# Service difficulty reports: Dehavilland DHC-6-200 A list on [Dehavilland DHC-6-200](https://openairdocs.org/model/dehavilland-dhc-6-200.md). Newest first. General aviation reporting is voluntary. Page 1 of 2 · 54 reports - [SDR CA190527026](https://openairdocs.org/sdr/CA190527026.md): Resistor · burned · Apr 25, 2019 · Dhav DHC6200 · Flight Compartment Lighting > (CAN) A FEW MINUTES AFTER TAKEOFF, THE PILOTS NOTICED AN ELECTRICAL BURNING SMELL. THE PILOTS COMPLETED THE CHECKLIST AND NOTICED THAT THE FUMES SEEMED TO DECREASE AFTER ONE MINUTE. THE PILOTS RETURNED THE AIRCRAFT TO BASE. MAINTENANCE INSPECTED AND FOUND ELEC - [SDR CA190328016](https://openairdocs.org/sdr/CA190328016.md): Skin · debonded · Mar 27, 2019 · Dhav DHC6200 · Wing, Plate/Skin > (CAN) WHEN SB V6/0018 WAS CARRIED OUT, DISBOND WAS FOUND TO THE OUTER LIMITS OF THE INSPECTION CRITERIA (YW 65 TO YW 155) ON THE RH UPPER WING SURFACE TO CORRUGATE. DUE TO THE EXTENT OF THE DISBOND, IT WAS DECIDED TO CARRY OUT FURTHER INSPECTION. DURING THE AD - [SDR CA190314011](https://openairdocs.org/sdr/CA190314011.md): Switch · failed · Mar 7, 2019 · Dhav DHC6200 · Propeller Feathering/Reversing > (CAN) DURING A TRAINING FLIGHT, THE CO-PILOT LET THE NOSE GET TOO HIGH, IN RESPONSE, THE PILOT PUSHED FORWARD AGGRESSIVELY TO AVOID A POTENTIAL STALL, AT WHICH POINT THE LEFT PROPELLER FEATHERED. AT THIS POINT THE AIRCRAFT ALTITUDE HAD BEEN CORRECTED. WHEN THE - [SDR CA190315016](https://openairdocs.org/sdr/CA190315016.md): Switch · failed · Mar 2, 2019 · Dhav DHC6200 · Propeller Feathering/Reversing > (CAN) PILOT REPORTED THAT THE PROPELLER DID NOT FEATHER WHILE CONDUCTING GROUND FUNCTION CHECK OF THE AUTO FEATHER SYSTEM. MAINTENANCE CHANGED THE SWITCH AND THE SYSTEM FUNCTION TESTED SERVICEABLE. - [SDR CA160317011](https://openairdocs.org/sdr/CA160317011.md): Strut · damaged · Feb 28, 2016 · Dhav DHC6200 · Wing, Attach Fittings > (CAN) DURING AN INSPECTION OF THE WING STRUT LOWER ATTACHMENT BOLTS, CORROSION WAS FOUND AT THE LOWER LUG ATTACHMENT POINT ON BOTH THE LT AND RT STRUTS. CORROSION WAS EVIDENT AROUND THE PHENOLIC WASHERS SO THE WASHERS WERE REMOVED FOR FURTHER INVESTIGATION WHI - [SDR CA150318016](https://openairdocs.org/sdr/CA150318016.md): Pressure Switch · failed · Mar 14, 2015 · Dhav DHC6200 · Propeller Feathering/Reversing > (CAN) AFTER ACFT HAD DOCKED, MAINTENANCE NOTICED AN OIL LEAK FROM THE NR 1 ENGINE COWLING. UPON INVESTIGATION IT WAS FOUND THAT THE SOURCE OF THE OIL LEAK WAS THE AUTOFEATHER TORQUE PRESSURE SWITCH. THE SWITCH WAS REPLACED AND A FUNCTION CHECK OF THE SYS CARR - [SDR CA150422003](https://openairdocs.org/sdr/CA150422003.md): Leg Assy · corroded · Nov 28, 2014 · Dhav DHC6200 · Nose/Tail Landing Gear Strut/Axle > (CAN) MAIN LANDING GEAR NDT`D BY AUTHORIZED FACILITY PER 5 YEAR INSPECTION REQUIREMENT. PITTING, CORROSION & BOLT FLANGE HOLES OUT OF LIMITS FOUND DURING INTERNAL INSPECTION. GEAR LEG BEYOND ECONOMICAL REPAIR. NEW GEAR LEG PURCHASED & INSTALLED. - [SDR CA141022009](https://openairdocs.org/sdr/CA141022009.md): Pressure Switch · failed · Oct 18, 2014 · Dhav DHC6200 · Propeller Feathering/Reversing > (CAN) AFTER TAKE OFF, THROUGH 400 FT. THE LEFT ENGINE FEATHERED. PILOTS ORIGINALLY THOUGHT THERE WAS AN ENGINE FAILURE AS TORQUE WAS INDICATING ZERO. PIC MADE THE CALL FOR FLAPS 30. UPON CONFIRMING AND PARTIALLY RETARDING NR 1 POWER LEVER, THE TORQUE CAME BACK - [SDR CA120606003](https://openairdocs.org/sdr/CA120606003.md): Compressor · fod · May 14, 2012 · Dhav DHC6200 · Turbine Engine Compressor Section > (CAN) DURING FLIGHT, THE PILOT REPORTED A LOUD NOISE FROM THE LT ENGINE. THE TORQUE PRESSURE DROPPED TO 20 LBS BUT ALL OTHER INDICATIONS WERE NORMAL. THE PILOT REDUCED POWER TO IDLE AND OBSERVED THE ENGINE TEMPERATURE STILL 750 C. THE ENGINE WAS SHUTDOWN AN - [SDR CA120514008](https://openairdocs.org/sdr/CA120514008.md): Engine · failed · May 10, 2012 · Dhav DHC6200 · Engine (Turbine/Turboprop) > (CAN) PILOT REPORTED A BIG BANG AND POP COMING FROM THE LT ENGINE, TORQUE PRESSURE DROPPED TO 20 LBS BUT ALL OTHER INDICATIONS WERE NORMAL. HE THEN REDUCED POWER TO IDLE AND OBSERVED LT TEMPERATURE STILL AT 750 CELSIUS, ALL OTHER INDICATIONS WERE NORMAL. HE TH - [SDR CA120323006](https://openairdocs.org/sdr/CA120323006.md): Bellcrank · warped · Mar 23, 2012 · Dhav DHC6200 · Elevator Control System > (CAN) DURING REPETITIVE INSPECTION OF ELEVATOR BELLCRANK AND AREA, AN AME NOTICED SLIGHT SIGNS OF CHAFFING AROUND UPPER AND LOWER ELEVATOR CABLE ATTACH POINTS. BELLCRANK WAS REMOVED AND FURTHER INVESTIGATION FOUND PART WAS WARPED CAUSING THE EVIDENT CHAFFING. - [SDR CA110922005](https://openairdocs.org/sdr/CA110922005.md): Head · loose · Sep 21, 2011 · Dhav DHC6200 · Fire Bottle, Portable > (CAN) PRESSURE GAUGE ON THE FIRE EXTINGUISHER READ ZERO. HEAD ASSY WAS FOUND TO BE LOOSE ON THE BOTTLE WHICH ALLOWED THE CONTENTS TO ESCAPE. FIRE EXTINGUISHER IS 4.5 YEARS OLD. UNIT IS MODEL HAL-035-AVN. - [SDR CA110120003](https://openairdocs.org/sdr/CA110120003.md): O-Ring · leaking · Jan 19, 2011 · Dhav DHC6200 · Engine Fuel Pump > (CAN) THE AIRCRAFT HAD A FUEL LEAK THAT ONLY STARTED AFTER A HIGH POWER APPLICATION. UPON INSPECTION, IT WAS NOTED THE O-RING HAD PARTIALLY DISPLACED FROM AROUND THE DISCHARGE FILTER BOWL AND A GAP WAS NOTED BETWEEN THE BOWL AND THE PUMP HOUSING. AFTER FURTHE - [SDR CA100218011](https://openairdocs.org/sdr/CA100218011.md): Oil Filter · separated · Feb 11, 2010 · Dhav DHC6200 · Turbine Engine Oil System > (CAN) INNER CONE (SCREEN) SEAMS ARE BECOMING UNGLUED. (TC 20100218011) - [SDR CA080407010](https://openairdocs.org/sdr/CA080407010.md): Cable · broken · Apr 2, 2008 · Dhav DHC6200 · Landing Gear Steering System > STEERING CABLE BROKE ON TAXI WHILE THE AIRCRAFT WAS PREPARING FOR TAKEOFF. - [SDR CA080401004](https://openairdocs.org/sdr/CA080401004.md): Engine · power loss · Mar 26, 2008 · Dhav DHC6200 · Engine (Turbine/Turboprop) > ON TAKEOFF, THE LEFT ENGINE LAGGED BEHIND NOT PRODUCING MAX. POWER, TROUBLE SHOOTING FOUND THE TEMPERATURE COMPENSATOR UNIT LEAKING P3 AIR. THE PART WAS REPLACED AND THE PROBLEM WAS FIXED. (TC NR 20080401004) - [SDR CA070515002](https://openairdocs.org/sdr/CA070515002.md): Collar · cracked · May 14, 2007 · Dhav DHC6200 · Landing Gear Steering System > (CAN) DURING MAINTENACE TO REPAIR THE NOSE GEAR ASSEMBLY IT WAS NOTED THAT THE STEERING COLLAR WAS CRACKED. THE NOSE GEAR WAS THEN FULLY DISASSEMBLED TO REMOVE THE CRACKED STEERING COLLAR. THE NLG WAS THEN VISUALLY INSPECTED AND SOME OF THE ITEMS SENT FOR NDT. - [SDR CA061219020](https://openairdocs.org/sdr/CA061219020.md): Engine · failed · Nov 15, 2006 · Dhav DHC6200 · Engine (Turbine/Turboprop) > (CAN) DURING TAXI, THE ENGINE EMITTED A NOISE AND LOST POWER. SUBSEQUENT INSPECTION REVEALED INTERNAL ENGINE DAMAGE. MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. - [SDR CA060315004](https://openairdocs.org/sdr/CA060315004.md): Relay · failed · Mar 9, 2006 · Dhav DHC6200 · DC Generator-Alternator > A/C SHUT DOWN AFTER FLT, CREW REPORTED NR 2 GENERATOR WARNING LIGHT DID NOT ILLUMINATE. A/C WAS RUN FOR TROUBLESHOOTING, DURING WHICH TIME GEN FUNCTIONED INTERMITTENTLY. WHEN ENGINES WERE SHUT DOWN, SMOKE BEGAN TO EMANATE FROM THE ELECTRICAL BAY IN THE CABIN - [SDR CA060208011](https://openairdocs.org/sdr/CA060208011.md): Fcu · fluctuates · Feb 2, 2006 · Dhav DHC6200 · Fuel Control/Turbine Engines > (CAN) WHEN AC WAS ABOUT 10 MIN FROM LANDING, ON DESCENT, ENG POWER LEVERS WERE RETARDED FROM 38 LBS OF TORQUE. THE RT ENGINE TQ AND T5 STARTED FLUCTUATING. RT POWER LEVER WAS BROUGHT BACK FURTHER BUT TQ AND T5 CONTINUED TO RISE. RT POWER LEVER WAS PUT TO IDLE - [SDR CA061201005](https://openairdocs.org/sdr/CA061201005.md): Rib · cracked · Dec 28, 2005 · Dhav DHC6200 · Elevator, Spar/Rib > (CAN) WHILE PERFORMING AD CF-82-21 R1 USING A BORESCOPE, CRACKS WERE FOUND AT THE ATTACHMENT POINT OF THE TORQUE TUBE TO THE ELEVATOR RIB. SEE PHOTOS AND DAMAGE REPORT. (TC NR 20061201005) - [SDR AU510001605](https://openairdocs.org/sdr/AU510001605.md): Fuel Sys · faulty · Nov 7, 2005 · Dhav DHC6200 · Aircraft Fuel System > FUEL SYSTEM SUSPECT FAULTY. LIMITED INFORMATION PROVIDED. - [SDR CA051108004](https://openairdocs.org/sdr/CA051108004.md): Pitot Head · damaged · Nov 4, 2005 · Dhav DHC6200 · Pitot/Static System > (CAN) THE CAPTAIN REPORTED A 10 - 15 KTS SPLIT ON AIRSPEED INDICATIONS BETWEEN PILOT-F/O INDICATORS. MAINTENANCE INVESTIGATION REVEALED THAT THE CAPTAINS (LT) PITOT HEAD WAS RESTRICTED SLIGHTLY. FURTHER INVESTIGATION REVEALED THAT THE AIR TUBE HAD BEGUN TO EX - [SDR CA050711007](https://openairdocs.org/sdr/CA050711007.md): Strut · damaged · Jul 8, 2005 · Dhav DHC6200 · Main Landing Gear Strut/Axle/Truck > (CAN) DURING WALKAROUND, THE FLIGHT CREW OBSERVED A RIVET HEAD MISSING FROM THE OUTSIDE OF THE LOWER LUG OF THE LT FORWARD FLOAT STRUT. THE AIRCRAFT WAS FERRIED TO MAINTENANCE WHERE THE STRUT WAS REMOVED AND INSPECTED. THE RIVET STEM SHOWED SIGNS OF INTERNAL - [SDR AU510001604](https://openairdocs.org/sdr/AU510001604.md): Panel · mismarked · Mar 6, 2005 · Dhav DHC6200 · Instrument Panel > NO LABELS ON DUAL RADIOS/INDICATORS AND ADVISORY LABELS AS REQUIRED BY ANO 108.34 SECTION 6.2. - [SDR CA050309013](https://openairdocs.org/sdr/CA050309013.md): Csu · failed · Mar 6, 2005 · Dhav DHC6200 · Propeller Controlling System > (CAN) ON RUNUP AFTER INSTALLATION, IT WAS FOUND THAT THE OVERHAULED PROPELLER CONTROL UNIT WOULD NOT FUNCTION PROPERLY. THE PROPELLER REMAINED IN THE BETA MODE AND THERE WAS NO CONTROL OTHER THAN FEATHER/UNFEATHER. ANY ADDITION OF POWER RESULTED IN THE PROPE - [SDR CA050128007](https://openairdocs.org/sdr/CA050128007.md): Hinge Bracket · damaged · Nov 20, 2004 · Dhav DHC6200 · Trailing Edge Flaps > (CAN) LOOSE RIVETS ATTACHING CENTER FLAP HINGE BRACKET TO IB AND OB PORTIONS OF FORE FLAP ASSY. HIDDEN PROBLEM DOES NOT REALLY SHOW UP UNTILL YOU TAKE THE FLAP OFF. FORE FLAP DISASSEMBLED AND RIVETS REPLACED WITH NEW. - [SDR CA040928014](https://openairdocs.org/sdr/CA040928014.md): Engine · failed · Sep 27, 2004 · Dhav DHC6200 · Engine (Turbine/Turboprop) > (CAN) ON DESCENT TO LAND, THE PILOT HEARD A LOUD BANG AND LOSS OF TQ IN THE LT ENGINE. ALL OTHER INDICATIONS WERE NORMAL. THEY SECURED THE LEFT ENGINE AND MADE A NORMAL LANDING. - [SDR CA040804011](https://openairdocs.org/sdr/CA040804011.md): Fuel Control · failed · Aug 3, 2004 · Dhav DHC6200 · Fuel Control/Turbine Engines > (CAN) WHEN THE FLIGHT CREW REDUCED POWER ON FINAL APPROACH, NR 1 ENGINE FAILED TO RESPOND TO POWER LEVEL INPUT, AND REMAINED AT 15 LBS TORQUE. THE TORQUE THEN SLOWLY DROPPED TO IDLE WITHOUT ANY POWER LEVER INPUT AND A LANDING WAS COMPLETED WITHOUTFURTHER INCI - [SDR CA030723005](https://openairdocs.org/sdr/CA030723005.md): Switch · misinstalled · Jul 19, 2003 · Dhav DHC6200 · Propeller Feathering/Reversing > (CAN) NR 1 ENGINE, BETA BACK-UP SYSTEM, STEADY BLUE LIGHT ILLUMINATED IN CRUISE. FAULT FOUND TO BE KLIXON SPRING PN KX5, DRILLED MOUNTING HOLES NOT LINING UP WITH SWITCH KX511. - [SDR AUS20030500](https://openairdocs.org/sdr/AUS20030500.md): Control Cable · frayed · Apr 24, 2003 · Dhav DHC6200 · Aileron Control System > (AUS) AILERON CABLES PNO C6CW1031-1 (2OFF) AND PNO C6CW1032-1 CONTAINED BROKEN STRANDS IN AREA OF WING ROOT FAIRLEADS. - [SDR CA021120007](https://openairdocs.org/sdr/CA021120007.md): Gear · worn · Nov 20, 2002 · Dhav DHC6200 · Engine Fuel Pump > (CAN) FUEL PUMP WAS REMOVED FROM ENGINE DURING ENGINE CONVERSION FROM PT6A-20 TO PT6A-27. THE PUMP WAS SENT TO PWC FOR BENCH TEST AND INHIBITING. CONTRACTOR ASSERTS THAT THE PUMP WAS TESTED AND THAT THE SEALS WERE LEAKING. DISMANTLED THE PUMP AND FOUND THAT TH - [SDR CA021011002](https://openairdocs.org/sdr/CA021011002.md): Engine · overtorqued · Sep 26, 2002 · Dhav DHC6200 · Engine (Turbine/Turboprop) > (CAN) AIRCRAFT HIT LARGE WAVE SWELL AND CREW INADVERTENTLY ALLOWED POWER LEVER TO ADVANCE FORWARD TO OVER TORQUE ENGINE. POWER SECTION WAS REPLACED. - [SDR CA020617004](https://openairdocs.org/sdr/CA020617004.md): Cover · failed · May 27, 2002 · Dhav DHC6200 · Fuselage Miscellaneous Structure > (CAN) THE PLASTIC COVER UNDER THE PILOT SEAT THAT PROTECTS THE AILERON PULLEY AND CABLE WAS DAMAGED. THE AIRCRAFT HIT SOME TURBULENCE AND A SMALL ROCK CAME OFF THE FLOOR AND DOWN INTO THE PULLEY BETWEEN THE CABLE AND PULLEY JAMMING THE CONTROL. AIRCRAFT MADE A - [SDR CA020507013](https://openairdocs.org/sdr/CA020507013.md): Bolt · sheared · Apr 24, 2002 · Dhav DHC6200 · Engine Mount Section > (CAN) DURING ENGINE REMOVAL OF A PT6A-20 FROM A DHC-6-200, TWO OF THE TWELVE (12) LEFT HAND ENGINE MOUNT BOLT SHEARED OFF. 1 BOLT TOP MOUNT, 1 BOLT R/H SIDE MOUNT. BOTH BOLTS FOUND BROKEN OFF AT AREA WHERE SHANK AREA IS REDUCED. BOTH BOLTS TURNED APPROX 1/4 O - [SDR AUS20011405](https://openairdocs.org/sdr/AUS20011405.md): Blade · failed · Nov 26, 2001 · Dhav DHC6200 · Turbine Section > (AUS) LT ENGINE INTERNAL FAILURE. INITIAL REPORTS INDICATE POWER TURBINE BLADE FAILURE. - [SDR AU000563](https://openairdocs.org/sdr/AU000563.md): Fire Detector · faulty · Jul 3, 2000 · Dhav DHC6200 · Fire Detection > (AUS) RIGHT ENGINE GEARBOX FIRE DETECTOR FAULTY. LOW RESISTANCE. - [SDR CA000712019](https://openairdocs.org/sdr/CA000712019.md): Bellcrank · twisted · Jul 3, 2000 · Dhav DHC6200 · Elevator Control System > (CAN) WHILE CARRYING OUT AD CF-72-06R4 PART III, THE ELEVATOR QUADRANT WAS FOUND TO BE RUBBING AGAINST THE SIDE OF THE CABLE GUARD AS DESCRIBED IN THE AD. THE QUADRANT ASSEMBLY INCLUDING SUPPORT BRACKET WAS REPLACED PRIOR TO FLIGHT. (X) - [SDR CA000621009](https://openairdocs.org/sdr/CA000621009.md): Attach Fitting · corroded · Jun 10, 2000 · Dhav DHC6200 · Wing, Attach Fittings > (CAN) LEVEL 3 CORROSION FOUND ON PLATE BETWEEN ATTACH POINTS. - [SDR CA000530012](https://openairdocs.org/sdr/CA000530012.md): Beta Switch · failed · May 15, 2000 · Dhav DHC6200 · Propeller Controlling System > (CAN) NR 2 ENGINE BETA BACK UNSERVICEABLE, PROPELLER REVERSES WITH NO BLUE LIGHT IN TEST MODE. - [SDR CA000306008](https://openairdocs.org/sdr/CA000306008.md): Armature · misoverhauled · Mar 6, 2000 · Dhav DHC6200 · Fuel Boost Pump > (CAN) PUMP WAS SENT FOR OVERHAUL. INTERNAL INSPECTION REVEALED THAT THE ARMATURE HAD BEEN MODIFIED BY REDUCING THE ARMATURE SHAFT SIZE AND SUBSTITUTING THE ORIGINAL BEARING WITH A COMMERCIAL BEARING THAT HAD THE SAME OUTSIDE DIAMETER, BUT A SMALLER INSIDE DIA - [SDR CA991209072](https://openairdocs.org/sdr/CA991209072.md): Rivet · loose · Nov 15, 1999 · Dhav DHC6200 · Elevator Control System > (CAN) DURING INSPECTION OF THE ELEVATOR CONTROL SYSTEM, IT WAS NOTICED THAT THE PUSH PULL RIVETS WERE BLACK AND STAINED.THE PUSH PULL ROD WAS REMOVED FROM THE AIRCRAFT AND INSPECTED.AT THAT POINT WE DISCOVERED THAT THE RIVETS WERE LOOSE. THE RIVETS WERE REMOV - [SDR CA991209002](https://openairdocs.org/sdr/CA991209002.md): Liner · wrong part · Nov 11, 1999 · Dhav DHC6200 · Starter-Generator > (CAN) UNIT SENT FOR OVERHAUL. DURING INSPECTION IT WAS NOTED THAT THE DRIVE END BALL BEARING LINER HAD BEEN REPAIRED WITH A COPPER LIKE PLATING, IN ORDER TO RESTORE THE LINERS ORIGINAL DEMENSIONS. ALTHOUGH A PLATING REPAIR IS AVAILABLE IN ORDER TO ACCOMPLISH T - [SDR SMPA99002](https://openairdocs.org/sdr/SMPA99002.md): Spar · corroded · Aug 6, 1999 · N711AS · Dhav DHC6200 · Wing Spar > PPG - DISCOVERED SEVERE CORROSION ON RT WING MAIN SPAR CAPS DURING AD 94-08-10, AND SP NR 57 INSPECTION. CORROSION WAS FOUND ON BOTH LOWER FORWARD AND AFT SPAR CAPS. THE FORWARD SPAR CAP IS CORRODED IN WING BAY STA 197.5 TO 210.0. THE AFT SPAR CAP CORROSION - [SDR SMPA99001](https://openairdocs.org/sdr/SMPA99001.md): Spar · corroded · Aug 6, 1999 · N719AS · Dhav DHC6200 · Wing Spar > PPG - RIGHT WING WAS INSPECTED IAW AD 94-08-10 AND EMMA SP NR 57, MAIN SPAR CAP INSP FOR CORROSION. A SPOT OF CORROSION WAS FOUND ON THE LOWER FORWARD SPAR CAP CENTERED AT WS 57. THE DAMAGE MEASURED APPROX 2.5 INCHES IN LENGTH BY 0.2 INCH WIDE AT MAX DEPTH O - [SDR CA990715015](https://openairdocs.org/sdr/CA990715015.md): Line · leaking · Apr 28, 1999 · Dhav DHC6200 · Engine Fuel Distribution > (CAN) AIRCRAFT PARKED FOR 5 MONTHS. ON INSPECTION, NOTED THAT FUEL WAS RUNNING DOWN STRUT. FUEL WAS NOTED COMING FROM STEEL BRAIDED LINE. TYPE 601 LINE MFD 2Q90. - [SDR AU981667](https://openairdocs.org/sdr/AU981667.md): Door · unlocked · Dec 20, 1998 · Dhav DHC6200 · Emergency Exits > (AUS) ON ROTATION, THE DOOR UNSAFE WARNING ANNUNICATOR ILLUMINATED. DURING GROUND INVESTIGATION, THE RT EMERGENCY EXIT DOOR LATCHING MECHANISM WAS REMOVED AND INSPECTED - NO OBVIOUS DEFECTS WERE NOTED OTHER THAN THE MECHANISM REQUIRED TIGHTENING AND THE DOOR - [SDR CA981202002](https://openairdocs.org/sdr/CA981202002.md): Bracket · corroded · Nov 25, 1998 · Dhav DHC6200 · Elevator Structure > (CAN) ELEVATOR HINGE BRACKETS FOUND WITH EXFOLIATION CORROSION. LESS THAN HALF OF THE MATERIAL REMAINING. - [SDR CA981207021](https://openairdocs.org/sdr/CA981207021.md): Skin · cracked · Nov 23, 1998 · Dhav DHC6200 · Fuselage Main, Plate/Skin > (CAN) CRACK FOUND ON SKIN UNDER LOWER VHF BLADE ANTENNA. SERVICE BULLETIN 6/305 IN REGARD TO THIS AREA HAD NOT BEEN CARRIED OUT. - [SDR CA981125027](https://openairdocs.org/sdr/CA981125027.md): Armature · wrong part · Sep 16, 1998 · Dhav DHC6200 · Starter-Generator > (CAN) THE WRONG ARMATURE WAS FOUND IN THE STARTER/GENERATOR DURING OVERHAUL. THE ARMATURE SHOULD HAVE BEEN A 23048-1031. THE ARMATURE USED BELONGS TO AN APC 250SG SERIES STARTER/GENERATOR AND IS NOT APPROVED FOR THE LSI LUCAS STARTER/GENERATOR. Next page: https://openairdocs.org/model/dehavilland-dhc-6-200/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 = 'DHC6200' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/model/dehavilland-dhc-6-200/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.