[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: 14CFR23.423]

[Page 206-207]
 
                     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 C--Structure
 
Sec. 23.423  Maneuvering loads.

    Each horizontal surface and its supporting structure, and the main 
wing of a canard or tandem wing configuration, if that surface has pitch 
control, must be designed for the maneuvering loads imposed by the 
following conditions:
    (a) A sudden movement of the pitching control, at the speed 
VA, to the maximum aft movement, and the maximum forward 
movement, as limited by the control stops, or pilot effort, whichever is 
critical.
    (b) A sudden aft movement of the pitching control at speeds above 
VA, followed by a forward movement of the pitching control 
resulting in the following combinations of normal and angular 
acceleration:

------------------------------------------------------------------------
                                     Normal
           Condition              acceleration     Angular acceleration
                                       (n)            (radian/sec2)
------------------------------------------------------------------------
Nose-up pitching...............  1.0             +39nm/Vx(nm-1.5)
Nose-down ptiching.............  nm              -39nm/Vx(nm-1.5)
------------------------------------------------------------------------


where--
    (1) nm=positive limit maneuvering load factor used in the 
design of the airplane; and
    (2) V=initial speed in knots.
    The conditions in this paragraph involve loads corresponding to the 
loads that may occur in a ``checked maneuver'' (a maneuver in which the 
pitching control is suddenly displaced in one direction and then 
suddenly moved in the opposite direction). The deflections and timing of 
the ``checked maneuver'' must avoid exceeding the limit maneuvering load 
factor. The total horizontal

[[Page 207]]

surface load for both nose-up and nose-down pitching conditions is the 
sum of the balancing loads at V and the specified value of the normal 
load factor n, plus the maneuvering load increment due to the specified 
value of the angular acceleration.

[Amdt. 23-42, 56 FR 353, Jan. 3, 1991; 56 FR 5455, Feb. 11, 1991]