Dehavilland DHC-6-100

Service difficulty reports · 53

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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 = 'DHC6100'
  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 2024FA0000861Attach Fitting · crackedDISCOVERED RH WING STRUT UPPER ATTACH FITTING CRACKED DURING VISUAL INSPECTION. REMOVED STRUT FOR REPLACEMENT AND FOUND CRACK TO BE COMPLETE SEPARATION,Nov 22, 2024 · N227WW · Dhav DHC6100 · Wing, Landing Gear Attach FittingsSDR 2019FA0000247Lever · brokenUPON TURNING ONTO THE RAMP AFTER LANDING, A LARGE POP WAS HEARD IN THE NOSE, ALONG WITH LOSS OF NOSE WHEEL STEERING. IT WAS DISCOVERED THE STEERING ACTUATOR LEVER P/N 71-159-1(OR -9)WAS BROKEN IN TWO. VISUAL INSPECTION OF THE FRACTURE SURFACES INDICATE A PREVAug 12, 2019 · N125PM · Dhav DHC6100 · Landing Gear Steering SystemSDR CA120507009Bleed Valve · malfunctioned(CAN) CLIMBING THROUGH FL90, THE PILOT NOTICED THAT THE RT ENGINE COMPRESSOR SPEED NG, WAS INDICATING 101.5 PERCENT. REDUCED THE POWER AND NG RETURNED TO 98 PERCENT THEN TO CROSS CHECK, HE RETURNED TO CLIMB POWER AND AGAIN NG WENT TO101.5 PERCENT. SHORTLY AFMay 2, 2012 · Dhav DHC6100 · Compressor Bleed ValveSDR CA090821002Oil System · leakingACFT WAS ON RUNWAY, ENGINES POWERED UP AND BLUE SMOKE WAS OBSERVED AND SMELLED COMING INTO CABIN. TAKEOFF WAS ABORTED AND ACFT RETURNED TO GATE. MX CHECKS FOUND THAT SMOKE WAS ENTERING ACFT WHEN NR1 ENG BLEED AIR SELECTED ON. INSP OF NR 1 ENGINE REVEALED OILAug 19, 2009 · Dhav DHC6100 · Turbine Engine Oil SystemSDR CA090703001Bolt · broken(CAN) HEARD A LOUD BANG IN FLIGHT AND PILOTS NOTICED MOVEMENT IN THE FLOATS, ACFT LANDED WITHOUT ANY PROBLEMS. (2) AN6-20A BOLTS HOLDING THE LUG-TIE ROD TO FUSELAGE WERE FOUND BROKEN. BOLTS WERE REPLACED AND FLOAT STRUTS AND SPREADER BARS AND ALL FLOAT ATTAJun 30, 2009 · Dhav DHC6100 · Wheel/Ski/FloatSDR CA090605006Clamp · unserviceable(CAN) DURING VISUAL INSP, IT WAS NOTED THAT THE LOCK HOLES FOR THE A304 LINK PINS WERE DRILLED THROUGH THE PIN AND INTO THE OPPOSITE WALL. IT APPEARS THAT THIS OCCURED DURING A PREVIOUS OVERHAUL.Jun 1, 2009 · Dhav DHC6100 · Propeller Blade SectionSDR CA081125014Pump · damaged(CAN) OVERHAULED FUEL BOOST PUMP MAKING GRINDING NOSE WHEN TURNED ON. PUMP REMOVED AND REPLACED WITH OVERHAULED BOOST PUMP. FAILED PUMP HAD ONLY 6.1 HOURS TIME IN SERVICE SINCE OVERHAUL AND 5 FLIGHT CYCLES. FAILED PUMP RETURNED TO INSTALLER.Oct 11, 2008 · Dhav DHC6100 · Fuel Boost PumpSDR CA090130007Gear · failedTHEENGINE SUFFERED A COMPLETE LOSS OF POWER DUE TO A FAILURE OF A FIRST STAGE REDUCTION GEARBOX PLANETARY GEAR. FAILURE OF THE PLANETARY GEAR WAS THE RESULT OF INTERGRANULAR AND FATIGUE CRACKING TO THE PLANETARY GEAR BORE. THE BEARING SLEEVE SPUN WITHIN THE Jul 29, 2008 · Dhav DHC6100 · Accessory GearboxesSDR CA080407005Engine · stoppedAFTER A NORMAL TAKEOFF, THE CREW WENT THROUGH POWER 1, FLAPS UP AND POWER 2 AND AFTER SETTING POWER 2 PRIOR TO CLIMB CHECKS, THE CREW HEARD A LOUD POP AND SCRAPPING NOISE FROM THE NUMBER ONE ENGINE. THE FLIGHT CREW OBSERVED THAT THE NUMBER ONE PROPELLER WAS SApr 3, 2008 · Dhav DHC6100 · Engine (Turbine/Turboprop)SDR CA080130001Bolt · broken(CAN) DURING INSPECTION, THE TIE ROD TO FUSELAGE LUG WAS FOUND TO HAVE ONE OF THE (2) ATTACH BOLTS BROKEN. THE BREAK OCCURRED IN THE THREADED AREA OF THE BOLT. BOTH BOLTS WERE REPLACED AND THE AC WAS RETURNED TO SERVICE. THIS AC IS OPERATED IN A GENERALLY ROUGJan 28, 2008 · Dhav DHC6100 · Wheel/Ski/FloatSDR CA071128006Engine · surges(CAN) DURING CRUISE, THE CREW OBSERVED ENGINE (SURGES) AND PERFORMED AN INFLIGHT SHUTDOWN. POST FLIGHT INSPECTION REVEALED A SEIZED PROPELLER SHAFT AND POWER TURBINE BLADE DISTRESS. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABNov 3, 2007 · Dhav DHC6100 · Engine (Turbine/Turboprop)SDR CA071107001Engine · failed(CAN) PILOTS HAD TO SHUTDOWN RT ENGINE. MAINTENANCE INSPECTION FOUND PROP WOULDN`T TURN, EXPECT POWER SECTION FAILURE. (TC NR 20071107001)Nov 3, 2007 · Dhav DHC6100 · Engine (Turbine/Turboprop)SDR CA071212024Exhaust Duct · cracked(CAN) WHILE INSPECTING THE POWER SECTION FOR REASSEMBLY AFTER HSI, CIRCUMFERENTIAL CRACKS WERE DISCOVERED ALONG THE WELDS OF THE EXHAUST DUCT JUST FWD OF THE PT VANE MOUNTING FLANGE. (4) CRACKS RANGED IN LENGTH FROM .75 INCH TO 4.75 INCH. THE POWER SECTION WASOct 26, 2007 · Dhav DHC6100 · Engine Collector/Tailpipe/NozzleSDR CA070717014Line · failed(CAN) THE CREW OF FLOATPLANE EXPERIENCED A 10 LB LOSS OF TORQUE IN CRUISE ALONG WITH LOWERED OIL PRESSURE AND AN INCREASE IN OIL TEMP. THE PILOT CONTINUED THE FLIGHT TO A MAINTENANCE BASE USING REDUCED POWER ON THE AFFECTED ENGINE. AN UNEVENTFUL LANDING AND Jul 11, 2007 · Dhav DHC6100 · Turbine Engine Oil SystemSDR CA070223004Skin · corroded(CAN) AIRCRAFT IS IN THE PROCESS OF GOING THROUGH ITS (5) YEAR CORROSION INSPECTION. DURING INSPECTION, SEVERAL AREAS OF CORROSION WERE NOTED IN AREAS WHERE CORROSION IS USUALLY NOT FOUND. THE HORIZONTAL STAB LOWER SKIN (CENTER) WAS CORRODED AROUND SOME ANCHORFeb 22, 2007 · Dhav DHC6100 · Fuselage Main, Plate/SkinSDR CA061128005Compressor · damaged(CAN) ON POWER APPLICATION FOR TAKEOFF, THE #2 ENGINE ACCELERATED NORMALLY TO TAKEOFF POWER. AS THE AIRCRAFT BEGAN TO CLIMB ONTO THE STEP, THE F/O OBSERVED A FLASH OF LIGHT AND HEARD A BANG FROM THE ENGINE. THE TAKEOFF WAS REFECTED AND THE AIRCRAFT RETURNED Nov 15, 2006 · Dhav DHC6100 · Turbine Engine Compressor SectionSDR CA051018003Frame · crackedDURING SCHEDULED INSPECTION FOR SB 6/521 AND CF 95-12, A SINGLE CRACK WAS SUSPECTED IN THE WEB AREA OF THE AFT SECTION OF THE RT SIDE FRAME. AN EDDY CURRENT INSPECTION CONFIRMED THE CRACK AS WELL AS SMALLER CRACKS EMANATING FROM THREE ADJACENT RIVETS. THE LAOct 10, 2005 · Dhav DHC6100 · Fuselage Main, FrameSDR CA050912004Mount · broken(CAN) AFTER TAKEOFF, PILOT ENCOUNTERED PWR LEVER MISMATCH AS REDUCED TO CLIMB POWER. REPORTED PROBLEM AND LANDED UNEVENTFULLY. INVESTIGATION REVEALED THAT TOP ENGINE MOUNT ON NR 1 ENG HAD BROKEN AT A POINT BETWEEN FLANGE AND BASE. THIS CAUSED ENG TO SAG ENOSep 9, 2005 · Dhav DHC6100 · Engine Mount SectionSDR CA050728008Switch · failedDURING CLIMB-OUT, THE FLT CREW EXPERIENCED NR 2 ENGINE AND PROP SURGING. ENG POWER WAS REDUCED, AND PROPS ADJUSTED TO MIN GOVERNING. IN THIS CONFIGURATION THE SURGING WAS NOT PRESENT. FLIGHT CREW DIVERTED TO A MAINTENANCE BASE AND LANDED UNEVENTFULLY WITHOUJul 22, 2005 · Dhav DHC6100 · Propeller Controlling SystemSDR CA050714003Cover · chafedON ENGINE SHUTDOWN, THE CAPTAIN HEARD A RUBBING SOUND EMANATING FROM THE NR 1 ENGINE. TURNING THE PROPELLER BY HAND REPRODUCED THE RUBBING SOUND. THE POWER SECTION WAS REMOVED FOR INVESTIGATION. REMOVAL OF THE PT WHEEL REVEALED THAT THE NR 3 BEARING COVER IJul 9, 2005 · Dhav DHC6100 · Turbine SectionSDR CA050708004Pump · failedDURING EMMA CHECK, THE NR 1 FUEL SYSTEM STRAINER WAS FOUND TO BE HEAVILY CONTAMINATED WITH A FINE, GRITTY SUBSTANCE THAT STAYED SUSPENDED IN THE FUEL. FUEL TANKS AND DRAINS WERE FOUND TO BE CLEAR. FURTHER INVESTIGATION REVEALED THAT THE OUT PUT FROM THE NR 1Jul 2, 2005 · Dhav DHC6100 · Fuel Boost PumpSDR CA050524003Connecting Rod · bindingDURING OVERHAUL AND FUNCTION TESTING, THE INTAKE DEFLECTOR ACTUATOR WAS FOUND TO BE BINDING DURING OPERATION. THE CONNECTING ROD HAD BEEN ASSEMBLED AND RIGGED IAW THE CMM CH 71-60-01, FIGURE 1, PAGE 5, WITH THE ROD ENDS AT 90 DEGREES TO EACH OTHER. IT WAS FOMay 24, 2005 · Dhav DHC6100 · Air Intake Anti/De-Ice SystemSDR CA050323010Bracket · corroded(CAN) DURING THE FIVE YEAR CORROSION CHECK, BOTH RUDDER TORQUE TUBE ATTACH BRACKETS WERE FOUND TO BE HEAVILY RUSTED FROM THE INSIDE. THERE WAS NO EVIDENCE OF CORROSION PROOFING HAVING BEEN INSTALLED ON THE INSIDE OF THE BRACKETS. AIRCRAFT IS OPERATED IN A CORMar 21, 2005 · Dhav DHC6100 · Rudder StructureSDR CA050207001Tube · corroded(CAN) INVESTIGATION OF A (FUEL SMELL IN THE CABIN) AND A MINOR EXTERNAL FUEL LEAK REVEALED THAT WELDED FUEL TUBE ASSY BETWEEN FUEL TANK AND FLEX HOSE TO THE WING STRUT WAS LEAKING. REMOVAL OF ADEL CLAMP REVEALED CORROSION PITS UNDERNEATH WITH ASSOCIATED FUEL Feb 5, 2005 · Dhav DHC6100 · Aircraft Fuel Distribution SystemSDR CA041104009Switch · failed(CAN) WHILE TROUBLESHOOTING A RECURRENT DC GENERATION SNAG, THE GENERATOR BUSS-TIE SWITCH WAS FOUND TO BE FAILING INTERMITTENTLY. THE SWITCH WAS REPLACED AND THE SNAG CLEARED. THIS SWITCH IS NOT A TRACKABLE ITEM AND THERE ARE NO EXISTING RECORDS OF IT EVER HAOct 26, 2004 · Dhav DHC6100 · DC Generating SystemSDR CA031119002Governor · failed(CAN) NR 1 ENGINE POWER SURGING PRIOR TO LANDING, AFTER LANDING ENGINE FLAME OUT OCCURED.Nov 13, 2003 · Dhav DHC6100 · Turbine GovernorSDR CA030925006Switch · shorted(CAN) WHILE TAXIING FROM DOCK, NR 1 ENGINE DID NOT RESPOND TO (REVERSE) COMMAND BUT POWERED UP TO FORWARD MODE. FOUND WIRING WRAP INTERFERED WITH PROP RESET SWITCH IN OVERHEAD POWER LEVER QUADRANT. MODIFICATION WAS COMPLETED IAW DHC-6-100, MOD6/1912 (INSTALLATSep 1, 2003 · Dhav DHC6100 · Propeller/Propulsor System WiringSDR CA021113005Case · cracked(CAN) CRACK FOUND IN CASE 6 O`CLOCK POSITION BY FUEL DUMP VALVE.Nov 6, 2002 · Dhav DHC6100 · Engine (Turbine/Turboprop)SDR CA021016027Switch · failed(CAN) AIRCRAFT WAS TAXIING AWAY FROM DOCK WHEN FLIGHT CREW DEMANDED REVERSE POWER FROM NR 2 ENGINE. IT FAILED TO RESPOND AND AIRCRAFT HIT THE DOCK WITH FRONT OF RT FLOAT. FAILURE OF PROP TO RESPOND TO POWER LEVER INPUT IS ATTRIBUTED TO THE PROP OVERSPEED TESOct 13, 2002 · Dhav DHC6100 · Propeller Controlling SystemSDR CA020627010Longeron · cracked(CAN) CRACK FOUND IN LONGERON IN NACELLE AS PER CF-81-07R4 (DHC SB6/509)Jun 22, 2002 · Dhav DHC6100 · Nacelle/Pylon, Frame/Spar/RibSDR CA020627011Sleeve · loose(CAN) DURING INSPECTION SLEEVE FOUND LOOSE.May 27, 2002 · Dhav DHC6100 · Elevator StructureSDR AUS20021467Arm · corroded(AUS) LH OUTBOARD AILERON HINGE ARM CONTAINED EXFOLIATION CORROSION AROUND BOLT HOLE.May 24, 2002 · Dhav DHC6100 · AileronsSDR CA020124002Wire · shorted(CAN) WIRE INSULATION WAS FOUND BURNED AND APPEARED TO HAVE SHORTED OUT ON OVERHEAD SWITCH PANEL IN FLIGHT COMPARTMENT, WHICH CAUSED ELECTRICAL BURNING ODOR IN THE FLIGHT DECK.Jan 23, 2002 · Dhav DHC6100 · Windshield/Door Rain/Ice RemovalSDR CA011002007Bleed Valve · failed(CAN) DROP IN ENGINE TORQUE, PROP LEVER PUSHED FORWARD, TEMPED OUT AT 35 LBS TORQUE.Sep 16, 2001 · Dhav DHC6100 · Compressor Bleed ControlSDR CA010910003Compressor Wheel · failed(CAN) HOT START LACK OF POWER.HOT SECTION REMOVED FROM POWER OLANT. SERVICEABLE HOT SECTION INSTALLED AIRCRAFT RUN CARRIED OUT. FOUND SATISFACTORY. SHROUD P/N 3020259STATOR ASSY P/N 3018490Aug 22, 2001 · Dhav DHC6100 · Turbine Engine Compressor SectionSDR AUS20010885Engine · misrepaired(AUS) FOLLOWING REPAIR FOR OVERTEMP AND FOD IN THE USA THE RT ENGINE WAS FITTED AND PREPARED FOR STARTING. THE ENGINE WAS WOUND OVER WITHOUT LIGHTING UP AND AN INTERNAL RUBBING NOISE WAS HEARD. THE ENGINE WAS PARTIALLY DISMANTLED AND INSPECTION FOUND THE COMPRAug 13, 2001 · Dhav DHC6100 · Turbine SectionSDR CA010423013Bolt · sheared(CAN) BOLT ATTACHING LUG TIE ASSEMBLY (C6UFM1038-27) SHEARED. SEE DHC 1 PC + 32-15-100, ITEM 470 OF DHC-6-100.Apr 5, 2001 · Dhav DHC6100 · Main Landing Gear Attach SectionSDR CA000530013Pump · jammed(CAN) HYDRAULIC HAND PUMP JAMMED.Jun 2, 2000 · Dhav DHC6100 · Hydraulic Handpump, MainSDR CA000530023Rod · cracked(CAN) FLIGHT CONTROL ROD FROM BELLCRANK TO AILERON FOUND CRACKED. ROD REPLACED.Apr 14, 2000 · Dhav DHC6100 · Aileron Control SystemSDR AU000305Pedal · broken(AUS) RIGHT RUDDER PEDAL BRAKE CONTROL OPERATING LEVER FAILED. PEDAL WAS FOUND TO BE A PRE-MOD TYPE.Feb 15, 2000 · Dhav DHC6100 · Rudder Control SystemSDR CA991209003Washer · displaced(CAN) THE NUT HOLDING THE BLEED VALVE PISTON ASSY WAS FOUND TO BE OVERTORQUED THIS.. THIS CAUSED THE SILICONE WASHER TO DISPLACE ALLOWING THE FACE PLATE TO SHIFT WHICH CAUSED THE LEAK.Oct 21, 1999 · Dhav DHC6100 · Compressor Bleed ValveSDR CA990301001Wheel · cracked(CAN) WHEEL FOUND CRACKED. CRACK 20 CM LONG HAD OPENED ABOUT 6 MM. THE CRACK HAD PASSED THROUGH TWO FINS AND WAS PROGRESSING TOWARDS THE OUTSIDE OF THE RIM. TIRE DID NOT DEFLATE. NO MECHANICAL DAMAGE IN AREA OF CRACK.Feb 8, 1999 · Dhav DHC6100 · Wheel/Ski/FloatSDR CA990111018Liner · failed(CAN) DURING FLIGHT, NR 1 ENGINE SURGED AND A BANG WAS HEARD, BUT ALL ENGINE PARAMETERS WERE NORMAL. THE CABIN THEN FILLED WITH SMOKE, BLEED AIR VALVES WERE CLOSED. THERE WERE TWO MORE SURGES AND BANGS WITH THE FUEL FLOW RISING. THE ENG WAS SHUTDOWN AND ACFDec 23, 1998 · Dhav DHC6100 · Turbine Engine Combustion SectionSDR CA981202003Rib · corroded(CAN) HEAVY CORROSION FOUND ON THE HORIZONTAL STABILIZER CENTER RIB. SPOT WELDS WERE DELAMINATED THREE-QUARTERS OF THE LENGTH OF THE PART.Nov 25, 1998 · Dhav DHC6100 · Horizontal Stabilizer, Spar/RibSDR CA971231030Circuit Breaker · fused(CAN) WHEN GROUND POWER APPLIED, AND CABIN LIGHTS SELECTED ON, SMOKE WAS OBSERVED COMING FROM THE OVERHEAD CIRCUIT BREAKER PANEL. WIRING FOR THE LEFT HAND CABIN LIGHTS DIM WAS FOUND COMPLETELY BURNT. THE 5 AMP CIRCUIT BREAKER WAS FUSED IN THE CLOSED POSITION. Dec 12, 1997 · Dhav DHC6100 · Passenger Compartment LightingSDR CA970728003Transfer Sleeve · scored(CAN) DURING INSEPECTION OF THE REDUCTION GEAR NOSE CASE CHIP DETECTOR AND OIL SCREENS, SUBSTANTIAL AMOUNTS OF METAL PARTICLES WERE FOUND. THE ENGINE WAS REMOVED AND SENT FOR INSPECTION AND REPAIR. DISASSEMBLY REVEALED THE PROPELLER SHAFT TRANSFER SLEEVE HAD SJul 13, 1997 · Dhav DHC6100 · Turbine Engine Reduction GearSDR CA970121006Deice Valve · failed(CAN) ON APPROACH AIRCRAFT ENCOUNTERED HEAVY ICING CONDITIONS. AFTER LANDING THE INBOARD HALF OF WING FOUND COVERED WITH ICE. WING DEICE DISTRIBUTOR VALVE WAS CYCLED BUT DID NOT WORK. VALVE REPLACED. A MOD WILL BE INTRODUCED TO INSTALL HEATER AROUND THE VALVESJan 9, 1997 · Dhav DHC6100 · Airfoil Anti/De-ice SystemSDR CA960924020Back Plate · worn out(CAN) DURING OVERHAUL A PIECE OF BRASS WAS NOTED PROTRUDING BETWEEN THE BACK PLATE AND THE ARMATURE SHAFT. BRASS TURNED OUT TO BE A BRASS SHIM. INSERTED BETWEEN THE ARMATURE AND THE BACK PLATE SEAT. BACK PLATE FOUND WORN WELL BEYOND TOLERANCES AND THE BRASS HAAug 23, 1996 · Dhav DHC6100 · Starter-GeneratorSDR CA961007008Chip Detector · broken(CAN) ON TAKEOFF OIL PRESSURE ON LEFT ENGINE STARTED DROPPING AND VISUAL INSPECTION NOTED OIL POURING FROM ENGINE COWLING. ENGINE SHUTDOWN AND AIRCRAFT RETURNED. CANNON PLUG ON CHIP DETECTOR WAS INSTALLED 180 DEGREES OUT AND WAS HITTING ON LOWER COWLING RIB.Jul 21, 1996 · Dhav DHC6100 · Reciprocating Engine Oil SystemSDR EY2R9600895Pilot Tube · corrodedPILOT TUBE FOUND CORRODED.Jul 1, 1996 · Dhav DHC6100 · Propeller Assembly
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