As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
COMPRESSOR TURBINE DISC BLADE FAILURE. SINGLE BLADE IN COMPRESSOR TURBINE DISC CRACKED IN FUR TREE AREA OF BLADE. CAUSED MISALIGNMENT OF CT BLADE AND SUBSEQUENT RUB ON SHROUD SEGMENTS. THE CRACK IN FIR TREE WAS NOT VISIBLE WITH ENGINE SPLIT IF PERFORMING A ROUTINE INSPECTION, HOWEVER BLADE MISALIGNMENT AND RUB WERE VISIBLE. THE BLADE CRACK BECAME VISIBLE WHEN CT DISC ASSY WAS REMOVED FROM ENGINE.