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 = '412' 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 = '412' 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 CA190715012Wire · missing(CAN) DURING FLIGHT TEST. CHSP CASS MESSAGE APPEARED IN FLIGHT. TROUBLESHOOT FOUND 1 WIRE MISSING (BUT NOT RELATED) (TC# 20190715012)SDR QMLA2019040279034Panel · delaminatedR/H TAILBOOM PANEL P/N 205 032 811 077 OUTER SKIN DELAMINATED APPROX. 24” X 3.5” BETWEEN BOOM STATIONS 77-101 WL 72.L/H TAILBOOM PANEL P/N H205 032 813 67 OUTER SKIN DELAMINATED APPROX. 15” X 2.75” BETWEEN BOOM STATIONS 73-88. ALSO PANEL HAS CORROSION ALONG TSDR 9EKA20160714008Pan · crackedAIRCRAFT RETURNED FROM AN MOC FLIGHT FOLLOWING A 300 HOUR / 12 MONTH INSPECTION AND UPON SHUTDOWN, THE PILOT NOTICED THAT THE UPPER PLANETARY GEAR OF THE MAIN TRANSMISSION CHIP LIGHT HAD ILLUMINATED. DURING TROUBLESHOOTING IT WAS FOUND THAT THE DEBRIS COLLECTSDR QMLA2016032216027Skin · crackedAT SHIFT CHANGE, DURING PRE-FLIGHT OF ACFT NOTED A CRACK IN SKIN ON RT SIDE OF VERTICAL FIN IN THE SHAPE OF A BACKWARD C OF ABOUT 5 INCHES, AFTER MEASUREMENT POSSIBLY THROUGH 2 RIVET LOCATIONS.SDR CA151110008Filter · failed(CAN) DURING A ROUTINE 100 HR P3 FILTER INSPECTION THE ENGINEER REMOVED THE P3 FILTER FROM THE POWER SECTION AND NOTICED THE SCREEN MATERIAL HAD SEPARATED FROM THE BASE OF THE FILTER. THE FILTER HAD BEEN O/H 60.3 HRS PREVIOUSLY ON PO 535474, JUNE 2015. THE FISDR 2015FA0000442Electrical Box · failedMFG WAS CONTACTED AND ADVISED THAT A HOIST, PN 42325-12-3, EXPERIENCED AN UNCOMMANDED REEL OUT DURING A LIVE LOAD LIFTING OPERATION. EVALUATED THE SYSTEM AND DETERMINED THAT THE FAILURE WOULD BE IN THE JUNCTION BOX, PN 42325-707. UPON ARRIVAL AT THE ACFT, TSDR CA150826001Screw · short(CAN) MAIN GEARBOX, PN 412-040-002-103, NOTE THAT SECTION 8 OF THIS FORM WOULD NOT ACCEPT THE MFG INFO AND THEREFORE WOULD NOT SAVE. LOW OIL INDCATION OBSERVED IN FLIGHT, PILOT MADE EMERGENCY LANDING. UPON INSPECTION OF THE ACFT IT WAS DETERMINED THAT THE MAISDR CA150813004Boot · disintegrated(CAN) ACFT HAD A HARD LANDING AFTER A MAIN DRIVESHAFT COUPLING FAILURE. DURING THE INVESTIGATION IT WAS NOTED THERE WAS A HIGH POSSIBILITY OF A DRIVE SHAFT BOOT FAILURE WHICH LEAD TO THE DRIVESHAFT COUPLING, TRANSMISSION END, FAILURE DUE TO AN OVERHEAT. THESDR CA150325021Packing · leaking(CAN) DURING A ROUTINE PASSENGER FLIGHT, AT FULL THROTTLE, AN OIL PRESSURE CAUTION WARNING CAME ON FOLLOWED BY AN ITT SURGE ABOVE 900 DEG C. CREW ELECTED TO SHUTDOWN THE ENGINE. OIL SPILL ON GROUND NOTICED AFTER SHUTDOWN. MAINTENANCE CREW DETERMINED THE CAUSDR 2015FA0000004Barrel Nut · cracked1 OF 4 BARREL NUTS THAT ATTACH THE TAILBOOM TO THE AIRFRAME WAS FOUND TO BE CRACKED ACROSS THE THREADS ON 2 SIDES. THE NUT HAD BEEN REMOVED AS PART OF A MAJOR INSPECTION.SDR CA141024027Drive Shaft · cracked(CAN) FUEL PUMP, PN 025277-300, SN PE5971 WAS REMOVED FOR 300 HR INSPECTION IAW MM TABLE 601. UPON INSPECTION, THE MAINTENANCE TECH NOTICED THAT THERE WAS A CRACK BELOW THE GEAR TEETH, ON THE SHAFT. PUMP WAS REMOVED FROM SERVICE AT 3347.8 TSO.SDR CA140710003Torque Tube · sheared(CAN) DURING A NORMAL APPROACH OF 75% TORQUE THE PILOT NOTICED THE MAST TORQUE INCREASE TO OVER 110% WHILE THE ENGINE TORQUES REMAINED UNCHANGED. HE LANDED IN A FIELD 10 MILES SOUTH AND CALLED IN THAT HE HAD AN OVERTORQUE. THE MONO POLE SENSOR, SIGNAL CONDITIOSDR CA140305006Bearing · failed(CAN) ON A COMBINING GEAR BOX REMOVAL, AME NOTICED A LARGE AMOUNT OF BLACK FRETTING MATERIAL BETWEEN THE C BOX AND BLOWER JOINT FLANGE. ONCE CLEANED UP THE AME WAS ABLE TO SEE THAT THE OUTER RACE OF THE BEARING ON THE BLOWER WAS ROTATING IN THE BLOWER CASTINGSDR CA140224024Bearing · failed(CAN) ON C BOX REMOVAL THE OIL COOLER BLOWER ON NR 2 SIDE HAD BOTH FWD AND REAR BEARINGS BEGINNING TO FAIL. GREASE HAD BEEN EJECTED FROM FWD BEARING ALONG WITH A BURNED ODOR. SHOP TECH: BEARING FAILED IN SERVICE. NO INDICATION OF CAUSE. IT APPEARS THE FAISDR CA131118007Blade · fractured(CAN) DURING POSITIONING PHASE JUST BEFORE LANDING, A SUDDEN DROP IN NR 1 ENGINE TORQUE OCCURRED. THE ACFT LANDED ON THE TAXI WAY. ENGINE PARAMETERS AFTER LANDING WERE NORMAL, HOWEVER WHEN THE ACFT WAS ABOUT TO LIFT OFF AGAIN, THE ROTOR RPM WARNING CAME ON ASDR CA131004007Bolt · sheared(CAN) 25HR AIR CONDITIONING INSPECTION C/O, LT CONDENSOR BLOWER MOTOR ATTACHMENT BOLT, 1 OF 3, WAS FOUND SHEARED AT MOTOR CASE. THIS IS THE THIRD OCCURRENCE OF THE ATTACHMENT BOLT FAILURE IN THE FLEET. ALL 3 BOLTS REPLACED WITH NEW.SDR CA131007008Fuel Heater · leaking(CAN) SIGNIFICANT FUEL LEAK NOTED ON NR 1 ENGINE DURING GROUND OPERATIONS. LEAK CONFIRMED AS CRACKED WELD ON OIL TO FUEL HEATER.SDR QMLA2013082213122Warning Light · false activationNR 1 ENGINE MASTER CAUTION LIGHT ILLUMINATED REPEATEDLY IN FLIGHT. NR 1 ENGINE GAUGE SHOWED OIL PRESSURE BOTTOM GREEN/TOP YELLOW AND THE TEMP SHOWED TOP OF GREEN/BOTTOM OF YELLOW. MX PERSONNEL WERE UNABLE TO DUPLICATE THE MALFUNCTION OR DETERMINE WHAT MIGHT SDR CA130726004Blade · debonded(CAN) WHILE CARRYING OUT A 25 HOUR INSPECTION, PERFORMED A TAP TEST WITH A BELL TAP HAMMER, FOUND THE EROSION STRIP PARTIALLY DEBONDED. TAIL ROTOR HUB AND BLADE ASSY, PN 212-011-701-123, TAIL ROTOR BLADE, PN 212-010-750-127FM.SDR CA130128024Wire · chafed(CAN) PILOT REPORTED LATERAL CYCLIC IMPULSES FELT IN ALL FLIGHT REGIMES WITH AUTO PILOT SELECTED ON ONLY. EXTENSIVE TROUBLESHOOTING WAS CARRIED OUT OVER A 3 WEEK PERIOD. THE FINAL RECERTIFICATION OF THE PROBLEM WAS THE REPLACEMENT OF WIRE C943D22, WHICH WAS FSDR CA121115006Link · failed(CAN) DURING 600 HR INSPECTION OF ACFT, LIFT LINK BEARINGS WERE FOUND SPINNING WITHIN BORE. OEM HAS NO REQUIRED INSPECTION OF THIS COMPONENT AND THIS IS NOT AN ISOLATED CASE.SDR EOPA20121022397Housing · crackedON INSPECTION, AN OIL LEAK WAS DISCOVERED IN THE COMBINED GEARBOX AREA. ON FURTHER INSPECTION THE NR 1 ENGINE CHIP DETECTOR HSG ATTACHED TO THE GEARBOX WAS FOUND CRACKED.SDR ALGA2012101101Nut · corrodedNUT FOUND UNSERVICEABLE DUE TO EXCESSIVE CORROSION.SDR CA120919001Turbine Wheel · fractured(CAN) IN FLIGHT SHUTDOWN. PILOT REPORTED THAT WHILE PULLING POWER, HE HEARD A SERIES OF NOISES, FOLLOWED BY A SHUDDER AND VIBRATION. THE RESULT OF THIS WAS A DECREASE IN ROTOR RPM, FOLLOWED BY A DECAY OF N1. THE FLIGHT OFFICER REPORTED N1 DROPPED TO APPROXIMSDR CA120824003Transistor · failed(CAN) WHEN THE DIM FUNCTION ON THE CONSOLE IS UTILIZED FOR THE INSTRUMENT LIGHTING, THE CIRCUIT BREAKER TRIPS. TRANSISTOR, PN 130-007-1 USED IN THE SYS HAS FOUND A GROUND ON THE BASE OR CASE. THE INSULATOR SEPARATING TRANSISTOR FROM ALUMINUM BRACKET IS A PLASSDR ALGA2012061805Support Case · crackedCRACKED SUPPORT CASE.SDR CA120615002Wire Harness · chafed(CAN) DURING INSPECTION, IT WAS NOTICED THAT TWO WIRE BUNDLES WERE CHAFING AGAINST EACH OTHER. THE WIRE BUNDLES ARE LOCATED IN THE UPPER LT DOOR POST. WHEN THE WIRE BUNDLES WERE SEPERATED, NUMEROUS WIRES WERE FOUND CHAFED COMPLETLY THROUGH TO THE BARE WIRE. TWSDR ALGA2012061202Flange · corrodedFLANGE, CORROSION BEYOND LIMITS.SDR CA120612009Magnetic Brake · no test(CAN) AS PART OF A DAILY MAINTENANCE INSPECTION THE FORCE TRIM RELEASE OF THE YAW MAGNETIC BRAKE ASSY WAS TESTED. THE MECHANIC WAS ABLE TO DETECT THAT THE BRAKE ASSY WAS NOT RELEASING ON APPLICATION OF THE FORCE TRIM SWITCH. THE UNIT WAS REMOVED AND A SERVICESDR CA120608011Connector · disconnected(CAN) WHILE IN CONFINED SPACE, FORCE TRIM OFF, PILOT FELT PEDALS BIND AND COULD NOT INPUT MORE TAIL ROTOR CONTROL. IT THEN BROKE LOOSE AND NORMAL FEEL WAS ESTABLISHED. MAINTENANCE WAS ABLE TO DUPLICATE THE SNAG IN THE HANGER. MAGNETIC BRAKE FOR THE TAIL CONTSDR CA120511006Tube · leaking(CAN) THE PILOT NOTICED THE NR1 HYDRAULIC SIDE RESEVOIR WAS NEARLY EMPTY ON SHUTDOWN AND HYDRAULIC FLUID LEAKING ON SPOT. MAINTENANCE WAS NOTIFIED. UPON INVESTIGATION, A LEAK WAS FOUND ON THE HYDRAULIC PIPE, BETWEEN THE 3 WAY CHECK VALVE AND THE INTEGRATED VSDR CA120430012Seal · cracked(CAN) CARRYING OUT INSPECTION OF MAIN TRANSMISSION OIL LEVEL, IT WAS DISCOVERED THAT THE QTY WAS LOW. A GROUND RUN AND LEAK CHECK WAS PERFORMED AND FOUND THAT THE NR 1 HYDRAULIC PUMP QUILL SHAFT SEALS WERE THE SOURCE. UPON REMOVAL OF THE PUMP IT WAS DISCOVERSDR ALGA2012042402Bearing · wornBEARING WORN AND CORRODED BEYOND LIMITS.SDR CA120312024Gear · failed(CAN) DURING HEAVY MAINTENANCE OF A CH146, 3000HR/5 YEAR INSPECTION IT WAS NOTICED THAT THE CHAIN FOR THE RGB FILLER CAP AND ADAPTER PN 212-062-504-001 HAD DETACHED FROM THE FILLER TUBE. A SECTION OF THE CHAIN WAS FOUND LODGED IN THE FILLER CHECK VALVE ASSY ASDR ALGA20122281215Nut · corrodedPITTING CORROSION BEYOND LIMITS.SDR ALGA20122281214Mast · corrodedMAST CORRODED BEYOND LIMITS.SDR CA120213007Trim Switch · intermittent(CAN) PILOT REPORTED, ATT MODE-ERRATIC PITCH. DISCUSSION WITH THE PILOT REVEALED THAT THE PROBLEM OCCURED IN THE DECENT AND IN ATT MODE. THE PILOT STATED THAT HE ELECTED NOT TO USE THE VERTICAL MODE AND REPORTED THE FAULT UPON LANDING. THE CO-PILOT CYCLIC SSDR ALGAR5493122711Floor Panel · separatedFLOOR PANEL DEBONDED AND SEPARATED BEYOND LIMITS.SDR ALGAR5501122711Floor Panel · corroded(9Y-BC, EXPORTED AIRCRAFT) FLOOR PANEL CORRODED BEYOND LIMITS IAW BHT-SRM-ALL.SDR CA111130009Transducer · failed(CAN) PILOT REPORTED PEDAL FEEDBACK DURING FLIGHT. FEEDBACK DISAPPEARED BELOW 40 KTS. MAINTENANCE REPORTED, TAIL ROTOR SCAS TUBE P/N 7018078 & NO. 1 YAW CMT P/N 412-074-101-103 REPLACED. DETAILS OF MAINTENANCE CARRIED OUT ONADDITIONAL TASK SHEETS (3). AIRCRAFSDR CA111101003Relief Valve · stuck(CAN) TRANSMISSION THERMAL RELIEF VLV PN 205-060-512-003, FOUND STUCK OPEN & WORN DURING 3000 HR INSPECTION OF BELL 412CF. VLV WAS REMOVED TO REPLACE GASKET & UPON VISUAL INSPECTION OF VLV ASSEMBLY, POPPET APPEARED LOOSE IN HOUSING. THE VLV WAS DISASSEMBLED SDR CA111026006Bearing · delaminated(CAN) BEARING FOUND DELAMINATED DURING DAILY INSPECTION.SDR CA111014001Bearing · delaminated(CAN) BEARING FOUND DELAMINATED AROUND FULL CIRCUMFERENCE OF BEARING ASSY.SDR CA110826008Bearing · delaminated(CAN) DURING A 25 HR/30 DAY SCHEDULED INSPECTION, MAINTENANCE PERSONNEL FOUND THE DAMPER BEARING, LOCATED ON THE INBOARD SIDE OF THE SPINDLE ASSEMBLY TO BE COMPLETELY DELAMINATED AROUND ITS FULL CIRCOMFERENCE. THE BEARING ITSELF WAS DELAMINATED INTERNALLY AS ASDR CA110803012Bleed Valve · stuckDURING FINAL APPROACH, THE PILOT DECLARED EMERGENCY AFTER PERFORMING A PRECAUTIONARY SHUTDOWN OF THE ENGINE DUE TO OBSERVED HIGH TEMPERATURE. AN UNEVENTFUL SINGLE ENGINE LANDING FOLLOWED. POST FLIGHT INSP FOUND A STUCK COMPRESSOR BLEED VALVE (BOV) PISTON AS SDR CA110722005Bleed Valve · stuckON APPROACH, THE CREW NOTICED THAT THEY HAD ZERO TORQUE INDICATION AND HIGH ITT ON ENGINE NR1. THE CREW SHUTDOWN THE NR 1 ENGINE AND LANDED WITHOUT FURTHER INCIDENT. THE ENGINEER TROUBLESHOOTING THE FAULT, NOTED THAT THE BLEED VALVE WAS STUCK IN THE CLOSED POSDR CA110602007Radar · intermittentPILOT REPORTED, "WX RADAR- DIM IMAGE AND GOING INTO "WAIT" MODE. THIS OCCURED DURING HEAVY RAIN. RADAR TURNED OFF RTB." AVIONCS PERSONNEL WERE ABLE TO REPRODUCE THE FAULT DURING A GROUND TEST. RADAR PEDESTAL AND SURROUNDING AREA IN THE AVIONICS BAY WAS FOUNSDR CA110527005Damper · delaminatedUPON RETURNING FROM THE FLIGHT, THE PILOT ADVISED MX OF "LATERAL VIBE IN HELICOPTER. VERY NOTICEABLE AT HIGH POWER SETTINGS." UPON INSP, MX HAD FOUND THAT THE DAMPER BEARING, LOCATED ON THE INBD SIDE OF THE SPINDLE, HAD DELAMINATED FROM THE SPINDLE. (THE SPINDSDR EOPA020211397ALFrame · crackedFRAME WAS FOUND CRACKED AT APPROX STA 78 IN TAILBOOM ABOVE BAGGAGE COMPARTMENT.SDR 2011F00024Blade · delaminatedM/R BLADE T/E "WEDGE" CAME DEBONDED. REMOVED REMAINING PORTION OF WEDGE AND TOUCHED UP PAINT IAW MFG PRODUCT SUPPORT ENGINEERING.
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