DOC AIRBUS | AMM A320FInspection after Leaving Runway or Taxiway
TASK 05-51-24-200-001-A
Inspection after Leaving Runway or Taxiway
1. Reason for the Job
When an aircraft moves off the runway or taxiway, the loads on the landing gear and the structure can increase. The necessary inspection after the aircraft moves off the runway or taxiway must include all the possible causes for the load to increase:
If a brake overheat occurred, do the inspection after the brake overheat (Ref. Task 05-51-16-200-001).
If a tire burst or a thread throw or a wheel failure occurred, do the inspection after a tire burst or a thread throw or a wheel failure (Ref. TASK 05-51-15-200-001).
The operators can release their aircraft after these inspections, if the runway-excursion is minor. When the runway-excursion is major, operators must contact Airbus for more recommendations.
a) Major runway-excursion:
You must tell Airbus about the incident before the next flight, and give the details of the incident. Airbus will then give you instructions to get the aircraft safely back into operation.
A runway-excursion is major when:
During the inspection, if there is no damage, it is not necessary to contact Airbus immediately and the operator can release their aircraft. It is mandatory to give the correct values of the below conditions, pilot report, aircraft trajectory sketch and aircraft pictures to Airbus for information in one week.
A runway-excursion is minor when:
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 05-51-24-481-050-A
Subtask 05-51-24-210-050-A
Subtask 05-51-24-866-051-A Subtask 05-51-24-410-050-A
[Rev.10 from 2021]
2026.03.31 22:51:41 UTC
Inspection after Leaving Runway or Taxiway
1. Reason for the Job
When an aircraft moves off the runway or taxiway, the loads on the landing gear and the structure can increase. The necessary inspection after the aircraft moves off the runway or taxiway must include all the possible causes for the load to increase:
- The speed of the aircraft
- The weight of the aircraft
- The type of the ground (soft or hard)
- The distance that the landing gear goes into the ground.
If a brake overheat occurred, do the inspection after the brake overheat (Ref. Task 05-51-16-200-001).
If a tire burst or a thread throw or a wheel failure occurred, do the inspection after a tire burst or a thread throw or a wheel failure (Ref. TASK 05-51-15-200-001).
The operators can release their aircraft after these inspections, if the runway-excursion is minor. When the runway-excursion is major, operators must contact Airbus for more recommendations.
a) Major runway-excursion:
You must tell Airbus about the incident before the next flight, and give the details of the incident. Airbus will then give you instructions to get the aircraft safely back into operation.
A runway-excursion is major when:
- The aircraft recovery was not done as necessary related to the Aircraft Recovery Manual (ARM) requirements, or
- The runway-excursion included drifting of a landing gear or pivoting around an MLG, or
- The NLG wheels were not aligned with the aircraft trajectory (turned) during the runway-excursion (NLG was in a skid), or
- The runway-excursion occurred at a ground speed of more than 20 kts, or
- The NLG went into the ground more than 5 cm or collected material in front of the wheels, or
- The NLG hit an obstacle or a step higher than 5 cm, or
- The MLG went into the ground more than 20 cm or collected material in front of the wheels, or
- The MLG hit an obstacle or a step higher than 5 cm, or
- There was damage found during the phase 1 inspection.
During the inspection, if there is no damage, it is not necessary to contact Airbus immediately and the operator can release their aircraft. It is mandatory to give the correct values of the below conditions, pilot report, aircraft trajectory sketch and aircraft pictures to Airbus for information in one week.
A runway-excursion is minor when:
- The aircraft recovery was done as necessary related to the ARM requirements, and
- The runway-excursion did not include drifting of a landing gear or pivoting around an MLG (if you can see the tire tracks, it must be straight or a gentle curve), and
- The NLG wheels were aligned with the aircraft trajectory during the runway-excursion (NLG was not in a skid), and
- The runway-excursion occurred at a ground speed of 20 kts or less, and
- The NLG did not go into the ground more than 5 cm and did not collect material in front of the wheels, and
- The NLG did not hit obstacles or steps higher than 5 cm, and
- The MLG did not go into the ground more than 20 cm and did not collect material in front of the wheels, and
- The MLG did not hit obstacles or steps higher than 5 cm.
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 3M (10 FT) |
| No specific | AR | WARNING NOTICE(S) |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 471AL, 471CL, 482AR, 482CR |
| 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 07-11-00-586-001-A | Lowering of the Aircraft at 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 27-50-00-866-008-A | Extension of the Flaps on the Ground |
| TASK 27-50-00-866-008-A-01 | Extension of the Flaps/Slats on the Ground |
| TASK 27-50-00-866-009-A | Retraction of the Flaps on the Ground |
| TASK 27-50-00-866-009-A-01 | Retraction of the Flaps/Slats on the Ground |
| TASK 28-10-00-910-002-A | Access to the Fuel Tanks and the Work Areas |
| TASK 28-25-00-650-001-A | Pressure Defuel |
| TASK 29-00-00-864-001-A | Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action |
| TASK 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 32-21-00-200-005-A | Detailed Inspection/Check of the NLG |
| 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 32-31-00-720-003-A | Functional Test of the Normal Extension and Retraction of the Nose 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 32-41-11-000-006-A | Removal of the MLG Wheel |
| TASK 32-41-11-400-006-A | Installation of the MLG Wheel |
| 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 32-42-27-000-001-A | Removal of the Brake |
| TASK 32-42-27-400-001-A | Installation of the Brake |
| TASK 32-42-71-000-001-A | Removal of the MLG Axle Adaptor-Sleeves |
| TASK 32-42-71-400-001-A | Installation of the MLG Axle Adaptor-Sleeves |
| TASK 32-48-51-000-005-A | Removal of the Fan Assy |
| TASK 32-48-51-400-005-A | Installation of the Fan Assy |
| TASK 35-23-00-710-001-A | Operational Check of Manual Mask Release |
| TASK 54-51-17-000-001-A | Removal of the Pylon-to-Wing Forward Attach-Fitting at RIB4 |
| TASK 54-51-17-000-002-A | Removal of the Pylon-to-Wing Aft Attach-Fitting at RIB10 |
| TASK 54-51-17-000-804-A | Removal of the Pylon-to-Wing Forward Attach-Fitting at RIB5 |
| TASK 54-51-17-000-805-A | Removal of the Pylon-to-Wing Aft Attach-Fitting at RIB10 |
| TASK 54-51-17-200-001-A | Inspection of the Pylon-to-Wing Forward Attach-Fitting |
| TASK 54-51-17-200-002-A | Inspection of the Pylon-to-Wing Aft Attach-Fitting |
| TASK 54-51-17-200-003-A | Inspection of the Shackles at RIB4 and the Spigot |
| TASK 54-51-17-200-004-A | Inspection of the Shackles at RIB10 |
| TASK 54-51-21-000-001-A | Removal of the Pylon Lateral Access-Doors |
| TASK 54-51-21-000-802-A | Removal of the Pylon Lateral Access-Doors |
| TASK 54-51-21-400-001-A | Installation of the Pylon Lateral Access-Doors |
| TASK 54-51-21-400-802-A | Installation of the Pylon Lateral Access-Doors |
| TASK 54-53-11-000-002-A | Removal of the Pylon-to-Wing Access Panels |
| TASK 54-53-11-000-002-B | Removal of the Pylon-to-Wing Access Panels |
| TASK 54-53-11-000-804-A | Removal of the Pylon-to-Wing Access Panels and Doors |
| TASK 54-53-11-400-002-A | Installation of the Pylon-to-Wing Access Panels |
| TASK 54-53-11-400-002-B | Installation of the Pylon-to-Wing Access Panels |
| TASK 54-53-11-400-804-A | Installation of the Pylon-to-Wing Access Panels and Doors |
| TASK 71-00-00-000-040-A | Removal of the Power Plant |
| TASK 71-00-00-000-040-A-01 | Removal of the Power Plant with the Engine Positioner TWW 75E |
| TASK 71-00-00-000-040-A-03 | Removal of the Power Plant with Jacxson Tool |
| TASK 71-00-00-000-042-A | Removal of the Power Plant |
| TASK 71-00-00-000-042-A-01 | Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG) |
| TASK 71-00-00-000-042-A-03 | Removal of the Power Plant with Jacxson Tool |
| TASK 71-00-00-400-040-A | Installation of the Power Plant |
| TASK 71-00-00-400-040-A-01 | Installation of the Power Plant with the Engine Positioner TWW 75E |
| TASK 71-00-00-400-040-A-03 | Installation of the Power Plant with Jacxson Tool |
| TASK 71-00-00-400-042-A | Installation of the Power Plant |
| TASK 71-00-00-400-042-A-01 | Installation of the Power Plant with the Engine Positioner TWW 75E (MIAG) |
| TASK 71-00-00-400-042-A-03 | Installation of the Power Plant with Jacxson Tool |
| TASK 71-00-20-000-040-A | Removal of the Power Plant |
| TASK 71-00-20-000-040-A-01 | Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG) |
| TASK 71-00-20-400-040-A | Installation of the Power Plant |
| TASK 71-00-20-400-040-A-01 | Installation of the Power Plant with the Engine Positioner TWW 75E (MIAG) |
| TASK 71-00-51-000-802-A | Removal of the Power Plant (Bootstrap Method) |
| TASK 71-00-51-000-802-A-01 | Removal of the Power Plant (JacXson Method) |
| TASK 71-00-51-400-802-A | Installation of the Power Plant (Bootstrap Method) |
| TASK 71-00-51-400-802-A-01 | Installation of the Power Plant (JacXson Method) |
| TASK 71-13-00-010-010-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 72-00-00-200-001-A | Inspection/Check of Foreign Object Damage (FOD) (Bird Strike Included) |
| TASK 72-00-00-200-006-A | Inspection/Check of Foreign Object Damage (FOD) (Bird Strike Included) |
| TASK 72-00-00-200-010-A | Inspection of the Engine after Bird Strike, Foreign Object or Slush Ingestion |
| TASK 72-00-00-210-807-A | Visual Examination (After Bird Strike (Foreign Object Damage)) |
| 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 78-32-00-860-802-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 78-36-00-010-040-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 |
Engine NacelleSubtask 05-51-24-481-050-A
A. Safety Precautions
(1) Make sure that the safety devices are installed on the landing gears (Ref. AMM TASK 32-00-00-481-001).
(2) Put the WARNING NOTICE(S) in the cockpit to tell persons not to operate the aircraft systems.
Subtask 05-51-24-860-050-A (1) Make sure that the safety devices are installed on the landing gears (Ref. AMM TASK 32-00-00-481-001).
(2) Put the WARNING NOTICE(S) in the cockpit to tell persons not to operate the aircraft systems.
B. 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).
Subtask 05-51-24-010-050-A (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).
C. 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).
(3) Put an ACCESS PLATFORM 3M (10 FT) in position.
Subtask 05-51-24-866-050-A 4. Procedure(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).
(3) Put an ACCESS PLATFORM 3M (10 FT) in position.
Subtask 05-51-24-210-050-A
A. General
Subtask 05-51-24-210-053-A NOTE: You can do non-destructive tests (refer to the Aircraft Non-destructive Testing Manual) if:
- You think it is necessary.
- The Airworthiness Authority tells you to.
- Airbus tell you to.
All the inspections are visual unless you get other instructions.
- You think it is necessary.
- The Airworthiness Authority tells you to.
- Airbus tell you to.
All the inspections are visual unless you get other instructions.
B. Inspection of the Fuselage
Subtask 05-51-24-210-054-A | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Fuselage bottom-surface. This includes cargo doors. | | | | | |
| A. | | Externally examine all the bottom- surface of the fuselage for dents, distortion, cracks, pulled or torn fasteners and damaged paintwork. If you find damage: | X | | | | |
| | | (1) Internally examine at and adjacent to the damaged area, all the frames, stringers, joints and cleats for damage. | | X | | | |
| | | (2) Inspect all the components, pipes, ducts and cables adjacent to the damaged area for damage or leakage. | | X | | | |
| 2. | | NLG Doors | | | | | |
| A. | | Examine the NLG doors for holes, delamination, cracked or flaking paint, loose fasteners and correct attachment. | X | | | | |
| 3. | | MLG Doors | | | | | |
| A. | | Examine the MLG doors for holes, delamination, cracked or flaking paint, loose fasteners and correct attachment. | X | | | | |
| 4. | | Belly Fairing | | | | | |
| A. | | Examine the belly fairing panels for holes, delamination, cracked or flaking paint, loose fasteners and correct attachment. If you find damage: | X | | | | |
| | | (1) Remove the panels and internally examine the belly fairing structure for buckling, cracks and damaged paintwork. | | X | | | |
| | | (2) Examine the pipes, ducts, electrical looms and their supports for: - fluid leakage, distortion, rupture, breaks, cracks, correct attachment and the condition of the safety devices. | | X | | | |
| B. | | Examine the air-conditioning pack intakes for unwanted material and damage from hits. | X | | | | |
| 5. | | APU Intake | | | | | |
| A. | | Examine the APU intake for unwanted material and damage from hits. | X | | | | |
C. Inspection of the NLG
Subtask 05-51-24-210-056-A NOTE: It is necessary to do the inspection of the NLG which went off the runway.
This inspection contains two inspection procedures.
To know which inspections to do, it is necessary to know if:
This inspection contains two inspection procedures.
To know which inspections to do, it is necessary to know if:
- The NLG wheels went into the ground.
- The NLG hit an obstacle on its path.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the NLG after the aircraft went off the runway and the NLG wheels went into the ground and/or the NLG hit an obstacle on its path. | | | | | |
| A. | | Initial Inspection | | | | | |
| | | (1) Lift the aircraft at forward jacking point (Ref. AMM TASK 07-11-00-581-003). | X | | | | |
| | | - Make sure that the extension of the NLG shock absorber is smooth and full. | X | | | | |
| | | - Examine the shock absorber sliding-rod (the part you can see) for blue color and signs of bronze or chrome damage. | X | | | | |
| | | (2) Do a check of the pressure in the NLG shock absorber (Ref. AMM TASK 12-14-32-614-004). | X | | | | |
| | | (3) Examine the shock absorber for external oil leakage. | X | | | | |
| | | (4) Do the inspection of the NLG (Ref. AMM TASK 32-21-00-200-005) for: - Out-of-roundness of the shock absorber sliding-rod. - Cracks, damaged paintwork and deformation on the steering actuator body (measure the bottom of actuator body). Make sure that the: - Rotating tube turns freely, - Drag strut/barrel pin turn and translate freely. | X | | | | |
| | | (5) Make sure that the wheels and the tires: - Turn freely - Are not damaged (Ref. AMM TASK 32-41-00-210-002). | X | | | | |
| | | If a wheel or a tire is damaged or if a wheel does not turn freely: - Remove the NLG wheel (Ref. AMM TASK 32-41-12-000-001). | | X | | | |
| | | - Make sure that the NLG axle sleeve turns without hard points. | | X | | | |
| | | - Remove the NLG axle sleeve and make sure that the axle sleeve moves without hard points (Ref. AMM TASK 32-41-12-000-002). | | X | | | |
| | | - Do a visual inspection of the axle and the axle sleeve for damage. | | X | | | |
| | | If you find damage: - Contact Airbus for more instructions. | | | X | | |
| | | - Install the NLG axle sleeve (Ref. AMM TASK 32-41-12-400-002). | | X | | | |
| | | - Install the new NLG wheel (Ref. AMM TASK 32-41-12-400-001). | | X | | | |
| | | (6) Do the functional test of the retraction and extension of the NLG (Ref. AMM TASK 32-31-00-720-003). | X | | | | |
| B. | | Subsequent Inspection of the NLG | | | | | |
| | | (1) If the initial inspection shows no unsatisfactory condition: | | | | | |
| | | (a) Do the inspection given in item 2 (Inspection of the NLG after the aircraft went off the runway but the NLG wheels did not go into the ground and there was no obstacle in the NLG path). | X | | | | |
| | | (2) If the initial inspection shows unsatisfactory condition(s): | | | | | |
| | | (a) Remove the NLG leg assembly, the NLG lockstay assembly and the NLG drag-strut assembly for overhaul: (Ref. AMM TASK 32-21-11-000-003) (Ref. AMM TASK 32-21-17-000-001) (Ref. AMM TASK 32-21-16-000-002) (refer to the manufacturer's instructions for the overhaul procedure). | | X | | | |
| | | (b) On the aircraft, examine the attachment fittings and the bearings of the NLG drag-strut assembly for distortion, cracks and damaged paintwork. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (c) On the aircraft, examine the attachment fittings of the NLG leg assembly for distortion, cracks and damaged paintwork. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (d) Examine the NLG actuating cylinder and its attachment fitting for distortion, cracks and damaged paintwork. If you find damage: | X | | | | |
| | | - Remove the NLG actuating cylinder for a strip-down inspection (Ref. AMM TASK 32-31-22-000-001) (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 | | | |
| | | If you find damage: - Tell Airbus about the results. | | | X | | |
| | | (e) In the avionics compartment, examine: - The gear-well roof - The roof-to-sidewall joint - The floor support-strut attach-fittings for distortion, cracks, pulled or damaged fasteners and damaged paintwork. | | X | | | |
| | | If you find damage: - Tell Airbus about the results. | | | X | | |
| | | (f) If you removed components, install serviceable components: - For the NLG actuating cylinder (Ref. AMM TASK 32-31-22-400-001) - For the NLG drag-strut assembly (Ref. AMM TASK 32-21-16-400-002) - For the NLG 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 NLG axle sleeve (Ref. AMM TASK 32-41-12-400-002) - For the NLG wheel (Ref. AMM TASK 32-41-12-400-001). | | X | | | |
| C. | | Lower the aircraft on its wheels (Ref. AMM TASK 07-11-00-586-001). | X | | | | |
| 2. | | Inspection of the NLG after the aircraft went off the runway and the NLG wheels did not go into the ground and there was no obstacle in the NLG path. NOTE: You can do this inspection with the aircraft on its wheels. | | | | | |
| A. | | Inspection | | | | | |
| | | (1) Do a check of the pressure in the NLG shock absorber. (Ref. AMM TASK 12-14-32-614-004) | X | | | | |
| | | (2) Do a visual inspection of the NLG wheels and tires: (Ref. AMM TASK 32-41-00-210-002). If you find damage: | X | | | | |
| | | (a) Remove the NLG wheels (Ref. AMM TASK 32-41-12-000-001). | | X | | | |
| | | (b) Make sure that the NLG axle sleeve turns without hard points. | | X | | | |
| | | (c) Remove the NLG axle sleeve and make sure that the axle sleeve moves without hard points (Ref. AMM TASK 32-41-12-000-002). | | X | | | |
| | | (d) Do a visual inspection of the axle and the axle sleeve for damage. | | X | | | |
| | | If you find damage: - Tell Airbus about the results. | | | X | | |
| | | (e) Install the NLG axle sleeve (Ref. AMM TASK 32-41-12-400-002). | | X | | | |
| | | (f) Install the new NLG wheel (Ref. AMM TASK 32-41-12-400-001). | | X | | | |
| | | (3) Examine: - The NLG and all the components installed on it for cracks, scores, tears, rupture, leakage and damaged paintwork. - The attachment fittings of the NLG. | X | | | | |
| | | If you find damage: - Tell Airbus about the results. | | X | | | |
| | | (4) Examine the sliding rod of the NLG shock absorber (the part you can see) for blue color, signs of bronze or chrome damage or external oil leaks. If you find damage: | X | | | | |
| | | - Remove the NLG shock absorber assembly for overhaul (Ref. AMM TASK 32-21-13-000-001) (refer to the manufacturer's instructions for the overhaul procedure). | | X | | | |
| | | (5) Examine the NLG drag-strut assembly and its attachment fittings for distortion, cracks and damaged paintwork. If you find damage: | X | | | | |
| | | (a) Remove the NLG drag-strut assembly for overhaul (Ref. AMM TASK 32-21-16-000-002) (refer to the manufacture's instruction for the overhaul procedure). | | X | | | |
| | | (b) On the aircraft, inspect the attachment fitting for damage. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (c) 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 | | | |
| | | - Remove the NLG leg assembly (Ref. AMM TASK 32-21-11-000-003). | | | X | | |
| | | (6) Examine the NLG lockstay assembly for distortion, cracks and damaged paintwork. | X | | | | |
| | | If you find damage: (a) Remove the NLG lockstay assembly for overhaul (Ref. AMM TASK 32-21-17-000-001) (refer to the manufacturer's instructions for the overhaul procedure). | | X | | | |
| | | (b) On the aircraft, inspect the attachment fittings for damage. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (7) Examine the NLG actuating cylinder and its attachment fittings for distortion, cracks, pulled or damaged fasteners and damaged paintwork. If you find damage: | X | | | | |
| | | (a) Remove the NLG actuating cylinder for a strip-down inspection (Ref. AMM TASK 32-31-22-000-001) (refer to the manufacturer's instructions for the strip-down inspection). | | X | | | |
| | | (b) On the aircraft, continue the inspection of the attachment fittings for damage. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (8) In the avionics compartment, examine: - The gear-well roof - The roof-to-sidewall joint - The floor support-strut attach-fittings for distortion, cracks, pulled or damaged fasteners and damaged paintwork. | X | | | | |
| | | If you find damage: - Tell Airbus about the results. | | X | | | |
| | | (9) If you removed components, install serviceable components: - For the NLG actuating cylinder (Ref. AMM TASK 32-31-22-400-001) - For the NLG 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 NLG drag-strut assembly (Ref. AMM TASK 32-21-16-400-002) - For the NLG shock-absorber assembly (Ref. AMM TASK 32-21-13-400-001) - For the NLG axle sleeve (Ref. AMM TASK 32-41-12-400-002) - For the NLG wheel (Ref. AMM TASK 32-41-12-400-001). | X | | | | |
D. Inspection of the MLG
Subtask 05-51-24-210-051-A NOTE: It is necessary to do the inspection of the MLG which went off the runway.
This inspection contains two inspection procedures.
To know which inspections to do, it is necessary to know if:
This inspection contains two inspection procedures.
To know which inspections to do, it is necessary to know if:
- The MLG wheels went into the ground
- The MLG hit an obstacle on its path.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the MLG after the aircraft went off the runway and the MLG wheels went into the ground and/or the MLG hit an obstacle on its path. NOTE: You can directly do the inspection given in item 2, if the MLG moved along the same path as the NLG (straight line and/or the same obstacles) and the NLG inspection showed no damage. | | | | | |
| | A. | Initial inspection | | | | | |
| | | (1) Lift the aircraft (Ref. AMM TASK 07-11-00-581-001). | X | | | | |
| | | - Make sure that the extension of the MLG shock absorber is smooth and full. | X | | | | |
| | | - Examine the shock absorber sliding-rod (the part you can see) for blue color and signs of bronze or chrome damage. | X | | | | |
| | | (2) Do a check of the pressure in the MLG shock absorber (Ref. AMM TASK 12-14-32-614-003). | X | | | | |
| | | (3) Examine the shock absorber for external leakage. | X | | | | |
| | | (4) 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 side-stay lower cardan pin-joint (side stay disconnected). - Distortion of the torque link pin. - Detailed visual inspection of the barrel in the drag-stay blend area. - Detailed visual inspection of the forward pintle-pin barrel area. - Detailed visual inspection of the rear pintle-pin mounting. | X | | | | |
| | | (5) Do a visual inspection of the MLG wheels, the tires, the brakes and the brake fans (if installed). | X | | | | |
| | | (a) Make sure that the MLG wheels and tires: - Turn freely - Are not damaged (Ref. AMM TASK 32-41-00-210-002). | X | | | | |
| | | (b) Make sure that the brakes have no damage or contamination (mud, grass or unwanted material). | X | | | | |
| | | (c) Make sure that the brake fan debris-guard (if installed) has no damage or contamination. | X | | | | |
| | | (d) Make sure that the hydraulic pipes and hoses are not damaged. | X | | | | |
| | | (e) Make sure that the electrical connectors and harnesses are not damaged. | X | | | | |
| | | If an MLG wheel or tire is damaged or if an MLG wheel does not turn freely: - Remove the MLG wheel (Ref. AMM TASK 32-41-11-000-006). | | X | | | |
| | | - Remove the MLG axle adaptor-sleeve (Ref. AMM TASK 32-42-71-000-001). | | X | | | |
| | | - Do a visual inspection of the axle and the axle adaptor-sleeve for damage (Ref. AMM TASK 32-11-00-200-006). | | X | | | |
| | | If you find damage: - Contact Airbus for more instructions. | | | X | | |
| | | If a brake has damage or contamination: - Replace it (Ref. AMM TASK 32-42-27-000-001) (Ref. AMM D/O 32-42-27-00) (Ref. AMM TASK 32-42-27-400-001) (Ref. AMM D/O 32-42-27-40). | | X | | | |
| | | If a brake fan debris-guard has damage or contamination: - Remove it for cleaning or replace it (Ref. AMM TASK 32-48-51-000-005) (Ref. AMM TASK 32-48-51-400-005). | | X | | | |
| | | If a pipe, a hose or a harness is damaged, replace it. | X | | | | |
| | | - Install the new axle adaptor-sleeve (Ref. AMM TASK 32-42-71-400-001). | | X | | | |
| | | - Install the new MLG wheels (Ref. AMM TASK 32-41-11-400-006). | | X | | | |
| | | (6) Do the functional test of the normal extension and retraction of the MLG (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 | | | | |
| | | (7) Do the functional test of the free-fall extension of the MLG (Ref. AMM TASK 32-33-00-720-001). | X | | | | |
| B. | | Subsequent Inspection of the MLG | | | | | |
| | | (1) If the initial inspection shows no unsatisfactory condition: | | | | | |
| | | (a) Do the inspection given in item 2 (Inspection of the MLG after the aircraft went off the runway but the MLG wheels did not go into the ground and there was no obstacle in the MLG path). | X | | | | |
| | | (2) If the initial inspection shows unsatisfactory condition(s): | | | | | |
| | | (a) Remove the MLG leg assembly, the MLG side-stay, the MLG lockstay assembly and the MLG lockstay actuating-cylinder 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 | | | |
| | | (b) On the aircraft, examine the attachment fittings and bearings of the MLG side-stay for distortion, cracks and damaged paintwork. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (c) On the aircraft, examine the attachment fittings of the MLG leg assembly for distortion, cracks and damaged paintwork. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (d) Examine the MLG actuating cylinder and its attachment fitting for distortion, cracks and damaged paintwork. If you find damage: | | X | | | |
| | | - Remove the MLG 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. If you find damage: - Tell Airbus about the results. | | | X | | |
| | | (e) Examine the MLG gear-well (all the items you can see) for distortion, cracks, pulled or damaged fasteners and damaged paintwork. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (f) If you removed components, install serviceable components: - For the MLG actuating cylinder (Ref. AMM TASK 32-31-46-400-001) - For the MLG lockstay actuating-cylinder (Ref. AMM TASK 32-11-21-400-001) - For the MLG lockstay assembly (Ref. AMM TASK 32-11-17-400-001) - For the MLG side-stay assembly (Ref. AMM TASK 32-11-16-400-001) - For the MLG leg assembly (Ref. AMM TASK 32-11-11-400-001) - For the MLG axle adaptor-sleeve (Ref. AMM TASK 32-42-71-400-001) - For the MLG wheel (Ref. AMM TASK 32-41-11-400-006) - For the MLG brake (Ref. AMM TASK 32-42-27-400-001) (Ref. AMM D/O 32-42-27-40) - For the MLG brake fan (Ref. AMM TASK 32-48-51-400-005). | | X | | | |
| C. | | Lower the aircraft on its wheels (Ref. AMM TASK 07-11-00-586-002). | X | | | | |
| 2. | | Inspection of the MLG after the aircraft went off the runway but the MLG wheels did not go into the ground and there was no obstacle in the MLG path. NOTE : You can do this inspection with the aircraft on its wheels. | | | | | |
| A. | | Inspection | | | | | |
| | | (1) Do a check of the pressure in the MLG shock absorber (Ref. AMM TASK 12-14-32-614-003). | X | | | | |
| | | (2) Do a visual inspection of the MLG wheels, the tires, the brakes and the brake fans (if installed). | X | | | | |
| | | (a) Make sure that the MLG wheels and tires are not damaged (Ref. AMM TASK 32-41-00-210-002). | X | | | | |
| | | (b) Make sure that the brakes have no damage or contamination (mud, grass or unwanted material). | X | | | | |
| | | (c) Make sure that the brake fan debris-guard (if installed) has no damage or contamination. | X | | | | |
| | | (d) Make sure that the hydraulic pipes and hoses are not damaged. | X | | | | |
| | | (e) Make sure that the electrical connectors and harnesses are not damaged. | X | | | | |
| | | If an MLG wheel or tire is damaged: - Remove the MLG wheel (Ref. AMM TASK 32-41-11-000-006). | | X | | | |
| | | - Remove the MLG axle adaptor-sleeve (Ref. AMM TASK 32-42-71-000-001). | | X | | | |
| | | - Do a visual inspection of the axle and the axle adaptor-sleeve for damage (Ref. AMM TASK 32-11-00-200-006). | | X | | | |
| | | If you find damage: - Contact Airbus for more instructions. | | | X | | |
| | | - Install the new MLG axle adaptor-sleeve (Ref. AMM TASK 32-42-71-400-001). | | X | | | |
| | | If a brake has damage or contamination: - Replace it (Ref. AMM TASK 32-42-27-000-001) (Ref. AMM D/O 32-42-27-00) (Ref. AMM TASK 32-42-27-400-001) (Ref. AMM D/O 32-42-27-40). | | X | | | |
| | | If a brake fan debris-guard has damage or contamination: - Remove it for cleaning or replace it (Ref. AMM TASK 32-48-51-000-005) (Ref. AMM TASK 32-48-51-400-005). | | X | | | |
| | | If a pipe, a hose or a harness is damaged, replace it. | X | | | | |
| | | - Install the new MLG wheel (Ref. AMM TASK 32-41-11-400-006). | | X | | | |
| | | (3) Examine: - The MLG and all the components installed on it for cracks, scores, tears, rupture, leakage and damaged paintwork (look very carefully at the drag stay blend and the forward pintle pin areas) - The attachment fittings of the MLG. | X | | | | |
| | | If you find damage: - Tell Airbus about the results. | | X | | | |
| | | (4) Examine the sliding rod of the MLG shock absorber (the part you can see) for blue color, signs of bronze or chrome damage or external oil leaks. If you find damage: | X | | | | |
| | | (a) Remove the MLG shock absorber for overhaul (Ref. AMM TASK 32-11-13-000-001) (refer to the manufacturer's instructions for the overhaul procedure). | | X | | | |
| | | (5) Examine the MLG side-stay assembly and its attachment fittings for distortion, cracks and damaged paintwork. If you find damage: | X | | | | |
| | | (a) Remove the MLG side-stay assembly for overhaul (Ref. AMM TASK 32-11-16-000-001) (refer to the manufacturer's instructions for the overhaul procedure). | | X | | | |
| | | (b) Do the dimensional inspection of the MLG side-stay cardan pin-joint lugs on the MLG leg (Ref. AMM TASK 32-11-00-220-004). If you find damage: | | X | | | |
| | | - Remove the MLG leg assembly (Ref. AMM TASK 32-11-11-000-001). | | | X | | |
| | | (c) On the aircraft, continue the inspection of the MLG side-stay attachment fitting. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (6) Examine the MLG lockstay assembly and the lockstay actuating cylinder for distortion, cracks and damaged paintwork. If you find damage: | X | | | | |
| | | (a) Remove the MLG lockstay assembly and the MLG lockstay actuating-cylinder 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 | | | |
| | | (b) On the aircraft, continue the inspection of the attachment fittings for damage. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (7) Examine the MLG actuating cylinder and its attachment fittings for distortion, cracks, and damaged paintwork. If you find damage: | X | | | | |
| | | (a) Remove the MLG 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 procedure). | | X | | | |
| | | (b) On the aircraft, continue the inspection of the attachment fittings for damage. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (8) Examine the MLG gear-well (all the items you can see) for distortion, cracks, pulled or damaged fasteners and damaged paintwork. If you find damage: | X | | | | |
| | | - Tell Airbus about the results. | | X | | | |
| | | (9) If you removed components, install serviceable components: - For the MLG actuating cylinder (Ref. AMM TASK 32-31-46-400-001) - For the MLG lockstay actuating-cylinder (Ref. AMM TASK 32-11-21-400-001) - For the MLG lockstay assembly (Ref. AMM TASK 32-11-17-400-001) - For the MLG leg assembly (Ref. AMM TASK 32-11-11-400-001) - For the MLG side-stay assembly (Ref. AMM TASK 32-11-16-400-001) - For the MLG shock absorber (Ref. AMM TASK 32-11-13-400-001) - For the MLG axle adaptor-sleeve (Ref. AMM TASK 32-42-71-400-001) - For the MLG wheel (Ref. AMM TASK 32-41-11-400-006) - For the MLG brake (Ref. AMM TASK 32-42-27-400-001) (Ref. AMM D/O 32-42-27-40) - For the MLG brake fan (Ref. AMM TASK 32-48-51-400-005). | X | | | | |
E. Inspection of the Wings
Subtask 05-51-24-210-052-A ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Wings | | | | | |
| A. | | Examine the skin panels for: - damage to the paint, - distortion, - 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 and rear spars, the internal structure and the fasteners for: - distortion, - cracks, - the condition of the sealant beads, - pulled fasteners. | | X | | | |
| | | (4) Close access to the wings tanks (Ref. AMM TASK 28-10-00-910-002). | | X | | | |
| | | (5) Examine the ducts, lines, pipes, mechanical linkages and their supports for: - distortion, - cracks or leaks of fluid, - the correct attachment of components, - damage. | | X | | | |
| 2. | | Flaps and flap track fairings | | | | | |
| A. | | Examine the flaps and the bottom flap track fairings for: - distortion, - dents, cracks, pulled or torn fasteners, - damage to the paint. | X | | | | |
| B. | | At rib 6, examine the flap track fairing and the adjacent structure for: - damage, - cracks, pulled or torn fasteners, - distortion. If you find damage: | X | | | | |
| | | (1) Examine the flap and carriages and tracks/beams for: - distortion, - cracks, - damage. | | X | | | |
| | | (2) Examine the adjacent structure for: - distortion, - cracks, pulled or torn fasteners, - damage. | | X | | | |
| | | (3) Examine the wing internal structure adjacent to the front and aft mountings of the flap beams for: - distortion, - cracks, - damage to the sealant. | | X | | | |
| | | (4) Examine the area where the MLG is attached and the adjacent structure for: - cracks or leaks of fuel, - distortion. | | X | | | |
F. Inspection of the Nacelles, Pylons and Engines
Subtask 05-51-24-210-052-B ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the Nacelles | | | | | |
| A. | | Externally examine the parts that follow for distortion, delamination, cracks, cracked or flaking paint, loose rivets or signs of shearing: - The air intake cowls - The fan cowls - The thrust reverser cowls. | X | | | | |
| B. | | Open the fan and the thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-040) (Ref. AMM TASK 78-36-00-010-040). | X | | | | |
| | | (1) Internally examine them for cracks, distortion, damaged paintwork or pulled or torn fasteners. | X | | | | |
| C. | | Examine the primary nozzle for correct attachment to the engine, distortion, delamination, cracks, loose rivets or signs of shearing. | X | | | | |
| D. | | Examine the attachment of the nose cowl to the fan case for distortion, cracks or pulled or torn fasteners. | X | | | | |
| E. | | Examine all the cowl attachment points on the pylon and all the cowl hinge fittings. | X | | | | |
| F. | | Examine all the cowl latches for damage and make sure that their operation is satisfactory. | X | | | | |
| | | (1) If you find damage on the thrust reverser cowls during the inspection, do an operational test of the thrust reverser system. Make sure that there is no fouling or binding during the movement (Ref. AMM TASK 78-31-00-710-040). | | X | | | |
| 2. | | Inspection of the Engines | | | | | |
| A. | | Do an inspection of the engines | | | | | |
| | | (1) Examine the engines for Foreign Object Damage (FOD) (Ref. AMM TASK 72-00-00-200-001). | X | | | | |
| | | (2) Examine the engines and the engine equipment for distortion, leakage, damage or signs of impact. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the engine (Ref. AMM TASK 71-00-00-000-040). | | X | | | |
| | | (b) Examine the pylon-to-engine attach fittings. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (c) Install the engine (Ref. AMM TASK 71-00-00-400-040). | | X | | | |
| B. | | Close the fan and thrust-reverser cowl doors (Ref. AMM TASK 78-36-00-410-040) (Ref. AMM TASK 71-13-00-410-040). | X | | | | |
| 3. | | Inspection of the Pylons | | | | | |
| A. | | Externally examine the pylon secondary structure and the pylon primary structure (lateral panels). Make sure that: - There is/are no buckling, shearing, distortion or cracks - The paint is in the correct condition - There are no pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage. | | X | | | |
| | | (b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001). | | X | | | |
| | | (c) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001). | | X | | | |
| | | (e) Install the access panels and doors on the secondary structure. | | X | | | |
| B. | | Open the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-040) and (Ref. AMM TASK 78-36-00-010-040). | X | | | | |
| | | (1) Externally examine the lower spar, the pylon lower area (all the items that you can see) and the cantilever structure, the fan cowl fittings and the thrust reverser fittings. Make sure that: - There is/are no buckling, shearing, distortion or cracks - The paint is in the correct condition - There are no pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage. | | X | | | |
| | | (b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001). | | X | | | |
| | | (c) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001). | | X | | | |
| | | (e) Install the access panels and doors on the secondary structure. | | X | | | |
| C. | | Remove the center fillets from the pylon-to-wing junction (Ref. AMM TASK 54-53-11-000-002). NOTE: This is only applicable for the left and right side panels between RIB4 and RIB5 and at RIB10. This is to make sure that you can see the pylon-to-wing attach fittings and the spigot ball joint. | X | | | | |
| | | (1) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 - The pylon-to-wing aft attach-fitting at RIB10 - The spigot ball joint between RIB4 and RIB5. Make sure that there are no signs of distortion, buckling, cracks or other damage. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the pylon-to-wing attach fittings (Ref. AMM TASK 54-51-17-000-001) and (Ref. AMM TASK 54-51-17-000-002). | | X | | | |
| | | (b) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 (Ref. AMM TASK 54-51-17-200-001) - The shackles at RIB4 and the spigot attach fitting (Ref. AMM TASK 54-51-17-200-003) - The shackles at RIB10 (Ref. AMM TASK 54-51-17-200-004) - The pylon-to-wing aft attach-fitting at RIB10 (Ref. AMM TASK 54-51-17-200-002). | | X | | | |
| | | (c) Contact Airbus. | | X | | | |
| D. | | Do a visual inspection of the engine mounts (all the items that you can see) for cracks or distortion (Ref. AMM TASK 71-21-11-210-040) and (Ref. AMM TASK 71-22-11-210-042). This includes the inspection of: - The pylon-to-engine forward attach-fitting in the forward area of RIB1 - The pylon-to-engine aft attach-fitting at the bottom of RIB3. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the engine (Ref. AMM TASK 71-00-00-000-040). | | X | | | |
| | | (b) Contact Airbus. | | X | | | |
| E. | | (1) Install the center fillets on the pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002). | X | | | | |
| | | (2) Close the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-410-040) (Ref. AMM TASK 78-36-00-410-040). | X | | | | |
F. Inspection of the Nacelles, Engines and Pylons
Subtask 05-51-24-210-052-C ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the Nacelles | | | | | |
| A. | | Externally examine the parts that follow for distortion, delamination, cracks, cracked or flaking paint, loose rivets or signs of shearing: - The air intake cowls - The fan cowls - The thrust reverser cowls. | X | | | | |
| B. | | Open the fan and the thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-010) (Ref. AMM TASK 78-32-00-010-010). | X | | | | |
| | | (1) Internally examine them for cracks, distortion, damaged paintwork or pulled or torn fasteners. | X | | | | |
| C. | | Examine the primary nozzle for correct attachment to the engine, distortion, delamination, cracks, loose rivets, and signs of shearing. | X | | | | |
| D. | | Examine the attachment of the nose cowl to the fan case for distortion, cracks, pulled or torn fasteners. | X | | | | |
| E. | | Examine all the cowl attachment points on the pylon and all the cowl hinge fittings. | X | | | | |
| F. | | Examine all the cowl latches for damage and make sure that their operation is satisfactory. | X | | | | |
| | | (1) If you find damage on the thrust reverser cowls during the inspection, do an operational test of the thrust reverser system. Make sure that there is no fouling or binding during the movement (Ref. AMM TASK 78-31-00-710-041). | | X | | | |
| 2. | | Inspection of the Engines | | | | | |
| A. | | Do an inspection of the engines | | | | | |
| | | (1) Examine the engines for Foreign Object Damage (FOD) (Ref. AMM TASK 72-00-00-200-010). | X | | | | |
| | | (1) Examine the engines and the engine equipment for distortion, leakage, damage or signs of impact. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the engine (Ref. AMM TASK 71-00-20-000-040). | | X | | | |
| | | (b) Examine the pylon-to-engine attach fittings. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (c) Install the engine (Ref. AMM TASK 71-00-20-400-040). | | X | | | |
| B. | | Close the fan and thrust-reverser cowl doors (Ref. AMM TASK 78-32-00-410-010) (Ref. AMM TASK 71-13-00-410-010). | X | | | | |
| 3. | | Inspection of the Pylons | | | | | |
| A. | | Externally examine the pylon secondary structure and the pylon primary structure (lateral panels). Make sure that: - There is/are no buckling, shearing, distortion or cracks - The paint is in the correct condition - There are no pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage. | | X | | | |
| | | (b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001). | | X | | | |
| | | (c) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001). | | X | | | |
| | | (e) Install the access panels and doors on the secondary structure. | | X | | | |
| B. | | Open the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-010) and (Ref. AMM TASK 78-32-00-010-010). | X | | | | |
| | | (1) Externally examine the lower spar, the pylon lower area (all the items that you can see) and the cantilever structure, the fan cowl fittings and the thrust reverser fittings. Make sure that: - There is/are no buckling, shearing, distortion or cracks - The paint is in the correct condition - There are no pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage. | | X | | | |
| | | (b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001). | | X | | | |
| | | (c) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001). | | X | | | |
| | | (e) Install the access panels and doors on the secondary structure. | | X | | | |
| C. | | Remove the center fillets from the pylon-to-wing junction (Ref. AMM TASK 54-53-11-000-002). NOTE: This is only applicable for the left and right side panels between RIB4 and RIB5 and at RIB10. This is to make sure that you can see the pylon-to-wing attach fittings and the spigot ball joint. | X | | | | |
| | | (1) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 - The pylon-to-wing aft attach-fitting at RIB10 - The spigot ball joint between RIB4 and RIB5. Make sure that there are no signs of distortion, buckling, cracks or other damage. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the pylon-to-wing attach fittings (Ref. AMM TASK 54-51-17-000-001) and (Ref. AMM TASK 54-51-17-000-002). | | X | | | |
| | | (b) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 (Ref. AMM TASK 54-51-17-200-001) - The shackles at RIB4 and the spigot attach fitting (Ref. AMM TASK 54-51-17-200-003) - The shackles at RIB10 (Ref. AMM TASK 54-51-17-200-004) - The pylon-to-wing aft attach-fitting at RIB10 (Ref. AMM TASK 54-51-17-200-002). | | X | | | |
| | | (c) Contact Airbus. | | X | | | |
| D. | | Do a visual inspection of the engine mounts (all the items that you can see) for cracks or distortion (Ref. AMM TASK 71-21-12-200-010) and (Ref. AMM TASK 71-22-11-200-010). This includes the inspection of: - The pylon-to-engine forward attach-fitting in the forward area of RIB1 - The pylon-to-engine aft attach-fitting at the bottom of RIB4. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the engine (Ref. AMM TASK 71-00-20-000-040). | | X | | | |
| | | (b) Contact Airbus. | | X | | | |
| E. | | (1) Install the center fillets on the pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002). | X | | | | |
| | | (2) Close the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-410-010) (Ref. AMM TASK 78-32-00-410-010). | X | | | | |
F. Inspection of the Nacelles, Engines and Pylons
Subtask 05-51-24-210-052-E ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the Nacelles | | | | | |
| A. | | Externally examine the parts that follow for distortion, delamination, cracks, cracked or flaking paint, loose rivets or signs of shearing: - The air intake cowls - The fan cowls - The thrust reverser cowls. | X | | | | |
| B. | | Open the fan and the thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-040) (Ref. AMM TASK 78-36-00-010-040). | X | | | | |
| | | (1) Internally examine them for cracks, distortion, damaged paintwork or pulled or torn fasteners. | X | | | | |
| C. | | Examine the primary nozzle for correct attachment to the engine, distortion, delamination, cracks, loose rivets, and signs of shearing. | X | | | | |
| D. | | Examine the attachment of the nose cowl to the fan case for distortion, cracks, pulled or torn fasteners. | X | | | | |
| E. | | Examine all the cowl attachment points on the pylon and all the cowl hinge fittings. | X | | | | |
| F. | | Examine all the cowl latches for damage and make sure that their operation is satisfactory. | X | | | | |
| | | (1) If you find damage on the thrust reverser cowls during the inspection, do an operational test of the thrust reverser system. Make sure that there is no fouling or binding during the movement (Ref. AMM TASK 78-31-00-710-042). | | X | | | |
| 2. | | Inspection of the Engines | | | | | |
| A. | | Do an inspection of the engines | | | | | |
| | | (1) Examine the engines for Foreign Object Damage (FOD) (Ref. AMM TASK 72-00-00-200-006). | X | | | | |
| | | (2) Examine the engines and the engine equipment for distortion, damage or signs of impact. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the engine (Ref. AMM TASK 71-00-00-000-042). | | X | | | |
| | | (b) Examine the pylon-to-engine attach fittings. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (c) Install the engine (Ref. AMM TASK 71-00-00-400-042). | | X | | | |
| B. | | Close the fan and thrust-reverser cowl doors (Ref. AMM TASK 78-36-00-410-040) (Ref. AMM TASK 71-13-00-410-040). | X | | | | |
| 3. | | Inspection of the Pylons | | | | | |
| A. | | Externally examine the pylon secondary structure and the pylon primary structure (lateral panels). Make sure that: - There is/are no buckling, shearing, distortion or cracks - The paint is in the correct condition - There are no pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage. | | X | | | |
| | | (b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001). | | X | | | |
| | | (c) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001). | | X | | | |
| | | (e) Install the access panels and doors on the secondary structure. | | X | | | |
| B. | | Open the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-040) and (Ref. AMM TASK 78-36-00-010-040). | X | | | | |
| | | (1) Externally examine the lower spar, the pylon lower area (all the items that you can see) and the cantilever structure, the fan cowl fittings and the thrust reverser fittings. Make sure that: - There is/are no buckling, shearing, distortion or cracks - The paint is in the correct condition - There are no pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage. | | X | | | |
| | | (b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001). | | X | | | |
| | | (c) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001). | | X | | | |
| | | (e) Install the access panels and doors on the secondary structure. | | X | | | |
| C. | | Remove the center fillets from the pylon-to-wing junction (Ref. AMM TASK 54-53-11-000-002). NOTE: This is only applicable for the left and right side panels between RIB4 and RIB5 and at RIB10. This is to make sure that you can see the pylon-to-wing attach fittings and the spigot ball joint. | X | | | | |
| | | (1) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 - The pylon-to-wing aft attach-fitting at RIB10 - The spigot ball joint between RIB4 and RIB5. Make sure that there are no signs of distortion, buckling, cracks or other damage. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the pylon-to-wing attach fittings (Ref. AMM TASK 54-51-17-000-001) and (Ref. AMM TASK 54-51-17-000-002). | | X | | | |
| | | (b) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 (Ref. AMM TASK 54-51-17-200-001) - The shackles at RIB4 and the spigot attach fitting (Ref. AMM TASK 54-51-17-200-003) - The shackles at RIB10 (Ref. AMM TASK 54-51-17-200-004) - The pylon-to-wing aft attach-fitting at RIB10 (Ref. AMM TASK 54-51-17-200-002). | | X | | | |
| | | (c) Contact Airbus. | | X | | | |
| D. | | Do a visual inspection of the engine mounts (all the items that you can see) for cracks or distortion (Ref. AMM TASK 71-21-11-210-040) and (Ref. AMM TASK 71-22-11-210-042). This includes the inspection of: - The pylon-to-engine forward attach-fitting in the forward area of RIB1 - The pylon-to-engine aft attach-fitting at the bottom of RIB3. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the engine (Ref. AMM TASK 71-00-00-000-042). | | X | | | |
| | | (b) Contact Airbus. | | X | | | |
| E. | | (1) Install the center fillets on the pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002). | X | | | | |
| | | (2) Close the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-410-040) (Ref. AMM TASK 78-36-00-410-040). | X | | | | |
F. Inspection of the Nacelles, Engines and Pylons
Subtask 05-51-24-210-060-A | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the Nacelles | | | | | |
| A. | | (1) Examine the nacelle external-surface cowls (inlet, fan, thrust reverser, nozzle and centerbody) for: - Failures, cracks, signs of buckling and permanent deformations - Unusual steps and gaps between the external cowl interfaces - Pulled, bent or loose rivets or fasteners - Opened or loose access covers, latches or panels. | X | | | | |
| | | (2) On the thrust reverser cowl-doors: - Open the 4 actuator access covers. - Examine the actuator fittings. | X | | | | |
| | | (3) Examine the edges of the interfacing cowl parts (leading or trailing edges, cowl edges near the pylon or latching areas) for signs of abutment (paint cracks, delamination or impacts). | X | | | | |
| B. | | (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802) and examine the parts that follow for failures, cracks, signs of buckling, permanent deformations or pulled, bent or loose rivets or fasteners: - The internal sides of the doors - The locators - The hold open rod - The hinges and latch fittings - The inlet flange with the engine case. If you find damage: | X | | | | |
| | | (a) Examine the adjacent areas and the adjacent structure of the damaged parts for cracks, failures, damaged fasteners or composite delamination or damage. | | X | | | |
| | | (b) Examine the structure adjacent to the aft bulkhead for cracks, failures or damaged fasteners. | | X | | | |
| C. | | (1) Open the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-010-802) and examine the C-duct skins that you can see (with the thermal blankets). If you find damage: | X | | | | |
| | | (a) Examine the parts that follow for failures, bearing, cracks, permanent deformations or damaged fasteners: - The forward interface with the engine (V-groove and V-blade) - The hinge and latch fittings - The actuator fittings and the forward frame - The interface between the nozzle and the engine - The interface between the centerbody and the engine. | | X | | | |
| | | (b) Examine the adjacent areas and the adjacent structure of the damaged parts for cracks, failures, damaged fasteners or composite delamination or damage. | | X | | | |
| | | (c) Examine the nozzle skins and centerbody skins for cracks, failures or damaged fasteners. | | X | | | |
| D. | | Do a manual extension of the thrust-reverser translating sleeves (Ref. AMM TASK 78-32-00-860-802). | X | | | | |
| | | (1) If you find resistance or unusual noises during the manual deployment of the thrust reverser: | | | | | |
| | | - Stop and replace the thrust reverser. | | X | | | |
| | | (2) If the thrust reverser is correctly deployed, examine the parts that follow for cracks, failures, damaged fasteners or composite delamination or damage: - The blocker door - The blocker door hinges - The drag links - The cascades - The translating sleeves. | X | | | | |
| E. | | If there is no damage, do a manual retraction of the thrust-reverser translating sleeves (Ref. AMM TASK 78-32-00-860-803). | X | | | | |
| F. | | Do an operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-805). Make sure that the thrust reversers can move fully and freely. | X | | | | |
| 2. | | Inspection of the Engines | | | | | |
| A. | | Do an inspection of the engines | | | | | |
| | | (1) Examine the engines for Foreign Object Damage (FOD) (Ref. AMM TASK 72-00-00-210-807). | X | | | | |
| | | (2) Examine the engines and the engine equipment for distortion, damage and signs of impact. If you find damage: | X | | | | |
| | | (a) Remove the engine (Ref. AMM TASK 71-00-51-000-802). | | X | | | |
| | | (b) Examine the engine-to-pylon attachment fittings. If you find damage: | | X | | | |
| | | - Tell Airbus about the results. | | | X | | |
| | | (c) Install the engine (Ref. AMM TASK 71-00-51-400-802). | | X | | | |
| B. | | Close the thrust reverser doors and the fan cowl doors (Ref. AMM TASK 78-36-00-410-802) (Ref. AMM TASK 71-13-00-410-802). | X | | | | |
| 3. | | 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:
| | 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. | 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 | | | | |
G. Inspection of the Cockpit and Cabin Equipment/Furnishings and the Cargo Compartments
5. Close-up| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the cockpit and cabin equipment/furnishings | | | | | |
| A. | | Do a visual check for disconnected parts, integrity of the latches and other damage 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:
| X | | | | |
| | | (3) Examine the cargo restraint system, door nets, divider nets and net attachment points. | X | | | | |
Subtask 05-51-24-866-051-A Subtask 05-51-24-410-050-A
B. Close Access
(1) Close all the access panels that you opened for the inspection.
(2) Close the doors of the main gear (Ref. AMM TASK 32-12-00-410-001).
(3) Close the doors of the nose gear (Ref. AMM TASK 32-22-00-410-001).
(4) Remove the WARNING NOTICE(S).
(5) Remove the access platform(s).
(6) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(1) Close all the access panels that you opened for the inspection.
(2) Close the doors of the main gear (Ref. AMM TASK 32-12-00-410-001).
(3) Close the doors of the nose gear (Ref. AMM TASK 32-22-00-410-001).
(4) Remove the WARNING NOTICE(S).
(5) Remove the access platform(s).
(6) Remove the ground support and maintenance equipment, the special and standard tools and all other items.