# Service difficulty reports: Bell 204-B

A list on [Bell 204-B](https://openairdocs.org/model/bell-204-b.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 2 · 77 reports

- [SDR QMLA2022081920055](https://openairdocs.org/sdr/QMLA2022081920055.md): None · none · Aug 15, 2022 · N529AM · Bell 204B · Auto Flight System
  > SUPPLEMENTAL INFO FOR SDR QMLA2022081920055 AC WAS EXPERIENCING UN-COMMANDED "ROLL" INPUTS WITH AP1 SHOWING "DEGRADED" AND AP2 NORMAL OPERATION. THE FLIGHT SYSTEMS PAGE SHOWED ROLL COMMAND INPUTS-UP SLIGHTLY AND THEN DOWN SLIGHTLY THAT CORRESPONDED WITH CYCLIC
- [SDR EVCA033022](https://openairdocs.org/sdr/EVCA033022.md): None · cracked · Mar 30, 2022 · N295AE · Bell 204B · Fuselage Structure (General)
  > THERE IS A SMALL CRACK, (1/4 INCH LONG), FORWARD LH SIDE THAT WE WILL STOP DRILL.
- [SDR CA190806009](https://openairdocs.org/sdr/CA190806009.md): Bolt · broken · Jul 31, 2019 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) DURING CRUISE FLIGHT THE PILOT HEARD "WHAT SOUNDED LIKE A SMALL BANG, A SOUND THAT IN THE PAST I HAD BEEN A METAL DRINK BOTTLE OR CELLPHONE DROPPING ONTO THE FLOOR." THE PILOT REDUCED POWER/AIRSPEED AND CHECKED THE GAUGES - NO VIBRATIONS OR ABNORMALITIES
- [SDR CA190705001](https://openairdocs.org/sdr/CA190705001.md): Fitting · cracked · Jul 2, 2019 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) DURING A SCHEDULED INSPECTION OF TAILBOOM ATTACHMENT FITTINGS THE UPPER L/H FITTING WAS SUSPECTED TO BE CRACKED. THE TAILBOOM AND COWLS WERE REMOVED FOR CLOSER INSPECTION. UPON CLOSER INSPECTION THE FITTING WAS FOUND TO BE CRACKED. TAILBOOM WAS REMOVED,
- [SDR CA150601014](https://openairdocs.org/sdr/CA150601014.md): Valve · broken · May 26, 2015 · Bell 204B · Hydraulic System, Main
  > (CAN) DURING FLIGHT TRAINING, TWO PILOTS WERE FLYING FOR A PPC. THE ACFT WAS JUST COMING OUT OF A TURN WHEN THE FLIGHT INSTRUCTOR SWITCHED THE HYDRAULICS OFF, AT THIS POINT THE CYCLIC IMMEDIATELY WENT HARD LT WITH BOTH PILOTS BEING UNABLE TO RESIST THE MOVEMEN
- [SDR CA150204016](https://openairdocs.org/sdr/CA150204016.md): Pin · cracked · Feb 4, 2015 · Bell 204B · Flight Compartment Equipment
  > (CAN) DURING A ROUTINE INSPECTION OF THE HEAD REST. THE ENGINEER NOTED THAT THE T HANDLE PORTION ON ON QUICK RELEASE PIN, PIP PIN, PN NAS1333A2S07D WAS CRACKED & THE HANDLE IS FREE TO MOVE APPROX 1MM ALONG THE AXIS OF THE PIN. THIS ASSEMBLY IS SUBJECT TO AD
- [SDR CA140708005](https://openairdocs.org/sdr/CA140708005.md): Doubler · cracked · Jun 27, 2014 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) CRACK WAS DISCOVERED DURING DAILY INSPECTION. THE CRACK WAS LOCATED IN THE TAIL BOOM DOUBLER BELOW THE 42" GEAR BOX WHERE IT IS NOTCHED TO ACCOMMODATE THE VERTICAL FIN SPAR. IT WAS APPROXIMATELY 1" IN LENGTH.
- [SDR CA130912007](https://openairdocs.org/sdr/CA130912007.md): Switch · failed · Aug 27, 2013 · Bell 204B · Rotorcraft Flight Control
  > (CAN) THE PILOT MADE A RADIO CALL AND THE SWITCH FAILED IN THE CLOSED, TRANSMIT, POSITION CAUSING THE VHF COM RADIO TO CONTINUOUSLY TRANSMIT. TURNED THE RADIO OFF AND RETURNED TO THE COMPANY BASE.
- [SDR CA130820004](https://openairdocs.org/sdr/CA130820004.md): Bolt · sheared · Aug 15, 2013 · Bell 204B · Tail Rotor Head
  > (CAN) DURING CRUISE FLIGHT, THE ACFT DEVELOPED A SUDDEN AND SEVERE VIBRATION. THE PILOT IMMEDIATELY LANDED AND SHUTDOWN. INSPECTION OF THE ACFT SHOWED THE INBD BOLT SECURING TAIL ROTOR PITCH LINK TO THE TAIL ROTOR GRIP HAD SHEARED AND THE TAIL ROTOR BLADES H
- [SDR CA130326007](https://openairdocs.org/sdr/CA130326007.md): Nut · damaged · Mar 26, 2013 · Bell 204B · Tail Rotor Drive Shaft
  > (CAN) DURING SCHEDULED MAINTENANCE OF TAIL ROTOR DRIVESHAFT, NEW BOLTS AND NUTS BEING INSTALLED, A NEW NUT WAS FOUND TO HAVE NO SELF LOCKING ABILITY ON ANY BOLT NEW OR OLD. SUSPECT MFG DEFECT.
- [SDR CA130212025](https://openairdocs.org/sdr/CA130212025.md): Fuel Cell · leaking · Feb 12, 2013 · Bell 204B · Fuel Storage
  > (CAN) FUEL CELL FOUND WEEPING FROM MULTIPLE LOCATIONS IN THE MIDDLE OF THE SIDES. ACFT FUEL RT FUEL CELL HAD A SLOW LEAK SO THE CELL WAS REMOVED AND INSPECTED. USING AIR THERE WAS NO APPARENT LEAK, BUT WHEN FILLED WITH WATER, THE SIDES OF THE CELL ARE FOUND T
- [SDR CA130212027](https://openairdocs.org/sdr/CA130212027.md): Gasket · blown · Aug 14, 2012 · Bell 204B · Main Rotor Gearbox
  > (CAN) WHILE IN CRUISE FLIGHT THE PILOT GOT AN INDICATION OF NO TRANSMISSION OIL PRESSURE ON THE WARNING LIGHT AND PRESSURE GAUGE. HE PROCEEDED TO LAND. WHEN HE ROLLED THE THROTTLE TO IDLE THE BLADE SLOWED QUICKER THEN NORMAL HE THEN SHUT THE ENGINE DOWN AND
- [SDR CA110727004](https://openairdocs.org/sdr/CA110727004.md): Bearing · failed · Jul 19, 2011 · Bell 204B · Main Rotor Mast/Swashplate
  > UPON ROUTINE INSP OF MAIN ROTOR TRANSMISSION ASSY INTERNAL WAFER FILTER, THE ON SITE AME DISCOVERED AN UNUSUALLY LARGE QUANTITY OF FERROUS METAL. FURTHER INVESTIGATION REVEALED METAL FOUND ON THE CHIP DETECTOR AND SUMP SCREEN OF THE TRANSMISSION. THE ACFT WA
- [SDR CA110516030](https://openairdocs.org/sdr/CA110516030.md): Panel · delaminated · May 16, 2011 · Bell 204B · Fuselage Miscellaneous Structure
  > DURING A VISUAL INSPECTION OF THE ACFT THE ENGINE DECK WAS FOUND TO BE DELAMINATED AND THE HONEYCOMB WAS FOUND TO BE SOFT IN THE ENTIRE PANEL. PANEL WAS REMOVED AND OVERHAULED.
- [SDR CA110516029](https://openairdocs.org/sdr/CA110516029.md): Panel · delaminated · May 16, 2011 · Bell 204B · Fuselage Main, Plate/Skin
  > DURING A VISUAL INSPECTION OF THE ABOVE NOTED ACFT THE CENTER ROOF SECTION WAS FOUND SEVERLY DELAMINATED. THE ROOF PANEL WAS REMOVED AND THE AREA FUTHER INSPECTED FOR DEFECTS. NONE NOTED.
- [SDR CA110204009](https://openairdocs.org/sdr/CA110204009.md): Volt Regulator · failed · Jan 31, 2011 · Bell 204B · DC Regulator
  > DURING CRUISE FLIGHT THE PILOT NOTICED THE AMMETER FLUCTUATE AND THE GENERATOR LIGHT FLICKER. THE PILOT BEGAN TO DESCEND WHEN THE GENERATOR LIGHT, LT BOOST PUMP LIGHT AND ROTOR RPM AUDIO ALL CAME ON AND THE COCKPIT BEGAN TO FILL WITH SMOKE. ALL UNNECESSARY SWI
- [SDR CA100607005](https://openairdocs.org/sdr/CA100607005.md): Bearing · rough · Jun 2, 2010 · Bell 204B · Engine Oil Cooler
  > NEW BEARING (PN P9103PPFS381A) PURCHASED FROM MFG, FOUND UNSERVICABLE, DUE TO LACK OF LUBRICATION AND ROUGH OPERATION. PART SCRAPPED AND WARRANTY RECEIVED FROM MFG. NOTE: THIS BEARING IS PART OF A BLOWER ASSY.
- [SDR CA100809003](https://openairdocs.org/sdr/CA100809003.md): Bearing · defective · May 29, 2010 · Bell 204B · Tail Rotor Head
  > DURING A FIRE MISSION, WITH THE BAMBI IN THE WATER GETTING FILLED ON A 100 FOOT LONG LINE, THE PILOT LOST AUTHORITY OF THE TAIL ROTOR CAUSING THE ACFT TO PERFORM 3 TO 4 TURNS CLOCKWISE. PILOT WAS ABLE TO GAIN CONTROL OF ACFT AND LAND SAFELY FOLLOWING PROCEDUR
- [SDR CA100809002](https://openairdocs.org/sdr/CA100809002.md): Balance Weight · separated · May 19, 2010 · Bell 204B · Engine Oil Cooler
  > ACFT WAS IN CRUISE FLIGHT WHEN THE TRANSMISSION OIL PRESSURE WARNING LIGHT ILLUMINATED. PILOT CARRIED OUT AN UNSCHEDULED LANDING. AT THE TIME OF ENG SHUTDOWN, THE TRANSMISSION WAS SHOWING OVER 20 PSI. THE ENGINEER ONBOARD INSPECTED THE OIL COOLER BLOWER COM
- [SDR CA090512011](https://openairdocs.org/sdr/CA090512011.md): Bulkhead · cracked · May 8, 2009 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) DURING A VISUAL INSP, A CRACK WAS FOUND AT THE BOTTOM OF THE RT ANGLE AT TAILBOOM TO FUSELAGE JUNCTION (PN 204-030-713-101). AFTER REMOVAL OF THE TAILBOOM AND SHIM PADS THE TAILBOOM ATTACHMENT BULKHEAD WAS FOUND CRACKED AT 3 OF THE 4 ATTACHMENT POINTS. (
- [SDR CA081208003](https://openairdocs.org/sdr/CA081208003.md): Cap · worn · Dec 6, 2008 · Bell 204B · Main Landing Gear
  > (CAN) PART FOUND TO HAVE UNAPPROVED MODIFICATION EMBODIED AFTER PART REMOVAL FROM THE AIRCRAFT WHEN COMPARED TO OEM PART. SUBSEQUENT INVESTIGATION BY QAM MANAGER OF ARCHIVED FILES REVEALED THAT 4 CAP ASSEMBLIES HAD UNDERGONE A PREVIOUS MODIFICATION BY A PROCE
- [SDR CA081017008](https://openairdocs.org/sdr/CA081017008.md): Longeron · cracked · Oct 3, 2008 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) DURING A VISUAL INSPECTION OF THE ACFT THE AME NOTICED A CRACK IN THE UPPER LT TAILBOOM LONGERON APROX. 3 INCHES AFT OF THE TAILBOOM ATTACHMENT FITTING. ACFT GROUNDED FOR REPAIRS.
- [SDR CA071010005](https://openairdocs.org/sdr/CA071010005.md): Blade · cracked · Aug 28, 2007 · Bell 204B · Main Rotor Blades
  > (CAN) ON TUESDAY THE 28TH OF AUGUST 2007, AT APPROX 19:00, LANDED AT THE STAGING AREA. THE PILOT COMMENTED THAT THERE WAS A VIOLENT LATERAL VIBRATION. AT THIS TIME THE TRANSMISSION WAS OBSERVED SHAKING EXCESSIVELY AND IT WAS DECIDED TO SHUT THE AIRCRAFT DOWN W
- [SDR CA070828004](https://openairdocs.org/sdr/CA070828004.md): Bearing · worn · Aug 21, 2007 · Bell 204B · Tail Rotor Head
  > (CAN) PILOT WAS FLYING HELICOPTER AND FELT TWO SLIGHT YAWS TO THE RT APPROXIMATELY 30 TO 40 SECONDS APART. AT FIRST THE PILOT SUSPECTED IT MIGHT HAVE BEEN A GUST OF WIND, BUT THE SECOND YAW ALERTED THE PILOT TO A PROBLEM WITH THE TAIL ROTOR AS IT WAS ACCOMPANI
- [SDR CA070506001](https://openairdocs.org/sdr/CA070506001.md): Nut · damaged · Apr 23, 2007 · Bell 204B · Tail Rotor Drive Shaft
  > (CAN) ON APRIL 23, 2007 DURING A TEST FLIGHT FOR MAINTENANCE THAT WAS PERFORMED, THE PILOT EXPERIENCED AN UNCONTROLLED YAW TO THE RIGHT WHILE IN A 4 FOOT HOVER. THE HELICOPTER WAS IMMEDIATELY SET DOWN ON THE TARMAC. THERE APPEARED TO BE A STEP WORN IN THE IN
- [SDR CA070122011](https://openairdocs.org/sdr/CA070122011.md): Collective Stick · ratcheting · Jan 22, 2007 · Bell 204B · Main Rotor Control
  > (CAN) PILOT COMPLAINED OF RATCHETING FEEL TO COLLECTIVE CONTROL STICK. AIRCRAFT RETURNED TO BASE. INSPECTION REVEALED THAT THE COLLECTIVE FRICTION SURFACE ROLL PIN WAS WORKING INTERNALLY AND CAUSING THE RATCHETING FEEL. ELBOW WAS REPLACED. (TC NR 2007012201
- [SDR CA060818004](https://openairdocs.org/sdr/CA060818004.md): Bolt · loose · Aug 14, 2006 · Bell 204B · Tail Rotor Control System
  > (CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTED A LARGE AMOUNT OF PLAY IN THE CLEVIS OF THE TAIL ROTOR FLIGHT CONTROL ROD. INVESTIGATION REVEALED AN UNDERSIZED BOLT, IE SMALLER DIAMETER, WAS INSTALLED. THE CORREECT BOLT, P/N AN175-20 WAS INSTALLED AN
- [SDR CA060605010](https://openairdocs.org/sdr/CA060605010.md): Transmission · making metal · May 13, 2006 · Bell 204B · Main Rotor Gearbox
  > (CAN) METAL PARTICLES FOUND IN TRANSMISSION INTERNAL FILTER AFTER ROUTINE INSPECTION. NO CHIP LIGHT INDICATION. OIL DRAINED WITH NEW FILTER INSTALLED, AIRCRAFT RUN FOR ONE HOUR ON GROUND WITH METAL PARTICLES FOUND IN INTERNAL AND INLINE FILTER ASSY. NO CHIP
- [SDR CA050715002](https://openairdocs.org/sdr/CA050715002.md): Turnbuckle · unsecure · Jul 10, 2005 · Bell 204B · Tail Rotor Head
  > LOCKWIRE LEFT UNLOCKWIRED RESULTING IN TURNBARREL BECOMING UNDONE RESULTING IN TAILROTOR PITCH CHANGE FAILURE. SPEED RIGS WERE LOCK WIRED ON THE ONE END BUT THE ENGINEER DIDN'T RECOGNIZE THE OTHER END REQUIRED LOCKWIRE.
- [SDR CA050418007](https://openairdocs.org/sdr/CA050418007.md): Relay · defective · Apr 11, 2005 · Bell 204B · DC Generating System
  > ON SHUTDOWN ENGINE CONTINUED TO MOTOR OVER SLOWLY. CONTACTS STUCK. RCR REPLACED AND PROBLEM SOLVED.
- [SDR CA050418008](https://openairdocs.org/sdr/CA050418008.md): Nut · cracked · Apr 8, 2005 · Bell 204B · Engine Controls
  > UPON INSP NOTICED CRACKED JAN NUT ON LINEAR ACTUATOR.
- [SDR CA050418006](https://openairdocs.org/sdr/CA050418006.md): Housing · worn · Apr 4, 2005 · Bell 204B · Tail Rotor Head
  > (CAN) DURING INSPECTION THE TAIL ROTOR CONTROL WAS REMOVED AND INSPECTED FOR WEAR. WEAR WAS FOUND BEYOND LIMITS IN THE HOUSING. THIS ITEM IS A 1000 HOUR OVERHAUL INTERVAL.
- [SDR CA050427008](https://openairdocs.org/sdr/CA050427008.md): Blade · damaged · Apr 1, 2005 · Bell 204B · Main Rotor Blades
  > VOID, CHORDWISE STATION 155 TO 157, HALF INCH WIDE THREE INCHES LONG. BELL HELICOPTER VERDICT THAT BLADE STILL SERVICEABLE. BHT ALLOWS VOID IN THIS AREA. 6 INCHES SPANWISE BY THE FULL CHORDWISE WIDTH OF CORE. BLADE RETURNED TO SERVICE. WILL CONTINUE TO MO
- [SDR CA040901005](https://openairdocs.org/sdr/CA040901005.md): Volt Regulator · failed · Jul 18, 2004 · Bell 204B · AC Regulator
  > (CAN) VOLTAGE REGULATOR DELIVERING OVER 30 VOLTS. THE AIRCRAFT WAS READY TO TAKE OFF WHEN THE PILOT SMELLED A STRONG ODOR IN THE COCKPIT. ASSUMING IT WAS THE BATTERY, HE SHUT DOWN THE ENGINE. IN THE INSPECTION THE BATTERY WAS FOUND TOO HOT AND THE VOLTAGE DELI
- [SDR CA040901003](https://openairdocs.org/sdr/CA040901003.md): Blade · cracked · Jul 4, 2004 · Bell 204B · Main Rotor Blades
  > (CAN) MAIN ROTOR BLADE FOUND CRACKED ON THE TOP SURFACE 90 INCHES FROM THE TIP. ABOUT 70 HOURS BEFORE, A CRACK ON THE BLADE PAINT WAS FOUND, AT THAT TIME NO CRACK WAS FOUND IN THE BLADE SKIN. IAW ASB204-49-96 PT I AND II, THE BLADE WAS INSPECTED DAILY (PART I
- [SDR CA040209012](https://openairdocs.org/sdr/CA040209012.md): Shaft · worn · Jan 27, 2004 · Bell 204B · Fuel Control/Turbine Engines
  > (CAN) FUEL CONTROL RECEIVED FROM CUSTOMER FOR INSPECTION FOLLOWING PREVIOUS RECORDS ABOUT PUMP FAILURE (WSDR 20040128006). FUEL CONTROL HAS TSO- 3195.3 AND WAS OPERATING ON EXTENSION TIME DUE TO A GOOD PERFORMANCES. IT WAS REMOVED FROM A/C FOR INSPECTION IAW
- [SDR CA040203011](https://openairdocs.org/sdr/CA040203011.md): Shaft · worn · Jan 27, 2004 · Bell 204B · Fuel Control/Reciprocating Engines
  > (CAN) UPON SUSPECTING A PROBLEM WITH FUEL CONTROL UNIT. REMOVED FCU FROM THE ENGINE TO INSPECT THE SPLINES IAW MFG SBT5313-107. FOUND THE INTERNAL SPLINES KNIFE EDGED AND VERY CLOSE TO TOTAL FAILURE OF THE FCU. THIS WOULD HAVE LEAD TO THE FAILURE AND SHUTDOWN
- [SDR CA030923010](https://openairdocs.org/sdr/CA030923010.md): Yoke · cracked · Sep 12, 2003 · Bell 204B · Tail Rotor Head
  > (CAN) TAIL ROTOR HUB ASSY WAS SENT FOR OVERHAUL. YOKE WAS SENT FOR NDT AS PART OF O/H AND WAS FOUND TO BE CRACKED.
- [SDR CA040301002](https://openairdocs.org/sdr/CA040301002.md): Compressor · failed · Aug 17, 2003 · Bell 204B · Turbine Engine Compressor Section
  > (CAN) THE AIRCRAFT DEPARTED A STAGING AREA, SHORTLY AFTER TAKEOFF, THE AIRCRAFT HAD AN ENGINE FAILURE AND CRASHED IN TALL TREES. THE PILOT WAS THE ONLY OCCUPANT AND WAS KILLED ON IMPACT. THE ENGINE WAS RECEIVED FROM OVERHAUL AND INSTALLED 18 HOURS PRIOR TO THE
- [SDR CA030610011](https://openairdocs.org/sdr/CA030610011.md): Spar · cracked · Jun 7, 2003 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) ENGINEER OPENED TAIL ROTOR DRIVESHAFT COVER TO CHANGE COUPLINGS AND FOUND A CRACK HAD DEVELOPED IN THE VERTICAL FIN SPAR. STARTING AT THE TOP LIGHTENING HOLE AND GOING LT TO THE OUTER EDGE OF THE SPARE. OUTER LT SKIN WAS ALSO CRACKED APPROX. SIX INCHES.
- [SDR CA030317016](https://openairdocs.org/sdr/CA030317016.md): Nut · cracked · Mar 14, 2003 · Bell 204B · Tail Rotor Head
  > (CAN) ON VISUAL INSPECTION NUT WAS FOUND TO BE CRACKED AT WORM GEAR THREAD. THESE PARTS HAVE A 1000 HR NDT INSPECTION. THIS COMPANY INCLUDE A 300 HR VISUAL THIS WAS FOUND DURING THE VISUAL.
- [SDR CA030421005](https://openairdocs.org/sdr/CA030421005.md): Longeron · cracked · Jan 31, 2003 · Bell 204B · Fuselage Main, Longeron/Stringer
  > (CAN) MODIFICATION OF THE DOOR ASSEMBLY WAS COMPLETED PRIOR IAW BHT. TB204-79-11. THE CRACKED PIECES WERE REPLACED WITH NEW PIECES AND REINSTALLED IAW TB 204-79-11.
- [SDR CA030421004](https://openairdocs.org/sdr/CA030421004.md): Longeron · cracked · Jan 31, 2003 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) UPPER LT ATTACH LONGERON CRACKED AFT OF HOT BONDED DOUBLER. CRACK APPEARS TO HAVE STARTED AT A RIVET HOLE. THE CRACK WAS DISCOVERED DURING A ENGINE REMOVAL WHERE THE AFT ENGINE COWL WAS REMOVED EXPOSING THE LONGERON. THE CRACK MEASURES APPROX 3 INCHES
- [SDR CA021105012](https://openairdocs.org/sdr/CA021105012.md): Bellcrank · cracked · Nov 4, 2002 · Bell 204B · Main Rotor Control
  > (CAN) AT 1000 HR INSPECTION BELLCRANK FOR THE CYCLIC WAS REMOVED FOT GREASING OF THE BEARINGS. BELLCRANK WAS FOUND TO BE CRACKED AT ONE BEARING. CRACK WAS COMPLETELY THROUGH TO THE OUTER RACE OF THE BEARING. BELLCRANK WAS REPLACED WITH A SERVICEABLE ONE.ALL OT
- [SDR CA021003007](https://openairdocs.org/sdr/CA021003007.md): Hose · leaking · Sep 13, 2002 · Bell 204B · Hydraulic System, Main
  > (CAN) HOSE ASSEMBLY FAILED RESULTING IN LOSS OF HYDRAULIC FLUID. THE LOSS OF FLUID RESULTED IN LOSS OF HYDRAULIC BOOST TO FLIGHT CONTROLS. AIRCRAFT WAS LANDED UNEVENTFULLY WITHOUT HYDRAULIC BOOST. THE HYDRAULIC LINE EXHIBITED NO SIGNS OF LEAKAGE PRIOR TO FAILU
- [SDR CA020918006](https://openairdocs.org/sdr/CA020918006.md): Bulkhead · cracked · Sep 6, 2002 · Bell 204B · Fuselage Main, Bulkhead
  > (CAN) THE ROTOR CONTROL BELLCRANK BULKEAD CRACKED IN MULTIPLE PLACES.
- [SDR CA020918010](https://openairdocs.org/sdr/CA020918010.md): Bulkhead · cracked · Sep 2, 2002 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) T/R FLIGHT CONTROL BELLCRANK SUPPORT ATTACHES TO BULKHEAD. THE BULKHEAD IS REINFORCED BY LOWER ANGLE AND UPPER ANGLE, SUSPECT THAT THE LOWER ANGLE CRACKED PROBABLY DUE TO CORROSION (NOT VERIFIED). THIS ALLOWED THE SUPPORT TO MOVE AND EVENTUALLY CRACKED
- [SDR CA011109007](https://openairdocs.org/sdr/CA011109007.md): Segment · missing · Oct 24, 2001 · Bell 204B · Tail Rotor Gearbox
  > (CAN) UPON INSTALLATION OF THE NEW CHAIN, THE ENGINEER NOTICED A SPACE BETWEEN SOME CHAIN LINKS. CHAIN IS MISSING A SEGMENT.
- [SDR CA010625047](https://openairdocs.org/sdr/CA010625047.md): Skin · cracked · May 25, 2001 · Bell 204B · Rotorcraft Tail Boom
  > (CAN) CRACK IN SKIN DUE TO BROKEN STIFFENER INSIDE FIN. APPROX LOCATION IS FSTA 444.75, WATERINE 85 RIGHT BUTTLINE 3.0. STIFFENER P/N 205-030-899-036 ALSO RIB P/N 204-030-827-015 WAS DAMAGED BY BROKEN STIFFENER.
- [SDR CA000906003](https://openairdocs.org/sdr/CA000906003.md): Servo · failed · Aug 16, 2000 · Bell 204B · Rotorcraft Servo System
  > (CAN) THE PILOT FELT A FEEDBACK IN THE CYCLIC STICK IN THE FORWARD RIGHT HAND QUADRANT. THIS FEEDBACK WAS NOT SATISFACTORY TO THE AIRCRAFT TYPE. THE RIGHT HAND SERVO WAS REMOVED AND EXCHANGED WITH THE LEFT HAND CYCLIC SERVO. THE SUSPECT SERVO NOW IN THE LEF

Next page: https://openairdocs.org/model/bell-204-b/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 = '204B'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/bell-204-b/reports

---
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