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When determining the landing performance of a Performance Class 1 helicopter, after a critical engine failure during its approach path, its estimated landing mass must permit to climb at least with a rate of 150 ft/min at 1 000 ft, above the:
  • A
    Destination or alternate/diversion heliport.
  • B
    Destination heliport.
  • C
    Alternate heliport.
  • D
    Take-off heliport.

According to CS 29.79 - Landing - Category A Rotorcraft:

  • The landing performance must be determined and scheduled so that if the critical engine fails at any point in the approach path, the rotorcraft can either land and stop safely or climb out and attain a rotorcraft configuration and speed allowing compliance with the climb requirement of CS 29.67.
According to CS 29.67 - Climb - One Engine Inoperative (OEI):
  • For Category A rotorcraft, in the critical take-off configuration existing along the take-off path, with the critical engine inoperative and the remaining engines at maximum continuous power, the following apply:
  1. The steady rate of climb without ground effect, 61 m (200 ft) above the take-off surface, must be at least 30 m (100 ft) per minute, for each weight, altitude, and temperature.
  2. The steady rate of climb without ground effect, 305 m (1 000 ft) above the take off surface, must be at least 46 m (150 ft) per minute, for each weight, altitude, and temperature.

The fore mentioned climb requirements apply at both destination and alternate operating sites.


NOTE:
According to CAT.POL.H.200-General:

  • Helicopters operated in Performance Class 1 shall be certified in Category A or equivalent as determined by the Agency.

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