[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: 14CFR25.203]



[Page 365]

 

                     TITLE 14--AERONAUTICS AND SPACE

 

CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION

 

PART 25_AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES--Table 

of Contents

 

                            Subpart B_Flight

 

Sec. 25.203  Stall characteristics.



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

unreversed use of the aileron and rudder controls, up to the time the 

airplane is stalled. No abnormal nose-up pitching may occur. The 

longitudinal control force must be positive up to and throughout the 

stall. In addition, it must be possible to promptly prevent stalling and 

to recover from a stall by normal use of the controls.

    (b) For level wing stalls, the roll occurring between the stall and 

the completion of the recovery may not exceed approximately 20 degrees.

    (c) For turning flight stalls, the action of the airplane after the 

stall may not be so violent or extreme as to make it difficult, with 

normal piloting skill, to effect a prompt recovery and to regain control 

of the airplane. The maximum bank angle that occurs during the recovery 

may not exceed--

    (1) Approximately 60 degrees in the original direction of the turn, 

or 30 degrees in the opposite direction, for deceleration rates up to 1 

knot per second; and

    (2) Approximately 90 degrees in the original direction of the turn, 

or 60 degrees in the opposite direction, for deceleration rates in 

excess of 1 knot per second.



[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-84, 

60 FR 30750, June 9, 1995]