A stress-cycling test (at - 103 F and room temperature) designed to simulate the spectrum of stresses which could occur during 500 aircraft flying hours (roughly 1 PAR interval), indicates that current specification and experimental aircraft coatings cannot meet these conditions without cracking around fastener heads. The coatings used were the MIL-C-22750 epoxy, the MIL-L-81352(WEP) all-acrylic, and two polyurethanes. The implication of this test is that, at the present state of the coatings art, paint films of the non-rubbery type cannot be expected to provide adequate corrosion protection by themselves in the fastener area- a persistent trouble area on naval aircraft. (Author)


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    Title :

    The Corrosion Protection Afforded by Various Coating Systems in Aircraft Fastener Areas


    Contributors:
    J. Ohr (author)

    Publication date :

    1966


    Size :

    2 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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