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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.
15/05/95
CL-604 Airplane Flight Manual
PSP 604–1
DOT Approved
REV 53, Jun 04/04
Engine Air Start Envelope (In Flight)
Figure 02–05–1
LIMITATIONS
Power Plant
02–05–5
ÍÍÍÍÍ
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ÍÍÍÍÍ
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ÍÍÍÍÍ
ÍÍÍÍÍ
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ALTITUDE X 1000 FT.
0 100 200 300 350
KIAS (KNOTS)
25
20
15
10
5
0
21,000 ft
STARTER
ASSISTED
10,000 ft
15,000 ft
300 348
N2
12%
W’MILL
N2
10%
8,000 ft
ÈÈÈÈÈ
ÈÈÈÈÈ
ÈÈÈÈÈ
N2
10%
W’MILL
200
15/05/95
CL-604 Airplane Flight Manual
PSP 604–1
DOT Approved
REV 53, Jun 04/04
LIMITATIONS
Power Plant
02−05−6
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 fuel 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%.
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 there
is at least 1996 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.
On airplanes incorporating Canadair 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.
15/05/95
CL-604 Airplane Flight Manual
PSP 604−1
DOT Approved
REV 63, Sep 11/06
LIMITATIONS
Power Plant
02–05–7
Auxiliary Tank Quantity / Tail Tank Quantity
– Relation Versus Centre of Gravity
Figure 02–05–2
AUXILIARY TANK QUANTITY X 1000 LB
0
TAIL TANK QUANTITY X 1000 LB
1
0
3
2
1.0 2.0 3.0
5
4
6
7
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