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.

The invention relates to: Control circuit (1) for an electrical device (2), said control circuit (1) receiving as input a discrete electrical control signal (CMD), the control circuit (1) comprising a source (11) of voltage (±V) configured so as to supply the circuit according to a negative or positive voltage; a switch (12) normally closed in the absence of any discrete electrical control signal (CMD) and configured so as to isolate the electrical device from the voltage source as a function of the electrical control signal (CMD), said switch being connected between the voltage source and the electrical device (2); the switch (12) being sensitive to the discrete electrical control signal (CMD) for just one sense of voltage.

A flexible fuel bladder assembly for an aircraft includes a flexible fuel bladder positioned at an airframe and having an opening to allow a flow of fuel into and/or out of the fuel bladder. A breakaway valve is operably connected to the fuel bladder at the opening to control a flow of fuel therethrough. A non-contacting or loose fitting reaction feature is affixed to the airframe and is interactive with the breakaway valve such that movement of the breakaway valve relative to the reaction feature results in breakage of a valve body of the breakaway valve and closure of the breakaway valve to prevent flow of fuel therethrough while also allowing for a second reaction mode to cause breakage of a valve body should the connecting hose be pulled relative to the breakaway valve.

A vehicle fuel tank assembly including a tank for storing fuel and a sensor device disposed inside the tank. The sensor device is integrated with a component of the tank. The sensor device detects the presence of a plurality of different chemical and/or biological entities in fuel stored in the tank. The plurality of different chemical and/or biological entities are suitable for use in determining whether at least two different types of contaminant are present in the fuel.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

A pipe joint with a socket, and a pipe fitted into the socket. An annular seal is compressed between the socket and the pipe. The seal is electrically conductive and resiliently flexible. The socket or the pipe has a recess which houses the seal. The recess has a ridge in a base of the recess and the seal has a groove which extends around a radial periphery of the seal. The ridge fits into the groove to fool proof the installation, such that a standard non-conductive O-ring seal is more difficult to install in error.

In some examples, an air treatment system includes a filter, an ozone sensor, and a separator configured to separate air into a nitrogen-enriched gas and an oxygen-enriched gas. The filter is configured to remove ozone from an air stream and supply filtered air to the separator. The ozone sensor is configured to sense an ozone level of the filtered air issuing from the filter prior to encountering the separator. The air treatment system may include processing circuitry configured to monitor the ozone level sensed. The air treatment system may be part of an inerting system configured to supply the nitrogen-enriched gas to an ullage space of a fuel tank.

An isolator fitting for an opening in a metallic rib of an aircraft wing. The isolator fitting has first isolator mountable to the rib to position a first isolator opening in alignment with the opening of the rib. A second isolator is mountable to the rib and has a nut housing segment defining a second isolator opening to be positioned in alignment with the opening of the rib. A conduit extends between a first end and a second end, and a nut is mountable about an outer surface of the conduit to abut against the first isolator and mount the conduit thereto. The conduit is positionable to extend through the opening of the rib and through the first and second isolator openings to position the nut within the nut housing segment of the second isolator such that the nut housing segment is positioned between the nut and the rib.