Continental TSIO-520-NB
Service difficulty reports · 310
Newest first. General aviation reporting is voluntary.
Query with SQL
duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE engine_model_key = 'TSIO520NB' ORDER BY difficulty_date DESC"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE engine_model_key = 'TSIO520NB' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR GNMA6640C021912Engine · making metalAIRCRAFT LEFT ENGINE WAS SHOWING LOW OIL PRESSURE 10 MINUTES OUT OF AIRPORT, ALL OTHER ENGINE GAUGES READ NORMAL. PILOT STARTED LEFT ENGINE FOR DEPARTURE BACK, BUT LEFT ENGINE OIL PRESSURE GAUGE DID NOT RESPOND. TROUBLESHOT ENGINE AND FOUND METAL SHAVING INSDR 2011FA0000790Cylinder · crackedTHE CYLINDER HEAD SEPARATED FROM THE BARREL ONE COOLING FIN BELOW THE CYLINDER HEAD.SDR 2012FA0000210Cylinder Head · failedENGINE HAD INFLIGHT SHUTDOWN DUE TO NR 2 CYLINDER HEAD BLOWN OUT AND MELTING NR 4 CYLINDER HEAD INTAKE, CAUSING MANIFOLD PRESSURE TO DROP AND FUEL AIR CHARGE TO IGNITE AND BLOW OUT THRU LOUVERS IN TOP OF COWL.SDR 2011FA0000782Cylinder · failedNEW CYLINDERS WERE INSTALLED ON ACFT. 2 OF THE 12 CYLINDERS FAILED AT 25.3 TIME IN SERVICE, WITH WHAT LOOKED LIKE THE NICKEL COATING SEPARATING FROM THE CYLINDER WALLS. UPON REMOVAL OF THE CYLINDER (1 FROM EACH ENGINE), THE NICKEL COATING HAD SEPARATED AND TSDR 2011FA0000503Connecting Rod · fracturedLEFT ENGINE NR 4 CYLINDER CONNECTING ROD, FRACTURED AND PUNCTURED THE ENGINE CASE ABOVE NR 4 CYLINDER MOUNT FLANGE. AT ENGINE TT 4096.7 (7/17/07) THIS ENGINE WAS O/H AND MODIFIED TO 335HP IAW STC SE09104SC RAM SERIES VII. AT THAT TIME MODIFIED CONNECTING RODSDR RJWR002Drive Shaft · shearedAFTER LANDING, PILOT REPORTED SUBSTANTIAL OIL LEAK. FOUND STARTER DRIVE/ SCAVENGE PUMP ASSY PN R-642085A17 HAD A SHEARED DRIVE SHAFT. THIS CAUSED EXCESSIVE OIL TO GO TO AIR OIL SEPERATOR AND OVERBOARD DUE TO SEPERATOR COULD NOT RETURN THE VOLUME OF OIL COMING SDR 2011FA0000253Cylinder Head · crackedCYLINDER CRACKS AT INTAKE VALVE SEAT AND LEAKING RAW FUEL FROM CRACK ON OUTSIDE OF CYLINDER HEAD, DRIPPING DOWN SIDE OF INTAKE TUBE.SDR 2011FA0000050Bearing · failed(VA1R) TURBOCHARGER FAILED IN FLIGHT. BEARING FAILURE DUE ASSY ISSUE.SDR 2011FA0000060Shaft · brokenTURBOCHARGER FAILED. THE CENTER SHAFT BROKE.SDR CA101126003Compressor Wheel · damagedPILOT REPORTED ON RUN-UP THAT EVERYTHING APPEARED NORMAL OTHER THAN THE LT ENGINE (MANIFOLD PRESSURE) MP WAS ABOUT 1 INCH HIGHER THAN THE RT ENGINE. PILOT HAD A NORMAL TAKEOFF WITH ALL INSTRUMENTS WITHIN NORMAL LIMITS. AFTER THE PLANE WAS SET UP FOR CRUISE ASDR BIGA111001Switch · out of adjustSTHE AIRCRAFT HAD THE LEFT ENGINE FLAME OUT ON DESCENT WHILE RUNNING ON THE LEFT MAIN TANK. THE PILOT SWITCHED TANKS TO THE AUX THEN RE-SELECTING THE LEFT MAIN TANK THE AIRCRAFT WAS RESTARTED AND LANDED WITHOUT FURTHER INCIDENT. THE AIRCRAFT WAS HANGERED ANDSDR 2010FA0001112Hose · brokenPILOT NOTICED OIL STREAMING FROM ATHE ENGINE COWLING DURING FLIGHT AND DECIDED TO FEATHER THE ENGINE BEFORE A CATASTROPHIC FAILURE OCCURRED. THE OIL DRAIN HOSE FROM THE AIR/OIL SEPARATOR IN THE WET VACUUM PUMP AND PRESSURIZATION SYSTEM SEPARATED WHICH DRAINS SDR 2010FA0001252Engine · failedENGINE SN 51773 WAS O/H UNDER WO 41675 ON 7/02/2010 AND INSTALLED IN POS 2. ACFT WAS OPERATED NORMALLY WITHOUT ANY INCIDENTS. ON 9/17/2010 THE ACFT RECEIVED A THOROUGH PREFLIGHT INSP ALONG WITH ENGINES RUN UP WITH NO DISCREPANCIES NOTED. 20 MINUTES AFTER TASDR 2010FA0001096Shaft · brokenCAUSED LOSS OF ENGINE OIL. OIL LEAKING FROM THE EXHAUST SIDE OF TURBOCHARGER SHAFT AND BURING OIL OUT OF THE EXHAUST PIPE. LET TURBO COOL DOWN SOME BEFORE SHUT DOWN. TURBO HAD EXCESSIVE COAKING SIGNS.SDR DD2RW900001Clutch Spring · overheated((DD2R)) NEWLY O/H'D STARTER ADAPTER FAILED APPROX 5 HOURS AFTER INSTALLATION. DISASSEMBLY & FAILURE ANALYSIS OF UNIT REVEALED OVERHEATED AND MANGLED CLUTCH SPRING. SPRING HAD A COLLAPSED COIL THAT HAD WOUND AROUND THE SHAFTGEAR MINOR DIAMETER BETWEEN CLUTSDR DD2RW900000Clutch Spring · overheated((DD2R)) NEWLY O/H STARTER ADAPTER FAILED 1.4 HOURS AFTER INSTALLATION. DISASSLY AND FAILURE ANALYSIS OF UNIT REVEALED OVERHEATED AND MANGLED CLUTCH SPRING. SPRING HAD A COLLAPSED COIL THAT HAD WOUND AROUND THE SHAFT GEAR MINOR DIAMETER BETWEEN CLUTCH DRUM SDR 2010FA0000179Cylinder · cracked(1) CYL HEAD SEPARATED AT 360 TTSN ON THE RT ENG. ALL CYL ON BOTH ENGINES HAD JUST PASSED COMPRESSION CHECK WITH VALUES IN THE MID TO UPPER 70'S BUT PILOT REPORTED VIBRATION IN CRUISE FLIGHT ON LT ENGINE - UPON FURTHER INSP USING SHOP AIR AND LIQUID LEAK DETESDR 2010FA0000155Cylinder · crackedON BOTH ENGINES, FOUND FUEL STAINS ON SEVERAL INDUCTION TUBES AFTER FURTHER INSPECTION FOUND FUEL STAINS ON CYLINDER FINS BY INTAKE VALVES/ REMOVED AND REPLACED ALL CYLINDERS/ LOOKING AT PAST RECORDS FOUND THAT INDUCTION GASKETS HAD BEEN CHANGED SEVERAL TIMES SDR 2010FA0000275Clamp · crackedDURING AN ANNUAL INSPECTION, THE CLAMP BETWEEN THE EXHAUST PIPE AND WASTEGATE ELBOW ON THE RT ENGINE WAS FOUND WITH A 2 INCH CRACK ALONG THE CIRCUMFERENCE.SDR 2009FA0000941Magneto · failedRIGHT ENGINE REPORTED TO RUN ROUGH DURING APPROACH. ENGINE HAS A 25 RPM MAGNETO DROP. COMPRESSION CHECK INDICATED A LEAKING EXHAUST VALVE WITH THE ENGINE HAVING ALLOWABLE COMPRESSION READINGS. CHT'S DID NOT COME UP EVENLY DURING INITIAL ENGINE START UP, SOMSDR 2009FA0000942Spring · brokenRT ENGINE REPORTED TO RUN ROUGH DURING APPROACH. ENGINE HAS A 25 RPM MAGNETO DROP. COMPRESSION CHECK INDICATED A LEAKING EXHAUST VALVE WITH THE ENGINE HAVING ALLOWABLE COMPRESION READINGS. CHT'S DID NOT COME UP EVENLY DURING INITIAL ENGINE START UP, SOME LASDR DD2R171075Clutch Spring · failedOVERHAULED STARTER ADAPTER FAILED LESS THAN 10 HRS AFTER INSTALLATION. 2ND OVERHAULED UNIT FAILED IN UNDER 5 HRS. DISASSEMBLY & FAILURE ANALYSIS OF BOTH UNITS REVEALED OVERHEATED & MANGLED CLUTCH SPRINGS. EACH HAD A COLLAPSED COIL THAT HAD WOUND AROUND THE SHASDR 2009FA0000685Cylinder Head · crackedDURING ROUTINE ENGINE OIL CHANGE, FUEL STAINS WERE NOTED ON INTAKE MANIFOLD BELOW EACH CYLINDER INTAKE PORT AND BETWEEN CYLINDER HEAD FINS IN THIS AREA. PERFORMED DIFFERENTIAL COMPRESSION TEST WITH LOW COMPRESSION NOTED ON NR 1 AND 5 CYLINDERS. SOAP BUBBLE LSDR 2009FA0000686Cylinder Head · crackedDURING ROUTINE ENGINE OIL CHANGE, FUEL STAINS WERE NOTED ON INTAKE MANIFOLD BELOW EACH CYLINDER INTAKE PORT AND BETWEEN THE CYLINDER HEAD FINS IN THIS AREA. PERFORMED DIFFERENTIAL COMPRESSION TEST WITH LOW COMPRESSION NOTED ON NR 1 AND 5 CYLINDERS. SOAP BUBBSDR 2009FA0000687Cylinder Head · crackedDURING ROUTINE ENGINE OIL CHANGE, FUEL STAINS WERE NOTED ON INTAKE MANIFOLD BELOW EACH CYLINDER INTAKE PORT AND BETWEEN THE CYLINDER HEAD FINS IN THIS AREA. PERFORMED DIFFERENTIAL COMPRESSION TEST WITH LOW COMPRESSION NOTED ON NR 1 AND 5 CYLINDERS. SOAP BUBBSDR 2009FA0000688Cylinder Head · crackedDURING ROUTINE ENGINE OIL CHANGE, FUEL STAINS WERE NOTED ON INTAKE MANIFOLD BELOW EACH CYLINDER INTAKE PORT AND BETWEEN THE CYLINDER HEAD FINS IN THIS AREA. PERFORMED DIFFERENTIAL COMPRESSION TEST WITH LOW COMPRESSION NOTED ON NR 1 AND 5 CYLINDERS. SOAP BUBBSDR 2009FA0000689Cylinder Head · crackedDURING ROUTINE ENGINE OIL CHANGE, FUEL STAINS WERE NOTED ON INTAKE MANIFOLD BELOW EACH CYLINDER INTAKE PORT AND BETWEEN THE CYLINDER HEAD FINS IN THIS AREA. PERFORMED DIFFERENTIAL COMPRESSION TEST WITH LOW COMPRESSION NOTED ON NR 1 AND 5 CYLINDERS. SOAP BUBBSDR 2009FA0000690Cylinder Head · crackedDURING ROUTINE ENGINE OIL CHANGE, FUEL STAINS WERE NOTED ON INTAKE MANIFOLD BELOW EACH CYLINDER INTAKE PORT AND BETWEEN THE CYLINDER HEAD FINS IN THIS AREA. PERFORMED DIFFERENTIAL COMPRESSION TEST WITH LOW COMPRESSION NOTED ON #1 AND 5 CYLINDERS. SOAP BUBBLESDR 2009FA0000732Cylinder Head · crackedCYLINDER HEAD FAILED IN FLIGHT AND BLEW OUT A SECTION OF THE HEAD AND FINS. INVESTIGATION REVEALED A .5 INCH HOLE DEVELOPED FROM A CRACK THAT PROGRESSED FROM THE EXHAUST VALVE SEAT TO UPPER SPARK PLUG HOLE. ADDITIONAL CRACK WAS FOUND ON THIS CYLINDER FROM THSDR 2009FA0000733Cylinder Head · crackedCYLINDER HEAD FOUND CRACKED FROM INJECTOR BOSS TO THE UPPER PLUG HOLE. AFTER INSPECTION OF ALL CYLINDERS ON BOTH ENGINES 5 OTHER OF THE ORIGINAL CYLINDERS INSTALLED AT O/H WERE FOUND CRACKED. ALL CRACKS WERE EITHER FROM THE INJECTOR BOSS TO THE UPPER PLUG HOSDR 2009FA0000734Cylinder Head · crackedCYLINDER HEAD FOUND CRACKED FROM INJECTOR BOSS TO THE UPPER PLUG HOLE. AFTER INSPECTION OF ALL CYLINDERS ON BOTH ENGINES 5 OTHER OF THE ORIGINAL CYLINDERS INSTALLED AT O/H WERE FOUND CRACKED. ALL CRACKS WERE EITHER FROM THE INJECTOR BOSS TO THE UPPER PLUG HOSDR 2009FA0000735Cylinder Head · crackedCYLINDER HEAD FOUND CRACKED FROM INJECTOR BOSS TO THE UPPER PLUG HOLE. AFTER INSPECTION OF ALL CYLINDERS ON BOTH ENGINES 5 OTHER OF THE ORIGINAL CYLINDERS INSTALLED AT O/H WERE FOUND CRACKED. ALL CRACKS WERE EITHER FROM THE INJECTOR BOSS TO THE UPPER PLUG HOSDR 2009FA0000736Cylinder Head · crackedCYLINDER HEAD FOUND CRACKED FROM INJECTOR BOSS TO THE UPPER PLUG HOLE. AFTER INSPECTION OF ALL CYLINDERS ON BOTH ENGINES 5 OTHER OF THE ORIGINAL CYLINDERS INSTALLED AT O/H WERE FOUND CRACKED. ALL CRACKS WERE EITHER FROM THE INJECTOR BOSS TO THE UPPER PLUG HOSDR 2009FA0000737Cylinder Head · crackedCYLINDER HEAD FOUND CRACKED FROM INJECTOR BOSS TO THE UPPER PLUG HOLE. AFTER INSPECTION OF ALL CYLINDERS ON BOTH ENGINES 5 OTHER OF THE ORIGINAL CYLINDERS INSTALLED AT O/H WERE FOUND CRACKED. ALL CRACKS WERE EITHER FROM THE INJECTOR BOSS TO THE UPPER PLUG HOSDR J7B2009F00000Cylinder Head · separatedWHILE IN FLIGHT, AT CRUISE POWER, A LOSS OF MANIFOLD PRESSURE AND ENGINE ROUGHNESS WAS EXPERIENCED. THE ENGINE WAS SHUTDOWN. A NORMAL LANDING WAS MADE AT THE INTENDED DESTINATION. INSP REVEALED THAT NR 2 CYLINDER HEAD HAD SEPARATED. NO STRUCTURAL DAMAGE OCSDR CA090403002Connecting Rod · worn(CAN) PISTON PIN BUSHING FAILED DUE TO LACK OF LUBRICATION. ENG DISMANTLED AND FAILURE DETERMINED TO BE CASUED BY SEALANT BLOCKING THE PISTON COOLING JET TO NR 2 CYLINDER. THE PROBLEM SEEMED TO BE CAUSED BY THE USE OF EXCESSIVE SEALANT (POSSIBLY LOCKTITE 515) SDR CA090310010Blade · corroded(CAN) DURING LPI INSP, CORROSION FOUND IN O-RING GROOVE. UNREPAIRABLE IAW MANUAL NR BOM100-1.SDR 2008FA0000922Spar · crackedDURING ROUTINE INSP, CRACKS WERE OBSERVED IN THE LT AUXILARY SPAR. THE MAIN GEAR IS ATTACHED AT THE OTBD END. THE CRACKS WERE AT THE 11,2,5 AND 7 O`CLOCK POSITIONS OF THE HOLE WHICH THE WIRE BUNDLE PASSES THROUGH, AND WERE OF VARYING LENGTH. CRACKS WERE ALSSDR CA081205007Line · corroded(CAN) UPON REACHING CRUISE FLIGHT AND ACTIVATING AIRFRAME PNEUMATIC DE-ICE SYSTEM, THE BOOTS WOULD REMAIN PARTIALLY TO MOSTLY INFLATED. THIS PROBLEM WOULD NOT DUPLICATE ON A GROUND RUN. THE VACUUM LINE TO THE FLOW VALVES WAS INSPECTED AND A LINE ASSEMBLY TOSDR 2008FA0000690Cylinder · crackedUPON INSPECTION FOUND THAT NR 1 AND NR 5 CYLINDERS WERE CRACKED AND LEAKING FUEL ORIGINATING JUST INBOARD OF THE FUEL NOZZLE BETWEEN THE 16TH AND 18TH COOLING FINS. CYLINDERS WERE NEW WHEN INSTALLED AT ENGINE OVERHAUL.SDR CA081002001Switch · intermittent(CAN) LANDING GEAR INTERMITTENTLY WOULD NOT RETRACT. FOUND ANNUNCIATOR PRESS TO TEST SWITCH INTERMITTENT.SDR 2008FA0000624Bushing · crackedDURING CYLINDER NR 2 REMOVAL TO CORRECT CRACKED CYLINDER, FOUND CONNECTING ROD PISTON P/N BUSHING CRACKED WITH LARGE PIECE MISSING FROM EDGE. FAILURE IS AS NOTED IN MFG SB071. REMOVED ALL 6 CYLINDERS FROM ENGINE AND FOUND 4 MORE BUSHINGS CRACKED IN SAME LOCATSDR CA080424003Brushes · missing(CAN) LT ENGINE REPORTED DIFFICULT TO START. MAGNETO REMOVED AND BENCH TESTED, FOUND TO HAVE LOW AND INCONSISTENT OUTPUT. MAGNETO DISASSEMBLED FOR INSP AND FOUND CARBON BRUSH ASSY NOT INSTALLED IN DISTRIBUTOR GEAR. NO EVIDENCE OF BRUSH OR SPRING REMNANTS FOUNDSDR N416RAValve Spring · brokenENGINE VIBRATION PROMPTED INFLIGHT SHUTDOWN OF ENGINE.SDR CA080305006Resistor · overheated(CAN) RESISTOR LOCATED UNDER CO-PILOT SEAT(CONTROLS HIGH LOW OPERATION OF HEATER BLOWER MOTOR. THERE ARE 3 RESISTORS OF THE SAME TYPE IN THIS LOCATION, IN THIS CASE HEATER RESISTOR-OR55-1 OVERHEATED CAUSING THE TY-RAP LOCATED ON THE UPPER PORTION OF RESISTOR SDR 4757Cylinder · crackedPILOT WAS INFORMED BY LINE PERSONNEL DURING TAXI TO TIE DOWN, THAT ENGINE WAS MAKING A LOUD (AIR PULSING) SOUND. PILOT COULD ONLY HEAR THE SOUND AFTER REMOVING NOISE CANCELLING HEAD SET. PILOT THEN SHUTDOWN ENGINE. INSPECTION REVEALED THE NR 4 CYLINDER TO BE CSDR 0001Cylinder · crackedPILOT WAS INFORMED BY LINE PERSONNEL DURING TAXI TO TIE DOWN, THAT ENGINE WAS MAKING A LOUD (AIR PULSING) SOUND. PILOT COULD ONLY HEAR THE SOUND AFTER REMOVING NOISE CANCELLING HEAD SET. PILOT THEN SHUTDOWN ENGINE. INSPECTION REVEALED THE NR 4 CYLINDER TO BE CSDR 2007FA0001017Turbocharger · crackedFOUND APPROX 1.25 INCH CRACK IN TURBO CHARGER HOUSING BELOW EXHAUST INLET AT WELD. (K)SDR 2007FA0000749Exhaust Pipe · crackedDURING COMPLIANCE WITH AD 2000-01-16 THE TAIL PIPE ON THE RT ENGINE WAS FOUND WITH A 6 INCH CRACK. THE LAST INSPECTION WAS 40 HRS PRIOR.SDR 2007FA0000713Cylinder · leakingWHILE PERFORMING OTHER MAINTENANCE A FUEL STAIN WAS NOTICED BETWEEN THE SECOND AND THIRD COOLING FIN AFT OF THE FUEL INJECTOR ON THE NR 6 CYLINDER OF THE RT ENGINE. THIS CONDITION PROMPTED A CLOSER INSPECTION OF THE ENGINE RESULTING IN THE DISCOVERY OF SIMILA
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