Abstract: Methods and processes are described that form ceramic wear surfaces on the outer surface of a cast part. A mold having a mold cavity is provided. The mold cavity may be washed using a refractory wash to provide for a smoother finish to the surface of the cast part and to maintain mold integrity. An adhesive is applied to predetermined locations in which increased wear during the use of the cast parts is anticipated to occur. Ceramic material may be applied to the predetermined locations by various means. A mask may be used to remove excess material from areas other than the predetermined locations. A molten metal is poured into the mold cavity and allowed to cool to form a cast part with a ceramic wear surface.

Abstract: An apparatus and methods for controlling the location and distribution of loose ceramic particles in a ceramic metal composite component formed via casting. A retaining structure that may include loose ceramic particles is placed in a casting mold at a desired location for ceramic particles in the composite component prior to pouring molten metal into the casting mold. Alternatively, the loose ceramic particles may be introduced into the mold concurrently with the molten metal.

Abstract: A tank assembly including an upright tank, a lid, a temperature control system, and an actuator assembly. The tank includes a closed bottom end, an open top end, a tank sidewall extending between the bottom and top ends and defining a tank interior having an interior surface, and an elliptical cross-sectional shape. The lid is positionable to seal closed the tank interior. The temperature control system may be operable to control a temperature of a substance retained within the tank interior. The lid may have a peripheral surface that is configured to seal with the interior surface of the tank. The lid may also have an elliptical shape.

Abstract: Chutes and other components may include composite liners to improve performance. Composite liners generally comprise a base metal having a ceramic material embedded therein. The composite liners exhibit improved resistance to wear and, therefore, have a longer usable life than liners formed of the base metal alone.

Abstract: A equipment service apparatus suited for use in servicing ground support equipment (GSE) or aircraft ground equipment (AGE). The apparatus includes a plurality of features for use in servicing and maintaining the GSE/AGE where the GSE/AGE is in use servicing an aircraft so that the GSE/AGE is not itself required to be transported to a remote location for servicing and/or maintenance. The apparatus may be constructed as a towable cart. The apparatus may include a fuel tank, a pump system configured to add fuel to or remove fuel from the fuel tank, and a fuel valve assembly operable to control fuel flow into and out of the fuel tank. The apparatus may also include a container storage portion configured to retain a plurality of removable fluid storage containers, at least one power source, and a power control system operable to control power from the at least one power source to operate at least some features of the equipment service apparatus.

Abstract: A tank assembly including a tank, a lid, and an actuator assembly. The tank defines a tank volume and has an opening defined therein. The lid is sized to cover the opening in sealing engagement with the tank. The actuator assembly includes a first actuator arrangement and a second actuator arrangement. The first actuator arrangement is configured to move the lid into and out of sealing engagement with the tank. The second actuator arrangement is configured to move the lid between a first position in alignment with the opening, and a second position removed from alignment with the opening to permit access into the opening.

Abstract: The present invention provides methods and apparatus for containing aircraft fuel. According to some embodiments the apparatus includes a structural connector comprising an open shape, a first surface and a second surface, a seal defining a suction area disposed in the first surface, and a boot extending from the structural connector. The boot may comprise a lateral opening. The boot includes first and second ends, such that the first end of the boot may be attached to the structural connector and the second end may be spaced from the structural member. According to some embodiments the second end comprises a center offset laterally from the center of the structural connector.

Abstract: A method and apparatus for defueling an aircraft. The apparatus includes a defueling fitting comprising one or more structural connectors, which may include one or more suction cups. The suction cups are disposed in a mount. The suction cups may be raised from a surface in the mount and arranged in a non-circular pattern to facilitate connection to contoured surfaces. An actuator assembly may be attached to the mount for opening an aircraft defueling valve. The suction cups may be operatively connected to a vacuum source to connect the defueling fitting to an aircraft body, with the actuator assembly positioned at the aircraft defueling valve. The defueling fitting facilitates safe and convenient defueling of aircraft, even aircraft with significantly contoured surfaces.

Abstract: A method and apparatus for defueling an aircraft. The apparatus includes a defueling fitting comprising one or more structural connectors, which may include one or more suction cups. The one or more structural members are attached to a mount. The mount may be of any shape, including generally straight, angled, polygonal, or circular. An actuator assembly is attached to the mount for opening an aircraft defueling valve. The first and second suction cups are operatively connected to a vacuum source to connect the defueling fitting to an aircraft body, with the actuator assembly positioned at the aircraft defueling valve. The defueling fitting facilitates safe and convenient defueling of certain aircraft that have recessed or covered fuel drain valves. For example, the Boeing C-17 has fuel drain valves that are recessed behind doors, heretofore presenting a great obstacle to appropriate defueling.

Abstract: An apparatus and method for defueling and aircraft. The apparatus includes a vacuum fuel tank comprising a first vacuum generator, a defueling hose in fluid communication with the vacuum fuel tank, a first defueling fitting attached to the first defueling hose, and a second vacuum generator operatively connected to the first defueling fitting. By providing both a first and a second vacuum generator, the defueling fitting can be attached and detached from an aircraft independent of the suction used to withdraw fuel from an aircraft. According to some embodiments, there may be multiple defueling hoses and additional vacuum generators. Further, some embodiments include a telescoping funnel that can be selectively isolated from the vacuum fuel tank so that the tank can be held at vacuum pressure.

Abstract: Disclosed is an impact shoe system generally for use in rock crushers, namely centrifugal rock crushers. This impact shoe system generally includes a plurality of wear inserts patterned within the impact shoe to substantially reduce the wear on the impact shoe, as well as to increase the useful life of the impact shoe.

Abstract: An upflow clarifier comprises an enclosure defining a bounded volume for holding liquid. An inlet is coupled to the enclosure, and an outlet is coupled to the enclosure above the inlet. A barrier is provided in the enclosure, between the inlet and the outlet. The barrier has a plurality of apertures therethrough, and the barrier defines an upper compartment above the barrier and a lower compartment below the barrier. A plurality of filter membranes are respectively mounted to the apertures, wherein liquid flowing through the apertures flows through the filter membranes. The filter membranes extend upwardly from the barrier.

Abstract: An upflow clarifier comprises an enclosure defining a bounded volume for holding liquid. An inlet is coupled to the enclosure, and an outlet is coupled to the enclosure above the inlet. A barrier is provided in the enclosure, between the inlet and the outlet. The barrier has a plurality of apertures therethrough, and the barrier defines an upper compartment above the barrier and a lower compartment below the barrier. A plurality of filter membranes are respectively mounted to the apertures, wherein liquid flowing through the apertures flows through the filter membranes. The filter membranes extend upwardly from the barrier.

Abstract: A waste water treatment system includes a first stage oil separator having a plurality of conically shaped members disposed inside an enclosure. The conically shaped members are preferably made of polypropylene. Oil within the waste water coalesces upon contacting the conically shaped members. Waste water is circulated in vortical flow paths between the conically shaped members to lengthen the flow path of the waste water between the members thereby promoting coalescence of oil. A second stage oil separator involves a bead pack container unit filled with polypropylene beads through which waste water passes to remove residual oil and debris from the waste water coming from the first stage oil separator.

Abstract: A liquid clarifier in the form of an enclosure in which a conical filter membrane is mounted. An inlet is mounted to the enclosure below the conical filter membrane and an outlet is mounted to the enclosure above the membrane so than an upflow of liquid is created during filtering. The upflow causes the liquid to sweep across the conical filter membrane to prevent accumulation of particulate matter on the membrane. A conical baffle is coupled to the inlet to reduce turbulence of the liquid at a lower end of the enclosure to promote separation by gravity of the particles from the liquid.

Abstract: A defueling fitting is adapted to facilitate removal of fuel from an aircraft fuel cell through a flush-mounted fuel drain having a depressable valve stem. It includes a flange with spaced circumferential seals. A vacuum outlet leads between the seals to facilitate attachment of the flange to an exterior aircraft surface surrounding a fuel drain. A separable probe includes a pin actuator for depressing the valve stem of the fuel drain and one or more liquid passages for directing draining fuel through the flange through an attached hose. The method for defueling involves first attaching the flange to the aircraft surface surrounding a fuel drain by application of reduced pressure between the circumferential seals and subsequently depressing the valve stem of the fuel drain to direct fuel through an enclosed liquid passage.

Abstract: A lid is described for floating on the surface of a liquid in a storage tank. The lid spans the tank interior and includes an inflatable peripheral seal arrangement selectively operable to seal the liquid within the tank upon inflation and, on deflation, will allow the lid to float freely on the surface of the liquid. The lid is formed of two plates spaced apart by a circumferential rim defining a flotation cavity. Buoyance of the lid is such that the inflatable seal is carried above the liquid surface. The bottom plate is arched toward the top plate of the lid by a tension member extending between the two. The tension member is hollow and open to the area below the lid. The pressure relief valve is mounted in the hollow passageway to selectively allow escape of pressurized gas from below the lid. The seal arrangement is made so that the liquid level always remains below the sealed area between the lid and tank walls.