DOC AIRBUS | AMM A320FStorage Periodic Ground Checks
TASK 10-12-00-553-802-A
Storage Periodic Ground Checks
This procedure gives the periodic ground checks of the aircraft during a storage period:
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Referenced Information
3. Job Set-up
Subtask 10-12-00-941-059-A
Subtask 10-12-00-210-092-A
5. Close-up
Subtask 10-12-00-942-068-A
[Rev.10 from 2021]
2026.03.31 22:53:23 UTC
Storage Periodic Ground Checks
WARNING:
BEFORE YOU OPEN AN AIRCRAFT DOOR, MAKE SURE THAT THE CABIN IS NOT PRESSURIZED. TO DO THIS, MAKE SURE THAT:
- THE AIR CONDITIONING GROUND-CART IS NOT CONNECTED TO THE AIRCRAFT, AND
- THE FORWARD AVIONICS-COMPARTMENT ACCESS-DOOR 811 IS OPEN.
IF THERE IS REMAINING PRESSURE IN THE AIRCRAFT, THE DOOR CAN OPEN WITH A SUDDEN FORCE. THIS CAN CAUSE INJURY TO YOU OR KILL YOU, AND/OR CAUSE DAMAGE TO THE AIRCRAFT.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING:
DO NOT USE THE EMERGENCY LIGHTS TO ILLUMINATE THE CABIN DURING MAINTENANCE. IF YOU USE THE EMERGENCY LIGHTS DURING MAINTENANCE, YOU CAN DECREASE THE LIFE OF THE EPSU BATTERIES AND THEIR INTERNAL VOLTAGE. IF THE INTERNAL VOLTAGE OF THE EPSU BATTERIES IS TOO LOW WHEN YOU CHARGE THEM, THERE IS A RISK OF EXPLOSION.
CAUTION:
DURING STORAGE OR PARKING PERIODS, DO NOT STOP OR CHANGE THE MAINTENANCE PROGRAM UNLESS IT WAS AGREED BY THE LOCAL AUTHORITIES. THE MAINTENANCE CALENDAR CLOCK CONTINUES DURING THESE PERIODS.
IF YOU DO THE AMM STORAGE OR PARKING PROCEDURES CORRECTLY, AND IF YOU HAVE THE AGREEMENT OF THE LOCAL AUTHORITIES, IT IS NOT NECESSARY TO DO ALL THE SCHEDULED MAINTENANCE TASKS (SUCH AS MPD TASKS) IMMEDIATELY DURING THE STORAGE/PARKING PERIOD. YOU CAN WAIT UNTIL THE END OF THE PERIOD. BUT YOU MUST DO THEM ALL BEFORE THE NEXT FLIGHT.
CAUTION:
DURING THIS PROCEDURE:
- MAKE SURE THAT THE LANDING GEAR GROUND SAFETIES, LOCKING DEVICES AND WHEEL CHOCKS ARE IN POSITION.
- KEEP THE ACCESS PLATFORM AT A SUFFICIENT DISTANCE FROM THE AIRCRAFT (IN WIND, SHOCK ABSORBER REBOUND CAN CAUSE MOVEMENT OF THE AIRCRAFT).
CAUTION:
BE CAREFUL WHEN YOU USE ALUMINIUM-FOIL ADHESIVE FILM-TAPE 05RAB9 BECAUSE OF ITS HIGH ADHESION CAPACITY. THIS TAPE CAN CAUSE DAMAGE TO THE PAINT DURING THE REMOVAL OF THE TAPE.
1. Reason for the JobThis procedure gives the periodic ground checks of the aircraft during a storage period:
- At 7-day intervals
- At 15-day intervals
- At 1-month intervals
- At 3-month intervals
- At 6-month intervals
- At 1-year intervals
- At 2-year intervals.
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | ACCESS PLATFORM 15M (49 FT) - ADJUSTABLE |
| No specific | 1 | ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE |
| No specific | AR | CHOCK - WHEEL(S) |
| No specific | AR | FINE NYLON NETTING |
| No specific | 3 | SPATULA - NON METALLIC |
| No specific | 1 | WARNING NOTICE(S) |
| 98D27803000000 | 1 | LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.02ABA1) | Phosphate Ester Hydraulic Fluid-General Power - - |
| (Material No.03GBC1) | Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - |
| (Material No.03HBD9) | Synthetic Ester base Grease-General Purpose Low Temp - |
| (Material No.03JCA9) | Silicone base Grease-Mechanisms and Seals - - |
| (Material No.03QDB1) | Dry lubricant-Anti Seizing PTFE Loaded - |
| (Material No.05RAB9) | Adhesive Film Tape-- Aluminium Foil - |
| (Material No.05RNN1) | Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - |
| (Material No.08BBB1) | Non Aqueous Cleaner-- Petroleum Based - |
| (Material No.12ABE2) | Corrosion Preventive Compound-Water Displacing Oily Film System |
| (Material No.12ADB1) | Corrosion Preventive Compound-Water Displacing & Heavy Duty Hard Film - |
| (Material No.12AGC2) | Corrosion Preventive Compound-- Soft Film System |
| (Material No.14HMB1) | Film-- Waterproof Barrier - |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 05-27-10-200-001-A | GENERAL VISUAL INSPECTION OF NOSE GEAR AND NOSE GEAR DOORS (EWIS) |
| TASK 05-27-30-200-001-A | General Visual Inspection of LH/RH Main Landing Gear including Cylinder and Secondary Doors (EWIS) |
| TASK 05-27-30-200-002-A | GENERAL VISUAL INSPECTION OF MAIN LANDING GEAR CYLINDER DOOR (EWIS) |
| TASK 05-27-30-200-003-A | GENERAL VISUAL INSPECTION OF MAIN LANDING GEAR SECONDARY DOOR (EWIS) |
| TASK 05-27-30-200-004-A | GENERAL VISUAL INSPECTION OF MAIN LANDING GEAR MAIN DOORS (EWIS) |
| TASK 07-12-00-582-001-A | Jacking of the Nose Landing Gear |
| TASK 07-12-00-582-002-A | Jacking of the Main Landing Gear |
| TASK 09-10-00-584-002-A | Towing by the Nose Landing Gear from the Front with a Towbar |
| TASK 10-10-00-550-801-A | Parking and Storage Procedure |
| TASK 10-11-00-555-013-A | Installation of the Aircraft Protection Equipment |
| TASK 10-11-00-555-014-A | Removal of the Aircraft Protection Equipment |
| TASK 10-11-00-555-015-A | Procedure for the Installation of Wheel Chocks on Aircraft |
| TASK 10-20-00-556-001-A | Mooring of Aircraft without Weight and Balance Provision on the Landing Gear Legs |
| TASK 10-20-00-556-001-A-01 | Mooring of Aircraft with Weight and Balance Provision on the Landing Gear Legs |
| TASK 12-11-28-650-003-A | Pressure Refuel with Automatic Control |
| TASK 12-11-28-650-004-A | Pressure Refuel with Manual Control |
| TASK 12-14-32-200-001-A | Inspection of the MLG Shock Absorbers before Flight |
| TASK 12-14-32-200-002-A | Check of the NLG Shock Absorber Bottoming |
| TASK 12-21-11-615-002-A | External Cleaning |
| TASK 12-22-27-640-003-A | Lubricate THS Actuator Ball Screw Nut |
| TASK 12-22-27-640-004-A | Lubricate all Carriage Rollers on all Flap Tracks |
| TASK 12-22-27-640-005-A | Lubricate Spoiler No 1 to 5 Actuator Attachments |
| TASK 12-22-27-640-006-A | Lubricate all Track Rollers and Pinions |
| TASK 12-22-27-640-007-A | Lubrication of THS Mechanical Control Chains and Rear Cable (Area of Tension Regulator) with Grease Mat. |
| TASK 12-22-27-640-803-A | Lubrication of Elevator Servocontrol Rod Eye End Bearing |
| TASK 12-22-27-640-804-A | Lubrication of Rudder Servocontrol Rod Eye End Bearing |
| TASK 12-22-27-640-805-A | Lubrication of THS Mechanical Control Chains and Rear Cable (Area of Tension Regulator) with Grease Mat. |
| TASK 12-22-32-640-001-A | Lubrication of Main Landing Gear and Doors |
| TASK 12-22-32-640-002-A | Lubrication of Nose Landing Gear and Doors |
| TASK 12-22-52-640-017-A | Lubrication of the Forward or Aft Cargo-Compartment Door-Seal |
| TASK 12-22-52-640-018-A | Lubrication of the Bulk Cargo-Compartment Door-Seal |
| TASK 12-22-53-640-001-A | Lubrication of Trimmable Horizontal Stabilizer Bearings and Attachment Fittings with Grease Mat. No. 04-004 (or Grease Mat. No. 03HBD9) |
| TASK 12-22-53-640-002-A | Lubrication of Trimmable Horizontal Stabilizer Bearings and Attachment Fittings with Grease Mat. No. 04-037 (or Grease Mat. No. 03GBC1) |
| TASK 12-22-55-640-001-A | Lubrication of Rudder Hinge Bearing No. 6 with Grease Mat. No. 04-004 (or Grease Mat. No. 03HBD9) |
| TASK 12-22-55-640-002-A | Lubrication of Rudder Hinge Bearing No. 6 with Grease MAT. No. 04-037 (or Grease MAT. No. 03GBC1) |
| TASK 12-24-34-600-001-A | Bleeding of the Standby Air Data System |
| TASK 12-31-12-660-002-A | De-Icing of the Aircraft in Power-Off Condition |
| TASK 12-31-21-660-001-A | Cold Weather Maintenance - Air Conditioning |
| TASK 12-31-24-660-001-A | Cold Weather Maintenance - Electrical Power |
| TASK 12-31-25-660-001-A | Cold Weather Maintenance - Equipment/Furnishings |
| TASK 12-31-27-660-001-A | Cold Weather Maintenance - Flight Controls |
| TASK 12-31-28-660-001-A | Cold Weather Maintenance - Fuel |
| TASK 12-31-31-660-001-A | Cold Weather Maintenance - Indicating/Recording systems and Navigation |
| TASK 12-31-32-660-001-A | Cold Weather Maintenance - Landing Gear |
| TASK 12-31-35-660-001-A | Cold Weather Conditions - Maintenance of the Oxygen System |
| TASK 12-31-38-660-001-A | Cold Weather Maintenance - Water/Waste |
| TASK 12-31-49-660-001-A | Cold Weather Maintenance - Auxiliary Power Unit |
| TASK 12-31-51-660-001-A | Cold Weather Maintenance - Structure |
| TASK 12-31-52-660-001-A | Cold Weather Maintenance - Doors |
| TASK 12-31-71-660-001-A | Cold Weather Maintenance - Power Plant |
| TASK 12-31-71-660-802-A | Cold Weather Maintenance - Power Plant |
| TASK 12-32-28-281-001-A | Drain Water Content |
| TASK 12-32-28-281-003-A | Sample Fuel for Microbiological Contamination Analysis |
| TASK 12-32-28-281-005-A | Operate Water Drain Valves in Installed ACT(S) to Drain Accumulated Water |
| TASK 12-32-29-281-001-A | Analyze Hydraulic Fluid |
| TASK 12-33-21-618-001-A-01 | Pre-conditioning through the HP Ground Connection |
| TASK 12-33-21-618-001-A-02 | Pre-conditioning with the APU |
| TASK 12-34-24-869-002-A | Aircraft Grounding (Earthing) for the Maintenance Operations |
| TASK 20-24-11-100-001-A | Cleaning and Protection of the Cables |
| TASK 20-24-12-200-001-A | Check of the Control Cables |
| TASK 20-24-12-200-003-A | Inspection of the Pulleys |
| TASK 21-26-00-710-001-A | Operational Check of the Avionics Equipment Ventilation-System via MCDU |
| TASK 21-26-00-710-001-A-01 | Operational Check of the Avionics Equipment Ventilation (without the CFDS) |
| TASK 21-28-00-710-006-A | Operational Test of the AFT Cargo-Compartment Ventilation-System |
| TASK 21-28-00-720-003-A | Functional Test of the FWD Cargo-Compartment Ventilation-System |
| TASK 24-38-51-000-001-A | Removal of the Battery |
| TASK 24-38-51-400-001-A | Installation of the Battery |
| TASK 24-41-00-861-002-A | Energize the Aircraft Electrical Circuits from the External Power |
| TASK 24-41-00-861-002-A-01 | Energize the Aircraft Electrical Circuits from the APU |
| TASK 24-41-00-861-002-A-02 | Energize the Aircraft Electrical Circuits from Engine 1(2) |
| 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 25-65-51-920-001-A | Discard and Replace Megaphone Batteries |
| TASK 27-14-00-710-001-A | Operational Test of the Aileron and Hydraulic Actuation |
| TASK 27-24-00-710-001-A | Operational Test of the Rudder Hydraulic Actuation |
| TASK 27-34-00-710-001-A | Operational Test of the Elevator and Hydraulic Actuation |
| TASK 27-44-00-710-002-A | Operational Test of the Trimmable Horizontal Stabilizer Actuator with the Individual Hydraulic Systems |
| TASK 27-50-00-866-008-A | Extension of the Flaps on the Ground |
| TASK 27-50-00-866-008-A-01 | Extension of the Flaps/Slats on the Ground |
| TASK 27-50-00-866-009-A | Retraction of the Flaps on the Ground |
| TASK 27-50-00-866-009-A-01 | Retraction of the Flaps/Slats on the Ground |
| TASK 27-54-00-710-001-A | Operational Test of the Flap System |
| TASK 27-64-00-710-001-A | Operational Test of the Spoiler Hydraulic Actuation |
| TASK 27-80-00-866-004-A | Extending the Slats on the Ground |
| TASK 27-80-00-866-005-A | Retracting the Slats on the Ground |
| TASK 27-84-00-710-001-A | Operational Test of the Slat System |
| TASK 28-11-00-600-020-A | Preventative Treatment Procedure for Microbiological Contamination - Biobor Method |
| TASK 28-11-00-600-023-A | Preventative Treatment Procedure for Microbiological Contamination - Kathon Method |
| TASK 28-23-00-720-001-A | Operational Check of Crossfeed Valve Using Individual Motors and Check Fuel Flow in "Open" and Fuel Shut Off in "Closed" Positions |
| TASK 28-24-00-710-002-A | Operational Test of the ENG 1(2) LP Fuel Valve |
| TASK 28-29-00-710-001-A | Operational Test of the APU Low Pressure Fuel Valve using each individual Motor in turn |
| TASK 29-10-00-200-001-A | Check Fluid Level on Reservoir Indicators |
| TASK 29-10-00-200-008-A | Check Nitrogen Charge Pressure on Hydraulic Power Accumulators |
| TASK 29-10-00-863-003-A | Pressurize the Blue Hydraulic System with a Hydraulic Ground Power-Cart |
| TASK 29-10-00-863-003-A-01 | Pressurize the Blue Hydraulic System with the Blue Electric Pump |
| TASK 29-10-00-864-003-A | Depressurize the Blue Hydraulic System |
| TASK 29-23-00-863-001-A | Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump |
| TASK 29-23-00-864-001-A | Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU |
| TASK 29-24-00-863-001-A | Pressurize the Yellow Hydraulic System with the Electric Pump |
| TASK 29-24-00-864-001-A | Depressurize the Yellow Hydraulic System |
| TASK 29-30-00-200-002-A | Check of the Reservoir Quantity Indication on the ECAM Display Unit |
| TASK 32-31-00-710-002-A | Operational Test of the Landing Gear Doors (With False Targets) |
| TASK 32-31-00-710-002-A-01 | Operational Test of the Landing Gear Doors (Without False Targets) |
| TASK 32-31-00-720-002-A | Functional Test of the Normal Extension and Retraction of the Landing Gear |
| TASK 32-41-00-210-002-A | Inspection/Check of the Wheels and Tires |
| TASK 32-41-00-210-003-A | Functional Check of Tire Pressures |
| TASK 32-44-11-200-001-A | Functional Check of Parking/Emergency Brake Accumulator by Reading the Charge Pressure on the Accumulator Gauge |
| TASK 33-51-38-000-001-A | Removal of the Emergency Power Supply Unit (EPSU) |
| TASK 33-51-38-400-001-A | Installation of the Emergency Power Supply Unit (EPSU) |
| TASK 35-10-00-040-001-A | OXY High Pressure Indication-Direct Reading |
| TASK 35-32-42-210-002-A | Check Connecting Hose, Mask and Pressure on Cylinder Pressure Gauge |
| TASK 49-20-00-600-002-A | Preservation/Storage/Return-to-Service of the APU (APS 3200) |
| TASK 49-20-00-600-803-A | APU Preservation / Storage / Return to Service (131-9(A)) |
| TASK 51-74-11-300-001-A | Repair of Corroded Areas |
| TASK 52-10-00-010-001-A | Opening of the Passenger/Crew Door |
| TASK 52-10-00-410-001-A | Closing of the Passenger/Crew Door |
| TASK 52-21-11-000-001-A | Removal of the Emergency Exit Hatch |
| TASK 52-21-11-400-001-A | Installation of the Emergency Exit Hatch |
| TASK 52-22-00-010-001-A | Opening of the Emergency Exit Doors from the Passenger Compartment |
| TASK 52-22-00-410-001-A | Closing of the Emergency Exit Doors from the Passenger Compartment |
| TASK 52-30-00-860-001-A | Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump |
| TASK 52-30-00-860-002-A | Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump |
| TASK 52-30-00-860-006-A | Open the Bulk Cargo-Compartment Door |
| TASK 52-30-00-860-008-A | Close the Bulk Cargo-Compartment Door |
| TASK 52-41-00-010-002-A | Open the Avionics Compartment Doors for Access |
| TASK 52-41-00-410-002-A | Close the Avionics Compartment Doors after Access |
| TASK 53-59-00-210-001-A | Operational Check of Single Drain Pipe Aft of FR70 from Outside |
| TASK 54-50-00-200-002-A | Flow Check of Individual Drain Lines of Pylon System |
| TASK 54-50-00-200-803-A | Operational Check of Pylon Drainage System in Zone C |
| TASK 71-00-00-550-010-A | General Data for Storage of Installed Engines |
| TASK 71-00-00-550-011-A | Depreservation of Installed Engine |
| TASK 71-00-00-550-805-A | Preservation General Procedure |
| TASK 71-00-00-630-802-A | Depreservation of the Engine |
| TASK 71-00-00-700-014-B | Cold Weather Operation Procedure |
| TASK 72-00-00-600-026-A | Recommendations for Engine Preservation |
| TASK 72-00-00-600-027-A | Depreservation |
| TASK 72-00-00-600-028-A | Depreservation |
| TASK 72-00-00-600-029-A | Recommendations for Engine Preservation |
| 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 54-50-00-00 | PYLONS - DESCRIPTION AND OPERATION |
| TASK 54-50-00-00-13 | PYLONS - DESCRIPTION AND OPERATION |
| TASK 54-50-00-00-21 | PYLONS - DESCRIPTION AND OPERATION |
Subtask 10-12-00-941-059-A
A. General Information
(1) During the storage period, you must do specific ground checks.
The steps you must do for the periodic ground check procedure are given in a table. You must do each step identified with a cross in the column related to the applicable ground check interval(s).
(2) For the ground checks during the storage period of "Not more than 1 year" and storage period of "More than 1 year", refer to the columns that follow:
Subtask 10-12-00-660-050-A ** ON A/C NOT FOR ALL (1) During the storage period, you must do specific ground checks.
The steps you must do for the periodic ground check procedure are given in a table. You must do each step identified with a cross in the column related to the applicable ground check interval(s).
(2) For the ground checks during the storage period of "Not more than 1 year" and storage period of "More than 1 year", refer to the columns that follow:
- At 7-day intervals: column "s7d"
- At 15-day intervals: column "s15d"
- At 1-month intervals: column "s1m"
- At 3-month intervals: column "s3m"
- At 6-month intervals: column "s6m"
- At 1-year intervals: column "s1y"
- At 2-year intervals: column "s2y".
NOTE: You can do a periodic ground check earlier in the specified interval in relation to your operational conditions.
You can do the different ground checks at the same time.
(3) You must do the applicable steps in the sequence of the table. You can do the different ground checks at the same time.
B. Cold Weather Conditions
Subtask 10-12-00-660-050-B ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
| (1) If the aircraft parking is in cold weather conditions, do the cold-weather maintenance procedures. (a) It is not necessary to do all the steps given in the cold-weather maintenance procedures. Use your experience and your knowledge of the local weather conditions to do only the necessary steps for the inspections and/or tests:
| X | X | X | X | X | X | X |
B. Cold Weather Conditions
Subtask 10-12-00-660-050-D ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
| (1) If the aircraft parking is in cold weather conditions, do the cold-weather maintenance procedures. (a) It is not necessary to do all the steps given in the cold-weather maintenance procedures. Use your experience and your knowledge of the local weather conditions to do only the necessary steps for the inspections and/or tests:
| X | X | X | X | X | X | X |
B. Cold Weather Conditions
Subtask 10-12-00-941-060-A ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
| (1) If the aircraft parking is in cold weather conditions, do the cold-weather maintenance procedures. (a) It is not necessary to do all the steps given in the cold-weather maintenance procedures. Use your experience and your knowledge of the local weather conditions to do only the necessary steps for the inspections and/or tests:
| X | X | X | X | X | X | X |
C. Job Set-up
Subtask 10-12-00-941-060-B ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Get Access. | | | | | | | |
| (a) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position near the aircraft. | | X | X | X | | X | |
| (b) Put the ACCESS PLATFORM 15M (49 FT) - ADJUSTABLE in position near the aircraft. | | | | | X | | |
| (c) Remove the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) from forward avionics-compartment access-door 811 and the door handle. 1_If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) : | X | X | X | X | X | | |
| (d) Open forward avionics-compartment access-door 811 (Ref. AMM TASK 52-41-00-010-002). NOTE: This step is done to remove the remaining pressure in the cabin. | X | X | X | X | X | | |
| (2) Removal of Protection | | | | | | | |
(a) Remove the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) from:
| | | X | | | | |
| (b) Remove all the Film-- Waterproof Barrier - (Material No.14HMB1) and all the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) . Do not remove the external Protection from the Cabin and Cockpit Windows. 1_ If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) : | | | | X | | | |
| (c) Remove the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) from the landing gears. | | | | X | X | | |
| (3) Aircraft Maintenance Configuration | | | | | | | |
| (a) If the Emergency Power Supply Units (EPSU) disconnection method was chosen at the entry into storage, connect the EPSUs (Ref. AMM TASK 33-51-38-400-001). NOTE: For EPSUs connection, only the steps related to the connection of EPSUs in the EPSU installation task are necessary. NOTE: EPSUs batteries charge when aircraft is energized. | | | X | X | X | | |
| (b) Install and connect batteries 2PB1 and 2PB2 (Ref. AMM TASK 24-38-51-400-001). | | | X | X | X | | |
| (c) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002). | | | X | X | X | | |
| (d) In the cockpit, on the overhead panel: 1_ On the CABIN PRESS section of panel 25VU:
| | | X | X | X | | |
| (e) If the EPSUs disconnection method was chosen at the entry into storage, let the aircraft energized for 3 hours. NOTE: Every 3 months, EPSUs must be energized for 3 hours to ensure a correct charge level. NOTE: The 3 hours of connection of includes the duration of the Non-Revenue Flight. | | | | X | | | |
| (f) Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001), (Ref. AMM TASK 29-24-00-863-001) and (Ref. AMM TASK 29-10-00-863-003). | | | | X | | | |
| (g) If the aircraft is moored, remove the mooring tool. | | | | X | X | | |
| (4) Fully extend the flaps (Ref. AMM TASK 27-50-00-866-008). | | | | X | | | |
| (5) Fully extend the slats (Ref. AMM TASK 27-80-00-866-004). | | | | X | | | |
| (6) Aircraft Cleaning | | | | | | | |
| If necessary, clean the aircraft externally (Ref. AMM TASK 12-21-11-615-002). | | | | X | | | |
| (7) Safety Precautions | | | | | | | |
| On panel 114VU, on the flap and slat control lever, install the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION in position. | | | | X | | | |
C. Job Set-up
Subtask 10-12-00-865-054-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Get Access | | | | | | | |
| (a) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position near the aircraft. | | X | X | X | | X | |
| (b) Put the ACCESS PLATFORM 15M (49 FT) - ADJUSTABLE in position near the aircraft. | | | | | X | | |
| (c) Remove the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) from forward avionics-compartment access-door 811 (Ref. AMM TASK 52-41-00-010-002) and the door handle. 1_If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) : | X | X | X | X | X | | |
| (d) Open forward avionics-compartment access-door 811 (Ref. AMM TASK 52-41-00-010-002). NOTE: This step is done to remove the remaining pressure in the cabin. | X | X | X | X | X | | |
| (2) Removal of Protection | | | | | | | |
(a) Remove the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) from:
| | | X | | | | |
| (b) Remove all the Film-- Waterproof Barrier - (Material No.14HMB1) and all the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) . Do not remove the external Protection from the Cabin and Cockpit Windows. 1_ If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) : | | | | X | | | |
| (c) Remove the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) from the landing gears. | | | | X | X | | |
| (3) Aircraft Maintenance Configuration | | | | | | | |
| (a) If the Emergency Power Supply Units (EPSU) disconnection method was chosen at the entry into storage, connect the EPSUs (Ref. AMM TASK 33-51-38-400-001). NOTE: For EPSUs connection, only the steps related to the connection of EPSUs in the EPSU installation task are necessary. NOTE: EPSUs batteries charge when aircraft is energized. | | | X | X | X | | |
| (b) Install and connect batteries 2PB1 and 2PB2 (Ref. AMM TASK 24-38-51-400-001). | | X | X | X | X | | |
| (c) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002). | | X | X | X | X | | |
| (d) In the cockpit, on the overhead panel: 1_ On the CABIN PRESS section of panel 25VU:
| | | X | X | X | | |
| (e) If the EPSUs disconnection method was chosen at the entry into storage, let the aircraft energized for 3 hours. NOTE: Every 3 months, EPSUs must be energized for 3 hours to ensure a correct charge level. NOTE: The 3 hours of connection of includes the duration of the Non-Revenue Flight. | | | | X | | | |
| (f) Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-863-001), (Ref. AMM TASK 29-24-00-863-001) and (Ref. AMM TASK 29-10-00-863-003). | | | | X | | | |
| (g) If the aircraft is moored, remove the mooring tool. | | | | X | X | | |
| (4) Fully extend the flaps (Ref. AMM TASK 27-50-00-866-008). | | | | X | | | |
| (5) Fully extend the slats (Ref. AMM TASK 27-80-00-866-004). | | | | X | | | |
| (6) Aircraft Cleaning | | | | | | | |
| If necessary, clean the aircraft externally (Ref. AMM TASK 12-21-11-615-002). | | | | X | | | |
| (7) Safety Precautions | | | | | | | |
| On panel 114VU, on the flap and slat control lever, install the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION in position. | | | | X | | | |
D. Make sure that this(these) circuit breaker(s) is(are) closed:
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B07 |
| 49VU | FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 | 5CV | B06 |
| ** ON A/C ALL | |||
| 49VU | HYD/HYD PWR/B WARN/& CTL | 2702GJ | C12 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B02 |
| 49VU | FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 | 5CV | B01 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | HYDRAULIC/HYD POWER/Y | 3803GX | N30 |
| ** ON A/C ALL | |||
| 121VU | FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 | 8CV | Q21 |
| 121VU | FLIGHT CONTROLS/SLT/CTL/SYS2 | 7CV | R21 |
| ** ON A/C NOT FOR ALL | |||
| 121VU | HYDRAULIC/HYD POWER/Y | 3803GX | N31 |
| ** ON A/C ALL | |||
| 123VU | B HYD/ELEC PUMP | 2701GJ | AB09 |
| 123VU | Y HYD/ELEC/PUMP | 3802GX | AB06 |
| 123VU | Y HYD/ELEC/ELEC PUMP/NORM | 3801GX | AB03 |
Subtask 10-12-00-210-092-A
A. Inspection
Subtask 10-12-00-210-096-A ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a General Visual Inspection (GVI) of the airframe from the ground to make sure that it is in the correct condition. (a) Make sure that the protective equipment is correctly installed. (b) If a protective cover is missing on the pitot probes, static probes, Total Air Temperature (TAT) sensors or Angle Of Attack (AOA) sensors:
NOTE: A flushing of the Air Data System (ADS) will be necessary during the return to operation after a storage period. (c) Make sure that there are no fluid leakages (hydraulic fluid, fuel or oil) from:
(e) Do a check for bird excrement. If there is bird excrement, remove it. (f) Do a check of the outer skin for unusual contamination. | X | | | | | | |
| (2) Do a visual inspection of the aircraft for Foreign Object Damage (FOD). Also examine for nests, fluid leakage (hydraulic fluid, fuel or oil), missing parts, blockage and corrosion of: (a) The upper and lower surfaces of the wings (b) The upper surfaces of the ailerons and the spoilers (c) The lower surfaces of the ailerons (d) The nacelles, the leading edges of the nacelles and the pylons (e) The flight control surfaces (f) The external surfaces of the fuselage (g) The leading edges of the horizontal and vertical stabilizers (h) The trailing edges of the horizontal and vertical stabilizers (i) The external skin of:
(k) The toilet areas (l) All the steel parts and the bare light-alloy areas. | | | | X | | | |
(3) Do a visual inspection of the trailing edge for impacts by FOD, fluid leakage (hydraulic fluid, fuel or oil), missing parts, blockage and corrosion of:
| | | | X | | | |
| (4) If you find corrosion, remove it (Ref. AMM TASK 51-74-11-300-001). | | | | X | | | |
B. Inspection of the Doors
Subtask 10-12-00-210-096-B ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
(1) Passenger/crew doors:
| | | | X | | | |
(2) Forward and aft cargo-compartment doors:
| | | | X | | | |
(3) Emergency exit hatch:
| | | | X | | | |
B. Inspection of the Doors
Subtask 10-12-00-210-096-C ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
(1) Passenger/crew doors:
| | | | X | | | |
(2) Forward and aft cargo-compartment doors:
| | | | X | | | |
(3) Emergency exit hatch:
| | | | X | | | |
(4) Bulk cargo-compartment door:
| | | | X | | | |
B. Inspection of the Doors
Subtask 10-12-00-680-057-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
(1) Passenger/crew doors:
| | | | X | | | |
(2) Forward and aft cargo-compartment doors:
| | | | X | | | |
(3) Emergency exit doors:
| | | | X | | | |
(4) Bulk cargo-compartment door:
| | | | X | | | |
C. Air data
Subtask 10-12-00-710-077-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Remove the water from the standby static line (Ref. AMM TASK 12-24-34-600-001). | | X | | | | | |
D. Landing Gears
Subtask 10-12-00-620-115-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a check of the tire and wheel conditions (Ref. AMM TASK 32-41-00-210-002). | | X | | | | | |
| (2) Do a check of the tire pressure (Ref. AMM TASK 32-41-00-210-003). If necessary, inflate the tires. | | X | | | | | |
(3) Make sure that the extension of the landing-gear shock absorbers is correct:
| | | X | | | | |
| (4) Do a GVI of: - The NLG and its doors (Ref. AMM TASK 05-27-10-200-001), - The MLG and its doors (Ref. AMM TASK 05-27-30-200-001) (Ref. AMM TASK 05-27-30-200-002) (Ref. AMM TASK 05-27-30-200-003) (Ref. AMM TASK 05-27-30-200-004). | | | | X | | | |
| (5) During the GVI, do a check for hydraulic leaks. You must make sure that there are no hydraulic leaks (because of a dry seal) on the landing gears and the landing-gear door actuators before you pressurize the hydraulic systems for the test. | | | | | X | | |
| (6) Remove the mooring tool from the NLG. | | | | X | | | |
| (7) Lift and turn the wheels by hand to make sure that there are no defects on the bearings: - For the NLG (Ref. AMM TASK 07-12-00-582-001) - For the MLG (Ref. AMM TASK 07-12-00-582-002). | | | | X | | | |
| (8) Put the aircraft on its wheels. | | | | X | | | |
| (9) Put the aircraft in mooring condition (Ref. AMM TASK 10-20-00-556-001). | | | | X | | | |
| (10) Do a check of each wheel-half for corrosion. If you find corrosion, clean with Non Aqueous Cleaner-- Petroleum Based - (Material No.08BBB1) . | | | | X | | | |
| (11) Do a check of all the painted and unpainted parts for corrosion. | | | | X | | | |
| (12) Lubricate all the landing gears and the landing gear doors: - The NLG and the NLG doors (Ref. AMM TASK 12-22-32-640-002). - The MLG and the MLG doors (Ref. AMM TASK 12-22-32-640-001). | | | | | X | | |
| (13) Clean all the actuator rods and apply a thin layer of Phosphate Ester Hydraulic Fluid-General Power - - (Material No.02ABA1) on them. | | | | | X | | |
| (14) Do a functional test of the normal extension and retraction of the landing gear (Ref. AMM TASK 32-31-00-720-002). | | | | | X | | |
| (15) Apply Silicone base Grease-Mechanisms and Seals - - (Material No.03JCA9) on: - The sliding tube of the shock absorbers - The actuator rods - The uplock rollers. | | | | X | X | | |
E. Protection of the Landing Gears
Subtask 10-12-00-614-052-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
(1) Do a check of the condition of the corrosion preventive compound on the landing gears equipment.
| | | | | X | | |
F. Oxygen
Subtask 10-12-00-710-078-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Crew oxygen system: (a) Do a check of the pressure of the crew oxygen cylinders (Ref. AMM TASK 35-10-00-040-001). (b) Make sure that all crew oxygen cylinder-valves are closed. | | | X | | | | |
| (2) Passenger gaseous oxygen system (if installed): (a) Do a check of the pressure of the passenger oxygen cylinders (Ref. AMM D/O 35-21-00-04). (b) If necessary, fill the passenger oxygen cylinders (Ref. AMM D/O 35-21-00-61). (c) Make sure that all passenger oxygen cylinder-valves are closed. | | | X | | | | |
| (3) Portable oxygen system (if installed): (a) Do a check of the pressure of the portable oxygen cylinders (Ref. AMM TASK 35-32-42-210-002) and (Ref. AMM D/O 35-31-42-22). (b) Make sure that all portable oxygen cylinder-valves are closed. | | | X | | | | |
G. Operational Tests
Subtask 10-12-00-710-079-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a test of the avionics equipment ventilation-system (Ref. AMM TASK 21-26-00-710-001). | | | X | | | | |
| (2) If the aft cargo-compartment ventilation-system is installed, do a test of the aft cargo-compartment ventilation-system (Ref. AMM TASK 21-28-00-710-006). | | | X | | | | |
| (3) If the forward cargo-compartment ventilation-system is installed, do a test of the forward cargo-compartment ventilation-system (Ref. AMM TASK 21-28-00-720-003). | | | X | | | | |
| (4) Do a test of ENG 1(2) LP-fuel-valve 12QM (13QM) (Ref. AMM TASK 28-24-00-710-002). | | | X | | | | |
H. Operational Tests
Subtask 10-12-00-710-080-A ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do an operational test of the crossfeed valves (Ref. AMM TASK 28-23-00-720-001). | | | | X | | | |
| (2) Do an operational test of the engine LP-fuel shut-off valve (Ref. AMM TASK 28-24-00-710-002). | | | | X | | | |
| (3) Do an operational test of the APU shut-off valve (Ref. AMM TASK 28-29-00-710-001). | | | | X | | | |
| (4) Do an operational test of the aileron and its hydraulic system (Ref. AMM TASK 27-14-00-710-001). | | | | X | | | |
| (5) Do an operational test of the elevator and its hydraulic system (Ref. AMM TASK 27-34-00-710-001). | | | | X | | | |
| (6) Do an operational test of the rudder hydraulic actuation (Ref. AMM TASK 27-24-00-710-001). | | | | X | | | |
| (7) Do an operational test of the Trimmable Horizontal Stabilizer (THS) actuator with the individual hydraulic systems (Ref. AMM TASK 27-44-00-710-002). Move the THS pitch-trim control-wheel back to the 2 UP position. | | | | X | | | |
| (8) Do an operational test of the flap system (Ref. AMM TASK 27-54-00-710-001). | | | | X | | | |
| (9) Do an operational test of the spoiler hydraulic system (Ref. AMM TASK 27-64-00-710-001). | | | | X | | | |
| (10) Do an operational test of the slat system (Ref. AMM TASK 27-84-00-710-001). | | | | X | | | |
| (11) Do an operational test of the landing gear doors (Ref. AMM TASK 32-31-00-710-002). | | | | X | | | |
I. Operational Check of the Drainage Systems
Subtask 10-12-00-710-080-B ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a check of the drains: (a) In the lower fuselage (Ref. AMM TASK 53-59-00-210-001). (b) On the pylons (Ref. AMM TASK 54-50-00-200-002). (c) On the engines. (d) In all other locations. Make sure that all the drain holes of the external structure are not clogged. | | | | X | | | |
I. Operational Check of the Drainage Systems
Subtask 10-12-00-210-093-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a check of the drains: (a) In the lower fuselage (Ref. AMM TASK 53-59-00-210-001). (b) On the pylons (Ref. AMM TASK 54-50-00-200-803). (c) On the engines. (d) In all other locations. Make sure that all the drain holes of the external structure are not clogged. | | | | X | | | |
J. Inspection of the Hydraulic System
Subtask 10-12-00-281-057-A ** ON A/C NOT FOR ALL | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
(1) Do a check of the hydraulic-reservoir fluid level:
| | | | X | | | |
| (2) Do a GVI of the hydraulic pipes and unions for corrosion in the areas which are open to the environment (landing gear wells, wings and stabilizers). Where applicable, move the flaps/slats/rudders to get access. NOTE: This inspection is not applicable to the parts that have the protection of the structure and to which you can only get access through panels and/or doors. | | | | X | | | |
| (3) If you find corrosion on the hydraulic pipes and unions, replace them. | | | | X | | | |
| (4) Read the maintenance record to find when the last hydraulic fluid sampling occurred (Ref. AMM TASK 12-32-29-281-001). If the last hydraulic fluid sampling occurred more than 24 months, do an analysis of the hydraulic fluid (Ref. AMM TASK 12-32-29-281-001). | | | | | X | | |
K. Protection of the Fuel System from Microbiological Contamination
(2) Protection of the fuel system without fuel treated with biocide
Subtask 10-12-00-281-057-B ** ON A/C NOT FOR ALL NOTE: Because microbiological contamination can expand in one tank or expand from tank to tank during routine fuel transfers, tests and protective treatments are necessary for all the fuel tanks.
(1) Protection of the fuel system with fuel treated with biocide | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a fuel sampling for microbiological contamination analysis at each water drain valve (Ref. AMM TASK 12-32-28-281-003). Do the fuel sampling procedure a minimum of one hour after the end of the refueling procedure. | | | X | | | | |
| (2) Do a check of the fuel quantity in each tank (wing tanks, center tank and Additional Center Tank (ACT) (if installed)). CAUTION:
IF A BIOCIDE WAS USED DURING THE LAST 30 REFUELING PROCEDURES, YOU MUST USE THE SAME BIOCIDE FOR THE PREVENTIVE TREATMENT. DO NOT MIX KATHON AND BIOBOR BIOCIDES. IF YOU MIX THEM, FORMATION OF PRECIPITATES WILL OCCUR AND CAN CAUSE INCORRECT OPERATION OF THE ENGINES. (a) If the fuel level in each wing tank and in the center tank is less than 10% of the capacity of the tank, refuel the tanks with fuel mixed with a biocide to a minimum of 10% of their capacities:
NOTE: It is not necessary to defuel the aircraft. (b) If the fuel level in the ACT (if installed) is less than 100% of the capacity of the tanks, refuel the tanks with fuel mixed with a biocide to 100% of their capacities:
NOTE: It is not necessary to defuel the aircraft. | | | | X | | | |
(3) Drain water at each water drain valve:
| | X | | | | | |
| (4) If you did the refueling procedure, get access to the ECAM page to make sure that all the fuel system valves are closed. | | X | | X | | | |
| Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a fuel sampling for microbiological contamination analysis at each water drain valve (Ref. AMM TASK 12-32-28-281-003). Do the fuel sampling procedure a minimum of one hour after the end of the refueling procedure. | | | X | | | | |
| (2) Do a check of the fuel quantity in each tank (wing tanks, center tank and ACT (if installed)). If the fuel level in each wing tank and in the center tank is less than 10% of the capacity of the tank, refuel the tanks to a minimum of 10% of their capacities. If the fuel level in the ACT (if installed) is less than 100% of the capacity of the tanks, refuel the tanks to 100% of their capacities (Ref. AMM TASK 12-11-28-650-003) or (Ref. AMM TASK 12-11-28-650-004). | | | | X | | | |
(3) Drain water at each water drain valve:
| X | | | | | | |
| (4) If you did the refueling procedure, get access to the ECAM page to make sure that all the fuel system valves are closed. | X | | | X | | | |
K. Protection of the Fuel System from Microbiological Contamination
(2) Protection of the fuel system without fuel treated with biocide
Subtask 10-12-00-640-053-A NOTE: Because microbiological contamination can expand in one tank or expand from tank to tank during routine fuel transfers, tests and protective treatments are necessary for all the fuel tanks.
(1) Protection of the fuel system with fuel treated with biocide | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a fuel sampling for microbiological contamination analysis at each water drain valve (Ref. AMM TASK 12-32-28-281-003). Do the fuel sampling procedure a minimum of one hour after the end of the refueling procedure. | | | X | | | | |
| (2) Do a check of the fuel quantity in each tank (wing tanks, center tank and Additional Center Tank (ACT) (if installed)). CAUTION:
IF A BIOCIDE WAS USED DURING THE LAST 30 REFUELING PROCEDURES, YOU MUST USE THE SAME BIOCIDE FOR THE PREVENTIVE TREATMENT. DO NOT MIX KATHON AND BIOBOR BIOCIDES. IF YOU MIX THEM, FORMATION OF PRECIPITATES WILL OCCUR AND CAN CAUSE INCORRECT OPERATION OF THE ENGINES. (a) If the fuel level in each wing tank and in the center tank is less than 10% of the capacity of the tank, refuel the tanks with fuel mixed with a biocide to a minimum of 10% of their capacities:
NOTE: It is not necessary to defuel the aircraft. (b) If the fuel level in the ACT (if installed) is less than 100% of the capacity of the tanks, refuel the tanks with fuel mixed with a biocide to 100% of their capacities:
NOTE: It is not necessary to defuel the aircraft. | | | | X | | | |
(3) Drain water at each water drain valve:
| | X | | | | | |
| (4) If you did the refueling procedure, get access to the ECAM page to make sure that all the fuel system valves are closed. | | X | | X | | | |
| Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a fuel sampling for microbiological contamination analysis at each water drain valve (Ref. AMM TASK 12-32-28-281-003). Do the fuel sampling procedure a minimum of one hour after the end of the refueling procedure. | | | X | | | | |
| (2) Do a check of the fuel quantity in each tank (wing tanks, center tank and ACT (if installed)). If the fuel level in each wing tank and in the center tank is less than 10% of the capacity of the tank, refuel the tanks to a minimum of 10% of their capacities. If the fuel level in the ACT (if installed) is less than 100% of the capacity of the tanks, refuel the tanks to 100% of their capacities (Ref. AMM TASK 12-11-28-650-003) or (Ref. AMM TASK 12-11-28-650-004). | | | | X | | | |
(3) Drain water at each water drain valve:
| X | | | | | | |
| (4) If you did the refueling procedure, get access to the ECAM page to make sure that all the fuel system valves are closed. | X | | | X | | | |
L. Flight Controls
Subtask 10-12-00-710-081-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do a check of all the flap tracks for corrosion. | | | | X | | | |
| (2) Do a check of all the slat tracks for corrosion. | | | | X | | | |
| (3) Do a check of the condition of the flight control cables: (a) Make sure that the rudder and THS cables are lubricated and have no corrosion in these areas (Ref. AMM TASK 20-24-12-200-001) and (Ref. AMM TASK 20-24-12-200-003):
NOTE: It is necessary to move the cable on the pulley. There can be some corrosion that you cannot see because of the pulley guard or pulley guide. 1_ If there is corrosion on the cables or no protection with Corrosion Preventive Compound-- Soft Film System (Material No.12AGC2) or Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) :
| | | | | X | | |
| (4) Lubricate the mechanical control chains of the THS (Ref. AMM TASK 12-22-27-640-007) or (Ref. AMM TASK 12-22-27-640-805) and the actuator ball screw-nut (Ref. AMM TASK 12-22-27-640-003). | | | | | X | | |
| (5) Lubricate the rollers of the flap tracks (Ref. AMM TASK 12-22-27-640-004). | | | | | X | | |
| (6) Lubricate all the rollers and pinions of the slat tracks (Ref. AMM TASK 12-22-27-640-006). | | | | | X | | |
| (7) Lubricate the spoiler servo-control bearings (Ref. AMM TASK 12-22-27-640-005). | | | | | X | | |
| (8) Lubricate the hinges and the attach fittings of the horizontal stabilizer (Ref. AMM TASK 12-22-53-640-001) or (Ref. AMM TASK 12-22-53-640-002). | | | | | X | | |
| (9) If the rod-end assembly is installed with the lubrication fittings, lubricate the elevator servo-control-rod eye-end-bearing (Ref. AMM TASK 12-22-27-640-803). | | | | | X | | |
| (10) Lubricate rudder bearing No. 6 (Ref. AMM TASK 12-22-55-640-001) or (Ref. AMM TASK 12-22-55-640-002). | | | | | X | | |
| (11) If the rod-end assembly is installed with the lubrication fittings, lubricate the rudder servo-control-rod eye-end-bearing (Ref. AMM TASK 12-22-27-640-804). | | | | | X | | |
M. Ventilation of the Cabin, Cockpit and Lavatory Areas
You can adapt this procedure to:
Subtask 10-12-00-620-107-A ** ON A/C NOT FOR ALL NOTE: This subtask helps to decrease the humidity in the cabin, cockpit and lavatory areas.
It is not necessary to do this subtask when there is no humidity problem during the storage period.You can adapt this procedure to:
- The weather and climate conditions (for example, wind speed and direction, precipitation)
- The available equipment.
- The frequency of this procedure,
- And its duration.
| Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Method 1 (with the passenger/crew doors): | | | X | | | | |
| (a) Open the cockpit door and the lavatory doors. | | | X | | | | |
| (b) From a passenger/crew door in the forward cabin area and other door on the opposite side in the aft cabin area: 1_ Remove the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) . a_ If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) : | | | X | | | | |
| (c) Open the applicable passenger/crew doors in the forward cabin area and on the opposite side in the aft cabin area to get a good airflow (Ref. AMM TASK 52-10-00-010-001). | | | X | | | | |
| (d) After the ventilation of the cabin, cockpit and lavatories, close the applicable passenger/crew doors (Ref. AMM TASK 52-10-00-410-001). | | | X | | | | |
| (e) Close the cockpit door and the lavatory doors. | | | X | | | | |
| (2) Method 2 (with the Air Conditioning System (ACS)): | | | X | | | | |
| (a) If you operate the ACS with the APU: NOTE: It can be necessary to do the APU de-preservation/preservation and to remove/install the covers during the engine and APU protections given in the subtask "Engine and APU Protections". Airbus recommends to get all the necessary information to optimize the maintenance periodic interval. 1_ Remove the protection cover from the APU (Ref. AMM TASK 10-11-00-555-014).2_ Make sure that there is no Foreign Object Damage (FOD) in the APU open areas. 3_ Do the APU de-preservation: Refer to the applicable recommendations of the APU manufacturer (in relation to the APU preservation procedure that you selected):
5_ Operate the ACS with the APU to remove the moisture (Ref. AMM TASK 12-33-21-618-001). 6_ Do the APU preservation: Refer to the applicable recommendations of the APU manufacturer (in relation to the APU preservation procedure that you selected):
| | | X | | | | |
| (b) If you operate the ACS with the HP ground connection: 1_ Open the cockpit door and the lavatory doors. 2_ Operate the ACS with the HP ground connection (Ref. AMM TASK 12-33-21-618-001). | | | X | | | | |
| (c) Close the cockpit door and the lavatory doors. | | | X | | | | |
N. Engine and APU Protections
Subtask 10-12-00-620-107-C ** ON A/C NOT FOR ALL NOTE: ATA 10 gives instructions related to the parking, storage, periodic checks and return to operation of the aircraft. These instructions do not include the engine and the APU.
For the parking, storage, periodic checks and return to operation of the engines and the APU, ATA 10 refers to the applicable procedures in the related ATA chapters (7X and 49).
For the parking, storage, periodic checks and return to operation of the engines and the APU, ATA 10 refers to the applicable procedures in the related ATA chapters (7X and 49).
| Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Engine protection: (a) Refer to the engine-manufacturer preservation procedure (Ref. AMM TASK 71-00-00-550-805), to know:
| X | X | X | | | | |
(c) If the engine start is necessary:
NOTE: For the location of the pylons drains (Ref. AMM D/O 54-50-00-00). 1_ If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) : | X | X | X | | | | |
| (2) APU protection: (a) Refer to the APU manufacturer preservation-procedure to know:
- For a 131-9(A) APU (Ref. AMM TASK 49-20-00-600-803). | X | X | X | | | | |
(c) If the APU start is necessary:
| X | X | X | | | | |
| (3) Thrust reverser: (a) Remove the thrust reverser protection (if not already removed) (Ref. AMM TASK 10-11-00-555-014). (b) Do a full thrust-reverser cycle (Ref. AMM TASK 78-31-00-710-805). | | X | | | | | |
| (4) Installation of the protection equipment: (a) If you started the engine and/or APU: WARNING:
MAKE SURE THAT THE PROBES, THE ENGINE AND THE APU ARE COOL BEFORE INSTALLATION OF THE PROTECTIVE DEVICES. IF THE PROBES ARE HOT, THERE IS A RISK OF INJURY AND THE PROTECTIVE DEVICES CAN MELT.
NOTE: The operational test of the pylons drains at the return to operation will not be necessary if the parking period is less than 15 days and if you sealed these drains. NOTE: The installation of the fine nylon netting and the adhesive-film tape on the pylons drains and the engine drain masts is not mandatory but it decreases the risk of clogging during the operational test of the pylons drains at the return to operation. | X | X | X | | | | |
N. Engine and APU Protections
Subtask 10-12-00-620-107-E ** ON A/C NOT FOR ALL NOTE: ATA 10 gives instructions related to the parking, storage, periodic checks and return to operation of the aircraft. These instructions do not include the engine and the APU.
For the parking, storage, periodic checks and return to operation of the engines and the APU, ATA 10 refers to the applicable procedures in the related ATA chapters (7X and 49).
For the parking, storage, periodic checks and return to operation of the engines and the APU, ATA 10 refers to the applicable procedures in the related ATA chapters (7X and 49).
| Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Engine protection: (a) Refer to the engine-manufacturer preservation procedure (Ref. AMM TASK 72-00-00-600-029), to know:
| X | X | X | | | | |
(c) If the engine start is necessary:
NOTE: For the location of the pylons drains (Ref. AMM D/O 54-50-00-00). 1_ If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) : | X | X | X | | | | |
| (2) APU protection: (a) Refer to the APU manufacturer preservation-procedure to know:
- For an APS 3200 APU (Ref. AMM D/O 49-20-00-60) - For a 131-9(A) APU (Ref. AMM TASK 49-20-00-600-803). | X | X | X | | | | |
(c) If the APU start is necessary:
| X | X | X | | | | |
| (3) Installation of the protection equipment: (a) If you started the engine and/or APU: WARNING:
MAKE SURE THAT THE PROBES, THE ENGINE AND THE APU ARE COOL BEFORE INSTALLATION OF THE PROTECTIVE DEVICES. IF THE PROBES ARE HOT, THERE IS A RISK OF INJURY AND THE PROTECTIVE DEVICES CAN MELT.
NOTE: The operational test of the pylons drains at the return to operation will not be necessary if the parking period is less than 15 days and if you sealed these drains. NOTE: The installation of the fine nylon netting and the adhesive-film tape on the pylons drains and the engine drain masts is not mandatory but it decreases the risk of clogging during the operational test of the pylons drains at the return to operation. | X | X | X | | | | |
N. Engine and APU Protections
Subtask 10-12-00-620-107-F ** ON A/C NOT FOR ALL NOTE: ATA 10 gives instructions related to the parking, storage, periodic checks and return to operation of the aircraft. These instructions do not include the engine and the APU.
For the parking, storage, periodic checks and return to operation of the engines and the APU, ATA 10 refers to the applicable procedures in the related ATA chapters (7X and 49).
For the parking, storage, periodic checks and return to operation of the engines and the APU, ATA 10 refers to the applicable procedures in the related ATA chapters (7X and 49).
| Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Engine protection: (a) Refer to the engine-manufacturer preservation procedure (Ref. AMM TASK 72-00-00-600-026), to know:
| X | X | X | | | | |
(c) If the engine start is necessary:
NOTE: For the location of the pylons drains (Ref. AMM D/O 54-50-00-00). 1_ If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) : | X | X | X | | | | |
| (2) APU protection: (a) Refer to the APU manufacturer preservation-procedure to know:
- For an APS 3200 APU (Ref. AMM TASK 49-20-00-600-002) - For a 131-9(A) APU (Ref. AMM TASK 49-20-00-600-803). | X | X | X | | | | |
(c) If the APU start is necessary:
| X | X | X | | | | |
| (3) Installation of the protection equipment: (a) If you started the engine and/or APU: WARNING:
MAKE SURE THAT THE PROBES, THE ENGINE AND THE APU ARE COOL BEFORE INSTALLATION OF THE PROTECTIVE DEVICES. IF THE PROBES ARE HOT, THERE IS A RISK OF INJURY AND THE PROTECTIVE DEVICES CAN MELT.
NOTE: The operational test of the pylons drains at the return to operation will not be necessary if the parking period is less than 15 days and if you sealed these drains. NOTE: The installation of the fine nylon netting and the adhesive-film tape on the pylons drains and the engine drain masts is not mandatory but it decreases the risk of clogging during the operational test of the pylons drains at the return to operation. | X | X | X | | | | |
N. Engine and APU Protections
Subtask 10-12-00-554-051-A NOTE: ATA 10 gives instructions related to the parking, storage, periodic checks and return to operation of the aircraft. These instructions do not include the engine and the APU.
For the parking, storage, periodic checks and return to operation of the engines and the APU, ATA 10 refers to the applicable procedures in the related ATA chapters (7X and 49).
For the parking, storage, periodic checks and return to operation of the engines and the APU, ATA 10 refers to the applicable procedures in the related ATA chapters (7X and 49).
| Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Engine protection: (a) Refer to the engine-manufacturer preservation procedure (Ref. AMM TASK 71-00-00-550-010), to know:
| X | X | X | | | | |
(c) If the engine start is necessary:
NOTE: For the location of the pylons drains (Ref. AMM D/O 54-50-00-00). 1_ If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) : | X | X | X | | | | |
| (2) APU protection: (a) Refer to the APU manufacturer preservation-procedure to know:
- For an APS 3200 APU (Ref. AMM D/O 49-20-00-60) - For a 131-9(A) APU (Ref. AMM TASK 49-20-00-600-803). | X | X | X | | | | |
(c) If the APU start is necessary:
| X | X | X | | | | |
| (3) Installation of the protection equipment: (a) If you started the engine and/or APU: WARNING:
MAKE SURE THAT THE PROBES, THE ENGINE AND THE APU ARE COOL BEFORE INSTALLATION OF THE PROTECTIVE DEVICES. IF THE PROBES ARE HOT, THERE IS A RISK OF INJURY AND THE PROTECTIVE DEVICES CAN MELT.
NOTE: The operational test of the pylons drains at the return to operation will not be necessary if the parking period is less than 15 days and if you sealed these drains. NOTE: The installation of the fine nylon netting and the adhesive-film tape on the pylons drains and the engine drain masts is not mandatory but it decreases the risk of clogging during the operational test of the pylons drains at the return to operation. | X | X | X | | | | |
O. Non-revenue Flight
Subtask 10-12-00-553-075-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Do the full return to operation after storage. | | | | | | | X |
| (2) Refer to the aircraft maintenance program and make sure that you do all the scheduled maintenance tasks that are due. | | | | | | | X |
| (3) Do a short non-revenue flight within the aircraft standard envelope. | | | | | | | X |
| (4) Do the storage procedure (Ref. AMM TASK 10-10-00-550-801). | | | | | | | X |
P. Movement of the Aircraft
Subtask 10-12-00-620-114-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Remove the protection from the brakes and the wheels. | | X | | | | | |
| (2) Remove the CHOCK - WHEEL(S) that you installed during the storage procedure. | | X | | | | | |
| (3) Turn the wheels by 1/4 turn to prevent damage to the tires: (a) Move the aircraft (Ref. AMM TASK 09-10-00-584-002) or (b) Refer to the jacking for wheel change procedures to turn each wheel separately: - The NLG (Ref. AMM TASK 07-12-00-582-001) - The MLG (Ref. AMM TASK 07-12-00-582-002). | | X | | | | | |
| (4) Put protection on the brakes and the wheels with Film-- Waterproof Barrier - (Material No.14HMB1) . | | X | | | | | |
| (5) If necessary, ground the aircraft (Ref. AMM TASK 12-34-24-869-002). | | X | | | | | |
| (6) Put the CHOCK - WHEEL(S) in position (Ref. AMM TASK 10-11-00-555-015). Make sure that the CHOCK - WHEEL(S) do not touch the tires. If a tire deflates, the CHOCK - WHEEL(S)will lock. | | X | | | | | |
| (7) If necessary, moor the aircraft (Ref. AMM TASK 10-20-00-556-001). | | X | | | | | |
Q. Protection of the Windows
Subtask 10-12-00-860-068-A | Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Open the cockpit and cabin window shades. Make sure that the sliding windows are closed. | | | | X | | | |
| (2) Make sure that the external protection of the cockpit windows are in the correct condition: (a) If the external protection or the adhesive tape is damaged or unsticked, replace it with the new Film-- Waterproof Barrier - (Material No.14HMB1) and the new Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) . 1_ If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) :
| | | | X | | | |
| (3) If the storage period is more than 1 year, make sure that the external protection of the cabin windows are in the correct condition: (a) If the external protection or the adhesive tape is damaged or unsticked, replace it with the new Film-- Waterproof Barrier - (Material No.14HMB1) and the new Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or new Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) . 1_ If you used Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) :
| | | | X | | | |
WARNING:
BEFORE YOU PUSH THE DITCHING PUSHBUTTON SWITCH, MAKE SURE THAT THERE IS NO SUPPLY OF AIR TO THE AIRCRAFT THROUGH THE LOW PRESSURE CONNECTION. IF THERE IS A SUPPLY OF AIR, YOU CAN CAUSE UNWANTED PRESSURIZATION OF THE AIRCRAFT. THIS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT.
R. Put the Aircraft Back to its Initial Configuration| Step | s 7 d | s 15 d | s 1 m | s 3 m | s 6 m | s 1 y | s 2 y |
|---|---|---|---|---|---|---|---|
| (1) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever. | | | | X | | | |
| (2) Retract the flaps (Ref. AMM TASK 27-50-00-866-009). | | | | X | | | |
| (3) Retract the slats (Ref. AMM TASK 27-80-00-866-005). | | | | X | | | |
| (4) In the cockpit, on the overhead panel: (a) On the CABIN PRESS section of panel 25VU:
| | | X | X | X | | |
| (5) If the aircraft was energized for other maintenance operation and the maintenance operation is completed, do the steps that follow: (a) On the overhead panel, on the CABIN PRESS section of panel 25VU:
| X | X | | | | X | X |
| (6) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-23-00-864-001), (Ref. AMM TASK 29-24-00-864-001), (Ref. AMM TASK 29-10-00-864-003). | | | | X | | | |
| (7) Install the Film-- Waterproof Barrier - (Material No.14HMB1) with the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) to seal the Left and Right Ailerons. | | | | X | | | |
| (8) Put protection at the bottom of the landing gears with the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) . | | | | X | X | | |
| (9) If necessary, moor the aircraft (Ref. AMM TASK 10-20-00-556-001). | | | | | X | | |
| (10) Remove all the batteries of: - The megaphones (if installed) (Ref. AMM TASK 25-65-51-920-001) - The flashlights. | | | | | X | | |
| (11) De-energize the aircraft electrical circuits supplied from the external power (Ref. AMM TASK 24-41-00-862-002). | | | X | X | X | | |
| (12) Disconnect and remove batteries 2PB1 and 2PB2 (Ref. AMM TASK 24-38-51-000-001). | | | X | X | X | | |
| (13) If the EPSUs disconnection method was chosen at the entry into storage, disconnect the EPSUs (Ref. AMM TASK 33-51-38-000-001). NOTE: For EPSUs disconnection, only the steps related to the disconnection of EPSUs in the EPSU removal task are necessary. | | | X | X | X | | |
(14) Use the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) to seal:
| | | X | | | | |
(15) Use the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) to seal all the openings that give access to:
| | | | X | | | |
| (16) Close forward avionics-compartment access-door 811 (Ref. AMM TASK 52-41-00-410-002). Use the Film-- Waterproof Barrier - (Material No.14HMB1) and the Adhesive Film Tape-Surface protection PVC film coated Pressure sensitive acrylic-based adhesiv - (Material No.05RNN1) or Adhesive Film Tape-- Aluminium Foil - (Material No.05RAB9) to seal forward avionics-compartment access-door 811 and the door handle. | X | X | X | X | X | | |
Subtask 10-12-00-942-068-A
A. Close-up
(1) Make sure that all the removed protection covers/plugs are installed on the fuselage, the engines and the APU areas (Ref. AMM TASK 10-11-00-555-013).
(2) Make sure that all the external connections (external power supply, etc.) are disconnected from the aircraft. This does not include the aircraft grounding (earthing) cable.
(3) Remove the access platform(s).
(4) Remove all the fixtures, tools, test and support equipment used during this procedure.
(5) If you find a defect, make an entry in the logbook.
(1) Make sure that all the removed protection covers/plugs are installed on the fuselage, the engines and the APU areas (Ref. AMM TASK 10-11-00-555-013).
(2) Make sure that all the external connections (external power supply, etc.) are disconnected from the aircraft. This does not include the aircraft grounding (earthing) cable.
(3) Remove the access platform(s).
(4) Remove all the fixtures, tools, test and support equipment used during this procedure.
(5) If you find a defect, make an entry in the logbook.