airbus a320 removal power plant

Customer : AEEType : TF-NRev. Date : Aug 01, 2015

Manual : AMMSelected applicability : ALL

71-00-20-000-040-A - Removal of the Power Plant

Print Date: October 27, 2015 of 28© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

** ON A/C ALL

TASK 71-00-20-000-040-ARemoval of the Power Plant

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDINGGEAR.

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOUSTART A TASK ON OR NEAR:- THE FLIGHT CONTROLS- THE FLIGHT CONTROL SURFACES- THE LANDING GEAR AND THE RELATED DOORS- COMPONENTS THAT MOVE.MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CANCAUSE DAMAGE TO THE EQUIPMENT.

WARNING: MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOUSUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

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

FIN : 1000EM1 , 1000EM2

NOTE: Make sure you carry out the appropriate storage procedures before you remove the power plant. The stor-age procedures are more effective when the engine can be run or motored.

1. Reason for the JobSelf explanatory

2Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment REFERENCE QTY DESIGNATIONNo specific AR ACCESS PLATFORM 1M(3 FT)No specific AR CAP - BLANKINGNo specific AR CONTAINER - CLEAN, APPLICABLENo specific AR SAFETY CLIP - CIRCUIT BREAKERNo specific AR WARNING NOTICE(S)No specific Torque wrench: range

to between 62.00 and 900.00 lbf.in (0.70 and 10.00 m.daN)No specific Torque wrench: range

to between 180.00 and 1800.00 lbf.in (2.00 and 20.00 m.daN) (98D71203001000) 1 CHEST,TORQUE SET-ENGINE R I (98D71203501000) 1 BOOTSTRAP SYSTEM (S1787CR) 1 ENGINE CRADLE (S487ETT2) 1 ENGINE TROLLEY (S889BH0) 1 BRACE - HOLD OPEN COWLS (TMHBS13-00-00) 1 BRACE-HOLD OPEN COWLS





REFERENCE QTY DESIGNATION (TMHEC29-00-00) 1 CRADLE,V2500 ENGINE (TMHET06-00-00) 1 TRAILER,ENGINE GROUND HANDLING(CFM56-5 AND IAE V2500)

B. Consumable Materials REFERENCE DESIGNATION(Material No. V02-147) lockwire(Material No. V10-077) lubricant (engine oil)

C. Work Zones and Access Panels ZONE/ACCESS ZONE DESCRIPTIONFOR 1000EM1 (ENGINE-1)437AL, 438AR,451AL, 452AR

FOR 1000EM2 (ENGINE-2)447AL, 448AR,461AL, 462AR

D. Expendable Parts FIG.ITEM DESIGNATION IPC-CSN6 seal ring 73-12-42-80-070

E. Referenced Information REFERENCE DESIGNATION

** ON A/C 001-018, 025-025, 027-028, 053-100, 251-450, 513-700(Ref. 05-57-00-200-001-A). Aircraft Stability

** ON A/C 101-104, 108-200, 451-500(Ref. 05-57-00-200-001-B). Aircraft Stability

** ON A/C 201-250(Ref. 05-57-00-200-001-C). Aircraft Stability

** ON A/C ALL(Ref. 29-10-00-864-001-A). Depressurize the Green Hydraulic System(Ref. 29-10-00-864-002-A). Depressurize the Yellow Hydraulic System(Ref. 29-14-00-614-001-A). Depressurization of the Hydraulic Reservoirs

** ON A/C 027-028, 251-300, 513-650(Ref. 31-36-00-740-006-A). Printout of the APU Hours and Cycles(Ref. 31-36-00-740-007-A). Printout of the Engine Hours and Cycles

** ON A/C 001-018, 025-025, 053-104, 108-250, 301-500, 651-700(Ref. 31-36-00-740-015-A). Printout of the Engine/APU Hours and Cycles Stored in the Flight Data

Interface and Management Unit (FDIMU)





REFERENCE DESIGNATION

** ON A/C 001-018, 025-025, 027-028, 053-104, 301-500, 513-700PRE SB 36-1055 for A/C 001-018, 025-025, 027-028, 053-054, 101-104, 301-302, 401-401, 451-452,513-513, 601-601(Ref. 36-11-49-000-016-A). Removal of the Sense Line between the Bleed Pressure-Regulator

Valve (PRV) and the Pylon Interface

** ON A/C ALL(Ref. 70-23-11-911-013-A). General Torque Tightening Techniques(Ref. 70-23-13-911-010-A). Procedures for the Installation of Preformed Packings(Ref. 71-13-00-010-010-A). Opening of the Fan Cowls 437AL(447AL),438AR(448AR)(Ref. 71-13-00-410-010-A). Closing of the Fan Cowls 437AL(447AL),438AR(448AR)(Ref. 71-71-42-000-010-A). Removal of the Drains Mast(Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for

Ground Maintenance(Ref. 78-32-00-010-010-A). Opening of the Thrust Reverser Halves(Ref. 78-32-00-410-010-A). Closing of the Thrust Reverser HalvesHydraulic Control Unit SHEET 1Fan Cowl and Thrust Reverser BracesFuel Drain Plug Location SHEET 1Power Plant, Right Side SHEET 1Left Interface Junction Box SHEET 1Forward Junction Box SHEET 1Power Plant, Left Side SHEET 1Left Connectors Location SHEET 1TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1Forward Engine Mount SHEET 1Bootstrap InstallationEngine Handling PointsAft Engine Mount SHEET 1





13480A

LEVER3 LOCKOUT

FLAG4 WARNING

2 LOCKPIN

PYLON

1 HCU

A

A

N_MM_710020_4_XAM0_01_00

Figure 71(IAE)-00-20-991-90000-A / SHEET 1/1 - Hydraulic Control Unit** ON A/C ALL





PYLON(1) ADJUSTABLE

STRUT(2) ADJUSTABLE

STRUT

T/R OPENING ACTUATOR

T/R COWL DOOR

A

N_MM_710020_4_YCN0_01_00

Figure 71(IAE)-00-20-991-91400-A / SHEET 1/3 - Fan Cowl and Thrust Reverser Braces** ON A/C ALL





ADJUSTABLESTRUT

T/R OPENINGACTUATOR

THRUST REVERSERCOWL DOOR PYLON

N_MM_710020_4_YCN0_02_00






A

FAN COWLDOOR

4SUPPORT ARM

3BRACKETS

THRUST REVERSERCOWL DOOR

N_MM_710020_4_YCN0_03_00






10889B

OIL COOLERFUEL COOLED

FUEL PLUG

6 SEALING RING

7 FUEL DRAINPLUG

A

B

A

B

N_MM_710020_4_YAM0_01_00

Figure 71(IAE)-00-20-991-91300-A / SHEET 1/1 - Fuel Drain Plug Location** ON A/C ALL





CONNECTOR4005VC

FORWARDJUNCTION BOX

14047

JUNCTION BOXFORWARD PYLON

W

N_MM_710020_4_XEM0_01_00

Figure 71(IAE)-00-20-991-90200-A / SHEET 1/1 - Power Plant, Right Side** ON A/C ALL





CONNECTOR4001HA-A

GP5

CONNECTOR452VC-A

CONNECTOR454VC

CONNECTOR450VC-A

14054

A

A

N_MM_710020_4_XGM0_01_00

Figure 71(IAE)-00-20-991-90300-A / SHEET 1/1 - Left Interface Junction Box** ON A/C ALL





DUCT6 PYLON STARTER

5

4 STARTERDUCT

gc00

a5m

155

3

1 PYLONTAI DUCT

2 TAI DUCT

448VC457VC

402VC

404VC

447VC

406VC

405VC

408VC

407VC

401VC

409VC

403VC

400VC

7

20°

A

A

T-BOLT

COUPLING

COUPLING

N_MM_710020_4_XCM0_01_02

Figure 71(IAE)-00-20-991-90100-A / SHEET 1/1 - Forward Junction Box** ON A/C ALL





16913

HOSESUCTION

1 HYDRAULIC

TUBEPRESSURE

2 HYDRAULIC

11 GASKET

10 WASHER

9 BOLT

8 FUEL SUPPLYTUBE

7 HYDRAULIC CASEDRAIN TUBE

3 GASKET

4 FUEL RETURNTO TANK

TUBE

5 WASHER

6 BOLT

PANELFLUID DISCONNECT

A

B C D EF

B

C

A

E

D

F

N_MM_710020_4_XJM0_01_00

Figure 71(IAE)-00-20-991-90400-A / SHEET 1/1 - Power Plant, Left Side** ON A/C ALL





14006

4004VCCONNECTOR

4101KS-BCONNECTOR

CONNECTOR4101KS-A

G

N_MM_710020_4_XLM0_01_00

Figure 71(IAE)-00-20-991-90500-A / SHEET 1/1 - Left Connectors Location** ON A/C ALL





SENSOR TUBE11 THERMOSTAT

20 PRVSENSOR TUBE

TAI DUCT PYLON

19 COUPLING

18 DUCT

PYLONBLEED AIR

DUCT

7 COUPLING

10 BLEED AIR DUCT19 COUPLING

TAI DUCT

17156A

HYDRAULIC TANKPRESSURISATION TUBE

A

B

C

D

E

A

E

DB

C

N_MM_710020_4_XNM0_01_00

Figure 71(IAE)-00-20-991-90600-A / SHEET 1/1 - TAI Locationand Hydraulic Reservoir Pressurization Tube Location

** ON A/C ALL





B

B

1 BOLT

2 WASHER

3 PYLON

19 SHEAR PIN(2 OFF)

4 forwardENGINE MOUNT

18 BOLT

17 WASHER

16 NUT

9 BOLT

10 WASHER

11 RETAINER

12 RETAINER

5 NUT

6 RETAINER

7 WASHER

8 NUT13 RETAINER

14 WASHER

15 NUT 16865C

C

B

A

C

B

B

A

N_MM_710020_4_XVM0_01_00

Figure 71(IAE)-00-20-991-91000-A / SHEET 1/1 - Forward Engine Mount** ON A/C ALL





3

4

6

3

5

2 11

4

7

5

2

A

A

B

B

N_MM_710020_4_XXM0_01_00

Figure 71(IAE)-00-20-991-91100-A / SHEET 1/2 - Bootstrap Installation** ON A/C ALL





8

9

8

C

C

N_MM_710020_4_XXM0_02_00

Figure 71(IAE)-00-20-991-91100-A / SHEET 2/2 - Bootstrap Installation** ON A/C ALL





VIEW ON

E

REAR SUPPORT

REAR HANDLING POINTS

VIEW ON

F

FRONT FIXTURE

FORWARD HANDLING POINTS

BALL PIN

BALL PIN

HANDLING POINT

HANDLING POINT

E

F

N_MM_710020_4_XXN0_01_00

Figure 71(IAE)-00-20-991-19500-A / SHEET 1/2 - Engine Handling Points** ON A/C ALL





TROLLEY

CRADLE

FWD BOOTSTRAP

REAR BOOTSTRAP

HOIST

BOOTSTRAPPING POINT

N_MM_710020_4_XXN0_02_00

Figure 71(IAE)-00-20-991-19500-A / SHEET 2/2 - Engine Handling Points** ON A/C ALL





UP

6 BARREL NUT

4 AFT MOUNT

2 BOLT

3 WASHER1 PYLON

5 SHEAR PIN

A

A

N_MM_710020_4_XZM0_01_00

Figure 71(IAE)-00-20-991-91200-A / SHEET 1/1 - Aft Engine Mount** ON A/C ALL





3. Job Set-up

Subtask 71-00-20-740-056-A

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) .

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.

Subtask 71-00-20-941-050-A

B. Safety Precautions

(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 thisprocedure.

(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 thepneumatic system.

Subtask 71-00-20-865-050-A

WARNING: MAKE SURE THAT YOU OPEN THE CIRCUIT BREAKERS AS FOLLOWS:- 1JH, 2JH1 AND 3JH1 BEFORE 2KS1- 1JH, 2JH2 AND 3JH2 BEFORE 2KS2.IF YOU DO NOT OBEY THIS SEQUENCE, THERE IS A RISK OF ELECTROCUTION. THIS ISBECAUSE YOU WILL START CONTINUOUS IGNITION IF YOU OPEN CIRCUIT BREAKER2KS1 OR 2KS2 FIRST.

WARNING: OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND5DA1(2,3) BEFORE YOU OPEN THE PHC CIRCUIT BREAKERS 2DA1(2,3). IF YOU DO NOTOBEY THIS SEQUENCE:- THE PROBES WILL BECOME TOO HOT.- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PER-

SONNEL.

C. Open, safety and tag these circuit breakers in this sequence:

PANEL DESIGNATION FIN LOCATION122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12





PANEL DESIGNATION FIN LOCATION49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z1649VU ANTI ICE/PROBES/AOA/1 4DA1 D04122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z1449VU ANTI ICE/RAIN/RPLNT/CAPT 1DB1 D01122VU ANTI ICE/RAIN/RPLNT/F/O 1DB2 W11122VU ANTI ICE/WINDOWS/L 4DG1 X14122VU ANTI ICE/WINDOWS/R 4DG2 W14123VU ANTI ICE/L/WHSLD 1DG1 AF10123VU ANTI ICE/R/WHSLD 1DG2 AF0349VU ENGINE/1 AND 2/IGN/SYS A 1JH A03121VU ENGINE/ENG1 AND 2 FIRE EX-

TIG/BTL1/SQUIB/A1WE1 Q43

121VU ENGINE/ENG1 AND 2 FIRE EX-TIG/BTL1/SQUIB/B

2WE1 Q44

121VU ENGINE/ENG1 AND 2 FIRE EX-TIG/BTL2/SQUIB/A

1WE2 Q41

121VU ENGINE/ENG1 AND 2 FIRE EX-TIG/BTL2/SQUIB/B

2WE2 Q42

121VU RCDR/DFDR 7TU K16

** ON A/C 001-018, 025-025, 027-028, 053-104, 108-500, 513-65049VU COM/CVR/SPLY 2RK E1449VU COM/CVR/CTL 4RK E13

** ON A/C 651-70049VU COM/CVR/SPLY 23RK E1449VU COM/CVR/CTL 26RK E13

** ON A/C ALLFOR FIN 1000EM1 (ENGINE-1)121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R4149VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A0449VU ENGINE/1/FIRE DET/LOOP A 7WD1 A06121VU ENGINE/ENG1/FIRE DET/LOOP B 8WD1 Q38122VU ELEC/GCU/1 2XU1 T26122VU ANTI ICE/ENG/1 1DN1 X10FOR FIN 1000EM2 (ENGINE-2)121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42121VU ENGINE/ENG2/FADEC B/AND EIU 2 4KS2 Q4049VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39





PANEL DESIGNATION FIN LOCATION49VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07122VU ELEC/GCU/2 2XU2 T27123VU Y HYD/ELEC/ELEC PUMP/NORM 3801GX AB03123VU Y HYD/ELEC/PUMP 3802GX AB06121VU HYDRAULIC/HYD POWER/Y 3803GX N30122VU ANTI ICE/ENG/2 1DN2 W10

Subtask 71-00-20-865-068-A

WARNING: OPEN THE PROBE HEATER AND WINDOW HEATER CIRCUIT-BREAKERS BEFOREYOU OPEN THE PHC AND WHC CIRCUIT BREAKERS. IF YOU DO NOT OBEY THIS SE-QUENCE:- THE PROBES WILL BECOME TOO HOT.- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PER-

SONNEL.

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

PANEL DESIGNATION FIN LOCATION49VU ANTI ICE/PROBES/PHC/1 2DA1 D03122VU ANTI ICE/WHC/2 5DG2 W13122VU ANTI ICE/WHC/1 5DG1 X13122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12

Subtask 71-00-20-864-050-A

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 71-00-20-010-050-A

F. Get Access

(1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010) :

(2) FOR 1000EM1 (ENGINE-1)437AL, 438AR


(4) Put the ACCESS PLATFORM 1M(3 FT) in position at engine level.

Subtask 71-00-20-040-050-A

G. Deactivate the Thrust Reverser

WARNING: THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) MUST BE DEACTIV-ATED BEFORE WORKING ON OR AROUND THE THRUST REVERSER. FAILURE TO





DEACTIVATE THE HCU CAN RESULT IN INADVERTENT THRUST REVERSER OPERA-TION 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) .(Ref. Fig. Hydraulic Control Unit SHEET 1)

Subtask 71-00-20-010-051-A

H. Open the thrust reverser doors (Ref. AMM TASK 78-32-00-010-010) but do not release the pressureafter you put the hold open rods in position.



Subtask 71-00-20-480-050-A

J. Install the BRACE - HOLD OPEN COWLS (S889BH0) or BRACE-HOLD OPENCOWLS (TMHBS13-00-00) to Support the Fan and Thrust Reverser Cowl Doors(Ref. Fig. Fan Cowl and Thrust Reverser Braces)

(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 fromthe 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) .

Subtask 71-00-20-680-050-A

K. Drain the Fuel that Stays in the Engine and the Pylon Fuel Hose, to Do this Drain at Level of the FuelFilter 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).(Ref. Fig. Fuel Drain Plug Location SHEET 1)

(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 IPC -CSN (73-12-42-80-070) seal ring (6) with clean lubricant(engine oil) (Material No. V10-077) 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 110 and 120 lbf.in (1.24 and 1.36 m.daN) (Ref. AMM TASK 70-23-11-911-013) .

(8) Safety the fuel drain plug with lockwire (Material No. V02-147).





Subtask 71-00-20-020-051-A

L. 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) .

NOTE: When you install the engine in the transportation stand it is only necessary to remove thedrains mast to prevent damage. It is not necessary to disconnect the drain tubes or removethe collector plate assembly.

(2) Remove these components from the right side of the engine.(Ref. Fig. Power Plant, Right Side SHEET 1)

(a) At the left interface electrical junction box:(Ref. Fig. Left Interface Junction Box SHEET 1) · Disconnect the electrical connectors 450VC, 452VC and 454VC.

(b) At the forward pylon electrical junction box:(Ref. Fig. Forward Junction Box SHEET 1)

1 Cut and discard the lockwire safetying the IDG harness connector 400VC and disconnectthe 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 1o'clock, looking forward.(Ref. Fig. Power Plant, Right Side SHEET 1)

(d) Remove the coupling (5) and disconnect the upper starter duct (4) from the pylon duct (6).(Ref. Fig. Forward Junction Box SHEET 1)

(e) Remove the coupling (3) and disconnect the Thermal Anti-ice duct (TAI) (2) located on the fancase close by the pylon from the pylon TAI duct (1).(Ref. Fig. Forward Junction Box SHEET 1)

(3) Remove these components from the left side of the engine.(Ref. Fig. Power Plant, Left Side SHEET 1) (Ref. Fig. Left Connectors Location SHEET 1) (Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)

(a) Disconnect the thrust reverser harness connectors 4101KS-A and 4101KS-B from the thrustreverser Hydraulic Control Unit (HCU).

(b) Disconnect the electrical connector 4004VC located by the V groove on the fan case, at 11o'clock, looking forward.(Ref. Fig. Left Connectors Location SHEET 1)

(c) Remove the couplings (19) and disconnect the TAI duct (18) located close by the forward mount.(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)

(d) Remove the coupling (7) and disconnect the cabin air duct (10).(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)

(e) Disconnect the hydraulic tubes from the fluid disconnect panel.(Ref. Fig. Power Plant, Left Side SHEET 1)

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.(Ref. Fig. Power Plant, Left Side SHEET 1)

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). Removeand discard the gasket (11).

(g) Disconnect the sensor tubes from the bracket situated forward of the pylon.(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)

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 onthe combustor case at 11 o'clock.(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)

** ON A/C 001-018, 025-025, 027-028, 053-104, 301-500, 513-700PRE SB 36-1055 for A/C 001-018, 025-025, 027-028, 053-054, 101-104, 301-302, 401-401, 451-452, 513-513,601-601

Subtask 71-00-20-020-070-A

M. 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) .

** ON A/C ALL

Subtask 71-00-20-620-050-A

N. Install CAP - BLANKING to all openings and connectors.

4. Procedure

Subtask 71-00-20-020-052-A

A. Loosen the Forward Engine Mount Bolts(Ref. Fig. Forward Engine Mount SHEET 1)

CAUTION: LOOSEN ONLY ONE BOLT AT A TIME. MAKE SURE THE BOLT IS TIGHT BEFORETHE 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 1056 and 1584 lbf.in (11.93 and 17.90 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 71-00-20-020-061-A

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 CHEST,TORQUE SET-ENGINE RI (98D71203001000) .





Subtask 71-00-20-480-051-A

C. Installation of the Support Equipment

(1) Install the BOOTSTRAP SYSTEM (98D71203501000) .(Ref. Fig. Bootstrap Installation)

(a) Put the rear beam (9) in position on the lower part of the pylon and install the pins (8).

(b) Install the spacer and the center hinge clamp (6) on the front of the pylon . Secure the spacerwith the clamps (7).

(c) Put the forward hinge arms (4) and (5) in position and install the pins (3).

(d) Make sure that the forward hinge arms (4) and (5) are and remain in the horizontal position. Todo this use the spirit levels installed on the arms.

(e) Install the link (2) and secure with the pins (1).

(f) Install the dynamometers and the chain pulley blocks.

(2) Install the ENGINE TROLLEY (S487ETT2) or TRAILER,ENGINE GROUND HANDLING(CFM56-5AND IAE V2500) (TMHET06-00-00) .(Ref. Fig. Engine Handling Points)

(a) Put in position the engine trolley and ENGINE CRADLE (S1787CR) or CRADLE,V2500ENGINE (TMHEC29-00-00) assembly from forward to aft, below the engine.

(b) Attach the chain hooks to the engine cradle.

(c) Remove the pins which attach the engine cradle to the engine trolley.

(d) Lift the engine cradle to the engine with the four chain pulley blocks.

(e) Install the pins of the front fixtures into the engine handling points and then install the rearsupport on the left and right sides. Attach to the engine with a ball pin.

NOTE: Use the chain pulley blocks to align the engine cradle with the engine.

(f) Operate the handling hoists at the same time until these values show on the dynamometers:

1 1900 daN (plus 150 daN or minus 100 daN) (4271 lbf) (1936 Kg) for the forwarddynamometers

2 500 daN (plus 100 daN or minus 50 daN) (1124 lbf) (509 Kg) for the aft dynamometers.

NOTE: The dynamometer values are applicable to the demountable power plant which in-cludes the engine assembly, the air inlet cowl, the CNA.

Subtask 71-00-20-020-050-A

D. Removal of the Power Plant

WARNING: DEATH OR SERIOUS INJURY MAY RESULT IF THE POWER PLANT FALLS ON PER-SONNEL. THE POWER PLANT WEIGHS APPROXIMATELY 7300 POUNDS.

WARNING: DO NOT TOW OR MOVE THE AIRCRAFT ON THE GROUND IF THE THRUST REVERS-ER IS ON THE PYLON WITH THE ENGINE REMOVED. MOVEMENT OF THE AIRCRAFTCAN CAUSE DAMAGE TO THE PYLON OR THE THRUST REVERSER.

CAUTION: DO NOT LET THE FORWARD ENGINE MOUNT FALL ON TO THE ENGINE WHEN THEBOLTS ARE REMOVED. THE VSV UNISON RINGS, HARNESSES AND TUBES CAN BEEASILY DAMAGED IF THE FORWARD MOUNT FALLS. PUT PADDING BETWEEN THEENGINE 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 TOOFAR, THERE IS A RISK OF DAMAGE TO HINGE N°4.

(1) Disconnect the forward engine mount.(Ref. Fig. Forward Engine Mount SHEET 1)

(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 attachthe front engine mount to the pylon.

(c) Remove nut (8), washer (7), retainer (6) and nut (5).

(2) Disconnect the aft engine mount.(Ref. Fig. Aft Engine Mount SHEET 1)

(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 enginemount (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 thepylon and the engine mount mating faces stay parallel so that you can easily disengage the shearpins.

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 asnear 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(Ref. Fig. Bootstrap Installation)

(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).

End of document

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