CS 23.2215 Flight load conditions

• ED Decision 2017/013/R found in: CS-23 Amdt 5 AMC-GM Issue 3 - Normal-Category Aeroplanes (Jul 2020)

CS 23.2215 Flight load conditions ED Decision 2017/013/R (a) Critical flight loads are established for symmetrical and asymmetrical loading from all combinations of airspeeds and load factors at and within the boundaries of the manoeuvre and gust envelope: (1) at each altitude within the operating limitations, where the effects of compressibility are taken into account when significant; (2) at each mass from the design minimum mass to the design maximum mass; and (3) at any practical but conservative distribution of disposable load within the operating limitations for each altitude and weight. (b) Vibration and buffeting does not result in structural damage up to dive speed. (c) Flight loads resulting from a likely failure of an aeroplane system, component, or engine are determined. CS 23.2215 Flight load conditions ED Decision 2017/013/R (a)     Critical flight loads are established for symmetrical and asymmetrical loading from all combinations of airspeeds and load factors at and within the boundaries of the manoeuvre and gust envelope: (1)     at each altitude within the operating limitations, where the effects of compressibility are taken into account when significant; (2)     at each mass from the design minimum mass to the design maximum mass; and (3)     at any practical but conservative distribution of disposable load within the operating limitations for each altitude and weight. (b)     Vibration and buffeting does not result in structural damage up to dive speed. (c)      Flight loads resulting from a likely failure of an aeroplane system, component, or engine are determined. #### CS 23.2215 Flight load conditions *ED Decision 2017/013/R* (a) Critical flight loads are established for symmetrical and asymmetrical loading from all combinations of airspeeds and load factors at and within the boundaries of the manoeuvre and gust envelope: (1) at each altitude within the operating limitations, where the effects of compressibility are taken into account when significant; (2) at each mass from the design minimum mass to the design maximum mass; and (3) at any practical but conservative distribution of disposable load within the operating limitations for each altitude and weight. (b) Vibration and buffeting does not result in structural damage up to dive speed. (c) Flight loads resulting from a likely failure of an aeroplane system, component, or engine are determined.