Amdt. 23-45, E.. 09/07/93

29.7 Stalls
FAR 23.201 : Wings level stall.
(a) [It must be possible to produce and to correct roll byunreversed use of the rolling control and to produce and to correct yaw by unreversed use of the directional control, up to the time the airplane stalls.
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Elodie Roux. Septembre 2003
Subpart B : Flight
(b)
The wings level stall characteristics must be demonstrated in .ight as follows. Star-ting from a speed at least 10 knots above the stall speed, the elevator control must be pulled back so that the rate of speed reduction will not exceed one knot per second until a stall is produced, as shown by either :

(1)
An uncontrollabledownwardpitching motion of the airplane;

(2)
A downward pitching motion of the airplane that results from the activation of a stall avoidancedevice(for example, stickpusher); or

(3)
The control reaching the stop.

(c)
Normal use of elevator control for recovery is allowed after the downward pitching motion ofparagraphs(b)(1) or(b)(2) of this sectionhas unmistakablybeenpro-duced, of after the control has been held against the stop for not less than the longer of two seconds or the time employed in the minimum steady slight speed determination of Sec. 23.49.

(d)
During the entry into and the recovery from the maneuver, it must be possible to prevent more than 15 degrees of roll or yaw by the normal use of controls.

(e)
Compliance with the requirements of this section mustbe shown under thefollowing conditions :

(1)
Wing Flaps : Retracted, fully extended, and each intermediate normal opera-ting 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 ratioat75percentof maximumcontinuouspowerresultin extremenose-high 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 notbe 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 r.p.m. position for the power o. condition.] Amdt. 23-50, E.. 03/11/96

FAR 23.203 : Turning .ight and accelerated turning stalls.
[Turning.ightand acceleratedturning stallsmustbedemonstratedintestsasfollows:
(a)
Establish and maintain a coordinated turn in a 30'bank. Reduce speed by steadily andprogressively tightening theturn with the elevatoruntil the airplaneisstalled, as de.ned in Sec. 23.201(b). The rate of speed reduction must be constant, and–

(1)
Foraturning .ightstall,may notexceed oneknotpersecond; and

(2)
For an accelerated turning stall, be 3 to 5 knots per second with steadily increasing normal acceleration.

(b)
After the airplane has stalled, as de.ned in Sec. 23.201(b), it must be possible to regainwingslevel.ightby normal useof the .ight controls,butwithoutincreasing power and without–]

(1)
Excessiveloss of altitude;

(2)
Undue pitchup;

(3)
Uncontrollabletendency to spin;

(4)
[Exceedinga bank angle of 60 degrees in the original direction of the turn or 30 degrees in the opposite direction in the case of turning .ight stalls;

(5)
Exceeding a bank angle of 90 degrees in the original direction of the turn or 60 degrees in the opposite direction in the case of accelerated turning stalls; and

(6)
Exceeding the maximum permissible speed or allowable limit load factor.

(c)
Compliance with the requirements of this section mustbe shown under thefollowing conditions :
　
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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(137)