Inspection after a Major Engine Failure

TASK 05-51-26-200-001-A
Inspection after a Major Engine Failure

1. Reason for the Job
You must do this inspection after a major engine failure if:

The engine is not balanced after one or more blades (fan or other blades) is/are damaged/missing.
The engine is seized.

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

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE
No specific	AR	WARNING NOTICE(S)

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
471AL, 471CL, 482AR, 482CR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 05-51-44-200-001-A	Inspection after Aircraft Operation with High Lateral Acceleration
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 27-50-00-866-008-A	Extension of the Flaps on the Ground
TASK 27-50-00-866-008-A-01	Extension of the Flaps/Slats on the Ground
TASK 27-50-00-866-009-A	Retraction of the Flaps on the Ground
TASK 27-50-00-866-009-A-01	Retraction of the Flaps/Slats on the Ground
TASK 28-10-00-910-002-A	Access to the Fuel Tanks and the Work Areas
TASK 28-25-00-650-001-A	Pressure Defuel
TASK 29-00-00-864-001-A	Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action
TASK 31-36-00-740-011-A	Printout of the Manually Requested Reports
TASK 32-00-00-481-001-A	Installation of the Safety Devices on the Landing Gears
TASK 32-11-00-200-001-A	General Visual Inspection of the Main Landing Gear
TASK 32-11-11-000-004-A	Removal of the MLG Uplock Pin
TASK 32-11-11-400-003-A	Installation of the MLG Uplock Pin
TASK 32-11-11-400-003-B	Installation of the MLG Uplock Pin
TASK 32-11-11-400-003-B-01	Installation of the MLG Uplock Pin with the Use of Liquid Nitrogen
TASK 32-12-00-010-001-A	Open the Main Gear Doors for Access
TASK 32-12-00-410-001-A	Close the Main Gear Doors after Access
TASK 32-21-00-200-002-A	General Visual Inspection of the Nose Landing Gear
TASK 32-21-16-000-002-A	Removal of the NLG Drag-Strut Assy
TASK 32-21-16-000-002-A-02	Removal of the Nose Landing Gear (NLG) Drag-Strut Assy (EV NLG)
TASK 32-21-16-400-002-A	Installation of the NLG Drag-Strut Assy
TASK 32-21-16-400-002-A-02	Installation of the Nose Landing Gear (NLG) Drag-Strut Assy (EV NLG)
TASK 32-22-00-010-001-A	Nose Gear Doors - Ground Doors Opening
TASK 32-22-00-410-001-A	Nose Gear Doors - Ground Doors Closing
TASK 32-31-21-000-001-A	Removal of the NLG Uplock Assy
TASK 32-31-21-400-001-A	Installation of the NLG Uplock Assy
TASK 32-31-44-000-001-A	Removal of the MLG Uplock Assembly
TASK 32-31-44-400-001-A	Installation of the MLG Uplock Assembly
TASK 32-46-00-740-001-A	BITE Test of the BSCU
TASK 32-69-00-740-001-A	BITE Check of Landing-Gear Control Interface-Unit (LGCIU) With Use of MCDU to Ensure that Continuous BITE is Operative
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 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 71-00-00-400-040-A	Installation of the Power Plant
TASK 71-00-00-400-040-A-01	Installation of the Power Plant with the Engine Positioner TWW 75E
TASK 71-00-00-400-040-A-03	Installation of the Power Plant with Jacxson Tool
TASK 71-00-00-400-042-A	Installation of the Power Plant
TASK 71-00-00-400-042-A-01	Installation of the Power Plant with the Engine Positioner TWW 75E (MIAG)
TASK 71-00-00-400-042-A-03	Installation of the Power Plant with Jacxson Tool
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 71-00-20-400-040-A	Installation of the Power Plant
TASK 71-00-20-400-040-A-01	Installation 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 71-00-51-400-802-A	Installation of the Power Plant (Bootstrap Method)
TASK 71-00-51-400-802-A-01	Installation of the Power Plant (JacXson Method)
TASK 71-13-00-200-010-A	Detailed Inspection of the Fan Cowl Doors
TASK 71-13-11-200-804-A	Visual Inspection of the Fan Cowl Doors
TASK 71-13-11-200-804-C	Visual Inspection of 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 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 78-32-00-200-010-A	Detailed Check of the Thrust Reverser Blocker Door Assemblies
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 78-32-11-210-001-A	Detailed Visual Inspection of the Thrust Reverser
TASK 78-32-11-210-040-A	Detailed Visual Inspection of the Thrust Reverser
TASK 31-37-73-00	AIDS - ENGINE REPORTS - DESCRIPTION AND OPERATION
TASK 31-37-73-00-01	AIDS - ENGINE REPORTS - DESCRIPTION AND OPERATION
TASK 31-37-73-00-02	AIDS - ENGINE REPORTS - DESCRIPTION AND OPERATION
Primary Structure ** ON A/C NOT FOR ALL
Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
Inspection of the Pylon Forward Secondary-Structure ** ON A/C NOT FOR ALL
Primary Structure ** ON A/C NOT FOR ALL
Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
Primary Structure ** ON A/C NOT FOR ALL
Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
Inspection of the Nacelle ** ON A/C NOT FOR ALL
Inspection of the V-blade ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 05-51-26-210-055-A

A. Inspection Preparation and Maintenance Actions
(1) Find the engine-fan vibration level that occured during the event (Ref. AMM TASK 31-36-00-740-011).

NOTE: The engine mechanical advisory report (7) gives the correct engine vibration code. Refer to (Ref. AMM D/O 31-37-73-00) for more information.

If you do not find the engine-fan vibration level in the engine mechanical advisory report (7), find the engine-fan vibration level from the Digital Flight Data Recorder (DFDR)/Quick Access Recorder (QAR) data.
(2) Event severity and maintenance actions
(a) Event severity conditions:

Landing gears were retracted during the event,
Fan blade(s) out of engine area or broken, and
N1 vibration was at saturation level (i.e. 9.9 CU) during the event.

(b) Maintenance actions:
1 If all the above conditions occur, do the steps that follow:
a Do all the inspections/actions given in the paragraph 4 "Procedure".
b Do the inspection after high lateral loads (Ref. AMM TASK 05-51-44-200-001).
c Contact Airbus for more information about the event.
2 If one or more of the three severity conditions given in the paragraph "Event severity conditions" did not occur, or if there was another major engine failure, do the steps that follow:
a Do all the inspections/actions given in the paragraph 4 "Procedure" other than the replacement of the landing gear uplocks and uplock roller/pins given in the subtask "Inspection of the Landing Gears".
b Do the inspection after high lateral loads (Ref. AMM TASK 05-51-44-200-001).
c Contact Airbus for more information about the event.

Subtask 05-51-26-481-050-A

B. Safety Precautions
(1) Make sure the safety devices are installed on the landing gears (Ref. AMM TASK 32-00-00-481-001).
(2) Put the WARNING NOTICE(S) in position in the cockpit to tell persons not to operate the aircraft systems.

Subtask 05-51-26-010-050-A

C. Get Access
(1) Open the Nose Landing Gear (NLG) doors (Ref. AMM TASK 32-22-00-010-001).
(2) Open the Main Landing Gear (MLG) doors (Ref. AMM TASK 32-12-00-010-001).

Subtask 05-51-26-860-050-A

D. Aircraft Maintenance Configuration
(1) Make sure that the hydraulic systems are depressurized
(Ref. AMM TASK 29-00-00-864-001).
(2) Make sure that the electrical systems are de-energized (Ref. AMM TASK 24-41-00-862-002).
(3) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position.

Subtask 05-51-26-020-050-B ** ON A/C NOT FOR ALL

E. Removal of the Power Plant
(1) Remove the power plant (Ref. AMM TASK 71-00-00-000-040).

Subtask 05-51-26-020-050-C ** ON A/C NOT FOR ALL

E. Removal of the Power Plant
(1) Remove the power plant (Ref. AMM TASK 71-00-20-000-040).

Subtask 05-51-26-020-050-D ** ON A/C NOT FOR ALL

E. Removal of the Power Plant
(1) Remove the power plant (Ref. AMM TASK 71-00-00-000-042).

Subtask 05-51-26-020-050-F ** ON A/C NOT FOR ALL

E. Removal of the Power Plant
(1) Remove the power plant (Ref. AMM TASK 71-00-51-000-802).

4. Procedure
Subtask 05-51-26-210-050-A ** ON A/C NOT FOR ALL

A. Inspection of the Pylons

Primary Structure ** ON A/C NOT FOR ALL

Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL

Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
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 attachments, failures, leaks, 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 - The pipes and ducts - 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.	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:
	(1) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage.		X
	(2) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001).		X
	(3) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachments, failures, leaks, 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 - The pipes and ducts - The drain pipes - The hydraulic and fuel pipes - The bleed-air system components.		X
	If you find damage:
	- Contact Airbus.			X
	(4) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001).		X
	(5) 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.	(1) Do a visual inspection of the engine mounts attached to the engine (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).	X
	(2) Do a visual 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:
	- Contact Airbus.		X
E.	Install the center fillets on the pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002).	X

Subtask 05-51-26-210-052-A ** ON A/C NOT FOR ALL

B. Inspection of the Nacelles

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
1.		Examine the fan cowl (Ref. AMM TASK 71-13-11-200-804).	X
2.		Examine the thrust reverser cowl (Ref. AMM TASK 78-32-11-210-040).	X

Subtask 05-51-26-210-050-B ** ON A/C NOT FOR ALL

C. Inspection of the Pylons

Inspection of the Pylon Forward Secondary-Structure ** ON A/C NOT FOR ALL

Primary Structure ** ON A/C NOT FOR ALL

Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL

Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
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 attachments, failures, leaks, missing fasteners 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 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.	Externally examine the parts that follow for buckling, shearing, distortion, cracks, damaged paintwork or pulled or missing fasteners/rivets: - The bottom area of the primary structure - The forward secondary structure (all the items that you can see) - The fan cowl fittings - The thrust reverser fittings - The secondary structure rods - The upper and lower rod fittings - The upper and lower bolt fittings. Inspection of the Pylon Forward Secondary-Structure ** ON A/C NOT FOR ALL	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 attachments, failures, leaks, missing fasteners 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 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. Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL	X
	If you find damage:
	(a) Do a detailed inspection of the forward and rear engine mounts for cracks or distortion (dimensional and Non-Destructive Test (NDT) inspection).		X
	(b) Contact Airbus.		X
E.	Install access panels 471AL 471CL 482AR and 482CR on the pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-804).	X

Subtask 05-51-26-210-052-E ** ON A/C NOT FOR ALL

D. Inspection of the Nacelles

Inspection of the Nacelle ** ON A/C NOT FOR ALL

Inspection of the V-blade ** ON A/C NOT FOR ALL

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Nacelle
A.	(1) Examine the nacelle external-surface cowls (inlet, fan, thrust reverser, nozzle and centerbody) for: - Failures, cracks, signs of buckling and permanent deformation - 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.	(1) For the fan cowl doors, examine the parts that follow for failures, cracks, signs of buckling, permanent deformation 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:
	(a) Examine the adjacent areas and the adjacent structure of the damaged parts for cracks, failures, damaged fasteners or composite delamination or damage.		X
	(b) Examine the structure adjacent to the aft bulkhead for cracks, failures or damaged fasteners.		X
C.	(1) For the thrust reverser cowl-doors, examine the parts that follow for failures, bearing, cracks, permanent deformation 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:
	(a) Examine the adjacent areas and the adjacent structure of the damaged parts for cracks, failures, damaged fasteners or composite delamination or damage.		X
	(b) 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 hear unusual noises during the manual deployment of the thrust reverser:
	- 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

Subtask 05-51-26-210-050-E ** ON A/C NOT FOR ALL

E. Inspection of the Pylons

Primary Structure ** ON A/C NOT FOR ALL

Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL

Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
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 attachments, failures, leaks, 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 - The pipes and ducts - 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.	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:
	(1) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage.		X
	(2) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001).		X
	(3) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachments, failures, leaks, 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 - The pipes and ducts - The drain pipes - The hydraulic and fuel pipes - The bleed-air system components.		X
	If you find damage:
	- Contact Airbus.			X
	(4) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001).		X
	(5) 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.	(1) Do a visual inspection of the engine mounts attached to the engine (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).	X
	(2) Do a visual 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:
	- Contact Airbus.		X
E.	Install the center fillets on the pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002).	X

Subtask 05-51-26-210-052-B ** ON A/C NOT FOR ALL

F. Inspection of the Nacelles

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
1.		Examine the fan cowl (Ref. AMM TASK 71-13-00-200-010).	X
2.		Examine the thrust reverser cowl (Ref. AMM TASK 78-32-00-200-010).	X

Subtask 05-51-26-210-050-G ** ON A/C NOT FOR ALL

G. Inspection of the Pylons

Primary Structure ** ON A/C NOT FOR ALL

Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL

Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
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 attachments, failures, leaks, 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 - The pipes and ducts - 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.	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:
	(1) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage.		X
	(2) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001).		X
	(3) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachments, failures, leaks, 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 - The pipes and ducts - The drain pipes - The hydraulic and fuel pipes - The bleed-air system components.		X
	If you find damage:
	- Contact Airbus.			X
	(4) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001).		X
	(5) 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.	(1) Do a visual inspection of the engine mounts attached to the engine (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).	X
	(2) Do a visual 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:
	- Contact Airbus.		X
E.	Install the center fillets on the pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002).	X

Subtask 05-51-26-210-052-C ** ON A/C NOT FOR ALL

H. Inspection of the Nacelles

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
1.		Examine the fan cowl (Ref. AMM TASK 71-13-11-200-804).	X
2.		Examine the thrust reverser cowl (Ref. AMM TASK 78-32-11-210-001).	X

Subtask 05-51-26-210-053-A ** ON A/C NOT FOR ALL

I. Inspection of the Engine-to-Pylon and Pylon-to-Wing Attach Fittings

NOTE: Only do this inspection if you find damage during the Phase 1 inspection of the pylon and the nacelle.

ITEM	INSPECTION TASKS	PHASE 2	PHASE 3
1.	Engine-to-Pylon Attach Fittings
A.	Do a detailed inspection of the attach fittings below the main ribs. (1) Make sure that there is/are no: - Distortion, damage to the structure (cracks, rupture etc.) or signs of oxidation or burns.	X
2.	Pylon-to-Wing Attach Fittings
A.	Remove the fillets.	X
B.	Detailed inspection of the front and rear pylon-to-wing attach fittings of the adjacent structure.	X
C.	If you find damage during Phase 2:
	(1) Examine the area adjacent to the pylon forward and aft attachment for: - Cracks, - Correct condition of all fasteners and safety devices.
	(2) Examine the area adjacent to the thrust-spigot attachment fitting for: - Cracks, - Damaged sealant, - Correct condition of all fasteners and safety devices.		X
	(3) Examine the wing bottom skin adjacent to the pylon forward and aft attachments and the thrust spigot for: - Cracks, - Correct condition of all fasteners and safety devices, - Fluid leaks.		X
	If you find damage: (1) Defuel the wing (Ref. AMM TASK 28-25-00-650-001). (2) Get access to the internal structure adjacent to RIB7 and RIB8 (Ref. AMM TASK 28-10-00-910-002). Do a full inspection for cracks, damage, damaged paint and sealant and correct condition, of all fasteners and safety devices in the following areas: - The rear face of the front spar, inboard of RIB7 and outboard of RIB8, - The front face of the rear spar inboard of RIB7 and outboard of RIB8, - The pylon rear attachment, - RIB7 and RIB8, - The stringers and the brackets.		X

Subtask 05-51-26-210-056-A

J. Inspection of the Landing Gears

ITEM	INSPECTION TASKS	PHASE 1
1.	Inspection of the MLG
A.	If the major engine failure occurred with the MLG extended (down and locked): Do a General Visual Inspection (GVI) of the MLG (Ref. AMM TASK 32-11-00-200-001). Do the BITE test of the Landing Gear Control and Interface Unit (LGCIU) (Ref. AMM TASK 32-69-00-740-001). Do the BITE test of the Braking and Steering Control Unit (BSCU) (Ref. AMM TASK 32-46-00-740-001).	X
B.	If the major engine failure occurred with the MLG retracted (up and locked), do the steps that follow:
	(1) Do a GVI of the MLG (Ref. AMM TASK 32-11-00-200-001).	X
	(2) If all the event severity conditions given in the subtask "Inspection Preparation and Maintenance Actions" occurred, it is necessary to do the steps that follow:
	(a) Replace the left and right MLG uplock pins and attachment bolts (Ref. AMM TASK 32-11-11-000-004) and (Ref. AMM TASK 32-11-11-400-003).	X
	(b) Replace the MLG uplocks: 1_ For 2509GM (2510GM): - Remove the MLG uplocks and install the new MLG uplocks (Ref. AMM TASK 32-31-44-000-001) and (Ref. AMM TASK 32-31-44-400-001).	X
2.	Inspection of the NLG
A.	If the major engine failure occurred with the NLG extended (down and locked): Do a GVI of the NLG (Ref. AMM TASK 32-21-00-200-002). Do the BITE test of the LGCIU (Ref. AMM TASK 32-69-00-740-001). Do the BITE test of the BSCU (Ref. AMM TASK 32-46-00-740-001).	X
B.	If the major engine failure occurred with the NLG retracted (up and locked), do the steps that follow:
	(1) Do a GVI of the NLG (Ref. AMM TASK 32-21-00-200-002).	X
	(2) If all the event severity conditions given in the subtask "Inspection Preparation and Maintenance Actions" occurred, it is necessary to do the steps that follow:
	(a) Replace the NLG uplock roller and the attachment bolts (Ref. AMM TASK 32-21-16-000-002) and (Ref. AMM TASK 32-21-16-400-002).	X
	(b) Replace the NLG uplock: 1_ For 2530GM: - Remove the NLG uplock and install a new NLG uplock (Ref. AMM TASK 32-31-21-000-001) and (Ref. AMM TASK 32-31-21-400-001).	X

Subtask 05-51-26-210-057-A

K. Inspection of the Aircraft Structure Aft of the Damaged Engine

NOTE: This inspection is necessary to make sure that the ejected engine parts did not cause damage to the aircraft structure aft of the damaged engine.

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Inspection of the Aircraft Structure Aft of the Damaged Engine
A.	Do a GVI of the engine fan and the turbine blades of the last stage for: Signs of damage or Signs of debris in the exhaust of the engine.	X
	If you find damage:
	(1) Fully extend the flaps (Ref. AMM TASK 27-50-00-866-008).		X
	(2) Do the below inspections on the side of the damaged engine: (a) Do a GVI of the underside of the wing, the flap fairings and the lower surface of the flap for: - Signs of scratches and damage because of the ejected debris. (b) Do a GVI of the lateral and lower panels of the fuselage (belly fairing included) for: - Signs of scratches and damage because of the ejected debris. (c) Do a GVI of the leading edge and the lower surface of the horizontal tail plane for: - Signs of scratches and damage because of the ejected debris. (d) If the event occurred during the extension or retraction of the landing gears, do a GVI of the MLG bays for: - Signs of scraches and damage because of the ejected debris.		X
	(3) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).		X

Subtask 05-51-26-420-050-B ** ON A/C NOT FOR ALL

L. Installation of the Power Plant
(1) Install the power plant (Ref. AMM TASK 71-00-00-400-040).

Subtask 05-51-26-420-050-C ** ON A/C NOT FOR ALL

L. Installation of the Power Plant
(1) Install the power plant (Ref. AMM TASK 71-00-20-400-040).

Subtask 05-51-26-420-050-D ** ON A/C NOT FOR ALL

L. Installation of the Power Plant
(1) Install the power plant (Ref. AMM TASK 71-00-00-400-042).

Subtask 05-51-26-420-050-F ** ON A/C NOT FOR ALL

L. Installation of the Power Plant
(1) Install the power plant (Ref. AMM TASK 71-00-51-400-802).

5. Close-up
Subtask 05-51-26-410-050-A

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the NLG doors (Ref. AMM TASK 32-22-00-410-001).
(3) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001).

Subtask 05-51-26-942-050-A

B. Put the aircraft back to the serviceable condition.
(1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(2) Remove the WARNING NOTICE(S).
(3) Remove the access platform(s).

[Rev.10 from 2021] 2026.03.31 22:51:46 UTC