CS 23.2200 Structural design envelope

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

CS 23.2200 Structural design envelope ED Decision 2017/013/R The applicant must determine the structural design envelope, which describes the range and limits of aeroplane design and operational parameters for which the applicant will show compliance with the requirements of this Subpart. The applicant must account for all aeroplane design and operational parameters that affect structural loads, strength, durability, and aeroelasticity, including: (a) structural design airspeeds to be considered when determining the corresponding manoeuvring and gust loads must: (1) be sufficiently greater than the stalling speed of the aeroplane to safeguard against loss of control in turbulent air; and (2) provide sufficient margin for the establishment of practical operational limiting airspeeds. (b) flight load conditions to be expected in service; (c) mass variations and distributions over the applicable mass and centre of gravity envelope, within the operating limitations; (d) loads in response to all designed control inputs; and (e) redistribution of loads if deflections under load would significantly change the distribution of external or internal loads. CS 23.2200 Structural design envelope ED Decision 2017/013/R The applicant must determine the structural design envelope, which describes the range and limits of aeroplane design and operational parameters for which the applicant will show compliance with the requirements of this Subpart. The applicant must account for all aeroplane design and operational parameters that affect structural loads, strength, durability, and aeroelasticity, including: (a)     structural design airspeeds to be considered when determining the corresponding manoeuvring and gust loads must: (1)     be sufficiently greater than the stalling speed of the aeroplane to safeguard against loss of control in turbulent air; and (2)     provide sufficient margin for the establishment of practical operational limiting airspeeds. (b)     flight load conditions to be expected in service; (c)      mass variations and distributions over the applicable mass and centre of gravity envelope, within the operating limitations; (d)     loads in response to all designed control inputs; and (e)     redistribution of loads if deflections under load would significantly change the distribution of external or internal loads. #### CS 23.2200 Structural design envelope *ED Decision 2017/013/R* The applicant must determine the structural design envelope, which describes the range and limits of aeroplane design and operational parameters for which the applicant will show compliance with the requirements of this Subpart. The applicant must account for all aeroplane design and operational parameters that affect structural loads, strength, durability, and aeroelasticity, including: (a) structural design airspeeds to be considered when determining the corresponding manoeuvring and gust loads must: (1) be sufficiently greater than the stalling speed of the aeroplane to safeguard against loss of control in turbulent air; and (2) provide sufficient margin for the establishment of practical operational limiting airspeeds. (b) flight load conditions to be expected in service; (c) mass variations and distributions over the applicable mass and centre of gravity envelope, within the operating limitations; (d) loads in response to all designed control inputs; and (e) redistribution of loads if deflections under load would significantly change the distribution of external or internal loads.