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 aircraft_model_key = '150L' 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 aircraft_model_key = '150L' 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 2025FA0000791Volt Regulator · defectiveVOLTAGE REGULATOR FAILURE IN FLIGHT RESULTED IN OVERVOLTAGE CONDITION. CAUSED BATTERY OVERHEATING/SWELLING AND COMMUNICATION RADIO FAILURE. NO FIRE OR SMOKE NOTED. PART INSTALLED PER AIRCRAFT MAINTENANCE MANUAL. AIRCRAFT LANDED SAFELY WITH LOSS OF COMMUNICATIOSDR 2022FA0000727Exhaust Valve · stuckENGINE ROUGH RUNNING DURING PRE-TAKE OFF RUN UP. COMPRESSION TEST FINDS NONE IN #4 CYLINDER. DISASSEMBLED, FOUND EXHAUST VALVE STUCK DUE CARBON BUILD UP IN VALVE GUIDE. CLEANED VALVE AND GUIDE, RE-ASSEMBLED, RE-INSTALLED, OPERATION SATIFACTORYSDR 2022FA0000752Exhaust Valve · destroyedEXHAUST VALVE BROKE OFF AT BASE OF VALVE STEM, CAUSING DESTRUCTION OF CYLINDER COMBUSTION CHAMBER AND SUBSEQUENT ENGINE FAILURE.SDR 2022FA0000695Seal · splitSTEERING ROD SEALS, BOTH LEFT AND RIGHT HAD SEVERAL SPLITS AND CRACKS IN THE SEAL MATERIAL. THESE ARE LOCATED ABOUT 12" - 15" AFT OF EXHAUST OUTLETS. SEALS HAD BEEN PREVIOUSLY REPLACED. EXHAUST GASSES MAY ENTER FUSELAGE THROUGH OPENINGS. CARBON MONOXIDE HAZARDSDR 2021FA0000088Seal · crackedLEFT AND RIGHT STEERING ROD SEALS HAD SEVERAL SPLITS AND CRACKS IN THE SEAL MATERIAL. CRACKS WERE LOCATED ABOUT 12 TO 15 INCHES AFT OF EXHAUST OUTLETS. SEALS HAD BEEN PREVIOUSLY REPLACED. EXHAUST GASSES MY ENTER FUSELAGE THROUGH OPENINGS. CARBON MONOXIDE HAZARSDR 2020FA0000249Crankshaft · crackedAIRCRAFT IN FOR ANNUAL INSPECTION, REMOVED SPINNER TO CHECK PROP HUB, S/N, MODEL. NOTICED CRANKSHAFT OIL PLUG MISSING, LOOKED INSIDE CRANKSHAFT BORED HOLE I NOTICE A 1/2" CRACK AT BOTTOM OF BORED HOLE CRACK STARTS AT CENTER OF CRANKSHAFT AND RADIATES OUTWARD.SDR 2016FA0000417Cylinder · separatedAIRCRAFT WAS IN NORMAL CRUISE WHEN THE PILOT HEARD A LOUD BANG FROM THE ENGINE, RESULTING IN A PARTIAL LOSS OF POWER. FORCED LANDING OFF-AIRPORT. EXAMINATION OF THE ENGINE REVEALED THAT THE NR 2 CYLINDER HAS BROKEN IN THE BARREL AREA. ENGINE PART TT IS UNKNSDR 2015FA0000332Solenoid · shortedWHILE IN PATTERN, COMMUNICATION WAS LOST BETWEEN ACFT AND TOWER. ACFT WAS CLEARED TO LAND USING LIGHT GUN SIGNALS. LANDING WAS UNEVENTFUL. MAINTENANCE FOUND STARTER SOLENOID HAD AN INTERNAL SHORT THAT DEPLETED ELECTRICAL POWER.SDR CA140127003Muffler · cracked(CAN) DURING CF-90-03, INSPECTION A CRACK WAS FOUND AT FORWARD FLANGE. CRACK IS APPROXIMATELY 75 PERCENT AROUND THE CIRCUMFERENCE. THERE IS SEPERATION ALONG THE CRACK. EXHAUST TRAILS ARE FOUND INSIDE SHROUD AND WELL DOWN INTO HOT AIR DUCTING. MUFFLER IDENTIFISDR 2011FA0000678Bulkhead · crackedTHE BULKHEAD WAS INSTALLED ON 5/5/2007, 1476.4 TT. ON LATEST INSPECTION, A CRACK WAS DISCOVERED AT THE BASE OF THE PROPELLER HUB. ON REMOVAL OF PROPELLER, IT WAS DISCOVERED THAT SEVERE CRACK WENT 85 PERCENT THE WAY AROUND THE CENTER OF THE BULKHEAD. SPINNERSDR CA110509011Piston Ring · worn(CAN) DURING AN INTERNAL INSPECTION OF THE ENGINE, WHEN THE PISTONS WERE REMOVED FROM THE CYLINDERS, EACH OF THE FACES OF THE TOP PISTON RINGS HAD STRIPS OF CHROME PLATING MISSING BETWEEN THE TOP AND THE BOTTOM OF THE RING AROUND APPROXIMATELY 70 PERCENT OF THSDR 2011FA0000221Cylinder · galledDURING O/H, NEW STEEL CYLINDERS WERE INSTALLED AT CUSTOMERS REQUEST. THE STEEL CYL KIT TIST61.1DCA CONSISTED OF CYL ASSEMBLIES SN: 22070-146, 22070-141,22070-140 & 22070-133. AFTER REINSTALLATION OF THE ENG, AN ENG TEST RUN WAS PERFORMED WITH NORMAL RESULTS.SDR CA110322002Shaft · bent(CAN) DURING INVESTIGATION OF AN UNRELATED ENG SNAG, THE THROTTLE SHAFT WAS FOUND TO BE SLIGHTLY BENT ON THE THROTTLE CONTROL ATTACH SIDE, JUST OUTSIDE THE THROTTLE BODY ASSEMBLY. THE CARBURETOR WAS REPLACED WITH A SERVICEABLE UNIT.SDR CA110314018Exhaust Pipe · cracked(CAN) EXHAUST PIPE WELD CRACKED AT HEAT EXCHANGER NR 4 CYLINDER.SDR CA090708001Firewall · deformed(CAN) INSP OF NOSE ASSY REVEILED A SOFT SHIMMY DAMPER, DAMPER WAS SERVICED. INSP REVEALED THAT ACFT PROBABLY HAD A NOSE TIRE LANDING SINCE MINOR DEFORMATION OF UPPER FIREWALL SKIN NOTED. INSP REVEALED THAT BOLT IDENTIFIED IN IPC FIGURE 32, ITEM 3, BENT SO THSDR CA090619006Valve · stuck(CAN) DURING FLIGHT TO PRACTICE AREA, ACFT DEVELOPED A VIBRATION AND LOST RPM. CREW DECIDED TO RETURN TO AIRPORT. RUN UP ON GROUND PERFORMED AND CONFIRMED ROUGH RUNNING ENGINE. TROUBLESHOOTING DISCOVERED THAT EXHAUST VALVE ON NR 3 CYLINDER WAS STUCK IN THE SDR CA090401020Bulkhead · cracked(CAN) BULKHEAD CRACKED.SDR 2008FA0000773Cylinder · crackedNR 4 CYLINDER FOUND CRACK AT BARREL BETWEEN COOLING FINS. CRACK WAS APPROX 300 DEGREES AROUND CYLINDER CIRCUMFERENCE. SYMPTOMS INCLUDED ROUGH RUNNING, LARGE OIL LEAK AND SMOKE. CATASTROPHIC FAILURE WAS EMANATE AND WOULD HAVE CAUSED COMPLETE LOSS OF ENGINE PSDR CA080221002Muffler · damaged(CAN) THIS IS AN ON GOING ISSUE. THIS EXHAUST MUFFLER PASSED THE VISUAL INSP AS CF90-03. WHEN PRESSURE TESTED WITH AIR AND WATER, 3 PIN HOLES SHOWED. 2 WERE IN OPEN BARE METAL SURFACE. ONE WAS IN THE LONGITUDINAL SEAM. ANOTHER EXPERIENCED AME WAS IN MY SHOP FOSDR CA071126006Gear · broken(CAN) STARTER DRIVE ENGAGES ON TEETH ON GEAR. STARTER WAS SLIPPING, TOOK APART TO EXAMINE AND FOUND 3 BROKEN TEETH. STARTER IS LIGHT WEIGHT. REPLACE STARTER SOLENOID 19 HOURS EARLIER AND BELIEVE FAULTY SOLENOID CAUSE OF PROBLEM. (TC NR 20071126006)SDR CA070910006Cylinder · stuck(CAN) ON CLIMB OUT AFTER TAKEOFF, THE PILOT NOTICED MILD TO MODERATE ENGINE VIBRATION WITH A PARTIAL LOSS OF POWER. A RETURN TO THE AIRSTRIP WAS CARRIED OUT WITH A SUCCESSFUL LANDING. ON INVESTIGATION BY AN AME, THE PROBLEM WAS NOTICED AS AN EXHAUST VALVE STUCSDR CA070329006Cylinder · detached(CAN) ENGINE VIBRATION AND POWER LOSS IN FLIGHT, ENGINE CAME TO TOTAL STOP ON TAXIWAY. CYLINDER NR 4 FOUND DETACHED. ENGINE (2587.4 HOURS). ENGINE REMOVED FOR OVERHAULED. (TC NR 20070329006)SDR CA070214004Exhaust Valve · broken(CAN) DURING TAKEOFF, AN ENGINE VIBRATION WAS FELT. A PRIORITY LANDING WAS REQUESTED. CYLINDER EXHAUST VALVE NR 3 FOUND BROKEN AT THE VALVE HEAD. CYLINDER SA10200, S/N AM1376 INSTALLED. OTHER VALVES INSPECTED AND REPLACED VALVES SA10204 ON CYLINDER NR 4 AND NRSDR CA051104008Washer · damaged(CAN) PARTIAL POWER LOSS IN-FLIGHT. UPON INSPECTION, CONTRACT AMO FOUND A WASHER LODGED UNDER AN INTAKE AND EXHAUST VALVE, CAUSING ZERO COMPRESSION. ON DISASSEMBLY, SCREW FOUND IN SCAT HOSE LEADING FROM CARB HEAT INTAKE PORT TO HEAT MUFF. LIKELY SCREW AND WASSDR 2005FA0001201Rotor Shaft · shearedALTERNATOR SHAFT SHEARED AT BEARING LOCATION. DRIVE GEAR, BUSHINGS, RETAINER AND COUPLING ASSEMBLY ROLLED BETWEEN ENGINE ACCESSORY CASE AND DRIVE GEAR. THE SHAFT HAD BEEN PREVIOUSLY CRACKED OVER 50 PERCENT PRIOR TO FAILURE. (K)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 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 CA041110006Flap Track · worn(CAN) ON INSPECTION FLAP TRACK GROOVES FOUND BADLEY WORN,PARTS WERE REPLACED AS REQUIRED.SDR CA041110005Flap Track · worn(CAN) ON INSPECTION FLAP TRACK GROOVES WERE FOUND BADLEY WORN. PARTS WERE 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 CA041110007Door Frame · cracked(CAN) ON INSPECTION FOUND CRACKED AT UPPER FWD RADIUS ABOUT 1.0 INCH IN LENGTH. PART WAS REPLACED AS REQUIRED.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 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 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 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 R142003F00002Caliper · corrodedLEFT BRAKE CALIPER REMOVED AND INSPECTION OF PART FOUND CORROSION AND PITTING ON CALIPER PISTON WALLS. PISTON WAS BINDING WHEN MOVED. THE PISTON WOULD NOT MOVE FREELY WITNIN CALIPER HOUSING. INSTALLED NEW LEFT BRAKE CALIPER.SDR 2003FA0001178Caliper · corrodedLT BRAKE CALIPER REMOVED AND INSPECTION OF PART FOUND CORROSION AND PITTING ON CALIPER PISTON WALLS. PISTON WAS BINDING WHEN MOVED. THE PISTON WOULD NOT MOVE FREELY WITHIN CALIPER HOUSING.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 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 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 H9Q2003F00000Elt · misoverhauledDURNG THE COURSE OF AN ANNUAL INSPECTION, ACCESS WAS GAINED TO THE ELT FOR TESTING AND BATTERY DATE VERIFICATION. THE FOLLOWING DISCREPANCIES WERE IMMEDIATELY OBVIOUS. THE UNIT HAD BEEN CONNECTED TO THE EXISTING SYSTEMS ANTENNA. THE REMOTE PANEL INDICATOR SSDR 2003FA0000199Spinner · damagedPROP REMOVED TO FACILITATE REPLACEMENT OF ENG CRANKSHAFT SEAL. REMOVAL OF SPINNER, SEVERE WEAR AND FRETTING OF INNER SURFACE WAS NOTED WHERE FWD BULKHEAD (PN04500503) CONTACTS SPINNER. AFTER REMOVING PROP, PROP MOUNT BOLTS WERE OVERTORQUED, RESULTING IN DEFOSDR CA030115005Door Frame · cracked(CAN) DOOR POST SKIN EXTERIOR FOUND 0.5 INCH CRACK AT THE CENTRE OF THE CURVE CUTOUT AT THE FORWARD UPPER DOOR ON THE FUSELAGE.SDR 2002FA0001208Transistor · unapproved partTRANSPONDER FAILURE: IDENT PULSE PRESENT AND REPLY LAMP LIT WHEN UNIT HOT. (NOT COMMANDED) FOUND Q22 AND ASSORTED CIRCUIT VERY TEMPERATURE SENSITIVE. REPLACED COMPONENTS AND FOUND Q22 NOT STANDARD PART. PART INSTALLED AN ECG TPE 123. PART REPLACED WITH ASDR CA020729011Wheel · cracked(CAN) UPON INSEPCTION IT WAS DISCOVERED THAT THE HUB WAS CRACKED IN THE AREA OF THE GREASE SEAL RETAINING RING. THE CRACK IS ONLY ABOUT 3/8 INCH LONG AND TRAVELS PARALLEL TO THE RETAINING RING GROOVE JUST BELOW IT. HUB WAS REPLACED.SDR CA020307015Gear · broken(CAN) PILOT RETURNED TO BLOCKS AND SHUT ENGINE DOWN AFTER NOTICING THAT THE RPM GAUGE WAS UNSERVICABLE. UPON FURTHER INSPECTION FOUND THAT THE UPPER OIL PUMP GEAR, WHICH IS ALSO THE TACHOMETER DRIVE SHAFT. HAD SPLIT. THE PIECE WAS RECOVERED. AND THE GEAR / SHSDR CA020307010Casting · corroded(CAN) WHILE REMOVING COMPONENTS OFF OF THE ACCESORIE CASE, (UN RELATED REPAIR) DISCOVERED VER DEEP PITTING AND CORROSSION AROUND THE RIGHT MAGNETO OPENING.CASTING WAS REPLACED.
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