Boeing DHC-8-301

Service difficulty reports · 571

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 = 'DHC8301'
  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 CA960709010Drain Line · chafed(CAN) CREW ON WALKAROUND FOUND A FUEL LEAK IN #1 ENGINE NACELLE. SOURCE WAS A DRAIN LINE WHICH HAD CHAFED THROUGH.Jun 28, 1996 · Dhav DHC8301 · Engine DrainsSDR CA961018005Connector · burnt(CAN) AT START OF POST ENGINE START CHECKS, THE CREW NOTICED AN ELECTRICAL BURNING SMELL, FOLLOWED BY SMOKE FROM BEHIND THE COPILOT SEAT. ONCE THE ENGINES SHUTDOWN, DC POWER REMOVED AND THE PASSENGER DOOR OPENED THE SMOKE SUBSIDED. OVERHEAD BIN CONNECTOR HAD BJun 20, 1996 · Dhav DHC8301 · Passenger Compartment LightingSDR CA960703018Clamp · loose(CAN) #2 ENGINE INDICATED FIRE DETECTION ON TAXI-OUT. ENGINE SHUTDOWN AND FIRE BOTTLE USED. INVESTIGATION REVEALED EXHAUST PIPE HAD SEPARATED OFF REAR ENGINE AT POWER TURBINE. THE 'V' CLAMP HAD BECOME LOOSE.Jun 19, 1996 · Dhav DHC8301 · Engine Collector/Tailpipe/NozzleSDR CA960614002Drive · damaged(CAN)AFTER TAKEOFF FLAPS FAILED TO RETRACT FROM 10 DEGREES. FLEX SECONDARY DRIVE REPLACED.Jun 14, 1996 · Dhav DHC8301 · Trailing Edge Flap Control SystemSDR CA960619040Micro Switch · failed(CAN) ON #1 ENGINE SHUTDOWN, ENGINE OVERTORQUE OCCURRED, ENGINE SHUTDOWN WITH "T" HANDLE. NP UNDERSPEED GOVERNING MICROSWITCH FAILED.Jun 12, 1996 · Dhav DHC8301 · Turbine GovernorSDR CA960620004Ahrs · failed(CAN) #2 ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS) FAILED IN FLIGHT. EADI ATTITUDE INFO TOPPLES. CYCLING THE #2 AHRS AND #2 AHRS CIRCUIT BREAKERS WOULD BRING AHRS BACK ON LINE. UNIT REPLACED.Jun 4, 1996 · Dhav DHC8301 · Attitude and Direction Data SystemSDR CA960524025Socket · shorted(CAN) RIGHT WING INSPECTION LIGHT CIRCUIT BREAKER FOUND POPPED. INVESTIGATION REVEALED A SHORT IN RIGHT LOWER NACELLE COWLING WING INSPECTION LIGHT SOCKET. SOLDER FROM CONTACT ASSEMBLY CENTRE CONTACT FOUND MELTED AND HAD FLOWED ACROSS TO SOCKET BASE ASSEMBLY GMay 9, 1996 · Dhav DHC8301 · Exterior LightingSDR CA960515010Rib · cracked(CAN)DURING REPAIR OF RUDDER TO REPLACE CENTRE HINGE FITTING, FOUND UPPER ADJACENT RIB CRACKED BETWEEN TWO RIVETS ALONG FORWARD RIVET ROW. REPAIR ACCOMPLISHED AS PER STRUCTURAL REPAIR MANUAL (SRM).May 9, 1996 · Dhav DHC8301 · Rudder, Spar/RibSDR CA960419009Fuel Control · malfunction(CAN)POWER EXCURSION REPORTED ON TAXI-OUT CONFIRMED BY FDR THAT MAXIMUM TORQUE EXCEEDED. PROPELLER ASSEMBLY REPLACED. MFC, ECU AND HARNESS REPLACED PENDING RESULTS OF PWC INVESTIGATION.Apr 14, 1996 · Dhav DHC8301 · Fuel Control/Turbine EnginesSDR CA960524020Control Cable · frayed(CAN)ON DAILY INSPECTION OF ENGINE, #1 ENGINE PROP/CONDITION CABLE CHAFED AND FRAYED AT ENGINE FIRE WALL PULLEY. LOWER CABLE P/N 87600518-001 REPLACED.Apr 13, 1996 · Dhav DHC8301 · Propeller Controlling SystemSDR CA960429009Turbine Case · punctured(CAN)AFTER TAKEOFF, VIBRATION FROM #2 ENGINE FOLLOWED BY ENGINE FIRE. AFM PROCEDURES CARRIED OUT, BOTH BOTTLES DISCHARGED. FIRE EXTINGUISHED BUT LATER REIGNITED AFTER LANDING, AIRPORT FIRE CREW EXTINGUISHED FIRE. A LARGE QUANTITY OF RESIDUAL OIL NOTED IN THEApr 11, 1996 · Dhav DHC8301 · Turbine SectionSDR CA960315006Spring · broken(CAN)CAPTAIN'S SEAT ASSEMBLY NOT POSITIVELY LOCKING IN FORE/AFT POSITION. SEAT UNLOCKED A COUPLE OF TIMES AND HAD TO BE SHAKEN BACK INTO POSITION IN TRACK. COMBINATION OF BOTH SEAT TRACK LOCKING PIN SPRING S BROKEN AND SEAT TRACK LOCKING HOLES FILLED WITH DUSTMar 8, 1996 · Dhav DHC8301 · Flight Compartment EquipmentSDR CA960311006Pc Board · burnt(CAN)ADVISORY LIGHT CONTROL BOX SHORTED OUT CAUSING A STRONG ELECTRICAL BURNING SMELL IN COCKPIT CAUTION LIGHTS SWITCHED FROM DIM TO BRIGHT ON THEIR OWN JUST PRIOR CREW COULD NOT SWITCH LIGHTS BACK TO DI M. ADVISORY LIGHT BOX PC BOARD 'B' FOUND BURNT.Feb 27, 1996 · Dhav DHC8301 · Flight Compartment LightingSDR CA960214005Blade · failed test(CAN) BLADE FAILED SHEAR WAVE TEST AS PER SB 14SF-61-A95.Feb 13, 1996 · Dhav DHC8301 · Propeller Blade SectionSDR CA960306001Selector Valve · failed(CAN)ON APPROACH THREE RED WARNING LIGHTS ON WITH NO GEAR MOVEMENT WHEN GEAR SELECTED DOWN. CREW DID GO AROUND. ALTERNATE GEAR EXTENSION, OK. ALSO NOSE WHEEL STEERING FAILED DURING TAXI. LANDING GEAR SELECTOR VALVE REPLACED.Feb 12, 1996 · Dhav DHC8301 · Landing Gear SelectorSDR CA960306002O-Ring · ruptured(CAN) ON APPROACH, THE CREW EXPERIENCED COMPLETE LOSS OF HYDRAULIC FLUID ON THE NUMBER TWO SYSTEM. THE CREW CARRIED OUT AN ALTERNATE GEAR EXTENSION. MAINTENANCE DISCOVERED THE PROBLEM TO BE CAUSED BY A RUPTURED 'O' RING ON A FITTING LEADING TO THE #2 ENGINE DRFeb 11, 1996 · Dhav DHC8301 · Hydraulic Pump (Electric/Engine), MainSDR CA960212010Carbon Seal · leaking(CAN) ON TAKEOFF ROLL, NR 2 ENGINE OIL PRESSURE WARNING LIGHT ON. TAKEOFF REJECTED. ENGINE OIL LEVEL FOUND DOWN 7 LITRES.Jan 29, 1996 · Dhav DHC8301 · Turbine Engine Accessory DriveSDR CA960129003Blade · failed ndt test(CAN)PROPELLER BLADE FAILED SHEAR WAVE NDT TEST AS PER SERVICE BULLETIN 14SF-61-A95.Jan 26, 1996 · Dhav DHC8301 · Propeller Blade SectionSDR CA960123010Torque Probe · faulty(CAN)ON DEPARTURE #2 ENGINE HAD AN UNCOMMANDED AUTOFEATHER. CREW SHUTDOWN THE ENGINE AND RETURNED TO BASE. MAINTENANCE REPLACED THE TORQUE PROBE. ENGINE RUN AND PROP CHECKS CARRIED OUT SERVICEABLE. AIRCRAF T RETURNED TO SERVICE.Jan 9, 1996 · Dhav DHC8301 · Engine BMEP/Torque IndicatingSDR CA951114004Line · leaking(CAN)HYDRAULIC LEAK FROUND IN NOSE LANDING GEAR BAY FROM GEAR EXTEND RETRACT LINE TO NLG DOOR.Nov 11, 1995 · Dhav DHC8301 · Landing Gear Door Retract SectionSDR CA960102003Connector · corroded(CAN)DURING SIO 8-61-03 INSPECTION, THE LEFT HAND CONNECTOR (9811-P13) WAS FOUND HEAVILY CORRODED. BACKSHELL AND CANNONN PLUG SHOWING SEVERE 'POWDERING' DUE TO EXCESSIVE CORROSION. THIS CORROSION POSSIBLY CAUSING LOSS OF CIRCUIT INTEGRITY IN AUTO-FEATHER SYSTOct 20, 1995 · Dhav DHC8301 · Propeller Feathering/Reversing
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