DOC AIRBUS | AMM A320FInstallation of the Gravity Fill Cap/Adaptor
TASK 28-11-43-400-001-A
Installation of the Gravity Fill Cap/Adaptor
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Expendable Parts
E. Referenced Information
3. Job Set-up
Subtask 28-11-43-941-052-A ** ON A/C NOT FOR ALL
Subtask 28-11-43-420-051-A ** ON A/C NOT FOR ALL
Subtask 28-11-43-410-050-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.02 06:17:06 UTC
Installation of the Gravity Fill Cap/Adaptor
WARNING:
THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL). CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.
WARNING:
MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION.
WARNING:
MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
FIN: 42QM ** ON A/C NOT FOR ALL
FIN: 43QM ** ON A/C NOT FOR ALL
FIN: 44QM ** ON A/C NOT FOR ALL
FIN: 45QM ** ON A/C NOT FOR ALL
1. Reason for the JobFIN: 43QM ** ON A/C NOT FOR ALL
FIN: 44QM ** ON A/C NOT FOR ALL
FIN: 45QM ** ON A/C NOT FOR ALL
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE |
| No specific | AR | SAFETY BARRIER(S) |
| No specific | Torque wrench: range to between 7.9 and 5.7 m.daN (58.26 and 42.04 lbf.ft )  | |
| 98D28004000000 | 1 | SPANNER-OVERWING FILLER |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.03FAB1) | Mineral Oil base Grease-- Vaseline or Petrolatum - |
| (Material No.06AAC1) | Polysulfide Sealant-General Purpose Interfay - |
| (Material No.06ABA1) | Polysulfide Sealant-Fuel Tank Brushable - |
| (Material No.06LCG9) | Non Hardening Jointing Putty-Medium Temp. Area - - |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.10ABC1) | Surface Pretreatment-Light Alloys Chemical Conversion Yellow - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| FOR [42QM] (ADAPTER-OVERWING REFUEL, L) | |
| FOR [44QM] (CAP-OVERWING REFUEL, L) | |
| 540PB | |
| FOR [43QM] (ADAPTER-OVERWING REFUEL, R) | |
| FOR [45QM] (CAP-OVERWING REFUEL, R) | |
| 640PB | |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 8 | BLIND RIVETS | AIPC 28-11-05-25-010 |
| 5 | O-RING | AIPC 28-11-05-25-040 |
| 6 | O-RING | AIPC 28-11-05-25-050 |
| 12 | COTTER PIN | AIPC 28-11-43-01-010 |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 12-11-28-650-003-A | Pressure Refuel with Automatic Control |
| TASK 20-28-00-720-006-A | Check of the Electrical Bonding of the Fluid Systems |
| TASK 28-10-00-910-001-A | Safety Procedures When You Do Work in a Fuel Tank |
| TASK 28-10-00-910-002-A | Access to the Fuel Tanks and the Work Areas |
| TASK 28-11-00-790-005-A | Leak Test of the Wing Tanks and Vent Surge Tank (without Fuel) by the Local Blowing Procedure |
| TASK 28-11-00-790-009-A | Leak Test of the Fuel Tanks - Without Fuel - Helium Procedure |
| TASK 28-11-00-790-802-A | Leak Test of the Wing Tanks and the Center Tank - Without Fuel - Pressurized Air and Helium/Air Procedure |
| TASK 28-12-46-000-001-A | Removal of the Overpressure Protector Outlet |
| TASK 28-12-46-400-001-A | Installation of the Overpressure Protector Outlet |
| TASK 28-25-00-650-001-A | Pressure Defuel |
| TASK 28-25-00-650-003-A | To Drain Remaining Fuel from the Wing Tanks and the Center Tank |
| TASK 28-25-00-650-003-A-01 | To Drain Remaining Fuel from the Wing Tanks and the Center Tank |
| TASK 28-25-00-869-001-A | Fuel Transfer |
| TASK 57-27-11-000-002-A | Removal of the Access Panel |
| TASK 57-27-11-400-002-A | Installation of the Access Panel |
Gravity Fill Cap/Adaptor.Subtask 28-11-43-941-052-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(2) Make sure that the SAFETY BARRIER(S) are in position.
Subtask 28-11-43-860-051-A ** ON A/C NOT FOR ALL WARNING:
BEFORE YOU DO WORK IN OR NEAR A FUEL TANK, MAKE SURE THAT YOU OBEY ALL THE SAFETY PROCEDURES. THIS WILL PREVENT INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT.
(1) You must obey the fuel safety procedures when you do work in a fuel tank (Ref. AMM TASK 28-10-00-910-001). (2) Make sure that the SAFETY BARRIER(S) are in position.
B. Aircraft Maintenance Configuration
(1) Make sure that the applicable fuel tank is defueled (Ref. AMM TASK 28-25-00-650-001).
(2) Make sure that the remaining fuel has been drained from the applicable fuel tank (Ref. AMM TASK 28-25-00-650-003).
(3) Make sure that the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE is below the applicable access panel 540PB(640PB).
(4) Make sure that the applicable access panel 540PB(640PB) is removed (Ref. AMM TASK 57-27-11-000-002) and (Ref. AMM TASK 28-10-00-910-002).
Subtask 28-11-43-860-051-B ** ON A/C NOT FOR ALL (1) Make sure that the applicable fuel tank is defueled (Ref. AMM TASK 28-25-00-650-001).
(2) Make sure that the remaining fuel has been drained from the applicable fuel tank (Ref. AMM TASK 28-25-00-650-003).
(3) Make sure that the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE is below the applicable access panel 540PB(640PB).
(4) Make sure that the applicable access panel 540PB(640PB) is removed (Ref. AMM TASK 57-27-11-000-002) and (Ref. AMM TASK 28-10-00-910-002).
B. Aircraft Maintenance Configuration
(1) Make sure that the applicable fuel tank is defueled (Ref. AMM TASK 28-25-00-650-001).
(2) Make sure that the remaining fuel has been drained from the applicable fuel tank (Ref. AMM TASK 28-25-00-650-003).
(3) Make sure that the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE is below the applicable access panel 540PB(640PB).
(4) Make sure that the applicable access panel 540PB(640PB) is removed (Ref. AMM TASK 28-12-46-000-001) and (Ref. AMM TASK 28-10-00-910-002).
4. Procedure(1) Make sure that the applicable fuel tank is defueled (Ref. AMM TASK 28-25-00-650-001).
(2) Make sure that the remaining fuel has been drained from the applicable fuel tank (Ref. AMM TASK 28-25-00-650-003).
(3) Make sure that the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE is below the applicable access panel 540PB(640PB).
(4) Make sure that the applicable access panel 540PB(640PB) is removed (Ref. AMM TASK 28-12-46-000-001) and (Ref. AMM TASK 28-10-00-910-002).
Subtask 28-11-43-420-051-A ** ON A/C NOT FOR ALL
A. Preparation for Installation
(1) Clean the component interface and/or the adjacent area with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Remove paint from the component interface on the wing with abrasive paper grade 320.
(4) Clean the area with Non Aqueous Cleaner-General - - (Material No.08BAA9) and a lint-free cloth.
(5) Do an inspection of the component interfaces and the adjacent area.
(6) Apply Surface Pretreatment-Light Alloys Chemical Conversion Yellow - (Material No.10ABC1) to the metal surface of the component interface.
(7) Lubricate the new AIPC 28-11-05-25-040 O-RING (5) and the new AIPC 28-11-05-25-050 O-RING (6) with Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) .
(8) Install the O-ring (6) in the seal ring (11).
(9) Install the O-ring (5) around the adaptor (4).
(10) Lubricate the threads of the adaptor (4) and the nut (7) with Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) .
Subtask 28-11-43-420-050-A ** ON A/C NOT FOR ALL (1) Clean the component interface and/or the adjacent area with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Remove paint from the component interface on the wing with abrasive paper grade 320.
(4) Clean the area with Non Aqueous Cleaner-General - - (Material No.08BAA9) and a lint-free cloth.
(5) Do an inspection of the component interfaces and the adjacent area.
(6) Apply Surface Pretreatment-Light Alloys Chemical Conversion Yellow - (Material No.10ABC1) to the metal surface of the component interface.
(7) Lubricate the new AIPC 28-11-05-25-040 O-RING (5) and the new AIPC 28-11-05-25-050 O-RING (6) with Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) .
(8) Install the O-ring (6) in the seal ring (11).
(9) Install the O-ring (5) around the adaptor (4).
(10) Lubricate the threads of the adaptor (4) and the nut (7) with Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) .
B. Installation of the Gravity Fill Cap/Adaptor
(1) Install the adaptor (4) with the diamond mark forward and aligned with the line of flight
(2) Make sure that the clearance between the adaptor (4) and the wing skin is between 0.5 mm (0.0197 in.) and 1.5 mm (0.0591 in.).
(3) Apply sufficient Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to fill the recess between the adaptor (4) and the wing skin.
(4) Install the seal ring (11), insulating gasket (10) and the nut (7) on the adaptor (4).
(5) Use the 98D28004000000 SPANNER-OVERWING FILLER and TORQUE the nut (7) to between 7.9 and 5.7 m.daN (58.26 and 42.04 lbf.ft ).
(8) To install the locking plate (9) on the nut (7) (removed nut):
(a) Install the locking plate (9) in a slot in the adaptor (4) and align with the holes on the nut (7):
(a) Install the locking plate (9) in a slot in the adaptor (4) and the nut (7), make a mark for the two rivet holes.
(b) Drill two new holes of 4.064 MM (0.16 IN.) dia on the nut (7).
(c) Deburr the holes.
(d) Make sure that you remove the swarf from the work area.
(10) Apply a thin layer of Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the mating surfaces of the locking plate (9).
(11) Hold the locking plate (9) in position and secure with the AIPC 28-11-05-25-010 BLIND RIVETS (8).
(12) Remove the unwanted sealant from around the locking plate (9). Make sure that you keep a smooth fillet around the edges.
(13) Attach the lanyard (3) to the locking plate (9).
(14) Put the lanyard (3) in position on the cap (2) and secure with the AIPC 28-11-43-01-010 COTTER PIN (12).
(15) Install the cap (2) in the adaptor (4). Align the handle (1) with the line of flight.
(16) Make sure that the FWD symbol is adjacent to the diamond mark.
(17) Make sure that the maximum in-to-wind or out-of-wind dimension (between the cap (2) and the wing skin) is between:
5. Close-up(1) Install the adaptor (4) with the diamond mark forward and aligned with the line of flight
(2) Make sure that the clearance between the adaptor (4) and the wing skin is between 0.5 mm (0.0197 in.) and 1.5 mm (0.0591 in.).
(3) Apply sufficient Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to fill the recess between the adaptor (4) and the wing skin.
(4) Install the seal ring (11), insulating gasket (10) and the nut (7) on the adaptor (4).
(5) Use the 98D28004000000 SPANNER-OVERWING FILLER and TORQUE the nut (7) to between 7.9 and 5.7 m.daN (58.26 and 42.04 lbf.ft )
. NOTE: Make sure that the diamond mark on the adaptor (4) stays aligned with the line of flight while the torque is applied.
WARNING:
THIS INSTRUCTION IS APPLICABLE TO A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL) ITEM. CAREFULLY OBEY ALL GIVEN INSTRUCTIONS WHEN YOU DO THIS STEP. IF YOU DO NOT OBEY THESE INSTRUCTIONS, A DANGEROUS CONDITION CAN OCCUR THAT CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.
(6) Do a bonding check: - Do a bonding check from the adaptor (4) to the wing skin panel (Ref. AMM TASK 20-28-00-720-006). The bonding resistance must be less than 10 milliohms.
(8) To install the locking plate (9) on the nut (7) (removed nut):
(a) Install the locking plate (9) in a slot in the adaptor (4) and align with the holes on the nut (7):
- If the holes do not align on the locking plate (9) and the nut (7), do the steps that follow for new nut (7).
NOTE: If new holes are necessary they must be approximately 180 degrees opposite to the damaged holes on the nut (7).
(9) To install the locking plate (9) on the nut (7) (new nut): (a) Install the locking plate (9) in a slot in the adaptor (4) and the nut (7), make a mark for the two rivet holes.
(b) Drill two new holes of 4.064 MM (0.16 IN.) dia on the nut (7).
(c) Deburr the holes.
(d) Make sure that you remove the swarf from the work area.
(10) Apply a thin layer of Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the mating surfaces of the locking plate (9).
(11) Hold the locking plate (9) in position and secure with the AIPC 28-11-05-25-010 BLIND RIVETS (8).
(12) Remove the unwanted sealant from around the locking plate (9). Make sure that you keep a smooth fillet around the edges.
(13) Attach the lanyard (3) to the locking plate (9).
(14) Put the lanyard (3) in position on the cap (2) and secure with the AIPC 28-11-43-01-010 COTTER PIN (12).
(15) Install the cap (2) in the adaptor (4). Align the handle (1) with the line of flight.
(16) Make sure that the FWD symbol is adjacent to the diamond mark.
(17) Make sure that the maximum in-to-wind or out-of-wind dimension (between the cap (2) and the wing skin) is between:
- +0.6 mm (0.0236 in.) and -0.6 mm (-0.0236 in.) in the direction of the line-of-flight
- +0.3 mm (0.0118 in.) and -0.3 mm (-0.0118 in.) across the direction of the line-of-flight.
Subtask 28-11-43-410-050-A ** ON A/C NOT FOR ALL
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-002):
(a) FOR [42QM] (ADAPTER-OVERWING REFUEL, L), [44QM] (CAP-OVERWING REFUEL, L)
install 540PB.
(b) FOR [43QM] (ADAPTER-OVERWING REFUEL, R), [45QM] (CAP-OVERWING REFUEL, R)
install 640PB.
Subtask 28-11-43-410-050-B ** ON A/C NOT FOR ALL (1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the applicable access panel (Ref. AMM TASK 57-27-11-400-002):
(a) FOR [42QM] (ADAPTER-OVERWING REFUEL, L), [44QM] (CAP-OVERWING REFUEL, L)
install 540PB.
(b) FOR [43QM] (ADAPTER-OVERWING REFUEL, R), [45QM] (CAP-OVERWING REFUEL, R)
install 640PB.
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the applicable access panel (Ref. AMM TASK 28-12-46-400-001):
(a) FOR [42QM] (ADAPTER-OVERWING REFUEL, L), [44QM] (CAP-OVERWING REFUEL, L)
install 540PB.
(b) FOR [43QM] (ADAPTER-OVERWING REFUEL, R), [45QM] (CAP-OVERWING REFUEL, R)
install 640PB.
Subtask 28-11-43-650-051-A ** ON A/C NOT FOR ALL (1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the applicable access panel (Ref. AMM TASK 28-12-46-400-001):
(a) FOR [42QM] (ADAPTER-OVERWING REFUEL, L), [44QM] (CAP-OVERWING REFUEL, L)
install 540PB.
(b) FOR [43QM] (ADAPTER-OVERWING REFUEL, R), [45QM] (CAP-OVERWING REFUEL, R)
install 640PB.
B. Fuel Configuration
(1) Refuel, defuel or transfer fuel as necessary (Ref. AMM TASK 12-11-28-650-003), (Ref. AMM TASK 28-25-00-650-001) or (Ref. AMM TASK 28-25-00-869-001).
Subtask 28-11-43-942-050-A ** ON A/C NOT FOR ALL (1) Refuel, defuel or transfer fuel as necessary (Ref. AMM TASK 12-11-28-650-003), (Ref. AMM TASK 28-25-00-650-001) or (Ref. AMM TASK 28-25-00-869-001).
C. Removal of Equipment
(1) Remove the safety barriers.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(1) Remove the safety barriers.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.