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The climb gradient of an aircraft after take-off is 6% in standard atmosphere, no wind, at 0 ft pressure altitude. Using the following corrections:

± 0.2% / 1 000 ft field elevation
± 0.1% / °C from standard temperature
-1% with wing anti-ice -0.5% with engine anti-ice.

The climb gradient after take-off from an airport situated at 1 000 ft, 17°C; QNH 1013,25 hPa, with wing and engine anti-ice operating for a functional check is:

  • A
    4.9%
  • B
    4.3%
  • C
    4.7%
  • D
    3.9%
Corrections to apply:
  • altitude -0.2%
  • temperature -0.4 % (ISA + 4)
  • wing and engine anti-ice -1.5%
Therefore the new climb gradient = 6 - 0.2 - 0.4 - 1.5 => 3.9%

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