W DOC AIRBUS | AMM A320F

Pressure Test of the Wing-Tank Vent System

TASK 28-12-00-730-801-A
Pressure Test of the Wing-Tank Vent System

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.
WARNING: MAKE SURE THAT YOU HAVE THE CORRECT FIRE FIGHTING EQUIPMENT AVAILABLE.
ZONE: 540
ZONE: 550
ZONE: 640
ZONE: 650
1. Reason for the Job
Self explanatory
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
1
ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE
No specific
1
AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY
No specific
AR
SAFETY BARRIER(S)
No specific
1
SPATULA - NON METALLIC
No specific
AR
WARNING NOTICE(S)
No specific
AR
WATER - SOAPY SOLUTION
No specific
Torque wrench: range to between 0.13 and 0.11 m.daN (11.50 and 9.73 lbf.in ) T
No specific
Torque wrench: range to between 0.16 and 0.14 m.daN (14.16 and 12.39 lbf.in ) T
98D28004005000
1
VENT STRINGER LEAK TEST KIT
98D57004014000
2
HOOK-COVER (RIB2-SURGE DOORS)
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.03FAB1)
Mineral Oil base Grease-- Vaseline or Petrolatum -
(Material No.06AAB1)
Polysulfide Sealant-General Purpose Fillet -
(Material No.14CBB1)
Testing Medium-Leak Detection Bubbles -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
540
FUEL TANK
550
VENT SURGE TANK
640
FUEL TANK
650
VENT SURGE TANK
540AB, 540BZ, 640AB, 640BZ
540JB, 640JB
 D. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
9
ORING
AIPC 28-12-05-30-180
9
O-RING
AIPC 28-12-85-22-180
 E. Referenced Information
REFERENCE
DESIGNATION
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 20-21-11-911-001-A
Tightening Torques for Standard Threaded Fasteners
TASK 20-28-00-869-002-A
Table of the Maximum Permitted Resistance-Values
TASK 20-28-00-912-802-A
Electrical Bonding - General Maintenance Procedure
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 28-12-43-000-002-A
Removal of the Vent Float-Valve
TASK 28-12-43-400-002-A
Installation of the Vent Float-Valve
TASK 28-12-44-000-001-A
Removal of the Check Valve
TASK 28-12-44-000-003-A
Removal of the Check Valve
TASK 28-12-44-400-001-A
Installation of the Check Valve
TASK 28-12-44-400-003-A
Installation of the Check Valve
TASK 28-12-47-000-001-A
Removal of the NACA Vent Intake
TASK 28-12-47-400-001-A
Installation of the NACA Vent Intake
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 57-27-11-000-001-A
Removal of the Access Panel
TASK 57-27-11-000-002-A
Removal of the Access Panel
TASK 57-27-11-400-001-A
Installation of the Access Panel
TASK 57-27-11-400-002-A
Installation of the Access Panel
TASK 57-27-12-000-002-A
Removal of the Rib 2 Access Panel 540AZ(640AZ) or 540BZ(640BZ)
TASK 57-27-12-400-002-A
Installation of the Rib 2 Access Panel 540AZ (640AZ) or 540BZ (640BZ)
F Wing-Tank Vent System - Location and Detail ** ON A/C NOT FOR ALL
F Wing-Tank Vent System - Location and Detail ** ON A/C NOT FOR ALL
F Wing-Tank Vent System - Location and Detail ** ON A/C NOT FOR ALL
3. Job Set-up
Subtask 28-12-00-941-063-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 safety procedures when you do work in a fuel tank (Ref. AMM TASK 28-10-00-910-001).
   (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
   (3) In the cockpit (zone 210), put the WARNING NOTICE(S) in position:
  • On the overhead panel, on fuel control-panel 40VU, to tell persons not to operate the fuel system.
  • On the flight controls, to tell persons not to operate the flight controls.
   (4) On refuel/defuel control-panel 800VU, put the WARNING NOTICE(S) in position to tell persons not to refuel the aircraft.
Subtask 28-12-00-860-067-A
B. Aircraft Maintenance Configuration
   (1) Defuel the applicable fuel tanks (Ref. AMM TASK 28-25-00-650-001).
   (2) Drain the remaining fuel from the applicable fuel tanks (Ref. AMM TASK 28-25-00-650-003).
Subtask 28-12-00-010-065-A ** ON A/C NOT FOR ALL
C. Get Access
   (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position below the applicable underwing tank access-panel(s):
     (a) For the left wing:
     (b) For the right wing:
   (2) Remove the applicable underwing tank access-panel(s) (Ref. AMM TASK 28-10-00-910-002), (Ref. AMM TASK 57-27-11-000-001) and (Ref. AMM TASK 57-27-11-000-002).
     (a) For the left wing:
     (b) For the right wing:
   (3) Open the applicable aft fuel-surge door(s) (Ref. AMM TASK 28-10-00-910-002):
     (a) For the left wing:
     (b) For the right wing:
   (4) Install the 98D57004014000 HOOK-COVER (RIB2-SURGE DOORS) to hold the fuel-surge door(s) open.
Subtask 28-12-00-010-065-B ** ON A/C NOT FOR ALL
C. Get Access
   (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position below the applicable underwing tank access-panel(s):
     (a) For the left wing:
     (b) For the right wing:
   (2) Remove the applicable underwing tank access-panel(s) (Ref. AMM TASK 28-10-00-910-002) and (Ref. AMM TASK 57-27-11-000-001):
     (a) For the left wing:
     (b) For the right wing:
   (3) Open the applicable aft fuel-surge door(s) (Ref. AMM TASK 28-10-00-910-002):
     (a) For the left wing:
     (b) For the right wing:
   (4) Install the 98D57004014000 HOOK-COVER (RIB2-SURGE DOORS) to hold the fuel-surge door(s) open.
Subtask 28-12-00-010-065-C ** ON A/C NOT FOR ALL
C. Get Access
   (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position below the applicable underwing tank access panels:
     (a) For the left wing:
     (b) For the right wing:
   (2) Remove the applicable underwing tank access panels (Ref. AMM TASK 28-10-00-910-002):
     (a) For the left wing:
     (b) For the right wing:
   (3) Remove the applicable RIB2 access panels:
     (a) For the left wing:
     (b) For the right wing:
Subtask 28-12-00-010-065-D ** ON A/C NOT FOR ALL
C. Get Access
   (1) Put the ACCESS PLATFORM 5M (16 FT)- ADJUSTABLE in position below the applicable underwing tank access panels:
     (a) For the left wing:
     (b) For the right wing:
   (2) Remove the applicable underwing tank access panels (Ref. AMM TASK 28-10-00-910-002):
     (a) For the left wing:
     (b) For the right wing:
   (3) Remove the applicable RIB2 access panels:
     (a) For the left wing:
     (b) For the right wing:
Subtask 28-12-00-480-050-B ** ON A/C NOT FOR ALL
CAUTION: DO NOT USE THE FUEL PIPES AND THE EQUIPMENT AS HANDHOLDS WHEN YOU DO WORK IN A FUEL TANK. THIS WILL PREVENT DAMAGE TO THEM.
CAUTION: YOU MUST ALWAYS PUT CAPS ON DISCONNECTED FUEL VENT PIPES. IF YOU DO NOT DO THIS, CONTAMINATION OF THE FUEL VENT PIPES CAN OCCUR.
CAUTION: WHEN YOU DO WORK ON OR NEAR FUEL VENT PIPES, BE CAREFUL NOT TO CAUSE DAMAGE TO THEM.
D. Installation of the Adapters and Blanks to the LH (RH) Wing-Tank Vent System
F Wing-Tank Vent System - Location and Detail ** ON A/C NOT FOR ALL
F Wing-Tank Vent System - Location and Detail ** ON A/C NOT FOR ALL
   (1) Use the applicable items from the 98D28004005000 VENT STRINGER LEAK TEST KIT.
   (2) Use a SPATULA - NON METALLIC to remove the sealant from:
  • The nuts (1), (7) and (13)
  • The bolts (14) and (17)
  • The screws (3) and (5).
   (3) Install vent inflation-adapter 98D28004007000 to the connector (8) at RIB 2 as follows:
     (a) Remove the nut (7) and the screw (5) from the pipe (4).
     (b) Move the bonding lead (6) away from the pipe (4).
     (c) Remove the nut (1) and the screw (3) from the pipe (4).
     (d) Move the bonding lead (2) away from the pipe (4).
     (e) Remove the nuts (13) and the bolts (14) from the fairlead (15).
     (f) Remove the fairlead (15) from the bracket (16).
     (g) Remove the bolts (17) from the support bracket (18).
     (h) Remove the pipe (4) from the connector (8).
     (i) Remove and discard the O-ring (9) from the pipe (4).
     (j) Install vent inflation-adapter 98D28004007000 to the connector (8).
     (k) Put the valve on vent inflation-adapter 98D28004007000 in the closed position.
   (4) Install sphincter blank 98D28204004000 to the drain valve (10) at RIB 2 as follows:
     (a) Remove the clamp (11) and the check valve (12) 120QM (121QM) (Ref. AMM TASK 28-12-44-000-003).
     (b) Install sphincter blank 98D28204004000 to the drain valve (10).
   (5) Install test rig air-pressure 98L28004035000 to vent inflation-adapter 98D28004007000 as follows:
     (a) Connect fuel test-hose 98D28204003000 to vent inflation-adapter 98D28004007000.
     (b) Connect fuel test-hose 98D28204003000 to test rig air-pressure 98L28004035000.
     (c) On test rig air-pressure 98L28004035000, make sure that the pressure isolation valve is in the CLOSED position.
     (d) Connect the AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY to test rig air-pressure 98L28004035000.
   (6) Install vent-stringer duct-blank 98D28004009000 to the vent stringer duct at RIB 22:
     (a) Remove the NACA vent intake (Ref. AMM TASK 28-12-47-000-001).
     (b) Install vent-stringer duct-blank 98D28004009000 to the vent stringer duct at RIB 22.
   (7) Install the float-valve blank 98D28004008000 to the adapter (19) at RIB 15 as follows:
     (a) Remove the vent float valve (20) 16QM (17QM) (Ref. AMM TASK 28-12-43-000-002).
     (b) Install float valve-blank 98D28004008000 to the adapter (19).
     (c) Put the valve on float-valve blank 98D28004008000 in the closed position.
   (8) Install sphincter blank 98D28204004000 to the drain valve (23) at RIB 15 as follows:
     (a) Remove the clamp (21) and the check valve (22) 52QM (53QM) (Ref. AMM TASK 28-12-44-000-001).
     (b) Install sphincter blank 98D28204004000 to the drain valve (23).
Subtask 28-12-00-480-050-C ** ON A/C NOT FOR ALL
CAUTION: DO NOT USE THE FUEL PIPES AND THE EQUIPMENT AS HANDHOLDS WHEN YOU DO WORK IN A FUEL TANK. THIS WILL PREVENT DAMAGE TO THEM.
CAUTION: YOU MUST ALWAYS PUT CAPS ON DISCONNECTED FUEL VENT PIPES. IF YOU DO NOT DO THIS, CONTAMINATION OF THE FUEL VENT PIPES CAN OCCUR.
CAUTION: WHEN YOU DO WORK ON OR NEAR FUEL VENT PIPES, BE CAREFUL NOT TO CAUSE DAMAGE TO THEM.
D. Installation of the Adapters and Blanks to the LH (RH) Wing-Tank Vent System
F Wing-Tank Vent System - Location and Detail ** ON A/C NOT FOR ALL
   (1) Use the applicable items from the 98D28004005000 VENT STRINGER LEAK TEST KIT.
   (2) Use a SPATULA - NON METALLIC to remove the sealant from:
  • The nuts (1), (7) and (13)
  • The bolts (14) and (17)
  • The screws (3) and (5).
   (3) Install vent inflation-adapter 98D28004007000 to the connector (8) at RIB 2 as follows:
     (a) Remove the nut (7) and the screw (5) from the pipe (4).
     (b) Move the bonding lead (6) away from the pipe (4).
     (c) Remove the nut (1) and the screw (3) from the pipe (4).
     (d) Move the bonding lead (2) away from the pipe (4).
     (e) Remove the nut (13) and the bolts (14) from the fairlead (15).
     (f) Remove the fairlead (15) from the bracket (16).
     (g) Remove the bolts (17) from the support bracket (18).
     (h) Remove the pipe (4) from the connector (8).
     (i) Remove and discard the O-ring (9) from the pipe (4).
     (j) Install vent inflation-adapter 98D28004007000 to the connector (8).
     (k) Put the valve on vent inflation-adapter 98D28004007000 in the closed position.
   (4) Install sphincter blank 98D28204004000 to the drain valve (10) at RIB 2 as follows:
     (a) Remove the clamp (11) and the check valve (12) 120QM (121QM) (Ref. AMM TASK 28-12-44-000-003).
     (b) Install sphincter blank 98D28204004000 to the drain valve (10).
   (5) Install test rig air-pressure 98L28004035000 to vent inflation-adapter 98D28004007000:
     (a) Connect fuel test-hose 98D28204003000 to vent inflation-adapter 98D28004007000.
     (b) Connect fuel test-hose 98D28204003000 to test rig air-pressure 98L28004035000.
     (c) On test rig air-pressure 98L28004035000, make sure that the pressure isolation valve is in the CLOSED position.
     (d) Connect the AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY to test rig air-pressure 98L28004035000.
   (6) Install vent-stringer duct-blank 98D28004009000 to the vent stringer duct at RIB 22 as follows:
     (a) Remove the NACA vent intake (Ref. AMM TASK 28-12-47-000-001).
     (b) Install vent-stringer duct-blank 98D28004009000 to the vent stringer duct at RIB 22.
4. Procedure
Subtask 28-12-00-730-050-A ** ON A/C NOT FOR ALL
A. Pressure Test of the Wing-Tank Vent System
NOTE: Airbus recommends you to keep the test air pressure less than or equal to 0.69 bar (10 psi).
   (1) Do the free flow air-test as follows:
WARNING: WHEN YOU USE COMPRESSED AIR:
  • USE THE CORRECT PROTECTION (FACE SHIELD OR GOGGLES)
  • DO NOT POINT THE AIRFLOW AT YOURSELF OR OTHER PERSONS.
LOOSE PARTICLES AND/OR HIGH PRESSURE AIR CAN CAUSE INJURY.
     (a) Open the valve on vent inflation-adapter 98D28004007000 at RIB 2 and float-valve blank 98D28004008000 at RIB 15.
     (b) Slowly open the pressure isolation valve on test rig air-pressure 98L28004035000.
     (c) Increase the air pressure until the pressure gage on the vent inflation adapter shows 0.69 bar (10 psi).
     (d) Make sure that there is a free flow of air from float-valve blank 98D28004008000 at RIB 15:
       1 If there is no free flow of air, stop the test and release the air pressure at a rate of not more than 0.07 bar (1 psi)/sec.
       2 Make sure that there is no blockage in the system.
     (e) Slowly close the pressure isolation valve on test rig air-pressure 98L28004035000 until the pressure gage at the vent inflation adapter at RIB 2 shows 0 bar (0 psi).
     (f) Close the valve on float-valve blank 98D28004008000 at RIB 15.
     (g) Remove vent-stringer duct-blank 98D28004009000 from the vent stringer duct at RIB 22.
     (h) Slowly open the pressure isolation valve on test rig air-pressure 98L28004035000.
     (i) Increase the air pressure until the pressure gage on the vent inflation adapter shows 0.69 bar (10 psi).
     (j) Make sure that there is a free flow of air from the vent stringer duct at RIB 22:
       1 If there is no free flow of air, stop the test and release the air pressure at a rate of not more than 0.07 bar (1 psi)/sec.
       2 Make sure that there is no blockage in the system.
   (2) When the free flow air-test is completed satisfactorily:
     (a) Slowly close the pressure isolation valve on test rig air-pressure 98L28004035000 until:
  • The pressure gage on the vent inflation adapter at RIB 2 shows 0 bar (0 psi).
     (b) Install vent-stringer duct-blank 98D28004009000 to the vent stringer duct at RIB 22.
   (3) Do the air pressure test as follows:
     (a) Slowly open the pressure isolation valve on test rig air-pressure 98L28004035000.
     (b) Increase the air pressure until the pressure gage on the vent inflation adapter shows 0.69 bar (10 psi).
     (c) Let the air pressure become stable at 0.69 bar (10 psi) at vent inflation-adapter 98D28004007000.
     (d) Close the valve on vent inflation-adapter 98D28004007000.
     (e) Slowly close the pressure isolation valve on test rig air-pressure 98L28004035000.
     (f) Keep the wing-tank vent pipes pressure at 0.69 bar (10 psi) for a minimum of 15 minutes.
     (g) If there is no pressure drop after 15 minutes, then the test is satisfactory:
       1 Do step (i).
     (h) If there is a pressure drop after 15 minutes, then the test is unsatisfactory.
     (i) Use a WATER - SOAPY SOLUTION or Testing Medium-Leak Detection Bubbles - (Material No.14CBB1) to find the leaks:
       1 Do an approved repair and do the test again.
     (j) When the test is completed satisfactorily, do the steps that follow:
       1 Remove the AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY from test rig air-pressure 98L28004035000.
       2 On test rig air-pressure 98L28004035000, set the pressure isolation valve to OPEN position:
NOTE: The valve is set to the OPEN position to release the air pressure from test rig air-pressure 98L28004035000.
       3 Remove the fuel test-hose 98D28204003000 from test rig air-pressure 98L28004035000 and vent inflation-adapter 98D28004007000.
       4 Slowly open the valve on vent inflation-adapter 98D28004007000:
  • To release the air pressure at a rate of not more than 0.07 bar (1 psi)/second until the pressure gage shows 0 bar (0 psi).
Subtask 28-12-00-730-050-B ** ON A/C NOT FOR ALL
A. Pressure Test of the Wing-Tank Vent System
NOTE: Airbus recommends you to keep the test air pressure less than or equal to 0.69 bar (10 psi).
   (1) Do the free flow air-test as follows:
WARNING: WHEN YOU USE COMPRESSED AIR:
  • USE THE CORRECT PROTECTION (FACE SHIELD OR GOGGLES)
  • DO NOT POINT THE AIRFLOW AT YOURSELF OR OTHER PERSONS.
LOOSE PARTICLES AND/OR HIGH PRESSURE AIR CAN CAUSE INJURY.
     (a) Open the valve on vent inflation-adapter 98D28004007000.
     (b) Remove vent-stringer duct-blank 98D28004009000 from the vent stringer duct at RIB 22.
     (c) Slowly open the pressure isolation valve on test rig air-pressure 98L28004035000.
     (d) Increase the air pressure until the pressure gage on the vent inflation adapter shows 0.69 bar (10 psi).
     (e) Make sure that there is a free flow of air from the vent stringer duct at RIB 22:
       1 If there is no free flow of air, stop the test and release the air pressure at a rate of not more than 0.07 bar (1 psi)/sec.
       2 Make sure that there is no blockage in the system.
   (2) When the free flow air-test is completed satisfactorily:
     (a) Slowly close the pressure isolation valve on test rig air-pressure 98L28004035000 until:
  • The pressure gage on the vent inflation adapter at RIB 2 shows 0 bar (0.00 psi).
     (b) Install the vent-stringer duct-blank 98D28004009000 to the vent stringer duct at RIB 22.
   (3) Do the air pressure test as follows:
     (a) Slowly open the pressure isolation valve on test rig air-pressure 98L28004035000.
     (b) Increase the air pressure until the pressure gage on the vent inflation adapter shows 0.69 bar (10 psi).
     (c) Let the air pressure become stable at 0.69 bar (10 psi) at vent inflation-adapter 98D28004007000.
     (d) Close the valve on vent inflation-adapter 98D28004007000.
     (e) Slowly close the pressure isolation valve on test rig air-pressure 98L28004035000.
     (f) Keep the wing-tank vent pipes pressure at 0.69 bar (10 psi) for a minimum of 15 minutes.
     (g) If there is no pressure drop after 15 minutes, then the test is satisfactory:
       1 Do step (i).
     (h) If there is a pressure drop after 15 minutes, then the test is unsatisfactory.
     (i) Use WATER - SOAPY SOLUTION or Testing Medium-Leak Detection Bubbles - (Material No.14CBB1) to find the leaks:
       1 Do an approved repair and do the test again.
     (j) When the test is completed satisfactorily, do the steps that follow:
       1 Remove the AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY from test rig air-pressure 98L28004035000.
       2 On test rig air-pressure 98L28004035000, set the pressure isolation valve to OPEN position:
  • To release the pressure from the test rig air-pressure 98L28004035000.
NOTE: The valve is set to the OPEN position to release the air pressure from the test rig air-pressure 98L28004035000.
       3 Remove fuel test-hose 98D28204003000 from test rig air-pressure 98L28004035000 and from vent inflation-adapter 98D28004007000.
       4 Slowly open the valve on vent inflation-adapter 98D28004007000:
  • To release the air pressure at a rate of not more than 0.07 bar (1 psi)/second until the pressure gage shows 0 bar (0 psi).
5. Close-up
Subtask 28-12-00-080-050-B ** ON A/C NOT FOR ALL
A. Removal of the Adapters and Blanks from the LH (RH) Wing-Tank Vent System
F Wing-Tank Vent System - Location and Detail ** ON A/C NOT FOR ALL
F Wing-Tank Vent System - Location and Detail ** ON A/C NOT FOR ALL
CAUTION: MAKE SURE THAT ALL THE BLEED/INFLATION ADAPTERS AND BLANKS ARE REMOVED FROM THE FUEL PIPE SYSTEM. IF THE BLANKS ARE NOT REMOVED, DAMAGE WILL OCCUR TO THE AIRCRAFT.
   (1) Preparation of components for installation:
     (a) Do a visual inspection of the component interface and/or the adjacent area.
     (b) Lubricate the new AIPC 28-12-85-22-180 O-RING (9) or AIPC 28-12-05-30-180 ORING (9) with Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) .
   (2) Removal of the vent-stringer duct-blank 98D28004009000 and installation of the NACA vent intake at RIB 22:
     (a) Remove the vent-stringer duct-blank 98D28004009000 from the vent stringer duct at RIB 22.
     (b) Install the NACA vent intake (Ref. AMM TASK 28-12-47-400-001).
   (3) Removal of the sphincter blank 98D28204004000 and installation of the check valve (22) 52QM (53QM) at RIB 15:
     (a) Remove the sphincter blank 98D28204004000 from the drain valve (23).
     (b) Install the check valve (22) 52QM (53QM) and the clamp (21) (Ref. AMM TASK 28-12-44-400-001).
   (4) Removal of the float valve blank 98D28004008000 and installation of the float valve (20) at RIB 15:
     (a) Remove the float valve blank 98D28004008000 from the adapter (19).
     (b) Install the vent float valve (20) 16QM(17QM) (Ref. AMM TASK 28-12-43-400-002).
   (5) Removal of the sphincter blank 98D28204004000 and installation of the check valve (12) 120QM (121QM) at RIB 2:
     (a) Remove the sphincter blank 98D28204004000 from the drain valve (10).
     (b) Install the check valve (12) 120QM (121QM) and the clamp (11) (Ref. AMM TASK 28-12-44-400-003).
   (6) Removal of the vent inflation adapter 98D28004007000 and installation of the pipe (4) at RIB 2:
     (a) Remove the vent inflation adapter 98D28004007000 from the connector (8).
     (b) Install the O-ring (9) on the pipe (4).
     (c) Install the pipe (4) to the connector (8).
     (d) Install the pipe (4) and the fairlead (15) to the bracket (16) with the bolts (14) and the nuts (13).
     (e) TORQUE the nuts (13) to between 0.13 and 0.11 m.daN (11.50 and 9.73 lbf.in ) T.
     (f) Install the pipe (4) to the support bracket (18) with the bolts (17).
     (g) Tighten the bolts (17) (Ref. AMM TASK 20-21-11-911-001).
     (h) Attach the bonding lead (2) to the pipe (4) with the screw (3) and the nut (1) (Ref. AMM TASK 20-28-00-912-802).
     (i) TORQUE the nut (1) to between 0.16 and 0.14 m.daN (14.16 and 12.39 lbf.in ) T.
     (j) Attach the bonding lead (6) to the pipe (4) with the screw (5) and the nut (7) (Ref. AMM TASK 20-28-00-912-802).
     (k) TORQUE the nut (7) to between 0.16 and 0.14 m.daN (14.16 and 12.39 lbf.in ) T.
Subtask 28-12-00-080-050-C ** ON A/C NOT FOR ALL
A. Removal of the Adapters and Blanks from the LH (RH) Wing-Tank Vent System
F Wing-Tank Vent System - Location and Detail ** ON A/C NOT FOR ALL
CAUTION: MAKE SURE THAT ALL THE BLEED/INFLATION ADAPTERS AND BLANKS ARE REMOVED FROM THE FUEL PIPE SYSTEM. IF THE BLANKS ARE NOT REMOVED, DAMAGE WILL OCCUR TO THE AIRCRAFT.
   (1) Preparation of components for installation:
     (a) Do a visual inspection of the component interface and/or the adjacent area.
     (b) Lubricate the new AIPC 28-12-85-22-180 O-RING (9) or AIPC 28-12-05-30-180 ORING (9) with Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) .
   (2) Removal of the vent stringer duct blank 98D28004009000 and installation of the NACA vent intake at RIB 22:
     (a) Remove the vent stringer duct blank 98D28004009000 from the vent stringer duct at RIB 22.
     (b) Install the NACA vent intake (Ref. AMM TASK 28-12-47-400-001).
   (3) Removal of the sphincter blank 98D28204004000 and installation of the check valve (12) 120QM (121QM) at RIB 2:
     (a) Remove the sphincter blank 98D28204004000 from the drain valve (10).
     (b) Install the check valve (12) 120QM (121QM) and the clamp (11) (Ref. AMM TASK 28-12-44-400-003).
   (4) Removal of the vent inflation adapter 98D28004007000 and installation of the pipe (4) at RIB 2:
     (a) Remove the vent inflation adapter 98D28004007000 from the connector (8).
     (b) Install the O-ring (9) on the pipe (4).
     (c) Install the pipe (4) to the connector (8).
     (d) Install the pipe (4) and the fairlead (15) to the bracket (16) with the bolts (14) and the nuts (13).
     (e) TORQUE the nuts (13) to between 0.13 and 0.11 m.daN (11.50 and 9.73 lbf.in ) T.
     (f) Install the pipe (4) to the support bracket (18) with the bolts (17).
     (g) Tighten the bolts (17) (Ref. AMM TASK 20-21-11-911-001).
     (h) Attach the bonding lead (2) to the pipe (4) with the screw (3) and the nut (1) (Ref. AMM TASK 20-28-00-912-802).
     (i) TORQUE the nut (1) to between 0.16 and 0.14 m.daN (14.16 and 12.39 lbf.in ) T.
     (j) Attach the bonding lead (6) to the pipe (4) with the screw (5) and the nut (7) (Ref. AMM TASK 20-28-00-912-802).
     (k) TORQUE the nut (7) to between 0.16 and 0.14 m.daN (14.16 and 12.39 lbf.in ) T.
Subtask 28-12-00-760-050-B
B. Electrical Bonding Test
   (1) Do the electrical bonding test on the wing-tank vent pipe system (Ref. AMM TASK 20-28-00-912-802) and (Ref. AMM TASK 20-28-00-869-002).
   (2) Use a SPATULA - NON METALLIC to apply a layer of the Polysulfide Sealant-General Purpose Fillet - (Material No.06AAB1) to:
  • The nuts (1), (7) and (13)
  • The bolts (14) and (17)
  • The screws (3) and (5).
Subtask 28-12-00-410-063-A ** ON A/C NOT FOR ALL
C. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) To close the applicable aft fuel-surge door(s):
     (a) Remove the 98D57004014000 HOOK-COVER (RIB2-SURGE DOORS) and close the aft fuel-surge door(s):
       1 For the left wing:
       2 For the right wing:
   (3) Install the applicable underwing tank access-panel(s) (Ref. AMM TASK 57-27-11-400-001) and (Ref. AMM TASK 57-27-11-400-002):
     (a) For the left wing:
     (b) For the right wing:
Subtask 28-12-00-410-063-B ** ON A/C NOT FOR ALL
C. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) To close the applicable aft fuel-surge door(s):
     (a) Remove the 98D57004014000 HOOK-COVER (RIB2-SURGE DOORS) and close the aft fuel-surge door(s):
       1 For the left wing:
       2 For the right wing:
   (3) Install the applicable underwing tank access-panel(s) (Ref. AMM TASK 57-27-11-400-001):
     (a) For the left wing:
     (b) For the right wing:
Subtask 28-12-00-410-063-C ** ON A/C NOT FOR ALL
C. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Install the applicable RIB2 access panels:
     (a) For the left wing:
     (b) For the right wing:
   (3) Install the applicable underwing tank access panels:
     (a) For the left wing:
     (b) For the right wing:
Subtask 28-12-00-410-063-D ** ON A/C NOT FOR ALL
C. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Install the applicable RIB2 access panels:
     (a) For the left wing:
     (b) For the right wing:
   (3) Install the applicable underwing tank access panels:
     (a) For the left wing:
     (b) For the right wing:
Subtask 28-12-00-650-060-A
D. Refuel
   (1) Refuel the applicable wing tanks (Ref. AMM TASK 12-11-28-650-003) or (Ref. AMM TASK 12-11-28-650-004).
Subtask 28-12-00-942-066-A
E. Removal of Equipment
   (1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
   (2) Remove the access platform(s).
   (3) Remove the WARNING NOTICE(S).
   (4) Remove the SAFETY BARRIERS.
[Rev.10 from 2021] 2026.04.02 07:01:21 UTC
"WTRUIB" 2025