Boeing DHC-7-102
Service difficulty reports · 246
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 = 'DHC7102' 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 = 'DHC7102' 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 2022FA0000365Bracket · crackedAFTER INSPECTION PER VIKING SB V7-27-03 REV0 ISSUED 18 OCT 21. PILOTS RUDDER PEDAL ADJUSTMENT BRACKET WAS FOUND TO BE CRACKED. REPLACED BRACKET. AWAITING UPDATE TO 1-7-7E MM FOR NEW INSPECTION FREQUENCY.SDR 2022FA0000364Bracket · crackedAFTER INSPECTION PER VIKING SB V7-27-03 REV0 ISSUED 18 OCT 21. PILOTS RUDDER PEDAL ADJUSTMENT BRACKET WAS FOUND TO BE CRACKED. REPLACED BRACKET. AWAITING UPDATE TO 1-7-7E MM FOR NEW INSPECTION FREQUENCY.SDR QM7R201906142503Bracket · crackedONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS.SDR QM7R201906142502Bracket · crackedONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS.SDR QM7R201906142501Bracket · crackedONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS.SDR 2019FA0000111Bracket · crackedPILOT'S RUDDER PEDAL CONTROL MECHANISM BRACKET ASSY CRACKED. IPC 27-20-00, FIG 10, ITEM 50, PN # 72710086-001. REPORTED A BRACKET HAD BROKEN ON THEIR AIRCRAFT AND RECOMMENDED "ONE TIME INSPECTION" FOR MAINTENANCE TO INSPECT THEIR ASSIGNED AIRCRAFT. INSPECTED ASDR 2019FA0000110Bracket · crackedPILOT'S RUDDER PEDAL CONTROL MECHANISM BRACKET ASSY CRACKED. IPC 27-20-00, FIG 10, ITEM 50, PN 72710086-001. REPORTED A BRACKET HAD BROKEN ON THEIR AIRCRAFT AND RECOMMENDED "ONE TIME INSPECTION" FOR MAINTENANCE TO INSPECT THEIR ASSIGNED AIRCRAFT. INSPECTED ASSSDR 2019FA0000109Bracket · crackedPILOT'S RUDDER PEDAL CONTROL MECHANISM BRACKET ASSY CRACKED. IPC 27-20-00, FIG 10, ITEM 50, PN 72710086-001. REPORTED A BRACKET HAD BROKEN ON THEIR AIRCRAFT AND RECOMMENDED "ONE TIME INSPECTION" FOR MAINTENANCE TO INSPECT THEIR ASSIGNED AIRCRAFT. INSPECTED ASSSDR QM7R201904020003Bracket · crackedONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS.SDR QM7R201904020002Bracket · crackedONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS.SDR QM7R201904020001Bracket · crackedONE TIME INSPECTION FOR CRACK/BREAK OF THE RUDDER CONTROL MECHANISM BRACKET. THE INSPECTION RESULTED IN IDENTIFYING A CRACK AT BOTTOM OF RADIUS.SDR K6JY2019040800001Bracket · crackedRUDDER CONTROL BRACKET ASSEMBLY P/N: 72710086-001 CRACKED AT PILOT'S RUDDER PEDAL'S ADJUSTMENT MECHANISM ASSEMBLY P/N 72710311-055. THE BRACKET APPEARS TO HAVE MATERIAL FATIGUE AT THE INBD ANGLE RUN-OUT OF THIS MACHINED PART. CRACK IS LOCATED IN THE RADII OF TSDR CA200102011Pump · malfunctioned(CAN) THE TEST RESULTS FOR TWO FUEL PUMPS WERE CALLED INTO QUESTION DURING THE 2018 PVI. THE OUT OF TOLERANCE CONDITIONS WERE DOCUMENTED ON NON-CONFORMANCE REPORTS AND APPROVED INTERNALLY BY QA, ENGINEERING AND THE PRM IN MAY 2017. PUMP S/NS 8071 AND 8074 COULSDR CA151229014Tube · chafed(CAN) MAINTENANCE WAS TROUBLESHOOTING A REPORTED FUEL SEEP FROM THE FUEL SHROUD DRAIN FOLLOWING AIRCRAFT REFUELING. WELDED REFUEL/DEFUEL TUBE ASSEMBLY P/N 72810012-001 WAS FOUND WITH A PIN HOLE CAUSED BY CHAFING OF THE WELDED REFUEL/DEFUEL TUBE ASSEMBLY WITH SDR CA151009001Indicator · malfunctioned(CAN) DURING CRUISE THE DECIMAL PART OF T5 GAUGE OF ENGINE 2 STOPPED GIVING INFORMATION. AFTER RECYCLING THE BREAKER THE CREW NOTICED THAT EVEN WITH BREAKER PULLED THE GAUGE WAS STILL POWERED. SHORTLY AFTER STARTING DESCENT, THE T5 GAUGE OF ENGINE 2 STOPPED GSDR CA150701009Garlock Seal · damaged(CAN) EN-ROUTE AT 15,000 FEET WHEN THE CREW RECEIVED A LOW OIL PRESS INDICATION FOR ONE OF THE LT ENGS. PT6A, & SHUT THE ENG DOWN AS A PRECAUTION. THE ACFT DIVERTED FOR A SAFE LANDING. IT WAS REPORTED THAT MX IDENTIFIED THE GARLOCK OIL SEAL ON THE HYD PUMP WSDR CA150515011Pump · failed(CAN) THE AIRCRAFT WAS ON A CREW CHANGE FLIGHT FOR A CUSTOMER, UPON START UP FOR DEPARTURE, THE FLIGHT CREW SAW THE HYDRAULIC QUANTITY FALL TO 0. THEY DISEMBARKED THEIR PASSENGERS AND CALLED MAINTENANCE. MAINTENANCE ARRIVED AND FOUND THAT THE NR 3 PUMP, SN 16SDR CA150113007Fcu · faulted(CAN) WHEN THE CREW REDUCED ENGINE POWER FOR THE DESCENT, THE LT ENGINE REMAINED AT CRUISE POWER OF 3800 FT-LBS. THE CREW VERIFIED THE ENGINE WAS RESPONSIVE ABOVE 3800 FT-LBS BUT WOULD NOT REDUCE BELOW, THEN THE PILOT REQUESTED TO RETURN TO THE AIRPORT. WHENSDR CA141209005Fuel Control · failed(CAN) WHILE IN THE DESCENT, THE POWER LEVER WAS REDUCED AND THE NUMBER 1 ENGINE TORQUE REMAINED AT CRUISE POWER SETTING OF 3800 FT-LBS. THE CREW VERIFIED THAT THE ENGINE AND GAUGES WERE RESPONSIVE ABOVE 3800 FT-LBS TORQUE BUT WOULD NOT REDUCE. A DIVERSION WAS SDR CA141126003Strap · corroded(CAN) FOLLOWING REMOVAL OF THE FOUR (4) ENGINE NACELLE INLET DEICE BOOTS, MISSING AND CORRODED RIVET HEADS WERE DISCOVERED ON THE FIBERGLASS INLET LIPS. FURTHER CORROSION WAS FOUND ON THE FOUR (4) ENGINE NACELLE STRAPS BENEATH THE FIBERGLASS INLET LIPS. MAISDR CA131217009Windscreen · arced(CAN) THE LT WINDSCREEN BEGAN ARCHING JUST AFTER TAKEOFF, THE WINDSHIELD HEAT WAS TURNED OFF AND THE ACFT RETURNED TO BASE, DURING THE RETURN TO DEPARTURE THE WINDSCREENS ICED UP REDUCING THE FLIGHT CREWS VISIBILITY. CADORS, 2013C5268 REFERENCES THIS INCIDENTSDR CA131218012Gcu · failed(CAN) RETURNED DUE TO AN ELECTRICAL PROBLEM (RT DC BUSS FAULT). ENGINE 1 THRU 4 GROUND RUN. DC SYSTEM BROUGHT ONLINE. NR 4 DC GEN OPENS DC BUS TIE AND AFTER A SHORT DELAY THERE WAS A RIGHT DC BUS FAULT. REPLACED NR 4 DC GCU. SYSTEM FUNCTION CHECKED, NO FAUSDR CA130125004Wire · damaged(CAN) BOTH NR 4 ENGINE FIRE DETECTION ELEMENTS FOUND TO HAVE CHAFE DAMAGE FROM CONTACT WITH AIRFRAME STRUCTURE CAUSING ACTIVATION OF THE FIRE WARNING. BOTH DETECTION ELEMENTS REPLACED, CHECKED SERVICEABLE.SDR CA120605006Turbine Blades · fractured(CAN) SHORTLY AFTER LEVELING OFF AT CRUISE ALTITUDE, THE FLIGHT CREW OBSERVED A DECREASE IN TORQUE FROM THE NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE FLIGHT RETURNED TO THE DEPARTURE POINT WHERE AN UNEVENTFUL LANDING WAS ACCOMPLISHED. POST FLIGHT INSPECTIOSDR CA120528009Blade · separated(CAN) APPROXIMATELY 40 NM NORTH OF AIRPORT, SHORTLY AFTER LEVELING OFF AT CRUISE ALTITUDE, THE FLIGHT CREW OBSERVED A DECREASE IN TORQUE FROM THE NR 2 ENGINE. THE NR 2 ENGINE WAS SHUTDOWN AND THE CREW RETURNED TO DEPARTURE. VISUAL INSPECTION OF THE 1ST STAGESDR CA120327003Angle · cracked(CAN) WHILE CONDUCTING A CORROSION INSPECTION, CRACKS WERE FOUND ON THE NR 1 NACELLE, OTBD LONGERON CHANNEL, PN 75410103-105, AND LONGERON ANGLE, PN 75410104-103, AND NR 4 NACELLE, INBD LONGERON CHANNEL, P/N 75410119-106, LONGERON ANGLE P/N 75410104-104, NR 4 SDR CA120216001Wire · chafed(CAN) WHILE CONDUCT EWIS TASK E-430 ON THE NR 3 NACELLE, NUMEROUS WIRES WERE FOUND TO HAVE BEEN CHAFED BY THE PHENOLIC BLOCK THAT SECURES THESE WIRES AS THEY PASS FROM THE RT MLG WHEEL WELL THROUGH THE FIRE WALL. THE WIRING AFFECTED IS AS FOLLOWS: 7160-30006DSDR CA120214006Longeron · cracked(CAN) WHILE CONDUCTING A CORROSION INSPECTION, CRACKS WERE FOUND ON THE NR 1 NACELLE OTBD LONGERON CHANNEL, PN 75410103-105 AND LONGERON ANGLE, PN 75410104-103 AND NR 4 NACELLE INBD LONGERON CHANNEL, PN 75410119-106 AND LONGERON ANGLE, PN 75410120-104. THE CSDR CA120213003Cable · broken(CAN) DURING PRE-FLIGHT INSPECTION OF THE ACFT, AFTER PULLING THE AILERON DISCONNECT HANDLES, IT WAS NOTICED THAT THE AILERON CONTROL WAS NOT ROTATING FULLY TO THE LT. MAINTENANCE INSPECTED AND COULD NOT REPRODUCE THE EFFECT UNTIL AFTER THEY OPERATED THE AUTO-SDR CA111219010Receiver · failed(CAN) INBOUND FOR LANDING, THE NR 2 GPS SCREEN WAS SEEN TEMPORARILY GOING BLANK THAN COMING BACK ON. WITHIN A FEW SECONDS BOTH CREW MEMBERS NOTED AN ODD ODOR IN THE COCKPIT. THE NR 2 GPS WAS TURNED OFF AND THE CIRCUIT BREAKERS WERE PULLED. THE ODOR DISSIPATEDSDR CA111110001Tire · separated(CAN) DURING A WALK AROUND A DEFECT WAS NOTICED ON THE INBD RT MAIN WHEEL TIRE. INVESTIGATION REVEALED THAT THE TIRE WAS SEPARATING/SPLITTING IN THE GAP BETWEEN THE TREAD, THIS WAS WELL INTO THE CORD. THE DEFECT WAS PRESENT 360 DEGREES AROUND THE TIRE IN VARYSDR CA110811005Line · failedDURING CRUISE , ENROUTE , NR 1 HYD SYS FAILED. CREW COMPLETED THEIR CHECKLIST AND LANDED NORMALLY WITHOUT INCIDENT AT AN ALTERNATE DESTINATION. ON GROUND LOCATED LEAK IN NR 1 NACELLE AT THE HYD MANIFOLD SUPPLY LINE. THE TUBE IN QUESTION HAD FRACTURED FOR APSDR CA110621009Pump · leakingUPON STARTING THE NR 3 ENGINE, THE T5 WAS OBSERVED TO BE RISING WHILE THE NG WAS SLOW TO RISE. THE START WAS ABORTED WHEN THE T5 HIT 900 DEGREES. MX INVESTIGATED AND FOUND THAT THE FUEL PUMP WAS LEAKING AND THE FUEL WAS GOING THROUGH THE GARLOCK SEAL AND INTSDR CA100804014Reservoir · leakingWHILE IN CRUISE FLIGHT, A ROUTINE CHECK OF THE ENGINES/SYS REVEALED THE NR 2 HYD FLUID QTY WAS INDICATING A SLIGHTLY LOWER LEVEL THAN EARLIER NOTED. AFTER A FEW MORE MINUTES OF MONITORING A SLIGHTLY FURTHER DROP WAS NOTED. THE DECISION WAS MADE TO RETURN TO BSDR K08R10FA0000470Bearing Race · damaged(K08R) UPON DISASSEMBLY OF THE PROPELLER ASSY, FOLLOWING REMOVAL FOR TIME CHANGE. THE NR 3 PROPELLER BLADE, PN PFA12D1-9, SN 862170, BEARING RACE WAS FOUND TO BE SIGNIFICANTLY DAMAGED WITH CONSIDERABLE SPALLING WITHIN THE RACE SURFACES WITH CRACKS AND THE ENDSDR 2010FA0000242Lever · separatedTHE ACFT LANDED WITH AN UNSAFE NOSE GEAR INDICATION. THE SUBSEQUENT INVESTIGATION DETERMINED THAT THE NOSE GEAR LOCK PIN LEVER SEPARATED FROM THE ACFT SOMETIME DURING TRAINING FLIGHT. A MORE DETAILED INSP OF LANDING GEAR COMPONENTS REVEALED THAT THE LOCK LEVSDR CA091126002Tube · misinstalled(CAN) DURING FLIGHT, NR 4 ENGINE LOST OIL PSI INDICATION ALONG WITH MASTER CAUTION & OIL PSI LIGHT ILLUMINATED ON ANNUNCIATOR PANEL. ENGINE SHUTDOWN & ACFT LANDED WITHOUT FURTHER INCIDENT. ENGINE INSPECTED & FOUND TO HAVE NO OIL IN OIL TANK. AFTER SERVICING OISDR HNAA2009081400254Light · brokenDURING INSPECTION IN SBY, FOUND EMERGENCY LIGHT SUB-ASSEMBLY BROKEN ON SIDEWALL PANEL AT ROW 4 A & C. REMOVED AND REPLACED SUB-ASSEMBLY AND SPLICED IN WIRES. OPERATIONAL CHECK WAS GOOD.SDR CA081222004Control Cable · corroded(CAN) DURING A PREFLIGHT, THE LEFT ELEVATOR DID NOT MOVE WITH THE CONTROL COLUMN INPUT. MAINTENANCE INVESTIGATED AND FOUND ONE OF THE CABLES SNAPPED UNDER THE LAVATORY. SUSPECT THAT A PREVIOUSLY REPAIRED LEAK FROM THE LAVATORY HAD LEAKED ON THE CABLES, AND TSDR CA080124011Skin Panel · corroded(CAN) WHILE CONDUCTING A CORROSION INSP ON AC, VENEZUELAN REGISTRATION YV1000, IAW THE CUSTOMERS EQUALIZED MAINT PROGRAM. NUMEROUS AREAS OF CORROSION WERE DETECTED THROUGHOUT THE AC. A THRESHOLD AND REPETITIVE CORROSION INSP PROGRAM IS MANDATED BY ADCF-98-03 SDR CA080116017Housing · cracked(CAN) DURING A 6 YEAR CORROSION INSPECTION, A CRACK WAS FOUND ON THE LT MLG OUTER HOUSING. THE CRACK IS LOCATED ON THE FWD SIDE AT ABOUT THE ONE O’CLOCK POSITION JUST WERE THE HOUSING TAPERS DOWN. EDDY CURRENT WAS USED ON THE CRACK, IT WAS DEEPER THAN THE 0.04SDR CA071217004Control Cable · disconnected(CAN) AFTER FLIGHT, THE NR 2 CONDITION LEVER WOULD NOT MOVE TO FEATHER OR CUTOFF, THE ENGINE HAD TO BE SHUTDOWN USING THE T-HANDLE. FURTHER INVESTIGATION REVEALED THAT THE NR 2 TELEFLEX CABLE HAD BECOME UNSCREWED NEAR THE BEARING. WE WERE UNAWARE THAT THE CASDR CA071115002Bearing · failed(CAN) AFTER LANDING THE LT OB MAIN WHEEL HUBCAP WAS DISCOVERED MISSING. FURTHER INVESTIGATION FOUND THE INNER BEARING WAS BLOWN APART, THE WHEEL AND BRAKE ASSY HAD EXTENSIVE DAMAGE FROM THE WHEEL RUBBING ON THE BRAKE ASSY. THE AXLE WAS INSPECTED, NO DAMAGE WASSDR CA070829004Intake Duct · corroded(CAN) LEVEL 3 CORROSION WAS FOUND BETWEEN THE LOWER INTAKE FORWARD LIP AND THE NACELLE STRUCTURE. (TC NR 20070829004)SDR CA070830006Rod · broken(CAN) DURING TROUBLESHOOTING, A PFCS INDICATOR PROBLEM, IT WAS NOTICED THAT THE ROD FOR THE RT IB ROLL SPOILER TRANSMITTER HAD SHEARED INSIDE OF THE ROD END AT THE SPOILER END. THERE WAS NO INDICATIONS OF THE ROD CONTACTING ANY OTHER SURFACE TO CAUSE IT TO BRESDR HNAA0700136Doubler · debondedDOUBLER UNDER STR 28 IS DISBONDED IN FRAME BAYS X424 TO X434.SDR CA070710004Guide Vane · failed(CAN) DURING FLIGHT, THE TURBINE TEMPERATURE ROSE SUDDENLY FROM 738 TO 785 DEGREES CELSIUS. A BORESCOPE INSPECTION REVEALED DAMAGE TO THE CT GUIDE VANE. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE HOT SECTION WAS REMOVED FROM THE ENGINE ASDR CA070214005Line · broken(CAN) AFTER LANDING THE NR 1 PROP RPM WAS LOWER THAN NORMAL. MAINTENANCE FOUND THAT THE P3 LINE FROM THE P3 FILTER BOWL TO THE ENGINE WAS BROKEN PN 3035279. THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20070214005)SDR CA061106015Diffuser · loose(CAN) SHORTLY AFTER LEVELLING OFF AT 17000 FEET, THE NR 2 ENGINE BEGAN TO SURGE AFFECTING ALL ENGINE PARAMETERS. THE POWER WAS REDUCED TO ALLEVIATE THE RESULTING OVER TEMPERATURE CONDITION. AT POWER SETTING ABOVE 70% NG THE ITT WOULD FLUCTUATE WILDLY TO OVER SDR CA060821004Fcu · failed(CAN) AFTER INSTALLING THE FRESHLY OVERHAULED ENGINE IN THE NR 1 POSITION, THE ENGINE WAS STARTED TO PERFORM THE BETA RIGGING; THE PROPELLER WAS UNFEATHERED, THE POWER LEVEL MOVED UP TO THE FWD BETA STOP TO RECORD NUMBERS, ALL THE PARAMETERS STABILIZED. THE N
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