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 HEEA075561Blade · mismanufacturedBLADE EXCESSIVELY HEAVY AND CANNOT GET TO 80 PERCENT ROTOR RPM.SDR HEEA075560Blade · damagedBLADE DIVES UNABLE TO TRACK.SDR HEEA075492Blade · corrodedEXTREME TRAILING EDGE SPAR CORRODED AT THE TIP OF THE BLADE.SDR AUS20010852Blade · delaminated(AUS) MAIN ROTOR BLADE SKIN DELAMINATED AT THE BLADE TIP JUST AFT OFTHE D' SPAR. AREA OF DELAMINATION 55MM BY 75MM (2IN BY 3IN).SDR 2001FA0000234Blade · crackedFOUND CRACK ON PREFLIGHT. NO SURE CAUSE FOR CRACK. CRACK BEYOND LIMITS.SDR B1H2001F00000Blade · debondedDURING A 50 HOUR INSPECTION THE CONDITION WAS FOUND. THE OUTER COMPOSITE LAYERS HAD DEBONDED FROM THE ROOT OF THE BLADE AND VOIDS WERE PRESENT. THE PROBLEM IS THE BLADE WILL HAVE TO BE SPREAD TO GET THE PITCH HORN IN AND THIS MAY BE THE CAUSE OF THE DEBONDINSDR ALG2001F00009Skin · separatedAFTER SHUTDOWN A PIECE OF SKIN WAS FOUND MISSING. LOWER SURFACE SKIN PEELED AND TORN AWAY APPROXIMATELY 7.5 INCHES X 5.0 INCHES AT APPROXIMATELY R. STA 218.5 R.STA. 226.0.SDR HEEA073710Blade · corrodedCORRODED AT BLADE TIP.SDR HEEA073709Blade · corrodedCORRODED AT BLADE TIP AND LATCH PLATE UNBONDED.SDR HEEA073784Blade · damagedTHE OUTBOARD LEADING EDGE STRIP SEPARATED IN SEVERAL AREAS. SENDING TO VENDOR FOR REPAIR.SDR HEEA073783Blade · damagedTHE OUTBOARD LEADING EDGE STRIP SEPARATED ON THE OUTBOARD TIP. SENDING TO VENDOR FOR REPAIR.SDR HEEA073671Blade · damagedCRACKED LEADING EDGE ABRASION STRIP. IN SHOP FOR REPAIR.SDR HEEA073670Blade · damagedSCARF JOINT SEPARATED AND LOOSE. IN SHOP FOR REPAIR.SDR HEEA073669Blade · damagedHAS SMALL SECTION OF SKIN MISSING NEAR OUTBOARD TAB. IN SHOP FOR REPAIR.SDR HEEA073668Blade · damagedOUTBOARD ABRASION STRIP HAS SEVERAL HOLES FROM EROSION. SENDING TO VENDOR FOR REPAIR.SDR ALG2001F00022Skin · corrodedDISCOVERED DURING ROUTINE AIRFRAME INSPECTION, FOUND CORROSION BENEATH OUTBOARD TRIM TAB, T/E EXTRUSION AND BLADE SKIN CORRODED BEYOND REPAIRABLE LIMITS.SDR CA010626007Blade · cracked(CAN) A/C STOPPED FOR REFUELING, DUE TO THE TQ EVENTS THAT HAD BEEN ACCUMULATED, (160) THE PILOTS CARRIED OUT A BLADE TORQUE EVENT INSPECTION I.A.W. SB600N-031. THEY FOUND THE WHITE BLADE TO BE CRACKED, BOTTOM SIDE, 12.5" O/B OF THE LAST BOLT ON THE BLADE GRIPSDR 20010613CW018Blade · crackedREMOVED FROM AIRCRAFT FOR BIM INDICATION. PERFORMED LEAK CHECK. DETECTED LEAK AND FOUND CRACK. CRACK IS CHORDWISE, AND .5000 INCH LONG WITH CORROSION PIT LOCATED IN CENTER. LOCATION OF CRACK IS 23.5 INCHES FROM TIP END ON BOTTOM SIDE OF BLADE AND 4 INCHES SDR 20010613CW017Blade · crackedBLADE REMOVED FOR BIM INDICATION. THE SPAR IS CRACKED ON BOTTOM SIDE UNDER NR 9 POCKET, APPROXIMATELY 1 INCH STARTING AT BACK WALL RADIUS, RUNNING CHORDWISE TOWARDS LEADING EDGE. PROBABLE CAUSE: CORROSION.SDR 20010531CW001Blade · delaminatedDOUBLER DELAMINATION NO SIGNS OF CORROSION OR IMPACT WHICH MIGHT CAUSE DELAMINATION. CAUSE UNKNOWNSDR CA020405022Bolt · worn(CAN) EXCESSIVE WEAR ON THE MAIN ROTOR BLADE BOLT SHANK.SDR HEEA072893Blade · damagedNUMBER ONE FINGER ON UPPER SURFACE TRAILING EDGE HAS 7 INCHES OF THE FINGER MISSING. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT.SDR CA010523015Blade · damaged(CAN) DURING HIS DI, THE PILOT NOTICED ADHESIVE MISSING FROM ONE MAIN ROTOR BLADE ROOT FITTING. MAINTENANCE WAS ADVISED. THE BLADE WAS REMOVED AND CHECKED AS PER DN188. THE ROOT FITTING FAILED THAT INSPECTION. THE REST OF THE BLADES WERE ALSO INSPECTED AND FOUSDR HEEA072472Bolt · damagedAREA OF SHANK BEHIND THREADS, IS OVERSIZED AND WILL NOT ALLOW BOLT TO GO THROUGH BUSHING. REPLACED WITH SERVICEABLE PART.SDR CA010423019Blade · failed(CAN) BOND VOIDS BEYOND LIMITS LOW SIDE OF BLADE. LETTER SENT FAA DATED 24 APR 01 EXPRESSING TC CONCERNS. (CADIS PROJECT REPORT20010079). CROSS REFER TO SDR 20010423018.SDR HEEA071924Tip Cap · crackedTOP INNER AND OUTER DOUBLER SEPARATED BEYOND LIMITS. ABRASION STRIP HAS CRACKS ON BOTH SIDES. SENT TO COMPOSITE TECHNICS FOR INSPECTION AND REPAIR.SDR HEEA071923Tip Cap · crackedTOP SKIN HAS A CRACK SPANWISE APPROXIMATELY 2 INCHES FROM TRAILING EDGE. THE ABRASION STRIP HAS A CRACK WITH SEPARATION. SENT TO COMPOSITE TECHNICS FOR INSPECTION AND REPAIR.SDR HEEA072177Blade · damagedNR 1 INBOARD STRIP HAS SEPARATION ON THE OUTBOARD END OF THE ABRASION STRIP.SDR HEEA071942Blade · corrodedTRAILING SKIN AND SPAR HAS EXCESSIVE CORROSION NEAR THE TIP ON THE LOWER SIDE.SDR 20010502CW005Blade · crackedA CRACK WAS NOTICED INSIDE DENT AFT OF THE SPAR ON THE TOP OF THE MAIN ROTOR BLADE. REMOVAL OF PAINT DETERMINED THE CRACK TO BE IN EXCESS OF 6 INCHES LONG. THE ROTOR BLADE WAS DETERMINED TO BE UNSERVICEABLE AND REMOVED FROM SERVICE.SDR CA010423018Blade · failed(CAN) BOND VOIDS BEYOND LIMITS LOW SIDE OF BLADE. LETTER SENT TO FAA DATED 24 APR 01 EXPRESSING TRANSPORT CANADA CONCERNS.(CADIS PROJECT REPORT 20010079. (CROSS REFER TO SDR 20010423019)SDR CA010405002Blade · cracked(CAN) UPPER AND LOWER SKIN CRACKED AT STN 36.5. CRACKED FROM TRAILING EDGE TOWARDS LEADING EDGE 4.25 INCHES.SDR CA010423011Boot · leaking(CAN) AIRCRAFT PARKED OVERNIGHT WITH COVERS AND HEATERS ON THE ENGINE. OVERNIGHT TEMP -35C. PILOT HAD LEFT PRINCE GEORGE, B.C., THE PREVIOUS DAY AND TEMP WAS ABOUT +5C AT CYXS. PILOT NOTED NO DEFECTS THE MORNING OF DEPARTURE ON HIS PRE-FLIGHT AND AS HE REMOVEDSDR AU010268Blade · corroded(AUS) MAIN ROTOR BLADE CORRODED IN AREA BETWEEN PAINT AND LEADING EDGESTRIP ON UNDERSIDE OF BLADE. CORROSION DEPTH APPROXIMATELY 1.52MM (0.060IN). FOUND BEFORE FITMENT.SDR HEED072211Blade · crackedSUSPECT CRACKING OF MAIN ROTOR SPAR. REPLACED UNIT.SDR AC2A072819Erosion Shield · damagedEROSION TAPE FOR MAIN ROTOR BLADE WAS FOUND BUBBLED. FUTHER INSPECTION FOUND BUBBLE WAS FULL OF WATER. THERE WAS NO SIGN OF AREA OF ENTRY. REPLACED EROSION TAPE.SDR CA010301029Blade · debonded(CAN) AIRCRAFT LANDED TO REFUEL. IT WAS NOTED THAT DURING A WALKAROUND THAT, A ROTOR BLADE POCKET HAD BECOME DEBONDED. A TEMPORARY REPAIR WAS MADE AND THE AIRCRAFT WAS FLOWN BACK TO BASE.SDR CA010518002Blade · cracked(CAN) DURING ROUTINE DAILY INSPECTION, MAIN ROTOR BLADE WAS FOUND TO HAVE TWO CRACKS ON THE UPPER SKIN AT STA 1177 AND STA 1182, RUNNING IN A CORD WISE DIRECTION. UPON REMOVED OF PART AND FURTHER INSPECTION, IT WAS DETERMINED THAT BLADE WAS NOT REPAIRABLE AS PSDR 20010208CW007Blade · crackedAIRCRAFT WAS FLYING LOW SPEED OVER A CORN FIELD AT NIGHT FOR FROST PREVENTION. ON RETURN LEG TO AIRPORT FOR REFUELING. AT 11:30 PM AIRCRAFT DEVELOPED SEVERE MAIN ROTOR VIBRATION. UPON SHUTDOWN, FOUND CRACK IN BLADE AREA.SDR AC2A072811Blade · crackedCRACKED INBOARD TRIM TAB REPLACED TRIM TABSDR RX8R2000001Blade · delaminatedHELICOPTER TECHNOLOGY COMPANY MAIN ROTOR BLADES PN 500P2100-101 WERE INSTALLED NEW 8/14/00 TTAC 5096.0. BLADES WERE INSPECTED IAW A.D.2000-24-51 (MSB 2100-02) ON 11/11/00, TTAC 5149.7 AND NO DEFECTS WERE NOTED. BLADES WERE INSPECTED IAW A.D. 2000-25-52 (MSB SDR 20010312CW007Pad · looseGRIP PAD COMES WITH ADHESIVE ON IT. TO APPLY, REMOVE PROTECTIVE TAPE, ROUGH UP PREAPPLIED ADHESIVE WITH SANDPAPER, THEN MIX UP ANOTHER ADHESIVE AND INSTALL GRIP PAD TO BLADE. PROBLEM IS THAT THE PREAPPLIED ADHESIVE LAYER IS TOO THICK, AFTER INSTALLATION OF GSDR CA010110014Bolt · misinstalled(CAN) INBOARD LATERAL BALANCE WEIGHTS LOOSE. INBOARD BOLT P/N AN4-12A WAS TOO LONG FOR THE AMOUNT BALANCE WEIGHTS INSTALLED. WE CONTACTED PRODUCT SUPPORT AND THEY SAID TO INSTALL A SHORTER AN4 BOLT. WE INSTALLED AN AN4-11A BOLT.SDR CA001201020Pin · broken(CAN) DURING AN APPROACH FOR LANDING TO REFUEL, THE PILOT AND ENGINEER ON BOARD EXPERIENCED A NOTICEABLE VIBRATION. UPON LANDING THE ENGINEER FOUND THAT A M/R BLADE PIN WAS SITTING A BIT HIGHER THAN THE OTHERS. WHEN HE UNLATCHED TO PIN, THE THREADED PORTION OSDR CA010518008Blade · cracked(CAN) MAIN ROTOR BLADE WAS REMOVED FROM AIRCRAFT AND SHIPPED TO REPAIR FACILITY FOR DEBONDING REPAIR REQUIRED TO STAINLESS STEEL LEADING EDGE. UPON FURTHER INSPECTION BY THE REPAIR FACILITY, THE BLADE WAS FOUND TO HAVE A SPAR BURNING CRACK LOCATED AT STN 1000,SDR CA010108021Blade · failed(CAN) M/R BLADE P/N 500P2100-101 S/N A204 WS INSPECTED I.A.W. THE MANUFACTURERS RECOMMENDATIONS AND HELICOPTER TECHNOLOGY CORP SB 2100-2 INSPECTION OF M/R BLADE FOR DEBONDING. THE M/R BLADE WAS INSTALLED ON THE A/C AND A SERIES OF FLIGHTS WERE CONDUCTED FOR TRSDR CA001218015Pin · broken(CAN) THE BROKEN PIN WAS DISCOVERED STILL SITTING IN PLACE INSIDE THE TWO BLADE PINS. THE PILOT CLAIMS TO HAVE DONE AN APPROPRIATE PRE-FLIGHT CHECK THAT MORNING. IT IS UNKNOWN HOW MANY HOURS THE AIRCRAFT FLEW IN THIS CONDITION.SDR CA001013028Blade · cracked(CAN) CRACK DETECTED IN M/R BLADE ASSY LOWER SKIN APPROX 16 INCHES FROM ROOT FITTING. CRACK APPEARS TO HAVE STARTED IN THE CENTRE OF THE BLADE SKIN AND PROGRESSED IN A CHORDWISE MANNER TOWARD THE TRAILING EDGE AND THE BLADE SPAR. CRACK WAS DISCOVERED DURING A SDR CA001027014Blade · broken(CAN) PILOT REPORTED A STRANGE VIBRATION IN THE HELICOPTER. UPON INVESTIGATION ENGINEERING FOUND THE UPPER LEADING EDGE LUG OF THE BLADE CRACKED AND BROKE LOOSE FROM THE BLADE AND ONE BLADE RETENTION PIN BENT. MAIN ROTOR BLADE AND BLADE RETENTION PINS WERE REPSDR 20001206SH001Blade · debondedDISCOVERED DURING POST-FLIGHT INSPECTION (VIBRATION WAS FELT DURING FLIGHT). EXTENSIVE UPPER SURFACE SKIN DISBOND. (X)
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