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 = '206L' 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 = '206L' 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 CA030617001Attach Fitting · cracked(CAN) DURING MAJOR INSPECTION THE TAILBOOM ATTACH FITTING UPPER LT FUSELAGE SIDE WAS FOUND CRACKED AT THE UPPER AFT RIVET HOLE.SDR CA031031006Governor · failed(CAN) NR DROOPING TO 97 WITHOUT RECOVERY UNDER POWER AND OVER SPEEDING TO 107 WHEN POWER REDUCED.SDR CA030612006Case · cracked(CAN) AFTER INPSECTION WITH THE ENGINE RUNNING A LEAK CHECK WAS CARRIED OUT BY PLACING A HAND IN AREA OF THE FUEL NOZZLE AND AIR WAS FELT. THE ENGINE WAS SHUT DOWN AND A CLOSE INSPECTION WAS CARRIED OUT IN THE AREA OF WHERE THE NOZZLE ADAPTER PLATE IS WELDED TSDR CA030612005Case · cracked(CAN) ROUTINE INSPECTON AND CHANGING FUEL NOZZLE IT WAS SUSPECTED THAT THERE WAS A CRACK ALONG THE WELD WHERE THE FUEL NOZZLE ADAPTER IS ATTATCHED TO THE END OF OUTER COMBUSTION CASE. ON CLOSER INSPECTION IT WAS NOTED THAT THE CRACK COVERED OVER HALF OF THE WSDR CA030218004Spring · broken(CAN) SPRING BROKE, TURNED SIDEWAYS AND CHAFED SPHERICAL COUPLING AND PLATE.SDR CA030210004Servo · leaking(CAN) HYDRAULIC SERVO LEAKING. REMOVED FOR REPAIR.SDR CA030204014Lever · failed(CAN) REQUIRED BOLT PN NAS6604D8 (AS PER 206L IPC) WOULD NOT FIT IN EXISTING HOLE OF FUEL CONTROL LEVER PN 206064713101 WITHOUT ENLARGING HOLE.SDR CA030127001Turbine · seized(CAN) DURING FIRST START OF THE ENGINE, FOLLOWING A TURBINE CHANGE, MAIN ROTOR BLADES INITIALLY STARTED TURNING BUT THEN STOPPED BEFORE ENGINE ACCELERATED TO IDLE SPEED. THE START WAS ABORTED.AME ATTEMPTED TO TURN THE MAIN ROTOR BLADES BACKWARDS BUT WAS UNABLESDR CA030103016Tube · chafed(CAN) AFTER A FLIGHT OF 3.7 HOURS, WHILE DOING THE DAILY INSPECTION A LARGE PATCH OF OIL WAS FOUND UNDER THE HELICOPTER. THE BELLY WAS COVERED BY OIL. INVESTIGATION REVEALED 2 TUBES FROM THE TRANSMISSION TO THE OIL COOLER HAD CHAFED AGAINST EACH OTHER AND WERSDR CA021104008Disc Pack · cracked(CAN) DURING ROUTINE INSPECTION, BOLTS ON THE MOST FORWARD DISC PACK WAS FOUND TO BE LOOSE. THE BOLTS WERE TORQUE SEALED AS PER MANUFACTURERS INSTRUCTIONS. THE LOOSE BOLTS WERE WORN, THE HOLES IN THE DISC PACK WERE ELONGATED AND ONE PLATE OF THE DISC PACK WASSDR CA020827008Sun Gear · cracked(CAN) CUSTOMER REPORTED TRANSMISSION TO BE MAKING METAL AT 185.1 SINCE OVERHAUL. TRANSMISSION RETURNED TO OUR FACILITY FOR TEARDOWN AND INSPECTION. ON TEARDOWN IT WAS FOUND THAT THE SUN GEAR HAD FAILED. THE SUN GEAR WAS INSTALLED NEW AT THE TIME OF OVERHAUL.SDR CA020612006Spur Adapter · spalled(CAN) ENGINE CHIP LIGHT FOUND METAL PARTICLES ON BOTH CHIP PLUGS. 2 1/2 BEARING AND INNER RACE ON THE SPUR ADAPTER FOUND SPALLED.SDR HEEA078703Bearing · failedREMOVED DUE TO ENGINE RAN WITH LOW OIL PRESSURE. NR 3 AND 4 BEARING FAILURE.SDR HEEA078702Bearing · failedREMOVED DUE TO ENGINE RAN WITH LOW OIL PRESSURE. NR 3 AND 4 BEARING FAILURE.SDR 2002FA0000705Gear · damaged(PTO GEAR) UPON VISUAL INSPECTION OF PART AFTER BEING CHECKED OUT OF STOCK. DAMAGE TO 4 EA SMALL GEAR TEETH AND 1 EACH TOOTH HAS ARC LIKE RECESSED AREA.SDR CA020412012Bushing · worn(CAN) TRANSMISSION STOP MOUNT HAS WORN BUSHINGS. REPLACED.SDR CA020408005Combustion Liner · cracked(CAN) ENGINE PERFORMANCE DETERIORATED, POWER CHECK CARRIED OUT, ENGINE DID NOT MEET SPECIFICATIONS. VISUAL INSPECTION REVEALED A CRACK IN LT ARMPIT OF THE OUTER COMBUSTION CAN. THE CAN WAS REPLACED.SDR CA020403008Stiffener · cracked(CAN) CRACKED VERTICAL STIFFENER. CUTOUT IN HORIZONTAL STIFFENER WAS TOO SMALL WHICH PUT PRESSURE ON VERTICAL STIFFENER CAUSING IT TO CRACK.SDR 2003FA0000325Control Unit · intermittentAUTO-RELIGHT SYSTEM ACTIVATES INTERMEDIATELY DURING NORMAL ENGINE OPERATION.SDR 2002FA0000145Support · mismanufacturedTRIED TO PUT SUPPORT IN FIXTURE TO LOCATE TO TAILBOOM. RADIUS BEND IS TOO WIDE. BETER QUALITY CONTROL AT MFG.SDR 2002FA0000144Support · mismanufacturedTRIED TO PUT SUPPORT IN FIXTURE TO LOCATE TO TAILBOOM. RADIUS BEND IS TOO WIDE. BETTER QUALITY CONTROL AT MFG.SDR 2002FA0000143Support · mismanufacturedTRIED TO PUT SUPPORT IN FIXTURE TO LOCATE TO TAILBOOM. RADIUS BEND IS TOO WIDE. BETTER QUALITY CONTROL AT MFG.SDR CA011105002Tube · corroded(CAN) DURING TRANSMISSION 1500 HOUR INSPECTION CORROSION AND PITTING FOUND ON THE FLARE OF THE TUBE ASSEMBLY.SDR CA011003009Leg Assy · corroded(CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION THE ENGINEER NOTICED A HILOCK COLLAR IN THE ENGINE BAY. UPON INVESTIGATION IT WAS NOTED THAT THE HI-LOCK PIN HAD CORRODED THROUGH & THE COLLAR FELL OFF. LEG ASSEMBLY REPLACED WITH NEW.SDR CA010912003Fitting · cracked(CAN) ROUTINE INSPECTION UPPER LEFT TAIL ATTACH FITTING FOUND CRACKED.REPLACED AS PER BELL STRUCTURAL REPAIR MANUAL 6-214, BUT NUMEROUS REPORTS OF CRACKS IN THIS LH UPPER FITTING AREA OF TAILBOOM/FUSELAGE INTERFACE.SDR CA010809016Case · damaged(CAN) ON WINDUP FROM GROUND IDLE TO FLIGHT IDLE, THE PILOT HEARD A POPPING NOISE AND A STEADY SOUND OF RUSHING AIR. THE TURBINE OUTLET TEMPERATURE (TOT) HAD CLIMBED INTO THE YELLOW ARC. DURING TROUBLLE SHOOTING THE COMPRESSOR CASE HALF WAS MISSING AND STATOR (SDR CA010725031Hose · leaking(CAN) DURING REFUELING OPERATION, FUEL WAS OBSERVED LEAKING FROM TANK VENT HOSE ASSEMBLY WHEN TANK WAS FILLED TO CAPACITY. HOSE APPEARS TO HAVE DETERIORATED WITH AGE ALLOWING FUEL TO LEAK. DUE TO THIS DEFECT ANOTHER AIRCRAFT WAS VERIFIED BY PRESSURE TESTING THSDR CA010725023Fitting · cracked(CAN) THE FITTING HAD TO BE REPLACED DUE TO CRACK. IT APPEARS TO HAVE CRACKED DUE TO INCORRECT INSTALLATION. THERE WAS A 100 INCH GAP BETWEEN THE LONGERON AND THE FITTING AND THIS PLACED THE FITTING UNDER STRESS. THE FITTING WAS REPLACED BY A NEW PART WITH CARSDR CA010725022Arm · damaged(CAN) FOUND NUT OF ACTUATOR ARM LOOSE IN ARM. UNIT REPLACED AND AIRCRAFT RETURNED TO SERVICE AFTER ADJUSTMENTS.SDR CA010704025Shaft · corroded(CAN) DURING AN UNSCHEDULED MAINTENANCE REMOVAL OF THE UNIT IT WAS NOTED THAT THERE WAS EXCESSIVE PITTING CORROSION ON THE INNER SHAFT IN THE AREA WHERE THE FELT WIPER OF THE FORWARD SEAL RIDES. THE WIPER APPEARS TO ABSORB MOISTURE AND HOLDS IT IN CONTACT WITHSDR CA010727015Bulkhead · cracked(CAN) THE TAIL BOOM WAS REMOVED FOR 1200 HOUR INSPECTION. CRACKS WERE FOUND AROUND THE TOP LEFT ATTACH BOLT HOLE SHIM PART # 206-032-400-117. WHEN THE BULKHEAD WAS REMOVED, CRACKS WERE FOUND ALONG THE TOP EDGE OF THE MATING SURFACE OF THE BULKHEAD AND BOLT ATTSDR CA010724032Fitting · corroded(CAN) THE FITTING WAS FOUND CORRODED ON 1200 HOUR INSPECTION AND NEW PART 206-033-173-001 WAS INSTALLED. THE ORIGINAL PART IS MANUFACTURED FROM MAGNESIUM WHERE THE NEW PART IS ALUMINUM SO AFTER 13109 OF FLYING ON A AIRCRAFT MANUFACTURED IN 1978 THIS WOULD NOTSDR CA010724031Bulkhead · cracked(CAN) THE TAIL BOOM WAS REMOVED FOR 1200 HOUR INSPECTION. CRACKS WERE FOUND AROUND THE TOP LEFT ATTACH BOLT HOLE SHIM PART 206-032-400-117, WHEN THE BULK HEAD WAS REMOVED CRACKS WERE FOUND ALONG THE TOP EDGE OF THE MATING SURFACE OF THE BULK HEAD AND BOLT ATTSDR CA010706014Pitch Horn · loose(CAN) DURING A DAILY INSPECTION, WE DISCOVERED THAT THE TORQUE OF THE BOLTS HOLDING THE PITCH HORN TO THE TAIL ROTOR BLADE WAS LOOSE. THE LOCKWIRE WAS STILLIN PLACE BUT THE 2 BOLTS WERE NO LONGER TORQUED.DURING THE DISMANTLING NO OTHER ANORMALITIES. THE PITCH SDR CA010507008Oil Cap · loose(CAN) LOCKING PINS IN TRANSMISSION OIL FILTER CAP ASSEMBLY CAME LOOSE AND FELL OUT OF TRANSMISSION OIL FILLER CAP ASSEMBLY. REPLACED WITH NEW OIL FILTER CAP ASSEMBLYSDR CA010510003Tube · cracked(CAN) CRACK WAS VISIBLE TO NAKED EYE EMINATING FROM LOWER INSERT FAYING SURFACE AND EXTENDING VERTICALLY UPWARD 0.4 INCHES. SOME CORROSION PRESENT. REPLACED BOTH PITCH LINK ASSEMBLY WITH LINK ASSY P/N 206-010-360-005. SUSPECT THEY ARE ORIGINAL WHICH MEANS 14,0SDR AU010268Blade · corroded(AUS) MAIN ROTOR BLADE CORRODED IN AREA BETWEEN PAINT AND LEADING EDGESTRIP ON UNDERSIDE OF BLADE. CORROSION DEPTH APPROXIMATELY 1.52MM (0.060IN). FOUND BEFORE FITMENT.SDR 20010208CW007Blade · crackedAIRCRAFT WAS FLYING LOW SPEED OVER A CORN FIELD AT NIGHT FOR FROST PREVENTION. ON RETURN LEG TO AIRPORT FOR REFUELING. AT 11:30 PM AIRCRAFT DEVELOPED SEVERE MAIN ROTOR VIBRATION. UPON SHUTDOWN, FOUND CRACK IN BLADE AREA.SDR CA010307013Cover · grooved(CAN)WHEN REINSTALLING A MAIN DRIVESHAFT AFTER A INPUT TRANSMISSION SEAL REPLACEMENT, FOUND THAT THE TRANSMISSION END OF THE SHAFT COULD NOT MOVE. OPENED THE COUPLING END FOUND THAT SPRINGS WAS NOT INSTALLED PROPERLY. THE COVER WAS GROOVED. INSPECTED THE INNSDR CA001123016Vent · clogged(CAN) DURING REPLACEMENT OF BOOT ON TAIL ROTOR PITCH CHANGE MECHANISM, THE VENT HOLE IN TUBE ASSY P/N 206-011-724-003 WAS FOUND OBSTRUCTED. FUTHER INVESTIGATION REVEALED THAT DRIED GREASE WAS PLUGGING THE HOLE. THE VENT HOLE WAS CLEANED, AND THE TUBE RE-ASSEMBSDR CA000928004Line · chafed(CAN) PILOT LANDED & SHUT DOWN NORMALLY. HE THEN NOTICED FLUID RUNNING DOWN SIDE OF FUSELAGE. INVESTIGATION REVEALED THAT LEAKING OIL WAS COMING FROM THE MGB OIL PRESSURE INDICATING LINE, LOCATED UNDER THE TRANSMISSION RESTRAINT. THE CHAFING OF THE FOIL FLEX LSDR CA001005019Support Bracket · broken(CAN) DURING A DAILY INSPECTION CHECK, TWO BREAKS WERE FOUND IN TH E UPPER MAIN ATTACHMENT POINT FOR THE VERTICAL FIN REAR SUPPORT. THE BROKEN PIECE IS APPROXIMATELY 1 INCH BY 1 INCH IN SIZE. (X)SDR CA000809004Governor · failed(CAN) WHILE IN A HOVER, 100 FT AGL, PILOT NOTICED N2, N2 SPEED BETWEEN 100 - 113 PERCENT. PILOT LANDED ROTORCRAFT WITHOUT FURTHER INCIDENT. GOVERNOR REPLACED.SDR CA000803006Chip Detector · missing(CAN) DURING DAILY INSPECTION, IT WAS NOTICED THAT A PIN WAS NOT IN THE CHIP DETECTOR HOUSING ASSEMBLY. UPON REMOVAL IT WAS FOUND THAT 2 OF THE 3 PINS WHICH HOLD THE CHIP DETECTOR IN PLACE WERE MISSING. PINS COULD NOT BE FOUND. CHIP DETECTOR ASSEMBLY WAS RESDR CA000719021Bearing · loose(CAN) EXCESS BEARING PLAY. BEARING WAS LOOSE IN THE SLEEVE. REPLACED BEARINGS IN ACCORDANCE WITH BHT 206L M&O.SDR CA000511040Bolt · cracked(CAN) CRACKED TAILBOOM ATTACHMENT BOLT FITTING.SDR CA000511016Bearing · making metal(CAN) NR 1 COMPRESSOR ROLLER BEARING MAKING METAL.SDR CA000511015Bearing · making metal(CAN) TWO TINY MARKS ON BEARING - MAKING METAL. REPLACED WITH NEW MAST BEARING 206-040-536-101, S/N J0394-1 AND 2, NEW SEAL AND COMPLY WITH 1500 HOUR INSPECTION.SDR CA000404026Drive Shaft · bent(CAN) STARTER/GENERATOR FAILED TO ENGAGE DURING START-UP. NO PRIOR INDICATIONS OF IMPENDING FAILURE. NEW STARTER/GENERATOR INSTALLED AND CHECKS SERVICEABLE.SDR CA000310009Spline Adapter · loose(CAN) DURING ENGINE POWER CHECK, IT WAS NOTED THAT BOTH N2 AND NR SPEEDS DROPPED BELOW NORMAL. ENGINE ALSO OVERSPEED ABOVE NORMAL WHILE LOWERING COLLECTIVE. GOVERNOR REMOVED AND LOOSE SPLINES WERE FOUND WHERE ENGAGING INTO ENGINE GEARBOX. SOME SPLINE PARTS
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