JASC 6200
Service difficulty reports · 168
Reports filed under 6200 · Main Rotor System, newest first.
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 jasc_code = '6200' 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.
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 jasc_code = '6200' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR M3XA20210322002Unknown · noisePILOT REPORTED IN CRUISE FLIGHT THE ROTOR NOISE CHANGED IN PITCH AND VOLUME SIGNIFICANTLY. MECHANIC PERFORMED VISUAL INSPECTIONS OF THE MAIN ROTOR SYSTEM, MAIN TRANSMISSION, BOTHE ENGINES AND THE TAIL ROTOR SYSTEM IAW EC135 AMM. NO DEFECTS NOTED. PILOT PERFSDR 8LFA20200423001Housing · crackedDURING INSPECTION, LAG DAMPER UPPER INBOARD ATTACHMENT HOUSING FOUND CRACKED ALL THE WAY THROUGH.SDR HDNA202002110018Angle · corrodedTHE LOWER ANGLE P.N. L533M1052318 FOR THE ATTACHMENT OF THE MAIN ROTOR CONTROL ROD CENTER POST CORRODED BEYOND SERVICEABLE LIMITS REQUIRING REPLACEMENT.SDR YV3R201912100221Tachometer · malfunctionedCUSTOMER REPORTED DUAL TACHOMETER P/N: C792-4 ENGINE RPM NEEDLE STICKS.SDR 2020FA0000049Rotor · crackedA CRACK INDICATION WAS INDICATED 7/16 INCHES LONG, 10 INCHES FROM UPPER END OF MAST. CRACK WAS FOUND WITH FLORESCENT MAGNETIC PARTICLE. INSPECTION WAS DONE PER TASK, AS REQUESTED BY CLIENT.SDR 2018FA0000394Bearing · backed outDURING INSTALLATION OF THE HELICAL LEVER THE BEARING PN 105-13142.03 BACKED OUT OF THE LEVER BORE HOLE. THE INSTALLATION REQUIRES THE BEARING TO BE FORCE PEENED. ON EXAMINATION OF THE BEARING IT APPEARS IT HAD NOT BEEN PEENED THERE ISN'T ANY EVIDENCE OF TOOL MSDR QMLA2018092718104Bolt · shearedMR DRIVE RING BOLT FOUND TO BE SHEARED DURING ANNUAL INSPECTION OF MR HEAD AND DRIVE SYSTEMSDR QR9R201808280001Pitch Link · crackedGREEN PITCH CHANGE LINK FOUND CRACKED IN TWO PLACES.. CRACKS WERE FOUND DURING A ROUTINE 12 MONTH INSPECTION.SDR O4VA002Absorber · deterioratedAFTER TAKEOFF PILOT FELT AN INCREASINGLY SIGNIFICANT VIBRATION AS AIRSPEED INCREASED. PILOT RETURNED TO BASE. AVA REPLACED ON AIRCRAFT WITH NO FURTHER DEFECTS NOTED.SDR 2016FA0000153Governor · inoperativeEPOXY CAME LOOSE FROM END OF DRIVE SHAFT. CLIP CAME LOOSE ALLOWING DRIVE SHAFT SPLINES TO WEAR AND CAUSE EXCESSIVE DROOPING DURING ENGINE POWER CHANGES.SDR CA151123007Scissor Link · scored(CAN) ON VISUAL DAILY INSPECTION THE COTTER PIN SAFETY DEVICE ON THE FASTENING BOLT/NUT FOR THE SCISSOR ASSEMBLY TO THE MAIN ROTOR MAST WAS FOUND SHEARED OFF ON THE TOP SIDE AND SEVERELY DEFORMED ON THE BOTTOM SIDE. UPON FURTHER INSPECTION THE SCISSOR ASSEMBLYSDR ALGA0916201590280Spring · defectiveTHE SPRINGS RECEIVED WERE MANUFACTURED APPROX 3/8 INCH TOO LONG, RESULTING IN DAMAGE TO THE PISTON FACE & CYLINDER INSIDE THE DAMPER.SDR CHIR201508242088Actuator · shortedON TEST PRIOR TO INSTALLATION IN ACFT, ACTUATOR DREW HIGH CURRENT IN FULL EXTEND WITH CHASSIS GROUNDED. FAILED BENCH TEST.SDR CA150814006Boot · torn(CAN) THIS DRIVE SHAFT WAS INSTALLED AS A REPLACEMENT FOR THE PREVIOUS DRIVE SHAFT THAT HAD A LEAKING BOOT. THERE WAS NO GREASE LEAKAGE AFTER THE MANDATORY GROUND RUN LEAK CHECK. THE ACFT HAD A 1.2 HR FERRY FLIGHT AND ON A POST FLIGHT INSPECTION THE ENGINEERSDR 2015FA0000209Strap · damagedA 1:1 VIBRATION WAS REPORTED BY PILOT AS AN ONGOING ISSUE. IN AN ATTEMPT TO ELIMINATE OTHER SYSTEMS SUCH AS SWASH PLATE, FLIGHT CONTROLS AND GEARBOXES, A COMPLETE INSPECTION WAS CONDUCTED BY DISCONNECTING ALL FLIGHT CONTROLS AND ISOLATING EACH SYSTEM INDIVIDSDR 9EKA2015040314Plate · tornDURING CRUISE FLIGHT , PILOT REPORTED UNUSUAL VIBRATIONS. DURING INSPECTION, NODAL BEAM PLATES & HELPER SPRING FOUND TO HAVE TORN ELASTOMERIC RUBBER.SDR CA150326007Bolt · mismanufactured(CAN) MISMANUFACTURED BLADE BOLT LOCK WIRE SAFETY LOCATION DRILLED IN WRONG LOCATION. RETURED TO VENDOR THE HOLE FOR THE LOCK WIRE SHOULD BE COMING OUT TO SIDE NOT DRILLED STRAIGHT THROUGH.SDR ALGA100820148431Spring · brokenBROKEN SPRING & INTERNAL DAMAGE.SDR ALGA2014081333292Bearing · wornCENTER BEARING & LINER WORN.SDR CA131223012Bracket · wrong part(CAN) STATIONARY SCISSORS ASSY, PN S6110-24035-002 DISASSEMBLED AND THE BRACKET APPEARS TO BE NON OEM. BRACKET, PN SHOULD BE S6110-24070-000. THERE ARE NO PN`S OR SN`S STAMPED ON THE UNIT, MACHINING AND ANODIZING COLOR DOES NOT APPEAR TO BE CONSISTENT WITH PROSDR CA130823009Bonding Strap · broken(CAN) DURING THE MORNING DAILY PREFLIGHT INSPECTION, THE AME DISCOVERED THE ELECTRICAL BONDING BRAID ON THE RED BLADE HAD BROKEN AT THE BLADE-END LUG. BONDING STRAP, PN 365A31-1937-00 WAS REPLACED AND ACFT RETURNED TO SERVICE.SDR EVCA201308120046Tube · crackedDURING ROUTINE 1200 HR INSPECTION, A CRACK WAS DETECTED ON THE PILOT'S CYCLIC CONTROL TUBE ASSY, BY BOLT HOLE.SDR CHIR201306250058Sprag Clutch · brokenON STARTUP, AFTER ADVANCING THE ENGINES TO FLIGHT IDLE, DISCOVERED THAT NR 2 ENGINE NF WAS HIGHER THAN NR AND NR 2 ENGINE TORQUE WAS CLOSE TO 0 PERCENT. WHEN NR 1 ENGINE WAS RETARDED TO GROUND IDLE, WITH NR 2 ENGINE STILL AT FLIGHT IDLE, NR DROPPED AND NR 2 ESDR ALGA050820137398Strap · deterioratedFOUND STRAP MATERIAL DETERIORATED AND WIRES EXPOSED ON STRAP.SDR CHIR201302261206Bevel Gear · crackedENGINE TRANSMISSION SPIRAL BEVEL GEAR WAS FOUND TO BE CRACKED ACROSS GEAR TOOTH, .2500" FROM THE HEEL.SDR QMLA2013022413029Unknown · unknownON APPROACH, THE TAILROTOR PEDALS KICKED HARD LT AND RT, YAW SAS TRIM ACTUATOR LIGHT ILLUMINATED FOR 3 SECONDS AND THEN EXTINGUISHED AND PEDALS RETURNED TO NORMAL. MX PERSONNEL PERFORMED CHECKS OF THE AUTO PILOT SYS, CLEANED CONNECTIONS AT THE YAW SEMA AND YSDR QMLA2013012613013Unknown · unknownPILOT REPORTED AFTER TAKEOFF, GOING THROUGH TRANSITIONAL LIFT, TRIM (YAW) TRIED TO MAKE NOSE YAW RIGHT, PILOT HAD TO EXCESSIVELY FIGHT TRIM. MECHANICS HAVE CHECKED THE TAIL ROTOR CONTROL SYS, INSPECTED AND CLEANED T/R BLADE GRIPS AND PERFORMED AUTOPILOT CHECKSDR CA120417007Seal · separated(CAN) PILOT WAS PERFORMING DAILY PRE-FLIGHT INSPECTION. HE FOUND GREASE LEAKAGE FROM THE FORWARD PART OF THE MAIN ROTOR DRIVE SHAFT AT THE TRANSMISSION COUPLING. THE GREASE LEAKED OUT OF THE SPLIT/SEPARATED SEAL/BOOT. THE INDICATOR HAS FLASHED OFF ON THE RESDR ALGA2012321000004Bearing · wornMAIN ROTOR DRIVE LINK BEARING WORN BEYOND LIMITS.SDR ALGA2012032100003Bearing · wornMAIN ROTOR DRIVE LINK BEARING WORN BEYOND LIMITS.SDR ALGA2012032100002Bearing · wornMAIN ROTOR DRIVE LINK BEARING WORN BEYOND LIMITS.SDR ALGA2012032100001Bearing · wornMAIN ROTOR DRIVE LINK BEARING WORN BEYOND LIMITS.SDR 2009F00057Isolator · leakingON THURSDAY 07/30/09 AT APPROX 0730 HRS TOOK OFF FOR AN INTER FACILITY TRANSFER. LANDED WITHOUT INCIDENT. TOOK OFF FOR RETURN AT APPROX 0822 HRS. CLIMB TO 8000 FT WENT FAIRLY SMOOTH AND WITHOUT INCIDENT. STARTED TO LEVEL OFF, HELICOPTER BEGAN TO SHAKE LATESDR 2008FA0000338Spring · damagedONE OF EIGHT SPRINGS BROKEN CAUSING DAMAGE TO LOWER HOUSING. LOWER HOUSING, SPRINGS 2 EA. AND PLUGS WERE REPLACED. UNKNOWN WHI SPRING BROKE, SPRING WAS FOUND BROKEN ON SCHEDULED 300 HOUR INSPECTION. (K)SDR AC2A119194Bolt · corrodedNEW BOLTS HAVE A PIT IN THE SHANK OFF THE BOLT.SDR AC2A119193Pin · debondedPIN DEBONDED.SDR AC2A118979Stop · crackedSTOP CRACKED IN RADIUS.SDR Y5CR200700003Sprag Clutch · brokenDURING A 300HR. INSPECTION ON THE O/R CLUTH THE CUSTOMER FOUND A BROKEN SPRAG CLIP ON THE SPRAG ASSY.SDR M7K2008F00138Cover · crackedTHIS PART WAS FOUND CRACKED DURING ROUTINE INSPECTION. THE CRACK ALWAYS OCCURS IN THE RADIUS OF THE LOWER IB CORNER FLANGE ALMOST ALL OF THESE SPRING COVERS WILL REQUIRE REPLACEMENT MULTIPLE TIMES WITHIN THE FIRST FEW THOUSAND FLIGHT HOURS OF THE AIRCRAFT. SDR CA071025001Spring · mismanufactured(CAN) POOR METAL COMPOSITION IN PART CAUSES CRACKING. THESE PARTS WILL CRACK WITHOUT BEING SUBJECT TO FLIGHT. ONE BATCH HAS BEEN DISPOSED OF AND THE NEXT BATCH HAS THE SAME ISSUE. THE MFG HAS BEEN NOTIFIED. REF MBB-BO-105 IPC 60-00-00 FIG 8 ITEM NR 440. (TC NRSDR M7K2008F00087Wire · damagedPILOT REPORTED NO LOW ROTOR RPM WARNING HORN (HEADSET BEEP) NR GAUGE INDICATIONS WAS NORMAL. SENSOR IS DUAL ELEMENT WITH ONE PORTION PROVIDING EACH SIGNAL FOR WARNING HORN AND NR INDICATION. INTERNAL WIRES ARE SO FINE THIS UNIT IS FAILURE PRONE, SUGGEST OPTISDR HEEA115422Connector · corrodedCONNECTOR CORRODED. SENT TO MFG FOR CREDIT.SDR UPX2007F00000Bearing · lack of lubeCLUTCH MAKING UNUSUAL NOISES ON COAST DOWN. UPON REMOVAL THE BEARINGS IN THE CLUTCH FELT ROUGH AND DRY. COMPONENT RETURNED TO MFG FOR O/H. (K)SDR YTRR114195Pitch Horn · corrodedDURING INSPECTION FOUND TUNGSTEN CARBIDE COATING ON INNER SURFACE DEBONDED AND CORRODED.SDR YTRR114194Pitch Horn · debondedDURING INSPECTION FOUND TUNGSTEN CARBIDE COATING ON INNER SURFACE DEBONDED AND CORRODED.SDR AC2A114169Restraint · wornWORN DUE TO SHEAR RESTRAINT BEING WORNSDR AC2A114168Restraint · wornWORN ELASTAMERSDR 2006FA0001088Adapter · damagedDURING INSPECTION AND REGREASE OF THE M/R TRANS DRIVE SHAFT, A CHECK OF THE TORQUE OF THE DRIVE SHAFT ADAPTOR BOLT WAS ACCOMPLISHED AND IT WAS DISCOVERED THAT THERE WAS NO TORQUE, THAT THE BREAKER BAR`S WEIGHT BROKE THE BOLT LOOSE, REMOVED THE ADAPTOR AND FOUNSDR 2006FA0001041Drive Belt · stretchedNEW DRIVE BELTS WERE INSTALLED, STRETCHED FOR 24 HOURS, AND RE-ADJUSTED IAW MM. THE AIRCRAFT WAS RETURNED TO SERVICE AND .5 HOUR INTO THE FIRST FLIGHT THE PILOT NOTICED THE MAIN ROTOR RPM DECAYING AND ENGINE RPM INCREASING. A STEEP DESCENT WITH POWER WAS PERSDR CA061005012Lever · damaged(CAN) LOAD COMPENSATOR ARM WAS FOUND TO HAVE ELONGATED ATTACHMENT HOLES. NEW LEVER INSTALLED. THE OLD LEVER HAS BEEN SENT TO MFG FOR EVALUATION AS TO WHAT MAY BE THE CAUSE OF THIS. SUSPECT EXCESSIVE FORCE APPLIED BY THE ACCUMULATOR. (TC NR 20061005012)
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