Abstract: A method for mounting an aircraft engine on a pylon includes positioning at least a first shear pin either in a first opening provided in a front engine fastener which is previously attached to the engine using connecting rods, or in a first bore provided in a front surface of the pylon; prepositioning the assembly including the engine and the front engine fastener relative to the pylon by placing the first shear pin opposite a receiving cavity, the receiving cavity being either the first bore, if the first shear pin has been positioned in the first opening, or the first opening, if the first shear pin has been positioned in the first bore; and inserting the first shear pin into the receiving cavity.

Abstract: An attachment structure for attaching a power plant including unducted propellers to a fuselage of an aircraft, the attachment structure being connected by first and second fasteners to respective front and rear spars penetrating into the fuselage and fastened to a carrier structure of the aircraft, and including a central longitudinal beam secured at its front end to a first frame, arranged in the plane of the front spar, that is secured at its rear end to a second rear frame, cantilevered out and arranged upstream from the unducted propellers, and that is secured to a third intermediate frame, arranged in the plane of the rear spar between the first and second frames. The first, second, and third frames are connected together by force-takeup beams, an assembly as constituted in this way forming a cradle for receiving the power plant via a standard attachment.

Abstract: A suspension for an engine on an aircraft strut is disclosed. The suspension includes a beam with a plate provided with a fixing device for fixing to the 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, a fixing device for fixing to a case of the engine.

Abstract: A turbojet engine with a fan and a nacelle element forming the secondary duct downstream of the fan is provided. The turbojet engine includes an intermediate casing with an outer shroud to which the nacelle element is fixed by a connecting member. The connecting member includes a cylindrical element secured to the shroud while at the same time being capable of a rotational movement with respect to the axis of the engine and connected to the nacelle element by a bayonet-type fitting.

Abstract: An attachment structure for attaching a power plant including unducted propellers to a fuselage of an aircraft, the attachment structure being connected by first and second fasteners to respective front and rear spars penetrating into the fuselage and fastened to a carrier structure of the aircraft, and including a central longitudinal beam secured at its front end to a first frame, arranged in the plane of the front spar, that is secured at its rear end to a second rear frame, cantilevered out and arranged upstream from the unducted propellers, and that is secured to a third intermediate frame, arranged in the plane of the rear spar between the first and second frames. The first, second, and third frames are connected together by force-takeup beams, an assembly as constituted in this way forming a cradle for receiving the power plant via a standard attachment.

Abstract: A method for mounting an aircraft engine on a pylon includes positioning at least a first shear pin either in a first opening provided in a front engine fastener which is previously attached to the engine using connecting rods, or in a first bore provided in a front surface of the pylon; prepositioning the assembly including the engine and the front engine fastener relative to the pylon by placing the first shear pin opposite a receiving cavity, the receiving cavity being either the first bore, if the first shear pin has been positioned in the first opening, or the first opening, if the first shear pin has been positioned in the first bore; and inserting the first shear pin into the receiving cavity.

Abstract: An air inlet duct and method for producing such for a turbojet nacelle, the air inlet duct including an upstream annular lip and a downstream outer annular structure. The upstream annular lip and the downstream outer annular structure are formed as a one-piece part made from composite material and the upstream lip is covered with a metal layer formed by electro-deposition or plastic forming. A turbofan engine can include such an air inlet duct.

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: 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: 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: The present invention relates to a turbojet engine with a fan (2) and a nacelle element (2) forming the secondary duct downstream of the fan, the turbojet engine comprising an intermediate casing (6) with an outer shroud (61) to which said nacelle element (8) is fixed by means of a connecting member, wherein the connecting member comprises a cylindrical element (62) secured to the shroud (61) while at the same time being capable of a rotational movement with respect to the axis of the engine and connected to said nacelle element (8) by a bayonet-type fitting.

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: The present invention relates to a turbojet suspended from an aircraft mast, the turbojet comprising 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 comprising a structural strut assembly of elongated shape. In said turbojet said strut assembly is attached upstream rigidly to said outer shroud of the intermediate casing by a front attachment comprising a means for transmitting the axial and lateral forces and downstream by a rear attachment to said exhaust casing.