As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
TWO EACH, STAGE 1 TURBINE BLADES FRACTURED AND LIBERATED THE TOP ONE-THIRD OF THE AIRFOIL CAUSING DAMAGE TO THE 2ND STAGE BLADES. SUBMITTER STATED INSUFFICIENT INSPECTION INFORMATION EXISTS IN THE ENGINE MANUAL TO DETECT THINNING/NECKING OF THE AIRFOIL SECTION DUE TO CREEP AND/OR OXIDATION AND/OR EROSION. THINNING OF THE BLADE AIRFOIL CROSS-SECTION RESULTS IN BLADE FRACTURE. (X)