Installation of the Power Plant (Bootstrap Method) [PW11]

TASK 71-00-51-400-802-A
Installation of the Power Plant (Bootstrap Method)

WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES. WORK ON THE HYDRAULIC SYSTEMS CAN BE DANGEROUS.

WARNING: DO NOT LET ENGINE FUEL STAY ON YOUR SKIN FOR A LONG TIME. FLUSH THE FUEL FROM YOUR SKIN WITH WATER. THE FUEL IS POISONOUS AND CAN GO THROUGH YOUR SKIN AND INTO YOUR BODY.

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

WARNING: BEFORE YOU INSTALL/REMOVE THE GSE TOOL, READ THE MANUFACTURER'S INSTRUCTIONS, AND, WHILE YOU OPERATE THIS TOOL, CAREFULLY OBEY THEM. IF YOU DO NOT DO THIS, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AND THE ADJACENT COMPONENTS AFTER ENGINE SHUTDOWN. THE ENGINE, THE ENGINE OIL AND THE ADJACENT COMPONENTS CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.

CAUTION: DO NOT LET ENGINE FUEL, OIL OR HYDRAULIC FLUID SPILL ON THE ENGINE. YOU MUST IMMEDIATELY REMOVE UNWANTED FUEL, OIL OR HYDRAULIC FLUID WITH A CLOTH. FUEL, OIL OR HYDRAULIC FLUID CAN CAUSE DAMAGE TO SOME ENGINE PARTS.

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.

ZONE: 210
ZONE: 400
FIN: 4020KM1 ** ON A/C NOT FOR ALL
FIN: 4020KM2 ** 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 2M (6 FT) - ADJUSTABLE
No specific	1	PLIERS - JAWED, SOFT
No specific	1	TIE WRAP(S)
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 1.0 and 0.9 m.N (8.85 and 7.96 lbf.in )
No specific	Torque wrench: range to between 2.4 and 2.2 m.N (21.24 and 19.47 lbf.in )
No specific	Torque wrench: range to between 17.8 and 13.8 m.N (13.13 and 10.18 lbf.ft )
No specific	Torque wrench: range to between 24.0 and 22.0 m.N (17.70 and 16.22 lbf.ft )
No specific	Torque wrench: range to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )
No specific	Torque wrench: range to between 0.79 and 0.62 m.daN (69.91 and 54.87 lbf.in )
No specific	Torque wrench: range to between 1.01 and 0.85 m.daN (89.38 and 75.22 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 2.49 and 2.03 m.daN (18.36 and 14.97 lbf.ft )
No specific	Torque wrench: range to between 2.82 and 2.37 m.daN (20.80 and 17.48 lbf.ft )
No specific	Torque wrench: range to between 2.77 and 2.43 m.daN (20.43 and 17.92 lbf.ft )
No specific	Torque wrench: range to between 3.91 and 3.58 m.daN (28.83 and 26.40 lbf.ft )
No specific	Torque wrench: range to between 4.75 and 3.84 m.daN (35.03 and 28.32 lbf.ft )
No specific	Torque wrench: range to between 6.69 and 5.57 m.daN (49.34 and 41.08 lbf.ft )
No specific	Torque wrench: range to between 11 and 9 m.daN (81.12 and 66.37 lbf.ft )
No specific	Torque wrench: range to between 15.7 and 14.7 m.daN (115.78 and 108.41 lbf.ft )
No specific	Torque wrench: range to between 22 and 18 m.daN (162.24 and 132.74 lbf.ft )
No specific	Torque wrench: range to between 27.6 and 22.4 m.daN (203.54 and 165.19 lbf.ft )
No specific	Torque wrench: range to between 57.2 and 46.8 m.daN (421.83 and 345.13 lbf.ft )
636-1000-27GSE	1	PYLON ECS INTERFACE DUCT SUPPORT
636-1000-32GSE	1	BLOCKING DEVICE - AFT ENGINE MOUNT PIN
636-3000-10GSE	1	TR HOLD OPEN STRUT TO PYLON
636-3000-13GSE	1	TR MANUAL HYDRAULIC OPENING SYSTEM
636-3000-26GSE	1	TR VAPOR BARRIER SEAL PROTECTOR
636GSE3009-901	1	TR HOLD OPEN STRUT
98D71203011000	1	BOOTSTRAP SYSTEM PW
98D71203013000	1	TORQUE WRENCH SET PW
ALT71000001	1	ELECTRICAL HOIST KIT
PWA211430	1	STAND, TRANSPORT

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.P05-005)	lint-free cotton cloth
(Material No.P05-289)	safety wire (lockwire) - steel, corrosion resistant
(Material No.PU1-0001)	cloth
(Material No.PU2-0001)	alcohol, isopropyl
(Material No.PU2-0002)	acetone
(Material No.PU5-0002)	anti-seize compound
(Material No.PU5-0005)	anti-seize compound
(Material No.PU5-0005A)	Royco 81 MS anti-seize compound
(Material No.PU5-0005B)	PT 605 anti-seize compound
(Material No.03BBB1)	Mineral base Lubricating Oil-General purpose Low Temp. -
(Material No.03QBC1)	Dry lubricant-General Assembly Molybdenum Disulfide & Silicone -
(Material No.08BCF1)	Non Aqueous Cleaner-Composite Structural Bonding -
(Material No.360200)	MOLYKOTE G-RAPID PLUS PASTE

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 [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
437AL, 438AR, 451AL, 452AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL, 448AR, 461AL, 462AR

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
22	PIN	AIPC 71-22-86-03-100
25	FACE SEAL	AIPC 73-11-86-02-030

E. Referenced Information

REFERENCE	DESIGNATION
TASK 05-57-00-200-001-A	Aircraft Stability
TASK 05-57-00-200-001-B	Aircraft Stability
TASK 10-20-00-556-001-A	Mooring of Aircraft without Weight and Balance Provision on the Landing Gear Legs
TASK 10-20-00-556-001-A-01	Mooring of Aircraft with Weight and Balance Provision on the Landing Gear Legs
TASK 12-13-24-612-803-A	Integrated Drive Generator (IDG) Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check
TASK 20-28-00-912-802-A	Electrical Bonding - General Maintenance Procedure
TASK 20-28-00-912-803-A	Bonding Surface Preparation
TASK 22-97-00-710-001-A	Operational Test of the LAND CAT III Capability
TASK 24-21-00-710-803-A	Operational Test of the IDG Disconnect and Reconnect Function - Engine Static
TASK 24-21-00-710-803-A-01	Operational Test of the IDG Disconnect and Reconnect Function - Engine in Operation
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 26-12-00-710-001-A	Operational Check of Loop/Squib
TASK 29-10-00-864-001-A	Depressurize the Green Hydraulic System
TASK 29-10-00-864-002-A	Depressurize the Yellow Hydraulic System
TASK 29-14-00-614-001-A	Depressurization of the Hydraulic Reservoirs
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 30-21-00-710-002-A	Operational Check of the Engine-Air-Intake Ice-Protection System (with the Engines in operation)
TASK 30-21-21-000-801-A	Removal of the Nacelle Anti-Ice Solenoid-Manifold
TASK 30-21-21-400-801-A	Installation of the Nacelle Anti-Ice Solenoid-Manifold
TASK 30-21-22-000-801-A	Removal of the Nacelle Anti-Ice Core-Pressure-Transducer
TASK 30-21-22-400-801-A	Installation of the Nacelle Anti-Ice Core-Pressure-Transducer
TASK 31-32-00-860-012-A	Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
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 36-11-49-000-824-A	Removal of the Environmental Control System (ECS) Interface Duct
TASK 36-11-49-400-824-A	Installation of the Environmental Control System (ECS) Interface Duct
TASK 36-11-53-000-802-A	Removal of the Overpressure Valve
TASK 36-11-53-400-802-A	Installation of the Overpressure Valve
TASK 54-57-22-000-805-A	Removal of the Aprons and the Profiles
TASK 54-57-22-000-810-A	Removal of the Rear Mount Fairing (RMF) Door
TASK 54-57-22-000-821-A	Removal of the Joint Plate and the Nose Fire Seal
TASK 54-57-22-400-805-A	Installation of the Aprons and the Profiles
TASK 54-57-22-400-810-A	Installation of the Rear Mount Fairing (RMF) Door
TASK 54-57-22-400-821-A	Installation of the Joint Plate and the Nose Fire Seal
TASK 71-00-00-720-813-A	Test No. 10 - System Maintenance (Post Engine Replacement Test)
TASK 71-00-00-860-832-A	Procedure to Prevent Engine Motoring and to Stop the Electrical Supply to the EEC
TASK 71-13-00-410-802-A	Closing of the Fan Cowl Doors
TASK 71-13-00-820-802-A	Adjustment of the Fan Cowl Doors
TASK 71-13-86-400-802-A	Installation of the Hold Open Rod (HOR) Bracket Bolts
TASK 71-21-41-210-802-A	Detailed Visual Inspection of the Forward Engine Mount Assembly
TASK 71-22-41-210-802-A	Detailed Visual Inspection of the Aft Engine Mount Assembly
TASK 72-21-04-000-801-A	Removal of the Fan Exit Fairing - Upper Bifi
TASK 72-21-04-400-801-A	Installation of the Fan Exit Fairing - Upper Bifi
TASK 73-25-34-400-802-A	Installation of the Engine Interface Unit (EIU)
TASK 78-30-00-440-805-A	Reactivation of the Thrust Reverser System after Ground Maintenance
TASK 78-30-00-820-803-A	Adjustment of the Thrust Reverser
TASK 78-30-06-000-801-A	Removal of the Thrust Reverser Hinge Access Panels
TASK 78-30-06-400-801-A	Installation of the Thrust Reverser Hinge Access Panels
TASK 78-31-00-710-805-A	Operational Test of Thrust Reverser with MCDU
TASK 78-31-00-710-805-A-01	Thrust Reverser Cycling Test (Engine Running)
TASK 78-31-06-820-801-A	Adjustment of the Inhibit Cable
TASK 78-36-00-410-802-A	Closing of the Thrust Reverser Cowl-Doors
TASK 78-36-04-400-801-A	Installation of the Thrust Reverser Hold Open Rods (HOR)
TASK 79-00-00-610-801-A	Check and Fill the Engine Oil
TASK 80-11-00-600-801-A	Fill the Starter with Oil
NTM 518000
NTM 545390
TASK 05-59-00-00	SPECIAL FLIGHTS - DESCRIPTION AND OPERATION
ECS Duct Support
Bootstrap Equipment with Electrical Hoist Kit
Thrust-Reverser Axial Locator and V-Blade
Ball Lock Pin
Power Plant Engine-Mounts
Power Plant Engine-Mounts
Positions of the Aft Mount Link
Power Plant (Engine Right-Side Locator)
Power Plant (Engine Right-Side Locator)
Power Plant (Engine Right-Side Locator)
Power Plant (Engine Right-Side Locator)
Power Plant (Engine Right-Side Locator)
Power Plant Bonding-Strap
Power Plant (Engine Left-Side Locator)
Power Plant (Engine Left-Side Locator)
Power Plant (Engine Left-Side Locator)
Power Plant (Engine Left-Side Locator) - Fuel Hoses
Door Operating System
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 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 [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 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 71-00-51-861-051-A ** ON A/C NOT FOR ALL

A. Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).

Subtask 71-00-51-941-052-A ** ON A/C NOT FOR ALL

B. Safety Precautions
(1) Make sure that you did the procedure to prevent engine motoring and to stop the electrical supply to the Electronic Engine Control (EEC)
(Ref. AMM TASK 71-00-00-860-832).
(2) On the overhead panel, on AIR COND panel 30VU:
(a) Make sure that the APU BLEED pushbutton switch is released (ON legend off).
(b) Make sure that the ENG 1(2) BLEED pushbutton is released (OFF legend is on).
(c) Make sure that the WARNING NOTICE(S) is in position to tell persons not to push the APU BLEED and ENG 1(2) BLEED pushbutton switches.
(3) Make sure that the aircraft is horizontal and stable

CAUTION: MAKE SURE THAT THE AIRCRAFT IS ON A HORIZONTAL AND FLAT SURFACE. IF YOU DO NOT OBEY THIS INSTRUCTION, SIDE LOADS WILL OCCUR AND THERE IS A RISK THAT THE ENGINE WILL NOT BE STABLE WHEN YOU LOWER OR LIFT IT. DAMAGE TO THE ENGINE CAN OCCUR.

(a) Make sure that the aircraft is on horizontal and flat surface.
(b) Make sure that the aircraft is stable (Ref. AMM TASK 05-57-00-200-001).

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

(4) Make sure that the WARNING NOTICE(S) is in position on the HP ground connector to tell persons not to pressurize the pneumatic system.
(5) Make sure that the engine intake is the direction of the wind. Attach the aircraft if the wind direction changes strongly (+/- 45 degrees) (Ref. AMM TASK 10-20-00-556-001).
(6) On the center pedestal, on FLAPS panel 115VU:
(a) Make sure that the slat and flap control lever is in the "0" (fully retracted) position.
(b) Make sure that the WARNING NOTICE(S) is in position to tell persons not to move the slat and flap control lever.
(7) If you are on post VSB PW1000G-C-79-00-0017-00A-930A-D, make sure that you also are on post VSB GRAA320NEO-A-71-13-0011-00001-930A-D.

Subtask 71-00-51-860-054-A ** ON A/C NOT FOR ALL

C. Aircraft Maintenance Configuration
(1) Do the EIS start procedure (lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
(2) On the ECAM control panel, push the FUEL key (on the lower ECAM DU, the FUEL page comes into view).
(a) Make sure that the LP valve is shown closed.

Subtask 71-00-51-864-052-A ** ON A/C NOT FOR ALL

D. Depressurization of the Aircraft Hydraulic Systems

WARNING: MAKE SURE YOU DEPRESSURIZED THE HYDRAULIC SYSTEM. IF YOU LOOSEN A HYDRAULIC TUBE FITTING WHEN THERE IS PRESSURE IN THE HYDRAULIC SYSTEM, YOU CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.

(1) On the overhead panel, on the HYD section of the control panel 40VU:
(a) Make sure that ENG1(2) PUMP pushbutton switch(es) is(are) released (OFF legend(s) is(are) on).
(b) Make sure that the WARNING NOTICE(S) is in position to tell persons not to pressurize the applicable system:
1 On panel 40VU
2 On the ground service panel of the applicable hydraulic system.
(2) Make sure that the applicable hydraulic system is depressurized (Ref. AMM TASK 29-10-00-864-001) or (Ref. AMM TASK 29-10-00-864-002).

NOTE: 4020KM1 (ENG1) supplies the GREEN hydraulic system and 4020KM2 (ENG2) supplies the YELLOW hydraulic system.

(3) Make sure that the applicable hydraulic system reservoir is depressurized (Ref. AMM TASK 29-14-00-614-001).

Subtask 71-00-51-865-053-A ** ON A/C NOT FOR ALL

E. 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
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B	2WE1	Q44
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A	1WE1	Q43
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B	2WE2	Q42
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A	1WE2	Q41
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B	2WE1	Q43
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A	1WE1	Q42
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B	2WE2	Q41
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A	1WE2	Q40
** ON A/C NOT FOR ALL
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	Y HYD/ELEC/PUMP	3802GX	AB06
123VU	Y HYD/ELEC/ELEC PUMP/NORM	3801GX	AB03
123VU	ANTI ICE/L/WHSLD	1DG1	AF10
123VU	ANTI ICE/R/WHSLD	1DG2	AF03
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08
49VU	ENGINE/1/FIRE DET/LOOP A	7WD1	A06
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
49VU	HYDRAULIC/G HYD/PUMP ENG1/CTL	1701GK	H12
** ON A/C NOT FOR ALL
121VU	DCV B/ENG1 PWR SUPPLY	103KS1	K44
121VU	DCV A/ENG1 PWR SUPPLY	102KS1	K42
121VU	ENG1/REV/LOCK	1EG1	N44
121VU	ICU A/ENG1 PWR SUPPLY	22KS1	R39
** ON A/C NOT FOR ALL
121VU	FUEL/LP VALVE/MOT2/ENG1	3QG	M25
121VU	OIL/PRESS/ENG1	10KC1	N40
121VU	PHMU/ENG1	95KS1	P44
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
121VU	ENGINE/LATCH DOORS & SLATS/ENG1	93KS1	P39
121VU	ENGINE/ENG1/FIRE DET/LOOP B	8WD1	Q38
121VU	ICU B/ENG1 PWR SUPPLY	101KS1	R42
** ON A/C NOT FOR ALL
121VU	DCV A/ENG1 PWR SUPPLY	102KS1	N44
121VU	DCV B/ENG1 PWR SUPPLY	103KS1	Q44
121VU	ENG1/REV/LOCK	1EG1	R44
121VU	ICU A/ENG1 PWR SUPPLY	22KS1	R38
** ON A/C NOT FOR ALL
122VU	ELEC/GCU/1	2XU1	T26
122VU	ELEC/IDG1/DISC	1XT	T24
122VU	ANTI ICE/ENG/1	1DN1	X10
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
49VU	ENGINE/2/FIRE DET/LOOP B	8WD2	A07
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
** ON A/C NOT FOR ALL
121VU	DCV B/ENG2 PWR SUPPLY	103KS2	K45
121VU	DCV A/ENG2 PWR SUPPLY	102KS2	K43
121VU	ENG2/REV/LOCK	1EG2	N45
121VU	ICU A/ENG2 PWR SUPPLY	22KS2	R40
** ON A/C NOT FOR ALL
121VU	FUEL/LP VALVE/MOT2/ENG2	4QG	M26
121VU	OIL/PRESS/ENG2	10KC2	N42
121VU	PHMU/ENG2	95KS2	P45
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42
121VU	ENGINE/LATCH DOORS & SLATS/ENG2	93KS2	P40
121VU	ENGINE/ENG2/FIRE DET/LOOP A	7WD2	Q39
121VU	HYDRAULIC/Y HYD/PUMP ENG2/CTL	3701GD	Q36
121VU	ICU B/ENG2 PWR SUPPLY	101KS2	R43
** ON A/C NOT FOR ALL
121VU	DCV A/ENG2 PWR SUPPLY	102KS2	N45
121VU	DCV B/ENG2 PWR SUPPLY	103KS2	Q45
121VU	ENG2/REV/LOCK	1EG2	R45
121VU	ICU A/ENG2 PWR SUPPLY	22KS2	R39
** ON A/C NOT FOR ALL
122VU	ELEC/GCU/2	2XU2	T27
122VU	ELEC/IDG2/DISC	2XT	T25
122VU	ANTI ICE/ENG/2	1DN2	W10
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22
** ON A/C NOT FOR ALL
FOR FIN: 101RH (DIRCIDS, 1)
49VU	COM/CIDS/DIR ESS/1	150RH	G01
** ON A/C NOT FOR ALL
49VU	AIR COND/CIDS/SDF/DIR1 ESS	15WH	C05
** ON A/C NOT FOR ALL
49VU	COM NAV/CIDS/DIR1 ESS	150RH	G01
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR NORM/1	151RH	M05
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR NORM/1	151RH	M06
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR1 NORM	151RH	M05
** ON A/C NOT FOR ALL
122VU	AIR COND/CIDS/SDF/DIR NORM/1	17WH	T17
** ON A/C NOT FOR ALL
FOR FIN: 102RH (DIRCIDS, 2)
49VU	COM/CIDS/DIR ESS/2	157RH	G02
** ON A/C NOT FOR ALL
49VU	COM/CIDS/DIR ESS/1	150RH	G01
** ON A/C NOT FOR ALL
49VU	AIR COND/CIDS/SDF/DIR2 ESS	18WH	C06
** ON A/C NOT FOR ALL
49VU	COM DIR ESS/2	157RH	G02
** ON A/C NOT FOR ALL
49VU	COM NAV/CIDS/DIR2 ESS	157RH	G02
49VU	COM NAV/CIDS/DIR1 ESS	150RH	G01
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR NORM/2	156RH	M06
121VU	COM NAV/CIDS/DIR NORM/1	151RH	M05
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR NORM/2	156RH	M07
121VU	COM NAV/CIDS/DIR NORM/1	151RH	M06
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR2 NORM	156RH	M06
121VU	COM NAV/CIDS/DIR1 NORM	151RH	M05
** ON A/C NOT FOR ALL
122VU	AIR COND/CIDS/SDF/DIR NORM/2	14WH	T18

Subtask 71-00-51-865-054-A ** ON A/C NOT FOR ALL

WARNING: MAKE SURE THAT CIRCUIT BREAKERS 1QG (2QG) AND 3QG (4QG) ARE OPEN BEFORE YOU OPEN CIRCUIT BREAKER 1KC1 (1KC2). IF YOU DO NOT OBEY THIS INSTRUCTION, THE LP FUEL VALVE WILL OPEN AND THERE IS A RISK THAT FUEL WILL FLOW OUT.

WARNING: MAKE SURE THAT YOU OPEN THE CIRCUIT BREAKERS AS FOLLOWS:

1JH AND 3JH1 BEFORE 2KS1
1JH 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.

WARNING: MAKE SURE THAT THE PROBE HEATER AND WINDOW HEATER CIRCUIT-BREAKERS ARE OPEN 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 INJURY TO MAINTENANCE PERSONNEL AND/OR DAMAGE TO EQUIPMENT.

F. 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	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
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
49VU	ENGINE/1/HP FUEL SOV	1KC1	A01
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R41
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R40
** ON A/C NOT FOR ALL
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
49VU	ENGINE/2/HP FUEL SOV	1KC2	A02
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	Q40
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	R41

Subtask 71-00-51-420-070-A ** ON A/C NOT FOR ALL

G. Get Access
(1) Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position.
(2) Remove the nacelle anti-ice solenoid-manifold (Ref. AMM TASK 30-21-21-000-801).
(3) Disconnect the electrical harness from nacelle anti-ice core pressure transducer (Ref. AMM TASK 30-21-22-000-801).
(4) Make sure that the hinge locators are installed to prevent the translation movement of the thrust reverser (sliding).
(a)
PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The hinge locator is a part of the 636-3000-10GSE TR HOLD OPEN STRUT TO PYLON tool assembly.

NOTE: The 636-3000-10GSE TR HOLD OPEN STRUT TO PYLON tool assembly includes four parts:

A hinge locator to prevent the translation movement of the thrust reverser cowl-door
A hold-open strut to keep the thrust reverser cowl-doors open
A thrust reverser for the fan-cowls hold-open brace to keep the fan cowl doors open
A seal compressor to protect the thrust-reverser cowl-door upper-seal.

END OF PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

(b)
POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The hinge locator is a part of the 636GSE3009-901 TR HOLD OPEN STRUT tool assembly.

NOTE: The 636GSE3009-901 TR HOLD OPEN STRUT tool assembly includes four parts:

A hinge locator to prevent the translation movement of the thrust reverser cowl-door
A hold-open strut to keep the thrust reverser cowl-doors open
A thrust reverser for the fan-cowls hold-open brace to keep the fan cowl doors open
A seal compressor to protect the thrust-reverser cowl-door upper-seal.

END OF POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

(5) Make sure that the 636-3000-26GSE TR VAPOR BARRIER SEAL PROTECTOR is installed.
(6) Make sure that the thrust-reverser hold-open strut to pylon is installed.
(a)
PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The thrust-reverser hold-open strut to pylon is a part of the 636-3000-10GSE TR HOLD OPEN STRUT TO PYLON tool assembly.

END OF PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

(b)
POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The thrust-reverser hold-open strut to pylon is a part of the 636GSE3009-901 TR HOLD OPEN STRUT tool assembly.

END OF POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

(7) Make sure that the fan-cowl hold-open brace is installed.
(a)
PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The fan-cowl hold-open brace is a part of the 636-3000-10GSE TR HOLD OPEN STRUT TO PYLON tool assembly.

END OF PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

(b)
POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The fan-cowl hold-open brace is a part of the 636GSE3009-901 TR HOLD OPEN STRUT tool assembly.

END OF POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

(8) Make sure the nose fire seal and the joint plate are removed (Ref. AMM TASK 54-57-22-000-821).
(9) Make sure that the forward and the aft of the 98D71203011000 BOOTSTRAP SYSTEM PW are correctly installed with the manual hoist kit or the ALT71000001 ELECTRICAL HOIST KIT (the beams, hoists and dynamometers). Refer to the manufacturer's instructions.

NOTE: Make sure that the aft wheel of the bootstrap turns freely.

NOTE: Make sure that the both translation beams are at the "0" position.

(10) Make sure that the Rear Mount Fairing (RMF) door is removed (Ref. AMM TASK 54-57-22-000-810).

Subtask 71-00-51-020-073-A ** ON A/C NOT FOR ALL

H. Remove both right and left upper fan exit fairings (Ref. AMM TASK 72-21-04-000-801).
(1) Attach the removed fan exit fairings on engine with TIE WRAP(S) to avoid they move when engine is lifted.

NOTE: Right and left upper fan exit fairings are maintained with lanyard to make sure they will stay on the installed engine.

Subtask 71-00-51-020-097-A ** ON A/C NOT FOR ALL

I. Make sure that the thrust reverser hinge access panels are removed (Ref. AMM TASK 78-30-06-000-801).

Subtask 71-00-51-020-098-A ** ON A/C NOT FOR ALL

J. Make sure that the pylon aprons and profiles are removed (Ref. AMM TASK 54-57-22-000-805).

Subtask 71-00-51-020-099-A ** ON A/C NOT FOR ALL

K. If the Overpressure Valve (OPV) and the interface duct are installed on the engine:
(1) Remove the interface duct from the engine (Ref. AMM TASK 36-11-49-000-824).
(2) Remove the OPV from the engine (Ref. AMM TASK 36-11-53-000-802).

Subtask 71-00-51-420-099-A ** ON A/C NOT FOR ALL

L. Make sure the interface duct is connected to pylon duct (Ref. AMM TASK 36-11-49-400-824).

Subtask 71-00-51-480-067-A ** ON A/C NOT FOR ALL

M. Make sure the 636-1000-27GSE PYLON ECS INTERFACE DUCT SUPPORT is installed to hold the interface duct.

ECS Duct Support ** ON A/C NOT FOR ALL

Subtask 71-00-51-210-051-A ** ON A/C NOT FOR ALL

N. Inspection of the Engine Mounts
(1) Do an inspection of the forward engine mount assembly (Ref. AMM TASK 71-21-41-210-802).
(2) Do an inspection of the aft engine mount assembly (Ref. AMM TASK 71-22-41-210-802).

Subtask 71-00-51-250-050-A ** ON A/C NOT FOR ALL

O. Inspection of the Engine Mount Bolts
(1) Do the eddy current inspection NTM 545390 of the forward mount bolts (9) and the aft mount bolts (17).
(a) No cracks are permitted.

NOTE: If the bolts are new or Component Maintenance Manual (CMM) inspected, then the eddy current inspection is not necessary.

(2) Do a visual inspection of the nuts (2), (12) and (21), screws (5), (7) and (19), washers (3), (10), (13) and (16), retainers (1), (4) and (11), lock plates (8) and (18) and cotter pins (22).
(a) No cracks are permitted.

NOTE: If the nuts, screws, washers, retainers, lock plates or cotter pins are new or CMM-inspected, then the visual inspection is not necessary.

(3) Do the fluorescent penetrant inspection of the aft mount pins (20) NTM 518000.
(a) No cracks are permitted.

NOTE: If the aft mount pins are new or CMM-inspected, then the fluorescent penetrant inspection is not necessary.

Subtask 71-00-51-250-050-B ** ON A/C NOT FOR ALL

O. Inspection of the Engine Mount Bolts
(1) Do the eddy current NTM 545390 or the fluorescent penetrant NTM 518000 inspection of the forward mount bolts (9) and the aft mount bolts (17).
(a) No cracks are permitted.

NOTE: If the bolts are new or Component Maintenance Manual (CMM) inspected, then the eddy current or the fluorescent penetrant inspection is not necessary.

NOTE: If the nuts, screws, washers, retainers, lock plates or cotter pins are new or CMM-inspected, then the visual inspection is not necessary.

(3) Do the fluorescent penetrant inspection of the aft mount pins (20) NTM 518000.
(a) No cracks are permitted.

NOTE: If the aft mount pins are new or CMM-inspected, then the fluorescent penetrant inspection is not necessary.

Subtask 71-00-51-840-053-A ** ON A/C NOT FOR ALL

P. Prepare the Mounts

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

(1) Lubricate the shear pin (spigot) of forward and aft pylon mounts with MOLYKOTE G-RAPID PLUS PASTE (Material No.360200) .
Do not lubricate the contact areas of the forward and aft mount assemblies.
(2) Clean the contact areas of the forward and aft mount assemblies with a clean lint-free cotton cloth (Material No.P05-005) made moist with Non Aqueous Cleaner-Composite Structural Bonding - (Material No.08BCF1) .
(3) Dry these areas with a clean dry lint-free cotton cloth (Material No.P05-005) before the Non Aqueous Cleaner-Composite Structural Bonding - (Material No.08BCF1) becomes dry.

Subtask 71-00-51-210-052-A ** ON A/C NOT FOR ALL

Q. Do a running torque check:
(1) On each engine forward-mount bolt (9):
(a) Apply MOLYKOTE G-RAPID PLUS PASTE (Material No.360200) on the threads of the bolt.
(b) Install the nut (2) on the bolt (9) until a minimum of two threads show on the other side of the nut.
(c) Use a 98D71203013000 TORQUE WRENCH SET PW to loosen the nut (2). The running torque must be a minimum of 1.02 m.daN (90.27 lbf.in).
(d) Install the nut (2) on the bolt (9) again until a minimum of two threads show on the other side of the nut.
(e) Use a 98D71203013000 TORQUE WRENCH SET PW to tighten the nut (2). The locking torque must be a maximum of 9.04 m.daN (66.67 lbf.ft):
1 Measure the torque necessary to tighten the bolt (9):
a The minimum torque must be 1.02 m.daN (90.27 lbf.in).
b The maximum torque must be 9.04 m.daN (66.67 lbf.ft).
2 If the torque of the nut (2) is less than 1.02 m.daN (90.27 lbf.in), replace the nut (2) and do steps 3.S.(1).(a) thru 3.S.(1).(e) again.
3 If the torque of the nut (2) is more than 9.04 m.daN (66.67 lbf.ft), remove the bolt (9) and the nut (2) and look for damaged threads. If the threads are damaged, replace the bolt (9) and the nut (2) and do steps 3.S.(1).(a) thru 3.S.(1).(e) again.
(2) On each engine aft-mount bolt (17):
(a) Apply MOLYKOTE G-RAPID PLUS PASTE (Material No.360200) on the threads of the bolt.
(b) Install the bolt (17) in the barrel nut (21) until a minimum of two threads show on the other side of the nut.
(c) Use a 98D71203013000 TORQUE WRENCH SET PW to loosen the bolt (17). The breakaway torque must be a minimum of 0.56 m.daN (49.56 lbf.in).
(d) Install the bolt (17) in the barrel nut (21) again until a minimum of two threads show on the other side of the nut.
(e) Use a 98D71203013000 TORQUE WRENCH SET PW to tighten the bolt (17). The locking torque must be a maximum of 8 m.daN (59.00 lbf.ft):
1 Measure the torque necessary to tighten the bolt (17):
a The minimum torque must be 0.56 m.daN (49.56 lbf.in).
b The maximum torque must be 8 m.daN (59.00 lbf.ft).
2 If the torque of the nut (21) is less than 0.56 m.daN (49.56 lbf.in), replace the nut (21) and do steps 3.S.(2).(a) thru 3.S.(2).(e) again.
3 If the torque of the nut (21) is more than 8 m.daN (59.00 lbf.ft), remove the bolt (17) and the nut (21) and look for damaged threads. If the threads are damaged, replace the bolt (17) and the nut (21) and do steps 3.S.(2).(a) thru 3.S.(2).(e) again.

4. Procedure
Subtask 71-00-51-840-054-A ** ON A/C NOT FOR ALL

A. Preparation of the Power Plant for the Installation

Bootstrap Equipment with Electrical Hoist Kit ** ON A/C NOT FOR ALL

(1) Remove the forward/rear mount holding-beams of the 636-1000-31GSE BEAM SUPPORT ENGINE MOUNTPWA211421 SUPPORT, SHIPPING, if installed.
(2) If necessary, install the 636-1000-32GSE BLOCKING DEVICE - AFT ENGINE MOUNT PIN on the aft engine mount (Refer to the tool manufacturer's notice).

NOTE: The 636-1000-32GSE BLOCKING DEVICE - AFT ENGINE MOUNT PIN holds the aft engine mount in position parallel to the pylon mount.

(3) Lower the cradle assembly on the engine PWA211430 STAND, TRANSPORT to the lower position (handling position). Refer to the manufacturer's notice.
(4) Position the engine transport stand with the power plant in the center under the pylon.

NOTE: The mark on ground done at the removal to identify the centerline helps to put in position the transport stand under the pylon.

(5) Make sure that the transport stand cradle is attached to the transport stand with the cradle pins correctly installed at the four locations.
(6) Attach the bootstrap to the cradle.
(7) Use the bootstrap chains of the manual hoist kit or the electrical hoists of the ALT71000001 ELECTRICAL HOIST KIT to equally lift the stand off the ground only 2 in. (50.80 mm) to align the stand under the pylon:

Aft mount: 480 daN (489.46 kg) maximum
Left Forward mount: 2959 daN (3017.34 kg) maximum
Right Forward mount: 2880 daN (2936.78 kg) maximum

(8) Lower the bootstrap hoists equally until the stand is on the ground and centered exactly under the pylon.

NOTE: The engine is now exactly below the pylon.

(9) Disconnect the stand cradle from the stand.
(10) Remove all the system plugs, except plugs from the hydraulic reservoir pressurization for the right engine.

NOTE: The hydraulic reservoir pressurization is only applicable on the left engine (ENG1).

Subtask 71-00-51-820-050-A ** ON A/C NOT FOR ALL

B. Monitor the items that follow when the bootstrap hoists are used to raise the power plant up to the pylon:
(1) Mating surfaces
(2) Front mount engagement
(3) Rear mount engagement
(4) Engine right side harness, tube and hose connections clearance
(5) Engine left side harness, tube and hose connections clearance
(6) Upper fan exit fairing and the pylon and the thrust reverser seals
(7) ECS elbow and the aft engine mount (if X motion)
(8) Aft Pylon Fairing (APF) and the exhaust
(9) Forward pylon fairing and the inlet.

Subtask 71-00-51-820-051-A ** ON A/C NOT FOR ALL

C. Raise the bootstrap hoists equally to align the power plant mounts and monitor the indications on the dynamometers for the manual hoist kit or on the desk display for the ALT71000001 ELECTRICAL HOIST KIT. Do not exceed the mount limits.

Bootstrap Equipment with Electrical Hoist Kit ** ON A/C NOT FOR ALL

Aft mount: 480 daN (489.46 kg) maximum
Left Forward mount: 2959 daN (3017.34 kg) maximum
Right Forward mount: 2880 daN (2936.78 kg) maximum

Subtask 71-00-51-820-052-A ** ON A/C NOT FOR ALL

D. Hoist the Engine

Bootstrap Equipment with Electrical Hoist Kit ** ON A/C NOT FOR ALL

(1) Use the bootstrap chains of the manual hoist kit or the desk display of the ALT71000001 ELECTRICAL HOIST KIT to lift the engine leveled and disengage the cradle from the stand.
(2) Make sure that both bootstrap translation beams are at the 0 position.

NOTE: With the beams at the 0 position, it is possible to lightly move the bootstrap forward or aft during the last adjustment of the engine mounts.

(3) Hoist the engine up to the pylon contact and make sure that the shear pins slide correctly.
(a) Make sure that the engine is correctly positioned:

Thrust-Reverser Axial Locator and V-Blade ** ON A/C NOT FOR ALL

CAUTION: WHEN YOU CLOSE THE THRUST REVERSER DOOR, MAKE SURE THAT THE ALIGNMENT FITTING AND V-BLADE CORRECTLY ENGAGE INTO THE FAN CASE V-GROOVE. IF THEY DO NOT CORRECTLY ENGAGE INTO THE FAN CASE V-GROOVE, DAMAGE TO THE COMPONENTS CAN OCCUR.

1 Make sure that the top of the V-blade on the thrust reversers correctly engages with the V-groove on the engine fan case.
2 Make sure that the shear pins slide correctly.
(b) Make sure that the mount mating surface remains parallel to the pylon mating surface during this operation.
(c) At the end of the hoisting, pay attention to the landing of the pylon visor on the air inlet and the APF on the nozzle.
(4) Make sure that the dynamometers for the manual hoist kit or the loads read on the desk display for the ALT71000001 ELECTRICAL HOIST KIT do not exceed the engine mounts limits:

Aft mount: 480 daN (489.46 kg) maximum
Left Forward mount: 2959 daN (3017.34 kg) maximum.
Right Forward mount: 2880 daN (2936.78 kg) maximum

Subtask 71-00-51-420-069-A ** ON A/C NOT FOR ALL

E. Installation of the Two Ball Lock Pins on the Forward Engine Mount

Bootstrap Equipment with Electrical Hoist Kit ** ON A/C NOT FOR ALL

Ball Lock Pin ** ON A/C NOT FOR ALL

NOTE: Left ball lock pins handle should be oriented at 9 o'clock when in position.

NOTE: The ball lock pins are parts of the 98D71203011000 BOOTSTRAP SYSTEM PW tool assembly.

(1) If it is difficult to install the ball lock pins, hoist the engine to apply a pre-load on forward and aft engine mounts.
(2) Read on dynamometers for the manual hoist kit or on the desk display for the ALT71000001 ELECTRICAL HOIST KIT to not exceed:

2959 daN (3017.34 Kg) maximum on left forward dynamometer
2880 daN (2936.78 Kg) on right forward dynamometer
480 daN (489.46 Kg) maximum on aft dynamometer

Subtask 71-00-51-420-066-B ** ON A/C NOT FOR ALL

F. Installation of the Forward and Aft Engine Mounts

Power Plant Engine-Mounts ** ON A/C NOT FOR ALL

(1) On the forward engine mount:
(a) Install the top retainer brackets (11), lower retainer brackets (4), washers (10) and (3), bolts (9) and nuts (2).
(b) Apply the MOLYKOTE G-RAPID PLUS PASTE (Material No.360200) :

Below the heads of the screws
On the threads of the screws and the nuts
On the two faces of the washers.

(c) Install the locking plates (1) and attach them to the retainer brackets (4) with the screws (5).
(d) TORQUE the screw (5) to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )

.
(2) On the aft engine mount:

CAUTION: INSTALL THE BARREL NUT WITH THE ROUNDED SIDE UP. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE BARREL NUT CAN OCCUR.

CAUTION: DURING THE INSTALLATION, MAKE SURE THAT THE THREE-POINT SHACKLE PINS ARE ON THE RIGHT SIDE AND THE TWO-POINT SHACKLE PINS ARE ON THE LEFT SIDE. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE REAR ENGINE MOUNT CAN OCCUR.

(a) Install the barrel nuts and their retainers (21) in the engine mount.
(b) Install the washers (16).
(c) Install the aft engine-mount bolt (17).
(d) Apply the MOLYKOTE G-RAPID PLUS PASTE (Material No.360200) :

Below the heads of the screws
On the threads of the screws and the nuts
On the two faces of the washers.

(e) TORQUE the forward and aft engine-mount bolts (9) and (17) as follows:
1 TORQUE the aft engine-mount bolts (17) in a diagonally opposite sequence to between 11 and 9 m.daN (81.12 and 66.37 lbf.ft )

.
2 TORQUE the forward engine-mount bolts (9) in a diagonally opposite sequence to between 27.6 and 22.4 m.daN (203.54 and 165.19 lbf.ft )

NOTE: This is not the last torque.

(f) Apply the last torque to the aft engine-mount bolts (17):

CAUTION: MAKE SURE THAT THE PROTRUSION OF THE BOLT ABOVE THE NUT IS EQUAL TO OR MORE THAN THE DIMENSION OF THE BOLT THREAD CHAMFER. IF THE PROTRUSION IS NOT SUFFICIENT, THERE IS A RISK THAT THE BOLT WILL NOT BE CORRECTLY INSTALLED.

1 TORQUE the aft engine-mount bolts (17) in a diagonally opposite sequence with the 98D71203013000 TORQUE WRENCH SET PW to between 22 and 18 m.daN (162.24 and 132.74 lbf.ft )

.
(3)

Positions of the Aft Mount Link ** ON A/C NOT FOR ALL

Subtask 71-00-51-020-061-A ** ON A/C NOT FOR ALL

G. Remove the bootstrap from the engine (Refer to the tool manufacturer's instructions):
(1) Disconnect the cradle from the engine.
(2) Lower the cradle with the help of the bootstrap.
(3) Disconnect the cradle from the bootstrap.
(4) Make sure that the PWA211430 STAND, TRANSPORT is in the lower position.
(5) Make sure that there is adequate clearance between the power plant and the PWA211430 STAND, TRANSPORT to remove the PWA211430 STAND, TRANSPORT
(6) Remove the PWA211430 STAND, TRANSPORT from the area.
(7) Remove the left and right TEC adapters from both sides of engine turbine exhaust-case.
(a) Refer to the tool manufacturer's notice.

NOTE: The TEC adapters are parts of PWA211430 STAND, TRANSPORT assembly.

(8) Remove the front and rear bootstrap beams.
(9) Apply the last torque to the forward engine-mount bolts with 98D71203013000 TORQUE WRENCH SET PW:

(a) TORQUE the forward engine-mount bolts (9) to between 57.2 and 46.8 m.daN (421.83 and 345.13 lbf.ft )

NOTE: Cross-tightening is mandatory.

Subtask 71-00-51-420-063-B ** ON A/C NOT FOR ALL

H. Locking of the Forward and Rear Mounts
(1) Lock the forward mount on the pylon as follows:

Power Plant Engine-Mounts ** ON A/C NOT FOR ALL

(a) Install the locking plates (8) and attach them to the retainer brackets (11) with the screws (7).
(b) TORQUE the screws (7) to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )

.
(2) Lock the aft mount to the pylon as follows:

Power Plant Engine-Mounts ** ON A/C NOT FOR ALL

(a) Install and attach the locking plates (18) to the retainer brackets with the screws (19).
(b) TORQUE the screws (19) to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )

.
(c) Install the screws (20), washers (13) and nuts (12):
1 Tighten the nuts (12) until the washers (13) are locked on the shoulder pins.
2 TORQUE the nuts (12) to between 6.69 and 5.57 m.daN (49.34 and 41.08 lbf.ft )

WARNING: USE PROTECTIVE GOGGLES WHEN YOU REMOVE OR INSTALL A COTTER PIN. EACH TIME YOU REMOVE A COTTER PIN DURING THE TASK, DISCARD IT IMMEDIATELY. A LOOSE COTTER PIN CAN CUT YOU OR MAKE YOU BLIND.

3 Install the two new AIPC 71-22-86-03-100 PIN (22).

NOTE: If necessary, loosen the nuts (12) 1/6 of a turn to install the cotter pins (22). If it is still not possible to install the cotter pins (22), replace the nuts (12).

(3) Remove the two ball lock pins from the forward engine mount.

Ball Lock Pin ** ON A/C NOT FOR ALL

NOTE: The ball lock pins are parts of the 98D71203011000 BOOTSTRAP SYSTEM PW tool assembly.

(4) Remove the 636-1000-32GSE BLOCKING DEVICE - AFT ENGINE MOUNT PIN from the aft engine mount, if installed (refer to the tool manufacturer's notice).
(5) Examine the assembly for unwanted objects, damage and correct assembly.

Subtask 71-00-51-420-067-A ** ON A/C NOT FOR ALL

I. Connect the Right-Side Power-Plant Interfaces

Power Plant (Engine Right-Side Locator) ** ON A/C NOT FOR ALL

CAUTION: REMOVE THE PROTECTION COVERS FROM THE OPENINGS AS NECESSARY TO PREVENT ENGINE DAMAGE.

CAUTION: DO NOT APPLY LUBRICANT TO THE THREADS OF THE SENSE TUBES OR THE ADAPTERS. CONTAMINATION OF THE SYSTEM CAN OCCUR.

(1) Installation of the Environmental Control System (ECS) connectors:
(a) Remove the 636-1000-27GSE PYLON ECS INTERFACE DUCT SUPPORT that holds the upper duct.

ECS Duct Support ** ON A/C NOT FOR ALL

(b) Install the upper duct on the three links (Ref. AMM TASK 36-11-49-400-824).
(c) Install the Overpressure Valve (OPV) on the ECS ducts (Ref. AMM TASK 36-11-53-400-802).
(2) Install the pylon structure drain on the pylon adapter:
(a) TORQUE the pylon structure drain to between 4.75 and 3.84 m.daN (35.03 and 28.32 lbf.ft )

with the Dry lubricant-General Assembly Molybdenum Disulfide & Silicone - (Material No.03QBC1) on the fitting.
(3) Installation of the sense lines:

CAUTION: APPLY THE ANTI-SEIZE COMPOUND TO ALL THE THREADS OF THE SENSE TUBE FITTING AND TO ALL THE THREADS OF THE MATING FITTING. MAKE SURE THAT THE ANTI-SEIZE COMPOUND DOES NOT GO INTO THE SENSE LINES. IF YOU DO NOT OBEY THESE INSTRUCTIONS, YOU CAN CAUSE INCORRECT OPERATION OF THE ECS.

(a) Apply a layer of the anti-seize compound (Material No.PU5-0005) or the Royco 81 MS anti-seize compound (Material No.PU5-0005A) or the PT 605 anti-seize compound (Material No.PU5-0005B) on the threads of the pylon sense-hose coupling-nuts and the mating fittings.
(b) Connect the two ECS hoses.
(c) TORQUE the two ECS hoses to between 2.77 and 2.43 m.daN (20.43 and 17.92 lbf.ft )

.
(4) Installation of the fuel connectors:
(a) Install the main fuel supply-hose on the pylon disconnect panel as follows:
1 Install the new AIPC 73-11-86-02-030 FACE SEAL (25) and the hose on the pylon disconnect panel with the four bolts (24).
a Apply the Dry lubricant-General Assembly Molybdenum Disulfide & Silicone - (Material No.03QBC1) on the two sides of the washers and on the full length of the screw.
2 TORQUE the four bolts (24) in a diagonally opposite sequence to between 0.79 and 0.62 m.daN (69.91 and 54.87 lbf.in )

.
(5) Installation of the hydraulic connectors:
(a) Install the hydraulic pressure hose (HP01) connector on the pylon.
1 TORQUE the free nut of the pylon to between 15.7 and 14.7 m.daN (115.78 and 108.41 lbf.ft )

.
(b) Connect the quick disconnect of the hydraulic suction hose (HS01) to the pylon.
(6) Install the nacelle anti-ice solenoid-manifold (Ref. AMM TASK 30-21-21-400-801).
(7) Installation of the electrical connectors:
(a) Install the WF07 wiring harness (4093KS) connector (P494) on the pylon receptacle (J494) as follows:
1 Examine, align and engage the connector.
2 Push the connector lightly in while you tighten the coupling ring.
3 Use the PLIERS - JAWED, SOFT to tighten the connector against the receptacle.
4 Make sure that you can feel the ratchet feature.
5 While you tighten, push the connector in and from side to side.
6 Use the PLIERS - JAWED, SOFT to turn the connector ring until the connector is fully tight.
(b) Install the WF06 wiring harness (4089KS) connector (P491) on the pylon receptacle (J491) as follows:
1 Examine, align and engage the connector.
2 Push the connector lightly in while you tighten the coupling ring.
3 Use the PLIERS - JAWED, SOFT to tighten the connector against the receptacle.
4 Make sure that you can feel the ratchet feature.
5 While you tighten, push the connector in and from side to side.
6 Use the PLIERS - JAWED, SOFT to turn the connector ring until the connector is fully tight.
(c) Install the WF02 wiring harness (4218KS) connectors (P402), (P406) and (P79) on the pylon receptacles (J402), (J406) and (J79) as follows:
1 Examine, align and engage the connector.
2 Push the connector lightly in while you tighten the coupling ring.
3 Use the PLIERS - JAWED, SOFT to tighten the connector against the receptacle.
4 Make sure that you can feel the ratchet feature.
5 While you tighten, push the connector in and from side to side.
6 Use the PLIERS - JAWED, SOFT to turn the connector ring until the connector is fully tight.
(d) Install the WF01 wiring harness (4217KS) connectors (P403) and (P407) on the pylon receptacles (J403) and (J407) as follows:
1 Examine, align and engage the connector.
2 Push the connector lightly in while you tighten the coupling ring.
3 Use the PLIERS - JAWED, SOFT to tighten the connector against the receptacle.
4 Make sure that you can feel the ratchet feature.
5 While you tighten, push the connector in and from side to side.
6 Use the PLIERS - JAWED, SOFT to turn the connector ring until the connector is fully tight.
(8) Connect the electrical harness to the nacelle anti-ice core-pressure-transducer (Ref. AMM TASK 30-21-22-400-801).
(9) Installation of the electrical bonding strap:

Power Plant Bonding-Strap ** ON A/C NOT FOR ALL

(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Connect the electrical bonding strap (40) from the pylon to the bracket installed on the rear face of the inlet with the bolt (41).
(c) TORQUE the bolt (41) to between 17.8 and 13.8 m.N (13.13 and 10.18 lbf.ft )

.
(d) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802):
1 Use the OHMMETER MULTIRANGE to measure the resistance between:

The ground strap lug and the inlet cowl bracket
The ground strap lug and the pylon bracket.

Make sure that the resistance value is not more than 0.5 miliohms.

Subtask 71-00-51-420-068-A ** ON A/C NOT FOR ALL

J. Connection of the Left-Side Power-Plant Interfaces

Power Plant (Engine Left-Side Locator) ** ON A/C NOT FOR ALL

CAUTION: REMOVE THE PROTECTION COVERS FROM THE OPENINGS AS NECESSARY TO PREVENT ENGINE DAMAGE.

CAUTION: DO NOT APPLY LUBRICANT TO THE THREADS OF THE SENSE TUBES OR THE ADAPTERS. CONTAMINATION OF THE SYSTEM CAN OCCUR.

(1) Installation of the power feeder cables on the pylon interface terminal:

Power Plant (Engine Left-Side Locator) ** ON A/C NOT FOR ALL

(a) If the terminal block with the pillar bolts (38) and the two washers (39) are removed from the engine, install them.
1 TORQUE the two pillar bolts (38) to between 2.4 and 2.2 m.N (21.24 and 19.47 lbf.in )

.
(b) Connect the white cable (neutral) to the stud (N1) with the nut (35) and the washer (36).
(c) Connect the red cable (A phase) to the stud (T1) with the nut (35) and the washer (36).
(d) Connect the yellow cable (B phase) to the stud (T2) with the nut (35) and the washer (36).
(e) Connect the blue cable (C phase) to the stud (T3) with the nut (35) and the washer (36).
(f) TORQUE the four nuts (35) to between 24.0 and 22.0 m.N (17.70 and 16.22 lbf.ft )

.
(g) Attach the terminal cover (37) with the two captive bolts.
(h) TORQUE the two captive bolts to between 1.0 and 0.9 m.N (8.85 and 7.96 lbf.in )

WARNING: USE 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.

(i) Safety the two captive bolts with the P05-289safety wire (lockwire) - steel, corrosion resistant.
(2) Installation of the fuel connections:

Power Plant (Engine Left-Side Locator) - Fuel Hoses ** ON A/C NOT FOR ALL

(a) Install the pylon fuel drain-line on the pylon adapter:
1 TORQUE the pylon fuel drain-line to between 2.82 and 2.37 m.daN (20.80 and 17.48 lbf.ft )

with the Dry lubricant-General Assembly Molybdenum Disulfide & Silicone - (Material No.03QBC1) .
(b) TORQUE the fuel return line to between 3.91 and 3.58 m.daN (28.83 and 26.40 lbf.ft )

with the Mineral base Lubricating Oil-General purpose Low Temp. - (Material No.03BBB1) .
(c) TORQUE the wing fuel drain-line to between 4.75 and 3.84 m.daN (35.03 and 28.32 lbf.ft )

with the Dry lubricant-General Assembly Molybdenum Disulfide & Silicone - (Material No.03QBC1) .
(3) Connection of the hydraulic reservoir pressurization-hose:

Power Plant (Engine Left-Side Locator) - Fuel Hoses ** ON A/C NOT FOR ALL

(a) On engine 1 only:
1 TORQUE the hydraulic reservoir pressurization-hose to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft )

.
(b) On engine 2 only:
1 Make sure that the blanking cap is installed on the hydraulic reservoir pressurization-port.
(4) Installation of the AC-generator control-harness electrical-connectors on the upper pylon-interface-panel receptacles:
(a) Examine, align and engage the connector.
(b) Push the connector lightly in while you tighten the coupling ring.
(c) Use the PLIERS - JAWED, SOFT to tighten the connector against the receptacle.
(d) Make sure that you can feel the ratchet feature.
(e) While you tighten, push the connector in and from side to side.
(f) Use the PLIERS - JAWED, SOFT to turn the connector ring until the connector is fully tight.
(5) Installation of the ECS and the fire-detection harness electrical-connectors on the lower pylon-interface-panel receptacles:
(a) Examine, align and engage the connector.
(b) Push the connector lightly in while you tighten the coupling ring.
(c) Use the PLIERS - JAWED, SOFT to tighten the connector against the receptacle.
(d) Make sure that you can feel the ratchet feature.
(e) While you tighten, push the connector in and from side to side.
(f) Use the PLIERS - JAWED, SOFT to turn the connector ring until the connector is fully tight.
(6) Installation of the hydraulic case-drain hose on the pylon check-valve adapter:
(a) Install the hydraulic case-drain hose on the pylon check-valve adapter.
(b) TORQUE the hydraulic case-drain hose to between 2.77 and 2.43 m.daN (20.43 and 17.92 lbf.ft )

.
(7) Connection of the Thrust Reverser Actuation System (TRAS) inhibition cable:
(a) Make sure that the inhibition lever is in the inhibited position and that the lockout pin is in the inhibited hole.
(b) Connect the TRAS inhibition cable to the pylon. If the tension of the cable wire is incorrect, adjust it (Ref. AMM TASK 78-31-06-820-801).
(8) Installation of the electrical bonding strap:

Power Plant Bonding-Strap ** ON A/C NOT FOR ALL

(a) Prepare the surface of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-803).
(b) Connect the electrical bonding strap (43) from the pylon to the bracket installed on the rear face of the inlet with the bolt (42).
(c) TORQUE the bolt (42) to between 17.8 and 13.8 m.N (13.13 and 10.18 lbf.ft )

.
(d) Do the electrical resistance measurement and the final protection of the bonding point(s)
(Ref. AMM TASK 20-28-00-912-802):
1 Use the OHMMETER MULTIRANGE to measure the resistance between:

The ground strap lug and the inlet cowl bracket
The ground strap lug and the pylon bracket.

Make sure that the resistance value is not more than 0.5 miliohms.

Subtask 71-00-51-860-056-A ** ON A/C NOT FOR ALL

K. Put the aircraft back to its initial configuration.
(1) Install the nose fire seal and the joint plate (Ref. AMM TASK 54-57-22-400-821).
(2) Install the right and the left upper fan exit fairings (Ref. AMM TASK 72-21-04-400-801).
(3) Install the RMF assembly (Ref. AMM TASK 54-57-22-400-810).
(4) Install the fan-cowl Hold Open Rod (HOR) bracket-bolts (Ref. AMM TASK 71-13-86-400-802).
(5) Install the telescopic HOR on the fan case.
(6) Position the two HORs in the open position.
(7) Remove the fan-cowl hold-open brace. Refer to the tool manufacturer's notice.
(a)
PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The fan-cowl hold-open brace tool is a part of the 636-3000-10GSE TR HOLD OPEN STRUT TO PYLON tool assembly.

END OF PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

(b)
POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The fan-cowl hold-open brace tool is a part of the 636GSE3009-901 TR HOLD OPEN STRUT tool assembly.

END OF POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

(8) Remove the fan case adapters from the left and the right side of the fan case:
(a) Refer to tool manufacturer's notice.

NOTE: The fan case adapters are parts of the PWA211430 STAND, TRANSPORT.

(9) Install the Door Operating System (DOS) actuator and the fittings:
(a) Connect the DOS fitting (2) to the fan case on the right and the left sides:
1 Clean the faying surface of the fitting (2) with the PU2-0001alcohol, isopropyl or equivalent. Remove the PU2-0001alcohol, isopropyl from the faying surface with a clean cloth (Material No.PU1-0001) before it dries.
2 Apply a layer of the anti-seize compound (Material No.PU5-0005) on the threads of the bolts (7).
3

Door Operating System ** ON A/C NOT FOR ALL

4 TORQUE the bolts (7) to between 1.01 and 0.85 m.daN (89.38 and 75.22 lbf.in )

.
(b) Connect the DOS actuator to the thrust reverser on the right and the left side:
1 Connect the flexible hose of the 636-3000-13GSE TR MANUAL HYDRAULIC OPENING SYSTEM tool to the quick disconnect fitting of the actuator (1).
2 Operate the 636-3000-13GSE TR MANUAL HYDRAULIC OPENING SYSTEM tool until the actuator (1) sufficiently opens to attach it to the thrust reverser.
3 Close the valve on the 636-3000-13GSE TR MANUAL HYDRAULIC OPENING SYSTEM tool to hold it in position.
4 Clean the threads of the upper bolts (3) and the upper nuts (6) with the acetone (Material No.PU2-0002) or equivalent. Remove the acetone (Material No.PU2-0002) from the bolt and the nut with a clean cloth (Material No.PU1-0001) before it dries.
5 Apply the anti-seize compound (Material No.PU5-0002) on the threads of the bolts (3) and the nuts (6).
6 Connect the upper part of the actuator (1) on the thrust reverser with the bolt (3), bushing (4), washer (5) and nut (6).
7 TORQUE the nuts (6) to between 2.49 and 2.03 m.daN (18.36 and 14.97 lbf.ft )

.
8 Disconnect the 636-3000-13GSE TR MANUAL HYDRAULIC OPENING SYSTEM tool from the actuator (1).
(10) Attach the thrust reverser HORs to the engine (Ref. AMM TASK 78-36-04-400-801).
(11) Remove the thrust-reverser hold-open strut to pylon. Refer to the tool manufacturer's notice.
(a)
PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The hold-open strut to pylon tool is a part of the 636-3000-10GSE TR HOLD OPEN STRUT TO PYLON tool assembly.

END OF PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

(b)
POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The hold-open strut to pylon tool is a part of the 636GSE3009-901 TR HOLD OPEN STRUT tool assembly.

END OF POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

Subtask 71-00-51-840-055-A ** ON A/C NOT FOR ALL

L. Preparation of the aircraft and the power plant for testing
(1) Fill the engine oil system (Ref. AMM TASK 79-00-00-610-801).
(2) Fill the starter oil system (Ref. AMM TASK 80-11-00-600-801).

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

(3) Fill the IDG oil system (Ref. AMM TASK 12-13-24-612-803).
(4) Pressurize the reservoir of the applicable hydraulic system (Ref. AMM TASK 29-14-00-614-002).

5. Close-up
Subtask 71-00-51-410-054-A ** ON A/C NOT FOR ALL

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Adjust the thrust reverser cowl-doors (Ref. AMM TASK 78-30-00-820-803).
(3) Close the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-410-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
451AL, 452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
461AL, 462AR.

Subtask 71-00-51-080-058-A ** ON A/C NOT FOR ALL

B. Remove the 636-3000-26GSE TR VAPOR BARRIER SEAL PROTECTOR.
(1) Refer to the tool manufacturer's notice

Subtask 71-00-51-020-079-A ** ON A/C NOT FOR ALL

C. Remove the hinge locator.
(1) Refer to the tool manufacturer's notice.
(a)
PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The hinge locator tool is a part of the 636-3000-10GSE TR HOLD OPEN STRUT TO PYLON tool assembly.

END OF PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

(b)
POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The hinge locator tool is a part of the 636GSE3009-901 TR HOLD OPEN STRUT tool assembly.

END OF POST SB GRAA320NEO-G-78-36-0001-00001-930A-C

(2) Install the pylon aprons and the profiles on the both engine sides (LH and RH) (Ref. AMM TASK 54-57-22-400-805).
(3) Install the thrust-reverser hinge access-panels on the both engine sides (LH and RH) (Ref. AMM TASK 78-30-06-400-801).

Subtask 71-00-51-440-052-A ** ON A/C NOT FOR ALL

D. Do the reactivation of the thrust reverser system after the deactivation for maintenance (Ref. AMM TASK 78-30-00-440-805).

Subtask 71-00-51-410-055-A ** ON A/C NOT FOR ALL

E. Close Access
(1) Adjust the fan cowl doors (Ref. AMM TASK 71-13-00-820-802).
(2) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
437AL, 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL, 448AR.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).

Subtask 71-00-51-865-055-A ** ON A/C NOT FOR ALL

WARNING: CLOSE THE CIRCUIT BREAKERS AS FOLLOWS:

2KS1 BEFORE 1JH AND 3JH1
2KS2 BEFORE 1JH AND 3JH2.

IF YOU DO NOT OBEY THIS SEQUENCE, YOU WILL START CONTINUOUS IGNITION AND THERE IS A RISK OF ELECTROCUTION.

WARNING: CLOSE THE CIRCUIT BREAKERS RELATED TO THE PHC AND WHC AND CIRCUIT BREAKER 4KS1(2) 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 INJURY TO MAINTENANCE PERSONNEL AND/OR DAMAGE TO EQUIPMENT.

F. 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
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
49VU	ENGINE/1/HP FUEL SOV	1KC1	A01
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R41
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R40
** ON A/C NOT FOR ALL
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
49VU	ENGINE/2/HP FUEL SOV	1KC2	A02
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	Q40
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	R41

Subtask 71-00-51-865-056-A ** ON A/C NOT FOR ALL

G. 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	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
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B	2WE1	Q44
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A	1WE1	Q43
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B	2WE2	Q42
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A	1WE2	Q41
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B	2WE1	Q43
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A	1WE1	Q42
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B	2WE2	Q41
121VU	ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A	1WE2	Q40
** ON A/C NOT FOR ALL
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	Y HYD/ELEC/PUMP	3802GX	AB06
123VU	Y HYD/ELEC/ELEC PUMP/NORM	3801GX	AB03
123VU	ANTI ICE/L/WHSLD	1DG1	AF10
123VU	ANTI ICE/R/WHSLD	1DG2	AF03
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
49VU	FUEL/LP VALVE/MOT1/ENG1	1QG	A08
49VU	ENGINE/1/FIRE DET/LOOP A	7WD1	A06
49VU	AIR BLEED/ENG 1/CTL	2HA1	D11
49VU	ANTI ICE/RAIN/RPLNT/CAPT	1DB1	D01
49VU	HYDRAULIC/G HYD/PUMP ENG1/CTL	1701GK	H12
** ON A/C NOT FOR ALL
121VU	DCV B/ENG1 PWR SUPPLY	103KS1	K44
121VU	DCV A/ENG1 PWR SUPPLY	102KS1	K42
121VU	ENG1/REV/LOCK	1EG1	N44
121VU	ICU A/ENG1 PWR SUPPLY	22KS1	R39
** ON A/C NOT FOR ALL
121VU	FUEL/LP VALVE/MOT2/ENG1	3QG	M25
121VU	OIL/PRESS/ENG1	10KC1	N40
121VU	PHMU/ENG1	95KS1	P44
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
121VU	ENGINE/LATCH DOORS & SLATS/ENG1	93KS1	P39
121VU	ENGINE/ENG1/FIRE DET/LOOP B	8WD1	Q38
121VU	ICU B/ENG1 PWR SUPPLY	101KS1	R42
** ON A/C NOT FOR ALL
121VU	DCV A/ENG1 PWR SUPPLY	102KS1	N44
121VU	DCV B/ENG1 PWR SUPPLY	103KS1	Q44
121VU	ENG1/REV/LOCK	1EG1	R44
121VU	ICU A/ENG1 PWR SUPPLY	22KS1	R38
** ON A/C NOT FOR ALL
122VU	ELEC/GCU/1	2XU1	T26
122VU	ELEC/IDG1/DISC	1XT	T24
122VU	ANTI ICE/ENG/1	1DN1	X10
122VU	AIR BLEED/ENG 1/MONG	3HA1	Z23
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
49VU	FUEL/LP VALVE/MOT1/ENG2	2QG	A09
49VU	ENGINE/2/FIRE DET/LOOP B	8WD2	A07
49VU	AIR BLEED/ENG 2/MONG	3HA2	D12
** ON A/C NOT FOR ALL
121VU	DCV B/ENG2 PWR SUPPLY	103KS2	K45
121VU	DCV A/ENG2 PWR SUPPLY	102KS2	K43
121VU	ENG2/REV/LOCK	1EG2	N45
121VU	ICU A/ENG2 PWR SUPPLY	22KS2	R40
** ON A/C NOT FOR ALL
121VU	FUEL/LP VALVE/MOT2/ENG2	4QG	M26
121VU	OIL/PRESS/ENG2	10KC2	N42
121VU	PHMU/ENG2	95KS2	P45
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42
121VU	ENGINE/LATCH DOORS & SLATS/ENG2	93KS2	P40
121VU	ENGINE/ENG2/FIRE DET/LOOP A	7WD2	Q39
121VU	HYDRAULIC/Y HYD/PUMP ENG2/CTL	3701GD	Q36
121VU	ICU B/ENG2 PWR SUPPLY	101KS2	R43
** ON A/C NOT FOR ALL
121VU	DCV A/ENG2 PWR SUPPLY	102KS2	N45
121VU	DCV B/ENG2 PWR SUPPLY	103KS2	Q45
121VU	ENG2/REV/LOCK	1EG2	R45
121VU	ICU A/ENG2 PWR SUPPLY	22KS2	R39
** ON A/C NOT FOR ALL
122VU	ELEC/GCU/2	2XU2	T27
122VU	ELEC/IDG2/DISC	2XT	T25
122VU	ANTI ICE/ENG/2	1DN2	W10
122VU	AIR BLEED/ENG 2/CTL	2HA2	Z22
** ON A/C NOT FOR ALL
FOR FIN: 101RH (DIRCIDS, 1)
49VU	COM/CIDS/DIR ESS/1	150RH	G01
** ON A/C NOT FOR ALL
49VU	AIR COND/CIDS/SDF/DIR1 ESS	15WH	C05
** ON A/C NOT FOR ALL
49VU	COM NAV/CIDS/DIR1 ESS	150RH	G01
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR NORM/1	151RH	M05
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR NORM/1	151RH	M06
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR1 NORM	151RH	M05
** ON A/C NOT FOR ALL
122VU	AIR COND/CIDS/SDF/DIR NORM/1	17WH	T17
** ON A/C NOT FOR ALL
FOR FIN: 102RH (DIRCIDS, 2)
49VU	COM/CIDS/DIR ESS/2	157RH	G02
** ON A/C NOT FOR ALL
49VU	COM/CIDS/DIR ESS/1	150RH	G01
** ON A/C NOT FOR ALL
49VU	AIR COND/CIDS/SDF/DIR2 ESS	18WH	C06
** ON A/C NOT FOR ALL
49VU	COM DIR ESS/2	157RH	G02
** ON A/C NOT FOR ALL
49VU	COM NAV/CIDS/DIR2 ESS	157RH	G02
49VU	COM NAV/CIDS/DIR1 ESS	150RH	G01
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR NORM/2	156RH	M06
121VU	COM NAV/CIDS/DIR NORM/1	151RH	M05
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR NORM/2	156RH	M07
121VU	COM NAV/CIDS/DIR NORM/1	151RH	M06
** ON A/C NOT FOR ALL
121VU	COM NAV/CIDS/DIR2 NORM	156RH	M06
121VU	COM NAV/CIDS/DIR1 NORM	151RH	M05
** ON A/C NOT FOR ALL
122VU	AIR COND/CIDS/SDF/DIR NORM/2	14WH	T18

Subtask 71-00-51-942-050-A ** ON A/C NOT FOR ALL

H. Aircraft Maintenance Configuration
(1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).
(2) Enter the engine hour and cycle data into the FDIMU for the installed engine (Ref. AMM TASK 31-36-00-740-014).

NOTE: This step is only applicable if you do not already have a dedicated procedure to monitor and record engine hours/cycles.

(3) Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001).
(4) Make sure that all the circuit breakers shown in the paragraph Procedure of the engine interface unit installation are closed. If they are not, close them in the recommended sequence
(Ref. AMM TASK 73-25-34-400-802)

Subtask 71-00-51-860-084-A ** ON A/C NOT FOR ALL

I. Check of the EEC Software
(1) Do a check of the EEC software PN (4000KS1 and 4000KS2) on the Multipurpose Control and Display Unit (MCDU):

Get access to the MCDU menu page (Ref. AMM TASK 31-32-00-860-012).
Push the FADEC engine reports button followed by LRU IDENT button and record the software PN.

(2) Make sure that the EEC software have compatible configurations on the two engines (refer to the PIPC and Airbus Service Bulletins).
(a) If the EEC software configurations on the two engines are not compatible, refer to the PIPC and Airbus Service Bulletins and update the EEC software, as necessary.

Subtask 71-00-51-720-051-A ** ON A/C NOT FOR ALL

J. Test
(1) Do the hydraulic maintenance procedure after an engine installation:
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
Do the maintenance procedure for Green hydraulic system (Ref. AMM TASK 29-11-51-860-040)
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
Do the maintenance procedure for Yellow hydraulic system (Ref. AMM TASK 29-13-51-860-001).
(2) Do an operational test of the IDG disconnect system (Ref. AMM TASK 24-21-00-710-803).
(3) Do an operational check of loop/squib (Ref. AMM TASK 26-12-00-710-001).
(4) Do an engine test No. 10 - replacement engine test (Ref. AMM TASK 71-00-00-720-813).

NOTE: Do not stop the engine at this step.

(5) While the engine is running, do this test:
(a) On the ECAM control panel, get the BLEED page.
(b) On AIR COND panel 30VU, push the ENG 1(2) BLEED pushbutton switch:

On the ENG 1(2) BLEED pushbutton switch, the OFF legend goes off.
On the lower ECAM DU, the PRV and HPV valves are shown open.
On the ENG page, monitor the nacelle temperature for unsatisfactory indication. If the temperature increases incorrectly, do the inspection of the bleed air-duct connections.

(c) On AIR COND panel 30VU, release the ENG 1(2) BLEED pushbutton switch.
(d) On the ENG 1(2) BLEED pushbutton switch, the OFF legend comes on.
(e) On the lower ECAM DU, the PRV and HPV valves are shown closed.
(6) While the engine is running, make sure that IDG 1(2) operates correctly:
(a) On the ECAM control panel, push the ELEC key to get the ELEC page.
(b) Make sure that the voltage of the IDG is 115VAC.
(c) Make sure that the frequency of the IDG is 400 Hz + or - 5 Hz.

NOTE: If the engine was removed after an IDG 1(2) disconnection, do a GCU 1(2) reset at the first engine start at idle. To do this, push (ON) then release GEN pushbutton switch.

(7) Do the operational test of the engine air intake ice protection (Ref. AMM TASK 30-21-00-710-002)
(8) Do an operational test of the thrust reverser:
(a) Do as follows:
1 Shutdown the engine
2 Do an operational test of the thrust reverser with the MCDU (Ref. AMM TASK 78-31-00-710-805)
(b) Alternative procedure:
1 Do the thrust reverser cycling test (Engine Running) (Ref. AMM TASK 78-31-00-710-805)
2 Shutdown the engine
(9) If the aircraft is operated in actual CAT III conditions, do an operational test of the LAND CAT III capability (Ref. AMM TASK 22-97-00-710-001).

Subtask 71-00-51-860-055-A ** ON A/C NOT FOR ALL

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

Subtask 71-00-51-862-051-A ** ON A/C NOT FOR ALL

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

Subtask 71-00-51-869-051-A ** ON A/C NOT FOR ALL

M. 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 recommendation.

[Rev.10 from 2021] 2026.04.01 02:31:52 UTC