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.
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
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR 2026F00209Fuel Line · kinkedFWD FUEL FLOW FLUCTUATING DURING TAKE OFF ROLL, ABORTED TAKE OFF AND RETURNED TO GATE.SDR HKGA20260602001Cap · looseHYDRAULIC PUMP CIRCUIT BREAKER POPPED IN FLIGHT AND MAIN SYSTEM WOULD NOT HOLD PRESSURE. CREW DECLARED AN EMERGENCY AND SAFELY LANDED AT KHYI. MAINTENANCE FOUND HYDRAULIC MANIFOLD CAP TOO BE LOOSE AS WELL AS A LEAK ON INLET, ON FILTER HOUSING AND SUBSEQUENTLY SDR S9BA2025121500004Gasket · burnedFLT/CREW REPORTED - UPON SETTING CRUISE POWER APPROX. 3 MINUTES AFTER ON FLIGHT # BB - 186 SPB / SSB " FIRE WARNING R ENGINE WITH NO EVIDENCE OF FIRE. THIS A REPEAT ITEM DATED 12/04/2025 - UNIQE CONTROL # S9BA202500003. CHECKED & INSPECTED FUEL NOZZLE SYSTEMSDR S9BA202512080003Fire Detector · out of toleranceFLT/CREW REPORTED - UPON LEVELING OUT ON FLIGHT NR BB-136 SSP / SSB RT ENGINE FIRE WARNING LIGHT CAME ON WITH AURAL FIRE BELL WARNING CAME ON ALSO. POWER LEVER / TQ WAS REDUCE AND BOTH FIRE WARNING EXTINGUSHED, F/O VISUALLY CONFIRMED NO FIRE OR SMOKE WAS COMINSDR S9BA202503110001Switch · loose03/07/2025 CREW REPORTED:'AILERON ACT. TRIM CB POPPED IN FLIGHT ELECTRICAL BURNING SMELL." MAINTENANCE INSPECTED DEFERRED THIS ITEM AS PER MEL 27-2. MAINTENANCE CORRECTIVE ACTION:" INSPECTED AILERON TRIM SYSTEM FOUND CONNECTION AT SWITCH LOOSE REPOSITIONED ANDSDR 2025FA0000005Control Cable · damagedUPON VISUAL INSPECTION OF PITCH SERVO AREA IT WAS NOTED THAT THERE APPEARS TO BE ELEVATOR CABLE DAMAGE ON THE CAPSTAN COVER OF THE PITCH SERVO. DAMAGE ON ONE OF THE SCREWS THAT ATTACH THE COVER INDICATE THE ELEVATOR CABLE WAS CAPTURED BY THE SCREW CAUSING THE SDR S9BA20240005Doubler · corrodedCORROSION FOUND BEYOND MFR LIMITS ON LH WING WS310.O FORE FLAP HINGE SKIN DOUBLERS. FOLLOWING PART NUMBERS WERE REMOVED AND REPLACED IAW DHC SRM. 969401-7 AND 969401-9.SDR S9BA20240004Stringer · corrodedCORROSION BEYOND MFR LIMITS ON STRINGERS AND INTERCOSTALS BETWEEN FS262 AND FS288 BETWEEN WL -4.68 AND -10.28. FOLLOWING PART NUMBERS WERE REMOVED AND REPLACED WITH NEW IAW DHC SRM. C6FS1620-29, C6FS1620-39, C6FS1620-31, C6FS2448-39, C6FS1620-37.SDR S9BA2024060403Mount Fitting · brokenCREW REPORTED; WHEN RIGHT FUEL LEVER SELECTED OFF, RIGHT ENGINE DID NOT SHUT DOWN. MAINTENANCE INSPECTED ENGINE CONTROL CABLES AND FOUND CABLES IN BIND. FURTHER INSPECTION FOUND THE RIGHT OUTBOARD ENGINE MOUNT BROKEN. REMOVED AND REPLACED ENGINE MOUNT IAW ASDR S9BA20240002Trim Tab · brokenIN SHALLOW CLIMB A DUPLICATABLE VIBRATION CAN BE FELT IN THE YOKE AND AIRPLANE. INSPECTION OF THE AIRCRAFT FOUND THE LH ELEVATOR TRIM TAB ATTACH BRACKET BROKEN. REMOVED AND REPLACED ELEVATOR TRIM TAB ASSEMBLY IAW DHC-6-300 AMM CH 27-30. OPERATIONAL CHECK ANSDR S9BA20240402001Longeron · crackedRH ENGINE NACELLE OUTBOARD LOWER LONGERON CRACKED.SDR S9BA202307210005Frame · corrodedRH SIDE FRAME AT FS219 CORRODED BEYOND MANUAL LIMITS.SDR S9BA202307210004Frame · corrodedLH SIDE FRAME AT FS218 CORRODED BEYOND MANUAL LIMITS.SDR S9BA20230003Structure · corrodedRH UPPER WING SKIN DOUBLER (.063) CORROSION WS135.0 (.040 DEEP) AT MAIN SPAR BEYOND SRM LIMITSSDR S9BA20230002Structure · corrodedLH UPPER WING SKIN DOUBLER (.063 THICK) CORROSION WS125.50 (.014 DEEP) AND 129.00 (.013 DEEP) AT MAIN SPAR BEYOND SRM LIMITS.SDR S9BA20230001Structure · corrodedSUPPLEMENT REPORT TO CONTROL NUMBER 2023F00064. PLEASE CHANGE CONTROL NUMBER FROM 2023F00064 TO OPERATOR UNIQUE CONTROL NUMBER S9BA20230001. ALL OTHER INFORMATION IS THE SAME. RH SIDE FUSELAGE SKIN (.050) CORRODED (.023) DEEP BEYOND SRM LIMITS (.006) AT FSSDR 2023F00064Structure · corrodedRH SIDE FUSELAGE SKIN (.050 THICK) CORRODED (.023 DEEP) BEYOND SRM LIMITS (.006) AT FS131-FS132 AT TOP OF WINDOW CUTOUT.SDR 2022FA0000754Proximity Switch · looseDURING MAINTENANCE FLIGHT, LEFT NOSE GEAR DOWN LIGHT DID NOT ILLUMINATE. ADJUSTED PROXIMITY SWITCH TO ILLUMINATE NOSE GEAR DOWN LIGHT. JACKED AIRCRAFT AND GEAR OPS CHECK GOOD IN REFERENCE TO WIPAIRE SERVICE MANUAL & ICA WIPLINE 13000 FLOATS CHAPTER 2. INSTSDR 2021FA0000372Autopilot Sys · malfunctionedDURING TEST FLIGHT FOR THE INSTALLATION OF AUTOPILOT SYSTEM GENESYS S-TEC3100 INTO THE DHC-6 AIRCRAFT SEVERAL PROBLEMS BECAME APPARENT. THESE ISSUES WERE: PITCH UP DURING INITIALISATION; CONCERN PITCH UP ON FIRST SELECTION OF AP; AP UNABLE TO MAINTAIN LEVEL FSDR 2021FA0000128Floorboard · damagedFLOOR BOARDS BOWED/WARPED/SAGGED CAUSING POOR SEAT LOCK PIN ENGAGEMENT.SDR HKGA20201001001Nozzle · leakingNUMBER 2 ENGINE FLAMED OUT DURING CRUISE FLIGHT. AFTER LANDING MAINTENANCE FOUND THE NUMBER 8 FUEL NOZZLE LEAKING FROM THE TRANSFER TUBES, DUE TO AN INCORRECTLY INSTALLED LOCKING PLATE. MAINTENANCE THEN REMOVED THE LOCKING PLATE AND TRANSFER TUBES, REPLACED SDR CA190801003Buss Bar · mismanufactured(CAN) NEW BUS BAR RECEIVED FROM VIKING AIR LIMITED. SLOTTED END DOES NOT FIT OVER EXTERNAL POWER RECEPTACLE MS3506-1. (REF: IPC PSM 1-63-4, CH 24-40-00, FIG 1, ITEM 5.) SHUNT END FITS PROPERLY. SLOT OPENING MEASURES 0.351-0.359 ACROSS. THREAD OF EXTERNAL RECEPSDR CA190731030Switch · malfunctioned(CAN) DURING THE TAKE-OFF SLIDE, THE AUTO FEATHER SWITCH WOULD NOT ARM. THE PILOTS ABORTED THE TAKE-OFF AND RETURNED TO THE DOCK. THE SWITCH WAS REPLACED, AND THE SYSTEM TESTED SERVICEABLE. NOTE: THIS OPERATOR HAS HAD MULTIPLE AUTO FEATHERS SWITCHES FAIL, SEVSDR CA190724012Switch · malfunctioned(CAN) THE AUTO FEATHER ARM LIGHT DID NOT TURN ON DURING THE TAKE-OFF SLIDE. THE AUTO FEATHER SWITCH WAS REPLACED, AND THE SYSTEM FUNCTION CHECKED SERVICEABLE. (TC# 20190724012)SDR CA190529010Bolt · defective(CAN) A REPLACEMENT ATTACH BOLT FOR THE FLIGHT CONTROL RODS WAS PURCHASED & RECEIVED BY NWA STORES. UPON PRE-INSTALLATION INSPECTION OF THE BOLT, (P/N NAS464P5-25) AN OPEN DEFECT WAS NOTED ON THE TOP CENTER OF THE HEAD AS WELL AS A DARK LINE IN THE SHANK JUST SDR CA190521017Block · mismanufactured(CAN) WE RECENTLY RECEIVED A PURCHASED SYSTEM 65 S-TEC KIT AND THERE IS A MICARTA BLOCK REQUIRED FOR THE INSTALLATION OF THE TRIM SERVO THAT IS NOT MANUFACTURED CORRECTLY FOR THE INSTALLATION. IT SERVES AS A CHAFF BLOCK AND ITS INSTALLATION IS VERBALLY DESCRIBSDR CA190717013Ski · cracked(CAN) ON MAY 7, 2019, AIR INUIT HAD AN INCIDENT WITH A DHC6-300 (C-XXXX). THE AIRCRAFT WAS OPERATE ON SKI ON AN OFF STRIP WHEN HE SUDDENLY LOST CONTROL OF THE AIRCRAFT DURING TAKE-OFF ROLL. THE AIRCRAFT SUFFERED SUBSTANTIAL DAMAGE (NOSE OLEO COMPLETELY RIP OFFSDR CA190416017Cable · slipped(CAN) WHEN PERFORMING SERVO MOUNT CLUTCH SLIP TEST ON APS-65 AUTOPILOT SYSTEM INSTALLED ON DHC6-300 AIRCRAFT IN ACCORDANCE WITH APS-65 MAINTENANCE MANUAL COLLINS PUBLICATION 523-0771867 PARA 5.4.2 THE BRIDAL CABLE CLAMPS ON THE MAIN CONTROL CABLES SLIPPED ALONSDR CA190410021Autopilot Sys · malfunctioned(CAN) APS-65 AUTOPILOT INSTALLED IN DHC6-300 BY MANUFACTURERS SERVICE BULLETIN SB 6-505 IS NOT MENTIONED IN THE AIRCRAFT MAINTENANCE MANUAL, HAS NO INSTRUCTIONS FOR CONTINUED AIRWORTHINESS OR INSPECTION REQUIREMENTS. THERE IS NO PROCEDURE FOR TESTING SYSTEM POSDR CA180423022Audio Control · malfunctioned(CAN) IT HAS BEEN DISCOVERED THAT WHEN BOTH AUDIO PANEL MIC SELECTIONS ARE SELECTED TO COM POSITION 3 A PTT TRANSMIT ON CO-PILOT`S SIDE ALSO CAUSES THE PILOT SIDE TO TRANSMIT. THIS CONDITION ONLY HAPPENS WHEN BOTH AUDIO PANELS ARE SELECTED TO POSITION COM 3 ASDR HKGA20170802005Landing Gear · crackedDURING A MAIN LANDING GEAR REPLACEMENT, A 2" CRACK WAS NOTED ON THE MAIN LANDING GEAR WELD. LANDING GEAR LEG WAS REPLACED WITH OVERHAULED UNIT IAW MAINTENANCE MANUAL.SDR GCNA20160725001Unknown · odorWHILE IN FLIGHT, CREW SMELLED SMOKE. THE CREW OPENED THE BUS TIE AND ISOLATED THE ELECTRICAL POWER. ACFT RETURNED TO BASE WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED ACFT AND FOUND 2 COMPONENTS BAD, BUT HAVE NOT DETERMINED YET IF THEY ARE RELATED. THE SDR CA160229005Light · burned out(CAN) AIRCRAFT DEPARTED FROM AIRPORT AND CREW SMELLED AND NOTICED SMOKE COMING FROM ONE OF THE OVERHEAD COCKPIT PANELS. AIRCRAFT RETURNED TO AIRPORT AND LANDED SAFELY. MAINTENANCE INVESTIGATED AND REMOVED LIGHTING PANEL C6NF1253-19, WHICH HAD A HOLE BURNT THROSDR CA160307001Turbine Blades · fractured(CAN) AFTER TAKE-OFF THE CREW OBSERVED A FLUCTUATION IN THE NR 2 TORQUE INDICATION AND COULD HEAR THE CHANGES IN ENGINE POWER SETTINGS. ALL OTHER PARAMETERS REMAINED NORMAL AND IN THE GREEN. THE ENGINE POWER LEVER WAS PULLED BACK TO OPERATE AT A REDUCED POWER SDR CA160212009Tube · corroded(CAN) UPON REMOVAL OF TUBE ASSEMBLY-LOWER RUDDER SUPPORT, (C6FS1828-1) FOR CORROSION REMOVAL AND RE CADMIUM PLATING, IT WAS NOTICED THAT THE TUBE ASSEMBLY WAS FILLED WITH WATER. THIS IS A WELDED SEALED UNIT, SO CONDENSTION BUILD UP IS OCCURING INSIDE THE STESDR CA160208004Exhaust Duct · damaged(CAN) ENGINE SENT FOR INVESTIGATION DUE TO THE CUSTOMER REPORTED A CRACKED AND DISTORTED EXHAUST DUCT. THE CUSTOMER ELECTED TO OVERHAUL THE ENGINE AT THIS TIME.SDR CA160317013Lever · failed(CAN) STEERING LEVER FAILED DURING TAXI.SDR CA160317012Lever · failed(CAN) STEERING LEVER BROKE DURING TAXI.SDR 2016FA0000000Oil System · oil consumptionENGINE WAS INSTALLED AFTER O/H. GROUND RUN AND PERFORMANCE RUN WAS SATISFACTORY. ACFT WAS FLIGHT TESTED FOR 45 MINUTES, 2 TIMES WAS RUNNING GOOD. ACFT WAS DEPARTED FOR EXPORT WHEN FLEW FOR 45 MINUTES OIL PRESSURE AND TORQUE PRESSURE FLUCTUATION WERE NOTICED.SDR CA151205001Axle · cracked(CAN) DURING ROUTINE EMMA INSPECTION AXLE P/N C6UM1134-27 WAS FOUND TO HAVE A SUSPECTED CRACK AROUND BARREL APPROXIMATELY 3" LONG. PART WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.SDR CA151214008Recorder · wrong part(CAN) CVR OUTPUT FROM KMA24H-70 AUDIO PANELS DOES NOT COMPLY WITH EITHER ARINC 557 OR ARINC 757 STANDARDS FOR VOICE RECORDER INPUT LEVELS. INTERFACING AN ARINC 557 CVR (50MV RMS TO 500MV RMS) THE SUMMED AUDIO OUTPUT TO THE CVR HAS THE FOLLOWING CHARACTERISTISDR CA151113004Connector · unsecure(CAN) NEW BRUSH BLOCK ASSEMBLIES RECEIVED INCORRECTLY ASSEMBLED. CAUSES THE ATTACHING CONNECTOR TO NOT INSTALL COMPLETELY AND WIRES FROM THE CONNECTOR TO BRUSH ASSEMBLIES TO BE CRIMPED OR DAMAGED.SDR CA151112003Wire · chafed(CAN) WIRES FROM DE-ICE BOOT TO CONNECTOR FOUND CHAFFED ON CONNECTOR MOUNTING BRACKET.SDR CA151023001Lever · broken(CAN) DURING TURN AT THE END OF THE RUNWAY, CREW HEARD A THUMP. MAINTENANCE FOUND STEERING LEVER P/N 71-159-9 BROKEN. STEERING LEVER REPLACED, AND STEERING TRAVEL LIMITS VERIFIED IAW DHC6 MM. FLEET INSPECTION ALREADY GENERATED BY SDR 20151019002 WILL BE MODIFSDR CA151121001Adapter · cracked(CAN) AFT ADAPTER ON VERTICAL STABILIZER WAS FOUND CRACKED UPON EXAMINATION CALLED OUT IN PART B OF SERVICE BULLETIN 6/454. INSPECTION REQUIRED EVERY 60 MONTHS. NDE REPORT CP4-2312 ON FILE. NEW ADAPTER WAS INSTALLED ON VERTICAL STABILIZER PER VIKING SERVICE BUSDR CA151027007Stud · sheared(CAN) BRACKET C3W25-3 HOLDS TWO STUDS C3W65-3 THAT SECURE THE UPPER AND LOWER AILERON CABLE PULLEYS IN THE OUTBOARD LH WING OF THE TWIN OTTER. ONE OF THE PULLEYS WAS UNSERVICEABLE AND NEEDED TO BE REPLACED. THE NEW PULLEY WAS SET ON THE STUD AND THE ATTACHING SDR S9BA2016F00006Fuel Control · failed(CGKBR) LEFT ENGINE NOT MAKING 50 PERCENT TORQUE ON LAST FLIGHT CHECKS. REPLACED FUEL PUMP AND FUEL CONTROL.SDR CA151019002Bolt · broken(CAN) STEERING ACTUATOR LINK BOLT P/N 71-146-1 FOUND BROKEN DURING NOSE WHEEL STEERING CABLE INSPECTION. BOLT WAS STILL IN ITS HOLE AND FELL AS IT GOT TOUCHED FOR INSPECTION.SDR S9BA201510170014Transducer · malfunctionedLT ENGINE ONLY PRODUCING 40 LBS TORQUE ON TAKEOFF. TAKEOFF WAS ABORTED. TORQUE TRANSDUCER WAS REPLACED IAW AMM 79-31.SDR CA150723004Collar · broken(CAN) PILOT LANDED AND NOTICE THAT NOSE WHEEL STEERING WAS STIFF AND DIFFICULT TO CONTROL. ALSO TILLER POSITION DID NOT CORRESPOND WITH THE DIRECTION AIRCRAFT WOULD TAXI. MAINTENANCE PERSONNEL PERFORMED A VISUAL INSPECTION OF THE NLG ASSY AND FOUND THE STEERI
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