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 2005FA0000237Bulkhead · crackedDURING 100 HOUR INSPECTION OF THE PROPELLER, CRACKS NOTED AROUND ALL BOLT HOLES OF THE FWD BULKHEAD. (K)SDR 2004FA0000804Audio Panel · smokeTHE AUDIO CONTROL PANEL EMITTED SMOKE AND STOPPED OPERATING DURING TAXI PRIOR TO FLIGHT. AIRCRAFT RETURNED TO BASE, MAINTENANCE REMOVED THE UNIT FROM AIRCRAFT AND VERIFIED AIRCRAFT BUS BAR VOLTAGE WITH ALTERNATOR OPERATING. A WORKING KMA-26 WAS INSTALLED, OSDR RO12004F00000Brushes · misinstalledTHIS IS THE 3RD OCCURRENCE OF ALTERNATOR FAILURE IN NEW MFG ALTERNATORS. EACH TIME ONE OF THE FIELD BRUSHES WAS FOUND INSTALLED WITH THE WIRE TOWARD THE SLIP RING (BACKWARDS). THIS IS THE 2ND M AND D REPORT SUBMITTED REGARDING THIS SAME INCIDENT. NEED TO INSDR 2005FA0000368Spring · missingON RETURN TO BASE, PILOT REPORTED WHEN CLIMING TO 8000 PT ENGINE SURGED/POWER DROP 2 TIMES. AIRCRAFT WAS DUE A PHASE 1 INSPECTION. WHILE INSPECTING THE ALT AIR DOOR, NOTICED THE DOOR STUCK IN THE OPEN POSITION. FURTHER INSPECTION REVEALED THE SPRING THAT COSDR 2004FA0000860Bulkhead · crackedPILOTS REPORTED AFT SPINNER BULKHEAD CRACKED AND SPINNER DOME BENT UP SLIGHTLY. UPON INSPECTION CORNER NUTPLATE FOUND COMPLETELY BROKEN OFF BULKHEAD.SDR MYN2004F00001Chain · failedFORWARD TRIM CHAIN TO CABLE LINK IS COMING APART. HAVE TO REPLACE FORWARD CABLE ASSY.SDR WIW2004F00001Spinner · crackedDURING A 100 HOUR INSPECTION OF THE PROPELLER IT WAS NOTICED THAT THERE WERE CRACKS AROUND THREE OF THE BOLT HOLES OF THE FORWARD SPINNER BULKHEAD. THE PROBABLE CAUSE IS THAT DURING THE TORQUING PROCESS THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS PULLED SDR CA040907002Alternator · damaged(CAN) ALTERNATOR CHARGING SYSTEM WOULD NOT COME ONLINE. TROUBLESHOOTING REVEALED THAT EVERYTHING SHOULD BE WORKING NORMALLY. HOWEVER SYSTEM WOULD NOT CHARGE. ALL VOLTAGES (IAW M.M.) APPEARED TO BE NORMAL BUT STILL THE CHARGING SYSTEM WAS SHOWING A DISCHARGE.SDR 2004FA0000739Controller · failedALTERNATOR VOLTAGE WENT OVER VOLT. OV PROTECTION FAILED AND BUSS VOLTAGE WENT WAY HIGH BURNING UP EVERTHING THAT WAS TURNED ON INCLUDING NAV LIGHTS, LANDING AND TAXI LIGHTS, ALL RADIOS, MOST INSTRUMENT LIGHTS AND ALL ELEC INSTRUMENTS, ANNUNCIATOR PANEL, INTERSDR 2004FA0000673Cylinder · detachedTHE CREW REPORTED A SEAT BACK WHICH WOULD NOT RECLINE PROPERLY. THE MAINTENANCE TECHNICIAN INSPECTED THE SEAT MECHANISM AND FOUND THE SEAT RECLINING ACTUATOR WAS BROKEN AT THE AFT ATTACH POINT. THE BREAKAGE WAS AT THE USAGE POINT.SDR N827SP1Indicator · inoperativeEGT/FUEL FLOW INDICATOR BECAME INOPERATIVE DURING FLIGHT.SDR 2004FA0000682Bolt · shearedDURING AN INSPECTION, FOUND 2 OF THE 3 THROUGH BOLTS SHEARED OFF AT THE THREADS, REPLACED THE STARTER. IF LT UNATTENDED WOULD CAUSE THE BACKPLATE OF THE STARTER TO COME OFF.SDR 2004FA0000554Lock · brokenPILOT SEAT BACK CYL LOCK ASSY ROD BROKE AT SWAGED ROD END. AC RETURNED TO AIRPORT. MFG RESCINDED SB DUE TO PROBLEMS WITH CYL LOCK ASSY. ANOTHER SB04-25-02 WHICH IS SUPPOSED TO TAKE CARE OF ANY PROBLEMS. ELECTED TO REMOVE ALL CYL LOCK ASSY, INSTALL SOLID RODSDR 2004FA0000571Servo · inoperativeAIRCRAFT WAS REPORTED, ENGINE DIES ON IDLE SPEED, EXCESSIVE RICH MIXTURE, BLACK SMOKE EMITTED FROM EXHAUST. IDLE SPEED AND MIXTURE COULD NOT BE ADJUSTED IAW AD 2001-06-17 INSTRUCTIONS REF D, L, I, THRU 2, 1.SDR CA040610008Bulkhead · broken(CAN) THE CORNER SECTION OF SPINNER AT LEADING EDGE OF PROPELLER BLADE CUT-OUT BADLY BENT (PEELED BACK) BY CENTRIFUGAL FORCE. THIS WAS CAUSED BY THE ADJACENT CORNER SECTION OF THE BACKPLATE (AROUND ANCHOR NUT) BREAKING OFF DURING OPERATION. NEW BACKPLATE DESISDR 2004FA0000655Starter · damagedSTARTER BENDIX FAILED CAUSING DAMAGE TO THE STARTER RING GEAR. THIS IS THE 6TH STARTER BENDIX FAILURE ON THIS AIRCRAFT.SDR 2004FA0000417Spar · damagedWHILE PERFORMING THE INSPECTIONS REQUIRED BY MFG SB04-55-01, FOUND THE RT SIDE HOLE IN THE HORIZONTAL STABILIZER AFT SPAR ELONGATED. THIS ELONGATION OPENED THE HOLE APPROX. .040 TO .050 INCHES IN THE 5 O`CLOCK DIRECTION (VIEWING THE HOLE FROM THE ACCESS IN THSDR CA040427018Rib · cracked(CAN) DURING INSPECTION OF HORIZONTAL STABILIZER ATTACH BOLT HOLES INSPECTION IAW MFG SB04-55-01, FOUND RT AFTER ATTACHMENT HOLE ON THE RIB HAS TWO .0937 INCH LONG CRACKS. THE CRACKS ARE HIDDEN UNDER THE MOUNTING WASHER.SDR 2004FA0000394Servo · inoperativeENGINE HAD VERY ROUGH AND RICH IDLE, COULD NOT ADJUST IDLE MIXTURE IAW AD. FUEL SERVO WAS INSTALLED ON A FRESH O/H ENGINE AND FUEL SERVO WAS ALSO FRESH FROM O/H. ENGINE WAS OPERATED AND LEAK CHECKED. AFTER .2 HOURS OF ENGINE OPERATION. FUEL SERVO BECOME ROSDR 2004FA0000383Engine · making metalDURING A PHASE INSPECTION, SOME METAL WAS FOUND IN THE FILTER, TOOK OIL SAMPLE FROM OIL COOLER, REMOVED SUCTION SCREEN, MORE METAL WAS FOUND, SENT FILTER AND OIL TO LAB FOR ANALYSIS, SENT METAL FROM SCREEN, WAS ADVISED THAT THE SCREEN MATERIAL WAS FROM BEARINSDR SO1450Rod · bentDURING PREFLIGHT, PILOT FOUND LT AILERON CONTROL ROD BENT AT AILERON SURFACE. AIRCRAFT GROUNDED AND TAKEN TO MAINTENANCE. REMOVED LT AILERON CONTROL ROD AND FOUND IT TO BE BENT APPROXIMATELY 25 DEGREES JUST AFT OF AFT ROD END BEARING. REPLACED WITH NEW ROD.SDR 2004FA0000395Servo · inoperativeFUEL MIXTURE CONTROL ARM WILL NOT ROTATE TO (IDLE CUT-OFF) POSITION.SDR 2004FA0000300Bridal Cable · wornROLL SERVO BRIDLE CABLE WAS IMPROPERLY INSTALLED. TOP PORTION OF CABLE WAS WRAPPED AROUND PRIMARY AILERON CABLE, CAUSING BRIDLE CABLE TO CHAFE AGAINST A PULLEY FLANGE. INSTALLATION OF CABLE ASSEMBLY OCCURRED AT THE FACTORY AND HAS NOT BEEN REPLACED SINCE AIRSDR CA040205005Drive Assy · jammed(CAN) STARTER DRIVE ONCE ENGAGED DID NOT RETRACT JAMMED OUTWARD.SDR 2004FA0000261Master Cylinder · inoperativePILOT REPORTED NO RESPONSE FROM LT BRAKE PEDAL, FOUND THAT BOTTOM LT BRAKE MASTER CYLINDER ATTACHMENT CLEVIS PIN MISSING. LOCATED CLEVIS PIN ON UPPERSIDE OF BELLY SKIN AND COTTER PIN. FOUND THAT COTTER PIN WAS BARELY BENT AND APPEARENTLY FELL OUT O F CLEVIS SDR 2004FA0000137Keeper · wornDURING A ROUTINE INSPECTION, AND WHILE ACCOMPLISHING SB 388, IT WAS DISCOVERED THAT THE VALVE KEY RETAINERS (P/N-17C21191) ON THE EXHAUST VALVE, WERE WORN WHERE THEY CONTACT THE ROTOR CAP. THE WEAR WAS RADIAL, AND THE DEPTH WAS ESTIMATED APPROXIMATELY .020 INCSDR 2004FA0000258Bulkhead · crackedDURING A PRE-FLIGHT INSPECTION THE PILOT NOTED A .7500 INCH CRACK IN THE SPINNER BULKHEAD. THIS CRACK WAS IN THE CORNER NEXT TO THE SPINNER MOUNT NUTPLATE. SEVERAL PREVIOUS M OR D ON THIS SAME PART.SDR 2004FA0000031Stud · meltedPOSITIVE TERMINAL ON ALTERNATOR MELTED. INSPECTED ALTERNATOR WIRING HARNESS FOR CORRECT ROUTING AND DAMAGE. PROBABLE CAUSE FOR THIS MALFUNCTION OCCURRED IN THE ALTERNATOR ITSELF, AS THE POSITIVE STUD AND NUT WERE RECOVERED WITH THE NUT IN THE TORQUED POSITION.SDR 2004FA0000099Contactor · failedRELAY, CONTACTOR FAILS UNDER LOAD ACCROSS TERMINALS. CAUSE IS CONTACTOR NOT DESIGNED TO HANDLE CONTINOUS LOAD, (CURRENT). SEVERAL FAILURES NOTED IN THE PAST. MFG WILL NOT ADDRESS THE PROBLEM. SEVERAL OCCURRENCES NOTED IN LAST 3 YEARS.SDR 2004FA0000100Contactor · failedRELAY, CONTACTOR FAILED UNDER LOAD ACROSS TERMINALS. CAUSE IS CONTACTOR NOT DESIGNED TO HANDLE CONTINOUS LOAD, (CURRENT). SEVERAL FAILURES NOTED IN PAST.SDR AUS20031263Injector · failed(AUS) ENGINE FUEL INJECTOR SYSTEM FAULTY. LIMITED INFORMATION PROVIDED.SDR 2004FA0000254Duct · misroutedDURING A ROUTINE INSPECTION, WE FOUND THAT THE PLASTIC GLOVEBOX WAS MELTED AT THE FORWARD RIGHT SIDE. WE FOUND THAT THE HEATER DUCTING WAS ROUTED UP AGAINST THE GLOVE BOX CAUSING THE BOX TO MELT. REOUTED HEAT DUCTING TO PREVENT FUTURE OCCURANCE.SDR 2004FA0000253Duct · misroutedDURING A ROUTINE INSPECTION, WE FOUND THAT THE PLASTIC GLOVEBOX WAS MELTED AT THE FORWARD RIGHT SIDE. WE FOUND THE HEATER DUCTING WAS ROUTED UP AGAINST THE GLOVEBOX CAUSING THE BOX TO MELT. REROUTED HEAT DUCTING TO PREVENT FUTURE OCCURANCE.SDR AUS20031252Brushes · worn(AUS) ALTERNATOR BRUSHES BADLY WORN. ALTERNATOR FAILED CAUSING WIRING TO BURN AND FAILURE OF ALTERNATOR CONTROL UNIT AND CURRENT SENSOR AND FUSING OF THE ALTERNATOR FIELD CIRCUIT BREAKER.SDR CA030930009Wire · burned(CAN) THE NAV. LIGHT CIRCUIT BREAKER/SWITCH WOULD TRIP INSTANTLY WHEN SELECTED ON. ALSO THE AMMETTER WOULD SPIKE TO 20+ AMPS FOR A MICRO-SECOND. I DEAD SHORT WAS DETECTED IN THE NAV LIGHT CIRCUIT. FURTHER INSPECTION REVEALED THAT, WITHIN THE LT WINGTIP THE LSDR CA030930007Bellcrank · worn(CAN) THE ELEVATOR BELLCRANK MAIN BEARING WAS FOUND SPINING LOOSE INSIDE THE BELLCRANK ASSEMBLY. THE BELLCRANK WAS WORN OUT BY THE OUTER PORTION OF THE BEARING. THE BEARING IS A PRESSED FIT, AND CANNOT BE REPLACED. THE ENTIRE ELEVATOR BELLCRANK ASSEMBLY HAD TSDR 2004FA0000283Pump · burnedPROBABLE CAUSE ENGINE COMPARTMENT FIRE OF UNDETERMINED SOURCE. REPORT CONCERNING SEPARATION OF FUEL LINE FROM FUEL PUMP. ACC REPORT NR IAD02FA086.SDR AUS20030838Pump · failed(AUS) FUEL BOOST PUMP FAILED. INVESTIGATION FOUND ONE VANE MISSING AND SIGNS OF ABRASION.SDR 2003FA0000639Fuel Control · out of adjustDURING A PRE TAKEOFF ENGINE CHECK, THE ENGINE WAS IDLING AT APPROXIMATELY 1000 RPM, AND WAS ROUGH. THE FUEL CONTROL WAS ADJUSTED...SDR 2003FA0000641Fuel Control · out of adjustDURING A RUNUP FOR A MAINTENANCE CHECK, THE IDLE RPM AS FOUND VERY LOW. IT WAS ADJUSTED AND CHECKED. THIS IS A PROBLEM WITH THIS FUEL CONTROL ENGINE COMBINATION THAT OCCURS REGULARLY.SDR 2003FA0000610Mount · debondedON THE NEW C-172 R AND S AIRCRAFT, THE WIRING UNDER THE CABIN FLOOR IS ATTACHED WITH TIE WRAPS TO ADHESIVE BACKED NYLON MOUNTS P/N S2606-1, THAT ARE ADHEARED TO THE AIRCRAFT SKIN. DURING PHASE 3 INSPECTION ON THIS AIRCRAFT WITH 1752.3 HOURS, FOUR MOUNTS WERE SDR 2003FA0000640Fuel Control · out of adjustDURING A PRETAKEOFF IDLE CHECK, THE IDLE WAS FOUND TOO LOW AND ROUGH. THE FUEL CONTROL WAS ADJUSTD AND THE IDLE SPEED AND MIXURE CONFIRMED CORRECT..SDR 2003FA0000525Plug · looseWHILE PRACTICING TOUCH AND GOES, THE INSTRUCTOR NOTICED A THIN FILM OF OIL ON THE WINDSHIELD. IT QUICKLY GOT WORSE. MADE EMERGENCY LANDING. MAINTENANCE DISCOVERED THE CRANKSHAFT PLUG HAD COME LOOSE. OIL LEVEL WAS AT 4.5 QTS. REPLACED CRANK PLUG, CHECKED ESDR 2003FA0000646Fuel Control · erraticDURING THE PRE TAKEOFF IDLE CHECK, THE IDLE RPM WAS FOUND VERY LOW. IT WAS ADJUSTED. THE IDLE MIXTURE/SPEED, ON THIS SERVO, IS VERY ERRATIC AND UNSTABLE WITHIN A VERY FEW NUMBER OF HOURS/DAYS.SDR 2003FA0000645Fuel Control · erraticDURING THE PRE TAKEOFF IDLE CHECK, THE IDLE RPM WAS FOUND VERY LOW. IT WAS ADJUSTED. THE IDLE MIXTURE/SPEED, ON THIS SERVO, IS VERY ERRATIC AND UNSTABLE WITHIN A VERY FEW NUMBER OF HOURS/DAYS.SDR 2003FA0000441Spinner · crackedDURING AN INSPECTION, THE SPINNER WAS FOUND CRACKED.SDR 2003FA0000443Manifold · inaccurateTHE PILOT REPORT A ROUGH ENGINE AT 1,000 FT. DURING SUBSEQUENT INSPECTION AND TROUBLESHOOTING, THE FUEL INJECTOR NOZZLES WERE CLEANED AND TESTED, THE FUEL MANIFOLD WAS REPLACED, AND THE FUEL SERVO WAS REPLACED.SDR 2003FA0000416Fuel Control · inaccurateDURING PRE TAKEOFF CHECK, THE IDLE WAS TOO LOW TO CONTINUE. THIS ENGINE/FUEL CONTROL COMBINATION REQUIRES SUBSTANTIAL ADJUSTMENT TO MAINTAIN THE CORRECT IDLE.SDR 2003FA0000415Spinner · crackedPILOT WROTE UP MISSING SCREW. UPON EXAMINATION THE SPNNER AND BULKHEAD WERE FOUND CRACKED.SDR 2003FA0000798Bolt · improper partTHE PROPELLER MOUNTING BOLTS ON NEW AC MODEL SEEM TO BE TOO SHORT. THEY DO NOT EXTRUDE AT ALL THRU THE CRANKSHAFT PRESSED THREADED BUSHINGS. USUALLY THE THREADS WILL EXTRUDE 2-3 THREADS THRU THE BUSHING. RECOMMENDATION IS TO HAVE A LONGER BOLT INSTALLED SO
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