[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: 14CFR23.203]



[Page 199-200]

 

                     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 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



[[Page 200]]



    (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]