Aspects of the invention regard an aircraft including: a gas turbine engine, the gas turbine engine including an intake, a nacelle, and gas turbine engine components located radially inside the nacelle; and an aircraft structure. The intake of the gas turbine engine is mounted to the aircraft structure in a manner such that its position can be adjusted. The nacelle and the gas turbine engine components located radially inside the nacelle are rigidly mounted to the aircraft structure. Other aspects of the invention regard a gas turbine engine and a method for adjusting the input of air flowing into a gas turbine engine.

Aspects of the invention regard an aircraft including: a gas turbine engine, the gas turbine engine including an intake, a nacelle, and gas turbine engine components located radially inside the nacelle; and an aircraft structure. The intake of the gas turbine engine is mounted to the aircraft structure in a manner such that its position can be adjusted. The nacelle and the gas turbine engine components located radially inside the nacelle are rigidly mounted to the aircraft structure. Other aspects of the invention regard a gas turbine engine and a method for adjusting the input of air flowing into a gas turbine engine.

A wear resistant composite material includes a first thickness of material, a second thickness of material, and a thickness of wear indicator located between and engaging the first thickness of material and the second thickness of material. The thickness of wear indicator has a colorant therein.

A wear resistant composite material includes a first thickness of material, a second thickness of material, and a thickness of wear indicator located between and engaging the first thickness of material and the second thickness of material. The thickness of wear indicator has a colorant therein.

A rotary wing aircraft with a fuselage that forms an aircraft interior region, the fuselage comprising an upper primary skin that separates the aircraft interior region from an aircraft upper deck arranged above the fuselage, wherein the aircraft upper deck comprises an engine accommodating region with a firewall arrangement, the engine accommodating region accommodating at least one aircraft engine within the firewall arrangement, wherein the firewall arrangement comprises at least one gasket for tightening pass-through of a torque tube that connects the at least one aircraft engine to a main gear box of the rotary wing aircraft, and wherein the at least one gasket comprises at least two fire proof shells and a ring-shaped flexible fire proof bellows.

A method of operating an aircraft including takeoff of an aircraft; transitioning the aircraft to a forward flight configuration by increasing an amount of forward propulsive force generated by a propeller assembly from equal to or less than 10% to at least 80% of a propeller assembly maximum and reducing the upward propulsive force generated by rotor assemblies from at least 80% of a rotor assembly maximum to equal to or less than 10%; flying the aircraft from a first location to a second location in the forward flight configuration; and transitioning the aircraft to a landing configuration at the second location by decreasing an amount of forward propulsive force generated by the propeller assembly and increasing the upward propulsive force generated by the rotor assemblies.

An aircraft propulsion unit includes a turbojet engine, a lateral pylon connected to the fuselage of the aircraft, and a nacelle on the lateral pylon. The nacelle includes an upstream section having an air intake, a downstream section housing a reverse thrust device, and a middle section having two fan half-cowls surrounding a fan housing of the turbojet engine, and when said half-cowls are in a closed position defining an aerodynamic continuity between the upstream and downstream sections. The fan half-cowls include a maintenance half-cowl positioned under the horizontal median plane of the nacelle, able to move between the closed position and an open position allowing access to the turbojet engine for maintenance operations on the turbojet engine. The nacelle further includes at least one standby lock, designed to hold the maintenance half-cowl in a position intermediate to the closed and open positions.

An aircraft propulsion unit includes a turbojet engine, a lateral pylon connected to the fuselage of the aircraft, and a nacelle on the lateral pylon. The nacelle includes an upstream section having an air intake, a downstream section housing a reverse thrust device, and a middle section having two fan half-cowls surrounding a fan housing of the turbojet engine, and when said half-cowls are in a closed position defining an aerodynamic continuity between the upstream and downstream sections. The fan half-cowls include a maintenance half-cowl positioned under the horizontal median plane of the nacelle, able to move between the closed position and an open position allowing access to the turbojet engine for maintenance operations on the turbojet engine. The nacelle further includes at least one standby lock, designed to hold the maintenance half-cowl in a position intermediate to the closed and open positions.

In order to further benefit from the principle of boundary layer ingestion by engines of an aircraft assembly, the rear portion of the fuselage of this aircraft assembly includes a front portion which splits up into at least two distinct rear portions, spaced apart from each other, and each integrating the rotary ring of the receiver of one of the engines.

A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.