Crack Distribution and Growth Rates for Critical Fastener Holes in Mirage Wing RH79.

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.

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Document Details

Document Type
Technical Report
Publication Date
Sep 18, 1987
Accession Number
ADA189080

Entities

People

  • S. Bowles

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Acoustic Emissions
  • Air Force
  • Aircrafts
  • Aluminum Oxides
  • Chemistry
  • Department Of Defense
  • Engineering
  • Failure Analysis
  • Fasteners
  • Fatigue Tests (Mechanics)
  • Fractography
  • Fretting
  • Inspection
  • Materials
  • Materials Science
  • Security
  • X Rays

Readers

  • Aerodynamics/Aeronautics.
  • Electrical Engineering
  • Materials Science (Mechanical Engineering).