Continental TSIO-520-R

Service difficulty reports · 129

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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.

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 WASJun 3, 2004 · N732WP · Cessna T210M · Engine Air Intake SystemSDR 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 MANDJun 3, 2004 · N7568M · Cessna T210M · Engine Air Intake SystemSDR 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 THMar 1, 2004 · N6246B · Cessna T210M · DC Generator-AlternatorSDR 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 UPFeb 20, 2004 · N210MT · Cessna T210N · Autopilot SystemSDR 2004FA0000208Cylinder · unserviceableINSPECTED NEW CYLINDER AS RECEIVED. FOUND EXHAUST VALVE GUIDE INSIDE DIAMETER TO BE BELOW MINIMUM SPECIFICATIONS, AND VALVE SEAT MACHINING NOT CONCENTRIC.Feb 11, 2004 · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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.Feb 10, 2004 · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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.Feb 3, 2004 · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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 NFeb 2, 2004 · N111VF · Cessna T210N · Exhaust TurbochargerSDR 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.Feb 2, 2004 · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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.Feb 2, 2004 · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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. ALLFeb 2, 2004 · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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.Feb 2, 2004 · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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.Feb 2, 2004 · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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.Feb 2, 2004 · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 2004FA0000021Vernatherm · failedVERNATHERM FAILED TO BYPASS OIL COOLER WHEN OIL TEMPS LOW.Dec 26, 2003 · N732YK · Cessna T210M · Engine Oil Indicating SystemSDR 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 IDSep 19, 2003 · N732YK · Cessna T210M · Reciprocating Engine Cylinder SectionSDR CA030916002Points · broken(CAN) POINT ASSEMBLY CONTACT ARM FAILED.Sep 15, 2003 · Cessna T210M · Magneto/DistributorSDR 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 TOJun 6, 2003 · N732XE · Cessna T210M · AC Generator-AlternatorSDR 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.Apr 16, 2003 · N6410N · Cessna T210N · Reciprocating Engine Oil SystemSDR 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.Mar 3, 2003 · N44EC · Cessna T210N · Nose/Tail Landing GearSDR GFV2002F00001Fuel Nozzle · dirtyFUEL NOZZLE THREADS AND ROCKER SHAFT BOLTS GRITTY.Sep 19, 2002 · N1974U · Cessna T210N · Reciprocating Engine Cylinder SectionSDR GFV2002F00002Fuel Nozzle · strippedFUEL NOZZLE THREADS NO GOOD. ROCKER SHAFT BOLTS STRIPPED.Sep 19, 2002 · N1974U · Cessna T210N · Reciprocating Engine Cylinder SectionSDR GFV2002F00003Fuel Nozzle · dirtyFUEL NOZZLE THREADS AND ROCKER SHAFT BOLT GRITTY.Sep 19, 2002 · N1974U · Cessna T210N · Reciprocating Engine Cylinder SectionSDR GFV2002F00004Fuel Nozzle · damagedFUEL NOZZLE THREADS, NO GOOD. ROCKER SHAFT BOLTS GRITTY.Sep 19, 2002 · N1974U · Cessna T210N · Reciprocating Engine Cylinder SectionSDR GFV2002F00005Fuel Nozzle · damagedROCKER COVER MATING SURFACE UN-EVEN AT WELD. FUEL NOZZLE THREADS, GRITTY.Sep 19, 2002 · N1974U · Cessna T210N · Reciprocating Engine Cylinder SectionSDR GFV2002F00006Rocker Cover · damagedDAMAGE TO ROCKER COVER MATING SURFACE. GRIT IN ROCKER SHAFT BOLT THREADS.Sep 19, 2002 · N1974U · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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 DIFFICApr 4, 2002 · N5132C · Cessna T210N · Nose/Tail Landing GearSDR 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 OJul 26, 2001 · N6506G · Cessna T210N · Manifold Pressure (MP) IndicatingSDR 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 RELJul 23, 2001 · N6506G · Cessna T210N · Manifold Pressure (MP) IndicatingSDR AUS20010557Transponder · faulty(AUS) TRANSPONDER GIVING FALSE ALTITUDE READINGS.May 18, 2001 · Cessna T210M · ATC Transponder SystemSDR 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 SJan 10, 2001 · Cessna T210M · Horizontal Stabilizer, Spar/RibSDR 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 elevatedDec 6, 2000 · N9403Y · Cessna T210N · Engine Exhaust SystemSDR 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, EXHAUSOct 15, 2000 · N967CC · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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 VSep 20, 2000 · N967CC · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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 6Aug 11, 2000 · N94203 · Cessna T210L · Magneto/DistributorSDR 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 6Aug 11, 2000 · N94203 · Cessna T210L · Magneto/DistributorSDR 20000516SH015Stud · brokenBOTH FORWARD AND AFT STUDS BROKEN HALF WAY OUT THROUGH .4375 INCH - 20 INCH THREADS. (X)Apr 27, 2000 · N730P · Cessna T210M · Reciprocating Engine Power SectionSDR 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 EXAJun 10, 1999 · N5360U · Cessna T210N · Reciprocating Engine Cylinder SectionSDR 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 PROPELLMay 7, 1999 · Cessna T210N · Propeller AssemblySDR 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 Apr 5, 1999 · N761VH · Cessna T210M · Reciprocating Engine Power SectionSDR 99ZZZX1116Pump · failedUNABLE TO TURN FUEL PRESSURE DOWN. UNABLE TO REGULATE PRESSURE.Feb 23, 1999 · N6622N · Cessna T210N · Engine Fuel PumpSDR 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.Dec 8, 1998 · N761AS · Cessna T210M · Reciprocating Engine Cylinder SectionSDR CA990318017Windshield · crazed(CAN) WINDOW CRAZED BEYOND LIMITS. REPLACED.Oct 23, 1998 · Cessna T210N · Flight Compartment WindowsSDR 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.Oct 1, 1998 · N4372Y · Cessna T210N · Engine Fuel PumpSDR 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.Oct 1, 1998 · N4702C · Cessna T210N · Engine Fuel PumpSDR 98ZZZX4323Cylinder · crackedDURING ANNUAL INSPECTION, FOUND ALL SIX CYLINDERS CRACKED BETWEEN TOP SPARK PLUG BOSS AND FUEL INJECTOR NOZZLE BOSS.Oct 1, 1998 · N67VM · Cessna P210N · Reciprocating Engine Cylinder SectionSDR 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.Sep 11, 1998 · N9535Y · Cessna T210N · Reciprocating Engine Power SectionSDR CA981006011Blade · corroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND ALL THREE BLADES HAD BEEN FIELD MODIFIED BELOW MINIMUM WIDTH.Aug 28, 1998 · Cessna T210M · Propeller Blade SectionSDR 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.May 15, 1998 · Cessna 210M · Reciprocating Engine Oil SystemSDR 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 Jul 21, 1997 · N5203A · Cessna T210N · Reciprocating Engine Oil System
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