Beech B200

Service difficulty reports · 830

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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 = 'B200'
  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 CA110105014Exciter · failedRT ENGINE FAILED TO START. RT IGNITION EXCITER WAS REMOVED AND REPLACED WITH USED, AND NO FURTHER INCIDENT PREVAILED.Oct 23, 2010 · Beech B200 · ExciterSDR 2010FA0001109Seal Ring · disintegratedENGINE ACCESSORY CASE INPUT SHAFT TEFLON WASHER (SEAL RING), PN 3118217-01, DISINTEGRATED AND WAS FOUND IN THE OIL SCAVENGE PUMP SCREEN DURING A SCHEDULED INSP. ACCESSORY CASE REMOVAL REQUIRED FOR WASHER REPLACEMENT.Oct 15, 2010 · N1MU · Beech B200 · Engine (Turbine/Turboprop)SDR 2010F00220Current Limiter · failedNR2 CURRENT LIMITER FAILED CAUSING THE NR2 GENERATOR TO DROP OFF LINE WHEN GEAR WAS SELECTED. THE PILOT SELECTED THE NR2 GENERATOR SWITCH TO OFF AND DONE A MANUAL EXTENSION FOR LANDING AT THE ORIGINAL DESTINATION. NO FURTHER DIFFICULTIES WERE REPORTED. THE BASOct 9, 2010 · N301HC · Beech B200 · AC Generator-AlternatorSDR CA110110002Probe · failedWHILE TROUBLESHOOTING A FUEL INDICATION SNAG IT WAS FOUND THAT A OVERHAULED PROBE THAT WAS PURCHASED FOR STOCK WAS FAULTY WHEN IT WAS INTRODUCED TO THE SYSTEM. A DIFFERENT PROBE WAS INSTALLED FROM STOCK AND THE AIRCRAFT SNAG WAS RECTIFIED.Oct 7, 2010 · Beech B200 · Fuel Quantity SensorSDR CA101230008Windshield · failed(CAN) AIRCRAFT WAS ENROUTE FL 160, WHEN THE RT WINDSHIELD OUTER PANE OF GLASS SHATTERED. AIRCRAFT LANDED WITHOUT INCIDENT AND THE WINDSHIELD WAS REPLACED.Sep 29, 2010 · Beech B200 · Flight Compartment WindowsSDR CA101109009Fastener · loose(CAN) WING CENTER SECTION - P/N 101-120140-5 SKIN P/N 101-120116-53 HAD LOOSE FASTENERS AT AFT EDGE AT SPAR.Sep 26, 2010 · Beech B200 · Wing, Plate/SkinSDR CA101230009Servo · failedON A FLIGHT, THE YAW DAMPER WAS NOTED TO HAVE FAILED. THE YAW DAMPER SERVO WAS REPLACED AND NO FURTHER INCIDENT PREVAILED.Sep 20, 2010 · Beech B200 · Rudder Control SystemSDR CA100916010Computer · malfunctionedAN ANOMOLY EXISTS IN THE AUTOPILOT FUNCTION OF THE APS-65H COMPUTER PN 622-9724-140 (COMPUTER MOD FROM A -130 TO ACCOMODATE THE INSTALLATION OF THE AHRS1000A SYS). WHEN THE ACFT IS CONFIGURED IN CLIMB MODE, AND THE PRE-SELECTOR SET TO A HIGHER ALTITUDE (SO THSep 15, 2010 · Beech B200 · Autopilot SystemSDR 2010FA0001041Transmitter · inoperativeTROUBLESHOT INOPERATIVE LT ENGINE FUEL FLOW INDICATION. FOUND ROTATING ELEMENT OF INLINE FUEL FLOW TRANSMITTER LOOSE AND SHIFTED FWD. REMOVED FUEL LINE FROM TRANSMITTER OUTLET AND FOUND ROTATING ELEMENT SNAP RING INSIDE FUEL LINE. REMOVED SNAP RING AND CLEASep 13, 2010 · N424RA · Beech B200 · Fuel Flow IndicatingSDR CA100906002Engine · failedACFT WAS CLIMBING THROUGH 3400 FT AT NIGHT AFTER TAKEOFF WHEN THE PILOTS SUDDENLY HEARD A GRINDING HIGH PITCHED SOUND FROM THE LT ENGINE ALONG WITH SPARKS SHOOTING FROM THE EXHAUST STACKS. THEY IDENTIFIED AN ENGINE FAILURE AND SECURED THE LT ENGINE AND RETURNSep 2, 2010 · Beech B200 · Engine (Turbine/Turboprop)SDR CA100830005Motor · burnedCREW SELECTED FLAPS UP ON ROLL-OUT. ACFT SAT FOR A COUPLE OF HOURS, PRE-FLIGHT CHECKS WERE NORMAL. PRIOR TO TAKEOFF, FLAPS WERE SET TO TAKEOFF POSITION. AT THIS TIME SMOKE WAS OBSERVED IN THE CABIN. EMERGENCY DRILL WAS CARRIED OUT AND THE ACFT EVACUATED AT Aug 26, 2010 · Beech B200 · Trailing Edge Flap Control SystemSDR 2010FA0001053Bolt · backed out(CTUR) DURING THE 1ST PHASE 3, 4 OF THE ACFT, TECH FOUND WASHER AND NUT LAYING ON INTERIOR OF ACFT SKIN, FOUND BOLT FOR RUDDER PUSH PULL TUBE TO TORQUE TUBE BACKED OUT AND SIGNS OF CONTACT TO SURROUNDING STRUCTURE WAS ALSO NOTED.Aug 18, 2010 · N181MP · Beech B200 · Rudder Control SystemSDR CA100816004Fcu · unserviceableAFTER REMOVAL OF RT ENGINE FCU FOR SCHEDULED MX. AN OVERHAULED FCU FROM MFG WAS INSTALLED AND RIGGED. UPON TRYING TO START ENGINE, MX FOUND THAT THE ENGINE STARTED BUT HAD A HUNG START AT 30 PERCENT. ENGINE WAS SHUTDOWN, RIGGING WAS RECHECKED, FLOW DIVIDER Aug 13, 2010 · Beech B200 · Fuel Control/Turbine EnginesSDR CA100901004Bracket · damagedFASTENERS ATTACHING FITTING PN 50-820182-14 TO INNER AND OUTER GEAR DOOR SKINS LOOSEN AFTER TIME. AMES REPLACE AND UPSIZE THE FASTENERS, WHICH IS STANDARD PRACTICE. THE FITTING IS ONLY .2500 INCH WIDE. THE ORIGINAL FASTENERS ARE .1250 DIAMETER, WHICH LEAVESJul 23, 2010 · Beech B200 · Landing Gear DoorsSDR CA100831014Screen · crackedFOD SCREEN, PN 101-910049-125 FOUND CRACKED.Jul 12, 2010 · Beech B200 · Engine Air Intake SystemSDR CA100831013Angle · crackedANGLES PN 101-910049-137, 101-910049-139, 101-910049-140, FOUND CRACKED. THESE INDIVIDUAL ANGLE FORM THE STRUCTURE SUPPORTING THE INTAKE FOD SCREEN.Jul 12, 2010 · Beech B200 · Engine Air Intake SystemSDR CA100831012Hinge · crackedICE VANE HINGE HALVES, PN 101-910020-13 AND 101-910020-15 FOUND CRACKED AND WORN.Jul 12, 2010 · Beech B200 · Engine Cowling SystemSDR CA100809018Blade · bent(CAN) THE AIRCRAFT HAD LEVELED OFF FL200 WHEN THE NG WENT DOWN TO 92 PERCENT AND THE ITT WENT UP TO 900. THE ENGINE WAS BROUGHT BACK TO FLIGHT IDLE AND CONTINUED TO DESTINATION. LIGHT ICING WAS NOTED AND THE ICE VANES WERE OPEN. UPON INSPECTION IT WAS NOTEDJul 10, 2010 · Beech B200 · Turbine Engine Compressor SectionSDR CA100630003Engine · making metal(CAN) FLIGHT CREW HAD A CHIP LIGHT INDICATION ON LT ENGINE SHORTLY AFTER TAKEOFF. AIRCRAFT RETURNED TO AIRPORT WITHOUT INCIDENT. MAINTENANCE WAS CALLED TO INSPECT ENGINE, ENGINEER FOUND TRACES OF FERROUS MATERIAL AT CHIP DETECTOR. ENGINE WAS REMOVED AND WILJun 27, 2010 · Beech B200 · Engine (Turbine/Turboprop)SDR HSRR13038Tube · splitBLEED AIR FAIL WARNING LIGHT CAME ON IN FLIGHT. FOUND BLEED TUBE SPLIT.Jun 25, 2010 · N793DC · Beech B200 · Pneumatic Distribution SystemSDR CA100809020Shock Absorber · shearedACFT WAS TAXIING IN AFTER LANDING, UPON TURNING TO THE RT THE PILOT HEARD A LOUD BANG AND THEN EXPERIENCED A LOSS OF STEERING CONTROL. THE ACFT CAME TO A STOP WITHOUT INCIDENT. UPON INSP IT WAS REVEALED THAT THE SHOCK ABSORBER CYLINDER HAD SHEARED APPROX 2 IJun 9, 2010 · Beech B200 · Nose/Tail Landing Gear Strut/AxleSDR IJAA2010061000001Solenoid Valve · defectiveAIRCRAFT WOULD NOT PRESSURIZE AFTER TAKEOFF. PERFORMED AIRTURN BACK TO AIRPORT. MAINTENANCE REMOVED AND REPLACED THE CABIN PRESSURE SAFETY SOLENOID VALVE. AIRCRAFT SYSTEM TEST AND FLIGHT CHECK SATISFACTORY.Jun 8, 2010 · N429EM · Beech B200 · Cabin Pressure Control SystemSDR CA100527007Support · cracked(CAN) SUPPORT P/N 101-430178-1 ON AIRSTAIR DOOR CRACKED AT FASTENERS ATTACHING DOOR CABLE POST CLEVIS TO ITSELF. DEFECT WAS NOTICED DUE TO EXCESSIVE CLEVIS MOVEMENT.May 26, 2010 · Beech B200 · Passenger/Crew DoorsSDR IFJA2010FA0000459Engine · leakingENGINE S/N 93901 WAS INSTALLED ON ACFT S/N BB-1219 AFTER OVERHAUL, DURING THE OPERATIONAL CHECK FLIGHT THE PILOT NOTICED SMOKE IN THE COCKPIT AND ABORTED THE CHECK FLIGHT RETURNING TO THE AIRPORT WITHOUT INCIDENT. AFTER TROUBLESHOOTING AND SPEAKING TO A TECH RMay 11, 2010 · N301H · Beech B200 · Engine (Turbine/Turboprop)SDR GNL2010F00000O-Ring · splitDURING A ROUTINE TRAINING FLIGHT, THE PILOT NOTICED THAT THE LT ENGINE TORQUE DROPPED FROM 2100 LBS TO 1600 LBS. HE INCREASED LT THROTTLE LEVER WITH NO RESPONSE NOTICED. HE LOOKED OUT THE SIDE WINDOW AND NOTICED WHAT SEEMED TO BE FUEL STREAMING FROM THE LT EMay 1, 2010 · N75LV · Beech B200 · Aircraft Fuel Distribution SystemSDR IJAA2010031600001Buss Bar · shortedPILOT REPORT OF SPARKS AND SMOKE FROM CO-PILOT'S CIRCUT BREAKER PANEL AND LOSS OF NR1 COMM, NR 1 NAV AND SATCOM. INSPECTED AND FOUND ADEL CLAMP LOCATED BEHIND CO-PILOT’S CIRCUIT BREAKER PANEL SHORTING AGAINST NR1 BUS BAR. REPOSITIONED ADEL CLAMP, REPLACED AVMar 15, 2010 · N429EM · Beech B200 · Electrical Power System WiringSDR CA100216016Indicator · erratic(CAN) CREW REPORTED THAT THE NR1 TORQUE INDICATOR WAS FLUCTUATING ERRATICALLY AND THE TORQUE INDICATOR CIRCUIT BREAKER HAD TRIPPED. AN INSP OF THE NR1 ENGINES FWD WIRE LOOM FOUND SEVERAL CHAFED WIRES. THE WIRES WERE CHAFING AGAINST THE FWD LOWER ENGINE COWL. Feb 12, 2010 · Beech B200 · Engine BMEP/Torque IndicatingSDR CA100129008Powerpack · malfunctioned(CAN) MX WAS CARRIED OUT ON THE ACFT THAT REQUIRED GEAR SWING(S). THE FIRST WAS SUCCESSFUL. THE SECOND SHOWED A WEAK RETRACTION AND THE THIRD POPPED THE 60AMP GEAR CB. TROUBLESHOOTING POINTED TOWARDS THE POWERPACK. THE POWERPACK WAS REMOVED AND SENT TO THE OJan 27, 2010 · Beech B200 · Landing Gear Retraction/Extension SystemSDR CA100127005Windshield · cracked(CAN) DURING CLIMB, PILOT HEARD AND THEN NOTICED THE LT WINDSHIELD HAD CRACKED. PILOT RETURNED TO AIRPORT. MX DETERMINED OUTER PANE HAD MULTIPLE CRACKS, MOSTLY VERTICAL, PARALLEL TO AND SLIGHTLY OTBD OF WINDSHIELD WIPER. HAVE SEEN OTHER WINDSHIELDS FAIL WIJan 26, 2010 · Beech B200 · Flight Compartment WindowsSDR CA100816002Door · unlatchedDOOR OPENED IN FLIGHT. TALKED TO THE PILOT INVOLVED AND HE SAID THE MEDICAL STAFF DID NOT LATCH THE DOOR. JUST INSPECTED LATCHES LAST WEEK AND THERE WAS STILL NO FAULT FOUND WITH THE LATCHING MECHANISM. SERVICE LETTER GIVES A NEW AND IMPROVED LOCK ASSY AND WJan 22, 2010 · Beech B200 · Accessory Compartment DoorsSDR CA100121002Control Unit · failed(CAN) CREW NOTICED A DECREASE IN CABIN DIFF. WHEN ACFT RETURNED TO MX BASE. IT WAS GROUND RUN AND THE LT FLOW CONTROL UNIT WAS NOT SUPPLYING THE REQUIRED AIR FLOW TO MAINTAIN THE CABIN DIFFERENTIAL. FLOW CONTROL UNIT WAS REPLACED WITH A SERVICEABLE UNIT AND GRJan 20, 2010 · Beech B200 · Cabin Pressure Control SystemSDR 2010F00019Terminal · looseCREW LANDED; UPON TAXING TO RAMP, DISCOVERED THAT THE FLAPS WOULD NOT MOVE OUT OF TAKEOFF/APPROACH. CREW CHECKED ALL CIRCUIT BREAKERS, NO DEFECTS NOTED. AFTER PARKING, PERFORMED WALK AROUND AND INSPECTED FLAP SYS, AGAIN NO DEFECTS NOTED. NOTIFIED MX. MX WAS Jan 20, 2010 · N727B · Beech B200 · Flight Control System WiringSDR CA100107006Skin · cracked(CAN) SKINS, P/N 101-910049-11 AND 12 CRACKED AT FOD SCREEN BRACKETS. THIS OCCURRED ON THE LEFT AND RIGHT AFT LOWER ENGINE COWL. THE LEFT AND RIGHT COWLS ARE THE SAME PART NUMBER. THESE SKINS FORM THE LOWER PORTION OF THE ENGINE INTAKE DUCT. (TC NR 20100107Dec 29, 2009 · Beech B200 · Engine Cowling SystemSDR CA091221007Selector · inaccurate(CAN) COMMENCING GPS OVERLAY FOR 09 IN YXE, CLEARED TO 3200 FT AND VECTORED THROUGH THE LOC, UPON REINTERCEPTION THE ALERTER CHIMED 1000 FT ABOVE ACKNOWLEDGED CHIME BY PUSHING IT IN, BUT WHEN PUSHED, IT RESET ITSELF TO 2000 FT, SO AT THAT POINT THE ACFT DID A Dec 17, 2009 · Beech B200 · Autopilot SystemSDR CA100107008Door Frame · damaged(CAN) FORWARD DOOR FRAME (AIRFRAME) SHEARED FASTENERS AT ATTACH POINT WITH FUSELAGE BULKHEAD. LOCATION IS FS 278.5, WATERLINE 83.0.0, LBL 25.0. (TC NR 20100107008)Dec 9, 2009 · Beech B200 · Fuselage Main, StructureSDR CA100107007Bulkhead · cracked(CAN) BULKHEAD AT FS 246.75 CRACKED UNDER FLOOR, WATERLINE 85.0, BUTTOCK LINE 25.0 LEFT. (TC NR 20100107007)Dec 9, 2009 · Beech B200 · Fuselage Main, BulkheadSDR 2009FA0001033Trim Tab · contaminatedT/E OF RUDDER ABOVE TRIM TAB FOUND TO BE FULL OF WATER DURING INSPECTION. SUGGEST SERVICE INFORMATION BE INTRODUCED TO CHECK RUDDER FOR PROPER DRAIN HOLES AND ANY OBSTRUCTIONS. (K)Nov 18, 2009 · N708WH · Beech B200 · Rudder, Tab StructureSDR CA091110008Frame · chafed(CAN) WHEN PERFORMING SB 24-3939, IT WAS DISCOVERED THAT ONE OF THE WIRING HARNESS WAS CONTACTING THE FWD FRAME OF THE CO-PILOT CIRCUIT BREAKER PANEL RECESS. CHAFING HAS NOT PENETRATED THE WIRING INSULATION. CONTACT AREA WAS LIMITED TO THE FRAME `TAB` PROTRUNov 7, 2009 · Beech B200 · Fuselage Main, FrameSDR 2009F00100Hook · obstructedTHE ENGINE COWLING LATCH INDICATED THE UPPER AND LOWER COWLS WERE PROPERLY LATCHED. THEY WERE NOT AND THE ENGINE COWL CAME LOOSE DURING A GROUND PERFORMANCE RUN. THE AFT PART OF THE UPPER FORWARD COWL LIFTED UP CAUSING THE FORWARD PORTION OF THE COWL TO CONTAOct 27, 2009 · N265EJ · Beech B200 · Engine Cowling SystemSDR CA091028004Control Cable · frayed(CAN) DURING PHASE THREE INSPECTION, THE LEFT HAND RUDDER CONTROL CABLE WAS FOUND TO HAVE APPROXIMATELY 15 FRAYED STRANDS WITHIN A TWO INCH LENGTH AT THE PULLEY AT STATION 305.260 JUST AFT OF THE PASSENGER DOOR, WHERE THE LOWER FUSELAGE CURVES UP TOWARDS THE TOct 16, 2009 · Beech B200 · Rudder Control SystemSDR CA091027005Armature · shorted(CAN) GENERATOR FAILED IN FLIGHT. SENT TO AMO FOR ASSESSMENT. AMO INSPECTED AND TESTED THE GENERATOR. BEFORE DISASSY, A FUNCTIONAL TEST WAS ATTEMPTED. THE GENERATOR HAD LOW RESIDUAL VOLTAGE AT IDLE, BUT SUFFICIENT TO ENERGIZE AND DEVELOP 30 VOLTS. IMMEDIATELY Oct 11, 2009 · Beech B200 · Starter-GeneratorSDR 2009FA0000829Turnbuckle · brokenAIR CONDITIONING BELT TENSION ADJUSTMENT TURNBUCKLE AND BRACKET BROKE. THE TURNBUCKLE BROKE AT THE ROD END AND THE BRCKET BROKE AT THE TAB CONNECTING THE COMPRESSOR BRACKET TO THE ENGINE. (K)Sep 11, 2009 · N225SL · Beech B200 · Cabin Cooling SystemSDR 2009FA0000826Grease · inadequateTHE NEW GREASE MIL-PRF-81322 AVIATION GREASE SHC 100 CALLED OUT FOR USE BY MFG IN CHAP 12-20-00 ON THE WHEEL BEARINGS DOES NO SUFFICIENTLY LUBRICATE THE BEARINGS CAUSING THEM TO SEIZE UP. (K)Sep 11, 2009 · N225SL · Beech B200 · Landing Gear SystemSDR ESM2009F00000Fuel Nozzle · damagedSUBJECT FUEL NOZZLE WAS INSTALLED IN A POST SB3250 ADAPTER, & AFTER 10.7 HOURS OF OPS, NOZZLE LOST TORQUE ALLOWING FUEL TO BYPASS NOZZLE ORIFICE ENTERING ENGINE AT SEALING SURFACE OF LOCK TAB. PILOT REPORTED A 50 DEGREE C JUMP IN TEMP ON LAST FLT, CHOSE TO COSep 2, 2009 · N200EA · Beech B200 · Engine Fuel DistributionSDR CA090728012Rib · cracked(CAN) DURING INSP, IT WAS FOUND THAT AT THE LT WING L/E, AT WS 121.966, RIB PN:50-980002-825 WAS CRACKED. THE CRACKING APPEARED TO BE FROM FATIGUE AND NOT FROM A TOOLING MARK OR OTHER INDUCED CAUSES. THE REASON FOR THIS SDR IS THAT THIS IS THE THIRD AIRCRAFT Jul 14, 2009 · Beech B200 · Wing, Rib/BulkheadSDR CA090709003Heater · cracked(CAN) A PREVIOUS WELD REPAIR HAD CRACKED ON THE OUTER HSG OF OIL-TO-FUEL HEATER, RESULTING IN OIL LOSS.Jun 25, 2009 · Beech B200 · Engine Fuel/Oil CoolerSDR CIEA200900008Bracket · crackedDURING THE 10000 CYCLE STRUCTURAL INSP, FOUND THE FWD DOOR SUPPORT CABLE EXTRUSION INSIDE THE DOOR IS CRACKED IN TWO PLACES. GAINED ACCESS TO THE FWD HANDRAIL BRACKET ON THE MAIN CABIN DOOR UNDER THE HANDRAIL SUPPORT BRACKET, REMOVED THE CRACKED BRACKET AND IJun 23, 2009 · N203LG · Beech B200 · Passenger/Crew DoorsSDR CA090728011Rib · cracked(CAN) DURING INSP, IT WAS FOUND THAT AT THE VERY L/E AT WS 121.966, LT WING RIBS AS WELL AS RT WING RIBS WERE CRACKED. THE CRACKING APPEARED TO BE FROM FATIGUE, AND NOT FROM A TOOLING MARK OR OTHER INDUCED CAUSES. THE REASON FOR FILING THIS SDR, IS THAT WE Jun 12, 2009 · Beech B200 · Wing, Rib/BulkheadSDR CA090604010Spring · broken(CAN) MX PERSONNEL DISCOVERED THERE WAS NO POSITIVE FEATHER DETENT ON RT PROP CONTROL AT THE PEDESTAL. INVESTIGATION DETERMINED THE DETENT SPRING HAD BROKEN. SPRING REPLACED WITH NEW PART.Jun 4, 2009 · Beech B200 · Propeller Controlling SystemSDR 2009FA0000520Drain · crackedCURTIS DRAIN VALVE LEAKING FUEL BECAUSE OF A CRACKED SEAL RETAINER. THIS RESULTED IN A MAJOR FUEL LEAK BECAUSE THE INTERNAL PLUNGER FELL COMPLETELY OUT OF THE VALVE. LEAK RATE WAS ABOUT 2 GALLONS PER MINUTE. HAVE 2 VALVES WHICH ARE DEFECTIVE. SEAL RETAINERMay 31, 2009 · N53GA · Beech B200 · Fuel Storage
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