THE CORROSION PROTECTION AFFORDED BY VARIOUS COATING SYSTEMS IN AIRCRAFT FASTENER AREAS
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 16, 1966
- Accession Number
- AD0640436
Entities
People
- Jack Ohr
Organizations
- Naval Air Engineering Station Lakehurst