CS 29.49 Performance at minimum operating speed

• ED Decision 2003/16/RM found in: CS-29 Amdt 10 - Large Rotercraft (Jan 2023)

CS 29.49 Performance at minimum operating speed ED Decision 2003/16/RM (a) For each Category A helicopter, the hovering performance must be determined over the ranges of weight, altitude and temperature for which take-off data are scheduled: (1) With not more than take-off power; (2) With the landing gear extended; and (3) At a height consistent with the procedure used in establishing the take-off, climbout and rejected take-off paths. (b) For each Category B helicopter, the hovering performance must be determined over the ranges of weight, altitude and temperature for which certification is requested, with: (1) Take-off power; (2) The landing gear extended; and (3) The helicopter in ground effect at a height consistent with normal take-off procedures. (c) For each helicopter, the out-of ground- effect hovering performance must be determined over the ranges of weight, altitude and temperature for which certification is requested, with take-off power. (d) For rotorcraft other than helicopters, the steady rate of climb at the minimum operating speed must be determined over the ranges of weight, altitude and temperature for which certification is requested, with: (1) Take-off power; and (2) The landing gear extended. CS 29.49 Performance at minimum operating speed ED Decision 2003/16/RM (a) For each Category A helicopter, the hovering performance must be determined over the ranges of weight, altitude and temperature for which take-off data are scheduled: (1) With not more than take-off power; (2) With the landing gear extended; and (3) At a height consistent with the procedure used in establishing the take-off, climbout and rejected take-off paths. (b) For each Category B helicopter, the hovering performance must be determined over the ranges of weight, altitude and temperature for which certification is requested, with: (1) Take-off power; (2) The landing gear extended; and (3) The helicopter in ground effect at a height consistent with normal take-off procedures. (c) For each helicopter, the out-of ground- effect hovering performance must be determined over the ranges of weight, altitude and temperature for which certification is requested, with take-off power. (d) For rotorcraft other than helicopters, the steady rate of climb at the minimum operating speed must be determined over the ranges of weight, altitude and temperature for which certification is requested, with: (1) Take-off power; and (2) The landing gear extended. #### CS 29.49 Performance at minimum operating speed *ED Decision 2003/16/RM* (a) For each Category A helicopter, the hovering performance must be determined over the ranges of weight, altitude and temperature for which take-off data are scheduled: (1) With not more than take-off power; (2) With the landing gear extended; and (3) At a height consistent with the procedure used in establishing the take-off, climbout and rejected take-off paths. (b) For each Category B helicopter, the hovering performance must be determined over the ranges of weight, altitude and temperature for which certification is requested, with: (1) Take-off power; (2) The landing gear extended; and (3) The helicopter in ground effect at a height consistent with normal take-off procedures. (c) For each helicopter, the out-of ground- effect hovering performance must be determined over the ranges of weight, altitude and temperature for which certification is requested, with take-off power. (d) For rotorcraft other than helicopters, the steady rate of climb at the minimum operating speed must be determined over the ranges of weight, altitude and temperature for which certification is requested, with: (1) Take-off power; and (2) The landing gear extended.