Definition

Under both EASA Certification Aircraft Structure Specifications (CS) 23 (Small Aeroplanes) and 25 (Large Aeroplanes) and the equivalent FAA specifications under 14 CFR Section 23/25, the Limit Load is the maximum load to be expected in service (Loads - CS 25.301 and Section 25.301). Any part of the structure of an aircraft must be able to support the limit load without permanent deformation.

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