W DOC AIRBUS | AMM A320F

Inspection after Aircraft Operation with High Lateral Acceleration

TASK 05-51-44-200-001-A
Inspection after Aircraft Operation with High Lateral Acceleration

1. Reason for the Job
To do an inspection of the aircraft for structural damage after a flight during which high lateral accelerations occurred.
NOTE: Typical examples of conditions that can cause high lateral loads:
  • Large movements in yaw and/or roll
  • Heavy turbulence
  • System failures such as rudder trim runaway with crew take-over.
NOTE: If the crew made a report about high lateral acceleration (higher than 0.42g) on the ground (landing, taxiing, etc.), do a hard landing inspection, refer to AMM 05-51-11-200-004.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
1
ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE
No specific
AR
CHOCK - WHEEL(S)
No specific
AR
SAFETY BARRIER(S)
No specific
AR
WARNING NOTICE(S)
 B. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
312AR, 321AL, 322AL, 322CL, 323AL, 323AR, 325AL, 325AR
471AL, 471CL, 482AR, 482CR
 C. Referenced Information
REFERENCE
DESIGNATION
TASK 05-51-17-200-001-A
Inspection after In-flight Excessive Load Factor due to Turbulence or Maneuver or in Excess of VMO/MMO
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 24-41-00-862-002-A
De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01
De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02
De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 25-11-00-200-001-A
Inspection/Check of the Cockpit Seats
TASK 25-21-00-210-001-A
Detailed Inspection of Seat Attachments, Seat Structure, Seat Belts, Buckles and Baggage Bar
TASK 25-22-00-210-001-A
Detailed Inspection of Cabin Attendant Seat Attachments, Seat Structure and Seat Belt (Including Seat Belt Attachments and Buckles)
TASK 25-50-00-200-002-A
Visual Check of Cargo Compartment Decompression, Lining, Floor Panels and Pressure Compensation Valve (as far as Visible, if ACT(s) or Sliding Carpet System Installed)
TASK 27-24-00-710-001-A
Operational Test of the Rudder Hydraulic Actuation
TASK 29-00-00-864-001-A
Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action
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 29-10-00-863-003-A
Pressurize the Blue Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-003-A-01
Pressurize the Blue Hydraulic System with the Blue Electric Pump
TASK 29-10-00-864-001-A
Depressurize the Green Hydraulic System
TASK 29-10-00-864-002-A
Depressurize the Yellow Hydraulic System
TASK 29-10-00-864-003-A
Depressurize the Blue Hydraulic System
TASK 31-37-00-200-001-A
Check of the Load-Report Parameter after Hard/Overweight Landing or Excessive Turbulence
TASK 35-23-00-710-001-A
Operational Check of Manual Mask Release
TASK 53-45-11-000-001-A
Removal of the Dorsal Fin
TASK 53-45-11-400-001-A
Installation of the Dorsal Fin
TASK 53-51-00-210-012-A
Detailed Inspection of Fin to Fuselage, Forward, MID and AFT Attach Fittings, Outside Fuselage, LH/RH
TASK 53-51-00-210-018-A
General Visual Inspection of Fuselage External Surface and Vertical Stabilizer Attachment Fitting, underneath Vertical Stabilizer/Fuselage Fairings
TASK 53-51-00-210-020-A
General Visual Inspection of the Rear Fuselage Internal Structure, between FR70 and FR77
TASK 53-55-11-000-001-A
Removal of the Vertical Stabilizer Fairings
TASK 53-55-11-400-001-A
Installation of the Vertical Stabilizer Fairings
TASK 53-55-12-000-001-A
Removal of the Rudder Fairings
TASK 53-55-12-400-001-A
Installation of the Rudder Fairings
TASK 54-51-17-000-001-A
Removal of the Pylon-to-Wing Forward Attach-Fitting at RIB4
TASK 54-51-17-000-002-A
Removal of the Pylon-to-Wing Aft Attach-Fitting at RIB10
TASK 54-51-17-000-804-A
Removal of the Pylon-to-Wing Forward Attach-Fitting at RIB5
TASK 54-51-17-000-805-A
Removal of the Pylon-to-Wing Aft Attach-Fitting at RIB10
TASK 54-51-17-200-001-A
Inspection of the Pylon-to-Wing Forward Attach-Fitting
TASK 54-51-17-200-002-A
Inspection of the Pylon-to-Wing Aft Attach-Fitting
TASK 54-51-17-200-003-A
Inspection of the Shackles at RIB4 and the Spigot
TASK 54-51-17-200-004-A
Inspection of the Shackles at RIB10
TASK 54-51-21-000-001-A
Removal of the Pylon Lateral Access-Doors
TASK 54-51-21-000-802-A
Removal of the Pylon Lateral Access-Doors
TASK 54-51-21-400-001-A
Installation of the Pylon Lateral Access-Doors
TASK 54-51-21-400-802-A
Installation of the Pylon Lateral Access-Doors
TASK 54-53-11-000-002-A
Removal of the Pylon-to-Wing Access Panels
TASK 54-53-11-000-002-B
Removal of the Pylon-to-Wing Access Panels
TASK 54-53-11-000-804-A
Removal of the Pylon-to-Wing Access Panels and Doors
TASK 54-53-11-400-002-A
Installation of the Pylon-to-Wing Access Panels
TASK 54-53-11-400-002-B
Installation of the Pylon-to-Wing Access Panels
TASK 54-53-11-400-804-A
Installation of the Pylon-to-Wing Access Panels and Doors
TASK 55-30-00-210-001-A
Detailed Inspection of Rudder Hinge Arm 1, 2, 3, 4 and 5 and Fin Actuator Fittings (Actuator 1, 2 and 3)
TASK 55-30-00-210-002-A
Detailed Inspection of Rudder Hinge Arm 6 and 7
TASK 55-32-11-000-001-A
Removal of the Vertical Stabilizer Leading-Edge
TASK 55-32-11-400-001-A
Installation of the Vertical Stabilizer Leading-Edge
TASK 55-33-13-010-002-A
Opening/Removal of the Trailing Edge Access-Panels of the Vertical Stabilizer
TASK 55-33-13-410-002-A
Closing/Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer
TASK 55-36-00-210-001-A
Detailed Inspection of Vertical Stabilizer, Attach Fittings, Including Load Introduction Area at Skin Panels
TASK 55-40-00-210-004-A
Detailed Inspection of Rudder Attach Fitting 1, 2, 3, 4 and 5 and Rudder Actuator Attach Fittings (Actuator 1, 2 and 3)
TASK 55-40-00-210-005-A
Detailed Inspection of Rudder Attach Fitting 6 and 7
TASK 57-31-23-000-801-A
Removal of the Sharklet
TASK 71-00-00-000-040-A
Removal of the Power Plant
TASK 71-00-00-000-040-A-01
Removal of the Power Plant with the Engine Positioner TWW 75E
TASK 71-00-00-000-040-A-03
Removal of the Power Plant with Jacxson Tool
TASK 71-00-00-000-042-A
Removal of the Power Plant
TASK 71-00-00-000-042-A-01
Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG)
TASK 71-00-00-000-042-A-03
Removal of the Power Plant with Jacxson Tool
TASK 71-00-00-710-012-B
Test No.3 : Idle Leak Check
TASK 71-00-00-710-013-C
Test No.11 : High Power Assurance Test
TASK 71-00-20-000-040-A
Removal of the Power Plant
TASK 71-00-20-000-040-A-01
Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG)
TASK 71-00-51-000-802-A
Removal of the Power Plant (Bootstrap Method)
TASK 71-00-51-000-802-A-01
Removal of the Power Plant (JacXson Method)
TASK 71-13-00-010-010-A
Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-010-040-A
Opening of the Fan Cowl Doors
TASK 71-13-00-010-040-B
Opening of the Fan Cowl Doors
TASK 71-13-00-010-802-A
Opening of the Fan Cowl Doors
TASK 71-13-00-410-010-A
Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-410-040-A
Closing of the Fan Cowl Doors
TASK 71-13-00-410-040-B
Closing of the Fan Cowl Doors
TASK 71-13-00-410-802-A
Closing of the Fan Cowl Doors
TASK 71-21-11-210-040-A
Detailed Inspection of Forward Engine Mount Installation
TASK 71-21-11-210-040-B
Detailed Inspection of the Forward Engine Mount
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 71-22-11-210-042-A
Detailed Inspection of Aft Engine Mount Installation
TASK 71-22-11-210-042-B
Detailed Inspection of Aft Engine Mount Installation
TASK 72-00-00-200-012-A
Borescope Inspection of the Low Pressure (LP) Turbine
TASK 72-00-00-200-013-B
Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes
TASK 72-00-00-200-014-B
Borescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments
TASK 72-00-00-200-014-B-01
Borescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments
TASK 72-00-00-200-015-B
Borescope Inspection of the Stage 2 High Pressure Turbine (HPT) Blades and Duct Segments
TASK 72-00-00-200-016-B
Inspection of the HP Compressor
TASK 72-00-00-200-016-B-01
Inspection of the HP Compressor
TASK 72-00-00-200-017-B
Inspection of the LP Compressor
TASK 72-00-00-200-812-A
Inspection of the Engine after Exposure to Excessive Turbulence, High Aircraft Lateral Loads or Heavy or Overweight Landings
TASK 72-21-00-290-001-A
Standard Borescope Inspection of Booster Rotor Blades, Stages 2, 3 and 4 through the Booster Inlet and Borescope Port SO
TASK 72-21-00-290-003-A
Borescope Inspection of the Booster Rotor Blades, Stages 2, 3, 4 and 5 through the Booster Inlet and Borescope Ports SO3 and SO5
TASK 72-23-00-210-001-A
Visual Inspection of the Fan Frame Assembly
TASK 72-23-00-210-003-A
Detailed Inspection of Spinner, Engine Inlet, Fan Blades, Fan Outlet and Abradable Material
TASK 72-23-00-210-003-C
Detailed Inspection of Spinner, Engine Inlet, Fan Blades, Fan Outlet and Abradable Material
TASK 72-23-00-210-004-A
Visual Inspection of the Fan Frame Assembly
TASK 72-31-00-290-001-A
Inspection of the High Pressure Compressor Rotor Assembly
TASK 72-31-00-290-002-A
Inspection of the High Pressure Compressor Rotor Assembly
TASK 72-56-00-210-001-A
Inspection/Check of the Turbine Frame Assembly
TASK 72-56-00-210-002-A
Inspection/Check of the Turbine Frame Assembly
TASK 78-31-00-710-040-A
Operational Test of the Thrust Reverser System
TASK 78-31-00-710-040-A-01
Operational Test of the Thrust Reverser without CFDS - Engine not Running
TASK 78-31-00-710-040-A-02
Operational Test of the Thrust Reverser without CFDS - Engine Running
TASK 78-31-00-710-041-A
Operational Test of the Thrust Reverser System with the CFDS
TASK 78-31-00-710-041-A-02
Operational test of the Thrust Reverser without the CFDS and Engine Running
TASK 78-31-00-710-042-A
Operational Test of the Thrust Reverser System
TASK 78-31-00-710-805-A
Operational Test of Thrust Reverser with MCDU
TASK 78-31-00-710-805-A-01
Thrust Reverser Cycling Test (Engine Running)
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 78-32-00-860-010-A
Manual Extension of the Thrust Reverser Translating Sleeves
TASK 78-32-00-860-011-A
Manual Retraction of the Thrust Reverser Translating Sleeves
TASK 78-32-00-860-802-A
Manual Extension of the Thrust-Reverser Translating Sleeves
TASK 78-32-00-860-803-A
Manual Retraction of the Thrust-Reverser Translating Sleeves
TASK 78-32-41-860-001-A
Manual Deployment of the Blocker Door
TASK 78-32-41-860-002-A
Manual Stowing of the Blocker Door
TASK 78-32-41-860-040-A
Manual Deployment of the Blocker Door
TASK 78-32-41-860-041-A
Manual Stowing of the Blocker Door
TASK 78-36-00-010-040-A
Opening of the Thrust Reverser Doors
TASK 78-36-00-010-040-B
Opening of the Thrust Reverser Doors
TASK 78-36-00-010-802-A
Opening of the Thrust Reverser Cowl-Doors
TASK 78-36-00-410-040-A
Closing of the Thrust Reverser Doors
TASK 78-36-00-410-040-B
Closing of the Thrust Reverser Doors
TASK 78-36-00-410-802-A
Closing of the Thrust Reverser Cowl-Doors
TASK 79-00-00-200-010-A
Inspection of the Oil System
TASK 79-00-00-281-002-A
Check of the Electrical Master Chip Detector (EMCD) for Particles
TASK 79-21-10-210-002-A
Check of the Lubrication Unit Magnetic Plugs and Scavenge Screens
F Inspection Areas of the Vertical Tail Plane (VTP)
F Rudder and Actuator Attach-Fittings
F Primary Structure ** ON A/C NOT FOR ALL
F Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
F Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
F Primary Structure ** ON A/C NOT FOR ALL
F Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
F Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
F Primary Structure ** ON A/C NOT FOR ALL
F Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
F Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
F Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL
F Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL
F Exhaust Nozzle: Engine Interface ** ON A/C NOT FOR ALL
F Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL
F Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL
F Common Nozzle Assembly: Engine Interface ** ON A/C NOT FOR ALL
F Inspection of the Nacelle ** ON A/C NOT FOR ALL
F Inspection of the V-blade ** ON A/C NOT FOR ALL
3. Job Set-up
Subtask 05-51-44-210-050-A ** ON A/C NOT FOR ALL
A. Inspection Requirements
   (1) If high vertical accelerations are more than the limits during turbulence, there can be an automatic load report 15. If this occurs, you must do a check for lateral accelerations recorded in the load report 15.
But there will not be a load report 15 after high lateral accelerations if:
  • The loads are only lateral (without vertical loads) or
  • The vertical accelerations that occur during the turbulence are below the limits.
NOTE: There will not be a load report 15 because of high lateral accelerations only.

If there was a flight crew report about in-flight high lateral-loads or a load report 15 for high vertical acceleration:
  • Do an analysis of the flight parameters with the Digital Flight Data Recorder (DFDR) or the Quick Access Recorder (QAR) (if installed),
   (2) Do this inspection, if the value of the in-flight lateral acceleration was more than plus or minus 0.35g.
It is necessary to get the lateral acceleration data from:
  • The DFDR or
  • The QAR (if installed).
NOTE: The plus or minus sign of the lateral acceleration is not important. It is the absolute value (magnitude) of the lateral acceleration that is important.
   (3) Requirements if an inspection is necessary:
     (a) If the value of the in-flight lateral acceleration is between 0.35g and 0.41g:
  • Do the inspection given in Para. 4.A of this procedure,
  • Send the DFDR report (or equivalent) for the section of the flight during which the event occurred to AIRBUS for analysis.
NOTE: Until the results of the AIRBUS analysis are available and on the condition that no damage is found during the visual inspection given in Para. 4.A, the aircraft can return-to-service for a period of 30 days/200 flight cycles maximum (whichever occurs first). AIRBUS will make an analysis of the event for final clearance or more instructions.
     (b) If the value of the in-flight lateral acceleration is equal to or more than 0.41g:
  • Return-to-service of the aircraft is not permitted.
  • Do the inspection given in Para. 4. of this procedure.
  • Send the DFDR report (or equivalent) for the section of the flight during which the event occurred to AIRBUS for analysis.
  • Get detailed instructions from AIRBUS for preparation of the aircraft.
  • AIRBUS will make an analysis of the event to see if the return-to-service of the aircraft is possible.
   (4) If the Digital Flight Data Recording System (DFDRS) report or QAR report (if installed) shows high vertical acceleration:
NOTE: If excessive turbulence caused the high lateral loads, it is possible that there were also high vertical loads.
   (5) Inspection preparation
NOTE: All inspections are visual unless specified differently in the text. Operators can refer to the Non-destructive Testing Manual (NTM) and use Non-Destructive Test (NDT) procedures.
Subtask 05-51-44-210-050-B ** ON A/C NOT FOR ALL
A. Inspection Requirements
   (1) After a crew report of a high lateral event experienced in flight or after the generation of load report 15 (trigger code 5600 or 5700) you must confirm the effect parameters to know the severity of the high lateral event.
  • Do an analysis of the flight parameters with the Digital Flight Data Recorder (DFDR) or the Quick Access Recorder (QAR) (if installed),
   (2) Do this inspection, if the lateral acceleration was more than plus or minus 0.35g (If available, load report 15 shows trigger codes 5600 or 5700).
It is necessary to get the lateral acceleration data from:
  • Load report 15 or
  • The DFDR or
  • The QAR (if installed).
NOTE: The plus or minus sign of the lateral acceleration is not important. It is the absolute value (magnitude) of the lateral acceleration that is important.
   (3) Requirements if an inspection is necessary:
     (a) If the value of the in-flight lateral acceleration is between 0.35g and 0.41g (If available, load report 15 shows trigger code 5600):
  • Do the inspection given in Para. 4.A of this procedure.
  • Send the DFDR report (or equivalent) for the section of the flight during which the event occurred to AIRBUS for analysis.
NOTE: Until the results of the AIRBUS analysis are available and on the condition that no damage is found during the visual inspection given in Para. 4.A, the aircraft can return-to-service for a period of 30 days/200 flight cycles maximum (whichever occurs first). AIRBUS will make an analysis of the event for final clearance or more instructions.
     (b) If the value of the in-flight lateral acceleration is equal to or more than 0.41g (If available, load report 15 shows trigger code 5700):
  • Return-to-service of the aircraft is not permitted.
  • Do the inspection given in Para. 4. of this procedure.
  • Send the DFDR report (or equivalent) for the section of the flight during which the event occurred to AIRBUS for analysis.
  • Contact Airbus for detailed instructions to prepare the aircraft.
  • AIRBUS will make an analysis of the event to see if the return-to-service of the aircraft is possible.
   (4) If the Digital Flight Data Recording System (DFDRS) report or QAR report (if installed) shows high vertical acceleration:
NOTE: If excessive turbulence caused the high lateral loads, it is possible that there were also high vertical loads.
   (5) Load report 15 available without pilot report:
     (a) If the flight crew confirms that the flight was without excessive turbulence:
  • Make an analysis of the load report to know if load report 15 is a correct report or a spurious (unjustified) report (Ref. AMM TASK 31-37-00-200-001).
       1 If the analysis confirms that load report 15 is a spurious (unjustified) report, discard it.
NOTE: No inspection is necessary.
       2 If the analysis does not confirm that load report 15 is a spurious (unjustified) report:
  • Do the inspections or
  • Do a check of the DFDR data to confirm the values in the report.
   (6) Inspection preparation
NOTE: All inspections are visual unless specified differently in the text. Operators can refer to the Non-destructive Testing Manual (NTM) and use Non-Destructive Test (NDT) procedures.
Subtask 05-51-44-210-050-F
A. Inspection Requirements
   (1) If high vertical accelerations are more than the limits during turbulence, there can be an automatic load report 15. If this occurs, you must do a check for lateral accelerations recorded in the load report 15.
But there will not be a load report 15 after high lateral accelerations if:
  • The loads are only lateral (without vertical loads) or
  • The vertical accelerations that occur during the turbulence are below the limits.
NOTE: There will not be a load report 15 because of high lateral accelerations only.

If there was a flight crew report about in-flight high lateral-loads or a load report 15 for high vertical acceleration:
  • Do an analysis of the flight parameters with the Digital Flight Data Recorder (DFDR) or the Quick Access Recorder (QAR) (if installed),
   (2) Do this inspection, if the value of the in-flight lateral acceleration was more than plus or minus 0.35g.
It is necessary to get the lateral acceleration data from:
  • The DFDR or
  • The QAR (if installed).
NOTE: The plus or minus sign of the lateral acceleration is not important. It is the absolute value (magnitude) of the lateral acceleration that is important.
   (3) Requirements if an inspection is necessary:
     (a) If the value of the in-flight lateral acceleration is between 0.35g and 0.41g:
  • Do the inspection given in Para. 4.A of this procedure,
  • Send the DFDR report (or equivalent) for the section of the flight during which the event occurred to AIRBUS for analysis.
NOTE: Until the results of the AIRBUS analysis are available and on the condition that no damage is found during the visual inspection given in Para. 4.A, the aircraft can return-to-service for a period of 30 days/200 flight cycles maximum (whichever occurs first). AIRBUS will make an analysis of the event for final clearance or more instructions.
     (b) If the value of the in-flight lateral acceleration is equal to or more than 0.41g:
  • Return-to-service of the aircraft is not permitted.
  • Do the inspection given in Para. 4. of this procedure.
  • Send the DFDR report (or equivalent) for the section of the flight during which the event occurred to AIRBUS for analysis.
  • Get detailed instructions from AIRBUS for preparation of the aircraft.
  • AIRBUS will make an analysis of the event to see if the return-to-service of the aircraft is possible.
   (4) If the Digital Flight Data Recording System (DFDRS) report or QAR report (if installed) shows high vertical acceleration:
NOTE: If excessive turbulence caused the high lateral loads, it is possible that there were also high vertical loads.
   (5) Inspection preparation
NOTE: All inspections are visual unless specified differently in the text. Operators can refer to the Non-destructive Testing Manual (NTM) and use Non-Destructive Test (NDT) procedures.
Subtask 05-51-44-941-050-A
B. Safety Precautions
   (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
   (2) Put the CHOCK - WHEEL(S) in position at the main landing gear.
   (3) Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to operate the systems.
Subtask 05-51-44-010-050-A
C. Get Access
   (1) Put the WARNING NOTICE(S) in position to tell persons not to operate the flight controls.
   (2) Put the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE in position.
   (3) Open access door 312AR.
   (4) Remove vertical stabilizer fairings 323AL and 323AR (Ref. AMM TASK 53-55-11-000-001).
   (5) Remove dorsal fin 321AL (Ref. AMM TASK 53-45-11-000-001).
   (6) Remove rudder fairings 325AL and 325AR (Ref. AMM TASK 53-55-12-000-001).
   (7) Remove leading-edge access panels 322AL and 322CL of the vertical stabilizer (Ref. AMM TASK 55-32-11-000-001).
   (8) Open the trailing-edge access panels of the vertical stabilizer (Ref. AMM TASK 55-33-13-010-002).
Subtask 05-51-44-860-050-A
D. Aircraft Maintenance Configuration
   (1) Make sure that the hydraulic systems are depressurized and put them in the maintenance configuration
(Ref. AMM TASK 29-00-00-864-001).
   (2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
4. Procedure
Subtask 05-51-44-210-051-A
A. Inspection of the Rear Fuselage and the Vertical Tail Plane (VTP)
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.

Inspection of the tail area.





A.

Do a detailed visual inspection (DVI)
for distortion, cracks, damaged
paintwork or sealant and loose or
pulled fasteners on the external
surface of the rear fuselage:
F Inspection Areas of the Vertical Tail Plane (VTP)







(1) The external surface below the
fin-to-fuselage fairings
(Ref. AMM TASK 53-51-00-210-018)
X






(2) The fin-to-fuselage FWD, MID, and
AFT attach lugs
(Ref. AMM TASK 53-51-00-210-012)
X






(3) The transverse load rod attachments
(Ref. AMM TASK 53-51-00-210-012).
X




B.

Do a detailed visual inspection (DVI)
for distortion, cracks, damaged
paintwork or sealant and loose or
pulled fasteners on the internal
surface of the rear fuselage at
Zone 310:







(1) Between FR70 and FR74 above
stringers 19LH and 19RH
(Ref. AMM TASK 53-51-00-210-020)
X






(2) All areas of FR77
(Ref. AMM TASK 53-51-00-210-020).
X




C.

Do a detailed visual inspection (DVI)
for distortion, cracks, damaged
paintwork or sealant and loose or
pulled fasteners on the vertical tail
plane (VTP):
F Inspection Areas of the Vertical Tail Plane (VTP)







(1) The attach-fitting areas
(this includes the load introduction
area at the skin panels)
(Ref. AMM TASK 55-36-00-210-001)
X






(2) The RIB1 lower surface
X






(3) The RIB2 upper and lower surfaces,
from the inspection holes at the VTP
front and rear spars
X






(4) Rudder hinge arms 1 to 7
(Ref. AMM TASK 55-30-00-210-001)
(Ref. AMM TASK 55-30-00-210-002)
X






(5) Actuator attach-fittings 1 to 3
(Ref. AMM TASK 55-30-00-210-001)
X






(6) The external surface of the front
spar between RIB1 and RIB2
X






(7) The external surface of the front
spar between RIB10 and RIB11
X






(8) The external surface of the rear
spar between RIB1 and RIB11.
X




D.

Do a detailed visual inspection (DVI)
for distortion, cracks, damaged
paintwork or sealant and loose or
pulled fasteners on the rudder:
F Rudder and Actuator Attach-Fittings







(1) Rudder attach-fittings 1 to 7
(Ref. AMM TASK 55-40-00-210-004)
(Ref. AMM TASK 55-40-00-210-005)
X






(2) Actuator attach-fittings 1 to 3
(Ref. AMM TASK 55-40-00-210-004).
X




Subtask 05-51-44-210-058-B ** ON A/C NOT FOR ALL
B. Inspection of the Pylons
F Primary Structure ** ON A/C NOT FOR ALL
F Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
F Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.

Inspection of the Pylons





A.

Externally examine the pylon secondary
structure and the pylon primary
structure (lateral panels).
Make sure that:
- There is/are no buckling, shearing,
distortion or cracks
- The paint is in the correct condition
- There are no pulled or missing
fasteners/rivets.
X






If you find damage:







(a) On the secondary structure, remove
the access panels and doors from the
damaged area to see the internal
damage.

X





(b) On the primary structure, remove
the access doors (Ref. AMM TASK 54-51-21-000-001).

X





(c) Internally examine the pylon
secondary structure and the pylon
primary structure (all the items that
you can see) for distortion, buckling,
cracks, defective attachment, missing
fasteners or other damage.
This includes:
- The lower and upper spars
- The ribs
- The lateral panels
- The fire protection system (specially
the attachments of the fire
extinguishing bottles)
- The electrical cables
- Failure on pipes and ducts
- Leaks in the drain pipes
- The hydraulic and fuel pipes
- The bleed-air system components.

X





If you find damage:







- Contact Airbus.


X




(d) Install the access doors on the
primary structure (Ref. AMM TASK 54-51-21-400-001).

X





(e) Install the access panels and doors
on the secondary structure.

X



B.

Open the fan and thrust-reverser cowl
doors
(Ref. AMM TASK 71-13-00-010-040) and
(Ref. AMM TASK 78-36-00-010-040).
X






(1) Externally examine the lower spar,
the pylon lower area (all the items
that you can see) and the cantilever
structure, the fan cowl fittings and
the thrust reverser fittings.
Make sure that:
- There is/are no buckling, shearing,
distortion or cracks
- The paint is in the correct condition
- There are no pulled or missing
fasteners/rivets.
X






If you find damage:







(a) On the secondary structure, remove
the access panels and doors from the
damaged area to see the internal
damage.

X





(b) On the primary structure, remove
the access doors (Ref. AMM TASK 54-51-21-000-001).

X





(c) Internally examine the pylon
secondary structure and the pylon
primary structure (all the items that
you can see) for distortion, buckling,
cracks, defective attachment, missing
fasteners or other damage.
This includes:
- The lower and upper spars
- The ribs
- The lateral panels
- The fire protection system (specially
the attachments of the fire
extinguishing bottles)
- The electrical cables
- Failure on pipes and ducts
- Leaks in the drain pipes
- The hydraulic and fuel pipes
- The bleed-air system components.

X





If you find damage:







- Contact Airbus.


X




(d) Install the access doors on the
primary structure (Ref. AMM TASK 54-51-21-400-001).

X





(e) Install the access panels and doors
on the secondary structure.

X



C.

Remove the center fillets from the
pylon-to-wing junction (Ref. AMM TASK 54-53-11-000-002).
NOTE: This is only applicable for the
left and right side panels between RIB4
and RIB5 and at RIB10. This is to make
sure that you can see the pylon-to-wing
attach fittings and the spigot ball
joint.
X






(1) Do a detailed visual inspection of:
- The pylon-to-wing forward
attach-fittings at RIB4
- The pylon-to-wing aft attach-fitting
at RIB10
- The spigot ball joint between RIB4
and RIB5.
Make sure that there are no signs of
distortion, buckling, cracks or other
damage.
X






If you find damage:







(a) Remove the pylon-to-wing attach
fittings
(Ref. AMM TASK 54-51-17-000-001) and
(Ref. AMM TASK 54-51-17-000-002).

X





(b) Do a detailed visual inspection of:
- The pylon-to-wing forward
attach-fittings at RIB4 (Ref. AMM TASK 54-51-17-200-001)
- The shackles at RIB4 and the spigot
attach fitting (Ref. AMM TASK 54-51-17-200-003)
- The shackles at RIB10 (Ref. AMM TASK 54-51-17-200-004)
- The pylon-to-wing aft attach-fitting
at RIB10 (Ref. AMM TASK 54-51-17-200-002).

X





(c) Contact Airbus.

X



D.

Do a visual inspection of the engine
mounts (all the items that you can
see) for cracks or distortion
(Ref. AMM TASK 71-21-11-210-040) and
(Ref. AMM TASK 71-22-11-210-042).
This includes the inspection of:
- The pylon-to-engine forward
attach-fitting in the forward area
of RIB1
- The pylon-to-engine aft
attach-fitting at the bottom of RIB3.
X






If you find damage:







(a) Remove the engine (Ref. AMM TASK 71-00-00-000-040).

X





(b) Contact Airbus.

X



E.

(1) Install the center fillets on the
pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002).
X






(2) Close the fan and thrust-reverser
cowl doors (Ref. AMM TASK 71-13-00-410-040) (Ref. AMM TASK 78-36-00-410-040).
X




Subtask 05-51-44-210-054-B ** ON A/C NOT FOR ALL
C. Inspection of the Nacelles
F Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL
F Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL
F Exhaust Nozzle: Engine Interface ** ON A/C NOT FOR ALL
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.







A.

Examine the nacelle external surface
cowls (inlet, fan cowl doors, thrust
reverser, nozzle) for:
- failures, cracks, signs of
buckling and permanent deformations
- unusual steps and gaps between
external cowl interfaces
- pulled, bent or loose rivets or
fasteners
- open or loose access covers, latches
or panels.
Examine the edges of the interfacing
cowl parts (leading or trailing edges,
cowl edges near the pylon or
latching areas) for signs of
abutment (paint cracks, delamination,
impacts).
X




B.

Open the fan cowl doors and examine
(Ref. Fig 602/TASK 05-51-44-991-002):
- the internal side of the doors for
cracks
- the locators
- the hinges and latch fittings for
permanent deformations.
X






If you find damage, examine:
- the fittings for cracks, failures,
damaged fasteners
- the adjacent area for composite
delamination.

X



C.

Open the thrust reverser and examine
(Ref. Fig 603/TASK 05-51-44-991-003,
604/TASK 05-51-44-991-004):
- the forward interface with the
engine:
V-Groove and J-ring for bearing,
cracks or failures
- the hinge and latch fittings for
permanent deformations
- the C-duct skins that you can see.
X






If you find damage, examine:
- the hinges and adjacent areas for
cracks or failures
- the latch fittings for cracks,
failure or damaged fasteners.

X



D

Do a manual deployment of the thrust
reverser system
(Ref. AMM TASK 78-32-41-860-040).
Examine the pivoting doors, pivoting
door hinges, actuator, lock, kicker
plate and seals. You can then
manually stow the thrust reverser
(Ref. AMM TASK 78-32-41-860-041).

X





If you find resistance or unusual
noise during the manual deployment of
the thrust reverser, then stop and
replace the damaged hardware.


X


E

If you find damage on the above parts,
examine:
- the engine and exhaust nozzle
interface for damaged fasteners
(Ref. Fig 605/TASK 05-51-44-991-005)
- the common Nozzle Assembly and
thrust reverser interface for
bearing, cracks or failures
- the inlet cowl rear bulkhead and
engine interface.
(Ref. Fig 601/TASK 05-51-44-991-001)

X



F

Do an operational test of the thrust
reverser system. Make sure that the
thrust reversers can move fully and
freely (Ref. AMM TASK 78-31-00-710-040).
X




Subtask 05-51-44-210-053-B ** ON A/C NOT FOR ALL
D. Inspection of the Engine
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.

Examine the Engine





A.

Turn the fan rotor with your hand.
Make sure that there is no bearing
roughness, unusual noises and
bindings.
X




B.

Visual inspection of the abradable
material of the fan inlet case: make
sure that there are no unusual wear
of the abradable material
(Ref. AMM TASK 72-23-00-210-003).
X




C.

Visual inspection of the fan frame
assembly (Ref. AMM TASK 72-23-00-210-001).
X




D.

Visual inspection of the turbine frame
assembly (Ref. AMM TASK 72-56-00-210-001).
X




E.

Visual inspection of the accessory and
hardware attachments for metal
fractures or excessive distortion.
X




F.

Visual inspection of piping
connections for leaks.
X




G.

Visual inspection of lines and tubing
for possible interferences.
If you find damage:
X






(1) Do a borescope inspection of the
HPC blades
(Ref. AMM TASK 72-31-00-290-001).

X





Note: If you do this task, engine
removal can be necessary.


X




(2) Do a borescope inspection of the
LPC blades
(Ref. AMM TASK 72-21-00-290-001).

X





Note: If you do this task, engine
removal can be necessary.


X




(3) Examine the lubrication unit
magnetic plugs/electrical master
chip detector for metal particles
caused by bearing damage
(Ref. AMM TASK 79-21-10-210-002).
If you do not find metal
particles, do the inspection each
day for one week, then each week
for one month.

X





Note: If you do this task, engine
removal can be necessary.


X


Subtask 05-51-44-210-058-D ** ON A/C NOT FOR ALL
E. Inspection of the Pylons
F Primary Structure ** ON A/C NOT FOR ALL
F Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
F Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.

Inspection of the Pylons





A.

Externally examine the pylon secondary
structure and the pylon primary
structure (lateral panels).
Make sure that:
- There is/are no buckling, shearing,
distortion or cracks
- The paint is in the correct condition
- There are no pulled or missing
fasteners/rivets.
X






If you find damage:







(a) On the secondary structure, remove
the access panels and doors from the
damaged area to see the internal
damage.

X





(b) On the primary structure, remove
the access doors (Ref. AMM TASK 54-51-21-000-001).

X





(c) Internally examine the pylon
secondary structure and the pylon
primary structure (all the items that
you can see) for distortion, buckling,
cracks, defective attachment, missing
fasteners or other damage.
This includes:
- The lower and upper spars
- The ribs
- The lateral panels
- The fire protection system (specially
the attachments of the fire
extinguishing bottles)
- The electrical cables
- Failure on pipes and ducts
- Leaks in the drain pipes
- The hydraulic and fuel pipes
- The bleed-air system components.

X





If you find damage:







- Contact Airbus.


X




(d) Install the access doors on the
primary structure (Ref. AMM TASK 54-51-21-400-001).

X





(e) Install the access panels and doors
on the secondary structure.

X



B.

Open the fan and thrust-reverser cowl
doors
(Ref. AMM TASK 71-13-00-010-040) and
(Ref. AMM TASK 78-36-00-010-040).
X






(1) Externally examine the lower spar,
the pylon lower area (all the items
that you can see) and the cantilever
structure, the fan cowl fittings and
the thrust reverser fittings.
Make sure that:
- There is/are no buckling, shearing,
distortion or cracks
- The paint is in the correct condition
- There are no pulled or missing
fasteners/rivets.
X






If you find damage:







(a) On the secondary structure, remove
the access panels and doors from the
damaged area to see the internal
damage.

X





(b) On the primary structure, remove
the access doors (Ref. AMM TASK 54-51-21-000-001).

X





(c) Internally examine the pylon
secondary structure and the pylon
primary structure (all the items that
you can see) for distortion, buckling,
cracks, defective attachment, missing
fasteners or other damage.
This includes:
- The lower and upper spars
- The ribs
- The lateral panels
- The fire protection system (specially
the attachments of the fire
extinguishing bottles)
- The electrical cables
- Failure on pipes and ducts
- Leaks in the drain pipes
- The hydraulic and fuel pipes
- The bleed-air system components.

X





If you find damage:







- Contact Airbus.


X




(d) Install the access doors on the
primary structure (Ref. AMM TASK 54-51-21-400-001).

X





(e) Install the access panels and doors
on the secondary structure.

X



C.

Remove the center fillets from the
pylon-to-wing junction (Ref. AMM TASK 54-53-11-000-002).
NOTE: This is only applicable for the
left and right side panels between RIB4
and RIB5 and at RIB10. This is to make
sure that you can see the pylon-to-wing
attach fittings and the spigot ball
joint.
X






(1) Do a detailed visual inspection of:
- The pylon-to-wing forward
attach-fittings at RIB4
- The pylon-to-wing aft attach-fitting
at RIB10
- The spigot ball joint between RIB4
and RIB5.
Make sure that there are no signs of
distortion, buckling, cracks or other
damage.
X






If you find damage:







(a) Remove the pylon-to-wing attach
fittings
(Ref. AMM TASK 54-51-17-000-001) and
(Ref. AMM TASK 54-51-17-000-002).

X





(b) Do a detailed visual inspection of:
- The pylon-to-wing forward
attach-fittings at RIB4 (Ref. AMM TASK 54-51-17-200-001)
- The shackles at RIB4 and the spigot
attach fitting (Ref. AMM TASK 54-51-17-200-003)
- The shackles at RIB10 (Ref. AMM TASK 54-51-17-200-004)
- The pylon-to-wing aft attach-fitting
at RIB10 (Ref. AMM TASK 54-51-17-200-002).

X





(c) Contact Airbus.

X



D.

Do a visual inspection of the engine
mounts (all the items that you can
see) for cracks or distortion
(Ref. AMM TASK 71-21-11-210-040) and
(Ref. AMM TASK 71-22-11-210-042).
This includes the inspection of:
- The pylon-to-engine forward
attach-fitting in the forward area
of RIB1
- The pylon-to-engine aft
attach-fitting at the bottom of RIB3.
X






If you find damage:







(a) Remove the engine (Ref. AMM TASK 71-00-00-000-042).

X





(b) Contact Airbus.

X



E.

(1) Install the center fillets on the
pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002).
X






(2) Close the fan and thrust-reverser
cowl doors (Ref. AMM TASK 71-13-00-410-040) (Ref. AMM TASK 78-36-00-410-040).
X




Subtask 05-51-44-210-054-D ** ON A/C NOT FOR ALL
F. Inspection of the Nacelles
F Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL
F Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL
F Exhaust Nozzle: Engine Interface ** ON A/C NOT FOR ALL
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.







A.

Examine the nacelle external surface
cowls (inlet, fan cowl doors, thrust
reverser, nozzle) for:
- failures, cracks, signs of
buckling and permanent deformations
- unusual steps and gaps between
external cowl interfaces
- pulled, bent or loose rivets or
fasteners
- open or loose access covers, latches
or panels.
Examine the edges of the interfacing
cowl parts (leading or trailing edges,
cowl edges near the pylon or
latching areas) for signs of
abutment (paint cracks, delamination,
impacts).
X




B.

Open the fan cowl doors and examine
(Ref. Fig 602/TASK 05-51-44-991-002):
- the internal side of the doors for
cracks
- the locators
- the hinges and latch fittings for
permanent deformations.
X






If you find damage, examine:
- the fittings for cracks, failures
or damaged fasteners
- the adjacent area for composite
delamination.

X



C.

Open the thrust reverser and examine
(Ref. Fig 603/TASK 05-51-44-991-003,
604/TASK 05-51-44-991-004):
- the forward interface with the
engine:
V-Groove and J-ring for bearing,
cracks or failures
- the hinge and latch fittings for
permanent deformations
- the C-duct skins that you can see.
X






If you find damage, examine:
- the hinges and adjacent areas for
cracks or failures
- the latch fittings for cracks,
failure or damaged fasteners.

X



D

Do a manual deployment of the thrust
reverser system
(Ref. AMM TASK 78-32-41-860-001).
Examine the pivoting doors, pivoting
door hinges, actuator, lock, kicker
plate and seals. You can then
manually stow the thrust reverser
(Ref. AMM TASK 78-32-41-860-002).

X





If you find resistance or unusual
noise during the manual deployment of
the thrust reverser, then stop and
replace the damaged hardware.


X


E

If you find damage on the above parts,
examine:
- the engine and exhaust nozzle
interface for damaged fasteners
(Ref. Fig 605/TASK 05-51-44-991-005)
- the common Nozzle Assembly and
thrust reverser interface for
bearing, cracks or failures
- the inlet cowl rear bulkhead and
engine interface.
(Ref. Fig 601/TASK 05-51-44-991-001)

X



F

Do an operational test of the thrust
reverser system. Make sure that the
thrust reversers can move fully and
freely (Ref. AMM TASK 78-31-00-710-042).
X




Subtask 05-51-44-210-053-D ** ON A/C NOT FOR ALL
G. Inspection of the Engine
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.

Examine the engine





A.

Turn the fan rotor with your hand.
Make sure that there is no bearing
roughness, unusual noises and
bindings.
X




B.

Visual inspection of the abradable
material of the fan inlet case: make
sure that there are no unusual wear
of the abradable material
(Ref. AMM TASK 72-23-00-210-003).
X




C.

Visual inspection of the fan frame
assembly (Ref. AMM TASK 72-23-00-210-004).
X




D.

Visual inspection of the turbine frame
assembly (Ref. AMM TASK 72-56-00-210-002).
X




E.

Visual inspection of the accessory and
hardware attachments for metal
fractures or excessive distortion.
X




F.

Visual inspection of piping
connections for leaks.
X




G.

Visual inspection of lines and tubing
for possible interferences.
If you find damage:
X






(1) Do a borescope inspection of the
HPC blades
(Ref. AMM TASK 72-31-00-290-002).

X





Note: If you do this task, engine
removal can be necessary.


X




(2) Do a borescope inspection of the
LPC blades
(Ref. AMM TASK 72-21-00-290-003).

X





Note: If you do this task, engine
removal can be necessary.


X




Examine the lubrication unit
magnetic plugs/electrical master
chip detector for metal particles
caused by bearing damage
(Ref. AMM TASK 79-00-00-281-002).
If you do not find metal
particles, do the inspection each
day for one week, then each week
for one month.

X





Note: If you do this task, engine
removal can be necessary.


X


Subtask 05-51-44-210-058-E ** ON A/C NOT FOR ALL
H. Inspection of the Pylons
F Primary Structure ** ON A/C NOT FOR ALL
F Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
F Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.

Inspection of the Pylons





A.

Externally examine the pylon secondary
structure and the pylon primary
structure (lateral panels).
Make sure that:
- There is/are no buckling, shearing,
distortion or cracks
- The paint is in the correct condition
- There are no pulled or missing
fasteners/rivets.
X






If you find damage:







(a) On the secondary structure, remove
the access panels and doors from the
damaged area to see the internal
damage.

X





(b) On the primary structure, remove
the access doors (Ref. AMM TASK 54-51-21-000-001).

X





(c) Internally examine the pylon
secondary structure and the pylon
primary structure (all the items that
you can see) for distortion, buckling,
cracks, defective attachment, missing
fasteners or other damage.
This includes:
- The lower and upper spars
- The ribs
- The lateral panels
- The fire protection system (specially
the attachments of the fire
extinguishing bottles)
- The electrical cables
- Failure on pipes and ducts
- Leaks in the drain pipes
- The hydraulic and fuel pipes
- The bleed-air system components.

X





If you find damage:







- Contact Airbus.


X




(d) Install the access doors on the
primary structure (Ref. AMM TASK 54-51-21-400-001).

X





(e) Install the access panels and doors
on the secondary structure.

X



B.

Open the fan and thrust-reverser cowl
doors
(Ref. AMM TASK 71-13-00-010-010) and
(Ref. AMM TASK 78-32-00-010-010).
X






(1) Externally examine the lower spar,
the pylon lower area (all the items
that you can see) and the cantilever
structure, the fan cowl fittings and
the thrust reverser fittings.
Make sure that:
- There is/are no buckling, shearing,
distortion or cracks
- The paint is in the correct condition
- There are no pulled or missing
fasteners/rivets.
X






If you find damage:







(a) On the secondary structure, remove
the access panels and doors from the
damaged area to see the internal
damage.

X





(b) On the primary structure, remove
the access doors (Ref. AMM TASK 54-51-21-000-001).

X





(c) Internally examine the pylon
secondary structure and the pylon
primary structure (all the items that
you can see) for distortion, buckling,
cracks, defective attachment, missing
fasteners or other damage.
This includes:
- The lower and upper spars
- The ribs
- The lateral panels
- The fire protection system (specially
the attachments of the fire
extinguishing bottles)
- The electrical cables
- Failure on pipes and ducts
- Leaks in the drain pipes
- The hydraulic and fuel pipes
- The bleed-air system components.

X





If you find damage:







- Contact Airbus.


X




(d) Install the access doors on the
primary structure (Ref. AMM TASK 54-51-21-400-001).

X





(e) Install the access panels and doors
on the secondary structure.

X



C.

Remove the center fillets from the
pylon-to-wing junction (Ref. AMM TASK 54-53-11-000-002).
NOTE: This is only applicable for the
left and right side panels between RIB4
and RIB5 and at RIB10. This is to make
sure that you can see the pylon-to-wing
attach fittings and the spigot ball
joint.
X






(1) Do a detailed visual inspection of:
- The pylon-to-wing forward
attach-fittings at RIB4
- The pylon-to-wing aft attach-fitting
at RIB10
- The spigot ball joint between RIB4
and RIB5.
Make sure that there are no signs of
distortion, buckling, cracks or other
damage.
X






If you find damage:







(a) Remove the pylon-to-wing attach
fittings
(Ref. AMM TASK 54-51-17-000-001) and
(Ref. AMM TASK 54-51-17-000-002).

X





(b) Do a detailed visual inspection of:
- The pylon-to-wing forward
attach-fittings at RIB4 (Ref. AMM TASK 54-51-17-200-001)
- The shackles at RIB4 and the spigot
attach fitting (Ref. AMM TASK 54-51-17-200-003)
- The shackles at RIB10 (Ref. AMM TASK 54-51-17-200-004)
- The pylon-to-wing aft attach-fitting
at RIB10 (Ref. AMM TASK 54-51-17-200-002).

X





(c) Contact Airbus.

X



D.

Do a visual inspection of the engine
mounts (all the items that you can
see) for cracks or distortion
(Ref. AMM TASK 71-21-12-200-010) and
(Ref. AMM TASK 71-22-11-200-010).
This includes the inspection of:
- The pylon-to-engine forward
attach-fitting in the forward area
of RIB1
- The pylon-to-engine aft
attach-fitting at the bottom of RIB4.
X






If you find damage:







(a) Remove the engine (Ref. AMM TASK 71-00-20-000-040).

X





(b) Contact Airbus.

X



E.

(1) Install the center fillets on the
pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002).
X






(2) Close the fan and thrust-reverser
cowl doors (Ref. AMM TASK 71-13-00-410-010) (Ref. AMM TASK 78-32-00-410-010).
X




Subtask 05-51-44-210-054-C ** ON A/C NOT FOR ALL
I. Inspection of the Nacelles
F Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL
F Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL
F Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL
F Common Nozzle Assembly: Engine Interface ** ON A/C NOT FOR ALL
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.







A.

Examine the nacelle external surface
cowls (inlet, fan cowl doors, thrust
reverser, nozzle) for:
- failures, cracks, signs of
buckling and permanent deformations
- unusual steps and gaps between
external cowl interfaces
- pulled, turned or loose rivets or
fasteners
- open or loose access covers, hatches
or panels.
Examine the edges of the interfacing
cowl parts (leading or trailing edges,
cowl edges near the pylon or
latching areas) for signs of
abutment (paint cracks, delamination,
impacts).
X




B.

Open the fan cowl doors and examine
(Ref. Fig 602A/TASK 05-51-44-991-002):
- the internal side of the doors for
cracks
- the locators
- the hinges and latch fittings for
permanent deformations.
X






If you find damage, examine:
- the fittings for cracks, failures
or damaged fasteners
- the adjacent area for composite
delamination.

X



C.

Open the thrust reverser and examine
(Ref. Fig 603A/TASK 05-51-44-991-003,
604A/TASK 05-51-44-991-004):
- the forward interface with the
engine:
V-Groove and J-ring for bearing,
cracks or failures
- the hinge and latch fittings for
permanent deformations
- the C-duct skins that you can see
X






If you find damage, examine:
- the hinges and adjacent areas
for cracks or failures
- the latch fittings for cracks,
failure or damaged fasteners.

X



D

Do a manual deployment of the thrust
reverser system
(Ref. AMM TASK 78-32-00-860-010).
If you find resistance or unusual
noises during the manual deployment of
the thrust reverser, then stop and
remove the thrust reverser.
If the thrust reverser is correctly
deployed, examine the blocker
doors, blocker door hinges, drag
links, cascades and translating
sleeves. You can then manually stow
the thrust reverser
(Ref. AMM TASK 78-32-00-860-011).

X



E

If you find damage on the above parts,
inspect:
- the engine and exhaust nozzle
interface for damaged fasteners
- the common Nozzle Assembly and
thrust reverser interface for
bearing, cracks or failures.
(Ref. Fig 606/TASK 05-51-44-991-006)
- the inlet cowl rear bulkhead and
engine interface.
(Ref. Fig 601/TASK 05-51-44-991-001)

X



Subtask 05-51-44-210-053-C ** ON A/C NOT FOR ALL
J. Inspection of the Engine
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.

Examine the Engine





A.

Turn the fan rotor with your hand
in the direction of normal engine
rotation. Make sure that there is no
bearing roughness, unusual noises or
bindings.
X






- Rub marks on the fan-track
attrition liner are normal. But
a new rub mark can be a sign that
the fan blade tips touched the
attrition liner during high lateral
acceleration. If you see a new rub
mark, then examine the fan blade
tips for signs of tip bluing
(overheat) or tip cracking. It can
be necessary to use a mirror to
see the reverse side of the fan blade
or to remove the blades for detailed
inspection.

X



B.

Examine the primary nozzle. Make sure
that:
- It is correctly attached to the
engine
- There is no distortion or cracks,
no loose rivets, no signs of
shearing or delamination.
X




C.

Lift the fan cowl doors and hold them
open with the hold-open rods. Examine
the nose cowl attachments to the fan
case. Make sure that there is no
distortion, delamination, cracks,
pulled or torn fasteners.
X




D.

Do a general visual inspection of the
engine:
- Lift the Thrust Reverser Halves.
Look at the engine fan case and core
engine zones. Look for fluid leaks,
distorted or broken linkages, brackets
or fasteners and for unusual
component positions and/or
orientations.
- Look in the exhaust at the LP
turbine blades and seals. Rubbing of
the seals and blade shrouds is normal.
But heavy rubbing between the shrouds
and the blade seal fins can cause:
  • The fins to be apparently flatter
  • Binding interference between the
    seals and the blade seal fins
  • Or signs of powdered or molten
    material.
These can be signs that internal
damage occurred.
X














- If you find damage:







(1) Refer to the applicable AMM
task to repair the damage and leaks
that you can see.

X





(2) Do a borescope inspection of the
LPC, HPC, Combustor, HPT and LPT
as per AMM
(Ref. AMM TASK 72-00-00-200-017)
(Ref. AMM TASK 72-00-00-200-016),
(Ref. AMM TASK 72-00-00-200-013),
(Ref. AMM TASK 72-00-00-200-014),
(Ref. AMM TASK 72-00-00-200-015) and
(Ref. AMM TASK 72-00-00-200-012). You must
examine the blade tip condition
very carefully (tip curls, bends,
rubs or cracks).

X





(3) Examine the magnetic chip
detectors and the items of the
scavenge oil filter for signs of
bearing distress
(Ref. AMM TASK 79-00-00-200-010).
If you do not find signs of
bearing distress, do the
inspection each day for one week,
then each week for one month.

X





(4) If you find damage that is not in
the AMM limits or if you find bearing
material, remove the engine
(Ref. AMM TASK 71-00-20-000-040).


X




(5) Do an Idle Leak Check
(Ref. AMM TASK 71-00-00-710-012).
- If you find leaks, repair as
necessary.

X





(6) Do a Power Assurance Check
(Ref. AMM TASK 71-00-00-710-013).
  • Make sure that the engine operates
    in the operating limits. You must
    carefully examine the engine N1 and
    N2 vibrations if they are more than
    the typical engine levels because
    this can be a sign of internal
    damage.

X





(a) If you cannot get stable engine
operation in the limits, then
remove the engine
(Ref. AMM TASK 71-00-20-000-040).


X




(7) Before engine shutdown, do a
functional test of the thrust
reverser system at idle conditions
(Ref. AMM TASK 78-31-00-710-041).

X





(8) After the test, examine the
magnetic chip detectors and the
items of the scavenge oil
filter for signs of bearing
distress
(Ref. AMM TASK 79-00-00-200-010).

X





(a) If you do not find signs of bearing
distress, do the inspection each day
for one week, then each week for one
month.

X





(b) If you find bearing material:


X


Subtask 05-51-44-210-058-G ** ON A/C NOT FOR ALL
K. Inspection of the Pylons
F Primary Structure ** ON A/C NOT FOR ALL
F Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
F Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.

Inspection of the Pylons





A.

Externally examine the pylon primary
and secondary structures for buckling,
shearing, distortion, cracks, damaged
paintwork or pulled or missing
fasteners/rivets.
X






If you find damage:







(a) On the secondary structure, remove
the access panels and doors of the
damaged area to see the internal
damage.

X





(b) On the primary structure, remove
the access doors
(Ref. AMM TASK 54-51-21-000-802).

X





(c) Internally examine the primary and
secondary structures (all the items
that you can see) for distortion,
buckling, cracks, defective attachment,
missing fasteners, leaks or other
damage.
This includes:
- The lower and upper spars
- The ribs
- The side panels
- The fire protection system
(specially the attachments of the
fire extinguishing bottles)
- The pipes and the ducts
- The drain pipes
- The hydraulic pipes.

X





(d) On the primary structure, install
the access doors
(Ref. AMM TASK 54-51-21-400-802).

X



B.

Open the fan cowl doors and the
thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-802) and
(Ref. AMM TASK 78-36-00-010-802).
X






(1) Externally examine the bottom area
of the primary structure, the forward
secondary structure (all the items that
you can see), the fan cowl fittings and
the thrust reverser fittings for:
- Buckling or
- Shearing or
- Distortion or
- Cracks or
- Damaged paintwork or
- Pulled or missing fasteners/rivets.
X






If you find damage:







(a) On the secondary structure, remove
the access panels and doors from the
damaged area to see the internal damage.

X





(b) On the primary structure, remove
the access doors
(Ref. AMM TASK 54-51-21-000-802).

X





(c) Internally examine the primary and
secondary structures (all the items
that you can see) for distortion,
buckling, cracks, defective attachment,
missing fasteners, leaks or other
damage.
This includes:
- The lower spar (specially the
splicing area between RIB2 and RIB3)
and the upper spar
- The ribs
- The side panels
- The fire protection system
(specially the attachments of the
fire extinguishing bottles)
- The pipes and the ducts
- The drain pipes
- The hydraulic pipes.

X





(d) On the primary structure, install
the access doors
(Ref. AMM TASK 54-51-21-400-802).

X



C.

Remove access panels
471AL 471CL 482AR and 482CR
from the pylon-to-wing junction
(Ref. AMM TASK 54-53-11-000-804).
X






(1) Do a detailed visual inspection of:
- The forward pylon-to-wing
attach-fittings at RIB5
- The spigot between RIB5 and RIB6
- The aft pylon-to-wing attach-fittings
at RIB10.
Make sure that there are no signs of
distortion, buckling, cracks or other
damage.
X






If you find damage:







(a) Remove the pylon-to-wing attach
fittings (Ref. AMM TASK 54-51-17-000-804) and (Ref. AMM TASK 54-51-17-000-805).

X





(b) Do a detailed visual inspection of:
- The forward attach fittings at RIB5
- The spigot between RIB5 and RIB6
- The aft attach fittings at RIB10.

X





(c) Contact Airbus.

X



D.

(1) Do a visual inspection of the
forward and rear engine mounts.
Make sure that there are no signs of
distortion, buckling, cracks or other
damage.
F Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
X






If you find damage:







(a) Remove the engine (Ref. AMM TASK 71-00-51-000-802).

X





(b) Do a detailed inspection of the
forward and rear engine mounts for
cracks or distortion
(dimensional and Non-Destructive Test
(NDT) inspection).

X





(c) Contact Airbus.

X



E.

(1) Install access panels
471AL 471CL 482AR and 482CR
on the pylon-to-wing junction
(Ref. AMM TASK 54-53-11-400-804).
X






(2) Close the thrust-reverser cowl
doors and the fan cowl doors (Ref. AMM TASK 78-36-00-410-802) and
(Ref. AMM TASK 71-13-00-410-802).
X




Subtask 05-51-44-210-054-E ** ON A/C NOT FOR ALL
L. Inspection of the Nacelles
F Inspection of the Nacelle ** ON A/C NOT FOR ALL
F Inspection of the V-blade ** ON A/C NOT FOR ALL
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
A.

(1) Examine the nacelle
external-surface cowls (inlet, fan,
thrust reverser, nozzle and
centerbody) for:
- Failures, cracks, signs of buckling
and permanent deformations
- Unusual steps and gaps between the
external cowl interfaces
- Pulled, bent or loose rivets or
fasteners
- Opened or loose access covers,
latches or panels.
X






(2) On the thrust reverser cowl-doors:
- Open the 4 actuator access covers.
- Examine the actuator fittings.
X






(3) Examine the edges of the
interfacing cowl parts (leading or
trailing edges, cowl edges near the
pylon or latching areas) for signs of
abutment (paint cracks, delamination
or impacts).
X




B.

Open the fan cowl doors
(Ref. AMM TASK 71-13-00-010-802)
and examine the parts
that follows for failures,
cracks, signs of buckling,
permanent deformations or
pulled, bent or loose rivets
or fasteners:
- The internal sides of the doors
- The locators
- The hold open rod
- The hinges and latch fittings
- The inlet flange with the engine
case.
X






If you find damage:







(1) Examine the adjacent areas and the
adjacent structure of the damaged
parts for cracks, failures, damaged
fasteners or composite delamination
or damage.

X





(2) Examine the structure adjacent to
the aft bulkhead for cracks, failures
or damaged fasteners.

X



C.

Open the thrust reverser cowl-doors
(Ref. AMM TASK 78-36-00-010-802)
and examine the parts that follow for
failures, bearing, cracks, permanent
deformations or damaged fasteners:
- The forward interface with the
engine (V-groove and V-blade)
- The hinge and latch fittings
- The actuator fittings and the
forward frame
- The C-duct skins that you can see
(with the thermal blankets)
- The interface between the nozzle
and the engine
- The interface between the centerbody
and the engine.
X






If you find damage:







(1) Examine the adjacent areas and the
adjacent structure of the damaged
parts for cracks, failures, damaged
fasteners or composite delamination
or damage.

X





(2) Examine the nozzle skins and
centerbody skins for cracks, failures
or damaged fasteners.

X



D.

Do a manual extension of the
thrust-reverser translating sleeves
(Ref. AMM TASK 78-32-00-860-802).
X






(1) If you find resistance or unusual
noises during the manual deployment
of the thrust reverser:
X






- Stop and replace the thrust
reverser.

X





(2) If the thrust reverser is
correctly deployed, examine the parts
that follow for cracks, failures,
damaged fasteners or composite
delamination or damage:
- The blocker door
- The blocker door hinges
- The drag links
- The cascades
- The translating sleeves.
X




E.

If there is no damage, do a manual
retraction of the thrust-reverser
translating sleeves
(Ref. AMM TASK 78-32-00-860-803).
X




F.

Do an operational test of the thrust
reverser system
(Ref. AMM TASK 78-31-00-710-805).
Make sure that the thrust reversers
can move fully and freely.
X




G.

Close the fan cowl doors and the
thrust reverser cowl-doors
(Ref. AMM TASK 71-13-00-410-802) and
(Ref. AMM TASK 78-36-00-410-802).
X




Subtask 05-51-44-210-053-E ** ON A/C NOT FOR ALL
M. Inspection of the Engine
   (1) Do a visual inspection of the engine after an overweight or heavy landing or excessive turbulence or high aircraft lateral loads (Ref. AMM TASK 72-00-00-200-812).
Subtask 05-51-44-210-057-B ** ON A/C NOT FOR ALL
N. Inspection of the Sharklets
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
4.

Sharklets





A.

Do a detailed visual inspection (DVI) for signs of distortion, tears, cracks, and pulled or loose fasteners on the items that follow:
  • the sharklet skin (from the tip cap to RIB27, including the leading edge and the trailing edge),
  • the wing upper skin joint (including the leading edge and the trailing edge),
  • the wing lower skin joint (including the leading edge and the trailing edge).
    If you find damage:
X






(1) Remove the sharklet (Ref. AMM TASK 57-31-23-000-801).

X





(2) Do an inspection of RIB27 (internal and external sides).

X





(3) Contact Airbus for more instructions.

X



Subtask 05-51-44-210-059-A
O. Inspection of the Cockpit and Cabin Equipment/Furnishings and the Cargo Compartments
ITEM
INSP CODE
INSPECTION TASKS
PHASE 1
PHASE 2
PHASE 3
INSP SIGN
REF. FIG.
1.

Inspection of the cockpit and cabin equipment/furnishings





A.

Do a visual check for disconnected parts, integrity of the latches and other damages on the equipment/furnishings. This includes:
-The crew seats and the cabin attendant seat
-The passenger seats with the in-flight entertainment devices
-The partitions
-The sidewall, decompression and ceiling panels in the cockpit and cabin
-The cockpit and cabin stowages
-The buffet/galleys
-The lavatories
-The emergency equipment
-The oxygen-mask stowage boxes.
X






If you find damage:







(1) On the passenger seat(s), do a detailed inspection of the damaged passenger seat(s) (Ref. AMM TASK 25-21-00-210-001).

X





(2) On the cockpit seats, do a visual inspection of the cockpit seats (Ref. AMM TASK 25-11-00-200-001).

X





(3) On the cabin attendant seat, do a detailed inspection of the cabin attendant seat (Ref. AMM TASK 25-22-00-210-001).

X





(4) On the oxygen-mask stowage boxes, do an operational test of the manual mask release (Ref. AMM TASK 35-23-00-710-001) or (Ref. AMM D/O 35-23-00-71).

X





(5) On other equipment/furnishing, contact airbus before return-to-service.

X



2.

Inspection of the cargo compartments





A.

Do a general visual inspection of the forward, aft and bulk cargo compartments:







(1) Examine the linings, floor panels, sealing strips, protection plates, center line cover-plates, access doors, decompression panels and pressure valve (Ref. AMM TASK 25-50-00-200-002).
X






(2) If installed, examine the loading and unloading systems of the containers/pallets.
In the forward and aft cargo compartments, examine the side guides, pallet locks and rollers (ball units, roller assemblies, drive units, guide latches and tracks) for:
  • Cracks, missing fasteners, deformation, misalignment and dents.
    Make sure that they move freely.
X






(3) Examine the cargo restraint system, door nets, divider nets and net attachment points.
X




Subtask 05-51-44-410-051-A
P. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Close the trailing-edge access panels of the vertical stabilizer (Ref. AMM TASK 55-33-13-410-002).
   (3) Install leading-edge access panels 322AL and 322CL of the vertical stabilizer (Ref. AMM TASK 55-32-11-400-001).
   (4) Install rudder fairings 325AL and 325AR (Ref. AMM TASK 53-55-12-400-001).
   (5) Install dorsal fin 321AL (Ref. AMM TASK 53-45-11-400-001).
   (6) Install vertical stabilizer fairings 323AL and 323AR (Ref. AMM TASK 53-55-11-400-001).
   (7) Close access door 312AR.
   (8) Remove the access platform(s).
   (9) Remove the WARNING NOTICE(S).
Subtask 05-51-44-860-051-A
Q. Aircraft Maintenance Configuration
   (1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
   (2) Pressurize the aircraft hydraulic systems
     (a) Pressurize the Green hydraulic system
(Ref. AMM TASK 29-10-00-863-001).
     (b) Pressurize the Yellow hydraulic system
(Ref. AMM TASK 29-10-00-863-002).
     (c) Pressurize the Blue hydraulic system
(Ref. AMM TASK 29-10-00-863-003).
Subtask 05-51-44-710-050-A
R. Do The Flight System Test
NOTE: The test below is necessary only if you find damage to the structure adjacent to the flight control surface.
   (1) Operate the rudder system.
Make sure that the travel is full and that the rudder moves freely (Ref. AMM TASK 27-24-00-710-001).
5. Close-up
Subtask 05-51-44-860-052-A
A. Put the aircraft back to its initial configuration.
   (1) Depressurize the aircraft hydraulic systems
     (a) Depressurize the Green hydraulic system
(Ref. AMM TASK 29-10-00-864-001).
     (b) Depressurize the Yellow hydraulic system
(Ref. AMM TASK 29-10-00-864-002).
     (c) Depressurize the Blue hydraulic system
(Ref. AMM TASK 29-10-00-864-003).
   (2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
   (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
[Rev.10 from 2021] 2026.03.31 22:52:02 UTC
"Aviabrain" 2025