# Service difficulty reports: Bell 205A-1 A list on [Bell 205A-1](https://openairdocs.org/model/bell-205a-1.md). Newest first. General aviation reporting is voluntary. Page 1 of 5 · 232 reports - [SDR H4QA20260619001](https://openairdocs.org/sdr/H4QA20260619001.md): Relay · failed · Jun 16, 2026 · N3804C · Bell 205A1 · Electrical Power System Wiring > ENROUTE TO A DIP SITE FOR ANOTHER BUCKET OF WATER THE PILOT SMELLED ELECTRICAL SMOKE IN THE CABIN OF THE AIRCRAFT. ODOR WAS IMMEDIATELY FOLLOWED BY SMOKE COMING FROM UNDER THE CENTER CONSOLE WHICH FILLED THE HELICOPTER CABIN. THE PILOT CALLED IN A MAYDAY OVER - [SDR 2022F00378](https://openairdocs.org/sdr/2022F00378.md): Hose · ruptured · Oct 3, 2022 · N456TA · Bell 205A1 · Hydraulic System, Main > AT APPROXIMATELY 10501.9 ACTT ON 9-29-22 AT 1530 PM I WAS TOLD THAT THERE HAD BEEN A HYDRAULIC SYSTEM 2 FAILURE ON N456TA. THE PILOT LANDED WITHOUT INCIDENT. AFTER SHUTDOWN I INVESTIGATED THE PROBLEM AND FOUND THAT THE #2 SYSTEM WAS ALMOST COMPLETELY EMPTY O - [SDR NKVA2025011500013](https://openairdocs.org/sdr/NKVA2025011500013.md): Swashplate · cracked · Oct 13, 2021 · N205PT · Bell 205A1 · Main Rotor Gearbox > A TECHNICIAN REPORTED THAT DURING HIS DAILY INSPECTION HE FELT SOME "LOOSENESS" IN THE SWASHPLATE THAT HE HAD NOT NOTICE ON PRIOR DAILY INSPECTIONS. HE INVESTIGATED FURTHER AND FOUND THAT THE SWASHPLATE INNER RING WAS CRACKED AT THE GIMBAL ATTACHMENT LUG. THE - [SDR 2021FA0000284](https://openairdocs.org/sdr/2021FA0000284.md): Swashplate · cracked · Oct 13, 2021 · N205PT · Bell 205A1 · Main Rotor Mast/Swashplate > A TECHNICIAN REPORTED THAT DURING HIS DAILY INSPECTION HE FELT SOME "LOOSENESS" IN THE SWASHPLATE THAT HE HAD NOT NOTICED ON PRIOR DAILY INSPECTIONS. HE INVESTIGATED FURTHER AND FOUND THAT THE SWASHPLATE INNER RING WAS CRACKED AT THE GIMBAL ATTACHMENT LUG. T - [SDR H4QA202007230001](https://openairdocs.org/sdr/H4QA202007230001.md): Crosstube · broken · Jul 20, 2020 · N205HQ · Bell 205A1 · Main Landing Gear > REAR AFT CROSSTUBE FAILED WHILE AIRCRAFT WAS NOT RUNNING. CREW WANTED TO FILL BELLY TANK WITH WATER AND MARK NUMBER OF GALLONS, DURING FILLING OPERATIONS FROM WATER TENDER, REAR CROSSTUBE FAILED, BREAKING IN HALF, CAUSING HELICOPTER TO SETTLE ON ISOLAIR BELLY - [SDR LJEA2020061600001](https://openairdocs.org/sdr/LJEA2020061600001.md): Gearbox · cracked · Jun 11, 2020 · N205RH · Bell 205A1 · Main Rotor Gearbox > MAIN GEARBOX CASE CRACKED IN WEBBING ABOVE INPUT QUILL. FERRY PERMIT REQUESTED TO RELOCATE AIRCRAFT TO A LOCATION FOR MAINTENANCE. - [SDR 2020F00078](https://openairdocs.org/sdr/2020F00078.md): Gearbox · cracked · Nov 20, 2019 · N304HA · Bell 205A1 · Main Rotor Gearbox > CRACK SUSPECTED IN MAIN GEARBOX CASE ABOVE INPUT QUILL PURSUANT TO GUIDANCE FROM BELL HELICOPTERS IN BELL 205 CR&O FIG 66-37. CRACK APPEARS TO EXTEND THROUGH WEB IN AREA IDENTIFIED. CONTACTED BELL & RECEIVED LETTER OF NO TECHNICAL OBJECTION FOR A ONE TIME FERR - [SDR 2016FA0000387](https://openairdocs.org/sdr/2016FA0000387.md): Fire Detector · failed · Aug 23, 2016 · N932CH · Bell 205A1 · Fire Detection > ENROUTE TO A FIRE, FIRE LIGHT CAME ON. NO SMOKE WAS DETECTED. LANDED AIRCRAFT BACK AT BASE. MECHANIC TROUBLESHOT THE SYSTEM AND FOUND BAD FIRE SENSOR PROBE IN ENGINE COMPARTMENT. CHANGED PROBE. - [SDR HEAA2016012501](https://openairdocs.org/sdr/HEAA2016012501.md): Crosstube · cracked · Jan 25, 2016 · N28HJ · Bell 205A1 · Main Landing Gear > DURING ROUTINE WINTER MAINTENANCE, AN INSPECTION OF THE LANDING GEAR CROSSTUBES WERE ACCOMPLISHED IAW THE MFG 300 HOUR INSPECTION. ONE OF THE SADDLES FOR THE ATTACHMENT OF SKID GEAR TO THE FUSELAGE WAS FOUND DEBONDED ON THE CROSSTUBE. ICA INSTRUCTIONS CALL FO - [SDR H4QA20151028559](https://openairdocs.org/sdr/H4QA20151028559.md): Support · bent · Oct 27, 2015 · N502HQ · Bell 205A1 · Main Rotor Mast/Swashplate > DURING SCHEDULED MX IT WAS DISCOVERED THAT A BEARING WOULD NOT FIT BETWEEN THE MOUNTING LUGS OF THE SWASHPLATE SUPPORT, PN 204-011-404-125, SN RE18039. THE SWASHPLATE SUPPORT LUGS WERE DIMENSIONALLY CHECKED & ENGINEERING CONTACTED. THE DIMENSIONAL CHECK REVE - [SDR CA150929013](https://openairdocs.org/sdr/CA150929013.md): Shaft · sheared · Sep 25, 2015 · Bell 205A1 · Starter-Generator > (CAN) STARTER GENERATOR SHAFT SHEARED IN FLIGHT UNDER NORMAL LOADS CAUSING LOSS OF DC POWER GENERATION. ACFT RETURNED TO BASE UNEVENTFULLY. - [SDR 2015FA0000355](https://openairdocs.org/sdr/2015FA0000355.md): Connector · burned · Jul 28, 2015 · N66HJ · Bell 205A1 · Electrical Power System Wiring > PILOT REPORTED BURNED PLASTIC ODOR FROM ENGINE COMPARTMENT. MECHANIC INSPECTED ENGINE COMPARTMENT AND FOUND A BURNED AREA ON THE STARTER/GENERATOR CONNECTOR PLUG BACKSHELL. REPLACED THE STARTER AND THE HARNESS FROM THE STARTER/GENERATOR TO THE ENGINE DECK. - [SDR CA150713024](https://openairdocs.org/sdr/CA150713024.md): Hydraulic Line · ruptured · Jul 11, 2015 · Bell 205A1 · Hydraulic System, Main > (CAN) DURING FLIGHT THE PILOT EXPERIENCED A LOSS OF NR 2 HYD PRESS. PILOT RETURN TO THE BASE AFTER ISOLATING THE SYS. ONCE THE ACFT LANDED SAFELY, THE INVESTIGATION REVEALED THE LINE TO THE PRESS SIDE OF HYD PUMP NR 2 HAD RUPTURED AT THE 90 DEGREE FITTING. - [SDR CA150421003](https://openairdocs.org/sdr/CA150421003.md): Blade · damaged · Apr 18, 2015 · Bell 205A1 · Turbine Section > (CAN) DURING A MAINTENANCE FLIGHT CHECKING MAIN ROTOR SYS TRACK AND BALANCE, THE ACFT WAS INCREASING AIRSPEED FROM 60 KNOTS TO 100 KNOTS. A LOUD BANG WAS HEARD IN THE CABIN, THE ACFT POWER WAS ROLLED OFF & THE ACFT WAS PUT INTO AN AUTOROTATION DESCENT. DURIN - [SDR CA150316004](https://openairdocs.org/sdr/CA150316004.md): Blade · cracked · Mar 15, 2015 · Bell 205A1 · Turbine Engine Compressor Section > (CAN) DURING INSPECTION OF ACFT BLOWER FAN, IT WAS NOTED THAT 4 OF THE FAN BLADES WERE CRACKED AT THE BASE. - [SDR CA150225006](https://openairdocs.org/sdr/CA150225006.md): Shield · leaking · Feb 23, 2015 · Bell 205A1 · Tail Rotor Drive System > (CAN) DURING DAILY INSPECTION, NOTICED THAT THE HANGER BEARING ASSEMBLY GREASE SHIELD WAS LEAKING. UNIT WAS REPLACED WITH SERVICEABLE, GND RUN CARRIED OUT & NO FURTHER FAULTS. ACFT RELEASED. - [SDR CA150121002](https://openairdocs.org/sdr/CA150121002.md): Spider Gear · cracked · Jan 20, 2015 · Bell 205A1 · Main Rotor Gearbox > (CAN) LOWER PLANETARY SPIDER ASSEMBLY PART NUMBER 205-040-785-003 FOUND CRACKED DURING ROUTINE OVERHAUL. NO KNOWN CAUSE AND NO OTHER DISCREPANCIES FOUND. PART REPLACED WITH NEW PART OF SAME PART NUMBER AND OVERHAUL OF TRANSMISSION COMPLETED. - [SDR CA140819004](https://openairdocs.org/sdr/CA140819004.md): Servo · malfunctioned · Aug 7, 2014 · Bell 205A1 · Rotorcraft Servo System > (CAN) WHEN PILOT CARRIED OUT START UP CHECK LIST AT IDLE, A HYDRAULIC SYSTEMS CHECK WAS CARRIED OUT. SYSTEM 2 WAS CLOSED AND CONTROLS FUCTIONED PROPERLY. SYSTEM 2 WAS TURNED ON AND SYSTEM 1 WAS CLOSED. THE COLLECTIVE BEGAN TO RISE SLOWLY. THE TEST WAS CARRI - [SDR CA140428004](https://openairdocs.org/sdr/CA140428004.md): Beam · cracked · Apr 28, 2014 · Bell 205A1 · Fuselage Main, Structure > (CAN) PERFORMING A SCHEDULE INSPECTION, A VISUAL INSPECTION WAS DONE ON THE LT MAIN BEAM CAP. THE CAP WAS FOUND TO BE CRACKED COMPLETELY THREW. A NEW CAP, PN 205-030-163-095S INSTALLED. - [SDR CA131129010](https://openairdocs.org/sdr/CA131129010.md): Blade · delaminated · Nov 26, 2013 · Bell 205A1 · Main Rotor Blades > (CAN) BLADE WAS REPAIRED IN JULY 2013 TO CORRECT SOME DELAMINATION FROM AN OLDER DENT AT 18" FROM THE BLADE TIP. UPON LANDING AT A REMOTE SITE AND SHUTTING DOWN THE ACFT THE PILOT OBSERVED A BLISTER AT 6" IN DIAMETER AND AT 20 CHORDWISE CREASES OTBD OF DAMAGE - [SDR CA130920009](https://openairdocs.org/sdr/CA130920009.md): Diffuser · cracked · Sep 19, 2013 · Bell 205A1 · Turbine Engine Compressor Section > (CAN) DURING A ROUTINE MAINTENANCE ACTION, A CRACK WAS DISCOVERED AROUND THE BLEED VALVE PORT. ACFT HAS BEEN REMOVED FROM SERVICE. UP-DATE: CRACK FOUND ON COMPRESSOR DIFFUSER MANIFOLD DURING DI.7500" LENGTH SPLITTING FROM BLEED AIR FITTING WELDED AREA. - [SDR CA131009002](https://openairdocs.org/sdr/CA131009002.md): Blade · separated · Aug 24, 2013 · Bell 205A1 · Tail Rotor Blades > (CAN) A SUDDEN MEDIUM FREQUENCY VIBRATION WAS FELT IN FLIGHT. A PRECAUTIONARY LANDING WAS CARRIED OUT. AFTER VISUAL INSPECTION, IT WAS DISCOVERED THAT THE TIP CAP FILLER HAD SEPARATED CAUSING THE VIBRATION. BOTH BLADES WERE REPLACED, THE TAIL ROTOR WAS BALA - [SDR CA140603003](https://openairdocs.org/sdr/CA140603003.md): Beam · cracked · Aug 19, 2013 · Bell 205A1 · Fuselage, Landing Gear Attach Fittings > (CAN) WHILE PERFORMING A DA!LY INSPECTION, IT WAS FOUND THAT THE UPPER LT MAIN BEAM CAP PORTION, EXTRUDING FROM THE ENGINE DECK, SOMETIMES REFEREED TO AS THE "INDICATOR." PORTION, WAS CRACKED. A FLIGHT PERMIT WAS ACTIVATED THROUGH TC AND THE FAA TO FLY TO A M - [SDR CA130813006](https://openairdocs.org/sdr/CA130813006.md): Support · mismanufactured · Aug 8, 2013 · Bell 205A1 · Main Rotor Mast/Swashplate > (CAN) UPON REMOVAL OF THE NEW SUPPORT, PN 204-011-404-125 FROM THE PACKAGING THE PART DISPLAYED THE FOLLOWING: SEVERAL AREAS WHERE MACHINING WAS NOT COMPLETE. TOOLING MARKS WERE EVIDENT IN SEVERAL AREAS. THE CASTING DISPLAYED VOIDS, POROSITY AND MATERIAL F - [SDR CA130705006](https://openairdocs.org/sdr/CA130705006.md): Fitting · cracked · Jul 3, 2013 · Bell 205A1 · Tail Rotor Drive Shaft > (CAN) AME WAS PERFORMING POST FLIGHT/DAILY INSPECTION FOLLOWING LAST FLIGHT OF DAY. DURING INSPECTION, A SMALL VERTICAL LINE WAS NOTED ON THE LT LUG OF THE FITTING THROUGH WHICH THE BOLT SECURING THE TAIL ROTOR DRIVE SHAFT FLEXIBLE COUPLING ASSY TO THE F1TTING - [SDR CA130627001](https://openairdocs.org/sdr/CA130627001.md): Quill · broken · Jun 14, 2013 · Bell 205A1 · Main Rotor Gearbox > (CAN) INPUT QUILL IN-FLIGHT FAILURE, FREEWHEEL UNIT FAILURE, INPUT DRIVESHAFT FAILURE, ENGINE OVERSPEED, AUTOROTATIVE LANDING. - [SDR CA130528009](https://openairdocs.org/sdr/CA130528009.md): Tube · cracked · May 27, 2013 · Bell 205A1 · Hydraulic System, Main > (CAN) CRACKED TUBE UNDERNEATH FITTING SLEEVE, TUBE POPPED OUT OF FITTING AND BLEW OUT MOST OF FLUID. - [SDR CA130323001](https://openairdocs.org/sdr/CA130323001.md): Shaft · sheared · Mar 21, 2013 · Bell 205A1 · Starter-Generator > (CAN) STARTER GENERATOR FAILED TO TURN OVER ENGINE FOR START. INSPECTION REVEALED THE SHAFT HAD SHEARED. - [SDR CA120912012](https://openairdocs.org/sdr/CA120912012.md): Blade · damaged · Sep 11, 2012 · Bell 205A1 · Main Rotor Blades > (CAN) MAIN ROTOR BLADE CRACKED FROM L/E TO T/E UPPER AND LOWER SURFACE AT APPROXIMATELY 77" FROM BLADE TIP. ACFT LANDED SAFELY, MAIN ROTOR BLADE INTACT AS 1 PIECE. BLADE WAS REPAIRED IN 2004 APPROXIMATELY 319 HOURS AGO. - [SDR CA120817001](https://openairdocs.org/sdr/CA120817001.md): Longeron · cracked · Aug 7, 2012 · Bell 205A1 · Fuselage Main, Longeron/Stringer > (CAN) TOP LT LONGERON ON ACFT LOCATED IN AFT COMPARTMENT WAS CRACKED BEHIND DOUBLER ON TOP LT TAILBOOM ATTACHMENT. CRACK WAS FOUND DURING DAILY INSPECTION, MACHINE WAS FLOWN TO ACFT SERVICE CENTER WERE LONGERON WAS REPLACED. - [SDR CA120629008](https://openairdocs.org/sdr/CA120629008.md): Bearing · damaged · Jun 18, 2012 · Bell 205A1 · Turbine Engine Compressor Section > (CAN) DEBRIS, METAL, FOUND ON ENGINE CHIP DETECTOR. 7.7 HRS LATER DEBRIS WAS FOUND AGAIN ON ENGINE CHIP DETECTOR. 1 HR AFTER ENGINE WAS REMOVED FROM ACFT DUE TO MORE METAL FOUND ON ENGINE CHIP DETECTOR. ENGINE INSPECTED AND FOUND NR 1 BEARING AND RACES TO BE - [SDR CA120629007](https://openairdocs.org/sdr/CA120629007.md): Nut · damaged · Jun 18, 2012 · Bell 205A1 · Turbine Engine Compressor Section > (CAN) DEBRIS, METAL, FOUND ON ENGINE CHIP DETECTOR. 7.7 HRS LATER DEBRIS WAS FOUND AGAIN ON ENGINE CHIP DETECTOR. 1 HR AFTER ENGINE WAS REMOVED FROM ACFT DUE TO MORE METAL FOUND ON ENGINE CHIP DETECTOR. DURING INSPECTION INTO METAL GENERATION BY ENGINES THE - [SDR CA120817004](https://openairdocs.org/sdr/CA120817004.md): Tachometer · failed · Jun 6, 2012 · Bell 205A1 · Engine RPM Indicating System > (CAN) CO-PILOT DUAL TACH N2 ENGINE RPM NEEDLE, FLUCUATES FROM 0 TO 50 PERCENT THEN STICKS. - [SDR CA120223006](https://openairdocs.org/sdr/CA120223006.md): Cap · fractured · Jan 28, 2012 · Bell 205A1 · Rotorcraft Tail Boom > (CAN) FAILURE OF CAP, IN ORDER TO EXAMINE THE FRACTURE SURFACE OF A STRUCTURAL LONGERON, HERE-IN REFERRED TO AS A CAP. THE CAP, PN 205-030-207-005 AND THE ASSOCIATED TAILBOOM ATTACHMENT FITTING, PN 205-030-767-005, WERE SUBSEQUENTLY SENT TO FOR EXAMINATION AND - [SDR CA120116003](https://openairdocs.org/sdr/CA120116003.md): Gimbal Ring · damaged · Jan 16, 2012 · Bell 205A1 · Main Rotor Mast/Swashplate > (CAN) DURING 100 HRS INSPECTION, 2 SMALL DAMAGED SCREWS WHERE FOUND IN THE BOTTOM OF THE MAIN TRANSMISSION BAY STILL ATTACHED WITH LOCKING WIRE. FURTHER INSPECTION REVEALED THAT THE SCREW BELONGED TO 1 OF THE 4 SWASHPLATE GIMBAL RING ATTACHEMENT POINTS. SWAS - [SDR CA111220005](https://openairdocs.org/sdr/CA111220005.md): Blade · cracked · Dec 20, 2011 · Bell 205A1 · Main Rotor Blades > (CAN) 3 CRACKS DEVELOPED ON BOTTOM SIDE OF BLADE SKIN, PN 212-015-501-115, SN A6009 (TSN) 3521.9, 1 CRACK 5.5", THE OTHER 2 CRACKS ARE 2.5" - 3.5" RESPECTIVELY. MEASURING FROM TRIM TAB EDGE INBD 41.5" IS THE LONG, 5.5. THE OTHER 2 CRACKS ARE OTBD A FEW INCHE - [SDR CA110909011](https://openairdocs.org/sdr/CA110909011.md): Governor · failed · Aug 14, 2011 · Bell 205A1 · Turbine Governor > (CAN) ACFT LEVELED OFF AFTER CLIMB, A BANG WAS HEARD THEN ACFT YAWED, ROTOR LOW HORN AND LIGHT SOUNDED. ENGINE FAILURE WAS CONFIRMED- N1 WAS AT 25 PERCENT AND TORQUE WAS READING 0. ACFT AUTOROTATED TO GROUND. FUEL CELLS AND AIRFRAME FILTER ON BOARD INSPECTE - [SDR CA110726007](https://openairdocs.org/sdr/CA110726007.md): Channel · mismanufactured · Jul 25, 2011 · Bell 205A1 · Fuselage Miscellaneous Structure > NEW PART DOES NOT FIT ACFT OR FIXTURE PLATE. MANUFACTURED.040 TOO WIDE. - [SDR CA110711020](https://openairdocs.org/sdr/CA110711020.md): Coupling · failed · Jul 8, 2011 · Bell 205A1 · Tail Rotor Drive Shaft > THE PILOT NOTICED A SLIGHT YAW AS HE WAS TOUCHING DOWN. HE ALSO NOTICED THAT WHEN WHEN APPLYING COLLECTIVE TO TAKEOFF, THERE WAS NO RESPONSE FROM THE PEDALS. THE AIRCRAFT WAS SHUTDOWN AND AS IT WAS WINDING DOWN, A LOUD GRINDING NOISE WAS HEARD COMING FROM TH - [SDR CA111222011](https://openairdocs.org/sdr/CA111222011.md): Diffuser · used · Mar 6, 2011 · Bell 205A1 · Engine Collector/Tailpipe/Nozzle > (CAN) UPON LANDING AND PERFORMING A POST FLIGHT VISUAL INSPECTION THE AME FOUND THE BOTTOM STRUT ON THE EXHAUST DIFFUSER CRACKED WITH A SECTION OF MATERIAL MISSING. THE EXHAUST DIFFUSER SERVES AS THE REAR BEARING SUPPORT. AS A RESULT OF THIS DEFECT THE POWER - [SDR CA101122028](https://openairdocs.org/sdr/CA101122028.md): Baffle · detached · Nov 22, 2010 · Bell 205A1 · Fuel Storage > BAFFLE DIVIDING FORWARD AND AFT SECTIONS OF FUEL CELL, FOUND DETACHED. FUEL IS ABLE TO MOVE AROUND POTENTIALLY CAUSING C OF G ISSUES. IN LOW FUEL SITUATIONS, SLOSHING FUEL MAY CAUSE SUPPLY TO THE PUMPS TO DIMINISH, POTENTIALLY CAUSING ENGINE FUEL STARVATION. - [SDR CA100901007](https://openairdocs.org/sdr/CA100901007.md): Beam · cracked · Aug 16, 2010 · Bell 205A1 · Fuselage Main, Attach Fittings > THE ACA HOLDER WAS DOING HIS DAILY PREFLIGHT WHEN HE NOTICED 2 BLACK LINES THAT APPEARED TO BE CRACKS. THE ACA HOLDER LOOKED CLOSER AND FOUND THE TRANSMISSION 5TH MOUNT FITTING BEAM WAS CRACKED ON THE BOTTOM OF THE BEAM, WHERE THE 5TH RUBBER MOUNT IS LOCATED. - [SDR H4QA2010F00111](https://openairdocs.org/sdr/H4QA2010F00111.md): Housing · cracked · May 20, 2010 · N205HQ · Bell 205A1 · Turbine Engine Combustion Section > COMBUSTION CHAMBER HOUSING FOUND CRACKED 8 INCHES LONG FROM (LOOKING FORWARD) 12:30-2:30 POSITION. CRACK WAS FOUND AFTER SHUTDOWN DURING DAILY INSPECTION BY MECHANIC. NO IRREGULAR INDICATIONS OR PERFORMANCE DURING FLIGHT WAS NOTICED OR EMERGENCY ACTIONS WERE - [SDR CA091120005](https://openairdocs.org/sdr/CA091120005.md): Igniter · failed · Nov 20, 2009 · Bell 205A1 · Spark Plug/Igniter > (CAN) FOUND IGNITER PLUG 1 OF 4 INSTALLED, FAILED CAUSED BY IGNITER INTERIOR CATHODE BECOMING LOOSE. - [SDR CA091120004](https://openairdocs.org/sdr/CA091120004.md): Igniter · failed · Nov 20, 2009 · Bell 205A1 · Spark Plug/Igniter > (CAN) FOUND IGNITER PLUG, 2 OF 4 INSTALLED FAILED CAUSED BY IGNITER INTERIOR CATHODE BECOMING LOOSE. - [SDR CA091109002](https://openairdocs.org/sdr/CA091109002.md): Boot · separated · Nov 6, 2009 · Bell 205A1 · Main Rotor Drive System > (CAN) DURING THE 12 MONTH INSP AND RE-GREASE OF THE INPUT DRIVE SHAFT, IT WAS DISCOVERED THAT THE INNER DIAMETER OF THE BOOT HAD COMPLETELY SEPERATED FROM THE RING IT IS SUPPOSED TO BE GLUED TO. GREASE WAS FOUND BETWEEN THE BOOT AND THE RING WHICH SHOWS THE AI - [SDR CA091006004](https://openairdocs.org/sdr/CA091006004.md): Shaft · worn · Sep 19, 2009 · Bell 205A1 · Engine Fuel Pump > (CAN) WHILE FLYING THE PILOT HAD A CAUTION LIGHT. IT WAS THE FUEL PUMP CAUTION LIGHT THAT HAD ILLUMINATED. THE PILOT LANDED AS SOON AS PRACTICAL. THE ENG FUEL CONTROL WAS REMOVED TO CORRECT THE DEFECT. A LITTLE HISTORY OF THE FUEL CONTROL. THE FUEL CONTROL W - [SDR CA090818006](https://openairdocs.org/sdr/CA090818006.md): Bolt · broken · Aug 14, 2009 · Bell 205A1 · Engine Mount Section > WHILE THE ENGINEER WAS CARRYING OUT A DAILY INSP, FOUND HALF A BOLT WITH NUT ATTACHED ON ENG DECK. FURTHER INVESTIGATION REVEALED THAT BOLT (ONE OF TWO) WAS PART OF THE ATTACHMENT OF THE PILLOW BLOCK ASSY TO THE ENG BIPOD MOUNT ASSY. PART OF THE BOLT APPEARE - [SDR CA090806005](https://openairdocs.org/sdr/CA090806005.md): Governor · unknown · Jul 30, 2009 · Bell 205A1 · Turbine Governor > EXCESSIVE ENGINE DROOP. - [SDR CA090702013](https://openairdocs.org/sdr/CA090702013.md): Fitting · cracked · Jul 1, 2009 · Bell 205A1 · Tail Rotor Drive System > DURING A POST FLIGHT INSP, THE TAIL ROTOR DRIVE FITTING WAS FOUND CRACKED. TIME ON THE FITTING IS UNKNOWN. CRACK WAS FOUND RADIATING FROM THE BORE OF THE BARREL NUT ATTACHMENT. UNSURE IT THIS MAYBE THE CAUSE OF OVER TORQUING OF THE BOLT. NUT WAS REPLACED W Next page: https://openairdocs.org/model/bell-205a-1/reports.md?page=2 ## The whole list in SQL Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS: ```sql 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 ``` This list as a web page: https://openairdocs.org/model/bell-205a-1/reports --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.