A7 Flight loads

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

A7 Flight loads ED Decision 2003/18/RM (a) Each flight load may be considered independent of altitude and, except for the local supporting structure for dead weight items, only the maximum design weight conditions must be investigated. (b) Tables 1 and 3 and figure A3 of this Appendix must be used to determine values of ni, n2, n3 and n4, corresponding to the maximum design weights in the desired Categories. (c) Figures A1 and A2 of this Appendix must be used to determine values of n3 and n4 corresponding to the minimum flying weights in the desired categories, and, if these load factors are greater than the load factors at the design weight, the supporting structure for dead weight items must be substantiated for the resulting higher load factors. (d) Each specified wing and tail loading is independent of the centre of gravity range. However, a c.g. range, must be selected for the aeroplane and the basic fuselage structure must be investigated for the most adverse dead weight loading conditions for the c.g. range selected. (e) The following loads and loading conditions are the minimums for which strength must be provided in the structure: (1) *Aeroplane equilibrium*. The aerodynamic wing loads may be considered to act normal to the relative wind, and to have a magnitude of 1.05 times the aeroplane normal loads (as determined from sub-paragraph [A9(b) and (c)](#_DxCrossRefBm584936946) of this Appendix) for the positive flight conditions and a magnitude equal to the aeroplane normal loads for the negative conditions. Each chordwise and normal component of this wing load must be considered. (2) *Minimum design airspeeds*. The minimum design airspeeds may be chosen by the applicant except that they may not be less than the minimum speeds found by using Table 3 of this Appendix. In addition, VCmin need not exceed values of 0.9 VH actually obtained at sea level for the lowest design weight category for which certification is desired. In computing these minimum design airspeeds, ni may not be less than 3.8. (3) *Flight load factor*. The limit flight load factors specified in Table 1 of this Appendix represent the ratio of the aerodynamic force component (acting normal to the assumed longitudinal axis of the aeroplane) to the weight of the aeroplane. A positive flight load factor is an aerodynamic force acting upward, with respect to the aeroplane.