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determined from Figure 06−03−1, for varying conditions of ambient temperature and
airport pressure altitude, taking into account the effects of different combinations of wing
and cowl anti-icing and 10th stage bleeds, and also the use of the APR system.
For take-offs with APR off, the weights presented in Figure 06−03−1 are limited by
second segment climb gradient requirements, as per FAR 25.121 (b). For take-offs with
APR armed, the weights presented in Figure 06−03−1 are limited by approach climb
gradient requirements, as per FAR 25.121 (d), following a 15 minute flight in accordance
with the requirements of FAR 25.1001 (a). The first segment climb and final segment
climb gradient requirements, as per FAR 25.121 (a) and FAR 25.121 (c), respectively,
are not limiting.
Example: ANTI-ICE ON
Associated Conditions:
Temperature = –8°C
Airport pressure altitude = 6,000 ft
Cowl anti-ice = On
10th stage bleeds = Closed
APR = Off
As shown in the example (Figure 06−03−1, Anti-ice On), the maximum take-off weight
limited by climb requirements is 21,700 kg (47,840 lb). The take-off weight in this case
may be less than the maximum approved take-off weight (Refer to Chapter 2;
LIMITATIONS – STRUCTURAL WEIGHT) and may be considered limiting.
Example: ANTI-ICE OFF
Associated Conditions:
Temperature = 27°C
Airport pressure altitude = 6,000 ft
Wing and cowl anti-ice = Off
10th stage bleeds = Closed
APR = Off
As shown in the example (Figure 06−03−1, Anti-ice Off), the maximum take-off weight
limited by climb requirements is 20,700 kg (45,636 lb). The take-off weight in this case is
less than the maximum approved take-off weight (Refer to Chapter 2; LIMITATIONS –
STRUCTURAL WEIGHT) and is considered limiting.
PERFORMANCE
Take−Off Performance
06−03−4
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE TAKE-OFF WEIGHT (CONT'D)
FAA Certified Airplanes
DFM0603_002 to_watlim_faa_ha.uni
Take-Off Weight Limited by Climb Requirements − Flaps 20°
Figure 06−03−1
PERFORMANCE
Take−Off Performance
06−03−5
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE TAKE-OFF WEIGHT (CONT'D)
B. Take-Off Weight Limited By Brake Energy – Flaps 20°
The maximum take-off weight limited by brake energy for a flaps-20° take-off is determined
from Figure 06−03−2, for varying conditions of ambient temperature and airport pressure
altitude, wind and runway slope.
The weight derived from Figure 06−03−2 must be corrected for the following conditions:
• With 10th stage bleeds open and packs on, decrease the weight by 80 kg (176 lb);
• With only the engine cowl anti-icing on, decrease the weight by 100 kg (221 lb);
• With both engine cowl and wing anti-icing on, decrease the weight by 360 kg (794 lb);
• With the APR system off, decrease the weight by 320 kg (705 lb);
NOTE
The above decrements are cumulative except between the two
anti-icing conditions. The 10th stage bleeds must be closed for
take-off with cowl and/or wing anti-icing on.
Example:
Associated Conditions:
Temperature = 0°C
Airport pressure altitude = 10,000 feet
Wind = Calm
Runway slope = +2%
Wing and cowl anti-ice = Off
10th stage bleeds = Closed
APR = Armed
The example in Figure 06−03−2 shows that the maximum take-off weight limited by brake
energy is 20,080 kg (44,269 lb).
PERFORMANCE
Take−Off Performance
06−03−6
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE TAKE-OFF WEIGHT (CONT'D)
DFM0603_003 WTBE604RC_22APR96
PERFORMANCE
Take−Off Performance
06−03−7
REV 66, Feb 01/07
Take-Off Weight Limited By Brake Energy − Flaps 20°
Figure 06−03−2
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE TAKE-OFF WEIGHT (CONT'D)
C. Take-Off Weight Limited by Maximum Tire Speed
The maximum take-off weight limited by the maximum tire speed of 210 mph (182 knots), for
a flaps-20° take-off, in varying conditions of ambient temperature, airport pressure altitude
and wind, is given by Figure 06−03−3.
The weights derived from Figure 06−03−3 are applicable for all engine bleed configurations.
　
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