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 = '2810' 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 = '2810' 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 USAA2011120700023Tank · leakingPHX FLT 702 EN ROUTE PHX TO PHL. STRONG KEROSENE ODOR OBSERVED IN COCKPIT AND CABIN AFTER ENGINE START. BOTH PACKS ON. BOTH BLEEDS ON. ISOLATION VALVE CLOSED. MX CLEANED AND RESEALED THE LT WING STRINGER TIE FITTING AT THE BULKHEAD SEPARATING THE LEFT ASDR IXXA110079OFuel Tank · leakingDURING TAKEOFF, THE CREW SMELLED A STRONG FUEL ODOR, THE PACKS WERE TURNED ON AND FUEL ODOR WENT AWAY. THE CREW LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED FUEL SYS AND FOUND FUEL LEAK COMMING FROM CRACKED FASTENER ON THE RT TANK AT PYLON. THEY REPLACED ANSDR AALA20111201TUL08Seal · leakingIAD - INFLIGHT EWR-DFW. FLIGHT ATTENDANT NOTICED A FUEL LEAK FROM LEFT WING. FIRST OFFICER NOTED LEAK NEAR BOOST PUMP AREA. FLIGHT DIVERTED IAD LANDED WITHOUT INCIDENT. AIRCRAFT REMOVED FROM SERVICE. REMOVED ACCESS PLATE 1307C LEFT WING AND REPLACED SEAL SDR CALA2011113000777Seal · leakingFUEL REPORTED COMING OUT OF THE RIGHT WING ON THE TAKEOFF ROLL BY THE CONTROL TOWER TRANSFERED PRESSURE RELIEF VALVE TO NEW TANK PANEL PER AMM 28-1 3-11-400-801 AND INSTALLED NEW PANEL PER AMM 28-11-11-400-802 NEEDS FUEL LEAK CHECK. TRANSFERED FUEL & LEAK CHESDR UALA2011112906553Drain Valve · not seatedFUEL DRIPPING NEAR NACA OUTLET ON LEFT WING. FOUND FUEL LEAKING FROM THE OUTBOARD FUEL WATER DRAIN VALVE. RESEATED VALVE. NO LEAK NOTED AFTER 5 MIN. THIS WAS THE LEFT WING SURGE TANK WATER DRAIN VALVE.SDR DJFA20111125047Fuel Cap · leakingCREW NOTED SIGNIFICANT AMOUNT OF FUEL LEAKING FOR THE OVERWING FUEL CAP ON THE RT WING. ACFT DIVERTED AND LANDED SAFELY. MX FOUND THE RT WING FUEL CAP UNSERVICEABLE. THE CAP WAS REPLACED.SDR FDEA201111245019Fuel Cell · corrodedCENTER TANK UPPER SKIN UPPER SURFACE FOUND CORRODED AT BS 920 , AT AREA JUST UNDER RT STUB BEAM CORROSION. REMOVED AND ASSESSED IAW SRM 57-10-01 MAX BLEND MATERIAL REMOVED 0.013 " MAX LIMIT 0.028" BLEND FOUND TO BE WITHIN LIMITS. DUE TO ACCUMALATIVE BLENDSSDR UALA2011111806338Tank · leakingFOUND STANDING RESIDUAL FUEL IN PAN BELOW HORIZONTAL STAB. LOCATED FUEL LEAKING FROM RIGHT AFT LOWER SECTION OF TANK AT THE CORNER SEAM. RESEALED HST FUEL LEAK AREA. SEALANT APPLIED AT 1700, HST CAN BE FUELED AND LEAK CHECKED AT 0500 11-19-11. LEAK CHECKEDSDR FDEA201111174959Fill Port · corrodedLT WING TANK OVERWING FILL PORT FAILED FUNCTIONAL BONDING CHECK.SDR CA111115013Fuel Tank · cracked(CAN) DURING THE IN HOUSE REQUIRED 10 YEAR STRUCTURAL INSPECTION & REPAIR PROGRAM, SIRP, THE FABRIC WAS REMOVED FROM THE WINGS & A CRACK APPROX 1 1/4" LONG WAS DISCOVERED ON THE TOP OF THE INBD FUEL TANK. THE FABRIC HAD LAST BEEN REMOVED OVER THE WINTER OF 20SDR USAA2011111500009Sealant · damagedFUEL LEAK - FUEL LEAKING FROM CENTER BOX DRY BAY DRAIN. LOCATED FUEL LEAK SOUCE IN DRY BAY AT CENTER SPAR FR42 AT RIB 1 LEFT LOWER CORNER ON FORWARD SIDE & NR 8 FASTENER, & ON AFT SIDE OF LEFT SEAM OPPISITE OF NR 8 FASTENER. PERFORMED TEMP REPAIR IAW SRM 51-7SDR USAA2011111400004Tank · leakingCLT - FLT 1079 EN ROUTE CLT TO STT. AFTER ENG START AND APU SHUT-DOWN VERY STRONG KEROSENE SMELL THROUGHOUT CABIN AND COCKPIT (STRONGEST IN COCKPIT). FOUND CENTER TANK LEAK IN RT PACK BAY. CENTER TANK LEAK WAS LOCATED, ISOLATED, REPAIRED AND LEAK CHECKED. SDR FDEA201111084802Fuel Cell · corrodedCENTER TANK UPPER SKIN SURFACE ATTACHED REPAIR PATCH AT BS 980-1000 RT STUB BEAM AREA FOUND DISBONDED. CORROSION REMOVED FROM AFFECTED AREA REPAIR CARRIED OUT IAW EA F-5710-154339.SDR FDEA201111084804Fuel Cell · corrodedCORROSION FOUND BENEATH STUB BEAM ON CENTER TANK SKIN AT BS 940 LT AND RT SIDE OF CABIN CORRODED AREAS REPAIRED IAW EA F-5710-154331.SDR FDEA201111084803Fuel Cell · corrodedCTR TANK UPPER SKIN UPPER SURFACE ATTACHED REPAIR PATCH AT BS 960-980 LT STUB BEAM AREA FOUND DISBONDED. CORRODED AREA BLENDED AND REPAIRED IAW EA F-5710-154339.SDR CALA2011110800725Unknown · malfunctionedAT APROXIMATELY 3000FT ON DEPARTURE THE AIRCRAFT REQUIRED SIGNIFICANT RIGHT AILERON TO HOLD WINGS LEVEL FLIGHT. A CHECK OF THE FUEL GAUGES SHOWED NR 1 TANK FULL NR 2 TANK WITH 6400 LBS, CTR TANK 4900 LBS. ALL PUMPS WERE ON XFEED (CONTINUE ON L/P 8961987). (SDR REXA201100792O-Ring · defectiveFUEL LEAK FOUND BY REFUELER. REMOVED AND REPLACED REFUEL/DEFUEL DUCT O-RINGS PER AMM 28-25-11, OPS CHECK GOOD, VERIFIED PARTS EFFECTIVITY. OK FOR SERVICE.SDR CA111026005Tank · cracked(CAN) FUEL WAS NOTED DRIPPING FROM SUMP DRAIN BOSS WHEN TANK WAS FULL. DRAIN VALVE WAS REPLACED BUT DRIP CONTINUED. INVESTIGATION NOTED FUEL STAINING ON TANK INSIDE WING, OPENING OF FABRIC REVEALED A CRACK AT THE INBOARD END OF THE TOP FORWARD STIFFENING BEAD SDR CA111021001Diaphragm · damaged(CAN) DIAPHRAGM THAT IS PART OF THE AEROBATIC PICKUP TUBE IN THE LT FUEL TANK WAS FOUND STIFF AND HARDENED. WHILE IN INVERTED FLIGHT, THE TUBE WOULD NOT BE ABLE TO FALL TO THE TOP OF THE TANK DUE TO THE STIFFNESS OF THE DIAPHRAGM. THERE IS NO REGULAR INSPECSDR QMLA2011101811102Fuel Tank · leakingTHE MEDICAL CREW REPORTED TO THE PILOT THAT THEY SMELLED FUEL IN THE CABIN SHORTLY AFTER TAKEOFF. THE PILOT IMMEDIATELY RETURNED TO THE HELIPAD. THE MECHANIC PERFORMED AN INPSECTION OF THE FUEL SYS AND FOUND THAT THE LOWER FITTING OF THE EXPANSION TANK WAS LSDR FDEA201110184571Fuel Cell · corrodedEXFOLIATED CORROSION FOUND BENEATH STUB BEAM AT BS940 LT SIDE OF CABIN AT CENTER TANK SKIN. REWORK CARRIED OUT ON NON ROUTINE N00425 AND EA F-5710-154331.SDR CALA2011101800666Seal · wornON TAKEOFF AN AIRCRAFT ON GROUND BEHIND US REPORTED WHAT THEY THOUGHT WAS FUEL LEAKING FROM LEFT WING. TEMP AND DEWPOINT WAS 26/08 VERY DRY AIR CONTINUED TO NEXT LOG PAGE 8912999 LOG NOTED SEE L/P 8912999 FOR CORRECTIVE ACTION AND SIGN OFF - CHECKED VOLUMETRSDR FWTA2011101401Drain · crackedFLIGHT RF-763, 10-14-2011, LOG BOOK ENTRY GROUND ITEM ENTERED BY LAN MXT AFTER FUELING A/C LEADING EDGE SLAT NR 4 INBOARD CANISTER DRAIN HAS HEAVY SEEP FUEL LEAK, NR 3 DRAIN. THE NATURE OF THE LEAK WAS A CRACKED DRAIN TUBE P/N 112T2019-143 PART WAS REMOVED ANSDR SIMA2011101328601Fuel Sys · leakingON FLIGHT 2962 DISPATCH REPORTED THE CREW DIVERTED TO LIT DUE TO A FUEL LEAK. THE AIRCRAFT LANDED WITHOUT INCIDENT. THE AIRCRAFT WAS REMOVED FROM SERVICE. PERFORMED POSITIVE PRESSURE ON LEFT HAND WING AT 2.5 PSI. SPRAY DOWN WITH SOAP WATER SOLUTION ON TOP SDR UALA2011101205530Float Valve · wornFUEL SEEMS TO TRANSFER INFLT FROM RIGHT WING TO LEFT W- CROSSFEED CLOSED. BURN +TOTAL CORRECT. T/S FOR WING TO WING TXFER COULD NOT DUPLICATE BUT DID FIND LT WING OUTER TANK VENT FLOAT WORN OUT CAUSING TXFER FROM OUTER TO INNER TXFER AT APPROX 200LB PER HOUR SDR IXXA110068OFuel Tank · leakingDURING TAKEOFF, THE CREW SMELLED A STRONG FUEL ODOR IN COKPIT WITH PACKS OFF. THEY CONTINUED ON WITH THE FLIGHT AND LANDED WITHOUT FURTHER INCIDENT. MX TROUBLESHOT SYS AND FOUND FUEL LEAK AT INBD LT WING OVER WING ROOT. THEY CLEANED, RESEALED, LEAK CHECKED GSDR UALA2011101005483Valve · malfunctionedLEFT WING BOTH REFUEL VALVES WILL NOT OPEN. DEFERED PER MEL, MTX WILL NEED TO ASSIST FUELING BY OPENING ONE REFUEL VALVE.SDR FDEA201110014253Panel · corrodedCORROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = 8 TO X = 27.5. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.052 INCH; MATERIAL REMAINED = 0.120 INCH - FOUND EXCEEDED SDR FDEA201110014252Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO STA 1239, X = 8 TO X = -8. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.035 INCH; MATERIAL REMAINED = 0.137 INCH - FOUND EXCEEDED LISDR FDEA201110014248Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = -75 TO X = -107. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.027 INCH; MATERIAL REMAINED = 0.142 INCH - FOUND EXCEEDEDSDR FDEA201110014242Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1256 TO 1273, X = -98 TO X = -107. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.285 INCH; MATERIAL REMOVED = 0.012 INCH; MATERIAL REMAINED = 0.273 INCH - FOUND EXCEEDEDSDR FDEA201110014241Panel · corrodedCABIN - COROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO 1239, X = 75 TO X =107. COROSSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.132 INCH; MATERIAL REMAINED = 0.040 INCH - FOUND EXSDR FDEA201110014258Fuel Cell · corrodedCOROSION ON CENTER WING TANK TOP PANEL SURFACE AT STA 1210 , X = -8 TO X = - 27.5. CORROSION REMOVED AS PER SRM 51-21-01, REV 47. ORIGINAL MATERIAL THICKNESS = 0.170 INCH; MATERIAL REMOVED = 0.011 INCH; MATERIAL REMAINED = 0.159 INCH - FOUND WITHIN LIMIT ASDR FDEA201110014257Structure · corrodedCORROSION ON CTR WING TANK TOP PANEL SURFACE AT STA 1210 , X = -8 TO X = 8. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.008 INCH; MATERIAL REMAINED = 0.112 INCH - FOUND EXCEEDED LIMIT AS PER MDSDR FDEA201110014259Panel · corrodedCORROSION ON CTR WING TANK TOP PANEL SURFACE AT STA 1210 , X = -47.5TO X = -75. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.170 INCH; MATERIAL REMOVED = 0.011 INCH; MATERIAL REMAINED = 0.159 INCH - FOUND EXCEEDED LIMIT AS PERSDR FDEA201110014256Panel · corrodedCORROSION ON CTR WING TANK TOP PANEL SURFACE AT STA 1210 , X =47.5 TO X =75. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.170 INCH; MATERIAL REMOVED = 0.010 INCH; MATERIAL REMAINED = 0.160 INCH - FOUND EXCEEDED LIMIT AS PER SRSDR FDEA201110014255Panel · corrodedCORROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = 75 TO X = 107. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.024 INCH; MATERIAL REMAINED = 0.148 INCH - FOUND EXCEEDED LIMSDR FDEA201110014254Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = 27.5 TO X = 47.5. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.043 INCH; MATERIAL REMAINED = 0.129 INCH - FOUND EXCEEDESDR FDEA201110014251Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = -8 TO X = -27.5. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.031 INCH; MATERIAL REMAINED = 0.141 INCH - FOUND EXCEEDED LISDR FDEA201110014250Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = -27.5 TO X = -47.5. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.041 INCH; MATERIAL REMAINED = 0.131 INCH - FOUND EXCEEDESDR FDEA201110014249Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = -47.5 TO X = -75. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.176 INCH; MATERIAL REMOVED = 0.015 INCH; MATERIAL REMAINED = 0.161 INCH - FOUND EXCEEDED LISDR FDEA201110014247Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X =47.5 TO X =75. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.027 INCH; MATERIAL REMAINED = 0.145 INCH - FOUND EXCEEDED LIMITSDR FDEA201110014245Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1209 TO 1219, X =107. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.193 INCH; MATERIAL REMOVED = 0.031 INCH; MATERIAL REMAINED = 0.162 INCH - FOUND EXCEEDED LIMIT AS PER SDR FDEA201110014244Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1239 TO STA 1256, X =98 TO X =107. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.247 INCH; MATERIAL REMOVED = 0.017 INCH; MATERIAL REMAINED = 0.230 INCH - FOUND EXCEEDED LISDR FDEA201110014243Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1256 TO 1273, X =98 TO X =107. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.285 INCH; MATERIAL REMOVED = 0.045 INCH; MATERIAL REMAINED = 0.240 INCH - FOUND EXCEEDED LIMIT ASDR FDEA201110014240Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO 1239, X = 47.5 TO X =75. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.027 INCH; MATERIAL REMAINED = 0.145 INCH - FOUND EXCEEDED LIMITSDR FDEA201110014239Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO 1239, X = 27.5 TO X = 47.5. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.043 INCH; MATERIAL REMAINED = 0.129 INCH - FOUND EXCEEDESDR FDEA201110014238Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT BS 1219 TO 1239, X = 8 TO X = 27.7. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.052 INCH; MATERIAL REMAINED = 0.120 INCH - FOUND EXCEEDED LIMSDR FDEA201110014237Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1199 TO STA 1219, X = 8 TO X = 27.5. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.013 INCH; MATERIAL REMAINED = 0.159 INCH - FOUND EXCEEDED SDR FDEA201110014236Panel · corrodedCABIN - COROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO STA 1239, X = 8 TO X = -8. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.035 INCH; MATERIAL REMAINED = 0.137 INCH - FOUND EXC
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