Controllability and maneuverability.

CFR · 2024-01-01 · US · Title 14

(a) The rotorcraft must be safely controllable and maneuverable— (1) During steady flight; and (2) During any maneuver appropriate to the type, including— (i) Takeoff; (ii) Climb; (iii) Level flight; (iv) Turning flight; (v) Autorotation; (vi) Landing (power on and power off); and (vii) Recovery to power-on flight from a balked autorotative approach. (b) The margin of cyclic control must allow satisfactory roll and pitch control at V (1) Critical weight; (2) Critical center of gravity; (3) Critical rotor r.p.m.; and (4) Power off (except for helicopters demonstrating compliance with paragraph (f) of this section) and power on. (c) Wind velocities from zero to at least 17 knots, from all azimuths, must be established in which the rotorcraft can be operated without loss of control on or near the ground in any maneuver appropriate to the type (such as crosswind takeoffs, sideward flight, and rearward flight)— (1) With altitude, from standard sea level conditions to the maximum takeoff and landing altitude capability of the rotorcraft or 7000 feet density altitude, whichever is less; with— (i) Critical Weight; (ii) Critical center of gravity; (iii) Critical rotor r.p.m.; (2) For takeoff and landing altitudes above 7000 feet density altitude with— (i) Weight selected by the applicant; (ii) Critical center of gravity; and (iii) Critical rotor r.p.m. (d) Wind velocities from zero to at least 17 knots, from all azimuths, must be established in which the rotorcraft can be operated wit

official document · source cfr-2024 · id 14:§ 27.143