquer thinner,
materials, for such materials will soften the
CLEANING PLASTIC WINDOWS
Plastic windows should be
gasoline, benzine, alcohol,
carbon
or
MAINTENANCE PRACTICES
dows should be done with
use
guisher or glass cleaner
on
windows.
Use the
1,
CAUTION
airplanes contains two windows on each side, behind the openable windows; a window in each of two utility doors, and matching cabin
Chart water.
on
side, just aft of the flight compartment. The
each
a
electrostatic
(26, Chart 1, 91-00-00) or hexane (59, 91-00-00), then rinse the window with clear
enclosed storm window. The cabin
airplane contains
of the
area
an
Remove oil and grease with a cloth moistened with kerosene (58, Chart 1, 91-00-00), aliphatic naphtha
flight compartment of each airplane is equipped with a windshield, cabin door window, and a left cabin an
plastic window with
cause
acrylic plexiglass.
The
window with
Do not rub the
dry cloth because this will charge which attracts dust.
washing, rinse the window thorrunning water and dry it with a clean,
If the windows
were
cleaned with
commercial cleaners mentioned
one
of the three
previously, it will
not
be necessary to apply wax. Each of these cleaners contains wax, as well as cleaning agents.
"END"
56-00-00
Page Ale
1
Oct 16/92
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
FLIGHT COMPARTMENT PRACTICES
MAINTENANCE
DEFROSTER DUCT ATTACHING SCREW
WINDSHIELD REMOVAL
(Figure I)
DEFROSTER
Remove the
a.
glareshield. Refer
to GLARESHIELD
REMOVAL, Chapter 39-10-00. Remove the
b.
duct and
move
attaching
screws
the duct to clear the lower
from the defroster row
of rivets
on
the
windshield. Mark the
c.
position of
the three
glareshield supports
attached to the inside of the windshield frame. d.
Mark the location and
and lower the headliner to
strips
remove the
permit
headliner trim
the windshield to be
removed.
WINDSHIELD FRAME
55-110-25
Remove any necessary molding that e. window frame to facilitate windshield removal.
covers
the
f.
Remove the rivets from around the windshield.
g.
Remove the windshield.
Figure
to
the
windshield
1
Install the headliner trim
k.
NOTE Due
Windshield
strips
and secure the
headliner in position. Install any windshield molding i. windshield removal.
being sealed,
considerable effort may be required to release the windshield from the canopy section.
Install the
m.
glareshield.
removed
for
Refer to GLARESHIELD
INSTALLATION, 39-10-00. WINDSHIELD INSTALLA TION FORWARD LEFT WINDOW REMOVAL a.
Touch´•up primer.
Remove any sealer around the canopy with toluol. any scratches or bare metal with zinc chromate
Place the windshield in
b.
position
and mark the
area
where material must be removed from the windshield to a proper fit. The windshield frame edge should not bind in the radius of the fuselage framework.
obtain
Remove the windshield
c.
material
as
d.
using
the
e.
and
trim
off
Remove the trim
b.
as
required
to
gain
strip
from around the inside of the
window. c.
Remove the rivets from around the window.
d.
Remove the window.
determined in step "b".
Place the windshield in
pilot
holes
position
and cleco in
place
using
the
existing
(17, Chart 1, 91-00-00)
apply
to the windshield
Using rivets, secure the windshield to the canopy making sure the glareshield supports are installed in the same position as they were removed. h.
section
Clean off the
excess
Presstite 576 sealer from the
outside of the window frame, a narrow
bead of EC1814 sealer (18, Chart
1, 91-00-00) to the outside window frame where the frame meets the canopy section. Remove excess sealer.
Clean the sealer from the canopy section where was removed using toluol (19, Chart 1,
a.
the old window
frame where it makes contact with the canopy section, Place the windshield in position and cleco in place. g.
Place
FORWARD LEFT WINDOW INS7ALLATION
provided.
Back drill the windshield frame
Presstite 576 sealer
j.
upholstery panels
window frame.
excess
holes in the canopy section as a guide, f. Remove the windshield, bun all holes and
i.
Remove the
a.
access to the
91-00-00). Touch up any scratches or bare metal primer (20, Chart 1, 91-00-00). Place the window in position and mark b.
with the
chromate
the area
where material must be removed from the window frame to obtain a proper fit. c.
material
Remove the window
and trim off the
excess
determined in step "b". Place the window in position and cleco in place d. using the pilot holes provided. e.
as
Back drill the window frame
using
the
existing
holes in the canopy section as a guide. f. Remove the window, burr all holes, and
apply
56-10-00
Page 1 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
Presstite 576 sealer (17, Chart 1, 91-00-00) to an area approximately 1/2 inch wide on the canopy section where the
old sealer
g.
was
position
and cleco in
place.
Using rivets, secure the window to the canopy making sure the trim strip clips are reinstalled in the same position as removed. Install the upholstery panels. i. Install the tirm strip. i. h.
Clean off the
excess
a narrow
strip clips. e.
Remove the rivets around the window retainer.
f.
Remove the window.
CABIN DOOR WINDOW INSTALLATION Clean the sealer from the door where the old
a.
(18, Chart 1, 91-00-00) to the outside window frame where the frame meets the canopy section. Remove excess sealer. Place
trim
Presstite 576 sealer from the
outside of the window frame, i.
To facilitate reinstallation, mark the location of the
d.
removed.
Place the window in
section
k.
Remove the trim strip around the inside of the
c.
window.
bead of EC1814 sealer
window was removed,
b. an area
STORM WINDOW REMOVAL
Apply Proseal 890 sealer (21, Chart 1, 91-00-00) to approximately 1/2 inch wide on the door where the
old sealer c.
a.
Open
the latch mechanism at the top of the storm
window, b.
Remove the two
internally threaded hinge pins
at
using toluol (19, Chart 1, 91-00-00).
Touch up any scratches or bare metal with zinc chromate primer (20, Chart 1, 91-00-00).
was
removed.
Place the
new
e.
internally
b.
the window, and
threaded
NOTE
hinge pins
When
at the
riveting the window in place, install the strip clips in the same locations as marked in step "d" of the window removal procedure.
trim
bottom of the storm window, i
over
Secure the window retainer to the door skin with
STORM WINDOW INSTALLATION Install the two
position.
Place the retainer in position, cleco the retainer to the cabin door. rivets.
the bottom of the storm window,
a.
window in
d.
Close the latch mechanism at the top of the storm
window.
CABIN DOOR WINDOW REMOVAL a.
Remove the inboard door handle, ash tray and
arm
rest.
b.
Remove the center
upholstery panel.
PageZ
May
9/80
Install the trim
g. h.
Clean and paint as necessary. Reinstall the center, upholstery
i.
Reinstall the inboard door handle, ash tray and
arm rest.
"END"
56-1 0-00
f.
strip.
panel.
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CABIN
MAINTENANCE PRACTICES
PR1221 81/2 sealer
OPENABLE WINDOW REMOVAL
in
strips a.
b.
(22, Chart 1, 91-00-00) to the area of the
window located in step "d". f. Place the window in
Remove the emergency release Remove the hinge pin.
position and
rivet the
retaining
place.
pin. NOTE
OPENABLE WINDOW INSTALLATION
Connect the latch link rod if the forward window is
a.
Install the
b.
install the emergency release
being replaced.
hinge pin. pin. g. window
Clean
edge
excess
sealer from
the outside of the
and install the interior window
molding.
UTILIN DOORS WINDOW REMOVAL (E-llll, E-1241 and after; EA-I and alter) a.
Remove the window
b.
Remove the rivets from the window
molding
WINDOWS AFT OF OPENABLE WINDOWS REMOVAL
trim.
retaining
strips,
a.
access to
b.
NOTE
Remove the upholstery panels the window frame.
Remove the rivets
on
or screws
the fomard window, remove the latch link rod
so
d.
that all the rivets
c.
are
Remove the window.
Clean the sealer from the cabin section where the was removed using toluol (19, Chart 1, 91-00Touch up any scratches or bare metal with zinc
a.
00).
chromate
retaining strips are required, dimple the rivet holes in the retaining strips with a 5/16 inch dimpler. c. Place the window in position and cleco the retaining strips in place. d. Tape the entire outside surface of the window, then trim the excess tape away from the area that overlaps the door frame. This procedure locates the area that the new sealer is to be applied. Remove the retaining strips and window. Apply e. If new
primer (20, Chart 1, 91-00-00). Apply Presstite 576 sealer (17, Chart 1,91-00-00) area approximately 1/2 inch wide on the cabin section
b.
removed, using toluol, (19, Chart 1, 91-00-00).
Touch up any scratches or bare metal with zinc chromate primer (20, Chart 1, 91-00-00). b.
(Model A36 series airplanes), retaining strips.
old window
Clean the old sealer from the door where the was
from the window
WINDOWS AFT OF OPENABLE WINDOWS INSTALLA 7/ON
Remove the window.
UTILIN DOORS WINDOW INSTALLATION and after; EA-1 and after)
window
gain
accessible.
(E-llll, E-1241 a.
to
Remove the trim strip from around the inside of the
c.
removing the
required
window.
rivets from the retainers
When
as
to an
where the old sealer
was removed. Place the window in position and install the window retaining strips to the cabin section with screws. On c.
the Model A36 series
airplanes only,
the
retaining strips
the top retainer and rivets side and bottom retainers. secured with
d. window
screws on
Clean
excess
are
on
the
sealer from the outside of the
edge and install the trim strips
to the inside of the
window. a.
Install the
upholstery panels.
"END"
56;-20-00
Page May
1
9/80
CHAPTER
VVINGS
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 57
WINGS
TABLE OF CONTENTS
PAGE
SUBJECT 57-00-00
Wings Description
and
1
Operation
2
Maintenance Practices
Wings
Wing Tip
2
Removal
Wing Tip Installation
2
Removal
2
Wing
Removal of
Leading Edge
Installation of
Wing
and Main
Leading Edge
3
Spar
and Main
3
Spar
Installation
8
the
9
Adjusting
Wings
Wing Bolt, Nut, and Fitting Inspection
10
Magnetic-Particle Inspection
14
Outboard
Wing
Main
16
Spar Cap Inspection 57-30-00
Plates/Skin
Wing Wing
1
Maintenance Practices
Access
1
Openings
2
Skin Thickness
57-40-00 Attach
Fittings
1
Maintenance Practices
57-50-00
Flight Surfaces Balancing
1
Maintenance Practices
1
the Aileron
1
Checking Balance
Equipment Required Balancing
to Perform Check
1
Balancing
1
Procedure
1
Counterbalancing Method
A22
57-CONTENTS
Nov
10/0 Page
1
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 57
WINGS
LIST OF PA GE EFFECTIVITY
CHA PTER-SECTION-SUBJECT
PAGE
DATE
57-Effectivity
1
Nov 10/00
S’ir-Contents
1
Nov 10/00
57-00-00
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2
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3
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4
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5
Nov 10/00
6
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7
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8
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11
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15
Nov 10/00
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Jan 20/82
2
Jan 20/82
57-30-00
9/80
57-40-00
1
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57-50-00
1
May 9/80
2
May 9/80
3
May9/80
A22
57-EFFECTIVITY
Nov
10/0 Page
1
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
WINGS
DESCRIPTION AND OPERATION
I
The all metal
wing group consists of the front and rear spars, leading edge, wing tips, flaps, ailerons, and fuel tanks. wing tips, flaps, and ailerons are readily removable. The forward wing attaching point is located at FS 83.00 while the rear wing attaching point is located at FS 118.00 on all Model 33 and 35 series airplanes. On Model A36 series airplanes, the forward wing attaching point is located at FS 73.00 while the rear wing attaching point is located at FS 108.00. An optional remote compass is located in the left wing tip on all serials except CJ-149 and after.
The
1~22
57-00-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
MAINTENANCE PRACTICES
WINGS
WING TIP REMOVAL
attaching
the
to the
a.
Remove the
b.
Disconnect the electrical leads to the
c.
Disconnect the remote compass at the left
screws
wing tip
wing.
navigation light. wing tip (if installed).
WING TIP INSTALLATION a.
Connect the remote compass at the left
b.
Connect the electrical leads to the
c.
Place the
wing tip
in
position
and
wing tip (if installed).
navigation light.
secure
it to the
wing with
screws.
WING REMOVAL
I
purgethefuelcells.
a.
Drainand
b.
Removethefront seats.
G.
Remove the
rear seat
d.
Remove the
wing mounting
panel. bolt
access
plates
from the top and bottom of the
wing.
airplane on jacks and raise the airplane until the wheels are clear of the ground. Refer to Chapter jacking instructions. A three point jack should be used because of the unbalanced condition of the airthe after plane wing is removed. e.
Place the
7-00-00 for
hydraulic
lines at the
f.
Disconnect and cap
g.
Operate
h.
Disconnect the inboard door actuator rod from the control horn.
i.
Disconnect the
landing
gear
j.
Disconnect the
landing
gear actuator rod from the V-brace in the wheel well.
k.
Disconnect and cap the fuel lines between the
i.
Disconnect and cap the
m.
Disconnect and label electrical
n.
Disconnect and
the
landing
wing
root.
gear switch until the inboard
identify
uplock cable
pitot
gear doors
are
fully
open.
at the inboard connection in the wheel well.
line at the left
wiring
landing
wing
wing
root rib and the
fuselage.
root in the wheel well.
in the wheel well.
the aileron cables at the turnbuckles located inside the cabin, forward of the
rear
spar
below the floorboards. o.
Disconnect the
p.
Cradiethe
q.
Place
Page
a
flap
drive shaft from the motor.
wing.
wing
stand under the
wing
57-00-00
not
being
removed and
place
a
stand under the tail.
nal
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL r.
Outline the
position
of the
wing
on
the
fuselage
guide for reinstallation.
as a
CAUTION t ICAUTION There should be the bolt s.
no bolt binding during removal. Should binding occur, adjust the wing position until disengages freely. Do not screw or drive a bolt in or out of the fittings.
Remove the
mounting nuts,
bolts and washers from the
wing.
WARNING) I WARNING A
bushing
is installed in the lower front spar attach fitting. This bushing should not be wing is removed, and must be in place when the wing is reinstalled.
re-
moved when the
NOTE Discard the
mounting
Discard the
special soft aluminum washer installing the wing.
nuts. Install
new
nuts when
mounting used
on
the
wing
installing upper
the
wing.
mounting
I
bolts. Install
new
alu-
minum washers when t.
Disconnect the cold air flex duct at the
u.
Remove the
wing by pulling
it
straight
wing leading edge.
away from the
fuselage.
REMOVAL OF LEADING EDGE AND MAIN SPAR The
wing must be removed from the airplane before the leading edge or main spar can be removed. Remove the attaching screws at the wing tip and wing butts. Access to the screws at the main spar root is through the wheel well. Pull the hinge pins which attach the leading edge, disconnect the landing gear and remove the main spar. NOTE
Support the landing gear to avoid damaging the aft spargear connection
or remove
the gear at both
connections.
INSTALLA TION OF LEADING EDGE AND MAIN SPAR are to be driven with a rivet gun by supporting the hinge pin in telescoping tube, repair kit 35-588 S. hinge halves are free of metal burrs and mated before attempting to drive the hinge pin. Grind the end of the pin to a point before starting it in the hinge. A second rivet gun or mallet may be used to tap along the upper or lower edge of the main spar to help the pin through the hinge. Use a wooden block as a pad to prevent damage to the spar.
The
hinge pins
Make
sure
the
I CAUTION I Do not attempt to to seize or break.
nnn
spin
the
hinge pin
in with
a
drill motor. Heat and
expansion may
cause
the wire
57-00-00Page
3
RaytheMI Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
~95-110025-1 WASHER [POSITION WITH RADIUS TOWARDS THE WING FITTING)
EB-126
95-110021 WASHER WITH COUNTERSINK BOLT HEAD)
MS20012-20 OR NAS152-37 OR 131790-1 BOLT
NUT
(EXTERNAL WRENCHING)
WING
(POSITION TOWARDS
FITTING
++M520002-12 WASHER DRAIN HO~E
7
FUSELAGE FITTING
105090A032-12K
WASHER
BOLT TOROUE: 2480 TO 2600 INCH-POUNDS. COAT THE COMPLETE BOLT, NUT, WING FITTING BOLT BORES, AND EXPOSED BOLT THREADS WITH MIL-C-16173, GRADE 2 CORROSION PREVENTIVE COMPOUND. WET
WASHER,
CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS. MS20002- 12 WASHERS MAY BE USED AS REOUIRED BETWEEN WASHER TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT.
USED
PRIOR TO CE-928,
CJ-156,
D-10353,
CHART BOLT
AND
95- 1 10025- 1
D-10353
AND
AFTER,
NOTE
NOTE WING
NUT
E-1758 AND EA-150
USED CD-928 AND AFTER, CJ-156 AND AFTER, E-1758 AND AFTER AND EA-150 AND AFTER.
SEE
THE
CONCURRENT WITH THE SCHEDULED TORQUE CHECK, INSPECT THE UPPER WING ATTACH FITTINGS TO ASSURE THAT THE DRAIN HOLES ARE CLEAR.
2 FOR TOOLS
f~´•k12NB126 NUT [INTERNAL WRENCHING)
EA57B
003141A~
Upper Fonnrard Wing Bolt Installation Figure 1
Nov
57-00I00
A22
Raylheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
105090AO32-1OJ
++95-1 10025-7 WASHER CHECK FOR A SMOOTH CDMPLETE RADIUS) POSITION RADIUS TOWARD THE FITTING) 12NB108
35-105111-3 WASHER [POSITION WITH COUNTERSINK TOWARDS BOLT HEAD)
WAS\HER
NUT
NAS150-33/M/ BOLT
WING FITTING
WET
BOLT
WASHERS, C-16173. USED
FUSELAGE FITTING
TORQUE: 1180 TO 1300 INCH-POUNDS. COAT THE COMPLETE BOLT, NUT, WING FITTING BOLT BORES. AND EXPOSED BOLT THREADS WITH MILGRADE 2 CORROSION PREVENTIVE COMPOUND.
PRIOR
TO
CE-935;
CJ-156;
D-10359:
E-1791;
USED CE-935 AND AFTER; CJ-156 AND AFTER: E-1791 AND AFTER; EA-177 AND AFTER.
EA-177.
D-10359
.MS20002- IO WASHER (ONE OR TWO MS20002-IO WASHERS MAY BE USED BETWEEN THE NUT AND THE FITTING TO PROVIDE PROPER BOLT GRIP ADJUSTMENT.
AND
AFTER;
NOTE SEE CHART 2 FOR WING BOLT TOOLS
O NOTE CONCURRENT WITH THE SCHEDULED TOROUE CHECK. INSPECT THE UPPER WING ATTACH FITTINGS TO ENSURE THAT THE DRAIN HOLES ARE UNOBSTRUCTED,
mAinA
Upper Aft Wing Bolt Figure 2
A22
Installation
57-0000
Nov
10/0 Page
5
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE CHART 2 FOR WING BOLT TOOLS SEE
12NB 126 xac** NUT INTERNAL WRENCHING
Q
#TAIL
A
50-105011 WASHER (REPLACES THE MS20002- 12 WASHER ON AIRPLANE SERIALS EA-242, EA-273 AND AFTER)
NOTE:
BUSHING NOT USED EA-273 AND AFTER
MS200 12-31/M/ OR 131790-2 BOLT
EA-242,
rc **~e *a
10094 BUSHING
we 000- 1
WING FITT
MS200 1 4-28 OR 131790-3 BOLT
A
MS20002-12 WASHER 1050 1 1-3
FUSELAGE
WASHER
FITTING
WET BOLT TOROUE: 2480 TO 2600 INCH-POUNDS (ALL SERIALS EXCEPT EA-242. EA-273 AND AFTER), 2800 TO 3000 INCH-POUNDS (EA-242, EA-273 AND AFTER). COAT THE COMPLETE BOLT, NUT, WASHER, WING FITTING BOLT BORES, AND EXPOSED THREADS WITH MIL-C-16173, GRADE 2 CORROSION PREVENTIVE COMPOUND. CHECK
TOWARD
WASHER FOR A BOLT HEAD.
SMOOTH
CONTINUOUS OUTER RADIUS
AND
POSITION
WITH
CE-748, CE-772 AND AFTER: CJ-149 AND AFTER: E-) I I I E-1~41 0-10097, D-10120 AND AFTER; EA-I THRU EA-272 EXCEPT EA-242. USED
arcre WASHER
YJ*C* USED
NOT
PRIOR
USED
UNDER BOLT HEAD EA-242,
TO D-10353;
CE-928;
CJ-156;
EA-273
E-1758;
USED 0-10353 AND AFTER: CE-928 AND AFTER: AFTER; EA-150 THRU EA-272, EXCEPT EA-242. USED
EA-242,
EA-273
AND
RADIUS
AND AFTER:
AFTER.
EA-150.
CJ-156 AND AFTER;
E-1758
AND
AND AFTER. EA57B oOJ142AA
Lower Forward
Wing Figure
Page
6
Nov10/00
57 00 00 I
I
Bolt Installation 3
A22
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
MS20002- IO WASHER (ONE OR TWO MS20002- IO WASHERS MAY BE USED BETWEEN THE NUT AND THE FITTING TO PROVIDE BOLT GRIP
ADJUSTMENT)
#TAIL
´•lc~cgg-110025-7 WASHERS MAY THE FITTING
A
WASHER (ONE OR TWD 95-110025-7 BE USED BETWEEN THE NUT AND TO PROVIDE BOLT GRIP ADJUSTMENT) 35-105111-3 WASHER (POSITION WITH COUNTERSINK TOWARDS BOLT
HEAD)
Al)
NAS150-35/M/BOLT
12NB108
NOTE SEE CHART WING BOLT
WET
BOLT
WASHERS, C-16173,
’Ic
NUT
(CHECK FOR
2 FOR TOOLS
A
SMOOTH
COMPLETE
RADIUS)(POSITION RADIUS TOWARD FITTING AS SHOWN)
COAT THE COMPLETE BOLT, NUT, TORQUE: 1180 TO 1300 INCH-POUNDS. WING FITTING BOLT BORES, AND EXPOSED BOLT THREADS WITH MILGRADE 2 CORROSION PREVENTIVE COMPOUND. TO CE-935:
D-10359;
E-1791;
USED
PRIOR
USED
CE-935 AND AFTER: CJ-156 AND AFTER; EA-177 AND AFTER.
CJ-156;
EA-177.
D-10359
AND AFTER;
E-1791
AND
AFTER;
EA578 00J143AA
Lower Aft
A22
Wing Bolt Installation Figure 4
57-00-00
Nov
10/0 Page
7
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
WING INSTALLATION
NOTE
replacing wing bolts make sure that the replacement bolts have been properly inspected using the magnetic particle process. Bolts must be magnetically inspected before installation as wing bolts. Bolts may be acquired through Raytheon Aircraft Parts Inventory and Distribution (RAPID). The individual placing the order must stipulate the need to have the bolts inspected before shipment. When
Using a nonmetallic brush and solvent (26 or 31, Chart 1, 91-00-00), clean all wing attach fittings and hardware (bolts, washers, and nuts). Inspect the wing attach fittings, bolts, washers, and nuts as instructed under WING BOLT, NUT, AND FITTING INSPECTION.
a.
WARNING IWARNINQ)
Wing
bolts that have reached their life limit
reused. The b.
(5,
mounting
Coat the
Chart 1,
fitting bolt 91-00-00).
nuts must be
bores and
~10 years after the initial inspection) replaced at each inspection interval.
bearing faces, bolts, washers,
and nuts with corrosion
must not be
preventive compound
WARIIIING I I WARNING The
bushing
lation of the c.
Move the
wing
installed in the lower forward spar attach attach bolts.
fitting
must be in
place prior to
instal-
wing
into
position, align
the
wing fittings
with the
carry-through fittings,
and insert the bolts.
CAUTION I I cnuTloa Each bolt must be inserted
by hand without binding. If a bolt cannot be easily inserted, reposition freely through fittings. Do not drive or screw bolt into the fittings. Bolts and nuts must be oriented as shown in applicable illustration for each location (Figure i, 2, 3, and 4). the
d.
until the bolt
on
the
bore. If bolt
Tighten
moves
the upper forward and aft bolts. Rotate the wing trailing edge until the wing is aligned with the fuselage. After alignment is established, verify that the lower forward bolt is not binding in the bolt
Start the nuts
outline
e.
wing
on
binding
is encountered,
adjust the wing position
until the bolt
moves
freely.
the upper forward and aft nuts.
CAUTION I cnuTloNI When
torquing wing nuts,
assure
could
that the wrenches do not bottom out
on
wing
attach
fittings.
Such
cause false torque readings and damage to fittings. After torquing the upper an occurrence forward wing attach nut, remove the holding force from the wing cradle and torque the remaining
three nuts.
Page
857-00-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL f.
Torque the nuts in the following order: upper fonnrard, adapter is used, the length of the adapter must be torque value computed as detailed in Chapter 20-00-00. wrench
upper aft, lower forward, and lower aft. When a torque added to the length of the torque wrench and the proper
CAUIION I I CAUTION Before the lower aft nut is
torqued,
a
slight gap may be evident between the fittings. This gap should torqued. Torque the wing attach
not exceed 0.060 in width. No gap should remain after the nut is bolts at the nut end, do not rotate the bolt in the bolt bore.
Coat the bolt threads that
g.
protrude through the
h.
Connect the cold air duct at the
i.
Connect the
j.
Connect the aileron cables at the turnbuckles.
k.
Connect the electrical
i.
Connect the
m.
Connect the fuel lines.
n.
Connectthe
landing gearactuator
o.
Connect the
landing
p.
Connect the inboard door actuator rod.
q.
Connect the
pitot
wiring
flap
hydraulic
At the first scheduled
Check the drain ports to
Chart 1,
91-00-00).
motor.
in the wheel well.
line in the wheel well
gear
preventive compound (5,
wing leading edge.
shaft to the
flap drive
nut with corrosion
uplock
(LH only).
rod.
cable.
brake lines and bleed the brakes.
inspection
assure
that
after the
wing
they
unobstructed.
are
has been
installed, check the attaching bolts for proper torque.
ADJUSTING THE WINGS After the
wing has been installed or repaired, flight tests may show the wing to be chronically heavy or light. This condition may be corrected by rotating the wing to lower the trailing edge of a heavy wing or raise the trailing edge of a light wing or by a combination of adjusting both wings. The aluminum washers between the upper wing fittings
replaced each time the position of the wing is changed. If both wings have been removed, install the right wing trailing edge at the highest point of the adjustment travel and the left wing 1/16 inch down from the of travel. The total adjustment on each wing is approximately 1/8 inch. The following steps should be highest point when implemented adjusting the wings: must be
with the
a.
Using
b.
Place the
a
grease
airplane
instructions. Place stand will also be
nan
pencil,
a
on a
outline the three
position
point jack
to
assure
wing
on
the
fuselage.
and raise until the wheels
suitable cradle under the
required
of the
wing being adjusted
are
and
a
clear. Refer to
wing
Chapter 7-00-00 for jacking opposite wing. A tail
stand under the
stability.
57-00-00Page
9
Ral~heon Aircraft SEECH BONANZA SERIES MAINTENANCE MANUAL on the lower wing attach bolts and remove the bolts and nuts from the upper wing attach fittings. bearing faces and bolt bores of the fittings, the complete bolt, washers, and nut with corrosion preventive compound (5, Chart 1, 91-00-00). Install new soft aluminum washers between the upper wing attach fittings. Install the bolts, washers, and nuts into the fittings. Raise or lower the trailing edge as required and torque the wing attach nuts in the following order: upper forward, upper aft, lower forward, and lower aft. There should be no gap between the fittings after the last nut is torqued. Torque each nut to the wet torque value shown in the appropriate illustration (Figure 1, 2, 3, and 4). Coat the exposed threads that protrude through the nuts with corrosion preventive compound (5, Chart 1, 91-00-00). c.
Loosen the nuts
Coat the
NOTE After torquing the upper forward wing attach nut, to torquing the remaining three nuts. d.
Remove the
e.
At the first scheduled
wing
and tail stands,
drain ports in the upper
remove
the
remove
airplane
the
from the
holding
jack,
force from the
and test
wing cradle prior
fly the airplane.
inspection after the wing has been adjusted, check for correct wing wing attach fittings to assure that they are unobstructed.
bolt torque. Check the
WING BOLT, NUT, AND FITTING INSPECTION
NOTE Read the entire section before
removing
any
wing bolts.
WARNING I I wnANINa The
wing
bolts installed in the Bonanza series
airplanes five years old or older must be reIf the bolts prove to be free of all damage, they may be reinstalled for an additional five year period. At the end of this period the bolts must again be removed and inspected. Ten years after the initial inspection, all wing bolts must be replaced with new moved and
inspected.
hardware. The
mounting
nuts must be
replaced
at each
inspection interval. Render warning. See Chart 1 for
viceable all components removed in compliance with this spection and replacement cycle of the wing bolts. a.
Before
bolt
binding position.
unser-
the in-
any wing bolt, draw an outline of the wing position on the fuselage with a grease pencil. If wing is encountered and the wing must be shifted, the outline will be helpful in returning the wing to its original
removing
CAUTION I i cnuTlou There should be
wing bolt binding during removal or installation of bolts. Do not screw or drive fittings. If wing bolt binding is encountered, place the airplane on a three point raise until and the wheels are clear (see Chapter 7-00-00 forjacking instructions). Place a wing jack stand under each wing and a tail stand under the aft fuselage. Defuel the wing, loosen the remaining three bolts and rotate the wing until the binding bolt moves freely through the fittings. Replace the soft aluminum washers between the upper wing attach fittings and torque the bolts as instructed under WING INSTALLATION. If bolt binding is not encountered and the wing has not shifted, replacement of soft aluminum washers between the upper wing attach fittings is not required. a
page
bolt in
or
no
out of the
1057-00-00
Ral~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOTE
Raytheon Aircraft Company supplies wing attach hardware that netic particle inspection since manufacture. These components on the head of the bolt and on some portion of the nut.
has been
given
additional magby the green dye
I
an
may be identified
WARNING Iwnrt~lrsl Use
only
the components
specified
in the
applicable
illustrations. DO NOT INSTALL THE
BLACK P/N H-20 NUTS, these nuts have been dry film lubricated with molybdenum disulfide. When MlL-C-16173 Grade II corrosion preventive compound is added to these nuts, the additional lubrication may
cause
improper preload
in the bolt when it is
b. Starting at the lower wing attach point on each side, remove, inspect, complete set of eight bolts and nuts have been inspected. c.
Using
a
nonmetallic brush,
thoroughly clean the bolt,
torqued.
and torque
one
washers and nut with solvent
(26
bolt at
or
a
time until the
31, Chart 1, 91-00-00).
CAUTION I I cnvnon
(Figure 1), the 50- 105011 (Figure 3), and the 95- 110025-7 (Figure 2 complete radius with no sharp edges that could damage the wing fittings.
Assure that the 95- 110025-1 and d.
4)
washers have
a
If the bolts and nuts do not exceed the life limit shown in Chart
1,visually inspect
each bolt and nut with
a
10-
stronger magnifying glass; inspect for corrosion, cracks, and mechanical damage. The cadmium plating power may display areas that appear rubbed, discolored, or polished. These areas are usually the result of prevailing inor
stallation
procedures and
are
of
no
significance.
A bolt should not be
ration; however, any component that is cracked, corroded e.
or
rejected
has mechanical
plating deterioreplaced.
because of cadmium
damage
must be
Using the magnetic particle inspection process described in this chapter, check each
nut for
longitudinal
indications and each bolt for circumferential crack indications. If the bolts and nuts prove to be free of all (corrosion, cracks, and mechanical damage), they may be reused after demagnetization and cleaning.
crack
damage
Clean the spar fitting bolt bores with naphtha or methyl ethyl ketone (26 or 31, Chart 1, 91-00-00). Do not strip the epoxy paint from this area. Inspect the surface condition of each fitting; focus special attention on the washer seat and bolt bore area. If scoring, corrosion pitting or washer impressions are discovered in this area, contact the f.
Department of Beech Aircraft Corporation. If the fitting is satisfactory, coat the bolt bore and fitting with Alodine 1200, 1200S or 1201 (53, Chart 1, 91-00-00). Allow the coating to remain on the surface for approximately five minutes. When the time has elapsed, wash the coated areas with water and blow dry (do not wipe dry). Paint the treated areas with zinc chromate primer (20. Chart 1, 91-00-00) and allow to dry. Commercial Service
bearing
g.
faces of the
Coat the
bearing
faces and bolt bores of the
preventive compound (5,
nz2
Chart 1,
fittings,
the
complete bolt, washers,
and nut with corrosion
91-00-00).
57-00-00
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL h.
Install the bolt washers, and nut into the
fitting.
CAUTION I I cnlmoa
wing bolt wrenches do not bottom out on the fittings when torquing damage to the wing fittings and erroneous torque readings.
Ensure that the could result in
the nut This
Torque the nut to the wet torque value shown in the appropriate illustration (Figure 1, 2, 3, and 4). When a torque adapter is used, the length of the adapter must be added to the length of the torque wrench and the proper value computed as detailed in Chapter 20-00-00. torque i.
wrench
Coat the exposed threads j. (5, Chart 1, 91-00-00).
that
Check that the decal shown in
k. sion
preventive compound
protrude through the
nut with corrosion
preventive compound
Figure 5 is affixed to the appropriate locations on the airplane. When applied to the wing bolts, affix the decal to the following locations:
the
corro-
has been
above the RH forward and aft
1.
On the side of the
2.
On the
wing immediately forward
3.
On the
wing immediately
forward of the lower forward
4.
On the
wing immediately
aft of the lower aft
fuselage immediately
i.
Check the drain ports in the upper
m.
At the first scheduled
inspection
of the ~H forward and aft wing bolt
wing
attach
after the
wing
wing
bolt
fittings
to
wing
bolt
bolts have been
that
covers.
covers.
covers on
covers on
ensure
wing bolt
both sides.
both sides.
they
inspected
unobstructed and free to drain.
are
or
replaced,
check for proper bolt
torque.
CHART1 WING BOLT AND NUT INSPECTION AND REPLACEMENT CYCLE
NEW
5 years
AIRPLANE
initial
5 years second
inspection
inspection
5 years
initial
(airplanes
I
NOTE: At each At each
Page
second
inspection 5 years old
or
older)
inspection
5 years
5 years
firstreplacement
repeat inspectionand
interval
replacement cycle
5 years
5 years
first replacement
repeat inspection and
interval
replacement cycle
inspection interval, the nuts must be replaced. replacement interval, all wing attach hardware (bolts, washers,
1257-00-00
and
nuts)
must be
replaced.
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHART2 WING BOLT WRENCHES AND TORQUE ADAPTERS POSITION
BOLT PART
WRENCH
NUMBER
PARTNUMBER
UPPER
NA1 52-37
TS1 222-3
FORWARD
or
NUT PART NUMBER
12NB-126
(PriortoCE-928,
CJ-156, D-10353,
MS20012-20 or
131790-1
LOWER
MS20012-31
FORWAR D
or
(CE-748,
CE-722 and after; CJ-149 and after;
iS1171-2, TS1176-2
TS1222-5, 50-590012, TS1222-4,
E-1758 and
and after,
TS1176-10,
TS1222-8
CJ-156 and after, D-10353 and after, E-1758 and after,
TS1171-10
EB-126
TS1222-5, 50-59001 2, TS1222-4,
EA-150)
(CE-928
EA-150 and
131790-2
NUT TORQUE ADAPTER
12NB-126
after)
(Priorto CE-928,
CJ-1 56, D-l 0353, E-1758 and
TS1171-2, TS1 1 76-2
EA-150)
TS1222-8 EB-126
(CE-928
and after,
TS1176-10,
E-llll, E-1241 and after; D-10097, D-10120 and after;
CJ-156 and after, D-10353 and after, E-1758 and after,
TS1171-10
EA-1 thru EA-272
EA-242)
EA-150 thru EA-272 except
except EA-242) MS20014-28 131790-3
EA273 and UPPER AFT
or
TS1222-3
EB-144
or
(EA-242,
(EA-242,
ZEB1845-144
EA-273 and
50-590014
after)
after)
NAS 150-33/M/
50-590012,
12NB-108
50-590013,
TS1 222-5,
TS1171-1,
TS1 222-4,
TS1176-1
TS1222-8 LOWER AFT
NAS150-35/M1
50-590012,
12NB-108
50-590013,
TS1 222-5,
TS1171-1,
TS1 222-4,
TS1176-1
TS1 222-8
A22
57-00-00
Nov
10/ 0Page
13
Raynheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
NOfICE WING BOLTS ARE LUBRICATED SEE MAINTENANCE MANUAL FOR CORRECT TORQUE VALUES
WHEN THE CORROSION PREVENTIVE COMPOUND AFFIX THE ABOVE DECAL TO THE FOLLOWING I.
ON
THE
OF
SIDE
THE
FUSELAGE
HAS BEEN APPLIED LOCATIONS:
IMMEDIATELY ABOVE
2.
ON
THE
WING
IMMEDIATELY
FORWARD
OF
THE
LH
3.
ON
THE
WING
IMMEDIATELY
FORWARD
OF
THE
LOWER
4.
ON
THE
WING
IMMEDIATELY
AFT
DF
THE
LOWER
THE
THE
RH FORWARD
FORWARD
AFT
TO
WING
AND
BOLTS.
AFI
WING
AFT
WING
BOLT
BOLT
COVERS
BOLT
COVERS
ON
BOLT
COVEF
COVERS.
WING
AND
FORWARD
WING
BOTH
ON
BOTH
SIDE
SIDES. THI IB 992996)
Lubrication Bolt Identification Placard
Figure
5
MAGNETIC-PARTICLE INSPECTION locating surface and subsurface discontinuities in ferromagnetic mate(i.e. capable being magnetized); consequently, nonferromagnetic materials (such as aluminum alloys, magnesium alloys, copper alloys, lead, titanium alloys, pickle base alloys and many stainless steel alloys) cannot be inspected by this method. Magnetic-Particle Inspection is based upon the principle that any discontinuities lying in a direction generally transverse to the direction of the magnetic field of the part magnetized for the test will cause a leakage field to be formed at and above the surface of the part. The presence of the leakage field denoting the discontinuity is detected by the use of finely divided ferromagnetic particles over the surface of the part. Some of the particles are magnetically gathered and held by the leakage field to form an outline indicating the location, size, shape and extent of the discontinuity. In general, magnetic particle inspection utilizes a variety of types of equipment for magnetization as well as several methods for application of ferromagnetic particles to the test part. Additionally, the ferromagnetic particles are available in a selection of colors (including fluorescent) and particle shapes. Magnetic particle inspections required by this manual can best be accomplished utilizing the "wet continuous method" on the standard wet horizontal type equipment with either visible or fluorescent magnetic particles suspended in a petroleum base vehicle (normally kerosene). Since magnetic particle indications are best obtained when the discontinuity lies in a direction transverse to the magnetic field, the following procedures are recommended for optimum detection of discontinuities in both bolts and nuts. Magnetic-Particle Inspection materials
rials
is
a
method for
of
WARNING
Improper operation of the particle inspection, because of faulty equipment or untrained operators, can jeopardize the ainnrorthiness of parts being tested. Minute electrical are burns caused during inspection by improper operation of the test equipment can result in eventual failure of the part.
Page
voN41
10100
57-00-00
A22
Ray~heon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
accomplished by longitudinal magnetization in a multiturn low-fill factor coil (i.e. the inner diameter). For proper magnetization the bolt is positioned close to the coil inside wall with the bolt length perpendicular to the winding direction. The magnetic particle suspension is flowed on the bolt and the appropriate current is applied to achieve adequate field strength. Using the described procedure, laboratory testing has indicated that the ampere turn values listed in Chart 3 provide for optimum detection of discontinuities perpendicular to the bolt axis. Bolts:
Inspection
of
diameter of the coil
a
bolt is
greatly
exceeds the bolt
Inspection of a nut is accomplished by circular magnetization on a central conductor (usually a copper rod) approximate size of the nut inside diameter. For proper magnetization, the central conductor bar is inserted through the nut and the bar is positioned between the heads of the wet horizontal equipment. The magnetic particle suspension is flowed on the nut and the appropriate current is applied through the central conductor to achieve adequate field strength. Using the described procedure, laboratory testing has indicated that the amperage values listed in Chart 4 provide for optimum detection of discontinuities parallel to the nut axis. Nuts:
the
magnetic particle inspection, the parts must be carefully demagnetized and cleaned of the ferromagnetic particles. Examine parts for any possible evidence of electric are burn that may have occurred during the inspection. After
CHART 3
MAGNETIC-PARTICLE INSPECTION
(STEEL BOLTS) TOTAL BOLT LENGTH INCLUDING
AMPERE
HEAD TO NEAREST 1/4 INCH
TURNS"
5/8 INCH
21/2 INCH
7900
5/8 INCH
23/4 INCH
7100
5/8 INCH
3
INCH
6600
3/4 INCH
3
INCH
7900
3/4 INCH
31/41NCH
7400
3/4 INCH
31/2 INCH
6700
3/4 INCH
33/4 INCH
6300
7/8 INCH
31/2 INCH
7900
7/8 INCH
33/4 INCH
7400
718 INCH
4
INCH
6900
7/8 INCH
5
INCH
5500
1 INCH
5
INCH
6300
BOLT DIAMETER
Amperage requirement is the ampere turns value divided by the number of turns example: A i-inch diameter x &inch long bolt tested on a 5-turn coil 6300 5, or 1260 amps. require
the coil. For
A22
on
would
57-00-00
Nov
10/00Pagel5
Raytheon Aircraft BEECH BONANZA SERIES MAINTENANCE MANUAL
CHART4 MAGNETIC-PARTICLE INSPECTION
(STEEL NUTS) NUT SIZE
AMPERAGE
CENTRAL CONDUCTOR SIZE
5/8 INCH
112 INCH
500 AMPS
314 INCH
5/8 INCH
600 AMPS
7/8 INCH
314 INCH
700 AMPS
1 INCH
7/8 INCH
800 AMPS
OUTBOARD WING R/IAIN SPAR CAP INSPECTION The outboard
wing main
spar cap must be
inspected annually
for corrosion.
WARNIIJG JWARNIIGL of the spar cap from the wing attach
All
areas
be
inspected.
fitting to the outboard end of the spar cap
must
NOTE Special emphasis should be placed on airplanes that have been operated or stored for extended periods (5 years or longer) where geographical locations or atmospheric conditions are highly conducive to corrosion.
Inspection
of the upper and lower spar cap should be
accomplished in the following
manner:
Examine the forward and aft sides of the spar cap where it meets the skin. If a whitish, salt-like, nonmetallic substance is noted in these areas, a thorough inspection should be performed to determine if corrosion has occurred. Wax or paint trapped between the edge of the skin and the exposed section of the spar cap should not be a.
misinterpreted
as
corrosion.
b.
Wash all
c.
Visually inspect
exposed all
areas
of the upper and lower spar cap.
exposed
areas
an
of the upper and lower spar caps for irregularities, such as paint blisters, exposed areas of the spar cap are extruded flat and irregularities could be
or uneven areas, and cracks. The indication of corrosion. Investigate all
raised
irregularities
to determine if any
damage
has occurred.
NOTE Uneven
or
by moving
raised a
If unusual conditions
straight edge are
the spar caps may be detected by sliding the fingers over the surface, over the surface or by sighting down the length of the par cap surface.
areas on
encountered that cannot be resolved
locally, contact Raytheon required.
for evaluation and determination of corrective action that may be
Nov
57-00-00
Aircraft Technical
Support
BEECHCRAFT BONANZA SERIES MAINTENANCE I~ANUAL
LEFT WING
ua~t3-
WINGS
TOP VIEW
RIGHT WING
WING TIP (EA-242, EA-273 AND AFTER.)
10
9
~I 11
PLATE SKIN
1
6
WINGS
Q
´•~IY
WING TIP (EA-242. EA-273 AND AFTER.) LEFT WING
MAINTENANCE PRACTICES
1.
Upper fuel cell and transmiiter
2.
Upper forward wing attach bolt
3.
Upper
4.
Optional
5.
Lower fuel cell
wing
6
BOTTOM VIEW
atom WING
WING ACCESS OPENINGS
aft
-----1-
access
attach bolt
remote compass
(Except CJ-149 and after)
6.
Flap
7.
Lower forward
8,
Lower aft
9.
Aileron bell crank
11
381514
actuator access
wing
wing
attach bolt
attach bolt
access
(EA-242, EA-273 and after)
10,
Fuel drain
11.
Fuel vent float valve, flame arrestor, vent and vacuum
refill valve
(EA-242, EA-273 and after)
access
Wing Access Openings Figure 1
51-30´•00
Page A4
1
Jan 20/82
BEECHORAFT BONANZA SERIES MAINTENANCE MANUAL
5 ~9
5
5
8
1
5
"9--r~ 5
g
8
-I-
LH UPPER
3
5
5
1
2
5
5
2
6
3
i
I
B
4
RH UPPER
5
1
5
3
4
6
RH LOWER
4
i
4
j
j
5
1
*FILLET USED ONLY ON SERIALS D10097.
1
4
f j
5
8
LH LOWER
0-10120 AND AFTER
13
NUMBER
MATERIAL
THICKNESS IN INCHES
1
2024-T
.016
2
2024-T3
.016
3
2024-T3
.020
4
2024´•T3
.025
5
2024-T3
.032
6
6061-T6
.016
7
6061-T6
.020
10
11.12
9
6061-T6 6061-0
i ~511
WING TIP EA-242, EA-273 AND AFTER
NUMBER
8
1
THICKNESS IN INCHES
6061-0
.032
11
UPPER 12 LOWER
2024-T3 2024-T3
.025
13
2024-T3
.020
10 t
.032
MATERIAL
020
.032 t HEAT TREAT TO T6 CONDITION 3C12-10
*Fil/ets used only on~serialsD-10097,
0-10120 and after.
Wing Skin Thickness Figure 2 "END" 57-30-00
Rage
2
Jan 20/82
A4
BEECHCRAFf BONANZA SERIES MAINTENANCE MANUAL
ATTACH FITTINGS
MAINTENANCE PRACTICES
major fittings in each wing are the supporting structures adjacent to the attachment points for the flap actuator, flap tracks and flap, aileron hinge brackets and hinges, main The
landing gear support brace and landing gear doors. Minor fittings include brackets to support cable pulleys, bell cranks, and similar components. If the landing gear hinge bolt fittings are cracked or ii the spar is warped or buckled, replacement is necessary.
"END"
57-40-00
Page 1 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CONTROL MAINTENANCE PRACTICES
BALANCING
SURFACES
BALANCING PROCEDURE COUNTERBALANCING METHOD
BALANCING THE AILERON
(Figure I)
tocate the chord line
by placing a straight edge at assembly so that one end is on other end is centered on the leading
a.
the inboard end of the aileron When the aileron control surface is it
the
by trailing edge leading edge. After
so
being repainted, suspend paint will drain toward repainting or repair, the finished
that excess
the
any surface must be check balanced to
ensure
that its static
hinge line is within the prescribed limits, The painted and primed aileron assembly must be noseheavy by 0.2 to 1.5 inch-pounds. The static moment of the 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 moment about the
and the distance in inches. The static moment of
percent balanced control surface is
0.0
a
100
inch-pounds. A
tail-heavy surface exhibits static underbalance. heavy surface exhibits static overbalance,
A
nose-
the
trailing edge and the edge. Mark the chord line with a suitable marker, such as a grease pencil, then remove the straight edge. Fit the correct size bolts in the hinge brackets and b. mount the aileron on the knife edge supports. Ascertain that the aileron is free to rotate about the hinge line. To determine if weight should be added or c. removed, suspend a paper cup from a point near the center of the aileron trailing edge. Use a short length of small diameter string secured to the surface with a small piece of masking tape: as illustrated in Figure 1.The cup must be free to hang vertically. d. Add small quantities of lead shot to the cup until the aileron balances with the chord line level. Check this by
holding
spirit
the
e.
level
hinge line. Measure point of the cup.
CHECKING BAL9NCE
f. The aileron balance must be checked in
a
draft free
area
with
completely assembled in flying condition. All painting, including stripes and touch-up, must be completed. The tab, 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:
aligned
with the marked chord line.
The distance "D" must be "D" from the
perpendicular to the hinge line to the suspension
Remove the cup, contents, and
string,
then
weigh
them.
the aileron
a.
force
or
Counterbalancing weight at a measured
b.
must be done
the aileron surface
single support line of the hinge.
known distance from the center
g.
on a
at
a
Caculate the static balance 1.
designated by 2.
designated by 3.
EQUIPMENT REQUIRED TO PERFORM CHECK BALANCING a.
Figure plane.
A stand with knife 1. The knife
edges
edge supports
must be in the
illustrated in
as
same
horizontal
The
as
follows:
of the cup and contents is
weight
"W".
The
over
or
underbalance
moment
is
"M". M=WxD
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 .150 pound" and "D 10.0 inches", 4.
The
then...
b.
A paper cup
c.
Approximately
d.
A
certified
or
A
1
light weight
similar
pound
beam
calibrated in units of .01 a.
carefully on scales that are certifed
for accuracy.
Measurement of the
Actual Force Measurement
applied by
Since any weighing error is magnified by the distance "D", weighing is most important and
The
distance from the
counter the unbalance moment
force
application of a known hinge line to of the aileron assembly.
NOTE
of lead shot.
balance
pound straight edge, ruler,
container.
or
weighing
less.
and
spirit
level.
M device
.150
x
10.0
inch-pounds. The product of "W x D". In this instance, "M" is within the required static balance range and is therefore acceptable. M
1.50
57-50-00
Pager May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
A
c";
~c-
A
a
KNIFE EDGE
STEEL TUBE WITH PIG LEAD D
-I
MASKING TAPE
(PLACE NEAR AILERON HINGE LINE)
~10 MUST BE HORIZONTALLY LEVEL
VIEW
A-A
CONTAINER
DETAIL
.B 38151-1A
Balancing the Aileron Figure 1
57-50-00
Page2 May 9/80
BEECHCRAFT
BONANZA SERIES MAINtENANCE,MANUAL
h. the
hinge
gravity of the aileron is forward on causing the surface to be nose-heavy. balance is obtained by adding or removing leading edge of the aiieron. The rod is 15/32
The center of
would be installed at the center brackets.
center line
Proper aileron lead rod at the
CAUTION
inch diameter and is installed in brackets attached to the
When
leading edge of the aiieron. When adding additional lead rod the maximum total of the length of the rod to be added is not to exceed 5 inches over the entire length of the aiieron and
balance, it must be installed securely with rivets. A
a
lead rod is added to obtain correct
loosely installed rod will vibrate and
an
may cause undersirable vibration of the surface.
"END"
57-50-00
Page 3 May 9/80
CHAPTER
PROPELLERS/
PROPU LSORS
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 61 LIST OF PAGE EFF=ECTIWN
CHAPTER SECTION DATE
PAGE
SUBJECT
´•Oct 7/83
1
61-EFFECTIVIT//CONTENTS 61-10-00
61-20-00
CHAPTER 61
1
´•Jan 20/82
2
................Oct 7/83
1
May 9/80
PROPELLERS
TABLE OF CONTENTS CHAPTER SECTION SUBJECT
SUBJECT
PAGE
.61-10-00
PROPELLER
Description and Operation.....~ Propellers
........f
Maintenance Practices
........1
........1 ........f
Propeller Removal Propeller Installation Propeller Adjustment. Minor Propeller Repair
........1 ........1 ........2 .61-20-00
CONTRO\-UNG
....,...1
Maintenance Practices
........1
Propeller Governor Removal Propeller Governor Installation Propeller Governor Adjustment High RPM Adjustment
........1 ........1 ........1
"END"
61 -EFFECTIVTTY/CO NTENTS
Pag´•l Oct 7/83
BEECHCRAR BONANZA SERIES MAINTENANCE MANUAL
PROPELLER
DESCRIPTION AND OPERATION
NOTE
PROPELLERS
When to
The Bonanza airplanes are blade Hartzell or McCauley
following
equipped propeller
with as
a
two or three
propeller deice is installed, it is necessary tape the brushes in place before the propeller
is removed.
indicated in the
chart. Place a drain trough under the attaching point of b. propeller to the crankshaft, to prevent oil draining into the engine cowl. Remove the propeller from the engine crankshaft c. flange. d. Vse clean shop rags to plug the center of the engine crankshaft and the propeller hub. the
McCauley
Hartzell
CE-748, CE-772 through CE-912, CE-917, CE-919,
CE-913
CE-978 and after.
CE-9T7.
through CE-916, CE-918, CE-920 through
D-10097, D-10120
D110350
through D-10349,
0-10382.
through PROPELLER INSTALLA 7/ON
0-10383 and after.
E-iil, E-1241 through E-1715, E-1932 and
E-1716, through
NOTE
E-1931. Before installation of the
after.
"O"
I
EA-1
EA-105
through
EA-107, EA-108, EA-110, EA-118, EA-242, EA-273 and after,
EA-106, EA-109, EA-11I
the
through EA-117, EA-119 through EA-241, EA-243 through EA-272.
oo-oo). a.
T/C mark
single-acting propellers in which the centrifugal twisting moment of the rotating blades is opposed by hydraulic pressure in the cylinder land spring force in the McCauley propellers) to obtain the correct pitch for the engine load. Govemor (engine driven) controls the amount and pressure of oil passing through the propeller shaft to the power piston in the propeller hub. An increase in engine power output causes oil to enter the piston, thus increasing propeller pitch. A decrease in engine power output results in oil leaving the piston, thus decreasing pitch. These
units
ring that propeller
propeller, lubricate the
is installed in the circular groove of hub with engine oil (2, Chart i, 91-
Place the No. 1 propeller blade on the crankshaft flange.
directly
over
the
are
NOTE Due to the close tolerance fit of the prop hub pilot on the crankshaft, the hub must
bore to the be
placed square on the engine shaft evenly to the crankshaft flange.
and
seated
b. Snug the six propeller attach nuts down evenly in diagonal pattern. Torque the attach bolts in a diagonal 5 foot-pounds for McCauley propellers, and pattem to 60 70 to 80 fed-pounds on Hartzell propellers;safety wire a
-e
PROPELLER
MAINTENANCE PRACTICES
PROPELLER REMOVAL
.tlobeht
It may be necessary to check the alignment of the c. deicer brushes to the slip ring as noted in Chapter 30-60-00. d.
Check the prop blade track after installation.
WARNING
possible injury, ansure thatthe ignition position before working on propeller.
To avoid
switch is in the OFF the
a.
studs
flange.
propeller attach nuts from the propeller to the engine cranks~haft
Remove the six
attaching
the
PROPELLER AD~USTiWENT For adjustments, service, overhaul and maintenance procedures, refer to the applicable FAA Approved Propeller Manual and or Approved Propeller Overhaul Shop Manual. All pitch measurements are made at the 30 inch station and are as
follows:
61-10´•00
Page A4
3an
1
20/82
I
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL ri:´•:´•~
i’
SECTION A-A Minor
McCauley
High
Low Pitch
STD´•249-3
Propeller Blade Repair Figure 1 shown in
Pitch
Figure 1. Reanodize only.
reworked
area
by the chromic
acid process
F33C, V35B
2 Blade
The diameter
2A36C23 Hub
29.7"r.5´
13.30+´•.20
848-0 Blades
propellers
specifications
are as
following
chart:
McCauley
F33A, V35B, A36
3 Blade
for the two and three blade
indicated in the
3A32C406 X Hub
29.0"t.50
13.3"-.2"
X 82NDB-2 Blades
f33C,
3 Blade
29.00~.50
13.30-c.20
82NB-2 Blades
A36TC
3A32C76-U Hub
34.50-.10"
15.0´~.2´
82NB-2 Blades
Min
80
78’/2
80
78’/2
3A32C76U/82NB-2
80
781/2
3A32C406 X/ 82NDB-4
78
77
D3A32C409 X 182NnB-2
80
79
Max
Min
84
82
Max
Min
80
78
B36TC
3A32C406 X Hub
34.9´-.5´
15.8´r.2´
X 82NDB-4 Blades
2 Blade
A36
3A32C409-X Hub 82NDB-2 Blades
Max
3A32C406 X /82NDB-2 3A32C76/82NB-2
V35B
3A32C76 Hub
13.70
r
.20
28.8´
1
.5´
2A36C23/848-0 HARTZELL
F33A, V35B, A36
Harttell
PHC9YF1RF Hub F8468A-6R Blades
12.00
.20
.1"
3 Blade
A36TC
PHC-3YF-1RF Hub F8468A-6R Blades
33.00
13.00,.29
36.0"-1.0~
PHC-3YF-1 RF/F8468A-6R
MINOR PROPELLER REPAIR
If shortening of the propeller is necessary for repair, care should be taken that the blades are not shortened to a
(Figure I) Minor nicks, dents, and gouges may be dressed out by qualified personnel only. Blend any nicks or gouges into the
leading edge
with smooth
curves
and generous radii
as
length less than the shortening a propeller must be shortened
identical
specified. When repair the tip(s) all of the blades equal amount and the tips have
minimum amount to
an
shapes.
"END"
61-10-00
Page2 Oct7/83
A6
BEECHCRAFT BONANZA SERIES MAINIENANCE MANUAL
CONTROLLING
MAINTENANCE PRACTICES
facing
into the
PROPELLER GOVERNOR REMOVAL
the
pad d.
the
engine cowling.
a
Open
b.
Disconnect the control rod end at the governor
body of
Remove the
c.
engine pad
and
wipe
engine pad
and
clean.
Reinstall the govemor
secure
with the four
to 220
inch-pounds.
control lever.
the governor. from the
cover
mounting
on
nuts.
the
Torque the
nuts to 180
a.
Reconnect the control rod to the governor lever.
i.
Close the
engine cowling.
NOTE
PROPELLER GOVERNOR ADJUSTMEM Care should be taken not to loosen the on
jam
nut
the control rod end which could alter the
Remove the four mounting nuts and the engine. from governor d. Cover the governor base and engine c.
propeller governor can be adjusted for a high rpm setting. The high rpm adjustment must be checked while the airplane is in flight. For instructions on adjustment of the low rpm setting, refer to IDLE SPEED AND MIXTURE ADJUSTMENT, Chapter 71-00-00. The
setting of the control rod,
the
pull pad
HIGH RPM ADJUSTMENT
to
protect them.
high rpm adjustment must be checked while the airplane is in flight. Observe the take-off rpm to see ii it exceeds the redline figure. If excessive rpm is observed, adjust the high rpm screw inward to reduce the rpm. The propeller govemor adjustment screw is located on the governor, facing outward from the engine. One complete revolution of the screw reduces the propeller rpm by approximately 25-30 revolutions.
The
PROPELLER GOVERNOR INSTALLATION a
wipe
Remove the
cover
from
the governor base
and
the base clean,
b. governor,
Install
a
ensun’ng
new
gasket on the protruding gasket screen is
governor mounting
that the
"END"
61-20-00
Page 1 May 9/80
C H A PT E R
POVVERP LANT
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 71
POWER PLANT
TABLE OF CONTENTS SUBJECT
CHAPTER
PAGE
71-00-00 General
Description and Operation
.1
IO-520-8A, 10-520-88 Engine (CE-748, CE-772 and after; 0-10097, 010120 and after; E-llll, E-1241 Thru E-2110 except E-2104 and E-1946) IO-550-B Engine (E-1946, E-2104, EA-1 and after Engine Air Induction System
E-2111,
and
after)
Troubleshooting the Engine
2
Maintenance Practices
.4
Engine Removal (CE-748, CE-772 and after; 03-149 and after; 0-10097, 0-10129 and after; E-llll, E-1241 and after) Engine Installation (CE-748, CE-772 and after; CJ-149 and after; 0-10097. 0-10129 and after; E-llll, E-1241 and after) Engine Removal (EA-1 and after) Engine Installation (EA-I and after) Engine Build-Up Air Pressure Pump Removal
4
5
6 Installation Engine Driven Fuel Pump Removal Engine Driven Fuel Pump Installation Ground Running and Warm-up .6 Idle Speed and Mixture Adjustment (CE-748, CE-772 and after;´•CJ-149 and after; 7 0-10097, 0-10120 and after; E-llll, E-1241 thru E-2110 except E-1946 and E-2104) Full Throttle Adjustment (CE-748, CE-772 and after; CJ-149 and after; 0-10097, 010120 and after; E-1111,E-124lthru E-2110 except E-1946 and E-2104)$C20. 7 Idle Speed and Mixture Adjustment (E-1946, E-2104, E-2111 and after) Full Throttle Adjustment (E-1946, E-2104, E-2111 and afteri 8 Fuel Flow System Calibration and Correction (E-1946, E-2104, E-2111 and after)3K5 II Fuel System Adjustment (EA-1 and after) 12 Manifold Pressure Adjustment 14 Oil Pressure Adjustment 18 Air Pressure
Pump
71-10-00
Cowling Maintenance Practices Cowling Removal
Cowling Installat7on Cowling Latch Rigging Cowling Flap Rigging 1’END"
A14
71-CONTENTS Page 1 Jun 20/91
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 71 LIST OF PAGE EFFECTIVITY
CHAPTER SECTION SUBJECT
DATE
PAGE
71-EFFECTIVITY
1
Jun 20/91
71-CONTENTS
1
Jun 20/91
71-00-00
71-10-00
1 2 3 4 5 6 6A 7 8 9 10 11 12 13 14 15 16 16A 168 160 17 18 1
Oct 7/83 Oct 7/83
May 9/80 May 9/80 May 9/80 Aug 28/87 Aug 28/87 Sep 27/84 Sep 27/84 Sep 27/84 Sep 27/84 Sep 27/84 Sep 27/84 20/91 20/91 20/91 20/91 20/91 20/91 20/91 Sep 27/84 Sep 27/84
Jun Jun Jun Jun Jun Jun Jun
May 9/80
"END"
71-EFFECTIVITY Page 1 A14
Jun
20/91
n710005b426j98 BEECHORAFI BONANZA SEAIES MAINTENANCE MANUAL
GENERAL
DESCRIPTION AND OPERATION
The
turbocharger is located beneath and to the left rear of engine and is driven by exhaust gases. The turbocharger is lubricated by engine oil and is dependent the
/0-520-BA, /0-520-88 ENGINE (CE-748, CE-772 and aHer; 0-10097, 0-10120 and after; E-llll, E1241 through E-2110 except E-2104 and E-1946)
upon the engine oil pump for its lubrication. For this reason the engine should be allowed to run at idle for a short pen‘od
of time
The above Bonanza sen’al
equipped with 1O520-8A Continental engines until the following serials, at which time they are equipped with 10-520-88 engines: CEairplanes
are
816 and after: CJ-149 and after; 0-10179 and after; and E1371 and after. The 10-520-88 engine differs from the previous engines in that it has an improved crankshaft and other changes related to the improved crankshaft. The engine is a fuel injected, direct-drive, air-cooled, hon’zontally opposed, 8-cylinder, 520 cubic-inch displacement, 285horsepower engine. The engine crankshaft rotates in the clockwise direction. Recommended fuel for the engine is Aviation Gasoline 100LL (blue), or 1001130 (green) minimum grade. The oil capacity for the engine is 12.0 quarts of oil conforming to Continental Motors Bulletin MHS248. For overhaul of the engine, refer to Continental 10-520 Series Aircraft Engines Overhaul Manual, FORM X-30039A.
to 5
minutes) before it is shut down. This idle time turbocharger to slow down and cool before its oil supply is shut off. The turbocharger can obtain maximum continuous speeds of 96.000 rpm tin an overspeed condition it must not exceed 115,000 rpm) and run for 1 to 2 minutes after the engine has been shut down. This 1 to 2 minutes of turbocharger operation occurs without oil pressure because the engine oil pump is not running. Therefore it is important that the turbocharger be allowed to slow down before the engine is shut down.
(4
will allow the
The
engine
is
designed
to
operate with
a
maximum manifold
pressure of 36 in. Hg., and is protected from overboost by an automatic pressure relief valve. This valve is located downstream from the
turbocharger
if the system reaches
an
For
and will relieve pressure overboost condition of 39.5 in. Hg.
specific information regarding Chapter 81-00-00.
the
turbocharger system,
refer to
lo-sso-s ENGINE (E-1946, E-2104, E-~lll and
after) At
the above noted
airplane sen’als. the A36 Bonanza equipped with 10-550-8 Continental engines. These are fuel injected, direct-drive, air-cooled, horizontally opposed, 6 cylinder, 550 cubic-inch displacement 300 horsepower engines. airplanes
were
ENi;INE AIR INDUCTION SYSTEM Engine
induction air is available from two sources, pn’mary primary air source is supplied through intake duct, located on the forward cowling below the
and altemate air. The The
engine
crankshaft rotates in the clockwise direction.
Recommended fuel for the
engine is Aviation Gasoline 100LL (blue), or 1001130 (green) minimum grade. The oil capacity for the engine is 12.0 quarts of oil conforming to
an
propeller. The pn’mary
air passes then into the induction system.
through
an
air filter and
Continental Motors Bulletin MHS-248. For overhaul of the
engine,
refer to Continental 10-550 Sen’es Aircraft
Engines
NOTE
Overhaul Manual, FORM X-30563.
If, after cleaning, the surfaces of the air filter show metallic wires
through the remaining flocking maten’al, the filter is no longer effective and should be replaced.
EA-I and after The
Turbocharged
with
turbocharged Continental engines. Airplane serial
Bonanza A36TC
airplanes
are
equipped EA-1
equipped with TSIO-520-U and 8A-2 and after are equipped with TSIO-520-UB engines. Thbse engines are rated at 300 horsepower at 2700 rpm. The turbocharger provides a means by which the engine can maintain takeoff power from sea level through a critical altitude of 20,500 feet with a maximum operating altitude of 25,000 feet. is
If the
primary
source
of
ram
system low pressure opens and
air is obstructed, the induction an
"Altemate Air Source" door
permits the required volume of engine performance. The alternate air aft of the air filter and
on
air flow for normal door is located
the left side of the
just primary
induction.
71-00-00
Pagel A6
Oct7/83
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
TROUBLESHOOT1NG THE ENGINE
i.
Engine
REMARKS
PROBABLE CAUSE
INDICA TION will not start.
a.
b.
No
No fuel gage pressure
fuel to
a.
Check fuel control for proper position,
auxiliary pump ON and operating, feed valves open. Fuel filteropen, and tank fuel level.
engine.
Have gage pressure flooded.
engine
b.
off
Turn
and
auxiliary pump
ignition
set throttle to FULL OPEN and
switch,
fuel control to IDLE CUT-OFF, and crank
engine to clear cylinders of Repeat starting procedures. c.
Have gage to
No fuel
piessure
c.
engine.
Check for bent one
or
fuel.
excess
loose fuel lines. Loosen
line at fuel noule. If
fuel shows
no
replace fuel manifold valve. 2.
Engine
starts but
fails to
keep
a.
Inadequate fuel
to
fuel
a.
manifold valve.
running.
Set fuel control in FULL RICH position, tum auxiliary pump ON check to be sure feed lines and filters
Clean b.
Defective
b.
ignition system,
or
Check
accessible defective
3.
Engine
runs
rough
at idle,
a.
Improper
idle
mixture
a.
adjustment.
Readjust nut
to
idle
4.
Engine
has poor acceleration.
b.
Fouled spark
a.
idle mixture too lean.
b.
Incorrect worn
plugs.
fuel-air mixture,
control
linkage,
loose connections.
spark plugs.
setting. Tighten adjustment
richen
adjustment
mixture and
off
back
nut to lean mixture.
b.
Remove and clean plugs, Replace defective plugs.
a.
Readjust idle
b.
Tighten
mixture
as
adjust
gaps.
described in 3a.
loose connections,
elements of
or
and
ignition cables
Tighten
connections.
Replace
not restn’cted.
are
replace defective components.
replace worn linkage. Service air cleaner.
restricted air cleaner.
c.
Defective
ignition system.
c.
Check
accessible
connections. 5.
Engine
runs
rough
at
speeds
a.
Improper fuel-air
mixture,
a.
and
Check manifold connections for leaks.
Tighten
above idle.
cables
Replace defective plugs.
control
loose connections. and
linkage
adjustment. Check
for
Check fuel
setting and
fuel filters and
screens
for dirt. Check for proper pump pressure, and replace pump if defective. b.
Restricted fuel noule.
c.
Ignition system plugs defective.
and
spark
b.
Remove and clean all nonies.
c.
Clean and
ignition
regap spark plugs. Check for defects. Replace
cables
defective components. 6.
lacks power, reduction maximum manifold
Engine in
pressure
or
critical altitude.
a.
Incorrectly adjusted throttle control, "sticky" linkage
dirty
air cleaner,
or
a.
Check movement of linkage by moving control from idle to full throttle. Make proper
adjustments
and
replace
worn
components. Service air cleaner. 71-0090
Page2 Oct7/83
A6
BEECHCRAFT
BONANtA SERIES MAIMENANCE MANUAL
TROUBLESHOOT1NG THE ENGINE IND/CA 7/ON 6.
maximum
pressure
or
RENARKS
PROgABLE CAUSE
Engine lacks power, reduction in
(Continued)
b.
Defective
b.
ignition system.
manifold
cn’tical altitude,
(Continued)
Inspect spark plugs for fouled electrodes, heavy carbon deposits, erosion of electrodes, improperly adjusted electrode gaps, and cracked porcelains. Test plugs for regular fin’ng under pressure. Replace damaged or misfin’ng plugs. Spark plug gap to be 0.015 to 0.019 inch.
c.
Loose
or
intake
damaged
c.
manifolding.
Inspect entire manifold system for possible
leakage at connections. Replace damaged components, tighten all connections and
clamps.
7.
Low fuel pressure,
d.
Fuel nonles defective.
d.
Check for restn’cted nonles and lines and dean or replace as necessary.
a.
Restn’cted flow to fuel meter-
a
Check mixture control for full travel. Check
ing
for restrictions in fuel filters and lines, ad-
valve.
just control and clean filters. Replace damaged parts. b.
Fuel control lever.
b.
Check operation of throttle control and for
possible contact with cooling shroud. Adjust as required to obtain conect operation. c.
d.
incorrect fuel
Check and
injector pump adjustment and operation.
c.
Defective fuel
pump
d.
Replace pump.
fuel
a
Check for restricted fuel nonles
injector
ment.
adjust using appropn’ate equip Replace defective pumps.
relief valve. 8.
High fuel
pressure.
a
ResMcted flow
control
beyond assembly.
manifold valve. Clean
or
Replace defective fuel manifold
9.
Fluctuating
fuel pressure,
b.
Defective relief valve operation in fuel injector.
b.
Replace fuel injector pump.
c.
Restn’cted tea’rculation passage in fuel injector pump.
c.
Replace pump.
a.
Vapor
in fuel system,
excess
a
fuel temperature.
or
fuel
replace nonles. valve.
Normally operating clear system.
the auxiliary pump will Operate auxiliary pump pnd
purge system. b.
Fuel gage line leak gage line.
air in
b.
Drain gage line and
c.
Restn’ction in vapor separator
c.
Check for restn’ction in
vent.
or
separator
cover.
tighten connections.
Clean
ejector jet of vapor jet with solvent
(only). Do Not Use Wire place defective parts.
As Probe. Re-
71-00-00
Page 3 May 9/80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
(Continued)
TROUBLESHOOTlNG THE ENGINE PROBABLE CAUSE
INDICA TIOIV 10.
Low oil pressure on engine gage or high oil temperature.
a
Insufficient oil in oil sump, oil dilution or using improper
grade ent
b.
REMARKS
oil for
change oil
a
Add oil,
b.
Check for defective
or
temperature.
Defective vematherm valve.
c.
Oil cooler restriction,
d.
Leaking, damaged,
or
loose
screen or
Clean oil cooler.
d.
Check for restn~cted lines and loose nections and for
partially plugged Clean parts, tighten connections
filter.
place
engine idle cut-off.
vernathern valve. Re-
if defective.
c.
oil line connection. Restn’cted
Poor
viscosity.
prevailing ambi-
place valve
11.
to proper
con-
oil filter. and
re-
defective parts. oil pressure if necessary.
a
Low oil pressure,
e.
Readjust
f.
Relief valve stuck open.
f.
Remove, clean, and reinstall.
a.
Engine getting
a.
Check fuel control for being in full IDLE CUT-OFF position. Check auxiliary pump for being OFF. Check for leaking fuel man-
fuel.
valve.
ifold
Replace
defective compo-
nents.
GENERAL
Remove the
b.
MAINTENANCE PRACTICES
engine cowling. (Refer to Chapter 71-
10-00.) ENGINE REMOI/AL (CE-748, CE-772 and after; CJ-149 and after; D10097 0-10120 and after; E-llll, E-1241 and after)
c.
Drain the
d.
Remove the
removing and installing the engine that no dirt or foreign objects, be allowed to enter the induction system. Be careful not to damage duct work when removing and installing the engine.
a.
Check that the
ignition
Chapter
61-10-
Disconnect and
identify the ducts, engine controls, Cap all open lines and fittings. f. Place a support under the tail of the airplane. Place the engine hoist in position and attach to the g. lifting eyes on the engine. h. Hoist the engine suffidently to remove the tension
plumbing and wiring
Care should be taken when
to
oo.) e.
CAUTION
engine oil sump. propeller. (Refer
harness.
from the shock mount bolts.
i.
Remove the shock mount bolts.
NOTE
switch is in the OFF
position. It is recommended that the shock mounts be
WARNING
replaced
at each
engine change. Replace the
complete set All the shock mounts particular engine should be of the same
mounts as a
To be safe, treat all magnetos as hot To ground the magneto, disconnect the ignition switch lead wire at the
pole. plug
on
leads.
a
manufacturer.
and ground the capacitor impractical, remove the ignition
capacitor
If this is
harness
on
the
magneto
or
disconnect the spark
Position the engine slightly nose down and hoist j. slowly, making certain that the engine crankshaft flange
clears the
71-00100
Page
4
May
9/80
nose
cowl.
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CAUTION
engine
As the
check to make
is hoisted away from the cowl, sure that all wires, hoses and
lines have been disconnected,
Remove the propeller. (See PROPELLER a REMOVAL procedure in Chapter 61-10-00). Remove the cowling as described in COWLING b.
REMOVAL in this chapter. Remove the upper c.
removing
NOTES
Remove the air induction
e.
box and the
Position the
to the
sling
attach
hoisting
in front of the
airplane.
Position the
engine slightly nose down and lower slowly, engine crankshaft flange clears the nose
certain the
h.
i. the
cowl. d.
Align
the shock mount bolt holes and install the
bonding strap. Torque the four engine inch-pounds. Disconnect the hoisting sling and move the hoist e. clear of the airplane. f. Uncap all lines and fittings and connect the ducts, engine controls, plumbing and win’ng harness. Adjust all engine controls. g. Install the engine cowling. h. Install the propeller. (Refer to Chapter 61-10-00.) i. Perform an engine run-up as described in this j. shock mounts and
mount bolts 300 to 350
Complete
the final
tubing
between the air
Disconnect the
engine controls, plumbing,
and
and label all items for reinstall~ttion. Be
cap all open tubing. Place a support under the tail of the airplane. Place the engine hoist in position and attach to
lifting eyes on the engine. Hoist the engine sufficiently to j.
remove
the tension
from the shock mount bolts. k. Remove the 2 front and the n’ght rear shock mount bolts. Remove the 6 bolts attaching the left rear engine mount to the wheel well. I. Carefully hoist the engine from the airplane.
CAUTION
engine is hoisted away from the airplane, check to make certain that all wires, hoses and lines have been disconnected. As the
chapter. k.
at the
turbocharger inlet.
win’ng hamess. Tag sure to
position
tubing
Disconnect the exhaust stack from the
g. the
hoist and
engine.
Move the hoist into
c.
making
engine
bug by
turbocharger.
noted in ENGINE REMOVAL.
as
b.
nose
the
mixer valve.
f. Observe the WARNINGS, CAUTIONS, and
a
portion of hinge pins.
Disconnect the heater induction
d.
ENGINE INS7ALLATION (CE-748, CE-n2 and after; 0/-149 and after; D10097 0-10120 and after; E-IIl I, EI241 and after)
the screws and
adjustments. ENGINE INS7ALLATION ~4-1 and after)
NOTE Install the left
a
if
newly overhauled engine has been installed, the engine must be depreserved and a new or
serviced.
torque
to 300 to 350
secun’ng the
(EA-I
mount to the
engine
engine
left
inch-pounds.
rear mount
Install the 6 bolts
to the wheel well.
Torque these
bolts to 100 to 105 inch-pounds. Remove the hoist from the d.
ENGINE REMOVAL and
rear
and torque to 300 to 350 inch-pounds. b. Carefully lower the engine into the airplane. Install the remaining 3 shock mount bolts and c.
after)
e.
Install the win’ng hamess,
engine. plumbing,
and
engine
controls.
CAUTION and The the
magnetos should be considered hot when
ground
lead is disconnected. To avoid
starting of the engine, ground the magneto by connecting a wire to the magneto switch lead and then to the engine case, or disconnect the spark plug leads. accidental
turbocharger. tubing between the air box
f.
Connect the exhaust to the
g.
Install the induction
tu~ocharger. tubing
at the mixer valve.
h.
Conned the heater
i.
Install the upper portion of the nose bug. Install the cowling as described in COWLING
j.
INSTALLATlON in this chapter. k.
Install the
propeller
as
described in PROPELLER
INSTALLATION in Chapter 61-10-00.
71-00-00
Page 5 May 9/90
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
ENGINE
BUILD-UP
Reinstall
c.
the
plumbing.
Engine build-up consists of the removal of accessories and equipment from the old engine and installing them on the new engine. Refer to the Continental Aircraft Engine Manuals for the proper torque val-
for
ues.
ENGINE DRIVEN FUEL PUMP REMOVAL
Start the engine and check for at the mounting flange, and check and operation pressure proper
d.
leakage
readings.
NOTE
Access to
a.
is
pump
gained
the engine-driven through the left
fuel upper
identify all hoses, washelectrical connectors, nuts, ers, locations and note harness clamp reinstallation for the on new Cap all open hoses and engine.
cowling.
engine ports
Disconnect the fuel plumbing c. drain the fuel from the pump.
Tag
or
to
prevent
b. rear,
contam-
ination.
AIR PRESSURE PUMP REMOVAL
in
The fuel Pump is located the center of the engine.
d. Remove fuel the shroud from the pump.
at
the
and
cooling
pump
NOTE Remove the pump the pump.
e.
All
from the intake filter to the pump and on the outlet side of the pressure pump must be thoroughly cleaned, and all the filters replaced when the presinstalled is or
plumbing
remove
retaining
nuts and
CAUTION
Make sure the fuel pump removed with the pump.
drive
is
ENGINE DRIVEN FUEL PUMP INSTALLATION a.
is
Access
to
gained through
the air pressure pump the left hand cowl door,
a.
gasket b. Disconnect the necessary from the pump.
Install the fuel pump with a new and tighten the two retaining nuts.
plumbing b. shroud.
Remove the four attaching nuts and c. washers and pull the pump straight out.
Install
c: Connect plumbing.
fuel
the
and
pump
cooling
tighten the fuel
pump
AIR PRESSURE PUMP INSTALLATION CAUTION
CAUTION
Never been
use
an
dropped
air pump which or mishandled.
Make sure the fuel pump drive is installed with the pump.
has
GROUND RUNNING AND a.
Install
a
new
gasket
on
mounting pad flange.
NOTE
CAUTION Never jam the engine
or
force the
WARM-UP
the
engine should be pre-oqled prior to starting, with spark the plugs removed to relieve To pre-oil, connect starter load. the auxiliary power unit and crank with the starter, (not to exceed 45 oil seconds) unti 1 slight The
pump onto
mounting pad.
b. Position the pump on the mounting and install the attaching nuts and
washers. 71-00-00 Page 6
Aug 28/87
A12
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
pressure
Reinstall
is detected on the gage, the spark plugs.
NOTE The open
cowl flaps should be during all ground operation.
engine
should be noted within 30 seconds in warm weather and 60 seconds in cold weather. If no pressure is noted within the specified time, stop the engine and investigate the cause. Normal oil pressure at maximum rpm should be 30-60 psi and 10 psi at idle.
CAUTION
After starting the engine, pressure
indication
of
an
10
oil
psi
71-00-00
Page 6A A12
Aug 28/87
BEECHCRAFF 80NANZA SERIES ~HAINnNANCE ;HAHAUL
a.
Head ule
b.
Start the
approximately warm
airplane
engine
inte ule wind.
and maintain the
MRoma
engine speed
900 to 1000 rpm for at least one minute in as required during cold weather to
weather, and
prevent cavitation in the pressure oil pump, andto adequate lubn~cation.
slightly
above and
ensure
lubrication
assu~e
O
ADJUSTMENT SCREN
;AIR
THROTTLE LEVER
a
~200 rpm for Vie rest of Me
propeller governor. Usa up procedure.
~STOP PIN
warm-
d. Operate the engine on the ground with the propeller blade set at the minimum angle thigh rpm) setting. Maintain the cylinder head:emperature between e. 20008 and 46008. Never allow the cylinder head temperature to exceed 46008. f. Extended periods of idling at low rpm may result in fouled spark plugs.
g. RICH
t,,
setting of 1200 rpm or cycle the propeller two or three times to of the oil transfer collar bearing and
Advance the throttle to
c.
soov7
UPSPEED
at
~-METERINGUNIT
IDLEMIXTURE ADJUSTMENT NUT
COOLING SHROUD
METERING UNIT VINV OF RIGHT SIDE OF THROTTLE 80DY AND
METERING UNIT.(THROTTLE LEVER. PLUMBING. INDUCTION AIR SYSTEM. ETC. OMIT~D FOR CLARITY.) 36-?82-14
The mixture control should remain in the FULL
position
unless
leaning
is
required dun’ng
the
chedtout
Body and Metering Unit Figure 1
RH Side of Throttle IDLE SPEED AND MIXTURE ADJUSTMENT (CE748, CE-772 and alter; CJ-149 and after; D-la097, D10120 and after; E-11I1, E-1241 thru E-2110 except E-1946 and E-2104)
metering
(Figure I)
shorten the
valve and air throttle levers.
mixture is
Start and run the
a
up procedures in this rich. b.
engine according chapter. Place nixture
Chapter 74-00´•00).
(see MAGNETO Maximum drop-
off differential should not exceed 50 rpm. If the differential is within limitations, proceed with the idle adjustment.
Slowly retard the throttle levrsr to the idle position. engine tachometer should irdicate 625650 rpm (normal idle setting). To adjust, tum the idle speed adjusting c.
1
f.
After each idle mixture
engine by running
adjustment change, clear making a
it up to 2000 rpm before
mixture check. If the idle setting does not remain stable, check linkage; any looseness in this linkage will cause erratic idling. In all cases, allowance should be made for this effect of weather conditions upon idling adjustments.
g. the idle
The
screw
at the throttle lever
stop until the desired rpm is
reached. d.
1), using
Set the pump pressure at idle RPM (refer to Chart the relief valve adjustment screw (Rgure 1A) on
the aft centerline of the
engine ~uel pump. Tum the screw clockwise to increase pressure and counterc!ockwise to decrease pressure. e.
the
When the idle
cockpit
setting
has been stabilized,
mixture control lever with
into the IDLE CUT-OFF
a
smooth
move
steady pull rpm during
position. Observe the Adjust the idle mixture to obtain approximately 25/50 rpm gain in the idle speed as the mixture control is slowly moved toward the IDLE CUT-OFF. (If the mixture is set too lean, the idle speed will drop under the same conditions.) The idle mixture adjustment is the locknut at the metering valve end of the linkage between the the
1
the nut to
linkage.
control in full
the
Proceed to check the magnttos
DROP-OFF CHECK in
to the warm-
Tightening
linkage provides a richer mixture. A leaner obtained by backing off the nut to lengthen the
leaning
FULL THROTTLE ADJUSTMENT (CE-748, CE-772 and after; CJ-149 and after; D-30097, 0-10120 and after; E-llll, E-1241 thru E-2110 except E-1946 and
E-2104) Complete before a.
the IDLE SPEED AND MIXTURE ADJUSTMENT
proceeding with this procedure. With the mixture control at full rich, advance the engine RFM to check the fuel flow.
throttle to full rated
out process.
NOTE Fuel flow values may be monitored by the fuel flow gage in the airplane or a pressure gage attached to the manifold valve.
71-00-00
A9
Page7 Sep 27/84
I
BEECHCRAFT BONANtA SERIES MAIMENANCE MANAUI;
Chart 1 Fuel Flow Chart Al top end values
are
shown for rated RPM and manifold pressure
RPM
Propeller
Engine 10-520-88
(10-520-88)
b.
To obtain the
specified
Unmetered
Metered
or
or
Pump PressurelNonle Pressure (psi) (psi)
600
0-11
2.0-2.5
2700
28-31
15.5-1 6.5
values
(Chart
1) of nonle pressure or fuel flow at full throttle and rated RPM, tum the van’able orifice adjusting screw (Figure 1A) (located on the side of the pump) clockwise to increase pressure and counterclockwise to decrease pressure.
proper idle
adjustment
Fuel Flow
Fuel now
Lbs.lHr.
Gal./Ht.
136-146
22.7-24.3
speed (see Figure I). screw
Turn the idle
clockwise to increase
speed
rpm
and
counterclockwise to decrease rpm. The engine-driven fuel pump pressure should c. read 8.00 to 10.00 psig. If adjustment is required to achieve
]I
proper fuel pump pressure, turn the relief valve adjustment screw (Figure 18) clockwise to increase pressure and counterclockwise to decrease pressure. d. Maintain the specified idle rpm and the fuel pump pressure. Adjust the idle mixture to attain a momentary gain
NOTE
of 25 to 50 rpm when the mixture control is moved toward the idle cut-off position. If the mixture is too lean, the ~pm
If the rated RPM cannot be achieved at full throttle
during static run-up, adjust nozzie pressure or fuel flow slightly below limits, certain
making
specified
values
when rated RPM is achieved
are
If
achieved
dun’ng take-off
roll.
an
idle mixture
is
tum the idle
adjustment required, (see Figure 1) as necessary (tighten the nut mixture or loosen the nut to lean the mixture)
mixture nut
to
enricfi the
to
obtain the correct idle mixture.
IDLE SPEED AND MIXTURE ADJUSTMENT
(E-
1946, E-2104, E-2111 and after)
(10-550
B
Engine)
NOTE
a pressure gage in the fuel line between driven fuel pump and the meten’ng unit. The gage will be used to monitor fuel pump idle pressure (also called unmetered pressure).
Install
a
the
engine
After each idle mixture
engine by running rpm before making
adjustment,
cleat the
up to approximately 2000 the next mixture check.
NOTE
The pressure gage should be vented to the
atmosphere. FULL THROTTLE ADJUSTMENT E-2111 and after)
1
b.
Start and
temperatures
are
run
the
attained
engine until normal operating (see POH). Move the mixture
control to full rich. The idle soeed should be 625 to 650 rpm. If the engine is not idling within the specified range, change
the idle
speed adjustment
screw as
required
to obtain the
(E-1946, E-2104,
(IO-5~i0-8 engine) a.
Install
engine fuel
a pressure gage in the line between the flow transducer and the manifold valve to read
metered fuel pressure.
71-00-00
Page8
Sep n184
A9
ii
BEECHCRAFT BONANZA SERIES MAINTENANCE MANAUL
INE DRIVEN FUEL PUMP
VALVE ADJUSTMENT
(USED TO SET IDLE PRESSURE)
SCREW PUMP
UP
FWD~f III VARIABLE ORIFICE ADJUSTING SCREW (USED TO SFT FULL THROTTLE PUMP
PRESSURE) VIEW OF LEFT SIDE OF ENGINE DRIVEN FUEL PUMP TYPICAL FOR THE 10-52088 ENGINES (FITTINGS, COOLING SHROUD, ETC. OMITTED FOR CLARIN) 36-283-2
Engine Figure 1A
LH Side of 10-520-88
Driven Fuel
Pump
ENGINE DRIVEN FUEL PUMP RELIEF VALVE
ADJUSTMENT SCRE~Y
(USED TO SET PUMF] IDLE PRESSURE) ANEROID STEM (DO NOT TURN)
UP
FWD
BYPASS ADJUSTMEN~ SCREW (USED TO SET FULL THROTTLE PUMP PRESSURE) VIEW OF LEFT SIDE OF ENGINE DRIVEN FUEL PUMP ON 10-550-8 ENGINE (FITTINGS, COOLING SHROUD, ETC. OMITTED FOR CLARITY) 36-283-3
10-550-8
Engine Driven Figure 1B
Fuel
Pump
71-00-00 A9
Page9 S~p 27/84
BEECHCRAFT BONANZA SEAIES MAIHTENANCE MANAUL
20.0 H H
H
19.0
"C"
OPERATING CONDITIONS FULL THROTTLE STATIC RPM FULL RICH
18.0
v,
e
H
H
H
i
17.0aiL!
cr
i
w
16.0
k ~ti
i
f
i
i
H
Hr
Q
riti
t;
Z0.51
k
I
SET METERED PRES F TO VALUE SHOWN c.3 PSIG it-t~t
14.0
LL
iiir:
rr:
23.0
24.0
-LLi
25.0 26.0 27.0 28.0 MANIFOLD PRESSURE (IN. HG.)
i
"A" 29.0
30.0
LOCATE MANIFOLD PRESSURE ATTAINED DURING FULL THROTTLE STATIC RPM RUN-UP
(POINT "A").
AT THE POINT WHERE THE MANIFOLD PRESSURE LINE INTERSECTS THE NOMINAL METERED PRESSURE LINE (POINT "B"), READ METERED FUEL PRESSURE IN PSIG (POINT "C").
THE POINTS "A", "B", AND "C" WHICH ARE SHOWN ARE AN U(AMPLE. THE ACTUAL POINTS "A", "B", AND "C" WILL VARY WITH ALTITUDE AND FROM AIRPLANE TO AIRPLANE.
Full Throttle fuel Pressure Chart For The 10-550-8 Chart 2
Engine
71-00-00
Page 10 Sep 27/84
A9
BEECHCRAFT BONANZA SEAIES MAIIJ~NANCE MANAUL
NOTE
Adjust the flow rater (using the adjustable valve) readings in Chart 3 and record the airplane fuel
c.
to the test
The pressure gage should be vented to the atmosphere and mounted at approximately the same
level
flow
(gph) from
the fuel flow indicator
on a
copy of Chart 3.
the manifold valve.
as
NOTE b.
Run the
temperatures c.
are
until normal
engine
With the mixture control in the full rich
advance the throttle control to full
static engine rpm. Check the engine manifold pressure. d.
engine operating
attained.
position,
throttle and maximum
metered fuel pressure
The throttle and mixture levers must be in the full forward
Use the
shown in
to
position. Figure 1C
adjustable
valve
adjust the fuel flow
as
necessary.
versus
Refer to Chart 2 for determination of conect
engine fuel pressure. If a fuel pressure adjustment required, tum the engine-driven fuel pump bypass
metered is
adjustment
necessary (clockwise to increase rounterclaclcwise to decrease pressure) to
screw
as
pressure or obtain a conect pressure
reading. See Figure
Once
d.
an error
in the
airplane
fuel flow hardware
has been determined, determine the system correction the following example:
as
in
1B.
EXAMPLE:
pph flow rate with the fuel temperature at 40"F, an airplane fuel flow indicator reads 13.0 gph. Using a fuel density of 5.9 Chart 3 shows the indicator should be reading 13.5 gph. Therefore, the instrument error is 0.5 gph low. When the airplane indicator is reading 13.0 gph, add 0.5 gph for system correction. At the 80
NOTE
adjustment procedure is NOT a complete procedure, but a starting point. For the complete procedure "FUEL FLOW CALIBRATION AND CORRECTION (E-lo46, E-2104, E-2111 and after)" MUST also be completed.
This fuel pump
FUEL FLOW SYSTEM CALIBRATION AND CORRECTION (E-1946, E-2104, E-2111 and afterl
NOTE This fuel flow indicator check, should be made at all six flow rates as the system error may vary
as
the flow rate
changes.
A fuel flow system calibration and correction should be obtained from the following procedure. NOTE a.
Install
flow meter at
a
a
Fisher Porter Row Rater
point
or
equivalent
between the fuel flow transducer and
(The Fisher Porter now Rater must be installed in a straight vertical position in order to provide the most accurate reading.) Return the fuel from the flow rater back to the airplane fuel system through the wing filler port. the
engine
fuel distributor valve.
The FULL THROTTLE ADJUSTMENT (E-1946, E-2104, E-2111 and after) procedure MUST be
completed before proceeding.
check for proper engine fuel schedule. climb at 110 kias (knots indicated air speed)
Right
e.
Establish
a
Throttle............................................................ NOTE
Prop
Full Forward
rpm Full Rich
.....................................................................2700
Mixture Use
an
providing
external power supply capable of .25 volts for the source of 28.25
Boost
Pump.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Of
electn’cal power.
NOTE b.
Turn the
airplane
AUX FUEL PUMP to HI.
Step "g."
should also be worked while in
flight.
71-00-00
A9
Page 11 Sep 27/84
BEECHCRAFT
BONANZA SEillES MAIMENANCE MANAUL
ENGINE FUEL FLOW TRANSDUCER
ENGINE DISTR18UTOR VALVE AND NOZZLES
AIRPLANE FUEL FILLER PORT FLOW RATOR BE IN A STRAIGHT
(MUST
VERTICAL
t
POSITION)
ADJUSTABLE VALVE
AIRPLANE WING AJ6-281-41
fuel Flow Calibration Figure 1C
f.
(altimeter
Record the
fuel flow at all pressure altitudes Hg.) shown in Chart 4 is possible.
set at 29.32 in.
While in flight at 8000 feet, set power to 20.5 in. g. manifold pressure, prop to 2300 rpm, and mixture control to full rich. The EGT margin should be 20"C rich of peak or
greater. Next lean mixture from peak The
margin should h.
be
20’C
lean of
to engine roughness. peak or greater.
if the corrected fuel flow does not fall within the
required fuel flow limits (see Chart 4) or if the n’ch of peak margin is not obtained, readjust the metered engine fuel pressure (Feference step "d." of FULL THROTTLE ADJUSTMENT (E-2104, E-2111 and after). Tum the engine-driven fuel pump bypass adjustment screw as´• necessary (Figure 18) clockwise to increase pressure (fuel flow) or counterclockwise to decrease pressure (fuel flow). One psi. is approximately equal to one gph.
FUEL SYSTEM ADJUSTMENT
(EA-I
and
after)
(Figure 2) The engine fuel system senses turbocharger deck pressure and any change in deck pressure or manifold pressure will be accompanied by a change in fuel flow. During an overboost condition with cold oil where manifold pressure 2 in. Hg over redline, a corresponding may increase 1 enn’chn?ent in fuel flow will be observed. This is
a
normal
characten’stic of the fuel system and is desirable to maintain mixture strength. The correct procedure is to retard the throttle to 36.0 in.
Hg which will provide
a
corresponding
decrease in fuel flow.
The fuel system on the Continental TS10-520-U 520-U8 engines may be adjusted as follows:
or
fSIO-
71-00-00
Page 12
Sep 27/84
A9
BEECHCRAFT
BONANZA SERIES MAINTENANCE MANUAL
’DEGREES F.
TEMPERATURE WHEN FUEL FLOW IS CHECKED (FUE~ TEMPERATURE) Flow Rater
Setting
in Pounds
per Hour
(pph)
Flow Of Fuel In Gallons Per Hour (gph) Based On
Record
Density (Temperature) Ibs/gal
Indicator
Density
Flow 60
pph
Flow 80
pph
Flow 90
pph
6.0
5.9
5.8
5.7
gph
gph
gph
gph
10.0
10.2
10.3
10.5
gph
gph
gph
gph
13.3
13.5
13.8
14.0
gph
gph
gph
gph
15.0
15.3
15.5
15.8
gph
gph
gph
gph
18.3
18.6
19.0
19.3
Flow 110
pph
gph
gph
gph
gph
Flow 120
pph
20.0
20.3
20.7
21.0
gph
gph
gph
gph
Flow 140
pph
23.3
23.7 1 24.1
24.5
Temperature
i
Airplane Fuel Flow System
(gph)
(+0.5 gph
(13.0 gph in example)
in
example)
70"F......,,...5.8 Ibs/gal 1000F.............5.7 Ibs/gal
200F.....:.......6.0 Ibs/gal 400F.............5.9 Ibs/gal
Density Of Fuel Based On
Correction To
Airplane
Fuel Flow From
CHART 3
Install a calibrated fuel pressure gage in a. the fuel line between the fuel pump and metering unit to monitor pump outlet pressures. This gage must be vented to atmosphere. b.
Start and
temperatures up c.
at
to
the metering unit to obtain which will result in a 25 50 rpm rise when the engine is leaned to best power setting with the mixture control. Turn the adjustment screw CW to lean the mixture and CCW to richen. screw
run engine to bring cylinder head approximately 1210C (2500F).
Using throttle lever,
approximately
idle mixture
set
engine
idle
speed
650 rpm.
(4)
on
the desirable fuel-air ratio
WARNING preclude the possibility of an engine compartment fire, airplanes EA-1 thru
To
EA-146 must have
a
fuel drain hose
con-
Set pump pressure at idle rpm to 6 7 PSI, using the relief adjustment screw (1) on the centerline of the fuel pump. Turn screw CW to increase pres-
mixture control screw housing boss. Route the fuel drain hose to the right hand cowling flap opening with
sure, and CCW to decrease pressure,
sufficient clearance to prevent rubbing or clearance Insure maximum chafing. the and the between hose
d.
NOTE
nected
over
the
turbocharger/exhaust system. adjustment change, clear the engine by running it up to 2000 rpm before making a mixture check.
After
e. sure
A14
each
mixture
Maintain the idle rpm and idle pump pres-
specified
above
(reset
as
required); adjust
the
Airplanes EA-147 and after (Figures 2B and 2C) have a small tray or shield assembly beneath the throttle body and fuel metering assembly. Check that the hose (approximately 2 inches long) is attached over the 71-00-00 Page 13 Jun 20/91
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
mixture control
screw
boss and
housing
Insure drains into the shield assembly. that a fuel drain hose(s) is attached to the shield assembly and routed to the right hand cowl flap opening with sufficient
prevent rubbing
clearance to Insure
maximum
hose(s)
clearance
or
chafing.
Fly the airplane
j.
10 to 15 minutes
or
at high power settings for more, then land and check the
fuel flow at maximum power settings before shutting down the engine. Readjust the fuel flow to (195 to 205
pounds per hour) 32.5 to 34.2 gallons per hour with the variable orifice adjusting screw (2) as required.
between the
NOTE
turbocharger/exhaust sys-
and the
tem. It has been observed that fuel flow may increase up to 2 gallons per hour above the redline as the airplane approaches
NOTE
Cylinder 1210C
otherwise inconsistent.
checked,
time rpm rise is
the
results
will
be
Advance throttle to full (rated) power setf, ting to check pump pressure and fuel flow. With approximately 2700 rpm, full throttle, and 36.0 in. Hg manifold pressure, set fuel flow at 32.5 34.2 gallons 205 Ibs/hr). The full power fuel flow per hour (195 is made setting by using the variable orifice adjusting
(2)
screw
aneroid
located
housing.
the ah end of the fuel pump Turn screw CW to decrease fuel
(jam nut must be loosened before turning screw and retightened carefully.after each adjustment). Pump pressure should be 33 to 37 PSI. Pump pressure values at full power are given for reference only to evaluate the functioning of other components in the fuel system. After
gallons
If the fuel flow does per hour. exceed 36.5 gallons per hour, the enginedriven fuel pump pressure should be
readjusted. MANIFOLD PRFSSURF ADJUSTMENT
on
flow and CCW to increase
g.
critical altitude. This is a normal’characteristic of the Continental engine fuel system as long as the fuel flow does not exceed 36.5 gallons per hour. The correct procedure is to adjust the mixture to 34.0
temperature must be 930
head
(200-2500F) each
completion
"c", "d" and "e". Readjust
of item "f", recheck items as
required.
When fuel system is accurately adjusted, h. engine idle speed to approximately 650 rpm with the idle speed adjustment screw (Figure 2A), CW to increase, CWW to decrease.
The wastegate is controlled by engine oil pressure, which is regulated by the variable absolute pressure
controller. For this reason manifold pressure is quite sensitive to oil pressure and temperature as well as ambient temperatures. It has been determined that the manifold pressure will vary: (1) 0.2 in. Hg per 100F
change in oil temperature, (2) 0.3 in. Hg per 10 psig in oil pressure and (3) 0.05 in. Hg per 100F change in ambient temperature. The best time to make adjustments is shortly after the airplane has been flown. Under the conditions described in step "c", the manifold pressure should be 36 in. of Hg.
set
i. When setting up full throttle fuel flow on a day (above 600F) the system should be set toward the lower flow limit. On a cold day ~below 600F) the system should be set toward the higher flow limit.
Locate the absolute variable pressure a. controller mounted on the top of the throttle body in the left side of the engine accessory compartment. b.
hot
proper
Check the controller-to-throttle
adjustment
important that manifold pressure and fuel flow be within the prescribed limitations simultaneously during a maximum power run-up. Incorrect manifold pressure settings will cause erroneous fuel flow readings. It is also important to note the propeller speed when setling the fuel flow. if the fuel system is adjusted to the prescribed limits with 2650 rpm during ground static run-up, an enrichment will occur when
2700 rpm
speed.
is
obtained
with
forward
aircraft
full travel.
linkage
for
follows:
Position the controller lever to allow
i. It is
as
Ensure that the throttle
push-pull cable
will allow full travel. 2.
With the controller lever in the posiFigure 2A and the throttle plate arm stop pin, adjust the connecting linkage a position allowing 0.01 to 0.02 inch gap
tion shown in
against stop
the
nuts to
between the
cam
arm
and the controller maximum
stop (see Figure 2A).’ On a new engine this adjustment should already be made by Continental Motors.
71-00-00
Page 14 Jun 20/91
A14
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
Start and run the engine to bring the c. engine oil temperature up to (1600 to 1800F) 710 to 820 C. Adjust the oil pressure to 40 to 50 psig (45 psig preferred) at 2600 to 2700 rpm.
d.
After engine warm-up, advance the throttle the vernier control cable knob) to its
(without turning
Pressure Altitude (Set Altimeter At
29.92 In.
Observed Fuel Flow In Flight
maximum position of 2600 2700 propeller rpm and full rich mixture. Check and (if required) adjust the manifold pressure adjustment screw on the absolute
variable pressure controller. Loosen the jam nut and rotate the adjustment screw counterclockwise to increase, or clockwise to decrease manifold pressure, then
System Correction
retighten
Corrected Fuel Flow
the
jam
nut.
Required Fuel Flow
(gph)
From Chart 3
Hg.)
Sea Level
23.8 to 27.4
2000
22.1 to 25.2
4000
20.5 to 23.8
6000
18.8 to 22.3
8000
17.2 to 21.0
10000
15.5 to 19.7
12000
13.8 to 18.2
14000
12.3 to 17.0
16000
10.8 to 15.8
CHART 4
71-00-00
Page 15 A14
Jun 20/91
BEECHCRAFI
BONANZA SERIES MAINTENANCE MANUAL
O
O
(j
r
-9 _$
~II
I! c
ii
I~
O
A36TC-282-ll
Fuel
Adjustment (EA-1 Figure 2
and
After)
71-00-00
Page
16
Jun 20/91
A14
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
VARIABLE ABSOLUTE PRESSURE CONTROLLER
CONTROLLER LEVER MANIFOLD PRESSURE ADJUSTMENT SCREW
(IN MAX. THROTTLE POSITION)
(0.5" HS~TURN) .01
GAP
/O
O JAM NUT CAM ARM
CONNECTING LINKAGE STOP NUTS
STOP PIN
O
I I
00 NOT CHANGE THIS ADJUSTMENT SETTING
I
\V
LIDLE MIXTURE ADJUSTMENT
THROTTLE BODY----/
SCREW
IDLE SPEED ADJUSTMENT
THROTTLE PLATE ARM
LOOKING AFT
Throttle
Body
A36~C-282-12
and Variable Absolute Pressure Controller
Figure 2A
71-00-00
Page 16A A14
Jun 20191
BEECHCRAFT BONANZA SERIES WIAINTENANCE WIANUAL
SHIELD BRACKET AND MOUNTING BOLT
THROTTLE BODY
THROTTLE BODY
B
’SIJPPORT BRACE
SCREW NUT WASHER
DETAIL
A
SHIELD ASSEMBLY
8
DETAIL
B dcstoolso
Body Shield Assembly (EA-147 thN EA-241) Figure 2B
Throttle
71-00-00
Page 16B Jun 20/91
A14
BEECHCRAFT BONANZA SERIES MAINTENAN(3E MANUAL
SHIELD BRACKFT AND MOUNTING BOLT
~Od THROTTLE BODY
SCREW NUT WASHER
THROTTLE BODY SUPPORT BRACE
DETAIL A SHIELD ASSEMBLY
DETAIL
B C9100179
Body Shield Assembly (EA-242 and After) Figure 2C
Throttle
71-OQ´•00
Page 16C A?4
Jun 20191
BEECHCRAFT BONANZA SEAIES MAINTENANCE MANUAt
0‘) AP
(O
o‘
o
o.
OIL FILTER ELEMENT
a t
OIL PRESSURE ADJUSTMENT SCREW 35-257-2
Adjustment figure 3
Oil Pressure
7100-00 p~17 AO
sepnla4
BEECHCAAFT BONANZA SERIES
MAINTENANCE MANAUL
simultaneously dun’ng
NOTE
a maximum power runIncorrect manifold pressure settings will cause erroneous fuel flow readings.
up.
If the manifold pressure is with engine oil temperature at (100oF) 38 C rather than the
ad~usted
71"
to
82"C (160"
to
180´F)
recommended,
a
CAUTION
decrease in manifold pressure will occur when the oil temperature increases to the normal
operating range. Under
these conditions,
Do not exceed 36 in.
a
decrease in manifold pressure of 1 to 2 in. of Hg below the rated 36 in, of Hg will occur
along flow.
with
If,
on
corresponding
a
is
temperature
at
Fly the airplane 10-15 minutes or more at high settings, land and check the manifold pressure at maximum power setting before shutting off the engine. Readjust to 36.0" Hg as required. e.
decrease in fuel
the other hand,
pressure
Hg manifold pressure.
power
the manifold
adjusted with engine oil (2300F) 1100C, a corresponding
increase in manifold pressure above 36.0 in. Hg will occur on the next flight if the oil
O1L PRESSURE ADJUSTMENT
temperature is then much lower. A
(f~gure 3)
corresponding
enrichment in full rich fuel flow
above the value obtained at 36.0 in.
also
Hg
will
since the full rich schedule is a function of both deck pressure and rpm. These occur
The oil pressure adjustment screw is located approximately 3 inches below the oil filter housing. To adjust, tum the
adjusting
screw
clockwise to increase
or
counterclockwise
characteristics must be taken into consideration when manifold pressure adjustments are made. It is important that manifold pressure and fuel
to decrease the oil pressure. The oil pressure should be between 30 and 60 psi at maximum operating rpm and
flow
idle rpm.
be
within the
temperature,
prescribed limitations
50
psi
at cruise rpm, and 10
psi
minimum at
"END"
71-00-00
Pagel8
Sep n184
AO
BEECHCRAFF BONANZA SERIES MAINTENANCE MANUAL
COWUNG
MAINTENANCE PRACTICES
Secure the hook
d.
pins
in this
position
with the
jam
nuts.
COWUNG REMOVAL
wiring from the
cowling.
There should be
it is moved from the
slight pre-latched to the
link rods. f.
engine cowling. Remove the bolts, spacers, and nuts at each end cowling angle, and carefully remove the
c.
as
The
position.
Disconnect the necessary electn’cal
b.
latch the
the latch
on
fully latched position, thus snugging down the upper cowl. pull down tension should not be enough to bow the two
Check to be sure that the engine magneto switch is
a
in the OFF
Fully
a.
tension
of the center
’cowling.
the latch mechanism is
on
accomplished by raising
or
lowering
the hook
pinsas
tension. cowling Secure the hook pins in the proper position with the g. jam nuts, and safety wire the jam nuts together.
require‘d
with the above
to secure the
COWLING INSTALLATION Check to be sure thatthe
a.
CAUTION
engine magneto switch is
in the Off position. b. Carefully place the
Secure the
c.
cowling in position. cowling at each end of
latching the cowling, always be sure Be jaws fully engage the shoulder of the hook pins. After latching the handlecs to on the forward and aft
When
latch
the center
with bolts, spacers, and nuts, Connect any necessary electn‘ml win’ng to the
cowling angle d.
check
cowling. e.
securely
for´•securitj~
the upper cowling will latch to the lower cowling when fully latched; if not,
Check to be
sure
proceed with COWUNG LATCH RIGGING. COWL FLAP RIGGING COWLING LATCH RIGGING
a
Attach the
flap control
rod end to the
flap.
Position the control arm, attached to the wheel well cover, up and forward so that the flap control rod parallels the control arm. Connect the rod to the control arm. b.
assembly on eact~ side of the cowling consists of outside master latch; two link rods, and two auxiliary two latches located on the inside on tft&~iriside of the brackets; ´•each containing a hook’
The latch an
pin\
c.
in snug
Adjust the control rod linkage so that the door pulls against the opening.
upper cowling. Actuating the outside 18tci~ moves each link rod to operate’its respective latch. The fore and aft inside latches each incorporate a set of jaws which are open only when the outside latch is
placed
in the
fully
NOTE
unlatched
position. The jaws remain dosed in both the latched and the pre-latched positions. To n’g the latches, proceed as follows: a
When
adjusting
the rod end
linkage,
insure
proper rod end engagement by observing threads in the sight hole of the control end.
Loosen the fore and aft inside Hartwell latches on position the latches so that when the upper
their brackets and
cowl door is lowered, the hook pin falls directly over the center of the latch. Secure the latch making sure the latch is
vertically straight. b. Open the outside latch and HOLD the latch in the fully unlatched position. The link r~ds should hold both sets of auxiliary latch jaws fully open in this position; if not, loosen the connecting points of the two link rods and position the rods to fully open each jaw with the outside latch held fully open. Tighten the connecting points of the two link rods, Hold the latch fully open and lower the top cowl c. until the latch jaws are-between th~shoulder: of the hook pins and the lip directly above the point. Ralease’tftetatch to the pre-latched position.
pushlpull control in the pilols compartment position. a. Rig the push-pull control arm assembly, at the wheel well cover (n’ght hand side), in the forward position so d.
Set the
to the closed
that the control rod will center over the
arm
hinge..00
to .06
inch overcenter is needed to prevent the cowl flaps from creeping open in flight. An amount greater than this
maximum may cause the control to ovem’de canter and lock. ~ttach the control rod ball joint link to the arm f.
assembly and pull the control to the full open position. The flap should open approximately 4 inches measured at the aft inboard end of the flap to the face of the exhaust stack flame shield.
"END" 71-10-00
Pagel May 9/80
CHAPTER
ENGINES
8EECHC~AFT BONANtA SERIES MAINTENANCE MANUAL
CHAPTER 72
LIST OF PAGE EFFECTIVITY CHAPTER
SECTTON
SUBJECT 72
PAGE
EFFECTnVTTY/CONTEMS
DATE
Oct 7/83
t
CHAPTER 72
ENGINE
TABLE OF CONTENTS CHAPTER SECT1ON
SUBJECT
SUBJECT
PAGE
INTRODUCTION GENERAL DESCRIPTION SPECIAL TOOLS AND EQUIPMEM
DISASSEMBLY
CLEANING, REPAIR 8 REPLACEMENT INSPECTION ASSEMBLY OF SUBASSEMBLIES
FINAL ASSEMBLY AND TEST LIST OF TABLES
NOTE For detailed information Aircraft
Engines
on
the above
subjects,
refer to the Continental 10-520 Sen’es
Overhaul Manual, FORM X-30039A
Overhaul Manual, FORM X-30042 FORM X-30568.
or
or
TSIO-520 Series Aircraft
10-550-8 Series Aircraft
Engines Engine Overhaul Manual.
CAUTION It is imperative that when replacement of
engine components
and accessories becomes
necessaty, all part numbers be verified to ensure that the proper part has been obtained for replacement. Inconect part replacement may result in extensive damage to the engine,
’END"
72-EFFECTNTTY/CONTE~JTS
Page A6
1
Octf/83
CHAPTER
ENGINE FUEL ANI~ CONTROL
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 73
LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT
PAGE
73-EFFECTIVIT//CONTENTS
1
73-30-00
1
CHAPTER 73
DATE
Oct 10/80
ENGINE FUEL AND CONTROL
TABLE OF CONTENTS CHAPTER SECTION SUBJECT
SUBJECT
FUEL DLOW INDICATING
PAGE
...73-30-00
Description and Operation
.......1
Fuel Flow Indicator
.......1
Maintenance Practices
.............1
Transducer
or
Transmitter Removal
.............1
Transducer
or
Transmitter installation
.............1
"END"
73-EFFECflVTr(lCONTENTS
paC~1 Oct 10/80
BEECHCRAFT BONAHZA SERIES MAINTENANCE MANUAL
FUEL FtOW INDICATING OPERATION
FUEL jLOW INDICATING PRACTICES
DESCRIPTION AND
MAINTENANCE
FUEL FLOWINDICATOR On the fuel Row systems pn’or to CE-929, 01-156, O10354, E-1766, and EA-159, the indicator in the instrument
panel
is teed into the fuel
throttle
servo.
In this
supply line down
stream from the
system the indicator
f
j
converts fuel
pressure to gallons per hour readout in fuel flow.
TRANSDUCER QR TRANSMITTER REMOVAL a
Open
b.
Disconnect the electn’cal connection.
c.
opening On sen’als CE-929 and after, CJ-156 and after, D-10354 and after, E-1766 and after, and EA-159 and after, thefuei
the
engine
cowi.
Disconnect the two fuel lines, and cover the prevent contamination. Remove the bolts holding the transducer or
to
d.
transmitter in place, and
remove
the unit.
flow system does not rely on fuel pressure to indicate fuel flow. In this system fuel Rowing through a transducer
signal which is directed to the fuel Row indicator in the instrument panel. The fuel flaw indicator creates an electric
a readout in gallons per hour. The major components of the system are the transducer or transmitter and the indicator. Engine fuel Rows through the transducer then to
gives
the
engine
fuel distributer valve. The transducer is attached
top of the engine crankcase, near the forward center line of the engine. The indicator has dual pointers, one for
to the
fuel Row and
one
is located in the
for manifold pressure. The circuit breaker
subpanel
in front of the
TRANSDUCER OR TRANSMTT~R INSTALLATION
a
attaching b. c.
d.
copilot.
Install the transducer bolts.
Torque
or
transmitter with the
to 180 to 220
inch-pounds.
Connect the two fuel lines. Connect the electn’cal connection. Close the engine cowl.
"END"
73-30-00
Page ’1 Oct 10/80
CHAPTER
IGNITION
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 74
(GNITION
TABLE OF CONTENTS
CHAPTER SECTION SUBJECT
SUBJECT
GENERAL
PAGE
74-00-00
Description
and
Operation
......1
CE-748, CE-772 and after, CJ-149 and after; D-10097, D-10120 and after, E-llll, E-1241 and after)
......1
EA-1 thru EA-439.............................................
......1
EA-440 and after
......I
Ignition and Starter Switch Troubleshooting Ignition System
......1
Maintenance Practices
......2
Magneto Drop-Off Check Magneto Point Gap and Timing Preparing the Magneto for Installation Magneto Pressurization Air Filter Removal of the
......1 ......2 .......3 on
the
Engine
.......3 .......3
Magnetos
.......3
Installation and
Timing
the
Installation
Timing
Timing of Magnetos Magnetos to the Engine and Timing of Magnetos (With
.......4 .......4 a
Disc and Pointer
......4A
DISTRIBUTION
74-20-00
Maintenance Practices
.......1
"END"
74-CONTENTS A12
Page 1 Aug 28/87
Qeechcr~ft BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 74
IGNITION
LIST OF PAGE EFFEC7IVITY CHAPTER-SECTION-SUBJECT
74-Effectivity ’46Contents
74-00-00
PAGE 1
Nov 16/94
1
Aug 28/87
1
Sep 27/84 Sep 27/84 Sep 27/84
2 3
6
Aug 28/87 Aug 28/87 Sep 27/84 Sep 27/84
1
May 9/80
4
4A 5
74-20-00
DATE
74-Effectivity Page A17
1
Nov 16/94
BEECHCRAFT BONANZA SERIES
MAIMWANCE MANAUL
GENERAL
DESCRIPTION AND OPERATION
coupled, pressurized magnetos. Pressurizing the magnetos prevent internal arcing which may occur in unpressurized magnetos while flying at high altitudes. The air to pressurize the magnetos is taken from the throttle body, and should be at or near sea level pressure at all
will
CE-748, CE-772 and after; 01-149 and afte~ D10097 0-10120 and after; E-llll, E-1241 and after The
engine
is
equipped with
two Bendix S6RN-1225
times. After the
impulse coupler, At starter cranking speeds the impulse coupler automatically retards the spark for starting purposes. Centrifugal force disengages the impulse coupling pn’or to reaching engine idle speed. The impulse coupler then acts as a straight dn’ve and the magnetos fire at the normal fin’ng position of the engine. magnetos. Each magneto incorporates
air leaves the throttle
pressurizing
it
body,
passes through a filter on the way to the magnetos. This filter should be checked every 50 hours and replaced as
an
required.
If the filter is white it may be continued in service, or contaminated the filter should be replaced.
but if it is red
IGNITION AND STARTER SWITCH EA-I
tfiroogh
EA-439 The combination
engine is equipped with a Bendix SGRN-1201 magneto (left side), and a Bendix S6RN-1205 magneto on the right side. This system incorporates a starter vibrator. The left magneto has two sets of points: the retard sat of wints is used for starting and the main set of points is used when the engine is running. When the starter is
engaged the right magneto
is
ignition
and starter switch has five
positions:
The
OFF
The magnetos are inoperative. The n’ght magne’to is fin’ng its plugs; the left
R
magneto is L
grounded
and the left magneto (using the retarded set of points) is supplied with pulsating current from the starter vibrator,
not
firing plugs.
The left magneto is firing its magneto is not firing plugs.
plugs;
the
n’ght
BOTH
Both the magnetos
START
On S6RN-1225 and Slick magnetos, the starter circuit is completed and the starter is
which received its current from the starter solenoid. The
operating.
starter vibrator is located on the left aft side of the firewall.
to retard the
are
fin’ng
their
plugs.
The
impulse coupling is engaged spark for starting. On SGRN-
1201 and S6RN-1205 magnetos, the starter is operating and the vibrator is
solenoid
j
EA-440 and after The
engine
is
equipped
energized causing with two Slick 6220,
impulse
retard breaker
on
right magneto
is
current to flow thru the
the left magneto while the
grounded.
TROUBLESHOOTING IGNITION SYSTEM PROBABLE CAUSE
INDICATION 1.
Engine
fails to start.
a
wet,
a
Clean
Magneto primary ground wire
b.
Check
Spark plugs loose, fouled,
b.
REMARKS
or
short circuited.
c.
Dirty,
burned
Moisture
replace
defective
spark plugs.
or
primary ground
wire between
magneto and switch. or
pitted
c.
magneto breaker points. d.
or
defective.
oil in magneto
Clean
paints
or
replace if badly burned
or
pitted. d.
Clean magneto distributor.
e.
Turn
distributor.
e.
Internal
magnetos.
trouble
with
engine over Replace magneto spark is weak.
and check if there is
spark jump. spark or ii
no
74-0090
A9
Pagel Sep27/64
I
BEECHCRAFT BONANZA SEAIES MAIMENNrJCE MANAUL
TROUBLESHOOTING
(Cont’d)
IGNITION SYSTEM
PROBABLE CAUSE
INDICATION
2.
Hard
starting.
to
a.
Time magneto to
are
b.
Set
Impulse coupling inoperative
c.
a
Magneto improperly timed engine.
b.
Magneto
c.
or
Rough running engine,
a
b.
breaker
points
engine.
points.
properly.
not set
3.
REMARKS
late. loose
Spark plugs
or
fouled.
Spark plugs, leads, oily, dirty
connectors
or
Remove
access cover
coupling
action.
and check
a
Clean and regap
b.
Clean leads and connectors and
damaged
or
impulse
spark plugs.
replace
connectors.
cradled.
c.
Defective
ignition hamess.
c.
Make
continuity and high voltage tests on Replace harness or leads ii
harness.
necessary.
4.
Low power.
d.
Magnetos incorrectly
a.
Dirty points.
a
burned breaker
or
Bumed
timed.
or
defective
ignition
d.
Time magnetos to
e.
Clean
or
a
Check
continuity
hamess. b. c.
ii
badly
bumed.
of harness and
replace
if
necessary.
Magnetos incorrectly timed. Internal
trouble
with
b.
Time magnetos to
c.
Turn
engine
engine.
over
Replace magneto if spark.
magnetos.
GENERAL
replace
engine.
MAIMENANCE PRACTICES
b.
and check
spark.
there is weak
or no
Set the throttle to
produce 1700 rpm. Note the amount of rpm differential between the LEFT and FtlGHT magnetos as the magneto switch is c.
MAGNETO DROP-OFF CHECK
tumed from BOTH to LEFT, back to BOTH, and then turned to the RIGHT
The
drop-off
check is
accomplished by switching
magneto switch from BOTH to either the RIGHT
position
and
a.
propeller
noting any
loss
or
or
the
LEFT
variance in rpm.
Thoroughly warm-up the engine and set the control in low pitch. Place the mixture control in
FULL RICH.
position.
The difference between the two
magnetos operated individually should not exceed 50 rpm. Normal magneto drop-off on either magneto should be within 50 rpm of each other. If the magneto drop-off is excessive on either magneto (150 rpm), an inspection to determine the cause should be accomplished. Common causes are incorrectly timed magnetos, or incorrect fuei/air ratio.
7eCO-00
Page2 Sep 27/84
A9
BEECHCRAFT SONAHZA SERIES MAINIENANCE MANAUL
PREPARING THE MAGNETO FOR INSTALLATION ON THE ENGINE
NOTE Due to the design changes in today’s higher performance engines, the compan’son of single magneto operation versus both magnetos is no longer a sound criteria for evaluation of magneto performance. Therefore, all magneto checks should be performed on a comparative basis between right and left magneto performance. In addition, absence of magneto dropsff should be caused for suspicion that the timing has been bumped up in advance of the specified setting.
On Bendix magnetos turn the magneto drive in the direction opposite to normal rotation (this keeps the impulse ~uplers from
engaging) (nonimpulse coupled magnetos may also be opposite to normal rotation) until the respective timing mark (viewed through the inspection hole) on the distributor gear is aligned with the divided casting line of the magneto housing. Now the magneto is ready to install on the engine and to fire number 1 cylinder. rotated
Slick magnetos may be engine as follows:
CAUTION
a.
prepared
for installation
timing pin for
Insert the T-118
a
on
the
naii)
6 penny
in
the R hole in the distributor block.
fouling the spark plugs, operation on magneto should not exceed 5 seconds,
b.
To avoid one
Turn the magneto drive in the direction opposite pin inserts through the hole in the
to normal rotation until the
gear
(approximately
’/4
inch).
MAGNETO POINT GAP AND TIMING NOTE
I
It is assumed that the magnetos have been properly internally timed and points adjusted per the applicable Bendix or Slide vendor publication. To adjust the magneto
If the
points other than that specified in the applicable vendor publication manual will alter the magneto "E gap" and cause a weak spark. This internal timing and point adjustment should not be made on the airplane. For inspection purposes the point gap may be checked when the cam follower is resting on the high point of the cam lobe. The magneto point gap should be as follows:
and
PO\NT GAP 1N INCHES
the
is
binding, b’ut
passed,
reinstall the
until the
pin
will not insert into the
c.
The As
magneto is
soon as
timing pin
pin
and continue rotation
inserts in the hole in the gear.
supply ignition spark d.
MAGNETO
pin
hole in the gear, it has hit the pointer on the gear. Pull the pin out until the pointer has
the
now
ready to
install
to number one
on
the
engine
cylinder.
magneto is installed
on
the
engine
MUST be removed.
Bendix S6RN-1201 and S6AN-1205 t
0.003
only) 0.016
c
0.006
Bendix SGRN-1225
0.016
t
0.003
Slick 6220
0.009
c
0.001
0.016
main breaker 201
retard breaker..................(SGRN-1
I
On the magnetos the intemal timing and point adjustment should be made at the time of assembly or overhaul (Bendix Timing Kit No. 11-8150-1 is available for intemal timing of
B
NOTE If the magneto dn’ve is rotated with the timing installed the magneto will be damaged.
pin
MAGNETO PRESSURa4TION AIR FILTER
the magneto. Slick 1100 Assembly and Timing Kit is available for Slick
magnetos.)
NOTE For adjustment of contact opening and intemal timing of Bendix magnetos, refer to Bendix, for applicable manuals. Magneto contact assemblies should be checked after the first 25 and 50 hours operation and each 50 hours thereafter.
The magneto pressuritation air filter is located on the top of the engine between the magnetos. This filter may be
continued in service as long as it appears white and is not contaminated. The filter should be checked every 50 hours and replaced as necessary.
REMOVAL OF THE MAGNETOS a.
Remove the four
outlet and
remove
screws
retaining the high
tension
the outlet from the magneto.
74-00-00 A9
Page3 Sep 27/84
BEECHCRAFT BONANZA SERlES MAINTENANCE MANUAL
CAUTION Current not have
production the
grounding
earlier devices featured on Scintilla magnetos. To be safe, treat all magnetos as hot whenever the ground lead (switch terminal) is di sconnected. To ground the
magneto, switch
ground
connect
Remove the
a.
a
wire
to
lead of the magneto the wire to the case.
grounding
drive the
the and
wire from the
Turn the crankshaft a few degrees g. counterclockwise and bring it back again unti 1 the this point,
b. Remove the two magneto retaining nuts and washers and pull the magneto away
from the accessory
case.
INSTALLATION MAGNETOS
AND
marks are aligned. At timing lights should go out at the same instant that the position halfway between the timing marks on the
Remove
Cover
the
timing lights do not go out time, loosen the magneto that
spark plug
from
is late or early and outlined in steps "e"
lower
spark plug
hole
TIMING
of No. 1 cylinder with thethumband turn the crankshaft until pressure is felt on the thumb.
Remove the plug in front of No. 6 observe the timing marks on an alternator the drive the as gear crankshaft is rotated. There are 2 marks; 1 at the 200 ETC position, and 1 at the 240 ETC position. When a position halfway between these marks is centered in the viewing hole, No. 1 cylinder is at the 220 ETC position of the compression stroke. c.
cylinder
NOTE
Prepare the magneto for installation the engine as described on PREPARING MAGNETO THE INSTALLATION ON THE ENGINE.
in
If the same
lower
cylinder. b.
both
OF
TIMING
h. the
timing
alternator drive gear appears in the center of the crankcase inspection hole.
at the a.
mate with the slots
f. Connect the timing light lead to the switch terminal (ground terminal) of each magneto. Both timing lights should be on. Tap the right magneto down until the light goes out. Secure the magnetos.
magneto.
each
coupling lugs
drive coupling. Install holding washers. lockwashcrs and nuts, but tighten only enough to permit turning the magneto for final timing, without looseness.
do
magnetos
automatic
so
of
FOR
repeat the process and Nf" above.
THE MclGNETOS
Remove a. each cylinder.
the
top
TO
THE
spark
ENGINE
plug
from
b. Remove the plug in front of No. 6 cylinder and observe the timing marks on
alternator the drive the as gear crankshaft is rotated. There are 2 marks; 1 at the 200 BTC position, and 1 at the 240 ETC position. When a position halfway between these marks is centered in the viewing hole, No.l cylinder is at the 220 ETC position of the compression stroke. Rotate the crankshaft in the c. direction of normal rotation to bring No. 1 cylinder up on its compression stroke. If the engine is equipped with impulse coupled magnetos, continue slowly rotating the engine until the impulse couplings snap.
d. it will
Hold the magneto in the position occupy when installed, and check alignment of the gear coupling slat and impulse coupling lugs. If not aligned, pull the gear out of mesh, but not out of the oil seal, and turn to correct alignment. Push the gear back into mesh.
d. switch
Connect a timing light to the terminal (ground terminal) of the right magneto and rotate the crankshaft in the direction opposite to normal rotation to a position past the timing marks the alternator drive gear (approxion
mately 260). e.
flange
Place a new gasket on the magneto and install the magneto carefully
74-00-00
Page 4 Aug 28/87
A12
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
Turn the crankshaft in the normal e. direction of rotation until the light goes out. If 220 ETC is indicated by the timing marks on the alternator drive gear, the magneto is correctly timed. f. Repeat steps left magneto. g.
timed,
"d"
"e"
for the
2. Set No. 1 indicated in steps
Rotate the
just goes 5.
magneto until
the
out.
Tighten
the
magneto
mounting
nuts.
TIMING AND A TIMING DISC
INSTALLATION MAGNETOS (WITH
OF AND
POINTER)
If the magnetos are not correctly proceed as follows:
Install the i. the magneto which is not
as
and
4.
light
timing
properly
~ylinder c"
light
on
timed,
at 220 ETC
through "e"
though the Continental engines have factory installed timing marks, a positive top dead center (TDC) locator and timing Even
similar to that provided with the "Universal Engine Timing Indicator" may be used to time the magneto to the engine disc
or
to
check
the
accuracy
of
the engine be timed
timing marks. The engine should 3. nuts.
Loosen
the
magneto
mounting
to
fire
at
220 +00
-20 before top center
(BTC).
74-00-00 A12
Page 4A Aug 28/87
BEECHCFIAFI
BONANZA SERIES MHUlTENAINCE ~ANUAL
rotation
WARNING
f. The magneto is
the
grounded through
ignition (pn’mary)
switch, therefore, any time the switch wire is disconnected from the magneto, the magneto is in a switch ON or HOT condition. Before turning the propeller by hand, disconnect all of
spark plug leads the engine.
to
until the
piston lightly touches the locator.
Install the
rotate the
timing
timing
disc
on
disc until O"
the
(TC)
propeller spinner and is located under the
pointer. Rotate the engine in the opposite direction to g. normal rotation until number 1 piston lightly touches the locator.
prevent accidental fin’ng
h.
Note the
the disc toward 00
reading
timing disc. Now rotate reading noted is shown. TDC locator from the spark plug
CTC) until
i.
Remove the
j.
Rotate the
on
the
112 the
hole.
CAUTION Cunent production magnetos do not have internal, automatic grounding devices. To be safe, treat all magnetos as hot whenever the lead is disconnected. To
ground
magneto, the filter
engine
ground
the
connect a wire to the switch lead at
the wire to the
capacitor and ground
in the normal direction of
compression stroke of number 1 cylinder and until the pointer arrives at the number of degrees noted last in step "h" (112 the first noted reading in step "h"). k. Rotate the timing disc until the pointer is positioned at 00 (TC). i. Rotate the engine opposite the normal direction of rotation to approximately 5" beyond the specified timing for the engine being timed. Rotate the engine in the normal direction to the m. specified before top center (BTC) fin’ng position (this is to remove gear backlash). further movement of the engine
case.
To locate the compression stroke of number one a cylinder, remove the lower spark plugs from each cylinder except number one cylinder. Remove the top plug from number one cylinder. b.
engine
rotation to the
Place thumb of
cylinder spark plug hole
one
hand
over
should not be necessary until the magnetos
are
installed.
NOTE
the number one
and rotate the crankshaft in the
Without
turning the magneto coupling, hold the magneto in the position it will occupy when
direction of normal rotation until the
compression stroke is indicated by positive pressure inside the cylinder lifting the thumb off the spark plug hole. After locating the compression stroke of number 1 c. the advanced firing position of number 1 locate cylinder, cylinder by the use of a timing disc and pointer or the factory installed timing marks on the engine.
installed
on the engine and check alignment of engine drive coupling slot and magneto impulse coupling lulls. If not aligned, pull engine gear out of mesh (but not out of the oil seal) and turn to alignment. Push gear back into mesh.
NOTE NOTE On
10-520, TSIO-520 and 10-550 series
engines
the
timing
marks
are
located
on
the
alternator dn’ve gear. Remove the plug in front of number 6 cylinder to observe the TDC and advance
timing
The magnetos fire number 1
prepared for installation, to cylinder, in PREPARING THE
were
MAGNETO fOR ENGINE in this
INSTALLATION ON THE
chapter.
marks.
Place
new gaskets on magneto flanges and install carefully so drive coupling lugs mate with slots of engine dn’ve coupling. Install holding washers, lockwashers and nuts, but tighten only enough to permit turning the magnetos for final timing, without looseness. Install timing lights on the magnetos. o. With the engine still positioned to fire number 1 p. cylinder at the specified ETC rotate the right magneto in the direction necessary to cause the points to just break open as indicated by the timing light. Secure the n’ght magneto. q. n.
the magnetos
In all cases, it must be definitely detenined that the number cylinder is at the correct firing position on the
one
compression stroke, after
the crankshaft is turned in its
normal direction of rotation. d.
If
a
universal
timing
disc and
install the TDC locator in the top 1
cylinder, e. Slowly
rotate the
pointer is to be used, spark plug hole of number
engine
in the normal direction of
74-00-00
A9
Page5 Sep 27/84
SEECHCRAFT BONAHZA SERIES
MAI)T~ENANCE MANUAL
r. s.
Repeat steps "p" and "o" on the left magneto. Recheck the magneto setting to confirm the a 00
2" has not been exceeded. Tum the engine crankshaft t.
degrees in the opposite direction to normal rotation and bn’ng it back again until the advance timing mark is under the pointer on timing disc. At this point both timing lights should indicate, at the a
few
same
time, that the magneto points opened.
u.
If the
timing lights
do not
respond
at the same
time, loosen the magneto that is either early repeat the process outlined in step "p". v.
Remove the
timing lights
and
or
late and
reinstall the
electn’cal leads to the magnetos.
"END"
74-00-00
Page6 Sep 27/84
A9
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
DISTRIBUTION
MAINTENANCE PRACTICES
In the event that
an ignition harness or an individual lead is to replaced, consult the Magneto Wire Routing Diagram, Figure 1, to be sure that the harness is correctly installed. Mark the locations of damps and clips to be certain that replacement is accomplished properly. For the engine firing order and magneto fin’ng order, refer to Figure 1.
be
(Figure 1) Conventional dual
ignition is provided by two magnetos. In ignition system the left magneto fires the 1-3-5 lower and 2-4-6 top spark plugs, while the n’ght magneto fires the 1-3-5 top and 2-4-6 lower spark plugs. this
60----7
UPPER SPARK PLUGS
1GNITION SWITCH
LEFT MAG.(
I
IRIGHT MAG.
LOWER SPARK PLUGS ENGINE FIRING ORDER: MAGNETO FIRING ORDER:
1-6-3-2-5-4 1-2-3-4-5-6
Engine Magneto Wire Routing Diagram Figure 1
"END" 74-20-00
Pager May 9/80
CHAPTER
ENGINE
INDICATING
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CHAPTER Ti~
LIST OF PAGE EFFECTIVIN CHAPTER SECTION DATE
PAGE
SUBJECT
77-EFFECTIVITY/CONTENTS
1
..............Jan 28/81
77-00-00 CONTENTS
1
..............Jan 28/81
77-00-00
1
..............Jan 28/81
CHAPTER n
ENGINE INDICATING
TABLE OF CONTENTS CHAPTER SECTION
SUBJECT
SUBJECT
GENERAL............
PAGE
....77-00-00 .......1
Maintenance Practices TIT Indicator Calibration
......1
AICal Calibration Unit
......1
"END"
n-EFFECTIVITY/CONTEKTS
Page
1
Jan 28/81
8EECHCRA~ BONAMA SERIES MAINTENANCE MANUAL
MAINTENANCE PRACTICES
GENERAL
O
T/T INDICATOR CAL/BRATION (EA-I AND AFTER)
i
TIT calibration is manditory because the engine or turbo charger may be damaged by operating at excessive
temperatures (operation limited to 60 seconds).
at
above
a
TIT of
1650"F.
is
Q
CAUTION
turbocharger turbine blades, coking and excessive oil consumption may be caused by turbine inlet temperatures above 16500F. Damage
1;
25"1LO’V
the
to
excessive turbine
APPLY TORQUE SEAL HERE
CAUBRATION SCRNV
~36TC´•3W´•14
To prevent a turbine inlet over-temperature condition due to an inaccurate TIT indicator reading, the indicator should be checked every 100 hours and calibrated if required. The
following procedure
TIT Indicator Figure 1
may be used to check and
calibrate the ni indicator:
a.
Remove the TIT
intake manifold.
probe from the turbocharger
not disconnect the wires from the
(Do
probe.) to
b. Using 16500F.
the AICal test
equipment,
heat the
probe
If the TIT indicator reads 1650oF the indicator is if the reading is not 16500F the calibrated. properly calibration screw on the face of the instrument should be
airplanes piston engine EGT systems, if the red line temperature is exceeded by the TlT indicators, the calibration unit will quickly determine if the fault lies with the indication system or the engine. The following method will accomplish the TIT calibration test:
c.
adjusted d.
to obtain this
If the seal
by applying Figure i.
reseal
in
e.
a
reading.
was
broken
on
the calibration
small amount of torque seal
as
screw.
shown
a. Light the AICal unit and support it from the engine cowling. Place the TIT thermocouple into the comparator b. port of the AICal unit until it is touching the reference thermocouple.
Raise
c.
Reinstall the probe in the turbocharger intake
the
(9000C)
AICal
unit until the
is indicated
on
the unit’s
reference meter.
manifold.
Because both
d. same
ALGAL GALIBRATION UNIT (EA-I AND AFTER)
Distributors and Dealers,
provides
checking and,
ii
a
simple and
necessary,
accurate
recalibrating
are
measuring
the
temperature. If the register 1650’F (900~C). being refer to,the adjustment procedure outlined under TIT INDICATOR CALIBRATION in this chapter. e. Replace the TIT thermocouple in the turbocharger intake manifold. Lubricate the threads on the probe with Mll-A-907D anti-seize compound (41. Chart 1.
indicator
The AICal Calibration unit, available locally through the Beechcraft Aero or Aviation Center and International
thermocouples
temperature, the aircraft-installed TIT indicator
should indicate the
method for
heat of the
temperature of 1650"F
same
red line
tested does not
91-00-00).
"END"
77-00-00
Page
1
Jan 28/81
CHAPTER
OIL
BEECHCRAFT BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 79 L1ST OF PAGE EFFECTIVIN CHAPTER
SECTION DATE
PAGE
SUBJECT
,Oct 7183
79-EFFECTIV~P(/CONTENTS 1...............´•
77-00-00
CHAPTER 79
´•Oct 7/83
,.....,..,..,.,Oct 7/83
2.
OIL
TABLE OF CONTENTS CHAPTER
SECTION SUBJECT
SUBJECT
79-00-00
GENERAL
Description
PAGE
and
....,...1
Operation
........I
Maintenance Practices
System High Oil Temperature
..............1
Oil Cooler Removal
..~...........1
Oil Cooler Installation
....,,..,,....1
Oil
Break-in
Engine
.....,..,.....1
..............1
Oil
Recommended Oil Grades for
...,.....2
Engines
"END"
74EFFECTIVTTY/CONTENTS Pag´•l Oct 7183
BEECHCRAFT BONANfA SERIES MAINTENANCE MANUAL
DESCRIPTION AND OPERATION
GENERAL The
has
engine oil system is a full-pressure, wet sump type and a 12-quart capacity. The oil system consists of an oil
HIGH O1L TEMPERATURE Oil temperature is controlled by a spring loaded\lematherm oil cooler control valve. Refer to the Engine Overhaul Manual
for Vernatherm
thermostat tjypass control, oil oil indicator, temperature pressure indicator, oil pressure
specifications. This valve
relief valve, oil drain in the
not become contaminated with dirt or other
radiator and automatic
engine sump and an oil pump engine. The oil system operating temperatures are controlled by the automatic thermostat bypass control. The bypass control will limit oil flow through the cooler when operating temperatures are
which is
an
integral part
of the
below normal and will
should it become
permit the clogged.
oil to
bypass
the cooler,
will
MAINTENANCE PRACTICES
cooler
control
valve
foreign particles. operating properly remove the valve and clean it in solvent (16, Chart 1, 91-0000). Also inspect the valve seat for damage. No repairs can be made to this valve and readjustments are not recommended since special testing equipment is required. The travel of the valve can be checked by immersing the valve assembly in heated water. The minimum amount of If indications
that the valve is not
are
travel should be 0.090 inch
GENERAL
oil
operate property if the oil has
from
120"F
to
as
1700F. Replace
the temperature is raised
defective valves.
OIL SYSTEM OIL COOLER REMOVAL
Servicing the engine oil system primarily involves maintaining the oil at the proper level and changing the oil and filter at the recommended intervals. Under normal
operating conditions, the recommended number of operating hours between oil changes is 100 hours. When operating under adverse weather conditions, the oil should be changed more frequently. The engines should be warmed up to operating temperature to assure complete draining of the oil. The engine oil drain plug is secured with lock wire. To remove and install the engine oil filter, refer to
a.
Access
to the
oil cooler may be
gained through
the left cowl door.
Disconnect the oil temperature wire and the oil
b.
pressure line. Remove the nine bolts and washers c. baffling to the oil cooler. d. at the
Remove the five
attaching
nuts and
top of the oil cooler, and three
secun’ng
the
washers, (two
at the oil cooler
inlet).
Remove the oil cooler.
OIL FILTER REMOVAL and OIL FILTER INSTALLAT(ON in
Chapter
12-10-00. When
the oil and filter,
changing
always
check for metal contamination in the used oil.
OIL COOLER INSTALLATION
CAUTION If metal
of the
system is detected and the cause is corrected, the oil cooler should be replaced. In addition, flush out the system through the interconnected oil contamination
system plumbing
and
replace
or
oil
a.
install
b.
Install the
c.
Install the oil temperature wire and the oil
a new
pressure line. d. Start the
gasket
attaching
engine
at the oil cooler inlet. nuts and washers.
and check for
engine.
BREAK-IN ENGINE OIL The
new
airplane
is delivered with Rustband oil
6529, Type II) in the engine. This is
NOTE
a
oil and should be removed at 20 hours
Metal contamination that warrants oil cooler would
also
and proper
clean any other
accesson’es that will remain with the
replacement investigation.
leakage
operation and temperatures.
warrant
engine
later than 25 hours of
(MIL-Cpreventive of operation, but no
corrosion
operation. If the Rustband oil is
not
removed at the proper time, varnish may form in the engine. Oil conforming to MIL-L-6082 may be added to the Rustband
79-00-00
Pagel A6
Oct7/83
BEECHCRAFT BONANZA SERIES MAIMENANCE MANUAL
as necessary. After removing the Rustband oil, refill with Mll-L-6082 mineral oil which should be used until oil
oil
has stabilized. After oil
consumption has dispersant oil, complying with Continental Motors’ Specification Ml-lS-24Band Mll-L-22851, must be used. For several suitable engine oils,
consumption stabilized
both
RECOMMENDED OIL GRADES FOR ENGINES
an
break-in
ashless
and
after break-in,
Materials Chart, Item 2, in
Chapter
see
the Consumable
AMBIENT AIR
TEMPERATURE
RECOMMENDED VISCOSITY
91-00-00.
NOTE
Above
40´F
SAEdO
Below
40oF
SAE-30
or
10W30
It is recommended to
use a
75% power
setting
pen’od. Avoid over cooling caused by long power-off andlor rapid descents. dun’ng
the break-in
Al temperatures
I
15W50
"END"
79-08-00
Page2 Oct 7/83
A6
CHAPTER
STARTING
BEECHCRAFT BONANZA SER1ES MAINfENANCE MANUAL
CHAPTER 80 LIST OF PAGE EFFECTIVIN
CHAPTER SECTION DATE
PAGE
SUBJECT
´•May 9/80
1
80-EFFECTIVIN/CONTENTS
1´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•
80-10-00
9/80
2
CHAPTER 80
STARTING
TABLE OF CONTENTS CHAPTER SECTION
SUBJECT
SUBJECT
PAGE
´•´•´•´•´•´•´•´•´•80-10-00
CRANKING......~
Description and Operation Troubleshooting Starter System
.......f
Maintenance Practices
.......1
.......1 .......1
Starter Removal
........1
Starter Installation
........1
Starter Overhaul
........1
Starter Lubrication
.,......2
Starter Brushes
L’END"
80-EFFECTIVITY/CONTENTS Page 1 May glSO
BEECHCRAFT
BON‘ANZA SERIES MAINTENANCE MANUAL
CPANKING _DESCRIPTIPN
AND OPERATION
drive gear. The starter is located
on
the
n’ght ah side of the
engine. When the The Bonanza Sen’es
airplanes
are
each
equipped
with
current is
a
24-volt starter which engages with the
ignition switch is placed in the START position, supplied by the battery bus to energize the starter
relay, providing high
current
to!he starter through the relay,
_
TROUBLESHOOLlNG STARTER SYSTEM TROUBLE 1.
Starter
PROBABLE CAUSE
inoperative.
a
Circuit breaker
b.
Starter switch
REMARKS
tn’pped.
inoperative.
a.
Reset circuit breaker.
b.
Check
cockpit lights; if not operative, battery solenoid.
check switches and c.
Defective starter relay,
c.
Check continuity of starter system.
d.
Low
d.
Test
battery,
if low,
battery;
replace
or
start with
external power. e.
Open circuit,
f.
Defective
starting
motor,
e.
Check
f.
Check brushes, spn’ngs, condition, and
continuity
commutator.
CRANKING
MAINTENANCE PRACTICES
f.
Start the
mounting flange
engine
of circuit.
Replace
if necessary.
to check for oil seepage at the
and check for proper
operation.
STARTER REMOVAL a.
n’gM
Access to the starter may be
gained through
the
STARTER OVERHAUL
hand cowl door. b. c.
Disconnect the electrical wiring from the starter. Remove the two "palnuts", hex nuts and
washers from the mounting studs, and
remove
a.
c.
150-180
d. e.
~lnstall
procedures.
the starter.
STARTER INSTALLA T7ON
b.
Refer to applicable Vendor Publications for complete tests and maintenance
STARTER LUBRICAT1ON
O-n‘ng on the flange of the starter. the starter on the mounting pad. Install the attaching nuts and torque the nuts to inch-pounds. Secure the attaching nuts with "palnuts". Connect the electrical win’ng to the starter. a new
Position
No lubrication is required on the starting motor except at the time of overhaul. Soak new bearings in SAE 20 oil (2, Chart 1, 91-00-00) before installation. Saturate the felt oiling pad in the commutator end head with SAE 20 oil,Allow excess oil to
drain out before
installing
of
end head
on
motor. Put
a
light film
1,
shaft before
assembling
the motor.
NOTE Pn’or to
attaching
the starter to the
any rust, corrosion surface~s.of Also check all sure
they
are
or
CAUTION
engine, clean mounting
dirt from the
motor and ~e engio~ ground strap connections to make clean and tight.
Do not clean the starter in any degreasing tank grease dissolving solvents. Avoid excessive
or
lubn’cation.
80-1040
Pagel May 9/80
BEECHCRA~T BONANZA SERIES MAINTENANCE MANUAL
replaced when they have worn to 1/4 inch or less. Proper brush spn’ng tension with new brushes installed is 32-40
STARTER BRUSHES
ounces,
The starter brushes should slide make full contact
on
freely
in the holder and
the commutator. The brushes should be
the
"END"
80-10-00
Pagea May 9180
This tension is measured with
the brush
spn’ng
near
a
the brush and the
spn’ng leaves the brush.
scale hooked under
reading taken just as
CHAPTER
TURBINES
BEECHCRATT
BONANZA SERIES MAINTENANCE MANUAL
CHAPTER 81
TURBINES
TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT
SUBJECT
GENERAL
PAGE
.81-00-00
........1
Operation Description Turbocharger System (EA-1 and after) Troubleshooting Turbocharger System
.......,1
Maintenance Practices
........5
Manifold Pressure
........5
and
........2
Adjustment
........7
Turbocharger Leak Test Procedure Freeing Turbocharger Shaft Turbocharger Removal Turbocharger Installation Turbocharger Controller Removal Turbocharger Controller installation
........8 ........8 ........8 ........8
........8
"END"
81-CONTEHTS
Pag´•
1
Jan 28/81
BEECHCRAFT BONANZA SERIES MAIHIDIANCE MANUAL
CHAPTER Sl L/S~ OF PAGE ErrECfIVrrY CHAPTER SECTION
SU&IECT
PAGE
DATE
81-EFFECflVTTY
1.
Jan 20/82
81-CONIENTS
1
Jan 28/81
1
May May May May
81-00-00
2 3 4
9/80 9/80 9/80
5
9180 Jan 28/81
6
Jan 28181
7
Jan 28181
8
Jan 20/82
"END"
B1-E~ECTIVIT(
Page 1 A4
Jan 20182
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
GENERAL
DESCRIPTION AND OPERATION
TURBOCHARGER SYSTEM
(E4-I
and after)
controller, the wastegate actuator and engine oil pressure. Engine oil is supplied to the inlet port of the actuator which is
permanently restricted by a capillary tube. The actuator is hydraulic cylinder with oil pressure acting against spring tension. The piston inside the cylinder with an actuating rod attached, is heavily spring loaded in the up, or retracted position. As the oil pressure increases within the chamber an expander-type seal on the piston seals the upper oil chamber from the lower chamber, forcing the piston down, against spring tension, extending the actuator rod which moves the attached wastegate butterfly toward the closed position. A decrease in oil pressure allows spn’ng tension to return the piston, retracting the actuating rod, and retuming the wastegate butterfly to the open position. Oil from the a
turbocharger is fully automatic, requin’ng no additional cockpit, and is designed to increase the power output and efficiency of the engine by supplying compressed ait to the engine intake manifold. The power to drive the turbocharger is drawn from the exhaust gases passing through the turbine housing and over the turbine wheel to spin the shaft which is connected to the compressor. Ambient, filtered. air is then drawn in through the air inlet duct to the compressor where it is compressed and delivered to the throttle. As the engine power output increases, the flow of exhaust gases increases resulting in a proportionate increase in speed of the rotating assembly and turbocharger output. The turbochargef system (see Figure 1) consists of an exhaust driven turbine and centrifugal compressor mounted on a common shaft. The center section of the unit contains the bearings and
The
controls in the
outlet oil
port of the
actuator is not restricted at the actuator
but is pressure controlled controller which contains
by
the van’able absolute pressure aneroid bellows sensitive to
an
pressure changes in the induction manifold. As the pressure it senses decreases, it expands, extending a meten‘ng pin which reduces the flow of oil
through
the
body of
the unit
lubrication passages and supports the turbine and compressor housing. Lubrication to the center section is
and increases the pressure across the actuator diaphragm forcing the piston down and moving the wastegate toward
supplied by regulated engine oil pressure at the oil cooler providing a constant oil flow over the bean’ngs. The oil then drains by gravity into the sump tank located at the lowest point in the system and is returned by scavenge pump to the engine sump. Exhaust headers, crossover pipe, turbine inlet plenum, wastegate, exhaust by-pass duct, and tail pipe
the closed
make up the exhaust system.
Automatic control of the system is supplied by three principal components; the variable absolute pressure
equipped
position. The lower chamber of the controller an adjustable cam is linked to the throttle
with
designed so that the controller setting is varied proportionally to the amount of power the pilot selects with the throttle by moving the metering pin seat. The compressor output is automatically controlled at a constant pressure by the variable absolute pressure controller providing the engine fuel pump and injector nonles with the required flow and pressure at altitudes they are referenced to. The fuel flow gage diaphragm is also referenced to this pressure to prevent an erroneous reading. valve and is
81-00-00
Page 1 May 9~80
BEECHCRAFT BONANZA SERIES MAINTENANCE MANUAL
CYL
S
3
1
INDUCTION "r’
ENGINE OIL COOLER
THROrrLE CONNECTED VARIABLE CONTROLLER
IKIECTOR NO~LE SHROUDS CYL
2
4
6
TO FUEL PRESSURE VENT PORT
I:
INTAKE
III
11
FUEL PUMP
MGINEINTAKE
ALTERNArEAIR SOURCE
i \(MROT~LE COMROL
E
AMBIENT
AIRuRI CHECK VALVE
ENGINE; DRIVEN SCAVENGE PUMP
INTAKE
Al~ FiLTER
ASS
II II
I f~lrr F~ n~x
1~
it
~h I
L~IM
U~‘"Y
ii
ENGINE EXHAUST
111
1 I leeuows
II bl III II
II
i’
II
RENRNfO CRANKCASE
iii
TANK~ i if ~LWASrrGP;jE VENT
ONE WAY CHECK VALVE
EXHAUST TAILPIPE
i:
II ACTUATOR
V~L OVERBOOST VALVE
I
VENT OVERBOARD
CONTROL SYSTEM SUMPTANK
A76´•603-~
Schematic 1
Figure
TROU8LESHOOTiNG TURBOCHARGER SYSTEM INDICA TION i.
PROBABLE CAUSE
Turbocharger inoperative.
a.
Turbocharger
b.
Controller malfunctioning.
c.
Wastegate linkage
REMARKS
jammed.
a.
Replace.
b.
Replace.
not
c.
Adjust
in actuator inlet
d.
BacMlush with PD680 solvent
rotor
or
replace.
functioning. d.
Meten’ng jet blocked.
2.
Engine altitude.
81-00-00
Page May 9/80
has
low
critical
i, 91-00-00), 50 psi. inlet blocked.
e.
Turbocharger
f.
Controller pressure line blocked.
a.
Controller out of calibration.
sensing
e.
Remove obstruction.
f.
Remove obstruction.
a.
Replace.
(16, Chart
BEECHCRAFT BONANtA SERIES MAINTENANCE MANUAL
TROUBLESHOOT1NG TURBOCHARGER SYSTEM
INDICA TION 2.
Engine altitude.
PROBABLE CAUSE
has
low
critical
REMARKS
b.
Controller malfunctioning.
c.
Wastegate
d.
Leak in exhaust system.
b.
Replace.
c.
Adjust.
d.
Eliminate any leaks.
e.
BacMlush with PD680 solvent, 50
f.
Remove obstruction.
g.
Eliminate any leaks.
a.
Replace.
b.
Backffush with PD680 solvent. 50
c.
Remove obstruction.
d.
Eliminate any leaks.
(Continued)
e.
out of
Meten’ng jet
n’g.
in actuator inlet
psi.
blocked.
3.
Manifold pressure surges at altitude.
f.
Controller pressure line blocked.
g.
Compressor discharge loose oi leaking.
a
Controller
b.
sensing
duct
malfunctioning.
Metering jet
in actuator inlet
psi.
blocked.
4.
5.
Engine
Oil
smokes at idle.
leaking
from actuator
c.
Controller pressure line blocked.
d.
Compressor discharge loose or leaking.
e.
Leak in exhaust system.
e.
Eliminate any leaks.
a.
Turbocharger jammed.
a.
Replace.
b.
Seal
b.
Replace.
c.
Turbocharger bean’ng leaking.
seals
c.
Replace.
a.
Actuator
ruptured.
a.
Replace.
a.
Controller out of calibration.
a.
Replace.
b.
Controller
b.
Replace.
c.
Controller pressure sensing line broken.
c.
Replace.
d.
Wastegate linkage functioning.
d.
Adjust
ruptured in
piston
sensing
duct
controller.
seal
drain. 6.
High
manifold
pressure at
take-off.
malfunctioning.
not
or
replace.
81-0090
Page May
3
9/80
BEECHCFIAFT BONANZA SERIES MAINfENANCE MANUAL
TROUBLESHOOTING TURBOCHARGER SYSTEFA
INDICA TION 6.
PROBABLE CAUSE
High manifold pressure (Continued)
at
e.
Controller pressure line blocked.
pressure at
a.
b.
take-off. 7.
Low manifold
REMARKS
sensing
e.
Remove obstruction.
Controller out of calibration,
a.
Replace.
Controller
b.
Replace.
c.
Remove obstruction.
duct
d.
Eliminate any leaks.
in actuator inlet
e.
BacMlush with PD680 solvent, 50
f.
Eliminate any leaks.
take-off.
c´•
malfunctioning,
Controller pressure
sensing
line blocked. d.
Compressor discharge loose or leaking.
e.
Meten’ng jet
psi.
blocked.
8.
High fuel
pressure at altitude.
f.
Leak in exhaust
a.
Leak in pressure reference line at fuel pressure line.
a
Eliminate any leaks.
Pressure
line
b.
Remove obstruction.
Leak in pressure reference
a.
Eliminate any leaks.
b.
system.
reference
blocked. 9.
Low fuel pressure at altitude.
a.
line at fuel pump.
b.
Pressure
reference
line
b.
Remove obstruction.
pumps not
on or
c.
Repair
a
Replace.
b.
Adjust.
c.
Eliminate any leaks.
blocked.
10.
11.
Turbocharger overspeeding.
Fcessive
noise
or
vibration.
c.
Auxiliary fuel inoperative.
a.
Controller
b.
Wastegate
c.
Compressor discharge loose or leaking.
a.
Improper bean~ng
malfunctioning. out of
n’g. duct
lubn’cation.
a.
or
replace.
Clean
or replace oil line; clean oil strainer, supply oil pressure. If trouble still persists, overhaul turbocharger.
and
b.
Leaking engine
intake
or
b.
exhaust manifold. 12.
Engine power.
81 40-00
Page 4 May 9/80
will not deliver rated
a
Clogged
manifold system.
a.
Tighten gaskets Clear all
connections or as
necessary.
ducting.
replace manifold
BEECHCFIAFT BONANZA SERIES MAIMENANCE MANUAL
TROUBLESNOOTING TURBOCHARGER SYSTEM
INDICA TION 12.
PROBABLE CAUSE
Engine
will not deliver rated
power.
(Continued)
b.
Foreign
material
compressor
REMARKS
lodged
in
turbine
b.
Disassemble and clean.
c.
Throughly clean
d.
Tighten gaskets
or
impeller. Excessive dirt build-up in
c.
compressor. Service air cleaner and check for leakage.
compressor. d.
Leak
in
engine intake
or
exhaust manifold,
Rotating assembly bean’ng
e.
connections as
Overhaul
e.
or
replace manifold
necessary.
turbocharger.
seiture.
GENERAL
MAINTENANCE PRACTICES
d. maximum
After
engine warm-u’p,
position
of 2600
n’ch mixture. Check and
MANIFOLD PRESSURE ADJUSTMENT
pressure
adjustment
pressure controller.
The wastegate is controlled by engine oil pressure, which is regulated by the van’able absolute pressure controller. For this reason manifold pressure is quite sensitive to ail and temperature as~well as ambient. temperatures. It has been determined that the manifold pressure will vary: (1) 0.2 in. Hg. per 10"F change in oil temperature, (2) 0.3 in. Hg per 10 psig in oil pressure and (3) 0.05 in. Hg per 10"F change in ambient temperature.
advance the throttle to its
2700
propeller rpm and full (if required) adjust the manifold
screw
on
the absolute variable
Loosen the
jam nut and rotate the counterclockwise to increase, or clockwise to decrease manifold pressure, then retighten the jam nut. adjustment
screw
pressure
The best time to make
airplane
adjustments
is
shortly after
the
has been flown. Under the conditions described in
step "c", the manifold pressure should be 36 in. of Hg.
NOTE If the manifold pressure is adjusted with
oil~emperature at(la00F1 71
to
82aC (160
to
38~C
1800F)
engine
rather than the
recommended,
a
decrease in manifold pressure will occur when the ail temperature increases to the normal
operating Locate the absolute variable pressure controller mounted on the top of the throttle body in the left side of the engine accessory compamnent. a.
b.
Check the controller-to-throttle
adjustment
as
linkage for
proper
follows:
range. Under these conditions, a decrease in manifold pressure of 1 to 2 in. of
Hg below the rated 36 in, of Hg will occur along with a corresponding decrease in fuel flow,
if,
pressure
on
the other hand,
is
temperature at 1.
the
manifold
adjusted with engine oil (2300F) 110"C, a corresponding
Position the controller lever to allow full travel. Ensure that the throttle push-pull cable will allow full
increase in manifold pressure above 36.0 in. Hg will occur on the next flight if the oil
travel.
temperature is then 2.
shown in
With the controller lever in the
Figure
2 and the throttle
plate
arm
stop pin, adjust the connecting linkage stop
position allowing arm new
position against the nuts to
0.01 to 0.02 inch gap between the
a
cam
and the controller maximum
stop (see Figure 2). On a engine this adjustment should already be made by
Continental Motors. Start and
2700 rpm.
run
the
engine
to
much
lower.
A
enn~chment in full rich fuel flow
above the value obtained at 36.0 in. Hg will also occur since the full rich schedule is a function of both deck pressure and RPM. These characteristics must be taken into consideration when
adjustments
bn’ng the engine oil temperature up to (1601 to 180"F) 71" to 82~C. Adjust the oil pressure to 40 to 50 psig (45 psig preferred) at 2600 to c.
corresponding
are
manifold
made.
It is
pressure that
important
manifold pressure and fuel flow be within the prescribed limitations simultaneously dun’ng a maximum power run-up. Incorrect manifold pressure settings will cause erroneous fuel flow
readings.
81-00-00
Page
5
Jan 28/81
BEECHCFIAFT BONANZA SERIES MAINTENANCE MANUAL
VARIABLE ABSOLUTE PRESSURE CONTROLLER
MANIFOLD PRESSURE ADJUSTMENT SCREW
CONTROLLER LEVER (IN MAX. THROTTLE POSITION)
(0.5" HS~TURN) .01
GAP
/O
O JAM NUT CAM ARM
CONNECTING LINKAGE STOP NUTS
STOP PIN
I
i
I
O
DO NOT CHANGE THIS ADJUSTMENT SETTING
I
\V
"IDLE MIXTURE ADJUSTMENT SCREW
THROTTLE 80DY IDLE SPEED ADJUSTMENT THROTTLE PLATE ARM
VIEW LOOKING AFT
Throttle
Body
and Variable Absolute Pressure Controller
Figure
81-00-00
Page
6
Jan 28/81
2
A36TC-282-12
BEECHCRAFf BONANZA SERIES MAINTENANCE MANUAL
CAUTION
7.
The wastegate flanges. (With the exhaust position.)
valve in the open Do not exceed 36 In.
longer
Hg
manifold pressure
dun’ng ground
than 10 seconds
run
checks.
NOTE The
wastegate flanges must be aligned correctly and care taken on assembly to prevent damage to the thin metal gaskets.
Fly the airplane 10 15 minutes or more at high power settings, then land and check the manifold pressure at maximum power setting before shutting off the engine. Readjust to 36.0 in. Hg as required. e.
8. 9.
TURBOCHARGER LE4K TEST PROCEDURE
the turbo outlet. 10.
The
turbocharger system may
The turbo inlet gasket and flange bolts. The clamp holding the exhaust tail.pipe to
be checked for leaks in the
The
slip joint
between the exhaust elbow
and the turbo inlet.
induction, exhaust and air reference sections of the system as
outlined in the
following procedure. NOTE
a
Plug the exhaust stack
with
large rubber
a
The
stopper. b.
Remove the tube between the induction filter and
the compressor inlet.
Plug
the inlet with
a
must be
slip joint
will not be
a
leak
good tight joint. a
fit. However, it
large tubber
stopper. c. Plug the manifold drain hose extending out the right side of the cowl opening. d. Remove one spark plug from any cylinder and rotate the propeller until the intake valve for the cylinder is in the open position. Proceed with the test as described below. When the intake valve test is complete, rotate the propeller until the exhaust valve for the cylinder is in the open position and again test the system as described
11.
Rigging of
the
wastegate
in the
completely
closed position.
NOTE
Rigging of the wastegate is checked by removing the wastegate assembly from the exhaust bypass, plugging the oil outlet line and applying an air pressure of 40 to 50 psi to the oil inlet line of the wastegate actuator. Observe the valve movement. Adjust the linkage
below.
Install a regulator valve to a shop air supply line. e. Apply approximately 5 psi air pressure to the turbocharger system through the spark plug port of the cylinder described in step "d".
between the actuator and the valve to obtain
following areas of the system should tested for leaks by applying a soap solution. i.
The
1.
The hose
clamps
on
he
tolerance of
a
.005 to .025 inch between the
wastegate butterfly and bore.
the induction manifold
of the engine. 2.
The
clamp
at the compressor
discharge
After
completing
the
preceding steps,
remove
all
plugs
and
reassemble the induction system.
outlet. 3.
The
clamps
on
the compressor
discharge
elbow at the throttle inlet. 4.
The clamps at the throttle outlet to the riser
FREEING -TURBOCHARGER SHAFT
manifold. All fittings in the compressor discharge lines to the fuel nozzles and fuel reference pressure 5.
pressure gage. 6. The exhaust ilanges at the
ports. (With the
cylinder
exhaust valve in the open
exhaust
position.)
deposits may form in the area of the turbocharger piston ring seal as a result of water vapor accumulation ii the airplane is subjected to short intervals of engine operation. This condition occurs only when the unit is new and combustion deposits have not formed a Rust
turbine shaft
81-00-00
Page 7 Jan 28/81
BEECHCRAFT BONANtA SERIES MAINTENANCE MANUAL
protective barn’ei on the seal surfaces. Although these deposits do restn’ct, and even stops shaft rotation, they are not harmful to subsequent turbocharger operation once they are removed sufficiently to give free shaft movement,
access
the the
When this condition is noted, remove the exhaust discharge stack and apply WD-40 penetrating oil or Mouse Milk (40,
Chart 1, 91-00-00), iiberally´•to the around the turbine shaft seal. After to tum the shaft, A
confirm
can
behind the wheel
few minutes, attempt, the shaft end with a soft
light tap on freeing the
mallet will often assist in
free, the engine
area a
be started and
shaft, Once the shaft is
power check made to the ground or in flight,
a
turbocharger output either on
opening
b.
on
the left side of the
Install the bolts which
mounting bradtet. install the gaskets c. turbocharger.
secure
airplane. turbocharger
the
and the turbo inlet
assembly
to
on
d.
Install the inlet to the heater exhaust system. covers from the oil lines and oil ports. Install the oil lines. f. Install the tail pipe. Tighten the V-band coupling to e.
40
Remove the dust
inch-pounds, Tap
tension, then torque
the
pen’phe~y
to 40
Install the turbocharger air inlet duct and g. the flex duct damps. h. i.
TURBOCHARGER REMOVAL
j.
tighten
Install the heat shield over the turbocharger. Connect the red and yellow TIT wires.
Install the induction tube which contains the relief tighten the damps.
valve. Install and
Open
a
the
engine cowl
on
the left side of the
airplane. b.
Remove the two louvered
left side of the
access
openings on the
d.
Remove the induction tube with the relief valve,
Remove the
heat shield
from
over
the
turbocharger. Loosen the flex ducts on the g. duct, and remove the air inlet duct, h.
Remove the tail
turbocharger air inlet
i.
air inlet duct.
access openings on the engine compartment. Close the cowling on the engine compartment.
TURBOCHARGER CONTROLLER REMOVAL a
Remove the
b.
Remove the
c.
Reinove the manifold pressure reference line.
d.
Remove the oil lines. Install dust
e.’
Remove
linkage linkage
to the throttle. to the
ihe safety
wire
butterfly.
on
covers.
the two
larger
mounting bolts.
pipe by removing
the
clamp
and
Dolt. dust
ram
air inlet duct.
by removing the clamps and lifting the tube away from the engine. Disconnect the red and yellow TIT wires. e, f.
Install the heater
Install the two louvered
m.
Remove the heater
ram
k. I.
left side of the
engine compartment
c.
Remove the oil lines from the
f.
Remove the three mounting bolts.
g.
Remove the turbocharger controller.
turbocharger. Install
covers.
Remove the inlet to heater exhaust system. Remove the turbo inlet assembly above the
i. k.
TURBOCHARGER CONTROLLER INSTAUATION
turbocharger. i. the
Remove the bolts that
mounting
the
turbocharger
to
opening.
Install the
Place the
turbocharger
controller in its
mounting
b,
Install the mounting bolts. wire the two appropriate bolts. d. Remove the dust covers from the oil lines and install the oil lines. c.
TURBOCHARGER INSTALLATION a.
a
location.
Remove the turbocharger through the forward
m.
access
secure
bracket.
turgocharger
through
e.
the forward
Safety
install the manifold pressure reference line. linkage to the throttle butterfly.
f.
Install the
g.
install the
linkage
to the throttle.
"END"
814090
Page8 Jan 20/82
1
of the band to distn’bute
inch-pounds.
A4
i
CHAPTER
CHARTS
Qeechcr~ft BONANZA SERIES
MAINTENANCE MANUAL
CHAPTER 91
CHARTS
TABLE OF CONTENTS SUBJECT
PAGE
91-00-00 Chart 1 Consumable Materials
Charts 2, 4 and 5
(Effecthrity: All)
(Effectlvity: All)
installation of Flared
Fittlngs (Effectivlty: All)
Chart 3 Thread Lubricants
(Effectivity: All)
1 10 10 10
91-Contents
Page 1 A18
Aug 18/95
aeechcraft BONANZA SERIES
MAINTENANCE MANUAL CHAPTER 91
CHARTS
LIST OF PAGE EFFECTIVIP/ CHAPTER-SECTION-SUBJECT
91-Effectivity 91-Contents
91-00-00
PAGE 1
Aug 18/95
1
Aug 18~95
1
Aug Aug Aug Aug Aug Aug Aug Aug Aug Aug
2 3 4
5 6
7 8 9 10
A18
DATE
18/95 18/95 18/95 18/95 18/95 18/95 18/95 18/95 18/95 18/95
91-Effectivity Page 1 Aug 18/95
Cj;~eechcraft BONANZA SERIES MAINTENANCE MANUAL
NOTE the basic number of each Military Specification is included in the Consumable Materials Chart. No attempt has been made to update the basic number with the letter suffix that designates the current issues of the various specifications,
Only
Suppliers listed as meeting Federal and Military Specifications are provided as reference only and are not specifically recommended by Beech Aircraft Corporation. Any product conforming to the specification may be used.
CHART1 CONSUMABLE MATERIALS MATERIAL
PRODUCT
SPECIFICATION 1 OOLL
Fuel, Engine
1.
(biue),
or
(Effectivity: All) SUPPLIER
100
(sreen) MlL-L-6082
Engine Oils (BREAK-IN)
2.
(First 20
to 30 hours of
Atlantic Richfield Co., Los Angeles, California 90071
Castrolaero 113
Castrol Oil Canada Ltd., P.O. Box 3, New Toronto Postal Station, Toronto, Ontario
(Grade 1065)
a new or
remanufactured
Formula LB-1123
engine)
CAUTION
Do not mix oils of different brands
or
oils of different
Any approved aircraft engine oil graded at 1100 (SAE 50) or 1065
types produced by the
same
manufacturer.
Grade 1100
Champlin
Mobil Aero Red Band
Mobii Oil Corporation, Shoreham Building, Washington, D.C. 20005
Aeroshell Oil 100
Shell Oil Company, 50 West 50th St., New York, New York 10020
Phillips
Phillips Petroleum Co., Bartlesviile, Okla’homa 74003
Oil Refining Co., P.O. Box 552, Enid, Oklahoma 73701
(SAE 30) (AFTER BREAK-IN)
TCM MHS-24B MlL-L-22851
66 Aviation
Oil, Type A; XIC Aviation
Multiviscosity
Oil
SAE 20W50: XIC Aviation
MultiviscosS Oil SAE 25W60
91-00-00
A18
Page 1 Aug 18/95
aeechcraft BONANZA SERIES MAINTENANCE MANUAL CHART
CONSUMABLE MATERIALS MATERlAL
SPEC1FICATION TCM MHS-24B
(Effectivity: AII) (Confinued) SUPPLIER
PRODUCT Aeroshell OilW Aeroshell Oil W SAE 15W50
Shell Oil Company, 50 West 50th St., New York, New York 10020
Conoco Aero S
Continental Oil Company, Ponca City, Oklahoma
Texaco Aircraft Engine Oil-Premium AD
Texaco, Inc.,
Mobil Aero Oil
Corporation, Building, Washington, D.C. 20005
135 E. 42nd Street, New York, New York 10017
Mobil Oil
Shoreham
Castrolaero AD Oil
Castro Oil Canada Ltd., P.O. Box 3, New Toronto Postal Station, Toronto, Ontario
Penntoil Aircraft Engine Oil
Pennzoil Company, Drake Building, Oil City, PA 16301
Sinclair Avoii
Sinclair Refining Co., 500 Fiffh Ave., New York, New York 10020
Esso Aviation Oil Enco Aviation Oil
Exxon
BP Aero Oil
BP Oil Corporation, BP (North American) Ltd., 620 Fifth Avenue, New York, New York 10020
Quaker State AD Aviation Engine Oil
Quaker State Oil
Company, U.S.A.
Box 2180, Houston, Texas 77001
Refining Corporation, City, PA 16301
Oil
Delta Petroleum Co., Inc., P.O. Box 10397, Jefferson, Louisiana 70181
Delta-Avoil Oil
Engine
Union Oil Company of California
Aviation AD
Gulf Oil Corp., 439 7th Ave., P.O. Box 1166, Pittsburg, PA 15230
Union Aircraft Oil HD
Gulfpride
3.
Corrosion Preventive
MIL-C-6529
Type
II
Anti-Corrode No.205
CitiesServiceOilCo., 60 Wall Tower, New York, New York
Rust Foil No. 652-2
Franklin Oii Corp., Bedford, Ohio 44146
Compound (Engine Oil)
91-OQ´•00
Page 2 Aug 18/95
A18
4;3eechcr~ft BONANZA SERIES
MAINTENANCE MANUAL CHART1 CONSUMABLE MATERIALS (Effectivity: MATERIAL
SPECIFICATION
AIl) (Confinued)
PRODUCT
SUPPLIER
Kendex No. 7038
Kendall Refining Co., 1177 Kendall Ave.,
Nude Oil 105
Daubert Chemical Co., 4700 S. Central Ave., Chicago, Illinois 60638
Protect VA
Penreco 106 S. Main St. Butler, PA 16001
Ferro-Gard 1009-G
Ranco Laboratories Inc., 3617 Brownsville Road,
Bradford, Pennsylvania 16701 4.
Preservative Oii
MlL-L-46002, Grade 1
Pittsburgh, Pennsylvania 5.
Corrosion Preventive Compound, Solvent
MIL-C-16173, Grade II
Braycote
137
Bray Oil Co., 1925 Marianna St., Los Angeles, California 90032
Cutback,
Cold-Application Petrotech 1-4
Penreco P.O. Box 671, Butler, PA 16001
Valvaline TECP/L 890
Ashland Oil Co., 1409 Winchester Ave.
Ashland, Turco 5351
6.
Grease, Automotive
MIL-G-10924
Kentucky’41101
Turco Products, Inc., Division of Purer Corp., Inc., 26400 South Main, Wilmington, California 90746
Shell A and A Grease Shell Oil Co., One Shell Plaza P.O. Box 2463 Houston, TX 77001 Cato Code 5210
Grease Go., Inc., Cato Oil P.O. Box 26868,
Oklahoma 73126
7.
Refrigerant,
Air
Conditioner
(Charging)
City, Oklahoma
SA8263242
Southwest Petro Chem Inc., 1400 S. Harrison, Olathe, Kansas 66061
Sunoco C-352-EP
Sun Oil Company, P.O. Box 426, Marcus Hook, Pennsylvania 19061
Racon 12
Racon Inc., 6040 S. Ridge Road, Wichita, Kansas 67215
91-00-00
A18
Page 3 Aug 18/95
I
aeechcraft BONANZA SERIES MAINTENANCE MANUAL CHART~ CONSUMABLE MATERIALS (Effectivity: MATERIAL
SPECIFICATION
AIl) (Confinued)
PRODUCT
SUPPLIER
Genetron 12
8.
500
Viscosity Oil, (Air
Allied Chemicals P.O. Box 4000R, Morristown, New
DuPont E I De Nemours and Company, Inc., Organic Chemicals Dept., 1007 Market Street, Wilmington, Delaware 19898
Suniso 5GS
Virginia Chemicals inc., 3340 W. Norfolk Road Portsmouth, VA 27303
Compressor) Texaco WF100
Hydraulic
Fluid
Jersey 07960
Freon 12
Conditioner
9.
Corp.,
MlL-H-5606
Texaco Inc., 135 East 42nd Street, New York, New York 10017
756[3
Brayco
Bray Oil Co., 3344 Medford Street, Los Angeles, California 90063
FED 3565
Standard Oil of California, 225 Bush Street, San Francisco, California 94104
Breathing
MIL-0-27210
Lubricating Grease (Aircraft and
MlL-G-23827
10. Aviator’s
Oxygen 11.
Supermil Grease
No.
A72832
instruments, Low
American Oil Co., 910 S. Michigan Ave., Chicago, Illinois 60605
High Temperature) Royco
12.
Lubricating Grease
13.
Oxygen System Leak Testing Compound
14. Rubber Hose
SolventorWhiteSpirits
Royal Lubricants Co., River Road, P.O. Box 95, Hanover, New Jersey 07936
Aeroshell Grease 7
Shell Oil Company, One Shell Plaza P.O. Box 2463 Houston, TX 77001
Andok-B
Exxon Co. U.S.A., P.O. Box 2180, Houston, Texas 77001
MIL-L-25567 MIl-H-5593
Lubripiate
15. Grease
16
27A
PD680orBritish 245
Specification
777
Fiske Brothers Refining Co., 129 Lockwood, Newark, New Jersey 07105
Stoddard Solvents
(Mineral Spirits)
91-00-00
Page 4 Aug 18/95
A18
BONANZA SERIES MAINTENANCE MANUAL CHART 1 CONSUMABLE MATERIALS (Effectivity: SPECIFICATION
MATERIAL
SUPPLIER
PRODUCT
Presstite 576
17. Sealer
All) (Confinued)
Presstite-Keystone Engineering Co., 3900 Choteau Ave., St. Louis, Missouri 63110
EC 1814
18. Sealer
Minnesota
Mining Manufacturing Co., 3M Center St. Paul, Minnesota 55101
19. Toluol
TT-T-548
(Toluene)
20. Zinc Chromate Primer
Mll-P-8585
21. Sealer
PR-1440
Courtaulds Aerospace Inc., 5454 San Fernando Rd., Glendale, CA 91209
22. Sealer
PR1221B1/2
PRC Products Research Chemical Corp.,
Burbank, California CRC-2-26
23. Solvent
Corrosion Reaction Consultants Inc.,
Philadelphia, Pennsylvania MIL-R-7575
24. Resin
25. Wash Primer
Laminac 4116
American Cyanamid Co., S. Cherry St., Wallingford, CT 06492
D(2016G
Ameron Industrial
Coatings Division, P.O. Box 2153
Wichita, Kansas 67201 26.
TT-N-95
Naphtha
27. Paint
Stripper
Turco 4260
Turco Products Inc., 26400 S. Main Los Angeles, California 90646
No. 27
Minnesota
28. Deleted
29.
Tape
Tape
Mining Manufacturing Co., 3M Center St. Paul, Minnesota 55101
30.
Tape, Anti-Seize, Tetrafluoroethylene dispenser (I-inch)
Johnson Johnson Inc., Permacel Division, U.S. Highway 1, New Brunswick, New Jersey
MIL-T-27730 with
08901 31.
Methyl ethyl
ketone
32. Black Rubber Cement
TT-M-261
EC678
Mining Manufacturing Co.,
Minnesota
3M Center, St. Paul, Minnesota 55101
91-00-00
Ai8
Page 5 Aug 18/95
I
CS3eechcraft BONANZA SERIES MAINTENANCE MANUAL CHART1
CONSUMABLE MATERIALS
MIL-C-8514
etching primer
34. Wash Primer
(See
SUPPLIER
PRODUCT
SPECIFICATION
MATERIAL 33. Acid
(Effectivity: Al)) (Continued)
Item
25.) 35.
T6070
Thinning Catalyst
Ameron Industrial
Catalyst
Coatings Division, P.O. Box 2153
Wichita, Kansas 67201 U.S. Paint
6165 Base
36. Primer Base
Lacquer
Chemical Co., 1501 No. Belmont, Wichita, Kansas 67208
37.
AA-92-C-4A
Catalyst
Catalyst
U.S. Paint Lacquer Chemical Co., 1501 N. Belmont, Wichita, Kansas U.S. Paint Lacquer Chemical Co.,
38. Urethane Primer
1501 N. Belmont, Wichita, Kansas
Presstite-Keystone Engineering Co.,
Presstite 176
39. Sealer
3900 Choteau Ave., St Louis, Missouri 63110 40.
Penetrating Oil
41. Anti-seize
Compound
MIL-A-907D
Mouse Milk
Worldwide Aircraft Filters Corp., 1685 Abram Ct., San Leandro, California 94577
Anti-seizeCompound
Fel-Pro Inc., 7450 McCormick, Skokie, Illinois 60076
C5A
42. Anti-seize
Graphite
Compound,
Armite Laboratories,
W-P-236
1845-49 Randolph St., Los Angeles, California 90001
Petrolatum
43. Thread Lubricant
Parker
Threadlube
Appliance Co.,
Cleveland, Ohio 44. Sealer
Dow Coming, S. Saginaw Road,
Silastic 1 40
Midland, Michigan 48641 45.
Sealing Compound
R-134-B Perfect Seal
Ford Motor Co.,
Dearborn, Michigan 46.
Grease, Aircraft General MIL-G-81322
Mobilgrease
Mobil Oil Corp. Shoreham Building, Washington, D.C. 20005
28
Purpose Wide Temperature Range 47.
Lubricating Grease (Gear)
Mobil
Compound
636
Mobil Oii Corporation, Shoreham Building, Washington, D.C. 20005
91-00-00
Page 6 Aug 18/95
A18
aeechcraft BONANZA SERIES MAINTENANCE MANUAL CHART1 CONSUMAELE MATERIALS fEffectivity: MATERIAL 48.
SPECIFICATION
PRODUCT Aeroshell Grease No.
Lubricating grease Onlheel Bearing)
49. Lubricant Moiybdenum Disulfide Powder
Ail) (Confinued)
5
MIL-M-7866
Molyikote
Z
SUPPLIER
Shell Oil Company, One Shell Plaza P.O. Box 2463 Houston, TX 77001 Wilco Co., 4425 Bandini Blvd. Los Angeles, CA 90023
Moly-Paul Products Ltd., Noble Road, London, England 50. Silicone
Compound
MIL-S-8660
DC-4
Dow Coming Corp., S. Saginaw Road
Midland, Michigan 48640 Union Carbide 333 Woodward Ave. P.O. Box 44,
Y-2136
Tonawanda, N.Y. 14150 XS 4005
51.
Lubricating
Oil
(Gear)
General Electric Silicon Products Dept. Mechanicville Rd. Waterford, N.Y. 12188
101-380016 or MIL-L-2105C Grade 75W
BEECHCRAFT Aero or Aviation Centers and International Distributors and Dealers Gulf Gearlube HT SAE 75W-90
Gulf Oil Canada, Limited Research Development
Dept. 2489 North Sheridan Way Sheridan Park, Ontario L5K 1A8 Oriofiat W75/M
Fiat Lubricant S.P.A. Via Santena, 1 10029 Villasteilone
(Tornio) italy 52. Adhesive
1300L
EC1403 Commercial
or
(Normal Designation) 63.
Coating
54. Translucent Adhesive
Minnesota Mining Manufacturing Co. 3M Center St. Paul Minnesota 55101
Produ~s,
Alodine 1200, 1200S, 1201
Amchem Inc., Spring Garden St., Ambler, PA 19002
R7V-108
General Electric Co., Silicone Products Dept., Waterford, NY 12188
91-00-00 A18
Page 7 Aug 18/95
aeechcraft BONANZA SERIES MAINTENANCE MANUAL CHART~ CONSUMABLE MATERIALS (Effectivity: MATERIAL 55.
AII) (Confinued)
No. 474
Tape
SUPPLIER
PRODUCT
SPECIFICATION
Minnesota
Mining Manufacturing Co., 3M Center, St. Paul, MN. 55101 U.S. Paint, Lacquer and Chemical Co., St. Louis, MO.
MIL-P-23377
56. Primer,
Epoxy-Polyamide Matterhorn White No. 61 60
57. Urethane Paint
Obtain
VV-K-211
58. Kerosene
Plexiglass Polish
and
P-P-560
P/N 403D
Cleaner
61. Paste Wax
Parko Anti-Static
Park Chemical Co., 8094
Meguiar’s MGH-10
Mirror Bright Polish Co. Inc., P.O. Box 17177 In/ine, GA 92714
Johnson’s J-Wax
S.C. Johnson Son, Inc., 1521 Howe St., Racine, WI 53403
Simonize
545
Sealing/Locking, Hydraulic
Conditioning Refrigerant
65. Oil
(Air Condition)
Military Ave., Detroit, MI 48204
Simonize Co., P.O. Box 368 Greenville, S.C. 29602 Loctite
Corp.,
705 No. Mountain Rd., Newington, CT 06111
PST 592
63. Sealant, Thread
64. Air
Permotex Inc., Kansas City, KS 66115
Polish
Paste
62.
Locally
J.T. Baker Chemical Co., 222 Red School Lane, Phillipsburg, N. J. 08865
59. Hexane
60.
U.S. Paint, Lacquer and Chemical Co. St. Louis, MO
Obtain
R-134a
RL-100S
Loctite Corp., 705 N. Mountain Rd., Newington, Ct 06111
Ester Oil
Locally
ICI Americas Inc., 3411 Silverside Road Wilmington, DE 19850
66. Adhesive/Sealant
Loctite 209
Loctite Corp. 705 N Mountain Rd Newington, CT 06111-1411
91-00-00
Page 8 Aug 18/95
A18
Qeechcraft BONANZA SERIES MAINTENANCE MANUAL CHART 1 CONSUMABLE MATERIALS (Effectivity: MATERIAL 67
Locquic Primer
SPECIFICATION
AII) (Continued)
PRODUCT Primer N
SUPPLIER Loctite Corp. 705 N Mountain Rd Newington, CT 06111-1411
91-00-00
Page A18
9
Aug 18/95
aeechcraft BONANZA SERIES
MAINTENANCE MANUAL
CHARTS 2, 4 AND 5
INSTALLATION OF FLARED FITTINGS
(Effectivity: All)
Charts 2, 4 and 5 were removed from Chapter 91 and added to Chapter 20. Chart 2 of 91-00-00 became Chart 1 of Chapter 20-06-00. Chart 4 of 91-00-00 became Chart 2 of Chapter 20-01-00. Chart S of
91-00-00 became Chart 1 of20-01-00.
(Effectivity: All) When installing flare fittings, make sure they are properly lubricated in accordance with Chart 3. Tighten the
fittings in accordance with Chart 00. Do not overtighten.
CHART 3 THREAD LUBRICANTS (Effectivity:
Type
of Line
Type
of Thread
1 in
Chapter
20-06-
All)
Type
of
Lubricant, Item, Chart 1
MIL-H-5606
Hydraulic
Loctite 545 Fuel
Alum, Brass, Steel
W-P-236
Oil
Alum, Brass, Steel
W-P-236
Oxygen
Tappered
MlL-T-27730 Size 1
Straight
None
Tappered
Loctite 592
Straight
None
Pitot and Static
Refrigerant Freon
Sunisco 5 GS
or
WF-100 NOTE
Lubricate engine fittings lubricated.
only with the fluid that will flow through the lines. Air lines
are
not to be
91-00-00
page 10 Aug 18/95
A18
