Abstract: An aircraft pylon comprising an aircraft pylon fairing extending along a longitudinal axis, a primary structure having a peg that is inserted in a through opening of an inner rib of the fairing and four yokes as well as four removable fixing elements that can be inserted from the outside of the fairing. The fixing elements are inserted in a direction perpendicular to said longitudinal axis of the fairing in order to hold in place a fitting of the primary structure that has an oblong through opening and is inserted into one of said yokes of the fairing. Also a method of assembling an aircraft pylon and an aircraft with such a pylon.

Abstract: An assembly of a pylon and of an engine with a rear engine attachment having two fittings, wherein each one has a shoe fastened to a lower spar of the pylon, two transverse arms, one front and one rear, which are as one with the shoe and offset such that the front transverse arm, respectively rear transverse arm, of one fitting bears in planar fashion against the front transverse arm, respectively rear transverse arm, of the other fitting, wherein each transverse arm is pierced with a bore, wherein the two front transverse arms and the two rear transverse arms are spaced apart parallel to the longitudinal direction and thus form a female clevis, and wherein the assembly also has a lower rod mounted articulated in the female clevis and on the engine. With such an assembly, the number of components is reduced.

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: A front engine attachment system having an engine pylon having a frontal rib fastened against a front face, a front engine attachment having a beam fastened to the frontal rib, two rods articulated to the beam respectively via two connection points and one connection point, and a front casing of an engine, wherein the first rod is articulated to the front casing via a connection point and wherein the second rod is articulated to the front casing via a connection point, wherein each point of connection of a rod to the beam is positioned inside a volume that extends the front face of the engine pylon towards the front. Such a front engine attachment system has reduced bulk and therefore less drag.

Abstract: A propulsion assembly includes an engine below a pylon by engine attachments, including a thrust force uptake device, the engine having a longitudinal axis and a vertical median plane parallel to the longitudinal axis, the thrust force uptake device having a main fitting fixed below the pylon and two links disposed on either side of the vertical median plane and which each have a rear end articulated to the main fitting by a spreader mounted to pivot on the main fitting about an axis of rotation which, on the one hand, is orthogonal to a mean plane for transmitting thrust forces parallel to the longitudinal axis of each of the links, and which is disposed in the vertical median plane, each link being articulated to the spreader by a connecting pin extending parallel to the mean plane for transmitting thrust forces and perpendicular to the longitudinal axis of the link.

Abstract: An assembly of a pylon and of an engine with a rear engine attachment having two fittings, wherein each one has a shoe fastened to a lower spar of the pylon, two transverse arms, one front and one rear, which are as one with the shoe and offset such that the front transverse arm, respectively rear transverse arm, of one fitting bears in planar fashion against the front transverse arm, respectively rear transverse arm, of the other fitting, wherein each transverse arm is pierced with a bore, wherein the two front transverse arms and the two rear transverse arms are spaced apart parallel to the longitudinal direction and thus form a female clevis, and wherein the assembly also has a lower rod mounted articulated in the female clevis and on the engine. With such an assembly, the number of components is reduced.

Abstract: A propulsion assembly includes an engine below a pylon by engine attachments, including a thrust force uptake device, the engine having a longitudinal axis and a vertical median plane parallel to the longitudinal axis, the thrust force uptake device having a main fitting fixed below the pylon and two links disposed on either side of the vertical median plane and which each have a rear end articulated to the main fitting by a spreader mounted to pivot on the main fitting about an axis of rotation which, on the one hand, is orthogonal to a mean plane for transmitting thrust forces parallel to the longitudinal axis of each of the links, and which is disposed in the vertical median plane, each link being articulated to the spreader by a connecting pin extending parallel to the mean plane for transmitting thrust forces and perpendicular to the longitudinal axis of the link.

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: A front engine attachment system having an engine pylon having a frontal rib fastened against a front face, a front engine attachment having a beam fastened to the frontal rib, two rods articulated to the beam respectively via two connection points and one connection point, and a front casing of an engine, wherein the first rod is articulated to the front casing via a connection point and wherein the second rod is articulated to the front casing via a connection point, wherein each point of connection of a rod to the beam is positioned inside a volume that extends the front face of the engine pylon towards the front. Such a front engine attachment system has reduced bulk and therefore less drag.

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 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: 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: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.

Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.