[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: 14CFR23.155]

[Page 189]
 
                     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]