Reduced Thrust Examples
Airbus Model A300-600
And example of the conservatism inherent in the use of the assumed (flexible) temperature method of reduced thrust calculation.
Conditions A300-600
GE CF680-C2A5
Sea level
O A T = 15°C
10000ft runway
Actual airplane weight = 168 T permits assumed (flexible) temperature of 40°C
Parameters Actual temp is 15°C and assumed (flexible) temp is 40°C Actual temp is 40°C Margin
N1 (%) 108.2 108.2
V1 (KIAS/TAS) 158 / 158 158 / 165 - 7 KTAS
VR (KIAS/TAS) 161 / 161 161 / 168 - 7 KTAS
V2 (KIAS/TAS) 164 / 164 164 / 171 - 7 KTAS
Thrust at V1, Lbs per engines 43.527 43.527 0 Lbs
Far field length ---ft 9432 9980 548 ft
Accelerate-stop distance (engine-out) ---ft 9065 9980 915 ft
Accelerate-go distance (engine-out) ---ft 9432 9980 548 ft
Accelerate-go distance (all-engine) ---ft 7979 8661 681 ft
Second segment gradient % 2.65 2.51 0.0 %
Second segment rate of climb ---ft per minute 417 435 - 18 Fpm
Reduced Thrust Examples
Airbus Model A320-200
And example of the conservatism inherent in the use of the assumed (flexible) temperature method of reduced thrust calculation.
Conditions A320
GE CFM56-5A1
Sea level
O A T = 15°C
9500ft runway
Actual airplane weight = 72 T permits assumed (flexible) temperature of 40°C
Parameters Actual temp is 15°C and assumed (flexible) temp is 40°C Actual temp is 40°C Margin
N1 (%) 95.5 95.5
V1 (KIAS/TAS) 150 / 150 150 / 156 - 6 KTAS
VR (KIAS/TAS) 151 / 151 151 / 157 - 6 KTAS
V2 (KIAS/TAS) 154 / 154 154 / 161 - 7 KTAS
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