Boeing DHC-6-300

Service difficulty reports · 655

Newest first. General aviation reporting is voluntary.

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 aircraft_model_key = 'DHC6300'
  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.

SDR S9BA20150005Longeron · crackedLEFT NACELLE OTBD LONGERON CRACKED. REMOVED CRACKED LONGERON, LOCATED NEW LONGERON AND INSTALLED. REF AC 43.13-1BJun 21, 2015 · Dhav DHC6300 · Nacelle/Pylon, Longeron/StringerSDR S9BA201506180004Engine · power lossLT ENGINE LOST POWER ON TAKEOFF, AUDIBLE GRINDING NOISE AND EXCESSIVE VIBRATION CAN BE HEARD AND FELT COMING FROM ENGINE.Jun 18, 2015 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR CA150612009Turnbuckle · cracked(CAN) DURING INSPECTION, FOUR TURNBUCKLES FROM A FLIGHT CONTROL TRIM SYSTEM WERE FOUND CRACKED. ONE MS21251B-5L, TWO MS21251B-2L, & ONE MS21251-B2L. CRACKS ARE LONGITUDINAL IN AREA OF LOCKING GROOVE. REMINDER THERE MAY STILL BE TURNBUCKLES IN SERVICE FROM TJun 12, 2015 · Dhav DHC6300 · Flight Control SystemSDR CA150604005Fuel Control · malfunctioned(CAN) FLIGHT CREW NOTICED THE ENGINE NG GAUGE WAS CONSTANTLY INCREASING. THE FLIGHT CREW PERFORMED AN AIR TURN BACK AND A PRECAUTIONARY LT ENGINE SHUTDOWN WAS CONDUCTED. NO EMERGENCY WAS DECLARED AND THE ACFT PERFORMED AN UNEVENTFUL SINGLE ENGINE LANDING. MAIMay 20, 2015 · Dhav DHC6300 · Fuel Control/Turbine EnginesSDR CA150806008Blade · damaged(CAN) DURING SCHEDULED MAINTENANCE AFTER HAVING A FOD INCIDENT ON THE OTHER ENGINE, IT WAS DECIDED TO REMOVE THE PROTECTIVE SCREEN AND INSPECT THE COMPRESSOR FOR FOD DAMAGE. THE FIRST STAGE COMPRESSOR BLADES WERE FOUND WITH HEAVY IMPACT DAMAGE. THE SECOND AND May 15, 2015 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR CA150602005Engine · overtorqued(CAN) INFLIGHT SHUTDOWN DUE TO ENG OVER TORQUE UP TO 75%. ONGOING POWER SECTION & PROPELLER REPLACEMENT. THE ACFT TO BE FERRIED TO MAIN BASE FOR AUTO FEATHER SYS CHECK.May 9, 2015 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR CA150512002Autofeather Sys · failed(CAN) ENGINE NR 2 OVER TORQUED IN FLIGHT & NP WAS HIGH AT APPROX 92%. AS A PRECAUTION, ENG %2 WAS SHUTDOWN IN FLIGHT. THE OVER TORQUE WAS BEYOND 70 PSI FOR AT LEAST 1 MINUTE. NR 2 ENG WAS FEATHERED AT HIGH TORQUE VALUE. OVER TORQUE INSPECTIONS HAVE BEEN COMay 7, 2015 · Dhav DHC6300 · Propeller Feathering/ReversingSDR CA150421001Line · chafed(CAN) UPON INSPECTION OF THE ACFT IT WAS FOUND THAT THE LT SKI UP LINE ON THE LT MLG LEG WAS CHAFED THROUGH WHERE THE LEG EXIT THE FUSELAGE ON AFT FUSELAGE GEAR FAIRING. ONCE SKIS WERE SELECTED UP ALL PRESSURE WAS LOST WAS LOST AFTER IT RAN OUT OF HYDRAULIC FApr 18, 2015 · Dhav DHC6300 · Hydraulic System, MainSDR CA150806007Blades · cracked(CAN) PILOT REPORTED CLICKING NOISE COMING FROM ENGINE DURING SHUTDOWN AND TURNING OVER ENGINE.MAINTENANCE INVESTIGATED AND FOUND THERE WAS A NOTICEABLE CLICKING NOISE COMING FROM THE COMPRESSOR AREA WHEN THE COMPRESSOR WAS TURNED OVER BY HAND. MIRROR AND BOREApr 15, 2015 · Dhav DHC6300 · Turbine Engine Compressor SectionSDR CA150331010Lever · broken(CAN) THE FLIGHT CREW STATED THAT THE NOSE-WHEEL STEERING WAS HARD TO USE. WHEN THE AME INVESTIGATED HE DISCOVERED THAT THE LEVER ASSY WAS BROKEN ON THE NLG. NO RELATED DEFECTS WERE FOUND DURING THE INVESTIGATION. THE LEVER ASSY WAS REPLACED. THERE HAVE BEEMar 23, 2015 · Dhav DHC6300 · Landing Gear Steering SystemSDR CA150312008Rod · unserviceable(CAN) DURING ROUTINE MAINTENANCE ACTIVITIES THE AME NOTICED A CRACK IN THE AILERON SERVO ROD. THIS SAME CRACKED AREA ON THE ROD WAS ALSO SWOLLEN AND IT IS SUSPECTED THAT WATER ACCUMULATED INSIDE THE ROD AND FROZE. THE AILERON ROD WAS REPLACED WITH NO ADDITIOMar 12, 2015 · Dhav DHC6300 · Aileron Tab Control SystemSDR CA150302007Blade · cracked(CAN) DUE TO POSSIBLE FATIGUE CRACKING IN 2 PT BLADES, WHICH IS CAUSE FOR SET REJECTION. THIS BLADE HAS LESS THAN 4000 HRS TSN, WHICH IS VERY UNUSUAL. AT FPI, CRACK INDICATIONS WERE FOUND ON 2 PT1 BLADES IN THE RADIUS BETWEEN THE AIRFOIL AND UPPER SHROUD. THEFeb 27, 2015 · Dhav DHC6300 · Turbine SectionSDR CA150303001Shock Absorber · debonded(CAN) DURING ACFT "EMMA" INSPECTION ON THE LANDING GEAR, THE ENGINEER FOUND THE LT REBOUND SHOCK ABSORBER ASSY DISBONDED FROM BOTH OF THE MOUNTING PLATES. THE REBOUND SHOCK ABSORBER WAS REPLACED BEFORE FURTHER FLIGHT. THE RT REBOUND SHOCK ABSORBER ASSY CHECKSFeb 16, 2015 · Dhav DHC6300 · Main Landing Gear Strut/Axle/TruckSDR CA150122002Probe · failed(CAN) FIRE INDICATION ON LEFT ENGINE IN FLIGHT. FLIGHT CREW DID FIRE PROCEDURES. AIRCRAFT LAND WITH NO INCIDENT. AFTER INSPECTIONS, FOUND 300 DEGREE TEMPERATURE PROBE AT FAULT.Jan 15, 2015 · Dhav DHC6300 · Fire DetectionSDR S9BA2015011500002Fitting · damagedDURING ACCOMPLISHMENT OF EDDY CURRENT INSPECTION IAW SIE-23-701, REV. G, DEFECT NOTED ON LT WING FITTING LUG, NR 7, INBD UPPER QUADRANT. DEFECT AT 30 PERCENT FSH. PROVIDED DAMAGE REPORT. UPON THEIR ANALYSIS, INSTRUCTIONS WERE PROVIDED TO REMOVE BUSHING AND Jan 12, 2015 · Dhav DHC6300 · Wing, Attach FittingsSDR CA150108012Pedal · fractured(CAN) PILOT REPORTED RT BRAKE PEDAL BROKEN ON P1 SIDE. INSPECTED FOR THE RUDDER PEDAL AS PER PSM 16-7, 27, ITEM 3.1, & 3.2. .Jan 5, 2015 · Dhav DHC6300 · Landing Gear Brake SystemSDR CA141224006Cable · worn(CAN) DURING THE FIVE YEAR SCHEDULED FLIGHT CONTROL CABLE CHANGE, THE ELEVATOR CABLE IN THE FORWARD NOSE WAS FOUND TO BE INTERFERING ON THE STEC AUTOPILOT PULLEY CLUSTER. IT WAS HELD IN THIS INCORRECT POSITION BY A SCREW ON THE PULLEY GUARD CLUSTER. THE ELEVATDec 14, 2014 · Dhav DHC6300 · Autopilot SystemSDR GCNA20141030001Engine · shutdownPILOT TOOKOFF, THEN REPORTED THAT AT 400 FEET AGL AFTER TAKEOFF, CREW HEARD WEIRD NOISES AND FELT PITCH CHANGES. RIGHT TORQUE INDICATED HIGH, WITH RT PROP RPM FLUCTUATING. RIGHT ENGINE WAS SHUTDOWN AND CREW RETURNED TO DEPARTURE WITH NO FURTHER INCIDENT.Oct 29, 2014 · N173GC · Dhav DHC6300 · Propeller Controlling SystemSDR CA141001007Beta Switch · failed(CAN) DURING CRUISE FLIGHT, THE CREW EXPERIENCE AN UNSCHEDULED FEATHERING OF NR 2 PROPELLER. THE CREW TRY TO REGAIN CONTROL OF THE PROPELLER WITH NO SUCCESS. THE ENGINE WAS SHUTDOWN AND THE AIRPLANE RETURNED TO AIRPORT SAFELY. THE NR 2 PROPELLER BETA SYSTEM SWSep 27, 2014 · Dhav DHC6300 · Propeller Feathering/ReversingSDR CA140924007Seal · worn(CAN) THE CREW OF ACFT ON A CARGO FLIGHT AFTER 20 MINUTES OF FLIGHT STARTED SMELLING A BURNING ODOR, WHEN THE ENGINE BLEED AIR SWITCHES WERE SET TO "OFF" THE ODOR WENT AWAY, ACFT RETURNED TO DEPARTURE POINT. DURING MAINTENANCE GROUND RUNS HOT AIR WAS DISCOVERSep 23, 2014 · Dhav DHC6300 · Air Distribution SystemSDR CA140822006Longeron · cracked(CAN) PART CRACKED 13" AFT OF ENGINE MOUNT ATTACHEMNT. ACFT TTAF 11598.9, TOTAL CYCLES 15913.Aug 10, 2014 · Dhav DHC6300 · Wing, Longeron/StringerSDR CA140821010Longeron · cracked(CAN) LONGERON CRACKED 13" AFT OF ENGINE MOUNT ATTACHEMENT.Aug 10, 2014 · Dhav DHC6300 · Wing, Longeron/StringerSDR CA140704001Warning Message · activated(CAN) REPORTED A CHIP DETECTOR LIGHT INDICATION FOLLOWED BY AN OIL PRESSURE AND OIL TEMPERATURE FLUCTUATION AND ENGINE TORQUE DROPPING TO ZERO.Jul 3, 2014 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR QOWR2014071800446Bushing · failedMFG INSTALLED NEW FIRST STAGE SUN GEAR, WITH NEW 1ST STAGE PLANET GEAR SET ASSY. ONE OF THE GEARS, HAD A BUSHING FAILURE, CAUSING THE GEAR TO SPIN AROUND. CAUSING CONTAMINATION OF THE OIL SYSTEM. GEAR HAD FOUR HRS OF TEST TIME ONLY SINCE NEW. REPAIR STATIOJul 2, 2014 · N148SA · Dhav DHC6300 · Turbine Engine Reduction GearSDR CA140602004Cap · unsecure(CAN) DURING FLIGHT, THE OIL PRESSURE STARTED TO FLUCTUATE. THE PILOT ELECTED TO SHUT THE ENGINE DOWN BEFORE MAKING AN UNEVENTFUL SINGLE ENGINE LANDING AT THE DEPARTURE AIRPORT. POST FLIGHT INSPECTION FOUND AN IMPROPERLY SECURED OIL FILLER CAP. MFG HAS RECOMApr 30, 2014 · Dhav DHC6300 · Turbine Engine Oil SystemSDR HKGA2014043000290Cap · unsecureDURING FLIGHT, CAPTAIN SAW THE NR 1 ENGINE OIL PRESSURE FLUCTUATING, IMMEDIATELY SHUT THE NR 1 ENGINE DOWN AND RETURNED TO DEPARTURE WITH NO FURTHER PROBLEMS. MX DISCOVERED THAT THE NR 1 ENGINE OIL CAP WAS NOT PROPERLY SECURED AND ALLOWING OIL TO SPILL OUT.Apr 30, 2014 · N675BA · Dhav DHC6300 · Turbine Engine Oil SystemSDR CA140602001Engine · making metal(CAN) DURING FLIGHT, THE LT ENGINE`S CHIP DETECTOR LIGHT ILLUMINATED APPROXIMATELY 20 NM FROM AIRPORT. THE CREW THEN DECIDED TO TURN AROUND AND HEAD BACK TO POINT OF DEPARTURE. THE ENGINE PARAMETERS STAYED NORMAL FOR A FEW MINUTES, AFTER WHICH THE OIL PRESSUMar 28, 2014 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR CA140526013Gasket · delaminated(CAN) IN CRUISE FLIGHT, ENGINE FAILED DUE TO LOSS OF OIL. INVESTIGATION REVEALED SECTIONS OF THE OVERSPEED GOVERNOR GASKET HAD SEPERATED FROM THE CORE AND MIGRATED OUTWARDS ALLOWING OIL TO LEAK FROM BETWEEN THE GOVERNOR BODY AND THE GASKET CENTER CORE. THE OVMar 28, 2014 · Dhav DHC6300 · Turbine Engine Oil SystemSDR S9BA2014031000004Frame · corrodedLT SIDE OF BS 218 FRAME CORRODED AROUND STEEL BUSHING FOR PYLON ATTACH POINT.Mar 8, 2014 · Dhav DHC6300 · Fuselage Main, FrameSDR CA140224007Unknown · unknown(CAN) CONTACT WAS LOST APPROXIMATELY 30 MIN, INTO A FLIGHT. THE WRECKAGE WAS LOCATED THE NEXT MORNING AT AN ELEVATION OF 7000. RECOVERY EFFORTS IN PROCESS, NO SURVIVORS WERE FOUND. SEVERE WEATHER CONDITIONS WERE REPORTED AT THE TIME OF THE ACCIDENT.Feb 16, 2014 · Dhav DHC6300 · Standard Practices/StructuresSDR S9BA201400002Wire · detachedDURING TAKE OFF ROLL, SMOKE WAS OBSERVED COMING BEHIND THE CAUTION LIGHTS PANEL. ABORTED TAKE OFF, RETURNED TO BLOCK. ATTACHED WIRE TO CAUTION BOX RECEPTACLE IAW AC 43-13-1B. OPS CHECKED GOOD. ACFT RETURNED TO SERVICE.Feb 16, 2014 · Dhav DHC6300 · Electrical Power System WiringSDR CA140224003Engine · warning light(CAN) DURING CRUISE FLIGHT, A BETA RANGE LIGHT WENT ON AND REMAINED STEADY. AT THE SAME TIME ENGINE NR 1 NP DECREASED SLOWLY TOWARDS THE FEATHER POSITION. PROPELLER MALFUNCTION PROCEDURE WAS APPLIED. ENGINE WAS SHUTDOWN, SAFELY LANDING WITH 1 ENGINE.Feb 10, 2014 · Dhav DHC6300 · Engine (Turbine/Turboprop)SDR S9BA201400001Pressure Switch · inoperativeLEFT PROPELLER, UNSCHEDULED FEATHER ENROUTE. R & R ENGINE AUTO FEATHER PRESSURE SWITCH.Jan 16, 2014 · Dhav DHC6300 · Propeller Feathering/ReversingSDR CA131209001Arm · cracked(CAN) PRIOR TO TOWING AN ACFT THE UPPER AND LOWER TORQUE ARMS WERE DISCONNECTED FROM EACH OTHER BY REMOVING THE LATCH PIN. IT WAS NOTICED THAT THE UPPER TORQUE ARM WAS CRACKED IN THE RT LATCH CHAIN INSTALLATION HOLE. UPPER TORQUE ARM WAS REPLACED PRIOR TO FUDec 5, 2013 · Dhav DHC6300 · Nose/Tail Landing GearSDR CA131119003Bracket · cracked(CAN) DURING ROUTINE MAINTENANCE THE RUDDER PEDALS WERE INSPECTED FOR CRACKS AND THERE WAS ONE DISCOVERED ON THE CO-PILOTS LT RUDDER PEDAL IN THE CENTER ATTACH BRACKET. THE RUDDER PEDAL WAS REPLACED AND W/O CLOSED.Nov 17, 2013 · Dhav DHC6300 · Rudder Control SystemSDR S9BA2013111500007Longeron · crackedRT NACELLE INBD LONGERON CRACKED. R & R RT NACELLE INBD LONGERON IAW SRM CHAPTER 54 AND AC 43.1B-1B.Nov 13, 2013 · Dhav DHC6300 · Nacelle/Pylon, Longeron/StringerSDR CA131112015Rudder Pedal · cracked(CAN) DURING ROUTINE MAINTENANCE A PIECE OF METAL WAS NOTICED ON THE COCKPIT FLOOR CLOSE TO THE LT RUDDER PEDALS. THE PIECE WAS FOUND TO BE FROM THE RT PEDAL ON THE CAPTAINS SIDE. THE RUDDER PEDAL WAS REPLACED AND WO CLOSED.Nov 10, 2013 · Dhav DHC6300 · Rudder Control SystemSDR CA131010001Selector · leaking(CAN) DURING FLIGHT, THE CREW NOTICED THE HYDRAULIC SYS PRESSURE INDICATION WAS ZERO AND A LARGE QTY OF HYDRAULIC FLUID WAS VISIBLE IN THE CENTER CABIN AREA DRIPPING FROM THE CABIN CEILING. ACFT RETURNED TO BASE FOR MAINTENANCE. INVESTIGATION REVEALED THAT THOct 9, 2013 · Dhav DHC6300 · Trailing Edge Flap Control SystemSDR S9BA201309160005Mount · corrodedLEFT ENGINE OTBD SIDE MOUNT PLATE CORRODED. R & R MOUNT PLATE IAW SRM RD6-54-006 WITH FACTORY NEW PART.Sep 14, 2013 · Dhav DHC6300 · Engine Mount SectionSDR S9BA201300004Doubler · corrodedRT NACELLE LONGERON DOUBLER PLATE IS CORRODED. R & R RT NACELLE LONGERON DOUBLER PLATE IAW SRM RD6-54-013 WITH FACTORY NEW PART.Sep 8, 2013 · Dhav DHC6300 · Nacelle/Pylon, Main FrameSDR S9BA201300003Terminal · unsecureRT FIRE WARNING LIGHT AND BELL ON IN FLIGHT. SECURED RING TERMINAL ON RT OTBD FIRE DETECTION. OPS CHECKED SATISFACTORY. OPENSep 5, 2013 · N888PV · Dhav DHC6300 · Fire Protection System WiringSDR S9BA20130821002Skin · dentedBIRD STRIKE ON LT WING, STA 322.8. INSPECTED ADJACENT AREAS FOR SECONDARY DAMAGE. R & R L/E IAW SRM 57-30-00 AND AC 43.13-B1. PRIMED AND REPAINTED AREA.Aug 20, 2013 · N888PV · Dhav DHC6300 · Wing, Plate/SkinSDR S9BA201308060001Skin · corrodedLEFT WING AILERON LOWER SKIN HAS CORROSION. R & R SKIN IAW SRM 57-50-11 AND AC 43.13-1B. AILERON STATICALLY BALANCED IAW MM 57-50-23.Jul 30, 2013 · N288SA · Dhav DHC6300 · AileronsSDR CA130726011Rudder Pedal · cracked(CAN) PRIOR TO ENTERING THE COCKPIT TO RELEASE THE BRAKES FOR TOWING THE MECHANIC NOTICED A PIECE OF METAL ON THE FLOOR BELOW THE RUDDER PEDALS. THE METAL PIECE WAS FOUND TO BE FROM THE PILOTS LT RUDDER PEDAL, THE PEDAL WAS REPLACED.Jul 25, 2013 · Dhav DHC6300 · Rudder Control SystemSDR CA130710008Hinge · cracked(CAN) DURING A ROUTINE INSPECTION, EXTERNAL WALK AROUND, IT WAS NOTICED THAT THE LT OTBD ELEVATOR HINGE ARM, PN C6TEM1016-33, LOWER ATTACHMENT POINT WAS DAMAGED, .3333 OF THE LOWER ATTACHMENT LUG WAS CRACKED OFF. THE ATTACHMENT HARDWARE WAS INCORRECT, 2 EA ANJul 8, 2013 · Dhav DHC6300 · Elevator Control SystemSDR GCNA20130611035Clevis Bolt · failedDURING CRUISE FLIGHT, PILOTS FELT AN AGGRESSIVE FLUTTER COMING FROM RUDDER. DECLARED AN EMERGENCY AND LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED THE ACFT AND DETERMINED THE RUDDER GEAR TAB HAD FAILED DUE TO A BROKEN CLEVIS BOLT. NOTICED THAT TO RIG THE RJun 2, 2013 · N177GC · Dhav DHC6300 · Rudder StructureSDR CA130527002Oil System · low pressure(CAN) THE PILOT SHUT DOWN THE NR 1 ENGINE DUE TO OIL PRESSURE LOSS. THE ON GROUND INSPECTION REVEALED THE LOSS OF OIL PRESSURE WAS ATTRIBUTED TO A PROPELLER ISSUE.May 5, 2013 · Dhav DHC6300 · Engine Oil PressureSDR CA130501005O-Ring · leaking(CAN) IN CRUISE ON A CARGO FLIGHT THE CREW NOTICED OIL PRESSURE FLUCTUATIONS ON THE NUMBER ONE ENGINE AND SHORTLY AFTER THE LOW OIL PRESSURE LIGHT ILLUMINATED. THE EMERGENCY CHECKLIST WAS FOLLOWED AND THE NUMBER ONE ENGINE WAS SHUT DOWN, AIRCRAFT RETURNED TO BApr 30, 2013 · Dhav DHC6300 · Propeller Hub SectionSDR CA130418007Bracket · buckled(CAN) DURING INSPECTION OF TAIL SECTION, ELEVATOR QUADRANT SUPPORT BRACKET WAS FOUND TO BE BUCKLED IN 2 PLACES. PART WAS REMOVED FOR REPLACEMENT AND APPEARED TO BE NOT IN A HEAT TREATED CONDITION.Apr 18, 2013 · Dhav DHC6300 · Elevator Control SystemSDR CA130411002Pump · overheated(CAN) AFTER DEPARTURE AND APPROXIMATELY 10 NM FROM AIRFIELD, SMOKE WAS OBSERVED COMING FROM THE COCKPIT FLOOR. THE EMERGENCY CHECKLIST WAS FOLLOWED AND ACFT RETURNED TO BASE. THE CAUSE OF THE SMOKE WAS THE HYD PUMP AND MOTOR ASSY, UNIT WAS REPLACED ALONG WITHApr 10, 2013 · Dhav DHC6300 · Hydraulic Pump (Electric/Engine), Main
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