DOC AIRBUS | AMM A320FFUEL - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
1. General
Critical Design Configuration Control Limitations (CDCCL)
Some procedures identify a fuel system item that is in a category known as a Critical Design Configuration Control Limitation (CDCCL). This category is applicable to items that are identified as the possible source of ignition of fuel in a fuel tank.
You must keep CDCCL items in a serviceable condition. It is possible that damage, wear or changes to a CDCCL item can cause a fuel tank explosion.
CDCCL items are identified by a WARNING in the procedures where they occur. When a procedure identifies a CDCCL item, it is a mandatory condition that you do the instruction correctly and accurately as the procedure tells you.
Critical Design Configuration Control Limitations (CDCCL)
Some procedures identify a fuel system item that is in a category known as a Critical Design Configuration Control Limitation (CDCCL). This category is applicable to items that are identified as the possible source of ignition of fuel in a fuel tank.
You must keep CDCCL items in a serviceable condition. It is possible that damage, wear or changes to a CDCCL item can cause a fuel tank explosion.
CDCCL items are identified by a WARNING in the procedures where they occur. When a procedure identifies a CDCCL item, it is a mandatory condition that you do the instruction correctly and accurately as the procedure tells you.
A. Description
The fuel system:
The airworthiness requirements for each sub-system are identified in the related sub-system.
The fuel system:
The fuel system:
- Keeps the fuel in the main fuel tanks and the center (transfer) tank, which are open to atmosphere through the vent surge tanks
- Controls and supplies the fuel in the correct quantities to the fuel tanks during refuel operations
- Supplies the fuel to the engines for thrust and to cool
- Supplies the fuel to the Auxiliary Power Unit (APU)
- Controls the movement of the fuel out of the center (transfer) tank
- Supplies the fuel to cool, the excess fuel decreases the temperature of the engines and the oil of the Integrated Drive Generators
- Gives indications in the cockpit of the usual system operation
- Gives indications in the cockpit of the failures that could cause an unusual condition.
- keeps the fuel in the main fuel tanks and the center tank, which are open to atmosphere through the vent surge tanks
- controls and supplies the fuel in the correct quantities to the fuel tanks during refuel operations
- supplies the fuel to the engines for thrust and to cool
- supplies the fuel to the Auxiliary Power Unit (APU)
- supplies the fuel to cool, the excess fuel decreases the temperature of the engines and the Integrated Drive Generators oil
- gives indications in the cockpit of the usual system operation
- gives indications in the cockpit of the failures that could cause an unusual condition.
The airworthiness requirements for each sub-system are identified in the related sub-system.
The fuel system:
- Keeps the fuel in the fuel tanks, which are open to atmosphere through the vent surge tanks
- Controls and supplies the fuel in the correct quantities to the fuel tanks during refuel operations
- Supplies the fuel to the engines for thrust and to cool
- Supplies the fuel to the Auxiliary Power Unit (APU)
- Controls the movement of the fuel out of the center tank
- Controls the movement of the fuel from the Additional Center Tank(s) (ACT)(s) to the center tank
- Supplies the fuel to cool, the excess fuel decreases the temperature of the engines and the oil of the Integrated Drive Generators (IDG)
- Gives indications in the cockpit of the usual system operation
- Gives indications in the cockpit of the failures that could cause an unusual condition.
B. Description
Airworthiness Requirements
The airworthiness requirements for each sub-system are identified in the related sub-system.
The fuel system:
Airworthiness Requirements
The airworthiness requirements for each sub-system are identified in the related sub-system.
The fuel system:
- keeps the fuel in the fuel tanks, which are open to atmosphere through the vent surge tanks
- controls and supplies the fuel in the correct quantities to the fuel tanks during refuel operations
- supplies the fuel to the engines for thrust and to cool
- supplies the fuel to the Auxiliary Power Unit (APU)
- controls the movement of the fuel out of the center tank
- controls the movement of the fuel from the Additional Center Tank ACT1 (if installed) to the center tank
- controls the movement of the fuel from the Additional Center Tank ACT2 (if installed) to the center tank
- supplies the fuel to cool, the excess fuel decreases the temperature of the engines and the Integrated Drive Generators (IDG) oil
- gives indications in the cockpit of the usual system operation
- gives indications in the cockpit of the failures that could cause an unusual condition.
2. Component Location
Fuel System - Wing and Center Tank ** ON A/C NOT FOR ALL
Fuel System - Wing and Center Tank ** ON A/C NOT FOR ALL
Fuel System - Wing and Center Tank (with ACT(s) installed) ** ON A/C NOT FOR ALL
Fuel System - Wing and Center Tank ** ON A/C NOT FOR ALL
Fuel System - Wing and Center Tank with ACT Provision ** ON A/C NOT FOR ALL
Fuel System Control Switches ** ON A/C NOT FOR ALL
Fuel System Control Switches ** ON A/C NOT FOR ALL
Fuel System Control Switches ** ON A/C NOT FOR ALL
Fuel System - Control Switches ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL Fuel System - Wing and Center Tank ** ON A/C NOT FOR ALL Fuel System - Wing and Center Tank ** ON A/C NOT FOR ALL Fuel System - Wing and Center Tank (with ACT(s) installed) ** ON A/C NOT FOR ALL Fuel System - Wing and Center Tank ** ON A/C NOT FOR ALL Fuel System - Wing and Center Tank with ACT Provision ** ON A/C NOT FOR ALL Fuel System Control Switches ** ON A/C NOT FOR ALL Fuel System Control Switches ** ON A/C NOT FOR ALL Fuel System Control Switches ** ON A/C NOT FOR ALL Fuel System - Control Switches ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL 3. System Description
A. Storage (Ref. 28-10-00)
The storage system:
The storage system:
- contains the fuel for the engines and the APU
- helps to protect the fuel system against fire
- gets the warm fuel from the IDGs and returns it to the wing tanks
- keeps the air pressure in the fuel system near to the external air pressure.
(1) Tanks (Ref. AMM D/O 28-11-00-00)
The fuel is kept in the fuel tanks that follow:
Each wing contains a vent surge tank. The vent surge tanks are installed outboard of each wing tank.
The vent surge tanks temporarily hold the fuel so that leakage does not occur during:
All the fuel tanks and the surge tanks have water drain valves at their lowest point.
After a refuel operation to the maximum tank capacity, the fuel can expand 2% (20 deg.C (36 deg.F) temperature increase) without leakage at the refuel attitude and during:
The fuel is kept in the fuel tanks that follow:
- the LH wing tank
- the RH wing tank
- the center tank (if installed)
- the Additional Center Tank(s) (ACT(s)) (if installed).
Each wing contains a vent surge tank. The vent surge tanks are installed outboard of each wing tank.
The vent surge tanks temporarily hold the fuel so that leakage does not occur during:
- aircraft movement on the ground
- aircraft rotation at take-off.
All the fuel tanks and the surge tanks have water drain valves at their lowest point.
After a refuel operation to the maximum tank capacity, the fuel can expand 2% (20 deg.C (36 deg.F) temperature increase) without leakage at the refuel attitude and during:
- subsequent towing
- aircraft movement on the ground
- take-off.
(2) Tank Venting System (Ref. AMM D/O 28-12-00-00)
The tank venting system makes sure that the air pressure in the fuel tanks (and the vent surge tanks) keeps near to the external air pressure. The system prevents a large difference between these pressures, which can cause damage to the fuel tank/aircraft structure. This is most important:
The vent surge tanks keep their related fuel tank open to the external air pressure. That is:
If a blockage occurs to the flow of air through the vent surge tank, a burst disk keeps the pressure to a specified limit.
The flame arrestors in the vent system intakes give protection against ground fires. The fuel system is protected from the effects of lightning through:
The tank venting system makes sure that the air pressure in the fuel tanks (and the vent surge tanks) keeps near to the external air pressure. The system prevents a large difference between these pressures, which can cause damage to the fuel tank/aircraft structure. This is most important:
- during the refuel or defuel operations
- when the aircraft climbs or descends.
The vent surge tanks keep their related fuel tank open to the external air pressure. That is:
- the LH vent surge tank for the LH wing tank and the center tank (if installed)
- the RH vent surge tank for the RH wing tank.
If a blockage occurs to the flow of air through the vent surge tank, a burst disk keeps the pressure to a specified limit.
The flame arrestors in the vent system intakes give protection against ground fires. The fuel system is protected from the effects of lightning through:
- the position of the vent intakes (which are outside lightning-strike zones 1 and 2 in the wing)
- the thickness of the wing skins.
(3) Tank Venting System (Ref. AMM D/O 28-12-00-00)
The tank venting system makes sure that the air pressure in the fuel tanks (and the vent surge tanks) keeps near to the external air pressure. The system prevents a large difference between these pressures, which can cause damage to the fuel tank/aircraft structure. This is most important:
Each vent surge tank keeps its related fuel tank(s) open to the external air pressure. That is:
The tank venting system makes sure that the air pressure in the fuel tanks (and the vent surge tanks) keeps near to the external air pressure. The system prevents a large difference between these pressures, which can cause damage to the fuel tank/aircraft structure. This is most important:
- during the refuel or defuel operations
- when the aircraft climbs or descends.
Each vent surge tank keeps its related fuel tank(s) open to the external air pressure. That is:
- the LH vent surge tank for the LH wing tank, the center tank, and the ACT(S) (if installed)
NOTE: The ACT(S) (if installed) are not open to external air pressure when the ACT pressure transfer system operates (Ref. AMM D/O 28-28-00-00).
- the RH vent surge tank for the RH wing tank.
If a blockage occurs to the flow of air through the vent surge tank, a burst disk keeps the pressure to a specified limit.
The flame arrestors in the vent system intakes give protection against ground fires. The fuel system is protected from the effects of lightning through: - the position of the vent intakes (which are outside lightning-strike zones 1 and 2 in the wing)
- the thickness of the wing skins.
(4) The Tank Venting System (Ref. AMM D/O 28-12-00-00)
The tank venting system makes sure that the air pressure in the fuel tanks (and the vent surge tanks) keeps near to the external air pressure. The system prevents a large difference between the air pressure and the external air pressure which can cause damage to the fuel tank/aircraft structure. This is most important:
The ACT venting system (Ref. AMM D/O 28-12-00-00) connects the ACT(s) (when it is installed) to the tank venting system.
Each vent surge tank keeps its related fuel tank(s) open to the external air pressure.
The flame arrestors in the vent system intakes give protection against ground fires. The fuel system has a protected from the effects of lightning through:
The tank venting system makes sure that the air pressure in the fuel tanks (and the vent surge tanks) keeps near to the external air pressure. The system prevents a large difference between the air pressure and the external air pressure which can cause damage to the fuel tank/aircraft structure. This is most important:
- During the refuel or defuel operations
- When the aircraft climbs or descends.
The ACT venting system (Ref. AMM D/O 28-12-00-00) connects the ACT(s) (when it is installed) to the tank venting system.
Each vent surge tank keeps its related fuel tank(s) open to the external air pressure.
- The LH vent surge tank for the LH wing tank, the center tank and the ACT(s) (if installed)
- The RH vent surge tank for the RH wing tank.
NOTE: The ACT(s) (is)are not open to external air pressure when the ACT transfer system operates (Ref. AMM D/O 28-28-00-00).
If there is a blockage in the vent surge tank that prevents airflow, a burst disk keeps the pressure to a specified limit. The flame arrestors in the vent system intakes give protection against ground fires. The fuel system has a protected from the effects of lightning through:
- The position of the vent intakes (which are outside lightning-strike zones 1 and 2 in the wing)
- The thickness of the wing skins.
(5) ACT venting System (Ref. AMM D/O 28-12-00-00)
The ACT venting system is connected to the center tank and is open to the external air pressure. Fuel or fuel gas in the ACT venting system pipework is released into the center tank. When the ACT/s is/are not installed, the related pipework in the fuselage is sealed with caps.
The ACT/s is/are isolated from the center tank in flight so that they can be pressurized for fuel transfer (Ref. AMM D/O 28-28-00-00). An electrically operated vent valve is installed in each ACT. When the fuel transfer system operates, the vent valves automatically close and air from the cabin pressure control system pressurizes the ACT/s for fuel transfer.
The ACT venting system is connected to the center tank and is open to the external air pressure. Fuel or fuel gas in the ACT venting system pipework is released into the center tank. When the ACT/s is/are not installed, the related pipework in the fuselage is sealed with caps.
The ACT/s is/are isolated from the center tank in flight so that they can be pressurized for fuel transfer (Ref. AMM D/O 28-28-00-00). An electrically operated vent valve is installed in each ACT. When the fuel transfer system operates, the vent valves automatically close and air from the cabin pressure control system pressurizes the ACT/s for fuel transfer.
(6) Center Tank External Ventilating System (Ref. AMM D/O 28-13-00-00)
The center-tank external ventilating-system makes sure that fuel and/or fuel gas (that comes out of the center tank) does not go into the air conditioning system (Ref. AMM D/O 21-00-00-00).
The center-tank external ventilating-system makes sure that fuel and/or fuel gas (that comes out of the center tank) does not go into the air conditioning system (Ref. AMM D/O 21-00-00-00).
(7) intercell Transfer System (Ref. AMM D/O 28-15-00-00)
The intercell transfer system controls the movement of fuel from the wing-tank outer cell to the wing-tank inner cell. Each wing tank has two intercell transfer valves in the bottom of the RIB15. Each intercell transfer valve has a related actuator that controls the position of the valve. The Fuel Level Sensing Control Units (FLSCUs) (Ref. AMM D/O 28-46-00-00), give an open or shut signal to the actuators of the intercell transfer valve. The FLSCUs will signal the actuators to open their related valves when the low level sensors of the related wing tank inner cell become dry.
The intercell transfer system controls the movement of fuel from the wing-tank outer cell to the wing-tank inner cell. Each wing tank has two intercell transfer valves in the bottom of the RIB15. Each intercell transfer valve has a related actuator that controls the position of the valve. The Fuel Level Sensing Control Units (FLSCUs) (Ref. AMM D/O 28-46-00-00), give an open or shut signal to the actuators of the intercell transfer valve. The FLSCUs will signal the actuators to open their related valves when the low level sensors of the related wing tank inner cell become dry.
(8) Fuel Recirculation for Cooling (Recirculation System) (Ref. AMM D/O 28-16-00-00)
Part of the fuel supply to each engine is used for the IDG cooling-system (Ref. AMM D/O 24-21-00-00). During the oil cooling process this fuel becomes warm. The recirculation system returns the warm fuel from the IDG cooling system to the wing tank. The Full Authority Digital Engine Control (FADEC) system (Ref. AMM D/O 73-20-00-00) stops the recirculation system if:
Part of the fuel supply to each engine is used for the IDG cooling-system (Ref. AMM D/O 24-21-00-00). During the oil cooling process this fuel becomes warm. The recirculation system returns the warm fuel from the IDG cooling system to the wing tank. The Full Authority Digital Engine Control (FADEC) system (Ref. AMM D/O 73-20-00-00) stops the recirculation system if:
- the fuel temperature increases to a high level
- the fuel flow rate to the engine is at a high level
- the engines have a gravity fuel feed only
- the fuel level in the wing tanks is low
- the fuel goes into a vent surge tank.
B. Distribution (Ref. 28-20-00)
The distribution system makes sure that the fuel:
The distribution system makes sure that the fuel:
The distribution system makes sure that the fuel:
The distribution system makes sure that the fuel:
The distribution system makes sure that the fuel:
- is supplied to the two engines during all flight conditions
- is supplied to the APU
- can be isolated from an engine or the APU when necessary
- is in the correct (and safe) configuration for flight
- can be moved from the center (transfer) tank to the related wing tank as necessary
- can be supplied to and removed from the aircraft.
The distribution system makes sure that the fuel:
- is supplied to the two engines during all flight conditions
- is supplied to the APU
- can be isolated from an engine or the APU when necessary
- is in the correct (and safe) configuration for flight
- can be supplied to, and removed from, the aircraft.
The distribution system makes sure that the fuel:
- is supplied to the two engines during all flight conditions
- is supplied to the APU
- can be isolated from an engine or the APU when necessary
- is in the correct (and safe) configuration for flight
- can be moved from tank to tank as necessary
- can be moved from the center (transfer) tank to the related wing tank as necessary
- can be moved from the ACT system to the center (transfer) tank as necessary
- can be supplied to and removed from the aircraft.
The distribution system makes sure that the fuel:
- Is supplied to the two engines during all flight conditions
- Is supplied to the APU
- Can be isolated from an engine or the APU when necessary
- Is in the correct (and safe) configuration for flight
- Can be moved from wing tank to wing tank as necessary
- Can be moved from the center tank to the wing tanks as necessary
- Can be moved from the ACT(s) (if installed) to the center tank as necessary
- Can be supplied to and removed from the aircraft.
C. Distribution (Ref. 28-20-00)
(1) Main Fuel Pump System (Ref. AMM D/O 28-21-00-00)
There are two fuel pumps in each wing tank. The fuel pumps operate together to supply fuel to their related engine. If one fuel pump has a failure, or is set to OFF, the other continues to supply fuel to its related engine. If the crossfeed system (Ref. AMM D/O 28-23-00-00) is used, the fuel pumps can also supply fuel to the other engine.
The fuel pumps also take fuel from the wing tanks and pass it through the jet pumps in the center (transfer) tank. This flow of fuel causes a suction pressure in the jet pumps. This suction pressure removes the fuel from the center tank and moves it to the related wing tank (Ref. AMM D/O 28-26-00-00).
There are two fuel pumps in each wing tank. The fuel pumps operate together to supply fuel to their related engine. If one fuel pump has a failure, or is set to OFF, the other continues to supply fuel to its related engine. If the crossfeed system (Ref. AMM D/O 28-23-00-00) is used, the fuel pumps can also supply fuel to the other engine.
The fuel pumps also take fuel from the wing tanks and pass it through the jet pumps in the center (transfer) tank. This flow of fuel causes a suction pressure in the jet pumps. This suction pressure removes the fuel from the center tank and moves it to the related wing tank (Ref. AMM D/O 28-26-00-00).
(2) Main Fuel Pump System (Ref. AMM D/O 28-21-00-00)
There are two fuel pumps in each wing tank and two in the center tank. The fuel pumps operate together to supply fuel to their related engine. Fuel is supplied to the engines in the sequence:
The wing tank fuel pumps also take fuel from the related wing tank and pass it through two jet pumps in the related wing tank outer cell. This flow of fuel causes the jet pumps to remove the fuel from the surge tank and the bottom of the wing tank outer cell. This fuel is then moved to one of the related intercell transfer valves.
There are two fuel pumps in each wing tank and two in the center tank. The fuel pumps operate together to supply fuel to their related engine. Fuel is supplied to the engines in the sequence:
- center tank fuel
- wing tank fuel.
The wing tank fuel pumps also take fuel from the related wing tank and pass it through two jet pumps in the related wing tank outer cell. This flow of fuel causes the jet pumps to remove the fuel from the surge tank and the bottom of the wing tank outer cell. This fuel is then moved to one of the related intercell transfer valves.
(3) APU Fuel-Pump System (Ref. AMM D/O 28-22-00-00)
The APU fuel pump is on the rear spar of the center wing section. The APU fuel pump supplies the fuel to the APU (Ref. AMM D/O 49-30-00-00). The APU fuel pump uses the fuel supplied from the LH wing tank.
The APU fuel pump is on the rear spar of the center wing section. The APU fuel pump supplies the fuel to the APU (Ref. AMM D/O 49-30-00-00). The APU fuel pump uses the fuel supplied from the LH wing tank.
(4) Crossfeed System (Ref. AMM D/O 28-23-00-00)
The valve of the crossfeed system is usually closed, and in this configuration it divides the main fuel pump system (Ref. AMM D/O 28-21-00-00) into two parts (one part for each engine). When the crossfeed valve is open, the two fuel supplies are connected together. Thus the two engines can be supplied with fuel from one of the wings or from the two wings.
The valve of the crossfeed system is usually closed, and in this configuration it divides the main fuel pump system (Ref. AMM D/O 28-21-00-00) into two parts (one part for each engine). When the crossfeed valve is open, the two fuel supplies are connected together. Thus the two engines can be supplied with fuel from one of the wings or from the two wings.
(5) Engine LP Fuel Shut Off (Ref. AMM D/O 28-24-00-00)
The fuel flow to each engine goes through a related Low Pressure (LP) fuel valve. When necessary the LP valve isolates its engine from the fuel. The operation of the LP valve is controlled by:
The fuel flow to each engine goes through a related Low Pressure (LP) fuel valve. When necessary the LP valve isolates its engine from the fuel. The operation of the LP valve is controlled by:
- the related ENG MASTER switch (Ref. AMM D/O 76-12-00-00)
- the related engine FIRE PUSH switch (Ref. AMM D/O 26-12-00-00).
(6) Refuel/Defuel System (Ref. AMM D/O 28-25-00-00)
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft.
It is controlled by the:
The control panels 800VU and 801VU include indicators and selector switches.
The applicable indicators and switches on control panel 801VU do not operate if there is no ACT installed.
A single refuel/defuel is the interface between the fuel tanks and the external fuel supply.
To fill the fuel tanks to their maximum capacity, the aircraft must be level.
It is possible to refuel the aircraft when it is at 2 degrees, or less, from level (but it is not possible to get the maximum capacity).
The fuel supply to each fuel tank during an automatic refuel is controlled by the Fuel Quantity Indicating Computer (FQIC) (Ref. AMM D/O 28-42-00-00).
The fuel supply to each fuel tank during a manual refuel is controlled by:
Defuel
The main fuel pump system (Ref. AMM D/O 28-21-00-00) is used to defuel the aircraft.
The pumps remove the fuel from the related wing tank and supply it to the refuel/defuel coupling.
The defuel/transfer valve and the crossfeed valve (Ref. AMM D/O 28-23-00-00) must be open to defuel the aircraft.
Defuel of the Center (Transfer) Tank (if installed)
To defuel the center (transfer) tank the main transfer system (Ref. AMM D/O 28-26-00-00) must be used to move the fuel to the related wing tank.
Defuel of the ACT(s) (if installed)
Fuel in the ACT(s) must be moved to the center tank. The fuel is moved by operation of the transfer pump in the ACT transfer system (Ref. AMM D/O 28-28-00-00).
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft.
It is controlled by the:
- control panel 800VU
- control panel 801VU (if installed)
- fuel quantity preselector 5QT
- fuel quantity indicator 6QT (if installed)
- cockpit fuel quantity preselector 10QT (if installed)
The control panels 800VU and 801VU include indicators and selector switches.
The applicable indicators and switches on control panel 801VU do not operate if there is no ACT installed.
A single refuel/defuel is the interface between the fuel tanks and the external fuel supply.
To fill the fuel tanks to their maximum capacity, the aircraft must be level.
It is possible to refuel the aircraft when it is at 2 degrees, or less, from level (but it is not possible to get the maximum capacity).
The fuel supply to each fuel tank during an automatic refuel is controlled by the Fuel Quantity Indicating Computer (FQIC) (Ref. AMM D/O 28-42-00-00).
The fuel supply to each fuel tank during a manual refuel is controlled by:
- the refuel/defuel control panel 800VU, for the wing tanks (and center tanks if installed)
- the refuel/defuel control panel 801VU, for the ACT(s) (if installed).
Defuel
The main fuel pump system (Ref. AMM D/O 28-21-00-00) is used to defuel the aircraft.
The pumps remove the fuel from the related wing tank and supply it to the refuel/defuel coupling.
The defuel/transfer valve and the crossfeed valve (Ref. AMM D/O 28-23-00-00) must be open to defuel the aircraft.
Defuel of the Center (Transfer) Tank (if installed)
To defuel the center (transfer) tank the main transfer system (Ref. AMM D/O 28-26-00-00) must be used to move the fuel to the related wing tank.
Defuel of the ACT(s) (if installed)
Fuel in the ACT(s) must be moved to the center tank. The fuel is moved by operation of the transfer pump in the ACT transfer system (Ref. AMM D/O 28-28-00-00).
(7) Refuel/Defuel System (Ref. AMM D/O 28-25-00-00)
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft.
It is controlled by the:
The control panels 800VU and 801VU include indicators and selector switches.
The applicable indicators and switches on the control panel 801VU do not operate if there is no ACT installed.
A single refuel/defuel is the interface between the fuel tanks and the external fuel supply.
To fill the fuel tanks to their maximum capacity, the aircraft must be level.
It is possible to refuel the aircraft when it is at 2 degrees, or less, from level (but it is not possible to get the maximum capacity).
The fuel supply to the wing and center tanks during an automatic refuel is controlled by the Fuel-Quantity Indicating Computer (FQIC) (Ref. AMM D/O 28-42-00-00).
Fuel supply to the installed ACT(s) during an automatic refuel is controlled by the Auxiliary Fuel-Management Computer (AFMC) (Ref. AMM D/O 28-51-00-00).
During a manual refuel, the fuel supply to each fuel tank is controlled on:
Defuel
The main fuel-pump system (Ref. AMM D/O 28-21-00-00) is used to defuel the aircraft.
The pumps remove the fuel from the related wing tank and supply it to the refuel/defuel coupling.
The defuel/transfer valve and the crossfeed valve (Ref. AMM D/O 28-23-00-00) must be open to defuel the aircraft.
Defuel of the Center (Transfer) Tank (if installed)
To defuel the center (transfer) tank the main transfer system (Ref. AMM D/O 28-26-00-00) must be used to move the fuel to the related wing tank.
The ACT transfer system (Ref. AMM D/O 28-28-00-00) is used to defuel the ACT(s) (when installed). The ACT transfer pump removes fuel from the installed ACT(s) and transfers it to the center tank. The pump operates when the MODE SEL pushbutton switch (41QH) is pushed in and the rotary selector (36QH) is set. These switches are on the ACT control panel 28VU in the cockpit.
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft.
It is controlled by the:
- Control panel 800VU
- Control panel 801VU
- Fuel quantity preselector 5QT
- Fuel quantity indicator 6QT.
The control panels 800VU and 801VU include indicators and selector switches.
The applicable indicators and switches on the control panel 801VU do not operate if there is no ACT installed.
A single refuel/defuel is the interface between the fuel tanks and the external fuel supply.
To fill the fuel tanks to their maximum capacity, the aircraft must be level.
It is possible to refuel the aircraft when it is at 2 degrees, or less, from level (but it is not possible to get the maximum capacity).
The fuel supply to the wing and center tanks during an automatic refuel is controlled by the Fuel-Quantity Indicating Computer (FQIC) (Ref. AMM D/O 28-42-00-00).
Fuel supply to the installed ACT(s) during an automatic refuel is controlled by the Auxiliary Fuel-Management Computer (AFMC) (Ref. AMM D/O 28-51-00-00).
During a manual refuel, the fuel supply to each fuel tank is controlled on:
- The refuel/defuel control panel 800VU, for the wing and center tanks
- The refuel/defuel control panel 801VU, for the installed ACT(s).
Defuel
The main fuel-pump system (Ref. AMM D/O 28-21-00-00) is used to defuel the aircraft.
The pumps remove the fuel from the related wing tank and supply it to the refuel/defuel coupling.
The defuel/transfer valve and the crossfeed valve (Ref. AMM D/O 28-23-00-00) must be open to defuel the aircraft.
Defuel of the Center (Transfer) Tank (if installed)
To defuel the center (transfer) tank the main transfer system (Ref. AMM D/O 28-26-00-00) must be used to move the fuel to the related wing tank.
The ACT transfer system (Ref. AMM D/O 28-28-00-00) is used to defuel the ACT(s) (when installed). The ACT transfer pump removes fuel from the installed ACT(s) and transfers it to the center tank. The pump operates when the MODE SEL pushbutton switch (41QH) is pushed in and the rotary selector (36QH) is set. These switches are on the ACT control panel 28VU in the cockpit.
(8) Main Transfer System (Ref. AMM D/O 28-26-00-00)
The main transfer system controls the flow of fuel from the center (transfer) tank to the two wing tanks. The system uses jet pumps that are supplied with fuel from the main fuel pump system (Ref. AMM D/O 28-21-00-00). The fuel goes through a nozzle in the jet pump to produce a suction. This suction removes the fuel from the center (transfer) tank and then moves it to the related wing tank. The main transfer system also uses gravity to move the fuel from the center (transfer) tank to the wing tanks. Gravity movement of fuel occurs when the fuel level in the center (transfer) tank is higher than that in the wing tanks. The Fuel Level Sensing Control Units (FLSCUs) automatically control the transfer system, but if necessary, the crew can manually control it from the cockpit.
The main transfer system controls the flow of fuel from the center (transfer) tank to the two wing tanks. The system uses jet pumps that are supplied with fuel from the main fuel pump system (Ref. AMM D/O 28-21-00-00). The fuel goes through a nozzle in the jet pump to produce a suction. This suction removes the fuel from the center (transfer) tank and then moves it to the related wing tank. The main transfer system also uses gravity to move the fuel from the center (transfer) tank to the wing tanks. Gravity movement of fuel occurs when the fuel level in the center (transfer) tank is higher than that in the wing tanks. The Fuel Level Sensing Control Units (FLSCUs) automatically control the transfer system, but if necessary, the crew can manually control it from the cockpit.
(9) ACT Transfer System (Ref. AMM D/O 28-28-00-00)
The ACT transfer system controls the fuel transfer from the installed ACT/s to the center tank. Pipes connect the ACT/s to:
When the aircraft is on the ground, fuel in the ACT/s can be transferred to the center tank by operation of the ACT transfer pump. The pump is controlled by the ACT AUTO pushbutton switch (P/BSW) on the cockpit overhead panel 40VU. When the P/BSW is pushed in (FWD), the ACT transfer pump operates and the ACT transfer valve and the ACT inlet valve open. Fuel transfer will start and continue until the ACT AUTO P/BSW is released out. The transfer of fuel will also stop if the HI LVL sensor in the center tank becomes wet.
The ACT transfer system controls the fuel transfer from the installed ACT/s to the center tank. Pipes connect the ACT/s to:
- the center tank
- the refuel/defuel gallery (in the center tank)
- the cabin pressure control system.
When the aircraft is on the ground, fuel in the ACT/s can be transferred to the center tank by operation of the ACT transfer pump. The pump is controlled by the ACT AUTO pushbutton switch (P/BSW) on the cockpit overhead panel 40VU. When the P/BSW is pushed in (FWD), the ACT transfer pump operates and the ACT transfer valve and the ACT inlet valve open. Fuel transfer will start and continue until the ACT AUTO P/BSW is released out. The transfer of fuel will also stop if the HI LVL sensor in the center tank becomes wet.
NOTE: To move fuel from the ACT to the center tank on the ground the FUELING BUS (501PP) must be powered (access panel door 192MB must be open). This causes the center tank high level sensor to be powered. When the center tank high level sensor is wet (or not powered) it is not possible to move fuel from the ACT.
(10) APU LP Fuel Shut Off (Ref. AMM D/O 28-29-00-00)
The APU LP fuel shut off valve controls the fuel supply from the fuel tank to the APU. When necessary the valve isolates the APU from its fuel supply. The operation of the APU LP valve is controlled by:
The APU LP fuel shut off valve controls the fuel supply from the fuel tank to the APU. When necessary the valve isolates the APU from its fuel supply. The operation of the APU LP valve is controlled by:
- the APU MASTER SW (Ref. AMM D/O 49-42-00-00)
- the APU SHUT OFF switch (Ref. AMM D/O 49-62-00-00)
- the APU FIRE switch (Ref. AMM D/O 26-13-00-00).
D. Indicating (Ref. 28-40-00)
The indicating system has:
The indicating system has:
- the Fuel Quantity Indicating (FQI) system, which gives separate and total fuel quantity indications
- the Magnetic Level Indicators (MLI), a secondary system used to estimate the fuel quantity when the aircraft is on the ground
- the tank level sensing, which gives indications and warnings when the fuel is at specified levels
- the fuel temperature measurement, which gives continuous temperature indications and warnings when the fuel temperature is at specified levels.
(1) Quantity Indicating (Ref. AMM D/O 28-42-00-00)
The FQI system measures the total quantity of fuel in the range unusable to overflow. It gives indications for these fuel tanks:
The FQIC monitors a diode within the probes 22QT1(22QT2) and 33QT1(33QT2) in the wing tanks. The FQIC uses signal conditioning to calculate the temperature of the fuel adjacent to these diodes. The fuel temperature is displayed on the System Display (SD) FUEL Page.
The FQI system measures the total quantity of fuel in the range unusable to overflow. It gives indications for these fuel tanks:
- the LH and RH wing tanks
- the center tank (if installed)
- the ACT(s) (if installed).
The system has FQI probes that the FQIC monitors. The FQIC uses signal conditioning to calculate the quantity of fuel in each fuel tank. The FQIC gives fuel quantity data to: - the Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) FUEL Page, which together make up the ECAM
- the multi-tank fuel quantity indicator (6QT) (if installed)
- the fuel quantity preselector (5QT)
- the cockpit preselector (10QT) (if installed).
The FQIC monitors a diode within the probes 22QT1(22QT2) and 33QT1(33QT2) in the wing tanks. The FQIC uses signal conditioning to calculate the temperature of the fuel adjacent to these diodes. The fuel temperature is displayed on the System Display (SD) FUEL Page.
(2) Quantity Indicating (Ref. AMM D/O 28-42-00-00)
The FQI system measures the total quantity of fuel in the range unusable to overflow. It gives indications for these fuel tanks:
Two temperature sensors are installed on one of the FQI probes in each wing tank. The FQIC uses signal conditioning to calculate the temperature of the fuel adjacent to these sensors. The fuel temperature is displayed on the System Display (SD) FUEL Page.
The FQI system measures the total quantity of fuel in the range unusable to overflow. It gives indications for these fuel tanks:
- the LH and RH wing tanks
- the center tank
- the ACT(s) (if installed).
The system has FQI probes that the FQIC monitors. The FQIC uses signal conditioning to calculate the quantity of fuel in each fuel tank. The FQIC gives fuel quantity data to: - the Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) FUEL Page, which together make up the ECAM
- the multi-tank fuel quantity indicator (6QT) (if installed)
- the fuel quantity preselector (5QT)
- the cockpit preselector (10QT) (if installed).
Two temperature sensors are installed on one of the FQI probes in each wing tank. The FQIC uses signal conditioning to calculate the temperature of the fuel adjacent to these sensors. The fuel temperature is displayed on the System Display (SD) FUEL Page.
(3) Quantity Indicating (Ref. AMM D/O 28-42-00-00)
The FQI system measures the total quantity of fuel in the range unusable to overflow. It gives indications for these fuel tanks:
The system has fuel quantity probes in:
All fuel quantity data from the FQIC goes to the AFMC. The AFMC gives fuel quantity data to:
The FQI system measures the total quantity of fuel in the range unusable to overflow. It gives indications for these fuel tanks:
- The LH and RH wing tanks
- The center tank
- The ACT(s) (if installed).
The system has fuel quantity probes in:
- The wing and center tanks
- The installed ACT(s).
All fuel quantity data from the FQIC goes to the AFMC. The AFMC gives fuel quantity data to:
- The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) FUEL Page, which together make up the ECAM
- The multi-tank fuel quantity indicator (6QT)
- The fuel quantity preselector (5QT).
(4) Magnetic Level Indicators (Ref. AMM D/O 28-43-00-00)
The MLIs are a secondary direct-reading system used to calculate the fuel quantity in the LH wing, RH wing and center tanks (when the A/C is on the ground). It is not necessary to have electrical power to use the indicators. The combined MLI indications, aircraft attitude and fuel relative density, are converted with tables (Ref. 12-11-28) to give the amount of fuel in each tank.
The MLIs are a secondary direct-reading system used to calculate the fuel quantity in the LH wing, RH wing and center tanks (when the A/C is on the ground). It is not necessary to have electrical power to use the indicators. The combined MLI indications, aircraft attitude and fuel relative density, are converted with tables (Ref. 12-11-28) to give the amount of fuel in each tank.
(5) Tank Level Sensing (Ref. AMM D/O 28-46-00-00)
The tank level sensing system monitors the level of fuel in:
The system has level sensors that the FLSCUs continuously monitor. The FLSCUs uses signal conditioning to find if the sensor is wet or dry. The FLSCUs use the fuel level data to:
The tank level sensing system monitors the level of fuel in:
- the LH(RH) surge tank
- the LH(RH) wing tank
- the center tank
- the ACT(s) (if installed).
The system has level sensors that the FLSCUs continuously monitor. The FLSCUs uses signal conditioning to find if the sensor is wet or dry. The FLSCUs use the fuel level data to:
- control the operation of the intercell transfer system (Ref. AMM D/O 28-15-00-00)
- control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00)
- control the operation of the main fuel pump system (Ref. AMM D/O 28-21-00-00)
- transmit fuel level data to the ACT transfer-control circuit (Ref. AMM D/O 28-28-00-00) (if installed)
- transmit fuel level warnings to the Engine/Warning Display (EWD) (Ref. 31-66-00)
- control high level shut-off for automatic and manual refuel (Ref. AMM D/O 28-25-00-00).
The tank level sensing system has temperature sensors in the wing tanks. The FLSCU uses signal conditioning to calculate the temperature of the fuel adjacent to the sensor.
The FLSCU uses the temperature data from the wing tanks to control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00).
(6) Tank Level Sensing (Ref. AMM D/O 28-46-00-00)
The tank level sensing system monitors the level of fuel in:
The system has level sensors that the FLSCUs continuously monitor. The FLSCUs uses signal conditioning to find if the sensor is wet or dry. The FLSCUs use the fuel level data to:
The tank level sensing system monitors the level of fuel in:
- the LH(RH) surge tank
- the LH(RH) wing tank
- the center tank
- the ACT(s) (if installed).
The system has level sensors that the FLSCUs continuously monitor. The FLSCUs uses signal conditioning to find if the sensor is wet or dry. The FLSCUs use the fuel level data to:
- control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00)
- control the operation of the main transfer system (Ref. AMM D/O 28-26-00-00)
- transmit fuel level data to the ACT transfer-control circuit (Ref. AMM D/O 28-28-00-00) (if installed)
- transmit fuel level warnings to the Engine/Warning Display (EWD) (Ref. 31-66-00)
- control high level shut-off for automatic and manual refuel (Ref. AMM D/O 28-25-00-00).
The tank level sensing system has temperature sensors in the wing tanks. The FLSCU uses signal conditioning to calculate the temperature of the fuel adjacent to the sensor.
The FLSCU uses the temperature data from the wing tanks to control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00).
(7) Tank Level Sensing (Ref. AMM D/O 28-46-00-00)
The tank level sensing system monitors the level of fuel in:
The system has level sensors that the FLSCUs continuously monitor. The FLSCUs uses signal conditioning to find if the sensor is wet or dry. The FLSCUs use the fuel level data to:
The tank level sensing system monitors the level of fuel in:
- The LH(RH) surge tank
- The LH(RH) wing tank
- The center tank
- The ACT(s) (if installed).
The system has level sensors that the FLSCUs continuously monitor. The FLSCUs uses signal conditioning to find if the sensor is wet or dry. The FLSCUs use the fuel level data to:
- Control the operation of the intercell transfer system (Ref. AMM D/O 28-15-00-00)
- Control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00)
- Control the operation of the main transfer system (Ref. AMM D/O 28-26-00-00)
- Transmit fuel level data to the ACT transfer-control circuit (Ref. AMM D/O 28-28-00-00) (if installed)
- Transmit fuel level warnings to the Engine/Warning Display (EWD) (Ref. 31-66-00)
- Control high level shut-off for automatic and manual refuel (Ref. AMM D/O 28-25-00-00).
The tank level sensing system has temperature sensors in the wing tanks. The FLSCU uses signal conditioning to calculate the temperature of the fuel adjacent to the sensor.
The FLSCU uses the temperature data from the wing tanks to control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00).
(8) Tank Level Sensing (Ref. AMM D/O 28-46-00-00)
The tank level sensing system monitors the level of fuel in:
The system has level sensors in the wing and center tanks that the FLSCUs continuously monitor. The FLSCUs uses signal conditioning to find if the sensors are wet or dry. The FLSCUs use the fuel level data to:
When the ACT(s) is(are) installed, the Auxiliary Level Sense Control Unit (ALSCU) monitors level sensors in the ACT(s). The ALSCU also uses signal conditioning to find if the sensors are wet or dry.
When the ACT(s) is(are) installed the tank level sensing system gives discrete outputs to:
The tank level sensing system has temperature sensors in the wing tanks. The FLSCU uses signal conditioning to calculate the temperature of the fuel adjacent to the sensor.
The FLSCU uses the temperature data from the wing tanks to control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00).
The tank level sensing system monitors the level of fuel in:
- The LH(RH) surge tank
- The LH(RH) wing tank
- The center tank
- The ACT(s) (if installed).
The system has level sensors in the wing and center tanks that the FLSCUs continuously monitor. The FLSCUs uses signal conditioning to find if the sensors are wet or dry. The FLSCUs use the fuel level data to:
- Control the operation of the intercell transfer system (Ref. AMM D/O 28-15-00-00)
- Control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00)
- Control the operation of the main fuel pump system (Ref. AMM D/O 28-21-00-00)
- Control the operation of the main transfer system (Ref. AMM D/O 28-26-00-00)
- Transmit fuel level warnings to the Engine/Warning Display (EWD) (Ref. 31-66-00)
- Control high level shut-off for automatic and manual refuel (Ref. AMM D/O 28-25-00-00).
When the ACT(s) is(are) installed, the Auxiliary Level Sense Control Unit (ALSCU) monitors level sensors in the ACT(s). The ALSCU also uses signal conditioning to find if the sensors are wet or dry.
When the ACT(s) is(are) installed the tank level sensing system gives discrete outputs to:
- Give system information to the AFMC (Ref. AMM D/O 28-51-00-00)
- Monitor the condition of the fuel and air pipes that connect the forward and rear ACTs
- Isolate the forward ACT(s) if the fuel or air pipes are damaged
- Limit fuel input to each ACT during refuel (Ref. AMM D/O 28-25-00-00)
- Identify when the fuel level in each ACT is at high or low level.
The tank level sensing system has temperature sensors in the wing tanks. The FLSCU uses signal conditioning to calculate the temperature of the fuel adjacent to the sensor.
The FLSCU uses the temperature data from the wing tanks to control the operation of the recirculation system (Ref. AMM D/O 28-16-00-00).
4. Power Supply
Fuel System - Electrical Symbols ** ON A/C NOT FOR ALL
Fuel System - Electrical Symbols ** ON A/C NOT FOR ALL
Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL
Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL
Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL
Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL
Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL Fuel System - Electrical Symbols ** ON A/C NOT FOR ALL Fuel System - Electrical Symbols ** ON A/C NOT FOR ALL Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL Fuel System - Electrical Power Supplies ** ON A/C NOT FOR ALL 5. Interfaces
Fuel System - Block Diagram ** ON A/C NOT FOR ALL
Fuel System - Block Diagram ** ON A/C NOT FOR ALL
Fuel System - Block Diagram ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL Fuel System - Block Diagram ** ON A/C NOT FOR ALL Fuel System - Block Diagram ** ON A/C NOT FOR ALL Fuel System - Block Diagram ** ON A/C NOT FOR ALL 6. Operation/Control and Indicating
A. Operation Limits
The fuel system is designed to operate in these limits:
The fuel system is designed to operate in these limits:
- maximum certificated altitude 12130 m (39797 ft.)
- ambient conditions.
B. The fuel types that follow can be used in the fuel system:
- JET A1
- JET B or JP4
- JET A
- JP5
- JP8
- RT
- TS-1
- No.3 JET.
This list is for general reference only. All kerosene and wide-cut fuels that are made to these specifications and are approved in your Flight Manual, can be used in the fuel system.
All the additives permitted in these specifications, plus other AIRBUS approved additives (which includes biocide and antistatic additives) can be used in the fuel system.
- a minimum of -54 deg.C (-65.2 deg.F) or the fuel freeze point
- a maximum of 50 deg.C (122 deg.F) or to a temperature at which the fuel starts to boil.
C. Control and Indicating
Fuel System Control Switches ** ON A/C NOT FOR ALL
Fuel System Control Switches ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
ECAM Displays and Control Panel ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL
Fuel System Control Switches ** ON A/C NOT FOR ALL Fuel System Control Switches ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL ECAM Displays and Control Panel ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL Refuel/Defuel Control Panel 800VU ** ON A/C NOT FOR ALL (1) Control
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
The cockpit overhead panel 20VU has control switches for:
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
- the main fuel pumps (Ref. AMM D/O 28-21-00-00)
- the crossfeed valve (Ref. AMM D/O 28-23-00-00).
The cockpit overhead panel 20VU has control switches for:
- ENG 1 FIRE
- ENG 2 FIRE
- APU FIRE.
When operated these switches put the related engine LP valve (Ref. AMM D/O 28-24-00-00) and/or the APU LP valve (Ref. AMM D/O 28-29-00-00) to the closed position.
- ENG 1 MASTER 1
- ENG 2 MASTER 2.
These switches control the position of the related engine LP valve (Ref. AMM D/O 28-24-00-00). In a fire the ENG FIRE switches close the related LP valve.
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
- a warning is given on the E/WD
- the FUEL page shows on the SD.
(2) Control
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
The cockpit overhead panel 20VU has control switches for:
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
- the main fuel pumps (Ref. AMM D/O 28-21-00-00)
- the crossfeed valve (Ref. AMM D/O 28-23-00-00)
- the main transfer system (Ref. AMM D/O 28-26-00-00).
The cockpit overhead panel 20VU has control switches for:
- ENG 1 FIRE
- ENG 2 FIRE
- APU FIRE.
When operated these switches put the related engine LP valve (Ref. AMM D/O 28-24-00-00) and/or the APU LP valve (Ref. AMM D/O 28-29-00-00) to the closed position.
- ENG 1 MASTER 1
- ENG 2 MASTER 2.
These switches control the position of the related engine LP valve (Ref. AMM D/O 28-24-00-00). In a fire the ENG FIRE switches close the related LP valve.
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
- a warning is given on the E/WD
- the FUEL page shows on the SD.
(3) Control
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
The cockpit overhead panel 20VU has control switches for:
The cockpit center-pedestal panel 115VU has control switches for:
Refuel and defuel of the aircraft (Ref. AMM D/O 28-25-00-00) is controlled from the refuel/defuel control panel. The refuel/defuel control panel has:
The control panel 800VU has indicators and selector switches and gives control of:
The control panel 801VU has indicators and switches and gives control of an automatic or manual pressure refuel of the installed ACT(s). The applicable indicators and switches of the control panel do not operate when the ACT(s) is/are not installed.
The ACT transfer pump is operated during a defuel of the installed ACT(s) (Ref. AMM D/O 28-28-00-00). The pump is controlled from the overhead panel 28VU and transfers fuel from the ACT(s) to the center tank.
The preselector 5QT and the fuel quantity indicator 6QT are adjacent to the control panel 800VU.
During a refuel operation the preselector 5QT shows The PRESELECTED and the ACTUAL fuel quantities. The preselector has a rocker switch that is used to set the PRESELECTED fuel quantity (Ref. AMM D/O 28-25-00-00).
During a refuel, or a defuel, the fuel quantity indicator 6QT shows the quantity of fuel in the tanks on five displays:
During a refuel or defuel operation the indicator shows the quantity of fuel in each tank.
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
- The main fuel pumps (Ref. AMM D/O 28-21-00-00)
- The crossfeed valve (Ref. AMM D/O 28-23-00-00)
- The main transfer system (Ref. AMM D/O 28-26-00-00)
The cockpit overhead panel 20VU has control switches for:
- ENG 1 FIRE
- ENG 2 FIRE
- APU FIRE.
The cockpit center-pedestal panel 115VU has control switches for:
- ENG 1 MASTER 1
- ENG 2 MASTER 2.
Refuel and defuel of the aircraft (Ref. AMM D/O 28-25-00-00) is controlled from the refuel/defuel control panel. The refuel/defuel control panel has:
- Two control panels 800VU and 801VU
- Preselector 5QT
- Fuel quantity indicator 6QT.
The control panel 800VU has indicators and selector switches and gives control of:
- Automatic or manual pressure refuel of the wing and center tanks
- Manual pressure defuel of the wing and center tanks.
The control panel 801VU has indicators and switches and gives control of an automatic or manual pressure refuel of the installed ACT(s). The applicable indicators and switches of the control panel do not operate when the ACT(s) is/are not installed.
The ACT transfer pump is operated during a defuel of the installed ACT(s) (Ref. AMM D/O 28-28-00-00). The pump is controlled from the overhead panel 28VU and transfers fuel from the ACT(s) to the center tank.
The preselector 5QT and the fuel quantity indicator 6QT are adjacent to the control panel 800VU.
During a refuel operation the preselector 5QT shows The PRESELECTED and the ACTUAL fuel quantities. The preselector has a rocker switch that is used to set the PRESELECTED fuel quantity (Ref. AMM D/O 28-25-00-00).
During a refuel, or a defuel, the fuel quantity indicator 6QT shows the quantity of fuel in the tanks on five displays:
- LEFT
- CTR
- RIGHT
- ACT
- TOTAL ACT
During a refuel or defuel operation the indicator shows the quantity of fuel in each tank.
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
- Warning is given on the E/WD
- The FUEL page shows on the SD.
(4) Control
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
The cockpit overhead panel 20VU has control switches for:
The control panel 800VU has indicators and selector switches and gives control of:
The control panel 801VU has indicators and switches and gives control of an automatic or manual pressure refuel of the installed ACT/s. The applicable indicators and switches of the control panel do not operate when the ACT/s is/are not installed.
The ACT transfer pump is operated during a defuel of the installed ACT/s (Ref. AMM D/O 28-28-00-00). The pump is controlled from the overhead panel 40VU and transfers fuel from the ACT/s to the center tank.
The preselector 5QT and the fuel quantity indicator 6QT are adjacent to the control panel 800VU.
During a refuel operation the preselector 5QT shows The PRESELECTED and the ACTUAL fuel quantities. The preselector has a rocker switch that is used to set the PRESELECTED fuel quantity (Ref. AMM D/O 28-25-00-00).
During a refuel, or a defuel, the fuel quantity indicator 6QT shows the quantity of fuel in the tanks on three displays:
During a refuel or defuel operation the indicator shows the quantity of fuel in each tank.
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
- the main fuel pumps (Ref. AMM D/O 28-21-00-00)
- the crossfeed valve (Ref. AMM D/O 28-23-00-00)
- the main transfer system (Ref. AMM D/O 28-26-00-00)
- the ACT transfer system (if installed) (Ref. AMM D/O 28-28-00-00).
The cockpit overhead panel 20VU has control switches for:
- ENG 1 FIRE
- ENG 2 FIRE
- APU FIRE.
When operated these switches put the related engine LP valve (Ref. AMM D/O 28-24-00-00) and/or the APU LP valve (Ref. AMM D/O 28-29-00-00) to the closed position.
- ENG 1 MASTER 1
- ENG 2 MASTER 2.
These switches control the position of the related engine LP valve (Ref. AMM D/O 28-24-00-00). In a fire the ENG FIRE switches close the related LP valve.
- two control panels 800VU and 801VU
- a preselector 5QT
- a fuel quantity indicator 6QT.
The control panel 800VU has indicators and selector switches and gives control of:
- an automatic or manual pressure refuel of the wing and center tanks
- a manual pressure defuel of the wing and center tanks.
The control panel 801VU has indicators and switches and gives control of an automatic or manual pressure refuel of the installed ACT/s. The applicable indicators and switches of the control panel do not operate when the ACT/s is/are not installed.
The ACT transfer pump is operated during a defuel of the installed ACT/s (Ref. AMM D/O 28-28-00-00). The pump is controlled from the overhead panel 40VU and transfers fuel from the ACT/s to the center tank.
The preselector 5QT and the fuel quantity indicator 6QT are adjacent to the control panel 800VU.
During a refuel operation the preselector 5QT shows The PRESELECTED and the ACTUAL fuel quantities. The preselector has a rocker switch that is used to set the PRESELECTED fuel quantity (Ref. AMM D/O 28-25-00-00).
During a refuel, or a defuel, the fuel quantity indicator 6QT shows the quantity of fuel in the tanks on three displays:
- LEFT
- CTR
- RIGHT
| - CTR+ACT (total quantity of the center tank and ACT/s) |
| - CTR (quantity in the center tank only) |
| - ACT 1 (quantity in the ACT1 only) |
| - ACT 2 (quantity in the ACT2 only) |
During a refuel or defuel operation the indicator shows the quantity of fuel in each tank.
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
- a warning is given on the E/WD
- the FUEL page shows on the SD.
(5) Control
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
The cockpit overhead panel 20VU has control switches for:
The control panel 800VU has indicators and selector switches and gives control of:
The control panel 801VU has indicators and switches and gives control of an automatic or manual pressure refuel of the installed ACT/s. The applicable indicators and switches of the control panel do not operate when the ACT/s is/are not installed.
The ACT transfer pump is operated during a defuel of the installed ACT/s (Ref. AMM D/O 28-28-00-00). The pump is controlled from the overhead panel 40VU and transfers fuel from the ACT/s to the center tank.
The preselector 5QT and the fuel quantity indicator 6QT are adjacent to the control panel 800VU.
During a refuel operation the preselector 5QT shows The PRESELECTED and the ACTUAL fuel quantities. The preselector has a rocker switch that is used to set the PRESELECTED fuel quantity (Ref. AMM D/O 28-25-00-00).
During a refuel, or a defuel, the fuel quantity indicator 6QT shows the quantity of fuel in the tanks on five displays:
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
The control of the fuel system is automatic, but the crew can manually control the system when necessary.
The cockpit overhead panel 40VU has control switches for:
- The main fuel pumps (Ref. AMM D/O 28-21-00-00)
- The crossfeed valve (Ref. AMM D/O 28-23-00-00)
- The main transfer system (Ref. AMM D/O 28-26-00-00)
- The ACT transfer system (if installed) (Ref. AMM D/O 28-28-00-00).
The cockpit overhead panel 20VU has control switches for:
- ENG 1 FIRE
- ENG 2 FIRE
- APU FIRE.
When operated these switches put the related engine LP valve (Ref. AMM D/O 28-24-00-00) and/or the APU LP valve (Ref. AMM D/O 28-29-00-00) to the closed position.
- ENG 1 MASTER 1
- ENG 2 MASTER 2.
These switches control the position of the related engine LP valve (Ref. AMM D/O 28-24-00-00). In a fire the ENG FIRE switches close the related LP valve.
- Two control panels 800VU and 801VU
- A preselector 5QT
- A fuel quantity indicator 6QT.
The control panel 800VU has indicators and selector switches and gives control of:
- An automatic or manual pressure refuel of the wing and center tanks
- A manual pressure defuel of the wing and center tanks.
The control panel 801VU has indicators and switches and gives control of an automatic or manual pressure refuel of the installed ACT/s. The applicable indicators and switches of the control panel do not operate when the ACT/s is/are not installed.
The ACT transfer pump is operated during a defuel of the installed ACT/s (Ref. AMM D/O 28-28-00-00). The pump is controlled from the overhead panel 40VU and transfers fuel from the ACT/s to the center tank.
The preselector 5QT and the fuel quantity indicator 6QT are adjacent to the control panel 800VU.
During a refuel operation the preselector 5QT shows The PRESELECTED and the ACTUAL fuel quantities. The preselector has a rocker switch that is used to set the PRESELECTED fuel quantity (Ref. AMM D/O 28-25-00-00).
During a refuel, or a defuel, the fuel quantity indicator 6QT shows the quantity of fuel in the tanks on five displays:
- LEFT
- CTR
- RIGHT
- ACT1
- ACT2
The Engine/Warning Display (EWD) (Ref. AMM D/O 31-66-00-00) and the System Display (SD) (which together make the ECAM) give fuel system data to the crew. When specified failures occur:
- A warning is given on the E/WD
- The FUEL page shows on the SD.
7. BITE Test
A. Hi-Level BITE (Ref. 28-46-00)
When the TEST switch (2QJ) (on the Refuel/Defuel control panel 800VU) is set to the HI. LVL position, a functional test of the hi-level circuits is done. If the circuits are serviceable, the HI. LVL. indicators (blue) (on the Refuel/Defuel Control Panel 800VU) change condition. That is, the HI. LVL. indicators that were off, come on and the HI. LVL. indicators that were on, go off. When the TEST switch is returned to its central position, the HI. LVL. indicators return to their initial condition.
When the TEST switch (2QJ) (on the refuel/defuel control panel 800VU) is set to the HI LVL position, a functional test of the hi-level circuits is done. If the circuits are serviceable, the HI LVL indicators (blue) (on the refuel/defuel Control Panel 800VU and 801VU ) change condition as follows:
The HI LVL indicator on the control panel 801VU do not operate when the ACT(s) is(are) not installed.
When the TEST switch (2QJ) (on the Refuel/Defuel control panel 800VU) is set to the HI. LVL position, a functional test of the hi-level circuits is done. If the circuits are serviceable, the HI. LVL. indicators (blue) (on the Refuel/Defuel Control Panel 800VU) change condition. That is, the HI. LVL. indicators that were off, come on and the HI. LVL. indicators that were on, go off. When the TEST switch is returned to its central position, the HI. LVL. indicators return to their initial condition.
When the TEST switch (2QJ) (on the refuel/defuel control panel 800VU) is set to the HI LVL position, a functional test of the hi-level circuits is done. If the circuits are serviceable, the HI LVL indicators (blue) (on the refuel/defuel Control Panel 800VU and 801VU ) change condition as follows:
- The HI LVL indicators that were off, come on
- The HI LVL indicators that were on, go off.
The HI LVL indicator on the control panel 801VU do not operate when the ACT(s) is(are) not installed.
B. Hi-Level BITE (Ref. 28-46-00)
When the TEST switch (2QJ) (on the refuel/defuel control panel 800VU) is set to the HI. LVL. position, a functional test of the hi-level circuits is done. If the circuits are serviceable, the HI. LVL. indicators (blue) (on the refuel/defuel Control Panel 800VU and 801VU ) change condition as follows:
The HI. LVL. indicators on the control panel 801VU do not operate when the ACT/s are not installed.
When the TEST switch (2QJ) (on the refuel/defuel control panel 800VU) is set to the HI. LVL. position, a functional test of the hi-level circuits is done. If the circuits are serviceable, the HI. LVL. indicators (blue) (on the refuel/defuel Control Panel 800VU and 801VU ) change condition as follows:
- the HI. LVL. indicators that were off, come on
- the HI. LVL. indicators that were on, go off.
The HI. LVL. indicators on the control panel 801VU do not operate when the ACT/s are not installed.
C. Fuel Quantity Indicating System (Ref. 28-42-00)
The Fuel Quantity Indicating Computer (FQIC) does the BITE test of the Fuel Quantity Indicating System (FQIS) and of the Fuel Level Sensing System (FLSS) (Ref. AMM D/O 28-46-00-00). The FQIS BITE test is done at aircraft power-up and is then done continuously whilst the FQIC is energized. The FLSS BITE test is done at aircraft power-up for the sensors that are fully in fuel and fully out of fuel. For the sensors that cannot be tested, the FQIC does a test of these sensors when the fuel is next at the correct level. The FLSS BITE test is only done when the aircraft is on the ground. The BITE test results can be accessed through the Multipurpose Control and Display Unit (MCDU) (Ref. AMM D/O 22-82-00-00), in the cockpit. The FQIC results are on the FQIC STATUS page and the FLSS results are on the FLSS STATUS page. The test results can only be accessed when the aircraft is on the ground.
If necessary, when the aircraft is on the ground, you can do a COMMAND FLSS BITE on the MCDU. The FQIC will do a FLSS BITE test and the results will be available on the FLSS STATUS page of the MCDU.
The Fuel Quantity Indicating Computer (FQIC) does the BITE test of the Fuel Quantity Indicating System (FQIS) and of the Fuel Level Sensing System (FLSS) (Ref. AMM D/O 28-46-00-00). The FQIS BITE test is done at aircraft power-up and is then done continuously whilst the FQIC is energized. The FLSS BITE test is done at aircraft power-up for the sensors that are fully in fuel and fully out of fuel. For the sensors that cannot be tested, the FQIC does a test of these sensors when the fuel is next at the correct level. The FLSS BITE test is only done when the aircraft is on the ground. The BITE test results can be accessed through the Multipurpose Control and Display Unit (MCDU) (Ref. AMM D/O 22-82-00-00), in the cockpit. The FQIC results are on the FQIC STATUS page and the FLSS results are on the FLSS STATUS page. The test results can only be accessed when the aircraft is on the ground.
If necessary, when the aircraft is on the ground, you can do a COMMAND FLSS BITE on the MCDU. The FQIC will do a FLSS BITE test and the results will be available on the FLSS STATUS page of the MCDU.