[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2004]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR23.203]

[Page 193-194]
 
                     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. 23.203  Turning flight and accelerated turning stalls.

    Turning flight and accelerated turning stalls must be demonstrated 
in tests as follows:
    (a) Establish and maintain a coordinated turn in a 30 degree bank. 
Reduce speed by steadily and progressively tightening the turn with the 
elevator until the airplane is stalled, as defined in Sec. 23.201(b). 
The rate of speed reduction must be constant, and--
    (1) For a turning flight stall, may not exceed one knot per second; 
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 defined in Sec. 23.201(b), it 
must be possible to regain wings level flight by normal

[[Page 194]]

use of the flight controls, but without increasing power and without--
    (1) Excessive loss of altitude;
    (2) Undue pitchup;
    (3) Uncontrollable tendency to spin;
    (4) Exceeding a bank angle of 60 degrees in the original direction 
of the turn or 30 degrees in the opposite direction in the case of 
turning flight 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 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 results 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 rpm position for the power off 
condition.

[Amdt. 23-14, 38 FR 31820, Nov. 19, 1973, as amended by Amdt. 23-45, 58 
FR 42159, Aug. 6, 1993; Amdt. 23-50, 61 FR 5191, Feb. 9, 1996]