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.

An aircraft gas turbine engine (110) comprises first and second non-coaxial propulsors (113a, 113b), each propulsor (113a, 113b) being driven by a common gas turbine engine core (176) comprising a propulsor drive turbine (143) arranged to drive the first and second propulsors (113a, 113b) via a propulsor drive coupling (127). The core (176) further comprises a first core module (190) comprising a first compressor (129) and a first turbine (131) interconnected by a first shaft (177), and a second core module (191) comprising a second compressor (128) and the propulsor drive turbine (143) interconnected by a second shaft (127), the first and second core modules (190, 191) being axially spaced.

An aircraft gas turbine engine (110) comprises first and second non-coaxial propulsors (113a, 113b), each propulsor (113a, 113b) being driven by a common gas turbine engine core (176) comprising a propulsor drive turbine (143) arranged to drive the first and second propulsors (113a, 113b) via a propulsor drive coupling (127). The core (176) further comprises a first core module (190) comprising a first compressor (129) and a first turbine (131) interconnected by a first shaft (177), and a second core module (191) comprising a second compressor (128) and the propulsor drive turbine (143) interconnected by a second shaft (127), the first and second core modules (190, 191) being axially spaced.

The present disclosure is directed to an aerodynamic stabilizer assembly for stabilizing an aft fan mounted to a fuselage of an aircraft. For example, the stabilizer assembly includes one or more generally horizontal stabilizers for mounting to a nacelle of the aft fan and the fuselage so as to stabilize the aft fan. Each of the generally horizontal stabilizers includes an inner portion and an outer portion. As such, the inner portions are mounted to a nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion.

The present disclosure is directed to an aerodynamic stabilizer assembly for stabilizing an aft fan mounted to a fuselage of an aircraft. For example, the stabilizer assembly includes one or more generally horizontal stabilizers for mounting to a nacelle of the aft fan and the fuselage so as to stabilize the aft fan. Each of the generally horizontal stabilizers includes an inner portion and an outer portion. As such, the inner portions are mounted to a nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion.

An aircraft strut includes a primary structure which includes: a top stringer, a bottom stringer, at least one transverse frame which links the top stringer to the bottom stringer, a front end wall which links a front end of the top stringer to a front end of the bottom stringer, a rear end wall which links a rear end of the top stringer to a rear end of the bottom stringer, two lateral frames arranged on either side of the transverse frame, each lateral frame having a lattice form. An aircraft includes at least one strut described herein.

A system comprises an engine mounted to an aircraft wing by a plurality of clevis pins, a respective strain sensor mounted in at least one of the clevis pins, and a monitoring system operatively connected to each respective strain sensor to monitor stress in each of the clevis pins having a respective strain sensor.

A coated wire suitable for aerospace applications includes a metallic conductor elongated along an axis and having an outer surface extending along the axis, and three coating layers surrounding the conductor. A first coating layer is connected to the outer surface of the conductor and extends along the axis to surround the conductor, and the first coating layer is formed of ethene-tetrafluoroethene. A second coating layer is connected to the first coating layer and extends along the axis to surround the first coating layer, and the second coating layer is formed of polyaryletherketone. A third coating layer is connected to the second coating layer and extends along the axis to surround the third coating layer, wherein the third coating layer is formed of ethene-tetrafluoroethene. The three coating layers may each be continuous and seamless extruded layers in one configuration.

An assembly having a pylon with an upper spar and four lateral scoops, a wing with a skin, longitudinal spars and fittings, and, for each lateral scoop, two fastening assemblies, wherein the skin and the fitting each have a first bore and wherein the upper spar and the lateral scoop each have a second bore, wherein each fastening assembly has a screw passing through the first and the second bores, a nut, two eccentric rings, threaded onto one another and onto the screw, and a system for stopping the eccentric rings rotating. The assembly makes it possible to dispense with the use of the spigots while also ensuring the reaction of the shear forces contained in the XY plane by the bolts on account of the reduced tolerances between the various bores, the external and internal surfaces of the eccentric rings and the plain zones of the screws.

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.