[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]