A method of assembling and installing an underwing package to an underside of an aircraft wing is disclosed. In various embodiments, the method includes assembling the underwing package, comprising at least a pylon and an engine, using a build frame; attaching a transfer cart to the underwing package; lowering the underwing package and the transfer cart from the build frame; transporting the underwing package and the transfer cart to the underside of the aircraft wing; and transferring the underwing package from the transfer cart to the underside of the aircraft wing.

An assembly between an aircraft structural pylon and an aircraft turbine engine is disclosed, with the assembly comprising a beam intended to be attached to the turbine engine and wherein a knuckle intended for the installation of a pad integral with the pylon is mounted, with the beam comprising suspension lugs each including a bore for the passage of a shaft intended to further go through a bore formed in the pylon to connect the beam with the pylon.

For fitting of a front engine attachment of an engine assembly for an aircraft, a shearing pin is oriented in a longitudinal direction and is integral with a front closure rib of the strut housing and projects forward, a main attachment body is arranged axially opposite the intermediate casing hub, at the rear of the latter, the main attachment body having an orifice for accommodation of the shearing pin, an arrangement for securing the main attachment body on the engine, and an arrangement for axial retention of the main attachment body relative to the rib, the axial retention arrangement comprising first screws, the heads of which cooperate with the rib, as well as barrel nuts which cooperate with the screws, and are accommodated in the main attachment body.

Compliant mounting systems, devices, and methods for mounting a vehicle engine to a vehicle structure or base include a top mount, a lower mount, a center trunnion mount, and an aft mount which are configured to react forces transmitted by the engine to the vehicle structure. Metallic and elastomeric elements can provide vibrational and force isolation characteristics. Stops (e.g., snubbing elements) allow for a specific range of motion before internal mount structures contact each other to act as a conventional hard mount. Fluid elements and compressible gas-filled spaces/bladders may be incorporated to provide fluid damping behaviors to complement the metallic and elastomeric elements.

A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader, extending between first and second ends that has a central part connected to the support by a principal link comprising a principal rotation axis, at least one system for limiting the deflection of the spreader comprising an extension secured to the spreader and also upper and lower stops, secured to a fitting secured to the support, between which the extension is positioned.

An engine attachment system for an engine including an engine nacelle. The engine attachment system includes an engine pylon with a starboard face and a port face, a starboard shoe having a starboard sole fixed to the starboard face and a starboard wall secured to the starboard sole, a port shoe having a port sole fixed to the port face and a port wall secured to the port sole, a starboard link fixed in an articulated manner by one of its ends to the starboard wall and configured to be articulatedly fixed by the other of its ends to the engine nacelle, a port link articulatedly fixed by one of its ends to the port wall and configured to be atriculatedly fixed by the other of its ends to the engine nacelle, and a fixing arrangement that fixes each sole to the corresponding face of the engine pylon.

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.

An aircraft rear engine attachment connecting a primary structure of a pylon and an engine of an aircraft. The rear engine attachment includes first and second rods, each of them including at least two parts, a first part including at least one support orifice, accommodating a support link bar, configured to connect the rod directly or indirectly to the primary structure, at least one second part including at least one engine orifice, accommodating an engine link bar, configured to connect the rod directly or indirectly to the engine, and also detachable link elements for connecting the first and second parts oriented parallel to the direction of the rod.

A rear engine fastener for an aircraft connecting a primary structure and an engine of an aircraft, the rear engine fastener comprising a support configured to be connected to the primary structure, at least one main shackle connected to the support by first and second support link pins, which are symmetrical relative to a vertical longitudinal plane, and to the engine by a first lateral engine link pin and by a central engine link pin, and at least one secondary shackle connected to the engine by a second lateral engine link pin and to the main shackle by a secondary link pin.

A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a high spool, and a low spool including a low pressure turbine that drives the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.