[DELTA](t) = [DELTA]1 sin([OMEGA]t) for 0 [LESS THAN EQUAL TO] t [LESS THAN EQUAL TO] tmax
Where-
[DELTA]1 = the maximum available displacement of the flight deck pitch control in the initial direction, as limited by the control system stops, control surface stops, or by pilot effort in accordance with § 25.397(b) ;
[DELTA](t) = the displacement of the flight deck pitch control as a function of time. In the initial direction, [DELTA](t) is limited to [DELTA]1. In the reverse direction, [DELTA](t) may be truncated at the maximum available displacement of the flight deck pitch control as limited by the control system stops, control surface stops, or by pilot effort in accordance with 25.397(b);
tmax = 3[PI]/2[OMEGA];
[OMEGA] = the circular frequency (radians/second) of the control deflection taken equal to the undamped natural frequency of the short period rigid mode of the airplane, with active control system effects included where appropriate; but not less than:
Where
V = the speed of the airplane at entry to the maneuver.
VA = the design maneuvering speed prescribed in § 25.335(c) .
[DELTA](t) = [DELTA]1 sin([OMEGA]t) for 0 [LESS THAN EQUAL TO] t [LESS THAN EQUAL TO] t1
[DELTA](t) = [DELTA]1 for t1 [LESS THAN EQUAL TO] t [LESS THAN EQUAL TO] t2
[DELTA](t) = [DELTA]1 sin([OMEGA][t + t1 - t2]) for t2 [LESS THAN EQUAL TO] t [LESS THAN EQUAL TO] tmax
Where-
t1 = [PI]/2[OMEGA]
t2 = t1 + [DELTA]t
tmax = t2 + [PI]/[OMEGA];
[DELTA]t = the minimum period of time necessary to allow the prescribed limit load factor to be achieved in the initial direction, but it need not exceed five seconds (see figure below).
14 C.F.R. §25.331