Abstract: 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.

Abstract: 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.

Abstract: A thrust reverser of a nacelle may include a translating sleeve and an inner fixed structure a pressure relief assembly. A pressure relief mechanism may include a pressure relief door coupled via a hinge and a latch to the inner fixed structure. Alternatively, a pressure relief door may be coupled to a frame via a hinge and a latch to the inner fixed structure. The pressure relief assembly may limit deflections between the thrust reverser and the pylon in response to a burst duct. The pressure relief door may release from the latch automatically in response to an over pressurization event.

Abstract: A diaphragm latch may comprise a housing, a diaphragm disposed in the housing, a pin coupled to the diaphragm, an opening in the housing, and a pin aperture disposed in the first side, wherein the pin extends from the pin aperture. The diaphragm may be configured to move in response to a pressure being communicated through the opening, and the pin may be configured to at least one of extend or retract from the pin aperture in response to the diaphragm moving. The diaphragm latch may passively couple an inner fixed structure (IFS) to an intermediate case (IMC) during an overpressure event.

Abstract: 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.

Abstract: A magnetic fire seal for a nacelle may comprise an exterior surface configured to form a sealing interface and an interior surface opposite the exterior surface. A fire-resistant material may be disposed between the exterior surface and the interior surface. A magnet may be located at the interior surface proximate the sealing interface. A portion of the fire-resistant material may be located between the magnet and the exterior surface.

Abstract: 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.

Abstract: 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.

Abstract: A thrust reverser of a nacelle may include a translating sleeve and an inner fixed structure a pressure relief assembly. A pressure relief mechanism may include a pressure relief door coupled via a hinge and a latch to the inner fixed structure. Alternatively, a pressure relief door may be coupled to a frame via a hinge and a latch to the inner fixed structure. The pressure relief assembly may limit deflections between the thrust reverser and the pylon in response to a burst duct. The pressure relief door may release from the latch automatically in response to an over pressurization event.

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes a cowl and a latch assembly. The cowl is configured to move between an open position and a closed position. The latch assembly includes a latch and a housing. The latch is pivotally mounted to the housing. The housing is connected to the cowl. The latch assembly is configured such that the latch is removable from the housing while the housing is connected to the cowl and the cowl is in the closed position.

Abstract: A thrust reverser of a nacelle may include a translating sleeve and an inner fixed structure a pressure relief assembly. A pressure relief mechanism may include a pressure relief door coupled via a hinge and a latch to the inner fixed structure. Alternatively, a pressure relief door may be coupled to a frame via a hinge and a latch to the inner fixed structure. The pressure relief assembly may limit deflections between the thrust reverser and the pylon in response to a burst duct. The pressure relief door may release from the latch automatically in response to an over pressurization event.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: Latch housing assemblies, latch hook assemblies, and latch assemblies are disclosed. Various disclosed latch housing assemblies include a latch pin coupled to an inner housing, and an outer housing having an inner surface coupled to an outer surface of the inner housing via at least one of a fuse pin and a spring. Various disclosed latch hook assemblies include a latch hook coupled to a latch housing, a weak point in the latch housing disposed between an inboard mount and an outboard mount, and a catch member mounted to the inboard mount and the outboard mount. Various disclosed latch assemblies include a latch housing, a bolt, and a deformable bushing at least partially surrounding the bolt, the deformable bushing configured to deform about a radius in response to a compressive load of about 1,000 lbf to about 3,000 lbf.

Abstract: A catch assembly is provided that includes a keeper, a guide and a catch. The catch includes a catch mount, a catch arm and a catch hook. The catch arm is cantilevered from the catch mount. The catch arm extends longitudinally away from the catch mount to a distal end of the catch. The catch hook is connected to the catch arm at the distal end. The catch is configured to bias the catch hook against the guide. The catch hook is configured to slide longitudinally along the guide from a first position to a second position where the catch hook engages the keeper.