DOC AIRBUS | AMM A320FRemoval of the Power Plant with the Engine Positioner TWW 75E (MIAG) [IAE]
TASK 71-00-20-000-040-A-01
Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG)
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 71-00-20-740-058-A ** ON A/C NOT FOR ALL
Subtask 71-00-20-865-069-A ** ON A/C NOT FOR ALL
Subtask 71-00-20-864-053-A ** ON A/C NOT FOR ALL
Subtask 71-00-20-020-067-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:28:29 UTC
Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG)
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.
WARNING:
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 |
| S889BH0 | 1 | BRACE - HOLD OPEN COWLS |
| TMHBS13-00-00 | 1 | BRACE-HOLD OPEN COWLS |
| TWW75E | 1 | ENGINE POSITIONER |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.V02-147) | lockwire |
| (Material No.V10-039) | engine oil |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| FOR [1000EM1] (ENGINE-1) | |
| 437AL, 438AR, 451AL, 452AR | |
| FOR [1000EM2] (ENGINE-2) | |
| 447AL, 448AR, 461AL, 462AR | |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 6 | SEALING 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 29-14-49-000-001-A | Removal of the Reservoir Pressurization Hose |
| 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 36-11-49-000-016-A | Removal of the Sense Line between the Bleed Pressure-Regulator Valve (PRV) and the Pylon Interface |
| TASK 54-57-22-000-004-A | Removal of the Lower Fairing Firewall Seals |
| TASK 54-57-22-400-004-A | Installation of the Lower Fairing Firewall Seals |
| TASK 70-11-56-910-001-A | Cleaning Requirements after Chemical Contact with Fire Extinguisher Agents, Hydraulic Fluid, Oil or Fuel |
| 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 71-00-20-740-058-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 31-36-00-740-015).
Subtask 71-00-20-941-054-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 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 71-00-20-865-057-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 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:
BEFORE YOU OPEN PHC CIRCUIT BREAKERS 2DA1(2,3), OPEN PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3). 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:
C. Open, safety and tag these circuit breakers in this sequence:- 1JH, 2JH1 AND 3JH1 BEFORE 2KS1
- 1JH, 2JH2 AND 3JH2 BEFORE 2KS2.
| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 122VU | ANTI ICE/PROBES/2/TAT | 1DA2 | Y15 |
| 122VU | ANTI ICE/PROBES/1/TAT | 1DA1 | Z12 |
| 49VU | ANTI ICE/PROBES/PITOT/1 | 3DA1 | D02 |
| 122VU | ANTI ICE/PROBES/2/PITOT | 3DA2 | Y14 |
| 122VU | ANTI ICE/PROBES/3/PITOT | 3DA3 | Z16 |
| 49VU | ANTI ICE/PROBES/AOA/1 | 4DA1 | D04 |
| 122VU | ANTI ICE/PROBES/2/AOA | 4DA2 | Y13 |
| 122VU | ANTI ICE/PROBES/3/AOA | 4DA3 | Z15 |
| 122VU | ANTI ICE/PROBES/1/STATIC | 5DA1 | Z13 |
| 122VU | ANTI ICE/PROBES/2/STATIC | 5DA2 | Y11 |
| 122VU | ANTI ICE/PROBES/3/STATIC | 5DA3 | Z14 |
| 49VU | ANTI ICE/RAIN/RPLNT/CAPT | 1DB1 | D01 |
| 122VU | ANTI ICE/RAIN/RPLNT/F/O | 1DB2 | W11 |
| 122VU | ANTI ICE/WINDOWS/L | 4DG1 | X14 |
| 122VU | ANTI ICE/WINDOWS/R | 4DG2 | W14 |
| 123VU | ANTI ICE/L/WHSLD | 1DG1 | AF10 |
| 123VU | ANTI ICE/R/WHSLD | 1DG2 | AF03 |
| 49VU | ENGINE/1 AND 2/IGN/SYS A | 1JH | A03 |
| 121VU | ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A | 1WE1 | Q43 |
| 121VU | ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B | 2WE1 | Q44 |
| 121VU | ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A | 1WE2 | Q41 |
| 121VU | ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B | 2WE2 | Q42 |
| 121VU | RCDR/DFDR | 7TU | K16 |
| 49VU | COM/CVR/SPLY | 23RK | E14 |
| 49VU | COM/CVR/CTL | 26RK | E13 |
| FOR FIN: 1000EM1 (ENGINE1) | |||
| 121VU | ENGINE/IGN/ENG1/SYS A BAT | 2JH1 | P39 |
| 121VU | ENGINE/IGN/ENG1/SYS B | 3JH1 | P41 |
| 121VU | ENGINE/ENG1/FADEC B/AND EIU 1 | 4KS1 | R41 |
| 49VU | ENGINE/1/FADEC A/AND EIU 1 | 2KS1 | A04 |
| 49VU | ENGINE/1/FIRE DET/LOOP A | 7WD1 | A06 |
| 121VU | ENGINE/ENG1/FIRE DET/LOOP B | 8WD1 | Q38 |
| 122VU | ELEC/GCU/1 | 2XU1 | T26 |
| 122VU | ANTI ICE/ENG/1 | 1DN1 | X10 |
| 49VU | FUEL/LP VALVE/MOT1/ENG1 | 1QG | A08 |
| 121VU | FUEL/LP VALVE/MOT2/ENG1 | 3QG | M25 |
| FOR FIN: 1000EM2 (ENGINE2) | |||
| 121VU | ENGINE/IGN/ENG2/SYS A BAT | 2JH2 | P40 |
| 121VU | ENGINE/IGN/ENG2/SYS B | 3JH2 | P42 |
| 121VU | ENGINE/ENG2/FADEC B | 4KS2 | Q40 |
| 49VU | ENGINE/2/FADEC A/AND EIU 2 | 2KS2 | A05 |
| 121VU | ENGINE/ENG2/FIRE DET/LOOP A | 7WD2 | Q39 |
| 49VU | ENGINE/2/FIRE DET/LOOP B | 8WD2 | A07 |
| 122VU | ELEC/GCU/2 | 2XU2 | T27 |
| 123VU | Y HYD/ELEC/ELEC PUMP/NORM | 3801GX | AB03 |
| 123VU | Y HYD/ELEC/PUMP | 3802GX | AB06 |
| 121VU | HYDRAULIC/HYD POWER/Y | 3803GX | N30 |
| 122VU | ANTI ICE/ENG/2 | 1DN2 | W10 |
| 49VU | FUEL/LP VALVE/MOT1/ENG2 | 2QG | A09 |
| 121VU | FUEL/LP VALVE/MOT2/ENG2 | 4QG | M26 |
WARNING:
OPEN THE PROBE HEATER AND WINDOW HEATER CIRCUIT-BREAKERS BEFORE YOU OPEN THE PHC AND WHC CIRCUIT BREAKERS. IF YOU DO NOT OBEY THIS SEQUENCE:
D. 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 | 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 |
E. 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 71-00-20-010-059-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).
F. 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 71-00-20-040-054-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.
G. Deactivate the Thrust Reverser
Subtask 71-00-20-010-060-A ** ON A/C NOT FOR ALL WARNING:
MAKE SURE THAT THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) IS DEACTIVATED BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER. IF THE HCU IS NOT DEACTIVATED, THERE IS A RISK OF UNWANTED THRUST REVERSER OPERATION WHICH CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
(1) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012). H. 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 71-00-20-480-058-A ** ON A/C NOT FOR ALL (1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR
I. 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) into 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 71-00-20-680-056-A ** ON A/C NOT FOR ALL (1) Put the adjustable struts (1) and (2) into 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). J. 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 SEALING RING (6) with clean engine oil (Material No.V10-039) and install it on the fuel drain plug (7) (Ref. AMM TASK 70-23-13-911-010).
(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 71-00-20-020-066-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 SEALING RING (6) with clean engine oil (Material No.V10-039) and install it on the fuel drain plug (7) (Ref. AMM TASK 70-23-13-911-010).
(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) .
K. Removal of Components from the Right and the Left Sides of the Engine
(1) Remove the drain 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).
2 Disconnect the hydraulic pressure tube (2).
3 Disconnect the hydraulic pump case drain tube (7).
4 Install CAP - BLANKING to hydraulic lines.
5 Clean any hydraulic fluid that may have leaked onto the fan case (Ref. AMM TASK 70-11-56-910-001).
(f) Disconnect the fuel tubes from the fluid disconnect panel.
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).
4 Install CAP - BLANKING to fuel lines.
5 Clean any fuel that may have leaked onto the fan case (Ref. AMM TASK 70-11-56-910-001).
(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 located on the combustor case at 11 o'clock (Ref. AMM TASK 29-14-49-000-001).
Subtask 71-00-20-020-071-A ** ON A/C NOT FOR ALL (1) Remove the drain 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 drain 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).
CAUTION:
DO NOT LET HYDRAULIC FLUID GO DOWN THE FAN CASE AND CONTACT THE SEAL RING BETWEEN THE FAN CASE AND THE ANGLE GEARBOX. REMOVE THE HYDRAULIC FLUID WITH A CLEAN LINT FREE CLOTH. THE HYDRAULIC FLUID CAN CAUSE DETERIORATION OF THE SEAL RING.
CAUTION:
USE A SECOND WRENCH TO APPLY COUNTERTORQUE TO THE UNION WHEN YOU DISCONNECT/CONNECT HYDRAULIC LINES ON UNIONS. IF YOU DO NOT USE THE SECOND WRENCH, THERE IS A RISK THAT YOU WILL LOOSEN OR TIGHTEN THE UNION TOO MUCH.
(e) Disconnect the hydraulic tubes from the fluid disconnect panel. NOTE: If the check valve is loosened by error, we must replace the seal before re-torqueing it.
1 Disconnect the hydraulic suction hose (1). 2 Disconnect the hydraulic pressure tube (2).
3 Disconnect the hydraulic pump case drain tube (7).
4 Install CAP - BLANKING to hydraulic lines.
5 Clean any hydraulic fluid that may have leaked onto the fan case (Ref. AMM TASK 70-11-56-910-001).
(f) Disconnect the fuel tubes from the fluid disconnect panel.
CAUTION:
DO NOT LET FUEL GO DOWN THE FAN CASE AND CONTACT THE SEAL RING BETWEEN THE FAN CASE AND THE ANGLE GEARBOX. REMOVE THE FUEL WITH A CLEAN LINT-FREE CLOTH. THE FUEL CAN CAUSE DETERIORATION OF THE SEAL RING.
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).
4 Install CAP - BLANKING to fuel lines.
5 Clean any fuel that may have leaked onto the fan case (Ref. AMM TASK 70-11-56-910-001).
(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 located on the combustor case at 11 o'clock (Ref. AMM TASK 29-14-49-000-001).
L. Removal of the Bleed Pressure Regulator Valve (PRV) Sense Line.
(1) Remove the sense line between the bleed pressure regulator valve (PRV) and the pylon interface (Ref. AMM TASK 36-11-49-000-016).
Subtask 71-00-20-620-051-A ** ON A/C NOT FOR ALL (1) Remove the sense line between the bleed pressure regulator valve (PRV) and the pylon interface (Ref. AMM TASK 36-11-49-000-016).
M. Install CAP - BLANKING to all openings and connectors.
4. ProcedureSubtask 71-00-20-020-067-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 three bolts (18) in turn.
Subtask 71-00-20-020-068-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 three bolts (18) 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 71-00-20-480-059-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. Installation of the Engine Positioner TWW 75E
(2) Install the engine cradle onto the rail system of the engine positioner.
(3) On the control panel of the positioner, push the button SET REFERENCE VALUE to set the load value to zero.
(4) Install the engine positioner under the engine.
(b) Position the engine positioner with the cradle on it, below the engine. Use the right joystick to move the positioner.
(c) Lift and adjust the engine positioner with the cradle assembly. Lightly move the positioner to adjust it. Use the left joystick to lift the positioner.
(d) Insert the pins of the front fixtures of the engine handling points and then install the rear support on the left side. Attach to the engine with a ball pin.
(e) Continue to lift the engine positioner until the tool takes over the weight of the engine from the wing.
(g) Lift the front and aft pillars together or only the front pillars or the aft pillars to obtain the front and aft preloads.
(h) When a lift pillar is at 100 percent of preload, the related load bar becomes red and the movement stops.
(i) On the control panel of the positioner, release this overload:
1 Push the RELEASE key.
(j) Lower the pillar which is overload.
(k) Lift the other pillars until all pillars are near to 300 daN (overload).
(l) Use the left joystick until all load values become stable and the up movement stops.
Subtask 71-00-20-020-069-A ** ON A/C NOT FOR ALL CAUTION:
MAKE SURE THAT THE ENGINE POSITIONER IS ON A FLAT, CONCRETE SURFACE. IF THERE IS A SLOPE, IT MUST NOT BE MORE THAN 2 DEG.
(1) Make sure that the TWW75E ENGINE POSITIONER is operational. (2) Install the engine cradle onto the rail system of the engine positioner.
(3) On the control panel of the positioner, push the button SET REFERENCE VALUE to set the load value to zero.
(4) Install the engine positioner under the engine.
CAUTION:
DO NOT CAUSE DAMAGE TO THE ENGINE WHILE YOU LIFT THE CRADLE.
CAUTION:
BE CAREFUL WHEN YOU INSTALL THE CRADLE ON, OR REMOVE IT FROM, THE ENGINE. IF NOT, YOU CAN CAUSE DAMAGE TO THE VIBRATION SENSOR CONNECTOR. THE VIBRATION SENSOR CONNECTOR IS IN FRONT OF THE FORWARD HANDLING POINT ON THE RIGHT SIDE.
(a) Start up the engine positioner. (b) Position the engine positioner with the cradle on it, below the engine. Use the right joystick to move the positioner.
(c) Lift and adjust the engine positioner with the cradle assembly. Lightly move the positioner to adjust it. Use the left joystick to lift the positioner.
(d) Insert the pins of the front fixtures of the engine handling points and then install the rear support on the left side. Attach to the engine with a ball pin.
(e) Continue to lift the engine positioner until the tool takes over the weight of the engine from the wing.
NOTE: From this point, the load taken over by the four pillars of the positioner must be monitored all the time on the control panel.
(f) Continue to lift and make sure that display on the control panel shows the load taken over by the four pillars of the positioner. When the load is between zero and 300 daN (overload), the load bar is green. When the load is more than 300 daN, the load bar becomes red and the lifting system of the engine positioner stops (overload protection). (g) Lift the front and aft pillars together or only the front pillars or the aft pillars to obtain the front and aft preloads.
(h) When a lift pillar is at 100 percent of preload, the related load bar becomes red and the movement stops.
(i) On the control panel of the positioner, release this overload:
1 Push the RELEASE key.
(j) Lower the pillar which is overload.
(k) Lift the other pillars until all pillars are near to 300 daN (overload).
(l) Use the left joystick until all load values become stable and the up movement stops.
D. Removal of the Power Plant
(a) Put the padding between the engine and the forward engine mount (4).
(b) Remove the nuts (16), retainers (12), washers (17) and bolts (18) which attach the forward engine mount (4) to the pylon (3).
(c) Remove the nut (8), washer (7), retainer (6) and nut (5).
(2) Disconnect the aft engine mount (4):
(a) Remove the lockwire:
(b) Remove the bolts (2), washers (3), barrel nuts (6) and retainers (7) that attach the aft engine mount (4) to the pylon (1).
(3) Remove the engine from the aircraft:
(a) Make sure that no lines or unions stay connected to the pylon.
(b) Apply or install protections on the engine air ducts and attach the engine air ducts to the pylon section.
(c) Use the left joystick to lower the engine.
(d) Make sure that an engine trolley with the 90 in. (2.2860 m) rail system is available.
(e) Move the TWW75E ENGINE POSITIONER away from the wing.
(f) Assemble the rail system of the engine positioner with the rail system of the engine trolley.
(g) Move the engine cradle from the rail system of the engine positioner to the engine trolley.
(4) In the fire bulkhead area, do an inspection of the anti-ice pylon duct (21) (with the castellated flange and the full flanges) and the pylon housing (22) for signs of damage:
(a) Make sure that there are no disengaged metal seals (23).
(b) If you find disengaged metal seals (23) out of the duct flanges, replace the duct.
(c) If the castellated flange (in the core area) and the full flanges (in the fan area) are twisted, bent or if they have cracks then, remove the duct and replace it.
(d) If there are other types of damage (nicks, gauges, scratches) on the anti-ice pylon duct (21) or the pylon housing (22), refer to the Duct and Fuel Pipe Repair Manual (Ref. DFPRM 51-12-00-001-200-A01).
(e) If there is no damage, no maintenance is necessary.
(5) Do a detailed inspection of the forward pylon fire-seal (U-shaped) for:
WARNING:
BEFORE YOU REMOVE OR INSTALL 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 (4):(a) Put the padding between the engine and the forward engine mount (4).
(b) Remove the nuts (16), retainers (12), washers (17) and bolts (18) which attach the forward engine mount (4) to the pylon (3).
(c) Remove the nut (8), washer (7), retainer (6) and nut (5).
(2) Disconnect the aft engine mount (4):
(a) Remove the lockwire:
WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
1 Cut and discard the lockwire that safeties the bolts (2). (b) Remove the bolts (2), washers (3), barrel nuts (6) and retainers (7) that attach the aft engine mount (4) to the pylon (1).
(3) Remove the engine from the aircraft:
(a) Make sure that no lines or unions stay connected to the pylon.
(b) Apply or install protections on the engine air ducts and attach the engine air ducts to the pylon section.
(c) Use the left joystick to lower the engine.
(d) Make sure that an engine trolley with the 90 in. (2.2860 m) rail system is available.
(e) Move the TWW75E ENGINE POSITIONER away from the wing.
(f) Assemble the rail system of the engine positioner with the rail system of the engine trolley.
(g) Move the engine cradle from the rail system of the engine positioner to the engine trolley.
(4) In the fire bulkhead area, do an inspection of the anti-ice pylon duct (21) (with the castellated flange and the full flanges) and the pylon housing (22) for signs of damage:
(a) Make sure that there are no disengaged metal seals (23).
(b) If you find disengaged metal seals (23) out of the duct flanges, replace the duct.
(c) If the castellated flange (in the core area) and the full flanges (in the fan area) are twisted, bent or if they have cracks then, remove the duct and replace it.
(d) If there are other types of damage (nicks, gauges, scratches) on the anti-ice pylon duct (21) or the pylon housing (22), refer to the Duct and Fuel Pipe Repair Manual (Ref. DFPRM 51-12-00-001-200-A01).
(e) If there is no damage, no maintenance is necessary.
(5) Do a detailed inspection of the forward pylon fire-seal (U-shaped) for:
- Wear
- Degradation
- Loose sides
- Cracks, and
- Missing sections.