Abstract: A nacelle for an aircraft, including a structure, a cap attached to the structure and a seal system including an arch forming a channel which extends beneath a rear edge of the cap and which has a bottom, the arch being attached to the structure, a seal in the form of a solid block in the channel and beneath the rear edge of the cap, a spring system arranged to move the seal away from the bottom, and a retaining arrangement configured to prevent the seal from leaving the channel under the action of the spring system. With an arrangement of this kind, it is not necessary to oversize the bead, this being replaced with a solid seal mounted on a spring system.

Abstract: A nacelle for an aircraft, including a structure, a cap attached to the structure and a seal system including an arch forming a channel which extends beneath a rear edge of the cap and which has a bottom, the arch being attached to the structure, a seal in the form of a solid block in the channel and beneath the rear edge of the cap, a spring system arranged to move the seal away from the bottom, and a retaining arrangement configured to prevent the seal from leaving the channel under the action of the spring system. With an arrangement of this kind, it is not necessary to oversize the bead, this being replaced with a solid seal mounted on a spring system.

Abstract: An engine mounting structure for aircraft including an engine mounting system including a device for transmission of the thrust efforts fitted with two lateral connecting rods and with a spreader beam mounted in connected fashion on a support element, through a principal connecting device defining a principal spreader beam hinge line positioned in a plane. The spreader beam is also mounted in connected fashion with some play on the element, using a secondary connecting device located at some distance, as seen from above, from the device, and defining a secondary spreader beam hinge line, which is also positioned in a plane. The rotation of the spreader beam is stopped by device coming into contact with the spreader beam.

Abstract: The invention relates to a device (9) for taking up thrust forces for an aircraft engine pylon, which includes safety means, associated with each of the two lateral link rods (90) for taking up forces and equipped with first end-stop means (108) fitted to the link rod, as well as second end-stop means (112) fitted to the spreader bar (91), where these end-stop means, once they have come into contact as a result of relative rotation between the spreader bar and the link rod around the axis (93) of a link rod pivot mechanism (92) and in a given direction of rotation, are used to stop the said relative rotation in the given direction of rotation.

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.

Abstract: An engine mounting structure for an engine aircraft including a rigid structure forming a caisson, together with an engine mounting system mounted on the structure, and a rear engine attachment, including an attachment strut to which is connected at least one shackle, to be connected to the engine. The engine mounting system includes a system for transmitting thrust efforts generated by the engine, including two lateral connecting rods connected to a spreader beam mounted in articulated fashion relative to the caisson. The attachment strut constitutes the spreader beam, wherein the body is mounted in articulated fashion relative to the caisson using an articulated shaft system.

Abstract: An engine mounting structure for aircraft including an engine mounting system including a device for transmission of the thrust efforts fitted with two lateral connecting rods and with a spreader beam mounted in connected fashion on a support element, through a principal connecting device defining a principal spreader beam hinge line positioned in a plane. The spreader beam is also mounted in connected fashion with some play on the element, using a secondary connecting device located at some distance, as seen from above, from the device, and defining a secondary spreader beam hinge line, which is also positioned in a plane. The rotation of the spreader beam is stopped by device coming into contact with the spreader beam.

Abstract: An engine mounting structure for an engine aircraft including a rigid structure forming a caisson, together with an engine mounting system mounted on the structure, and a rear engine attachment, including an attachment strut to which is connected at least one shackle, to be connected to the engine. The engine mounting system includes a system for transmitting thrust efforts generated by the engine, including two lateral connecting rods connected to a spreader beam mounted in articulated fashion relative to the caisson. The attachment strut constitutes the spreader beam, wherein the body is mounted in articulated fashion relative to the caisson using an articulated shaft system.

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.

Abstract: The invention relates to a device (9) for taking up thrust forces for an aircraft engine pylon, which includes safety means, associated with each of the two lateral link rods (90) for taking up forces and equipped with first end-stop means (108) fitted to the link rod, as well as second end-stop means (112) fitted to the spreader bar (91), where these end-stop means, once they have come into contact as a result of relative rotation between the spreader bar and the link rod around the axis (93) of a link rod pivot mechanism (92) and in a given direction of rotation, are used to stop the said relative rotation in the given direction of rotation.