DOC AIRBUS | TSM A320FRefuel - Fuel Spillage From NACA Vent During Refuel
TASK 28-25-00-810-816-A
Refuel - Fuel Spillage From NACA Vent During Refuel
A. Referenced Information
3. Fault Confirmation
Subtask 28-25-00-710-065-B ** ON A/C NOT FOR ALL
Subtask 28-25-00-810-067-B ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:28:46 UTC
Refuel - Fuel Spillage From NACA Vent During Refuel
WARNING:
OBEY THE FUEL SAFETY PROCEDURES.
CAUTION:
DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM SAFE PRESSURE OF 50psi (3.45bar).
1. Possible CausesFLSS high level channel(s) the incoming fuel pressure is more than 55psi (3.79bar) a fuel tank (one or more) becomes full and the fuel flow, refuel or transfer (in), is not stopped - VALVE-REFUEL, CTR TK [10QU]
- VALVE-REFUEL, R WING TK [8QU]
- VALVE-REFUEL, L WING TK [7QU]
- VALVE-DEFUEL/TRANSFER [11QM]
P/BSW-FUEL/CTR TK/MODE SELECT/AUTO (4QL) - SENSOR-FULL LVL, L WNG TK INR 1 CHANNEL B [23QJ1]
- SENSOR-FULL LVL, R WNG TK INR 1 CHANNEL B [23QJ2]
- SENSOR-FULL LVL, L WNG TK INR 2 CHANNEL B [27QJ1]
- SENSOR-FULL LVL, R WNG TK INR 2 CHANNEL B [27QJ2]
- VALVE-REFUEL, ACT [41QU]
- VALVE-FUEL TRANSFER, ACT [165QM]
- ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH]
- VALVE-FUEL INLET, ACT1 [166QM1]
- VALVE-FUEL INLET, ACT2 [166QM2]
- ACTUATOR-FUEL INLET VALVE, ACT1 [5QH1]
- ACTUATOR-FUEL INLET VALVE, ACT2 [5QH2]
- VALVE-FLOAT VENT, L WING TK OUTR [15QM]
- VALVE-FLOAT VENT, R WING TK OUTR [18QM]
- VALVE-FLOAT VENT, L WING TK INR [16QM]
- VALVE-FLOAT VENT, R WING TK INR [17QM]
Obstruction (blockage) - Overpressure Protector
- Refuel System
- Defuel System
- Crossfeed Valve
vent/surge tank scavenge system - jet adaptor assembly
- JET PUMP-WATER SCAVENGE, L VENT SURGE TK or JET PUMP-WATER SCAVENGE, L VENT SURGE TK [66QM]
- JET PUMP-WATER SCAVENGE, R VENT SURGE TK or JET PUMP-WATER SCAVENGE, R VENT SURGE TK [69QM]
- CHECK VALVE-FUEL PUMP, L VENT SURGE TK [37QM]
- CHECK VALVE-FUEL PUMP, R VENT SURGE TK [38QM]
- fuel-pump suction valve
engine fuel feed line, Air Release Valve - VALVE-FLOAT VENT, LEFT WING [212QM]
- VALVE-FLOAT VENT, RIGHT WING [213QM]
- CLACK VALVE [214QM]
- CLACK VALVE [216QM]
- CLACK VALVE [215QM]
- CLACK VALVE [217QM]
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| TSM TASK 28-21-00-810-825-A | Internal Fuel Leak Which Causes a Fuel Imbalance or a Discharge From a NACA Vent During Taxi or Flight |
| TSM TASK 28-26-00-810-804-A | Fuel, Main Transfer System - Control Valve 1 (Left) Does Not Close |
| TSM TASK 28-26-00-810-805-A | Fuel, Main Transfer System - Control Valve 2 (Right) Does Not Close |
| AMM 12-11-28-650-003 | Pressure Refuel with Automatic Control |
| AMM 12-11-28-650-004 | Pressure Refuel with Manual Control |
| AMM 12-11-28-650-005 | Pressure Refuel without Electrical Power |
| AMM 12-11-28-650-006 | Overwing (Gravity) Refuel |
| AMM 28-00-00-000-001 | Removal of the Fuel Pipes |
| AMM 28-00-00-400-001 | Installation of the Fuel Pipes |
| AMM 28-11-42-000-002 | Removal of the Clack Valve |
| AMM 28-11-42-400-002 | Installation of the Clack Valve |
| AMM 28-12-00-200-001 | Inspection of the Tank Venting System |
| AMM 28-12-41-200-002 | Inspection of the Overpressure Protector |
| AMM 28-12-41-200-003 | Inspection of the Overpressure Protector |
| AMM 28-12-43-000-001 | Removal of the Vent Float-Valve |
| AMM 28-12-43-000-002 | Removal of the Vent Float-Valve |
| AMM 28-12-43-000-003 | Removal of the Float Vent Valve |
| AMM 28-12-43-400-001 | Installation of the Vent Float-Valve |
| AMM 28-12-43-400-002 | Installation of the Vent Float-Valve |
| AMM 28-12-43-400-003 | Installation of the Float Vent Valve |
| AMM 28-12-47-200-001 | Visual Check of NACA Intake for Signs of Blockage |
| AMM 28-21-41-000-001 | Removal of the Low Pressure (LP) Air-Release-Valve 86QM(87QM) |
| AMM 28-21-41-400-001 | Installation of the Low Pressure (LP) Air-Release-Valve 86QM(87QM) |
| AMM 28-21-42-000-001 | Removal of the Fuel-Pump Suction Valve |
| AMM 28-21-42-400-001 | Installation of the Fuel-Pump Suction Valve |
| AMM 28-21-43-000-003 | Removal of the Fuel-Pump Check-Valve |
| AMM 28-21-43-400-003 | Installation of the Fuel-Pump Check-Valve |
| AMM 28-21-53-000-001 | Removal of the Jet Pump |
| AMM 28-21-53-000-003 | Removal of the Jet Adaptor Assembly |
| AMM 28-21-53-400-001 | Installation of the Jet Pump |
| AMM 28-21-53-400-003 | Installation of the Jet Adaptor Assembly |
| AMM 28-23-00-720-001 | Operational Test of Crossfeed Valve Using Individual Motors: ... |
| AMM 28-25-00-650-003 | To Drain Remaining Fuel from the Wing Tanks and the Center Tank |
| AMM 28-25-00-710-002 | Operational Test of the Defuel System |
| AMM 28-25-00-710-003 | Operational Test of the Refuel System |
| AMM 28-25-00-869-001 | Fuel Transfer |
| AMM 28-25-43-000-001 | Removal of the Defuel/Transfer Valve |
| AMM 28-25-43-400-001 | Installation of the Defuel/Transfer Valve |
| AMM 28-25-51-000-001 | Removal of the Refuel Valve |
| AMM 28-25-51-000-002 | Removal of the Refuel Valve |
| AMM 28-25-51-000-004 | Removal of the Refuel Valve |
| AMM 28-25-51-400-001 | Installation of the Refuel Valve |
| AMM 28-25-51-400-002 | Installation of the Refuel Valve |
| AMM 28-25-51-400-004 | Installation of the Refuel Valve |
| AMM 28-26-00-710-001 | Operational Test of the Main Transfer System |
| AMM 28-28-00-710-002 | Operational Check of the Individual Motors of the Transfer Valve |
| AMM 28-28-33-000-001 | Removal of the ACT Fuel Transfer-Valve |
| AMM 28-28-33-400-001 | Installation of the ACT Fuel Transfer-Valve |
| AMM 28-28-34-000-001 | Removal of the ACT Fuel Inlet Valve (166QM) |
| AMM 28-28-34-400-001 | Installation of the ACT Fuel Inlet Valve (166QM) |
| AMM 28-28-53-000-001 | Removal of the ACT Transfer-Valve Actuator |
| AMM 28-28-53-400-001 | Installation of the ACT Transfer-Valve Actuator |
| AMM 28-28-54-000-001 | Removal of the ACT Fuel Inlet Valve Actuator (5QH) |
| AMM 28-28-54-400-001 | Installation of the ACT Fuel Inlet Valve Actuator (5QH) |
| AMM 28-46-00-710-001 | Test of the Tank High-Level Sensing-System |
| AMM 28-46-00-740-001 | Functional (BITE) Test |
Fuel Spillage Refuel sheet A318/319/320.Subtask 28-25-00-710-065-B ** ON A/C NOT FOR ALL
A. General (synopsis of refuel system description and operation)
There are four different types of refuel procedures, these are as follows:
Refueling is usually automatic, the required fuel load is set on the preselector at the refuel panel (800VU).
A fuel gallery connects the refuel coupling to the refuel valve of each tank. The refuel valves are used to control the fuel flow into the tanks in three types of refuel (procedures) and are as follows:
The fuel flow in the Overwing method is controlled by the delivery system (fuel tanker or pump unit).
During an automatic refuel, when all the refuel valve control switches are set to NORMAL, the Fuel Quantity Indicating Computer (FQIC) controls the refuel valves. Each refuel valve is closed when the actual fuel load for its related tank equals an amount, computed by the FQIC, that is related to the preselected fuel quantity. Fuel is supplied to all tanks at the same time. This is to keep the refuel time to a minimum. The fuel is loaded in the order that follows:
Left and right wing tank outer cells, which when full, overflow into the related inner cell through a spill pipe.
Center tank (if the preselected fuel load is more than the two wing tank capacities).
During a Manual Pressure Refuel each refuel valve is closed, by one of the ground (refuel) crew, when its refuel valve control switch is set to SHUT.
During the automatic and manual pressure refuel procedures the Fuel Level Sensing System (FLSS) high level channels prevent an overfill and possible spillage.
The FLSS high level channels are automatically switched on (to standby) when the refuel panel door is open (or cockpit refuel is set to on). If the incoming fuel reaches the level of a high level sensor and the sensor becomes wet it will automatically close (de-energize) the refuel valve of the related tank.
If the FQIC (when in automatic refuel) or the ground crew (when in manual refuel) fail to to close the refuel valve(s) the applicableFLSS high level channel(s) will operate to prevent a fuel spillage before the related fuel tank becomes (completely) full.
Ifthe incoming fuel pressure is more than 55psi (3.79bar) , a refuel valve can remain (partially) open due to the excessive fuel pressure (even when it is commanded to close). The command to close will come from:
The refuel valve will close automatically:
A fuel spill can be caused whena fuel tank (one or more) becomes full and the fuel flow, refuel or transfer (in), is not stopped . The continuing fuel overflow will then start to go out through the applicable tank(s) vent system. A refuel overflow from the center tank will normally flow to (both) the left and right sides. The escape routing of the center tank overflow fuel is through the center tank:
A jet pump scavenge system, powered by fuel pressure supplied by the related wing tank fuel pumps, is used to transfer fuel from the surge tank to the wing tank outer cell. When the intercell transfer valves are closed and the fuel level in the outer cell reaches the level of the spill pipe, gravity will cause the fuel to flow through the spill pipe into the wing tank inner cell.
A transfer valve is installed between the engine fuel feed line and the refuel gallery. When open this lets the fuel pumps:
Subtask 28-25-00-710-070-A ** ON A/C NOT FOR ALL There are four different types of refuel procedures, these are as follows:
- Automatic Pressure
- Manual Pressure (with electric power)
- Manual Pressure (without electric power)
- Manual Overwing, (gravity and without electric power).
Refueling is usually automatic, the required fuel load is set on the preselector at the refuel panel (800VU).
A fuel gallery connects the refuel coupling to the refuel valve of each tank. The refuel valves are used to control the fuel flow into the tanks in three types of refuel (procedures) and are as follows:
- Automatic Pressure
- Manual Pressure (with electric power)
- Manual Pressure (without electric power).
The fuel flow in the Overwing method is controlled by the delivery system (fuel tanker or pump unit).
During an automatic refuel, when all the refuel valve control switches are set to NORMAL, the Fuel Quantity Indicating Computer (FQIC) controls the refuel valves. Each refuel valve is closed when the actual fuel load for its related tank equals an amount, computed by the FQIC, that is related to the preselected fuel quantity. Fuel is supplied to all tanks at the same time. This is to keep the refuel time to a minimum. The fuel is loaded in the order that follows:
Left and right wing tank outer cells, which when full, overflow into the related inner cell through a spill pipe.
Center tank (if the preselected fuel load is more than the two wing tank capacities).
During a Manual Pressure Refuel each refuel valve is closed, by one of the ground (refuel) crew, when its refuel valve control switch is set to SHUT.
During the automatic and manual pressure refuel procedures the Fuel Level Sensing System (FLSS) high level channels prevent an overfill and possible spillage.
The FLSS high level channels are automatically switched on (to standby) when the refuel panel door is open (or cockpit refuel is set to on). If the incoming fuel reaches the level of a high level sensor and the sensor becomes wet it will automatically close (de-energize) the refuel valve of the related tank.
If the FQIC (when in automatic refuel) or the ground crew (when in manual refuel) fail to to close the refuel valve(s) the applicable
If
- the FQIC in automatic refuel
- the applicable REFUEL VALVES selector switch when set to SHUT in a manual refuel.
The refuel valve will close automatically:
- if the pressure of the fuel is reduced to less than 50psi (3.45bar)
- the refuel supply is shut-off.
A fuel spill can be caused when
- vent pipe to the left wing surge tank.
- pressure relief vale to the right wing tank.
A jet pump scavenge system, powered by fuel pressure supplied by the related wing tank fuel pumps, is used to transfer fuel from the surge tank to the wing tank outer cell. When the intercell transfer valves are closed and the fuel level in the outer cell reaches the level of the spill pipe, gravity will cause the fuel to flow through the spill pipe into the wing tank inner cell.
A transfer valve is installed between the engine fuel feed line and the refuel gallery. When open this lets the fuel pumps:
- transfer fuel from one tank to another
- defuel the aircraft through the refuel coupling.
B. Identification of the cause of the spill
(1) Complete the Fuel Spill Reporting Sheet
(a) Record the aircraft configuration when fuel spill occurs as follows:
Subtask 28-25-00-710-065-D ** ON A/C NOT FOR ALL (1) Complete the Fuel Spill Reporting Sheet
(a) Record the aircraft configuration when fuel spill occurs as follows:
- Fuel loads
- Fuel Distribution
- Fuel Pump configuration
- Fuel Tank Hi level sensor state.
NOTE: Record the data accurately for easier trouble shooting.
(b) Use the data recorded to help you trouble shoot the procedure and refer the data to AIRBUS. C. General (synopsis of refuel system description and operation)
There are four different types of refuel procedures, these are as follows:
Refueling is usually automatic, the required fuel load is set on the preselector at the refuel panel (800VU).
A fuel gallery connects the refuel coupling to the refuel valve of each tank. The refuel valves are used to control the fuel flow into the tanks in three types of refuel (procedures) and are as follows:
The fuel flow in the Overwing method is controlled by the delivery system (fuel tanker or pump unit).
During an automatic refuel, when all the refuel valve control switches are set to NORMAL, the Fuel Quantity Indicating Computer (FQIC) controls the refuel valves. Each refuel valve is closed when the actual fuel load for its related tank equals an amount, computed by the FQIC, that is related to the preselected fuel quantity. When the refuel of the last (or only) ACT is complete, and the related inlet valve closes, DC power is removed from the ACT refuel valve solenoid to close the refuel valve. Fuel is supplied to all tanks at the same time. This is to keep the refuel time to a minimum. The fuel is loaded in the order that follows:
Left and right wing tanks.
Center tank (if the preselected fuel load is more than the two wing tank capacities).
Additional Center Tank(s) (ACT) in their numerical sequence when two are installed (if the preselected fuel load is more than the two wing tank and the center tank capacities).
During a Manual Pressure Refuel each refuel valve is closed, by one of the ground (refuel) crew, when its refuel valve control switch is set to SHUT.
During the automatic and manual pressure refuel procedures the Fuel Level Sensing System (FLSS) high level channels prevent an overfill and possible spillage.
The FLSS high level channels are automatically switched on (to standby) when the refuel panel door is open (or cockpit refuel is set to on). If, in a main aircraft tank, the incoming fuel reaches the level of a high level sensor and the sensor becomes wet it will automatically close (de-energize) the refuel valve of the related tank. If, in an ACT (when installed), the incoming fuel reaches the level of a high level sensor and the sensor becomes wet it will automatically close the inlet valve of the related ACT.
If the FQIC (when in automatic refuel) or the ground crew (when in manual refuel) fail to to close the refuel valve(s) the applicableFLSS high level channel(s) will operate to prevent a fuel spillage before the related fuel tank becomes (completely) full.
Ifthe incoming fuel pressure is more than 55psi (3.79bar) , a refuel valve can remain (partially) open due to the excessive fuel pressure (even when it is commanded to close). The command to close will come from:
The refuel valve will close automatically:
A fuel spill can be caused whena fuel tank (one or more) becomes full and the fuel flow, refuel or transfer (in), is not stopped . The continuing fuel overflow will then start to go out through the applicable tank(s) vent system. A refuel overflow from the center tank will normally flow to (both) the left and right sides. The escape routing of the center tank overflow fuel is through the center tank:
Two clack valves (non return valves) are at the bottom of the RIB22 and connect the surge tank to the related wing tank. In normal operation the clack valves:
A transfer valve is installed between the engine fuel feed line and the refuel gallery. When open this lets the fuel pumps:
Subtask 28-25-00-710-070-B ** ON A/C NOT FOR ALL There are four different types of refuel procedures, these are as follows:
- Automatic Pressure
- Manual Pressure (with electric power)
- Manual Pressure (without electric power)
- Manual Overwing, (gravity and without electric power).
Refueling is usually automatic, the required fuel load is set on the preselector at the refuel panel (800VU).
A fuel gallery connects the refuel coupling to the refuel valve of each tank. The refuel valves are used to control the fuel flow into the tanks in three types of refuel (procedures) and are as follows:
- Automatic Pressure
- Manual Pressure (with electric power)
- Manual Pressure (without electric power).
The fuel flow in the Overwing method is controlled by the delivery system (fuel tanker or pump unit).
During an automatic refuel, when all the refuel valve control switches are set to NORMAL, the Fuel Quantity Indicating Computer (FQIC) controls the refuel valves. Each refuel valve is closed when the actual fuel load for its related tank equals an amount, computed by the FQIC, that is related to the preselected fuel quantity. When the refuel of the last (or only) ACT is complete, and the related inlet valve closes, DC power is removed from the ACT refuel valve solenoid to close the refuel valve. Fuel is supplied to all tanks at the same time. This is to keep the refuel time to a minimum. The fuel is loaded in the order that follows:
Left and right wing tanks.
Center tank (if the preselected fuel load is more than the two wing tank capacities).
Additional Center Tank(s) (ACT) in their numerical sequence when two are installed (if the preselected fuel load is more than the two wing tank and the center tank capacities).
During a Manual Pressure Refuel each refuel valve is closed, by one of the ground (refuel) crew, when its refuel valve control switch is set to SHUT.
During the automatic and manual pressure refuel procedures the Fuel Level Sensing System (FLSS) high level channels prevent an overfill and possible spillage.
The FLSS high level channels are automatically switched on (to standby) when the refuel panel door is open (or cockpit refuel is set to on). If, in a main aircraft tank, the incoming fuel reaches the level of a high level sensor and the sensor becomes wet it will automatically close (de-energize) the refuel valve of the related tank. If, in an ACT (when installed), the incoming fuel reaches the level of a high level sensor and the sensor becomes wet it will automatically close the inlet valve of the related ACT.
If the FQIC (when in automatic refuel) or the ground crew (when in manual refuel) fail to to close the refuel valve(s) the applicable
If
- the FQIC in automatic refuel
- the applicable REFUEL VALVES selector switch when set to SHUT in a manual refuel.
The refuel valve will close automatically:
- if the pressure of the fuel is reduced to less than 50psi (3.45bar)
- the refuel supply is shut-off.
A fuel spill can be caused when
- vent pipe to the left wing surge tank
- pressure relief valve to the right wing tank
- main transfer system (28-26-00) to the left and right wing wing tanks (by gravity/pressure even when set to OFF).
Two clack valves (non return valves) are at the bottom of the RIB22 and connect the surge tank to the related wing tank. In normal operation the clack valves:
- let the fuel that has entered the surge tank return to the related wing tank, by gravity, if the fuel levels and/or aircraft atitude is appropriate
- do not let fuel enter the surge tank from the wing tank.
A transfer valve is installed between the engine fuel feed line and the refuel gallery. When open this lets the fuel pumps:
- transfer fuel from one tank to another
- defuel the aircraft through the refuel coupling.
D. Identification of the cause of the spill
(1) Complete the Fuel Spill Reporting Sheet
(a) Record the aircraft configuration when fuel spill occurs as follows:
Subtask 28-25-00-710-066-B ** ON A/C NOT FOR ALL (1) Complete the Fuel Spill Reporting Sheet
(a) Record the aircraft configuration when fuel spill occurs as follows:
- Fuel loads
- Fuel Distribution
- Fuel Pump configuration
- Fuel Tank Hi level sensor state.
NOTE: Record the data accurately for easier trouble shooting.
(b) Use the data recorded to help you trouble shoot the procedure and refer the data to AIRBUS. E. Tests
(1) Before you do more steps, stop the refuel.
(a) Put a container (example, barrel - 42 gal) under the applicable NACA vent.
(b) Remove all the spilt fuel in accordance with the local regulations.
(c) Clean the fuel spillage from the:
(a) Drain any remaining fuel from the applicable wing surge tank AMM 28-25-00-650-003.
(b) Do a fuel transfer or defuel to decrease the quantity of fuel in the wing tank that you think has overflowed. A minimum of 400 kg (880 lb) of fuel must be transfered or defueled from each applicable tank.
(a) Do the Functional (BITE) Test of the FLSS (with the refuel panel door open) AMM 28-46-00-740-001.
1 Look at the FLSS STATUS page.
2 If a fault message is shown, do the applicable troubleshooting before you do more steps in this procedure.
(b) Do the Test of the Refuel Panel 800VU, High Level Lights at the (switch) positions LTS then TEST AMM 28-46-00-710-001.
1 If a fault observation is seen, do the applicable troubleshooting before you do more steps in this procedure.
(5) This (passive) step is to see to if you can identify the tank that filled to full and then failed to close (SHUT) its related refuel (or ACT inlet) valve.
(a) On the ECAM System Display Page and the Fuel Quantity Indicator (6QT) read the FQIs of all the fuel tanks.
1 Make a record of the FQI values.
(b) Make an analysis of the fuel spillage observation reports that are available.
Example - from the left or the right side NACA vent.
(a) Transfer with manual control approximately 500 kg (1100 lb) of fuel AMM 28-25-00-869-001.
Look for changes (leakage) in FQI values that are not normal.
Make sure that:
2 Transfer fuel from the left wing tank to the right wing tank. Make sure that the fuel quantities do not change (increase) in the center tank (with the center tank refuel valve closed).
a If, in the center tank, there is a change of FQI (increase/variation), examine:
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, if necessary.
4 Transfer fuel from the left wing tank tank to the center tank. Make sure that the fuel quantities do not change (increase) in the right wing (with the right wing refuel valve closed).
a If, on the right wing side, there is a change of FQI (increase/variation), examine:
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
6 Transfer fuel from the right wing tank to the left wing tank. Make sure that the fuel quantities do not change (increase) in the center tank (with the center tank refuel valve closed).
a If, in the center tank, there is a change of FQI (increase/variation) examine:
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
8 Defuel/transfer valve check.
a Set the SW-MODE SELECT/REFUEL/OFF/DEFUEL/XFR (3QU) to OFF to close (shut) the defuel/transfer valve 11QM.
b Release (out) the P/BSW-FUEL/X FEED (4QE) to close (shut) the crossfeed valve 10QM.
c Set the left wing refuel valve to open.
d Set the right wing tank fuel pumps to on.
e Check for any transfer from the right wing to the left wing.
If such a transfer occurs, do a check of and replace, if necessary, the VALVE-DEFUEL/TRANSFER [11QM] AMM 28-25-43-000-001 and AMM 28-25-43-400-001.
(7) If no reason for the fuel spillage is known but the problem area has been identified, go to Para. 4.A. and do the tests listed for the (identified) tanks related systems.
(8) If no reason for the fuel spillage is known and no fuel tank malfunction has been identified, go to Para. 4.A. and do all the tests given.
Subtask 28-25-00-710-066-E ** ON A/C NOT FOR ALL (1) Before you do more steps, stop the refuel.
(a) Put a container (example, barrel - 42 gal) under the applicable NACA vent.
(b) Remove all the spilt fuel in accordance with the local regulations.
(c) Clean the fuel spillage from the:
- area on the ground (hard standing)
- aircraft.
NOTE: It is possible for more spillage to occur if fuel remains in the surge tanks and the aircraft is moved.
(2) Before movement of the aircraft, do step (a) or step (b). (a) Drain any remaining fuel from the applicable wing surge tank AMM 28-25-00-650-003.
(b) Do a fuel transfer or defuel to decrease the quantity of fuel in the wing tank that you think has overflowed. A minimum of 400 kg (880 lb) of fuel must be transfered or defueled from each applicable tank.
NOTE: When the fuel quantity decreases in the wing tank, fuel in the surge tank will transfer into the wing tank.
(3) Do a check of the refuel supply system (fuel tanker, hydrant or pump unit) delivery fuel pressure to make sure that it is not more than 50psi (3.45bar). NOTE: This is important if a fuel spillage has occured on more than one aircaft during refuels from the same (common) refuel supply unit.
This action can be initiated (started) at the same time as the FLSS high level light systems are tested, step (6).
This procedure from step (9) is:
(4) Do a complete test of the Fuel Level Sensing System, high level channels, as follows: This action can be initiated (started) at the same time as the FLSS high level light systems are tested, step (6).
This procedure from step (9) is:
- only valid for trouble shooting if the (refuel supply system) fuel pressure was known (guaranteed) to be less than 50psi (3.45bar)
- valid for the identification of possible damage to the refuel galleries.
(a) Do the Functional (BITE) Test of the FLSS (with the refuel panel door open) AMM 28-46-00-740-001.
1 Look at the FLSS STATUS page.
2 If a fault message is shown, do the applicable troubleshooting before you do more steps in this procedure.
(b) Do the Test of the Refuel Panel 800VU, High Level Lights at the (switch) positions LTS then TEST AMM 28-46-00-710-001.
1 If a fault observation is seen, do the applicable troubleshooting before you do more steps in this procedure.
(5) This (passive) step is to see to if you can identify the tank that filled to full and then failed to close (SHUT) its related refuel (or ACT inlet) valve.
(a) On the ECAM System Display Page and the Fuel Quantity Indicator (6QT) read the FQIs of all the fuel tanks.
1 Make a record of the FQI values.
(b) Make an analysis of the fuel spillage observation reports that are available.
Example - from the left or the right side NACA vent.
NOTE: If the fuel spillage was from the left wing NACA vent the problem is in one of the tanks that follows:
If the fuel spillage was from the right wing NACA vent the problem is in one of the tanks that follows:
(6) This (active and relatively quick) step, (from the cockpit and refuel control panel) is to see to if you can identify (or confirm/validate) any malfunction(s) or damage in the refuel and associated systems. - left wing tank
- center tank.
If the fuel spillage was from the right wing NACA vent the problem is in one of the tanks that follows:
- right wing tank
- center tank.
(a) Transfer with manual control approximately 500 kg (1100 lb) of fuel AMM 28-25-00-869-001.
Look for changes (leakage) in FQI values that are not normal.
Make sure that:
- all the fuel removed from the (donor/supply - decreasing FQI) tank is transferred to the (receptor/supplied/receiving - increasing FQI) tank
- no fuel is moved into, or out of, the other tanks (changes in FQIs).
2 Transfer fuel from the left wing tank to the right wing tank. Make sure that the fuel quantities do not change (increase) in the center tank (with the center tank refuel valve closed).
a If, in the center tank, there is a change of FQI (increase/variation), examine:
- the VALVE-REFUEL, CTR TK [10QU] and replace, if necessary AMM 28-25-51-000-002 and AMM 28-25-51-400-002.
- the center tank refuel gallery and repair, if necessary.
NOTE: This step sets the conditions to see if the right wing refuel valve can close and then increases the fuel pressure in the fuel galleries.
There will be a small transfer of fuel through the suction inlet valve under the conditions given.
a If the VALVE-REFUEL, R WING TK [8QU] did not close during step 3_, replace it AMM 28-25-51-000-001 and AMM 28-25-51-400-001. There will be a small transfer of fuel through the suction inlet valve under the conditions given.
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, if necessary.
4 Transfer fuel from the left wing tank tank to the center tank. Make sure that the fuel quantities do not change (increase) in the right wing (with the right wing refuel valve closed).
a If, on the right wing side, there is a change of FQI (increase/variation), examine:
- the VALVE-REFUEL, R WING TK [8QU] and replace, if necessary AMM 28-25-51-000-001 and AMM 28-25-51-400-001.
- the right wing refuel gallery and repair, if necessary.
NOTE: This step sets the conditions to see if the center tank refuel valve can close and then increases the fuel pressure in the fuel galleries.
a If the VALVE-REFUEL, CTR TK [10QU] did not close during step 5_, replace it AMM 28-25-51-000-002 and AMM 28-25-51-400-002. b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
6 Transfer fuel from the right wing tank to the left wing tank. Make sure that the fuel quantities do not change (increase) in the center tank (with the center tank refuel valve closed).
a If, in the center tank, there is a change of FQI (increase/variation) examine:
- the VALVE-REFUEL, CTR TK [10QU] and replace, if necessary AMM 28-25-51-000-002 and AMM 28-25-51-400-002.
- the center tank refuel gallery and repair, if necessary.
NOTE: This step sets the conditions to see if the left wing refuel valve can close and then increases the fuel pressure in the fuel galleries.
a If the VALVE-REFUEL, L WING TK [7QU] did not close during step 7_, replace it AMM 28-25-51-000-001 and AMM 28-25-51-400-001. b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
8 Defuel/transfer valve check.
a Set the SW-MODE SELECT/REFUEL/OFF/DEFUEL/XFR (3QU) to OFF to close (shut) the defuel/transfer valve 11QM.
b Release (out) the P/BSW-FUEL/X FEED (4QE) to close (shut) the crossfeed valve 10QM.
c Set the left wing refuel valve to open.
d Set the right wing tank fuel pumps to on.
e Check for any transfer from the right wing to the left wing.
If such a transfer occurs, do a check of and replace, if necessary, the VALVE-DEFUEL/TRANSFER [11QM] AMM 28-25-43-000-001 and AMM 28-25-43-400-001.
(7) If no reason for the fuel spillage is known but the problem area has been identified, go to Para. 4.A. and do the tests listed for the (identified) tanks related systems.
(8) If no reason for the fuel spillage is known and no fuel tank malfunction has been identified, go to Para. 4.A. and do all the tests given.
E. Tests
(1) Before you do more steps, stop the refuel.
(a) Put a container (example, barrel - 42 gal) under the applicable NACA vent.
(b) Remove all the spilt fuel in accordance with the local regulations.
(c) Clean the fuel spillage from the:
(a) Drain any remaining fuel from the applicable wing surge tank AMM 28-25-00-650-003.
(b) Do a fuel transfer or defuel to decrease the quantity of fuel in the wing tank that you think has overflowed. A minimum of 400 kg (880 lb) of fuel must be transfered or defueled from each applicable tank.
(a) TheP/BSW-FUEL/CTR TK/MODE SELECT/AUTO (4QL) is in the AUTO position.
(b) All the fuel-pump P/BSWs are in the ON position
(c) The center tank L and R XFR P/BSWs are in the ON position.
(4) Do a check of the refuel supply system (fuel tanker, hydrant or pump unit) delivery fuel pressure to make sure that it is not more than 50psi (3.45bar).
(a) Refer to Start Troubleshooting, CFDS for the related TSM procedure.
(7) Do a complete test of the Fuel Level Sensing System, high level channels, as follows:
(a) Do the Functional (BITE) Test of the FLSS (with the refuel panel door open) AMM 28-46-00-740-001.
1 Look at the FLSS STATUS page.
2 If a fault message is shown, do the applicable troubleshooting before you do more steps in this procedure.
(b) Do the Test of the Refuel Panel 800VU, High Level Lights at the (switch) positions LTS then TEST AMM 28-46-00-710-001.
1 If a fault observation is seen, do the applicable troubleshooting before you do more steps in this procedure.
(8) Do the Operational Test of the Main Transfer System AMM 28-26-00-710-001.
(a) If the main transfer system:
(10) This (passive) step is to see to if you can identify the tank that filled to full and then failed to close (SHUT) its related refuel (or ACT inlet) valve.
(a) On the ECAM System Display Page and the Fuel Quantity Indicator (6QT) read the FQIs of all the fuel tanks.
1 Make a record of the FQI values.
(b) Make an analysis of the fuel spillage observation reports that are available.
Example - from the left or the right side NACA vent.
(a) Transfer with manual control approximately 500 kg (1100 lb) of fuel AMM 28-25-00-869-001.
Look for changes (leakage) in FQI values that are not normal.
Make sure that:
2 Transfer fuel from the left wing tank to the right wing tank. Make sure that the fuel quantities do not change (increase) in the center tank (with the center tank refuel valve closed).
a If, in the center tank, there is a change of FQI (increase/variation), examine:
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, if necessary.
4 Transfer fuel from the left wing tank tank to the center tank. Make sure that the fuel quantities do not change (increase) in the right wing (with the right wing refuel valve closed).
a If, on the right wing side, there is a change of FQI (increase/variation), examine:
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
6 Transfer fuel from the right wing tank to the left wing tank. Make sure that the fuel quantities do not change (increase) in the center tank (with the center tank refuel valve closed).
a If, in the center tank, there is a change of FQI (increase/variation) examine:
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
8 Defuel/transfer valve check.
a Set the SW-MODE SELECT/REFUEL/OFF/DEFUEL/XFR (3QU) to OFF to close (shut) the defuel/transfer valve 11QM.
b Release (out) the P/BSW-FUEL/X FEED (4QE) to close (shut) the crossfeed valve 10QM.
c Set the left wing refuel valve to open.
d Set the right wing tank fuel pumps to on.
e Check for any transfer from the right wing to the left wing.
If such a transfer occurs, do a check of and replace, if necessary, the VALVE-DEFUEL/TRANSFER [11QM] AMM 28-25-43-000-001 and AMM 28-25-43-400-001.
(12) If no reason for the fuel spillage is known but the problem area has been identified, go to Para. 4.A. and do the tests listed for the (identified) tanks related systems.
(13) If no reason for the fuel spillage is known and no fuel tank malfunction has been identified, go to Para. 4.A. and do all the tests given.
Subtask 28-25-00-710-066-F ** ON A/C NOT FOR ALL (1) Before you do more steps, stop the refuel.
(a) Put a container (example, barrel - 42 gal) under the applicable NACA vent.
(b) Remove all the spilt fuel in accordance with the local regulations.
(c) Clean the fuel spillage from the:
- area on the ground (hard standing)
- aircraft.
NOTE: It is possible for more spillage to occur if fuel remains in the surge tanks and the aircraft is moved.
(2) Before movement of the aircraft, do step (a) or step (b). (a) Drain any remaining fuel from the applicable wing surge tank AMM 28-25-00-650-003.
(b) Do a fuel transfer or defuel to decrease the quantity of fuel in the wing tank that you think has overflowed. A minimum of 400 kg (880 lb) of fuel must be transfered or defueled from each applicable tank.
NOTE: When the fuel quantity decreases in the wing tank, fuel in the surge tank will transfer into the wing tank.
(3) In the cockpit, on the overhead panel 40VU make sure that: (a) The
(b) All the fuel-pump P/BSWs are in the ON position
(c) The center tank L and R XFR P/BSWs are in the ON position.
(4) Do a check of the refuel supply system (fuel tanker, hydrant or pump unit) delivery fuel pressure to make sure that it is not more than 50psi (3.45bar).
NOTE: This is important if a fuel spillage has occured on more than one aircaft during refuels from the same (common) refuel supply unit.
This action can be initiated (started) at the same time as the FLSS high level light systems are tested, step (6).
This procedure from step (9) is:
(5) Examine the FLSS STATUS page for one or more of the messages that follow: This action can be initiated (started) at the same time as the FLSS high level light systems are tested, step (6).
This procedure from step (9) is:
- only valid for trouble shooting if the (refuel supply system) fuel pressure was known (guaranteed) to be less than 50psi (3.45bar)
- valid for the identification of possible damage to the refuel galleries.
- SENSOR-FULL LVL, L WNG TK INR 1 CHANNEL B [23QJ1]
- SENSOR-FULL LVL, R WNG TK INR 1 CHANNEL B [23QJ2]
- SENSOR-FULL LVL, L WNG TK INR 2 CHANNEL B [27QJ1]
- SENSOR-FULL LVL, R WNG TK INR 2 CHANNEL B [27QJ2] .
- none of the messages are shown, go to step (6).
- one or more of the messages is shown, go to the next step.
(a) Refer to Start Troubleshooting, CFDS for the related TSM procedure.
(7) Do a complete test of the Fuel Level Sensing System, high level channels, as follows:
(a) Do the Functional (BITE) Test of the FLSS (with the refuel panel door open) AMM 28-46-00-740-001.
1 Look at the FLSS STATUS page.
2 If a fault message is shown, do the applicable troubleshooting before you do more steps in this procedure.
(b) Do the Test of the Refuel Panel 800VU, High Level Lights at the (switch) positions LTS then TEST AMM 28-46-00-710-001.
1 If a fault observation is seen, do the applicable troubleshooting before you do more steps in this procedure.
(8) Do the Operational Test of the Main Transfer System AMM 28-26-00-710-001.
(a) If the main transfer system:
- operates as specified, no troubleshooting work is necessary.
- does not operate as specified (and the left and right main transfer control valves do not close), do the next step.
(10) This (passive) step is to see to if you can identify the tank that filled to full and then failed to close (SHUT) its related refuel (or ACT inlet) valve.
(a) On the ECAM System Display Page and the Fuel Quantity Indicator (6QT) read the FQIs of all the fuel tanks.
1 Make a record of the FQI values.
(b) Make an analysis of the fuel spillage observation reports that are available.
Example - from the left or the right side NACA vent.
NOTE: If the fuel spillage was from the left wing NACA vent the problem is in one of the tanks that follows:
If the fuel spillage was from the right wing NACA vent the problem is in one of the tanks that follows:
(11) This (active and relatively quick) step, (from the cockpit and refuel control panel) is to see to if you can identify (or confirm/validate) any malfunction(s) or damage in the refuel and associated systems. - left wing tank
- center tank.
If the fuel spillage was from the right wing NACA vent the problem is in one of the tanks that follows:
- right wing tank
- center tank.
(a) Transfer with manual control approximately 500 kg (1100 lb) of fuel AMM 28-25-00-869-001.
Look for changes (leakage) in FQI values that are not normal.
Make sure that:
- all the fuel removed from the (donor/supply - decreasing FQI) tank is transferred to the (receptor/supplied/receiving - increasing FQI) tank
- no fuel is moved into, or out of, the other tanks (changes in FQIs).
2 Transfer fuel from the left wing tank to the right wing tank. Make sure that the fuel quantities do not change (increase) in the center tank (with the center tank refuel valve closed).
a If, in the center tank, there is a change of FQI (increase/variation), examine:
- the VALVE-REFUEL, CTR TK [10QU] and replace, if necessary AMM 28-25-51-000-002 and AMM 28-25-51-400-002.
- the center tank refuel gallery and repair, if necessary.
NOTE: This step sets the conditions to see if the right wing refuel valve can close and then increases the fuel pressure in the fuel galleries.
There will be a small transfer of fuel through the suction inlet valve under the conditions given.
a If the VALVE-REFUEL, R WING TK [8QU] did not close during step 3_, replace it AMM 28-25-51-000-001 and AMM 28-25-51-400-001. There will be a small transfer of fuel through the suction inlet valve under the conditions given.
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, if necessary.
4 Transfer fuel from the left wing tank tank to the center tank. Make sure that the fuel quantities do not change (increase) in the right wing (with the right wing refuel valve closed).
a If, on the right wing side, there is a change of FQI (increase/variation), examine:
- the VALVE-REFUEL, R WING TK [8QU] and replace, if necessary AMM 28-25-51-000-001 and AMM 28-25-51-400-001.
- the right wing refuel gallery and repair, if necessary.
NOTE: This step sets the conditions to see if the center tank refuel valve can close and then increases the fuel pressure in the fuel galleries.
a If the VALVE-REFUEL, CTR TK [10QU] did not close during step 5_, replace it AMM 28-25-51-000-002 and AMM 28-25-51-400-002. b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
6 Transfer fuel from the right wing tank to the left wing tank. Make sure that the fuel quantities do not change (increase) in the center tank (with the center tank refuel valve closed).
a If, in the center tank, there is a change of FQI (increase/variation) examine:
- the VALVE-REFUEL, CTR TK [10QU] and replace, if necessary AMM 28-25-51-000-002 and AMM 28-25-51-400-002.
- the center tank refuel gallery and repair, if necessary.
NOTE: This step sets the conditions to see if the left wing refuel valve can close and then increases the fuel pressure in the fuel galleries.
a If the VALVE-REFUEL, L WING TK [7QU] did not close during step 7_, replace it AMM 28-25-51-000-001 and AMM 28-25-51-400-001. b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
8 Defuel/transfer valve check.
a Set the SW-MODE SELECT/REFUEL/OFF/DEFUEL/XFR (3QU) to OFF to close (shut) the defuel/transfer valve 11QM.
b Release (out) the P/BSW-FUEL/X FEED (4QE) to close (shut) the crossfeed valve 10QM.
c Set the left wing refuel valve to open.
d Set the right wing tank fuel pumps to on.
e Check for any transfer from the right wing to the left wing.
If such a transfer occurs, do a check of and replace, if necessary, the VALVE-DEFUEL/TRANSFER [11QM] AMM 28-25-43-000-001 and AMM 28-25-43-400-001.
(12) If no reason for the fuel spillage is known but the problem area has been identified, go to Para. 4.A. and do the tests listed for the (identified) tanks related systems.
(13) If no reason for the fuel spillage is known and no fuel tank malfunction has been identified, go to Para. 4.A. and do all the tests given.
E. Tests
(1) Before you do more steps, stop the refuel.
(a) Put a container (example, barrel - 42 gal) under the applicable NACA vent.
(b) Remove all the spilt fuel in accordance with the local regulations.
(c) Clean the fuel spillage from the:
(a) Drain any remaining fuel from the applicable wing surge tank AMM 28-25-00-650-003.
(b) Do a fuel transfer or defuel to decrease the quantity of fuel in the wing tank that you think has overflowed. A minimum of 400 kg (880 lb) of fuel must be transfered or defueled from each applicable tank.
(a) TheP/BSW-FUEL/CTR TK/MODE SELECT/AUTO (4QL) is in the AUTO position.
(b) All the fuel-pump P/BSWs are in the ON position
(c) The center tank L and R XFR P/BSWs are in the ON position.
(4) Do a check of the refuel supply system (fuel tanker, hydrant or pump unit) delivery fuel pressure to make sure that it is not more than 50psi (3.45bar).
(a) Refer to Start Troubleshooting, CFDS for the related TSM procedure.
(7) Do a complete test of the Fuel Level Sensing System, high level channels, as follows:
(a) Do the Functional (BITE) Test of the FLSS (with the refuel panel door open) AMM 28-46-00-740-001.
1 Look at the FLSS STATUS page.
2 If a fault message is shown, do the applicable troubleshooting before you do more steps in this procedure.
(b) Do the Test of the Refuel Panel 800VU/801VU, High Level Lights at the (switch) positions LTS then TEST AMM 28-46-00-710-001.
1 If a fault observation is seen, do the applicable troubleshooting before you do more steps in this procedure.
(8) Do the Operational Test of the Main Transfer System AMM 28-26-00-710-001.
(a) If the main transfer system:
(a) On the ECAM System Display Page and the Fuel Quantity Indicator (6QT) read the FQIs of all the fuel tanks.
1 Make a record of the FQI values.
(b) Make an analysis of the fuel spillage observation reports that are available.
Example - from the left or the right side NACA vent.
(a) Transfer with manual control approximately 500 kg (1100 lb) of fuel AMM 28-25-00-869-001.
Look for changes (leakage) in FQI values that are not normal.
Make sure that:
2 Transfer fuel from the left wing tank to the right wing tank. Make sure that the fuel quantities do not change (increase) in the center tank or the ACT(s).
a If, in the center tank or the ACT(s) there is a change of FQI (increase/variation), examine the items that follow and replace, if necessary:
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, if necessary.
4 Transfer fuel from the left wing tank tank to the center tank. Make sure that the fuel quantities do not change (increase) in the right wing tank or the ACT(s).
a If, in the right wing tank or the ACT(s) there is a change of FQI (increase/variation), examine the items that follow and replace, if necessary:
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
6 Transfer fuel from the right wing tank to the left wing tank. Make sure that the fuel quantities do not change (increase) in the center tank or the ACT(s).
a If, in the center tank or the ACT(s) there is a change of FQI (increase/variation) examine the items that follow and replace, if necessary:
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
8 ACT fuel transfer line check
For aircraft provisioned for ACTs but with no ACTs installed, do steps a_ thru f_. Ignore the references to the ACT fuel quantities in steps d_ and e_.
For aircraft with ACT(s) installed , do steps a_ thru g_.
a Make sure that the defuel/transfer valve 11QU is still open.
b Set the right wing tank pumps to run to pressurize the refuel gallery.
c Manually (hold) open the ACT refuel valve 41QU.
d Monitor the FQI of the center tank and each (operational) ACT.
e Make sure that the fuel quantities do not change (increase) in the center tank or operational ACTs.
f If, in the center tank there is a change of FQI (increase/variation), examine the items that follow and replace, if necessary:
a Set the SW-MODE SELECT/REFUEL/OFF/DEFUEL/XFR (3QU) to OFF to close (shut) the defuel/transfer valve 11QM.
b Release (out) the P/BSW-FUEL/X FEED (4QE) to close (shut) the crossfeed valve 10QM.
c Set the left wing refuel valve to open.
d Set the right wing tank fuel pumps to on.
e Check for any transfer from the right wing to the left wing.
If such a transfer occurs, do a check of and replace, if necessary, the VALVE-DEFUEL/TRANSFER [11QM] AMM 28-25-43-000-001 and AMM 28-25-43-400-001.
(11) If no reason for the fuel spillage is known but the problem area has been identified, go to Para. 4.A. and do the tests listed for the (identified) tanks related systems.
(12) If no reason for the fuel spillage is known and no fuel tank malfunction has been identified, go to Para. 4.A. and do all the tests given.
4. Fault Isolation(1) Before you do more steps, stop the refuel.
(a) Put a container (example, barrel - 42 gal) under the applicable NACA vent.
(b) Remove all the spilt fuel in accordance with the local regulations.
(c) Clean the fuel spillage from the:
- area on the ground (hard standing)
- aircraft.
NOTE: It is possible for more spillage to occur if fuel remains in the surge tanks and the aircraft is moved.
(2) Before movement of the aircraft, do step (a) or step (b). (a) Drain any remaining fuel from the applicable wing surge tank AMM 28-25-00-650-003.
(b) Do a fuel transfer or defuel to decrease the quantity of fuel in the wing tank that you think has overflowed. A minimum of 400 kg (880 lb) of fuel must be transfered or defueled from each applicable tank.
NOTE: When the fuel quantity decreases in the wing tank, fuel in the surge tank will transfer into the wing tank.
(3) In the cockpit, on the overhead panel 40VU make sure that: (a) The
(b) All the fuel-pump P/BSWs are in the ON position
(c) The center tank L and R XFR P/BSWs are in the ON position.
(4) Do a check of the refuel supply system (fuel tanker, hydrant or pump unit) delivery fuel pressure to make sure that it is not more than 50psi (3.45bar).
NOTE: This is important if a fuel spillage has occured on more than one aircaft during refuels from the same (common) refuel supply unit.
This action can be initiated (started) at the same time as the FLSS high level light systems are tested, step (6).
This procedure from step (9) is:
(5) Examine the FLSS STATUS page for one or more of the messages that follow: This action can be initiated (started) at the same time as the FLSS high level light systems are tested, step (6).
This procedure from step (9) is:
- only valid for trouble shooting if the (refuel supply system) fuel pressure was known (guaranteed) to be less than 50psi (3.45bar)
- valid for the identification of possible damage to the refuel galleries.
- SENSOR-FULL LVL, L WNG TK INR 1 CHANNEL B [23QJ1]
- SENSOR-FULL LVL, R WNG TK INR 1 CHANNEL B [23QJ2]
- SENSOR-FULL LVL, L WNG TK INR 2 CHANNEL B [27QJ1]
- SENSOR-FULL LVL, R WNG TK INR 2 CHANNEL B [27QJ2] .
- none of the messages are shown, go to step (6).
- one or more of the messages is shown, go to the next step.
(a) Refer to Start Troubleshooting, CFDS for the related TSM procedure.
(7) Do a complete test of the Fuel Level Sensing System, high level channels, as follows:
(a) Do the Functional (BITE) Test of the FLSS (with the refuel panel door open) AMM 28-46-00-740-001.
1 Look at the FLSS STATUS page.
2 If a fault message is shown, do the applicable troubleshooting before you do more steps in this procedure.
(b) Do the Test of the Refuel Panel 800VU/801VU, High Level Lights at the (switch) positions LTS then TEST AMM 28-46-00-710-001.
1 If a fault observation is seen, do the applicable troubleshooting before you do more steps in this procedure.
(8) Do the Operational Test of the Main Transfer System AMM 28-26-00-710-001.
(a) If the main transfer system:
- operates as specified, no troubleshooting work is necessary.
- does not operate as specified (and the left and right main transfer control valves do not close), do the next step.
(a) On the ECAM System Display Page and the Fuel Quantity Indicator (6QT) read the FQIs of all the fuel tanks.
1 Make a record of the FQI values.
(b) Make an analysis of the fuel spillage observation reports that are available.
Example - from the left or the right side NACA vent.
NOTE: Aircraft with provision for ACTs only
Ignore the references to ACT(s) in the fuel transfer checks that follow and check the aircraft as if it is a normal three tank type.
Ignore the references to ACT(s) in the fuel transfer checks that follow and check the aircraft as if it is a normal three tank type.
NOTE: Aircraft with one ACT installed only
An overflow cannot be caused by by the ACT refuel valve open as there is also an ACT 1 inlet valve in series with it. The two (both) will close when commanded to close. If one valve fails in the open position, refuel will still stop by the closure of the other. The ACT refuel valve will open only if it receives a ground - ACT transfer valve shut/closed (interlock). This stops the possibility of a double failure, refuel and transfer valve failed open, that would cause an uncontrolled fuel flow into the center tank through this route.
An overflow cannot be caused by by the ACT refuel valve open as there is also an ACT 1 inlet valve in series with it. The two (both) will close when commanded to close. If one valve fails in the open position, refuel will still stop by the closure of the other. The ACT refuel valve will open only if it receives a ground - ACT transfer valve shut/closed (interlock). This stops the possibility of a double failure, refuel and transfer valve failed open, that would cause an uncontrolled fuel flow into the center tank through this route.
NOTE: Aircraft with two ACTs installed
If when one ACT is full its ACT inlet valve does not shut, that (related) ACT will overflow into the center tank through the ACT vent line while the other ACT is filling. The ACT overflow will stop when the ACT refuel is complete and the ACT refuel valve shuts. The ACT refuel valve will open only if it receives a ground - ACT transfer valve shut/closed (interlock). This stops the possibility of a double failure, refuel and transfer valve failed open, that would cause an uncontrolled fuel flow into the center tank through this route.
If when one ACT is full its ACT inlet valve does not shut, that (related) ACT will overflow into the center tank through the ACT vent line while the other ACT is filling. The ACT overflow will stop when the ACT refuel is complete and the ACT refuel valve shuts. The ACT refuel valve will open only if it receives a ground - ACT transfer valve shut/closed (interlock). This stops the possibility of a double failure, refuel and transfer valve failed open, that would cause an uncontrolled fuel flow into the center tank through this route.
NOTE: If the fuel spillage was from the left wing NACA vent the problem is in one of the tanks that follows:
If the fuel spillage was from the right wing NACA vent the problem is in one of the tanks that follow:
(10) This (active and relatively quick) step, (from the cockpit and refuel control panel) is to see to if you can identify (or confirm/validate) any malfunction(s) or damage in the refuel and associated systems. - left wing tank
- center tank
- ACT tank(s).
If the fuel spillage was from the right wing NACA vent the problem is in one of the tanks that follow:
- right wing tank
- center tank
- ACT tank(s).
(a) Transfer with manual control approximately 500 kg (1100 lb) of fuel AMM 28-25-00-869-001.
Look for changes (leakage) in FQI values that are not normal.
Make sure that:
- all the fuel removed from the (donor/supply - decreasing FQI) tank is transferred to the (receptor/supplied/receiving - increasing FQI) tank
- no fuel is moved into, or out of, the other tanks (changes in FQIs).
2 Transfer fuel from the left wing tank to the right wing tank. Make sure that the fuel quantities do not change (increase) in the center tank or the ACT(s).
a If, in the center tank or the ACT(s) there is a change of FQI (increase/variation), examine the items that follow and replace, if necessary:
- the VALVE-REFUEL, CTR TK [10QU] AMM 28-25-51-000-002 and AMM 28-25-51-400-002
- the VALVE-REFUEL, ACT [41QU] AMM 28-25-51-000-004 and AMM 28-25-51-400-004
- the center tank refuel gallery
- the ACT(s) refuel gallery.
NOTE: This step sets the conditions to see if the right wing refuel valve can close and then increases the fuel pressure in the fuel galleries.
There will be a small transfer of fuel through the suction inlet valve under the conditions given.
a If the VALVE-REFUEL, R WING TK [8QU] did not close during step 3_, replace it AMM 28-25-51-000-001 and AMM 28-25-51-400-001. There will be a small transfer of fuel through the suction inlet valve under the conditions given.
b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, if necessary.
4 Transfer fuel from the left wing tank tank to the center tank. Make sure that the fuel quantities do not change (increase) in the right wing tank or the ACT(s).
a If, in the right wing tank or the ACT(s) there is a change of FQI (increase/variation), examine the items that follow and replace, if necessary:
- the VALVE-REFUEL, R WING TK [8QU] AMM 28-25-51-000-001 and AMM 28-25-51-400-001
- the VALVE-REFUEL, ACT [41QU] AMM 28-25-51-000-004 and AMM 28-25-51-400-004
- the right wing refuel gallery
- the ACT(s) refuel gallery.
NOTE: This step sets the conditions to see if the center tank refuel valve can close and then increases the fuel pressure in the fuel galleries.
a If the VALVE-REFUEL, CTR TK [10QU] did not close during step 5_, replace it AMM 28-25-51-000-002 and AMM 28-25-51-400-002. b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
6 Transfer fuel from the right wing tank to the left wing tank. Make sure that the fuel quantities do not change (increase) in the center tank or the ACT(s).
a If, in the center tank or the ACT(s) there is a change of FQI (increase/variation) examine the items that follow and replace, if necessary:
- the VALVE-REFUEL, CTR TK [10QU] AMM 28-25-51-000-002 and AMM 28-25-51-400-002
- the VALVE-REFUEL, ACT [41QU] AMM 28-25-51-000-004 and AMM 28-25-51-400-004
- the center tank refuel gallery
- the ACT(s) refuel gallery.
NOTE: This step sets the conditions to see if the left wing refuel valve can close and then increases the fuel pressure in the fuel galleries.
a If the VALVE-REFUEL, L WING TK [7QU] did not close during step 7_, replace it AMM 28-25-51-000-001 and AMM 28-25-51-400-001. b If any tank(s) FQI is seen to increase, examine the refuel gallery in the related tank(s) and repair, as necessary.
8 ACT fuel transfer line check
For aircraft provisioned for ACTs but with no ACTs installed, do steps a_ thru f_. Ignore the references to the ACT fuel quantities in steps d_ and e_.
For aircraft with ACT(s) installed , do steps a_ thru g_.
a Make sure that the defuel/transfer valve 11QU is still open.
b Set the right wing tank pumps to run to pressurize the refuel gallery.
c Manually (hold) open the ACT refuel valve 41QU.
d Monitor the FQI of the center tank and each (operational) ACT.
e Make sure that the fuel quantities do not change (increase) in the center tank or operational ACTs.
f If, in the center tank there is a change of FQI (increase/variation), examine the items that follow and replace, if necessary:
- the VALVE-FUEL TRANSFER, ACT [165QM] AMM 28-28-33-000-001 and AMM 28-28-33-400-001
- the ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH] AMM 28-28-53-000-001 and AMM 28-28-53-400-001
- the center tank refuel gallery between the ACT refuel valve 41QU and the ACT transfer valve 165QM.
- the VALVE-FUEL INLET, ACT1 [166QM1] or VALVE-FUEL INLET, ACT2 [166QM2] AMM 28-28-34-000-001 and AMM 28-28-34-400-001
- the ACTUATOR-FUEL INLET VALVE, ACT1 [5QH1] or ACTUATOR-FUEL INLET VALVE, ACT2 [5QH2] AMM 28-28-54-000-001 and AMM 28-28-54-400-001
- the refuel line (gallery) with in the ACT.
a Set the SW-MODE SELECT/REFUEL/OFF/DEFUEL/XFR (3QU) to OFF to close (shut) the defuel/transfer valve 11QM.
b Release (out) the P/BSW-FUEL/X FEED (4QE) to close (shut) the crossfeed valve 10QM.
c Set the left wing refuel valve to open.
d Set the right wing tank fuel pumps to on.
e Check for any transfer from the right wing to the left wing.
If such a transfer occurs, do a check of and replace, if necessary, the VALVE-DEFUEL/TRANSFER [11QM] AMM 28-25-43-000-001 and AMM 28-25-43-400-001.
(11) If no reason for the fuel spillage is known but the problem area has been identified, go to Para. 4.A. and do the tests listed for the (identified) tanks related systems.
(12) If no reason for the fuel spillage is known and no fuel tank malfunction has been identified, go to Para. 4.A. and do all the tests given.
Subtask 28-25-00-810-067-B ** ON A/C NOT FOR ALL
A. Procedure
(4) On the opposite side wing to the fuel spillage, do a General Visual Inspection of NACA Vent Intake For Signs ofObstruction (blockage) AMM 28-12-47-200-001.
(5) Do an Inspection of the Overpressure Protectors (Wing and Vent Surge Tanks) AMM 28-12-41-200-003.
(6) If the fuel spillage was from the left side, do the Inspection of the Overpressure Protector 96QM AMM 28-12-41-200-002.
(7) Do the Operational Test of the Refuel System AMM 28-25-00-710-003.
(8) Do the Operational Test of the Defuel System AMM 28-25-00-710-002.
(9) Do the Operational Test of the Crossfeed Valve AMM 28-23-00-720-001.
(10) Do a check of and replace, if necessary, items of thevent/surge tank scavenge system that follow:
(b) The JET PUMP-WATER SCAVENGE, L VENT SURGE TK or JET PUMP-WATER SCAVENGE, L VENT SURGE TK [66QM] ( JET PUMP-WATER SCAVENGE, R VENT SURGE TK or JET PUMP-WATER SCAVENGE, R VENT SURGE TK [69QM] ) AMM 28-21-53-000-001 and AMM 28-21-53-400-001.
(c) The CHECK VALVE-FUEL PUMP, L VENT SURGE TK [37QM] ( CHECK VALVE-FUEL PUMP, R VENT SURGE TK [38QM] ) AMM 28-21-43-000-003 and AMM 28-21-43-400-003.
(d) The jet-pump (feed/drive supply) pipe-lines, between:
(f) The jet-pump (output/discharge) pipe-line(s), between the jet-pump 66QM (69QM) and the fuel discharge (outlet) adjacent to the intercell transfer valve 28QM (30QM) outboard of RIB15.
(g) Repair/replace all the unserviceable fuel pipes and connections AMM 28-00-00-000-001 and AMM 28-00-00-400-001.
(h) The fuel-pump suction valve AMM 28-21-42-000-001 and AMM 28-21-42-400-001.
(11) If the fuel spillage occurred with the fuel pumps set to ON (Post Flight Config) do:
(a) Examine the applicableengine fuel feed line, Air Release Valve and, if necessary, replace AMM 28-21-41-000-001 and AMM 28-21-41-400-001.
(b) If necessary, do Internal Fuel Leak Which Causes a Fuel Imbalance or a Discharge From a NACA Vent During Taxi or Flight (Ref. TSM TASK 28-21-00-810-825).
Subtask 28-25-00-810-067-D ** ON A/C NOT FOR ALL NOTE: The tests listed here are a guide only.
They can be done in an order (any) best suited to:
If only a test is called for, take any resulting ECAM WARNING(s), failure message(s) and/or observation(s) and do the applicable trouble shooting.
(1) Do a check for damage to the float vent valve(s) 15QM, 16QM, 17QM and 18QM. Make sure the applicable valve moves freely through its full range of movement: They can be done in an order (any) best suited to:
- the local conditions in which the fuel spillage occurred
- the tools and equipment available.
If only a test is called for, take any resulting ECAM WARNING(s), failure message(s) and/or observation(s) and do the applicable trouble shooting.
- If necessary, replace the applicable VALVE-FLOAT VENT, L WING TK OUTR [15QM] or VALVE-FLOAT VENT, R WING TK OUTR [18QM] AMM 28-12-43-000-001 and AMM 28-12-43-400-001.
- If necessary, replace the applicable VALVE-FLOAT VENT, L WING TK INR [16QM] or VALVE-FLOAT VENT, R WING TK INR [17QM] AMM 28-12-43-000-002 and AMM 28-12-43-400-002.
- Pressure Refuel with Automatic Control AMM 12-11-28-650-003
- Pressure Refuel with Manual Control AMM 12-11-28-650-004
- Pressure Refuel without Electric Power AMM 12-11-28-650-005
- Overwing (Gravity) Refuel AMM 12-11-28-650-006
- Fuel Transfer AMM 28-25-00-869-001.
(4) On the opposite side wing to the fuel spillage, do a General Visual Inspection of NACA Vent Intake For Signs of
(5) Do an Inspection of the Overpressure Protectors (Wing and Vent Surge Tanks) AMM 28-12-41-200-003.
(6) If the fuel spillage was from the left side, do the Inspection of the Overpressure Protector 96QM AMM 28-12-41-200-002.
(7) Do the Operational Test of the Refuel System AMM 28-25-00-710-003.
(8) Do the Operational Test of the Defuel System AMM 28-25-00-710-002.
(9) Do the Operational Test of the Crossfeed Valve AMM 28-23-00-720-001.
(10) Do a check of and replace, if necessary, items of the
NOTE: If the vent/surge tank scavenge system is inoperative, the fuel level in the vent/surge tank will increase because it cannot be collected and transferred back into a main tank. If, during these conditions, a fuel surge were to occur during the refuel, less fuel can be held in the vent/surge tank than if it was continuously drained and almost empty. This will increase the possibility of a fuel spillage because the usable capacity of the vent/surge tank has been reduced.
(a) The jet adaptor assembly AMM 28-21-53-000-003 and AMM 28-21-53-400-003. (b) The JET PUMP-WATER SCAVENGE, L VENT SURGE TK or JET PUMP-WATER SCAVENGE, L VENT SURGE TK [66QM] ( JET PUMP-WATER SCAVENGE, R VENT SURGE TK or JET PUMP-WATER SCAVENGE, R VENT SURGE TK [69QM] ) AMM 28-21-53-000-001 and AMM 28-21-53-400-001.
(c) The CHECK VALVE-FUEL PUMP, L VENT SURGE TK [37QM] ( CHECK VALVE-FUEL PUMP, R VENT SURGE TK [38QM] ) AMM 28-21-43-000-003 and AMM 28-21-43-400-003.
(d) The jet-pump (feed/drive supply) pipe-lines, between:
- the left-wing fuel-manifold (adjacent to the check valves 33QM and 34QM, in-board on RIB2) and the jet-pump 66QM
- the right-wing fuel-manifold (adjacent to the check valves 36QM and 35QM, in-board on RIB2) and the jet-pump 69QM.
(f) The jet-pump (output/discharge) pipe-line(s), between the jet-pump 66QM (69QM) and the fuel discharge (outlet) adjacent to the intercell transfer valve 28QM (30QM) outboard of RIB15.
(g) Repair/replace all the unserviceable fuel pipes and connections AMM 28-00-00-000-001 and AMM 28-00-00-400-001.
(h) The fuel-pump suction valve AMM 28-21-42-000-001 and AMM 28-21-42-400-001.
(11) If the fuel spillage occurred with the fuel pumps set to ON (Post Flight Config) do:
(a) Examine the applicable
(b) If necessary, do Internal Fuel Leak Which Causes a Fuel Imbalance or a Discharge From a NACA Vent During Taxi or Flight (Ref. TSM TASK 28-21-00-810-825).
A. Procedure
(a) If the fuel spill is in the left wing:
If necessary, replace AMM 28-11-42-000-002 and AMM 28-11-42-400-002.
(3) Make sure that the applicable refuel (transfer) task, as follows, was/is complied with in all respects:
(5) Do the Inspection of the Tank Venting System AMM 28-12-00-200-001.
(6) On the opposite side wing to the fuel spillage, do a General Visual Inspection of NACA Vent Intake For Signs ofObstruction (blockage) AMM 28-12-47-200-001.
(7) Do an Inspection of the Overpressure Protectors (Wing and Vent Surge Tanks) AMM 28-12-41-200-003.
(8) If the fuel spillage was from the left side, do the Inspection of the Overpressure Protector 96QM AMM 28-12-41-200-002.
(9) Do the Operational Test of the Refuel System AMM 28-25-00-710-003.
(10) Do the Operational Test of the Defuel System AMM 28-25-00-710-002.
(11) Do the Operational Test of the Crossfeed Valve AMM 28-23-00-720-001.
(12) If the fuel spillage occurred with the fuel pumps set to ON (Post Flight Config) do:
(a) Examine the applicableengine fuel feed line, Air Release Valve and, if necessary, replace AMM 28-21-41-000-001 and AMM 28-21-41-400-001.
(b) If necessary, do Internal Fuel Leak Which Causes a Fuel Imbalance or a Discharge From a NACA Vent During Taxi or Flight (Ref. TSM TASK 28-21-00-810-825).
(13) Replace the fuel-pump suction valve AMM 28-21-42-000-001 and AMM 28-21-42-400-001.
NOTE: The tests listed here are a guide only.
They can be done in an order (any) best suited to:
If only a test is called for, take any resulting ECAM WARNING(s), failure message(s) and/or observation(s) and do the applicable trouble shooting.
(1) Do a check of the applicable float vent valve: They can be done in an order (any) best suited to:
- the local conditions in which the fuel spillage occurred
- the tools and equipment available.
If only a test is called for, take any resulting ECAM WARNING(s), failure message(s) and/or observation(s) and do the applicable trouble shooting.
(a) If the fuel spill is in the left wing:
- Do a visual inspection of the float vent valve 212QM for signs of damage. Make sure the valve moves easily through its full range of movement.
- If necessary, replace the VALVE-FLOAT VENT, LEFT WING [212QM] , AMM 28-12-43-000-003 and AMM 28-12-43-400-003.
- Do a visual inspection of the float vent valve 213QM for signs of damage. Make sure the valve moves easily through its full range of movement.
- If necessary, replace the VALVE-FLOAT VENT, RIGHT WING [213QM] , AMM 28-12-43-000-003 and AMM 28-12-43-400-003.
NOTE: In normal operation the clack valves in the RIB22 let the fuel that has entered the vent/surge tanks return to the related wing tank. The clack valves do not let fuel enter the vent/surge tanks from the wing tanks.
If the two (both) clack valves in the Rib 22 remain in the closed position the fuel level in the tank will increase because it cannot drain back to its related wing tank.
If, during these conditions, a fuel surge were to occur during the refuel, less fuel can be held in the vent/surge tank than if it was continuously drained and almost empty. This will increase the possibility of a fuel spillage because the usable capacity of the vent/surge tank has been reduced.
(a) Make sure that the clack valves are serviceable (have a full and free movement). If the two (both) clack valves in the Rib 22 remain in the closed position the fuel level in the tank will increase because it cannot drain back to its related wing tank.
If, during these conditions, a fuel surge were to occur during the refuel, less fuel can be held in the vent/surge tank than if it was continuously drained and almost empty. This will increase the possibility of a fuel spillage because the usable capacity of the vent/surge tank has been reduced.
If necessary, replace AMM 28-11-42-000-002 and AMM 28-11-42-400-002.
(3) Make sure that the applicable refuel (transfer) task, as follows, was/is complied with in all respects:
- Pressure Refuel with Automatic Control AMM 12-11-28-650-003
- Pressure Refuel with Manual Control AMM 12-11-28-650-004
- Pressure Refuel without Electric Power AMM 12-11-28-650-005
- Overwing (Gravity) Refuel AMM 12-11-28-650-006
- Fuel Transfer AMM 28-25-00-869-001.
(5) Do the Inspection of the Tank Venting System AMM 28-12-00-200-001.
(6) On the opposite side wing to the fuel spillage, do a General Visual Inspection of NACA Vent Intake For Signs of
(7) Do an Inspection of the Overpressure Protectors (Wing and Vent Surge Tanks) AMM 28-12-41-200-003.
(8) If the fuel spillage was from the left side, do the Inspection of the Overpressure Protector 96QM AMM 28-12-41-200-002.
(9) Do the Operational Test of the Refuel System AMM 28-25-00-710-003.
(10) Do the Operational Test of the Defuel System AMM 28-25-00-710-002.
(11) Do the Operational Test of the Crossfeed Valve AMM 28-23-00-720-001.
(12) If the fuel spillage occurred with the fuel pumps set to ON (Post Flight Config) do:
(a) Examine the applicable
(b) If necessary, do Internal Fuel Leak Which Causes a Fuel Imbalance or a Discharge From a NACA Vent During Taxi or Flight (Ref. TSM TASK 28-21-00-810-825).
(13) Replace the fuel-pump suction valve AMM 28-21-42-000-001 and AMM 28-21-42-400-001.