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 ALGA112909657ALBlade · delaminatedON DAILY SERVICE CHECK, MX FOUND M/R BLADE DELAMINATED.SDR ALGA112409437ALBlade · debondedDURING DAILY SERVICE CHECK, MX FOUND PREVIOUSLY INSTALLED MAIN ROTOR BLADE REPAIR DEBONDED.SDR ALGA111009N92TZBlade · debondedWHILE PERFORMING MAIN ROTOR TRACK AND BALANCE PROCEDURES, MX FOUND A M/R BLADE INBD TRIM TAB DEBONDED.SDR 2009FA0000633Blade · dislodgedBALANCE WEIGHT CAME LOOSE INSIDE OF MAIN ROTOR BLADE. WEIGHT WAS PROJECTED OUT OF THE OTBD BLADE CAP CAUSING THE TIE DOWN RING AND END CAP TO COME DISLODGED FROM THE ROTOR BLADE.SDR CA090716008Blade · delaminated(CAN) HELICOPTER M/R VIBRATIONS INCREASED RAPIDLY OVER A FEW DAYS. M/R WAS TRACKED AND BALANCED TO WITHIN LIMITS. WITHIN 2 DAYS, VIBRATIONS LEVELS HAD INCREASED BEYOND LIMITS AGAIN. FURTHER INSP REVEALED BLADE DELAMINATION SUSPECTED TO BE ABOVE LIMITS ON THESDR CA090716007Blade · delaminated(CAN) HELICOPTER M/R VIBRATIONS INCREASED RAPIDLY OVER A FEW DAYS. M/R WAS TRACKED AND BALANCED TO WITHIN LIMITS. WITHIN 2 DAYS, VIBRATIONS LEVELS HAD INCREASED BEYOND LIMITS AGAIN. FURTHER INSP REVEALED BLADE DELAMINATION SUSPECTED TO BE ABOVE LIMITS ON THESDR RMXA062620097217Blade · debondedDURING FLIGHT, A NOISE WAS HEARD IN THE MAIN ROTOR SYS, FOLLOWED BY A VIBRATION THAT INCREASED. A PRECAUTIONARY LANDING WAS PERFORMED. FOUND EROSION TAPE HAD SEPARATED FROM NR1 MAIN ROTOR BLADE. WHEN THE TAPE SEPARATED, IT ALSO PULLED UP SOME FILLER MATERIASDR CA090706005Blade · debondedM/R BLADE UPPER SKIN DEBONDED AT BLADE TIP AT STA 218.07 AREA OF DAMAGE 1 INCH BY INCH.SDR RMXA051720097211Blade · delaminatedVERTICAL VIBRATION NOTICED IN FLIGHT. VIBRATION CEASED WHILE STILL IN FLIGHT. PILOT MADE AN UNSCHEDULED LANDING. VISUAL INSPECTION REVEALED 1 MAIN ROTOR BLADE EROSION PROTECTIVE TAPE HAD PEELED BACK AND A .7500 INCH X 3 INCH PORTION OF THE FIBERGLASS SKIN HAD SDR 2009FA0000339Blade · debondedTHE AERODYNAMIC FILLER THAT IS USED TO MAINTAIN CONTOUR OF MAIN ROTOR BLADE BETWEEN L/E AND BLADE SKIN WAS FOUND TO LIFTING OR DEBONDING DURING A ROUTINE 100 HR INSP IAW MFG INSP PROGRAM. AREA THAT WAS LIFTING WAS AT APPROX 55 INCHES X 57 INCHES FROM ROOT OF SDR EVCA 2009/03/30Blade · crackedDURING POST FLIGHT INSPECTION, PILOT DISCOVERED A CRACK IN A MAIN ROTOR BLADE STARTING AT THE TRAILING EDGE AND CONTINUING FORWARD TO THE SPAR.SDR CA090316002Blade · failed(CAN) BLADE POCKET ON LWR MAIN ROTOR BLADE FAILED DURING FLIGHT.SDR CA090303002Blade · corroded(CAN) INSP CARRIED OUT IAW AD2007-26-12. INSP REVEALED CORROSION ALONG TIP CAP WHICH RESULTED IN BLADE SKIN TO CAP SEPARATION. THE PART IS DEEMED SCRAP.SDR YTRR2008121880114Blade · damagedON POST FLIGHT INSP, PILOT FOUND BOTH MAIN ROTOR BLADES HAD EVIDENCE OF IMPACT DAMAGE. FURTHER INSP REVEALED THAT BOTH MAIN ROTOR BLADES HAD CONTACTED THE WINGLETS ON THE HORIZ STABILIZER. THE PILOT REPORTED THAT IN CRUISE FLIGHT HE ENCOUNTERED SOME TURBULENCESDR MV1R200808429Blade · delaminatedDURING 3 YEAR MAIN ROTOR BLADE INSP FOUND DELAMINATION IN BLACK MAIN ROTOR BLADE ROOT END. DATA SENT TO MFG FOR EVALUATION. TOTAL DELAMINATED AREA IS 1.472 SQUARE INCHES.SDR 2008FA0000897Bolt · debondedMAIN ROTOR BLADE BOLT LWR PLUG, PN 206-011-137-001, FELL OUT ON ENG SHUTDOWN WHEN ROTOR RPM DROPPED BELOW 40 PERCENT. THIS ALLOWED LEAD BALANCE WEIGHTS TO ALSO FALL OUT OF BOLT. THIS PLUG IS BONDED INTO THE BOLT AT MFG AND APPEARS TO NOT HAVE HAD ADEQUATE ADHESDR 2009FA0000580Blade · separatedDURING CRUISE FLIGHT, 1 OR 2 CONTROL ROTOR BLADE ASSEMBLIES SEPARATED FROM ROTOR HEAD. ROTOR CONTROL BLADE ASSY TUBE BROKE OTBD OF 2 BOLTS ATTACHING IT TO CUFF ASSY. THIS CAUSED A VIOLENT VIBRATION AND MINIMMAL CONTROL OF ACFT. LOWERED COLLECTIVE AND TRIEDSDR CA081113008Tab · deformed(CAN) LOUD BANG WAS NOTED WITHING 10 MINUTES OF FLIGHT. LEVEL OF VIBRATION DID NOT INCREASE. INSP AFTER LANDING FOUND THAT THE TRIM TAB WAS DEFORMED (UPPER SIDE WAS BENT UPWARD AND LOWER SIDE BENT DOWNWARD). PEEL-PLY HAS BEEN LEFT ON THE TRIM TAB.SDR 2008FA0000646Blade · crackedM/R BLADE HAS 2706.0 HRS TT WHEN CLEANING BLADE FOR REINSTALLATION, MANY SHALLOW CRACKS WERE FOUND ON THE TOP SURFACE OF BLADE 24 INCH IB OF TRIM TAB. THE CRACKS RUN 45 DEGREES TO BLADE SPAN. CONTACTED MFG PRODUCT SUPPORT AND WAS INFORMED THAT THIS CONDITION ISDR CA080625005Blade · delaminated(CAN) DELAMINATION AT ROOT OF BLADE ON UPPER SURFACE OF THE GIP PLATE FINGER. VISUAL SEPARATION NOTED ON DAILY INSP.SDR EGI2008F00001Blade · damagedVISUAL INSPECTION OF M/R BLADE PRIOR TO INSTALLATION FOUND A .017 IN. DEEP DENT IN THE LOWER GRIP PLATE AT STATION 17.5. THIS M/R BLADE WAS PREVIOUSLY REMOVED IN SERVICEABLE CONDITION AND PLACED IN STOCK. COMMUNICATION WITH MFG PSE RECOMMENDS SENDING TO RBI FOSDR 2562Blade · crackedDURING INDUCTION, INSPECTION INTO A ROTOR BLADE REPAIR FACILITY, MAIN ROTOR BLADE SPAR WAS FOUND CRACKED (INTERNAL ROOT END). CRACK ORIGINATES FROM LEADING EDGE, OB LOWER ATTACHMENT BOLT HOLE. PHENOLIC BLOCK WAS REMOVED AND DYE PENETRANT INSPECTION WAS PERFORMSDR M7K2008F00093Blade · crackedPREFLIGHT INSPECTION REVEALED THAT HAMMER BLADE HAD CRACKED IN TWO AND THE WEIGHTS AND BLADE WERE CAPTURED BY THE CONTAINMENT BOX ASSY. AS THIS BLADE IS NORMALLY UNDER A 1200 FLEX PER MINUTE OPERATION IT IS EXPECTED TO WORK HARDEN OR FATIGUE OVER TIME. THIS SDR M7K2008F00092Tuning Unit · crackedROUTINE 100 HOUR INSPECTION REVEALED THAT HAMMER BLADE HAD CRACKED. AS THIS BLADE IS NORMALLY UNDER A 1200 FLEX PER MINUTE OPERATION IT IS EXPECTED TO WORK HARDEN OR FATIGUE OVER TIME. SUSPECT A METAL DEFECT OF SOME NATURE AS MOST OF THESE BLADES LAST MUCH LSDR 2008F00001Blade · crackedCOMPOSITE MAIN ROTOR BLADE CRACKED FROM STA 4855 TO 4880, (45 DEGREE CRACK) FROM TRAILING EDGE FWD TO EDGE OF SPAR. MFG TECHNICAL INFORMATION LETTER NR EC135 014-2005 ADDRESSES 45 DEGREE CRACKS IN EARLIER S/N BLADES. OPERATOR GROUNDED AIRCRAFT AND CONTACTED SDR CA080821011Balance Weight · debonded(CAN) IT WAS THOUGHT THAT THE BLADE TIE DOWN WAS LEFT ON THE ACFT. THIS WAS NOT THE CASE IAW A REPORT. THE FOLLOWING OCCURRED. INSP AND SCRAPPED THE M/R BLADE DUE TO WEIGHT POCKET RETAINING HOLES DAMAGED BEYOND LIMITS. DAMAGE CAUSED BY TELL TALE LEAD COUPON (SSDR BAQA20080002Bolt · misinstalledWHILE PERFORMING AN 800 HOUR INSP OF THE MAIN ROTOR BLADES, FOUND 2 BLADES THAT THE BEARING PIN, EXPANSION BOLT, AND NUT WERE NOT INSTALLED PROPERLY BY THE MFG. BOTH EXPANSION BOLTS WERE BROKEN DURING REMOVAL FOR THE FIRST 800 INSPECTION INTERVAL ON THESE BLASDR 705712212007Fitting · crackedWHILE PERFORMING AIRWORTHINESS CK, MECHANIC FOUND CRACK IN OB LOWER END OF MAIN ROTOR BLADE CUFF (BLADE FITTING 0 DEGREE - NEW STYLE) EXTENDING FROM THE BLADE ROOT OPENING TO THE ATTACHMENT BOLT THAT HOLDS THE UPPER AND LOWER CUFF HALVES TOGETHER ON THE SECONDSDR CA071127003Bearing · spalled(CAN) WHILE CONDUCTING A DI, THE M/R BLADE BOOT WAS FOUND DISTORTED. THE BOOT WAS REPLACED AND A CHECK OF THE SPINDLE BEARINGS WERE FOUND TO BE ROUGH. FURTHER INVESTIGATION REVEALED THE NR 6 BEARING INNER RACE WAS FOUND SPALLING. BEARING REPLACED AND ASSY REINSDR AWTR118188Blade · crackedBLADE LEADING EDGE CAP CRACKED.SDR BAQA200700038Blade · separatedDURING NORMAL FLIGHT PILOT EXPERIENCED ABNORMAL VIBRATIONS. THE PILOT INITIATED AN EMERGENCY LANDING AND LANDED WITH THE GEARS UP IN A FIELD. MAINTENANCE PERSONNEL INSPECTED THE AIRCRAFT AND FOUND THE TIP CAP UPPER SKIN ON MAIN ROTOR BLADE P/N 709-0103-01-109 SDR CA071026006Blade · broken(CAN) DURING NORMAL TRAINING FLIGHT, VIBRATION WAS FELT AND AUTOROTATION LANDING CARRIED OUT. UPON SHUTDOWN AND INSPECTION OF BLADES, A FIVE (5) FOOT SECTION OF BLADE COVERING WAS DISCOVERED MISSING FROM THE UNDERSIDE OF THE BLADE FROM THE TIP EXPOSING THE WOOSDR CA070914019Blade · leaking(CAN) BIM WARNING LIGHT ILLUMINATED IN FLIGHT. SPAR PRESSURE WAS FOUND TO BE .25 LBS BELOW MINIMUM CHECKING PRESSURE. SPAR PRESSURE WAS SERVICED APPROXIMATELY 80 DAYS PREVIOUS. (TC NR 20070914019)SDR 2007FA0000868Blade · crackedEXCESSIVE 1 PER REVOLUTION VIBRATION NOTICED IN MAIN ROTOR SYSTEM. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED CORD WISE CRACKS IN UPPER AND LOWER SKINS AT STATION 1979 EXTENDING FROM THE TRAILING EDGE TO THE AFT SIDE OF THE SPAR. THE HSDR BAQA200700030Blades · crackedWHILE PERFORMING MAINTENANCE, PILOT FELT AN USUALLY HIGH VIBRATION LEVEL DURING LANDING. A POST FLIGHT INSPTION REVEALED A CORDWISE CRACKS FROM THE TRAILING EDGE TO THE AFT SIDE OF THE SPAR ON THE TOP AND BOTTOM SKINS. THE BLADE WAS REPLACED WITH P/N 109-0103-SDR CA071010005Blade · cracked(CAN) ON TUESDAY THE 28TH OF AUGUST 2007, AT APPROX 19:00, LANDED AT THE STAGING AREA. THE PILOT COMMENTED THAT THERE WAS A VIOLENT LATERAL VIBRATION. AT THIS TIME THE TRANSMISSION WAS OBSERVED SHAKING EXCESSIVELY AND IT WAS DECIDED TO SHUT THE AIRCRAFT DOWN WSDR AOC0701Bearing · damagedDURING A PREFLIGHT INSPECTION OF THE SUBJECT AIRCRAFT, A PITCH CHANGE LINK BEARING (ATTACHED TO THE DRIVER END) APPEARED TO BE WORN. THE PILOT ATTEMPTED TO MOVE THE DRIVER TO CHECK FOR WEAR BUT THE BEARING, BOLT AND DRIVER WERE TIGHT. THE PILOT THEN OBSERVED TSDR 2007F00041Blade · crackedVISUAL INSPECTION REVEALED CRACK IN M/R BLADE APPROX. 103 INCHES FROM BLADE ROOT. CRACK RUN FROM AFT OF SPAR TO THE TRAILING EDGE.SDR CA070814002Blade · damaged(CAN) UPON LANDING IN A BRUSH AREA, THE PILOT LOWERED THE COLLECTIVE, WHICH IN TURN RAISED (2) TREES THAT WERE SITUATED ON THE LEFT AND THEN HIT THE ROTOR DISK. THE PILOT THEN DISPLACED THE AIRCRAFT TO THE RT. AN ENGINE SHUTDOWN WAS PERFORMED AND VISUAL INSPESDR CA070523007Pin · broken(CAN) PIN FOUND BROKEN AT FIRST THREAD / SHANK. NUT WAS CAPTURED IN THE HANDLE CLIP.SDR 2007FA0000473Blade · crackedSKIN CRACKS WERE DISCOVERED IN THIS BLADE UPON INVESTIGATION OF AN UNUSUALLY HIGH VIBRATION LEVEL AS REPORTED BY THE PILOT. THE ONE-PER-REV VERTICAL VIBRATION WAS ESPECIALLY NOTICEABLE DURING THE LANDING PHASE OF FLIGHT. INSPECTION OF THIS BLADE REVEALED CORSDR BAQB200700018Blade · crackedDURING A MAINTENANCE CHECK FLIGHT PILOT NOTICED A UNUSUAL VIBRATION. PILOT LANDED WITHOUT INCIDENT. UPON INSPECTION MECHANIC FOUND A CRACK IN THE MAIN ROTOR BLADE P/N 109-0103-01-9 S/N 1841R. THE CRACK STARTED AT A REPAIR IN THE BLADE. THE BLADE WAS REPLACED SDR CA070309002Blade · cracked(CAN) BLADE CRACKED BY TRAILING EDGE OF TRIM TAB, IB SIDE. (TC NR 20070309002)SDR CA070309003Blade · cracked(CAN) PILOT FELT A VIBRATION AND UPON LANDING CHECKED MAIN ROTOR BLADES. A CRACK APPROXIMATELY 18 INCHES FROM THE ROOT, RUNNING PERPENDICULAR TO THE TRAILING EDGE WAS DISCOVERED. IT APPEARS AS IF THE BLADE DEBONDED AT A RIB, AS THE CRACK FOLLOWS STRAIGHT FROM SDR CA070223007Blade · dented(CAN) WHILE IN HANGAR, METAL PIECE OUT OF HANGAR OVERHEAD HEATER FELL ON M/R BLADE AND DENTED THE BLADE. BLADE WAS REMOVED AND SENT FOR INSPECTION. HANGAR STAFF AND MANAGER WERE NOTIFIED AND REQUESTED TO INSPECT ALL OVERHEAD ACCESSORIES INCLUDING HEATERS FOR LSDR CA070131004Blades · out of balance(CAN) COULD NOT ACHEIVE DYNAMIC BALANCE OF A/C. (TC NR 20070131004)SDR CA070118006Blade · cracked(CAN) THE UPPER BLADE SURFACE IS CRACKED CHORDWISE FROM LEADING EDGE TO TRAILING EDGE BETWEEN BLADE STATION 120 AND 124. THE LOWER BLADE SURFACE IS ALSO CRACKED IN THE MID CORD AREA BETWEEN STATION 120 AND 124 BUT DOES NOT EXTENT TO THE LEADING EDGE OR TRAILINSDR 2006FA0001172Boot · leakingFLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.SDR 2006FA0001171Boot · leakingFLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.SDR 2006FA0001169Boot · leakingFLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.
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