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.
AMC1 23.2200 Structural design envelope
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
6.1 Structural Design Envelope:
F.3116/F3116M-18 Standard Specification for Design Loads and Conditions
Remarks
F3116 revised from -15 to -18
AMC2 23.2200 Structural design envelope
ED Decision 2017/025/R
CS-23 Amdt 4
23.321(b), (c) Flight Loads - General
23.333(a), (b), (d) Flight envelope
23.335 Design airspeeds
23.337 Limit manoeuvring load factors
23.341 Gust load factors
AMC3 23.2200 Structural design envelope
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.321 Flight Loads - General
VLA.333 Flight envelope
VLA.335 Design airspeeds
VLA.337 Limit manoeuvring load factors
VLA.341 Gust load factors
CS 23.2205 Interaction of systems and structures
ED Decision 2017/013/R
For aeroplanes equipped with systems that affect structural performance, either directly or as a result of failure or malfunction, the applicant must account for the influence and failure conditions of these systems when showing compliance with the requirements of this Subpart.
AMC1 23.2205 Interaction of systems and structures
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
TBD
Remarks
Consensus standard in development
Remarks
Provision not included in CS 23 Amdt 4
Remarks
Provision not included in CS VLA Amdt 1