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 = 'AW139' 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 = 'AW139' 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 AC2R2016050901Rod End · scoredROD END HAS POSSIBLE CRACK. DISCOVERED WHILE PERFORMING BT139-450. ROD END WILL BE RETURNED TO MFG FOR FURTHER EVALUATION.SDR AC2R2016050401Skin · corrodedRT UPPER SKIN CORRODED BS 3120 - 6700.SDR AC2R2016040801Erosion Shield · brokenTAIL ROTOR BLADE LIGHTNING BONDING STRIP BROKE IN FLIGHT AND CONTACTED MAIN ROTOR BLADE. REPLACED LIGHTNING BONDING STRIP, TAIL ROTOR BLADE AND MAIN ROTOR BLADE.SDR ULXR2016051800001Contactor · burnedAFTER EXECUTING SEVERAL PRACTICE HOIST EVOLUTIONS, SMELLED A FAINT ODOR OF BURNING ELECTRICAL AND SIMULTANEOUSLY EXPERIENCED A 2 GEN FAIL WITH A BUS TIE FAIL IN THE CAS WINDOW. THE ACFT EXPERIENCED A K10 BUSS TIE CONTACTOR FAILURE. THIS CONTACTOR CONNECTS TSDR AC2R2018042003Bearing · lack of lubeREMOVE OIL COOLER FAN FOR DRY BEARING.SDR AC2R2016032901Fitting · galledWHILE PERFORMING THE MGB BOLT INSPECTION ON THE LT LOWER FITTING, WE REMOVED THE COTTER PIN AND REMOVED THE NUT FROM THE FWD BOLT. WE ENSURED THE BOLT SPUN FREELY BEFORE WE ATTEMPTED TO REMOVE THE BOLT, WHICH IT DID BY HAND. THE BOLT EASILY REMOVED UPWARD UNSDR ALGA20160307001Skin · debondedDURING INVESTIGATION FOLLOWING A HUMS RED TRDS INDICATION & A SHARP RISE NOTED ON TRDS FSA S001A7 AT CRUISE. DARF BR-WH-021 INSPECTIONS REVEALED DE-BONDED SKIN UNDER THE SUPPORT STRUCTURE FOR THE TRDS BEARING. CURRENTLY WAITING FOR A REPLY FROM ENGINEERING.SDR AC2R2016021801Seat · corrodedSEAT, PN: 3G2520V00131 HAS CORROSION WHERE SEAT BACK CUSHION, PN: 3G2520L00251 CONTACTS THE METAL WEBBING ATTACHED TO THE FRAME. AFTER FURTHER INVESTIGATION IT HAS BEEN FOUND THAT OTHER SEAT BACK CUSHIONS ARE MFG WITH A DIFFERENT MATERIAL THAT CONTACTS THE WESDR AC2R201602180001Plate · corrodedLEFT SPONSON AFT PLATE CORRODED. WHEN THE CORROSION WAS REMOVED, THE DEPTH EXCEEDED THE ALLOWABLE LIMIT. THE CORROSION APPEARS TO HAVE STARTED FROM PREVIOUSLY DRILLED HOLES WHICH WERE UNTREATED WITH A CORROSION PREVENTATIVE COMPOUND. THIS SHOULD HAVE BEEN ASDR CA160219008Hydraulic Line · chafed(CAN) A HYDRAULIC CHAFED RETURN LINE FOUND TO CONTACT AT BS 8150 ON THE BULKHEAD.SDR CA160209007Blade · mismanufactured(CAN) PN 4G6410A00133, THE BONDING STRIP IS IN FULL CONTACT WITH A DATA PLATE THERE IS NO SEALANT BETWEEN THE BONDING STRIP AND T/R BLADE THERE IS NO SEALANT AROUND THE CONNECTOR OR CONNECTOR ATTACHMENT SCREWS THERE IS A NON-STANDARD FILLISTER HEAD SCREW RETAISDR CA160209003Bearing · corroded(CAN) WHILE REMOVING THE ECS PULLEY TO CHANGE A OIL SEAL ON THE ECS PULLEY SHAFT THE ENGINEER NOTICED CORROSION ON THE BEARING. THE ECS PULLEY DRIVE SHAFT IS ALSO WORN SLIGHTLY UNDERSIZE.SDR CA160127001Sensor · intermittent(CAN) IN CRUISE. CAS WARNING MGB TEMP. MGB TEMPERATURE GAUGE OBSERVED TO BE FLASHING BETWEEN INVALID AND 130C. QRH FOLLOWED, LAND AS SOON AS POSSIBLE. COMMENCED APPROACH FOR LANDING IN FARM FIELD, INFORMED MEDICS. INDICATIONS SUDDENLY RETURNED TO NORMAL. AS THSDR CA160120017Filter · wrong part(CAN) THE AMP TASKS 39-A-29-11-01-02A-921A-A PRESSURE FILTER, NR 1 POWER CONTROL MODULE, REPLACEMENT, AMP 39-A-29-11-01-03A-921A-A RETURN FILTER, NR 1 POWER CONTROL MODULE, REPLACEMENT, AMP 39-A-29-12-01-02A-921A-A PRESSURE FILTER, NR 2 POWER CONTROL MODULE. ASDR HEER20160119122Blade · damagedAFTER LANDING POST FLIGHT INSPECTION REVEALED DAMAGE TO UNDERSIDE NEAR TIP OF WHITE MAIN ROTOR BLADE. FOUND YELLOW TAIL ROTOR BLADE EROSION SHIELD EXTENSION BROKE OFF AT ATTACHMENT LOCATION.SDR CA160122005Generator · failed(CAN) WHILE IN CRUISE, NR 1 WINDSHIELD HEAT SYS FAILED, FLIGHT CREW CYCLED THE IPS, ICE PROTECTION SYSTEM AND THE WINDSHIELD HEAT RESET. IN ANOTHER 5 MINUTES, THE FLIGHT CREW NOTICED AN ACRID BURNING ODOR. IPS SYS AND HEATERS WERE SWITCHED OFF, THE ODOR IMMESDR CA160119004Bearing · debonded(CAN) Y6-Y7 BELLCRANK BEARING FOUND DISBONDED.SDR CA160111011Bearing · debonded(CAN) WHILE DOING UNRELATED WORK AROUND THE AREA, IT HAS BEEN OBSERVED THAT THE BELLCRANK Y9-Y10 WAS MOVED ALL THE WAY DOWN. NORMALLY THEY ARE CENTERED WITHIN THE ATTACHMENT POINT. THE BEARING IN THE BELLCRANK WAS DISBONDED AND COULD MOVE FREELY.SDR CA151201008Engine · power loss(CAN) DURING AN OFFSHORE FLIGHT IN A HEAVY RAIN CONDITION PILOT HEARD FEW POPS ON ENGINE NR 2, ABOUT 3-4 SECONDS IN BETWEEN, PILOT BROUGHT THE ENGINE TO IDLE AND ENGINE WAS FINE AND ALL PARAMETERS ARE OK. PILOT TRIED TO INCREASE POWER AGAIN SAME SURGE REPEATEDSDR CA151119007Damper · broken(CAN) DURING CRUISE FLIGHT THE AIRCREW FELT AN ABNORMAL VIBRATION COME ON ALL OF A SUDDEN. THEY REDUCED AIRSPEED AND LOWERED LANDING GEAR. LANDED BACK AT BASE. UPON INSPECTION AFTER THE ACFT HAD SHUTDOWN, ON OF THE MAIN ROTOR DAMPERS WAS FOUND HANGING FROM 1SDR AC2R2018042004Oil Cooler · vibrationOIL COOLER FAN HIGH VIBRATION READINGS.SDR 2015FA0000505Window · missingFLYING AIRCRAFT, WHERE WE HAD DROPPED OFF OUR 2 PASSENGERS AND WERE RETURNING TO DEPARTURE WITHOUT PASSENGERS. OUR LOCATION WAS APPROXIMATELY 10-11 MILES TO THE EAST OF DESTINATION. THE TEMPERATURE WAS 5 DEGREES C, WE WERE AT 2500 FEET AND COUPLED FLYING AT SDR CA151022009Actuator · failed(CAN) MGB SUMP CHIP DETECTOR CAS OCCURRED, BURNER PUSHED. WHEN ACFT RETURNED TO BASE CHIP PLUGS PULLED. METAL CONTAMINATION FOUND. RIGHT FREEWHEEL ACTUATOR FOUND UNSERVICEABLE. REPLACED RT FREEWHEEL ACTUATOR WITH NEW AND SUBSEQUENT INSPECTIONS AND CHECKS IAWSDR CA150914004Bearing · debonded(CAN) Y9-Y10 BELLCRANK, BEARING FOUND DISBONDED FROM HOUSING DURING ROUTINE INSPECTION.SDR CA150908009Clamp · departed(CAN) MAIN ROTOR SWASHPLATE BOOT WAS REPLACED WITH A SPLIT BOOT IAW AMP 39-A-62-31-04-00A-720B-A SWASHPLATE BOOT, SPLITTED. INSTALL PROCEDURES. THE UPPER AND LOWER BOOT CLAMPS WERE RE-USED DURING THE INSTALLATION PROCESS. DURING A DAILY INSPECTION THE FOLLOSDR CA150825007Gearbox · making metal(CAN) TRANSMISSION SUMP CHIP LIGHT ON STARTUP. BURNED AND REPAIRED 3 TIMES. AC FERRIED BACK TO BASE. SCHEDULED FOR MGB REPLACEMENT.SDR CA150806001Connector · misinstalled(CAN) WHEN THE FIRE BOTTLE WAS REMOVED FOR REPLACEMENT, IT WAS FOUND THAT THE SHORTING SPRING WAS LEFT INSERTED IN THE CONNECTOR WHEN THE BOTTLE WAS INSTALLED. THIS SPRING COULD HAVE PREVENTED THE PROPER FIRING OF THE BOTTLE HAD THE NEED AROSE FOR IT. INSPECTSDR CA150508008Lever · malfunctioned(CAN) DURING PRE-FLIGHT CHECKS BY THE FLIGHT CREW, THE ENGINE POWER LEVERS WERE BEING "BEEPED" THROUGH TO CHECK THEIR RANGE. WHILE PERFORMING THIS CHECK, THE NR 2 ENGINE CONTROL MOVED FREELY AS NORMAL AND THE NR 1 ENGINE FAILED TO MOVE. PRESSURE WAS APPLIED SDR CA150506016Generator · damaged(CAN) DURING REMOVAL OF M/R, NR 2 ACFT GEN WAS REMOVED AND DISCOVERED THAT THE NUT THAT HOLDS THE SPLINED DRIVE SHAFT HAD COME OFF AND FELL INTO THE COMPONENT IMPELLER CAUSING SUBSTANTIAL DAMAGE TO THE IMPELLER ITSELF, THE INTAKE COVER AND TO THE INTERNALS OF SDR CA150505004Windscreen · cracked(CAN) RIGHT WINDSCREEN CRACKED ON LANDING.SDR CA150429009Gearbox · making metal(CAN) MAIN ROTOR GEARBOX SUMP CHIP CAS ILLUMINATED POST START-UP. WOULD NOT BURN.SDR CA150507003Blade · missing(CAN) CUSTOMER REPORTED VIBRATION AT 40 PERCENT NG, BOTH AT START AND SHUTDOWN. DURING INSPECTION, CUSTOMER FOUND PT BLADE MISSING.SDR 2015FA0000089Window · detachedTHE INCIDENT OCCURRED WHILE THE FLIGHT CREW, PILOT AND MAINTENANCE TECH, WAS ATTEMPTING TO RECORD THE
ENGINE PARAMETERS AND VIBRATION LEVEL WHILE AT AT VNE OR VH. PIC WAS FLYING THE AIRCRAFT "ATTENTIVELY" AND UTILIZING THE "AS " MODE TO ACCELERATE THE HELICOPSDR CA150218004Generator · failed(CAN) NR 1 DC GENERATOR FUNCTION CHECK FAILED DURING ENGINE RUNS. DC GENERATOR REPLACED. FURTHER ON, AN INSPECTION WAS C/O ON THE FAILED DC GENERATOR AND FOUND A SCREW HOLDING ONE OF THE TERMINAL CABLES CHAFED. THE INSULATION MATERIAL BENEATH THE PROTECTINGSDR CA150224009Engine · making metal(CAN) RT ENGINE CHIP DETECTOR INDICATION ILLUMINATED IN FLIGHT. ACFT RETURNED TO BASE AND LANDED UNEVENTFULLY. THE CREW RETARDED NR 2 ENGINE TO GROUND IDLE, BUT DID NOT SHUTDOWN THE ENGINE. OEI OPERATION WAS APPROXIMATELY 25 MINUTES. CHIP DETECTOR REMOVED &SDR CA150217010Warning Light · illuminated(CAN) NUMBER 2 ENGINE CHIP CAS MESSAGE ILLUMINATED IN FLIGHT & STAYED ON.SDR CA150113005Warning Message · illuminatedTHE PILOTS HAD STARTED BOTH ENGINES AND SELECTED 102 PERCENT PRIOR TO TAKEOFF. AT THIS TIME THE "1 EEC FAIL" CAS MESSAGE ANNUNCIATED. THERE WERE NO OTHER INDICATIONS OF A PROBLEM AND THE CREW ADVISES ALL ENGINE INDICATIONS APPEARED NORMAL, N2 INDICATED 102 PSDR CA150113001Engine · making metal(CAN) THE PILOT REPORTED THE NR 2 ENGINE FLAME OUT WITH STRONG NOISE. DURING TROUBLESHOOTING THE MAINTENANCE PERFORMED THE ENGINE VISUAL INSPECTION AT THE POWER TURBINE AND FOUND METAL PARTICLES INSIDE EXHAUST AREA. MAINTENANCE ATTEMPTED TO ROTATE THE PROPELLESDR GQRR2014FA0000706Heat Shield · chafedHEAT SHIELD CHAFED THROUGH.SDR ALGA201411118503Panel · corrodedLEFT BELLY PANEL HAD CORROSION THAT WAS BEYOND LIMITS IAW SRM. SENT ITEM OUT FOR REPAIR.SDR CA141031003Door · stuck(CAN) LT CABIN SLIDING DOOR STUCK IN THE CLOSED POSITION. WILL NOT OPEN.SDR CA141008016Gearbox · making metal(CAN) MGB CHIP SUMP CAS MESSAGE FOUND PRIOR TO ENGINE START.SDR CA141010006Warning Message · illuminated(CAN) SHORTLY BEFORE LANDING, THE PILOT NOTICED A DC NR 1 GENERATOR FAILED FOR A MOMENT. IT CAME BACK ONLINE AGAIN AND FOLLOWED BY AN OEI SITUATION ON ENGINE NR 1 SHORTLY BEFORE REACHING THE LANDING POINT. CHECKLIST ACTIONS PERFORMED, PILOT DECIDED TO PROCEEDSDR CA141008003Indicator · malfunctioned(CAN) DURING LAST OPERATIONS BEFORE LANDING THE PILOT REPORTED THAT NR 1 ENGINE TORQUE INDICATION WAS DECREASING WHILE NR 2 ENGINE TORQUE WAS INCREASING. ITT THEN SUDDENLY DASHED OUT. THE PILOT ELECTED TO ABORT LANDING AND RETURNED TO POINT OF ORIGIN. ITT CSDR CA140910009Module · malfunctioned(CAN) WHILE IN COUPLED CRUISE FLIGHT, THE NR 2 ENGINE SURGED HIGH TWICE IN ABOUT A MINUTE. THE FIRST TIME UP TO 102 PERCENT.SDR CA141006007Pump · failed(CAN) THE PILOT REPORTED N1 AND TORQUE ISSUE IN FLIGHT. DURING GROUND RUN TROUBLESHOOTING, THE ENGINE WOULD NOT ACCELERATE ABOVE 80 PERCENT N1 IN AUTO OR MANUAL MODES. METAL WAS DISCOVERED AND IT IS BELIEVE THE SOURCE IS THE HP FUEL PUMP. FMM/FCOC/ECOLOGY ACSDR ALGA2014080833253Warning System · false activationON TAKEOFF AT 40KTS NR 2 ENG FIRE LIGHT & AUDIO CAME ON. CONTINUED CRITICAL PHASE OF FLIGHT, TAKE OFF. BY VY 75KTS ENG FIRE LIGHT & AUDIO HAD GONE OUT. ACFT RETURNED WITHOUT FURTHER INCIDENT OR INDICATION.SDR CA140801003Gearbox · making metal(CAN) CAS MESSAGE DISPLAYED DURING CRUISE. MAIN GEARBOX MAGNETIC CHIP DETECTOR ILLUMINATED. ACFT LANDED SAFELY AT THE HOSPITAL HELIPAD. MAGNETIC PARTICLES FOUND ON THE CHIP DETECTOR AND THE OIL FILTER. ACFT DECLARED UNSERVICEABLE. PENDING ARRANGEMENTS FORSDR CA140804011Seal · leaking(CAN) A FUEL LEAKAGE WAS FOUND FROM FMM SEAL DRAIN. SINCE THE FUEL LEAKAGE FROM SEAL DRAIN REACHED TO 50CC/HOUR, THEY DECIDED TO REPLACE THE UNIT. THE UNIT WILL BE REPLACED WITH A SERVICEABLE ONE AND THE REMOVED UNIT WILL BE SENT TO A SHOP FOR REPAIR/INVESTIGSDR CA140723001Pedal · stiff(CAN) TAIL ROTOR CONTROL PEDALS STIFF IN FLIGHT, ABNORMAL FORCE REQUIRED.
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