Removal of the Power Plant with 2D Bootstrap [CFML]

TASK 71-00-51-000-803-A
Removal of the Power Plant with 2D Bootstrap

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

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

WARNING: OBEY THE HYDRAULIC SAFETY PROCEDURES.

WARNING: BE CAREFUL NOT TO GET AIRCRAFT FUEL IN YOUR MOUTH OR IN YOUR EYES. IF YOU GET FUEL ON YOUR SKIN OR ON YOUR CLOTHES, FLUSH IT IMMEDIATELY WITH WATER. IF NECESSARY, GET MEDICAL HELP. AIRCRAFT FUEL IS POISONOUS.

WARNING: 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, INJURY AND/OR DAMAGE 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: 210
ZONE: 400
FIN: 4020KM

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 1M (3 FT)-ADJUSTABLE
No specific	1	ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	1	TAPE - ADHESIVE
No specific	1	TIE WRAP(S)
No specific	AR	WARNING NOTICE(S)
636-1000-31GSE	1	BEAM SUPPORT ENGINE MOUNT
956A6046	1	ADAPTER, PLATE AND SPHERICAL JOINT - FAN MODULE
956A7314G03	1	SET, LIFTING BRACKET - TURBINE REAR FRAM
956A7610P01	1	COVER, PROTECTOR - 8 O-CLOCK OGV ARM
956A7644	1	STAND, SHIPPING - ENGINE ASSEMBLY
98D71203010000	1	BOOTSTRAP SYSTEM CFM
98N7100H001-000	1	THRUST REVERSER HOLD OPEN STRUT
98N7100H002-001	1	HOLD OPEN BRACE - FAN COWL
98N7100H005-000	1	T/R AXIAL LOCATOR
ALT71000001	1	ELECTRICAL HOIST KIT

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

C. Referenced Information

REFERENCE	DESIGNATION
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 24-21-51-000-806-A	Removal of the Integrated Drive Generator (IDG) - IDG 1(2)
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 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 36-11-49-000-827-A	Removal of the Environmental Control System (ECS) Ducts from the Engine Case Ports to the Pylon Connections
TASK 54-57-22-000-815-A	Removal of the Rear Mount Fairing (RMF) Door
TASK 71-13-00-010-803-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-803-A	Closing of the Fan Cowl Doors
TASK 71-13-12-000-803-A	Removal of the Forward Fan Cowl Hold Open Rod
TASK 71-21-11-220-803-A	Detailed Inspection of Forward Engine Mount and Secondary Load Path Clearance, Fail Safe Pin
TASK 71-22-11-220-803-A	Detailed Inspection of Aft Engine Mount and Secondary Load Path Clearance, Fail Safe Pin
TASK 72-24-03-000-801-A	Removal of the Strut 1
TASK 72-24-03-400-801-A	Installation of the Strut 1
TASK 73-11-05-000-801-A	Removal of the Main Fuel Pump
TASK 73-11-46-000-802-A	Removal of the Main Fuel Line from the Pylon to the Fuel Pump
TASK 73-11-49-000-804-A	Removal of the Fuel Return Hose from the Fuel Return Valve (FRV) to the Pylon
TASK 78-30-00-040-807-A	Deactivation of the Thrust Reverser System for Nacelle Maintenance (ICU)
TASK 78-36-00-010-806-A	Opening of the Thrust Reverser Cowl Doors
TASK 78-36-00-410-806-A	Closing of the Thrust Reverser Cowl Doors
TASK 78-36-45-000-801-A	Removal of the Thrust Reverser Hinge Access Panels
TASK 78-36-51-000-802-A	Removal of the Thrust Reverser Cowl Opening System
Hold Open Brace and Hold Open Strut
Adhesive Tape and Cover Protection
Strut 1
TRU Connectors
Right Electrical Bonding
Hydraulic Fittings
ECS duct
Power Plant Interface
Pylon Fuel Drain Line
Ball Lock Pins
Forward Engine Mount
Bootstrap with Manual Hoist Kit
Bootstrap with Electrical Hoist Kit
Adapters
Aft Engine Mount
Engine Removal Workflow
Bootstrap Beam before Engine Removal with Manual Hoist Kit
Dog Head, Upper Engine Kit and ECS Duct

3. Job Set-up
Subtask 71-00-51-861-052-A

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

Subtask 71-00-51-740-051-A

B. 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).

Subtask 71-00-51-941-054-A

C. Safety Precautions
(1) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE selector switch is in the NORM position.
(b) Make sure that the ENG/MASTER 1(2) control switch was in the OFF position not less than five minutes before you do this procedure.
(c) Put a WARNING NOTICE(S) in position to tell persons not to operate:

The ENG/MODE selector switch
The ENG/MASTER 1(2) control switch.

(2) On the ENG section of maintenance panel 50VU:
(a) Make sure that the ON legend of the FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).
(3) 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 a WARNING NOTICE(S) in position to tell persons not to push the APU BLEED and ENG 1(2) BLEED pushbutton switches.
(4) 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).
(5) 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.

(6) Put a WARNING NOTICE(S) in position on the HP ground connector to tell persons not to pressurize the pneumatic system.
(7) On the center pedestal, on flaps panel 114VU:
(a) Make sure that the flap and slat control lever is in the "0" (fully retracted) position.
(b) Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to move the slat and flap control lever.

Subtask 71-00-51-860-058-A

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 71-00-51-864-054-A

E. 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 hydraulic 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 HYD/FUEL 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 71-00-51-865-062-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C 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
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
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, ENGINE 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
121VU	FUEL/LP VALVE/MOT2/ENG1	3QG	M25
121VU	DCV A/ENG1 PWR SUPPLY	102KS1	N44
121VU	OIL/PRESS/ENG1	10KC1	N40
121VU	EEC BLOWER/ENG1	90KS1	P44
121VU	ENGINE/IGN/ENG1/SYS B	3JH1	P41
121VU	ENGINE/LATCH DOORS & SLATS/ENG1	93KS1	P39
121VU	DCV B/ENG1 PWR SUPPLY	103KS1	Q44
121VU	ENGINE/ENG1/FIRE DET/LOOP B	8WD1	Q38
121VU	ENG1/REV/LOCK	1EG1	R44
121VU	ICU B/ENG1 PWR SUPPLY	101KS1	R42
121VU	ICU A/ENG1 PWR SUPPLY	22KS1	R38
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, ENGINE 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
121VU	EEC BLOWER/ENG2	90KS2	M44
121VU	FUEL/LP VALVE/MOT2/ENG2	4QG	M26
121VU	DCV A/ENG2 PWR SUPPLY	102KS2	N45
121VU	OIL/PRESS/ENG2	10KC2	N42
121VU	ENGINE/IGN/ENG2/SYS B	3JH2	P42
121VU	ENGINE/LATCH DOORS & SLATS/ENG2	93KS2	P40
121VU	DCV B/ENG2 PWR SUPPLY	103KS2	Q45
121VU	ENGINE/ENG2/FIRE DET/LOOP A	7WD2	Q39
121VU	HYDRAULIC/Y HYD/PUMP ENG2/CTL	3701GD	Q36
121VU	ENG2/REV/LOCK	1EG2	R45
121VU	ICU B/ENG2 PWR SUPPLY	101KS2	R43
121VU	ICU A/ENG2 PWR SUPPLY	22KS2	R39
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
FOR FIN: 101RH (DIRCIDS, 1)
49VU	AIR COND/CIDS/SDF/DIR1 ESS	15WH	C05
49VU	COM NAV/CIDS/DIR1 ESS	150RH	G01
121VU	COM NAV/CIDS/DIR1 NORM	151RH	M05
122VU	AIR COND/CIDS/SDF/DIR NORM/1	17WH	T17
FOR FIN: 102RH (DIRCIDS, 2)
49VU	AIR COND/CIDS/SDF/DIR2 ESS	18WH	C06
49VU	COM NAV/CIDS/DIR2 ESS	157RH	G02
49VU	COM NAV/CIDS/DIR1 ESS	150RH	G01
121VU	COM NAV/CIDS/DIR2 NORM	156RH	M06
121VU	COM NAV/CIDS/DIR1 NORM	151RH	M05
122VU	AIR COND/CIDS/SDF/DIR NORM/2	14WH	T18

Subtask 71-00-51-865-063-A

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 DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL .

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.

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C 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, ENGINE 1)
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
49VU	ENGINE/1/HP FUEL SOV	1KC1	A01
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R40
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
49VU	ENGINE/2/HP FUEL SOV	1KC2	A02
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	R41

Subtask 71-00-51-010-058-A

H. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-803):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL 438AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL 448AR.

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.

(2) Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-040-807).
(3) Remove the thrust reverser hinge access panel (Ref. AMM TASK 78-36-45-000-801).

CAUTION: MAKE SURE THAT THE THRUST REVERSER AXIAL LOCATOR IS INSTALLED. IF IT IS NOT, DAMAGE TO THE COWL CAN OCCUR.

(a) Put in place the thrust reverser axial locator 98N7100H005-000 T/R AXIAL LOCATOR on the hinge 4. Refer to the manufacturer's notice.
(4) Open the thrust reverser cowl doors (Ref. AMM TASK 78-36-00-010-806):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
451AL 452AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
461AL 462AR.
(5) Put a ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position.
(6) Remove the rear mount fairing door assembly (473AR/AL) to get access to the aft engine mounts (Ref. AMM TASK 54-57-22-000-815).

Subtask 71-00-51-480-059-A

I. Install the left and the right 98N7100H001-000 THRUST REVERSER HOLD OPEN STRUT

Hold Open Brace and Hold Open Strut

(1) Refer to the manufacturer's notice.
(2) Use ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE.

Subtask 71-00-51-480-060-A

J. Install the 98N7100H002-001 HOLD OPEN BRACE - FAN COWL.

Hold Open Brace and Hold Open Strut

(1) Refer to the manufacturer's notice.

Subtask 71-00-51-020-080-A

K. Remove/Disconnect the following equipment from the engine only:
(1) Disconnect the Thrust Reverser (TR) Hold Open Rod (HOR) (Ref. AMM TASK 78-36-00-410-806).
(2) Disconnect the TR Cowl Opening System (COS) (Ref. AMM TASK 78-36-51-000-802).
(3) Store the TR COS on the TR with TIE WRAP(S).
(4) Remove the forward fan cowl HOR (Ref. AMM TASK 71-13-12-000-803).
(5) Disconnect the aft fan cowl HOR (Ref. AMM TASK 71-13-00-410-803).

Subtask 71-00-51-420-092-A

L. Install the 956A7610P01 COVER, PROTECTOR - 8 O-CLOCK OGV ARM to the 8 O'Clock OGV arm.

Adhesive Tape and Cover Protection

Subtask 71-00-51-020-081-A

M. Removal of the Strut 1

Strut 1

Adhesive Tape and Cover Protection

(1) Put TAPE - ADHESIVE on the segment shrouds 1, 2, 3, 4 and 5 in order to avoid object lost inside the engine.
(2) Remove the Strut 1 (31) and (32) (Ref. AMM TASK 72-24-03-000-801).

Subtask 71-00-51-020-082-A

N. Disconnection of the Power Plant Interfaces (Right Side)

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

(1) Disconnect the electrical connectors:

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.

(a) Disconnect the ten electrical connectors (29) at the pylon junction box.

TRU Connectors

(b) Disconnect the Integrated Drive (IDG) harnesses from the pylon terminal block (23).

TRU Connectors

1 Remove the two outer bolts (28) that attach the bar clamp (22) to the mounting plate (23).
2 Remove the three bolts (27) that attach the terminal block cover (26) to the pylon terminal block (24).
3 Remove the four nuts (25) that attach the power feeder cables (21) to the pylon terminal block (24).
4 Lift the four power feeder cables (21) off of the studs on the pylon terminal block (24).
5 Carefully pull the four power feeder cables (21) out of the top half of the bar clamp (22).

NOTE: Mark the cables (N1, T1, T2 and T3) for the subsequent installation.

TRU Connectors

1 Remove the 2 screws (19) and (18) of the TRU harness clamps (12) and (13), pull the harnesses out of the top half of the clamps (12) and (13).
2 Disconnect the 6 TRU harnesses connectors (10), (11), (14), (15), (16) and (17).
(d) Remove the bolt (6) and disconnect the RHS bonding strap (5).

Right Electrical Bonding

(2) Get access to the core compartment (right side).
(3) Disconnect the engine fittings:

Hydraulic Fittings

(a) Disconnect the HPV upstream (BMPS) and the HPV downstream (BPS) senses lines (55) and (57).
(b) Disconnect the HPV/PRV harness (40).
(c) Disconnect the two sensor lines (41) and (42).
(d) Remove the forward fire seal
1 Remove the four screws to remove the pylon cover (43) from the pylon frame.
2 Remove the fire seal (44).
3 Disengage the harnesses from the fire seal (44).
(e) Disconnect the pneumatic ECS duct (Ref. AMM TASK 36-11-49-000-827).

ECS duct

1 Remove the V-band clamp (39) that attaches the ECS duct to the lower bleed elbow.
2 Remove the ECS duct (37) from the engine.
3 Remove and discard the E-seal (38).

Subtask 71-00-51-020-083-A

O. Disconnection of the Power Plant Interfaces (Left Side)

Power Plant Interface

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

(1) Disconnection of the electrical connector:
(a) Remove the bolt (105) and disconnect the bonding straps (69) from the pylon on the brackets located on the rear face of the inlet.
(2) Disconnection of the air duct:
(a) Disconnect the starter air duct (60).
1 Open and remove the V-retainer coupling (61) that attaches the starter air duct (60) to the pylon duct elbow.
2 Remove and discard the seal (106) from the flange of the pylon duct elbow.
(3) Disconnection of hydraulic connectors:

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

(a) Disconnect the pressure hose (62).
(b) Disconnect the suction hose (63).
(c) Disconnect the case drain (64).
(4) Drain the fuel from the supply line:
(a) Refer to the removal of the main fuel pump (Ref. AMM TASK 73-11-05-000-801).
(5) Disconnect the fuel supply fittings:

WARNING: DO NOT GET FUEL IN YOUR MOUTH, IN YOUR 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) Removal of the bolts (66) and disconnection of fuel main line (65) (Ref. AMM TASK 73-11-46-000-802).
1 Discard the gasket between the main fuel line (65) and the pylon.
(b) Removal of the bolts (67) and disconnection of the Fuel Return Valve (FRV) tube (68) (Ref. AMM TASK 73-11-49-000-804).
1 Discard the gasket between FRV tube (68) and the pylon.
(6) Get access to the core compartment (Left side).
(7) On ENGINE 1 only:
(a) Disconnect the hydraulic tank pressurization line (56).

CAUTION: MAKE SURE THAT THE HYDRAULIC PRESSURIZATION LINE STAYS ATTACHED TO THE PYLON WHILE THE ENGINE IS REMOVED. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE CAN OCCUR.

1 Disconnect on the engine air pipe, not on the pylon side fitting.
(8) Disconnect the two pylon drain lines.

Pylon Fuel Drain Line

Subtask 71-00-51-020-089-A

P. If the IDG is not installed on the new engine, remove it from this one (Ref. AMM TASK 24-21-51-000-806).

NOTE: The IDG cannot be removed from the engine when positioned on his stand.

Subtask 71-00-51-220-051-A

Q. Do the inspection of the engine mount
(1) Do the detailed inspection of the secondary load-path clearance on the forward engine mount (Ref. AMM TASK 71-21-11-220-803).
(2) Do the detailed inspection of the secondary load-path clearance on the aft engine mount (Ref. AMM TASK 71-22-11-220-803).

Subtask 71-00-51-480-061-A

R. Install the BALL LOCK PINS (98D71203010553) on the Forward (FWD) Engine Mount (85).

Ball Lock Pins

(1) Insert the ball lock pin in the right and the left side centering pins holes for FWD engine mounts.

NOTE: BALL LOCK PINS (98D71203010553) is a part of BOOTSTRAP SYSTEM CFM (98D7120301000).

Subtask 71-00-51-020-084-A

S. On the FWD mount (85):

Forward Engine Mount

(1) Remove screws (86).
(2) Remove the upper locking plates (87).
(3) Loosen the four bolts (88).

NOTE: No sequence to loosen the bolts (88) recommended.

(4) Remove the screws (84).
(5) Remove the lower retaining plate (80).

4. Procedure
Subtask 71-00-51-480-062-A

A. Installation of the Bootstrap with the Bootstrap System CFM or Bootstrap Electrical hoist Kit

Bootstrap with Manual Hoist Kit

Bootstrap with Electrical Hoist Kit

NOTE: During the next steps of the procedure, we will call bootstrap, the tool assembly of:
- Bootstrap tool with Manual Hoist Kit 98D71203010000 BOOTSTRAP SYSTEM CFM or
- Bootstrap tool with Electrical Hoist Kit ALT71000001 ELECTRICAL HOIST KIT.
Except when mentioned.

(1) Install the forward and aft bootstraps 98D71203010000 BOOTSTRAP SYSTEM CFM for Manual Hoist Kit or ALT71000001 ELECTRICAL HOIST KIT for Electrical Hoist Kit. Refer to the manufacturer's notice.
(2) Move the bootstrap beam to the stop position with worm screw fully apparent ("27 to -1" visible on the scale located at the bootstrap beam). Refer to manufacturer's instruction.

Subtask 71-00-51-480-063-B

B. Preparation of the Power Plant for Removal with the Bootstrap System CFM or Bootstrap Electrical Hoist Kit

Adapters

Bootstrap with Electrical Hoist Kit

NOTE: During the next steps of the procedure, we will call Bootstrap, the tool assembly of:

Bootstrap tool with Manual Hoist Kit 98D71203010000 BOOTSTRAP SYSTEM CFM or
Bootstrap tool with Electrical Hoist Kit ALT71000001 ELECTRICAL HOIST KIT.
Except when mentioned.

(1) Install the 956A6046 ADAPTER, PLATE AND SPHERICAL JOINT - FAN MODULE on the fan frame (hoisting tool) on the left and the right of the engine.
(2) Install the 956A7314G03 SET, LIFTING BRACKET - TURBINE REAR FRAM on the turbine rear frame on the left and the right of the engine.
(3) Put and align a band of red speed tape on the floor just under the engine X axis.

NOTE: You can use plumb line.

(4) Position the engine transport 956A7644 STAND, SHIPPING - ENGINE ASSEMBLY under the bootstrap from front to rear by aligning the red mark on the engine transport 956A7644 STAND, SHIPPING - ENGINE ASSEMBLY and the red speed tape on the floor.
(5) Lower the bootstrap hoists and connect them to the cradle lift fittings. Refer to BOOTSTRAP and STAND manufacturer's instructions.
(6) Lift and lower the engine transport 956A7644 STAND, SHIPPING - ENGINE ASSEMBLY to position it exactly in the perpendicular with the hoists.
(7) Disconnect the cradle from the engine transport 956A7644 STAND, SHIPPING - ENGINE ASSEMBLY.
(8) Lift the cradle with the bootstrap hoists and make the dedicated sequence (lift and move rearward) to install the cradle to the engine. Refer to STAND manufacturer's instructions.
(9) Attach the cradle to the adapters (hoisting points) installed to the engine.
(10) Do not exceed the following values:
(a) 2833 kg (6246 lb), 2779 daN (6247.44 lbf) on the forward right dynamometer for Manual Hoist Kit 98D71203010000 BOOTSTRAP SYSTEM CFM or on the Instrumented shackle for Electrical Hoist Kit ALT71000001 ELECTRICAL HOIST KIT.
(b) 2960 kg (6526 lb), 2903 daN (6526.20 lbf) on the forward left dynamometer for Manual Hoist Kit 98D71203010000 BOOTSTRAP SYSTEM CFM or on the Instrumented shackle for Electrical Hoist Kit ALT71000001 ELECTRICAL HOIST KIT.
(c) 619 kg (1365 lb), 608 daN (1366.84 lbf) on the aft left dynamometer for Manual Hoist Kit 98D71203010000 BOOTSTRAP SYSTEM CFM or on the Instrumented shackle for Electrical Hoist Kit ALT71000001 ELECTRICAL HOIST KIT.
(11) Remove the ball lock pins. Refer to the manufacturer's notice.
(12) Remove the aft engine mount (101) bolts:

Aft Engine Mount

(a) Use the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE.

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.

(b) Remove the two cotter pins (102) of the nuts (99).
(c) Remove the screws (98), the washers (100) and the nuts (99).
(d) Remove the screws (91) and the locking plate (92).
(e) Remove the bolts (93) and the washers (94) from the mount locking plate (95).

NOTE: The mount locking plate (95) stays installed on the pylon.

(f) Remove the barrel nuts (97) and the retainer (96).
(13) Remove the forward engine mount (85) bolts.

Forward Engine Mount

(a) Remove the four bolts (88), the washers (89) and the upper retaining plate (90).
(b) Remove the washers (82), the nuts (81) and the locking plate (83).

Subtask 71-00-51-020-085-A

C. Removal of the Power Plant from the Pylon

Engine Removal Workflow

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.

CAUTION: MAKE SURE THAT THE ENGINE STAYS IN THE HORIZONTAL POSITION WHILE YOU LOWER IT. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE BOOTSTRAP CAN OCCUR OR THE ENGINE CAN FALL.

CAUTION: MAKE SURE THAT THE STAND IS WELL POSITIONED UNDER THE ENGINE/CRADLE ASSY.

(1) Make sure that no lines or unions stay connected to the pylon.
(2) Make sure that the bootstrap is fully to the stop position with worm screw fully apparent ("27 to -1" visible on the scale located at the bootstrap beam).

Bootstrap Beam before Engine Removal with Manual Hoist Kit

(3) Lower the engine and the cradle paying attention to the small gaps between the pylon dog head (36) and the upper engine kit (35) and between the ECS duct (37) and the engine core.

Dog Head, Upper Engine Kit and ECS Duct

(4) If necessary, install the strut 1 panels (Ref. AMM TASK 72-24-03-400-801).

CAUTION: WHEN YOU REMOVE/INSTALL THE POWER PLANT FROM/TO THE PYLON, MAKE SURE THAT YOU LOWER/LIFT AND MOVE THE POWER PLANT FORWARD/AFT A MINIMUM OF THREE TIMES. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE ENGINE OR AIRCRAFT CAN OCCUR.

(5) Carefully lower the engine using all four chain pulley blocks for Manual Hoist Kit 98D71203010000 BOOTSTRAP SYSTEM CFM or the service desk display for Electrical Hoist Kit ALT71000001 ELECTRICAL HOIST KIT at the same time.

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

NOTE: This sequence and the number of Para. 4.C.(a) to Para. 4.C.(d) are given for information. At any time during the lift down, you must ensure there is no interference between the engine and pylon parts, on fan and core compartment.

(a) Lower the engine.
(b) Move the engine forward.
(c) Lower the engine.
(d) Move the engine forward.
(e) Move forward the stand below the engine and cradle.
(f) Lower the engine until the cradle axis engages the stand axis on the rear.

NOTE: During the engine lowering procedure, the engine-cradle will not reach the stand perfectly horizontal. The rear axis will be first engaged and then the forward axis will be engaged by doing a small rotation of 2 degrees.

(6) Install the pins to lock the engine cradle on to the engine stand.
(7) Remove the four pulley chain blocks (for the manual hoist kit) or the Electrical Hoists (for the Electrical Hoist Kit) from the engine cradle.

NOTE: Put and align a band of red speed tape on the floor just in front of the cradle front wheel. This will help to position the cradle with the new engine at the right emplacement, in the case the same stand P/N is used for installation.

(8) Transfer of the engine out of the aircraft:

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.

(a) Transfer the engine from the area by moving forward the assembly (engine, cradle and stand).
(9) Install the 636-1000-31GSE BEAM SUPPORT ENGINE MOUNT on the engine mounts. Refer to the manufacturer's notice.
(10) Make sure that the protection covers are installed:
(a) On all the pylon interface openings.
(b) On all the power plant interface openings.

[Rev.10 from 2021] 2026.04.01 12:38:44 UTC