Abstract: An aircraft propulsion system (10) is connected to a strut, fixed to the wing or fuselage, by a fixing device comprising at least one rear mount (22) and two front mounts (24, 26). The rear mount (22) and a first (24) of the front mounts connect a main part (12a) of the frame (12) of the strut to the central casing (16) of the engine. The other front mount (26) connects a front part (12b) projecting from the strut frame (12) to the fan stator case (20) and mainly takes up the vertical forces (Z). Thus, the first front mount (24) can be simplified and bending or sagging of the engine is reduced.

Abstract: A device for the attachment of an aircraft engine to a strut comprises a main attachment structure (18, 24) able to transmit normally to the strut forces exerted in two directions (X′, Y′), whereof one is mainly parallel to the longitudinal axis (OX) of the engine and the other mainly perpendicular to said axis and to a median plane common to the engine and the strut. The device also comprises an emergency attachment structure essentially constituted by an element (10) fixed to the strut and also forming part of the main attachment structure. The element (10), preferably implemented in the form of two coupled together parts (10a, 10b), comprises a pin (42) penetrating with clearance a recess formed on the aircraft casing (C).

Abstract: A particularly simple and compact attachment device to be interposed between an aircraft engine casing (C) and a strut connected to the wing or fuselage of an aircraft, is designed so as to only transmit forces exerted in a single direction (OZ). The device comprises a crossbar (18), articulated to an element (10) fixed to the strut and also fulfilling an emergency function. The ends of the crossbar (18) are connected to the engine casing (C) by rods (24). The element (10) is preferably formed from two parts (10a, 10b), each being able to transmit all the forces in the direction (OZ).

Abstract: On an aircraft, particularly of the commercial type, a landing gear (16) placed in front of a fuel tank (18) comprises a rod system (32) capable of coming into contact with a sliding rail (52) formed on a reinforced structural part (48) of the aircraft, in the event of accidental tilting of the gear to the rear. The deformation resulting from the rod system (32) then successively induces the complete slackening of the damper (24) of the gear, the rupture of its slack limit stop (25), followed by the rupture of a part of the rod system (32). The lower part of the gear (16) is then ejected and guided by a rear part (52b) of the sliding rail (52), with no risk of perforation of the tank (18).

Abstract: A structure for attaching the landing gear (16) to an aircraft fuselage incorporates a force take-up bar (32), housed coaxially in the barrel (24) of the landing gear. The force take-up bar (32) transmits lateral forces exerted by the landing gear (16) towards the outside of the aircraft when it is on the ground, to a ventral beam (22) connected to the fuselage. This characteristic permits the landing gear barrel (24) to be mounted in the non-reinforced lateral fitting (20), connected to the fuselage.