A repair method for repairing a component (6a) of a gas turbine engine (10). The method comprises first and second steps. The first step comprises directing an energy beam toward the component (6a) to ablate a first region (54) of material to form a gap extending through the component (6a) between a repair region (58) a base region (58) of the component, wherein subsequent to the first step the repair region (58) and base region (56) are joined by a connecting portion (60). In the second step, an energy beam is direct toward the component (6a) to ablate the repair region (58) to remove the repair region (58) from the component (6a).