Continental TSIO-520-R
Service difficulty reports · 129
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 = 'TSIO520R' 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 = 'TSIO520R' 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 2004FA0000770Plate · separatedENGINE ALTERNATE AIR DOOR IS HELD CLOSED WITH A MAGNETIC LATCH ORIGINAL PN 1250938-8. THE MAGNETIC LATCH HAS 2 STEEL SMALL PLATES BONDED TO THE MAGNET THAT MAKE CONTACT WITH THE ALTERNATE AIR DOOR. ONE STEEL PLATE CAME DEBONDED FROM AGE VIBRATION. PLATE WASSDR 2004FA0000800Latch · failedDURING THE ANNUAL INSPECTION, FOUND THE PN 1250938-8, MAGNET LATCH ON THE ALTERNATE AIR DOOR WITH ONE OF ITS STEEL BONDED PLATES LOOSE AND READY TO FALL INTO THE TURBO, COULD CAUSE INFLIGHT FAILURE. INSTALLED THE NEW IMPROVED CATCH PN C100200. RECOMMEND MANDSDR PO82004F00000Alternator · failedALTERNATOR FAILED INFLIGHT AFTER 134 HOURS TSO. UNIT SENT OUT TO A CERTIFIED REPAIR STATION FOR REPAIR. TEARDOWN REPORT STATED ONE BAD BEARING AND A FAILED STATOR. PREVIOUS OVERHAULED ALTERNATOR LASTED FIVE MINUTES BEFORE AND THE OVERHAULED UNIT PRIOR TO THSDR 2004FA0000204Autopilot Sys · malfunctionedONCE ESTABLISHED IN CRUISE FLIGHT WITH ALTITUDE HOLD ENGAGED, THE S-TEC SYSTEM 55X AUTOPILOT FREQUENTLY BEGINS TO GENTLY PORPOISE IN PITCH. THIS GETS PROGRESSIVELY WORSE UNTIL THE AUTOPILOT CAUSES SERIOUS PITCH EXCURSIONS OF SEVERAL HUNDRED FEET PER MINUTE UPSDR 2004FA0000208Cylinder · unserviceableINSPECTED NEW CYLINDER AS RECEIVED. FOUND EXHAUST VALVE GUIDE INSIDE DIAMETER TO BE BELOW MINIMUM SPECIFICATIONS, AND VALVE SEAT MACHINING NOT CONCENTRIC.SDR 2004FA0000205Cylinder · mismanufacturedINSPECTED NEW CYLINDER AS RECEIVED. FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE DID NOT MEET MINIMUM SIZE DIMENSIONS AND VALVE SEAT MACHINING NOT CONCENTRIC.SDR 2004FA0000207Cylinder · unserviceableINSPECTED NEW CYLINDER ASSY TISN 71.2BCA AS RECEIVED. FOUND VALVE SEAT MACHINING NOT CONCENTRIC AND EXHAUST VALVE SEAT DIAMETER CUT TO APPX. 1.847 INCH WHEN IT SHOULD BE APPX. 1.781 INCH ACCORDING TO PRINT DIMENSIONS IN OVERHAUL MANUAL.SDR 2004FA0000199Inlet · mismanufacturedUPON INSPECTION OF NEW PARTS DEFECTS WERE FOUND WITH THE TURBO INLET COMPONENT. DAMAGE WAS NOTED ON THE TURBOCHARGER MOUNTING FLANGE AND THE WELDING HAD VERY POOR PENETRATION. PART REJECTED AND SENT BACK TO O/H FACILITY. UPON RECEIVING PARTS, FACILITY WAS NSDR 2004FA0000210Cylinder · mismanufacturedINSPECTED NEW CYLINDER ASSY AS RECEIVED. FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE DID NOT MEET MINIMUM MFG. DIMENSIONS, AND VALVE SEAT MACHINING NOT CONCENTRIC.SDR 2004FA0000211Cylinder · mismanufacturedINSPECTED NEW CYLINDER ASSY AS RECEIVED. FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MINIMUM MFG SPECS., AND VALVE SEAT MACHINING NOT CONCENTRIC.SDR 2004FA0000212Cylinder · unserviceableINSPECTED NEW CYLINDER ASSY. AS RECEIVED. FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MINIMUM MFG. SPECS. AND VALVE SEAT MACHINING NOT CONCENTRIC. PRE-SIZED GUIDES ARE USED ON THIS UNIT AND 5 OTHERS IN THIS BATCH INSPECTED. ALL UNAIRWORTHY. ALLSDR 2004FA0000213Cylinder · unserviceableINSPECTED NEW CYLINDER ASSY. AS RECEIVED. FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MFG. MINIMUM SPECS. AND VALVE SEAT MACHINING NOT CONCENTRIC.SDR 2004FA0000209Cylinder · mismanufacturedINSPECTED NEW CYLINDER ASSY. AS RECEIVED. FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MINIMUM MFG. SPECS. AND VALVE SEAT MACHING NOT CONCENTRIC.SDR 2004FA0000214Cylinder · unserviceableINSPECTED NEW CYLINDER ASSY. AS RECEIVED. FOUND INSIDE DIAMETER OF EXHAUST VALVE GUIDE TO BE BELOW MINIMUM MFG. SPECS. AND VALVE SEAT MACHINING NOT CONCENTRIC.SDR 2004FA0000021Vernatherm · failedVERNATHERM FAILED TO BYPASS OIL COOLER WHEN OIL TEMPS LOW.SDR 2003FA0001119Exhaust Valve · wornCYLINDER FAILED COMPRESSION CHECK DUE TO EXHAUST VALVE LEAKAGE. VISUAL INSPECTION REVEALED BURNED EXHAUST VALVE WITH NO SIGNS OF OVER TEMP OR CARBON BUILD UP. VALVE STEM AND GUIDE WORN BEYOND SERVICE LIMITS. EXHAUST VALVES IN CYLINDERS 4 AND 5 EXPERIENCE IDSDR CA030916002Points · broken(CAN) POINT ASSEMBLY CONTACT ARM FAILED.SDR RCO2003F00000Alternator · brokenWHILE INSTALLING A 135 AMP ALTERNATOR KIT UNDER A STC FROM MFG, IT LOOKED LIKE THE COOLING FAN PN 8-4 HAD A SMALL CRACK IN IT. THIS PULLEY IS A ONE-PIECE CAST ASSEMBLY MADE OF ALUMINUM. WHEN THE ALTERANTOR WAS REMOVED FOR CLOSER INSP, THE PULLEY WAS FOUND TOSDR CTU2003F00005O-Ring · leakingO-RING FAILED TO SEAL PROPERLY ALLOWING OIL TO LEAK AT THE OIL FILTER ADAPTER TO ENGINE ATTACHMENT. CAUSE OF THE FAILURE COULD BE ATTRIBUTED TO O-RING TOTAL TIME. ALL WORK WAS DOEN IAW MM AND INSTRUCTIONS CONTAINED IN AD 96-12-22.SDR 2003FA0000222Trunnion · brokenNOSE GEAR COLLAPSED DURING TAXI, AFTER LANDING, TOOK PLACE AFT NORMAL LANDING. COLLAR BROKE WHERE TRUNION ATTACHES TO NOSE GEAR BARREL, PREVIOUS CRACK EXISTED.SDR GFV2002F00001Fuel Nozzle · dirtyFUEL NOZZLE THREADS AND ROCKER SHAFT BOLTS GRITTY.SDR GFV2002F00002Fuel Nozzle · strippedFUEL NOZZLE THREADS NO GOOD. ROCKER SHAFT BOLTS STRIPPED.SDR GFV2002F00003Fuel Nozzle · dirtyFUEL NOZZLE THREADS AND ROCKER SHAFT BOLT GRITTY.SDR GFV2002F00004Fuel Nozzle · damagedFUEL NOZZLE THREADS, NO GOOD. ROCKER SHAFT BOLTS GRITTY.SDR GFV2002F00005Fuel Nozzle · damagedROCKER COVER MATING SURFACE UN-EVEN AT WELD. FUEL NOZZLE THREADS, GRITTY.SDR GFV2002F00006Rocker Cover · damagedDAMAGE TO ROCKER COVER MATING SURFACE. GRIT IN ROCKER SHAFT BOLT THREADS.SDR 2002FA0000686Trunnion · collapsedWHILE RETRIEVING AIRCRAFT FROM NOSE GEAR COLLAPSE, FOUND LOWER TRUNNION ASSEMBLY. BROKEN AT AFT SIDE WHERE COLLAR WRAPS AROUND GEAR. APPEARS THERE WERE CRACKS AT LEFT AND RIGHT TOP CORNERS JUST FORWARD OF THE BRACE SUPPORT MOUNTS. THEY ARE IN A VERY DIFFICSDR 010726Relief Valve · malfunctionedAFTER A REBUILT TCM ENGINE WAS INSTALLED INTO THIS AIRFRAME A SECOND REBUILT ABSOLUTE PRESSURE RELIEF VALVE FROM CONSOLIDATED FUEL SYSTEMS, INC. WAS INSTALLED AND THE ENGINE WOULD NOT PRODUCE 36.5 IN OF MANIFOLD PRESSURE REQUIRED FOR TAKEOFF. REINSTALLED THE OSDR 010204Relief Valve · failedA TCM REBUILT ENGINE WAS INSTALLED INTO THIS AIRCRAFT WITH ALL THE ASSOIATED NEW PARTS. THE AIRCRAFT COULD NOT ACHIVE 36.5 IN. AT 2700 RPM FOR TAKEOFF POWER. ALL INDICATING INSTRUMENTS WERE VERIFIED FOR CALIBRATION. WE INSTALLED THE OLD ABSOLUTE PRESSURE RELSDR AUS20010557Transponder · faulty(AUS) TRANSPONDER GIVING FALSE ALTITUDE READINGS.SDR CA010131018Rib · cracked(CAN) DURING A 50 HOUR INSPECTION OF THE HORIZONTAL STAB, THE 4 RIBS WERE FOUND TO BE LOOSE & CRACKED. THIS IS DONE BY SQUEEZING THE NOSE RIBS (WITH A MODERATE AMOUNT OF PRESSURE) AND LISTEN FOR CLICKING SOUNDS & FEELING OF LOOSE RIVETS. THEREFORE, THE LOWER SSDR B3OR20010001Boot Assembly · small cutsThis aircraft has an electronic carbon monoxide detector. In cruise flight, the detector registered a reading of 98 ppm CO. OSHA limits exposure to 50 ppm in normal circustances, avation sources suggest a much more conservative 10 to 20 ppm due to the elevatedSDR 20001120SH003Valve · wornCYLINDER NR 4 REMOVED FOR LOW COMPRESSION DUE TO LEAKAGE PAST THE EXHAUST VALVE. THE REPAIR STATION THAT REPAIRED THE CYLINDER ASSY REPLACED THE INTAKE AND EXHAUST VALVES, EXHAUST VALVE GUIDE, AND ASSOCIATED PARTS. THE INTAKE VALVE''S FACE WAS CUPPED, EXHAUSSDR 20001120SH004Valve · wornCYLINDER NR 2 REMOVED FOR LOW COMPRESSION DUE TO LEAKAGE PAST THE INTAKE VALVE. THE REPAIR STATION THAT REPAIRED THE CYLINDER ASSEMBLY REPLACED THE INTAKE AND EXHAUST VALVES, EXHAUST GUIDE, AND ASSOCIATED PARTS. THE INTAKE VALVE''S FACE WAS CUPPED, EXHAUST VSDR 20000821SH008Magneto · corrodedPRESSURIZED SLICK MAGNETOS ON CESSNA T210L. DURING ANNUAL, INSPECTED MAGS INTERNALLY FOR CONDITION. FOUND SEVERE MOISTURE-CASED CORROSION ALL AROUND INSIDE. MAGNETO MANUAL CALLS FOR INSPECTION OF 6200 SERIES EACH 100 HOURS, NOTHING FOUND FOR INSPECTION OF 6SDR 20000821SH009Magneto · corrodedPRESSURIZED SLICK MAGNETOS ON CESSNA T210L. DURING ANNUAL, INSPECTED MAGS INTERNALLY FOR CONDITION. FOUND SEVERE MOISTURE-CASED CORROSION ALL AROUND INSIDE. MAGNETO MANUAL CALLS FOR INSPECTION OF 6200 SERIES EACH 100 HOURS, NOTHING FOUND FOR INSPECTION OF 6SDR 20000516SH015Stud · brokenBOTH FORWARD AND AFT STUDS BROKEN HALF WAY OUT THROUGH .4375 INCH - 20 INCH THREADS. (X)SDR 99ZZZX2440Bushing · misinstalledWHEN NR 2 CYLINDER WAS REMOVED FOR REPAIR, NOTED THE CONNECTING ROD BUSHING HAD BEEN PUSHED OUT OF THE CONNECTING ROD FOR A DISTANCE OF ABOUT .1250 INCH. FURTHER EXAMINATION OF THE ENGINE REVEALED 2 MORE BUSHINGS THAT HAD BEEN SIMILARLY DISPLACED. CLOSER EXASDR CA990514003Roll Pin · missing(CAN) AFTER PROPELLER INSTALLATION, WHILE CARRYING OUT AN ENGINE RUNUP AT 2,700 RPM, THERE WAS A VIBRATION SIMILAR TO MISS ON A CYLINDER. THE ENGINE WAS SHUT DOWN. P OST RUNUP INVESTIGATION FOUND THAT ONE OF THE PROP BLADES COULD BE MOVED BY HAND. T HE PROPELLSDR 99ZZZX1885Lifter · spalledDURING 100-HOUR INSPECTION, FOUR CYLINDERS SHOWED LOW COMPRESSION. UPON REMOVAL OF CYLINDERS, NOTED THE NR 5 CYLINDER EXHAUST CAM FOLLOWER WAS SPALLED BAD. INSPECTION OF CAM LOBE DID NOT APPEAR NEARLY AS BAD AS CAM FOLLOWER. CAMSHAFT AND CAM FOLLOWERS WERE SDR 99ZZZX1116Pump · failedUNABLE TO TURN FUEL PRESSURE DOWN. UNABLE TO REGULATE PRESSURE.SDR 98ZZZX4791Lifter · failedSPALLED LIFTER WAS FOUND AFTER NR 1 CYLINDER WAS REMOVED DUE TO LOW COMPRESSION. SUSPECT MANUFACTURING DEFECT OR OIL FILM FAILURE. ENGINE WAS USING AEROSHELL 15W-50.SDR CA990318017Windshield · crazed(CAN) WINDOW CRAZED BEYOND LIMITS. REPLACED.SDR 98ZZZX4076Fuel Pump · out of adjustENGINE CAME IN RUNNING ROUGH. FOUND FUEL PRESSURE HIGH. ADJUSTED PUMP AND RETURNED TO SERVICE. APPROXIMATELY 50 HOURS LATER, AIRCRAFT CAME IN WITH THE SAME CONDITION. THE THIRD TIME, PUMP WOULD NOT ADJUST AND PUMP WAS REJECTED.SDR 98ZZZX4077Fuel Pump · leakingAFTER ENGINE INSTALLATION POST-RUN, THE FUEL PUMP LEAKED FORM DRAIN TUBE. RAN ENGINE SEVERAL MORE TIMES. THIS DID NOT REMEDY THE CONDITION.SDR 98ZZZX4323Cylinder · crackedDURING ANNUAL INSPECTION, FOUND ALL SIX CYLINDERS CRACKED BETWEEN TOP SPARK PLUG BOSS AND FUEL INJECTOR NOZZLE BOSS.SDR 99ZZZX269Bolt · failedHEAD SEPARATED FROM ROD BOLT. SUBMITTER STATED CONTINENTAL ALSO ALLOWED RE-USE. CRUISE FLIGHT FAILURE. SUBMITTER SUGGESTED CONTINENTAL SPECIFY MANDATORY ROD BOLT REPLACEMENT WITH NEW AT OVERHAUL.SDR CA981006011Blade · corroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND ALL THREE BLADES HAD BEEN FIELD MODIFIED BELOW MINIMUM WIDTH.SDR AU980660Hose · burnt(AUS) FLEXIBLE OIL SUPPLY LINES TO TURBOCHARGER AND OIL PRESSURE HOSE BURNT DUE TO BEING ROUTED UNDER THE REAR EXHAUST PIPE. ONE HOSE HAD BEEN BURNT SUFFICIENTLY FOR OIL LEAKAGE TO OCCUR.SDR 97ZZZX3693Oil Tube · dislodgedDISCOVERED AT MAJOR OVERHAUL. NEW VAR CRANKSHAFT INSTALLED 1985, ACCUMULATED 1,550 HOURS. FOUND NR 3 OIL TUBE (INSIDE SHAFT) HAD DISLODGED AND WORKED ITS WAY OUT AND HAD PRACTICALLY CUT THE BEARING IN HALF. SUBMITTER BELIEVES THE VAR CRANKSHAFT HAS AS MANY
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