Minimum control speed.

CFR · 2024-01-01 · US · Title 14

(a) In establishing the minimum control speeds required by this section, the method used to simulate critical engine failure must represent the most critical mode of powerplant failure with respect to controllability expected in service. (b) V (c) (1) Maximum available takeoff power or thrust on the engines; (2) The most unfavorable center of gravity; (3) The airplane trimmed for takeoff; (4) The maximum sea level takeoff weight (or any lesser weight necessary to show (5) The airplane in the most critical takeoff configuration existing along the flight path after the airplane becomes airborne, except with the landing gear retracted; (6) The airplane airborne and the ground effect negligible; and (7) If applicable, the propeller of the inoperative engine— (i) Windmilling; (ii) In the most probable position for the specific design of the propeller control; or (iii) Feathered, if the airplane has an automatic feathering device acceptable for showing compliance with the climb requirements of § 25.121. (d) The rudder forces required to maintain control at (e) V (1) The airplane in each takeoff configuration or, at the option of the applicant, in the most critical takeoff configuration; (2) Maximum available takeoff power or thrust on the operating engines; (3) The most unfavorable center of gravity; (4) The airplane trimmed for takeoff; and (5) The most unfavorable weight in the range of takeoff weights. (f) V (1) The airplane in the most critical configuration (or, at the option

official document · source cfr-2024 · id 14:§ 25.149