Abstract: An aircraft fuel system, comprising: a fuel tank; a fuel line; and an engine; wherein the fuel line includes a first conduit configured to carry fuel from the tank towards the engine, and a second conduit configured to carry fuel from the engine towards the tank, wherein one of the first conduit or the second conduit is disposed annularly around the other of the first conduit or the second conduit. Also, a method of operating the system. The system may be used to suppress ice formation in the first conduit and/or provide leakage detection.

Abstract: An aircraft fuel tank arrangement for the relief of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere is provided. The aircraft fuel tank arrangement comprises a removable cartridge received within a cartridge-receiving body located at least partially in the fuel tank, said cartridge comprising a first burstable member operable to rupture in the presence of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere which is greater than a predetermined pressure differential.

Abstract: A fluid flow control valve is housed within a canister (31) which is semi-permanently fixed in the wall (12) of a fuel tank, and has pipe connections (17, 18). The movable valve parts, including a valve sub-assembly (32, 33) and an electrical actuator (34), may be removed without requiring access to the fuel tank.

Abstract: An aircraft fuel tank system comprising an aircraft fuel tank and a time domain reflectometry (TDR) fuel gauge for measuring a filling level of fuel in the aircraft fuel tank. The TDR fuel gauge comprises an electromagnetic signal generator and a cable, the cable comprising a first cable part and a second cable part which are coupled in series to the signal generator. The first cable part extends downwardly within the fuel tank and the second cable part extends upwardly within the fuel tank. The first and second cable parts are arranged such that for at least one filling level the first cable part extends down into the fuel from an ullage space at a first location and the second cable part extends up out of the fuel into an ullage space at a second location which is spaced apart from the first location.

Abstract: A method of installing fuel system components in an aircraft wing in which the fuel system components are attached to ribs before the ribs are assembled into the wing. The ribs are structural ribs for the wing and may be assembled to form a combined rib and fuel system component assembly before the assembly is added to the wing.

Abstract: An aircraft fuel system, comprising: a fuel tank; a fuel line; and an engine; wherein the fuel line includes a first conduit configured to carry fuel from the tank towards the engine, and a second conduit configured to carry fuel from the engine towards the tank, wherein one of the first conduit or the second conduit is disposed annularly around the other of the first conduit or the second conduit. Also, a method of operating the system. The system may be used to suppress ice formation in the first conduit and/or provide leakage detection.

Abstract: An aircraft comprising a Rubens' tube for distributing gas within the aircraft. The Rubens' tube comprises a tube with a plurality of outlets; an inlet for feeding the gas into the tube; and a loudspeaker arranged to set up a standing acoustic wave within the tube. Typically the Rubens' tube is arranged to feed inert gas into a fuel tank of the aircraft.

Abstract: An aircraft fuel tank system comprising an aircraft fuel tank and a time domain reflectometry (TDR) fuel gauge for measuring a filling level of fuel in the aircraft fuel tank. The TDR fuel gauge comprises an electromagnetic signal generator and a cable, the cable comprising a first cable part and a second cable part which are coupled in series to the signal generator. The first cable part extends downwardly within the fuel tank and the second cable part extends upwardly within the fuel tank. The first and second cable parts are arranged such that for at least one filling level the first cable part extends down into the fuel from an ullage space at a first location and the second cable part extends up out of the fuel into an ullage space at a second location which is spaced apart from the first location.

Abstract: A fluid flow control valve is housed within a canister (31) which is semi-permanently fixed in the wall (12) of a fuel tank, and has pipe connections (17, 18). The movable valve parts, including a valve sub-assembly (32, 33) and an electrical actuator (34), may be removed without requiring access to the fuel tank.

Abstract: A aircraft fuel tank inerting arrangement is provided for providing oxygen-depleted gas to one or more aircraft fuel tanks, the aircraft fuel tank inerting arrangement comprising a gas inlet, an oxygen remover configured to remove oxygen from an oxygen-containing gas, thereby producing an oxygen-depleted gas, a first flow control valve and at least one gas outlet to deliver oxygen-depleted gas to an aircraft fuel tank, the gas inlet being in gaseous communication with, and upstream of, the oxygen remover, the oxygen remover being in gaseous communication with, and upstream of, the at least one outlet, the first flow control valve being operable to provide a variable rate of flow of oxygen depleted gas to at least one gas outlet.

Abstract: An aircraft fuel tank arrangement for the relief of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere is provided. The aircraft fuel tank arrangement comprises a removable cartridge received within a cartridge-receiving body located at least partially in the fuel tank, said cartridge comprising a first burstable member operable to rupture in the presence of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere which is greater than a predetermined pressure differential.

Abstract: An aircraft comprising a Rubens' tube for distributing gas within the aircraft. The Rubens' tube comprises a tube with a plurality of outlets; an inlet for feeding the gas into the tube; and a loudspeaker arranged to set up a standing acoustic wave within the tube. Typically the Rubens' tube is arranged to feed inert gas into a fuel tank of the aircraft.

Abstract: The present invention provides a method, device and apparatus for determining a quantity of fuel within a fuel tank having a drain valve penetrating a lower boundary of the fuel tank. The method includes inserting a pressure measurement probe having a pressure sensor into the drain valve to permit contact between the pressure sensor and fuel within the tank, and measuring a pressure of the fuel with the pressure sensor. The measured pressure is used to determine the quantity of fuel within the tank, e.g. by consulting look-up tables comprising data indicating the relationship between measured pressure and fuel quantity, or by using one or more conversion equations.

Abstract: A method of installing fuel system components in an aircraft wing is disclosed. An aircraft wing having a plurality of structural elements such as ribs which are joined together during assembly. The method includes the step of attaching at least some of the fuel system components to at least one of the structural elements prior to joining said structural elements together to assemble a wing. Also disclosed is a structural rib for an aircraft wing, configured to receive one or more fuel system components, and a combined structural rib and fuel system assembly.

Abstract: A container for housing an injectable fluid vial. The container includes a calculation aid formed specific to the injectable fluid vial. The container is formed from a bottom, a top, and an inset side wall therebetween with a resealable lid. The top includes an opening constructed and arranged to receive the fluid vial housing. Alternatively, the container is formed from two half sections that are hinged together for holding the fluid vial housing therebetween. An inner label is permanently attached to the sidewall having at least one row of dosing indicia coordinated with a base line indicia selected from the group of weight, age, fluid volume or area. An outer label is rotatably secured over said inner label with at least one transparent window allowing selective viewing of the dosing and base line indicia and predetermined dosing rate.

Abstract: A top loading container for housing a fluid vial is described. The top loading container includes a calculation aid formed specific to the fluid vial. The top loading container is formed from a bottom, a top, and an inset side wall there between. The top is adapted to be securable to a fluid vial so that the fluid vial rests in a suspended position within the interior of the top loading container. An inner label is permanently attached to the sidewall having at least one row of dosing indicia coordinated with a base line indicia selected from the group of weight, age, fluid volume or area. An outer label is rotatably secured over the inner label with at least one transparent window allowing selective viewing of the dosing and base line indicia and predetermined dosing rate.

Abstract: The present invention is directed toward a method of administering an oral solution containing one or more active ingredients, preferably formulations for non-prescription medicines, vital fluids, and/or nutritional supplements, optimally dosed based upon a patient's weight. The method includes providing an oral solution having an effective amount of one or more active ingredients; determining the weight of the individual, preferably to an individual less than 12 years old; and administrating an appropriate amount of the oral solution in a single dose dispensing unit in accordance with the weight determination of the individual, whereby the total amount of active ingredient administered corresponds to an effective amount of the active ingredient based on the individual's weight.

Abstract: The present invention is directed toward a method of administering an oral solution containing one or more active ingredients, preferably formulations for non-prescription medicines, vital fluids, and/or nutritional supplements, optimally dosed based upon a patient's weight. The method includes providing an oral solution having an effective amount of one or more active ingredients; determining the weight of the individual, preferably to an individual less than 12 years old; and administrating an appropriate amount of the oral solution in a single dose dispensing unit in accordance with the weight determination of the individual, whereby the total amount of active ingredient administered corresponds to an effective amount of the active ingredient based on the individual's weight.

Abstract: A container for housing an injectable fluid vial. The container includes a calculation aid formed specific to the injectable fluid vial. The container is formed from a bottom, a top, and an inset side wall therebetween with a resealable lid. The top includes an opening constructed and arranged to receive the fluid vial housing. Alternatively, the container is formed from two half sections that are hinged together for holding the fluid vial housing therebetween. An inner label is permanently attached to the sidewall having at least one row of dosing indicia coordinated with a base line indicia selected from the group of weight, age, fluid volume or area. An outer label is rotatably secured over said inner label with at least one transparent window allowing selective viewing of the dosing and base line indicia and predetermined dosing rate.

Abstract: A system and method for the transfer of an absent human's distinctive scent to a remote dependent. A pad, which acts as the transfer medium, is worn by the human to absorb its distinctive pheromones and odors. The pad is thereafter inserted into a pocket provided within a blanket. The blanket comprises fabric that includes fibers embedded with activated carbon for adsorbing undesired scent-masking odors.