Bell 205A-1

Service difficulty reports · 232

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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 aircraft_model_key = '205A1'
  ORDER BY difficulty_date DESC"

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SDR CA050816006Mount · cracked(CAN) THE ENGINE MOUNT WAS MODIFIED BY STC SH99-11 WHICH ALLOWS THE MOUNT TO BECOME ADJUSTABLE. THE ADJUSTABLE PORTION OF THE MOUNT IS RIVETED TO ONE LEG AND IT CRACKED FROM ONE OF RIVET HOLES SECURING THE ADJUSTABLE TURNBARREL TO THE MOUNT LEG.Aug 12, 2005 · Bell 205A1 · Engine Mount SectionSDR CA050816005Mount · cracked(CAN) THE ENGINE MOUNT WAS MODIFIED BY STC SH99-11 WHICH ALLOWS THE MOUNT TO BECOME ADJUSTABLE. THE ADJUSTABLE PORTION OF THE MOUNT IS RIVETED TO ONE LEG AND IT CRACKED FROM ONE OF RIVET HOLES SECURING THE ADJUSTABLE TURN BARREL TO THE MOUNT LEG.Aug 12, 2005 · Bell 205A1 · Engine Mount SectionSDR CA040821001Spherical Bearin · failed(CAN) A/C WAS CLIMBING AFTER FILLING THE WATER BUCKET WHEN HE LOST COMPLETE TAIL ROTORAUTHORITY.THE A/C MADE SEVERAL 360 DEGREE TURNS AFTER COMING TO REST IN A CON FINED AREA. SUBSTANTIAL DAMAGE WAS DONE TOTHE MAIN ROTOR BLADES AS THEY STRUCK A TREE UPON LANDIAug 20, 2004 · Bell 205A1 · Tail Rotor HeadSDR 2004FA0000148Fitting · damagedUPON OPENING PACKED FOR FITTING ASSEMBLY FOUND THREADS ON LONG SIDE OF FITTING PULLED LOOSE. PART REJECTED BEFORE INSTALLATION.Jan 9, 2004 · N4750R · Bell 205A1 · Engine Mount SectionSDR CA040128006Pump · worn(CAN) FUEL CONTROL P/N 1-170-240-93, S/N 5ADS1907 WAS RECEIVED DUE TO DAMAGED MAIN DRIVE SHAFT SPLINE. DISASSEMBLED AND INSPECTED FCU AND FOUND DAMAGED PUMP ASSEMBLY. RECORD OF INSPECTION IAW SB73-39. FCU S 91 AND 93 HAVE TIP SEAL PUMP, AND THEY CAN BE INSDec 28, 2003 · Bell 205A1 · Fuel Control/Reciprocating EnginesSDR CA040127014Pump · failed(CAN) WHILE HELICOPTER WAS CONDUCTING AERIAL LIFT WORK THE PILOT NOTED THE ENGINE FUEL PUMP LIGHT CAME ON. HE RETURNED TO THE STAGING AREA AND LANDED UNEVENTFULLY. THROUGH TROUBLESHOOTING ON THE GROUND IT WAS DISCOVERED THAT ONE ELEMENT OF A DUAL ELEMENT PUMPDec 28, 2003 · Bell 205A1 · Fuel Control/Reciprocating EnginesSDR CA040204006Fuel Control · failed(CAN) ENGINE STOPPED IN-FLIGHT.Sep 11, 2003 · Bell 205A1 · Fuel Controlling SystemSDR CA030915008Boot · torn(CAN) DURING THE INSPECTION AFTER THE LAST FLIGHT OF THE DAY, THE ENGINEER INSPECTED THE MAIN DRIVESHAFT BOOTS FOR LEAKAGE. THERE WAS NO VISUAL SIGN OF A GREASE LEAKAGE. AS THE ENGINEER PUT HIS HAND UNDER THE, ENGINE SIDE, DRIVESHAFT COUPLING, HE FELT A BUILTSep 7, 2003 · Bell 205A1 · Engine/Transmission CouplingSDR CA031001006Fitting · cracked(CAN) PART REMOVED FROM SERVICE.NEW PART INSTALLED.Aug 25, 2003 · Bell 205A1 · Fuselage Main, Attach FittingsSDR CA030912003Gear · failed(CAN) A/C PERFORMING NORMAL APPROACH. DURING FINAL, A LIGHT WHINING SOUND HEARD AS POWER APPLIED. AS POWER INCREASED, SOUND INCREASED. AT APPROX 8 FT FROM TOUCHDOWN, ENG STOPPED, & CHIP CAUTION LIGHT ILLUMINATED. CONTROL MAINTAINED HELICOPTER LANDED WITHOUT INJul 28, 2003 · Bell 205A1 · Accessory GearboxesSDR FZO2003F00000Drive Shaft · chafedPILOT FELT HARMONIC VIBRATION DURING REDUCE POWER DECENT INTO DIP SITE. FOUND T/R DRIVE SHAFT PN 204-040-623-011 RUBBING ON 205-060-923-001 BOOT ASSY. BOOT SEAL ECE-300-3/3 OIL SOAKED AND DEBONDED FROM BOOT LETTING BOOT SIDE. DOWN AND AMAKING CONTACT WITH TJul 18, 2003 · N6288Y · Bell 205A1 · Tail Rotor Drive ShaftSDR CA030910004Spar Cap · cracked(CAN) WHILE DOING A ROUTINE INSPECTION, A 15 INCH CRACK WAS FOUND IN THE ENGINE DECK AT ITS FORWARD END UNDER THE TRANSMISSION TAIL ROTOR OUTPUT AREA. FURTHER INVESTIGATION WAS CARRIED OUT AND FOUND THAT THE SPAR CAP WAS CRACKED. UPON DISSAMBLY FOR THE CAP REPJul 17, 2003 · Bell 205A1 · Fuselage Miscellaneous StructureSDR AUS20030596Compressor · fod(AUS) ENGINE VARIABLE INLET GUIDE VANES (VIGV) AND COMPRESSOR BLADES DAMAGED BY FOD. INVESTIGATION FOUND THAT DAMAGE HAD BEEN CAUSED BY AN OBJECT WITH A DIAMETER OF APPROXIMATELY 3.175MM TO 4.762MM(0.125IN TO 0.1875IN). AN OBJECT OF THIS SIZE COULD NOT PASS Apr 3, 2003 · Bell 205A1 · Turbine Engine Compressor SectionSDR CA030404003Case · cracked(CAN) NOTICED SMALL AMOUNT OF HYDRAULIC FLUID ON HYDRAULIC PUMP CASE. THOUGHT IT WAS LOOSE BUT WAS NOT. REMOVED LINE ATTACHED TO IT AND FOUND SMALL CRACK.Apr 3, 2003 · Bell 205A1 · Hydraulic Pump (Electric/Engine), MainSDR CA021203011Sun Gear · spalled(CAN) TRANSMISSION REMOVED FOR METAL CONTAMINATION SUN GEAR FOUND DAMAGED ON INSPECTION.Dec 2, 2002 · Bell 205A1 · Main Rotor GearboxSDR CA021119002Drive Shaft · scored(CAN) WHILE DOING A 100 HOUR INSPECTION ON THE BELL 205A-1, THE TAIL ROTOR DRIVE SHAFT ASSEMBLY WAS FOUND SCORED BEYOND LIMITS. THE INSPECTION IS A CLEARANCE CHECK BETWEEN THE T/R DRIVE SHAFT COVER AND THE T/R DRIVE SHAFT. THIS CLEARANCE CHECK IS DUE TO POSSINov 1, 2002 · Bell 205A1 · Tail Rotor Drive ShaftSDR CA021001010Drive Shaft · chafed(CAN) AT TIME OF RE-GREASING THE T/R DRIVESHAFT COUPLINGS. T/R DRIVESHAFT WAS REMOVED FROM TUNNEL UNDER ENGINE. FOUND CONTACT WAS MADE WITH TUNNEL AT ENTRANCE DIRECTLY AFT OF TRANSMISSION. SHAFT IS OF NEWER STYLE -011 WHICH IS OF A GREATER DIAMETER THAN THAT OSep 20, 2002 · Bell 205A1 · Tail Rotor Drive ShaftSDR CA021007007Hanger Assy · cracked(CAN) HANGER CRACKED AT BOTH ATTACH POINTS FOR THE FLEX COUPLING ATTACH.Sep 18, 2002 · Bell 205A1 · Tail Rotor Drive ShaftSDR CA020918004Longeron · cracked(CAN) WHILE AIRCRAFT WAS IN THE HANGAR FOR SCHEDULED MAINTENANCE, IT WAS NOTED THAT THERE WAS MOVEMENT OF THE TAILBOOM SKIN AND NO MOVEMENT OF FITTING WHEN THE TAILBOOM WAS MANUALLY FLEXED. FURTHER INVESTIGATION REVEALED THE LOWER FITTING OF THE LONGERON WAS CAug 30, 2002 · Bell 205A1 · Rotorcraft Tail BoomSDR CA021001002Bearing · cracked(CAN) FOUND A CRACK (ON A DAILY CHECK) ON THE NR 1 TAILBOOM TAIL ROTOR DRIVE SHAFT BEARING SUPPORT, AS INDICATED IN THE DRAWING SENT. THE SUPPORT POSITIONS THE T/R DRIVE SHAFT BEARING HANGAR. THE T/R BEARING HANGAR IS REMOVED EVERY 6 MONTHS OR 600 HOURS. THIS Aug 18, 2002 · Bell 205A1 · Tail Rotor Drive ShaftSDR EHA2002F00002Circuit Breaker · failedRIGHT FUEL BOOST PUMP INOPERATIVE. REPLACED CIRCUIT BREAKER.Jul 21, 2002 · N4750R · Bell 205A1 · Fuel Boost PumpSDR EHA2002F00006Pressure Switch · intermittentMAIN TRANSMISSION OIL PRESSURE SWITCH LIGHT INTERMITTNETLY INOPERATIVE. REPLACED PRESSURE SWITCH.Jul 18, 2002 · N4750R · Bell 205A1 · Main Rotor GearboxSDR CA020729002Indicator · failed(CAN) FROM REPORTS: THE AIRCRAFT WAS HOVERING WITH A WATER BUCKET OVER A FIRE. ROTOR SPEED DECAYED AND PILOT MADE A FORCED LANDING IN A CLEARING. THE AIRCRAFT LANDED VERY HARD AND ROLLED ON TO ITS RIGHT SIDE. PILOT CRAWLED OUT AND SUSTAINED MINOR INJURIES. THEJul 11, 2002 · Bell 205A1 · Main Rotor Indicating SystemSDR CA020918008Engine · flamed out(CAN) DURING ROUTINE FLIGHT AFTER FUELING FROM A SUPPLIED SEALED DRUM OF PRE-MIXED JET FUEL (FSII) ADDED. THE ENGINE FLAMED OUT AND A FORCED LANDING RESULTING IN NO DAMAGE TO THE HELICOPTER.Jul 10, 2002 · Bell 205A1 · Engine (Turbine/Turboprop)SDR AUS20020899Bolt · cracked(AUS) MAIN ROTOR BLADE BOLT SUSPECT CRACKED. FOUND DURING FLUORESCENT MAGNETIC PARTICLE INSPECTION.Jul 9, 2002 · Bell 205A1 · Main Rotor HeadSDR CA020726017Blade · bent(CAN) THE LT WING TIP OF A CL-415 WATER BOMBER CONTACTED THE FORWARD ROTOR BLADE OF THE 205. THE 205 WAS PARKED AND TIED DOWN. THE CL-415 WAS DESCRIBED AS TRAVELLING AT A "SLOW TAXI SPEED". ONE BLADE SUSTAINED MINOR DAMAGE (REPAIRABLE) AT TIP. NO OTHER DAMAGE Jul 1, 2002 · Bell 205A1 · Main Rotor BladesSDR CA020627007Fuel Cell · contaminated(CAN) CRYSTALS WERE FOUND IN THE FUEL CELL WHILE IT WAS FIRE-FIGHTING HOUSE LAKE FIRE. THE CRYSTALS WERE FOUND DUE TO A BLOCKED EJECTOR PUMP. SOURCE OF THE CRYSTALS IN UNKNOWN. A SAMPLE OF THE CRYSTALS WAS PROVIDED FOR ANALYSIS. IT WAS DETERMINED THAT THE Jun 20, 2002 · Bell 205A1 · Aircraft Fuel Distribution SystemSDR GAK2002F00000Wire Harness · meltedDEPARTED AIRPORT ABOUT 1415 HOURS. AFTER A NORMAL START PROCEDURE AND RUN-UP A DEPARTURE WAS MADE TO AIRPORT. ABOUT 10 MINUTE INTO THE FLIGHT, ACRID SMELL WAS NOTICED. SCANNED THE INSTRUMENT PANEL ALL INSTRUMENTS WERE IN THE GREEN. THERE WERE NO CAUTION LIJun 7, 2002 · N205BD · Bell 205A1 · Starter-GeneratorSDR 2002F00639Wire Harness · burnedSERVICE ABOUT 1415 HOURS. AFTER A NORMAL START PROCEDURE AND RUN-UP A DEPARTURE WAS MADE. ABOUT 10 MINUTES INTO FLIGHT, ACID SMELL WAS NOTICED. SCANNED THE INSTRUMENT PANEL ALL INSTRUMENTS WERE IN THE GREEN THERE WERE NO CAUTION LIGHTS. MASTER CAUTION LIGHJun 7, 2002 · N205BD · Bell 205A1 · Electrical Power System WiringSDR CA020619007Bearing · failed(CAN) WHEN TURNING FREEWHEEL ROUGHNESS WAS DETECTED, FURTHER INVESTIGATION REEALED A CLICKING NOISE. THE MAIN ROTOR TRANS. INPUT ADAPTER FREEWHEEL UNIT WAS REMOVED. THE FREEWHEEL UNIT WAS DISASSEMBLED, A BEARING THAT SUPPORTS THE INNER/OUTER COUPLING WAS DETERJun 6, 2002 · Bell 205A1 · Engine/Transmission CouplingSDR CA020607007Engine · failed(CAN) A/C WAS IN PROGRESS OF FIREFIGHTING WHEN ENGINE 'FIRE WARNING' ILLUMINATED. AFTER VERIFYING FIRE VIBRATION, PILOT DECIDED TO CARRY OUT AN EMERG LDG. ON DESCENT FROM AP PROX 150 FEET, ENGINE CHIP LIGHT CAME ON AS WELL AS ENGINE OIL LOW PRESSURE WARNING LIJun 2, 2002 · Bell 205A1 · Engine (Turbine/Turboprop)SDR CA020611003Valve Seat · failed(CAN) DURING THE SCHEDULED 25 HOUR INSPECTION THE AME NOTED THAT THE VALVE SEAT HAD UNSCREWED ITSELF FROM THE FILTER BODY AND DAMAGED THE FILTER, WAFER. THE VALVE SEAT WAS SECURED AND THE FILTER, WAFER WAS REPLACED.May 30, 2002 · Bell 205A1 · Main Rotor GearboxSDR CA020530002Bleed Band · out of adjust(CAN) WHILE WATER BUCKETING A COMPRESSOR STALL OCCURRED. THE PILOT HOVER TAXIED WITH REDUCED POWER TO THE SHORELINE. AT THE SHORELINE HE DROPPED HIS LOAD AND THE AIRCRAFT WAS RETURNED BACK TO STAGING AREA AND A NORMAL ENGINE SHUTDOWN WAS CARRIED OUT. AFTER TMay 26, 2002 · Bell 205A1 · Engine Bleed Air SystemSDR CA020507009Mount · cracked(CAN) DURING MAIN ROTOR TRANSMISSION REMOVAL FOUND CRACK EXTENDING FROM LOWER MOST BOLT HOLE OF 5TH MOUNT ATTACHMENT ANGLE, RT SIDE OF TRANSMISSION PYLON AREA.CRACK REPAIRED I.A.W. THE BELL MEDIUM STRUCTURAL REPAIR MANUAL (BHT-MED-SRM-1) SECTION 4-6-3, "MAIN BApr 30, 2002 · Bell 205A1 · Main Rotor GearboxSDR CA020507010Beam · cracked(CAN) SMALL CRACK FOUND ON TOP "T" CAP OF LT VERTICAL MAIN BEAM ASSEMBLY. CRACK WAS OBSERVED WERE "T" CAP TRANSITIONS FROM UNDER THE ENGINE DECK GOING FORWARD THROUGH THE AFT SIDE OF THE MAIN ROTOR PYLON AREA.NEW "T" CAP INSTALLED IAW BELL MEDIUM STRUCTURAL REApr 17, 2002 · Bell 205A1 · Fuselage Miscellaneous StructureSDR CA020501002Fitting · cracked(CAN) CRACK FOUND AT BOTTOM OF BEAM (FITTING HOUSING) WHERE 5TH MOUNT IS HOUSED, 3/4 INCH LONG. BELL MAINTENANCE MANUAL SPECIFIES NO CRACKS IN THIS AREA.Apr 11, 2002 · Bell 205A1 · Main Rotor Transmission MountSDR CA020306005Barrel · cracked(CAN) NDT REVEALED A 1.5 INCH CRACK ON THE INTERIOR OF THE COARSE THREADED END. THE CRACK IS NOT VISIBLE ON THE EXTERIOR.Mar 5, 2002 · Bell 205A1 · Main Rotor HeadSDR CA030610003Tube · cracked(CAN) THE TUBE ASSEMBLY WAS REMOVED DURING A NORMAL INSPECTION AND FOUND TO HAVE EXCESSIVE WEAR ON THE SEAL JOURNAL. THE TUBE WAS SENT TO A REPAIR STATION TO HAVE THE JOURNAL REPLATED IAW TB 205-91-89. THE TUBE WAS INSPECTED BY MAGNETIC PARTICAL INSPECTION Mar 1, 2002 · Bell 205A1 · Tail Rotor GearboxSDR CA020226001Cover · cracked(CAN) DURING THE DAILY INSPECTOIN, DAMAGE TO THE M/R BLADE WAS NOTICED. INSPECTION OF THE AIRCRAFT REVEALED THAT THE COVER, EXHAUST DIFFUSER, HELD BY A SPEC. BOLT AND TABWASHER ON THE COVER, TURB., REAR WAS MISSING. THE BOLT & TABWASHER WHERE STILL IN PLACFeb 2, 2002 · Bell 205A1 · Engine Collector/Tailpipe/NozzleSDR CA020213014Case · cracked(CAN) THE LIFT LINK BEARING BOSS WAS FOUND CRACKED DURING ROUTINE MAINTENANCE.Feb 2, 2002 · Bell 205A1 · Main Rotor GearboxSDR GDM2002F00000Connector · fireLANDED, PROCEEDED WITH NORMAL SHUTDOWN PROCEDURES. DURING TWO-MINUTE SHUTDOWN, NOTICED GENERATOR CYCLING ON AND OFF, FIRE LIGHT ILLUMINATED MOMENTARILY THEN WENT OUT. FIRE LIGHT CAME ON AGAIN WITH MORE GENERATOR CYCLING. EXITED HELICOPTER WITH ENGINE AT FLINov 13, 2001 · N28HJ · Bell 205A1 · Electrical Power System WiringSDR CA011012003Cap · cracked(CAN) ON A TURN AROUND CHECK AFTER REFUELING THE AIRCRAFT, AN ENGINEER FOUND A CRACK ON THE EXPOSED SIDE OF THE LEFT BEAM CAP THAT IS LOCATED NEAR THE FORWARD VERTICAL WALL.Oct 2, 2001 · Bell 205A1 · Fuselage Miscellaneous StructureSDR CA010921005O-Ring · split(CAN) O-RING ON ACCUMULATOR SPLIT CAUSING HYDRAULIC FLUID LOSS. SUBSEQUENTLY THE PILOT TURNED THE #2 HYDRAULIC SYSTEM OFF AND LANDED THE AIRCRAFT. FURTHER INVESTIGATION REVEALED THAT THE #2 HYDRAULIC RESERVOIR WAS COMPLETELY DRY. THE ACCUMULTOR WAS DISASSEMBLESep 2, 2001 · Bell 205A1 · Hydraulic System, MainSDR CA010724015Bearing · worn(CAN) WHILE PERFORMING REGULAR MAINTENANCE (DAILY INSPECTION) EXCESSIVE PLAY WAS OBSERVED IN THE M/R DAMPER RODEND ON ONE OF THE DAMPER ASSEBLIES. FURTHER INVESTIGATION REVEALED THAT THE TEFLON LINER (APPROX. 50%) WAS EXTRUDING FROM THE BEARING. THE BEARING WAJul 8, 2001 · Bell 205A1 · Main Rotor HeadSDR CA010711005Link · broken(CAN) WHILE TRACKING & BALANCING THE MAIN ROTOR SYS THE PILOT & ENGINEER COULD FEEL AN UNUSUAL VERTICAL VIBS,ON THE NEXT FLIGHT UNUSUAL LATERAL VIBS,ENGINEER MADE ADJUSTMENT TO M/R SYS BUT THE READING ONTHEEQUIPMENT STILL READ ROUGH.WHILE RUNNING ON THE GROUNDJul 6, 2001 · Bell 205A1 · Main Rotor GearboxSDR CA010727001Turbine · cracked(CAN) VIBRATION ON BLOWER ASSY. EXAMINE BLOWER ASSY & FOUND TWO CRACKS ON THE ROOT OF TWO BLADE.Jul 4, 2001 · Bell 205A1 · Tail Rotor Drive ShaftSDR CA010703034Bearing · broken(CAN) ENGINE CHIP LT CAME ON. METAL CHIPS WERE FOUND IN CHIP PLUG & FILTER. REPLACED ENGINE. INVESTIGATION SHOWS BEARING P/N 1-300-004-05 CAGE WAS BROKEN & INNER/ OUTER RACE BEARING SURFACE HAD FLAKE DAMAGE.Jun 17, 2001 · Bell 205A1 · Turbine Engine Reduction GearSDR GDMA073295Bearing · roughMEDIUM FREQ VIBRATION IN THE AIRFRAME. REPLACED BEARINGS IN THE FANJun 12, 2001 · N97HJ · Bell 205A1 · Engine Oil Storage (Airframe Furnished)SDR CA001013033Line · chafed(CAN) NR 1 HYDRAULIC SYSTEM RETURN LINE WAS CHAFED WITH NR 2 PUMP PRESSURE LINE, REPLACED. THIS TUBE ASSEMBLY WAS INSTALLED 293.1 HOURS BEFORE.FOUND PRESSURE LINE WAS ROUTED OTHER SIDE OF NR 2 PUMP.Sep 29, 2000 · Bell 205A1 · Hydraulic System, MainSDR CA001013032Lever · failed(CAN) PIN PRESSED INTO ASSEMBLY CAME LOOSE. FOUND WHEN SWASHPLATE ASSY CHANGE.Sep 13, 2000 · Bell 205A1 · Main Rotor Control
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