Abstract
The purpose of the program is to evaluate the use of the acoustic emission (AE) technique to provide a definitive continuous monitor of fatigue crack growth in a critical aircraft structural member. The program started in September, 1977, with Phase I consisting of defining technical and procedural details and developing and fabricating an AE monitor system. A unique AE monitoring system was fabricated and laboratory tested. It utilizes a source isolation feature to distinguish AE signals originating from an identified area of interest. Two parameters of AE information are recorded on one solid state digital memory for later retrieval and analysis. Phase I was completed in April, 1978. Phase 2 was concerned with installing and testing the AE monitoring system in an aircraft. Installation was made in RAAF Macchi 326 aircraft A7-201 during a major maintenance overhaul. The system is monitoring AE from fatigue cracks in a fastener hole in the tension member of the wing structure center section continuously during flight. Installation was completed in August, 1978, with four test flights to evaluate system performance and make necessary adjustments. Follow-up support to the Australian Aeronautical Research Laboratory (ARL) on this program is continuing.
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