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.

A vehicle includes a tilt rotor that is aft of a fixed wing and that is attached to the fixed wing via a pylon. A flight computer configured to instruct the tilt rotor to produce a maximum downward angle including by updating an actuator authority database associated with the flight computer to reflect the maximum downward angle, and generating a rotor control signal for the tilt rotor using the updated actuator authority database that reflects the maximum downward angle, wherein the maximum downward angle is adjustable.

An assembly of at least one extinguishing agent tank in the interior of an aircraft strut. The strut has an elongate chamber form extending in a longitudinal direction and includes a plurality of ribs which are spaced apart and arranged in parallel along the strut, each extending orthogonally to the longitudinal direction. The ribs are covered by lateral walls, at least one of the walls comprising a window opening into a space between two consecutive ribs, and via which a spherical extinguishing agent tank is installed in the interior of the strut. The assembly of the tank on the strut includes a frame arranged in the interior of the strut, facing the window and secured on each of the two consecutive ribs. The frame forms a support area on which the tank is supported. A system locks the extinguishing agent tank on the frame.

An assembly for reacting a thrust load from an engine, the assembly comprising a frame, a pin, an evener bar, and left and right thrust links. The frame includes an upper pin interface and a lower pin interface. The pin extends through the upper pin interface and the lower pin interface and includes an upper end and a lower end. The evener bar engages the lower end of the pin below the lower pin interface and connects the left and right thrust links to the pin. The pin is configured to react the thrust load at the lower pin interface and the upper pin interface thereby forming a distributed force couple between the lower pin interface and the upper pin interface.

An engine vibration isolation subframe for aircraft includes a forward frame and a forward beam connected to the forward frame. The forward beam includes a first end configured to connect to a first engine and a second end configured to connect to a second engine. An aft frame is disposed aft of the forward frame and includes a first aft beam connected to the aft frame and the first engine and a second aft beam connected to the aft frame and the second engine, where the second aft beam is disposed substantially opposite the first aft beam. At least one forward isolator assembly is connected to the forward frame and at least one aft isolator assembly is connected to the aft frame.

An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

An aircraft propulsion assembly including a front engine mount including a transverse beam which is connected to the engine via first and second convergent connection rods. This transverse beam includes an upper extension which is at least partially positioned opposite a front transverse reinforcement of the primary structure and which is connected thereto via at least one first connection element and right and left lateral extensions which are positioned at one side and another of the upper extension, each of them being connected via a least one second fixing element to a first wing of a right or left bracket, a second wing of the right or left bracket being connected via at least one third connection element to the primary structure.

A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.

A front engine attachment system for an engine of an aircraft. The front engine attachment system has 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 is made up of a front plate and a rear plate that are fastened together in a removable manner. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. Each link-rod system is fastened to the rear 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 assembly is disclosed including a first component, a second component, and a spacer component. The first component has a first interface surface. The second component has a second interface surface with a curvature different to the curvature of the first interface surface. The second component is connected to the first component such that the second interface surfaces faces the first interface surface. The spacer component is disposed between the first interface surface and the second interface surface and is configured to be pivotable relative to the first interface surface.