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APU FUEL FEED
The APU fuel feed is established from the right collector tank to the APU by the right main ejector or by the right DC fuel pump if the ejector pressure is low. This system includes an APU shutoff valve.
ELECTRIC FUEL PUMPS
The electric fuel pumps provide fuel pressure to the engines when the main ejector pumps cannot, such as during engine start and main ejector pump failure. The electric fuel pumps also provide fuel pressure to transfer fuel from one wing tank to the other.
COMPONENTS AND OPERATION FUEL COMPUTER
A dual-channel fuel system computer calculates the onboard fuel quantity and controls the refueling. One channel controls one side and the other channel controls the opposite side. If the onside channel fails, the other channel automatically as-sumes control. Each channel receives signals from the probes and aircraft attitude information from the AHRS.
The computer calculates the fuel quantity as weight in each tank. The computer uses the following information: fuel density, fuel probes readings, aircraft attitude and accelerations, and WOW signal.
MOTIVE FLOW
The ejectors operate by using motive flow pressure from the engine-driven pump. As high-pressure motive flow passes through the venturi of the ejectors, fluid velocity is increased and low pressure is created. The suction caused by the low pressure moves the fuel out of the tank.
SCAVENGE EJECTOR
The scavenge ejectors are operated by motive flow created by the high-pressure output of the engine-driven fuel pumps. The two ejectors are located at the lowest inboard point of each wing tank. The ejectors transfer fuel from the wing tanks to the collector tanks.
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
12-01-05 FUEL DISTRIBUTION (Cont)
COLLECTOR TANK
All fuel consumed by the engines comes from the collector tanks. The collector tanks are located in the aft section of each wing tank. Fuel from the wings flows into the left and right collector tanks from the associated wing tank through the flap-per check valves. When operating, scavenge ejectors also remove fuel from the wing tanks and delivers the fuel to the as-sociated collector tank.
MAIN EJECTOR
Two main ejectors are operated by motive flow created by the high-pressure output of the engine-driven fuel pumps. Each ejector pump takes fuel from its associated collector tank and delivers the fuel to the engine. The main ejectors are installed on the bottom of the collector tanks.
FUEL SYSTEM CONTROLS
The fuel system controls are as follows:
-L PUMP and R PUMP standby boost pump rotary switch (OFF, AUTO, ON)
-XFER SWITCH
-GRAVITY XFLOW switch
-L (R) ENG FIRE switches
In order to provide pressure during engine start or in the event of feed ejector failure, a standby boost pump is fitted in parallel with each feed ejector. When the engine RUN switch is selected ON and the respective standby boost pump is armed, it will be commanded ON as long as the feed ejector does not deliver sufficient pressure to the dedicated engine. For added safety, when sufficient pressure is achieved at the primary ejector outlet, a time delay will command the boost pump to remain ON for an additional 10 seconds.
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本文链接地址：庞巴迪挑战者300公务机机组操作手册 Bombardier Challenger-燃油(5)
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