aircraft maintenance manual - part i system description

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AIRCRAFT MAINTENANCE MANUAL - PART ISYSTEM DESCRIPTION SECTION

CHAPTER 12 − SERVICING

LIST OF EFFECTIVE PAGES

12 - EFFECTIVE PAGES

Jan 15/2005

Ch-Se-Su Effectivity Page Date Ch-Se-Su Effectivity Page Date

EFFECTIVITY: ALL

SERVICING 12-00-00SERVICING A01 ALL 1INTRODUCTIONGENERAL DESCRIPTIONTRAINING INFORMATION POINTS

REPLENISHING, SYSTEMS AND COMPONENTS 12-10-00REPLENISHING, SYSTEMS AND COMPONENTS A01 ALL 1INTRODUCTIONGENERAL

REPLENISHING, FUEL SYSTEM 12-11-00REPLENISHING THE FUEL SYSTEM A01 ALL 1INTRODUCTIONGENERAL DESCRIPTIONTRAINING INFORMATION POINTS

SERVICING, HYDRAULIC SYSTEM 12-12-00SERVICING THE HYDRAULIC SYSTEM A01 ALL 1INTRODUCTIONGENERAL DESCRIPTIONTRAINING INFORMATION POINTS

REPLENISHING, OIL SYSTEM 12-13-00OIL SYSTEM A01 ALL 1INTRODUCTIONGENERAL DESCRIPTIONTRAINING INFORMATION POINTS 5

CREW OXYGEN SYSTEM 12-16-00REPLENISHING THE OXYGEN SYSTEM A01 ALL 1INTRODUCTIONGENERAL DESCRIPTIONTRAINING INFORMATION POINTS


CHAPTER 12 − SERVICING

TABLE OF CONTENTS

12 - CONTENTSPage 1

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Subject Ch-Se-Su Effectivity Page

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REPLENISHING, WATER/WASTE SYSTEM 12-18-00WATER AND WASTE A01 ALL 1INTRODUCTIONGENERAL DESCRIPTIONTRAINING INFORMATION POINTS 4

SCHEDULED SERVICING 12-20-00SCHEDULED SERVICING A01 ALL 1INTRODUCTIONGENERAL DESCRIPTIONTRAINING INFORMATION POINTSSCHEDULED SERVICING AA1 ALL 8INTRODUCTIONGENERAL DESCRIPTIONTRAINING INFORMATION POINTS

UNSCHEDULED SERVICING 12-30-00UNSCHEDULED SERVICING A01 ALL 1INTRODUCTIONGENERAL DESCRIPTIONTRAINING INFORMATION POINTS


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On A/C 10001-10999, 15001-15990

TASK 12−00−00−001−A01SERVICING

INTRODUCTION

The servicing chapter contains data andprocedures for the servicing tasks to be doneduring normal operations. This chapter isdivided into the sections that follow:

• Replenishing

• Scheduled servicing

• Unscheduled servicing

GENERAL DESCRIPTION

Figure 12-00-00-991-801.

REPLENISHING

Replenishing the aircraft systems includes thesupply of materials and fluids necessary forthe correct operation of the aircraft systems.The systems that require servicing are asfollows:

• Servicing the fuel system (Section 12-11-00)

• Servicing the hydraulic system(Section 12-12-00)

• Replenishing the oil systems(Section 12-13-00)

• Replenishing the oxygen system(Section 12-16-00)

• Replenishing the water/waste systems(Section 12-18-00)

• Scheduled servicing (Section 12-20-00)

• Unscheduled servicing (Section 12-30-00)

SCHEDULED AND UNSCHEDULEDSERVICING

The detailed servicing data for the scheduledand unscheduled servicing procedures arefound in Part 2 chapter 12 of the AircraftMaintenance Manual. The servicingprocedures are listed the sections that follow:

• Aircraft cleaning (Section 12-21-00)

• Periodic lubrication of components(Section 12-22-00)

• Cold weather protection (Section 12-31-00)

TRAINING INFORMATION POINTS

Only use the correct fluid that is specified forthe system. Do not use mixed fluids.

When lubricating aircraft systems orcomponents, the aircraft must be in an areafree of sand, dirt and dust to prevent systemcontamination

Static grounding of the aircraft during servicingdecreases the risk of explosions caused byelectrical arcs from static electricity, lightningor stray currents.

When working with dimensions, volumes,pressures, temperature, density, etc., theinterpretation of correct units is very important.Always refer to conversion tables when indoubt.

Only use calibrated test equipment and toolsduring maintenance.

It is recommended that a recording of serialnumbers and calibration due dates of test toolsand equipment be kept for reference.


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APU

ADG

ADG PUMP

GROUND AIRCONDITIONING AIR

SINGLE−POINTREFUEL/DEFUEL

REFUEL/DEFUELCONTROL PANEL

FORWARDPOTABLEWATER

OXYGENREFILL

#1 & #2HYDRAULICSYSTEMS

AFT LAVATORYWASTE DRAIN

#3 HYDRAULICSYSTEM

FORWARDLAVATORYWASTE DRAIN

EXTERNALSERVICES

GROUNDPOWER

OVERWING GRAVITYFUEL FILLER

ENGINE STARTHIGH−PRESSURE AIR

LAVATORYPOTABLE WATER

OVERWING GRAVITYFUEL FILLER

BRAKEACCUMULATORS


Servicing PanelsFigure 12-00-00-000001

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On A/C 10001-10999, 15001-15990

TASK 12−10−00−001−A01REPLENISHING, SYSTEMS AND

COMPONENTS

INTRODUCTION

This section contains data for the servicing ofthe different aircraft systems that operate withliquids or gases. For detailed servicingprocedures refer to part 2 of the AircraftMaintenance Manual (AMM).

GENERAL

Servicing data is given for the systems thatfollow:

• Fuel System (Section 11-00)

• Hydraulic System (Section 12-00)

• Oil Systems (Section 13-00)

• Oxygen System (Section 16-00)

• Water and Waste System (Section 18-00)

• Scheduled Servicing (Section 20-00)

• Unscheduled Servicing (Section 30-00)


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On A/C 10001-10999, 15001-15990

TASK 12−11−00−001−A01REPLENISHING THE FUEL

SYSTEM

INTRODUCTION

The servicing procedures to refuel or defuelthe aircraft include pressure refueling, gravityrefueling and suction defueling.

GENERAL DESCRIPTION

Figure 12-11-00-000001.

For pressure refueling it is necessary to havea pressure source at the refuel/defuel adapter.

For suction defueling it is necessary to have asuction source at the refuel/defuel adapter.

Gravity refueling is done through two overwinggravity filler caps. Gravity refueling only fillsthe wing tanks. To put fuel in the center tank,fuel transfer is used.

PRESSURE REFUELING

Pressure refueling operations are done with apressurized fuel source connected to therefuel/defuel adapter. The refuel/defueladapter is installed at the leading edge of theright wing root. The operator controls therefueling operation from the refuel/defuelcontrol panel.

SUCTION DEFUELING

Pressure defueling operations are done with asuction source connected to the refuel/defueladapter. The refuel/defuel adapter is installedat the leading edge of the right wing root. Theoperator controls the defueling operation fromthe refuel/defuel control panel.

GRAVITY REFUELING

The gravity refuel is accomplished through theflush overwing gravity filler caps when apressurized refueling source is not available.There is one gravity filler cap for each wingtank. A grounding socket is provided on eachwing near the filler cap for grounding therefueling nozzle.


When refueling, make sure that the aircraft ison level ground. This will ensure that theaircraft fuel tanks accept the correct ormaximum amount of fuel

Make sure that the aircraft is electricallygrounded at all times when it is parked formaintenance or during bad weather. Staticelectrical charges in the aircraft can causeinjury to persons and damage to equipment

Obey all local safety regulations and fuelsafety precautions when working on the fuelsystem and fuel system components. Failureto obey the safety precautions can causeinjury to persons and damage to equipment.

Make sure that the fuel tender, the aircraft andthe fuel nozzle are grounded before refuelingor defueling the aircraft. A static electricalspark during the procedure can cause anexplosion or fire.

Make sure that the defuel adapter, the fuelcontainer, and the aircraft are grounded beforegravity defueling the aircraft. A static electricalspark can cause an explosion or fire.

Gravity defueling must be done in an open,well ventilated area. Fuel and fuel fumes aretoxic and highly explosive. This can causeinjury to person and damage to the aircraftequipment.

Obey all local safety regulations and fuelsafety precautions when discarding waste fuel.


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Waste fuel can cause contamination of theenvironment.

Ensure the overwing filler caps are chained tothe wing. This is to prevent an unsecured fillercap from flying off.

Draining water contamination from the bottomof the fuel tanks must be done before flight.This will make sure that the engines operatecorrectly and can also prevent corrosion of thefuel system components.

Use of fungicide additives are highlyrecommended. The additives are used tosterilize and to keep the fuel system free offungus and/or microbial life.

Before refueling, the wheel chocks should bemoved a short distance away from the tires.This is done to prevent the chocks from beingcaught when the tires spread out with theadditional fuel weight.


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GRAVITY FILLER CAP

REFUEL/DEFUEL CONTROL PANEL

PRESSURE−REFUEL / DEFUELADAPTER DOOR

D

WATER DRAIN VALVE

D

A

C

C

B

B

EF

F

E

C

A

D


Refueling Points and DrainsFigure 12-11-00-000001

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On A/C 10001-10999, 15001-15990

TASK 12−12−00−001−A01SERVICING THE HYDRAULIC

SYSTEM

INTRODUCTION

Replenishment of the hydraulic systemsincludes the procedures to do quantity checksand to add fluid and/or compressed gas to thesystems. The hydraulic systems use aphosphate ester-based hydraulic fluid andnitrogen gas.

GENERAL DESCRIPTION

The aircraft hydraulic systems supply fluid andpower to many aircraft components for systemoperation and control. The hydraulic fluid andcompressed gas in the landing gear shockstruts absorb the shock during landing. Thesystems and components that requirehydraulic servicing are as follows:

• Hydraulic systems no. 1, 2, and 3.

• Landing gear shock struts

• Air driven generator (ADG)

REPLENISHING THE HYDRAULICSYSTEMS

Figure 12-12-00-000001.

Three bootstrap-type hydraulic reservoirssupply fluid to the systems. Each of thereservoir bootstrap chamber is pressurized toprevent pump cavitation during start-up.

Each reservoir has a quantity indicator thatreads from 0 to 100 percent. In the flightcompartment, hydraulic fluid quantity can bechecked on the EICAS “HYDRAULIC” synopticpage.

The components and servicing points forsystems no. 1 and 2 are located in the aftequipment compartment. The components for

system no. 3 are in the aft wing box structure.The servicing point for no. 3 hydraulic systemis at the right rear wing root.

REPLENISHING THE LANDING GEAR

The landing gear shock struts are filled with amineral-based hydraulic fluid. The shock strutsare charged with compressed nitrogen. Aplacard on each shock strut provides data forservicing.

The main landing gear uses hydraulic fluid andcompressed nitrogen in the same chamber toact as a shock absorber. Fluid andcompressed nitrogen are forced through acalibrated orifice controlled by a metering pin.This restriction in fluid transfer absorbs theloads imposed on the landing gear duringlanding.

The nose landing gear hydraulic fluid andcompressed nitrogen are contained inindividual chambers, separated by a floatingpiston. The movement of the pistoncompressing the nitrogen absorbs the loadsimposed on the landing gear during landing.

REPLENISHING THE AIR DRIVENGENERATOR (ADG)

Figure 12-12-00-000002.

The ADG has a separate hydraulic system thatis used to retract the ADG after it has beendeployed. The retraction system consists of areservoir and hand pump that is filled withmineral-based hydraulic fluid.


Before starting work on the ADG, make surethat all applicable safety precautions havebeen reviewed and understood.

Safety precaution must be used when workingaround highly toxic phosphate ester-basedhydraulic fluids.


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Obey all operator policies and local regulationswhen discarding waste/drained hydraulic fluid.


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QUICKDISCONNECT

A

NO.3 HYDRAULIC SYSTEM SERVICE PANELA

CAP

QUICKDISCONNECT

CAP

QUICKDISCONNECT

CAP

NO. 2 HYDRAULIC SYSTEM SERVICE PANEL

NO. 1 HYDRAULIC SYSTEM SERVICE PANELC

C

B

B


Replenishing the Hydraulic SystemFigure 12-12-00-000001

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A

B FLOATING BALL (REF)

LOOKING AFT ONRESERVOIR SIGHT GAUGE B

A

ADG


Servicing - ADGFigure 12-12-00-000002

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On A/C 10001-10999, 15001-15990

TASK 12−13−00−001−A01OIL SYSTEM

INTRODUCTION

The function of the oil system is to providelubrication and cooling to the engine bearingsand gears. Servicing of the oil system includesthe procedures for quantity checks, draining,and to adding oil to the components thatfollow:

• Engine oil tanks

• Airframe mounted engine oil tank

• Auxiliary power unit (APU)

• Air turbine starter (ATS)

GENERAL DESCRIPTION

Figures 12-13-00-000001and 12-13-00-000003.

ENGINE OIL TANKS

Each engine is lubricated with oil contained inan external engine oil tank. Access to the oiltank is gained by opening the engine nacellesand core cowls. The engine oil supply can bemanually replenished at the engine, or throughan optional remote replenishment system inthe aft equipment compartment.

The servicing components for the engine oilsystem include the components that follow:

• Oil quantity sight gauge

• Oil quantity transmitter

• Oil tank

• Gravity fill port

• Remote filling system (optional)

When the oil level is low, oil is added directlyto the oil tank. Oil is drained from the tankwhen the level is too high or for maintenance

servicing. The oil tank level indicator isprovided near the upper gravity fill adapter. Ithas a power ON switch and a FULL indicatorlight. Engine oil quantity indication is alsoprovided on the EICAS MENU page. Thegravity filler port has a removable cap which isremoved when it is necessary to add oil to thetank manually. Oil can also be added to the oiltank through the remove fill connection.

AIRFRAME MOUNTED OIL TANK(OPTIONAL)

The optional, airframe mounted, remote oiltank is installed in the aft equipmentcompartment. The system allows maintenancepersonnel to fill the left and right engine oiltanks using oil from the remote tank. Thesystem is controlled from the remote engine oilservicing panel in the aft equipmentcompartment. The servicing components forthe remote replenishment system include:

• Oil replenishment tank

• Quantity sight gauge

• Selector valve

• Control panel

• Oil replenishment pump

A 28 Vdc electric pump supplies the engineswith oil from the replenishment tank. Thesupply pump is controlled from the controlpanel. Oil quantity indications of the engine oiltanks are supplied with the signal conditionerunit.

The control panel has the switch/lights thatfollow:

• “ON”PTT/POWER switch/light

• LH/RH FILL switch/light

• LH/RH 100% switch/light

On the control panel, push and hold the“ON”PTT/POWER switch/light and make surethat all three switch/lights illuminate. Release


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the PTT/POWER switch/light and make surethat the “ON” switch/light stays on and that theLH/RH FILL and LH/RH 100% switch/lights goout.

NOTE

When the PTT/POWER is pushed andreleased, electrical power to thereplenishment pump will only be availablefor 10 minutes.

To service an engine oil system, move thespring-loaded selector valve from the OFFposition and hold it to the applicable LH or RHposition. Make sure that the respective LH orRH FILL switch/light comes on. Continue tohold the selector valve until the respective100% switch/light comes on. At the same timethe respective FILL switch/light will go out andthe pump will stop. Release the selector valveto the OFF position.

Servicing of the remote replenishment oil tankis completed by the maintenance crew. To addoil, the filler cap is removed and the necessaryquantity of oil is added as shown by a sightgauge. Oil is drained from the tank using thedrain valve on the bottom of the tank.


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A

FILLERCAP

QUANTITYSIGHTGAUGE

VENT/OVERFLOWDRAIN

OIL SPILLDRAIN

TANKDRAIN

CONTROLPANELASSEMBLY

MANUALSELECTORVALVE

PUMP

OILREPLENISHMENTTANK

OIL LEVELCONTROL PANEL

A

LIGHTS

SWITCH

OIL LEVEL INDICATOR

GRAVITYFILL CAP

REAR MOUNTRING SUPPORT OIL TANK INTEGRAL

PART OF ACCESSORYDRIVE GEARBOX

G

SELECTOR VALVE

C

COMBUSTOR CASE FWD/

COMPRESSOR CASE AFT FLANGE

C

D

D

F G

F

B

E

B

E


Engine and Remote Oil ServicingFigure 12-13-00-000001

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ACCESSORYGEARBOXASSEMBLY (REF)

CHIPDETECTOR

OVERFLOWPLUG

FILL PLUG

AIR TURBINESTARTER


Air Turbine Starter Oil - ServicingFigure 12-13-00-000003

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AUXILIARY POWER UNIT (APU)

Figure 12-13-00-000002.

The APU is installed in a closed area in the tailcone of the aircraft. Servicing of the APU oilsystem is done manually.

The oil level is examined through the gravityfiller port found on the left side of the APU.The filler port has a cap which is removedwhen it is necessary to add oil to the APU oiltank. Oil must be manually added until itreaches the top edge of the cap. Oil is drainedfrom the oil tank by removing the drain plug atthe bottom of the APU oil tank.

AIR TURBINE STARTER (ATS)

There are two ATS units installed on theaircraft, one mounted on each engine. Whenservicing is necessary, the cowl doors for theengine are opened to gain access to the ATS.

The servicing components for the ATS oilsystem include the components that follow:

• Filler port

• Magnetic drain plug

To fill the ATS reservoir, the cap is firstremoved and oil is then added to the oil tankdirectly through the filler port. When the oil isat the bottom of the filler port threads, the oillevel is correct. If too much oil is added, itcomes out of the filler port.

To drain the ATS reservoir, the drain plug isremoved and the oil is permitted to flow out ofthe ATS oil tank. When the necessary quantityof oil is drained, the drain plug is installed.


Before examining the ADG oil level, make surethat the aircraft is parked on level ground.


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APU OIL − SERVICINGA

B

OIL FILTER & SIGHT GAUGEB

C

OIL SERVICE CAP

A

FULL

ADD

FULL

ADD

C


APU Oil ServicingFigure 12-13-00-000002

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On A/C 10001-10999, 15001-15990

TASK 12−16−00−001−A01REPLENISHING THE OXYGEN

SYSTEM

INTRODUCTION

Replenishing of the oxygen system is throughthe oxygen ground servicing panel located onthe right side of the forward fuselage.

GENERAL DESCRIPTION

Figure 12-16-00-000001.

The oxygen replenishment system has thecomponents that follow:

• Oxygen storage cylinder and regulatorassembly

• Oxygen ground servicing panel pressuregauge

• Oxygen filler valve

• Oxygen pressure transducer

OXYGEN STORAGE CYLINDERS ANDREGULATOR ASSEMBLY

The oxygen storage cylinders and regulatorassemblies are located in an enclosure to therear of the crew wardrobe.

OXYGEN GROUND SERVICING PANELPRESSURE GAUGE

The oxygen ground servicing panel pressuregauge is installed on the oxygen groundservicing panel. It is mechanical and indicatesthe total oxygen pressure in the cylinders. Thisgauge has a range of 0 to 2000 psi, in 100 psiincrements.

OXYGEN FILLER VALVE

The oxygen filler valve is used by the groundcrew to fill the oxygen storage cylinders.

OXYGEN PRESSURE TRANSDUCER

The EICAS STATUS page shows the totaloxygen pressure in the oxygen storagecylinders. The oxygen pressure transducer is asealed unit that has provisions to compensatefor temperature changes. The transducersends electrical signals to the engineindication and crew alerting system (EICAS).

The temperature correction chart must beused when servicing the oxygen system. Thisis done by comparing the oxygen pressureindication on the EICAS STATUS page withthe pressure indication given by the groundservicing panel pressure gauge.


Use the pressure versus temperaturecorrection chart when filling the oxygensystem.

Ensure dirt, oil, grease or solvents do not geton hands, clothing, system components or onequipment in service. These substances canburn or explode on contact with pressurizedoxygen.


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CREW OXYGEN BOTTLE

FWD

TO "FULL" PRESSURE200 PSI/MIN

NOT TO EXCEEDCHARGE CYL. AT RATEOXY. CYL. SERVICING

PRESS. PSIFULL

TEMP. C°AMBIENT

0

500

10001500

2000

PSIOILUSE NO

OXYGENSUPPLY PRESSURE

A

A

19901900180517101620153014351340

382716

−7−18−29−40

5

PRESS. PSIFULL

TEMP. C°AMBIENT


Replenishing the Oxygen SystemFigure 12-16-00-000001

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TASK 12−18−00−001−A01WATER AND WASTE

INTRODUCTION

The potable/wash water system stores andsupplies heated and pressurized water to thegalleys and lavatories. A drain systemremoves waste water from the sinks. Theaircraft also has provisions for storing, flushingand removing lavatory waste.

GENERAL DESCRIPTION

Figures 12-18-00-000001and 12-18-00-000002.

POTABLE/WASH WATER SYSTEM

The potable/wash water system stores,supplies and controls the flow of water to thegalleys and lavatories. The water/wastereplenishing system includes procedures forquantity checks, draining, flushing and fillingthe lavatory waste waster system.

POTABLE/WASH WATER SYSTEMREPLENISHING

The aft potable/wash water has a 10.1 U.S.gallon tank that is replenished through anexterior service panel. The service panel islocated on the left side of fuselage, aft of thewing. The forward potable/wash water has a11.5 U.S. gallon tank. The service panel islocated on right lower side of forward fuselage.The service panels include the componentsthat follow:

• Water fill connection

• Tank overflow outlet

• Tank drain/fill handle

• Tank full/empty level indicator lights

To fill the water tank, the operator connects awater pressure source to the water fill port,then the fill and drain T—handle is turned tothe right which opens the fill valve. When thetank is FULL water will flow out through theoverflow drain. The water quantity is alsochecked using the FULL/EMPTY water levellights on the potable water control panel in thegalley

When the fill/drain T-handle is turned to the leftit operates a drain valve on the bottom of thewater tank.


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POTABLE WATERSERVICING

TOILETSERVICING

POTABLE WATERSERVICING


Water and Waste ServicingFigure 12-18-00-000001

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AFT LAVATORY

WASTE DISPOSALPANEL

POTABLE/WASHWATER SYSTEM

FS928.00

FS281.00

GALLEY NO.1

POTABLE/WASH WATERSYSTEM AIR SUPPLY

POTABLE/WASHWATER SYSTEM

WATER FILL/DRAIN PANEL

WATER FILL/DRAIN PANEL


Water and Waste SystemFigure 12-18-00-000002

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WASTE WATER SYSTEM REPLENISHING

Figure 12-18-00-000003.

The lavatory waste water system isreplenished through a service panel at theright wing aft root fairing. The service panelincludes a waste outlet, a recharge port, awaste tank drain handle and a waste containerfull indicator light. The service panel has ahinged cover that latches closed. The cover isopened to connect the external waste drainline from a lavatory servicing cart to the wasteoutlet.

When the waste tank drain T-handle is pulledand turned left, it operates a drain valve on thebottom of the lavatory waste tank. When thevalve is opened, the contents of the wastetank flow under gravity, out of the waste outletinto the external drain line of the servicing cart.

Upon draining the waste, the recharging linefrom the servicing cart is connected to therecharge port. The waste tank is then flushedand filled with a fresh quantity of chemicalsolution. The T-handle must be turned towardthe right and pushed in to close the drain forfilling.

NOTE

THE T-HANDLE MUST BE IN THECLOSED AND LOCKED POSITIONBEFORE THE LAVATORY SERVICEPANEL CAN BE CLOSED.


Make sure all service panel ports are closedtight. Leaking fluids will turn to ice up at highaltitudes and may forms large masses, whichcan break off and cause damage to aircraft.

Make sure there is flushing solution in the tankbefore using the flush switch. This can causethe pump to run dry and overheat.

When the aircraft is parked overnight in verycold weather, all the water and lavatory fluidmust be drained to prevent freezing.

The filling and draining instructions are locatedon the back of the service panel and in part 2of the AMM.


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T−HANDLE

FILLPORT

FORWARD WATER / WASTE DOOR

WASTEOUTLET

RINSE/FILLPORT

T−HANDLE

FULL INDICATORLIGHT

VENT

WASTE DISPOSAL SYSTEM SERVICE PANEL


Water and Waste Servicing SystemFigure 12-18-00-000003

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On A/C 10001-10999

TASK 12−20−00−001−A01SCHEDULED SERVICING

INTRODUCTION

Scheduled servicing procedures include thosetasks included in the preventive maintenanceschedule of the aircraft. Generally, these arethe minimum standards established to makethe aircraft airworthy. Operators can usehigher approved standards to suit individualoperations.

GENERAL DESCRIPTION

Figures 12-20-00-000001, 12-20-00-000002,12-20-00-000003, 12-20-00-000004and 12-20-00-000005.

Scheduled servicing procedures include:

• Aircraft cleaning

• Lubrication

AIRCRAFT CLEANING

The exterior of the aircraft must be washedand polished to prevent deterioration of thepainted surfaces and corrosion of the polishedsurfaces. The interior surfaces, carpets andfurnishings must also be cleaned frequently.

Areas that require attention during cleaningare:

• Floor coverings

• Toilet enclosure

• Aircraft exterior

• Aircraft internal surfaces and furnishings

• Windshields

• Side windows

• Passenger windows

• Navigation lights

• Anticollision lights

• Landing/taxi light covers

LUBRICATION

Mechanical components require regularlubrication to make sure they operationcorrectly and to prevent corrosion. Lubricantsthat are used include grease, aerosollubricants, dry lubricant and siliconecompounds. Lubricants may be applied bygrease gun, oil can, aerosol spray, brush or byhand.

Aircraft areas that require regular lubricationinclude:

• Nose landing gear

• Nose landing gear doors

• Main landing gear

• Main landing gear doors

• Overwing emergency exits

• Baggage compartment door

• Passenger door

• Horizontal stabilizer trim actuator

• Flap and slat components

• Air-driven generator


Before starting a task, make sure that allsafety precautions are read and understood.

Always use approved window cleaningsolutions and procedures.

Before applying lubricants, make sure that thesurface area is free of all dirt and moisture.

Only use approved materials for servicing.

Remove unwanted lubricants after servicing.


TASK 12-20-00-001-A0112-20-00 Page 1

Jan 15/2005


Do a leak check if any fluid lines are replacedor disturbed.


TASK 12-20-00-001-A0112-20-00 Page 2

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UV

X

Y

Z

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LR

RP

ACAB

AA

Z

M. No. 3 hyd. sys. acc. charging pt., press. gauge & reservoir filler conn.. N. AFT toilet servicing. P. Engine oil storage tank. R. IDG oil servicing. T. No. 2 hydraulic system accumulator / fill point. U. No. 1 hydraulic system accumulator & rear interphone / fill point. V. H.P. ground air servicing. W. APU servicing. X. Tail bumper servicing. Y. Horizontal stab. trim actuator oil servicing. Z. Wing grounding points.AA. Forward toilet servicing (optional).AB. L.P. air conditioning connection.AC. Single point oil replenishment system.

LEGEND

Located on the lower side. Located on the upper side.A. Brake acc. charge.B. AC external power.C. Ground crew service panel with interphone.D. ADG oil servicing.E. NLG tire/oleo servicing/lubrication.F. Oxygen system charging valve & gauge.G. Potable Water servicing.H. Press. refuel/defuel panel & adapter.J. MLG tire/oleo servicing/lubrication.K. Fuel tank water drain (typical).L. Overwing gravity fuel filler.


Aircraft Servicing - LocationsFigure 12-20-00-000001

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GROUND AIR CONNECTIONA


Ground Air SupplyFigure 12-20-00-000002

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A

B

B

C

2

4

3

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LEGEND

1. Strut.2. Cap.3. Charge valve.4. Thin nut.

C

1

PRESSURE

PSIG

600

1500

1800

900

1200

2100

2400

200

300

DIMENSION ’ X ’ (INCHES)

0 2 4 6 8 10 12

RELEASE NITROGEN PRESSURE IN STRUT THROUGH CHARGING VALVE BEFORE DISASSEMBLY

MAINTENANCE : WITH AIRCRAFT ON THE GROUND THEACCEPTABLE PRESSURES ARE ASFOLLOWS : DIM ’ X ’

INCHES

111098

7654321

NOTE : FULLY EXTENDED PRESSURE : 341.50 PSIG.

" X "

WARNING

PRESSUREP 25 PSIG

429469516574

646737858

1024126616512340

1. REMOVE NITROGEN CHARGING VALVE CAPATTACH OVERFLOW LINE TO CHARGE VALVE MS28889−2

2. CONNECT MIL−H−5606 FLUID SUPPLY TO CHECK VALVE1C1010 AND FILL STRUT WITH HYDRAULIC FLUID UNTILNO BUBBLES ARE OBSERVED IN OVERFLOW LINE.

3. REMOVE FLUID SUPPLY AND REPLACE BLANKING CAP ONCHECK VAVLE.

4. CONNECT NITROGEN SOURCE TO CHARGING VALVE ANDPRESSURIZE STRUT TO OBTAIN VALVES SHOWN ON TABLE/GRAPH.

5. CLOSE CHARGING VALVE. REMOVE NITROGEN SOURCE ANDREPLACE CAP ON CHARGING VALVE.

AND OPEN CHARGE VALVE TO FULLY COMPRESS SHOCK STRUT.

SHOCK STRUT ASSY, MAIN LANDING GEARDESIGNED AND MANUFACTURED BY:Coltec Industries

MENASCO AEROSPACEOAKVILLE, ONTARIO, CANADACAGE CODE 02121

SUMITOMO PRECISION PRODUCTSAMAGASAKI, HYOGO, JAPANCAGE CODE 0ABG4

FABRICATED BY: FOR CRJ SERIES 700

PART No. 49200−

SERIAL No.

ASSY DATE:

ENGINEERING SPEC : D−458 FLUID : MIL−H−5606

INSTRUCTION FOR SERVICING

MOD. STATUS

S. B. NO. DATE


Main Landing Gear Shock Strut ExtensionFigure 12-20-00-000003

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2

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A

SHOCK STRUT ASSY, NOSE LANDING GEAR



PART No. 52100−

SERIAL No.

ASSY DATE:


WARNINGRELEASE NITROGEN PRESSURE IN STRUT THROUGH CHARGING VALVE BEFORE DISASSEMBLY



INCHESPRESSUREP 25 PSIG

12 21011 23010 2539 282

8 3187 3636 4225 5034 6213 8082 1142

NOTE : FULLY EXTENDED PRESSURE210 PSIG


1. ATTACH OVERFLOW LINE TO CHARGE VALVE MS28889−2AND OPEN CHARGE VALVE TO FULLY COMPRESS SHOCK STRUT.


3. REMOVE FLUID SUPPLY AND REPLACE BLANKING CAP ONCHECK VALVE.



MOD. STATUS

S. B. NO. DATEDESIGN AND MANUFACTURED BY:Coltec Industries


PRESSURE

PSIG

400

700

800

500

600

900

1300

1200

1000

200

300

2 3 4 5 6 7 8 9 10 11 12 X


Nose Landing Gear Shock StrutFigure 12-20-00-000004

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SYMBOL APPLICATION METHOD

OIL CAN

4

3

1

A

2

LEGEND

1. Fill plug.2. Packing.3. Fill port.4. Sight gauge.


Horizontal Stabilizer Trim Actuator Oil SystemFigure 12-20-00-000005

TASK 12-20-00-001-A0112-20-00 Page 7

Jan 15/2005


On A/C 15001-15990

TASK 12−20−00−001−AA1SCHEDULED SERVICING

INTRODUCTION

The scheduled servicing procedures includesaircraft lubrication and cleaning. Scheduledservicing procedures also include tasks in thepreventive maintenance schedule of theaircraft. Generally, these are the minimumstandards established to make the aircraftairworthy. Operators can use higher approvedstandards to suit individual operations.

GENERAL DESCRIPTION

Figures 12-20-00-000006, 12-20-00-000007,12-20-00-000008, 12-20-00-000009and 12-20-00-000010.

Scheduled servicing procedures include thetasks that follow:

• External and internal cleaning

• Lubrication

AIRCRAFT CLEANING

The exterior of the aircraft must be washedand polished to prevent deterioration of thepainted surfaces and corrosion of the polishedsurfaces. The interior surfaces, carpets andfurnishings must also be cleaned frequently.

The servicing procedures give the approvedmaterials, methods, and precautions forcleaning of the aircraft exterior, interior and thelavatory waste system.

Areas that require attention during cleaningare:

• Aircraft exterior

• Windshields

• Side windows

• Passenger windows

• Navigation light covers

• Anticollision light covers

• Landing/taxi light covers

• Aircraft internal surfaces and furnishings

• Floor coverings

• Toilet enclosure

LUBRICATION

Mechanical components require regularlubrication to make sure they operationcorrectly and to prevent corrosion. Lubricantsthat are used include greases, aerosollubricants, dry film lubricants and siliconecompounds. Lubricants may be applied bygrease gun, oil can, aerosol spray, brush or byhand application.

Aircraft areas that require regular lubricationinclude:

• Nose landing gear

• Nose landing gear doors

• Main landing gear

• Main landing gear doors

• Passenger door

• Galley service doors

• Baggage compartment doors

• Avionics compartment door

• Overwing emergency exits

• Horizontal stabilizer trim actuator

• Spoilers

• Flap and slat components

• Thrust reversers

• Air-driven generator


• Always use approved window cleaningsolutions and procedures.

• Before applying lubricants, make sure thatthe surface area is free of all dirt andmoisture.

• Only use approved materials for servicing.


TASK 12-20-00-001-AA112-20-00 Page 8

Jan 15/2005


• Remove unwanted lubricants after servicing.

• Do a leak check if any fluid lines arereplaced or disturbed.


TASK 12-20-00-001-AA112-20-00 Page 9

Jan 15/2005


babd

8a01

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BD

E

F G H

J

K

WG

L

M N

P

T

UV

X

Y

Z

C

LR

RP

ACAB

AA

Z

M. No. 3 hyd. sys. acc. charging pt., press. gauge & reservoir filler conn.. N. AFT toilet servicing. P. Engine oil storage tank. R. IDG oil servicing. T. No. 2 hydraulic system accumulator / fill point. U. No. 1 hydraulic system accumulator & rear interphone / fill point. V. H.P. ground air servicing. W. APU servicing. X. Tail bumper servicing. Y. Horizontal stab. trim actuator oil servicing. Z. Wing grounding points.AA. Forward toilet servicing (optional).AB. L.P. air conditioning connection.AC. Single point oil replenishment system.

LEGEND

Located on the lower side. Located on the upper side.A. Brake acc. charge.B. AC external power.C. Ground crew service panel with interphone.D. ADG oil servicing.E. NLG tire/oleo servicing/lubrication.F. Oxygen system charging valve & gauge.G. Potable Water servicing.H. Press. refuel/defuel panel & adapter.J. MLG tire/oleo servicing/lubrication.K. Fuel tank water drain (typical).L. Overwing gravity fuel filler.


Aircraft Servicing - LocationsFigure 12-20-00-000006

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GROUND AIR CONNECTIONA


Ground Air SupplyFigure 12-20-00-000007

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A

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1

PRESSURE

PSIG

600

1500

1800

900

1200

2100

2400

200

300


0 2 4 6 8 10 12

RELEASE NITROGEN PRESSURE IN STRUT THROUGH CHARGING VALVE BEFORE DISASSEMBLY


INCHES

111098

7654321

NOTE : FULLY EXTENDED PRESSURE : 341.50 PSIG.

" X "

WARNING

PRESSUREP 25 PSIG

429469516574

646737858

1024126616512340

1. REMOVE NITROGEN CHARGING VALVE CAPATTACH OVERFLOW LINE TO CHARGE VALVE MS28889−2


3. REMOVE FLUID SUPPLY AND REPLACE BLANKING CAP ONCHECK VAVLE.



AND OPEN CHARGE VALVE TO FULLY COMPRESS SHOCK STRUT.

SHOCK STRUT ASSY, MAIN LANDING GEARDESIGNED AND MANUFACTURED BY:Coltec Industries




PART No. 49200−

SERIAL No.

ASSY DATE:



MOD. STATUS

S. B. NO. DATE


Main Landing Gear Shock Strut ExtensionFigure 12-20-00-000008

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SHOCK STRUT ASSY, NOSE LANDING GEAR



PART No. 52100−

SERIAL No.

ASSY DATE:


WARNINGRELEASE NITROGEN PRESSURE IN STRUT THROUGH CHARGING VALVE BEFORE DISASSEMBLY



INCHESPRESSUREP 25 PSIG

12 21011 23010 2539 282

8 3187 3636 4225 5034 6213 8082 1142

NOTE : FULLY EXTENDED PRESSURE210 PSIG


1. ATTACH OVERFLOW LINE TO CHARGE VALVE MS28889−2AND OPEN CHARGE VALVE TO FULLY COMPRESS SHOCK STRUT.


3. REMOVE FLUID SUPPLY AND REPLACE BLANKING CAP ONCHECK VALVE.



MOD. STATUS

S. B. NO. DATEDESIGN AND MANUFACTURED BY:Coltec Industries


PRESSURE

PSIG

400

700

800

500

600

900

1300

1200

1000

200

300

2 3 4 5 6 7 8 9 10 11 12 X


Nose Landing Gear Shock StrutFigure 12-20-00-000009

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babk

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SYMBOL APPLICATION METHOD

OIL CAN

4

3

1

A

2

LEGEND

1. Fill plug.2. Packing.3. Fill port.4. Sight gauge.


Horizontal Stabilizer Trim Actuator Oil SystemFigure 12-20-00-000010

TASK 12-20-00-001-AA112-20-00 Page 14

Jan 15/2005


On A/C 10001-10999, 15001-15990

TASK 12−30−00−001−A01UNSCHEDULED SERVICING

INTRODUCTION

The unscheduled servicing of the aircraftincludes the servicing procedures that follow:

• Cold weather parking

• Snow removal

• Aircraft deicing/anti-icing standard practices

Cold weather protection includes theprocedures and precautions necessary toprevent damage to the aircraft caused by coldtemperatures.

GENERAL DESCRIPTION

COLD WEATHER PARKING

Special precautions must be taken when theaircraft is parked in an open area during coldweather. If the aircraft is parked for more thatseven days in cold weather, additionalprecautions must be taken.

SNOW REMOVAL

Accumulated snow must be removed from theaircraft structure and adjacent area when:

• The depth of the snow is more thanpermitted limits on the aircraft wings,horizontal stabilizer or fuselage

• Higher than usual temperatures causefreezing rain or melted snow

• The depth of the snow below and around theaircraft prevents the regular inspection of theaircraft

• It is necessary to move the aircraft

AIRCRAFT DEICING/ANTI-ICINGSTANDARD PRACTICES

Industry and regulatory agencies issueinformation, precautions and standardpractices to prevent snow, ice, and frost fromaccumulating on the aircraft. The operatormust use the correct procedures for theambient weather conditions. This must includedeicing and anti-icing.

Aircraft deicing is to be done to remove frost,ice or snow that collects on the aircraftsurfaces.

Aircraft anti-icing is done using an anti-icingfluid mixture applied to the aircraft surfaces.This is done to make sure that ice, snow orfrost does not collect on the aircraft surfaces.


Obey all safety precautions, when deicing theaircraft with the APU air intake door open. Ifthe APU is in operation, the entry of deicingfluid may cause the APU to shut down or maycause contamination of the passengercompartment conditioned air system.


TASK 12-30-00-001-A0112-30-00 Page 1

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aircraft maintenance manual - part i system description

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