As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.
What was found
(CAN) UPON REMOVAL OF TURBINE TO FACILITATE COMPRESSOR CHANGE, FIRST STAGE NOZZLE DOME WAS CRACKED IN CENTER AREA. FIRST STAGE NOZZLE WAS CRACKED ON THE OUTER RING AT 2 ADJACENT VANES. THE OVERHAUL SHOP FOUND A CRACK IN THE EXHAUST COLLECTOR/TURBINE SUPPORT AND BURNING CONSISTANT WITH AN UNEVEN FUEL NOZZLE SPRAY PATTERN. THE FUEL NOZZLE HAD BEEN REPLACED EARLIER DUE TO ERRATIC STARTS.