-
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.
(1) Main Fuel Pump System (Ref. 28-21-00)
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:
-center tank fuel
-wing tank fuel. If one or two of the fuel pumps has a failure, or is set to OFF, the other(s) continue(s) to supply fuel to its related engine. If the crossfeed system (Ref. 28-23-00) is used, the fuel pumps can also supply fuel to the other engine. 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.
**ON A/C 301-399,
B. Distribution (Ref. 28-20-00)
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.
1EFF : ALL 1 28-00-00Page 19 1 1 Aug 01/05 1 1 1CES 1 (1) Main Fuel Pump System (Ref. 28-21-00)
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. 28-23-00) 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. 28-26-00).
**ON A/C ALL
(2)
APU Fuel-Pump System (Ref. 28-22-00) 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. 49-30-00). The APU fuel pump uses the fuel supplied from the LH wing tank.
(3)
Crossfeed System (Ref. 28-23-00) The valve of the crossfeed system is usually closed, and in this configuration it divides the main fuel pump system (Ref. 28-21-00) 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.
(4)
Engine LP Fuel Shut Off (Ref. 28-24-00) 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 related ENG MASTER switch (Ref.76-12-00)
-
the related engine FIRE PUSH switch (Ref. 26-12-00).
(5)
Refuel/Defuel System (Ref. 28-25-00)
R **ON A/C 001-049, 052-099, 101-149, 151-199, 201-299, 301-399, 401-499,
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. It is controlled from the refuel/defuel control panel 800VU and the preselector 5QT in the RH lower belly-fairing. A single refuel/defuel coupling is in the leading edge of the RH wing. This is the interface between the refuel/defuel system and the external fuel supply.
1EFF : ALL 1 28-00-00Page 20 1 1 Aug 01/05 1 1 1CES 1 **ON A/C 051-051,
The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. It is controlled from the refuel/defuel control panel 800VU and the preselector 5QT in the RH lower belly-fairing. A single refuel/defuel coupling is installed in the leading edge of each wing. These are the interfaces between the fuel tanks and the external fuel supply.
**ON A/C ALL
Refuel
There are two different procedures to refuel the aircraft. These are:
-
the pressure refuel (automatic or manual)
-
the overwing refuel (gravity).
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. 28-42-00). The fuel supply to each fuel tank during a manual refuel is controlled on the refuel/defuel control panel 800VU.
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