(b) Pilot effort effects. In the control surface flight loading condition, the air loads on movable surfaces and the corresponding deflections need not exceed those that would result in flight from the application of any pilot force within the ranges specified in paragraph (c) of this section. Two-thirds of the maximum values specified for the aileron and elevator may be used if control surface hinge moments are based on reliable data. In applying this criterion, the effects of servo mechanisms, tabs, and automatic pilot systems, must be considered.
(c) Limit pilot forces and torques. The limit pilot forces and torques are as follows:
|Control||Maximum forces or torques||Minimum forces or torques|
|Stick||100 lbs||40 lbs.|
|Wheel1||80 D in.-lbs2||40 D in.-lbs.|
|Stick||250 lbs||100 lbs.|
|Wheel (symmetrical)||300 lbs||100 lbs.|
|Wheel (unsymmetrical)3||100 lbs.|
|Rudder||300 lbs||130 lbs.|
1The critical parts of the aileron control system must be designed for a single tangential force with a limit value equal to 1.25 times the couple force determined from these criteria.
2 D =wheel diameter (inches).
3The unsymmetrical forces must be applied at one of the normal handgrip points on the periphery of the control wheel.
[Doc. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25–38, 41 FR 55466, Dec. 20, 1976; Amdt. 25–72, 55 FR 29776, July 20, 1990]