Abstract: An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

Abstract: A cargo carrier removably attaches to a square hitch receiver on the back of a vehicle. The cargo carrier is collapsible when not in use. A base plate has a series of first arms pivotally attached thereto each first arm extending outwardly for use and secured thereat and folding upwardly for storage. A removable plate secures the first arms in the extended position. A second arm is attached to an outer end of a first arm and pivots between an extended position extending upwardly from the first arm and a collapsed position flush against the first arm. Each second arm is lockable in its extended position. A flexible cable is attached to the distal end of each second arm to help retain cargo within the device.

Abstract: Methods, systems, and products for determining performance of a software entity running on a data processing system. The method comprises allowing extended execution of the software entity without monitoring code. The method also comprises intermittently sampling behavior data for the software entity. Intermittently sampling behavior data may be carried out by injecting monitoring code into the software entity to instrument the software entity, collecting behavior data by utilizing the monitoring code, and removing the monitoring code. The method also comprises repeatedly performing iterations of the allowing and sampling steps until collected behavior data is sufficient for diagnosing performance of the software entity. The method may further comprise analyzing the collected behavior data to diagnose performance of the software entity.

Abstract: A phase change ink formulation comprising an ink base, carbon black pigment and a poly(hydroxystearic acid) derived dispersant.

Abstract: A method and ground support equipment (GSE) for attaching an engine core to an engine fan module on an aircraft pylon. The GSE may comprise GSE supports and lifting components attached to the pylon, two suspension rails attached to the lifting components, two translating rails translatably attached to the two suspensions rails and fixedly attached to opposite sides of the engine core, and two alignment fittings fixed to the engine fan module. The method of using the GSE may comprise lifting the engine core vertically using the lifting components and anchoring the suspension rails to the alignment fittings. The translating rails and engine core may then be translated in an aft-to-forward direction such that portions of the translating rails engage portions of the alignment fittings to cooperatively guide the translating rails into a final forward position in which the engine core is aligned relative to the engine fan module.

Abstract: A prefetch optimizer tool for an information handling system (IHS) may improve effective memory access time by controlling both hardware prefetch operations and software prefetch operations. The prefetch optimizer tool selectively disables prefetch instructions in an instruction sequence of interest within an application. The tool measures execution times of the instruction sequence of interest when different prefetch instructions are disabled. The tool may hold hardware prefetch depth constant while cycling through disabling different prefetch instructions and taking corresponding execution time measurements. Alternatively, for each disabled prefetch instruction in the instruction sequence of interest, the tool may cycle through different hardware prefetch depths and take corresponding execution time measurements at each hardware prefetch depth.

Abstract: An aircraft nacelle comprising an outer cowl and an inner cowl located inward of the outer cowl with an air flow path formed therebetween. The inner cowl may comprise a forward portion and an aft portion slidable in a forward-to-aft direction via one or more actuators. When translated aftward, the aft portion may decrease the area of the nacelle's fan duct nozzle. The greatest radial distance between the inner cowl and a center axis of the nacelle may occur at or forward of a location in which the forward and aft portions overlap each other. The forward portion may be comprised of a different material than the aft portion.

Abstract: An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

Abstract: An aircraft nacelle having a fixed structure fixed relative to an aircraft pylon, a translating thrust reverser sleeve translatable aftward, relative to the fixed structure, and a translating variable area fan nozzle (VAFN) panel translatable aftward, relative to the translating thrust reverser sleeve. The nacelle may also include a VAFN actuator mounted on the translating thrust reverser sleeve and a VAFN drive unit attached to the fixed structure. The VAFN drive unit may be coupled to drive the VAFN actuator via first and second coupling components when the translating thrust reverser sleeve is stowed. When the translating thrust reverser sleeve is deployed, the first and second coupling components may decouple, disconnecting the VAFN drive unit from the VAFN actuator.

Abstract: A prefetch optimizer tool for an information handling system (IHS) may improve effective memory access time by controlling both hardware prefetch operations and software prefetch operations. The prefetch optimizer tool selectively disables prefetch instructions in an instruction sequence of interest within an application. The tool measures execution times of the instruction sequence of interest when different prefetch instructions are disabled. The tool may hold hardware prefetch depth constant while cycling through disabling different prefetch instructions and taking corresponding execution time measurements. Alternatively, for each disabled prefetch instruction in the instruction sequence of interest, the tool may cycle through different hardware prefetch depths and take corresponding execution time measurements at each hardware prefetch depth.

Abstract: A mounting apparatus for an aircraft engine that provides load path redundancy includes a forward mount that attaches the aircraft engine to a pylon at a forward position of the aircraft engine, an aft mount that attaches the aircraft engine to the pylon at an aft position of the aircraft engine and a thrust assembly connected to the forward mount, and the aft mount. The forward mount includes an aircraft engine attachment assembly and a fail-safe assembly. The aft mount includes an aircraft engine attachment assembly and a fail-safe assembly.

Abstract: A facility safety and compliance information system is provided as a Web-based application for managing information about deficiencies and repairs to facilities, that are subject to health and safety codes, security measures, and production and maintenance standards. The facility safety and compliance information system can maintain facility quality and keep maintenance costs in line, while also reducing liability and satisfying other regulatory constraints. The facility safety and compliance information system leverages computer information system, network, and communication technologies for automating the collection of data and the generation of regulatory and compliance documentation, while also improving the timeliness and accuracy of a facilities reporting, preparedness, and adherence to safety and compliance codes.

Abstract: A cargo carrier removably attaches to a square hitch receiver on the back of a vehicle. The cargo carrier is collapsible when not in use. A base plate has a series of first arms pivotally attached thereto each first arm extending outwardly for use and secured thereat and folding upwardly for storage. A removable plate secures the first arms in the extended position. A second arm is attached to an outer end of a first arm and pivots between an extended position extending upwardly from the first arm and a collapsed position flush against the first arm. Each second arm is lockable in its extended position. A flexible cable is attached to the distal end of each second arm to help retain cargo within the device.

Abstract: A load-bearing structure, such as a pylon or strut, having a monolithic tubular-shaped first central structure composed of composite material and a plurality of metal fittings for supporting an engine on an airframe structure of an aircraft, such as a wing. Most of the fittings are integrated into the load-bearing structure through bonding. The metal fittings carry the high bearing loads that are transmitted into the pylon at the engine-pylon and wing-pylon interfaces. The load-bearing structure may also include a second central structure of a tubular shape composed of composite material and integrated with one end portion of the first central structure by bonding and/or mechanical fasteners.

Abstract: One embodiment includes a swing aid to help athletes (e.g., golfers, batters, or tennis players) learn how to properly hinge their wrists during a swing of a golf club, bat, or racquet. A device comprises a plurality of weights (e.g., balls) included in a conduit. In a low first swing position the balls are located together at a distal end of the conduit. In a high second swing position the balls are located together at a proximal end of the conduit. When transferring from the second position to the first position the balls make a first sound (which indicates improper wrist action) or a second plurality of sounds (which indicates proper wrist action) based on when the user rotates the device about the proximal end of the conduit (e.g., unhinges the wrist). Other embodiments are described herein.

Abstract: An aircraft pylon is disclosed, the pylon including a strut, a modular fluid containment structure and a modular firewall. The strut presents an open structure and connects an aircraft external element to the aircraft. The fluid containment structure is associated with a fluid transfer component, wherein the fluid containment structure contains escaped fluid from the fluid transfer component and channels the escaped fluid away from the aircraft. Both the fluid containment component and the firewall are modular and separable from the strut.

Abstract: A mounting apparatus for an aircraft engine that provides load path redundancy includes a forward mount that attaches the aircraft engine to a pylon at a forward position of the aircraft engine, an aft mount that attaches the aircraft engine to the pylon at an aft position of the aircraft engine and a thrust assembly connected to the forward mount, and the aft mount. The forward mount includes an aircraft engine attachment assembly and a fail-safe assembly. The aft mount includes an aircraft engine attachment assembly and a fail-safe assembly.

Abstract: An aircraft nacelle comprising an outer cowl and an inner cowl located inward of the outer cowl with an air flow path formed therebetween. The inner cowl may comprise a forward portion and an aft portion slidable in a forward-to-aft direction via one or more actuators. When translated aftward, the aft portion may decrease the area of the nacelle's fan duct nozzle. The greatest radial distance between the inner cowl and a center axis of the nacelle may occur at or forward of a location in which the forward and aft portions overlap each other. The forward portion may be comprised of a different material than the aft portion.

Abstract: A method and ground support equipment (GSE) for attaching an engine core to an engine fan module on an aircraft pylon. The GSE may comprise GSE supports and lifting components attached to the pylon, two suspension rails attached to the lifting components, two translating rails translatably attached to the two suspensions rails and fixedly attached to opposite sides of the engine core, and two alignment fittings fixed to the engine fan module. The method of using the GSE may comprise lifting the engine core vertically using the lifting components and anchoring the suspension rails to the alignment fittings. The translating rails and engine core may then be translated in an aft-to-forward direction such that portions of the translating rails engage portions of the alignment fittings to cooperatively guide the translating rails into a final forward position in which the engine core is aligned relative to the engine fan module.

Abstract: A system for integrating and administering multi-organizational compliance monitoring of entities passing between the organizations. The system is configured to allow each organization to be individually responsible for and administer information related to the compliance status of an entity. The system increases an entity's mobility by allowing an organization other than the entity's home organization to determine the compliance status of the entity without additional compliance testing.