AIRBUS A320 Removal Power Plant

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

** ON A/C ALL TASK 71-00-20-000-040-A Removal of the Power Plant WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR.

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. MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.

WARNING:

MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

WARNING:

BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'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 storage procedures are more effective when the engine can be run or motored. 1.

Reason for the Job Self explanatory

2

Job Set-up Information A.

Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific No specific No specific

QTY AR AR AR AR AR

No specific (98D71203001000) (98D71203501000) (S1787CR) (S487ETT2) (S889BH0) (TMHBS13-00-00)

1 1 1 1 1 1

DESIGNATION ACCESS PLATFORM 1M(3 FT) CAP - BLANKING CONTAINER - CLEAN, APPLICABLE SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) Torque wrench: range to between 62.00 and 900.00 lbf.in (0.70 and 10.00 m.daN) Torque wrench: range to between 180.00 and 1800.00 lbf.in (2.00 and 20.00 m.daN) CHEST,TORQUE SET-ENGINE R I BOOTSTRAP SYSTEM ENGINE CRADLE ENGINE TROLLEY BRACE - HOLD OPEN COWLS BRACE-HOLD OPEN COWLS

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

Page 1 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

REFERENCE (TMHEC29-00-00) (TMHET06-00-00) B.

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

Consumable Materials REFERENCE (Material No. V02-147) (Material No. V10-077)

DESIGNATION lockwire lubricant (engine oil)

C. Work Zones and Access Panels ZONE/ACCESS FOR 1000EM1 (ENGINE-1) 437AL, 438AR, 451AL, 452AR FOR 1000EM2 (ENGINE-2) 447AL, 448AR, 461AL, 462AR

ZONE DESCRIPTION

D. Expendable Parts FIG.ITEM 6 E.

DESIGNATION seal ring

IPC-CSN 73-12-42-80-070

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). (Ref. 29-10-00-864-002-A). (Ref. 29-14-00-614-001-A).

Depressurize the Green Hydraulic System Depressurize the Yellow Hydraulic System 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)

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

Page 2 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

REFERENCE

DESIGNATION

** ON A/C 001-018, 025-025, 027-028, 053-104, 301-500, 513-700 PRE 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). (Ref. 70-23-13-911-010-A). (Ref. 71-13-00-010-010-A). (Ref. 71-13-00-410-010-A). (Ref. 71-71-42-000-010-A). (Ref. 78-30-00-040-012-A).

General Torque Tightening Techniques Procedures for the Installation of Preformed Packings Opening of the Fan Cowls 437AL(447AL),438AR(448AR) Closing of the Fan Cowls 437AL(447AL),438AR(448AR) Removal of the Drains Mast Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance Opening of the Thrust Reverser Halves Closing of the Thrust Reverser Halves

(Ref. 78-32-00-010-010-A). (Ref. 78-32-00-410-010-A). Hydraulic Control Unit SHEET 1 Fan Cowl and Thrust Reverser Braces Fuel Drain Plug Location SHEET 1 Power Plant, Right Side SHEET 1 Left Interface Junction Box SHEET 1 Forward Junction Box SHEET 1 Power Plant, Left Side SHEET 1 Left Connectors Location SHEET 1 TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1 Forward Engine Mount SHEET 1 Bootstrap Installation Engine Handling Points Aft Engine Mount SHEET 1

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

Page 3 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

A PYLON 1 HCU

2 LOCKPIN

4 WARNING FLAG

A

3 LOCKOUT LEVER

13480A 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 Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

A

T/R OPENING ACTUATOR

(1) ADJUSTABLE STRUT

PYLON

(2) ADJUSTABLE STRUT

T/R COWL DOOR

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

Page 5 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

THRUST REVERSER COWL DOOR

ADJUSTABLE STRUT

T/R OPENING ACTUATOR

PYLON

N_MM_710020_4_YCN0_02_00

Figure 71(IAE)-00-20-991-91400-A / SHEET 2/3 - Fan Cowl and Thrust Reverser Braces ** ON A/C ALL Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

THRUST REVERSER COWL DOOR

A

FAN COWL DOOR

3 BRACKETS

4 SUPPORT ARM

N_MM_710020_4_YCN0_03_00

Figure 71(IAE)-00-20-991-91400-A / SHEET 3/3 - Fan Cowl and Thrust Reverser Braces ** ON A/C ALL Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

A

A

B

FUEL COOLED OIL COOLER

B

FUEL PLUG 6 SEALING RING 7 FUEL DRAIN PLUG

10889B 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 Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

FORWARD PYLON JUNCTION BOX

W

FORWARD JUNCTION BOX

CONNECTOR 4005VC

14047 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 Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

A CONNECTOR 450VC-A

A

CONNECTOR 454VC

GP5

CONNECTOR 452VC-A

CONNECTOR 4001HA-A

14054

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

Page 10 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

A

457VC

448VC

406VC

402VC

405VC 408VC

404VC 447VC

407VC 401VC

A

6 PYLON STARTER DUCT

400VC

409VC 403VC 20°

1 PYLON TAI DUCT

7 T-BOLT 3 COUPLING 5 COUPLING 4 STARTER DUCT

gc00a5m155

2 TAI DUCT

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

Page 11 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

2 HYDRAULIC PRESSURE TUBE

1 HYDRAULIC SUCTION HOSE

A B FLUID DISCONNECT PANEL

B

C

D

C

E F

A

11 GASKET 3 GASKET 10 WASHER

D 5 WASHER 9 BOLT 6 BOLT

F E 8 FUEL SUPPLY TUBE

4 FUEL RETURN TO TANK TUBE

7 HYDRAULIC CASE DRAIN TUBE

16913 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 Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

CONNECTOR 4101KS-B CONNECTOR 4101KS-A

CONNECTOR 4004VC

G

14006 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 Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 13 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

A C B A PYLON TAI DUCT

E 19 COUPLING

D HYDRAULIC TANK PRESSURISATION TUBE

E 11 THERMOSTAT SENSOR TUBE 18 DUCT

D B

20 PRV SENSOR TUBE PYLON BLEED AIR DUCT TAI DUCT

7 COUPLING

C

10 BLEED AIR DUCT

19 COUPLING 17156A

N_MM_710020_4_XNM0_01_00

Figure 71(IAE)-00-20-991-90600-A / SHEET 1/1 - TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C ALL Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 14 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

A

1 BOLT

A

2 WASHER

3 PYLON

B B 19 SHEAR PIN (2 OFF)

B B C B

4 forward ENGINE MOUNT

18 BOLT 9 BOLT 17 WASHER

C 10 WASHER

11 RETAINER 16 NUT

5 NUT 6 RETAINER

12 RETAINER

7 WASHER 8 NUT

13 RETAINER 14 WASHER 16865C

15 NUT

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

Page 15 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

A B

1 2 1

A

6 3 3

5

4

B

2

4

5 7

N_MM_710020_4_XXM0_01_00

Figure 71(IAE)-00-20-991-91100-A / SHEET 1/2 - Bootstrap Installation ** ON A/C ALL Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 16 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

C

C 8

8

9

N_MM_710020_4_XXM0_02_00

Figure 71(IAE)-00-20-991-91100-A / SHEET 2/2 - Bootstrap Installation ** ON A/C ALL Print Date: October 27, 2015 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 17 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

HANDLING POINT

F BALL PIN HANDLING POINT

E

FRONT FIXTURE

REAR SUPPORT

FORWARD HANDLING POINTS

REAR HANDLING POINTS

VIEW ON

VIEW ON

E

F BALL PIN

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

Page 18 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

REAR BOOTSTRAP FWD BOOTSTRAP

CRADLE

TROLLEY

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

Page 19 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

A

A 2 BOLT 1 PYLON

3 WASHER

5 SHEAR PIN

4 AFT MOUNT

UP

6 BARREL NUT

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

Page 20 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

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 followup (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 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 71-00-20-865-050-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 IS BECAUSE YOU WILL START CONTINUOUS IGNITION IF YOU OPEN CIRCUIT BREAKER 2KS1 OR 2KS2 FIRST.

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: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.

C.

Open, safety and tag these circuit breakers in this sequence: PANEL 122VU 122VU

DESIGNATION ANTI ICE/PROBES/2/TAT ANTI ICE/PROBES/1/TAT

FIN 1DA2 1DA1

LOCATION Y15 Z12

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

Page 21 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

PANEL 49VU 122VU 122VU 49VU 122VU 122VU 122VU 122VU 122VU 49VU 122VU 122VU 122VU 123VU 123VU 49VU 121VU

FIN 3DA1 3DA2 3DA3 4DA1 4DA2 4DA3 5DA1 5DA2 5DA3 1DB1 1DB2 4DG1 4DG2 1DG1 1DG2 1JH 1WE1

D02 Y14 Z16 D04 Y13 Z15 Z13 Y11 Z14 D01 W11 X14 W14 AF10 AF03 A03 Q43

2WE1

Q44

1WE2

Q41

2WE2

Q42

7TU

K16

** ON A/C 001-018, 025-025, 027-028, 053-104, 108-500, 513-650 49VU COM/CVR/SPLY 2RK 49VU COM/CVR/CTL 4RK

E14 E13

** ON A/C 651-700 49VU COM/CVR/SPLY 49VU COM/CVR/CTL

23RK 26RK

E14 E13

2JH1 3JH1 4KS1 2KS1 7WD1 8WD1 2XU1 1DN1

P39 P41 R41 A04 A06 Q38 T26 X10

2JH2 3JH2 4KS2 2KS2 7WD2

P40 P42 Q40 A05 Q39

121VU 121VU 121VU 121VU

** ON A/C ALL FOR FIN 1000EM1 121VU 121VU 121VU 49VU 49VU 121VU 122VU 122VU FOR FIN 1000EM2 121VU 121VU 121VU 49VU 121VU

DESIGNATION ANTI ICE/PROBES/PITOT/1 ANTI ICE/PROBES/2/PITOT ANTI ICE/PROBES/3/PITOT ANTI ICE/PROBES/AOA/1 ANTI ICE/PROBES/2/AOA ANTI ICE/PROBES/3/AOA ANTI ICE/PROBES/1/STATIC ANTI ICE/PROBES/2/STATIC ANTI ICE/PROBES/3/STATIC ANTI ICE/RAIN/RPLNT/CAPT ANTI ICE/RAIN/RPLNT/F/O ANTI ICE/WINDOWS/L ANTI ICE/WINDOWS/R ANTI ICE/L/WHSLD ANTI ICE/R/WHSLD ENGINE/1 AND 2/IGN/SYS A ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A ENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A ENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B RCDR/DFDR

(ENGINE-1) ENGINE/IGN/ENG1/SYS A BAT ENGINE/IGN/ENG1/SYS B ENGINE/ENG1/FADEC B/AND EIU 1 ENGINE/1/FADEC A/AND EIU 1 ENGINE/1/FIRE DET/LOOP A ENGINE/ENG1/FIRE DET/LOOP B ELEC/GCU/1 ANTI ICE/ENG/1 (ENGINE-2) ENGINE/IGN/ENG2/SYS A BAT ENGINE/IGN/ENG2/SYS B ENGINE/ENG2/FADEC B/AND EIU 2 ENGINE/2/FADEC A/AND EIU 2 ENGINE/ENG2/FIRE DET/LOOP A

LOCATION

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

Page 22 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

PANEL 49VU 122VU 123VU 123VU 121VU 122VU

DESIGNATION ENGINE/2/FIRE DET/LOOP B ELEC/GCU/2 Y HYD/ELEC/ELEC PUMP/NORM Y HYD/ELEC/PUMP HYDRAULIC/HYD POWER/Y ANTI ICE/ENG/2

FIN 8WD2 2XU2 3801GX 3802GX 3803GX 1DN2

LOCATION A07 T27 AB03 AB06 N30 W10

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

D.

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: - THE PROBES WILL BECOME TOO HOT. - THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.

Open, safety and tag this(these) circuit breaker(s): PANEL 49VU 122VU 122VU 122VU 122VU

DESIGNATION ANTI ICE/PROBES/PHC/1 ANTI ICE/WHC/2 ANTI ICE/WHC/1 ANTI ICE/PROBES/PHC/3 ANTI ICE/PROBES/PHC/2

FIN 2DA1 5DG2 5DG1 2DA3 2DA2

LOCATION D03 W13 X13 Y16 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 (3) FOR 1000EM2 (ENGINE-2) 447AL, 448AR (4) Put the ACCESS PLATFORM 1M(3 FT) in position at engine level.

Subtask 71-00-20-040-050-A G. Deactivate the Thrust Reverser WARNING: THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) MUST BE DEACTIVATED BEFORE WORKING ON OR AROUND THE THRUST REVERSER. FAILURE TO

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

Page 23 of 28

Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

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) . (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 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 71-00-20-480-050-A J.

Install the BRACE - HOLD OPEN COWLS (S889BH0) or BRACE-HOLD OPEN COWLS (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 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) .

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 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). (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).

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

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Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

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 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. (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 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. (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 fan case 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 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. (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).

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

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Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

(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). Remove and 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 on the 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, 513-700 PRE 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. 4.

Install CAP - BLANKING to all openings and connectors.

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 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 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 R I (98D71203001000) .

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

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Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

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 spacer with 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. To do 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(CFM56-5 AND IAE V2500) (TMHET06-00-00) . (Ref. Fig. Engine Handling Points) (a) Put in position the engine trolley and ENGINE CRADLE (S1787CR) or CRADLE,V2500 ENGINE (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 rear support 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 forward dynamometers

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 includes 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 PERSONNEL. THE POWER PLANT WEIGHS APPROXIMATELY 7300 POUNDS. 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.

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

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Customer : AEE Manual : AMM Type : TF-N Selected applicability : ALL Rev. Date : Aug 01, 2015 71-00-20-000-040-A - Removal of the Power Plant

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. (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 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. (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 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 (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

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

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