Continental O-200A
Service difficulty reports · 438
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 = 'O200A' 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 = 'O200A' 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 CA050404003Magneto · failed(CAN) ON LANDING, ENGINE BECAME NOTICEABLY ROUGH. AFTER LANDING A MAGNETO CHECK WAS ACCOMPLISHED. THE MAG CHECK REVEALED THAT THE RT MAGNETO WAS NOT FIRING. UPON INSPECTION OF SAME IT WAS DISCOVERED THAT THE INTERNAL NYLON GEAR HAD FAILED (TEETH STRIPPED). SDR CA050405003Shimmy Dampener · failed(CAN) SHIMMY DAMPNER FAILED AT TAKEOFF CAUSING A VIBRATION. AIRCRAFT CAME TO REST WITH ONLY MINIMAL DAMAGE. SHIMMY DAMPNER REPLACED.SDR 2005FA0000259Muffler · crackedCRACKING AROUND FRONT RISER. PART HAS BEEN INSPECTED IAW AD 67-03-01. PRESSURE CHECK AS REQUIRED AT 100 DEGREE INTERVELS. AIRCRAFT NOT FLOWN SINCE LAST ANNUAL. 8.9 HOURS SINCE LAST REQUIRED INSPECTION IAW AD. RECOMMEND INSPECTION ANNUALLY IAW AD. (K)SDR 2005FA0000177Magneto · brokenFLANGE BROKEN ON RT SIDE FOR SUPPORT OF MAG. FOUND ON ANNUAL INSP. 4001 MAG TT 394. (K)SDR CA050126003Exhaust Valve · corroded(CAN) POOR ACCELERATION AND SLUGGISH PERFORMANCE DURING POWER UP AND DIFFERENT POWER SETTINGS. WHEN APPLYING POWER, ENGINE STUMBLED. INITIALLY SUSPECTED CARB ICING BUT GROUND CHECK RESULTED IN SAME FAILURE TO PRODUCE POWER. PRELIMINARY D/P CHECK SHOWED LOW POSDR CA041130004Line · worn(CAN) THE OIL PRESSURE LINE UNDER THE INSTRUMENT PANEL WAS CHAFED AGAINST THE CABIN HEATER CONTROL CABLE. WE REPLACED THE PRESSURE LINE AND INSTALLED IT CORRECTLY.SDR CA041110007Door Frame · cracked(CAN) ON INSPECTION FOUND CRACKED AT UPPER FWD RADIUS ABOUT 1.0 INCH IN LENGTH. PART WAS REPLACED AS REQUIRED.SDR CA041110004Rib · cracked(CAN) THE RIB WAS FOUND CRACKED AROUND ONE OF THE STRENGTHENING DIMPLES OF THE RIB, ABOUT 1.5 INCHES IN LENGTH. A NEW PART WAS INSTALLED AS REQUIRED.SDR CA041110005Flap Track · worn(CAN) ON INSPECTION FLAP TRACK GROOVES WERE FOUND BADLEY WORN. PARTS WERE REPLACED AS REQUIRED.SDR CA041110006Flap Track · worn(CAN) ON INSPECTION FLAP TRACK GROOVES FOUND BADLEY WORN,PARTS WERE REPLACED AS REQUIRED.SDR CA041109004Control Cable · corroded(CAN) AILERON CONTROL CABLE FOUND CORRODED AT COPILOT FOOT AREA. THIS PROBLEM HAS BEEN NOTICED ON OTHER CESSNA 150. SUSPECT DIRT FROM SHOES CAUSING CORROSION. TO SEE THE CABLE YOU NEED TO REMOVE COVER (YOKE) AND MOVE AILERON TO TRAVEL LIMITS.SDR CA041012004Windshield · failedDURING A ROUTINE TRAINING FLT FOR A-CLASS IV INSTRUCTOR RATING, WINDSHIELD CRACKED AND BLEW IN. PRIOR TO WINDSHIELD BREAKING, INSTRUCTOR CANDIDATE HAD BEEN PERFORMING SPIRAL DIVE LESSON DEMONSTRATION WHEN THE WINDSHIELD BROKE, AND HAD JUST COMPLETED A RECOVERSDR CA040914008Flange · corroded(CAN) PROPELLER REMOVED FOR CORROSION INSPECTION UNDER CAR 625, APPENDIX C, PARA 5. MOUNTING FLANGE CORRODED BEYOND REPAIR.SDR CA040907001Rib · cracked(CAN) PART NUMBER 0432001-46 & 0432001-6 LEADING EDGE RIB ASSEMBLIES (FIGURE 18, ITEM 18 & 17 CESSNA PARTS MANUAL) ARE VERY DIFFICULT TO SEE. THE USE OF A MIRROR THROUGH THE HORIZONTAL SPAR AND RIB LIGHTNING HOLES IS THE ONLY WAY TO SEE THE CRACKS ALONG THE TASDR CA040830001Exhaust Valve · eroded(CAN) ENGINE PLACED ON (PISTON ENGINE ON CONDITION PROGRAM). DURING ON-CONDITION 100 HOUR INSPECTION, THE NR 2 CYLINDER COMPRESSION TEST WAS LOW AND LEAKING FROM VALVES. ON FURTHER INSPECTION, EXHAUST VALVE STEM WAS FOUND TO BE ERODED TO ABOUT HALF OF DIAMETESDR 2004FA0000555Carburetor · brokenAC ENTERED A POWER ON STALL, DURING RECOVERY THE ENGINE BEGAN LOOSING POWER. INSTRUCTOR TRIED TO MAINTAIN POWER BY MANEUVERING THROTTLE IN AND OUT BUT WAS ONLY ABLE TO MAINTAIN ABOUT 1100 RPM MAXIMUM CONTINUES. MECHANICS QUICKLY IDENTIFIED THE PROBLEM AS THESDR CA040610010Line · corroded(CAN) FUEL LINE ASSEMBLY LOCATION/LOCATED UNDER FLOOR AND UNDER CENTER CONSOLE. THIS LINE IS DIRECTLY FORWARD OF THE BELLY DRAIN. IT IS UP STREAM FROM THE GASCOLATOR AND DOWN STREAM OF THE FUEL SHUT-OFF. FUEL SMELL WAS DETECTED. FUEL STAINING WAS PRESENT. THSDR 2004FA0000544Spar · damagedA LONGITUDINAL CRACK WAS FOUND AT OB AILERON ATTACH FITTING OF THE REAR WOOD SPAR. THE CRACK IS LOCATED ON RT WING REAR SPAR, OB AILERON ATTACH POINT EMANATING FROM LOWER BOLT HOLE ON FORWARD SIDE OF SPAR. THE CRACK WAS FOUND DURING ANNUAL INSP WHILE COMPLINSDR CA040520003Retaining Ring · dislodged(CAN) STARTER GEAR RETAINING RING (P/N 6401740) DISENGAGED FROM THE STARTER SHAFT AND LODGED IN THE STARTER GEAR NEEDLE BEARING (P/N 639788). THE NEEDLE BEARING FAILED WITH THE BEARING NEEDLES ENTERING THE ENGINE REAR CASE AND OIL SYSTEM. THE NEEDLES IN THE OSDR 2004FA0000529Cylinder · crackedPILOT REPORTED ENG RUNNING ROUGH AND SMELLED OIL IN COCKPIT SHORTLY AFTER TAKE OFF, MANAGED TO MAKE EMERGENCY LANDING ON DEPARTURE AIRPORT, DETERMINED CYLINDER NR 2 BARREL CRACKED ALMOST ALL THE WAY AROUND 2.8750 INCHES UP FROM BASE CAUSE UNKNOWN EXCEPT POSSIBSDR CA040308001Bolt · broken(CAN) DURING INSTALLATION OF THE PROPELLER, WHEN TIGHTENING THE BOLTS TO THE SPECIFIC TORQUE OF 25-30 POUNDS FOOT. ONE OF THE BOLTS BROKE AT APPROXIMATELY 27 POUNDS FOOT. THE BOLT BROKE AT THE BASE OF THE THREADS NEAR THE START OF THE GRIP. A SECOND BOLT WASSDR CA040310008Bolt · sheared(CAN) UPON APPLICATION OF 27 FT/LBS TO 2 OF THE MOUNTING BOLTS AT THE THREADS FAILED. BOLTS FORWARDED TO COMPANY FOR EVALUATION.SDR CA040225015Bolt · broken(CAN) PROPELLER BOLTS WERE BEING INSTALLED AND TORQUED TO THE SPECIFIED VALUE OF 25 - 30 POUNDS FOOT. AS THE TORQUE WAS REACHING APPROXIMATELY 27 FOOT POUNDS, THE BOLT BROKE. THE BREAK WAS WHERE THE THREADS MEET THE GRIP. A SECOND BOLT WAS TORQUED AND IT BROKESDR 2004FA0000190Skin · crackedREMOVED HORIZONTAL STABILIZER FOR TAILCONE REPAIR. FOUND TWO 1.5 INCH CRACKS RADIATING FROM LOWER FORWARD CORNER OF TAIL CONE SKIN WHERE BOTTOM OF HORIZONTAL LEADING EDGE RESTS. CRACKS PROGRESSING TOWARDS FORWARD HORIZONTAL STABILIZER MOUNT BOLT HOLES. APPESDR 2004FA0000191Skin · crackedREMOVED HORIZONTAL STABILIZER FOR TAILCONE REPAIR. FOUND TWO 1.5 INCH CRACKS RADIATING FROM LOWER FORWARD CORNER OF TAIL CONE SKIN WHERE BOTTOM OF HORIZONTAL LEADING EDGE RESTS. CRACKS PROGRESSING TOWARDS FORWARD HORIZONTAL STABILIZER MOUNT BOLT HOLES. APPESDR 2004FA0000259Cylinder · brokenAIRCRAFT WAS SUBSTANTIALLY DAMAGED DURING A FORCED LANDING AFTER TOTAL LOSS OF ENGINE POWER. INVESTIGATION SHOWED THE CYLINDER HAD COMPLETELY SEPARATED IN THE MIDDLE WHILE IN FLIGHT, CAUSING THE TOTAL LOSS OF POWER.SDR W592004F00000Spacer · crackedPROPELLER SPACER WAS FOUND CRACKED FROM DOWEL PIN HOLES. ONE CRACK PROGRESSED COMPLETELY THROUGH SPACEER, THE SECOND WAS 90 PERCENT THROUGH SPACER. PROPELLER DOWEL PIN HOLES ARE ELONGATED AND OVERSIZE, PROPELLER WAS BENT SEVERELY AT ONE TIME AND IMPROPERY RESDR CA040730003Exhaust Valve · deformedON 200 HOUR INSPECTION, BOTH LEFT SIDE EXHAUST VALVES FOUND TO BE DEFORMED AT TOP OF STEM BELOW VALVE SEAT CYLINDERS 2 AND 4, JAN 12/04. ENGINE TIME AT INSPECTION 1506.5. ENGINE OVERHAULED SEPT. 20/90 BY VOWELL AVIATION. TTSB 4724,5. EXHAUST VALVES REPLACED. SDR CA031119003Carburetor · iced(CAN) DEPARTING, CLIMBED UP TO CRUISING ALTITUDE OF 4,500 FT, STARTED DESCENT BY REDUCING POWER FROM 2,500 RPM TO APPROX 2,350 RPM. TEMP WAS -2 AND DEWPOINT -9 FOR 6,000 FT. GOT DOWN TO 3,500, LEVELED OFF, WENT TO ADD POWER FOR CRUISE, ENG SPUTTERED, WENT TO ISDR 2003FA0001098Rocker Boss · failedON APRIL 19, FLYING BACK TO LGU, THE ENGINE SUDDENLY BEGAN VIBRATING AND LOST A LOT OF POWER. COULD NOT MAINTAIN ALTITUDE, LANDED IN A FIELD. MECHANIC CAME AND FOUND THAT THE ROCKER BOSSES OF CYL NR 3 HAD FAILED. INSTALLED AN NEW CYLINDER ASSY AND FLEW IT BASDR CA031027007Rib · cracked(CAN) WHEN REPLACING THE LT LEADING EDGE HORIZONTAL STABILIZER SKIN PN 0432001-16 DUE TO IT BEING DENTED. IT WAS FOUND THAT BOTH INBOARD NOSE RIB ASSEMBLIES WERE CRACKED. THEY WERE REPLACED WITH NEW FACTORY PART PN 0432001-6 RT AND PN 0432001-46 LT.SDR CA030827002Exhaust Valve · eroded(CAN) DURING THE BOROSCOPE INSPECTION OF THE ON-CONDITION PROGRAM, SPECIAL EFFORT WAS MADE TO INSPECT THE EXHAUST VALVE AS WE HAD FOUND A PREVIOUS VALVE OF THE SAME PART NUMBER IN POOR CONDITION. THE NR 2 CYLINDER EXHAUST VALVE WAS FOUND SEVERELY ERODED 1/3 TSDR 2003FA0000977Bushing · wornEIGHT ROCKER ARM BUSHINGS SHOWED INDICATIONS OF EXCESSIVE WEAR. THE PROBLEM WAS INDICATED AT THE FIRST OIL CHANGE (10 HOURS) AFTER ENGINE OVERHAUL AS BRONZE PARTICLES IN THE OIL FILTER. THE OVERHAULED ROCKER ARMS WERE INSTALLED IN NEW MFG CYLINDERS P/N 65381SDR AUS20030842Bracket · cracked(AUS) HORIZONTAL STABILISER BRACKET CRACKED AROUND NUT PLATES.SDR CA030812003Rocker · worn(CAN) ON VISUAL INSPECTION OF VALVE TRAIN ASSY ON ALL FOUR CYLINDERS. NOTED EXCESSIVE WEAR TO ROCKER ARM BOSSES, ROCKER ARM BUSHINGS & ROCKER SHAFTS. SHAFTS ARE ANCHORED BY SET SCREWS. FIRST INDICATION IS THAT THE LINE UP MARKS ON THE ENDS OF THE PINS DO NOT SDR CA030703017Exhaust Valve · corroded(CAN) UPON INSTALLATION OF CYLINDERS AFTER OVERHAUL OF CRANKCASE THE EXHUAST VALVE IN ONE CYLINDER WAS NOTICED TO BE BADLY CORRODED AND ERODED AT THE NECK OF THE VALVE.ALL OTHER EXHAUST VALVES WERE INSPECTED SERVICEABLE AND THE ONE WILL BE REPLACED. IT SHOULDSDR CA030626009Cylinder Head · worn(CAN) ON INSPECTION FINE BRONZE PARTICLES FOUND IN OIL FILTER & SCREEN. FURTHER INVESTIGATION REVEALED ROCKER ARM BUSHINGS WORN. ALSO CYLINDER HEAD BOSSES WORN. THE ROCKER SHAFTS ON THESE NEW STYLE CYLINDERS ARE HELD IN PLACE WITH SET SCREWS WHICH SEEM TO LOOSSDR AUS20030653Spar · cracked(AUS) STABILIZER SPAR CRACKED IN AREA AROUND ATTACHMENT BRACKET NUT PLATE. CRACK LENGTH 12.7MM (0.5 IN).SDR CA030702005Fitting · cracked(CAN) DURING PREFLIGHT INSPECTION PILOT NOTICED CRACK, PARALLEL ALONG 90 DEGREES ANGLE.SDR CA030627007Screw · loose(CAN) ROCKER SHAFT SET SCREW BECAME LOOSE AFTER 148.1 HRS OF OPERATION AND WORE THE ROCKER SHAFT BOSS IN CYLINDER HEAT MAKING THE CYLINDER UNSERVICEABLE.SDR CA030517002Rudder · binding(CAN) INCORPORATION OF AD 2000-20R1 (CESSNA S/B SEB01-1) RESULTS IN BINDING BETWEEN NEW STOP BOLTS AND RUDDER STRUCTURE DUE TO THE INCREASED SIZE OF THE STOP BOLTS. BINDING WAS NOT APPARENT UNLESS PRESSURE WAS APPLIED TO BOTH RUDDER PEDALS.SDR CA030514012Starter · blocked(CAN) ON ENGINE START UP, PILOT NOTICED THAT THE PROP WAS NOT TURNING. AFTER INVESTIGATION WE DISCOVERED THAT THE STARTER WAS DEFECTIVE.SDR 2003FA0000502Cylinder · galledENGINE INSPECTED AFTER APPROXIMATELY 70 HOURS OF OPERATION ON NEW MFG ASSY. GALLING HAD OCCURED ON THE ROCKERSHAFTS. THE MFG HAD MODIFIED THE AGE OLD DESIGN TO INCLUDE LOCKING THE ROCKER SHAFT IN PLACE WITH A SET SCREW. THE SHAFT, BEING UNABLE TO FLOAT AND SDR CA030423006Rib · cracked(CAN) LEADING EDGE RIB ASSEMBLIES ARE VERY DIFFICULT TO SEE.THE USE OF A MIRROR THROUGH THE HORIZONTAL SPAR AND RIB LIGHTNING HOLES IS THE ONLY WAY TO SEE THE CRACKS ALONG THE TABS.WE BELIEVE THE RIBS ARE CRACKING DUE TO IMPROPER GROUND HANDLING.THE PRACTICE OSDR CA030401004Spar · cracked(CAN) ON INSPECTION 0432001-15 SPAR REINFORCEMENT FOUND CRACKED AFTER DISASSEMBLEY LT & RT SPARS ALSO FOUND CRACKED. REASSEMBLED WITH NEW PARTS INCLUDING NEW STYLE BRACKET. AIRCRAFT RETURNED TO SERVICE.SDR CA030331007Exhaust Valve · stuck(CAN) PILOT REPORT OF INTERMITTENT ENGINE ROUGH RUNNING. NR 4 EXHAUST VALVE FOUND STICKY. GUIDE AND STEM CLEANED. GROUND RUN SATISFACTORY.SDR CA030423004Rib · cracked(CAN) LEADING EDGE RIB ASSEMBLIES ARE VERY DIFFICULT TO SEE.THE USE OF A MIRROR THROUGH THE HORIZONTAL SPAR AND RIB LIGHTNING HOLES IS THE ONLY WAY TO SEE THE CRACKS ALONG THE TABS.I HAVE INCLUDED TWO PHOTOS. ONE OF THE PHOTOS SHOWS A NEW PART AND WERE THE LOCSDR CA030318011Drive Gear · worn(CAN) DURING 50 HR INSPECTION, OIL FILTER ELEMENT WAS INSPECTED. STEEL PARTICLES WERE FOUND. NR 2 & 4 CYLINDERS WERE REMOVED FOR EXAMINATION OF CAMSHAFT & FOLLOWERS. NO FAULT FOUND. REMOVED THE TCM LIGHTWEIGHT STARTER, THE DRIVE GEAR WAS FOUND TO BE EXCESSIVESDR CA030320003Cylinder Head · cracked(CAN) CRACK IN ALUMINUM HEAD RUNNING UNDER TOP SPARKPLUG HOLE. CRACK DOES NOT EXTEND INTO COMBUSTION CHAMBER - NO LEAKAGE FOUND DURING PRESSURE TEST. CYLINDER REMOVED AND REPLACED WITH RECONDITIONED UNIT.SDR CA030218008Control Cable · corroded(CAN) 2 CABLES FOUND CORRODED AND FRAYED AT FUSELAGE STA. 20.5. BOTTOM OF FORWARD LANDING GEAR BULKHEAD. DEFECT WAS FOUND ON CABLES BECAUSE THEY HAD TO BE REMOVED FOR MAJOR STRUCTURAL REPAIRS. THOSE CABLES RUN ON PULLIES ATTACHED TO THE BULKHEAD AT THE VERY BO
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