Limit Load refers to the maximum load an aircraft structure is expected to experience during its service life. According to the EASA Certification Aircraft Structure Specifications (CS) for both Small (CS 23) and Large Aeroplanes (CS 25), as well as the FAA regulations under 14 CFR Section 23/25, this concept is crucial for safety. Each part of an aircraft’s structure must withstand the limit load without undergoing any permanent deformation. This means that when an aircraft is in operation, it should be able to handle these loads effectively, ensuring the integrity of its design.
