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Significant factors


  1. The wing landing gear trunnion did not conform to the design specifications. The component's wall thickness in the region of the failure was less than the allowable minimum and the internal bore had not been adequately shot peened.
  2. Several fatigue cracks developed in the inner bore at the bore transition region.
  3. The fatigue cracks were likely present during the last overhaul, but were not detected during the magnetic particle inspection.
  4. The fatigue cracks developed until the loads during the pushback operation exceeded the residual strength of the component, leading to failure of the trunnion.
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