SUBPART C — STRUCTURES
Normal-Category Aeroplanes (CS-23) · CS-23 · CS 23.2200 – CS 23.2270
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CS 23.2200 Structural design envelope
The applicant must determine the structural design envelope, which describes the range and limits of aeroplane design and operational parameters for…
AMC1 23.2200 Structural design envelope
CS 23.2205 Interaction of systems and structures
For aeroplanes equipped with systems that affect structural performance, either directly or as a result of failure or malfunction, the applicant must…
AMC1 23.2205 Interaction of systems and structures
CS 23.2210 Structural design loads
The applicant must: determine structural design loads resulting from likely externally or internally applied pressure, force or moment which may occur in…
AMC1 23.2210 Structural-design loads
CS 23.2215 Flight load conditions
Critical flight loads are established for symmetrical and asymmetrical loading from all combinations of airspeeds and load factors at and within the…
AMC1 23.2215 Flight load conditions
CS 23.2220 Ground and water load conditions
The applicant must determine the structural design loads resulting from taxi, take-off, landing, and handling conditions on the applicable surface in…
AMC1 23.2220 Ground and water load conditions
CS 23.2225 Component loading conditions
The applicant must determine the loads acting upon all relevant structural components, in response to:
AMC1 23.2225 Component loading conditions
CS 23.2230 Limit and ultimate loads
Unless special or other factors of safety are necessary to meet the requirements of this Subpart, the applicant must determine:
AMC1 23.2230 Limit and ultimate loads
CS 23.2235 Structural strength
The structure must support: limit loads without: interference with the safe operation of the aeroplane;
AMC1 23.2235 Structural strength
CS 23.2240 Structural durability
The applicant must develop and implement inspections or other procedures to prevent structural failures due to foreseeable causes of strength…
AMC1 23.2240 Structural durability
CS 23.2245 Aeroelasticity
The aeroplane must be free from flutter, control reversal, and divergence:
CS 23.2250 Design and construction principles
Each part, article, and assembly must be designed for the expected operating conditions of the aeroplane.
AMC1 23.2250 Design and construction principles
CS 23.2255 Protection of structure
Each part of the aeroplane, including small parts such as fasteners, must be protected against deterioration or loss of strength due to any cause likely…
AMC1 23.2255 Protection of structure
CS 23.2260 Materials and processes
The applicant must determine the suitability and durability of materials used for parts, articles, and assemblies, the failure of which could prevent…
AMC1 23.2260 Materials and processes
CS 23.2265 Special factors of safety
The applicant must determine a special factor of safety for each critical design value for each part, article, or assembly for which that critical design…
AMC1 23.2265 Special factors of safety
CS 23.2270 Emergency conditions
The aeroplane, even when damaged in an emergency landing, must protect each occupant against injury that would preclude egress when:
AMC1 23.2270 Emergency conditions
Consolidated from the EASA Easy Access Rules (revision 13 May 2026, extracted 17 Aug 2026) for convenience. Not the official publication — verify against the Official Journal of the European Union and the EASA publications before operational use.
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