# Service difficulty reports: Dehavilland DHC-6-100 A list on [Dehavilland DHC-6-100](https://openairdocs.org/model/dehavilland-dhc-6-100.md). Newest first. General aviation reporting is voluntary. Page 1 of 2 · 53 reports - [SDR 2024FA0000861](https://openairdocs.org/sdr/2024FA0000861.md): Attach Fitting · cracked · Nov 22, 2024 · N227WW · Dhav DHC6100 · Wing, Landing Gear Attach Fittings > DISCOVERED RH WING STRUT UPPER ATTACH FITTING CRACKED DURING VISUAL INSPECTION. REMOVED STRUT FOR REPLACEMENT AND FOUND CRACK TO BE COMPLETE SEPARATION, - [SDR 2019FA0000247](https://openairdocs.org/sdr/2019FA0000247.md): Lever · broken · Aug 12, 2019 · N125PM · Dhav DHC6100 · Landing Gear Steering System > UPON 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 PREV - [SDR CA120507009](https://openairdocs.org/sdr/CA120507009.md): Bleed Valve · malfunctioned · May 2, 2012 · Dhav DHC6100 · Compressor Bleed Valve > (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 AF - [SDR CA090821002](https://openairdocs.org/sdr/CA090821002.md): Oil System · leaking · Aug 19, 2009 · Dhav DHC6100 · Turbine Engine Oil System > ACFT 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 OIL - [SDR CA090703001](https://openairdocs.org/sdr/CA090703001.md): Bolt · broken · Jun 30, 2009 · Dhav DHC6100 · Wheel/Ski/Float > (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 ATTA - [SDR CA090605006](https://openairdocs.org/sdr/CA090605006.md): Clamp · unserviceable · Jun 1, 2009 · Dhav DHC6100 · Propeller Blade Section > (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. - [SDR CA081125014](https://openairdocs.org/sdr/CA081125014.md): Pump · damaged · Oct 11, 2008 · Dhav DHC6100 · Fuel Boost Pump > (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. - [SDR CA090130007](https://openairdocs.org/sdr/CA090130007.md): Gear · failed · Jul 29, 2008 · Dhav DHC6100 · Accessory Gearboxes > THEENGINE 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 - [SDR CA080407005](https://openairdocs.org/sdr/CA080407005.md): Engine · stopped · Apr 3, 2008 · Dhav DHC6100 · Engine (Turbine/Turboprop) > AFTER 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 S - [SDR CA080130001](https://openairdocs.org/sdr/CA080130001.md): Bolt · broken · Jan 28, 2008 · Dhav DHC6100 · Wheel/Ski/Float > (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 ROUG - [SDR CA071128006](https://openairdocs.org/sdr/CA071128006.md): Engine · surges · Nov 3, 2007 · Dhav DHC6100 · Engine (Turbine/Turboprop) > (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 ESTAB - [SDR CA071107001](https://openairdocs.org/sdr/CA071107001.md): Engine · failed · Nov 3, 2007 · Dhav DHC6100 · Engine (Turbine/Turboprop) > (CAN) PILOTS HAD TO SHUTDOWN RT ENGINE. MAINTENANCE INSPECTION FOUND PROP WOULDN`T TURN, EXPECT POWER SECTION FAILURE. (TC NR 20071107001) - [SDR CA071212024](https://openairdocs.org/sdr/CA071212024.md): Exhaust Duct · cracked · Oct 26, 2007 · Dhav DHC6100 · Engine Collector/Tailpipe/Nozzle > (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 WAS - [SDR CA070717014](https://openairdocs.org/sdr/CA070717014.md): Line · failed · Jul 11, 2007 · Dhav DHC6100 · Turbine Engine Oil System > (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 - [SDR CA070223004](https://openairdocs.org/sdr/CA070223004.md): Skin · corroded · Feb 22, 2007 · Dhav DHC6100 · Fuselage Main, Plate/Skin > (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 ANCHOR - [SDR CA061128005](https://openairdocs.org/sdr/CA061128005.md): Compressor · damaged · Nov 15, 2006 · Dhav DHC6100 · Turbine Engine Compressor Section > (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 - [SDR CA051018003](https://openairdocs.org/sdr/CA051018003.md): Frame · cracked · Oct 10, 2005 · Dhav DHC6100 · Fuselage Main, Frame > DURING 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 LA - [SDR CA050912004](https://openairdocs.org/sdr/CA050912004.md): Mount · broken · Sep 9, 2005 · Dhav DHC6100 · Engine Mount Section > (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 ENO - [SDR CA050728008](https://openairdocs.org/sdr/CA050728008.md): Switch · failed · Jul 22, 2005 · Dhav DHC6100 · Propeller Controlling System > DURING 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 WITHOU - [SDR CA050714003](https://openairdocs.org/sdr/CA050714003.md): Cover · chafed · Jul 9, 2005 · Dhav DHC6100 · Turbine Section > ON 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 I - [SDR CA050708004](https://openairdocs.org/sdr/CA050708004.md): Pump · failed · Jul 2, 2005 · Dhav DHC6100 · Fuel Boost Pump > DURING 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 1 - [SDR CA050524003](https://openairdocs.org/sdr/CA050524003.md): Connecting Rod · binding · May 24, 2005 · Dhav DHC6100 · Air Intake Anti/De-Ice System > DURING 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 FO - [SDR CA050323010](https://openairdocs.org/sdr/CA050323010.md): Bracket · corroded · Mar 21, 2005 · Dhav DHC6100 · Rudder Structure > (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 COR - [SDR CA050207001](https://openairdocs.org/sdr/CA050207001.md): Tube · corroded · Feb 5, 2005 · Dhav DHC6100 · Aircraft Fuel Distribution System > (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 - [SDR CA041104009](https://openairdocs.org/sdr/CA041104009.md): Switch · failed · Oct 26, 2004 · Dhav DHC6100 · DC Generating System > (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 HA - [SDR CA031119002](https://openairdocs.org/sdr/CA031119002.md): Governor · failed · Nov 13, 2003 · Dhav DHC6100 · Turbine Governor > (CAN) NR 1 ENGINE POWER SURGING PRIOR TO LANDING, AFTER LANDING ENGINE FLAME OUT OCCURED. - [SDR CA030925006](https://openairdocs.org/sdr/CA030925006.md): Switch · shorted · Sep 1, 2003 · Dhav DHC6100 · Propeller/Propulsor System Wiring > (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 (INSTALLAT - [SDR CA021113005](https://openairdocs.org/sdr/CA021113005.md): Case · cracked · Nov 6, 2002 · Dhav DHC6100 · Engine (Turbine/Turboprop) > (CAN) CRACK FOUND IN CASE 6 O`CLOCK POSITION BY FUEL DUMP VALVE. - [SDR CA021016027](https://openairdocs.org/sdr/CA021016027.md): Switch · failed · Oct 13, 2002 · Dhav DHC6100 · Propeller Controlling System > (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 TES - [SDR CA020627010](https://openairdocs.org/sdr/CA020627010.md): Longeron · cracked · Jun 22, 2002 · Dhav DHC6100 · Nacelle/Pylon, Frame/Spar/Rib > (CAN) CRACK FOUND IN LONGERON IN NACELLE AS PER CF-81-07R4 (DHC SB6/509) - [SDR CA020627011](https://openairdocs.org/sdr/CA020627011.md): Sleeve · loose · May 27, 2002 · Dhav DHC6100 · Elevator Structure > (CAN) DURING INSPECTION SLEEVE FOUND LOOSE. - [SDR AUS20021467](https://openairdocs.org/sdr/AUS20021467.md): Arm · corroded · May 24, 2002 · Dhav DHC6100 · Ailerons > (AUS) LH OUTBOARD AILERON HINGE ARM CONTAINED EXFOLIATION CORROSION AROUND BOLT HOLE. - [SDR CA020124002](https://openairdocs.org/sdr/CA020124002.md): Wire · shorted · Jan 23, 2002 · Dhav DHC6100 · Windshield/Door Rain/Ice Removal > (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. - [SDR CA011002007](https://openairdocs.org/sdr/CA011002007.md): Bleed Valve · failed · Sep 16, 2001 · Dhav DHC6100 · Compressor Bleed Control > (CAN) DROP IN ENGINE TORQUE, PROP LEVER PUSHED FORWARD, TEMPED OUT AT 35 LBS TORQUE. - [SDR CA010910003](https://openairdocs.org/sdr/CA010910003.md): Compressor Wheel · failed · Aug 22, 2001 · Dhav DHC6100 · Turbine Engine Compressor Section > (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 3018490 - [SDR AUS20010885](https://openairdocs.org/sdr/AUS20010885.md): Engine · misrepaired · Aug 13, 2001 · Dhav DHC6100 · Turbine Section > (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 COMPR - [SDR CA010423013](https://openairdocs.org/sdr/CA010423013.md): Bolt · sheared · Apr 5, 2001 · Dhav DHC6100 · Main Landing Gear Attach Section > (CAN) BOLT ATTACHING LUG TIE ASSEMBLY (C6UFM1038-27) SHEARED. SEE DHC 1 PC + 32-15-100, ITEM 470 OF DHC-6-100. - [SDR CA000530013](https://openairdocs.org/sdr/CA000530013.md): Pump · jammed · Jun 2, 2000 · Dhav DHC6100 · Hydraulic Handpump, Main > (CAN) HYDRAULIC HAND PUMP JAMMED. - [SDR CA000530023](https://openairdocs.org/sdr/CA000530023.md): Rod · cracked · Apr 14, 2000 · Dhav DHC6100 · Aileron Control System > (CAN) FLIGHT CONTROL ROD FROM BELLCRANK TO AILERON FOUND CRACKED. ROD REPLACED. - [SDR AU000305](https://openairdocs.org/sdr/AU000305.md): Pedal · broken · Feb 15, 2000 · Dhav DHC6100 · Rudder Control System > (AUS) RIGHT RUDDER PEDAL BRAKE CONTROL OPERATING LEVER FAILED. PEDAL WAS FOUND TO BE A PRE-MOD TYPE. - [SDR CA991209003](https://openairdocs.org/sdr/CA991209003.md): Washer · displaced · Oct 21, 1999 · Dhav DHC6100 · Compressor Bleed Valve > (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. - [SDR CA990301001](https://openairdocs.org/sdr/CA990301001.md): Wheel · cracked · Feb 8, 1999 · Dhav DHC6100 · Wheel/Ski/Float > (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. - [SDR CA990111018](https://openairdocs.org/sdr/CA990111018.md): Liner · failed · Dec 23, 1998 · Dhav DHC6100 · Turbine Engine Combustion Section > (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 ACF - [SDR CA981202003](https://openairdocs.org/sdr/CA981202003.md): Rib · corroded · Nov 25, 1998 · Dhav DHC6100 · Horizontal Stabilizer, Spar/Rib > (CAN) HEAVY CORROSION FOUND ON THE HORIZONTAL STABILIZER CENTER RIB. SPOT WELDS WERE DELAMINATED THREE-QUARTERS OF THE LENGTH OF THE PART. - [SDR CA971231030](https://openairdocs.org/sdr/CA971231030.md): Circuit Breaker · fused · Dec 12, 1997 · Dhav DHC6100 · Passenger Compartment Lighting > (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. - [SDR CA970728003](https://openairdocs.org/sdr/CA970728003.md): Transfer Sleeve · scored · Jul 13, 1997 · Dhav DHC6100 · Turbine Engine Reduction Gear > (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 S - [SDR CA970121006](https://openairdocs.org/sdr/CA970121006.md): Deice Valve · failed · Jan 9, 1997 · Dhav DHC6100 · Airfoil Anti/De-ice System > (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 VALVES - [SDR CA960924020](https://openairdocs.org/sdr/CA960924020.md): Back Plate · worn out · Aug 23, 1996 · Dhav DHC6100 · Starter-Generator > (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 HA - [SDR CA961007008](https://openairdocs.org/sdr/CA961007008.md): Chip Detector · broken · Jul 21, 1996 · Dhav DHC6100 · Reciprocating Engine Oil System > (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. - [SDR EY2R9600895](https://openairdocs.org/sdr/EY2R9600895.md): Pilot Tube · corroded · Jul 1, 1996 · Dhav DHC6100 · Propeller Assembly > PILOT TUBE FOUND CORRODED. Next page: https://openairdocs.org/model/dehavilland-dhc-6-100/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 = 'DHC6100' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/model/dehavilland-dhc-6-100/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.