CS 22.395 Control system loads

• ED Decision 2003/13/RM found in: Sailplane Rule Book - Part-SAO Part-SFCL CS-22 (Nov 2022)

CS 22.395 Control system loads ED Decision 2003/13/RM (a) Each flight control system, including stops, and its supporting structure must be designed for the loads corresponding to at least 125% of the computed hinge moments of the movable control surfaces in the conditions prescribed in [CS 22.415](#_DxCrossRefBm2056272133) through [CS 22.455](#_DxCrossRefBm2056272119). In computing the hinge moments reliable aerodynamic data must be used. The effects of tabs must be taken into account. In no case must the loads in any part of the system be less than those resulting from the application of 60% of the pilot efforts specified in [CS 22.397(a)](#_DxCrossRefBm2056272132). (b) Pilot forces used for design are assumed to act at the appropriate control grips or pads as they would in flight, and to be reacted at the attachments of the control system to the control surface horns.