Accession Number : ADA189080
Title : Crack Distribution and Growth Rates for Critical Fastener Holes in Mirage Wing RH79.
Descriptive Note : Technical memo.,
Corporate Author : AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)
Personal Author(s) : Bowles, S
PDF Url : ADA189080
Report Date : 18 Sep 1987
Pagination or Media Count : 42
Abstract : Results of fractographic inspection of fatigue cracks found in the fastener holes (excepting hole 1 and SLAN rivet holes) in the inboard end of the lower flange of RH79 wing-spar, as a result of fatigue testing for 5600 hours, are presented. The largest crack found was only 2.18 mm deep and occurred in hole 10 in the rearward flange of the spar. Holes 1 to 4 remained crack-free as a result of the refurbishment procedures. Keywords: Fatigue crack growth, Mirage aircraft, Wing spars, Fastener holes, Fractography.
Descriptors : *CRACK PROPAGATION, *FASTENINGS, *FATIGUE(MECHANICS), *HOLES(OPENINGS), *FIGHTER AIRCRAFT, CRACKS, DISTRIBUTION, FATIGUE TESTS(MECHANICS), FLANGES, FRACTOGRAPHY, GROWTH(GENERAL), RATES, RIVETS, SPARS, WINGS, AUSTRALIA
Subject Categories : Attack and Fighter Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE