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

TASK 71-00-51-000-802-A
Removal of the Power Plant (Bootstrap Method)

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

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.

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.

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	1	ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE
No specific	1	CONTAINER 20L (5 USGAL)
No specific	1	CONTAINER 5 L (1.32 USGAL)
No specific	1	PLIERS - JAWED, SOFT
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	TIE WRAP(S)
No specific	AR	WARNING NOTICE(S)
No specific	1	WRENCH - TORQUE
No specific	Torque wrench: range to between 70.00 and 60.00 lbf.in (0.79 and 0.68 m.daN )
No specific	Torque wrench: range to between 70.00 and 63.00 lbf.in (0.79 and 0.71 m.daN )
636-1000-27GSE	1	PYLON ECS INTERFACE DUCT SUPPORT
636-1000-31GSE	1	BEAM SUPPORT ENGINE MOUNT
OR	OR
PWA211421	1	SUPPORT, SHIPPING
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
PWA211430	1	STAND, TRANSPORT

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.P03-001)	lubricant, aircraft turbine engine, (synthetic base)
(Material No.P05-005)	wipe, lint-free
(Material No.PU5-0003)	anti-seize compound
(Material No.PU6-0001)	oil

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
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
4	PACKING	EIPC 73-11-02-01-280
7	GASKET	AIPC 73-11-86-01-100

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 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 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 30-21-21-000-801-A	Removal of the Nacelle Anti-Ice Solenoid-Manifold
TASK 30-21-22-000-801-A	Removal of the Nacelle Anti-Ice Core-Pressure-Transducer
TASK 31-36-00-740-015-A	Printout of the Engine/APU Hours and Cycles Stored in the Flight Data Interface and Management Unit (FDIMU)
TASK 31-60-00-860-001-A	EIS Start Procedure
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 71-00-00-550-805-A	Preservation General Procedure
TASK 71-00-00-860-832-A	Procedure to Prevent Engine Motoring and to Stop the Electrical Supply to the EEC
TASK 71-13-00-010-802-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-802-A	Closing of the Fan Cowl Doors
TASK 71-13-86-000-802-A	Removal of the Hold Open Rod (HOR) Bracket Bolts
TASK 71-21-41-220-805-A	Detailed Inspection of Forward Engine Mount and Secondary Load Path Clearance, Fail-Safe Pin
TASK 71-22-41-220-805-A	Detailed Inspection of Aft Engine Mount and Secondary Load Path Clearance, Fail Safe Pin
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 78-30-00-040-805-A	Deactivation of the Thrust Reverser System for Ground Maintenance
TASK 78-30-06-000-801-A	Removal of the Thrust Reverser Hinge Access Panels
TASK 78-32-41-000-803-A	Removal of the Left Thrust Reverser Thermal Insulation Blankets
TASK 78-32-71-000-802-A	Removal of the Right Thrust Reverser Thermal Insulation Blankets
TASK 78-36-00-010-802-A	Opening of the Thrust Reverser Cowl-Doors
TASK 78-36-00-410-802-A	Closing of the Thrust Reverser Cowl-Doors
TASK 79-00-00-680-801-A	Drain the Engine Oil
Door Operating System
Fuel Draining
Main Fuel Line
Power Plant Bonding-Strap
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)
ECS Duct Support
Power Plant (Engine Left-Side Locator)
Power Plant (Engine Left-Side Locator) - Fuel Hoses
Power Plant (Engine Left-Side Locator)
Power Plant (Engine Left-Side Locator)
Ball Lock Pin
Power Plant Engine-Mounts
Power Plant Engine-Mounts
Bootstrap Equipment with Electrical Hoist Kit
Dog Head

3. Job Set-up
Subtask 71-00-51-941-060-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) 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.

(2) Point the engine intake in the direction of the wind. Attach the aircraft if the wind direction changes strongly (+/- 45 degrees) (Ref. AMM TASK 10-20-00-556-001).

Subtask 71-00-51-861-050-A ** ON A/C NOT FOR ALL

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

Subtask 71-00-51-740-050-A ** ON A/C NOT FOR ALL

C. Do a print-out of the engine hours and cycles and keep the print with the engine for follow-up (Ref. AMM TASK 31-36-00-740-015).

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

Subtask 71-00-51-860-057-A ** ON A/C NOT FOR ALL

D. 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 71-00-51-941-053-A ** ON A/C NOT FOR ALL

E. Safety Precautions
(1) Do 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) Put the WARNING NOTICE(S) in position to tell persons not to push the APU BLEED and the ENG 1(2) BLEED pushbutton-switches.
(3) Put the WARNING NOTICE(S) in position on the HP ground connector to tell persons not to pressurize the pneumatic system.
(4) On the center pedestal, on FLAPS panel 115VU:
(a) Make sure that the flap and slat control lever is in the "0" (fully retracted) position.
(b) Put the WARNING NOTICE(S) in position in the cockpit to tell persons not to move the flap and slat control lever.

Subtask 71-00-51-864-053-A ** ON A/C NOT FOR ALL

F. Depressurize 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 switches are released (OFF legend is ON)
(b) Put a WARNING NOTICE(S) 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) Depressurize the applicable hydraulic system (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) Depressurize the reservoir of the applicable hydraulic system (Ref. AMM TASK 29-14-00-614-001).

Subtask 71-00-51-865-060-A ** ON A/C NOT FOR ALL

G. Open, safety and tag 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
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 71-00-51-865-061-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.

H. Open, safety and tag 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 71-00-51-010-056-A ** ON A/C NOT FOR ALL

I. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
437AL, 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL, 448AR.

Subtask 71-00-51-040-052-A ** ON A/C NOT FOR ALL

J. Deactivation of the Thrust Reverser for Maintenance

WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE.

(1) Do the deactivation of the thrust reverser system for maintenance (Ref. AMM TASK 78-30-00-040-805).

Subtask 71-00-51-010-063-A ** ON A/C NOT FOR ALL

K. Get Access
(1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.
(2) Remove the thrust-reverser hinge access-panels on the left and the right sides (Ref. AMM TASK 78-30-06-000-801).
(3) Remove the pylon aprons and the profiles on the left and the right sides (Ref. AMM TASK 54-57-22-000-805).
(4) Install the 636-3000-26GSE TR VAPOR BARRIER SEAL PROTECTOR. Refer to the tool manufacturer's instructions.
(5) Install the hinge locator in the maximum allowed position. Refer to the tool manufacturer's instructions.
(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

(6) Open the thrust-reverser cowl-doors (Ref. AMM TASK 78-36-00-010-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
451AL, 452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
461AL, 462AR.
(7) Remove the Rear Mount Fairing (RMF) door on the left and the right sides of the engine to get access to the aft engine mounts (Ref. AMM TASK 54-57-22-000-810).

Subtask 71-00-51-020-095-A ** ON A/C NOT FOR ALL

L. Remove the nacelle anti-ice solenoid-manifold (Ref. AMM TASK 30-21-21-000-801)

NOTE: Before you install the forward bootstrap, it is necessary to remove the nacelle anti-ice solenoid-manifold.

Subtask 71-00-51-020-100-A ** ON A/C NOT FOR ALL

M. Disconnect the electrical harness from Nacelle Anti-Ice Core Pressure Transducer (Ref. AMM TASK 30-21-22-000-801).

Subtask 71-00-51-420-079-A ** ON A/C NOT FOR ALL

N. Installation of the thrust-reverser hold-open strut.
(1) Remove the related thermal blankets (Ref. AMM TASK 78-32-41-000-803) and (Ref. AMM TASK 78-32-71-000-802).
(2) Install the thrust-reverser hold-open strut. Refer to the tool manufacturer's notice.
(a)
PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The thrust-reverser hold-open strut 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 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 71-00-51-020-075-A ** ON A/C NOT FOR ALL

O. Disconnection of the Thrust Reverser Hold Open Rods (HOR) (Ref. AMM TASK 78-36-00-410-802)
(1) Disconnect the two HORs from the engine brackets
(2) Store the two HORs on their thrust reverser storage brackets.

Subtask 71-00-51-020-076-A ** ON A/C NOT FOR ALL

P. Remove the Door Operating System (DOS) actuators and the fittings.

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

(1) Remove the bolt (3), washer (5), bushing (4) and nut (6) that attach the actuator (1) to the thrust reverser.
(2) Connect the flexible hose of the 636-3000-13GSE TR MANUAL HYDRAULIC OPENING SYSTEM to the quick disconnect fitting of the actuator (1).
(3) Open the pressure relief valve of the 636-3000-13GSE TR MANUAL HYDRAULIC OPENING SYSTEM to release the pressure from the actuator (1).
(4) Retract the actuator (1) to its stowed position.

NOTE: If necessary, you can push against the actuator (1) to help it retract.

(5) Disconnect the 636-3000-13GSE TR MANUAL HYDRAULIC OPENING SYSTEM from the actuator (1).
(6) Remove the six bolts (7) and six washers (8) that attach the fitting (2) and actuator (1) assembly to the engine.

Subtask 71-00-51-420-096-A ** ON A/C NOT FOR ALL

Q. Install the fan case adapters on right and left side.
(1) Refer to the tool manufacturer's notice.

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

Subtask 71-00-51-420-080-A ** ON A/C NOT FOR ALL

R. Install the fan-cowl hold-open brace:
(1) Install 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 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

(2) Make sure that the thrust-reverser cowls are in the fully open position.
(3) Put the thrust-reverser hold-open strut to pylon in tension.
(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

Subtask 71-00-51-020-078-A ** ON A/C NOT FOR ALL

S. Disconnection of the Hold Open Rods (HOR) of the Fan Cowls
(1) Disconnect the telescopic fan-cowl HORs from the engine brackets (Ref. AMM TASK 71-13-00-410-802).
(2) Put the aft fan-cowl HORs on their fan cowl storage-brackets.
(3) Attach the forward fan-cowl HORs to the adjacent fan cowl structure with the TIE WRAP(S).

CAUTION: MAKE SURE THAT YOU REMOVE THE BOLTS. IF YOU DO NOT REMOVE THEM, DAMAGE TO THE BOLTS CAN OCCUR BECAUSE OF THE CHAFING WITH THE ENGINE DOLLY AFTER THE ENGINE REMOVAL.

(4) Remove the fan-cowl HOR bracket-bolts (Ref. AMM TASK 71-13-86-000-802).

Subtask 71-00-51-420-097-A ** ON A/C NOT FOR ALL

T. Install the thrust-reverser seal compressor:
(1) Refer to the tool manufacturer's notice.
(a)
PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

NOTE: The thrust-reverser seal compressor 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 seal compressor 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 71-00-51-930-050-A ** ON A/C NOT FOR ALL

U. Put a mark on the ground to identify the engine centerline.
(1) This will show the stand position under the pylon for correct engine installation.

Subtask 71-00-51-680-054-A ** ON A/C NOT FOR ALL

V. Drain the engine fuel system as follows:

WARNING: BEFORE YOU DRAIN THE FUEL, PUT A DRIP PAN THAT COVERS A LARGE AREA ON THE GROUND TO COLLECT EXCESS FUEL. A WET FLOOR CAN CAUSE YOU TO SLIP AND FALL. IF YOU DO NOT OBEY THIS WARNING, INJURY CAN OCCUR.

(1) Drain at the fuel manifold:

Fuel Draining ** ON A/C NOT FOR ALL

(a) Put the CONTAINER 20L (5 USGAL) below the fuel manifold.
(b) Loosen the drain-plug retention bolt (1).
(c) Turn the drain plug (3) to disengage the retention tab from below the drain-plug retention bolt (1) and the washer (2).

CAUTION: DO NOT PRY ON THE RETENTION TAB TO REMOVE THE DRAIN PLUG. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE DRAIN PLUG CAN OCCUR.

(d) Hold the drain plug (3) at the square while you turn, and pull it as necessary to remove it from the fuel manifold.
(e) Drain the fuel into the CONTAINER 20L (5 USGAL).
(f) Wipe the remaining fuel with a P05-005wipe, lint-free.
(g) Remove and discard the packing (4) from the drain plug (3).
(h) Apply P03-001lubricant, aircraft turbine engine, (synthetic base) on the new EIPC 73-11-02-01-280 PACKING (4).
(i) Install the packing (4) on the drain plug (3).
(j) Installation of the drain plug (3):

CAUTION: DO NOT PUSH ON THE RETENTION TAB TO INSTALL THE DRAIN PLUG. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE DRAIN PLUG CAN OCCUR.

1 Hold the drain plug (3) at the square, and press and turn the drain plug (3) until it fully seats against the fuel manifold.
2 Make sure that the drain plug (3) is fully seated against the mating surface.
3 Turn the drain plug (3) so that the retention tab is below the drain-plug retention bolt (1) and the washer (2).
(k) TORQUE the drain-plug retention bolt (1) to between 70.00 and 60.00 lbf.in (0.79 and 0.68 m.daN )

.
(2) Drain at the main fuel line:

Main Fuel Line ** ON A/C NOT FOR ALL

(a) Put the CONTAINER 5 L (1.32 USGAL) below the connection of the fuel suction hose (1) and the Integrated Fuel Power Control (IFPC).
(b) Remove the four bolts (5) and the four washers (6) from the bottom of the fuel suction hose (1).
(c) Remove the gasket (7) and move the fuel suction hose (1) from the IFPC.
(d) Drain the remaining fuel from the fuel suction hose (1) into the CONTAINER 5 L (1.32 USGAL).
(e) Apply a thin layer of oil (Material No.PU6-0001) on the new AIPC 73-11-86-01-100 GASKET (7).
(f) Apply a thin layer of anti-seize compound (Material No.PU5-0003) on the threads of the four bolts (5).
(g) Install the gasket (7) and the fuel suction hose (1) on the IFPC on the engine with the four bolts (5) and the four washers (6).
(h) Make sure that the gasket (7) is between the IFPC and the fuel suction hose (1).
(i) TORQUE the bolts (5) to between 70.00 and 63.00 lbf.in (0.79 and 0.71 m.daN )

.
(j) Remove the CONTAINER 5 L (1.32 USGAL).

Subtask 71-00-51-680-055-A ** ON A/C NOT FOR ALL

W. Drain the engine oil system to send the engine to the engine workshop or to do the engine preservation (this is not applicable to a preservation of seven days or less) (Ref. AMM TASK 71-00-00-550-805) and (Ref. AMM TASK 79-00-00-680-801).

NOTE: It is not necessary to change the oil filter for the preservation if the engine has been operated in the last seven days and is going to an overhaul facility or the engine is within the desired preservation method time period that has been previously performed.

Subtask 71-00-51-010-062-A ** ON A/C NOT FOR ALL

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

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

(2) Remove the nose fire seal and the joint plate (Ref. AMM TASK 54-57-22-000-821).

Subtask 71-00-51-020-091-A ** ON A/C NOT FOR ALL

Y. Disconnect the Power Plant Interfaces (Right Side).

CAUTION: INSTALL PROTECTION COVERS ON ALL THE OPENINGS IMMEDIATELY TO PREVENT DAMAGE TO THE ENGINE.

(1) Disconnect the bonding strap:

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

(a) Remove the bolt (41).
(b) Disconnect the electrical bonding strap (40) from the pylon on the bracket installed on the rear face of the inlet.
(2) Disconnect the electrical connectors:

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

(a) Disconnect the WF07 wiring harness (4093KS) connector (P494) from the pylon with the PLIERS - JAWED, SOFT.
(b) Disconnect the WF06 wiring harness (4089KS) connector (P491) from the pylon with the PLIERS - JAWED, SOFT.
(c) Disconnect the WF01 wiring harness (4217KS) connectors (P403) and (P407) from the pylon with the PLIERS - JAWED, SOFT.
(d) Disconnect the WF02 wiring harness (4218KS) connectors (P402) and (P406) from the pylon with the PLIERS - JAWED, SOFT.
(e) Disconnect the WF02 wiring harness (4218KS) connector (P79) from the interphone harness with the PLIERS - JAWED, SOFT.
(3) Disconnect the hydraulic connectors:

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

CAUTION: YOU MUST NOT LET HYDRAULIC FLUID FALL ON THE ENGINE. UNWANTED HYDRAULIC FLUID MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT- FREE CLOTH. THE HYDRAULIC FLUID CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND SOME PARTS.

(a) Disconnect the hydraulic pressure hose (HP01) from the pylon.
(b) Disconnect the quick disconnect of the hydraulic suction hose (HS01) from the pylon.
(4) Disconnect the fuel connector:

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

WARNING: DO NOT GET FUEL IN YOUR MOUTH, EYES OR ON YOUR SKIN. DO NOT BREATHE THE FUMES FROM THE FUEL. KEEP THE FUEL AWAY FROM SPARKS, FLAME AND HEAT. FUEL IS POISONOUS AND FLAMMABLE, WHICH CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

(a) Disconnect the main fuel supply-hose from the pylon disconnect panel as follows:
1 Remove the four bolts (24).
2 Disconnect the hose and discard the face seal (25).
(5) Disconnect the pylon fuel drain-hose from the pylon.

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

(6) Disconnect the Environmental Control System (ECS):

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

(a) Disconnect the two ECS hoses.
(b) Disconnect the ECS duct:
1 Remove the coupling (24) from the upper duct and the Overpressure Valve (OPV).
2 Disconnect the interface duct from the three links:

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

a Remove the three nuts (36) and the three bolts (34).
b Install the 636-1000-27GSE PYLON ECS INTERFACE DUCT SUPPORT to hold the upper duct.
c Remove the three bushings (35) and the three bushings (37).
d Remove the interface duct from the three links.

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

Subtask 71-00-51-020-092-A ** ON A/C NOT FOR ALL

Z. Disconnect the Power Plant Interfaces (Left Side).
(1) Disconnect the AC-generator control-harness electrical-connectors from the upper pylon-interface-panel receptacles with the PLIERS - JAWED, SOFT.

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

(2) Disconnect the Environmental Control System (ECS) and the fire-detection harness electrical-connectors from the lower pylon-interface-panel receptacles with the PLIERS - JAWED, SOFT.

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

(3) Disconnect the hydraulic reservoir pressurization-hose:

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

NOTE: The hydraulic reservoir pressurization is only applicable to the left engine (engine 1).

(a) Disconnect the hydraulic reservoir pressurization-hose from the engine side.

CAUTION: MAKE SURE THAT ALL IDG POWER FEEDER CABLES ARE DISCONNECTED FROM THE PYLON TERMINAL BLOCK. IF THEY ARE NOT, DAMAGE TO THE ENGINE CAN OCCUR.

(4) Disconnect the power feeder cables from the pylon interface terminal as follows:

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

(a) Remove the two captive bolts and the terminal cover (37) from the pillar bolts (38).
(b) Make marks on cables N1 (white), T3 (blue), T2 (yellow) and T1 (red) for the subsequent installation.
(c) Remove the four nuts (35) and the four washers (36) from the terminal block studs.
(d) Disconnect the four cables.
(e) If the two pillar bolts (38) and the washers (39) are installed, remove them.

CAUTION: INSTALL PROTECTION COVERS ON ALL THE OPENINGS IMMEDIATELY TO PREVENT DAMAGE TO THE ENGINE.

(5) Disconnect the hydraulic case-drain hose from the pylon check valve.

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

(6) Disconnect the Thrust Reverser Actuation System (TRAS) inhibition cable.

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

(7) Disconnect the fuel connections:

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

(a) Disconnect the wing fuel drain-line.
(b) Disconnect the fuel return line.
(c) Disconnect the pylon fuel drain-line.
(8) Disconnect the electrical bonding strap:

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

(a) Remove the bolt (42).
(b) Disconnect the electrical bonding strap (43) from the pylon on the bracket installed on the rear face of the inlet.

Subtask 71-00-51-220-052-A ** ON A/C NOT FOR ALL

AA. Inspection of the Engine Mount
(1) Do the detailed inspection of the secondary load-path clearance on the forward engine mount (Ref. AMM TASK 71-21-41-220-805).
(2) Do the detailed inspection of the secondary load-path clearance on the aft engine mount (Ref. AMM TASK 71-22-41-220-805).

4. Procedure
Subtask 71-00-51-420-095-A ** ON A/C NOT FOR ALL

A. Installation of the Bootstrap

CAUTION: MAKE SURE THAT THE BOOTSTRAP HOIST CHAINS ARE ALONGSIDE THE ENGINE WHEN YOU USE THEM. IF NOT, THE CHAINS CAN HIT THE ENGINE AND CAUSE DAMAGE TO IT.

(1) Install the two ball lock pins 98D71203011000 BOOTSTRAP SYSTEM PW on left and right sides of the forward engine mount.

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: Ball lock pins are designed to hold engine weight when engine forward mount bolts are removed

(2) Remove the locking plates system of the forward engine mounts on left and right sides.

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

(a) Remove the four screws (7) that attach the four locking plates (8) to the retainer (11).
(b) Remove the four locking plates (8).
(c) Loosen the four forward engine mounts bolts (9) with 98D71203013000 TORQUE WRENCH SET PW as necessary to be able to loose them with a WRENCH - TORQUE.
(3) Remove the forward engine mount bolts on left and right sides.

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

(a) Loosen the four bolts (9) to remove the remaining torque.
(b) Remove two screws (5) and remove retainer (1).
(c) Remove two nuts (2) and remove retainer (4) and the two washers (3).
(d) Remove the two bolts (9), the two washers (10) and the retainer (11).
(e) Repeat steps (b) to (d) on the right side.
(4) Remove and discard the two cotter pins (22) from the nuts (12)

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

(5) Loosen the nuts (12) sufficiently to remove the torque.
(a) Do not remove the nuts (12) at this time.
(6) Install the forward and aft 98D71203011000 BOOTSTRAP SYSTEM PW. Refer to the manufacturer's notice.
(7) Make sure that the two engine translation beams are in fully aft position by turning the aft beam wheel handle blocker on the mechanical stop.
(8) Install the Turbine Exhaust Case (TEC) adapters on left and right side.
(a) Refer to tool manufacturer's notice.

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

Subtask 71-00-51-840-056-B ** ON A/C NOT FOR ALL

B. Prepare the Power Plant for the Removal

CAUTION: BEFORE YOU INSTALL/REMOVE THE GSE-TOOL, READ THE INSTRUCTIONS IN THE APPLICABLE GSE INSTRUCTION MANUAL. WHILE YOU OPERATE THIS TOOL, CAREFULLY OBEY THEM. IF YOU DO NOT OBEY THE INSTRUCTIONS, DAMAGE TO EQUIPMENT CAN OCCUR.

CAUTION: BEFORE YOU PUT THE ENGINE TRANSPORT STAND IN POSITION BELOW THE ENGINE, PUT THE ARMS OF THE STAND IN THE LOWER POSITION. IF YOU DO NOT OBEY THIS PRECAUTION, THE THRUST REVERSER COWLS CAN TOUCH THE STAND AND BECOME DAMAGED.

(1) Lower the arms of the stand.
(a) Refer to the tool manufacturer's instructions.
(2) Fully lower the cradle assembly on the engine PWA211430 STAND, TRANSPORT (handling position). Refer to the tool manufacturer's instructions.
(3) Put the engine transport stand below the power plant in the center below the pylon.
(4) Make sure that the cradle is attached to the engine PWA211430 STAND, TRANSPORT.
(5) Lower the bootstrap hoists and connect them to the cradle lift fittings (refer to the tool manufacturer's instructions).
(6) Lock the brakes of the stand.
(7) Lift the bootstrap hoists equally to lift the stand only 2 in. (50.80 mm) from the ground and align it below the power plant.

NOTE: It is important to lift all the bootstrap hoists (forward, aft, inboard and outboard) equally to correctly put the stand in position and align it with the engine.

(8) Lower the bootstrap hoists equally.

NOTE: The stand is now accurately below the engine.

(9) Release the pins that attach the engine cradle to the stand and lift the engine cradle to the engine.
(10) Lift the cradle to attach the cradle to the engine.
(a) Lift the cradle from the ground, then gradually tilt the front of the cradle up to adjust the approach angle of the cradle to the fan case and TEC adapters.

NOTE: The front of the engine is tilted 2.2 deg. up in relation to the aircraft axis.

(b) Safety the engine on the cradle.

CAUTION: BEFORE YOU SAFETY THE ENGINE ON THE CRADLE, MAKE SURE THAT THE CAP ON THE ADAPTERS OF THE TRANSPORT STAND, THAT IS INSTALLED ON THE TURBINE EXHAUST CASE, WILL NOT TOUCH THE ENGINE-CORE FIRE LOOP. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE ENGINE CAN OCCUR.

1 Safety the engine on the cradle with the cap on the adapters.
a Refer to tool manufacturer's instructions.
(11) Remove the two ball lock pins.

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

(12) If it is difficult to remove the ball lock pins, apply a load on the forward and aft engine mounts with the boostrap chains as follows:

Left forward dynamometer: + 300 daN (then + 100 daN increments if necessary) but not more then 2959 daN (3017.34 kg)
Right forward dynamometer: + 300 daN (then + 100 daN increments if necessary) but not more than 2880 daN (2936.78 kg)
Aft dynamometer: + 200 daN (then + 100 daN increments if necessary) but not more than 480 daN (489.46 kg).

(13) Remove the aft engine-mount bolts.

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

(a) Remove the four screws (19).
(b) Remove the four locking plates (18).
(c) Loosen the four bolts (17) to remove the torque.
(d) Remove four bolts (17), four washers (16).
(e) Remove the two nuts (12) and two washers (13).
(f) Remove the two bolts (20).

Subtask 71-00-51-020-072-A ** ON A/C NOT FOR ALL

C. Removal of the power plant from the pylon.

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

CAUTION: WHEN YOU LOWER THE ENGINE, CAREFULLY MONITOR ALL DISCONNECTED TUBES, DUCTS AND HARNESSES TO MAKE SURE THAT THE CLEARANCE IS SUFFICIENT. IF THE CLEARANCE IS NOT SUFFICIENT, DAMAGE TO THE ENGINE OR AIRCRAFT CAN OCCUR.

(1) Make sure that no lines or unions stay connected to the pylon.
(2) Lower the engine and cradle the assembly.
(a) Make sure that the clearance is sufficient between the upper BiFi and:

The pylon dog head.
Dog Head ** ON A/C NOT FOR ALL
PRE SB GRAA320NEO-G-78-36-0001-00001-930A-C

The thrust reverser seals (where the seal compressors from the 636-3000-10GSE TR HOLD OPEN STRUT TO PYLON tool assembly are installed).

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

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

The thrust reverser seals (where the seal compressors from the 636GSE3009-901 TR HOLD OPEN STRUT tool assembly are installed).

END OF POST SB GRAA320NEO-G-78-36-0001-00001-930A-C
The thrust reverser seals (where the 636-3000-26GSE TR VAPOR BARRIER SEAL PROTECTOR tool is installed).

(b) Carefully lower the engine using the all four chain pulley blocks at the same time.

NOTE: Make sure that the load read on the dynamometers for the manual hoist kit or on the desk display for the ALT71000001 ELECTRICAL HOIST KIT is less than:

Aft mount: 480 daN (1079 lbf) (489.46 kg (1079 lb)) maximum
Left forward mount: 2959 daN (6652 lbf) (3017.34 kg (6652 lb)) maximum.
Right forward mount: 2880 daN (6474 lbf) (2936.78 kg (6474 lb)) maximum.

NOTE: Be careful not to cause dynamic effects during the descent.

(3) Put the engine cradle in position on the trolley.

NOTE: Put first the aft section of the engine cradle in position on the trolley, then the forward section.

(4) Install the pins to lock the engine cradle on to the engine stand.
(5) Remove the four pulley chain blocks from the engine cradle.

CAUTION: REMOVE THE ENGINE FROM THE FRONT OF THE WING. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE ENGINE AND PYLON CAN OCCUR.

(6) Remove the engine from the area in forward direction.
(7) Make sure that the protection covers are installed:
(a) On all the pylon interface openings.
(b) On all the power plant interface openings.
(8) Install the both right and left upper fan exit fairings (Ref. AMM TASK 72-21-04-400-801).
(9) Install the forward/rear mount holding-beams of the 636-1000-31GSE BEAM SUPPORT ENGINE MOUNTPWA211421 SUPPORT, SHIPPING.

NOTE: The forward/rear mount holding-beams are parts of the 636-1000-31GSE BEAM SUPPORT ENGINE MOUNTPWA211421 SUPPORT, SHIPPING tool assembly.

[Rev.10 from 2021] 2026.04.01 02:31:49 UTC