Bell 214B-1

Service difficulty reports · 18

Newest first. General aviation reporting is voluntary.

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 = '214B1'
  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 CA130715017Fcu · malfunctioned(CAN) PART WAS RECEIVED AS AN O/H UNIT AND INSTALLED. ABILITY TO MAINTAIN DESIRED RPM WITHIN LIMITS DEGRADED QUICKLY. FINAL TEST FLIGHTS HAD MINOR SURGING AND HUNTING NOTED. ON REMOVAL, NOTED FUEL LEAKS IN THE DRIVE SPLINE, 2 SEALS, WASHING OUT THE GREASE SJul 13, 2013 · Bell 214B1 · Fuel Control/Turbine EnginesSDR CA130610012Barrel · cracked(CAN) MAIN ROTOR ACTUATOR, SERVO, FOUND TO HAVE INCREASING LEAKAGE DURING DAILY INSPECTIONS OVER A PERIOD OF 3 OPS DAYS UNTIL IT WAS REMOVED FOR EXCESSIVE LEAKAGE. UNIT LATER SENT FOR REPAIR AND FOUND TO HAVE CRACKED BARREL, PN 41005043 THAT CAUSED THE LEAKAGEJul 20, 2011 · Bell 214B1 · Rotorcraft Servo SystemSDR CA100903013Turbine Nozzle · crackedDURING AN ENGINE "HOT-SECTION INSP" A SUBSTANTIAL CRACK WAS DISCOVERED IN THE 2ND TURBINE NOZZLE ASSY, THE CRACK IS LOCATED AT THE JOINT FORMED BY THE RING ASSY AND OUTER SHROUD. THIS CIRCUMFERENTIAL CRACK IS APPROX (6) INCHES IN LENGTH. FURTHER ANALYTICAL Apr 16, 2010 · Bell 214B1 · Turbine SectionSDR CA090430003Spindle · mismanufactured(CAN) ASB 214-08-70 NOW IN REVISION `C` RELATES TO IMPOSING A LIMIT LIFE ON SPINDLE ASSY 214-030-606-005. WHEN THE ORIGINAL ASB 214-08-70 CAME OUT. THE NEW MFG SPINDLES WHERE SUPPLIED AT THE SAME TIME. THE HOLE PATTERN WAS NOT CORRECT AND THE PIECE WOULD NOT FApr 17, 2009 · Bell 214B1 · Main Rotor HeadSDR CA081017006Horn · cracked(CAN) BOTH `EARS` (LT & RT) OF THE HORN TO WHICH THE ELEVATORS ATTACH CRACKED. COMMON PROBLEM WITH THESE HELICOPTERS. SENT A PREVIOUSLY CRACKED HORN TO BELL HELICOPTER FOR ENGINEERING ANALYSIS, BUT HAVE NOT HEARD ANY RESULTS YET.Sep 25, 2008 · Bell 214B1 · Rotorcraft Tail BoomSDR CA080404003Liner · sheared(CAN) DURING THE COURSE OF A 100 HR INSP, AME FOUND A LARGE AMOUNT OF NON-FERROUS METAL PARTICLES IN THE REDUCTION GEARBOX OIL FILTER AND THE OIL DRAINED FROM THE GEARBOX. CHIP PLUG WAS INSPECTED AND FOUND CLEAN. REDUCTION GEARBOX WAS REMOVED AND REPLACED WITHAug 7, 2007 · Bell 214B1 · Accessory GearboxesSDR CA060627003Spindle · broken(CAN) TRANSMISSION SPINDLE ASSY P/N 214-040-606-005 S/N A12-01304 BROKE IN HALF DURRING FLIGHT, AND THE PILOT HEARD A LOUD BANG AND BEGAN A EMERGENCY LANDING. APON SUCSESSFULL LANDING THE ENGINEER FOUND THE SPINDLE CRACKED IN HALF. DURRING THE SHORT TIME IN THJun 25, 2006 · Bell 214B1 · Main Rotor HeadSDR CA060317007Horn · crackedCRACK FOUND ON ELEVATOR HORN ASSY ON REGULAR INSPECTION. REMOVED FROM SERVICE AND REPLACED WITH NEW ASSEMBLY. PART HAS A RETIREMENT LIFE OF 2500 HOURS.Feb 13, 2006 · Bell 214B1 · Elevator StructureSDR CA060209004Horn · cracked(CAN) AFTER LANDING AND SHUTDOWN, DURING REGULAR INSPECTION, A CRACK WAS FOUND IN THE ELEVATOR HORN ASSY. PART WAS REMOVED AND REPLACED BEFORE FURTHER FLIGHT. (UNDER CODES F1 WAS USED HOWEVER FLIGHT CONTROLS WERE NOT AFFECTED, AS PILOT DID NOT NOTICE ANY CHANFeb 6, 2006 · Bell 214B1 · Elevator Miscellaneous StructureSDR CA041228002Housing · stripped(CAN) DURING REFUELING BETWEEN HELI-LOGGING CYCLES AME ON SITE ROUTINELY OPENS ENGINE COWLS FOR AN INSPECTION OF ENGINE COMPARTMENT AREA. HE NOTICED AFT ENGINE MOUNT ROD END (BELL PN 214-060-114-001) HAD COMPLETELY PULLED OUT OF ENGINE COMPRESSOR HALF CASTINGDec 5, 2004 · Bell 214B1 · Turbine Engine Compressor SectionSDR CA040531005Support · wornDURING AN INSPECTION CHECK ON THE SWASH PLATE THE FRICTION WAS NOTED AS VERY TIGHT. UPON DISASSEMBLY, IT WAS FOUND THAT ONE OF THE FOUR BEARINGS RIDING ON THE SUPPORT HAD LOST IT'S 'COATING' ENTIRELY. THE RESULTING METAL/METAL CONTACT WORE INTO THE SUPPORT, CDec 3, 2003 · Bell 214B1 · Main Rotor Mast/SwashplateSDR 2001FA0000437Cylinder · crackedSURFACE MATERIAL DEFECT/CRACKED.Aug 31, 2001 · Bell 214B1 · Hydraulic System, MainSDR 2001FA0000433Cylinder · crackedSURFACE MATERIAL DEFECT/CRACK.Aug 31, 2001 · Bell 214B1 · Hydraulic System, MainSDR CA010724008Liner · unserviceable(CAN) AFTER RECEIVING CHIP IND. FROM REDUCTION GEARBOX FILTER REMVD FOR INSP. OIL IN FILTER & BOWL FOUND TO BE BLACK WITH FERROUS MATERIAL PRESENT. REDUCTION GEARBOX THEN REMOVED & INIT INSP REVEALED THAT GEARBOX INPUT GEAR NUT P/N 214-040-236-001 HAD LOST TOJul 5, 2001 · Bell 214B1 · Turbine Engine Reduction GearSDR CA000925006Fuel Control · worn(CAN) PERIODIC ENGINE N2 DROOP WITH POWER APPLICATION WITH SLOW RECOVERY WAS REPORTED. DURING SUBSEQUENT TROUBLESHOOTING, N2 DROOPED WITH NO NR RECOVERY UNTIL COLLECTIVE WAS CYCLED SEVERAL TIMES. N2 LEVER ON FUEL CONTROL UNIT APPEARS TO BE ROUGH WHEN CYCLED Aug 9, 2000 · Bell 214B1 · Fuel Control/Turbine EnginesSDR CA000110005Spur Gear · broken(CAN) SPUR GEAR THAT DRIVES FCU FAILED. THIS WAS SPECIFIED TO BE A GEAR ALLIENMENT PROBLEM ORIGINATING AT MANUFACTURE. TSB NOTIFIED BY OPERATOR. BULLETIN EXPECTED TO FOLLOW FROM ALLIED TO HAVE RGB BORE ALIGNMENT CHECKED AT O/H.Sep 24, 1999 · Bell 214B1 · Turbine Engine Reduction GearSDR CA990513001Servo · defective(CAN) MAIN HYDRAULIC SERVO'S RETURNED FROM REPAIR FACILITY. MANY DEFECTS WERE NOTED WHICH AFFECT AIRWORTHINESS. SERVO'S REPAIRED AND RETURNED TO SERVICEABLE STATUS.Apr 28, 1999 · Bell 214B1 · Hydraulic System, MainSDR CA980402001Shim · misinstalled(CAN) TWENTY HOURS TIME SINCE OVERHAUL. SWASHPLATES FOUND WITH SHIM INSTALLED UNDER OUTER RING. THIS GAVE THE IMPRESSION OF PROPER SWASHPLATE FRICTION, BUT THE PINCH FIT OF THE BEARING BY THE RING WAS LOST. THIS ALLOWED THE BEARING TO FLOAT ON THE INNER RINMar 11, 1998 · Bell 214B1 · Main Rotor Mast/Swashplate
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