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Wing and cowl anti-ice = Off
10th stage bleeds = Closed
As shown in the example (Figure 06−07−1, Anti-ice Off), the maximum landing weight
limited by climb requirements is 24,500 kg (54,013 lb). The landing weight in this case is
greater than the maximum approved landing weight (Refer to Chapter 2; LIMITATIONS –
STRUCTURAL WEIGHT) and is not considered limiting.
PERFORMANCE
Landing Performance
06−07−2
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE LANDING WEIGHT (CONT'D)
DFM0607_001 ldg_watlim_405_ha.uni
PERFORMANCE
Landing Performance
06−07−3
REV 66, Feb 01/07
Landing Weight Limited by Climb Requirements − Approach Flaps 20°/Landing Flaps 45°
Figure 06−07−1
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE LANDING WEIGHT (CONT'D)
FAA Certified Airplanes
The maximum landing weight limited by climb requirements for varying conditions of airport
pressure altitude and temperature for the flaps 20° approach climb configuration and a
subsequent landing flaps 45° configuration, are given in Figure 06−07−1. The chart
incorporates all applicable anti-icing and 10th stage bleeds combinations.
NOTE
If ice accumulation is suspected on unprotected surfaces, then reduce
the maximum landing weight values derived from Figure 06−07−1 by
800 kg (1,764 lb).
Example: ANTI-ICE ON
Associated Conditions:
Temperature = –8°C
Airport pressure altitude = 4,000 ft
Cowl anti-ice = On
10th stage bleeds = Closed
As shown in the example (Figure 06−07−1, Anti-ice On), the maximum landing weight
limited by climb requirements is 23,400 kg (51,588 lb). The landing weight in this case is
greater than the maximum approved landing weight (Refer to Chapter 2; LIMITATIONS –
STRUCTURAL WEIGHT) and is not considered limiting.
Example: ANTI-ICE OFF
Associated Conditions:
Temperature = 27°C
Airport pressure altitude = 4,000 ft
Wing and cowl anti-ice = Off
10th stage bleeds = Closed
As shown in the example (Figure 06−07−1, Anti-ice Off), the maximum landing weight
limited by climb requirements is 23,000 kg (50,706 lb). The landing weight in this case is
greater than the maximum approved landing weight (Refer to Chapter 2; LIMITATIONS –
STRUCTURAL WEIGHT) and is not considered limiting.
PERFORMANCE
Landing Performance
06−07−4
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. MAXIMUM ALLOWABLE LANDING WEIGHT (CONT'D)
FAA Certified Airplanes
DFM0607_002 ldg_watlim_faa_ha.uni
Landing Weight Limited by Climb Requirements − Approach Flaps 20°/Landing Flaps 45°
Figure 06−07−1
PERFORMANCE
Landing Performance
06−07−5
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
3. LANDING FIELD LENGTH AND SPEED
A. Landing Field Length and Landing Speed, Flaps 45°
The landing field length required for varying conditions of airplane landing weight, airport
pressure altitude and wind is provided by Figure 06−07−2. The actual landing distance
required is also given within this chart.
The landing approach speed (VREF) for varying airplane landing weights and airport pressure
altitude is also given by Figure 06−07−2.
The actual landing distance given on Figure 06−07−2 is the distance from a 50 foot height at
VREF with flaps 45°, to a full stop on a smooth, dry, level, hard-surfaced runway and
ISA temperature.
NOTE
1. The landing field length derived from Figure 06−07−2 includes
factors for operational rules which require use of 60% of the available
runway (landing field length required).
2. Operational rules may require that for wet or slippery runway surfaces,
the runway length available be at least 115% of the landing field length
derived from Figure 06−07−2 .
Example:
Associated Conditions:
Landing gross weight = 16,000 kg (35,274 lb)
Airport pressure altitude = 2,000 feet
Wind = 20 knots, headwind
The example in Figure 06−07−2, shows that for the above conditions, the actual landing
distance is 750 meters (2,461 feet) and the landing field length is 1,250 meters (4,100 feet).
VREF for the same conditions as above is 128 KIAS.
PERFORMANCE
Landing Performance
06−07−6
　
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