Rohr, Inc.

Sean Pretty

Jihad I Ramlaoui

Erik Linde

Martin C Bell

A dual axis hinge configured for pivotally securing a cowl to a fixed structure of an aircraft is disclosed. In various embodiments, the dual axis hinge includes a link having a first end and a second end; a first pin configured to pivotally secure the first end of the link to the fixed structure and a second pin configured to pivotally secure the second end of the link to the cowl; and a first hinge stop configured for connection to the cowl and a second hinge stop configured for connection to the link.

Dual axis hinge radial displacement limiter

An assembly is provided for an aircraft propulsion system. This assembly includes a first drain tube, a second drain tube, a container and a gas tube. The container fluidly couples the first drain tube to the second drain tube. The container is configured to receive fluid from the first drain tube. The gas tube is fluidly coupled with the container. The gas tube is configured to direct gas into the container for propelling the fluid received within the container into the second drain tube.

Fluid drain system for an aircraft propulsion system

An assembly is provided for an aircraft propulsion system. The assembly includes a fixed structure, an inner cowl door and an outer cowl door. The inner cowl door is pivotally connected to the fixed structure. The outer cowl door is pivotally connected to the fixed structure. The outer cowl door is radially outboard of and overlaps the inner cowl door. The linkage extends between and is movably connected to the inner cowl door and the outer cowl door.

Linkage(s) between inner and outer cowl doors

An assembly is provided for an aircraft propulsion system. This assembly includes an inner cowl door, an outer cowl door and a flexible linkage. The outer cowl door is radially outboard of and overlaps the inner cowl door. The flexible linkage is configured to connect to and thereby link the inner cowl door and the outer cowl door.

Linkage supporting a door of an aircraft propulsion system

An assembly is provided for an aircraft propulsion system. A first seal wedge is configured with a first wedge-shaped cross-sectional geometry when viewed in a reference plane. A first aperture extends along a first axis within the first seal wedge. A second seal wedge is configured with a second wedge-shaped cross-sectional geometry when viewed in the reference plane. A second aperture extends along a second axis within the second seal wedge. A first drain tube supports the first seal wedge and is fluidly coupled with the first aperture. A second drain tube supports the second seal wedge and is fluidly coupled with the second aperture. A manifold is configured with an outlet. The manifold supports the first drain tube and the second drain tube. The manifold fluidly couples the first drain tube and the second drain tube in parallel with the outlet.

Drain mast seal assembly with seal wedge(s)

A pin assembly is provided with an axial centerline. This pin assembly includes an outer pin, an inner pin, a first collar and a second collar. The outer pin extends axially along the axial centerline between an outer pin first end and an outer pin second end. The inner pin extends axially along the axial centerline within a bore of the outer pin. The first collar circumscribes the outer pin. The first collar is connected to the outer pin and the inner pin at the outer pin first end. The second collar circumscribes the outer pin. The second collar is connected to the outer pin and the inner pin at the outer pin second end.

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Jamul, CA, United States of America

Sean Pretty