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 = '750' 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 = '750' 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 2003F00228Warning Light · activatedVENTED FUEL OVERBOARD FROM RIGHT WING. 3240 NR INDICATED YELLOW CAS MESSAGE 'WING TANK OVERFILL RIGHT' ILLUMINATED. AIRCRAFT RATE OF CLIMB WAS 1000 FEET PER MINUTE. PERFORMED WING TANK REFUELING AND TRANSFER SHUTOFF OPERATIONAL CHECKS PER CESNA MM. NO DEFESDR 2003F00231Transmitter · malfunctionedON PREFLIGHT PRETEST SECONDARY TRIM FAILED SEVERAL TIMES IN THE NOSE UP DIRECTION. MOVEMENT STOPPED AND AMBER CAS 'SEC TRIM FALL' ILLUMINATED. REPLACED FAULTY STABILIZER POSITION TRANSMITTER. RIGGED AND TESTED PER CESSNA MM. OPERATIONAL CHECK IS GOOD AND ASDR 2003F00154Warning Light · illuminatedCABIN DOOR OPEN AMBER LIGHT FLASHED ON AND OFF WHILE TAXIING IN AT DTW. CLEANED AND LUBRICATED DOOR BAYONETS, CLOSING LATCH AND HANDLE RELEASE MECHANISM. OPERATIONAL CHECK IS NORMAL. AIRCRAFT WAS RETURNED TO SERVICE. (M)SDR DXTA200300001Circuit Board · failedON APPROACH TO GSO, (LT TR AUTOSTOW) AMBER CAS MESSAGE ILLUMINATED AND THROTTLE ROLLED BACK TO IDLE.SDR 2003F00328Frame · crackedFOUND DURING INSPECTION TAILCONE BELTFRAME AT FUSELAGE STATION 691 IS CRACKED. RANDOM CRACKING ORIGINATING AT ASSEMBLY PROCESS OF TAILCONE. REPLACED BELTFRAME P/N 6712617-13. (M)SDR UG8AG0243Control Module · malfunctionedSHORTLY AFTER TAKEOFF THE (RUDDER LIMIT FAIL) CAS MESSAGE ILLUMINATED. PERFORMED RUDDER CONTROL LIMITER TEST IAW MM. NO FAULTS DURING 3 HOURS OF TESTING. RESET RUDDER LIMIT CONTROL MODULE NK123. PERFORMED OPERATIONAL CHECK FLIGHT. NO PROBLEMS WERE ENCOUNTSDR DXTA200300004Circuit Board · failedUPON LANDING THE LT THRUST REVERSER DEPLOYED, BUT THE HANDLE WOULD NOT LET THRUST GO ABOVE IDLE.SDR UG8AG0342Flap Track · contaminatedAFTER SELECTING FLAPS UP, AMBER FLAPS FALL LIGHT CAME ON. UNABLE TO RESET. RETURN TO DTW. SLATS OK. ZERO FLAPS. ICE, WATER AND SAND FOUND IN THE LT AND RT INBOARD FLAP WELLS AND FLAP TRACKS. CAUSED FLAP MOTOR OVERCURRENT DURING FLAP ACTUATION.SDR CNQ2003F00000Hose · rupturedON CLIMB OUT, HYDRAULIC SYSTEM (A) LOST ALL FLUID. UPON INSPECTION THE HOSE THT RUNS FROM SYSTEM (A) PRESSURE FILTER TO POWER TRANSFER UNIT WAS NOTED TO BE REPTURED. THE HOLE WAS SENT TO TEAM (X) AT ICT.SDR G0241Wire · brokenDURING TAXI, THE RT PITOT HEAT FAIL CAS MESSAGE ILLUMINATED. BROKEN GROUND WIRE AT THE RIGHT HAND PITOT TUBE. REPAIRED BROKEN GROUND WIRE. OPERATIONAL CHECK IS GOOD.SDR 2002FA0001303Tube · failedPILOTS COMPLAINT OF RT ANTI-ICE HOT MESSAGE WHEN SYSTEM TURNED ON. VERIFIED SENSOR AND LOGIC CARD OPERATION OK. REMOVED RT LEADING EDGE AND FOUND MAIN TUBE HAD BURST WITH A 2.5 X .375 INCH HOLE, BLOWING AWAY INSULATION AROUND ASSEMBLY. THIS WAS JUST INBOARD OFSDR UG8A235JActuator · faultyDURING CLIMB-OUT OF DTW, THE RUDDER LIMIT FAIL AT 24 PERCENT AMBER CAS MESSAGE ILLUMINATED. ALSO,THE PITOT HEATER FAIL SB AMBER CAS MESSAGE ILLUMINATED. REPLACED FAULTY LINEAR ACTUATOR. REPLACED FAULTY LOGIC MODULE. (M)SDR UG82002F00011Display · malfunctionedAFTER TAXIING FROM RAMP, RETURNED TO PARKING RAMP WITH EICAS YELLOW CAUTION MESSAGE FOR THE NR 5 COCKPIT DISPLAY UNIT. MESSAGE CREATED IN WRAP AROUND CIRCUIT BETWEEN THE NR 1 AND NR 5 DISPLAY UNITS. CYCLED AVIONICS MASTER SWITCH OFF THEN BACK ON. SYSTEM OPESDR DXT2002F00004Manifold · inoperativeAFTER 1.5 HOURS AT FL430, WHILE DESCENDING THROUGH FL180 AT 240 KNOTS, THE CREW HEARD A LOUD RUSHING NOISE FROM FRONT OF THE AIRCRAFT AND THE NOSE GEAR LIGHT CAME ON FOR 2 SECONDS. THE LIGHT THEN WENT OUT, THE NOISE STOPPED AND THE GEAR LOWERED NORMALLY IN TSDR 2002F00927Wire · damagedBWG - FLT 436 - AMBER ANTI-SKID FAIL MESSAGE ILLUMINATED ON START UP AND WOULD NOT EXTINGUISH. DAMAGED ANTI-SKID WIRING ON RIGHT MLG. THE WIRING WAS REPAIRED PER CESSNA CITATION X MAINTENANCE MANUAL PROCEDURES, THE SYSTEM TESTED AND THE AIRCRAFT DISCREPANCY SDR 2002F00933Control Valve · failedDESCENDING THROUGH 18,000 FEET LIGHT THUMP AND LANDING GEAR UNLOCK LIGHT ILLUMINATED. THIS HAPPENED TWICE MORE AT 10,000 FEET AND 6,000 FEET. AIRCRAFT LANDED WITHOUT INCIDENT IN PBI. MAINTENANCE REMOVED AND REPLACED LANDING GEAR CONTROL VALVE AND APPROVED TSDR 2002F00969Damper · malfunctionedAMBER YAW DAMP NOT CENTERED MESSAGE ILLUMINATED DURING TAKEOFF. TAKEOFF WAS ABORTED. YAW DAMP NOT CENTERED. CREW REFERENCED AND FOLLOWED APPROVED FLIGHT MANUAL PROCEDURES ON PAGES 3-151/3-152 OF THE AFM. SYSTEM RESET WAS NORMAL. CREW CONTINUED TRIP. (M)SDR UG82002F00008Damper · misinstalledAMBER YAW DAMP NOT CENTERED, MESSAGE ILLUMINATED DURING TAKEOFF. TAKEOFF WAS ABORTED. YAW DAMPER NOT CENTERED. CREW REFERENCED AND FOLLOWED APPROVED FLIGHT MANUAL PROCEDURES OF AFM. SYSTEM RESET WAS NORMAL. CREW CONTINUED TRIP.SDR CWQ2002F00003Bushing · frozenELEVATOR FEELS ABNORMALLY STIFF. AILERON CONTROL FEELS NORMAL. CONTROL CHECKS NORMAL. ELEVATOR FEELS SIMILAR TO MANUAL REVISION MADE IN SIMULATOR. TROUBLESHOOT ELEVATOR SYSTEM. FOUND COPILOT PUSH/PULL TUBE AFT/BELOW COCKPIT PEDESTAL, BUSHINGS FROZE, REPLASDR 2002F00988Pump · failedYNG - AMBER RIGHT HYDRAULIC PUMP FAIL MESSAGE ILLUMINATED WHEN THRUST REVERSERS WERE DEPLOYED WHILE LANDING AT YNG. RIGHT ENGINE DRIVEN HYDRAULIC PUMP FAILED. REPLACED RIGHT ENGINE DRIVEN HYDRAULIC PUMP. OPERATIONAL CHECK OF THE NEW PUMP WAS GOOD AND THE AISDR 2002F00973Warning System · activatedYNG - 118 - AMBER RIGHT HYDRAULIC PUMP FAIL MESSAGE ILLUMINATED WHEN THRUST REVERSERS WERE DEPLOYED WHILE LANDING AT YNG. TROUBLE SHOOTING IN PROGRESS. (M)SDR UG82002F00005Computer · malfunctionedPITCH FEEL FAIL LIGHT CAME ON, COULD NOT EXTINGUISH. SYSTEM LOCKUP. RESET PITCH FEEL SYSTEM, CLEARED EICAS FAIL MESSAGE. OPERATION RETURNED TO NORMAL.SDR UG82002F00004Start Valve · stuckRT ENGINE START VALVE OPEN LIGHT REMAINED ILLUMINATED AFTER ENGINE START. START REGULATOR VALVE FOR RT ENGINE, FAILED. REPLACED AND OPERATIONALLY CHECKED RIGHT ENGINE START REGULATOR VALVE PER MFG MM.SDR CNQ2002F00001Tube · corrodedWHEN THE AUXILIARY POWER UNIT FIRE EXTINGUISHER DEPLOYMENT TUBE WAS REMOVED FOR MAINTENANCE, TECHNICIANS FOUND APPROXIMATELY THREE INCHES OF WATER IN THE VERTICALLY MOUNTED TUBE. MINOR CORROSION WAS REMOVED BEFORE REINSTALLING THE TUBE.SDR UG82002F00001Actuator · stickingUPPER RUDDER CHANNEL (B) FAILED DURING PREFLIGHT. FOUND UPPER RUDDER ACTUATOR INTERMITTENTLY STICKING. REMOVED AND REPLACED UPPER RUDDER ACTUATOR. OPERATIONAL CHECK IS GOOD. AIRCRAFT RELEASED FOR FLIGHT.SDR UG82002F00003B-Nut · looseTOTAL LOSS OF (A) HYDRAULIC SYSTEM FLUID. B-NUT ON LINE ASSEMBLY LOOSENED AND BACKED OFF DUE TO INCORPORATION OF SB. FURTHER INSTALLATIONS OF THIS BULLETIN HAVE BEEN TEMPORARILY TERMINATED BY MFG. SECURED B-NUT, SERVICED (A) HYDRAULIC SYSTEM. SERVICED EMESDR 2002FA0000662Magnetic Seal · wornCREW RECEIVED ENGINE CHIP-L CAS MESSAGE. AIRCRAFT LANDED AT DESTINATION. MAGNETIC INDICATOR PLUG INSPECTED AND SINGLE SLIVER FOUND. 3RD INCIDENT OF THIS NATURE ON THIS ENGINE. ANALYSIS BY ROLL-ROYCE ON 2ND INCIDENT SLIVER SHOWED STAINLESS 410 ALLOY. FOUND WAVESDR UG82002F00002Engine · out of toleranceRIGHT ENGINE OIL PRESSURE OUT OF LIMITS, HI/RED 106 PSI AT 80-90 KTS. ENGINE INTERNAL BEARING SEAL AIR LEAKAGE WHICH MAY OCCUR AS ENGINE APPROACHES ITS MIDLIFE INSPECTION. VISUALLY INSPECTED ENGINE OIL FILTER BYPASS BUTTON. PERFORMED TAKEOFF POWER RUN UP. SDR CA020429001Bracket · cracked(CAN) COMPLIED WITH CESSNA CUSTOMER LETTER NO 0423 DATED APRIL 23, 02. (INSPECTION OF LT AND RT ELEVATOR INBD HINGE BRACKETS) ONE BRACKET HAS TWO SURFACES: INBD AND OUTB.FOUND LEFT ELEVATOR INBD HINGE BRACKET CRACKED. INBD CRACK DIMENSION :. 062 INCH OUTB CRASDR CA020422002Shaft · damaged(CAN) DURING INSPECTION OF THE LPT ASSEMBLY IT WAS DISCOVERED THAT THE LPT SHAFT HAD A SEVERE RUB AND HEAT DISCOLORATION ON THE OUTSIDE DIAMETER, LOCATED IN THE AREA OF THE HPT SLEEVE ALSO RUBBED AT FOUR LOCATION. THE SLEEVE IS ASSEMBLED INSIDE THE HPT SHAFTSDR CA020607001Hinge Bracket · cracked(CAN) A CRACK OF 0.30 INCHES WAS FOUND IN THE INBOARD SIDE OF THE HINGE BRACKET LOCATED IN THE FORWARD FROM THE TRAILING EDGE UNDER STIFFENER.SDR 2002FA0000363Duct · out of positionLEADING EDGES REMOVED FOR INSPECTION IT WAS DISCOVERED THE BLEED AIR TUBE IN BOTH SIDES, P/N UNAVAILABLE, HAD MIGRATED OUTBOARD. THE RETAINING SHEET METAL DIFFUSER WAS GOUGING INTO THE WELDED -T-.SDR 2002F00899Module · failedEN ROUTE TO THE US FROM MKJS THE A/C EXPERIENCED AN UNCOMMANDED EXTENSION OF THE L/G AT FL410, .89 MACH. THE L/G REMAINED EXTENDED FOR APPROX 1 MINUTE AND THEN RETRACTED. SEVERAL MINUTES LATER THE L/G EXTENDED AGAIN UNTIL DESCENT TO FL230, 210 KIAS WHEN THE SDR DXT2002F00002Generator · inoperativeDC GENERATOR BEARING MESSAGE ILLUMINATED. COUNTERSUNK SCREW HOLES ENLONGATED ON MOUNTING SIDE FLANGE CAUSING WEAR ON GENERATOR AND QD PAD.SDR DXT2002F00001Pin · loosePIN THAT SECURES PILOTS INBOARD BRAKE PEDAL INBOARD PIN TO BRAKE ACTUATING ROD CLEVIS IS WORKING LOOSE. THE PIN WAS FOUND PROTRUDING FROM CLEVIS. PIN LOOSE ENOUGH TO BE REMOVED BY HAND. RECOMMEND REPLACE PIN WITH LOCKING DEVICE. IE: A BOLT WITH CASTLE NUT SDR DXT2002F00000Tube · chafedDURING ROUTINE INSPECTION RIGHT FUEL SUPPLY TUBE ASSEMBLY WAS FOUND TO BE NEARLY 100 PERCENT CHAFFED THROUGH BY THE RIGHT ELEVATOR CABLE JUST FORWARD OF THE RIGHT BATTERY. MAINTENANCE REMOVED AND REPLACED THE FUEL SUPPLY TUBE ASSEMBLY WITH A NEW ASSEMBLY. MSDR 2002F00984Proximity Switch · faultyPSP - MAIN CABIN DOOR WARNING LIGHT WOULD NOT EXTINGUISHED WHEN CLOSED. FAULTY DOOR HANDLE PROXIMITY SWITCH. PROBLEM WAS CORRECTED BY REPLACEMENT OF THE SWITCH. OPERATIONAL CHECK OF SYSTEM WAS GOOD IAW 750 MM CHAPTER 52-70-00. (M)SDR CWQ2002F00000Transorb · burnedDISPLAY UNITS 4 AND 5, FMS 2 SCREEN AND RADIO CONTROL UNIT SCREEN BLANK. AVIONICS FAN INSPECTION AND CAS MESSAGES DISPLAYED. CAUSE OF DISCREPENCY APPEARS TO BE TRANSORB (PN S3106-5) WIRED INTO QUICK DISCONNECT FITTING CONNECTED TO THE RIGHT SIDE AVIONICS RELSDR 2002FA0000092Tie Rod · stiffDURING INSPECTION AND PERFORMANCE, BEARING ROD END LUBRICATION, P/N 676033215 TIE ROD, INTERCONNECTING THE TWO OUTBOARD ELEVATOR BELLCRANKS, WAS FOUND TIGHT AND NOT ABLE TO ROTATE SLIGHTLY ABOUT ITS LONGITUDINAL AXIS. IT WAS DISCOVERED THAT THE ROD ENDS, WHISDR UG82001F00011Seal · damagedHORIZONTAL STABILIZER TRIM ACTUATOR TEFLON SEAL ON JACKSCREW DAMAGED AND PROTRUDING. FOUND DURING SCHEDULED LUBRICATION CALL OUT. REPLACED WITH SERVICEABLE UNIT.(K)SDR CNQ2001F00000Sensor · intermittentTHE LEFT ENGINE OIL PRESSURE DROPPED IN FLIGHT. TROUBLESHOT TO AN INTERMITTENT OIL PRESSURE SENSOR. REMOVED AND REPLACED THE SENSOR.SDR UG82001F00010Switch · bentDOOR LIGHT WONT EXTINGUISH. MALFUNCTION OF CABIN DOOR WARNING SYSTEM. STRAIGHTENED FORWARD LOWER DOOR SWITCH PLUNGER, OPS CHECK NORMAL.SDR UG82001F00009Power Unit · failedVIBRATION FELT ON CABIN FLOOR AS WELL AS HUM. LT HYD (A) SYSTEM FLUCTUATED BETWEEN 2400-3300 PSI. WHEN GEAR WAS SELECTED DOWN LT HYD PRES WAS 2100 AND RT HAD AN OT (AMBER) LIGHT. UPON LANDING THEY GOT A (B) SYSTEM FAIL MESSAGE, BOTH SYSTEM PRESSURES WERE 180SDR UG82001F00008Hydraulic System · malfunctionedVIBRATION FELT ON CABIN FLOOR AS WELL AS HUM. LEFT HYDRAULIC (A) SYSTEM FLUCTUATED BETWEEN 2400-3300 PSI. WHEN GEAR WAS SELECTED DOWN LEFT HYDRAULIC PRESSURE WAS 2100 AND RIGHT HAD AN OT(AMBER) LIGHT. UPON LANDING THEY GOT A (B) SYSTEM FALL MESSAGE, BOTH SYSSDR UG82001F00005Module · failedPRIOR TO TAXI THE CREW NOTED AND AMBER CONFIG MISMATCH CAS MESSAGE. FAILED NR 2 CONFIGURATION MODULE. REPLACED NR 2 CONFIGURATION MODULE PER AMM. OPERATIONAL CHECK IS GOOD.SDR UG82001F00002Power Unit · failedPROBLEM ENCOUNTERED: FLAPS FAILED. FLAP SYSTEM COMPONENT FAILURE. REPLACED FLAP POWER DRIVE UNIT, OPS CHECKED NORMAL.SDR 2001F00361Strut · lowDTW - AFTER TAKEOFF AND UPON LANDING GEAR RETRACTION THE NOSE GAR FAILED TO RETRACT. NLG STRUT LOWER CHAMBER NITROGEN PRESSURE LOW. SERVICED STRUT PER CESSNA MM. (M)SDR 2001FA0000342Acm · seizedFORWARD AIR CYCLE MACHINE SEIZED DURING ROUTINE USAGE. PROBABLE CAUSE IS BEARING FAILURE. UNIT WAS OPERATED NORMALLY, AND WAS SERVICED AS SCHEDULED.SDR UG82001F00001Transducer · defectiveNO A SYSTEM HYDRAULIC PRESSURE INDICATION. INDICATION SYSTEM FAULT. REMOVED AND REPLACED TRANSDUCER, INDICATION NORMALSDR 2001F00330O-Ring · damagedIND - PILOT WALKAROUND PRIOR TO DEPARTURE, TWO HYD PUDDLES UNDER TAIL OF A/C. 'A' HYD SYSTEM INDICATES 25 PERCENT. APPEARS TO BE COMING FROM ELEVATOR. REPLACED O-RING UNDER HYD FITTING (PRESSURE) ON RIGHT INBOARD PCU. (M)
Back to Textron 750