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 PN1R202603200003Torque Link · corrodedDURING INSPECTION, FOUND WHITE AND BLUE M/R TENSION LINK BUSHINGS FRETTED OUT OF PERMISSIBLE LIMITS. LIMIT: 39.040MM - WHITE: 39.050, BLUE: 39.050. S/N'S MC-10-0810 AND MCL1636SDR PN1R202603200002Torque Link · crackedDURING INSPECTION, FOUND RED MAIN ROTOR TENSION LINK CRACKED. S/N MCL1771SDR PN1R202603200001Torque Link · crackedDURING INSPECTION FOUND RED, WHITE, YELLOW, AND BLACK MAIN ROTOR TENSION LINKS CRACKED. YELLOW S/N MCL1501, BLACK S/N MCL1535, WHITE S/N MCL1595, & RED S/N MCL1534.SDR PN1R202603190001Link · crackedDURING INSPECTION FOUND WHITE, YELLOW, AND BLACK MAIN ROTOR TENSION LINKS CRACKED.SDR QMLA012920007Unknown · vibrationACFT LAUNCHED FROM BASE, 13 MIN FLT WAS UNEVENTFUL, GW WAS 2754 & POWER WAS NORMAL. WHEN LIFTING FROM LOW ROOFTOP PAD, ACFT REQUIRED MORE TORQUE THAN EXPECTED TO HOGE, ASSUMPTION WAS HIGHER THAN EXPECTED WEIGHT BUT POST FLT DETAILED ANALYSIS: GW WAS 2778, OATSDR QMLA2025062120068Sensor · failedLOSS OF NR INDICATION ONE CLIMB OUT. REMOVED NR SPEED SENSOR AND REPLACED WITH NEW AS PER AIRBUS AS350B3 AMM 62-31-00, 4-3 .CLEANED AND APPLIED STABILANT 22 TO MGB HARNESS CANON PLUG. GROUND RAN AIRCRAFT. OPS CHECK GOOD.SDR QMLA2025032820043Absorber · leakingMRB VIBE ABSORBERS LEAKING.SDR QMLA2024122320151Monitor · faultedWHILE TRANSITIONING FROM CRUISE INTO HIGH RECON & STARTING A DESCENT FOR A HOSPITAL HELIPAD, LOW ROTOR SYSTEM ACTIVATED. AS IS MY PRACTICE, ALREADY HOLDING THE INCR/DCR SWITCH TO RAISE ROTOR SPEED IF SOMETHING LIKE THIS SHOULD HAPPEN HOWEVER THERE WAS NO RISE SDR EVCA202406240002Blade · crackedM/R BLADE INBOARD TRIM TABS CRACKEDSDR QMLA2024060720059Tube · interferenceCONTROL INTERFERENCE. CYCLIC DISPLACES IN LATERAL AXIS WHEN COLECTIVE IS MOVED. PILOT WAS MOVING THE AIRCRAFT FROM THE GRASS NEXT TO THE HELIPAD TO HELIPAD. WHILE PICKING THE AIRCRAFT UP INTO A HOVER HE NOTED THAT WHILE PULLING COLLECTIVE THE CYCLIC WAS MOVINSDR QR9R2024040900004Bolt · failed inspDURING 800 HR INSPECTION, DETECTED CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024040900003Bolt · failed inspDURING 800 HR INSPECTION, DETECTED CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024040900002Bolt · failed inspDURING 800 HR INSPECTION, DETECTED CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024040900001Bolt · failed inspDURING 800 HR INSPECTION, DETECTED CRACKS IN BOLT USING NDI METHOD.SDR M3XA20240329004Rotor · unknownPILOT REPORTED A BIRD STRIKE TO THE ROTOR SYSTEM.SDR QR9R2024031500001Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024031400002Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024031400001Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400010Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400009Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400008Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400007Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400006Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400005Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400004Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400003Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400002Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR QR9R2024030400001Bolt · crackedDURING 800 HR INSPECTION, FOUND CRACKS IN BOLT USING NDI METHOD.SDR 2024FA0000139Damper · crackedAFTER THE SECOND GROUND TURN ON A/C 61703 FEBRUARY 06, 2024 THE DAMPER LISTED ABOVE CRACKED AT THE INBOARD SIDE OF THE DAMPER HOUSING. THE AIRCRAFT PERFORMED ONE GROUND TURN PRIOR TO THIS DAY. WE REMOVED THE DAMPER AND PERFORMED A DISASSEMBLY TO ACCESS WHAT CSDR 2023FA0000811Bushing · scoredDURING INSPECTION FOUND WHITE TENSION LINK FLANGE BUSHING BORE SCORED.SDR 2023FA0000808Ring · gougedDURING INSPECTION, FOUND GOUGES ON THE DISTANCE RINGS OF ALL (4EA) MAIN ROTOR BLADE VIBRATION ABSORBER ASSEMBLIES.SDR EVCA20231027001Blade · crackedVAN HORN M/R BLADE INBOARD TRIM TABS CRACKED.SDR 2023FA0000506Spindle · brinelledSPINDLE BEARINGS FOUND TO BE BRINELLING AFTER 130 HOURS OF FLIGHT WITH NO REPORTED OVERSPEED. THIS IS THE SECOND TIME THIS HAS HAPPENED TO THIS HELICOPTER WITH IN THE SPAN OF 3 MONTHS. WITH THE BLADES REMOVED FROM THE HELICOPTER YOU CAN TURN THE SPINDLE AND HASDR EVCA2023083020Blade · unknownDISCOVERED PERPENDICULAR CRACK 104 INCHES FROM TIP CAP STARTING AT TRAILING EDGE RUNNING UP TO SPAR ON BELL MAIN ROTOR BLADE P/N 206-015-001-119 S/N VL00249530SDR 2023FA0000426Bolt · groovedIT WAS REPORTED AS THE AIRCRAFT WAS COMING IN FOR A 200-HOUR INSPECTION. A SLIGHT BUMP COULD BE FELT IN FLIGHT; DURING THE INSPECTION, ALL PC LINK ROD ENDS, AND BOLTS WERE INSPECTED, AND THE BLUE UPPER BOLT WAS FOUND TO HAVE A STEP WORN INTO IT, THE BOLT WAS RSDR 2023F00178Servo · brokenTHERE WAS A CATASTROPHIC FAILURE OF THE LEFT HAND MAIN ROTOR SYSTEM CAUSING THE AIRCRAFT TO CRASH. A SERVO FLAP BROKE OFF WHILE THE PILOT WAS LIFTING AN EXTERNAL LOAD CAUSING THE LEFT WHITE BLADE TO MAKE CONTACT WITH THE RIGHT ROTOR HEAD THAT LEAD ROTOR SYSTEMSDR EVCA03102023Blade · unserviceableMR BLADE TRIM TAB CTRACKEDSDR 2022FA0000413Bearing · brinelledPILOT REPORTED ABNORMAL AND HEAVY CYCLIC FORCES DURING AUTOROTATION AND LOW POWER DESCENTS. FOUND BOTH MR SPINDLES TO BE BRINELLED. REMOVED SPINDLE ASSEMBLIES AND PERFORMED MR SPINDLE BEARING REPLACEMENT IAW RHC COMPONENT MAINTENANCE MANUAL. (NEW NHBB MANUFACSDR 2022FA0000412Bearing · brinelledPILOT REPORTED ABNORMAL AND HEAVY CYCLIC FORCES DURING AUTOROTATION AND LOW POWER DESCENTS. FOUND BOTH MR SPINDLES TO BE BRINELLED. REMOVED SPINDLE ASSEMBLIES AND PERFORMED MR SPINDLE BEARING REPLACEMENT IAW RHC COMPONENT MAINTENANCE MANUAL (NEW NHBB MANUFACTUSDR 2022FA0000411Bearing · brinelledPILOT REPORTED ABNORMAL AND HEAVY CYCLIC FORCES DURING AUTOROTATION AND LOW POWER DESCENTS. FOUND BOTH MR SPINDLES TO BE BRINELLED. REMOVED SPINDLE ASSEMBLIES FOR FURTHER EVALUATION. INSTALLED NEW A005-15 SPINDLE ASSEMBLIES, TRACKED AND BALANCED MR SYSTEM AND SDR 2022FA0000410Bearing · brinelledPILOT REPORTED ABNORMAL AND HEAVY CYCLIC FORCES DURING AUTOROTATION AND LOW POWER DESCENTS. FOUND BOTH MR SPINDLES TO BE BRINELLED. REMOVED SPINDLE ASSEMBLIES FOR FURTHER EVALUATION. INSTALLED NEW A005-15 SPINDLE ASSEMBLIES, TRACKED AND BALANCED MR SYSTEM AND SDR 2022FA0000286Hub · crackedA CRACK WAS FOUND ON THE OUTSIDE OF M/R HUB ORIGINATING FROM INBOARD TT PIN HOLE. THE CRACK EXTENDS FROM THE INSIDE DIAMETER OF THE BORE TO THE OUTSIDE OF THE HUB. AFTER CLOSE EXAMINATION IT SEEMS THAT THERE ARE ROUGH MACHINING MARKS THAT CAUSED A STRESS CONCESDR 2022FA0000409Bearing · brinelledPILOT REPORTED ABNORMAL AND HEAVY CYCLIC FORCES DURING AUTOROTATION AND LOW POWER DESCENTS. FOUND BOTH MR SPINDLES TO BE BRINELLED. REMOVED MR BLADE AND SPINDLE ASSEMBLIES FOR FURTHER EVALUATION. INSTALLED NEW MR BLADES AND SPINDLE ASSEMBLIES, TRACKED AND BALASDR 2022FA0000408Bearing · brinelledPILOT REPORTED ABNORMAL AND HEAVY CYCLIC FORCES DURING AUTOROTATION AND LOW POWER DESCENTS. FOUND BOTH MR SPINDLES TO BE BRINELLED. REMOVED MR BLADE AND SPINDLE ASSEMBLIES FOR FURTHER EVALUATION. INSTALLED NEW MR BLADES AND SPINDLE ASSEMBLIES, TRACKED AND BALASDR 2025FA0000707Bearing · brinelledFOUND BOTH SPINDLE BEARING SETS P/N A159-3, TSN: 318.3, BRINELLED. NO OVER SPEEDSSDR L9QR202111100002Spindle · brinelledMAIN ROTOR SPINDLES BRINELLED AFTER 554.2 HOURS TIS. NO OVERSPEEDS REPORTEDSDR L9QR202111100001Spindle · brinelledMAIN ROTOR SPINDLE BEARINGS BRINELLED AFTER 298.2 HOURS TIS. NO REPORTED OVERSPEEDSDR EVCA102621(2)Blade · crackedGREEN MR BLADE CRACKEDSDR EVCA102621Blade · crackedORANGE MR BLADE CRACKES AS MARKED APPROX 73" AND 80" FROM BLADE ROOT BOTTOM SIDE OF BLADESDR QR9R20210825001Bolt · crackedNDI INSPECTION REVEALED HEX BOLT WAS CRACKED ON BASE OF BOLT HEAD.
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