Textron 172S
Service difficulty reports · 1,104
Newest first. General aviation reporting is voluntary.
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 = '172S' 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 = '172S' 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 2026FA0000773Bushing · defectiveTHE RIGHT LANDING GEAR LEG BUSHING WHICH SECURES THE LEG TIGHTLY TO THE AIRFRAME STRUCTURE HAD A DELAMINATED BUSHING LINER. WITHOUT THE LINER THE GEAR LEG IS NOT TIGHTLY SECURED TO THE AIRFRAME STRUCTURE, INSTEAD IT WILL FLOP AROUND.SDR 2026FA0000167Cylinder Head · crackedENGINE WAS REPORTED RUNNING ROUGH, WAS FOUND TO HAVE A CRACK ON THE CYLINDER HEAD ON #4 CYLINDER. THE SAME PROBLEM WAS FOUND ON ANOTHER ENGINE, SAME TYPE AIRCRAFT, ENGINE AND CYLINDER.SDR 2026FA0000775Bushing · defectiveTHE RIGHT LANDING GEAR LEG BUSHING WHICH SECURES THE LEG TIGHTLY TO THE AIRFRAME STRUCTURE HAD A DELAMINATED BUSHING LINER. WITHOUT THE LINER THE GEAR LEG IS NOT TIGHTLY SECURED TO THE AIRFRAME STRUCTURE, INSTEAD IT WILL FLOP AROUND.SDR NX422026022700010Stud · displacedUPON DISASSEMBLY FOR IT'S FIRST OVERHAUL, DAMAGE WAS FOUND ON ONE OF THE THRU STUDS. THE DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THE THREADED PORTION ON THE SHOULDER OF THE THRU STUD. THE DAMAGE IS MINOR BUT DUE TO THE SIMILAR LOCATION AND SEVERITY OF THE DSDR NX422026022700009Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE TO ONE THRU STUD LOCATION. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORE. SIMILAR DAMAGE ON OTHER ENGINES WAS PREVSDR NX422026021800008Stud · displacedUPON DISASSEMBLY FOR IT'S FIRST OVERHAUL, DAMAGE WAS FOUND ON 2 OF THE THRU STUDS. THE DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THE THREADED PORTION ON THE SHOULDER OF THE THRU STUD. THE DAMAGE IS MINOR BUT DUE TO THE SIMILAR LOCATION AND SEVERITY OF THE DAMSDR NX422026021800007Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE TO ALL 4 THRU STUD LOCATIONS. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORE. ON THREE OF THE THRU STUD BORES THE DSDR 2026FA0000128Cap · leakingTHIS IS TO REPORT POSSIBLE DEFECTS IN PN 259-P-04. THE AIRCRAFT DRAIN PLUGS WERE LOCATED ON THE DRAIN TEE FOR THE GDC74A. A POSSIBLE FAULT COULD BE THE INSTALLATION. WHILE THE AIRCRAFT HAS NOT HAD THE PITOT OR STATIC SYSTEMS LEAKED CHECK SINCE THE FACTORYSDR NX422026021800006Stud · displacedUPON DISASSEMBLY FOR IT'S FIRST OVERHAUL, DAMAGE WAS FOUND ON 1 OF THE THRU STUDS. THE DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THE THREADED PORTION ON THE SHOULDER OF THE THRU STUD. THE DAMAGE IS MINOR BUT DUE TO THE SIMILAR LOCATION AND SEVERITY OF THE DAMSDR NX422026021800005Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE TO ALL 4 THRU STUD LOCATIONS. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORE. IN ADDITION, 1 OF THE THRU STUDS HAVESDR 2026FA0000088Fairlead · frayedWE HAVE NOTICED A TREND IN (STAINLESS STEEL) AILERON CABLE WEAR ON RH AILERON CROSSOVER CABLE P/N 0510106-365 AT FAIRLEAD P/N 0560065-2 RH WING STATION 57.68. ON OUR AIRCRAFT, N9347T 172S S/N 11166 TT: 6524, THE CABLE HAS FRAYED WIRES DUE TO WEARING ON THE FAISDR 2026FA0000087Fairlead · frayedWE HAVE NOTICED A TREND IN (STAINLESS STEEL) AILERON CABLE WEAR ON RH AILERON CROSSOVER CABLE P/N: 0510106-365 AT FAIRLEAD P/N 0560065-2 RH WING STATION 57.68. ON OUR AIRCRAFT, N172HG 172S S/N 11139 TT: 7109.8, THE CABLE HAS FRAYED WIRES DUE TO WEARING ON THE SDR NX422026020600004Stud · displacedUPON DISASSEMBLY FOR IT'S FIRST OVERHAUL, DAMAGE WAS FOUND ON 2 OF THE THRU STUDS. THE DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THE THREADED PORTION ON THE SHOULDER OF THE THRU STUDS. THE DAMAGE APPEARS TO BE VERY MINOR BUT DUE TO THE SIMILAR LOCATION AND SESDR NX422026020600003Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE TO THE UPPER MIDDLE FLOATING THRU STUD LOCATION. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORE. IN ADDITION, 2 OF SDR NX422026020600001Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE ON ALL 4 OF THE FLOATING THRU STUD LOCATIONS. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORES. IN ADDITION, 2 OF THSDR NX422026020600002Stud · displacedON DISASSEMBLY FOR ITS 1ST OVERHAUL, DAMAGE FOUND ON 2 OF THRU STUDS. DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THREADED PORTION ON SHOULDER OF THRU STUDS. ON 1 THRU STUD. DAMAGE IS SEVERE WITH DISPLACED METAL FROM SMALLER NECKED DOWN PORTION OF STUD UP TO SDR 2026FA0000198Impulse Coupling · destroyedPILOT REPORT OF FLUCTUATING RPM'S WHILE IN CRUISE FLIGHT, PLUS OR MINUS 400RPM. DURING GROUND RUN FOR TROUBLESHOOTING, RH MAGNETO MAG DROP WAS EXCESSIVE. FURTHER ATTEMPTS AT CLEARING PLUGS, ETC, TO THEN RECHECK RH MAGNETO DROP RESULTED IN COMPLETE ENGINE SHUT SDR 2026FA0000137Pump · inoperativeDURING CLIMB THE PILOT NOTICED ENGINE RPM FLUCTUATIONS. AIRCRAFT RETURNED BACK TO THE AIRPORT, DID ENGINE RUN UPS AND NOTICED VACUUM PUMP WAS INOPERATIVE. MAINTENANCE REMOVED FAILED PUMP AND FOUND DRIVE SPLINE SHEARED AND PUMP SEIZED.SDR 2026FA0000184Bulkhead · crackedFOUND REPLACEMENT SPINNER BULKHEAD CRACKED AT BOLT HOLES AFTER 485 HOURS OF SERVICE.SDR 2025FA0000793Bushing · delaminatedTHE RIGHT LANDING GEAR LEG BUSHING WHICH SECURES THE LEG TIGHTLY TO THE AIRFRAME STRUCTURE HAD A DELAMINATED BUSHING LINER WHICH COMPLETELY WORKED ITSELF OUT OF THE BUSHING. THE LANDING GEAR LEG WAS FLOPPING AROUND INSIDE THIS BUSHING.SDR 2025FA0000769Bushing Sleeve · debondedDURING ANNUAL INSPECTION IT WAS NOTED THAT THE LT MLG HAD A DISBONDED BUSHING LINER.SDR OF1R202510240001Bulkhead · crackedFUSELAGE BULKHEAD IN AFT BAGGAGE COMPARTMENT HAS A ONE INCH CRACK ON BOTH LEFT AND RIGHT SIDES.SDR 2026FA0000765Bushing · defectiveTHE RIGHT LANDING GEAR LEG BUSHING WHICH SECURES THE LEG TIGHTLY TO THE AIRFRAME STRUCTURE HAD A DELAMINATED BUSHING LINER. WITHOUT THE LINER THE GEAR LEG IS NOT TIGHTLY SECURED TO THE AIRFRAME STRUCTURE, INSTEAD IT WILL FLOP AROUND.SDR 2025FA0000600Servo · contaminatedFUEL SERVO FOUND TO HAVE CONTAMINATION. HEAVY THICK BLUE STAIN.SDR IKBR2025082600579Elec Connector · intermittentENGINE OIL PRESSURE INDICATION ERRATIC. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER WIRING CONNECTOR WITH NEW P/N S2800-277 REFERENCING CESSNA 172S WDG CH.77-40-01 (REV. A1). ENGINE RUN, OIL PRESSURE OPERATIONAL CHECK SATISFACTORY.SDR 2025FA0000578Elec Connector · failedFUEL PRESSURE INDICATIONS ERRATIC. REPLACE FUEL PRESSURE TRANSDUCER CONNECTOR (JN001) PN: S2800-277 REFERENCING TEXTRON MODEL 172 (SERIES 1996 AND ON) WIRING DIAGRAM MANUAL REV A1 SECTION 77-20-01, FIGURE 02 (REV A0).SDR 2025FA0000577Elec Connector · intermittentENGINE OIL PRESSURE ERRATIC.REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) WITH NEW P/N S2800-277 REFERENCING CESSNA 172S WDG CH.79-30-01 (REV.A1). ENGINE RUN, OIL PRESSURE SYSTEM OPERATIONAL CHECK SATISFACTORY.SDR IKBR2025082600576Elec Connector · failedENGINE OIL PRESSURE ERRATIC. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) WITH NEW P/N S2800-277 REFERENCING CESSNA 172S WDG CH.79-30-01 (REV.A1). ENGINE RUN, OIL PRESSURE SYSTEM OPERATIONAL CHECK SATISFACTORY.SDR 2025FA0000575Elec Connector · intermittentENGINE OIL PRESSURE ERRATIC. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) WITH NEW P/N S2800-277 REFERENCING CESSNA 172S WDG CH.79-30-01 (REV.A1). ENGINE RUN, OIL PRESSURE SYSTEM OPERATIONAL CHECK SATISFACTORY.SDR 2025FA0000574Elec Connector · intermittentENGINE OIL PRESSURE FLUCTUATES. REMOVED AND REPLACED THE OIL PRESSURE TRANSDUCER CONNECTOR JN004 PN: S2800-277 REFERENCING CESSNA/TEXTRON MODEL 172 (SERIES 1996 AND ON) WIRING DIAGRAM MANUAL REV A1, 77-40-01, FIGURE 03: SHEET 02 “ENGINE AND AIRFRAME MONITOR”.SDR 2025FA0000601Servo · contaminatedMOMENTARY ENGINE ROUGHNESS/VIBRATION. AIRCRAFT HAD MOMENTARY POWER LOSS AFTER ADDING FULL POWER ON A TOUCH AND GO. ABORTED TAKEOFF. TOOK AIRCRAFT TO A RUNUP AREA AND CYCLED THE ENGINE FROM POWER IDLE TO FULL POWER MULTIPLE TIMES AND COULD NOT RECREATE THE ISSUSDR 2025FA0000648Autopilot Sys · deactivatedWHEN RETURNING FROM LBX TO LVJ, THE FLIGHT PLAN IN THE G100 CALLED FOR A PRACTICE RNAV 32 APPROACH AT LVJ. WEATHER WAS VFR WITH NO CLOUDS AND LIGHT WINDS. THE AUTOPILOT WAS ACTIVATED IN NAV MODE AFTER COURSE ESTABLISHED. JUST PRIOR TO THE IAF THE APR BUTTON OSDR 2025FA0000643Servo · contaminatedAIRCRAFT DIED IN RUNUP AREA TWICE. ONCE ON RAMP, ONCE IN RUNUP. FAILED IDLE CHECK. FUEL SERVO WAS REMOVED AND FOUND TO BE CONTAMINATED. REPLACED WITH NEW.SDR 2025FA0000599Servo · contaminatedFUEL SERVO FOUND TO HAVE ENGINE OIL CONTAMINATION.SDR 2025FA0000644Servo · contaminatedAIRCRAFT HAD MOMENTARY POWER LOSS/VIBRATION AFTER ADDING FULL POWER ON A TOUCH AND GO. ABORTED TAKEOFF. TOOK AIRCRAFT TO A RUNUP AREA AND CYCLED THE ENGINE FROM POWER IDLE TO FULL POWER MULTIPLE TIMES AND COULD NOT RECREATE THE ISSUE. FUEL SERVO REPLACED.SDR 2025FA0000563Bushing · debondedDURING ANNUAL INSPECTION IT WAS NOTED THAT LEFT MLG HAS DISBONDED BUSHING LINER.SDR 2025FA0000562Bushing · debondedDURING ANNUAL INSPECTION IT WAS NOTED THAT LEFT MLG HAS DISBONDED BUSHING LINER. IT WAS ALSO NOTED THE RIGHT BUSHING BEGINNING TO DISBOND.SDR 2025FA0000602Servo · contaminatedMOMENTARY ENGINE ROUGHNESS/VIBRATION. CLIMBING OUT ON THE MISSED APPROACH AT CRQ, ENGINE LOST BETWEEN 200-400RPM AND BEGAN CHUGGING, I CHECKED MIXTURE WHICH WAS FULL RICH, LEANED SLIGHTLY, THE CHUGGING STOPPED. I THEN MOVED THE MIXTURE FULL RICH AND DID NOT ENSDR 2025FA0000595Bushing · looseLEFT MAIN GEAR ATTACH BUSHING P/N 0541202-4 LINER BECAME DISBONDED CREATING PLAY IN THE GEAR LEG. THIS AIRCRAFT IS OUTSIDE THE S.N. RANGE OF SEL-32-08 YET HAS THE SAME PROBLEM.SDR 2025FA0000594Bushing · looseLEFT AND RIGHT MAIN GEAR ATTACH BUSHINGS P/N 0541202-4 LINER BECAME DISBONDED CREATING PLAY IN THE GEAR LEG. THIS AIRCRAFT IS OUTSIDE THE S.N. RANGE OF SEL-32-08 YET HAS THE SAME PROBLEM.SDR 2025FA0000598Servo · contaminatedMOMENTARY ENGINE ROUGHNESS/VIBRATION/ LOSS OF POWER. PILOT REPORTED:"IN THE UPWIND ON FIRST LAP IN THE PATTERN ENGINE RPM DROPPED SIGNIFICANTLY WHILE ENGINE SPUTTERED, SEEMED TO STABILIZE WITH AUX FUEL PUMP ON, DID NOT FEEL LIKE WE WERE GETTING FUEL POWER LANDSDR 2025FA0000596Servo · contaminatedMOMENTARY ENGINE ROUGHNESS/VIBRATION WHILE IN THE PATTERN TURNING FROM CROSSWIND TO DOWNWIND, LOSS OF RPM. ENGINE INDICATIONS OTHERWISE NORMAL. NORMAL RUNUP. LANDED AND DID ANOTHER RUNUP WHICH WAS ALSO NORMAL. FUEL SERVO REPLACED.SDR 2025FA0000603Servo · contaminatedMOMENTARY ENGINE ROUGHNESS/VIBRATION/LOSS OF POWER. PILOT SQUAWK: PARTIAL LOSS OF ENGINE POWER RIGHT AFTER TAKEOFF, 200-300 RPMS, CAME BACK AFTER A COUPLE SECONDS BUT DID NOT WANT TO CONTINUE FLIGHT. FUEL SERVO REPLACED.SDR 2025FA0000597Servo · contaminatedMOMENTARY ENGINE ROUGHNESS/VIBRATION/ LOSS OF POWER. PILOT REPORTED:"ON TAKEOFF OUT OF LVK AT 600 AGL THE ENGINE LOST TOTAL POWER FOR A MINIMUM OF ONE SECOND. AFTER THE LOSS OF POWER THE ENGINE IMMEDIATELY CAME BACK. I ENTERED THE TRAFFIC PATTERN AND DISCONTINSDR ODAR2025080600002Cylinder Head · crackedSUBSTANTIAL ENGINE VIBRATION REPORTED BY PILOT DURING FLIGHT. #4 CHT CONSISTENTLY ~40% HIGHER THAN OTHER CYLINDERS. MAG CHECKS NORMAL. VIBRATION REMAINED THE SAME REGARDLESS OF MAGS SELECTED. OIL PRESSURE AND TEMP REMAINED IN GREEN. PERFORMED COMPRESSION CHECKSDR 2025FA0000593Bushing · looseLEFT MAIN GEAR ATTACH BUSHING P/N 0541202-4 LINER BECAME DISBONDED CREATING PLAY IN THE GEAR LEG. THIS AIRCRAFT IS OUTSIDE THE S.N. RANGE OF SEL-32-08 YET HAS THE SAME PROBLEM.SDR 2025FA0000592Bushing · looseRIGHT MAIN GEAR ATTACH BUSHING P/N 0541202-4 LINER BECAME DISBONDED CREATING PLAY IN THE GEAR LEG. THIS AIRCRAFT IS OUTSIDE THE S.N. RANGE OF SEL-32-08 YET HAS THE SAME PROBLEM.SDR 2025FA0000527Elec Connector · abnormalERRATIC ENGINE OIL PRESSURE INDICATION. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) P/N S2800-277 (KIT) AT THE TRANSDUCER.SDR 2025FA0000526Elec Connector · faultedERRATIC ENGINE OIL PRESSURE READINGS. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) P/N S2800-277 (KIT) AT THE TRANSDUCER.SDR N3XR202507250941Hinge · crackedDURING A ROUTINE INSPECTION, THE LOWER RUDDER HINGE FITTING WAS FOUND CRACKED ON THE LOWER PORTION AROUND EACH CORNER BETWEEN RIVET HOLES
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