Abstract: A translating sleeve assembly for use with an aircraft engine thrust reverser broadly comprises a slider track, a lifting bolt, and a hinge. The slider track may include a tubular sidewall and a guide channel formed therein that follows a curved path along a length thereof. The lifting bolt may be slidably positioned within the slider track. The hinge may include a first hinge element with a base coupled to an outer cowl shroud, a second hinge element with a hinge rod slidably positioned within the guide channel, and a pin about which the first hinge element and the second hinge element pivot. During deployment of the thrust reverser, the lifting bolt slides aftward and the hinge rod slides within the guide channel, urging the lifting bolt to pivot and the hinge to open, thereby lifting the outer cowl shroud away from the center of the aircraft engine.

Abstract: A translating sleeve assembly for use with an aircraft engine thrust reverser broadly comprises a slider track, a lifting bolt, and a hinge. The slider track may include a tubular sidewall and a guide channel formed therein that follows a curved path along a length thereof. The lifting bolt may be slidably positioned within the slider track. The hinge may include a first hinge element with a base coupled to an outer cowl shroud, a second hinge element with a hinge rod slidably positioned within the guide channel, and a pin about which the first hinge element and the second hinge element pivot. During deployment of the thrust reverser, the lifting bolt slides aftward and the hinge rod slides within the guide channel, urging the lifting bolt to pivot and the hinge to open, thereby lifting the outer cowl shroud away from the center of the aircraft engine.

Abstract: A blocker door system to be used with an aircraft engine thrust reverser comprises a push ring, a plurality of connecting rods, a plurality of crankshafts, a plurality of blocker doors, and a plurality of linking elements. The push ring may encircle the aircraft engine. The connecting rods may connect along the circumference of the push ring. The crankshafts may rotatably couple to the connecting rods. The blocker doors may be positioned adjacent one another around the circumference of the aircraft engine wherein at least a portion of one blocker door covers at least a portion of the adjacent blocker door. The linking elements may connect one blocker door to the adjacent blocker door and may be operable to guide the motion of the blocker doors relative to one another.

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: A duct having a continuous C-shaped cross section slidably attached to a strut supporting an aircraft engine. The duct may comprise an inner wall, an outer wall, a first end wall, a second end wall, at least one slider, a thrust reverser, and an outer cowl panel of a thrust reverser. The inner wall may comprise a forward section and an aft section. The aft section may be integral with the first end wall, the second end wall, the outer wall, and the at least one slider. The forward section may comprise a right half and a left half which may be pivotally attached to the strut and may pivot to an open position when the rest of the fan duct is slid aftward away from the engine. The duct, excluding the forward section of the inner wall, may slide aftward on its at least one slider, providing engine access.

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.