Abstract: A nacelle mounted above a wing of an aircraft. A support structure on the nacelle above the pylon resists forces in different directions, and includes door supports allowing the door to be opened upwardly. A retaining structure on the pylon below the nacelle resists forces in different directions, and includes a fixed support track and multiple keepers. Each keeper includes a first end which slides within the channel, and a second end which engages a latch on the closed door. A pylon below the nacelle supports the nacelle and an engine in the nacelle above the wing, increases aerodynamic efficiency, and may include a side spar for supporting the engine from the side. A fire seal assembly includes a depressor surface and a fire seal, and the latter does not contact the former until the door is almost closed, so that compression is substantially direct and scrubbing is reduced.

Abstract: An aircraft engine attachment assembly having a wing section, an engine pylon, upper secondary attachment links, lateral load attachment links, and a number of fuse pins. The engine pylon is mounted to the front end of the wing section so that the engine pylon is not restricted by a minimum structural depth. The wing section, engine pylon, upper secondary attachment links, and lateral load links form primary and secondary attachment joints configured to form alternate load paths if one of the joints fails. The wing section and engine pylon include knuckle-off geometries for promoting mechanical fusing of the fuse pins during high energy dynamic events.

Abstract: An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

Abstract: An aircraft nacelle having a fixed structure fixed relative to an aircraft pylon, a translating thrust reverser sleeve translatable aftward, relative to the fixed structure, and a translating variable area fan nozzle (VAFN) panel translatable aftward, relative to the translating thrust reverser sleeve. The nacelle may also include a VAFN actuator mounted on the translating thrust reverser sleeve and a VAFN drive unit attached to the fixed structure. The VAFN drive unit may be coupled to drive the VAFN actuator via first and second coupling components when the translating thrust reverser sleeve is stowed. When the translating thrust reverser sleeve is deployed, the first and second coupling components may decouple, disconnecting the VAFN drive unit from the VAFN actuator.

Abstract: An assembly and method for attaching an engine pylon to an aircraft wing. The method may include attaching a first forward wing-mounted fitting to the pylon at a first side of the pylon between upper and lower spars of the pylon and attaching a second forward wing-mounted fitting to the pylon at a second side of the pylon between the upper and lower spars of the pylon. The second side of the pylon is located opposite of the first side of the pylon. Mechanical attachment devices may be inserted through holes on the sides of the pylon aligned with holes formed through the forward wing-mounted fittings. The mechanical attachment devices may be made of steel and the forward wing-mounted fittings may be made of composite or aluminum material.

Abstract: An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

Abstract: An aircraft pylon is disclosed, the pylon including a strut, a modular fluid containment structure and a modular firewall. The strut presents an open structure and connects an aircraft external element to the aircraft. The fluid containment structure is associated with a fluid transfer component, wherein the fluid containment structure contains escaped fluid from the fluid transfer component and channels the escaped fluid away from the aircraft. Both the fluid containment component and the firewall are modular and separable from the strut.

Abstract: An assembly and method for attaching an engine pylon to an aircraft wing. The method may include attaching a first forward wing-mounted fitting to the pylon at a first side of the pylon between upper and lower spars of the pylon and attaching a second forward wing-mounted fitting to the pylon at a second side of the pylon between the upper and lower spars of the pylon. The second side of the pylon is located opposite of the first side of the pylon. Mechanical attachment devices may be inserted through holes on the sides of the pylon aligned with holes formed through the forward wing-mounted fittings. The mechanical attachment devices may be made of steel and the forward wing-mounted fittings may be made of composite or aluminum material.

Abstract: An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

Abstract: A method and ground support equipment (GSE) for attaching an engine core to an engine fan module on an aircraft pylon. The GSE may comprise GSE supports and lifting components attached to the pylon, two suspension rails attached to the lifting components, two translating rails translatably attached to the two suspensions rails and fixedly attached to opposite sides of the engine core, and two alignment fittings fixed to the engine fan module. The method of using the GSE may comprise lifting the engine core vertically using the lifting components and anchoring the suspension rails to the alignment fittings. The translating rails and engine core may then be translated in an aft-to-forward direction such that portions of the translating rails engage portions of the alignment fittings to cooperatively guide the translating rails into a final forward position in which the engine core is aligned relative to the engine fan module.

Abstract: An aircraft nacelle comprising an outer cowl and an inner cowl located inward of the outer cowl with an air flow path formed therebetween. The inner cowl may comprise a forward portion and an aft portion slidable in a forward-to-aft direction via one or more actuators. When translated aftward, the aft portion may decrease the area of the nacelle's fan duct nozzle. The greatest radial distance between the inner cowl and a center axis of the nacelle may occur at or forward of a location in which the forward and aft portions overlap each other. The forward portion may be comprised of a different material than the aft portion.

Abstract: An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

Abstract: An aircraft nacelle having a fixed structure fixed relative to an aircraft pylon, a translating thrust reverser sleeve translatable aftward, relative to the fixed structure, and a translating variable area fan nozzle (VAFN) panel translatable aftward, relative to the translating thrust reverser sleeve. The nacelle may also include a VAFN actuator mounted on the translating thrust reverser sleeve and a VAFN drive unit attached to the fixed structure. The VAFN drive unit may be coupled to drive the VAFN actuator via first and second coupling components when the translating thrust reverser sleeve is stowed. When the translating thrust reverser sleeve is deployed, the first and second coupling components may decouple, disconnecting the VAFN drive unit from the VAFN actuator.

Abstract: A mounting apparatus for an aircraft engine that provides load path redundancy includes a forward mount that attaches the aircraft engine to a pylon at a forward position of the aircraft engine, an aft mount that attaches the aircraft engine to the pylon at an aft position of the aircraft engine and a thrust assembly connected to the forward mount, and the aft mount. The forward mount includes an aircraft engine attachment assembly and a fail-safe assembly. The aft mount includes an aircraft engine attachment assembly and a fail-safe assembly.

Abstract: A load-bearing structure, such as a pylon or strut, having a monolithic tubular-shaped first central structure composed of composite material and a plurality of metal fittings for supporting an engine on an airframe structure of an aircraft, such as a wing. Most of the fittings are integrated into the load-bearing structure through bonding. The metal fittings carry the high bearing loads that are transmitted into the pylon at the engine-pylon and wing-pylon interfaces. The load-bearing structure may also include a second central structure of a tubular shape composed of composite material and integrated with one end portion of the first central structure by bonding and/or mechanical fasteners.

Abstract: An aircraft pylon is disclosed, the pylon including a strut, a modular fluid containment structure and a modular firewall. The strut presents an open structure and connects an aircraft external element to the aircraft. The fluid containment structure is associated with a fluid transfer component, wherein the fluid containment structure contains escaped fluid from the fluid transfer component and channels the escaped fluid away from the aircraft. Both the fluid containment component and the firewall are modular and separable from the strut.

Abstract: A mounting apparatus for an aircraft engine that provides load path redundancy includes a forward mount that attaches the aircraft engine to a pylon at a forward position of the aircraft engine, an aft mount that attaches the aircraft engine to the pylon at an aft position of the aircraft engine and a thrust assembly connected to the forward mount, and the aft mount. The forward mount includes an aircraft engine attachment assembly and a fail-safe assembly. The aft mount includes an aircraft engine attachment assembly and a fail-safe assembly.

Abstract: An aircraft nacelle comprising an outer cowl and an inner cowl located inward of the outer cowl with an air flow path formed therebetween. The inner cowl may comprise a forward portion and an aft portion slidable in a forward-to-aft direction via one or more actuators. When translated aftward, the aft portion may decrease the area of the nacelle's fan duct nozzle. The greatest radial distance between the inner cowl and a center axis of the nacelle may occur at or forward of a location in which the forward and aft portions overlap each other. The forward portion may be comprised of a different material than the aft portion.

Abstract: A method and ground support equipment (GSE) for attaching an engine core to an engine fan module on an aircraft pylon. The GSE may comprise GSE supports and lifting components attached to the pylon, two suspension rails attached to the lifting components, two translating rails translatably attached to the two suspensions rails and fixedly attached to opposite sides of the engine core, and two alignment fittings fixed to the engine fan module. The method of using the GSE may comprise lifting the engine core vertically using the lifting components and anchoring the suspension rails to the alignment fittings. The translating rails and engine core may then be translated in an aft-to-forward direction such that portions of the translating rails engage portions of the alignment fittings to cooperatively guide the translating rails into a final forward position in which the engine core is aligned relative to the engine fan module.

Abstract: A load-bearing structure, such as a pylon or strut, comprising a monolithic tubular-shaped first central structure composed of composite material and a plurality of metal fittings for supporting an engine on an airframe structure of an aircraft, such as a wing. Most of the fittings are integrated into the load-bearing structure through bonding. The metal fittings carry the high bearing loads that are transmitted into the pylon at the engine-pylon and wing-pylon interfaces. The load-bearing structure may also comprise a second central structure of a tubular shape composed of composite material and integrated with one end portion of the first central structure by bonding and/or mechanical fastening means.