[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: 14CFR23.147]



[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. 23.147  Directional and lateral control.



    (a) For each multiengine airplane, it must be possible, while 

holding the wings level within five degrees, to make sudden changes in 

heading safely in both directions. This ability must be shown at 1.4 

VS1 with heading changes up to 15 degrees, except that the 

heading change at which the rudder force corresponds to the limits 

specified in Sec. 23.143 need not be exceeded, with the--

    (1) Critical engine inoperative and its propeller in the minimum 

drag position;

    (2) Remaining engines at maximum continuous power;

    (3) Landing gear--

    (i) Retracted; and

    (ii) Extended; and

    (4) Flaps retracted.

    (b) For each multiengine airplane, it must be possible to regain 

full control of the airplane without exceeding a bank angle of 45 

degrees, reaching a dangerous attitude or encountering dangerous 

characteristics, in the event of a sudden and complete failure of the 

critical engine, making allowance for a delay of two seconds in the 

initiation of recovery action appropriate to the situation, with the 

airplane initially in trim, in the following condition:

    (1) Maximum continuous power on each engine;

    (2) The wing flaps retracted;

    (3) The landing gear retracted;

    (4) A speed equal to that at which compliance with Sec. 23.69(a) 

has been shown; and

    (5) All propeller controls in the position at which compliance with 

Sec. 23.69(a) has been shown.

    (c) For all airplanes, it must be shown that the airplane is safely 

controllable without the use of the primary lateral control system in 

any all-engine configuration(s) and at any



[[Page 194]]



speed or altitude within the approved operating envelope. It must also 

be shown that the airplane's flight characteristics are not impaired 

below a level needed to permit continued safe flight and the ability to 

maintain attitudes suitable for a controlled landing without exceeding 

the operational and structural limitations of the airplane. If a single 

failure of any one connecting or transmitting link in the lateral 

control system would also cause the loss of additional control 

system(s), compliance with the above requirement must be shown with 

those additional systems also assumed to be inoperative.



[Doc. No. 27807, 61 FR 5188, Feb. 9, 1996]