Dassault FALCON 2000
Service difficulty reports · 527
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 = 'FALCON2000' 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 = 'FALCON2000' 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 DXTA200500534Resolver · malfunctionedAFTER T/O, FLAP ASYM LIGHT ON AND SLIGHT ROLLING. FLAP INDICATES SLIGHTLY DOWN AND SLATS EXTENDED. GAINED ACCESS TO FLAP ASYM RESOLVERS & FOUND LT RESOLVER CABLE LOOSE. RESET RESOLVER AS REQUIRED, OPS CHECK GOOD. ALL WORK PERFORMED IAW FALCON 2000 MM CHAPTSDR DXTA200500522Aileron · lockedAFTER T/O FLAP RETRACTION AILERON LOCKED, VERY HARD TO MOVE. NO FLAP ASYMMETRY LIGHT. PITCH OK, PERFORMED NO FLAP LANDING AT LAX. ITEM IS UNDER INVESTIGATION.SDR DXTA200400509Duct · splitSMOKE SMELL & HAZE IN AFT CABIN AFTER T/O. SHUTOFF LT CABIN PAX SMOKE CLEARED. INSPECTED LT & RT TEMP SENSORS, A/C DUCTING AND AREA IN BAGGAGE UNIT, NO DEFECTS NOTED. INSPECTED FWD SERVICE COMPT, FOUND BLOWN INSULATION. FOUND DUCT SPLIT APART & MISSING INSSDR DXTA200400497Leg Assy · vibrationNOSE GEAR SCISSORS NOT PINNED PRIOR TO TAKE OFF, NLG WOULD NOT RETRACT INTO WHEEL-WELL, SEVERE VIBRATION FROM NOSE WHEEL WAS NOTED ON TOUCHDOWN. REMOVED NOSE LANDING GEAR LEG ASSY PN- D23332000-4 SN- B147. INSTALLED AN OVERHAULED NOSE GEAR LEG ASSY PN D233320SDR DXTA200400495Warning Light · illuminatedAFTER LOWERING GEAR A -BRAKE- YELLOW LIGHT WAS SEEN. PERFORMED CHECKLIST, LANDED WITH -BRAKE- YELLOW LIGHT ON. AFTER LOWERING GEAR A -BRAKE PRESS- YELLOW LIGHT WAS NOTICED. IN THE COURSE OF A FEW MINUTES LIGHT EXTINGUISHED BY ITSELF. ITEM IS UNDER INVESTIGSDR CA041222015Start Valve · failed(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN DURING CLIMB AND THE AIRCRAFT DIVERTED TO NEAREST AIRPORT. SUBSEQUENT INSPECTION REVEALED THE AIRFRAME AIR-START VALVE STUCK IN THE OPEN POSITION AND EVIDENCE OF LOCALIZED OVER HEATING. A (START VALVE FAILSDR DXTA200400483Engine · malfunctionedIN FLIGHT AT FL370- NOTICABLE VIBRATION (INTERMITTENTLY), NO WARNING LIGHTS OR INDICATIONS. RIGHT ENGINE ROLLED BACK, NO ABNORMAL INDICATION, IGNITION LIGHT MOMENTARY ILLUMINATION ONLY RIGHT THROTTLE NOT RESPONSIVE DISCENDING THRU APPROX 29000 FT. ITT EXCEEDSDR 2005FA0000238Clamp · looseCLIMBING THROUGH 27,000 FT THE RT GENERATOR WENT OFFLINE, SHORTLY AFTERWARDS, LT GENERATOR WENT OFFLINE, AN EMERGENCY WAS DECLARED AND THE AC LANDED WITH NO FURTHER INCIDENT, INVESTIGATION FOUND A LOOSE CLAMP CONNECTING A BLEED AIR DUCT TO THE CABIN COLD TEMPESDR DXTA200400407Odor · detectedELECTRICAL SMOKE SMELL IN COCKPIT WITH ELECTRICAL POWER ON, WHEN CIRCUIT BREAKER PANEL PUSH TO LIGHT BUTTON WAS USED THE OVERHEAD CIRCUIT BREAKER ON ESSENTIAL BUSS POPPED, STRONGEST SMELL ON LT SIDE. ITEM IS UNDER INVESTIGATION.SDR DXTA200400380Light · inoperativeON APPROACH GEAR SELECTED DOWN LT GEAR INDICATOR INOP, TESTED GEAR LIGHTS AND LT GEAR LIGHTS FAILED TO TEST. ACCOMPLISHED GEAR NOT DOWN CHECKLIST IAW PILOT EMERGENCY PROCEDURES, USED ALTERNATE GEAR EXTENSION CHECKLIST TO LOWER INSURE GEAR DOWN. REPLACED BOTHSDR DXTA200400374Actuator · failedDURING TAKEOFF ROLL WITH POWER LEVERS IN TAKEOFF FOR APPROXIMATELY 10-15 SECONDS AND AT 40 KNTS NO TAKEOFF CONFIGURATION WARNING ACTIVATED. REASON FOR WARNING CANNOT BE DETERMINED, CONFIGURATION WAS NORMAL FOR ALL SYSTEMS. REPLACED PITCH FEEL ACTUATOR IAW F2SDR DXTA200400372Warning Horn · activatedDURING T/O ROLL WITH POWER LEVERS IN T/O FOR APPROXIMATLEY 10-15 SECONDS AND AT APPROXIMATELY 40KNTS (NO TAKE OFF) CONFIG WARNING ACTIVATED REASON FOR WARNING CANNOT BE DETERMINED, CONFIGURATION WAS NORMAL FOR ALL SYSTEMS.- ITEM IS UNDER INVESTIGATION.SDR 2004FA0000586Actuator · delaminatedMAIN CABIN DOOR ACTUATOR DELAMINATED.SDR 2004FA0000585Actuator · delaminatedMAIN CABIN DOOR ACTUATOR (WISHBONE) DELAMINATING.SDR Y292004F00000Elt · activatedON GOING PROBLEMS WITH OUR ELT COMING ON IN FLIGHT FOR NO APPARENT REASON. THE PILOTS ARE USUALLY ABLE TO RESET FROM COCKPIT. REPLACED THE ELT UNIT 3 TIMES. TROUBLESHOT AND INSPECTED REST OF SYSTEM WITH NO FAULTS FOUND. WOULD LIKE TO KNOW IF THIS IS A PROBSDR DXTA220400317Light · inoperativeON APPROACH LOWERED GEAR HANDLE AND DID NOT RECEIVE GREEN LIGHT, PERFORMED EMERGENCY GEAR EXTENSION AND DECLARED EMERGENCY. AIRCRAFT LANDED SAFELY. PLACED AIRCRAFT ON JACKS AND PERFORMED GEAR SWING, FOUND BOTH RT GREEN LIGHTS BURNED OUT, REPLACED BULBS AND SYSDR DXTA200400314Engine · malfunctionedAT FL370 NR 1 ENGINE OIL PRESSURE DROPPED BELOW 25 PSI. PRECAUTIONARY SHUT DOWN NR 1 ENGINE AND DIVERTED TO IA, AIRCRAFT LANDED SAFELY. ITEM IS UNDER INVESTIGATION.SDR DXTA200400297Circuit Board · failedDURING FLIGHT THE RIGHT GENERATOR FAILED AFTER TAKEOFF, GENERATOR SWITCH REMAINED CLOSED. GENERATOR VOLT METER INDICATED 0 VOLTS, ACCOMPLISHED AIR TURN BACK AND LANDED OVERWEIGHT. - REMOVED AND REPLACED NR 2 ALTERNATOR PRINTED CIRCUIT BOARD (524PCZ) IAW FALCONSDR UO22004F00004Clamp · brokenCLAMP T LOCK BROKE AND SAFETY LATCH DID NOT STAY LATCHED ALLOWING BLEED AIR TO FILL THE AREA WHENEVER WING ANTI-ICE WAS SELECTED.SDR DXTA200400245Warning Light · illuminatedFIFTEEN MINUTES INTO FLIGHT AT FL290, LT WHEEL WELL OVERHEAT LIGHT ILLUMINATED WITH AUDIO FOR 1 SECOND. TWO MINUTES LATER IT OCCURRED AGAIN, 3 MINUTES LATER LIGHT CAME ON WITH AUDIO FOR APPROXIMATELY 15 SECONDS. ALL THREE TIMES LIGHT EXTINGUISHED BY ITSELF, SDR CW1R075KTube · crackedFITTING FOR PRESSURE SENSOR CRACKED ON IB WING ANTI-ICE TUBE. CRACK WAS IN WELD AREA. POSSIBLY HOT AIR FROM DUCT COULD DAMAGE CONTROL PUSH PULL ROD. CHECK AREA CAREFULLY BY REMOVING LAGGING AROUND TUBE DURING INSPECTION.SDR DXTA200400214Proximity Switch · inoperativeDURING APPROACH, PLACED GEAR HANDLE IN THE DOWN POSITION AND GOT GEAR UNSAFE LIGHTS. RECYCLED GEAR HANDLE AND GOT ONE GREEN LIGHT AND 3 RED. FOLLOWED EMERGENCY GEAR EXTENSION AND LANDED SAFELY. FOUND LANDING GEAR DOOR PROX SWITCHES INOPERATIVE, REMOVED AND RSDR SVU2004F00000Cable · bindingCABLE BINDING AND CAUSES FLAP ASYMMETRY.SDR DXTA200300143Circuit Card · failedDURING CRUISE AMBER "THRUST REVERSER" WARNING LIGHT CAME ON, NO AIRCRAFT BUFFETING OR ENGINE POWER REDUCTION NOTED. - INSPECT LT THRUST REVERSER IAW FALCON SERVICE ADVISORY FSA2000 78-30/03 ALL ITEMS GOOD AT THIS TIME. FOUND L40ER PC CARD BAD, REMOVED AND INSSDR 2003FA0001041Door · crackedON POSTFLIGHT INSPECTION A CRACK WAS FOUND ON AUX GEAR DOOR NEAR UPPER RT BOLT HOLE. THERE IS NO EVIDENCE OF IMPACT BY A FOREIGN OBJECT.SDR CW12003F00002Pipe · crackedWHILE PERFORMING A ROUTINE ENGINE INSPECTION, A BLEED AIR TAP FOR NACELLE ANTI-ICE PRESSURE SWITCHES WAS FOUND TO BE CRACKED AT THE WELD LOCATION. PROBABLE CAUSE WAS VIBRATION. THIS COULD BE PREVENTED BY INSTALLING SUPPORT BRACKET AND NOTING SPECIFIC AREA FOSDR CW12003F00001Pressure Switch · crackedWHILE PERFORMING A ROUTINE ENGINE INSPECTION A BLEED AIR TAP FOR NACELLE ANTI-ICE PRESSURE SWITCHES WAS FOUND TO BE CRACKED AT THE WELD LOCATION. PROBABLE CAUSE WAS VIBRATION. THIS COULD BE PREVENTED BY INSTALLING SUPPORT BRACKET AND NOTING SPECIFIC AREA FORSDR CW12003F00000Line · crackedWHILE PERFORMING A ROUTINE ENGINE INSPECTION A BLEED AIR TAP FOR NACELLE ANTI-ICE PRESSURE SWITCHES WAS FOUND TO BE CRACKED AT THE WELD LOCATION. PROBABLE CAUSE WAS VIBRATION. THIS COULD BE PREVENTED BY INSTALLING SUPPORT BRACKET AND NOTING SPECIFIC AREA FORSDR DXTA200300011Warning Light · inoperativeLEFT HAND WHEELWELL OVERHEAT WARNING LIGHT CAME ON DURING DESCENT.SDR CW12002F00002Pressure Switch · failedWHILE AIRCRAFT WAS WAITING TO DEPART, WITH BOTH ENGINES RUNNING, THE HYDRAULIC PRESSURE SWITCH INTERNALLY FAILED CAUSING ALL NR 2 SYSTEM HYDRAULIC FLUID TO EMPTY INTO THE AIRCRAFT AND ONTO THE GROUND. THE FLUID ESCAPED THROUGH A RELIEF HOLE ON THE BODY OF THESDR BTV2002F00000Latch · failedREFUELING DOOR CAME OFF IN FLIGHT, STRIKING RIGHT HORIZONTAL STABILIZER. DOOR LATCH FAILURE.SDR CW12002F00000Air Duct · collapsedCREW REPORTED CABIN COULD NOT WARM UP IN AUTOMATIC MODE, INSPITE OF TEMPERATURE INCREASE ON POTENTIOMETER. UPON EXAMINATION INSIDE OF DUCT PN 721-407 WAS FOUND TO HAVE INSULATION AND INTERIOR MESH COLLASPED RESTRICTING AIR FLOW. CAUSE OF COLLAPSE, UNKNOWN. SDR CW12001F00003Anti-Ice Valve · intermittentINTERMITTENT FAILURE OF THE WING ANTI-ICE SYSTEM CAUSING COCKPIT INDICATION TO GO FROM GREEN TO AMBER. SUSPECT VALVE IS STICKING.SDR CW12001F00002Anti-Ice Valve · failedINTERMITTENT FAILURE OF THE WING ANTI-ICE SYSTEM CAUSING COCKPIT INDICATION TO GO FROM GREEN TO AMBER. SUSPECT VALVE IS STICKING.SDR CW12001F00001Anti-Ice Valve · failedINTERMITTENT FAILURE OF THE WING ANTI-ICE SYSTEM, CAUSING COCKPIT INDICATION TO GO FROM GREEN TO AMBER. SUSPECT VALVE IS STICKING.SDR CW12001F00000Anti-Ice Valve · intermittentINTERMITTENT FAILURE OF THE WING ANIT-ICE SYSTEM CAUSING COCKPIT INDICATION TO GO FROM GREEN TO AMBER. SUPPORT VALVE IS STICKING.SDR 20010510AP004Door · leakingFOUND INSTRUMENTS AND RADIO DISPLAYS FOGGED OVER DUE TO CABIN WATER-LEAKS. LEAKS FOUND AROUND CABIN DOOR. SUSPECT LEAKAGE DUE IMPROPER DOOR ALIGNMENT AND/OR SEALING DURING MAUFACTURING. THIS CONDITION IF NOT CORRECTED WILL CAUSE PREMATURE CORROSION OF THE AIRCSDR 20010510AP003Line · leakingRIGHT MLG BRAKE LINE WAS FOUND LEAKING FROM THE B NUT THAT CONNECTS THE LINE TO THE BRAKE CALIPER FITTING. THE BRAKE LINE IS MADE OF CLEAR PLASTIC TUBING AND THE B NUT IS BRASS AND UTILIZES A BRASS COMPRESSION FITTING TO FORM THE SEAL AT THE CALIPER FITTING. SSDR 20010413CW012Control Rod · separatedMETAL END OF CONTROL ROD IS SEPARATING FROM CARBON FIBER. A MOVEMENT OF .003 IN WAS OBSERVED DURING OPERATION OF SYSTEM DURING C INSPECTION PART SENT FOR EVALUATION.SDR 20010222AP005Valve · failedFALCON 2000 COCKPIT PAX AND CREW LIGHTS ILLUMINATED ON THE GROUND. FOLLOWING COMPUTER DOWNLOAD FAULT ANALYSIS RECOMMENDATION, REPLACED CONDITIONING CONTROL VALVE. THIRD FAILURE OF SAME P/N VALVE IN EIGHT MONTHS OF OPERATION - EACH TIME IN A DIFFERENT POSITIOSDR 20001129SH013Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICCIENT CLEARANCE BETWEEN THE SEAL AND STAGE 2 HPT ROTOR DISC AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER SB CFE 738-A72-8041. (X)SDR 20001129SH012Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICCIENT CLEARANCE BETWEEN THE SEAL AND STAGE 2 HPT ROTOR DISC AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER SB CFE 738-A72-8041. (X)SDR 20001129SH011Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND STAGE 2 HPT ROTOR DISC AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER SB CFE 738-A72-8041. (X)SDR 20001129SH010Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND STAGE 2 HPT ROTOR DISC AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER SB CFE 738-A72-8041. (X)SDR 20000907SH030Seal · separatedLP FORWARD STATIC SEAL HAS INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER CFE FIELD ENGINEERING INSTRUCTIONS NR CFE 738-FSDR 20000907SH029Seal · separatedLP FORWARD STATIC SEAL HAS INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER CFE FIELD ENGINEERING INSTRUCTIONS NR CFE 738-FSDR 20000907SH028Seal · separatedLP FORWARD STATIC SEAL HAS INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE. INSPECTION PER DFE FIELD ENGINEERING INSTRUCTIONS NR CFE 738SDR 20000907SH027Seal · separatedLP FORWARD STATIC SEAL HAS INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE. INSPECTION PER DFE FIELD ENGINEERING INSTRUCTIONS NR CFE 738SDR 20000831SH023Seal · separatedLP FWD STATIC SEAL HAD INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER CFE FIELD ENGINEERING INSTRUCTION NR CFE 738-FEI-00SDR 20000831SH022Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER CFE FIELD ENGINEERING INSTRUCTION NR CFE 738-FE
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