Method and arrangement for fastening composite aircraft skins
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United States of America Patent
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Dec 8, 1998
Grant Date -
N/A
app pub date -
Jun 2, 1995
filing date -
Jun 2, 1994
priority date (Note) -
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status (Latency Note)
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Abstract
The present invention provides a method of fastening an outer composite aircraft skin (12) to an inner substructure (14), which may be the wall of a fuel tank. The method includes the steps of incorporating an electrically conductive layer (26) in an outer surface of the outer composite skin (12), inserting a bolt (11) through the electrically conductive layer (26) and the outer composite skin (12) and through the inner substructure (14), securing the bolt (11) by means of a nut (22) directly or indirectly engaging the inner surface of the inner substructure (14), and applying insulating material (34) over the head (16) of the bolt.
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