Abstract: The inventive fixing system comprises a front attachment (6), a rear attachment (7) and an intermediate attachment (8) connecting a strut (1) to a wing (2), wherein the lower fitting (17) of the rear attachment (7) is fixedly connected to the transversal rear face (1G) of said strut on the extension thereof and said lower fitting (17) is substantially in flush with the top face of the strut.

Abstract: An aircraft the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following, air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

Abstract: When an aircraft is propelled by at least one jet engine fixed in a rear part of the aircraft, at least one substantially horizontal rear aerodynamic surface, the rear horizontal surface, is arranged at the rear of the aircraft and at least one jet engine is fixed under the rear horizontal surface by an attachment mast fixed by its upper part to the rear horizontal surface and maintains, by its lower part, the jet engine. The rear horizontal surface is also the horizontal tail unit of the aircraft or a horizontal surface maintained above the fuselage. The rear surfaces and the fuselage are arranged such that the engines are installed and removed using a vertical movement of the engines, which are advantageously one, two or three in number, in the rear zone of the aircraft.

Abstract: The invention relates to a multi-engine aircraft whose at least two engines (2, 3) are fixed to the fuselage wings symmetrically with respect to the longitudinal vertical plane of symmetry thereof, respectively and the third engine (7) is provided for the tail of the fuselage which comprises tail-planes in the view of said longitudinal plane. The tail-planes (9, 10) define a channel (11) symmetrical with respect to the longitudinal plane of the fuselage and the third engine (7) is disposed on the plane of symmetry of the channel corresponding to the longitudinal plane and mounted on the top part of the fuselage in an elevated manner and before the tail-planes in such a way that output of said third engine is arranged substantially upon the input of the channel (11) defined by said tail-planes.

Abstract: A multi-engine aircraft having one engine positioned at the tail of the fuselage may include rear tail units in a vertical longitudinal plane-of-symmetry of the fuselage. The tail engine is disposed in front of the rear tail units on the upper part of the tail of the fuselage. The tail engine is mounted, in a detachable manner, on a rigid supporting structure attached to the supporting structure of the fuselage. A lowering shaft, formed in the tail of the fuselage and plumb with the engine, is supported by the rigid supporting structure. The lowering shaft provides a passage for the engine between a high position corresponding to the operational position of the engine and a low position in which the engine is removed from the fuselage.

Abstract: The present invention relates to a multi-engined aircraft of which one (7) of the engines is positioned at the tail (9) of the fuselage (6), which comprises the rear tail units, and in the vertical longitudinal plane of symmetry of said fuselage. Advantageously, said tail engine (7) is disposed in front of the rear tail units, on the upper part (8) of the tail of the fuselage, and is mounted, in detachable manner, on a rigid supporting structure (15) attached to that of said fuselage and there is formed, in the tail (9) of said fuselage and plumb with said engine (7) supported by said structure (15), a lowering shaft (16) for the passage of said engine between, on the one hand, a high position corresponding to the operational position of said engine and, on the other hand, following the separation of said engine from the supporting structure and its displacement through said lowering shaft, a low position in which said engine has come out of said fuselage (6) and is under said tail.