THE CORROSION PROTECTION AFFORDED BY VARIOUS COATING SYSTEMS IN AIRCRAFT FASTENER AREAS
NAVAL AIR ENGINEERING CENTER LAKEHURST NJ AERONAUTICAL MATERIALS LAB
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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- 81352WEP 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.
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