The failure of an F-111 wing during a full-scale fatigue test had important implications for the structural integrity management of the RAAF F-111 fleet. This failure was due to a fatigue crack which initiated in the bore of a fastener hole. To assure structural integrity, an automated ultrasonic inspection has been developed which will be applied to up to 1200 fastener holes in each wing. The holes are inspected from the lower surface and definitive assessments of wing serviceability must be made without removing fasteners. The inspection system uses focussed immersion probes to perform a 45-degree angle-beam shear wave inspection, utilising full-waveform capture and post-processing. This style of complex, computer-based inspection system is new to the Australian Defence Organisation and challenged many existing engineering processes for performing NDT and interpreting the results. This paper reviews the application of automated ultrasonic inspection for the F-111 lower wing skin and outlines some of the significant challenges for both the science behind the inspection and the associated engineering processes. The lessons learnt will aid the successful integration of new technologies into existing NDT practices in the future.
Automated ultrasonic inspection for crack detection AT F-111 lower wing skin fastener holes
Automatische Ultraschallprüfung zum Rissnachweis an AT F-111 Unterflügel-Außenschicht Befestigungslöchern
2006
8 Seiten, 14 Bilder, 5 Quellen
Aufsatz (Konferenz)
Englisch
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