Abstract
AbstractMaintaining aircraft airworthiness to ensure the fleet's safe operation and maintain its readiness is critically dependent on accurate modelling and reliable predictions of fatigue crack growth. In this process, a knowledge of the representative initial discontinuity sizes that cause fatigue crack nucleation and early growth in aircraft is essential. Here the effective pre‐crack size of aluminum alloy 2024, from samples of aircraft production material and tested under aircraft spectra, are considered.
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