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 aircraft (10) is described as including a reference axis extending along at least a portion of the aircraft, and a propulsion system having a thrust vector feature (43) defining generally a direction of thrust of the turbofan engine (18), the thrust vector feature (43) extending relative to a thrust vector axis, where the turbofan engine (18) is disposed on the aircraft with the thrust vector feature (43) oriented with respect to the reference axis of the aircraft.

An aircraft (10) is described as including a reference axis extending along at least a portion of the aircraft, and a propulsion system having a thrust vector feature (43) defining generally a direction of thrust of the turbofan engine (18), the thrust vector feature (43) extending relative to a thrust vector axis, where the turbofan engine (18) is disposed on the aircraft with the thrust vector feature (43) oriented with respect to the reference axis of the aircraft.

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.

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.

A heat shield assembly for use with an aircraft engine. The heat shield assembly includes a structural member, a heat shield panel adapted for exposure to aircraft engine exhaust, an index joint coupling the heat shield panel to the structural member in a fixed positional location, and a plurality of slip joints coupling the heat shield panel to the structural member. Each slip joint includes at least one wear buffer coupled to the heat shield panel, and a slip fastener insertable through a slip joint hole in the heat shield panel with a clearance fit. A gap defined by the clearance fit is sized to provide a tolerance for expansion and contraction of the heat shield panel relative to the fixed positional location, and the at least one wear buffer is engageable by the slip fastener during expansion and contraction of the heat shield panel.

A heat shield assembly for use with an aircraft engine. The heat shield assembly includes a structural member, a heat shield panel adapted for exposure to aircraft engine exhaust, an index joint coupling the heat shield panel to the structural member in a fixed positional location, and a plurality of slip joints coupling the heat shield panel to the structural member. Each slip joint includes at least one wear buffer coupled to the heat shield panel, and a slip fastener insertable through a slip joint hole in the heat shield panel with a clearance fit. A gap defined by the clearance fit is sized to provide a tolerance for expansion and contraction of the heat shield panel relative to the fixed positional location, and the at least one wear buffer is engageable by the slip fastener during expansion and contraction of the heat shield panel.

A system includes a gas turbine engine of an aircraft, the gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool and a high spool motor configured to augment rotational power of the high speed spool. The system further includes a controller configured to cause fuel flow. The controller is configured to control a thrust response of the gas turbine engine to a thrust target between zero and a thrust level to move the aircraft during engine start and during engine idle. The controller is also configured to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.

An engine pylon for mounting a jet engine beneath a wing of an aircraft, the engine pylon having a primary structure having two internal lateral fittings that face one another and a rib that is fastened between the two internal lateral fittings and a primary box that at least partially surrounds the primary structure and comprises a first part made from a composite material.