NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Determination of the Corrosive Conditions Present within Aircraft Lap-Splice JointsThe complexity of airframe structure lends itself to damage resulting from crevice corrosion. Fuselage lap-splice joints are a particularly important structural detail in this regard because of the difficulty associated with detection and measurement of corrosion in these occluded regions. The objective of this work is to develop a laboratory corrosion test protocol to identify the chemistry to which lap joints are exposed and to develop a model of the corrosion within the joints. A protocol for collecting and identifying the chemistry of airframe crevice corrosion has been developed. Capillary electrophoresis (CE) is used to identify the ionic species contained in corrosion product samples removed from fuselage lap splice joints. CE analysis has been performed on over sixty corrosion product samples removed from both civilian and military aircraft. Over twenty different ions have been detected. Measurements of pH of wetted corroded surfaces indicated an alkaline occluded solution. After determining the species present and their relative concentrations, the resultant solution was reproduced in bulk and electrochemical tests were performed to determine the corrosion rate. Electrochemical analyses of the behavior of AA2024-T3 in these solutions gave corrosion rates of up to 250 microns per year (10 mpy). Additional tests have determined the relative importance of each of the detected ions in model solutions used for future predictive tests. The statistically significant ions have been used to create a second generation solution. Laboratory studies have also included exposure tests involving artificial lap joints exposed to various simulated bulk and crevice environments. The extent and morphology of the attack in artificial lap joints has been compared to studies of corroded samples from actual aircraft. Other effects, such as temperature and potential, as well as the impact of the environment on fatigue crack growth have also been studied.
Document ID
19990028764
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Lewis, Karen S.
(Virginia Univ. Charlottesville, VA United States)
Kelly, Robert G.
(Virginia Univ. Charlottesville, VA United States)
Piascik, Robert S.
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1999
Publication Information
Publication: The Second Joint NASA/FAA/DoD Conference on Aging Aircraft
Issue: Pt. 2
Subject Category
Metallic Materials
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available