Textron 208B
Service difficulty reports · 1,669
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 = '208B' 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 = '208B' 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 ENHA200620801Tire · deflatedAIRCRAFT EXPERIENCED LOSS OF TIRE PRESSURE LT MLG DURING ROLL OUT AND TAXI. WHEEL AND TIRE ASSY REPLACED, AIRCRAFT RETURNED TO SERVICE.SDR BSYA200600002Bleed Valve · inoperativePILOT ENROUTE, WHEN THE ENGINE POPPED AND STARTED TO SHUTDOWN WHEN IT POPPED AGAIN AND STARTED TO SHUTTER. PILOT ELECTED TO LAND, NO PROBLEMS. MFG FOUND BLEED VALVE MAKING ENGINE POP, REMOVED AND REPLACED BLEED VALVE OPS CHECKS GOOD.SDR CA060227004Turbine Blades · damagedTHE PILOT REPORTED A LOSS OF ENGINE POWER AND ATTEMPTED A FORCED LANDING. THE AIRCRAFT CRASHED DURING THE ATTEMPT. PRELIMINARY INVESTIGATION HAS REVEALED TURBINE BLADE DISTRESS. P&WC WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHSDR CA060125003Control Cable · damaged(CAN) DURING NORMAL INSPECTION IT WAS FOUND THAT ONE OF THE AILERON WING LOOP CABLES WAS WEARING INTO THE SIDE OF THE LIGHTNING HOLE OF THE FIRST WING RIB ON THE LT WING. THE CABLE WAS DAMAGED AS WELL. THE AIRCRAFT WAS GROUNDED UNTIL THE CABLE WAS REPLACED, SDR VLI2006F00001Bracket · crackedFLAP ACTUATOR BRACKET FAILED DURING NORMAL OPERATION RENDERING FLAP SYSTEM INOPERATIVE. INSTALLED KIT SK208-158. (K)SDR VLI2006F00000Bracket · crackedFLAP ACTUATOR BRACKET FAILED DURING NORMAL OPERATION RENDERING FLAP SYSTEM INOPERATIVE. INSTALLED KIT SK208-158. (K)SDR COEA0501753Unknown · unknownON TAKEOFF THE AIRCRAFT WOULD NOT GAIN ALTITUDE. AIRCRAFT CLEARED THE AIRPORT PROPERTY AND IMPACTED THE GROUND JUST AFTER THE FENCE. (K)SDR MPFACTUATOR1Actuator · inoperativeBOTH PRIMARY AND STAND-BY FLAP ACTUATOR WAS INOPERATIVE. ACTIVATION OF EITHER SYSTEM WOULD CAUSE THE RESPECTIVE CIRCUIT BREAKER TO OPEN. DISASSASEMBLY OF THE ACTUATOR REVEALED A SHEARED ROLL PIN AND ROUGH WORM SHAFT BEARING.SDR 2005AP052501Roll Pin · shearedBOTH PRIMARY AND STAND-BY FLAP ACTUATOR WAS INOPERATIVE. ACTIVATION OF EITHER SYSTEM WOULD CAUSE THE RESPECTIVE CIRCUIT BREAKER TO OPEN. DISASSEMBLY OF THE ACTUATOR REVEALED A SHEARED ROLL PIN AND ROUGH WORM SHAFT BEARING.SDR 2005AP012502Roll Pin · shearedBOTH PRIMARY AND STAND-BY FLAP ACTUATOR WAS IN-OPERATIVE. ACTIVATION OF EITHER SYSTEM WOULD CAUSE THE RESPECTIVE CIRCUIT BREAKER TO OPEN. DISASSEMBLY OF THE ACTUATOR REVEALED A SHEARED ROLL PIN AND ROUGH WORM SHAFT BEARING.SDR AU510001531Compressor · failedCABIN AIRCONDITIONING COMPRESSOR FAILED. FLUID LEAKING FROM REAR CASE AND ALL COVER BOLTS LOOSE. REAR COVER WAS REMOVED AND INTERNAL DAMAGE FOUND. SUSPECT DAMAGE CAUSED BY INCORRECT ROTATION OF COMPRESSOR DUE TO THIS MODEL OF COMPRESSOR NOT BEING MANUFACTURSDR AWH2006F00009Coupling · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IAW MM, FUEL PUMP COUPLING IN-SITU INSPECTION. MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED NEARLY TO THE POINT OF FAILURE. THE FUEL PUMP ASSEMBLY WAS REPLACED WITH A FRESH OVERHAULED USDR AWH2006F00001Coupling · corrodedPRECAUTIONARY INSPECTIO OF THE FUEL PUMP DRIVE SPLINE IAW MM. FUEL PUMP COUPLING INSITU INSPECTION. MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED. TH FUEL PUMP ASSY WAS REPLACED WITH A FRESH OVERHAULED UNIT AND THE AIRCRAFT RETURNED TO SERVSDR 2005F00113Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IAW MM, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED. THE FUEL PUMP ASSEMBLY WAS REPLACED WITH A FRESH OVERHAULEDSDR 2005F00112Pump · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IAW MM, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED. THE FUEL PUMP ASSEMBLY WAS REPLACED WITH A FRESH OVERHAULED SDR 2005F00111Pump · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IAW MM, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGED TO THE POINT OF NEAR FAILURE. THE FUEL PUMP ASSEMSDR 2005F00116Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR 2005F00115Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR 2005F00114Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR 5005120805Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR AWHA5005Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGESDR 120805BSpline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGESDR AWHA120805Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR CA051205003Engine · fodDURING CRUISE, THE PILOT HEARD A LOUD WHINING SOUND FROM THE ENGINE. MX FOUND THE WHINING STARTED AT 850 PROP RPM. THE RGB CHIP AND THE MAIN OIL FILTER WAS EXAMINED AND CLASS 3 UNACCEPTABLE DEBRIS IAW MM CHAP 79 WAS FOUND. THIS COUPLED WITH THE NOISE FROM TSDR CA051123004Indicator · stuck(CAN) AIRCRAFT WAS DEPARTING RUNWAY AND THE PILOT NOTICED ON TAKEOFF ROLL THAT THE RT AIRSPEED INDICATOR HAS STUCK AT THE 50KT INDICATION. THE PILOT DECIDED TO ABORT THE TAKEOFF AND RETURNED TO THE RAMP. MAINTENANCE INSPECTED THE SYSTEM AND MEL THE SYSTEM IAW SDR CA051129017Engine · power lossDURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED AND UNRECOVERABLE REDUCTION IN POWER ACCOMPANIED BY A REDUCTION IN FUEL FLOW AND COMPRESSOR SPEED. THE FLIGHT DIVERTED. P&WC WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESDR COE2006F00001Coupling · looseWHEN INSPECTING FUEL PUMP IAW CAB 05-18 AND PWC1645 FOR REDDISH-BROWN STAIN ON COUPLING SHAFT AREA. FOUND NO VISIBLE SIGN. COUPLING WAS LOOSE ON SHAFT WHEN COUPLING WAS REMOVED. FOUND SPLINES WORN ON FUEL PUMP AND COUPLING. THE SB MUST SUPPLY A MEANS TO RESDR CA051104004Engine · failed(CAN) THE ENGINE WAS REPORTED TO HAVE (FAILED) IN FLIGHT AND AN EMERGENCY LANDING WAS CARRIED OUT. THE AIRCRAFT CONTACTED POWER LINES AND SUBSEQUENTLY CRASHED INTO A HOUSE. PRELIMINARY EVALUATION OF THE ENGINE REVEALED NO ANOMALIES. MFG WILL INVESTIGATE THE SDR AU510002165Bolt · shearedHORIZONTAL STABILIZER FORWARD LT ATTACHMENT BOLT SHEARED. AIRCRAFT IS PNG REGISTERED.SDR HSY2005F00004Support · damagedDAMAGE TO NOSE GEAR SUPPORT. (K)SDR 2005FA0001428Plenum · corrodedWHILE REMOVING THE ENGINE FOR A SCHEDULED OVERHAUL, WE NOTICED 5 RIVETS SHEARED OF THE TOP HALF OF THE INDUCTION AIR PLENUM BAND ASSY. A SHEARED RIVET HEAD CAN EASILY FIT THRU THE ENGINE INLET SCREEN AND COULD BE INGESTED BY THE ENGINE CAUSING GREAT DAMAGE ORSDR 2005FA0001427Plenum · damagedWHILE REMOVING THE ENGINE FOR A SCHEDULED OVERHAUL, WE NOTICED 5 RIVETS SHEARED OFF THE TOP HALF OF THE INDUCTION AIR PLENUM BAND ASSEMBLY. A SHEARED RIVET HEAD CAN EASILY FIT THRU THE ENGINE INLET SCREEN AND COULD BE INGESTED BY THE ENGINE CAUSING GREAT DAMASDR 01100405Drag Link · brokenON RUN-UP BEFORE TAKEOFF, THE PILOT HEARD A POPPING NOISE AND RETURNED TO THE BLOCKS TO HAVE MAINTENANCE INSPECT THE NOSE LANDING GEAR. MAINTENANCE DISCOVERED THAT THE NOSE GEAR SPRING HAD BROKEN COMPLETELY AWAY AT THE REAR ATTACHMENT POINT (BEARING CAP/SUPPOSDR CA050926005Connector · melted(CAN) APPROXIMATELY 5 TO 10 MIN BEFORE LANDING THE PILOT NOTICED A FAINT SMELL OF SMOKE OR SOMETHING BURNING. EVERYTHING WAS OPERATING NORMALLY AND HE LANDED WITHOUT MISHAP. UPON INSPECTION, THE PROP HEAT WIRE CONNECTOR BETWEEN THE CIRCUIT BREAKER AND PROP DE-SDR PNSA050804Caliper · shearedON LANDING AT KCQ RIGHT BRAKE FAILED. MX FOUND TOP ANCHOR PIN OF RT BRAKE CALIBER SHEARED. BRAKE CAUSED DAMAGE TO WHEEL ASSY AND BRAKE TORQUE PLATE. REPLACED BRAKE TORQUE PLATE, ANCHOR PINS, WHEEL ASSY AND BRAKE PADS. AIRCRAFT RETURNED TO SERVICE.SDR CA050831005Blades · damaged(CAN) THE ENGINE WAS REPORTED TO LOSE POWER DURING TAKEOFF AND THE AIRCRAFT CRASHED. PRELIMINARY INVESTIGATION EVIDENCED FRACTURED COMPRESSOR AND POWER TURBINE BLADES. P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.SDR CA050824007Engine · malfunctioned(CAN) IN CRUISE, THE ENGINE EXHIBITED AN UNCOMMANDED INCREASE IN ITT. ENGINE POWER WAS REDUCED TO IDLE AND THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING. PWC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE, ONCE DETERMINED.SDR CA050725011Turbine Blades · fractured(CAN) THE ENGINE SUFFERED AN IN-FLIGHT SHUT-DOWN RESULTING IN A FORCED LANDING. SUBSEQUENT INSPECTION FOUND BIRD REMAINS IN THE ENGINE INLET AND HIGH PRESSURE COMPRESSOR. FURTHER INSPECTION REVEALED A FRACTURED COMPRESSOR TURBINE BLADE. P&WC WILL INVESTIGATSDR F2P2005F00000Mount · crackedDURING INSPECTION FOR A PILOT REPORTED ENGINE OIL LEAK, CRACKS WERE FOUND ON THE FORWARD ENGINE MOUNT. CRACKS ON BOTTOM LT CORNER ALONG WELD JOINING THE HORIZONTAL AND VERTICAL TUBE, MEASURES 2.5 INCHES AND 3.2500 INCHES IN LENGTH. CRACKS ON BOTTOM RT CORNERSDR CA050512003Bowl · crackedDURING DAILY INSPECTION IT WAS NOTICED THAT THE MAIN FUEL FILTER BOWL WAS WEAPING FUEL. MAINTENANCE INSPECTED THE ASSEMBLY AND DETERMINED THAT THE FUEL BOWL FILTER ASSEMBLY CASTING WAS CRACKED. THE AREA IN QUESTION WAS BETWEEN THE HANGER BRACKET AND CASTING. SDR CA050503008Support Bracket · cracked(CAN) ACCOMPLISHMENT INSTRUCTIONS, FOUND FLAP ACTUATOR SUPPORT BRACKET CRACKED. SERVICE KIT SK208-158 ORDERED AOG, WILL BE INSTALLED UPON RECEIPT.SDR 2005FA0001056Antenna · inoperativeFOUND LOWER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE. (K)SDR CA050419006Engine · failed(CAN) DURING CRUISE, THE ENGINE EXHIBITED A LOUD NOISE ACCOMPANIED BY A LOSS OF POWER. THE AIRCRAFT DIVERTED AND A DEAD-STICK LANDING WAS ACCOMPLISHED. INITIAL INVESTIGATION REVEALED A FRACTURED REDUCTION GEARBOX HOUSING AND POWER TURBINE BLADES WITH LOSS OSDR CA050527011Engine · failedDURING TAKEOFF ROLL, THE ENGINE CHIP DETECTOR ANNUNCIATED. THE TAKEOFF WAS ABORTED AND THE ENGINE WAS SHUT DOWN. SUBSEQUENT INSPECTION REVEALED HOT SECTION DAMAGE INCLUDING DISTRESSED COMPRESSOR TURBINE AND POWER TURBINE BLADESSDR CA050527013Cap · leakingDURING SERVICING, EXTERNAL OIL LEAKAGE WAS FOUND BECAUSE OF A LOSS OF THE OIL TANK CAP RETENTION. THIS WAS DEEMED AS RESULTING FROM A LOSS OF TORQUE OF THE CAP ASSEMBLY NUT.SDR 03032905Shutoff Valve · contaminatedDURING CLIMBOUT, OBSERVED A MIST OR CONDENSATION IN COCKPIT & INSIDE OF WINDSCREEN. PILOT SELECTED WINDSHIELD DEFROST WHICH ACCELERATED RATE OF CONDENSATION. DESELECTED DEFROST, CABIN HEAT & DONNED EMERGENCY O2. DECLARED EMERGENCY DUE TO SUSPECTED SMOKE & RSDR 2005FA0000550Rib · misinstalledUPON INSPECTION OF HORIZONTAL STABILIZER, MECHANIC NOTED THAT ALL RIVETS SECURING FORWARD FLANGE OF RIB P/N 2632021-25 TO FORWARD SPAR WERE MISSING. HOLES WERE DRILLED THRU WITH BARE METAL SHOWING (NO PRIMER IN HOLES). ASSUMPTION IS THAT RIVETS WERE OMITTED SDR HSYA01031505Indicator · smokeSMOKE COMING FROM THE RADAR INDICATOR.SDR HSY2005F00000Indicator · unserviceableAIR RETURNED, DUE TO PILOT EXPERIENCING SMOKE IN THE COCKPIT. PILOT NOTICED THE RADAR INDICATOR BLINKING OFF AND ON. MAINT CONFIRMED THAT THE SMOKE WAS COMING FROM THE RADAR INDICATOR. THE RADAR SYSTEM WAS DEFERRED AND IT WAS CONFIRMED THAT NO POWER WAS TO SDR CA050317003Retaining Ring · deformed(CAN) A REVIEW OF AIRCRAFT RECORDS SHOWED THE ENGINE WAS ASSEMBLED USING SHROUD SEGMENTS WITH A RETAINING RING. THE ENGINE WAS BORESCOPE INSPECTED IAW SB 1631. 2 SEGMENTS WERE FOUND TO BE AXIALLY DISPLACED WITH COMPRESSOR TURBINE BLADE TIP RUB ON ONE SEGMENT
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