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: 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: 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 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 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: An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure, a blocker door and a folding linkage. The translating structure is configured to move between a stowed position and a deployed position. The blocker door is pivotally attached to the translating structure at a first pivot joint. The folding linkage links the blocker door to the fixed structure. The folding linkage includes a member pivotally attached to the blocker door at a second pivot joint that is radially outboard of a skin of the blocker door when the translating structure is in the stowed position. The second pivot joint is radially outboard of the first pivot joint when the translating structure is in the stowed position.

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 thrust reverser may comprise a frame, a first reverser door being movable relative to the frame, and a second reverser door being movable relative to the frame and rotationally movable relative to the first reverser door via a first pivot point, the first pivot point being movable relative to the frame via a first link rotationally mounted to the frame via a second pivot point.

Abstract: A latch arrangement for a door includes a plurality of steps disposed at an interior of the door. One of the plurality of steps is rotatable relative to the door between a first position and a second position. The door is movable between a closed position and an open position. A latch is in operable communication with the rotatable step. The latch is engageable with a latch receiver to lock the door in the closed position in response to the rotatable step being in the first position. The latch is disengageable from the latch receiver when the step is in the second position thereby allowing the door to move to the open position.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure, a blocker door and a folding linkage. The translating structure is configured to move between a stowed position and a deployed position. The blocker door is pivotally attached to the translating structure at a first pivot joint. The folding linkage links the blocker door to the fixed structure. The folding linkage includes a member pivotally attached to the blocker door at a second pivot joint that is radially outboard of a skin of the blocker door when the translating structure is in the stowed position. The second pivot joint is radially outboard of the first pivot joint when the translating structure is in the stowed position.

Abstract: A kinematic system is provided that includes an outer cylinder, a mid-cylinder and an inner cylinder. The mid-cylinder is within the outer cylinder, and mated with the outer cylinder at a mid-outer threaded interface configured to transform axial translation of the outer cylinder into rotational motion of the mid cylinder along an axis. The inner cylinder is within the mid-cylinder, and mated with the mid-cylinder at a mid-inner threaded interface configured to transform the rotational movement of the mid-cylinder into axial translation of the inner cylinder along the axis. A first one of the mid-outer threaded interface and the mid-inner threaded interface includes a thread configured with a first thread portion and a second thread portion. The first thread portion is disposed at a first angle relative to the axis. The second thread portion is disposed at a second angle relative to the axis that is different from the first angle.

Abstract: A thrust reverser for a gas turbine engine may comprise a frame, a first reverser door pivotally mounted to the frame at a first pivot point, a second reverser door pivotally mounted to the frame at a second pivot point, a first nacelle defining a first trailing edge of the gas turbine engine coupled between the frame and the first reverser door, and a second nacelle defining a second trailing edge of the gas turbine engine coupled between the frame and the second reverser door. The first nacelle and the second nacelle translate in an aft and radial outward direction relative to the gas turbine engine in response to the thrust reverser moving to a deployed position.

Abstract: An assembly is provided for an aircraft propulsion system with an axial centerline. The assembly includes a translating sleeve, a sleeve actuator and a locking apparatus. The sleeve actuator is connected to the translating sleeve. The sleeve actuator is configured to move the translating sleeve along the axial centerline between a stowed position and a deployed position. The locking apparatus includes a lock and a lock actuator. The lock comprises a locking element. The lock actuator is configured to move the locking element between a locked position and an unlocked position. The locking element is configured to lock the translating sleeve in the stowed position when the locking element is in the locked position. A first portion of the locking apparatus axially overlaps the sleeve actuator along the axial centerline. A second portion of the locking apparatus does not axially overlap the sleeve actuator along the axial centerline.

Abstract: An assembly is provided for an aircraft propulsion system with an axial centerline. This assembly includes a nacelle structure and a thrust reverser system. The nacelle structure includes a fan cowl, where a forward cavity extends axially into the nacelle structure from an aft end of the fan cowl. The thrust reverser system includes a sleeve, a cascade structure, a blocker door and a linkage. The sleeve is configured to translate axially along the centerline and relative to the nacelle structure between a forward stowed position and an aft deployed position. The cascade structure, the blocker door and the linkage are at least partially within the forward cavity when the sleeve is in the forward stowed position. The cascade structure is fixedly attached to the sleeve. The linkage extends between and is pivotally attached to the cascade structure and the blocker door.

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: 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: 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 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.