DOC AIRBUS | AMM A320FInspections After a Hard Landing or a Hard Overweight Landing for Aircraft with Enhanced DMU/FDIMU Load Report 15
TASK 05-51-11-200-004-B
Inspections After a Hard Landing or a Hard Overweight Landing for Aircraft with Enhanced DMU/FDIMU Load Report 15
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 a load report 15 (trigger code 4XXX), you must:
If the landing occurs with one MLG or NLG shock absorber deflated, damage can occur on the landing gear components or on the adjacent structure. It is possible that the FCR or load report 15 do not identify the damage. Contact Airbus for more instructions.
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 05-51-11-210-090-A ** ON A/C NOT FOR ALL
Subtask 05-51-11-210-105-A ** ON A/C NOT FOR ALL
Subtask 05-51-11-410-055-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.03.31 22:51:17 UTC
Inspections After a Hard Landing or a Hard Overweight Landing for Aircraft with Enhanced DMU/FDIMU Load Report 15
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 a load report 15 (trigger code 4XXX), you must:
- Do an analysis of the landing parameters.
- If necessary, do the subsequent steps.
If the landing occurs with one MLG or NLG shock absorber deflated, damage can occur on the landing gear components or on the adjacent structure. It is possible that the FCR or load report 15 do not identify the damage. Contact Airbus for more instructions.
NOTE: An accurate load report <15> is available on:
(a) All aircraft that have an Flight Data Interface and Management Unit (FDIMU) (FIN10TV) or
(b) Aircraft that have a Data Management Unit (DMU) (FIN 1TV) with the software (FIN 1TV2) that follows:
2. Job Set-up Information(a) All aircraft that have an Flight Data Interface and Management Unit (FDIMU) (FIN10TV) or
(b) Aircraft that have a Data Management Unit (DMU) (FIN 1TV) with the software (FIN 1TV2) that follows:
- DMU (FIN 1TV) Part Number (P/N) ED45A100 with software (FIN 1TV2) P/N 360-03587-320
- DMU (FIN 1TV) P/N ED45A300 with software (FIN 1TV2) P/N 360-03796-015
- DMU (FIN 1TV) P/N ED45A300 with software (FIN 1TV2) P/N 360-03796-016
- DMU (FIN 1TV) P/N 795040-31-003.
To know the P/Ns of the DMU/FDIMU and related software, you can refer to the Line Replaceable Unit (LRU) identification page or Illustrated Parts Catalog (IPC) 31-36-08.
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) |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 312AR, 321AL, 322AL, 322CL, 323AL, 323AR, 325AL, 325AR | |
| 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 07-11-00-586-002-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 71-00-00-710-012-B | Test No.3 : Idle Leak Check |
| TASK 71-00-00-710-013-C | Test No.11 : High Power Assurance Test |
| TASK 71-00-20-000-040-A | Removal of the Power Plant |
| TASK 71-00-20-000-040-A-01 | Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG) |
| TASK 71-00-51-000-802-A | Removal of the Power Plant (Bootstrap Method) |
| TASK 71-00-51-000-802-A-01 | Removal of the Power Plant (JacXson Method) |
| TASK 71-13-00-010-010-A | Opening of the Fan Cowls 437AL(447AL),438AR(448AR) |
| TASK 71-13-00-010-040-A | Opening of the Fan Cowl Doors |
| TASK 71-13-00-010-040-B | Opening of the Fan Cowl Doors |
| TASK 71-13-00-010-802-A | Opening of the Fan Cowl Doors |
| TASK 71-13-00-410-010-A | Closing of the Fan Cowls 437AL(447AL),438AR(448AR) |
| TASK 71-13-00-410-040-A | Closing of the Fan Cowl Doors |
| TASK 71-13-00-410-040-B | Closing of the Fan Cowl Doors |
| TASK 71-13-00-410-802-A | Closing of the Fan Cowl Doors |
| TASK 71-21-11-210-040-A | Detailed Inspection of Forward Engine Mount Installation |
| TASK 71-21-11-210-040-B | Detailed Inspection of the Forward Engine Mount |
| TASK 71-21-12-200-010-A | Detailed Inspection of FWD Engine Mount Installation |
| TASK 71-22-11-200-010-A | Detailed Inspection of Aft Engine Mount Installation |
| TASK 71-22-11-210-042-A | Detailed Inspection of Aft Engine Mount Installation |
| TASK 71-22-11-210-042-B | Detailed Inspection of Aft Engine Mount Installation |
| TASK 72-00-00-200-003-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 72-00-00-200-012-A | Borescope Inspection of the Low Pressure (LP) Turbine |
| TASK 72-00-00-200-013-B | Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes |
| TASK 72-00-00-200-014-B | Borescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments |
| TASK 72-00-00-200-014-B-01 | Borescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments |
| TASK 72-00-00-200-015-B | Borescope Inspection of the Stage 2 High Pressure Turbine (HPT) Blades and Duct Segments |
| TASK 72-00-00-200-016-B | Inspection of the HP Compressor |
| TASK 72-00-00-200-016-B-01 | Inspection of the HP Compressor |
| TASK 72-00-00-200-017-B | Inspection of the LP Compressor |
| TASK 72-00-00-200-812-A | Inspection of the Engine after Exposure to Excessive Turbulence, High Aircraft Lateral Loads or Heavy or Overweight Landings |
| TASK 78-31-00-710-040-A | Operational Test of the Thrust Reverser System |
| TASK 78-31-00-710-040-A-01 | Operational Test of the Thrust Reverser without CFDS - Engine not Running |
| TASK 78-31-00-710-040-A-02 | Operational Test of the Thrust Reverser without CFDS - Engine Running |
| TASK 78-31-00-710-041-A | Operational Test of the Thrust Reverser System with the CFDS |
| TASK 78-31-00-710-041-A-02 | Operational test of the Thrust Reverser without the CFDS and Engine Running |
| TASK 78-31-00-710-042-A | Operational Test of the Thrust Reverser System |
| TASK 78-31-00-710-805-A | Operational Test of Thrust Reverser with MCDU |
| TASK 78-31-00-710-805-A-01 | Thrust Reverser Cycling Test (Engine Running) |
| TASK 78-32-00-010-010-A | Opening of the Thrust Reverser Halves |
| TASK 78-32-00-410-010-A | Closing of the Thrust Reverser Halves |
| TASK 78-32-00-860-010-A | Manual Extension of the Thrust Reverser Translating Sleeves |
| TASK 78-32-00-860-011-A | Manual Retraction of the Thrust Reverser Translating Sleeves |
| TASK 78-32-00-860-802-A | Manual Extension of the Thrust-Reverser Translating Sleeves |
| TASK 78-32-00-860-803-A | Manual Retraction of the Thrust-Reverser Translating Sleeves |
| TASK 78-32-41-860-001-A | Manual Deployment of the Blocker Door |
| TASK 78-32-41-860-002-A | Manual Stowing of the Blocker Door |
| TASK 78-32-41-860-040-A | Manual Deployment of the Blocker Door |
| TASK 78-32-41-860-041-A | Manual Stowing of the Blocker Door |
| TASK 78-36-00-010-040-A | Opening of the Thrust Reverser Doors |
| TASK 78-36-00-010-040-B | Opening of the Thrust Reverser Doors |
| TASK 78-36-00-010-802-A | Opening of the Thrust Reverser Cowl-Doors |
| TASK 78-36-00-410-040-A | Closing of the Thrust Reverser Doors |
| TASK 78-36-00-410-040-B | Closing of the Thrust Reverser Doors |
| TASK 78-36-00-410-802-A | Closing of the Thrust Reverser Cowl-Doors |
| TASK 79-00-00-200-010-A | Inspection of the Oil System |
| TASK 31-37-51-00 | AIDS - STRUCTURE REPORTS - DESCRIPTION AND OPERATION |
Subtask 05-51-11-210-090-A ** ON A/C NOT FOR ALL
A. Inspection Requirements for a Hard Landing or a Hard Overweight Landing
(1) Definitions
There are different categories of hard landings or hard overweight landings:
(a) Hard landing
A hard landing is a landing with an aircraft weight that is equal to or less than the Maximum Landing Weight (MLW) and:
A severe hard landing is a landing with an aircraft weight that is equal to or less than the MLW and:
A hard overweight landing is a landing with an aircraft weight that is more than the MLW and:
A severe hard-overweight landing is a landing with an aircraft weight that is more than the MLW and:
A high pitch-rate de-rotation-landing is a landing during which the de-rotation is too fast.
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) It is the responsibility of the flight crew to make a report if they think that there was a hard landing or a hard overweight landing.
(b) After a crew report of a hard landing or a hard overweight landing or after the generation of load report 15 (trigger code 4XXX):
Hard landing or a Hard Overweight landing Category for Aircraft with Enhanced DMU/FDIMU ** ON A/C NOT FOR ALL
1 If the category of the landing is a hard landing or a hard overweight landing:
a Do the inspections for each 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.
3 If you cannot confirm the impact parameter values with the DMU/FDIMU or the QAR or the DFDR:
a You must do the inspection after a severe hard landing or a severe hard-overweight landing:
(a) We recommend that you get information from the flight crew about the landing conditions, for example:
(c) After a touchdown on the nose gear only or a high pitch-rate de-rotation:
(g) You must also do all the additional checks related to the events given in the FCR or the PFR.
Subtask 05-51-11-481-069-A ** ON A/C NOT FOR ALL (1) Definitions
There are different categories of hard landings or hard overweight landings:
(a) Hard landing
A hard landing is a landing with an aircraft weight that is equal to or less than the Maximum Landing Weight (MLW) and:
- A normal acceleration (VRTA) that is equal to or more than 2.6 g and less than 2.86 g at the aircraft Center of Gravity (CG).
A severe hard landing is a landing with an aircraft weight that is equal to or less than the MLW and:
- A normal acceleration (VRTA) that is equal to or more than 2.86 g at the aircraft CG.
A hard overweight landing is a landing with an aircraft weight that is more than the MLW and:
- A normal acceleration (VRTA) that is equal to or more than 1.7 g and less than 2.6 g at the aircraft CG.
A severe hard-overweight landing is a landing with an aircraft weight that is more than the MLW and:
- A normal acceleration (VRTA) that is equal to or more than 2.6 g at the aircraft CG.
A high pitch-rate de-rotation-landing is a landing during which the de-rotation is too fast.
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) It is the responsibility of the flight crew to make a report if they think that there was a hard landing or a hard overweight landing.
(b) After a crew report of a hard landing or a hard overweight landing or after the generation of load report 15 (trigger code 4XXX):
- You must confirm the effect parameters to know the category of the landing.
- The DMU load report <15> (Ref. AMM TASK 31-37-00-200-001) or
- The QAR data read-out (if available) or
- The DFDR read-out.
| Line | Value for |
|---|---|
| CE | GW |
| S3 and T3 | VRTA |
NOTE: For more information about how to read the load report <15> (Ref. AMM D/O 31-37-51-00).
NOTE: T3 is only available if there was a bounce landing.
For more information about how to read the load report <15> (Ref. AMM D/O 31-37-51-00).
Read the report <15> values to get the impact parameters: For more information about how to read the load report <15> (Ref. AMM D/O 31-37-51-00).
- Aircraft weight in kg = Gross Weight (GW) x 10 or
- Aircraft weight in lbs = GW x 100
- VRTA (normal acceleration) in g = VRTA / 100.
Example: If the load report <15> displays: - GW = 6321 if the aircraft weight is in kg, the aircraft weight is 63210 kg or
- GW = 1393 if the aircraft weight is in lbs, the aircraft weight is 139300 lbs.
- VRTA: 0291, the normal acceleration is 2.91 g.
Hard landing or a Hard Overweight landing Category for Aircraft with Enhanced DMU/FDIMU ** ON A/C NOT FOR ALL - You must do the inspections for that category.
a Do the inspections for each 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.
3 If you cannot confirm the impact parameter values with the DMU/FDIMU or the QAR or the DFDR:
a You must do the inspection after a severe hard landing or a severe hard-overweight landing:
- If you do not find damage during this inspection, the temporary return-to-service of the aircraft is possible. Confirm the category of the hard landing in the next 200 Flight Cycles (FC)/30 days maximum.
- 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:
Send the raw data from the DFDR or from the QAR to Airbus.
Send the data about the event and inspection results to Airbus.
Contact Airbus for technical instructions.
Obey the Airbus instructions before the next flight.
(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.
(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 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.
- 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.
- 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 or the PFR.
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 05-51-11-866-052-A ** ON A/C NOT FOR ALL (1) Make sure that the safety devices are installed on the landing gears (Ref. AMM TASK 32-00-00-481-001).
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 05-51-11-010-052-A ** ON A/C NOT FOR ALL (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).
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 05-51-11-010-056-A ** ON A/C NOT FOR ALL (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).
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 05-51-11-860-053-A ** ON A/C NOT FOR ALL (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).
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(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.
Subtask 05-51-11-210-105-A ** ON A/C NOT FOR ALL
A. General Inspection Recommendations
(2) If it is necessary to open (remove) access panels and doors, examine them.
Make sure that:
Subtask 05-51-11-210-106-A ** ON A/C NOT FOR ALL NOTE: All the inspections are visual unless specified differently in the text. Operators can refer to the Non-destructive 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 (remove) access panels and 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.
B. General Inspection
Do a walk around inspection of the aircraft. Make sure that you cannot see damage and fluid leaks. Carefully examine the landing gears, the wheels, the tires and the brake units.
Subtask 05-51-11-210-091-A ** ON A/C NOT FOR ALL Do a walk around inspection of the aircraft. Make sure that you cannot see damage and fluid leaks. Carefully examine the landing gears, the wheels, the tires and the brake units.
C. Inspection of the NLG
Subtask 05-51-11-210-103-A ** ON A/C NOT FOR ALL NOTE: This inspection is applicable if there was a hard landing or a hard overweight landing on:
- The nose gear only (high pitch-rate de-rotation) or
- The nose and main gears.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 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: - 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 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). | | | | | |
D. Inspection of the NLG Section of the Fuselage
Subtask 05-51-11-210-092-A ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 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 | | | |
E. Inspection of the Main Landing Gears (MLG)
Subtask 05-51-11-210-093-B ** ON A/C NOT FOR ALL NOTE: This inspection contains two inspection procedures:
If you do not know the category, go directly to item 2. Inspection after a severe hard landing or a severe hard overweight-landing.
- Item 1. Inspection after a hard landing or a hard overweight landing
- Item 2. Inspection after a severe hard landing or a severe hard overweight-landing.
If you do not know the category, go directly to item 2. Inspection after a severe hard landing or a severe hard overweight-landing.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the MLG after a hard landing or a hard overweight landing 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 | | | | | |
| 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 (Ref. Fig. 613/TASK 05-51-11-991-023): 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 | | | | |
F. Inspection of the Nacelles
Subtask 05-51-11-210-094-B ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | | | | | | |
| A. | | Examine the nacelle external-surface cowls (inlet, fan cowl doors, thrust reverser, nozzle) for: - Failures, cracks, signs of buckling and permanent deformations - Unusual steps and gaps between external cowl interfaces - Pulled, bent or loose rivets or fasteners - Open or loose access covers, latches or panels. Examine the edges of the interfacing cowl parts (leading or trailing edges, cowl edges near the pylon or latching areas) for signs of abutment (paint cracks, delamination, impacts). | X | | | | |
| B. | | - The internal side of the doors for cracks - The locators - The hinges and latch fittings for permanent deformations. | X | | | | |
| | | If you find damage, examine: - The fittings for cracks, failures, damaged fasteners - The adjacent area for composite delamination. | | X | | | |
| C. | | Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL 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, for any damages or cracks. | X | | | | |
| | | If you find damage, examine: - The hinges and adjacent areas for cracks or failures - The latch fittings for cracks, failure or damaged fasteners. | | X | | | |
| D | | Do a manual deployment of the thrust reverser system (Ref. AMM TASK 78-32-41-860-040). Examine the pivoting doors, pivoting door hinges, actuator, lock, kicker plate and seals. You can then manually stow the thrust reverser (Ref. AMM TASK 78-32-41-860-041). | | X | | | |
| | | If you find resistance or unusual noise during the manual deployment of the thrust reverser, then stop and replace the damaged hardware. | | | X | | |
| E | | If you find damage on the above parts, examine: - The engine and exhaust nozzle - The Common Nozzle Assembly (CNA) and thrust reverser interface for bearing, cracks or failures | | X | | | |
| F | | Do an operational test of the thrust reverser system. Make sure that the thrust reversers can move fully and freely (Ref. AMM TASK 78-31-00-710-040). | X | | | | |
G. Inspection of the Pylons
Subtask 05-51-11-210-095-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 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 | | | | |
H. Inspection of the Engine
(1) Do the inspections after a hard or hard overweight landing (Ref. AMM TASK 72-00-00-200-003).
Subtask 05-51-11-210-093-C ** ON A/C NOT FOR ALL (1) Do the inspections after a hard or hard overweight landing (Ref. AMM TASK 72-00-00-200-003).
I. Inspection of the Nacelles
Subtask 05-51-11-210-094-C ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | | | | | | |
| A. | | Examine the nacelle external-surface cowls (inlet, fan cowl doors, thrust reverser, nozzle) for: - Failures, cracks, signs of buckling and permanent deformations - Unusual steps and gaps between external cowl interfaces - Pulled, bent or loose rivets or fasteners - Open or loose access covers, hatches or panels. Examine the edges of the interfacing cowl parts (leading or trailing edges, cowl edges near the pylon or latching areas) for signs of abutment (paint cracks, delamination, impacts). | X | | | | |
| B. | | - The internal sides 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. | | Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL 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, for any damages or cracks. | X | | | | |
| | | If you find damage, examine: - The hinges and adjacent areas for cracks or failures - The latch fittings for cracks, failure or damaged fasteners. | | X | | | |
| D | | Do a manual deployment of the thrust reverser system (Ref. AMM TASK 78-32-00-860-010). If you find resistance or unusual noises during the manual deployment of the thrust reverser, then stop and remove the thrust reverser. If the thrust reverser is correctly deployed, examine the blocker doors, blocker door hinges, drag links, cascades and translating sleeves. You can then manually stow the thrust reverser (Ref. AMM TASK 78-32-00-860-011). | | X | | | |
| E | | If you find damage on the above parts, inspect: - The engine and exhaust nozzle interface for damaged fasteners - The Common Nozzle Assembly (CNA) and thrust reverser interface for - The inlet-cowl rear bulkhead and | | X | | | |
J. Inspection of the Pylons
Subtask 05-51-11-210-095-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 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 | | | | |
K. Inspection of the Engine (Ref. AMM TASK 72-00-00-200-017) (Ref. AMM TASK 72-00-00-200-016) (Ref. AMM TASK 72-00-00-200-013) (Ref. AMM TASK 72-00-00-200-014) (Ref. AMM TASK 72-00-00-200-015) (Ref. AMM TASK 72-00-00-200-012) (Ref. AMM TASK 79-00-00-200-010) (Ref. AMM TASK 71-00-20-000-040) (Ref. AMM TASK 71-00-00-710-012)
(Ref. AMM TASK 71-00-00-710-013) (Ref. AMM TASK 78-31-00-710-041)
Subtask 05-51-11-210-093-D ** ON A/C NOT FOR ALL (Ref. AMM TASK 71-00-00-710-013) (Ref. AMM TASK 78-31-00-710-041)
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Examine the Engine | | | | | |
| A. | | Turn the fan rotor with your hand in the direction of normal engine rotation. Make sure that there is no bearing roughness, unusual noises and bindings. | X | | | | |
| | | - Rubbing marks on the fan track attrition liner are normal. But, a new rub mark can be a sign that contact occurred between the fan blade tips and the attrition liner during the hard landing or a hard overweight landing. If you see this, then examine the fan blade tips for signs of tip bluing (overheat) or cracking of the tip. It can be necessary to use a mirror to see the reverse side of the fan blade or to remove the blades for detailed inspection. | | X | | | |
| B. | | Examine the primary nozzle. Make sure that: - it is correctly attached to the engine - there is no distortion or cracks, no loose rivets, no signs of shearing or delamination. | X | | | | |
| C. | | Lift the fan cowl doors and hold them open with the hold-open rods. Examine the nose cowl attachments to the fan case. Make sure that there is no distortion, delamination, cracks, pulled or torn fasteners. | X | | | | |
| D. | | Do a general visual inspection of the engine: - lift the Thrust Reverser Halves. Look at the engine fan case and core engine zones. Look for fluid leaks, distorted or broken linkages, brackets or fasteners and for unusual component positions and/or orientations. - look in the exhaust at the LP turbine blades and seals. Rubbing of the seals and blade shrouds is normal. But, heavy rubbing between the shrouds and the blade seal fins such that the fins look flatter, binding interference between the seals and the blade seal fins or signs of powdered or molten material can be a sign that internal damage occurred. If you find damage: | X | | | | |
| | | (1) Repair all the damage and fluid leaks that you can see. | | X | | | |
| | | (2) Do a borescope inspection of the LPC, HPC, Combustor, HPT and LPT as shown in the AMM (Ref. AMM TASK 72-00-00-200-017), (Ref. AMM TASK 72-00-00-200-016), (Ref. AMM TASK 72-00-00-200-013), (Ref. AMM TASK 72-00-00-200-014), (Ref. AMM TASK 72-00-00-200-015) and (Ref. AMM TASK 72-00-00-200-012). You must examine the blade tip condition very carefully (tip curls, bends, rubs or cracks). | | X | | | |
| | | (3) Examine the magnetic chip detectors and the items of the scavenge oil filter for signs of bearing distress (Ref. AMM TASK 79-00-00-200-010). | | X | | | |
| | | (4) If you find damage that is not in AMM limits or if you find bearing material: | | | | | |
| | | - remove the engine (Ref. AMM TASK 71-00-20-000-040). | | | X | | |
| | | (5) Do an Idle Leak Check (Ref. AMM TASK 71-00-00-710-012). - If you find leaks, repair as necessary. | | X | | | |
| | | (6) Do a Power Assurance Check (Ref. AMM TASK 71-00-00-710-013). - Make sure that the engine operates in the operating limits. You must carefully examine the engine N1 and N2 vibration when more than typical engine levels, this can be a sign of internal damage. | | X | | | |
| | | (a) If you cannot get stable engine operation in limits: | | | | | |
| | | - remove the engine (Ref. AMM TASK 71-00-20-000-040). | | | X | | |
| | | (7) Before engine shutdown: - do one thrust reverser deploy and re-stow cycle at idle conditions - or, after shutdown, do an operational test of the thrust reverser system with the CFDS (Ref. AMM TASK 78-31-00-710-041). | | X | | | |
| | | (8) After the test, examine the magnetic chip detectors and the items of the scavenge oil filter for signs of bearing distress (Ref. AMM TASK 79-00-00-200-010). | | X | | | |
| | | (a) If you do not find signs of bearing distress, do the inspection each day for one week, then each week for one month. | | X | | | |
| | | (b) If you find bearing material: | | | | | |
| | | - Remove the engine (Ref. AMM TASK 71-00-20-000-040). | | | X | | |
L. Inspection of the Nacelles
Subtask 05-51-11-210-094-D ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | | | | | | |
| A. | | Examine the nacelle external-surface cowls (inlet, fan cowl doors, thrust reverser, nozzle) for: - Failures, cracks, signs of buckling and permanent deformations - Unusual steps and gaps between external cowl interfaces - Pulled, bent or loose rivets or fasteners - Open or loose access covers, latches or panels. Examine the edges of the interfacing cowl parts (leading or trailing edges, cowl edges near the pylon or latching areas) for signs of abutment (paint cracks, delamination, impacts). | X | | | | |
| B. | | - 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. | | Thrust Reverser: Hinge Fittings ** ON A/C NOT FOR ALL Thrust Reverser: Latch Fittings ** ON A/C NOT FOR ALL 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, for any damages or cracks. | X | | | | |
| | | If you find damage, examine: - The hinges and adjacent areas for cracks or failures - The latch fittings for cracks, failure or damaged fasteners. | | X | | | |
| D | | Do a manual deployment of the thrust reverser system (Ref. AMM TASK 78-32-41-860-001). Examine the pivoting doors, pivoting door hinges, actuator, lock, kicker plate and seals. You can then manually stow the thrust reverser (Ref. AMM TASK 78-32-41-860-002). | | X | | | |
| | | If you find resistance or unusual 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 - The Common Nozzle Assembly (CNA) and thrust reverser interface for bearing, cracks or failures - The inlet-cowl rear bulkhead and | | X | | | |
| F | | Do an operational test of the thrust reverser system. Make sure that the thrust reversers can move fully and freely (Ref. AMM TASK 78-31-00-710-042). | X | | | | |
M. Inspection of the Pylons
Subtask 05-51-11-210-095-D ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the Pylons | | | | | |
| A. | | Externally examine the pylon secondary structure and the pylon primary structure (lateral panels). Make sure that: - There is/are no buckling, shearing, distortion or cracks - The paint is in the correct condition - There are no pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage. | | X | | | |
| | | (b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001). | | X | | | |
| | | (c) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001). | | X | | | |
| | | (e) Install the access panels and doors on the secondary structure. | | X | | | |
| B. | | Open the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-040) and (Ref. AMM TASK 78-36-00-010-040). | X | | | | |
| | | (1) Externally examine the lower spar, the pylon lower area (all the items that you can see) and the cantilever structure, the fan cowl fittings and the thrust reverser fittings. Make sure that: - There is/are no buckling, shearing, distortion or cracks - The paint is in the correct condition - There are no pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors from the damaged area to see the internal damage. | | X | | | |
| | | (b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-001). | | X | | | |
| | | (c) Internally examine the pylon secondary structure and the pylon primary structure (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners or other damage. This includes: - The lower and upper spars - The ribs - The lateral panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The electrical cables - Failure on pipes and ducts - Leaks in the drain pipes - The hydraulic and fuel pipes - The bleed-air system components. | | X | | | |
| | | If you find damage: | | | | | |
| | | - Contact Airbus. | | | X | | |
| | | (d) Install the access doors on the primary structure (Ref. AMM TASK 54-51-21-400-001). | | X | | | |
| | | (e) Install the access panels and doors on the secondary structure. | | X | | | |
| C. | | Remove the center fillets from the pylon-to-wing junction (Ref. AMM TASK 54-53-11-000-002). NOTE: This is only applicable for the left and right side panels between RIB4 and RIB5 and at RIB10. This is to make sure that you can see the pylon-to-wing attach fittings and the spigot ball joint. | X | | | | |
| | | (1) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 - The pylon-to-wing aft attach-fitting at RIB10 - The spigot ball joint between RIB4 and RIB5. Make sure that there are no signs of distortion, buckling, cracks or other damage. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the pylon-to-wing attach fittings (Ref. AMM TASK 54-51-17-000-001) and (Ref. AMM TASK 54-51-17-000-002). | | X | | | |
| | | (b) Do a detailed visual inspection of: - The pylon-to-wing forward attach-fittings at RIB4 (Ref. AMM TASK 54-51-17-200-001) - The shackles at RIB4 and the spigot attach fitting (Ref. AMM TASK 54-51-17-200-003) - The shackles at RIB10 (Ref. AMM TASK 54-51-17-200-004) - The pylon-to-wing aft attach-fitting at RIB10 (Ref. AMM TASK 54-51-17-200-002). | | X | | | |
| | | (c) Contact Airbus. | | X | | | |
| D. | | Do a visual inspection of the engine mounts (all the items that you can see) for cracks or distortion (Ref. AMM TASK 71-21-11-210-040) and (Ref. AMM TASK 71-22-11-210-042). This includes the inspection of: - The pylon-to-engine forward attach-fitting in the forward area of RIB1 - The pylon-to-engine aft attach-fitting at the bottom of RIB3. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) Remove the engine (Ref. AMM TASK 71-00-00-000-042). | | X | | | |
| | | (b) Contact Airbus. | | X | | | |
| E. | | (1) Install the center fillets on the pylon-to-wing junction (Ref. AMM TASK 54-53-11-400-002). | X | | | | |
| | | (2) Close the fan and thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-410-040) (Ref. AMM TASK 78-36-00-410-040). | X | | | | |
N. Inspection of the Engine
(1) Do the inspections after a hard or hard overweight landing (Ref. AMM TASK 72-00-00-200-008).
Subtask 05-51-11-210-093-H ** ON A/C NOT FOR ALL (1) Do the inspections after a hard or hard overweight landing (Ref. AMM TASK 72-00-00-200-008).
O. Inspection of the Nacelles
Subtask 05-51-11-210-094-H ** 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 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 4 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 | | | | |
P. Inspection of the Pylons
Subtask 05-51-11-210-095-H ** ON A/C NOT FOR ALL | ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the Pylons | | | | | |
| A. | | Externally examine the pylon primary and secondary structures for buckling, shearing, distortion, cracks, damaged paintwork or pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors of the damaged area to see the internal damage. | | X | | | |
| | | (b) On the primary structure, remove the access doors (Ref. AMM TASK 54-51-21-000-802). | | X | | | |
| | | (c) Internally examine the primary and secondary structures (all the items that you can see) for distortion, buckling, cracks, defective attachment, missing fasteners, leaks or other damage. This includes: - The lower and upper spars - The ribs - The side panels - The fire protection system (specially the attachments of the fire extinguishing bottles) - The pipes and the ducts - The drain pipes - The hydraulic pipes. | | X | | | |
| | | (d) On the primary structure, install the access doors (Ref. AMM TASK 54-51-21-400-802). | | X | | | |
| B. | | Open the fan cowl doors and the thrust-reverser cowl doors (Ref. AMM TASK 71-13-00-010-802) and (Ref. AMM TASK 78-36-00-010-802). | X | | | | |
| | | (1) Externally examine the bottom area of the primary structure, the forward secondary structure (all the items that you can see), the fan cowl fittings and the thrust reverser fittings for: - Buckling or - Shearing or - Distortion or - Cracks or - Damaged paintwork or - Pulled or missing fasteners/rivets. | X | | | | |
| | | If you find damage: | | | | | |
| | | (a) On the secondary structure, remove the access panels and doors 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. | 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 | | | | |
Q. Inspection of the Engine
Do the inspection of the engine after a hard landing, or a hard overweight landing, or a severe hard landing or a severe hard overweight landing (Ref. AMM TASK 72-00-00-200-812).
Subtask 05-51-11-210-096-A ** ON A/C NOT FOR ALL Do the inspection of the engine after a hard landing, or a hard overweight landing, or a severe hard landing or a severe hard overweight landing (Ref. AMM TASK 72-00-00-200-812).
R. Inspection of the Wing
Subtask 05-51-11-210-096-C ** ON A/C NOT FOR ALL NOTE: This inspection contains two inspection procedures:
If you do not know the category, go directly to item 2.
Inspection after a severe hard landing or a severe hard overweight-landing.
- Item 1. Inspection after a hard landing or a hard overweight landing
- Item 2. Inspection after a severe hard landing or a severe hard overweight landing.
If you do not know the category, go directly to item 2.
Inspection after a severe hard landing or a severe hard overweight-landing.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the wing after a hard landing or a hard overweight landing | | | | | |
| 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. 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: (1) 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). | | | | | |
R. Inspection of the Wing
Subtask 05-51-11-210-096-D ** ON A/C NOT FOR ALL NOTE: This inspection contains two inspection procedures:
If you do not know the category, go directly to item 2.
Inspection after a severe hard landing or a severe hard overweight-landing.
- Item 1. Inspection after a hard landing or a hard overweight landing
- Item 2. Inspection after a severe hard landing or a severe hard overweight landing.
If you do not know the category, go directly to item 2.
Inspection after a severe hard landing or a severe hard overweight-landing.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the wing after a hard landing or a hard overweight landing | | | | | |
| 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 visual inspection of the slat 1 outboard end area for bent, buckling or 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: (1) 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). | | | | | |
R. Inspection of the Wing
Subtask 05-51-11-210-097-A ** ON A/C NOT FOR ALL NOTE: This inspection contains two inspection procedures:
If you do not know the category, go directly to item 2.
Inspection after a severe hard landing or a severe hard overweight-landing.
- Item 1. Inspection after a hard landing or a hard overweight landing
- Item 2. Inspection after a severe hard landing or a severe hard overweight landing.
If you do not know the category, go directly to item 2.
Inspection after a severe hard landing or a severe hard overweight-landing.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the wing after a hard landing or a hard overweight landing | | | | | |
| 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: (1) 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). | | | | | |
S. Inspection of the Flaps
Subtask 05-51-11-210-100-A ** 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 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 | | | |
T. Inspection of the Fuselage
Subtask 05-51-11-210-099-A ** ON A/C NOT FOR ALL NOTE: This inspection contains two inspection procedures:
If you do not know the category, go directly to item 2. Inspection after a hard landing or a severe hard overweight landing.
- Item 1. Inspection after a hard landing or a hard overweight landing
- Item 2. Inspection after a severe hard landing or a severe hard overweight landing.
If you do not know the category, go directly to item 2. Inspection after a hard landing or a severe hard overweight landing.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the fuselage after a hard landing or a hard overweight landing | | | | | |
| 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 | | | | | |
| A. | | Do the inspection of the fuselage after a hard landing or a hard overweight landing (Ref. item 1.) | 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 | | | | |
U. Inspection of the Tail Area
(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)
Subtask 05-51-11-210-098-A ** ON A/C NOT FOR ALL NOTE: This inspection contains two inspection procedures:
If you do not know the category, go directly to item 2. Inspection after a severe hard landing or a severe hard overweight landing.
(Ref. AMM TASK 27-44-00-710-002) (Ref. AMM TASK 55-16-00-200-001)- Item 1. Inspection after a hard landing or a hard overweight landing
- Item 2. Inspection after a severe hard landing or a severe hard overweight landing.
If you do not know the category, go directly to item 2. Inspection after a severe hard landing or a severe hard overweight landing.
(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 | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the tail area after a hard landing or a hard overweight landing | | | | | |
| 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 | | | | | |
| A. | | Do the inspection of the tail area after a hard landing or a hard overweight landing (Ref. item 1.) | 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 | | | | |
V. Inspection of the Avionics compartment
Subtask 05-51-11-210-101-A ** ON A/C NOT FOR ALL NOTE: This inspection is necessary only for a severe hard landing or a severe hard overweight landing.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 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 | | | | |
W. Inspection of the Water tanks
Subtask 05-51-11-210-102-A ** ON A/C NOT FOR ALL NOTE: This inspection is necessary only for a severe hard landing or a severe hard overweight landing
| 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 | | | | |
X. Inspection of the Cockpit and Cabin Equipment/Furnishings, the Cargo Compartments and the Emergency Locator Transmitter (ELT)
Subtask 05-51-11-210-149-A ** ON A/C NOT FOR ALL NOTE: This inspection is necessary only for a severe hard landing or a severe hard overweight-landing.
| 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 (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:
| 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 | | | |
Y. Inspection of the Rear Fuselage and the Vertical Tail Plane (VTP)
You must do this inspection only if the landing that occurred was a drift landing.
5. Close-upYou must do this inspection only if the landing that occurred was a drift landing.
NOTE: The inspection of the rear fuselage and VTP is not necessary after a landing that was not a drift landing.
| ITEM | INSP CODE | INSPECTION TASKS | PHASE 1 | PHASE 2 | PHASE 3 | INSP SIGN | REF. FIG. |
|---|---|---|---|---|---|---|---|
| 1. | | Inspection of the tail area after a drift landing. | | | | | |
| A. | | Do a detailed visual inspection (DVI) for distortion, cracks, damaged paintwork or sealant and loose or pulled fasteners on the external surface of the rear fuselage: | | | | | |
| | | (1) The external surface below the fin-to-fuselage fairings (Ref. AMM TASK 53-51-00-210-018) | X | | | | |
| | | (2) The fin-to-fuselage FWD, MID, and AFT attach lugs (Ref. AMM TASK 53-51-00-210-012) | X | | | | |
| | | (3) The transverse load rod attachments (Ref. AMM TASK 53-51-00-210-012). | X | | | | |
| B. | | Do a detailed visual inspection (DVI) for distortion, cracks, damaged paintwork or sealant and loose or pulled fasteners on the internal surface of the rear fuselage at Zone 310: | | | | | |
| | | (1) Between FR70 and FR74 above stringers 19LH and 19RH (Ref. AMM TASK 53-51-00-210-020) | X | | | | |
| | | (2) All areas of FR77 (Ref. AMM TASK 53-51-00-210-020). | X | | | | |
| C. | | Do a detailed visual inspection (DVI) for distortion, cracks, damaged paintwork or sealant and loose or pulled fasteners on the vertical tail plane (VTP): | | | | | |
| | | (1) The attach-fitting areas (this includes the load introduction area at the skin panels) (Ref. AMM TASK 55-36-00-210-001) | X | | | | |
| | | (2) The RIB1 lower surface | X | | | | |
| | | (3) The RIB2 upper and lower surfaces, from the inspection holes at the VTP front and rear spars | X | | | | |
| | | (4) Rudder hinge arms 1 to 7 (Ref. AMM TASK 55-30-00-210-001) (Ref. AMM TASK 55-30-00-210-002) | X | | | | |
| | | (5) Actuator attach-fittings 1 to 3 (Ref. AMM TASK 55-30-00-210-001) | X | | | | |
| | | (6) The external surface of the front spar between RIB1 and RIB2 | X | | | | |
| | | (7) The external surface of the front spar between RIB10 and RIB11 | X | | | | |
| | | (8) The external surface of the rear spar between RIB1 and RIB11. | X | | | | |
| D. | | Do a detailed visual inspection (DVI) for distortion, cracks, damaged paintwork or sealant and loose or pulled fasteners on the rudder: | | | | | |
| | | (1) Rudder attach-fittings 1 to 7 (Ref. AMM TASK 55-40-00-210-004) (Ref. AMM TASK 55-40-00-210-005) | X | | | | |
| | | (2) Actuator attach-fittings 1 to 3 (Ref. AMM TASK 55-40-00-210-004). | X | | | | |
Subtask 05-51-11-410-055-A ** ON A/C NOT FOR ALL
A. Special Closing of Access After a Drift Landing Inspection
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the trailing-edge access panels of the vertical stabilizer (Ref. AMM TASK 55-33-13-410-002).
(3) Install leading-edge access panels 322AL and 322CL of the vertical stabilizer (Ref. AMM TASK 55-32-11-400-001).
(4) Install rudder fairings 325AL and 325AR (Ref. AMM TASK 53-55-12-400-001).
(5) Install dorsal fin 321AL (Ref. AMM TASK 53-45-11-400-001).
(6) Install vertical stabilizer fairings 323AL and 323AR (Ref. AMM TASK 53-55-11-400-001).
(7) Close access door 312AR.
(8) Remove the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE in position at Zone 320.
(9) Remove the WARNING NOTICE(S).
Subtask 05-51-11-410-051-A ** ON A/C NOT FOR ALL (1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the trailing-edge access panels of the vertical stabilizer (Ref. AMM TASK 55-33-13-410-002).
(3) Install leading-edge access panels 322AL and 322CL of the vertical stabilizer (Ref. AMM TASK 55-32-11-400-001).
(4) Install rudder fairings 325AL and 325AR (Ref. AMM TASK 53-55-12-400-001).
(5) Install dorsal fin 321AL (Ref. AMM TASK 53-45-11-400-001).
(6) Install vertical stabilizer fairings 323AL and 323AR (Ref. AMM TASK 53-55-11-400-001).
(7) Close access door 312AR.
(8) Remove the ACCESS PLATFORM 12M (40 FT) - ADJUSTABLE in position at Zone 320.
(9) Remove the WARNING NOTICE(S).
B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Fully retract the Flaps (Ref. AMM TASK 27-50-00-866-009)
(3) Fully retract the Slats (Ref. AMM TASK 27-80-00-866-005)
(4) Fully retract the Spoilers (Ref. AMM TASK 27-60-00-866-002)
(5) Close the access doors and panels opened during the inspection.
(6) Close the nose gear doors (Ref. AMM TASK 32-22-00-410-001).
(7) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001).
(8) Remove the access platform(s).
(9) Remove the WARNING NOTICE(S).
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Fully retract the Flaps (Ref. AMM TASK 27-50-00-866-009)
(3) Fully retract the Slats (Ref. AMM TASK 27-80-00-866-005)
(4) Fully retract the Spoilers (Ref. AMM TASK 27-60-00-866-002)
(5) Close the access doors and panels opened during the inspection.
(6) Close the nose gear doors (Ref. AMM TASK 32-22-00-410-001).
(7) Close the main gear doors (Ref. AMM TASK 32-12-00-410-001).
(8) Remove the access platform(s).
(9) Remove the WARNING NOTICE(S).