Nondestructive Inspection of Piper PA-25 Forward Spar Fuselage Attachment Fitting
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1995-09-01
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TRIS Online Accession Number:00857979
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NTL Classification:NTL-AVIATION-AVIATION;NTL-SAFETY AND SECURITY-Aviation Safety/Airworthiness;
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Abstract:The Federal Aviation Administration's (FAA's) Aging Aircraft NDI Validation
Center (AANC) at Sandia National Laboratoriess applied two nondestructive
inspection (NDI) techniques for the inspection of a Piper PA-25 forward spar
fuselage attachment fitting. A review of two PA-25 accidents revealed the
susceptibility of these fittings to corrosion and corrosion-induced-cracking.
It was believed that corrosion was a precursor to the cracking and hence this
effort focused primarily on developing techniques to detect the material
thinning. The nondestructive testing techniques attempted were based on
radiography and ultrasonics. Each of these techniques did reveal material
thinning in the attachment fitting samples from a PA-25 aircraft. Efforts to
detect cracks in the attachment fitting using NDI proved unreliable due to
geometry constraints and were therefore abandoned. Based on the results of
these experiments, an ultrasonic test procedure was subsequently developed for
identifying the material thinning and is appendixed to this report. This
procedure has since been incorporated by the FAA into a revision of
Airworthiness Directive 93-21-12. Document downloads as a Word file using
WINWORD.EXE.
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