Fatigue Failure Analysis of the Rear Pressure Bulkhead of the Crashed Boeing 747 Jumbo Jet Plane

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  • ボーイング747型ジャンボジェット墜落事故機の後部圧力隔壁の疲労破壊解析
  • ボーイング 747ガタ ジャンボ ジェット ツイラク ジコキ ノ コウブ アツ

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Abstract

The fatigue crack growth emanating from fastener holes is believed to have caused the failure of the rear pressure bulkhead of the crashed Boeing 747 jumbo jet plane. To evaluate the initial flaw criticality at fastener holes, the fatigue crack growth tests were conducted for plate specimens with drilled holes which simulate fastener holes. The initial flaws of 1.27mm in size were induced in the holes as required by the damage tolerance design.<br>The results of fatigue crack growth characteristics and the through-holes fatigue lives were compared with analysis. Finally, the fatigue failure analysis of the bulkhead of the crashed plane was attempted.<br>The following are the results obtained.<br>(1) When the flawed hole is adjacent to the sound holes, the fatigue cracks from the flaws are arrested at the sound holes and crack reinitiation cycles are satisfactorily long.<br>(2) On the other hand, when two or three adjacent holes are flawed, the specimen shows a drastic reduction in life. This case is found to give the quantitative simulation for the fatigue failure of the bulkhead of the crashed plane.<br>(3) If the damage tolerance design or the in-service inspection based on this had been adopted, it is judged that the fatal failure would not have occured.

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