Abstract: A method of assembling and installing an underwing package to an underside of an aircraft wing is disclosed. In various embodiments, the method includes assembling the underwing package, comprising at least a pylon and an engine, using a build frame; attaching a transfer cart to the underwing package; lowering the underwing package and the transfer cart from the build frame; transporting the underwing package and the transfer cart to the underside of the aircraft wing; and transferring the underwing package from the transfer cart to the underside of the aircraft wing.

Abstract: A system for a thrust reverser of an aircraft includes a primary sleeve and a secondary sleeve having cascades. The secondary sleeve is coupled to a set of blocker doors. The sliding motions of the primary sleeve and the secondary sleeve are not directly coupled when each moves between its stowed and deployed positions. The sliding motion of the primary sleeve may begin at a different time and continue at a different rate from the sliding motion of the secondary sleeve.

Abstract: A nacelle may comprise a fixed structure and a translating structure configured to translate relative to the fixed structure. A first drive system may be operationally coupled to the translating structure. The drive system may comprise a primary actuator coupled to the fixed structure and including a primary rod and a primary gear rotationally coupled to the primary rod, a torque shaft rotationally coupled to the primary gear, and a secondary actuator operationally coupled to the primary actuator via the torque shaft.

Abstract: An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a nacelle inlet structure. The nacelle inlet structure includes an inner inlet opening, an outer inlet opening and a rotating structure. The rotating structure extends circumferentially about the inner inlet opening. The rotating structure is configured to rotate about an axis between a first position and a second position. The rotating structure at least partially closes the outer inlet opening in the first position. The rotating structure at least partially opens the outer inlet opening in the second position.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a center body, a scarfed inlet structure and an inlet passage. The scarfed inlet structure extends circumferentially about the center body. The inlet passage is radially between and formed by at least the center body and the scarfed inlet structure. A first component of the assembly is configured to rotate about an axis relative to a second component of the assembly between: (A) a first position where a metering portion of the inlet passage has a first area; and (B) a second position where the metering portion has a second area. The first component is one of the center body or the scarfed inlet structure, and the second component is the other one of the center body or the scarfed inlet structure.

Abstract: A thrust reverser for a gas turbine engine includes a frame, a first reverser door pivotally mounted to the frame, and a second reverser door pivotally mounted to the first reverser door.

Abstract: A nacelle system having a translating structure is disclosed. In various embodiments, the system includes a fixed structure; a thrust reverser having a translating sleeve configured to translate relative to the fixed structure and in response to a first hydraulic system; and a variable area fan nozzle having a translating nozzle configured to translate relative to the translating sleeve and in response to a second hydraulic system. In various embodiments, the first hydraulic system and the second hydraulic system include a primary hydraulic actuator, the primary hydraulic actuator having a primary hydraulic fluid end and a primary gaseous fluid end; a secondary hydraulic actuator having a secondary hydraulic fluid end and a secondary gaseous fluid end; and a hydraulic supply line configured to fluidly couple the primary hydraulic fluid end of the primary hydraulic actuator to the secondary hydraulic fluid end of the secondary hydraulic actuator.

Abstract: A nacelle system having a translating structure is disclosed. In various embodiments, the nacelle system includes a fixed structure; a thrust reverser having a translating sleeve configured to translate relative to the fixed structure and in response to a first dual-circuit hydraulic system; and a variable area fan nozzle having a translating nozzle configured to translate relative to the translating sleeve and in response to a second dual-circuit hydraulic system.

Abstract: A system for mounting a gas turbine engine to a pylon and for detecting a failure within the system, the gas turbine engine comprising a first case, is disclosed. In various embodiments, the system includes a first mount connecting the first case to the pylon; and a first sensor configured to detect a first relative motion between the first case and the first mount.

Abstract: A thrust reverser may include a frame, a track disposed on the frame, a carrier operatively coupled to the track, and a first reverser door operatively coupled to the carrier. The first reverser door is movable relative to the frame, wherein the first reverser door is configured to move to a first position in response to the carrier moving with respect to the track in a first direction, and move to a second position in response to the carrier moving with respect to the track in a second direction.

Abstract: A thrust reverser may include a frame, a track disposed on the frame, a carrier operatively coupled to the track, a first reverser door operatively coupled to the carrier, the first reverser door is movable relative to the frame, wherein the first reverser door is configured to move to a first position in response to the carrier moving with respect to the track in a first direction, and move to a second position in response to the carrier moving with respect to the track in a second direction, and a deployable fairing pivotally coupled to the frame, the deployable fairing operatively coupled to the carrier, wherein the deployable fairing is configured to move away from a central axis of the thrust reverser to provide clearance for the reverser door to rotate into a deployed position.

Abstract: An assembly is provided that includes a barrel nut, a barrel nut retainer and a fastener. The barrel nut includes a threaded aperture. The barrel nut retainer includes a one-way installation guide. The fastener is configured to thread into the threaded aperture. The fastener is further configured to pass through the threaded aperture and project into the one-way installation guide when the fastener is inserted into the barrel nut retainer along a first direction.

Abstract: A thrust reverser may include a frame, an actuation arrangement, a reverser door pivotally coupled to the frame, and a deployable fairing pivotally coupled to the frame, wherein the deployable fairing is configured to move away from a central axis of the thrust reverser to provide clearance for one of more thrust reverser pivot doors to rotate into a deployed position.

Abstract: The present disclosure provides a thrust reverser comprising a stationary structure defining an annular body with a centerline, a first reverser door pivotally coupled to the stationary structure by a pair of first reverser door hinges, a first reverser door hinge axis extending through the first reverser door hinges and positioned at a first angle relative to a centerline, and a second reverser door pivotally coupled to the stationary structure by a pair of second reverser door hinges, a second hinge line axis extending through the second reverser door hinges and positioned at a second angle relative to the centerline.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a first actuator, a second actuator and a linkage system. The linkage system is configured to transfer torque between the first actuator and the second actuator. The linkage system includes a first linkage shaft, a second linkage shaft and a gearbox. The first linkage shaft has a first centerline. The second linkage shaft has a second centerline offset from the first centerline. The gearbox is coupled to and is between the first linkage shaft and the second linkage shaft.

Abstract: A system for deploying a blocker door of a nacelle includes a master link configured to be coupled to a fixed structure of the nacelle and a master crank pivotally attached to the master link. The system further includes a first door crank and a first door link pivotally coupled to the first door crank. The system further includes a first blocker door coupled to the first door link and a first driveshaft coupled to the master crank and to the first door crank and configured to transfer motion from the master crank to the first door crank such that aft translation of a translating sleeve of the nacelle drives the master crank via the master link, which drives the first door link via the first driveshaft and the first door crank to move the first blocker door into a bypass air duct defined by the nacelle.

Abstract: An assembly for an aircraft propulsion system is provided, the assembly having an axial centerline. The assembly comprises a fixed structure, a first thrust reverser door, and a second thrust reverser door. The first thrust reverser door being pivotally attached to the fixed structure along a first pivot axis, and the second thrust reverser door being pivotally attached to the fixed structure along a second pivot axis. The first pivot axis and the second pivot axis are both radially located at a first distance from the assembly axial centerline. The first pivot axis is located at a first axial position, and the second pivot axis is located at a second axial position. The second axial position is displaced from the first axial position.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure and a nacelle. The nacelle includes a first fan cowl and a first thrust reverser section adjacent the first fan cowl. The first fan cowl is movably attached to and arranged on a first side of the fixed structure. The first fan cowl is configured to move between a first fan cowl closed position and a first fan cowl second position. The first thrust reverser section is movably attached to and arranged on the first side of the fixed structure. The first thrust reverser section is configured to move between a first thrust reverser section closed position and a first thrust reverser section open position when the first fan cowl is in the first fan cowl closed position.

Abstract: A thrust reverser includes a frame having a longitudinal axis, a first reverser door pivotally mounted to the frame, a second reverser door pivotally mounted to the frame, a crank pivotally mounted to the frame, a first link connecting the crank to the first reverser door, and a second link connecting the crank to the second reverser door. In various embodiments, both the first reverser door and the second reverser door are driven by a single actuator.

Abstract: Aspects of the disclosure are directed to a thrust reverser system of an aircraft comprising: a translating cascade sleeve, a blocker door, and a kinematic mechanism configured to actuate the blocker door, the kinematic mechanism comprising: a first link coupled to the translating cascade sleeve, a second link coupled to the first link and a fixed structure, and a third link coupled to the first link and the blocker door.