DOC AIRBUS | AMM A320FDISTRIBUTION - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
1. General
The fuel distribution system is in four parts. These are:
** ON A/C NOT FOR ALL The fuel distribution system is in four parts. These are:
- the supply to the engine
- the supply to the Auxiliary Power Unit (APU)
- the refuel/defuel system
- the main transfer system.
- the supply to the engine
- the supply to the Auxiliary Power Unit (APU)
- the refuel/defuel system.
- The supply to the engine
- The supply to the Auxiliary Power Unit (APU)
- The refuel/defuel system
- The main transfer system
- The ACT transfer system.
2. Component Location
Fuel Distribution - Component Location ** ON A/C NOT FOR ALL
Fuel Distribution - Component Location ** ON A/C NOT FOR ALL
Fuel Distribution - Component Location ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL Fuel Distribution - Component Location ** ON A/C NOT FOR ALL Fuel Distribution - Component Location ** ON A/C NOT FOR ALL Fuel Distribution - Component Location ** ON A/C NOT FOR ALL 3. System Description
A. Engine Supply
(1) The Main Fuel-Pump System (Ref. AMM D/O 28-21-00-00)
The main fuel-pump system moves the fuel from the fuel tanks to the engines. The system has two main fuel-pumps (main pumps) in each wing and two main pumps in the center tank. The wing tank pumps operate continuously at the same time. If a wing tank pump has a failure (or is set to OFF) the other pump automatically supplies fuel. The center tank pumps are set to on or off (by the Fuel Level Sensing Control Units (FLSCUs) (Ref. AMM D/O 28-46-00-00)) when the wing tank fuel is at specified levels. The closed crossfeed system (Ref. AMM D/O 28-23-00-00) divides the engine supply system into two parts. Each part contains three main fuel-pumps which supply one engine. When the crossfeed valve is open, it is possible for one fuel-pump to supply fuel to the two engines. An air release valve automatically releases air from each of the engine supply pipes.
The main fuel-pump system moves the fuel from the fuel tanks to the engines. The system has two main fuel-pumps (main pumps) in each wing and two main pumps in the center tank. The wing tank pumps operate continuously at the same time. If a wing tank pump has a failure (or is set to OFF) the other pump automatically supplies fuel. The center tank pumps are set to on or off (by the Fuel Level Sensing Control Units (FLSCUs) (Ref. AMM D/O 28-46-00-00)) when the wing tank fuel is at specified levels. The closed crossfeed system (Ref. AMM D/O 28-23-00-00) divides the engine supply system into two parts. Each part contains three main fuel-pumps which supply one engine. When the crossfeed valve is open, it is possible for one fuel-pump to supply fuel to the two engines. An air release valve automatically releases air from each of the engine supply pipes.
(2) The Main Fuel-Pump System (Ref. AMM D/O 28-21-00-00)
The main fuel-pump system moves the fuel from the wing tanks to the engines. The system has two main fuel-pumps (main pumps) in each wing. The pumps operate at the same time, but if a main pump has a failure (or is set to OFF) the other pump automatically supplies fuel. The closed crossfeed system (Ref. AMM D/O 28-23-00-00) divides the engine supply system into two parts. Each part contains two main fuel-pumps which supply one engine. When the crossfeed valve is open, it is possible for one fuel-pump to supply fuel to the two engines. An air release valve automatically releases air from each of the engine supply pipes.
The main fuel pumps connect to the jet pumps in the center (transfer) tank. The jet pumps move fuel from the center (transfer) tank to the wing tanks (Ref. AMM D/O 28-26-00-00).
The main fuel-pump system moves the fuel from the wing tanks to the engines. The system has two main fuel-pumps (main pumps) in each wing. The pumps operate at the same time, but if a main pump has a failure (or is set to OFF) the other pump automatically supplies fuel. The closed crossfeed system (Ref. AMM D/O 28-23-00-00) divides the engine supply system into two parts. Each part contains two main fuel-pumps which supply one engine. When the crossfeed valve is open, it is possible for one fuel-pump to supply fuel to the two engines. An air release valve automatically releases air from each of the engine supply pipes.
The main fuel pumps connect to the jet pumps in the center (transfer) tank. The jet pumps move fuel from the center (transfer) tank to the wing tanks (Ref. AMM D/O 28-26-00-00).
(3) Crossfeed System (Ref. AMM D/O 28-23-00-00)
The crossfeed valve in the center tank is usually in the closed position. In this position, 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, any main pump can supply fuel to each engine.
The crossfeed valve in the center tank is usually in the closed position. In this position, 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, any main pump can supply fuel to each engine.
(4) Engine Low-Pressure (LP) Fuel Shut-Off System (Ref. AMM D/O 28-24-00-00)
The engine LP fuel shut-off system has one LP fuel valve for each engine. When necessary, each LP valve isolates its engine from the fuel supply. The related ENG MASTER switch (Ref. AMM D/O 76-12-00-00) controls the operation of the LP valve. When the related engine FIRE PUSH switch (Ref. AMM D/O 26-12-00-00) is pushed (in), the LP valve closes.
The engine LP fuel shut-off system has one LP fuel valve for each engine. When necessary, each LP valve isolates its engine from the fuel supply. The related ENG MASTER switch (Ref. AMM D/O 76-12-00-00) controls the operation of the LP valve. When the related engine FIRE PUSH switch (Ref. AMM D/O 26-12-00-00) is pushed (in), the LP valve closes.
B. APU Fuel-Feed System
(1) APU Fuel-Pump System (Ref. AMM D/O 28-22-00-00)
The APU fuel supply system has a fuel pump on the center tank rear spar. The APU fuel pump supplies the fuel to the APU as required, normally from the left-wing tank.
When the crossfeed valve is open any fuel tank can supply fuel to the APU.
The APU fuel supply system has a fuel pump on the center tank rear spar. The APU fuel pump supplies the fuel to the APU as required, normally from the left-wing tank.
When the crossfeed valve is open any fuel tank can supply fuel to the APU.
(2) The APU LP Fuel Shut-Off System (Ref. AMM D/O 28-29-00-00)
The APU LP fuel shut-off system has a LP fuel valve that controls the supply of fuel to the APU. If an APU fire occurs, the APU emergency shut down system closes the LP fuel valve to stop the flow of fuel.
The APU fuel system also has a vent and drain valve and a LP fuel switch installed in the tail cone.
The APU LP fuel shut-off system has a LP fuel valve that controls the supply of fuel to the APU. If an APU fire occurs, the APU emergency shut down system closes the LP fuel valve to stop the flow of fuel.
The APU fuel system also has a vent and drain valve and a LP fuel switch installed in the tail cone.
C. Refuel/Defuel System (Ref. 28-25-00)
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the RH lower belly-fairing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of the RH wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel coupling to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the RH lower belly-fairing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of each wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel couplings to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the leading edge of the right hand wing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of the RH wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel coupling to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the RH lower belly-fairing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of the RH wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel coupling to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the RH lower belly-fairing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of each wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel couplings to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the leading edge of the right hand wing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of the RH wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel coupling to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
D. Refuel/Defuel System (Ref. 28-25-00)
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the RH lower belly-fairing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of each wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel couplings to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the RH lower belly-fairing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of the RH wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel couplings to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the RH lower belly-fairing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of each wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel couplings to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. A refuel/defuel control panel in the RH lower belly-fairing controls the refuel/defuel operation.
There is a refuel/defuel coupling (installed in the leading-edge of the RH wing) that is the interface between the refuel/defuel system and the external fuel-source. A refuel/defuel gallery connects the refuel/defuel couplings to the fuel tanks.
There is an overwing refuel adaptor in the top surface of each wing. The overwing refuel adaptor allows you to refuel the aircraft when you cannot use the refuel/defuel coupling.
E. Main Transfer System (Ref. 28-26-00)
The main transfer system controls the flow of fuel from the center (transfer) tank to the two wing tanks. The system uses the main fuel pump pressure (Ref. AMM D/O 28-21-00-00) to operate the jet pumps. The jet pumps move fuel by suction from the center (transfer) tank to the wing tanks. The operation of the main transfer system is usually automatic, but the crew can manually control the system when necessary.
The main transfer system controls the flow of fuel from the center (transfer) tank to the two wing tanks. The system uses the main fuel pump pressure (Ref. AMM D/O 28-21-00-00) to operate the jet pumps. The jet pumps move fuel by suction from the center (transfer) tank to the wing tanks. The operation of the main transfer system is usually automatic, but the crew can manually control the system when necessary.
F. ACT Transfer System (Ref. 28-28-00)
The ACT transfer system controls the flow of fuel from the ACT/s (when installed) to the center tank. The system uses air pressure, taken from the cabin pressurization-system, to automatically move the fuel from the ACT/s to the center tank.
The movement of fuel can also be controlled manually, in flight (at low altitude) or on the ground, when the ACT AUTO P/BSW (on the panel 40VU) is pushed in. This operates the ACT transfer pump which moves the fuel forward to the center tank until it is set to off.
The ACT transfer system controls the flow of fuel from the ACT/s (when installed) to the center tank. The system uses air pressure, taken from the cabin pressurization-system, to automatically move the fuel from the ACT/s to the center tank.
The movement of fuel can also be controlled manually, in flight (at low altitude) or on the ground, when the ACT AUTO P/BSW (on the panel 40VU) is pushed in. This operates the ACT transfer pump which moves the fuel forward to the center tank until it is set to off.
4. Power Supply
Fuel Distribution - AC Power Supplies ** ON A/C NOT FOR ALL
Fuel Distribution - AC Power Supplies ** ON A/C NOT FOR ALL
Fuel Distribution - AC Power Supplies ** ON A/C NOT FOR ALL
Fuel Distribution - DC Power Supplies ** ON A/C NOT FOR ALL
Fuel Distribution - DC Power Supplies ** ON A/C NOT FOR ALL
Fuel Distribution - DC Power Supplies ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL Fuel Distribution - AC Power Supplies ** ON A/C NOT FOR ALL Fuel Distribution - AC Power Supplies ** ON A/C NOT FOR ALL Fuel Distribution - AC Power Supplies ** ON A/C NOT FOR ALL Fuel Distribution - DC Power Supplies ** ON A/C NOT FOR ALL Fuel Distribution - DC Power Supplies ** ON A/C NOT FOR ALL Fuel Distribution - DC Power Supplies ** ON A/C NOT FOR ALL 5. Interface
Fuel Distribution - Interfaces ** ON A/C NOT FOR ALL
Fuel Distribution - Interfaces ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL Fuel Distribution - Interfaces ** ON A/C NOT FOR ALL Fuel Distribution - Interfaces ** ON A/C NOT FOR ALL 6. Operation/Control and Indicating
A. Control and Indication
(1) Control
Control of the fuel distribution system is usually automatic, but the crew can manually control the system when necessary. Most of the controls are in the cockpit. However, the controls for the refuel/defuel system are on the refuel/defuel control panel 800VU.
The cockpit overhead panel 40VU has the control switches for:
The cockpit overhead panel 20VU has the control switches for:
Control of the fuel distribution system is usually automatic, but the crew can manually control the system when necessary. Most of the controls are in the cockpit. However, the controls for the refuel/defuel system are on the refuel/defuel control panel 800VU.
The cockpit overhead panel 40VU has the control switches for:
- the L TK PUMPS 1 and 2 (Ref. AMM D/O 28-21-00-00)
- the R TK PUMPS 1 and 2 (Ref. AMM D/O 28-21-00-00)
- the CTR TK PUMPS 1 and 2 (Ref. AMM D/O 28-21-00-00)
- the MODE SEL AUTO (Ref. AMM D/O 28-21-00-00)
- the X FEED (crossfeed) system (Ref. AMM D/O 28-23-00-00).
The cockpit center-pedestal panel 115VU has the control switches for: - ENG 1 MASTER 1
- ENG 2 MASTER 2
These switches open the related engine LP valve (Ref. AMM D/O 28-24-00-00) when they are set to ON.
The cockpit overhead panel 20VU has the 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.
- a warning is given on the E/WD
- the FUEL page shows on the SD.
(2) Control
Control of the fuel distribution system is usually automatic, but the crew can manually control the system when necessary. Most of the controls are in the cockpit. However, the controls for the refuel/defuel system are on the refuel/defuel control panel 800VU.
The cockpit overhead panel 40VU has the control switches for:
The cockpit overhead panel 20VU has the control switches for:
Control of the fuel distribution system is usually automatic, but the crew can manually control the system when necessary. Most of the controls are in the cockpit. However, the controls for the refuel/defuel system are on the refuel/defuel control panel 800VU.
The cockpit overhead panel 40VU has the control switches for:
- the L TK PUMPS 1 and 2 (Ref. AMM D/O 28-21-00-00)
- the R TK PUMPS 1 and 2 (Ref. AMM D/O 28-21-00-00)
- the CTR TK L(R) XFR (Ref. AMM D/O 28-26-00-00)
- the MODE SEL AUTO (Ref. AMM D/O 28-26-00-00)
- the X FEED (crossfeed) system (Ref. AMM D/O 28-23-00-00).
The cockpit center-pedestal panel 115VU has the control switches for: - ENG 1 MASTER 1
- ENG 2 MASTER 2
These switches open the related engine LP valve (Ref. AMM D/O 28-24-00-00) when they are set to ON.
The cockpit overhead panel 20VU has the 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.
- a warning is given on the E/WD
- the FUEL page shows on the SD.
(3) Control
Control of the fuel distribution system is usually automatic, but the crew can manually control the system when necessary. Most of the controls are in the cockpit. However, the controls for the refuel/defuel system are on the refuel/defuel control panels 800VU and 801VU.
The cockpit overhead panel 40VU has the control switches for:
The cockpit overhead panel 20VU has the control switches for:
Control of the fuel distribution system is usually automatic, but the crew can manually control the system when necessary. Most of the controls are in the cockpit. However, the controls for the refuel/defuel system are on the refuel/defuel control panels 800VU and 801VU.
The cockpit overhead panel 40VU has the control switches for:
- the L TK PUMPS 1 and 2 (Ref. AMM D/O 28-21-00-00)
- the R TK PUMPS 1 and 2 (Ref. AMM D/O 28-21-00-00)
- the CTR TK L(R) XFR (Ref. AMM D/O 28-26-00-00)
- the MODE SEL AUTO (Ref. AMM D/O 28-26-00-00)
- the X FEED (crossfeed) system (Ref. AMM D/O 28-23-00-00)
- the ACT transfer pump (Ref. AMM D/O 28-28-00-00).
The cockpit center-pedestal panel 115VU has the control switches for: - ENG 1 MASTER 1
- ENG 2 MASTER 2
These switches open the related engine LP valve (Ref. AMM D/O 28-24-00-00) when they are set to ON.
The cockpit overhead panel 20VU has the 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.
- a warning is given on the E/WD
- the FUEL page shows on the SD.