Abstract: An actuation system for a control surface for an aircraft includes a first, second, third and fourth actuator, a first and second bell crank, and at least one push pull rod system. Each of the first and second bell cranks comprises a first and a second crank arm, the first and second crank arms intersect with and are joined to each other at an intersection, the first and second crank arms extend from the intersection at an angle to each other, the first bell crank is pivotally connected to the sub-structure by a first pivot extending through the first bell crank's intersection, and the second bell crank is pivotally connected to the sub-structure by a second pivot extending through the second bell crank's intersection.

Abstract: An electrical connection comprises a first connector, a second connector, a first wall surrounding the first connector, and a second wall surrounding the second connector. The first wall is configured to fit inside the second wall when the first and second connectors are connected. The first and second walls include leading faces comprising first and second chamfered portions, respectively. The first and second chamfered portions are angled complementarily for guiding the first wall inside the second wall during connection of the first and second connectors.

Abstract: A screw (20) assembly for an actuator (10) is described comprising: a screw (20); a nut (22) threaded on said screw (20), such that rotation of said screw (20) causes axial movement of said nut (22); a stop located at an end of said screw (20) and defining an axial limit of said nut (22); a first feature located on said nut (22); and a second feature located on said stop; wherein said first and second features are configured to cooperate with one another substantially upon contact of said nut (22) with said stop so as to indicate an amount of free movement between said nut (22) and said screw (20).

Abstract: A control valve comprises a first spool 22, a second spool 24 encircling at least part of the first spool 22 and angularly moveable relative thereto, and a sleeve 32 encircling at least part of the second spool 24, the second spool 24 being angularly moveable relative to the sleeve 32, the first and second spools 22, 24 having first and second series of ports 28, 30 registrable with one another, depending upon the relative angular positions of the first and second spools 22, 24, to control communication between at least a pressure line 16, a return line 18 and a control line 50 provided in or connected to the sleeve 32, the second spool 24 and the sleeve 32 having third and fourth series of ports 66, 68, axially spaced from the first and second series of ports 28, 30 and registrable with one another, depending upon the relative angular positions of the second spool 24 and the sleeve 32, to control communication between at least the control line 50 and the return line 18, and latch means 56 operable to resist

Abstract: A device (13) for detecting the breakage of a primary path in a flight control actuator, said actuator having a primary path (1) comprising a rotary hollow screw (2), a secondary path (10) comprising a safety rod (3) that reacts the load passing through the screw (2), said device (13) being characterized in that it comprises a position sensor (15), connected to the screw (2), to measure information representative of the angular position thereof, and a disconnection system (17) able to disconnect the screw (2) position sensor (15) in the event of relative movement of the rod (3) with respect to the screw (2) if there is a break in the primary path (1).

Abstract: The invention relates to a flight-control actuator comprising a control screw (1) that engages with a primary nut (2), the actuator also comprising a secondary nut (5) that engages with the control screw in the event the primary nut fails. The primary nut and the secondary nut are remote from one another, the secondary nut moving substantially along a portion of the screw that is usually not fitted with the primary nut.

Abstract: The disclosure relates to a device for testing means of detecting the loading of the secondary path of a flight control actuator of the type including a primary path and a secondary path able to take up the effort of the primary path in the event of a breakdown of the latter, wherein a tool is able to press against at least one zone of at least one element of the secondary path, as well as a lever arm which by tilting allows the tool to press against the zone so that it exerts a traction and/or compression force on the secondary path, the lever arm being mounted pivotingly on a support able to be fastened on a structure that is mechanically independent of the secondary path.

Abstract: The invention relates to a no-back device for a mobile element actuating device including a screw shaft having first and second braking means each comprising a ratchet wheel. These ratchet wheels are mounted opposite one another so that the first braking means are adapted to resist an unwanted movement of the screw shaft in a first direction, and the second braking means are adapted to resist an unwanted movement of the screw shaft in an opposite direction. The no-back device also includes means for detecting the state of the rotation of the ratchet wheels and indicating means for furnishing, according to the state of the rotation of the wheels, an indication concerning the operating state of the no-back device.

Abstract: The assembly comprises a first and a second nut intended to cooperate with a screw in particular provided in an adjustable tailplane actuator for an aircraft, and a mechanical connection between the first and the second nut comprising means for fusible driving of the second nut by the first nut, in which the mechanical connection also comprises adjustable spacing means forming a wedge between the first and second nuts.

Abstract: The disclosure relates to a device for testing means of detecting the loading of the secondary path of a flight control actuator of the type including a primary path and a secondary path able to take up the effort of the primary path in the event of a breakdown of the latter, wherein a tool is able to press against at least one zone of at least one element of the secondary path, as well as a lever arm which by tilting allows the tool to press against the zone so that it exerts a traction and/or compression force on the secondary path, the lever arm being mounted pivotingly on a support able to be fastened on a structure that is mechanically independent of the secondary path.

Abstract: The use of at least one attachment screw (12) that includes means (14, 15, 17a, 17b, 20) for detecting the secondary path loading of a flight-control actuator, or associated with a bush that includes such means, for the attachment of the top coupling of the secondary path of a flight-control actuator.

Abstract: Device for sensing load relief by a secondary path of a flight control actuator having a primary path and a secondary path capable of relieving the load of the primary path in the event of a breakdown thereof, the primary path comprising a screw, the screw terminating in a fastener of the primary path, the secondary path comprising an emergency load relief rod passing through the screw, this rod terminating in a male shape which, when the primary path is carrying the load, is accommodated inside of a female shape of a fastener of the secondary path, characterized in that at least one sensing element is disposed on the male shape terminating the rod, on the female shape or between both of these two shapes, this sensing element being designed to wear down due to the friction between the male shape and the female shape, when the secondary path is loaded and is relieving the load, this sensing element being connected or capable of being connected to means capable of sensing wear on this sensing element and of tri

Abstract: A linear screw actuator including, an outer housing which is fixed in use, an electric motor within the housing, the motor including a hollow rotatable output shaft, a rotatable but axially fixed nut driven by said output shaft, an elongate hollow axially translatable output member, said output member extending within said output shaft of said motor and cooperating with said rotatable nut, and, an elongate anchor member secured against rotation relative to said housing and extending within said output member, said anchor member cooperating with said output member to hold said output member against rotation whereby rotation of said nut relative to said output member causes axial translation of said non-rotatable output member relative to the housing.

Abstract: The invention relates to an actuator for actuating a moving member, said actuator essentially comprising a screw and at least two nuts engaged on the screw, relative movement between the screw and the nuts generating said actuation, said actuator further comprising a pin through which an electrical link passes, a force-transmitting element placed in the path of the force between the screw and the moving member via one of the nuts, and a mechanical extension of said force-transmitting element that extends to the vicinity of the other nut, the pin passing both through the mechanical extension and through an element coupled to the other nut so that any abnormal shift in the force-transmitting element relative to the screw results in shear between its mechanical extension and the element coupled to the other nut, causing the pin to break and causing the electrical link to be broken.

Abstract: The invention relates to a no-back device for a mobile element actuating device including a screw shaft having first and second braking means each comprising a ratchet wheel. These ratchet wheels are mounted opposite one another so that the first braking means are adapted to resist an unwanted movement of the screw shaft in a first direction, and the second braking means are adapted to resist an unwanted movement of the screw shaft in an opposite direction. The no-back device also includes means for detecting the state of the rotation of the ratchet wheels and indicating means for furnishing, according to the state of the rotation of the wheels, an indication concerning the operating state of the no-back device.