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)
The Corrosion Protection Afforded by Various Coating Systems in Aircraft Fastener Areas
1966
2 pages
Report
No indication
English
Ceramics, Refractories, & Glass , Hydraulic & Pneumatic Equipment , Aircraft , Coatings , Corrosion inhibition , Mechanical fasteners , Naval aircraft , Performance(Engineering) , Plastic paints , Epoxy plastics , Acrylic resins , Tests , Isocyanate plastics , Fatigue(Mechanics) , Fracture(Mechanics)
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