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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.
AFT XFER Switch
selection − Provides a means of transferring fuel from
the aft tank to the wing tank. Controlled by the FMQGC.
selection − Provides a manual method of controlling
the transfer schedule.
selection − Inhibits the forward/aft transfer of fuel.
RECIRC switch
(If installed)
light −
Indicates that
the FRTT
valve is open
when commanded
by
flight crew.
AUTO
<− or −>
OFF
OPEN
OFF
AUTO
ON
OFF
ON
FAIL
OFF
AUTO
WING XFER
OFF
AUTO
AFT XFER
OFF ON
WING FEED
INHIBIT
AUX PUMP
OFF
PRI PUMP
OFF
L RECIRC
ON
L
WING FEED
INHIBIT
AUX PUMP
OFF
PRI PUMP
OFF
R RECIRC
ON
R
XFEED SOV
FAIL
OPEN
WING XFEED switch
FUEL
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
12−10−4
FUEL TANKS
All fuel is carried in three integral tanks (left wing, right wing and centre wing) and a smaller aft
fuselage tank (contained in a structurally enclosed bladder).
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 centre of gravity shifts in airplane
changes of attitude. Fuel is also transferred into the feed tanks from the centre wing and aft fuselage
tanks by the transfer system.
SERVICE POINTS
GF1210_004
WING FUEL TANK
WATER DRAIN AFT FUEL TANK FUEL
AND WATER DRAIN
WING FUEL TANK
GRAVITY FUEL FILL
CENTRE WING
GRAVITY FUEL FILL
WING FUEL TANK
WATER DRAIN
CENTRE 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 centre tank gravity refueling.
FUEL
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
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, centre and aft tanks.
The vent system is fully redundant such that any single blockage does not affect the venting
capability.
VENT SYSTEM SCHEMATIC
GF1210_005
LEFT WING TANK RIGHT WING TANK
AFT
TANK
CENTRE
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 shut off valve. They are located in the wing, centre and aft tanks. The aft tank
relief valve has a similar function as the centre and wing tank relief system, but also incorporates a
negative pressure relief feature which can activate in an emergency descent.
　
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