A turboprop gas turbine engine mountable to an aircraft has an engine core and a gearbox driving a propeller, the engine core and the gearbox being enclosed within a nacelle. The propeller is located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft. An air intake is disposed within the nacelle and formed to direct ambient air into the engine core. The air intake includes an air inlet duct, having a forward-facing intake inlet receiving the ambient air, with an upstream section and a downstream section. The upstream section is in fluid communication with the intake inlet and extends downstream from the intake inlet. The downstream section fluidly connects to and directs air from the upstream section into the engine air inlet. A second air outlet duct is located within the nacelle and directs air into an air-cooled-oil-cooler (ACOC).

A system includes an inboard tiltrotor subsystem and an outboard tiltrotor subsystem. The inboard tiltrotor subsystem includes an inboard pylon, an inboard tiltrotor, and a single and non-redundant drivetrain. The outboard tiltrotor subsystem includes an outboard pylon that is coupled to a wing and an outboard tiltrotor. The outboard tiltrotor has a range of motion and is coupled to the wing via the outboard pylon, such that the outboard tiltrotor is aft of the wing. The outboard tiltrotor subsystem further includes a redundant drivetrain (which has a plurality of motors and a plurality of motor controllers) that drives one or more blades and the one or more blades.

An assembly of a pylon and of an engine with a rear engine attachment having two fittings, wherein each one has a shoe fastened to a lower spar of the pylon, two transverse arms, one front and one rear, which are as one with the shoe and offset such that the front transverse arm, respectively rear transverse arm, of one fitting bears in planar fashion against the front transverse arm, respectively rear transverse arm, of the other fitting, wherein each transverse arm is pierced with a bore, wherein the two front transverse arms and the two rear transverse arms are spaced apart parallel to the longitudinal direction and thus form a female clevis, and wherein the assembly also has a lower rod mounted articulated in the female clevis and on the engine. With such an assembly, the number of components is reduced.

An engine pylon for an aircraft and comprising an inverted U-shaped upper spar with two lateral walls, a U-shaped lower spar with two lateral walls, where the free ends of the lateral walls of the spars are adjacent, an arrangement to the free end of a lateral wall of one spar to the free end of the lateral wall of the other spar, and ribs between the spars where each has a top end fixed to the lateral walls of the upper spar and a bottom end fixed to the lower spar. Such an engine pylon thus offers a reduced number of component parts and a single row of fixings per side, enabling a saving in weight and in assembly time.

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 assembly of a pylon and of a wing of an aircraft, the pylon including a primary structure with a rear face and an upper spar. The assembly includes a rear fastening system including a pair of vertical shackles articulated between the rear face of the primary structure and a first shoe fastened to the wing, wherein the shackles are fastened to the primary structure by a clevis-type connection, and a pair of transverse shackles articulated between the rear face of the primary structure and a second shoe fastened to the wing, wherein the shackles are fastened to the primary structure by a clevis-type connection. With such an assembly, the bulk of the rear fastening system is reduced.

A duct for a ducted-rotor aircraft may include internal structural components such as a spindle that is supported by a fuselage of the aircraft, first and second annular spars that are attached to an end of the spindle, a central hub that supports a motor of the aircraft, a plurality of stators that extend from the central hub to the second spar, and a plurality of ribs that are attached to the first spar and the second spar at respective opposed ends. The spindle may include an attachment interface to which the first and second spars are attached. The attachment interface may be disposed at the second end of the spindle. The attachment interface may define first and second arc-shaped planar surfaces to which the first and second spars, respectively, are attached.

An assembly for mounting an aircraft engine to an aircraft includes an engine casing flange having a first annular wall extending radially to terminate at an annular rim. A second flange of an additional engine component mounted aft of the engine casing includes a second annular wall. An aft mount bracket has an annular body extending uninterrupted about the center axis and a spigot extending axially from the annular body, the spigot extending circumferentially about an entire circumference of the annular body. The aft mount bracket is axially disposed between the engine casing flange and the additional engine component, with corresponding holes in the first annular wall, second annular wall and aft mount bracket being circumferentially aligned, and the spigot radially abutting the annular rim of the engine casing flange.

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.

An engine support truss assembly for aircraft includes a mounting plate having a front side and a back side opposite the front side, a truss structure mechanically coupled to the front side of the mounting plate, and a backup structure mechanically coupled to the back side of the mounting plate. The truss structure includes a plurality of structural members each including precipitation-hardened stainless steel. The backup structure is configured to provide mechanical support to the truss structure.