The invention relates to a method for metering fuel in a fuel supply circuit of an aircraft engine, the circuit comprising a metering device for a fuel circuit of an aircraft engine comprising, downstream of a fuel pumping system and upstream of injectors: —a fuel inlet (E), —a metering device (FMV) and a cut-off device (HPSOV) arranged in series, —an adjustment valve (VR) arranged on a fuel recirculation branch, such that any excess fuel supplied by the pumping system is fed back into the fuel circuit, wherein at least one flow-metric sensor (WFM1) is arranged on the recirculation branch, a density value for the metered fuel is determined according to the sensor measurements and the metering device is controlled according to the fuel density value thus determined.

A pipe element suitable for use in a fuel system of an aircraft comprises an inner pipe and an outer pipe sealingly surrounding the inner pipe and connected to the inner pipe. The pipe element is constructed in one piece and is produced by a 3D printing process.

A tank defines an inner cavity and at least an opening. A filler tube device comprises a tube passing through the opening in the tank, the tube forming a joint with at least one degree of freedom with the tank such that the tube is displaceable relative to the tank. The tube has an open end in the inner cavity of the tank, and an opposite open end outside of the tank, whereby the tube defines a passage for filling the tank. A sealing component is in the inner cavity of the tank, the sealing component configured for collaborating with the open end of the tube when the tube is moved into engagement therewith to close the open end of the tube inside the tank in a protective position.

An aircraft gas transport system including a high pressure gas supply line having a supply valve, and an equilibrium gas line joined at junctions with the high pressure gas supply line upstream and downstream from the supply valve, and in flow communication with the high pressure gas supply line, the equilibrium gas line having an equilibrium valve and a flow restrictor, the equilibrium valve having an exit orifice and the flow restrictor being offset from the exit orifice of the equilibrium valve.

An aircraft gas transport system including a high pressure gas supply line having a supply valve, and an equilibrium gas line joined at junctions with the high pressure gas supply line upstream and downstream from the supply valve, and in flow communication with the high pressure gas supply line, the equilibrium gas line having an equilibrium valve and a flow restrictor, the equilibrium valve having an exit orifice and the flow restrictor being offset from the exit orifice of the equilibrium valve.

A method for the circulation of fuel in an aircraft uses at least one diaphragm pump having an undulating diaphragm that can undulate between two flanges, under the action of an actuator, for circulating the fuel between an admission line of the pump and an exhaust line of the pump.

A method for the circulation of fuel in an aircraft uses at least one diaphragm pump having an undulating diaphragm that can undulate between two flanges, under the action of an actuator, for circulating the fuel between an admission line of the pump and an exhaust line of the pump.

A sensor assembly includes a capacitive probe, a resistive element, an electronic circuit and an optical interface. A capacitance of the capacitive probe and a resistance of the resistive element are indicative of characteristics of an environment. The electronic circuit is configured to convert the capacitance and the resistance into optical data. The optical interface is configured to provide the optical data to an optical link.

To provide a fuel pipe of an aircraft that makes it possible to maintain temperature of fuel in the fuel pipe at appropriate temperature while giving consideration to reliability that is constantly required for the aircraft. A fuel pipe provided in an airframe of the aircraft includes: an inner pipe defining a flow path through which fuel flows; and an outer pipe surrounding an outer periphery of the inner pipe. A gap is provided between the outer periphery of the inner pipe and an inner periphery of the outer pipe. The inner pipe is made of a rubber material, and the outer pipe is made of a metal material.

A gasket for placement between a base of an aircraft structure and the underside of a workpiece, such as an aircraft antenna, is disclosed. The gasket has a cured polyurethane elastomeric gel body with a multiplicity of holes therethrough. The body typically has a flat lower surface and upstanding side walls, but the top surface is non-flat. The top surface may have sloped areas or raised tabular areas or a combination. The gel body may also have a skeleton member, such as a flexible metallic screen or other woven member. When the gasket is placed between the aircraft base and the workpiece, threaded on fasteners, and the fasteners torqued down, the non-flat upper surface will flow such that, at proper torque setting, it fully coats and fully covers the underside of the workpiece and, typically, makes contact with the screen or skeleton member, which also makes contact with the upper surface of the base.