Longitudinal control.

CFR · 2024-01-01 · US · Title 14

(a) It must be possible, at any point between the trim speed prescribed in § 25.103(b)(6) and stall identification (as defined in § 25.201(d)), to pitch the nose downward so that the acceleration to this selected trim speed is prompt with (1) The airplane trimmed at the trim speed prescribed in § 25.103(b)(6); (2) The landing gear extended; (3) The wing flaps (i) retracted and (ii) extended; and (4) Power (i) off and (ii) at maximum continuous power on the engines. (b) With the landing gear extended, no change in trim control, or exertion of more than 50 pounds control force (representative of the maximum short term force that can be applied readily by one hand) may be required for the following maneuvers: (1) With power off, flaps retracted, and the airplane trimmed at 1.3 V (2) Repeat paragraph (b)(1) except initially extend the flaps and then retract them as rapidly as possible. (3) Repeat paragraph (b)(2), except at the go-around power or thrust setting. (4) With power off, flaps retracted, and the airplane trimmed at 1.3 V (5) Repeat paragraph (b)(4) except with flaps extended. (6) With power off, flaps extended, and the airplane trimmed at 1.3 V (c) It must be possible, without exceptional piloting skill, to prevent loss of altitude when complete retraction of the high lift devices from any position is begun during steady, straight, level flight at 1.08 V (1) Simultaneous movement of the power or thrust controls to the go-around power or thrust setting; (2) The landing

official document · source cfr-2024 · id 14:§ 25.145