Abstract: The invention relates to an assembly for an aircraft comprising a wing element (2) and a suspension pylon (4) for an engine (10) under the wing element, the suspension pylon (4) comprising a rigid structure (6) forming a box provided with an aft closing element (28), and the wing element (2) having a forward spar (34) extending substantially parallel to a leading edge (30) of the wing element. According to the invention, the rigid structure is assembled on the wing element such that the aft closing element bears in contact with the forward spar (34).

Abstract: An aircraft engine assembly including a turbojet, a turbojet attachment pylon, and a nacelle mounted on the attachment pylon and surrounding the turbojet. The nacelle includes at least one mobile nacelle portion forming a single piece envelope all around a section of the turbojet, this mobile nacelle portion being mounted free to slide on the attachment pylon so that it can be moved from the forward position in the aft direction, and vice versa.

Abstract: A mount for an aircraft turbojet engine. The mount includes a central box formed by an assembly of two side panels joined via transverse ribs and two side boxes secured to a forward part of the box and arranged either side thereof, each side box including an aft closure frame. One of the ribs forming the box includes two side extensions made in a single piece with the rib and respectively projecting from the two side panels outwardly from the box, the two extensions being fixedly mounted on the frame of each of the two side boxes, respectively.

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: The invention refers to a suspension pylon (4) for an aircraft engine (2), the pylon including a rigid structure (10) forming a box provided with a lower spar (28) and an upper spar (26), and an engine mounting system (11) installed fixed on the structure (10) and in particular including a forward attachment (6) with an attachment body provided with a horizontal fixing surface (40) held in contact with a horizontal fixing surface (38) of the structure (10). According to the invention, the attachment body is arranged such that its horizontal fixing surface (40) is located along a vertical direction (Z) of the pylon, upwards from a forward end (28a) of the lower spar and downwards from a forward end (26a) of the upper spar. Furthermore, the structure (10) includes at least one forward fitting (42a, 42b) making up a forward closing rib (36) of the box, this fitting (42a, 42b) defining said horizontal fixing surface (38).

Abstract: An engine mount for an aircraft engine. The engine mount includes a rigid structure forming a box closed at its forward end by a forward closure rib, and a mounting system including a forward engine attachment having an attachment body fixedly mounted on the rigid structure. The attachment body lies against a forward surface, and the engine mount includes at least one shear pin passing at least in part through the attachment body and forward closure rib.

Abstract: An aircraft engine assembly including a turbojet engine, an engine mount, and a plurality of engine attachments. The engine attachments include first and second forward attachments fixed to a fan case and located symmetrically in relation to a plane defined by a longitudinal axis of the turbojet engine and a vertical direction thereof, both forward attachments configured to transfer loads exerted in a longitudinal direction of the turbojet engine and in the vertical direction thereof. Moreover, each of the two forward attachments includes a shear pin mounted on the case and going through two walls of a clevis fixed on the engine mount.

Abstract: The invention relates to an engine suspension pylon for an aircraft including a rigid structure provided with a box (24), this pylon also including an engine aft attachment (8) provided with an attachment body (38), and a thrust resistance device (9) generated by the engine. The rigid structure according to the invention includes an offset rib (35) for the attachment body (38), this rib (35) being mounted fixed on the box (24) between the box and the engine (2) and carrying the attachment body. Furthermore, the device (9) includes a thrust resistance spar (9b) of which the forward end is mounted fixed on the rib (35), and the aft end is mounted fixed on the box.

Abstract: A device for suspension of an engine, configured to be inserted between an aircraft wing and the engine. The device includes a rigid structure and a forward aerodynamic structure mounted fixed on the structure through a suspension mechanism. The forward aerodynamic structure is configured to carry engine fan casings and to be inserted between the rigid structure and the wing. The suspension mechanism includes at least one adjustable length connecting rod of which one end is mounted on the rigid structure, and the other end is mounted on the forward aerodynamic structure.

Abstract: The invention concerns a method to mount an aircraft engine on a rigid structure of an engine mount, comprising a securing step, on the structure, to secure an attachment body (46) for an engine attachment, this attachment body being intended to lie against a contact surface of the rigid structure oriented forwardly, and secured to this structure by at least one shear pin (68) passing through a first and a second primary orifice, the securing step of the body (46) comprising the following operations: pre-positioning the engine relative to the engine mount for the purpose of placing the first orifice opposite the second orifice; and inserting a pin fitted with a convex centering head through the two orifices, so that this pin forms the shear pin.

Abstract: An engine assembly including an engine mount, the engine mount including a rigid structure including a box and a mounting system positioned between the engine and the rigid structure. This mounting system includes an aft attachment. The assembly further includes a thermal protection system for the box, including a preferably ventilated duct forming a heat barrier and extending between the box and the engine. The duct extends rearward beyond the aft engine attachment.

Abstract: A structure for an aircraft engine assembly suspension pylori. The pylori includes a monolithic frame, manufactured for example by casting or welding, covered with mechanically assembled skins. Advantageously, stiffeners are mechanically fixed to points through which forces are applied. The dual structure makes it possible to take advantage of integration during manufacturing while respecting safety criteria due to mechanical assemblies.

Abstract: An assembly for an aircraft including a wing element, a suspension pylon, a mechanism of attaching the pylon onto the element, including two forward half-attachments, each including a shackle and configured to resist forces applied along a vertical direction. The shackle is mounted firstly articulated onto a first fitting fixed to a forward spar of the element extending along the direction of the width, and is secondly mounted articulated onto a second fitting fixed to the rigid structure of the pylon. The two shackles are arranged in the same plane parallel to the direction of the width.

Abstract: An engine attachment pylon for an aircraft including an aft engine attachment fitted with an aft attachment body and a first shear pin capable of resisting forces applied along a transverse direction of the pylon. The first pin passes through a lower spar of a rigid structure of the pylon and includes a lower end housed in the aft attachment body. The lower end includes a reaming through which a first pin passes, that also passes through the aft attachment body.

Abstract: The invention relates to an engine suspension pylon for an aircraft including a rigid structure provided with a box (24), this pylon also including an engine aft attachment (8) provided with an attachment body (38), and a thrust resistance device (9) generated by the engine. The rigid structure according to the invention includes an offset rib (35) for the attachment body (38), this rib (35) being mounted fixed on the box (24) between the box and the engine (2) and carrying the attachment body. Furthermore, the device (9) includes a thrust resistance spar (9b) of which the forward end is mounted fixed on the rib (35), and the aft end is mounted fixed on the box.

Abstract: The invention refers to a suspension pylon (4) for an aircraft engine (2), the pylon including a rigid structure (10) forming a box provided with a lower spar (28) and an upper spar (26), and an engine mounting system (11) installed fixed on the structure (10) and in particular including a forward attachment (6) with an attachment body provided with a horizontal fixing surface (40) held in contact with a horizontal fixing surface (38) of the structure (10). According to the invention, the attachment body is arranged such that its horizontal fixing surface (40) is located along a vertical direction (Z) of the pylon, upwards from a forward end (28a) of the lower spar and downwards from a forward end (26a) of the upper spar. Furthermore, the structure (10) includes at least one forward fitting (42a, 42b) making up a forward closing rib (36) of the box, this fitting (42a, 42b) defining said horizontal fixing surface (38).