Pratt & Whitney PT6T-3

Service difficulty reports · 421

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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 engine_model_key = 'PT6T3'
  ORDER BY difficulty_date DESC"

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SDR CA060906014Connector · shorted(CAN) FLASHING LIGHT OF ENGINE FUEL VALVE NR 2 ON STARTING PROCEDURE. CONNECTOR 1B14P1 SHORTED TOGETHER BETWEEN PINS A AND B AND WATER CONTAMINATION FOUND INSIDE BACK SHELL. INTERNAL LEAKAGE MEASURED ON THE CONNECTOR BETWEEN PINS A AND B CAUSING ON-OFF SIMULTASep 6, 2006 · Bell 412EP · Fuel System WiringSDR CA060815003Pressure Switch · leaking(CAN) FLUID LEAK AT UNION OF SWITCH BODY. THE BODY NORMALY HAS A RIVET TO KEEP THE UNIT FROM BEING TAKEN APART, BUT THIS RIVET WAS FOUND TO BE MISSING. THE THREADS HAD DAMAGE WHERE THE RIVET HOLE WAS. A HOLE IS PROVIDED IN THE THREADS TO INSTALL A RIVET. TAug 15, 2006 · Bell 212 · Engine Oil PressureSDR CA060728001Check Valve · jammed(CAN) UPON FIRST GROUND RUN OF M412 DURING MANUFACTURING FTP`S (WITHOUT M/R BLADES INSTALLED), A NOISE (BANG) WAS HEARD TWICE AND HYDR PRESSURE RAISED TO +1300 PSI ON THE GAGE. PILOT SHUTDOWN THE HYDR SYSTEM AND ABORTED GROUND RUN FOR INVESTIGATION. FURTHER IJul 11, 2006 · Bell 412EP · Hydraulic System, MainSDR CA060731010Engine · making metal(CAN) THE ENGINE WAS REPORTED TO LOSE POWER IN HOVER ACCOMPANIED BY A CHIP DETECTOR INDICATION. SUBSEQUENT INSPECTION REVEALLED LOSS OF DRIVE TO THE ACCESSORY GEARBOX. MFG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 2006073101Jul 5, 2006 · Bell 412 · Engine (Turbine/Turboprop)SDR CA060605012Blade · cracked(CAN) MAIN ROTOR BLADE SMALL DEBOND FOUND ON LOWER SURFACE APPROX 81.5 INCHES FROM BUTT END JUST AFT OF THE STAINLESS STEEL LEADING EDGE STRIP ON DISASSEMBLY. (APRIL 07 2006) BLADE WILL BE INSPECTED WHEN ARRIVING BACK FOR REPAIR EVALUATION. PAINT REMOVED FROM May 25, 2006 · Bell 212 · Main Rotor BladesSDR CA060524007Control Unit · malfunctioned(CAN) TROUBLESHOOTING A FUEL QUANTITY INDICATING A/C SYSTEM DEFECT. WITH BOTH POWER SECTIONS RUNNING THE FUEL QUANTITY INDICATION WOULD CHANGE WITH NO FUEL ADDED. FUEL QUANTITY SELECTOR WOULD BE POSITIONED TO LT TANK AND VERY SLOWLY THE INDICATOR WOULD SHOW THMay 19, 2006 · Bell 212 · Fuel Quantity IndicatorSDR CA060515004Blade · corroded(CAN) AT REASSEMBLY OF T/R BLADES IT WAS NOTED THAT WHITE POWDER WAS PRESENT IN THE CUFF AREA OF THE BLADES. BLADES QTY 2 WERE SENT TO COMPOSITE TECHNOLOGY FOR EVALUATION. BOTH BLADES WERE SCRAPPED DUE TO DEEP CORROSION INSIDE OF UPPER AND LOWER GRIP PLATES. TMay 8, 2006 · Bell 212 · Tail Rotor BladesSDR CA060503001Wire · brokenDURING ROUTINE INSPECTION, THE INDICATOR WAS SHOWING RED INDICATING FILTER BYPASS CONDITION. UPON INVESTIGATION BY AME NONE OF THE FILTERS HAD BYPASSED ON THE INTEGRATED VALVE AND FILTER ASSEMBLY. AT THIS TIME IT WAS DETERMINED THAT THE CLOGGING INDICATOR WAApr 26, 2006 · Bell 212 · Hydraulic Power System WiringSDR EGI2006F00000Line · leakingOIL WAS DISCOVERED LEAKING FROM BELLY OF AC AFT OF AFT CROSSTUBE. INVESTIGATION REVEALED THAT TRANSMISSION PRESSURE OIL LINE TO OIL COOLER HAD CHAFED AGAINST OIL COOLER DRAIN LINE CAUSING A HOLE TO BE CHAFED INTO PRESSURE LINE. OIL COOLER DRAIN LINE IS A STAApr 11, 2006 · N413EV · Bell 412EP · Main Rotor GearboxSDR CA060410008Rod End · damaged(CAN) DURING A SCHEDULED INSPECTION OF THE ROD ENDS, IT WAS NOTED THAT THE BEARING WAS SHOWNING EVIDENCE OF MOVEMENT. BEARING WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060410008)Apr 2, 2006 · Bell 212 · Flight Control SystemSDR CA060601006Detector · failed(CAN) ENGINE OUT LIGHT STAYS ON AFTER ENGINES STARTED. RPM LIGHT INTERMITTENT WITH RPM IN NORMAL OPERATING RANGE.THE RELIABILITY OF THESE UNITS ARE NOT GOOD.IN OUR FLEET OF 4 BELL 212'S WE GO THROUGH 6 RPM BOXES IN 1 SUMMER (TC NR 20060601006)Mar 27, 2006 · Bell 212 · Engine RPM Indicating SystemSDR CA060306006Turbine Blades · damaged(CAN) POWER SECTION WAS RECEIVED FROM THE OPERATOR FOR REPAIR DUE TO HIGH VIBRATION LEVELS. INSPECTION REVEALED THAT THE COMPRESSOR TURBINE BLADES HAD SUFFERED EXTENSIVE DAMAGE. 12 CT BLADES WERE FOUND DAMAGED TO VARYING DEGREES OF THE BLADE SURFACE MISSING. Mar 6, 2006 · Turbine SectionSDR CA060614004Fitting · cracked(CAN) PILOT REPORTED A FORE-AFT KICK IN THE CYCLIC, AT THE SAME TIME THEY HEARD A NOISE. ON ARRIVAL OF THE AC, INSPECTED THE M/R SYSTEM, SWASHPLATE, SCISSORS AND SLEEVE, TRANSMISSION MOUNTS AND NO DAMAGE WAS FOUND. A/C WAS FLOWN AGAIN AND THE PILOT REPORTED ANFeb 24, 2006 · Bell 212 · Main Rotor GearboxSDR 2006FA0000237Debris Monitor · debondedAFTER REMOVAL OF DEBRIS MONITOR FOR 50 HR, CLEAN AND INSP, THE SCAVENGE CUP/SCREEN TUBE ASSY (PN A8858 IS UNSCREWED FROM UNIT. THE O-RING FLANGE RING GLUED ONTO SCREEN TUBE SHEARS OFF OF SCREEN GLUE LINE, AND STAYS IN THE MAIN UNIT. FIX MAYBE TO APPLY GLUE TFeb 17, 2006 · N911KW · Bell 212 · Aircraft Fuel SystemSDR CA060313011Collective Stick · brokenTHE AME WAS MANIPULATING THE COLLECTIVE STICK TO EXPOSE GREASE FITTINGS ON THE SWASHPLATE DURING A ROUTINE SERVICING OPERATION. WHEN THE COLLECTIVE STICK WAS PULLED UP, STICK ASSY DETAIL P/N 212-001-181-001 BROKE AND SEPARATED AT THE SLOT WHERE THE NR 2 THROTFeb 2, 2006 · Bell 212 · Main Rotor ControlSDR CA060104009Shaft · crackedPERFORMED MAGNETIC PARTICLE INSPECTION IAW BHT-ALL-SPM, SHAFT P/N 2660-1635-01 WAS FOUND TO BE CRACKED IN KEY WAY, PART HAS BEEN SUBSEQUENTLY SCRAPED. BELL HELICOPTER HAS BEEN NOTIFIED FOR INTEREST AND INFORMATION ONLY.Jan 4, 2006 · Bell 212 · Engine Oil CoolerSDR AU510001984Nut · crackedFUEL SYSTEM HOSE ASSEMBLY NUT CRACKED ON FLARE FITTING. FUEL LEAKING.Dec 12, 2005 · Bell 412 · Aircraft Fuel Distribution SystemSDR HEEA107314Packing · inoperativeON CLIMB-OUT HEARD A LOUD WHINNING NOISE, HYDRAULIC CAUTION LIGHT CAME ON AND NR 1 HYDRAULIC PRESSURE WENT TO ZERO. STARTED EMERGENCY CHECK LIST AND NOISE STOPPED AND PRESSURE CAME BACK UP. MOMENTS LATER NOISE RETURNED AND PRESSURE DROPPED TO ZERO. MAINTENANov 9, 2005 · N5736J · Bell 212 · Hydraulic System, MainSDR CA051104009Tube · leaking(CAN) THE ENGINE WAS REPORTED TO HAVE FLAMED OUT IN FLIGHT RESULTING IN AN UNSCHEDULED LANDING. SUBSEQUENT INSPECTION REVEALED AN ENGINE FUEL DELIVERY TUBE LEAK. THE ENGINE EXHAUST DUCT WAS ALSO FOUND CRACKED.Oct 24, 2005 · Bell 412 · Engine Fuel DistributionSDR CA051006011Panel · debonded(CAN) DEBONDED BEYOND LIMITS ON LT SIDE BETWEEN STATION 241.22 AND 324.51.Oct 4, 2005 · Bell 212 · Rotorcraft Tail BoomSDR U0GA106181Crossover Tube · brokenDURING NORMAL SHUTDOWN PROCEDURES, THE FORWARD CROSS TUBE BROKE IN HALF CAUSING THE NOSE OF THE AIRCRAFT TO LOWER. NO HARD LANDING WAS REPORTED PRIOR TO THIS FAILURE. INITIAL EXAMINATION OF THE TUBE REVEALS THAT THE TUBE BREAK WAS NOT FRESH. THE ATTACHMENT SASep 27, 2005 · N507EH · Bell 212 · Main Landing Gear Strut/Axle/TruckSDR CA051017009Fuel Heater · unserviceableNR 2 ENGINE FUEL HEATER FOUND TOO HOT TO TOUCH FOLLOWING SHUTDOWN. HEATER REPLACED AND A/C RETURNED TO SERVICE.Sep 9, 2005 · Bell 212 · Fuel HeaterSDR CA051104019Bleed Valve · stuckCOMPRESSOR STALL CAUSED OSCILLATIONS IN AIRFRAME. ENGINE POWER REDUCED TO IDLE. A SINGLE ENGINE LANDING CARRIED OUT IN NEAR BY FIELD. ENGINE REPLACED WITH SERVICEABLE UNIT. IT WAS FOUND TO BE A STUCK CLOSED, BLEEDVALVE AND 3RD STAGE COMPRESSOR BLADE DAMAGEAug 3, 2005 · Bell 212 · Compressor Bleed ValveSDR CA060329005Engine · failedWHILE IN CRUISE, A LOUD BANG WAS HEARD FOLLOWED BY AIRFRAME SHUDDER. AN EMERGENCY WAS DECLARED AND AIRCRAFT STARTED LANDING PROCEDURES. NR 2 ENGINE INDICATING FAILURE AND ROLLED BACK. AIRCRAFT SUCCESSFULLY LANDED IN A FIELD. POWER RECOVERY OF NR 2 ENGINE AAug 1, 2005 · Bell 212 · Turbine Engine Compressor SectionSDR CA060329003Case · brokenWHILE IN CRUISE, A LOUD BANG WAS HEARD AND AC SHUDDERED. AC SETTLED OUT AND CREW DIVERTED TO AIRPORT. INSPECTION OF AC REVEALED MAIN TRANSMISSIOM SUPPORT CASE BROKEN AT DRAG LINK ATTACHMENT POINT. AC GROUNDED AND MAIN TRANSMISSION REPLACED. AC RELEASED BACJul 30, 2005 · Bell 212 · Main Rotor GearboxSDR CA050728010Engine · shutdownTHE ENGINE EXPERIENCED A POWER LOSS IN CRUISE. THE POWER SECTION WAS SHUT DOWN IN FLIGHT. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.Jul 24, 2005 · Bell 212 · Engine (Turbine/Turboprop)SDR CA050826009Fuel Control · malfunctioned(CAN) DURING POST INSPECTION RUN UP, THE NR 2 ENGINE WOULD NOT START. THE AFCU WAS REPLACED AND FURTHER GROUND RUNS CARRIED OUT AND ENGINE STARTED WITH NO FURTHER PROBLEMS. THE AIRCRAFT WAS RETURNED TO THE FLIGHT LINE.Jul 1, 2005 · Bell 212 · Fuel Controlling SystemSDR CA050615001Fitting · cracked(CAN) FITTING FOUND CRACKED AT ATTACHMENT BOLT HOLE. DEFECT FOUND BY NDT TECHNICIAN USING EDDY CURRENT INSPECTION METHOD.Jun 14, 2005 · Bell 212 · Rotorcraft Tail BoomSDR CA050607001Saddle · cracked(CAN) THE RT OUTER SADDLE CRACKED AT THE AFT SPLIT LINE AT THE RIDGE LINE FOLLOWING THE CONTOUR OF THE SKID TUBE AND CROSS TUBE. THE CRACK TURNS 90 DEGREES FROM THE TOP OF THE SADDLE TO THE REAR. THE PART WAS SENT TO HEADQUARTERS FOR INSPECTION.Jun 6, 2005 · Bell 212 · Main Landing Gear Strut/Axle/TruckSDR CA050527033Nut · cracked(CAN) THE M/R HUB WAS IN FOR OVERHAUL, AS PART OF THE OVERHAUL THE ACORN NUTS HAD TOBE NDT. ONE NUT PASSED AND THE OTHER REJECTED. TO CONFIRM THE NDT OF THE ACORN NUT WE SENT IT TO ANOTHER NDT AMO. STRIKE TWO THIS ACORN NUT WAS REJECTED DUE TO A CRACK. THE CRAMay 16, 2005 · Bell 212 · Main Rotor HeadSDR CA050526006Line · failed(CAN) RAPID LOSS OF HYDRAULIC PRESSURE ON GROUND RUN-UP. FOUND TO BE BLOWN FLEX LINE AT BOTTOM FITTING CRIMP RESULTING IN LOSS OF NR 2 HYDRAULIC PRESSURE & FLUID. PROBABLE CAUSE COMBINATION OF TWISTED LINE & TRANSMISSION MOVEMENT CAUSED LINE TO FATIQUE & RUPTMay 16, 2005 · Bell 212 · Hydraulic System, MainSDR CA050527030Compressor · seizedDURING CRUISE, ENGINE TURBINE TEMPERATURE STEADILY INCREASED ACCOMPANIED BY A DECEASE IN COMPRESSOR SPEED. THE CREW SHUT THE ENGINE DOWN IN-FLIGHT AND THE AIRCRAFT WAS DIVERTED. SUBSEQUENT INSPECTION EVIDENCED COMPRESSOR SEIZURE. P&WC WILL INVESTIGATE THE IMay 11, 2005 · Bell 412EP · Turbine Engine Compressor SectionSDR CA050401011Table · wrong part(CAN) MFG 5 MAN SEAT POSITION IS SHOWN AT FS 119. SEAT HAS 2 IN THICK BACK CUSHION AT TRANSMISSION BULKHEAD STA. MM PUTS 5 MAN TROOP SEAT AT FS 117. MIDDLE PASSENGER FOR THAT SEAT CONFIGURATION HAS ITS BACK DIRECTLY AGAINST THE TRANSMISSION BULKHEAD. IT SEEMSApr 1, 2005 · Bell 212 · Passenger Compartment EquipmentSDR CA050228013Engine · unknown(CAN) A/F 18258 HOURS. HELI SKIING OPERATION. PILOT WAS DESCENDING DOWN A HILL AND SETTING UP HIS APPROACH TO LAND HELICOPTER. THE PILOT PULLED IN POWER TO CONTROL HIS DESCENT RATE AND NOTICED THAT THE ENGINES REMAINED IN FLIGHT IDLE. HE CHECKED HIS THROTTLE Feb 24, 2005 · Bell 212 · Engine (Turbine/Turboprop)SDR CA050223007Connector · improper part(CAN) DURING ENGINE VISUAL INSPECTION AT MFG, WE HAVE IDENTIFIED THAT 2 ITEMS FROM THE FUEL PRESSURE TUBING WERE NOT GENUINE AND WERE MANUFACTURED BY AN UNKNOWN SOURCE. THOSE 2 ITEMS HAVE NO IDENTIFICATION NUMBERS BUT WERE INSTALLED IN REPLACEMENT OF: FUEL CONFeb 22, 2005 · Engine Fuel DistributionSDR CA050223006Connector · improper part(CAN) DURING ENGINE VISUAL INSPECTION AT MFG, WE HAVE IDENTIFIED THAT 2 ITEMS FROM THE FUEL PRESSURE TUBING WERE NOT GENUINE AND WERE MANUFACTURED BY AN UNKNOWN SOURCE. THOSE 2 ITEMS HAVE NO IDENTIFICATION NUMBERS BUT WERE INSTALLED IN REPLACEMENT OF: FUEL COFeb 11, 2005 · Engine Fuel DistributionSDR CA050125017Collective Stick · broken(CAN) THE ENGINEER WAS ABOUT TO GREASE THE SWASHPLATE. TO GREASE SOME OF THE ZERK FITTINGS IT IS EASIER TO LIFT THE COLLECTIVE CONTROL STICK UP. THE ENGINEER WAS MOVING THE COLLECTIVE CONTROL STICK UP WHEN THE RIDGED TUBE BENT AND BROKE IN TWO. THE BREAKAGE Jan 25, 2005 · Bell 212 · Main Rotor ControlSDR CA050214002Engine · inoperative(CAN) FOLLOWING FIRST START OF THE DAY THE ENGINE EXPERIENCED AN UNCOMMANDED N2 ACCELERATION. THE PILOT SHUT THE ENGINE DOWN. MFG WILL INVESTIGATE THE EVENT AND WILL SUPPLEMENT THIS REPORT TO PROVIDE ROOT CAUSE, ONCE DETERMINED.Jan 24, 2005 · Engine (Turbine/Turboprop)SDR 2005FA0000413Blade · vibrationON FIRST GROUND RUN, AFTER APPROX 24 HOURS OF HARD RAIN, THE HELICOPTER DEVELOPED A SEVERE VIBRATION. THE VIBRATION WAS TRACED TO A TAIL ROTOR BLADE. SUSPECT BLADE COLLECTED THE RAIN WATER. THE BLADE WAS SCRAPPED IAW THE MM. (K)Jan 11, 2005 · N304FD · Bell 412EP · Tail Rotor BladesSDR CA050110003Coupling · corroded(CAN) DURING SCHEDULED INSPECTION PITTING CORROSION IN EXCESS OF .005 INCH HAS BEEN DISCOVERED. THE PATTERN AND LOCATION OF CORROSION PITTING CONFORMS TO PROCESS STAMP IMPRESSION (186). IT IS LIKELY THAT IMPROPER INK HAS BEEN USED DURING SHAFT OVERHAUL. OVEJan 5, 2005 · Bell 212 · Engine/Transmission CouplingSDR CA041213003Tube · wrong part(CAN) DURING ENGINE VISUAL INSPECTION AT MFG, HAVE IDENTIFIED THAT 2 ITEMS FROM THE FUEL PRESSURE TUBING WERE NOT GENUINE AND WERE MANUFACTURED BY AN UNKNOWN SOURCE. THOSE 2 ITEMS HAVE NO IDENTIFICATION NUMBERS BUT WERE INSTALLED IN REPLACEMENT OF: FUEL CONNECDec 13, 2004 · Miscellaneous HardwareSDR 2005FA0000160Ring Gear · damagedRING GEAR DAMAGED.Nov 1, 2004 · N827MW · Skrsky S58JT · Main Rotor GearboxSDR CA041007008Control Tube · cracked(CAN) WE ARE PRESENTLY DOING A 3000 HOUR AIRFRAME INSPECTION. THIS VERTICAL UPPER SERVO CONTROL TUBE WAS SENT TO A NDT SHOP FOR INSPECTION. THE NDT SHOP STATED THAT THEIR WAS A LONGDITUDANAL CRACK ON THE UPPER END OF CONTROL TUBE. SINCE THE LAST INSPECTION TOct 7, 2004 · Bell 212 · Main Rotor ControlSDR CA040901008Panel · cracked(CAN) DURING ROUTINE INSPECTION AME DISCOVERED A CRACK SURROUNDING ELEVATOR CONTROL SUPPORT (P/N 205-001-920-001) IN A FWD AND AFT SKIN OF TAILBOOM PANEL (205-032-819-3). PANEL REPLACED, A/C RETURNED TO SERVICE.Sep 29, 2004 · Bell 212 · Rotorcraft Tail BoomSDR CA041109008Wire · arced(CAN) FUEL QUANTITY REPORTED AS FLUCTUATING. DURING TROUBLESHOOTING PROCESS ONE OF THE WIRES ON THE RT TANK FORWARD FUEL PROBE WAS FOUND ARCING. PROBE REPLACED.Sep 27, 2004 · Bell 212 · Fuel System WiringSDR 21200003EAIBearing · failedDURING FIRST GROUND RUN AFTER INSTALLATION OF AIRCOM CABIN AIR CONDITIONING SYSTEM (P/N 412AC-106-2 - STC SR00066DE) A MECHANIC INSPECTING THE SYSTEM NOTICED THE IDLER PULLY ON P/N 412AC-3036-1 SHAFT ASSEMBLY WAS NO LONGER IN ALIGNMENT WITH THE MAIN DRIVE PULLSep 23, 2004 · Bell 412EP · Cabin Cooling SystemSDR CA040910002Hose · burstBEFORE FIRST FLIGHT DURING HYDRAULIC TESTING, PILOT SWITCHED 'OFF' NR 2 HYDRAULIC SYSTEM. AFTER THE SYSTEM WAS SWITCHED BACK 'ON' PRESSURE INDICATION FELL OFF TOZERO. A/C WAS SHUTDOWN. SUBSEQUENT INSPECTION REVEALED THAT THE BRAIDED NR 2 HYDRAULIC HOSE FROMAug 24, 2004 · Bell 212 · Hydraulic System, MainSDR KHS2004F00000O-Ring · cutNR 1 HYD SYSTEM ACCUMULATOR O-RING (PN MS28775-212) FAILURE, CAUSING LOSS OF HYDRAULIC FLUID IN THAT SYSTEM. NR 1 SYSTEM WAS SHUT OFF AND AIRCRAFT RETURNED TO AIRPORT ON NR 2 SYSTEM WITH NO FURTHER INCIDENT. NR 1 HYDRAULIC ACCUMULATOR O-RING, (PNMS28775212).Aug 23, 2004 · N144WA · Bell 212 · Hydraulic Power Accumulator, MainSDR CA040831005Engine · failed(CAN) DURING HIGH HOVER (LONG LINE) TO PICK UP LOAD, NR1 POWER SECTION FAILED. INITIAL COMPRESSOR INLET INSPECTION (PLENUM AREA) REVEALED MOLTEN PARTICLES. FURTHER INVESTIGATION ON POWER SECTION REMOVAL/TEARDOWN INSPECTION.Aug 19, 2004 · Bell 212 · Engine (Turbine/Turboprop)SDR CA040908005Turbine · failedDURING HIGH HOVER (LONG LINE) TO PICK UP LOAD, NR 1 POWER SECTION FAILED. INITIAL COMPRESSOR INLET INSPECTION (PLENUM AREA) REVEALED MOLTEN PARTICLES. FURTHER INVESTIGATION WILL COMMENCE ON POWER SECTIONREMOVAL/TEARDOWN INSPECTION. (ALTSN-6421.0).Aug 19, 2004 · Bell 212 · Turbine Section
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