Abstract: A method of repair for a metallic part of an aircraft engine includes detecting a defect inside a bore of the metallic part wherein the defect represents a departure from an intended geometry of the bore, the bore having a diameter and defining a longitudinal axis, and wherein the defect is located within the bore at a depth of at least greater than one diameter along the longitudinal axis. The method also includes measuring a geometry of the defect, preparing a patch with a complementary geometry to fill the geometry of the defect, placing the patch in the bore with the complementary geometry of the patch seated against the geometry of the defect, directing a welding beam from outside the bore, through the bore and onto the patch to weld the patch to the bore, and removing a portion of the patch to provide the intended geometry for the bore.

Abstract: Methods of repairing a periphery of a threaded hole of a part are provided. An embodiment of the method includes adding material to a region of the part including on a periphery of the threaded hole. New threads are formed in the added material. The new threads are continuous with existing threads formed in the hole.

Abstract: A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

Abstract: Methods of repairing a periphery of a threaded hole of a part are provided. An embodiment of the method includes adding material to a region of the part including on a periphery of the threaded hole. New threads are formed in the added material. The new threads are continuous with existing threads formed in the hole.

Abstract: A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

Abstract: A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

Abstract: A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

Abstract: A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

Abstract: Methods of repairing a periphery of a threaded hole of a part are provided. An embodiment of the method includes adding material to a region of the part including on a periphery of the threaded hole. New threads are formed in the added material. The new threads are continuous with existing threads formed in the hole.

Abstract: Methods of repairing and maintaining rotor blade tips are provided. Filler wire may be positioned at an angle to an electrode and positioned vertically above a blade tip. Filler wire may be deposited from vertically above a blade tip to be repaired. The melting and depositing may occur in an inert environment.

Abstract: A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

Abstract: The method can include inserting a first portion of a backing device into a fluid aperture of a first conduit component, inserting a second portion of the backing device into a fluid aperture of a second conduit component, and bringing the second conduit component adjacent the first component over the backing device, fusion welding the first conduit component to the second conduit over the backing device, and removing the backing device by circulating a fluid inside the welded conduit components. The backing device can be made of a soluble material.

Abstract: The method can include inserting a first portion of a backing device into a fluid aperture of a first conduit component, inserting a second portion of the backing device into a fluid aperture of a second conduit component, and bringing the second conduit component adjacent the first component over the backing device, fusion welding the first conduit component to the second conduit over the backing device, and removing the backing device by circulating a fluid inside the welded conduit components. The backing device can be made of a soluble material.