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Alerting System (EICAS), in the form of a visual and/or aural alert and/or maintenance diagnostics.
FUEL SPECIFICATIONS
For information on fuel additives, temperature limitations and approved fuels, refer to Airplane Flight
Manual (AFM) CSP 700−5000−1 − LIMITATIONS Chapter.
Fuel remaining in a tank when the appropriate fuel quantity indicator reads zero is not usable. Refer
to the AFM CSP 700−5000−1 for exact tank and total fuel quantity.
FUEL
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
12−10−2
FUEL SYSTEM SYNOPTIC PAGE
The FUEL synoptic page provides an overview of system status, as represented below with both left
and right engines running and no transferring of fuel taking place.
DC AUXILIARY PUMPS
AC BOOST PUMPS
CENTER TRANSFER
PUMPS
FGF1210_002
FUEL
TOTAL FUEL
35616 LBS
FUEL USED
0 LBS
14900 LBS 14900 LBS
5816 LBS
AUX AUX
23 °C 23 °C
P
P
P P P
APU
32 °C
P
P
P
32 °C
AC Boost Pumps
Two AC boost pumps, also referred to as primary boost pumps, are located in each feed tank.
They normally supply fuel to the engines in all airplane ground and flight mode operations. Each
pump is capable of maintaining an engine (fuel demand) in all modes of engine operation. The two
pumps are continuously on, whenever the engine is operating and AC power is available. Both
boost pumps (two on each side) may be inhibited by selection of one of the individual switches on
the fuel control panel. The boost pumps are controlled automatically through the Alternating
Current Power Center (ACPC), when a fuel command is received.
DC Auxiliary Pumps
DC powered auxiliary pumps (AUX pumps) one in each feed tank, are used for the following:
· APU starting
· Wing to wing transferring of fuel
· Engine feed in the event of an AC boost pump failure
· During takeoff and landing with at least one of the following:
Flaps > 0°, landing gear down and in flight, or low wing fuel condition (600 pounds each
wing)
Each AUX pump may be inhibited by selecting off a switch on the fuel control panel. The pumps
are automatically controlled by the Secondary Power Distribution Assembly (SPDA).
FUEL
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
12−10−3
FUEL SYSTEM SYNOPTIC PAGE (CONT'D)
Center Transfer Pumps
Two center transfer pumps (controlled by the FMQGC) are used to transfer fuel from the center
tank to the main wing tank. There is no manual selection available to transfer fuel from the center
tank to the wings.
FUEL CONTROL PANEL
The fuel control panel is located on the overhead panel in the flight compartment. The fuel control
panel defines the operational modes, component controls and component inhibits.
The fuel control panel has switches, which when selected, override the automatic control of certain
components within the fuel system. Switch selections from this panel are sent to the ACPC. The
ACPC will then control the system from the inputs received from the panel. The switch lamps come
on in combination with certain EICAS messages, which represent the panel configuration or failure
within a given system. FGF1210_003
selection − Provides a means of transferring fuel from one
wing to the other. Controlled by the FMQGC.
selection − A left to right or a right to left selection,
provides a means of transferring fuel (in the direction of the arrow) from
one wing tank to the other.
selection − Provides a method of inhibiting wing to wing transfer.
PRI PUMPS Switch
light − Indicates that
both left wing primary pumps
have been disarmed. The
right PRI PUMPS switch has
similar logic.
AUX PUMP switch
light − Indicates that
the right auxiliary pump has
been disarmed. The left
AUX PUMP has similar
logic.
XFEED SOV switch
light − Will come
on when the valve does
not go to the commanded
position.
light − When the
switch is selected, the
crossfeed valve opens
and interconnects the
engine feed lines.
RECIRC INHIBIT switch
light − Indicates that
the FRTT valve is closed when
commanded by the flight crew.
AUTO
<− or −>
OFF
OPEN
OFF
OFF
FAIL
OFF
AUTO
WING XFER
OFF
WING FEED
INHIBIT
AUX PUMP
OFF
PRI PUMP
OFF
　
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