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system is On:
Green − Temperature of
fuel in tanks is between
−35°C and 0°C.
Amber − Temperature of
fuel in tanks is lower than
−35°C or greater than 0°C.
FUEL
TOTAL FUEL
42800 LBS
FUEL USED
200 LBS
14900 LBS 14900 LBS
11100 LBS
AUX AUX
23 °C 23 °C
APU
P P
32 °C
P
P
P
P
P
P
P P
2200LBS
32 °C
FUEL
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
12−10−28
FUEL PUMP DISPLAYS
GF1210_027
Centre Transfer Pumps
Controlled by the FMQGC and
transfers centre tank fuel to the
wing tanks.
L or R AC Boost Pumps
ON − At all times with the
engines running.
OFF − When commanded
by the switch on the Fuel
Control Panel.
L or R DC Auxiliary Pumps
ON − For engine starting,
take−off and landing, primary pump
failure and wing transfer of fuel.
NOTE: The AUX PUMP cannot be
used to support the engine feed
system and wing transfer at the
same time.
OFF − When commanded by the
switch on the Fuel Control Panel
or when both primary pumps are on.
Aft Transfer Pumps
ON − When requested by the
computer or selected on the Fuel
Control Panel.
OFF − When commanded by the
switch on the Fuel Control Panel
or when commanded by the
FMQGC in AUTO mode.
FUEL
TOTAL FUEL
37000 LBS
FUEL USED
5600LBS
13600 LBS 13200 LBS
8000 LBS
AUX AUX
23 °C 23 °C
APU
32 °C
P
P
P
P P
2200LBS
32 °C
P P P
P
P
FUEL
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
12−10−29
FUEL SHUT-OFF DISPLAYS
GF1210_028
Engine Feed ShutOff
Valve
Activated by the engine
run switches on the throttle
quadrant.
Applicable engine FIRE
DISCH handle.
APU Feed ShutOff
Valve
Activated by the RUN position
switch on the APU control panel.
Also controlled by the APU FIRE
DISCH handle.
Aft Tank Transfer Valve
Controlled by the FMQGC
or the AFT XFER switch
on the fuel control panel.
Wing Transfer SOV
Controlled by the FMQGC or the
WING XFER switch on the fuel
control panel.
Fuel Crossfeed SOV
Controlled by the switch on
the Fuel Control Panel. It is
used to interconnect the
engine feed lines.
FUEL
TOTAL FUEL
10400 LBS
FUEL USED
32000 LBS
4600 LBS 4000 LBS
0 LBS
AUX AUX
23 °C 23 °C
APU
32 °C
P
P
P
P
1800LBS
32 °C
P P P
P
P
P
FUEL
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
12−10−30
FUEL SYNOPTIC PAGE SYMBOLS
The following represents the EICAS symbols and flow line logic for the fuel synoptic page. The
symbols are shown in serviceable and failure conditions.
EICAS Philosophy
GF1210_029
VALVE AND FLOW LINE LOGIC
OPEN
VALVE
NOT FAILED
CLOSED
TRANSIT
INVALID
VALVE
FAILED
DIRECTION OF FLOW
PUMP AND FLOW LINE LOGIC
ON
PUMP
INVALID
OFF
FAILED
OFF
PUMP
FAILED
ON
P
P
P
P
P
DIRECTION OF FLOW
FUEL MANAGEMENT QUANTITY GAUGING SYSTEM (FMQGS)
The FMQGS consists of a dual channel computer with BITE, utilizing capacitance type probes in
each tank to continuously measure the quantity of usable fuel. The fuel computer performs all digital
processing related to the system control and indication and performs computations associated with
fuel gauging system requirements. The following schematic represents inputs and outputs of various
components and systems operations.
FUEL
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
12−10−31
FMQGC SCHEMATIC
ENGINE INDICATING AND CREW ALERTING SYSTEM
AND
CENTRAL AIRCRAFT INFORMATION MANAGEMENT SYSTEM
FMQGC
CHANNEL
1
CHANNEL
2
LEFT WING TANK RIGHT WING TANK
CENTRE WING TANK
AFT TANK
Fuel Quantities
Fuel Temperature
EICAS Messages
Caution
Advisory
Status
EICAS Inputs from
other sources
Sensor Data:
Tank Probes
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