DOC AIRBUS | AMM A320FRemoval of the Power Plant with Cobra Tool [IAE]
TASK 71-00-20-000-040-A-02
Removal of the Power Plant with Cobra Tool
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Expendable Parts
E. Referenced Information
3. Job Set-up
Subtask 71-00-20-740-054-A ** ON A/C NOT FOR ALL
Subtask 71-00-20-864-054-A ** ON A/C NOT FOR ALL
Subtask 71-00-20-020-074-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2017]
2026.04.01 02:28:35 UTC
Removal of the Power Plant with Cobra Tool
WARNING:
MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.
WARNING:
PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- COMPONENTS THAT MOVE.
WARNING:
MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 1M(3 FT) |
| No specific | AR | CAP - BLANKING |
| No specific | AR | CONTAINER - CLEAN, APPLICABLE |
| No specific | AR | SAFETY CLIP - CIRCUIT BREAKER |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 120 and 110 lbf.in (1.36 and 1.24 m.daN )  | |
| No specific | Torque wrench: range to between 1584 and 1056 lbf.in (17.90 and 11.93 m.daN ) | |
| 98D71203001000 | 1 | CHEST,TORQUE SET-ENGINE R I |
| EC001-002 | 1 | |
| ED005-002 | 1 | |
| S889BH0 | 1 | BRACE - HOLD OPEN COWLS |
| SG233-001 | 1 | SAFETY DEVICE |
| SG233-050 | 1 | BEAM FOR SAFETY DEVICE |
| TMHBS13-00-00 | 1 | BRACE-HOLD OPEN COWLS |
| TP91G1A1A0A | 1 | COBRA TOOL |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.V02-147) | lockwire |
| (Material No.V10-077) | lubricant (engine oil) |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| FOR [1000EM1] (ENGINE-1) | |
| 437AL, 438AR, 451AL, 452AR | |
| FOR [1000EM2] (ENGINE-2) | |
| 447AL, 448AR, 461AL, 462AR | |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 6 | seal ring | AIPC 73-12-42-80-070 |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 05-57-00-200-001-B | Aircraft Stability |
| 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 31-36-00-740-006-A | Printout of the APU Hours and Cycles |
| TASK 31-36-00-740-007-A | Printout of the Engine Hours and Cycles |
| 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 70-23-11-911-013-A | General Torque Tightening Techniques |
| TASK 70-23-13-911-010-A | Procedures for the Installation of Preformed Packings |
| TASK 71-13-00-010-010-A | Opening of the Fan Cowls 437AL(447AL),438AR(448AR) |
| TASK 71-13-00-410-010-A | Closing of the Fan Cowls 437AL(447AL),438AR(448AR) |
| TASK 71-71-42-000-010-A | Removal of the Drains Mast |
| TASK 78-30-00-040-012-A | Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance |
| TASK 78-32-00-010-010-A | Opening of the Thrust Reverser Halves |
| TASK 78-32-00-410-010-A | Closing of the Thrust Reverser Halves |
Hydraulic Control UnitSubtask 71-00-20-740-054-A ** ON A/C NOT FOR ALL
A. Do a print-out of the engine hours and cycles and keep the print with the engine for follow-up (Ref. AMM TASK 31-36-00-740-006) or (Ref. AMM TASK 31-36-00-740-007) or (Ref. AMM TASK 31-36-00-740-015).
Subtask 71-00-20-941-055-A ** ON A/C NOT FOR ALL NOTE: Some tasks will possibly not be applicable depending on whether a Data Management Unit (DMU) or a Flight Data Interface and Management Unit (FDIMU) is installed on the aircraft.
B. Safety Precautions
(1) Make sure that the A/C is stable (Ref. AMM TASK 05-57-00-200-001).
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(3) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(4) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
(5) On the panel 30VU:
(a) Make sure that the APU BLEED pushbutton switch is released (ON legend off).
(b) Install a warning notice to tell the persons not to press the APU BLEED pushbutton switch.
(6) Put a WARNING NOTICE(S) on the HP ground connector to tell persons not to pressurize the pneumatic system.
Subtask 71-00-20-865-060-A ** ON A/C NOT FOR ALL (1) Make sure that the A/C is stable (Ref. AMM TASK 05-57-00-200-001).
NOTE: When the A/C is on jacks, make sure that it is leveled before you remove the engine.
(2) On the center pedestal, on the ENG panel 115VU: (a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(3) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(4) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
(5) On the panel 30VU:
(a) Make sure that the APU BLEED pushbutton switch is released (ON legend off).
(b) Install a warning notice to tell the persons not to press the APU BLEED pushbutton switch.
(6) Put a WARNING NOTICE(S) on the HP ground connector to tell persons not to pressurize the pneumatic system.
WARNING:
MAKE SURE THAT YOU OPEN THE CIRCUIT BREAKERS AS FOLLOWS:
- 1JH, 2JH1 AND 3JH1 BEFORE 2KS1
- 1JH, 2JH2 AND 3JH2 BEFORE 2KS2.
WARNING:
OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3) BEFORE YOU OPEN THE PHC CIRCUIT BREAKERS 2DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE:
C. Open, safety and tag this(these) circuit breaker(s):- THE PROBES WILL BECOME TOO HOT.
- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | ENGINE/1 AND 2/IGN/SYS A | 1JH | A03 |
| 49VU | ANTI ICE/PROBES/AOA/1 | 4DA1 | D04 |
| 49VU | ANTI ICE/PROBES/PHC/1 | 2DA1 | D03 |
| 49VU | ANTI ICE/PROBES/PITOT/1 | 3DA1 | D02 |
| 49VU | ANTI ICE/RAIN/RPLNT/CAPT | 1DB1 | D01 |
| 49VU | COM/CVR/SPLY | 2RK | E14 |
| 49VU | COM/CVR/CTL | 4RK | E13 |
| 121VU | RCDR/DFDR | 7TU | K16 |
| 121VU | ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B | 2WE1 | Q44 |
| 121VU | ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A | 1WE1 | Q43 |
| 121VU | ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B | 2WE2 | Q42 |
| 121VU | ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A | 1WE2 | Q41 |
| 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/PHC/3 | 2DA3 | Y16 |
| 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/PHC/2 | 2DA2 | Y12 |
| 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 | ANTI ICE/L/WHSLD | 1DG1 | AF10 |
| 123VU | ANTI ICE/R/WHSLD | 1DG2 | AF03 |
| FOR FIN: 1000EM1 (ENGINE1) | |||
| 49VU | ENGINE/1/FIRE DET/LOOP A | 7WD1 | A06 |
| 49VU | ENGINE/1/FADEC A/AND EIU 1 | 2KS1 | A04 |
| 121VU | ENGINE/IGN/ENG1/SYS B | 3JH1 | P41 |
| 121VU | ENGINE/IGN/ENG1/SYS A BAT | 2JH1 | P39 |
| 121VU | ENGINE/ENG1/FIRE DET/LOOP B | 8WD1 | Q38 |
| 121VU | ENGINE/ENG1/FADEC B/AND EIU 1 | 4KS1 | R41 |
| 122VU | ELEC/GCU/1 | 2XU1 | T26 |
| 122VU | ANTI ICE/ENG/1 | 1DN1 | X10 |
| FOR FIN: 1000EM2 (ENGINE2) | |||
| 49VU | ENGINE/2/FIRE DET/LOOP B | 8WD2 | A07 |
| 49VU | ENGINE/2/FADEC A/AND EIU 2 | 2KS2 | A05 |
| 121VU | HYDRAULIC/HYD POWER/Y | 3803GX | N30 |
| 121VU | ENGINE/IGN/ENG2/SYS B | 3JH2 | P42 |
| 121VU | ENGINE/IGN/ENG2/SYS A BAT | 2JH2 | P40 |
| 121VU | ENGINE/ENG2/FADEC B/AND EIU 2 | 4KS2 | Q40 |
| 121VU | ENGINE/ENG2/FIRE DET/LOOP A | 7WD2 | Q39 |
| 122VU | ELEC/GCU/2 | 2XU2 | T27 |
| 122VU | ANTI ICE/ENG/2 | 1DN2 | W10 |
| 123VU | Y HYD/ELEC/PUMP | 3802GX | AB06 |
| 123VU | Y HYD/ELEC/ELEC PUMP/NORM | 3801GX | AB03 |
D. Depressurize these Hydraulic Systems
(1) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the applicable system.
(a) On the panel 40VU.
(b) 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).
(3) Depressurize the reservoir of the applicable hydraulic system (Ref. AMM TASK 29-14-00-614-001).
Subtask 71-00-20-010-062-A ** ON A/C NOT FOR ALL (1) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the applicable system.
(a) On the panel 40VU.
(b) 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).
(3) Depressurize the reservoir of the applicable hydraulic system (Ref. AMM TASK 29-14-00-614-001).
E. Get Access
(1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(2) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(3) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(4) Put the ACCESS PLATFORM 1M(3 FT) in position at engine level.
Subtask 71-00-20-040-056-A ** ON A/C NOT FOR ALL (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(2) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(3) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(4) Put the ACCESS PLATFORM 1M(3 FT) in position at engine level.
F. Deactivate the Thrust Reverser
Subtask 71-00-20-010-063-A ** ON A/C NOT FOR ALL WARNING:
THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) MUST BE DEACTIVATED BEFORE WORKING ON OR AROUND THE THRUST REVERSER. FAILURE TO DEACTIVATE THE HCU CAN RESULT IN INADVERTENT THRUST REVERSER OPERATION AND INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
(1) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012). G. Open the thrust reverser doors (Ref. AMM TASK 78-32-00-010-010) but do not release the pressure after you put the hold open rods in position.
(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR
Subtask 71-00-20-480-060-A ** ON A/C NOT FOR ALL (1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR
H. Install the S889BH0 BRACE - HOLD OPEN COWLS or TMHBS13-00-00 BRACE-HOLD OPEN COWLS to Support the Fan and Thrust Reverser Cowl Doors
(1) Put the adjustable struts (1) and (2) in to position.
(2) Adjust the length of the struts so that they hold the weight of the thrust reverser halves.
(3) Put the thrust reverser half hold-open rods in their storage positions (Ref. AMM TASK 78-32-00-410-010).
(4) Open the valve on the hydraulic hand pump.
(5) Install the left and right support arms (4) so that they hold the weight of the fan cowls.
Subtask 71-00-20-680-057-A ** ON A/C NOT FOR ALL (1) Put the adjustable struts (1) and (2) in to position.
(2) Adjust the length of the struts so that they hold the weight of the thrust reverser halves.
(3) Put the thrust reverser half hold-open rods in their storage positions (Ref. AMM TASK 78-32-00-410-010).
(4) Open the valve on the hydraulic hand pump.
(5) Install the left and right support arms (4) so that they hold the weight of the fan cowls.
NOTE: The support arms (4) must be installed so that the brackets (3) are on the second latch from the front of the thrust reverser halves.
(6) Put the fan cowl hold-open rods in their storage positions (Ref. AMM TASK 71-13-00-410-010). I. Drain the Fuel that Stays in the Engine and the Pylon Fuel Hose, to Do this Drain at Level of the Fuel Filter as Follows:
(1) Put a CONTAINER - CLEAN, APPLICABLE under the fuel filter.
(2) Cut and discard the lockwire which safeties the fuel drain plug (7).
(3) Remove the fuel drain plug and drain the fuel into the container.
(5) Lubricate a new AIPC 73-12-42-80-070 seal ring (6) with cleanV10-077 lubricant (engine oil)
(6) Install the fuel drain plug (7).
(7) TORQUE the fuel drain plug to between 120 and 110 lbf.in (1.36 and 1.24 m.daN ) (Ref. AMM TASK 70-23-11-911-013).
(8) Safety the fuel drain plug with lockwire (Material No.V02-147) .
Subtask 71-00-20-020-072-A ** ON A/C NOT FOR ALL (1) Put a CONTAINER - CLEAN, APPLICABLE under the fuel filter.
(2) Cut and discard the lockwire which safeties the fuel drain plug (7).
(3) Remove the fuel drain plug and drain the fuel into the container.
NOTE: Do not put fuel that you drained from the engine back into the fuel system.
(4) Remove the seal ring (6) from the fuel drain plug (7). Discard the seal ring. (5) Lubricate a new AIPC 73-12-42-80-070 seal ring (6) with clean
(6) Install the fuel drain plug (7).
(7) TORQUE the fuel drain plug to between 120 and 110 lbf.in (1.36 and 1.24 m.daN )
(Ref. AMM TASK 70-23-11-911-013). (8) Safety the fuel drain plug with lockwire (Material No.V02-147) .
J. Removal of Components from the Right and the Left Sides of the Engine
(1) Remove the drains mast (Ref. AMM TASK 71-71-42-000-010).
(a) At the left interface electrical junction box:
1 Cut and discard the lockwire safetying the IDG harness connector 400VC and disconnect the connector.
2 Disconnect connectors 401VC, 403VC, 407VC and 409VC.
3 Disconnect connectors 402VC, 404VC, 405VC, 406VC, 408VC, 447VC, 448VC and 457VC.
(c) Disconnect the electrical connector 4005VC located by the V groove on the fan case, at 1 o'clock, looking forward.
(d) Remove the coupling (5) and disconnect the upper starter duct (4) from the pylon duct (6).
(e) Remove the coupling (3) and disconnect the Thermal Anti-ice duct (TAI) (2) located on the fan case close by the pylon from the pylon TAI duct (1).
(3) Remove these components from the left side of the engine.
(a) Disconnect the thrust reverser harness connectors 4101KS-A and 4101KS-B from the thrust reverser Hydraulic Control Unit (HCU).
(b) Disconnect the electrical connector 4004VC located by the V groove on the fan case, at 11 o'clock, looking forward.
(c) Remove the couplings (19) and disconnect the TAI duct (18) located close by the forward mount.
(d) Remove the coupling (7) and disconnect the cabin air duct (10).
(e) Disconnect the hydraulic tubes from the fluid disconnect panel.
2 Disconnect the hydraulic pressure tube (2).
3 Disconnect the hydraulic pump case drain tube (7).
(f) Disconnect the fuel tubes from the fluid disconnect panel.
1 Cut and discard the lockwire which safeties the bolts attaching the tubes.
2 Remove the 4 bolts (6) and the washers (5) and disconnect the fuel return to tank tube (4). Remove and discard the gasket (3).
3 Remove the 4 bolts (9),the washers (10) and disconnect the fuel supply tube (8). Remove and discard the gasket (11).
(g) Disconnect the sensor tubes from the bracket situated forward of the pylon.
1 Disconnect the pressure regulating valve (PRV) sensor tube (20).
2 Disconnect the thermostat sensor tube (11).
(h) On engine 1 only, disconnect the hydraulic reservoir pressurizing tube from the union located on the combustor case at 11 o'clock.
Subtask 71-00-20-620-052-A ** ON A/C NOT FOR ALL (1) Remove the drains mast (Ref. AMM TASK 71-71-42-000-010).
NOTE: When you install the engine in the transportation stand it is only necessary to remove the drains mast to prevent damage. It is not necessary to disconnect the drain tubes or remove the collector plate assembly.
(2) Remove these components from the right side of the engine. (a) At the left interface electrical junction box:
- Disconnect the electrical connectors 450VC, 452VC and 454VC.
1 Cut and discard the lockwire safetying the IDG harness connector 400VC and disconnect the connector.
2 Disconnect connectors 401VC, 403VC, 407VC and 409VC.
3 Disconnect connectors 402VC, 404VC, 405VC, 406VC, 408VC, 447VC, 448VC and 457VC.
(c) Disconnect the electrical connector 4005VC located by the V groove on the fan case, at 1 o'clock, looking forward.
(d) Remove the coupling (5) and disconnect the upper starter duct (4) from the pylon duct (6).
(e) Remove the coupling (3) and disconnect the Thermal Anti-ice duct (TAI) (2) located on the fan case close by the pylon from the pylon TAI duct (1).
(3) Remove these components from the left side of the engine.
(a) Disconnect the thrust reverser harness connectors 4101KS-A and 4101KS-B from the thrust reverser Hydraulic Control Unit (HCU).
(b) Disconnect the electrical connector 4004VC located by the V groove on the fan case, at 11 o'clock, looking forward.
(c) Remove the couplings (19) and disconnect the TAI duct (18) located close by the forward mount.
(d) Remove the coupling (7) and disconnect the cabin air duct (10).
(e) Disconnect the hydraulic tubes from the fluid disconnect panel.
NOTE: It is permitted to secure the nut against the fluid disconnect panel during the hydraulic tubes removal to prevent loosening of the union.
1 Disconnect the hydraulic suction hose (1). 2 Disconnect the hydraulic pressure tube (2).
3 Disconnect the hydraulic pump case drain tube (7).
(f) Disconnect the fuel tubes from the fluid disconnect panel.
1 Cut and discard the lockwire which safeties the bolts attaching the tubes.
2 Remove the 4 bolts (6) and the washers (5) and disconnect the fuel return to tank tube (4). Remove and discard the gasket (3).
3 Remove the 4 bolts (9),the washers (10) and disconnect the fuel supply tube (8). Remove and discard the gasket (11).
(g) Disconnect the sensor tubes from the bracket situated forward of the pylon.
1 Disconnect the pressure regulating valve (PRV) sensor tube (20).
2 Disconnect the thermostat sensor tube (11).
(h) On engine 1 only, disconnect the hydraulic reservoir pressurizing tube from the union located on the combustor case at 11 o'clock.
K. Install CAP - BLANKING to all openings and connectors.
4. ProcedureSubtask 71-00-20-020-074-A ** ON A/C NOT FOR ALL
A. Loosen the Forward Engine Mount Bolts
(2) Loosen one forward mount bolt (18) and TORQUE it again to between 1584 and 1056 lbf.in (17.90 and 11.93 m.daN ) (Ref. AMM TASK 70-23-11-911-013) or the maximum load that a mechanic can apply with a standard wrench.
Apply the same procedure for each of the other four bolts in turn.
Subtask 71-00-20-020-075-A ** ON A/C NOT FOR ALL CAUTION:
LOOSEN ONLY ONE BOLT AT A TIME. MAKE SURE THE BOLT IS TIGHT BEFORE THE SUBSEQUENT BOLT IS LOOSENED.
(1) Remove the nuts (15), the washers (14) and (10), the bolts (9) and remove the retainers (13) and (11). (2) Loosen one forward mount bolt (18) and TORQUE it again to between 1584 and 1056 lbf.in (17.90 and 11.93 m.daN )
(Ref. AMM TASK 70-23-11-911-013) or the maximum load that a mechanic can apply with a standard wrench. Apply the same procedure for each of the other four bolts in turn.
B. Remove the center bolt (1)
(1) Cut and discard the lockwire which safeties the center bolt (1) of the mount.
(2) Remove the center bolt (1) and the washer (2) with the 98D71203001000 CHEST,TORQUE SET-ENGINE R I.
Subtask 71-00-20-480-061-A ** ON A/C NOT FOR ALL (1) Cut and discard the lockwire which safeties the center bolt (1) of the mount.
(2) Remove the center bolt (1) and the washer (2) with the 98D71203001000 CHEST,TORQUE SET-ENGINE R I.
C. Prepare and install the STAND,TRANSPORTATION CRADLE-ENGINE and TROLLEY - ENGINE) and Cobra tool (1).
(2) Move the STAND,TRANSPORTATION in the engine area, under the power plant.
(a) The complete stand must be aligned in X and Y axis. The position is managed with a plumb line attached to the pylon mount (rear or front) and targeting the engine. The Y position is managed by a tape on ground, near the 4 stand wheels. Install TAPE - ADHESIVE on ground, on front of the wheel access of the STAND,TRANSPORTATION.
(b) Insert the lift adapters to the STAND,TRANSPORTATION.
(c) Position the Cobra tool (1) TP91G1A1A0A COBRA TOOL in the engine area.
(d) Connect the lift adapters to the Cobra chains.
(e) Align the Cobra tool (1) with the STAND,TRANSPORTATION.
(f) Connect the hose package (electrical + hydraulic) to the Cobra tool (master and slave unit).
(i) If used, install the safety device SG233-001 SAFETY DEVICE and SG233-050 BEAM FOR SAFETY DEVICE (2).
(j) Lift the STAND,TRANSPORTATION until 50 mm (1.9685 in.) between the cradle-stand and the engine trunnion.
(k) If used, lock the satety device (2) in position.
(l) Adjust position of the STAND,TRANSPORTATION to be in contact with the engine trunnion.
(m) Connect engine trunnions.
(n) Adjust position of the safety device (2) to be in contact with the STAND,TRANSPORTATION.
(3) Monitor loads in order to not exceed 974 daN (2190 lbf) on the forward Cobra Tool and 2377 daN (5344 lbf) on the aft Cobra tool.
Subtask 71-00-20-020-076-A ** ON A/C NOT FOR ALL NOTE: Engine contour given for exemple, should differ from real configuration
NOTE: You must also obey the instruction provided by the STAND,TRANSPORTATION and Cobra tool Manufacturer's Instruction Manuals.
NOTE: Airbus recommends to use safety device (SG233-001 and SG233-050) (2).
(1) Install the fork tube (3) on the STAND,TRANSPORTATION EC001-002 (2) Move the STAND,TRANSPORTATION in the engine area, under the power plant.
(a) The complete stand must be aligned in X and Y axis. The position is managed with a plumb line attached to the pylon mount (rear or front) and targeting the engine. The Y position is managed by a tape on ground, near the 4 stand wheels. Install TAPE - ADHESIVE on ground, on front of the wheel access of the STAND,TRANSPORTATION.
(b) Insert the lift adapters to the STAND,TRANSPORTATION.
(c) Position the Cobra tool (1) TP91G1A1A0A COBRA TOOL in the engine area.
(d) Connect the lift adapters to the Cobra chains.
(e) Align the Cobra tool (1) with the STAND,TRANSPORTATION.
(f) Connect the hose package (electrical + hydraulic) to the Cobra tool (master and slave unit).
NOTE: Keep always the master unit out of the lifting device area.
(g) Set parameters: - Select the engine and shipping stand combination.
- Check preload values for correct operation, -10 kg (-22 lb) on the forward pillars and 390 kg (860 lb) on the rear pillards.
(i) If used, install the safety device SG233-001 SAFETY DEVICE and SG233-050 BEAM FOR SAFETY DEVICE (2).
(j) Lift the STAND,TRANSPORTATION until 50 mm (1.9685 in.) between the cradle-stand and the engine trunnion.
(k) If used, lock the satety device (2) in position.
(l) Adjust position of the STAND,TRANSPORTATION to be in contact with the engine trunnion.
(m) Connect engine trunnions.
(n) Adjust position of the safety device (2) to be in contact with the STAND,TRANSPORTATION.
(3) Monitor loads in order to not exceed 974 daN (2190 lbf) on the forward Cobra Tool and 2377 daN (5344 lbf) on the aft Cobra tool.
NOTE: These loads include the preload defined previously.
D. Removal of the Engine Mounts
(a) Put padding between the engine and the forward mount.
(b) Remove the nuts (16), the retainers (12), the washers (17) and the four bolts (18) which attach the front engine mount to the pylon.
(c) Remove nut (8), washer (7), retainer (6) and nut (5).
(2) Disconnect the aft engine mount.
(a) Cut and discard the lockwire which safeties the bolt (2).
(b) Remove the bolts (2) and the washers (3) and the barrel nuts (6) which attach the aft engine mount (4) to the pylon (1).
(3) Make sure that no lines or unions stay connected to the pylon.
(4) Put the pulley lock levers in the DOWN position.
(5) Carrefully lower the engine using all four chain pulley blocks at the same time. Make sure that the pylon and the engine mount mating faces stay parallel so that you can easily disengage the shear pins.
(7) Remove the four pulley chain blocks from the engine cradle.
(8) Remove the forward hinge arms from the bootstrap system
(a) Remove the four chain hooks from the bootstrap system.
(b) Remove the pins (1) and (3), the link (2) and remove the hinge arms (4) and (5).
Subtask 71-00-20-020-077-A ** ON A/C NOT FOR ALL WARNING:
BEFORE YOU REMOVE THE POWER PLANT, MAKE SURE THAT ALL PERSONNEL IS AWAY FROM THE AIRCRAFT. THE POWER PLANT WEIGHS APPROXIMATELY 7300 POUNDS. IF IT FALLS ON PERSONS, INJURY OR DEATH CAN OCCUR.
WARNING:
DO NOT TOW OR MOVE THE AIRCRAFT ON THE GROUND IF THE THRUST REVERSER IS ON THE PYLON WITH THE ENGINE REMOVED. MOVEMENT OF THE AIRCRAFT CAN CAUSE DAMAGE TO THE PYLON OR THE THRUST REVERSER.
CAUTION:
DO NOT LET THE FORWARD ENGINE MOUNT FALL ON TO THE ENGINE WHEN THE BOLTS ARE REMOVED. THE VSV UNISON RINGS, HARNESSES AND TUBES CAN BE EASILY DAMAGED IF THE FORWARD MOUNT FALLS. PUT PADDING BETWEEN THE ENGINE AND THE FORWARD MOUNT BEFORE THE BOLTS ARE REMOVED.
CAUTION:
IF YOU MUST CLOSE THE ENGINE COWLS WHEN THE ENGINE IS NOT INSTALLED, BE CAREFUL WITH THE THRUST REVERSER COWLS. IF THE COWLS CLOSE TOO FAR, THERE IS A RISK OF DAMAGE TO HINGE N°4.
(1) Disconnect the forward engine mount. (a) Put padding between the engine and the forward mount.
(b) Remove the nuts (16), the retainers (12), the washers (17) and the four bolts (18) which attach the front engine mount to the pylon.
(c) Remove nut (8), washer (7), retainer (6) and nut (5).
(2) Disconnect the aft engine mount.
(a) Cut and discard the lockwire which safeties the bolt (2).
(b) Remove the bolts (2) and the washers (3) and the barrel nuts (6) which attach the aft engine mount (4) to the pylon (1).
(3) Make sure that no lines or unions stay connected to the pylon.
(4) Put the pulley lock levers in the DOWN position.
(5) Carrefully lower the engine using all four chain pulley blocks at the same time. Make sure that the pylon and the engine mount mating faces stay parallel so that you can easily disengage the shear pins.
NOTE: Make sure that the differential load read on the dynamometers is less than:
- 600 daN (1348.9 lbf) (612 kg) between the two front chains.
- 200 daN (449.6 lbf) (204 kg) between the two rear chains.
NOTE: Use the level indicators on the forward hinge arms of the bootstrap to keep this hinge arms as near as possible to the horizontal position.
NOTE: Be careful not to cause the dynamic effects during descent.
NOTE: Put the aft part of the engine cradle in position on the trolley before the front part.
(6) Install the pins to lock the engine cradle on to the engine trolley. (7) Remove the four pulley chain blocks from the engine cradle.
(8) Remove the forward hinge arms from the bootstrap system
(a) Remove the four chain hooks from the bootstrap system.
(b) Remove the pins (1) and (3), the link (2) and remove the hinge arms (4) and (5).
E. Remove the Power Plant from the Pylon
(2) Carefully use the Cobra tool (1) to lower the power plant down from the pylon.
(4) When Cobra tool (1) reach 300 mm (11.8110 in.) for ground, if used, remove the safety device (2).
(5) Lower Cobra tool (1) to hand STAND TRANSPORTATION on the ground.
(6) Disengage the Cobra tool (1) from the STAND TRANSPORTATION.
(7) Move the power plant away from the area.
(8) In the fire bulkhead area, do an inspection of the anti-ice pylon duct (21) including castellated and full flanges and the pylon housing (22) for signs of damage. Make sure that there are no disjoined metal seals (23).
(a) If you find disjoined metal seals (23) out of the duct flanges, remove the duct and replace it.
(b) If the castellated flange (in the core area) and the full flanges (in the fan area) are twisted, bent or cracked, then remove the duct and replace it.
(c) If there is other kind of damage (nicks, gauges, scratches) on the duct or on the pylon housing, refer to the Duct and Fuel Pipe Repair Manual (Ref. DFPRM 51-12-00-001-200-A01).
(d) If there is no damage, no further action is necessary.
NOTE: Make sure that no lines union remains connected to the pylon.
NOTE: While you remove the power plant, you must monitor the interfaces at the mounts, all disconnect locations and the load value on Cobra tool (1).
(1) If used, unlock the safety device (2) and turn it into the lifting down mode. (2) Carefully use the Cobra tool (1) to lower the power plant down from the pylon.
NOTE: Lower the engine checking that the assembly is level and never in a nose down attitude.
NOTE: Closely monitor the loads to maintain stable loads indication during the lowering sequence.
(3) Continue to lower the power plant and STAND,TRANSPORTATION. (4) When Cobra tool (1) reach 300 mm (11.8110 in.) for ground, if used, remove the safety device (2).
(5) Lower Cobra tool (1) to hand STAND TRANSPORTATION on the ground.
(6) Disengage the Cobra tool (1) from the STAND TRANSPORTATION.
(7) Move the power plant away from the area.
(8) In the fire bulkhead area, do an inspection of the anti-ice pylon duct (21) including castellated and full flanges and the pylon housing (22) for signs of damage. Make sure that there are no disjoined metal seals (23).
(a) If you find disjoined metal seals (23) out of the duct flanges, remove the duct and replace it.
(b) If the castellated flange (in the core area) and the full flanges (in the fan area) are twisted, bent or cracked, then remove the duct and replace it.
(c) If there is other kind of damage (nicks, gauges, scratches) on the duct or on the pylon housing, refer to the Duct and Fuel Pipe Repair Manual (Ref. DFPRM 51-12-00-001-200-A01).
(d) If there is no damage, no further action is necessary.