Continental IO-550 series
Service difficulty reports · 239
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 = 'IO550' 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 = 'IO550' 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 2005FA0001582Pneumatic System · contaminatedPNEUMATIC SYSTEM INSPECTED AND TRACES OF WATER WERE FOUND IN THE EJECTOR VALVE AND AREA BELOW THE VALVE. FURTHER INSPECTION REVEALED WATER IN THE PNEUMATIC MANIFOLD VALVE AND ASSOCIATED PLUMBING. APPROXIMATELY .5 OZ OF WATER WAS REMOVED FROM THE SYSTEM. THESDR 2005FA0001572Pneumatic System · contaminatedDURING PROLONGED PERIODS OF OPERATION IN HEAVY PRECIPITATION CONSIDERABLE AMOUNTS OF WATER ENTER INTO THE PNEUMATIC SYSTEM. INSP OF PNEUMATIC SYS REVEALED LG AMOUNTS OF WATER BEING PASSED THROUGH DEICE BOOT EJECTOR, FURTHER DISASSEMBLY INSP REVEALED SEVERAL OSDR 2005FA0001573Pneumatic System · contaminatedDURING PROLONGED PERIODS OF OPERATION IN HEAVY PRECIPITATION CONSIDERABLE AMOUNTS OF WATER ENTER INTO THE PNEUMATIC SYSTEM. INSP OF PNEUMATIC SYS REVEALED LARGE AMOUNTS OF WATER BEING PASSED THROUGH DEICE BOOT EJECTOR, FURTHER DISASSEMBLY INSP REVEALED SEVERASDR 2005F00110Pneumatic System · contaminatedDURING PROLINGED PERIODS OF OPERATION IN HEAVY PRECIPITATION CONSIDERABLE AMOUNTS OF WATER ENTER INTO THE PNEUMATIC SYSTEM. INSP OF PNEUMATIC SYS REVEALED LARGE AMOUNTS OF WATER BEING PASSED THROUGH DEICE BOOT EJECTOR, FURTHER DISASSEMBLY INSP REVEALED SEVERASDR 2005FA0001574Pneumatic System · contaminatedDURING PROLONGED PERIODS OF OPERATION IN HEAVY PRECIPITATION CONSIDERABLE AMOUNTS OF WATER INTO THE PNEUMATIC SYSTEM. INSP OF PNEUMATIC SYS REVEALED LARGE AMOUNTS OF WATER BEING PASSED THROUGH DEICE BOOT EJECTOR, FURTHER DISASSEMBLY INSP REVEALED SEVERAL OUNCSDR 2005FA0001435Bellcrank · fracturedTHE CO-PILOTS RUDDER/STEERING BELLCRANK FRACTURED AT THE CENTER CONNECTING POINT CAUSING A LACK OF NOSE WHEEL STEERING ON THE CO-PILOTS SIDE.SDR M1555Bracket · splitDURING SCHEDULED ENGINE OIL CHANGE, FOUND BRACKET INDUCTION AIR FILTER SPLIT AT MANUFACTURED SEAM. SUSPECT ADHESIVE USED AT MANUFACTURE OF THE FOAM TYPE FILTER IS INADEQUATE FOR THE TASK.SDR 2005FA0001287Wire Harness · burnedWHEN TROUBLESHOOTING, THE SQUAWK (RECOGNITION LIGHTS ON ALL THE TIME) WE FOUND CARRED WIRE INSULATION IN THE WIRE HARNESS FEEDING THE OVERHEAD BANK OF SWITCHES THAT CONTROL THE SHIPS EXTERIOR LIGHTING. WE TRACED THE CHARRED INSULATION TO AN OVERHEATED CONDITISDR 2005FA0001288Wire Harness · burnedWHEN TROUBLESHOOTING THE SQUAWK (RECOGNITION LIGHTS ON ALL THE TIME), FOUND CHARED WIRE INSULATION IN THE WIRE HARNESS FEEDING THE OVERHEAD BANK OF SWITCHES THAT CONTROL THE SHIPS EXTERIOR LIGHTING. TRACED THE CHARRED INSULATION TO AN OVERHEATED CONDITION IN SDR 2005FA0001204Alternator · seizedAIRCRAFT WAS RUN UP PRIOR TO 50 HOUR INSPECTION AND NO DEFECTS WERE FOUND DURING RUN UP. AFTER INSPECTION, PERFORMED POST INSPECTION RUN AND NOTICED A LOUD SQUEALING NOISE AND SMOKE COMING FROM ENGINE COMPARTMENT. ENGINE WAS SHUTDOWN AND INSPECTION REVEALED THSDR 2005FA0001232Line · chafedMAIN FUEL SUPPLY LINE FROM FUEL SELECTOR TO FIREWALL HAD HOLE CHAFED IN IT. THE WIRE BUNDLE TO THE CB PANEL WAS CHAFING LINE. (K)SDR 2005FA0001128Door · failedBOTH DOORS WILL (POP) OPEN IN FLIGHT, CAUSING A SAFETY DISTRACTION TO THE PILOT AND WIND NOISE THAT KEEPS THE PILOT FROM HEARING AT INSTRUCTIONS. THIS STILL HAPPENS AFTER SEVER TRIPS TO MFG REPAIR STATION AND BACK TO FACTORY FOR REPAIRS. MFG RESPONSE IS THATSDR 2005FA0001111Fuel Tank · pluggedRT AUXILIARY FUEL TIP TANK IMPLODED. DETERMINED PROBABLE CAUSE WAS A PLUGGED VENT. GUIDANCE SUGGEST: WHEN PARKED, KEEP VENT CAPPED LIKE A PITOT COVER. DURING PREFLIGHT, TO OPEN GAS CAP AND BLOW OR AFFIX A TUBE TO THE .2500 INCH VENT AND BLOW TO VERIFY VENT SDR B3OR20050718Intake Pipe · crackedWHILE REMOVING LT MAGNETO FOR TBO, THE NR 4 CYLINDER INTAKE PIPE HAD TO BE REMOVED FOR ACCESS TO THE MAGNETO. REMOVAL OF THE INTAKE PIPE REVEALED THAT THE INTAKE PIPE HAD A CRACK IN THE FLARE END THAT IS SECURED TO THE CYLINDER INTAKE PORT. FURTHER INVESTIGATISDR AU510001440Relay · failed(AUS) LANDING GEAR RETRACTION SYSTEM DYNAMIC RELAY FAULTY.(OTHER CAUSE: HIGH HOURS ) (CASA# 510001440)SDR 2005FA0000969Impulse Coupling · wornMAGS REMOVED FOR TROUBLESHOOTING OF ENGINE HIGH ALTITUDE OPERATION PROBLEM. DURING PREINSTALLATION INSPECTION OF COUPLINGS. ONE WAS FOUND WORN BEYOND LIMITS. (K)SDR 2005FA0000847Spark Plug · brokenSPARK PLUG MAIN INSULATOR BROKE-OFF INTO ENGINE DURING OPERATIONS BETWEEN 88 AND 106 HOURS OF USE. A MAJOR PIECE OF CERAMIC MATERIAL WAS INJESTED INTO THE ENGINE.SDR 2005FA0000981Bulkhead · crackedBULKHEAD CRACKED APPROX .3750 INCH ON UPPER LT AREA ON BEND RADIUS, BULKHEAD TIES IN VERTICAL AND HORIZONTAL STABILIZERS TOGETHER. FATIGUE DUE TO HIGH TT ON AIRFRAME, PROBABLE CAUSE? (SW01200504869) (K)SDR 2005FA0000842Bulkhead · crackedTAIL BULKHEAD AT STA 272.0, FOUND CRACKS ON TOP PORTION IN BEND RADIUS AREA, APPROX .5 INCH TO .2500 INCH LONG ON TOP, LT AND RT AREA. PROBABLE CAUSE SEEMS TO BE FATIGUE DUE TO HIGH TOTAL TIME ON AIRFRAME. (K)SDR 2005FA0000844Bulkhead · crackedBULKHEAD CRACKED AT TOP PORTION AT JOGGLED AREA BELOW AFT HORIZONTAL ATTACH BRACKET/SPAR CRACK TO BE ABOUT .2500 INCH ON RT, ABOUT 1 INCH ON LT, CAUSE PROBABLY DUE TO HIGH AIRFRAME TT AND FATIGUE. (SW01200504562) (K)SDR 2005FA0001088Battery · corrodedSECOND ELT FOUND WITH BATTERIES IN THIS CORRODED CONDITION. (K)SDR 2005FA0000840Bulkhead · crackedBULKHEAD AT STA 272, REAR AFT FUSELAGE FOUND CRACKS AT TOP PORTION OF BULKHEAD AT RADIUS OVER CRACK APPROX .5 ON LT AND ABOUT 1.5 ON RT ALSO CAUSING DOUBLER TO CRACK OUT THAT HOLDS THE 2 SKINS TOGETHER. (K)SDR 2005FA0000841Bulkhead · crackedWEB BULKHEAD AT STA 272 REAR AFT FUSELAGE, FOUND CRACKS AT TOP PORTION ON RADIUS OF POST. CRACK TO BE APPROX 1 INCH ON LT AND ABOUT .2400 INCH ON RT, ALSO CAUSING DOUBLER TO CRACK OUT THAT HOLDS THE 2 SKINS TOGETHER. PROBABLE CAUSE, JUST HIGH TIME IN AIRFRAMSDR 2005FA0000735Gasket · out of positionTHE MATERIAL THE UPPER AND LOWER GASKETS ARE NOW MADE OF IS MUCH SOFTER THAN THE ORIGINAL DESIGN. THEY TEND TO COMPRESS AND SLIDE OUT FROM UNDER THE STRAINER WALL INTO THE CENTER OF THE FUEL STRAINER BODY AND BEGAN TO LEAK FUEL. THE STRAINER HOUSING IS NOT MSDR 2005FA0000643Spar · crackedWHERE HORIZONTAL STAB SPAR ATTACHES. THE BULKHEAD IS CUT AWAY, TO ALLOW THIS, AND IS FORMED BY JOGGLE BEND. SIDE TO SIDE. AT THIS JOGGLE, IT IS CRACKED, FORE AND AFT, TO INCLUDE BOTH BULKHEAD AND FORMER. (SW01200504216) (K)SDR B3OR20050505Spinner · crackedPROPELLER SPINNER WAS INSPECTED DURING A PRE-FLIGHT INSPECTION AND FOUND TO HAVE A CRACK. THE CRACK WAS FROM A SCREW HOLE AND EXTENDED TO BLADE CUT-OUT. THE SPINNER WAS REPLACED AND INSPECTED AFTER ITS FIRST FLIGHT, NO CRACKS WERE FOUND OR NOTED ON THE REPLACESDR 2005FA0000607Rib · crackedDURING SCHEDULED ANNUAL INSPECTION, FOUND LT WING BATT RIB AFT ANGLE AT IB MLG DOOR AFT ATTACH POINT CRACKED. HAVE NOTED SIMILAR CRACKING IN OTHER LOW-TIME RAC MODEL 58 AIRCRAFT. CRACKING SEEMS TO BE RELATED TO INSTALLATION OF MACHINED ALUMINUM DOORS THAT RESDR 2005FA0000869Impulse Coupling · looseDURING ANNUAL INSPECTION, COMPLY WITH 500 HR MAGNETO INTERNAL INSPECTION, WHICH INCLUDES THE IMPULSE COUPLING IAW MFG SB. ONE IMPULSE COUPLING WAS FOUND TO BE VERY LOOSE, DUE TO LOOSE RIVETS, WOULD HAVE FAILED SOON. FAILURE OF THIS TYPE CAN CAUSE EXTENSIVE DSDR 2005FA0000264Contactor · failedSTARTER CONTACTOR DID NOT DISENGAGE AFTER ENGINE START. THIS RESULTED IN FAILURE OF THE STARTER AS WELL. THE SITUATION DID NOT BECOME APPARENT UNTIL AFTER TAKEOFF. THIS AIRCRAFT HAS A (STARTER ENGAGED) WARNING LIGHT INSTALLED BUT IT DID NOT INDICATE CLEARLYSDR 2005FA0000781Spark Plug · intermittentENGINE PERFORMANCE ROUGH ABOVE 10,000 FT. APPEARS TO BE LIKE MISS LT OR RT MAG. INSPECTED AIR FILTER, CHECKED OK. INSPECTED LT AND RT MUFFLERS FOR BLOCKAGE CHECKED OK, CHECKED ALL IGNITION WIRES WITH HIGH TENSION TEST ON CHECKED OK. CHECKED MAG TIMING CHESDR 2005FA0000203Muffler · crackedVERY SIMILAR TO THE CRACKS REFERENCED IN AD NR 95-12-16 BUT ITS OUTSIDE OF THE SN RANGE LISTED. (K)SDR 2005FA0000762Switch · faultyINTERNAL UPPER BRAIDED CONDUCTOR ON LINE SIDE FAILED, SEPARATED FROM ITS CONTACT OR WELD. SPRING MECHANISM FOR SWITCH BECOMES CONDUCTOR. SPRING CAN NOT HANDLE THE CURRENT OF LANDING LIGHT CIRCUIT, AND OVERHEATS. OVERHEATING OF SPRING CAUSED NYLON TOGGLE ASSSDR 2005FA0000681Strut · looseDURING INSPECTION OF NOSE GEAR STRUT HARDWARE IT WAS FOUND TO HAVE LOOSE STRUT MOUNTING HARDWARE. (K)SDR 2005FA0000690Support Angle · crackedDURING ANNUAL INSPECTION FOUND SUPPORT ANGLE WHERE LT IB MAIN GEAR DOOR HINGE IS ATTACHED, CRACKED. PART WAS REPLACED 2 YEARS PREVIOUSLY FOR SAME OCCURRENCE. ALSO FOUND ANGLE ON ADJACENT LT IB DOOR HINGE SUPPORT CRACKED, AS WELL AS SUPPORT ANGLES FOR RT MAINSDR 2004FA0000844Elt · incorrectDURING A RECENT INSPECTION OF A NEW AC IT WAS NOTED THAT THE ELT SWITCH WAS IN THE OFF POSITION FROM THE MANUFACTURE, UPON FURTHER INVESTIGATION THE PILOT RECEIVED THE AIRCRAFT FROM THE FACTORY AND WAS NOT INFORMED THAT THE SWITCH WAS OFF DURING HIS FLY-OFF FRSDR MW82004F00001Plate · corrodedSPAR KIT PN 58-4008-9S WAS ORDERED FROM MFG AND UPON INSPECTION OF KIT, PITTING WAS NOTICED ALONG THE EDGE OF THE LT PLATE PN 36-430056-6. AFTER CLEANING SOME OF THE PRIMER OFF, THE PITTING WAS NOTICED ON THE ALUMINUM ITSELF. THIS COULD POSSIBLY BE FROM CORRSDR 2004FA0000792Wire · brokenPILOT REPORTED LT ALTERNATOR INOPERATIVE. FOUND TERMINAL FOR B+ WIRE BROKEN OFF, WHICH RESULTED IN INTERMITTENT CONTACT CAUSING SEVERE ELECTRICAL ARCING BETWEEN ALTERNATOR AND WIRE TERMINAL END.SDR 2004FA0000734Panel · missingDURING A LT TURN IN A PLEASURE FLIGHT; THE TOP LT IB PANEL FLEW OFF AND THERE WAS LOSS OF LIFT IN LT WING. IN TRYING TO LAND, HAD TO MAINTAIN HIGH AIRSPEED, MADE A HARD LANDING. NOSE WHEEL BROKE OFF, PROPELLER WAS DAMAGED. MISSING PANEL IS JUST OB OF THE FUSSDR HJL2004F00001Spring · failedREPLACED (NO BACK) SPRING, INSP GEARS AND ACTUATOR IAW SB M20-282 AND SI 102000-1-901 REV 2. ON 9-3-2004, AFTER 16 HOURS, GEAR DOWN SAFETY LIGHT WOULD INDICATE UNSAFE CONDITION WHEN TAXIING AC AND TURNING RT AND LT. AC WAS PUT ON JACKS, GEAR WAS ELECTRICALLYSDR 2004FA0000741Bearing · stickingPILOT REPORTS THAT THE AILERON CONTROL LOCKS UP AND WILL NOT TURN IN EITHER DIRECTION AND THEN RELEASES AND RETURNS TO NORMAL. UPON INSPECTION OF AILERON SYSTEM, IT WAS FOUND THAT THE CONTROL YOKE CONNECTION BEARING WAS STICKING AND WOULD NOT RELEASE UNTIL THSDR NF22004FCCCWire · chafedALTERNATOR OUTPUT WIRE CHAFED ON THE RT FWD VALVE COVER AND BURNED A .2500 INCH HOLE IN THE VALVE COVER. WIRE AND BAFFLE ABOVE VALVE COVER NEED TO BE SECURED BETTER. SHORTING OF THE WIRE ALSO CAUSED DAMAGE TO COMPONENTS IN THE MCU AND SUBSEQUENT NR 1 ALTERNASDR MPY2004F00000Heat Shield · gougedHEAT SHIELD PN 600429-503 WAS FOUND TO BE MAKING CONTACT WITH TUBULAR ENGINE MOUNT. THIS CONTACT CREATED A GOUGE APPROX .200 INCH LONG AND APPROX .045 INCH DEEP.SDR 2004FA0000549Heat Shield · gougedHEAT SHIELD WAS FOUND TO BE MAKING CONTACT WITH TUBULAR ENGINE MOUNT. THIS CONTACT CREATED A GOUGE APPROXIMATELY .200 INCH IN LENGTH AND APPROXIMATELY .045 INCH DEEP.SDR B3OR20040709Line · cutPILOTS ENTERED THE AC AND TAXIED DOWN THE TAXIWAY. AS BRAKES WERE BEING APPLIED, IT WAS NOTICED THAT RT BRAKE WAS NOT OPERATING. AC EXITED TAXI WAY AT A LOW SPEED CAME TO A STOP IN ABOUT FOUR INCHES OF MUD ALONGSIDE OF TAXIWAY. THERE WAS NO DAMAGE TO AC OR PROSDR FIP2004F00000Flange · crackedTOP MOUNT EAR AND IB BAFFLE FLANGE CRACKED UNDER NORMAL OPERATING CONDITIONS.SDR AUS20040246Strut · cracked(AUS) MAIN LANDING GEAR STRUT SLIDING MEMBER CRACKED CIRCUMFERENTIALLYAROUND THE LOWER SECTION.SDR FPI2004F00002Crankcase · crackedRT CASE CRACKED AT CYLINDER NR 1. 7TH STUD LOWER RECESS IN CASE.SDR AKG2004F00004Rod End · failedWHILE REPLACING THE ENGINE POWER CONTROL CABLE. THE ROD END AT THE THROTTLE BODY WAS FOUND WITH THE BRASS INSERT AND THE STEEL PIVOT BALL FALLING OUT OF THE ROD END HOUSING. THERE IS NOT A LARGE AREA SAFETY WASHER INSTALLED. IT WAS JUST A MATER OF TIME AND SDR FPI2004F00001Distributor Gear · looseDISTRIBUTOR GEAR FINGER LOOSENED UP AT SHAFT.SDR S1F2004F00000Buss Bar · inoperativeBUSS BAR ON EXTERNAL SUPPLY NEGATIVE POST HAD NO GROUND. BUSS BAR HAD MASKING TAPE ON IT WHEN FACTORY HAD PAINTED IT AND INSTALLED WITHOUT REMOVING TAPE. THEREFORE NO GROUND FOR EXTERNAL SUPPLY.
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