Method for repairing a guide blade segment for a jet engine

A method for repairing a guide blade segment, the guide blade segment preferably being fashioned as a twin guide blade segment within a guide blade composite element, having at least two guide blades that are situated between an inner cover strip and/or an outer cover strip and are connected to one another via these strips, the guide blades also being formed from a nose segment and a rear edge segment, and the method comprising:

• identification, within a guide blade segment, of a non-repairable guide blade that is to be separated from the guide blade composite structure;
• separation of at least one non-repairable guide blade from at least one repairable guide blade in a first plane of division;
• division of at least one separated guide blade in a second plane of division between the nose segment and the rear edge segment;
• reconditioning of the at least one repairable nose segment and/or rear edge segment;
• joining of a reconditioned and/or new nose segment to a reconditioned and/or new rear edge segment to form at least one guide blade;
• and
• joining of at least two guide blades to form said guide blade segment.