Failure Analysis of Engineering Structures: Methodology and Case Histories
Case 7: Failure of a Stabilizer Link Rod in an Aircraft
This chapter explains how investigators determined that a stabilizer link rod fractured due to overload, possibly by a combination of tension and bending forces that occurred during an accident. It includes images comparing the fractured rod with its undamaged counterpart recovered from the starboard side of the aircraft. A close-up view of the threads near the fracture surface provides evidence of bending, while the presence of dimples in an SEM fractograph supports the theory that the link rod failed as a result of overload.
Failure of a Stabilizer Link Rod 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 78–79, https://doi.org/10.31399/asm.tb.faesmch.t51270078
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