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 = '172M' 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 = '172M' 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 CA970523005Control Cable · broken(CAN) CARBURETOR HEAT CABLE BROKE OFF 3 INCHES FROM KNOB DURING GROUND CHECK. REPLACED.SDR 97ZZZX2099Bulkhead · misinstalledVERTICAL FIN AFT SPAR TO BULKHEAD CLEARANCE EXCESSIVE. MAXIMUM CLEARANCE .070 INCH PER CESSNA 172 SM. P/N 0512159-3 INSTALLED INCORRECTLY OR MACHINED INCORRECTLY BY FACTORY AT LOWER HOLE MACHINE FACE. MISSING .090 INCH OF MATERIAL. FIXED BY INSTALLING .090SDR AU970537Bulkhead · cracked(AUS) LOWER AFT DOOR POST BULKHEAD CRACKED - FOUND DURING INSPECTION IAW CESSNA SEB 97-1SDR CA970429012Wheel · cracked(CAN) WHILE PERFORMING AN INSPECTION THE AME FOUND BOTH WHEEL ASSEMBLIES TO HAVE CRACKS PROPAGATING FROM EACH BOLT HOLE.SDR 97ZZZX1976Frame · crackedFOUND BOTH AFT LOWER DOOR POST FRAMES CRACKED WHILE C/W SEB 97-1. INSTALLED SK172-149-1 AND SK172-149-2 TO REPAIR. INSTRUCTIONS CALL FOR THIS TO BE A 1,000 HOUR REPETITION INSPECTION. SUBMITTER STATED THAT IS MUCH TOO LONG. SHOULD BE INCLUDED ON EACH ANNUASDR CA970428011Brake · cracked(CAN) RIGHT BRAKE HOUSING CRACKED. REPLACED.SDR CA970421073Blade · stone damage(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE ON LEADING EDGE AND FACE.SDR CA970409003Door Post · cracked(CAN) AIRCRAFT WAS INSPECTED AS PER SEB 97-1. INSPECTION FOUND CRACKS ON BOTH THE RIGHT HAND AND LEFT HAND LOWER AFT DOOR POSTS AS STATED IN THE SERVICE BULLETIN. AIRCRAFT WAS GROUNDED UNTIL MODIFICATIONS CAN BE COMPLETED AS PER CESSNA SK 172-149.SDR CA970401008Filler Tube · cracked(CAN) SMALL AMOUNT OF FUEL STAIN NOTED AT INBOARD LOWER TRAILING EDGE OF RIGHT HAND WING. USUALLY OCCURRED AFTER FILLING TANK. INSPECTION FOUND A CRACK IN THE WELD AT THE FILLER TUBE.SDR 97ZZZX1197Hub · wornWHEN NOSE WHEEL WAS REMOVED TO GREASE BEARINGS, DISCOVERED THAT BEARING CUP (KOYO MFG) WAS LOOSE IN WHEEL HUB. WHEEL HUB WAS WORN WHERE CUP HAD BEEN SPINNING IN HUB. THE CUP IS NORMALLY A PRESS FIT INTO THE WHEEL. A/C HAD NOSE WHEEL SHIMMY COMPLAINT PRIOR TOSDR 97ZZZX1196Switch · corrodedDURING ANNUAL INSPECTION, DISCOVERED WIRE TERMINAL AT LANDING LIGHT SWITCH PARTIALLY MELTED CAUSED BY INCREASED RESISTANCE DUE TO CORRODED WIRES AT TERMINAL. REPLACED TERMINALS. FOUND SIMILAR CONDITION ON 1 OTHER TYPE A/C.SDR 97ZZZX1226Switch · failedPILOT OBSERVED HIGH DISCHARGE RATE ON AMMETER APPROXIMATELY 45 MINUTES INTO FLIGHT. NO HIGH VOLTAGE LIGHT INDICATION. PILOT MADE PRECAUTIONARY LANDING. REPLACED OVERVOLTAGE LIGHT ASSEMBLY AND OVERVOLTAGE SWITCH. ALL OTHER COMPONENTS BENCH CHECKED WITH NO DISDR AU970214Magneto · failed(AUS) MAGNETO FAILED - INSPECTION FOUND HT COIL SECONDARY WIRING OPEN CIRCUITSDR AU970156Adapter · corroded(AUS) LH AND RH ELEVATOR TORQUE TUBE ADAPTERS CONTAINED SEVERE CORROSION BETWEEN ADAPTERS AND INBOARD RIBS - FLANGES ON ADAPTERS CRACKED DUE TO CORROSIONSDR 97ZZZX175Lifter · spalledFERROUS METAL FOUND IN OIL SCREEN AT INSPECTION. AFTER FURTHER INVESTIGATION, FOUND ALL 4 INTAKE LIFTER BODIES SEVERELY SPALLED AND THE 2 CAM LOBES THAT OPERATE THEM WORN.SDR CA970326007Windshield · distorted(CAN) NEW WINDSHIELD ORDERED. WINDSHIELD FOUND UNACCEPTABLE BY CUSTOMER. DISTORTION PREVENTED CLEAR VIEW. A SECOND WINDSHIELD ORDERED WAS ALSO FOUND UNACCEPTABLE DUE TO DISTORTION P/N 0513230-12.SDR 96ZZZX5875Drive Assy · defectiveWHILE C/W AD 960910C, IT WAS DISCOVERED AD 75-8-9R3 HAD NOT BEEN C/W. (REQUIRED REPLACEMENT OF DRIVE ASSY 75288 WITH DRIVE ASSY PN 61174) A CHECK OF AD 75-8-9R3 AND RELATED SB. ENG S/N WAS NOT LISTED. AD APPLICABLE TO S/N 33229-27A TO 41054-27A. NO RECORD SDR 96ZZZX5589Saf T Stop · misuseTHE SAF-T-STOP ITSELF IS NOT THE PROBLEM. IT IS THE WAY IT IS INSTALLED ON SEAT RAILS. OWNERS AND OPERATORS ARE USING THE SAF-T-STOP FOR PRIMARY SEAT STOPS EVEN THOUGH INSTRUCTIONS STATE OTHERWISE. SUBMITTER STATES ONLY FIX IS TO REMOVE PRODUCT FROM SERVICESDR 96ZZZX5407Tire · rubs caliperBRAKE CALIPER DRAGS WHEN TIRE INSTALLED ON AIRCRAFT. MEASURED LEFT AND RIGHT HAND TIRE SIDEWALL WHEN PRESSURED TO 28 PSI. LEFT TIRE SIDEWALL 1.25 INCH WIDER THAN RIGHT TIRE.SDR CA961007011Control Cable · frayed(CAN) ELEVATOR CABLE FOUND FRAYED AT THE REAR UPPER FUSELAGE PULLEY.SDR CA961009009Track · cracked(CAN) FLAP TRACK FOUND CRACKED ON THE INBOARD SIDE, PROBABLY DUE TO A DEFECTIVE ROLLER BEARING.SDR 96ZZZX4955Hub · crackedINSPECTION FOUND HUB CRACKED 2 PLACES.SDR 96ZZZX4752Hub Assy · crackedFOUND ON TIRE CHANGE, HUB ASSY HAS 4 CRACKS ON ONE SIDE AND TWO CRACKS ON THE BACK SIDE. ALL CRACKS ARE AT BOLT HOLES.SDR 96ZZZX4091Control Cable · deterioratedINSPECTION FOUND THROTTLE OUTER CABLE HOUSING VERY DETERIORATED DUE TO AGE/HEAT EXPOSURE. INNER HOUSING LOOSE AT FORWARD END, ABOUT TO SEPARATE. SUBMITTER STATED IF NOT CORRECTED, LOSS OF THROTTLE CONTROL AND ENGINE POWER WILL RESULT. THIS IS THE SECOND REPSDR 96ZZZX4055Axle Nut · misinstalledDURING GROUND TAXI OPERATIONS, THE RT AXLE NUT SEPARATED FROM THE AXLE. UPON RETURN FROM FLIGHT, THE NUT WAS FOUND MISSING BY THE PILOT. THE AXLE NUT WITH COTTER PIN INSTALLED WAS RECOVERED BY UNKNOWN PERSONS. THE WHEEL WAS DISASSEMBLED, INSPECTED, AND RE-ASDR 96ZZZX4315Connectiing Rod · bolt failedENGINE FAILED IN-FLIGHT WITH LOUD BANG. AIRPLANE FORCE LANDED ON ROAD. INSPECTION REVEALED NR 1 CYLINDER ROD HAD COME LOOSE FROM CRANK AND PUNCHED HOLE IN BOTTOM OF CASE. INSPECTION OF ENGINE FOUND CONNECTING ROD BOLTS, P/N 78027, ON NR 1 AND NR 4 CYLINDERSSDR AU961093Camshaft · worn(AUS) CAMSHAFT EXHAUST VALVE LOBES AND ASSOCIATED TAPPETS PNO 72877 WORN - WEAR WAS BETWEEN 4.572MM AND 5.08MM (0.180IN AND 0.200IN)SDR 96ZZZX3528Coil · failedENGINE SUDDENLY BECAME ROUGH. MAG CHECK INDICATED TROUBLE WITH RIGHT MAG, FLIGHT CONTINUED ON SINGLE MAG. OPERATION - AT TERMINATION OF FLIGHT, MAGS RE-CHECKED. RT MAG DEAD; OPENING UP MAG REVEALED 'BEARING' GREASE IN MAG HOUSINGS. COIL APPEARED INTACT, BUSDR 96ZZZX3527Bearing · roughENGINE SUDDENLY BECAME ROUGH. MAG CHECK INDICATED TROUBLE WITH RIGHT MAG, FLIGHT CONTINUED ON SINGLE MAG. OPERATION - AT TERMINATION OF FLIGHT, MAGS RE-CHECKED. RT MAG DEAD; OPENING UP MAG REVEALED 'BEARING' GREASE IN MAG HOUSINGS. COIL APPEARED INTACT, BUSDR 96ZZZX5300Bolt · bentDURING ANNUAL INSPECTION AND INSTALLATION OF WHEEL PANTS, FOUND AN5-47A BOLT BENT AFTER REMOVAL. THIS BOLT RETAINS THE FORK TO THE LOWER BARREL AND SECURES THE PIN BASE PLUG IN PLACE. SUBMITTER SUSPECTS CAUSE IS HIGH TOTAL TIME WITH POSSIBLY HARD LANDINGSSDR CA960620002Regulator · malfunction(CAN) DURING RUN-UP FOR OIL CHANGE THE ALTERNATOR SWITCH WAS CYCLED AND THE AMMETER SHOWED A FULL CHARGE. IN THE 'ON' POSITION A NORMAL RATE OF CHARGE WAS NOTED. WITH THE MASTER IN THE 'OFF' POSITION THE PANEL LIGHTS BECAME VERY BRIGHT. THE AUTOMOTIVE VOLTAGE SDR 97ZZZX679Switch · malfunctionTHE AIRPLANE CRASHED 18-19 SECONDS AFTER BECOMING AIRBORNE. THE AIRCRAFT IMPACTED TERRAIN BEYOND THE DEPARTURE END OF THE RUNWAY. FLAPS WERE FULLY DOWN AT THE ACCIDENT SCENE. THE FLAP SWITCH WAS REMOVED AND SENT TO CESSNA FOR FUNCTIONAL TESTING. THIS SWITCSDR 96ZZZX3332Stiffener · corrodedUPON ANNUAL INSPECTION, RT WING STRUT LOWER AFT BULKHEAD STIFFENER WAS FOUND WITH SURFACE CORROSION (RUST) ON LOWER 60 PERCENT OF PART. AIRCRAFT HANGARED ON FARM STRIP AND HAS HAD RODENT (MICE) PROBLEMS IN THE PAST. DROPPINGS AND ODOR ACCOUNT FOR THIS. COMBSDR 96ZZZX3219Filter Assy · defectiveIN C/W AD 96-09-06 TO REPLACE BRACKETT FILTER ASSY, NEW OUT-OF-BOX INSPECTION FOUND GLUE USED FOR GASKET ON BACK SIDE OF MESH SCREEN. REMOVED DRIED GLUE MATERIAL AND INSTALLED. SUBMITTER STATED THIS I.A. HAS FOUND NEW PARTS INFERIOR IN QUALITY CONTROL. JUSTSDR AU960621Rib · cracked(AUS) FUSELAGE RIB LOCATED AT STN 81 IN AREA OF REAR SEAT FORWARD ATTACHMENT NUTS CRACKED LONGITUDINALLY IN SEVERAL PLACES - CRACK LENGTHS 50.8MM TO 76.2MM (2IN TO 3IN)SDR CA960524019Dowel · sheared(CAN)METAL CONTAMINATION IN THE OIL FILTER AT 50 HOUR INSPECTION. SOURCE OF METAL IS #3 CONROD BEARING AND #2 MAIN BEARING. MAIN BEARING DOWEL PIN SEHARED AND CAUSED F.O.D. TO MAIN AND CONROD BEARINGS. ALL MAIN BEARING DOWELS RENEWED.SDR 96ZZZX3066Sensor · defectiveOVERVOLTAGE SENSOR DEFECTIVE: NO POWER OUT ON ORANGE WIRE TO ALTERNATOR FIELD SWITCH TO ENERGIZE ALTERNATOR FIELDS - NO CHARGING.SDR CA960404005Stabilizer · cracked(CAN) INSPECTION PER SE 1394-8 FOUND SPAR AND SKIN CRACKED.SDR CA960404004Thermo Valve · loose nut(CAN)INSPECTION AS PER LYCOMING SB 518A FOUND NUT CRIMPED ONLY ON ONE SIDE AND EXTREMELY LOOSE.SDR 96ZZZX1707Ammeter · seizedAMMETER NEEDLE FROZEN. WOULD NOT SHOW ANY SIGN OF CHARGE OR DISCHARGE. NO LOW VOLTAGE INDICATOR ON 172M. 1975 MODEL SKYHAWK.SDR 96ZZZX1989Control Cable · frayedDURING ROUTINE ANNUAL INSPECTION, THE AILERON BALANCE CABLE WAS FOUND FRAYED WITH APPROXIMATELY 50 PERCENT OF THE STRANDS BROKEN. LOCATION OF THIS DEFECT WAS WHERE THE CABLE PASSED BY THE THREE NYLON CABLE PULLEYS IN THE CENTER FUSELAGE AREA, ACCESSED THROUGHSDR 96ZZZX877Skin · crackedLEFT HORIZONTAL STABILIZER HAD DAMAGE TO THE RIB AND THE LEADING EDGE. THE RIB HAD BEEN CRUSHED AND THE SKIN AT THE RIB HAD A SMALL CRACK. SUBMITTER STATED THIS DAMAGE DEVELOPED FROM THE IMPROPER HANDLING OF THE AIRCRAFT ON THE GROUND. ALL OTHER AREAS OF TASDR 96ZZZX876Rib · damagedLEFT HORIZONTAL STABILIZER HAD DAMAGE TO THE RIB AND THE LEADING EDGE. THE RIB HAD BEEN CRUSHED AND THE SKIN AT THE RIB HAD A SMALL CRACK. SUBMITTER STATED THIS DAMAGE DEVELOPED FROM THE IMPROPER HANDLING OF THE AIRCRAFT ON THE GROUND. ALL OTHER AREAS OF TASDR CA960115101Control Cable · frayed(CAN)DURING THE PREFLIGHT INSPECTION THE PILOT MOVED THE ELEVATOR AND HEARD A RUBBING NOISE AGAINST THE SKIN. INSPECTION REVEALED THE UPPER ELEVATOR CABLE WAS SEVERELY FRAYED AT THE AFT PULLEY LOCATION. TH E PULLEY WAS FOUND TO MOVE FREELY BUT HAD A SLIGHT GROSDR AU960199Control Cable · corroded(AUS) FLAP CABLES PNO 0510105-93 (2OFF) AND PNO 0510105-94 (2OFF) CORRODED - SUSPECT CAUSED BY POOR PREPARATION PRIOR TO PAINT STRIPPING - SEE MDR 96/0195 FOR ADDITIONAL INFORMATIONSDR AU960198Control Cable · corroded(AUS) ELEVATOR TRIM CABLES PNO 0510105-44 AND PNO 0510105-45 AND ELEVATOR CONTROL CABLES PNO 0510105-291 AND PNO 0510105-290CORRODED - SUSPECT CAUSED BY POOR PREPARATION PRIOR TO PAINT STRIPPING - SEE MDR 96/0195 FOR ADDITIONAL INFORMATIONSDR AU960197Spar · cracked(AUS) HORIZONTAL STABILIZER SKIN AND SPAR CRACKED IN AREA OF LIGHTENINGHOLE - FOUND DURING INSPECTION IAW CESSNA SERVICE BULLETIN SE94-8SDR AU960196Skin · corroded(AUS) VERTICAL STABILIZER LEADING EDGE SKIN PN 0531006-96 AND LEADING EDGE RIB PN 0531006-5 CORRODED IN AREA WHERE MASKED BY DORSAL FINSKIN - SUSPECT CAUSED BY INADEQUATE PROTECTION AND PROCEDURES DURING PAINT STRIPPING - PERSONNEL/MAINTENANCE ERROR - SEE MDSDR AU960195Control Cable · corroded(AUS) AILERON CABLES PNO 0501015-224 (2OFF) AND AILERON BALANCE CABLE PNO 0510105-13 (1OFF) CORRODED - TURNBARRELS PNO AN155B32L (1OFF), PNO AN155B165 (2OFF) AND PNO AN155B8L CORRODED - SUSPECT CAUSED BY POOR PREPARATION PRIOR TO PAINT STRIPPING AND THE USEOFSDR AU960104Spring · broken(AUS) RUDDER RETURN SPRING BROKEN
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