"The regulatory requirements for the safety of aircraft have drastically evolved and have become more stringent based on significant service and test experience. In order to ensure structural integrity, original equipment manufacturers (OEMs) are required to conduct fatigue and damage tolerance (F&DT) studies across design, manufacturing, and in-service stages. These studies entail extensive evaluation, analysis using approved methods, and rigorous reporting that require significant resources, time, and effort.
This paper demonstrates the process of performing F&DT analysis with regard to the calculation of fatigue life and determining the crack growth period for an aircraft component, in ensuring the structural safety of an aircraft. It also showcases our extensive capability in performing F&DT analysis studies for both metallic and composite airframe structural parts across pre- and post-manufacturing stages of aircraft life cycle.
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