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 2002FA0001163Cylinder Head · separatedENGINE CYLINDER HEAD AND BARREL SEPERATED DURING ENGINE RUN.SDR 2002FA0001164Cylinder Head · separatedENGINE CYLINDER HEAD AND BARREL SEPERATED.SDR MW22002F00000Crankshaft · brokenCRANKSHAFT BROKEN IN TWO PIECES AT NR 3 ROD CHEEK.SDR 2002F00758Cylinder Head · crackedCYLINDER HEAD SEPERATED FROM BARREL DURING CLIMB OUT. ENGINE FEATHERED AND AIRCRAFT LANDED SAFTELY. CYLINDER HEAD CRACKED ABOVE THREADED AREA TO BARREL.SDR 2002FA0000822Swivel · failedTHIS ITEM IS INSTALLED ON A CESSNA T337G THAT HAS HAD TCM TSIO-520 ENGINES INSTALLED AS AN STC MODIFICATION. THE PART IS A BALL-TYPE SWIVEL THAT CONNECTS THE MIXTURE CABLE TO THE MIXTURE CONTROL ARM. THE BALL HAS PULLED OUT OF ITS SWAGED HOUSING. THIS IS THE TSDR CA020722006Sight Tube · failed(CAN) SUSPECT HYDRAULIC FLUID OVERHEATED AND MELTED RESERVOIR SIGHT TUBE. HYDRAULIC RESERVOIR THEN LEAKED ALL FLUID OVERBOARD, THROUGH OPEN SIGHT TUBE PORTS. PILOT DEACTIVATED NORMAL HYDRAULIC SYSTEM, AND USED EMERGENCY BLOW DOWN SYSTEM TO LOCK LANDING GEAR DOSDR CA020614001Seal · cracked(CAN) RIGHT GEAR HAD LOST ITS NITROGEN CHARGE DURING FLIGHT. REPLACED SEALS IN OLEO AND WHILE SERVICING OLEO IT WAS NOTED HYDRAULIC FLUID WAS APPEARING IN LOWER AREA OF BARREL. ON CLOSER INSPECTION FOUND BARREL CRACKED AT POINT WHERE BARRELL IS FITTED WITH MAISDR CA020325006Fuseable Plug · open(CAN) NORTHWEST OF CALGARY (CYYC)APPROX. 15 MINS AFTER TAKEOFF, A/C SUFFERED TOTAL ELECT. FAILURE: EMERG DESCENT INITIATED. ATC INFORMED. EMERG DECLARED, & PILOT ALTERED COURSE FOR RED DEER, ALBERTS (CYQF). LDG GEAR COULD NOT BE LOWERED IN NORMAL MANNER BECAUSSDR 2002FA0000130Valve · faultyREPLACED DEFECTIVE SURFACE DEICE CONTROL VALVE WITH NEW 2H48-14 S/N 2AU 29. ON RUN CHECK FOUND SYSTEM TO HAVE UNCOMMANDED SURFACE DEICE ACTIVATION. CHECKED SYSTEM AND FOUND NEW VALVE LEAKING FROM FAULTY ASSEMBLY AT RIVETED TOP CAP WHERE SOLENOID IS ATTACHED.SDR 2001F00758Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. APPEAR TO BE MANUFACTURING DEFECTS.SDR 2001F00764Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. APPEAR TO BE MANUFACTURING DEFECTS.SDR 2001FA0000589Crankshaft · brokenCRANKSHAFT BROKE IN 3 SECTIONS, HAD 595.9 SMOH. NO SIGNS OF OIL STARVATION.SDR 2001FA0000661Coupling · shearedPNEUMATIC PUMP COUPLING SHEARED AFTER 230.7 HOURS OF OPERATION.SDR 2001F00763Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. APPEAR TO BE MANUFACTURING DEFECTS.SDR 2001FA0000531Screw · brokenDOWNLOCK ADJUSTING SCREW BROKE FOR REASONS UNKNOWN.THIS ALLOWED LEFT MAIN GEAR TO LOSE DOWNLOCK TENSION. LEFT MAIN LANDING GEAR RETRACTED UNTIL IT STOPPED AGAINST INBOARD GEAR DOOR. THIS ALLOWED PROP TO HIT THE GROUND AND DAMAGE TO LEFT FLAPS OCCURED.SDR 2001FA0000545Magneto · corrodedPILOT NOTED INTERMITTENT ROUGH ENGINE AND FLUCTUATING EGT. DURING SUBSEQUENT TROUBLE SHOOTING, NOTED ONLY ONE IMPULSE COUPLING SOUND. WHEN PULLING ENGINE THROUGH WITH SPARK PLUGS OUT AND TIMING WAS WAY OFF. UPON REMOVAL FOUND THAT COULD BARELY TURN THE MAGSDR 2001F00436Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. FOUR CLAMPS IN 201 HOURS. ALL CLAMPS APPEAR TO BE MANUFACTURING DEFECTS. NON LIFE LIMITED CLAMPS.SDR 2001F00448Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. TWO CLAMPS IN LAST 200 HOURS. BOTH APPEAR TO BE MANUFACTURING DEFECTS. NON LIFE LIMITED CLAMPS.SDR 2001FA0000662Pump · shearedPNEUMATIC PUMP SHEARED AFTER 113 HOURS OF OPERATION. PUMP COULD BE ROTATED WHEN REMOVED. COUPLING SHOWED SIGNS OF HEAT (MELTED EDGES).SDR 2001F00757Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. APPEAR TO BE MANUFACTURING DEFECTS.SDR 2001F00762Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. APPEAR TO BE MANUFACTURING DEFECTS.SDR 2001F00756Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. APPEAR TO BE MANUFACTURING DEFECTS.SDR SAE06011Camshaft · damagedTHIS ENGINE WAS RECEIVED FOR REPAIR OF METAL IN THE OIL FILTER. ENGINE WAS RECEIVED WITHOUT THE EXHAUST AND TURBOCHARGER SYSTEMS, AS THESE ARE MAINLY AIRFRAME MOUNTED. THE EXCEPTION IS THAT THE RAM CONVERSION OF THIS ENGINE INCREASES BOTH THE MAXIMUM POWER OSDR SAE06012Camshaft · damagedTHIS ENGINE WAS RECEIVED FOR REPAIR OF METAL IN THE OIL FILTER. NO REFERENCE ON THE ORDER AS BEING RAM CONVERSION. THE ENGINE WAS RECEIVED WITHOUT THE EXHAUST AND TURBOCHARGER SYSTEMS. THESE ARE MAINLY AIRFRAME MOUNTED. THE RAM CONVERSION OF THIS ENGINE INSDR 2001F00761Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. APPEAR TO BE MANUFACTURING DEFECTS.SDR 2001F00760Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. APPEAR TO BE MANUFACTURING DEFECTS.SDR 2001F00759Clamp · crackedNEW AEROQUIP EXHAUST CLAMPS ARE CRACKING AROUND OUTER PERIPHERY. APPEAR TO BE MANUFACTURING DEFECTS.SDR CA010409010Pump · failed(CAN) LT ENGINE WOULD NOT RUN WITHOUT AUXILIARY ELECTRIC FUEL PUMP ON HIGH. FUEL PUMP AT DRIVE REPLACED, GROUND CHECKED OK.SDR 20010124CW012Crankshaft · brokenCRANKSHAFT BROKEN IN FRONT OF NR1 ROD JOURNAL. LESS THAN 100 HOURS SINCE OVERHAUL.ATTACHED PICTURES WITH ORIGINALSDR CA000927009Line · chafed(CAN) DURING GROUND HANDLING FUEL LEAK ON LT ENGINE WAS OBSERVED. FURTHER INVESTIGATION REVEALED THAT FUEL LINE BETWEEN FCU AND FUEL LIMITER WAS CHAFED THROUGH. TEMPORARY REPAIR TO FLY AIRCRAFT BACK TO HOME BASE. AT HOME BASE FUEL LINE REPLACED BY NEW AND AIRCSDR CA000801027Pump · shorted(CAN) THE ELECTRICAL WIRE WHERE IT ENTERS THE PUMP HAS SHORTED. THIS WIRE IS COVERED BY A BRAIDED WIRE. NO DISASSEMBLY HAS BEEN CARRIED OUT, HOWEVER, 24V WAS APPLIED TO PUMP TO CONFIRM SHORT. SUBMITTER STATED THIS IS THE SECOND PUMP REPLACEMENT ON THIS AIRCSDR CA000824029Seat · cracked(CAN) PILOTS SEAT SUPPORT LEFT/RIGHT CHANNELS CRACKED / BROKEN / MISSING PIECES. NEW LEFT / RIGHT SUPPORT CHANNELS FABRICATED AND INSTALLED. FOUND DURING ROUTINE SCHEDULED INSPECTION.SDR 20000803SH012Crankshaft · brokenRIGHT ENGINE CRANKSHAFT BROKE IN CRUISE FLIGHT 15,000 FEET, 31 FEET MP, 2,300 RPM, NR 1 PISTON NOT MOVING WHEN PROPELLER IS TURNED. NR 5 CYLINDER, NO COMPRESSION. METAL FOUND IN OIL FILTER AND GOVERNOR GASKET SCREEN. (X)SDR 20000707SH003Crankshaft · brokenRIGHT ENGINE CRANKSHAFT BROKE IN CRUISE FLIGHT 15,000 FEET, 2,300 RPM. NR 1 PISTON NOT MOVING WHEN PROPELLER IS TURNED. NR 5 CYLINDER, NO COMPRESSION. METAL FOUND IN OIL FILTER AND GOVERNOR GASKET SCREEN. (X)SDR 20000531SH010Collar · scoredPROPELLER FEATHERING AT HIGH RPM''S. OIL TRANSFER COLLAR WAS SCORED CAUSING INSUFFICIENT OIL PRESSURE BETWEEN COLLAR AND CRANKSHAFT PILOT SHAFT. RECOMMEND DESIGN CHANGE ON TRANSFER COLLAR, OR CRANKCASE MODIFICATION TO ALLOW REPLACEMENT OF LEFT HALF OF COLLARSDR CA000621016Elbow · cracked(CAN) MINOR HEAT STRESS CRACK ADJACENT TO EXISTING SEAM WELD.SDR 20000613SH025Coupling · cracked***TONY, LAST SENTENCE?????***WASTEGATE ELBOW COUPLING INSTALLED ON RAM SERIES VII C-340 AND 414, IAW STC SA4331SW. FOUND CRACKED AND REPLACED EACH 50 - 100 HOURS FOR 150 HOURS. (X)SDR CA000530037Connector · burned(CAN) DURING CRUISE FLIGHT, ONE POST LIGHT CONNECTOR BURNT. IT APPEARED THAT THE CONNECTOR SPRING BROKE AND CAUSED AN ARC, OVERHEATING THE CONNECTOR AND CAUSING SMOKE IN THE COCKPIT. THE LIGHTING SYSTEM WAS DEACTIVATED AND THE AIRCRAFT RETURNED TO BASE.SDR 20000515SH013Beam · corrodedENGINE BEAM FOUND EXFOLIATED/CRACKED ON THE TOP OUTBOARD ANGLE, JUST FORWARD AND INBOARD OF THE TAILPIPE. AD 2000-01-16 PAR(D) HAD BEEN C/W 64 HOURS AND 10 WEEKS PREVIOUSLY. (X)SDR 20000504SH025Crankshaft · failedENGINE IN-FLIGHT FAILURE DUE TO BROKEN CRANKSHAFT. THIS CRANKSHAFT INSTALLED AS NEW ON MAY 4, 1999 TO REPLACE PREVIOUS NEW CRANKSHAFT AFFECTED BY AD 99-19-01. THIS S/N CRANCKSHAFT, SN B129901N, IS NOT IN AD. CRNAKSHAFT S/N''S IN AD GO THROUGH 12-1998. (X)SDR 20000407SH033Crankcase · crackedCRANKCASE CRACKED FROM BASE OF NR 4 CYLINDER ACROSS THE TOP OF THE BACKBONE TO THE BASE OF NR 3 CYLINDER. CAUSE UNKNOWN AT THIS TIME. (X)SDR CA000218006Clamp · dislodged(CAN) DURING TAKEOFF, AN INDUCTION PIPE SEAL CLAMP SLIPPED OFF, CAUSING AN INDUCTION AIR LEAK AND SUBSEQUENT LOSS OF POWER.SDR AU000128025Engine · making metal(AU) ENGINE MAKING METAL.SDR CA000118026Bolt · missing(CAN) DURING SERVICING OF THE AIRCRAFT TIRES, MAINTENANCE PERSONNEL NOTICED A WHEEL THRU BOLT MISSING FROM A MAIN WHEEL. 300 HOURS LATER A SECOND BOLT WAS FOUND MISSING AT WHICH TIME ALL WHEEL BOLTS WERE REPLACED WITH NEW,AND NEW NUTS AND WASHERS WERE ALSO INSSDR 99ZZZX4384Pin · missingPURCHASED NEW CRANKSHAFT P/N 649898 FROM TELEDYNE CONTINENTAL AND RECEIVED WITH COUNTERWEIGHT PIN PN 643626-105 MISSING ON REAR COUNTERWEIGHT ASSY PN 639195. SUBMITTER RECOMMENDED THOROUGH INSPECTION ON ANY NEW PART OR ASSY.SDR 99ZZZX4385Tube · missingPURCHASED NEW CRANKSHAFT PN 649898 FROM TELEDYNE CONTINENTAL AND RECEIVED WITH ALL OIL SUPPLY TUBES MISSING PN 629757 TUBE. ALSO, FOUND LOOSE TUBE ON ANOTHER CRANKSHAFT. SUBMITTER SUGGESTED A THOROUGH INSPECTION OF ANY NEW PART OR ASSY.SDR 20000531SH011Crankcase · crackedBROKEN CYLINDER BASE STUDS AND 7TH STUD WERE FOUND AT NR 3 CYLINDER LOCATION. CRANKCASE STRESS WAS CAUSE OF CRANKSCASE TO CRACK (4 INCH CRACK) AT NR 3 CYLINDER. HIGH MANIFOLD PRESSURE MAY HAVE CONTRIBUTED TO THE CAUSE. ENGINE IS RATED TO 41 INCHES M/P FOR SDR CA991007068Trunnion · cracked(CAN) DURING SCHEDULED MAINTENANCE, LANDING GEAR WAS INSPECTED IAW CESSNA SB 79-11. THE LEFT MAIN LANDING GEAR TRUNNION WAS FOUND CRACKED IN THE UPPER WEB AREA BETWEEN THE ATTACH POINTS.SDR CA990804013Wire · shorted(CAN) ALTERNATOR FIELD WIRE AND VOLTAGE REGULATOR SHORTED, LEFT SYSTEM.SDR 99ZZZX2478Drive Gear · wornDURING ROUTINE MAINTENANCE, A METALLIC CLUNK WAS DETECTED WHILE ROCKING THE PROPELLER. FURTHER INVESTIATION REQUIRED REMOVAL OF THE ALTERNATOR. NOISE DID NOT EXIT WITH ALTERNATOR REMOVED. VISUAL INSPECTION OF THE RING GEAR ON THE CRANKSHAFT SHOWED IRREGULAR
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