Failure Analysis of Engineering Structures: Methodology and Case Histories
Case 43: Cracking of Filter Components in an Aircraft
Two filtration components installed on a developmental aircraft cracked during pressure impulse testing. Both parts were made from an aluminum alloy, solutionized and aged, and cracked due to fatigue. In both cases, the crack initiated at a transition region on an inner surface and progressed circumferentially outward. Based on these observations and the results of SEM fractography and microstructural analysis, the fatigue cracking can be traced to insufficient fillet radius at the transition zone.
Cracking of Filter Components in an Aircraft, Failure Analysis of Engineering Structures: Methodology and Case Histories, By V. Ramachandran, A.C. Raghuram, R.V. Krishnan, S.K. Bhaumik, ASM International, 2005, p 165–167, https://doi.org/10.31399/asm.tb.faesmch.t51270165
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