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 S9BA200700020Skin · corroded"OPEN" RT WING BOTTOM SKIN CORRODED OB OF NACELLE AT STATION 147.SDR CA071025005O-Ring · failed(CAN) PILOT OBSERVED A SUDDEN DROP IN OIL PRESSURE AND ELECTED TO PERFORM AN IN FLIGHT SHUTDOWN. FLIGHT WAS DIVERTED. GROUND INSPECTION REVEALED A DEFECTIVE O-RING ASSOCIATED WITH THE PCU (PROPELLOR CONTROL UNIT) ASSEMBLY. (TC NR 20071025005)SDR S9BA200700023Inlet Guide Vane · crackedDURING 400 HOUR BORESCOPE INSPECTION, FOUND CRACKS ON CT STATOR THAT ARE BEYOND SERVICEABLE LIMITS. PERFORMED HOT SECTION INSPECTION. REPLACED IE DUCT ASSEMBLY.SDR CA071001003Power Supply · damaged(CAN) DURING CRUISE, THE INTERNAL COCKPIT LIGHTING WAS SWITCHED ON, OVERHEAD PANEL LIGHTS DID NOT ILLUMINATE. OVERHEAD PANEL LIGHT CIRCUIT BREAKER WAS OBSERVED AS TRIPPED. CIRCUIT BREAKER WAS RESET. A FEW MINUTES LATER A SUSPECTED ELECTRICAL BURNING SMELL WAS SDR CA070924007Fitting · damaged(CAN) NEW AILERON CABLE P/N JNL-C6CF1153-3 FROM JNL (W/O 022. THE CSP FITTING MEASURES .4405. THE CSP FITTING WILL NOT ENGAUGE INTO THE AILERON QUARDRANT. ORIGINAL CABLE CSP FITTING MEASURES .4320 (TC NR 20070924007)SDR CA070924005Fitting · mismanufactured(CAN) NEW AILERON CABLE P/N JNL-C6CF1125-3 FROM JNL (W.O. 091) THE CSP FITTING ON IT MEASURES .4405. THE CSP FITTING WILL NOT ENGAUGE INTO THE RECEPTICAL ON THE QUADRANT. THE CABLE REMOVED MEASURES .4310. (TC NR 20070924005)SDR S9BA200700017Relay · burnedSMOKE ODOR IN CABIN. FOUND A/C RELAY BURNED UP. DEFERRED AIR CONDITIONING IAW MEL 21-1 WILL PROVIDE SUPPLEMENTAL INFORMATION WHEN GENERATED. REMOVED AND REPLACED RELAY M83536/9-026M. NO SN THIS ACTION CLEARED DMI 8743 ACTT 19842.6 ACTC 43532SDR CA080213011Stud · sheared(CAN) DURING TAXI, A SNAP WAS HEARD BY THE FLIGHT CREW AND HYDRAULIC STEERING CONTROL WAS LOST. THE AC WAS TAXIED TO THE RAMP USING DIFFERENTIAL PWR AND BRAKING. THE STUD SECURING THE HYD STEERING ACTUATOR WAS FOUND SHEARED. THE NOSE GEAR ASSY WAS REPLACED ANSDR CA070803002Tscu · inoperative(CAN) AUTOFEATHER DID NOT ARM DURING THE TAKEOFF ROLL. TAKEOFF WAS ABORTED AND AN AUTOFEATHER TEST PERFORMED ON THE TAXIWAY WHICH ALSO DID NOT ARM THE AUTOFEATHER. RETURNED TO BLOCK WHERE MAINTENANCE PERFORMED TROUBLESHOOTING AND REPLACED THE RT TSCU. (TC NRSDR CA070802008Connector · unserviceable(CAN) ON CLIMB OUT SHORTLY AFTER TAKEOFF, THE BETA WARNING LIGHTS (BOTH) CAME ON AND THE NR 2 PROPELLER STARTED TO FEATHER. THE PILOT PULLED THE BETA SYSTEM CIRCUIT BREAKER BUT THE LIGHTS DID NOT GO OFF, BUT THE PROPELLER STOPPED GOING TO FEATHER. THE PILOT SDR S9BA1407Arm · corrodedLEFT HAND I/B FORE FLAP O/B HINGE ARM CORRODED. REMOVED AND REPLACED FORE FLAPSDR S9BA1007Fan · odorODOR OF BURNING WIRES IN AIRCRAFT. SHUTDOWN AIR CONDITIONING AND CABIN FANS. ODOR SUBSIDED. REMOVED AND REPLACED LT AND RT CABIN BLOWER FANS. (SZ57-003-2A)SDR CA070704002Rod · mismanufactured(CAN) DURING INSPECTION OF THE FLAP RODS IAW S/B 6/502 AND 6/388 IT WAS NOTICED THAT THE SWAGED END OF THE FLAP ROD WAS NOT COMPRESSED. UPON INSPECTION OF THE ROD IT WAS NOTED THAT THE COLLAR WAS NOT IN THE CORRECT POSITION AND HAD NOT BEEN COMPRESSED ENOUGH.SDR CA070704016Gearbox · distressed(CAN) PRIOR TO START OF DESCENT, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE. DURING THE DESCENT THE ENGINE FLAMED OUT. SUBSEQUENT INSPECTION REVEALED REDUCTION GEARBOX DISTRESS. MFG WILL INVESTIGATE THE EVENT AND ADVICE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR SDR CA070515007Oil System · malfunctioned(CAN) DURING CRUISE FLIGHT, THE FLIGHT CREW NOTICED A MOMENTARY FLUCTUATION AND THEN DECREASING OIL PRESSURE, THEN EVERYTHING RETURNED TO NORMAL. MOMENTS LATER, THE ENGINE FAILED AND THE CREW CARRIED OUT THE SHUTDOWN. THE AIRCRAFT LANDED WITHOUT INCIDENT, ONSDR S9BA0707Attach Bracket · crackedRIGHT HAND FLOAT FORWARD SPREADER BAR ATTACH FITTING HAS A LONGITUDINAL CRACK (WITH THE GRAIN) ACROSS THE TOP OF THE SPREADER BAR ATTACHMENT LUG.SDR S9BA0607Attach Fitting · corrodedRT WING AFT ATTACH FITTING CORRODED. REMOVED AND REPLACED WING ATTACH FITTING IAW SB 6/295 REV D.SDR S9BA00407Spar Cap · corrodedFOUND CORROSION ON RT WING LOWER MAIN WING SPAR CAP BETWEEN STATION 35.2 AND STATION 74. REPAIRED IAW RD-57-24 AND INSTALLED SKIN PATCH IAW SRM 57-30-00 FROM STA 47 TO STATION 60.SDR CA070413004Control Box · failed(CAN) THE AIRCRAFT WAS BEING USED FOR CREW TRAINING WHEN, ON TAKEOFF, THE RT PROPELLER RPM DROPPED TO 30 PERCENT. THE PILOTS ABORTED THE TAKEOFF AND RETURNED TO THE RAMP. THE PILOTS NOTED THAT NP WAS STILL AT 30 PERCENT WITH THE POWER LEVER AT IDLE. THE PROPELSDR S9BA00307Attach Fitting · corrodedRT FORWARD FRAME 239 AFT WING ATTACHMENT LUG HAS CORROSION. REMOVED AND REPLACED FRAME SUBASSEMBLY, SIDE FUSELAGE STA 239.88SDR CA070405008Torque Link · cracked(CAN) LOWER TORQUE LINK CRACKED AT ATTACHMENT LUG TO UPPER TORQUE LINK. CRACK FOUND ON ROUTINE MAINTENANCE INSPECTION (TC NR 20070405008)SDR CA070405006Collar · cracked(CAN) STEERING COLLAR CRACKED AT RADIUSED AREA OF ATTACH STUD TO STEERING ACTUATOR. FOUND AT ROUTINE MAINTENANCE INSPECTION (TC NR 20070405006)SDR CA070405005Flapper Valve · obstructed(CAN) THE RAM AIR FLAPPER VALVE, P/N C6VF1153-1, BECAME JAMMED IN IT`S DUCT. ATTEMPTS BY THE PILOT TO RECTIFY THE PROBLEM BY MOVING THE CONTROL LEVER BACK AND FORTH RESULTED IN THE CONTROL CABLE, P/N 130-032A22.75B29.0, BECOMING KINKED AND UNSERVICEABLE. DIS-SDR CA070329007Governor · unserviceable(CAN) A GROUND INCIDENT OCCURRED WHERE ONE AC TAXIED INTO ANOTHER. BOTH AIRCRAFT WERE ON STRAIGHT SKIS. AFTER START-UP THE AC MOVED FORWARD FROM ITS PARKING SPOT, THEN WHEN THE PILOT MOVED THE POWER LEVER INTO REVERSE THE NR 2 PROP WENT INTO REVERSE MOMENTARSDR CA070307008Skin Panel · corroded(CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM THE EXHAUST STACKS. REPAIRS TO CORRODED RIVETS WAS INITIATED AND REVEALED CORROSION UNDER THE RIVET HEADS EXISTED TO A DEPTH OF 0.011. REPAIRSDR CA070307007Skin · corroded(CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM THE EXHAUST STACKS. REPAIRS CARRIED OUT IAW REO6-57-30-V019 (YW 85-91.25) AND REO6-57-30-V020 (YW 122-135). (TC NR 20070307007)SDR CA070307006Skin · corroded(CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM THE EXHAUST STACKS. REPAIRS CARRIED OUT IAW REO6-57-30-V017 (YW 85-91.25) AND REO6-57-30-V018 (YW 127-146). (TC NR 20070307006)SDR CA070307004Skin Panel · debonded(CAN) DEBONDING OF UPPER WING SKIN, IB OF NACELLE. DEBONDING DETECTED DURING ULTRA SONIC INSPECTION IAW SB 6/543. REPAIR CARRIED OUT IAW REO6-57-30-V012 REV A. (TC NR 20070307004)SDR CA070307003Skin Panel · debonded(CAN) DEBONDING OF UPPER WING SKIN, OB OF NACELLE. DEBONDING DETECTED DURING ULTRA SONIC INSPECTION IAW SB 6/543. REPAIR CARRIED OUT IAW REO6-57-30-V013 REV A. (TC NR 20070307003)SDR CA070307002Buckle · damaged(CAN) WHEN COMPLYING WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 AN INSPECTION FOR INTERFERENCE BETWEEN THE YOKE AND SEATBELT BUCKLE WAS CARRIED OUT IAW NM-06-29.THE RESTRAINT RELEASE MECHANISM ON PILOT AND COPILOTS SEAT BELTS CAN BE OPERATED UNINTENTIONALLY BYSDR CA070219008Bracket · loose(CAN) WHILE FLIGHT CREW WHERE CONDUCTING A GROUND RUN, MAINTENANCE ON THE GROUND NOTED THE RT ELEVATOR WAS MOVING UP AND DOWN EXCESSIVELY. UPON INVESTIGATION, MAINTENANCE FOUND BRACKET P/N C6TPM1022-28 WITH RIVETS WORKING AND SEVERAL WHERE ACTUALLY MISSING. THSDR CA070131001Connector · separated(CAN) AIRCREW REPORTED THAT THE NR 1 FUEL FLOW WAS FLUCTUATING WITH NO OTHER ENGINE PARAMETERS BEING AFFECTED. MAINTENANCE TROUBLESHOT THE SYSTEM, SWAPPED GAUGES FROM SIDE TO SIDE, PERFORMED ENGINE RUNS AND COULD NOT FAULT THE SYSTEM. AIRCRAFT WAS RELEASED FOSDR CA070130001Line · leaking(CAN) FLIGHT CREWS REPORTED THAT FUEL FLOW FLUCTUATES WHEN BOOST PUMPS ARE SELECTED OFF. SEVERAL VACUUM LEAKS WHERE FOUND IN THE FUEL LINES IN THE NACELLE AREA. SYSTEM SEALED AS REQUIRED, ENGINE GROUND RUNS CARRIED OUT AND NO FLUCTUATIONS NOTED AT TAKEOFF POWESDR CA070117005Cable · damaged(CAN) NEW CABLE, THE BALL END OF THE TRIM CABLE IS OUT OF ROUND AND WILL NOT FIT INTO THE TRIM JACK ASSEMBLY. WHERE THE CABLE MEETS THE BALL END IT HAS BEEN BRAZED AND THE CABLE HAS NOW FRAYED AFTER ATTEMPTING TO INSTALL IT INTO HTE TRIM JACK ASSEMBLY. (TC NR SDR CA070129004Buckle · damaged(CAN) SPECIAL INSPECTION OF CREW SEAT BELT ROTORY LATCH SYSTEM PERFORMED. BOTH LT AND RT CREW SEATBELT BUCKLE ASSEMBLIES WERE CAPABLE OF BEING UNLATCHED WHEN CONTACTED BY THE CONTROL YOKE WHEN ROTATED LT OR RT WITH THE YOKE FULL AFT AND THE SEAT IN THE MOST FOSDR CA070115016Control Cable · broken(CAN) TRIM CABLE WAS FOUND BROKEN AND WAS REPLACED. THE BROKEN CABLE IS BEING ANALYZED AT THEIR LOCAL AIRWORTHINESS AUTHORITY AND WE AWAIT THE RESULTS. (TC NR 20070115016)SDR CA070103011Turbine Blades · fractured(CAN) ENGINE OIL PRESSURE AND TORQUE WERE SEEN TO FLUCTUATE IN FLIGHT FOLLOWED BY A LOUD NOISE AND AN ENGINE FLAMEOUT. SUBSEQUENT INSPECTION REVEALED METAL IN THE ENGINE OIL AND FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR THE INVESTIGATION OF THE EVENT SDR CA070209006Turbine Blades · fractured(CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE AND SHUTDOWN UNCOMMANDED. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE SDR CA070115010Turbine · disintegrated(CAN) DURING CRUISE FLIGHT, THE CREW NOTICED OIL PRESSURE ON THE NR 2 ENGINE FLUCTUATING BETWEEN 60-70 PSI, WITHIN SECONDS THE TQ PRESSURE STARTED TO FLUCTUATE. THE ENGINE MADE 3 BIG BANGS AND SHUTDOWN. THE CREW LANDED THE AIRCRAFT AT THE NEAREST AIRPORT WITHOSDR CA070105002Turbine Blades · fractured(CAN) ENGINE OIL PRESSURE WERE REPORTED TO FLUCTUATE IN CRUISE FOLLWED BY A LOUD NOISE AND AN UNCOMMANDED ENGINE SHUTDOWN. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL AND FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THESDR CA070302003Switch · tripped(CAN) FOLLOWING REMOVAL OF THE CVR FOR TESTING IT WAS DETERMINED THAT THE INERTIA SWITCH HAD BEEN PREVIOUSLY TRIPPED CAUSING THE REQUIRED DATA NOT TO BE RECORDED. A RESET OF THE SWITCH HAD THE SAME RESULTS WITH PREMATURE ACTIVATION CAUSING THE RECORDING TO STOSDR CA061129004Clamp · damaged(CAN) THIS DEFECT WAS ORIGINALLY IDENTIFIED IN THE SUBJECT AIRCRAFT FLIGHT LOG DATED OCTOBER 26, 2006.SUBSEQUENT INVESTIGATION BY OUR QUALITY ASSURANCE DEPARTMENT GENERATED THE REQUEST THAT A SDR BE FILED. THE AIRCRAFT ARRIVED IN OTTAWA FOR A SCHEDULED INSPECTSDR CA061218020Pressure Switch · failed(CAN) ON INVESTIGATION OF THE REPORTED AUTOFEATHER DEFECT, THE LT ENGINE PRESSURE SWITCH, PN 8190026, WAS FOUND TO BE DEFECTIVE. REPLACEMENT OF THE COMPONENT CURED THE PROBLEM WHICH IS CONSIDERED TO BE AN ISOLATED RANDOM FAILURE. (TC NR 20061218020)SDR S9BA00906Hinge · corrodedDURING INSPECTION, FOUND LT IB FORE FLAP IB HINGE (PN 6WFM1109-33) WITH ATTACHED RIB CORRODED.SDR S9BA00806Hinge · corrodedDURING INSPECTION, FOUND LT IB FORE FLAP OB HINGE (PN C6WF1101045) CORRODED.SDR CA061220003Turbine Blades · damaged(CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A DECAY ON ENGINE PARAMETERS. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED DAMAGE TO COMPRESSOR AND POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT ANDSDR CA061019007Pressure Switch · failed(CAN) AFTER TAKE OFF WHILE REDUCING POWER FROM TAKE OFF POWER TO CLIMB, THE L/H PROP AUTOFEATHERED. AUTO FEATHER CIRCUIT BREAKER PULLED AND PROP RETURNED TO NORMAL. MAINTENANCE CONFIRMED SNAG AND REPLACED THE AUTOFEATHER PRESSURE SWITCH, CARRIED OUT GROUND RUNSDR CA061020007Unknown · unknown(CAN) TYPE CERTIFICATE HOLDER (TCH) RECEIVED CALL INDICATING THIS AIRCRAFT WAS IN LEVEL FLIGHT WITH AN INDICATED AIRSPEED OF 120 KNOTS. THE PILOT FELT A VIBRATION IN THE AIRFRAME, LOOKED OUT THE LT WINDOW AND SAW THAT THE LT WING WAS FLUTTERING UP AND DOWN. THSDR 9SBA00706Frame · corrodedCORROSION FOUND ON LT NACELLE HOOP FRAME (ANGLE FIREWALL) REMOVED AND REPLACE HOOP FRAME IAW AC 43.13-1B PARA 4.23 AND 4-6.SDR S9BA00606Mount · corrodedRIGHT ENGINE RIGHT ENGINE MOUNT PLATE HAS CORROSION. REMOVED AND REPLACED RIGHT ENGINE MOUNT PLATE IAW RD-54-006.
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