In combination a wear indicator and a component of a gas turbine engine is provided. The wear indicator is secured to a surface of the component of the gas turbine engine. The wear indicator comprising: a first side delaminates when impacted by a blade of the gas turbine engine; a second side parallel to the first side, the second side being secured to a surface of the component of the gas turbine engine; a mid-section interposed between the first side and the second side; and a reference dimension remains constant when the first side delaminates.