As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
NR 2 ENGINE SECOND STAGE HIGH PRESSURE TURBINE BLADE DAMAGED BEYOND LIMITS. *S/D* ONE HPT 2ND STAGE BLADE WAS SEPARATED ALONG A LINE PARALLEL TO THE BLADE CHORD AND APPROXIMATELY 1.5 INCHES OUTBOARD OF THE BLADE PLATFORM. PRIME CAUSE OF FAILURE WAS INTERNAL OXIDATION RESULTING IN FATIGUE FAILURE.