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 = '206B' 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 = '206B' 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 CA001205009Pitch Link · misinstalled(CAN) INCORRECT P/N FORK INSTALLED ON THE UPPER END OF THE ASSEMBLY. THIS FORK HAS THE SAME DIMENSION AS THE BOTTOM FORK (.8621). WHEN INSTALLED OVER THE TRUNNION THERE IS A SPREAD STRESS OF .013 INCHES.SDR CA001122011Screw · sheared(CAN) THE SCREW HEAD RETAINING THE FUEL CONTROL UNIT RATIO LEVER COVER (FUEL SIDE) SEPARATED IN-FLIGHT ALLOWING FUEL TO LEAK INTO THE ENGINE COMPARTMENT UNDER HIGH PRESSURE AND REDUCE THE FUEL FLOW TO THE ENGINE TO THE POINT WHERE CONTINUED FLIGHT WAS NOT POSSSDR CA001013019Turbine · failed(CAN) DURING A COMPRESSOR WASH, BRULIN AND WATER MIX WAS COMING OUT OF THE NR 6 AND NR 7 AIR DELIVERY TUBE. UPON FURTHER INVESTIGATON IT WAS DISCOVERED THAT THE TUBE WAS NOT WELDED TO THE ASSY. (X)SDR CA000614012Bolt · loose(CAN) DURING A ROUTINE CLEANING BEHIND HAT RACK AREA, 2 BOLTS ATTACHING A SUPPORT ASSY (ITEM 34, 206 IPC FIG.67-2) WERE FOUND SIGNIFICANTLY LOOSE. AREA WAS INSPECTED FOR FURTHER DEFECTS, NONE FOUND. BOLTS WERE TIGHTENED PER BELL 206 MAINTENANCE MANUAL. A QUSDR CA000606009Bearing · worn(CAN) WHILE IN-FLIGHT, THE PILOT COULD HEAR A LOUD METALLIC SCREAMING GRINDING NOISE FROM THE ENGINE. HE LANDED AT A CLEARING AND SHUT DOWN ENGINE. THE ENGINE GEARBOX HAD QUICK DISCONNECT CHIP PLUGS, PULLED THE CHIP DETECTORS AND FOUND FERROUS METAL ON THE OSDR CA001013015Gearbox · loose(CAN) NOTED ENGINE MOUNT WAS LOOSE. TURBINE TO GEARBOX ATTACHMENT FOUND LOOSE. NOTED ENGINE NOISE AND VIBRATION. GEARBOX REPLACED.SDR CA000516001Battery · leaking(CAN) ELT WAS REMOVED FOR ANNUAL INSPECTION AND IT WAS NOTED THAT WHITE POWDER WAS ON OUTSIDE OF BATTERY AND ELT CASE. UPON INSPECTION AFTER BATTERY REMOVAL, A LEAK WAS DETECTED. BATTERY STILL HAD 5 MONTHS LEFT ON ITS LIFE. EXPIRATION, SEPT 2000. BATTERY SDR CA000713004Nut · cracked(CAN) DURING A SCHEDULED OVERHAUL OF THE ABOVE DESCRIBED MAIN ROTOR HUB ASSEMBLY, A COMPONENT WITHIN THIS ASSEMBLY KNOWN AS THE MAST NUT WAS FOUND TO HAVE A CRACK INDICATION. THIS WAS DETECTED DURING THE MAGNETIC PARTICLE INSPECTION. THIS NUT HAS SINCE BEEN SESDR CA000516015Governor · defective(CAN) PILOT COMPLAINED OF LAGGING GOVERNOR WHICH ALSO TENDED TO UNDERSPEED AND OIVERSPEED AS COLLECTIVE WAS CHANGED AND NOT RECOVER TO THE SET RPM. UPON REMOVAL, THE AME NOTICED SOMETHING WAS NOT QUITE RIGHT AT THE DRIVESHAFT. UPON INPSPECTION, THE EPOXY, CISDR CA000706035Casting · cracked(CAN) CRACK FOUND AT AFT CASTING WHERE TAIL ROTOR GEARBOX MOUNTS IN TAILBOOM ON R/H HOLE. CASTING REMOVED BY OVERHAUL SHOP FOR REPLACEMENT AND CRACK ALSO LOCATED IN LT MOUNTING AREA. CRACK WAS FOUND ON SCHEDULED 100 HOUR INSPECTION OF AIRCRAFT.SDR CA000614011Pitch Link · unsafetied(CAN) DURING MAINTENANCE, PERFORMED BELOW THE ENGINE PAN, A TAIL ROTOR FLIGHT CONTROL BOLT WAS FOUND UNFASTENED. T/R ANTI-TORQUE CONTROL TUBE (ITEM NR 21, 206 IPC FIG.67-2) REAR ATTACHMENT BOLT FOUND WITH NUT BACKED OFF, NO COTTER PIN INSTALLED. AIRCRAFT GROSDR CA000505011Shield · cracked(CAN) WHEN COMPLETING CEB A-1370, 1ST STAGE NOZZLE SHIELD INSPECTION, FOUND AREA OF INSPECTION CRACKED.SDR CA001013010Bearing · loose(CAN) BEARING FOUND LOOSE IN THE DRAG PIN, POOR STAKING SEEMS TO BE THE CAUSE.SDR CA000414009Brush Block · broken(CAN) POST-FLIGHT INSPECTION REVEALED THAT ONE OF THE BRUSHES WAS WORN DOWN TWICE AS MUCH AS THE OTHER VISIBLE BRUSH. UPON REMOVAL, IT WAS THEN NOTED THAT ONE OTHER BRUSH WAS BROKEN AND/OR BURNT OFF. HOWEVER, THE STARTER/GENERATOR WAS STILL FUNCTIONING AS ITSDR CA000427015Exhaust Stack · cracked(CAN) CRACK AT RIVET JOINT (TOP) WHICH THEN CAUSED THE CLAMP TO BREAK.SDR 20000510SH020Bulkhead · crackedDURING ROUTINE INSPECTION, DISCOVERED HARILINE CRACK IN SKIN. SUBMITTER SUGGESTED MORE FREQUENT CHADWICK BALANCE & TRACK OR OTHER FORM OF VIBRATION TEST AT OR OF TALL ROTOR BLADES AS THIS HIGH FREQUENCY VIBRATION, WHICH RESULTS FROM TAIL ROTOR OUT OF BALANCE SDR 20000427SH002Indicator · malfunctionedPILOT REPORTED FLUCTUATIONS IN THE FUEL QUANTITY INDICATOR. FLUCTUATED FROM ZERO TO KNOWN QUANTITY. SOLDERED WIRE CONNECTION AT ZERO ADJUST RESISTOR, WAS CORRODED AND LOOSE. RE-SOLDERED AND RECALIBRATED FUEL QUANTITY SYSTEM. SUBMITTER RECOMMENDED THAT HEATSDR 20000601SH012Static Line · failedPILOT REPORTED AIRSPEED INDICATED LOW AT CRUISE. FOUND THAT LANDING LIGHT CHAFED A HOLE IN THE PITOT STATIC LINE (IPC REF: FIG 95-7, PAGE 28 ITEM 16). REPLACED TUBE AND REPOSITIONED AS NOT TO CHAFE. (X)SDR 20000426SH022Pump · failedAFT BOOST PUMP INOPERATIVE. INSPECTED AIRFRAME FUEL FILTER AND FOUND FILTER WAS COATED WITH A BLACK CARBON LIKE MATERIAL THAT WAS SUSPECTED TO BE RESIDUE FROM THE MAGNETS SURROUNDING THE BOOST PUMP CORE. (X)SDR 20000426SH021Support Bracket · corrodedDURING THE ANNUAL INSPECTION, THE PIVOT SUPPORT ASSEMBLY WAS FOUND CORRODED. REPLACED SUPPORT ASSEMBLY WITH NEW PART. SUBMITTER RECOMMENDED SPRAYING A CORROSION PREVENTATIVE COMPOUND IN THE AREA OF THE SUPPORT ASSEMBLY. (X)SDR 20000425SH044Fitting · corrodedTHIS PART WAS DISCOVERED CORRODED WITH AREAS IN EXCESS OF 25 PERCENT OF THE MATERIAL MISSING. THIS WAS FOUND DURING AN ANNUAL INSPECTION. THE AREA OF THIS FITTING IS ENCLOSED AND FILLED WITH INSULATION WHICH RETAINED MOISTURE CONTRIBUTING TO THE CORROSION. SSDR 20000412SH024Coupling · chippedDURING NORMAL 600-HOUR/12-MONTH INSPECTION AND REPACK OF MAIN ROTOR DRIVESHAFT, DISCOVERED A GEAR TOOTH (ON THE END) OF THE OUTER COUPLING WAS CHIPPED. SUBMITTER SIFTED THROUGH THE GREASE, BUT COULD NOT FIND ANY EVIDENCE OF THIRD CHIP. PART WAS RED-TAGGED ASDR 20000424SH019Bearing · making metalMETAL FLAKES DETECTED ON MAGNETIC PICK-UP IN LOWER GEARBOX AND OIL PUMP MAGNETIC PICK-UP. DISASSEMBLED GEARBOX FOR INSPECTION. BEARING INNER AND OUTER RACES BOTH HAD AREAS THAT HAD FLAKED OFF METAL. (X)SDR CA000307001Structure · cracked(CAN) SECURING LUGS (P/N D2731) THAT SECURE THE HIGH SKID GEAR STEP ASSY FOUND CRACKED. SUBMITTER SUSPECTED CAUSE OF CRACKS IS IMPROPER TORQUE OF THE NUT AND BOLT WHICH SHOULD BE UP TO 60 INCH/POUNDS. MANUFACTURER HAS BEEN NOTIFIED.SDR 20000510SH001Frame · crackedFRAME CRACKED AT TOP RIGHT HAND POSITION, (1:00 O''CLOCK). (X)SDR CA000308003Bolt · broken(CAN) REAR/TOP ATTACHMENT BOLT OF VERTICAL FIN ASSY WAS FOUND BROKEN (STILL IN PLACE) ON 600 HOUR CHECK. THE OTHER 3 BOLTS WERE FOUND BELOW MINIMUM TORQUE VALUE.SDR 20000601SH002Bulkhead · crackedPART IN QUESTION IS LOCATED ON THE AFT MOST SECTION ON THE HELICOPTER TAIL BOOM. THE TAIL ROTOR GEARBOX AFT MOUNT STUDS PASS THROUGH THE TOP OF THIS FITTING ON THE LEFT AND RIGHT SIDES. CRACKS DEVELOPED FROM THESE STUD HOLES TO ADJACENT MOUNTING RIVET HOLES.SDR CA000224022Fan · separated(CAN) DURING CRUISE FLIGHT, THE AIR DISTRIBUTION FAN DEPARTED THE MOTOR/FAN ASSEMBLY. THE FAN THEN CHEWED THROUGH THE LOWER CHIN BUBBLE AND DEPARTED THE AIRCRAFT.SDR CA000301019Skin · cracked(CAN) FOLLOWING RECEIPT OF SERVICE DIFFICULTY ADVISORY AV-1999-03R1, AN INSPECTION REVEALED A CRACK IN THE BULKHEAD BELOW THE NUTPLATES. CRACK HAD PREVIOUSLY BEEN REPAIRED WITH A PATCH BUT CRACK HAD SPREAD INTO AN ADJOINING STRUCTURAL PANEL. ANOTHER CRACK WAS SDR CA000218009Bearing Cage · failed(CAN) STARTER/GENERATOR REMOVED BECAUSE OF EXCESSIVE VIBRATIONS . IT WAS LATER FOUND THAT BEARING LINER WAS VERY LOOSE IN THE DRIVE END END BELL WHICH ALLOWED THE ARMATURE TO FLOP AROUND. NEW END BELL WAS INSTALLED. FAULTY STARTER/GEN WAS QUARANTINED.SDR CA000324003Indicator · malfunctioned(CAN) ALTITUDE DIGITIZER COMES ON AFTER 3 MINUTES, BUT THEN CLIMBS TO 500 FEET ABOVE ACTUAL ALTITUDE AND THEN SLOWLY RETURNS TO ACTUAL ALTITUDE. AFTER 10 MINUTES THIS UNIT FUNCTIONS CORRECTLY. HOWEVER, THE OPERATOR OF THIS ROTORCRAFT HAS BEEN REQUESTED BY ATCSDR CA000215009Brush Block · destroyed(CAN) BRUSHES ARE FAILING PREMATURELY, SUBMITTER SPECIFIED THAT THIS IS A NATIONAL PROBLEM THAT IS NOT ISOLATED TO THIS PN BRUSH OR PN STARTER.SDR 20000405SH028Combustion Liner · crackedDURING HOVERING ON A TRAINING FLIGHT, THE PILOT NOTICED THAT TOT TEMPERATURE WAS HIGHER THAN NORMAL. AFTER TROUBLESHOOTING WHICH INCLUDED CHANGING BLEED VALVE AND CHECKING ANTI-ICE FOR PROPER CLOSING, THERE WAS NO CHANGE. POWER CHECK ON ENGINE INDICATED SUBSSDR CA000203010Line · damaged(CAN) FUEL LINES HAD DECAYED TO THE POINT THAT RUBBER WAS COMING THRU BRAID. THESE SMALL PIECES OF RUBBER CAUSED FUEL CHECK VALVES TO STICK OPEN AND CAUSED LOW PRESS FUEL PRESSURE READINGS. NEW FUEL HOSES INSTALLED.SDR AU000203010Line · decayed(AU) FUEL LINES HAD DECAYED TO THE POINT THAT RUBBER WAS COMING THROUGHTHE BRAID. THESE SMALL PIECES OF RUBBER CAUSED FUEL CHECK VALVES TO STICK OPEN AND CAUSED LOW PRESSURE FUEL PRESSURE READINGS. NEW FUEL HOSES INSTALLED.SDR CA000128030Brush Block · broken(CAN) WHILE PERFORMING 100 HR INSPECTION ON STARTER/GEN, A BRUSH LEAD WAS FOUND BROKEN AND ANOTHER BADLY DAMAGED. SUBMITTER STATED THIS IS THE 3RD OCCURRENCE IN THE LAST 3 MONTHS.SDR 2000ZZZX727Governor · malfunctionedIN CRUISE FLIGHT, THE POWER TURBINE ROTOR DROOPED TO 90 PERCENT AND WOULD NOT RECOVER. THE PILOT LOWERED COLLECTIVE, RECOVERED ROTOR SPEED AND DID A POWER ON RECOVERY.SDR 2000ZZZX88Plug · mismanufacturedSUSPECT COMPOSIT THRUST PLUGS WERE MISMANUFACTURED OR IMPROPERLY INSTALLED ALLOWING TRUNNION TO SHIFT. THIS CAUSED AN OUT-OF-BALANCE CONDITION. THE TAIL ROTOR HUB AND BLADE ASSEMBLY WAS DYNAMICALLY BALANCED ON SEVERAL OCCASIONS. EACH TIME THE TAIL ROTOR VIBSDR CA000110033Stator · failed(CAN) STARTER GENERATOR SENT TO OVERHAUL AFTER ONLY 96 HOURS. STATOR COWLING OUTLET SCREEN FOUND TO BE CLOGGED WITH SOME FOREIGN INSULATION WHICH HAD OCCURRED DURING THE PREVIOUS REWIND. STATOR IS NOW QUARANTINED UNTIL FURTHER INVESTIGATION IS COMPLETED AS TO SDR AU000110033Stator · misoverhauled(AU) STARTER/GENERATOR SENT TO OVERHAUL AFTER ONLY 96 HOURS. STATOR COWLING OUTLET SCREEN FOUND TO BE CLOGGED WITH SOME FOREIGN INSULATION WHICH HAD OCCURRED DURING THE PREVIOUS REWIND. STATOR IS NOW QUARANTINED UNTIL FURTHER INVESTIGATION IS COMPLETED AS TOSDR CA000110006Shaft · stripped(CAN) HYDRAULIC SYSTEM FAILURE WHICH WAS LATER ATTRIBUTED TO COUPLING FAILURE INSIDE HYD PUMP.SDR CA991229066Bushing · cracked(CAN) DURING 100 HOUR INSPECTION, RT ENGINE MOUNT WAS FOUND LOOSE. UPON DISASSEMBLY, THE BUSHING WAS FOUND TO BE SEPARATED (RUBBER BONDS WERE SEPARATED). BUSHING ID & OD WERE WORN BEYOND LIMITS. RT ENGINE MOUNT LEGS WERE ALSO FOUND TO HAVE THE BUSHING MOUNTINGSDR CA991229020Nozzle · contaminated(CAN) N2 BLEED OFF EXPERIENCED WHEN POWER REQUESTED. FUEL NOZZEL REMOVED AND FOUND TO HAVE CARBON BUILD-UP. NOZZEL SENT FOR O/H.SDR CA000404014Servo · failed(CAN) EXCESSIVE VERTICAL PLAY AT PILOT INPUT TRUNNION AND PILOT VALVE AREA OF THE SERVO. FEEDBACK IS EXCESSIVE, ALSO CHATTERING AN VIBRATING AND NOISY DURING GROUND RUN AND TEST FLIGHTS.SDR CA991209007Bleed Valve · failed(CAN) COMPRESSOR STALLS WHEN POWER APPLIED AT ALT.SDR 2000ZZZX152Combustion Case · crackedPILOTS REPORTED LOW POWER AND HIGH TOT. TROUBLESHOOTING FOUND A LARGE CRACK IN THE ARM PIT AREA WHERE IT IS REINFORCED WITH A BRAZED ON SCREEN, RIGHT SIDE. PART REMOVED AND SENT IN FOR POSSIBLE REPAIR. POSSIBLE CAUSE, METAL FATIGUE.SDR 99ZZZX4588Rotor · crackedUPON VISUAL INSPECTION OF THE POWER TURBINE SECTION WHEN REMOVED FOR 10W POWER REPAIR. DISASSEMBLED P.T. ROTOR AND FOUND CRACKED DIAPHRAGM THROUGH NR 4 NOZZLE INNER BAND. POSSIBLE CAUSE IS DUE TO NOZZLE UNABLE TO HANDLE STRESS FROM HEAT. NOTE: THIS DIAPHRASDR 20000329SH042Blade · damagedMAIN ROTOR BLADE FACTORY INSTALLED WEIGHT DISLODGED DURING OPERATION STRIKING MAIN ROTOR BLADE TIP CAP. TIP CAP TRAILING EDGE WAS BENT OUTBOARD APPROXIMATELY 30 DEGREES AND APPROXIMATELY ONE INCH OF WEIGHT PROTRUDED THROUGH OUTBOARD END OF SPAR. UPPER AND LOSDR 99ZZZX4436Blade · damagedMAIN ROTOR BLADE FACTORY INSTALLED WEIGHT DISLODGED DURING OPERATION STRIKING MAIN ROTOR BLADE TIP CAP. TIP CAP TRAILING EDGE WAS BENT OUTBOARD APPROXIMATELY 30 DEGREES AND APPROXIMATELY ONE INCH OF WEIGHT PROTRUDED THROUGH OUTBOARD END OF SPAR. UPPER AND LOSDR 2000ZZZX420Blade · damagedMAIN ROTOR BLADE FACTORY INSTALLED WEIGHT DISLODGED DURING OPERATION STRIKING MAIN ROTOR BLADE TIP CAP. TIP CAP TRAILING EDGE WAS BENT OUTBOARD APPROXIMATELY 30 DEGREES AND APPROXIMATELY ONE INCH OF WEIGHT PROTRUDED THROUGH OUTBOARD END OF SPAR. UPPER AND L
Back to Bell 206B