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 COEA9801875Cylinder · leakingWHILE TURNING OUT OF PARKING SPOT TO REPOSITION AIRCRAFT, PILOT REPORTED RT BRAKE PEDAL WENT TO FLOOR AND BRAKING ACTION WENT TO ZERO ON RT SIDE. PILOT SHUT DOWN AIRCRAFT AND SAW THAT RT BRAKE CYLINDER HAD STARTED LEAKING BRAKE FLUID. MAINTENANCE WAS NOTIFIESDR CA980506004Fcu · failed(CAN) DURING CLIMB THROUGH 9,000 FEET, THE ENGINE CEASED OPERATION WITHOUT WARNING, AS IF THE CONDITION LEVER HAD BEEN MOVED TO THE CUTOFF POSITION. AN ATTEMPTED RE-LITE WAS UNSUCCESSFUL. POST-FLIGHT INSPECTION FOUND THE P3 LINE FROM THE GAS GENERATOR TO THESDR CA980430010Plate · misinstalled(CAN) PRESSURE PLATE FOUND INSTALLED BACKWARDS PLACING THE ORGANIC LINING AGAINST THE BRAKE PISTONS AND THE STEEL BACKSIDE OF THE PRESSURE PLATE CONTACTING THE BRAKE DISC. ON BRAKING, THE FRICTION OF STEEL ON STEEL WAS CAUSING METAL TRANSFER. NO INDICATION FSDR COEA9801976Rt Unit · inoperativeON CLIMB-OUT, PILOT FOUND WEATHER RADAR NOT DISPLAYING RETURNS OF VISIBLE MOISTURE AHEAD, AND OTHER PILOTS WERE REPORTING HEAVY WEATHER RETURNS ON SAME DEPARTURE AND DIRECTION AT SAME TIME. PILOT ELECTED TO RETURN TO BASE AND NOT PROCEED WITHOUT THE ASSISTANCSDR COEA9801709Pitot Heat · failedDURING CLIMB-OUT IN IMC CONDITIONS, THE PAR WARNING ILLUMINATED INDICATING EXCESS AIRSPEED. COPILOT AIRSPEED INDICATOR WAS ABOVE REDLINE. PILOT DECLARED AN EMERGENCY AND RETURNED TO BASE WITHOUT EVENT. MAINTENANCE FOUND NR 2 PITOT HEAT INOPERATIVE AND HAD ISDR CA970731023Wire Harness · chafed(CAN) DURING CLIMB, THE CREW NOTED SPARKS AND SMOKE FROM THE LEFT HAND KICK PANEL BY THE PILOT'S KNEE. INVESTGATION FOUND A CHAFED WIRE BUNDLE BY THE ALTERNATE PITOT STATIC SYSTEM.SDR CA980325030Stringer · cracked(CAN) SAME STRINGER IN EACH WING CRACKED WHERE THE STRINGER ATTACHES TO THE RIB. APPROX .500 INCH LONG ORIGINATING AT RIVET HOLE.SDR CA980325029Stringer · cracked(CAN) SAME STRINGER IN EACH WING CRACKED WHERE THE STRINGER ATTACHES TO THE RIB. APPROX .500 INCH LONG ORIGINATING AT RIVET HOLE.SDR CA980318027Connector · burned(CAN) DURING INSPECTION THE LT CB PANEL WAS ORENED AND A WIRE CONNECTION FOR THE PROP DEICE SYSTEM WAS FOUND BADLY BURNED. THE PROP SYSTEM FUNCTIONED BUT THE CONNECTION REQUIRED REPLACEMENT.SDR CA980318026Control Unit · failed(CAN) DURING INSPECTION THE STARTER WOULD ENGAGE WITH THE BATTERY SWITCH ON BUT THE STARTER SWITCH IN THE NORMAL POSITION. ALTERNATOR CONTROL UNIT WAS FOUND TO BE STICKING. REPLACED.SDR CA980318021Governor · intermittent(CAN) FLIGHT CREW REPORTED PROPELLER SPEED LIMITED TO 1800 RPM DURING CRUISE. MAINTENANCE FOUND THE OVERSPEED GOVERNOR TEST SOLENOID WAS ENGAGING INTERMITTENTLY WHICH CAUSED THE GOVERNOR TO LIMIT RPM.SDR 98ZZZX234Anchor Bolt · mismanufacturedBRAKE CALIPER PINS (ANCHOR BOLTS) WERE SHORTER THAN PINS INSTALLED ON OTHER BRAKE CALIPERS. THIS WAS A NEW BRAKE ASSEMBLY INSTALLED ON A NEW AIRCRAFT RECEIVED FROM FACTORY. RETURNED TO BRAKE MANUFACTURER FOR REPAIR.SDR CA980318033Stator · failed(CAN) DURING HOT SECTION INSPECTION INTERNAL DAMAGE AND FOD WAS FOUND AROUND THE COMBUSTION LINER. INVESTIGATION FOUND THAT PART OF THE 3RD STAGE COMPRESSOR FAILED AND DEBRIS FOUND ITS WAY THROUGH THE ENGINE. THE ENGINE WAS REPLACED.SDR CA971223004Wing · bird strike(CAN) ON APPROACH BIRD STRIKE, DUCK, ON LT WING LEADING EDGE STA 276L. LARGE DENT AND RIB DAMAGE, REPAIRED.SDR 98ZZZX156Line · chafedFORWARD FUEL LINE COMING FROM THE WING AS IT ENTERS RESERVOIR TANK COMPARTMENT. THERE ARE THREE AN3 BOLTS RETAINING A SEAL IN THE SIDE WALL OF COMPARTMENT. FORWARD BOLT CHAFING LINE, BOLT TURNED OUT TO BE AN3-4A, PARTS MANUAL CALLS FOR AN3-3A. BOTH SIDES OFSDR COEA9701918Servo Tab · crushedPARKED AIRCRAFT 918FE WAS RUN INTO BY A TAXIING AIRCRAFT. THE LEFT SERVO TRIM TAB WAS CRUSHED AND THE LEFT WING UNDERSIDE RECEIVED A .0625 INCH WIDE SCRATCH IN THE PAINT FROM TRAILING EDGE TO LEADING EDGE 2 FEET FROM THE WING TIP. A SMALL DENT .0937 INCH DEESDR 97ZZZX5039Bearing · frozenDURING INSPECTION, AILERON CONTROL WAS DISCOVERED TO HAVE UNUSUALLY HIGH RESISTANCE. RESISTANCE WAS EVENTUALLY ISOLATED TO THE LEFT AILERON. BOTH BEARINGS WERE REPLACED AND THE OUTBOARD BEARING WAS FOUND ALMOST FROZEN WITH CORROSION. THESE ARE SEALED BEARINSDR 97ZZZX4805Blade · crackedINSPECTION FOUND ALL 3 BLADES HAVE CHORDWISE CRACKS BEYOND THE 3.5 INCH LIMIT. ALL CRACKS LEAD UP TO AND POSSIBLY UNDER THE EROSION SHIELD. THE CRACKS WERE FOUND DURING INSPECTION PER HARTZELL JB 169A. PROPELLER REMOVED FROM SERVICE AT THIS TIME.SDR 97ZZZX4804Blade · crackedINSPECTION FOUND ALL 3 BLADES HAVE CHORDWISE CRACKS BEYOND THE 3.5 INCH LIMIT. ALL CRACKS LEAD UP TO AND POSSIBLY UNDER THE EROSION SHIELD. THE CRACKS WERE FOUND DURING INSPECTION PER HARTZELL JB 169A. PROPELLER REMOVED FROM SERVICE AT THIS TIME.SDR 97ZZZX4803Blade · crackedINSPECTION FOUND ALL 3 BLADES HAVE CHORDWISE CRACKS BEYOND THE 3.5 INCH LIMIT. ALL CRACKS LEAD UP TO AND POSSIBLY UNDER THE EROSION SHIELD. THE CRACKS WERE FOUND DURING INSPECTION PER HARTZELL JB 169A. PROPELLER REMOVED FROM SERVICE AT THIS TIME.SDR CA971003008Valve · failed(CAN) AIRCRAFT RETURNED TO BASE AFTER PILOT OBSERVED HIGH ITT INDICATION. AIRCRAFT WAS GROUND RUN AND ENGINE PERFORMANCE INDICATED COMPRESSOR OR COLD SECTION PROBLEM WITH THE ENGINE. ENGINE WAS GROUND RUN AGAIN WITH HEATER IN GROUND MODE WHICH USES BLEED AIR FSDR CA970915004Wheel · corroded(CAN) DURING INSPECTION, CORROSION WAS FOUND IN THE BEARING AREA OF NOSE WHEEL. THE BEARING SEALS WERE FOUND IN GOOD CONDITION. WATER APPEARS TO HAVE ENTERED THE AREA FROM THE NOSE FORK AND SPACER TRAVELING DOWN AXEL TUBE INTO THE BEARING AREA.SDR COEA9701850Wire · chafedFUEL PRESSUR LOW LIGHT ILLUMINATED IN FLIGHT FROM FLG TO PHX. LOUD NOISE IN ENGINE COMPARTMENT, COUPLED WITH ERRATIC FUEL FLOW INDICATING. USED EMERGENCY POWER LEVER FOR REMAINDER OF FLIGHT. AIRCRAFT DIVERTED TO PRESCOTT AND LANDED WITHOUT INCIDENT. TROUBLSDR 97ZZZX3499Gusset · chafedWHILE REMOVING THE ELEVATOR TRIM ACTUATOR, DISCOVERED THE TRIM CONTROL CABLE WAS INCORRECTLY ROUTED BENEATH THE GUSSET IN THE TAIL CONE RATHER THAN THROUGH THE GUSSET. THIS CAUSED THE CABLES TO RIDE AGAINST THE AFT FLANGE OF THE GUSSET. MINIMAL DAMAGE WAS DOSDR 97ZZZX3148Switch · mismanufacturedAIR CONDITIONER PRESSURE SWITCH NOT MACHINED ADEQUATELY TO ACCEPT THE SEALING O-RING.SDR 97ZZZX3446Nut · wornDURING SCHEDULED INSPECTION, MAINTENANCE OBSERVED THE RUDDER TRIM NUT TO HAVE GROOVES WORN INTO THE NUT ON BOTH ENDS WHERE THE NUT ATTACHED TO THE RUDDER BAR. THE RUDDER NUT PASSES THROUGH TWO ARMS ATTACHED TO THE RUDDER BAR. ACTUATION OF THE RUDDER TRIM CAUSDR 97ZZZX3432Nut · wornDURING SCHEDULED INSPECTION, MAINTENANCE OBSERVED THE RUDDER TRIM NUT TO HAVE GROOVES WORN INTO THE NUT ON BOTH ENDS WHERE THE NET ATTACHED TO THE RUDDER BAR. THE RUDDER NUT PASSES THROUGH TWO ARMS ATTACHED TO THE RUDDER BAR. ACTUATION OF THE RUDDER TRIM CAUSDR 97ZZZX3335Trim Shaft · wornINSPECTION FINDING RUDDER TRIM NUT (SHAFT) WEARS OUT. VIBRATION AND PRESSURE ARE CONCENTRATED ON A SMALL AREA OF THIS PARTICULAR PART AND THE PART BEING MADE OF SOFTER METAL WEARS OUT.SDR 98ZZZX1024Bracket · crackedCENTER EXHAUST HANGER ON CESSNA 208B CARAVAN DEVELOPED CRACK .25 INCH LONG IN FORWARD, OUTBOARD BEND RADIUS DUE TO EXCESSIVE STRESS CAUSED BY IMPROPER SPACING (VIA WASHER SPACERS) BETWEEN LOWER ENGINE COWL AND BRACKET.SDR 97ZZZX2619Longeron · corrodedON INSPECTION, CORROSION WAS FOUND ON LONGERONS BETWEEN FS 188.70 AND FS 214.40 AND ON THE BELLY SKIN FLANGE WHERE THE NUTPLATES ARE INSTALLED FOR THE MLG FORWARD STRAPS TO BOLT ONTO. THIS ACFT CAME FROM A SALT WATER CLIMATE. WATER RUNS INTO WING ATTACH AREASDR 97ZZZX2618Longeron · corrodedON INSPECTION, CORROSION WAS FOUND ON LONGERONS BETWEEN FS 188.70 AND FS 214.40 AND ON THE BELLY SKIN FLANGE WHERE THE NUTPLATES ARE INSTALLED FOR THE MLG FORWARD STRAPS TO BOLT ONTO. THIS ACFT CAME FROM A SALT WATER CLIMATE. WATER RUNS INTO WING ATTACH AREASDR 97ZZZX1890Pressure Plate · misinstalledDURING INSP, RT BRAKE PRESSURE PLATE FOUND INSTALLED IN WRONG POSITION. LINING SIDE WAS FACING THE PISTON HOUSING. ACFT BRAKING METAL-TO-METAL CAUSING VERY HIGH BRAKE TEMPERATURES AND SUSPECTED SPARKS CAME OUT ON EVERY BRAKE APPLICATION. PRESSURE PLATE AND SDR 97ZZZX1877Bolt · brokenA NEW OPERATOR HAS FOUND ONE OR TWO BOLTS BROKEN APART AND MISSING FROM MAIN WHEELS DURING INTRANSIT INSPECTION OF AIRCRAFT. THIS HAPPENED QUITE OFTEN ON FLEET AIRCRAFT. THEY WERE USING 53-57 PSI TIRE PRESSURE IAW CESSNA PHASE CHECK TACK CARD 321004. PROBLEMSDR 97ZZZX1325Line · holedDURING A SCHEDULED INSPECTION, NOTED THE SECOND CYCLE OF THREE WAS NOT HOLDING ENOUGH PRESSURE IN THE SURFACE DEICE SYSTEM. INSPECTION REVEALED A HOLE IN AN ALUMINUM LINE CAUSED BY A SCREW IN AN INSPECTION COVER MAKING CONTACT. SUGGEST MAKING SURE ADEQUATE CSDR 97ZZZX1255Bracket · wornEMERGENCY POWER CABLE AND ATTACH BRACKETS WORN. THE BRACKETS WORN WITHIN .0625 INCH OF BEING COMPLETELY THROUGH MATERIAL. EMERGENCY POWER CABLE WORN THROUGH ATTACH POINT ON CABLE. SUGGEST WEAR IS NORMAL, CABLE AND ATTACH BRACKETS NEED TO BE OF HEAVIER MATERSDR 97ZZZX1254Bracket · wornEMERGENCY POWER CABLE AND ATTACH BRACKETS WORN. THE BRACKETS WORN WITHIN .0625 INCH OF BEING COMPLETELY THROUGH MATERIAL. EMERGENCY POWER CABLE WORN THROUGH ATTACH POINT ON CABLE. SUGGEST WEAR IS NORMAL, CABLE AND ATTACH BRACKETS NEED TO BE OF HEAVIER MATERSDR 97ZZZX1253Control Cable · wornEMERGENCY POWER CABLE AND ATTACH BRACKETS WORN. THE BRACKETS WORN WITHIN .0625 INCH OF BEING COMPLETELY THROUGH MATERIAL. EMERGENCY POWER CABLE WORN THROUGH ATTACH POINT ON CABLE. SUGGEST WEAR IS NORMAL, CABLE AND ATTACH BRACKETS NEED TO BE OF HEAVIER MATERSDR 97ZZZX1095Switch · failedAIRCRAFT LEFT LANDING LIGHT WOULD NOT SHUT OFF. PILOT REPORTED FAINT SMOKE SMELL IN COCKPIT. IINVESTIGATION REVEALED LANDING LIGHT SWITCH HAD SHORTED AND SHOWED SIGNS OF OVERHEATING. THE SWITCH WAS REPLACED AND SYSTEM OPERATED NORMALLY.SDR 97ZZZX838Connector · openDURING ATTEMPTED START, STARTER 'BUZZED' OR 'GROWLED'. AFTER START, GENERATOR DID NOT COME ON-LINE. TROUBLESHOT TO GCU POWER WIRE PB87 CONNECTOR OPENED INTERMITTENTLY. FOUND CONNECTOR CRIMPED ON INSULATION WITH STRANDS OF WIRE EXTENDING BEYOND AND MAKING SOSDR 97ZZZX459Relay · inopPILOT REPORTED PRIMARY FLAP SYSTEM AND STBY FLAP SYSTEM INOP. MEHCANICS FOUND FLAP RELAY K21 WITH INTERNAL MALFUNCTION. RELAY WAS INSPECTED AND IT WAS FOUND THAT INTERNAL CONTACTOR A3 DID NOT HAVE THE SILVER CONTACT WELDED TO TERMINAL, THEREFORE, AN INTERNALSDR 97ZZZX31Gcu · failedPILOT REPORTED WHILE EN ROUTE FROM ONT TO SBA, THE RED GENERATOR OFF LIGHT ILLUMINATED. THE STAND-BY ALTERNATOR DID NOT COME ON LINE. THE STAND-BY ELECTRICAL POWER ON LIGHT NOR THE STAND-BY ELECTRICAL POWER OFF LIGHT ILLUMINATED. THE AIRCRAFT WAS OPERATING SDR CA970110005Indicator · leaking(CAN) TORQUE INDICATOR WAS NOTED TO BE LEAKING AND FILLING WITH OIL.SDR CA970702010Rudder Bearing · worn(CAN) RUDDER NOTICED TO BE RESTING LOWER THAN NORMAL. INSPECTION FOUND THE UPPER BEARING HAD BECOME SEVERELY WORN. ALL BEARINGS REPLACED.SDR 97ZZZX479Stringer · crackedWING STRINGER WAS FOUND CRACKED DURING A ROUTINE INSPECTION. CAUSE OF STRINGER FAILURE UNKNOWN. TWELVE OTHER, P/N 2622000-64, STRINGERS HAVE BEEN FOUND CRACKED ON 208 AND 208B AIRCRAFT WITH PART TT RANGING FROM 596 TO 6511 HOURS.SDR 97ZZZX478Stringer · crackedWING STRINGER WAS FOUND CRACKED DURING A ROUTINE INSPECTION. CAUSE OF STRINGER FAILURE UNKNOWN. TWELVE OTHER, P/N 2622000-64, STRINGERS HAVE BEEN FOUND CRACKED ON 208 AND 208B AIRCRAFT WITH PART TT RANGING FROM 596 TO 6511 HOURS.SDR 97ZZZX477Stringer · crackedWING STRINGER WAS FOUND CRACKED DURING A ROUTINE INSPECTION. CAUSE OF STRINGER FAILURE UNKNOWN. TWELVE OTHER, P/N 2622000-64, STRINGERS HAVE BEEN FOUND CRACKED ON 208 AND 208B AIRCRAFT WITH PART TT RANGING FROM 596 TO 6511 HOURS.SDR 97ZZZX476Stringer · crackedWING STRINGER WAS FOUND CRACKED DURING A ROUTINE INSPECTION. CAUSE OF STRINGER FAILURE UNKNOWN. TWELVE OTHER, P/N 2622000-64, STRINGERS HAVE BEEN FOUND CRACKED ON 208 AND 208B AIRCRAFT WITH PART TT RANGING FROM 596 TO 6511 HOURS.SDR 97ZZZX475Stringer · crackedWING STRINGER WAS FOUND CRACKED DURING A ROUTINE INSPECTION. CAUSE OF STRINGER FAILURE UNKNOWN. TWELVE OTHER, P/N 2622000-64, STRINGERS HAVE BEEN FOUND CRACKED ON 208 AND 208B AIRCRAFT WITH PART TT RANGING FROM 596 TO 6511 HOURS.SDR 97ZZZX474Stringer · crackedWING STRINGER WAS FOUND CRACKED DURING A ROUTINE INSPECTION. CAUSE OF STRINGER FAILURE UNKNOWN. TWELVE OTHER, P/N 2622000-64, STRINGERS HAVE BEEN FOUND CRACKED ON 208 AND 208B AIRCRAFT WITH PART TT RANGING FROM 596 TO 6511 HOURS.SDR 97ZZZX473Stringer · crackedWING STRINGER WAS FOUND CRACKED DURING A ROUTINE INSPECTION. CAUSE OF STRINGER FAILURE UNKNOWN. TWELVE OTHER, P/N 2622000-64, STRINGERS HAVE BEEN FOUND CRACKED ON 208 AND 208B AIRCRAFT WITH PART TT RANGING FROM 596 TO 6511 HOURS.
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