Inspection after In-flight Excessive Load Factor due to Turbulence or Maneuver or in Excess of VMO/MMO

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

1. Reason for the Job
To examine the aircraft for structural damage after a flight where excessive load factors occurred. Such load factors can be caused by high turbulence, maneuvers not in the usual limits, or VMO/MMO values that are more than the specified limits.
To know if the inspection is necessary, refer to Para.3.A.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	WARNING NOTICE(S)

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
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 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 27-14-00-710-001-A	Operational Test of the Aileron and Hydraulic Actuation
TASK 27-24-00-710-001-A	Operational Test of the Rudder Hydraulic Actuation
TASK 27-34-00-710-001-A	Operational Test of the Elevator and Hydraulic Actuation
TASK 27-44-00-710-002-A	Operational Test of the Trimmable Horizontal Stabilizer Actuator with the Individual Hydraulic Systems
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 27-54-00-710-001-A	Operational Test of the Flap System
TASK 27-64-00-710-001-A	Operational Test of the Spoiler Hydraulic Actuation
TASK 27-80-00-866-004-A	Extending the Slats on the Ground
TASK 27-80-00-866-005-A	Retracting the Slats on the Ground
TASK 27-84-00-710-001-A	Operational Test of the Slat System
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 31-37-00-200-001-A	Check of the Load-Report Parameter after Hard/Overweight Landing or Excessive Turbulence
TASK 32-00-00-481-001-A	Installation of the Safety Devices on the Landing Gears
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 35-23-00-710-001-A	Operational Check of Manual Mask Release
TASK 52-21-11-000-001-A	Removal of the Emergency Exit Hatch
TASK 52-21-11-400-001-A	Installation of the Emergency Exit Hatch
TASK 52-22-00-010-802-A	Opening of the Overwing Emergency-Exit Door from the Passenger Compartment
TASK 52-22-00-410-802-A	Closing of the Overwing Emergency-Exit Door from the Passenger Compartment
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 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
Flow Chart Diagram
Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL
Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL
Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL
Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL
Exhaust Nozzle: Engine Interface ** ON A/C NOT FOR ALL
Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
Primary Structure ** ON A/C NOT FOR ALL
Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL
Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL
Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL
Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL
Common Nozzle Assembly: Engine Interface ** ON A/C NOT FOR ALL
Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
Primary Structure ** 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
Pylon-to-Engine Attach Fittings and Engine Mounts ** ON A/C NOT FOR ALL
Primary Structure ** ON A/C NOT FOR ALL
Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 05-51-17-941-054-A

A. Inspection Requirements

Flow Chart Diagram

(1) Definition:
Excessive turbulence is turbulence that causes large or sudden changes in the altitude and/or the attitude. It usually causes large changes in airspeed. Passengers and crew are moved suddenly against their seat belts and loose objects are moved in the aircraft.
Do this inspection after a flight crew report of flight in excessive turbulence or if data from the Digital Flight Data Recording System (DFDRS) or from the Quick Access Recorder (QAR) (if installed) show turbulence or maneuvers that caused a normal acceleration (VRTA) equal to or more than:
(a) + 2.5 g or - 1 g (clean configuration): VRTA >= 2.5 g or VRTA <= - 1 g,
(b) + 2 g or 0 g (flaps and/or slats extended): VRTA >= 2 g or VRTA <= 0 g, or
(c) + 2 g or 0 g and VMO/MMO condition i.e. CAS >= VMO or M >=MMO; and VRTA >= 2 g or VRTA <= 0 g.
During a flight in excessive turbulence, high lateral loads can occur.
(2) Excessive VMO-MMO
Do this inspection after a flight crew report of flight in excess of VMO/MMO or if data from the DFDRS or from the QAR (if installed) show:
(a) Speeds that were more than or equal to VMO + 20 Kts (CAS), or
(b) Speeds that were more than or equal to MMO + 0.04 M, or
(c) Speeds that were more than or equal to VMO or MMO and at which there was a normal acceleration out of the 0 g to + 2 g (inclusive) range.
(3) Confirmation that the inspection is necessary:
(a) Excessive turbulence
After a report of flight in excessive turbulence, you must do the inspection before the next flight if:

The parameters from the DFDR/QAR (if installed) or the Data Management Unit (DMU) load report 15 (with trigger code 5XX0) are equal to or more than the values specified in the above paragraph (Ref. AMM TASK 31-37-00-200-001).

(b) Excessive VMO/MMO
After a flight crew report of flight in excess of VMO/MMO, you must do the inspection before the next flight if:

The values in the flight crew report are equal to or more than the values specified in the above paragraph, or
The parameters from the DFDR/QAR (if installed) are equal to or more than the values specified in the above paragraph.

(4) Also do this inspection if there was a DMU load report 15 (with trigger code 5XX0). This report shows that excessive vertical acceleration occurred during the flight (Ref. AMM TASK 31-37-00-200-001).

NOTE: A DMU load report 15 can occur immediately after the vertical acceleration, or during flight phase 9 or 10 in relation to the DMU programming.

(5) DMU 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) After a pilot report of high lateral acceleration, refer to (Ref. AMM TASK 05-51-44-200-001).
If there is no pilot report of high lateral loads, you must do inspections as per (Ref. AMM TASK 05-51-44-200-001) if:

There is a DMU load report 15 that shows values above 0.35 g (Ref. AMM TASK 31-37-00-200-001) or
Data from the DFDR/QAR (if installed) shows values above 0.35 g.

(7) Requirements if there are findings during the inspection

If you find damage during the inspection, send to Airbus:

Load report 15 (with trigger code 5XX0)
The DFDR data (raw data)
The load and trim sheet
The pilot report
The inspection findings.

Wait for and obey the instructions from Airbus before the next flight.
(8) If there is no finding during the inspection:

The aircraft can go back to service.

Subtask 05-51-17-941-052-A

B. Not Applicable

Subtask 05-51-17-010-050-A

C. Get Access
(1) Open the main gear doors and install the safety devices (Ref. AMM TASK 32-12-00-010-001).

Subtask 05-51-17-481-050-A

D. Safety Precautions
(1) Make sure that the safety devices are installed on the main landing gear (Ref. AMM TASK 32-00-00-481-001).

Subtask 05-51-17-866-050-A

E. Extension of the Flaps and the Slats
(1) Fully extend the flaps (Ref. AMM TASK 27-50-00-866-008).
(2) Fully extend the slats (Ref. AMM TASK 27-80-00-866-004).

Subtask 05-51-17-860-050-A

F. 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 circuits are de-energized (Ref. AMM TASK 24-41-00-862-002).
(3) Put the WARNING NOTICE(S) in the cockpit to tell persons not to operate the aircraft systems.
(4) Put the access platform in position.

4. Procedure
Subtask 05-51-17-210-051-A

A. General

NOTE: All these inspections are visual unless the text gives other instructions.
You can do non-destructive tests (refer to the Aircraft Non-destructive Test Manual - NTM) if:

You think it is necessary,
Your airworthiness authority tells you to.

If, because of the inspection, you disconnect or remove components, pipes, ducts, cables, electrical connectors or mechanical linkages, a functional test of the related system(s) is then necessary.

Subtask 05-51-17-210-063-A ** ON A/C NOT FOR ALL

B. Inspection of the Fuselage

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
1.	Belly fairing and fuselage (FR36 to FR46)
A.	Examine externally all the belly fairing panels, specially the leading- edge fairings and upper and lower wing fairings, for: - Correct attachment, delamination, damaged paintwork, pulled or torn fasteners. If you find damage:	X
	(1) Remove the damaged panel and internally examine the belly fairing structure.		X
	(2) Examine all the components, pipes, ducts, electrical looms and their mounts for distortion, cracks, breaks and fluid leakage.		X
	(3) Refer to item 2.		X
B.	At the joint of the wing spar box with the wing (FR36 to FR46), RIB1, examine: - The rear-spar web splice, - The fuselage skin panels, - The panel splices, for distortion, cracks, pulled or torn fasteners, damaged paintwork. If you find damage, refer to item 2.	X
C.	Fuselage section between FR35 and FR47: - If the overwing emergency-exit hatches are installed, remove them (Ref. AMM TASK 52-21-11-000-001). - Examine the operation of overwing emergency-exit hatches for jamming or distortion. - Examine all corners of the door surround structure, the x-stops and the hinges for loose fasteners, cracked or flaking paint, incorrect attachment or distortion. If you find damage, refer to item 2. - If the overwing emergency-exit hatches are removed, install them (Ref. AMM TASK 52-21-11-400-001).	X
D.	At and around FR46, examine the lower skin panel of the fuselage between stringer 41RH and stringer 41LH for: - Distortion, cracks, pulled or torn fasteners, damaged paintwork. If you find damage, refer to item 2.	X
2.	Fuselage (FR26 to FR70) If you find damage when you do item 1.A, 1.B, 1.C or 1.D, then do the inspections that follow:
A.	From FR26 to FR35: - Externally examine the skin panels, the splicing and the riveting for distortion, cracks, pulling, tears and damaged paintwork. If you find damage:		X
	(1) Remove the forward cargo- compartment panels and examine the floor support structure, frames, skin panels, splicing, rivets and stringers for: - Distortion, cracks, pulled and torn fasteners, damaged paintwork.			X
B.	At FR35, examine the top of the joint between stringer 6RH and stringer 6LH for: - Distortion, cracks, pulled or torn fasteners, damaged paintwork.		X
C.	From FR35 to FR47: - In the MLG well and on the upper fuselage section (exter- nal): - Examine the frames, skin panels, splices, stringers and riveting for distortion, cracks, pulling, tears and damaged paintwork. If you find damage:		X
	(1) Examine the upper fuselage section internally (the frames, stringers, cleats, and splices) for: - Distortion, cracks pulled or torn fasteners, damaged paintwork.			X
D.	From FR47 to FR70: - Examine the frames, skin panels, splices, stringers and rivets for: - Distortion, cracks, pulling, tears and damaged paintwork.		X
E.	Examine the cut-out corners and rivets of the emergency-exit surround panel for: - Distortion, cracks, pulling, tears and damaged paintwork.		X
F.	Examine the hinge fittings of the bulk cargo-compartment door for cracks, pulled or torn fasteners and damaged paintwork.		X
G.	Examine the cut-out corner and rivet areas of the surround panel of the bulk cargo-compartment door for: - Distortion, cracks, pulling, tears and damaged paintwork.		X
3.	Horizontal stabilizer cut-out
A.	Examine the cut-out corners for cracks. If you find damage:	X
	Examine the cut-out edges of the top and bottom stringers for: - Distortion, cracks, pulled or torn fasteners and damaged paintwork. NOTE: These inspections are done together, with the horizontal stabilizer inspection.		X

Subtask 05-51-17-210-063-D ** ON A/C NOT FOR ALL

B. Inspection of the Fuselage

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
1.	Belly fairing and fuselage (FR36 to FR46)
A.	Examine externally all the belly fairing panels, specially the leading- edge fairings and upper and lower wing fairings, for: - Correct attachment, delamination, damaged paintwork, pulled or torn fasteners. If you find damage:	X
	(1) Remove the damaged panel and internally examine the belly fairing structure.		X
	(2) Examine all the components, pipes, ducts, electrical looms and their mounts for distortion, cracks, breaks and fluid leakage.		X
	(3) Refer to item 2.		X
B.	At the joint of the wing spar box with the wing (FR36 to FR46), RIB1, examine: - The rear-spar web splice, - The fuselage skin panels, - The panel splices, for distortion, cracks, pulled or torn fasteners, damaged paintwork. If you find damage, refer to item 2.	X
C.	Fuselage section between FR35 and FR47: - Open the overwing emergency-exit doors (Ref. AMM TASK 52-22-00-010-802). - Examine the operation of overwing emergency-exit doors for jamming or distortion. - Examine all corners of the door surround structure, the x-stops and the hinges for loose fasteners, cracked or flaking paint, incorrect attachment or distortion. If you find damage, refer to item 2. - Close the overwing emergency-exit doors (Ref. AMM TASK 52-22-00-410-802).	X
D.	At and around FR46, examine the lower skin panel of the fuselage between stringer 41RH and stringer 41LH for: - Distortion, cracks, pulled or torn fasteners, damaged paintwork. If you find damage, refer to item 2.	X
2.	Fuselage (FR26 to FR70) If you find damage when you do item 1.A, 1.B, 1.C or 1.D, then do the inspections that follow:
A.	From FR26 to FR35: - Externally examine the skin panels, the splicing and the riveting for distortion, cracks, pulling, tears and damaged paintwork. If you find damage:		X
	(1) Remove the forward cargo- compartment panels and examine the floor support structure, frames, skin panels, splicing, rivets and stringers for: - Distortion, cracks, pulled and torn fasteners, damaged paintwork.			X
B.	At FR35, examine the top of the joint between stringer 6RH and stringer 6LH for: - Distortion, cracks, pulled or torn fasteners, damaged paintwork.		X
C.	From FR35 to FR47: - In the MLG well and on the upper fuselage section (exter- nal): - Examine the frames, skin panels, splices, stringers and riveting for distortion, cracks, pulling, tears and damaged paintwork. If you find damage:		X
	(1) Examine the upper fuselage section internally (the frames, stringers, cleats, and splices) for: - Distortion, cracks pulled or torn fasteners, damaged paintwork.			X
D.	From FR47 to FR70: - Examine the frames, skin panels, splices, stringers and rivets for: - Distortion, cracks, pulling, tears and damaged paintwork.		X
E.	Examine the cut-out corners and rivets of the emergency-exit surround panel for: - Distortion, cracks, pulling, tears and damaged paintwork.		X
F.	Examine the hinge fittings of the bulk cargo-compartment door for cracks, pulled or torn fasteners and damaged paintwork.		X
G.	Examine the cut-out corner and rivet areas of the surround panel of the bulk cargo-compartment door for: - Distortion, cracks, pulling, tears and damaged paintwork.		X
3.	Horizontal stabilizer cut-out
A.	Examine the cut-out corners for cracks. If you find damage:	X
	Examine the cut-out edges of the top and bottom stringers for: - Distortion, cracks, pulled or torn fasteners and damaged paintwork. NOTE: These inspections are done together, with the horizontal stabilizer inspection.		X

Subtask 05-51-17-210-052-B ** ON A/C NOT FOR ALL

C. Inspection of the Pylons and the Nacelles

Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL

Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL

Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL

Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL

Exhaust Nozzle: Engine Interface ** ON A/C NOT FOR ALL

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

Primary Structure ** 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) Remove the access doors of the primary structure (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) Remove the access doors of the primary structure (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
2.	Inspection of the Nacelles
A.	Examine the nacelle external-surface cowls (the inlet, the fan cowl doors, the thrust reverser and the nozzle) 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 - 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 or impacts).	X
B.	Open the fan cowl doors and examine: Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL - The internal side of the doors for cracks - The locators - The hinge and latch fittings for signs of 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: Thrust Reverser: Hinge Fittings ON A/C NOT FOR ALL Thrust Reverser: Latch Fittings ON A/C NOT FOR ALL - The forward interface with the engine - The 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 those parts, examine: - The engine and exhaust nozzle interface for damaged fasteners Exhaust Nozzle: Engine Interface ON A/C NOT FOR ALL - The common nozzle assembly and thrust reverser interface for bearing, cracks or failures - The inlet cowl, rear bulkhead and engine interface. Inlet Cowl: Engine Interface and Rear Bulkhead ON A/C NOT FOR ALL		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 05-51-17-210-064-B ** ON A/C NOT FOR ALL

D. Inspection of the Engine

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
1.	Examine the Engine
A.	Turn the fan rotor with your hand. Make sure that there is (are) no bearing roughness, unusual noises and bindings.	X
B.	Visual inspection of the abradable material of the fan inlet case: make sure that there is 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.	X
	If you find damage:
	(1) Do a borescope inspection of the HPC blades (Ref. AMM TASK 72-31-00-290-001).		X
	NOTE: Engine removal can be necessary to do this task (Ref. AMM TASK 71-00-00-000-040).			X
	(2) Do a borescope inspection of the LPC blades (Ref. AMM TASK 72-21-00-290-001).		X
	NOTE: Engine removal can be necessary to do this task (Ref. AMM TASK 71-00-00-000-040).			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: Engine removal can be necessary to do this task (Ref. AMM TASK 71-00-00-000-040).			X

Subtask 05-51-17-210-052-C ** ON A/C NOT FOR ALL

E. Inspection of the Pylons and Nacelles

Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL

Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL

Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL

Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL

Common Nozzle Assembly: Engine Interface ** ON A/C NOT FOR ALL

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

Primary Structure ** 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) Remove the access doors of the primary structure (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) Remove the access doors of the primary structure (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
2.	Inspection of the Nacelles
A.	Examine the nacelle external-surface cowls (the inlet, the fan cowl doors, the thrust reverser and the nozzle) for: - Failures, cracks, signs of buckling and permanent deformations - Unusual steps and gaps between the 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 or impacts).	X
B.	Open the fan cowl doors and examine: Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL - The internal side of the doors for cracks - The locators - The hinge and latch fittings for signs of 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: Thrust Reverser: Hinge Fittings ON A/C NOT FOR ALL Thrust Reverser: Latch Fittings ON A/C NOT FOR ALL - The forward interface with the engine - The 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, the blocker door hinges, the drag links, the cascades and the 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 those parts, examine: - The engine and exhaust nozzle interface for damaged fasteners - The common nozzle assembly and thrust reverser interface for bearing, cracks or failures. Common Nozzle Assembly: Engine Interface ON A/C NOT FOR ALL - The inlet cowl, rear bulkhead and engine interface. Inlet Cowl: Engine Interface and Rear Bulkhead ON A/C NOT FOR ALL		X

Subtask 05-51-17-210-064-C ** ON A/C NOT FOR ALL

F. Inspection of the Engine

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
1.	Examine the Engine
A.	Turn the fan rotor with your hand in the direction of normal engine rotation. Make sure that there is (are) 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 excessive turbulence, maneuvers or VMO/MMO exceeded. 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 (are) no distortion or cracks, no loose rivets or 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 (are) 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: - Remove the engine (Ref. AMM TASK 71-00-20-000-040).			X

Subtask 05-51-17-210-052-E ** ON A/C NOT FOR ALL

G. Inspection of the Pylons and the Nacelles

Inlet Cowl: Engine Interface and Rear Bulkhead ** ON A/C NOT FOR ALL

Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL

Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL

Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL

Exhaust Nozzle: Engine Interface ** ON A/C NOT FOR ALL

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

Primary Structure ** 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) Remove the access doors of the primary structure (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) Remove the access doors of the primary structure (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
2.	Inspection of the Nacelles
A.	Examine the nacelle external-surface cowls (the inlet, the fan cowl doors, the thrust reverser and the 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 or impacts).	X
B.	Open the fan cowl doors and examine: Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL - The internal side of the doors for cracks - The locators - The hinge and latch fittings for signs of 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: Thrust Reverser: Hinge Fittings ON A/C NOT FOR ALL Thrust Reverser: Latch Fittings ON A/C NOT FOR ALL - The forward interface with the engine - The 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 those parts, examine: - The engine and exhaust nozzle interface for damaged fasteners Exhaust Nozzle: Engine Interface ON A/C NOT FOR ALL - The common nozzle assembly and thrust reverser interface for bearing, cracks or failures - The inlet cowl, rear bulkhead and engine interface. Inlet Cowl: Engine Interface and Rear Bulkhead ON A/C NOT FOR ALL		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 05-51-17-210-064-D ** ON A/C NOT FOR ALL

H. Inspection of the Engine

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
1.	Examine the engine
A.	Turn the fan rotor with your hand. Make sure that there is (are) no bearing roughness, unusual noises and bindings.	X
B.	Visual inspection of the abradable material of the fan inlet case: make sure that there is 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.	X
	If you find damage:
	(1) Do a borescope inspection of the HPC blades (Ref. AMM TASK 72-31-00-290-002).		X
	NOTE: Engine removal can be necessary to do this task (Ref. AMM TASK 71-00-00-000-042).			X
	(2) Do a borescope inspection of the LPC blades (Ref. AMM TASK 72-21-00-290-003).		X
	NOTE: Engine removal can be necessary to do this task (Ref. AMM TASK 71-00-00-000-042).			X
	(3) 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: Engine removal can be necessary to do this task (Ref. AMM TASK 71-00-00-000-042).			X

Subtask 05-51-17-210-052-G ** ON A/C NOT FOR ALL

I. Inspection of the Pylons and Nacelles

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

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

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

Primary Structure ** 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) Remove the access doors of the primary structure (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 of the damaged area to see the internal damage.		X
	(b) Remove the access doors of the primary structure (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. 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
2.	Inspection of the Nacelles
A.	(1) Examine the nacelle external surface cowls (inlet, fan cowl doors, thrust reverser, nozzle, 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, impacts).	X
B.	Open the fan cowl doors and examine (Ref. AMM TASK 71-13-00-010-802) : - the internal side of the doors - the locators - the Hold Open Rod - the hinges and latch fittings - the inlet flange with the engine for: - failures, cracks, signs of buckling and permanent deformations - pulled, bent or loose rivets or fasteners.	X
	If you find damage: (1) Examine the adjacent areas and the adjacent structure of the damaged parts for cracks, failures, damaged fasteners or any composite delamination or damage. (2) Examine the structure adjacent to the aft bulkhead for cracks, failures or damaged fasteners.		X
C.	Open the thrust reverser cowl doors and examine (Ref. AMM TASK 78-36-00-010-802): - 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 (including the thermal blankets), - the interface between nozzle and engine, - the interface between centerbody and engine, for: failures, bearing, cracks, permanent deformations or fasteners damages.	X
	If you find damage: (1) Examine the adjacent areas and adjacent structure of the damaged parts for cracks, failures or damaged fasteners and composite delamination or damage. (2) Examine the nozzle skin and centerbody skin 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: - stop and replace the thrust reverser.		X
	(2) If the thrust reverser is correctly deployed, examine: - the blocker door, - the blocker door hinges, - the drag links, - the cascades, - the translating sleeves, for: cracks, failure, damaged fasteners or any composite damage or delamination.	X
E.	If there is no damage, stow 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) (Ref. AMM TASK 78-36-00-410-802)	X

Subtask 05-51-17-210-064-F ** ON A/C NOT FOR ALL

J. Inspection of the Engine
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 05-51-17-210-053-A

K. Inspection of the Horizontal Stabilizer

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Wing center box (RIB3)
A.	Examine the top and bottom skin panels and actuator fittings, the ribs and the spar rivets for: - Distortion, cracks, pulling, tears and damaged paintwork.	X
	If you find damage:
	(1) Examine the rear spar web on each side of the pivot bearing fittings for: - distortion, cracks, pulled or torn fasteners and damaged paintwork.		X
	(2) Examine the hydraulic lines, mechanical linkages, electrical looms and their mounts for : - distortion, cracks, rupture and fluid leakage.		X

Subtask 05-51-17-210-054-A

L. Inspection of the Vertical Stabilizer

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Primary Structure of the Vertical Stabilizer
A.	Examine the primary structure externally for distortion, cracks, pulled or torn fasteners and damaged paintwork. If you find damage:	X
	(1) Open the access panels and examine the attachment fittings and their adjacent structure for: - distortion, cracks, pulled or torn fasteners and damaged paintwork.		X
	(2) Examine the front and rear spar webs for: - distortion, cracks, pulled or torn fasteners and damaged paintwork.		X
	(3) On the rear spar, examine the hydraulic lines, mechanical linkages, electrical looms and their mounts for: - distortion, cracks, rupture and fluid leakage.		X

Subtask 05-51-17-210-055-A ** ON A/C NOT FOR ALL

M. Inspection of the Wings and Flight Control Surfaces

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Skin Panels
A.	Do an inspection of the skin panels to make sure that there is (are) no: - distortion or damage, - cracks, tears or fuel leaks. If you find damage:	X
	(1) Defuel the tanks (Ref. AMM TASK 28-25-00-650-001).		X
	(2) Get access to the wing tanks (Ref. AMM TASK 28-10-00-910-002).		X
	(3) Examine the front spar, the rear spar, the ribs, the skin panels and the skin panel joints. Make sure that: - there is no distortion, - there are no cracks and the skin panels are correctly attached.		X
	(4) Examine the internal structure and the fasteners. Make sure that: - there is no damage or distortion, - the sealant beads are in good condition, - there are no pulled fasteners.		X
	(5) Examine the attachment fittings of the engine pylon. Make sure that: - there is no distortion, - there are no cracks, - the components are correctly attached.		X
	(6) On the front and rear spars, examine the ducts, lines, cables, mechanical linkages and their installation. Make sure that: - there is no distortion, - there are no cracks, - there are no leaks, - the components are correctly attached.		X
	(7) Close access to the wing tanks (Ref. AMM TASK 28-10-00-910-002).
2.	Flaps and Slats
A.	Examine the slats, flaps and fairing. Make sure that there is (are) no: - distortion, - cracks or pulled fasteners, - damage.	X
3.	Ailerons
A.	Examine the ailerons. Make sure that there is (are) no: - damage or distortion, - cracks or pulled fasteners. If you find damage:	X
	(1) Examine the aileron hinges and actuator: Make sure that there is (are) no: - cracks, - damage or distortion.		X

Subtask 05-51-17-210-055-B ** ON A/C NOT FOR ALL

M. Inspection of the Wings and Flight Control Surfaces

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Skin Panels
A.	Do an inspection of the skin panels to make sure that there is (are) no: - distortion or damage, - cracks, tears or fuel leaks. If you find damage:	X
	(1) Defuel the tanks (Ref. AMM TASK 28-25-00-650-001).		X
	(2) Get access to the wing tanks (Ref. AMM TASK 28-10-00-910-002).		X
	(3) Examine the front spar, the rear spar, the ribs, the skin panels and the skin panel joints. Make sure that: - there is no distortion, - there are no cracks and the skin panels are correctly attached.		X
	(4) Examine the internal structure and the fasteners. Make sure that: - there is no damage or distortion, - the sealant beads are in good condition, - there are no pulled fasteners.		X
	(5) Examine the attachment fittings of the engine pylon. Make sure that: - there is no distortion, - there are no cracks, - the components are correctly attached.		X
	(6) On the front and rear spars, examine the ducts, lines, cables, mechanical linkages and their installation. Make sure that: - there is no distortion, - there are no cracks, - there are no leaks, - the components are correctly attached.		X
	(7) Close access to the wing tanks (Ref. AMM TASK 28-10-00-910-002).
2.	Flaps and Slats
A.	Examine the slats, flaps and fairing. Make sure that there is (are) no: - distortion, - cracks or pulled fasteners, - damage.	X
3.	Ailerons
A.	Examine the ailerons. Make sure that there is (are) no: - damage or distortion, - cracks or pulled fasteners. If you find damage:	X
	(1) Examine the aileron hinges and actuator: Make sure that there is (are) no: - cracks, - damage or distortion.		X
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 05-51-17-210-068-A

N. Inspection of the Cockpit and Cabin Equipment/Furnishings and the Cargo Compartments

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
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 05-51-17-410-050-A

O. Close Access
(1) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001).
(2) Make sure that the work area is clean and clear of tools and other items.
(3) Close all the panels and doors that you opened for the inspection.

Subtask 05-51-17-866-052-A

P. Retraction of the Flaps and Slats
(1) Retract the flaps (Ref. AMM TASK 27-50-00-866-009).
(2) Retract the slats (Ref. AMM TASK 27-80-00-866-005).

Subtask 05-51-17-710-050-B ** ON A/C NOT FOR ALL

Q. Operational Test of the System

ITEM	INSPECTION TASKS	PHASE 2
	NOTE: These tests are only necessary if damage was found during the inspection on the structure adjacent to: - a flight control surface, - a cowl.
1.	Do an operational test of the ailerons. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-14-00-710-001).	X
2.	Do an operational test of the rudder. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-24-00-710-001).	X
3.	Do an operational test of the elevators. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-34-00-710-001).	X
4.	Do an operational test of the trimmable horizontal stabilizer. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-44-00-710-002).	X
5.	Do an operational test of the flaps. Make sure that the movement is full and free (there is no fouling and binding) (Ref. AMM TASK 27-54-00-710-001).	X
6.	Do an operational test of the spoilers. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-64-00-710-001).	X
7.	Do an operational test of the slats. Make sure that the movement is full and free (there is no fouling and binding) (Ref. AMM TASK 27-84-00-710-001).	X
8.	Do an operational test of the thrust reverser system. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 78-31-00-710-040).	X

Subtask 05-51-17-710-050-C ** ON A/C NOT FOR ALL

Q. Operational Test of the System

ITEM	INSPECTION TASKS	PHASE 2
	NOTE: These tests are only necessary if damage was found during the inspection on the structure adjacent to: - a flight control surface, - a cowl.
1.	Do an operational test of the ailerons. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-14-00-710-001).	X
2.	Do an operational test of the rudder. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-24-00-710-001).	X
3.	Do an operational test of the elevators. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-34-00-710-001).	X
4.	Do an operational test of the trimmable horizontal stabilizer. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-44-00-710-002).	X
5.	Do an operational test of the flaps. Make sure that the movement is full and free (there is no fouling and binding) (Ref. AMM TASK 27-54-00-710-001).	X
6.	Do an operational test of the spoilers. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-64-00-710-001).	X
7.	Do an operational test of the slats. Make sure that the movement is full and free (there is no fouling and binding) (Ref. AMM TASK 27-84-00-710-001).	X
8.	Do an operational test of the thrust reverser system. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 78-31-00-710-041).	X

Subtask 05-51-17-710-050-D ** ON A/C NOT FOR ALL

Q. Operational Test of the System

ITEM	INSPECTION TASKS	PHASE 2
	NOTE: These tests are only necessary if damage was found during the inspection on the structure adjacent to: - a flight control surface, - a cowl.
1.	Do an operational test of the ailerons. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-14-00-710-001).	X
2.	Do an operational test of the rudder. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-24-00-710-001).	X
3.	Do an operational test of the elevators. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-34-00-710-001).	X
4.	Do an operational test of the trimmable horizontal stabilizer. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-44-00-710-002).	X
5.	Do an operational test of the flaps. Make sure that the movement is full and free (there is no fouling and binding) (Ref. AMM TASK 27-54-00-710-001).	X
6.	Do an operational test of the spoilers. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-64-00-710-001).	X
7.	Do an operational test of the slats. Make sure that the movement is full and free (there is no fouling and binding) (Ref. AMM TASK 27-84-00-710-001).	X
8.	Do an operational test of the thrust reverser system. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 78-31-00-710-805).	X

Subtask 05-51-17-710-050-E ** ON A/C NOT FOR ALL

Q. Operational Test of the System

ITEM	INSPECTION TASKS	PHASE 2
	NOTE: These tests are only necessary if damage was found during the inspection on the structure adjacent to: - a flight control surface, - a cowl.
1.	Do an operational test of the ailerons. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-14-00-710-001).	X
2.	Do an operational test of the rudder. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-24-00-710-001).	X
3.	Do an operational test of the elevators. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-34-00-710-001).	X
4.	Do an operational test of the trimmable horizontal stabilizer. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-44-00-710-002).	X
5.	Do an operational test of the flaps. Make sure that the movement is full and free (there is no fouling and binding) (Ref. AMM TASK 27-54-00-710-001).	X
6.	Do an operational test of the spoilers. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 27-64-00-710-001).	X
7.	Do an operational test of the slats. Make sure that the movement is full and free (there is no fouling and binding) (Ref. AMM TASK 27-84-00-710-001).	X
8.	Do an operational test of the thrust reverser system. Make sure that the movement is full and free (there is no fouling or binding) (Ref. AMM TASK 78-31-00-710-042).	X

5. Close-up
Subtask 05-51-17-942-054-A

A. Put the aircraft back to its initial configuration.
(1) Remove the WARNING NOTICE(S).
(2) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

[Rev.10 from 2021] 2026.04.01 04:14:11 UTC