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Engine Change

This document outlines the procedures for the removal and installation of the power plant on Airbus A318/A319/A320/A321 aircraft, including safety warnings and required tools. It details the necessary equipment, consumables, and references for the task, emphasizing the importance of safety measures and proper handling. The document is intended for maintenance personnel and includes specific instructions to ensure safe and effective execution of the job.

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0% found this document useful (0 votes)

78 views108 pages

Engine Change

Uploaded by

Amit Kc

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You are on page 1/ 108

Customer : RNA Manual : AMM

Type : A318/A319/A320/A321 Selected applicability : 001-001

Rev. Date : Feb 01, 2018
71-00-20 PB 401 CONF 13 - POWER PLANT -
DEMOUNTABLE - REMOVAL/INSTALLATION

** ON A/C ALL

71-00-20 PB 401 CONF 13 - POWER PLANT -

DEMOUNTABLE - REMOVAL/INSTALLATION

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. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURY TO PERSONS AND DAM-
AGE 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.
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. UNWANTED ELECTRICAL POWER CAN
BE DANGEROUS.

WARNING: YOU MUST FIND AND OBEY THE MANUFACTURER'S HEALTH AND SAFETY DATA FOR THE
MATERIAL (MSDS). YOU MUST ALSO REFER TO LOCAL REGULATIONS TO MAKE SURE
THAT THE PROCEDURES ARE DONE SAFELY. IF YOU DO NOT DO THIS, AN INJURY OR EN-
VIRONMENTAL DAMAGE CAN OCCUR.

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 Job

Self 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 1 CONTAINER - CLEAN, APPLICABLE
No specific AR SAFETY CLIP - CIRCUIT BREAKER
No specific AR WARNING NOTICE(S)
No specific Torque wrench: range to between 75 and 100 lbf.in
(0.85 and 1.13 m.daN)
No specific Torque wrench: range to between 110 and 120 lbf.in
(1.24 and 1.36 m.daN)

Print Date: February 18, 2018 Page 1 of 108

© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
Customer : RNA Manual : AMM
Type : A318/A319/A320/A321 Selected applicability : 001-001
Rev. Date : Feb 01, 2018
71-00-20 PB 401 CONF 13 - POWER PLANT -
DEMOUNTABLE - REMOVAL/INSTALLATION

REFERENCE QTY DESIGNATION

No specific Torque wrench: range to between 1056 and 1584 lbf.in
(11.93 and 17.90 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
(TMHEC29-00-00) 1 CRADLE,V2500 ENGINE
(TMHET06-00-00) 1 TRAILER,ENGINE GROUND HANDLING

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 DESCRIPTION

FOR 1000EM1 (ENGINE-1)
437AL, 438AR,
451AL, 452AR
FOR 1000EM2 (ENGINE-2)
447AL, 448AR,
461AL, 462AR

D. Expendable Parts

FIG.ITEM DESIGNATION IPC-CSN

6 seal ring 73-12-42-80-070

E. Referenced Information

REFERENCE DESIGNATION
(Ref. 05-57-00-200-001-A). Aircraft Stability
(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
(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)

** ON A/C ALL
PRE SB 36-1055 for A/C 001-002
(Ref. 36-11-49-000-016-A). Removal of the Sense Line between the Bleed Pressure-Regulator
Valve (PRV) and the Pylon Interface

Print Date: February 18, 2018 Page 2 of 108

REFERENCE DESIGNATION

** ON A/C ALL
(Ref. 70-11-56-910-001-A). Cleaning Requirements after Chemical Contact with Fire Extinguisher
Agents, Hydraulic Fluid, Oil or Fuel
(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 Halves
Hydraulic Control Unit SHEET 1
Fan Cowl and Thrust Reverser Braces
Fuel Drain Plug Location SHEET 1
LP/HP Fuel Pump Bleeder Plug 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
Anti-Ice Pylon Duct SHEET 1

Print Date: February 18, 2018 Page 3 of 108

A
PYLON

1 HCU

2 LOCKPIN

4 WARNING
FLAG

3 LOCKOUT
A LEVER

13480A
N_MM_710020_4_XAM0_01_00

Figure 71(IAE)-00-20-991-90000-13-A / SHEET 1/1 - Hydraulic Control Unit

** ON A/C ALL

Print Date: February 18, 2018 Page 4 of 108

T/R OPENING ACTUATOR

(1) ADJUSTABLE (2) ADJUSTABLE

STRUT PYLON STRUT

T/R COWL DOOR

N_MM_710020_4_YCN0_01_00

Figure 71(IAE)-00-20-991-91400-13-A / SHEET 1/3 - Fan Cowl and Thrust Reverser Braces
** ON A/C ALL

Print Date: February 18, 2018 Page 5 of 108

THRUST REVERSER ADJUSTABLE T/R OPENING

COWL DOOR STRUT ACTUATOR PYLON

N_MM_710020_4_YCN0_02_00

Figure 71(IAE)-00-20-991-91400-13-A / SHEET 2/3 - Fan Cowl and Thrust Reverser Braces
** ON A/C ALL

Print Date: February 18, 2018 Page 6 of 108

THRUST REVERSER
COWL DOOR

FAN COWL
3
DOOR
BRACKETS

4
SUPPORT ARM

N_MM_710020_4_YCN0_03_00

Figure 71(IAE)-00-20-991-91400-13-A / SHEET 3/3 - Fan Cowl and Thrust Reverser Braces
** ON A/C ALL

Print Date: February 18, 2018 Page 7 of 108

FUEL COOLED
OIL COOLER

FUEL PLUG
6 SEALING RING

7 FUEL DRAIN
PLUG

10889B

N_MM_710020_4_YAM0_01_00

Figure 71(IAE)-00-20-991-91300-13-A / SHEET 1/1 - Fuel Drain Plug Location

** ON A/C ALL

Print Date: February 18, 2018 Page 8 of 108

B
25 BLEEDER PLUG
PN MS9954-06
24 SEAL RING
PN M25988/1-906
TORQUE 75-100 LBF.IN
(8.47-11.30 N.M)

FUEL PUMP

B
pwzxxa0111

A
PWV

N_MM_710020_4_XAN0_01_00

Figure 71(IAE)-00-20-991-94900-13-A / SHEET 1/1 - LP/HP Fuel Pump Bleeder Plug

** ON A/C ALL

Print Date: February 18, 2018 Page 9 of 108

FORWARD PYLON
JUNCTION BOX

FORWARD
JUNCTION BOX

CONNECTOR
4005VC

14047

N_MM_710020_4_XEM0_01_00

Figure 71(IAE)-00-20-991-90200-13-A / SHEET 1/1 - Power Plant, Right Side

** ON A/C ALL

Print Date: February 18, 2018 Page 10 of 108

A
CONNECTOR
450VC-A

A CONNECTOR
454VC CONNECTOR
452VC-A

GP5 CONNECTOR
4001HA-A

14054

N_MM_710020_4_XGM0_01_00

Figure 71(IAE)-00-20-991-90300-13-A / SHEET 1/1 - Left Interface Junction Box

** ON A/C ALL

Print Date: February 18, 2018 Page 11 of 108

457VC 448VC

406VC 402VC

405VC 404VC
447VC
A 408VC

407VC

401VC

6 PYLON STARTER
DUCT 400VC 409VC

403VC

20° 1 PYLON
TAI DUCT

7
T-BOLT
3
COUPLING

5
COUPLING
4 STARTER
DUCT

2 TAI DUCT
gc00a5m155

N_MM_710020_4_XCM0_01_02

Figure 71(IAE)-00-20-991-90100-13-A / SHEET 1/1 - Forward Junction Box

** ON A/C ALL

Print Date: February 18, 2018 Page 12 of 108

1 HYDRAULIC 2 HYDRAULIC
SUCTION PRESSURE
HOSE TUBE

A
B
FLUID DISCONNECT
PANEL C
B C D E
F

11 GASKET
3 GASKET

10 WASHER

D
5 WASHER
9 BOLT
6 BOLT
F
E
4 FUEL RETURN
TO TANK
TUBE
8 FUEL SUPPLY 7 HYDRAULIC CASE
TUBE DRAIN TUBE

16913

N_MM_710020_4_XJM0_01_00

Figure 71(IAE)-00-20-991-90400-13-A / SHEET 1/1 - Power Plant, Left Side

** ON A/C ALL

Print Date: February 18, 2018 Page 13 of 108

CONNECTOR
4101KS-B

CONNECTOR
4101KS-A

CONNECTOR
4004VC

14006

N_MM_710020_4_XLM0_01_00

Figure 71(IAE)-00-20-991-90500-13-A / SHEET 1/1 - Left Connectors Location

** ON A/C ALL

Print Date: February 18, 2018 Page 14 of 108

A
PYLON
TAI DUCT

E
19 COUPLING

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 19 COUPLING
10 BLEED AIR DUCT
17156A

N_MM_710020_4_XNM0_01_00

Figure 71(IAE)-00-20-991-90600-13-A / SHEET 1/1 - TAI

Location and Hydraulic Reservoir Pressurization Tube Location
** ON A/C ALL

Print Date: February 18, 2018 Page 15 of 108

1 BOLT

A 2 WASHER

3 PYLON
B
B

19 SHEAR PIN
(2 OFF)

B
C
4 forward
ENGINE MOUNT
B

18 BOLT

9 BOLT
17 WASHER
C
10 WASHER

5 NUT
11 RETAINER
6 RETAINER
16 NUT
12 RETAINER
7 WASHER
8 NUT
13 RETAINER

14 WASHER
15 NUT 16865C

N_MM_710020_4_XVM0_01_00

Figure 71(IAE)-00-20-991-91000-13-A / SHEET 1/1 - Forward Engine Mount

** ON A/C ALL

Print Date: February 18, 2018 Page 16 of 108

B
1 2 1

3
5
4

2
B

N_MM_710020_4_XXM0_01_00

Figure 71(IAE)-00-20-991-91100-13-A / SHEET 1/2 - Bootstrap Installation

** ON A/C ALL

Print Date: February 18, 2018 Page 17 of 108

N_MM_710020_4_XXM0_02_00

Figure 71(IAE)-00-20-991-91100-13-A / SHEET 2/2 - Bootstrap Installation

** ON A/C ALL

Print Date: February 18, 2018 Page 18 of 108

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)-00-20-991-19500-13-A / SHEET 1/2 - Engine Handling Points

** ON A/C ALL

Print Date: February 18, 2018 Page 19 of 108

REAR BOOTSTRAP

FWD BOOTSTRAP

CRADLE

TROLLEY

HOIST

BOOTSTRAPPING POINT

N_MM_710020_4_XXN0_02_00

Figure 71(IAE)-00-20-991-19500-13-A / SHEET 2/2 - Engine Handling Points

** ON A/C ALL

Print Date: February 18, 2018 Page 20 of 108

2 BOLT
1 PYLON
3 WASHER

5 SHEAR PIN

4 AFT MOUNT

6 BARREL NUT

N_MM_710020_4_XZM0_01_00

Figure 71(IAE)-00-20-991-91200-13-A / SHEET 1/1 - Aft Engine Mount

** ON A/C ALL

Print Date: February 18, 2018 Page 21 of 108

22
21

NOTE:

INSPECTION AREA
N_MM_710020_4_XHM0_01_00

Figure 71(IAE)-00-20-991-94400-13-A / SHEET 1/1 - Anti-Ice Pylon Duct

** ON A/C ALL

Print Date: February 18, 2018 Page 22 of 108

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 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 PER-
SONNEL.

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

PANEL DESIGNATION FIN LOCATION

122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15
122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12

Print Date: February 18, 2018 Page 23 of 108

PANEL DESIGNATION FIN LOCATION

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 EX- 1WE1 Q43
TIG/BTL1/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE1 Q44
TIG/BTL1/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE2 Q41
TIG/BTL2/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE2 Q42
TIG/BTL2/SQUIB/B
121VU RCDR/DFDR 7TU K16
49VU COM/CVR/SPLY 2RK E14
49VU COM/CVR/CTL 4RK E13
FOR FIN 1000EM1 (ENGINE-1)
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 (ENGINE-2)
121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40
121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42
121VU ENGINE/ENG2/FADEC B/AND EIU 2 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

Print Date: February 18, 2018 Page 24 of 108

PANEL DESIGNATION FIN LOCATION

122VU ANTI ICE/ENG/2 1DN2 W10
49VU FUEL/LP VALVE/MOT1/ENG2 2QG A09
121VU FUEL/LP VALVE/MOT2/ENG2 4QG M26
Subtask 71-00-20-865-068-A

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 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 LOCATION

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
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 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) .

Print Date: February 18, 2018 Page 25 of 108

(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:

NOTE: There is an alternative fuel drain procedure in step 4.K.(2) where the fuel can be drained from the
bleeder plug (25) of the LP/HP fuel pump instead of the fuel cooled oil cooler. Only one of these
procedures is required.

(1) Procedure to drain the fuel from the fuel cooled oil cooler drain plug
(a) Put a CONTAINER - CLEAN, APPLICABLE under the fuel filter.
(b) Removal of the lockwire

WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR IN-
STALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DIS-
CARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU
BLIND, AND/OR CAN CAUSE DAMAGE.

1 Cut and discard the lockwire which safeties the fuel drain plug (7).
(Ref. Fig. Fuel Drain Plug Location SHEET 1)
(c) Remove the fuel drain plug and drain the fuel into the CONTAINER - CLEAN, APPLICABLE.

NOTE: Do not put fuel that you drained from the engine back into the fuel system.

(d) Remove the seal ring (6) from the fuel drain plug (7). Discard the seal ring (6).

Print Date: February 18, 2018 Page 26 of 108

(e) 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) .
(f) Install the fuel drain plug (7).
(g) TORQUE the fuel drain plug (7) to between 110 and 120 lbf.in (1.24 and 1.36 m.daN)
(Ref. AMM TASK 70-23-11-911-013) .
(h) Installation of the lockwire

1 Safety the fuel drain plug with lockwire (Material No. V02-147).
(2) Alternate fuel drain procedure from LP/HP fuel pump
(a) Put a CONTAINER - CLEAN, APPLICABLE under the LP/HP fuel pump.
(b) Removal of the lockwire

1 Cut and discard the lockwire which safeties the bleeder plug (25).
(Ref. Fig. LP/HP Fuel Pump Bleeder Plug SHEET 1)
(c) Remove the bleeder plug (25) from the HP/LP fuel pump and drain the fuel into the CONTAINER
- CLEAN, APPLICABLE.

NOTE: Do not put fuel that you drained from the engine back into the fuel system.

(d) Lubricate a new seal ring (24) (IPC-CSN 73-12-41-80A-XXX) with lubricant (engine
oil) (Material No. V10-077) and install it on the bleeder plug (25).
(e) Install the bleeder plug on the HP/LP fuel pump.
(f) TORQUE the bleeder plug (25) to between 75 and 100 lbf.in (0.85 and 1.13 m.daN)
(Ref. AMM TASK 70-23-11-911-013) .
(g) Installation of the lockwire

1 Safety the bleeder plug (25) 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) .

Print Date: February 18, 2018 Page 27 of 108

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)

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.

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

NOTE: It is permitted to secure the nut against the fluid disconnect panel during the hydraulic
tubes removal to prevent loosening of the union.

Print Date: February 18, 2018 Page 28 of 108

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

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 DETERIOR-
ATION 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.
(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 ALL
PRE SB 36-1055 for A/C 001-002
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)

Print Date: February 18, 2018 Page 29 of 108

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) .
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 (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.

Print Date: February 18, 2018 Page 30 of 108

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 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.

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.

Print Date: February 18, 2018 Page 31 of 108

(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).
(9) 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).
(Ref. Fig. Anti-Ice Pylon Duct SHEET 1)
(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 51-12-00-200-801-A01).
(d) If there is no damage, no further action is necessary.

TASK 71-00-20-000-040-A01
Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG)

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
GEAR. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURY TO PERSONS AND DAM-
AGE TO THE AIRCRAFT AND/OR EQUIPMENT.

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.

FIN : 1000EM1 , 1000EM2

1. Reason for the Job
Self explanatory
2 Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

Print Date: February 18, 2018 Page 32 of 108

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 110 and 120 lbf.in
(1.24 and 1.36 m.daN)
No specific Torque wrench: range to between 1056 and 1584 lbf.in
(11.93 and 17.90 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

B. Consumable Materials

REFERENCE DESIGNATION
(Material No. V02-147) lockwire
(Material No. V10-039) engine oil

C. Work Zones and Access Panels

ZONE/ACCESS ZONE DESCRIPTION

FOR 1000EM1 (ENGINE-1)
437AL, 438AR,
451AL, 452AR
FOR 1000EM2 (ENGINE-2)
447AL, 448AR,
461AL, 462AR

D. Expendable Parts

FIG.ITEM DESIGNATION IPC-CSN

6 seal ring 73-12-42-80-070

E. Referenced Information

** ON A/C ALL
PRE SB 36-1055 for A/C 001-002
(Ref. 36-11-49-000-016-A). Removal of the Sense Line between the Bleed Pressure-Regulator
Valve (PRV) and the Pylon Interface

Print Date: February 18, 2018 Page 33 of 108

REFERENCE DESIGNATION

** ON A/C ALL
(Ref. 70-11-56-910-001-A). Cleaning Requirements after Chemical Contact with Fire Extinguisher
Agents, Hydraulic Fluid, Oil or Fuel
(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 Halves
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
Aft Engine Mount SHEET 1
Anti-Ice Pylon Duct SHEET 1

3. Job Set-up
Subtask 71-00-20-740-058-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 71-00-20-941-054-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:

Print Date: February 18, 2018 Page 34 of 108

(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

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

PANEL DESIGNATION FIN LOCATION

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 EX- 1WE1 Q43
TIG/BTL1/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE1 Q44
TIG/BTL1/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE2 Q41
TIG/BTL2/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE2 Q42
TIG/BTL2/SQUIB/B

Print Date: February 18, 2018 Page 35 of 108

PANEL DESIGNATION FIN LOCATION

121VU RCDR/DFDR 7TU K16
49VU COM/CVR/SPLY 2RK E14
49VU COM/CVR/CTL 4RK E13
FOR FIN 1000EM1 (ENGINE-1)
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 (ENGINE-2)
121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40
121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42
121VU ENGINE/ENG2/FADEC B/AND EIU 2 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
Subtask 71-00-20-865-069-A

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

PANEL DESIGNATION FIN LOCATION

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
Subtask 71-00-20-864-053-A
E. Depressurize these Hydraulic Systems
(1) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the applicable system.

Print Date: February 18, 2018 Page 36 of 108

(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
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
G. Deactivate the Thrust Reverser

(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 71-00-20-010-060-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 71-00-20-480-058-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) 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) .

Print Date: February 18, 2018 Page 37 of 108

Subtask 71-00-20-680-056-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 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 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 71-00-20-020-066-A
L. 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) .

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.

Print Date: February 18, 2018 Page 38 of 108

(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)

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).

Print Date: February 18, 2018 Page 39 of 108

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 ALL
PRE SB 36-1055 for A/C 001-002
Subtask 71-00-20-020-071-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 71-00-20-620-051-A
N. Install CAP - BLANKING to all openings and connectors.
4. Procedure
Subtask 71-00-20-020-067-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.

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 ENGINE POSITIONER (TWW75E) 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.

Print Date: February 18, 2018 Page 40 of 108

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 CON-
NECTOR. THE VIBRATION SENSOR CONNECTOR IS IN FRONT OF THE FOR-
WARD 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.
Subtask 71-00-20-020-069-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 AIRCRAFT
CAN CAUSE DAMAGE TO THE PYLON OR THE THRUST REVERSER.

Print Date: February 18, 2018 Page 41 of 108

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 the nut (8), the washer (7), the retainer (6) and the 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) Remove the engine from the aircraft.
(a) Make sure that no line union remains connected from the pylon.
(b) Use the left joystick to lower the engine.
(c) Have an engine trolley available with the 90 inch rail system.
(d) Move the engine positioner away from the wing and assemble the rail system of the engine
positioner with the rail system of the engine trolley.
(e) Move the cradle from the positioner to the engine trolley.
(4) 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).
(Ref. Fig. Anti-Ice Pylon Duct SHEET 1)
(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.

TASK 71-00-20-400-040-A
Installation of the Power Plant

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

WARNING: MAKE SURE THAT THE LANDING GEAR GROUND SAFETIES AND THE WHEEL CHOCKS
ARE IN POSITION. MOVEMENT OF THE AIRCRAFT CAN BE DANGEROUS.

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.

Print Date: February 18, 2018 Page 42 of 108

CAUTION: DO A CHECK OF THE ENGINE DATA PLATE TO MAKE SURE THAT THE ENGINE IS COR-
RECT FOR THE AIRCRAFT.
IF YOU INSTALL AN ENGINE THAT DOES NOT HAVE THE CORRECT CONFIGURATION FOR
THE AIRCRAFT:
- DAMAGE TO EQUIPMENT CAN OCCUR IF YOU OPERATE THE ENGINE.
- THE TEST AFTER THE INSTALLATION WILL TELL YOU THAT THE ENGINE CONFIGURA-
TION IS NOT CORRECT AND MORE WORK WILL BE NECESSARY.

CAUTION: MAKE SURE THAT THE EEC STANDARDS INSTALLED ARE CORRECT. SOME EEC STAND-
ARDS CANNOT BE INTERMIXED ON A SAME AIRCRAFT.

CAUTION: MAKE SURE THAT THE TWO ENGINES INSTALLED ON THE AIRCRAFT HAVE THE SAME
GROUND IDLE CAPABILITY (REDUCED GROUND IDLE OR NON-REDUCED GROUND IDLE).
TWO ENGINES WITH DIFFERENT GROUND IDLE CAPABILITIES CAN CAUSE THRUST DIS-
SYMMETRY AND THUS DAMAGE TO THE AIRCRAFT.

FIN : 1000EM1 , 1000EM2

1. Reason for the Job
Self 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 1 DRILL - NO 21 (DIA 0.159 IN - 4.039 MM)
No specific 1 DYNAMOMETER 15 DAN (33 LBF) - PULL
No specific 1 MAGNIFYING GLASS POWER 10X
No specific AR PENCIL
No specific AR PLATE - STEEL, 500X500X3 MM (19.68X19.68X0.12 IN)
No specific AR WARNING NOTICE(S)
No specific 1 WRENCH - STRAP
No specific Torque wrench: range to between 88.49 and 132.74 lbf.ft
(12.00 and 18.00 m.daN)
No specific Torque wrench: range to between 6 and 8 lbf.in
(0.07 and 0.09 m.daN)
No specific Torque wrench: range to between 24 and 36 lbf.in
(0.27 and 0.41 m.daN)
No specific Torque wrench: range to between 35 and 40 lbf.in
(0.40 and 0.45 m.daN)
No specific Torque wrench: range to between 90 and 110 lbf.in
(1.02 and 1.24 m.daN)
No specific Torque wrench: range to between 215 and 245 lbf.in
(2.43 and 2.77 m.daN)
No specific Torque wrench: range to between 0.38 and 0.42 m.daN
(33.63 and 37.17 lbf.in)
No specific Torque wrench: range to between 0.79 and 0.9 m.daN
(69.91 and 79.65 lbf.in)
No specific Torque wrench: range to between 0.85 and 0.96 m.daN
(75.22 and 84.96 lbf.in)

Print Date: February 18, 2018 Page 43 of 108

REFERENCE QTY DESIGNATION

No specific Torque wrench: range to between 1.5 and 1.7 m.daN
(11.06 and 12.54 lbf.ft)
No specific Torque wrench: range to between 2.0 and 2.3 m.daN
(14.75 and 16.96 lbf.ft)
No specific Torque wrench: range to between 9.7 and 10.7 m.daN
(71.53 and 78.91 lbf.ft)
No specific Torque wrench: range to between 43.39 and 47.45 m.daN
(319.99 and 349.93 lbf.ft)
No specific Torque wrench: range to between 65 and 70.5 m.daN
(479.35 and 519.91 lbf.ft)
(98D71203001000) 1 CHEST,TORQUE SET-ENGINE R I
(98D71203501000) 1 BOOTSTRAP SYSTEM
(S1787CR) 1 ENGINE CRADLE
(S487ETT2) 1 ENGINE TROLLEY
(TMHEC29-00-00) 1 CRADLE,V2500 ENGINE
(TMHET06-00-00) 1 TRAILER,ENGINE GROUND HANDLING

B. Consumable Materials

REFERENCE DESIGNATION
(Material No. V01-457) solvent
(Material No. V02-147) lockwire
(Material No. V02-158A) release agent
(Material No. V02-272) safety cable
(Material No. V02-273) safety cable
(Material No. V02-274) safety cable
(Material No. V02-275) safety cable
(Material No. V02-276) safety cable
(Material No. V02-277) safety cable
(Material No. V02-278) safety cable
(Material No. V02-279) safety cable
(Material No. V02-280) safety cable
(Material No. V02-281) safety cable
(Material No. V08-030) sealant
(Material No. V08-032) primer
(Material No. V10-085) anti seize compound
(Material No. 14SBA1) Textile-Lint free Cotton -

C. Work Zones and Access Panels

ZONE/ACCESS ZONE DESCRIPTION

FOR 1000EM1 (ENGINE-1)
437AL, 438AR,
451AL, 452AR
FOR 1000EM2 (ENGINE-2)
447AL, 448AR,
461AL, 462AR

D. Expendable Parts

Print Date: February 18, 2018 Page 44 of 108

FIG.ITEM DESIGNATION IPC-CSN

17 screws 71-51-46-80-010
16 seal assembly 71-51-46-80-020
15 seal assembly 71-51-46-80-030
3 gasket 73-11-48-80-080
11 gasket 73-11-48-80-120

E. Referenced Information

REFERENCE DESIGNATION
(Ref. 05-57-00-200-001-A). Aircraft Stability
(Ref. 12-13-24-612-011-A). IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a
Level Check
(Ref. 12-13-79-610-012-A). Prime the Engine Oil System
(Ref. 12-13-80-600-010-B). Replenishment of Starter Oil System
(Ref. 20-28-00-720-005-A). Check of the Electrical Bonding of the Different Components (But not
Fluid Systems and Components Installed on Composite materials)
(Ref. 22-97-00-710-001-A). Operational Test of the LAND CAT III Capability
(Ref. 24-21-00-710-042-A). Operational Test of the IDG Disconnect and Reconnect (Reset) Func-
tion - Engine Static
(Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power
(Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU
(Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2)
(Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External
Power
(Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU
(Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine
1(2)
(Ref. 30-21-00-710-002-A). Operational Check of the Engine-Air-Intake Ice-Protection System
(with the Engines in operation)
(Ref. 30-21-49-790-010-A). Leak Test of the Inlet Cowl Anti-Ice Supply Ducts with the Engine in
Operation
(Ref. 30-21-49-820-001-A). Rig the Anti-ice Ducts
(Ref. 31-36-00-740-014-A). Update of the Engine Hours and Cycles in the Flight Data Interface
and Management Unit (FDIMU)
(Ref. 31-60-00-860-001-A). EIS Start Procedure
(Ref. 31-60-00-860-002-A). EIS Stop Procedure

** ON A/C ALL
PRE SB 36-1055 for A/C 001-002
(Ref. 36-11-49-400-016-A). Installation of the Sense Line between the Bleed Pressure-Regulator
Valve (PRV) and the Pylon Interface

Print Date: February 18, 2018 Page 45 of 108

REFERENCE DESIGNATION
(Ref. 70-40-11-911-014-A). Locking Devices General Information
(Ref. 70-40-11-911-016-A). General Instructions for Uses of Safety Cable
(Ref. 71-00-00-700-011-B). Test No.13 : Pretested Replacement Engine Test
(Ref. 71-00-00-710-012-B). Test No.3 : Idle Leak Check
(Ref. 71-00-00-710-022-B). Test No.6 : ELectronic Engine Control (EEC) System Idle Test
(Ref. 71-00-00-710-046-B). Test No.2 : Wet Motor Leak Check
(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. 71-13-00-800-010-A). Functional Check of Fan Cowl Latch Tension
(Ref. 71-21-12-200-010-A). Detailed Inspection of FWD Engine Mount Installation
(Ref. 71-22-11-200-010-A). Detailed Inspection of AFT Engine Mount Installation
(Ref. 71-71-42-400-010-A). Installation of the Drains Mast
(Ref. 72-61-49-400-010-B). Installation of the Gearbox Breather Outlet Duct (GBOD)
(Ref. 73-13-42-720-010-A). Functional Test of the Fuel Recirculation Cooling System without Bar-
field Tester and without AIDS
(Ref. 73-13-42-720-010-A-01). Functional Test of the Fuel Recirculation Cooling System with Barfield
Tester and without AIDS
(Ref. 73-13-42-720-010-A-02). Functional Test of the Fuel Recirculation Cooling System without Bar-
field Tester and with AIDS
(Ref. 73-13-42-720-010-A-03). Functional Test of the Fuel Recirculation Cooling System with Barfield
Tester and with AIDS
(Ref. 73-22-34-710-040-A). Operational Test of the EEC
(Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for
Ground Maintenance
(Ref. 78-30-00-440-012-A). Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after
Ground Maintenance
(Ref. 78-30-00-820-010-A). Rig of the Thrust Reverser System
(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 Halves
(Ref. 80-13-49-820-010-B). Rig the Starter Ducts
(Ref. 80-13-51-710-040-B). Operational Test of the Pneumatic Starter Valve and FMU with the CF-
DS
Ref. ESPM 20-48-23
Ref. ESPM 20-48-24
SPM 702305
(Ref. 05-59-00-00). SPECIAL FLIGHTS - DESCRIPTION AND OPERATION
Engine Identification Plate SHEET 1
Table 1 - New Data Entry Plug PN 2A4378 Variants SHEET 1
Table 2 - New Data Entry Plug PN 2A4378 Variants SHEET 1
Data Entry Plug Back Shell Inscription SHEET 1
Forward Engine Mount SHEET 1
Aft Engine Mount SHEET 1
Bootstrap Installation
Hinge Crossover Beam SHEET 1
Fan Cowl and Thrust Reverser Braces
TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1
Power Plant, Left Side SHEET 1
Left Connectors Location SHEET 1
Power Plant, Right Side SHEET 1
Forward Junction Box SHEET 1

Print Date: February 18, 2018 Page 46 of 108

REFERENCE DESIGNATION
Upper/Lower Link Starter Duct and Link Assembly SHEET 1
Forward Junction Box SHEET 1
Left Interface Junction Box SHEET 1
Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire
Seals SHEET 1
Fire Seal Installation SHEET 1
Hydraulic Control Unit SHEET 1
FOR 1000EM1 (ENGINE-1)
(Ref. 29-11-51-860-040-A). Hydraulic Maintenance Procedure after an Engine Installation (with En-
gine Pump Installed) or after an Engine Pump Installation
FOR 1000EM2 (ENGINE-2)
(Ref. 29-13-51-860-001-A). Hydraulic Maintenance Procedure after an Engine Installation (with En-
gine Pump Installed) or after an Engine Pump Installation

Print Date: February 18, 2018 Page 47 of 108

International EPR
MOD
Aero EnginesTM EMISSIONS FAR34 COMPLY

MODEL V2533-A5
TAKE-OFF RATING-BUMP VARIANT TYPE CERTIFICATE

31600 IDEAL 2-00 02 PROD CERTIFICATE 114NE

MODEL V2530-A5 MODEL V2527M-A5
TAKE-OFF RATING-BUMP VARIANT TAKE-OFF RATING-BUMP VARIANT
29900 IDEAL 3-00 12 24800 IDEAL 9-00 47
MODEL V2527-A5 MODEL V2524-A5
TAKE-OFF RATING-BUMP VARIANT TAKE-OFF RATING-BUMP VARIANT
24800 IDEAL 6-00 32 24480 IDEAL 8-00 42
MODEL V2527E-A5 MODEL V2522-A5
TAKE-OFF RATING-BUMP VARIANT TAKE-OFF RATING-BUMP VARIANT
24800 IDEAL 7-00 37 23040 IDEAL 10-00 52

DATE

ENGINE IDENTIFICATION PLATE (PN 5A1875)

International EPR
MOD
Aero EnginesTM EMISSIONS FAR34 COMPLY

MODEL V2533-A5
TAKE-OFF RATING-BUMP VARIANT TYPE CERTIFICATE

31600 IDEAL 2- PROD CERTIFICATE 114NE

MODEL V2530-A5 MODEL V2527M-A5
TAKE-OFF RATING-BUMP VARIANT TAKE-OFF RATING-BUMP VARIANT
29900 IDEAL 3- 24800 IDEAL 9-
MODEL V2527-A5 MODEL V2524-A5
TAKE-OFF RATING-BUMP VARIANT TAKE-OFF RATING-BUMP VARIANT
24800 IDEAL 6- 24480 IDEAL 8-
MODEL V2527E-A5 MODEL V2522-A5
TAKE-OFF RATING-BUMP VARIANT TAKE-OFF RATING-BUMP VARIANT
24800 IDEAL 7- 23040 IDEAL 10-

DATE

BLANK FOR MARKING OF DEP VARIANT AND

ENHANCEMENT/BUMP RATING
ENGINE IDENTIFICATION PLATE (PN 5A1942)
N_MM_710020_4_XAC0_01_00

Figure 71(IAE)-00-20-991-94500-13-A / SHEET 1/1 - Engine Identification Plate

** ON A/C ALL

Print Date: February 18, 2018 Page 48 of 108

VARIANT APPLICABLE THRUST BUMP CRANK RGI THRUST

NUMBER ENGINE LEVEL NUMBER (SEC) CAPABLE ENHANCEMENTS
CONFIGURATION (IF APPLICABLE)

01 A5-STANDARD V2533 00 30 No VSV MORE OPEN

SCHEDULE
02 A5-STANDARD V2533 00 30 No
04 A5-STANDARD V2533 02 30 No ENHANCED MCL
06 A5-SELECTTWO TM V2533 00 30 No
07 A5-SELECTTWO TM V2533 01 30 No BUMP ENABLED
08 A5-SELECTTWO TM V2533 02 30 No ENHANCED MCL
09 A5-SELECTTWO TM V2533 03 30 No BUMP ENABLED,
ENHANCED MCL

ENHANCED MCL,
11 A5-STANDARD V2533 02 30 No VSV MORE OPEN
SCHEDULE
12 A5-STANDARD V2530 00 30 No
14 A5-SELECTTWO TM V2530 00 30 No
15 A5-SELECTTWO TM V2533 10 30 YES
16 A5-SELECTTWO TM V2533 12 30 YES ENHANCED MCL
17 A5-SELECTTWO TM V2533 11 30 YES BUMP ENABLED
18 A5-SELECTTWO TM V2533 13 30 YES BUMP ENABLED,
ENHANCED MCL
19 A5-SELECTTWO TM V2530 10 30 YES
TM
20 A5-SELECTTWO V2527 10 30 YES
21 A5-SELECTTWO TM V2527E 10 30 YES
22 A5-SELECTTWO TM V2527E 11 30 YES BUMP ENABLED
23 A5-SELECTTWO TM V2527M 10 30 YES
24 A5-SELECTTWO TM V2524 10 30 YES
25 A5-SELECTTWO TM V2522 10 30 YES
32 A5-STANDARD V2527 00 30 No
34 A5-SELECTTWO TM V2527 00 30 No
37 A5-STANDARD V2527E 00 30 No
42 A5-STANDARD V2524 00 30 No
47 A5-STANDARD V2527M 00 30 No
49 A5-SELECTTWO TM V2527M 00 30 No
52 A5-STANDARD V2522 00 30 No
54 A5-SELECTTWO TM V2522 00 30 No
55 A5-SELECTTWO TM V2524 00 30 No
59 A5-SELECTTWO TM V2527E 00 30 No
60 A5-SELECTTWO TM V2527E 01 30 No BUMP ENABLED

N_MM_710020_4_XAD0_01_00

Figure 71(IAE)-00-20-991-94600-13-A / SHEET 1/1 - Table 1 - New Data Entry Plug PN 2A4378 Variants
** ON A/C ALL

Print Date: February 18, 2018 Page 49 of 108

BUMP NUMBER DESCRIPTION

00 NO BUMP
01 BUMP AVAILABLE FOR TAKE OFF
02 MCL ACTIVATED
03 BUMP FOR TAKE OFF AND MCL (BOTH AVAILABLE)
10 REDUCED GROUND IDLE WITH NO BUMP
11 REDUCED GROUND IDLE WITH BUMP AVAILABLE FOR TAKE OFF
12 REDUCED GROUND IDLE WITH MCL ACTIVATED
REDUCED GROUND IDLE WITH BUMP FOR TAKE OFF AND MCL
13
(BOTH AVAILABLE)

N_MM_710020_4_XAE0_01_00

Figure 71(IAE)-00-20-991-94700-13-A / SHEET 1/1 - Table 2 - New Data Entry Plug PN 2A4378 Variants
** ON A/C ALL

Print Date: February 18, 2018 Page 50 of 108

MARK THE ENGINE

RATING No

MARK THE BUMP No

MARK CL01

RATING - BUMP X-YY

P/N XXXXXX CL YY
EPR MOD XX-YY
VARIANT XX MARK THE PART No

MARK THE ENGINE

SERIAL No

MARK THE
EPR MODIFIER No

MARK THE
VARIANT WIRING No

N_MM_710020_4_XAF0_01_00

Figure 71(IAE)-00-20-991-94800-13-A / SHEET 1/1 - Data Entry Plug Back Shell Inscription
** ON A/C ALL

Print Date: February 18, 2018 Page 51 of 108

HINGE CROSS-OVER BEAM (1)

FAN CASE B
HINGE CROSS-OVER BEAM (1)

FAN CASE

V-GROOVE (2)

C
N_MM_710020_4_XZN0_01_00

Figure 71(IAE)-00-20-991-19600-13-A / SHEET 1/1 - Hinge Crossover Beam

** ON A/C ALL

Print Date: February 18, 2018 Page 52 of 108

A
17 UPPER LINK
ASSEMBLY

16 UPPER LINK
UPPER/LOWER ASSEMBLY
LINK ASSEMBLY
9 WASHER

7 NUT

BOLT 8
7 NUT
8 BOLT

7 NUT
9 WASHER

13 NUT
12 LOWER LINK
8 BOLT ASSEMBLY
18 BOLT
UPPER/LOWER
LINK ASSEMBLY
FAN CASE
BRACKET
8 BOLT

7 NUT
11 LOWER LINK
13 NUT ASSEMBLY

18 BOLT
pwzxxe9397

N_MM_710020_4_XDM0_01_00

Figure 71(IAE)-00-20-991-94200-13-A / SHEET 1/1 - Upper/Lower Link Starter Duct and Link Assembly
** ON A/C ALL

Print Date: February 18, 2018 Page 53 of 108

D
FLANGE A1
A
E
TYPICAL

13
D 11
16 B
15
17

FLANGE A
9
17 9
E
7
7

7
B
10
7

9 8
16 10 9
8 10 7 10
9
7 7
E E 11
8 8
10 10
C C
8
8 9 10
13 12
A5M029

8
14
N_MM_710020_4_XFM0_01_00

Figure 71(IAE)-00-20-991-94300-13-A / SHEET 1/1 - Forward Junction Box

** ON A/C ALL

Print Date: February 18, 2018 Page 54 of 108

BLOCK SEAL

A FIRE SHIELD
15 FIRE SEAL
ASSEMBLY

THRUST REVERSER
BRACKET

16 FIRE SEAL
ASSEMBLY

BLOCK SEAL

B8373
N_MM_710020_4_XAA0_01_00

Figure 71(IAE)-00-20-991-19700-13-A / SHEET 1/1 - Inspection for the Thrust

Reverser Brackets and Inspection for/Installation of the Engine Fire Seals
** ON A/C ALL

Print Date: February 18, 2018 Page 55 of 108

A
POST-SB-ENG-72-0230

15 FIRE SEAL ASSEMBLY

FIRE SHIELD

17 SCREWS (4 PLACES)

16 FIRE SEAL ASSEMBLY

GC00A5M073
N_MM_710020_4_XAB0_01_00

Figure 71(IAE)-00-20-991-19800-13-A / SHEET 1/1 - Fire Seal Installation

** ON A/C ALL

Print Date: February 18, 2018 Page 56 of 108

3. Job Set-up
Subtask 71-00-20-860-052-B
A. Aircraft Maintenance Configuration
(1) Make sure that the two engines have the same ground idle capability (reduced ground idle or non-
reduced ground idle).
(a) To find the engine ground idle capability, do a check of:
· The engine identification plate and tables 1 and 2.
(Ref. Fig. Engine Identification Plate SHEET 1)
(Ref. Fig. Table 1 - New Data Entry Plug PN 2A4378 Variants SHEET 1)
(Ref. Fig. Table 2 - New Data Entry Plug PN 2A4378 Variants SHEET 1)
· The data entry plug back shell inscription
(Ref. Fig. Data Entry Plug Back Shell Inscription SHEET 1)
· The data entry plug pin-out configuration (given in SB V2500-ENG-72-0285).
(2) Make sure the aircraft is stable (Ref. AMM TASK 05-57-00-200-001) .

NOTE: If the aircraft is on jacks, make sure it is leveled before you install the engine.

(3) On the center pedestal, on the ENG panel 115VU, make sure that a WARNING NOTICE(S) is in
position to tell persons not to start the engine.
(4) On the overhead maintenance panel 50VU, make sure that the ON legend of the ENG/FADEC GND
PWR/1(2) pushbutton switch is off. Make sure that a WARNING NOTICE(S) is in position to tell
persons not to energize the FADEC 1(2).
(5) On the panel 30VU, make sure that the APU BLEED pushbutton switch is released (ON legend
off). Make sure that a WARNING NOTICE(S) is in position to tell persons not to press the APU
BLEED pushbutton switch. Make sure that a WARNING NOTICE(S) is in position on the HP ground
connector to tell persons not to pressurize the pneumatic system.
(6) Make sure that the ACCESS PLATFORM 1M(3 FT) is in position.
Subtask 71-00-20-010-053-A
B. Make sure that the fan cowl doors are open (Ref. AMM TASK 71-13-00-010-010) :
(1) FOR 1000EM1 (ENGINE-1)
437AL, 438AR
(2) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
Subtask 71-00-20-040-051-A
C. Make sure that the thrust reverser Hydraulic Control Unit (HCU) is deactivated (Ref. AMM TASK 78-30-
00-040-012) .
Subtask 71-00-20-865-051-A

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:

Print Date: February 18, 2018 Page 57 of 108

- THE PROBES WILL BECOME TOO HOT.

- THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PER-
SONNEL.

D. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL DESIGNATION FIN LOCATION

49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
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 EX- 2WE1 Q44
TIG/BTL1/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE1 Q43
TIG/BTL1/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE2 Q42
TIG/BTL2/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE2 Q41
TIG/BTL2/SQUIB/A
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/2/TAT 1DA2 Y15
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
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 (ENGINE-1)
49VU FUEL/LP VALVE/MOT1/ENG1 1QG A08
49VU ENGINE/1/FIRE DET/LOOP A 7WD1 A06
49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04
49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03
121VU RCDR/DFDR 7TU K16
121VU FUEL/LP VALVE/MOT2/ENG1 3QG M25
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 (ENGINE-2)
49VU FUEL/LP VALVE/MOT1/ENG2 2QG A09

Print Date: February 18, 2018 Page 58 of 108

PANEL DESIGNATION FIN LOCATION

49VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07
49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05
121VU FUEL/LP VALVE/MOT2/ENG2 4QG M26
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
Subtask 71-00-20-865-070-A

E. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL DESIGNATION FIN LOCATION

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
Subtask 71-00-20-210-050-A
F. Check of the Cowling for Correct Condition
(1) Do a check of the electrical connectors of the aft and forward junction boxes, for correct condition.
(2) Make sure that these parts are not damaged:
(a) The forward engine mount (Ref. AMM TASK 71-21-12-200-010)
(b) The aft engine mount (Ref. AMM TASK 71-22-11-200-010)
(c) The pylon structure that you can see.
Subtask 71-00-20-110-052-A
G. Clean Components
(1) Clean these parts by (Ref. AMM TASK 70-11-50-100-802) .
(a) The mating faces and the shear pins and the fastener holes on the forward and aft engine
mounts
(b) The forward and aft mount pads on the pylon.
(2) Clean the bolts (1), (18) and (2), the nuts (16) and (5) and the barrel nuts (6) by (Ref. AMM TASK 70-
11-50-100-802) .
(Ref. Fig. Forward Engine Mount SHEET 1)
(Ref. Fig. Aft Engine Mount SHEET 1)

Print Date: February 18, 2018 Page 59 of 108

(3) Make sure that there are no traces of seizure or wear.

Subtask 71-00-20-230-051-A
H. Do an ultra-high sensitivity fluorescent penetrant inspection of the engine mount bolts (1), (2) and (18)
SPM 702305. No cracks are permitted.
(Ref. Fig. Forward Engine Mount SHEET 1)
(Ref. Fig. Aft Engine Mount SHEET 1)
Subtask 71-00-20-240-051-A
J. Visual Inspections
(1) Do a visual inspection of the forward engine mount nuts (5) and (16) with a MAGNIFYING GLASS
POWER 10X. Do not remove the silver plating.
(Ref. Fig. Forward Engine Mount SHEET 1)
If an engine nut is cracked, reject it.
(2) Do a visual inspection of the barrel nuts (6) with a MAGNIFYING GLASS POWER 10X . No cracks,
nicks, scratches or gouges are allowed. If any damage is found, replace the barrel nut. Silver plating
missing from the external surface of the barrel nut is acceptable.
The threads must be in good condition and no silver plating is allowed to be missing from the threads.
If silver plating is missing from the barrel nut threads, the barrel nut must be replaced.
Subtask 71-00-20-210-060-A
K. Do a Check of the Running Torque of the Forward and Aft Mount Bolts
(1) Do a check of the running torque of the forward engine mount bolts as follows:
(Ref. Fig. Forward Engine Mount SHEET 1)
(a) Apply a thin layer of anti seize compound (Material No. V10-085) to the threads of the engine
mount bolts, the nuts and the washers.
(b) Install the washers under the head of the bolts (1) and (18).
(c) Install the bolts (1) and (18) through holes in the pylon and the forward mount.
(d) Install the nuts (5) and (16) on the bolts (1) and (18).
(e) Tighten the nuts by hand until they are hard to turn.

NOTE: Make sure that the nuts are correctly threaded on the bolts.

(f) Use a torque wrench to tighten the nuts until at least two full threads show on the other side of
the nuts (Ref. AMM TASK 70-23-11-911-013) .
1 Measure the torque required to tighten the bolt (Ref. AMM TASK 70-23-11-911-013) . The
minimum torque should be 70 lbf.in (0.79 m.daN). The maximum torque should be 600 lbf.in
(6.78 m.daN).
2 If the bolt torque is less than 70 lbf.in (0.79 m.daN), replace the nut (5) or (16) and do steps
(a) thru (f) 1_ again.
3 If the torque is more than 600 lbf.in (6.78 m.daN), remove the bolt and the nut and look for
damaged threads. If the threads are damaged, replace the bolt and nut and do steps (a) thru
(f) 2_ again.
(g) Remove the forward mount bolts and nuts.
(2) Do a check of the running torque of the aft engine mount bolts as follows:
(Ref. Fig. Aft Engine Mount SHEET 1)
(a) Apply a thin layer of anti seize compound (Material No. V10-085) to the threads of the engine
mount bolts, the nuts and the washers.

Print Date: February 18, 2018 Page 60 of 108

(b) Install the washers (3) under the head of the bolts (2).
(c) Install the aft engine mount bolts (2) into the barrel nuts (6).
(d) Tighten the bolts by hand until they are hard to turn.

NOTE: Make sure that the nuts are correctly threaded on the bolts.

(e) Use a torque wrench to tighten the nuts until at least two full threads show on the other side of
the nuts (Ref. AMM TASK 70-23-11-911-013) .
1 Measure the torque required to tighten the bolt (Ref. AMM TASK 70-23-11-911-013) . The
minimum torque should be 90 lbf.in (1.02 m.daN). The maximum torque should be 800 lbf.in
(9.04 m.daN).
2 If the bolt torque is less than 90 lbf.in (1.02 m.daN), replace the nut (6) and do steps (a) thru
(e) 1_ again.
3 If the torque is more than 800 lbf.in (9.04 m.daN), remove the bolt and the nut and look for
damaged threads. If the threads are damaged, replace the bolt and nut and do steps (a) thru
(e) 2_ again.
(f) Remove the aft mount bolts and nuts.
Subtask 71-00-20-420-050-A
L. If replacement engine does not have all its equipment, remove the accessories from the removed engine
and install them on the replacement engine.
4. Procedure
Subtask 71-00-20-420-051-A
A. Put the replacement engine in position under the pylon
(1) Put the ENGINE TROLLEY (S487ETT2) or TRAILER,ENGINE GROUND HANDLING (TMHET06-
00-00) and ENGINE CRADLE (S1787CR) or CRADLE,V2500 ENGINE (TMHEC29-00-00) with the
replacement engine in position under the pylon.
(2) Install the forward hinge arm (4) and (5) with the ball pins (1) on the forward BOOTSTRAP
SYSTEM (98D71203501000) .
(Ref. Fig. Bootstrap Installation)
(3) Install the dynamometers and chain pulley blocks on the bootstrap system.
(4) Attach the chain hooks to the engine cradle.
(5) Remove the pins that attach the engine cradle to the engine trolley.
(6) Put the locking levers of the handling hoist in UP position. Lift the engine cradle to disengage it from
the trolley.
(7) Slightly raise the forward section of the engine cradle then the aft section.

NOTE: Make sure that the differential load read on the dynamometers is less than:
- 600 daN (1350 lbf) (611.6 Kg) between the 2 front chains.
- 200 daN (450 lbf) (203.9 Kg) between the 2 rear chains.

NOTE: Use the level indicators on the forward hinge arms of the bootstrap to keep the hinge arms as
near as possible to the horizontal position.

Subtask 71-00-20-210-052-A
B. Make certain that the hinge crossover beam (1) is correctly engaged in the V-groove (2).
(Ref. Fig. Hinge Crossover Beam SHEET 1)

Print Date: February 18, 2018 Page 61 of 108

Subtask 71-00-20-420-052-A
C. Put the Power Plant in position

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

CAUTION: DO NOT INSERT THE SHEAR PINS OF ONE MOUNT BEFORE THE OTHER OR DAM-
AGE TO THE MOUNTS AND PYLON CAN RESULT.

(1) Keep the pylon and engine face of the forward and aft attach fittings parallel so as to put the locating
pins easily in their location.

NOTE: Rear lifts give the roll attitude.

NOTE: At the forward end you can move the engine laterally by plus or minus 20 mm (0.79 in.).

(a) To move the engine to the left side, lift with the right hand hoist and/or lower with the left hand
hoist.
(b) To move the engine to the right side, lift with the left hand hoist and/or lower with the right hand
hoist.
(2) Lift the engine:

CAUTION: DO NOT INSTALL THE LOCATING PINS OF ONE MOUNT BEFORE THE OTHER OR
DAMAGE TO MOUNTS AND PYLON COULD RESULT.

CAUTION: MAKE SURE THAT THE PYLON FORWARD FAIRING IS CORRECTLY SEATED
ON THE TRAILING EDGE LAND OF THE AIR INTAKE COWL. IF THE PYLON FOR-
WARD FAIRING IS NOT IN THE CORRECT POSITION, DAMAGE CAN OCCUR.

(a) Slowly lift the engine to the pylon. Make sure that the shear pins on the engine mounts engage
with the holes in the pylon.
(3) Lift the engine chain continuously until a mating load of 200 daN (450 lbf) (203.9 Kg) maximum for
each chain is shown on the dynamometers.
Subtask 71-00-20-420-053-A
D. Installation of the Forward and Aft Engine Mounts
(1) Install the forward engine mount.
(Ref. Fig. Forward Engine Mount SHEET 1)
(a) Lubricate the bolts (1) and (18), the washers (2) and (17), the nuts (5) and (16) and the shear
pins (19) with anti seize compound (Material No. V10-085).

NOTE: The forward center bolt has no upper retainer, it is locked by lockwire.

(b) Install the bolts (18), the washers (17), the retainers (12) and the nuts (16).
(c) Put the nut (5) and the retainer (6) in position.
(d) Install the washer (7) and the nut (8).
(e) TORQUE the nut (8) to between 35 and 40 lbf.in (0.40 and 0.45 m.daN).
(f) Install the bolt (1) and the washer (2) on the middle front engine mount.
(g) Tighten the bolts (1) and (18) with a standard wrench.

Print Date: February 18, 2018 Page 62 of 108

NOTE: You must install the washers (17) and (2) with the recessed side against bolt head.

(h) Torque the forward engine mount bolts.

CAUTION: THIS IS NOT THE FINAL TORQUE FOR THE FORWARD ENGINE MOUNT
BOLTS.

1 Hold the nut (16) stable with a wrench and TORQUE the bolts (1) and (18)
to between 88.49 and 132.74 lbf.ft (12.00 and 18.00 m.daN).
(i) Remove the padding from between the engine and the engine mount.
(2) Install the aft engine mount attach fittings.
(Ref. Fig. Aft Engine Mount SHEET 1)
(a) Lubricate the bolts (2), the washers (3) and the shear pins (5) with anti seize
compound (Material No. V10-085).
(b) Installation of the barrel nut:

CAUTION: BARREL NUT MUST BE INSTALLED WITH ROUNDED SIDE UP.

1 Install the barrel nut (6), the bolts (2) and washers (3).

NOTE: You must install the washers (3) with the recessed side against bolt head.

(c) TORQUE (final value) the bolts (2) to between 65 and 70.5 m.daN (479.35 and 519.91 lbf.ft)
(Ref. AMM TASK 70-23-11-911-013) .
1 Check the torque on the aft engine mount bolts (2) again to make sure the final torque is
correct.

NOTE: After you tighten the engine mount bolts to the final torque, make sure that the sur-
faces between the pylon and the aft engine mount are in contact.

(d) Install safety cable (Material No. V02-275) (Ref. AMM TASK 70-40-11-911-016) on bolts (2).
Alternate: Use lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-
014) , safety cable (Material No. V02-272), safety cable (Material No. V02-273),
safety cable (Material No. V02-274), safety cable (Material No. V02-276), safety
cable (Material No. V02-277), safety cable (Material No. V02-278),
safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safety
cable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .

NOTE: If the pylon flexible seals were removed, install them.

Subtask 71-00-20-080-050-A
E. Removal of the Lifting Equipment and Bootstrap Assembly
(1) Remove the lifting equipment.
(a) Put the pulley locking levers in the DOWN position.
(b) Reduce the load on the engine cradle using the pulley blocks.
(c) Disconnect the engine cradle from the engine.
(d) Lower the engine cradle. Make sure that the engine cradle does not hit the engine.
(e) Install the engine cradle on the engine trolley.

Print Date: February 18, 2018 Page 63 of 108

(f) Remove the four chain hooks from the engine cradle.
(g) Remove the engine trolley rearwards.
(2) Remove the bootstrap assembly as follows:
(Ref. Fig. Bootstrap Installation)
(a) Remove the four chain pulley blocks and the dynamometers from the rear beam (9) and the
forward hinge arms (4) and (5).
(b) Remove the pins (8) and remove the rear beam (9).
(c) Remove the pins (1) and remove the link (2).
(d) Remove the pins (3) and remove the left and right hinge arms (4) and (5).
(e) Release the left and right clamps (7) and remove the spacer and the center hinge clamp from the
pylon.
Subtask 71-00-20-760-050-A
F. Do a check of the electrical bonding
(1) Measure the resistance value (ohmic) (Ref. AMM TASK 20-28-00-720-005) . Make sure that the
resistance between the engine and the pylon is not more than 1.5 milliohm.
Subtask 71-00-20-420-054-A
G. Final Torque of the Bolts of the Forward Mount

CAUTION: MAKE SURE THAT THE TORQUE WRENCH DOES NOT TOUCH THE FORWARD EN-
GINE MOUNT DURING TIGHTENING TO NOT CHANGE THE TORQUE APPLIED TO
THE BOLTS.

(1) Use the special tool CHEST,TORQUE SET-ENGINE R I (98D71203001000) to TORQUE

the forward mount bolts to the final torque value to between 43.39 and 47.45 m.daN
(319.99 and 349.93 lbf.ft) (Ref. AMM TASK 70-23-11-911-013) .

NOTE: The given torque values take into account the length of the torque wrench.

(a) Use the Torque Wrench to torque the four forward mount bolts (18).
1 Check the torque on the forward engine mount bolts (18) again to make sure the final torque
is correct.
(b) Use the Torque Wrench and Load Reducer to torque the center bolt (1) of the forward mount.
1 Check the torque on the forward engine mount bolts (1) again to make sure the final torque
is correct.

NOTE: The use of the load reducer (P/N GA184A) with the torque wrench (P/N TQFRM14)
changes the value of the torque selected. You must set a value between 13 m.daN
(95.87 lbf.ft) and 14 m.daN (103.24 lbf.ft) on the wrench to get the torque required for
the forward center mount bolt.

NOTE: After you tighten the engine mount bolts to the final torque, make sure that the sur-
faces between the pylon and the forward engine mount are in contact.

(2) Install safety cable (Material No. V02-275) (Ref. AMM TASK 70-40-11-911-016) on bolt (1).
Alternate: Use lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) , safety
cable (Material No. V02-272), safety cable (Material No. V02-273), safety cable (Material No. V02-
274), safety cable (Material No. V02-276), safety cable (Material No. V02-277), safety
cable (Material No. V02-278),

Print Date: February 18, 2018 Page 64 of 108

safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safety
cable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .

NOTE: You can use lockwire diameters ranging from 0.8mm to 1.2mm to safety the bolt (1).

(3) Install the retainers (11) and (13) secured with the bolt (9), the washers (10) and (14) and the nut
(15).
(4) TORQUE the bolts (9) to between 24 and 36 lbf.in (0.27 and 0.41 m.daN) (Ref. AMM TASK 70-23-
11-911-013) .
(5) Remove the fan cowl and thrust reverser braces
(Ref. Fig. Fan Cowl and Thrust Reverser Braces)
(a) Put the fan cowl hold-open rods into position to hold the weight of the fan cowls
(Ref. AMM TASK 71-13-00-010-010) .
(b) Put the thrust reverser half hold-open rods into position to hold the weight of the thrust reverser
halves (Ref. AMM TASK 78-32-00-010-010) .
(c) Remove the support arms (5) and (6) from the fan cowls and the thrust reverser halves.
(d) Remove the adjustable struts (1) and (2).
5. Close-up
Subtask 71-00-20-020-081-A
A. Remove ballast installed for aircraft stability.
(1) If all engines are in place, remove all ballast installed for aircraft stability.
Subtask 71-00-20-630-050-A
B. Remove caps from the open ends.

** ON A/C ALL
PRE SB 36-1055 for A/C 001-002
Subtask 71-00-20-420-096-A
C. Installation of the Bleed Pressure Regulator Valve (PRV) Sense Line.
(1) Install the sense line between the bleed pressure regulator valve (PRV) and the pylon interface
(Ref. AMM TASK 36-11-49-400-016) .

** ON A/C ALL
Subtask 71-00-20-420-055-A
D. Installation of Components on the Left and the Right Sides of the Engine
(1) Install these components on the left side of the engine.
(a) Connect the sensor tubes.
(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)
1 Connect the pressure regulating valve sensor tube (20).
2 TORQUE the tube union nut to between 2.0 and 2.3 m.daN (14.75 and 16.96 lbf.ft).
3 Connect the thermostat sensor tube (11).
4 TORQUE the union nut to between 1.5 and 1.7 m.daN (11.06 and 12.54 lbf.ft)
(Ref. AMM TASK 70-23-11-911-013) .
(b) Connect the fuel tubes to the fluid disconnect panel.
(Ref. Fig. Power Plant, Left Side SHEET 1)

Print Date: February 18, 2018 Page 65 of 108

1 Install a new IPC -CSN (73-11-48-80-120) gasket (11) on the fuel supply tube (8)
(Ref. AMM TASK 70-23-13-911-010) .
2 Put the fuel supply tube in position on the fluid disconnect panel and install the four bolts (9)
and the washers (10).
3 TORQUE the bolts to between 90 and 110 lbf.in (1.02 and 1.24 m.daN)
(Ref. AMM TASK 70-23-11-911-013) .
4 Safety the bolts (9) with lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-
014) .
Alternate: Use safety cable (Material No. V02-272), safety cable (Material No. V02-
273), safety cable (Material No. V02-274), safety cable (Material No. V02-275),
safety cable (Material No. V02-276) safety cable (Material No. V02-277), safety
cable (Material No. V02-278),
safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safety
cable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .
5 Install a new IPC -CSN (73-11-48-80-080) gasket (3) on the fuel return to tank tube (4).
6 Put the fuel return to tank tube in position on the fuel disconnect panel and install the four
bolts (6) and the washers (5).
7 TORQUE the bolts (6) to between 0.38 and 0.42 m.daN (33.63 and 37.17 lbf.in)
(Ref. AMM TASK 70-23-11-911-013) .
8 Safety the bolts (6) with lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-
014) .
Alternate: Use safety cable (Material No. V02-272), safety cable (Material No. V02-
273), safety cable (Material No. V02-274), safety cable (Material No. V02-275),
safety cable (Material No. V02-276) safety cable (Material No. V02-277), safety
cable (Material No. V02-278),
safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safety
cable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .
9 Clean any fuel that may have leaked onto the fan case (Ref. AMM TASK 70-11-56-910-
001) .
(c) Connect the hydraulic tubes to the fluid disconnect panel.

CAUTION: DO NOT LET HYDRAULIC FLUID GO DOWN THE FAN CASE AND CONTACT
THE SEAL RING BETWEEN THE FAN CASE AND THE ANGLE GEARBOX. RE-
MOVE THE HYDRAULIC FLUID WITH A CLEAN LINT FREE CLOTH. THE HY-
DRAULIC FLUID CAN CAUSE DETERIORATION OF THE SEAL RING.

Print Date: February 18, 2018 Page 66 of 108

5 Connect the hydraulic suction tube connector (1) to the fluid disconnect panel. Handtighten
the connector.
6 Clean any hydraulic fluid that may have leaked onto the fan case (Ref. AMM TASK 70-11-
56-910-001) .
(d) Connect the cabin air duct.
(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)
1 Position the duct and install the coupling (7).
2 TORQUE the coupling to between 0.85 and 0.96 m.daN (75.22 and 84.96 lbf.in).
3 Install the coupling. To do this, tap the coupling with a mallet.
4 TORQUE the coupling again to between 0.79 and 0.9 m.daN (69.91 and 79.65 lbf.in).
5 Tap the coupling again.
6 TORQUE the coupling again to between 0.79 and 0.9 m.daN (69.91 and 79.65 lbf.in).
(e) Connect the Thermal Anti-Ice (TAI) duct.
(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)
1 Position the TAI duct and install the couplings (19). Do not tighten the coupling at this time.
(f) On the fan case near the V-groove at 11 o'clock, connect the electrical connector 4004VC.
(Ref. Fig. Left Connectors Location SHEET 1)
(g) Connect the thrust reverser harness connectors 4101KS-A and 4101KS-B on the thrust reverser
Hydraulic Control Unit (HCU).
(Ref. Fig. Left Connectors Location SHEET 1)
(2) Install these components from the right side of the engine.
(Ref. Fig. Power Plant, Right Side SHEET 1)
(a) Connect the starter duct.
(Ref. Fig. Forward Junction Box SHEET 1)
(Ref. Fig. Upper/Lower Link Starter Duct and Link Assembly SHEET 1)
(Ref. Fig. Forward Junction Box SHEET 1)
1 Position the starter duct (4) on the pylon starter duct (6) and install the coupling (5). Do not
tight the coupling at this time.

NOTE: If necessary, adjust the lengths of the link assemblies to align both ducts.

2 Rig the starter duct (Ref. AMM TASK 80-13-49-820-010) .

(b) Connect the TAI duct (2).
(Ref. Fig. Forward Junction Box SHEET 1)

CAUTION: MAKE SURE THE COUPLINGS DO NOT TOUCH ADJACENT COMPONENTS

OR FAN COWL DOORS (WHEN CLOSED). DAMAGE TO COMPONENTS CAN
OCCUR.

Print Date: February 18, 2018 Page 67 of 108

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

(d) On the forward pylon junction box, connect the electrical connectors 402VC, 404VC, 405VC,
406VC, 408VC, 447VC, 448VC and 457VC (Ref. AMM TASK 70-23-15-912-010) .
(Ref. Fig. Forward Junction Box SHEET 1)
(e) On the pylon junction box, connect the electrical connectors 401VC, 403VC, 407VC and 409VC
(Ref. AMM TASK 70-23-15-912-010) .
(Ref. Fig. Forward Junction Box SHEET 1)
(f) On the pylon junction box, connect the generator harness connector 400VC.

CAUTION: CONTACTS HAVE TO BE REPLACED IN CASE OF ANY WEAR AND TEAR

SIGNS (HOLES, SCRATCH, DISCOLORATION, TEARS, PITTED MARKS).

1 Do not clean the contacts with abrasive material.

2 Connect a DYNAMOMETER 15 DAN (33 LBF) - PULL to the test pin to do a pin retention
check of the sockets.
a The minimum extraction force value must be 1.2 daN (2.7 lbf) for a CANNON contact
Ref. ESPM 20-48-23.
b The minimum extraction force value must be 2.8 daN (6.3 lbf) for a FRAMATOME
(former SOURIAU) contact Ref. ESPM 20-48-24.
3 Tighten the connector with a WRENCH - STRAP until the orange colour is shown in
the window of the coupling nut and safety the generator harness connector 400VC with
lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) .
Alternate: Use safety cable (Material No. V02-272), safety cable (Material No. V02-
273), safety cable (Material No. V02-274), safety cable (Material No. V02-
275), safety cable (Material No. V02-276), safety cable (Material No. V02-277),
safety cable (Material No. V02-278), safety cable (Material No. V02-279), safety
cable (Material No. V02-280) or
safety cable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .
(Ref. Fig. Forward Junction Box SHEET 1)
(g) On the aft interface junction box, connect the electrical connectors 450VC, 452VC and 454VC.
(Ref. Fig. Left Interface Junction Box SHEET 1)
(h) On the forward section of the combustion case at 11 o'clock, connect the hydraulic reservoir
pressurization tube to the union (engine 1 only).

NOTE: The elbowed union of the hose must be connected to the engine.

(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)
TORQUE the union to between 1.5 and 1.7 m.daN (11.06 and 12.54 lbf.ft)
(Ref. AMM TASK 70-23-11-911-013) .
(i) Install the drains mast (Ref. AMM TASK 71-71-42-400-010) .
Subtask 71-00-20-410-062-B
E. If the engine fire seals are not present, install them as follows:
(Ref. Fig. Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire
Seals SHEET 1)
(Ref. Fig. Fire Seal Installation SHEET 1)
(1) Close the relevant thrust reverser half (Ref. AMM TASK 78-32-00-410-010) :
(2) FOR 1000EM1 (ENGINE-1)
451AL, 452AR

Print Date: February 18, 2018 Page 68 of 108

(3) FOR 1000EM2 (ENGINE-2)

461AL, 462AR
(4) Put the fire IPC -CSN (71-51-46-80-030) seal assembly (15) or IPC -CSN (71-51-46-80-020) seal
assembly (16) on the heatshield so there is full contact between the seal and the thrust reverser
bracket assembly. The fire seal should rest against the bracket with no compression.
(5) Mark the forward and bottom outline of the fire seal on the heatshield with a PENCIL.
(6) Open the relevant thrust reverser half (Ref. AMM TASK 78-32-00-010-010) :
(7) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(8) FOR 1000EM2 (ENGINE-2)
461AL, 462AR
(9) Measure 0.125 in. (3.18 mm) aft of the fire seal forward outline and make a parallel line on the
heatshield with a PENCIL.
(10) Align the fire seal with the aft outline and bottom outline on the heatshield.
(11) Put a PLATE - STEEL, 500X500X3 MM (19.68X19.68X0.12 IN) between the strut fairing and the
heatshield before you drill the holes to protect the strut fairing.
(12) Drill through the three fire seal pilot holes into the heatshield. Enlarge the holes with a DRILL - NO 21
(DIA 0.159 IN - 4.039 MM).
(13) Remove the burrs from the holes in the fire seal and the heatshield.
(14) Cleaning
(a) Clean the fire seal and the aft and inboard surfaces of the heatshield and block seal with a
Textile-Lint free Cotton - (Material No. 14SBA1) made moist with solvent (Material No. V01-457).
Wipe the surfaces dry before the cleaning solvent evaporates.
(15) Applying of primer
(a) Apply primer (Material No. V08-032) to the mating surfaces of the fire seal assembly. Allow to air
dry for twenty minutes.
(16) Apply release agent (Material No. V02-158A) to the aft surface and inboard corner of the block seal.
(17) Applying of sealant
(a) Apply sealant (Material No. V08-030) to the mating surfaces of the fire seal.
(18) Put the fire seal into position on the heatshield.
(19) Installation of the fire seals as follows:
(a) Install the fire IPC -CSN (71-51-46-80-030) seal assembly (15) and IPC -CSN (71-51-46-80-
020) seal assembly (16) on the fire shield with IPC -CSN (71-51-46-80-010) screws (17).
(b) TORQUE the screws (17) to between 6 and 8 lbf.in (0.07 and 0.09 m.daN).
(20) Using of sealant
(a) Fill all the voids in the fire seal with sealant (Material No. V08-030). Allow the sealant to cure for
24 hours at 77 deg. F (25 deg.C) and 50 percent humidity.
Subtask 71-00-20-820-050-A
F. Do the Adjustment
(1) Adjust the thrust reverser latches, bumpers and compression struts (Ref. AMM TASK 78-30-00-820-
010) .
(2) Adjust the fan cowls (Ref. AMM TASK 71-13-00-800-010) .

Print Date: February 18, 2018 Page 69 of 108

NOTE: Make sure that the gearbox breather outlet duct (GBOD) aligns with the gearbox breather out-
let vent on the right fan cowl. If it does not align, loosen the GBOD fasteners, align the GBOD
with the vent and torque the fasteners (Ref. AMM TASK 72-61-49-400-010) .

Subtask 71-00-20-410-051-A
G. Close access
(1) Check the HP bleed and pressure regulating valves configuration.

NOTE: Make sure that HP bleed and pressure regulating valves are not mechanically locked and can
operate freely.

(2) Close the thrust reverser cowls (Ref. AMM TASK 78-32-00-410-010) :
(3) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(4) FOR 1000EM2 (ENGINE-2)
461AL, 462AR
Subtask 71-00-20-440-050-A
H. Activate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-440-012) .
(Ref. Fig. Hydraulic Control Unit SHEET 1)
Subtask 71-00-20-611-050-A
J. Do a Check of the Engine Oil System and Prime It
(1) Prime the engine oil system (Ref. AMM TASK 12-13-79-610-012) .
(2) Fill the Integrated Drive Generator (IDG) oil system (Ref. AMM TASK 12-13-24-612-011) .
Subtask 71-00-20-612-050-B
K. Service the Starter with Oil (Ref. AMM TASK 12-13-80-600-010) .

NOTE: The starter may have been drained when the engine was removed.

Subtask 71-00-20-410-053-A
L. Close Access
(1) Close the fan cowl (Ref. AMM TASK 71-13-00-410-010) :
(2) FOR 1000EM1 (ENGINE-1)
437AL, 438AR
(3) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
(4) Remove the access platform(s).
(5) Remove the warning notice(s).
Subtask 71-00-20-865-072-A

WARNING: CLOSE THE PHC AND WHC CIRCUIT BREAKERS BEFORE YOU CLOSE THE PROBE
HEATER AND WINDOW HEATER 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.

Print Date: February 18, 2018 Page 70 of 108

M. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION

122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15
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
123VU ANTI ICE/L/WHSLD 1DG1 AF10
123VU ANTI ICE/R/WHSLD 1DG2 AF03
122VU ANTI ICE/WINDOWS/L 4DG1 X14
122VU ANTI ICE/WINDOWS/R 4DG2 W14
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE1 Q43
TIG/BTL1/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE1 Q44
TIG/BTL1/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE2 Q41
TIG/BTL2/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE2 Q42
TIG/BTL2/SQUIB/B
121VU RCDR/DFDR 7TU K16
49VU COM/CVR/SPLY 2RK E14
49VU COM/CVR/CTL 4RK E13
FOR FIN 1000EM1 (ENGINE-1)
49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04
121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41
121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41
121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39
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

Print Date: February 18, 2018 Page 71 of 108

PANEL DESIGNATION FIN LOCATION

49VU FUEL/LP VALVE/MOT1/ENG1 1QG A08
121VU FUEL/LP VALVE/MOT2/ENG1 3QG M25
FOR FIN 1000EM2 (ENGINE-2)
49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05
121VU ENGINE/ENG2/FADEC B/AND EIU 2 4KS2 Q40
121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42
121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40
49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03
121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39
49VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07
122VU ELEC/GCU/2 2XU2 T27
122VU ANTI ICE/ENG/2 1DN2 W10
123VU Y HYD/ELEC/ELEC PUMP/NORM 3801GX AB03
123VU Y HYD/ELEC/PUMP 3802GX AB06
121VU HYDRAULIC/HYD POWER/Y 3803GX N30
49VU FUEL/LP VALVE/MOT1/ENG2 2QG A09
121VU FUEL/LP VALVE/MOT2/ENG2 4QG M26
FOR FIN 1000EM1 (ENGINE-1)
49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03
Subtask 71-00-20-861-050-A
P. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .
Subtask 71-00-20-740-057-A
Q. Update the engine hours and cycles (Ref. AMM TASK 31-36-00-740-005) or (Ref. AMM TASK 31-36-
00-740-014) .

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 71-00-20-860-050-A
R. Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001) .
Subtask 71-00-20-720-050-B
S. On the MCDU do the following Test:
(1) Push the line key adjacent to the ENG indication. The SYSTEM REPORT/TEST ENG menu comes
into view.
(2) Push the line key adjacent to the FADEC 1(2) A(B) indication. The ENGINE 1(2) MAIN MENU page
comes into view.
(3) Push the line key adjacent to the TROUBLE SHOOTING indication. The FADEC 1(2) A(B) TROUBLE
SHOOTING MENU page comes into view.
(4) Push the line key adjacent to the EEC CONFIGURATION indication. The FADEC 1(2) EEC
CONFIGURATION page comes into view.
(5) Read the data that come on the MCDU (EEC P/N, ENGINE RATING, BUMP LEVEL, EPR MODIFIER
and ENGINE SERIAL NUMBER) to make sure they are the same as written on the EEC, data entry
plug and engine identification plate using the following engine ratings comparison table.

MCDU (EEC CONFIG Menu) ENGINE DATA PLATE (Engine Model)

22000 lbs V2522
24000 lbs V2524

Print Date: February 18, 2018 Page 72 of 108

MCDU (EEC CONFIG Menu) ENGINE DATA PLATE (Engine Model)

24000E lbs V2524E
27000 lbs V2527
27000E lbs V2527E
27000M lbs V2527M
30000 lbs V2530
30000 lbs V2530
33000 lbs V2533

(6) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page
comes into view.
(7) Stop the MCDU.
Subtask 71-00-20-710-051-A
T. Do an operational test of the EEC (Ref. AMM TASK 73-22-34-710-040) .

NOTE: If the aircraft operates in correct CAT III conditions, do a land test (Ref. AMM TASK 22-97-00-
710-001) .

Subtask 71-00-20-710-061-B
U. Do the operational test of the Starter valve and FMU (Ref. AMM TASK 80-13-51-710-040) .
Subtask 71-00-20-710-050-A
V. Do these Tests
(1) Do a functional test of the IDG disconnect system (Ref. AMM TASK 24-21-00-710-042) .
(2) Do an operational test of the anti-ice protection system of the engine air intake (Ref. AMM TASK 30-
21-00-710-002) .
(3) Do the Hydraulic Maintenance Procedure after an engine installation:
(a) FOR 1000EM1 (ENGINE-1)
· Do the maintenance procedure for Green Hydraulic System (Ref. AMM TASK 29-11-51-860-
040) .
(b) FOR 1000EM2 (ENGINE-2)
· Do the maintenance procedure for Yellow Hydraulic System (Ref. AMM TASK 29-13-51-860-
001) .
Subtask 71-00-20-790-050-B
W. Do these Leak Checks
(1) Do a wet motor leak check (Ref. AMM TASK 71-00-00-710-046) .
(2) Do a leak check of the fuel return valve (Ref. AMM TASK 73-13-42-720-010) to make sure that there
are no leaks at pylon connection.
(3) Do leak test of the inlet-cowl anti-ice supply-ducts with the engine in operation (Ref. AMM TASK 30-
21-49-790-010) .
(4) Do a minimum idle leak check and do a check for leaks (Ref. AMM TASK 71-00-00-710-012) .
(5) Do an Electronic Engine Control (EEC) system idle test (Ref. AMM TASK 71-00-00-710-022) .
Subtask 71-00-20-210-053-B
X. Make sure that the IDG is connected:
(1) If the IDG is not connected, make sure that the maintenance message "IDG1(2) (E1(2)-4000XU)
RECONFIG" is shown on the EPGS GROUND REPORT page.

Print Date: February 18, 2018 Page 73 of 108

(a) Make sure that the related GCU is energized.

(b) Reset the GCU:
1 On the ELEC control panel 35VU, release (OFF) then push the related ELEC/GEN
pushbutton switch 3XU.
(c) On the ELEC page of the lower ECAM DU, make sure that the line connection between the
IDG1(2) and the related busbar is shown green. Make sure that the frequency and voltage
indications are correct.
(2) If the IDG1(2) is not connected after the GCU reset, do a check for other maintenance messages
related to the IDG.
Subtask 71-00-20-720-055-A
Y. Do this Test
(1) Do a pretested replacement engine test (Ref. AMM TASK 71-00-00-700-011) .
(2) Do not stop the engine at this step.
Subtask 71-00-20-710-052-A
AA. While the Engine is Running Do this Test
(1) On the lower ECAM DU, get the BLEED page.
(2) On the panel 30VU:
Push the ENG 1 (2) BLEED pushbutton switch
· on the ENG 1 (2) pushbutton switch, the OFF legend goes off.
· on the lower ECAM DU, the PRV and HP valves are shown open.
· Monitor the nacelle temperature for unsatisfactory indication. If the temperature increases
incorrectly, do the inspection of the bleed air duct connections.
(3) On the panel 30VU:
Release the ENG 1(2) BLEED pushbutton switch
· on the ENG 1(2) pushbutton switch the OFF legend comes on.
· on the lower ECAM DU, the PRV and HP valves are shown closed.
Subtask 71-00-20-860-051-A
AB. Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .
Subtask 71-00-20-862-050-A
AC. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .
Subtask 71-00-20-869-058-A
AD. Installation of the two engines.
(1) If the two engines were installed simultaneously refer to (Ref. AMM D/O 05-59-00-00) for specific
recommendations.

TASK 71-00-20-400-040-A01
Installation of the Power Plant with the Engine Positioner TWW 75E (MIAG)

WARNING: MAKE SURE THAT THE LANDING GEAR GROUND SAFETIES AND THE WHEEL CHOCKS
ARE IN POSITION. MOVEMENT OF THE AIRCRAFT CAN BE DANGEROUS.

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.

Print Date: February 18, 2018 Page 74 of 108

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

CAUTION: MAKE SURE THAT THE EEC STANDARDS INSTALLED ARE CORRECT. SOME EEC STAND-
ARDS CANNOT BE INTERMIXED ON A SAME AIRCRAFT.

FIN : 1000EM1 , 1000EM2

1. Reason for the Job
Self explanatory
2 Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE QTY DESIGNATION

Print Date: February 18, 2018 Page 75 of 108

REFERENCE QTY DESIGNATION

No specific Torque wrench: range to between 0.51 and 0.62 m.daN
(45.13 and 54.87 lbf.in)
No specific Torque wrench: range to between 0.6 and 0.8 m.daN
(53.10 and 70.80 lbf.in)
No specific Torque wrench: range to between 0.79 and 0.9 m.daN
(69.91 and 79.65 lbf.in)
No specific Torque wrench: range to between 0.85 and 0.96 m.daN
(75.22 and 84.96 lbf.in)
No specific Torque wrench: range to between 1 and 1.2 m.daN
(88.50 and 106.19 lbf.in)
No specific Torque wrench: range to between 1.5 and 1.7 m.daN
(11.06 and 12.54 lbf.ft)
No specific Torque wrench: range to between 2.0 and 2.3 m.daN
(14.75 and 16.96 lbf.ft)
No specific Torque wrench: range to between 9.7 and 10.7 m.daN
(71.53 and 78.91 lbf.ft)
No specific Torque wrench: range to between 43.38 and 47.45 m.daN
(319.91 and 349.93 lbf.ft)
No specific Torque wrench: range to between 65 and 70.5 m.daN
(479.35 and 519.91 lbf.ft)
(98D71203001000) 1 CHEST,TORQUE SET-ENGINE R I
(TWW75E) 1 ENGINE POSITIONER

B. Consumable Materials

REFERENCE DESIGNATION
(Material No. V01-457) solvent
(Material No. V02-126) lockwire
(Material No. V02-147) lockwire
(Material No. V02-158A) release agent
(Material No. V02-272) safety cable
(Material No. V02-273) safety cable
(Material No. V02-274) safety cable
(Material No. V02-275) safety cable
(Material No. V02-276) safety cable
(Material No. V02-277) safety cable
(Material No. V02-278) safety cable
(Material No. V02-279) safety cable
(Material No. V02-280) safety cable
(Material No. V02-281) safety cable
(Material No. V08-030) sealant
(Material No. V08-032) primer
(Material No. V10-085) anti seize compound
(Material No. 14SBA1) Textile-Lint free Cotton -

C. Work Zones and Access Panels

ZONE/ACCESS ZONE DESCRIPTION

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

Print Date: February 18, 2018 Page 76 of 108

ZONE/ACCESS ZONE DESCRIPTION

451AL, 452AR
FOR 1000EM2 (ENGINE-2)
447AL, 448AR,
461AL, 462AR

D. Expendable Parts

FIG.ITEM DESIGNATION IPC-CSN

3 gasket 73-11-48-80-080
11 gasket 73-11-48-80-120

E. Referenced Information

REFERENCE DESIGNATION
(Ref. 05-57-00-200-001-A). Aircraft Stability
(Ref. 12-13-24-612-011-A). IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a
Level Check
(Ref. 12-13-79-610-012-A). Prime the Engine Oil System
(Ref. 12-13-80-600-010-B). Replenishment of Starter Oil System
(Ref. 20-28-00-720-005-A). Check of the Electrical Bonding of the Different Components (But not
Fluid Systems and Components Installed on Composite materials)
(Ref. 22-97-00-710-001-A). Operational Test of the LAND CAT III Capability
(Ref. 24-21-00-710-042-A). Operational Test of the IDG Disconnect and Reconnect (Reset) Func-
tion - Engine Static
(Ref. 24-41-00-861-002-A). Energize the Aircraft Electrical Circuits from the External Power
(Ref. 24-41-00-861-002-A-01). Energize the Aircraft Electrical Circuits from the APU
(Ref. 24-41-00-861-002-A-02). Energize the Aircraft Electrical Circuits from Engine 1(2)
(Ref. 24-41-00-862-002-A). De-energize the Aircraft Electrical Circuits Supplied from the External
Power
(Ref. 24-41-00-862-002-A-01). De-energize the Aircraft Electrical Circuits Supplied from the APU
(Ref. 24-41-00-862-002-A-02). De-energize the Aircraft Electrical Circuits Supplied from the Engine
1(2)
(Ref. 29-10-00-863-001-A). Pressurize the Green Hydraulic System with a Hydraulic Ground
Power-Cart
(Ref. 29-10-00-863-002-A). Pressurize the Yellow Hydraulic System with a Hydraulic Ground
Power-Cart
(Ref. 29-14-00-614-002-A). Pressurization of the Hydraulic Reservoirs through the Ground Con-
nector
(Ref. 29-14-00-614-002-A-01). Pressurization of the Hydraulic Reservoirs with the Auxiliary Power
Unit (APU)
(Ref. 30-21-00-710-002-A). Operational Check of the Engine-Air-Intake Ice-Protection System
(with the Engines in operation)
(Ref. 30-21-49-790-010-A). Leak Test of the Inlet Cowl Anti-Ice Supply Ducts with the Engine in
Operation
(Ref. 30-21-49-820-001-A). Rig the Anti-ice Ducts
(Ref. 31-36-00-740-014-A). Update of the Engine Hours and Cycles in the Flight Data Interface
and Management Unit (FDIMU)
(Ref. 31-60-00-860-001-A). EIS Start Procedure
(Ref. 31-60-00-860-002-A). EIS Stop Procedure

Print Date: February 18, 2018 Page 77 of 108

REFERENCE DESIGNATION

** ON A/C ALL
PRE SB 36-1055 for A/C 001-002
(Ref. 36-11-49-400-016-A). Installation of the Sense Line between the Bleed Pressure-Regulator
Valve (PRV) and the Pylon Interface

** ON A/C ALL
(Ref. 70-11-50-100-802-A). Local Swab or Wipe Cleaning with Solvent
(Ref. 70-11-56-910-001-A). Cleaning Requirements after Chemical Contact with Fire Extinguisher
Agents, Hydraulic Fluid, Oil or Fuel
(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. 70-23-15-912-010-A). Connection of Electrical Connectors
(Ref. 70-40-11-911-014-A). Locking Devices General Information
(Ref. 70-40-11-911-016-A). General Instructions for Uses of Safety Cable
(Ref. 71-00-00-700-011-B). Test No.13 : Pretested Replacement Engine Test
(Ref. 71-00-00-710-012-B). Test No.3 : Idle Leak Check
(Ref. 71-00-00-710-022-B). Test No.6 : ELectronic Engine Control (EEC) System Idle Test
(Ref. 71-00-00-710-045-A). Test No.1 : Dry Motor Leak Check
(Ref. 71-00-00-710-046-B). Test No.2 : Wet Motor Leak Check
(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. 71-13-00-800-010-A). Functional Check of Fan Cowl Latch Tension
(Ref. 71-21-12-200-010-A). Detailed Inspection of FWD Engine Mount Installation
(Ref. 71-22-11-200-010-A). Detailed Inspection of AFT Engine Mount Installation
(Ref. 71-71-42-400-010-A). Installation of the Drains Mast
(Ref. 72-61-49-400-010-B). Installation of the Gearbox Breather Outlet Duct (GBOD)
(Ref. 73-13-42-720-010-A). Functional Test of the Fuel Recirculation Cooling System without Bar-
field Tester and without AIDS
(Ref. 73-13-42-720-010-A-01). Functional Test of the Fuel Recirculation Cooling System with Barfield
Tester and without AIDS
(Ref. 73-13-42-720-010-A-02). Functional Test of the Fuel Recirculation Cooling System without Bar-
field Tester and with AIDS
(Ref. 73-13-42-720-010-A-03). Functional Test of the Fuel Recirculation Cooling System with Barfield
Tester and with AIDS
(Ref. 73-22-34-710-040-A). Operational Test of the EEC
(Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for
Ground Maintenance
(Ref. 78-30-00-440-012-A). Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after
Ground Maintenance
(Ref. 78-30-00-820-010-A). Rig of the Thrust Reverser System
(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 Halves
(Ref. 80-13-49-820-010-B). Rig the Starter Ducts
(Ref. 80-13-51-710-040-B). Operational Test of the Pneumatic Starter Valve and FMU with the CF-
DS
Ref. ESPM 20-48-23
Ref. ESPM 20-48-24
SPM 702305
(Ref. 05-59-00-00). SPECIAL FLIGHTS - DESCRIPTION AND OPERATION

Print Date: February 18, 2018 Page 78 of 108

REFERENCE DESIGNATION
Engine Identification Plate SHEET 1
Table 1 - New Data Entry Plug PN 2A4378 Variants SHEET 1
Table 2 - New Data Entry Plug PN 2A4378 Variants SHEET 1
Data Entry Plug Back Shell Inscription SHEET 1
Forward Engine Mount SHEET 1
Aft Engine Mount SHEET 1
Fan Cowl and Thrust Reverser Braces
TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1
Power Plant, Left Side SHEET 1
Left Connectors Location SHEET 1
Power Plant, Right Side SHEET 1
Forward Junction Box SHEET 1
Upper/Lower Link Starter Duct and Link Assembly SHEET 1
Forward Junction Box SHEET 1
Left Interface Junction Box SHEET 1
Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire
Seals SHEET 1
Fire Seal Installation SHEET 1
Hydraulic Control Unit SHEET 1
FOR 1000EM1 (ENGINE-1)
(Ref. 29-11-00-710-001-A). Operational Test of the Green Hydraulic System
FOR 1000EM2 (ENGINE-2)
(Ref. 29-13-00-710-002-A). Operational Test of the Yellow Hydraulic System

3. Job Set-up
Subtask 71-00-20-860-059-B
A. Aircraft Maintenance Configuration
(1) Make sure that the two engines have the same ground idle capability (reduced ground idle or non-
reduced ground idle).
(a) To find the engine ground idle capability, do a check of:
· The engine identification plate and tables 1 and 2.
(Ref. Fig. Engine Identification Plate SHEET 1)
(Ref. Fig. Table 1 - New Data Entry Plug PN 2A4378 Variants SHEET 1)
(Ref. Fig. Table 2 - New Data Entry Plug PN 2A4378 Variants SHEET 1)
· The data entry plug back shell inscription
(Ref. Fig. Data Entry Plug Back Shell Inscription SHEET 1)
· The data entry plug pin-out configuration (given in SB V2500-ENG-72-0285).
(2) Make sure the aircraft is stable (Ref. AMM TASK 05-57-00-200-001) .

NOTE: If the aircraft is on jacks, make sure it is leveled before you install the engine.

Print Date: February 18, 2018 Page 79 of 108

BLEED pushbutton switch. Make sure that a WARNING NOTICE(S) is in position on the HP ground
connector to tell persons not to pressurize the pneumatic system.
(6) Make sure that the ACCESS PLATFORM 1M(3 FT) is in position.
Subtask 71-00-20-010-061-A
B. Make sure that the fan cowl doors are open (Ref. AMM TASK 71-13-00-010-010) :
(1) FOR 1000EM1 (ENGINE-1)
437AL, 438AR
(2) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
Subtask 71-00-20-040-055-A
C. Make sure that the thrust reverser Hydraulic Control Unit (HCU) is deactivated (Ref. AMM TASK 78-30-
00-040-012) .
Subtask 71-00-20-865-058-A

D. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL DESIGNATION FIN LOCATION

49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
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 ENGINE/ENG1 AND 2 FIRE EX- 2WE1 Q44
TIG/BTL1/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE1 Q43
TIG/BTL1/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE2 Q42
TIG/BTL2/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE2 Q41
TIG/BTL2/SQUIB/A
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/2/TAT 1DA2 Y15

Print Date: February 18, 2018 Page 80 of 108

PANEL DESIGNATION FIN LOCATION

122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
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 (ENGINE-1)
49VU FUEL/LP VALVE/MOT1/ENG1 1QG A08
49VU ENGINE/1/FIRE DET/LOOP A 7WD1 A06
49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04
121VU RCDR/DFDR 7TU K16
121VU FUEL/LP VALVE/MOT2/ENG1 3QG M25
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 (ENGINE-2)
49VU FUEL/LP VALVE/MOT1/ENG2 2QG A09
49VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07
49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05
121VU FUEL/LP VALVE/MOT2/ENG2 4QG M26
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
Subtask 71-00-20-210-061-A
E. Check of the Cowling for Correct Condition
(1) Do a check of the electrical connectors of the aft and forward junction boxes, for correct condition.
(2) Make sure that these parts are not damaged:
(a) The forward engine mount (Ref. AMM TASK 71-21-12-200-010)
(b) The aft engine mount (Ref. AMM TASK 71-22-11-200-010)
(c) The pylon structure that you can see.
Subtask 71-00-20-110-055-A
F. Clean Components
(1) Clean these parts by (Ref. AMM TASK 70-11-50-100-802) .

Print Date: February 18, 2018 Page 81 of 108

(a) The mating faces and the shear pins and the fastener holes on the forward and aft engine
mounts
(b) The forward and aft mount pads on the pylon.
(2) Clean the bolts (1), (18), (2), the nuts (16) and (5) and the barrel nuts (6) by (Ref. AMM TASK 70-11-
50-100-802) .
(Ref. Fig. Forward Engine Mount SHEET 1)
(Ref. Fig. Aft Engine Mount SHEET 1)
(3) Make sure that there are no traces of seizure or wear.
Subtask 71-00-20-230-052-A
G. Do an ultra-high sensitivity fluorescent penetrant inspection of the engine mount bolts (1), (2) and (18)
SPM 702305. No cracks are permitted.
(Ref. Fig. Forward Engine Mount SHEET 1)
(Ref. Fig. Aft Engine Mount SHEET 1)
Subtask 71-00-20-240-052-A
H. Visual Inspections
(1) Do a visual inspection of the forward engine mount nuts (5) and (16) with a MAGNIFYING GLASS
POWER 10X . Do not remove the silver plating.
(Ref. Fig. Forward Engine Mount SHEET 1)
If an engine nut is cracked reject it.
(2) Do a visual inspection of the barrel nuts (6) with a MAGNIFYING GLASS POWER 10X . No cracks,
nicks, scratches or gouges are allowed. If any damage is found, replace the barrel nut. Silver plating
missing from the external surface of the barrel nut is acceptable.
The threads must be in good condition and no silver plating is allowed to be missing from the threads.
If silver plating is missing from the barrel nut threads, the barrel nut must be replaced.
Subtask 71-00-20-210-062-A
J. Do a Check of the Running Torque of the Forward and Aft Mount Bolts
(1) Do a check of the running torque of the forward engine mount bolts as follows:
(Ref. Fig. Forward Engine Mount SHEET 1)
(a) Apply a thin layer of anti seize compound (Material No. V10-085) to the threads of the engine
mount bolts, the nuts and the washers.
(b) Install the washers under the head of the bolts (1) and (18).
(c) Install the bolts (1) and (18) through holes in the pylon and the forward mount.
(d) Install the nuts (5) and (16) on the bolts (1) and (18).
(e) Tighten the nuts by hand until they are hard to turn.

NOTE: Make sure that the nuts are correctly threaded on the bolts.

Print Date: February 18, 2018 Page 82 of 108

3 If the torque is more than 600 lbf.in (6.78 m.daN), remove the bolt and the nut and look for
damaged threads. If the threads are damaged, replace the bolt and nut and do steps (a) thru
(f) 2_ again.
(g) Remove the forward mount bolts and nuts.
(2) Do a check of the running torque of the aft engine mount bolts as follows:
(Ref. Fig. Aft Engine Mount SHEET 1)
(a) Apply a thin layer of anti seize compound (Material No. V10-085) to the threads of the engine
mount bolts, the nuts and the washers.
(b) Install the washers (3) under the head of the bolts (2).
(c) Install the aft engine mount bolts (2) into the barrel nuts (6).
(d) Tighten the bolts by hand until they are hard to turn.

NOTE: Make sure that the nuts are correctly threaded on the bolts.

(e) Use a torque wrench to tighten the nuts until at least two full threads show on the other side of
the nuts (Ref. AMM TASK 70-23-11-911-013) .
1 Measure the torque required to tighten the bolt (Ref. AMM TASK 70-23-11-911-013) . The
minimum torque should be 90 lbf.in (1.02 m.daN). The maximum torque should be 800 lbf.in
(9.04 m.daN).
2 If the bolt torque is less than 90 lbf.in (1.02 m.daN), replace the nut (6) and do steps (a) thru
(e) 1_ again.
3 If the torque is more than 800 lbf.in (9.04 m.daN), remove the bolt and the nut and look for
damaged threads. If the threads are damaged, replace the bolt and nut and do steps (a) thru
(e) 2_ again.
(f) Remove the aft mount bolts and nuts.
Subtask 71-00-20-420-090-A
K. If replacement engine does not have all its equipment, remove the accessories from the removed engine
and install them on the replacement engine.
4. Procedure
Subtask 71-00-20-420-091-A
A. Installation of the Engine Positioner TWW 75E
(1) Use the right joystick to install the ENGINE POSITIONER (TWW75E) , the engine cradle and the
replacement engine under the pylon.
(2) Make sure, as per the load page, that the correct values are preset for forward and aft preset loads
and preloads.
(3) Use the left joystick to lift the engine positioner and make the necessary movements to mate the
engine mounts. Make sure that clearance is correct between the aft edge of the fan case and the
leading edge of the reversers.
(4) Monitor the engine when you put it in position.

CAUTION: MAKE SURE THAT THE BLADES OF THE THRUST REVERSER R1 HINGE FITTING
ARE IN THE CORRECT POSITION IN THE V-GROOVE OF THE ADAPTOR RING AS-
SEMBLY.

(a) When the distance between the engine mounts and the pylon mounts is 10 mm (0.3937 in.)
approximately, slowly lift the engine. Engage the front and rear locating pins at the same time.

Print Date: February 18, 2018 Page 83 of 108

(b) Continue to lift the engine slowly.

NOTE: Make sure that the engine mounts touch the pylon mounts.

(c) Lift the engine cradle gradually until the forward and aft mating loads are 300 daN. Then install
the mount bolts as follows.
Subtask 71-00-20-420-093-A
B. Installation of the Forward and Aft Engine Mounts
(1) Install the forward engine mount.
(Ref. Fig. Forward Engine Mount SHEET 1)
(a) Lubricate the bolts (1) and (18), the washers (2) and (17), the nuts (5) and (16) and the shear
pins (19) with anti seize compound (Material No. V10-085).

NOTE: The forward center bolt has no upper retainer, it is locked by lockwire.

NOTE: You must install the washers (17) and (2) with the recessed side against bolt head.

(h) Torque the forward engine mount bolts.

CAUTION: THIS IS NOT THE FINAL TORQUE FOR THE FORWARD ENGINE MOUNT
BOLTS.

1 Hold the nut (16) stable with a wrench and torque the bolts (1) and (18)
to between 88.49 and 132.74 lbf.ft (12.00 and 18.00 m.daN).
(i) Remove the padding from between the engine and the engine mount.
(2) Install the aft engine mount attach fittings.
(Ref. Fig. Aft Engine Mount SHEET 1)
(a) Lubricate the bolts (2), the washers (3) and the shear pins (5) with anti seize
compound (Material No. V10-085).
(b) Installation of the barrel nut:

CAUTION: BARREL NUT MUST BE INSTALLED WITH ROUNDED SIDE UP.

1 Install the barrel nut (6), the bolts (2) and washers (3).

NOTE: You must install the washers (3) with the recessed side against bolt head.

Print Date: February 18, 2018 Page 84 of 108

NOTE: After you tighten the engine mount bolts to the final torque, make sure that the sur-
faces between the pylon and the aft engine mount are in contact.

(d) Safety the bolts (2) with lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) .
Alternate: Use safety cable (Material No. V02-272), safety cable (Material No. V02-
273), safety cable (Material No. V02-274), safety cable (Material No. V02-275),
safety cable (Material No. V02-276) safety cable (Material No. V02-277), safety
cable (Material No. V02-278),
safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safety
cable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .

NOTE: If the pylon flexible seals were removed, install them.

Subtask 71-00-20-080-052-A
C. Removal of the Engine Cradle and Engine Positioner TWW 75E

CAUTION: BE CAREFUL WHEN YOU INSTALL THE CRADLE ON, OR REMOVE IT FROM, THE EN-
GINE. IF NOT, YOU CAN CAUSE DAMAGE TO THE VIBRATION SENSOR CONNECT-
OR. THE VIBRATION SENSOR CONNECTOR IS IN FRONT OF THE FORWARD HAND-
LING POINT ON THE RIGHT SIDE.

(1) Disconnect the engine cradle from the engine.

(2) Use the left joystick to lower the engine positioner.
(3) Remove the engine cradle onto the rail system of the engine positioner.
Subtask 71-00-20-760-051-A
D. Do a check of the electrical bonding
(1) Measure the resistance value (ohmic) (Ref. AMM TASK 20-28-00-720-005) . Make sure that the
resistance between the engine and the pylon is not more than 1.5 milliohm.
Subtask 71-00-20-420-094-A
E. Final Torque of the Bolts of the Forward Mount

CAUTION: MAKE SURE THAT THE TORQUE WRENCH DOES NOT TOUCH THE FORWARD EN-
GINE MOUNT DURING TIGHTENING TO NOT CHANGE THE TORQUE APPLIED TO
THE BOLTS.

(1) Use the special tool CHEST,TORQUE SET-ENGINE R I (98D71203001000) to TORQUE

the forward mount bolts to the final torque value to between 43.38 and 47.45 m.daN
(319.91 and 349.93 lbf.ft) (Ref. AMM TASK 70-23-11-911-013) .

NOTE: The given torque values take into account the length of the torque wrench.

Print Date: February 18, 2018 Page 85 of 108

NOTE: After you tighten the engine mount bolts to the final torque, make sure that the sur-
faces between the pylon and the forward engine mount are in contact.

(2) Safety the bolt (1) with lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) .
Alternate: Use safety cable (Material No. V02-272), safety cable (Material No. V02-273), safety
cable (Material No. V02-274), safety cable (Material No. V02-275), safety cable (Material No. V02-
276) safety cable (Material No. V02-277), safety cable (Material No. V02-278),
safety cable (Material No. V02-279), safety cable (Material No. V02-280) or safety
cable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .

NOTE: You can use lockwire diameters ranging from 0.8mm to 1.2mm to safety the bolt (1).

(3) Install the retainers (11) and (13) secured with the bolt (9) the washers (10) and (14) and the nut (15).
(4) TORQUE the bolts (9) to between 24 and 36 lbf.in (0.27 and 0.41 m.daN) (Ref. AMM TASK 70-23-
11-911-013) .
(5) Remove the fan cowl and thrust reverser braces
(Ref. Fig. Fan Cowl and Thrust Reverser Braces)
(a) Put the fan cowl hold-open rods into position to hold the weight of the fan cowls
(Ref. AMM TASK 71-13-00-010-010) .
(b) Put the thrust reverser half hold-open rods into position to hold the weight of the thrust reverser
halves (Ref. AMM TASK 78-32-00-010-010) .
(c) Remove the support arms (5) and (6) from the fan cowls and the thrust reverser halves.
(d) Remove the adjustable struts (1) and (2).
5. Close-up
Subtask 71-00-20-020-082-A
A. Remove ballast installed for aircraft stability.
(1) If all engines are in place, remove all ballast installed for aircraft stability.
Subtask 71-00-20-630-051-A
B. Remove caps from the open ends.

** ON A/C ALL
PRE SB 36-1055 for A/C 001-002
Subtask 71-00-20-420-097-A
C. Installation of the Bleed Pressure Regulator Valve (PRV) Sense Line.
(1) Install the sense line between the bleed pressure regulator valve (PRV) and the pylon interface
(Ref. AMM TASK 36-11-49-400-016) .

** ON A/C ALL
Subtask 71-00-20-420-095-A
D. Installation of Components on the Left and the Right Sides of the Engine
(1) Install these components on the left side of the engine.

Print Date: February 18, 2018 Page 86 of 108

(a) Connect the sensor tubes.

(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)
1 Connect the pressure regulating valve sensor tube (20).
2 TORQUE the tube union nut to between 2.0 and 2.3 m.daN (14.75 and 16.96 lbf.ft).
3 Connect the thermostat sensor tube (11).
4 TORQUE the union nut to between 1.5 and 1.7 m.daN (11.06 and 12.54 lbf.ft)
(Ref. AMM TASK 70-23-11-911-013) .
(b) Connect the fuel tubes to the fluid disconnect panel.
(Ref. Fig. Power Plant, Left Side SHEET 1)

CAUTION: DO NOT LET HYDRAULIC FLUID GO DOWN THE FAN CASE AND CONTACT
THE SEAL RING BETWEEN THE FAN CASE AND THE ANGLE GEARBOX. RE-

Print Date: February 18, 2018 Page 87 of 108

MOVE THE HYDRAULIC FLUID WITH A CLEAN LINT FREE CLOTH. THE HY-
DRAULIC FLUID CAN CAUSE DETERIORATION OF THE SEAL RING.

1 Connect the hydraulic case drain connector (7) to the fluid disconnect panel.
2 TORQUE the connector (7) to between 215 and 245 lbf.in (2.43 and 2.77 m.daN)
(Ref. AMM TASK 70-23-11-911-013) .
3 Connect the hydraulic pressure tube connector (2) to the fluid disconnect panel.
4 TORQUE the connector (2) to between 9.7 and 10.7 m.daN (71.53 and 78.91 lbf.ft)
(Ref. AMM TASK 70-23-11-911-013) .
5 Connect the hydraulic suction tube connector (1) to the fluid disconnect panel. Handtighten
the connector.
6 Clean any hydraulic fluid that may have leaked onto the fan case (Ref. AMM TASK 70-11-
56-910-001) .
(d) Connect the cabin air duct.
(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)
1 Position the duct and install the coupling (7).
2 TORQUE the coupling to between 0.85 and 0.96 m.daN (75.22 and 84.96 lbf.in).
3 Install the coupling. To do this, tap the coupling with a mallet.
4 TORQUE the coupling again to between 0.79 and 0.9 m.daN (69.91 and 79.65 lbf.in).
5 Tap the coupling again.
6 TORQUE the coupling again to between 0.79 and 0.9 m.daN (69.91 and 79.65 lbf.in).
(e) Connect the Thermal Anti-Ice (TAI) duct.
(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)
1 Position the TAI duct and install the couplings (19). Do not tight the coupling at this time
(f) On the fan case near the V-groove at 11 o'clock, connect the electrical connector 4004VC.
(Ref. Fig. Left Connectors Location SHEET 1)
(g) Connect the thrust reverser harness connectors 4101KS-A and 4101KS-B on the thrust reverser
Hydraulic Control Unit (HCU).
(Ref. Fig. Left Connectors Location SHEET 1)
(2) Install these components from the right side of the engine.
(Ref. Fig. Power Plant, Right Side SHEET 1)
(a) Connect the starter duct.
(Ref. Fig. Forward Junction Box SHEET 1)
(Ref. Fig. Upper/Lower Link Starter Duct and Link Assembly SHEET 1)
(Ref. Fig. Forward Junction Box SHEET 1)
1 Position the starter duct (4) on the pylon starter duct (6) and install the coupling (5). Do not
tight the coupling at this time.

NOTE: If necessary, adjust the lengths of the link assemblies to align both ducts.

2 Rig the starter duct (Ref. AMM TASK 80-13-49-820-010) .

(b) Connect the TAI duct (2)
(Ref. Fig. Forward Junction Box SHEET 1)

Print Date: February 18, 2018 Page 88 of 108

CAUTION: MAKE SURE THE COUPLINGS DO NOT TOUCH ADJACENT COMPONENTS

OR FAN COWL DOORS (WHEN CLOSED). DAMAGE TO COMPONENTS CAN
OCCUR.

1 Position the duct on the pylon and install the coupling (3). Do not tight the coupling at this
time
2 Make sure that the coupling is installed correctly. Make sure that the T-bolt (7) on the
coupling (3) is installed at a 20-degree angle from the top of the duct and does not touch the
fan cowl door hinge when closed.
3 Rig the TAI duct (Ref. AMM TASK 30-21-49-820-001) .
4 TORQUE the coupling to between 0.51 and 0.62 m.daN (45.13 and 54.87 lbf.in).
5 Install the coupling. To do this, tap the coupling with a mallet.
6 TORQUE the coupling again to between 0.51 and 0.62 m.daN (45.13 and 54.87 lbf.in).
7 Tap the coupling again.
8 TORQUE the coupling again to between 0.51 and 0.62 m.daN (45.13 and 54.87 lbf.in).
(c) Connect the starter duct.
(Ref. Fig. Forward Junction Box SHEET 1)
(Ref. Fig. Forward Junction Box SHEET 1)

NOTE: Adjust the link assemblies when the engine is installed on the pylon.

1 Remove the four nuts (7), washers (9) and bolts (8) from the two upper link assemblies (16)
and (17). Remove the upper link assemblies.
2 Remove the four nuts (7), washers (9) and bolts (8) from the lower link assemblies (11) and
(12). Remove the lower link assemblies.

NOTE: It may be necessary to loosen the coupling at the valve. If this is required torque the
coupling nut as explained in steps 4_ thru 7_.

3 Position the starter duct (4) on the pylon starter duct (6) and install the coupling (5).
4 TORQUE coupling (5) to between 0.79 and 0.9 m.daN (69.91 and 79.65 lbf.in).
5 Lightly hit around the outside of the coupling with a fiber hammer.
6 TORQUE coupling (5) again to between 0.79 and 0.9 m.daN (69.91 and 79.65 lbf.in).
7 Repeat steps 4_ thru 6_ two more times.
8 Connect the lower link assemblies (11) and (12) to the Fan case brackets with bolts (8),
washers (9) and nuts (7). Do not torque the nuts at this time.
9 Connect the upper link assemblies (16) and (17) to the Fan case brackets with bolts (8),
washers (9) and nuts (7). Do not torque the nuts at this time.
10 Loosen the nut (13) on the support links (11), (12), (16) and (17).
11 Adjust the links as needed to attach to the starter duct (4) without preload.
12 Install the four link assemblies (11), (12), (16) and (17) onto the starter duct (4) with bolts (8),
washers (9) and nuts (7).
13 TORQUE the eight nuts (7) to between 0.6 and 0.8 m.daN (53.10 and 70.80 lbf.in).
14 TORQUE the four nuts (13) on the link assemblies (11), (12), (16) and (17)
to between 1 and 1.2 m.daN (88.50 and 106.19 lbf.in). The link threads must

Print Date: February 18, 2018 Page 89 of 108

block the safety holes in the link assemblies. This can be checked with a piece of
lockwire (Material No. V02-126), put the lockwire into each safety hole. The lockwire must
not go through.
15 Rig the starter duct (Ref. AMM TASK 80-13-49-820-010) .
(d) On the fan case near the V-groove at 1 o'clock, connect the electrical connector 4005VC.
(Ref. Fig. Power Plant, Right Side SHEET 1)
(e) On the forward pylon junction box, connect the electrical connectors 402VC, 404VC, 405VC,
406VC, 408VC, 447VC, 448VC and 457VC (Ref. AMM TASK 70-23-15-912-010) .
(Ref. Fig. Forward Junction Box SHEET 1)
(f) On the pylon junction box, connect the electrical connectors 401VC, 403VC, 407VC and 409VC
(Ref. AMM TASK 70-23-15-912-010) .
(Ref. Fig. Forward Junction Box SHEET 1)
(g) On the pylon junction box, connect the generator harness connector 400VC.

CAUTION: CONTACTS HAVE TO BE REPLACED IN CASE OF ANY WEAR AND TEAR

SIGNS (HOLES, SCRATCH, DISCOLORATION, TEARS, PITTED MARKS).

1 Do not clean the contacts with abrasive material.

2 Connect a DYNAMOMETER 15 DAN (33 LBF) - PULL to the test pin to do a pin retention
check of the sockets.
a The minimum extraction force value must be 1.2 daN (2.7 lbf) for a CANNON contact
Ref. ESPM 20-48-23.
b The minimum extraction force value must be 2.8 daN (6.3 lbf) for a FRAMATOME
(former SOURIAU) contact Ref. ESPM 20-48-24.
3 Tighten the connector with a WRENCH - STRAP until the orange colour is shown in
the window of the coupling nut and safety the generator harness connector 400VC with
lockwire (Material No. V02-147) (Ref. AMM TASK 70-40-11-911-014) .
Alternate: Use safety cable (Material No. V02-272), safety cable (Material No. V02-
273), safety cable (Material No. V02-274), safety cable (Material No. V02-
275), safety cable (Material No. V02-276) safety cable (Material No. V02-277),
safety cable (Material No. V02-278), safety cable (Material No. V02-279), safety
cable (Material No. V02-280) or
safety cable (Material No. V02-281) (Ref. AMM TASK 70-40-11-911-016) .
(Ref. Fig. Forward Junction Box SHEET 1)
(h) On the aft interface junction box, connect the electrical connectors 450VC, 452VC and 454VC.
(Ref. Fig. Left Interface Junction Box SHEET 1)
(i) On the forward section of the combustion case at 11 o'clock, connect the hydraulic reservoir
pressurization tube to the union (engine 1 only).

NOTE: The elbowed union of the hose must be connected to the engine.

(Ref. Fig. TAI Location and Hydraulic Reservoir Pressurization Tube Location SHEET 1)
TORQUE the union to between 1.5 and 1.7 m.daN (11.06 and 12.54 lbf.ft)
(Ref. AMM TASK 70-23-11-911-013) .
(j) Install the drain mast (Ref. AMM TASK 71-71-42-400-010) .
Subtask 71-00-20-410-063-B
E. If the engine fire seals are not present, install them as follows:
(Ref. Fig. Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire
Seals SHEET 1)

Print Date: February 18, 2018 Page 90 of 108

(Ref. Fig. Fire Seal Installation SHEET 1)

(1) Close the relevant thrust reverser half (Ref. AMM TASK 78-32-00-410-010) :
(2) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(3) FOR 1000EM2 (ENGINE-2)
461AL, 462AR
(4) Put the fire seal assembly (15) or (16) on the heatshield so there is full contact between the seal
and the thrust reverser bracket assembly. The fire seal should rest against the bracket with no
compression.
(5) Mark the forward and bottom outline of the fire seal on the heatshield with a PENCIL.
(6) Open the relevant thrust reverser half (Ref. AMM TASK 78-32-00-010-010) :
(7) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(8) FOR 1000EM2 (ENGINE-2)
461AL, 462AR
(9) Measure 0.125 in. (3.18 mm) aft of the fire seal forward outline and make a parallel line on the
heatshield with a PENCIL.
(10) Align the fire seal with the aft outline and bottom outline on the heatshield.
(11) Put a PLATE - STEEL, 500X500X3 MM (19.68X19.68X0.12 IN) between the strut fairing and the
heatshield before you drill the holes to protect the strut fairing.
(12) Drill through the three fire seal pilot holes into the heatshield. Enlarge the holes with a DRILL - NO 21
(DIA 0.159 IN - 4.039 MM).
(13) Remove the burrs from the holes in the fire seal and the heatshield.
(14) Cleaning
(a) Clean the fire seal and the aft and inboard surfaces of the heatshield and block seal with a
Textile-Lint free Cotton - (Material No. 14SBA1) made moist with solvent (Material No. V01-457).
Wipe the surfaces dry before the cleaning solvent evaporates.
(15) Applying of primer
(a) Apply primer (Material No. V08-032) to the mating surfaces of the fire seal assembly. Allow to air
dry for twenty minutes.
(16) Apply release agent (Material No. V02-158A) to the aft surface and inboard corner of the block seal.
(17) Applying of sealant
(a) Apply sealant (Material No. V08-030) to the mating surfaces of the fire seal.
(18) Put the fire seal into position on the heatshield.
(19) Installation of the fire seals as follows:
(a) Install the fire seal assembly (15) and (16) on the fire shield with screws (17).
(b) TORQUE the screws (17) to between 6 and 8 lbf.in (0.07 and 0.09 m.daN).
(20) Using of sealant
(a) Fill all the voids in the fire seal with sealant (Material No. V08-030). Allow the sealant to cure for
24 hours at 77 deg. F (25 deg.C) and 50 percent humidity.
Subtask 71-00-20-820-055-A
F. Do the Adjustment

Print Date: February 18, 2018 Page 91 of 108

(1) Adjust the thrust reverser latches, bumpers, and compression struts (Ref. AMM TASK 78-30-00-820-
010) .
(2) Adjust the fan cowls (Ref. AMM TASK 71-13-00-800-010) .

NOTE: Make sure that the gearbox breather outlet duct (GBOD) aligns with the gearbox breather out-
let vent on the right fan cowl. If it does not align, loosen the GBOD fasteners, align the GBOD
with the vent, and torque the fasteners (Ref. AMM TASK 72-61-49-400-010) .

Subtask 71-00-20-410-064-A
G. Close access
(1) Check the HP bleed and pressure regulating valves configuration.

NOTE: Make sure that HP bleed and pressure regulating valves are not mechanically locked and can
operate freely.

(2) Close the thrust reverser cowls (Ref. AMM TASK 78-32-00-410-010) :
(3) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(4) FOR 1000EM2 (ENGINE-2)
461AL, 462AR
Subtask 71-00-20-440-053-A
H. Activate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-440-012) .
(Ref. Fig. Hydraulic Control Unit SHEET 1)
Subtask 71-00-20-611-054-A
J. Do a Check of the Engine Oil System and Prime It
(1) Prime the engine oil system (Ref. AMM TASK 12-13-79-610-012) .
(2) Fill the Integrated Drive Generator (IDG) oil system (Ref. AMM TASK 12-13-24-612-011) .
Subtask 71-00-20-612-051-A
K. Service the Starter with Oil (Ref. AMM TASK 12-13-80-600-010) or (Ref. AMM TASK 12-13-80-600-
010)

NOTE: The starter may have been drained when the engine was removed.

Subtask 71-00-20-863-054-A
L. Pressurize these Hydraulic Systems

WARNING: PRESSURIZATION OF THE HYDRAULIC SYSTEM CAN RESULT IN INADVERTENT

THRUST REVERSER OPERATION. REMOVE ALL PERSONNEL FROM THE AREA
AROUND THE THRUST REVERSER BEFORE THE HYDRAULIC SYSTEM IS PRESSUR-
IZED. FAILURE TO COMPLY CAN RESULT IN INJURY TO PERSONNEL.

(1) Pressurize the applicable hydraulic system (Ref. AMM TASK 29-10-00-863-001) or
(Ref. AMM TASK 29-10-00-863-002) .
(2) Pressurize the hydraulic reservoirs (Ref. AMM TASK 29-14-00-614-002) .
Subtask 71-00-20-410-065-A
M. Close Access
(1) Close the fan cowl (Ref. AMM TASK 71-13-00-410-010) :

Print Date: February 18, 2018 Page 92 of 108

(2) FOR 1000EM1 (ENGINE-1)

437AL, 438AR
(3) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
(4) Remove the access platform(s).
(5) Remove the warning notice(s).
Subtask 71-00-20-865-073-A

N. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION

Print Date: February 18, 2018 Page 93 of 108

PANEL DESIGNATION FIN LOCATION

121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE2 Q41
TIG/BTL2/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE2 Q42
TIG/BTL2/SQUIB/B
121VU RCDR/DFDR 7TU K16
49VU COM/CVR/SPLY 2RK E14
49VU COM/CVR/CTL 4RK E13
FOR FIN 1000EM1 (ENGINE-1)
49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04
121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41
121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41
121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39
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 (ENGINE-2)
49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05
121VU ENGINE/ENG2/FADEC B/AND EIU 2 4KS2 Q40
121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42
121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40
49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03
121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39
49VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07
122VU ELEC/GCU/2 2XU2 T27
122VU ANTI ICE/ENG/2 1DN2 W10
123VU Y HYD/ELEC/ELEC PUMP/NORM 3801GX AB03
123VU Y HYD/ELEC/PUMP 3802GX AB06
121VU HYDRAULIC/HYD POWER/Y 3803GX N30
49VU FUEL/LP VALVE/MOT1/ENG2 2QG A09
121VU FUEL/LP VALVE/MOT2/ENG2 4QG M26
FOR FIN 1000EM1 (ENGINE-1)
49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03
Subtask 71-00-20-861-053-A
Q. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002) .
Subtask 71-00-20-740-059-A
R. Update the engine hours and cycles (Ref. AMM TASK 31-36-00-740-005) or (Ref. AMM TASK 31-36-
00-740-014) .

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 71-00-20-860-060-A
S. Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001) .
Subtask 71-00-20-720-053-B
T. On the MCDU do the following Test:

Print Date: February 18, 2018 Page 94 of 108

(1) Push the line key adjacent to the ENG indication. The SYSTEM REPORT/TEST ENG menu comes
into view.
(2) Push the line key adjacent to the FADEC 1(2) A(B) indication. The ENGINE 1(2) MAIN MENU page
comes into view.
(3) Push the line key adjacent to the TROUBLE SHOOTING indication. The FADEC 1(2) A(B) TROUBLE
SHOOTING MENU page comes into view.
(4) Push the line key adjacent to the EEC CONFIGURATION indication. The FADEC 1(2) EEC
CONFIGURATION page comes into view.
(5) Read the data that come on the MCDU (EEC P/N, ENGINE RATING, BUMP LEVEL, EPR MODIFIER
and ENGINE SERIAL NUMBER) to make sure they are the same as written on the EEC, data entry
plug and engine identification plate using the following engine ratings comparison table.

MCDU (EEC CONFIG Menu) ENGINE DATA PLATE (Engine Model)

22000 lbs V2522
24000 lbs V2524
24000E lbs V2524E
27000 lbs V2527
27000E lbs V2527E
27000M lbs V2527M
30000 lbs V2530
30000 lbs V2530
33000 lbs V2533

(6) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page
comes into view.
(7) Stop the MCDU.
Subtask 71-00-20-710-064-A
U. Do an operational test of the EEC (Ref. AMM TASK 73-22-34-710-040) .

NOTE: If the aircraft operates in correct CAT III conditions, a land test (Ref. AMM TASK 22-97-00-710-
001) .

Subtask 71-00-20-710-065-B
V. Do the operational test of the Starter valve and FMU (Ref. AMM TASK 80-13-51-710-040) .
Subtask 71-00-20-710-066-A
W. Do these Tests
(1) Do a functional test of the IDG disconnect system (Ref. AMM TASK 24-21-00-710-042) .
(2) Do a dry motor leak check (Ref. AMM TASK 71-00-00-710-045) and do an operational test of the
hydraulic pump:
(3) FOR 1000EM1 (ENGINE-1)
· operational test of the Green hydraulic system (Ref. AMM TASK 29-11-00-710-001) .
(4) FOR 1000EM2 (ENGINE-2)
· operational test of the Yellow hydraulic system (Ref. AMM TASK 29-13-00-710-002) .
Subtask 71-00-20-790-051-B
X. Do these Leak Checks
(1) Do a wet motor leak check (Ref. AMM TASK 71-00-00-710-046) .

Print Date: February 18, 2018 Page 95 of 108

(2) Do a leak check of the fuel return valve (Ref. AMM TASK 73-13-42-720-010) to make sure that there
are no leaks at pylon connection.
(3) Do leak test of the inlet-cowl anti-ice supply-ducts with the engine in operation (Ref. AMM TASK 30-
21-49-790-010) .
(4) Do a minimum idle leak check and do a check for leaks (Ref. AMM TASK 71-00-00-710-012) .
(5) Do an Electronic Engine Control (EEC) system idle test (Ref. AMM TASK 71-00-00-710-022) .
(6) Do an operational test of the anti-ice protection system of the engine air intake (Ref. AMM TASK 30-
21-00-710-002) .
Subtask 71-00-20-210-064-B
Y. Make sure that the IDG is connected:
(1) If the IDG is not connected, make sure that the maintenance message "IDG1(2) (E1(2)-4000XU)
RECONFIG" is shown on the EPGS GROUND REPORT page.
(a) Make sure that the related GCU is energized.
(b) Reset the GCU:
1 On the ELEC control panel 35VU, release (OFF) then push the related ELEC/GEN
pushbutton switch 3XU.
(c) On the ELEC page of the lower ECAM DU, make sure that the line connection between the
IDG1(2) and the related busbar is shown green. Make sure that the frequency and voltage
indications are correct.
(2) If the IDG1(2) is not connected after the GCU reset, do a check for other maintenance messages
related to the IDG.
Subtask 71-00-20-720-054-A
AA. Do this Test
(1) Do a pretested replacement engine test (Ref. AMM TASK 71-00-00-700-011) .
(2) Do not stop the engine at this step.
Subtask 71-00-20-710-067-A
AB. While the Engine is Running Do this Test
(1) On the lower ECAM DU get the BLEED page.
(2) On the panel 30VU:
Push the ENG 1 (2) BLEED pushbutton switch
· on the ENG 1 (2) pushbutton switch, the OFF legend goes off.
· on the lower ECAM DU the PRV and HP valves are shown open.
· Monitor the nacelle temperature for unsatisfactory indication. If the temperature increases
incorrectly, do the inspection of the bleed air duct connections.
(3) On the panel 30VU:
Release the ENG 1(2) BLEED pushbutton switch
· on the ENG 1(2) pushbutton switch the OFF legend comes on.
· on the lower ECAM DU the PRV and HP valves are shown closed.
Subtask 71-00-20-860-061-A
AC. Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002) .
Subtask 71-00-20-862-053-A
AD. De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002) .
Subtask 71-00-20-869-059-A

Print Date: February 18, 2018 Page 96 of 108

AE. Installation of the two engines.

(1) If the two engines were installed simultaneously refer to (Ref. AMM D/O 05-59-00-00) for specific
recommendations.

TASK 71-00-20-400-802-A
Reload the Power Plant

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

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
GEAR. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURY TO PERSONS AND DAM-
AGE TO THE AIRCRAFT AND/OR EQUIPMENT.

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.

1. Reason for the Job

Self explanatory
2 Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE QTY DESIGNATION

No specific AR WARNING NOTICE(S)

B. Work Zones and Access Panels

ZONE/ACCESS ZONE DESCRIPTION

FOR 1000EM1 (ENGINE-1)
437AL, 438AR,
451AL, 452AR
FOR 1000EM2 (ENGINE-2)
447AL, 448AR,
461AL, 462AR

C. Referenced Information

REFERENCE DESIGNATION
(Ref. 05-57-00-200-001-A). Aircraft Stability
(Ref. 30-21-49-400-011-B). Installation of the Anti-ice Duct No. 2

Print Date: February 18, 2018 Page 97 of 108

REFERENCE DESIGNATION
(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. 71-71-42-400-010-A). Installation of the Drains Mast
(Ref. 78-30-00-040-012-A). Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for
Ground Maintenance
(Ref. 78-30-00-440-012-A). Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after
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 Halves
Bootstrap Installation
Fan Cowl and Thrust Reverser Braces

3. Job Set-up
Subtask 71-00-20-941-056-A
A. Safety Precautions
(1) Make sure that the A/C is stable (Ref. AMM TASK 05-57-00-200-001) .
(2) On the center pedestal, on ENG panel 115VU:
(a) Make sure that a WARNING NOTICE(S) is in position to tell persons not to start the engine.
(3) 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) Make sure that a WARNING NOTICE(S) is in position to tell persons not to energize the FADEC
1(2).
(4) On panel 30VU:
(a) Make sure that the APU BLEED pushbutton switch is released (ON legend off).
(b) Make sure that a WARNING NOTICE(S) is in position to tell persons not to press the APU
BLEED pushbutton switch.
(5) Make sure that a WARNING NOTICE(S) is in position on the HP ground connector to tell persons not
to pressurize the pneumatic system.
Subtask 71-00-20-865-067-A

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

Print Date: February 18, 2018 Page 98 of 108

PANEL DESIGNATION FIN LOCATION

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 EX- 2WE1 Q44
TIG/BTL1/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE1 Q43
TIG/BTL1/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE2 Q42
TIG/BTL2/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE2 Q41
TIG/BTL2/SQUIB/A
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 (ENGINE-1)
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 (ENGINE-2)
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

Print Date: February 18, 2018 Page 99 of 108

PANEL DESIGNATION FIN LOCATION

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
Subtask 71-00-20-040-059-A
C. Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU)

(1) Make sure that the thrust reverser Hydraulic Control Unit (HCU) is deactivated (Ref. AMM TASK 78-
30-00-040-012) .
4. Procedure
Subtask 71-00-20-020-078-A
A. Removal of the Lifting Equipment and Bootstrap Assembly
(1) Remove the lifting equipment.
(a) Put the pulley locking levers in the DOWN position.
(b) Reduce the load on the engine cradle using the pulley blocks.
(c) Disconnect the engine cradle from the engine.
(d) Lower the engine cradle. Make sure that the engine cradle does not hit the engine.
(e) Install the engine cradle on the engine trolley.
(f) Remove the four chain hooks from the engine cradle.
(g) Remove the engine trolley rearwards.
(2) Remove the bootstrap assembly as follows:
(Ref. Fig. Bootstrap Installation)
(a) Remove the four chain pulley blocks and the dynamometers from the rear beam (9) and the
forward hinge arms (4) and (5).
(b) Remove the pins (8) and remove the rear beam (9).
(c) Remove the pins (1) and remove the link (2).
(d) Remove the pins (3) and remove the left and right hinge arms (4) and (5).
(e) Release the left and right clamps (7) and remove the spacer and the center hinge clamp from the
pylon.
Subtask 71-00-20-420-107-A
B. Installation of Components on the Left and the Right Sides of the Engines
(1) Install the anti-ice duct No. 2 (Ref. AMM TASK 30-21-49-400-011) .
(2) Install the drains mast (Ref. AMM TASK 71-71-42-400-010) .
(3) Remove the fan cowl and thrust reverser braces
(Ref. Fig. Fan Cowl and Thrust Reverser Braces)

Print Date: February 18, 2018 Page 100 of 108

(a) Put the fan cowl hold-open rods into position to hold the weight of the fan cowls
(Ref. AMM TASK 71-13-00-010-010) .
(b) Put the thrust reverser half hold-open rods into position to hold the weight of the thrust reverser
halves (Ref. AMM TASK 78-32-00-010-010) .
(c) Remove the support arms (5) and (6) from the fan cowls and the thrust reverser halves.
5. Close-up
Subtask 71-00-20-410-069-A
A. Close the thrust reverser cowl doors (Ref. AMM TASK 78-32-00-410-010) :
(1) FOR 1000EM1 (ENGINE-1)
451AL, 452AR
(2) FOR 1000EM2 (ENGINE-2)
461AL, 462AR
Subtask 71-00-20-440-055-A
B. Reactivation of the Thrust Reverser HCU
(1) Do the re-activation of the thrust reverser HCU after maintenance (Ref. AMM TASK 78-30-00-440-
012) .
Subtask 71-00-20-865-063-A
C. Remove the safety clips and tags and close these circuit breakers in this sequence:

PANEL DESIGNATION FIN LOCATION

122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12
122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16
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
123VU ANTI ICE/L/WHSLD 1DG1 AF10
123VU ANTI ICE/R/WHSLD 1DG2 AF03
122VU ANTI ICE/WINDOWS/L 4DG1 X14
122VU ANTI ICE/WINDOWS/R 4DG2 W14
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE1 Q43
TIG/BTL1/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE1 Q44
TIG/BTL1/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE2 Q41
TIG/BTL2/SQUIB/A

Print Date: February 18, 2018 Page 101 of 108

PANEL DESIGNATION FIN LOCATION

121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE2 Q42
TIG/BTL2/SQUIB/B
121VU RCDR/DFDR 7TU K16
49VU COM/CVR/SPLY 2RK E14
49VU COM/CVR/CTL 4RK E13
FOR FIN 1000EM1 (ENGINE-1)
49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04
121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41
121VU ENGINE/IGN/ENG1/SYS B 3JH1 P41
121VU ENGINE/IGN/ENG1/SYS A BAT 2JH1 P39
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
FOR FIN 1000EM2 (ENGINE-2)
49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05
121VU ENGINE/ENG2/FADEC B/AND EIU 2 4KS2 Q40
121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42
121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40
49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03
121VU ENGINE/ENG2/FIRE DET/LOOP A 7WD2 Q39
49VU ENGINE/2/FIRE DET/LOOP B 8WD2 A07
122VU ELEC/GCU/2 2XU2 T27
122VU ANTI ICE/ENG/2 1DN2 W10
123VU Y HYD/ELEC/ELEC PUMP/NORM 3801GX AB03
123VU Y HYD/ELEC/PUMP 3802GX AB06
121VU HYDRAULIC/HYD POWER/Y 3803GX N30
FOR FIN 1000EM1 (ENGINE-1)
49VU ENGINE/1 AND 2/IGN/SYS A 1JH A03
Subtask 71-00-20-410-070-A
D. Close Access
(1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010) :
(2) FOR 1000EM1 (ENGINE-1)
437AL, 438AR
(3) FOR 1000EM2 (ENGINE-2)
447AL, 448AR
(4) Remove the access platform(s).
(5) Remove the warning notice(s).

TASK 71-00-20-000-802-A
Unload the Power Plant

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

Print Date: February 18, 2018 Page 102 of 108

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
GEAR. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURY TO PERSONS AND DAM-
AGE TO THE AIRCRAFT AND/OR EQUIPMENT.

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.

1. Reason for the Job

Self explanatory
2 Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE QTY DESIGNATION

No specific 1 ACCESS PLATFORM 1M(3 FT)
No specific AR WARNING NOTICE(S)
(98D71203501001) 1 BOOTSTRAP SYSTEM
(AM2228-A1) 1
(AM2228-B1) 1
(S1787CR) 1 ENGINE CRADLE
(S487ETT2) 1 ENGINE TROLLEY
(S889BH0) 1 BRACE - HOLD OPEN COWLS
(TMHBS13-00-00) 1 BRACE-HOLD OPEN COWLS
(TMHEC29-00-00) 1 CRADLE,V2500 ENGINE
(TMHET06-00-00) 1 TRAILER,ENGINE GROUND HANDLING

B. Work Zones and Access Panels

ZONE/ACCESS ZONE DESCRIPTION

FOR 1000EM1 (ENGINE-1)
437AL, 438AR,
451AL, 452AR
FOR 1000EM2 (ENGINE-2)
447AL, 448AR,
461AL, 462AR

C. Referenced Information

REFERENCE DESIGNATION
(Ref. 05-57-00-200-001-A). Aircraft Stability

Print Date: February 18, 2018 Page 103 of 108

REFERENCE DESIGNATION
(Ref. 30-21-49-000-011-B). Removal of the Anti-ice Duct No. 2
(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 Halves
Hydraulic Control Unit SHEET 1
Fan Cowl and Thrust Reverser Braces
Bootstrap Installation
Engine Handling Points

3. Job Set-up
Subtask 71-00-20-941-057-A
A. Safety Precautions
(1) Make sure that the A/C is stable (Ref. AMM TASK 05-57-00-200-001) .
(2) On the center pedestal, on ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(3) 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) in position to tell persons not to energize the FADEC 1(2).
(4) On panel 30VU:
(a) Make sure that the APU BLEED pushbutton switch is released (ON legend off).
(b) Put a WARNING NOTICE(S) in position to tell the persons not to press the APU BLEED
pushbutton switch.
(5) Put a WARNING NOTICE(S) in position on the HP ground connector to tell persons not to pressurize
the pneumatic system.
Subtask 71-00-20-865-065-A

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

Print Date: February 18, 2018 Page 104 of 108

PANEL DESIGNATION FIN LOCATION

49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15
122VU ANTI ICE/PROBES/PHC/2 2DA2 Y12
122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16
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 EX- 1WE1 Q43
TIG/BTL1/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE1 Q44
TIG/BTL1/SQUIB/B
121VU ENGINE/ENG1 AND 2 FIRE EX- 1WE2 Q41
TIG/BTL2/SQUIB/A
121VU ENGINE/ENG1 AND 2 FIRE EX- 2WE2 Q42
TIG/BTL2/SQUIB/B
121VU RCDR/DFDR 7TU K16
49VU COM/CVR/SPLY 2RK E14
49VU COM/CVR/CTL 4RK E13
FOR FIN 1000EM1 (ENGINE-1)
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
FOR FIN 1000EM2 (ENGINE-2)
121VU ENGINE/IGN/ENG2/SYS A BAT 2JH2 P40
121VU ENGINE/IGN/ENG2/SYS B 3JH2 P42
121VU ENGINE/ENG2/FADEC B/AND EIU 2 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

Print Date: February 18, 2018 Page 105 of 108

PANEL DESIGNATION FIN LOCATION

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
Subtask 71-00-20-010-065-A
C. 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 the engine.
Subtask 71-00-20-040-058-A
D. Deactivation of the Thrust Reverser

(1) Do the deactivation of the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-
040-012) .
(Ref. Fig. Hydraulic Control Unit SHEET 1)
Subtask 71-00-20-010-066-A
E. 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 71-00-20-480-063-A
F. 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 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.

Print Date: February 18, 2018 Page 106 of 108

(6) Put the fan cowl hold-open rods in their storage positions (Ref. AMM TASK 71-13-00-410-010) .
Subtask 71-00-20-020-079-A
G. 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 the anti-ice duct No. 2 (Ref. AMM TASK 30-21-49-000-011) .
4. Procedure
Subtask 71-00-20-480-062-A
A. Installation of the Support Equipment
(1) Install the BOOTSTRAP SYSTEM (98D71203501001) .
(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 (TMHET06-00-00) or (AM2228-B1) .
(Ref. Fig. Engine Handling Points)
(a) Put in position the engine trolley and ENGINE CRADLE (S1787CR) or CRADLE,V2500
ENGINE (TMHEC29-00-00) (AM2228-A1) 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 in-
cludes the engine assembly, the air inlet cowl, the CNA.

Print Date: February 18, 2018 Page 107 of 108

NOTE: If the mechanics stand on the bootstrap device the weight of the mechanics must be
considered on the dynamometer at both the forward and the aft positions.

Figure 71(IAE)-00-20-991-94900-13-A / SHEET 1/1 - LP/HP Fuel Pump Bleeder Plug

Figure 71(IAE)-00-20-991-94400-13-A / SHEET 1/1 - Anti-Ice Pylon Duct
Figure 71(IAE)-00-20-991-90100-13-A / SHEET 1/1 - Forward Junction Box
Figure 71(IAE)-00-20-991-94300-13-A / SHEET 1/1 - Forward Junction Box
Figure 71(IAE)-00-20-991-94200-13-A / SHEET 1/1 - Upper/Lower Link Starter Duct and Link Assembly
Figure 71(IAE)-00-20-991-90000-13-A / SHEET 1/1 - Hydraulic Control Unit
Figure 71(IAE)-00-20-991-91400-13-A / SHEET 1/3 - Fan Cowl and Thrust Reverser Braces
Figure 71(IAE)-00-20-991-91400-13-A / SHEET 2/3 - Fan Cowl and Thrust Reverser Braces
Figure 71(IAE)-00-20-991-91400-13-A / SHEET 3/3 - Fan Cowl and Thrust Reverser Braces
Figure 71(IAE)-00-20-991-90200-13-A / SHEET 1/1 - Power Plant, Right Side
Figure 71(IAE)-00-20-991-90300-13-A / SHEET 1/1 - Left Interface Junction Box
Figure 71(IAE)-00-20-991-90400-13-A / SHEET 1/1 - Power Plant, Left Side
Figure 71(IAE)-00-20-991-90500-13-A / SHEET 1/1 - Left Connectors Location
Figure 71(IAE)-00-20-991-90600-13-A / SHEET 1/1 - TAI Location and Hydraulic Reservoir Pressurization Tube
Location
Figure 71(IAE)-00-20-991-91000-13-A / SHEET 1/1 - Forward Engine Mount
Figure 71(IAE)-00-20-991-91100-13-A / SHEET 1/2 - Bootstrap Installation
Figure 71(IAE)-00-20-991-91100-13-A / SHEET 2/2 - Bootstrap Installation
Figure 71(IAE)-00-20-991-91200-13-A / SHEET 1/1 - Aft Engine Mount
Figure 71(IAE)-00-20-991-91300-13-A / SHEET 1/1 - Fuel Drain Plug Location
Figure 71(IAE)-00-20-991-19500-13-A / SHEET 1/2 - Engine Handling Points
Figure 71(IAE)-00-20-991-19500-13-A / SHEET 2/2 - Engine Handling Points
Figure 71(IAE)-00-20-991-19600-13-A / SHEET 1/1 - Hinge Crossover Beam
Figure 71(IAE)-00-20-991-19700-13-A / SHEET 1/1 - Inspection for the Thrust Reverser Brackets and Inspection
for/Installation of the Engine Fire Seals
Figure 71(IAE)-00-20-991-19800-13-A / SHEET 1/1 - Fire Seal Installation
Figure 71(IAE)-00-20-991-94500-13-A / SHEET 1/1 - Engine Identification Plate
Figure 71(IAE)-00-20-991-94600-13-A / SHEET 1/1 - Table 1 - New Data Entry Plug PN 2A4378 Variants
Figure 71(IAE)-00-20-991-94700-13-A / SHEET 1/1 - Table 2 - New Data Entry Plug PN 2A4378 Variants
Figure 71(IAE)-00-20-991-94800-13-A / SHEET 1/1 - Data Entry Plug Back Shell Inscription

End of document

Print Date: February 18, 2018 Page 108 of 108

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