Sec. 23.161 - Trim.
(a) General. Each airplane must meet the trim requirements of this section after being trimmed and without further pressure upon, or movement of, the primary controls or their corresponding trim controls by the pilot or the automatic pilot. In addition, it must be possible, in other conditions of loading, configuration, speed and power to ensure that the pilot will not be unduly fatigued or distracted by the need to apply residual control forces exceeding those for prolonged application of §23.143(c). This applies in normal operation of the airplane and, if applicable, to those conditions associated with the failure of one engine for which performance characteristics are established.
(b) Lateral and directional trim. The airplane must maintain lateral and directional trim in level flight with the landing gear and wing flaps retracted as follows:
(1) For normal, utility, and acrobatic
category airplanes, at a speed of 0.9 V
(2) For commuter category airplanes, at
all speeds from 1.4 V
(c) Longitudinal trim. The airplane must maintain longitudinal trim under each of the following conditions:
(1) A climb with --
(i) Takeoff power, landing gear retracted, wing flaps in the takeoff position(s), at the speeds used in determining the climb performance required by §23.65; and
(ii) Maximum continuous power at the speeds and in the configuration used in determining the climb performance required by §23.69(a).
(2) Level flight at all speeds from the
lesser of V
(3) A descent at V
(4) Approach with landing gear extended and with --
(i) A 3 degree angle of descent, with
flaps retracted and at a speed of 1.4 V
(ii) A 3 degree angle of descent, flaps
in the landing position(s) at V
(iii) An approach gradient equal to the
steepest used in the landing distance demonstrations of §23.75, flaps in
the landing position(s) at V
(d) In addition, each multiple airplane must maintain longitudinal and directional trim, and the lateral control force must not exceed 5 pounds at the speed used in complying with §23.67(a), (b)(2), or (c)(3), as appropriate, with --
(1) The critical engine inoperative, and if applicable, its propeller in the minimum drag position;
(2) The remaining engines at maximum continuous power;
(3) The landing gear retracted;
(4) Wing flaps retracted; and
(5) An angle of bank of not more than five degrees.
(e) In addition, each commuter category
airplane for which, in the determination of the takeoff path in accordance
with §23.57, the climb in the takeoff configuration at V
(1) The critical engine inoperative and its propeller in the minimum drag position;
(2) The remaining engine(s) at takeoff power;
(3) Landing gear retracted;
(4) Wing flaps in the takeoff position(s); and
(5) An angle of bank not exceeding 5 degrees.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23-21, 43 FR 2318, Jan. 16, 1978; Amdt. 23-34, 52 FR
1828, Jan. 15, 1987; Amdt. 23-42, 56 FR 351, Jan. 3, 1991; 56 FR 5455,
Feb. 11, 1991; Amdt. 23-50, 61 FR 5189, Feb. 9, 1996]