# Service difficulty reports: Bell 206B-3

A list on [Bell 206B-3](https://openairdocs.org/model/bell-206b-3.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 15 · 708 reports

- [SDR 2025FA0000365](https://openairdocs.org/sdr/2025FA0000365.md): Cargo Hook · corroded · May 20, 2025 · N103NJ · Bell 206B3 · Cargo Compartments
  > DURING INSPECTION, FOUND CORRODED HARDWARE ON CARGO HOOK ATTACHMENT. INSTALLED 4EA NEW BOLTS P/N AN4-10A AND NEW 4EA NEW WASHERS P/N 140-009C16S48.
- [SDR 2025F00130](https://openairdocs.org/sdr/2025F00130.md): Drive Shaft · cracked · May 19, 2025 · N868JB · Bell 206B3 · Tail Rotor Drive Shaft
  > DURING 12 MONTH INSPECTION FOUND CRACKS RADIATING FROM WHERE THE RIVETS ARE INSTALLED ON EITHER END ON ONE OF THE SEGMENTED RIVETED DRIVE SHAFT ASSEMBLY. THIS WAS DETECTED WITH A 10X MAGNIFYING GLASS. THE OTHER SEGMENTED SHAFTS CHECKED OUT OK. PART WITH REPLAC
- [SDR 2022F00242](https://openairdocs.org/sdr/2022F00242.md): Freewheel Unit · failed · May 18, 2022 · N910BR · Bell 206B3 · Engine/Transmission Coupling
  > THE FREEWHEELING UNIT WAS FAILING CAUSING THE MAIN GEARBOX CHIP LIGHT TO INTERMITTENTLY ILLUMINATE. WHEN THE CHIP DETECTORS WERE INSPECTED THERE WAS NO METAL NOTED. NOTHING APPEARED IN THE OIL FILTER OR SCREEN DURING THE SERVICEABILITY CHECK.
- [SDR ULXR2020040200000](https://openairdocs.org/sdr/ULXR2020040200000.md): Throttle Cable · failed · Mar 31, 2020 · N306FD · Bell 206B3 · Power Lever
  > THROTTLE CABLE FAILED ON STARTUP CAUSING ENGINE OVER-TEMP.
- [SDR YH7R20190201001](https://openairdocs.org/sdr/YH7R20190201001.md): Drive Shaft · cracked · Feb 1, 2019 · N233HC · Bell 206B3 · Tail Rotor Drive Shaft
  > IN PERFORMING BEL HELICOPTER 100HR PERIODIC INSPECTION A CRACK WAS IDENTIFIED ON THE FORWARD SEGMENT OF THE TAIL ROTOR DRIVE SHAFT AT FLANGE. THE CRACK IS LOCATED AT THE AFT FLEX COUPLING MOUNTING FLANGE. THE CRACK TRAVELS LONGITUDINALLY ACROSS A SECURING RIVE
- [SDR 2017F00164](https://openairdocs.org/sdr/2017F00164.md): Attach Fitting · cracked · Sep 22, 2017 · N8052G · Bell 206B3 · Rotorcraft Tail Boom
  > DURING SCHEDULED AIR FRAME INSPECTION, DISCOVERED A CRACK IN THE UPPER LEFT HAND TAIL BOOM ATTACH FITTING. (AIR-FRAME SIDE OF TAIL BOOM.) PERFORMED DYE PENETRATE TEST THAT CONFIRMED CRACK LOCATION BETWEEN THE TWO AFT OUTBOARD RIVET LOCATIONS.
- [SDR 2017FA0000132](https://openairdocs.org/sdr/2017FA0000132.md): Frame · cracked · Mar 23, 2017 · N16203 · Bell 206B3 · Fuselage Main, Frame
  > THE LT BS 130 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 5.0 INCH FROM THE INBOARD FLANGE FREE EDGE AT LBL 67. THE FRAME WAS REPLACED.
- [SDR 2017FA0000124](https://openairdocs.org/sdr/2017FA0000124.md): Longeron · cracked · Mar 23, 2017 · N16202 · Bell 206B3 · Fuselage Main, Longeron/Stringer
  > THE LH UPPER AFT LONGERON WAS FOUND CRACKED. THE CRACK EXTENDED DOWNWARD FROM THE UPPER FLANGES FREE EDGE AT BS 130. THE LONGERON WAS REPLACED.
- [SDR 2017F00027](https://openairdocs.org/sdr/2017F00027.md): Blade · failed · Dec 4, 2016 · Bell 206B3 · Main Rotor Blades
  > DURING CLIMB 850 FEET, LATERAL VIBRATION CAME. LANDING PROCEDURES, AFTER VISUAL INSPECTION MAIN ROTOR BLADE TIP CAME OUT. AFTER DEEP INSPECTION AT HOME BASE, TELL-TALE WEIGHT SHEARED OFF INSIDE THE SPAR. CAUSING BLADE UNSERVICEABLE AFTER THIS EVENT.
- [SDR IAVA2016F00016](https://openairdocs.org/sdr/IAVA2016F00016.md): Compressor · defective · Oct 23, 2015 · N297CA · Bell 206B3 · Turbine Engine Compressor Section
  > INITIATED A NORMAL TAKEOFF TO THE SOUTH FROM TB-45. APPROXIMATELY 3-5 SECONDS AFTER INITIATION, A LOUD BANG WAS HEARD WITH ACCOMPANING AIRFRAME SHUTTER. ABORTED TAKE OFF. SECOND BANG AND SHUTTER FOLLOWED AS ACFT SETTLED TO THE GROUND.
- [SDR 2017FA0000130](https://openairdocs.org/sdr/2017FA0000130.md): Frame · cracked · Oct 16, 2015 · N16203 · Bell 206B3 · Fuselage Main, Frame
  > THE RT BS 130 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 5.0 INCHES FROM THE INBOARD FLANGE FREE EDGE AT RBL 67. THE FRAME WAS REPLACED.
- [SDR 2017FA0000123](https://openairdocs.org/sdr/2017FA0000123.md): Fitting · cracked · Oct 5, 2015 · N16267 · Bell 206B3 · Rotorcraft Tail Boom
  > THE LH UPPER AFT TAILBOOOM ATTACH FITTING WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OVER 75% OF THE OUTBOARD FLANGE THROUGH THE FIRST ROW OF FASTENERS. NAVAIR ENGINEERING ANALYZED THE DAMAGE AND DETERMINED THAT AT THIS CRACK LENGT
- [SDR 2017FA0000129](https://openairdocs.org/sdr/2017FA0000129.md): Longeron · cracked · Jul 17, 2015 · N16332 · Bell 206B3 · Fuselage Main, Longeron/Stringer
  > THE RT UPPER AFT LONGERON WAS FOUND CRACKED. THE CRACK EXTENDED DOWNWARD FROM THE UPPER FLANGES FREE EDGE BETWEEN BS 117 - 130. THE LONGERON WAS REPLACED.
- [SDR 2017FA0000128](https://openairdocs.org/sdr/2017FA0000128.md): Longeron · cracked · Jul 17, 2015 · N16280 · Bell 206B3 · Fuselage Main, Longeron/Stringer
  > THE LT UPPER AFT LONGERON WAS FOUND CRACKED. THE CRACK EXTENDED DOWNWARD FROM THE UPPER FLANGES FREE EDGE BETWEEN TS 117 - 130. THE LONGERON WAS REPLACED.
- [SDR 2017FA0000126](https://openairdocs.org/sdr/2017FA0000126.md): Longeron · cracked · Jul 17, 2015 · N16204 · Bell 206B3 · Fuselage Main, Longeron/Stringer
  > THE RT UPPER AFT LONGERON WAS FOUND CRACKED. THE LONGERON WAS REPLACED.
- [SDR 2017FA0000137](https://openairdocs.org/sdr/2017FA0000137.md): Frame · cracked · Jun 8, 2015 · N16281 · Bell 206B3 · Fuselage Main, Frame
  > THE RT BS 117 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 5.0 INCH FROM THE INBOARD FLANGE FREE EDGE AT RBL 67. THE FRAME WAS REPLACED.
- [SDR 2017FA0000125](https://openairdocs.org/sdr/2017FA0000125.md): Longeron · cracked · May 1, 2015 · N16204 · Bell 206B3 · Fuselage Main, Longeron/Stringer
  > THE LT UPPER AFT LONGERON WAS FOUND CRACKED. THE CRACK EXTENDED DOWNWARD FROM THE UPPER FLANGE’S FREE EDGE AT BS 130. THE LONGERON WAS REPLACED.
- [SDR 2017FA0000134](https://openairdocs.org/sdr/2017FA0000134.md): Frame · cracked · Apr 15, 2015 · N16206 · Bell 206B3 · Fuselage Main, Frame
  > THE LT BS 130 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 2.0 INCH FROM THE INBOARD FLANGE FREE EDGE AT LBL 67. THE FRAME WAS REPLACED.
- [SDR 2017FA0000133](https://openairdocs.org/sdr/2017FA0000133.md): Frame · cracked · Apr 15, 2015 · N16204 · Bell 206B3 · Fuselage Main, Frame
  > THE LT BS 130 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 2.0 INCH FROM THE INBOARD FLANGE FREE EDGE AT LBL 67. THE FRAME WAS REPLACED.
- [SDR 2017FA0000140](https://openairdocs.org/sdr/2017FA0000140.md): Frame · cracked · Apr 9, 2015 · N16332 · Bell 206B3 · Fuselage Main, Frame
  > THE RT BS 117 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 5.0 INCH FROM THE INBOARD FLANGE FREE EDGE AT RBL 67. THE FRAME WAS REPLACED.
- [SDR 2017FA0000139](https://openairdocs.org/sdr/2017FA0000139.md): Frame · cracked · Apr 9, 2015 · N16280 · Bell 206B3 · Fuselage Main, Frame
  > THE RT BS 117 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 5.0 INCH FROM THE INBOARD FLANGE FREE EDGE AT RBL 67. THE FRAME WAS REPLACED.
- [SDR 2017FA0000136](https://openairdocs.org/sdr/2017FA0000136.md): Frame · cracked · Feb 5, 2015 · N16204 · Bell 206B3 · Fuselage Main, Frame
  > THE RT BS 117 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 3.0 INCH FROM THE INBOARD FLANGE FREE EDGE AT RBL 67. THE FRAME WAS REPLACED.
- [SDR 2017FA0000135](https://openairdocs.org/sdr/2017FA0000135.md): Frame · cracked · Feb 5, 2015 · N16204 · Bell 206B3 · Fuselage Main, Frame
  > THE RT BS 117 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 1.5 INCH FROM THE INBOARD FLANGE FREE EDGE AT RBL 67. THE FRAME WAS REPLACED.
- [SDR 2017FA0000138](https://openairdocs.org/sdr/2017FA0000138.md): Frame · cracked · Jan 30, 2015 · N16280 · Bell 206B3 · Fuselage Main, Frame
  > THE RT BS 117 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 5.0 INCH FROM THE INBOARD FLANGE FREE EDGE AT RBL 67. THE FRAME WAS REPLACED.
- [SDR CA150204008](https://openairdocs.org/sdr/CA150204008.md): Line · failed · Jan 26, 2015 · Bell 206B3 · Hydraulic System, Main
  > (CAN) CURRENTLY DID A 300 HR/ANNUAL MPI. REMOVED THE AND CLEANED THE HYDRAULIC FILTER. THE TEST FLIGHT WAS COMPLETED AND NO ISSUES PICKED UP. THE FOLLOWING DAY THE OWNER OF THE MACHINE CAME TO COLLECT IT AND UPON STARTING, SPOOLED THE MACHINE UP TO FIND HE
- [SDR 2017FA0000131](https://openairdocs.org/sdr/2017FA0000131.md): Frame · cracked · Jan 8, 2015 · N16205 · Bell 206B3 · Fuselage Main, Frame
  > THE RT BS 130 FRAME WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OUTBOARD 5.0 INCH FROM THE INBOARD FLANGE FREE EDGE AT RBL 67. THE FRAME WAS REPLACED.
- [SDR FTYRN201410180001](https://openairdocs.org/sdr/FTYRN201410180001.md): Combustion Case · cracked · Oct 27, 2014 · N64JB · Bell 206B3 · Turbine Engine Combustion Section
  > NOTED A HIGH TOT INDICATION ON APPROACH TO LAND AT HOME STATION. VISUALLY INSPECTED AND FOUND CRACK IN OUTER COMBUSTION CASE ASSEMBLY.
- [SDR 2014FA0000598](https://openairdocs.org/sdr/2014FA0000598.md): Combustion Case · cracked · Sep 25, 2014 · N37WA · Bell 206B3 · Turbine Engine Combustion Section
  > PILOT STATED THE TOT HAS INCREASED 30+ DEGREES C FROM THE NORMAL CRUISE OPERATING TEMPERATURE. NO DEGRADATION IN POWER WAS MENTIONED OR NOTED. ON INSPECTION, FOUND A 2.75 INCH CRACK ON THE RT SIDE OF THE OUTER COMBUSTION CASE JUST BELOW THE SPLIT WELD LINE W
- [SDR CA130806006](https://openairdocs.org/sdr/CA130806006.md): Drive Shaft · overheated · Aug 2, 2013 · Bell 206B3 · Main Rotor Drive System
  > (CAN) FOUND BLACKENED, INDICATING OVER-HEAT, YELLOW AND RED TEMP-PLATES ON FWD COUPLING OF MAIN DRIVESHAFT DURING A "TURN-AROUND" CHECK. SHAFT REMOVED, INSPECTED, RE-GREASED, NEW TEMPLATES INSTALLED AND SHAFT RE-INSTALLED. COUPLING OVER-HEATED AGAIN AFTER 1.
- [SDR 2017FA0000122](https://openairdocs.org/sdr/2017FA0000122.md): Fitting · cracked · Jul 8, 2013 · N16202 · Bell 206B3 · Rotorcraft Tail Boom
  > THE LEFT UPPER AFT TAILBOOOM ATTACH FITTING WAS FOUND CRACKED DURING A PHASE VISUAL INSPECTION. THE CRACK EXTENDED OVER 75% OF THE OUTBOARD FLANGE THROUGH THE FIRST ROW OF FASTENERS. THE FITTING WAS REPLACED BEFORE THE ENTIRE FITTING FAILED. NAVAIR ENGINEERING
- [SDR CA130612005](https://openairdocs.org/sdr/CA130612005.md): Drive Shaft · cracked · Jun 4, 2013 · Bell 206B3 · Tail Rotor Drive Shaft
  > (CAN) TAIL ROTOR DRIVESHAFT FOUND CRACKED DURING ROUTINE INSPECTION. THIS ACFT HAS NO KNOWN INCIDENT OR ACCIDENT DAMAGE.
- [SDR 2013FA0000294](https://openairdocs.org/sdr/2013FA0000294.md): Engine · making metal · May 15, 2013 · Bell 206B3 · Engine (Turbine/Turboprop)
  > DURING FLIGHT, PILOT HEARD INCREASING "RUMBLING" NOISE. PILOT LANDED TO THE NEAREST LANDABLE SIDE APPROX 2 MIN AFTER THE NOISE STARTED. RUMBLING DECREASED SIMULTANEOUSLY WITH ENGINE LOAD. ENGINE CHIP CAUTION ILLUMINATED AT THE END. ENGINE HAS NOT BEEN RUN
- [SDR 2013FA0000668](https://openairdocs.org/sdr/2013FA0000668.md): Bearing · failed · May 3, 2013 · Bell 206B3 · Engine (Turbine/Turboprop)
  > ENGINE CHIP LIGHT, DURING FLIGHT, PILOT HEARD INCREASING "RUMBLING" NOISE. LANDED TO THE NEAREST LANDABLE SITE, APPROX 2 MIN AFTER THE NOISE STARTED. RUMBLING DECREASED SIMULTANEOUSLY WITH ENGINE LOAD. ENGINE CHIP CAUTION ILLUMINATED AT THE END. AFTER REMO
- [SDR 2013FA0000667](https://openairdocs.org/sdr/2013FA0000667.md): Bearing · failed · May 3, 2013 · Bell 206B3 · Engine (Turbine/Turboprop)
  > ENGINE CHIP LIGHT DURNG FLIGHT, PILOT HEARD INCREASING "RUMBLING" NOISE. LANDED TO THE NEAREST LANDABLE SITE, APPROXIMATELY TWO MINUTES AFTER THE NOISE STARTED. RUMBLING DECREASED SIMULTANEOUSLY WITH ENGINE LOAD. ENGINE CHIP CAUTION ILLUMINATED AT THE END.
- [SDR 2013FA0000708](https://openairdocs.org/sdr/2013FA0000708.md): Plate · misinstalled · Apr 17, 2013 · Bell 206B3 · Main Rotor Gearbox
  > FREEWHEEL ARRIVED TO OUR FACILITY FOR REPAIR DUE TO METAL PARTICLES ON FREEWHEEL AND ON TRANSMISSION OIL FILTER MAGNETIC PLUG. DURING DISASSEMBLY WE FOUND THAT PLATE, PN 206-040-204-001 WAS INSTALLED INCORRECT. AS STATED BHT-206-A/B/L-SERIES CR&O CHAP 63-55,
- [SDR 2013FA0000707](https://openairdocs.org/sdr/2013FA0000707.md): Nut · misinstalled · Apr 17, 2013 · Bell 206B3 · Main Rotor Gearbox
  > TRANSMISSION ARRIVED TO OUR FACILITY FOR REPAIR DUE TO METAL PARTICLES FOUND IN FREEWHEEL AND ON TRANSMISSION OIL FILTER MAGNETIC PLUG. DURING OUR INSPECTION, WE FOUND THAT NUT PN 206-040-045-001 WAS INSTALLED INCORRECT, THE RESULT OF THIS WAS 2 BROKEN TANGS
- [SDR 2013FA0000706](https://openairdocs.org/sdr/2013FA0000706.md): Bearing · misinstalled · Apr 17, 2013 · Bell 206B3 · Fuselage Miscellaneous Structure
  > TRANSMISSION, PN SN ARRIVED TO OUR FACILITY FOR REPAIR DUE TO METAL PARTICLES FOUND IN FREEWHEEL AND ON TRANSMISSION OIL FILTER MAGNETIC PLUG. DURING OUR INSPECTION, WE FOUND BEARING, PN 206-040-038-101, SN MB4486 INSTALLED INCORRECT. THE BEARING WAS INSTAL
- [SDR 2013FA0000553](https://openairdocs.org/sdr/2013FA0000553.md): Bulkhead · cracked · Jan 22, 2013 · Bell 206B3 · Rotorcraft Tail Boom
  > BULKHEAD CRACKED IN LT AFT GEARBOX ATTACHMENT HOLE. CRACKING FOUND VISUALLY DURING CORROSION INSPECTION.
- [SDR 2013FA0000552](https://openairdocs.org/sdr/2013FA0000552.md): Bulkhead · cracked · Dec 17, 2012 · Bell 206B3 · Rotorcraft Tail Boom
  > BULKHEAD CRACKED IN LT AFT GEARBOX ATTACHMENT HOLE. CRACKING WAS FOUND VISUALLY DURING CORROSION INSPECTION.
- [SDR CA121221010](https://openairdocs.org/sdr/CA121221010.md): Actuator · malfunctioned · Dec 15, 2012 · Bell 206B3 · Rotorcraft Flight Control
  > (CAN) PILOT NOTICED ON PREFLIGHT GROUND CHECK THAT HIS N2 DROOP COMPENSATOR, BEEP RANGE, WAS WRONG, 103-94 PERCENT N2, INSTEAD OF REQUIRED 101-96 PERCENT AND NOTIFIED MAINTENANCE STAFF. MAINTENANCE RESET, BEEP RANGE AND INSTRUCTED PILOT TO CHECK AGAIN UPON RU
- [SDR CA121115010](https://openairdocs.org/sdr/CA121115010.md): Mast · separated · Nov 12, 2012 · Bell 206B3 · Main Rotor Mast/Swashplate
  > (CAN) THE PILOT HAD JUST DEMONSTRATED A SUCCESSFUL AUTO-ROTATION FOR THE EXAMINER, WHEN SITTING ON THE GROUND AT IDLE, WHEN SUDDENLY THE HELICOPTER BEGUN TO VIBRATE. THE VIBRATION CEASED FOR 5 SECONDS, THEN CAME BACK STRONG, AT THIS TIME, THE ENGINE WAS IMMEDI
- [SDR CA120913006](https://openairdocs.org/sdr/CA120913006.md): Support · cracked · Aug 28, 2012 · Bell 206B3 · Tail Rotor Gearbox
  > (CAN) MFG HAS RECEIVED A REPORT CUSTOMER, TT: 9930 HRS, OF A REPORTED 1 PIECE T/R GEARBOX SUPPORT CRACKED. THE CRACK WAS NOTED FOLLOWING AN INSPECTION AFTER THE PILOT REPORTED VIBRATIONS IN FLIGHT. THE AREA HAD BEEN PREVIOUS INSPECTED 30 HOURS PRIOR DURING T
- [SDR 2012FA0000577](https://openairdocs.org/sdr/2012FA0000577.md): Stator Vane · failed · Aug 19, 2012 · N205PA · Bell 206B3 · Turbine Engine Compressor Section
  > WHILE IN FLIGHT, ENGINE LOST POWER WHICH RESULTED IN AUTO ROTATION ENDING IN HARD LANDING. FOUND THIRD STAGE EITHER STATOR OR 3RD STAGE WHEEL VANE FAILED CAUSING STAGES 4, 5, 6, 7 TO FAIL. THESE FAILURES FURTHER EXTENDED INTO COMBUSTION CAN AND TURBINE. ALL
- [SDR CA120829003](https://openairdocs.org/sdr/CA120829003.md): Skin · cracked · Jun 1, 2012 · Bell 206B3 · Rotorcraft Tail Boom
  > (CAN) DURING THE 300 HR AIRFRAME INSPECTION, A CRACK ON THE TAIL BOOM UPPER SKIN NEAR THE AREA WHERE THE T/R GEARBOX SUPPORT FRAME IS ATTACHED TO THE TAIL BOOM WAS FOUND. CRACK SEEMS TO HAVE STARTED FROM 1 OF THE T/R GEARBOX FAIRING ATTACHMENT ANCHOR NUT HOLE
- [SDR CA120614006](https://openairdocs.org/sdr/CA120614006.md): Nut · fractured · May 14, 2012 · Bell 206B3 · Tail Rotor Head
  > (CAN) WHILE UNDOING THE NUT AS PART OF MAINTENANCE, THE NUT FAILED INTO 2 HALVES. MINIMAL TORQUE WAS APPLIED. THERE IS EVIDENCE OF A PRE-EXISTING CRACK. THE NUT WAS REPLACED AND TORQUED TO MFG SPECIFICATIONS.
- [SDR CA111205015](https://openairdocs.org/sdr/CA111205015.md): Support · cracked · Nov 3, 2011 · Bell 206B3 · Tail Rotor Gearbox
  > (CAN) DURING FIELD INSPECTION OF AFT TAIL ROTOR GEAR BOX SUPPORT, THE LT BOLT ATTACH HOLE THROUGH CASTING WAS FOUND TO BE CRACKED. DURING REPAIR OF DAMAGED PART, 3 RIVETS IN LOCAL AREA WERE FOUND TO BE SHEARED, AND SEVERED. AFTER ASSESSING THE DAMAGED AREA, I
- [SDR 3HCR20110928001](https://openairdocs.org/sdr/3HCR20110928001.md): Bearing · missing · Sep 28, 2011 · N239RA · Bell 206B3 · Turbine Governor
  > REMOVED GOVERNOR FOR ENGINE SURGING. TESTED AS RECEIVED. FAILED TEST POINT 4.020-4.050. INSPECTED AND FOUND BEARING NOT INSTALLED ON CAM FOLLOWER LEVER.
- [SDR 2011FA0000743](https://openairdocs.org/sdr/2011FA0000743.md): Fitting · failed · Sep 23, 2011 · N204PA · Bell 206B3 · Tail Rotor Drive Shaft
  > AFTER SUSPECTED TAIL ROTOR STRIKE IN SNOW, TAIL ROTOR DRIVE SYS WAS VISUALLY INSPECTED. TAIL TO FREEWHEELING UNIT, NO DAMAGE NOTED. ACFT GROUND RUN AND NO DISCREPANCIES NOTED. ON ATTEMPTING TO HOVER ACFT TO A MORE LEVEL SPOT ON GLACIER, NR 3 TAILROTOR DRIVE
- [SDR YTRA20110827241](https://openairdocs.org/sdr/YTRA20110827241.md): Engine · flamed out · Aug 27, 2011 · N83AL · Bell 206B3 · Engine (Turbine/Turboprop)
  > IN CRUSIE FLIGHT, THE ENGINE FLAMED OUT. PROBABLE CAUSE WAS FUEL STARVATION.
- [SDR CA110615011](https://openairdocs.org/sdr/CA110615011.md): Bearing · loose · Jun 14, 2011 · Bell 206B3 · Main Rotor Gearbox
  > DRAG PIN BEARING CAME LOOSE IN THE SLEEVE.

Next page: https://openairdocs.org/model/bell-206b-3/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 = '206B3'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/bell-206b-3/reports

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