Abstract: An aircraft refueling system incorporates a fuel port adapter configured to allow the use of jet fuel nozzle spout but prevent the use of avgas nozzle spout. The device has an opening that configured to receive a standard jet fuel nozzle spout. The device also includes a blocking plate that prevents a smaller, round standard avgas nozzle spout from being inserted into the opening. In addition, the device includes one or more spring-loaded flapping doors to prevent incorrect refueling while the jet fuel nozzle spout is not inserted through the flapping doors.

Abstract: The inert gas generating system includes a compressed air source, a cooling air source, and a separation module. The separation module includes first and second inlets and outlets. The first inlet is coupled to the compressed air source. The first outlet is coupled to the first inlet via a bundle of hollow fiber membranes. The second inlet is coupled to the cooling air source, and the second outlet is coupled to the second inlet via a space surrounding the bundle of hollow fiber membranes.

Abstract: A modular, on-board, inert gas generating system for aircraft is disclosed in which main components such as a heat exchanger, filter, air separation module, and turbocharger are provided in a modular unit sized to provide a variable flow of nitrogen-enriched air to the aircraft spaces to be inerted. For different inert gas requirements, for example in larger aircraft, multiple modular units may be provided without redesigning the basic system. A method for inerting fuel tanks, cargo holds and other void spaces using the modular approach and turbocharged engine bleed air is also disclosed.

Abstract: A modular, on-board, inert gas generating system for aircraft is disclosed in which main components such as a heat exchanger, filter, air separation module, and turbocharger are provided in a modular unit sized to provide a variable flow of nitrogen-enriched air to the aircraft spaces to be inerted. For different inert gas requirements, for example in larger aircraft, multiple modular units may be provided without redesigning the basic system. A method for inerting fuel tanks, cargo holds and other void spaces using the modular approach and turbocharged engine bleed air is also disclosed.

Abstract: The piston engine cooling system includes multiple pistons rotatably coupled to a crankshaft. Each piston includes a piston head defining a cooling chamber therein, and a connecting rod coupled to the piston head. The connecting rod includes a connecting rod inlet channel therein allowing oil to enter the cooling chamber, and a connecting rod outlet channel receiving oil exiting the cooling chamber. The crankshaft defines a crankshaft inlet channel allowing oil to flow through the connecting rod inlet channel, and a crankshaft outlet channel receiving oil flowing through the connecting rod outlet channel.

Abstract: A modular, on-board, inert gas generating system for aircraft is disclosed in which main components such as a heat exchanger, filter, air separation module, and turbocharger are provided in a modular unit sized to provide a variable flow of nitrogen-enriched air to the aircraft spaces to be inerted. For different inert gas requirements, for example in larger aircraft, multiple modular units may be provided without redesigning the basic system. A method for inerting fuel tanks, cargo holds and other void spaces using the modular approach and turbocharged engine bleed air is also disclosed.

Abstract: The gas monitoring system may include a gas line, an oxygen sensor, a filter, a pump, a indicator, and a controller. The gas line is configured to convey gas from a space configured to receive inert gas to a location remote from the space. The oxygen sensor is fluidly coupled to the gas line at the location. The oxygen sensor is configured to determine a partial pressure of oxygen present in the gas. The filter is fluidly coupled to the gas line between the space and the location. The filter is configured to remove combustible contaminants from the gas before it reaches the oxygen sensor. The controller is electrically coupled to the oxygen sensor and to the indicator. The controller is configured to activate the indicator when the partial pressure of oxygen exceeds a predetermined level.

Abstract: A drain valve including a housing, a poppet, a seal, a follower pin, and a biasing mechanism. The housing defines a passage there-through from a first end to a second end, a cam surface at the second end with at least two detents therein, and at least one slot in the housing fluidly coupling the passage to exterior of the housing. The poppet is disposed within the passage. The seal is disposed between the housing and the poppet. The follower pin is coupled to the poppet near the poppet second end. The follower pin is configured to move along the cam surface and settle in at least one of the at least two detents. The spring is configured to bias the poppet away from the second end.

Abstract: The inert gas generating system includes a compressed air source, a cooling air source, and a separation module. The separation module includes first and second inlets and outlets. The first inlet is coupled to the compressed air source. The first outlet is coupled to the first inlet via a bundle of hollow fiber membranes. The second inlet is coupled to the cooling air source, and the second outlet is coupled to the second inlet via a space surrounding the bundle of hollow fiber membranes.

Abstract: A modular, on-board, inert gas generating system for aircraft is disclosed in which main components such as a heat exchanger, filter, and an air separation module, and a pressure scheduling valve are provided in a modular unit sized to provide a variable flow of nitrogen-enriched air to the aircraft spaces to be inerted. For different inert gas requirements, for example in larger aircraft, multiple modular units may be provided without redesigning the basic system. A method for inerting fuel tanks, cargo holds and other void spaces using the modular approach and pressure scheduling valve is also disclosed.

Abstract: A modular, on-board, inert gas generating system for aircraft is disclosed in which main components such as a heat exchanger, filter and air separation module are provide in a modular unit sized to provide predetermined flow of nitrogen-enriched air to the aircraft spaces to be inerted. For different inert gas requirements, for example in larger aircraft, multiple modular units may be provided without redesigning the basic system. A method for inerting fuel tanks, cargo holds and other void spaces using the modular approach is also disclosed.

Abstract: A modular, on-board, inert gas generating system for aircraft is disclosed in which main components such as a heat exchanger, filter and air separation module are provide in a modular unit sized to provide predetermined flow of nitrogen-enriched air to the aircraft spaces to be inerted. For different inert gas requirements, for example in larger aircraft, multiple modular units may be provided without redesigning the basic system. A method for inerting fuel tanks, cargo holds and other void spaces using the modular approach is also disclosed.

Abstract: A cyclonic separator is provided for separating a mixture containing three phases of mater into the constituent phases. The separator contains three concentric cylindrical chambers in fluid connection with each other. These three chambers are an upper chamber, a lower chamber, and an outlet chamber. Tangential fluid inlets and outlets are provided to minimize pressure loss across the separator. A radially disposed annular debris collector is located at the junction of the upper and lower chambers, and a gas support platform for directing gas out of the separator is disposed in the outlet chamber a sufficient distance from the debris collector so as to prevent turbulence adjacent the debris collector.

Abstract: A positive lift pin means is provided which operates to force open an aircraft drain valve door at least to an unsealed position when the door is released from its closed position.

Abstract: A fuel cap is disclosed which is particularly effective in not only addressing the problem of permitting reliable relief pressure, but also in providing adequate sealing for varying environmental conditions, such as extreme pressure, temperature and swelling. The cap includes a plug member having at its lower end an elastomer sealing member integrally molded into a groove that extends around the periphery of the cap. Moreover, the sealing member is uniquely oblong shaped such that with increasing internal pressure within the tank the sealing member is deformed such as to assist in the sealing.

Abstract: A static discharger for discharging charge accumulation from the surface of the wing of an aircraft, comprises a generally flat layer of non-conductive material which is dimensioned and configured so that it can be secured to a portion of the wing surface and so as to conform generally to the shape of the wing surface. A generally flat base member is dimensioned and configured so as to be capable of being placed in conforming relationship with at least a portion of the surface of the layer of non-conductive material which insulates the base member from electrically contacting the surface of the aircraft. A plurality of strands formed of a discharging material are embedded in the base member. The plurality of strands are electrically connected to the wing surface of the aircraft so that charge accumulation may pass from the wing surface of the aircraft to the plurality of strands and be discharged at the trailing ends of the strands.

Abstract: A filler cap assembly including a filler cap and an adapter member for attachment to the opening in a fuel tank. The adapter has a central opening therein for receipt of the filler cap. The inner periphery of the adapter about the central opening has a raised convex seat and the cap has a flanged outer periphery with the undersurface grooved to form a concave surface mating with the raised seat of the adapter. The cap also includes seal means along the concave surface of the flange for sealing against the seat of the adapter.