Abstract: A fluid assembly comprising: a first conduit extending in an axial direction and configured to carry a fluid, a double walled outer second conduit extending in the axial direction; the second conduit having an inner wall and outer wall and a first interspace between the inner and outer walls, wherein the first conduit is housed inside the second conduit to form a second interspace between the first conduit and the inner wall of the second conduit.

Abstract: A method of controlling a pressure in a hydrogen fuel tank of an aircraft hydrogen fuel system. The hydrogen fuel tank stores hydrogen fuel. The method comprises receiving leak information indicative of a leak of hydrogen fuel from the hydrogen fuel system. The method also comprises, based on the leak information received, causing control of the pressure in the hydrogen fuel tank.

Abstract: A landing gear system for an aircraft includes a retractable landing gear assembly, a hydraulic actuator for actuating movement part, for example a bogie of the landing gear assembly, and an accumulator associated with the actuator. The accumulator comprises a volume of pressurised gas separated from hydraulic fluid by a separator piston. Travel of the separator piston beyond a certain position is indicative of a fault. The accumulator includes a snubbing device that acts to slow movement of the separator piston beyond that position. A monitoring system measures the time taken for the movement of the landing gear part effected by the hydraulic actuator. If the measured time is longer than a threshold time, that is indicative of a possible fault in the accumulator, that might, without the snubbing, remain undetected and/or hidden from view.

Abstract: A landing gear system for an aircraft includes a retractable landing gear assembly, a hydraulic actuator for actuating movement part, for example a bogie of the landing gear assembly, and an accumulator associated with the actuator. The accumulator comprises a volume of pressurised gas separated from hydraulic fluid by a separator piston. Travel of the separator piston beyond a certain position is indicative of a fault. The accumulator includes a snubbing device that acts to slow movement of the separator piston beyond that position. A monitoring system measures the time taken for the movement of the landing gear part effected by the hydraulic actuator. If the measured time is longer than a threshold time, that is indicative of a possible fault in the accumulator, that might, without the snubbing, remain undetected and/or hidden from view.

Abstract: A computer-implemented method for determining a configuration of a plurality of components in a systems installation which satisfies one or more constraints.