What was found
(CAN) UPON ROUTINE INSPECTION OF COMPRESSOR CASE HALFS (WHILE ENGINE WAS REMOVED FROM AIRFRAME) IT WAS FOUND THAT ONE OF THE 6TH STAGE STATOR BLADES HAD BROKEN OFF ONE OF THE CASE HALFS AND BEEN INJESTED INTO THE COMPRESSOR CENTRIFUGAL COMPRESSOR SECTION, AND THROUGH INTO COMBUSTION AND TURBINE SECTION OF ENGINE. IT IS UNKNOWN WHEN THE BLADE WAS ACTUALLY SHED, AS THERE WERE NO COMPLAINTS FROM PILOTS IN PAST FLIGHTS OF ANY ANOMOLIES, BE IT POWER, NOISE OR VIBRATION. COMPRESSOR ASSEMBLY SUFFERED EXTENSIVE DAMAGE. COMBUSTION SECTION AND TURBINE ASSEMBLY DID NOT SUSTAIN ANY APPRECIABLE DAMAGE (AS DETERMINED BY ENGINE OVERHAUL SHOP UPON FULL EVALUATION). (TC# 20190507012)