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 S9BA00506Mount · corrodedRIGHT ENGINE UPPER ENGINE MOUNT PLATE HAS CORROSION. REMOVED AND REPLACED UPPER ENGINE MOUNT PLATE IAW RD-54-006.SDR S9BA00406Angle · corrodedRIGHT HAD ENGINE NACELLE HOOP (ANGLE FIREWALL) FRAME HAS CORROSION. REMOVED AND REPLACED HOOP FRAME.SDR S9BA00306Frame · corrodedDURING WING STRUT BOLT INSPECTION, FOUND CORROSION ON STS 218.11 (MAIN FRAME). REMOVED AND REPLACED MAIN FRAME IAW SERVICE BULLETIN 6/354.SDR OEZ2006F00000Oil Cap · leakingENROUTE, RT ENGINE OIL PRESSURE WAS DROPPING TO 45 PSI. AIR CREW IMMEDIATELY BEGAN TROUBLESHOOTING WITH THE CHECKLISTS. THE OIL PRESSURE LIGHT BEGAN TO FLICKER, AIRCREW SHUTDOWN THE RT ENGINE, DECLARED AND EMERGENCY WITH APPROACH AND LANDED NORMALLY SINGLE ESDR S9B2006F00004Ring · crackedREF NR (S9BA-002) DURING HSI FOUND CRACK ON THE PT VANE RING. LOOKING FROM AFT TO FWD AT 3 OCLOCK POSITION CRACK EXTENDS ACROSS INNER HOUSING THROUGH THE FILLET RADIUS AND AIRFOIL. REMOVED AND REPLACED PT VANE RING. (K)SDR OEZ2006F00001Relay · shortedODOR OF BURNING WIRE AFTER LANDING FOLLOWED BY ELECTRICAL FAILURE NR 1 FOUND LT REVERSE CURRENT RELAY SHORTED OUT NR 2 FOUND REVERSE CURRENT RELAY CIRCUIT BREAKER AND BUS TIE RELAY SHORTED OUT BY THE RCR FAILURE. THE REVERSE CURRENT RELAY IS CURRENTLY IN OUR SDR S9B2006F00003Skin · corrodedCORRODED SKIN ALONG THE FIRST ROW OF RIVETS ON UPPER LEFT WING IB OF THE NACELLE BETWEEN STATIONS 60 AND 72.5. CORRODED SKIN WAS TRIMMED OUT AND AN EXTERNAL PATCH RIVETED IN PLACE IAW RD6-57-077. (K)SDR CA060731007Oil System · leaking(CAN) DURING CLIMB, ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE FOLLOWED BY A LOSS IN OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED INTERNAL OIL LEAKAGE. MFG WILL INVESTIGATESDR CA060612007Leg Assy · damagedDURING A NORMAL LANDING PROCEDURE, THE LEFT MAIN LANDING GEAR BROKE OFF FOR A REASON UNKNOWN TO US. THE AIRCRAFT CONTINUED TO SKID ON THE STUD OF THE GEAR UNTIL COMING TO A COMPLETE STOP. AT THE END, THE AIRCRAFT TIPPED TO THE LEFT AND DAMAGED THE LEFT WING SDR CA060607002Metering Tube · failed(CAN) FRACTURED AT LOWER THREAD WHERE THE TUBE SCREWS INTO THE PISTON. THIS ALLOWED THE UPPER AND LOWER SECTIONS OF THE SHOCK STRUT TO DISENGAGE CAUSING GEAR COLLAPSE. THE FAILED TUBE IS MADE OF ALUMINUM ALLOY. PART AND PICTURES AVAILABLE UPON REQUEST (TC NR 2SDR CA060330005Mount · mismanufactured(CAN) ENGINE MOUNT PLATE INCORRECTLY MANUFACTURED. THE HOLE FOR THE ENGINE MOUNT BOLT (MS21250-06042) IS NOT DRILLED AT THE CORRECT ANGLE. THE HOLE FROM THE MOUNT PLATE TO THE FITTING, ENGINE MOUNT P/N C6WM 1517-28 DOES NOT LINE UP. MARKINGS ON THE PLATE ARE,SDR CA060403012Bleed Valve · faultyDURING APPROACH, THE ENGINE EMITTED AN UNUSUAL NOISE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FAULTY COMPRESSOR BLEED VALVE.SDR S9B2006F00000Structure · corroded(REF NR: 888-07)LT LWR FINLET REQUIRES CHANGE DUE TO CORROSION. REMOVED AND REPLACED LT LWR FINLET ASSY IAW MM.(K)SDR 2006FA0000245Engine · making metalLT ENGINE OIL PRESSURE STARTED FLUCTUATING. PILOT RETURNED TO AIRPORT. MAINTENANCE CHECKED OIL FILTER AND FOUND METAL IN OIL. ENGINE REMOVED AND SENT TO REPAIR FACILITY. (K)SDR CA060210001Fitting · cracked(CAN) UPON INSPECTION OF WING FRONT SPAR ADAPTER FITTINGS IAW REO 6-57-30-013, CRACKS WERE FOUND ON THE LT AND RT WING FRONT SPAR ADAPTER FITTINGS AS FOLLOWS; LT WING, BETWEEN WING STATION 35.15 AND 47.5, ONE CRACK BETWEEN 5TH AND 6TH RIVET. LT WING, BETWEEN WSDR CA060227016Engine · power lossDURING DESCENT, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER. A SINGLE-ENGINE LANDING WAS ACCOMPLISHED. PWC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.SDR CA060208015Mount · broken(CAN) THE PILOT REPORTED AFTER LANDING THE LT ENGINE WAS BROKEN. THE MAINTENANCE CREW REPLACED THE BROKEN TOP LT ENGINE MOUNT ALONG WITH THE VIBRATION ISOLATOR AND NEW GASKETS AND ATTACHMENT BOLTS. (TC NR 20060208015)SDR CA060123004Window · missing(CAN) AFTER A TRAINING FLIGHT, AC CAME BACK TO DEPARTURE, WHERE ON THE VISUAL INSPECTION OF EXTERIOR OF FUSELAGE IT WAS NOTICED THAT RT AFT DOOR WAS MISSING EXTERIOR PART OF WINDOW (PLEXIGLASS) INCLUDING WEATHER STRIP AND THE FILLER STRIP. INTERIOR PART OF THESDR CA060216007Mount · crackedDURING EDDY CURRENT INSPECTION PER MULDIVES AD CAD/2005/1, A CRACK INDICATION WAS FOUND IN THE RADIUS OF THE TOP ENGINE VIBRATION ISOLATOR MOUNT.SDR AU510002187Retaining Ring · missingENGINE PROPELLER SHAFT ADAPTER PLUG RETAINING RING MISSING. ADAPTER PLUG P/N 3013146 DISLODGED AND LOOSE IN THE PROPELLER SHAFT INTERNAL BORE. RETAINING RING COULD NOT BE FOUND. SUSPECT RETAINING RING HAD NOT BEEN INSTALLED. PERSONNEL/MAINTENANCE ERROR. ASDR CA051206008Strut · damagedFLIGHT CREW REPORTED A CONSTANT LOSS OF FLUID AND PRESSURE OF NOSE STRUT ASSEMBLY. NOSE STRUT DISASSEMBLED TO BE RE-SEALED. THE RETAINING SCREW THAT HOLDS THE PISTON NUT SECURE WAS NOT WOUND IN PROPERLY/COMPLETELY. THIS PROTRUDING SCREW HEAD THEN MADE REPEASDR CA051116007Reservoir · cracked(CAN) FLUID WAS DRIPPING FROM THE HYD AREA.OPON INSPECTION IT WAS NOTICED THAT THE TANK WAS CRACKED ALONG THE FILLER NECK.SDR CA060208014Mount · broken(CAN) AFTER LANDING IT WAS NOTICED NO REVERSE ON THE RT ENGINE AND THE THERE WAS STIFFNESS IN THE OPERATION OF THE POWER LEVERS THAN IT ULTIMATLLY GOT STUCK. MAINTENANCE IDENTIFIED THE PROBLEM AS A BROKEN ENGINE MOUNT. (TC NR20060208014)SDR CA060208012Mount · broken(CAN) ON TAKE-OFF THERE WAS A NOISE AND THE AC NOSE HAD AN UNCONTROLLED PITCH UP, AND IT YAWED TO THE RT AND THE TORQUE PRESSURE FELL TO 80 PERCENT. THE TAKE-OFF WAS ABORTED AND THE AC RETURNED TO THE DOCK. IT WAS THAN DISCOVERED THAT THE RT ENGINE MOUNT WAS SDR CA051013005Bracket · crackedUPON VISUAL INSPECTION, TOP PLATE OF AFT REVERSING TELEFLEX BRACKET WAS FOUND CRACKED 70 PERCENT THROUGH. TOTAL FAILURE OF THIS BRACKET WOULD ALLOW THE REVERSING TELEFLEX TO MOVE FORE AND AFT CAUSING DIFFICULTIES IN ENGINE CONTROL DURING REVERSE OPERATIONS. SDR CA051012005Skin · debondedFOUND LT AND RT WING DISBONDING OF THE UPPER WING SKIN, INBOARD AND OUTBOARD OF NACELLES FROM YW 60 TP YW 150. BOMBARDIER IS IN THE PROCESS OF ISSUING A SB TO COVER INSPECTION OF THE UPPER WING SKINS. DARK AREAS ON THE SKETCHES INDICATE DISBONDING. MODEL P/SDR CA060216008Mount · crackedTOP, ENGINE VIBRATION ISOLATOR MOUNT (RIGHT ENGINE) WAS FOUND CRACKED DURING INSPECTION.SDR CA050928002Longeron · cracked(CAN) WHILE CARRYING OUT THE LOWER LONGERON INSPECTION IAW AD CF 81-07R4 AND SB 6/509, THE LT IB LONGERON ON THE RT NACELLE WAS FOUND CRACKED LATERALLY ACROSS THE WEB. THE CRACK WAS JUST AFT OF THE ENGINE MOUNT.SDR CA050923007Glide Slope · malfunctionedGLIDESLOPE DEVIATION ON EHSI INVERTED. GLIDESLOPE INFORMATION INTERFACED ON ARINC 429 DATA BUS. EFIS MANUFACTURER ACKNOWLEDGES PROBLEM IS SOFTWARE IN EHSI, AWAITING SOFTWARE FIX FROM MANUFACTURER. DEFECT IS ALSO PRESENT IN EADI WHEN EADI IS IN FORCED COMPOSSDR CA050728003Friction Ring · wornDURING INSPECTION, THE FAN WAS FOUND TO HAVE MOVED AFT CONTACTING THE FAN HOUSING. BOTH THE FAN AND HOUSING WERE DAMAGED. THE FRICTION RING AT THE FWD END OF THE SHAFT WAS FOUND COMPLETELY WORN OUT. SUSPECT MIS-ALIGNMENT OF THE GENERATOR INSTALLATION CAUSINSDR 2005FA0001007Spar Cap · damagedSMOKING MS20470DD8 RIVETS OBSERVED AT WS122 - 140 PROX DURING SCHEDULED INSPECTION. THESE RIVETS ARE CRITICAL TO WING INTEGRITY. IT APPEARS THAT THE RIVETS DID NOT PROPERLY ENGAGE THE HOLE DURING OEM INSTALLATION. SUGGEST ALL WING BOXES WITHIN 10 SERIAL NUSDR CA050801001Duct · leakingWHEN TROUBLESHOOTING A HIGH ENGINE TEMPERATURE PROBLEM, IT WAS DISCOVERED THAT THE BLEED AIR DUCT COMING OFF THAT ENGINE WAS LEAKING THROUGH A CRACK IN THE FLEXIBLE BELLOWS SECTION OF THE DUCT, WHICH IS NOT VISIBLE UNDER THE DUCT'S SHIELD. THE CRACK WAS DETECSDR CA050623003Flex Drive · seized(CAN) A FEW MINUTES AFTER DEPARTURE, THE FLIGHT CREW NOTICED A BURNING ODOR FOLLOWED BY SMOKE EMITTING FROM THE GLARESHIELD. ON INVESTIGATION BY MAINTENANCE, THE FLEX DRIVE BETWEEN THE WIPER MOTOR AND PILOT CONVERTER WAS FOUND TO BE OVERHEATING AND MELTED A POSDR CA050527004Pin · mismanufacturedPDA PART ROD SECURING PIN DEHAVILLAND P/N C6CWM1043-27 INCORRECTLY MANUFACTURED. PIN OUTSIDE DIAMETER TOO LARGE TO FIT INTO 'H' BEAM HOLE. REFERENCE DHC-6-300 IPC CHAPTER 27-10-00 FIGURE 4 ITEM 560. 'H' BEAM ATTACHMENT HOLE EDGE DISTANCE MAY BE TOO SMALL IF SDR CA050527022Engine · leakingDURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE PILOT SHUT THE ENGINE DOWN IN FLIGHT. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED OIL LEAKAGE FROM THE NR 3 BEARING SEAL AREA.SDR CA050530006Lever · fractured(CAN) NO RESPONSE TO NWS AFTER LANDING. LEVER ARM FRACTURED AT RADIUS WHERE CONNECTS TO ACTUATOR HOUSING BOSS. SEE MFG AMM FIGURE 201.RDIMS LETTER NR 1199637 SENT - CAA IN RESPONSE TO TO HIS LETTER TO TC. REFERENCE ATTACHMENT.SDR CA050513001Skin · debondedDURING INSTALLATION OF A REPAIR DOUBLER INBOARD OF THE RT NACELLE AS PER RD6-57-618 IT WAS FOUND THAT 3 AREAS OF DISBOND HAD OCCURRED BETWEEN THE UPPER WING SKIN AND THE CORRUGATION . AS PER INSTRUCTIONS IN THE REPAIR DEFINITION THE MANUFACTURE WAS CONTACTED ASDR CA050509005Plate · torn(CAN) UPON ENTERING CRUISE FLIGHT, THE PILOT HEARD A LOUD BANG AND FELT THE AIRCRAFT SHUTTER. HE NOTICED THAT THE RT SKI HARNESS HAD COME UNATTACHED TO THE UPPER WING ATTACH FITTING, LETTING THE RT SKI ROTATE UPWARD AGAINST THE WING STRUT. THE PILOT TOOK MEASSDR 2005FA0001059Antenna · inoperativeFOUND UPPER UAT ANTENNA UNSERVICEABLE DURING UAT UPGRADE. (K)SDR CA050408012Washer · missing(CAN) SERVICING THE NOSE OLEO, THE ENGINEER NOTICED THAT THE FORK WAS LOOSE ON THE STRUT. REMOVAL OF THE STRUT REVEALED THAT IT WAS ASSEMBLED INCORRECTLY. THE WASHER P/N 71-309-9 WAS MISSING AND THAT EXTRA PEEL ABLE SHIMS HAD BEEN ADDED. THE SHIMS ARE A SMASDR CA050408003Collar · sheared(CAN) ON AIRCRAFT ARRIVAL AT YZF, THE CREW REPORTED LOSS OF NOSE WHEEL STEERING. INVESTIGATION BY MAINTENANCE STAFF REVEALED THAT THE NWS COLLAR P/N 71-161-11 WAS SHEARED OFF. THE ENTIRE NOSE GEAR ASSEMBLY WAS REPLACED AND THE SURROUNDING AREA WAS INSPECTED SDR CA050328003Fairlead · chafed(CAN) PRESUMED THAT RH AILERON CABLE BROKE DUE TO CHAFFING ON A THE FAIRLEAD. MORE DETAILS WILL FOLLOW ON REVISION 1 OF THE INCIDENT REPORT FILED BY AIR GUYANE SP WITH THEIR LOCAL AVIATION AUTHORITY.SDR CA060208013Mount · brokenAFTER A SMOOTH LANDING, THE A/C HIT AN ABNORMALLY LARGE WAVE, WHICH CAUSED THE A/C TO GET AIRBORNE THAN CAME DOWN HARD ON A SMALLER WAVE, WHICH RESULTED IN A LARGE JOLT TO THE A/C. IT WAS THEN NOTICED THAT THE LT ENGINE AND POWER LEVERS HAD SHIFTED FORWARD. SDR CA050224007Hinge Bracket · corroded(CAN) CORROSION FOUND UNDER BLOCK. WHILE INSPECTING CENTER HINGE BRACKET IAW SB 6/512. CORROSION VISIBLE ON SURFACE SURROUNDING BLOCK. BLOCKS REMOVED FOR FURTHER INSPECTION AND EXFOLIATION/CORROSION FOUND UNDER BOTH SIDES.SDR CA041216004Bolt · sheared(CAN) AT ENGINE REMOVAL, ONE OF THE TOP ENGINE MOUNT BOLTS P/N CSP282-29 BOLT FAILED. THE HEADS SHEARED OFF AFTER APPROXIMATELY A .7500 TURN OF THE BOLT. REVIEWED (TC NR 20041216004)SDR CA041216003Bolt · sheared(CAN) AT ENGINE REMOVAL 3 OF THE 4 TOP ENGINE MOUNT BOLTS PN CSP282-29 BOLT FAILED. THE HEADS SHEARED OFF AFTER APPROXIMATELY 3/1 - 1.25 TURN(S) OF THE BOLT. (TC NR 20041216003)SDR CA041216001Cable · misinstalled(CAN) NOSE WHEEL STEERING CABLE ROUTED INCORRECTLY RESULTING IN ALMOST SAWING THROUGH THE HYDRAULIC HAND PUMP SUCTION LINE P/N C6H1001-294.SDR CA041206005Plate · misdrilled(CAN) MAIN BOLT AND SPIGOT HOLES ARE DRILLED APPROXIMATELY 0.250 INCHES TOO FAR AFT WHICH DOES NOT ALLOW MINIMUM EDGE DISTANCE FOR THE AFT ROW OF RIVETS TO BE MAINTAINED. ONLY PROVIDES 7/32' (0.21875') EDGE DISTANCE FOR A MS20470AD6 RIVET WHEREMINIMUM EDGE ISSDR CA041001008Barrel Nut · damaged(CAN) WHEN TORQUE CHECK OF ENGINE MOUNT BOLTS PERFORMED OB BOLT CORRECT TORQUE COULD NOT BE ACHIEVED. BARREL NUT REMOVED AND FOUND TO HAVE DAMAGED THREADS AND WAS OF FIBER LOCK STYLE. BARRREL NUT AND BOLT REPLACED WITH IPC REQUIRED PARTS.SDR CA050221002Seal · cracked(CAN) DURING FLIGHT FUEL FUMES ENTERED IN THE AIRCRAFT CABIN. AFTER LANDING 3 PAX WERE TAKEN TO THE HOSPITAL DUE TO FEELING SICK FROM THE FUMES. FUEL CAP WAS SUSPECTED TO BE LEAKING WHICH CAUSED THE FUEL TO ENTER THE CABIN THRU THE PAX DOOR SEAL. FUEL CAP W
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