[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: 14CFR23.155]



[Page 195]

 

                     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. 23.155  Elevator control force in maneuvers.



    (a) The elevator control force needed to achieve the positive limit 

maneuvering load factor may not be less than:

    (1) For wheel controls, W/100 (where W is the maximum weight) or 20 

pounds, whichever is greater, except that it need not be greater than 50 

pounds; or

    (2) For stick controls, W/140 (where W is the maximum weight) or 15 

pounds, whichever is greater, except that it need not be greater than 35 

pounds.

    (b) The requirement of paragraph (a) of this section must be met at 

75 percent of maximum continuous power for reciprocating engines, or the 

maximum continuous power for turbine engines, and with the wing flaps 

and landing gear retracted--

    (1) In a turn, with the trim setting used for wings level flight at 

VO; and

    (2) In a turn with the trim setting used for the maximum wings level 

flight speed, except that the speed may not exceed VNE or 

VMO/MMO, whichever is appropriate.

    (c) There must be no excessive decrease in the gradient of the curve 

of stick force versus maneuvering load factor with increasing load 

factor.



[Amdt. 23-14, 38 FR 31819, Nov. 19, 1973; 38 FR 32784, Nov. 28, 1973, as 

amended by Amdt. 23-45, 58 FR 42158, Aug. 6, 1993; Amdt. 23-50, 61 FR 

5189 Feb. 9, 1996]