Bombardier_Challenger_Global_00-Fuel(2)

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Components and Operation....................................................................................... 12-01-09
Fuel Quantity Probes ................................................................................................. 12-01-09
Fuel Temperature Probe ............................................................................................12-01-09
Fuel Level Sensors .................................................................................................... 12-01-09
Fuel Quantity Gaging Computer ................................................................................ 12-01-09
Refuel/Defuel Control Panel ......................................................................................12-01-09
Fuel Quantity Gaging ..........................................................................................................12-01-10
Description................................................................................................................. 12-01-10
Components and Operation....................................................................................... 12-01-10
Fuel Computer ........................................................................................................... 12-01-10
Controls and Indication........................................................................................................ 12-01-10
Description................................................................................................................. 12-01-10
Fuel Control Panel ..................................................................................................... 12-01-10
Fuel Display ............................................................................................................... 12-01-11
Fuel Temperature Readouts ...................................................................................... 12-01-11
Fuel Quantity Indications ........................................................................................... 12-01-11
Fuel Synoptic Page.................................................................................................... 12-01-12
EICAS Messages ................................................................................................................12-01-13
REV 1

FUEL
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 12-01-01
INTRODUCTION
The fuel tanks are located in the left and right wings and supply fuel to the engines and APU. Tanks can be refueled through
a single-point adapter or manually by overwing refueling. The fuel computer controls automatic refueling, powered crossflow,
fuel transfer, measurement of fuel quantity and temperature. Fuel system data is presented on the EICAS and synoptic
pages.
REV 1
FUEL
Volume 2 Flight Crew Operating Manual Sep 13/2004
12-01-02 CSP 100-6 REV 1
FUEL TANK SYSTEM
DESCRIPTION
The Challenger 300 stores fuel in the left and right wing tanks. The tanks are sealed with a fuel resistant sealant.
The tanks provide single-point and overwing refueling capability and provisions for removing condensation from the tanks
through underwing water drains. Low drag NACA vent scoops provide static venting of the tanks. Fuel quantity and temperature
measurement probes in the tanks provide indications for the EICAS.
All fuel supplied to the engines flows through the collector tanks. The left and right collector tanks are located inside each
wing tank at the rear and inboard of the wing. Each collector tank is replenished by gravity through flapper check valves
installed on the division between the collector and the wing tanks and by a scavenge ejector when the engines are operating.
The right side backup DC fuel pump takes fuel from the right collector tank and delivers it to the APU.
FUEL TANK CAPACITIES
Maximum usable fuel loads are given in the tables below.
Pressure Refuel
Fuel Tank Fuel Mass †
Right 7075 lb 3210 kg
Left 7075 lb 3210 kg
Left & Right 14 150 lb 6420 kg
† Based on a fuel density of 6.75 lb/USG (0.809 kg/litre), rounded to the nearest 5 lb or
5 kg. Fuel Mass is provided for reference only and should not be considered limiting.
Gravity Refuel (Airplane Level)
Fuel Tank Fuel Mass †
Right 6500 lb 2950 kg
Left 6500 lb 2950 kg
Left & Right 13 000 lb 5900 kg
† Based on a fuel density of 6.75 lb/USG (0.809 kg/litre), rounded to the nearest 50 lb
or 25 kg. Fuel Mass is provided for reference only and should not be considered limiting.
FUEL
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 12-01-03
FUEL TANK SYSTEM (Cont)
COMPONENTS AND OPERATIONS
TANK CONSTRUCTION
The wing tanks are integral type fuel tanks that use a wet wing design and are sealed with a fuel resistant sealant.
　
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