AMM A320F | Leak Test of the Wing Tanks and the Center Tank - Without Fuel

REFERENCE	QTY	DESIGNATION
No specific	AR	ACCESS PLATFORM 6M (20 FT)
No specific	AR	SAFETY BARRIER(S)
No specific	AR	WARNING NOTICE(S)
98D27803000000	1	LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION
DETHEBP	2	HELITEST
TPS300K	2	TANK PRESSURIZATION SYSTEM
TPSAICPA320	2	AIRBUS A320 INTERFACES KIT

ZONE/ACCESS	ZONE DESCRIPTION
140	CENTER WING
540	FUEL TANK
550	VENT SURGE TANK
640	FUEL TANK
650	VENT SURGE TANK

REFERENCE	DESIGNATION
TASK 12-11-28-650-003-A	Pressure Refuel with Automatic Control
TASK 12-34-24-869-001-A	Aircraft Bonding and Grounding (Earthing) for the Refuel/Defuel or Oxygen Servicing Operations
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 27-50-00-866-008-A	Extension of the Flaps on the Ground
TASK 27-50-00-866-008-A-01	Extension of the Flaps/Slats on the Ground
TASK 27-50-00-866-009-A	Retraction of the Flaps on the Ground
TASK 27-50-00-866-009-A-01	Retraction of the Flaps/Slats on the Ground
TASK 27-80-00-866-004-A	Extending the Slats on the Ground
TASK 27-80-00-866-005-A	Retracting the Slats on the Ground
TASK 28-10-00-910-001-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 28-12-41-200-003-A	Inspection of the Overpressure Protector
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 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 51-76-12-300-001-A	Local Repair of the Fuel Tank Sealant
TASK 57-27-11-400-001-A	Installation of the Access Panel
TASK 57-27-11-400-002-A	Installation of the Access Panel
Helium Mapping Kit - Left Wing Tank and Center Tank - Connections
Helium Mapping Kit - Right Wing Tank - Connections

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).
(2) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the flight controls.
(3) Put the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION on the slat/flap control lever.
(4) Put the SAFETY BARRIER(S) in position.

B. Aircraft Maintenance Configuration
(1) Make sure that the aircraft is grounded (earthed) correctly (Ref. AMM TASK 12-34-24-869-001).
(2) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(3) In the cockpit:
(a) On the panel 25VU, make sure that the APU MASTER SW P/BSW is in the off position (the ON legend is off).
(b) On the panel 115VU, make sure that the ENG/MASTER 1 and ENG/MASTER 2 switches are in the OFF position.
(c) On the panel 40VU, make sure that the X FEED P/BSW is released (the ON legend is off).
(4) Do the EIS start procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001), then:

On the ECAM control panel (CP), push (in) the FUEL P/BSW
Make sure that the FUEL page shows on the ECAM lower display unit (DU).

(5) On the ECAM lower DU, make sure that:

The engine LP valves are shown closed (amber cross-line)
The APU LP valve shows closed (green crossed line)
The X FEED valve shows closed (green crossed line).

(6) On the refuel/defuel panel 800VU, make sure that:

The MODE SELECT switch is in the OFF and guarded position
All the REFUEL VALVE switches are in the SHUT position.

(7) Defuel the applicable fuel tank(s) (Ref. AMM TASK 28-25-00-650-001).
(8) Drain the remaining fuel from the applicable fuel tank(s) (Ref. AMM TASK 28-25-00-650-003).
(9) Fully extend the flaps and the slats (Ref. AMM TASK 27-50-00-866-008) and (Ref. AMM TASK 27-80-00-866-004).
(10) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is installed on the slat/flap control lever.
(11) Make sure that the applicable overpressure protector on each NACA inlet is serviceable (Ref. AMM TASK 28-12-41-200-003).
(12) Make sure that the manhole access panels of all wing tanks are installed correctly (Ref. AMM TASK 57-27-11-400-001) and (Ref. AMM TASK 57-27-11-400-002).
(13) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
(14) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

C. Get Access
(1) Put the ACCESS PLATFORM 6M (20 FT) in position below the applicable access panel.
(2) Remove the applicable access panels.
(a) To get access to the front of the fuel tank, remove the applicable wing leading-edge access-panels.
(b) To get access to the rear of the fuel tank, remove the applicable wing trailing-edge access-panels.
(c) To get access to the center tank, remove the applicable belly fairing access-panel.

CAUTION: MAKE SURE THAT THE MAXIMUM PRESSURE IN THE TANK IS NOT MORE THAN 0.1378 BAR (2.0 PSI). THIS WILL PREVENT DAMAGE TO THE FUEL SYSTEM.

A. Leak Test of the Left Wing Tank and the Center Tank - Without Fuel - Pressurized Air and Helium/Air Procedure

Helium Mapping Kit - Left Wing Tank and Center Tank - Connections ** ON A/C NOT FOR ALL

NOTE: To do the test, use the applicable items from:

The TPS300K TANK PRESSURIZATION SYSTEM
The TPSAICPA320 AIRBUS A320 INTERFACES KIT
The DETHEBP HELITEST.

(1) Connect the compressed air supply to the control unit (4).
(2) Connect the power supply and set the control unit (4) switch to the ON position.
(3) Install the NACA plug holder (3) on the NACA plug (2).
(4) Install the NACA plug (2) on the left-wing NACA inlet.
(5) Make sure that the NACA plug (2) is connected to the control unit (4).
(6) Connect the water drain-valve adapter (1) from the control unit (4) to the water drain valve 25QM.
(7) Do an air leak test as follows:
(a) Operate the control unit (4) to start the air test.

NOTE: The system will automatically increase the pressure to 0.10 bar (1.5 psi).

(b) When the pressure has got to 0.10 bar (1.5 psi), monitor the pressure in the tank(s) for a period of 10 minutes.
(c) If the pressure in the tank(s) decreases to less than 0.09 bar (1.3 psi), find the exit point of the leak.

NOTE: The control unit (4) will keep the air pressure supplied to help to find the exit point of the leak.

(d) Listen around the tank(s) boundaries for any hissing sounds of air pressure leak.
(e) If a hissing sound is heard, repair the leak.
(f) If the pressure in the tank(s) is stable at 0.09 bar (1.3 psi), operate the control unit (4) to depressurize the tank(s).
(g) Make sure that the pressure in the tank(s) is back to atmospheric pressure.
(8) Do the air/helium leak test as follows:
(a) Connect the helium supply to the control unit (4).
(b) Set the control unit (4) to supply the air and the helium to the tank(s).
(c) Operate the control unit (4) to start the test.

NOTE: The system will automatically increase the pressure to 0.10 bar (1.5 psi).

(d) Wait for 10 minutes to let the helium mix with the air in the tank(s). This makes sure that there is approximately 10 percent helium and 90 percent air.
(e) Use the portable helium detector to find the leak point on external surfaces of the tank(s).

NOTE: A fuel leak can move for a long distance in the aircraft structure. Compressed air can be used to remove the helium build up in the area. This will make it easier to find the point of the leak.

(f) Make a mark at each exit point as you find them.

NOTE: This will help you to find them when you do a leak test to find the source of the leak.

NOTE: The exit point of leakage can be at a long distance from the source of the leak.

NOTE: Air/helium can leak through the system valves and effect the test results.

(g) Operate the control unit (4) to depressurize the tank(s).
(h) Make sure that the pressure in the tank(s) is fully released before you continue.
(i) Get access to the applicable fuel tank(s) (Ref. AMM TASK 28-10-00-910-002).
1 Make sure that the remaining helium content in the tank(s) is fully removed, to prevent the background signal.
(j) Do a leak test at each of the exit points where you made a mark (Ref. AMM TASK 28-11-00-790-009).
(k) At source of each leak:
1 Do the necessary repair procedure (Ref. AMM TASK 51-76-12-300-001).
2 Do the step (8) again to make sure that the leak is repaired.
(9) Remove the NACA plug (2) from the left-wing NACA inlet.
(10) Remove the NACA plug holder (3) from the NACA plug (2).
(11) Remove the water drain-valve adapter (1) from the water drain valve 25QM.
(12) Disconnect the compressed air supply and the helium supply from the control unit (4).

CAUTION: MAKE SURE THAT THE MAXIMUM PRESSURE IN THE TANK IS NOT MORE THAN 0.1378 BAR (2.0 PSI). THIS WILL PREVENT DAMAGE TO THE FUEL SYSTEM.

B. Leak Test of the Right Wing Tank - Without Fuel - Pressurized Air and Helium/Air Procedure

Helium Mapping Kit - Right Wing Tank - Connections ** ON A/C NOT FOR ALL

NOTE: To do the test, use the applicable items from:

The TPS300K TANK PRESSURIZATION SYSTEM
The TPSAICPA320 AIRBUS A320 INTERFACES KIT
The DETHEBP HELITEST.

(1) Connect the compressed air supply to the control unit (2).
(2) Connect the power supply and set the control unit (2) switch to the ON position.
(3) Install the NACA plug holder (3) on the NACA plug (4).
(4) Install the NACA plug (4) on the right-wing NACA inlet.
(5) Make sure that the NACA plug (4) is connected to the control unit (2).
(6) Connect the water drain-valve adapter (1) from the control unit (2) to the water drain valve 26QM.
(7) Do an air leak test as follows:
(a) Operate the control unit (2) to start the air test.

NOTE: The system will automatically increase the pressure to 0.10 bar (1.5 psi).

(b) When the pressure has got to 0.10 bar (1.5 psi), monitor the pressure in the tank for a period of 10 minutes.
(c) If the pressure in the tank decreases to less than 0.09 bar (1.3 psi), find the exit point of the leak.

NOTE: The control unit (2) will keep the air pressure supplied to help to find the exit point of the leak.

(d) Listen around the tank boundaries for any hissing sounds of air pressure leak.
(e) If a hissing sound is heard, repair the leak.
(f) If the pressure in the tank is stable at 0.09 bar (1.3 psi), operate the control unit (2) to depressurize the tank.
(g) Make sure that the pressure in the tank is back to atmospheric pressure.
(8) Do the air/helium leak test as follows:
(a) Connect the helium supply to the control unit (2).
(b) Set the control unit (2) to supply the air and the helium to the tank.
(c) Operate the control unit (2) to start the test.

NOTE: The system will automatically increase the pressure to 0.10 bar (1.5 psi).

(d) Wait for 10 minutes to let the helium mix with the air in the tank. This makes sure that there is approximately 10 percent helium and 90 percent air.
(e) Use the portable helium detector to find the leak point on external surfaces of the tank.

NOTE: A fuel leak can move for a long distance in the aircraft structure. Compressed air can be used to remove the helium build up in the area. This will make it easier to find the point of the leak.

(f) Make a mark at each exit point as you find them.

NOTE: This will help you to find them when you do a leak test to find the source of the leak.

NOTE: The exit point of leakage can be a long distance from the source of the leak.

NOTE: Air/helium can leak through the system valves and effect the test results.

(g) Operate the control unit (2) to depressurize the tank.
(h) Make sure that the pressure in the tank is fully released before you continue.
(i) Get access to the applicable fuel tank(s) (Ref. AMM TASK 28-10-00-910-002).
1 Make sure that the remaining helium content in the tank is fully removed, to prevent the background signal.
(j) Do a leak test at each of the exit points where you made a mark (Ref. AMM TASK 28-11-00-790-009).
(k) At source of each leak:
1 Do the necessary repair procedure (Ref. AMM TASK 51-76-12-300-001).
2 Do the step (8) again to make sure that the leak is repaired.
(9) Remove the NACA plug (4) from the right-wing NACA inlet.
(10) Remove the NACA plug holder (3) from the NACA plug (4).
(11) Remove the water drain-valve adapter (1) from the water drain valve 26QM.
(12) Disconnect the compressed air supply and the helium supply from the control unit (2).

CAUTION: MAKE SURE THAT THE MAXIMUM PRESSURE IN THE TANK IS NOT MORE THAN 0.1378 BAR (2.0 PSI). THIS WILL PREVENT DAMAGE TO THE FUEL SYSTEM.

C. Leak Test of the Left Wing Tank and the Center Tank - Without Fuel - Pressurized Air and Helium/Air Procedure

Helium Mapping Kit - Left Wing Tank and Center Tank - Connections ** ON A/C NOT FOR ALL

NOTE: To do the test, use the applicable items from:

The TPS300K TANK PRESSURIZATION SYSTEM
The TPSAICPA320 AIRBUS A320 INTERFACES KIT
The DETHEBP HELITEST.