What happened
The FAA’s narrative, in sentence case. The FAA writes it in capitals and removes private details.
(-23) Pilot made emergency landing at kric due to right engine failure in flight. Upon investigation, found the RH engine #3 cylinder separated from the crankcase. The crankcase was broken in several places around the perimeter of where the cylinder base attaches to the case. Engine records indicate the engine was overhauled 126 hours earlier and has 31 hours since last annual inspection. Engine was shipped to repair facility for evaluation and inspection. (-23 amendment) evaluation and inspection of engine performed in coordination with engine overhaul repair station pmi. No separation of the cylinder head to cylinder was noted. There was no indication of valve failure, push rod failure, or rocker arm failure. The crankshaft and camshaft were intact. All of the remaining cylinder assemblies were intact. There was no evidence of failure due to lack of lubrication. The engine turned freely. Due to the destruction of the piston, it was not feasible to perform a metallurgical analysis. The number three piston pin and plugs were found intact. The small end of the connecting rod was found broken and bent back. Due to the extent of damage, it was not possible to determine wehre the actual failure occurred.
As the FAA filed it
(-23) PILOT MADE EMERGENCY LANDING AT KRIC DUE TO RIGHT ENGINE FAILURE IN FLIGHT. UPON INVESTIGATION, FOUND THE RH ENGINE #3 CYLINDER SEPARATED FROM THE CRANKCASE. THE CRANKCASE WAS BROKEN IN SEVERAL PLACES AROUND THE PERIMETER OF WHERE THE CYLINDER BASE ATTACHES TO THE CASE. ENGINE RECORDS INDICATE THE ENGINE WAS OVERHAULED 126 HOURS EARLIER AND HAS 31 HOURS SINCE LAST ANNUAL INSPECTION. ENGINE WAS SHIPPED TO REPAIR FACILITY FOR EVALUATION AND INSPECTION. (-23 AMENDMENT) EVALUATION AND INSPECTION OF ENGINE PERFORMED IN COORDINATION WITH ENGINE OVERHAUL REPAIR STATION PMI. NO SEPARATION OF THE CYLINDER HEAD TO CYLINDER WAS NOTED. THERE WAS NO INDICATION OF VALVE FAILURE, PUSH ROD FAILURE, OR ROCKER ARM FAILURE. THE CRANKSHAFT AND CAMSHAFT WERE INTACT. ALL OF THE REMAINING CYLINDER ASSEMBLIES WERE INTACT. THERE WAS NO EVIDENCE OF FAILURE DUE TO LACK OF LUBRICATION. THE ENGINE TURNED FREELY. DUE TO THE DESTRUCTION OF THE PISTON, IT WAS NOT FEASIBLE TO PERFORM A METALLURGICAL ANALYSIS. THE NUMBER THREE PISTON PIN AND PLUGS WERE FOUND INTACT. THE SMALL END OF THE CONNECTING ROD WAS FOUND BROKEN AND BENT BACK. DUE TO THE EXTENT OF DAMAGE, IT WAS NOT POSSIBLE TO DETERMINE WEHRE THE ACTUAL FAILURE OCCURRED.
Other reports on N54857 · 3
Matched to the same aircraft by N-number and date.