The Boeing Company

Other

Richard Kevin Johnson

Douglas Dean Maben

Daniel F Lewinski

Michael L Trent

Julie K Plessner

George A McEachen

Mark E Smith

Kevin Scott Callahan

Daniel J Murray

Justin D Cottet

Kelly Thomas Jones

Mitchell Loren Ray Mellor

James E Cusworth

Mark Nicholas Simpson

George Sonnenburg

Royal E Boggs

Alan D Amort

Harry H Ayubi

Mohammad M Malik

Frederic Lacaux

John Rubrecht Lowell

Bruce Lee Drolen

James C Russell

Mehdy Barekatein

Michael Leslie Gilbertson

Nels A Olson

Timothy R North

Howard E McKenzie

Gregory Dale Perrigo

Thomas P Barrera

Kevin E Clark

Jon P Michel

Mike R Madden

David C Shangraw

Jean-Philippe Belieres

Richard P Lorenz

Matthew J O'Brien

John W Algeo

Alfred R Carlo

Craig G Robotham

Michael R Madden

Al R Carlo

Mitchell Loren Mellor

Justin Cottet

An aircraft landing gear structure includes a strut assembly and a wheel assembly operatively coupled to the strut assembly. The strut assembly includes an upper tubular housing and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing such that the overall length of the strut assembly is transitioned between an extended configuration and a retracted configuration for stowage during flight. The wheel assembly includes a forward link pivotally coupled to the upper tubular housing and a truck beam that is pivotally coupled to the lower tubular housing such that translation of the lower tubular housing with respect to the upper tubular housing causes pivoting of the forward link and the truck beam with respect to one another, thereby tilting and/or raising a wheel of the wheel assembly with respect to the upper tubular housing.

Aircraft landing gear having a lever assembly, aircraft including the same, and related methods

According to an embodiment, an aircraft comprises a fuselage including composite skin; an enclosure located inside the fuselage; a rechargeable battery disposed inside the enclosure; and a ventilation conduit extending from the enclosure to an opening in the composite skin, the ventilation conduit including: a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.

Ventilation conduit for an aircraft

Pass-through mounting assemblies include an outer sleeve, an inner sleeve, a bushing component, and a cap that are configured to be assembled onto a partition aperture in a partition to retain a tube as the tube passes through the partition. The outer sleeve is sized to fit into the partition aperture. The inner sleeve is sized to nest into the outer sleeve and includes a non-concentric inner rim. The bushing component defines a tube aperture configured to retain the tube and includes an outer rim sized to nest into the inner rim of the inner sleeve. The tube aperture is non-concentric with the outer rim of the bushing component. The cap includes an inner rim sized to nest over the outer rim of the inner sleeve. The tube aperture position may be adjusted by changing the relative angular position of the bushing component, the inner sleeve, and the cap.

Electromagnetic effects-sensitive pass-through mounting assemblies with adjustable offset

An aircraft comprises composite skin having an opening, and a ventilation conduit having an end portion that extends to the opening in the composite skin. The conduit is made of metal except for the end portion, which functions as an electrical insulator.

An aircraft comprises a rechargeable battery including an array of battery cells, and means for mitigating consequences of failure of the rechargeable battery due to aircraft operating cycles.

Aircraft including mitigation system for rechargeable batteries

An apparatus comprises a rechargeable battery susceptible to thermal runaway, and a metal enclosure for the battery. The enclosure is configured to mitigate battery failure consequences resulting from thermal runaway.

Enclosure for rechargeable batteries

Apparatus and methods provide an electrically isolating clamp that is suitable for use, among other locations, within a composite wing structure and other fuel environments. According to embodiments described herein, the clamp includes a clamp body and cushion. The clamp body is manufactured from a non-conductive material and includes a strap and a base. The cushion may be manufactured from a different non-conductive material to provide at least two layers of electrical isolation between the tube or other object being secured and a structure. The cushion material allows for axial movement of the tube through the cushion. The cushion is disposed between the strap and the base. Shoulder flanges prevent axial movement of the cushion with respect to the clamp body. The clamp may have a cushion retention mechanism to secure the cushion within the strap prior to installation around the tube.

Clamp for securing an object to a structure

Apparatus for injecting flowable material in which a container holds flowable material. Disposed within the container is a plunger which is formed with metering apertures extending therethrough. The metering apertures store predetermined quantities of material to be mixed with the material in the container. A flexible member is disposed adjacent the plunger between the discharge opening of the container and the plunger. When the plunger travels away from the discharge opening, the flexible member unseals the metering apertures for mixing the material in the plunger with the material in the container. When the plunger travels toward the discharge opening, the flexible member seals the metering apertures in the plunger to discharge the mixed material in the container through the discharge opening.

Apparatus for producing sterility in female animals

Growing community of inventors

Camano Island, WA, United States of America

Richard Kevin Johnson