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 DGCA971Line · separatedLT MLG BEGAN LOWERING OUT OF THE NACELLE DURING FLIGHT.Mar 19, 2009 · N347D · Beech B200 · Hydraulic System, MainSDR 2009F00024Line · separatedLT MLG BEGAN LOWERING OUT OF NACELLE DURING FLIGHT.Mar 19, 2009 · N347D · Beech B200 · Hydraulic System, MainSDR 2009FA0000166Antenna · brokenELT ANTENNA BREAKS IN HALF AND LEAVES THE AIRPLANE IN FLIGHT. WE HAVE INSTALLED (2) ELT ANTENNAS P/N 110-323 AND BOTH HAVE BROKEN OFF. WE ARE NOW INSTALLING A THIRD. THEY KNOW THERE IS A PROBLEM WITH THE ANTENNAS, BUT AT THIS TIME, IT IS NOT A PRIORITY TO COFeb 27, 2009 · N520DG · Beech B200 · Emergency Locator BeaconSDR CIEA200900006Stringer · crackedDURING COMPLIANCE WITH MFG MANDATORY SB 53-2472, REVISION 4, DATED JULY 2003 AND AD 2005-01-18, AMENDMENT 39-13943, EFFECTIVE DATE MARCH 01, 2005 THE LT STRINGER NR 9 AT AFT PRESSURE BULKHEAD WAS FOUND TO BE CRACKED. REPAIRED THE NR 9 AFT FUSELAGE STRINGER ONFeb 25, 2009 · N203LG · Beech B200 · Fuselage Main, Longeron/StringerSDR CA090203002Power Cable · seizedTHE POWER CABLE WAS REPLACED 200 HRS PRIOR DUE TO VERY STIFF OPERATION AND 200 HRS LATER DURING A SCHEDULED INSPECTION. THE SAME CABLE WAS FOUND VERY STIFF AND HAD EXCESSIVE END PLAY. SUSPECT SUB-QUALITY AIRCRAFT PART.Jan 29, 2009 · Beech B200 · Power LeverSDR QMLA2009011509002Windshield · crackedENROUTE AT 23000 FT THE COPILOT'S WINDSHIELD CRACKED. THE EMERGENCY CHECKLIST WAS REVIEWED AND FOLLOWED. A NON EMERGENCY DESCENT AND 180 DEGREE TURN WAS REQUESTED FROM ATC. THE CREW DESCENDED TO 10,000 FT AND RETURNED TO DEPARTURE. A NORMAL LANDING WAS PERFORMJan 15, 2009 · N220TB · Beech B200 · Flight Compartment WindowsSDR CA090126005Wire · broken(CAN) AIR CONDITIONING RESET SWITCH LOCATED IN THE WHEEL WELL FOUND BROKEN. UPON EXAMINATION OF SWITCH IT WAS NOTED FACTORY INSTALLED HEAT SHRINK TUBING WAS NOT PROPERLY INSTALLED THEREBY ALLOWING IT TO MIGRATE AWAY FROM THE SWITCH CONNECTOR. THIS IN TURN CANov 24, 2008 · Beech B200 · Air Conditioning System WiringSDR HDNA200811030001Cowling · departedDURING CRUISE FLIGHT, THE AIRCRAFT SHUDDERED LIGHTLY AND THE PILOT SAW A FLASH OF WHITE. THE NR 1 ENGINE TOP FORWARD COWLING DISENGAGED FROM THE AIRPLANE. INITIAL THOUGHT WAS A BIRD STRIKE, BUT THERE WAS NO VISIBLE EVIDENCE. THE ENGINE INSTRUMENTS WERE MONINov 1, 2008 · N315MS · Beech B200 · Engine Cowling SystemSDR CA081007009C/Breaker Panel · burned(CAN) PILOTS REPORTED FLAMES AND FIRE FROM LOWER RT CORNER OF THE RT CIRCUIT BREAKER PANEL AND MADE AN EMERGENCY LANDING. THE CIRCUIT BREAKER FOR THE EDGE LIGHTED PANEL LIGHTS OPENED AS A RESULT OF THE SHORT AT 1 BULB BUT NOT BEFORE THE HEAT HAD BURNED PART WAOct 1, 2008 · Beech B200 · Light System WiringSDR CA080908003Float Valve · dislodged(CAN) ATTACH PIN MIGRATED OFF ALLOWING FLOAT TO BECOME DISLODGED FROM FLOAT VALVE PIN 118-381002-1. ATTACH PIN MIGRATED TO ORIGINAL POSITION AFTER FLOAT BECAME DISLODGED. THE FLOAT WAS LOCATED AT THE RT FUEL FILLER. THE NEW VALVE WAS DATED IN 2000 WHILE THE DESep 2, 2008 · Beech B200 · Fuel StorageSDR 2008FA0000508Bracket · misinstalledPILOT REPORTED DOOR CAME OPEN IN FLIGHT. UPON LANDING, IT WAS FOUND THE MAIN CABIN DOOR HAD DEPARTED AIRCRAFT. DOOR WAS RECOVERED. DURING INSPECTION AND DISASSEMBLY OF THE DOOR, SEVERAL ISSUES WERE FOUND. 1) UPPER FORWARD LATCH HOOK WAS FOUND WITHOUT RIGGIJul 16, 2008 · N786DD · Beech B200 · Passenger/Crew DoorsSDR XOR2008F00000Brake · smokePILOTS DEVIATED FROM THE PILOT OPERATING PROCEDURES FOR TAXIING OF THE AC PROCEEDING A MLG BRAKE AND WHEEL TIRE CHANGE THE AC RETURNED TO THE RAMP AREA WITH NO ABNORMAL INDICATIONS, OTHER THAN THE BRAKE/RUDDER PEDALS ACHIEVING EXCESSIVE TRAVEL TO THE FLIGHT DJul 9, 2008 · N200EG · Beech B200 · Landing Gear Brake SystemSDR 772AFCheck Valve · defectiveFLAPPERS IN BLEED AIR INLET CHECK VALVE CAME LOOSE AND CHAFED THE INSIDE OF THE HOUSING. ONE FLAPPER CHAFED A HOLE THROUGH THE HOUSING.Jun 3, 2008 · N772AF · Beech B200 · Pneumatic Distribution SystemSDR N772AFHinge · corrodedCENTER RUDDER HINGE FOUND TO HAVE EXCESSIVE CORROSION.Jun 2, 2008 · N772AF · Beech B200 · Rudder StructureSDR 2008FA0000412Control Arm · wornLT ENGINE NACELLE ICE-VANE CONTROL ARM HAD WORN OUT OR DESTROYED BUSHINGS AT ALL 3 ACTUATING CONTROL ARM DRIVE POINTS AND LINKS, CAUSING POTENTIAL FOR F.O.D. TO ENGINE. WHEN ICE VANE IS IN THE RETRACTED POSITION THERE ARE NO HARD STOPS TO KEEP IT FROM VIBRATIMay 28, 2008 · N6604L · Beech B200 · Engine Anti-Icing SystemSDR 2008FA0000540Wheel · crackedCRACK INDICATIONS LOCATED IN BEAD AREA OF WHEELS, REVEALED BY FLUORESCENT PENETRANT. (K)May 2, 2008 · N200ND · Beech B200 · Wheel/Ski/FloatSDR 2008FA0000539Wheel · crackedCRACK INDICATIONS LOCATED IN BEED AREA OF WHEELS REAVEALED BY FLUORESCENT PENETRANT. (K)May 2, 2008 · N200ND · Beech B200 · TireSDR 2008FA0000184Compressor · damagedDURING PERFORMANCE OF A SCHEDULED 1800 HOUR HOT SECTION INSPECTION OF THE RT ENGINE, AT 1771 HOURS AND 7 YEARS TIS SINCE OVERHAUL, INITIAL VISUAL INSPECTION OF THE CT BLADES TIP CLEARANCE REVEALED CLEARANCES IN EXCESS OF ALLOWABLE FOR RETURN TO SERVICE. IT WAMar 4, 2008 · N185XP · Beech B200 · Turbine Engine Compressor SectionSDR 2008FA0000183Turbine · damagedDURING PERFORMANCE OF A SCHEDULED 1800 HOUR HOT SECTION INSPECTION OF THE RT ENGINE, AT 1771 HOURS AND 7 YEARS TIME IN SERVICE SINCE OVERHAUL, INITIAL VISUAL INSPECTION OF THE CT BLADES TIP CLEARANCE REVEALED CLEARANCES IN EXCESS OF ALLOWABLE FOR RETURN TO SERMar 4, 2008 · N185XP · Beech B200 · Turbine SectionSDR 35741Fire Detector · false activationDEPARTING TUCSON, DURING CLIMBOUT, NW BOUND, COPILOT ANNOUNCED "MASTER WARN - RT ENG FIRE". NO OBVIOUS INDICATION OF A FIRE. REQUESTED A CHANGE OF COURSE DUE TO THE FIRE DETECTION SYS DESIGN - PHOTO-SENSITIVE. AFTER FLYING THE NEW HEADING FOR APPROX 3 MIN, Feb 20, 2008 · N32WC · Beech B200 · Fire DetectionSDR CA080107003Torque Knee · cracked(CAN) WHILE PERFORMING AN INSPECTION ON THE GEAR IT WAS NOTICED THAT GREASE WAS COMING FROM THE HORIZOTAL CRACK IN THE BOTTOM OF THE TORQUE KNEE. A NEW KNEE WAS ORDERED AND REPLACED. (TC NR 20080107003)Jan 7, 2008 · Beech B200 · Landing Gear Retraction/Extension SystemSDR CA080102005Cover · cracked(CAN) FOUND EXHAUST SOOT IN COWLS. CLOSER INSPECTION FOUND THE BUTTERFIELD STC COVER PLATE LEAKING AND THE HEATED INLET CRACKED IN MULTIPLE LOCATIONS ON BOTH COWLS. (TC NR 20080102005)Dec 31, 2007 · Beech B200 · Nacelle/Pylon Miscellaneous StructureSDR 20071227209Pressure Switch · corrodedDURING TAKEOFF ROLL THE RUDDER PEDALS KICKED HARD LT CAUSING LOSS OF DIRECTIONAL CONTROL. ABORTED TAKEOFF AND TAXIED TO RAMP. MX PERFORMED A RUDDER BOOST TEST AND NOTED DURING RUN-UP THAT THE RT ENGINE RUDDER BOOST DID NOT RESPOND. THE LT ENGINE RUN-UP CAUSDec 27, 2007 · N209CM · Beech B200 · Rudder Control SystemSDR T4OR4765001Lever · twistedWHILE TRYING TO RIG THE CABIN DOOR UPPER LATCH HOOKS FOR PROPER OVERCENTER, IT WAS FOUND PROPER OVERCENTER COULD NOT BE OBTAINED WITHOUT THE ADJUSTING ROD END WITNESS HOLES BEING EXPOSED. CLOSER EXAMINATIONS SHOWED THE FWD AND AFT DOOR ACTUATION LEVER ASSEMBLDec 21, 2007 · N240CT · Beech B200 · Passenger/Crew DoorsSDR CA071210004Hinge · worn(CAN) LT AND RT OB FLAPS IB HINGES WORN DUE TO ROLLER DIGGING INTO OB BRACKETS P/N 35-165050-30 AND 35-165050-31. THE AFT BEARINGS/ROLLERS HAVE TO BE REMOVED TO GET A GOOD INSPECTION OF THIS AREA. IT SHOULD NOT BE DONE (IN-SITU). THIS IS THE 3RD AIRCRAFT IN THDec 9, 2007 · Beech B200 · Trailing Edge FlapsSDR CA071128008Brushes · failed(CAN) WHILE ON FINAL THE PILOT NOTICED THAT THE LT GENERATOR HAD FAILED. UPON LANDING, AN INSPECTION WAS CARRIED OUT ON THE GENERATOR. IT WAS NOTICED THAT THE BRUSHES WERE ALL BROKEN WHICH WOULD INDICATE AN INTERNAL FAILURE. (TC NR 20071128008)Nov 28, 2007 · Beech B200 · Starter-GeneratorSDR BB1402111207Resistor · looseDURING APPROACH TO LANDING PILOT NOTICED SPARKING TWICE UNDER THE COPILOTS YOKE, AND NOTICED A BURNING SMELL. LANDED WITHOUT INCIDENT. THE MECHANIC FOUND A DIMMING RESISTOR LOOSE IN SUBPANEL. HE REPAIRED THE ITEM AND APPROVED THE A/C FOR RETURN TO SERVICE.Nov 12, 2007 · N791DC · Beech B200 · Light System WiringSDR CA071106007Indicator · leaking(CAN) WE HAD A PRESSURE GAUGE THAT HAD A SMALL LEAK SO WE PURCHASED A NEW GAUGE FROM MFG AND INSTALLED IT ON THE AIRCRAFT. WHEN SYSTEM WAS BROUGHT UP TO THE PROPER PRESSURE THE NEW GAUGE LEAKED WORSE THAN THE ORIGINAL GAUGE. THE GAUGE WAS SENT BACK TO BEECH ANNov 6, 2007 · Beech B200 · Hydraulic Pressure IndicatorSDR CA071029005Bolt · missing(CAN) DURING MAINTENANCE ON AIRCRAFT, NR 4 MAIN TIRE WORN TO LIMITS. DURING NR 4 MAIN WHEEL AND TIRE CHANGE, FOUND 3 OUT OF 6 BRAKE TORQUE PLATE ATTACH BOLTS MISSING AND REMAINING ATTACH BOLTS LOOSE. A LOOSE BOLT WAS FOUND LODGED IN WHEEL BETWEEN A WHEEL HALFOct 27, 2007 · Beech B200 · Landing Gear Brake SystemSDR CA071025007Roller · seized(CAN) ON APPROACH WHEN FLAPS WERE SELECTED DOWN, THE RT WING BECAME HEAVY. AILERON CONTROL WAS REDUCED AND FELT DIFFERENT THAN NORMAL. THE PILOT LANDED WITHOUT FURTHER INCIDENT AND SELECTED FLAPS UP. THE FLAPS DID NOT MOVE WHEN SELECTED UP, SPLIT-FLAP SAFETY MOct 24, 2007 · Beech B200 · Trailing Edge FlapsSDR 2009FA0000304Windshield · crackedCO-PILOTS WINDSHIELD INSTALLED, OCT 25, 2001 AT ACFT TT 5173.4, LANDING 5598. WINDSHIELD CRACKED IN FLIGHT OCT 21, 2007. APPROX 30 MINUTES AFTER DEPARTURE RT WINDSHIELD EXPERIENCED SEVERE CRACKING. PILOT RETURNED TO DEPARTURE. (K)Oct 21, 2007 · N401HC · Beech B200 · Flight Compartment WindowsSDR CA071025006Engine · making metal(CAN) 15 MINUTES INTO FLIGHT, THE ENGINE CEASED OPERATION AND SIMUTANEOUSLY ILLUMINATED THE CHIP DETECTOR INDICATOR. THE CHIP DETECTOR CIRCUIT BREAKER WAS THEN REPORTED TO HAVE `POPPED`. AIRCRAFT RETURNED TO POINT OF DEPARTURE. POST FLIGHT INSPECTION REVEALEDOct 11, 2007 · Beech B200 · Engine (Turbine/Turboprop)SDR 2007F00058Windscreen · crackedCOPILOTS WINDSHIELD INNER PANE CRACKED.Oct 8, 2007 · N277GE · Beech B200 · Flight Compartment WindowsSDR CA071024008Engine · failed(CAN) AT FL260, ITT INCREASED TO NEAR MAXIMUM. POWER WAS REDUCED TO FLIGHT IDLE HOWEVER ITT REMAINED HIGH. HEAVY SMOKE WAS OBSERVED COMING FROM EXHAUST. CREW ELECTED TO SHUTDOWN ENGINE AND PERFORM SINGLE ENGINE LANDING. POST FLIGHT INSPECTION REVEALED OIL DRIPOct 4, 2007 · Beech B200 · Engine (Turbine/Turboprop)SDR CA070831002Drive Assy · mismanufactured(CAN) ON LANDING, WHEN FLAPS SELECTED FROM 40 PERCENT TO 100 PERCENT, FLAPS STOPPED AT APPROXIMATELY 60 PERCENT, LT OB FLAP WAS SPLIT APPROXIMATELY 10 PERCENT. FLAP WOULD NOT EXTEND OR RETRACT. LT OB FLAP ACTUATOR FOUND TO HAVE COME APART AT THE 90 DEGREE DRIAug 30, 2007 · Beech B200 · Trailing Edge Flap ActuatorSDR 2007FA0000758Drive Shaft · shearedWHILE AT CRUISE FLIGHT, LT ENGINE SHUTDOWN WITHOUT WARNING. LANDED WITHOUT INCIDENT. FOUND HIGH PRESSURE FUEL PUMP SHAFT SPLINES SHEARED ON INSIDE OF DRIVE COUPLING RENDERING FUEL PUMP AND FUEL CONTROL INOPERABLE. INSPECTION WOULD NOT BE POSSIBLE WITHOUT PUMP Aug 28, 2007 · N544P · Beech B200 · Engine Fuel PumpSDR CA070826000Tube · detached(CAN) ON TAKEOFF THE CREW NOTICED A STRONG VIBRATION. THEY DECIDED TO CANCEL THE FLIGHT AND LAND BACK AT AIRPORT. FOUND THE NOSE TIRE BALANCE PATCH (FACTORY INSTALLED) HAD COME DISCONNECTED AND WAS TUMBLING LOOSE INSIDE THE TIRE. (TC NR 20070826000)Aug 25, 2007 · Beech B200 · Tire TubeSDR 2007FA0000735Ground Wire · brokenWIRE NR P73G16N AT RT ENGINE FIREWALL GROUND POINT GS15 SEPARATED FROM THE WIRE TERMINAL DURING CRUISE FLIGHT. THIS WIRE CONNECTS GROUND TO THE GCU PIN G. THE RT GENERATOR OUTPUT SPIKED AND OPENED THE 325 AMP RT BUSS CURRENT LIMITER, THE 50 AMP RT INVERTER CURAug 9, 2007 · N1925P · Beech B200 · Electrical Power System WiringSDR 2007AP0821001Terminal · brokenWIRE NUMBER P73G16N AT RT ENGINE FIREWALL GROUND POINT GS15 SEPARATED FROM THE WIRE TERMINAL DURING CRUISE FLIGHT. THIS WIRE CONNECTS GROUND TO THE GCU PIN G. THE RT GENERATOR OUTPUT SPIKED AND OPENED THE 325 AMP RT BUSS CURRENT LIMITER, THE 50 AMP RT INVERTERAug 9, 2007 · N1925P · Beech B200 · Electrical Power System WiringSDR 2007F00043Windshield · crackedAIRCRAFT DEPARTED, ENROUTE, ABOUT 45 MINUTES INTO FLIGHT, CREW REPORTED THEY WERE AROUND FL220 AND STARTED THEIR DESCENT INTO CMS, WHEN AT FL190 THE PILOTS WINDSHIELD CRACKED AND SPIDERWEBBED ACROSS THE ENTIRE WINDSHIELD. CREW LANDED THE AIRCRAFT WITHOUT ANYJul 5, 2007 · N177LA · Beech B200 · Flight Compartment WindowsSDR 2007F00038Windshield · crackedAIRCRAFT DEPARTED, ENROUTE, ABOUT 45 MINUTES INTO FLIGHT, CREW REPORTED THEY WERE AROUND FL220 AND STARTED THEIR DESCENT, WHEN AT FL190 THE PILOT'S WINDSHIELD CRACKED AND SPIDER WEBBED ACROSS THE ENTIRE WINDSHIELD. CREW LANDED THE AIRCRAFT WITHOUT ANY OTHER ISJul 5, 2007 · N177LA · Beech B200 · Flight Compartment WindowsSDR CA070622008Torque Tube · mismanufactured(CAN) DURING RIGGING CHECK, DUE TO REPLACEMENT OF THE ELEVATOR TORQUE TUBE, DISCOVERED THE ARM LOCATION WAS INCORRECT IN RELATION TO THE MOUNTING PLATE. THIS RESULTED IN NOT BEING ABLE TO ACHIEVE FULL TRAVEL OF THE ELEVATOR. THIS WAS CONFIRMED WHEN COMPARED Jun 12, 2007 · Beech B200 · Elevator Control SystemSDR F222007F00001Motor · failedTHE LANDING GEAR MOTOR, PN 115-38002-5, SN 977, GAVE NO INDICATIONS PRIOR TO FAILURE, NO SLUGGISH OR NOISY OPERATION. THE PART HAD 770.1 HOURS AND 765 CYCLES USED OF ITS 8000 CYCLE TBO. THE MOTOR HAD BEEN REMOVED FROM ANOTHER AC PRIOR TO THE OVERHAUL FOR POOJun 12, 2007 · N888ZX · Beech B200 · Landing Gear Retraction/Extension SystemSDR CA070705002Seal · leaking(CAN) ENGINE OIL PRESSURE WAS SEEN TO REDUCE AND FLUCTUATE IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FAULTY LIP SEAL (RECENTLY REPLACED) ON THE STARTER GENERATOR DRIVE SHAFT. (TC NR 20070705002)May 30, 2007 · Beech B200 · Starter-GeneratorSDR CA070704017Engine · overtemp(CAN) IN CRUISE, THE ENGINE INTER-TURBINE TEMPERATURE WAS SEEN TO INCREASE AND FLAMES AND SPARKS WERE SEEN EXITING THE EXHAUST. THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 200707040May 23, 2007 · Beech B200 · Engine (Turbine/Turboprop)SDR ZES2007F00000Fuel Control · inoperativeON APPROACH, RT ENGINE LOST POWER AND WAS UNRESPONSIVE TO THROTTLE MOVEMENT. FUEL CONTROL WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (K)Apr 21, 2007 · N6WU · Beech B200 · Fuel Controlling SystemSDR CA070424004Powerpack · failed(CAN) DURING A ROUTINE MEDEVAC AND TEN MINUTES AFTER DEPARTURE THE RED LIGHT IN THE IN THE LANDING GEAR HANDLE ILLUMINATED.VISUAL CONFIRMATION OUT CAPT SIDE WINDOW OF LANDING GEAR PARTIALLY DOWN. A MANUAL GEAR EXTENSION WAS INITIATED AND A UNEVENTFUL LANDINGApr 19, 2007 · Beech B200 · Hydraulic Pump (Electric/Engine), MainSDR 2007FA0000354Connector · corrodedTHE AIRCRAFT WAS FLYING THROUGH IMC, WITH ALOT OF RAIN ON THEIR WAY TO DESTINATION. AS THE CREW WAS LETTING DOWN TO LAND THE LT ENGINE FIRE LIGHT LIT UP. THE CREW SCANNED ALL THE GAGES, AND DETERMINED THAT THIS WAS A FALSE LIGHT. THE AC LANDED WITHOUT COMPLApr 2, 2007 · N200VU · Beech B200 · Fire Protection System WiringSDR 2007FA0000309Pin · brokenUPON EXTENDING THE LANDING GEAR, THE PILOTS GOT A RED GEAR UNSAFE LIGHT IN THE HANDLE, AND THE LT DOWN AND LOCKED LIGHT WAS NOT LIT UP. THE PILOTS TRIED TO EXTEND THE GEAR MANUALLY, BUT THE HANDLE WOULD NOT EXTEND THE GEAR ANY FURTHER, THE PILOTS RETRACTED THEApr 2, 2007 · N65TW · Beech B200 · Main Landing GearSDR 2007FA0000308Pin · brokenUPON EXTENDING THE LANDING GEAR, THE PILOTS GOT A RED GEAR UNSAFE LIGHT IN THE HANDLE, AND THE LT DOWN AND LOCKED LIGHT WAS NOT LIT UP. THE PILOTS TRIED TO EXTEND THE GEAR MANUALLY, BUT THE HANDLE WOULD NOT EXTEND THE GEAR ANY FURTHER, THE PILOTS RETRACTED THEApr 2, 2007 · N65TW · Beech B200 · Main Landing Gear Attach Section
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