(1)
Wings Flaps : Retracted, fully extended, and each intermediate normal ope-rating position;]

(2)
Landing Gear :Retracted and extended;

(3)
Cowl Flaps : Appropriate to con.guration;

(4)
[Power :

(i)
Power o.; and

(ii)
75percent maximum continuouspower.However,if thepower-to-weight ratio at75percent of maximum continuouspower resultsin extreme nose-up attitudes, the test may be carried out with the power required for level .ight in the landing con.guration at maximum landing weight and a speed of1.4 VS0, except that thepower may not be less than 50percent of maximum continuouspower.]

(5)
Trim : The airplane trimmed at a speed as near 1.5 VS1 as practicable.

(6)
[Propeller : Full increase rpm position for the power o. condition.] Amdt. 23-50, E.. 3/11/96

FAR23.205 :[Removed.]
[Removed.] Amdt. 23-50, E.. 03/11/96
FAR 23.207 : Stall warning.
(a)
Theremustbeaclearanddistinctivestall warning,with the .apsandlandinggear in any normal position, in straight and turning .ight.

(b)
The stall warning may befurnished eitherthrough theinherent aerodynamicquali-ties of the airplane or by a device that will give clearly distinguishable indications under expected conditions of .ight. However, a visual stall warning device that requires the attention of the crew within the cockpit is not acceptable by itself.

(c)
[During the stall tests required by Sec. 23.201(b) and Sec. 23.203(a)(1), the stall warning must begin at a speed exceeding the stalling speed by a margin of not less than 5 knots and must continue until the stall occurs.

(d)
When followingproceduresfurnished in accordance with Sec. 23.1585, the stall war-ning must not occurduring a takeo. with all engines operating, a takeo. continued with one engine inoperative, or during an approach to landing.

′
Elodie Roux. Septembre 2003
Subpart B : Flight
(e)
During the stall tests required by Sec. 23.203(a)(2), the stall warning must begin su.ciently in advance of the stall for the stall to be averted by pilot action taken after the stall warning .rst occurs.

(f)
For acrobatic categoryairplanes, an arti.cial stall warning maybe mutable,provided that it is armed automatically during takeo. and rearmed automatically in the approach con.guration.]

Amdt. 23-50, E.. 03/11/96
29.8 Spinning
FAR 23.221 : Spinning.
(a) [Normal category airplanes. A single-engine, normal category airplane must be able to recover from a one-turn spin or a three-second spin, whichever takes longer, in not more than one additional turn after initiation of the .rst control action for recovery, or demonstrate compliance with the optional spin resistant requirements of this section.
(1)
The following apply to one turn or three-second spins :

(i)
For both the .aps-retracted and .aps-extended conditions, the applicable airspeed limit and positive limit maneuvering load factor must not be exceeded;

(ii)
No controlforces or characteristic encounteredduringthe spin or recovery may adversely a.ect prompt recovery;

(iii) It must be impossible to obtain unrecoverable spins with any use of the .ightorenginepowercontrolseitheratthe entryintoorduring the spin; and
(iv) For the .aps-extended condition, the .aps may be retracted during the recovery but not before rotation has ceased.

(2)
At the applicant’s option, the airplane may be demonstrated to be spin resis-tant by the following :

(i)
During the stall maneuvers contained in Sec. 23.201, the pitch control must be pulled back and held against the stop. Then, using ailerons and rudders in the proper direction, it must be possible to maintain wings-level .ight within 15 degrees of bank and to roll the airplane from a 30 degree bank in one direction to a 30 degree bank in the other direction;
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 1(138)