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Windmilling Altitude from 21,000 to 10,000 feet:
Airspeed from 300 to 348 KIAS, and from 12 to 55% N2.
Altitude from 10,000 to 8,000 feet:
Airspeed from 300 to 348 KIAS, and from 10 to 55% N2.
Altitude from sea level to 8,000 feet:
Airspeed 300 KIAS and from 10 to 55% N2.
NOTE
N2 should be stable or increasing.
Starter-assisted Cross Bleed Altitude from 21,000 feet to 15,000 feet:
Airspeed from 200 KIAS up to 300 KIAS, and from 0 to 55% N2.
Altitude from 15,000 feet to sea level:
Airspeed from 140 KIAS up to 300 KIAS, and from 0 to 55% N2.
15
20
25
10
5
0
0 100
350
300
KIAS (KNOTS)
ALTITUDE X 1000 FT.
200
DFM0205_001
200
15,000 ft
21,000 ft 300 348
N2 >10%
W’MILL
N2 >12%
W’MILL
8,000 ft
STARTER
ASSISTED
10,000 ft
N2 >10%
Engine Air Start Envelope (In Flight)
Figure 02−05−1
LIMITATIONS
Power Plant
02−05−4
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
8. 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 2205 kg (4,860 lb)
Right main tank 2205 kg (4,860 lb)
Auxiliary tank 3251 kg (7,168 lb)
Tail tank 1411 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%.
On airplanes incorporating Service Bulletin 604−28−007:
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.
OR
Alternative AUX/TAIL Fuel Distribution for Aft CG Limit at ZFW:
• If the aircraft CG at ZFW is within the envelope aft lower zone (CG between 32,000 lb/35%,
30,000 lb/34%, 28,000 lb/34%, 26,000 lb/32.5% and 26,000 lb/35%) an alternative manual
fuel distribution may be applied. Auxiliary tank quantity must be full, or at least 2.95 times
the tail tank quantity (as shown in Figure 02−05−2, Detail C, Alternative Fuel Distribution
for Take-Off).
LIMITATIONS
Power Plant
02−05−5
REV 71, Oct 31/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
8. FUEL (CONT'D)
DFM0205_005
Auxiliary Tank Quantity/Tail Tank Quantity − Relation Verses Centre of Gravity (Page 1 of 2)
Figure 02−05−2
LIMITATIONS
Power Plant
02−05−6
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
8. FUEL (CONT'D)
DFM0205_006
Auxiliary Tank Quantity/Tail Tank Quantity − Relation Verses Centre of Gravity (Page 2 of 2)
Figure 02−05−2
LIMITATIONS
Power Plant
02−05−7
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
8. FUEL (CONT'D)
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 (1500 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 the
minimum quantity of fuel in each wing tank is as per Figure 02−05−3.
• For example, if there is at least 1,724 kg (3,800 lb) of fuel in each wing tank, then according
　
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