<p>The Federal Aviation Administration (FAA) has been participating with the Society of Automotive Engineers (SAE) Aerospace Industry Steering Committee (AISC) to develop a methodology for calculating the Probability of Detection (POD) for SHM for damage detection on commercial aviation.&nbsp; Two POD methodologies were developed: one by Dr. William Meeker, Iowa State University and the other by Dr. Dennis Roach, Sandia National Laboratories.&nbsp; With Dr. Seth Kessler, Metis Design Corp, a test program of 24 samples of aluminum strips to be fatigued on MTS machines was developed.&nbsp; The samples were designed to meet the ASTM E647.&nbsp; Twelve samples had 2 SHM modalities on the front and back from Metis (PZT and carbon nanotubes),and the other twelve had SHM sensors from Structural Monitoring Systems (SMS) (comparative vacuum monitoring – CVM) and Acellent Technologies (PZT).&nbsp;&nbsp; The tests were performed at the FAA William J Hughes Technical Center in Atlantic City.&nbsp; The samples were cycled every 1500 cycles and then stopped for SHM data collection.&nbsp; Once the crack exceeded 0.125 inches and provided for a minimum of 15 inspections, a new sample was tested until all 12 samples were completed.&nbsp; The data was provided to each company to be set up in the format needed to run through the POD methodologies.&nbsp; Then the data was provided to Dr. Meeker and Dr. Roach for analysis.&nbsp; This paper will provide the results of those tests.&nbsp;</p>

Federal Aviation Administration's Probability of Detection Testing Results for Structural Health Monitoring

Paper Proceedings: https://asmedigitalcollection.asme.org/qnde/QNDE2021/volume/85529

ASME 2021 48th Annual Review of Progress in Quantitative Nondestructive Evaluation (QNDE2021)

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