A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.

A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.

A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.

A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.

A propulsion assembly for an aircraft, the propulsion assembly having a jet engine, an attachment pylon having a rigid structure, and an extinguishing system. The extinguishing system is located in a front position relative to the rigid structure, the extinguishing system being positioned between the rigid structure and the jet engine.

An aircraft is disclosed, including a fuselage having a compartment configured to house refueling apparatus. An auxiliary power unit is mounted in the compartment.

A front engine attachment system for an engine having an engine pylon with a nose having a main female clevis and a cylindrical housing, a main rod fastened to the engine by a secondary ball joint connection about a secondary axis, a main shaft realizing a main ball joint connection of the main rod in the main female clevis about a main axis, wherein the main axis and the secondary axis are in the same vertical plane, a hollow outer cylinder with a vertical axis, of which a first end is fastened in the cylindrical housing and of which a second end is mounted so as to be able to move, via an annular linear connection, with respect to the front casing and an inner cylinder threaded and fastened in the outer cylinder.

An engine support assembly for operatively connecting an engine to an aircraft, the aircraft, the aircraft having a support frame surrounded by opposing first and second skins. The engine support assembly broadly comprises first and second support structures. The first support structure is secured to the support frame and extends away from the first skin. The second support structure is releasably connected to the first support structure and releasably connected to the engine.

An aircraft propulsion system comprising a turbojet having a fan casing with a rear face, a pylon with a front part and a lower spar with a rear fitting fixed to it, and a front engine attachment fixed between an upper part of the fan casing and the front part, a front arch having two arms, each having a first end fixed to the lower spar and a second end fastened in an articulated manner to the rear face, and two lateral rods, each having a first end fastened in an articulated manner to the rear fitting and a second end fastened in an articulated manner to the rear face.

An assembly of an attachment pylon with an aircraft engine comprising a front engine mount comprising a front tang and a front clevis, a lower tang and a lower clevis connecting the attachment pylon and the engine via a front pin mounted in the front tang and clevis and a lower pin mounted in the lower tang and clevis, and port/starboard links mounted between the attachment pylon and the engine via mounting pins, wherein the front and lower pins are orthogonal to a mid-plane, and wherein the mounting pins of the links are parallel to the mid-plane.