Boeing DHC-8-301
Service difficulty reports · 571
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 = 'DHC8301' 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 = 'DHC8301' 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 CA070205004Bellcrank · broken(CAN) AN OPERATOR MADE AIR TURN BACK DUE TO NOSE GEAR DOOR MALFUNCTION. THE NLG DOORS WON’T CLOSE WHEN SELECTED. THE AMBER NOSE GEAR DOOR LIGHT SHOWED ON LANDING GEAR CONTROL PANEL. MAINTENANCE FOUND THE NOSE GEAR BELLCRANK BROKEN AT ONE OF THE LUGS. (TC NR 20SDR CA070202014Windshield · cracked(CAN) DURING FLIGHT, SMOKE AND FLAMES STARTING COMING FROM THE TOP OF FO`S WINDSCREEN. SECONDS LATER WINDSCREEN SHOWED SEVERAL CRACKS. FOUND TERMINAL END L2 BURNED, REMOVED AND REPLACED TERMINAL END AND F/O`S WINDSHIELD. (TC NR 20070202014)SDR CA070209018Packing · leaking(CAN) THE ENGINE LOST POWER IN CRUISE AND WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION FOUND A LEAK AT THE FUEL MANIFOLD TRANSFER TUBES. ALL TRANSFER TUBE O-RING PACKINGS WERE REPLACED. ON JAN 4TH FUEL LEAKAGE FROM THE SAME TRANSFER TUBES WAS OBSERVED DURISDR CA061211005Bearing Race · fractured(CAN) LIGHT TO MODERATE PROP VIBRATION IN CRUISE, AS POWER WAS REDUCED FOR DESCENT VIBRATION BECAME EXCESSIVE. AS A RESULT THE NR 1 PROP (CONDITION LEVER) WAS SELECTED TO START FEATHER (VIBRATION STOP) AND THEN NR 1 ENGINE WAS SHUTDOWN. ALL ENGINE PARAMETERSSDR CA061205001Yoke · cracked(CAN) DURING SCHEDULED A CHECK, RT MLG YOKE WAS FOUND TO HAVE A CRACKED FITTING AT THE AUX ACTUATOR ATTACH POINT. (TC NR 20061205001)SDR CA061107005Windshield · cracked(CAN) DURING CLIMB OUT, ALTITUDE APPROX. FL70, THE CO-PILOT NOTICED A SMALL CRACK IN THE MIDDLE OF HIS WINDSHIELD, WHICH WAS GETTING RAPIDLY BIGGER. EMERGENCY CHECKLIST FOR CRACKED WINDSHIELD WAS PERFORMED. RELANDING WAS UNEVENTFUL. A/C HANDED OVER TO MAINTENASDR CA061025003Cable · broken(CAN) FINDINGS DURING C-CHECK INSPECTION IN AREA WING STA 171, AFT SPAR, LT AND RT REVEALED HEAVILY CHAFED AILERON CABLES IN PULLEY AREA AT WING BS 171. ON RT SIDE THE CABLE WAS SEVERELY DAMAGED AND ONLY A PART OF ONE STRAND WAS LEFT INTACT. THE CABLE IS OF TYSDR CA061019008Seal · leaking(CAN) DURING CRUISE, FLIGHT CREW REPORTED R SIDE EMERG EXIT DOOR SEAL FAILED (LEAKING) RESULTING IN PRESSURIZATION LOSS . AIRCRAFT REQUESTED AND WAS CLEARED TO A LOWER ALTITUDE. AFTER NORMAL LANDING, MAINTENANCE INSPECTED AND REPLACED EMERGENCY EXIT DOOR SEAL.SDR CA061012005Pseu · warning light(CAN) AFTER TAKEOFF GEAR SELECTED UP , VISUALLY CONFIRMED GEAR WAS UP , INDICATION STILL SHOWED GEAR DOWN AND LOCKED (3 GREEN LIGHTS) , NORMAL GEAR EXTENSION AND AIRCRAFT RETURNED TO DEPARTURE AIRPORT FOR NORMAL LANDING. MAINTENANCE INSPECTION FOUND PSEU INTERSDR CA061102006Housing · failed(CAN) DURING APPROACH WHEN CREW SELECTED GEAR DOWN, NR 2 HYD ENG PUMP CAUTION LIGHT ILLUMINATED DURING EXTENSION CYCLE. NOSE GEAR DOORS AND RT MAIN GEAR DOORS REMAINED OPEN, LT MAIN GEAR DOOR CLOSED. QRH ITEMS FOR NR 2 HYDRAULIC SYSTEM AND GEAR DOORS OPEN WERESDR CA060928001O-Ring · damaged(CAN) DURING THE ACCOMPLISHMENT OF THE TASK 2150/05 (HEAT EXCHANGER CORE CLEANNING) WE FOUND A NEW O-RING DAMAGED IN THE ORIGINAL PACKAGE. THE O-RING COME FROM NATIONNAL O-RING MFGR. COMPD. NR V-14 MFG BATCH NR: 58978 CURE DATE: 4088 EXP. DATE: OCT 01,2009SDR CA060919003Socket · burned(CAN) AFTER BOARDING WAS COMPLETED AND DOORS CLOSED, CA1 REPORTED A STRONG SMELL OF SMOKE COMBINED WITH LIGHT SMOKE DEVELOPMENT IN THE CABIN. CONTROLLED DISEMBARKATION WAS ORDERED, MAYDAY CALL PERFORMED AND ON GROUND EMERGENCY ITEMS COMPLETED ON THE FLIGHT DECSDR CA061103008Fuel Control · faulty(CAN) THE ENGINE FLAMEOUT IN CLIMB AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. THE HYDROMECHANICAL FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103008)SDR CA061002003Diode · burned(CAN) ON DECENT THROUGH 10,000 FEET, F/O NOTICED A HAZY SMOKE IN THE COCKPIT. BOTH THE CAPTAIN AND THE F/O BEGAN TO FEEL A BURNING SENSATION IN THEIR THROATS. THEY DONNED THEIR OXYGEN MASKS AND REQUESTED A VISUAL DIRECT APPROACH. THERE WAS A DEFINITE ELECTRICSDR CA060921002Union · sheared(CAN) CREW REPORTED NR 2 ENG HYD PUMP CAUTION ILLUMINATED, PRESS AND QTY DEPLETED. FOLLOWING GEAR EXTENSION ON APPROACH. NO EMERGENCY DECLARED. MAINTENANCE FOUND THE HYD FITTING FROM THE EDP TO THE PRESS MANIFOLD SHEARED. SYD 8-29-002, REPLACEMENT OF ALUMINIUSDR CA061016001Wire · burned(CAN) AN OPERATOR EXPERIENCED AN EXTERNAL AC POWER PROBLEM THAT WAS TRACED TO SEVERAL BURNED WIRES AND A BLOWN (F4) FUSE. IT IS DETERMINED THAT THE MOST PROBABLE CAUSE FOR THIS EVENT WAS THE (12 GAUGE) FEEDER CABLES CHAFING TOGETHER ON THE ADJACENT STRUCTURE.SDR CA060816005Bearing · seized(CAN) DURING ROUTINE MAINTENANCE INSPECTION OF MFG TASK 422 (A CHECK 500 HR REPETITIVE TASK) ZONAL INSPECTION OF RT ENGINE COMPARTMENT. FOUND POWER AND CONDITION CABLE PULLEYS (2 EACH SYSTEM, TOTAL 4 PULLEYS) IN THE UPPER AFT NACELLE/FRONT OF WING SPAR, TO ALSDR CA060815002Mechanism · seized(CAN) DURING INTERNALLY GENERATED MAINTENANCE FLEET CAMPAIGN TO CHECK FOR EMERGENCY DOOR OPERATING FORCE. MAINTENANCE UNABLE TO OPEN FORWARD EMERGENCY EXIT DOOR USING INTERNAL OR EXTERNAL HANDLE ( TASK 5220/07). REQUIRED DISASSEMBLY OF DOOR OUTER SHAFT MECHANISDR CA060810001Rod End · seized(CAN) DURING A C-CHECK INSPECTION THE TASK WAS CALL UP TO INSPECT THE FWD EMERGENCY EXIT. UPON INSPECTION IT WAS DETERMINED THAT IT WAS EXTREMELY STIFF AND DIFFICULT TO OPERATE. UPON REMOVAL AND TROUBLESHOOTING IT WAS DETERMINED THAT THE CONNECTING ROD END (X1SDR CA060816002Guard · damaged(CAN) DURING CLIMB, AFTER GEAR UP SELECTION AMBER AND RED LIGHTS ILLUMINATED IN GEAR HANDLE, ALONG WITH 3 AMBER LANDING GEAR DOOR LIGHTS. A LOUD GRINDING NOISE WAS HEARD IN THE COCKPIT. AIRCRAFT RETURNED AND LANDED SAFELY TO THE ORIGINATING AIRPORT. MAINTENANCSDR CA060705004Shaft · broken(CAN) LOSS OF PROPELLER CONTROL DUE TO BROKEN ENGINE CONTROL SPRING STRUT; THE FAILURE OCCURRED DURING FLIGHT AND DISABLED CONTROL OF THE NO 1 PROPELLER. THE EMERGENCY FUEL SHUT-OFF HAD TO BE OPERATED TO SHUT THE ENGINE DOWN AFTER LANDING. AT THE TIME OF THE ISDR CA060804003Fitting · fractured(CAN) DURING THE FLIGHT, OPERATOR LOST ALL HYDRAULIC QUANTITY AND PRESSURE FROM THE SYSTEM NR 1 AND ALL ASSOCIATED LIGHTS. CREW COMPLETED THE RESPECTIVE CHECKLIST AND LANDED WITH FLAPS 0° AND WITHOUT NORMAL BRAKING, INVESTIGATION REVEALED THAT THE NR 1 PRESSUSDR CA060804001Control Rod · misinstalled(CAN) DURING CLIMB NR 2 ENGINE WAS MAKING ONLY 78 PERCENT POWER AND THE ENGINE POWER LEVER WAS JAMMED 1.5 INCH FROM FULL TRAVEL. AIRCRAFT RETURN ON GROUND SAFELY SHORTLY AFTER TAKEOFF. MAINTENANCE FOUND NR 2 CONTROL AND CONDITION LEVER RODS HARDWARE (BOLT ANSDR CA060424008Shaft · brokenFLIGHT CREW REPORTED EXCESS BACKLASH AND PROP SYNC DOES NOT SYNC. PROP WANDERING + - 5 TO 7 RPM. ENGINE SPRING STRUT ASSEMBLY REPLACED. AFTER DISASSEMBLY IN THE O/H SHOP, SHAFT P/N 87620130-101 WAS FOUND BROKEN AT POINT RIVET P/N MS204170AD3. THE SIZE OF THSDR CA060804004Indicator · malfunctioned(CAN) DURING DESCENT, CREW DETECTED A STRONG BURNING SMELL ON THE FLIGHT DECK. FLIGHT CREW DONNED OXYGEN MASKS AND LANDED WITHOUT FURTHER INCIDENT. FLIGHT CREW HAD REPORTED TO ENGINEERING THAT THE WEATHER RADAR WAS INOPERATIVE FROM TOP OF DESCENT. UPON INVESTSDR CA060804005Seal · leaking(CAN) DURING FLIGHT, NR 1 PROP LOST APPROXIMATELY 7 QUARTS OF OIL FROM THE HUB. UPON ARRIVAL AIRCRAFT WAS COVERED IN OIL (LT). THERE WAS NOT AN INFLIGHT SHUTDOWN AND NO EMERGENCY MEASURES WERE REQUIRED OR TAKEN. THE AIRCRAFT RESPONDED NORMALLY. THE PROP SEALSDR CA060322010Fuel Control · looseDURING CRUISE PILOT REPORTED ENGINE PARAMETERS WANDERING. NH +-0.4% NL +- 0.2%, RPM +- 2 . MAINTENANCE INSPECTION FOUND POWER LEVERS ARMS LOOSE (LOW TORQUE/STILL COTTER PINNED ARMS RETIGHTEN AT ALL PIVOT POINTS AND RE-COTTER PINNED. AIRCRAFT RETURNED TO SERSDR CA060221011Bracket · crackedDURING CRUISE FLIGHT, CREW REPORTED AILERON CONTROL SEEMED STIFF. AFTER NORMAL LANDING MAINTENANCE INSPECTION FOUND RT AILERON SUPPORT BRACKET FOR AILERON INPUT QUADRANT CRACKED. CAUSING OUTBOARD AILERON QUADRANT TO RUB ON BRACKET. THIS AIRCRAFT IS PRE MOD SDR CA060127001Door · separated(CAN) ON ARRIVAL TO BASE, THE DOOR FOR THE REFUEL PANEL WAS FOUND TO HAVE SEPARATED FROM THE NACELLE. THE HINGES, HINGE ATTACHMENT BOLTS AND SMALL FRAGMENTS OF THE COMPOSITE PANEL REMAINED ATTACHED. (TC NR 20060127001)SDR CA060127009Smoke Detector · malfunctionedEN ROUTE CAPT CONTACTED MX TO ADVISE BAGG SMOKE DETECT LIGHT FLICKERED A COUPLE OF TIMES. A FEW MINS LATER CAPT CONTACTED FLT DISPATCH AGAIN TO ADVISE LIGHT WAS NOW ON CONSTANT, DECLARED EMERG DIVERTING TO YYY. COMMUNICATION WAS LOST WITH FLT AND A CALL WAS SDR CA051205001Hose · rupturedAT T/O WHEN L/G WAS SELECTED 'UP', ABNORMAL IND LIGHTS WERE OBSERVED ON THE GEAR SELECTOR ANNUNCIATOR PANEL. IN ADDITION NR 2 OUTBOARD SPOILER CAUTION LIGHTS ILLUMINATED WITH NR 2 HYD SYSTEM IND GAUGES BOTH AT ZERO. FOLLOWING A MANUAL GEAR EXTENSION, A/C RETSDR CA061005008Windshield · failed(CAN) APPROXIMATELY 53 MINUTES INTO FLIGHT, SOON AFTER LEAVING FL 190, CREW HEARD A LONG (BANG) FOLLOWED BY THE OBSERVATION OF THE CAPTAIN’S MAIN WINDSHIELD SHATTERING, CREW CONTINUED DESCENT TO FL 100 AT RESTRICTED AIRSPEED OF 188 KNOTS AND MAINTAINED A CABINSDR CA050929001Shaft · broken(CAN) DURING POST ENGINE CHANGE RIGGING NR 1 ENGINE SPRING STRUT ASSEMBLY WAS REMOVED DUE TO EXCESSIVE PLAY (SLOPPY AT LOOSE). AFTER DISASSEMBLY AND INSPECTION SHAFT P/N87620130 WAS BROKEN AT POINT RIVET P/N MS204170AD3. THE SIZE OF THE RIVET LEAVES MINIMAL MSDR CA050819001Check Valve · leaking(CAN) AN OPERATOR EXPERIENCED A LOSS OF HYDRAULIC SYSTEM NR 2, IN FLIGHT, DUE TO A FRACTURED CHECK VALVE. A VISUAL INSPECTION OF THE CHECK VALVE REVEALED A CRACK AROUND THE CIRCUMFERENCE OF THE VALVE BODY. THE CHECK VALVE IS BEING RETURNED TO MFG FOR INVESTISDR CA050824009Turbine Blades · damaged(CAN) FOLLOWING TAKEOFF, THE ENGINE DEVELOPED HIGH VIBRATIONS ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES. P&WSDR CA050728002Control Unit · failedAN AIRCRAFT EXPERIENCE LT MLG NR 1 TIRE BURST ON LANDING, THEN THE LT MLG NR 2 TIRE BURST DURING TAXI. MAINTENANCE REPLACED LT MLG WHEELS REPLACED, ASCU AND LT GEAR A/S CONTROL VALVE. PERFORMED A/S SYSTEM TEST. AIRCRAFT RTS.SDR CA050718001Line · brokenOPERATOR EXPERIENCED A LOSS OF HYD SYSTEM NR 1 AFTER TAKEOFF. FLIGHT CREW MADE AN UNSCHEDULED LANDING. EDP NR 1 PRESS LINE FOUND BROKEN IN LT NACELLE. HYD LINE AND EDP NR 1 REPLACED. PURGED SYSTEM. AIRCRAFT RTS.SDR CA050718004Circuit Board · burnedOVERNIGHT MX, F/A STATED A NUMBER OF PAX CALL BUTTON LIGHTS COULD NOT BE RESET. DURING CHECK DISCOVERED ALL OF PAX SERVICE UNITS CONTROL CIRCUIT BOARDS HAD BEEN HEAT DAMAGED. INVESTIGATION REVEALED WIRE ON OUTLET SIDE OF ALL OF PSU CONTROL CIRCUIT BOARDS HADSDR CA050708003Collar · failedDURING HEAVY MAINTENANCE IT WAS DISCOVERED ON THE LHS WING FWD SPAR AT WS 490.0 SPLICE JOINT. 4 CRACKED LOCKBOLT COLLARS PN BACC30BK5 WERE FOUND. REQUEST HAS BEEN SENT TO BOMBARDIER TO REPLACE LOCKBOLTS AND COLLARS WITH HILOCK SUBSTITUTES. DETAILED VISUAL INSDR CA050630010Line · leakingAFTER TAKEOFF AND GEAR RETRACTION, CREW NOTICED LOSS OF HYDRAULIC FLUID IN THE NR 2 SYSTEM. AIRCRAFT RETURNED FOR NORMAL LANDING. MAINTENANCE INSPECTION FOUND THE HYDRAULIC FLEX LINE TO THE NOSE GEAR DRAG STRUT ACTUATOR LEAKING. LINES REPLACED. FLUID TOPPESDR CA050601004Heater · failed(CAN) AN OPERATOR HAS EXPERIENCED A SECOND INCIDENT OF PITOT HEAT FAILURE WITH SUBSEQUENTLY LOSS OF AIRSPEED INDICATION CAUSED BY A POPPED CB.SIX WEEKS AGO THE SAME OPERATOR LOST BOTH AIRSPEEDS BY POPPED CBS PITOT HTR 1 AND 2 SIMULTANEOUS. MOISTURE HAS BEEN FOSDR CA050527001Switch · burnedFLIGHT CREW REPORTED DURING THE APPROACH PHASE OF FEELING UNWELL, IT WAS THEN NOTED THE RUDDER TRIM SWITCH WAS HOT AND UNABLE TO FULLY OPERATE. THE C/B FOR RUDDER TRIM ACTUATOR WAS THEN NOTED AS TRIPPED. MAINTENANCE FOUND RUDDER TRIM SWITCH BURNT. THE SWITCHSDR CA050512001Spring · misinstalledAS A RESULT OF 'C CHECK' RECTIFICATIONS, THE A/C'S ELEV GUST LOCK SYS REQUIRED RE-RIGGING. DURING THE RE-RIGGING TASK AN UNUSUAL NOISE WAS NOTICED COMING FROM THE ELEV SYSTEM WHEN THE ELEVATORS WERE MOVED THROUGH THEIR OP RANGE. FURTHER INVESTIGATION WAS CARRISDR CA050421001Link · broken(CAN) AN OPERATOR HAS SUFFERED DAMAGE THEIR AIRCRAFT AS A RESULT OF AN NLG-UP LANDING. THE PRELIMINARY INVESTIGATION HAS REVEALED THAT LINK HAS FAILED.SDR CA050308008Collar · cracked(CAN) 8 COLLARS WERE FOUND CRACKED ON THE RT WING FORWARD SPAR AT EXTENSION SPLICE YW 490.00, ANOTHER 2 OF THE SAME COLLARS WERE ALSO CRACKED ON THE SAME LOCATION ON THE AFT SIDE. INSPECTION OF THE LT WING IN THE SAME YW 490.00 LOCATION REVEALED FURTHER TWO FSDR CA050221007Starter Gen · open(CAN) DURING CRUISE AT 16,000 FT, AC DEPRESSURIZED W/ILLUMINATION OF MSTR WARN LIGHT, MSTR CAUTION LIGHT, GPWS WARN LIGHT. SYS THAT REPORTED TO STOP WORKING: FMS, NAV, TRANSPONDER SYS. NR2 ADF WAS REPORTED TO BE WORKING, WAS USED TO LAND. ON APPROACH, LG WAS SDR CA050329004Engine · malfunctioned(CAN) DURING CRUISE, ENGINE TORQUE INCREASED UNCOMMANDED, ACCOMPANIED BY A LOW OIL PRESSURE WARNING ANNUNCIATION WITH OIL PRESSURE DECREASING TO ZERO. THE ENGINE WAS SHUTDOWN IN FLIGHT AND SUBSEQUENTLY REMOVED FOR INVESTIGATION. MFG WILL INVESTIGATE THE INCISDR CA050211004Hose · ruptured(CAN) AFTER TAKE-OFF AND ON GEAR UP SELECTION, THE NOSE GEAR FAILED TO RETRACT AND IT WAS OBSERVED BY THE CREW THAT THE NR 2 HYDRAULIC SYSTEM WAS ALMOST DEPLETED OF OIL. AIRCRAFT WAS MAINTAINED VISUALLY IN THE CIRCUIT WHILE ALL RELEVANT QRH PROCEDURES WERE COMSDR CA050209005Turbine Blades · damaged(CAN) CREW NOTED THAT THEY HAD NO NP INDICATION AFTER START OF THE NR 2 ENGINE, AND OBSERVED THAT THERE WAS NO PROPELLER ROTATION THE ENGINE WAS THEN SHUTDOWN. CREW REPORTED ALL OTHER ENGINE INDICATIONS WERE NORMAL DURING THE START. INITIAL INVESTIGATION NOTSDR CA050519003Housing · cracked(CAN) PILOT REPORTED GETTING A VIBRATION WHEN APPLIED BRAKE PRESSURE WHILE SLOWING DOWN AFTER LANDING AND EVEN WHILE TAXING. ENGINEERS INSPECTED THE BRAKES AND FOUND THE NR 4 POSITION BRAKE WORN TO LIMITS. BRAKE WAS REPLACED AND SENT TO THE BRAKE SHOP. THE U
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