W DOC AIRBUS | AMM A320F

Installation of the Power Plant with Jacxson Tool [CFMB]

TASK 71-00-00-400-042-A-03
Installation of the Power Plant with Jacxson Tool

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING: MAKE SURE THAT YOU HAVE THE CORRECT FIRE FIGHTING EQUIPMENT AVAILABLE.
WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.
WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:
  • THE FLIGHT CONTROLS
  • THE FLIGHT CONTROL SURFACES
  • THE LANDING GEAR AND THE RELATED DOORS
  • COMPONENTS THAT MOVE.
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.
CAUTION: DO A CHECK OF THE ENGINE DATA PLATE TO MAKE SURE THAT THE ENGINE IS CORRECT 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 CONFIGURATION IS NOT CORRECT AND MORE WORK WILL BE NECESSARY.
ZONE: 210
ZONE: 400
FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL
1. Reason for the Job
This task gives the information for the installation of the power plant with the jacxson tool.
The power plant can be installed in particular configuration. It is allowed to install the power plant with or without the air intake cowl installed. This maintenance procedure is approved only if you use the transportation stand (engine trolley 537100601 and engine cradle 537100572).
NOTE: The engine thrust rating must be the same as on opposite engine and consistent with the aircraft model.
NOTE: Engine and nacelle are 2 ways interchangeable but with condition.
NOTE: Interferences between the LPTACC inlet airscoop assy and the thrust reverser cowl have been observed in production on a limited number of A320 family aircraft powered with CFM56-5B/3 engines. CFM has issued SB CFM56-5B S/B 75-0044. In order to recover the gap between the LPTACC scoop and the thrust reverser cowl to avoid potential interference, Airbus recommends to incorporate this SB at the opportunity of engine removal/installation.
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
ACCESS PLATFORM 2M (6 FT)
No specific
1
DYNAMOMETER 15 DAN (33 LBF) - PULL
No specific
AR
INSTALLATION TOOL - CABLE TERMINATOR BERGEN BM327 TYPE
No specific
1
MAGNIFYING GLASS POWER 10X
No specific
AR
PAD - PROTECTIVE FOAM
No specific
AR
PLIERS - NOSE, SOFT, LONG
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 20.41 and 17.92 lbf.ft (2.77 and 2.43 m.daN ) T
No specific
Torque wrench: range to between 78.75 and 71.25 lbf.ft (10.68 and 9.66 m.daN ) T
No specific
Torque wrench: range to between 350 and 320 lbf.ft (47.45 and 43.39 m.daN ) T
No specific
Torque wrench: range to between 580 and 480 lbf.ft (78.64 and 65.08 m.daN ) T
No specific
Torque wrench: range to between 25 and 20 lbf.in (0.28 and 0.23 m.daN ) T
No specific
Torque wrench: range to between 36.0 and 24.0 lbf.in (0.41 and 0.27 m.daN ) T
No specific
Torque wrench: range to between 80 and 70 lbf.in (0.90 and 0.79 m.daN ) T
No specific
Torque wrench: range to between 90 and 81 lbf.in (1.02 and 0.92 m.daN ) T
No specific
Torque wrench: range to between 100 and 85 lbf.in (1.13 and 0.96 m.daN ) T
No specific
Torque wrench: range to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft ) T
No specific
Torque wrench: range to between 3.44 and 3.34 m.daN (25.37 and 24.63 lbf.ft ) T
537100572
1
ENGINE CRADLE
537100601
1
ENGINE TROLLEY
98D27803500001
1
LOCKING TOOL ZERO POS
98D71203002002
1
CHEST TORQUE SET NM - CFM56-5 ENGINE
JXU70
1
JACXSON
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.CP1041)
isopropyl alcohol
(Material No.CP5063)
silicone lubricant
(Material No.CP8001)
safetywire 0.032 in. (0.8 mm) dia.
(Material No.CP8002)
safetywire 0.032 in. (0.8 mm) dia.
(Material No.CP8006)
safety cable 0.032 in. (0.8 mm) dia.
(Material No.MS20995C32)
lockwire
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
210
CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD
400
POWER PLANT, NACELLES AND PYLONS
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 451AL, 452AR, 473AL, 473AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL, 462AR, 483AL, 483AR
 D. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
15
GASKET
AIPC 73-11-11-01-070
10
GASKET
AIPC 73-11-48-01-030
 E. Referenced Information
REFERENCE
DESIGNATION
TASK 05-57-00-200-001-A
Aircraft Stability
TASK 05-57-00-200-001-B
Aircraft Stability
TASK 12-13-79-610-002-A
Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector)
TASK 12-13-79-610-002-A-01
Check oil level and replenish (Pressure Filling)
TASK 12-13-80-610-002-B
Replenish Oil System
TASK 20-28-00-720-005-A
Check of the Electrical Bonding of the Different Components (but not the Fluid Systems and Components Installed on Composite materials)
TASK 22-97-00-710-001-A
Operational Test of the LAND CAT III Capability
TASK 24-21-00-210-046-A
Check IDG Oil Level and Differential Pressure Indicator (DPI)
TASK 24-21-00-710-040-A
Operational Test of the IDG Disconnect and Reconnect Function - Engine Static
TASK 24-41-00-861-002-A
Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01
Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02
Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 30-21-00-710-002-A
Operational Check of the Engine-Air-Intake Ice-Protection System (with the Engines in operation)
TASK 31-32-00-860-012-A
Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
TASK 31-36-00-740-014-A
Update of the Engine Hours and Cycles in the Flight Data Interface and Management Unit (FDIMU)
TASK 31-60-00-860-001-A
EIS Start Procedure
TASK 34-10-00-860-004-A
Inertial Reference (IR) Alignment-Procedure
TASK 34-10-00-860-004-A-01
Automatic Inertial Reference (IR) Alignment-Procedure
TASK 34-10-00-860-004-A-02
Inertial Reference (IR) Alignment-Procedure to do a Check of the Links between each Flight Management and Guidance Computer (FMGC) and the three Air Data/Inertial Reference Units (ADIRUs)
TASK 36-11-49-400-026-A
Installation of the Sense Line between the Bleed Pressure-Regulator Valve (PRV) and the Pylon Interface
TASK 71-00-00-710-003-B
Engine Automatic Start
TASK 71-00-00-710-006-B
Minimum Idle Check
TASK 71-00-00-710-008-B
Power Assurance Check
TASK 71-00-00-710-009-B
Vibration Check
TASK 71-00-00-710-025-A
Accel Check
TASK 71-00-00-710-028-B
Engine Shutdown
TASK 71-13-00-010-040-B
Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-B
Closing of the Fan Cowl Doors
TASK 71-13-00-800-041-A
Adjustment of the Fan Cowl Doors
TASK 71-21-11-210-040-B
Detailed Inspection of the Forward Engine Mount
TASK 71-22-11-210-042-B
Detailed Inspection of Aft Engine Mount Installation
TASK 71-73-49-000-025-A
Removal of the Fuel Overboard Drain Tube
TASK 71-73-49-400-025-A
Installation of the Fuel Overboard Drain Tube
TASK 73-11-50-360-002-A
Leak Check and Functional Test of the Fuel Return Valve
TASK 73-21-60-720-040-B
Functional Test of the Electronic Control Unit (ECU)
TASK 73-21-60-740-005-A
Entry of the Core Chevron Nozzle Status Through MCDU
TASK 73-21-60-740-006-A
Read the LRU Identification Report and the Thrust Reverser Shut-off Valve Status
TASK 73-21-60-740-008-A
Entry of the Engine Serial Number Through MCDU
TASK 73-21-90-860-001-A
Programming of the Identification Plug (Push-Pull Design) for SAC engines
TASK 73-21-90-860-001-A-01
Programming of the Identification Plug (Push-Pull Design) for DAC engines
TASK 73-29-00-710-040-B
Operational Test of the FADEC on the Ground (with Engine Motoring)
TASK 73-29-00-710-040-B-02
Operational Test of the FADEC on the Ground (with Engine Non motoring)
TASK 77-32-34-860-041-A
Change the configuration of the Accelerometer
TASK 78-30-00-081-041-B
Make the Thrust Reverser Serviceable after Maintenance
TASK 78-30-00-481-041-B
Make the Thrust Reverser Unserviceable for Maintenance
TASK 78-31-00-710-042-A
Operational Test of the Thrust Reverser System
TASK 78-36-00-010-040-B
Opening of the Thrust Reverser Doors
TASK 78-36-00-410-040-B
Closing of the Thrust Reverser Doors
TASK 78-36-41-820-042-A
Adjustment of the Thrust Reverser Half Door Latches
TASK 78-36-41-820-043-A
Inspection of the Thrust Reverser Half Door Latches
TASK 78-36-42-820-002-A
Adjustment of the LH or R/H Thrust Reverser "J" Ring on Wing
ESPM 2048230
ESPM 2048240
SPM 703213
SPM 703223
TASK 05-59-00-00
SPECIAL FLIGHTS - DESCRIPTION AND OPERATION
F JACXSON TOOL
F Forward Engine Mount
F Aft Engine Mount
F Tool Adaptor
F Aft Engine Mount Safety Wire
F Forward Engine Mount Safety Wire
F Hold Open Cowl Braces - Installation
F Pneumatic System
F Power Plant - Left Side
F Power Plant - Right Side
F Thrust Reverser Electrical Connectors
FOR [1000EM1] (ENGINE-1)
TASK 29-11-00-710-001-A
Operational Test of the Green Hydraulic System
TASK 29-11-51-860-040-A
Hydraulic Maintenance Procedure after an Engine Installation (with Engine Pump Installed) or after an Engine Pump Installation
FOR [1000EM2] (ENGINE-2)
TASK 29-13-00-710-002-A
Operational Test of the Yellow Hydraulic System
TASK 29-13-51-860-001-A
Hydraulic Maintenance Procedure after an Engine Installation (with Engine Pump Installed) or after an Engine Pump Installation
3. Job Set-up
Subtask 71-00-00-865-233-A ** ON A/C NOT FOR ALL
WARNING: OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3) BEFORE ENG1(2)FADEC A and EIU 1(2) C/B'S 2KS1 AND 2KS2. IF YOU DO NOT OBEY THIS SEQUENCE:
  • THE PROBES WILL BECOME TOO HOT.
  • THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUCOM/CVR/SPLY2RKE14
49VUCOM/CVR/CTL4RKE13
** ON A/C NOT FOR ALL
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
49VUANTI ICE/PROBES/AOA/14DA1D04
49VUANTI ICE/PROBES/PITOT/13DA1D02
** ON A/C NOT FOR ALL
49VUANTI ICE/RAIN/RPLNT/CAPT1DB1D01
** ON A/C NOT FOR ALL
49VUCOM/CVR/SPLY23RKE14
49VUCOM/CVR/CTL26RKE13
** ON A/C NOT FOR ALL
121VURCDR/DFDR7TUK16
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B2WE1Q44
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A1WE1Q43
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B2WE2Q42
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A1WE2Q41
122VUANTI ICE/WINDOWS/R4DG2W14
122VUANTI ICE/WINDOWS/L4DG1X14
122VUANTI ICE/PROBES/2/TAT1DA2Y15
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/1/TAT1DA1Z12
** ON A/C NOT FOR ALL
122VUANTI ICE/RAIN/RPLNT/F/O1DB2W11
** ON A/C NOT FOR ALL
FOR FIN: 1000EM1 (ENGINE1)
49VUFUEL/LP VALVE/MOT1/ENG11QGA08
49VUENGINE/1/FIRE DET/LOOP A7WD1A06
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
121VUFUEL/LP VALVE/MOT2/ENG13QGM25
121VUENGINE/IGN/ENG1/SYS B3JH1P41
121VUENGINE/IGN/ENG1/SYS A BAT2JH1P39
121VUENGINE/ENG1/FIRE DET/LOOP B8WD1Q38
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R41
122VUELEC/GCU/12XU1T26
122VUANTI ICE/ENG/11DN1X10
FOR FIN: 1000EM2 (ENGINE2)
49VUFUEL/LP VALVE/MOT1/ENG22QGA09
49VUENGINE/2/FIRE DET/LOOP B8WD2A07
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
121VUFUEL/LP VALVE/MOT2/ENG24QGM26
121VUHYDRAULIC/HYD POWER/Y3803GXN30
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
121VUENGINE/ENG2/FADEC B4KS2Q40
121VUENGINE/ENG2/FIRE DET/LOOP A7WD2Q39
122VUELEC/GCU/22XU2T27
122VUANTI ICE/ENG/21DN2W10
123VUY HYD/ELEC/PUMP3802GXAB06
123VUY HYD/ELEC/ELEC PUMP/NORM3801GXAB03
Subtask 71-00-00-865-234-A ** ON A/C NOT FOR ALL
WARNING: OPEN THE PROBE HEATER AND WINDOW HEATER CIRCUIT-BREAKERS BEFORE YOU OPEN THE PHC AND WHC CIRCUIT BREAKERS. IF YOU DO NOT OBEY THIS SEQUENCE:
  • THE PROBES WILL BECOME TOO HOT.
  • THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/WHC/25DG2W13
122VUANTI ICE/WHC/15DG1X13
122VUANTI ICE/PROBES/PHC/32DA3Y16
122VUANTI ICE/PROBES/PHC/22DA2Y12
Subtask 71-00-00-860-270-A ** ON A/C NOT FOR ALL
C. Aircraft Maintenance Configuration
CAUTION: MAKE SURE THAT THE ECU STANDARDS INSTALLED ARE CORRECT. SOME ECU STANDARDS CANNOT BE INTERMIXED ON A SAME AIRCRAFT.
   (1) Make sure the aircraft is stable (Ref. AMM TASK 05-57-00-200-001).
     (a) If the aircraft is on jacks, make it level before you install the engine.
   (2) 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.
   (3) 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).
   (4) Make sure that the ACCESS PLATFORM 1M(3 FT) is in position.
   (5) Make sure that the slats are retracted and install 98D27803500001 LOCKING TOOL ZERO POS on the flap and slat control lever.
   (6) Make sure there is a WARNING NOTICE(S) on the HP ground connector to tell persons not to pressurize the pneumatic system.
Subtask 71-00-00-010-238-A ** ON A/C NOT FOR ALL
D. Get Access
   (1) Make sure that the fan cowl doors are open (Ref. AMM TASK 71-13-00-010-040):
     (a) FOR [1000EM1] (ENGINE-1)
437AL, 438AR
     (b) FOR [1000EM2] (ENGINE-2)
447AL, 448AR
   (2) Make sure that the thrust reverser doors are open (Ref. AMM TASK 78-36-00-010-040):
     (a) FOR [1000EM1] (ENGINE-1)
451AL, 452AR
     (b) FOR [1000EM2] (ENGINE-2)
461AL, 462AR
Subtask 71-00-00-040-125-A ** ON A/C NOT FOR ALL
E. Make sure that the thrust reverser is unserviceable (Ref. AMM TASK 78-30-00-481-041).
Subtask 71-00-00-080-064-A ** ON A/C NOT FOR ALL
F. Remove the RSE1224 SPLINT-ENGINE MOUNT AFT from the aft engine mount.
Subtask 71-00-00-210-131-A ** ON A/C NOT FOR ALL
G. Check before Installation
CAUTION: DO A DETAILED VISUAL INSPECTION OF THE FORWARD AND AFT ENGINE MOUNTS AND ALL PARTS THAT ATTACH THE MOUNTS. THE PARTS MUST BE IN GOOD CONDITION. IF THE PARTS ARE NOT IN GOOD CONDITION, FAILURE OF THE MOUNTS CAN OCCUR.
   (1) Do a detailed visual inspection of the forward and aft engine mounts (Ref. AMM TASK 71-21-11-210-040) and (Ref. AMM TASK 71-22-11-210-042).
   (2) Do a detailed visual inspection of the forward central part (the snout) of the forward engine mount (Ref. AMM TASK 71-21-11-210-040).
   (3) Do a check of the cowling for correct condition.
   (4) Do a check of the electrical connectors of the aft and forward junction boxes for correct condition.
   (5) Do a check of the visible part of the pylon for correct condition.
CAUTION: YOU MUST REPLACE CONTACTS THAT SHOW WEAR AND TEAR SIGNS (HOLES, SCRATCHES, DISCOLORATION, TEARS AND PITTED MARKS).
CAUTION: YOU MUST REPLACE CONTACTS THAT SHOW WEAR AND TEAR SIGNS (HOLES, SCRATCHES, DISCOLORATION, TEARS AND PITTED MARKS).
   (6) Do a pin retention check of the sockets of the IDG connector ESPM 2048230 (CANNON), ESPM 2048240 (FRAMATONE-former SOURIAU) and FLIGHT CONNECTOR in the 400VCA connector of the generator harness.
  • Use a DYNAMOMETER 15 DAN (33 LBF) - PULL, the CANNON value is 1.2 daN (2.70 lbf) minimum, the FRAMATONE (former SOURIAU) value is 2.8 daN (6.29 lbf) for NEW sockets and 2.2 daN (4.95 lbf) for OLD sockets and the FLIGHT CONNECTOR value is 3.5 daN (7.87 lbf), in accordance with pin/socket type used. Do not clean the contacts with abrasive material.
Subtask 71-00-00-110-074-A ** ON A/C NOT FOR ALL
H. Cleaning
   (1) If you use the same bolts (85) and (135), nuts (120) and (155), retainers (125) and (150), and washers (90) and (140) again, do steps 3.H.(3), 3.J. and 3.K.
   (2) If you use new bolts (85) and (135), nuts (120) and (155), retainers (125) and (150), and washers (90) and (140), or you use CMM examined bolts (85) and (135), nuts (120) and (155), retainers (125) and (150), and washers (90) and (140), you do not need to do steps 3.H., 3.J. and 3.K.
   (3) Clean the bolts (85) and (135), nuts (120) and (155), retainers (125) and (150), and washers (90) and (140) with isopropyl alcohol (Material No.CP1041) .
Subtask 71-00-00-210-132-A ** ON A/C NOT FOR ALL
I. Make sure there are no signs of important seizure or wear on the bolts (85) and (135), and the nuts (120) and (155).
Subtask 71-00-00-230-059-A ** ON A/C NOT FOR ALL
J. Inspection of the bolts (85) and (135), retainers (125) and (150), and washers (90) and (140).
   (1) Do a fluorescent penetrant inspection level 3 of the mount bolts (85) and (135). No cracks are permitted. See CFMI standard Practices Manual SPM 703213 or SPM 703223.
   (2) Visually examine the retainers (125) and (150), and the washers (90) and (140) for indication of damage. If there are scratches, marks and/or other damage, reject the parts.
   (3) Do a visual inspection of the barrel nuts (155) with a MAGNIFYING GLASS POWER 10X. Carefully examine the thread root area of the last two threads. No cracks are permitted. If cracks are found, notify Rohr Inc.
Subtask 71-00-00-110-075-A ** ON A/C NOT FOR ALL
K. Carefully clean the mating faces, the shear or locating pin holes and the fastener holes.
Subtask 71-00-00-869-433-A ** ON A/C NOT FOR ALL
L. If some equipment is not installed on the new engine, remove it from the removed engine. Then install it on the new engine.
Subtask 71-00-00-941-190-A ** ON A/C NOT FOR ALL
M. Put PAD - PROTECTIVE FOAM between:
  • The aft mount and the engine
  • The forward mount and engine
  • And at the upper part of the fan case so that the parts cannot hit during hoisting operations.
   (1) At the half upper part of the fan frame, seal the fan duct panels with adhesive tape.
Subtask 71-00-00-010-239-A ** ON A/C NOT FOR ALL
N. If installed, remove the fuel overboard drain tube at the rear of the drain mast.

PRE SPIB CFM02253MW1

   (1) At the rear of the drain mast, remove the fuel overboard drain tube (Ref. AMM TASK 71-73-49-000-025).

END OF PRE SPIB CFM02253MW1


POST SPIB CFM02253MW1

   (2) Not Applicable

END OF SPIB CFM02253MW1

Subtask 71-00-00-080-066-A ** ON A/C NOT FOR ALL
O. Remove the access platform(s).
4. Procedure
Subtask 71-00-00-640-061-A ** ON A/C NOT FOR ALL
A. Apply a thin layer silicone lubricant (Material No.CP5063) to the threads of the engine mount bolts (85) and (135) , the washers (90) and (140) and the nuts (120) and (155).
Subtask 71-00-00-480-099-A ** ON A/C NOT FOR ALL
WARNING: ONLY USE THE JACXSON TOOL WITH THE CRADLE/TROLLEY ASSEMBLY THAT IS GIVEN IN THE JOB SET-UP INFORMATION PARAGRAPH. THE JACXSON TOOL IS APPROVED ONLY FOR THIS CRADLE/TROLLEY ASSEMBLY. IF YOU USE A DIFFERENT CRADLE/TROLLEY ASSEMBLY, THERE IS A RISK OF INJURY TO PERSONS AND DAMAGE TO THE ENGINE AND TO THE CRADLE/TROLLEY ASSEMBLY.
WARNING: OBEY THE INSTRUCTIONS GIVEN IN THE MANUFACTURER’S MANUAL FOR THE TRANSPORTATION STAND AND THE JACXSON TOOL TO PREPARE AND OPERATE THE TRANSPORTATION STAND AND THE JACXSON TOOL. IF YOU DO NOT OBEY THIS PRECAUTION, INJURY TO PERSONS AND DAMAGE TO THE ENGINE, THE TRANSPORTATION STAND OR THE JACXSON TOOL CAN OCCUR.
B. Prepare the TRANSPORTATION STAND (537100572 ENGINE CRADLE, 537100601 ENGINE TROLLEY and JXU70 JACXSON)
F JACXSON TOOL ** ON A/C NOT FOR ALL
   (1) Obey the transportation stand manufacturer's instructions to prepare and operate the transportation stand.
   (2) Make sure that the cradle has the power plant installed correctly on it.
   (3) Make sure that the cradle is correctly attached to the transportation stand with the cradle pins.
   (4) Make sure that the transportation stand/cradle assembly is in correct configuration to engage under the power plant.
   (5) Install the transportation stand assembly on the Jacxson tool as follows:
     (a) Move the Jacxson tool from the forward side and engage it around the transportation stand.
     (b) Connect the Jacxson lifting adapters to the forklift pockets of the transportation stand.
     (c) Hold the transportation stand with the Jacxson forks.
   (6) Move the transportation stand assembly under the pylon.
   (7) Lift the transportation stand with the Jacxson tool to reach a ground clearance between 50 MM (1.97 IN.) and 100 MM (3.94 IN.).
     (a) Monitor the loads shown on the Jacxson display during all the lifting to make sure that they are not more than the values that follow:
  • At the forward mount: 2509 daN (2558 kg)
  • At the aft mount: 4057 daN (4136 kg)
    or
  • At the left forward or right forward mount: 1255 daN (1279 kg)
  • At the left aft or right aft mount: 2029 daN (2068 kg).
Subtask 71-00-00-200-060-A ** ON A/C NOT FOR ALL
C. Inspection
   (1) As you lift the power plant to the pylon, do a check at the locations that follow:
  • The mating surfaces
  • The front mount engagement
  • The rear mount engagement
  • The engine right-side harness, tube and hose connection clearance
  • The engine left-side harness, tube and hose connection clearance
  • The pylon and thrust reverser seals
  • The Environmental Control System (ECS) elbow and aft engine mount (if X motion)
  • The aft pylon fairing and exhaust
  • The forward pylon fairing and inlet.
Subtask 71-00-00-420-124-A ** ON A/C NOT FOR ALL
D. Lift and align the power plant to touch the pylon mounts:
WARNING: DURING ALL THE NEXT PROCEDURE STEPS, MONITOR THE LOADS SHOWN ON THE DISPLAY OF THE JACXSON TOOL. IF THE LOADS ARE MORE THAN THE SPECIFIED LOAD LIMITS, THE ENGINE CAN FALL. THIS CAN CAUSE DEATH OR INJURY TO PERSONS AND DAMAGE TO THE EQUIPMENT.
   (1) Monitor the load shown on the Jacxson display.
   (2) Make sure that you do not apply loads that are more than the mount limits that follow:
  • At the forward mount: 2509 daN (2558 kg)
  • At the aft mount: 4057 daN (4136 kg)
    or
  • At the left forward or right forward mount: 1255 daN (1279 kg)
  • At the left aft or right aft mount: 2029 daN (2068 kg).
   (3) Lift and align the engine in the 3 axes with the Jacxson tool to reach the pylon mounts.
   (4) Monitor the interface locations that follow:
  • Forward mount engagement
  • Aft mount engagement.
   (5) Make sure that the transportation stand stays horizontal.
   (6) Stop lifting before contact between the engine mounts and the pylon.
   (7) Make sure that the distance between the forward-mount assembly contact surface and the pylon contact surface is the same as the distance between the aft-mount assembly contact surface and the pylon contact surface.
   (8) Make sure that the forward-mount assembly is parallel to the pylon contact surface.
   (9) Lift the transportation stand carefully until the forward and aft-mount assembly are in contact with the pylon contact surface.
WARNING: DURING ALL THE NEXT PROCEDURE STEPS, MONITOR THE LOADS SHOWN ON THE DISPLAY OF THE JACXSON TOOL. IF THE LOADS ARE MORE THAN THE SPECIFIED LOAD LIMITS, THE ENGINE CAN FALL. THIS CAN CAUSE DEATH OR INJURY TO PERSONS AND DAMAGE TO THE EQUIPMENT.
     (a) Monitor the loads shown on the Jacxson display.
     (b) Make sure that you do not apply loads that are more than the mount limits that follow:
  • At the forward mount: 2509 daN (2558 kg)
  • At the aft mount: 4057 daN (4136 kg)
    or
  • At the left forward or right forward mount: 1255 daN (1279 kg)
  • At the left aft or right aft mount: 2029 daN (2068 kg).
     (c) Make sure that the forward mount assembly is fully and correctly engaged in the pylon.
     (d) Make sure that the aft mount assembly is fully and correctly engaged in the pylon.
Subtask 71-00-00-869-434-A ** ON A/C NOT FOR ALL
E. Do a test of the nuts used on the forward and aft engine mounts to make sure the self-locking property works correctly.
   (1) Forward engine mount nuts.
     (a) Put the washers (90) under the head of the bolts (85).
     (b) Install the bolts (85) through holes in the pylon and the forward mount.
     (c) Install the nuts (120) on the bolts (85).
     (d) Tighten the nuts by hand until they are hard to turn.
       1 Make sure that the nuts are correctly threaded on the bolts.
     (e) Use a torque wrench to tighten the nuts (120) until at least two full threads show beyond the nut.
     (f) Measure the torque required to tighten the bolt (85). The minimum torque should not be less than 70 lbf.in (0.79 m.daN). The maximum torque should not be more than 50 lbf.ft (6.78 m.daN).
     (g) If the bolt (85) torque is less than 70 lbf.in (0.79 m.daN), replace the nut (120) and do again steps (a) thru (f).
     (h) If the bolt (85) torque is more than 50 lbf.ft (6.78 m.daN), remove the bolt and nut and look for damaged threads. If the threads are damaged, replace the bolt and nut and do again steps (a) thru (g).
   (2) Aft engine mount nuts.
     (a) Put the bolts (135) in the barrel nuts (155).
     (b) Tighten the bolts by hand until they are hard to turn.
       1 Make sure that the nuts are correctly threaded on the bolts.
     (c) Use a torque wrench to tighten the bolts (135) until at least two full threads show beyond the nut.
     (d) Measure the torque required to tighten the bolts (135). The minimum torque should not be less than 90 lbf.in (1.02 m.daN). The maximum torque should not be more than 66.66 lbf.ft (9.04 m.daN).
     (e) If the bolt (135) torque is less than 90 lbf.in (1.02 m.daN), replace the barrel nut (155) and do again steps (a) thru (d).
     (f) If the bolt torque is more than 66.66 lbf.ft (9.04 m.daN), remove the bolt and nut and look for damaged threads. If the threads are damaged, replace the bolt and nut and do again steps (a) thru (d).
Subtask 71-00-00-420-121-A ** ON A/C NOT FOR ALL
F. Installation of the engine mounts:
F Forward Engine Mount ** ON A/C NOT FOR ALL
F Aft Engine Mount ** ON A/C NOT FOR ALL
   (1) At the aft engine mount:
CAUTION: INSTALL THE BARREL NUT WITH THE ROUNDED SIDE UP. IF NOT, DAMAGE TO THE BARREL NUT CAN OCCUR.
     (a) Put the barrel nuts (155), with the rounded side up, and the retainers (150) in the aft engine mount (145).
     (b) Installation of the washers
CAUTION: THE INNER DIAMETER OF THE WASHER HAS A CHAMFER ON ONE SIDE ONLY. YOU MUST PUT THE CHAMFER AGAINST THE HEAD OF THE BOLT SO THAT IT AGREES WITH THE RADIUS OF THE HEAD OF THE BOLT. INCORRECT INSTALLATION OF THE WASHER CAN DAMAGE THE HEAD OF THE BOLT.
       1 Put the washers (140) on the bolts (135) so the chamfer of the washer (140) agrees with the radius of the head of the bolt (135).
     (c) Put the bolts (135) through the holes in the pylon and the aft engine mount (145).
     (d) Install the bolts (135) in to the barrel nuts (155).
     (e) TORQUE the aft mount bolt using the 98D71203002002 CHEST TORQUE SET NM - CFM56-5 ENGINE.
     (f) TORQUE the bolt (135) to between 580 and 480 lbf.ft (78.64 and 65.08 m.daN ) T. Make sure that the mating surface of the aft engine mount (145) touches the pylon after you torque the bolts.
       1 If using tool adaptor P/N 98D71203002208 with the angle of 22.5 degrees: set the torque wrench to between 451 lbf.ft (61.15 m.daN) and 545 lbf.ft (73.89 m.daN) to get the required TORQUE. Make sure that the mating surface of the aft engine mount (145) touches the pylon after you torque the bolts.
       2 If using tool adaptor P/N 98D71203002208 with the angle of 67.5 degrees: set the torque wrench to between 461 lbf.ft (62.50 m.daN) and 557 lbf.ft (75.52 m.daN) to get the required TORQUE. Make sure that the mating surface of the aft engine mount (145) touches the pylon after you torque the bolts.
F Tool Adaptor ** ON A/C NOT FOR ALL
       3 Check the torque on the aft engine mount bolts (135) again to make sure the final torque is correct.
     (g) Safety of the bolts
F Aft Engine Mount Safety Wire ** ON A/C NOT FOR ALL
CAUTION: YOU CAN USE SAFETY CABLE OR SAFETY WIRE TO SAFETY THE BOLTS. YOU MUST INSTALL THE SAFETY WIRE OR THE CABLE TIGHTLY. IF YOU DO NOT OBEY THIS PRECAUTION, DAMAGE TO THE PYLON CAN OCCUR.
       1 Safety each bolt (135) with CP8006safety cable 0.032 in. (0.8 mm) dia. or CP8002safetywire 0.032 in. (0.8 mm) dia. or safetywire 0.047 in. (1.2 mm) dia., MS20995C47.
         a Use INSTALLATION TOOL - CABLE TERMINATOR BERGEN BM327 TYPE for safety cable AMS5689.
         b Use safety cable terminator tool (BM series) Bergen Cable Technology or DMC Safe-T-Cable Tool & Parts Kit, Daniels Manufacturing Corporation.
         c When you use safety cable at aft mount, install a filler washer from the safety cable supplier to prevent ferrule to go through the aft mount beam hole.
         d Make sure that the safety cable or safety wire points down.
   (2) At the forward engine mount:
CAUTION: THE INNER DIAMETER OF THE WASHER HAS A CHAMFER ON ONE SIDE ONLY. YOU MUST PUT THE CHAMFER AGAINST THE HEAD OF THE BOLT SO THAT IT AGREES WITH THE RADIUS OF THE HEAD OF THE BOLT. INCORRECT INSTALLATION OF THE WASHER CAN DAMAGE THE HEAD OF THE BOLT.
     (a) Put the washers (90) on the bolts (85) so the chamfer of the washer (90) agrees with the radius of the head of the bolt (85).
     (b) Put the bolts (85) through the holes in the pylon and the forward engine mount (95).
     (c) Install the nuts (120) on the bolts (85).
     (d) Turn the nuts (120) until they lightly touch the surface of the forward engine mount (95).
F Forward Engine Mount ** ON A/C NOT FOR ALL
   (3) Put the retainers (125) over the heads of the nuts (120).
   (4) Tighten the nuts (120) until the holes in the retainers (125) align with the holes in the forward engine mount (95).
   (5) Remove the retainers (125) from the nuts (120).
   (6) TORQUE the forward mount bolts using the 98D71203002002 CHEST TORQUE SET NM - CFM56-5 ENGINE.
     (a) Hold the nuts (120) and TORQUE the bolts (85) to between 350 and 320 lbf.ft (47.45 and 43.39 m.daN ) T. Make sure that the mating surface of the forward engine mount (95) touches the pylon after you torque the bolts.
       1 If using tool adaptor P/N 98D71203002206 with the angle of 22.5 degrees: set the torque wrench to between 301 lbf.ft (40.81 m.daN) and 329 lbf.ft (44.61 m.daN) to get the required TORQUE.
       2 If using tool adaptor P/N 98D71203002206 with the angle of 67.5 degrees: set the torque wrench to between 307 lbf.ft (41.62 m.daN) and 336 lbf.ft (45.55 m.daN) to get the required TORQUE.
F Tool Adaptor ** ON A/C NOT FOR ALL
   (7) Put the retainers (125) over the nuts (120) and install the retainers (125) on the forward engine mount (95) with the washers (105 and 115), bolts (100), and nuts (110).
   (8) TORQUE the bolts (100) to between 36.0 and 24.0 lbf.in (0.41 and 0.27 m.daN ) T.
CAUTION: YOU CAN USE SAFETY CABLE OR SAFETY WIRE TO SAFETY THE BOLTS. YOU MUST INSTALL THE SAFETY WIRE OR THE CABLE TIGHTLY. IF YOU DO NOT OBEY THIS PRECAUTION, DAMAGE TO THE PYLON CAN OCCUR.
   (9) Safety of the bolts
F Forward Engine Mount Safety Wire ** ON A/C NOT FOR ALL
     (a) Safety each bolt (85) with CP8006safety cable 0.032 in. (0.8 mm) dia. or CP8002safetywire 0.032 in. (0.8 mm) dia. or safetywire 0.047 in. (1.2 mm) dia., MS20995C47.
       1 Use INSTALLATION TOOL - CABLE TERMINATOR BERGEN BM327 TYPE for safety cable AMS5689.
         a Use safety cable terminator tool (BM series) Bergen Cable Technology or DMC Safe-T-Cable Tool & Parts Kit, Daniels Manufacturing Corporation.
Subtask 71-00-00-080-067-A ** ON A/C NOT FOR ALL
G. Lower and Remove the Jacxson Tool from the front
   (1) Disconnect the cradle from the engine.
   (2) Lower the transportation stand with the Jacxson on the ground and disconnect the lifting adapters from the Jacxson forks.
   (3) Remove the cradle adapters from the engine.
CAUTION: WHEN YOU REMOVE THE JACXSON TOOL AND THE TRANSPORTATION STAND, MAKE SURE THAT:
  • THE JACXSON TOOL IS DISENGAGED FROM THE FORWARD PART OF THE AIRCRAFT
  • THE TRANSPORTATION STAND IS DISENGAGED FROM THE AFT PART OF THE AIRCRAFT.
IF THE JACXSON TOOL IS NOT DISENGAGED CORRECTLY, DAMAGE TO THE NACELLE CAN OCCUR.
   (4) Disengage the Jacxson tool from the transportation stand and clear it from the front side of the aircraft.
   (5) Make sure that there is a sufficient clearance between the power plant and the transportation stand to remove the transportation stand.
   (6) Clear the transportation stand from the aft side of the aircraft.
   (7) Put the ACCESS PLATFORM 2M (6 FT) in position at the engine level.
   (8)
F Hold Open Cowl Braces - Installation ** ON A/C NOT FOR ALL
     (a) Install the fan cowl and thrust reverser cowl hold open rods.
     (b) Remove the hold open cowl braces.
5. Close-up
Subtask 71-00-00-942-091-A ** ON A/C NOT FOR ALL
A. Remove the foam rubber protective pads from the upper part of the fan case and from the engine mounts.
Subtask 71-00-00-420-123-A ** ON A/C NOT FOR ALL
B. Installation of the Pressure Regulator Valve (PRV) Sense Line.
   (1) Install the sense line between the bleed PRV and the pylon interface (Ref. AMM TASK 36-11-49-400-026).
Subtask 71-00-00-410-216-B ** ON A/C NOT FOR ALL
C. Install these components:
CAUTION: USE TWO WRENCHES TO REMOVE OR INSTALL THE TUBE COUPLING NUTS:
  • ONE WRENCH TO HOLD THE UNION, AND
  • ONE TO LOOSEN OR TIGHTEN THE COUPLING NUT.
THIS PREVENTS DAMAGE TO THE PARTS.
   (1) Install these components on the left side of the engine:
     (a) Connect the pylon interface duct to the pylon duct with the coupling (65).
F Pneumatic System ** ON A/C NOT FOR ALL
     (b) TORQUE the coupling as follows:
       1 TORQUE the coupling nut to the value shown on the coupling.
       2 Lightly hit the coupling perimeter in different places with a fiber hammer.
       3 TORQUE the coupling again to the specified value.
       4 Lightly hit the coupling perimeter again.
       5 TORQUE the coupling again to the specified value.
     (c)
F Pneumatic System ** ON A/C NOT FOR ALL
       1 Make sure that the union is installed on the upper high-pressure manifold duct and is attached with lockwire. If not:
         a Install the union and TORQUE to between 3.44 and 3.34 m.daN (25.37 and 24.63 lbf.ft ) T.
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
         b Install the lockwire (Material No.MS20995C32) .
       2 Connect the pressure hose (70) to the union.
       3 TORQUE the hose coupling to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft ) T.
     (d)
F Pneumatic System ** ON A/C NOT FOR ALL
       1 Make sure that you torque the cap on the upper high-pressure manifold.
         a TORQUE the cap to between 3.44 and 3.34 m.daN (25.37 and 24.63 lbf.ft ) T.
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
         b Install the lockwire (Material No.MS20995C32) .
     (e) Connect the sense tubes (75) and (80) to the pylon interface tubes.
F Pneumatic System ** ON A/C NOT FOR ALL
     (f) TORQUE the tubes coupling to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft ) T.
     (g) Install a new AIPC 73-11-11-01-070 GASKET (15) and the main fuel supply hose (20) to the fluid disconnect panel with the four bolts (25) and washers (30).
F Power Plant - Left Side ** ON A/C NOT FOR ALL
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL SAFETYWIRE. EACH TIME YOU CUT SAFETYWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE SAFETYWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
     (h) TORQUE the four bolts (25) to between 90 and 81 lbf.in (1.02 and 0.92 m.daN ) T. Safety with CP8001safetywire 0.032 in. (0.8 mm) dia..
     (i) Install a new AIPC 73-11-48-01-030 GASKET (10) and the fuel/return by-pass hose (45) to the fluid disconnect panel with the bolts (35) and washers (40).
F Power Plant - Left Side ** ON A/C NOT FOR ALL
     (j) TORQUE the four bolts (35) to between 36 and 24 lbf.in (0.41 and 0.27 m.daN ) T.
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL SAFETYWIRE. EACH TIME YOU CUT SAFETYWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE SAFETYWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
     (k) Safety the bolts (35) with CP8001safetywire 0.032 in. (0.8 mm) dia. or CP8002safetywire 0.032 in. (0.8 mm) dia..
     (l) Connect the upper case drain hose (50) to the fluid disconnect panel.
F Power Plant - Left Side ** ON A/C NOT FOR ALL
     (m) TORQUE the hose coupling to between 20.41 and 17.92 lbf.ft (2.77 and 2.43 m.daN ) T.
     (n) Connect the hydraulic pressure hose (55) to the fluid disconnect panel.
F Power Plant - Left Side ** ON A/C NOT FOR ALL
     (o) TORQUE the hose coupling to between 78.75 and 71.25 lbf.ft (10.68 and 9.66 m.daN ) T.
     (p) Connect the suction hose (60) coupling half to the fluid disconnect panel and tighten the coupling half handtight.
F Power Plant - Left Side ** ON A/C NOT FOR ALL
     (q) Connect the hose/tube (175) to the check valve restrictor pipe interface on the HCU.
F Power Plant - Left Side ** ON A/C NOT FOR ALL
       1 TORQUE the hose coupling to between 100 and 85 lbf.in (1.13 and 0.96 m.daN ) T.
NOTE: To get better access to the HCU, it is possible to move the left thrust reverser from the 45 degrees open position to the 35 degrees open position.
     (r) Connect the thrust reverser harness connectors 4100KSA and 4100KSB to electrical junction box. Tighten the connectors fingertight plus one-eighth turn with PLIERS - NOSE, SOFT, LONG.
F Power Plant - Left Side ** ON A/C NOT FOR ALL
   (2) Install these components on the right side of the engine:
     (a) Connect the upper starter duct to the pylon duct with the coupling (5).
F Power Plant - Right Side ** ON A/C NOT FOR ALL
     (b) TORQUE the coupling as follows:
       1 TORQUE the coupling to between 80 and 70 lbf.in (0.90 and 0.79 m.daN ) T.
       2 Lightly hit the coupling perimeter in different places with a fiber hammer.
       3 TORQUE the coupling again to the specified value.
       4 Lightly hit the coupling perimeter again.
       5 TORQUE the coupling again to the specified value.
     (c) Connect the electrical connectors:
CAUTION: MAKE SURE THAT THE CONNECTORS ARE CORRECTLY LOCKED. IF THE CONNECTORS HAVE A LOCK DISPLAY WINDOW, MAKE SURE THAT YOU CAN SEE THE ORANGE OR RED COLOR IN THE WINDOW. THIS SHOWS THAT THE CONNECTORS ARE CORRECTLY LOCKED.
       1 Connect the electrical connectors 401VCA, 402VCA, 403VCA, 404VCA, 405VCA, 406VCA, 407VCA, 408VCA, 409VCA, 447VCA and 448VCA to the pylon junction box. Tighten the connectors fingertight plus one-eighth turn with PLIERS - NOSE, SOFT, LONG.
F Power Plant - Right Side ** ON A/C NOT FOR ALL
       2 Connect the thrust reverser harness connectors 4101KSA, 4101KSB and 4102KSA to the thrust reverser hydraulic control unit. Tighten the connectors fingertight plus one-eighth turn with PLIERS - NOSE, SOFT, LONG.
F Power Plant - Right Side ** ON A/C NOT FOR ALL
       3 Put the clamp (10) on the harness for connector 4101KSB.
       4 Attach the clamp (10) and the clamp (25) to the bracket on the HCU with the screw (15) and nut (20).
       5 TORQUE the nut (20) to between 25 and 20 lbf.in (0.28 and 0.23 m.daN ) T.
       6 Connect the generator harness connector 400VCA to the forward pylon junction box.
F Power Plant - Right Side ** ON A/C NOT FOR ALL
         a Do not clean the contacts with abrasive material.
         b Tighten the connector with strap wrench until the orange (or red) color is visible in the lock display (window).
       7 Connect the electrical connectors 450VCA, 452VCA, 454VCA, and 457VCA to the aft pylon junction box. Tighten the connectors fingertight plus one-eighth turn with PLIERS - NOSE, SOFT, LONG.
F Thrust Reverser Electrical Connectors ** ON A/C NOT FOR ALL
       8 Install the two clamps which attach the core harness to the pylon.
         a Make sure that you install the correct clamps on the core harness. Two clamp sizes (diameter) can be found depending on the core harness diameter.
Subtask 71-00-00-410-217-A ** ON A/C NOT FOR ALL
D. Close access
   (1) Check the High Pressure bleed and Pressure Regulating Valves configuration.
     (a) Make sure that HP bleed and pressure regulating valves are not mechanically locked and can operate freely.
   (2) Make sure that the work area is clean and clear of tools and other items.
   (3) Remove the adhesive tape from the fan duct panels.
   (4) Install the access panels:
     (a) FOR [1000EM1] (ENGINE-1)
       1 473AL, 473AR
     (b) FOR [1000EM2] (ENGINE-2)
       1 483AL, 483AR

PRE SPIB CFM02253MW1
   (5) Install the fuel overboard drain tube at the rear of the drain mast
(Ref. AMM TASK 71-73-49-400-025).

END OF PRE SPIB CFM02253MW1


POST SPIB CFM02253MW1

   (6) Not Applicable

END OF SPIB CFM02253MW1

Subtask 71-00-00-869-436-A ** ON A/C NOT FOR ALL
E. Check 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 milliohms.
Subtask 71-00-00-820-107-A ** ON A/C NOT FOR ALL
F. Do the adjustment of the LH or RH thrust reverser "J" ring (Ref. AMM TASK 78-36-42-820-002).
Subtask 71-00-00-820-108-A ** ON A/C NOT FOR ALL
G. Do the adjustment of the thrust reverser half door latches (Ref. AMM TASK 78-36-41-820-042).
Subtask 71-00-00-820-109-A ** ON A/C NOT FOR ALL
H. Do the check of the adjustment of the thrust reverser half door latches (Ref. AMM TASK 78-36-41-820-043).
Subtask 71-00-00-440-115-A ** ON A/C NOT FOR ALL
I. Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041).
Subtask 71-00-00-612-058-A ** ON A/C NOT FOR ALL
J. Do a check of the oil levels
   (1) Make sure that the IDG oil level is correct (Ref. AMM TASK 24-21-00-210-046).
   (2) Make sure that the starter oil level is correct (Ref. AMM TASK 12-13-80-610-002).
   (3) Make sure that the oil tank level is correct (Ref. AMM TASK 12-13-79-610-002).
Subtask 71-00-00-614-058-A ** ON A/C NOT FOR ALL
K. Do the hydraulic maintenance procedure after an engine installation:
   (1) FOR [1000EM1] (ENGINE-1)
   (2) FOR [1000EM2] (ENGINE-2)
Subtask 71-00-00-942-094-A ** ON A/C NOT FOR ALL
L. Remove the access platform(s).
Subtask 71-00-00-410-218-A ** ON A/C NOT FOR ALL
M. Close the thrust reverser cowl doors (Ref. AMM TASK 78-36-00-410-040):
   (1) FOR [1000EM1] (ENGINE-1)
451AL, 452AR
   (2) FOR [1000EM2] (ENGINE-2)
461AL, 462AR
Subtask 71-00-00-865-235-A ** ON A/C NOT FOR ALL
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 SEQUENCE:
  • THE PROBES WILL BECOME TOO HOT.
  • THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
N. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUANTI ICE/PROBES/PHC/12DA1D03
122VUANTI ICE/WHC/25DG2W13
122VUANTI ICE/WHC/15DG1X13
122VUANTI ICE/PROBES/PHC/32DA3Y16
122VUANTI ICE/PROBES/PHC/22DA2Y12
Subtask 71-00-00-865-236-A ** ON A/C NOT FOR ALL
O. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUCOM/CVR/SPLY2RKE14
49VUCOM/CVR/CTL4RKE13
** ON A/C NOT FOR ALL
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
49VUANTI ICE/PROBES/AOA/14DA1D04
49VUANTI ICE/PROBES/PITOT/13DA1D02
** ON A/C NOT FOR ALL
49VUANTI ICE/RAIN/RPLNT/CAPT1DB1D01
** ON A/C NOT FOR ALL
49VUCOM/CVR/SPLY23RKE14
49VUCOM/CVR/CTL26RKE13
** ON A/C NOT FOR ALL
121VURCDR/DFDR7TUK16
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/B2WE1Q44
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL1/SQUIB/A1WE1Q43
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/B2WE2Q42
121VUENGINE/ENG1 AND 2 FIRE EXTIG/BTL2/SQUIB/A1WE2Q41
122VUANTI ICE/WINDOWS/R4DG2W14
122VUANTI ICE/WINDOWS/L4DG1X14
122VUANTI ICE/PROBES/2/TAT1DA2Y15
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/2/STATIC5DA2Y11
122VUANTI ICE/PROBES/3/PITOT3DA3Z16
122VUANTI ICE/PROBES/3/AOA4DA3Z15
122VUANTI ICE/PROBES/3/STATIC5DA3Z14
122VUANTI ICE/PROBES/1/STATIC5DA1Z13
122VUANTI ICE/PROBES/1/TAT1DA1Z12
** ON A/C NOT FOR ALL
122VUANTI ICE/RAIN/RPLNT/F/O1DB2W11
** ON A/C NOT FOR ALL
FOR FIN: 1000EM1 (ENGINE1)
49VUFUEL/LP VALVE/MOT1/ENG11QGA08
49VUENGINE/1/FIRE DET/LOOP A7WD1A06
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
121VUFUEL/LP VALVE/MOT2/ENG13QGM25
121VUENGINE/IGN/ENG1/SYS B3JH1P41
121VUENGINE/IGN/ENG1/SYS A BAT2JH1P39
121VUENGINE/ENG1/FIRE DET/LOOP B8WD1Q38
121VUENGINE/ENG1/FADEC B/AND EIU 14KS1R41
122VUELEC/GCU/12XU1T26
122VUANTI ICE/ENG/11DN1X10
FOR FIN: 1000EM2 (ENGINE2)
49VUFUEL/LP VALVE/MOT1/ENG22QGA09
49VUENGINE/2/FIRE DET/LOOP B8WD2A07
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
121VUFUEL/LP VALVE/MOT2/ENG24QGM26
121VUHYDRAULIC/HYD POWER/Y3803GXN30
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
121VUENGINE/ENG2/FADEC B4KS2Q40
121VUENGINE/ENG2/FIRE DET/LOOP A7WD2Q39
122VUELEC/GCU/22XU2T27
122VUANTI ICE/ENG/21DN2W10
123VUY HYD/ELEC/PUMP3802GXAB06
123VUY HYD/ELEC/ELEC PUMP/NORM3801GXAB03
Subtask 71-00-00-942-093-A ** ON A/C NOT FOR ALL
P. Put the aircraft back to its initial configuration.
   (1) Remove the WARNING NOTICE(S).
   (2) On the panel 114VU, remove the locking tool from the flap and slat control lever.
Subtask 71-00-00-861-128-A ** ON A/C NOT FOR ALL
Q. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
Subtask 71-00-00-869-435-A ** ON A/C NOT FOR ALL
R. Do the EIS start procedure (upper and lower ECAM DU's only) (Ref. AMM TASK 31-60-00-860-001).
Subtask 71-00-00-740-068-A ** ON A/C NOT FOR ALL
S. Update the engine hours and cycles (Ref. AMM TASK 31-36-00-740-005).
NOTE: Some tasks will possibly not be applicable depending on whether a DMU or an FDIMU is installed on the aircraft.
Subtask 71-00-00-720-093-A ** ON A/C NOT FOR ALL
T. Do the tests:
   (1) On the left or right MCDU, do this check:
NOTE: This subtask is applicable for DAC engines.
     (a) Get access to the screen of the SYSTEM REPORT/TEST ENG (Ref. AMM TASK 31-32-00-860-012).
     (b) Push the line key adjacent to the FADEC 1(2) A(B): the ENGINE MAIN MENU page comes into view.
     (c) Do a functional test of the ECU (Ref. AMM TASK 73-21-60-720-040).
     (d) Read the LRU identification report of the engine 1(2) (Ref. AMM TASK 73-21-60-740-006).
NOTE: The LRU identification check is only required on one channel of the ECU A or B.
       1 Push the line key adjacent to the LRU IDENT indication: CHANNEL A(B) page comes into view.
       2 Read the data that comes on the MCDU screen and check for consistency with the actual engine configuration:
         a Engine thrust rating and type:
  • These inputs are available on the engine name plate.
NOTE: The engine thrust rating must be the same as on opposite engine and consistent with the aircraft model.
         b "LRU PART NO" (ECU part number):
  • The P/N is available on the ECU identification plate.
NOTE: Make sure that the intermix ability of both ECU standards is correct.
         c "N1 TRIM":
  • The N1 trim level (0 through 7) is available on the engine name plate.
         d "BUMP" option: must read "Y" or "N".
         e "PMUX" option:
  • PMUX engine (4 hoses connected to the ECU) must read "Y".
  • Non PMUX engine (2 hoses connected to the ECU) must read "N".
         f "CONFIG" (system configuration): check the engine Engine Data Submittal (EDS) for reference:
  • "RACSB" applies to CFM56-5BX/2 non/P equipped with a RACSB Valve.
  • "TBV" applies to CFM56-5BX/2P or -5BX/3 equipped with a TBV Valve.
  • "NACTB" applies to CFM56-5BX/2P equipped with NACTB Valve.
         g "DAC CONFIG" (DAC hardware configuration): check the engine EDS for reference:
  • "1" = DAC 1 (DAC 1 combustor with DAC 1 fuel nozzles)
  • "2" = DAC FN (DAC 1 combustor with DAC 2 fuel nozzles)
  • "3" = DAC 2 COMB (DAC 2 combustor with DAC 2 fuel nozzles).
       3 If some inconsistencies are noticed in the above data, refer to the task (Ref. AMM TASK 73-21-90-860-001) to correctly program the identification plug.
NOTE: Change of the engine thrust rating is only allowed by Service Bulletin application. It cannot be done by the plug programming.
       4 Do the entry of the "ENGINE" S/N through the MCDU menu according to instructions of the procedure (Ref. AMM TASK 73-21-60-740-008).
NOTE: If a pre Service Bulletin 72-108 engine identification connector is installed (P/N 320-XXX-XXX-0), the Engine Serial Number (ESN) is automatically entered into the ECU memory.
NOTE: The engine serial number check is required on both channels A and B.
         a Make sure the "ENGINE" S/N displayed on the screen is the same as the one written on the engine name plate.
       5 Make sure EVMU configuration get the data from the N1 bearing vibration sensor through MCDU (Ref. AMM TASK 77-32-34-860-041).
       6 Check that the "TRSOV" installation status matches the aircraft configuration.
NOTE: The TRSOV check is required on both channels A and B.
         a "Y" must be displayed if the thrust reverser shut-off valve is installed.
         b "N" must be displayed if the thrust reverser shut-off valve is not installed.
         c Change the installation status through the MCDU menu if required according to instructions of the procedure (Ref. AMM TASK 73-21-60-740-006).
     (e) If you operate the aircraft in actual CAT III conditions, do these tests:
  • Make sure that there is no CAT 3 DUAL INOP message on the lower ECAM DU with FADEC GND PWR 1 & 2 pushbutton switches (maintenance panel 50VU) pushed (ON legends on) and 3 IR'S aligned (Ref. AMM TASK 34-10-00-860-004).
  • Do the operational test of the LAND CAT III capability (Ref. AMM TASK 22-97-00-710-001).
Subtask 71-00-00-720-094-A ** ON A/C NOT FOR ALL
U. Do the tests:
   (1) On the left or right MCDU, do this check:
NOTE: This subtask is applicable for SAC engines.
     (a) Get access to the screen of the SYSTEM REPORT/TEST ENG (Ref. AMM TASK 31-32-00-860-012).
     (b) Push the line key adjacent to the FADEC 1(2) A(B): The ENGINE MAIN MENU page comes into view.
     (c) Do a functional test of the ECU (Ref. AMM TASK 73-21-60-720-040).
     (d) Read the LRU IDENTIFICATION Report of the engine 1(2) (Ref. AMM TASK 73-21-60-740-006).
NOTE: The LRU identification check is only required on one channel of the ECU A or B.
       1 Push the line key adjacent to the LRU IDENT indication: CHANNEL A(B) page comes into view.
       2 Read the data that comes on the MCDU screen and check for consistency with the actual engine configuration:
         a Engine thrust rating and type:
  • These inputs are available on the engine name plate.
NOTE: The engine thrust rating must be the same as on opposite engine and consistent with the aircraft model.
         b "LRU PART NO" (ECU part number):
  • The P/N is available on the ECU identification plate.
NOTE: Make sure that the intermix ability of both ECU standards is correct.
         c "N1 TRIM":
  • The N1 trim level (0 through 7) is available on the engine name plate.
         d "BUMP" option: must read "Y" or "N".
         e If "OVERBOOST" is displayed on the screen: must read "N".
         f "PMUX" option:
  • PMUX engine (4 hoses connected to the ECU) must read "Y".
  • Non PMUX engine (2 hoses connected to the ECU) must read "N".
         g If "CONFIG" is displayed on the screen:
  • "RACSB" applies to CFM56-5BX non/P equipped with a RACSB valve.
  • "TBV" applies to CFM56-5BX/P or -5BX/3 equipped with a TBV valve.
       3 If some inconsistencies are noticed in the above data, refer to the task (Ref. AMM TASK 73-21-90-860-001) to correctly program the identification plug.
NOTE: Change of the engine thrust rating is only allowed by Service Bulletin application. It cannot be done by the plug programming.
       4 Do the entry of the "ENGINE" S/N through the MCDU menu according to instructions of the procedure (Ref. AMM TASK 73-21-60-740-008).
NOTE: For CFM56-5B-non/P: if a pre Service Bulletin 72-215 engine identification connector is installed (P/N 320-XXX-XXX-0), the ESN is automatically entered into the ECU memory.
NOTE: The engine serial number check is required on both channels A and B.
         a Make sure the "ENGINE" S/N displayed on the screen is the same as the one written on the engine name plate.
       5 Make sure EVMU configuration get the data from the N1 bearing vibration sensor through MCDU Menu according to instructions of the procedure (Ref. AMM TASK 77-32-34-860-041).
       6 Check that the "TRSOV" installation status matches the aircraft configuration.
NOTE: The TRSOV check is required on both channels A and B.
         a "Y" must be displayed if the thrust reverser shut-off valve is installed.
         b "N" must be displayed if the thrust reverser shut-off valve is not installed.
         c Change the installation status through the MCDU menu if required according to instructions of the procedure (Ref. AMM TASK 73-21-60-740-006).
       7 Check that the "Core Chevron Nozzle" installation status matches the aircraft configuration.
         a "Y" must be displayed if the engine is fitted with acoustic modifier CCNECU (Core Chevron Nozzle).
         b "N" must be displayed if the engine is fitted with common core nozzle.
         c If necessary, change the installation status through the MCDU menu according to instructions of the procedure (Ref. AMM TASK 73-21-60-740-005).
     (e) If you operate the aircraft in actual CAT III conditions, do these tests:
  • Make sure that there is no CAT 3 DUAL INOP message on the lower ECAM DU with FADEC GND PWR 1 & 2 pushbutton switches (maintenance panel 50VU) pushed (ON legends on) and 3 IR'S aligned (Ref. AMM TASK 34-10-00-860-004).
  • Do the operational test of the LAND CAT III capability (Ref. AMM TASK 22-97-00-710-001).
Subtask 71-00-00-710-304-A ** ON A/C NOT FOR ALL
V. Do an operational test:
   (1) Do an operational test of the FADEC with engine motoring (Ref. AMM TASK 73-29-00-710-040)
     (a) Do an operational test of the hydraulic pump during the FADEC test:
   (2) FOR [1000EM1] (ENGINE-1)
(Ref. AMM TASK 29-11-00-710-001)
   (3) FOR [1000EM2] (ENGINE-2)
(Ref. AMM TASK 29-13-00-710-002)
   (4) Do a check for leaks on the hydraulic and fuel lines.
Subtask 71-00-00-710-305-B ** ON A/C NOT FOR ALL
W. Do an operational test:
   (1) Do an operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-042).
NOTE: As an alternative procedure, you can do this operational test without the CFDS.
   (2) Start the engine 1(2) (Ref. AMM TASK 71-00-00-710-003).
   (3) Do an operational test of the ice protection of the engine air intake (Ref. AMM TASK 30-21-00-710-002).
   (4) Do a minimum idle check and a check for leaks (Ref. AMM TASK 71-00-00-710-006).
   (5) Make sure that the IDG is connected:
     (a) 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.
       1 Make sure that the related GCU is energized.
       2 Reset the GCU:
  • On the ELEC control panel 35VU, release (OFF) then push the related ELEC/GEN pushbutton switch 3XU.
       3 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.
     (b) If the IDG1(2) is not connected after the GCU reset, do a check for other maintenance messages related to the IDG.
   (6) Do a leak check of the fuel return valve (Ref. AMM TASK 73-11-50-360-002) to make sure that there are no leaks at pylon connection.
   (7) Stop the engine (Ref. AMM TASK 71-00-00-710-028).
Subtask 71-00-00-410-219-A ** ON A/C NOT FOR ALL
X. Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040):
   (1) FOR [1000EM1] (ENGINE-1)
437AL, 438AR
   (2) FOR [1000EM2] (ENGINE-2)
447AL, 448AR
Subtask 71-00-00-820-106-A ** ON A/C NOT FOR ALL
Y. Do the adjustment/test of the fan cowl doors (Ref. AMM TASK 71-13-00-800-041).
Subtask 71-00-00-710-306-A ** ON A/C NOT FOR ALL
Z. Do the tests that follow:
   (1) Start the engine 1(2) (Ref. AMM TASK 71-00-00-710-003).
   (2) Do this test:
PRESSURE REGULATING VALVE AND HIGH PRESSURE BLEED VALVE CHECK
ACTION
RESULT
1.On the lower ECAM DU, select the BLEED page.

2.On the panel 30VU, push the AIR COND PACK 1(2) pushbutton switch.
  • On the AIR COND PACK 1(2) pushbutton switch, the OFF legend goes off.
3.On the panel 30VU, confirm that the APU bleed is closed.
  • On the APU BLEED pushbutton switch, the ON legend is off.
4.On the panel 30VU, release the ENG 1(2) BLEED pushbutton switch.
  • On the ENG 1(2) BLEED pushbutton switch, the OFF legend comes on.
  • On the lower ECAM DU, the PRV and HP valves are shown closed.
5.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.
6.Slowly move the throttle control lever to increase power above idle.
  • On the lower ECAM DU, the HP valve closes above idle.
7.Slowly move the throttle control lever to decrease power to idle.
  • On the lower ECAM DU, the HP valve opens at idle.
8.On the panel 30VU, release the AIR COND PACK 1(2) pushbutton switch.
  • On the AIR COND PACK 1(2) pushbutton switch, the OFF legend comes on.
   (3) Do a power assurance check (Ref. AMM TASK 71-00-00-710-008).
NOTE: A power assurance check is not necessary if:
  • The engine was tested and accepted in an approved test cell, or
  • The engine was previously removed for convenience or time staggering, or
  • The engine was removed for a turbine rear frame replacement.
   (4) Do a vibration check (Ref. AMM TASK 71-00-00-710-009).
NOTE: A vibration check is not necessary if:
  • The engine was tested and accepted in an approved test cell, or
  • The engine was previously removed for convenience or time staggering.
   (5) Do an accel check (Ref. AMM TASK 71-00-00-710-025).
NOTE: An accel check is not necessary if:
  • The engine was tested and accepted in an approved test cell, or
  • The engine was previously removed for convenience or time staggering, or
  • The engine was removed for a turbine rear frame replacement.
   (6) Stop the engine (Ref. AMM TASK 71-00-00-710-028).
   (7) Do an operational test of the IDG disconnect system (Ref. AMM TASK 24-21-00-710-040).
Subtask 71-00-00-869-437-A ** ON A/C NOT FOR ALL
AA. 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.
[Rev.10 from 2021] 2026.04.01 02:24:30 UTC
"Aviabrain" 2025