BOMBARDIER BD-100-1A10, Operating Manual

Page: 388 / 544

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 tem-
perature 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 limit-
ing.