Abstract: An actuation device for a thrust reverser includes thrust-reversal movable elements carried by a nacelle and displaceable between a retracted and deployed position. The actuating device includes two actuators mounted on the nacelle and connected to a motor and to the movable elements. The actuation device drives the movable elements in a retraction or deployment direction over a course of the actuators between the retracted and deployed position. The actuation device further includes locks for locking the movable elements in the retracted position and antideployment members associated with the actuators which allow free operation of the actuators in the direction of retraction and retain the actuators in the direction of deployment. The antideployment bodies further provide free operation of the actuators in the direction of deployment over part of the actuators stroke that corresponds to a shift from an over-retraction position to the retraction position of the movable elements.

Abstract: An actuation device for a thrust reverser includes thrust-reversal movable elements carried by a nacelle and displaceable between a retracted and deployed position. The actuating device includes two actuators mounted on the nacelle and connected to a motor and to the movable elements. The actuation device drives the movable elements in a retraction or deployment direction over a course of the actuators between the retracted and deployed position. The actuation device further includes locks for locking the movable elements in the retracted position and antideployment members associated with the actuators which allow free operation of the actuators in the direction of retraction and retain the actuators in the direction of deployment. The antideployment bodies further provide free operation of the actuators in the direction of deployment over part of the actuators stroke that corresponds to a shift from an over-retraction position to the retraction position of the movable elements.

Abstract: A method and device automatically engage an emergency descent function of an aircraft as a function of pressure variation measured in the cabin of the aircraft.

Abstract: Method and device for the automatic control of an emergency descent of an aircraft The device (1) comprises means (2) for automatically engaging an emergency descent function of an aircraft, as a function of a variation in the pressure measured in the cabin of the aircraft.