Sec. 23.145 - Longitudinal control.
(a) With the airplane as nearly as
possible in trim at 1.3 V
(1) Maximum continuous power on each engine;
(2) Power off; and
(3) Wing flap and landing gear --
(i) retracted, and
(b) Unless otherwise required, it must be possible to carry out the following maneuvers without requiring the application of single-handed control forces exceeding those specified in §23.143(c). The trimming controls must not be adjusted during the maneuvers:
(1) With the landing gear extended, the
flaps retracted, and the airplanes as nearly as possible in trim at 1.4 V
(i) With power off; and
(ii) With the power necessary to maintain level flight in the initial condition.
(2) With landing gear and flaps
extended, power off, and the airplane as nearly as possible in trim at 1.3
(3) With landing gear and flaps
extended, in level flight, power necessary to attain level flight at 1.1 V
(i) From the fully extended position to the most extended gated position;
(ii) Between intermediate gated positions, if applicable; and
(iii) From the least extended gated position to the fully retracted position.
(4) With power off, flaps and landing
gear retracted and the airplane as nearly as possible in trim at 1.4 V
(5) With power off, landing gear and
flaps extended, and the airplane as nearly as possible in trim at V
(6) With maximum takeoff power, landing
gear retracted, flaps in the takeoff position, and the airplane as nearly
as possible in trim at V
(c) At speeds above V
(d) It must be possible, with a pilot
control force of not more than 10 pounds, to maintain a speed of not more
(e) By using normal flight and power controls, except as otherwise noted in paragraphs (e)(1) and (e)(2) of this section, it must be possible to establish a zero rate of descent at an attitude suitable for a controlled landing without exceeding the operational and structural limitations of the airplane, as follows:
(1) For single-engine and multiengine airplanes, without the use of the primary longitudinal control system.
(2) For multiengine airplanes --
(i) Without the use of the primary directional control; and
(ii) If a single failure of any one connecting or transmitting link would affect both the longitudinal and directional primary control system, without the primary longitudinal and directional control system.
[Doc. No. 26269, 58 FR 42157, Aug. 6, 1993; Amdt.
23-45, 58 FR 51970, Oct. 5, 1993, as amended by Amdt. 23-50, 61 FR 5188,
Feb. 9, 1996]