N3378Q

Part: FITTING — BROKEN (OIL SEPARATOR) · airframe 24,376 hrs

PILOT REPORT: UPON DEPARTING ADS (GTX936 ADS-LBB) TOWER REPORTED SEEING A CONTRAIL STREAMING FROM THE PLANE. PILOT CONFIRMED AND SAID HE WOULD RETURN. NOT LONG LATER REPORTED THE RT ENGINE STARTING TO RUN ROUGH AND REQUESTED PRIORITY TO LAND. TOWER DISPATCHED THE FIRE TRUCKS. LANDED WITHOUT INCIDENT AND RETURNED TO THE RAMP. ON OBSERVATION THERE IS OIL STREAKING DOWN THE SIDE AS WELL AS UNDER THE COWLING AND DRIPPING ON THE GROUND. MAINTENANCE HAS INSPECTED THE RIGHT ENGINE AND FOUND THE AIR/OIL SEPARATOR RETURN LINE FITTING HAD BROKEN OF THE AIR/OIL SEPARATOR. MAINTENANCE REPLACED THE AIR/OIL SEPARATOR CANNISTER (SERVICEABLE UNIT). NACELLE AND ENGINE COMPARTMENT CLEANED. AIRCRAFT WAS TAKEN TO THE MAINTENANCE RUN-UP AREA, NO LEAKS NOTED. MECHANICS PERFORMED A TAKE-OFF POWER RUN TO DETERMINE ROUGH ENGINE REPORTED. ENGINE FUEL SET-UP CHECKED AND ADJUSTED AS NEEDED. OPERATIONAL CHECK WAS GOOD.

Part: BRACKET — CRACKED (LG ACTUATOR) · airframe 24,067 hrs

DURING A ROUTINE 200 HOUR INSPECTION OF THE AIRFRAME, MECHANIC OBSERVED MOVEMENT IN THE LANDING GEAR ACTUATOR MOUNTING BRACKET. UPON FURTHER VISUAL INSPECTION OF THE BRACKET A CRACK WAS OBSERVED IN THE RADIUS ON ONE SIDE OF THE BRACKET. BRACKET P/N: 5011013-1 WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT. GEAR RIGGING CHECK AND GEAR SWINGS WERE GOOD.

Part: FITTING — CORRODED (WING) · airframe 23,964 hrs

AIRCRAFT WAS IN MAINTENANCE FOR A ROUTINE 200 HOUR INSPECTION. MAINTENANCE WAS COMPLYING WITH MULTI-ENGINE OWNER ADVISORY MEL-57-02 WING- FORWARD LOWER CARRY-THRU SPAR CAP INSPECTION. DURING THIS INSPECTION CORROSION WAS NOTED ON THE CARRY-THRU SPAR LOWER FORWARD LEFT FITTING. REFERENCE TO SID 57-10-10 #4 INSPECTION INSTRUCTIONS ITEM C INSPECT THE SPAR AND FITTING FOR CORROSION. IF CORROSION IS FOUND ON THE FITTING INSTALL A NEW FITTING. WE CONTACTED CESSNA STRUCTURES FOR REPAIR PROCEDURES AND WAS TOLD "PER ENGINEERING, ONCE THE SPAR FITTING GETS DAMAGED (WHETHER GOUGING OR CORROSION) IT MUST BE REPLACED". "PART REPLACEMENT SHOULD BE DONE PER BEST SHOP PRACTICES".

Part: CASE — CRACKED (ENGINE)

ENGINE CASE CRACK FROM CYLINDER NR3 LOWER AFT THRU BOLT AREA THRU MIDDLE OF CASE TOWARDS CYLINDER NR4 INCLUDING CRACK INTO THE OTHER CASE HALF.

Part: CYLINDER — CRACKED (NR 1)

CASE CRACKED, TOP OF NR 1 CYL, FWD TOP STUD 3 INCHES LONG. GOING UP TO TOP OF CASE. (K)

Part: CYLINDER — CRACKED (ENGINE)

CRACKED BETWEEN FIN NR 1 AND FIN NR 3 AFT OF THE INJECTOR. MFG REV 3 E SERIES CYLINDER. ALL DEFECTIVE! (K)

Part: CYLINDER — CRACKED (ENGINE)

CRACKED BETWEEN FIN NR 1 AND FIN NR 3 AFT OF THE INJECTOR. MFG REV E SERIES CYLINDER. ALL DEFECTIVE! (K)

Part: CYLINDER HEAD — CRACKED (ENGINE)

CYLINDER HEAD CRACKED IN THE EXHAUST SIDE. (K)

Part: CYLINDER — CRACKED (ENGINE)

CYLINDER HEAD CRACKED IN THE EXHAUST SIDE. (K)

Part: CYLINDER HEAD — CRACKED (NR 5)

FOUND CRACKED CYLINDER HEAD WHILE DOING A 50 HR INSPECTION. DUE TO THE NR OF CYLINDER HEAD FAILURES, DOING COMPRESSION CHECK AT EACH SCHEDULED INSPECTIONS (50 HOURS). (K)

Part: BOLT — BROKEN (NOSE FORK)

THE NOSE GEAR WOULD NOT RETRACT AFTER DEPARTURE. AIRCRAFT LANDED WITHOUT PROBLEMS. FOUND THE NOSE GEAR RETRACT FORK BOLT BROKEN. THE BOLT SEPARATED AT THE LAST THREAD BEFORE WHERE THE SHANK STARTS. THE BELLCRANK THAT THE BOLT SCREWS INTO WAS ALSO DAMAGED AND WAS REPLACED AT THE SAME TIME. (PN 0842104-3) SUGGEST THESE BOLTS BE REMOVED AND INSPECTED WITH NDT INSPECTION PROCEDURE. PROBABLE CAUSE, METAL FATIGUE. (SW05200403502)

Part: CRANKSHAFT — FAILED (RT ENGINE)

ENGINE SHUT DOWN DURING FLIGHT FROM HOUSTON TO DALLAS. UPON TEAR DOWN, DISCOVERED THAT THE CRANKSHAFT HAD BROKEN. SUBMITTER STATED CAUSE IS UNKNOWN PENDING FURTHER INVESTIGATION.