[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2003]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR23.201]

[Page 193]
 
                     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]