Patent ID: 9598183
Date: 2017-03-21
CPC Classifications: B23B,B23Q,B64C,B64F

Claim:
1. A method of repairing an aircraft wing, the method comprising the steps of: generating a skin template having template holes corresponding to each fastener hole of an original skin, wherein the template holes have a diameter no greater than a diameter of the corresponding fastener holes of the original skin; drilling pilot holes corresponding to each of the template holes in a new skin, wherein the pilot holes have a diameter smaller than the diameter of the corresponding fastener holes of the original skin; aligning the new skin with an existing underlying wing structure such that each of the pilot holes is aligned with a corresponding fastener hole of the existing underlying aircraft wing structure such that a center point of each fastener hole of the existing underlying aircraft wing structure is accessible through the corresponding pilot hole of the new skin; aligning a mill bit with the center point of each fastener hole of the existing underlying wing structure such that the mill bit extends through the corresponding pilot hole of the new skin; and milling material from around the entire perimeter of each pilot hole of the new skin to form fastener holes in the new skin that align with the fastener holes of the existing underlying wing structure.