Continental TSIO-520 series
Service difficulty reports · 403
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 = 'TSIO520' 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 = 'TSIO520' 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 2001FA0000519Skin · crackedFOUND ONE INCH LONG CRACK IN AFT UPPER FUSELAGE SKIN AT BASE OF VERTICAL FIN. CRACK STARTS AT LEFT FORWARD STABILIZER SPAR EXTENSION CUTOUT AND EXTENDS UPWARD. SUSPECT LACK OF PROPER RADIUS IN CORNER OF CUTOUT CREATED A STRESS RISER WHICH CAUSED THE SKIN TO SDR 2001FA0000520Skin · crackedLOWER INBOARD LEADING EDGE SKIN CRACKED BETWEEN FUEL TANK DRAIN FITTING HOLE AND REAR EDGE OF SKIN. CRACK IS THROUGH AND AREA APPROXIMATELY 2 INCHES WIDE THAT HAS NO RIVET CONNECTING SKIN TO FRONT SPAR STRUCTURE. NORMAL FLEXING OF WING APPEARS TO BE STRESSINSDR HYI2001F00006Master Switch · failedON PREFLIGHT INSPECTION AVIONICS MASTER SWITCH AND RETURNED AIRCRAFT TO SERVICE.SDR HYI2002F00007Master Switch · failedON PRE-FLIGHT INSPECTION AVIONICS MASTER SWITCH FAILED. MAINTENANCE REPLACED SWITCH AND RETURNED AIRCRAFT TO SERVICE.SDR HYI2001F00001Master Switch · failedWHILE AIRCRAFT WAS TAXING, AVIONICS SYSTEM FAILED. CREW ENGAGED EMERGENCY AVIONICS BY PASS SWITCH, AND RETURNED TO THE GATE. MECHANICS REMOVED AND REPLACED AVIONICS MASTER SWITCH AND RELEASE AIRCRAFT BACK TO SERVICE.SDR 2001FA0000398Throttle Cable · chafedPILOT COMPLAINED, RIGHT THROTTLE VERY STIFF, THROTTLE HAD BEEN REPLACED FOUR MONTHS EARLIER FOR SAME REASON. UPON REMOVAL IT WAS DISCOVERED THAT THE CABLE, WHICH WAS COVERED WITH FIRE SLEEVE, HAD BEEN CHAFFING ON THE LOWER PART OF THE TURBOCHARGER COMPRESSOR SDR 2001FA0000458Lifter · spalledDURING ROUTINE OIL CHANGE, METAL WAS FOUND IN FILTER. ENGINE WAS REMOVED AND DISASSEMBLED. CAUSE WAS FOUND TO BE LIFTER FACE AND CAM LOBE SPALLING ON CYLINDER CAM LOBES NR5 AND NR6 INTAKE. NO CORROSION NOTED. TWO OTHER INTAKE LIFTERS EXHIBIT PREMATURE WEARSDR 2001FA0000459Cylinder · out of toleranceCUSTOMER COMPLAINED OF INTERMITTENT ROUGHNESS. REMOVAL OF CYLINDERS REVEALED STICKING INTAKE VALVES. GUIDE TO VALVE TOLERANCE TOO TIGHT, BELOW MFG MINIMUM LIMITS. MFG CLAIMS TOLERANCE TOO TIGHT FROM NORMAL OPERATION. NO BUILD UP NOTED OF ANY KIND ON VALVE SDR 2001FA0000361Rib · crackedLEFT WING RIB CRACKED WHERE LEFT FLAP BELLCRACK SUPPORT BRACKETS ARE MOUNTED, CRACK RUNS FROM INBOARD LOWER SUPPORT BRACKET RIVET HOLE APPROX. ONE(1) INCH IN LENGTH DOWN AND TO THE LEFT. PROBABLE CAUSE: FLAPS EXTENDED AT TOO HIGH OF AN AIRSPEED.SDR FPI2001F00000Trunnion · crackedTHE PN 1243009-7 TRUNNION ASSEMBLY CRACKED AT THE TRUNNION ASSEMBLY-LOWER (ITEM 14), WHERE THE TWO LEGS MEET THE CIRCULAR PORTION THAT ATTACHES TO THE BARREL ASSEMBLY. THIS PART SHOWED SIGNS OF A PRE-EXISTING CRACK AT BOTH LEGS. THIS AREA IS DIFFICULT TO INSSDR HYI2001F00004Circuit Breaker · failedAVIONIC CIRCUIT BREAKER/SWITCH FAILED IN FLIGHT CAUSING COMPLETE AVIONIC FAILURE CREW UTILIZED EMERGENCY AVIONIC BUS SWITCH AND LANDED WITHOUT INCIDENT. SEVERAL SUCH FAILURES RECORDED RECENTLY. THIS SWITCH HAS A HIGH UTILIZATION FACTOR.(K)SDR 2001FA0000380Line · chafedBRAKE LINE ROUTED UNDER THE CO-PILOTS SEAT PEDESTAL AREA IS CHAFFING ON HEAT DUCT TUBING. SLIDING A 193-6 LOW PRESSURE HOSE OVER THE BRAKE LINE WILL KEEP THE BRAKE LINE FROM DEVELOPING A HOLE.SDR FD62001F00000Strobe · burned outPRIOR TO ROLLOUT, PILOT ACTIVATED THE PULSELIGHT SWITCH. AS HE WAS ON ROLLOUT, THERE WAS SMOKE IN THE CABIN. PILOT ABORTED TAKEOFF AND THE AIRCRAFT WAS TAKEN TO MAINTENANCE. THE TECH FOUND THE INSTALLATION NOT TO BE IAW THE STC INSTALLATION INSTRUCTIONS. (TSDR 2003FA0000400Bumper Block · debondedLT AND RT MAIN LANDING GEAR SHELL BUMPER DEBONDS. THE BUMPER EDGES CURL OVER PREVENTING MAIN GEAR STRUT FROM MAKING FULL DOWN TRAVEL. THIS CONDITION PREVENTS MAIN GEAR STRUT FROM CONTACTING DOWNLOCKS AND PROPER DOWNLOCK SWITCH ACTUATION, THEREFORE, AN UNSAFESDR 2001FA0000456Line · chafedRIGHT BRAKE LINE HAD A HOLE CHAFFED IN IT FROM BEING IN CONTACT WITH THE LINE HEATER DUCT LINE UNDER THE CO-PILOTS SEAT. THE BRAKE LINE RUNS UNDER THE HEAT DUCT AND IS VERY DIFFICULT TO SEE. THIS IS AN ORIGINAL PART.SDR QTV2001F00000Control Cable · brokenON SHORT FINAL THE CABLE BROKE AND THE LEFT FLAP RETRACTED WHICH CAUSED A SPLIT FLAP CONDITION. REPLACED CABLE . INSPECTED THE OTHER FLAP CABLES, NO DEFECTS NOTED.SDR 2002FA0000105Housing · fracturedON FINAL APPROACH, CREW NOTICED OIL LEAKING FROM LEFT ENGINE COWL. OIL PRESSURE AND TEMPERATURE WERE INDICATING NORMAL. CREW SHUT DOWN LEFT ENGINE AS A PRECAUTION AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND SCAVENGE PUMP HOUSING FRACTURED AND LEAKING. TSDR B4O2001F00000Sealant · deterioratedTHE WINGS WERE OPENED TO COMPLY WITH A 1200 HOUR INSPECTION AND THE FOLLOWING SITUATION WAS FOUND: 1) SEALANT: TURNING BROWN/TAN, TEXTURE: SOFTER THAN NORMAL WITH FUEL DRAINED AND TANK PLATES OPEN, AFTER 4 DAYS EXPOSED TO AIR, SEALANT TEXTURE WAS RETURNING TOSDR 2002FA0000028Fuel Cell · rottedRIGHT OUTBOARD WING FUEL CELL (PN 4142-4) REPLACES (PN 5026102-4). FUEL CELL IS 11 YEARS OLD. MPG, DATE 2-90. FUEL CELL CAME APART (TOTALLY ROTTEN AND BRITTLE) AT TOP OF FILLER NECK. FUEL CELL WAS MADE OF DIFFERENT MATERIAL, NOT OF THE NORMAL RUBBER. BAD SDR GNB2001F00000Wastegate Valve · failedUNABLE TO CONTROL MAIN PRESSURE.SDR GNB2001F00001Pump · erraticENGINE DRIVEN FUEL PUMP - FUEL PUMP ERRATIC ON UNMETERED FUEL PRESSURES.SDR 2001FA0000350Controller · failedUNABLE TO CONTROL MANIFOLD PRESSURESDR NT22001F00000Bulkhead · crackedDURING ANNUAL INSPECTION, THE LEFT TIP TANK AFT SUPPORT BULKHEAD PN 0823400-109, WAS FOUND TO BE CRACKED. THE CRACK WAS LOCATED APPROXIMATELY .2500 INCH ABOVE THE TOP ADJUST HOLE THAT ATTACHES THE FORWARD DOUBLER TOT THE -109 BULKHEAD. THE CRACK WAS APPROX SDR 2001FA0000267Tube · corrodedFATAL INTERNAL CORROSION, CAUSED BY TRAPPED MOISTURE INSIDE PUSH PULL CONTROL TUBE FOR AILERON. CORROSION WAS FOUND DURING ANNUAL INSPECTION.SDR CDH2001F00000Oil Cooler · crackedOVERHAULED OIL COOLER CRACKED AT LOWER MOUNTING FLANGE. REPLACEMENT OVERHAULED OIL FAILED (ONE OF THE CENTER TUBES BURST) INFLIGHT AFTER 1.5 HOURS. ENGINE LOST 4 QUARTS IN 10 MINUTES.SDR 20010430CW004Engine · lack of lubeOWNER DISCOVERED A GREAT LOSS OF ENGINE OIL, FOLLOWING A COLD WEATHER FLIGHT. TEMPERATURE WAS 40 DEGREES C/F. AIR/OIL SEPARATOR INSTALLED PRIOR TO RECENT CYLINDER REPLACEMENT.SDR 20010507CW003Alternator · malfunctionedAIRCRAFT UNDER IMC WHEN LOW VOLT LIGHT CAME ON AND VOLTAGE DROP TO 23.0 VOLTS. PILOT SHUT EVERYTHING OFF AND DECLARED AN EMERGENCY WITH CASCADE APPROACH. LANDED WITHOUT INCIDENT. PART WAS UNDER WARRANTY SO COULD NOT DISASSEMBLE TO FIND OUT CAUSE OF FAILURE,SDR 20010514CW008Exhaust Pipe · damagedWHILE ON FINAL APPROACH, THE PILOT REPORTED A LOSS OF MANIFOLD PRESSURE WITH THE RIGHT ENGINE. IT WAS FOUND THAT THERE WAS A HOLE APPROX 1.5 X 3.0 INCHES IN THE RIGHT ENGINE EXHAUST, MOST SPECIFICALLY FOCUSED AROUND THE NR 3 CYLINDER EXHAUST PIPE. THE EXHAUSDR 20010416CW002Structure · damagedTHE 206 SEAPLANE RUDDER ASSEMBLY IS PRONE TO DAMAGE AFT OF PN 12310661, DOUBLER AT THE BOTTOM OF THE RUDDER. DAMAGE OF THIS NATURE IS EVIDENT BY A KINK AT THE BOTTOM OF THE RUDDER ON BOTH SIDES. THIS DAMAGE IS CAUSED BY THE WIND WHEN A RUDDER LOCK IS NOT USSDR 20010413CW009Resistor · brokenAUTOPILOT WAS INOPERATIVE IN PITCH. THE PITCH RESISTOR WAS BROKEN CAUSING THE AUTOPILOT TO BE INOPERATIVE. THE PART IS ON THE CONTROL UNIT.SDR 20010508CW009Coil · inoperativeMAGNETO INOPERATIVE BELOW 1,000 RPMS. OK AT 1,700 RPMS PER THE P.O.M. PILOTS HAD DONE A MAG CHECK AT IDLE WHICH LEAD TO THE DISCOVERY. OPENED MAGNETO FOR INSPECTION. TESTED COIL AND FOUND SECONDARY WINDING. RESISTANCE TOO HIGH BY FACTOR OF 10.SDR 20010418CW006Jam-Nut · crackedGOVERNOR JAM NUT AS INSTALLED BY OVERHAULER RESULTED IN CRACKED STOP WHEN ADJUSTED AND RETIGHTENED. GOVERNOR STOP ARM HAS A FLAT SURFACE AND CURVED SURFACE THROUGH WHICH THE STOP BOLT IS ATTACHED. TRADITIONALLY WE HAVE SEEN THE JAM NUT ON THE FLAT SURFACE. SDR 20010416CW010Control Cable · brokenCABLE SNAPPED BY FIRST PULLEY OUTBOARD OF FLAP MOTOR, RIGHT SIDE. NO EVIDENCE OF WEAR OR CORROSION. PULLEY WAS TURNING FREE. FAILURE CAUSED SPLIT FLAPS ON LANDING.SDR 20010406CW010Pressure Switch · inoperativeFOUND COMBUSTION AIR PRESSURE SWITCH IN THE CLOSED POSITION WHEN HOOKED UP BETWEEN THE COMMON AND NORMAL OPEN TERMINALS WHEN NO PRESSURE WAS PRESENT. THIS IS THE NEW STYLE PRESSURE SWITCH, WHICH DOES NOT REQUIRE TESTING.SDR 20010417CW012Clamp · brokenENROUTE, CRUISE. LT ENGINE TURBOCHARGER DAMAGED, BROKEN SHAFT AND SEIZED. PILOT FEATHERED LEFT PROP, SECURED ENGINE AND HAD SINGLE ENG LANDING. LANDED SAFELY. TANG PORTION OF CLAMP FOUND BROKEN OFF.SDR 20010328CW006Window · failedAIRCRAFT HAD BEEN CRUISING AT FL240 FOR 1 HOUR PLUS TEMP-40 DEGREE. ON DESCENT OUT OF FL200 THE LEFT MID CABIN WINDOW BLEW OUT OF AIRCRAFT, CABIN DEPRESSURIZATION. PILOT CONTINUED DESCENT TO LOWER ALTITUDE AND LANDED WITHOUT FURTHER INCIDENT. WINDOWS WEW INSDR 20010403CW011Strut · dischargedUPON GEAR RETRACT, HYDR PRES LIGHT REMAINED ILLUMINATED. GEAR EXTENSION WAS ATTEMPTED, NOSE GEAR FAILED TO EXTEND. GEAR WAS EXTENDED USING EMERGENCY BLOW DOWN PROCEDURE, ALL GEAR DOWN INDICATORS SHOWED GREEN AND AIRCRAFT LANDED WITHOUT INCIDENT. MECH FOUND SDR 20010406CW007Skin · crackedDURING SCHEDULED INSPECTION OF AIRCRAFT, FOUND CRACKS IN LEFT AND RIGHT UPPER WING SKINS APPROXIMATELY 5 IN TO 6 INCHES IN LENGTH FORWARD OF WING BAGGAGE LOCKER AND AFT OF FIREWALL OVER CENTER RIBS AT WING STATIONS 57.50. THIS AREA IS NORMALLY COVERED BY NACSDR 20010319CW001Brake · leakingWHILE INVESTIGATING HYDRAULIC LEAK EVIDENCE ON BELLY OF AIRCRAFT, FOUND RIGHT PILOTS BREAK LINE UNDER THE FLOOR, WET. PRESSURE TEST OF LINE SHOWED PIN HOLE DUE TO CORROSION. ROUTING OF LINE PUTS IT AGAINST HEAT DUCT HOSE, WHICH APPREARS TO REACT WITH THE 505SDR 20010322CW003Bulkhead · crackedHORIZONTAL STABILIZER WAS REMOVED FOR THE REPLACEMENT OF AFT REINFORCEMENTS. THE BULKHEAD ASSEMBLY PN1212133-1 WAS NOTICED TO BE CRACKED AT LEFT AFT RELIEF CUTOUT, JUST FORWARD OF THE HORIZONTAL STABILIZER AFT ATTACHMENT. CRACK WAS ABOUT .3750 INCH LONG. PNSDR 20010322CW004Fitting · crackedDURING ANNUAL INSPECTION THE HORIZONTAL STABILIZER ATTACHMENT POINT REINFORCEMENT ON THE LEFT SIDE WAS FOUND CRACKED. THIS REINFORCEMENT WAS THE NEW STYLE STEEL PN 12326241 THAT WAS CRACKED. THIS AC IS USED FOR LOW LEVEL OVERLAND SURVEY AND THESE REINFORCEMESDR 20010227CW007Solenoid · shortedAIRCRAFT CAME IN WITH DEAD BATTERY, FOUND BATTERY OVERHEATED. PUT TEST BATTERY IN AND IMMEDIATELY WENT HIGH DISCHARGE. WHEN STARTER WIRE REMOVED DISCHARGED STOPPED. STARTER WAS SHORTED OUT. UPON FURTHER INVESTIGATION, FOUND STARTER SOLENOID CONTACTS WERE WSDR 20010319CW008Control Cable · separatedSTART UP, PILOT PUSHED MIXTURE FORWARD, COULD NOT START LEFT MOTOR OR GET FUEL FLOW. INVESTIGATION REVEALLED MIXTURE KNOB WOULD MOVE, ROD END AT MIXTURE CONTROL DID NOT. FOUND CABLE HOUSING SEPARATED FROM FACTORY CRIMP INSIDE FUSELAGE AT CONTROL COLUM AREA.SDR 20010409CW013Skin · wrinkledAIRCRAFT WAS INSPECTED AND REPAIRED DUE TO HARD LANDING. ALL LANDING GEAR WERE REMOVED AND INSPECTED. LOWER WING SKINS WERE REPLACED ON BOTH WINGS DUE TO BEING WRINKLED. REPLACED. SEVERAL WHEEL WELL FORMERS WHICH WERE BENT. REINSTALLED LANDING GEAR AND RISDR 20010205CW003Relay · failedSHORTLY AFTER TAKEOFF, CREW NOTICED INSTRUMENTS AND RADIOS FLICKERING, FOLLOWED BY TOTAL ELECTRICAL FAILURE. CREW RETURNED AND LANDED WITHOUT INCIDENT. MECH FOUND RT START RELAY FAILED IN CLOSED POSITION, PERMANENTLY ENGAGING THE STARTER. MECH REMOVED AND RSDR EY2R57052Nut · corrodedCORROSION IN THREADS OF BLADE NUT. REPLACED PART.SDR EY2R57052APin · corrodedACTUATING PIN CORRODED ON SURFACE. (QTY. 2) REPLACED.SDR 2003FA0000395Bumper Block · debondedLEFT AND RIGHT MAIN LANDING GEAR SHELL BUMPER DEBONDS, THE BUMPER EDGES CURL OVER PREVENTING MAIN GEAR STRUT FROM MAKING FULL DOWN TRAVEL. THIS CONDITION PREVENTS MAIN GEAR STRUT FROM CONTACTING DOWNLOCKS AND PROPER DOWNLOCK SWITCH ACTUATION, THEREFORE, AN USDR CA980928008Cylinder · failed(CAN) DURING CRUISE, THE NR 1 ENGINE BEGAN RUNNING ROUGH, AIRCRAFT RETURNED TO DEPARTURE POINT. POST-FLIGHT INSPECTION FOUND NO COMPRESSION ON NR 6 CYLINDER AND METAL WAS FOUND IN THE OIL FILTER. THE ENGINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICSDR 97ZZZX3895Cylinder · scoredDURING COMPLETION OF CONTINENTAL CRITICAL SB CSB 97-10A, FOUND NR 2 CYLINDER SEVERELY SCORED DURING A BORESCOPE INSPECTION. DAMAGE COVERS 50 PERCENT OF TOTAL CYLINDER WALL AND IS BEYOND PISTON PIN WEAR AREA. HIGH AMOUNT OF ALUMINUM SHAVINGS FOUND IN OIL FILT
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