W DOC AIRBUS | AMM A320F

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

TASK 71-00-51-000-802-A-01
Removal of the Power Plant (JacXson 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
This task gives the information for the removal of the power plant with the JacXson tool.
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
Torque wrench: range to between 70.00 and 60.00 lbf.in (0.79 and 0.68 m.daN ) T
No specific
Torque wrench: range to between 70.00 and 63.00 lbf.in (0.79 and 0.71 m.daN ) T
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
98D71203013000
1
TORQUE WRENCH SET PW
JXU70
1
JACXSON
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 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
F Door Operating System
F Fuel Draining
F Main Fuel Line
F Power Plant Bonding-Strap
F Power Plant (Engine Right-Side Locator)
F Power Plant (Engine Right-Side Locator)
F Power Plant (Engine Right-Side Locator)
F Power Plant (Engine Right-Side Locator)
F Power Plant (Engine Right-Side Locator)
F ECS Duct Support
F Power Plant (Engine Left-Side Locator)
F Power Plant (Engine Left-Side Locator) - Fuel Hoses
F Power Plant (Engine Left-Side Locator)
F Power Plant (Engine Left-Side Locator)
F JacXson Tool
F Power Plant Engine-Mounts
F Power Plant Engine-Mounts
F Dog Head
3. Job Set-up
Subtask 71-00-51-941-061-A ** ON A/C NOT FOR ALL
A. Safety Precautions
   (1) Make sure that 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).
       1 When the aircraft is on jacks, make sure that it is level before you remove the engine.
   (2) Point the engine intake in the direction of the wind. Attach the aircraft if there are stong changes in the wind direction (+/- 45 degrees) (Ref. AMM TASK 10-20-00-556-001).
Subtask 71-00-51-861-057-A ** ON A/C NOT FOR ALL
B. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
Subtask 71-00-51-740-054-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 the engine hours/cycles.
Subtask 71-00-51-860-071-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 71-00-51-941-058-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 (the ON legend is off).
     (b) Make sure that the ENG 1(2) BLEED pushbutton switch is released (the 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.
   (3) Put a 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 a WARNING NOTICE(S) in position in the cockpit to tell persons not to move the slat and flap control lever.
Subtask 71-00-51-864-057-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 panel 40VU:
     (a) Make sure that the ENG1(2) PUMP pushbutton switches are released (the OFF legends are 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: The engine-1 demountable power-plant (4020KM1) supplies the Green hydraulic system and the engine-2 demountable power-plant (4020KM2) supplies the Yellow hydraulic system.
   (3) Depressurize the reservoir of the applicable hydraulic system (Ref. AMM TASK 29-14-00-614-001).
Subtask 71-00-51-865-076-A ** ON A/C NOT FOR ALL
G. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
49VUANTI ICE/PROBES/AOA/14DA1D04
49VUANTI ICE/PROBES/PITOT/13DA1D02
49VUANTI ICE/RAIN/RPLNT/CAPT1DB1D01
** ON A/C NOT FOR ALL
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B2WE1Q44
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A1WE1Q43
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B2WE2Q42
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A1WE2Q41
** ON A/C NOT FOR ALL
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B2WE1Q43
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A1WE1Q42
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B2WE2Q41
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A1WE2Q40
** ON A/C NOT FOR ALL
122VUANTI ICE/WINDOWS/R4DG2W14
122VUANTI ICE/RAIN/RPLNT/F/O1DB2W11
122VUANTI ICE/WINDOWS/L4DG1X14
122VUANTI ICE/PROBES/2/TAT1DA2Y15
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/1/TAT1DA1Z12
123VUY HYD/ELEC/PUMP3802GXAB06
123VUY HYD/ELEC/ELEC PUMP/NORM3801GXAB03
123VUANTI ICE/L/WHSLD1DG1AF10
123VUANTI ICE/R/WHSLD1DG2AF03
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
49VUFUEL/LP VALVE/MOT1/ENG11QGA08
49VUENGINE/1/FIRE DET/LOOP A7WD1A06
49VUAIR BLEED/ENG 1/CTL2HA1D11
49VUHYDRAULIC/G HYD/PUMP ENG1/CTL1701GKH12
** ON A/C NOT FOR ALL
121VUDCV B/ENG1 PWR SUPPLY103KS1K44
121VUDCV A/ENG1 PWR SUPPLY102KS1K42
121VUENG1/REV/LOCK1EG1N44
121VUICU A/ENG1 PWR SUPPLY22KS1R39
** ON A/C NOT FOR ALL
121VUFUEL/LP VALVE/MOT2/ENG13QGM25
121VUOIL/PRESS/ENG110KC1N40
121VUPHMU/ENG195KS1P44
121VUENGINE/IGN/ENG1/SYS B3JH1P41
121VUENGINE/LATCH DOORS & SLATS/ENG193KS1P39
121VUENGINE/ENG1/FIRE DET/LOOP B8WD1Q38
121VUICU B/ENG1 PWR SUPPLY101KS1R42
** ON A/C NOT FOR ALL
121VUDCV A/ENG1 PWR SUPPLY102KS1N44
121VUDCV B/ENG1 PWR SUPPLY103KS1Q44
121VUENG1/REV/LOCK1EG1R44
121VUICU A/ENG1 PWR SUPPLY22KS1R38
** ON A/C NOT FOR ALL
122VUELEC/GCU/12XU1T26
122VUELEC/IDG1/DISC1XTT24
122VUANTI ICE/ENG/11DN1X10
122VUAIR BLEED/ENG 1/MONG3HA1Z23
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
49VUFUEL/LP VALVE/MOT1/ENG22QGA09
49VUENGINE/2/FIRE DET/LOOP B8WD2A07
49VUAIR BLEED/ENG 2/MONG3HA2D12
** ON A/C NOT FOR ALL
121VUDCV B/ENG2 PWR SUPPLY103KS2K45
121VUDCV A/ENG2 PWR SUPPLY102KS2K43
121VUENG2/REV/LOCK1EG2N45
121VUICU A/ENG2 PWR SUPPLY22KS2R40
** ON A/C NOT FOR ALL
121VUFUEL/LP VALVE/MOT2/ENG24QGM26
121VUOIL/PRESS/ENG210KC2N42
121VUPHMU/ENG295KS2P45
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/LATCH DOORS & SLATS/ENG293KS2P40
121VUENGINE/ENG2/FIRE DET/LOOP A7WD2Q39
121VUHYDRAULIC/Y HYD/PUMP ENG2/CTL3701GDQ36
121VUICU B/ENG2 PWR SUPPLY101KS2R43
** ON A/C NOT FOR ALL
121VUDCV A/ENG2 PWR SUPPLY102KS2N45
121VUDCV B/ENG2 PWR SUPPLY103KS2Q45
121VUENG2/REV/LOCK1EG2R45
121VUICU A/ENG2 PWR SUPPLY22KS2R39
** ON A/C NOT FOR ALL
122VUELEC/GCU/22XU2T27
122VUELEC/IDG2/DISC2XTT25
122VUANTI ICE/ENG/21DN2W10
122VUAIR BLEED/ENG 2/CTL2HA2Z22
** ON A/C NOT FOR ALL
FOR FIN: 101RH (DIRCIDS, 1)
49VUCOM/CIDS/DIR ESS/1150RHG01
** ON A/C NOT FOR ALL
49VUAIR COND/CIDS/SDF/DIR1 ESS15WHC05
** ON A/C NOT FOR ALL
49VUCOM NAV/CIDS/DIR1 ESS150RHG01
** ON A/C NOT FOR ALL
121VUCOM NAV/CIDS/DIR NORM/1151RHM05
** ON A/C NOT FOR ALL
121VUCOM NAV/CIDS/DIR NORM/1151RHM06
** ON A/C NOT FOR ALL
121VUCOM NAV/CIDS/DIR1 NORM151RHM05
** ON A/C NOT FOR ALL
122VUAIR COND/CIDS/SDF/DIR NORM/117WHT17
** ON A/C NOT FOR ALL
FOR FIN: 102RH (DIRCIDS, 2)
49VUCOM/CIDS/DIR ESS/2157RHG02
** ON A/C NOT FOR ALL
49VUCOM/CIDS/DIR ESS/1150RHG01
** ON A/C NOT FOR ALL
49VUAIR COND/CIDS/SDF/DIR2 ESS18WHC06
** ON A/C NOT FOR ALL
49VUCOM DIR ESS/2157RHG02
** ON A/C NOT FOR ALL
49VUCOM NAV/CIDS/DIR2 ESS157RHG02
49VUCOM NAV/CIDS/DIR1 ESS150RHG01
** ON A/C NOT FOR ALL
121VUCOM NAV/CIDS/DIR NORM/2156RHM06
121VUCOM NAV/CIDS/DIR NORM/1151RHM05
** ON A/C NOT FOR ALL
121VUCOM NAV/CIDS/DIR NORM/2156RHM07
121VUCOM NAV/CIDS/DIR NORM/1151RHM06
** ON A/C NOT FOR ALL
121VUCOM NAV/CIDS/DIR2 NORM156RHM06
121VUCOM NAV/CIDS/DIR1 NORM151RHM05
** ON A/C NOT FOR ALL
122VUAIR COND/CIDS/SDF/DIR NORM/214WHT18
Subtask 71-00-51-865-075-A ** ON A/C NOT FOR ALL
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.
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.
H. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/WHC/25DG2W13
122VUANTI ICE/WHC/15DG1X13
122VUANTI ICE/PROBES/PHC/32DA3Y16
122VUANTI ICE/PROBES/PHC/22DA2Y12
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENG 1)
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
49VUENGINE/1/HP FUEL SOV1KC1A01
** ON A/C NOT FOR ALL
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R41
** ON A/C NOT FOR ALL
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R40
** ON A/C NOT FOR ALL
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENG 2)
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
49VUENGINE/2/HP FUEL SOV1KC2A02
** ON A/C NOT FOR ALL
121VUENGINE/ENG2/FADEC B/AND EIU24KS2Q40
** ON A/C NOT FOR ALL
121VUENGINE/ENG2/FADEC B/AND EIU24KS2R41
Subtask 71-00-51-010-060-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 71-00-51-040-053-A ** ON A/C NOT FOR ALL
J. Deactivation of the Trust 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 71-00-51-010-064-A ** ON A/C NOT FOR ALL
K. Get Access
   (1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at engine 1(2).
   (2) Remove the thrust-reverser hinge access-panels on the left and the right sides of the engine (Ref. AMM TASK 78-30-06-000-801).
   (3) Remove the pylon aprons and the profiles on the left and the right sides of the engine (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 permitted 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 to fan-cowl 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 to fan-cowl 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 to get access to the aft engine mounts (Ref. AMM TASK 54-57-22-000-810).
Subtask 71-00-51-420-112-A ** ON A/C NOT FOR ALL
L. 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 instructions.
     (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 71-00-51-020-117-A ** ON A/C NOT FOR ALL
M. 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) Put the two HORs on their thrust reverser storage-brackets.
Subtask 71-00-51-020-118-A ** ON A/C NOT FOR ALL
N. Remove the door operating-system actuators and the fittings.
F 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: 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 the six washers (8) that attach the fitting (2) and the actuator (1) assembly to the engine.
Subtask 71-00-51-420-113-A ** ON A/C NOT FOR ALL
O. Install the fan case adapters on the right and left sides.
   (1) Refer to the tool manufacturer's instructions.
NOTE: The fan case adapters are parts of the PWA211430 STAND, TRANSPORT.
Subtask 71-00-51-420-114-A ** ON A/C NOT FOR ALL
P. Installation of the Fan-Cowl Hold-Open Brace
   (1) Install the fan-cowl hold-open brace. Refer to the tool manufacturer's instructions.
     (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 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 part of the 636GSE3009-901 TR HOLD OPEN STRUT tool assembly.

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

Subtask 71-00-51-020-119-A ** ON A/C NOT FOR ALL
Q. 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 71-00-51-420-115-A ** ON A/C NOT FOR ALL
R. Installation of the Thrust-Reverser Seal Compressor
   (1) Refer to the tool manufacturer's instructions.
     (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 71-00-51-680-058-A ** ON A/C NOT FOR ALL
S. 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:
F 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) Remove 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 push and turn the drain plug (3) until it is fully against the fuel manifold.
       2 Make sure that the drain plug (3) is fully against the mating surface on the fuel manifold.
       3 Turn the drain plug (3) until 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 ) T.
   (2) Drain at the main fuel line:
F 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 remove 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 ) T.
     (j) Remove the CONTAINER 5 L (1.32 USGAL).
Subtask 71-00-51-680-059-A ** ON A/C NOT FOR ALL
T. 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 to do the preservation if you operated the engine in the last seven days and you send it to an overhaul facility, or if the engine is in a preservation time period.
Subtask 71-00-51-010-061-A ** ON A/C NOT FOR ALL
U. Get Access
   (1) Remove the two right and left upper fan-exit-fairings (Ref. AMM TASK 72-21-04-000-801).
     (a) Attach the removed fan exit fairings to the engine with TIE WRAP(S) to make sure that they do not move when you lower the engine.
NOTE: A lanyard holds the right and left upper fan-exit-fairings to make sure that 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 71-00-51-020-120-A ** ON A/C NOT FOR ALL
V. 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 electrical bonding strap:
F 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:
F 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:
F 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:
F 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.
F Power Plant (Engine Right-Side Locator) ** ON A/C NOT FOR ALL
   (6) Disconnect the Environmental Control System (ECS):
F 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:
F 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.
F ECS Duct Support ** ON A/C NOT FOR ALL
Subtask 71-00-51-020-121-A ** ON A/C NOT FOR ALL
W. Disconnect the Power Plant Interfaces (Left Side).
   (1) Disconnect the electrical connectors of the AC generator control-harness from the upper pylon-interface-panel receptacles with the PLIERS - JAWED, SOFT.
F 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.
F Power Plant (Engine Left-Side Locator) ** ON A/C NOT FOR ALL
   (3) Disconnect the hydraulic reservoir pressurization-hose.
F 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:
F 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.
F Power Plant (Engine Left-Side Locator) ** ON A/C NOT FOR ALL
   (6) Disconnect the Thrust Reverser Actuation System (TRAS) inhibition cable.
F Power Plant (Engine Left-Side Locator) ** ON A/C NOT FOR ALL
   (7) Disconnect the fuel connections:
F 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:
F 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 71-00-51-220-053-A ** ON A/C NOT FOR ALL
X. 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 71-00-51-840-061-B ** ON A/C NOT FOR ALL
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.
A. Prepare the power plant for the removal.
F JacXson Tool ** ON A/C NOT FOR ALL
   (1) Make sure that the two engine translation beams are in the fully aft position. To do this, turn the aft beam wheel-handle-blocker on the mechanical stop.
   (2) Install the Turbine Exhaust Case (TEC) adapters on the left and right sides.
     (a) Refer to the tool manufacturer's instructions.
NOTE: The TEC adapters are parts of the PWA211430 STAND, TRANSPORT tool.
   (3) Put the arms of the stand in the lower position.
     (a) Refer to the tool manufacturer's instructions.
   (4) Lower the cradle assembly on the engine PWA211430 STAND, TRANSPORT to the lower position (handling position). Refer to the tool manufacturer's instructions.
   (5) Make sure that the cradle is attached to the engine PWA211430 STAND, TRANSPORT.
   (6) Move the PWA211430 STAND, TRANSPORT to the engine area. Put the transport stand below the power plant from the aft side of the aircraft.
WARNING: DURING ALL THE SUBSEQUENT PHASE, MONITOR THE LOADS READ ON THE JACXSON DISPLAY, AND MAKE SURE THAT THE LOADS ARE AS FOLLOWS: - AT THE FORWARD MOUNT: A MAXIMUM OF 3090 DAN (3154 KG) - AT THE AFT MOUNT: A MAXIMUM OF 3350 DAN (3416 KG) OR - AT THE LEFT FORWARD OR RIGHT FORWARD MOUNT: A MAXIMUM OF 1547 DAN (1577 KG) - AT THE LEFT AFT OR RIGHT AFT MOUNT: A MAXIMUM OF 1675 DAN (1708 KG). IF THE LOADS ARE MORE THAN THE SPECIFIED LOAD LIMITS, THE ENGINE CAN FALL. THIS CAN CAUSE DEATH OR INJURY TO PERSONS AND DAMAGE TO THE EQUIPMENT.
WARNING: MAKE SURE THAT NO UNWANTED PRESSURE IS APPLIED TO THE ENGINE OR TO THE JACXSON TOOL. UNWANTED PRESSURE ON THE ENGINE OR ON THE JACXSON TOOL CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
   (7) Move the JXU70 JACXSON from forward side of the aircraft and engage it with the PWA211430 STAND, TRANSPORT:
     (a) Engage the lift adapters in the PWA211430 STAND, TRANSPORT.
     (b) Engage the JXU70 JACXSON on the engine PWA211430 STAND, TRANSPORT.
     (c) Connect the jacXson lifting adapters to the forklift pockets of the stand.
     (d) Lift the PWA211430 STAND, TRANSPORT with the JXU70 JACXSON tool up to 50 MM (2 IN.).
     (e) Move the JXU70 JACXSON tool to lift and put the engine PWA211430 STAND, TRANSPORT in position, with the center below the pylon.
   (8) Lift the PWA211430 STAND, TRANSPORT to attach the cradle to the engine.
     (a) Lift the PWA211430 STAND, TRANSPORT from the ground, then gradually tilt the front of the cradle up, to adjust the final approach angle of the cradle in relation to the fan case and TEC adapters.
NOTE: The front of the engine is tilted 2.2 degrees up, in relation to the aircraft axis.
     (b) Monitor the loads read on the JacXson display during maintenance to make sure that they are not more than:
  • At the forward mount: 3090 daN (3154 kg)
  • At the aft mount: 3350 daN (3416 kg)
Or
  • At the left forward or right forward mount: 1547 daN (1577 kg)
  • At the left aft or right aft mount: 1675 daN (1708 kg).
     (c) Safety the engine on the cradle with the cap on the adapters.
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 the tool manufacturer's instructions.
   (9)
F Power Plant Engine-Mounts ** ON A/C NOT FOR ALL
     (a) Remove the locking plate system of the forward engine mounts on the left and right sides.
     (b) Remove the four screws (7) that attach the four locking plates (8) to the retainer (11).
     (c) Remove the four locking plates (8).
     (d) Loosen the four forward engine-mount bolts (9) with the 98D71203013000 TORQUE WRENCH SET PW as necessary to loosen them with a WRENCH - TORQUE.
     (e) Loosen the four bolts (9) to remove the remaining torque.
     (f) Remove the two screws (5) and remove the retainer (1).
     (g) Remove the two nuts (2) and remove the retainer (4) and the two washers (3).
   (10)
F 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 the four bolts (17) and the four washers (16).
     (e) Remove the two nuts (12) and the two washers (13).
     (f) Remove the two bolts (20).
Subtask 71-00-51-020-122-A ** ON A/C NOT FOR ALL
B. Removal of the Power Plant from the Pylon
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 assembly.
     (a) Make sure that the clearance is sufficient between the upper bifi and:
  • The pylon dog head
    F 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.
       1 Make sure that the load read on the JacXson display is less than:
  • At the forward mount: 3090 daN (3154 kg)
  • At the aft mount: 3350 daN (3416 kg)
Or
  • At the left forward or right forward mount: 1547 daN (1577 kg)
  • At the left aft or right aft mount: 1675 daN (1708 kg).
       2 Make sure that you do not cause dynamic effects when you lower the engine.
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.
   (3) Remove the engine from the area in the forward direction.
   (4) Make sure that the protection covers are installed:
     (a) On all the pylon interface openings
     (b) On all the power-plant interface openings.
   (5) Install the two right and left upper fan-exit-fairings (Ref. AMM TASK 72-21-04-400-801).
   (6) 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 02:31:50 UTC
"Aviabrain" 2025