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 V (b) A sudden aft movement of the
pitching control at speeds above V ------------------------------------------------------------------------ Normal Angular acceleration Condition acceleration (radian/sec[INF]2[/ (n) INF]) ------------------------------------------------------------------------ Nose-up pitching............... 1.0 +39n[INF]m[/ INF]÷Vx(n[INF]m[/ INF]-1.5) Nose-down ptiching............. n[INF]m[/INF] -39n[INF]m[/ INF]÷Vx(n[INF]m[/ INF]-1.5) ------------------------------------------------------------------------ where -- (1) n (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 surface load for both
nose-up and nose-down pitching conditions is the sum of the balancing
loads at [Amdt. 23-42, 56 FR 353, Jan. 3, 1991; 56 FR
5455, Feb. 11, 1991] |