000_BO105_Section_00

BO 105 Training Manual General

General Description

For training and information only

October 2005 (DRAFT)

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Table of Contents The Development of the BO 105 . . . . . . . . . . . . . . . . . . . . . . . . . General Describtion of the BO 105 . . . . . . . . . . . . . . . . . . . . . . Structural Groups of the BO 105 . . . . . . . . . . . . . . . . . . . . . . . . Maintenance Concept . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Documentation of the BO 105 . . . . . . . . . . . . . . . . . . . . . . . . . . . EUROCOPTER BO 105 Documentation . . . . . . . . . . . . . . . . . Other Manufacturer’s Documentation . . . . . . . . . . . . . . . . . . . The EUROCOPTER Documentation . . . . . . . . . . . . . . . . . . . . . . Maintenance Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Illustrated Parts Catalog . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cockpit Arrangement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flight Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pitot and Static Pressure System . . . . . . . . . . . . . . . . . . . . . . . Pitot Tube Heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Air Speed Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rate of Climb Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Outside Air Temperature Indicator . . . . . . . . . . . . . . . . . . . . . . Clock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Compass . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Monitoring Instruments . . . . . . . . . . . . . . . . . . . . . . . . . n1 RPM Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . n2 RPM Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Torque Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Turbine Outlet Temperature Indicator . . . . . . . . . . . . . . . . . . . .


4 6 10 14 16 16 18 20 20 22 24 26 28 28 30 32 32 32 34 34 34 36 38 38 38 38 38

System Monitoring Instruments . . . . . . . . . . . . . . . . . . . . . . . . . Mast Moment Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Triple Oil Temperature Indicator . . . . . . . . . . . . . . . . . . . . . . . . Triple Oil Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Quantity Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Pressure Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . nRO Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Warning Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operator Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Overhead Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Handling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Parking and Mooring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hoisting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jacking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

40 40 40 40 42 42 42 44 48 50 52 54 56 58

This training document comprises the following ATA chapters: Overhead Panel Instrument Panel Warning Lights Analog Instruments LH and RH Section of Instrument Panel Pitot--Static System Hoisting, Jacking Shoring Towing, Mooring Parking, Storage


ATA 24 ATA 31 ATA 31 ATA 31, 34 ATA 30, 34 ATA 34 ATA 07 ATA 09 ATA 10

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INTENTIONALLY LEFT BLANK



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The Development of the BO 105 History

In addition, MBB set requirements for:

The first MBB helicopter with glass fiber rotor blades was the single blade helicopter BO 102, a captive trainer, operating for the first time in 1957. In 1961 the single seater BO 103 followed, the only helicopter to fly with one rotor blade. In 1962/63, a new hingeless rotor system was created, and successfully tried on an Allouette II, 1966 in Marignane, France. From 1960 to 64 the high speed helicopter BO 46 was designed with the Derschmidt rotor system. In 1964 a new concept of a light transport helicopter was established to fulfill the requirements of the seventies and eighties: the BO 105. Market research had shown the need for a multi purpose helicopter of the 2 ton class.

Requirements The following requirements were set: --------

4 -- 6 seats, max. speed over 230 km/h, high safety standards, high performance, operational dependability, simple maintenance, quick change--of--mission adaptability.


-- good overall stability, -- high manoeuverability, and -- controllability under all flight conditions. The last 2 requirements were met by the Bölkow hingeless rotor system.

Bölkow Rotor System The main rotor blades are manufactured from glass--fiber--reinforced plastic (GRP) and are directly connected to the rigid titanium rotor head. Flap and lead--lag movement is accomplished by the elasticity of the blades. The only possible relative movement between the blades and rotor head is during changes of pitch. This arrangement is referred to as a hingeless rotor system.All rotor reaction forces are transmitted directly from the rotor system through the main rotor mast into the fuselage.The construction of the rotor head is very simple. The number of parts have been reduced to approximately 20 % of a conventional or articulated system because the drag hinges, flapping hinges and such components as dampers have been omitted.


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Flight Trials The easy handling of the helicopter under all conditions was demonstrated during the flight trials. The main stages are listed below: In January, 1966, the first flight of the hingeless three--blade rotor system, installed in the Allouette II helicopter, was successfully performed by the Aerospatiale helicopter chief test pilot. On February 16th, 1967, MBB helicopter chief test pilot performed the successfull first flight of the BO 105, which was equipped with a hingeless, four--blade rotor system. During the next 4 years, four prototypes of the BO 105 passed all tests required successfully. At the end of 1970, the certification by the German Airworthiness Authority (LBA) of the BO 105 was completed.

BO 105 Series S stretched version (e.g. CS, CBS, DBS), airframe stretched 10 inches. BO 105 CB, CBS (e.g. DB,DBS) two Allison 250--C20B engines of 420 SHP (313 kW) each, take--off weight 2400 kg, main transmission ZF FS 72 B (MT 2x86 %), BO 105 CB--4, CBS--4 (DB--4, DBS--4) take--off weight increased from 2400 kg to 2500 kg. BO 105 CB--5, CBS--5 (DB--5, DBS--5) take--off weight 2600 kg with external load, high performance main rotor blades (Type II), modified hydraulic system, different TCI intervals.

Versions

BO 105 CB--5, CBS--5 (DB--5, DBS--5) “Super Five” the main transmission ZF FS 72 E is installed for VTOL certification according JAR PART 29 CAT. A.

BO 105 Series A, two Allison 250--C18 engine, 317 SHP (236 kW) each, take--off weight 2100 kg, main transmission ZF FS 72 A or FS 72 B (MT 2x85 %).

BO 105 LS A--3 take--off weight 2600 kg, two Allison 250--C28C engines of 500 SHP (368 kW) each, main transmission ZF FS 112.

BO 105 Series B, two MAN 6022 single shaft turbines of 320 SHP (240 kW) each (not launched).

BO 105 LS A--3 “Superlifter” take--off weight 2850 kg with external load, high performance main rotor blades (Type II), the modified hydraulic system, and improved tail rotor blades.

BO 105 Series C, two Allison 250--C20 or 250--C20B engines of 400 SHP (300 kW) each, take--off weight 2300 kg, main transmission ZF FS 72 A or FS 72 B (MT 2x79 %), BO 105 Series D additionally, further requirements of the CAA have been met.



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General Describtion of the BO 105 General The BO 105 is a multi purpose twin engine helicopter in the 2.5 t class with five seats in the basic version.

Tail Rotor System

Main Rotor System The main rotor blades are manufactured from fiber--reinforced plastic and are directly connected to the rigid titanium rotor head. Flap and lead--lag movement is accomplished by the elasticity of the blades. The only possible relative movement between the blades and rotor head is during changes of pitch. This arrangement is referred to as a hingeless rotor system. All reaction forces are transmitted directly from the rotor system through the main rotor mast into the fuselage. The construction of the rotor head is very simple. The number of parts have been reduced to approximately 20 % of a conventional or articulated system because the drag hinges and flapping hinges have been omitted. The main rotor gearbox is a three stage light weight reduction gearbox produced by ZF (Zahnradfabrik Friedrichshafen).

Fuselage The fuselage structure is a conventional semi--monocoque construction made in a modular design concept, consisting mainly out of aluminum sheet metal. Bottom shell, doors, engine cowlings and access panels are made of composite material.


The cabin is accessible through six doors: two hinged doors for the crew, two sliding doors for the passengers, and two aft clamshell doors for the rear compartment.

The helicopter is equipped with a semi--rigid two blade tail rotor. The blades are made from glass--fiber--reinforced plastic (GRP). The tail rotor is mounted to a light weight aluminum sheet metal tail boom made in a semi--monocoque construction and controlled via rods routed from the pedals to the input of the titanium tail rotor head.

Flight Controls The main rotor is controlled by rods and bellcranks, routed from the control elements via the cabin sideshell to the transmission deck mounted hydraulic system. The hydraulic system is a tandem system, i.e. it consists of two separate systems, which operate independently of each other (fail safe system). Under normal operating conditions only one system (No.1 main system) functions as a booster, the second system (No.2 standby system) stay in standby. In case of a failure in the main system, it will be immediately cut off and the standby system will be actuated automatically to ensure safe operation and landing.


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Landing Gear The BO 105 has two cross tubes and two skids. The cross tubes are constructed to absorb forces during touch down of the helicopter, by bending.

Fuel System The fuel system comprises three fuel tanks, a fuel supply system, a refueling and ventilation system and a monitoring system. The main tanks and the separated supply tank, with overflow to the main tank, are installed under the cabin floor.

Engines The BO 105 is powered by two Allison 250--C20B engines with a power output of 420 shp each.

Electrical System The fully redundant 28 V DC electrical system is supplied by two generators and a battery.



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BO 105 Training Manual General Dimensions

Streched airframe area



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BO 105 Training Manual General Cargo Loading Configurations

! NOTE

S--versions: Cargo length + 254 mm.



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Structural Groups of the BO 105 General

30 Tail Unit

The BO 105 multi--purpose helicopter is divided into nine structural groups, which constitute the basic structure of the documentation.

The tail unit comprises:

10 Lifting System The lifting system comprises:

2 tail rotor drive with intermediate transmission and tail rotor transmission,

1 main transmission,

3 tail rotor,

2 rotor brake system,

4 tail rotor blades.

3 main rotor system,

40 Flight Control System

4 main rotor blades.

The flight control system comprises:

20 Fuselage

1 main rotor controls with collective and cyclic control system,

The fuselage comprises:

2 tail rotor controls,

1 fuselage with tailboom mounting cone, doors and windows,

3 hydraulic system.

2 cowlings.

50 Landing Gear

1 tailboom with vertical fin and horizontal stabilizer,

The landing gear comprises: 1 landing gear with two skids and two crosstubes.



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BO 105 Training Manual General Structural Groups of the BO 105

60 Power Plant

10 Lifting System

20 Fuselage

30 Tail Unit 70 Standard Equipment

40 Flight Control System

90 Instruments and Electrical System

50 Landing Gear For training and information only


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60 Power Plant

90 Instruments and Electrical System

The power plant comprises:

The instruments and electrical system comprises:

1 engine,

1 instrument system,

2 fuel system with tank,

2 electrical system.

3 lubrication system including oil cooler, 4 fire walls, 5 engine operation and control.

70 Standard Equipment The standard equipment comprises: 1 pilot and copilot seats, 2 cabin equipment, 3 interior panelling, 4 cabin vent system, 5 mast moment indication system.

80 Optional Equipment ECD offers a wide range of optional equipment, which is shown in a separate volume of the Maintenance Manual and in the Flight Manual. Optional equipment is not described in this Training Manual.



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BO 105 Training Manual General Helicopter Number Plate

Call Sign

D--HTRAINER

BAUREIHE MODELL

Helicopter Number Plate


BO 105 CB--5

GERÄTE--NR. REGISTER--NO.

3025

WERK--NR: SERIAL--NO.

S--251

BAUJAHR YEAR OF MANUF.

1978


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Maintenance Concept General

Intermediate Level

“Maintenance” covers all scheduled and unscheduled maintenance activities. It also applies to the on condition maintenance. It is based on condition monitoring by visual checks/inspections and diagnostic features such as chip detectors, filter bypass indicators, boroscope access, failure indications, built-in tests, warning lights etc.

The intermediate level covers repairs on/off helicopter, extended periodical inspections as specified in the aircraft maintenance manual. To meet these tasks, maintenance facility, qualified personal, test equipment and special tools are required. ! NOTE

Maintenance Levels BO 105 maintenance is split into three maintenance levels:

Depot Level (D)

-- Organizational Level (O) -- Intermediate Level (I) -- Depot Level (D)

Depot level covers major repair or overhaul at the manufacturer or at authorized service stations under industrial premises. More extensive tools/test equipment and specialized personnel are necessary.

Organizational Level The organizational level covers tasks of the daily servicing, maintenance checks, inspections for condition, exchange of components (e.g. LRU) and quick, simple repairs as specified in the maintenance manual (MM). The work generally takes place at the operators site. After an “on the job training” these checks can be carried out by pilots, mechanics and operators.


The maintenance manual covers all tasks of organizational level and intermediate level.

! NOTE

Documentation and spares for depot level tasks will be delivered to authorized customers only.

! NOTE

Information about inspections and intervals are to be found in chapter Inspections of this training manual.


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BO 105 Training Manual General Maintenance Concept

Maintenance Scheduled Unscheduled On Condition

Organizational Level (O)

Daily servicing, maintenance checks inspections for condition, exchange of LRU’s. acc. to MM -- Can be carried out by a mechanic or by the pilot (i.e. main transmission servicing).

Intermediate Level (I)

Repair on/off the helicopter extended periodical inspections acc. to MM -- maintenance facility, qualified personnel, test equipment and special tools are required (i.e. main transmission change).

Manufacturer/authorized customers only Depot Level (D)


Major repair or overhaul at the manufacturer or at authorized service stations acc. to special documentation. Tools/test equipment and specialized personnel are necessary (i.e. main transmission overhaul).


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Documentation of the BO 105 General

Mechanic’s Documentation

The documentation of the BO 105 consists of two main groups:

The mechanic has available:

-- EUROCOPTER -- BO 105 helicopter documentation, -- other manufacturer’s documentation.

EUROCOPTER BO 105 Documentation The EUROCOPTER BO 105 documentation consists of three main groups:

Maintenance Manual (MM), Repair Manual (REM), Illustrated Parts Catalog (IPC), Ground Support Equipment (GSE), Wiring Diagram Manual (WDM), Operation Manual (OPM).

Operator’s Technical Control Documentation

Pilot’s Documentation

The following documents are kept by the operator’s technical control:

The pilot has available three documents: -- Flight Manual, -- Log Book, -- Pilot’s Checklist. ! NOTE

-------

Flight Manual, Log Book, and Pilot’s Checklist must always be present in the helicopter.

-------

Historical Records, LOAP, Alert Service Bulletins (ASB), Service Bulletins (SB), Alert Service Information (ASI), Service Information (SI).

! NOTE



The valid manuals inclusive revision status are published in the LOAP.

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ECD Helicopter Documentation BO 105

Mechanic

Pilot

Flight Manual Log Book Pilot’s Checklist

Historical Record

MM

LOAP

REM

Alert Service Bulletins

IPC

Service Bulletins

GSE WDM OPM


Operator’s Technical Control


Alert Service Informations Service Informations

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Other Manufacturer’s Documentation General The other manufacturer’s documentation comprises: -------------

engine Operation and Maintenance Manual (OMM), engine Illustrated Parts Catalog (IPC), engine Comercial Service Letters (CSL), Comercial Engine Bulletin (CEB), Allison Service Letter (ASL), Installation Bulletin (IB), Manual for the transmission (integrated in BO 105 MM, issued by EUROCOPTER), Manaul for the dual hydraulic system (integrated in BO 105 MM issued by EUROCOPTER), avionics systems, special optional equipment, Marvel Balancer (integrated in BO 105 MM), Tracking Balancing (acc. Operation Manual of the manufacturer).



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Other Manufacturer’s Documentation

OMM Engine IPC Engine CSL, CEB, IB, ASL


Transmission (integrated in MM) Dual Hydraulic System (integrated in MM)


Avionics Systems Special Optional Equipment

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The EUROCOPTER Documentation General

Arrangement

The following EUROCOPTER--Documentation is described:

The maintenance manual is arranged according to the main assemblies (structural groups). Additionally in a chapter general, basic information about the helicopter is given and in a chapter 100 some subchapters are added for special maintenance information.

-- MM -- IPC -- REM Repair and overhaul work to be performed according to the Repair Manual (REM) is only permissible after completion of a special maintenance course.

Chapters

Maintenance Manual

The chapters give information about the subassemblies of the respective main assembly. The chapters are numbered by two, or in case of standard (70) and optional equipment (80) by three digits. The first digit corresponds to the main assembly, the following to the subassemblies.

General

Paragraphs

The maintenance manual (MM) is used for maintenance procedures, repair, and inspections to be performed on the helicopter. In combination with the maintenance manual, the following documents are used:

The chapters are subdivided into paragraphs, which give detailed information about the subassemblies, troubleshooting and maintenance procedures. The paragraphs are numbered in sequence (e.g. paragraph 31--1).

-- repair manual (REM) for repair of assemblies, which are not described in the maintenance manual; -- wiring diagram manual (WDM) to assist inspections of the electrical system; -- illustrated parts catalog (IPC) -- vendor documentation for repair of assemblies which are not manufactured by ECD.


Example As an example of the manual numbering the maintenance instructions of the tail rotor drive is described: -- first step: the tail rotor drive belongs to chapter 30-- tail unit; -- second step: the tail rotor drive is listed as the second subassembly of chapter 30 (chapter 32); -- third step: the maintenance instructions are described in paragraph 32--4.


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BO 105 Training Manual General The Maintenance Manual MM General

01 Dimensions and Reference Planes

02 General Instructions

03 Consumable Materials

Lifting System

Fuselage

11

21

Main Transmission

Fuselage

12

22

Rotor Brake System

Cowlings

13 Main Rotor System

04

14

Self Manu-facturable Special Tools

Main Rotor Blade

Tail Unit

31 Tail Boom Assembly

32 Tail Rotor Drive

33 Tail Rotor

Flight Control System

Landing Gear

Power Plant

41

51

61

Main Rotor Controls

Landing Gear

Engine

Refer to Table of Contents Chapter 700

Optional Equipment

Refer to Table of Contents Chapter 800

Instruments and Electrical System

Inspections and Procedures

91

101

Instrument System

Inspections and Airworthiness Limitations

42

62

92

102

Tail Rotor Controls

Fuel System

Elecrical System

Rigging of M. Rotor and Tail Rotor Controls

43

63

103

Hydraulic System

Lubrication System

Measuring the Helicopter

34 Tail Rotor Blade

Standard Equipment

64

104

Fire Walls

Weighing the Helicopter

05

65

105

Ground Handling

Engine Operation and Control

Ground Run/ Functional Test Flight

06

107

Refueling and Defueling


Balancing of Tail Rotor System


106 Tracking and Balancing of Main Rotor Sytem

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Illustrated Parts Catalog General

Part Number

The Illustrated Parts Catalog (IPC) contains exploded views of parts belonging to the BO 105. The arrangement of the IPC is shown in the figure below and is described in the following.

The part number is built up by the drawing number and the revision index. The drawing number is arranged as shown in the figure below. The revision index is a letter.

Arrangement

No letter or letter “a” defines the original part, “b” the first, “c” the second, “d” the third change.

The IPC is divided into three sections: -- section general contains an introduction explaining how to use the catalog, a vendor list, a list of all incorperated service bulletins and a list of abbreviations; -- section numerical index contains two alpha--numerical listings, one of all electrical identification indices mentioned in section detailed parts list and one of all part numbers mentioned in section detailed parts list; -- section detailed parts list contains exploded views of the assemblies and is subdivided in accordance with the nine structural groups.

Page Numbering The pages of the sections general and numerical index are numbered consecutively within each section. In section detailed parts list the figures (exploded views) in each chapter are used for a consecutive numbering and the parts list belonging to a figure is also numbered in this manner. 10--00--00 FIG. 03 Page 2


Model Codes The following Model Codes are used: ------

A = BO105 A C = BO105 D E = BO105 CBS--5 G = BO105 CB--5 I = NBO--105 CB

-----

B = BO105 C D = BO105 S F = BO105 DBS--5 H = BO105 DBS

The codification according to serial numbers means e. g.: -- 481--999: This part is to be used on helicopters starting with serial number 481 -- 161--480: This part is to be used on helicopters starting with serial number 161 to 480 -- 001--060: This part is to be used on helicopters starting up to serial number 060 There are no use codes in the major assembly group 80--00--00 “Optional Equipment”. The valiidity of the items of this group has to be checked by the cusomer individually.


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BO 105 Training Manual General Illustrated Parts Catalog IPC

General

Numerical Index

Detailed Parts List

Introduction Vendor List SB List Abbreviations

Electrical Identifier Index Parts Numerical Index

9 Structural Groups

Structural Group 90

Structural Group 10 Lifting System 10--00--00

Electrical System 90--00--00

Part Number Arrangement Example: 105--31802.02c 105 -- 3

1802 . 02

c Change Index (2nd Change) Item Number (Bushing). Special tool if letter W followed by a number Component Number (Tail Rotor Shaft Assy) Number of Structural Group (Empennage) Aircraft Type (BO 105)

This part number describes the “Bushing of the Tail Rotor Shaft”



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Cockpit Arrangement General The BO 105 is provided with several units for monitoring, warning and control purposes. These units are installed to certain control panels.

Control Panels The control panels installed in the BO 105 are subdivided into: -----

Overhead Panel Instrument Panel Operator Panel Center Console



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BO 105 Training Manual General Cockpit Arrangement Overhead Panel Outside Air Temperature Indicator Power Lever

Magnetic Compass Instrument Panel Operator Panel

Stick Copilot

Stick Pilot

Pedals

Collective Lever Copilot Center Console For training and information only


Collective Lever Pilot

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Instrument Panel General

Engine Monitoring Instruments

Indicating instruments located on the instrument panel are used to monitor the flight operations of the helicopter.

The engine monitoring instruments comprise:

Panel Subdivision The panel is divided into: -----

flight instruments, engine monitoring instruments, system monitoring instruments, warning lights.

Flight Instruments The flight instruments comprise: --------

air speed indicator, altimeter, rate of climb indicator, gyro horizon, directional gyro, clock, magnetic compass.

-------

triple RPM indicator (n2 eng. 1, n2 eng. 2, nRO), torque indicator (eng. 1, eng. 2), TOT indicator eng. 1, TOT indicator eng. 2, n1 indicator eng. 1, n1 indicator eng. 2.

System Monitoring Instruments The system monitoring instruments comprise: ------

mast moment indicator, triple oil temperature indicator, triple oil pressure indicator, fuel quantity indicator, fuel pressure indicator.

Instrument Lighting Instrument lighting is provided and operated via the switch INSTR LIGHT on the operator panel and may be dimmed by a potentiometer INSTR LIGHT on the instrument panel.

Warning Lights The warning lights are located in the warning panel together with a test switch. For training and information only


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BO 105 Training Manual General Instrument Panel Fire Warning Light

Gyro Horizon

Warning Lights

Pitot Heating Indicator

PITOT HEATING

Test Switch

Altimeter Air Speed Indicator Instrument Light Brightness Control Test Switch Warning Lights

Directional Gyro TEST

Rate of Climb Indicator

WARN.-- LIGHTS

Clock n2 (eng 1+2) + nRO Indicator

Mast Moment Indicator

TOT Indicator (eng 1) TOT Indicator (eng 2)

Torque Indicator (eng 1 + 2) Triple Oil Temperature Indicator

n1 Indicator (eng 1) n1 Indicator (eng 2)

Triple Oil Pressure Indicator


Fuel Quantity Indicator Fuel Pressure Indicator


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Flight Instruments Pitot and Static Pressure System

Location

General

There are two static and one ram air pressure pick--up (pitot tube). The static pressure pick--ups are located on the left and right outside of the helicopter in front of the FWD cross tube (near bottom of the fuselage). The pitot tube is located on the right side below the static pressure pick--up.

The Pitot static system supplies static pressure to the Vertical speed indicator and the Altimeter, and pitot and static pressure to the Airspeed indicator. The instruments give readouts of airspeed, altitude and the vertical speed. The pitot--static system consists of:

The static pressure pick--ups pass on the static atmospheric pressure.

-- Pitot tube -- Tube and hose line -- 2 Static ports

Pitot Tube

Static pressure is exerted on the instruments via the static ports and the tube/hose line assembly. The pitot tube supplies pitot pressure to the airspeed indicator and the Air data computer. The pitot tube can be heated to prevent the formation of ice. A tee with cap assembly is installed in the tube/hose line assembly to drain condensation water and to connect test equipment. ! NOTE

Static Pressure Pick--up

The pitot tube is subjected to the dynamic pressure during forward flight of the helicopter.

The instruments function is independent of any electrical power supply.



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BO 105 Training Manual General Location of the Pitot and Static Pressure System

Dynamic and Static Pressure System Schematic Pitot Tube Static Pressure Pick--up, right

Air Speed Indicator Altimeter Drain Plug

CLIMB

1000 FT PER MIN UP

DOWN

Static Pressure Pick--up, left

Pitot Tube

Static Pressure Pick--up

Static Pressure Pitot Pressure

Rate of Climb Indicator



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Pitot Tube Heating General To prevent icing, the Pitot tube can be heated electrically. The Pitot tube heating system consists of: -- Pitot tube heating, -- Pitot heating switch, -- Electromechanical indicator. The heating element is installed inside the pitot tube, heating the front section of the probe. On ground, the pitot tube heating should be switched on only for a short period. Pitot tube heating is not cooled down by the airspeed and will overheat with the risk of burning out.

Power Supply The pitot heating is supplied with electrical power from the main busbar PP21 via the circuit breaker 1HG at the lower right side of the instrument panel and the toggle switch 4HG in the operators panel. It is labelled PITOT HEATING and has the two positions ON and OFF. The function of the system is indicated by the electro--mechanical indicator 2HG located at the top of the Instrument Panel. It is a non illuminated, electro--mechanical indicator, labelled PITOT HEATING. If Pitot heating is OFF, white sectors are visible on a black background. If Pitot heating is ON, the front side of the indicator is black, no white sectors are visible.



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BO 105 Training Manual General Pitot Tube Heating

Connecting Flange Airframe

Main Busbar PP21

Hose Line

Circuit Breaker 1HG

Contact Pins Toggle Switch PITOT HEATING 4HG

Pitot Tube Heating 3HG

Electro Mechanical Indicator PITOT HEATING 2HG Pitot Tube



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Air Speed Indicator General

-- the rotating scale indicates ten thousands per digit.

The air speed indicator measures the actual speed of the helicopter relative to the surrounding air (IAS).

Operation A membrane capsule for the pitot and the static pressure transmits the motion to a gear, which is connected to the pointer of the instrument. The pointer indicates the pressure difference between pitot pressure and static pressure.

Indication Range The indication range is calibrated from 10 to 150 knots with an interval of 5 knots.

Altimeter Operation The altimeter measures static pressure changes in the atmosphere via an aneroid capsule. These static pressure changes are equivalent to changes in altitude.

Indication The scale is marked in feet. Three pointers indicate the altitude at any given moment:

The daily barometric pressure can be set by turning the setting knob at the instrument.

Rate of Climb Indicator General The rate of climb indicator, also called vertical speed indicator (VSI), shows the rate of climb or descent in feet/min.

Operation The rate of climb indicator is a pressure capsule instrument, which measures the static pressure variations resulting from altitude changes. When a change in altitude has been completed, the pressure is equalized via a permanent capillary bleed and the pointer returns to its initial “0” position.

Indication Range The indication range for the rate of descent is from 0 to 6000 feet/min and for the rate of climb from 0 to 6000 feet/min. The scale is divided into intervals of 100 feet up to 1000 feet/min, and intervals of 500 feet between 1000 and 6000 feet/min. ! NOTE


-- the large pointer indicates hundreds, -- the circle pointer indicates thousands,



00 -- 32

BO 105 Training Manual General Pitot and Static Pressure Flight Instruments

Dial Pointer 10000 ft Red Line, VNE

Rate of Climb

Short Pointer 1000 ft

Yellow Range, 10--45 kts

CLIMB

1000 FT PER MIN INHg

mb

UP

DOWN

ENCODING

Green Range, 45--145 kts Air Speed Indicator


Barometric Scale

Large Pointer 100 ft

Setting Knob Altimeter


Rate of Decent Rate of Climb Indicator

00 -- 33


Outside Air Temperature Indicator

Compass

General

General

The outside air temperature indicator is located on the upper side of the right windshield. It is a rod--shaped bimetallic thermometer.

The magnetic compass is mounted above the instrument panel at the center beam of the cabin frame and serves as an auxiliary compass. It operates on the principle of a liquid--dampened magnetic compass and indicates the heading of the helicopter to magnetic north.

Indication The outside air temperature indicator has one pointer, which indicates on two scales with two different graduations: -- centigrade graduation (°C) at the inner scale, indication range from: --50 to +60 °C, -- Fahrenheit graduation (°F) at the outer scale, indication range from: --70 to +150 °F.

Clock

Indication The compass card is located on a float with markings at 10 deg intervals. The cardinal directions are marked N, E, S and W, and numbers indicate the heading in 30 deg increments. The float is free to move in all three dimensions with silicone fluid as the damping medium. Deflections caused by interfering magnetic fields are compensated by the compensation device. ! NOTE

General


The clock is a mechanical chronometer with an additional pointer used for the stop--watch function. The outer scale of the clock is a rotating bezel that can be used to measure elapsed time.



00 -- 34

BO 105 Training Manual General Outside Air Temperature Indicator, Compass, Clock

Outside Air Temperature Indicator Start/Stop/Reset Knob

11 12 1 2 10 3 9 8 4 7 6 5 Compass Clock 6

3

N

33 30

Compass Card

Winding Knob

Compensation Device



00 -- 35


Instrument Markings General

Operation Ranges and Limits

For easier reading of the instruments, pointers and scales are marked with numbers, letters, and colors.

To localize the ranges and limits of the instruments, the scales are marked as follows:

Markings To identify the indications of the units, pointers and scales are marked as follows: left engine right engine main rotor transmission main tank supply tank

1 and/or red 2 and/or green R and/or black M S


Transient limit Start limits Min. and max. limits OEI 2.5 min OEI MCP Takeoff power or Caution Range Normal or Continous Range Calibration point


red point red triangle red radial red dashed radial yellow dashed radial yellow arc green arc white radial

00 -- 36

BO 105 Training Manual General Instrument Markings (Example)

Takeoff or Caution Range Transient

Normal or Continous

Start

Normal

40

60

Max. Limit

80

20 100 0

% 120 TORQUE

OEI MCP OEI 2.5 min

Transient



00 -- 37


Engine Monitoring Instruments General

Operation

The performance of each engine is monitored by four indicating systems:

The system comprises three tacho--generators, which drive three synchronous electric motors in the RPM indicator.

-----

n1 RPM indication, n2 RPM indication, torque indication, turbine outlet temperature indication.

! NOTE

Torque Indicator General

The instruments function are indipendent of any electrical power supply.

Operation The torque indicating system is hydraulically operated, using engine oil pressure which is proportional to engine power. The transfer to the instrument is done via air.

n1 RPM Indicator General The system indicates the gas producer turbine RPM (n1). There is one system for each engine. The RPM is indicated in percent.

Operation The system comprises a tacho generator, which drives a synchronous electric motor in the RPM indicator.

Turbine Outlet Temperature Indicator General The turbine outlet temperature (TOT) gives information about the operating condition of the engine. One instrument for each engine indicates the TOT in degrees centigrade.

Operation

n2 RPM Indicator General A triple RPM indicator indicates the power turbine RPM (n2) of each engine and the RPM of the main rotor (nRO). For training and information only

The torque indicator is used to monitor the torque of each engine in per cent. This is necessary to match power sharing between the engines.

A thermocouple with four probes senses an average temperature of the turbine gases between the gas producer and the power turbine. The DC voltage thus generated is proportional to the TOT, and is indicated by a millivoltmeter system within the indicator.


00 -- 38

BO 105 Training Manual General Engine Monitoring Instruments

n1 Indicator


Torquemeter

n2 eng. 1, n2 eng. 2, nRO Indicator


TOT Indicator

00 -- 39


System Monitoring Instruments General

Triple Oil Temperature Indicator

The operation of the helicopter system is monitored by five indicating systems:

General

-------

mast moment indicator, triple oil temperature indicator, triple oil pressure indicator, fuel quantity indicator, fuel pressure indicator, nRO indicator.

The instrument gives information about the oil temperature of the two engines and of the main transmission.

Operation The system consists of three temperature sensors and three cross--coil measurement units inside the indicator.

Triple Oil Pressure Indicator Mast Moment Indicator

General

General The BO 105 is equipped with an hingeless rotor and therefore high bending moments on the rotor mast can occur. The pilot has to avoid extreme cyclic stick motions on the ground with the rotor turning. The bending of the rotor shaft is monitored by the mast moment indication system.

The instrument gives information about the oil pressure of the two engines and of the main transmission.

Operation The system consists of three pressure controlled potentiometers and three cross--coil measurement units inside the indicator.

Operation The system comprises a strain gauge (Wheatstone) bridge arrangement within the mast, an inductive rotary transmitter, and an indicator on the instrument panel.



00 -- 40

BO 105 Training Manual General System Monitoring Instruments

CAL TEST

LIMIT

Mast Moment Indicator


Triple Oil Temperature Indicator


Triple Oil Pressure Indicator

00 -- 41


Fuel Quantity Indicator

nRO Indicator

General

General

The instrument monitors the fuel quantity of the main tank and of the supply tank.

A triple RPM indicator indicates the power turbine RPM (n2) of each engine and the RPM of the main rotor (nRO).

Operation

Operation

The system consists of two float wire resistance transmitter and cross--coil measurement units within the indicator.

The system comprises three tacho--generators, which drive three synchronous electric motors in the RPM indicator. ! NOTE

Fuel Pressure Indicator

The instrument function is indipendent of any electrical power supply.

General The fuel pressure of the supply tank pumps is indicated upstream of the engine fuel pumps.

Operation The system consists of a pressure transmitter whose resistance varies proportionally, and is indicated via cross--coil measurement units.



00 -- 42

BO 105 Training Manual General System Monitoring Instruments

30

M

S

kp x10

20

1

4

1 2

kp/cm Press

1

2

2

10 0

0

Fuel Quantity Indicator


2

2

6

0

0

Fuel Pressure Indicator


n2 Engine 1, n2 Engine 2, nRO Indicator

00 -- 43


Warning Lights General

RPM

Some parameters of the helicopter systems do not require constant monitoring by the pilot, unless preset limits are exceeded or definite malfunctions occur. For this reason, warning lights are installed in the instrument panel. They are arranged in a warning light panel.

If latest Warning Box Type K--DW02/01 is installed, “RPM” will illuminate and an audio signal is triggered if

Fire Warning Light The red fire warning lights, one for each engine, are marked with an “F” and located beside the warning light panel. In the event of overtemperature (fire) in one of the engine compartments, the corresponding warning light will illuminate. Functional testing of the system is made by the push--to--test switch “TEST FIRE”. A separate lamp testing can be done by depressing the warning lights itselfs.

n1 Split 12 % nRO 75--95 % nRO 102 % nRO 108 %

Warning Light/Tone intermittent and resetable Warning Light/Tone intermittent Warning Light Warning Light/Tone constant

Warning Light Tone intermittent Tone constant

5 times/sec 5 times/sec, 650 Hz 2,600 Hz

LOW FUEL

T OIL

“LOW FUEL” will illuminate, if there are less than 60 kg of fuel in supply tank; pilot has to land within the next 10 minutes.

“T OIL” will illuminate if,

HY BLOCK “HY Block” will illuminate, if a jammed servo valve in the hydraulic system 1 occurs.

-- oil pressure of the main transmission is below 0.5 bar, and/or -- oil temperature of the main transmission is above 105 °C.

GEN 1, GEN 2 “GEN 1”, “GEN 2” will illuminate, if: -- respective generator is switched off, or -- reverse current relay is defective.



00 -- 44

BO 105 Training Manual General Warning Lights TEST FIRE

TEST FIRE LOW FUEL HY BLOCK

Fire Warning Test Switch

T OIL

GEN 1

FILT 1

GEN 2

FILT 2

Fire Warning Light Engine 1 HYD 2

MAG PLUG 1 MAG PLUG 2

START 1

BAT 60

START 2

BAT 70

HYD 1

Warning Lights

RPM

OIL COOL

Fire Warning Test Switch Fire Warning Light Engine 2

Test Switch Warning Lights TEST

T PLUG WARN.--LIGHTS



00 -- 45


FILT 1, FILT 2

Test

“FILT 1”, “FILT 2” will illuminate, if the fuel pump filter of the respective engine is contaminated.

To test the function of all indicator lights (except “Fire Warning”) a test push button labeled “TEST WARN. LIGHTS” is installed below the warning light panel.

HYD1, HYD 2 “HYD 1”, “HYD 2” will illuminate, if the oil pressure is below the min. value range of 65--72 bar.

By pushing the button a lamp test of all indicator lights and a system test only of the battery (BAT60, BAT70) as well as the Transmission (T OIL) monitoring is performed.

MAG PLUG 1, MAG PLUG 2 “MAG PLUG 1”, “MAG PLUG 2” will illuminate, if metallic particles contaminate the oil system of the respective engine.

START 1/START 2 (Opt. / Standard Super Five) “START 1”, “START 2” will illuminate, if the switch of the single hand starting device is pushed to “ON”.

BAT 60, BAT 70 “BAT 60”, “BAT 70” will illuminate, if the temperature of the battery rises to 60 °C, 70 °C.

OIL COOL If “OIL COOL” is illuminated, the differential pressure switch at the air inlet duct is activated and indicates a failure of the oil cooling fan.

T PLUG (Opt.) “T PLUG” will illuminate, if metallic particles contaminate the oil system of the main transmission.



00 -- 46

BO 105 Training Manual General Warning Lights TEST FIRE

TEST FIRE LOW FUEL HY BLOCK

Fire Warning Test Switch

T OIL

GEN 1

FILT 1

GEN 2

FILT 2

Fire Warning Light Engine 1 HYD 2

MAG PLUG 1 MAG PLUG 2

START 1

BAT 60

START 2

BAT 70

HYD 1

Warning Lights

RPM

OIL COOL

Fire Warning Test Switch Fire Warning Light Engine 2

Test Switch Warning Lights TEST

T PLUG WARN.--LIGHTS



00 -- 47


Operator Panel General

Battery Switch

The operator panel is located below the instrument panel. It mainly serves as an operational and monitoring system, consisting of:

The battery switch has two positions:

-----

circuit breakers, caution lights, switches, instruments for monitoring the electrical system.

-- BAT OFF/EPU ON: the electrical system is supplied only by an external power unit (EPU); -- EPU OFF/BAT ON: the electrical system is supplied by the battery.

EPU Warning Light

Voltmeter The voltmeter indicates the operating voltage of the main busbar in DC--Volts.

Amperemeter

The EPU warning light indicates that the external power unit is connected to the helicopter and supplies current.

Hydraulic Test Switch The hydraulic test switch has three positions:

The indication of the amperemeter is dependent on the position of the amperemeter switch. The indication range of the amperemeter is from --150 A to +150 A, with the zero position in the center.

Amperemeter Switch The amperemeter switch, located below the amperemeter, has three positions:

-- Test (spring loaded) used only on ground to test switch over from hydraulic system 1 to system 2; -- Normal (center position) used for normal operation of the hydraulic system; -- Reset (spring loaded) used for switch over from system 2 to system 1.

-- center position: the current being taken from the main busbar will be indicated as minus Ampere; -- left position: the current being produced by generator 1 will be indicated as plus Ampere; -- right position: the current being produced by generator 2 will be indicated as plus Ampere. For training and information only


00 -- 48

BO 105 Training Manual General Operator Panel (Example)

35 RADIO NAV 1

35

15

5

ICS

HYDR CONTROLS

10

3

RADIO LANDING NAV 2 LIGHT 2

2

3

5

STARTER/IGN ENG 1 ENG 2

5

3

3

5

2

BLOWER

5

5

H Y D R II R E S E T

N2 CONTROL

3

3

1 2 ENG ANTI--ICING

LOW FUEL

20

1 2 PITOT HEATING

TEST

INSTR LIGHT

10

DC--SOCKET WIPER

2 HEATING

1

7.5

1 2 ENG ANTI--ICING ANTI 1 ICING ANTI ICING 2

0

Ampermeter

DC AMPS

Hydraulic Control Switch HYDR TEST

1 GEN

O N P A R K WIPER

2 GEN

DC AMPS

Ampermeter Switch

EMER DC BUS 1 2 EMERG FUEL VALVE

ELT LOAD HOOK

EPU ON

C O N T I G N

ENG 1

C ENG 2 ON O N O T F F I G VNT N

EPU Warning Light EPU ON

BAT ON EPU OFF

BAT ON EPU OFF ON

OFF

GENERATOR

Battery Switch

Single Hand Starting Device Opt./Standard Super Five October 2005 (DRAFT)

IGNITION ENG 1 ENG 2 GEN ON ON

OFF BAT OFF EPU ON


0

BUS BAR CURRENT IND

STARTER/IGNITION

Test Low Fuel (D and --5 only)

DC VOLTS

Voltmeter

DC VOLTS

1 2 LANDING LIGHT EMERG FUEL VALVE

SUPPLY TANK MAIN TANK FUEL PUMPS

7.5

TRIM PULSED ACTUATOR CHIP DET

3

BAT OFF START EPU ON STARTER/GENERATOR

Starter/Generator Control Switches--Standard

00 -- 49


Overhead Panel General

Also a hand lamp is installed on the left side.

The overhead panel is located in the middle of the canopy. It consists of two or three sections:

COM/NAV Circuit Breaker Panel Section (Opt.)

-- a power lever section, -- a switch panel section, -- a COM/NAV circuit breaker panel section (Opt.).

Depending on optional COM/NAV equipment a circuit breaker section can be added at the rear of the overhead panel, together with to two COM/NAV master switches.

Power Lever Section The gas producer fuel controls N1 are operated by Teleflex cables connected to two power levers mounted side--by--side in front of the overhead panel. The levers have three positions: OFF -- IDLE -FLIGHT. A power lever lock in the IDLE position prevents the power levers from being inadvertently shifted directly from OFF to FLIGHT, or vice versa.

Switch Panel Section The switch panel is the center part of the overhead panel and contains the standard switches for: -- fuel pumps, -- lights, -- generator control (D and/or --5). and several optional switches e. g.: -- heating, -- fire extinguisher, -- winch. For training and information only


00 -- 50

BO 105 Training Manual General Overhead Panel (Example) Generator Control

Power Lever Engine No. 1 Power Lever Engine No. 2

GEN TRIP 1

GEN TRIP 2

1 GEN RES

2 GEN RES

II 0 I EMERG. FLOATS TEST

FIRE--EXT TEST

ENG 1 ENG 2 1 2 SUPPLY TANK MAIN TANK FUEL PUMPS

PULSED CHIP DET

Fuel Pumps Lights

INTERNAL LIGHT

POSITION ANTICOLL. LIGHT LIGHT

STROBE LIGHTS

CARGO COMP. HEATING

BLOWER OFF HEATING HEATING



TEMP CONT

00 -- 51


Handling General

Operation

To handle the helicopter on the ground, ground handle wheels must be installed to the skids. Two men push the helicopter either at:

The helicopter is lifted by pumping with the control handle of the hydraulic jack. Thereby it has to be ensured that the relief valve is closed (turn right with the handle). After the helicopter is lifted, engage the mechanical lock and release pressure from the jack.

-----

front canopy lateral windshield frame, or cabin structure left and right, or engine compartment floor rear edge, or cross tubes of the landing gear.

! NOTE

Move the helicopter only with engaged mechanical lock and released pressure from the jack.


00 -- 52

In addition, one man supports the helicopter at the tail boom skid for steering and balancing. ! NOTE

Pushing on the canopy or on the rear cargo doors can result in damage!

Moving backwards results in easier handling of the helicopter.

Ground Handling Wheels Ground handling wheels are delivered as standard with the helicopter and serve for moving the BO 105 on ground.

Installation Ground handling wheels are connected to the pickup pins on each skid.


BO 105 Training Manual General Handling

Control Handle

Mechanical Lock

Relief Valve Ground Handling Wheel

Pick--up Pin

Towing Bar



00 -- 53


Parking and Mooring General

Tie Down

To protect the helicopter from environmental influence, it has to be covered and tied down depending on weather conditions. With the helicopter parked outdoors, it is recommended to moor the helicopter to the ground and secure the rotor blades by tie-downs.

The main rotor is tied down with a hook (type I rotor blades) or a lashbag (type II rotor blades) to the tail boom. The main rotor has to be turned in direction of rotation until one of the blades is aligned with the tail boom. The hook must be attached to the locking plate at the end of the rotor blade or the lashbag must be fitted over the end of the blade. Then the hook or lashbag must be secured to the tail boom by wrapping the attached belt and sack around the tail boom.

Short-Time Covers All short--time covers and tie-downs are stowed in a storage sack, which should be carried on the helicopter during flights.

Procedure All the electrical equipment has to be switched off. The helicopter must be grounded at the ground connection with the ground cable. Then all doors, windows and access doors must be closed. ! NOTE

The tail rotor is tied down to the tail skid. A clamp must be attached to the end of a tailrotor blade, then it must be secured to the tail skid by wrapping the attached belt and sack around the tail skid. ! NOTE

Turn the main and tail rotor only in direction of rotation.

The engine outlets may be hot!



00 -- 54

BO 105 Training Manual General Short Term Covers and Tie Downs Type I Blades

Type II Blades

Main Rotor Blade Tie Down

Tail Rotor Blade Tie Down

Air Inlet Cover

Exhaust Cover (with Cowlings)

Exhaust Cover (without Cowlings)

Pitot Tube Cover



00 -- 55


Hoisting General

Hoisting Ring

For certain maintenance work, it is necessary to hoist the helicopter or parts of it. Therefore the appropriate hoisting fixtures must be used.

In the absence of the recommended hoisting fixtures, the hoisting ring attached to the main rotor head can be used only for hoisting the main rotor head and/or installed main transmission.

Hoisting Fixtures

! NOTE

During hoisting the helicopter and/or the tailboom, the end of the tailboom must be supported for balance!


00 -- 56

The following units to be hoisted are listed with the required hoisting fixtures: Units

Hoisting fixture

Max. load

fully equipped helicopter, main rotor head, main rotor transmission (rotor head installed)

105--14101 W5 1121--14102W1 117W3

2000 kg 2300 kg 3500 kg

main rotor transmission (rotor head removed)

105W27 117W27

3600 kg 3600 kg

engine

105--60001 W2 Allison 67 96 96 3

tailboom

105--30051 W3 117--30001W3


BO 105 Training Manual General Hoisting Equipment Hoisting Fixture 105--14101 W5 1121--14102 W1 117--W3

Hoisting Fixture 105 30051 W3

Hoisting Ring

Hoisting Fixture 105 W27 117 W27

Hoisting Fixture 105 60001 W2

Tail Boom Rack 117--30001W1



00 -- 57


Jacking General

Measuring and Weighing

The fully equipped helicopter can be raised by either four jacks or three jacks together with a weighing beam. The jacks and the weighing beam must be positioned underneath the jacking points.

Three jacks and the weighing beam are used:

Jacking Points There are four jacking points. Two are attached to the double frame 4, and two to the double frame 9.

-- position the weighing beam underneath the two front jacking points and insert pins, -- position one jack underneath the weighing beam and support it, ! NOTE

Procedures In the following, two jacking procedures are described:

Use tail skid to balance the helicopter during lowering and raising if necessary.

-- position two jacks underneath the rear jacking points, -- operate the jacks simultaneously, until the desired ground clearance is reached, -- tighten locking rings of the jacks.

-- jacking up for general maintenance work, -- jacking up for leveling and weighing.

Maintenance Work Four jacks have to be used for jacking the helicopter: -- position jacks underneath the jacking points, -- operate the jacks simultaneously, until the desired ground clearance is reached, -- tighten locking rings of the jacks.



00 -- 58

BO 105 Training Manual General Jacking the Helicopter for General Operation

Jacking the Helicopter for Levelling and Weighing

Jacking Point Fitting

Weighing Beam

Hydraulic Jack



00 -- 59

000_BO105_Section_00

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