Inspections After a Hard Landing or a Hard Overweight Landing for Aircraft with FDIMU Load Report 15 included in Software 10TVSW2 or 10TVSW5

TASK 05-51-11-200-004-C
Inspections After a Hard Landing or a Hard Overweight Landing for Aircraft with FDIMU Load Report 15 included in Software 10TVSW2 or 10TVSW5

1. Reason for the Job
After a Flight Crew Report (FCR) of a hard landing or a hard overweight landing,or after the generation of load report 15 (trigger code 4XXX), you must:

Do an analysis of the landing parameters.
If necessary, do the subsequent steps.
After a FCR of a hard landing or a hard overweight landing, if load report 15 or the Digital Flight Data Recorder (DFDR)/Quick Access Recorder (QAR) data tells you that the landing was not hard, no inspection is necessary.

NOTE: This AMM task is only applicable for aircraft with the Flight Data Interface and Management Unit (FDIMU) installed with following software and subsequent version:

10TVSW2 PN D13SACFXXXXXXXX
10TVSW2 PN D14SACFXXXXXXXX
10TVSW2 PN D16SAFCXXXXXXXX
10TVSW2 PN D18SAFCXXXXXXXX
10TVSW2 PN D19SACFXXXXXXXX
10TVSW5 PN 263321489-0195

To know the PNs of the Data Management Unit (DMU)/FDIMU and related software, you can refer to the Line Replaceable Unit (LRU) identification page or Illustrated Parts Catalog (IPC) 31-36-08.

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

REFERENCE	QTY	DESIGNATION
No specific	AR	ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE
No specific	AR	WARNING NOTICE(S)

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
312AR, 321AL, 322AL, 322CL, 323AL, 323AR, 325AL, 325AR
471AL, 471CL, 482AR, 482CR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 07-11-00-581-001-A	Lifting for Aircraft Maintenance Operations
TASK 07-11-00-581-003-A	Lifting of the Aircraft at the Forward Jacking Point, MLG Wheels on the Ground
TASK 07-11-00-586-002-A	Lowering of the Aircraft for Maintenance Operations
TASK 12-14-32-614-003-A	Functional Check of MLG Shock Absorber Charge Pressure
TASK 12-14-32-614-004-A	Check of the NLG Shock Absorber Charge-Pressure
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 25-11-00-200-001-A	Inspection/Check of the Cockpit Seats
TASK 25-21-00-210-001-A	Detailed Inspection of Seat Attachments, Seat Structure, Seat Belts, Buckles and Baggage Bar
TASK 25-22-00-210-001-A	Detailed Inspection of Cabin Attendant Seat Attachments, Seat Structure and Seat Belt (Including Seat Belt Attachments and Buckles)
TASK 25-50-00-200-002-A	Visual Check of Cargo Compartment Decompression, Lining, Floor Panels and Pressure Compensation Valve (as far as Visible, if ACT(s) or Sliding Carpet System Installed)
TASK 27-24-00-710-001-A	Operational Test of the Rudder Hydraulic Actuation
TASK 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 27-54-00-200-001-A	Detailed Visual Inspection of the Transmission Assembly
TASK 27-54-00-710-001-A	Operational Test of the Flap System
TASK 27-60-00-866-002-A	Extension-Retraction of the Spoilers for Maintenance
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 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 32-11-00-200-005-A	Inspection of the MLG after the Aircraft has gone off the Runway
TASK 32-11-00-200-006-A	Inspection of the MLG Axles after the Aircraft has gone off the Runway
TASK 32-11-00-220-004-A	Inspection of the MLG Side Stay Attachment Lug(s) after the Aircraft has gone off the Runway
TASK 32-11-11-000-001-A	Removal of the MLG Leg Assembly
TASK 32-11-11-400-001-A	Installation of the MLG Leg Assembly
TASK 32-11-13-000-001-A	Removal of the MLG Shock Absorber
TASK 32-11-13-400-001-A	Installation of the MLG Shock Absorber
TASK 32-11-16-000-001-A	Removal of the MLG Side-Stay Assembly - Pre-EV MLG
TASK 32-11-16-000-001-A-01	Removal of the MLG Side Stay Assembly - Post-EV MLG
TASK 32-11-16-400-001-A	Installation of the MLG Side-Stay Assembly - Pre-EV MLG
TASK 32-11-16-400-001-A-01	Installation of the MLG Side Stay Assembly - Post-EV MLG
TASK 32-11-17-000-001-A	Removal of the MLG Lock Stay
TASK 32-11-17-400-001-A	Installation of the MLG Lock Stay
TASK 32-11-21-000-001-A	Removal of the MLG Lockstay Actuating-Cylinder
TASK 32-11-21-000-001-A-02	Removal of the MLG Lockstay Actuating-Cylinder
TASK 32-11-21-400-001-A	Installation of the MLG Lockstay Actuating Cylinder
TASK 32-11-21-400-001-A-02	Installation of the MLG Lockstay Actuating Cylinder
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 32-21-00-200-006-A	Inspection/Check of the Barrel/Drag strut connection
TASK 32-21-11-000-003-A	Removal of the NLG Leg Assembly
TASK 32-21-11-400-003-A	Installation of the NLG Leg Assembly
TASK 32-21-13-000-001-A	Removal of the NLG Shock Absorber Assy
TASK 32-21-13-000-001-A-01	Removal of the NLG Shock Absorber Assy (with nose jacking only)
TASK 32-21-13-400-001-A	Installation of the NLG Shock Absorber Assy
TASK 32-21-13-400-001-A-01	Installation of the NLG Shock Absorber Assy (with nose jacking only)
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 32-21-17-000-001-A	Removal of the NLG Lockstay Assy
TASK 32-21-17-400-001-A	Installation of the NLG Lockstay Assy
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 32-31-00-720-002-A	Functional Test of the Normal Extension and Retraction of the Landing Gear
TASK 32-31-22-000-001-A	Removal of the NLG Actuating Cylinder
TASK 32-31-22-400-001-A	Installation of the NLG Actuating Cylinder
TASK 32-31-46-000-001-A	Removal of the MLG Actuating Cylinder
TASK 32-31-46-400-001-A	Installation of the MLG Actuating Cylinder
TASK 32-33-00-720-001-A	Functional Check of Free-Fall Extension
TASK 32-41-00-210-002-A	Inspection/Check of the Wheels and Tires
TASK 32-41-12-000-001-A	Removal of the NLG Wheel
TASK 32-41-12-000-002-A	Removal of the Axle Sleeve
TASK 32-41-12-400-001-A	Installation of the NLG Wheel
TASK 32-41-12-400-002-A	Installation of the Axle Sleeve
TASK 35-23-00-710-001-A	Operational Check of Manual Mask Release
TASK 53-45-11-000-001-A	Removal of the Dorsal Fin
TASK 53-45-11-400-001-A	Installation of the Dorsal Fin
TASK 53-51-00-210-012-A	Detailed Inspection of Fin to Fuselage, Forward, MID and AFT Attach Fittings, Outside Fuselage, LH/RH
TASK 53-51-00-210-018-A	General Visual Inspection of Fuselage External Surface and Vertical Stabilizer Attachment Fitting, underneath Vertical Stabilizer/Fuselage Fairings
TASK 53-51-00-210-020-A	General Visual Inspection of the Rear Fuselage Internal Structure, between FR70 and FR77
TASK 53-55-11-000-001-A	Removal of the Vertical Stabilizer Fairings
TASK 53-55-11-400-001-A	Installation of the Vertical Stabilizer Fairings
TASK 53-55-12-000-001-A	Removal of the Rudder Fairings
TASK 53-55-12-400-001-A	Installation of the Rudder Fairings
TASK 54-51-17-000-001-A	Removal of the Pylon-to-Wing Forward Attach-Fitting at RIB4
TASK 54-51-17-000-002-A	Removal of the Pylon-to-Wing Aft Attach-Fitting at RIB10
TASK 54-51-17-000-804-A	Removal of the Pylon-to-Wing Forward Attach-Fitting at RIB5
TASK 54-51-17-000-805-A	Removal of the Pylon-to-Wing Aft Attach-Fitting at RIB10
TASK 54-51-17-200-001-A	Inspection of the Pylon-to-Wing Forward Attach-Fitting
TASK 54-51-17-200-002-A	Inspection of the Pylon-to-Wing Aft Attach-Fitting
TASK 54-51-17-200-003-A	Inspection of the Shackles at RIB4 and the Spigot
TASK 54-51-17-200-004-A	Inspection of the Shackles at RIB10
TASK 54-51-21-000-001-A	Removal of the Pylon Lateral Access-Doors
TASK 54-51-21-000-802-A	Removal of the Pylon Lateral Access-Doors
TASK 54-51-21-400-001-A	Installation of the Pylon Lateral Access-Doors
TASK 54-51-21-400-802-A	Installation of the Pylon Lateral Access-Doors
TASK 54-53-11-000-002-A	Removal of the Pylon-to-Wing Access Panels
TASK 54-53-11-000-002-B	Removal of the Pylon-to-Wing Access Panels
TASK 54-53-11-000-804-A	Removal of the Pylon-to-Wing Access Panels and Doors
TASK 54-53-11-400-002-A	Installation of the Pylon-to-Wing Access Panels
TASK 54-53-11-400-002-B	Installation of the Pylon-to-Wing Access Panels
TASK 54-53-11-400-804-A	Installation of the Pylon-to-Wing Access Panels and Doors
TASK 55-10-00-210-001-A	Detailed Inspection of Horizontal Stabilizer, Internal Structure of Torque Box, Inboard of Fuselage Fairings
TASK 55-16-00-200-001-A	Detailed Inspection of Horizontal Stabilizer, Rear support fittings, Upper and Lower Attach Fittings and Surrounding External Structure, LH/RH
TASK 55-30-00-200-001-A	Detailed Inspection of Vertical Stabilizer, Center Box, Internal Structure as far as Visible, Front Spar Forward Face and Upper Closing Rib, Upper Surface
TASK 55-30-00-210-001-A	Detailed Inspection of Rudder Hinge Arm 1, 2, 3, 4 and 5 and Fin Actuator Fittings (Actuator 1, 2 and 3)
TASK 55-30-00-210-002-A	Detailed Inspection of Rudder Hinge Arm 6 and 7
TASK 55-32-11-000-001-A	Removal of the Vertical Stabilizer Leading-Edge
TASK 55-32-11-400-001-A	Installation of the Vertical Stabilizer Leading-Edge
TASK 55-33-13-010-002-A	Opening/Removal of the Trailing Edge Access-Panels of the Vertical Stabilizer
TASK 55-33-13-410-002-A	Closing/Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer
TASK 55-36-00-210-001-A	Detailed Inspection of Vertical Stabilizer, Attach Fittings, Including Load Introduction Area at Skin Panels
TASK 55-40-00-210-004-A	Detailed Inspection of Rudder Attach Fitting 1, 2, 3, 4 and 5 and Rudder Actuator Attach Fittings (Actuator 1, 2 and 3)
TASK 55-40-00-210-005-A	Detailed Inspection of Rudder Attach Fitting 6 and 7
TASK 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 71-00-51-000-802-A	Removal of the Power Plant (Bootstrap Method)
TASK 71-00-51-000-802-A-01	Removal of the Power Plant (JacXson Method)
TASK 71-13-00-010-040-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 71-13-00-410-040-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 71-22-11-210-042-A	Detailed Inspection of Aft Engine Mount Installation
TASK 71-22-11-210-042-B	Detailed Inspection of Aft Engine Mount Installation
TASK 72-00-00-200-003-A	Procedure After the Engine has Exceeded the Operational Limits
TASK 72-00-00-200-008-A	Inspection/Check After the Engine has Exceeded the Operational Limits
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 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 78-31-00-710-042-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 78-32-00-860-802-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
Hard Landing or Hard-Overweight Landing Category for Aircraft with latest FDIMU ** ON A/C NOT FOR ALL
Flow Chart for the Aircraft with Enhanced latest DMU/FDIMU ** ON A/C NOT FOR ALL
Nose Landing-Gear Leg ** ON A/C NOT FOR ALL
Nose Landing Gear ** ON A/C NOT FOR ALL
Illustration of the Main Landing Gear ** ON A/C NOT FOR ALL
Main Landing-Gear Leg ** 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
Exhaust Nozzle: Engine Interface ** 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
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
Engine-to-Pylon Attach Fittings ** ON A/C NOT FOR ALL
Pylon-to-Wing Attach Fittings ** ON A/C NOT FOR ALL
MLG Forward Lug Area ** ON A/C NOT FOR ALL
Lower Part of the Center Fuselage ** ON A/C NOT FOR ALL
Center Section ** ON A/C NOT FOR ALL
Component Location in the Belly Fairing Structure ** ON A/C NOT FOR ALL
Main Structure of the Cone/Rear Fuselage ** ON A/C NOT FOR ALL
Inspection Areas of the Vertical Tail Plane (VTP) after a Drift Landing ** ON A/C NOT FOR ALL
Rudder and Actuator Attach-Fittings ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 05-51-11-210-173-A ** ON A/C NOT FOR ALL

A. Inspection Requirements for a Hard Landing or a Hard Overweight Landing
(1) Definitions

The assessment of a hard landing or hard overweight landing is based on the following parameters:

Nz kpi: This indicator is computed based on the following parameters extracted around first and second (if any) touchdown times: vertical acceleration, aircraft gross weight and roll angle.
Ny kpi: This indicator of lateral acceleration at first and second (in case of a bounce landing) touchdown.
The landing events are then classified according to the severity as hard landing/hard overweight landing (Amber zone) or severe hard landing/severe hard-overweight landing (Red zone).
The classification is made with the values of the computed Nz kpi/Ny kpi and summed up by the load report 15 trigger code:
Hard Landing or Hard-Overweight Landing Category for Aircraft with latest FDIMU ** ON A/C NOT FOR ALL

(a) Hard landing (Amber zone): Hard landing is a landing during which 1.80 <= Nz kpi <= 2.06 or 0.45 <= Ny kpi <= 0.5. The associated LR15 trigger codes are 4520or 4620.
(b) Hard overweight landing (Amber zone): It is a landing during which 1.80 <= Nz kpi <= 2.06 or 0.45 <= Ny kpi <= 0.5. The associated LR15 trigger codes are 4420or 4320.
(c) Severe hard landing (Red zone): It is a landing during which Nz kpi >= 2.06 or Ny kpi >= 0.5. The associated LR15 trigger codes are 4510 or 4610.
(d) Severe hard-overweight landing (Red zone): It is a landing during which Nz kpi >= 2.06 or Ny kpi >= 0.5. The associated LR15 trigger codes are 4410 or 4310.
(e) Normal landing (Green zone): It is a landing during which Nz kpi < 1.80 and Ny kpi < 0.45. The associated LR15 trigger codes are 7XXX.
For more details, refer to DMU load report<15> (Ref. AMM TASK 31-37-00-200-001).

(f) High pitch-rate de-rotation-landing is not given by Aircraft Condition Monitoring System (ACMS) LR15. A high pitch-rate de-rotation-landing is a landing during which the de-rotation is too fast. In this condition:

You must not use load report 15 to confirm a high pitch-rate de-rotation.
You must send the data of the event to Airbus.

(2) Confirmation of a hard landing or a hard overweight landing
(a) If the flight crew think that there was a hard landing or a hard overweight landing, it is its responsibility to make a report.
(b) After a crew report of a hard landing or a hard overweight landing or after the generation of a load report 15 (trigger code 4XXX):
You must extract the LR15 and do the analysis of the trigger code or Nz kpi / Ny kpi indicator according to the classification given above to find the category of the landing.

Flow Chart for the Aircraft with Enhanced latest DMU/FDIMU ** ON A/C NOT FOR ALL

1 If the category of the landing is a hard landing or a hard overweight landing (Amber zone):
You must do the inspections for that category.
2 If the category of the landing is a severe hard landing or a severe hard-overweight landing (Red zone), you must:
a Do the inspections for that category.
b Send the raw data from the DFDR or from the QAR to Airbus.
c Send the data about the event and inspection results to Airbus.
d Contact Airbus for technical instructions.
e Obey the Airbus instructions before the next flight.
(c) If the pilots reported a hard landing event but you cannot find the category of the landing due to unavailability of the load report 15, contact Airbus and send the raw data of the event from the DFDR or from the QAR to Airbus.
1 If you cannot confirm the category of the landing with the DMU/FDIMU load report 15 and if the QAR or DFDR data cannot be downloaded immediately:
a You must do the inspection after a severe hard landing or a severe hard-overweight landing (Red zone):

If you do not find damage during this inspection, the temporary return-to-service of the aircraft is possible. Make sure that the category of the hard landing is correct in the next 200 flight cycles / 30 days maximum.

b In the shortest possible period, and in less than 200 Flight cycles / 30 days, send the raw data from the DFDR or from the QAR to Airbus. This is to find the category of the hard landing.

If the landing is a hard landing or a hard overweight landing, no more inspections are necessary.
If the landing is a severe hard landing or a severe hard-overweight landing, obey the Airbus instructions before the next flight.

(3) Inspection preparation
(a) We recommend that you get information from the flight crew about the landing conditions, for example:

A touchdown straight, drifting, wing low, tail or nose heavy
A touchdown on the main gears or on the main and nose gears or a high pitch-rate de-rotation on the nose gear

NOTE: Three touchdown configurations are possible:

A hard touchdown on the main gears only
A touchdown on the nose gear only or a high pitch-rate de-rotation
A touchdown on the nose and main gears.

The weight of the aircraft
The quantity of fuel in each tank
The instrument indications
Other information, for example noise that can be related to a structural failure.

(b) After a hard touchdown on the main gears only, the inspection of the nose gear area is not necessary.
(c) After a touchdown on the nose gear only or a high pitch-rate de-rotation:

Only the inspection of the nose gear and the Nose Landing Gear (NLG) section of the fuselage area is necessary.
Send the raw data from the DFDR or from the QAR to Airbus.
Send the data about the event and the inspection results to Airbus.
Contact Airbus for technical instructions.
Obey the Airbus instructions before the next flight.

(d) After a touchdown on the nose and main gears:

The full inspection is necessary.
Send the raw data from the DFDR or from the QAR to Airbus.
Send the data about the event and the inspection results to Airbus.
Contact Airbus for technical instructions.
Obey the Airbus instructions before the next flight.

(e) After a drift landing:

Refer to the touchdown configuration and obey the applicable requirements given in paragraphs 3.A.(3)(a) and (b) or (c) or (d).
Do the special access procedure for the inspection after a drift landing.
Do the special inspections of the rear fuselage and the vertical tail plane after a drift landing.

NOTE: The last inspection paragraph gives the necessary inspections after a drift landing.

(f) We recommend that you get the Post Flight Report (PFR) related to a hard landing or a hard overweight landing.
(g) You must also do all the additional checks related to the events given in the FCR the PFR.

Subtask 05-51-11-481-070-A ** ON A/C NOT FOR ALL

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

Subtask 05-51-11-866-056-A ** ON A/C NOT FOR ALL

C. Extension of the Flight Control Surfaces
(1) Extend the flaps (Ref. AMM TASK 27-50-00-866-008).
(2) Extend the slats (Ref. AMM TASK 27-80-00-866-004).
(3) Extend the spoilers (Ref. AMM TASK 27-60-00-866-002).

Subtask 05-51-11-010-057-A ** ON A/C NOT FOR ALL

D. Get Access
(1) Open the main gear doors and install the safety devices (Ref. AMM TASK 32-12-00-010-001).
(2) Open the nose gear doors and install the safety devices (Ref. AMM TASK 32-22-00-010-001).

Subtask 05-51-11-010-058-A ** ON A/C NOT FOR ALL

E. Special Access for the Inspection after a Drift Landing
(1) Put the WARNING NOTICE(S) in position to tell persons not to operate the flight controls.
(2) Put the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE in position at Zone 320.
(3) Open access door 312AR.
(4) Remove vertical stabilizer fairings 323AL and 323AR (Ref. AMM TASK 53-55-11-000-001).
(5) Remove dorsal fin 321AL (Ref. AMM TASK 53-45-11-000-001).
(6) Remove rudder fairings 325AL and 325AR (Ref. AMM TASK 53-55-12-000-001).
(7) Remove leading-edge access panels 322AL and 322CL of the vertical stabilizer (Ref. AMM TASK 55-32-11-000-001).
(8) Open the trailing-edge access panels of the vertical stabilizer (Ref. AMM TASK 55-33-13-010-002).

Subtask 05-51-11-860-055-A ** ON A/C NOT FOR ALL

F. Aircraft Maintenance Configuration
(1) Make sure that the electrical circuits are de-energized (Ref. AMM TASK 24-41-00-862-002).
(2) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-00-00-864-001).
(3) Put WARNING NOTICE(S) in the cockpit to tell persons not to operate the systems.
(4) Put the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE in position.

4. Procedure
Subtask 05-51-11-210-174-A ** ON A/C NOT FOR ALL

A. General Inspection Recommendations

NOTE: All the inspections are visual unless specified differently in the text. Operators can refer to the Nondestructive Testing Manual (NTM) and use the non-destructive procedures.

(1) If you find damage during an inspection and if it is necessary to disconnect or remove components (pipes, ducts, cables, electrical connectors and mechanic linkages), do a functional test of the related system after re-assembly.
(2) If it is necessary to open or remove the access panels and the doors, examine them. Make sure that:

They are aligned correctly
They have no distortion or cracks
The paint is not damaged
All fasteners and safety devices are in the correct position.

(3) If there is damage to the aircraft structure, refer to the Structural Repair Manual (SRM). The SRM has the approved damage limits and repair procedures.

Subtask 05-51-11-210-175-A ** ON A/C NOT FOR ALL

B. General Inspection

(1) Do a walk around inspection of the aircraft.

(2) Make sure that you cannot see damage and fluid leaks.

(3) Carefully examine the landing gears, the wheels, the tires and the brake units.

Subtask 05-51-11-210-176-A ** ON A/C NOT FOR ALL

C. Inspection of the NLG

NOTE: This inspection is applicable if there was a hard landing/hard overweight landing (Amber zone) or a severe hard landing/severe hard-overweight landing (Red zone) on:

The nose gear only (high pitch-rate de-rotation) or
The nose and main gears.

The NLG inspection is not necessary after a hard landing/hard overweight landing touchdown on the MLG only.

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
1.	Inspection of the NLG
A.	Lift the aircraft: - On the forward jacking point only (Ref. AMM TASK 07-11-00-581-003) or - On the 3 jacking points (Ref. AMM TASK 07-11-00-581-001).	X
B.	(1) Make sure that the shock absorber extends fully and smoothly. Measure dimension H: Nose Landing-Gear Leg ** ON A/C NOT FOR ALL - The dimension must be between 447 mm (17.5984 in.) and 451 mm (17.7559 in.).	X
	(2) If the shock absorber does not extend fully and smoothly or if dimension H is not in the specified limits:
	- Contact Airbus for more instructions before the next flight.		X
C.	Do a check of the pressure in the shock absorber (Ref. AMM TASK 12-14-32-614-004). If you find an unsatisfactory condition:	X
	(1) Remove the shock absorber assembly for overhaul (Ref. AMM TASK 32-21-13-000-001).		X
D.	Do a visual inspection of the wheels for distortion, cracks and damaged paintwork. If you find damage:	X
	(1) Remove the wheels (Ref. AMM TASK 32-41-12-000-001).		X
	(2) Remove the axle sleeve (Ref. AMM TASK 32-41-12-000-002).		X
	(3) Do a visual inspection of the axle and sleeve for damage. If you find damage:		X
	(a) Remove the NLG leg assembly for overhaul (Ref. AMM TASK 32-21-11-000-003).			X
E.	Examine the NLG and all the components installed on it for: - Cracks - Scores - Tears - Rupture - Leakage - Damaged paintwork. Examine the attachment fittings on the NLG. Examine the hydraulic lines and the electrical harnesses for the correct condition. If you find damage in the avionics compartment, examine:	X
	(1) The gear well roof, the roof-to-sidewall joint and the floor support-strut attach-fittings for: - Distortion - Pulled or damaged fasteners - Damaged paintwork.		X
F.	Make sure that you can install the NLG safety lock easily.	X
G.	Examine the shock absorber sliding-rod (the part that you can see) for blue color, signs of bronze, chrome damage or external oil leaks. If you find damage:	X
	(1) Remove the shock absorber assembly for overhaul (Ref. AMM TASK 32-21-13-000-001) (refer to the manufacturer's instructions for the overhaul procedure).		X
H.	Examine the drag strut assembly and its attachment fittings for distortion, cracks and damaged paintwork. If you find damage:	X
	(1) Remove the drag strut assembly for overhaul (Ref. AMM TASK 32-21-16-000-002) (refer to the manufacturer's instructions for the overhaul procedure).		X
	(2) On the aircraft, examine the attachment fitting for damage.		X
	(3) Examine the drag strut attachment-lugs on the NLG leg and measure the distance between them (Ref. AMM TASK 32-21-00-200-006). If you find damage:		X
	(a) Remove the NLG leg assembly (Ref. AMM TASK 32-21-11-000-003).			X
J.	Examine the lockstay assembly for distortion, cracks and damaged paintwork. If you find damage:	X
	(1) Remove the lockstay assembly for overhaul (Ref. AMM TASK 32-21-17-000-001) (refer to the manufacturer's instructions for the overhaul procedure).		X
	(2) On the aircraft, examine the attachment fittings for damage.		X
K.	Examine the NLG actuating cylinder and its attachment fittings for distortion, cracks, pulled or damaged fasteners and damaged paintwork. If you find damage:	X
	(1) Remove the actuating cylinder for strip-down inspection (Ref. AMM TASK 32-31-22-000-001) (refer to the manufacturer's instructions for the strip-down inspection).		X
	(2) On the aircraft, continue the inspection of the attachment fittings for damage.		X
L.	If you removed components, install serviceable components: - For the actuating cylinder (Ref. AMM TASK 32-31-22-400-001) - For the lockstay assembly (Ref. AMM TASK 32-21-17-400-001) - For the NLG leg assembly (Ref. AMM TASK 32-21-11-400-003) - For the drag strut assembly (Ref. AMM TASK 32-21-16-400-002) - For the shock absorber assembly (Ref. AMM TASK 32-21-13-400-001) - For the axle sleeve (Ref. AMM TASK 32-41-12-400-002) - For the wheels (Ref. AMM TASK 32-41-12-400-001).

Subtask 05-51-11-210-177-A ** ON A/C NOT FOR ALL

D. Inspection of the NLG Section of the Fuselage

Nose Landing Gear ** ON A/C NOT FOR ALL

ITEM	INSPECTION TASKS	PHASE 2
1.	Fuselage-nose/landing-gear section between FR9 and FR20 NOTE : This inspection is necessary if you found damage during the phase 1 checks of the NLG.
A.	Nose-gear upper-strut attachments (FR14)
	(1) Examine: - The area around the bearing - The attachment of the fitting on FWD frame and roof of the nose wheel well - The link rods.	X
B.	Nose-gear actuating cylinder attachment-fitting (FR20) (1) Examine the attachment of the actuating cylinder fitting to the upper link at FR19 and FR20.	X
C.	Nose-gear leg attachments (FR19) (1) Examine the attachments at FR19 and FR20 and the longitudinal beams.	X

Subtask 05-51-11-210-178-A ** ON A/C NOT FOR ALL

E. Inspection of the Main Landing Gear (MLG)

NOTE: This inspection contains two inspection procedures:

Item 1. Inspection after a hard landing or a hard overweight landing (Amber zone)
Item 2. Inspection after a severe hard landing or a severe hard-overweight landing (Red zone).

If you know the category of the landing, go directly to the necessary inspection.
If you do not know the category, go directly to item 2. Inspection after a severe hard landing or a severe hard-overweight landing (Red zone).

Illustration of the Main Landing Gear ** ON A/C NOT FOR ALL

Main Landing-Gear Leg ** ON A/C NOT FOR ALL

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
1.	Inspection of the MLG after a hard landing or a hard overweight landing (Amber zone) NOTE : You can do this inspection with the aircraft on its wheels or on jacks.
A.	Do a check of the pressure in the MLG shock absorber (Ref. AMM TASK 12-14-32-614-003).	X
B.	Do a visual inspection of the wheels for distortion, cracks, damaged paintwork and correct installation. Examine the side walls of the tires for damage (Ref. AMM TASK 32-41-00-210-002). If you find damage:	X
	(1) Do the inspection of the axle and the axle sleeve for damage and out-of-roundness (Ref. AMM TASK 32-11-00-200-006).		X
C.	Examine: - The MLG and all the components installed on it for cracks, scores, tears, rupture, leakage and damaged paintwork (carefully examine the dragstay blend and the forward pintle-pin area). - The attachment fittings of the MLG.	X
D.	Examine the shock-absorber sliding rod (the part that you can see) for blue color, signs of bronze, chrome damage or external oil leaks. If you find damage:	X
	(1) Remove the shock absorber for overhaul: (Ref. AMM TASK 32-11-13-000-001) (refer to the manufacturer's instructions for the overhaul procedure).		X
E.	Examine the sidestay assembly and its attachment fittings for distortion, cracks, damaged paintwork and chrome plating. If you find damage:	X
	(1) Remove the sidestay assembly for overhaul (Ref. AMM TASK 32-11-16-000-001) (refer to the manufacturer's instructions for the overhaul procedure).		X
	(2) Do the dimensional inspection of the sidestay cardan-pin joint-lugs on the MLG leg (Ref. AMM TASK 32-11-00-220-004). If you find damage:		X
	- Remove the MLG (Ref. AMM TASK 32-11-11-000-001).			X
	(3) On the aircraft, continue the inspection of the sidestay attachment fitting.		X
F.	Examine the lockstay assembly and the lockstay actuator for distortion, cracks, damaged paintwork and chrome plating. If you find damage:	X
	(1) Remove the lockstay assembly and the lockstay actuator for overhaul (Ref. AMM TASK 32-11-17-000-001) (Ref. AMM TASK 32-11-21-000-001) (refer to the manufacturer's instructions for the overhaul procedure).		X
	(2) On the aircraft, continue the inspection of the attachment fittings for damage.		X
G.	Examine the MLG retraction actuator and its attachment fittings for distortion, cracks, damaged paintwork and chrome plating. If you find damage:	X
	(1) Remove the retraction actuator for a strip-down inspection (Ref. AMM TASK 32-31-46-000-001) (refer to the manufacturer's instructions for the strip-down procedure).		X
	(2) On the aircraft, continue the inspection of the attachment fittings for damage.		X
H.	Examine the MLG well for distortion, cracks, pulled or torn fasteners and damaged paintwork.	X
I.	Examine the electrical conduits, connections, connectors and flexible conduits for damage.	X
J.	If you removed components, install serviceable components: - For the retraction actuator (Ref. AMM TASK 32-31-46-400-001) - For the lockstay actuator (Ref. AMM TASK 32-11-21-400-001) - For the lockstay assembly (Ref. AMM TASK 32-11-17-400-001) - For the MLG (Ref. AMM TASK 32-11-11-400-001) - For the sidestay assembly (Ref. AMM TASK 32-11-16-400-001) - For the shock absorber (Ref. AMM TASK 32-11-13-400-001).
2.	Inspection of the MLG after a severe hard landing or a severe hard- overweight landing (Red zone)
A.	Do the inspection of the MLG after a hard landing or a hard overweight landing (Ref. item 1.).	X
B.	Lift the aircraft: (Ref. AMM TASK 07-11-00-581-001).	X
	- Make sure that the extension of the shock absorber is smooth and full. Measure dimension H: Main Landing-Gear Leg ** ON A/C NOT FOR ALL It must be between 483.05 mm (19.018 in.) and 487.85 mm (19.207 in.).	X
	- Examine the sliding rod (the part that you can see) for blue color, signs of bronze or chrome damage.	X
C.	Examine the shock absorber for external leaks.	X
D.	Do a check of the pressure in the MLG shock absorber (Ref. AMM TASK 12-14-32-614-003).	X
E.	Do the inspection of the MLG (Ref. AMM TASK 32-11-00-200-005) for: - Out-of-roundness of the shock absorber sliding-rod - Distortion of the lower cardan-pin joint of the sidestay (with the sidestay disconnected) - Distortion of the torque link pin - Detailed visual inspection of the barrel in the dragstay blend area - Detailed visual inspection of the forward pintle-pin area of the barrel.	X
F.	Do the functional test of the normal Extension/Retraction of the landing gear (Ref. AMM TASK 32-31-00-720-002): - With the MLG door open and the safety lock installed, make sure that the MLG is correctly engaged in the MLG uplock (MLG in the center of the uplock).	X
G.	Do the functional test of the free fall extension of the landing gear (Ref. AMM TASK 32-33-00-720-001).	X
H.	If you find an unsatisfactory condition(s):	X
	(1) Remove the MLG, the sidestay, the lockstay assembly and the lockstay actuator for overhaul (Ref. AMM TASK 32-11-11-000-001) (Ref. AMM TASK 32-11-16-000-001) (Ref. AMM TASK 32-11-17-000-001) (Ref. AMM TASK 32-11-21-000-001) (refer to the manufacturer's instructions for the overhaul procedure).		X
	(2) On the aircraft, examine the attachment fittings and bearings of the sidestay for distortion, cracks and damaged paintwork.		X
	(3) On the aircraft, examine the attachment fittings of the MLG for distortion, cracks and damaged paintwork.		X
	(4) Examine the MLG actuating cylinder and its attachment fitting for distortion, cracks and damaged paintwork. If you find damage:		X
	- Remove the actuating cylinder for a strip-down inspection (Ref. AMM TASK 32-31-46-000-001) (refer to the manufacturer's instructions for the strip-down inspection procedure).			X
	- On the aircraft, continue the inspection of the attachment fitting for damage.			X
	(5) Examine the gear well for distortion, cracks, pulled or torn fasteners and damaged paintwork. (6) If you removed components, install serviceable components: - For the actuating cylinder (Ref. AMM TASK 32-31-46-400-001) - For the lockstay actuator (Ref. AMM TASK 32-11-21-400-001) - For the lockstay assembly (Ref. AMM TASK 32-11-17-400-001) - For the sidestay assembly (Ref. AMM TASK 32-11-16-400-001) - For the MLG (Ref. AMM TASK 32-11-11-400-001).		X
I.	Lower the aircraft on its wheels (Ref. AMM TASK 07-11-00-586-002).	X

Subtask 05-51-11-210-179-A ** ON A/C NOT FOR ALL

F. Inspection of the Nacelles (Ref. AMM TASK 78-32-41-860-001) (Ref. AMM TASK 78-32-41-860-002) (Ref. AMM TASK 78-31-00-710-042)

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

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
1.	Inspection of the nacelles
A.	Examine the nacelle external surface cowls (inlet, fan cowl doors, thrust reverser, nozzle) for: - Failures, cracks, signs of buckling and permanent deformations - Unusual steps and gaps between external cowl interfaces - Pulled, bent or loose rivets or fasteners - Open or loose access covers, latches or panels. Examine the edges of the interfacing cowl parts (leading or trailing edges, cowl edges near the pylon or latching areas) for signs of abutment (paint cracks, delamination, impacts).	X
B.	Open the fan cowl doors and examine Fan Cowl Doors: Hinge and Latch Fittings ** ON A/C NOT FOR ALL - The internal side of the doors for cracks - The locators - The hinges and latch fittings for permanent deformations.	X
	If you find damage, examine: - The fittings for cracks, failures or damaged fasteners - The adjacent area for composite delamination.		X
C.	Open the thrust reverser and examine 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: 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) or (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 78-32-41-860-002) or (Ref. AMM TASK 78-32-41-860-041).		X
	If you find resistance or unusual noises during the manual deployment of the thrust reverser, then stop and replace the damaged hardware.			X
E.	If you find damage on the above parts, examine: - The engine and exhaust nozzle interface for damaged fasteners 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) or (Ref. AMM TASK 78-31-00-710-040).	X

Subtask 05-51-11-210-180-A ** 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 attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components.		X
	If you find damage:
	- Contact Airbus.			X
	(d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001).		X
	(e) Install the access panels and doors on the secondary structure.		X
B.	Open the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-040) and (Ref. AMM TASK 78-36-00-010-040).	X
	(1) Externally examine the lower spar, the pylon lower area (all the items that you can see) and the cantilever structure, the fan cowl fittings and the thrust reverser fittings. Make sure that: - There is/are no buckling, shearing, distortion or cracks - The paint is in the correct condition - There are no pulled or missing fasteners/rivets.	X
	If you find damage:
	(a) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage.		X
	(b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001).		X
	(c) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components.		X
	If you find damage:
	- Contact Airbus.			X
	(d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001).		X
	(e) Install the access panels and doors on the secondary structure.		X
C.	Remove the center fillets from the pylon-to-wing junction (Ref. AMM TASK 54-53-11-000-002). NOTE: This is only applicable for the left and right side panels between RIB4 and RIB5 and at RIB10. This is to make sure that you can see the pylon-to-wing attach fittings and the spigot ball joint.	X
	(1) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 - The pylon-to-wing aft attach-fitting at RIB10 - The spigot ball joint between RIB4 and RIB5. Make sure that there are no signs of distortion, buckling, cracks or other damage.	X
	If you find damage:
	(a) Remove the pylon-to-wing attach fittings (Ref. AMM TASK 54-51-17-000-001) and (Ref. AMM TASK 54-51-17-000-002).		X
	(b) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 (Ref. AMM TASK 54-51-17-200-001) - The shackles at RIB4 and the spigot attach fitting (Ref. AMM TASK 54-51-17-200-003) - The shackles at RIB10 (Ref. AMM TASK 54-51-17-200-004) - The pylon-to-wing aft attach-fitting at RIB10 (Ref. AMM TASK 54-51-17-200-002).		X
	(c) Contact Airbus.		X
D.	Do a visual inspection of the engine mounts (all the items that you can see) for cracks or distortion (Ref. AMM TASK 71-21-11-210-040) and (Ref. AMM TASK 71-22-11-210-042). This includes the inspection of: - The pylon-to-engine forward attach-fitting in the forward area of RIB1 - The pylon-to-engine aft attach-fitting at the bottom of RIB3.	X
	If you find damage:
	(a) Remove the engine (Ref. AMM TASK 71-00-00-000-042) or (Ref. AMM TASK 71-00-00-000-040).		X
	(b) Contact Airbus.		X
E.	- Install the center fillets on the pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002).	X
	- Close the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-410-040) (Ref. AMM TASK 78-36-00-410-040).	X

Subtask 05-51-11-210-181-A ** ON A/C NOT FOR ALL

H. Inspection of the Engine
(1) Do the inspections after a hard landing/hard overweight landing (Amber zone) or a severe hard landing/severe hard-overweight landing (Red zone) (Ref. AMM TASK 72-00-00-200-008) or (Ref. AMM TASK 72-00-00-200-003).

Subtask 05-51-11-210-182-B ** ON A/C NOT FOR ALL

I. Inspection of the Wing

NOTE: This inspection contains two inspection procedures:

Item 1. Inspection after a hard landing or a hard overweight landing (Amber zone).
Item 2. Inspection after a severe hard landing or a severe hard-overweight landing (Red zone).

If you know the category of the landing, go directly to the necessary inspection.
If you do not know the category, go directly to item 2.
Inspection after a severe hard landing or a severe hard-overweight landing (Red zone).

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Inspection of the wing after a hard landing or a hard overweight landing (Amber zone)
A.	Examine the wing top skin from RIB 1 to RIB 10 and from RIB 18 to RIB 20, the shroud panel and its attachment. Make sure that: - There is no distortion - There are no cracks - The paint and the sealant are not damaged - The fasteners are in the correct condition. Carefully examine the fasteners at the rear spar between RIB 3 and RIB 6 and the gear rib.	X
B.	Do an inspection of the wing bottom skin. Carefully examine the areas adjacent to: - The flap beams - The engine pylon - The MLG attachments - The shroud-box outboard seal and the seal support. Make sure that: - There is no distortion - There are no cracks - There are no fluid leaks - The paint and the sealant are not damaged - The fasteners are in the correct condition. Carefully examine the fasteners at the rear spar between RIB 3 and RIB 6 and the gear rib. If there are signs of damage on the wing top or bottom skins.	X
	(1) Defuel the wing (Ref. AMM TASK 28-25-00-650-001).		X
	(2) Get access to the area adjacent to the damage (Ref. AMM TASK 28-10-00-910-002).		X
	(3) Do an internal inspection of: - The applicable ribs, the front and rear spars, the top and bottom skins, the stringers, the riblets, the brackets and the plates.		X
C.	Do a detailed visual inspection of the MLG support rib 5. MLG Forward Lug Area ** ON A/C NOT FOR ALL Examine the lugs for: - Cracks - Damaged paint - Damaged sealant - Bush migration. Examine the upper flange, spar flange and lower flange for: - Damaged fasteners - Damaged paint - Damaged sealant. Examine the stiffener for signs of damage and distortion.	X
2.	Inspection of the wing after a a severe hard landing or a severe hard-overweight landing
A.	Do the inspection of the wing after a hard landing or a hard overweight landing (Ref. item 1).	X
B.	Do an inspection of the front and rear spars. Examine: - The front spar at the forward pylon attachment-area - The rear-spar aft face between RIBS 6 and 9 and the area between RIBS 7 and 8 and the aft pylon attachment- fitting - The inner rear spar at the MLG attachment fittings - The shroud box. Make sure that: - There are no cracks - There is no damage - The paint and the sealant are not damaged - There are no fluid leaks - The fasteners and safety devices are in the correct condition. If there are signs of damage on the front and rear spars:	X
	(1) Defuel the wing (Ref. AMM TASK 28-25-00-650-001).		X
	(2) Get access to the wing area adjacent to the damage (Ref. AMM TASK 28-10-00-910-002).		X
	(3) Do an internal inspection of all the ribs, riblets, stringers, brackets and plates.		X
	(4) Do an inspection of all the pipes, hoses, electrical looms and raceways. Make sure that: - There are no cracks - There is no damage - The paint and the sealant are not damaged - The fasteners are in the correct condition.		X
	If there are indications of damage on the rear spar: (a) Do an inspection of these items: - The top diagonal stiffener - The MLG attachment - The top edge beam - The MLG pintle fitting - The MLG actuator fitting - The sidestay attachment fitting - The MLG support rib - The riblets, stringers and brackets. Make sure that: - There are no cracks - There is no damage - The paint and the sealant are not damaged - The fasteners are in the correct condition.		X
C.	Close access to the wing tanks (Ref. AMM TASK 28-10-00-910-002).

Subtask 05-51-11-210-179-D ** ON A/C NOT FOR ALL

J. 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	PHASE 3
1.	Inspection of the nacelles after a hard landing or a hard overweight landing
A.	(1) Examine the nacelle external-surface cowls (inlet, fan cowl doors, thrust reverser, nozzle and centerbody) for: - Failures, cracks, signs of buckling and permanent deformations - Unusual steps and gaps between the external cowl interfaces - Pulled, bent or loose rivets or fasteners - Opened or loose access covers, latches or panels.	X
	(2) Examine the inboard top area of the nacelle external surface below the outboard end of slat 1 for signs of contact during extension. This includes failures, cracks, signs of buckling and permanent deformations.	X
	If you find damage:
	- Refer to the SRM-approved damage limits and repair procedures.		X
	If the damage is more than the SRM allowable damage:
	- Contact Airbus for more instructions.			X
	(3) On the thrust reverser cowl-doors, open the four actuator access covers and examine the actuator fittings.	X
	(4) 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 (Ref. AMM TASK 71-13-00-010-802). Then examine the parts that follow for failures, cracks, signs of buckling and permanent deformations and/or pulled, bent or loose rivets pulled, bent or loose rivets or fasteners: - The internal sides of the doors - The locators - The Hold Open Rod (HOR) - 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, composite delamination or damage.		X
	(b) Examine the structure adjacent to the aft bulkhead for cracks, failures or damaged fasteners.		X
C.	Open the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-010-802) and examine the parts that follow for failures, cracks, permanent deformation or damaged fasteners: - The forward interface with the engine (V-groove and V-blade) - The hinge and latch fittings - The inner fixed-structure skins that you can see - The actuator fittings and the forward frame - 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 adjacent structure of the damaged parts for cracks, failures, damaged fasteners, composite delamination or damage.		X
	(b) Examine the nozzle skins and centerbody skins for cracks, failures or damaged fasteners.		X
D.	Do a manual deployment 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 parts that follow for cracks, failures, damaged fasteners, composite delamination or damage: - The blocker door - The blocker door hinges - The drag links - The cascades - The translating sleeves.	X
E.	If there is no damage, do a manual retraction of the thrust-reverser translating sleeves (Ref. AMM TASK 78-32-00-860-803).	X
F.	Do an operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-805). Make sure that the thrust reversers can move fully and freely.	X
G.	Close the fan cowl doors and the thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-410-802) and (Ref. AMM TASK 78-36-00-410-802).	X

Subtask 05-51-11-210-180-D ** ON A/C NOT FOR ALL

K. Inspection of the Pylons

Primary Structure ** ON A/C NOT FOR ALL

Engine-to-Pylon Attach Fittings ** 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 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) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-802).		X
	(c) Internally examine the primary and secondary structures (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners, leaks or other damage. This includes: - The lower spar (specially the splicing area between RIB2 and RIB3) and the upper spar - The ribs - The side panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The pipes and the ducts - The drain pipes - The hydraulic pipes.		X
	(d) On the primary structure, install the access doors (Ref. AMM TASK 54-51-21-400-802).		X
C.	(1) Remove access panels 471AL, 471CL, 482AR and 482CR from the pylon-to-wing junction (Ref. AMM TASK 54-53-11-000-804).	X
	(2) 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. Engine-to-Pylon Attach Fittings ** 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-on-wing junction (Ref. AMM TASK 54-53-11-400-804).	X
	(2) Close the thrust-reverser cowl doors and the fan cowl doors (Ref. AMM TASK 78-36-00-410-802) and (Ref. AMM TASK 71-13-00-410-802).	X

Subtask 05-51-11-210-181-D ** ON A/C NOT FOR ALL

L. Inspection of the Engines
(1) Do the inspection of the engine after a hard landing/hard overweight landing (Amber zone) or a severe hard landing/severe hard-overweight landing (Red zone) (Ref. AMM TASK 72-00-00-200-812).

Subtask 05-51-11-210-182-A ** ON A/C NOT FOR ALL

M. Inspection of the Wing

NOTE: This inspection contains two inspection procedures:

Item 1. Inspection after a hard landing or a hard overweight landing (Amber zone)
Item 2. Inspection after a severe hard landing or a severe hard-overweight landing (Red zone).

If you know the category of the landing, go directly to the necessary inspection.
If you do not know the category, go directly to item 2.
Inspection after a severe hard landing or a severe hard-overweight landing (Red zone).

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Inspection of the wing after a hard landing or a hard overweight landing (Amber zone)
A.	Examine the wing top skin from RIB 1 to RIB 10 and from RIB 18 to RIB 20, the shroud panel and its attachment. Make sure that: - There is no distortion - There are no cracks - The paint and the sealant are not damaged - The fasteners are in the correct condition. Carefully examine the fasteners at the rear spar between RIB 3 and RIB 6 and the gear rib.	X
B.	Do an inspection of the wing bottom skin. Carefully examine the areas adjacent to: - The flap beams - The engine pylon - The MLG attachments - The shroud-box outboard seal and the seal support. Make sure that: - There is no distortion - There are no cracks - There are no fluid leaks - The paint and the sealant are not damaged - The fasteners are in the correct condition. Carefully examine the fasteners at the rear spar between RIB 3 and RIB 6 and the gear rib. If there are signs of damage on the wing top or bottom skins.	X
	(1) Defuel the wing (Ref. AMM TASK 28-25-00-650-001).		X
	(2) Get access to the area adjacent to the damage (Ref. AMM TASK 28-10-00-910-002).		X
	(3) Do an internal inspection of the applicable ribs, the front and rear spars, the top and bottom skins, the stringers, the riblets, the brackets and the plates.		X
2.	Inspection of the wing after a a severe hard landing or a severe hard-overweight landing
A.	Do the inspection of the wing after a hard landing or a hard overweight landing (Ref. item 1).	X
B.	Do an inspection of the front and rear spars. Examine: - The front spar at the forward pylon attachment-area - The rear-spar aft face between RIBS 6 and 9 and the area between RIBS 7 and 8 and the aft pylon attachment- fitting - The inner rear spar at the MLG attachment fittings - The shroud box. Make sure that: - There are no cracks - There is no damage - The paint and the sealant are not damaged - There are no fluid leaks - The fasteners and safety devices are in the correct condition. If there are signs of damage on the front and rear spars:	X
	(1) Defuel the wing (Ref. AMM TASK 28-25-00-650-001).		X
	(2) Get access to the wing area adjacent to the damage (Ref. AMM TASK 28-10-00-910-002).		X
	(3) Do an internal inspection of all the ribs, riblets, stringers, brackets and plates.		X
	(4) Do an inspection of all the pipes, hoses, electrical looms and raceways. Make sure that: - There are no cracks - There is no damage - The paint and the sealant are not damaged - The fasteners are in the correct condition.		X
	If there are indications of damage on the rear spar: (a) Do an inspection of these items: - The top diagonal stiffener - The MLG attachment - The top edge beam - The MLG pintle fitting - The MLG actuator fitting - The sidestay attachment fitting - The MLG support rib - The riblets, stringers and brackets. Make sure that: - There are no cracks - There is no damage - The paint and the sealant are not damaged - The fasteners are in the correct condition.		X
C.	Close access to the wing tanks (Ref. AMM TASK 28-10-00-910-002).

Subtask 05-51-11-210-183-A ** ON A/C NOT FOR ALL

N. Inspection of the Flaps

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Inspection of the flaps
A.	Do a visual inspection of the upper and lower surfaces of the inner and outer flaps for distortion.	X
B.	Do fully the operational test of the flap system (Ref. AMM TASK 27-54-00-710-001). If there are indications of damage:	X
	(1) Do the detailed visual inspection of the transmission assembly (Ref. AMM TASK 27-54-00-200-001).		X
	(2) Do the detailed inspection of the flap attachment parts (drive arms and brackets).		X

Subtask 05-51-11-210-185-A ** ON A/C NOT FOR ALL

O. Inspection of the Fuselage

NOTE: This inspection contains two inspection procedures:

Lower Part of the Center Fuselage ** ON A/C NOT FOR ALL

Center Section ** ON A/C NOT FOR ALL

Component Location in the Belly Fairing Structure ** ON A/C NOT FOR ALL

Item 1. Inspection after a hard landing or a hard overweight landing (Amber zone)
Item 2. Inspection after a severe hard landing or a severe hard-overweight landing (Red zone).

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2
1.	Inspection of the fuselage after a hard landing or a hard overweight landing (Amber zone)
A.	Fuselage section between FR20 and FR35:
	- From the ground, examine the lower skin for loose fasteners, cracked or flaking paint or distortion.	X
B.	Fuselage section between FR35 and FR47:
	- Examine the belly fairing panels for loose fasteners, cracked or flaking paint, incorrect attachment or delamination. If you find damage:	X
	(1) Remove the panels and examine internally the belly fairing for the correct attachment of all the components or loose rivets.		X
	(2) Examine the fuselage skin externally below the belly fairing zone for: - Buckling, loose rivets, cracked or flaking paint.		X
	- Examine the operation of Overwing Door (OWD) 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.	X
C.	Fuselage section between FR47 and FR70: - From the ground, examine the lower skin for loose fasteners, cracked or flaking paint or distortion.	X
2.	Inspection of the fuselage after a severe hard landing or a severe hard- overweight landing (Red zone)
A.	Do the inspection of the fuselage after a hard landing or a hard overweight landing (Ref. item 1.) (Amber zone).	X
B.	Examine the keel beam connections to the fuselage under forward cargo compartment at frame 35 and under aft cargo compartment at frame 46/47 for distortion and cracks.	X

Subtask 05-51-11-210-186-A ** ON A/C NOT FOR ALL

P. Inspection of the Tail Area

Main Structure of the Cone/Rear Fuselage ** ON A/C NOT FOR ALL

NOTE: This inspection contains two inspection procedures:

Item 1. Inspection after a hard landing or a hard overweight landing (Amber zone)
Item 2. Inspection after a severe hard landing or a severe hard-overweight landing (Red zone).

If you know the category of the landing, go directly to the necessary inspection.
If you do not know the category of the landing, go directly to item 2. Inspection after a severe hard landing or a severe hard-overweight landing (Red zone).

(Ref. AMM TASK 27-44-00-710-002) (Ref. AMM TASK 55-16-00-200-001)
(Ref. AMM TASK 55-36-00-210-001) (Ref. AMM TASK 55-30-00-200-001)
(Ref. AMM TASK 55-10-00-210-001) (Ref. AMM TASK 27-24-00-710-001)
(Ref. AMM TASK 27-34-00-710-001)

ITEM	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3
1.	Inspection of the tail area after a hard landing or a hard overweight landing (Amber zone)
A.	Do the operational test of the THS (Ref. AMM TASK 27-44-00-710-002). If you find unsatisfactory condition(s):	X
	(1) Do a general visual inspection of: - The attachment areas of the horizontal stabilizer (Ref. AMM TASK 55-16-00-200-001) - The attachment areas of the vertical stabilizer (Ref. AMM TASK 55-36-00-210-001). If you find damage:		X
	(a) Do a detailed visual inspection of the vertical stabilizer center box (Ref. AMM TASK 55-30-00-200-001).			X
	(b) Do a visual inspection of the THS sparbox (Ref. AMM TASK 55-10-00-210-001).			X
B.	Do the operational test of the rudder and the elevators (Ref. AMM TASK 27-24-00-710-001) (Ref. AMM TASK 27-34-00-710-001) If you find unsatisfactory condition(s):	X
	(1) Examine the hinges of the elevators and the rudder for cracks.		X
2.	Inspection of the tail area after a severe hard landing or a severe hard- overweight landing (Red zone)
A.	Do the inspection of the tail area after a hard landing or a hard overweight landing (Ref. item 1.) (Amber zone).	X
B.	Do a general inspection of the APU compartment for leaks.	X
C.	Examine the APU for correct installation. Examine the mountings for damage, distortion and signs of movement.	X
D.	Examine the container brackets and the container of the APU fire extinguisher for damage, condition and correct installation.	X

Subtask 05-51-11-210-187-A ** ON A/C NOT FOR ALL

Q. Inspection of the Avionics compartment

NOTE: This inspection is necessary only for a severe hard landing or a severe hard-overweight landing (Red zone).

ITEM	INSPECTION TASKS	PHASE 1
1.	Inspection of the Avionics Compartment
A.	Examine the attachments of rack 80VU and 90VU.	X
B.	Examine the vertical rods above the NLG bay between FR12 and FR20.	X

Subtask 05-51-11-210-188-A ** ON A/C NOT FOR ALL

R. Inspection of the Water tanks

NOTE: This inspection is necessary only for a severe hard landing or a severe hard-overweight landing (Red zone).

ITEM	INSP CODE	INSPECTION TASKS	PHASE 1	PHASE 2	PHASE 3	INSP SIGN	REF. FIG.
1.		Inspection of the water tanks
A.		Examine the tanks for correct attachment and signs of leaks.	X

Subtask 05-51-11-210-189-A ** ON A/C NOT FOR ALL

S. Inspection of the Cockpit and Cabin Equipment/Furnishings, the Cargo Compartments and the Emergency Locator Transmitter (ELT)

NOTE: This inspection is necessary only for a severe hard landing or a severe hard-overweight landing.

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 (CAS) - 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 CAS, do a detailed inspection of the CAS (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
3.	ELT
	(1) Automatic ELT (if installed)
	(a) Make sure that the automatic ELT is not in automatic transmission mode.	X
	(b) In the cockpit, on the overhead panel, on the remote control panel (111MX), make sure that the RED indicator is off.	X
	If the RED indicator is on: - Immediately set the ELT switch to TEST/RESET position (or push the TEST/RESET pushbutton) until the RED indicator goes off, to stop the transmission. Then, release the ELT switch (or TEST/RESET pushbutton switch).		X
	(c) In the aft cabin, make sure that the ELT buzzer does not operate.	X
	If the buzzer operates: - Remove the ELT access panel - Set the ELT switch to OFF or ARMED to stop the transmission.		X
	(2) Survival ELT (if installed)
	(a) Make sure that the survival ELT is in the correct condition and installed correctly.	X
	(b) Make sure that the switch of the survival ELT did not move to the ON position (for an ELT that has a switch).	X
	If the ELT switch is at ON: - Set the ELT switch back to OFF or ARMED, as necessary. (refer to local regulations).		X

Subtask 05-51-11-210-190-A ** ON A/C NOT FOR ALL

T. Inspection of the Rear Fuselage and the Vertical Tail Plane
You must do this inspection only if the landing that occurred was a drift landing.

ITEM	INSPECTION TASKS	PHASE 1
1.	Inspection of the tail area after a drift landing
A.	Do a detailed visual inspection for distortion, cracks, damaged paintwork or sealant and loose or pulled fasteners on the external surface of the rear fuselage: Inspection Areas of the Vertical Tail Plane (VTP) after a Drift Landing ** ON A/C NOT FOR ALL
	(1) The external surface below the fin-to-fuselage fairings (Ref. AMM TASK 53-51-00-210-018).	X
	(2) The fin-to-fuselage FWD, MID, and AFT attach lugs (Ref. AMM TASK 53-51-00-210-012).	X
	(3) The transverse load rod attachments (Ref. AMM TASK 53-51-00-210-012).	X
B.	Do a detailed visual inspection for distortion, cracks, damaged paintwork or sealant and loose or pulled fasteners on the internal surface of the rear fuselage at Zone 310:
	(1) Between FR70 and FR74 above stringers 19LH and 19RH (Ref. AMM TASK 53-51-00-210-020).	X
	(2) All areas of FR77 (Ref. AMM TASK 53-51-00-210-020).	X
C.	Do a detailed visual inspection for distortion, cracks, damaged paintwork or sealant and loose or pulled fasteners on the vertical tail plane : Inspection Areas of the Vertical Tail Plane (VTP) after a Drift Landing ** ON A/C NOT FOR ALL
	(1) The attach-fitting areas (this includes the load introduction area at the skin panels) (Ref. AMM TASK 55-36-00-210-001).	X
	(2) The RIB1 lower surface.	X
	(3) The RIB2 upper and lower surfaces, from the inspection holes at the front and rear spars.	X
	(4) Rudder hinge arms 1 to 7 (Ref. AMM TASK 55-30-00-210-001) (Ref. AMM TASK 55-30-00-210-002).	X
	(5) Actuator attach-fittings 1 to 3 (Ref. AMM TASK 55-30-00-210-001).	X
	(6) The external surface of the front spar between RIB1 and RIB2.	X
	(7) The external surface of the front spar between RIB10 and RIB11.	X
	(8) The external surface of the rear spar between RIB1 and RIB11.	X
D.	Do a detailed visual inspection for distortion, cracks, damaged paintwork or sealant and loose or pulled fasteners on the rudder: Rudder and Actuator Attach-Fittings ** ON A/C NOT FOR ALL
	(1) Rudder attach-fittings 1 to 7 (Ref. AMM TASK 55-40-00-210-004). (Ref. AMM TASK 55-40-00-210-005)	X
	(2) Actuator attach-fittings 1 to 3 (Ref. AMM TASK 55-40-00-210-004).	X

5. Close-up
Subtask 05-51-11-410-056-A ** ON A/C NOT FOR ALL

A. Special Closing of Access After a Drift Landing Inspection
(1) Close the trailing-edge access panels of the vertical stabilizer (Ref. AMM TASK 55-33-13-410-002).
(2) Install leading-edge access panels 322AL and 322CL of the vertical stabilizer (Ref. AMM TASK 55-32-11-400-001).
(3) Install rudder fairings 325AL and 325AR (Ref. AMM TASK 53-55-12-400-001).
(4) Install dorsal fin 321AL (Ref. AMM TASK 53-45-11-400-001).
(5) Install vertical stabilizer fairings 323AL and 323AR (Ref. AMM TASK 53-55-11-400-001).
(6) Close access door 312AR.
(7) Remove the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE from Zone 320.
(8) Remove the WARNING NOTICE(S).

Subtask 05-51-11-410-057-A ** ON A/C NOT FOR ALL

B. Close Access
(1) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).
(2) Fully retract the slats (Ref. AMM TASK 27-80-00-866-005).
(3) Fully retract the spoilers (Ref. AMM TASK 27-60-00-866-002).
(4) Close the access doors and panels opened during the inspection.
(5) Close the nose gear doors (Ref. AMM TASK 32-22-00-410-001).
(6) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001).
(7) Remove the access platform(s).
(8) Remove the WARNING NOTICE(S).
(9) Make sure that the work area is clean and clear of tools and other items.

[Rev.10 from 2021] 2026.03.31 22:51:17 UTC