CS-VLA 561 General

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

CS-VLA 561 General ED Decision 2003/18/RM (a) The aeroplane, although it may be damaged in emergency landing conditions, must be designed as prescribed in this paragraph to protect each occupant under those conditions. (b) The structure must be designed to give each occupant reasonable chances of escaping injury in a minor crash landing when (1) Proper use is made of seat belts and shoulder harnesses; and (2) The occupant experiences the ultimate inertia forces listed below - Ultimate Inertia Load Factors Upward 3.0 g Forward 9.0 g Sideward 1.5 g. (c) Each item of mass that could injure an occupant if it came loose must be designed for the load factors stated above, except that the engine mount and supporting structure must withstand 15 g forward for engines installed behind and above the seating compartment. (d) The structure must be designed to protect the occupants in a complete turnover, assuming, in the absence of a more rational analysis - (1) An upward ultimate inertia force of 3g; and (2) A coefficient of friction of 0.5 at the ground. (e) Each aeroplane with retractable landing gear must be designed to protect each occupant in a landing - (1) With the wheels retracted; (2) With moderate descent velocity; and (3) Assuming, in the absence of a more rational analysis (i) A downward ultimate inertia force of 3g; and (ii) A coefficient of friction of 0.5 at the ground.