Black Hawk bushing removal and reamer device

A device for reaming a helicopter stabilator lug bushing comprising:

• a reamer, and
• a reaming block assembly,
• wherein the reaming block assembly comprises an outer block, an inner block, and a reamer guide block,
• wherein the outer block is positioned onto an outer surface of a helicopter stabilator lug, wherein the outer block includes:
• a first outer surface, a second outer surface opposite to the first outer surface, and a peripheral surface extending between the first outer surface and the second outer surface, wherein a central recess in the peripheral surface extends between the first outer surface and the second outer surface, wherein the peripheral surface includes a central convexly curved protrusion opposite to the central recess, the central convexly curved protrusion extends between the first outer surface and the second outer surface,
• two bushing openings, wherein each of the two bushing openings has a central longitudinal axis, the central longitudinal axis of each bushing opening is equidistant from a middle longitudinal axis of an outer block middle channel, wherein each of the two bushing openings allows the reamer to make contact with an inside lining of the helicopter stabilator lug bushing, wherein each of the two bushing openings is formed to allow the reamer to move in and out of each of the two bushing openings,
• wherein the outer block middle channel accepts a first alignment bolt, wherein the outer block middle channel is positioned at a point that is one-half a length of the outer block measured in a first direction perpendicular to the middle longitudinal axis,
• two outer block pin channels, wherein each of the two outer block pin channels is formed to accept a respective guide pin, wherein each of the two outer block pin channels has a central longitudinal axis, wherein each central longitudinal axis of the two outer block pin channels is equidistant from the middle longitudinal axis of the outer block middle channel,
• two outer block bolt channels, wherein each of the two outer block bolt channels has a central longitudinal axis, wherein each central longitudinal axis of the two outer block bolt channels is equidistant from the middle longitudinal axis of the middle channel, wherein each of the two outer block bolt channels accepts a respective second alignment bolt, wherein, in a second direction perpendicular to the middle longitudinal axis, one of the two outer block bolt channels is positioned below a respective one of the two outer block pin channels, wherein each of the two outer block bolt channels and each of the two outer block pin channels is at a greater distance from the middle longitudinal axis of the outer block middle channel than the two bushing openings, and
• at least two reaming guide block coupling channels, wherein the at least two reaming guide block coupling channels are threaded for attaching the reamer guide block to the first outer surface of the outer block,
• wherein the inner block is positioned onto an inner surface of the helicopter stabilator lug, wherein the inner block includes:
• two inner block bushing openings, wherein each of the two inner block bushing openings has a central longitudinal axis, the central longitudinal axis of each bushing opening is equidistant from an inner block mid-plane extending parallel to the central longitudinal axis of each of the two inner block bushing openings, wherein the two inner block bushing openings are respectively mirror symmetric about the inner block mid-plane,
• an inner block middle channel, wherein the inner block middle channel accepts the first alignment bolt, wherein the inner block middle channel is positioned at a point that is one-half a length of the inner block, wherein the inner block mid-plane intersects the inner block middle channel,
• two guide pins, wherein each of the guide pins is formed onto an exterior surface of the inner block, wherein each of the two guide pins is inserted into a respective one of the outer block pin channels, wherein the two guide pins are respectively mirror symmetric about the inner block mid-plane, and
• two inner block bolt channels, wherein each of the two inner block bolt channels has a central longitudinal axis, wherein each central longitudinal axis of the two inner block bolt channels is equidistant from the inner block mid-plane, wherein each of the two inner block bolt channels accepts the respective second alignment bolt, wherein each of the two inner block bolt channels is positioned below a respective one of the two guide pins, wherein each of the two inner block bolt channels and each of the two guide pins is at a greater distance from the inner block mid-plane than the two inner block bushing openings, wherein the two inner block bolt channels are respectively mirror symmetric about the inner block mid-plane,
• wherein the outer block and the inner block are attached to each other via the first alignment bolt, each of the respective second alignment bolt, the two guide pins, and an alignment pin received within one of the two bushing openings in the outer block and a corresponding one of the two inner block bushing openings,
• wherein the reamer guide block is positioned onto the outer block, wherein the reamer guide block includes:
• a reamer opening, wherein the reamer opening is formed to allow the reamer to make contact with the inside lining of the helicopter stabilator lug bushing, wherein the reamer opening is in alignment with one of the two bushing openings in the outer block and a matching one of the two inner block bushing openings, and
• two reaming block coupling channels, wherein each of the two reaming block coupling channels is formed to accept a captive screw, wherein each captive screw couples the reamer guide block to the outer block.