CS-VLA 333 Flight envelope

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

CS-VLA 333 Flight envelope ED Decision 2003/18/RM (a) *General*. Compliance with the strength requirements of this subpart must be shown at any combination of airspeed and load factor on and within the boundaries of a flight envelope (similar to the one in sub-paragraph (d) of this paragraph) that represents the envelope of the flight loading conditions specified by the manoeuvring and gust criteria of sub-paragraphs (b) and (c) of this paragraph respectively. (b) *Manoeuvring envelope*. Except where limited by maximum (static) lift coefficients, the aeroplane is assumed to be subjected to symmetrical manoeuvres resulting in the following limit load factors: (1) The positive manoeuvring load factor specified in [CS-VLA 337](#_DxCrossRefBm584936676) at speeds up to VD; (2) The negative manoeuvring load factor specified in [CS-VLA 337](#_DxCrossRefBm584936676) at VC; and (3) Factors varying linearly with speed from the specified value at VC to 0.0 at VD. (c) *Gust envelope* (1) The aeroplane is assumed to be subjected to symmetrical vertical gusts in level flight. The resulting limit load factors must correspond to the conditions determined as follows: (i) Positive (up) and negative (down) gusts of 15·24 m/s at VC must be considered. (ii) Positive and negative gusts of 7·62 m/s at VD must be considered. (2) The following assumptions must be made: (i) The shape of the gust is -  where - S = distance penetrated into gust (m); C̅ = mean geometric chord of wing (m); and Ude = derived gust velocity referred to in sub-paragraph (c)(1) (m/s) (ii) Gust load factors vary linearly with speed between VC and VD. (d) *Flight envelope*  Point G need not be investigated when the supplementary condition specified in [CS-VLA 369](#_DxCrossRefBm584936675) is investigated.