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To determine the landing performance of a Performance Class 1 helicopter, with the critical engine inoperative during its approach path, its mass must permit a minimum rate of climb of (1) _____ at (2) _____ above the take-off terrain.
  • A
    (1) 1 000 ft/min; (2) 150 ft
  • B
    (1) 60 m/sec; (2) 200 ft
  • C
    (1) 300 ft/min; (2) 150 ft
  • D
    (1) 100 ft/min; (2) 61 m

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.

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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