# Service difficulty reports: Beechcraft B200C

A list on [Beechcraft B200C](https://openairdocs.org/model/beechcraft-b200c.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 4 · 169 reports

- [SDR TIMA20240716008](https://openairdocs.org/sdr/TIMA20240716008.md): Engine · faulted · Jul 16, 2024 · N125K · Beech B200C · Engine (Turbine/Turboprop)
  > ON 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.
- [SDR 2023FA0000541](https://openairdocs.org/sdr/2023FA0000541.md): Panel · shorted · Sep 14, 2023 · N581EA · Beech B200C · Indicating/Recording System
  > SMELLED 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 BU
- [SDR 2023FA0000537](https://openairdocs.org/sdr/2023FA0000537.md): Unknown · unknown · Sep 12, 2023 · N581EA · Beech B200C · Fuselage Structure (General)
  > ENCOUNTERED 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.
- [SDR 1EAA2021052700158](https://openairdocs.org/sdr/1EAA2021052700158.md): Coupling · failed · Apr 12, 2021 · N389RA · Beech B200C · Engine Fuel Pump
  > FAILURE OF THE #1 ENGINE HP FUEL PUMP DRIVE COUPLING
- [SDR 2017FA0000159](https://openairdocs.org/sdr/2017FA0000159.md): Bolt · broken · Apr 6, 2017 · Beech B200C · Landing Gear Retraction/Extension System
  > LT 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 ASSOC
- [SDR 2016FA0000473](https://openairdocs.org/sdr/2016FA0000473.md): Tube · chafed · Oct 6, 2016 · N4489A · Beech B200C · Power Lever
  > DURING 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. I
- [SDR USAR201601050003](https://openairdocs.org/sdr/USAR201601050003.md): Door Frame · cracked · Jan 4, 2016 · Beech B200C · Fuselage Main, Structure
  > (00484) AIRSTAIR DOOR FUSELAGE FRAME ENTRY LOWER FWD CORNER CRACK 0.750" LENGTH.
- [SDR USAR201601050002](https://openairdocs.org/sdr/USAR201601050002.md): Door Frame · cracked · Jan 4, 2016 · Beech B200C · Fuselage Main, Structure
  > (00484) AIR-STAIR DOOR FUSELAGE FRAME ENTRY UPPER FORWARD CORNER CRACKED, 0.500" LENGTH.
- [SDR USAR201601050001](https://openairdocs.org/sdr/USAR201601050001.md): Frame · cracked · Jan 4, 2016 · Beech B200C · Fuselage Main, Frame
  > AIRSTAIR DOOR FUSELAGE FRAME ENTRY UPPER AFT CORNER CRACKED, 1.125" LENGTH.
- [SDR USAR201508210003](https://openairdocs.org/sdr/USAR201508210003.md): Door Frame · cracked · Aug 19, 2015 · Beech B200C · Fuselage Main, Structure
  > DOOR FRAME CRACKED GREATER THAN 1.0" FOUND IN LOWER THRESHOLD SILL CLOSURE.
- [SDR USAR201508210002](https://openairdocs.org/sdr/USAR201508210002.md): Door Frame · cracked · Aug 19, 2015 · Beech B200C · Fuselage Main, Structure
  > DOOR FRAME CRACKED GREATER THAN 1.0" FOUND IN UPPER FORWARD CLOSURE.
- [SDR USAR201508210001](https://openairdocs.org/sdr/USAR201508210001.md): Structure · cracked · Aug 19, 2015 · Beech B200C · Fuselage Miscellaneous Structure
  > CRACKS GREATER THAN 1.0" FOUND IN UPPER AFT CLOSURE.
- [SDR USAR201508190001](https://openairdocs.org/sdr/USAR201508190001.md): Door Sill · cracked · Aug 14, 2015 · Beech B200C · Fuselage Miscellaneous Structure
  > (00155) ENTRY DOOR SILL CLOSURE WAS INSPECTED AND FOUND TO HAVE 1 EA, 0.75" CRACK IN THE UPPER AFT CORNER CLOSURE.
- [SDR CA150817003](https://openairdocs.org/sdr/CA150817003.md): Engine · flamed out · Aug 4, 2015 · Beech B200C · Engine (Turbine/Turboprop)
  > (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.
- [SDR USAR201508060003](https://openairdocs.org/sdr/USAR201508060003.md): Threshold · cracked · Aug 4, 2015 · Beech B200C · Fuselage Miscellaneous Structure
  > (00150) INSPECTOR FOUND.250 INCH CRACK IN THE LOWER THRESHOLD ENTRY DOOR CLOSURE.
- [SDR USAR201508060002](https://openairdocs.org/sdr/USAR201508060002.md): Door Frame · cracked · Aug 4, 2015 · Beech B200C · Fuselage Main, Structure
  > (00150) INSPECTOR FOUND ONE INCH CRACK IN THE UPPER FORWARD CORNER OF ENTRY DOOR CLOSURE.
- [SDR USAR201508060001](https://openairdocs.org/sdr/USAR201508060001.md): Door Frame · cracked · Aug 4, 2015 · Beech B200C · Fuselage Main, Structure
  > (00150) INSPECTOR FOUND A ONE INCH CRACK IN UPPER AFT CORNER OF ENTRY DOOR CLOSURE.
- [SDR USAR201508060004](https://openairdocs.org/sdr/USAR201508060004.md): Door Frame · cracked · Aug 3, 2015 · Beech B200C · Fuselage Main, Structure
  > (03329) CRACKS LESS THAN.7 INCH WERE FOUND IN THE LOWER FORWARD AND LOWER AFT CORNER CLOSURE.
- [SDR USAR201507280003](https://openairdocs.org/sdr/USAR201507280003.md): Door Frame · cracked · Jul 17, 2015 · Beech B200C · Fuselage Main, Structure
  > (00320) INSPECTOR FOUND.2 INCH CRACK IN UPPER FORWARD CORNER OF ENTRY DOOR CLOSURE AT WELL NUT HOLE.
- [SDR USAR201506120002](https://openairdocs.org/sdr/USAR201506120002.md): Structure · cracked · Jun 8, 2015 · Beech B200C · Fuselage Main, Structure
  > ENTRY DOOR: DURING INSPECTION A.080" CRACK AT WELL NUT HOLE ON FORWARD VERTICAL CLOSURE WAS NOTED.
- [SDR USAR201506120001](https://openairdocs.org/sdr/USAR201506120001.md): Door Frame · cracked · Jun 8, 2015 · Beech B200C · Fuselage Main, Structure
  > ENTRY DOOR FRAME: LOWER CLOSURE HAS A.100" CRACK AT A WELL NUT HOLE.
- [SDR CA150521002](https://openairdocs.org/sdr/CA150521002.md): Motor · failed · May 19, 2015 · Beech B200C · Hydraulic System, Main
  > (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.
- [SDR USAR2015004240001](https://openairdocs.org/sdr/USAR2015004240001.md): Structure · cracked · Apr 17, 2015 · Beech B200C · Fuselage Miscellaneous Structure
  > (00489) DOOR SILL CLOSURE FATIGUE CRACK, UPPER FORWARD CORNER.250" APPROXIMATELY.
- [SDR CA140318003](https://openairdocs.org/sdr/CA140318003.md): Motor · failed · Feb 28, 2014 · Beech B200C · Landing Gear Retraction/Extension System
  > (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 L
- [SDR CA131021015](https://openairdocs.org/sdr/CA131021015.md): Coupling · disengaged · Oct 12, 2013 · Beech B200C · Fuel Control/Reciprocating Engines
  > (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 FR
- [SDR CA131021013](https://openairdocs.org/sdr/CA131021013.md): Engine · unknown · Oct 10, 2013 · Beech B200C · Engine (Turbine/Turboprop)
  > (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 MOME
- [SDR CA130824001](https://openairdocs.org/sdr/CA130824001.md): Engine · power loss · Aug 22, 2013 · Beech B200C · Engine (Turbine/Turboprop)
  > (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.
- [SDR CA130318002](https://openairdocs.org/sdr/CA130318002.md): Fuel Control · failed · Feb 18, 2013 · Beech B200C · Fuel Control/Turbine Engines
  > (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.
- [SDR EHAA20120225002](https://openairdocs.org/sdr/EHAA20120225002.md): Windshield · cracked · Feb 25, 2012 · N134WJ · Beech B200C · Flight Compartment Windows
  > ON CLIMBOUT, HEARD A STRANGE SOUND AS THE GEAR WAS RETRACTED. IT WAS DARK. UPON FURTHER INVESTIGATION, SAW CRACKS ON THE CO-PILOTS WINDSHIELD.
- [SDR 2011FA0000112](https://openairdocs.org/sdr/2011FA0000112.md): Display · malfunctioned · Feb 15, 2011 · N7232R · Beech B200C · Central Display
  > THE 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 FUN
- [SDR 2011FA0000111](https://openairdocs.org/sdr/2011FA0000111.md): Display · malfunctioned · Dec 16, 2010 · N7232R · Beech B200C · Central Display
  > ON 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. M
- [SDR CA090526009](https://openairdocs.org/sdr/CA090526009.md): Skin · cracked · May 20, 2009 · Beech B200C · Fuselage Main, Plate/Skin
  > (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.
- [SDR CA081002005](https://openairdocs.org/sdr/CA081002005.md): Line · leaking · Sep 29, 2008 · Beech B200C · Aircraft Fuel Distribution System
  > (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 THR
- [SDR 2008FA0000377](https://openairdocs.org/sdr/2008FA0000377.md): Skin · cracked · Jul 1, 2008 · N7232R · Beech B200C · Wing, Plate/Skin
  > DURING 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 W
- [SDR CA061221003](https://openairdocs.org/sdr/CA061221003.md): Motor · failed · Dec 18, 2006 · Beech B200C · Landing Gear Retraction/Extension System
  > (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
- [SDR AU510001942](https://openairdocs.org/sdr/AU510001942.md): Ring · cracked · Dec 12, 2005 · Beech B200C · Turbine Section
  > (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)
- [SDR AU510001575](https://openairdocs.org/sdr/AU510001575.md): Servo · faulty · Dec 12, 2005 · Beech B200C · Autopilot Main Servo
  > RUDDER AUTOPILOT SERVO/YAW DAMPER FAULTY, OTHER CAUSE: FAILURE OF INTERNAL MECHANISM.
- [SDR CA051215001](https://openairdocs.org/sdr/CA051215001.md): Actuator · failed · Dec 6, 2005 · Beech B200C · Landing Gear Actuator
  > AFTER 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 FUR
- [SDR CA050117001](https://openairdocs.org/sdr/CA050117001.md): Frame · cracked · Jan 13, 2005 · Beech B200C · Nacelle/Pylon, Frame/Spar/Rib
  > (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 LIGHT
- [SDR 2005FA0000034](https://openairdocs.org/sdr/2005FA0000034.md): Relay · failed · Oct 19, 2004 · N7232R · Beech B200C · Trailing Edge Flap Control System
  > WHILE 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 DUPLICATE
- [SDR CA040922005](https://openairdocs.org/sdr/CA040922005.md): Actuator · worn · Sep 21, 2004 · Beech B200C · Landing Gear Actuator
  > (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 SE
- [SDR CA040922001](https://openairdocs.org/sdr/CA040922001.md): Snap Ring · out of position · Sep 21, 2004 · Beech B200C · Landing Gear Retraction/Extension System
  > (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, T
- [SDR EHA2004F00006](https://openairdocs.org/sdr/EHA2004F00006.md): Unknown · malfunctioned · Jul 26, 2004 · N134WJ · Beech B200C · Cabin Compressor System
  > PRELIMINARY - 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, PR
- [SDR 2004FA0000524](https://openairdocs.org/sdr/2004FA0000524.md): Torque Tube · loose · Jul 1, 2004 · N7232R · Beech B200C · Elevator Control System
  > DURING 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 TUB
- [SDR CA040624001](https://openairdocs.org/sdr/CA040624001.md): Mount · mismanufactured · Jun 17, 2004 · Beech B200C · Engine Mount Section
  > (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 ALL
- [SDR 2004FA0000523](https://openairdocs.org/sdr/2004FA0000523.md): Torque Tube · loose · Jun 1, 2004 · N7232R · Beech B200C · Elevator Structure
  > DURING 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
- [SDR AUS20040433](https://openairdocs.org/sdr/AUS20040433.md): Seal · worn · May 20, 2004 · Beech B200C · Turbine Engine Oil System
  > (AUS) ENGINE ACCESSORY GEARBOX STARTER-GENERATOR DRIVE SHAFT SEAL WORN. LOSS OF ENGINE OIL.
- [SDR AUS20040400](https://openairdocs.org/sdr/AUS20040400.md): Turbine Blades · cracked · May 12, 2004 · Beech B200C · Turbine Section
  > (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.
- [SDR AUS20040222](https://openairdocs.org/sdr/AUS20040222.md): Shaft · failed · Mar 23, 2004 · Beech B200C · Landing Gear Retraction/Extension System
  > (AUS) LT MAIN LANDING GEAR RETRACTION DRIVE TUBE FAILED DUE TO INTERFERENCE WITH PNEUMATIC DUCTING CLAMP.
- [SDR AUS20040213](https://openairdocs.org/sdr/AUS20040213.md): Valve · faulty · Mar 12, 2004 · Beech B200C · Fuel Transfer Valve
  > (AUS) DEFECT REPORT NR WAS CREATED IN LIEU OF DATA BEING ATTACHED TO MDR 04/0176. CANCELLED, DATED 25TH MARCH 2004.

Next page: https://openairdocs.org/model/beechcraft-b200c/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
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
```

This list as a web page: https://openairdocs.org/model/beechcraft-b200c/reports

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