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A method of repairing a casing for a gas turbine engine, wherein the casing has a wall extending generally axially, and between at least one radially extending flange, the radially extending flange being formed with a plurality of bolt holes, includes the steps of removing a portion of the flange in

A method of repairing a casing for a gas turbine engine, wherein the casing has a wall extending generally axially, and between at least one radially extending flange, the radially extending flange being formed with a plurality of bolt holes, includes the steps of removing a portion of the flange including at least one bolt hole. The removed portion is associated with a defect and a remaining portion of the flange includes at least one non-removed bolt hole. A replacement portion is obtained to replace the removed portion. The replacement portion is secured in an opening left in the flange by the removed portion. A repaired gas turbine engine casing is also disclosed.

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1. A method of repairing a casing for a gas turbine engine, wherein the casing has a wall extending generally axially, and away from a radially extending flange, the radially extending flange being formed with a plurality of bolt holes, the method including the steps of: removing a portion of said f

1. A method of repairing a casing for a gas turbine engine, wherein the casing has a wall extending generally axially, and away from a radially extending flange, the radially extending flange being formed with a plurality of bolt holes, the method including the steps of: removing a portion of said flange including at least one of the plurality of bolt holes, the removed portion associated with a defect and a remaining portion of said flange including at least one non-removed bolt hole of the plurality of bolt holes;obtaining a replacement portion to replace the removed portion;securing said replacement portion in an opening left in said flange by said removed portion; andwherein the removed portion also includes a portion of said wall. 2. The method as set forth in claim 1, wherein the securement step is provided by welding the replacement portion into circumferential edges of the flange defining the removed portion. 3. The method as set forth in claim 2, wherein the securement step also includes the step of welding the replacement portion into a remaining portion of said wall. 4. The method as set forth in claim 1, wherein the securement step is provided by welding the replacement portion into circumferential edges of the flange defining the removed portion. 5. The method as set forth in claim 1, wherein the defect is the removed portion including a crack extending from said at least one bolt hole, and radially toward said wall. 6. The method as set forth in claim 1, wherein the defect relates to the at least one bolt hole. 7. The method as set forth in claim 1, wherein said wall is at least one of cylindrical and conical. 8. The method as set forth in claim 1, wherein said flange extends radially outwardly from the wall. 9. The method as set forth in claim 8, wherein said flange includes a radially outer portion generally circumferentially aligned with said at least one bolt hole, and scallops on circumferential sides of said outer portion, with said removed portion being removed within circumferentially spaced scallop portions. 10. The method as set forth in claim 1, wherein the replacement portion is pre-machined to a standard size, and said removed portion of said flange is removed to match the size of said pre-machined replacement portion. 11. The method as set forth in claim 1, wherein a size of said replacement portion is machined to match the size of said removed portion. 12. A repaired gas turbine engine casing comprising: a wall extending generally axially, and having a radially extending bolt flange at one axial end, there being a plurality of bolt holes in said radially extending bolt flange; anda portion of said at least one radially extending bolt flange having a replacement bolt hole portion secured into an opening formed by the removal of a defective bolt hole portion, and said replacement bolt hole portion including a portion of said wall. 13. The repaired gas turbine engine casing as set forth in claim 12, wherein said radially extending bolt flange extends radially outwardly from said wall. 14. The repaired gas turbine engine casing as set forth in claim 13, wherein said at least on radially extending bolt flange includes a radially outer portion generally circumferentially aligned with said at least one bolt hole, and scallops on circumferential sides of said outer portion, with said removed portion being removed within circumferentially spaced scallop portions. 15. The repaired gas turbine engine casing as set forth in claim 12, wherein a size of said replacement bolt hole portion is machined to match a size of the defective bolt hole portion. 16. A method of repairing a casing for a gas turbine engine, wherein the casing has a wall extending generally axially, and away from a radially outwardly extending flange, the radially outwardly extending flange being formed with a plurality of bolt holes, the method including the steps of: removing a portion comprising a section of said wall and a section of said flange including at least one bolt hole, the removed portion associated with a defect, and a remaining portion of said flange including at least one non-removed bolt hole;obtaining a replacement portion to replace the removed portion; andwelding said replacement portion into circumferential edges of the flange defining the removed portion, and also welding the replacement portion into a remaining portion of said wall. 17. The method as set forth in claim 16, wherein the replacement portion is pre-machined to a standard size, and said removed portion of said flange is removed to match the size of said pre-machined replacement portion. 18. The method as set forth in claim 16, wherein a size of said replacement portion is machined to match the size of said removed portion.