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Filiform Corrosion Associated with Commonly Applied Aircraft Metal Pretreatments and Finishes
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1973 by SAE International in United States
Annotation ability available
The filiform corrosion problems encountered on aircraft structures in geographical areas experiencing constant warm temperature and elevated relative humidity indicate that finishing systems evaluations consisting of standard salt spray exposure do not adequately relate the efficiency of a system in inhibiting corrosion. An alternate method of testing is proposed: simulating the actual service environment with production of filiform corrosion on aluminum and steel alloys which have been pretreated and finished with commonly applied aircraft finishes. A comparison between salt spray exposure and this simulated service environment with coating and pretreatment evaluations is described.
|Aerospace Material Specification||Primer Zinc Molybdate|
|Aerospace Material Specification||Fibers, Carbon, Tow and Yarn For Structural Composites|
|Aerospace Standard||Molded Rigid Plastic Parts|
CitationGann, M., "Filiform Corrosion Associated with Commonly Applied Aircraft Metal Pretreatments and Finishes," SAE Technical Paper 730311, 1973, https://doi.org/10.4271/730311.
- Hoch G. M. Tobias R. F. “Mechanisms of Filiform Corrosion.” Lockheed California Co. Burbank
- “Interim Report on Aluminum Filiform Corrosion Project.” Oregon State University Corvallis August 1970