From the BEA site picture:
For the uninitiated, Looks like the crack initiated at what appears to be the base of some circumferential threads and proceeded to grow fanwise from the 9:30 direction before the stress changed into the propeller spanwise direction. From there, it proceeded very rapidly until it reached the central bore and an instantaneous failure of the remaining 2/3 of the blade shank tore away the remainder of the blade.