Beech B200C

Service difficulty reports · 169

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 = 'B200C'
  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.

SDR TIMA20240716008Engine · faultedON FIANL APPROACH TO LANDING PILOT GOAT A NUMBER 1 ENGINE FUEL PRESSURE LIGHT ON QUICKLY FOLLOWED BY THE SAME ENGINE RILLING BACK AND SHUTTING OFF. AT THIS POINT THE PILOT WAS ON FINAL SO THE PILOT CONTINUED TO LAND AND WAS ABLE TO TAXI BACK.Jul 16, 2024 · N125K · Beech B200C · Engine (Turbine/Turboprop)SDR 2023FA0000541Panel · shortedSMELLED ELECTRICAL FIRE 30 MILES FROM ELP, PILOT PFD GOT BRIGHT - LOOKED OVER AND SAW PILOT PFD FUSE HAD POPPED. ONCE AIRCRAFT WAS ON GROUND IN ELP MAINTENANCE TEAM INSPECTED COCKPIT AND FOUND RIGHT SIDE CIRCUIT BREAKER ILLUMINATED PANEL HAD SEVERAL SHORTED BUSep 14, 2023 · N581EA · Beech B200C · Indicating/Recording SystemSDR 2023FA0000537Unknown · unknownENCOUNTERED SEVERE TURBULENCE ABOVE VA DURING FLIGHT. COMPLETED A FIRST LEVEL INSPECTION IN ACCORDANCE WITH AMM CH 5-50-00 TABLE 607 WITH NO DEFECTS NOTED AT THIS TIME.Sep 12, 2023 · N581EA · Beech B200C · Fuselage Structure (General)SDR 1EAA2021052700158Coupling · failedFAILURE OF THE #1 ENGINE HP FUEL PUMP DRIVE COUPLINGApr 12, 2021 · N389RA · Beech B200C · Engine Fuel PumpSDR 2017FA0000159Bolt · brokenLT MAIN GEAR EXTENDED IN FLIGHT WHILE ENROUTE. AIRCRAFT LANDED AT DESTINATION WITH NO DAMAGE. UPON POST LANDING WALKAROUND, CREW DISCOVERED LEFT MAIN GEAR LOCK LINK ASSEMBLY HAD FAILED IN-FLIGHT. THE ASSEMBLY WAS FOUND TO MISSING THE SPRING, BUSHING, AND ASSOCApr 6, 2017 · Beech B200C · Landing Gear Retraction/Extension SystemSDR 2016FA0000473Tube · chafedDURING PHASE INSPECTION, FOUND THE NR 1 THROTTLE PUSH/PULL TUBE IN CENTER PEDESTAL RUBBING ON WIRE BUNDLE TRAY. NORMAL TUBE OD IS .497 AND OD FOR AREA BEING RUBBED .472. IOct 6, 2016 · N4489A · Beech B200C · Power LeverSDR USAR201601050003Door Frame · cracked(00484) AIRSTAIR DOOR FUSELAGE FRAME ENTRY LOWER FWD CORNER CRACK 0.750" LENGTH.Jan 4, 2016 · Beech B200C · Fuselage Main, StructureSDR USAR201601050002Door Frame · cracked(00484) AIR-STAIR DOOR FUSELAGE FRAME ENTRY UPPER FORWARD CORNER CRACKED, 0.500" LENGTH.Jan 4, 2016 · Beech B200C · Fuselage Main, StructureSDR USAR201601050001Frame · crackedAIRSTAIR DOOR FUSELAGE FRAME ENTRY UPPER AFT CORNER CRACKED, 1.125" LENGTH.Jan 4, 2016 · Beech B200C · Fuselage Main, FrameSDR USAR201508210003Door Frame · crackedDOOR FRAME CRACKED GREATER THAN 1.0" FOUND IN LOWER THRESHOLD SILL CLOSURE.Aug 19, 2015 · Beech B200C · Fuselage Main, StructureSDR USAR201508210002Door Frame · crackedDOOR FRAME CRACKED GREATER THAN 1.0" FOUND IN UPPER FORWARD CLOSURE.Aug 19, 2015 · Beech B200C · Fuselage Main, StructureSDR USAR201508210001Structure · crackedCRACKS GREATER THAN 1.0" FOUND IN UPPER AFT CLOSURE.Aug 19, 2015 · Beech B200C · Fuselage Miscellaneous StructureSDR USAR201508190001Door Sill · cracked(00155) ENTRY DOOR SILL CLOSURE WAS INSPECTED AND FOUND TO HAVE 1 EA, 0.75" CRACK IN THE UPPER AFT CORNER CLOSURE.Aug 14, 2015 · Beech B200C · Fuselage Miscellaneous StructureSDR CA150817003Engine · flamed out(CAN) ENGINE FLAMEOUT IN CRUISE 4 HRS INTO THE FLIGHT. PILOT NOTICED INCREASING FUEL FLOW FLUCTUATION ON ONE ENGINE FOLLOWED BY A FLAMEOUT. THE PILOT LOWERED ALTITUDE LEVEL TO 15000FT BEFORE RESTARTING THE ENGINE. FLIGHT RESUMED NORMALLY.Aug 4, 2015 · Beech B200C · Engine (Turbine/Turboprop)SDR USAR201508060003Threshold · cracked(00150) INSPECTOR FOUND .250 INCH CRACK IN THE LOWER THRESHOLD ENTRY DOOR CLOSURE.Aug 4, 2015 · Beech B200C · Fuselage Miscellaneous StructureSDR USAR201508060002Door Frame · cracked(00150) INSPECTOR FOUND ONE INCH CRACK IN THE UPPER FORWARD CORNER OF ENTRY DOOR CLOSURE.Aug 4, 2015 · Beech B200C · Fuselage Main, StructureSDR USAR201508060001Door Frame · cracked(00150) INSPECTOR FOUND A ONE INCH CRACK IN UPPER AFT CORNER OF ENTRY DOOR CLOSURE.Aug 4, 2015 · Beech B200C · Fuselage Main, StructureSDR USAR201508060004Door Frame · cracked(03329) CRACKS LESS THAN .7 INCH WERE FOUND IN THE LOWER FORWARD AND LOWER AFT CORNER CLOSURE.Aug 3, 2015 · Beech B200C · Fuselage Main, StructureSDR USAR201507280003Door Frame · cracked(00320) INSPECTOR FOUND .2 INCH CRACK IN UPPER FORWARD CORNER OF ENTRY DOOR CLOSURE AT WELL NUT HOLE.Jul 17, 2015 · Beech B200C · Fuselage Main, StructureSDR USAR201506120002Structure · crackedENTRY DOOR: DURING INSPECTION A .080" CRACK AT WELL NUT HOLE ON FORWARD VERTICAL CLOSURE WAS NOTED.Jun 8, 2015 · Beech B200C · Fuselage Main, StructureSDR USAR201506120001Door Frame · crackedENTRY DOOR FRAME: LOWER CLOSURE HAS A .100" CRACK AT A WELL NUT HOLE.Jun 8, 2015 · Beech B200C · Fuselage Main, StructureSDR CA150521002Motor · failed(CAN) ON DEPARTURE, THE LANDING GEAR WAS SELECTED UP BUT DID NOT MOVE FROM THE EXTENDED POSITION. TROUBLESHOOTING IDENTIFIED THE HYDRAULIC PUMP DC MOTOR WAS INOPERATIVE.May 19, 2015 · Beech B200C · Hydraulic System, MainSDR USAR2015004240001Structure · cracked(00489) DOOR SILL CLOSURE FATIGUE CRACK, UPPER FORWARD CORNER .250" APPROXIMATELY.Apr 17, 2015 · Beech B200C · Fuselage Miscellaneous StructureSDR CA140318003Motor · failed(CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN THERE WAS NO MOVEMENT OF THE MLG, NO IN TRANSIT LIGHT AND THE CREW RECEIVED A MASTER CAUTION INDICATION. THE CREW PERFORMED AN OVERSHOOT AND CARRIED OUT A MLG MANUAL EXTENSION AND RECEIVED 3 GREEN DOWN AND LFeb 28, 2014 · Beech B200C · Landing Gear Retraction/Extension SystemSDR CA131021015Coupling · disengaged(CAN) AN UNCONTROLLED ACCELERATION WAS EXPERIENCED DURING THE STARTING PROCEDURE FOR MEDICAL RETRIEVAL MISSION. THE PILOT SHUTDOWN THE ENGINE AND NO ACCIDENCES WERE RECORDED. THE ON GROUND INVESTIGATION REVEALED THAT THE FCU COUPLING WAS FOUND DISENGAGED FROct 12, 2013 · Beech B200C · Fuel Control/Reciprocating EnginesSDR CA131021013Engine · unknown(CAN) UPON LANDING, THE ACFT EXITED THE RUNWAY. DURING THE ON GROUND INVESTIGATION, THE ENGINEER AND THE PILOT ON SITE TRIED TO START THE ACFT ENGINES AND THE LT ENGINE ACCELERATED UNCONTROLLABLY CAUSING THE ITT TO FLASH AMBER AND THE TORQUE TO FLASH RED MOMEOct 10, 2013 · Beech B200C · Engine (Turbine/Turboprop)SDR CA130824001Engine · power loss(CAN) A CHARTERED ACFT WAS FORCED TO CARRY OUT A DITCHING IN THE LAKE. THE AIRPLANE HAD REPORTEDLY LOSS ENGINE POWER WHILE ENROUTE. ALL 7 OCCUPANTS WERE RESCUED. ACFT ENGINE ASSISTANCE WAS OFFERED BY FIELD SERVICE REPRESENTATIVE.Aug 22, 2013 · Beech B200C · Engine (Turbine/Turboprop)SDR CA130318002Fuel Control · failed(CAN) DURING LANDING ROLLOUT THE ENGINE MADE AN UNCOMMANDED POWER INCREASE, TORQUE LIMITER CUT IN. THE PILOT SHUT THE ENGINE DOWN. TROUBLESHOOTING FOUND A FAULTY FUEL CONTROL WHICH WAS REPLACED BEFORE THE ACFT WAS RETURNED TO SERVICE.Feb 18, 2013 · Beech B200C · Fuel Control/Turbine EnginesSDR EHAA20120225002Windshield · crackedON CLIMBOUT, HEARD A STRANGE SOUND AS THE GEAR WAS RETRACTED. IT WAS DARK. UPON FURTHER INVESTIGATION, SAW CRACKS ON THE CO-PILOTS WINDSHIELD.Feb 25, 2012 · N134WJ · Beech B200C · Flight Compartment WindowsSDR 2011FA0000112Display · malfunctionedTHE PILOT REPORTED THE EX600 MFD DISPLAY REMAINED DIM AND NOT LEGIBLE FOR APPROX 10 TO 15 MINUTES DURING THE ACFT GROUND RUN-UP CHECKS PRIOR TO TAXI. WHEN THE DISPLAY ACHIEVED 'NORMAL' BRIGHTNESS AND WAS READABLE IN DAYLIGHT CONDITIONS, ALL THE ASSOCIATED FUNFeb 15, 2011 · N7232R · Beech B200C · Central DisplaySDR 2011FA0000111Display · malfunctionedON THE EX600 MFD WHICH HAD JUST BEEN INSTALLED IN AUGUST OF 2010, THE PILOT REPORTED THE FOLLOWING MESSAGES WERE DISPLAYED: BROADCAST RECEIVER NOT COMMUNICATING, BROADCAST DATA NOT YET RECEIVED. THE MFD WOULD NOT DISPLAY THE WEATHER DATA FROM THE WSI-301. MDec 16, 2010 · N7232R · Beech B200C · Central DisplaySDR CA090526009Skin · cracked(CAN) DURING A PHASE 4 INSP, A CRACK WAS FOUND ON THE BELLY SKIN ALONG A STRINGER AT THE CENTERLINE OF THE ACFT. THIS CRACK MEASURED TO BE 3.5 INCHES LONG BETWEEN STA 139.00 AND 143.00 APPROX.May 20, 2009 · Beech B200C · Fuselage Main, Plate/SkinSDR CA081002005Line · leaking(CAN) DURING DAILY INSP, WITH POWER ON A FEW MOMENTS, NOTICED FUEL LEAKING FROM LT GEAR WELL. POWER TURNED OFF, NOTED FUEL LEAKING FROM SUPPLY LINE WHICH IS LOCATED BETWEEN AUX FUEL TANK AND NACELLE FUEL TANK. ON CLOSER INSP NOTICED WHERE FUEL LINE PASSED THRSep 29, 2008 · Beech B200C · Aircraft Fuel Distribution SystemSDR 2008FA0000377Skin · crackedDURING A PREFLIGHT INSPECTION, MAINTENANCE TECH NOTED A 3.75 INCH LONG CRACK IN THE RT WING LOWER WING SKIN JUST FWD OF THE IB SECTION OF THE OB FLAP. ADDITIONALLY A SUPPORT/ ANCHOR TAB THAT ATTACHES THE LOWER WING SKIN TO THE IB MOST FLAP WELL RIB OF THE OB WJul 1, 2008 · N7232R · Beech B200C · Wing, Plate/SkinSDR CA061221003Motor · failed(CAN) DURING FLIGHT THE LANDING GEAR WOULD NOT EXTEND AND AN EMERGENCY WAS DECLARED. A MANUAL GEAR EXTENSION WAS COMPLETED THE (3) GREEN LIGHTS ILLUMINATED AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE INVESTIGATED AND FOUND THAT THE LANDING Dec 18, 2006 · Beech B200C · Landing Gear Retraction/Extension SystemSDR AU510001942Ring · cracked(AUS) POWER TURBINE STATOR VANE RING CRACKED AND SEPARATED AT THE ROOT ENDS WITH CURLING OF THE TIPS. (OTHER CAUSE: NOT KNOWN AT THIS STAGE ) (CASA# 510001942)Dec 12, 2005 · Beech B200C · Turbine SectionSDR AU510001575Servo · faultyRUDDER AUTOPILOT SERVO/YAW DAMPER FAULTY, OTHER CAUSE: FAILURE OF INTERNAL MECHANISM.Dec 12, 2005 · Beech B200C · Autopilot Main ServoSDR CA051215001Actuator · failedAFTER T/O, GEAR WAS SELECTED UP AND CLUNK WAS HEARD, T/O CONTINUED TO SAFE ALT AND WAS VISUALLY CONFIRMED THAT RT GEAR HAD NOT RETRACTED. THE GEAR WAS RECYCLED DOWN 3 GREEN LIGHTS CONFIRMED ALL GEAR DOWN AND LOCKED. A/C RETURNED TO AIRPORT AND LANDED W/O FURDec 6, 2005 · Beech B200C · Landing Gear ActuatorSDR CA050117001Frame · cracked(CAN) DURING A ROUTINE INSPECTION A CRACK WAS FOUND PROPAGATING FROM THE OVAL HOLE IN THE RT FRAME AT STATION 207.125 (HALF WAY BETWEEN THE FLOOR AND THE WINDOW). THE CRACK WAS APPROXIMATELY 1 = INCH LONG AND EXTENDED FROM THE 11 O`CLOCK POSITION OF THE LIGHTJan 13, 2005 · Beech B200C · Nacelle/Pylon, Frame/Spar/RibSDR 2005FA0000034Relay · failedWHILE THE AIRCRAFT WAS IN FLIGHT, THE FLAPS FAILED TO EXTEND TO THE SELELCTED APPROACH POSITION. THE PILOT CYCLED THE FLAP SELECT SWITCH TO UP AD BACK TO APPROACH AND THE FLAPS EXTENDED. MAINTENANCE INVESTIGATED THE REPORTED PROBLEM AND WAS ABLE TO DUPLICATEOct 19, 2004 · N7232R · Beech B200C · Trailing Edge Flap Control SystemSDR CA040922005Actuator · worn(CAN) DURING ROUTINE 1000 CYCLE ENDPLAY CHECK OF THE NOSE GEAR ACTUATOR, THE ACTUATOR FAILED WITH 0.020 OF AN INCH ENDPLAY THE MAX ALLOWABLE IS 0.016. THIS UNIT ONLY HAD 997 CYCLES SINCE OVERHAUL (OVERHAUL DUE AT 7500 CYCLES). THE ACTUATOR WAS REMOVED FROM SESep 21, 2004 · Beech B200C · Landing Gear ActuatorSDR CA040922001Snap Ring · out of position(CAN) DURING ENDPLAY CHECK (1000 CYCLES) ON LT MAIN GEAR ACTUATOR, INPUT GEAR WAS FOUND TO HAVE 0.090 INCH ENDPLAY. THIS CHECK USED TO VERIFY THAT THRUST BEARING IS PROPERLY INSTALLED, MAXIMUM ENDPLAY IS 0.050. THESE ACTUATORS ARE OVERHAULED AT 7500 CYCLES, TSep 21, 2004 · Beech B200C · Landing Gear Retraction/Extension SystemSDR EHA2004F00006Unknown · malfunctionedPRELIMINARY - AIRCRAFT DEPARTED ON MEDICAL EVACUATION TRIP. AIRCRAFT DID NOT PRESSURIZE. PIC NOTED LACK OF PRESSURIZATION BY THE EMERGENCY OXYGEN MASK AUTOMATIC DEPLOYMENT. AIRCRAFT AIR TURNED BACK. AIRCRAFT REMOVED FROM SERVICE. PERFORMED MM 21-30-00, PRJul 26, 2004 · N134WJ · Beech B200C · Cabin Compressor SystemSDR 2004FA0000524Torque Tube · looseDURING AN INSPECTION, THE LT ELEVATOR CORNTOL TORQUE TUBE THAT ATTACHES TO IB END RIB OF THE LT ELEVATOR WAS FOUND TO HAVE PLAY BETWEEN THE ACTUATING HORN AND THE TORQUE TUBE ITSELF. THE COLLAR WITH THE FLANGE AND THE 4 MOUNTING BOLTS ATTACHING THE TORQUE TUBJul 1, 2004 · N7232R · Beech B200C · Elevator Control SystemSDR CA040624001Mount · mismanufactured(CAN) DURING ENGINE MOUNT REPLACEMENT IT WAS NOTICED THAT THE NEW MOUNTS WERE MANUFACTURED WITH THE BEVEL ON THE WRONG SIDE OF THE METAL PART OF THE CORE (R20700-11). THE CORE IS MADE OF RUBBER SANDWICHED BETWEEN TWO PIECES OF METAL. THE BEVEL IS THERE TO ALLJun 17, 2004 · Beech B200C · Engine Mount SectionSDR 2004FA0000523Torque Tube · looseDURING PHASE INSPECTION, THE RT ELEVATOR CONTROL TORQUE TUBE THAT ATTACHES TO THE IB END RIB OF THE RT ELEVATOR WAS FOUND TO HAVE PLAY BETWEEN THE COLLAR WITH THE FLANGE THAT BOLTS TO THE END RIB AND THE TORQUE TUBE ITSELF. THE 4 MOUNTING BOLTS WERE TIGHT TO Jun 1, 2004 · N7232R · Beech B200C · Elevator StructureSDR AUS20040433Seal · worn(AUS) ENGINE ACCESSORY GEARBOX STARTER-GENERATOR DRIVE SHAFT SEAL WORN. LOSS OF ENGINE OIL.May 20, 2004 · Beech B200C · Turbine Engine Oil SystemSDR AUS20040400Turbine Blades · cracked(AUS) COMPRESSOR TURBINE BLADES (3 OFF) CRACKED. CRACKS EMANATE FROM BLADE TIP RADIALLY TOWARDS BLADE ROOT. CRACK LENGTHS UP TO APPROXIMATELY 7MM (0.27IN). FOUND DURING BOROSCOPE INSPECTION.May 12, 2004 · Beech B200C · Turbine SectionSDR AUS20040222Shaft · failed(AUS) LT MAIN LANDING GEAR RETRACTION DRIVE TUBE FAILED DUE TO INTERFERENCE WITH PNEUMATIC DUCTING CLAMP.Mar 23, 2004 · Beech B200C · Landing Gear Retraction/Extension SystemSDR AUS20040213Valve · faulty(AUS) DEFECT REPORT NR WAS CREATED IN LIEU OF DATA BEING ATTACHED TO MDR 04/0176. CANCELLED, DATED 25TH MARCH 2004.Mar 12, 2004 · Beech B200C · Fuel Transfer Valve
Back to Beech B200C