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 AWHA1120Wire · shortedDEPARTING, EXPERIENCED SMOKE IN THE COCKPIT. THE PILOT JUST HAVING ROTATED REDUCED POWER AND LANDED IMMEDIATELY. ASKED BY CONTROL, STATUS OK, BUT NEEDED TO RETURN TO HANGER. NO EMERGENCY WAS DECLARED. MAINTENANCE HAD JUST PERFORMED A MINI CHECK ON THE AIRCSDR CA021118009Alternator(CAN) PILOT REPORTED STANDBY ALTERNATOR INOP LIGHT CAME ON. THE SYSTEM WAS SHUT DOWN AND RETURN TO BASE. THE ALTERNATOR WAS FOUND TO BE UNSERVICABLE. A SEARCH OF THE AIRCRAFT RECORDS FOUND THAT THIS WAS T HE ORIGINAL ALTERNATOR. THERE IS NO T.B.O. PUT ON THISDR 2003F00144Bracket · crackedPRIMARY FLAP MOTOR CB POPPED WHEN SELECTING FULL FLAPS IN FLT. ON GROUND PROBLEM COULD NOT BE DUPLICATED, RIGGING CHECKED. FURTHER MAINT INSP REVEALED FORE AND AFT SUPPORT BRACKET, OF FLAP MOTOR, BUCKLING AND COMPLETE TRANSVERSE CRACKS OF THE AFT SUPPORT BRSDR 2003F00025Wire · faultyGFK - FLT 7563 - DURING CRUISE, THE PILOT NOTICED THE CIRCUIT BREAKER FOR THE PROP ANTI-ICE WAS OPEN. THE PITOT RESET THE CIRCUIT BREAKER, AND A BURNED PLASTIC SMELL WAS EMANATING FROM THE INSTRUMENT PANEL NEAR THE PROP ANTI-ICE AMMETER. POWER WAS REMOVED FRSDR AUS20021250Controller · faulty(AUS) AUTOPILOT COMPUTER CONTROLLER FAULTY.SDR JOU2002F00002Wire · chafedPILOT REPORTED FLASHING BEACON TRIPPED CIRCUIT BREAKER INTERMITTENTLY. TROUBLESHOT BEACON CIRCUIT AND FOUND WIRE INSULATION CHAFING ON RIB LOCATED IN RUDDER FIN TIP ASSEMBLY. CONVELEX TUBING WAS FOUND INSTALLED ON WIRE HARNESS, IT WAS NOT SECURED TO PREVENTSDR CA021016032Mount · cracked(CAN) CRACK FOUND IN LOWER CORNERS OF ENGINE MOUNT RING.SDR HSY2002F0000ABulkhead · crackedSTRUCTURAL DEFECT DISCOVERED DURING SCHEDULED INSPECTION (PHASE 5). METAL FATIGUE, CANTED BULKHEAD, STRUCTURAL REPAIR INITIATED, AND WORK IS IN PROCESS.SDR D5H2002F00000Pin · loosePILOT REPORTED SMOKE IN COCKPIT 30 MINUTES INTO FLIGHT. CONNECTOR FROM PROPELLER HEAT CIRCUIT BREAKER (P-186/J-186). CONNECTOR, 12 GAUGE WIRE(HA-36). MAINTENANCE CREW FOUND CONNECTOR FULLY ENGAGED AND STILL ATTACHED TO WIRE BUNDLE. MAINTENANCE FOUND TERMINSDR CA020905008Tire · damaged(CAN) AFTER TOWING AIRCRAFT OUT FOR DEPARTURE A BULGE WAS FOUND IN THE TIRE. THE WHEEL ASSEMBLEY WAS REPLACED WITH A OVERHAULED UNIT.SDR CA020820007Cooling Fan · failed(CAN) AIRCRAFT RETURNED TO BASE DUE TO SMOKE AND ELECTRICAL SMELL IN COCKPIT. ALL AVIONICS EQUIPMENT, WIRING, LIGHTING, RHEOSTATS, INSPECTED SATISFACTORY. FAULT FOUND IN GPS COOLING FAN. THE FAN WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.NO FURTHSDR BSY2002F00020Wire · looseON TAKE OFF OUT OF BOSTON, SPARKS WERE FLYING OUT FROM UNDERNEATH PILOTS PANEL, RETURNED TO BASE. FOUND EXPOSED WIRE OUT OF CONNECTOR P160 ON WIRE NR HA20 ON PROPELLER DEICE CIRCUIT, SHORTED ON SIDE PANEL REPAIRED CONNECTOR, OPS GOOD.SDR BSY2002F00016Latch · failedTOP AFT CARGO DOOR CAME OPEN AFTER TAKEOFF. REBUILT UPPER CABIN LATCH ASSEMBLY OPS CHECK GOOD.SDR 2002FA0000899Nut · crackedFOUND RIGHT LOWER WING STRUT ATTACH HARDWARE LIGHTLY CORRODED. FURTHER INSPECTION FOUND THAT NUT WAS COMPLETELY CRACKED THROUGH. NEW NUT AND BOLT INSTALLED. PART MAY HAVE BEEN OVERTORQUED UPON INSTALLATION.SDR BSY2002F00013Spring · out of adjustTOP CARGO DOOR CAME OPEN ON TAKEOFF, RETURNED TO AIRPORT. ADJUSTED SPRING TENSION ON UPPER DOOR HANDLE. OPS CHECK GOOD.SDR HSY2002F00000Barrel · burstFOUND NOSE GEAR SHIMMY DAMPNER BURST AT SNAP RING END OF SHIMMY DAMPNER CYLINDER.SDR CA020529005Latch · loose(CAN) WHILE ON A BIRD DOGGING MISSION OVER A FIRE. THE AIRCRAFT WAS IN A TURN OVER THE TARGET, A THUMP WAS HEARD, AN INITIAL SEVERE VIBRATION WAS FELT, ON CLIMBING TO ALTITUDE THE VIBRATION BECAME INTERMITTENT. THE AIRCRAFT RETURNED TO BASE, UPON ARRIVAL AT THSDR CA020607008Connector · damaged(CAN) CESSNA SERVICE BULLETIN CAB00-11. THIS SERVICE BULLETIN, WHICH IS OPTIONAL, WAS OUT ON OUR AIRCRAFT AND A SEVERELY BURNT CONNECTOR WAS FOUND.SDR 2003FA0000215Inverter · failedDIRECTIONAL GYRO FAILED DUE TO UNACCEPTABLE INSTALLATION OF A MD26-28 INVERTER WITH ITS 26V AC OUTPUT IN PARALLEL WITH THE KG102A 26V AC OUTPUT. THIS WAS DONE IN ERRO TO BOOST THE CURRENT CAPACITY ON THE 26V AC LINE. CANNOT PARALLED INVERTER OUTPUT UNLESS THSDR 2002FA0000550Hub · crackedPROPELLER WAS DISASSEMBLED AND INSPECTED FOR OVERHAUL. PROPELLER HUB WAS STRIPPED, ETCHED AND DYE PENETRANT INSPECTED. INDICATIONS OF CRACKS WERE APPEARANT AT 5 LOCATIONS ON THE REAR HALF OF THE HUB NEXT TO THE REAR BETA ROD BUSHING SOCKETS. EDDY CURRENT INSDR WO56083Shaft · brokenTHE ELEVATOR TRIM WHEEL SHAFT IN THE COCKPIT CONTROL QUADRANT WAS FOUND TO BE BROKEN. THE BREAK IN THE SHAFT WAS WHERE A MOUNTING/ALIGNING PLATE WAS WELDED TO THE SHAFT. THE TRIM WHEEL, WITH THE SPROCKETS AND END OF THE BROKEN SHAFT ASSY, FELL OFF RELEIVING TSDR 2002F00319Gear Shaft · excess playDURING A 100 HOUR INSPECTION, LEAK WAS NOTED ON ACCESSORY DRIVE UNIT. FURTHER INSPECTION REVEALED THAT THE FEMALE SPLINES IN THE ENGINE WERE WORN TO APPROX 80 PERCENT, SAME AS THE MALE END. SUGGEST AN ON TIME INSPECTION TO DETERMINE AMOUNT OF WEAR SINCE THERSDR CA020408014Gyro · failed(CAN) TAKEOFF RUNWAY CLIMBING THROUGH 4,500 FT. THE PILOT REPORTED A COMPLETE AVIONICS FAILURE, AND THEN A RETURN TO NORMAL OPERATION. CONDUCTING AN I.F.R. APPROACH TO RUNWAY. THE PILOT REPORTED AN ERRATIC HSI CDI. TOWER GRANTED A CONTACT APPROACH. THE AIRCRASDR 2002F00209Drive Shaft · wornDURING A 100 HOUR INSPECTION, LEAK WAS NOTED ON THE AIR CONDITIONING DRIVE UNIT. FURTHER INSPECTION REVEALED THE SPLINES OF THE MALE END OF DRIVE WORN OVER 80 PERCENT. FURTHER INSPECTION REVEALED THE FEMALE END IN THE ENGINE WERE WORN THE SAME AMOUNT.SDR DKB2002F00000Cable · brokenRIGHT FLAP CABLE THAT ATTACHES TO THE OUTBOARD END OF FLAP, FOUND WITH BROKEN STRANDS, WHERE THE CABLE IS SWAGED TO THE TERMINAL THAT CONNECTS TO THE FLAP.SDR 2002FA0000341Pump · shearedENGINE FAILED IN FLIGHT DUE TO SHEARED FUEL PUMP DRIVE, AIRCRAFT LANDED SAFELY IN FARMERS FIELD. NO AIRCRAFT DAMAGE. SUGGEST MANDATORY DRIVE REPLACEMENT AT EACH OVERHAUL.SDR 2002FA0000176Pump · failedHAD AN ENGINE FAILURE WHICH RESULTED IN THE AIRCRAFT LANDING SHORT OF THE AIRPORT. NO ONE WAS INJURED AND THE AIRCRAFT WAS NOT DAMAGED. ENGINE QUIT DUE TO ENGINE DRIVEN FUEL PUMP FAILURE. FUEL PUMP WAS REMOVED, A NEW PUMP INSTALLED, AND THE AIRCRAFT RETURNESDR 2003F00012Brake Assy · contaminatedBZN - FLT 8771 - LEFT BRAKE WAS SPONGY AND HAD MINIMAL EFFECTIVENESS. AIR ENTRAPMENT IN THE BRAKE SYSTEM. BLED BOTH LEFT AND RIGHT BRAKE SYSTEMS, OPERATIONALLY CHECKED OK. NO EVIDENCE OF LEAKAGE. (M)SDR CA020128004Doubler · cracked(CAN) THE LOWER FWD DOUBLER IS SITUATED ON BOTTOM OF FIREWALL & SUPPORTS NOSEGEAR SPRING ATTACH. DOUBLER FOUND CRACKED ON ITS LT WEB NEAR BOTTOM.SDR CA020118011Actuator · failed(CAN) AFTER TAKEOFF FROM YHM, THE AIRCRAFT LOST ELEVATOR TRIM ELECTRICAL AND MANUAL CONTROL AND THE AUTOPILOT FAILED. THE AIRCRAFT RETURNED TO THE AIRPORT. MAINTENANCE INVESTIGAITON FOUND ONE OF THE TWO RODS ON THE LT ELEVATOR TRIM ACTUATOR WAS BINDING A LITTLSDR AUS20011412Lever · cracked(AUS) ENGINE INERTIAL SEPARATOR SELECTION LEVER CRACKED AT MID POINT.SDR CA011219007Placard · missing(CAN) AIRSPEED LIMIT PLACARD NOT INSTALLED ON COMPANY PER T.C. A37CE.SDR AUS20011319Exhaust Pipe · cracked(AUS) ENGINE PRIMARY EXHAUST DUCT CRACKED AND HOLED. HOLE WAS APPROXIMATELY228.6MM (9IN) BY 146MM (5.75IN). ESCAPING EXHAUSTGAS DAMAGED OIL COOLER SHROUD RUBBERS AND DISCOLOURED THE PAINT ON THE LOWER RH COWL.SDR AUS20011336Circuit Breaker · failed(AUS) NR 1 AVIONICS BUS CIRCUIT BREAKER/SWITCH INTERNAL FAILURE.SDR 2001FA0000669Resistor · failedPROPELLER ANTI-ICE VARISTOR MELTED PLUGS. PLUGS SEEM TO OPEN AND WEAR CAUSING INTERMITTENT POWER TO BRUSH BLOCK, DUE MOST LIKELY TO VIBRATION. CHANGING CONNECTORS WOULD FIX PROBLEM.SDR CA011210013Wire · shorted(CAN) NAV. LIGHT CIRCUIT BREAKER WAS FOUND POPPED THE WIRES TO THE LIGHT IN THE TAIL CONE WERE SHORTED TOGETHER. THESE 2 WIRES SHORTED PORTION WERE REMOVED AND THE WIRES SPLICED TOGETHER. THERE ARE TIE-WRAPS HOLDING THE WIRES TO THE SIDE OF THE TAIL CONE.SDR CA011116013Actuator · seized(CAN) ON APPROACH FLAPS SELECTED FROM 10 TO 20 AS FLAPS TRAVELLED THROUGH APPROXIMATELY 15 DEGREES THE FORWARD FLAP MOTOR FAILED AND BROKE FREE OF THE TRANSMISSION/JACKSCREW ASSY. THIS CAUSED THE FLAP ACTUATOR ASSEMBLY TO BRAKE FREE OF THE ATTACHING STRUCTURESDR CA011105004Actuator · stuck(CAN) PILOT REPORTED IN FLIGHT FAILURE OF FLAP SYSTEM LOCKED IN ONE POSITION. RETURNED TO MAINTENANCE BASE AND REPLACED FLAP ACTUATOR. AIRCRAFT RETURNED TO SERVICE.SDR CA011105001Flange · cracked(CAN) THE EXHAUST FLANGE WAS FOUND CRACKED AT THE FORWARD RADIUS IN 3 SPOTS. THERE IS A HOLE IN THE FLANGE THAT LINES UP WITH THE THREADS OF A BOLT FROM THE OIL COOLER. THIS HOLE DID NOT LINE UP WITH THE BOLT AND PRODUCED STRESS ON THE FLANGE RESULTING IN THE SDR CA011019001Gcu(CAN) DURING CRUISE, PILOT NOTICED STANDBY POWER ON ANNUNCIATOR FLASHING FOLLOWED SHORTLY BY THE STANDBY POWER INOP ANNUNCIATOR ON STEADILY.THIS WAS FOLLOWED BY THE GENERATOR OFF ANNUNCIATOR ILLUMINATING.BOTH GENERATOR POWER AND STANDBY POWER COULD BE RETURNEDSDR COE2001F00000Gyro · failedON CLIMBOUT AFTER DEPARTURE OF FLIGHT HSI(ARTIFICIAL HORIZON) AND RMI(RADIO MAGNETIC INDICATOR) FLAGGED. PILOT HAD NOT YET ENTERED IMC(INSTRUMENT MET SYSTEM) BUT CONTINUED FLIGHT WOULD REQUIRE THIS SYSTEM. PILOT INITIATED AIR TURNBACK AND LANDED WITHOUT INCISDR UNI2001F00000Fuel Line · splitWHILE PERFORMING A ROUTINE PERFORMANCE RUN THE TORQUE AND FUEL FLOW DROPPED. FOUND METERED FUEL FLOW TUBE FROM FUEL FLOW TRANSMITTER TO FCU SPLIT ON INBOARD SIDE ABOUT 1 INCH LONG IN THE CENTER BEND RADIUS. NEW TUBE INSTALLED, LEAK CHECKED AND RETURNED TO SESDR AUS20011140Lever · broken(AUS) FUEL CONDITION LEVER BROKE AT THE LOWER BEND IN THE CONTROL KNOBARM.SDR COE2001F00001Servo · misalignedON CLIMB OUT FOR DEPARTURE, PILOT EXPERIENCED BINDING IN THE AILERON CONTROL SYSTEM. THE PILOT INITIATED AN AIR TURN BACK AND LANDED WITHOUT FURTHER INCIDENT. NO INFLIGHT EMERGENCY WAS DECLARED. TROUBLESHOOTING REVEALED THE COVER ON THE ROLL SERVO WAS MISALSDR CA011017008Screw · damaged(CAN) FLIGHT CREW REPORTED JAMMED ELEVATOR TRIM. INSPECTION REVEALED DAMAGED SCREW THREADS ON THE ELEVATOR TRIM ACTUATOR (PARTS ENCLOSED).SCREW P/N 2661215-8 INTERNAL SCREW P/N 2661215-6SDR 2001FA0000404Mount · crackedDURING NON ROUTINE INSPECTION OF ENGINE MOUNT, A CRACK WAS FOUND IN THE WELD OF THE LOWER RIGHT ATTACH POINT (RING TO AIRCRAFT SUPPORT) SHIMMY DAMPENER WAS IN GOOD CONDITION WITH NO LEAKS DETECTED. NOSE GEAR BUSHINGS WERE ALSO SATISFACTORY.SDR CA011005004Bellcrank · worn(CAN) DURING SCHEDULED MAINTENANCE, EXCESSIVE PLAY WAS FOUND BETWEEN THE RT OUTBOARD AILERON BELL CRANK AND THE RESPECTIVE AILERON PUSH / PULL TUBE. FURTHER INVESTIGATION REVEALED THAT THE ATTACH POINT HOLE DIMENSIONS WERE BEOND ACCEPTABLE LIMITS. BELL CRANK WSDR AUS20010923Tire · faulty(AUS) MAIN LANDING GEAR TYRE HAD EXCESSIVE SIDEWARDS DEFLECTION DURING LANDING CAUSING THE TYRE TO CONTACT THE BRAKE ASSEMBLY. TYRE SIZE 29X11.0X10 10PLY.SDR AUS20010872Tire · faulty(AUS) MAIN LANDING GEAR TIRE SUSPECT FAULTY. DURING LANDING THE TIRE EXHIBITED EXCESSIVE SIDEWARD DEFLECTION COUPLED WITH MINIMAL CLEARANCE CAUSED THE INSIDE WALL OF THE TIRE TO CONTACT THE BRAKE ASSEMBLY.SDR CA010821010Bolt · broken(CAN) ON TAKE OFF PILOT BEARD A BANG. THIS WAS FOLLOWED BY A NOTICEABLE LOSS OF NOSE WHEEL CONTROL (STREERING). TAKE OFF WAS ABORTED, INSPECTION REVEALED ONE OF THE NOSE GEAR FORK ATTACH BOLTS WAS BROKEN.
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