Assembly for an aircraft, the assembly having a pylon and a wing

Abstract

An assembly (200) for an aircraft, comprising a pylon (106) with an upper spar (202) and four lateral buckets (212a), a wing with a skin (210), longitudinal spars (206a-b) and fittings (208); two fastening assemblies (250) for each lateral bucket, the skin and fitting each having a first hole (251), and wherein the upper spar and the lateral bucket each having a second hole (253), each fastening assembly comprising a screw (254) passing through the first and second holes, a nut (255), two eccentric rings (256, 258) threadedly connected to each other and to the screw, and a system (260) for preventing the eccentric rings from rotating. The tolerances between the holes, the outer and inner surfaces of the eccentric rings and the flat areas of the screws are reduced, and the assembly can eliminate the use of pull nails while ensuring the reaction of the bolts to shear forces contained in the XY plane.

Description

Technical Field

[0001] The invention relates to an assembly for an aircraft, comprising a pylon and a wing, an aircraft having at least one such assembly and a method for assembling such an assembly. Background Art

[0002] An aircraft generally comprises a fuselage with wings fastened to each side of the fuselage, the wings supporting pylons to which the jet engines are fastened. The wing has at least one front spar extending along the leading edge of the wing and to which the pylons are at least partially fastened.

[0003] Figure 8 A top view of a prior art assembly 700 is shown having a pylon 702 and a wing 704 .

[0004] The wing 704 has a plurality of spars 706a - b extending within a skin 707 .

[0005] The pylon 702 has an upper spar 708, starboard and port side panels extending vertically on either side of the upper spar 708, and four lateral scoops 710a-b, each secured outboard against the side panels and secured to either side of the upper spar 708, one at the rear of the pylon 702 and one in the middle of the pylon.

[0006] The assembly 700 also has two tension bolts 712a-b for each lateral scoop 710a-b, which clamp the lateral scoop 710a-b to an element of the wing 704, in this case, the spar 706a-b. To this end, the spars 706a-b and the lateral scoop 710a-b have holes therethrough, through which the threaded rods of the tension bolts 712a-b pass. The tension bolts 712a-b ensure the reaction to forces perpendicular to the main plane of the interface, in this case, along the main vertical direction.

[0007] Due to tolerances in the construction and positioning of pylon 702 relative to wing 704, significant clearance must be provided between the flat areas of the shanks of bolts 712a-b and the holes that receive them. To counteract these forces, vertical pins 714 (also known as "spigots") are positioned between pylon 702 and wing 704 in the XY plane. There are two spigots 714 forward on both the port and starboard sides, and a central spigot 714 at the rear.

[0008] Although such a mounting method is completely satisfactory, it is necessary to find a different mounting method that avoids the need for pull studs and allows the tensioning bolts 712a-b to react the shear forces, which are contained in the main planes of the interface, without the need for the task of counter-drilling at the stations where the subassemblies are assembled, particularly at the stations in the final assembly line. Summary of the Invention

[0009] The object of the present invention is to propose an assembly for an aircraft having a wing and a pylon fastened to the wing, the construction of which makes it possible to avoid installing pull studs while ensuring that the bolts react forces in the XY plane.

[0010] To this end, a component for an aircraft is proposed, comprising:

[0011] a pylon having an upper spar, two side panels extending vertically below the upper spar, and four lateral scoops, each lateral scoop being fastened on the outside against the side panel below the upper spar, each side panel having two lateral scoops, one at the rear of the pylon and one approximately in the middle of the pylon,

[0012] - a wing having a skin, longitudinal spars and fittings fastened to the inner side of the skin and the longitudinal spars, and

[0013] for each lateral scoop, there are two fastening assemblies, wherein for each fastening assembly, the skin and the fitting each have a first hole extending mutually, and the upper spar and the lateral scoop each have a second hole extending mutually,

[0014] Each fastening assembly has:

[0015] a screw passing through each first hole and each second hole, the screw having a flat area on one side of its head and a threaded area opposite its head,

[0016] - a nut screwed onto the threaded area of ​​the screw,

[0017] an inner eccentric ring having a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution offset relative to each other, wherein the inner eccentric ring is threaded onto the flat area of ​​the screw,

[0018] an outer eccentric ring having a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution offset relative to each other, wherein the outer eccentric ring is threadedly connected to the inner eccentric ring, wherein the two eccentric rings are received and mounted in the second bore with a radially tight fit, and

[0019] - a rotation prevention system that prevents the eccentric rings from rotating,

[0020] Among them, between the head of the screw and the nut, the shoulder of the inner eccentric ring, the shoulder of the outer eccentric ring, the lateral bucket-shaped part, the upper spar, the skin and the accessories are sandwiched in sequence.

[0021] The present invention proposes an assembly for an aircraft, comprising:

[0022] a pylon having an upper spar, two side panels extending vertically below the upper spar, and four lateral scoops, each lateral scoop being fastened on the outside against the side panel below the upper spar, each side panel having two lateral scoops, one at the rear of the pylon and one approximately in the middle of the pylon,

[0023] - a wing having a skin, longitudinal spars and fittings fastened to the inner side of the skin and the longitudinal spars, and

[0024] for each lateral scoop, there are two fastening assemblies, wherein for each fastening assembly, the upper spar and the lateral scoop each have a first hole extending mutually, and the skin and the fitting each have a second hole extending mutually,

[0025] Each fastening assembly has:

[0026] a screw passing through each first hole and each second hole, the screw having a flat area on one side of its head and a threaded area opposite its head,

[0027] - a nut screwed onto the threaded area of ​​the screw,

[0028] an inner eccentric ring having a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution offset relative to each other, wherein the inner eccentric ring is threaded onto the flat area of ​​the screw,

[0029] an outer eccentric ring having a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution offset relative to each other, wherein the outer eccentric ring is threadedly connected to the inner eccentric ring, wherein the two eccentric rings are received and mounted in the second bore with a radially tight fit, and

[0030] - a rotation prevention system that prevents the eccentric rings from rotating,

[0031] Among them, between the head of the screw and the nut, the shoulder of the inner eccentric ring, the shoulder of the outer eccentric ring, the accessories and the skin, the upper spar and the lateral bucket are sandwiched in sequence.

[0032] In each of these embodiments, due to the reduced tolerances between the holes, the outer and inner surfaces of the eccentric rings, and the flat areas of the screws, the assembly can eliminate the use of pull studs while ensuring the bolt's reaction to shear forces contained in the XY plane.

[0033] Advantageously, the diameter of the first hole is adapted to the diameter of the flat area of ​​the screw, so as to provide a tight fit.

[0034] Advantageously, the inner eccentric ring is threaded onto the flat area of ​​the shank of the screw with a radially tight fit, while the outer eccentric ring is threaded onto the inner eccentric ring with a radially tight fit.

[0035] According to one embodiment, each rotation prevention system comprises a grooved washer fastened to the lateral bucket, that is to say to the fitting respectively, the shoulder of the outer eccentric ring being grooved on each of its faces, while the shoulder of the inner eccentric ring is grooved on the face in contact with the shoulder of the outer eccentric ring.

[0036] According to a particular embodiment, each rotation prevention system comprises a plate fastened to the lateral bucket, that is to say respectively to the fitting, the outer periphery of the shoulder of each eccentric ring being grooved and, for each shoulder, the plate having a grooved section cooperating with the groove of said shoulder in order to prevent its rotation.

[0037] The invention also proposes an aircraft having at least one assembly according to one of the aforementioned variants.

[0038] The present invention also provides a method for assembling the assembly according to the first embodiment, wherein the method comprises:

[0039] - a placement step during which the pylon is positioned relative to the wing by visually aligning the eight pairs of first and second holes,

[0040] For each pair of first and second holes:

[0041] a presentation step during which the fastening assembly is presented at the aforementioned pair of holes by inserting the end of the shank of the screw into the second hole and then into the first hole,

[0042] a positioning step during which the end of the cylindrical body of the outer eccentric ring is brought to the entrance of the second hole of the lateral bucket without entering the hole,

[0043] - an adjustment step during which the inner and outer eccentric rings are manipulated in rotation about their axes so as to align the outer surface of the barrel of the outer eccentric ring with the second hole of the lateral bucket while keeping the screw in position relative to the first hole,

[0044] - an advancement step during which the fastening assembly is pushed into the second hole,

[0045] a rotation prevention step during which the rotation prevention system prevents the eccentric rings from rotating, and

[0046] - Tightening step, during which the nut is tightened onto the shank of the screw.

[0047] The present invention also provides a method for assembling the assembly according to the second embodiment, wherein the method comprises:

[0048] - a placement step during which the pylon is positioned relative to the wing by visually aligning the eight pairs of first and second holes,

[0049] For each pair of first and second holes:

[0050] a presentation step during which the fastening assembly is presented at the aforementioned pair of holes by inserting the end of the shank of the screw into the second hole and then into the first hole,

[0051] - a positioning step during which the end of the barrel of the outer eccentric ring is brought to the entrance of the second hole of the fitting without entering this hole,

[0052] - an adjustment step during which the inner and outer eccentric rings are manipulated in rotation about their axes so as to align the outer surface of the barrel of the outer eccentric ring with the second hole of the fitting while simultaneously maintaining the screw in position relative to the first hole,

[0053] - an advancement step during which the fastening assembly is pushed into the second hole,

[0054] a rotation prevention step during which the rotation prevention system prevents the eccentric rings from rotating, and

[0055] - Tightening step, during which the nut is tightened onto the shank of the screw. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] The above and other features of the present invention will become more apparent upon reading the following description of exemplary embodiments given with reference to the accompanying drawings, in which:

[0057] Figure 1 is a side view of an aircraft having an assembly of the present invention,

[0058] Figure 2 A perspective view showing the components of a first embodiment of the invention in side view,

[0059] Figure 3 The first embodiment of the present invention, Figure 2 Cross-sectional view on plane III in,

[0060] Figure 4 is with Figure 3 Similar views showing alternative means of preventing rotation,

[0061] Figure 5is an alternative means of preventing rotation along Figure 4 The view of arrow V in

[0062] Figure 6 is similar to Figure 3 , which is a second embodiment of the present invention,

[0063] Figure 7 is an exploded perspective view of the fastening assembly, and

[0064] Figure 8 is a top view of a prior art assembly. DETAILED DESCRIPTION

[0065] Figure 1 An aircraft 100 is shown having a fuselage 102 to each side of which are fastened wings 104 carrying at least one jet engine 150 , in particular a turbofan engine.

[0066] Jet engine 150 is secured beneath wing 104 via pylon 106 .

[0067] In the following description, and by convention, the X direction is the longitudinal direction of the jet engine 150, oriented toward the front of the aircraft 100; the Y direction is the lateral direction, which is horizontal when the aircraft is on the ground; and the Z direction is the vertical direction, with these three directions X, Y and Z being orthogonal to each other.

[0068] Furthermore, the terms "forward" and "rearward" should be considered relative to the direction of forward motion of the aircraft 100 when the jet engine 150 is operating, which is indicated by arrow F in FIG. Figure 1 It is schematically shown in FIG.

[0069] Figure 2 and Figure 3 An assembly 200 of a first embodiment of the present invention is shown.

[0070] The assembly 200 of the first embodiment of the present invention comprises a pylon 106 having an upper spar 202 and two side panels 204, one port side panel and one starboard side panel.

[0071] The assembly 200 also comprises a wing 104 having a skin 210 forming the aerodynamic surface of the wing 104, within which longitudinal spars 206a-b and fittings 208 are arranged, wherein each fitting spar and fitting is in the form of a bracket in this case. The skin 210 is fastened to the longitudinal spars 206a-b, while the fittings 208 are arranged against the longitudinal spars 206a-b and each fitting 208 is fastened to the longitudinal spars 206a-b and to the inside of the skin 210.

[0072] The pylon 106 also has four lateral scoops 212a-b, each of which is fastened on the outside to a side panel 204 below the upper spar 202. There are two lateral scoops 212a-b per side, i.e., per side panel 204, and for each side panel 204 there is one lateral scoop 212b at the rear of the tower 106 and a lateral scoop 212a approximately in the middle of the pylon 106.

[0073] In this case, each lateral scoop 212a-b is in the form of a bracket and has an upper contact surface carried under the upper spar 202 and a lateral contact surface carried against the side panel 204, the lateral contact surface being fastened thereto, for example by bolts, spot welds or the like.

[0074] Figure 3 A section extending in a plane YZ perpendicular to the longitudinal direction X is shown.

[0075] The assembly 200 has two fastening assemblies 250 for each lateral scoop 212a - b , wherein each fastening assembly 250 fastens the lateral scoop 212a - b to one of the fittings 208 through the upper spar 202 and the skin 210 .

[0076] For each fastening assembly 250, the skin 210 on the wing side and the fitting 208 each have a first hole 251. The first hole 251 of the skin 210 and the first hole 251 of the fitting 208 extend mutually and are therefore coaxial.

[0077] In the same way, the lateral scoops 212a-b on the pylon side and the upper spar 202 each have a second hole 253. The second hole 253 of the upper spar 202 and the second hole 253 of the lateral scoops 212a-b extend mutually and are therefore coaxial.

[0078] Thus, there are eight pairs of first holes 251 and the same number of second holes 253. The first holes 251 in the skin 210 and the first holes 251 in the fitting 208 have the same diameter. The second holes 253 in the upper spar 202 and the second holes 253 in the lateral scoops 212a-b have the same diameter. Each pair of second holes 253 on the pylon side is aligned with a pair of first holes 251 on the wing side, and the diameter of the second holes 253 is larger than the diameter of the first holes 251.

[0079] Each fastening assembly 250 includes a bolt 252 with a screw 254 and a nut 255, two eccentric rings 256 and 258, and a rotation prevention system 260 that prevents the eccentric rings 256 and 258 from rotating before tightening the screw 254 and nut 255. To this end, the shank of the screw 254 has a flat area on one side of its head and a threaded area opposite its head. The screw 254 is sized so that the flat area extends along the first hole 251 and the second hole 253, while the threaded area extends beyond the first hole 251.

[0080] Thus, the fastening assembly 250 has an inner eccentric ring 256 and an outer eccentric ring 258 .

[0081] Each eccentric ring 256, 258 has a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution that are offset relative to each other, ie, their axes are parallel but separated.

[0082] The inner eccentric ring 256 is threaded onto the flat area of ​​the shank of the screw 254 and is a tight fit in the radial direction, while the outer eccentric ring 258 is threaded onto the inner eccentric ring 256 and is a tight fit in the radial direction. The two eccentric rings 256 and 258 are received in the second hole 253 and are "installed with a tight fit" in terms of diameter. The shank of the screw 254 is passed through the first hole 251 and the second hole 253, thereby screwing the threaded area of ​​the screw 254 into the nut 255.

[0083] It should be noted that the concept of a "tight fit" described above consists in having a connection with a pin and a hole of the same nominal diameter, with a clearance reduced to its minimum to allow their assembly. This type of "tight" fit is known to those skilled in the art as one that is capable of transmitting shear forces through contact without the risk of slippage and deterioration of the connection. For example, this type of tight fit is of the H7g6 type.

[0084] The shoulders of the eccentric rings 256 and 258 are both clamped between the lower bearing surfaces of the lateral buckets 212 a - b and the bearing surface below the head of the screw 254 .

[0085] Therefore, by rotating each eccentric ring 256, 258 independently, it is possible to find an adjustment combination that makes the axis of the first hole 251 coaxial with the axis of the inner surface of the cylinder of the inner eccentric ring 256, so that the screw 254 is perfectly aligned with this axis on the wing side, and to adjust the position of the outer surface of the cylinder of the outer eccentric ring 258 relative to the second hole 253 on the pylon side.

[0086] The diameter of the first hole 251 is adapted to the diameter of the flat area of ​​the screw 254 so as to provide a tight fit, for example of the H7g6 type.

[0087] The clearance between each screw 254 and the hole surrounding it is reduced, and the shear forces contained in the XY plane can be reacted by each bolt 252 of each fastener assembly 250, eliminating the need to place pull studs in place.

[0088] exist Figure 3 In the embodiment of the invention shown, between the head of the screw 254 and the nut 255, the shoulder of the inner eccentric ring 256, the shoulder of the outer eccentric ring 258, the lateral buckets 212a-b, the upper spar 202, the skin 210 and the fitting 208 are sandwiched in sequence.

[0089] exist Figure 3 In the embodiment of the invention shown, additional washers have been put in place at the head of the screw 254 and the nut 255.

[0090] exist Figure 3 and Figure 7 In the embodiment shown (which is an exploded view of the fastener assembly 250), each rotation prevention system 260 has a striped washer 262 that is fastened to the lateral buckets 212a-b around the second hole 253 and against the face opposite the upper spar 202. In this case, the striped washer 262 is located between the lateral buckets 212a-b and the shoulder of the outer eccentric ring 258.

[0091] The shoulder of the outer eccentric ring 258 is also ribbed on each face thereof, and the shoulder of the inner eccentric ring 256 is also ribbed on the face that contacts the shoulder of the outer eccentric ring 258. Pushing the eccentric rings 256 and 258 into the second hole 253 causes the various ribs to contact and interlock, and prevent rotation of the eccentric rings 256, 258.

[0092] exist Figure 4 and Figure 5 In the embodiment of , each rotation prevention system 460 has a plate 462 fastened to the lateral buckets 212a-b, against the face opposite the upper spar 202. In this case, the fastening is ensured by screws.

[0093] The outer periphery of the shoulder of each eccentric ring 256, 258 is grooved, and for each shoulder, the plate 462 has a grooved section that is used to cooperate with the groove of the shoulder to prevent its rotation.

[0094] Thus, after the eccentric rings 256 and 258 have been placed in position and adjusted, the plate 462 is secured, thereby immobilizing the eccentric rings 256 and 258, and the screws 254 and nuts 255 can then be tightened, thereby finalizing the assembly.

[0095] A method for assembling an assembly 200, comprising:

[0096] a placement step during which the pylon 106 is positioned relative to the wing 104 by visually aligning the eight pairs of first holes 251 and second holes 253 ,

[0097] For each pair of first hole 251 and second hole 253:

[0098] a presentation step during which the fastening assembly 250 is presented at the pair of holes by inserting the end of the shank of the screw 254 into the second hole 253 and then into the first hole 251, the screw 254 being fixed in place concentrically with respect to the axis of the first hole 251 due to the tight fit of the first hole 251,

[0099] a positioning step during which the end of the cylindrical body of the outer eccentric ring 258 is brought to the entrance of the second hole 253 of the lateral bucket 212a-b without entering the same hole,

[0100] an adjustment step during which the inner eccentric ring 256 and the outer eccentric ring 258 are manipulated in rotation about their axes so as to align the outer surface of the barrel of the outer eccentric ring 258 with the second holes 253 of the lateral buckets 212 a - b while keeping the screws 254 in position relative to the first holes 251,

[0101] - an advancement step, during which the fastening assembly 250 is pushed into the second hole 253,

[0102] a rotation prevention step during which the rotation prevention system 260 prevents the eccentric rings 256 and 258 from rotating, and

[0103] A tightening step, during which the nut 255 is tightened onto the shank of the screw 254 .

[0104] During the presentation step, both the inner eccentric ring 256 and the outer eccentric ring 258 , ie in this case an additional washer, are threaded onto the shank of the screw 254 before the shank of the screw 254 is inserted.

[0105] Preferably, the adjustment of the inner eccentric ring 256 and the adjustment of the outer eccentric ring 258 are performed with pliers that grip the shoulders. Figure 5 In the embodiment shown, the grooves in the shoulder make it easier for the pliers to engage the shoulder. Figure 3 In the embodiment shown, each groove may be replaced by a polygonal, hexagonal, or other double hexagonal shape.

[0106] Figure 6 A second embodiment is shown which differs from the first embodiment in that the orientation of the assembly 600 is reversed.

[0107] The assembly 600 has two fastening assemblies 650 for each lateral scoop 212a - b , wherein each fastening assembly 650 fastens the lateral scoop 212a - b to one of the fittings 208 through the upper spar 202 and the skin 210 .

[0108] For each fastening assembly 650, the lateral scoops 212a-b on the pylon side and the upper spar 202 each have a first hole 651. The first holes 651 of the upper spar 202 and the first holes 651 of the lateral scoops 212a-b extend mutually and are therefore coaxial.

[0109] In the same manner, the skin 210 and the fitting 208 on the wing side each have a second hole 653. The second hole 653 of the skin 210 and the second hole 653 of the fitting 208 extend mutually and are therefore coaxial.

[0110] Thus, there are eight pairs of first holes 651 and the same number of second holes 653. The first holes 651 in the upper spar 202 and the first holes 651 in the lateral buckets 212a-b have the same diameter. The second holes 653 in the skin 210 and the second holes 653 in the fittings 208 have the same diameter. Each pair of second holes 653 on the wing side is aligned with a pair of first holes 651 on the pylon side, and the diameter of the second holes 653 is larger than the diameter of the first holes 651.

[0111] Each fastening assembly 650 includes a bolt 252 with a screw 254 and a nut 255, two eccentric rings 256 and 258, and a rotation prevention system 260 that prevents rotation of the eccentric rings 256 and 258. To this end, the shank of the screw 254 has a flat area on one side of its head and a threaded area opposite its head. The screw 254 is sized so that the flat area extends along the first hole 651 and the second hole 653, while the threaded area extends beyond the first hole 651.

[0112] Thus, the fastening assembly 650 has an inner eccentric ring 256 and an outer eccentric ring 258 .

[0113] Each eccentric ring 256, 258 has a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution that are offset relative to each other, ie, their axes are parallel but separated.

[0114] Inner eccentric ring 256 is threaded onto the flat area of ​​the shank of screw 254 and is a tight fit in the radial direction, while outer eccentric ring 258 is threaded onto inner eccentric ring 256 and is a tight fit in the radial direction. Both eccentric rings 256 and 258 are received in second hole 653 and are mounted with a tight fit in the radial direction. The shank of screw 254 is passed through first hole 651 and second hole 653, thereby threading the threaded area of ​​screw 254 into nut 255.

[0115] It should be noted that the concept of a "tight fit" described above consists in having a connection with a pin and hole of the same nominal diameter, with a clearance reduced to its minimum to allow their assembly. This type of "tight fit" is known to those skilled in the art as being able to transmit shear forces through contact without the risk of slippage and deterioration of the connection. For example, this type of tight fit is of the H7g6 type.

[0116] The shoulders of the eccentric rings 256 and 258 are both clamped between the bearing surface of the fitting 208 and the bearing surface under the head of the screw 254.

[0117] Therefore, by rotating each eccentric ring 256, 258 independently, it is possible to find an adjustment combination that makes the axis of the first hole 651 on the pylon side coaxial with the axis of the inner surface of the cylinder of the inner eccentric ring 256, so that the screw 254 is perfectly aligned with this axis, and to adjust the position of the outer surface of the cylinder of the outer eccentric ring 258 relative to the second hole 653 on the wing side.

[0118] The diameter of the first hole 651 is adapted to the diameter of the flat area of ​​the screw 254 so as to provide a tight fit, for example of the H7g6 type.

[0119] The clearance between each screw 254 and the hole surrounding it is reduced, and the shear forces contained in the XY plane can be reacted by each bolt 250 of each fastener assembly 650, eliminating the need to place pull studs in place.

[0120] exist Figure 6 In the embodiment of the invention shown, between the head of the screw 254 and the nut 255, the shoulder of the inner eccentric ring 256, the shoulder of the outer eccentric ring 258, the fitting 208, the skin 210, the upper spar 202 and the lateral buckets 212a-b are sandwiched in sequence.

[0121] exist Figure 6 In the embodiment of the invention shown, additional washers have been put in place at the head of the screw 254 and the nut 255.

[0122] exist Figure 6 In the embodiment of FIG. 5 , the striped washer 262 of the rotation prevention system 260 is secured to the fitting 208 around the second hole 653 and against the face opposite the skin 210. In this case, the striped washer 262 is located between the fitting 208 and the shoulder of the outer eccentric ring 258. Additional stripes may also be present on the shoulder of the inner eccentric ring 256 and the shoulder of the outer eccentric ring 258.

[0123] Figure 4 and Figure 5 The blocking system in may also be implemented by fastening the plate 462 to the fitting 208 against the face opposite the skin 210 .

[0124] A method for assembling an assembly 600, comprising:

[0125] a placement step during which the pylon 106 is positioned relative to the wing 104 by visually aligning the eight pairs of first holes 651 and second holes 653 ,

[0126] For each pair of first hole 651 and second hole 653:

[0127] a presentation step during which the fastening assembly 651 is presented at the pair of holes by inserting the end of the shank of the screw 254 into the second hole 653 and then into the first hole 650, the screw 254 being fixed in place concentrically with respect to the axis of the first hole 651 due to the tight fit of the first hole 651,

[0128] a positioning step during which the end of the barrel of the outer eccentric ring 258 is brought to the entrance of the second hole 653 of the fitting 208 without entering the same hole,

[0129] an adjustment step during which the inner eccentric ring 256 and the outer eccentric ring 258 are manipulated in rotation about their axes so as to align the outer surface of the barrel of the outer eccentric ring 258 with the second hole 653 of the fitting 208 while keeping the screw 254 in position relative to the first hole 651,

[0130] - an advancement step, during which the fastening assembly 650 is pushed into the second hole 653,

[0131] a rotation prevention step during which the rotation prevention system 260 prevents the eccentric rings 256 and 258 from rotating, and

[0132] A tightening step, during which the nut 255 is tightened onto the shank of the screw 254 .

[0133] During the presentation step, the inner eccentric ring 256 and the outer eccentric ring 258 , ie in this case an additional washer, are threadedly connected to the screw 254 before the shaft of the screw 254 is inserted.

Claims

1. An assembly (200) for an aircraft (100), the assembly (200) comprising: - a pylon (106) having an upper spar (202), two side panels (204) and four lateral scoops (212a-b), the side panels extending vertically below the upper spar (202), each of the lateral scoops being fastened on the outside against the side panels (204) below the upper spar (202), each of the side panels (204) having two lateral scoops (212a-b), one lateral scoop (212b) being at the rear of the pylon (106) and one lateral scoop (212a) being approximately in the middle of the pylon (106), - a wing (104) having a skin (210), longitudinal spars (206a-b) and fittings (208) fastened to the inner side of the skin (210) and the longitudinal spars (206a-b), and - For each of said lateral buckets (212a-b), there are two fastening assemblies (250), wherein, For each of the fastening assemblies (250), the skin (210) and the fitting (208) each have a first hole (251) extending mutually, and the upper spar (202) and the lateral buckets (212a-b) each have a second hole (253) extending mutually, Wherein, each of the fastening components (250) has: a screw (254) passing through said first hole (251) and said second hole (253), said screw having a flat area on one side of its head and a threaded area opposite its head, - a nut (255) screwed onto the threaded zone of the screw (254), an inner eccentric ring (256) having a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution offset relative to each other, wherein the inner eccentric ring (256) is threaded onto the flat area of ​​the screw (254), - an outer eccentric ring (258) having a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution offset relative to each other, wherein the outer eccentric ring (258) is threadedly connected to the inner eccentric ring (256), wherein the two eccentric rings (256, 258) are received and mounted in the second hole (253) with a radially tight fit, and - a rotation prevention system (260, 460) preventing the eccentric ring (256, 258) from rotating, Wherein, between the head of the screw (254) and the nut (255), the shoulder of the inner eccentric ring (256), the shoulder of the outer eccentric ring (258), the lateral bucket-shaped portion (212a-b), the upper wing beam (202), the skin (210) and the accessory (208) are successively clamped.

2. An assembly (600) for an aircraft (100), the assembly (600) comprising: - a pylon (106) having an upper spar (202), two side panels (204) and four lateral scoops (212a-b), the side panels extending vertically below the upper spar (202), each lateral scoop being fastened on the outside against the side panel (204) below the upper spar (202), each side panel (204) having two lateral scoops (212a-b), one lateral scoop (212b) being at the rear of the pylon (106) and one lateral scoop (212a) being approximately in the middle of the pylon (106), - a wing (104) having a skin (210), longitudinal spars (206a-b) and fittings (208) fastened to the inner side of the skin (210) and the longitudinal spars (206a-b), and - for each of the lateral scoops (212a-b), there are two fastening assemblies (650), wherein, for each of the fastening assemblies (650), the upper spar (202) and the lateral scoops (212a-b) each have a first hole (651) extending mutually, and the skin (210) and the fitting (208) each have a second hole (653) extending mutually, Wherein, each of the fastening components (650) has: a screw (254) passing through said first hole (651) and said second hole (653), said screw having a flat area on one side of its head and a threaded area opposite its head, - a nut (255) screwed onto the threaded zone of the screw (254), an inner eccentric ring (256) having a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution offset relative to each other, wherein the inner eccentric ring (256) is threaded onto the flat area of ​​the screw (254), - an outer eccentric ring (258) having a barrel and a shoulder, wherein the inner surface of the barrel and the outer surface of the barrel are cylinders of revolution offset relative to each other, wherein the outer eccentric ring (258) is threadedly connected to the inner eccentric ring (256), wherein the two eccentric rings (256, 258) are received and mounted in the second hole (653) with a radially tight fit, and - a rotation prevention system (260, 460) preventing the eccentric ring (256, 258) from rotating, Wherein, between the head of the screw (254) and the nut (255), the shoulder of the inner eccentric ring (256), the shoulder of the outer eccentric ring (258), the accessory (208), the skin (210), the upper wing spar (202) and the lateral bucket-shaped portion (212a-b) are successively clamped.

3. The assembly (200, 600) according to claim 1 or 2, characterized in that The diameter of the first hole (251, 651) is adapted to the diameter of the flat area of ​​the screw (254) to achieve a tight fit.

4. The assembly (200, 600) according to claim 1 or 2, characterized in that The inner eccentric ring (256) is threadedly connected to the flat area of ​​the rod of the screw (254) and is radially tight fit, and wherein the outer eccentric ring (258) is threadedly connected to the inner eccentric ring (256) and is radially tight fit.

5. The assembly (200, 600) according to claim 1 or 2, characterized in that Each of the rotation prevention systems (260) has a striped washer (262) fastened to the lateral buckets (212a-b), i.e., respectively, to the fitting (208), wherein the shoulder of the outer eccentric ring (258) is striped on each of its faces, and wherein the shoulder of the inner eccentric ring (256) is striped on the face in contact with the shoulder of the outer eccentric ring (258).

6. The assembly (200, 600) according to claim 1 or 2, characterized in that Each of the rotation prevention systems (460) comprises a plate (462) fastened to the lateral buckets (212a-b), i.e. respectively to the fitting (208), wherein the outer periphery of the shoulder of each of the eccentric rings (256, 258) is grooved and, for each shoulder, the plate (462) comprises a grooved section that cooperates with the groove of the shoulder to prevent rotation of the shoulder.

7. An aircraft (100) having at least one assembly according to claim 1 or 2.

8. A method for assembling the assembly (200) according to claim 1, characterized in that The method comprises: - a placement step during which the pylon (106) is positioned relative to the wing (104) by visually aligning eight pairs of first holes (251) and second holes (253), For each pair of the first hole (251) and the second hole (253): - a presentation step during which the fastening assembly (250) is presented at a pair of said holes by inserting the end of the shank of said screw (254) into said second hole (253) and then into said first hole (251), - a positioning step, during which the end of the cylindrical body of the outer eccentric ring (258) is brought to the entrance of the second hole (253) of the lateral bucket-shaped portion (212a-b) without entering the second hole, - an adjustment step during which the inner eccentric ring (256) and the outer eccentric ring (258) are manipulated to rotate about their axes so as to align the outer surface of the cylinder of the outer eccentric ring (258) with the second hole (253) of the lateral bucket (212a-b) while keeping the screw (254) in position relative to the first hole (251), - an advancement step during which the fastening assembly (250) is pushed into the second hole (253), - a rotation preventing step during which the rotation preventing system (260, 460) prevents the eccentric ring (256, 258) from rotating, and - a tightening step during which the nut ( 255 ) is tightened onto the shank of the screw ( 254 ).

9. A method for assembling an assembly (200) according to claim 2, characterized in that The method comprises: - a placement step during which the pylon (106) is positioned relative to the wing (104) by visually aligning eight pairs of first holes (651) and second holes (653), For each pair of the first hole (651) and the second hole (653): - a presentation step during which the fastening assembly (650) is presented at a pair of said holes by inserting the end of the shank of said screw (254) into said second hole (653) and then into said first hole (651), - a positioning step during which the end of the barrel of the outer eccentric ring (258) is brought to the entrance of the second hole (653) of the fitting (208) without entering the second hole, - an adjustment step during which the inner eccentric ring (256) and the outer eccentric ring (258) are manipulated in rotation about their axes so as to align the outer surface of the barrel of the outer eccentric ring (258) with the second hole (653) of the fitting (208) while keeping the screw (254) in position relative to the first hole (651), - an advancement step, during which the fastening assembly (650) is pushed into the second hole (653), - a rotation preventing step during which the rotation preventing system (260, 460) prevents the eccentric ring (256, 258) from rotating, and - a tightening step during which the nut ( 255 ) is tightened onto the shank of the screw ( 254 ).

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