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A method of inspecting a repaired metal alloy part to analyze a microstructure of the metal part includes placing a replicating material on a surface of the metal part to create an inverted replica of the microstructure. The replicating material is then removed from the surface. An image of the inve

A method of inspecting a repaired metal alloy part to analyze a microstructure of the metal part includes placing a replicating material on a surface of the metal part to create an inverted replica of the microstructure. The replicating material is then removed from the surface. An image of the inverted replica on the replicating material is magnified in order to evaluate the microstructure for incipient melting and areas of boride concentration. This inspection method facilitates that evaluation without causing any destruction to the metal part.

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The invention claimed is: 1. A method of inspecting a repaired metal part to determine whether further repair is appropriate, the method comprising: placing a replicating material on a surface of the metal part to create an inverted replica of a microstructure of the surface; removing the replicati

The invention claimed is: 1. A method of inspecting a repaired metal part to determine whether further repair is appropriate, the method comprising: placing a replicating material on a surface of the metal part to create an inverted replica of a microstructure of the surface; removing the replicating material from the surface of the metal part; magnifying an image of the inverted replica on the replicating material; and analyzing the image to determine whether an area of boron concentration is present on the metal part. 2. The method of claim 1 further comprising: determining whether the metal part can be repaired and returned to service based on an amount of boron concentration present on the metal part. 3. The method of claim 1 further comprising: inspecting the image for a presence of voids in a base metal alloy of the metal part. 4. The method of claim 1 wherein the replicating material is cellulose acetate. 5. The method of claim 1 wherein the replicating material is collodion. 6. The method of claim 1 further comprising: applying a chrome coating to the replicating material after removing the replicating material from the surface. 7. The method of claim 1 further comprising: preparing the surface of the metal part prior to placing the replicating material on the surface. 8. The method of claim 7 wherein preparing the surface of the metal part includes polishing the surface using at least one grit paper. 9. The method of claim 7 wherein preparing the surface of the metal part includes applying acetone to the surface. 10. The method of claim 7 wherein preparing the surface of the metal part includes chemically etching the surface. 11. The method of claim 1 wherein the metal part is a component of a gas turbine engine. 12. The method of claim 11 wherein the metal part is a turbine vane assembly of a gas turbine engine. 13. The method of claim 11 further comprising: comparing the image to samples of metal alloys to determine if the metal part may be returned to service in a gas turbine engine, wherein the samples include at least one unacceptable sample having incipient melting and at least one acceptable sample without incipient melting. 14. A method of analyzing a microstructure of a metal alloy part used in a gas turbine engine, the method comprising: preparing a surface of the metal alloy part; placing a replicating material on the surface of the metal alloy part; leaving the replicating material on the surface of the metal alloy part for a time sufficient to create an inverted replica of the microstructure of the metal alloy part; removing the replicating material from the surface of the metal alloy part; and evaluating a magnified image of the inverted replica to determine whether an area of boron concentration is present on the metal alloy part. 15. The method of claim 14 wherein the replicating material includes at least one of cellulose acetate and collodion. 16. The method of claim 14 wherein preparing the surface of the metal alloy part includes at least one of grinding, polishing, etching, and applying acetone. 17. The method of claim 14 wherein evaluating the magnified image of the inverted replica includes determining a presence of voids in the microstructure and determining a presence of borides in the microstructure. 18. The method of claim 14 further comprising: comparing the magnified image to a set of metal alloy samples including acceptable samples without incipient melting and unacceptable samples having incipient melting; and determining whether the metal alloy part may be returned for use in a gas turbine engine. 19. The method of claim 14 wherein the metal alloy part is a turbine vane. 20. A method of evaluating a metal alloy of a gas turbine engine airfoil to determine if incipient melting has occurred as a result of a braze alloy repair, the method comprising: preparing a surface of the airfoil; applying a replicating material to the surface of the airfoil for a time sufficient to create an inverted replica of a microstructure of the airfoil on the replicating material; and magnifying an image of the inverted replica to determine if incipient melting has occurred in the metal alloy of the airfoil as a result of the braze alloy repair by inspecting the inverted replica for an area of boron concentration. 21. The method of claim 20 wherein preparing the surface of the airfoil includes at least one of grinding, polishing, chemical etching, and applying acetone to the surface. 22. The method of claim 20 wherein the time sufficient to create an inverted replica of the microstructure of the airfoil is between approximately three and ten minutes. 23. The method of claim 20 wherein the metal alloy is a nickel alloy. 24. The method of claim 20 wherein the replicating material includes at least one of cellulose acetate and collodion. 25. The method of claim 20 wherein determining if incipient melting has occurred further comprises evaluating a presence of voids in the metal alloy. 26. The method of claim 20 further comprising: comparing the magnified image of the inverted replica to a set of metal alloy samples to evaluate whether the metal airfoil is in an acceptable condition to be returned to service in a gas turbine engine, wherein the set of metal alloy samples includes at least one acceptable sample having no incipient melting and at least one unacceptable sample having incipient melting.