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 jasc_code = '6420' 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 jasc_code = '6420' 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 CA130531013Stator Vane · damaged(CAN) DURING AN INSPECTION, THE PAINT ON TWO FENESTRON STATOR VANES HAS BEEN FOUND CRACKED, AND THE SHAPE OF THE VANES "SWOLLEN", ABOUT 1" OF THE L/E.SDR CA130618012Bearing · worn(CAN) THE TAIL ROTOR LAMINATED BEARING FOUND WORN.SDR K97A2013F00102Lever · groovedTORQUE SHAFT LEVER ASSY IS WORN WHERE RIGID CONNECTING LINK ATTACHES. GROOVE WORN IN TS LEVER ASSY.SDR CA130410010Bushing · loose(CAN) ON PERFORMING AN 600 HR INSPECTION ON THE STARFLEX 2 OUT OF 3 BUSHINGS WHERE FOUND LOOSE. THE BUSHING WHERE FOUND TIGHT TO HAND PRESSURE, BUT WHEN PUT IN A VISE THEY WHERE FOUND LOOSE. THE STARFLEX WAS REMOVED AND A NEW STARFLEX INSTALLED. THE OLD ONE SDR QMLA2013030113030Spar · crackedTAILROTOR ASSY SPAR CRACKED INTERNALLY. FOUND DURING MX.SDR CA130129002Bearing · cracked(CAN) LAMINATED BEARINGS INSPECTED IAW EASA AD 2012-0217E, SEPARATION NOTICED ON THE INBD AND OTBD AREA`S OF EACH HALF BEARINGS.SDR CA121214010Bearing · failed(CAN) PILOT REPORTED HEAVY VIBRATION ON FINAL APPROACH TO THE HELIPAD. FOUND THE INBD TAIL ROTOR HUB FLAPPING BEARING FAILED. OTBD TAIL ROTOR HUB, PN 429-012-101-117, SN DR18, FLAPPING BEARING ALSO EXTRUDING RUBBER AND HAS GAPS AND WILL ALSO BE CHANGED.SDR CA121017005Bearing · failed(CAN) UPON DAILY/PRE-FLIGHT INSPECTION, ENGINEER FOUND SOME BLISTERING AND CRACKS DEVELOPING ON OTBD BEARINGS, X2, INNER BEARINGS INSPECTED AND FOUND ACCEPTABLE CONDITION. ACFT GROUNDED, TAILROTOR ASSY REPLACED WITH SPARE ASSY. MFG ADVISED, WARRANTY CLAIM FORSDR K97A2012F00175Bushing · debondedDURING PRE-FLIGHT CHECK, PILOT COMPLAINED THAT THE TAIL ROTOR PEDALS WERE STIFF. MECHANIC CONFIRMED THIS AND DETERMINED THAT THE TAIL ROTOR HUB ASSEMBLY NEEDED TO BE DISSASEMBLED FOR FURTHER INVESTIGATION. UPON DISSASEMBLY MECHANIC FOUND TEFLON FRICTION WASHESDR ALGA2012091901Bearing · wornFOUND TAILROTOR HUB & BLADE ASSY ONE BEARING WORN.SDR CA120723020Bearing · cracked(CAN) AFTER INSTALLING A NEW SET OF TAIL ROTOR BLADES AND TGB ASSY AFTER THE LAST HALF SHELL FAILURE. WE FLEW THE ACFT HOME. ON INSPECTION OF THE HALF SHELL, WEAR WAS NOTICED. IAW ACFT MFG SAFETY INFORMATION NOTICE NR 2482-S-64. WE WILL BE REPLACING THE BESDR QMLA2012072312123Horn · crackedTAIL ROTOR PITCH CHANGE HORN CRACKED: VISIBLE FROM THE OTBD FACE OF THE TAIL ROTOR PITCH CHANGE HORN, RUNNING TANGENT FROM THE BOLT HOLE, ALONG THE EDGE THICKNESS, TO THE EDGE OF THE CONICAL INSERT ON THE INBD FACE. WITH THE ROTOR BRAKE SET AND APPLYING FORCESDR CA120716023Bearing · cracked(CAN) AIRCRAFT WAS FLYING FROM A TO B WHEN THE PILOT AND AME HERD A LOAD NOISE COMING FROM THE TAIL ROTOR FOLLOWED BY HIGH LEVELS OF VIBRATION. THIS VIBRATION INCREASED AS THE FLIGHT UNTIL THEY BOTH THOUGHT IT WAS TOO MUCH AND LANDED THE ACFT TO INSPECT THE TSDR CA120716024Bearing · cracked(CAN) ON INSPECTION OF THE TAIL ROTOR BLADE IT WAS FOUND THAT THESE HALF SHELLS OR LAMINATED BEARING WHERE WEARING OUT AT A VERY HIGH RATE AND WOULD NOT LAST FOR MORE THAN 100 HRS. THESE BEARING WHERE REMOVED AND A NEW SET INSTALLED. ACFT BALANCED AND PUT BASDR ALGA2012062501Bushing · crackedTAIL ROTOR HUB YOKE HAS A CRACKED BUSHING.SDR CA120622003Bushing · worn(CAN) WHEN THE TAIL ROTOR BLADES WERE REMOVED FOR SCHEDULED MX. THE CONTROL SPIDER ASSEMBLY WAS FOUND TO BE MOVING LOOSELY ON THE SHAFT. AFTER FURTHER INVESTIGATION IT WAS FOUND THAT THE SPHERICAL BEARING AT THE END OF THE TAIL ROTOR CONTROL TUBE WAS LOOSE. SDR CA120614006Nut · fractured(CAN) WHILE UNDOING THE NUT AS PART OF MAINTENANCE, THE NUT FAILED INTO 2 HALVES. MINIMAL TORQUE WAS APPLIED. THERE IS EVIDENCE OF A PRE-EXISTING CRACK. THE NUT WAS REPLACED AND TORQUED TO MFG SPECIFICATIONS.SDR ALGA20123200003Pitch Horn · corrodedTAIL ROTOR HEAD PITCH HORN CORRODED BEYOND REPAIRABLE LIMITS.SDR ALGA20123200002Pitch Horn · corrodedTAIL ROTOR HUB PITCH HORN HAS CORROSION BEYOND REPAIRABLE LIMITS.SDR QMLA2012010612002Bearing · shearedTHE INBD TAIL ROTOR HUB ELASTOMERIC BEARING WAS FOUND SHEARED ON A PREFLIGHT INSP. MX CONFIRMED THE DISCREPANCY AND ORDERED A REPLACEMENT TAIL ROTOR HUB ASSY. THE HUB ASSY WAS REPLACED AND THE ACFT WAS RETURNED TO SERVICE.SDR ALGAR201112080011Bearing · unstakedINBD BEARING UNSTAKED. ALL 4 FEATHER BEARINGS WERE NEVER ROLL STAKED. NEW YOKE FROM MFG WAS INSTALLED.SDR CA110816004Control Lever · loose(CAN) THE UPPER BUSHING ON THE TAIL ROTOR LEVER BECAME LOOSE. INSTALLED A NEW LEVER WITH NO FURTHER DEFECTS.SDR CA110803016Hub · seizedDURING INSP, TAIL ROTOR BLADE BOLTS REQUIRED A ARBOR PRESS TO BE REMOVED. UPON INSPECTION OF BLADE BOLT IT WAS FOUND TO HAVE BEEN WET ASSEMBLED WITH DRY MOLY LUBRICATE, ADDITIONALLY WHEN THE BLADE WAS TO BE REMOVED FOR INSP, IT REQUIRED EXCESSIVE FORCE TO REMSDR QMLDMG2181Torsion Bar · mismanufacturedTHIS WAS A NEW PART AND WAS BEING INSTALLED INTO THIS TAIL ROTOR HEAD. BORE HOLE MISALIGNED, LAMINATES BUCKLES WHEN PARTS ARE INSTALLED.SDR UNFR2011040200002Rotor Head · unbalancedTRACKING AND BALANCING T/R WITH TRACKING ON GROUND RUNS AND COULD NOT GET T/R TO BALANCE DYNAMICALLY. HAS BEEN INSTALLED ON 3 ACFT PRIOR AND REMOVAL HAS BEEN FOR UNABLE TO BALANCE DYNAMICAL IN LESS THAN 200 HOURS.SDR 7EMA409020711Bearing · failedAFTER TAKEOFF FROM ICT, 10 MINUTES INTO FLIGHT. PILOT NOTICED A HIGH FQUEQUENCY VIBRATION IN THE TAIL ROTOR PEDALS. ACFT DIVERTED AND MADE A PRECAUTIONARY LANDING. ACFT WAS PLACED OUT OF SERVICE FOR FURTHER INSPECTIONS AND REPAIRS. VIBRATION WAS DETERMINESDR RMXA2010F00240Pitch Link · delaminatedUPON ARRIVING TO CRUISE FLIGHT A LOW FREQUENCY VIBRATION BEGAN AND LASTED APPROX 20 MINUTES AND THEN DISAPPEARED FOR THE REMAINDER OF THE FLIGHT.SDR CA100818002Yoke · damagedDURING HIS WALK AROUND, THE PILOT DISCOVERED A HAIRLINE CRACK IN THE PAINT OF THE FWD EDGE OF THE TAIL ROTOR HUB (IN LINE WITH THE AXIS OF OUTPUT SHAFT OF THE TAIL ROTOR GEARBOX) AND ON THE ORANGE BLADE SIDE. AME 1 WASN`T HAPPY WITH THE WAY IT LOOKED ON PRELISDR CA100730010Bearing · wornTEETER BEARING FOUND WORN BEYOND LIMITS DURING INSP.SDR CA100707006Rotor Head · corroded(CAN) DURING A 300 HOUR INSPECTION, DIS-ASSEMBLY OF THE TAIL ROTOR , THE ENGINEER EXPERIENCED DIFFICULTY REMOVING THE TAIL ROTOR TO SHAFT ATTACHMENT BOLT. UPON REMOVAL OF THE BOLT AND INSPECTION OF THE T/R ASSY. THE ENGINEER DISCOVERED THAT THERE WAS CONSIDESDR CA100809003Bearing · defectiveDURING A FIRE MISSION, WITH THE BAMBI IN THE WATER GETTING FILLED ON A 100 FOOT LONG LINE, THE PILOT LOST AUTHORITY OF THE TAIL ROTOR CAUSING THE ACFT TO PERFORM 3 TO 4 TURNS CLOCKWISE. PILOT WAS ABLE TO GAIN CONTROL OF ACFT AND LAND SAFELY FOLLOWING PROCEDURSDR CA100521009Spindle · contaminatedWITH AUX HYDRAULICS OFF, RIGHT YAW PEDAL HANGS UP WHEN PUSHED FORWARD. TAIL ROTOR SYSTEM INSPECTED, DISCONNECTED T/R PITCH LINKS TO ROTATE SPINDLES. FELT ROUGHNESS/FLAT SPOTS WHILE ROTATING SPINDLES. THREE OF THE FIVE SPINDLES HAD ROUGHNESS IN THEM. SUSPESDR CA100429007Bushing · loose(CAN) DURING A ROUTINE INSPECTION, THE LEVER ARM WAS REMOVED FOR AN UNRELATED PURPOSE. WHEN THE ARM WAS REMOVED THE BUSHINGS WERE NOTED AS BEING LOOSE. NORMALLY BONDED IN, BOTH BUSHINGS WERE ABLE TO FREELY MOVE. A NEW LEVER ARM WILL BE INSTALLED.SDR CA091109001Nut · cracked(CAN) DURING REMOVAL OF T/R PITCH CHANGE CROSS HEAD NUT, THE NUT WAS FOUND TO BE CRACKED IN 2 OF THE RELIEF SLOTS. THE NUT WAS COMPLETELY SEPARATED AFTER REMOVAL. NUT WAS DISCARDED AND REPLACED WITH NEW.SDR 2009FA0000912Rotor Head · crackedDURING INSP OF THE TAIL ROTOR ASSY, A CRACK WAS FOUND BETWEEN THE BLADE RETENTION BOLT AND THE FACTORY BALANCE WEIGHT PLATES.SDR CA090901001Pitch Horn · cracked(CAN) ROUTINE INSP REVEALED APPARENT CRACK IN T/R PITCH CHANGE BEAM (HORN, ADJACENT TO BUSHING). BEAM SN IS A067-00042. AFTER REMOVAL OF PROTECTIVE PAINT COATING EXISTENCE OF CRACK WAS CONFIRMED BOTH VISUALLY AND BY LPI METHOD. CRACK EXTENDS FROM THE OD OF THESDR CA090703002Bearing · crackedDURING A SCHEDULED TAIL ROTOR GEARBOX CHANGE THE PITCH LINKS WERE INSPECTED. PITCH LINK WAS FOUND TO HAVE CRACKS IN THE INNER RACE OF THE INBD ELASTAMERIC BEARING. THE RUBBER PORTION OF THE BEARING APPEARED NORMAL. THE PART IS TO BE SENT TO MFG FOR O/H.SDR CA090608007Sleeve · dislodged(CAN) WHILE GREASING THE T/R GEARBOX PITCH CHANGE ASSEMBLY IT WAS NOTED THAT THE BOOT P/N 406-312-106-101 WAS BEING PRESSURIZED BY THE GREASING. REMOVED THE T/R GEARBOX PITCH CHANGE ASSEMBLY AS PER BELL MM. THE ASSEMBLY WAS DISASSEMBLED. IT WAS FOUND THAT THE SDR CA090323001Bushing · cracked(CAN) CRACKS FOUND IN BUSHING OF TAIL ROTOR PITCH LINKS, PN 350A33-2145-01 DURING ROUTINE INSPECTION.SDR 2009FA0000275Nut · looseDURING COURSE OF SCHEDULED INSP, NUT RETAINING THE TAIL ROTOR PITCH CHANGE CONTROL BEARING WAS FOUND TO BE LOOSE ALLOWING BEARING INNER RACE TO SPIN ON ITS SEAT. BEARING RETAINING NUT PN 222-012-717-001 IS PREVENTED FROM MOVING BY THE USE OF A LOCKRING PN 222-SDR CA090126006Bolt · brokenOPERATING A SCHWEIZER 269 C MODEL SERIAL NUMBER S1575 TSN 6449.5 THE CONICAL BRGS WERE REPLACE WITH NEW AT 6338.8 AND A NEW BOLT WAS INSTALLED AT THIS TIME P/N 269A6092-3 WHICH WAS PURCHASE NEW FROM SCHWEIZER ON. THE RETORQUE WAS CARRIED OUT AT 6416.1 TSN NO SDR CA090408013Rotor Head · damaged(CAN) RECENTLY WE HAVE HAD 2 LOWER SLIDER ASSEMBLIES THAT HAVE HAD THE UMBRELLA MOVING INDEPENDENTLY TO THE SLEEVE. IAW THE INSP CRITERIA OF TASK CARD 201 IN CHAPTER 065.71.06 THERE SHOULD NOT BE ANY PRESENCE OF THE UMBRELLA TURNING SEPARATELY TO THE SLEEVE. SDR CA081203006Spindle · unserviceable(CAN) S61 TAIL ROTOR SPINDLE FAILED INITIAL ETCH INSP IAW SB61B10-18J S/N`S K071-00394, K071-00392.SDR CA081203004Spindle · unserviceable(CAN) S61 TAIL ROTOR SPINDLE FAILED NITAL ETCH INSP IAW SB61B10-18J S/N`S K071-00144, K071-00132, K071-00137.SDR CA081113007Bushing · deformed(CAN) WASHER BETWEEN THE T/R PITCH HORN AND PITCH LINK FOUND DEFORMED.SDR AC2A2008093078342Rod End · brokenDURING TRANSITION FROM CLIMB TO CRUISE FLIGHT THE ACFT DEVELOPED A SEVERE VIBRATION. FOUND TAIL ROTOR DAMPER ROD END BROKEN. REPLACED TAIL ROTOR BLADE AND DAMPER.SDR 109RX5202008Nut · looseDURING PREFLIGHT INSPECTION, PILOT NOTED THE TAIL ROTOR BALANCE WHEEL HAD SLIGHT ROTATIONAL MOVEMENT. MAINTENANCE WAS DISPATCHED TO INSPECT THE TAIL ROTOR ATTACHMENT. TAIL ROTOR RETENTION NUT 109-0130-85-1 WAS LOOSE CAUSING SLIGHT WEAR TO THE TAIL ROTOR GEARSDR CA080507004Fork · binding(CAN) ACFT WAS UNDERGOING A TEST FLIGHT FOR RADAR ALTIMETER TROUBLESHOOTING. 5 MINUTES INTO CRUISE FLIGHT, A SUDDEN VIBRATION WAS INDUCED INTO AIRFRAME AND ALL FLIGHT CONTROLS. PILOT IMMEDIATELY RETURNED TO BASE FOR AN UNSCHEDULED LANDING WITHOUT INCIDENT. UPOSDR CA080813009Bellcrank · improper part(CAN) DURING T/R RIGGING CHECK, IT WAS NOTED THAT WHEN FULL LT PEDAL WAS APPLIED, THE COUNTERWEIGHT LINK TO COUNTER WEIGHT ARM HARDWARE WOULD CONTACT T/R CROSSHEAD ASSY. UPON INVESTIGATION THE WRONG P/N OF COUNTERWEIGHT BELLCRANK ASSY`S WERE INSTALLED FOR THE SDR 2008FA0000111Bearing · seizedTHE THRUST BEARINGS IN THE TAIL ROTOR BLADE GRIPS ARE OF MATCHED SETS. THESE SETS HAVE A SPECIFIC INSTALLATION ORIENTATION. ORIENTATION OF THESE BEARINGS ARE MARKED WITH A (V). THE (V) IS TO BE ORIENTED TOWARD THE CENTER OF THE TAIL ROTOR SPINDLE HUB. ON THESE
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