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HIGHLIGHTS__________

REVISION NO. 43 Aug 01/01

Pages which have been revised are outlined below, together with the Highlights of theRevision

-------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY

PAGES-------------------------------------------------------------------------------------

CHAPTER 71__________

L.E.P. 1- 6 REVISED TO REFLECT THIS REVISION INDICATINGNEW,REVISED, AND/OR DELETED PAGES

71-00-00 CORRECTION/ADDITION/AMPLIFICATION 001-099,512 REVISED SAFETY PRECAUTIONS FOR THE

ENGINE IGNITION SYSTEM

71-HIGHLIGHTS Page 1 of 1REVISION NO. 43 Aug 01/01

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CHAPTER 71__________

POWER PLANT

LIST OF EFFECTIVE PAGES_______________________N, R or D indicates pages which are New, Revised or Deleted respectivelyRemove and insert the affected pages and complete the Record of Revisions and

the Record of Temporary Revisions as necessary

CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE

RECORD 71-00-00 416 May01/01 71-00-00 504 Feb01/99OF TEMP. 71-00-00 417 Feb01/00 71-00-00 505 Feb01/99REVISION 71-00-00 418 Feb01/00 71-00-00 506 Feb01/99

71-00-00 419 Feb01/00 71-00-00 507 Feb01/99L.E.P. R 1- 6 Aug01/01 71-00-00 420 Feb01/00 71-00-00 508 Feb01/99T. of C. 1 Feb01/00 71-00-00 421 Feb01/00 71-00-00 509 Feb01/99T. of C. 2 May01/01 71-00-00 422 Feb01/00 71-00-00 510 Feb01/99T. of C. 3 May01/01 71-00-00 423 Feb01/00 71-00-00 511 Feb01/99T. of C. 4 May01/01 71-00-00 424 Feb01/00 71-00-00 R 512 Aug01/01T. of C. 5 May01/01 71-00-00 425 Feb01/00 71-00-00 513 Feb01/99T. of C. 6 May01/01 71-00-00 426 Feb01/00 71-00-00 514 Feb01/99T. of C. 7 May01/01 71-00-00 427 May01/01 71-00-00 515 Feb01/99T. of C. 8 May01/01 71-00-00 428 May01/01 71-00-00 516 Feb01/99

71-00-00 429 May01/00 71-00-00 517 May01/0171-00-00 1 Feb01/99 71-00-00 430 May01/00 71-00-00 518 May01/9971-00-00 2 Feb01/99 71-00-00 431 Feb01/00 71-00-00 519 Feb01/9971-00-00 3 Feb01/99 71-00-00 432 Feb01/00 71-00-00 520 May01/9971-00-00 4 Feb01/99 71-00-00 433 Feb01/00 71-00-00 521 Feb01/9971-00-00 5 Feb01/99 71-00-00 434 Feb01/00 71-00-00 522 May01/9971-00-00 6 Feb01/99 71-00-00 435 Feb01/00 71-00-00 523 Feb01/0071-00-00 201 Feb01/99 71-00-00 436 Nov01/00 71-00-00 524 May01/99

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71-73-49 435 Feb01/99 71-73-49 606 Feb01/9971-73-49 436 Feb01/99 71-73-49 607 Feb01/9971-73-49 437 Feb01/99 71-73-49 701 Feb01/9971-73-49 438 Feb01/99 71-73-49 702 Feb01/9971-73-49 439 Feb01/99 71-73-49 703 Feb01/9971-73-49 440 Feb01/99 71-73-49 704 Feb01/9971-73-49 441 Feb01/99 71-73-49 705 Feb01/9971-73-49 442 Feb01/9971-73-49 443 Feb01/9971-73-49 444 Feb01/9971-73-49 445 Feb01/9971-73-49 446 Feb01/9971-73-49 447 Feb01/9971-73-49 448 Feb01/9971-73-49 449 Feb01/9971-73-49 450 Feb01/9971-73-49 451 Feb01/9971-73-49 452 Feb01/9971-73-49 453 Feb01/9971-73-49 454 Feb01/9971-73-49 455 Feb01/9971-73-49 456 Feb01/9971-73-49 457 Feb01/9971-73-49 458 Feb01/9971-73-49 459 Feb01/99

71-73-49 460 Feb01/9971-73-49 461 Feb01/9971-73-49 462 Feb01/9971-73-49 463 Feb01/9971-73-49 464 Feb01/9971-73-49 465 Feb01/9971-73-49 466 Feb01/9971-73-49 467 Feb01/9971-73-49 468 Feb01/9971-73-49 469 Feb01/9971-73-49 470 Feb01/9971-73-49 471 Feb01/9971-73-49 472 Feb01/99

71-73-49 473 Feb01/9971-73-49 474 Feb01/9971-73-49 475 Feb01/9971-73-49 476 Feb01/9971-73-49 477 Feb01/9971-73-49 478 Feb01/9971-73-49 479 Feb01/9971-73-49 480 Feb01/99


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CHAPTER 71__________

POWER PLANT

TABLE OF CONTENTS_________________

SUBJECT CH/SE/SU C PAGE EFFECTIVITY_______ ________ _ ____ ___________

POWER PLANT - GENERAL 71-00-00_____________________DESCRIPTION AND OPERATION 1 001-099,

General 1 001-099,Description 1 001-099,Engine 1 001-099,Cowling 1 001-099,Mounts 6 001-099,Attachment Fittings 6 001-099,Fire Seals 6 001-099,Electrical Harness 6 001-099,Engine Drains 6 001-099,

MAINTENANCE PRACTICES 201 001-099,Oil Circuit Air Flow Check 201 001-099,

REMOVAL/INSTALLATION 401 001-099,Removal of the Power Plant 401 001-099,Installation of the Power Plant 426 001-099,

ADJUSTMENT/TEST 501 001-099,Wind Limitations During Engine 501 001-099,Ground OperationsSafety Precautions During Engine 504 001-099,Ground OperationsDry Motoring Check 516 001-099,Wet Motoring Check 525 001-099,Engine Automatic Start 534 001-099,Engine Manual Start 543 001-099,

Start Abort 553 001-099,Minimum Idle Check 555 001-099,Power Assurance Check 561 001-099,Vibration Check 582 001-099,Accel Check 586 001-099,Engine Shutdown 591 001-099,Fan Trim Balance - 1 Sensor 3 593 001-099,SpeedFan Trim Balance - 1 Sensor 1 A538 001-099,SpeedAbnormal Operation and Emergency A544 001-099,ProceduresLeak Test of the Accessory-Gearbox A556 001-099,

(AGB) Carbon SealLeak Check after the Replacement A579 001-099,of a Sealol Seal or a MagneticSeal on the AGB Drive Pads of theIDG, Hydraulic Pump, Starter andFuel PumpLeak Test of the Accessory Gearbox A583 001-099,pad (AGB) Starter cavity (between

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equipement and AGB)Fuel or Hydraulic or Oil Leakage A587 001-099,LimitsDrain Mast Leakage Identification A594 001-099,Procedure

COWLING 71-10-00_______DESCRIPTION AND OPERATION 1 001-099,

General 1 001-099,

AIR INTAKE COWL 71-11-00DESCRIPTION AND OPERATION 1 001-099,

General 1 001-099,Description 1 001-099,Air Intake Cowl Configuration 1 001-099,Air Intake Cowl Anti-icing 1 001-099,Air Intake Cowl Access 8 001-099,Air Intake Cowl Acoustic 8 001-099,TreatmentAir Intake Cowl Structure 8 001-099,

REMOVAL/INSTALLATION 401 001-099,Removal of the Air Intake Cowl 401 001-099,Installation of the Air Intake 407 001-099,Cowl

INSPECTION/CHECK 601 001-099,

Visual Inspection of the Air 601 001-099,Intake CowlGeneral Visual Inspection of 619 001-099,Intake Cowl Aft Bulkhead

FAN COWL 71-13-00DESCRIPTION AND OPERATION 1 001-099,

General 1 001-099,Description 1 001-099,Opening/Closing 1 001-099,Access Doors 1 001-099,Pressure Relief Door 438BR 10 001-099,(448BR)

Fan Cowl Structure 10 001-099,MAINTENANCE PRACTICES 201 001-099,Opening of the Fan Cowl Doors 201 001-099,Closing of the Fan Cowl Doors 206 001-099,

ADJUSTMENT/TEST 501 001-099,Adjustment of the Fan Cowl Doors 501 001-099,Functional Test of Fan Cowl Latch 511 001-099,Tensions

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COWL DOORS - FAN 71-13-11REMOVAL/INSTALLATION 401 001-099,

Removal of the Fan Cowl Doors 401 001-099,Installation of the Fan Cowl Doors 405 001-099,

INSPECTION/CHECK 601 001-099,Visual Inspection of the Fan Cowl 601 001-099,DoorsFunctional Check of the Pressure 609 001-099,Relief Door on the Right Hand FanCowlDetailed Visual Inspection of the 613 001-099,Fan Cowl Doors to Check forMismatch at the Air Intake Cowl.

ROD - FAN COWL DOOR HOLD OPEN 71-13-12REMOVAL/INSTALLATION 401 001-099,

Removal of the Hold-open Rod of 401 001-099,the Fan Cowl DoorInstallation of the Hold-open Rod 405 001-099,of the Fan Cowl Door

LATCH - FAN COWL DOOR 71-13-13REMOVAL/INSTALLATION 401 001-099,

Removal of the Fan Cowl Door 401 001-099,LatchesInstallation of the Fan Cowl Door 404 001-099,Latches

INSPECTION/CHECK 601 001-099,Detailed Visual Inspection of the 601 001-099,Fan Cowl Latches, Fittings andHingesDetailed Visual Inspection of the 604 001-099,Keeper Assy Fan Cowl LockingDevice

STRAKE - AERODYNAMIC, FAN COWL 71-13-15REMOVAL/INSTALLATION 401 001-099,

Removal of the Aerodynamic Strake 401 001-099,from the Fan Cowl DoorInstallation of the Aerodynamic 405 001-099,Strake on the Fan Cowl Door

MOUNTS 71-20-00______DESCRIPTION AND OPERATION 1 001-099,

General 1 001-099,

FORWARD MOUNT 71-21-00DESCRIPTION AND OPERATION 1 001-099,

Description 1 001-099,


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MOUNT - FORWARD 71-21-11REMOVAL/INSTALLATION 401 001-099,

Removal of the Forward Engine 401 001-099,MountInstallation of the Forward Engine 404 001-099,MountRemoval of the Forward Engine 410 001-099,Mount Bolts One at a TimeInstallation of the Forward Engine 414 001-099,Mount Bolts One at a TimeRemoval of the Forward Engine 418 001-099,Mount Links and Cross BeamAssembly without Engine RemovalInstallation of the Forward Engine 424 001-099,Mount Links and Cross BeamAssembly without Engine Removal

INSPECTION/CHECK 601 001-099,Detailed Visual Inspection of the 601 001-099,Forward Engine Mount with theEngine InstalledDetailed Visual Inspection of the 611 001-099,Forward Engine Mount with theEngine Removed

AFT MOUNT 71-22-00

DESCRIPTION AND OPERATION 1 001-099,Description 1 001-099,MOUNT - AFT 71-22-11

REMOVAL/INSTALLATION 401 001-099,Removal of the Aft Engine Mount 401 001-099,Installation of the Aft Engine 405 001-099,MountRemoval of the Aft Engine Mount 408 001-099,without Engine RemovalInstallation of the Aft Engine 418 001-099,Mount without Engine Removal

INSPECTION/CHECK 601 001-099,Detailed Visual Inspection of the 601 001-099,

Aft Engine Mount with the EngineRemovedDetailed Visual Inspection of the 603 001-099,Aft Engine Mount with the EngineInstalled

ATTACH FITTINGS (FOR SYSTEM INSTALLATION 71-40-00________________________________________ONLY)_____


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DESCRIPTION AND OPERATION 1 001-099,General 1 001-099,

ELECTRICAL HARNESS 71-50-00__________________DESCRIPTION AND OPERATION 1 001-099,

General 1 001-099,Description 1 001-099,Fan Harnesses 1 001-099,Core Harness 4 001-099,Attachment and Connection 4 001-099,

INSPECTION/CHECK 601 001-099,Visual Inspection of the Power 601 001-099,Plant Wire HarnessesContinuity Check-Power Plant Wire 611 001-099,Harnesses WiresShorted Wire and Insulation 614 001-099,Resistance Check-Power Plant WireHarnesses Wires

ELECTRICAL HARNESS - FAN ZONE 71-51-44REMOVAL/INSTALLATION 401 001-099,

Removal of the Generator Power 401 001-099,Harness 238W0903Installation of the Generator 407 001-099,Power Harness 238W0903Removal of the Thrust Reverser 414 001-099,

Harness 238W0908Installation of the Thrust 424 001-099,Reverser Harness 238W09098Removal of the Integrated Drive 431 001-099,Genetor (IDG) Control and Anti-iceHarness 238W0904Installation of the Integrated 441 001-099,Drive Generator (IDG) Control andAnti-ice Harness 238W0904Removal of the Electronic Control 448 001-099,Unit (ECU) Channel A Harness238W0904Installation of the Electronic 460 001-099,

Control Unit (ECU) Channel AHarness 238W0904Removal of the Electronic Control 467 001-099,Unit (ECU) Channel B Harness238W0904Installation of the Electronic 479 001-099,Control Unit (ECU) Channel BHarness 238W0904


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Removal of the Vibration Sensor 486 001-099,Harness 238D0912Installation of the Vibration 494 001-099,Sensor Harness 238D0912Removal of the Left Side Harness 499 001-099,238W0904Installation of the Left Side A412 001-099,Harness 238W0904

ELECTRICAL HARNESS - CORE ZONE 71-52-43REMOVAL/INSTALLATION 401 001-099,

Removal of the Electrical Harness 401 001-099,of the Core ZoneInstallation of the Electrical 412 001-099,Harness of the Core Zone

POWER PLANT DRAINS 71-70-00__________________DESCRIPTION AND OPERATION 1 001-099,

General 1 001-099,Drain and Vent System 1 001-099,Collector 1 001-099,Module Assembly 1 001-099,Drain Mast 1 001-099,

System Operation 1 001-099,DRAIN MODULE 71-71-41

REMOVAL/INSTALLATION 401 001-099,

Removal of the Drain Module 401 001-099,Installation of the Drain Module 404 001-099,MAST - DRAIN 71-71-42

REMOVAL/INSTALLATION 401 001-099,Removal of the Drain Mast 401 001-099,Installation of the Drain Mast 405 001-099,

INSPECTION/CHECK 601 001-099,Visual Inspection of the Drain 601 001-099,Mast Outlet

DRAIN MANIFOLD MODULE 71-71-43REMOVAL/INSTALLATION 401 001-099,

Removal of the Drain Manifold 401 001-099,Module

Installation of the Drain Manifold 405 001-099,ModuleTUBES - OIL HYDRAULIC AND WATER DRAIN 71-73-49

REMOVAL/INSTALLATION 401 001-099,Removal of the Oil Tank Drain Tube 401 001-099,and HoseInstallation of the Oil Tank Drain 406 001-099,Tube and Hose


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Removal of the Fan Case Drain Tube 409 001-099,Installation of the Fan Case Drain 411 001-099,TubeRemoval of the Fuel Pump Drain 414 001-099,TubesInstallation of the Fuel Pump 417 001-099,Drain TubesRemoval of the Fuel Servos Drain 420 001-099,TubesInstallation of the Fuel Servos 424 001-099,Drain TubesRemoval of the Fuel Overboard 427 001-099,Drain TubeInstallation of the Fuel Overboard 429 001-099,Drain TubeRemoval of the Heat Exchanger 432 001-099,Drain TubeInstallation of the Heat Exchanger 435 001-099,Drain TubeRemoval of the Hydro Mechanical 438 001-099,Unit (HMU) Drain TubeInstallation of the Hydro 440 001-099,Mechanical Unit (HMU) Drain TubeRemoval of the Hydraulic Pump 443 001-099,Drain Tube

Installation of the Hydraulic Pump 445 001-099,Drain TubeRemoval of the Forward Oil Sump 448 001-099,Drain TubeInstallation of the Forward Oil 450 001-099,Sump Drain TubeRemoval of the Reservoir To 453 001-099,Manifold Hydraulic Oil Drain TubeInstallation of the Reservoir To 455 001-099,Manifold Hydraulic Oil Drain TubeRemoval of the Reservoir To 457 001-099,Manifold Oil Drain TubeInstallation of the Reservoir To 459 001-099,

Manifold Oil Drain TubeRemoval of the Reservoir To 462 001-099,Manifold Pressurized Air DrainTubeInstallation of the Reservoir To 464 001-099,Manifold Pressurized Air DrainTubeRemoval of the Starter Pad Oil 466 001-099,


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Drain TubeInstallation of the Starter Pad 468 001-099,Oil Drain TubeRemoval of the IDG Oil Drain Tube 470 001-099,Installation of the IDG Oil Drain 472 001-099,TubeRemoval of the Turbine Rear Frame 474 001-099,(TRF) Drain TubeInstallation of the Turbine Rear 477 001-099,Frame (TRF) Drain Tube

INSPECTION/CHECK 601 001-099,Inspection of the Oil, Hydraulic, 601 001-099,and Water Drain Tubes

CLEANING/PAINTING 701 001-099,Cleaning Tubes-Oil, Hydraulic and 701 001-099,Water Drain


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POWER PLANT - GENERAL - DESCRIPTION AND OPERATION_________________________________________________

1. General_______Each engine is housed in a nacelle suspended from a pylon attached to thewing lower surface.The right and left power plant are interchangeable. Except the cascades thatprovide specific efflux pattern control during reverse operation.

The demountable power plant consists of the engine and its accessories, theengine air intake, the primary exhaust (including centerbody), the enginemounts.

2. Description___________

A. Engine(Ref. Fig. 001)The engine is a dual-rotor, variable stator, high-bypass ratio turbofanpower plant. The design and configuration of the engine are based onobtaining long life high reliability and easy access for linemaintenance.It is a modular design which permits the changing of a major assemblywithout complete dissassembly of the engine. The principal modules of theengine are low pressure compressor (fan stator and fan rotor), highpressure compressor, turbine frame, combustion chamber, high pressureturbine, low pressure turbine and gearbox.The weight of the demountable power plant is approximately 5147 lbs (2335kg).

B. Cowling(Ref. Fig. 002, 003, 004)The cowling assembly consists of:- the air intake cowl,- the fan cowl,

- the fan reverser,- the primary exhaust (primary nozzle and center body).The fan reverser and the primary exhaust are covered by chapter 78.The hinged fan reverser and fan cowls are attached to the pylon.The fan cowls are hinged at the upper part by three hinges.They are held open by hold-open rods providing access to the engine for:- maintenance,- rigging,- trouble shooting.The composite components of the nacelle incorporate a lightningprotection system consisting of:- a conductive graphite material within the skin.Mechanical attachments and fittings conduct the current into the

pylon/engine structure.

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Engine - SchematicFigure 001

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NacelleFigure 002

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Nacelle DimensionsFigure 003

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Lightning ZonesFigure 004

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(Ref. 71-20-00)The engine is attached to the pylon by two damage tolerant mounts. Themounts are the main attaching structures (forward and aft).The forward mount comprises four attach bolts that connect the enginedirectly to the pylon.The aft mount consists of a link and beam system attaching the engine to

the pylon.

D. Attachment Fittings(Ref. 71-40-00)The attachment fittings and support brackets ensure the attachment on theengine of:- components,- ducts,- pipes,- electrical cables.The attachment fittings and support brackets are attached on:- the engine core,- the fan case,- the accessories,- the accessory gearbox.

E. Fire SealsThe fire seals provide fire protection between the engine compartments(fan and core compartments). The fire seals separate the space within theengine into compartments.This provides a means of isolation to limit fire propagation.

F. Electrical Harness(Ref.71-50-00)The engine electrical harness serves for connection with the electrical

components mounted in the nacelle pylon.The engine electrical harness:

(1) distributes the power required by the aircraft electrical system,

(2) transmits signals for:- nacelle sub-systems,- engine control,- monitoring functions.

G. Engine Drains(Ref. 71-70-00)The drain and vent system consists of lines collecting and carrying waste

fluids and vapors overboard.This system drains accessories and engine components.

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POWER PLANT - GENERAL - MAINTENANCE PRACTICES_____________________________________________

TASK 71-00-00-820-001

Oil Circuit Air Flow Check

1. Reason for the Job__________________

Use this procedure to calibrate the test rig and to do the check of theengine oil circuits.

2. Job Set-up Information______________________

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION-------------------------------------------------------------------------------

No specific test rig856A2662 1 TOOL KIT - MASTER AIR NOZZLE856A3267 1 ADAPTER, TEST RIG - AIR FLOW CHECK

B. Referenced Information

-------------------------------------------------------------------------------REFERENCE DESIGNATION-------------------------------------------------------------------------------

71-00-00-991-921 Fig. 20171-00-00-991-922 Fig. 20271-00-00-991-923 Fig. 203

3. Job Set-up__________

Subtask 71-00-00-869-213

A. Not Applicable.

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4. Procedure_________

(Ref. Fig. 201/TASK 71-00-00-991-921, 202/TASK 71-00-00-991-922, 203/TASK71-00-00-991-923)

Subtask 71-00-00-820-056

A. Calibration of the Air Flow Test RigIt is necessary to calibrate the test rig used for the oil circuit airflow check. This calibration permits to check an air flow range from 7.3to 74.6 pph (2.7 to 28 m3/h), which can be used on all CFM56 engines.

(1) Connect the test rig air compressed air supply fitted with ADAPTER,TEST RIG - AIR FLOW CHECK (856A3267G02), to TOOL KIT - MASTER AIRNOZZLE (856A2662G01).

(2) Firmly hold the body of the master air nozzle.

(3) One after the other, put the 3 jets, calibrated hole first, insidethe body of the tool.

(4) Measure the air flow rate with each jet, under the test conditionswhich follow:

(a) Pressure: 19.8 psig (137 kPa)

(b) Temperature: 68 deg.F (20 deg.C)

(c) Characteristics of the air supply hose installed between the testrig and the master air nozzle:

NOTE : You must use the same hose when you do the airflow tests.____

1 Minimum section: 0.1 in.2 (64 mm2)_

2 Maximum length: 13 ft. (4 m)_

(d) The standard flow rates to be obtained, are given in the table201.

(5) Correct the flow rates given in table 201, with the formula given in(Ref. Fig. 203/TASK 71-00-00-991-923)figure, for direct comparison with the flow indicated on theflowmeter.

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Connection of the Master Air Nozzle to the AdapterFigure 201/TASK 71-00-00-991-921

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Test Rig for Engine Oil Circuit Air Flow CheckFigure 202/TASK 71-00-00-991-922

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Formula for the Calculation of the Correction FactorFigure 203/TASK 71-00-00-991-923

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C F M 56 -----------------------------------------------------------------------------| JET DIAMETER | || | AIR FLOW RATES ||(ENGRAVED ON JETS) | ||---------------------------------------------------------------------------|| in. | mm | PPH | KG/H | SCFM | M3/H ||---------------------------------------------------------------------------|

| 0.06 | 1.5 | 7.3/7.9 | 3.3/3.6 | 1.6/1.8 | 2.7/3.0 ||---------------------------------------------------------------------------|| 0.13 | 3.4 | 37.3/41.3 | 16.9/18.7 | 8.2/9.2 | 14.0/15.5 ||---------------------------------------------------------------------------|| 0.18 | 4.5 | 67.4/74.6 | 30.5/33.8 | 14.9/16.5 | 25.3/28.0 |-----------------------------------------------------------------------------

Table 201Standard Air Flow Rates

Subtask 71-00-00-820-057

B. Engine Air Flow Rates

(1) Testing parameters

(a) Air: clean and dry.

(b) Pressure: 19.8 psi (137 kPa).

(c) Temperature: 68 deg.F (20 deg.C)

(2) The air flow rates of each engine oil circuit is given in the table202 below, in these conditions:

(a) The test rig must be selected to the large size selector: 0.18

in. (4.6 mm) diameter, for the forward engine sump.(b) The test rig must be selected to the medium size selector: 0.13

in. (3.3 mm) diameter, for the rear engine sump and for theAGB/TGB.

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C F M 56 -----------------------------------------------------------------------------| ENGINE OIL CIRCUIT | AIR FLOW RATES || |------------------------------------------------------|| | PPH | KG/H | SCFM | M3/H ||---------------------------------------------------------------------------|| FORWARD SUMP | 59.1/67.9 | 26.82/30.78 | 12.9/14.8 | 21.9/25.1 ||---------------------------------------------------------------------------|

| REAR SUMP | 22.2/25.4 | 10.08/11.52 | 4.75/5.45 | 8.1/9.3 ||---------------------------------------------------------------------------|| AGB/TGB | 38.5/42.45 | 17.46/19.26 | 8.4/9.25 | 14.25/15.7 |-----------------------------------------------------------------------------

Table 202Engine Air Flow Rates

5. Close-up________

Subtask 71-00-00-869-214

A. Not Applicable.

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POWER PLANT - GENERAL - REMOVAL/INSTALLATION____________________________________________

TASK 71-00-00-000-040

Removal of the Power Plant

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS_______

ONLY WITH A GOOD SUPPLY OF AIR.OBEY THE MANUFACTURERS INSTRUCTIONS.PUT ON PROTECTIVE CLOTHING.DO NOT GET THEM IN YOUR MOUTH.DO NOT SMOKE.DO NOT BREATHE THE GAS.THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING_______GEAR.

WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU_______START A TASK ON OR NEAR:- THE FLIGHT CONTROLS- THE FLIGHT CONTROL SURFACES- THE LANDING GEAR AND THE RELATED DOORS- COMPONENTS THAT MOVE.

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE_______YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.


Self Explanatory

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No specific adhesive tapeNo specific circuit breaker(s) safety clip(s)No specific soft nose pliersNo specific warning noticeNo specific access platform 1 m (3 ft. 3 in.)No specific container 1 USgal (3.7854 l)No specific container (1 USgal) 4 l (1.0566 USgal)No specific Torque Wrench : range 36.00 to 220.00 lbf.in

(0.40 to 2.60 m.daN)No specific Torque Wrench : range 2.00 to 20.00 m.daN

(15.00 to 150.00 lbf.ft)RSE1224 2 SPLINT - ENGINE MOUNT AFTS487ETT2 1 ENGINE TROLLEYS587BH0 1 BRACE - HOLD OPEN COWLSS686CR56-5 1 ENGINE CRADLETMHBS10-10-00 1 BRACE - HOLD OPEN COWLSTMHEC28-00-00 1 ENGINE CRADLETMHET06-00-00 1 ENGINE TROLLEY98D27803500001 1 TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER98D71203500000 1 BOOTSTRAP SYSTEM98D71203501000 1 BOOTSTRAP SYSTEM

B. Consumable Materials


No specific TY WRAPMaterial No. CP8001 *

lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)R Material No. CP8006 *R safety cable 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)

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05-57-00-200-001 Aircraft Stability

29-14-00-614-001 Depressurization of the Hydraulic Reservoirs31-36-00-740-007 To make a Printout of the Engine hours and cycles.71-13-00-010-040 Opening of the Fan Cowl Doors78-30-00-481-041 Make the Thrust Reverser Unserviceable for

Maintenance78-36-00-010-040 Opening of the Thrust Reverser Doors71-00-00-991-900 Fig. 40171-00-00-991-901 Fig. 40271-00-00-991-930 Fig. 40371-00-00-991-903 Fig. 40471-00-00-991-904 Fig. 40571-00-00-991-905 Fig. 40671-00-00-991-906 Fig. 40771-00-00-991-908 Fig. 40871-00-00-991-907 Fig. 40971-00-00-991-909 Fig. 410

3. Job Set-up__________

Subtask 71-00-00-941-064

A. Safety Precautions

R (1) Make sure the aircraft is stable (Ref. TASK 05-57-00-200-001)

NOTE : If the aircraft is on jacks, make sure that it is leveled____ before you remove the engine.

(2) On the center pedestal, on the ENG panel 115VU:

(a) Put a warning notice to tell persons not to start the engine.

(3) Make sure that the engine 1(2) shutdown occurred not less than 5minutes before you do this procedure.

(4) On the overhead maintenance panel 50VU:

(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2)

pushbutton switch is off.

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(b) Put a warning notice to tell persons not to energize the FADEC1(2).

(5) Make sure that the slats are retracted and install TOOL-ZERO LOCKING,FLAP SLAT CTL LEVER (98D27803500001) on the flap and slat controllever.

(6) On the panel 30VU make sure that the APU BLEED pushbutton switch isreleased (ON legend off) and install a warning notice to tell thepersons not to use it.

(7) Put a warning notice on the HP ground connector to tell the personsnot to pressurize the pneumatic system.

Subtask 71-00-00-740-050

B. Do a print-out of the engine hours and cycles and keep the print with theengine for follow-up (Ref. TASK 31-36-00-740-007).

Subtask 71-00-00-865-075

C. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION-------------------------------------------------------------------------------49VU ENGINE/1 AND 2/IGN/SYS A 1JH A0349VU ANTI ICE/PROBES/AOA/1 4DA1 D0449VU ANTI ICE/PROBES/PHC/1 2DA1 D0349VU ANTI ICE/PROBES/PITOT/1 3DA1 D0249VU ANTI ICE/RAIN/RPLNT/CAPT 1DB1 D0149VU COM/CVR/SPLY 2RK E14

49VU COM/CVR/CTL 4RK E13121VU RCDR/DFDR 7TU K16121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B 2WE1 Q44121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 1WE1 Q43121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 2WE2 Q42121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A 1WE2 Q41122VU ANTI ICE/WINDOWS/R 4DG2 W14122VU ANTI ICE/F/O/RAIN/RPLNT 1DB2 W11122VU ANTI ICE/WINDOWS/L 4DG1 X14122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16

R 122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15R 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14

122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13

122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12R 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11

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-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION-------------------------------------------------------------------------------

R 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15

R 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14R 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

R 122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12

**ON A/C 001-099,

Post SB 30-1037 For A/C 001-099,

122VU ANTI ICE/RAIN/RPLNT/F/O 1DB2 W11

**ON A/C 001-099,

FOR 1000EM149VU ENGINE/1/FIRE DET/LOOP A 7WD1 A0649VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39121VU ENGINE/ENG1/FIRE DET/LOOP B 8WD1 Q38121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41122VU ELEC/GCU/1 2XU1 T26122VU ANTI ICE/ENG/1 1DN1 X10FOR 1000EM249VU ENGINE/2/FIRE DET/LOOP B 8WD2 A0749VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05121VU HYDRAULIC/HYD POWER/Y 3803GX N30121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42

121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40121VU ENGINE/ENG2/FADEC B 4KS2 Q40121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39122VU ELEC/GCU/2 2XU2 T27122VU ANTI ICE/ENG/2 1DN2 W10123VU Y HYD/ELEC/PUMP 3802GX AB06123VU Y HYD/ELEC PUMP/NORM 3801GX AB03

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Subtask 71-00-00-865-078

R D. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION-------------------------------------------------------------------------------

FOR 1000EM149VU ENGINE/1/HP FUEL SOV 1KC1 A01

FOR 1000EM249VU ENGINE/2/HP FUEL SOV 1KC2 A02

Subtask 71-00-00-941-065

R E. Put a warning notice on the circuit breaker 1KC1(2) to tell the personsnot to open it (them).

Subtask 71-00-00-864-050

R F. Depressurize the hydraulic reservoir (Ref. TASK 29-14-00-614-001):FOR 1000EM1- Depressurize the Green hydraulic reservoir.FOR 1000EM2

- Depressurize the Yellow hydraulic reservoir.

Subtask 71-00-00-010-084

R G. Open the fan cowl doors (Ref. TASK 71-13-00-010-040):FOR 1000EM1437AL, 438ARFOR 1000EM2447AL, 448AR

Subtask 71-00-00-040-066

R H. Make the thrust reverser unserviceable (Ref. TASK 78-30-00-481-041).

Subtask 71-00-00-010-087

R J. Get Access

CAUTION : BEFORE OPENING THE THRUST REVERSER DOORS TO THE 45 DEGREES_______POSITION MAKE SURE THAT THE SLATS ARE RETRACTED. IF NOT THESLATS CAN TOUCH THE INBOARD THRUST REVERSER DOOR.

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(1) Open the thrust reverser doors to the 45 degrees position (Ref. TASK78-36-00-010-040):FOR 1000EM1451AL, 452ARFOR 1000EM2461AL, 462AR

(2) Put the access platform in position at the engine level.

Subtask 71-00-00-941-062

K. At the half upper part of the fan frame seal off the fan duct panels withadhesive tape(Ref. Fig. 401/TASK 71-00-00-991-900)

Subtask 71-00-00-480-055

L. Install BRACE - HOLD OPEN COWLS (S587BH0) or BRACE - HOLD OPEN COWLS(TMHBS10-10-00) to support the fan and thrust reverser cowl doors.(Ref. Fig. 402/TASK 71-00-00-991-901)

Subtask 71-00-00-680-050

M. Drain the remaining fuel from the engine and the pylon fuel hose at thefuel filter as follows :

(1) Put a container (1 USgal) under the fuel filter.

R (2) Cut and remove the lockwire or safety cable and remove the drain plugR from the filter bowl. Drain the fuel into the container.

R (3) Install the drain plug and TORQUE to between 45 and 55 lbf.in (0.50

R and 0.62 m.daN). Safety with lockwire 0.032 in. (0.8 mm) dia.R (Material No. CP8001) or safety cable 0.032 in. (0.8 mm) dia.R (Material No. CP8006).

Subtask 71-00-00-010-085

N. Remove the components.(Ref. Fig. 403/TASK 71-00-00-991-930)

(1) At the rear of the drain mast, remove the fuel averboard drain tube.

(a) Put container (1l) below the overboard drain tube to catch anyfluid remaining in the tube.

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Fan Duct Panels and Sealing Fitting AssyFigure 401/TASK 71-00-00-991-900

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Hold Open Cowl Braces - InstallationFigure 402/TASK 71-00-00-991-901

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R Fuel Overboard Drain TubeR Figure 403/TASK 71-00-00-991-930

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R (b) Disconnect the overboard drain tube (205) from the engine tubeR and allow the fluid to drainRR PRE SB RA32071-13R

R (c) Remove the clamp (210), the screw (215), the washer (220), the

R spacer (225), and the nut (230) that attach the tube (205) to theR tube (235).RR POST SB RA32071-13R

R (d) Remove the clamp (210), the screw (215), the washer (220), theR spacer (225) and the nut (230) that attach the tube (205) to theR tube (235).

R (e) Remove the bolt (240), the washer (220), and the nut (230) thatR attach the tube (205) to the transfer gearbox bracket.RR END OF SB RA32071-13R

R (f) Remove the fuel overboard drain tube (205) from the engine.

R (g) Put protective covers on the engine tube and the overboard drainR tube (205).

R (h) Remove the container from below the drain mast.

R (2) Remove the access panels :FOR 1000EM1

473AL, 473ARFOR 1000EM2483AL, 483AR

R (3) Remove these components from the right side of the engine :

(a) Disconnect the electrical connectors 450VCA, 452VCA, 454VCA, and457VCA from the aft pylon junction box.

R (Ref. Fig. 404/TASK 71-00-00-991-903)

NOTE : If nececessary, use the soft nose pliers to loosen the____electrical connectors.

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R Thrust Reverser Electrical ConnectorsR Figure 404/TASK 71-00-00-991-903

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R (b) Open the two flip-lock clamps that attach the core wire harnessR to the pylon and remove the harness from the clamps.R

(c) Disconnect the generator harness connector 400VCA from theforward pylon junction box.

R (Ref. Fig. 405/TASK 71-00-00-991-904)

(d) Disconnect the thrust reverser harness connectors 4101KSB,4101KSA and 4102KSA from the thrust reverser hydraulic controlunit.

R (Ref. Fig. 405/TASK 71-00-00-991-904)

(e) Disconnect the electrical connectors 401VCA, 402VCA, 403VCA,404VCA, 405VCA, 406VCA, 407VCA, 408VCA, 409VCA, 447VCA, and448VCA from the forward pylon junction box.

R (Ref. Fig. 405/TASK 71-00-00-991-904)

(f) Remove the coupling (5) and disconnect the upper starter ductfrom the pylon duct.

R (Ref. Fig. 405/TASK 71-00-00-991-904)

R (4) Remove these components from the left side of engine:

(a) Disconnect the thrust reverser harness connector 4100KSA from thethrust reverser electrical jonction box.

(b) Disconnect the suction hose from the coupling half. Disconnectthe pressure hose, and the upper case drain hose from the fluiddisconnect panel.

R (Ref. Fig. 406/TASK 71-00-00-991-905)

(c) Remove the bolts (80), the washers (85), that attach thefuel/return by-pass hose, from the fluid disconnect panel. Removeand discard the gasket (90).

R (Ref. Fig. 406/TASK 71-00-00-991-905)

(d) Remove the bolts (10), the washers (15), that attach the mainfuel supply hose from the fluid disconnect panel. Remove anddiscard the gasket (20).

R (Ref. Fig. 406/TASK 71-00-00-991-905)

(e) Install the protective covers on the disconnected hoses andtubes.

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Power Plant - Right SideR Figure 405/TASK 71-00-00-991-904

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Power Plant - Left sideR Figure 406/TASK 71-00-00-991-905

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(f) Disconnection of the tubes:

CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING_______NUTS.ONE WRENCH TO HOLD THE UNION AND ONE TO LOOSEN ORTIGHTEN THE COUPLING NUT. THIS WILL PREVENT DAMAGE TOTHE HARDWARE.

1 Disconnect the sense tubes from the pylon interface tubes._(Ref. Fig. 407/TASK 71-00-00-991-906)

2 Disconnect the pressure tube from the union installed in the_upper high-pressure manifold duct (engine 1 only).(Ref. Fig. 407/TASK 71-00-00-991-906)

3 Remove the coupling (25) and disconnect the joint duct from_the interface duct.(Ref. Fig. 407/TASK 71-00-00-991-906)

4 Disconnect the fan lower zone extinguishing line forward of_the hydraulic junction box.

Subtask 71-00-00-020-058

P. Remove the bolts (180), the washers (185) and (195), the retainers (190),and the nuts (200) from the engine mount (150).(Ref. Fig. 408/TASK 71-00-00-991-908)

R (1) Cut and remove the lockwire or safety cable and loosen the boltsR (135) as follows :

(a) Loosen one bolt. TORQUE again the bolt to between 12 and 18 m.daN

(88.49 and 132.74 lbf.ft) or the maximum load that a mechanic canapply with a standard wrench.

(b) Apply this procedure on the three remaining bolts one by one.

Subtask 71-00-00-480-056

Q. Installation of the bootstrap system

(1) Install BOOTSTRAP SYSTEM (98D71203500000) or BOOTSTRAP SYSTEM(98D71203501000)(Ref. Fig. 409/TASK 71-00-00-991-907)

(a) Install the rear beam (9) on the lower part of the pylon andattach with the ball pins (8).

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R Pneumatic SystemR Figure 407/TASK 71-00-00-991-906

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Forward Engine MountR Figure 408/TASK 71-00-00-991-908

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INTENTIONALLY BLANK

R Page 419 71-00-00

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Bootstrap InstallationR Figure 409/TASK 71-00-00-991-907- 12 (SHEET 1)

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Bootstrap InstallationR Figure 409/TASK 71-00-00-991-907- 22 (SHEET 2)

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(b) Install the spacer and the center hinge clamp (6) on the pyramid.Attach the spacer to the pyramid with the right and left clamps(7).

(c) Install the forward hinge arms (4) and (5) with the ball pins(3).

(d) Install the link (2) at the upper part of the hinge arms (4) and(5) with the ball pins (1).

(e) Install the dynamometers and the chain pulley blocks.

(2) Install the engine cradle

CAUTION : BE CAREFUL WHEN YOU INSTALL THE CRADLE ON, OR REMOVE IT_______FROM, THE ENGINE. IF NOT, YOU CAN CAUSE DAMAGE TO THEVIBRATION SENSOR CONNECTOR. THE VIBRATION SENSOR CONNECTORIS IN FRONT OF THE FORWARD HANDLING POINT ON THE RIGHTSIDE.

(a) Put the ENGINE TROLLEY (S487ETT2) or ENGINE TROLLEY (TMHET06-00-00) , together with the ENGINE CRADLE (S686CR56-5) or ENGINECRADLE (TMHEC28-00-00) in position below the engine.

(3) Attach the chain hooks to the engine cradle.

(4) Release the pins that attach the engine cradle to the trailer andlift the engine cradle to the engine.

NOTE : Make the engine cradle level. To do this chain pulleys.____

(5) Put the pins of the front fixtures into the engine handling points

and then install the rear support on the left side. Attach to theengine with a ball pin.

(6) Put the pins in to each fixture. Then at the same time, adjust thetension of the handling hoists so that you can read these values onthe dynamometers : 1975 daN (4440 lbf) (2015 kg) for the forwarddynamometers and 400 daN (899.2 lbf) (408 kg) for the aftdynamometers.

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Subtask 71-00-00-020-057

A. Remove the bolts of the engine mounts

(1) Remove the bolts (135), the nuts (140), the washers (145), which

attach the forward engine mount (150) to the pylon.R (Ref. Fig. 408/TASK 71-00-00-991-908)

(2) Remove the bolts (155), the washers (160), which attach the aftengine mount (165) to the pylon.

R (Ref. Fig. 410/TASK 71-00-00-991-909)

Subtask 71-00-00-869-169

B. Make sure that no lines or unions stay connected to the pylon.

Subtask 71-00-00-480-057

C. Installation of the support equipment

CAUTION : MAKE SURE THAT THE PYLON FORWARD MOUNT DOES NOT TOUCH THE UPPER_______STRUT OR THE UPPER SEAL ASSY WHEN YOU LOWER THE ENGINE ORDAMAGE CAN OCCUR.

(Ref. Fig. 401/TASK 71-00-00-991-900)

(1) Put the pulley locking levers in down position then lower the enginewith the four chain pulley blocks.

NOTE : During the lowering procedure make sure that:____

- the difference of load between front cables is less than 600daN (1348.9 lbf) (612 kg).- the difference of load between rear cables is less than 200

daN (449.6 lbf) (204 kg).

NOTE : Use the level indicators on the forward hinge arms of the____bootstrap to keep this hinge arms as near as possible to thehorizontal position.

NOTE : Be careful not to cause dynamic effects while you lower the____engine.

(2) Put first the aft section of the engine cradle in position on the

trailer then the forward section.

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Aft Engine MountR Figure 410/TASK 71-00-00-991-909

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(3) Lock the engine cradle to the trailer with ball pins

(4) Remove the four chain hooks from the engine cradle stirrups andremove the four chain pulley blocks from the bootstrap system.

Subtask 71-00-00-020-056

D. Remove the engine

WARNING : DEATH OR SERIOUS INJURY MAY RESULT IF THE POWER PLANT FALLS ON_______THE PERSONNEL. THE POWER PLANT WEIGHS APPROXIMATELY 6280 POUNDS(2850KG). MAKE SURE THAT ALL PERSONNEL IS AWAY FROM THEAIRCRAFT WHEN THE POWER PLANT IS REMOVED.

Subtask 71-00-00-420-073

E. Installation of the AFT ENGINE MOUNT ANTI GOUGE SPLINTS.

(1) Put the top slint assemblies (larger) on the outside of the aftengine mount links.

NOTE : The end of the splint assembly marked TOP must touch the beam____assembly. The other end marked BOTTOM must touch the links.

(2) Put the bottom splint (smaller) on the inside of the aft engine mountlinks.

(3) Attach the SPLINT - ENGINE MOUNT AFT (RSE1224) to the engine mounttwo places with TY WRAP.

(a) Wind the TY WRAP around the splints and the aft mount where thesplint touches the beam assembly.

(b) Wind the TY WRAP around the splints and the aft mount where thesplint touches the link.

(c) Make sure that the TY WRAP is wound very tight and that thesplints can not move.

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TASK 71-00-00-400-040

Installation of the Power Plant

WARNING : MAKE SURE THAT YOU HAVE THE CORRECT FIRE FIGHTING EQUIPMENT_______AVAILABLE.

WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING_______GEAR.

WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU_______START A TASK ON OR NEAR:- THE FLIGHT CONTROLS- THE FLIGHT CONTROL SURFACES- THE LANDING GEAR AND THE RELATED DOORS- COMPONENTS THAT MOVE.

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE_______YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

CAUTION : DO A CHECK OF THE ENGINE DATA PLATE TO MAKE SURE THAT THE ENGINE IS_______CORRECT FOR THE AIRCARFT.IF YOU INSTALL AN ENGINE THAT DOES NOT HAVE THE CORRECT CONFIGURATIONFOR THE AIRCRAFT.- DAMAGE TO EQUIPMENT CAN OCCUR IF YOU OPERATE THE ENGINE. - THE TESTAFTER THE INSTALLATION WILL TELL YOU THE ENGINE CONFIGURATION IS NOTCORRECT AND MORE WORK WILL BE NECESSARY.


Self Explanatory

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No specific dynamometerNo specific foam rubber protective padsNo specific soft nose pliersNo specific warning noticeNo specific contener 0.25 USgal (0.9463 l)No specific access platform 1 m (3 ft. 3 in.)No specific Torque Wrench : range 120.00 to 600.00 lbf.ft

(15.00 to 82.00 m.daN)No specific Torque Wrench : range 20 to 25 lbf.in

(0.22 to 0.28 m.daN)No specific Torque Wrench : range 24 to 36 lbf.in

(0.27 to 0.40 m.daN)No specific Torque Wrench : range 36.00 to 220.00 lbf.in



(2.00 to 20.00 m.daN)No specific Torque Wrench : range 2.00 to 20.00 m.daN

(15.00 to 150.00 lbf.ft)RSE1224 2 SPLINT - ENGINE MOUNT AFT98D27803500001 1 TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER

B. Consumable Materials


R No specific corrosion resistant steel lockwire 0.047 in. (1.2R mm) dia.

Material No. CP1008 *trichloroethylene (1,1,1) (Ref. 70-30-00)

Material No. CP5063 *silicone lubricant (Ref. 70-30-00)

R Material No. CP8001 *R lockwire 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)

R Material No. CP8006 *R safety cable 0.032 in. (0.8 mm) dia. (Ref. 70-30-00)

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-------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN-------------------------------------------------------------------------------

R 20 gasket 73-11-11 01 -100

90 gasket 73-11-48 01 -030

D. Referenced Information


12-13-79-610-001 Check of the Oil Level and Gravity Filling20-28-00-869-002 Table of the Maximum Permitted Resistance Values22-97-00-710-001 Operational Test of the LAND CAT III Capability24-21-00-210-046 Check of the Oil Level and Filter Differential

Pressure Indicator (DPI)24-21-00-720-041 Functional Test of the IDG Disconnect System - Engine

in Operation24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power30-21-00-710-002 Operational Test of the Engine Air Intake Ice

Protection (with the Engines in operation)31-32-00-860-012 Procedure to Get Access to the SYSTEM REPORT/TEST/ENG

Page31-36-00-740-005 To update the Engine hours and cycles into the DMU

after Engine or DMU replacment.31-60-00-860-001 EIS Start Procedure34-10-00-860-004 IR Alignment Procedure

71-00-00-710-003 Engine Automatic Start71-00-00-710-006 Minimum Idle Check71-00-00-710-008 Power Assurance Check71-00-00-710-009 Vibration Check71-00-00-710-010 Accel Check71-00-00-710-028 Engine Shutdown71-13-00-010-040 Opening of the Fan Cowl Doors71-13-00-410-040 Closing of the Fan Cowl Doors71-13-00-800-040 Adjustment of the Fan Cowl Doors71-21-11-210-040 Detailed Visual Inspection of the Forward Engine

Mount with the Engine Installed71-22-11-210-040 Detailed Visual Inspection of the Aft Engine Mount

with the Engine Removed

73-11-50-360-001 Leak Check of the Fuel Return Valve (Method 1).73-21-60-720-040 Functional Test of the Electronic Control Unit (ECU)73-21-60-740-009 Entry of the Engine Serial Number through the MCDU

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73-21-60-740-025 Entry of the Thrust Reverser Hydraulic IsolationValve Status through the MCDU

73-29-00-710-040 Operational Test of the FADEC on the ground (with

Engine Motoring)78-30-00-081-041 Make the Thrust Reverser Serviceable after

Maintenance78-30-00-481-041 Make the Thrust Reverser Unserviceable for

Maintenance78-31-00-710-040 Operational Test of the Thrust Reverser System78-31-00-710-040 Operational Test of the Thrust Reverser without CFDS

- Engine not Running78-31-00-710-040 Operational Test of the Thrust Reverser without CFDS

- Engine Running78-36-00-010-040 Opening of the Thrust Reverser Doors78-36-00-410-040 Closing of the Thrust Reverser DoorsCMM 712106CMM 71220771-00-00-991-900 Fig. 40171-00-00-991-901 Fig. 40271-00-00-991-930 Fig. 40371-00-00-991-903 Fig. 40471-00-00-991-904 Fig. 40571-00-00-991-905 Fig. 40671-00-00-991-906 Fig. 40771-00-00-991-908 Fig. 40871-00-00-991-907 Fig. 40971-00-00-991-909 Fig. 41071-00-00-991-920 Fig. 411

**ON A/C 001-099,

Post SB 73-1050 For A/C 001-099,R Post SB 73-1054 For A/C 001-099,

71-00-00-991-920-A Fig. 411AFOR FIN 1000EM129-11-00-710-001 Operational Test of the Green Hydraulic System29-14-00-614-002 Pressurization of the Hydraulic Reservoirs through

the Ground ConnectorFOR FIN 1000EM229-13-00-710-002 Operational Test of the Yellow Hydraulic System

29-14-00-614-002 Pressurization of the Hydraulic Reservoirs throughthe Ground Connector

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**ON A/C 001-099,

3. Job Set-up__________

Subtask 71-00-00-865-076

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied andtagged

-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION-------------------------------------------------------------------------------49VU ENGINE/1 AND 2/IGN/SYS A 1JH A0349VU ANTI ICE/PROBES/AOA/1 4DA1 D0449VU ANTI ICE/PROBES/PHC/1 2DA1 D0349VU ANTI ICE/PROBES/PITOT/1 3DA1 D0249VU ANTI ICE/RAIN/RPLNT/CAPT 1DB1 D0149VU COM/CVR/SPLY 2RK E1449VU COM/CVR/CTL 4RK E13121VU RCDR/DFDR 7TU K16121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B 2WE1 Q44121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A 1WE1 Q43121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B 2WE2 Q42121VU ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A 1WE2 Q41122VU ANTI ICE/WINDOWS/R 4DG2 W14122VU ANTI ICE/F/O/RAIN/RPLNT 1DB2 W11122VU ANTI ICE/WINDOWS/L 4DG1 X14122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16

R 122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15R 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14

122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13

122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12R 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11R 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16

122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15R 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14R 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13R 122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12

**ON A/C 001-099,

Post SB 30-1037 For A/C 001-099,

122VU ANTI ICE/RAIN/RPLNT/F/O 1DB2 W11

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-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION-------------------------------------------------------------------------------**ON A/C 001-099,

FOR 1000EM1

49VU ENGINE/1/FIRE DET/LOOP A 7WD1 A0649VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39121VU ENGINE/ENG1/FIRE DET/LOOP B 8WD1 Q38121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41122VU ELEC/GCU/1 2XU1 T26122VU ANTI ICE/ENG/1 1DN1 X10FOR 1000EM249VU ENGINE/2/FIRE DET/LOOP B 8WD2 A0749VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05121VU HYDRAULIC/HYD POWER/Y 3803GX N30121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40121VU ENGINE/ENG2/FADEC B 4KS2 Q40121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39122VU ELEC/GCU/2 2XU2 T27122VU ANTI ICE/ENG/2 1DN2 W10123VU Y HYD/ELEC/PUMP 3802GX AB06123VU Y HYD/ELEC PUMP/NORM 3801GX AB03

Subtask 71-00-00-860-059

B. Aircraft Maintenance Configuration

(1) On the center pedestal, on the ENG panel 115VU, make sure that awarning notice is in position to tell persons not to start theengine.

(2) On the overhead maintenance panel 50VU, make sure that the ON legendof the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make surethat a warning notice is in position to tell persons not to energizethe FADEC 1(2).

(3) Make sure that the access platform is in position.

(4) Make sure that the slats are retracted and install TOOL-ZERO LOCKING,FLAP SLAT CTL LEVER (98D27803500001) on the flap and slat control

lever.

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(5) Make sure there is a warning notice on the HP ground connector totell persons not to pressurize the pneumatic system.

Subtask 71-00-00-010-088

C. Get Access

(1) Make sure that the fan cowl doors are open (Ref. TASK 71-13-00-010-040):FOR 1000EM1437AL, 438ARFOR 1000EM2447AL, 448AR

(2) Make sure that the thrust reverser doors are open (Ref. TASK 78-36-00-010-040):FOR 1000EM1451AL, 452ARFOR 1000EM2461AL, 462AR

Subtask 71-00-00-040-065

D. Make sure that the thrust reverser is unserviceable (Ref. TASK 78-30-00-481-041).

Subtask 71-00-00-020-063

E. Remove the SPLINT - ENGINE MOUNT AFT (RSE1224) from the aft engine mount.

Subtask 71-00-00-210-056

F. Check before installationCAUTION : DO A DETAILED VISUAL INSPECTION OF THE FORWARD AND AFT ENGINE_______

MOUNTS AND ALL PARTS THAT ATTACH THE MOUNTS. THE PARTS MUST BEIN GOOD CONDITION. IF THE PARTS ARE NOT IN GOOD CONDITION THEMOUNT COULD FAIL.

(1) Do a detailed visual inspection of the forward and aft engine mount(Ref. TASK 71-21-11-210-040) and (Ref. TASK 71-22-11-210-040).

(2) Do a detailed visual inspection of the forward central part (thesnout) of the forward engine mount (Ref. TASK 71-21-11-210-040).

(3) Do a check of the cowling for correct condition.

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(4) Do a check of the electrical connectors of the aft and forwardjunction boxes for correct condition.

(5) Do a check of the visible part of the pylon for correct condition.

Subtask 71-00-00-110-051

G. Clean bolts (135) and (155), nuts (140) and (170) with trichloroethylene(1,1,1) (Material No. CP1008).

Subtask 71-00-00-210-057

H. Make sure that there are no traces of important seizure or wear.

Subtask 71-00-00-230-050

J. Do a dye penetrant inspection of the mount bolts. No cracks arepermitted.

NOTE : Make sure the forward and aft engine mount bolts (135) and (155)____have been previously inspected per (Ref. CMM 712106) and (Ref. CMM712207) (FPI inspection level 4).

Subtask 71-00-00-110-050

K. Clean carefully the mating faces, the shear or locating pin holes and thefastener holes.

Subtask 71-00-00-869-171

L. Some the equipment are not installed on the new engine, remove them fromthe removed engine. Then install them on the new engine.

Subtask 71-00-00-941-063

M. Put foam rubber protective pads between:- the aft mount and the engine,- forward mount and engine- and at the upper part of the fan case so that the parts cannot hitduring hoisting operations.

(1) At the half upper part of the fan frame, seal the fan duct panelswith adhesive tape.

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Subtask 71-00-00-010-086

R N. Installed, remove the fuel overboard drain tube:R (Ref. Fig. 403/TASK 71-00-00-991-930)

R (1) If installed remove the fuel overboard drain tube at the rear of theR drain must.

R (a) Put contener (1l) below the overboard drain tube to catch anyR fluid remaining in thetube.

R (b) Disconnect the overboard drain tube (205) from the engine tubeR and allow the fluid to drain.RR PRE SB RA32071-13R

R (c) Remove the clamp (210), the screw (215), the washer (220), theR spacer (225) and the nut (230) that attach the tube (205) to theR tube (235).RR POST SB RA32071-13R

R (d) Remove the clamp (210), the screw (215), the washer (220), theR spacer (225) the nut (230) that attach the tube (205) to the tubeR (235).

R (e) Remove the bolt (240), the washer (220), and the nut (230) thatR attach the tube (205) to the transfer gearbox bracket.RR END OF SB RA32071-13

RR (f) Remove the fuel overboard drain tube (205) from the engine.

R (g) Put protective covers on the engine tube and the overboard drainR tube (205).

R (h) Remove the container from below the drain mast.

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Subtask 71-00-00-480-058

A. Installation of the booststrap:

(1) Install the engine trolley complete with the engine cradle and the

replacement engine under the pylon.

(2) Install chain pulley blocks on the bootstrap system.

(3) Attach the chain hooks to the engine cradle.

(4) Free the pins attaching the engine cradle to the trolley.

(5) Place the locking levers of the handling hoist in up position.

(6) Raise the engine cradle to disengage it from the trolley.

CAUTION : MAKE SURE THAT THE PYLON FORWARD MOUNT DOES NOT TOUCH THE_______UPPER STRUT OR THE UPPER SEAL ASSY WHEN YOU RAISE THEENGINE OR DAMAGE CAN OCCUR.

(Ref. Fig. 401/TASK 71-00-00-991-900)

(a) Slightly raise the forward section of the engine cradle then theaft section.

NOTE : During hoisting procedure make sure that:____- the difference of load between front cables is less than

600 daN (1348.9 lbf) (612 kg)- the difference of load between rear cables is less than

200 daN (449.6 lbf) (204 kg).NOTE : Use the level indicators on the forward hinge arms of the____

bootstrap to keep this hinge arms as near as possible tothe horizontal position.

(7) When the distance between the engine mounts and the pylon mounts isapproximately 10 mm (0.4 in.) slowly raise the engine.

CAUTION : DO NOT INSTALL THE LOCATING PINS OF ONE MOUNT BEFORE THE_______OTHER OR DAMAGE TO MOUNTS AND PYLON COULD RESULT.

(a) Install front and rear locating pins.

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(8) Raise the engine cradle gradually until a mating load is indicated onthe dynamometers. Do not apply more than 200 daN (449.6 lbf) (204 kg)for each cable.

Subtask 71-00-00-640-050

R B. Apply silicone lubricant (Material No. CP5063) to the bolt (135) and

(155) threads, the washers (145) and (160), the nuts (140) and (170) andthe pin holes.

Subtask 71-00-00-869-170

C. Do a test of the self-locking feature of the nuts used on the forward andaft engine mounts.

(1) forward engine mount nuts.

(a) Put the washers (145) under the head of the bolts (135).

(b) Install the bolts (135) thru holes in the pylon and the forwardmount.

(c) Install the nuts (140) on the bolts (135).

(d) Tighten the nuts by hand until they are hard to turn.

NOTE : Make sure that the nuts are correctly threaded on the____bolts.

(e) Use a torque wrench to tighten the nuts (140) until at least twofull threads show beyond the nut.

(f) Measure the torque required to tighten the bolt (135). Theminimum torque should not be less than 70 lbf.in (0.79 m.daN).The maximum torque should not be more than 600 lbf.in (6.78m.daN).

(g) If the bolt (135) torque is less than 70 lbf.in (0.79 m.daN),replace the nut (140) and do again steps (a) thru (f).

(h) If the bolt (135) torque is more than 600 lbf.in (6.78 m.daN),remove the bolt and nut and look for damaged threads. If thethreads are damaged, replace the bolt and nut and do again steps(a) thru (g).

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(2) Aft engine mount nuts.

(a) Put the bolts (155) in the barrel nuts (170).

(b) Tighten the bolts by hand until they are hard to turn.

NOTE : Make sure that the nuts are correctly threaded on the____

bolts.

(c) Use a torque wrench to tighten the bolts (155) until at least twofull threads show beyond the nut.

(d) Measure the torque required to tighten the bolts (155). Theminimum torque should not be less than 90 lbf.in (1.01 m.daN).The maximum torque should not be more than 800 lbf.in (9.04m.daN).

(e) If the bolt (155) torque is less than 90 lbf.in (1.01 m.daN),replace the barrel nut (170) and do again steps (a) thru (d).

(f) If the bolt torque is more than 800 lbf.in (9.04 m.daN), removethe bolt and nut and look for damaged threads. If the threads aredamaged, replace the bolt and nut and do again steps (a) thru(d).

Subtask 71-00-00-420-062

D. Installation of the engine mounts:

CAUTION : INSTALL THE BARREL NUT WITH THE ROUNDED SIDE UP. IF NOT, DAMAGE_______TO THE NUT CAN OCCUR.

CAUTION : INCORRECT INSTALLATION OF THE WASHER CAN DAMAGE THE BOLT HEAD._______ THE INNER DIAMETER OF THE WASHER HAS A CHAMFER ON ONE SIDEONLY. YOU MUST PUT THE CHAMFER AGAINST THE BOLT HEAD SO THAT ITAGREES WITH THE BOLT HEAD RADIUS.

(1) Install the nuts (170) on the aft engine mount holes, the bolts (155)and the washers (160).(Ref. Fig. 410/TASK 71-00-00-991-909)

R (2) TORQUE the aft mount bolts (155) to between 480 and 580 lbf.ft (65.07R and 78.63 m.daN) and safety with corrosion resistant steel lockwireR 0.047 in. (1.2 mm) dia., lockwire 0.032 in. (0.8 mm) dia. (MaterialR No. CP8001), or safety cable 0.032 in. (0.8 mm) dia. (Material No.

R CP8006).

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R NOTE : You can use lockwire or safety cable ranging from 0.032 in.____R (0.8 mm) dia. to 0.047 in. (1.2 mm) dia. to safety the boltsR (155).

R

NOTE : After you tighten the engine mount bolts to the final torque,____

make sure that the surfaces between the pylon and the aftengine mount are in contact.

(3) At the forward mount:

(a) Install the four bolts (135), the four washers (145) and the fournuts (140) at the forward mount.(Ref. Fig. 408/TASK 71-00-00-991-908)

NOTE : You must install a washer (145) under each bolt (135).____

(b) Turn the nuts (140) until they lightly touch the lower face ofthe forward mount surface. Put the retainers (190) on the nuts(140) and set the retainers in the correct assembled position.Remove the retainers from this position and hold the nuts (140)with a wrench. While you hold the nut stable with the wrench,TORQUE the bolts (135) to between 12 and 18 m.daN (88.49 and132.74 lbf.ft) or to the maximum load that a mechanic can applywith a standard wrench.

NOTE : This is not the final torque of the forward engine mount____bolts (135).

Subtask 71-00-00-080-053

E. Remove the removal/installation equipment of the engineCAUTION : BE CAREFUL WHEN YOU INSTALL THE CRADLE ON, OR REMOVE IT FROM,_______

THE ENGINE. IF NOT, YOU CAN CAUSE DAMAGE TO THE VIBRATIONSENSOR CONNECTOR. THE VIBRATION SENSOR CONNECTOR IS IN FRONT OFTHE FORWARD HANDLING POINT ON THE RIGHT SIDE.

(1) Put the pulley locking levers in down position and slightly releasethe tension on the pulleys.

(2) Disconnect the engine cradle from the engine.

(3) Lower the engine cradle. Make sure that the engine cradle does not

hit the engine.

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(4) When the engine cradle is on the trolley, lock the rollers to thetrolley chassis.

(5) Remove the bootstrap assembly as follows :(Ref. Fig. 409/TASK 71-00-00-991-907)

(a) Remove the chain pulley blocks and the dynamometers from the rear

beam (9) and the forward hinge arms (4) and (5).

(b) Remove the two ball pins (8) then remove the rear beam (9) fromthe pylon.

(c) Remove the ball pins (1) then remove the link (2).

(d) Remove the ball pins (3) and remove the forward hinge arms (4)and (5).

(e) Release the left and right clamps (7) and remove the spacer andthe center hinge clamp (6) from the pyramid.

(6) Remove the hold open cowl braces:(Ref. Fig. 402/TASK 71-00-00-991-901)

(a) Install the fan cowl and thrust reverser cowl hold open rods.

(b) Remove the hold open cowl braces.

Subtask 71-00-00-420-061

F. TORQUE the forward mount bolts:

(1) TORQUE the forward mount bolts (135) to between 320 and 350 lbf.ft

R (43.38 and 47.45 m.daN): this is applicable if the nuts (140) doesR not turn. Safety with corrosion resistant steel lockwire 0.047 in.R (1.2 mm) dia., lockwire 0.032 in. (0.8 mm) dia. (Material No.R CP8001), or safety cable 0.032 in. (0.8 mm) dia. (Material No.R CP8006).

R NOTE : You can use lockwire or safety cable ranging from 0.032 in.____R (0.8 mm) dia. to 0.047 in. (1.2 mm) dia. to safety the boltsR (135).

NOTE : After you tighten the engine mount bolts to the final torque,____make sure that the surfaces between the pylon and the forwardengine mount are in contact.

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(2) Install the bolts (180), the washers (185), the retainers (190), thewashers (195) and nuts (200) to engine mount (150).

(3) TORQUE the bolts (180) to between 24 and 36 lbf.in (0.27 and 0.40m.daN)

5. Close-up________

Subtask 71-00-00-942-053

A. Remove the foam rubber protective pads from the upper part of the fancase and from the engine mounts.

Subtask 71-00-00-410-086

B. Install these components:

CAUTION : USE 2 WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS._______ONE WRENCH TO HOLD THE UNION AND ONE TO LOOSEN OR TIGHTEN THECOUPLING NUT. THIS WILL PREVENT DAMAGE TO THE HARDWARE.

(1) Install these components on the left side of the engine :

(a) Connect the fan lower zone extinguishing line forward of thehydraulic junction box. TORQUE union to between 800 and 900lbf.in (9.04 and 10.17 m.daN) .

(b) Connect the joint duct to the interface duct with the coupling(25).(Ref. Fig. 407/TASK 71-00-00-991-906)

(c) TORQUE the coupling as follows:

1 TORQUE the coupling to between 115 and 125 lbf.in (1.29 and_1.41 m.daN).

2 Lightly hit the coupling perimeter in different places with a_fiber hammer.

3 TORQUE the coupling again to the specified value._

4 Lightly hit the coupling perimeter again._

5 TORQUE the coupling again to the specified value._

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71.power plant

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