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INHIBIT
L
WING FEED
INHIBIT
AUX PUMP
OFF
PRI PUMP
OFF
INHIBIT
R
XFEED SOV
FAIL
OPEN
WING XFEED switch
OFF OFF
L RECIRC R RECIRC
FUEL
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
12−10−4
FUEL TANKS
All fuel is carried in three integral tanks (left wing, right wing and center wing).
The inboard section of each wing is designated as a feed tank, from which each engine draws its
fuel. Fuel flows from the outboard sections of each wing tank, into the feed tank (by gravity), through
swing check valves in the baffles of each main tank. The check valves allow fuel flow in the inboard
direction only. This will restrict large fuel movements and limit center of gravity shifts in airplane
changes of attitude. Fuel is also transferred into the feed tanks from the center wing tank by the
transfer system.
SERVICE POINTS
FGF1210_004
WING FUEL TANK
WATER DRAIN
WING FUEL TANK
GRAVITY FUEL FILL
CENTER WING
GRAVITY FUEL FILL
WING FUEL TANK
WATER DRAIN
CENTER FUEL TANK
WATER DRAINS
GRAVITY FUEL FILL
LEGEND
LOWER SURFACE
UPPER SURFACE
All tanks have flush selfclosing
water drain valves, installed at various low points, to permit draining
of any accumulated water or residual fuel. They are located at the low point of each wing. Three
gravity fill caps are provided for wing and center tank gravity refueling.
FUEL
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
12−10−5
VENT SYSTEM
An open vent (no float valves or flame arrestors) system is used to control the pressure in the fuel
tanks. It consists of vent line tubing and ram air outlets (scoops) to ensure adequate venting of all
fuel tanks. The vent lines connect the two air scoops to the fuel tanks and the fuel tanks to each
other. The lines are drained of fuel which is returned to the feed tanks during operation. The low point
of the main vent line is continuously scavenged by a jet pump.
The vent line distribution is to a high point in the fuselage, preventing fuel from reaching either of the
two ram outlets and spilling overboard. If any fuel passes the high point, it is collected by the surge
box and is drained back to the tank before it reaches the outlet. Each surge box vent line tubing runs
vertically along the fuselage side wall and is coupled to the wing and center tanks.
The vent system is fully redundant such that any single blockage does not affect the venting
capability.
VENT SYSTEM SCHEMATIC
FGF1210_005
LEFT WING TANK RIGHT WING TANK
CENTER
WING
TANK
LEFT
SURGE
BOX
RIGHT
SURGE
BOX
AIR
SCOOP
AIR
SCOOP
Relief valves are used to protect the tanks from over pressurization, in the case of failure of the vent
system and/or refuel shutoff valve. They are located in the wing and center tanks.
FUEL
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
12−10−6
TRANSFER SYSTEM
Fuel contained in the center tank cannot be fed directly to the engine, but must be first delivered to
the feed tanks by the transfer pumps. The normal sequence of fuel usage is to transfer center tank
fuel into the wings as required to keep the wings full during climb and cruise.
After depletion of center tank fuel quantity, no further transfer of fuel is required, since all remaining
fuel is contained in the wing tanks.
Control of fuel transfer from the center tank is normally under control of the fuel computer. There is
no manual override for the center tank transfer system.
Center Transfer
Fuel transfer from the center tank to wing tank is completely automatic through the control of the
FMQGC. The FMQGC monitors the fuel level and quantities in the wing tank (using fuel probes,
compensators, densitometers and temperature sensors) to control fuel transfer from the center
tank to the wing tanks. Fuel will be transferred from the center tank and delivered to the wing feed
tanks, through the use of two center transfer pumps.
The FMQGC will start the applicable center transfer pump(s) when each individual wing tank
reaches approximately 93% of its fuel tank capacity. The FMQGC will automatically stop the
center transfer pump(s) when the respective wing tank reaches greater than 97% of its fuel tank
capacity.
CENTER TRANSFER
PUMPS
FGF1210_006
FUEL
TOTAL FUEL
35616 LBS
FUEL USED
0 LBS
14900 LBS 14900 LBS
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
Bombardier_Global_000-Fuel(3)
