Abstract: A routing plate assembly is provided and includes a gearbox having an aft surface, first and second hydraulic components, a routing plate comprising a forward side affixable to the aft surface of the gearbox, an aft side to which the first and second hydraulic components are affixable and a body. The body is formed to define interfacial pathways by which the gearbox and the first and second hydraulic components are communicative.

Abstract: A routing plate assembly is provided and includes a gearbox having an aft surface, first and second hydraulic components, a routing plate comprising a forward side affixable to the aft surface of the gearbox, an aft side to which the first and second hydraulic components are affixable and a body. The body is formed to define interfacial pathways by which the gearbox and the first and second hydraulic components are communicative.

Abstract: A brush wear indicating arrangement is provided. The brush wear indicating arrangement includes an insert, a first electrically conductive brush, and a wear indicator. The insert is disposed within a brush block housing and defines a first aperture. The first electrically conductive brush is movably engaged within the first aperture. The electrically conductive brush is configured to move outward from the first aperture as a wear surface of the first electrically conductive brush wears. The wear indicator is coupled to the first electrically conductive brush. The wear indicator is configured to extend beyond a first insert face of the insert as wear condition of the wear surface of the first electrically conductive brush exceeds a wear threshold.

Abstract: A routing plate assembly is provided and includes a gearbox having an aft surface, first and second hydraulic components, a routing plate comprising a forward side affixable to the aft surface of the gearbox, an aft side to which the first and second hydraulic components are affixable and a body. The body is formed to define interfacial pathways by which the gearbox and the first and second hydraulic components are communicative.

Abstract: A yoke plate arrangement may comprise a yoke plate, a wear plate comprising a wear surface and a contact surface, wherein a post extends from the contact surface, and a yoke plate ear extending from the yoke plate in a radial direction, wherein a first aperture is disposed in the yoke plate ear, the post located at least partially within the first aperture, the contact surface being in contact with the yoke plate ear. The yoke plate arrangement may further comprise a retaining feature for coupling the wear plate to the yoke plate. The wear surface may be for engaging a trunnion bearing.

Abstract: A brush wear indicating arrangement is provided. The brush wear indicating arrangement includes an insert, a first electrically conductive brush, and a wear indicator. The insert is disposed within a brush block housing and defines a first aperture. The first electrically conductive brush is movably engaged within the first aperture. The electrically conductive brush is configured to move outward from the first aperture as a wear surface of the first electrically conductive brush wears. The wear indicator is coupled to the first electrically conductive brush. The wear indicator is configured to extend beyond a first insert face of the insert as wear condition of the wear surface of the first electrically conductive brush exceeds a wear threshold.

Abstract: A yoke plate arrangement may comprise a yoke plate, a wear plate comprising a wear surface and a contact surface, wherein a post extends from the contact surface, and a yoke plate ear extending from the yoke plate in a radial direction, wherein a first aperture is disposed in the yoke plate ear, the post located at least partially within the first aperture, the contact surface being in contact with the yoke plate ear. The yoke plate arrangement may further comprise a retaining feature for coupling the wear plate to the yoke plate. The wear surface may be for engaging a trunnion bearing.

Abstract: A brush block assembly and a method of assembling the same are described. The brush block assembly includes two or more brushes arranged in one or more rows, each of the two or more brushes comprised of a pressed electrically conductive material with an integral lead wire and a terminal, and one or more terminal studs, each of the two or more brush blocks within a same one of the one or more rows being separated by one of the one or more terminal studs, a helical spring coupled respectively to each of the two or more brushes, and insulated wires from a power supply and the respective terminal of each of the two or more brushes within the same one of the one or more rows being retained by the one of the one or more terminal studs in the one of the one or more rows.

Abstract: A routing plate assembly is provided and includes a gearbox having an aft surface, first and second hydraulic components, a routing plate comprising a forward side affixable to the aft surface of the gearbox, an aft side to which the first and second hydraulic components are affixable and a body. The body is formed to define interfacial pathways by which the gearbox and the first and second hydraulic components are communicative.

Abstract: A fastening system includes a removable stud and a retaining plate. The removable stud includes a threaded portion configured to be removably threaded into a threaded bore of a housing, a shank portion arranged coaxially with the threaded portion and configured to be inserted through a bore of a housing of a line replaceable component, and an anti-rotation portion disposed between the threaded portion and the shank portion. The retaining plate is configured to be mounted between the housing and the line replaceable component. The retaining plate includes a mating hole configured to mate with the anti-rotation portion of the removable stud.

Abstract: A fluid filter assembly comprises an outer housing, a filter element including a face, and a filter portion extending from the face. The housing has an inlet and an outlet. A spring biases the face against a housing structure at the inlet. A pressure drop across the filter assembly biases the filter element against the spring force such that if the pressure drop exceeds the spring force, the filter element can move to a bypass position. A hydraulic system is also disclosed.

Abstract: A brush block assembly and a method of assembling the same are described. The brush block assembly includes two or more brushes arranged in one or more rows, each of the two or more brushes comprised of a pressed electrically conductive material with an integral lead wire and a terminal, and one or more terminal studs, each of the two or more brush blocks within a same one of the one or more rows being separated by one of the one or more terminal studs, a helical spring coupled respectively to each of the two or more brushes, and insulated wires from a power supply and the respective terminal of each of the two or more brushes within the same one of the one or more rows being retained by the one of the one or more terminal studs in the one of the one or more rows.

Abstract: A propeller system for an aircraft includes a propeller assembly rotatable about a central axis and a reduction gearbox operably connected to the propeller assembly via a propeller shaft. An electrical power transfer system is positioned such that the gearbox is located axially between the electrical power transfer system and the propeller assembly. The electrical power transfer system includes a slip ring assembly secured to an oil transfer tube extending to the propeller assembly and a brush block interactive with the slip ring assembly to transfer electrical power to a plurality of lead wires extending from the slip ring assembly to the propeller assembly. The brush block is positioned such that brush block tips of the brush block extend toward the slip ring assembly in a substantially radial direction relative to the central axis of the propeller assembly.

Abstract: A propeller system for an aircraft includes a propeller assembly rotatable about a central axis and a reduction gearbox operably connected to the propeller assembly via a propeller shaft. An electrical power transfer system is positioned such that the gearbox is located axially between the electrical power transfer system and the propeller assembly. The electrical power transfer system includes a slip ring assembly operably connected to an oil transfer tube extending to the propeller assembly and a brush block interactive with the slip ring assembly to transfer electrical power to a plurality of lead wires extending from the slip ring assembly to the propeller assembly. The brush block is positioned such that brush block tips of the brush block extend toward the slip ring assembly in a substantially axial direction relative to the central axis.

Abstract: A fastening system includes a removable stud and a retaining plate. The removable stud includes a threaded portion configured to be removably threaded into a threaded bore of a housing, a shank portion arranged coaxially with the threaded portion and configured to be inserted through a bore of a housing of a line replaceable component, and an anti-rotation portion disposed between the threaded portion and the shank portion. The retaining plate is configured to be mounted between the housing and the line replaceable component. The retaining plate includes a mating hole configured to mate with the anti-rotation portion of the removable stud.

Abstract: A propeller system for an aircraft includes a propeller assembly rotatable about a central axis and a reduction gearbox operably connected to the propeller assembly via a propeller shaft. An electrical power transfer system is positioned such that the gearbox is located axially between the electrical power transfer system and the propeller assembly. The electrical power transfer system includes a slip ring assembly secured to an oil transfer tube extending to the propeller assembly and a brush block interactive with the slip ring assembly to transfer electrical power to a plurality of lead wires extending from the slip ring assembly to the propeller assembly. The brush block is positioned such that brush block tips of the brush block extend toward the slip ring assembly in a substantially radial direction relative to the central axis of the propeller assembly.

Abstract: A propeller system for an aircraft includes a propeller assembly rotatable about a central axis and a reduction gearbox operably connected to the propeller assembly via a propeller shaft. An electrical power transfer system is positioned such that the gearbox is located axially between the electrical power transfer system and the propeller assembly. The electrical power transfer system includes a slip ring assembly operably connected to an oil transfer tube extending to the propeller assembly and a brush block interactive with the slip ring assembly to transfer electrical power to a plurality of lead wires extending from the slip ring assembly to the propeller assembly. The brush block is positioned such that brush block tips of the brush block extend toward the slip ring assembly in a substantially axial direction relative to the central axis.