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Oct 05/06
9. FUEL
The maximum permissible fuel imbalance between the contents of the main left tank and the
main right tank is 182 kg (400 lb) for take-off and taxi.
The maximum permissible fuel imbalance between the contents of the main left tank and the
main right tank is 363 kg (800 lb) in flight.
The maximum permissible fuel imbalance between the contents of the main left tank and the
main right tank is 182 kg (400 lb) for landing.
Fuel remaining in a tank when the appropriate fuel quantity indicator reads zero is not usable.
Based upon a fuel density of 6.75 lb/US gallon, the maximum usable fuel load achieved by
pressure refueling for each tank is given below:
Left main tank 2,205 kg (4,860 lb)
Right main tank 2,205 kg (4,860 lb)
Auxiliary tank 3,251 kg (7,168 lb)
Tail tank 1,411 kg (3,112 lb)
Total 9,072 kg (20,000 lb)
To determine approximate maximum usable fuel load achieved by gravity refueling, reduce weight by 7%. Take-off with up to 230 kg (500 lb) of fuel in the auxiliary tank is permitted, provided that there is
at least 690 kg (1,500 lb) of fuel in each wing tank and no fuel in the tail tank.
Take-off with more than 230 kg (500 lb) of fuel in the auxiliary tank is permitted, provided that there is at least 1,996 kg (4400 lb) of fuel in each wing tank. The minimum fuel quantity for go-around is 230 kg (500 lb) per wing (with the airplane level) and
assuming a maximum airplane climb attitude of 10° nose up.
Normal AUX/TAIL Fuel Distribution for Take-Off:
.
Auxiliary tank quantity must be full, or at least 2.65 times the tail tank quantity, for take-off (as shown in Figure 02.05.2, Detail A, Normal Fuel Distribution for Take-Off).
OR
Provisional AUX/TAIL Fuel Distribution for Forward CG Limit Take-Off:
.
Where the normal fuel distribution would cause the airplane centre of gravity to fall ahead of the forward limit for take-off, the provisional fuel distribution may be applied to bring the airplane centre of gravity within the permissible forward CG limit (as shown in Figure 02.05.2, Detail B, Provisional Fuel Distribution for Take-Off). This fuel distribution is permitted only if the resulting CG remains ahead of 34% MAC.
LIMITATIONS Power Plant Vol. 1 02.05.7
Oct 05/06
9. FUEL (CONT'D)
TAIL TANK QUANTITY X 1000 KG
0.25 0.50 0.75 1.0 1.25 1.5 8
3.5
AUXILIARY TANK QUANTITY X 1000 LB
AUXILIARY TANK QUANTITY X 1000 LB
7
6
AUXILIARY TANK QUANTITY X 1000 KG
AUXILIARY TANK QUANTITY X 1000 KG
DFM0205_002
3.0
2.5
5 4 3 2 1 0
TAIL TANK QUANTITY X 1000 LB
Detail A . Normal Fuel Distribution for Take-Off
0.25
8 7
TAIL TANK QUANTITY X 1000 KG
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本文链接地址：庞巴迪挑战者605公务机机组操作手册 CL605-CHAPTER 2 -限制 LIMITATIONS(10)
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