JASC 6210
Service difficulty reports · 1,561
Reports filed under 6210 · Main Rotor Blades, 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 = '6210' 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 = '6210' 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 CA050427008Blade · damagedVOID, 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 MOSDR YTRR099952Blade · delaminatedON ROUTINE INSPECTION FOUND THE 5TH FINGER FROM THE ROOT END DELAMINATED APPROXIMATLEY 1 - 2 INCHES. BLADE RETURNED TO BHT FOR INSPECTIONSDR CA050404006Blade · damaged(CAN) CRACK IN THE LEADING EDGE EROSION STRIP WAS DISCOVERED WHILE TRYING TO WORK THE MAIN ROTOR WITH THE RADS. ON INITIAL INSPECTION THE CRACK APPEARED TO BE A MASKED EDGE FROM THE NICKEL ABRASION COATING BUT AFTER THE BLADE WAS FLEXED, IT OPENED UP TO REVEASDR CA050406007Blade · cracked(CAN) WHILE TROUBLESHOOTING MAIN ROTOR SYSTEM FOR CAUSE OF DIFFICULTY WITH M/R TRACK AND BALANCE A HAIRLINE CRACK WAS DISCOVERED IN THE DISCREPANT BLADE LEADING EDGE ABRASION STRIP APPROXIMATELY 77 INCHES FROM THE BLADE TIP. THE BLADE AS PLACED ON A WORK STANSDR CA050328001Blade · cracked(CAN) M/R BLADE EXHIBITS CRACKS IN THE NICKEL PLATING ON THE LEADING EDGES (EROSION STRIP).SDR KBM2005F00082Blade · damagedM/R BLADE, RE BLENDED DOUBLER. INSPECTED AND REPAIRED. (K)SDR KBM2005F00187Blade · debondedMAIN ROTOR BLADE, UPPER DOUBLER DEBONDING. REPAIRED BY ROTOR BLADES, INC. (K)SDR CA050306001Blade · cracked(CAN) MAIN ROTOR BLADE SKIN CRACKED AT DOUBLER LIP ON BOTTOM SIDE OF BLADE CHORDWISE. CRACK LENGTH 2 INCHES. RUNS UNDERNEATH SEALANT THAT BOND DOUBLER TO THE BLADE. FOUND DURING 100 HR INSPECTION M/R TORQUE EVENT INSPECTION.SDR 2005FA0000341Spar · cracked(MDR05-074) THE SPAR IS CRACKED ON THE BOTTOM SIDE OF THE BLADE BETWEEN POCKET LOCATIONS NR 5 AND NR 6. CRACK IS APPROXIMATELY .300 INCH IN LENGTH .650 INCH FROM THE BACKWALL RUNNING CHORDWISE TO .950 INCH FROM THE BACKWALL. BLADE HAD A BIM INDICATION AND WASDR CA050401010Blade · cracked(CAN) FOUND M/R BLADE WITH A CRACK IN THE L/E EROSION STRIP. CRACK IS 3.250 INCH IN LENGTH CHORDWISE AND 107.5 INCH IB FROM THE BLADE TIP (BLADE STATION 114.5).SDR 2004FA0000923Blade · delaminatedPREFLIGHT INSPECTION FOUND ONE OF THE BLADES APPEARED TO HAVE SKIN SEPARATION AT TRAILING EDGE TIP APPROX 1/4" LONG. SENT DIGITAL PHOTO TO ROBINSON AND THEY REQUESTED BOTH BLADES BE SENT TO THEM FOR INSPECTION. UPON INSPECTION AT FACTORY BOTH BLADES WERE SCRSDR 2005FA0000002Spar · crackedBLADE WAS RECEIVED WITH AN UNSERVICEABLE BIM INDICATION. DURING LEAK CHECK, A CHORDWISE CRACK, APPROX .5 INCH LONG WITH A CORROSION PIT IN THE CENTER, WAS FOUND. THE CRACK IS LOCATED APPROX 70.75 INCH FROM TIP END AND 3.25 INCH FROM L/E. CORROSION PIT A CENSDR CA041124007Blade · cracked(CAN) DURING FLIGHT, THE ROTOR BLADE INTEGRITY MONITOR SYSTEM INDICATED A LEAK IN ONE OF THE MAIN ROTOR BLADES. THE PILOT LANDED THE AIRCRAFT SAFELY AND MAINTENANCE REPLACED THE BLADE AND SENT IT IN FOR INSPECTION. DURING INSPECTION, A LEAK WAS INDICATED UNDESDR CA041104010Blade · cracked(CAN) M/R BLADE FOUND WITH CHORDWISE CRACK AT STA 90.0 DURING ROUTINE 100 HOUR INSPECTION.PILOT THOUGHT HE FELT A SLIGHT CHANGE IN AIRCRAFT VIBRATION LEVELS DURING FLIGHT TO MAINTENANCE FACILITY. THE CRACKEXTENDED 4 INCHES FROM THE TRAILING EDGE OFTHE BLADE SSDR CA041013006Blade · cracked(CAN) HELICOPTER WAS FLYING WITH EXTERNAL LOAD WHEN THE PILOT FELT A (BUMP) IN THE CONTROLS. THE WEATHER WAS DETERIOATING WHERE HE WAS OPERATING SO HE RETURNED TO THE STAGING AREA. THE PILOT INSPECTED THE BLADES AFTER SHUTDOWN AND FOUND A 4.5 INCH CRACK 19 INCSDR ERAA098184Pad · missingWEAR PAD MISSING. DEFORMING SHOULDER. RESULT, CRACKED. RECOMMEND ASSEMBLY PRACTICES DEVELOPED. VISUAL INSPECTION AND NDT CONFIRMATION. SCRAP AND RETURN TO ERA.SDR ALGA096731Blade · corrodedTRAILING EDGE EXTRUSION EXFOLIATED, LOWER O/B GRIP FINGER DOUBLER SEPARATED AND CORRODED, ALSO CORROSION BETWEEN SKIN AND SPAR. SCRAPPED BLADE, AND INSTALLED A NEW BLADE.SDR CA041110003Blade · cracked(CAN) DURING DI, THE TIP BLOCK WAS FOUND CRACKED ADJACENT TO IMPACT MARK.SDR ALGA096801Bearing · bindingBINDING, AXIAL WEAR BEYOUND MAX, AND ROUGH. REPLACED WITH NEW PART IN FIELD.SDR ALGA096800Bearing · bindingBINDING, AXIAL WEAR BEYOND MAX., AND ROUGH. REPLACED WITH NEW PART IN FIELD.SDR ALGA096566Blade · debondedLOWER SURFACE OB GRIP FINGER DOUBLER DEBONDED. FOUND CORROSION BETWEEN SKIN AND SPAR. REPLACED UNIT W/NEW BLADE.SDR ALGA096403Blade · separatedFOUND CORROSION AND SEPARATION AT SKIN/SPAR INTERFACE NEAR LOWER OB GRIP FINGER DOUBLER. REMOVED AND REPLACED DEFECTIVE BLADE WITH NEW BLADE. SCRAPPED DEFECTIVE BLADE.SDR ALGA096402Blade · separatedFOUND CORROSION AND SEPARATION AT SKIN/SPAR INTERFACE NEAR LOWER OB GRIP FINGER DOUBLER. REMOVED AND REPLACED DEFECTIVE BLADE WITH NEW BLADE. SCRAPPED DEFECTIVE BLADE.SDR ALGA096565Blade · debondedDURING ROUTINE INSPECTION DISBOND WAS NOTED ON LOWER SURFACE OB OF GRIP FINGER. REPLACED UNIT W/NEW BLADE.SDR CA040817003Blade · cracked(CAN) DURING A 100 HOUR INSPECTION A 5.500 INCH (138MM) CRACK WAS DISCOVERED ON THE UPPER SURFACE IN ZONE C OF ONE MAIN ROTOR BLADE. THE CRACK WAS BEYOND THE LIMIT OF 100 MM FOR THIS AREA.SDR ERAA097095Blade · damagedSET SCREW MISSING IN TIP CAP SUSPECT FACTORY BALANCE WEIGHTS MISSING. INSPECTED, PERFORMED 2500 HOUR INSPECTIONS PER BHT-412-MM CHAPTER 5; REPLACED INBOARD AND CENTER TRIM TABS PER 204-099-223 APPENDIX B SECTION 2 PARAGRAPH 2.7REV L; REPAIRED SKIN ON UPPER SUSDR CA040901003Blade · cracked(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 ISDR ALGA095355Blade · flakingM/R BLADE T/E EXTRUSION EXFOLIATED AT APPROX. STA. 120.00. REMOVED BLADE FROM SERVICE AND INSTALLED A SERVICABLE UNIT.SDR ALGA095354Blade · flakingMAIN ROTOR BLADE TRAILING EDGE EXFOLIATED APPROX. 14.SDR ALGA095348Blade · flakingFOUND TRAILING EDGE EXTRUSION EXFOLIATED AT STA. 178.00. REMOVED BLADE FROM SERVICE.SDR ALG2004F00035Blade · delaminatedIN CRUISE FLIGHT, AIRCRAFT COMMENCED AN APPROX 1/1 VERTICAL BEAT WITH AN UNUSUAL NOISE AND (HUM) IN THE AIRFRAME. PILOT DIVERTED TO FIELD LANDING SITE. AFTER SHUT-DOWN, PILOT FOUND BLADE SKIN DELAMINATING NEAR TIP. MAINTENANCE REMOVED AFFECTED BLADE AND INSSDR AUS20040506Blade · corroded(AUS) MAIN ROTOR BLADE CORRODED ON BLADE TIP.SDR ALGA095160Blade · corrodedDURING ROUTINE A/F INSPECTION, CORROSION AND SEPARATION WAS NOTED ON LOWER SURFACE SKIN/SPAR INTERFACE IMMEDIATELY O/B OF GRIPFINGER. REPLACED W/SERVICABLE PART.SDR CA040601009Blade · unserviceableUPON INSPECTION, A LINE WAS NOTICED EXTENDING CHORDWISE FROM THE LOWER ROOT FITTING. AFTER REMOVING THE PAINT, THE DOULBER HAD ABOUT A 2.5 INCH CRACK THAT EXTENDED BOTH FOR AND AFT OF THE LOWER ROOT FITTING OF THE M/R BLADE. THE BLADE WAS REMOVED FORM SERVICSDR ERAA096623Tip Cap · debondedTIP CAP ASSY BOTTOM DISBONDED. SENT TO CTI FOR REPAIR. INSPECTED PER SA4047-76-5 REV11; REPAIRED KEVLAR PER PROCEDURE NR 2 AND NR 18 1 PLY; REFINISHED PER DRWG NO 76150-09043; STATIC BALANCE PER RS-005N-VI.SDR ERAA097096Blade · debondedMID LEADING EDGE SCARF JOINT DEBONDED, LEADING EDGE BOND LINE VOIDED NEAR TIP AND UNDER SIDE OF BLADE DETERIORATED. SENT TO CTI FOR REPAIR. INSPECTED PERFORMED 2500 HOUR INSPECTION AND REPAIRED.SDR ALGA094414Universal · ratchetingFOUND BEARING ROUGH AND RATCHETY. REPLACED WITH NEW PART.SDR ERAA097103Blade · damagedM/R BLADE REJECTED FOR FLIGHT DUE TO LOOP A AREA BEING TOO THIN ON INNER RADIUS. BLADE SCRAPPED.SDR ERAA097102Blade · damagedM/R BLADE REJECTED FOR FLIGHT DUE TO LOOP A AREA BEING TOO THIN ON INNER RADIUS. BLADE SCRAPPED.SDR HXS2004F00099Blade · crackedMAIN ROTOR BLADE WAS FOUND TO HAVE A CRACK ON THE LOWER SURFACE OF THE BLADE, 172.72 CM FROM PIN ROOT. CRACK IS 5.08 CM LONG. (AL05200400824)SDR CA040503003Blade · damaged(CAN) BLADE RETURNED FOR EVALUATION. AT STA 760 MM, AT ROOT END, AN AREA OF SKIN (150 MM LONG BY 2 MM WIDE) WAS MISSING FROM THE ROOT MATING FACE. THIS APPEARS TO BE A MANUFACTURING DEFECT AND HAS BEEN RETURNED TO THE MANUFACTURER FOR EVALUATION/REPAIR.SDR ERAA096622Blade · peelingTRIM TAD PEALING/SEPARATED. INSPECTED, PERFORMED X RAY ULTRASONIC INSPECTIONS PER QATI 3048, 3016, SS8806 & 3095, PERFORMED ALL INSPECTIONS UP TO AND INCLUDING 900 HOUR INSPECTIONS, COMPLIED WITH AD 884-10-02 & ASB 76-65-18C; REPLACED TRIM TAB 1 ER PER RS-006SDR HXS2004F00000Blade · crackedON 3/25/04, MAIN ROTOR BLADE, SN 7530 REMOVED FROM AC DURING ANNUAL INSPECTION. 130MM SPANWISE CRACK FOUND AT 68.375.SDR ERAA096628Blade · crackedM/R BLADE HAS CRACKS, VOIDS AT STA 90. SENT TO CTI FOR REPAIR INSPECTED, PERFORMED 2500 HOUR INSPECTIONS AND REPAIRED.SDR ALGA093984Blade · corrodedFOUND MAIN ROTOR TRAILING EDGE EXTRUSION EXFOLIATED APPROXIMATELY 2.5.SDR MDR04047Spar · crackedTHE BLADE WAS REMOVED FROM THE AIRCRAFT DUE TO A RED BIM INDICATION. DURING A 10 DAY LEAK CHECK, LOSS OF PRESSURE WAS NOTED. FURTHER INVESTIGATION FOUND A .6250 INCH CRACK LOCATED ON TOP OF BLADE. THE CRACK IS LOCATED 142.5 INCHES FROM TIP END, 6.75 INCH FRSDR ALGA093732Blade · corrodedMAIN ROTOR BLADE TRAILING EDGE EXTRUSION EXFOLIATED AT STA. 98 AND 130. DAMAGE IS CONSIDERED A MATERIAL DEFECT.SDR ALGA093731Blade · corrodedMAIN ROTOR BLADE TRAILING EDGE EXTRUSION EXFOLIATED AT STA. 179.0. DAMAGE IS CONSIDERED A MATERIAL DEFECT.SDR ALGA093730Blade · corrodedTRAILING EDGE EXTRUSION HAS AREA APPROX. 5.SDR AC2A093681Trim Tab · crackedTRIM TAB ON MAIN ROTOR BLADE IS CRACKED. REPLACED TRIM TAB.
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