An engine attachment system comprising an engine pylon with a top wall, a bottom wall and two lateral walls, and a front engine attachment with a beam which bears two connecting rods for fixing the engine. The engine attachment system also comprises an intermediate piece with a bottom wall and four lateral walls, wherein the beam is fixed against an outer face of the bottom wall, wherein the intermediate piece is fitted at a front-end face of the engine pylon in such a way that an inner face of the bottom wall comes against the front-end face of the engine pylon, and in such a way that the lateral walls of the intermediate piece are superposed with the walls of the engine pylon. In such an engine attachment system, the front engine attachment is thus located on the front-end face of the engine pylon, allowing a space saving.

The invention relates to a suspension pylon comprising: at least one arm (3) for suspending a propulsion unit (4) from the fuselage (2) of an airplane (1), an oil exchange circuit (70) configured to be connected, on the one hand, to an oil pump (5) in the fuselage (2) and on the other hand, to the propulsion unit (4) the arm (3) whereof provides for suspension, said circuit (70) comprising a feed line (72) and a return line (74), which both extend inside said arm (3), an intermediate shaft (6) which extends in said arm (3), said shaft being configured, on the one hand, to be driven by the propulsion unit (4) the arm (3) whereof provides for suspension and, on the other hand, to drive the oil pump (5) in the fuselage (2),
wherein the arm (3) has a structure adapted for cooling the oil exchange circuit at the arm (3).

An aircraft engine pylon having an upper fitting, an upper panel located below the upper fitting, a shear pin at least partially coupling the upper fitting and the upper panel, and tension fasteners at least partially coupling the upper fitting and the upper panel with the shear pin defining a shear force load path and the tension fasteners defining tension force load paths.

An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical hearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

An aircraft engine unit comprising an engine, a mast and an engine connection connecting the engine and the mast. The aircraft engine unit includes a front engine attachment of the engine connection which comprises at least one front rod connecting the primary structure of the mast and the core of the engine and which assures the take-up of vertical forces, and at least one connection connecting the primary structure of the mast and the fan casing of the engine and which assures the take-up of forces that are horizontal and perpendicular to the axis of rotation of the engine and/or a torque about the axis of rotation of the engine.

A structure for linking and supporting a turbine engine on an aircraft pylon, the structure having a first longitudinal axis intended to extend parallel to a second longitudinal axis of the pylon, the structure including a first axial portion for fastening to the pylon, the first portion having an upper end that defines a substantially horizontal plane of interface with the pylon, and a lower end bearing suspension rods for suspending the turbine engine, which extend in a rear vertical plane; and a second axial portion that is intended to extend forward of the pylon and includes at least one suspension member of the turbine engine in a front vertical plane.

An engine mount may include a clevis and a lug defining a hole therethrough. A pin may be joined to the clevis and may extend through the hole of the lug with the pin and the lug defining a clearance therebetween. A trigger system may be disposed on the lug and operatively associated with the pin.

A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.

A ducted fan gas turbine engine has a propulsive fan, a fan case surrounding the fan, a core engine, and a plurality of support structures which transmit loads from the core engine to the fan case. Each support structure has two support struts which extend from the core engine to a joint radially outwardly of the fan case. The support struts are spaced apart at the core engine but converge to meet at the joint. Each support structure further has two structural elements which extend from the joint to respective fixing positions on the fan case at opposite sides of the joint.

An aircraft engine assembly including a set of rear engine attachments comprising a first shackle hinged on a bracket secured to the engine and on a bracket made as one piece with one of the two side panels, the shackle being oriented along a vertical direction, a second shackle hinged on a bracket secured to the engine and on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction, and a third shackle for transversally transmitting loads, inclined relative to the vertical direction and hinged on a bracket secured to the engine and on a bracket secured to the primary structure.