[Code of Federal Regulations]

[Title 14, Volume 1]

[Revised as of January 1, 2006]

From the U.S. Government Printing Office via GPO Access

[CITE: 14CFR23.201]



[Page 199]

 

                     TITLE 14--AERONAUTICS AND SPACE

 

CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION

 

PART 23_AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND 

COMMUTER CATEGORY AIRPLANES--Table of Contents

 

                            Subpart B_Flight

 

Sec. 23.201  Wings level stall.



    (a) It must be possible to produce and to correct roll by unreversed 

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.

    (b) The wings level stall characteristics must be demonstrated in 

flight as follows. Starting 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 uncontrollable downward pitching motion of the airplane;

    (2) A downward pitching motion of the airplane that results from the 

activation of a stall avoidance device (for example, stick pusher); or

    (3) The control reaching the stop.

    (c) Normal use of elevator control for recovery is allowed after the 

downward pitching motion of paragraphs (b)(1) or (b)(2) of this section 

has unmistakably been produced, or 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 must be shown 

under the following conditions:

    (1) Wing flaps. Retracted, fully extended, and each intermediate 

normal operating position.

    (2) Landing gear. Retracted and extended.

    (3) Cowl flaps. Appropriate to configuration.

    (4) Power:

    (i) Power off; and

    (ii) 75 percent of maximum continuous power. However, if the power-

to-weight ratio at 75 percent of maximum continuous power result in 

extreme nose-up attitudes, the test may be carried out with the power 

required for level flight in the landing configuration at maximum 

landing weight and a speed of 1.4 VSO, except that the power 

may not be less than 50 percent of maximum continuous power.

    (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 off 

condition.



[Doc. No. 27807, 61 FR 5191, Feb. 9, 1996]