Abstract: A method for replacing a damaged or defective section of a length of original piping or tubing located within a structrue such as the turbine of a jet engine wherein access to the tubing is limited, and replacing such damaged section with a new section of tubing comprises inserting a cutter mounted at one end of a flexible shaft into the interior of the original tubing and rotating the shaft to cut out and remove the damaged section of tubing leaving at least one stub section of original tubing. The stub sections of original tubing are then prepared for welding or brazing to a section of replacement tubing with a series of tools each mounted to an elongated shaft. These tools include a chamfering tool, a deburring tool, and a polishing tool.

Abstract: A gas turbine engine air cooled vane assembly which includes inner and outer platform members and an airfoil member therebetween is repaired by removing from the vane assembly a vane assembly segment comprising at least a portion of the leading edge wall, a portion of the airfoil body wall and a portion of at least one platform member connected with the leading edge wall. The vane assembly segment is removed along a preselected path which, during operation of the vane assembly in a gas turbine engine, experiences relatively low mechanical stresses. A replacement member of substantially the same type of material and of a size and shape which matches the removed vane assembly segment is placed into registry with the vane assembly and then metallurgically bonded to the vane assembly.