W DOC AIRBUS | AMM A320F

Installation of the Power Plant [IAE]

TASK 71-00-20-400-040-A
Installation of the Power Plant

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.
WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING: MAKE SURE THAT THE LANDING GEAR GROUND SAFETIES AND THE WHEEL CHOCKS ARE IN POSITION. MOVEMENT OF THE AIRCRAFT CAN BE DANGEROUS.
WARNING: MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.
CAUTION: DO A CHECK OF THE ENGINE DATA PLATE TO MAKE SURE THAT THE ENGINE IS CORRECT FOR THE AIRCRAFT. IF YOU INSTALL AN ENGINE THAT DOES NOT HAVE THE CORRECT CONFIGURATION FOR THE AIRCRAFT:
  • DAMAGE TO EQUIPMENT CAN OCCUR IF YOU OPERATE THE ENGINE.
  • THE TEST AFTER THE INSTALLATION WILL TELL YOU THAT THE ENGINE CONFIGURATION IS NOT CORRECT AND MORE WORK WILL BE NECESSARY.
CAUTION: MAKE SURE THAT THE EEC STANDARDS INSTALLED ARE CORRECT. SOME EEC STANDARDS CANNOT BE INTERMIXED ON A SAME AIRCRAFT.
CAUTION: MAKE SURE THAT THE TWO ENGINES INSTALLED ON THE AIRCRAFT HAVE THE SAME GROUND IDLE CAPABILITY (REDUCED GROUND IDLE OR NON-REDUCED GROUND IDLE). TWO ENGINES WITH DIFFERENT GROUND IDLE CAPABILITIES CAN CAUSE THRUST DISSYMMETRY AND THUS DAMAGE TO THE AIRCRAFT.
ZONE: 210
ZONE: 400
FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL
1. Reason for the Job
Self explanatory
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
ACCESS PLATFORM 1M(3 FT)
No specific
1
DRILL - NO 21 (DIA 0.159 IN - 4.039 MM)
No specific
1
DYNAMOMETER 15 DAN (33 LBF) - PULL
No specific
1
MAGNIFYING GLASS POWER 10X
No specific
1
MALLET - PLASTIC
No specific
AR
PENCIL
No specific
AR
PLATE - STEEL, 500X500X3 MM (19.68X19.68X0.12 IN)
No specific
AR
WARNING NOTICE(S)
No specific
1
WRENCH - STRAP
No specific
Torque wrench: range to between 132.74 and 88.49 lbf.ft (18.00 and 12.00 m.daN ) T
No specific
Torque wrench: range to between 8 and 6 lbf.in (0.09 and 0.07 m.daN ) T
No specific
Torque wrench: range to between 36 and 24 lbf.in (0.41 and 0.27 m.daN ) T
No specific
Torque wrench: range to between 40 and 35 lbf.in (0.45 and 0.40 m.daN ) T
No specific
Torque wrench: range to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T
No specific
Torque wrench: range to between 110 and 90 lbf.in (1.24 and 1.02 m.daN ) T
No specific
Torque wrench: range to between 245 and 215 lbf.in (2.77 and 2.43 m.daN ) T
No specific
Torque wrench: range to between 0.42 and 0.38 m.daN (37.17 and 33.63 lbf.in ) T
No specific
Torque wrench: range to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in ) T
No specific
Torque wrench: range to between 0.96 and 0.85 m.daN (84.96 and 75.22 lbf.in ) T
No specific
Torque wrench: range to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft ) T
No specific
Torque wrench: range to between 2.3 and 2.0 m.daN (16.96 and 14.75 lbf.ft ) T
No specific
Torque wrench: range to between 10.7 and 9.7 m.daN (78.91 and 71.53 lbf.ft ) T
No specific
Torque wrench: range to between 47.45 and 43.39 m.daN (349.93 and 319.99 lbf.ft ) T
No specific
Torque wrench: range to between 70.5 and 65 m.daN (519.91 and 479.35 lbf.ft ) T
98D71203001000
1
CHEST,TORQUE SET-ENGINE R I
98D71203501000
1
BOOTSTRAP SYSTEM
ALT71000001
1
ELECTRICAL HOIST KIT
S1787CR
1
ENGINE CRADLE
S487ETT2
1
ENGINE TROLLEY
TMHEC29-00-00
1
CRADLE,V2500 ENGINE
TMHET06-00-00
1
TRAILER,ENGINE GROUND HANDLING
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.V01-457)
solvent
(Material No.V02-147)
lockwire
(Material No.V02-158A)
release agent
(Material No.V02-272)
safety cable
(Material No.V02-273)
safety cable
(Material No.V02-274)
safety cable
(Material No.V02-275)
safety cable
(Material No.V02-276)
safety cable
(Material No.V02-277)
safety cable
(Material No.V02-278)
safety cable
(Material No.V02-279)
safety cable
(Material No.V02-280)
safety cable
(Material No.V02-281)
safety cable
(Material No.V08-030)
sealant
(Material No.V08-032)
primer
(Material No.V10-078)
anti-seize compound
(Material No.14SBA1)
Textile-Lint free Cotton -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
210
CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD
400
POWER PLANT, NACELLES AND PYLONS
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 451AL, 452AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL, 462AR
 D. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
17
SCREWS
AIPC 71-51-46-80-010
16
FIRE SEAL ASSEMBLY
AIPC 71-51-46-80-020
15
FIRE SEAL ASSEMBLY
AIPC 71-51-46-80-030
3
GASKET
AIPC 73-11-48-80-080
11
GASKET
AIPC 73-11-48-80-120
14
RIVET
AIPC 78-32-49-83-130
12
FIRE SEAL ASSEMBLY
AIPC 78-32-49-83-140
14
RIVET
AIPC 78-32-79-81-090
13
FIRE SEAL ASSEMBLY
AIPC 78-32-79-81-100
 E. Referenced Information
REFERENCE
DESIGNATION
TASK 05-57-00-200-001-B
Aircraft Stability
TASK 12-13-24-612-011-A
Integrated Drive Generator (IDG) Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check
TASK 12-13-79-610-012-A
Prime the Engine Oil System
TASK 12-13-80-600-010-B
Replenishment of Starter Oil System
TASK 20-28-00-720-005-A
Check of the Electrical Bonding of the Different Components (but not the Fluid Systems and Components Installed on Composite materials)
TASK 22-97-00-710-001-A
Operational Test of the LAND CAT III Capability
TASK 24-21-00-710-042-A
Operational Test of the IDG Disconnect and Reconnect Function - Engine Static
TASK 24-41-00-861-002-A
Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01
Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02
Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A
De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01
De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02
De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 29-14-49-400-001-A
Installation of the Reservoir Pressurization Hose
TASK 30-21-00-710-002-A
Operational Check of the Engine-Air-Intake Ice-Protection System (with the Engines in operation)
TASK 30-21-49-790-010-A
Leak Test of the Inlet Cowl Anti-Ice Supply Ducts with the Engine in Operation
TASK 30-21-49-820-001-A
Rig the Anti-ice Ducts
TASK 31-36-00-740-014-A
Update of the Engine Hours and Cycles in the Flight Data Interface and Management Unit (FDIMU)
TASK 31-60-00-860-001-A
EIS Start Procedure
TASK 31-60-00-860-002-A
EIS Stop Procedure
TASK 36-11-49-400-016-A
Installation of the Sense Line between the Bleed Pressure-Regulator Valve (PRV) and the Pylon Interface
TASK 70-11-50-100-802-A
Local Swab or Wipe Cleaning with Solvent
TASK 70-11-56-910-001-A
Cleaning Requirements after Chemical Contact with Fire Extinguisher Agents, Hydraulic Fluid, Oil or Fuel
TASK 70-23-11-911-013-A
General Torque Tightening Techniques
TASK 70-23-13-911-010-A
Procedures for the Installation of Preformed Packings
TASK 70-23-15-912-010-A
Connection of Electrical Connectors
TASK 70-40-11-911-014-A
Locking Devices General Information
TASK 70-40-11-911-016-A
General Instructions for Uses of Safety Cable
TASK 71-00-00-700-011-B
Test No.13 : Pretested Replacement Engine Test
TASK 71-00-00-710-012-B
Test No.3 : Idle Leak Check
TASK 71-00-00-710-022-B
Test No. 6: Electronic Engine Control (EEC) System Idle Test
TASK 71-00-00-710-046-B
Test No.2 : Wet Motor Leak Check
TASK 71-13-00-010-010-A
Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-410-010-A
Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-800-010-A
Functional Check of Fan Cowl Latch Tension
TASK 71-21-12-200-010-A
Detailed Inspection of FWD Engine Mount Installation
TASK 71-22-11-200-010-A
Detailed Inspection of Aft Engine Mount Installation
TASK 71-71-42-400-010-A
Installation of the Drains Mast
TASK 72-61-49-400-010-B
Installation of the Gearbox Breather Outlet Duct (GBOD)
TASK 73-13-42-720-010-A
Functional Test of the Fuel Recirculation Cooling System without Barfield Tester and without AIDS
TASK 73-13-42-720-010-A-01
Functional Test of the Fuel Recirculation Cooling System with Barfield Tester and without AIDS
TASK 73-13-42-720-010-A-02
Functional Test of the Fuel Recirculation Cooling System without Barfield Tester and with AIDS
TASK 73-13-42-720-010-A-03
Functional Test of the Fuel Recirculation Cooling System with Barfield Tester and with AIDS
TASK 73-22-34-710-040-A
Operational Test of the EEC
TASK 78-30-00-040-012-A
Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance
TASK 78-30-00-440-012-A
Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance
TASK 78-30-00-820-010-A
Rigging of the Thrust Reverser System
TASK 78-32-00-010-010-A
Opening of the Thrust Reverser Halves
TASK 78-32-00-410-010-A
Closing of the Thrust Reverser Halves
TASK 80-13-49-820-010-B
Rig the Starter Ducts
TASK 80-13-51-710-040-B
Operational Test of the Pneumatic Starter Valve and FMU with the CFDS
ESPM 2048230
ESPM 2048240
SPM 702304230501
TASK 05-59-00-00
SPECIAL FLIGHTS - DESCRIPTION AND OPERATION
F Engine Identification Plate
F Table 1 - New Data Entry Plug PN 2A4378 Variants
F Table 2 - New Data Entry Plug PN 2A4378 Variants
F Data Entry Plug Back Shell Inscription
F Forward Engine Mount
F Aft Engine Mount
F Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire Seals
F Fire Seal Installation
F Bootstrap Installation
F Bootstrap Installation Manual Hoist Kit
F Bootstrap Installation Electrical Hoist Kit
F Hinge Crossover Beam
F Fan Cowl and Thrust Reverser Braces
F TAI Location and Hydraulic Reservoir Pressurization Tube Location
F Power Plant, Left Side
F Left Connectors Location
F Power Plant, Right Side
F Forward Junction Box
F Upper/Lower Link Starter Duct and Link Assembly
F Forward Junction Box
F IDG Cable Assembly
F Left Interface Junction Box
F Inspection of the Thrust Reverser Brackets and Inspection of the Engine Fire Seals
F Hydraulic Control Unit
FOR [1000EM1] (ENGINE-1)
TASK 29-11-51-860-040-A
Hydraulic Maintenance Procedure after an Engine Installation (with Engine Pump Installed) or after an Engine Pump Installation
FOR [1000EM2] (ENGINE-2)
TASK 29-13-51-860-001-A
Hydraulic Maintenance Procedure after an Engine Installation (with Engine Pump Installed) or after an Engine Pump Installation
3. Job Set-up
Subtask 71-00-20-860-052-B ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
   (1) Make sure that the two engines have the same ground idle capability (reduced ground idle or non-reduced ground idle).
     (a) To find the engine ground idle capability, do a check of:
   (2) Make sure the aircraft is stable (Ref. AMM TASK 05-57-00-200-001).
NOTE: If the aircraft is on jacks, make sure it is leveled before you install the engine.
   (3) On the center pedestal, on the ENG panel 115VU, make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.
   (4) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC 1(2).
   (5) On the panel 30VU, make sure that the APU BLEED pushbutton switch is released (ON legend off). Make sure that a WARNING NOTICE(S) is in position to tell persons not to press the APU BLEED pushbutton switch. Make sure that a WARNING NOTICE(S) is in position on the HP ground connector to tell persons not to pressurize the pneumatic system.
   (6) Make sure that the ACCESS PLATFORM 1M(3 FT) is in position.
Subtask 71-00-20-010-053-A ** ON A/C NOT FOR ALL
B. Make sure that the fan cowl doors are open (Ref. AMM TASK 71-13-00-010-010):
   (1) FOR [1000EM1] (ENGINE-1)
437AL, 438AR
   (2) FOR [1000EM2] (ENGINE-2)
447AL, 448AR
Subtask 71-00-20-040-051-A ** ON A/C NOT FOR ALL
C. Make sure that the thrust reverser Hydraulic Control Unit (HCU) is deactivated (Ref. AMM TASK 78-30-00-040-012).
Subtask 71-00-20-865-051-A ** ON A/C NOT FOR ALL
WARNING: BEFORE YOU OPEN PHC CIRCUIT BREAKERS 2DA1(2,3), OPEN PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
WARNING: MAKE SURE THAT YOU OPEN THE CIRCUIT BREAKERS AS FOLLOWS:
  • 1JH, 2JH1 AND 3JH1 BEFORE 2KS1
  • 1JH, 2JH2 AND 3JH2 BEFORE 2KS2.
IF YOU DO NOT OBEY THIS SEQUENCE, THERE IS A RISK OF ELECTROCUTION. THIS IS BECAUSE YOU WILL START CONTINUOUS IGNITION IF YOU OPEN CIRCUIT BREAKER 2KS1 OR 2KS2 FIRST.
D. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/AOA/14DA1D04
49VUANTI ICE/PROBES/PITOT/13DA1D02
49VUANTI ICE/RAIN/RPLNT/CAPT1DB1D01
49VUCOM/CVR/SPLY23RKE14
49VUCOM/CVR/CTL26RKE13
121VURCDR/DFDR7TUK16
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B2WE1Q44
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A1WE1Q43
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B2WE2Q42
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A1WE2Q41
122VUANTI ICE/WINDOWS/R4DG2W14
122VUANTI ICE/RAIN/RPLNT/F/O1DB2W11
122VUANTI ICE/WINDOWS/L4DG1X14
122VUANTI ICE/PROBES/2/TAT1DA2Y15
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/1/TAT1DA1Z12
123VUANTI ICE/L/WHSLD1DG1AF10
123VUANTI ICE/R/WHSLD1DG2AF03
FOR FIN: 1000EM1 (ENGINE1)
49VUFUEL/LP VALVE/MOT1/ENG11QGA08
49VUENGINE/1/FIRE DET/LOOP A7WD1A06
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
121VURCDR/DFDR7TUK16
121VUFUEL/LP VALVE/MOT2/ENG13QGM25
121VUENGINE/IGN/ENG1/SYS B3JH1P41
121VUENGINE/IGN/ENG1/SYS A BAT2JH1P39
121VUENGINE/ENG1/FIRE DET/LOOP B8WD1Q38
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R41
122VUELEC/GCU/12XU1T26
122VUANTI ICE/ENG/11DN1X10
FOR FIN: 1000EM2 (ENGINE2)
49VUFUEL/LP VALVE/MOT1/ENG22QGA09
49VUENGINE/2/FIRE DET/LOOP B8WD2A07
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
121VUFUEL/LP VALVE/MOT2/ENG24QGM26
121VUHYDRAULIC/HYD POWER/Y3803GXN30
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
121VUENGINE/ENG2/FADEC B4KS2Q40
121VUENGINE/ENG2/FIRE DET/LOOP A7WD2Q39
122VUELEC/GCU/22XU2T27
122VUANTI ICE/ENG/21DN2W10
123VUY HYD/ELEC/PUMP3802GXAB06
123VUY HYD/ELEC/ELEC PUMP/NORM3801GXAB03
Subtask 71-00-20-865-070-A ** ON A/C NOT FOR ALL
WARNING: OPEN THE PROBE HEATER AND WINDOW HEATER CIRCUIT-BREAKERS BEFORE YOU OPEN THE PHC AND WHC CIRCUIT BREAKERS. IF YOU DO NOT OBEY THIS SEQUENCE:
  • THE PROBES WILL BECOME TOO HOT.
  • THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
E. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/WHC/25DG2W13
122VUANTI ICE/WHC/15DG1X13
122VUANTI ICE/PROBES/PHC/32DA3Y16
122VUANTI ICE/PROBES/PHC/22DA2Y12
Subtask 71-00-20-210-050-A ** ON A/C NOT FOR ALL
F. Check of the Cowling for Correct Condition
   (1) Do a check of the electrical connectors of the aft and forward junction boxes, for correct condition.
   (2) Make sure that these parts are not damaged:
     (a) The forward engine mount (Ref. AMM TASK 71-21-12-200-010)
     (b) The aft engine mount (Ref. AMM TASK 71-22-11-200-010)
     (c) The pylon structure that you can see.
Subtask 71-00-20-110-052-A ** ON A/C NOT FOR ALL
G. Cleaning of the Components
   (1) Clean the parts that follow (Ref. AMM TASK 70-11-50-100-802).
     (a) The mating faces, the shear pins and the fastener holes on the forward engine mount and the aft engine mount.
     (b) The forward and aft mount pads on the pylon.
   (2) Clean the bolts (1), (18) and (2), nuts (16) and (5), barrel nuts (6) and retainer (7) (Ref. AMM TASK 70-11-50-100-802).
F Forward Engine Mount ** ON A/C NOT FOR ALL
F Aft Engine Mount ** ON A/C NOT FOR ALL
   (3) Make sure that there are no signs of seizure or wear.
Subtask 71-00-20-230-051-A ** ON A/C NOT FOR ALL
H. Do an ultra-high-sensitivity post-emulsified fluorescent-penetrant inspection of the engine mount bolts (1), (2) and (18). Refer to PN 2A4414 IAE V2500 SPM 702304230501. No damage or cracks are permitted.
F Forward Engine Mount ** ON A/C NOT FOR ALL
F Aft Engine Mount ** ON A/C NOT FOR ALL
NOTE: Fluorescent penetrant inspection is only required for the bolts that have been used previously. New or CMM inspected bolts do not require this inspection.
Subtask 71-00-20-240-051-A ** ON A/C NOT FOR ALL
I. Visual Inspections
   (1) Do a visual inspection of the forward engine mount nuts (5) and (16) with a MAGNIFYING GLASS POWER 10X. Do not remove the silver plating.
F Forward Engine Mount ** ON A/C NOT FOR ALL
If an engine nut is cracked, reject it.
   (2) Do a visual inspection of the barrel nuts (6) with a MAGNIFYING GLASS POWER 10X . No cracks, nicks, scratches or gouges are allowed. If any damage is found, replace the barrel nut. Silver plating missing from the external surface of the barrel nut is acceptable.
The threads must be in good condition and no silver plating is allowed to be missing from the threads. If silver plating is missing from the barrel nut threads, the barrel nut must be replaced.
Subtask 71-00-20-420-050-A ** ON A/C NOT FOR ALL
J. If replacement engine does not have all its equipment, remove the accessories from the removed engine and install them on the replacement engine.
Subtask 71-00-20-410-072-A ** ON A/C NOT FOR ALL
K. If the engine fire seals (Post SBE 72-0230) are applicable, install them as follows:
F Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire Seals ** ON A/C NOT FOR ALL
F Fire Seal Installation ** ON A/C NOT FOR ALL
   (1) Close the applicable thrust reverser halves (Ref. AMM TASK 78-32-00-410-010):
     (a) FOR [1000EM1] (ENGINE-1)
451AL and 452AR
     (b) FOR [1000EM2] (ENGINE-2)
461AL and 462AR.
   (2) Put the AIPC 71-51-46-80-030 FIRE SEAL ASSEMBLY (15) and the AIPC 71-51-46-80-020 FIRE SEAL ASSEMBLY (16) in position on the heat shield.
   (3) Make sure that the fire seal assemblies (15) and (16) fully touch the thrust-reverser bracket assembly.
   (4) Make sure that the fire seal assemblies (15) and (16) are against the bracket and that they are not compressed.
   (5) Make marks to show the contour of the forward and bottom surfaces of the fire seal assemblies (15) and (16) on the heat shield with the PENCIL.
   (6) Open the applicable thrust reverser halves (Ref. AMM TASK 78-32-00-010-010):
     (a) FOR [1000EM1] (ENGINE-1)
451AL and 452AR
     (b) FOR [1000EM2] (ENGINE-2)
461AL and 462AR.
   (7) Install the fire seal assemblies (15) and (16) as follows:
     (a) Install the AIPC 71-51-46-80-030 FIRE SEAL ASSEMBLY (15) and the AIPC 71-51-46-80-020 FIRE SEAL ASSEMBLY (16) on the fire shield with the AIPC 71-51-46-80-010 SCREWS (17).
     (b) TORQUE the screws (17) to between 8 and 6 lbf.in (0.09 and 0.07 m.daN ) T.
   (8) Fill all the spaces in the fire seal assemblies (15) and (16) with the sealant (Material No.V08-030) :
     (a) Let the sealant cure for 24 hours at 77 deg.F (25.00 deg.C) and 50 percent humidity.
4. Procedure
Subtask 71-00-20-420-051-A ** ON A/C NOT FOR ALL
A. Put the replacement engine in position under the pylon
   (1) Put the S487ETT2 ENGINE TROLLEY or TMHET06-00-00 TRAILER,ENGINE GROUND HANDLING and S1787CR ENGINE CRADLE or TMHEC29-00-00 CRADLE,V2500 ENGINE with the replacement engine in position under the pylon.
   (2) Install the forward hinge arm (4) and (5) with the ball pins (1) on the forward 98D71203501000 BOOTSTRAP SYSTEM.
   (3)
F Bootstrap Installation ** ON A/C NOT FOR ALL
     (a)
F Bootstrap Installation Manual Hoist Kit ** ON A/C NOT FOR ALL
       1 Put the dynamometers (4) and the clamps (3) in position on the forward hinge arms (1) and (7) and the rear beam (8).
       2 Install the pins (2), the clamps (3) and the dynamometers (4) on the bootstrap system.
       3 Install the four chain pulley blocks (5).

or

     (b)
F Bootstrap Installation Electrical Hoist Kit ** ON A/C NOT FOR ALL
       1 Put the dynamometric shackle (4) and the clamps (3) in position on the forward hinge arms (1) and (7) and the rear beam (9).
       2 Install the pins (2), the clamps (3) and the dynamometric shackles (4) on the bootstrap system.
       3 Install the four electrical hoist 2T (5).
NOTE: Make sure that the dynamometers or the electrical motors are installed outboard of the engine.
   (4) Attach the chain hooks (6) to the engine cradle.
   (5) Remove the pins that attach the engine cradle to the engine trolley.
   (6) Put the locking levers of the handling hoist in UP position (for the manual hoist kit).
   (7) Lift the engine cradle to disengage it from the trolley.
   (8) Slightly raise the forward section of the engine cradle then the aft section.
NOTE:
F Bootstrap Installation Electrical Hoist Kit ** ON A/C NOT FOR ALL
F Bootstrap Installation Manual Hoist Kit ** ON A/C NOT FOR ALL
  • 600 daN (1350 lbf) (611.6 Kg) between the 2 front chains.
  • 200 daN (450 lbf) (203.9 Kg) between the 2 rear chains.
NOTE: Use the level indicators on the forward hinge arms of the bootstrap to keep the hinge arms as near as possible to the horizontal position.
Subtask 71-00-20-210-052-A ** ON A/C NOT FOR ALL
B. Make certain that the hinge crossover beam (1) is correctly engaged in the V-groove (2).
F Hinge Crossover Beam ** ON A/C NOT FOR ALL
Subtask 71-00-20-420-052-A ** ON A/C NOT FOR ALL
C. Put the Power Plant in position
WARNING: BEFORE YOU REMOVE OR INSTALL THE POWER PLANT, MAKE SURE THAT ALL PERSONNEL IS AWAY FROM THE AIRCRAFT. THE POWER PLANT WEIGHS APPROXIMATELY 7300 POUNDS. IF IT FALLS ON PERSONS, INJURY OR DEATH CAN OCCUR.
CAUTION: DO NOT INSERT THE SHEAR PINS OF ONE MOUNT BEFORE THE OTHER OR DAMAGE TO THE MOUNTS AND PYLON CAN RESULT.
   (1) Keep the pylon and engine face of the forward and aft attach fittings parallel so as to put the locating pins easily in their location.
NOTE: Rear lifts give the roll attitude.
NOTE: At the forward end you can move the engine laterally by plus or minus 20 mm (0.79 in.).
     (a) To move the engine to the left side, lift with the right hand hoist and/or lower with the left hand hoist.
     (b) To move the engine to the right side, lift with the left hand hoist and/or lower with the right hand hoist.
   (2) Lift the engine:
CAUTION: DO NOT INSTALL THE LOCATING PINS OF ONE MOUNT BEFORE THE OTHER OR DAMAGE TO MOUNTS AND PYLON COULD RESULT.
CAUTION: MAKE SURE THAT THE PYLON FORWARD FAIRING IS CORRECTLY SEATED ON THE TRAILING EDGE LAND OF THE AIR INTAKE COWL. IF THE PYLON FORWARD FAIRING IS NOT IN THE CORRECT POSITION, DAMAGE CAN OCCUR.
     (a) Slowly lift the engine to the pylon. Make sure that the shear pins on the engine mounts engage with the holes in the pylon.
   (3)
F Bootstrap Installation Electrical Hoist Kit ** ON A/C NOT FOR ALL
F Bootstrap Installation Manual Hoist Kit ** ON A/C NOT FOR ALL
Subtask 71-00-20-210-073-A ** ON A/C NOT FOR ALL
D. Do a Check of the Running Torque of the Forward and Aft Mount Bolts
   (1) Do a check of the running torque of the forward engine mount bolts as follows:
F Forward Engine Mount ** ON A/C NOT FOR ALL
     (a) Apply a thin layer of anti-seize compound (Material No.V10-078) to the threads of the engine mount bolts, the nuts and the washers.
     (b) Install the washers under the head of the bolts (1) and (18).
     (c) Install the bolts (1) and (18) through holes in the pylon and the forward mount.
     (d) Install the nuts (5) and (16) on the bolts (1) and (18).
     (e) Tighten the nuts by hand until they are hard to turn.
NOTE: Make sure that the nuts are correctly threaded on the bolts.
     (f) Use a torque wrench to tighten the nuts until at least two full threads show on the other side of the nuts (Ref. AMM TASK 70-23-11-911-013).
       1 Measure the torque required to tighten the bolt (Ref. AMM TASK 70-23-11-911-013). The minimum torque should be 70 lbf.in (0.79 m.daN). The maximum torque should be 600 lbf.in (6.78 m.daN).
       2 If the bolt torque is less than 70 lbf.in (0.79 m.daN), replace the nut (5) or (16) and do steps (a) thru (f) 1_ again.
       3 If the torque is more than 600 lbf.in (6.78 m.daN), remove the bolt and the nut and look for damaged threads. If the threads are damaged, replace the bolt and nut and do steps (a) thru (f) 2_ again.
     (g) Remove the forward mount bolts and nuts.
   (2) Do a check of the running torque of the aft engine mount bolts as follows:
F Aft Engine Mount ** ON A/C NOT FOR ALL
     (a) Apply a thin layer of anti-seize compound (Material No.V10-078) to the threads of the engine mount bolts, the nuts and the washers.
     (b) Install the washers (3) under the head of the bolts (2).
     (c) Install the aft engine mount bolts (2) into the barrel nuts (6).
     (d) Tighten the bolts 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 until at least two full threads show on the other side of the nuts (Ref. AMM TASK 70-23-11-911-013).
       1 Measure the torque required to tighten the bolt (Ref. AMM TASK 70-23-11-911-013). The minimum torque should be 90 lbf.in (1.02 m.daN). The maximum torque should be 800 lbf.in (9.04 m.daN).
       2 If the bolt torque is less than 90 lbf.in (1.02 m.daN), replace the nut (6) and do steps (a) thru (e) 1_ again.
       3 If the torque is more than 800 lbf.in (9.04 m.daN), remove the bolt and the nut and look for damaged threads. If the threads are damaged, replace the bolt and nut and do steps (a) thru (e) 2_ again.
     (f) Remove the aft mount bolts and nuts.
Subtask 71-00-20-420-053-A ** ON A/C NOT FOR ALL
E. Installation of the Forward and Aft Engine Mounts
   (1) Install the forward engine mount (4):
F Forward Engine Mount ** ON A/C NOT FOR ALL
     (a) Lubricate the bolts (1) and (18), washers (2) and (17), nuts (5) and (16) and shear pins (19) with the anti-seize compound (Material No.V10-078) .
NOTE: Lockwire locks the forward center bolt which has no upper retainer.
     (b) Install the retainers (12), washers (17), bolts (18) and nuts (16).
       1 Make sure that you install the washers (17) with the recess against the bolt heads.
     (c) Put the nut (5) and the retainer (6) in position.
     (d) Install the washer (7) and the nut (8).
     (e) TORQUE the nut (8) to between 40 and 35 lbf.in (0.45 and 0.40 m.daN ) T.
     (f) Install the washer (2) and the bolt (1) on the middle part of the forward engine mount (4).
       1 Make sure that you install the washer (2) with the recess against the bolt head.
     (g) Use a standard wrench to tighten the bolts (1) and (18).
     (h) Torque the bolts (1) and (18) of the forward engine mount (4):
       1 Hold the nut (16) with a wrench and make sure that it is stable.
CAUTION: THIS IS NOT THE FINAL TORQUE FOR THE FORWARD ENGINE MOUNT BOLTS.
       2 TORQUE the bolts (1) and (18) to between 132.74 and 88.49 lbf.ft (18.00 and 12.00 m.daN ) T.
     (i) Remove the padding installed between the engine and the forward engine mount (4).
   (2) Install the aft engine mount (4):
F Aft Engine Mount ** ON A/C NOT FOR ALL
     (a) Lubricate the bolts (2), washers (3) and shear pins (5) with the anti-seize compound (Material No.V10-078) .
     (b) Install the barrel nuts (6):
CAUTION: INSTALL THE BARREL NUT WITH THE ROUNDED SIDE UP. IF NOT, DAMAGE TO THE BARREL NUT CAN OCCUR.
       1 Install the barrel nuts (6), retainers (7), washers (3) and bolts (2).
         a Make sure that you install the washers (3) with the recess against the bolt heads.
     (c) TORQUE (final value) the bolts (2) to between 70.5 and 65 m.daN (519.91 and 479.35 lbf.ft ) T (Ref. AMM TASK 70-23-11-911-013):
       1 Do a check of the torque value of the bolts (2) of the aft engine mount (4) to make sure that the final torque value is correct.
       2 Make sure that the surfaces between the pylon (1) and the aft engine mount (4) touch each other.
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
     (d) Safety the bolts (2) with the safety cable (Material No.V02-275) (Ref. AMM TASK 70-40-11-911-016).
Alternate: Use the lockwire (Material No.V02-147) (Ref. AMM TASK 70-40-11-911-014), safety cable (Material No.V02-272) , safety cable (Material No.V02-273) , safety cable (Material No.V02-274) , safety cable (Material No.V02-276) , safety cable (Material No.V02-277) , safety cable (Material No.V02-278) ,
safety cable (Material No.V02-279) , safety cable (Material No.V02-280) or safety cable (Material No.V02-281) (Ref. AMM TASK 70-40-11-911-016).
     (e) Install the flexible seals on the pylon (1).
Subtask 71-00-20-080-050-A ** ON A/C NOT FOR ALL
F. Removal of the lifting equipment and the bootstrap assembly:
   (1) Remove the lifting equipment:
     (a) Put the pulley locking levers in the DOWN position (for the manual hoist kit).
     (b) Reduce the load on the engine cradle using the four hoists.
     (c) Disconnect the engine cradle from the engine.
     (d) Lower the engine cradle. Make sure that the engine cradle does not hit the engine.
     (e) Install the engine cradle on the engine trolley.
     (f) Remove the four chain hooks (6) from the engine cradle.
     (g) Remove the engine trolley rearwards.
   (2) Remove the bootstrap assembly as follows:
F Bootstrap Installation ** ON A/C NOT FOR ALL
     (a) Removal of the Hoist Kit:

       1
F Bootstrap Installation Manual Hoist Kit ** ON A/C NOT FOR ALL
         a Remove the four chain pulley blocks (5).
         b Hold the dynamometers (4) and the clamps (3) in position on the forward hinge arms (1) and (7) and the rear beam (8) of the bootstrap system.
         c Remove the pins (2), the clamps (3) and the dynamometers (4) from the bootstrap system.
       2
F Bootstrap Installation Electrical Hoist Kit ** ON A/C NOT FOR ALL
         a Remove the four electrical hoist 2T (5).
         b Hold the dynamometric shackle (4) and the clamps (3) in position on the forward hinge arms (1) and (7) and the rear beam (9) of the bootstrap system.
         c Remove the pins (2), clamps (3) and dynamometric shackles (4) from the bootstrap system.
     (b) Remove the pins (8) and remove the rear beam (9).
     (c) Remove the pins (1) and remove the link (2).
     (d) Remove the pins (3) and remove the left and right hinge arms (4) and (5).
     (e) Release the left and right clamps (7).
CAUTION: DO NOT LET THE BOOTSTRAP SPACER STAY INSTALLED ON THE PYLON AFTER THE BOOTSTRAP REMOVAL. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE POWER PLANT CAN OCCUR.
     (f) If the bootstrap is equipped with a spacer:
       1 Remove the spacer (10) from the pylon.
     (g) Remove the center hinge clamp (6) from the pylon.
Subtask 71-00-20-760-050-A ** ON A/C NOT FOR ALL
G. Do a check of the electrical bonding
   (1) Measure the resistance value (ohmic) (Ref. AMM TASK 20-28-00-720-005). Make sure that the resistance between the engine and the pylon is not more than 1.5 milliohm.
Subtask 71-00-20-420-054-A ** ON A/C NOT FOR ALL
H. Final Torque of the Bolts of the Forward Mount
CAUTION: MAKE SURE THAT THE TORQUE WRENCH DOES NOT TOUCH THE FORWARD ENGINE MOUNT DURING TIGHTENING TO NOT CHANGE THE TORQUE APPLIED TO THE BOLTS.
   (1) Use the special tool 98D71203001000 CHEST,TORQUE SET-ENGINE R I to TORQUE the forward mount bolts to the final torque value to between 47.45 and 43.39 m.daN (349.93 and 319.99 lbf.ft ) T (Ref. AMM TASK 70-23-11-911-013).
NOTE: The given torque values take into account the length of the torque wrench.
     (a) Use the Torque Wrench to torque the four forward mount bolts (18).
       1 Check the torque on the forward engine mount bolts (18) again to make sure that the final torque is correct.
     (b) Use the torque wrench and load reducer to torque the center bolt (1) of the forward mount.
       1 Check the torque on the center bolt (1) again to make sure that the final torque is correct.
NOTE: The use of the load reducer (P/N GA184A) with the torque wrench (P/N TQFRM14) changes the value of the torque selected. You must set a value between 13 m.daN (95.87 lbf.ft) and 14 m.daN (103.24 lbf.ft) on the wrench to get the torque required for the forward center mount bolt.
NOTE: After you tighten the engine mount bolts to the final torque, make sure that the surfaces between the pylon and the forward engine mount are in contact.
   (2) Install safety cable (Material No.V02-275) (Ref. AMM TASK 70-40-11-911-016) on the bolt (1).
Alternate: Use lockwire (Material No.V02-147) (Ref. AMM TASK 70-40-11-911-014), safety cable (Material No.V02-272) , safety cable (Material No.V02-273) , safety cable (Material No.V02-274) , safety cable (Material No.V02-276) , safety cable (Material No.V02-277) , safety cable (Material No.V02-278) ,
safety cable (Material No.V02-279) , safety cable (Material No.V02-280) or safety cable (Material No.V02-281) (Ref. AMM TASK 70-40-11-911-016).
NOTE: You can use lockwire diameters ranging from 0.8 mm to 1.2 mm to safety the bolt (1).
   (3) Install the retainers (11) and (13) secured with the bolt (9), the washers (10) and (14) and the nut (15).
   (4) TORQUE the bolts (9) to between 36 and 24 lbf.in (0.41 and 0.27 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
   (5) Remove the fan cowl and thrust reverser braces.
F Fan Cowl and Thrust Reverser Braces ** ON A/C NOT FOR ALL
     (a) Put the fan cowl hold-open rods into position to hold the weight of the fan cowls (Ref. AMM TASK 71-13-00-010-010).
     (b) Put the thrust reverser half hold-open rods into position to hold the weight of the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010).
     (c) Remove the support arms (5) and (6) from the fan cowls and the thrust reverser halves.
     (d) Remove the adjustable struts (1) and (2).
5. Close-up
Subtask 71-00-20-020-081-A ** ON A/C NOT FOR ALL
A. Remove ballast installed for aircraft stability.
   (1) If all engines are in place, remove all ballast installed for aircraft stability.
Subtask 71-00-20-630-050-A ** ON A/C NOT FOR ALL
B. Remove caps from the open ends.
Subtask 71-00-20-420-096-A ** ON A/C NOT FOR ALL
C. Installation of the Bleed Pressure Regulator Valve (PRV) Sense Line.
   (1) Install the sense line between the bleed pressure regulator valve (PRV) and the pylon interface (Ref. AMM TASK 36-11-49-400-016).
Subtask 71-00-20-420-055-A ** ON A/C NOT FOR ALL
D. Installation of the Components on the Left and Right Sides of the Engine
   (1) Install these components on the left side of the engine.
     (a) Connect the sensor tubes.
F TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL
       1 Connect the pressure-regulating-valve sensor tube (20).
       2 TORQUE the tube union nut to between 2.3 and 2.0 m.daN (16.96 and 14.75 lbf.ft ) T.
       3 Connect the thermostat sensor tube (11).
       4 TORQUE the union nut to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft ) T (Ref. AMM TASK 70-23-11-911-013).
     (b) Connect the fuel tubes on the fluid disconnect panel.
F Power Plant, Left Side ** ON A/C NOT FOR ALL
CAUTION: DO NOT LET FUEL GO DOWN THE FAN CASE AND CONTACT THE SEAL RING BETWEEN THE FAN CASE AND THE ANGLE GEARBOX. REMOVE THE FUEL WITH A CLEAN LINT-FREE CLOTH. THE FUEL CAN CAUSE DETERIORATION OF THE SEAL RING.
       1 Install the new AIPC 73-11-48-80-120 GASKET (11) on the fuel supply tube (8) (Ref. AMM TASK 70-23-13-911-010).
       2 Put the fuel supply tube (8) in position on the fluid disconnect panel and install the four bolts (9) and washers (10).
       3 TORQUE the bolts (9) to between 110 and 90 lbf.in (1.24 and 1.02 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
       4 Safety the bolts (9) with lockwire (Material No.V02-147) (Ref. AMM TASK 70-40-11-911-014).
Alternative: Use the safety cable kit (Material No.V02-272) , safety cable kit (Material No.V02-273) , safety cable kit (Material No.V02-274) , safety cable kit (Material No.V02-275) , safety cable kit (Material No.V02-276) safety cable kit (Material No.V02-277) , safety cable kit (Material No.V02-278) ,
safety cable kit (Material No.V02-279) , safety cable ferrule (Material No.V02-280) or safety cable ferrule (Material No.V02-281) (Ref. AMM TASK 70-40-11-911-016).
       5 Install the new AIPC 73-11-48-80-080 GASKET (3) on the fuel return to the tank tube (4).
       6 Put the fuel return to the tank tube (4) in position on the fuel disconnect panel and install the four bolts (6) and washers (5).
       7 TORQUE the bolts (6) to between 0.42 and 0.38 m.daN (37.17 and 33.63 lbf.in ) T (Ref. AMM TASK 70-23-11-911-013).
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
       8 Safety the bolts (6) with lockwire (Material No.V02-147) (Ref. AMM TASK 70-40-11-911-014).
Alternative: Use the safety cable kit (Material No.V02-272) , safety cable kit (Material No.V02-273) , safety cable kit (Material No.V02-274) , safety cable kit (Material No.V02-275) , safety cable kit (Material No.V02-276) safety cable kit (Material No.V02-277) , safety cable kit (Material No.V02-278) ,
safety cable kit (Material No.V02-279) , safety cable ferrule (Material No.V02-280) or safety cable ferrule (Material No.V02-281) (Ref. AMM TASK 70-40-11-911-016).
       9 If there is fuel leakage on the fan case, remove it (Ref. AMM TASK 70-11-56-910-001).
     (c) Connect the hydraulic tubes on the fluid disconnect panel.
CAUTION: DO NOT LET HYDRAULIC FLUID GO DOWN THE FAN CASE AND CONTACT THE SEAL RING BETWEEN THE FAN CASE AND THE ANGLE GEARBOX. REMOVE THE HYDRAULIC FLUID WITH A CLEAN LINT FREE CLOTH. THE HYDRAULIC FLUID CAN CAUSE DETERIORATION OF THE SEAL RING.
       1 Connect the hydraulic-case drain connector (7) on the fluid disconnect panel.
       2 TORQUE the connector (7) to between 245 and 215 lbf.in (2.77 and 2.43 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
       3 Connect the hydraulic-pressure tube connector (2) on the fluid disconnect panel.
       4 TORQUE the connector (2) to between 10.7 and 9.7 m.daN (78.91 and 71.53 lbf.ft ) T (Ref. AMM TASK 70-23-11-911-013).
       5 Connect the hydraulic-suction tube connector (1) on the fluid disconnect panel.
         a Tighten the hydraulic-suction tube connector (1) with your hand.
       6 If there is fuel leakage on the fan case, remove it (Ref. AMM TASK 70-11-56-910-001).
     (d) Connect the cabin air duct.
F TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL
       1 Put the bleed-air duct (10) in position on the pylon bleed-air duct and install the coupling (7).
       2 TORQUE the coupling (7) to between 0.96 and 0.85 m.daN (84.96 and 75.22 lbf.in ) T.
       3 Install the coupling (7). To do this, tap the coupling (7) with the MALLET - PLASTIC.
       4 TORQUE the coupling (7) again to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in ) T.
       5 Tap the coupling (7) again.
       6 TORQUE the coupling (7) again to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in ) T.
     (e) Connect the Thermal Anti-Ice (TAI) duct.
F TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL
       1 Put the duct (18) in position between the TAI duct and the pylon TAI duct and install the couplings (19). Do not tighten the couplings (19) at this time.
     (f) On the fan case near the V-groove at the 11 o'clock position, connect electrical connector 4004VC.
F Left Connectors Location ** ON A/C NOT FOR ALL
     (g) Connect thrust-reverser harness connectors 4101KS-A and 4101KS-B on the thrust reverser Hydraulic Control Unit (HCU).
F Left Connectors Location ** ON A/C NOT FOR ALL
   (2) Install these components from the right side of the engine.
F Power Plant, Right Side ** ON A/C NOT FOR ALL
     (a) Connect the starter duct (4).
F Forward Junction Box ** ON A/C NOT FOR ALL
F Upper/Lower Link Starter Duct and Link Assembly ** ON A/C NOT FOR ALL
F Forward Junction Box ** ON A/C NOT FOR ALL
       1 Put the starter duct (4) in position on the pylon starter duct (6) and install the coupling (5). Do not tighten the coupling (5) at this time.
         a Adjust the lengths of the link assemblies to align the two ducts, if necessary.
       2 Adjust the starter duct (4) (Ref. AMM TASK 80-13-49-820-010).
     (b) Connect the TAI duct (2).
F Forward Junction Box ** ON A/C NOT FOR ALL
CAUTION: MAKE SURE THE COUPLINGS DO NOT TOUCH ADJACENT COMPONENTS OR FAN COWL DOORS (WHEN CLOSED). DAMAGE TO COMPONENTS CAN OCCUR.
       1 Put the TAI duct (2) in position on the pylon TAI duct (1) and install the coupling (3). Do not tighten the coupling (3) at this time.
       2 Make sure that the coupling (3) is installed correctly.
         a Make sure that the T-bolt (7) on the coupling (3) is installed at a 20-degree angle from the top of the duct.
         b Make sure that the T-bolt (7) does not touch the fan-cowl door hinge when the fan cowl door is closed.
       3 Adjust the TAI duct (2) (Ref. AMM TASK 30-21-49-820-001).
     (c) On the fan case near the V-groove at the 1 o'clock position, connect electrical connector 4005VC.
F Power Plant, Right Side ** ON A/C NOT FOR ALL
     (d) On the forward pylon junction-box, connect electrical connectors 402VC, 404VC, 405VC, 406VC, 408VC, 447VC, 448VC and 457VC (Ref. AMM TASK 70-23-15-912-010).
F Forward Junction Box ** ON A/C NOT FOR ALL
     (e) On the pylon junction box, connect electrical connectors 401VC, 403VC, 407VC and 409VC (Ref. AMM TASK 70-23-15-912-010).
F Forward Junction Box ** ON A/C NOT FOR ALL
     (f) Do a check of the bend on the IDG cable assembly.
F IDG Cable Assembly ** ON A/C NOT FOR ALL
       1 Make sure that there is not too much bend on the cable assembly (2) that will cause too much force on the connector contacts.
       2 If there is too much bend on the cable assembly (2), adjust the cable routing and the bracket (14) as follows:
         a Loosen the nuts (16) from the bolts (15).
         b Move the bracket (14) along the slots to remove the bend on the cable assembly (2).
         c TORQUE the nuts (16) to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
     (g) On the pylon junction box, connect generator harness connector 400VC.
CAUTION: CONTACTS HAVE TO BE REPLACED IN CASE OF ANY WEAR AND TEAR SIGNS (HOLES, SCRATCH, DISCOLORATION, TEARS, PITTED MARKS).
       1 Do not clean the contacts with abrasive material.
       2 Connect the DYNAMOMETER 15 DAN (33 LBF) - PULL on the test pin and do a pin retention check of the sockets.
         a For a CANNON contact ESPM 2048230, make sure that the minimum extraction force value is 1.2 daN (2.7 lbf).
         b For the FRAMATOME (former SOURIAU) contact ESPM 2048240, make sure that the minimum extraction force value is 2.8 daN (6.3 lbf).
       3 Tighten the connector with the WRENCH - STRAP until the orange color is shown in the window of the coupling nut.
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
         a Safety generator harness connector 400VC with lockwire (Material No.V02-147) (Ref. AMM TASK 70-40-11-911-014).
Alternative: Use the safety cable kit (Material No.V02-272) , safety cable kit (Material No.V02-273) , safety cable kit (Material No.V02-274) , safety cable kit (Material No.V02-275) , safety cable kit (Material No.V02-276) , safety cable kit (Material No.V02-277) , safety cable kit (Material No.V02-278) , safety cable kit (Material No.V02-279) , safety cable ferrule (Material No.V02-280) or safety cable ferrule (Material No.V02-281) (Ref. AMM TASK 70-40-11-911-016).
F Forward Junction Box ** ON A/C NOT FOR ALL
     (h) On the aft interface junction-box, connect electrical connectors 450VC-A, 452VC-A and 454VC.
F Left Interface Junction Box ** ON A/C NOT FOR ALL
     (i) On the forward section of the combustion case at the 11 o'clock position, connect the hydraulic-reservoir pressurization tube (engine 1 only) (Ref. AMM TASK 29-14-49-400-001).
F TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL
     (j) Install the drain mast (Ref. AMM TASK 71-71-42-400-010).
Subtask 71-00-20-410-071-A ** ON A/C NOT FOR ALL
E. If the engine fire seals (Pre SBE 72-0230) are applicable, install them as follows:
F Inspection of the Thrust Reverser Brackets and Inspection of the Engine Fire Seals ** ON A/C NOT FOR ALL
   (1) Close the applicable thrust reverser halves (Ref. AMM TASK 78-32-00-410-010):
     (a) FOR [1000EM1] (ENGINE-1)
451AL and 452AR
     (b) FOR [1000EM2] (ENGINE-2)
461AL and 462AR.
   (2) Put the AIPC 78-32-49-83-140 FIRE SEAL ASSEMBLY (12) and the AIPC 78-32-79-81-100 FIRE SEAL ASSEMBLY (13) in position on the heat shield.
   (3) Make sure that the fire seal assemblies (12) and (13) fully touch the thrust-reverser bracket assembly.
   (4) Make sure that the fire seal assemblies (12) and (13) are against the bracket and that they are not compressed.
   (5) Make marks to show the contour of the forward and bottom surfaces of the fire seal assemblies (12) and (13) on the heat shield with the PENCIL.
   (6) Open the applicable thrust reverser halves (Ref. AMM TASK 78-32-00-010-010):
     (a) FOR [1000EM1] (ENGINE-1)
451AL and 452AR
     (b) FOR [1000EM2] (ENGINE-2)
461AL and 462AR.
   (7) Measure 0.125 in. (3.17 mm) from the aft part of the forward contour of the fire seal assemblies (12) and (13) and make a parallel line on the heat shield with the PENCIL.
   (8) Align the fire seal assemblies (12) and (13) with the aft contour and the bottom contour on the heat shield.
   (9) Before you drill the holes, put the PLATE - STEEL, 500X500X3 MM (19.68X19.68X0.12 IN) in position between the strut fairing and the heat shield to protect the strut fairing.
   (10) Drill through the three pilot holes of the fire seal assemblies (12) and (13) into the heat shield:
     (a) Make the holes larger with the DRILL - NO 21 (DIA 0.159 IN - 4.039 MM).
   (11) Remove the burrs from the holes in the fire seal assemblies (12) and (13) and the heat shield.
   (12) Clean the fire seal assemblies (12) and (13) and the surfaces of the heat shield and block seal:
     (a) Make a Textile-Lint free Cotton - (Material No.14SBA1) moist with the solvent (Material No.V01-457) and clean:
  • The fire seal assemblies (12) and (13)
  • The aft and inboard surfaces of the heat shield
  • The aft and inboard surfaces of the block seal.
     (b) Let the solvent (Material No.V01-457) dry.
   (13) Apply primer on the surface:
     (a) Apply the primer (Material No.V08-032) on the mating surfaces of the fire seal assemblies (12) and (13).
     (b) Let the primer (Material No.V08-032) dry for 20 minutes.
   (14) Apply the release agent (Material No.V02-158A) on the aft surface and the inboard corner of the block seal.
   (15) Apply sealant on the surface:
     (a) Apply the sealant (Material No.V08-030) on the mating surfaces of the fire seal assemblies (12) and (13).
   (16) Put the fire seal assemblies (12) and (13) in position on the heat shield.
   (17) Install the rivets:
CAUTION: THERE IS LIMITED SPACE BETWEEN THE HEATSHIELD AND THE STRUT FAIRING. INSTALL THE RIVETS GRADUALLY AND WITH PROGRESSIVE DEPTH ATTAINMENT OR DAMAGE TO THE STRUT FAIRING AND/OR HEATSHIELD MAY OCCUR. PUT A WEDGE BLOCK BETWEEN THE HEATSHIELD AND THE STRUT FAIRING TO GENTLY SPRING THE OPENING WIDER TO ALLOW FOR ADDITIONAL SPACE TO INSTALL RIVETS. DO NOT BEND THE HEATSHIELD.
     (a) Install the AIPC 78-32-49-83-130 RIVET (14) and the AIPC 78-32-79-81-090 RIVET (14) in the center hole.
     (b) Install the rivets (14) in the upper and lower holes.
   (18) Fill all the spaces in the fire seal assemblies (12) and (13) with the sealant (Material No.V08-030) :
     (a) Let the sealant cure for 24 hours at 77 deg.F (25.00 deg.C) and 50 percent humidity.
Subtask 71-00-20-820-050-A ** ON A/C NOT FOR ALL
F. Do the Adjustment
   (1) Adjust the thrust reverser latches, bumpers and compression struts (Ref. AMM TASK 78-30-00-820-010).
   (2) Adjust the fan cowls (Ref. AMM TASK 71-13-00-800-010).
NOTE: Make sure that the gearbox breather outlet duct (GBOD) aligns with the gearbox breather outlet vent on the right fan cowl. If it does not align, loosen the GBOD fasteners, align the GBOD with the vent and torque the fasteners (Ref. AMM TASK 72-61-49-400-010).
Subtask 71-00-20-410-051-A ** ON A/C NOT FOR ALL
G. Close access
   (1) Check the HP bleed and pressure regulating valves configuration.
NOTE: Make sure that HP bleed and pressure regulating valves are not mechanically locked and can operate freely.
   (2) Close the thrust reverser cowls (Ref. AMM TASK 78-32-00-410-010):
     (a) FOR [1000EM1] (ENGINE-1)
451AL, 452AR.
     (b) FOR [1000EM2] (ENGINE-2)
461AL, 462AR.
Subtask 71-00-20-440-050-A ** ON A/C NOT FOR ALL
H. Activate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-440-012).
F Hydraulic Control Unit ** ON A/C NOT FOR ALL
Subtask 71-00-20-611-050-A ** ON A/C NOT FOR ALL
I. Do a Check of the Engine Oil System and Prime It
   (1) Prime the engine oil system (Ref. AMM TASK 12-13-79-610-012).
   (2) Fill the Integrated Drive Generator (IDG) oil system (Ref. AMM TASK 12-13-24-612-011).
Subtask 71-00-20-612-050-B ** ON A/C NOT FOR ALL
J. Service the Starter with Oil (Ref. AMM TASK 12-13-80-600-010).
NOTE: The starter may have been drained when the engine was removed.
Subtask 71-00-20-410-053-A ** ON A/C NOT FOR ALL
K. Close Access
   (1) Close the fan cowl (Ref. AMM TASK 71-13-00-410-010):
     (a) FOR [1000EM1] (ENGINE-1)
437AL, 438AR.
     (b) FOR [1000EM2] (ENGINE-2)
447AL, 448AR.
   (2) Remove the access platform(s).
   (3) On the center pedestal, on the ENG panel 115VU:
     (a) Remove the WARNING NOTICE(S).
   (4) On the overhead maintenance panel 50VU:
     (a) Remove the WARNING NOTICE(S).
   (5) On the panel 30VU:
     (a) Remove the WARNING NOTICE(S) from the APU BLEED pushbutton switch.
   (6) Remove the WARNING NOTICE(S) on the HP ground connector.
Subtask 71-00-20-865-072-A ** ON A/C NOT FOR ALL
WARNING: CLOSE THE PHC AND WHC CIRCUIT BREAKERS BEFORE YOU CLOSE THE PROBE HEATER AND WINDOW HEATER CIRCUIT-BREAKERS. IF YOU DO NOT OBEY THIS SEQUENCE:
  • THE PROBES WILL BECOME TOO HOT.
  • THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
L. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/WHC/25DG2W13
122VUANTI ICE/WHC/15DG1X13
122VUANTI ICE/PROBES/PHC/32DA3Y16
122VUANTI ICE/PROBES/PHC/22DA2Y12
Subtask 71-00-20-865-052-A ** ON A/C NOT FOR ALL
M. Remove the safety clips and tags and close these circuit breakers in this sequence:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
122VUANTI ICE/PROBES/1/TAT1DA1Z12
122VUANTI ICE/PROBES/2/TAT1DA2Y15
49VUANTI ICE/PROBES/PITOT/13DA1D02
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
49VUANTI ICE/PROBES/AOA/14DA1D04
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
49VUANTI ICE/RAIN/RPLNT/CAPT1DB1D01
122VUANTI ICE/RAIN/RPLNT/F/O1DB2W11
123VUANTI ICE/L/WHSLD1DG1AF10
123VUANTI ICE/R/WHSLD1DG2AF03
122VUANTI ICE/WINDOWS/L4DG1X14
122VUANTI ICE/WINDOWS/R4DG2W14
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A1WE1Q43
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B2WE1Q44
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A1WE2Q41
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B2WE2Q42
121VURCDR/DFDR7TUK16
49VUCOM/CVR/SPLY23RKE14
49VUCOM/CVR/CTL26RKE13
FOR FIN: 1000EM1 (ENGINE1)
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R41
121VUENGINE/IGN/ENG1/SYS B3JH1P41
121VUENGINE/IGN/ENG1/SYS A BAT2JH1P39
49VUENGINE/1/FIRE DET/LOOP A7WD1A06
121VUENGINE/ENG1/FIRE DET/LOOP B8WD1Q38
122VUELEC/GCU/12XU1T26
122VUANTI ICE/ENG/11DN1X10
49VUFUEL/LP VALVE/MOT1/ENG11QGA08
121VUFUEL/LP VALVE/MOT2/ENG13QGM25
FOR FIN: 1000EM2 (ENGINE2)
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
121VUENGINE/ENG2/FADEC B4KS2Q40
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
121VUENGINE/ENG2/FIRE DET/LOOP A7WD2Q39
49VUENGINE/2/FIRE DET/LOOP B8WD2A07
122VUELEC/GCU/22XU2T27
122VUANTI ICE/ENG/21DN2W10
123VUY HYD/ELEC/ELEC PUMP/NORM3801GXAB03
123VUY HYD/ELEC/PUMP3802GXAB06
121VUHYDRAULIC/HYD POWER/Y3803GXN30
49VUFUEL/LP VALVE/MOT1/ENG22QGA09
121VUFUEL/LP VALVE/MOT2/ENG24QGM26
FOR FIN: 1000EM1 (ENGINE1)
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
Subtask 71-00-20-861-050-A ** ON A/C NOT FOR ALL
N. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
Subtask 71-00-20-740-057-A ** ON A/C NOT FOR ALL
O. Update the engine hours and cycles (Ref. AMM TASK 31-36-00-740-005).
NOTE: Some tasks will possibly not be applicable depending on whether a Data Management Unit (DMU) or a Flight Data Interface and Management Unit (FDIMU) is installed on the aircraft.
Subtask 71-00-20-860-050-A ** ON A/C NOT FOR ALL
P. Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001).
Subtask 71-00-20-720-050-B ** ON A/C NOT FOR ALL
Q. On the MCDU do the following Test:
   (1) Push the line key adjacent to the ENG indication. The SYSTEM REPORT/TEST ENG menu comes into view.
   (2) Push the line key adjacent to the FADEC 1(2) A(B) indication. The ENGINE 1(2) MAIN MENU page comes into view.
   (3) Push the line key adjacent to the TROUBLE SHOOTING indication. The FADEC 1(2) A(B) TROUBLE SHOOTING MENU page comes into view.
   (4) Push the line key adjacent to the EEC CONFIGURATION indication. The FADEC 1(2) EEC CONFIGURATION page comes into view.
   (5) Read the data that come on the MCDU (EEC P/N, ENGINE RATING, BUMP LEVEL, EPR MODIFIER and ENGINE SERIAL NUMBER) to make sure they are the same as written on the EEC, data entry plug and engine identification plate using the following engine ratings comparison table.
MCDU (EEC CONFIG Menu)
ENGINE DATA PLATE (Engine Model)
22000 lbs
V2522
24000 lbs
V2524
24000E lbs
V2524E
27000 lbs
V2527
27000E lbs
V2527E
27000M lbs
V2527M
30000 lbs
V2530
30000 lbs
V2530
33000 lbs
V2533
   (6) On the MCDU, push the line select key adjacent to the RETURN indication until the CFDS menu page comes into view.
   (7) Stop the MCDU.
Subtask 71-00-20-710-051-A ** ON A/C NOT FOR ALL
R. Do an operational test of the EEC (Ref. AMM TASK 73-22-34-710-040).
NOTE: If the aircraft operates in correct CAT III conditions, do a land test (Ref. AMM TASK 22-97-00-710-001).
Subtask 71-00-20-710-061-B ** ON A/C NOT FOR ALL
S. Do the operational test of the Starter valve and FMU (Ref. AMM TASK 80-13-51-710-040).
Subtask 71-00-20-710-050-A ** ON A/C NOT FOR ALL
T. Do these Tests
   (1) Do a functional test of the IDG disconnect system (Ref. AMM TASK 24-21-00-710-042).
   (2) Do an operational test of the anti-ice protection system of the engine air intake (Ref. AMM TASK 30-21-00-710-002).
   (3) Do the Hydraulic Maintenance Procedure after an engine installation:
     (a) FOR [1000EM1] (ENGINE-1)
     (b) FOR [1000EM2] (ENGINE-2)
Subtask 71-00-20-790-050-B ** ON A/C NOT FOR ALL
U. Do these Leak Checks
   (1) Do a wet motor leak check (Ref. AMM TASK 71-00-00-710-046).
   (2) Do a leak check of the fuel return valve (Ref. AMM TASK 73-13-42-720-010) to make sure that there are no leaks at pylon connection.
   (3) Do leak test of the inlet-cowl anti-ice supply-ducts with the engine in operation (Ref. AMM TASK 30-21-49-790-010).
   (4) Do a minimum idle leak check and do a check for leaks (Ref. AMM TASK 71-00-00-710-012).
   (5) Do an Electronic Engine Control (EEC) system idle test (Ref. AMM TASK 71-00-00-710-022).
Subtask 71-00-20-210-053-B ** ON A/C NOT FOR ALL
V. Make sure that the IDG is connected:
   (1) If the IDG is not connected, make sure that the maintenance message "IDG1(2) (E1(2)-4000XU) RECONFIG" is shown on the EPGS GROUND REPORT page.
     (a) Make sure that the related GCU is energized.
     (b) Reset the GCU:
       1 On the ELEC control panel 35VU, release (OFF) then push the related ELEC/GEN pushbutton switch 3XU.
     (c) On the ELEC page of the lower ECAM DU, make sure that the line connection between the IDG1(2) and the related busbar is shown green. Make sure that the frequency and voltage indications are correct.
   (2) If the IDG1(2) is not connected after the GCU reset, do a check for other maintenance messages related to the IDG.
Subtask 71-00-20-720-055-A ** ON A/C NOT FOR ALL
W. Do this Test
   (1) Do a pretested replacement engine test (Ref. AMM TASK 71-00-00-700-011).
   (2) Do not stop the engine at this step.
Subtask 71-00-20-710-052-A ** ON A/C NOT FOR ALL
X. While the Engine is Running Do this Test
   (1) On the lower ECAM DU, get the BLEED page.
   (2) On the panel 30VU:
Push the ENG 1 (2) BLEED pushbutton switch
  • on the ENG 1 (2) pushbutton switch, the OFF legend goes off.
  • on the lower ECAM DU, the PRV and HP valves are shown open.
  • Monitor the nacelle temperature for unsatisfactory indication. If the temperature increases incorrectly, do the inspection of the bleed air duct connections.
   (3) On the panel 30VU:
Release the ENG 1(2) BLEED pushbutton switch
  • on the ENG 1(2) pushbutton switch the OFF legend comes on.
  • on the lower ECAM DU, the PRV and HP valves are shown closed.
Subtask 71-00-20-860-051-A ** ON A/C NOT FOR ALL
Y. Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
Subtask 71-00-20-862-050-A ** ON A/C NOT FOR ALL
Z. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
Subtask 71-00-20-869-058-A ** ON A/C NOT FOR ALL
AA. Installation of the two engines.
   (1) If the two engines were installed simultaneously refer to (Ref. AMM D/O 05-59-00-00) for specific recommendations.
[Rev.10 from 2021] 2026.04.01 02:28:29 UTC
"Aviabrain" 2025