Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader having a central part connected to the support and a first and a second end that are connected to thrust rods, at least one limiting system for limiting the travel of the spreader having an upper and a lower stop between which is positioned the first or second end of the spreader, the upper and the lower stop being connected to one another so as to form a single part connected to a fitting secured to the support.

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall that has a front face, and a front engine attachment having a beam that is fixed against the front face and to which is fixed, on either side of a median plane, a rod system, wherein each rod system is fixed to the beam in an articulated manner by at least one first connection point, and is configured to be fixed to a front part of the engine in an articulated manner by at least one second connection point. Such a front engine attachment system thus has rod systems having two rods, allowing the shape of the rods and the shape of the beam to be simplified.

Abstract: A front engine attachment system for an engine of an aircraft. The front engine attachment system has an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam is made up of a front plate and a rear plate that are fastened together in a removable manner. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. Each link-rod system is fastened to the rear plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

Abstract: A front engine attachment system for an aircraft engine, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam has front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate. Each link-rod system is fastened to the intermediate plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

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 front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam, which is fastened to the front face and to which a link rod is fastened on either side of a median plane. Each link rod is fastened to the beam in an articulated manner by at least one first connection point and is configured to be fastened to the engine in an articulated manner by at least one second connection point. The beam is made up of front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate.

Abstract: A front engine attachment system for an engine of an aircraft. An engine pylon has a frontal rib with a front engine attachment with a first link rod which is fixed directly to the frontal rib by two connecting points. A second link rod is provided which has a first end fixed to the first link rod by a connecting point. The first link rod is fixed directly to an engine casing by at least two connecting points and a second end of the second link rod is fixed to the engine casing by a third connecting point. The first link rod may be made up of two adjoining plates that are fixed together. Also, an aircraft with such a front engine attachment system.

Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader having a central part connected to the support and a first and a second end that are connected to thrust rods, at least one limiting system for limiting the travel of the spreader having an upper and a lower stop between which is positioned the first or second end of the spreader, the upper and the lower stop being connected to one another so as to form a single part connected to a fitting secured to the support.

Abstract: A rear engine attachment having a beam fixed to a pylon, a spreader pivotally mounted on the beam, the spreader comprising two ends situated on either side of a median plane, two rods located one on either side of the median plane, each rod having a first end fixed to one end of the spreader by a ball joint and a second end fixed to the engine, each ball joint comprising a clevis with two arms at the first end of the rod, a swivel bearing arranged on the end of the spreader, and a hinge pin passing through the two arms, the swivel bearing arranged between the two arms and fitted on the hinge pin. For each ball joint, an interface part is removably interposed between the end of the spreader and the first end of the rod and forms a contact surface between the spreader and the rod.

Abstract: An assembly for an aircraft, which includes a pylon with a bearing face and a contact face, an engine mount with a bearing face and a contact face bearing against the contact face of the pylon, at least two bolts comprising a threaded stem with a head and a nut bearing against the bearing face of the engine mount, for each head, a bearing washer with a first bearing face and a second bearing face, where the second bearing face of the bearing washer bears against the bearing face of the pylon, and where the head bears against the first bearing face of the bearing washer, a shoe, and, for each bearing washer, a clamp that is secured to the shoe and comprises a first branch and a second branch between which the bearing washer is clamped and is free to rotate.

Abstract: A forward engine attachment system for an engine of an aircraft, the forward engine attachment system including a jet engine pylon including, in the region of the forward part thereof, a front part having an attachment wall, and a forward engine attachment with a connecting rod system on either side of a median plane, wherein each connecting rod system is fixed in articulated manner by at least one first link point to the attachment wall and is designed to be fixed in an articulated manner by at least one second link point to a forward part of the engine. Such a forward engine attachment system thus includes a direct coupling between the jet engine pylon and the engine, allowing the production of an assembly that is less heavy and is easier to produce.

Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader, extending between first and second ends that has a central part connected to the support by a principal link comprising a principal rotation axis, at least one system for limiting the deflection of the spreader comprising an extension secured to the spreader and also upper and lower stops, secured to a fitting secured to the support, between which the extension is positioned.

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 front engine attachment system for an aircraft engine, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam has front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate. Each link-rod system is fastened to the intermediate plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall that has a front face, and a front engine attachment having a beam that is fixed against the front face and to which is fixed, on either side of a median plane, a rod system, wherein each rod system is fixed to the beam in an articulated manner by at least one first connection point, and is configured to be fixed to a front part of the engine in an articulated manner by at least one second connection point. Such a front engine attachment system thus has rod systems having two rods, allowing the shape of the rods and the shape of the beam to be simplified.

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam, which is fastened to the front face and to which a link rod is fastened on either side of a median plane. Each link rod is fastened to the beam in an articulated manner by at least one first connection point and is configured to be fastened to the engine in an articulated manner by at least one second connection point. The beam is made up of front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate.

Abstract: A forward engine attachment system for an engine of an aircraft, the forward engine attachment system including a jet engine pylon including, in the region of the forward part thereof, a front part having an attachment wall, and a forward engine attachment with a connecting rod system on either side of a median plane, wherein each connecting rod system is fixed in articulated manner by at least one first link point to the attachment wall and is designed to be fixed in an articulated manner by at least one second link point to a forward part of the engine. Such a forward engine attachment system thus includes a direct coupling between the jet engine pylon and the engine, allowing the production of an assembly that is less heavy and is easier to produce.

Abstract: A front engine attachment system for an engine of an aircraft. The front engine attachment system has an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam is made up of a front plate and a rear plate that are fastened together in a removable manner The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. Each link-rod system is fastened to the rear plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader, extending between first and second ends that has a central part connected to the support by a principal link comprising a principal rotation axis, at least one system for limiting the deflection of the spreader comprising an extension secured to the spreader and also upper and lower stops, secured to a fitting secured to the support, between which the extension is positioned.

Abstract: A rear engine attachment having a beam fixed to a pylon, a spreader pivotally mounted on the beam, the spreader comprising two ends situated on either side of a median plane, two rods located one on either side of the median plane, each rod having a first end fixed to one end of the spreader by a ball joint and a second end fixed to the engine, each ball joint comprising a clevis with two arms at the first end of the rod, a swivel bearing arranged on the end of the spreader, and a hinge pin passing through the two arms, the swivel bearing arranged between the two arms and fitted on the hinge pin. For each ball joint, an interface part is removably interposed between the end of the spreader and the first end of the rod and forms a contact surface between the spreader and the rod.