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 CA001013024Blade · cracked(CAN) BLADE CRACKED AT STATION 570, ALSO LEADING EDGE EROSION.SDR 20001017SH028Bolt · crackedAGC/CJI - DURING POST-FLIGHT FOUND MAIN ROTOR BLADE SECONDARY BOLT PROTRUDING UP 1 INCH OUT OF BOLT HOLE. NUT AND REMAINING PART OF BOLT MISSING. (COMPLETELY CRACKED IN HALF). POSSIBLE CAUSE: UNDER INVESTIGATION. (X)SDR AU000712Nut · mismanufactured(AUS) MAIN ROTOR RETENTION BOLT NUT FAULTY. NO LEAD ON THREAD. SUBMITTER STATED NUT WAS A NEW ITEM FROM ROBINSON. (X)SDR CA000824009Main Rotor · cracked(CAN) WHILE WASHING THE M/R BLADES THE WASHER ON THE UNDERSIDE OF M/R BLADE A-1567 THAT THE SOAP BUBBLED AS PUSHED UP ON THE BLADE. FURTHER INVESTIGATION FOUND A CRACK RUNNING CHORDWISE FROM THE AFT EDGE OF THE SPAR TO ABOUT 4 INCHES FORWARD OF THE TRAILING ESDR 20001219SH020Blade · crackedTHE TOP SIDE OF THE TRAILING EDGE RETENTION BLOCK SCREW HOLE HAD A CRACK WHICH EXTENDED APPROXIMATELY 360 DEGREES AT A 7 O CLOCK POSITION (AS VIEWED FROM THE TOPSIDE LOOKING DOWN). THIS CRACK WAS DISCOVERED DURING A VISUAL INSPECTION PERFORMED IN THE FIELD. SDR 20001218SH001Blade · crackedTHE TOP SIDE OF THE TRAILING EDGE RETENTION BLOCK SCREW HOLE HAD A CRACK WHICH EXTENDED APPROXIMATELY .360 INCH AT A 7 O''CLOCK POSITION (AS VIEWED FROM THE TOPSIDE LOOKING DOWN). THIS CRACK WAS DISCOVERED DURING A VISUAL INSPECTION PERFORMED IN THE FIELD. (SDR AC2A0000068Blade · corrodedDURING ZONE 1 INSPECTION, CORROSION WAS FOUND THROUGHOUT LOWER SURFACE OF MAIN ROTOR BLADE. THE ALUMINUM WIRE MESH WAS FOUND WITH NUMEROUS CORROSION PITS THROUGHOUT THE LOWER SURFACE OF THE BLADE. REMOVED CORROSION AND SPOT PAINTED PER COMPOSITE REPAIR MANUASDR AC2A0000067Blade · corrodedDURING ZONE 1 INSPECTION, CORROSION WAS FOUND THROUGHOUT THE LOWER SURFACE OF THE YELLOW MAIN ROTOR BLADE. THE ALUMINUM WIRE MESH WAS FOUND WITH NUMEROUS SMALL PITS OF CORROSION THROUGHOUT THE LOWER SURFACE OF THE BLADE. REMOVED CORROSION AND SPOT PAINTED PESDR CA000706024Blade · leaking(CAN) WHILE IN-FLIGHT, THE B.I.M. CAUTION LIGHT ILLUMINATED. AIRCRAFT LANDED AND SHUTDOWN. BLADE PRESSURE WAS COMFIRMED TO BE LOWER THAN MINIMUM. ALLOWABLE. BLADE WAS REMOVED AND SENT TO REPAIR FACILITY WHERE IT WAS DETERMINED TO BE LEAKING FROM THE AREA OF SDR 20000918SH014Blade · debondedPROTECTION PLATE DEBONDING. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. DAMPERS REMOVED: LK0911, LK0878. (X)SDR 20000918SH010Blade · debondedPROTECTION PLATE DEBONDING. REPLACED WITH NEW UNITS, CORRECTED PROBLEM. DAMPERS REMOVED: LK0670, LK0771. (X)SDR 20000918SH009Blade · debondedPROTECTION PLATE DEBONDING. REPLACED WITH NEW UNITS, CORRECTED PROBLEM. DAMPERS REMOVED: LK0888, LK0894. (X)SDR 20000718SH013Blade · corrodedDURING DAILY INSPECTION, FOUND HEAVY INTERGRANULAR CORROSION ON TRAILING EDGE EXTRUSION. (X)SDR AU000539Spar · cracked(AUS) MAIN ROTOR BLADE SPAR CRACKED FROM OUTBOARD LOWER FORWARD BLADE ATTACHMENT BOLT HOLE. LENGTH OF VISIBLE PORTION OF CRACK APPROXIMATELY 44.45 MM (1.75 INCHES). FOUND DURING INSPECTION IAW AD/S76/16 AMDT2.SDR 20000601SH010Blade · delaminatedBLADE WAS RETURNED TO BLADE SHOP FOR REPAIR OF SKIN TO TRAILING EDGE DISBOND. UPON INSPECTION, APPEARS THAT CLEANING AND/OR METAL PREP PROCESS FAILED CAUSING SKIN AND TRAILING EDGE TO SEPARATE. SUBMITTER RECOMMENDED INSPECTING ALL BLADES IN METAL PREP BATCH SDR AU000392Bracket · cracked(AUS) MAIN ROTOR BLADE VIBRATION ABSORBER LOWER BRACKET CRACKED.SDR 20000531SH013Blade · delaminatedDURING POST-FLIGHT, TECHNICIAN NOTED A LARGE CRACK OR DELAMINATION OF THE INBOARD ROTOR BLADE STARTING ABOUT 20 INCHES FROM THE ROOF ON THE TRAILING EDGE, EXTENDING ABOUT 5 INCHES LENGTHWISE, THEN DIAGONALLY TO JUST BEHIND THESPAR AND THEN LENGTHWISE ABOUT 12 SDR CA001013012Blade · failed(CAN) MAIN ROTOR BLADE AFTER BALANCING SEVERAL TIMES WINDS UP FLYING OUT OF TRACK, CAUSING A CYCLIC STICK FEEDBACK WHEN THE HYDRAULICS ARE OFF.SDR CA001013008Blade · cracked(CAN) CRACKED AT STATION 570, ALSO LEADING EDGE EROSION. BLADE REPLACED.SDR AU000331Blade · cracked(AUS) MAIN ROTOR BLADE CRACKED. BUSHING LOOSE.SDR CA000419006Bolt · cracked(CAN) DURING O/H OF MAAIN ROTOR HEAD, ONE OF THE BLADE BOLTS WAS FOUND TO BE CRACKED BY NON DESTRUCTIVE TESTING. BLADE BOLT P/N 206-101-152-1 CAN HAVE EIHTER NUTS (P/N 206-011-119-101 TORQUED TO 185-215 FT/LBS OR P/N 206-011-119-005 TORQUED TO 275-340 FT/LBS).SDR 20000718SH007Blade · corrodedINSPECTION OF AIRCRAFT DURING REFURBISHING FOUND INTERGRANULAR CORROSION OF LEADING EDGE OF MAIN ROTOR BLADES. (X)SDR 20000718SH006Blade · corrodedINSPECTION OF AIRCRAFT DURING REFURBISHING, FOUND INTERGRANULAR CORROSION OF LEADING EDGE OF MAIN ROTOR BLADES. (X)SDR 20000502SH014Blade · debondedDURING 500-HOUR INSPECTION, FOUND TIP PLATE COMPLETELY DEBONDED. (X)SDR 20000523SH005Bolt · wornSECONDARY BLADE REMOVED FOR WEAR. REMOVED AND REPLACED. (X)SDR 2000ZZZX811Blade · corrodedDURING DAILY INSPECTION, CORROSION AND DEBONDED AT ROOT END GRIP PLATE.SDR 20000721SH003Blade · debondedLEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROXIMATELY BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING EDGE, BOTH UPPER/LOWER SURFACES. (X)SDR 20000721SH002Blade · debondedLEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROXIMATELY BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING EDGE, BOTH UPPER/LOWER SURFACES. (X)SDR 20000721SH001Blade · debondedLEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROXIMATELY BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING EDGE, BOTH UPPER/LOWER SURFACES. (X)SDR 20000720SH014Blade · debondedLEADING EDGE SKIN UNDER BONDED PV-FILM IN NOSE AREA TO APPROX BLADE STA 922 (SECTION 1) IS DEBONDING ON TRAILING EDGE, BOTH UPPER/LOWER SURFACES. (X)SDR CA000201007Blade · damaged(CAN) M/R BLADES WERE FOUND TO HAVE DENTS THAT EXCEEDED THE .010 INCH LIMIT AND WERE LOCATED APPROX 23 INCH - 33 INCHES FROM THE TIP. M/R BLADES SENT TO AN APPROVED REPAIR FACILITY FOR FURTHER INSPECTION THE DENTS EXCEEDEDTHE ALLOWABLE LIMTS. HOWEVER THE LEADISDR AU000201007Blade · damaged(AU) M/R BLADES WERE FOUND TO HAVE DENTS THAT EXCEEDED THE .010 INCH LIMIT AND WERE LOCATED APPROXIMATELY 23-33INCHES FROM THE TIP. M/R BLADES SENT TO AN APPROVED REPAIR FACILITY FOR FURTHER INSPECTION. THE DENTS EXCEEDED THE ALLOWABLE LIMTS. HOWEVER, THE SDR 20000413SH027Blade · debondedLEADING EDGEOF MAIN ROTOR BLADE DEBONDING (INBOARD JOINT). 193.4 HOURS SINCE REPAIR/OVERHAUL. REMOVED AND REPLACED. (X)SDR CA000118003Blade · torn(CAN) ROTORCRAFT WAS RETURNING TO BASE WHEN SOUND WAS HEARD OF BLADE TAPE COMING OFF A BLADE. NO FURTHER SOUNDS OR PROBLEMS OCCURRED. UPON ARRIVAL AT BASE, IT WAS DISCOVERED THAT THE BOTTOM SIDE OF A MAIN ROTOR BLADE POCKET HAD DEPARTED THE ROTORCRAFT.SDR 2000ZZZX435Bearing · debondedFOUND ON POST-FLIGHT, ELASTOMERIC BEARING DEBONDED COMPLETELY.SDR 20000406SH029Blade · unbondedBLADE WAS COMING UNSTACKED IN-FLIGHT. REMOVED AND REPLACED. (X)SDR 20000406SH028Blade · damagedBLADE WOULD NOT BALANCE WITH OPPOSITE BLADE. REMOVED AND REPLACED. (X)SDR HEED065818Tip Cap · disbondedRETENTION DOUBLER STRIPS UNBONDED. REPLACED UNIT.SDR HEED065817Tip Cap · disbondedRETENTION DOUBLER STRIPS UNBONDED. REPLACED UNIT.SDR HEED065749Spindle · delaminatedRED SPINDLE MAIN ROTOR BLADE RETENTION (PIVOT) BEARING HAS ELASTOMERIC DELAMINATION. REPLACED UNIT.SDR HEEA065250Blade · crackedMAIN ROTOR BLADE CRACKED AT TRAILING EDGE BY TRIM TAB.SDR HEEA065249Blade · crackedMAIN ROTOR BLADE CRACKED AT TRAILING EDGE BY TRIM TAB.SDR HEEA065165Blade · damagedROTOR BLADE ASSY HAD TIP CAP SEPARATION.SDR HEEA065053Blade · crackedMAIN ROTOR BLADE CRACKED FORWARD AND AFT OF THE TRIM TAB.SDR HEED064616Blade · crackedMAIN ROTOR BLADE CRACKED LEADING EDGE AND LOWER SKIN. REPLACED PART.SDR AC2A0000009Blade · delaminatedSKIN DELAMINATED ON TOP FROM STA 32 EXTENDING OUT TO STA 105, 6 INCHES BACK FROM LEADING EDGE ABOUT 5 INCHES. (X)SDR 20000329SH042Blade · damagedMAIN ROTOR BLADE FACTORY INSTALLED WEIGHT DISLODGED DURING OPERATION STRIKING MAIN ROTOR BLADE TIP CAP. TIP CAP TRAILING EDGE WAS BENT OUTBOARD APPROXIMATELY 30 DEGREES AND APPROXIMATELY ONE INCH OF WEIGHT PROTRUDED THROUGH OUTBOARD END OF SPAR. UPPER AND LOSDR 99ZZZX4436Blade · damagedMAIN ROTOR BLADE FACTORY INSTALLED WEIGHT DISLODGED DURING OPERATION STRIKING MAIN ROTOR BLADE TIP CAP. TIP CAP TRAILING EDGE WAS BENT OUTBOARD APPROXIMATELY 30 DEGREES AND APPROXIMATELY ONE INCH OF WEIGHT PROTRUDED THROUGH OUTBOARD END OF SPAR. UPPER AND LOSDR 2000ZZZX420Blade · damagedMAIN ROTOR BLADE FACTORY INSTALLED WEIGHT DISLODGED DURING OPERATION STRIKING MAIN ROTOR BLADE TIP CAP. TIP CAP TRAILING EDGE WAS BENT OUTBOARD APPROXIMATELY 30 DEGREES AND APPROXIMATELY ONE INCH OF WEIGHT PROTRUDED THROUGH OUTBOARD END OF SPAR. UPPER AND LSDR CA991103018Blade · cracked(CAN) M/R BLADE CHORDWISE CRACK (90 MM LONG) DETECTED DURING SCHEDULED MAINTENANCE. CRACK WAS ON UNDERSIDE OF BLADE AT 179 MM FROM LEADING EDGE AND AT BLADE STATION 1160 MM. THERE WAS ALSO DEBONDING ON THE STAINLESS STEEL LEADING EDGE OF THE BLADE.
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