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When airborne, tail tank fuel is transferred forward to the auxiliary tank system at a constant
rate. Tail tank fuel transfer is controlled and monitored by the FSCU.
Fuel Quantity Measurement
The FSCU measures fuel quantity through a network of 17 DC-type capacitance probes, located
throughout the main, auxiliary, and tail tank systems. The FSCU receives attitude information
from IRS 1 and IRS 2, and corrects fuel quantity measurements for aircraft attitude. Fuel tank
quantity information is processed by the data concentrator units (DCUs), and displayed (in
pounds or kilograms) on the EICAS primary page.
Water Drains
In order to check fuel tanks for contamination, water drains are provided for every tank. A drain
valve is located at the bottom of the tail cone tank and the tail tank sump, to enable fuel
sampling and complete drainage when necessary.
FUEL SYSTEM
Description
Vol. 2 12−10−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
FUEL TANK SYSTEM (CONT'D)
Water Drains Arrangement
Figure 12−10−2
Vent System
Two wing mid-span NACA scoops vent all wing and auxiliary tanks, to ensure they feed freely.
The tail tanks are vented through their own dedicated system. All three (3) tail tanks are vented
through a common vent line, running down the vertical fin and out the bottom of the fuselage.
Ram air is used to provide a slight positive pressure during flight.
Manual Vent Relief Valves
Two manual vent relief are located underneath the wings near the tips, and a third relief valve is
located beneath the center of the auxiliary tank, to prevent overpressurizing the tanks during
refueling. A fourth vent relief valve, for the tail tank system, is located on the left side of the
vertical fin, but cannot be tested manually.
FUEL SYSTEM
Description
Vol. 2 12−10−3
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
FUEL TANK SYSTEM (CONT'D)
Fuel Vent System (Manual Vent Relief Valves)
Figure 12−10−3
Tail Tank Relief Valve
Figure 12−10−4
CAUTION
If the tail tank relief valve has opened (popped), it indicates an
overpressure condition in the tail tank system, which must be
corrected before flight.
FUEL SYSTEM
Description
Vol. 2 12−10−4
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
FUEL DISTRIBUTION
Description
There are two separate fuel distribution systems; the engine fuel feed system, and the APU fuel
feed system.
The engine fuel feed system controls the flow of fuel from the main fuel tanks to the engines.
The APU fuel feed system supplies fuel to the APU. For additional information on the APU fuel
feed system, see Chapter 5, Auxiliary Power Unit.
Components and Operation
The components of the engine fuel feed system are as follows:
Collector Tanks
Two collector tanks, located at the lowest point of the center auxiliary tank, are considered part
of the main tank system. They receive fuel from their respective main wing tank via gravity or
scavenge ejector pump flow. Fuel from the collector tanks is supplied to each engine-driven
pump unit by main ejector pumps or electric boost pumps.
Boost Pumps
Two DC electric boost pumps provide the engine with a standby fuel feed system. They are
available for engine starting, and as backup fuel feed source if either main ejector pump output
pressure is too low to satisfactorily feed its respective engine. The left boost pump is powered
by the DC battery bus, and the right boost pump by DC bus 2. The boost pumps are located
downstream of their respective collector tanks, on the fuel feed lines to the engine-driven
pumps. During normal operation, the only pilot action required is to arm both BOOST PUMP
switches on the FUEL control panel prior to engine start, and disarm them after shutdown.
When both BOOST PUMP switches are armed, the boost pumps are activated if low pressure is
sensed at either left or right main ejector pressure switch (this is the case prior to engine start).
If a single BOOST PUMP switch is armed, both boost pumps will be activated, if low pressure is
sensed on the armed side’s main ejector pressure switch. For example, if only the left BOOST
PUMP switch is armed (pressed in), then both pumps will activate if low pressure is sensed at
the left main ejector output. The boost pumps can provide fuel to both engine’s fuel feed
systems through a crossover feed line.
If a boost pump has been activated, sufficient pump output pressure is indicated by the green
ON legend in the switch/light. Insufficient output pressure is indicated by the amber INOP
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庞巴迪挑战者604操作手册 Operating Manual 4(30)
