Abstract: A propulsion system of an aircraft comprising a turbojet extending around a longitudinal axis and having a vertical median plane passing through the longitudinal axis and having a fan casing with a rear face perpendicular to the longitudinal axis, a pylon presenting a rigid structure with a front wall and a lower spar, and an engine attachment comprising a front ring coaxial with the longitudinal axis and comprising first fixation element for securing the front ring to the rear face of the fan casing and second fixation element for securing the front ring to the front wall of the pylon.

Abstract: A propulsion system comprising a turbojet with a fan casing and a central casing, a pylon with an upper spar, a front wall and on either side of a vertical median plane, a fitting rigidly fixed to the rigid structure, a cylindrical pin as one with the fan casing and inserted in a hole of the upper spar, a shackle with at the vertical median plane, an upper articulation between the shackle and the front wall and on either side of the vertical median plane, a lower articulation between the shackle and the central casing, and two reaction rods disposed on either side of the median plane, where each rod is articulated, at a front end, on the central casing, and, at rear end, on the fitting.

Abstract: An aircraft propulsion system comprising a turbojet having a fan casing with a rear face, a pylon with a front part and a lower spar with a rear fitting fixed to it, and a front engine attachment fixed between an upper part of the fan casing and the front part, a front arch having two arms, each having a first end fixed to the lower spar and a second end fastened in an articulated manner to the rear face, and two lateral rods, each having a first end fastened in an articulated manner to the rear fitting and a second end fastened in an articulated manner to the rear face.

Abstract: An assembly of an attachment pylon with an aircraft engine comprising a front engine mount comprising a front tang and a front clevis, a lower tang and a lower clevis connecting the attachment pylon and the engine via a front pin mounted in the front tang and clevis and a lower pin mounted in the lower tang and clevis, and port/starboard links mounted between the attachment pylon and the engine via mounting pins, wherein the front and lower pins are orthogonal to a mid-plane, and wherein the mounting pins of the links are parallel to the mid-plane.

Abstract: An assembly comprising a wing with a lower surface panel and an upper surface panel and an engine pylon comprising a primary structure fixed to the wing with a fixing base. The fixing base comprises fourth fixing yokes while the primary structure bears fourth fittings, the fourth fixing yokes being secured to the fourth fittings with fourth rods.

Abstract: An engine pylon for an aircraft and comprising an inverted U-shaped upper spar with two lateral walls, a U-shaped lower spar with two lateral walls, where the free ends of the lateral walls of the spars are adjacent, an arrangement to the free end of a lateral wall of one spar to the free end of the lateral wall of the other spar, and ribs between the spars where each has a top end fixed to the lateral walls of the upper spar and a bottom end fixed to the lower spar. Such an engine pylon thus offers a reduced number of component parts and a single row of fixings per side, enabling a saving in weight and in assembly time.

Abstract: The invention relates to a propulsion assembly having a jet engine with an intermediate casing with a rear face and a core casing to the rear of the intermediate casing, and an attachment pylon with a frontal wall and two lateral walls, a front engine attachment having a front fitting fastened in an articulated manner via two lateral fastening points to the rear face and in a rigid manner via an upper fastening zone to the frontal wall, and an intermediate engine attachment comprising a front link rod and a rear link rod on each side. Each of the link rods is mounted in an articulated manner between the front fitting and the lateral wall. With such an arrangement, the bulk of the engine attachments is reduced in the bypass flow.

Abstract: An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.

Abstract: An aircraft having a fixed structure, an engine pylon, and a cowling system, a slider bearing a rear cowl and able to move in translation from an advanced position to a retracted position, a displacement system having, on either side of a median plane of the engine pylon, a guide as one with the fixed structure, a sliding element as one with the slider and sliding along each guide disposed on the same side, and a support as one with the fixed structure and having a blade parallel to the translation direction and on which a surface parallel to the translation direction of the slider rests. The presence of the mobile cowl ensures, inter alia, easy access to the inside of the engine pylon and to the systems that are housed therein.

Abstract: An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.

Abstract: An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.

Abstract: A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

Abstract: An engine pylon of an aircraft having a rear portion, two rear cowls around the rear portion, each rear cowl having an upper fixed cowl and a lower movable cowl mounted articulated on the rear portion, wherein in the closed position the two lower movable cowls are moved close to one another, such that their lower edges are contiguous, wherein in the open position the two lower movable cowls are tilted such that their lower edges are moved away from one another, for each lower movable cowl, a hinge system fixed between the lower movable cowl and the rear portion, and at least one locking system which locks the two lower movable cowls to one another in the closed position. The presence of the lower movable cowls ensures, among other things, easy access to the interior of the engine pylon.

Abstract: An engine mounting pylon for suspending a turbofan beneath an aircraft wing, including a primary structure, a fastening device for fastening to the turbofan, and a fastening device for fastening to the wing. The engine mounting pylon furthermore comprises multiple rigid braces that mechanically connect the primary structure to the wing of the aircraft, a first brace-attachment device that mechanically connects a first end of each brace to the wing, and a second brace-attachment device that mechanically connects a second end of each brace to the primary structure. This braced-pylon architecture makes it possible to reduce the dimensions of the primary structure and the various elements that constitute the first and second attachment devices.

Abstract: An engine pylon has a primary structure fastened between an engine and an aircraft wing and a cowling system having a front set of fixed cowls, a rear cowl, a displacement system having a first structure as one with the rear cowl and having a first slide mechanism, and a second structure fastened to a fixed structure of the wing and having second slide mechanism. The slide mechanisms cooperate so as to realize a sliding connection and to move the rear cowl in translation from an advanced position to a retracted position. An immobilizing system locks the rear cowl in the advanced position.

Abstract: An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

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: An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.

Abstract: An assembly having a pylon with an upper spar and four lateral scoops, a wing with a skin, longitudinal spars and fittings, and, for each lateral scoop, two fastening assemblies, wherein the skin and the fitting each have a first bore and wherein the upper spar and the lateral scoop each have a second bore, wherein each fastening assembly has a screw passing through the first and the second bores, a nut, two eccentric rings, threaded onto one another and onto the screw, and a system for stopping the eccentric rings rotating. The assembly makes it possible to dispense with the use of the spigots while also ensuring the reaction of the shear forces contained in the XY plane by the bolts on account of the reduced tolerances between the various bores, the external and internal surfaces of the eccentric rings and the plain zones of the screws.

Abstract: An engine pylon for an aircraft and comprising an inverted U-shaped upper spar with two lateral walls, a U-shaped lower spar with two lateral walls, where the free ends of the lateral walls of the spars are adjacent, an arrangement to the free end of a lateral wall of one spar to the free end of the lateral wall of the other spar, and ribs between the spars where each has a top end fixed to the lateral walls of the upper spar and a bottom end fixed to the lower spar. Such an engine pylon thus offers a reduced number of component parts and a single row of fixings per side, enabling a saving in weight and in assembly time.