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 = '206B' 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 = '206B' 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 CA090529002Governor · fluctuates(CAN) GOVERNOR FLUCTUATES.SDR CA090525003Drive Shaft · mismanufactured(CAN) AIRFRAME AND T/R VIBRATION. THE RUNOUT OF THE TAILROTOR DRIVESHAFT WAS CHECKED AND THE FINDING WAS THE FWD SPLINES ARE BONDED INTO THE T/R INCORRECTLY, THE FWD SPLINES WERE 0.040 INCHES OVER. THE T/R LONG DRIVE SHAFT WAS REPLACED AND THE ACFT WAS RETURNESDR CA090528004Bearing · worn(CAN) BEARINGS FOUND WORN.SDR CA090528003Gearbox · leaking(CAN) GEARBOX LEAKING EXCESSIVELY.SDR CA090309002Mount · corroded(CAN) DURING COMPLIANCE OF TB206-89-129 (REMOVAL OF ENGINE MOUNT LEG CLAMSHELL DAMPERS), IT WAS NOTICED AFTER THE REMOVAL OF THE CLAMSHELL DAMPERS AND THEIR PACKING MATERIAL, EXTREME CORROSION WAS FORMING UNDER THE PRIMER, WHICH WAS FOUND TO BE BEYOND LIMITS. SDR CA090217004Pump · failed(CAN) DURING NORMAL FLAT AND LEVEL CRUISE FLIGHT AT APPROX. 4000` ASL THE PILOT INITIATED A GENTLE RT TURN. UPON MOVING THE CYCLIC CONTROL THE PILOT NOTED ROUGH OPERATION AND FEEDBACK THROUGH THE CYCLIC GRIP. THE PILOT CUT HYD AND RESTORED THEM. THE CYCLIC MOSDR CA090213006Shaft · bent(CAN) TAILROTOR WAS UNABLE TO BALANCE, TROUBLESHOOTING REVEALED THE OUTPUT SHAFT WAS BENT.SDR CA090211003Support · crackedSEVERAL CRACKS DISCOVERED WHERE SUPPORT ASSEMBLY, ATTACHES TO THE FORWARD SIDE OF THE CROSS TUBE FUNNEL. ONE CRACK EXTENDS PAST THE STANDARD REPAIR AREA AS STATED IN THE SRM. OTHER CRACKS ARE OUT SIDE THE ALLOWABLE REPAIR AREA ALONG THE 90 DEGREE BEND AT THE SDR CA090202006Frame · crackedDURING 1200 HR/12 MONTH INSPECTION AFT LEFT FRAME OF ROLLOVER BULKHEAD FOUND CRACKED. CRACK IS 2.5 INCHES LONG AND IS LOCATED AT STA 130, WL 68, AND BL 26.SDR CA090123001Fan · failed(CAN) SLIGHT VIBRATION FELT THROUGH ACCELERATION DURING START TO FLIGHT IDLE RPM. OIL COOLER FAN BRGS REPLACED AND FAN BALANCED CHECKED SERVICEABLE. VIBRATION DISAPPEARED BUT WITHIN 30 FLIGHT HOURS BEGAN INCREASING IN FREQUENCY AGAIN DURING THE SPOOL UP THEN SSDR CA090123002Drive Gear · loose(CAN) THE EXPOXY HOLDING THE RETAINING CLIP IN PLACE CAME UNBONDED, ALLOWING THE CLIP TO MOVE, THERFORE ALLOWING THE DRIVE GEAR TO DISCONNECT FROM THE SHAFT.SDR CA090114005Skid · unserviceableTHE AIRCRAFT WAS BEING POSITIONED IN THE HANGER FOR MAINTENANCE. THE TAIL SKID WAS BEING USED TO STEADY THE HELICOPTER AS IT WAS BEING HOISTED TO HAVE THE LANDING GEAR REMOVED. A PORTION OF THE TAIL SKID BROKE OFF IN THE ENGINEER’S HAND. THE CAUSE OF THE BRSDR CA090121012Pump · unknownDURING ENGINE TROUBLESHOOTING A STARTING ISSUE, THE FUEL PUMP WAS REPLACED DUE TO UNDETERMINED REASONS.SDR CA090122009Support Tube · crackedDURING A FUEL CELL CHANGE (DUE TO FUEL SEEPAGE), A SMALL CRACK WAS FOUND IN THE AFT CROSSTUBE SUPPORT STRUCTURE, ON THE RT SIDE OF THE AIRCRAFT. THE LOCATION OF THE CRACK WAS AT THE FWD BOTTOM RIVET OF THE CROSSTUBE SUPPORT. THE CRACK WAS APPROXIMATELY 1/4 INSDR CA081125005Washer · cracked(CAN) THE VERTICAL FIN WAS REMOVED TO FACILITATE SEAL REPLACEMENT OF THE PITCH CHANGE MECHANISM. THE RADIUS WASHERS THAT ARE USED ON THE VERTICAL FIN ATTACHMENT WERE INSPECTED, AND IT WAS NOTED THAT 3 OF THE 4 WASHERS HAD CRACKS ON THE OUTSIDE PERIMETER OF THESDR CA090130009Clutch · malfunctionedON RUNDOWN OF HELICOPTER PILOT NOTED N2 AND M/R RPM LOCKED UP. INVESTIGATED AND FOUND CLUTCH ASSY WAS NOT DISENGAGING. REMOVED AND REPLACED WITH FREE WHEEL ASSY PN206-040-270-003 TSN 11046.6 TSO 0.0HRS. CLUTCH CL42250-1 TSN0.0 HRS. SENT DAMAGED ASSEMBLY INSDR CA081113008Tab · deformed(CAN) LOUD BANG WAS NOTED WITHING 10 MINUTES OF FLIGHT. LEVEL OF VIBRATION DID NOT INCREASE. INSP AFTER LANDING FOUND THAT THE TRIM TAB WAS DEFORMED (UPPER SIDE WAS BENT UPWARD AND LOWER SIDE BENT DOWNWARD). PEEL-PLY HAS BEEN LEFT ON THE TRIM TAB.SDR CA081009003Governor · inoperative(CAN) BENDIX KING GOVERNOR NOT RESPONDING WHEN BEEPED,SDR CA081201011Spindle · worn(CAN) TRANSMISSION MOUNTS REMOVED DUE TO BEARING WEAR. UPON FURTHER INSP, SPINDLE ALSO FOUND DAMAGED IN LOCATION OF WASHER P/N 206-030-507-001. HARD WASHER MOVEMENT DUE TO BEARING WEAR HAD WORN INTO THE RADII OF THE SPINDLE MOUNTING AREA. SPINDLE SCRAPED. SDR CA081209002Clutch · cracked(CAN) APPROX 100 HRS PRIOR TO SCHEDULED REMOVAL OF THE FREEWHEEL ASSY, METAL WAS DISCOVERED ON FREEWHEEL CHIP DETECTOR. CREW ORDERED REPLACEMENT ASSY AND MONITORED FURTHER INDICATIONS. UPON DISASSEMBLY AT THE OPERATOR`S OVERHAUL FACILITY, IT WAS NOTED THAT THESDR CA080918005Spring · broken(CAN) DURING TAKEOFF THE LOW ROTOR HORN SOUNDED. THE PILOT ABORTED THE TAKEOFF, SHUT DOWN THE ENGINE AND CALLED MX. WHEN THE ENGINE COWL WAS OPENED THE FCU THROTTLE RETURN SPRING WAS FOUND IN THE BOTTOM OF THE ENGINE PAN.SDR CA080917017Connector · misinstalled(CAN) INSTALLATION OF NEW 406 ELT ON INSTALLATION OF CONNECTOR FOR REMOTE SWITCH THE ELT WAS SET OFF. THE ELT WAS NOT FULLY INSTALLED SO THE ELT ACTIVATION WAS NOT NOTICED. HAVE SINCE SPOKE WITH THE MFG AND FOUND THAT THIS IS A COMMON PROBLEM WITH THE INSTALLASDR CA081014009Wire · chafed(CAN) PILOT TURNS ON ALL REQUIRED BREAKERS FOR FLIGHT INCLUDING NAV LIGHTS. PRE LIFT-OFF THE PILOT NOTES THE BREAKER FOR THE NAV LIGHTS AT MIDPOINT. PILOT RESETS SWITCH AND LIFTS OFF. AS THE ACFT FLIES THROUGH 300 FT, THE PILOT TURNS ON THE HEATER AND IN A FESDR CA081201010Hose · chafed(CAN) UPON ENGINE SHUTDOWN WALK-AROUND, PILOT REPORTED A TRANSMISSION OIL LEAK ON MACHINE. LEAK INSPECTED AND FOUND TO BE FROM THE MAIN HYDRAULIC PUMP HOSE. HOSE HAD CHAFED THROUGH ON A MS21919WDG CLAMP HOLDING IT DOWN TO THE TOP DECK OF A/C. WDG CLAMP SERISDR CA080822005Battery · discharged(CAN) DURING ACFT START, THE BATTERY WAS FOUND WITH NO CHARGE, BATTERY REPLACED.SDR CA080925009Starter Gen · damaged(CAN) STARTER WAS SNAGGED BY PILOT WHICH MOTORED UNDER ITS OWN POWER. EXCESSIVE ROTATION CAUSED INTERNAL DAMAGE. STARTER WAS REPLACED AND NO ISSUES WERE NOTED.SDR CA080718007Pump · dislodged(CAN) THE SEAL FOR THE TRANSMISSION OIL PUMP BECAME DISLODGED, AND LOSS OF OIL OCCURRED.SDR CA080715007Pitch Horn · damaged(CAN) THE PITCH HORN STUD FAILED WHILE INSTALLING A NUT P/N MS14145L5. A "CLICKER-TYPE" TORQUE WRENCH SET TO 60 INCH/LBS WAS USED TO INSTALL THE NUT. THE REQUIRED FINAL TORQUE FOR THIS NUT IS 50-60 INCH/LBS PLUS TARE. THE TIGHTENING TORQUE NEVER REACHED 60 INCSDR CA080822014Labyrinth Seal · leaking(CAN) DURING INSPECTION, OIL WAS FOUND POOLING IN EXHAUST COLLECTOR, SUSPECT NR 5 LAB SEAL.SDR CA080717001Governor · malfunctioned(CAN) DURING GROUND RUN THE GOVERNOR WOULD NOT MAINTAIN ENGINE RPM. REMOVED AND SERVICEABLE GOVERNOR INSTALLED.SDR 2008FA0000459Meter · malfunctionedAC MAINT HOBBS METER FOUND RUNNING SLOW. THIS PROBLEM CAUSES THE ACTUAL TT OF THE AC TO BE INCORRECT. THIS PROBLEM CAUSED THE AC TO OVER RUN INSPECTIONS, AND TIME LIFE ITEM. PROBABLE CAUSE OF THIS PROBLEM, HOBBS METERS GETTING OLD AND WORN OUT. RECOMMENDATSDR CA081209006Drive Shaft · failed(CAN) ON DESCENT PILOT SMELLED BURNING GREASE. AFTER LANDING AND POST FLIGHT INSPECTION FOUND GREASE THROWN FROM DRIVESHAFT COUPLING. DRIVESHAFT WAS REPLACED AND FOUND ISOLATION MOUNT TO BE WEAK. REPLACED ISOLATION MOUNT AND PROBLEM WENT AWAY.SDR CA080610001Lever · mismarked(CAN) MFG HAS BEEN MADE AWARE THAT A QUANTITY OF 94 LEVER ASEMBLIES HAVE BEEN MIS-IDENTIFIED AS -107 INSTEAD OF -105 AS REQUIRED BY ENGINEERING DRAWING NOTE. -105 IS A TIME LIFED COMPONENT AND GOVERNED BY MM CHAPTER 4 , -107 IS NOT.SDR CA080527002Stator · missing(CAN) COMPRESSOR ASSY WAS REMOVED FOR O/H, AT WHICH TIME IT WAS NOTED THE 6TH STAGE STATOR BAND WAS MISSING ONE BLADE, WITH IMPACT DAMAGE NOTED ON OTHER BLADES ALSO IN THE 6TH BAND. NO DAMAGE NOTED FWD OF 6 TH STAGE. BURNER CAN REMOVED AND TURBINE INSPECTED FOSDR CA080521007Clutch · malfunctioned(CAN) NOISE FROM FREEWHEEL ON SPOOLDOWN, NO INDICATIONS ON CHIP PLUG. REMOVED FREEWHEEL ASSY AND FOUND CLUTCH NOT FULLY RELEASING. REPLACED FREEWHEEL ASSY.SDR Z0A2008F00000Hydraulic Line · defectiveLOSS OF HYDRAULIC SYSTEM IN FLIGHT RESULTING IN PILOT RETURNING TO AIRPORT UNEVENTFULLY. HYDRAULIC SYSTEM HOSE WAS FOUND DEFECTIVE. (K)SDR CA080303005Fuel Control · leakingAFTER INSTALLING THE FCU, IT WAS NOTED THAT FUEL WAS LEAKING FROM LOWER THROTTLE ARM HOUSING. FCU WAS REMOVED. (TC NR 20080303005)SDR CA080227008Bearing Race · spalled(CAN) METAL WAS FOUND ON ENGINE LOWER CHIP PLUG. THE 2 1/2 BEARING IN THE GEARBOX WAS REMOVED AND FOUND THE SPALLING ON THE OUTER RACE.SDR CA080227007Bearing Race · spalledDURING FLIGHT THE PILOT HAD A CHIP LIGHT INDICATION. UPON INSPECTION, THE CHIP PLUG HAD LITTLE DEBRIS AND SMUDGE. THE CHIP WAS CLEANED, REINSTALLED AND FURTHER GROUND RUNS WHERE CARRIED OUT PRIOR TO FLIGHT. NO FURTHER ISSUES WERE NOTED AND THE FLIGHT CONTINSDR CA080821011Balance Weight · debonded(CAN) IT WAS THOUGHT THAT THE BLADE TIE DOWN WAS LEFT ON THE ACFT. THIS WAS NOT THE CASE IAW A REPORT. THE FOLLOWING OCCURRED. INSP AND SCRAPPED THE M/R BLADE DUE TO WEIGHT POCKET RETAINING HOLES DAMAGED BEYOND LIMITS. DAMAGE CAUSED BY TELL TALE LEAD COUPON (SSDR CA080215005Case Half · damaged(CAN) ON SPLITTING THE COMPRESSOR CASE HALVES FOR AN INSPECTION, IT WAS NOTED THERE WERE AREAS OF THE PLASTIC COATING THAT WERE MISSING. CASES REPLACED. (TC NR 20080215005)SDR CA080227004Frame · cracked(CAN) THE UPPER RT ATTACH POINT ON THE AIRFRAME SIDE CRACKED ON THE FRAME RING ONLY. PART REPLACED WITH NEW FROM MFG. (TC NR 20080227004)SDR CA080227005Stiffener · cracked(CAN) LT STIFFENER UNDER THE OIL COOLER HANGER BEARING CRACKED FROM FWD ANCHOR NUT WHOLE. REPLACED WITH NEW PART. (TC NR 20080227005)SDR CA080228007Skid · cracked(CAN) UPON INSTALLATION OF GROUND HANDLING WHEELS IT WAS DISCOVERED THAT THE MOUNTING LUGS ON THE FWD LT SIDE WAS DETACHED AND LOOSE DUE TO LARGE PERFORATION (HOLE) IN THE ATTACHMENT AREA. FURTHER VISUAL INSPECTION REVEALED CIRCUMFERENTIAL CRACK APPROXIMATELY SDR CA080118001Freewheel Unit · leaking(CAN) AFTER FLIGHT THE FREEWHEEL ASSY WAS DISCOVERED LEAKING FROM THE FWD HSG CAP. FREEWHEEL ASSY CHANGED, LEAK CHECK CARRIED OUT SERVICEABLE. (TC NR 20080118001)SDR CA071204001Governor · inoperative(CAN) WHILE CARRYING OUT A START, THE ENGINE WAS SLOW TO REACH IDLE, WITH THE N2 INDICATOR STICKING ON START. ONCE DESNAGGED IT WAS DISCOVERED THE GOVENOR WAS THE CAUSE.SDR CA071127006Bulkhead · cracked(CAN) AFT BULKHEAD P/N 206-030-446-001F CRACKED AT RT GEARBOX MOUNTING HOLE. (TC NR 20071127006)SDR CA071126012Bulkhead · cracked(CAN) LT AFT MOUNTING HOLE FOR T/R GEARBOX FOUND CRACKED. (TC NR 20071126012)SDR CA071120004Shim · inoperative(CAN) T/R VIBRATION DISCOVERED AND SUBSEQUENT STROBING WAS NOT EFFECTIVE AT REMOVING THE VIBRATION. DURING INSPECTION OF THE T/R HUB ASSEMBLY WAS FOUND TO HAVE BOTH PRE AND POST (TB: 206-91-139) METHODS OF TRUNNION CENTERING PERFORMED. SHIM 120-006C15-0 AND THSDR CA071030010Housing · mismanufactured(CAN) DUE TO A INTERNAL CASTING DEFECT INSIDE THE OIL FILTER HOUSING, THE PRESSURE REGULATING POPPET CANNOT FULLY BOTTOM OUT WHEN INSTALLED. THIS THEN GIVES A FALSE INDICATION OF PROPER POSITION OF THE POPPET WHEN (BACKED OUT) 5.5 TURNS FOR INITIAL ADJUSTMENT
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