A method of locally repairing a coating (50) on a gas turbine engine nozzle guide vane (26) or a turbine blade (30,30B) comprises removing a damaged portion of the coating (50) from a portion (53) of the article. Any oxidized layer (54) is removed from the portion (53) of the surface of the article. Material is placed on the portion (53) of the article (26,30,30B) to form a patch coating (50B). The material is heated to form a patch coating (50B) on the portion (53) of the article (26,30,30B) and to bond the patch coating (50B) to the portion (53) of the article (26,30,30B) and to the coating surrounding the patch coating (50B). A high energy beam is impinged on the coating (50) and the high energy beam is moved from the periphery (60) of the patch coating (50B) to the periphery (62) of the coating (50) in a pattern (P) to uniformly heat the periphery (60) of the patch coating (50B) and the periphery (62) of the coating (50). The advantage is that a halo effect around the patch coating (50B) is obviated.