Schweizer 269C
Service difficulty reports · 118
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 = '269C' 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 = '269C' 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 98ZZZX3854Rod · failedAIRCRAFT WAS HOVERING. LOUD BANG WAS HEARD, FOLLOWED BY ENGINE SUDDEN STOPPAGE. AIRCRAFT CONTACTED GROUND HARD CAUSING LANDING GEAR DAMAGE. SUBMITTER STATED IT APPEARED THE NR 3 CYLINDER PISTON CONNECTING ROD FAILED. ENGINE WAS DUE OVERHAUL IN APPROXIMATELSDR 2000ZZZX270Piston Pin · brokenC/W ROUTINE 50-HOUR OIL CHANGE. FOUND CHUNK OF ALUMINUM IN DRAIN PLUG, ALUM FND IN OIL SCREEN, FILTER. PULLED ALL SPARK PLUGS, FOUND OIL ON NR 4 CYL PLUGS. PULLED NR 4 CYL. FOUND NO PISTON PIN CAPS IN PLACE AND A LARGE CHUNK OF MATERIAL BROKEN OFF INSIDE OSDR AU981036Blade · delaminated(AUS) TAIL ROTOR BLADE LEADING EDGE ABRASION STRIP DEBONDED. AREA OF DELAMINATION APPROXIMATELY 50.8MM BY 25.4MM (2 INCHES BY 1 INCH). PART TC: 2,267.SDR AU980770Control Rod · worn(AUS) TAIL ROTOR CONTROL ROD RUBBING ON `POP' RIVET TAIL. THE RIVET HAD BEEN INSTALLED SOME TIME IN THE PREVIOUS TWO YEARS TO SECURE A BRACKET UNDER THE TAIL BOOM FOR SECURING THE STATIC SYSTEM TUBE. PART TOTAL CYCLES: 161.SDR AU980769Fitting · improper part(AUS) CLUTCH ACTUATOR FITTING INCORRECT PART. FITTING P/N 269A5490 IS USED ON 269A AND 269B MODELS ONLY. FITTING P/N 269A5491-5 IS USED ON 269C MODELS. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.SDR AU980735Pinion · damaged(AUS) MAIN ROTOR TRANSMISSION PINION GEAR TEETH BRINELLED IN AREA INDICATED IN SB B 244-3. PART TOTAL CYCLES: 896.SDR AU980734Gear · damaged(AUS) MAIN ROTOR TRANSMISSION RING GEAR TEETH BRINELLED IN AREA INDICATED IN SB B 244-3. PART TOTAL CYCLES: 896.SDR 98ZZZX2785Fitting · failedPILOT REPORTED THE TAIL BOOM FORWARD ATTACH FITTING FAILED DURING A SUDDEN APPLICATION OF POWER WHILE RECOVERING FROM A SIMULATED AUTOROTATION. OTHER EVIDENCE SUGGESTS THE FITTING LUG MAY HAVE FAILED DUE TO TAIL ROTOR CONTACT WITH SOFT GROUND.SDR 98ZZZX2031Valve Guide · defectiveDURING PRE-TAKEOFF RUNUP, ENGINE STARTED VIBRATING AT MID-RPM RANGE AND WOULD NOT ACCELERATE. FOUND NR 3 AND NR 4 EXHAUST VALVES STICKING. REAMED GUIDES TO PROPER DIMENSION. ENGINE HAS 107.6 HOURS SINCE FACTORY OVERHAUL. THIS OPERATOR HAS HAD NUMEROUS LOW SDR CA980402002Bearing · cracked(CAN) ROUGHNESS FOUND DURING INSPECTION. PITCH HOUSING DISASSEMBLED AND INBOARD OUTER RACE FOUND CRACKED.SDR 98ZZZX1027Strap · brokenDURING A ROUTINE PRE-FLIGHT INSPECTION, THE PILOT DISCOVERED THE INBOARD FUEL TANK STRAP WAS LOOSE. CLOSER INSPECTION REVEALED THE STRAP WAS BROKEN. THE BREAK WAS ACROSS TWO SPOT WELDS MADE DURING MANUFACTURE.SDR AU980167Damper · delaminated(AUS) MAIN ROTOR ELASTOMERIC DAMPERS FAULTY. AIRCRAFT HAD SUFFERED A HARD LANDING/SUDDEN STOPPAGE APPROXIMATELY 150 HOURS PREVIOUSLY.INSPECTION THEN FOUND NIL DEFECTS BUT SINCE THAT TIME THE AIRCRAFT HAD DEVELOPED A VIBRATION AND AN INSPECTION HAD FOUND ONE DASDR HEEA0012660Indicator · failedHEADING INDICATOR INOPERATIVE.SDR AU980029Torque Tube · worn(AUS) COLLECTIVE TORQUE TUBE WORN BY BOOT PNO 269A-4031-19 LOCATED AT REAR OF CABIN.SDR HEEA0012527Indicator · sticksHSI CARD INTERMITTENTLY STICKS IN SLAVE MODE.SDR HEEA0012513Hsi Control · failedHSI HEADING POINTER WILL NOT INDICATE.SDR HEEA0012151Gyro · failedGYRO POINTS OFF COURSE.SDR AU971471Engine · failed(AUS) ENGINE SUFFERED A POWER LOSS FOLLOWED BY A STOPPAGE. AIRCRAFT CRASHED.SDR AU971481Pulley · worn(AUS) DRIVE BELT IDLER PULLEY HAD THE ANODIZED COATING WORN THROUGH IN ALL GROOVES.SDR AU971480Scroll · failed(AUS) ENGINE SCROLL ASSEMBLY LOWER MOUNT SEPARATED. UPPER RH BRACKET PNO 269A8597 WAS ALSO FOUND TO BE UNSERVICEABLE. THE SCROLL WAS FOULING ON THE IMPELLER.SDR AU971478Hub · mis installed(AUS) ENGINE TO TRANSMISSION UPPER CLUTCH HUB INSTALLED THE WRONG WAY AROUND. BEARING SEAT SHOULDER SHEARED OFF. PERSONNEL/MAINTENANCE ERROR.SDR AU971476Valve · illegal mod(AUS) INTAKE ALTERNATE AIR VALVE ILLEGALLY MODIFIED. THE VALVE WAS SEALED CLOSED WITH SEALANT AND A PLASTIC OIL BOTTLE WAS GLUED OVER THE TOP. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED MODIFICATION.SDR HEEA0011454Idler Pulley · groovedIDLER PULLEY GROOVED BEARING SHAFT.SDR HEEA0011298Gyro · driftsGYRO DRIFTS OFF 30 DEG IN FLIGHT.SDR HEEA0010856Shaft · corrodedCORROSION ON DRIVESHAFT.SDR HEEA0010855Idler Pulley · failedIDLER PULLEY DAMAGED AT BEST CLOSURE. GROOVES WITHIN BEARING FAILED.SDR 97ZZZX3733Bolt · failedAT 500.0 HOURS TSO, THE ENGINE FAILED IN-FLIGHT. ENGINE TEAR DOWN REVEALED NR 4 CONNECTING ROD HAD FAILED, PUNCHING A HOLE THROUGH THE CRANKCASE. THE TWO CONNECTING ROD BOLTS HAD FAILED ALLOWING THE CONNECTING ROD TO COME LOOSE FROM THE CRANKSHAFT. THE BOLTSDR 97ZZZX3449Cover Assy · jammed throttleFLIGHT AFTER ANNUAL INSP FOR M/R TRACK AND BALANCE, THROTTLE STUCK FULL ON IN CRUISE FLT NOT ALLOWING REDUCTION IN POWER WITHOUT OVERSPEED OF ENG AND ROTOR. CAUSE FOUND IN-FLIGHT AND CORRECTED. BETWEEN PILOT'S AND COPILOT'S SEAT IS A VERTICAL PANEL THAT WHENSDR HEEA0010321Fuel Pump · failedFUEL PUMP HAS NO FUEL PRESSURE.SDR HEEA0010059Gyro · faultyCOMPASS RING LOCKS WHEN VHF IS KEYED BETWEEN 118.0 TO 126.0 MHZ. SENT FOR INSPECTION AND REPAIR.SDR HAIHEEA9951Blade · crackedBLADE IS CRACKED. (CRACK NEAR BUTT END)SDR AU970558Case · broken(AUS) MAIN ROTOR TRANSMISSION UPPER CASE FLIGHT CONTROL SYSTEM LH MOUNTING LUG BROKEN - INDICATIONS APPEAR THAT THE LUG HAD BEEN CRACKED FOR SOME TIME - SUSPECT MOUNTING BOLT OVERTORQUED DURING INSTALLATIONSDR HAIHEEA9859Cylinder · defectiveCYLINDER DOES NOT PERFORM TO SPECS.SDR HAIHEEA9569Blade · separationM/R BLADE SEPARATED ON TRAILING EDGE.SDR AU970348Vent · blocked(AUS) FUEL TANK VENT BLOCKED BY MUD WASP NESTSDR 97ZZZX1237Cylinder · defectiveAFTER THIS CYLINDER WAS INSTALLED, THE ENGINE OIL CONSUMPTION INCREASED. EVEN AFTER A SUFFICIENT BREAK-IN PERIOD, THE CONSUMPTION DID NOT DROP. AFTER APPROXIMATELY 162 HOURS, THE ENGINE RAN EXTREMELY ROUGH EVEN WITHOUT THE MAIN ROTOR ENGAGED. THE SPARK PLUGSDR 97ZZZX912Gear Tooth · chippedDURING AIRCRAFT RUN-UP, ROTOR TACHOMETER WENT TO ZERO. FOUND ONE TOOTH ON RING GEAR CHIPPED. FOUND CHIP JAMMED IN OIL PUMP GEARS WHICH CAUSED OIL PUMP DRIVESHAFT TO SHEAR. SCHWEIZER SB 244.2 ADDRESSES THIS SUBJECT. THIS IS ALSO ADDRESSED IN THE 50/100 HR CSDR 97ZZZX962Cylinder · studs brokeON TWO DIFFERENT SCHWEIZER HELICOPTERS EQUIPPED WITH HIO360D1A ENGINES, NR 2 CYLINDER BROKE 6 BASE STUDS. THE TWO THROUGH-STUDS REMAINED INTACT IN BOTH CASES. ONE ENGINE HAD 932 HOURS AND THE OTHER 1,424 HOURS SINCE MAJOR OVERHAUL. BREAKS ARE CLEAN WITH NO SDR 97ZZZX961Cylinder · studs brokeON TWO DIFFERENT SCHWEIZER HELICOPTERS EQUIPPED WITH HIO360D1A ENGINES, NR 2 CYLINDER BROKE 6 BASE STUDS. THE TWO THROUGH-STUDS REMAINED INTACT IN BOTH CASES. ONE ENGINE HAD 932 HOURS AND THE OTHER 1,424 HOURS SINCE MAJOR OVERHAUL. BREAKS ARE CLEAN WITH NO SDR 97ZZZX209Guide · wornFOUND LOW COMPRESSION (30/80) DURING NORMAL MAINT INSPECTION. REMOVED CYL AND FOUND .009 INCH WEAR AT PORT END OF EX GUIDE AND .002 INCH WEAR ON VALVE STEM. THIS WAS A LYCOMING FACTORY NEW CYL KIT INSTALLED DURING RECENT MAJOR OVERHAUL.SDR 97ZZZX91Fuel Sender · arm bentPILOTS MADE PRECAUTIONARY LANDING DUE TO ILLUMINATION OF LOW FUEL LIGHT. AFTER INVESTIGATION, FOUND THAT THE FUEL SENDER FLOAT CONTACTED THE LOW FUEL SENDING UNIT NOT ALLOWING THE FLOAT TO DROP ANY FURTHER,THEREFORE, THE GAUGE CONTINUED TO READ APPROX 8 GALLOSDR 97ZZZX93Engine · failedTHE ENGINE WAS REMOVED FROM THE A/C FOR A VIBRATION OF UNKNOWN CAUSE WHICH WAS DISCOVERED DURING A POST-INSPECTION RUN-UP. THE USUAL TROUBLESHOOTING PROCEDURES DID NOT PRODUCE SATISFACTORY RESULTS. THE COMPLETE ENGINE WAS SENT BACK TO THE LYCOMING FACTORY FOSDR AU961048Droop Stop · cracked(AUS) MAIN ROTOR DROOP STOP RING CRACKED IN SEVERAL PLACESSDR AU960970Points · out of adjust(AUS) MAGNETO POINTS GAP TOO SMALLSDR AU960895Shaft · fractured(AUS) LH MAGNETO BREAKER POINT DRIVE SHAFT FRACTURED IN AREA OF CAM SLOTSDR 96ZZZX3407Line · chafed'THE INCIDENT OF HELICOPTER HAVING AN ENGINE FAILURE WAS CAUSED BY AN OIL LEAK FROM THE OIL LINE FROM THE ACCESSORY SECTION OF THE AFT OIL COOLER. THE LINE CHAFED THROUGH ON AN ADJACENT LINE.' SUBMITTER STATED THIS COULD HAVE BEEN PREVENTED BY BETTER SECURINSDR 96ZZZX2922Attach Fitting · crackedDURING ROUTINE INSPECTION, FOUND EXCESSIVE PLAY WHEN INSPECTING SECURITY OF VERTICAL STABILIZER. DISCOVERED LOOSE ATTACHMENT HARDWARE AT FORWARD END OF THE ATTACHMENT OF THE TAILBOOM ASSEMBLY. SUBMITTER RECOMMENDS A RETORQUE OF ATTACHMENT HARDWARE AT A CERTASDR AU960464Drive Shaft · rusted(AUS) MAIN ROTOR DRIVE SHAFT (MAST) BORE BADLY RUSTEDSDR 96ZZZX1036Clutch Cable · brokenWHILE HERDING CATTLE, PILOT LANDED TO OPEN GATE. PILOT HEARD A LOUD POP. ON INVESTIGATION, HE FOUND THE CLUTCH CABLE BROKEN. FURTHER INVESTIGATION REVEALED THE CABLE BROKE AT SWAGED BALL END. THIS CABLE ASSY IS NOT INSPECTED UNTIL THE 400-HOUR INSPECTION ESDR 96ZZZX1042Clutch Cable · failedWHILE HERDING CATTLE AT 75 FEET, AGL. PILOT HEARD A LOUD BANG AND ROTOR RPM DECREASED AND ENGINE RPM INCREASED. AIRCRAFT IMPACTED GROUND CAUSING SUBSTANTIAL DAMAGE TO THE AIRCRAFT. INVESTIGATION OF THE NOISE REVEALED THE CLUTCH CABLE HAD BROKEN AT CABLE END
Back to Schweizer 269C