Abstract: A rear engine attachment includes a beam attached to the reactor strut, a rudder mounted by a pivot connection on the beam about a main rotational axis, and two thrust rods each exhibiting a first end attached to the rudder and a second end attached to a front section of an engine, the two thrust rods and the rudder attached to the beam together defining a primary thrust path between the engine and the reactor strut to bear the engine thrust. For each thrust rod, the rear engine attachment exhibits a waiting fail-safe system activated in the event of a failure of the primary thrust path. The rear engine attachment includes, for each thrust rod, a break detector integral with the rudder which is provided to come into contact with the beam in the event of a failure of the primary thrust path. The attachment allows a quick inspection to be made to determine whether there has been a failure of the primary thrust path.

Abstract: A fire seals system positioned in a corner of a region of attachment between a rear engine mount and a pylon and comprising a metal shoe comprising a fitting comprising two first vanes forming an L fixed in the corner and a lower second vane between the lower edges of the two first vanes and an upper second vane between the upper edges of the two first vanes, and a flexible tongue having a fixed upstream end and a free downstream end in which an intermediate part of the tongue is arranged between the lower second vane and the upper second vane, and a longilinear seal attached to a thrust reverser cowl with one end of the longilinear seal bearing against the tongue. Such a fire seals system makes it possible to limit the spread of flames and to absorb movements of the nacelle.

Abstract: A rear engine attachment includes a beam attached to the reactor strut, a rudder mounted by a pivot connection on the beam about a main rotational axis, and two thrust rods each exhibiting a first end attached to the rudder and a second end attached to a front section of an engine, the two thrust rods and the rudder attached to the beam together defining a primary thrust path between the engine and the reactor strut to bear the engine thrust. For each thrust rod, the rear engine attachment exhibits a waiting fail-safe system activated in the event of a failure of the primary thrust path. The rear engine attachment includes, for each thrust rod, a break detector integral with the rudder which is provided to come into contact with the beam in the event of a failure of the primary thrust path. The attachment allows a quick inspection to be made to determine whether there has been a failure of the primary thrust path.

Abstract: A fire seals system positioned in a corner of a region of attachment between a rear engine mount and a pylon and comprising a metal shoe comprising a fitting comprising two first vanes forming an L fixed in the corner and a lower second vane between the lower edges of the two first vanes and an upper second vane between the upper edges of the two first vanes, and a flexible tongue having a fixed upstream end and a free downstream end in which an intermediate part of the tongue is arranged between the lower second vane and the upper second vane, and a longilinear seal attached to a thrust reverser cowl with one end of the longilinear seal bearing against the tongue. Such a fire seals system makes it possible to limit the spread of flames and to absorb movements of the nacelle.

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis said assembly comprising a blocking device. The blocking device comprising a screw with a first cylindrical portion which is screwed into an extension of the second sleeve and against which the second end of the articulation spindle can come to press, and a second portion, in the extension of the first portion, with a smaller cross section than said first cylindrical portion, a locking washer which is interposed between the second portion of the screw and the extension of the second sleeve in a locked position, and a longilinear element which passes through the screw and the second sleeve in a locked state.

Abstract: An assembly with an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis. The assembly comprises a blocking device. The blocking device comprises a nut screwed onto a threaded portion of an extension of the second sleeve and comprising an inner shoulder against which the second end of the articulation spindle can come to bear, a locking washer able to adopt a locked state in which it prevents the nut from rotating with respect to the extension and an unlocked state in which it allows the nut to be unscrewed, and a longilinear element able to adopt a locked state in which it passes through at least the nut so as to prevent it from rotating.

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis. The assembly comprises a blocking device which comprises a cylindrical stop housed in an extension of the second sleeve and comprising a front face against which a second end of the articulation spindle can come to bear, and a bolt-and-nut able to adopt a locked state, in which it passes through the stop and the extension so as to immobilize the stop in the extension, and an unlocked state, in which it does not pass through the stop and allows the stop to be removed from the extension.

Abstract: An engine fastener for an aircraft, to secure an engine to a pylon and comprising a fastener body fixed to the pylon and having a cylindrical extension, and a fixing assembly comprising a paddle fixed to the engine and a connection arrangement joined to the paddle and arranged on the cylindrical extension to form a ball-and-socket joint between the cylindrical extension and the paddle. The connection arrangement comprises a ball, formed in one piece, having a central bore in which the cylindrical extension fits, and of which the outer surface is a spherical portion, a fixing element fixing the ball on the cylindrical extension, and two cages, each having an inner surface assuming the form of a spherical portion. The two inner surfaces are arranged opposite one another to house the ball, and for each cage, a joining element joins the cage to the paddle.

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis, and a blocking device. The blocking device comprises a nut screwed onto an extension of the second sleeve and comprising an inner shoulder acting as a stop for a second end of the articulation spindle, at least two locking washers engaging with the nut, a tab washer comprising an element immobilizing it in rotation with respect to the second arm of the clevis, and for each locking washer, a blocking element limiting the rotational movement of the locking washer with respect to the tab washer.

Abstract: An engine fastener for an aircraft, to secure an engine to a pylon and comprising a fastener body fixed to the pylon and having a cylindrical extension, and a fixing assembly comprising a paddle fixed to the engine and a connection arrangement joined to the paddle and arranged on the cylindrical extension to form a ball-and-socket joint between the cylindrical extension and the paddle. The connection arrangement comprises a ball, formed in one piece, having a central bore in which the cylindrical extension fits, and of which the outer surface is a spherical portion, a fixing element fixing the ball on the cylindrical extension, and two cages, each having an inner surface assuming the form of a spherical portion. The two inner surfaces are arranged opposite one another to house the ball, and for each cage, a joining element joins the cage to the paddle.

Abstract: An assembly with an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis. The assembly comprises a blocking device. The blocking device comprises a nut screwed onto a threaded portion of an extension of the second sleeve and comprising an inner shoulder against which the second end of the articulation spindle can come to bear, a locking washer able to adopt a locked state in which it prevents the nut from rotating with respect to the extension and an unlocked state in which it allows the nut to be unscrewed, and a longilinear element able to adopt a locked state in which it passes through at least the nut so as to prevent it from rotating.

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis. The assembly comprises a blocking device which comprises a cylindrical stop housed in an extension of the second sleeve and comprising a front face against which a second end of the articulation spindle can come to bear, and a bolt-and-nut able to adopt a locked state, in which it passes through the stop and the extension so as to immobilize the stop in the extension, and an unlocked state, in which it does not pass through the stop and allows the stop to be removed from the extension.

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis said assembly comprising a blocking device. The blocking device comprising a screw with a first cylindrical portion which is screwed into an extension of the second sleeve and against which the second end of the articulation spindle can come to press, and a second portion, in the extension of the first portion, with a smaller cross section than said first cylindrical portion, a locking washer which is interposed between the second portion of the screw and the extension of the second sleeve in a locked position, and a longilinear element which passes through the screw and the second sleeve in a locked state.

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis, and a blocking device. The blocking device comprises a nut screwed onto an extension of the second sleeve and comprising an inner shoulder acting as a stop for a second end of the articulation spindle, at least two locking washers engaging with the nut, a tab washer comprising an element immobilizing it in rotation with respect to the second arm of the clevis, and for each locking washer, a blocking element limiting the rotational movement of the locking washer with respect to the tab washer.

Abstract: The present invention relates to an engine assembly for an aircraft comprising an attachment means, a turboprop on an attachment mast, this means including a plurality of front engine attachments (16) each having an engine vibration insulation system (20) including a housing (22), a stress transmitting member (24) extending along a first axis (26) parallel to an axis of rotation of the propeller and a hollow member (28) integrated in the housing and extending along a second axis (30) orthogonal to and intersecting the first axis. According to the invention, a support means for supporting the system (20) is formed by a plurality of clevises (32a, 32b) each having a middle plane parallel to its clevis heads, integrating one of the first and second axes and orthogonal to the other of said axes.

Abstract: The present invention relates to an engine assembly for an aircraft comprising an attachment means, a turboprop on an attachment mast, this means including a plurality of front engine attachments (16) each having an engine vibration insulation system (20) including a housing (22), a stress transmitting member (24) extending along a first axis (26) parallel to an axis of rotation of the propeller and a hollow member (28) integrated in the housing and extending along a second axis (30) orthogonal to and intersecting the first axis. According to the invention, a support means for supporting the system (20) is formed by a plurality of clevises (32a, 32b) each having a middle plane parallel to its clevis heads, integrating one of the first and second axes and orthogonal to the other of said axes.

Abstract: An aircraft engine mounting device attachment arrangement includes a fitting perforated with two orifices, and two ball joints respectively housed in the orifices. The arrangement also includes two anti-rotation systems used to lock the ball joints in their orifices, the system including a main plate traversed by an external ring of the ball joint and including tappets cooperating with notches provided on the ring, the system including a main plate traversed by a main plate of the ball joint and including tappets cooperating with notches provided on the ring. In addition, the plates are connected rigidly to each other.

Abstract: This invention relates to a mounting structure (1) for mounting an engine (2) under an aircraft wing (4), the structure comprising a rigid structure (8) and means (10) of fastening this rigid structure under the wing, the mounting means comprising a forward fastener (14), an intermediate fastener (15) and an aft fastener (16). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis (5) of the engine (2), placed in a vertical plane oriented along a longitudinal direction (X) of the aircraft. Furthermore, the intermediate fastener comprises a connecting rod capable of transferring forces applied in a direction (Y) transverse to the aircraft, and the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Abstract: This invention relates to a structure (1) for mounting an engine (2) under an aircraft wing (4), comprising a rigid structure (8) and means (10) of mounting this rigid structure under the wing, the mounting means (10) comprising a forward fastener (14) and an aft fastener (16). According to the invention, the forward fastener has at least one triangular shackle on each side of a vertical plane passing through a longitudinal axis (5) of the engine, placed in a vertical plane oriented along a direction inclined with respect to a longitudinal direction (X) and a transverse direction (Y) of the aircraft, and located in a horizontal plane defined by these directions (X) and (Y). Furthermore, the aft fastener comprises at least one shackle oriented along a vertical direction (Z) of the aircraft.

Abstract: The present invention relates to an aircraft engine mounting device attachment arrangement (23) comprising a fitting (24) perforated with two orifices (102a, 102b), and two ball joints (25a, 25b) respectively housed in said orifices. The arrangement also comprises two anti-rotation systems (122a, 122b) used to lock the ball joints in their orifices, the system (122a) comprising a main plate (124a) traversed by an external ring (108a) of the ball joint (25a) and comprising tappets (132) cooperating with notches (120) provided on the ring (108a), the system (122b) comprising a main plate (124b) traversed by a main plate (108b) of the ball joint (25b) and comprising tappets (132) cooperating with notches (120) provided on the ring (108b). In addition, the plates (124a, 124b) are connected rigidly to each other.