W DOC AIRBUS | AMM A320F

Installation of the Access Panel

TASK 57-27-11-400-001-A
Installation of the Access Panel

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: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:
  • THE FLIGHT CONTROLS
  • THE FLIGHT CONTROL SURFACES
  • THE LANDING GEAR AND THE RELATED DOORS
  • COMPONENTS THAT MOVE.
MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.
ZONE: 540
ZONE: 640
1. Reason for the Job
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
1
PROBE DIA 1.57 TO 1.65 MM (0.062 TO 0.065 IN)
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 30 and 25 lbf.in (0.34 and 0.28 m.daN ) T
No specific
Torque wrench: range to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T
98D27803500001
1
LOCKING TOOL ZERO POS
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.03FAB1)
Mineral Oil base Grease-- Vaseline or Petrolatum -
(Material No.03FDG1)
Mineral Oil base Grease-Anti-Fretting - -
(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.05LCA1)
Adhesive-Vapor Seal Fuel Tank - -
(Material No.06ABB1)
Polysulfide Sealant-Fuel Tank Fillet -
(Material No.06LCG9)
Non Hardening Jointing Putty-Medium Temp. Area - -
(Material No.08BAA9)
Non Aqueous Cleaner-General - -
(Material No.14SBA1)
Textile-Lint free Cotton -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
540
FUEL TANK
640
FUEL TANK
540AB, 540BB, 540CB, 540DB, 540EB, 540FB, 540GB, 640AB, 640BB, 640CB, 640DB, 640EB, 640FB, 640GB
 D. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
15
KNITTED GASKET
AIPC 57-27-05-01-030
20
KNITTED GASKET
AIPC 57-27-05-01-030
26
KNITTED GASKET
AIPC 57-27-05-01-070
31
KNITTED GASKET
AIPC 57-27-05-01-070
4
KNITTED GASKET
AIPC 57-27-05-08-030
9
KNITTED GASKET
AIPC 57-27-05-08-030
14
PROTECTIVE RING
AIPC 57-27-11-01-040
25
PROTECTIVE RING
AIPC 57-27-11-01-040
3
PROTECTIVE RING
AIPC 57-27-11-01-040
13
SEALING RING
AIPC 57-27-11-01-070
19
SEALING RING
AIPC 57-27-11-01-070
2
SEALING RING
AIPC 57-27-11-01-070
8
SEALING RING
AIPC 57-27-11-01-070
24
SEALING RING
AIPC 57-27-11-02-070
30
SEALING RING
AIPC 57-27-11-02-070
15
KNITTED GASKET
AIPC 57-27-85-01-030
20
KNITTED GASKET
AIPC 57-27-85-01-030
26
KNITTED GASKET
AIPC 57-27-85-01-060
31
KNITTED GASKET
AIPC 57-27-85-01-060
4
KNITTED GASKET
AIPC 57-27-85-08-030
9
KNITTED GASKET
AIPC 57-27-85-08-030
 E. Referenced Information
REFERENCE
DESIGNATION
TASK 12-11-28-650-003-A
Pressure Refuel with Automatic Control
TASK 20-28-00-912-802-A
Electrical Bonding - General Maintenance Procedure
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 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 28-11-00-790-009-A
Leak Test of the Fuel Tanks - Without Fuel - Helium Procedure
TASK 28-18-00-200-002-A
Detailed Inspection of Tank Bonding Leads (SFAR88)
TASK 28-18-00-200-002-A-01
Detailed Inspection of Tank Bonding Leads (SFAR88)
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 28-42-00-740-001-A
Status Report (BITE)
TASK 28-46-00-740-001-A
Functional (BITE) Test
TASK 57-55-11-000-001-A
Removal of the Flap Track Fairings Nos. 2, 3 and 4
TASK 57-55-11-000-004-A
Removal of the Flap Track Fairings Nos. 2, 3 and 4
TASK 57-55-11-400-001-A
Installation of the Flap Track Fairings Nos. 2, 3 and 4
TASK 57-55-11-400-004-A
Installation of the Flap Track Fairings Nos. 2, 3 and 4
TASK 71-00-00-710-003-A
Engine Automatic Start
TASK 71-00-00-710-003-B
Engine Automatic Start
TASK 71-00-00-710-004-A
Engine Manual Start
TASK 71-00-00-710-004-B
Engine Manual Start
TASK 71-00-00-710-043-A
Normal Engine Automatic-Start Procedure
TASK 71-00-00-710-047-A
Normal Engine Manual-Start Procedure
TASK 71-00-00-860-822-A
Start the Engine (Normal Manual Start)
TASK 71-00-00-860-823-A
Start the Engine (Normal Automatic Start)
TASK 73-11-06-000-801-A
Removal of the Fuel Filter Element
TASK 73-11-06-400-801-A
Installation of the Fuel Filter Element
TASK 73-11-10-920-001-A
Remove, Inspect and Replace Fuel Filter Element
TASK 73-11-10-920-001-B
Remove, Inspect and Replace Fuel Filter Element
TASK 73-12-42-920-010-A
Remove, Inspect for Contamination and Replace Main Fuel Filter
SRM 517512
F Access Panels - Rib 2 to Rib 13
F Access Panels - Rib 2 to Rib 13 Bolt Removal/Tightening Sequence ** ON A/C NOT FOR ALL
F Access Panels - Rib 2 to Rib 13 Bolt Removal/Tightening Sequence ** ON A/C NOT FOR ALL
3. Job Set-up
Subtask 57-27-11-941-070-A
A. Safety Precautions
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) and (Ref. AMM TASK 28-10-00-910-002).
   (2) Make sure that the WARNING NOTICE(S) are in position in the cockpit to tell persons not to operate the flaps or slats.
   (3) Make sure that the 98D27803500001 LOCKING TOOL ZERO POS is correctly positioned on the flap/slat control lever.
Subtask 57-27-11-860-060-A
B. Aircraft Maintenance Configuration
   (1) Make sure that the applicable fuel tank has been 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).
Subtask 57-27-11-865-054-A
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFUEL/XFR VALVE1/WING/R2QPA11
49VUFUEL/XFR VALVE1/WING/L1QPA10
** ON A/C ALL
49VUFUEL/X FEED/VALVE/MOT12QEA12
** ON A/C NOT FOR ALL
121VUFUEL/CTR TK/PUMP2 SPLY30QAP26
121VUFUEL/CTR TK/PUMP1 SPLY29QAP23
** ON A/C NOT FOR ALL
121VUFUEL/RFL/DFL/SPLY2QUL24
121VUFUEL/RFL/DFL/XFR/DEFUEL/VALVE1QUL23
** ON A/C ALL
121VUFUEL/L WING TK/PUMP2 SPLY7QAN26
121VUFUEL/L WING TK/PUMP1 SPLY1QAN23
121VUFUEL/R WING TK/PUMP2 SPLY8QAQ26
121VUFUEL/R WING TK/PUMP1 SPLY2QAQ23
** ON A/C NOT FOR ALL
121VUFUEL/RFL/DFL/SPLY2QUL23
121VUFUEL/RFL/DFL/XFR/DEFUEL/VALVE1QUL22
Subtask 57-27-11-010-061-A ** ON A/C NOT FOR ALL
D. Get Access
   (1) Make sure that the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE is in position below the applicable access panel:
   (2) Make sure that the forward and aft fixed fairings of the flap track 3 have been removed (Ref. AMM TASK 57-55-11-000-001):
Subtask 57-27-11-010-061-B ** ON A/C NOT FOR ALL
D. Get Access
   (1) Make sure that the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE is in position below the applicable access panel:
   (2) Make sure that the forward and aft fixed fairings of the flap track 3 have been removed (Ref. AMM TASK 57-55-11-000-004):
4. Procedure
Subtask 57-27-11-560-050-A
A. Preparation of a Component for Installation
   (1) To install panel 540AB( 640AB):
     (a) To install the PRE modification 30100J2130 panel:
       1 We recommend that the sealing ring (2) and the protective ring (3) are replaced each time the access panel (1) is installed. If a new seal is not used, you must make sure that the sealing ring (2) and the protective ring (3) are:
  • Assembled correctly
  • Bonded on the access panel (1)
  • Not twisted or damaged.
       2 Examine the knitted gasket (4) for damage. If necessary, remove and discard it.
       3 Use the Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean:
  • The groove in the access panel (1) for the sealing ring (2) if a new seal is being installed
  • The mating surface for the protective ring (3) if a new protective ring is being installed
  • The clamp ring (5)
  • The interfaces of the access panel (1) and the wing skin.
       4 Examine for damage the interfaces of:
  • The access panel (1)
  • The clamp ring (5)
  • The wing skin
  • The bolt holes in the clamp ring (5).
     (b) To install the POST modification 30100J2130 panel:
       1 We recommend that the sealing ring (8) is replaced each time the access panel (7) is installed. If a new seal is not used, you must make sure that the sealing ring (8) is:
  • Assembled correctly
  • Bonded on the access panel (7)
  • Not twisted or damaged.
       2 Examine the knitted gasket (9) for damage. If necessary, remove and discard it.
       3 Use the Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean:
  • The groove in the access panel (7) for the sealing ring (8) if a new seal is being installed
  • The outer access panel (10)
  • The interfaces of the access panel (7) and the wing skin.
       4 Examine for damage the interfaces of:
  • The access panel (7)
  • The outer access panel (10)
  • The wing skin
  • The bolt holes in the outer access panel (10).
   (2) To install panels 540BB( 640BB) and 540CB( 640CB):
     (a) To install the PRE modification 30100J2130 panel:
       1 We recommend that the sealing ring (13) and the protective ring (14) are replaced each time the access panel (12) is installed. If a new seal is not used, you must make sure that the sealing ring (13) and the protective ring (14) are:
  • Assembled correctly
  • Bonded on the access panel (12)
  • Not twisted or damaged.
       2 Examine the knitted gasket (15) for damage. If necessary, remove and discard it.
       3 Use the Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean:
  • The groove in the access panel (12) for the sealing ring (13) if a new seal is being installed
  • The mating surface for the protective ring (14) if a new protective ring is being installed
  • The clamp ring (16)
  • The interfaces of the access panel (12) and the wing skin.
       4 Examine for damage the interfaces of:
  • The access panel (12)
  • The clamp ring (16)
  • The wing skin
  • The bolt holes in the clamp ring (16).
     (b) To install the POST modification 30100J2130 panel:
       1 We recommend that the sealing ring (19) is replaced each time the access panel (18) is installed. If a new seal is not used, you must make sure that the sealing ring (19) is:
  • Assembled correctly
  • Bonded on the access panel (18)
  • Not twisted or damaged.
       2 Examine the knitted gasket (20) for damage. If necessary, remove and discard it.
       3 Use the Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean:
  • The groove in the access panel (18) for the sealing ring (19) if a new seal is being installed
  • The outer access panel (21)
  • The interfaces of the access panel (18) and the wing skin.
       4 Examine for damage the interfaces of:
  • The access panel (18)
  • The outer access panel (21)
  • The wing skin
  • The bolt holes in the outer access panel (21).
   (3) To install panels 540DB( 640DB), 540EB( 640EB), 540FB( 640FB) and 540GB( 640GB):
     (a) To install the PRE modification 30100J2130 panel:
       1 We recommend that the sealing ring (24) and the protective ring (25) are replaced each time the access panel (23) is installed. If a new seal is not used, you must make sure that the sealing ring (24) and the protective ring (25) are:
  • Assembled correctly
  • Bonded on the access panel (23)
  • Not twisted or damaged.
       2 Examine the knitted gasket (26) for damage. If necessary, remove and discard it.
       3 Use the Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean:
  • The groove in the access panel (23) for the sealing ring (24) if a new seal is being installed
  • The mating surface for the protective ring (25) if a new protective ring is being installed
  • The clamp ring (27)
  • The interfaces of the access panel (23) and the wing skin.
       4 Examine for damage the interfaces of:
  • The access panel (23)
  • The clamp ring (27)
  • The wing skin
  • The bolt holes in the clamp ring (27).
     (b) To install the POST modification 30100J2130 panel:
       1 We recommend that the sealing ring (30) is replaced each time the access panel (29) is installed. If a new seal is not used, you must make sure that the sealing ring (30) is:
  • Assembled correctly
  • Bonded on the access panel (29)
  • Not twisted or damaged.
       2 Examine the knitted gasket (31) for damage. If necessary, remove and discard it.
       3 Use the Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean:
  • The groove in the access panel (29) for the sealing ring (30) if a new seal is being installed
  • The outer access panel (32)
  • The interfaces of the access panel (29) and the wing skin.
       4 Examine for damage the interfaces of:
  • The access panel (29)
  • The outer access panel (32)
  • The wing skin
  • The bolt holes in the outer access panel (32).
Subtask 57-27-11-420-050-A
B. Preparation for the Installation
CAUTION: YOU MUST FOLLOW THESE STEPS OF THE PROCEDURE ACCURATELY. THIS WILL PREVENT DAMAGE TO THE PARTS.
   (1) Installation of panel 540AB( 640AB):
     (a) To install the PRE modification 30100J2130 panel:
       1 If you install the new AIPC 57-27-11-01-070 SEALING RING (2), apply a thin layer of Adhesive-Vapor Seal Fuel Tank - - (Material No.05LCA1) on the groove of the access panel (1).
       2 Before you install the sealing ring (2), make sure that the sealant is dry.
       3 Put the sealing ring (2) with the flat edge down into the groove of the access panel (1).
       4 If you install the new AIPC 57-27-11-01-040 PROTECTIVE RING (3), apply a layer of Polysulfide Sealant-Fuel Tank Fillet - (Material No.06ABB1) on the mating surface.
       5 Put the protective ring (3) in position on the access panel (1).
       6 Lubrication of the knitted gasket (4):
NOTE: You can use Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) as an alternative to Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) . It is not permitted to mix Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) with Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) and use them at the same time. It is necessary to clean and remove the grease from the parts before you use an alternative grease.
         a If you install the new AIPC 57-27-05-08-030 KNITTED GASKET (4) or the new AIPC 57-27-85-08-030 KNITTED GASKET (4), apply Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) on it.
         b If you install the removed knitted gasket (4), make sure that it is sufficiently soaked with Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) .
       7 Put the knitted gasket (4) on the clamp ring (5).
       8 Align the holes in the knitted gasket (4) with the holes in the clamp ring (5).
       9 Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the shanks, the threads and below the heads of the bolts (6).
     (b) To install the POST modification 30100J2130 panel:
       1 If you install the new AIPC 57-27-11-01-070 SEALING RING (8), apply a thin layer of Adhesive-Vapor Seal Fuel Tank - - (Material No.05LCA1) on the groove of the access panel (7).
       2 Before you install the sealing ring (8), make sure that the sealant is dry.
       3 Put the sealing ring (8) with the flat edge down into the groove of the access panel (7).
       4 Lubrication of the knitted gasket (9):
NOTE: You can use Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) as an alternative to Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) . It is not permitted to mix Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) with Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) and use them at the same time. It is necessary to clean and remove the grease from the parts before you use an alternative grease.
         a If you install the new AIPC 57-27-05-08-030 KNITTED GASKET (9) or the new AIPC 57-27-85-08-030 KNITTED GASKET (9), apply Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) on it.
         b If you install the removed knitted gasket (9), make sure that it is sufficienlty soaked with Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) .
       5 Put the knitted gasket (9) on the outer access panel (10).
       6 Align the holes in the knitted gasket (9) with the holes in the outer access panel (10).
       7 Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the shanks, the threads and below the heads of the bolts (11).
   (2) Installation of panels 540BB( 640BB) and 540CB( 640CB):
     (a) To install the PRE modification 30100J2130 panel:
       1 If you install the new AIPC 57-27-11-01-070 SEALING RING (13), apply a thin layer of Adhesive-Vapor Seal Fuel Tank - - (Material No.05LCA1) on the groove of the access panel (12).
       2 Before you install the sealing ring (13), make sure that the sealant is dry.
       3 Put the sealing ring (13) with the flat edge down into the groove of the access panel (12).
       4 If you install the new AIPC 57-27-11-01-040 PROTECTIVE RING (14), apply a layer of Polysulfide Sealant-Fuel Tank Fillet - (Material No.06ABB1) on the mating surface.
       5 Put the protective ring (14) in position on the access panel (12).
       6 Lubrication of the knitted gasket (15):
NOTE: You can use Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) as an alternative to Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) . It is not permitted to mix Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) with Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) and use them at the same time. It is necessary to clean and remove the grease from the parts before you use an alternative grease.
         a If you install the new AIPC 57-27-05-01-030 KNITTED GASKET (15) or the new AIPC 57-27-85-01-030 KNITTED GASKET (15), apply Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) on it.
         b If you install the removed knitted gasket (15), make sure that it is sufficiently soaked with Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) .
       7 Put the knitted gasket (15) on the clamp ring (16).
       8 Align the holes in the knitted gasket (15) with the holes in the clamp ring (16).
       9 Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the shanks, the threads and below the heads of the bolts (17).
     (b) To install the POST modification 30100J2130 panel:
       1 If you install the new AIPC 57-27-11-01-070 SEALING RING (19), apply a thin layer of Adhesive-Vapor Seal Fuel Tank - - (Material No.05LCA1) on the groove of the access panel (18).
       2 Before you install the sealing ring (19), make sure that the sealant is dry.
       3 Put the sealing ring (19) with the flat edge down into the groove of the access panel (18).
       4 Lubrication of the knitted gasket (20):
NOTE: You can use Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) as an alternative to Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) . It is not permitted to mix Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) with Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) and use them at the same time. It is necessary to clean and remove the grease from the parts before you use an alternative grease.
         a If you install the new AIPC 57-27-05-01-030 KNITTED GASKET (20) or the new AIPC 57-27-85-01-030 KNITTED GASKET (20), apply Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) on it.
         b If you install the removed knitted gasket (20), make sure that it is sufficiently soaked with Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) .
       5 Put the knitted gasket (20) on the outer access panel (21).
       6 Align the holes in the knitted gasket (20) with the holes in the outer access panel (21).
       7 Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the shanks, the threads and below the heads of the bolts (22).
   (3) Installation of panels 540DB( 640DB), 540EB( 640EB), 540FB( 640FB) and 540GB( 640GB):
     (a) To install the PRE modification 30100J2130 panel:
       1 If you install the new AIPC 57-27-11-02-070 SEALING RING (24), apply a thin layer of Adhesive-Vapor Seal Fuel Tank - - (Material No.05LCA1) on the groove of the access panel (23).
       2 Before you install the sealing ring (24), make sure that the sealant is dry.
       3 Put the sealing ring (24) with the flat edge down into the groove of the access panel (23).
       4 If you install the new AIPC 57-27-11-01-040 PROTECTIVE RING (25), apply a layer of Polysulfide Sealant-Fuel Tank Fillet - (Material No.06ABB1) on the mating surface.
       5 Put the protective ring (25) in position on the access panel (23).
       6 Lubrication of the knitted gasket (26):
NOTE: You can use Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) as an alternative to Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) . It is not permitted to mix Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) with Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) and use them at the same time. It is necessary to clean and remove the grease from the parts before you use an alternative grease.
         a If you install the new AIPC 57-27-05-01-070 KNITTED GASKET (26) or the new AIPC 57-27-85-01-060 KNITTED GASKET (26), apply Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) on it.
         b If you install the removed knitted gasket (26), make sure that it is sufficiently soaked with Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) .
       7 Put the knitted gasket (26) on the clamp ring (27).
       8 Align the holes in the knitted gasket (26) with the holes in the clamp ring (27).
       9 Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the shanks, the threads and below the heads of the bolts (28).
     (b) To install the POST modification 30100J2130 panel:
       1 If you install the new AIPC 57-27-11-02-070 SEALING RING (30), apply a thin layer of Adhesive-Vapor Seal Fuel Tank - - (Material No.05LCA1) on the groove of the access panel (29).
       2 Before you install the sealing ring (30), make sure that the sealant is dry.
       3 Put the sealing ring (30) with the flat edge down into the groove of the access panel (29).
       4 Lubrication of the knitted gasket (31):
NOTE: You can use Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) as an alternative to Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) . It is not permitted to mix Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) with Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) and use them at the same time. It is necessary to clean and remove the grease from the parts before you use an alternative grease.
         a If you install the new AIPC 57-27-05-01-070 KNITTED GASKET (31) or the new AIPC 57-27-85-01-060 KNITTED GASKET (31), apply Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) on it.
         b If you install the removed knitted gasket (31), make sure that it is sufficiently soaked with Mineral Oil base Grease-Anti-Fretting - - (Material No.03FDG1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) .
       5 Put the knitted gasket (31) on the outer access panel (32).
       6 Align the holes in the knitted gasket (31) with the holes in the outer access panel (32).
       7 Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) on the shanks, the threads and below the heads of the bolts (33).
Subtask 57-27-11-420-051-A
C. Installation of the Access Panel
   (1) To install the panel 540AB( 640AB):
     (a) To install the PRE modification 30100J2130 panel:
       1 Make sure that there are no unwanted objects and materials, tools or other equipment in the wing.
       2 Make sure that all of the bonding leads (Ref. AMM TASK 28-18-00-200-002):
  • Are in position and connected correctly
  • Are not damaged or broken
  • Show no sign of corrosion.
       3 Make sure that the work area is clean and clear of tools and equipment before you install the access panel (1).
       4 Apply a thin layer of lubricant to the shank, the threads and below the head of each bolt (6):
  • For PRE modification 25850J1637, use Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) .
  • For POST modification 25850J1637, use Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) .
       5 Remove the identification label from the access panel (1).
       6 Apply a light coating of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) to the mating face of the sealing ring (2) on the access panel (1).
       7 Put the access panel (1) in position on the wing. Make sure that the access panel and its sealing ring (2) do not move after they are put in position.
       8 Install the knitted gasket (4) and the clamp ring (5). Make sure that grease does not enter the bolt holes in the access panel (1), as a hydraulic effect can occur.
CAUTION: YOU MUST REMOVE AND INSTALL THE BOLTS IN THE SPECIFIED SEQUENCE. THIS WILL PREVENT DAMAGE TO THE ACCESS PANEL.
       9 Loosely install the bolts (6).
  • You must install with bolts NAS1790-4R5.
       10 Apply new paint to the head of the bolts (6) SRM 517512.
NOTE: It is not necessary to apply paint to the head of the bolts (6) that are made of stainless steel material.
       11 Not applicable.
CAUTION: YOU MUST TIGHTEN AND TORQUE THE BOLTS IN THE CORRECT SEQUENCE TO PREVENT DAMAGE TO THE COMPONENTS.
       12 Lightly tighten each bolt (6) (to make sure that the access panel (1) cannot tilt and damage the sealing ring (2) when the bolts are fully torque tightened).
       13 TORQUE the bolts (6) in the sequence A thru AF to between 30 and 25 lbf.in (0.34 and 0.28 m.daN ) T.
       14 TORQUE the bolts (6) in the sequence A thru AF again to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
       15 Make sure that the maximum in-to-wind or out-of-wind dimension (between the clamp ring (5) and the wing skin) is between:
  • +1.0 mm (0.0394 in.) and -1.0 mm (-0.0394 in.) along the long axis
  • +0.5 mm (0.0197 in.) and -0.5 mm (-0.0197 in.) along the short axis.
       16 Make sure that the dimension X is between 1.0 mm (0.0394 in.) and 3.0 mm (0.1181 in.).
       17 Make sure that the access panel (1) is correctly bonded:
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.
         a Do a bonding test (Ref. AMM TASK 20-28-00-912-802). Make sure that the electrical resistance is less than 10 milliohms:
  • Between the clamp ring (5) and the wing skin
  • Between the clamp ring (5) and the access panel (1).
         b Remove one bolt (6).
         c Apply a PROBE DIA 1.57 TO 1.65 MM (0.062 TO 0.065 IN) on the surface of the access panel (1) through the bolt hole.
NOTE: It is necessary that the pressure applied on the probe is sufficient to prevent the oscillations of the milliohmmeter/ohmmeter display.
       18 Install the bolt (6).
       19 TORQUE the bolt (6) to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
     (b) To install the POST modification 30100J2130 panel:
       1 Make sure that there are no unwanted objects and materials, tools or other equipment in the wing.
       2 Make sure that all of the bonding leads (Ref. AMM TASK 28-18-00-200-002):
  • Are in position and connected correctly
  • Are not damaged or broken
  • Show no sign of corrosion.
       3 Make sure that the work area is clean and clear of tools and equipment before you install the access panel (7).
       4 Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to the shank, the threads and below the head of each bolt (11).
       5 Remove the identification label from the access panel (7).
       6 Apply a light coating of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) to the mating face of the sealing ring (8) on the access panel (7).
       7 Put the access panel (7) in position on the wing. Make sure that the access panel and its sealing ring (8) do not move after they are put in position.
       8 Install the knitted gasket (9) and the outer access panel (10). Make sure that grease does not enter the bolt holes in the access panel (7), as a hydraulic effect can occur.
CAUTION: YOU MUST REMOVE AND INSTALL THE BOLTS IN THE SPECIFIED SEQUENCE. THIS WILL PREVENT DAMAGE TO THE ACCESS PANEL.
       9 Loosely install the bolts (11).
  • You must install with bolts NAS1790C4R3P.
       10 Apply new paint to the head of the bolts (11) SRM 517512.
NOTE: It is not necessary to apply paint to the head of the bolts (11) that are made of stainless steel material.
       11 Not applicable.
CAUTION: YOU MUST TIGHTEN AND TORQUE THE BOLTS IN THE CORRECT SEQUENCE TO PREVENT DAMAGE TO THE COMPONENTS.
       12 Lightly tighten each bolt (11) (to make sure that the access panel (7) cannot tilt and damage the sealing ring (8) when the bolts are fully torque tightened).
       13 TORQUE the bolts (11) in the sequence A thru AF to between 30 and 25 lbf.in (0.34 and 0.28 m.daN ) T.
       14 TORQUE the bolts (11) in the sequence A thru AF again to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
       15 Make sure that the maximum in-to-wind or out-of-wind dimension (between the outer access panel (10) and the wing skin) is between:
  • +1.0 mm (0.0394 in.) and -1.0 mm (-0.0394 in.) along the long axis
  • +0.5 mm (0.0197 in.) and -0.5 mm (-0.0197 in.) along the short axis.
       16 Make sure that the dimension X is between 0.5 mm (0.0197 in.) and 2.5 mm (0.0984 in.).
       17 Make sure that the access panel (7) is correctly bonded:
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.
         a Do a bonding test (Ref. AMM TASK 20-28-00-912-802). Make sure that the electrical resistance is less than 10 milliohms:
  • Between the outer access panel (10) and the wing skin
  • Between the outer access panel (10) and the access panel (7).
         b Remove one bolt (11).
         c Apply a PROBE DIA 1.57 TO 1.65 MM (0.062 TO 0.065 IN) on the surface of the access panel (7) through the bolt hole.
NOTE: It is necessary that the pressure applied on the probe is sufficient to prevent the oscillations of the milliohmmeter/ohmmeter display.
       18 Install the bolt (11).
       19 TORQUE the bolt (11) to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
   (2) To install panels 540BB( 640BB) and 540CB( 640CB):
     (a) To install the PRE modification 30100J2130 panel:
       1 Make sure that there are no unwanted objects and materials, tools or other equipment in the wing.
       2 Make sure that all of the bonding leads (Ref. AMM TASK 28-18-00-200-002):
  • Are in position and connected correctly
  • Are not damaged or broken
  • Show no sign of corrosion.
       3 Make sure that the work area is clean and clear of tools and equipment before you install the access panel (12).
       4 Apply a thin layer of lubricant to the shank, the threads and below the head of each bolt (17):
  • For PRE modification 25850J1637, use Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) .
  • For POST modification 25850J16370, use Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) .
       5 Remove the identification label from the access panel (12).
       6 Apply a light coating of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) to the mating face of the sealing ring (13) on the access panel (12).
       7 Put the access panel (12) in position on the wing. Make sure that the access panel and its sealing ring (13) do not move after they are put in position.
       8 Install the knitted gasket (15) and the clamp ring (16). Make sure that grease does not enter the bolt holes in the access panel (12), as a hydraulic effect can occur.
CAUTION: YOU MUST REMOVE AND INSTALL THE BOLTS IN THE SPECIFIED SEQUENCE. THIS WILL PREVENT DAMAGE TO THE ACCESS PANEL.
       9 Loosely install the bolts (17).
  • You must install with bolts NAS1790-4R5.
       10 Apply new paint to the head of the bolts (17) SRM 517512.
NOTE: It is not necessary to apply paint to the head of the bolts (17) that are made of stainless steel material.
       11 Not applicable.
CAUTION: YOU MUST TIGHTEN AND TORQUE THE BOLTS IN THE CORRECT SEQUENCE TO PREVENT DAMAGE TO THE COMPONENTS.
       12 Lightly tighten each bolt (17) (to make sure that the access panel (12) cannot tilt and damage the sealing ring (13) when the bolts are fully torque tightened).
       13 TORQUE the bolts (17) in the sequence A thru AF to between 30 and 25 lbf.in (0.34 and 0.28 m.daN ) T.
       14 TORQUE the bolts (17) in the sequence A thru AF again to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
       15 Make sure that the maximum in-to-wind or out-of-wind dimension (between the clamp ring (16) and the wing skin) is between:
  • +1.0 mm (0.0394 in.) and -1.0 mm (-0.0394 in.) along the long axis
  • +0.5 mm (0.0197 in.) and -0.5 mm (-0.0197 in.) along the short axis.
       16 Make sure that the dimension X is between 1.0 mm (0.0394 in.) and 3.0 mm (0.1181 in.).
       17 Make sure that the access panel (12) is correctly bonded:
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.
         a Do a bonding test (Ref. AMM TASK 20-28-00-912-802). Make sure that the electrical resistance is less than 10 milliohms:
  • Between the clamp ring (16) and the wing skin
  • Between the clamp ring (16) and the access panel (12).
         b Remove one bolt (17).
         c Apply a PROBE DIA 1.57 TO 1.65 MM (0.062 TO 0.065 IN) on the surface of the access panel (12) through the bolt hole.
NOTE: It is necessary that the pressure applied on the probe is sufficient to prevent the oscillations of the milliohmmeter/ohmmeter display.
       18 Install the bolt (17).
       19 TORQUE the bolt (17) to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
     (b) To install the POST modification 30100J2130 panel:
       1 Make sure that there are no unwanted objects and materials, tools or other equipment in the wing.
       2 Make sure that all of the bonding leads (Ref. AMM TASK 28-18-00-200-002):
  • Are in position and connected correctly
  • Are not damaged or broken
  • Show no sign of corrosion.
       3 Make sure that the work area is clean and clear of tools and equipment before you install the access panel (18).
       4 Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to the shank, the threads and below the head of each bolt (22).
       5 Remove the identification label from the access panel (18).
       6 Apply a light coating of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) to the mating face of the sealing ring (19) on the access panel (18).
       7 Put the access panel (18) in position on the wing. Make sure that the access panel and its sealing ring (19) do not move after they are put in position.
       8 Install the knitted gasket (20) and the outer access panel (21). Make sure that grease does not enter the bolt holes in the access panel (18), as a hydraulic effect can occur.
CAUTION: YOU MUST REMOVE AND INSTALL THE BOLTS IN THE SPECIFIED SEQUENCE. THIS WILL PREVENT DAMAGE TO THE ACCESS PANEL.
       9 Loosely install the bolts (22).
  • You must install with bolts NAS1790C4R3P.
       10 Apply new paint to the head of the bolts (22) SRM 517512.
NOTE: It is not necessary to apply paint to the head of the bolts (22) that are made of stainless steel material.
       11 Not applicable.
CAUTION: YOU MUST TIGHTEN AND TORQUE THE BOLTS IN THE CORRECT SEQUENCE TO PREVENT DAMAGE TO THE COMPONENTS.
       12 Lightly tighten each bolt (22) (to make sure that the access panel (18) cannot tilt and damage the sealing ring (19) when the bolts are fully torque tightened).
       13 TORQUE the bolts (22) in the sequence A thru AF to between 30 and 25 lbf.in (0.34 and 0.28 m.daN ) T.
       14 TORQUE the bolts (22) in the sequence A thru AF again to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
       15 Make sure that the maximum in-to-wind or out-of-wind dimension (between the outer access panel (21) and the wing skin) is between:
  • +1.0 mm (0.0394 in.) and -1.0 mm (-0.0394 in.) along the long axis
  • +0.5 mm (0.0197 in.) and -0.5 mm (-0.0197 in.) along the short axis.
       16 Make sure that the dimension X is between 0.5 mm (0.0197 in.) and 2.5 mm (0.0984 in.).
       17 Make sure that the access panel (18) is correctly bonded:
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.
         a Do a bonding test (Ref. AMM TASK 20-28-00-912-802). Make sure that the electrical resistance is less than 10 milliohms:
  • Between the outer access panel (21) and the wing skin
  • Between the outer access panel (21) and the access panel (18).
         b Remove one bolt (22).
         c Apply a PROBE DIA 1.57 TO 1.65 MM (0.062 TO 0.065 IN) on the surface of the access panel (18) through the bolt hole.
NOTE: It is necessary that the pressure applied on the probe is sufficient to prevent the oscillations of the milliohmmeter/ohmmeter display.
       18 Install the bolt (22).
       19 TORQUE the bolt (22) to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
   (3) To install panels 540DB( 640DB), 540EB( 640EB), 540FB( 640FB) and 540GB( 640GB):
     (a) To install the PRE modification 30100J2130 panel:
       1 Make sure that there are no unwanted objects and materials, tools or other equipment in the wing.
       2 Make sure that all of the bonding leads (Ref. AMM TASK 28-18-00-200-002):
  • Are in position and connected correctly
  • Are not damaged or broken
  • Show no sign of corrosion.
       3 Make sure that the work area is clean and clear of tools and equipment before you install the access panel (23).
       4 Apply a thin layer of lubricant to the shank, the threads and below the head of each bolt (28):
  • For PRE modification 25850J1637, use Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) .
  • For POST modification 25850J1637, use Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) .
       5 Remove the identification label from the access panel (23).
       6 Apply a light coating of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) to the mating face of the sealing ring (24) on the access panel (23).
       7 Put the access panel (23) in position on the wing. Make sure that the access panel and its sealing ring (24) do not move after they are put in position.
       8 Install the knitted gasket (26) and the clamp ring (27). Make sure that grease does not enter the bolt holes in the access panel (23), as a hydraulic effect can occur.
CAUTION: YOU MUST REMOVE AND INSTALL THE BOLTS IN THE SPECIFIED SEQUENCE. THIS WILL PREVENT DAMAGE TO THE ACCESS PANEL.
       9 Loosely install the bolts (28).
  • You must install with bolts NAS1790-4R5.
       10 Apply new paint to the head of the bolts (28) SRM 517512.
NOTE: It is not necessary to apply paint to the head of the bolts (28) that are made of stainless steel material.
       11 Not applicable.
CAUTION: YOU MUST TIGHTEN AND TORQUE THE BOLTS IN THE CORRECT SEQUENCE TO PREVENT DAMAGE TO THE COMPONENTS.
       12 Lightly tighten each bolt (28) (to make sure that the access panel (23) cannot tilt and damage the sealing ring (24) when the bolts are fully torque tightened).
       13 TORQUE the bolts (28) in the sequence A thru AF to between 30 and 25 lbf.in (0.34 and 0.28 m.daN ) T.
       14 TORQUE the bolts (28) in the sequence A thru AF again to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
       15 Make sure that the maximum in-to-wind or out-of-wind dimension (between the clamp ring (27) and the wing skin) is between:
  • +1.0 mm (0.0394 in.) and -1.0 mm (-0.0394 in.) along the long axis
  • +0.5 mm (0.0197 in.) and -0.5 mm (-0.0197 in.) along the short axis.
       16 Make sure that the dimension X is between 1.0 mm (0.0394 in.) and 3.0 mm (0.1181 in.).
       17 Make sure that the access panel (23) is correctly bonded:
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.
         a Do a bonding test (Ref. AMM TASK 20-28-00-912-802). Make sure that the electrical resistance is less than 10 milliohms:
  • Between the clamp ring (27) and the wing skin
  • Between the clamp ring (27) and the access panel (23).
         b Remove one bolt (28).
         c Apply a PROBE DIA 1.57 TO 1.65 MM (0.062 TO 0.065 IN) on the surface of the access panel (23) through the bolt hole.
NOTE: It is necessary that the pressure applied on the probe is sufficient to prevent the oscillations of the milliohmmeter/ohmmeter display.
       18 Install the bolt (28).
       19 TORQUE the bolt (28) to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
     (b) To install the POST modification 30100J2130 panel:
       1 Make sure that there are no unwanted objects and materials, tools or other equipment in the wing.
       2 Make sure that all of the bonding leads (Ref. AMM TASK 28-18-00-200-002):
  • Are in position and connected correctly
  • Are not damaged or broken
  • Show no sign of corrosion.
       3 Make sure that the work area is clean and clear of tools and equipment before you install the access panel (29).
       4 Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to the shank, the threads and below the head of each bolt (33).
       5 Remove the identification label from the access panel (29).
       6 Apply a light coating of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) to the mating face of the sealing ring (30) on the access panel (29).
       7 Put the access panel (29) in position on the wing. Make sure that the access panel and its sealing ring (30) do not move after they are put in position.
       8 Install the knitted gasket (31) and the outer access panel (32). Make sure that grease does not enter the bolt holes in the access panel (29), as a hydraulic effect can occur.
CAUTION: YOU MUST REMOVE AND INSTALL THE BOLTS IN THE SPECIFIED SEQUENCE. THIS WILL PREVENT DAMAGE TO THE ACCESS PANEL.
       9 Loosely install the bolts (33).
  • You must install with bolts NAS1790C4R3P.
       10 Apply new paint to the head of the bolts (33) SRM 517512.
NOTE: It is not necessary to apply paint to the head of the bolts (33) that are made of stainless steel material.
       11 Not applicable.
CAUTION: YOU MUST TIGHTEN AND TORQUE THE BOLTS IN THE CORRECT SEQUENCE TO PREVENT DAMAGE TO THE COMPONENTS.
       12 Lightly tighten each bolt (33) (to make sure that the access panel (29) cannot tilt and damage the sealing ring (30) when the bolts are fully torque tightened).
       13 TORQUE the bolts (33) in the sequence A thru AF to between 30 and 25 lbf.in (0.34 and 0.28 m.daN ) T.
       14 TORQUE the bolts (33) in the sequence A thru AF again to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
       15 Make sure that the maximum in-to-wind or out-of-wind dimension (between the outer access panel (32) and the wing skin) is between:
  • +1.0 mm (0.0394 in.) and -1.0 mm (-0.0394 in.) along the long axis
  • +0.5 mm (0.0197 in.) and -0.5 mm (-0.0197 in.) along the short axis.
       16 Make sure that the dimension X is between 0.5 mm (0.0197 in.) and 2.5 mm (0.0984 in.).
       17 Make sure that the access panel (29) is correctly bonded:
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.
         a Do a bonding test (Ref. AMM TASK 20-28-00-912-802). Make sure that the electrical resistance is less than 10 milliohms:
  • Between the outer access panel (32) and the wing skin
  • Between the outer access panel (32) and the access panel (29).
         b Remove one bolt (33).
         c Apply a PROBE DIA 1.57 TO 1.65 MM (0.062 TO 0.065 IN) on the surface of the access panel (29) through the bolt hole.
NOTE: It is necessary that the pressure applied on the probe is sufficient to prevent the oscillations of the milliohmmeter/ohmmeter display.
       18 Install the bolt (33).
       19 TORQUE the bolt (33) to between 70 and 60 lbf.in (0.79 and 0.68 m.daN ) T.
Subtask 57-27-11-865-052-A
D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFUEL/XFR VALVE1/WING/R2QPA11
49VUFUEL/XFR VALVE1/WING/L1QPA10
** ON A/C ALL
49VUFUEL/X FEED/VALVE/MOT12QEA12
** ON A/C NOT FOR ALL
121VUFUEL/CTR TK/PUMP2 SPLY30QAP26
121VUFUEL/CTR TK/PUMP1 SPLY29QAP23
** ON A/C NOT FOR ALL
121VUFUEL/RFL/DFL/SPLY2QUL24
121VUFUEL/RFL/DFL/XFR/DEFUEL/VALVE1QUL23
** ON A/C ALL
121VUFUEL/L WING TK/PUMP2 SPLY7QAN26
121VUFUEL/L WING TK/PUMP1 SPLY1QAN23
121VUFUEL/R WING TK/PUMP2 SPLY8QAQ26
121VUFUEL/R WING TK/PUMP1 SPLY2QAQ23
** ON A/C NOT FOR ALL
121VUFUEL/RFL/DFL/SPLY2QUL23
121VUFUEL/RFL/DFL/XFR/DEFUEL/VALVE1QUL22
Subtask 57-27-11-860-059-A ** ON A/C NOT FOR ALL
E. Aircraft Maintenance Configuration
   (1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
   (2) Refuel the wing tanks to the high level cut-off or to the quantity shown in the table as follows (Ref. AMM TASK 12-11-28-650-003):
Access Panel Identification
Fuel Quantity
540AB(640AB)
1500kg(3307lb)
540BB(640BB)
3100kg(6834lb)
540CB(640CB)
4300kg(9480lb)
540DB(640DB)
4700kg(10362lb)
540EB(640EB)
5100kg(11244lb)
540FB(640FB)
5500kg(12125lb)
540GB(640GB)
5700kg(12566lb)
Subtask 57-27-11-860-059-B ** ON A/C NOT FOR ALL
E. Aircraft Maintenance Configuration
   (1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
   (2) Refuel the wing tanks to the high level cut-off or to the quantity shown in the table as follows: (Ref. AMM TASK 12-11-28-650-003):
Access Panel Identification
Fuel Quantity
540AB(640AB)
800kg(1764lb)
540BB(640BB)
2400kg(5291lb)
540CB(640CB)
3600kg(7937lb)
540DB(640DB)
4000kg(8819lb)
540EB(640EB)
4400kg(9700lb)
540FB(640FB)
4800kg(10582lb)
540GB(640GB)
5000kg(11023lb)
Subtask 57-27-11-790-050-A
F. Test
   (1) Do a status report (BITE) of the fuel quantity indicating system (Ref. AMM TASK 28-42-00-740-001).
   (2) Do a functional (BITE) test of the fuel quantity sensors (Ref. AMM TASK 28-46-00-740-001).
   (3) Examine the access panel you have installed for leaks.
Subtask 57-27-11-790-058-A
G. Leak Test
   (1) Do the leak test of the fuel tanks (Ref. AMM TASK 28-11-00-790-009).
NOTE: This leak test is an alternative to the leak test from paragraph F.
5. Close-up
Subtask 57-27-11-410-050-A ** ON A/C NOT FOR ALL
A. Close Access
   (1) Install the forward and aft fixed fairings of flap track No. 3 (Ref. AMM TASK 57-55-11-400-001):
Subtask 57-27-11-410-050-B ** ON A/C NOT FOR ALL
A. Close Access
   (1) Install the forward and aft fixed fairings of flap track No. 3 (Ref. AMM TASK 57-55-11-400-004):
Subtask 57-27-11-960-050-A ** ON A/C NOT FOR ALL
B. Aircraft Maintenance Configuration
   (1) If you have done a fuel tank repair and there is a risk of unwanted material remaining in the tank:
     (a) Start the engine and let it operate to flush the contamination from the fuel tank (Ref. AMM TASK 71-00-00-710-003) or (Ref. AMM TASK 71-00-00-710-004).
     (b) Replace the fuel filter (Ref. AMM TASK 73-11-10-920-001) at scheduled intervals, refer to (Ref. MPD 730000-C4-1) for scheduled replacement intervals.
   (2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
Subtask 57-27-11-960-050-B ** ON A/C NOT FOR ALL
B. Aircraft Maintenance Configuration
   (1) If you have done a fuel tank repair and there is a risk of unwanted material remaining in the tank:
     (a) Start the engine and let it operate to flush the contamination from the fuel tank (Ref. AMM TASK 71-00-00-710-043) or (Ref. AMM TASK 71-00-00-710-047).
     (b) Replace the fuel filter (Ref. AMM TASK 73-12-42-920-010) at scheduled intervals, refer to (Ref. MPD 731000-I1-1) for scheduled replacement intervals.
NOTE: For aircraft operating to the standards for ETOPS, refer also to the latest revision of the CMP 28-2-0000-002 for additional requirements (Ref. MPD 282100-03-1).
   (2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
Subtask 57-27-11-960-050-C ** ON A/C NOT FOR ALL
B. Aircraft Maintenance Configuration
   (1) If you have done a fuel tank repair and there is a risk of unwanted material remaining in the tank:
     (a) Start the engine and let it operate to flush the contamination from the fuel tank (Ref. AMM TASK 71-00-00-710-003) or (Ref. AMM TASK 71-00-00-710-004).
     (b) Replace the fuel filter (Ref. AMM TASK 73-11-10-920-001) at scheduled intervals, Refer to (Ref. MPD 730000-C4-1) for scheduled replacement intervals.
   (2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
Subtask 57-27-11-960-050-F ** ON A/C NOT FOR ALL
B. Aircraft Maintenance Configuration
   (1) If you did a fuel tank repair and there is a risk of unwanted material remaining in the tank, do the steps that follow:
     (a) Start the engine and let it operate to flush the contamination from the fuel tank (Ref. AMM TASK 71-00-00-860-823) or (Ref. AMM TASK 71-00-00-860-822).
     (b) If necessary, replace the fuel filter cartridge (Ref. AMM TASK 73-11-06-000-801) and (Ref. AMM TASK 73-11-06-400-801).
NOTE: Airbus recommends to replace the fuel filter cartridge at 500FH and 1500FH after delivery, after you do work on the tank or as described in (Ref. AMM TASK 73-11-06-000-801) and (Ref. AMM TASK 73-11-06-400-801).
   (2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
Subtask 57-27-11-942-055-A
C. Removal of Equipment
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Remove the safety barriers.
   (3) Remove the access platform(s).
   (4) Remove the 98D27803500001 LOCKING TOOL ZERO POS from the flap/slat control lever.
   (5) Remove the WARNING NOTICE(S).
   (6) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
[Rev.10 from 2021] 2026.04.01 03:54:11 UTC
"Aviabrain" 2025