§25.397. Control system loads. — Inbound Citations

(1) The maximum control forces expected in service as specified in §§ 25.301 and 25.397.

(b) Pilot effort effects, in § 25.397;

(b) Pilot corrective action may be assumed to be initiated at the time maximum yawing velocity is reached, but not earlier than two seconds after the engine failure. The magnitude of the corrective action may be based on the control forces specified in § 25.397(b) except that lower forces may be assumed where it is shown by anaylsis or test that these forces can control the yaw and roll resulting from the prescribed engine failure conditions.

(a) Trim tabs must be designed to withstand loads arising from all likely combinations of tab setting, primary control position, and airplane speed (obtainable without exceeding the flight load conditions prescribed for the airplane as a whole), when the effect of the tab is opposed by pilot effort forces up to those specified in § 25.397(b).

(c) The loads must not be less than those resulting from application of the minimum forces prescribed in § 25.397(c).

(2) The minimum forces specified in § 25.397(c).

(i) The loads corresponding to the maximum pilot loads in § 25.397(c) for each pilot alone; or