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Summary

Summary

While climbing through FL 210 on route from Broom to Perth, the aircraft's No 1 engine experienced a sudden failure. The crew shut the engine down and diverted the aircraft to Newman where it landed safely. The engine examination revealed extensive secondary damage to the High Pressure Turbine (HPT) section caused by failure in the HPT Stage 2 area. All Stage 2 blades had failed. The blade fracture surfaces contained small area of fatigue at the trailing edges. The fatigue area was not large enough the cause failure of the blades. It is suspected that the Stage 2 nozzle honeycomb abraidable material partially separated from the nozzle, initiating a one per revolution vibration that resulted in fatigue propagating through majority of the Stage 2 blades. The engine failure was probably caused by a section of the honeycomb separating and causing blades failure.
 
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