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DFM0602_014 mxct_acu_3b2.uni
PERFORMANCE
Thrust Settings
06−02−19
REV 66, Feb 01/07
Maximum Continuous Thrust (Single Engine Climb) − 10th Stage Bleed Open/One Pack On
(Page 2 of 2)
Figure 06−02−9
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
1. THRUST SETTINGS (CONT'D)
DFM0602_015 mxct_cowl_3b.uni
PERFORMANCE
Thrust Settings
06−02−20
REV 66, Feb 01/07
Maximum Continuous Thrust (Single Engine Climb) − 10th Stage Bleed Open/One Pack On and
Engine Cowl Anti-Icing On
Figure 06−02−10
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
1. THRUST SETTINGS (CONT'D)
DFM0602_016 mxct_wing_3b_uni
PERFORMANCE
Thrust Settings
06−02−21
REV 66, Feb 01/07
Maximum Continuous Thrust (Single Engine Climb) − 10th Stage Bleed Open/One Pack On/Engine
Cowl and Wing Anti-Icing On
Figure 06−02−11
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
PERFORMANCE
Thrust Settings
06−02−22
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
THIS PAGE INTENTIONALLY LEFT BLANK
1. INTRODUCTION
The Take-Off Performance section contains the charts used to obtain the take-off performance
data for varying conditions of temperature, airport pressure altitude, and airplane weight for the
specified take-off configurations.
2. MAXIMUM ALLOWABLE TAKE-OFF WEIGHT
The maximum allowable take-off weight is limited by the most restrictive of the following:
• Maximum approved take-off weight
(Refer to Chapter 2; LIMITATIONS – STRUCTURAL WEIGHT),
• Runway length available,
• Climb requirements,
• Maximum demonstrated brake energy,
• Maximum tire speed,
• Wheel brake cooling limitations
(Refer to TURN-AROUND TIME – Cooling of Wheels, Brakes and Tires in this chapter).
PERFORMANCE
Take−Off Performance
06−03−1
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE TAKE-OFF WEIGHT (CONT'D)
A. Take-Off Weight Limited By Climb Requirements – Flaps 20°
The maximum take-off weight limited by climb requirements for a flaps-20° take-off is
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.
The weights presented in Figure 06−03−1 are limited by second segment climb gradient
requirements, as per FAR 25.121 (b). 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 21,600 kg (47,620 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
06−03−2
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE TAKE-OFF WEIGHT (CONT'D)
DFM0603_001 to_watlim_405_ha.uni
PERFORMANCE
Take−Off Performance
06−03−3
REV 66, Feb 01/07
Take-Off Weight Limited by Climb Requirements − Flaps 20°
Figure 06−03−1
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE TAKE-OFF WEIGHT (CONT'D)
FAA Certified Airplanes
The maximum take-off weight limited by climb requirements for a flaps-20° take-off is
　
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