A turbine engine component can include a surface comprising at least one edge and a coating disposed upon the surface that can extend to the edge. A spall break can be disposed along a line upon the surface adjacent the edge to prevent spallation of the coating from spreading from the edge onto the surface beyond the spall break. The spall break can comprise a discontinuity of the coating. A method of coating a turbine component can include preparing a substrate to receive a coating and selecting a fail location along the substrate for a coating. One or more coating can be applied to the substrate and a spall break can be incorporated into the one or more coatings. The spall break can comprise a line of discontinuity in the one or more coatings along the fail location.