Abstract: A device for attaching an aircraft engine including a thrust force take-up device that includes a main fitting to be fixed to an engine mounting beam fixed to a box structure, an additional fitting fixed to the main fitting, and two load reacting link rods connected to the main fitting by a balance beam, each of the link rods being connected to the balance beam by a first longitudinal end by a first mechanical connection that has at least one axis of rotation, each of the link rods being connected to the additional fitting by a second longitudinal end by a second mechanical connection that has at least one axis of rotation, the second mechanical connection having play, the first and second mechanical connections having at least one axis of rotation in common.

Abstract: A full time lean air fuel mixture running spark ignited air cooled aircraft piston engine. In one embodiment, a drop-in substitution is provided for an equivalent make, model, and engine size, wherein the new, rebuilt, or reconfigured engine provides as much or more horsepower when compared to the original engine, but runs at a lean air fuel ratio condition during normal operating modes, including takeoff, climb, and cruise, thus saving significantly on fuel. In yet another embodiment, a drop-in substitution having a somewhat larger cylinder displacement volume may be provided to attain equivalent or enhanced maximum horsepower while operating at lean air fuel ratios. Enhanced engine life may be anticipated, since cylinder head temperatures (CHTs) may be reduced, compared to engines using rich air fuel ratios for climb and cruise conditions. Aircraft using such engines are also disclosed.

Abstract: A load-bearing structure, such as a pylon or strut, having a monolithic tubular-shaped first central structure composed of composite material and a plurality of metal fittings for supporting an engine on an airframe structure of an aircraft, such as a wing. Most of the fittings are integrated into the load-bearing structure through bonding. The metal fittings carry the high bearing loads that are transmitted into the pylon at the engine-pylon and wing-pylon interfaces. The load-bearing structure may also include a second central structure of a tubular shape composed of composite material and integrated with one end portion of the first central structure by bonding and/or mechanical fasteners.

Abstract: A pylon for fixing an aircraft engine having unducted pusher propellers, the pylon ensuring the fixation of a propulsive system on the boattail of the aircraft, the pylon having a trailing edge, with an upper face and a lower face, for an airflow encountered by the pylon, wherein at least one of the two faces of the upper face and the lower face of the trailing edge is inclinable, at least in part.

Abstract: A system for attaching an engine to the structure of an aircraft, such as a sail wing aircraft is disclosed. The system includes an upper beam which is firmly fixed at its front end to a first frame mounted on the aircraft structure, and firmly fixed at its median part to a second frame located to the rear of the first frame. The engine is hooked beneath the upper beam. The system is orientated in relation to a longitudinal axis X, a transverse axis Y and a vertical axis Z. Two front engine attachment points are arranged symmetrically on either side of the vertical median plane of the engine. The front attachment points include a shaft which is inclined relative to the Y-direction and to the Z-direction so that they bear the forces along the longitudinal direction and forces which are inclined relative to the Z-direction and Y-direction.

Abstract: An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage.

Abstract: A securing mast for securing an engine to the wing of an aircraft, wherein the device includes two fasteners, a first end of each fastener being secured to the engine and the second end of each fastener being secured to the wing, wherein the fasteners include hinged junction means capable of modifying the geometry of the aforementioned fasteners in order to modify a distance between the engine and the wing.

Abstract: A wing arrangement of an aircraft has a wing and at least one pylon for suspending an engine below the wing. The wing has a leading edge with a high-lift device, which is able to move between a deployed position in which the high-lift device projects forward of the leading edge, and which is interrupted in a forward intermediate region of the wing located at the leading edge, the pylon having a forward edge extending forward of the leading edge of the wing between a forward upper portion connected to the wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine. An element of narrow elongate shape protrudes longitudinally from the forward edge and, during flight at a high angle of attack of the aircraft, generates a vortex of aerodynamic flow that is propagated toward the forward intermediate region above the wing.

Abstract: A device for attaching an aircraft engine including a rigid structure forming a structure box, and a device for absorbing thrust loads including a main fitting fixedly mounted on one of the spars forming the structure box, by a fixing mechanism. The fixing mechanism includes a fixing peg mounted on the spar and including a main portion located on the outside relatively to the box, the fitting being crossed by the portion of the peg and pressed against the spar by a bell-shaped supporting washer surrounding the main portion and stressed by a screw crossing it, the latter being screwed into a barrel nut housed in a bore made within the main portion.

Abstract: An arrangement for an aircraft includes a fuselage, a wing, and a propulsor. The wing may have a wing upper surface, a rear spar and a wing trailing edge. The propulsor may include at least one rotor having a rotor diameter and a rotor axis. The propulsor may be mounted such that the rotor is located longitudinally between the rear spar and the wing trailing edge. The propulsor may also be mounted such that a lowest point of the rotor diameter is located vertically above the wing upper surface.

Abstract: An aircraft including a wing and a pylon, wherein the pylon provides an airfoil inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series LEARJET® is provided. The improvement includes an increased distance between a leading edge of a wing and an intake of an engine of the aircraft, which reduces drag and increases lift for improved flight dynamics of the aircraft. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamics of the aircraft. The method includes steps of removing an original engine from an original pylon, removing the original pylon from the fuselage of the aircraft, and mounting a new pylon in a new location adjacent to the fuselage, wherein the new location is aft of the original location.

Abstract: A tail structure for an aircraft or spacecraft, which adjoins a fuselage section of the aircraft or spacecraft, includes a support construction for supporting at least one craft component, and a bulkhead unit intended for the pressure-tight sealing of the fuselage section and able to be coupled both to the support construction and to the fuselage section so as to form a force flow path between the at least one craft component and the fuselage section.

Abstract: An assembly for an aircraft including: a mechanism attaching a primary structure of an attachment strut to a wing, forming an isostatic system; an attachment housed in a leading edge of the wing and configured to only take up forces exerted along the transverse and longitudinal directions; and an attachment including a connecting rod extending rearwardly, of which one end is connected to the primary structure and the other end is connected to the wing element, the connecting rod being offset along the vertical direction of the attachment.

Abstract: An engine assembly for an aircraft including a dual-flow turbomachine and an attachment strut. The turbomachine includes a structural case extending downstream of the hub of an intermediate casing, the case contributing to the internal radial delimitation of a passage for a secondary flow of the turbomachine. Also, the primary structure includes a structural case, assembled on the structural case and positioned directly downstream of the structural case such that it also contributes to the internal radial delimitation of the passage for the secondary flow. The primary structure also includes an offset structure positioned in the passage, and configured to connect the case to an element of the aircraft. The structural case also includes a thrust reversal system.

Abstract: An aircraft pylon is disclosed, the pylon including a strut, a modular fluid containment structure and a modular firewall. The strut presents an open structure and connects an aircraft external element to the aircraft. The fluid containment structure is associated with a fluid transfer component, wherein the fluid containment structure contains escaped fluid from the fluid transfer component and channels the escaped fluid away from the aircraft. Both the fluid containment component and the firewall are modular and separable from the strut.

Abstract: A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a vertical load, a side load, and a torque load of the gas turbine engine.

Abstract: The disclosed embodiments relates to a jet engine for an aircraft, characterized in that it bears at least one stabilizer, the stabilizer being fastened on the rigid structure of said jet engine so as to form a one-piece assembly. The jet engine can also bear one or more auxiliary devices required for the operation of the jet engine. The disclosed embodiments also relates to an aircraft provided with such a jet engine, and to a method of mounting such a jet engine on an aircraft.

Abstract: An aircraft assembly including a wing element and an attachment pylon of a turboengine, including a rigid structure forming a caisson defined externally by a first longeron, a second longeron, and two lateral panels. The assembly also includes an attachment mechanism of the structure on the wing element, fitted with two front attachments, each including two first fittings solid with the associated lateral panel. For each front attachment, the two first fittings are arranged respectively on either side of their associated lateral panel.

Abstract: An aircraft engine assembly including an engine, an engine mounting structure, and a nacelle surrounding the engine and including an air intake and fan cowls. The assembly further includes a cradle supporting the fan cowls, fixedly mounted on the mounting structure or else on an entity including a fan case and the air intake attached to the case. The engine assembly further includes a junction aerodynamic fairing including a first mounting mechanism mounted on the cradle, and including a second mounting mechanism mounted on the other of the elements from among the mounting structure and the entity.

Abstract: A support structure is provided for attaching a gas turbine engine to a pylon. The gas turbine engine has an engine casing surrounding an engine core, and the pylon has first and second attachment positions, the second attachment position being forward of the first attachment position relative to the working gas flow direction through the engine. The support structure has three elongate members joined to form a triangular frame encircling the engine casing. A first vertex of the triangular frame attaches to the pylon via a first attachment arrangement at the first attachment position. Two thrust struts respectively extend from the other two vertices of the triangular frame and attach to the pylon via a second attachment arrangement at the second attachment position. Three engine connection formations extend from the respective vertices of the triangular frame to positions on the engine casing to connect the support structure to the engine casing.

Abstract: A suspension for an engine on an aircraft strut, the suspension comprising a beam with a plate provided with fixing means for fixing to said strut and a suspension arch linked to the beam by at least one pivot link whose axis is intended to be parallel to the axis of the engine, the suspension arch having, at each of its ends, fixing means for fixing to a case of the engine.

Abstract: An engine mounting apparatus that includes thrust struts, a balance yoke, and primary and secondary mount blocks. The thrust struts are connected to the balance yoke and the primary mount block has at least one thrust load connection connectable to the balance yoke for transferring thrust loads from an engine during normal operation of the engine mounting apparatus. The engine mounting apparatus is characterized in that the secondary mount block is connected to the balance yoke via at least one thrust load catcher connection, the at least one thrust load catcher connection being arranged to be unloaded during normal operation of the engine mounting arrangement and to transfer the thrust loads from the engine in the event of a failure condition of the primary mount block.

Abstract: The present invention relates to an aircraft assembly (200) comprising a wing (2) and an engine attachment pylon (4) fixed to the wing by means of attachment means comprising a first and a second front wing system cleat (109, 109) connecting a rigid structure (108) of the attachment pylon and a front longeron (201) of the wing. The first front wing system cleat (109) comprises a first shearing pin (202) oriented in the transversal direction (Y) to ensure take-up of forces exerted in the longitudinal (X) and vertical (Z) directions of the pylon, and the second front wing system cleat (109) comprises a second shearing pin (208) oriented in the longitudinal direction (X) to ensure take-up of forces exerted in the transversal (Y) and vertical (Z) directions of the pylon.

Abstract: The present invention relates to a take-up device for thrust forces (14) for an aircraft engine attachment pylon (4), comprising a first fitting (194) attached to a rigid structure (108) of the attachment pylon, and two lateral connecting rods (14a) for take-up of thrust forces. It also comprises an axis system (190) bearing three first ball joint organs (192a, 196a) arranged along the latter and belonging respectively to a primary ball joint (192) and two secondary ball joints (196) arranged on either side of the primary ball joint, the first fitting (194) integrating a second ball joint organ (192b) cooperating with the first organ (192a) of the primary ball joint (192), and an end of each of the two connecting rods (14a) integrating a second ball joint organ (196b) cooperating respectively with the first organs (196a) of the two secondary ball joints (196).

Abstract: An attachment device for an aircraft engine that includes a rigid structure and an attachment mechanism of the engine to the rigid structure. The attachment mechanism includes a device reacting to thrust forces generated by the engine, the reacting device including two link rods mechanically connected to a balance beam at a rear end by a first mechanical connection, a main fitting fixed to the rigid structure to which the balance beam is mechanically connected, and two additional fittings fixed to the rigid structure to which the link rods are mechanically connected with play. The mechanical connections between the balance beam and the main fitting and between the link rods and the additional fittings each include a pin orthogonal to a mid-plane of transmission of the forces.

Abstract: A turbojet suspended from an aircraft mast is disclosed. The turbojet includes a front fan, an intermediate casing downstream of the fan with an outer shroud and a hub connected together by radial arms, and an exhaust casing with an outer shroud, the two casings being aligned on one and the same axis XX. The mast includes a structural strut assembly of elongated shape. The strut assembly is attached upstream rigidly to the outer shroud of the intermediate casing by a front attachment including a device for transmitting the axial and lateral forces and downstream by a rear attachment to the exhaust casing.

Abstract: A turbomachine fan duct is disclosed. The fan duct includes two coaxial cylindrical walls, these being an internal wall and an external wall, respectively. The internal wall includes a framework to which panels are removably attached, and the external wall includes a single support structure with openings closed by removable panels. The openings in the external wall have dimensions that allow the panels of the internal wall to pass and allow these panels to be fitted onto and removed from the framework of the internal wall.

Abstract: The aircraft exhaust engine nozzle system includes a fan nozzle to receive a fan flow from a fan disposed adjacent to an engine disposed above an airframe surface of the aircraft, a core nozzle disposed within the fan nozzle and receiving an engine core flow, and a pylon structure connected to the core nozzle and structurally attached with the airframe surface to secure the engine to the aircraft.

Abstract: The invention relates to a pylon for attaching a turbine engine for an aircraft, having a rigid structure (10) and means for attaching the pylon on a wing of the aircraft, said means for attaching the pylon on the wing comprising two side front ties (11a, 11b) each designed so as to take the thrust forces and comprising a fitting (54) pierced with a first orifice (65) firmly attached to the rigid structure (10), as well as a yoke (66) firmly attached to the wing. According to the invention, a central front tie (15) positioned between the side ties comprises a ball joint (27), and is laid out between both side front ties so that the centre (72) of the ball joint is located, as seen along the transverse direction (Y), in each of the first two orifices (65) of the side front ties.

Abstract: A mount system for a gas turbine engine includes an aft mount which reacts at least a portion of a thrust load at an engine case generally parallel to an engine axis.

Abstract: The object of the invention is an aircraft nacelle that comprises, on the inside, an inside pipe (56) that empties out toward the front at an air intake (58), and, on the outside, an aerodynamic wall that extends from the air intake (58) up to the rear end of the nacelle, and a hood (62) that comprises said air intake (58) as well as a cylindrical wall (64) that forms at least one portion of the aerodynamic surface of the outside of the nacelle, whereby said hood (62) can move translationally relative to a stationary part of the nacelle toward the front along slides (72), each slide (72) comprising a guide element (74) that is connected to the hood (or to the stationary part of the nacelle), whereby said guide element (74) can slide into a pipe (78) that is connected to the stationary part of the nacelle (or to a hood) and has a section that is above the section of the guide element (74) so as to allow the hood (62) to rotate in order to immobilize it in the closed position.

Abstract: A mounting system for a gas turbine engine includes a thrust ring and a linkage assembly. The linkage assembly is at least partially received by the thrust ring. The linkage assembly reacts at least a side load and a thrust load communicated from the thrust ring.

Abstract: A rear lower aerodynamic fairing for an attachment device for an aircraft engine, including two side panels assembled together with transverse stiffening inner ribs spaced apart from each other along a longitudinal direction of the fairing, and a heat protection floor to be closely followed by a primary flow of the engine. The floor includes plural floor segments distributed along the direction and non-rigidly bound to each other, and the fairing further includes an assembling mechanism assembling the floor segments, offsetting the latter of the ribs to which are connected the assembling mechanism.

Abstract: To be able to transport and replace in an autonomous manner one of its failing propulsion engines, a plane includes: a fuselage; propulsion engines maintained above the fuselage; maintenance wells traversing the fuselage substantially vertically with respect to the engines in which the engines can be lifted or lowered; a cargo compartment including a floor arranged in the fuselage, where the height, length and width dimensions of the cargo compartment are compatible with the transport of an engine; the cargo compartment and the wells have a common separation wall including an exit whose dimensions allow the passage of an engine; and a lower hatch or ramp for closing the lower opening of the well includes a position in which the upper surface of the ramp is substantially horizontal and substantially in the extension of the floor of the cargo compartment.

Abstract: The present invention relates to an isostatic suspension for mounting a turbojet engine on a pylon of an aircraft, the turbojet engine comprising a front fan, an intermediate casing downstream of the fan with an outer shell and a hub interconnected by radial arms, and an exhaust casing with an outer shell on the same axis XX, the suspension comprising a front attachment on the intermediate casing, a rear attachment with at least two rear attachment links connected to the outer shell of the exhaust casing, a pair of thrust bars being fixed at their upstream ends to the hub of the intermediate casing. It is characterized in that the plane formed by the two links of the rear attachment is inclined with respect to the plane of the exhaust casing.

Abstract: In an embodiment the invention includes an aircraft engine mounting system (20) for mounting an aircraft engine to an aircraft. The aircraft engine mounting system preferably includes an airframe structure member having a first engine end (28) and a distal second engine end (30), with an aircraft attachment between the first engine end and the distal second engine end, the aircraft attachment for interfacing the airframe structure member with the aircraft, the airframe structure member having an airframe structure member length (YL) from the first engine end to the distal second engine end. The aircraft engine mounting system preferably includes a first engine attachment structure member (36), the airframe structure member first engine end (28) contained by the first engine attachment structure member, with the first engine attachment structure member having an outer engine mount member (38) grounded to the aircraft engine.

Abstract: A device (2) for connecting a first body to a second body comprises: a first element (20) having a connection end (21) adapted for being connected to the first body and comprising a first tubular portion (22) extending along a longitudinal axis (X); and a second element (30) having a connection end (31) adapted for being connected to the second body and comprising a second tubular portion (32) extending along the longitudinal axis (X), in the first tubular portion (22) of the first element (20). The first tubular portion (22) and the second tubular portion (32) are interlocked by at least one complementary tubular portion (41, 42, 43) extending along the longitudinal axis (X), in the first tubular portion (22) and around the second tubular portion (32). Each of the tubular portions has, in a section crosswise to the said longitudinal axis (X), a surface (S) of identical value. Use in particular in an aircraft engine assembly.

Abstract: The invention relates to a mounting for attaching an engine to an aircraft structure, said mounting including a metal spring and being adapted for fulfilling the following conditions: the stiffness of the mounting for load values falling within a predetermined range ([CA, CB]) is less than the stiffness of the mounting for load values that fall below or above the predetermined range; considering a first load value (CS2) corresponding to a first operating mode (MF2), the load values due to dynamic variations during said first operating mode around said first value (CS2) fall within the predetermined range; the mounting comprising a means for limiting the movement of the spring with a given maximum value when applying a load with a value falling above the predetermined range ([CA, CB]).

Abstract: A mounting apparatus for an aircraft engine that provides load path redundancy includes a forward mount that attaches the aircraft engine to a pylon at a forward position of the aircraft engine, an aft mount that attaches the aircraft engine to the pylon at an aft position of the aircraft engine and a thrust assembly connected to the forward mount, and the aft mount. The forward mount includes an aircraft engine attachment assembly and a fail-safe assembly. The aft mount includes an aircraft engine attachment assembly and a fail-safe assembly.

Abstract: A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.

Abstract: An aircraft engine assembly including a mounting pylon including a rigid structure fitted with a central box, together with a forward extension and a rear extension each including an attached upper organ supported on an upper surface of the central box, and an attached lower organ supported on a lower surface of the front end. The forward and rear extensions support at least a part of the first fasteners interposed between the rigid structure and a turbine engine.

Abstract: An aircraft including a wing and a pylon, wherein the pylon provides an airfoil inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series LEARJET® is provided. The improvement includes an increased distance between a leading edge of a wing and an intake of an engine of the aircraft, which reduces drag and increases lift for improved flight dynamics of the aircraft. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamics of the aircraft. The method includes steps of removing an original engine from an original pylon, removing the original pylon from the fuselage of the aircraft, and mounting a new pylon in a new location adjacent to the fuselage, wherein the new location is aft of the original location.

Abstract: Noise generated by a gas turbine engine 6 supported by a pylon 8 on a wing 2 of an aircraft is reduced by influencing a shear layer generated between the free-stream flowfield and flow from the engine 6. The shear layer is influenced by means of one or more winglets 18, 20, 22 which interact with the free-stream flowfield to deflect the shear layer 14 downwardly, to avoid interaction with a flap 4 on the wing 2, or to reduce the strength of the shear layer 14.

Abstract: A pylon is provided for attachment of a gas turbine engine to a wing of an aircraft. The gas turbine engine comprises a core fairing surrounding a core generator and defining a nozzle for discharging a core gas flow, and a fan nacelle surrounding the core fairing to define an annular bypass duct therebetween for discharging fan air. The pylon has a trailing edge which is rearward of the trailing edge of the core fairing and the trailing edge of the fan nacelle. The pylon further has having two laterally-spaced side faces which span the bypass duct between the fan nacelle and the core fairing and extend in the rearward direction of the engine to end at the trailing edge of the pylon. Each side face has a bottom edge which extends in a rearward direction of the engine from the core fairing to the bottom end of the trailing edge of the pylon.

Abstract: An arrangement configured to connect an evener bar onto a rigid structure of an aircraft engine mount, including a pin system slidingly mounted in a first passageway of a bracket to permit its displacement along a first longitudinal axis, in a first direction from a normal extended position to a retracted position in which the pin system is retracted within this same bracket, and conversely. The arrangement also includes a pin extending member carried by the system and configured to be moved parallel to the longitudinal axis, in a second direction from a normal retracted position to an extended position in which the pin extending member is joined to the system and projects beyond the system, and conversely.

Abstract: An aircraft configuration that may reduce the level of noise, infrared radiation, or combination thereof directed towards the ground from an aircraft in flight. An embodiment of an aircraft includes a fuselage, two forward swept wings, at least one engine mounted to the aircraft and higher than the wings, and vertical stabilizers mounted on each wing outboard of the outermost engine. The leading edge of the wing may extend forward of the leading end of the engine, and the trailing edge of the aft deck may extend aft of the trailing end of the engine. The aft deck may include an upwardly rotatable pitch control surface at the trailing edge of the deck. Engine types may vary, including but not limited to turbofans, prop-fans, and turbo-props. Main wings may be mounted above the longitudinal axis of the fuselage, and canards may likewise be mounted above or below the axis.

Abstract: A gas turbine engine 2 is supported on an aircraft fuselage by a pylon 10 which carries a mounting ring 6. The mounting ring 6 is releasably coupled to an engine ring 8 on the casing of the engine 2, centred on the engine axis. A further member 12 extends from the pylon 10 and is secured to a location on the engine which is axially spaced from the mounting ring 6. The arrangement enables the engine 2 to be on the pylon in different orientations, to suit different mounting configurations on the aircraft 22.

Abstract: The invention relates to an aircraft support pylon (1), designed to attach a turbomachine housed in a nacelle (7) to an aircraft fuselage (8). The pylon comprises a cooler (21), located substantially in the vicinity of a leading edge (12) of the pylon, and able to be heated by a hot fluid, said hot fluid intended to be cooled by heat exchange with cold air outside said cooler. The pylon also comprises at least one air evacuation duct (22), at the exit from the cooler (21) and extending longitudinally in an internal volume of the pylon to a trailing edge (11) of the pylon.

Abstract: In one embodiment, a loading fitting includes at least one of an I, a T, and a J shaped cross-section having a flange attached to at least one supporting structure. In another embodiment, a method is disclosed for attaching a loading fitting to at least one supporting structure.

Abstract: A device for mounting a suspension member on the casing of a turbine engine is disclosed. The device includes a yoke with at least one lug, secured to the casing, a pin fixed to the yoke supporting the member via a ring surrounding the pin, and a rotation-prevention device that includes a counter-rotation plate attached to the lug. The plate and the pin include an assembly consisting of a peg and of a cutout or a hole, into which the peg fits in order to prevent the pin from rotating in the yoke.