Dassault FALCON 10
Service difficulty reports · 134
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 = 'FALCON10' 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 = 'FALCON10' 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 98ZZZX4360Flap Track · crackedDURING B-INSPECTION OF AIRFRAME, MAINTENANCE DISCOVERED THE CRACK IN THE LOWER CHANNEL OF THE RIGHT INBOARD FLAP, INBOARD TRACK. THE TRACK WAS REMOVED AND REPLACED AND THE ROLLER FOR THAT TRACK WAS REPLACED. NO BINDING OR ABNORMAL WEAR WAS DISCOVERED EXCEPT SDR 98ZZZX4028Tire · mismanufacturedAIRCRAFT BLEW OUT 2 RIGHT MAIN TIRES AT V1. INSP FOUND DEFECT ON 2 MORE TIRES ON A/C. CRACK STARTS AS A LIGHT CRAZING MARK THEN SPLITS TIRES IN TWO. GOODYEAR FLIGHT EAGLE 18X5.75.8, 190 MPH.SDR 99ZZZX53Line · crackedSMALL CRACK DEVELOPED IN-FLIGHT ON ALUMINUM LINE, P/N F10 22157, BETWEEN TEE AND RIGHT HAND OUTFLOW VALVE IN MANUAL CONTROL SYSTEM. ALLOWED CABIN AIR PRESSURE IN-FLIGHT (ACFT AT 18,000 FEET) INTO LINE RESULTING IN THE CLOSING OF BOTH OUTFLOW VALVES. CABIN PRSDR 98ZZZX3620Pump · failedDURING START OF THE RIGHT (NR 2) ENGINE, THE CREW NOTICED AN UNUSUAL NOISE THAT LASTED APPROXIMATELY 30 SECONDS. SCANNING THE INSTRUMENTATION REVEALED THE 'HYD 2' LIGHT ILLUMINATED AND THE HYDRAULIC PRESSURE GAUGE INDICATED ZERO. EXAMINATION OF THE RT ENGINESDR 98ZZZX2953Terminal · failedRIGHT ENGINE WOULD NOT CRANK, INSPECTION FOUND THE THROUGH-HULL TERMINAL AND WIRE LUG BURNED THROUGH. SUSPECT TERMINAL LOOSENED FROM TIME IN SERVICE. NOTE: BOLT WAS SECURED BY LOCK TAB AND WAS TIGHT.SDR 98ZZZX2248Line · leakingAFTER A NORMAL FLIGHT, HYDRAULIC FLUID WAS NOTICED RUNNING DOWN THE VERTICAL STABILIZER EMANATING FROM THE AFT ELEVATOR AREA. INVESTIGATION REVEALED THAT ONE OF THE FLEX HYDRAULIC HOSES FOR THE RUDDER/YAW SERVO WAS MAKING CONTACT WITH AND RUBBED THROUGH THE RSDR 98ZZZX2027Generator · shortedAN OVERHAULED STARTER/GENERATOR WAS INSTALLED ON THE NR 1 ENGINE OF A FALCON10. DURING ENGINE START, THE GENERATOR SWITCH IN THE COCKPIT TRIPPED TO 'OFF'. START WAS VERY SLOW. PUT GENERATOR SWITCH 'ON' AND GENERATOR WOULD NOT WORK. TROUBLESHOOTING SHOWED TSDR 98ZZZX2003Engine · failedTHE CREW INDICATED THEY WERE AT CRUISE ALTITUDE WHEN A VIBRATION WAS FELT AND AIRCRAFT YAWED. NR 2 ENGINE READINGS WERE BAD AND THE ENGINE WAS SHUT DOWN. THE CREW DIVERTED TO LITTLE ROCK, ARK AND LANDED AIRCRAFT SAFELY. THE ACFT WAS BROUGHT TO DASSAULT FALCSDR 98ZZZX1637Flap Track · crackedWHILE PERFORMING A-CHECK, NOTICED LT INBD FLAP LOOSE. PERFORMED INSPECTION AND FOUND 4 INCH CRACK IN LOWER RAIL. REMOVED PART FROM SERVICE AND INSTALLED NEW. PERFORMED NDT INSPECTION ON OTHER FLAP TRACK, NO INDICATIONS. SUSPECT CAUSE: LOWERING FLAPS AT EXCSDR 97ZZZX4965Driveshaft · wornSTARTER/GENERATOR DRIVESHAFT AND STARTER/GENERATOR DRIVESHAFT SPLINES WORN COMPLETLY AWAY CAUSING GENERATOR TO CEASE FUNCTIONING DURING OTHERWISE NORMAL FLIGHT. POSSIBLY LARGER SPLINES COULD HAVE PREVENTED THIS PROBLEM.SDR CA970930021Eng Inlet · failed(CAN) A PIECE OF THE ENG INLET FROM THE 9 O'CLOCK POSITION BROKE OFF AND WAS INGESTED INTO THE ENGINE. A/C REQUIRED TO MAKE UNSCHEDULED LANDING. INVESTIGATION REVEALED DAMAGE TO FAN AREA, FOUND PIECE OF METAL WEDGED IN STATOR VANES. SEVEN FAN BLADES REPLACESDR 97ZZZX4722Blade · failedIN-FLIGHT SHUT DOWN AND LOCK-UP OF ENGINE OCCURRED. ENGINE SENT TO THIS FACILITY FOR INSPECTION AND REPAIR. FOUND 4 EACH 3072712-1 HP TURBINE BLADES HAD RELEASED AT MID-SPAN OF BLADES. THIS WAS A CONTAINED FAILURE. THE BLADES AND TURBINE DISK WERE NEW AT LSDR 97ZZZX4721Blade · failedIN-FLIGHT SHUT DOWN AND LOCK-UP OF ENGINE OCCURRED. ENGINE SENT TO THIS FACILITY FOR INSPECTION AND REPAIR. FOUND 4 EACH 3072712-1 HP TURBINE BLADES HAD RELEASED AT MID-SPAN OF BLADES. THIS WAS A CONTAINED FAILURE. THE BLADES AND TURBINE DISK WERE NEW AT LSDR 97ZZZX4720Blade · failedIN-FLIGHT SHUT DOWN AND LOCK-UP OF ENGINE OCCURRED. ENGINE SENT TO THIS FACILITY FOR INSPECTION AND REPAIR. FOUND 4 EACH 3072712-1 HP TURBINE BLADES HAD RELEASED AT MID-SPAN OF BLADES. THIS WAS A CONTAINED FAILURE. THE BLADES AND TURBINE DISK WERE NEW AT LSDR 97ZZZX4719Blade · failedIN-FLIGHT SHUT DOWN AND LOCK-UP OF ENGINE OCCURRED. ENGINE SENT TO THIS FACILITY FOR INSPECTION AND REPAIR. FOUND 4 EACH 3072712-1 HP TURBINE BLADES HAD RELEASED AT MID-SPAN OF BLADES. THIS WAS A CONTAINED FAILURE. THE BLADES AND TURBINE DISK WERE NEW AT LSDR 97ZZZX2639Motor · screw loosePILOTS REPORTED FLAP CIRCUIT BREAKER TRIPPED ON SELECTION, RESET AND WORKED FINE. OPS CHECKED ON GROUND, COULD NOT DUPLICATE. APPROXIMATELY 20 DAYS LATER, HAPPENED AGAIN. REMOVED FLAP REDUCTION GEAR MOTOR, DISASSEMBLED, FOUND SET SCREW, PN ATQ1ED040005UL, ASDR 97ZZZX3039Detector · shortedUPON LANDING, ACFT PULLED RIGHT AND DEPARTED RUNWAY. MAINTENANCE FOUND NR 2 DETECTOR (TACH GEN) FOR THE ANTI-SKID SYSTEM HAD 'SHORTED OUT' WHERE THE WIRES ENTER THE CONNECTOR. THE DEAD SHORT APPARENTLY CAUSED THE CONTROL BOX TO READ A SKID SITUATION AND PRESDR 97ZZZX985Bellville Washer · failed600 HOUR SOAP SAMPLE INDICATED HIGH METAL CONTENT. SUSPECT FROM THE PLANET GEARS. INSPECTION INDICATED BELLVILLE WASHER WAS SPINNING. PLANET GEARSHAFT AND WASHER REPLACED. ENGINE WAS APPROXIMATELY 600 HOURS OUT OF MPI.SDR 97ZZZX983Blade · separatedTHE NR 2 ENGINE WAS SHUT DOWN DURING CLIMB-OUT DUE TO EXCESSIVE VIBRATIONS. INITIAL FINDS DURING TEAR DOWN INDICATE THAT SEVERAL BLADES SEPARATED FROM THE NR 3 L.P.T. THIS CAUSED SEVERE VIBRATIONS THAT, IN TURN, CAUSED THE N2 SECTION TO RUB.SDR 97ZZZX576Tire · leakingDURING ROUTINE AIR CHECK, FOUND TIRE PRESSURE LOW (NORMAL 145 POUNDS). RE-CHECKED TIRE FOR 3 DAYS, FOUND TO LOSE 11 TO 15 POUNDS PER DAY. THIS TIRE WAS OKAY ON THE FIRST 40 HOURS OF SERVICE. REMOVED, FOUND 5 SIDEWALL BLEED VENTS LEAKING. REPLACED WHEEL ANDSDR 96ZZZX5417Line · pin holeUPON LANDING, THE FLT CREW NOTICED HYD FLUID IN THE AREA OF THE VERT STAB. INVEST REVEALED THE RUD SERVO HYD RETURN LINE HAD BEEN CHAFED BY THE BRAIDED STEEL RUD SERVO LINE PN 000AE90-4-0232 WHERE A PIN HOLE HAD DEVELOPED. LINE WAS REPLACED AND PROTECTED WITHSDR JZBR12924Manifold · crackedCREW REPORTED RT ENGINE CANNOT MAKE TAKEOFF POWER DUE TO TEMP INDICATION. TROUBLESHOT SYSTEM AND FOUND NO TEMPERATURE DIFFERENCE BETWEEN NORMAL AND MANUAL MODE INDICATIONS. BLEED VALVE OPEN AT ALL TIMES. REPLACED BLEED VALVE, PROBLEM STILL EXISTED. CHECKEDSDR 96ZZZX4082Rod End · failedWHILE TAXIING AFTER LANDING, THE FLIGHT CREW HEARD A SNAPPING NOISE AND LOST NORMAL STEERING CONTROL. FOUND THE STEERING ACTUATOR ROD END SHEARED ON THE STEERING ACTUATOR. THE THREAD AREA WHERE THE FAILURE OCCURRED CANNOT BE INSPECTED UNLESS THE SEALER IS RESDR 96ZZZX2241Engine · failedNR 2 ENGINE HAD HIGH VIBRATION AND EGT 1 HOUR INTO THE FLIGHT. AIRCRAFT WAS EN ROUTE AT CRUISE GOING FROM 33,000 FEET TO 35,000 FEET. THE PILOT MADE A MANUAL ENGINE SHUT DOWN AND LANDED. INSPECTION OF NR 2 ENGINE UPON LANDING SHOWS METAL IN THE TAIL PIPE. SDR 96ZZZX748Actuator · defectiveUNABLE TO OBTAIN RT MLG GREEN LIGHT. FLYBY INDICATED GEAR DOWN - UNABLE TO VERIFY LOCKED. RT MLG FOLDED ON LANDING. INVESTIGATION REVEALED RT MLG DOWNLOCK WAS NOT LOCKING. RT MLG ACTUATOR DEFECTIVE.SDR 95ZZZX6600Bracket · crackedWHILE PERFORMING A-CHECK GENERAL VISUAL INSPECTION ITEM ON THE MLG DOORS, NOTICED A CRACK IN THE LOWER RADIUS OF THE LT GEAR DOOR UPLOCK BRACKET. THE CRACK WOULD NOT BE NORMALLY VISIBLE UNLESS LOOKING THROUGH THE HOLE IN THE DOOR INNER SKIN, AT THE LOWER OUTBSDR 95ZZZX6026Transmitter · explodedDURING GROUND CHECKS, POWER WAS SUPPLIED TO THE STALL VANE HEATER. AT THAT MOMENT, A LOUD EXPLOSION WAS HEARD AND OILY SMOKE DETECTED IN THE COCKPIT. FURTHER INVEST REVEALED TRANSMITTER HAD, IN FACT, EXPLODED WITH ENOUGH FORCE TO BLOW OFF MECHANISM HOUSING ASDR GQRR431EBreaker · trippedNR 1 FUEL TRANSFER CIRCUIT BREAKER 'POPPED' IN-FLIGHT, CAUSE UNKNOWN. THIS CIRCUIT BREAKER CONTROLS THE FUEL SOLENOID FROM THE LEFT WING AS WELL AS THE TIMER THAT CONTROLS THE SOLENOID. UNREGULATED FUEL OVERFILLED BOTH FEEDER TANKS THEN WAS PIPED, UNDER PRESSDR 95ZZZX4455Starter · bearing failedFORWARD BEARING FAILED DUE TO SUSPECTED LACK OF LUBRICATION. THIS IS 3RD BEARING FAILURE ON THIS PART NUMBER STARTER/GENERATOR. CHAPTER 5 REQUIREMENT FOR BEARING REPLACEMENT IS 900 HOURS. WERE CHANGING AT 600 HOURS, BUT WILL NOW CHANGE AT 500 HOURS.SDR 95ZZZX3728Line · rupturedRIGHT WING OUTBOARD SLAT INBOARD SLAT ACTUATOR, THE EXTEND HYDRAULIC LINE FRACTURED AT RADIUS LEADING TO SWIVEL FITTING DURING FUNCTION CHECK OF SLATS DURING TAXI OUT TO END OF RUNWAY. SLATS WOULD NOT RETRACT AND LOW QUANTITY OF HYDRAULIC FLUID AND LOW PRESSUSDR JGVR052601Cable · chafedDURING A DETAILED INSPECTION OF THE COCKPIT AREA, FOUND THE FORWARD UPPER CABIN DOOR CABLE (P/N 59047) CHAFING ON THE WIRE BUNDLE. THE BUNDLE RUNS TO THE CIRCUIT BREAKER PANEL WHICH IS LOCATED BEHIND THE PILOTS SEAT. THE WIRE BUNDLE CLAMPS WERE REPOSITIONED SDR 95ZZZX2830Wire · terminal looseWHILE PERFORMING A ROUTINE INSPECTION, FOUND WIRE TERMINAL ON WIRE NR PP19E6, ATTACHED TO TERMINAL NR 2 OF AUXILIARY BUS 'D' RELAY 51P, WAS NOT CRIMPED ON THE WIRE PROPERLY. THIS LEAD TO INCREASED RESISTANCE AT THIS CONNECTION WITH THE TERMINAL END AND APPROXSDR 95ZZZX1867Bolt · shearedDURING 2A INSPECTION, REMOVED STARTER/GENERATOR SHROUD TO INSPECT BRUSHES, FOUND BOLT HEAD THAT HOLDS PRESSURE PLATE, PN 36C717455G1, SECURED BY SAFETY WIRE ONLY. SUBMITTER SUSPECTS WRONG BOLT USED UPON ASSEMBLY (A NON-SHANKED BOLT WAS USED). INSTALLED PROPESDR 95ZZZX1260Switch · failedTHE THRUST REVERSERS HORN WOULD SOUND WITH ANY MOVEMENT OF THE NR 2 THROTTLE CONTROL ASSY. (NO DEPLOY LIGHTS WOULD ILLUMINATE AT THAT TIME.) FOUND SWITCH NR S-18 FAILING IN THE CLOSED POSITION WHEN MOVED. THIS IS THE DEPLOY POSITION OF THIS SWITCH.
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