(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 VH, VC, or VMO/MO, whichever is lowest; and
(2) For commuter category airplanes, at all speeds from 1.4 VS1to the lesser of VHor VMO/MMO.
(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 VHand either VNOor VMO/MMO(as appropriate), to 1.4 VS1, with the landing gear and flaps retracted.
(3) A descent at VNOor VMO/MMO, whichever is applicable, with power off and with the landing gear and flaps retracted.
(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 VS1;
(ii) A 3 degree angle of descent, flaps in the landing position(s) at VREF; and
(iii) An approach gradient equal to the steepest used in the landing distance demonstrations of §23.75, flaps in the landing position(s) at VREF.
(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 V2extends beyond 400 feet above the takeoff surface, it must be possible to reduce the longitudinal and lateral control forces to 10 pounds and 5 pounds, respectively, and the directional control force must not exceed 50 pounds at V2with—
(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]