The Boeing Company

Brian Henry Korenaga

Richard Bruce Tanner

Jeffrey F Stulc

Robert Graham Albers

Thomas V Gendzwill

Richard Allen Miller, Ii

David W Evans

Ian C Burford

Gregory B Doty

America Olsen Schaaf

William M Sampedro-Thompson

James R Huck

Dean E Wilson

Mark Charles Iden

Kevin L Braun

Scott Telford O'Farrell

Mark S Novak

Ii Richard Allen Miller

Mark C Iden

Ian C Burtord

An apparatus automatically places, forms and compacts an adhesive strip on an edge of a structure in a single pass.

Method and apparatus for applying a strip of material over an edge on a structure

An access door structure for a wing skin is received in an access hole opening which incorporates a protective glove having a set of mistake resisting features and engaging the periphery of the access hole opening. An inner door seals an interior of the access hole opening and has multiple fastener attachment elements and a set of mating mistake resisting features. An outer door engaged over an exterior of the access hole opening has fastener holes for mating alignment with the fastener attachment elements and receives a plurality of fasteners for engagement of the inner and outer doors.

Mistake resistant design for wing fuel tank access door alignment features

A method of installing a door in an access opening in a skin of an aircraft. A composite inner door panel is positioned against an inside face of the skin. A composite outer door panel is positioned against an outside face of the skin. A plurality of fasteners is installed through fastener openings in the composite outer door panel. The plurality of fasteners is tightened to form a chamfered interface between the skin and the composite outer door panel.

Composite access door

A door for an aircraft wing fuel tank access opening includes an outer impact resistant composite door panel, and an inner composite door panel. Double seals on the inner door panel prevent fuel leakage, and a chamfered outer edge on the outer door panel transfers a component of impact loads laterally into the wing skin to increase kinetic energy absorption.

An innovative wing structure provides fibs to support skin panels without an attachment between the rib and the stringer free flange or the web. The support is provided by rib shear ties installed directly to the stringer skin flange. The rib incorporates a cut away to allow the stringer to pass through the rib. The composite stringer is an 'I' section and is stable under compression, not requiring mechanical methods to prevent rolling over.

Rib support for wing panels

A method and apparatus for an aircraft structure. In one advantageous embodiment, the aircraft structure may have a rib, a plurality of stringers, and a set of shear ties. The plurality of stringers may have skin flanges at ends of the plurality of stringers capable of being fastened to skin for the aircraft structure. The set of shear ties may extend from the rib and have a set of elongate members in which the set of elongate members are attached to the plurality of stringers.

Growing community of inventors

Shoreline, WA, United States of America

Brian Henry Korenaga