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 = '204B' 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 = '204B' 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 QMLA2022081920055None · noneSUPPLEMENTAL INFO FOR SDR QMLA2022081920055 AC WAS EXPERIENCING UN-COMMANDED "ROLL" INPUTS WITH AP1 SHOWING "DEGRADED" AND AP2 NORMAL OPERATION. THE FLIGHT SYSTEMS PAGE SHOWED ROLL COMMAND INPUTS-UP SLIGHTLY AND THEN DOWN SLIGHTLY THAT CORRESPONDED WITH CYCLICSDR EVCA033022None · crackedTHERE IS A SMALL CRACK, (1/4 INCH LONG), FORWARD LH SIDE THAT WE WILL STOP DRILL.SDR CA190806009Bolt · broken(CAN) DURING CRUISE FLIGHT THE PILOT HEARD "WHAT SOUNDED LIKE A SMALL BANG, A SOUND THAT IN THE PAST I HAD BEEN A METAL DRINK BOTTLE OR CELLPHONE DROPPING ONTO THE FLOOR." THE PILOT REDUCED POWER/AIRSPEED AND CHECKED THE GAUGES - NO VIBRATIONS OR ABNORMALITIESSDR CA190705001Fitting · cracked(CAN) DURING A SCHEDULED INSPECTION OF TAILBOOM ATTACHMENT FITTINGS THE UPPER L/H FITTING WAS SUSPECTED TO BE CRACKED. THE TAILBOOM AND COWLS WERE REMOVED FOR CLOSER INSPECTION. UPON CLOSER INSPECTION THE FITTING WAS FOUND TO BE CRACKED. TAILBOOM WAS REMOVED, SDR CA150601014Valve · broken(CAN) DURING FLIGHT TRAINING, TWO PILOTS WERE FLYING FOR A PPC. THE ACFT WAS JUST COMING OUT OF A TURN WHEN THE FLIGHT INSTRUCTOR SWITCHED THE HYDRAULICS OFF, AT THIS POINT THE CYCLIC IMMEDIATELY WENT HARD LT WITH BOTH PILOTS BEING UNABLE TO RESIST THE MOVEMENSDR CA150204016Pin · cracked(CAN) DURING A ROUTINE INSPECTION OF THE HEAD REST. THE ENGINEER NOTED THAT THE T HANDLE PORTION ON ON QUICK RELEASE PIN, PIP PIN, PN NAS1333A2S07D WAS CRACKED & THE HANDLE IS FREE TO MOVE APPROX 1MM ALONG THE AXIS OF THE PIN. THIS ASSEMBLY IS SUBJECT TO AD SDR CA140708005Doubler · cracked(CAN) CRACK WAS DISCOVERED DURING DAILY INSPECTION. THE CRACK WAS LOCATED IN THE TAIL BOOM DOUBLER BELOW THE 42" GEAR BOX WHERE IT IS NOTCHED TO ACCOMMODATE THE VERTICAL FIN SPAR. IT WAS APPROXIMATELY 1" IN LENGTH.SDR CA130912007Switch · failed(CAN) THE PILOT MADE A RADIO CALL AND THE SWITCH FAILED IN THE CLOSED, TRANSMIT, POSITION CAUSING THE VHF COM RADIO TO CONTINUOUSLY TRANSMIT. TURNED THE RADIO OFF AND RETURNED TO THE COMPANY BASE.SDR CA130820004Bolt · sheared(CAN) DURING CRUISE FLIGHT, THE ACFT DEVELOPED A SUDDEN AND SEVERE VIBRATION. THE PILOT IMMEDIATELY LANDED AND SHUTDOWN. INSPECTION OF THE ACFT SHOWED THE INBD BOLT SECURING TAIL ROTOR PITCH LINK TO THE TAIL ROTOR GRIP HAD SHEARED AND THE TAIL ROTOR BLADES HSDR CA130326007Nut · damaged(CAN) DURING SCHEDULED MAINTENANCE OF TAIL ROTOR DRIVESHAFT, NEW BOLTS AND NUTS BEING INSTALLED, A NEW NUT WAS FOUND TO HAVE NO SELF LOCKING ABILITY ON ANY BOLT NEW OR OLD. SUSPECT MFG DEFECT.SDR CA130212025Fuel Cell · leaking(CAN) FUEL CELL FOUND WEEPING FROM MULTIPLE LOCATIONS IN THE MIDDLE OF THE SIDES. ACFT FUEL RT FUEL CELL HAD A SLOW LEAK SO THE CELL WAS REMOVED AND INSPECTED. USING AIR THERE WAS NO APPARENT LEAK, BUT WHEN FILLED WITH WATER, THE SIDES OF THE CELL ARE FOUND TSDR CA130212027Gasket · blown(CAN) WHILE IN CRUISE FLIGHT THE PILOT GOT AN INDICATION OF NO TRANSMISSION OIL PRESSURE ON THE WARNING LIGHT AND PRESSURE GAUGE. HE PROCEEDED TO LAND. WHEN HE ROLLED THE THROTTLE TO IDLE THE BLADE SLOWED QUICKER THEN NORMAL HE THEN SHUT THE ENGINE DOWN AND SDR CA110727004Bearing · failedUPON ROUTINE INSP OF MAIN ROTOR TRANSMISSION ASSY INTERNAL WAFER FILTER, THE ON SITE AME DISCOVERED AN UNUSUALLY LARGE QUANTITY OF FERROUS METAL. FURTHER INVESTIGATION REVEALED METAL FOUND ON THE CHIP DETECTOR AND SUMP SCREEN OF THE TRANSMISSION. THE ACFT WASDR CA110516030Panel · delaminatedDURING A VISUAL INSPECTION OF THE ACFT THE ENGINE DECK WAS FOUND TO BE DELAMINATED AND THE HONEYCOMB WAS FOUND TO BE SOFT IN THE ENTIRE PANEL. PANEL WAS REMOVED AND OVERHAULED.SDR CA110516029Panel · delaminatedDURING A VISUAL INSPECTION OF THE ABOVE NOTED ACFT THE CENTER ROOF SECTION WAS FOUND SEVERLY DELAMINATED. THE ROOF PANEL WAS REMOVED AND THE AREA FUTHER INSPECTED FOR DEFECTS. NONE NOTED.SDR CA110204009Volt Regulator · failedDURING CRUISE FLIGHT THE PILOT NOTICED THE AMMETER FLUCTUATE AND THE GENERATOR LIGHT FLICKER. THE PILOT BEGAN TO DESCEND WHEN THE GENERATOR LIGHT, LT BOOST PUMP LIGHT AND ROTOR RPM AUDIO ALL CAME ON AND THE COCKPIT BEGAN TO FILL WITH SMOKE. ALL UNNECESSARY SWISDR CA100607005Bearing · roughNEW BEARING (PN P9103PPFS381A) PURCHASED FROM MFG, FOUND UNSERVICABLE, DUE TO LACK OF LUBRICATION AND ROUGH OPERATION. PART SCRAPPED AND WARRANTY RECEIVED FROM MFG. NOTE: THIS BEARING IS PART OF A BLOWER ASSY.
SDR 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 CA100809002Balance Weight · separatedACFT WAS IN CRUISE FLIGHT WHEN THE TRANSMISSION OIL PRESSURE WARNING LIGHT ILLUMINATED. PILOT CARRIED OUT AN UNSCHEDULED LANDING. AT THE TIME OF ENG SHUTDOWN, THE TRANSMISSION WAS SHOWING OVER 20 PSI. THE ENGINEER ONBOARD INSPECTED THE OIL COOLER BLOWER COMSDR CA090512011Bulkhead · cracked(CAN) DURING A VISUAL INSP, A CRACK WAS FOUND AT THE BOTTOM OF THE RT ANGLE AT TAILBOOM TO FUSELAGE JUNCTION (PN 204-030-713-101). AFTER REMOVAL OF THE TAILBOOM AND SHIM PADS THE TAILBOOM ATTACHMENT BULKHEAD WAS FOUND CRACKED AT 3 OF THE 4 ATTACHMENT POINTS. (SDR CA081208003Cap · worn(CAN) PART FOUND TO HAVE UNAPPROVED MODIFICATION EMBODIED AFTER PART REMOVAL FROM THE AIRCRAFT WHEN COMPARED TO OEM PART. SUBSEQUENT INVESTIGATION BY QAM MANAGER OF ARCHIVED FILES REVEALED THAT 4 CAP ASSEMBLIES HAD UNDERGONE A PREVIOUS MODIFICATION BY A PROCESDR CA081017008Longeron · cracked(CAN) DURING A VISUAL INSPECTION OF THE ACFT THE AME NOTICED A CRACK IN THE UPPER LT TAILBOOM LONGERON APROX. 3 INCHES AFT OF THE TAILBOOM ATTACHMENT FITTING. ACFT GROUNDED FOR REPAIRS.SDR CA071010005Blade · cracked(CAN) ON TUESDAY THE 28TH OF AUGUST 2007, AT APPROX 19:00, LANDED AT THE STAGING AREA. THE PILOT COMMENTED THAT THERE WAS A VIOLENT LATERAL VIBRATION. AT THIS TIME THE TRANSMISSION WAS OBSERVED SHAKING EXCESSIVELY AND IT WAS DECIDED TO SHUT THE AIRCRAFT DOWN WSDR CA070828004Bearing · worn(CAN) PILOT WAS FLYING HELICOPTER AND FELT TWO SLIGHT YAWS TO THE RT APPROXIMATELY 30 TO 40 SECONDS APART. AT FIRST THE PILOT SUSPECTED IT MIGHT HAVE BEEN A GUST OF WIND, BUT THE SECOND YAW ALERTED THE PILOT TO A PROBLEM WITH THE TAIL ROTOR AS IT WAS ACCOMPANISDR CA070506001Nut · damaged(CAN) ON APRIL 23, 2007 DURING A TEST FLIGHT FOR MAINTENANCE THAT WAS PERFORMED, THE PILOT EXPERIENCED AN UNCONTROLLED YAW TO THE RIGHT WHILE IN A 4 FOOT HOVER. THE HELICOPTER WAS IMMEDIATELY SET DOWN ON THE TARMAC. THERE APPEARED TO BE A STEP WORN IN THE INSDR CA070122011Collective Stick · ratcheting(CAN) PILOT COMPLAINED OF RATCHETING FEEL TO COLLECTIVE CONTROL STICK. AIRCRAFT RETURNED TO BASE. INSPECTION REVEALED THAT THE COLLECTIVE FRICTION SURFACE ROLL PIN WAS WORKING INTERNALLY AND CAUSING THE RATCHETING FEEL. ELBOW WAS REPLACED. (TC NR 2007012201SDR CA060818004Bolt · loose(CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTED A LARGE AMOUNT OF PLAY IN THE CLEVIS OF THE TAIL ROTOR FLIGHT CONTROL ROD. INVESTIGATION REVEALED AN UNDERSIZED BOLT , IE SMALLER DIAMETER, WAS INSTALLED. THE CORREECT BOLT, P/N AN175-20 WAS INSTALLED ANSDR CA060605010Transmission · making metal(CAN) METAL PARTICLES FOUND IN TRANSMISSION INTERNAL FILTER AFTER ROUTINE INSPECTION. NO CHIP LIGHT INDICATION. OIL DRAINED WITH NEW FILTER INSTALLED, AIRCRAFT RUN FOR ONE HOUR ON GROUND WITH METAL PARTICLES FOUND IN INTERNAL AND INLINE FILTER ASSY. NO CHIP SDR CA050715002Turnbuckle · unsecureLOCKWIRE LEFT UNLOCKWIRED RESULTING IN TURNBARREL BECOMING UNDONE RESULTING IN TAILROTOR PITCH CHANGE FAILURE. SPEED RIGS WERE LOCK WIRED ON THE ONE END BUT THE ENGINEER DIDN'T RECOGNIZE THE OTHER END REQUIRED LOCKWIRE.SDR CA050418007Relay · defectiveON SHUTDOWN ENGINE CONTINUED TO MOTOR OVER SLOWLY. CONTACTS STUCK. RCR REPLACED AND PROBLEM SOLVED.SDR CA050418008Nut · crackedUPON INSP NOTICED CRACKED JAN NUT ON LINEAR ACTUATOR.SDR CA050418006Housing · worn(CAN) DURING INSPECTION THE TAIL ROTOR CONTROL WAS REMOVED AND INSPECTED FOR WEAR. WEAR WAS FOUND BEYOND LIMITS IN THE HOUSING. THIS ITEM IS A 1000 HOUR OVERHAUL INTERVAL.SDR CA050427008Blade · damagedVOID, CHORDWISE STATION 155 TO 157, HALF INCH WIDE THREE INCHES LONG. BELL HELICOPTER VERDICT THAT BLADE STILL SERVICEABLE. BHT ALLOWS VOID IN THIS AREA. 6 INCHES SPANWISE BY THE FULL CHORDWISE WIDTH OF CORE. BLADE RETURNED TO SERVICE. WILL CONTINUE TO MOSDR CA040901005Volt Regulator · failed(CAN) VOLTAGE REGULATOR DELIVERING OVER 30 VOLTS. THE AIRCRAFT WAS READY TO TAKE OFF WHEN THE PILOT SMELLED A STRONG ODOR IN THE COCKPIT. ASSUMING IT WAS THE BATTERY, HE SHUT DOWN THE ENGINE. IN THE INSPECTION THE BATTERY WAS FOUND TOO HOT AND THE VOLTAGE DELISDR CA040901003Blade · cracked(CAN) MAIN ROTOR BLADE FOUND CRACKED ON THE TOP SURFACE 90 INCHES FROM THE TIP. ABOUT 70 HOURS BEFORE, A CRACK ON THE BLADE PAINT WAS FOUND, AT THAT TIME NO CRACK WAS FOUND IN THE BLADE SKIN. IAW ASB204-49-96 PT I AND II, THE BLADE WAS INSPECTED DAILY (PART ISDR CA040209012Shaft · worn(CAN) FUEL CONTROL RECEIVED FROM CUSTOMER FOR INSPECTION FOLLOWING PREVIOUS RECORDS ABOUT PUMP FAILURE (WSDR 20040128006). FUEL CONTROL HAS TSO- 3195.3 AND WAS OPERATING ON EXTENSION TIME DUE TO A GOOD PERFORMANCES. IT WAS REMOVED FROM A/C FOR INSPECTION IAW SDR CA040203011Shaft · worn(CAN) UPON SUSPECTING A PROBLEM WITH FUEL CONTROL UNIT. REMOVED FCU FROM THE ENGINE TO INSPECT THE SPLINES IAW MFG SBT5313-107. FOUND THE INTERNAL SPLINES KNIFE EDGED AND VERY CLOSE TO TOTAL FAILURE OF THE FCU. THIS WOULD HAVE LEAD TO THE FAILURE AND SHUTDOWN SDR CA030923010Yoke · cracked(CAN) TAIL ROTOR HUB ASSY WAS SENT FOR OVERHAUL. YOKE WAS SENT FOR NDT AS PART OF O/H AND WAS FOUND TO BE CRACKED.SDR CA040301002Compressor · failed(CAN) THE AIRCRAFT DEPARTED A STAGING AREA, SHORTLY AFTER TAKEOFF, THE AIRCRAFT HAD AN ENGINE FAILURE AND CRASHED IN TALL TREES. THE PILOT WAS THE ONLY OCCUPANT AND WAS KILLED ON IMPACT. THE ENGINE WAS RECEIVED FROM OVERHAUL AND INSTALLED 18 HOURS PRIOR TO THESDR CA030610011Spar · cracked(CAN) ENGINEER OPENED TAIL ROTOR DRIVESHAFT COVER TO CHANGE COUPLINGS AND FOUND A CRACK HAD DEVELOPED IN THE VERTICAL FIN SPAR. STARTING AT THE TOP LIGHTENING HOLE AND GOING LT TO THE OUTER EDGE OF THE SPARE. OUTER LT SKIN WAS ALSO CRACKED APPROX. SIX INCHES. SDR CA030317016Nut · cracked(CAN) ON VISUAL INSPECTION NUT WAS FOUND TO BE CRACKED AT WORM GEAR THREAD. THESE PARTS HAVE A 1000 HR NDT INSPECTION. THIS COMPANY INCLUDE A 300 HR VISUAL THIS WAS FOUND DURING THE VISUAL.SDR CA030421005Longeron · cracked(CAN) MODIFICATION OF THE DOOR ASSEMBLY WAS COMPLETED PRIOR IAW BHT. TB204-79-11. THE CRACKED PIECES WERE REPLACED WITH NEW PIECES AND REINSTALLED IAW TB 204-79-11.SDR CA030421004Longeron · cracked(CAN) UPPER LT ATTACH LONGERON CRACKED AFT OF HOT BONDED DOUBLER. CRACK APPEARS TO HAVE STARTED AT A RIVET HOLE. THE CRACK WAS DISCOVERED DURING A ENGINE REMOVAL WHERE THE AFT ENGINE COWL WAS REMOVED EXPOSING THE LONGERON. THE CRACK MEASURES APPROX 3 INCHES SDR CA021105012Bellcrank · cracked(CAN) AT 1000 HR INSPECTION BELLCRANK FOR THE CYCLIC WAS REMOVED FOT GREASING OF THE BEARINGS. BELLCRANK WAS FOUND TO BE CRACKED AT ONE BEARING. CRACK WAS COMPLETELY THROUGH TO THE OUTER RACE OF THE BEARING. BELLCRANK WAS REPLACED WITH A SERVICEABLE ONE.ALL OTSDR CA021003007Hose · leaking(CAN) HOSE ASSEMBLY FAILED RESULTING IN LOSS OF HYDRAULIC FLUID. THE LOSS OF FLUID RESULTED IN LOSS OF HYDRAULIC BOOST TO FLIGHT CONTROLS. AIRCRAFT WAS LANDED UNEVENTFULLY WITHOUT HYDRAULIC BOOST. THE HYDRAULIC LINE EXHIBITED NO SIGNS OF LEAKAGE PRIOR TO FAILUSDR CA020918006Bulkhead · cracked(CAN) THE ROTOR CONTROL BELLCRANK BULKEAD CRACKED IN MULTIPLE PLACES.SDR CA020918010Bulkhead · cracked(CAN) T/R FLIGHT CONTROL BELLCRANK SUPPORT ATTACHES TO BULKHEAD. THE BULKHEAD IS REINFORCED BY LOWER ANGLE AND UPPER ANGLE, SUSPECT THAT THE LOWER ANGLE CRACKED PROBABLY DUE TO CORROSION (NOT VERIFIED). THIS ALLOWED THE SUPPORT TO MOVE AND EVENTUALLY CRACKEDSDR CA011109007Segment · missing(CAN) UPON INSTALLATION OF THE NEW CHAIN, THE ENGINEER NOTICED A SPACE BETWEEN SOME CHAIN LINKS. CHAIN IS MISSING A SEGMENT.SDR CA010625047Skin · cracked(CAN) CRACK IN SKIN DUE TO BROKEN STIFFENER INSIDE FIN. APPROX LOCATION IS FSTA 444.75, WATERINE 85 RIGHT BUTTLINE 3.0. STIFFENER P/N 205-030-899-036 ALSO RIB P/N 204-030-827-015 WAS DAMAGED BY BROKEN STIFFENER.SDR CA000906003Servo · failed(CAN) THE PILOT FELT A FEEDBACK IN THE CYCLIC STICK IN THE FORWARD RIGHT HAND QUADRANT. THIS FEEDBACK WAS NOT SATISFACTORY TO THE AIRCRAFT TYPE. THE RIGHT HAND SERVO WAS REMOVED AND EXCHANGED WITH THE LEFT HAND CYCLIC SERVO. THE SUSPECT SERVO NOW IN THE LEF
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