The subject matter of this specification can be embodied in, among other things, an engine assembly includes a nacelle configured to at least partially surround an engine, and a thrust reverser coupled to the nacelle, the thrust reverser having a thrust-reversing element movable relative to the nacelle between a stowed position and a deployed position, a hydraulic actuator operably coupled to move the thrust-reversing element between the stowed position and the deployed position, and a fluid control system configured to operate the hydraulic actuator, the fluid control system having an electrohydraulic servo valve operable to selectively route fluid between a pressurized fluid source, the hydraulic actuator, and a fluid return reservoir, and a bypass fluid line providing fluid communication between the hydraulic actuator and the fluid return reservoir independent of the electrohydraulic servo valve.

A propulsion assembly for an aircraft includes a pylon, a turbofan including a structure fixed to the pylon, and at least one thrust reverser, each having a top beam extending parallel to a longitudinal direction and mobile in rotation on the structure around a rotation axis parallel to the longitudinal direction. For each thrust reverser, an actuator is provided, a first end of which is articulated on the pylon and a second end of which is articulated on the top beam of the thrust reverser and the articulation axis of the actuator on the top beam is not coaxial with the rotation axis. Such assembly allows a positioning of the actuator in the upper part of the turbofan between the top beam of the thrust reverser and the pylon to free some space.

A bypass turbofan engine comprising a nacelle surrounding a flow path for a secondary flow and comprising a fixed structure, a mobile assembly with a slide capable of translational movement on the fixed structure and bearing a mobile cowl and a frame capable of translational movement on the fixed structure and bearing deflectors. The mobile assembly is able to move between a forward position and a retreated position making it possible to open a passage between the flow path and the outside through the deflectors. A differentiation mechanism ensures a length of travel of the slide that is different from the length of travel of the frame, and actuators providing a translational travel of the slide. Fitting a differentiation mechanism means that the length of travel of the deflectors with respect to the length of travel of the mobile cowl can be regulated.

An active locking system of a movable element for a thrust reverser of an aircraft nacelle includes an active locking device of the movable element, movable between a locking position and an unlocking position, an actuator of the locking device controlled by a command for actuating the locking device, a blocking device for blocking the locking device in the unlocked position, movable between a blocking position and an unblocking position, and a device for displacing the blocking device. The actuation command controls the closure of the movable element, and the device for displacing the blocking device displaces the blocking device in the unblocking position when the movable element is at a predetermined position.

A thrust reverser for an aircraft propulsion assembly includes a movable structure provided with external covers connected to hinges through a pivot connection allowing the external covers to rotate between a closed position and a maintenance position. The hinges are connected to secondary rails rigidly attached to an engine pylon through a sliding connection allowing the external covers to move in translation between a direct thrust position and a reverse thrust position. The hinges and the secondary rails are independent of beams to which the parts of the movable structure other than the external covers are connected. A method for maintaining an aircraft propulsion unit is also disclosed. The method includes positioning of the external covers in maintenance position followed by a placement of the beams and of the parts of the movable structure other than the external covers.

Locking actuators for thrust reverser actuation systems, engines and aircraft including the same, and associated methods. A locking actuator includes an actuator housing, an extension element, and a lock assembly. The extension element is configured to translate along an actuator axis to transition between a retracted state and an extended state. The lock assembly transitions between a locked state and an unlocked state independent of transitioning the extension element between the retracted and extended states. In examples, a thrust reverser actuation system includes an actuator assembly with the locking actuator and a hydraulic control assembly. In examples, an engine includes a thrust generator, a nacelle, a transcowl, and the thrust reverser actuation system. In examples, a method of operating a thrust reverser actuation system includes transitioning a lock assembly from a locked state to an unlocked state and transitioning an extension element from a retracted state to an extended state.

A thrust reverser for an aircraft propulsion assembly, this reverser including a mobile annular external structure, a single actuator for controlling the position of this mobile external structure and a device for guiding the mobile external structure when changing its position. The actuator and the guiding device are housed in a fairing of a pylon of the propulsion assembly to a wing or fuselage of the aircraft.

An interspatial blocker for a thrust reverser system of a turbofan engine, and a thrust reverser system and a turbofan engine incorporating the same. The interspatial blocker includes a first and second flap that rotate from a stored position to a blocking position, and a leading-edge structure rotatably coupling the first flap to the second flap. The leading-edge structure is set up to be installed in a fan nacelle of a turbofan engine in a substantially radial orientation such that the first flap rotates in a first direction about a first axis extending in a substantially radial direction from the stored position to the blocking position, and such that the second flap rotates in a second direction about a second axis extending in the substantially radial direction from the stored position to the blocking position, with the first direction being opposite to the second direction.

A turbofan with a nacelle having a slider that is movable between an advanced position and a retracted position to open a window between a duct and the outside, blades, each one being able to move in rotation between a stowed position and a deployed position, and a maneuvering system that moves each blade, a transmission arrangement that rotates the blades one after the other, a drive system that converts the translational movement of the slider into a rotational movement of a first blade and that has a ball screw system, an epicyclic gear train, and an assembly of arms and levers.

A leadscrew assembly includes a screw shaft along which is formed a first helical groove and a primary nut along which is form a second helical groove. The first helical groove and the second helical groove cooperate to define a track. The assembly also includes a secondary nut along which is formed a third helical groove. The first helical groove and the third helical groove cooperate to define a track with a nominal running clearance. A preload X is provided wherein when a load applied to the screw exceeds the predetermined preload, the secondary nut engages with the track such that load of the screw above preload X is transferred through the secondary nut and thus protecting the primary nut.