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 = '400A' 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 = '400A' 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 DJFA20120508005Rib · crackedDURING SCHDULED INSP, MX TECH FOUND 8 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 8 RIBS WERE RESDR DJFA20120508006Rib · crackedDURING SCHDULED INSP, MX FOUND 8 RIBS CRACKED IN THE HORIZ STABILIZER. EA CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 8 RIBS WERE REPLACED SDR DJFA20120508007Rib · crackedDURING SCHDULED INSP, MX TX FOUND 8 RIBS CRACKED IN THE HORIZ STABILIZER. EA CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 8 RIBS WERE REPLACSDR DJFA20120508008Rib · crackedDURING SCHDULED INSP, MX FOUND 8 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 8 RIBS WERE REPLACESDR DJFA20120508001Rib · crackedDURING SCHDULED INSPECTION, MX FOUND 8 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 8 RIBS WERE RSDR 2012FA0000319Wire · burnedDURING A D-CHECK INSPECTION, WIRING IN THE AFT BAGGAGE RT LOWER AREA IT WAS NOTED THAT SOME WERE BURNED. THESE HAD SHORTED OUT AND HAD BURNED THRU INSULATION. THE W740 RT FAN N1 RPM INDICATOR. THE W748 RT TURBINE N2 INDICATOR. WIRES WERE REPLACED.SDR BUER2012050251Control Cable · brokenWHILE INSPECTING FLAP SYSTEM, DURING AN A & B INSPECTION, FOUND FLAP SYS CABLES EXTREMELY LOOSE. FURTHER INVESTIGATION FOUND CABLE CORRODED WHERE INTERCONNECT CABLE IS SWEDGED IN CABLE GIMBLE SLIDE ASSY. PULLED ON CABLE AND CABLE BROKE OFF SWEDGE. CHECKED OSDR DJFA20120501012Rib · crackedDURING SCHEDULED INSPECTION, MX TECH FOUND 12 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RISDR DJFA20120501011Rib · crackedDURING SCHEDULED INSPECTION, MX TECH FOUND 12 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RISDR DJFA20120501010Rib · crackedDURING SCHDULED INSPECTION, MX FOUND 12 RIBS CRACKED IN THE HORIZONTAL STAB. CRACKS WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERE REPSDR DJFA20120501009Rib · crackedDURING SCHDULED INSP, MX FOUND 12 RIBS CRACKED IN THE HORIZONTAL STAB. CRACKS WERE FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERE REPLACEDSDR DJFA20120501008Rib · crackedDURING SCHDULED INSPECTION, MX FOUND 12 RIBS CRACKED IN THE HORIZ STABILIZER. CRACKS WERE FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERE RSDR DJFA20120501007Rib · crackedDURING SCHDULED INSPECTION, MX FOUND 12 RIBS CRACKED IN THE HORIZONTAL STAB. CRACKS WERE FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERE RSDR DJFA20120501006Rib · crackedDURING SCHDULED INSPECTION, MX FOUND 12 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERSDR DJFA20120501005Rib · crackedDURING SCHDULED INSP, MX TECH FOUND 12 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERSDR DJFA20120501004Rib · crackedDURING SCHDULED INSP, MX TECH FOUND 12 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERESDR DJFA20120501003Rib · crackedDURING SCHDULED INSPECTION, FOUND 12 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERE SDR DJFA20120501002Rib · crackedDURING SCHDULED INSP, MX TECH FOUND 12 RIBS CRACKED IN THE HORIZ STABILIZER. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERESDR DJFA20120501001Rib · crackedDURING SCHDULED INSPECTION, FOUND 12 RIBS CRACKED IN THE HORIZONTAL STAB. EACH CRACK WAS FOUND TO BE EMINATING OUTWARD FROM A FASTENER HOLE ON THE ATTACHEMENT FLANGES OF THE RIBS WHERE THE BLIND FASTENERS WERE INSTALLED ON THE LOWER SKIN. ALL 12 RIBS WERE RESDR 9JLA2012071704216Inverter · defectiveCREW REPORTED THE LT INVERTER FAILED IN FLIGHT. FOUND THE LT AC INVERTER TO BE DEFECTIVE. INSTALLED AN O/H UNIT, FUNCTIONAL CHECKED SATISFACTORY.SDR 2LWR201200001Cover Plate · misrepaired(ACFT YV2452) RECEIVED TWO MC 10-15-18 OXYGEN MASKS. DURING BENCH AND PRELIMINARY INSPECTIONS, TECH DISCOVERED A REPAIR TO THE COVER PLATE, WHICH APPEARS TO BE AN UNAUTHORIZED REPAIR TO BE INSUFFICIENT.SDR DXTA2012040504944Brake Sys · malfunctionedBOTH PILOT AND COPILOT BRAKE PEDALS REQUIRE EXECESSIVE PRESSURE TO ACTUATE THE BRAKES. CHECKED BRAKE WEAR & FLUID LEVELS. NO DEFECTS NOTED. TAXIED ACFT AND PERFORMED BRAKE CHECKS ALL CHECKS NORMAL. PILOT VERIFIED PROPER BRAKE, OPS ON HIGH SPEED TAXI. ALL WSDR DXTA2012031904924Brake Sys · malfunctionedPARKING BRAKE WILL NOT SET FROM LT SIDE. BRAKE WILL SET FROM THE RT. SHUTDOWN ENGINE AND RELEASE AND RESET PARKING BRAKE SEVERAL TIMES OPERATED NORMAL IAW MM 32-400.SDR 2012FA0000155Uplock Switch · shortedACFT EXPERIENCED A LANDING GEAR UNSAFE LIGHT (RED HANDLE) IN FLIGHT, PILOT ATTEMPTED AND WAS ABLE TO CYCLE LANDING GEAR NUMEROUS TIMES, LIGHT WOULD NOT EXTINGUISH. PILOT VARIED GEAR DOWN AND LOCKED, LANDED ACFT.SDR CA120312003Fuel Control · malfunctioned(CAN) DURING TAXI-OUT, 1 ENGINE ROLLED BACK TO SUB-IDLE AND SEEMED TO HUNG. THE ENGINE WAS SHUTDOWN AND LARGE AMOUNT OF SMOKE APPEARED IN THE BACK. STREAM OF FUEL POOLED UNDER THE ENGINE. ACFT WAS TOWED BACK TO ORIGIN. GROUND TECH CONFIRMED FUEL LEAKING FRSDR MGOR20120223001Bolt · shearedDURING TAXI FOR TAKEOFF, THE LT MAIN WHEEL HAD 2 WHEEL HALF BOLTS SHEAR CAUSING WHEEL DEFLATION.SDR DJFA20120130008Unknown · odorON APPROACH FOR LANDING, CREW REPORTED AN ELECTRICAL BURNING ODOR COMING FROM THE PILOT'S SIDE GLARESHIELD. ACFT LANDED SAFELY. NO SMOKE WAS NOTED. MAINTENANCE PERFORMED VISUAL INSPECTION BUT COULD NOT FIND THE SOURCE OF SMOKE OR FUMES; ENGINE RUNS AND OTSDR DJFA01302012009Inverter · failedON APPROACH FOR LANDING, CREW REPORTED HEARING A SOUND LIKE A SPARK FOLLOWED BY AN ELECTRICAL BURNING SMELL AND NR1 INVERTER FAILURE INDICATION. ACFT LANDED SAFELY. MAINTENANCE FOUND THE NR 1 INVERTER FAILED AND THE "AC SELECT" SWITCH MALFUNCTIONING. BOTH SDR 2012FA0000104Shutoff Valve · failedDURING FLIGHT, LEFT HIGH FLOW PRESSURE RELIEF/SHUTOFF VALVE FAILED TO REGULATE LT ENGINE BLEED AIR RESULTING IN DOWN STREAM OVER PRESSURE CONDITION CAUSING THE OVER PRESSURE RELIEF VALVE TO OPEN PREVENTING WHICH FURTHER DAMAGED TO DOWN STREAM COMPONENTS. FAILSDR DJFA2011112004Dimmer · failedDURING FLIGHT, CREW NOTED COCKPIT LIGHTS FLICKERING FOLLOWED BY AN ELECTRICAL BURNING SMELL. ACFT DIVERTED TO ANOTHER AIRPORT AND LANDED SAFELY. MX FOUND THE ALTITUDE AWARENESS PANEL AND ITS ASSOCIATED LIGHTING POWER SUPPLY FAILED. BOTH UNITS WERE REPLACED.SDR DJFA2012003Rib · crackedDURING A SCHEDULED MX EVENT, WHILE PERFORMING A BOROSCOPE INSPECTION OF THE HORIZONTAL STABILIZER RIBS, SEVERAL CRACKS WERE FOUND ON SEVERAL RIBS IN THE LT AND RT SIDES OF THE HORIZ STABILIZER. THE CRACKS WERE FOUND ON THE ATTACHMENT FLANGES FROM THE RIBS WHESDR DXTA2012011804849Control Box · malfunctionedDURING TAXI TO RAMP, RIGHT BRAKE RELEASED FOR 2 SECONDS. CONTINUED TO SLOW & MADE A SLIGHT RIGHT TURN, APPLYING A LITTLE MORE RIGHT BRAKE THAN LEFT. AGAIN RT BRAKE RELEASED FOR 2 SECONDS. TAXIING STRAIGHT (6 MPH) BOTH BRAKES RELEASED. ROLLED FOWARD ABOUT 1SDR DJFA2012002Dimmer · malfunctionedDURING APPROACH TO LANDING AT DUSK, THE CREW ACTIVATED THE COCKPIT LIGHTS AND NOTED THE LIGHTS WERE FLICKERING. SOON THEREAFTER, THE CREW NOTED A BURNING SMELL FOLLOWED BY SMOKE EMINATING FROM THE BEHIND THE GLARESHIELD. THEY DEACTIVATED THE LIGHTS AND THE SSDR E81R2011010232281Flap System · malfunctionedINVESTIGATED FLAP SYS ASSYMETRY WARNING ANNUNCIATOR LIGHT INDICATION. FOUND RT FLAP FOLLOW-UP SWITCH ACTUATING ARM .075 IN. LONGER THAN LT FOLLOW-UP SWITCH ACTUATING ARM. ADJUSTED RT FOLLOW-UP SWITCH ACTUATING ARM TO MATCH LT FOLLOW-UP SWITCH ACTUATING SWITCSDR DJFA20120102001Dimmer · smokeON APPROACH, CREW REPORTED SMOKE EMANATING FROM THE INSTRUMENT PANEL, WITH AN ELECTRICAL BURNING SMELL. CREW DECLARED AN EMERGENCY, CONTINUED THE APPROACH TO A SAFE LANDING. MX FOUND THE DIMMER POWER SUPPLY (DS104) OUTPUT VOLTAGE OUT OF LIMITS WHICH RESULTEDSDR E81R201112312271Servo · malfunctionedDURING TROUBLESHOOTING FOR INOPERATIVE AUTOPILOT PITCH TRIM, RECEIVED A RUDDER SERVO FAULT INDICATION ON ACFT MX DIAGNOSTIC COMPUTER. REPLACED THE RUDDER SERVO WITH AN O/H SERVO. NO FAULT INDICATIONS NOTED, OPS NORMAL. RECOMMEND SERVO MFR INVESTIGATE FAIL INSDR E81R2011121302271Flt Controls · unknownINVESTIGATED IN-FLIGHT "AP PITCH TRIM FAIL" ANNUNCIATOR INDICATION. VERIFIED AUTOPILOT NOSE UP PITCH TRIM FUNCTION INOPERATIVE. SWAPPED NR 1 AND NR 2 FCC-4007 CARDS FOR TROUBLESHOOTING, NO FAULTS INDICATED. AUTOPILOT NOSE-UP TRIM CONTROLLED BY NR 2 FCC-4007 CSDR 2012F00030Roll Servo · bindingUPON LANDING YOKE WOULD NOT TURN TO THE RIGHT. HAD NO CONTROL.SDR E81R2011122232191Circuit Card · failedFLIGHT CREW REPORTED ACFT STARTED "PORPOISING" +/- 300 FT AT 800 FPM WHILE IN CRUISE FLIGHT AT FL400. COPILOT'S SIDE DISPLAY SIMULTANEOUSLY DISPLAYED "PITCH TRIM FAIL" INDICATION. ACFT DIVERTED. FOUND ELEVATOR CABLES AND ELEVATOR SERVO BRIDLE CABLE TENSIONSSDR DXTA2011121304824Control Box · malfunctionedON TAXI OUT, EXPERIENCED A LOSS OF BRAKING FOR BOTH PILOT & COPILOT. BRAKE PEDALS PULSATED AS IF ANTI-SKID ACTIVATING. R & R ANTI-SKID CONTROL BOX WITH UNIT. OPS CHECKED SATISFACTORY IAW MM 32-40-00.SDR 2011FA0000804Bearing · failedWHILE PERFORMING A 200 HR A INSPECTION ON THE RT ENGINE OF ACFT, THE MAGNETIC CHIP COLLECTORS WERE REMOVED FROM THE GEAR BOX AND OIL TANK. METAL PARTICLES WERE FOUND ON BOTH COLLECTORS. OIL SOAP SAMPLES WERE SENT TO FOR EVALUATION. THE OIL FILTER ANALYSIS RSDR 2011FA0000803Mount · crackedDURING THE REMOVAL OF THE LT ENGINE, IT WAS NOTICED THAT THE LT ENGINE MOUNT HAD A LARGE CRACK.SDR 9JLA201201121877Pressure Switch · defectiveTHE CREW REPORTED THAT THE LT FUEL BOOST PUMP, LOW PRESSURE INDICATION WAS SLOW TO REACT TO PREFLIGHT TESTING. TROUBLESHOOTING IDENTIFIED THE LT FUEL LOW PRESSURE SENSOR SWITCH WAS DEFECTIVE. THE SWITCH WAS REPLACED WITH NEW FUNCTIONAL CHECK SATISFACTORY.SDR DXTA2011120204811Windshield · unknownON CLIMBOUT PASSING FL 370 SUDDEN, LOUD, CONTINUOUS HIGH PITCHED NOISE EMANATING FROM SOMEWHERE IN THE FWD PEDESTAL/CENTER INSTRUMENT PANEL AREA. LEVELED AT FL 380, DECLARED EMERGENCY AND BEGAN DESCENT WITH NOISE CONSTANT. PASSING FL330, NOISE BEGAN TO GRADUASDR CA111201002Engine · damaged(CAN) DURING FLIGHT, THE NR 2 ENGINE SURGED WITH A RAISE IN TEMPERATURE. THE PILOT REDUCED THROTTLE AND WITHIN 15 SEC., THE ENGINE LOST POWER. THE ENGINE WAS SHUT DOWN AND THE FLIGHT WAS DIVERTED TO HOME BASE WHERE AND UNEVENTFUL SINGLE ENGINE LANDING WAS MADESDR 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 9JLA201112211874Computer · defectiveCREW REPORTED THAT THE AUTO-PILOT PITCH TRIM FAIL ANNUNCIATOR ILLUMINATED WITH THE AUTO-PILOT ENGAGED. TROUBLESHOOTING FOUND THE NR 1 FCC, PN 822-1019-313, SN 262Y DEFECTIVE. INSTALLED A MODIFIED FCC. FUNCTIONAL CHECKS SATISFACTORY.SDR DBCA2011110600006Starter Gen · failedAFTER FUEL STOP IN GRI LEFT ENGINE WOULD NOT SPOOL. CREW CONTACTED MX. MX CONTACTED LOCAL MX TO EVALUATE. LOCAL MX FOUND LEFT STARTER/GENERATOR FAILED. REPLACED STARTER/GENERATOR WITH OVERHAULED UNIT, OPS CHECK GOOD.SDR 9JLA201111031872Actuator · faultyTHE CREW REPORTED THAT DURING PREFLIGHT CHECKS THAT THE RUDDER TRIM WOULD NOT TEST WHILE ON AIRCRAFT BATTERY POWER, BUT WOULD TEST WITH EXTERNAL POWER APPLIED TO AIRCRAFT. TROUBLESHOOTING FOUND THAT THE TRIM ACTUATOR WAS DEFECTIVE. REMOVED THE RUDDER TRIM ACSDR BLUA2012F00027Line · leakingCABIN LOW PRESSURE LIGHT ILLUMINATED AT ALTITUDE. REPAIRED NUMEROUS LEAKS IN ACM AND BLEED SOURCE LINES REPLACED 3 BLEED SOURCE CHECK VALVES, OPS CHECKED PRESSURIZATION CONTROL SYSTEMS.
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