Pin latch assemblies and cam latch assemblies are disclosed. A pin latch assembly is provided comprising a pin housing at least partially enclosing a pin, an actuating device coupled to the pin, and a retaining feature comprising an aperture.

A thrust reverser is described that comprises a new type of locking means for locking an actuator in position so that maintenance can be performed on the machine. The locking means comprises a removable locking device for preventing movement of an actuator. The locking means may also function in one configuration as an end cap. An actuator is also described comprising a removable torque limiting device for limiting torque of the actuator.

The turbojet includes, linking two of its parts as a main nacelle portion and a rear nacelle portion, a device which moves them relative to one another, for example in order to open a reverse gas thrust slot. The device includes a sleeve and two rods which are coaxial connected together by two screw links and two locking devices which may be engaged independently, such that the deployment of one of the rods results in the opening of the slot and the movement of the other rod, controlled by the same device, only occurs under specific turbojet maintenance circumstances.

An architecture for controlling and/or monitoring at least one actuator of a mobile cowl of a thrust reverser equipping a nacelle, the actuator being driven by at least one engine, includes at least one engine sensor to provide its control according to instructions, the architecture including an electronic control system to process at least one piece of information generated by the engine sensor and to calculate, using at least this same piece of information, the position of the mobile cowl of the thrust reverser.

A thrust reverser is described that comprises a new type of locking means for locking an actuator in position so that maintenance can be performed on the machine. The locking means comprises a removable locking device for preventing movement of an actuator. The locking means may also function in one configuration as an end cap. An actuator is also described comprising a removable torque limiting device for limiting torque of the actuator.

A locking system includes a locking element which is movable between a first, locking position and a second unlocking position and an unlocking actuator for moving the locking element (from the first position to the second position over an unlocking stroke length (Su). The system further comprises a control unit configured to command the unlocking actuator to move the locking element from the first position to a third position over an anti-icing stroke length (Sa) which is shorter than the unlocking stroke length (Su).

A cascade box is provided that includes a plurality of lengthwise extending side turning vanes and a plurality of forward turning vanes. Each of the plurality of lengthwise extending side turning vanes is configured to have a side turning angle. Each of the plurality of forward turning vanes is attached to respective adjacent ones of the plurality of side turning vanes, and each forward turning vane is configured to have a forward turning angle, and at least one of the forward turning vanes is configured to have a negative forward turning angle.

A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.

Locking linear actuators, thrust reversers for aircraft that include the locking linear actuators, and methods of manufacturing the locking linear actuators. The disclosed locking linear actuators include an actuator housing that defines a bore housing an actuator piston and a lock sleeve. A portion of the actuator piston defines a lock aperture, housing a locking tab capable of radial movement. When the actuator is retracted, the locking tab engages with a step in the surface of the bore to lock the linear actuator, a distal portion of the lock sleeve extends into a portion of the actuator piston to prevent the locking tab from disengaging from the step in the surface of the bore.

An aircraft has a fuselage, left and right wings, and left and right engine assemblies connected to the wings. Each engine assembly has a nacelle, an engine housed in the nacelle, the engine having a plurality of rotors defining an uncontained rotor impact area, a pylon connecting the nacelle to its wing, at least one hydraulic actuator connected to at least one of the engine and the nacelle, at least one directional control valve hydraulically connected to the at least one hydraulic actuator, and at least one isolation valve hydraulically connected to the at least one directional control valve for selectively cutting off a supply of hydraulic fluid to the at least one directional control valve, the at least one isolation valve being disposed rearward of the uncontained rotor impact area and forward of a trailing edge of its corresponding wing.