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

TASK 71-00-51-400-803-A
Installation of the Power Plant with 2D Bootstrap

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: 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 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
This task gives the information for the installation of the power plant. The power plant can be installed in a particular configuration. It is permitted to install the power plant before or after installation of the components that follow: The air intake cowl, The exhaust nozzle, The centerbody (exhaust plug)
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	MALLET - PLASTIC
No specific	1	MAT - PROTECTIVE
No specific	1	OHMMETER MULTIRANGE
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	TAPE - ADHESIVE
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 421.83 and 345.13 lbf.ft (57.19 and 46.79 m.daN )
No specific	Torque wrench: range to between 41.59 and 32.74 lbf.in (0.47 and 0.37 m.daN )
No specific	Torque wrench: range to between 74.34 and 65.49 lbf.in (0.84 and 0.74 m.daN )
No specific	Torque wrench: range to between 74.34 and 67.26 lbf.in (0.84 and 0.76 m.daN )
No specific	Torque wrench: range to between 125 and 115 lbf.in (1.41 and 1.30 m.daN )
No specific	Torque wrench: range to between 4.70 and 3.70 m.N (41.59 and 32.74 lbf.in )
No specific	Torque wrench: range to between 66.90 and 55.70 m.N (49.34 and 41.08 lbf.ft )
No specific	Torque wrench: range to between 165.00 and 135.00 m.N (121.68 and 99.56 lbf.ft )
No specific	Torque wrench: range to between 286.00 and 234.00 m.N (210.91 and 172.57 lbf.ft )
No specific	Torque wrench: range to between 330.00 and 270.00 m.N (243.36 and 199.12 lbf.ft )
No specific	Torque wrench: range to between 0.11 and 0.09 m.daN (9.73 and 7.96 lbf.in )
No specific	Torque wrench: range to between 0.294 and 0.237 m.daN (26.02 and 20.97 lbf.in )
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 0.68 m.daN (69.91 and 60.18 lbf.in )
No specific	Torque wrench: range to between 1.41 and 1.30 m.daN (124.78 and 115.04 lbf.in )
No specific	Torque wrench: range to between 1.90 and 1.63 m.daN (14.01 and 12.02 lbf.ft )
No specific	Torque wrench: range to between 2.11 and 1.8 m.daN (15.56 and 13.27 lbf.ft )
No specific	Torque wrench: range to between 3.16 and 2.43 m.daN (23.30 and 17.92 lbf.ft )
No specific	Torque wrench: range to between 3.2 and 2.9 m.daN (23.60 and 21.39 lbf.ft )
No specific	Torque wrench: range to between 5.9 and 5.31 m.daN (43.51 and 39.16 lbf.ft )
No specific	Torque wrench: range to between 5.9 and 5.4 m.daN (43.51 and 39.82 lbf.ft )
No specific	Torque wrench: range to between 10.7 and 9.7 m.daN (78.91 and 71.53 lbf.ft )
636-1000-31GSE	1	BEAM SUPPORT ENGINE MOUNT
636-1000-32GSE	1	BLOCKING DEVICE - AFT ENGINE MOUNT PIN
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
98D71203014000	1	TORQUE WRENCH SET CFM
98N7100H001-000	1	THRUST REVERSER HOLD OPEN STRUT
98N7100H005-000	1	T/R AXIAL LOCATOR
98N7830H013-000	1	THRUST REVERSER OPEN PUMP.
ALT71000001	1	ELECTRICAL HOIST KIT

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP1041)	isopropyl alcohol
(Material No.03QEA1)	Dry lubricant-Anti Friction - -

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

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
38	E-SEAL	AIPC 36-11-49-05-030
106	SEAL	AIPC 80-12-49-01-080

E. 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 12-13-24-612-804-A	Integrated Drive Generator (IDG) Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check
TASK 12-13-79-610-802-A	Draining of the Accessory Gearbox (AGB)
TASK 12-13-79-610-805-A	Check of the Oil Level and Replenishing
TASK 12-13-79-610-808-A	Draining of the Oil Tank
TASK 20-28-00-912-802-A	Electrical Bonding - General Maintenance Procedure
TASK 22-97-00-710-001-A	Operational Test of the LAND CAT III Capability
TASK 24-21-00-210-808-A	Check IDG Oil Level and Differential Pressure Indicator
TASK 24-21-00-710-805-A	Operational Test of the IDG Disconnect and Reconnect Function - Engine Static
TASK 24-21-00-710-805-A-01	Operational Check of Integrated Drive Generator (IDG) Disconnect and Reconnect Function
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 29-11-00-710-001-A	Operational Test of the Green Hydraulic System
TASK 29-13-00-710-002-A	Operational Test of the Yellow Hydraulic System
TASK 29-14-00-614-001-A	Depressurization of the Hydraulic Reservoirs
TASK 31-36-00-740-014-A	Update of the Engine Hours and Cycles in the Flight Data Interface and Management Unit (FDIMU)
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 36-11-49-400-827-A	Installation of the Environmental Control System (ECS) Ducts from the Engine Case Ports to the Pylon Connections
TASK 36-11-49-400-831-A	Installation of the Indicating Tubes on the Environmental Control System (ECS) Ducts
TASK 54-57-22-000-815-A	Removal of the Rear Mount Fairing (RMF) Door
TASK 54-57-22-400-815-A	Installation of the Rear Mount Fairing (RMF) Door
TASK 70-24-00-910-814-A	Standard Torque Recommendations
TASK 71-00-00-700-805-A	Dry-Motoring Check
TASK 71-00-00-710-813-A	Vibration Check
TASK 71-00-00-710-814-A	Accel Check
TASK 71-00-00-710-816-A	Power Assurance Check
TASK 71-00-00-790-805-A	Fuel or Hydraulic or Oil Leakage Limits
TASK 71-00-00-790-810-A	Pneumatic Leak Test of the Engine EBU Air Ducts
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 71-13-11-820-802-A	Adjustment of the Fan Cowl Doors Clearance
TASK 71-13-13-820-801-A	Adjustment of the Fan Cowl Door Latches
TASK 71-21-11-200-802-A	Inspection of the Forward Engine Mount System
TASK 71-22-11-200-805-A	Inspection of the Aft Engine Mount System
TASK 72-00-00-630-802-A	Depreservation of an Engine
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 73-11-46-400-802-A	Installation of the Main Fuel Line from the Pylon to the Fuel Pump
TASK 73-11-49-400-804-A	Installation of the Fuel Return Hose from the Fuel Return Valve (FRV) to the Pylon
TASK 73-21-50-860-801-A	Programming of the Data Entry Plug (DEP)
TASK 73-29-00-710-802-A	FADEC Test (Menu Mode)
TASK 73-29-00-710-804-A	Weight Configuration (Menu Mode)
TASK 73-29-00-740-802-A	Actuators Test (Menu Mode)
TASK 73-29-00-740-803-A	Idle Test (Menu Mode)
TASK 73-29-00-740-804-A	Thrust Reverser Cycling Test (Menu Mode)
TASK 73-29-00-740-809-A	Read the LRU Identification Report (Menu Mode)
TASK 73-29-00-740-810-A	Entry of the Engine Serial Number (ESN) (Menu Mode)
TASK 78-30-00-040-807-A	Deactivation of the Thrust Reverser System for Nacelle Maintenance (ICU)
TASK 78-30-00-440-807-A	Reactivation of the Thrust Reverser System after Nacelle Maintenance (ICU)
TASK 78-32-11-820-801-A	Adjustment of the Thrust Reverser Cowl Doors Clearance
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 78-36-41-820-802-A	Adjustment of the Thrust Reverser Cowl Latch Tension
TASK 78-36-45-400-801-A	Installation of the Thrust Reverser Hinge Access Panels
TASK 78-36-51-400-802-A	Installation of the Thrust Reverser Cowl Opening System
TASK 79-36-00-220-801-A	Detailed Inspection of the Oil Debris Monitoring System (ODMS) Sensor for Debris
TASK 80-11-05-600-803-A	Servicing of the Pneumatic Air Starter
NTM 518000
NTM 545390
TASK 05-59-00-00	SPECIAL FLIGHTS - DESCRIPTION AND OPERATION
Hydraulic Fittings
Adhesive Tape and Cover Protection
Forward Engine Mount
Aft Engine Mount
Cover Protector
Bootstrap with Electrical Hoist Kit
Bootstrap with Manual Hoist Kit
Bootstrap Beam before Engine Installation with Manual Hoist Kit
Engine Mount Blocking Device
Shears Pins
Engine Installation Workflow
TR V-Blade
Engagement of the Pylon Shear Pin
Ball Lock Pins
Link Nominal Position
Strut 1
Power Plant Interface
Pylon Fuel Drain Line
Right Electrical Bonding
TRU Connectors
ECS duct
Hold Open Brace and Hold Open Strut
Opening of the T/R Cowl Doors
T/R and Fan-Cowl HOR Engine-Fitting on the Left Side
T/R and Fan-Cowl HOR Engine-Fitting on the Right Side
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
TASK 29-11-51-860-040-A	Hydraulic Maintenance Procedure after an Engine Installation (with Engine Pump Installed) or after an Engine Pump Installation
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
TASK 29-13-51-860-001-A	Hydraulic Maintenance Procedure after an Engine Installation (with Engine Pump Installed) or after an Engine Pump Installation

3. Job Set-up
Subtask 71-00-51-861-053-A

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

Subtask 71-00-51-941-055-A

B. 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) 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.
(4) 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 levelled before you install the engine.

(5) Make sure that the WARNING NOTICE(S) is in position on the HP ground connector to tell persons not to pressurize the pneumatic system.
(6) Make sure that the 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).
(7) On the center pedestal, on FLAPS panel 114VU:
(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.

Subtask 71-00-51-860-059-A

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 Low Pressure (LP) valve is shown closed.

Subtask 71-00-51-860-065-A

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). Make sure that the WARNING NOTICE(S) is 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) 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 71-00-51-865-064-A

E. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

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 71-00-51-865-065-A

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 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 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.

F. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

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 71-00-51-420-082-A

G. Get Access

CAUTION: MAKE SURE THAT THERE IS NO CONTACT BETWEEN THE ENGINE AND THE TOOL.

(1) Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position.
(2) Make sure that the fan cowl doors are open (Ref. AMM TASK 71-13-00-010-803).
(3) If installed, remove the strut 1 panels (Ref. AMM TASK 72-24-03-000-801).
(4) Make sure the Thrust Reverser (T/R) is unserviceable (Ref. AMM TASK 78-30-00-040-807).
(5) Make sure that T/R cowls are open up to max position (Ref. AMM TASK 78-36-00-010-806).
(6) Make sure that HOS, HOB and 98N7100H005-000 T/R AXIAL LOCATOR are in position.
(7) Make sure that the pylon fire seal landing (RHS) is removed.

Hydraulic Fittings

(8) Make sure that the forward and aft bootstraps are correctly installed (beams, hoists, dynamometers) for the manual hoist kit or the Instrumented shackles and the electrical hoists for the electrical hoist kit. Refer to the manufacturer's instructions.

NOTE: Make sure that the forward beam of the bootstraps turns freely.

(9) Make sure that the Rear Mount Fairing (RMF) assembly (473AR/AL) is removed (Ref. AMM TASK 54-57-22-000-815).
(10) Remove the 636-1000-31GSE BEAM SUPPORT ENGINE MOUNT from the engine mounts. Refer to the manufacturer's notice.

Subtask 71-00-51-250-051-C

H. Check Before Installation

Adhesive Tape and Cover Protection

CAUTION: DO A DETAILED VISUAL INSPECTION OF THE FORWARD AND AFT ENGINE MOUNTS AND ALL PARTS THAT ATTACH THE MOUNTS. THE PARTS MUST BE IN GOOD CONDITION. IF THE PARTS ARE NOT IN GOOD CONDITION, FAILURE OF THE MOUNTS CAN OCCUR.

(1) Do the inspection of the forward and aft engine mounts and all parts that attach the mounts:
(a) Carefully clean the pylon and mounts mating faces, the shear or locating pin holes and the fastener holes with isopropyl alcohol (Material No.CP1041) .
(b) Do an inspection of the forward engine mount (Ref. AMM TASK 71-21-11-200-802).
(c) Do an inspection of the aft engine mount (Ref. AMM TASK 71-22-11-200-805).
(d) Clean all the components attaching the mounts (bolts, nuts, washers, retainers and screws) with the isopropyl alcohol (Material No.CP1041) .

Forward Engine Mount

Aft Engine Mount

(e) Do the inspection of the bolts, nuts and washers of the forward mount:
1 Do the visual inspection of the bolts (88), nuts (81), washers (82) and (89), retainers (80), (83), (87) and (90) and screws (84) and (86) of the forward mount assembly for damage as wear, cracks, corrosion, damaged thread.
2 Corrosion and damaged threads are not permitted. Replace the damaged parts.
3 Cracks are not permitted. Replace the damaged parts.

NOTE: If you use new engine mounts bolts, screws, washers, nuts, retainers, the inspection is not required.

(f) Do the inspection of the bolts, nuts and washers of the aft mount:
1 Do the visual inspection of the bolts (93) and (98), barrel nuts (97) and nuts (99), washers (94) and (100) and retainers (95) and (96) of the aft mount assembly for damage as wear, cracks, corrosion, damaged thread.
2 Corrosion and damaged threads are not permitted. Replace the damaged parts.
3 Cracks are not permitted. Replace the damaged parts.

NOTE: If you use new engine mounts bolts, washers, nuts, retainers, the inspection is not required.

(g) Do an eddy current inspection of the forward and aft mount bolts (88) and (93) NTM 545390 or a fluorescent inspection NTM 518000:

No cracks are permitted.

NOTE: If the bolts are new or CMM inspected, then eddy current or fluorescent inspection is not required.

(h) Do a running torque check on each of the 25.4 mm (1.0 in.) diameter engine forward mount self-lock nuts (81) as follows:
1 Apply Dry lubricant-Anti Friction - - (Material No.03QEA1) to the threads of the bolt (88).
2 Install the nut (81) on the bolt (88) and tighten until a minimum of two full threads show on the other side of the nut (81).
3 Use the torque wrench to loosen the nut (81). Measure the breakaway torque. It must be 10.2 m.N (90.3 lbf.in) minimum.
4 If the breakaway torque is less than 10.2 m.N (90.3 lbf.in), install a new nut (81).
5 Again install the nut (81) on the bolt (88) and tighten until a minimum of two full threads show on the other side of the nut (81).
6 Use the torque wrench to tighten the nut (81). Measure the locking torque. It must be 90.4 m.N (66.7 lbf.ft) maximum.
7 If the locking torque is more than 90.4 m.N (66.7 lbf.ft), install a new nut (81).

NOTE: If you use new nut (81), the running torque inspection is not required.

(i) Do a running torque check on each of the 22.2 mm (0.9 in.) diameter engine rear mount barrel nuts (97) as follows:
1 Apply the Dry lubricant-Anti Friction - - (Material No.03QEA1) to the threads of the bolt (93).
2 Install the barrel nut (97) on the bolt (93) and tighten until a minimum of two full threads show on the other side of the barrel nut (97).
3 Use the torque wrench to loosen the bolt (93). Measure the breakaway torque. It must be 7.9 m.N (69.9 lbf.in) minimum.
4 If the breakaway torque is less than 7.9 m.N (69.9 lbf.in), install a new barrel nut (97).
5 Again install the barrel nut (97) on the bolt (93) and tighten until a minimum of two full threads show on the other side of the barrel nut (97).
6 Use the torque wrench to tighten the bolt (93). Measure the locking torque must be 67.8 m.N (50.0 lbf.ft) maximum.
7 If the locking torque is more than 67.8 m.N (50.0 lbf.ft), install a new barrel nut (97).

NOTE: If you use new barrel nut (97), the running torque inspection is not required.

NOTE: Inspection is to be performed before installation on the pylon.

(2) Do a check of the visible part of the pylon for correct condition.
(3) Do a check of the cowling for correct condition.

CAUTION: YOU MUST REPLACE CONTACTS THAT SHOW WEAR AND TEAR SIGNS (HOLES, SCRATCHES, DISCOLORATION, TEARS AND PITTED MARKS).

(4) Do a check of the electrical connectors of the aft and forward junction boxes for correct condition.
(5) Install the 956A7610P01 COVER, PROTECTOR - 8 O-CLOCK OGV ARM on the 8 O'clock OGV arm.
(6) Put the TAPE - ADHESIVE on struts 2, 3, 4 and 5.
(7) Install the MAT - PROTECTIVE at the lower T/R strut.

Cover Protector

Subtask 71-00-51-869-052-A

I. If some equipment is not installed on the new engine, remove it from the removed engine. Then install it on the new engine.

4. Procedure
Subtask 71-00-51-480-065-A

A. Prepare the Power Plant for Installation with the Bootstrap System CFM or Bootstrap Electrical Hoist Kit

Bootstrap with Electrical Hoist Kit

Bootstrap with Manual 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) Make sure that the 98D71203010000 BOOTSTRAP SYSTEM CFM beam is fully to the stop position with worm screw not apparent ("-1" on the scale located at the bootstrap beam).

Bootstrap Beam before Engine Installation with Manual Hoist Kit

(2) Align the cradle with the bootstrap chains hoisting points.
(3) Remove the forward/rear mount holding beams, if installed.
(4) Attach the bootstrap to the cradle.
(5) Install the Blocking Device 636-1000-32GSE BLOCKING DEVICE - AFT ENGINE MOUNT PIN on the aft engine mount.

Engine Mount Blocking Device

(6) Apply Dry lubricant-Anti Friction - - (Material No.03QEA1) on the following items:

Shears Pins

(a) On the shear pins (105)
(b) On the shear pins (106).
(7) Disconnect the cradle from the stand 956A7644 STAND, SHIPPING - ENGINE ASSEMBLY.
(8) Use the bootstrap chains for Manual Hoist Kit 98D71203010000 BOOTSTRAP SYSTEM CFM or the service desk display (for Electrical Hoist Kit ALT71000001 ELECTRICAL HOIST KIT) to equally lift the cradle off the stand.

Subtask 71-00-51-980-050-A

B. Monitor the items that follow when the bootstrap hoists are used to raise the power plant up to the pylon:

Mating surfaces
Front mount engagement
Rear mount engagement
Engine right side harness, tube and hose connections clearance
Engine left side harness, tube and hose connections clearance
ECS elbow and the aft engine mount
Aft Pylon Fairing (APF) and the exhaust
Forward pylon fairing and the inlet.

Subtask 71-00-51-820-053-A

C. Raise the bootstrap hoists equally to align the power plant mounts and monitor the indications on the dynamometers for Manual Hoist Kit 98D71203010000 BOOTSTRAP SYSTEM CFM or on the service desk display (for Electrical Hoist Kit ALT71000001 ELECTRICAL HOIST KIT.
(1) Do not exceed the mount limits:
(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 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 the Instrumented shackle 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 the Instrumented shackle ALT71000001 ELECTRICAL HOIST KIT.

Subtask 71-00-51-820-054-A

D. Hoist the Engine

Engine Installation Workflow

TR V-Blade

CAUTION: MAKE SURE THAT THE V-BLADE CORRECTLY ENGAGES INTO THE FAN CASE V-GROOVE. IF THE V-BLADE DOES NOT ENGAGE CORRECTLY INTO THE FAN CASE V-GROOVE, DAMAGE TO THE EQUIPMENT CAN OCCUR.

(1) Make sure that the top of the V-blade on the T/Rs correctly engages with the V-groove on the engine fan case.

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.

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

(2) Hoist the engine up to the pylon contact and make sure that the shear pins slide correctly.

NOTE: This sequence and the number of steps are given for information. At any time during the lift, you must ensure there is no interference between the engine and pylon parts, on FAN and core compartment.

(a) Lift the engine.
(b) Move the engine aft.
(c) Lift the engine.
(d) Move the engine aft.
(e) Lift the engine until to start to engage the pylon shear pins.
(f) If necessary, slowly turn the assembly nose of the forward mount down by few degrees angle around the horizontal axis to make the engine mount strictly horizontal and engage the pylon shear pins in the forward engine mount.
(g)

Engagement of the Pylon Shear Pin

(h) Continue to lift the engine until the engine mounts are in contact with the pylon plates.
(3) Make sure that the engine is correctly positioned.

Subtask 71-00-51-480-066-A

E. Installation of the Ball Lock Pins.

Ball Lock Pins

(1) Install the ball pins on the forward engine mount. Refer to the manufacturer's instructions.

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

Subtask 71-00-51-420-087-B

F. Installation of the Forward and Aft Engine Mounts
(1) On the forward mount (85):

Forward Engine Mount

(a) Apply Dry lubricant-Anti Friction - - (Material No.03QEA1) pon the following items:

Under the bolts heads (88)
On the screws (84) and nuts threads (81)
On both faces of the washers (82) and (89).

(b) Install the upper retaining plate (90), the washers (89) and the bolts (88).
(c) Install the lower retaining plate (83), the washers (82), the nuts (81) and the locking plate (80).
(d) Install and TORQUE the screws (84) to between 4.70 and 3.70 m.N (41.59 and 32.74 lbf.in )

.
(e) Install and TORQUE the four head bolts (88) following the sequence installation A-B-C-D to between 286.00 and 234.00 m.N (210.91 and 172.57 lbf.ft )

intermediate value (equal 50 percent of final torque).

NOTE: This is not the FINAL TORQUE.

(2) On the aft mount (101):

Aft Engine Mount

(a) Apply Dry lubricant-Anti Friction - - (Material No.03QEA1) on the following items:

Under the bolts heads (93)
On the screws (91) and the threads of the barrel nuts (97)
On both faces of the washers (94).

(b) Install the barrel nuts (97) and the retainer (96).

CAUTION: INSTALL THE BARREL NUT WITH THE ROUNDED SIDE UP. IF NOT, DAMAGE TO THE BARREL NUT CAN OCCUR.

1 Check that the barrel nut is in good position and orientation.
(c) Install the bolts (93) through the washers (94) and pylon locking plates (95).
1 Check that the washers are in good position to have the chamfer on the top (under the screw head).
(d) TORQUE the four head bolts (93) following the sequence installation E-F-G-H to between 165.00 and 135.00 m.N (121.68 and 99.56 lbf.ft )

intermediate value (equal to 50 percent of final torque).

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.

(e) Final TORQUE the four head bolts (93) following the sequence installation E-F-G-H to between 330.00 and 270.00 m.N (243.36 and 199.12 lbf.ft )

.
(f) Install the locking plate (92).
(g) Install and TORQUE the screws (91) to between 4.70 and 3.70 m.N (41.59 and 32.74 lbf.in )

.
(h) Install the bolts (98), the washers (100) and the nuts (99).
(i) TORQUE the bolts (98) to between 66.90 and 55.70 m.N (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.

(j) Install two cotter pins (102).

NOTE: If necessary, loosen the nut to ensure that the pins fit the hole of the pin/screw and the nut.

(k) Remove the Blocking Device 636-1000-32GSE BLOCKING DEVICE - AFT ENGINE MOUNT PIN on the rear mount.
(l)

Link Nominal Position

Subtask 71-00-51-080-054-A

G. Removal of the Bootstrap System CFM or Bootstrap Electrical Hoist Kit

(1) Remove the bootstrap from the engine (Refer to the manufacturer's instructions):
(a) Disconnect the cradle from the engine.
(b) Lower the cradle with the help of the bootstrap.
(c) Disconnect the cradle from the bootstrap.
(d) Remove the front and rear bootstrap beams.

Subtask 71-00-51-420-084-A

H. Final Torque of the Forward Engine Mounts.
(1) Finalize the tightening of the forward engine mounts with 98D71203014000 TORQUE WRENCH SET CFM:

(a) TORQUE the four head bolts following the sequence installation A-B-C-D to between 421.83 and 345.13 lbf.ft (57.19 and 46.79 m.daN )

.
(b) Install upper locking plates (87).
(c) Install and TORQUE screws (86) to between 41.59 and 32.74 lbf.in (0.47 and 0.37 m.daN )

Subtask 71-00-51-080-055-A

I. Removal of the Ball Lock Pins

Ball Lock Pins

(1) Remove the Ball Lock Pin in the right and the left side centering pins holes for FWD engine mounts.

Subtask 71-00-51-420-091-A

J. Installation of the Strut 1

Strut 1

Adhesive Tape and Cover Protection

(1) Install the strut 1 (31) and (32) (Ref. AMM TASK 72-24-03-400-801).
(a) Remove the TAPE - ADHESIVE from the segment shrouds 1, 2, 3, 4 and 5.

Subtask 71-00-51-020-090-A

K. Remove the 956A7610P01 COVER, PROTECTOR - 8 O-CLOCK OGV ARM from the 8 O'Clock OGV arm.

Adhesive Tape and Cover Protection

Subtask 71-00-51-020-139-A

L. Remove the 956A7314G03 SET, LIFTING BRACKET - TURBINE REAR FRAM from the turbine rear frame on the left and the right of the engine.

Subtask 71-00-51-020-101-A

M. Remove the 956A6046 ADAPTER, PLATE AND SPHERICAL JOINT - FAN MODULE on the fan frame (hoisting tool) on the left and the right of the engine.

Subtask 71-00-51-420-088-A

N. Connection of the Power Plant Interfaces (Left Side)

Power Plant Interface

(1) Connect 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) Connect the Fuel Return Valve (FRV) tube (68):
1 Installation of the gasket and the four bolts (67):
a Follow (Ref. AMM TASK 73-11-49-400-804).
(b) Connect the main fuel line (65):
1 Installation of the gasket and the four bolts (66) to maintain the fuel line:
a Follow (Ref. AMM TASK 73-11-46-400-802).
(2) Connect the 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) Connect the suction hose (63):
1 Connect the suction hose (63) and tighten it with your hand.
(b) Connect the pressure hose (62):
1 TORQUE the pressure hose (62) to between 10.7 and 9.7 m.daN (78.91 and 71.53 lbf.ft )

. Do the triple TORQUE procedure (Ref. AMM TASK 70-24-00-910-814).
2 Make sure that the pressure hose (62) is not in contact with the suction hose (63).
(c) Connect the case drain (64):
1 TORQUE the case drain (64) to between 3.16 and 2.43 m.daN (23.30 and 17.92 lbf.ft )

. Do the triple TORQUE procedure (Ref. AMM TASK 70-24-00-910-814).
(3) Connect the starter air duct (60):
(a) Put a new AIPC 80-12-49-01-080 SEAL (106) in position on the flange of the pylon duct elbow.
(b) Align the upper flange of the starter air duct (60) with the flange of the pylon duct elbow.
(c) Assemble the V-retainer coupling (61) around the two flanges and tighten the nut with your hand.
(d) TORQUE the upper V-retainer coupling (61) as follows:
1 TORQUE the nut on the V-retainer coupling (61) to between 1.41 and 1.30 m.daN (124.78 and 115.04 lbf.in )

.
2 Lightly tap around the outer diameter of the V-retainer coupling (61) with the MALLET - PLASTIC. Do not hit the latch mechanism on the V-retainer coupling (61).
3 TORQUE the nut on the V-retainer coupling (61) to between 1.41 and 1.30 m.daN (124.78 and 115.04 lbf.in )

a second time.
(4) Connect the electrical connectors:
(a) Connect the bonding straps (69) from the pylon on the brackets located on the rear face of the inlet (Ref. AMM TASK 20-28-00-912-802).
(b) TORQUE the bolt (105) to between 74.34 and 67.26 lbf.in (0.84 and 0.76 m.daN )

.
(c) Check the electrical bonding:
1 Measure the resistance between the ground strap lug and the inlet cowl bracket and between the ground strap lug and the pylon bracket with the OHMMETER MULTIRANGE. Make sure that the resistance value is not more than 0.5 milliohms.
(5) Get access to the core compartment:

Pylon Fuel Drain Line

Hydraulic Fittings

(a) Connect the two pylon fuel drain lines:
1 TORQUE the two drain lines to between 5.9 and 5.31 m.daN (43.51 and 39.16 lbf.ft )

. Do the triple TORQUE procedure (Ref. AMM TASK 70-24-00-910-814).
(b) On ENGINE 1 only:
1 Connect the hydraulic tank pressurization line (56):
a TORQUE to between 3.2 and 2.9 m.daN (23.60 and 21.39 lbf.ft )

. Do the triple TORQUE procedure (Ref. AMM TASK 70-24-00-910-814).
(c) On ENGINE 2 only:
1 On the hydraulic tank pressurization line (56) make sure that the cap is torqued:
a TORQUE the cap of the hydraulic tank pressurization line (56) to between 2.11 and 1.8 m.daN (15.56 and 13.27 lbf.ft )

Subtask 71-00-51-420-089-A

O. Connection of the Power Plant Interfaces (Right Side)

Right Electrical Bonding

TRU Connectors

(1) Connect the electrical connectors.
(a) Connect the RHS bonding strap (5). (Ref. AMM TASK 20-28-00-912-802)
(b) TORQUE the nut (6) to between 74.34 and 65.49 lbf.in (0.84 and 0.74 m.daN )

.
(c) Check the electrical bonding.
1 Measure the resistance between the ground strap lug and the inlet cowl bracket and between the ground strap lug and the pylon bracket with OHMMETER MULTIRANGE. Make sure that the resistance value is not more than 0.5 milliohms.
(d) Connect the 6 TRU harnesses connectors:

Harness 4062VC-A connector (10)
Harness 4062VC-B connector (11)
Harness 4063VC-A connector (14)
Harness 4063VC-B connector (15)
Harness 4063VC-C connector (16)
Harness 4063VC-D connector (17)

(e) Push the following harnesses in the top half of the clamps (12):

4062VC-A
4062VC-B
4063VC-B
4063VC-D

(f) Push the following harnesses in the top half of the clamps (13):

4063VC-A
4063VC-C

(g) Install the 2 TRU harness clamps (12) and (13).
1 TORQUE the 2 screws (18) and (19) to between 0.294 and 0.237 m.daN (26.02 and 20.97 lbf.in )

.
(h) Connect the IDG harnesses to the terminal block (24).
1 Install the cables (21) from the terminal (use the mark written on the cables (N1, T1, T2 and T3)).
2 Install the four nuts (25).
3 TORQUE the nuts to between 1.90 and 1.63 m.daN (14.01 and 12.02 lbf.ft )

.
4 Install the terminal cover (26) on the shield and install the three bolts (27).
5 TORQUE the three bolts (27) to between 0.11 and 0.09 m.daN (9.73 and 7.96 lbf.in )

.
6 Install the clamping device (22).
7 Install the 2 bolt (28) that maintain the clamping device (22).
8 TORQUE the 2 bolts (28) to between 0.79 and 0.68 m.daN (69.91 and 60.18 lbf.in )

.
(i) Connect the ten electrical connectors 405VC-A, 408VC-A, 406VC-A, 407VC-A, 404VC-A, 402VC-A, 403VC-A, 409VC-A and 401VC-A at the pylon junction box.

Power Plant Interface

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

Hydraulic Fittings

(a) Connect the pneumatic ECS duct (Ref. AMM TASK 36-11-49-400-827).

ECS duct

1 Remove all the COVER - PROTECTION from the openings, tubes and hoses.
2 Install the new AIPC 36-11-49-05-030 E-SEAL (38) in the opening of the lower bleed elbow.
3 Put the ECS duct (37) in position adjacent to the lower bleed elbow.
4 Install the V-band clamp (39) to connect the ECS duct to the lower bleed elbow as follows:
a Loosely assemble the V-band clamp (39) around the flange of the ECS duct and lower bleed elbow.
b TORQUE the nut on the V-band clamp (39) to between 125 and 115 lbf.in (1.41 and 1.30 m.daN )

.
c Lightly tap around the outer diameter of the V-band clamp (39) with a MALLET - PLASTIC. Do not hit the latch mechanism on the V-band clamp (39).
d TORQUE the nut on the V-band clamp (39) to between 125 and 115 lbf.in (1.41 and 1.30 m.daN )

a second time.
(b) Install the forward fire seal.
1 Engage harnesses in the fire seal (44).
2 Install the fire seal (44).
3 Install the pylon seal land plate (43):
a Install the 4 screws.
b TORQUE the 4 screws to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )

.
(4) Connect the two sensor lines (41) and (42).
(5) Connect the HPV/PRV harness (40).
(6) Connect the HPV upstream (BMPS) and the HPV downstream (BPS) sense lines (55) and (57) (Ref. AMM TASK 36-11-49-400-831).

CAUTION: MAKE SURE THAT THE HPV UPSTREAM AND DOWNSTREAM SENSE LINES ARE CORRECTLY INSTALLED. IF THEY ARE NOT CORRECTLY INSTALLED, DAMAGE CAN OCCUR.

(7) TORQUE the HPV upstream (BMPS) to between 5.9 and 5.4 m.daN (43.51 and 39.82 lbf.ft )

. Do the triple TORQUE procedure (Ref. AMM TASK 70-24-00-910-814).
(8) TORQUE the HPV downstream (BPS) to between 3.2 and 2.9 m.daN (23.60 and 21.39 lbf.ft )

. Do the triple TORQUE procedure (Ref. AMM TASK 70-24-00-910-814).

Subtask 71-00-51-860-060-A

P. Put the aircraft back to its initial configuration.
(1) Install the Rear Mount Fairing (RMF) assembly (473AL/AR) (Ref. AMM TASK 54-57-22-400-815).
(2) Make sure that the transport stand is in the lower position.
(3) Make sure that there is adequate clearance between the power plant and the transport stand to remove the transport stand.
(4) Remove the transport stand from the area.
(5) Examine the assembly for foreign objects, damage and correct assembly.

Subtask 71-00-51-080-056-A

Q. Removal of the Fan-Cowl Hold-Open Braces

Hold Open Brace and Hold Open Strut

(1) Manually hold the left fan-cowl door.
(2) Remove the 98N7100H002-001 HOLD OPEN BRACE - FAN COWL from the left side of the pylon.
(3) Put the forward and aft Hold Open Rods (HORs) of the fan cowl door in position to hold the weight of the fan cowls (Ref. AMM TASK 71-13-00-010-803).
(4) Do Para. 4.S.(1) thru Para. 4.S.(3) again to remove the 98N7100H002-001 HOLD OPEN BRACE - FAN COWL from the right side of the pylon.

Subtask 71-00-51-080-057-A

R. Removal of the Left and Right Hold-Open Struts

Hold Open Brace and Hold Open Strut

Opening of the T/R Cowl Doors

T/R and Fan-Cowl HOR Engine-Fitting on the Left Side

T/R and Fan-Cowl HOR Engine-Fitting on the Right Side

(1) Remove the TIE WRAP(S) that attached the T/R Cowl Opening System (COS) to the left T/R cowl door.
(2) Connect the T/R COS to the engine (Ref. AMM TASK 78-36-51-400-802).
(3) Connect the 98N7830H013-000 THRUST REVERSER OPEN PUMP.:

CAUTION: MAKE SURE THAT YOU USE THE THRUST REVERSER OPEN PUMP 98N7830H013-000. IF YOU DO NOT OBEY THIS INSTRUCTION, OIL LEAKAGE CAN OCCUR.

(a) Put the 98N7830H013-000 THRUST REVERSER OPEN PUMP. in position.
(b) Connect the hose of the 98N7830H013-000 THRUST REVERSER OPEN PUMP. to the opening actuator manifold (113) on the T/R half.
(c) Make sure that the 98N7830H013-000 THRUST REVERSER OPEN PUMP. reservoir is filled.
(4) Remove the 98N7100H001-000 THRUST REVERSER HOLD OPEN STRUT:

CAUTION: DO NOT CONNECT THE HOLD OPEN ROD (HOR) BEFORE THE THRUST REVERSER COWL IS OPEN TO 45 DEGREES. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE HOR AND ITS FITTING CAN OCCUR.

(a) Close the valve on the 98N7830H013-000 THRUST REVERSER OPEN PUMP..
(b) Operate the 98N7830H013-000 THRUST REVERSER OPEN PUMP. until to 45 degrees for unloading the T/R cowl door weight on the hold open strut.
(c) Remove the 98N7100H001-000 THRUST REVERSER HOLD OPEN STRUT.
(5) Connect the HOR:
(a) Operate the 98N7830H013-000 THRUST REVERSER OPEN PUMP. until the T/R half is open to 35 degrees.
(b) Disconnect the HOR (112) from the forward frame storage fitting (111).
(c) Move the HOR (112) to the engine fitting.

WARNING: MAKE SURE THAT YOU CONNECT THE HOLD-OPEN ROD TO THE THRUST-REVERSER HOLD-OPEN ROD ENGINE FITTING AND NOT TO THE FAN-COWL HOLD-OPEN ROD ENGINE FITTING. IF YOU DO NOT OBEY THIS INSTRUCTION, THERE IS A RISK OF INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

CAUTION: WHEN YOU ATTACH THE HOR TO ITS FITTING, MAKE SURE THAT THE HOR HOOK DOES NOT HIT THE HOR FITTING. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE HOR FITTING CAN OCCUR.

(d) Connect the HOR (112) to the engine fitting.
1 Operate the 98N7830H013-000 THRUST REVERSER OPEN PUMP. until the HOR (112) locks automatically.
2 POST SPOL BD-TR-17021
Make sure that you can see the green strip indicator of the HOR (112), which shows that the HOR (112) is fully extended and locked.
END OF POST SPOL BD-TR-17021
3 Open the valve on the 98N7830H013-000 THRUST REVERSER OPEN PUMP. to load the HOR (112).
(e) Close the valve on the 98N7830H013-000 THRUST REVERSER OPEN PUMP..
(f) Disconnect the hose of the 98N7830H013-000 THRUST REVERSER OPEN PUMP. from the actuator manifold connector of the T/R half.
(6) Do the Para. 4.T.(1) thru Para. 4.T.(5) again for the right side.

Subtask 71-00-51-820-055-A

S. Adjustment of the T/R Cowl Doors
(1) Do the adjustment of the T/R cowl doors clearance (Ref. AMM TASK 78-32-11-820-801) and the adjustment of the T/R cowl doors latches tension (Ref. AMM TASK 78-36-41-820-802).
(2) Do the adjustment of the fan cowl doors clearance (Ref. AMM TASK 71-13-11-820-802) and the adjustment of the fan cowls door latches (Ref. AMM TASK 71-13-13-820-801).
(3) Keep the fan and reverser cowls opened.

Subtask 71-00-51-612-050-A

T. Check of the Oil Levels
(1) Do a check of the oil levels:
(a) Make sure that the IDG oil level is correct (Ref. AMM TASK 24-21-00-210-808).
(b) Make sure that the starter is serviced with oil before engine run to ensure initial start lubrication. The starter can be serviced with oil either before it is installed on the gearbox or after installation. If unsure of oil quantity in starter fill the starter with oil (Ref. AMM TASK 80-11-05-600-803).

CAUTION: MAKE SURE THAT THE OIL TANK IS FILLED TO THE "MAX" MARK MINUS THREE QUARTS. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE ENGINE CAN OCCUR.

(c) Make sure that the oil tank level is correct. If required, replenish the oil system (Ref. AMM TASK 12-13-79-610-805).
(d) Drain and refill the oil tank and Accessory Gearbox (AGB) if preservation fluid is present in the oil system engine previously preserved for more than 90 days (Ref. AMM TASK 12-13-79-610-802), (Ref. AMM TASK 12-13-79-610-808) and (Ref. AMM TASK 12-13-79-610-805).

Subtask 71-00-51-790-050-A

U. Prepare the Engine for a Leak Check of the Engine Build-up Unit (EBU) and ECS Valves and Ducts.
(1) Do the Leak Check of the NAI valves and Ducts, the ECS valves and ducts, the Engine starter valve and duct (Ref. AMM TASK 71-00-00-790-810).

Subtask 71-00-51-970-050-A

V. Check of the EEC Software
(1) Do a check of the PNs of the EEC software installed on the two EECs to know if they are the same.

NOTE: The EEC software PN is written on a sticker that is on the EEC front panel.

(a) If the EEC software PNs are different, refer to the IPC and program again a minimum of one EEC channel, as necessary.
(2) Make sure that the EEC software have compatible configurations on the two engines (refer to the PIPC).
(a) If the EEC software configurations on the two engines are not compatible, refer to the PIPC and program again the two EEC channels, as necessary.

Subtask 71-00-51-865-066-A

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 DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.

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.

W. Remove the safety clip(s) and the tag(s) and close 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 71-00-51-865-067-A

X. Remove the safety clip(s) and the tag(s) and close 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 71-00-51-861-054-A

Y. Aircraft Maintenance Configuration
(1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).

Subtask 71-00-51-860-062-A

Z. EIS Start Procedure
(1) Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001).

Subtask 71-00-51-740-052-A

AA. Engine Hour and Cycle Data into the Flight Data Interface and Management Unit (FDIMU)
(1) Enter the engine hour and cycle data into the FDIMU for the installed engine (Ref. AMM TASK 31-36-00-740-014).

NOTE: If you go to next subtask, do not de-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).

Subtask 71-00-51-710-050-A

AB. Operational Check of Loop/Squib
(1) Do an operational check of loop/squib (Ref. AMM TASK 26-12-00-710-001).

NOTE: Do not do tasks already completed (energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) and EIS start procedure (Ref. AMM TASK 31-60-00-860-001)).
If you go to next subtask, do not de-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).

Subtask 71-00-51-860-063-A

AC. Aircraft System Configuration
(1) Remove the WARNING NOTICE(S) on 30VU, 50VU, 114VU, 115VU and at HP ground connector.
(2) On the overhead panel, on the ENG section of maintenance panel 50VU:
(a) Push the pushbutton switch of the FADEC GND PWR/1(2) to ON position.

Subtask 71-00-51-710-051-A

AD. FADEC Test

CAUTION: DO A DUAL POWER CYCLE OF THE EEC TO AVOID AN EGT INCREASE DURING THE NEXT TAKE OFF.

CAUTION: LP VALVE SHALL BE FORCED OPEN TO ENSURE A PROPER PRIMING OF THE ENGINE FUEL PUMP DURING THE MOTORING.

(1) Do the tests that follow:

NOTE: If you go to the next test of the subtask, do not de-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) after each test.
If you go to the next test of the subtask, do not close fan cowl doors (Ref. AMM TASK 71-13-00-410-803) after each test.

(a) Do the entry of the Engine Serial Number (ESN) on both EEC channels (Ref. AMM TASK 73-29-00-740-810).

NOTE: Do not do the FADEC test. It will be completed in test (d).

(b) Input the engine-trim balance-weight configuration to EEC memory on one of the EEC channels. The weight configuration will automatically be saved to the other EEC channel (Ref. AMM TASK 73-29-00-710-804).
(c) Do the LRU Identification Report of both channels (Ref. AMM TASK 73-29-00-740-809).
1 Read the data that comes on the multipurpose control and display unit screen and check for consistency with the actual engine configuration:
a Engine thrust rating and type:

These inputs are available on the engine name plate.

b "EEC AS Software" Part Number (SW1):

The P/N is available on the EEC Software identification plate.
Make sure the AS Software PN is the same on the other Channel.

NOTE: Make sure that the intermixability of engines EEC AS software standards is correct (Engine 1 AS Software versus Engine 2 AS Software). Refer to the applicable Service Bulletin.

c "EEC OMAP Software" Part Number (SW2).

NOTE: Make sure the OMAP Software P/N (SW2) is the same on both EEC channels. Refer to IPC to determine the applicable OMAP Software.

d "N1 TRIM":

The N1 trim level (zero through seven) is available on the engine name plate.

e "BUMP".

NOTE: Option will read "Y" or "N" depending on bump availability.

f "ENGINE S/N".

NOTE: The engine serial number is available on the engine data plate.

g "HW CONFIG".

NOTE: The hardware configuration value is available in Table 2 for applicable engine thrust ratings and types (Ref. AMM TASK 73-21-50-860-801).

h "HPT DETERIORATION".

NOTE: Must read "N".

POST SB 73-0021

i "EEC PHM Software" Part Number (SW3).
j "MTC CONFIGURATION".

NOTE: Option will read "SINGLE" or "DUAL".

k Accelerometer configuration.

NOTE: Option will read "NORM", "TCF" or "PX36".

l Aircraft type.

END OF POST SB 73-0021

(d) Do a FADEC Test on both EEC Channels (Ref. AMM TASK 73-29-00-710-802).
(e) Make sure that the T/R cowls are open (Ref. AMM TASK 78-36-00-010-806).
(f) Do the hydraulic maintenance procedure after an engine installation:

NOTE: Do not do tasks already completed (EIS start procedure (Ref. AMM TASK 31-60-00-860-001)).

1 FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
(Ref. AMM TASK 29-11-51-860-040) for the green hydraulic system.
2 FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
(Ref. AMM TASK 29-13-51-860-001) for the yellow hydraulic system.

NOTE: The engine dry motoring test of these two tasks will be done later in the test sequence.

(g) Do a dry motoring check (Ref. AMM TASK 71-00-00-700-805).

CAUTION: ON THE SD, ON THE "FUEL" PAGE, MAKE SURE THAT THE LP VALVE IS OPEN. IF THE VALVE IS NOT OPEN, DAMAGE TO THE ENGINE CAN OCCUR.

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

1KC1/2 (49VU ENGINE / 1(2) / HP FUEL SOV).

2 Do an operational test of the hydraulic pump during the motoring test:
a For Engine 1 (Ref. AMM TASK 29-11-00-710-001).
b For Engine 2 (Ref. AMM TASK 29-13-00-710-002).

NOTE: Make sure the hydraulic pressure is 3000 psi (206.8427 bar) + or - 100 psi (6.8948 bar).

(h) Do an actuator test (Ref. AMM TASK 73-29-00-740-802).

NOTE: Do not do tasks already completed:

Check of the oil quantity (Ref. AMM TASK 12-13-79-610-805).
Check of the drain ports for fuel, oil and hydraulic leaks (Ref. AMM TASK 71-00-00-790-805).
Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-803).

Open the T/R cowl doors (Ref. AMM TASK 78-36-00-010-806).
Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).

(i) Do a check for leaks on the hydraulic, oil and fuel systems (Ref. AMM TASK 71-00-00-790-805).
(j) Do the depreservation (Ref. AMM TASK 72-00-00-630-802).

Subtask 71-00-51-410-056-A

AE. Close the T/R Cowl Doors (Ref. AMM TASK 78-36-00-410-806).

Subtask 71-00-51-020-087-A

AF. Removal of the T/R Axial locator.
(1) Remove the 98N7100H005-000 T/R AXIAL LOCATOR on the Hinge 4.
(a) Refer to the manufacturer's notice.

Subtask 71-00-51-420-101-A

AG. Install the T/R hinge access panel (Ref. AMM TASK 78-36-45-400-801).

Subtask 71-00-51-410-060-A

AH. Make the T/R Serviceable (Ref. AMM TASK 78-30-00-440-807).

Subtask 71-00-51-710-052-A

AI. Tests
(1) Do a dry motoring test during 2 minutes (Ref. AMM TASK 71-00-00-700-805).
(2) Do the T/R cycling test (Ref. AMM TASK 73-29-00-740-804).
(3) Do the idle leak check (menu mode) (Ref. AMM TASK 73-29-00-740-803).
(a) Select APU Bleed OFF.
(b) Select NAI ON for 2 minutes.
(c) Do a check of the IDG system as follows:
1 On the lower ECAM DU, select the ELEC page:
a Make sure that the frequency and voltage indications are correct with engine running.
(4) If the engine is not tested, do a check and cleaning of the oil-debris monitoring-system sensor (Ref. AMM TASK 79-36-00-220-801).
(5) Do the operation test of the IDG disconnect and reconnect (Reset) function (Ref. AMM TASK 24-21-00-710-805).

Subtask 71-00-51-410-057-A

AJ. Open the T/R Cowl Doors (Ref. AMM TASK 78-36-00-010-806).

Subtask 71-00-51-210-053-A

AK. Checks of the ECS, NAI Valves and Duct
(1) Checks for correct sealing of the ECS and NAI valves and duct and remove the aluminium foils (Ref. AMM TASK 71-00-00-790-810).

Subtask 71-00-51-410-058-A

AL. Aircraft System Configuration
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the access platform(s).
(3) Close the T/R cowl doors (Ref. AMM TASK 78-36-00-410-806).

Subtask 71-00-51-440-053-A

AM. Reactivate the T/R (Ref. AMM TASK 78-30-00-440-807).

Subtask 71-00-51-210-054-A

AN. Do a check of the IDG oil level. If required, do a servicing of the IDG (Ref. AMM TASK 12-13-24-612-804).

Subtask 71-00-51-410-059-A

AO. Close the Fan Cowls Doors (Ref. AMM TASK 71-13-00-410-803)

Subtask 71-00-51-860-066-A

AP. System Configuration
(1) If the fault message "EIU1(2)-01XX-NACELLE FAILED OPEN FAULT" has been triggered during the test, do a reset of EIU 1 (2) Circuit Breaker 2KS1 and 2KS2.
(2) 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 71-00-51-710-053-A

AQ. Tests

NOTE: If you go to the next step of the subtask, do not de-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) after each test.

(1) Do a vibration check (Ref. AMM TASK 71-00-00-710-813).

NOTE: A vibration check is not necessary if:
-The engine was tested and accepted in an approved test cell, or
-The engine was previously removed for convenience or time staggering.

(2) Do an accel check (Ref. AMM TASK 71-00-00-710-814).

NOTE: An accel check is not necessary if:
-The engine was tested and accepted in an approved test cell, or
-The engine was previously removed for convenience or time staggering.

(3) Do a power assurance check (Ref. AMM TASK 71-00-00-710-816).

NOTE: A power assurance check is not necessary if:
-the engine was tested and accepted in an approved test cell, or
-the engine was previously removed for convenience or time staggering.

Subtask 71-00-51-860-064-A

AR. Aircraft System Configuration
(1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).

Subtask 71-00-51-862-052-A

AS. De-Energize the Electrical Circuits
(1) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).

Subtask 71-00-51-869-053-A

AT. 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 12:38:44 UTC