W DOC AIRBUS | AMM A320F

Installation of the Power Plant with Cobra Tool [IAE]

TASK 71-00-20-400-040-A-02
Installation of the Power Plant with Cobra Tool

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.
WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
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.
CAUTION: MAKE SURE THAT THE EEC STANDARDS INSTALLED ARE CORRECT. SOME EEC STANDARDS 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 DISSYMMETRY AND THUS DAMAGE TO THE AIRCRAFT.
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
DYNAMOMETER 15 DAN (33 LBF) - PULL
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 132.74 and 88.49 lbf.ft (18.00 and 12.00 m.daN ) T
No specific
Torque wrench: range to between 8 and 6 lbf.in (0.09 and 0.07 m.daN ) T
No specific
Torque wrench: range to between 36 and 24 lbf.in (0.41 and 0.27 m.daN ) T
No specific
Torque wrench: range to between 40 and 35 lbf.in (0.45 and 0.40 m.daN ) T
No specific
Torque wrench: range to between 245 and 215 lbf.in (2.77 and 2.43 m.daN ) T
No specific
Torque wrench: range to between 0.42 and 0.38 m.daN (37.17 and 33.63 lbf.in ) T
No specific
Torque wrench: range to between 0.62 and 0.51 m.daN (54.87 and 45.13 lbf.in ) T
No specific
Torque wrench: range to between 0.8 and 0.6 m.daN (70.80 and 53.10 lbf.in ) T
No specific
Torque wrench: range to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in ) T
No specific
Torque wrench: range to between 0.9 and 0.8 m.daN (79.65 and 70.80 lbf.in ) T
No specific
Torque wrench: range to between 0.96 and 0.85 m.daN (84.96 and 75.22 lbf.in ) T
No specific
Torque wrench: range to between 1.2 and 1 m.daN (106.19 and 88.50 lbf.in ) 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 2.3 and 2.0 m.daN (16.96 and 14.75 lbf.ft ) T
No specific
Torque wrench: range to between 10.7 and 9.7 m.daN (78.91 and 71.53 lbf.ft ) T
No specific
Torque wrench: range to between 47.45 and 43.39 m.daN (349.93 and 319.99 lbf.ft ) T
No specific
Torque wrench: range to between 70.5 and 65 m.daN (519.91 and 479.35 lbf.ft ) T
98D71203001000
1
CHEST,TORQUE SET-ENGINE R I
EC001-002
1

ED005-002
1

SG233-001
1
SAFETY DEVICE
SG233-050
1
BEAM FOR SAFETY DEVICE
TP91G1A1A01
1

 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.V02-282)
safety cable
(Material No.V02-283)
safety cable
(Material No.V02-283A)
safety cable
(Material No.V02-284)
safety cable
(Material No.V02-285)
safety cable
(Material No.V02-286)
safety cable
(Material No.V02-287)
safety cable
(Material No.V02-288)
safety cable
(Material No.V02-289)
safety cable
(Material No.V02-290)
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
FIG.ITEM
DESIGNATION
IPC-CSN
17
screws
AIPC 71-51-46-80-010
16
seal assembly
AIPC 71-51-46-80-020
15
seal assembly
AIPC 71-51-46-80-030
3
gasket
AIPC 73-11-48-80-080
11
gasket
AIPC 73-11-48-80-120
 E. Referenced Information
REFERENCE
DESIGNATION
TASK 05-57-00-200-001-B
Aircraft Stability
TASK 12-13-24-612-011-A
IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check
TASK 12-13-79-610-012-A
Prime the Engine Oil System
TASK 12-13-80-600-010-B
Replenishment of Starter Oil System
TASK 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)
TASK 22-97-00-710-001-A
Operational Test of the LAND CAT III Capability
TASK 24-21-00-710-042-A
Operational Test of the IDG Disconnect and Reconnect (Reset) 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 29-10-00-863-001-A
Pressurize the Green Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-002-A
Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-14-00-614-002-A
Pressurization of the Hydraulic Reservoirs through the Ground Connector
TASK 29-14-00-614-002-A-01
Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU)
TASK 30-21-00-710-002-A
Operational Check of the Engine-Air-Intake Ice-Protection System (with the Engines in operation)
TASK 30-21-49-790-010-A
Leak Test of the Inlet Cowl Anti-Ice Supply Ducts with the Engine in Operation
TASK 30-21-49-820-001-A
Rig the Anti-ice Ducts
TASK 31-36-00-740-005-A
Update of the Engine Hours and Cycles in the DMU after Engine or DMU Replacement
TASK 31-60-00-860-001-A
EIS Start Procedure
TASK 31-60-00-860-002-A
EIS Stop Procedure
TASK 70-11-50-100-802-A
Local Swab or Wipe Cleaning with Solvent
TASK 70-23-11-911-013-A
General Torque Tightening Techniques
TASK 70-23-13-911-010-A
Procedures for the Installation of Preformed Packings
TASK 70-23-15-912-010-A
Connection of Electrical Connectors
TASK 70-40-11-911-014-A
Locking Devices General Information
TASK 70-40-11-911-016-A
General Instructions for Uses of Safety Cable
TASK 71-00-00-700-011-B
Test No.13 : Pretested Replacement Engine Test
TASK 71-00-00-710-012-B
Test No.3 : Idle Leak Check
TASK 71-00-00-710-022-B
Test No.6 : ELectronic Engine Control (EEC) System Idle Test
TASK 71-00-00-710-045-A
Test No.1 : Dry Motor Leak Check
TASK 71-00-00-710-046-B
Test No.2 : Wet Motor Leak Check
TASK 71-13-00-010-010-A
Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-410-010-A
Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-800-010-A
Functional Check of Fan Cowl Latch Tension
TASK 71-21-12-200-010-A
Detailed Inspection of FWD Engine Mount Installation
TASK 71-22-11-200-010-A
Detailed Inspection of AFT Engine Mount Installation
TASK 71-71-42-400-010-A
Installation of the Drains Mast
TASK 72-61-49-400-010-B
Installation of the Gearbox Breather Outlet Duct (GBOD)
TASK 73-13-42-720-010-A
Functional Test of the Fuel Recirculation Cooling System without Barfield Tester and without AIDS
TASK 73-13-42-720-010-A-01
Functional Test of the Fuel Recirculation Cooling System with Barfield Tester and without AIDS
TASK 73-13-42-720-010-A-02
Functional Test of the Fuel Recirculation Cooling System without Barfield Tester and with AIDS
TASK 73-13-42-720-010-A-03
Functional Test of the Fuel Recirculation Cooling System with Barfield Tester and with AIDS
TASK 73-22-34-710-040-A
Operational Test of the EEC
TASK 78-30-00-040-012-A
Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance
TASK 78-30-00-440-012-A
Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance
TASK 78-30-00-820-010-A
Rig of the Thrust Reverser System
TASK 78-32-00-010-010-A
Opening of the Thrust Reverser Halves
TASK 78-32-00-410-010-A
Closing of the Thrust Reverser Halves
TASK 80-13-49-820-010-B
Rig the Starter Ducts
TASK 80-13-51-710-040-B
Operational Test of the Pneumatic Starter Valve and FMU with the CFDS
ESPM 2048230
ESPM 2048240
SPM 702305
TASK 05-59-00-00
SPECIAL FLIGHTS - DESCRIPTION AND OPERATION
F Engine Identification Plate
F Table 1 - New Data Entry Plug PN 2A4378 Variants
F Data Entry Plug Back Shell Inscription
F Forward Engine Mount
F Aft Engine Mount
F Cobra Tool
F Hinge Crossover Beam
F Fan Cowl and Thrust Reverser Braces
F TAI Location and Hydraulic Reservoir Pressurization Tube Location
F Power Plant, Left Side
F Left Connectors Location
F Power Plant, Right Side
F Forward Junction Box
F Upper/Lower Link Starter Duct and Link Assembly
F Forward Junction Box
F Left Interface Junction Box
F Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire Seals
F Fire Seal Installation
F Hydraulic Control Unit
FOR [1000EM1] (ENGINE-1)
TASK 29-11-00-710-001-A
Operational Test of the Green Hydraulic System
FOR [1000EM2] (ENGINE-2)
TASK 29-13-00-710-002-A
Operational Test of the Yellow Hydraulic System
3. Job Set-up
Subtask 71-00-20-860-063-A ** ON A/C NOT FOR ALL
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:
   (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 71-00-20-010-064-A ** ON A/C NOT FOR ALL
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 71-00-20-040-057-A ** ON A/C NOT FOR ALL
C. Make sure that the thrust reverser Hydraulic Control Unit (HCU) is deactivated (Ref. AMM TASK 78-30-00-040-012).
Subtask 71-00-20-865-061-A ** ON A/C NOT FOR ALL
WARNING: MAKE SURE THAT YOU OPEN THE CIRCUIT BREAKERS AS FOLLOWS:
  • 1JH, 2JH1 AND 3JH1 BEFORE 2KS1
  • 1JH, 2JH2 AND 3JH2 BEFORE 2KS2.
IF YOU DO NOT OBEY THIS SEQUENCE, THERE IS A RISK OF ELECTROCUTION. THIS IS BECAUSE YOU WILL START CONTINUOUS IGNITION IF YOU OPEN CIRCUIT BREAKER 2KS1 OR 2KS2 FIRST.
WARNING: OPEN THE PROBE HEATER CIRCUIT-BREAKERS 1DA1(2), 3DA1(2,3), 4DA1(2,3) AND 5DA1(2,3) BEFORE YOU OPEN THE PHC CIRCUIT BREAKERS 2DA1(2,3). IF YOU DO NOT OBEY THIS SEQUENCE:
  • THE PROBES WILL BECOME TOO HOT.
  • THIS CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY TO MAINTENANCE PERSONNEL.
D. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
49VUANTI ICE/PROBES/AOA/14DA1D04
49VUANTI ICE/PROBES/PHC/12DA1D03
49VUANTI ICE/PROBES/PITOT/13DA1D02
49VUANTI ICE/RAIN/RPLNT/CAPT1DB1D01
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/RAIN/RPLNT/F/O1DB2W11
122VUANTI ICE/WINDOWS/L4DG1X14
122VUANTI ICE/PROBES/PHC/32DA3Y16
122VUANTI ICE/PROBES/2/TAT1DA2Y15
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/PHC/22DA2Y12
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
FOR FIN: 1000EM1 (ENGINE1)
49VUENGINE/1/FIRE DET/LOOP A7WD1A06
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
49VUCOM/CVR/SPLY2RKE14
49VUCOM/CVR/CTL4RKE13
121VURCDR/DFDR7TUK16
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)
49VUENGINE/2/FIRE DET/LOOP B8WD2A07
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
121VUHYDRAULIC/HYD POWER/Y3803GXN30
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
121VUENGINE/ENG2/FADEC B/AND EIU 24KS2Q40
121VUENGINE/ENG2/FIRE DET/LOOP A7WD2Q39
122VUELEC/GCU/22XU2T27
122VUANTI ICE/ENG/21DN2W10
123VUY HYD/ELEC/PUMP3802GXAB06
123VUY HYD/ELEC/ELEC PUMP/NORM3801GXAB03
Subtask 71-00-20-210-065-A ** ON A/C NOT FOR ALL
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 71-00-20-110-056-A ** ON A/C NOT FOR ALL
F. 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).
F Forward Engine Mount ** ON A/C NOT FOR ALL
F Aft Engine Mount ** ON A/C NOT FOR ALL
   (3) Make sure that there are no traces of seizure or wear.
Subtask 71-00-20-230-053-A ** ON A/C NOT FOR ALL
G. Do an ultra-high sensitivity fluorescent penetrant inspection of the engine mount bolts (1), (2) and (18) SPM 702305.
F Forward Engine Mount ** ON A/C NOT FOR ALL
F Aft Engine Mount ** ON A/C NOT FOR ALL
Subtask 71-00-20-240-053-A ** ON A/C NOT FOR ALL
H. Visual Inspections
   (1) Do a visual inspection of the forward engine mount nuts (5) and (16). Do not remove the silver plating.
F Forward Engine Mount ** ON A/C NOT FOR ALL
If an engine nut is cracked, reject it.
   (2) Do a visual inspection of the barrel nuts (6). 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 71-00-20-210-066-A ** ON A/C NOT FOR ALL
I. 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:
F Forward Engine Mount ** ON A/C NOT FOR ALL
     (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:
F Aft Engine Mount ** ON A/C NOT FOR ALL
     (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 (5) or (16) 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 71-00-20-420-098-A ** ON A/C NOT FOR ALL
J. 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 71-00-20-420-099-A ** ON A/C NOT FOR ALL
WARNING: FOR THE INSTALLATION OF COBRA TOOL FORK TUBES ON THE TRANSPORTATION STAND, MAKE SURE THAT THERE IS A STICKER ON THE STAND TO SHOW THE POSITION OF THE FORK TUBES. IF THERE IS NO STICKER, CONTACT COBRA TOOL MANUFACTURER FOR ALL THE INFORMATION NECESSARY TO PUT THE FORK TUBES IN THE CORRECT POSITION.
WARNING: DO NOT USE THE COBRA TOOL WITH A CRADLE/TROLLEY ASSEMBLY OTHER THAN THE ASSEMBLY REFERENCED IN THE JOB SET-UP INFORMATION PARAGRAPH. THE COBRA TOOL IS CERTIFIED 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.
A. Prepare the STAND,TRANSPORTATION (CRADLE-ENGINE and TROLLEY- ENGINE) and Cobra tool (1)
F Cobra Tool ** ON A/C NOT FOR ALL
NOTE: Engine contour given for exemple, should differ from real configuration
NOTE: You must also obey the instructions provided by the STAND,TRANSPORTATION Manufacturer's Instruction Manual to prepare and operate the STAND,TRANSPORTATION.
NOTE: Airbus recommend to use SG233-001 SAFETY DEVICE and SG233-050 BEAM FOR SAFETY DEVICE (2).
   (1) Install the fork tube (3) on the STAND,TRANSPORTATION EC001-002 and ED005-002 in a clear area.
   (2) Move the STAND,TRANSPORTATION and the power plant under the pylon.
     (a) You can use the ground marks you made during the removal of the engine to align the STAND,TRANSPORTATION, or if necessary realign the STAND,TRANSPORTATION with the engine pylon.
   (3) Make sure that the stand cradle is attached to the STAND,TRANSPORTATION.
   (4) Insert the Cobra tool lift adapters on the fork tube (3) to the STAND,TRANSPORTATION.
   (5) Position the Cobra tool TP91G1A1A01 (1) in the engine area.
   (6) Connect the lift adapters to the Cobra chains.
   (7) Align the Cobra tool (1) with the STAND,TRANSPORTATION.
     (a) See the Cobra tool Manufacturer user guide.
   (8) Connect the hose package (electrical + hydraulic) to the Cobra tool (master and slave unit).
NOTE: Keep always the master unit out of the lifting device area.
   (9) Set parameters:
  • Select the engine and shipping stand combination.
  • Check preload values for correct operation, -10 kg (-22 lb) on the forward pillars and 390 kg (860 lb) on the rear pillars.
   (10) Lift the STAND,TRANSPORTATION up to 300 mm (11.8110 in.).
   (11) If used, install the safety device (SG233-001 and SG233-050) (2).
   (12) Lift the STAND,TRANSPORTATION until 50 mm (1.9685 in.) before mount (pylon/engine) contact.
   (13) Adjust position of the safety device (SG233-001 and SG233-050) (2) to be in contact with the STAND,TRANSPORTATION.
Subtask 71-00-20-210-067-A ** ON A/C NOT FOR ALL
B. Make certain that the hinge crossover beam (1) is correctly engaged in the V-groove (2).
F Hinge Crossover Beam ** ON A/C NOT FOR ALL
Subtask 71-00-20-420-100-A ** ON A/C NOT FOR ALL
C. Install the power plant to the pylon.
CAUTION: MAKE SURE THAT YOU DO THE STEPS THAT FOLLOW. IF YOU DO NOT, DAMAGE TO EQUIPMENT CAN OCCUR.
   (1) Check preload for the STAND,TRANSPORTATION and nominal adjustement.
  • You can decrease rear preload until forward and aft attachment are in position.
  • Do not decrease forward and rear values not more than nominal value.
NOTE: It is recommended to slightly lift down the engine to increase the gaps.
   (2) Monitor the interface locations including the following:
     (a) Forward mount engagement.
     (b) Aft mount engagement.
   (3) Raise the STAND,TRANSPORTATION equally to align the power plant mounts.
NOTE: During rising of the STAND,TRANSPORTATION make sure that the frame stay horizontal.
     (a) Stop rising before contact between the engine mounts and the pylon.
     (b) 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.
     (c) Make sure that the forward-mount assembly is parallel to the pylon contact surface.
     (d) Raise carefully the STAND,TRANSPORTATION until the forward and aft-mount assembly are in contact (or almost, approximately 5 mm (0.20 in.)) with the pylon contact surface.
NOTE: Do not apply an overload on the Cobra tool indicator for final contact.
       1 Make sure that the forward mount assembly is correctly engaged in the pylon.
       2 Make sure that the aft mount assembly is correctly engaged in the pylon.
   (4) Raise the STAND,TRANSPORTATION equally.
   (5) Monitor the indications on the load indicator. Do not exceed exceed 2632 daN (5916.97 lbf) at the front and 878 daN (1973.82 lbf) at rear.
   (6) Make sure that the forward and aft mounts are fully and correctly engaged.
Subtask 71-00-20-420-101-A ** ON A/C NOT FOR ALL
D. Installation of the Forward and Aft Engine Mounts
   (1) Install the forward engine mount.
F Forward Engine Mount ** ON A/C NOT FOR ALL
     (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 40 and 35 lbf.in (0.45 and 0.40 m.daN ) T.
     (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.
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 132.74 and 88.49 lbf.ft (18.00 and 12.00 m.daN ) T.
     (i) Remove the padding from between the engine and the engine mount.
   (2) Install the aft engine mount attach fittings.
F Aft Engine Mount ** ON A/C NOT FOR ALL
     (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 70.5 and 65 m.daN (519.91 and 479.35 lbf.ft ) T (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 surfaces 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 71-00-20-080-053-A ** ON A/C NOT FOR ALL
E. Removal of the Cobra Tool.
   (1) Disconnect the cradle from the engine as described in the cradle user guide and recommended by the cradle manufacturer.
   (2) If used, unlock the safety device and turn it into the lifting down mode.
   (3) Lower the stand transportation and safety device. When Cobra tool reach one meter from the ground, if used, remove safety device.
   (4) Lower STAND, TRANSPORTATION and Cobra tool till the ground and disengage Cora tool and fork tube.
   (5) Remove the STAND, TRANSPORTATION from the area.
Subtask 71-00-20-760-052-A ** ON A/C NOT FOR ALL
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 71-00-20-420-102-A ** ON A/C NOT FOR ALL
G. Final Torque of the Bolts of the Forward Mount
CAUTION: MAKE SURE THAT THE TORQUE WRENCH DOES NOT TOUCH THE FORWARD ENGINE MOUNT DURING TIGHTENING TO NOT CHANGE THE TORQUE APPLIED TO THE BOLTS.
   (1) Use the special tool 98D71203001000 CHEST,TORQUE SET-ENGINE R I to TORQUE the forward mount bolts to the final torque value to between 47.45 and 43.39 m.daN (349.93 and 319.99 lbf.ft ) T (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 (TEM item 10) 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 (TEM item 20) and Load Reducer (TEM item 60) 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 surfaces 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) ,
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 36 and 24 lbf.in (0.41 and 0.27 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
   (5) Remove the fan cowl and thrust reverser braces
F Fan Cowl and Thrust Reverser Braces ** ON A/C NOT FOR ALL
     (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 71-00-20-630-052-A ** ON A/C NOT FOR ALL
A. Remove caps from the open ends.
Subtask 71-00-20-420-104-A ** ON A/C NOT FOR ALL
B. 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.
F TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL
       1 Connect the pressure-regulating-valve sensor tube (20).
       2 TORQUE the tube union nut to between 2.3 and 2.0 m.daN (16.96 and 14.75 lbf.ft ) T.
       3 Connect the thermostat sensor tube (11).
       4 TORQUE the union nut to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft ) T (Ref. AMM TASK 70-23-11-911-013).
     (b) Connect the fuel tubes to the fluid disconnect panel.
F Power Plant, Left Side ** ON A/C NOT FOR ALL
       1 Install a new AIPC 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 0.9 and 0.8 m.daN (79.65 and 70.80 lbf.in ) T (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 AIPC 73-11-48-80-080 gasket (3) on the fuel return to the tank tube (4).
       6 Put the fuel return to the 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 0.42 and 0.38 m.daN (37.17 and 33.63 lbf.in ) T (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).
     (c) Connect the hydraulic tubes to the fluid disconnect panel.
       1 Connect the hydraulic case drain connector (7) to the fluid disconnect panel.
       2 TORQUE the connector (7) to between 245 and 215 lbf.in (2.77 and 2.43 m.daN ) T (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 10.7 and 9.7 m.daN (78.91 and 71.53 lbf.ft ) T (Ref. AMM TASK 70-23-11-911-013).
       5 Connect the hydraulic-suction tube connector (1) to the fluid disconnect panel. Handtighten the connector.
     (d) Connect the cabin air duct.
F TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL
       1 Position the duct and install the coupling (7).
       2 TORQUE the coupling to between 0.96 and 0.85 m.daN (84.96 and 75.22 lbf.in ) T.
       3 Install the coupling. To do this, tap the coupling with a mallet.
       4 TORQUE the coupling again to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in ) T.
       5 Tap the coupling again.
       6 TORQUE the coupling again to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in ) T.
     (e) Connect the Thermal Anti-Ice (TAI) duct.
F TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL
       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.
F Left Connectors Location ** ON A/C NOT FOR ALL
     (g) Connect the thrust-reverser harness connectors 4101KS-A and 4101KS-B on the thrust reverser Hydraulic Control Unit (HCU).
F Left Connectors Location ** ON A/C NOT FOR ALL
   (2) Install these components from the right side of the engine.
F Power Plant, Right Side ** ON A/C NOT FOR ALL
     (a) Connect the starter duct.
F Forward Junction Box ** ON A/C NOT FOR ALL
F Upper/Lower Link Starter Duct and Link Assembly ** ON A/C NOT FOR ALL
F Forward Junction Box ** ON A/C NOT FOR ALL
       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).
F Forward Junction Box ** ON A/C NOT FOR ALL
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 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 0.62 and 0.51 m.daN (54.87 and 45.13 lbf.in ) T.
       5 Install the coupling. To do this, tap the coupling with a mallet.
       6 TORQUE the coupling again to between 0.62 and 0.51 m.daN (54.87 and 45.13 lbf.in ) T.
       7 Tap the coupling again.
       8 TORQUE the coupling again to between 0.62 and 0.51 m.daN (54.87 and 45.13 lbf.in ) T.
     (c) Connect the starter duct.
F Forward Junction Box ** ON A/C NOT FOR ALL
NOTE: Adjust the link assemblies when the engine is installed on the pylon.
       1 Remove the four nuts (7),the washers (9) and the bolts (8) from the two upper link assemblies (16) and (17). Remove the upper link assemblies.
       2 Remove the four nuts (7),the washers (9) and the 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 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in ) T.
       5 Lightly hit around the outside of the coupling with a fiber hammer.
       6 TORQUE coupling (5) again to between 0.9 and 0.79 m.daN (79.65 and 69.91 lbf.in ) T.
       7 Repeat steps 4_ thru 6_ two more times.
       8 Connect the lower link assemblies (11) and (12) to the fan case brackets with the bolts (8), the washers (9) and the 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 the bolts (8), the washers (9) and the 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 the bolts (8), the washers (9) and the nuts (7).
       13 TORQUE the eight nuts (7) to between 0.8 and 0.6 m.daN (70.80 and 53.10 lbf.in ) T.
       14 TORQUE the four nuts (13) on the link assemblies (11), (12), (16) and (17) to between 1.2 and 1 m.daN (106.19 and 88.50 lbf.in ) T. The link threads must block the safety holes in the link assemblies. This can be checked with a piece of lockwire (Material No.V02-126) .
Alternate: Use safety cable (Material No.V02-282) , safety cable (Material No.V02-283) , safety cable (Material No.V02-283A) , safety cable (Material No.V02-284) , safety cable (Material No.V02-285) , safety cable (Material No.V02-286) , safety cable (Material No.V02-287) ,
safety cable (Material No.V02-288) , safety cable (Material No.V02-289) or safety cable (Material No.V02-290) .
Put the lockwire or safety cable into each safety hole. The lockwire or safety cable 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.
F Power Plant, Right Side ** ON A/C NOT FOR ALL
     (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).
F Forward Junction Box ** ON A/C NOT FOR ALL
     (f) On the pylon junction box, connect the electrical connectors 401VC, 403VC, 407VC and 409VC (Ref. AMM TASK 70-23-15-912-010).
F Forward Junction Box ** ON A/C NOT FOR ALL
     (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 ESPM 2048230.
         b The minimum extraction force value must be 2.8 daN (6.3 lbf) for a new FRAMATOME (former SOURIAU) contact and 2.2 daN (4.9 lbf) for an old FRAMATOME (former SOURIAU) contact ESPM 2048240.
       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).
F Forward Junction Box ** ON A/C NOT FOR ALL
     (h) On the aft interface junction box, connect the electrical connectors 450VC, 452VC and 454VC.
F Left Interface Junction Box ** ON A/C NOT FOR ALL
     (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.
F TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL
TORQUE the union to between 1.7 and 1.5 m.daN (12.54 and 11.06 lbf.ft ) T (Ref. AMM TASK 70-23-11-911-013).
     (j) Manually move the hydraulic-reservoir pressurization tube and make sure that there is a minimum clearance of approximately 25.4 mm (1.0000 in.) between the hydraulic- reservoir pressurization tube and the adjacent pipes.
F TAI Location and Hydraulic Reservoir Pressurization Tube Location ** ON A/C NOT FOR ALL
       1 If the clearance is not correct, do the adjustment again.
     (k) Install the drains mast (Ref. AMM TASK 71-71-42-400-010).
Subtask 71-00-20-410-066-B ** ON A/C NOT FOR ALL
C. If the engine fire seals are not present, install them as follows:
F Inspection for the Thrust Reverser Brackets and Inspection for/Installation of the Engine Fire Seals ** ON A/C NOT FOR ALL
F Fire Seal Installation ** ON A/C NOT FOR ALL
   (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 AIPC 71-51-46-80-030 seal assembly (15) or AIPC 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 No. 21 drill.
   (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 AIPC 71-51-46-80-030 seal assembly (15) and AIPC 71-51-46-80-020 seal assembly (16) on the fire shield with AIPC 71-51-46-80-010 screws (17).
     (b) TORQUE the screws (17) to between 8 and 6 lbf.in (0.09 and 0.07 m.daN ) T.
   (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 71-00-20-820-056-A ** ON A/C NOT FOR ALL
D. 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).
NOTE: Make sure that the gearbox breather outlet duct (GBOD) aligns with the gearbox breather outlet 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 71-00-20-410-067-A ** ON A/C NOT FOR ALL
E. 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 71-00-20-440-054-A ** ON A/C NOT FOR ALL
F. Activate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-440-012).
F Hydraulic Control Unit ** ON A/C NOT FOR ALL
Subtask 71-00-20-611-055-A ** ON A/C NOT FOR ALL
G. 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 71-00-20-612-052-A ** ON A/C NOT FOR ALL
H. 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 71-00-20-863-055-A ** ON A/C NOT FOR ALL
I. 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 PRESSURIZED. 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 71-00-20-410-068-A ** ON A/C NOT FOR ALL
J. 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 71-00-20-865-062-A ** ON A/C NOT FOR ALL
K. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUENGINE/1 AND 2/IGN/SYS A1JHA03
49VUANTI ICE/PROBES/AOA/14DA1D04
49VUANTI ICE/PROBES/PHC/12DA1D03
49VUANTI ICE/PROBES/PITOT/13DA1D02
49VUANTI ICE/RAIN/RPLNT/CAPT1DB1D01
49VUCOM/CVR/SPLY2RKE14
49VUCOM/CVR/CTL4RKE13
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/PHC/32DA3Y16
122VUANTI ICE/PROBES/2/TAT1DA2Y15
122VUANTI ICE/PROBES/2/PITOT3DA2Y14
122VUANTI ICE/PROBES/2/AOA4DA2Y13
122VUANTI ICE/PROBES/PHC/22DA2Y12
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
FOR FIN: 1000EM1 (ENGINE1)
49VUENGINE/1/FIRE DET/LOOP A7WD1A06
49VUENGINE/1/FADEC A/AND EIU 12KS1A04
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)
49VUENGINE/2/FIRE DET/LOOP B8WD2A07
49VUENGINE/2/FADEC A/AND EIU 22KS2A05
121VUHYDRAULIC/HYD POWER/Y3803GXN30
121VUENGINE/IGN/ENG2/SYS B3JH2P42
121VUENGINE/IGN/ENG2/SYS A BAT2JH2P40
121VUENGINE/ENG2/FADEC B/AND EIU 24KS2Q40
121VUENGINE/ENG2/FIRE DET/LOOP A7WD2Q39
122VUELEC/GCU/22XU2T27
122VUANTI ICE/ENG/21DN2W10
123VUY HYD/ELEC/PUMP3802GXAB06
123VUY HYD/ELEC/ELEC PUMP/NORM3801GXAB03
Subtask 71-00-20-861-054-A ** ON A/C NOT FOR ALL
L. Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
Subtask 71-00-20-740-055-A ** ON A/C NOT FOR ALL
M. Update the engine hours and cycles (Ref. AMM TASK 31-36-00-740-005) or (Ref. AMM D/O 31-36-00-74).
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 71-00-20-860-064-A ** ON A/C NOT FOR ALL
N. Do the EIS start procedure (Ref. AMM TASK 31-60-00-860-001).
Subtask 71-00-20-720-056-A ** ON A/C NOT FOR ALL
O. 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
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 select key adjacent to the RETURN indication until the CFDS menu page comes into view.
   (7) Stop the MCDU.
Subtask 71-00-20-710-068-A ** ON A/C NOT FOR ALL
P. 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 71-00-20-710-069-A ** ON A/C NOT FOR ALL
Q. Do the operational test of the Starter valve and FMU (Ref. AMM TASK 80-13-51-710-040).
Subtask 71-00-20-710-070-A ** ON A/C NOT FOR ALL
R. 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 a dry motor leak check (Ref. AMM TASK 71-00-00-710-045) and do an operational test of the hydraulic pump:
   (4) FOR [1000EM1] (ENGINE-1)
   (5) FOR [1000EM2] (ENGINE-2)
Subtask 71-00-20-790-052-A ** ON A/C NOT FOR ALL
S. 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 71-00-20-210-068-A ** ON A/C NOT FOR ALL
T. Do a check of the IDG system as follows:
   (1) On the lower ECAM DU, get the ELEC page.
   (2) Make sure that the frequency and voltage indications are correct with engine running.
Subtask 71-00-20-720-057-A ** ON A/C NOT FOR ALL
U. 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 71-00-20-710-071-A ** ON A/C NOT FOR ALL
V. 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 71-00-20-860-065-A ** ON A/C NOT FOR ALL
W. Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
Subtask 71-00-20-862-054-A ** ON A/C NOT FOR ALL
X. Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
Subtask 71-00-20-869-060-A ** ON A/C NOT FOR ALL
Y. 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.8 from Aug 2017] 2026.04.01 02:28:37 UTC
"Aviabrain" 2025