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 CA980928003Crankshaft · pitted(CAN) TO COMPLY WITH AD 98-02-08, IN ACCORDANCE WITH LYCOMING SERVICE BULLETIN 505B, PITTING WAS NOTED ON THE INTERNAL BORE OF THE CRANKSHAFT. FPI CARRIED OUT, NO CRACKS WERE FOUND.SDR 20000501SH012Hose · deterioratedOWNER/OPERATOR COMPLAINED OF ERRATIC VACUUM PRESSURE AFTER INSTALLATION OF NEW VACUUM PUMP AT ANOTHER FACILITY. UPON INSP OF VACUUM SYSTEM, FOUND ALL IMPERIAL EASTMAN HYTRON REDI-SEAL P/N B906 AND B903 HOSES INSTALLED IN THE VACUUM SYS HAD DETERIORATED INTERNSDR 20000501SH011Hose · deterioratedOWNER/OPERATOR COMPLAINED OF ERRATIC VACUUM PRESSURE AFTER INSTALLATION OF NEW VACUUM PUMP AT ANOTHER FACILITY. UPON INSP OF VACUUM SYSTEM, FOUND ALL IMPERIAL EASTMAN HYTRON REDI-SEAL P/N B906 AND B903 HOSES INSTALLED IN THE VACUUM SYS HAD DETERIORATED INTERNSDR CA980928001Crankshaft · pitted(CAN) TO COMPLY WITH AD 98-02-08, IN ACCORDANCE WITH LYCOMING SERVICE BULLETIN 505B, PITTING WAS NOTED ON THE INTERNAL BORE OF THE CRANKSHAFT. FPI CARRIED OUT, NO CRACKS WERE FOUND.SDR 98ZZZX3036Spar · crackedDURING ANNUAL INSPECTION, HORIZONTAL STABILIZER MAIN SPAR LEFT DOUBLER WAS FOUND CRACKED ONE-HALF OUTBOARD OF LEFT BUTT RIB. CRACK EXTENDED VERTICALLY INTO DOUBLER BEND RADIUS. DOUBLER WILL BE REPLACED PER CESSNA SEB94-8 WITH IMPROVED UNIT.SDR 98ZZZX3015Brake Cylinder · crackedDURING ANNUAL INSPECTION, BOTH BRAKE CYLINDERS WERE FOUND CRACKED AT UPPER CALIPER BOLT HOLE. BELIEVED CAUSED BY AGE (ORIGINAL EQUIPMENT) AND POSSIBLY PAST OVERTORQUE OF BOLTS. REPLACED BOTH ASSEMBLIES.SDR AU980844Skin · cracked(AUS) RIGHT WING UPPER SKIN CRACKED IN THREE PLACES ADJACENT TO THE RIVETS SECURING THE SKIN TO THE WING RIB AT STN 100.0. MAXIMUM LENGTH OF CRACKS 4 MM (0.157 INCHES). PART TOTAL CYCLES: 12,704.SDR AU980843Skin · cracked(AUS) LEFT WING UPPER SKIN CRACKED IN THREE PLACES ADJACENT TO THE RIVETS SECURING THE SKIN TO THE WING RIB AT STN 100.0. MAXIMUM LENGTH OF CRACKS 4 MM (0.157 INCHES). PART TOTAL CYCLES: 12,704.SDR AU980838Rib · corroded(AUS) LT AND RT WING NR 2 NOSE RIBS LOCATED AT STN 32.75 ADJACENT TO THE LEADING EDGE CABIN AIR DUCTS SEVERELY CORRODED. PART TOTAL CYCLES: 12,704.SDR AU980851Rib · corroded(AUS) LEFT AND RIGHT WING NR 2 NOSE RIBS LOCATED AT STN 32.75 ADJACENT TO THE LEADING EDGE CABIN AIR DUCTS SEVERELY CORRODED. PART TOTAL CYCLES: 12,650.SDR AU980849Skin · cracked(AUS) RIGHT WING UPPER SKIN CRACKED IN TWO PLACES IN AREA ADJACENT TO RIVETS ATTACHING SKIN TO WING RIB AT STN 100.0. MAXIMUM CRACK LENGTH 3MM (0.118 INCHES). PART TOTAL CYCLES: 12,650.SDR AU980848Skin · cracked(AUS) LEFT WING UPPER SKIN CRACKED IN THREE PLACES IN AREA ADJACENT TO RIVETS SECURING THE SKIN TO WING RIBS AT STN 100.0. CRACK LENGTHS 4 MM (0.157 INCHES). PART TOTAL CYCLES: 12,650.SDR CA980623008Blade · damaged(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE FOUND ON THE LEADING EDGES OF THE BLADES. SUBMITTER STATED THE BLADES WERE FOUND TO BE BELOW THE MINIMUM WIDTH, THE PROPELLER WAS RETURNED TO THE CUSTOMER AS IS.SDR 98ZZZX3485Valve · crackedWHILE REPLACING FLOAT AND LEVER ASSY, FOUND RUBBER TIP OF FLOAT VALVE CRACKED AND DETERIORATED. REPLACED UNIT.SDR 98ZZZX3484Float · failedPILOT REPORTED ENGINE RUNNING ROUGH. FOUND FUEL DRIPPING FROM CARBURETOR HEAT BOX. DISASSEMBLY OF CARBURETOR REVEALED BRASS FLOAT HAD LEAKED AND SUNK RESULTING IN EXTREME RICH MIXTURE. REPLACED FLOAT ASSEMBLY.SDR 98ZZZX1997Shaft · brokenREMOVED SUCTION SCREEN FOUND CHUNK OF METAL. REMOVED MAGS, LEFT IDLER GEAR 'LOOSE'. REMOVED ACCESSORY CASE, SHAFT-CRANKSHAFT IDLER BASE BROKEN.SDR CA980507008Blade · damaged(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. CORROSION AND STONE DAMAGE WAS FOUND ON THE PROPELLER BLADES.SDR 98ZZZX2158Gear · misdrilledWHILE COMPLETING SERVICE KIT SK172-37 ON THE AIRCRAFT'S RT MAIN GEAR LEG, IT WAS DECIDED TO CHANGE THE LEG WITH A NEW ONE. INSTALLING THE NEW LEG REVEALED THAT THE BOLT HOLE, FOR MOUNTING THE LEG TO THE AIRFRAME, WAS MISDRILLED AND WOULD NOT ALLOW THE BOLT TOSDR CA980819004Crankshaft · pitting(CAN) PITTING CORROSION FOUND DURING INSPECTION IN ACCORDANCE WITH AD 98-02-08. LIQUID PENETRANT INSPECTION CARRIED OUT. NO CRACKS EVIDENT. CRANKSHAFT IS ON 100 HOUR RE-INSPECTION CYCLE.SDR CA980819002Crankshaft · pitting(CAN) PITTING CORROSION FOUND DURING INSPECTION IN ACCORDANCE WITH AD 98-02-08. LIQUID PENETRANT INSPECTION CARRIED OUT. NO CRACKS EVIDENT. CRANKSHAFT IS ON 100 HOUR RE-INSPECTION CYCLE.SDR 98ZZZX1675Valve Guide · defectiveON TAKEOFF, A MOMENTARY ENGINE ROUGHNESS PROMPTED THE PILOT TO ABORT TAKEOFF. THE AIRCRAFT EXCEEDED RUNWAY LENGTH AND STRUCK AN ANTENNA. INSPECTION OF THE ENGINE REVEALED A BUILD-UP OF CARBON IN THE NR 3 EXHAUST VALVE GUIDE. NOTE: ALL EXHAUST VALVE GUIDES SDR 98ZZZX1624Control Cable · frayedDURING INCORPORATION OF SK 172-149 KIT TO C/W SB 97-1, FOUND RT AILERON DIRECT CABLE FRAYED WHERE IT TRAVELS UNDER THE RT OUTBOARD PULLEY LOCATED AT THE LOWER AFT DOOR FRAME AREA. THIS IS A VERY DIFFICULT AREA TO INSPECT DURING ROUTINE INSPECTIONS. THE FRAYISDR CA980415020Cylinders · failed(CAN) ON APPROACH, THE ENGINE EXPERIENCED POWER LOSS, WITH ENGINE PERFORMANCE DETERIORATING THE ENGINE FAILED AND THE AIRCRAFT GLIDED TO A SAFE LANDING. POST-FLIGHT ENGINE COMPRESSION TEST REVEALED ALL FOUR CYLINDERS HAD LOW COMPRESSION. THE CYLINDERS AND PISSDR 98ZZZX1284Fuel Line · cutIMPROPERLY INSTALLED FUEL LINE RUBBING ON RUDDER CABLE CAUSING MAIN FUEL SUPPLY TO BE CUT COMPLETELY OFF. SUBMITTER STATED INSTALLATION APPEARS TO BE FACTORY.SDR CA980819003Crankshaft · pitting(CAN) PITTING CORROSION FOUND DURING INSPECTION IN ACCORDANCE WITH AD 98-02-08. LIQUID PENETRANT INSPECTION CARRIED OUT. NO CRACKS EVIDENT. CRANKSHAFT IS ON 100 HOUR RE-INSPECTION CYCLE.SDR 98ZZZX1448Valve Seat · damagedDURING AIRCRAFT RUN-UP, THE PILOT NOTICED THE ENGINE WAS RUNNING ROUGH. THE MECHANIC PULLED A COMPRESSION CHECK AND FOUND THAT NR 3 CYLINDER HAD NO COMPRESSION. FURTHER INVESTIGATING AND CYLINDER REMOVAL SHOWED THE EXHAUST VALVE SEAT INSIDE THE CYLINDER HAD SDR 98ZZZX1332Spar · buckledUNDER SIDE OF RIGHT STABILIZER DAMAGED AT THIRD RIB OUTBOARD OF CENTER OF STABILIZER RESULTING IN RIB BUCKLING AND ALSO FORWARD SPAR AT CENTER LIGHTENING HOLE BUCKLED AND CRACKED IN THE WEB. DAMAGE POSSIBLY CAUSED BY GROUND HANDLING OF AIRCRAFT. DAMAGE FOUNDSDR 98ZZZX1331Rib · buckledUNDER SIDE OF RIGHT STABILIZER DAMAGED AT THIRD RIB OUTBOARD OF CENTER OF STABILIZER RESULTING IN RIB BUCKLING AND ALSO FORWARD SPAR AT CENTER LIGHTENING HOLE BUCKLED AND CRACKED IN THE WEB. DAMAGE POSSIBLY CAUSED BY GROUND HANDLING OF AIRCRAFT. DAMAGE FOUNDSDR 98ZZZX1322Spinner · crackedDURING A 100-HOUR INSPECTION, THE SPINNER, PN 0550236-13, WAS FOUND CRACKED AT THE BLADE OUTLET JUST AFT OF THE FORWARD BULKHEAD, PN 0550321-4. FURTHER INSPECTION REVEALED THE FORWARD BULKHEAD HAD SEVERAL CRACKS UNDER THE MOUNTING BOLT HEAD WASHERS.SDR 98ZZZX1321Spinner · crackedDURING A 100-HOUR INSPECTION, THE SPINNER PN 0550236-13, WAS FOUND CRACKED AT THE BLADE OUTLET JUST AFT OF THE FORWARD BULKHEAD, PN 0550321-4. NO OTHER DEFECTS NOTED.SDR 98ZZZX1554Hose · deterioratedVACUUM SYSTEM HOSE BELIEVED TO BE FACTORY INSTALLED HAD A VACUUM LEAK. TROUBLESHOOTING, HOSE APPEARED OK UNTIL WIGGLED BY HAND. CRACKS IN HOSE APPEARED AND INTERNAL HOSE MATERIAL DISINTEGRATED.SDR AU980408Bulkhead · cracked(AUS) LT AND RT LOWER AFT DOOR POST BULKHEADS (PN 0512187-1 LT AND PN 0512187-2 RT) CRACKED. FOUND DURING INSPECTION IAW SB SEB 97-1. PART TC: 5,920.SDR AU980301Bulkhead · cracked(AUS) FUSELAGE AFT DOOR POSTS P/N 0512187-1 (LT) AND P/N 0512187-2 (RT) CRACKED. FOUND DURING INSPECTION IAW CESSNA SB SEB 97-1.SDR AU980302Bulkhead · cracked(AUS) FUSELAGE LOWER AFT DOOR POST BULKHEADS P/N 0512187-1 AND P/N 0512187-2 CRACKED. FOUND DURING INSPECTION IAW CESSNA SB SEB97-1.SDR 98ZZZX832Hinge · crackedDURING PRE-FLIGHT INSPECTION, LEFT CABIN DOOR, LOWER FORWARD HINGE WAS FOUND CRACKED. REPLACED HINGE HALF.SDR CA980311006Exhaust Valve · stuck(CAN) IN CRUISE AT 2,400 RPM THE ENGINE ABRUPTLY LOST 200 RPM AND BEGAN TO RUN VERY ROUGH. AFTER LANDING THE FAULT COULD NOT BE DUPLICATED. SUSPECT EXHAUST VALVE(S) STICKING INTERMITTENTLY. LYCOMING SERVICE BULLETIN 388B CARRIED OUT. ALL EXHAUST VALVE GUIDES WSDR 98ZZZX443Pitot Tube · leakedPILOT REPORTED LOW AIRSPEED INDICATION. PITOT SYSTEM WAS PRESSURE CHECKED AND FOUND TO HAVE A LEAK. FOUND PITOT HEAT WIRING CHAFED/MELTED INTO PITOT PRESSURE TUBE APPROXIMATELY 3 INCHES ABOVE CONNECTOR. REPLACED TUBING AND SYSTEM PITOT HEAT WIRING SECURED ASDR 98ZZZX472Drain Valve · leakingFUEL DRAIN VALVE HAS DEFECTIVE O-RING ON SEAT CAUSING SEVERE LEAK.SDR 98ZZZX1127Cylinder · failedFOLLOWING 45 MINUTES OF FLIGHT, ENGINE BECAME ROUGH. CARBURETOR HEAT APPLIED, BUT ROUGHNESS THE SAME. APPLIED FULL POWER AND RETURNED AND ON SHORT FINAL, TOWER REPORTED HEAVY SMOKE. INSPECTION FOUND ENGINE HAD ONLY 3 QUARTS OF OIL LEFT. NR 1 CYLINDER PISTOSDR 97ZZZX5197Spinner · crackedFATIGUE CRACK FOUND IN PROPELLER SPINNER. 45 HOURS TT.SDR 97ZZZX5196Spinner · crackedFATIGUE CRACK FOUND IN PROPELLER SPINNER. 35 HOURS TT.SDR 97ZZZX5127Disc · overheatedUPON INSTALLATION OF NEW CLEVELAND BRAKE DISC AND LININGS ON RT MAIN WHEEL, ACFT WAS TAXIED FOR RUN-UP AND LOUD SQUEELING EMITTED FROM RT BRAKE. PAINT ON DISC DAMAGED LININGS AND CAUSED OVERHEATING. REMOVED PAINT FROM DISC WHERE PADS RIDE, INSTALLED NEW LINISDR 97ZZZX4583Elt · failed testELT FAILED G-FORCE TEST REQUIRED BY FAR 91.207D. ONLY VERY HARD BLOWS WITH A HAMMER WOULD ACTIVATE G-SWITCH. MANUAL OPERATION OF THE ELT WAS NORMAL AND NO CORROSION WAS FOUND.SDR 97ZZZX4451Hose · deterioratedVACUUM SYSTEM SHOWED LOW VACUUM. PER MM, PUMP REMOVED AND CHECKED SATISFACTORILY. VACUUM REGULATOR REPLACED. SYSTEM STILL LOW. INSTRUMENT PANEL REMOVED AND SPECIAL REINFORCED HOSE TO AND FROM REGULATOR FOUND TERRIBLY DECOMPOSED AND SIMPLY TOUCHING IT WOULDSDR 97ZZZX3901Skin · crackedUPON INSPECTION PER SB 94-8-A, THE SKIN WAS FOUND CRACKED. THE SKIN AND REINFORCEMENT WERE REPLACED WITH NEW PARTS. NO OTHER PROBLEMS FOUND.SDR 97ZZZX3900Reinforcement · crackedUPON INSPECTION PER SB 94-8-A, THE SKIN WAS FOUND CRACKED. THE SKIN AND REINFORCEMENT WERE REPLACED WITH NEW PARTS. NO OTHER PROBLEMS FOUND.SDR AU970636Frame · cracked(AUS) LH AND RH FUSELAGE FRAMES CRACKED FROM RELIEF NOTCH TOWARDS UPPER OUTBOARD `HI-SHEAR' FASTENER OF OUTBOARD UNDERCARRIAGE CASTINGSDR AU970646Bulkhead · cracked(AUS) FUSELAGE BULKHEAD LH AND RH LOWER AFT DOOR POSTS PNO 0512187-1 LH AND PNO 0512187-2 RH CRACKED IN AREA INDICATED BY SERVICE BULLETINSDR AU970623Bulkhead · cracked(AUS) LH AND RH FUSELAGE DOOR FRAME BULKHEADS CRACKED BEHIND LAP JOINTSDR AU970600Door Post · cracked(AUS) FUSELAGE BULKHEAD DOOR POST FRAME CRACKED
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