000_BO105_Section_00

BO 105Training ManualGeneral

00 -- 1October 2005 (DRAFT)For training and information only

General Description



Table of Contents

The Development of the BO 105 4. . . . . . . . . . . . . . . . . . . . . . . . .General Describtion of the BO 105 6. . . . . . . . . . . . . . . . . . . . . .Structural Groups of the BO 105 10. . . . . . . . . . . . . . . . . . . . . . . .Maintenance Concept 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Documentation of the BO 105 16. . . . . . . . . . . . . . . . . . . . . . . . . . .

EUROCOPTER BO 105 Documentation 16. . . . . . . . . . . . . . . . .Other Manufacturer�s Documentation 18. . . . . . . . . . . . . . . . . . .

The EUROCOPTER Documentation 20. . . . . . . . . . . . . . . . . . . . . .Maintenance Manual 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Illustrated Parts Catalog 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Cockpit Arrangement 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Instrument Panel 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Flight Instruments 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Pitot and Static Pressure System 28. . . . . . . . . . . . . . . . . . . . . . .Pitot Tube Heating 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Air Speed Indicator 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Altimeter 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Rate of Climb Indicator 32. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Outside Air Temperature Indicator 34. . . . . . . . . . . . . . . . . . . . . .Clock 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Compass 34. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Instrument Markings 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Engine Monitoring Instruments 38. . . . . . . . . . . . . . . . . . . . . . . . .

n1 RPM Indicator 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .n2 RPM Indicator 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Torque Indicator 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Turbine Outlet Temperature Indicator 38. . . . . . . . . . . . . . . . . . . .

System Monitoring Instruments 40. . . . . . . . . . . . . . . . . . . . . . . . .Mast Moment Indicator 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Triple Oil Temperature Indicator 40. . . . . . . . . . . . . . . . . . . . . . . .Triple Oil Pressure Indicator 40. . . . . . . . . . . . . . . . . . . . . . . . . . . .Fuel Quantity Indicator 42. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Fuel Pressure Indicator 42. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .nRO Indicator 42. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Warning Lights 44. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Operator Panel 48. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Overhead Panel 50. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Handling 52. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Parking and Mooring 54. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Hoisting 56. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .Jacking 58. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

This training document comprises the following ATA chapters:

Overhead Panel ATA 24

Instrument Panel ATA 31

Warning Lights ATA 31

Analog Instruments ATA 31, 34

LH and RH Section of Instrument Panel ATA 30, 34

Pitot--Static System ATA 34

Hoisting, Jacking Shoring ATA 07

Towing, Mooring ATA 09

Parking, Storage ATA 10



INTENTIONALLY LEFT BLANK



The Development of the BO 105

History

The first MBB helicopter with glass fiber rotor blades was the singleblade helicopter BO 102, a captive trainer, operating for the first timein 1957.

In 1961 the single seaterBO103 followed, the only helicopter to flywithone rotor blade. In 1962/63, a newhingeless rotor systemwascreated,and successfully tried on an Allouette II, 1966 in Marignane, France.

From 1960 to 64 the high speed helicopter BO 46 was designed withthe Derschmidt rotor system.

In 1964 a new concept of a light transport helicopter was establishedto fulfill the requirements of the seventies and eighties: the BO 105.Market research had shown the need for a multi purpose helicopter ofthe 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.

In addition, MBB set requirements for:

-- good overall stability,

-- high manoeuverability, and-- controllability under all flight conditions.

The last 2 requirements were met by the Bölkow hingeless rotorsystem.

Bölkow Rotor System

The main rotor blades are manufactured from glass--fiber--reinforcedplastic (GRP) and are directly connected to the rigid titanium rotorhead. Flap and lead--lag movement is accomplished by the elasticityof the blades. The only possible relative movement between theblades and rotor head is during changes of pitch. This arrangement isreferred to as a hingeless rotor system.All rotor reaction forces aretransmitted directly from the rotor system through the main rotor mastinto the fuselage.The construction of the rotor head is very simple. Thenumber of parts have been reduced to approximately 20 % of aconventional or articulated system because the drag hinges, flappinghinges and such components as dampers have been omitted.



Flight Trials

The easy handling of the helicopter under all conditions wasdemonstrated during the flight trials. Themain stages are listed below:

In January, 1966, the first flight of the hingeless three--blade rotorsystem, installed in the Allouette II helicopter, was successfullyperformed by the Aerospatiale helicopter chief test pilot.

On February 16th, 1967, MBB helicopter chief test pilot performed thesuccessfull first flight of the BO 105, which was equipped with ahingeless, four--blade rotor system. During the next 4 years, fourprototypes of the BO 105 passed all tests required successfully.

At the end of 1970, the certification by the German AirworthinessAuthority (LBA) of the BO 105 was completed.

Versions

BO 105 Series A,two Allison 250--C18 engine, 317 SHP (236 kW) each, take--off weight2100 kg, main transmission ZF FS 72 A or FS 72 B (MT 2x85 %).

BO 105 Series B,two MAN 6022 single shaft turbines of 320 SHP (240 kW) each (notlaunched).

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 FS72 B (MT 2x79 %),

BO 105 Series D additionally,further requirements of the CAA have been met.

BO 105 Series Sstretched 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--offweight 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 mainrotor blades (Type II), modified hydraulic system, different TCIintervals.

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

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

BO 105 LS A--3 �Superlifter�take--off weight 2850 kg with external load, high performance mainrotor blades (Type II), the modified hydraulic system, and improved tailrotor blades.



General Describtion of the BO 105

General

The BO 105 is a multi purpose twin engine helicopter in the 2.5 t classwith five seats in the basic version.

Main Rotor System

The main rotor blades are manufactured from fiber--reinforced plasticand are directly connected to the rigid titanium rotor head. Flap andlead--lag movement is accomplished by the elasticity of the blades.The only possible relative movement between the blades and rotorhead is during changes of pitch. This arrangement is referred to as ahingeless rotor system.

All reaction forces are transmitted directly from the rotor systemthrough the main rotor mast into the fuselage. The construction of therotor head is very simple. The number of parts have been reduced toapproximately 20 % of a conventional or articulated system becausethe drag hinges and flapping hinges have been omitted.

Themain rotor gearbox is a three stage light weight reduction gearboxproduced by ZF (Zahnradfabrik Friedrichshafen).

Fuselage

The fuselage structure is a conventional semi--monocoqueconstruction made in a modular design concept, consisting mainly outof aluminum sheet metal. Bottom shell, doors, engine cowlings andaccess panels are made of composite material.

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

Tail Rotor System

The helicopter is equipped with a semi--rigid two blade tail rotor. Theblades are made from glass--fiber--reinforced plastic (GRP). The tailrotor ismounted to a lightweight aluminumsheetmetal tail boommadein a semi--monocoque construction and controlled via rods routed fromthe pedals to the input of the titanium tail rotor head.

Flight Controls

The main rotor is controlled by rods and bellcranks, routed from thecontrol elements via the cabin sideshell to the transmission deckmounted hydraulic system.

The hydraulic system is a tandem system, i.e. it consists of twoseparate systems, which operate independently of each other (failsafe system). Under normal operating conditions only one system(No.1 main system) functions as a booster, the second system (No.2standby system) stay in standby. In case of a failure in the mainsystem, it will be immediately cut off and the standby system will beactuated automatically to ensure safe operation and landing.



Landing Gear

The BO 105 has two cross tubes and two skids. The cross tubes areconstructed to absorb forces during touch down of the helicopter, bybending.

Fuel System

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

Engines

TheBO105 is powered by twoAllison 250--C20B engineswith a poweroutput of 420 shp each.

Electrical System

The fully redundant 28 V DC electrical system is supplied by twogenerators and a battery.



Dimensions

Streched airframe area



Cargo Loading Configurations

! NOTE S--versions: Cargo length + 254 mm.



Structural Groups of the BO 105

General

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

10 Lifting System

The lifting system comprises:

1 main transmission,

2 rotor brake system,

3 main rotor system,

4 main rotor blades.

20 Fuselage

The fuselage comprises:

1 fuselage with tailboom mounting cone, doors and windows,

2 cowlings.

30 Tail Unit

The tail unit comprises:

1 tailboom with vertical fin and horizontal stabilizer,

2 tail rotor drive with intermediate transmission and tail rotortransmission,

3 tail rotor,

4 tail rotor blades.

40 Flight Control System

The flight control system comprises:

1 main rotor controls with collective and cyclic control system,

2 tail rotor controls,

3 hydraulic system.

50 Landing Gear

The landing gear comprises:

1 landing gear with two skids and two crosstubes.



Structural Groups of the BO 105

40 Flight Control System

30 Tail Unit

60 Power Plant

10 Lifting System

20 Fuselage

90 Instruments andElectrical System

50 Landing Gear

70 Standard Equipment



60 Power Plant

The power plant comprises:

1 engine,

2 fuel system with tank,

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 aseparate volume of the MaintenanceManual and in the Flight Manual.Optional equipment is not described in this Training Manual.

90 Instruments and Electrical System

The instruments and electrical system comprises:

1 instrument system,

2 electrical system.



Call Sign

Helicopter Number Plate

BAUREIHEMODELL

GERÄTE--NR.REGISTER--NO.

WERK--NR:SERIAL--NO.

BAUJAHRYEAR OF MANUF.

D--HTRAINER

BO 105 CB--5

3025

S--251

1978Helicopter Number Plate



Maintenance Concept

General

�Maintenance� covers all scheduled and unscheduled maintenanceactivities. It also applies to the on condition maintenance. It is basedon condition monitoring by visual checks/inspections and diagnosticfeatures such as chip detectors, filter bypass indicators, boroscopeaccess, failure indications, built-in tests, warning lights etc.

Maintenance Levels

BO 105 maintenance is split into three maintenance levels:

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

Organizational Level

The organizational level covers tasks of the daily servicing,maintenance checks, inspections for condition, exchange ofcomponents (e.g. LRU) and quick, simple repairs as specified in themaintenance manual (MM).

The work generally takes place at the operators site. After an �on thejob training� these checks can be carried out by pilots, mechanics andoperators.

Intermediate Level

The intermediate level covers repairs on/off helicopter, extendedperiodical inspections as specified in the aircraft maintenancemanual.To meet these tasks, maintenance facility, qualified personal, testequipment and special tools are required.

! NOTE The maintenance manual covers all tasks oforganizational level and intermediate level.

Depot Level (D)

Depot level covers major repair or overhaul at the manufacturer or atauthorized service stations under industrial premises.

More extensive tools/test equipment and specialized personnel arenecessary.

! NOTE Documentation and spares for depot level taskswill be delivered to authorized customers only.

! NOTE Information about inspections and intervals are tobe found in chapter Inspections of this trainingmanual.



Maintenance

ScheduledUnscheduledOn Condition

OrganizationalLevel (O)

IntermediateLevel (I)

Depot Level (D)

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

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

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

Manufacturer/authorized customers only

Maintenance Concept



Documentation of the BO 105

General

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

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

EUROCOPTER BO 105 DocumentationThe EUROCOPTER BO 105 documentation consists of three maingroups:

Pilot�s Documentation

The pilot has available three documents:

-- Flight Manual,-- Log Book,

-- Pilot�s Checklist.

! NOTE Flight Manual, Log Book, and Pilot�s Checklistmust always be present in the helicopter.

Mechanic�s Documentation

The mechanic has available:

-- 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

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

-- Historical Records,-- LOAP,

-- Alert Service Bulletins (ASB),-- Service Bulletins (SB),

-- Alert Service Information (ASI),

-- Service Information (SI).

! NOTE The valid manuals inclusive revision status arepublished in the LOAP.



Pilot�s Checklist

Flight Manual

Alert ServiceInformations

Historical Record

Alert ServiceBulletins

Service BulletinsGSE

REM

MM

IPC

ECD Helicopter Documentation BO 105

Operator�s Technical ControlPilot Mechanic

Log Book

ServiceInformations

WDM

OPM

LOAP



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 105MM issued by EUROCOPTER),

-- avionics systems,

-- special optional equipment,-- Marvel Balancer (integrated in BO 105 MM),

-- Tracking Balancing (acc. Operation Manual of themanufacturer).



Avionics SystemsTransmission(integrated in MM)

OMM Engine

IPC Engine Special OptionalEquipment

Dual HydraulicSystem(integrated in MM)

Other Manufacturer�s Documentation

CSL, CEB, IB, ASL



The EUROCOPTER Documentation

General

The following EUROCOPTER--Documentation is described:

-- MM-- IPC

-- REM

Repair and overhaul work to be performed according to the RepairManual (REM) is only permissible after completion of a specialmaintenance course.

Maintenance Manual

General

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

-- repair manual (REM) for repair of assemblies, which arenot described in the maintenance manual;

-- wiring diagram manual (WDM) to assist inspections of theelectrical system;

-- illustrated parts catalog (IPC)

-- vendor documentation for repair of assemblies which arenot manufactured by ECD.

Arrangement

The maintenance manual is arranged according to the mainassemblies (structural groups). Additionally in a chapter general, basicinformation about the helicopter is given and in a chapter 100 somesubchapters are added for special maintenance information.

Chapters

The chapters give information about the subassemblies of therespective main assembly. The chapters are numbered by two, or incase of standard (70) and optional equipment (80) by three digits. Thefirst digit corresponds to the main assembly, the following to thesubassemblies.

Paragraphs

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

Example

As an example of the manual numbering the maintenance instructionsof 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 secondsubassembly of chapter 30 (chapter 32);

-- third step: the maintenance instructions are described inparagraph 32--4.



The Maintenance Manual

01 11 21 31 41 51 61 91 101

Dimensionsand

ReferencePlanes

MainTransmission

Fuselage TailBoomAssembly

MainRotorControls

LandingGear

EngineRefer toTableofContentsChapter 700

InstrumentSystem

Inspectionsand

AirworthinessLimitations

02 12 22 32 42 62 92 102

GeneralInstructions

RotorBrakeSystem

Cowlings TailRotorDrive

TailRotorControls

FuelSystem ElecricalSystem

RiggingofM.Rotor andTailRotorControls

03 43 103

ConsumableMaterials

MainRotorSystem

HydraulicSystem

Measuringthe

Helicopter

13 33 63

TailRotor LubricationSystem

04 14 34 64 104

SelfManu--facturable

SpecialTools

MainRotorBlade

TailRotorBlade

FireWalls Weighingthe

Helicopter

05 65 105

GroundHandling

EngineOperationandControl

GroundRun/FunctionalTestFlight

06 107 106

BalancingofTailRotorSystem

TrackingandBalancingofMainRotorSytem

Refuelingand

Defueling

Refer toTableofContentsChapter 800

General LiftingSystem Fuselage TailUnit FlightControlSystem

LandingGear PowerPlant StandardEquipment

OptionalEquipment

Instrumentsand

ElectricalSystem

Inspectionsand

Procedures

MM



Illustrated Parts CatalogGeneral

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

Arrangement

The IPC is divided into three sections:

-- section general contains an introduction explaining how touse the catalog, a vendor list, a list of all incorperatedservice bulletins and a list of abbreviations;

-- section numerical index contains two alpha--numericallistings, one of all electrical identification indices mentionedin section detailed parts list and one of all part numbersmentioned in section detailed parts list;

-- section detailed parts list contains exploded views of theassemblies and is subdivided in accordance with the ninestructural groups.

Page Numbering

The pages of the sections general and numerical index are numberedconsecutively within each section. In section detailed parts list thefigures (exploded views) in each chapter are used for a consecutivenumbering and the parts list belonging to a figure is also numbered inthis manner.

10--00--00 FIG. 03 Page 2

Part Number

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

No letter or letter �a� defines the original part, �b� the first, �c� thesecond, �d� the third change.

Model Codes

The following Model Codes are used:

-- A = BO105 A -- B = BO105 C

-- C = BO105 D -- D = BO105 S-- E = BO105 CBS--5 -- F = BO105 DBS--5

-- G = BO105 CB--5 -- H = BO105 DBS-- I = NBO--105 CB

The codification according to serial numbers means e. g.:

-- 481--999: This part is to be used on helicopters startingwith serial number 481

-- 161--480: This part is to be used on helicopters startingwith serial number 161 to 480

-- 001--060: This part is to be used on helicopters starting upto 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 bechecked by the cusomer individually.



General

Illustrated Parts Catalog

Numerical Index Detailed Parts List

Structural Group 10

Lifting System10--00--00

IPC

Part Number ArrangementExample: 105--31802.02c

105 -- 3 1802 . 02 cChange 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�

Structural Group 90

Electrical System90--00--00

9 Structural GroupsElectrical Identifier IndexParts Numerical Index

IntroductionVendor ListSB List

Abbreviations



Cockpit Arrangement

General

The BO 105 is provided with several units for monitoring, warning andcontrol 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



Cockpit Arrangement

Outside Air Temperature Indicator

Overhead Panel

Power Lever

Instrument Panel

Operator Panel

Stick Pilot

Pedals

Collective Lever PilotCenter Console

Collective Lever Copilot

Stick Copilot

Magnetic Compass



Instrument Panel

General

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

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.

Engine Monitoring Instruments

The engine monitoring instruments comprise:

-- 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 INSTRLIGHT on the operator panel and may be dimmed by a potentiometerINSTR LIGHT on the instrument panel.

Warning Lights

The warning lights are located in the warning panel togetherwith a testswitch.



Mast Moment Indicator

Instrument Panel

Clock

Air Speed Indicator

Warning Lights Gyro Horizon Pitot Heating Indicator

Altimeter

Rate of Climb Indicator

Directional Gyro

n2 (eng 1+2)+ nRO Indicator

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

n1 Indicator (eng 2)

Fuel Pressure Indicator

n1 Indicator (eng 1)

Torque Indicator (eng 1 + 2)

Triple Oil Pressure Indicator

Triple Oil Temperature Indicator

Fuel Quantity Indicator

Instrument LightBrightness Control

PITOTHEATING

Fire Warning Light

Test Switch

Test Switch Warning Lights

TEST

WARN.-- LIGHTS



Flight Instruments

Pitot and Static Pressure System

General

The Pitot static system supplies static pressure to the Vertical speedindicator and the Altimeter, and pitot and static pressure to theAirspeed indicator. The instruments give readouts of airspeed, altitudeand the vertical speed.

The pitot--static system consists of:

-- Pitot tube-- Tube and hose line

-- 2 Static ports

Static pressure is exerted on the instruments via the static ports andthe tube/hose line assembly. The pitot tube supplies pitot pressure tothe airspeed indicator and the Air data computer. The pitot tube canbe heated to prevent the formation of ice. A tee with cap assembly isinstalled in the tube/hose line assembly to drain condensation waterand to connect test equipment.

! NOTE The instruments function is independent of anyelectrical power supply.

Location

There are two static and one ram air pressure pick--up (pitot tube). Thestatic pressure pick--ups are located on the left and right outside of thehelicopter in front of the FWDcross tube (near bottomof the fuselage).The pitot tube is located on the right side below the static pressurepick--up.

Static Pressure Pick--up

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

Pitot Tube

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



DOWN

UP

CLIMB1000 FT PER MIN

Location of the Pitot and Static Pressure System Dynamic and Static Pressure System Schematic

Pitot Tube Static PressurePick--up


Altimeter

Air SpeedIndicator

Pitot Tube

Static PressurePick--up, right

Static PressurePick--up, left

Drain Plug

Static Pressure

Pitot Pressure



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 frontsection of the probe.

On ground, the pitot tube heating should be switched on only for ashort period. Pitot tube heating is not cooled down by the airspeed andwill overheat with the risk of burning out.

Power Supply

The pitot heating is suppliedwith electrical power from themain busbarPP21 via the circuit breaker 1HG at the lower right side of theinstrument panel and the toggle switch 4HG in the operators panel. Itis labelled PITOT HEATING and has the two positions ON and OFF.The function of the system is indicated by the electro--mechanicalindicator 2HG located at the top of the Instrument Panel. It is a nonilluminated, electro--mechanical indicator, labelled PITOT HEATING.If Pitot heating isOFF, white sectors are visible on a black background.If Pitot heating is ON, the front side of the indicator is black, no whitesectors are visible.



Toggle SwitchPITOT HEATING4HG

Pitot Tube Heating

PP21

Circuit Breaker1HG

Electro MechanicalIndicatorPITOT HEATING2HG

Pitot Tube Heating3HG

Main Busbar

Connecting Flange

Airframe

Contact PinsHose Line

Pitot Tube



Air Speed IndicatorGeneral

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

Operation

Amembrane capsule for the pitot and the static pressure transmits themotion to a gear, which is connected to the pointer of the instrument.The pointer indicates the pressure difference between pitot pressureand static pressure.

Indication Range

The indication range is calibrated from 10 to 150 knots with an intervalof 5 knots.

Altimeter

Operation

The altimetermeasures static pressure changes in the atmosphere viaan aneroid capsule. These static pressure changes are equivalent tochanges in altitude.

Indication

The scale is marked in feet. Three pointers indicate the altitude at anygiven moment:

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

-- the rotating scale indicates ten thousands per digit.

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


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, whichmeasures the static pressure variations resulting from altitudechanges.Whena change in altitudehas been completed, the pressureis equalized via a permanent capillary bleed and the pointer returns toits initial �0� position.

Indication Range

The indication range for the rate of descent is from 0 to 6000 feet/minand for the rate of climb from 0 to 6000 feet/min. The scale is dividedinto intervals of 100 feet up to 1000 feet/min, and intervals of 500 feetbetween 1000 and 6000 feet/min.




Air Speed Indicator Altimeter Rate of Climb Indicator

ENCODING

mb INHg

DOWN

UP

CLIMB1000 FT PER MIN

Pitot and Static Pressure Flight Instruments

Red Line, VNE

Green Range,45--145 kts

Yellow Range,10--45 kts

Setting Knob

BarometricScale

Large Pointer100 ft

Short Pointer1000 ft

Dial Pointer10000 ft

Rate of Climb

Rate of Decent



Outside Air Temperature Indicator

General

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

Indication

The outside air temperature indicator has one pointer, which indicateson 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

General

The clock is amechanical chronometerwith an additional pointer usedfor the stop--watch function. The outer scale of the clock is a rotatingbezel that can be used to measure elapsed time.

Compass

General

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

Indication

The compass card is located on a float with markings at 10 degintervals. The cardinal directions are marked N, E, S and W, andnumbers indicate the heading in 30 deg increments. The float is freeto move in all three dimensions with silicone fluid as the dampingmedium. Deflections caused by interfering magnetic fields arecompensated by the compensation device.




Outside AirTemperature Indicator

Outside Air Temperature Indicator, Compass, Clock

3033N6 3

12

3

12

4567

89

1011

Compass

Compensation Device

Compass Card

Start/Stop/Reset Knob

Winding Knob

Clock



Instrument Markings

General

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

Markings

To identify the indications of the units, pointers and scales are markedas follows:

left engine 1 and/or redright engine 2 and/or greenmain rotor transmission R and/or blackmain tank Msupply tank S

Operation Ranges and Limits

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

Transient limit red point

Start limits red triangle

Min. and max. limits red radial

OEI 2.5 min red dashed radial

OEI MCP yellow dashed radial

Takeoff power or Caution Range yellow arc

Normal or Continous Range green arc

Calibration point white radial



Instrument Markings (Example)

0

TORQUE%

20

4060

80

100

120

Transient

Start

Takeoff or Caution Range

Normal

Normal or Continous

Max. Limit

OEI MCP

OEI 2.5 min

Transient




General

The performance of each engine is monitored by four indicatingsystems:

-- n1 RPM indication,

-- n2 RPM indication,

-- torque indication,-- turbine outlet temperature indication.

! NOTE The instruments function are indipendent of anyelectrical power supply.

n1 RPM Indicator

General

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

Operation

The system comprises a tacho generator, which drives a synchronouselectric motor in the RPM indicator.

n2 RPM Indicator

General

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

Operation

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

Torque Indicator

General

The torque indicator is used tomonitor the torque of each engine in percent. This is necessary to match power sharing between the engines.

Operation

The torque indicating system is hydraulically operated, using engineoil pressure which is proportional to engine power. The transfer to theinstrument is done via air.

Turbine Outlet Temperature Indicator

General

The turbine outlet temperature (TOT) gives information about theoperating condition of the engine. One instrument for each engineindicates the TOT in degrees centigrade.

Operation

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




n1 Indicator Torquemeter n2 eng. 1, n2 eng. 2, nRO Indicator TOT Indicator




General

The operation of the helicopter system is monitored by five indicatingsystems:

-- mast moment indicator,

-- triple oil temperature indicator,

-- triple oil pressure indicator,-- fuel quantity indicator,

-- fuel pressure indicator,-- nRO indicator.


General

The BO 105 is equipped with an hingeless rotor and therefore highbending moments on the rotor mast can occur. The pilot has to avoidextreme cyclic stick motions on the ground with the rotor turning. Thebending of the rotor shaft is monitored by the mast moment indicationsystem.

Operation

The system comprises a strain gauge (Wheatstone) bridgearrangement within the mast, an inductive rotary transmitter, and anindicator on the instrument panel.

Triple Oil Temperature Indicator

General

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

Operation

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

Triple Oil Pressure Indicator

General

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

Operation

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





Triple Oil TemperatureIndicator

Triple Oil PressureIndicator

CAL TEST LIMIT



Fuel Quantity Indicator

General

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

Operation

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

Fuel Pressure Indicator

General

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

Operation

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

nRO Indicator

General

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

Operation

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

! NOTE The instrument function is indipendent of anyelectrical power supply.




2 2

11

00

1 2kp/cm2

Press

Fuel Pressure IndicatorFuel Quantity Indicator n2 Engine 1, n2 Engine 2,nRO Indicator

SMkp

30 6

420

00

210

x10



Warning Lights

General

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

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 ofovertemperature (fire) in one of the engine compartments, thecorresponding 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 thewarning lights itselfs.

LOW FUEL

�LOWFUEL� will illuminate, if there are less than 60 kg of fuel in supplytank; pilot has to land within the next 10 minutes.

HY BLOCK

�HY Block� will illuminate, if a jammed servo valve in the hydraulicsystem 1 occurs.

RPM

If latest Warning Box Type K--DW02/01 is installed, �RPM� willilluminate and an audio signal is triggered if

n1 Split 12 % Warning Light/Tone intermittentand resetable

nRO 75--95 % Warning Light/Tone intermittent

nRO 102 % Warning Light

nRO 108 % Warning Light/Tone constant

Warning Light 5 times/sec

Tone intermittent 5 times/sec, 650 Hz

Tone constant 2,600 Hz

T OIL

�T OIL� will illuminate if,

-- 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.



Warning Lights

Fire Warning Light Engine 1 Fire Warning Light Engine 2

Warning Lights

Fire Warning Test Switch Fire Warning Test Switch

TEST

WARN.--LIGHTS


LOWFUELHY

BLOCK

RPM

T OIL

GEN 1 FILT 1

FILT 2GEN 2

HYD 1 MAG

HYD 2

PLUG 1MAGPLUG 2

START 1

START 2

BAT 60

BAT 70

OIL

T PLUG

COOL

TESTFIRE

TESTFIRE



FILT 1, FILT 2

�FILT 1�, �FILT 2� will illuminate, if the fuel pump filter of the respectiveengine is contaminated.

HYD1, HYD 2

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

MAG PLUG 1, MAG PLUG 2

�MAG PLUG 1�, �MAG PLUG 2� will illuminate, if metallic particlescontaminate 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 handstarting device is pushed to �ON�.

BAT 60, BAT 70

�BAT60�, �BAT70�will illuminate, if the temperature of the battery risesto 60 °C, 70 °C.

OIL COOL

If �OIL COOL� is illuminated, the differential pressure switch at the airinlet 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 systemof the main transmission.

Test

To test the function of all indicator lights (except �Fire Warning�) a testpush button labeled �TEST WARN. LIGHTS� is installed below thewarning light panel.

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



Warning Lights

Fire Warning Light Engine 1 Fire Warning Light Engine 2

Warning Lights

Fire Warning Test Switch Fire Warning Test Switch

TEST

WARN.--LIGHTS


LOWFUELHY

BLOCK

RPM

T OIL

GEN 1 FILT 1

FILT 2GEN 2

HYD 1 MAG

HYD 2

PLUG 1MAGPLUG 2

START 1

START 2

BAT 60

BAT 70

OIL

T PLUG

COOL

TESTFIRE

TESTFIRE



Operator Panel

General

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

-- circuit breakers,

-- caution lights,

-- switches,-- instruments for monitoring the electrical system.

Voltmeter

The voltmeter indicates the operating voltage of the main busbar inDC--Volts.

Amperemeter

The indication of the amperemeter is dependent on the position of theamperemeter 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 threepositions:

-- center position: the current being taken from the mainbusbar will be indicated as minus Ampere;

-- left position: the current being produced by generator 1 willbe indicated as plus Ampere;

-- right position: the current being produced by generator 2will be indicated as plus Ampere.

Battery Switch

The battery switch has two positions:

-- BAT OFF/EPU ON: the electrical system is supplied only byan external power unit (EPU);

-- EPU OFF/BAT ON: the electrical system is supplied by thebattery.

EPU Warning Light

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

Hydraulic Test Switch

The hydraulic test switch has three positions:

-- Test (spring loaded) used only on ground to test switchover from hydraulic system 1 to system 2;

-- Normal (center position) used for normal operation of thehydraulic system;

-- Reset (spring loaded) used for switch over from system 2to system 1.



EPU Warning Light

Ampermeter Switch

Ampermeter

Hydraulic Control Switch

Voltmeter

Battery Switch

Operator Panel (Example)

DCAMPS

0

DCVOLTS

Single Hand Starting DeviceOpt./Standard Super Five

LOW FUEL

TEST

Test Low Fuel(D and --5 only)

DCVOLTS

DCAMPS

0

35 15 5 3 3

35 3 3 5 5 5 5

3327.52

210

RADIONAV 1 ICS

HYDRCONTROLS

1 2EMERG FUEL VALVE

RADIONAV 2

STARTER/IGNENG 1

SUPPLYTANKFUEL

MAIN TANKPUMPS

TRIMACTUATOR

BLOWER N2CONTROL

1 2ENG ANTI--ICING

INSTRLIGHT

1PITOT HEATING

1 2ENG ANTI--ICING

DC--SOCKET WIPER HEATING

20

WIPER

HYDRTEST

BUS BARCURRENT IND

1 2GEN GEN

EMERG FUEL VALVE1 2

HYDRIIRESET

ON

PARK

3

LANDINGLIGHT

LANDINGLIGHT 2

10

ENG 2

5

PULSEDCHIP DET

2

1

LOAD HOOKELT

7.5 DC BUS

ANTIICING

ICINGANTI

1

2

EMER

EPU

ON

STARTER/IGNITION

ENG 1 ENG 2CONTIGN

ON

VNT

OFF

BAT ONEPU OFF

BAT OFFEPU ON

GENERATOR

ON

OFF

EPU

ON

ENG 1BAT ONEPU OFF

BAT OFFEPU ON

START

ON

OFF

STARTER/GENERATOR

ENG 2IGNITION

GEN ON

CONTIGN

Starter/Generator ControlSwitches--Standard



Overhead Panel

General

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

-- a power lever section,

-- a switch panel section,

-- a COM/NAV circuit breaker panel section (Opt.).

Power Lever Section

The gas producer fuel controls N1 are operated by Teleflex cablesconnected to two power levers mounted side--by--side in front of theoverhead panel. The levers have three positions: OFF -- IDLE --FLIGHT. A power lever lock in the IDLE position prevents the powerlevers 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 containsthe standard switches for:

-- fuel pumps,

-- lights,-- generator control (D and/or --5).

and several optional switches e. g.:

-- heating,

-- fire extinguisher,-- winch.

Also a hand lamp is installed on the left side.

COM/NAV Circuit Breaker Panel Section (Opt.)

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



INTERNALLIGHT

HEATING

ENG 1SUPPLY TANK

FUEL PUMPS

1MAIN TANK

2

1GEN RES

FIRE--EXT TEST

BLOWER

OFF

HEATINGTEMP CONT

LIGHT LIGHT LIGHTS HEATINGPOSITION ANTICOLL. STROBE CARGO COMP.

ENG 2PULSEDCHIP DET

II

0

I

EMERG. FLOATSTEST

2GEN RES

1 2GEN TRIP GEN TRIP

Fuel Pumps

Overhead Panel (Example)

Lights

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

Generator Control



Handling

General

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

-- front canopy lateral windshield frame, or

-- cabin structure left and right, or

-- engine compartment floor rear edge, or-- cross tubes of the landing gear.

In addition, one man supports the helicopter at the tail boom skid forsteering and balancing.

! NOTE Pushing on the canopy or on the rear cargo doorscan result in damage!

Moving backwards results in easier handling of the helicopter.

Ground Handling Wheels

Ground handling wheels are delivered as standard with the helicopterand serve for moving the BO 105 on ground.

Installation

Ground handling wheels are connected to the pickup pins on eachskid.

Operation

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

! NOTE Move the helicopter only with engaged mechanicallock and released pressure from the jack.



Towing Bar

Handling

Ground Handling Wheel

Pick--up Pin

Relief Valve

Mechanical LockControl Handle



Parking and MooringGeneral

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

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 helicoptermustbe grounded at the ground connection with the ground cable. Then alldoors, windows and access doors must be closed.

! NOTE The engine outlets may be hot!

Tie Down

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

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

! NOTE Turn the main and tail rotor only in direction ofrotation.



Pitot Tube Cover

Short Term Covers and Tie Downs

Air Inlet Cover

Exhaust Cover(without Cowlings)

Main Rotor BladeTie Down

Tail Rotor BladeTie Down

Exhaust Cover(with Cowlings)

Type I Blades Type II Blades



HoistingGeneral

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

Hoisting Fixtures

The following units to be hoisted are listed with the required hoistingfixtures:

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

Hoisting Ring

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

! NOTE During hoisting the helicopter and/or the tailboom,the end of the tailboom must be supported forbalance!



Hoisting Fixture105--14101 W51121--14102 W1117--W3

Hoisting Equipment

Hoisting Fixture105 W27117 W27

Hoisting Fixture105 60001 W2

Hoisting Fixture105 30051 W3

Tail Boom Rack117--30001W1

Hoisting Ring



JackingGeneral

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

Jacking Points

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

Procedures

In the following, two jacking procedures are described:

-- 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.

Measuring and Weighing

Three jacks and the weighing beam are used:

-- position the weighing beam underneath the two frontjacking points and insert pins,

-- position one jack underneath the weighing beam andsupport it,

! NOTE Use tail skid to balance the helicopter duringlowering and raising if necessary.

-- position two jacks underneath the rear jacking points,

-- operate the jacks simultaneously, until the desired groundclearance is reached,

-- tighten locking rings of the jacks.



Jacking the Helicopter for General Operation Jacking the Helicopter for Levelling and Weighing

Weighing Beam

Hydraulic Jack

JackingPoint Fitting

Date post:	21-Apr-2015
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