VTOL.2200 Structural
design envelope
n/a
The applicant must determine the structural design envelope, which describes the range and limits of aircraft design and operational parameters for which the applicant will show compliance with the requirements of this Subpart. The applicant must account for all aircraft 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) if part of the lift is generated by a wing, be sufficiently greater than the stalling speed of the aircraft to safeguard against loss of control in turbulent air, if applicable; 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.
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