CS-VLA 395 Control system loads

• ED Decision 2003/18/RM found in: CS-VLA Amdt 1 - Very Light Aeroplanes (Mar 2009)

CS-VLA 395 Control system loads ED Decision 2003/18/RM (a) Each flight control system and its supporting structure must be designed for loads corresponding to at least 125% of the computed hinge moments of the movable control surface in the conditions prescribed in [CS-VLA 391](#_DxCrossRefBm584936695) to [459](#_DxCrossRefBm584936664). In addition, the following apply: (1) The system limit loads need not exceed the loads that can be produced by the pilot. Pilot forces used for design need not exceed the maximum forces prescribed in [CS-VLA 397(b)](#_DxCrossRefBm584936696). (2) The design must, in any case, provide a rugged system for service use, considering jamming, ground gusts, taxying downwind, control inertia, and friction. Compliance with this sub-paragraph may be shown by designing for loads resulting from application of the minimum forces prescribed in [CS-VLA 397(b)](#_DxCrossRefBm584936696). (b) A 125% factor on computed hinge movements must be used to design elevator, aileron, and rudder systems. However, a factor as low as 1.0 may be used if hinge moments are based on accurate flight test data, the exact reduction depending upon the accuracy and reliability of the data. (c) Pilot forces used for design are assumed to act at the appropriate control grips or pads as they would in flight, and to react at the attachments of the control system to the control surface horns.