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E. FUEL SYSTEM (Cont’d)
4. On airplanes 3015 and subsequent equipped with Forward and Aft
fuselage fuel tanks, maximum usable fuel quantity is:
Left Main Tank 4,909 lb (2,227 kg)
Right Main Tank 4,909 lb (2,227 kg)
Fuselage Tanks 6,868 lb (3,115 kg)
Total 16,686 lb (7,569 kg)
5. On airplanes 3015 and subsequent equipped with Aft fuselage fuel tank
only, maximum usable fuel quantity is:
Left Main Tank 4,909 lb (2,227 kg)
Right Main Tank 4,909 lb (2,227 kg)
Fuselage Tanks 5,736 lb (2,601 kg)
Total 15,554 lb (7,055 kg)
6. On airplanes 3015 and subsequent equipped with Forward and Aft
fuselage fuel tanks, incorporating Canadair Service Bulletin 601−0535,
maximum usable fuel quantity is:
Left Main Tank 4,909 lb (2,227 kg)
Right Main Tank 4,909 lb (2,227 kg)
Fuselage Tanks 2,610 lb (1,184 kg)
Total 12,428 lb (5,638 kg)
On airplanes incorporating Canadair Service Bulletin 601−0535, operation
with more than 2,610 lb (1,184 kg) of fuel in the auxiliary tank is
prohibited.
N O T E
Following a rejected take-off on airplanes
incorporating Canadair Service Bulletin
601−0535, inspect the forward auxiliary tank
to ensure that there has been no migration of
fuel, in accordance with paragraph 2.C. of
Canadair Service Bulletin 601−0535.
F. STALL PROTECTION SYSTEM
Both stall protection systems must be fully operative for take-off and
remain on for all phases of flight.
The stall protection test indicator must only be used for S.P.S.
functional test purposes.
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
DOT Approved
Jan 19/07
44,600/45,100
LIMITATIONS
Page 28
8. SYSTEMS LIMITATIONS (Cont’d)
G. NOT USED
H. NOT USED
I. NOT USED
J. WHEEL BRAKE COOLING LIMITATIONS
Brake cooling times (established in accordance with the procedures in
NORMAL PROCEDURES-LANDING GEAR WHEELS AND BRAKES) must be observed
between a landing or a low-energy rejected take-off (RTO) and a
subsequent take-off, to ensure that sufficient brake energy is available
to bring the airplane to a complete stop, if the subsequent take-off is
rejected.
If a fusible plug releases, the affected wheel, brakes and the anti-skid
wheel speed sensors must be inspected in accordance with the procedures
in the CL-601 Time Limits/Maintenance Checks, PSP601−5, and any damage
rectified before the next take-off.
K. WHEEL BRAKES ANTI-SKID
Take-off with the wheel brakes anti-skid system inoperative is
prohibited.
L. BLEED AIR SYSTEMS
The bleed air 10th stage valves must be closed for take-off and landing
with cowl and/or wing anti-ice systems on.
M. NOT USED
N. TIRE PRESSURES
When operating with 25.75 x 6.75 − 14 PR mainwheel tires at unloaded
inflation pressures between 198 psi and 145 psi, the maximum take-off
weight (MTOW) is limited (refer to Figures 8 and 9).
The maximum nosewheel tire pressure is 151 psi (1041 kPa) +5%, −0 on the
ground.
On airplanes incorporating Canadair Service Bulletin 601−0205,
Modification − Flight Compartment Tire Pressure Caution Placard − Special
Operating Conditions Only:
Tire pressures must be verified daily and a placard installed on the
pilot’s instrument panel.
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
canadair
chaiienQer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
　
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