An end effector provides one up assembly drilling through mated components, including a panel, by preloading the components. The end effector includes a drill and clamp dispenser for temporarily inserting and removing expansible single-sided clamps at various pre-drilled locations in the panel. In one method, pilot holes are first pre-drilled into mated components, for example an aircraft wing panel and a wing rib or spar; an initial pilot hole location is identified, and an expansible clamp is inserted into a pilot hole adjacent a desired initial fastener hole location. The clamp is torqued, causing its expansion for preloading the wing panel and rib and/or spar components under a predetermined load. The fastener hole is then drilled, the end effector untorques and removes the clamp and identifies a second (and/or next) pilot hole location, and the process is replicated.

A method includes making a first structure with a first plurality of pre-drilled holes at pre-defined locations, making a second structure with a second plurality of pre-drilled holes at pre-defined locations, making a third structure without pre-drilled full-size holes, measuring the location and orientation of the first and second plurality of pre-drilled holes in the first and second structures, determining the location of a third plurality of holes to be drilled in the third structure that correspond to first and second plurality of pre-drilled holes measured in the first and second structures, creating a program to drill the third plurality of holes in the third structure that align with the measured location and orientation of the first and second plurality of pre-drilled holes in the first and second structures based on the measure location and orientation of the first and second plurality of pre-drilled holes in the first and second structure, drilling the third plurality of holes in the third structure based on the program, positioning the third structure on the first and second structures such that the third plurality of holes in the third structure are aligned with the first and second plurality of pre-drilled holes in the first and second structures, and inserting fasteners through the third plurality of holes and the first and second plurality of predrilled holes that are aligned with the third plurality of holes to secure the second structure to the first structure using the third structure.

A system and method for drilling a hole in a vehicle structure and installing a fastener in the hole. A drill plate having openings and associated machine-readable elements is positioned on the structure. A drill gun is positioned in a particular opening and reads hole information from the associated element, and a computer determines whether the drill gun is properly set-up to drill the hole. A fastener insertion gun is positioned in the particular opening and reads fastener information from the element, and the computer determines whether the hole has been drilled and, if so, whether the fastener insertion gun is properly set-up to insert the fastener. A fastener delivery subsystem stores, tracks, and delivers fasteners to the fastener insertion gun. A system computer monitors the drilling of every hole, the insertion of every fastener, and the overall operation of the fastener delivery subsystem.

An apparatus and corresponding method for machining at least one spline in an aeronautical component. The apparatus comprises a holder defining an axial direction about which the holder is moveable, and a cutting insert attachable to the holder. The apparatus further comprises a coupling for attaching the cutting insert to the holder about a second direction that is perpendicular to the axial direction of the holder. The holder may comprise a first alignment feature for orientating the cutting insert at a single orientation with respect to the holder. The cutting insert may comprise at least one cutting tooth, wherein each cutting tooth comprises a cutting edge. The cutting insert may comprise a first datum surface which is spaced from each cutting edge by a respective predetermined spacing.

A method and apparatus for manufacturing an aircraft structure. A drivable support may be driven from a first location to a second location to bring the drivable support together with at least one other drivable support to form a drivable support system. A structure may be held in a desired position using the drivable support system.

Ribs for working an aircraft component having an aircraft component surface, fixtures for the same, and methods for the same, are provided herein. The rib includes a rib surface configured to receive the aircraft component and to be in abutting contact with at least a portion of the aircraft component surface. The rib further includes an extension extending away from the rib and configured to couple to a worksurface. Orientation of the rib is configured to be adjustable relative to the worksurface for improving working of the aircraft component. The fixture includes a mount defining an aperture and configured to be coupled to the worksurface and the rib. The method includes providing the fixture including the rib. The method further includes coupling the extension to a worksurface. The method further includes disposing the aircraft component on the rib surface.

A system and method for processing a flexible part comprising holding the flexible part securely in an unconstrained position using a holder; and controlling a positioner to process the flexible part based on a comparison of a shape and/or position of the flexible part in the unconstrained position with design specifications of the part not in the unconstrained position.

A system and method for processing a flexible part comprising holding the flexible part securely in an unconstrained position using a holder; and controlling a positioner to process the flexible part based on a comparison of a shape and/or position of the flexible part in the unconstrained position with design specifications of the part not in the unconstrained position.

A system and method for drilling a hole in a vehicle structure and installing a fastener in the hole. A drill plate having openings and associated machine-readable elements is positioned on the structure. A drill gun is positioned in a particular opening and reads hole information from the associated element, and a computer determines whether the drill gun is properly set-up to drill the hole. A fastener insertion gun is positioned in the particular opening and reads fastener information from the element, and the computer determines whether the hole has been drilled and, if so, whether the fastener insertion gun is properly set-up to insert the fastener. A fastener delivery subsystem stores, tracks, and delivers fasteners to the fastener insertion gun. A system computer monitors the drilling of every hole, the insertion of every fastener, and the overall operation of the fastener delivery subsystem.

A system and a method include a fixture template configured to be secured to a component. The fixture template includes a plurality of insert holes. A plurality of guide inserts have channels. Each of the channels has an orientation. The orientation of at least two of the plurality of guide inserts differs. Each of the plurality of guide inserts is removably secured within a respective one of the plurality of inserts holes to position and orient the channels in relation to a pattern of openings to be formed in relation to the component. Each of the channels is configured to receive an operative member of a tool that is configured to form the pattern of openings in relation to the component.