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 2019FA0000392Exhaust Valve · burnedPILOT REPORTED ROUGH RUNNING ENGINE AT 2200 RPM SPECIFICALLY. INSPECTED ENGINE SPARK PLUGS, NO DEFECTS NOTED. CHECKED IDLE MIXTURE CUTOFF, NO DEFECTS. RAN AIRCRAFT ENGINE AND DUPLICATED PILOTS SQUAWK. PERFORMED CYLINDER #2 DIFFERENTIAL PRESSURE CYLINDER LEAKSDR 2020FA0000013Exhaust Valve · stickingENGINE S/N L-359141-51E WAS FOUND STICKING EXHAUST VALVE AT 381.8 TOTAL TIME. LYCOMING SB388C WAS THEN COMPLIED WITH, AND DURING THE WOBBLE CHECK, NR 2 WAS ACTUALLY STUCK. ALL THE GUIDES WERE THEN REAMED TO WITHIN TOLERANCE. THIS ENGINE INCORPORATES NI-RESISDR 2020FA0000011Exhaust Valve · stickingENGINE WAS FOUND WITH A STICKING EXHAUST VALVE AT582.4 HOURS TOTAL TIME. LYCOMING SB388C WAS PERFORMED, ALL GUIDES WERE REAMED TO WITHIN TOLERANCE. THIS ENGINE INCORPORATES NI-RESIST VALVE GUIDES AND THE TIME TO FAILURE IS CONSIDERED BY THIS AGENCY TO BE PRESDR 5SWS2020010800008Exhaust Valve · stickingENGINE S/N RL-35534-51E WAS FOUND WITH A STICKING EXHAUST VALVE AT 434.1 HOURS TOTAL TIME. THE CYLINDER WAS REPLACED. THIS ENGINE INCORPORATES NI-RESIST VALVE GUIDES AND THE TIME TO FAILURE IS CONSIDERED BY THIS AGENCY TO BE PREMATURE.SDR 5SW2020010800000Exhaust Valve · stickingENGINE S/N L-19263-51E WAS FOUND WITH A STICKING EXHAUST EXHAUST VALVE AT 385.3 HOURS TOTAL TIME. LYCOMING SB388C WAS PERFORMED, ALL THE GUIDES WERE REAMED WITHIN BALANCE. THIS ENGINE INCORPORATES NI-RESIST VALVE GUIDES AND THE TIME TO FAILURE IS CONSIDERED SDR 2020FA0000007Exhaust Valve · stickingENGINE S/N L3049651E EXPERIENCED A STICKING EXHAUST VALVE AT 582.4 HOURS TOTAL TIME WHILE IN FLIGHT. THE PILOT MADE A SUCCESSFUL PARTIAL-POWER LANDING. CYLINDER NR 3 EXHAUST VALVE STUCK IN FLIGHT, THE VALVE HIT THE PISTON AND THE PUSH ROD WAS BENT. THAT CYLSDR 2019FA0000345Brake · wornPILOT REPORTED LOSS OF RIGHT BRAKE UPON LANDING, FOLLOWED BY EVIDENCE OF BRAKE FLUID LEAK ON RIGHT LANDING GEAR. RIGHT BRAKE WAS FOUND TO BE COMPLETELY INEFFECTIVE.
ON INSPECTION, FOUND A HOLE APPROXIMATELY 1/8" DIAMETER, WORN THROUGH THE RIGHT BRAKE RIGID SDR 2019FA0000342Exhaust Valve · wornDURING STANDARD 50 HOUR SCHEDULED OIL CHANGE AS S.O.P. DIFFERENTIAL CYLINDER LEAK CHECKS ARE PERFORMED. CYLINDER #1 WAS 60/80 PSI, OTHER CYLINDERS WERE IN MID TO UPPER 70'S. ENGINE HAD LEAKING EXHAUST VALVE. ENGINE TIME SINCE OVERHAUL: 1271.8 HOURS.SDR 2019FA0000324Spar · crackedDURING PRE-FLIGHT INSPECTION, IT WAS NOTICED THE HORIZONTAL STABILIZER HAD A NOISE COMING FROM THE ATTACHING POINTS. GAIN ACCESS AND VISUALLY INSPECTED ATTACHING POINTS WITH NO DEFECT NOTED, AFTER FURTHER INSPECTION IT WAS NOTICED THAT THE FWD SPAR ASSEMBLY WASDR 2019FA0000297Spring Assy · brokenON AUGUST 15, 2019 AT 1355 EASTERN DAYLIGHT TIME, RECEIVED MINOR DAMAGE WHILE LANDING AT AIRPORT (MIV). THERE WERE NO INJURIES TO EITHER OF THE TWO PILOTS ON BOARD. THE INSTRUCTIONAL FLIGHT WAS CONDUCTED UNDER THE PROVISIONS OF TITLE 14 CODE OF FEDERAL REGULSDR CA190912007Starter · binding(CAN) DURING WALKAROUND, IT WAS OBSERVED THAT THE STARTER ENGAGEMENT GEAR WAS RUBBING ON THE CRANKSHAFT RING GEAR. IT APPEARS AS IF THE ENGAGEMENT GEAR IS UNABLE TO FULLY RETURN TO ITS RESTING POSITION. (TC# 20190912007)SDR CA190729014Axle · damaged(CAN) WHEN WE WERE REPLACING THE TIRE ASSEMBLY ON THE R/H MLG, WE NOTICED THAT THE AXLE P/N 0541199-1 HAS SOME PLAY (BOTH UP AND DOWN AND ROTATIONAL) ON THE MAIN LANDING GEAR. THE BOLT THAT HOLDS THE AXLE ON WAS WAS TIGHT. WE TRIED A NEW AXLE AND IT WENT ON VESDR CA190718004Exhaust Valve · stiff(CAN) FOLLOWING IS SNAG BY PILOT - ENGINE PRODUCED FULL POWER INITIALLY DURING GO AROUND THEN DROPPED TO 2200 RPM THEN BACK TO FULL POWER. WHAT MAINTENANCE FOUND - AFTER THE SECOND OCCURRENCE OF POWER LOSS WE DECIDED TO PERFORM LYCOMING SB 388. (EXHAUST VALVE SDR 2019FA0000214Tube · wornDURING A VISUAL INSPECTION OF THE AREA/SYSTEM, IT WAS NOTED THAT THE PARKING BRAKE CABLE HAD WORN A HOLE IN THE ALUMINUM GUIDE TUBE THAT THE CABLE IS ROUTED IN. THE CABLE IS USE TO ACTUATE THE PARKING BRAKE. IT WAS STILL OPERATIONAL BUT THE GUIDE TUBE WAS DASDR CA190615001Tube · bent(CAN) C-XXXX WAS ON APPROACH INTO XXX WHEN THE AIRCRAFT ENGINE STARTED VIBRATING EXCESSIVELY. PILOT PROCEEDED TO LAND AIRCRAFT WITH NO ISSUES. UPON INSPECTION THE AME FOUND A BENT PUSH ROD TUBE & SHROUD AS A RESULT OF A STUCK EXHAUST VALVE. (TC# 20190615001)SDR 2019FA0000128Not Reported · malfunctionedAFTER UPGRADING THE AIRCRAFT FOR ADS-B PER SB, AND UPDATING G1000 SOFTWARE, THE AIRCRAFT BEGAN LOSING MAGNETIC HEADING AND DISPLAYING RED "X".SDR CA190502023Spring · missing(CAN) DURING 500 HOUR INSPECTION IT WAS NOTED THAT ONE OF THE IMPULSE COUPLING SPRINGS WAS MISSING. (TC# 20190502023)SDR 2019FA0000113Cylinder · unknownINTERMITTENT "HUNG VALVE CONDITION" ON THE EXHAUST SIDE OF (2) FACTORY NEW CYLINDERS P/N 05K21104 WITH 750 HRS TSN. CONDITION CAUSING ROUGH RUNNING ENGINE ON OCCASION.SDR CA190408008Transponder · malfunctioned(CAN) AIRCRAFT WAS SNAGGED THAT IT LOST ITS HEADING INDICATION MOMENTARILY DURING FLIGHT AND THAT IT HAD A GDL90 FAILURE. THE AIRCRAFT IS G1000 EQUIPPED AND IS AT S/W VERSION 563.35 (LATEST CESSNA S/W) DONE IN FEB 2018. WE ARE UNABLE TO REPLICATE THE ISSUE ON SDR N3XR2019040500001Plug · leakingDURING A 100 HR INSPECTION, OIL WAS FOUND LEAKING FROM THE CRANKSHAFT EXPANSION PLUG P/N-STD-1211. THE PLUG WAS REPLACED.SDR CA190405012Magneto · failed(CAN) SNAG: PILOT REPORTS ON SHUT DOWN, NOTICED LEFT MAGNETO NOT FUNCTIONING. INSPECTED ENGINE LEFT HAND IGNITION SYSTEM FOR ANY ANOMALIES THAT WOULD CAUSE THE LEFT HAND MAGNETO TO NOT FUNCTION, UPON TURNING THE PROPELLER IT WAS NOTICED THAT THE LEFT MAGNETO SDR N3XR2019040500002Plug · leakingDURING A 100 HR INSPECTION, OIL WAS FOUND LEAKING FROM THE CRANKSHAFT EXPANSION PLUG P/N-STD-1211. THE PLUG WAS REPLACED.SDR CA190404007Alternator · failed(CAN) OVERHAULED ALTERNATOR WITH LESS THAN 250 HRS TSOH. PILOT REPORTED DISCHARGE AT LOW RPM AND WAS CONFIRMED WITH GROUND RUN. RECOMMENDED OVERHAUL IS 2500 HRS.SDR 2019FA0000118Fuel Line · crackedDURING NORMAL CRUISE FLIGHT PILOT REPORTED ROUGH RUNNING ENGINE AND ASSUMED A SPARK PLUG HAD FAILED. MAINTENANCE INSPECTION DETERMINED THE NR 1 ENGINE CYLINDER, FUEL INJECTOR NOZZLE FAILED. THE INJECTOR LINE FAILED AT THE BRAZED PORTION CLOSEST TO THE FUEL NOZSDR 2019FA0000108Cylinder · separatedWHILE PERFORMING A LOCAL INSTRUCTION FLIGHT FOR AN IFR RATING. AFTER PERFORMING AN APPROACH AND A TOUCH AND GO ON RUNWAY 10 AT POMPANO BEACH AIRPARK (KPMP), THE AIRCRAFT INITIATED A CLIMB AT VX 62 KNOTS AND HEADED NORTH EAST BOUND TO BE HANDED OFF TO APPROACH.SDR CA190305017Camshaft · damaged(CAN) FACTORY NEW CAMSHAFT VISUALLY INSPECTED AND SIGNIFICANT AREAS OF CORROSION OBSERVED ON LOBE JOURNALS AND BEARING JOURNALS. CORROSION INCLUDED SURFACE PITTING AND PENETRATION. NO EVIDENCE OF THE PACKAGE OR LYCOMING CAMSHAFT BOX BEING OPENED OR TAMPERED WISDR CA190305011Camshaft · worn(CAN) DURING A GROUND RPM CHECK IT WAS NOTICED THAT WE WERE UNABLE TO MAKE STATIC RPM ON THE AIRCRAFT WITH MINIMUM REQUIREMENT BEING 2300 WE COULD ONLY MAKE 2250. AFTER TRYING SEVERAL THINGS WITH NO IMPROVEMENT IT WAS DECIDED TO PULL ONE CYLINDER TO INVESTIGATSDR 2019FA0000051Piston · brokenAFTER A TOUCH AND TAKE OFF, THE PILOT REPORTED BRAKE MALFUNCTION, THE PISTON AT THE MASTER CYLINDER WAS FOUND BROKEN. PART REPLACED.SDR 2019FA0000046Piston · brokenTHE PILOT REPORT THE BRAKE LT INOPERATIVE AFTER TAKE OFF, AFTER LANDING THE MASTER CYLINDER PISTON WAS FOUND BROKEN.SDR CA190218008Magneto · malfunctioned(CAN) ALL GROUND CHECKS WERE GOOD BUT IN FLIGHT THERE WAS AN INTERMITTENT RPM LOSS OF ABOUT 50RPM WITH ASSOCIATED ROUGH RUNNING. FAULT WOULD NOT REPRODUCE ON GROUND SO AIRCRAFT WAS TEST FLOWN AND FAULT REPRODUCED BUT SEEMED TO CLEAR WHEN ELECTRIC FUEL PUMP WASSDR 2019FA0000030Hinge Fitting · corrodedDURING ROUTINE SURVEILLANCE, THE CENTER RUDDER HINGE HALF WAS OBSERVED WITH SEVERE EXFOLIATION/INTER-GRANULAR CORROSION.SDR 2018FA0000530Spring · brokenWHILE TAXI FOR TAKE OFF, THE LEFT RUDDER RETURN SPRING P/N 0310196-5 BROKE AT THE FORWARD ATTACHMENT HOOK, CAUSING LOSS OF DIRECTIONAL CONTROL ON THE GROUND AND THE AIRCRAFT TO EXIT THE TAXI WAY INTO THE GRASS MEDIAN. THE AIRCRAFT IS USED FOR TRAINING APPOX. 1SDR 2018FA0000509Exhaust Valve · stuckEXHAUST VALVE IN NR 4 CYLINDER STUCK IN FLIGHT CAUSING THE EXHAUST PUSH ROD TO BEND AND BREAK. THE PUSH ROD TUBE ALSO BROKE ALLOWING ENG OIL TO ESCAPE. THERE WAS A DRASTIC LOSS OF ENG OIL AND ENG OIL PRESSURE.SDR N3XR2018111600Alternator · failedDURING CRUISE FLIGHT, THE CREW OBSERVED AN ALTERNATOR FAILURE ANNUNCIATION. THE DECLARED AN EMERGENCY AND LANDED.INSPECTION REVEALED THAT THE ALTERNATOR HAD FAILED.SDR 2018FA0000428Rotor · looseDURING RUN UP THE PILOT EXPERIENCED ABNORMAL RPM DROPS WHEN CHECKING THE MAGNETOS. THE MAGNETO MODEL NR 4371 SERIAL NR 18021142 TIMING TO THE ENGINE WAS FOUND TO BE 20 DEGREES BTDC INSTEAD OF 25 DEGREES BTDC. UPON OPENING THE COVER OF THE MAGNETO THE ROTOR ANDSDR 2020FA0000053Control Cable · chafedRT WING, AILERON CONTROL CABLES, TWO EACH, CHAFED AT RUB-BLOCK INBOARD OF THE AUTOPILOT SERVO. CABLE STRANDS ARE NOT FRAYED, CANNOT DETECT CHAFE DAMAGE WITH RUNNING A RAG OVER THE DAMAGE. BUT STRANDS ARE DEFINITELY CHAFED BEYOND AN AMOUNT TO CAUSE CONCERN. SDR YN8R201809260001Attach Bracket · brokenFUEL INJECTION SPIDER BRACKET, P/N 07A22996, WAS FOUND BROKEN DURING ANNUAL INSPECTION. IT BROKE AT THE 90 DEGREE BEND IN THE METAL. AD2015-19-07 CALLS FOR THE FUEL INJECTION LINES AND CLAMPS TO BE INSPECTED IAW MSB342G. THIS WAS FOUND BROKEN 100 HOURS SINCSDR CA180925017Pressure Switch · malfunctioned(CAN) REPORTING FAILURE OF TWO NEW OIL PRESSURE SWITCHES P/N 83278. SHIPPED DIRECT FROM CESSNA-THESE SWITCHES HAVE AN AIRWORTHINESS LIMITATION OF 3000 HRS & ARE AFFECTED BY AD2013-11-11. THE FIRST SWITCH, INSTALLED IN COMPLIANCE WITH AD2013-11-11, FAILED DURSDR 2018FA0000353Control Cable · wornPREMATURE WEAR IN AILERON CONTROL CABLES. WEAR HAS OCCURRED IN TWO SEPARATE PLACES, BOTH DIRECT CABLES (P/N:0510105-260) AND THE CROSSOVER CABLE (P/N: 0510105-264) WORE AT THE PULLEYS IN THE CABIN OVERHEAD AND DIRECT CABLES P/N: 0510105-262 AND CROSSOVER CABLESDR 2018FA0000212Control Cable · wornDURING PRE-FLIGHT INSPECTION, A ROUGHNESS WAS HEARD IN THE AILERON FLIGHT CONTROL CABLES. ON FURTHER INSPECTION THE AILERON CARRY THROUGH CABLE WAS FOUND EXCESSIVELY WORN WITH MULTIPLE BROKEN STRANDS AT THE FAIRLEAD RUB STRIP IN THE LEFT WING. THE REGION WHERESDR N3XR201804270632Plug · looseDURING CRUISE FLIGHT AT NIGHT, THE WINDSCREEN BECAME COVERED IN OIL. THE PILOT MADE AN EMERGENCY RETURN TO THE AIRPORT AND MADE AN UNEVENTFUL LANDING.. INSPECTION REVEALED THAT THE EXPANSION PLUG IN THE CRANKSHAFT (LYCOMING P/N-STD-1211) HAD BEEN DISPLACED ALLSDR N3XR2018042300479Cylinder · crackedDURING AN INSPECTION AND WHEN PERFORMING THE COMPRESSION CHECK, IT WAS DISCOVERED THAT THE NR 1 AND 3 CYLINDERS WERE FOUND CRACKED AT THE BARREL-HEAD CONNECTION.SDR 2018FA0000063Control Cable · frayedDURING AN ANNUAL INSPECTION A RUBBING NOISE WAS HEARD DURING THE AILERON MOVEMENT. INSPECTION IN THE LEFT WING, WING STATION 70.85 (RIB OUTBOARD OF THE FLAP ACTUATOR ROD), THE AILERON CABLES TRAVEL THROUGH AN OPENING IN THE RIB. A PIECE OF PHENOLIC IS RIVETESDR CA180223006Wire · chafed(CAN) SMOKE IN COCKPIT AFTER LANDING. WIRE FROM NAVIGATION LIGHT CIRCUIT BREAKER SWITCH TO SPLICE (FROM SINGLE WIRE TO 3 WIRES, FOR EACH NAVIGATION LIGHT) BURNED. RIGHT NAVIGATION LIGHT WIRE FROM SPLICE TO RIGHT SIDE OF COCKPIT BURNED. SOME ADJACENT WIRES INSDR 8HBR20180118012Pressure Switch · failedOIL PRESSURE WARNING SWITCH FAILURE AFTER 30.2 HOURS TIS.SDR 2018FA0000191Pressure Switch · failedNEW OIL PRESSURE SWITCH CAUSED ERRONEOUS LOW OIL PRESSURE ANNUNCIATION AND HOUR METER FAILURE. REPLACING THE SWITCH WITH A UNIT OF A DIFFERENT LOT NUMBER RESOLVED THE PROBLEM WITH NO DEFECTS TO EITHER THE OIL PRESSURE INDICATION AND RESTORED THE FUNCTION OF TSDR 8HBR20171206010Pressure Switch · failedOIL PRESSURE SWITCH FAILED WITH 364.8 TIS.SDR 2017FA0000577Rivet · looseTHE MAGNETO WAS REMOVED FROM SERVICE FOR THE 500HR INSPECTION. THE RIVETS RETAINING THE IMPULSE COUPLING PAWLS WERE FOUND TO BE LOOSE. ABLE TO ROTATE THE RIVETS. FAILURE OF THE RIVETS COULD CAUSE TOTAL ENGINE FAILURE.SDR 2017FA0000576Rivet · looseTHE MAGNETO WAS REMOVED FROM SERVICE FOR THE 500HR INSPECTION. THE RIVETS RETAINING THE IMPULSE COUPLING PAWLS WERE FOUND TO BE LOOSE DURING THE INSPECTION. ABLE TO ROTATE THE RIVETS. FAILURE OF THE RIVETS COULD CAUSE TOTAL ENGINE FAILURE.SDR 2017FA0000575Rivet · looseTHE MAGNETO WAS REMOVED FROM SERVICE FOR THE 500HR INSPECTION. THE RIVETS RETAINING THE IMPULSE COUPLING PAWLS WERE FOUND TO BE LOOSE DURING THE INSPECTION. ABLE TO ROTATE THE RIVETS. FAILURE OF THE RIVETS COULD CAUSE TOTAL ENGINE FAILURE.
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