A front engine attachment system for an aircraft engine, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam has front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate. Each link-rod system is fastened to the intermediate plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

An attachment for attaching an aircraft engine with a first receiving element to an aircraft structure with a second receiving element may include at least three fasteners and a stacked layer. Stacked layer may include at least two sheets, at least three holes through the stacked layer, a first connecting portion that includes a first hole of the at least three holes, a second connecting portion that includes second and third holes of the at least three holes, and a suspension portion that is located between the first connecting portion and the second connecting portion.

An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.

An assembly for an aircraft that has a wing and an engine pylon having a primary structure with right-side and left-side panels, an upper and a lower spar and a rear rib, two sets of upper or lower shackles, one set fastening the right-side panel to the wing, and a second set fastening the left-side panel to the wing, a fastening element secured to the rear rib or to the lower spar, a rear rod connecting the fastening element to the wing, a transverse shackle connecting the upper spar to the wing, a line connecting two centers of the transverse shackle being oriented transversely relative to a longitudinal axis of the engine pylon, and a reinforcing panel, at each joint between a right-side or left-side panel and an upper or lower shackle, which is fastened along a height against the panel and to which the shackle is also fastened.

A propulsion assembly having a jet engine with a central casing, an attachment pylon having a rigid structure, a front engine attachment and a device for reacting the thrust forces. The front engine attachment has, on either side of a median plane, a front rod articulated via a connection point respectively to the rigid structure and to the central casing, and the reaction device has two central rods, two first fittings as one with the rigid structure and two second fittings as one with the central casing, wherein the two first fittings are independent of one another and wherein each central rod is articulated between a first fitting and a second fitting.

An assembly for connecting an engine to an aircraft, including a first support configured to be structurally connected to the engine, a second support configured to be structurally connected to the aircraft, and a thrust link. The thrust link includes a load transferring member having opposed ends each connected to a respective one of the supports for transferring engine thrust loads from the engine to the aircraft along a longitudinal axis of the load transferring member. The opposed ends have a fixed position relative to each other. The thrust link further includes a tuned absorber coupled to the load transferring member intermediate the opposed ends. The tuned absorber is tuned to absorb engine noise of at least one predetermined frequency. A thrust link and a method for reducing a transfer of noise generated by the engine to the aircraft are also discussed.

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 having a central part connected to the support and a first and a second end that are connected to thrust rods, at least one limiting system for limiting the travel of the spreader having an upper and a lower stop between which is positioned the first or second end of the spreader, the upper and the lower stop being connected to one another so as to form a single part connected to a fitting secured to the support.

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.

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.

An integrated propulsion system according to an example of the present disclosure includes, among other things, a fan section, a gas turbine engine, a geared architecture, a nacelle assembly and a mounting assembly. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.