There is provided a robotic end effector assembly having a base configured to be connected to a robot. The base includes a robot adapter coupled to a base plate. The robotic end effector assembly further has a spindle support plate positioned substantially parallel with and coupled to the base plate, via two flexure members. The robotic end effector assembly further has a spindle disposed on the spindle support plate. The robotic end effector assembly further has an actuator coupled between the base plate and the spindle support plate. The actuator is configured to engage an actuator mount attached to the spindle support plate, to displace the spindle support plate. The flexure members inhibit an off-axis drilling motion, as the spindle support plate is displaced.

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.

Certain embodiments of the present disclosure provide an acoustic inlet barrel of an engine. The acoustic inlet barrel may include an inner barrel configured to provide a boundary for directing airflow through the engine. The inner barrel may include an inner face sheet separated from an outer face sheet by an acoustic core. The inner barrel may include a plurality of elongated, non-circular perforations formed through the inner face sheet.

An apparatus includes a spindle, a pecking mechanism, and a clutch mechanism coupled to the pecking mechanism. The spindle includes a drill tool and the spindle is configured to be fed in a first direction during a drilling operation. The pecking mechanism is configured to retract the drill periodically during the drilling operation. The clutch mechanism is configured to selectively engage the pecking mechanism during a portion of the drilling operation. The clutch mechanism is configured to constrain the rotation of the washer such that the spindle drill is retracted a predefined distance periodically.

The method of locating hole features so that old components can be replaced with new components and still match fit with the airframe includes the steps of adhering a bushing assembly into a fixture plate, rigidly attaching the fixture plate with the bushing assembly to the old component, heating the liquid metal above the liquid metal melting temperature such that the cylindrical drill bushing can move within the assembly, inserting an alignment pin within the cylindrical drill bushing such that the alignment pin is also inserted into an existing hole in the old component and the airframe, allowing the liquid metal to re-solidify; removing the alignment pin from the old component, replacing the old component with the new component, and using the re-solidified assembly as a drill guide for replacing holes in the new component.

An apparatus for clamping a robotically controlled tool to a workpiece comprises a tool support mountable on a robotic arm and configured to support the tool, a plurality of clamping modules, each of which includes at least one vacuum cup arranged to clamp the tool support to the workpiece, and an adjustment mechanism configured to adjust the position of the tool support relative to the workpiece.

A cutter assembly for increasing a diameter of an initial pair of holes that includes a first hole defined through a first component and a second hole defined through a second component. The cutter assembly includes a pilot member having a pilot diameter corresponding to a tolerance of misalignment of the first hole and the second hole. Further included is a cutter section associated with the pilot member wherein the cutter section has a cutting diameter larger than the pilot diameter and the cutter section is configured to produce a second pair of aligned holes in the first and second components having a diameter dimension of that of the cutting diameter.

Embodiments herein provide drill hole location transfer between remote components. One embodiment is an apparatus for replicating drill holes of a first workpiece on a second workpiece remotely located from the first workpiece. The apparatus includes an interface to receive coordinate data of first alignment pins installed to first template holes of a first drill plate, and a receptacle to receive a second drill plate having second template holes that match a pattern of the first templates holes of the first drill plate. A pin setting device moves a reference member in a plane over the receptacle, and positions the reference member with respect to the second drill plate based on the coordinate data of the first alignment pins, thus indicating locations within the second template holes to position drill bushings for replicating the first holes of the first workpiece on the second workpiece.

An automatic drilling machine for simultaneously drilling at least two holes through a surface of a crosspiece. The machine comprises an automatic drilling unit having at least two tool holders, each one adapted for receiving a drilling tool. The automatic drilling unit has a cross-shaped channel configured to receive, at least partially, the crosspiece to be drilled inside the automatic drilling unit with. The tool holders are arranged, such as, when the drilling machine is mounted with the crosspiece to be drilled, the tool holders are positioned in accordance with the locations of the crosspiece where a hole is to be drilled.

A manufacturing method is provided. During this method, a panel is provided that includes non-conductive material and a plurality of conductive elements at least partially embedded within the non-conductive material. The conductive elements include a first conductive element. An electric current is applied to the first conductive element such that the first conductive element produces a signature. A location of the first conductive element in the panel is determined based on the signature. An aperture is formed in the panel based on the determined location of the first conductive element.