CS 29.473 Ground loading conditions and assumptions

• ED Decision 2003/16/RM found in: CS-29 Amdt 11 - Large Rotercraft (Feb 2023)

CS 29.473 Ground loading conditions and assumptions ED Decision 2003/16/RM (a) For specified landing conditions, a design maximum weight must be used that is not less than the maximum weight. A rotor lift may be assumed to act through the centre of gravity throughout the landing impact. This lift may not exceed two- thirds of the design maximum weight. (b) Unless otherwise prescribed, for each specified landing condition, the rotorcraft must be designed for a limit load factor of not less than the limit inertia load factor substantiated under [CS 29.725](#_DxCrossRefBm1178331821). (c) Triggering or actuating devices for additional or supplementary energy absorption may not fail under loads established in the tests prescribed in [CS 29.725](#_DxCrossRefBm1178331821) and [29.727](#_DxCrossRefBm1178331820), but the factor of safety prescribed in [CS 29.303](#_DxCrossRefBm1178331783) need not be used. CS 29.473 Ground loading conditions and assumptions ED Decision 2003/16/RM (a) For specified landing conditions, a design maximum weight must be used that is not less than the maximum weight. A rotor lift may be assumed to act through the centre of gravity throughout the landing impact. This lift may not exceed two- thirds of the design maximum weight. (b) Unless otherwise prescribed, for each specified landing condition, the rotorcraft must be designed for a limit load factor of not less than the limit inertia load factor substantiated under [CS 29.725](#_DxCrossRefBm1513259428). (c) Triggering or actuating devices for additional or supplementary energy absorption may not fail under loads established in the tests prescribed in [CS 29.725](#_DxCrossRefBm1513259428) and [29.727](#_DxCrossRefBm1513259427), but the factor of safety prescribed in [CS 29.303](#_DxCrossRefBm1513259401) need not be used. #### CS 29.473 Ground loading conditions and assumptions *ED Decision 2003/16/RM* (a) For specified landing conditions, a design maximum weight must be used that is not less than the maximum weight. A rotor lift may be assumed to act through the centre of gravity throughout the landing impact. This lift may not exceed two- thirds of the design maximum weight. (b) Unless otherwise prescribed, for each specified landing condition, the rotorcraft must be designed for a limit load factor of not less than the limit inertia load factor substantiated under [CS 29.725](#_DxCrossRefBm1685772286). (c) Triggering or actuating devices for additional or supplementary energy absorption may not fail under loads established in the tests prescribed in [CS 29.725](#_DxCrossRefBm1685772286) and [29.727](#_DxCrossRefBm1685772285), but the factor of safety prescribed in [CS 29.303](#_DxCrossRefBm1685772248) need not be used.