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During full body fatigue testing, an aircraft wing spar initiated a crack from a rivet hole and crack growth data was obtained unique to the test spectrum loading. Fatigue testing of the 7050-T73511 spar material was used to obtain crack growth rate data and variable amplitude fatigue crack growth tests were performed on specimens fabricated from the spar material. Calculated results were in excellent agreement with these experimental results. A layered analysis of the adhesively bonded spar showed that the stress intensity in the lower cap was approximately constant, independent of crack length. When the constant stress intensity is used in a variable amplitude fatigue crack growth analysis, there is good correlation between the predicted and observed crack growth rates.

Prepared under the auspices of the SAE Fatigue Design and Evaluation Committee. This book focuses on the fatigue and fracture analysis of an induction hardened shaft subjected to combined bending and torsion. It includes the complexities of varying material and hardness distribution through the thickness of the shaft along with internal residual stresses. Subjects covered include: Sample definition and experimental data Material and process information Realistic load histories Understanding of the state of stress Analytical techniques and tools