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 = '737200' 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 = '737200' 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 CA040412001Pitot Line · leaking(CAN) B737-200 PITOT TUBE ASSEMBLY FAILED BENCH CHECK WITH A PITOT LEAK IN EXCESS OF 200 KTS/MIN. THE LEAK WAS DETERMINED TO BE ORIGINATING WHERE THE PITOT TUBE AIRFRAME ATTACHMENT CONNECTS TO THE BASE OF THE PITOT TUBE ASSEMBLY. THE COMPONENT WAS A USED PARSDR 0402001Ground Stud · detachedBATTERY VOLTS BELOW MINIMUMS FOUND GROUND LUG DETACHED FROM FORMED SECTION REPAIRED FORMED SECTION IAW BOEING SRM 51-40-3 PG 5 FIG 1 SHEETS 1-5.SDR CA040102002Adc · intermittent(CAN) PRIOR TO DEPARTURE THE FLIGHT CREW A MACH AIRSPEED WARNING CLACKER INOPERATIVE ASSOCIATED WITH A FLAG ON THE MACH AIRSPEED INDICATOR. RECTIFICATION THE MACH AIRSPEED INDICATOR WAS REPLACED. HOWEVER THE SNAG RETURNED ON DECEMBER 29. THE SYSTEM WAS PLACEDSDR COOSDR030061Carriage · damagedLT AND RT INBOARD MIDFLAP (PN 6571902-11/12) CARRIAGE ASSY PN 65-52246-9/10 AND 11/12 DAMAGED.SDR COOSDR030060Thrust Bearing · damagedRT AND LT WING, OB MIDFLAP THRUST BEARING DAMAGED.SDR COOSDR030059Splice · crackedRT WING, REAR SPAR LOWER CHORD SECTION, OUTBOARD SPLICE PN 6550821144 CORRODED AND CRACKED.SDR COOSDR030057Spar · crackedRT WING, REAR SPAR LOWER CHORD SECTION, FROM WBL 113 INCHES TO WBL 130 INCH OB SPLICE PN 65-50821-142.SDR COOSDR030056Web · wornRT HORIZONTAL STABILIZER TRAILING EDGE, HINGE RIB, WEB WITH WEAR.SDR COOSDR030055Seal · crackedLT HORIZONTAL STABILIZER BLADE SEAL CRACKED.SDR COOSDR030054Skin · delaminatedRT WING, AILERON (PN-65-46454-2) SN 305, SKIN DELAMINATED.SDR COOSDR030053Skin · delaminatedRT WING, IB GROUND SPOILER (PN 65-79952-6) SN MA358, DELAMINATED.SDR COOSDR030052Skin · corrodedNR 2 ENGINE OB COWLING EXTERNAL SKIN CORRODED.SDR COOSDR030051Flap Track · corrodedLT WING, FLAP TRACK NR 2 CORRODED.SDR COOSDR030050Panel · delaminatedRT WING, FIXED PANEL PN 65-50820-142, TMC-284 DELAMINATED.SDR COOSDR030049Channel · corrodedRT WING TRAILING EDGE CAVITY UPPER FIXED PANEL CHANNEL CORRODED.SDR COOSDR030048Channel · crackedLT MAIN LANDING GEAR CHANNEL, CRACKED.SDR COOSDR030047Channel · crackedRT MAIN LANDING GEAR CHANNEL.SDR COOSDR030046Skin · delaminatedRT WING, FLIGHT SPOILER NR 7 UPPER SURFACE DELAMINATED.SDR COOSDR030045Rib · crackedRT WING, FSS 266 LEADING EDGE RIB CRACKED.SDR COOSDR030044Rib · crackedRT WING, FSS 263 LEADING EDGE RIB CRACKED.SDR COOSDR030043Angle · corrodedRT WING, TRAILING EDGE - RSS486, ANGLE CORRODED.SDR IU62003F00020Housing · overtorquedCRACKED INSIDE THE MOUNTING HOLE. OVER-TORQUED OR OVER-PRESSURIZED. EVALUATE THE DESIGN/ MATERIAL HOUSING IS MADE FROM.SDR BJNA021102Cover · brokenHARD COMPRESSOR STALL ON NR 1 ENGINE AT 2.20 EPR - 96 PERCENT N1 - 20 KNOTS SPEED, POWER WAS PULLED TO IDLE WITHIN 300 FT OF TAKE OFF ROLL, TAKE OFF ABORTED. ENGINE INSPECTION: NOSE CONE OFF AND DAMAGED BASEBALL SIZE DAMAGE TO INNER LINER AND HONEYCOMB STRUCSDR TSAA0277173Transmitter · inoperativeNR 1 ENGINE EPR DROPPED OFF ON CLIMB OUT OF 7,000 FEET. NR 1 ENGINE EPR WAS 1.73 AND NR 2 ENGINE EPR WAS 1.85. BOTH THE NR 1 AND NR 2 ENGINES NR 1 WAS 89 PERCENT AND NR 2 WAS 92 PERCENT. THE AIRCRAFT RETURNED AND LANDED IN HNL WITH NO FURTHER INCIDENT. (ETSDR 2002FA0000599Housing · crackedUNIT IS CRACKED IN BOTH PRIORTY PORTS.SDR 2002FA0000605Housing · crackedHOUSING IS CRACKED.SDR 2002FA0000606Housing · crackedHOUSING, UNIT IS CRACKED IN (D) PRIORTY PORT.SDR CA011010002Uplock Sensor · failed(CAN) SHORTLY AFTER TAKEOFF DUE TO UNSAFE LT MLG INDICATION. CREW REPORTED ON CLIMB OUT LEFT MAIN GEAR RED UNSAFE LIGHT ILLUMINATED AFTER GEAR LEVER SELECTED UP. DECISION MADE TO RETURN TO YEG & A/C LANDED W/O INCIDENT. MAINTENANCE INSPECTION REVEALED PROBLEM SDR AWXA0002095Skin · crackedFWD ENTRY DOORWAY AFT LWR CORNER OF CUTOUT IS CRACKED. HFEC INSP OF HOLES ACCOMPLISHED PER 737 NDT MAN PT 6 51-00-00. ACCOMPLISHED SB 737-53-1083R FOG .2 & FIG 4.SDR CA010625035Wheel · cracked(CAN) DURING TEAR DOWN FOR OVERHAUL CRACK WERE DISCOVERED EMANTAING FROM THE BEARING CUP BORE AND EXTENDING INTO THE SPOKE WEBS ABD REACHING TO WITHIN 1" OF SPLITTING THE HUB. THE PART WAS BER'D THE LAST OVERHAUL INCLUDED LIQUID PENETRANT INSPECTION AND HIGH FSDR 20010315CW002Housing · crackedHOUSING ASSEMBLY IS CRACKED AROUND THE NUT FLANGE AREA. FATIGUED, OVERSTRESSED.SDR 20001212SH019Cover · crackedCOVER IS CRACKED ACROSS EXTERIOR SURFACE FROM THE SHAFT HOLE OUTWARD. POSSIBLE CAUSE, STRESS, FATIGUE AND/OR WEAK POINT IN DESIGN OF COVER. (X)SDR CA001027005Bolt · worn(CAN) ACCOMPLISHING D CHECK ON US REGISTERED B737 IT WAS NOTED THAT LEFT HAND AND RIGHT HAND AFT HORIZ STAB ATTACH POINT BOLTS FOUND ONLY HAND TIGHT. UPON FURTHER INVESTIGATION ALL THREE BOLTS AFT ON R/H HORIZ STAB AND ALL THREE BOLTS AFT LT HORIZ STAB HAVE WESDR 20000424AP009Pressure Switch · damagedDURING FLIGHT, AIRCRAFT RETURNED TO SJO, BECAUSE IT WAS REPORTED THAT ISOLATION VALVE LIGHT ILLUMINATED AND TAKEOFF CONFIGURATION WARNING LIGHT CAME ON. AT SJO, SWITCHERS WERE REPLACED AND TESTED SYSTEM IAW MM 32-33-11, IT WAS WORKING SATISFACTORY. AIRCRAFT SDR 20000420AP002Switch · damagedDURNG FLIGHT LR-628, AIRCRAFT RETURN TO SJO STATION, BECAUSE IT WAS REPORTED THAT ISOLATION VALVE LIGHT ILLUMINATED AND TAKEOFF CONFIGURATION WARNING LIGHT CAME ON. AT SJO STATION, SWITCHERS WERE REPLACED AND TESTED SYSTEM IAW MM 32-33-11, IT WAS WORKING SATISDR CA970807005Cylinder · cracked(CAN) TWO OVERHAULED CYLINDERS DISPLAYED MULTIPLE CRACKS ON AFT TRUNNION BEARING AREA. ALSO DISPLAYED A BURN MARK, WITH REWORK FLAT SPOT FORMED ON CYLINDER SURFACE. THE CHROME PLATE AND BAKE PROCESS WERE DELAYED 38.5 HOURS AND BOEING MAX BETWEEN PROCESSES IS 1
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