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 engine_model_key = 'CT581401' 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 engine_model_key = 'CT581401' 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 CA990818001Link · cracked(CAN) PART WAS NEW AT PREVIOUS OVERHAUL OF ROTOR HEAD ASSY, HOWEVER, DISASSEMBLY REVEALED THAT A 0.125 INCH CRACK AT THE PIN BORE EDGE FOUND DURING NDT INSPECTION.SDR CA990224002Clutch · failed(CAN) HELICOPTER DROPPED LOGS OFF AT LANDING THEN HEADED UP HILL AT 70 PERCENT TORQUE. PILOT NOTICED NR 1 ENGINE HAD LOW POWER OUTPUT, LOW TORQUE, LOW N1, LOW FUEL PRESSURE. FAN SPEED ON NR 1 ENGINE WAS 107 PERCENT AND NR 2 ENGINE WAS AT 100 PERCENT. AIRCSDR CA991007061Fuel Filter · clogged(CAN) FUEL FILTERS BLOCKED WITH ALLUMINUM, FROM PURIFIER WEAR.SDR CA990719002Engine · failed(CAN) ENGINE FLAMED OUT WHILE HOVERING. ROTORCRAFT RETURNED TO MAINTENANCE BASE USING REMAINING ENGINE. ENGINE CHANGED.SDR CA990927027Blade · low pressure(CAN) MAIN ROTOR BLADE BIM INDICATION IN COCKPIT. LOW PRESSUREON BIM TEST.SDR CA981123004Gear · cracked(CAN) ON POST-FLIGHT INSPECTION, CRACK FOUND ON LOWER FLANGE OF THE MAIN GEARBOX RING GEAR.SDR CA981022002Blade · malfunctioned(CAN) M/R BLADE BIM INDICATION IN-FLIGHT. BLADE REMOVED AND SENT FOR TESTING IAW S61 MAINT MANUAL. SPAR PRESSURE TESTED FOR 10 DAYS. BLADE RETURNED TO SERVICE. 70 FLIGHT HOURS LATER, SAME INDICATION RECURRED.SDR CA981022001Blade · cracked(CAN) M/R BLADE BIM CAUTION LIGHT ACTIVATED. BLADE REMOVED, TESTED SERVICEABLE ON PRESSURE TEST IAW S61 MAINT MANUAL. 5 HOURS AFTER REINSTALL, ANOTHER BIM INDICATION. BLADE SENT TO SIKORSKY WHERE IT FAILED SIKORSKY'S TEST. TEST INDICATED A CRACKED SPAR.SDR CA981125041Driveshaft · failed(CAN) SEVERE HIGH FREQUENCY VIBRATION IN THE CABIN AT THE NR 3 TAIL ROTOR DRIVE SHAFT AREA. THIS SHAFT HAD BEEN STRAIGHTENED ON THE LAST REPAIR.SDR CA980818016Wire · misinstalled(CAN) MAIN ROTOR BLADE B.I.M. TRANSDUCER TEST IN COCKPIT OK BUT ALL 5 M/R BLADE TRANSDUCERS DID NOT TEST. WIRES CROSSED AT TERMINAL STRIP 46.SDR CA970421045Seal · cut(CAN) FUEL LEAKING FROM NR 1 ENG FUEL PURIFIER. "O" RING CUT IN TWO PLACES, POSSIBLY DONE ON INSTALLATION, REPLACED.SDR CA971231003Engine · malfunction(CAN) 73 HOURS AFTER INSTALLATION, NR 1 ENGINE BEGAN TO VENT OIL. OIL FLUSHED THREE TIMES. VENTING IMPROVED EACH TIME. WHILE WORKING ON ENGINE OIL PROBLEM, NR 1 ENGINE BEGAN TO SHOW OIL PRESSURE FLUCTUATIONS. DURING THE LAST FLIGHT, FUEL PRESSURE AND NG FLSDR CA971113034Fcu · failed(CAN) NR 2 ENG FAILED TO RESPOND TO THE POWER DEMAND. EMERGENCY THROTTLE WAS USED AND ENGINE RESPONDED. FCU REPLACED.SDR 97ZZZX4865Actuator · malfunctionedENGINE WOULD BEEP UP, BUT NOT DOWN. EMERG SYS WORKED AS REQUIRED. FOUND THE SYS WOULD APPEAR TO WORK NORMALLY ON THE GROUND, BUT WOULD FAIL DURING RAPID CLTV INPUTS. EVEN THE EMERGENCY SYSTEM FAILED TO BREAK IT FREE. TAPPING THE UNIT WITH A SCREW DRIVER 'BSDR CA971113033B-Nut · misinstalled(CAN) ENGINE WOULD NOT ACCELERATE AFTER DESCENT WITH SLING LOAD EMERGENCY THROTTLE USED FOR LANDING. T2 HARD LINE B-NUT AT THE COMPRESSOR DISCHARGE FOUND CROSS THREADED. BELLOWS HAD ALL FOUR SCREWS LOOSE. B-NUT PROPERLY INSTALLED AND SCREWS TIGHTENED.SDR CA970722005Bolt · broken(CAN) ON LOGGING CYCLE TRANSMISSION 'CHIP' LIGHT ON. DISASSEMBLY OF TRANSMISSION REVEALED A SAFETY WIRED BOLT HAD BROKEN AT THE HEAD AND CONTACTED INTERNAL GEARS. BOLTS NOT NORMALLY INSPECTED.SDR CA970709001Blade · damaged(CAN) AIRCRAFT FLEW THROUGH HAIL STORM WHICH PEELED BACK TRAILING EDGE OF TAIL ROTOR BLADES. ALL FIVE BLADES DAMAGED. TWO SUBSTANIALLY DAMAGED.SDR CA970528014Gear · broken(CAN) PIECE OF BEVEL GEARBOX FOUND ON FORWARD ACCESSORY GEARBOX CHIP DETECTOR AT PI CHECK, .250 INCH LONG BY .083 INCH WIDE. TWO TEETH FOUND MISSING ON MAIN GEAR, 1 TOOTH APART.SDR CA970311054Oil Cooler · leaking(CAN) LEAKING FUEL FROM UPPER AFT CENTRE WELD SEAM.SDR CA970311069Blade · cracked(CAN) T/R BLADE SKIN WAS FOUND CRACKED NEAR THE BLADE ROOT.SDR CA970311012Fuel Contrl Unit · failed(CAN) ENGINE WILL NOT TOP. CANNOT OBTAIN ACCEPTABLE TORQUE. TAKE OVER MANUAL SPEED LEVER AND ENGINE IS NORMAL. PART TC: 1.SDR CA970311010Fuel Contrl Unit · failed(CAN) ENGINE WILL NOT MEET MINIMUM ACCEPTABLE TORQUE. LOW POWER, LOW T5, HIGH NG. NO CHANGE ON MANUAL THROTTLE. PART TC: 29.SDR CA961007004Oil Jet · obstructed(CAN) DURING GROUND RUN FOLLOWING ENGINE INSTALLATION, IT WAS OBSERVED THAT NR 2 ENGINE OIL PRESSURE WAS HIGHER THAN NORMAL (60 VICE 45 PSI). ENGINE REMOVED AND A PIECE OF O-RING WAS FOUND OBSTRUCTING NR 1 OIL JET. ENGINE INSTALLED AND GROUND RUN NORMAL.SDR CA960712105Adapter · cracked(CAN) DURING EDDY CURRENT INSPECTION (MIZ-20A) OF #5 SYNCH SHAFT ADAPTER AS PER BV AD82-11-05, A CRACK IN THE KEY SLOT WAS DETECTED. A SUBSEQUENT DYE PENETRANT INSPECTION REVEALED NO FURTHER CONFIRMATION OF SUSPECTED CRACK. COMPONENT WAS REMOVED FROM AIRCRAFT SDR CA960614004Bearing · loose(CAN) THE TEFLON LINING ON THE INNER RACE OF THE BEARING IS BREAKING OUT ALLOWING EXCESSIVE PLAY OF THE BEARING.SDR CA960313001Hydraulic Pump · bearing failed(CAN)IN FLIGHT, THE CYCLIC CONTROL STARTED GETTING STIFF, ACCOMPANIED BY A GROWLING NOISE FROM MAIN GEARBOX AREA. AFTER HYDRAULIC PUMP WAS REMOVED IT WAS FOUND THAT A BEARING HAD FAILED. NOTE THIS PUMP HASHAD A PREVIOUS HISTORY OF PREMATURE FAILURE.SDR 96ZZZX269Bearing · failedTHE ENGINE LOST FUEL AND OIL PRESSURE IN-FLIGHT AND QUIT. THE ACCESSORY DRIVE GEARBOX PINION SHAFT BEARINGS FAILED AND ALLOWED GEAR DISSENGAGEMENT TO FAILURE POINT. SUBMITTER RECOMMENDS REPLACING BEARINGS AT 3,600 HOURS TT.
Back to GE CT58-140-1