Bell 206B-3

Service difficulty reports · 708

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 = '206B3'
  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 95ZZZX1327Bearing · misinstalledUPON INSPECTION OF M/R MAST BEARING DUE TO METAL CONTAMINATION, IT WAS DISCOVERED THE BEARING HAD BEEN INSTALLED UPSIDE DOWN AND THE INNER RACE WAS DAMAGED BEYOND LIMITS. BELL INSTRUCTIONS ARE SPECIFIC ON THE ORIENTATION OF THE BEARING ON INSTALLATION.Mar 3, 1995 · N5743H · Bell 206B3 · Main Rotor Mast/SwashplateSDR HEEA954466Tub · mis mfgREMOVED SHELL ASSY FROM CRATE. FOUND AREA NEAR R/H NAV. LIGHT HOLE, ON INSIDE SKIN HAVING A GOUGE (HOLE) IN SKIN, WHICH WAS FILLED WITH ADHESIVE AND ADDED INSERT. FOUND INSIDE SKIN POLISHED DUE TO EXCESSIVE SEALANT DROPPINGS, CAUSING PROTECTIVE COATING TO BEMar 1, 1995 · N2268W · Bell 206B3 · Fuselage Main, StructureSDR HEEA954378Shaft · defectiveTEMP-PLATE PEELING OFF. REPLACED INPUT DRIVE SHAFT.Feb 15, 1995 · N2268V · Bell 206B3 · Engine/Transmission CouplingSDR HEEA954304Gearshaft · stepwearENGINE REMOVED DUE TO COMPRESSOR OVERHAUL AND TURBINE 1750 HOUR INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEARSHAFT. AFA# 17920AFeb 6, 1995 · N22751 · Bell 206B3 · Turbine Engine Compressor SectionSDR HEEA954300Washer · deterioratedEXCESSIVE LOAD ON PLUGS CAUSING MATERIAL TO DETERIORATE. PARTS SCRAPPED LOCALLY. APPLIED TORQUE ON ADJUSTING SCREWS AND LOWERED PRELOAD ON THRUST PLUGS.Feb 1, 1995 · N2268W · Bell 206B3 · Main Rotor HeadSDR 95ZZZX2153Frame · crackedTHE FRAME WAS FOUND CRACKED IN THE RADIUS AFT OF THE FORWARD RIGHT ENGINE MOUNT. THE CRACK EXTENDED 1.5 INCHES OUTBOARD AND 3 INCHES INBOARD OF THE MOUNT BOLT HOLE AND FORWARD 2.5 INCHES AT THE OUTBOARD END. THE STIFFENERS AT BOTH FORWARD ENGINE MOUNTS WERE Jan 30, 1995 · N35Q · Bell 206B3 · Fuselage Main, FrameSDR HEEA954276Bearing · crackedCRACKED OUTBOARD BEARINGS. ALSO REPLACED TWO EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/R HUB S/N AFS-5985, T.T. 1582:35. SCRAPPED BEARINGS AND SLEEVES LOCALLY.Jan 20, 1995 · N2268W · Bell 206B3 · Tail Rotor BladesSDR HEEA954275Bearing · crackedCRACKED INBOARD BEARINGS. ALSO REPLACED TWO EACH SLEEVES P/N 206-010-733-003. REMOVED FROM T/R HUB S/N AFS-5985, T.T. 1582:35. SCRAPPED BEARINGS AND SLEEVES LOCALLY. BLADE S/N CS3073 & CS3064Jan 20, 1995 · N2268W · Bell 206B3 · Tail Rotor Blades
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