Abstract: An aircraft propulsion unit including a turbojet and a heat exchanger located above the turbojet and drawing a cooling air stream and a hot air stream in the turbojet. Wherein the cooling air intake and hot air intake surfaces in the housing are directed forward of the turbojet and have normal lines inclined relative to the axis of the turbojet. The embodiment also concerns an aircraft equipped with at least one such propulsion unit.

Abstract: An aircraft engine attachment pylon including a rigid structure forming a caisson, and a rear engine attachment including an attachment body and at least one lateral fitting arranged on either side of the caisson. Each fitting includes a first portion pierced by first assembly holes enabling it to be fixed to the caisson, and a second portion defining a fixing surface of the body. The second portion includes a housing orifice receiving a self-locking nut cooperating with a screw supported against the body and, in transversal section, an axis of the screw passes through the first holes.

Abstract: An aircraft engine assembly including an engine, an engine mounting structure, and a nacelle surrounding the engine and including fan cowls. The mounting structure includes a rigid structure and a forward aerodynamic structure on which the fan cowls are hinged, the forward aerodynamic structure including a cradle provided with an aft mounting mechanism mounted on the rigid structure. The cradle also includes a forward mounting mechanism mounted on a fan case of the engine.

Abstract: An aircraft engine attachment device including a rigid structure and a mechanism attaching the engine on the rigid structure, the attachment mechanism including a rear engine attachment and a device for taking-up thrust forces generated by the engine. The rear engine attachment is attached to the rigid structure by two lateral fittings attached to the rigid structure. The force take-up device includes two connecting rods mechanically connected to a spreader beam by a mechanical connection, a connection fitting attached to the rear engine attachment and mechanically connected to the rigid structure by a thrust pin, the lateral fittings including a stop mechanism to limit pivoting of the spreader beam if a connecting rod breaks and ensuring transmission of thrust forces to the rigid structure.

Abstract: An aircraft engine attachment device including a rigid structure and a mechanism attaching the engine on the rigid structure, the attachment mechanism including a rear engine attachment and a device for taking-up thrust forces generated by the engine. The rear engine attachment is attached to the rigid structure by two lateral fittings attached to the rigid structure. The force take-up device includes two connecting rods mechanically connected to a spreader beam by a mechanical connection, a connection fitting attached to the rear engine attachment and mechanically connected to the rigid structure by a thrust pin, the lateral fittings including a stop mechanism to limit pivoting of the spreader beam if a connecting rod breaks and ensuring transmission of thrust forces to the rigid structure.

Abstract: An aircraft engine attachment pylon including a rigid structure forming a caisson, and a rear engine attachment including an attachment body and at least one lateral fitting arranged on either side of the caisson. Each fitting includes a first portion pierced by first assembly holes enabling it to be fixed to the caisson, and a second portion defining a fixing surface of the body. The second portion includes a housing orifice receiving a self-locking nut cooperating with a screw supported against the body and, in transversal section, an axis of the screw passes through the first holes.

Abstract: The present invention relates to an aircraft engine assembly comprising an engine, an engine mounting structure (4) and a nacelle surrounding the engine and provided with fan cowls (34), the mounting structure (4) comprising a rigid structure (8) and a forward aerodynamic structure (24) on which the fan cowls are hinged, this forward aerodynamic structure (24) being equipped with a cradle (40) provided with aft mounting means (44a, 44b) mounted on the rigid structure (8). According to the invention, the cradle is also equipped with forward mounting means (42) mounted on a fan case (18) of the engine.

Abstract: An aircraft propulsion unit including a turbojet and a heat exchanger located above the turbojet and drawing a cooling air stream and a hot air stream in the turbojet. Wherein the cooling air intake and hot air intake surfaces in the housing are directed forward of the turbojet and have normal lines inclined relative to the axis of the turbojet. The embodiment also concerns an aircraft equipped with at least one such propulsion unit.

Abstract: Method for the production of a silicone-based fireproof protection means and protection means thus obtained.According to the invention, the protection means include:an inner polymerized unfilled silicone coating (3) adhering to an object (2) to be protected; anda fire-resistant fibrous jacket (5) carried by said inner coating (3), without adhering to it.Application to the protection of pipes, especially hydraulic pipes.

Abstract: Method for the production of a silicone-based fire-proof protection article. The protection article includes an inner polymerized unfilled silicone coating (3) adhering to an object (2) to be protected, and a fire-resistant fibrous jacket (5) carried by said inner coating (3), without adhering to it. The protection article can be used for the protection of pipes, especially hydraulic pipes.