US 5,014,934 AGranted

Removable seal for discontinuities in aircraft skin

AssigneeThe Boeing Company

InventorJames K. McClaflin

Life of this patent

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Abstract

A first fastener component (26) is secured to an inner aircraft skin surface (6) by a mounting flange (12) and extends across a discontinuity (8) in the skin (2). A second fastener component (28) is secured to a rib (24) on the inner surface of a resilient blade (22) and extends through the discontinuity (8) into engagement with the first component (26). Inward pressure on the blade (22) urges the components (26, 28) into releasable locked engagement with each other. The components (26, 28) secure the blade (22) in a flattened use position in which it is substantially flush with and sealingly engages the outer skin surface (4). The blade (22) may be removed by inserting a tool under it and exerting a lifting force to disengage the components (26, 28). The blade (22) may be dimensioned to cover the outer ends of adjacent fasteners (14) extending through the skin (2). The blade (22) is preferably conductive to provide a continuous electrical path along the outer skin surface (4) across the discontinuity (8).

Claims12

Dependent claims

A removable seal for covering and sealing a discontinuity extending through an outer skin portion of an aircraft, said seal comprising:

a resilient sealing member having a use position in which it covers said discontinuity and overlaps the outer surface of said outer skin portion;
and
a fastener having a first component secured to an inner surface of said outer skin portion and extending at least partially across said discontinuity, and a second component secured to said sealing member and dimensioned to extend inwardly into said discontinuity and engage said first component;
said first and second components having portions that automatically releasably lock said components together, when inward pressure is exerted on said sealing member to urge said first component into engagement with said second component, to secure said sealing member in said use position and urge said sealing member into sealing engagement with said outer surface of said outer skin portion, and that are releasable when a lifting force is exerted on said sealing member to disengage said components from each other.

1 more element

Dependencies are inferred from the claim text.

Facts

Application: 07/374,529Filed 30 Jun 1989
Granted: 14 May 1991
Term ends: Not estimatedThe source records don’t support an estimate.

Classification8 codes

F16B 21/073
In which the socket has a resilient part: the socket having a resilient part on its inside
B64C 1/12
Frames; Stringers; Longerons ; Fuselage sections: construction or attachment of skin panels
B64C 1/14
Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like: windows; Doors; Hatch covers or access panels;…
F16B 21/078
In which the socket has a resilient part: the socket having a further molded-in or embedded component, e.g. a ring with snap-in teeth molded into it