Installation of the Power Plant with the Engine Positioner TWW 75E (MIAG) [IAE]

TASK 71-00-20-400-040-A-01
Installation of the Power Plant with the Engine Positioner TWW 75E (MIAG)

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: 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.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

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	HAMMER - FIBER
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 )
No specific	Torque wrench: range to between 8 and 6 lbf.in (0.09 and 0.07 m.daN )
No specific	Torque wrench: range to between 36 and 24 lbf.in (0.41 and 0.27 m.daN )
No specific	Torque wrench: range to between 40 and 35 lbf.in (0.45 and 0.40 m.daN )
No specific	Torque wrench: range to between 105 and 85 lbf.in (1.19 and 0.96 m.daN )
No specific	Torque wrench: range to between 110 and 90 lbf.in (1.24 and 1.02 m.daN )
No specific	Torque wrench: range to between 245 and 215 lbf.in (2.77 and 2.43 m.daN )
No specific	Torque wrench: range to between 0.42 and 0.38 m.daN (37.17 and 33.63 lbf.in )
No specific	Torque wrench: range to between 0.62 and 0.51 m.daN (54.87 and 45.13 lbf.in )
No specific	Torque wrench: range to between 0.8 and 0.6 m.daN (70.80 and 53.10 lbf.in )
No specific	Torque wrench: range to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in )
No specific	Torque wrench: range to between 0.96 and 0.85 m.daN (84.96 and 75.22 lbf.in )
No specific	Torque wrench: range to between 1.2 and 1 m.daN (106.19 and 88.50 lbf.in )
No specific	Torque wrench: range to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft )
No specific	Torque wrench: range to between 2.3 and 2.0 m.daN (16.96 and 14.75 lbf.ft )
No specific	Torque wrench: range to between 10.7 and 9.7 m.daN (78.91 and 71.53 lbf.ft )
No specific	Torque wrench: range to between 47.45 and 43.38 m.daN (349.93 and 319.91 lbf.ft )
No specific	Torque wrench: range to between 70.5 and 65 m.daN (519.91 and 479.35 lbf.ft )
98D71203001000	1	CHEST,TORQUE SET-ENGINE R I
TWW75E	1	ENGINE POSITIONER

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.V01-457)	solvent
(Material No.V02-126)	lockwire
(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.V02-282)	safety cable kit
(Material No.V02-283)	safety cable kit
(Material No.V02-283A)	safety cable kit
(Material No.V02-284)	safety cable kit
(Material No.V02-285)	safety cable kit
(Material No.V02-286)	safety cable kit
(Material No.V02-287)	safety cable kit
(Material No.V02-288)	safety cable kit
(Material No.V02-289)	safety cable ferrule
(Material No.V02-290)	safety cable ferrule
(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
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	SEAL ASSEMBLY	AIPC 78-32-49-83-140
14	RIVET	AIPC 78-32-79-81-090
13	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 29-10-00-863-001-A	Pressurize the Green Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-002-A	Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-14-00-614-002-A	Pressurization of the Hydraulic Reservoirs through the Ground Connector
TASK 29-14-00-614-002-A-01	Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU)
TASK 29-14-49-400-001-A	Installation of the Reservoir Pressurization Hose
TASK 29-23-00-863-001-A	Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump
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 71-00-00-710-045-A	Test No.1 : Dry Motor Leak Check
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
Engine Identification Plate
Table 1 - New Data Entry Plug PN 2A4378 Variants
Table 2 - New Data Entry Plug PN 2A4378 Variants
Data Entry Plug Back Shell Inscription
Forward Engine Mount
Aft Engine Mount
Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire Seals
Fire Seal Installation
Fan Cowl and Thrust Reverser Braces
TAI Location and Hydraulic Reservoir Pressurization Tube Location
Power Plant, Left Side
Left Connectors Location
Power Plant, Right Side
Forward Junction Box
Upper/Lower Link Starter Duct and Link Assembly
Forward Junction Box
IDG Cable Assembly
Left Interface Junction Box
Inspection of the Thrust Reverser Brackets and Inspection of the Engine Fire Seals
Hydraulic Control Unit
FOR [1000EM1] (ENGINE-1)
TASK 29-11-00-710-001-A	Operational Test of the Green Hydraulic System
FOR [1000EM2] (ENGINE-2)
TASK 29-13-00-710-002-A	Operational Test of the Yellow Hydraulic System

3. Job Set-up
Subtask 71-00-20-860-059-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:

The engine identification plate and tables 1 and 2.
Engine Identification Plate ** ON A/C NOT FOR ALL
Table 1 - New Data Entry Plug PN 2A4378 Variants ** ON A/C NOT FOR ALL
Table 2 - New Data Entry Plug PN 2A4378 Variants ** ON A/C NOT FOR ALL
The data entry plug back shell inscription
Data Entry Plug Back Shell Inscription ** ON A/C NOT FOR ALL
The data entry plug pin-out configuration (given in SB V2500-ENG-72-0285).

(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 71-00-20-010-061-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 71-00-20-040-055-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 71-00-20-865-058-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:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03
49VU	ANTI ICE/PROBES/AOA/1	4DA1	D04
49VU	ANTI ICE/PROBES/PITOT/1	3DA1	D02
49VU	ANTI ICE/RAIN/RPLNT/CAPT	1DB1	D01
49VU	COM/CVR/SPLY	23RK	E14
49VU	COM/CVR/CTL	26RK	E13
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B	2WE1	Q44
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A	1WE1	Q43
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B	2WE2	Q42
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A	1WE2	Q41
122VU	ANTI ICE/WINDOWS/R	4DG2	W14
122VU	ANTI ICE/RAIN/RPLNT/F/O	1DB2	W11
122VU	ANTI ICE/WINDOWS/L	4DG1	X14
122VU	ANTI ICE/PROBES/2/TAT	1DA2	Y15
122VU	ANTI ICE/PROBES/2/PITOT	3DA2	Y14
122VU	ANTI ICE/PROBES/2/AOA	4DA2	Y13
122VU	ANTI ICE/PROBES/2/STATIC	5DA2	Y11
122VU	ANTI ICE/PROBES/3/PITOT	3DA3	Z16
122VU	ANTI ICE/PROBES/3/AOA	4DA3	Z15
122VU	ANTI ICE/PROBES/3/STATIC	5DA3	Z14
122VU	ANTI ICE/PROBES/1/STATIC	5DA1	Z13
122VU	ANTI ICE/PROBES/1/TAT	1DA1	Z12
123VU	ANTI ICE/L/WHSLD	1DG1	AF10
123VU	ANTI ICE/R/WHSLD	1DG2	AF03
FOR FIN: 1000EM1 (ENGINE1)
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08
49VU	ENGINE/1/FIRE DET/LOOP A	7WD1	A06
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
121VU	RCDR/DFDR	7TU	K16
121VU	FUEL/LP VALVE/MOT2/ENG1	3QG	M25
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
121VU	ENGINE/IGN/ENG1/SYS A BAT	2JH1	P39
121VU	ENGINE/ENG1/FIRE DET/LOOP B	8WD1	Q38
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R41
122VU	ELEC/GCU/1	2XU1	T26
122VU	ANTI ICE/ENG/1	1DN1	X10
FOR FIN: 1000EM2 (ENGINE2)
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
49VU	ENGINE/2/FIRE DET/LOOP B	8WD2	A07
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
121VU	FUEL/LP VALVE/MOT2/ENG2	4QG	M26
121VU	HYDRAULIC/HYD POWER/Y	3803GX	N30
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42
121VU	ENGINE/IGN/ENG2/SYS A BAT	2JH2	P40
121VU	ENGINE/ENG2/FADEC B	4KS2	Q40
121VU	ENGINE/ENG2/FIRE DET/LOOP A	7WD2	Q39
122VU	ELEC/GCU/2	2XU2	T27
122VU	ANTI ICE/ENG/2	1DN2	W10
123VU	Y HYD/ELEC/PUMP	3802GX	AB06
123VU	Y HYD/ELEC/ELEC PUMP/NORM	3801GX	AB03

Subtask 71-00-20-210-061-A ** ON A/C NOT FOR ALL

E. 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 71-00-20-110-055-A ** ON A/C NOT FOR ALL

F. Cleaning of the Components
(1) Clean these 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).

Forward Engine Mount ** ON A/C NOT FOR ALL

Aft Engine Mount ** ON A/C NOT FOR ALL

(3) Make sure that there are no signs of seizure or wear.

Subtask 71-00-20-230-052-A ** ON A/C NOT FOR ALL

G. 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.

Forward Engine Mount ** ON A/C NOT FOR ALL

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 71-00-20-240-052-A ** ON A/C NOT FOR ALL

H. 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.

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 71-00-20-420-090-A ** ON A/C NOT FOR ALL

I. If replacement engine does not have all its equipment, remove the accessories from the removed engine and install them on the replacement engine.

Subtask 71-00-20-410-075-A ** ON A/C NOT FOR ALL

J. If the engine fire seals (Post SBE 72-0230) are not present, install them as follows:

Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire Seals ** ON A/C NOT FOR ALL

Fire Seal Installation ** ON A/C NOT FOR ALL

(1) Close the relevant thrust reverser half (Ref. AMM TASK 78-32-00-410-010):
(2) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(3) FOR [1000EM2] (ENGINE-2)
461AL 462AR
(4) Put the fire seal assembly (15) or (16) on the heatshield so there is full contact between the seal and the thrust reverser bracket assembly. The fire seal should rest against the bracket with no compression.
(5) Mark the forward and bottom outline of the fire seal on the heatshield with a PENCIL.
(6) Open the relevant thrust reverser half (Ref. AMM TASK 78-32-00-010-010):
(7) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(8) FOR [1000EM2] (ENGINE-2)
461AL 462AR
(9) Install the fire seals as follows:
(a) Install the fire seal assembly (15) and (16) on the fire shield with screws (17).
(b) TORQUE the screws (17) to between 8 and 6 lbf.in (0.09 and 0.07 m.daN )

.
(10) Use sealant:
(a) Fill all the voids in the fire seal with sealant (Material No.V08-030) . Allow the sealant to cure for 24 hours at 77 deg. F (25 deg.C) and 50 percent humidity.

4. Procedure
Subtask 71-00-20-420-091-A ** ON A/C NOT FOR ALL

A. Installation of the Engine Positioner TWW 75E
(1) Use the right joystick to install the TWW75E ENGINE POSITIONER, the engine cradle and the replacement engine under the pylon.
(2) Make sure, as per the load page, that the correct values are preset for forward and aft preset loads and preloads.
(3) Use the left joystick to lift the engine positioner and make the necessary movements to mate the engine mounts. Make sure that clearance is correct between the aft edge of the fan case and the leading edge of the reversers.
(4) Monitor the engine when you put it in position.

CAUTION: MAKE SURE THAT THE BLADES OF THE THRUST REVERSER R1 HINGE FITTING ARE IN THE CORRECT POSITION IN THE V-GROOVE OF THE ADAPTOR RING ASSEMBLY.

(a) When the distance between the engine mounts and the pylon mounts is 10 mm (0.3937 in.) approximately, slowly lift the engine. Engage the front and rear locating pins at the same time.
(b) Continue to lift the engine slowly.

NOTE: Make sure that the engine mounts touch the pylon mounts.

(c) Lift the engine cradle gradually until the forward and aft mating loads are 300 daN. Then install the mount bolts as follows.

Subtask 71-00-20-210-075-A ** ON A/C NOT FOR ALL

B. 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:

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:

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 71-00-20-420-093-A ** ON A/C NOT FOR ALL

C. Installation of the Forward and Aft Engine Mounts
(1) Install the forward engine mount (4):

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 )

.
(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 )

.
(i) Remove the padding installed between the engine and the forward engine mount (4).
(2) Install the aft engine mount (4):

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 )

(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 lockwire (Material No.V02-147) (Ref. AMM TASK 70-40-11-911-014).
Alternate: Use the safety cable (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) 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 71-00-20-080-052-A ** ON A/C NOT FOR ALL

D. Removal of the Engine Cradle and Engine Positioner TWW 75E

CAUTION: BE CAREFUL WHEN YOU INSTALL THE CRADLE ON, OR REMOVE IT FROM, THE ENGINE. IF NOT, YOU CAN CAUSE DAMAGE TO THE VIBRATION SENSOR CONNECTOR. THE VIBRATION SENSOR CONNECTOR IS IN FRONT OF THE FORWARD HANDLING POINT ON THE RIGHT SIDE.

(1) Disconnect the engine cradle from the engine.
(2) Use the left joystick to lower the engine positioner.
(3) Remove the engine cradle onto the rail system of the engine positioner.

Subtask 71-00-20-760-051-A ** ON A/C NOT FOR ALL

E. 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 71-00-20-420-094-A ** ON A/C NOT FOR ALL

F. 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 43.38 m.daN (349.93 and 319.91 lbf.ft )

(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 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 forward engine mount bolts (1) again to make sure 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) Safety the bolt (1) with lockwire (Material No.V02-147) (Ref. AMM TASK 70-40-11-911-014).
Alternate: Use safety cable (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) or safety cable (Material No.V02-281) (Ref. AMM TASK 70-40-11-911-016).

NOTE: You can use lockwire diameters ranging from 0.8mm to 1.2mm 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 )

(Ref. AMM TASK 70-23-11-911-013).
(5) Remove the fan cowl and thrust reverser braces

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 71-00-20-020-082-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 71-00-20-630-051-A ** ON A/C NOT FOR ALL

B. Remove caps from the open ends.

Subtask 71-00-20-420-097-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 71-00-20-420-095-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.

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 )

.
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 )

(Ref. AMM TASK 70-23-11-911-013).
(b) Connect the fuel tubes on the fluid disconnect panel.

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 )

(Ref. AMM TASK 70-23-11-911-013).

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 )

(Ref. AMM TASK 70-23-11-911-013).

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 )

(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 )

(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.

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 )

.
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 )

.
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 )

.
(e) Connect the Thermal Anti-Ice (TAI) duct.

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.

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).

Left Connectors Location ** ON A/C NOT FOR ALL

(2) Install these components from the right side of the engine.

Power Plant, Right Side ** ON A/C NOT FOR ALL

(a) Connect the starter duct (4).

Forward Junction Box ** ON A/C NOT FOR ALL

Upper/Lower Link Starter Duct and Link Assembly ** ON A/C NOT FOR ALL

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).

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).
4 TORQUE the coupling (3) to between 0.62 and 0.51 m.daN (54.87 and 45.13 lbf.in )

.
5 Install the coupling (3).
a To do this, tap the coupling (3) with the MALLET - PLASTIC.
6 TORQUE the coupling (3) again to between 0.62 and 0.51 m.daN (54.87 and 45.13 lbf.in )

.
7 Tap the coupling (3) again.
8 TORQUE the coupling (3) again to between 0.62 and 0.51 m.daN (54.87 and 45.13 lbf.in )

.
(c) Connect the starter duct (4).

Forward Junction Box ** ON A/C NOT FOR ALL

1 Adjust the link assemblies when the engine is installed on the pylon.
2 Remove the four nuts (7), washers (9) and bolts (8) from the two upper link assemblies (16) and (17).
a Remove the upper link assemblies (16) and (17).
3 Remove the four nuts (7), washers (9) and bolts (8) from the lower link assemblies (11) and (12).
a Remove the lower link assemblies (11) and (12).
b It may be necessary to loosen the coupling at the valve. If this is required, torque the coupling nut as in steps 5.D.(2)(c)5_ thru 5.D.(2)(c)7_.
4 Put the starter duct (4) in position on the pylon starter duct (6) and install the coupling (5).
5 TORQUE the coupling (5) to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in )

.
6 Lightly hit around the outside of the coupling with the HAMMER - FIBER.
7 TORQUE the coupling (5) again to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in )

.
8 Repeat steps 5.D.(2)(c)5_ thru 5.D.(2)(c)7_ two more times.
9 Connect the lower link assemblies (11) and (12) on the fan case brackets with the bolts (8), washers (9) and nuts (7). Do not torque the nuts (7) at this time.
10 Connect the upper link assemblies (16) and (17) on the fan case brackets with the bolts (8), washers (9) and nuts (7). Do not torque the nuts (7) at this time.
11 Loosen the nut (13) on the support links (11), (12), (16) and (17).
12 Adjust the links sufficiently to attach to the starter duct (4) without preload.
13 Install the four link assemblies (11), (12), (16) and (17) on the starter duct (4) with the bolts (8), washers (9) and nuts (7).
14 TORQUE the eight nuts (7) to between 0.8 and 0.6 m.daN (70.80 and 53.10 lbf.in )

.
15 TORQUE the four nuts (13) on the link assemblies (11), (12), (16) and (17) to between 1.2 and 1 m.daN (106.19 and 88.50 lbf.in )

16 Make sure that the link threads fill the safety holes in the link assemblies.
Do a check with a piece of lockwire (Material No.V02-126) .
Alternative : Use the safety cable kit (Material No.V02-282) , safety cable kit (Material No.V02-283) , safety cable kit (Material No.V02-283A) , safety cable kit (Material No.V02-284) , safety cable kit (Material No.V02-285) , safety cable kit (Material No.V02-286) , safety cable kit (Material No.V02-287) , safety cable kit (Material No.V02-288) , safety cable ferrule (Material No.V02-289) or safety cable ferrule (Material No.V02-290) .
Put the lockwire or safety cable into each safety hole.
a Make sure that the lockwire or safety cable does not go through the hole.
17 Adjust the starter duct (4) (Ref. AMM TASK 80-13-49-820-010).
(d) On the fan case near the V-groove at the 1 o'clock position, connect electrical connector 4005VC.

Power Plant, Right Side ** ON A/C NOT FOR ALL

(e) 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).

Forward Junction Box ** ON A/C NOT FOR ALL

(f) On the pylon junction box, connect electrical connectors 401VC, 403VC, 407VC and 409VC (Ref. AMM TASK 70-23-15-912-010).

Forward Junction Box ** ON A/C NOT FOR ALL

(g) Do a check of the bend on the IDG cable assembly.

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 )

(Ref. AMM TASK 70-23-11-911-013).
(h) 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 a 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.

Forward Junction Box ** ON A/C NOT FOR ALL

4 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).
(i) On the aft interface junction-box, connect electrical connectors 450VC-A, 452VC-A and 454VC.

Left Interface Junction Box ** ON A/C NOT FOR ALL

(j) 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).

TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL

(k) Install the drain mast (Ref. AMM TASK 71-71-42-400-010).

Subtask 71-00-20-410-076-A ** ON A/C NOT FOR ALL

E. If the engine fire seals (Pre SBE 72-0230) are not present, install them as follows:

Inspection of the Thrust Reverser Brackets and Inspection of the Engine Fire Seals ** ON A/C NOT FOR ALL

(1) Close the relevant thrust reverser half (Ref. AMM TASK 78-32-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
(2) Put the fire AIPC 78-32-49-83-140 SEAL ASSEMBLY (12) or AIPC 78-32-79-81-100 SEAL ASSEMBLY (13) on the heatshield so there is full contact between the seal and the thrust reverser bracket assembly. The fire seal should rest against the bracket with no compression.
(3) Mark the forward and bottom outline of the fire seal on the heatshield with a PENCIL.
(4) Open the relevant thrust reverser half (Ref. AMM TASK 78-32-00-010-010):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
(5) Measure 0.125 in. (3.18 mm) aft of the fire seal forward outline and make a parallel line on the heatshield with a PENCIL.
(6) Align the fire seal with the aft outline and bottom outline on the heatshield.
(7) Put a PLATE - STEEL, 500X500X3 MM (19.68X19.68X0.12 IN) between the strut fairing and the heatshield before you drill the holes to protect the strut fairing.
(8) Drill through the three fire seal pilot holes into the heatshield. Enlarge the holes with a DRILL - NO 21 (DIA 0.159 IN - 4.039 MM).
(9) Remove the burrs from the holes in the fire seal and the heatshield.
(10) Cleaning
(a) Clean the fire seal and the aft and inboard surfaces of the heatshield and block seal with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with solvent (Material No.V01-457) . Wipe the surfaces dry before the cleaning solvent evaporates.
(11) Applying of primer
(a) Apply primer (Material No.V08-032) to the mating surfaces of the fire seal assembly. Allow to air dry for twenty minutes.
(12) Apply release agent (Material No.V02-158A) to the aft surface and inboard corner of the block seal.
(13) Applying of sealant
(a) Apply sealant (Material No.V08-030) to the mating surfaces of the fire seal.
(14) Put the fire seal into position on the heatshield.
(15) Installation of 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 a AIPC 78-32-49-83-130 RIVET (14) or AIPC 78-32-79-81-090 RIVET (14) in the center hole.
(b) Install rivets (14) in the upper and lower holes.
(16) Using of sealant
(a) Fill all the voids in the fire seal with sealant (Material No.V08-030) . Allow the sealant to cure for 24 hours at 77 deg. F (25 deg.C) and 50 percent humidity.

Subtask 71-00-20-820-055-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 71-00-20-410-064-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):
(3) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(4) FOR [1000EM2] (ENGINE-2)
461AL 462AR

Subtask 71-00-20-440-053-A ** ON A/C NOT FOR ALL

H. Activate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-440-012).

Hydraulic Control Unit ** ON A/C NOT FOR ALL

Subtask 71-00-20-611-054-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 71-00-20-612-051-A ** ON A/C NOT FOR ALL

J. Service the Starter with Oil (Ref. AMM TASK 12-13-80-600-010) or (Ref. AMM TASK 12-13-80-600-010)

NOTE: The starter may have been drained when the engine was removed.

Subtask 71-00-20-863-054-A ** ON A/C NOT FOR ALL

K. Pressurize these Hydraulic Systems

WARNING: PRESSURIZATION OF THE HYDRAULIC SYSTEM CAN RESULT IN INADVERTENT THRUST REVERSER OPERATION. REMOVE ALL PERSONNEL FROM THE AREA AROUND THE THRUST REVERSER BEFORE THE HYDRAULIC SYSTEM IS PRESSURIZED. FAILURE TO COMPLY CAN RESULT IN INJURY TO PERSONNEL.

(1) Pressurize the applicable hydraulic system (Ref. AMM TASK 29-10-00-863-001) or (Ref. AMM TASK 29-10-00-863-002) or (Ref. AMM TASK 29-23-00-863-001).
(2) Pressurize the hydraulic reservoirs (Ref. AMM TASK 29-14-00-614-002).

Subtask 71-00-20-410-065-A ** ON A/C NOT FOR ALL

L. Close Access
(1) Close the fan cowl (Ref. AMM TASK 71-13-00-410-010):
(2) FOR [1000EM1] (ENGINE-1)
437AL, 438AR
(3) FOR [1000EM2] (ENGINE-2)
447AL, 448AR
(4) Remove the access platform(s).
(5) On the center pedestal, on the ENG panel 115VU:
(a) Remove the WARNING NOTICE(S).
(6) On the overhead maintenance panel 50VU:
(a) Remove the WARNING NOTICE(S).
(7) On the panel 30VU:
(a) Remove the WARNING NOTICE(S) from the APU BLEED pushbutton switch.
(8) Remove the WARNING NOTICE(S) on the HP ground connector.

Subtask 71-00-20-865-073-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.

M. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	ANTI ICE/PROBES/PHC/1	2DA1	D03
122VU	ANTI ICE/WHC/2	5DG2	W13
122VU	ANTI ICE/WHC/1	5DG1	X13
122VU	ANTI ICE/PROBES/PHC/3	2DA3	Y16
122VU	ANTI ICE/PROBES/PHC/2	2DA2	Y12

Subtask 71-00-20-865-059-A ** ON A/C NOT FOR ALL

N. Remove the safety clips and tags and close these circuit breakers in this sequence:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
122VU	ANTI ICE/PROBES/1/TAT	1DA1	Z12
122VU	ANTI ICE/PROBES/2/TAT	1DA2	Y15
49VU	ANTI ICE/PROBES/PITOT/1	3DA1	D02
122VU	ANTI ICE/PROBES/2/PITOT	3DA2	Y14
122VU	ANTI ICE/PROBES/3/PITOT	3DA3	Z16
49VU	ANTI ICE/PROBES/AOA/1	4DA1	D04
122VU	ANTI ICE/PROBES/2/AOA	4DA2	Y13
122VU	ANTI ICE/PROBES/3/AOA	4DA3	Z15
122VU	ANTI ICE/PROBES/1/STATIC	5DA1	Z13
122VU	ANTI ICE/PROBES/2/STATIC	5DA2	Y11
122VU	ANTI ICE/PROBES/3/STATIC	5DA3	Z14
49VU	ANTI ICE/RAIN/RPLNT/CAPT	1DB1	D01
122VU	ANTI ICE/RAIN/RPLNT/F/O	1DB2	W11
123VU	ANTI ICE/L/WHSLD	1DG1	AF10
123VU	ANTI ICE/R/WHSLD	1DG2	AF03
122VU	ANTI ICE/WINDOWS/L	4DG1	X14
122VU	ANTI ICE/WINDOWS/R	4DG2	W14
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A	1WE1	Q43
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B	2WE1	Q44
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A	1WE2	Q41
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B	2WE2	Q42
121VU	RCDR/DFDR	7TU	K16
49VU	COM/CVR/SPLY	23RK	E14
49VU	COM/CVR/CTL	26RK	E13
FOR FIN: 1000EM1 (ENGINE1)
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R41
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
121VU	ENGINE/IGN/ENG1/SYS A BAT	2JH1	P39
49VU	ENGINE/1/FIRE DET/LOOP A	7WD1	A06
121VU	ENGINE/ENG1/FIRE DET/LOOP B	8WD1	Q38
122VU	ELEC/GCU/1	2XU1	T26
122VU	ANTI ICE/ENG/1	1DN1	X10
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08
121VU	FUEL/LP VALVE/MOT2/ENG1	3QG	M25
FOR FIN: 1000EM2 (ENGINE2)
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
121VU	ENGINE/ENG2/FADEC B	4KS2	Q40
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42
121VU	ENGINE/IGN/ENG2/SYS A BAT	2JH2	P40
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03
121VU	ENGINE/ENG2/FIRE DET/LOOP A	7WD2	Q39
49VU	ENGINE/2/FIRE DET/LOOP B	8WD2	A07
122VU	ELEC/GCU/2	2XU2	T27
122VU	ANTI ICE/ENG/2	1DN2	W10
123VU	Y HYD/ELEC/ELEC PUMP/NORM	3801GX	AB03
123VU	Y HYD/ELEC/PUMP	3802GX	AB06
121VU	HYDRAULIC/HYD POWER/Y	3803GX	N30
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
121VU	FUEL/LP VALVE/MOT2/ENG2	4QG	M26
FOR FIN: 1000EM1 (ENGINE1)
49VU	ENGINE/1 AND 2/IGN/SYS A	1JH	A03

Subtask 71-00-20-861-053-A ** ON A/C NOT FOR ALL

O. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).

Subtask 71-00-20-740-059-A ** ON A/C NOT FOR ALL

P. 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 71-00-20-860-060-A ** ON A/C NOT FOR ALL

Q. Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001).

Subtask 71-00-20-720-053-B ** ON A/C NOT FOR ALL

R. 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 71-00-20-710-064-A ** ON A/C NOT FOR ALL

S. 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, a land test (Ref. AMM TASK 22-97-00-710-001).

Subtask 71-00-20-710-065-B ** ON A/C NOT FOR ALL

T. Do the operational test of the Starter valve and FMU (Ref. AMM TASK 80-13-51-710-040).

Subtask 71-00-20-710-066-A ** ON A/C NOT FOR ALL

U. Do these Tests
(1) Do a functional test of the IDG disconnect system (Ref. AMM TASK 24-21-00-710-042).
(2) Do a dry motor leak check (Ref. AMM TASK 71-00-00-710-045) and do an operational test of the hydraulic pump:
(3) FOR [1000EM1] (ENGINE-1)

operational test of the Green hydraulic system (Ref. AMM TASK 29-11-00-710-001).

(4) FOR [1000EM2] (ENGINE-2)

operational test of the Yellow hydraulic system (Ref. AMM TASK 29-13-00-710-002).

Subtask 71-00-20-790-051-B ** ON A/C NOT FOR ALL

V. 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).
(6) Do an operational test of the anti-ice protection system of the engine air intake (Ref. AMM TASK 30-21-00-710-002).

Subtask 71-00-20-210-064-B ** ON A/C NOT FOR ALL

W. 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 71-00-20-720-054-A ** ON A/C NOT FOR ALL

X. 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 71-00-20-710-067-A ** ON A/C NOT FOR ALL

Y. 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 71-00-20-860-061-A ** ON A/C NOT FOR ALL

Z. Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).

Subtask 71-00-20-862-053-A ** ON A/C NOT FOR ALL

AA. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).

Subtask 71-00-20-869-059-A ** ON A/C NOT FOR ALL

AB. 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 02:28:31 UTC