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M.L.W. (38000 lb/17237 kg)
(43000 lb/19505 kg)
MIN FLIGHT WEIGHT (26000lb/11794 kg)
For aircraft CG in this
zone, use Alternative
AUX/TAIL
Fuel Distribution
(Figure 02−05−2,
Detail C).
Centre of Gravity Limits (MTOW 47,600 lb)
Figure 02−03−3
LIMITATIONS
Centre of Gravity
Vol. 1 02−03−3
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
2. CENTRE OF GRAVITY LIMITS (MTOW 47,600 LB) (CONT'D)
On airplanes 5301 to 5547, 5549 and 5550 NOT incorporating Service Bulletin
604–28–007 and airplanes 5301 to 5571 NOT incorporating Service Bulletin 604–27–009
or 604–27–012:
The maximum permissible centre of gravity (CG) limits are as shown in Figure 02−03−4.
The airplane including interior payload, passengers and fuel (refer to Figure 02–05–2) must
be loaded such that the airplane weight and centre of gravity are maintained within the
specified limits (including variations due to fuel consumption, passenger movement, retraction
of landing gear, etc.).
40
12
14
16
18
A/C CG % MAC
A/C WEIGHT (kg)
DFM0203_005 THOUSANDS
20
22
MAX RAMP WEIGHT (47700 lb/21637 kg)
28.0%
M.T.O.W
(47600 lb/21591 kg)
50
20.0%
16.0%
25
15
A/C WEIGHT (lb)
THOUSANDS
39500 lb/17917 kg
40
45
TAKE−OFF LIMIT
44750 lb/20298 kg
M.L.W. (38000 lb/17237 kg)
M.Z.F.W. (32000 lb/14515 kg)
35
30
30 35
MIN FLIGHT WEIGHT (26000lb/11794 kg)
20 25
34.5%
For aircraft CG in this
zone, use Alternative
AUX/TAIL
Fuel Distribution
(Figure 02−05−2,
Detail C).
Centre of Gravity Limits (MTOW 47,600 lb)
Airplanes 5301 to 5547, 5549 and 5550 NOT incorporating Service Bulletin 604−28−007 and
airplanes 5301 to 5571 NOT incorporating Service Bulletin 604−27−009 or 604−27−012
Figure 02−03−4
LIMITATIONS
Centre of Gravity
Vol. 1 02−03−4
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
1. ALTITUDE AND TEMPERATURE OPERATING LIMIT
The altitude and temperature operating limit is as shown in Figure 02−04−1.
• Maximum airport pressure altitude for take-off and landing is 10,000 feet.
• Maximum operating altitude is 41,000 feet.
• Maximum ambient air temperature approved for take-off and landing is ISA + 35°C.
• Minimum ambient temperature approved for take-off is –40°C (–40°F).
• At altitudes above 25,000 feet, a safety harness must be worn by at least one pilot.
DFM0204_001 CHP1−01−17APR92
Altitude and Temperature Operating Limits
Figure 02−04−1
LIMITATIONS
Operating Limitations
Vol. 1 02−04−1
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
2. TAKE-OFF
A. Rotation Rate and Pitch Attitude
WARNING
Excessive rotation rates (exceeding 3 degrees per second) or
over-rotations may lead to high pitch attitudes and angles of attack
being attained while the aircraft is near the ground. This can reduce
stall margins significantly resulting in stick shaker/pusher activation
and potentially loss of control. Pilots must rotate smoothly towards
the target pitch attitude then transition to speed control.
B. Pitch Trim
WARNING
Failure to set the pitch trim appropriate to the computed centre of
gravity may result in excessive rotation rate at take-off.
Pitch trim must be set according to the airplane’s computed centre of gravity.
C. Take-Off Pitch Target
On airplanes NOT incorporating Service Bulletin 604−22−006:
The initial target for rotation is 10 degrees.
If Flight Director is used for take-off, set pitch target to 10 degrees. Refer to Chapter 6;
SUPPLEMENTARY PROCEDURES – AUTOMATIC FLIGHT CONTROL SYSTEM –
TAKE-OFF.
Take-off performance data contained in Chapter 6 − Performance of the Airplane Flight
Manual remains applicable.
To obtain pitch mode, select TO as normal, then rotate the Flight Control Panel (FCP) VS
pitch wheel to reduce the FD command to 10 degrees.
NOTE
The VS pitch wheel will adjust the FD command in 0.50 degree
steps.
LIMITATIONS
Operating Limitations
Vol. 1 02−04−2
REV 77, Oct 20/09
CL−604 Operating Manual
PSP 604−6
3. COLD WEATHER OPERATIONS
WARNING
Even small amounts of frost, ice, snow or slush on the wing leading
　
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