Stress panel repair insert for aircraft

Details Stress panel repair insert for aircraft Stress panel repair insert for aircraft

1980-12-05

1983-08-23

Frankfort, Charles E.

Aeronautics and astronautics

Aircraft structure

Details

49463, 244 1R, 244117R, 244119, 244121, B64C 114

Patent

active

043999654

ABSTRACT:
A thick panel is provided constructed of resilient deformable material and of a plan, size and shape to be snugly received in an airframe opening formed by the removal of an airframe stress panel. The resilient panel is positionable within the airframe opening in a manner fully closing the latter against the entrance of foreign material into the interior of the airframe from the exterior thereof. The thick panel includes an outer surface provided with a peripheral rabbet formed therein whereby the outer margin of the thick panel may be received beneath the airframe outer skin portions disposed about and defining the opening in which the thick panel is received. Further, the outer surface of the thick panel includes a flexible coating of substantially fluid impervious material.

REFERENCES:
patent: Re28756 (1976-04-01), Fork
patent: 2392835 (1946-01-01), Conlon
patent: 2744382 (1956-05-01), Sokol et al.
patent: 2959671 (1960-11-01), Stevinson
patent: 3305196 (1967-02-01), Hanlon
patent: 3692084 (1972-09-01), Irvine
patent: 4290568 (1981-09-01), Vollmoeller

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