The Boeing Company

Patrick James Macko

Santiago M Mejia

Byron James Autry

Sara Murphy

Paul Gabriel Werntges

David Raines

Larry Scott Smotherman

James R Kendall

Matthew S Stauffer

Samuel James Knutson

Steven P Wanthal

Christopher A Greer

Brian Timothy Peters

Andrew David Clark

Daniel Joseph Goering

Jeremiah D Langston

Constantin C Lazar

Michael J Bailey

Thomas Chlaupek

Taurus Brackett, Ii

Jason Christopher Parsons

Jeffrey Scott Harasha

Rocco Tomasso

Nathan W Vance

A nacelle inlet for an engine. The nacelle inlet includes an inner flow surface, an outer flow surface, and a turbulator segment positioned along the inner flow surface. The turbulator segment extends outward beyond the inner flow surface and is configured to transition laminar airflow along the inner flow surface upstream from the turbulator segment to turbulent airflow downstream from the turbulator segment.

Engine nacelle inlet having a turbulator segment

A device to assemble a skin and a frame of an aircraft fuselage. The device includes first and second brace members that extend along opposing sides of a gap. Arches are spaced apart and fixedly connected to the first and second brace members and that extend across the gap. A strongback is attached to and movable along the first and second brace members with the strongback having a curved shape that matches the plurality of arches. The strongback includes clamps configured to engage with the frame. First and second tension devices apply tension to the skin at the strongback.

Method and apparatus for the application of frame to fuselage pull-up force via fuselage skin waterline tensioning

Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.

Circumferential lap splices for sections of fuselage

A method for making a pressure bulkhead assembly of an aircraft includes determining first locations and first orientations of a plurality of first holes, pre-drilled in an aft pressure bulkhead. The method also includes determining a first surface profile of a first interface surface of the aft pressure bulkhead and determining a second surface profile of a second interface surface of each one of a plurality of splice angles. The method also includes determining second locations and second orientations of a plurality of second holes to be drilled in each one of the plurality of splice angles corresponding to the plurality of first holes in the aft pressure bulkhead and drilling the plurality of second holes in each one of the plurality of splice angles at the second locations and second orientations.

Pressure bulkhead assembly methods and systems

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Charleston, SC, United States of America

Patrick James Macko