Abstract: A rear engine fastener for an aircraft connecting a primary structure and an engine of an aircraft, the rear engine fastener comprising a support configured to be connected to the primary structure, at least one main shackle connected to the support by first and second support link pins, which are symmetrical relative to a vertical longitudinal plane, and to the engine by a first lateral engine link pin and by a central engine link pin, and at least one secondary shackle connected to the engine by a second lateral engine link pin and to the main shackle by a secondary link pin.

Abstract: An engine attachment system for an engine including an engine nacelle. The engine attachment system includes an engine pylon with a starboard face and a port face, a starboard shoe having a starboard sole fixed to the starboard face and a starboard wall secured to the starboard sole, a port shoe having a port sole fixed to the port face and a port wall secured to the port sole, a starboard link fixed in an articulated manner by one of its ends to the starboard wall and configured to be articulatedly fixed by the other of its ends to the engine nacelle, a port link articulatedly fixed by one of its ends to the port wall and configured to be atriculatedly fixed by the other of its ends to the engine nacelle, and a fixing arrangement that fixes each sole to the corresponding face of the engine pylon.

Abstract: A rear engine attachment having first and second parts, wherein the first part has two first clevises fixed to a lower face of a pylon, two second clevises fixed to a structural casing, two connecting rods mounted to be articulated between first and second clevises, and two shafts realizing the connections between the connecting rods and the clevises. The second part has a shoe fixed to the lower face and having a bore, a main rod which bears a vertical peg engaging in the bore and which is fixed to the structural casing by a first pivot connection, and a secondary rod fixed to the main rod by a second pivot connection and to the structural casing by a third pivot connection. Such a rear engine attachment is more compact, taking up space in the longitudinal direction and thus minimizing the space taken up in the transverse direction.

Abstract: An assembly comprising a wing with lower spars, a mounting pylon having an upper spar and two lateral panels, a front fixing system and a rear fixing system, each comprising a beam pierced with a principal bore and, for each beam, an upper bore traversing the upper spar and a shear pin positioned in the upper bore and in the principal bore. The assembly also comprises, for each fixing system, bolts, the nut of which is accommodated in a secondary hole of the beam and the screw of which traverses the upper spar and the beam in order to be screwed into the nut.

Abstract: An assembly of a pylon and of a wing of an aircraft, the pylon including a primary structure with a rear face and an upper spar. The assembly includes a rear fastening system including a pair of vertical shackles articulated between the rear face of the primary structure and a first shoe fastened to the wing, wherein the shackles are fastened to the primary structure by a clevis-type connection, and a pair of transverse shackles articulated between the rear face of the primary structure and a second shoe fastened to the wing, wherein the shackles are fastened to the primary structure by a clevis-type connection. With such an assembly, the bulk of the rear fastening system is reduced.

Abstract: An assembly of an engine with a pylon, including a force reacting assembly having a connection device and two rods, the connection device including a shoe. A spreader extends between first and second ends and has a central part connected to the shoe by a main connection including a main rotation pin and axis in a plane of symmetry of the connection device. Two fittings are on either side of the plane of symmetry each having two arms between which the spreader is positioned. A first, respectively second, rod includes a front end fastened to the engine and a rear end fastened to the first, respectively second, end of the spreader and to the first, respectively second, fitting by a secondary connection. Two extensions of the spreader are each associated with a pair of elastic stops. For the first, respectively second, end of the spreader, each stop is between an arm of the first, respectively second, fitting and the extension.

Abstract: A propulsion assembly including a primary structure of a pylon having right and left extensions projecting with respect to right and left lateral panels of the primary structure and also right and left brackets, each having a first flank connected to the right or left lateral panel of the primary structure and a second flank pressed against the right or left extension, a front engine mount having first and second links, each connected to an engine and directly to the front transverse reinforcement by a first or second reinforcement connection pin passing through the right or left extension and the second flank of the right or left bracket.

Abstract: A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.

Abstract: An assembly for an aircraft that has a wing and an engine pylon having a primary structure with right-side and left-side panels, an upper and a lower spar and a rear rib, two sets of upper or lower shackles, one set fastening the right-side panel to the wing, and a second set fastening the left-side panel to the wing, a fastening element secured to the rear rib or to the lower spar, a rear rod connecting the fastening element to the wing, a transverse shackle connecting the upper spar to the wing, a line connecting two centers of the transverse shackle being oriented transversely relative to a longitudinal axis of the engine pylon, and a reinforcing panel, at each joint between a right-side or left-side panel and an upper or lower shackle, which is fastened along a height against the panel and to which the shackle is also fastened.

Abstract: An assembly including a connecting device, connecting first and second parts, including first and second links positioned on respective opposite sides of the first and second parts and an interleaved stiffener, positioned between the first and second links, having a first contact face oriented toward the first link and a second contact face oriented toward the second link, parallel to the first face, the first and second contact faces being separated by a distance equal to that separating the first and second links. This interleaved stiffener makes it possible to limit the risks of bending of the links when they are loaded in compression.

Abstract: A cold regulating valve for a heat exchanger system of an aircraft propulsion system, where the cold regulating valve includes an open frame which delimits an opening, two shutters with an external convex shape slidably mounted on the open frame between a closed position and an open position, a mechanism linked to the shutters and mobile between a first position and a second position, and wherein the mechanism moves the shutters from the closed position to the open position when it moves from the first position to the second position and vice versa, and an actuator acting on the mechanism to move it from the first position to the second position and vice versa. The specific embodiment of the cold regulating valve generates a low drag when the shutters are in a closed position.

Abstract: An aircraft including a rear wing attachment, connecting a primary structure of an aircraft pylon to its wing, and including at least one right-hand link connected to the wing by a first right-hand connecting element and to the primary structure by a second right-hand connecting element and configured to react loads oriented parallel to the vertical direction only, at least one left-hand link connected to the wing by a first left-hand connecting element and to the primary structure by a second left-hand connecting element and configured to react loads oriented parallel to the vertical direction only, a shear pin secured to the primary structure and housed in operation in a housing secured to the wing, the shear pin and the housing being configured to react loads oriented in a plane approximately perpendicular to the vertical direction.

Abstract: A rear engine attachment system for an aircraft engine. The attachment system has an engine pylon with a lower spar having a lower surface, and a rear engine attachment having a beam fixed against the lower surface and to which a pair of rods is fixed. Each rod is fixed to the beam by at least one first connection point and to the engine by at least one second connection point. The beam includes front and rear fittings, and an intermediate fitting with a shoe and an intermediate clevis. The shoe presses against the lower surface. The front fitting presses against the intermediate fitting at the front and the rear fitting presses against the intermediate fitting at the rear. The fixing to the lower spar is ensured by bolts, each passing through the front base or the rear base, the shoe and the lower spar.

Abstract: A rear engine attachment having first and second parts, wherein the first part has two first clevises fixed to a lower face of a pylon, two second clevises fixed to a structural casing, two connecting rods mounted to be articulated between first and second clevises, and two shafts realizing the connections between the connecting rods and the clevises. The second part has a shoe fixed to the lower face and having a bore, a main rod which bears a vertical peg engaging in the bore and which is fixed to the structural casing by a first pivot connection, and a secondary rod fixed to the main rod by a second pivot connection and to the structural casing by a third pivot connection. Such a rear engine attachment is more compact, taking up space in the longitudinal direction and thus minimizing the space taken up in the transverse direction.

Abstract: An engine attachment system for an engine including an engine nacelle. The engine attachment system includes an engine pylon with a starboard face and a port face, a starboard shoe having a starboard sole fixed to the starboard face and a starboard wall secured to the starboard sole, a port shoe having a port sole fixed to the port face and a port wall secured to the port sole, a starboard link fixed in an articulated manner by one of its ends to the starboard wall and configured to be articulatedly fixed by the other of its ends to the engine nacelle, a port link articulatedly fixed by one of its ends to the port wall and configured to be atriculatedly fixed by the other of its ends to the engine nacelle, and a fixing arrangement that fixes each sole to the corresponding face of the engine pylon.

Abstract: An aircraft rear engine attachment connecting a primary structure of a pylon and an engine of an aircraft. The rear engine attachment includes first and second rods, each of them including at least two parts, a first part including at least one support orifice, accommodating a support link bar, configured to connect the rod directly or indirectly to the primary structure, at least one second part including at least one engine orifice, accommodating an engine link bar, configured to connect the rod directly or indirectly to the engine, and also detachable link elements for connecting the first and second parts oriented parallel to the direction of the rod.

Abstract: A rear engine fastener for an aircraft connecting a primary structure and an engine of an aircraft, the rear engine fastener comprising a support configured to be connected to the primary structure, at least one main shackle connected to the support by first and second support link pins, which are symmetrical relative to a vertical longitudinal plane, and to the engine by a first lateral engine link pin and by a central engine link pin, and at least one secondary shackle connected to the engine by a second lateral engine link pin and to the main shackle by a secondary link pin.

Abstract: An assembly comprising a wing with lower spars, a mounting pylon having an upper spar and two lateral panels, a front fixing system and a rear fixing system, each comprising a beam pierced with a principal bore and, for each beam, an upper bore traversing the upper spar and a shear pin positioned in the upper bore and in the principal bore. The assembly also comprises, for each fixing system, bolts, the nut of which is accommodated in a secondary hole of the beam and the screw of which traverses the upper spar and the beam in order to be screwed into the nut.

Abstract: An aircraft engine attachment pylon including a rigid structure forming a caisson, and a rear engine attachment including an attachment body and at least one lateral fitting arranged on either side of the caisson. Each fitting includes a first portion pierced by first assembly holes enabling it to be fixed to the caisson, and a second portion defining a fixing surface of the body. The second portion includes a housing orifice receiving a self-locking nut cooperating with a screw supported against the body and, in transversal section, an axis of the screw passes through the first holes.

Abstract: An engine attachment pylon for an aircraft including an intermediate piece interposed between a crossbar support and a rigid caisson, a first shear slug passing through a first interface fixing plane between the piece and the caisson, and a second shear slug passing through a second interface fixing plane between the piece and the support. Also, in side elevation, the intersection point between an axis of the pin and the plane, as well as the intersection point between an axis of the pin and the plane, are located on the common axis of two lateral thrust force collection connecting rods articulated on the crossbar.