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 = 'A119' 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 = 'A119' 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 CA070514019Engine · low pressure(CAN) ENGINE OIL PRESSURE WAS SEEN TO INCREASE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUE ONCE ESTABLISHED. (TC NR 20070514019)SDR PO72007F00000Bearing · inoperativeDURING A WALK AROUND INSPECTION WE NOTICED THAT ONE MAIN ROTOR DAMPER HAD A BEARING WHICH IS ROTATING AND PULLING AWAY FROM WITHIN THE ROD END. (K)SDR PO72007F00001Rod End · damagedDURING A WALK AROUND INSPECTION, NOTICED THAT ONE MAIN ROTOR DAMPER HAD A BEARING WHICH IS ROTATING WITHIN THE ROD END. ACCORDING TO THE FORM 8130-3 THIS PART HAD BEEN REPAIRED ON SEPT 7, 2006. (K)SDR U0GA113886Damper · shearedPILOT FELT VIBRATION WHEN ROTOR BRAKE WAS ENGAGED AFTER LANDING AND SHUTDOWN. POSTFLIGHT INSPECTION REVEALED THE DAMPER HAD SHEARED AT THE ROD END FLUSH WITH THE OUTER THREADED PORTION OF THE DAMPER ASSEMBLYSDR CA070314020Turbine Blades · fractured(CAN) ON LANDING FOLLOWING A TRAINING FLIGHT, THE ENGINE EMITTED A LOUD NOISE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070314020)SDR AACSDR061006BLine · maint errorAIR CONDITIONING SYSTEM STC NR SR00463DE UTILIZES RIGID FREON LINES RUNNING FORE AND AFT ON THE ENGINE DECK. AT THE FORWARD END, THESE LINES CONNECT TO FLEX LINES. AT THIS CONNECTION THE LINES WERE SWAPPED. THE CONNECTIONS ARE LOCATED RIGHT NEXT TO EACH OTHERSDR 2006FA0000435Rod End · separatedDURING DAILY INSPECTION FOUND RED BLADE MAIN ROTOR DAMPER OB ROD END HAD COME APART. BEARING HAD SEPARATED COMPLETELY FROM ROD END. (K)SDR DT12006F00000Grip · debondedGRIP FOR MAIN ROTOR BLADE IS COMPOSITE LAMINATE. DEBONDED ON LEADING EDGE. 2ND GRIP ON AIRCRAFT. AIRCRAFT IS POLICE HELICOPTER. (K)SDR 2006FA0000049Oil Cooler · crackedOIL COOLER, TRANSMISSION SIDE OF COOLER CRACKED AND SPRAYED OIL BELOW ENGINE DECK. (K)SDR U0GA106526Drive Link · misinstalledUPON PREFLIGHT, PILOT NOTICED THAT ROTATING SCISSORS LINK WAS INCORRECTLY INSTALLED.SDR RMX2005F00000Damper · leakingDAMPER HYDRAULIC FLUID COMPLETELY LEAKED OUT OF END SEAL IN A 0.1 HOUR FLIGHT. (K)SDR CA050824006Fitting · loose(CAN) ON APPROACH, THE CREW NOTED A VIBRATION/SHUDDER WITH A CORRESPONDING DECREASE IN ENGINE AND MAIN ROTOR SPEEDS AND A LOW ROTOR WARNING ANNUNCIATION. THIS CALUMNIATED IN A HARD LANDING. SUBSEQUENT INSPECTION REVEALED LOOSE PNEUMATIC FITTINGS ON THE ENGINESDR 14038052105Float · activatedDURING MAINT, TECH ATTEMPTED TO INSTALL SAFETY PIN IN RESERVOIR ASSY, FLOATS DEPLOYED. IT WAS LATER DISCOVERED THAT ELEC ACT USED TO DEPLOY FLOATS HAD BEEN PARTIALLY DEPLOYED. CHECK OF SYS REVEALED THAT ACT ONLY ENERGIZES WHILE DEPLOYMENT BUTTON IS DEPRESSED.SDR CA050329010Egu · oscillates(CAN) DURING AIRCRAFT DELIVERY FLIGHT, THE CREW REPORTED ROTOR OSCILLATION. THE ENGINE'S GOVERNING UNIT (EGU) WAS SUBSEQUENTLY REPLACED. MFG WILL MONITOR INVESTIGATION OF THE SUSPECT EGU AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.SDR HDS0315051Frame · crackedTHIS IS TO REPORT CRACKS IN THE FRAMES ON THE VERTICAL FIN, IN THE AREAS AT WL 2145.0 AND 2520.0. THESE CRACKS ARE OCCURRING APPROXIMATELY BETWEEN FS 9350.0 TO 9850.0. (SW19200508005) (K)SDR 2004FA0000748Mount · damagedAT 25 HR INSPECTION, MECH HEARD A RATTLING NOISE WHEN INSPECTING NIGHTSUN II. LENS WAS REMOVED, REFLECTION WAS REMOVED. FOUND BOTH MOUNTING PLATES (PN032452, PN 032470) REV X1 BROKEN COMPLETELY OFF AT REFLECTOR BUT STILL SCREWED TO MOUNT. ALSO, BULB SET SCRSDR 2004F00102Strap · brokenMAIN ROTOR BONDING STRAP BROKEN. THIS IS A CONSTANT PROBLEM, PORTION OF THE STRAP WHICH CONTINUES TO BREAK IS MADE OF COPPER. THIS END OF THE STRAP BOLTS TO A STAINLESS STEEL CONNECTION WHICH NEVER BREAKS. THE ENDS OF THE BONDING STRAPS SHOULD BE MADE OF A SDR BAQA090154Compass · inaccurateMAG COMPASS 20 DEGREES OFF AND DG INOPERATIVE. REPLACED WITH SERVICEABLE UNIT.SDR 2003FA0000903Bearing · dislodgedDURING INSPECTION TAIL ROTOR DRIVE SHAFT BEARING WAS FOUND WITH SEAL AND RETAINING RING DISLODGED FROM BEARING. THIS BEARING IS CHECKED BY FLIGHT CREW. THIS IS THE SECOND BEARING REPLACED IN 72.1 HOURS.SDR AUS20030027Structure · cracked(AUS) TAIL BOOM ASSEMBLY CRACKED. LIMITED INFORMATION PROVIDED.SDR AUS20021489Blade · cracked(AUS) TAIL ROTOR BLADE CRACKED. MANUFACTURER STATES THAT CRACKING IS CAUSED BY SLIPPAGE OF THE GLUE BETWEEN THE FINGER DOUBLER AND THE BLADE SKIN.SDR AUS20021488Blade · cracked(AUS) TAIL ROTOR BLADE CRACKED. MANUFACTURER STATES THAT CRACKING IS CAUSED BY SLIPPAGE OF THE GLUE BETWEEN THE FINGER DOUBLER AND THE BLADE SKIN.SDR AUS20021487Blade · cracked(AUS) TAIL ROTOR BLADE CRACKED. MANUFACTURER STATES THAT CRACKING IS CAUSED BY SLIPPAGE OF THE GLUE BETWEEN THE FINGER DOUBLER AND THE BLADE SKIN.SDR AUS20021486Blade · cracked(AUS) TAIL ROTOR BLADE CRACKED. MANUFACTURER STATES THAT CRACKING IS CAUSED BY SLIPPAGE OF THE GLUE BETWEEN THE FINGER DOUBLER AND THE BLADE SKIN.SDR AUS20020905Blade · damaged(AUS) TAIL ROTOR BLADE PAINT CRACKED.SDR AUS20020058Wire · chafed(AUS) FIRE DETECTOR WIRING CHAFED IN INTAKE AREA ON LT SIDE OF ENGINE DECK.SDR AUS20011388Fuel Control · contaminated(AUS) FUEL CONTROL UNIT CONTAMINATED WITH BRONZE PARTICLES.SDR AUS20011164Structure · cracked(AUS) TAIL BOOM CRACKED.SDR AUS20011109Blade · cracked(AUS) TAIL ROTOR BLADE CRACKED IN AREA OF DOUBLER WHERE THE FINGERS ARE BLENDED INTO THE BLADE SKIN. CRACKS FOUND USING THE NAKED EYE AND CONFIRMED USING DYE PENETRANT INSPECTION.SDR AUS20010864Blade · cracked(AUS) TAIL ROTOR BLADE CRACKED ON INNER FACE. THE CRACK LENGTH RUNS FOR ALMOST THE FULL CHORD OF THE BLADE. FOUND DURING INSPECTION IAW AD/119/1 PT1.
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