Demonstration of static longitudinal stability.

CFR · 2024-01-01 · US · Title 14

(a) (1) Critical weight; (2) Critical center of gravity; (3) Maximum continuous power; (4) The landing gear retracted; and (5) The rotorcraft trimmed at (b) (1) Critical weight; (2) Critical center of gravity; (3) Power for level flight at 0.8 V (4) The landing gear retracted; and (5) The rotorcraft trimmed at 0.8 V (c) (1) Critical weight; (2) Critical center of gravity; (3) Power required for level flight at V (4) The landing gear retracted; and (5) The rotorcraft trimmed at V (d) (1) Airspeeds from the minimum rate of descent airspeed−10 kt to the minimum rate of descent airspeed + 10 kt, with— (i) Critical weight; (ii) Critical center of gravity; (iii) The landing gear extended; and (iv) The rotorcraft trimmed at the minimum rate of descent airspeed. (2) Airspeeds from best angle-of-glide airspeed−10 kt to the best angle-of-glide airspeed + 10 kt, with— (i) Critical weight; (ii) Critical center of gravity; (iii) The landing gear retracted; and (iv) The rotorcraft trimmed at the best angle-of-glide airspeed.

official document · source cfr-2024 · id 14:§ 27.175