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 = '172P' 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 = '172P' 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 2010FA0000474Fitting · damagedSENT TANK (AMO110-90) FOR REPLACEMENT OF OUTLET FITTING COLLAR DUE TO DAMAGED THREADS. ON RETURN, FOUND THREADS IN NEW FITTING TO BE SEVERELY DAMAGED OR DEFECTIVE. RETURNED TANK FOR REDO. EITHER NO INSP OF PART BEFORE WELDING NOR INSPECTION OF COMPLETED WORSDR 2010FA0000440Piston · broken(Z94E) THE BRAKE PISTON ON THE LT BRAKE MASTER CYLINDER BROKE AT THE THREADED END WHERE IT ATTACHES TO THE CLEVIS. WHEN THE BRAKES FAILED THE PILOT VEERED TO THE RT AND STRUCK A RUNWAY TAXI LIGHT.SDR CA100205003Bulkhead · cracked(CAN) SMALL HAIRLINE CRACKS DISCOVERED ON THE FWD SPINNER BULKHEAD AROUND 3 OF THE 6 BOLT HOLES THAT SECURE THE PROPELLER TO THE ACFT. (TC 20100205003)SDR CA100205002Muffler · cracked(CAN) CRACKED MUFFLER AT TAIL PIPE TO CAN WELD. FOUND WHEN SHINING A LIGHT THROUGH SMALL HOLE FOUND ON TAILPIPE SUPPORT. (TC 20100205002)SDR CA100122008Bulkhead · cracked(CAN) WHILE DOING A 200HR INSP, AME NOTICED THAT THE SPINNER SCREWS WERE LOOSE AND THE SPINNER WAS CRACKED. SPINNER WAS REMOVED AND IT WAS NOTICED THAT THE REAR BULKHEAD WAS CRACKED BY THE PROP BLADE. THIS WAS THE NEW STYLE OF SPINNER AND REAR BULKHEAD - HEAVISDR 2010FA0000018Connector · burnedLANDING & TAXI LIGHTS INOP ON PRE-FLIGHT. FOUND COWLING CONNECTOR ASSY, COMPRISING PN S1637-3 & -4, PLUS POWER WIRE AND CONNECTOR PINS BURNED AND CONNECTOR MELTED. REPLACED CONNECTOR AND REMOVED BURNED POWER WIRE. OPS CHECK SAT. THIS CONDITION IS CAUSED BYSDR 2009FA0000980Gear · looseCUSTOMER COMPLAINED OF DEAD LT MAGNETO ON GROUND RUN UP. REMOVED AND OPENED MAGNETO HSG TO FIND A LOT OF DUST. UPON INVESTIGATION, DISCOVERED THAT ROTOR GEAR HAD MOVED UP ON ITS SHAFT AND RUBBED DISTRIBUTOR GEAR HSG. CALLED SERVICE SUPPORT, THEY TOLD US THASDR CA091021005Torque Tube · damaged(CAN) DURING A SCHEDULED ENGINE CHANGE IT WAS DISCOVERED THAT PAN ASSEMBLY P/N 0513109-4 WAS BUCKLED. AIRCRAFT WAS TAKEN TO CONVAIR AVIATION LTD FOR REPAIRS. ONCE THE FIREWALL WAS REMOVED FURTHER DAMAGE TO THE INTERNAL STRUCTURES WAS DISCOVERED AS FOLLOWS: FOUSDR CA090915008Alternator · failed(CAN) CHARGING SYSTEM WARNING LIGHT CAME ON IN FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE ALTERNATOR AND GROUND TESTED SERVICEABLE. THE AIRCRAFT WAS RELEASED BACK TO SERVICE. (TC# 20090915008)SDR 2009FA0000506Carburetor · looseTHE CARBURETOR HALVES ARE BECOMING LOOSE DUE TO THE IMPROPER INSTALLATION OF THE LOCKTAB WASHERS AT OVERHAUL. THE LOCKTABS ARE BENT DOWN ON THE "TIGHTEN" SIDE OF THE CORNERS OF THE CARBURETOR WHICH ALLOWS THE BOLTS TO LOOSEN APPROX .2500 TURN WITHOUT DISTURBISDR CA090331007Regulator · failed(CAN) ALTERNATOR QUIT CHARGING - REPLACED VOLTAGE REGULATOR AND THAT FIXED IT.SDR CA090304007Rotor · misinstalled(CAN) MAG WAS RECEIVED FOR PROP STRIKE INSP ON AN ENG. WHEN DISASSEMBLED ROTOR GEAR WAS WORN ON TOP EDGE OF THE TEETH WHERE THE DISTRIBUTOR GEAR SITS DOWN ON THIS EDGE. DISTRIBUTOR GEAR TEETH WERE WORN AT THE BASE OF THE TEETH. CAUSE OF INTERFERENCE WAS DETERSDR CA090106009Spinner · cracked(CAN) FOUND DURING 100 HOUR INSPECTION, CRACK IS QUITE VISABLE TO THE NAKED EYE.SDR 2008FA0000884Discharge Tube · looseDURING 100 HR INSP, FOUND THE PUMP DISCHARGE TUBE ON A MA-4SPA LOOSE. THIS IS THE THIRD SUCH FIND. OTHER ACFT HAVE HAD THE PUMP DISCHARGE TUBE MISSING AND FOUND AT THE BOTTOM OF THE CARB AIRBOX.SDR CA081215004Bulkhead · cracked(CAN) CRACKS PERPENDICULAR TO PROP BOLT HOLES READILY VISIBLE TO THE NAKED EYE.SDR CA081215003Spinner · cracked(CAN) CRACKS PERPENDICULAR TO TOP OF PROP BOLT HOLES BARELY VISIBLE TO THE NAKED EYE, CONFIRMED WITH LPI.SDR 2008FA0000649Magneto · seizedDURING FLIGHT, A SHUDDER AND SLIGHT LOSS OF POWER WAS REPORTED BY THE PILOT. PRIOR TO THE NEXT FLT DURING THE MAGNETO CHECK IT WAS DISCOVERED THAT THE LT MAGNETO WAS INOPERATIVE. FURTHER INVESTIGATION FOUND THE LT MAGNETO CONDENSER WAS OUT OF THE MAGNETO CASE SDR 2008FA0000287Cover · crackedFOUND ROCKER BOX COVER CRACKED DURING 100 HOUR INSPECTION. CRACKS CAUSED DUE TO IMPROPER CLEARANCE BETWEEN COVER AND ROCKER ARMS ALLOWING ROCKER ARMS TO CONTACT COVER. THERE IS A NOTABLE CLEARANCE DIFFERENCE BETWEEN AN ORIGINAL MFG COVER AND THE OTHER MFG CSDR 2008FA0000286Cover · crackedFOUND ROCKER BOX COVER WITH MULTIPLE CRACKS DURING AC FLEET INSPECTION, FOLLOWING DISCOVERY OF ANOTHER CRACKED COVER ON A DIFFERENT AC. CRACKS CAUSED, DUE TO IMPROPER CLEARANCE BETWEEN COVER AND ROCKER ARMS ALLOWING ROCKER ARMS TO CONTACT COVER. THERE IS A NSDR CA071128018Cable · broken(CAN) COMPLIED WITH SB07-5 PILOT SECONDARY SEAT STOP INSTALLATION. THE AIRCRAFT LEFT OUR SHOP SERVICABLE AND IN COMPLIANCE WITH THE SB. BROUGHT IT IN THE NEXT DAY TO DO UNSCHEDULED MAINT. LOOKING OVER THE JOB FOR A SECOND TIME FOUND THE THREADED PLASTIC END SDR FAA122707001Cylinder Head · crackedHEAD CAME OFF BARRELL OF CYLINDER P/N AEL65102 SN0.41 S/N 20255-13 1083.3 HOURS ON CYLINDER SINCE INSTRUCTION OF 10/5/04 (HEAD, BARRELL SEPARATED).SDR 2007FA1015001Starter Gen · making metalSTARTER BENDIX DRIVE HAS NOT BEEN FULLY RETRACTING AFTER ENGINE START AND HAS BEEN SCRAPING THE ENGINE STARTER RING GEAR, CAUSING WEAR ON STARTER RING GEAR AND BENDIX ENGAGEMENT GEAR. WHEN THE BENDIX DRIVE DOES NOT DISENGAGE FROM STARTER RING GEAR COMPLETELY,SDR CA071003008Bracket · worn(CAN) ON A 100 HOUR INSPECTION, MAINT DISCOVERED THE RUDDER PEDAL TORQUE TUBE SPRING ATTACHMENT BRACKET HOLE WAS WORN MORE THAN HALF THRU. THIS IS A HARD TO INSPECT AREA AT THE FWD TUNNEL CENTER SECTION UNDER THE DASH. THE BRACKET WAS REPLACED AND RUDDER RE-RISDR 2007FA0000824Fitting · crackedAC WAS BEING TAXIED FROM THE RAMP TO THE TAXIWAY, AND DURING TAXI, THE PILOTS REPORTED THAT THE NOSE GEAR STEERING SEEMED TO BE MALFUNCTIONING. UPON INSPECTION, THE NOSE GEAR STRUT APPEARED TO BE PRESSED UP AGAINST THE REAR HALF OF THE LOWER COWLING. THE LOWSDR 2007FA0000841Cylinder · failedDURING CRUISE FLIGHT, THE PILOT REPORTED A LOUD BANG FOLLOWED BY EXCESSIVE VIBRATION, INCREASED POWER TO FULL TO MAINTAIN ALTITUDE AND MADE A WELL-EXECUTED,, PRECAUTIONARY LANDING. AFTER SHUTDOWN THERE WAS A LARGE OIL PUDDLE DEVELOPING UNDER THE AIRCRAFT. AISDR CA070711005Seat · cracked(CAN) DEFECT REPORTED IN THE JOURNEY LOG BOOK THAT RT SEAT WOULD NOT ADJUST. REMOVED SEAT, INSPECTED, AND FOUND THE SEAT BOTTOM FRAME CRACKED COMPLETELY IN (2) PIECES. AREA IS DIFFICULT TO INSPECT BECAUSE OF UPHOLSTERY INSTALLATION. LOWEST TIME IN THE FLEETSDR CA070704007Bulkhead · cracked(CAN) BULKHEAD IS CRACKED AROUND SEVERAL OF THE PROP THROUGH BOLT HOLES. (TC NR 20070704007)SDR 2007FA0000658Vent · obstructedENGINE QUIT IN FLIGHT WITH HALF TANK OF FUEL REMAINING. UPON VISUAL INSPECTION OF LT WING, FOUND THE FUEL VENT LINE PN 052355912 OBSTRUCTED WITH INSET REMAINS (WASP). PHYSICALLY REMOVED OBSTRUCTION AND OPS TESTED ENGINE ON ALL TANK SETTINGS. UPON SUCCESSFULSDR CA070704008Bulkhead · cracked(CAN) CRACKED AROUND SEVERAL OF THE PROP BOLT THROUGH HOLES. (TC NR 20070704008)SDR CA070517002Engine · failed(CAN) INTERMITTENT VIBRATION AFTER UNUSUAL FLIGHT ATTITUDES DURING TRAINING. (TC NR 20070517002)SDR CA070313002Bulkhead · cracked(CAN) THIS AIRCRAFT HAS HAD ALL THE AFT BULKHEAD AND HEAVIER SPINNER UPGRADES AND HAS HAD IT ALL ASSEMBLED IAW THE LATEST SB. CRACKS WERE FOUND FORMING PARALLEL FROM THE PROP BOLT HEAD CONTACT SURFACE ON (3) OF THE (6) HOLES. YOU HAVE TO LOOK VERY CAREFULLY ASSDR CA070517003Control Wheel · failed(CAN) EXCESSIVE PLAY IN (U) JOINT ON LT CONTROL WHEEL. (TC NR 20070517003)SDR CA070517004Pump · failed(CAN) LOSS OF VACUUM DURING START-UP. (TC NR 20070517004)SDR 2006FA0000939Hose · failedINVESTIGATION INTO FAILED ATTITUDE INDICATOR ON LISTED AIRCRAFT FOUND APPARENT CAUSE OF FAILURE TO BE FROM CONTAMINATION FROM DISINTEGRATING VACUUM HOSE. THE HOSES IN QUESTION ARE MARKED B906 AND B904 HOSE. TO PREVENT RECURRENCE, SB SEB96-10 SHOULD BE ACCOMPSDR 2006FA0000785Motor · shortedLIGHT WEIGHT STARTER MOTOR FAILED (SHORTED INTERNALLY) AFTER 1.5 YEARS SERVICE. (K)SDR CA060724007Bulkhead · cracked(CAN) THIS BULKHEAD HAS CRACKS DIRECTLY ABOVE THE BOLT HOLES APPROXIMATELY ONE INCH LONG RADIALY ALONG THE INNER BEND RADIUS ABOVE THE BOLT HOLE BUT NOT INTERSECTING THE BOLT HOLE. (TC NR 20060724007)SDR CA060724006Bulkhead · cracked(CAN) THIS BULKHEAD HAS CRACKS DIRECTLY ABOVE THE BOLT HOLES APPROXIMATELY ONE INCH LONG RADIALY ALONG THE INNER BEND RADIUS ABOVE THE BOLT HOLE BUT NOT INTERSECTING THE BOLT HOLE. (TC NR 20060724006)SDR CA060711007Bulkhead · cracked(CAN) THIS FORWARD SPINNER BULKHEAD HAS BEEN IN SERVICE WITH THE ORIGINAL (THIN MATERIAL) SPINNER. THE BULKHEAD HAS CRACKS TO 1.25 INCHES ACROSS EACH/ALL 6 PROP BOLK HOLES. (TC NR 20060711007)SDR CA060711006Cylinder Head · cracked(CAN) THIS IS CYL NR 4 IN 100HRS. THE PREVIOUS 3 CYLINDERS EXHIBITED THE SAME TYPE AND LOCAL OF CRACKS. THIS CYLINDER HAS A ONE AND A HALF INCH LONG CRACK AT THE OUTER MOST EXHAUST FLANGE STUD MOVING TOWARDS THE EXHAUST VALVE SEAT. ALSO A CRACK BEGINNING AT THSDR CA060711005Cylinder Head · cracked(CAN) THIS THE 3RD CYLINDER IN 100 HOURS IS CRACKED THE SAME AS THE PREVIOUS 2. CRACKED APPROXIMATLY 30 PERCENT AROUND THE CYLINDER HEAD. CRACKED FROM THE OUTER MOST EXHAUST FLANGE STUD ROUGHLY 2 OR 3 INCHES TO THE EXHAUST VALVE SEAT. THEN CRACK CONTINUING FROSDR CA060630004Seat · cracked(CAN) INSPECTION OF SEAT FRAME ASS`Y DURING SCHEDULED MAINTENANCE REVEALED A CRACKED SUPPORT LEG. SAFETY OF SEAT ASS`Y MAY BE COMPROMISED DUE TO THE WEAKENED SUPPORT LEG. (TC# 20060630004)SDR CA060630002Stop · cracked(CAN) DURING A ROUTINE SEAT REMOVAL PROCEDURE IT WAS NOTICED THAT THE SEAT STOP WAS BROKEN APART AROUND THE FASTENING SCREW HOLE. THERE IS NOT MUCH MATERIAL BETWEEN THE SCREW HOLE AND THE EDGE OF THE STOP WHICH COULD HAVE LED TO A FAILURE OF THIS AFT POSITIONESDR CA060608002Cylinder · crackedOIL LEAK FOUND COMING FROM ENGINE COWLING. AFTER FURTHER INVESTIGATION A CRACK WAS DISCOVERED IN THE NR 2 CYLINDER BARREL.SDR CA060509006Cylinder Head · cracked(CAN) ONE CRACK RUNNING BETWEEN UPPER SPARK PLUG HOLE AND EXHAUST VALVE. SECOND CRACK FROM LOWER SPARK PLUG HOLE EXTENDING APPROX 1 INCH INTO CYL HEAD. (TC NR 20060509006)SDR 2006FA0000494Air Box · maint errorAC HAD 180 HP ENGINE INSTALLED ON 7/10/96. AC HAS 1443.5 HOURS SINCE INSTALLATION. OPERATOR NOTED 2300 RPM AT CRUISE, FULL THROTTLE. INSPECTED AND FOUND AIRBOX STILL HAD THE HOLE SIZE FOR 160 HP ENGINE. AIRBOX HAD NOT BEEN MODIFIED IAW STC. IT HAD BEEN REPSDR CA060228013Switch · seizedUPON APPROACH TO LAND, PILOT TURNED ON LANDING LIGHT AND OBSERVED A SMALL AMOUNT OF SMOKE COMING FROM THE SWITCH AND WAS UNABLE TO TURN THE SWITCH OFF DUE TO IT SEIZING IN THE 'ON' POSITION. TURNED OFF THE AIRCRAFT MASTER SWITCH INSTEAD AND LANDED SAFELY. THSDR CA051123002Bearing · stiff(CAN) ROTOR BEARINGS ROUGH AND SHAFT HARD TO TURN. MAGNETO WOULD NOT TURN FAST ENOUGH TO START ENGINE.SDR 053006Drive Assy · failedON ENGINE START, STARTER DRIVE DID NOT DISENGAGE AND THE DRIVE GEARS SHEARED OFF, DAMAGING THE ENGINE RING GEAR. THE PILOT DID NOT DETECT THE FAILURE UNTIL LANDING AND TRYING TO RESTART THE ENGINE.SDR CA051102007Skin · cracked(CAN) OPENED LEADING EDGE OF RT FLAP SKIN FOR REPAIR. VISUALLY NOTICED CRACKED CENTER LEADING EDGE RIB AT BOLT HOLE FOR FLAP ACUATING PUSH ROD BRACKET ATTACHMENT. OUTER LEADING EDGE SKIN NOT DAMAGED AT THIS LOCATION.SDR 2005FA0001631Support Bracket · crackedWING T/E SKIN SUPPT BRACKET CRACKED IN BEND RADIUS. LOCATION OF CRACKED PART IS IB SIDE OF RT FLAP TRACK RIB AT STA 39. PART HAS .2500 INCH CRACK FROM L/E OF TAB AFT, ANOTHER CRACK IN SAME BEND RADIUS .7500 INCH FROM T/E OF TAB FWD. BEND RADIUS CRACK IS UND
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