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 = '208' 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 = '208' 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 CA130516010Support Bracket · cracked(CAN) FLAP ACTUATOR BRACKET ASSY FOUND CRACKED AT LIGHTING RELIEF HOLES AND ACROSS DOUBLER, FROM FLANGE TO LIGHTING HOLE DURING PHASE INSPECTION. SERVICE KIT SK208-158 INSTALLED TO RECTIFY PROBLEM.SDR 2013FA0000277Terminal · looseDISCOVERED LOOSE TERMINAL CONNECTION ON FLAP LIMIT SWITCHES.SDR CA121115008Transistor · shorted(CAN) THE KC 192 IS PART OF THE KFC 150 AUTOPILOT SYS. Q211 IN THE KC 192 AP COMPUTER APPLIES 28VDC TO THE CLUTCH ENGAGE SOLENOIDS IN THE PITCH AND ROLL SERVOS WHEN THE AUTOPILOT IS ENGAGED. A SHORTED Q211 WILL CAUSE THE PITCH AND ROLL SERVO CLUTCHES TO REMAISDR CA121109004Mount · cracked(CAN) RT ENGINE MOUNT BRACKET FOUND TO BE CRACKED AT THE FWD ENDS OF REINFORCEMENT GUSSETS ACROSS WELD AREAS.SDR 2012FA0000703Sleeve · deformedENGINE LOST ABILITY TO GOVERN THE PROPELLER RPM DRIVING THE PROPELLER TO FEATHER. LOSS OF PROPELLER RPM LED TO A NO-POWER SITUATION REQUIRING A NO POWER GLIDING APPROACH BACK TO DEPARTURE AIRFIELD. TROUBLESHOOTING FOUND THE PROBLEM TO BE A ROTATED PROPELLER SSDR CA120925002Skin · cracked(CAN) CRACK FOUND UNDER ACTUATOR ATTACH BRACKET, EXTENDING BETWEEN AND EXTENDING BEYOND ATTACHMENT BOLT HOLES. CRACK WAS ON THE ELEVATOR TRIM TAB SKIN.SDR CA120830006Wire · short(CAN) THE CUSTOMER REPORTED THAT THE AUTOPILOT WOULD NOT ENGAGE. THE KC 140 AUTOPILOT COMPUTER WAS PREVIOUSLY REMOVED AND Q211 SERVO CLUTCH ENGAGE TRANSISTOR WAS REPLACED. PRIOR TO INSTALLATION OF THE AP COMPUTER, THE WIRING CONTINUITY WAS CHECKED FOR SHORTSSDR 2012FA0000591Blade · damagedPILOT REPORTED INFLIGHT ENGINE SHUTDOWN DUE TO LOSS OF POWER DURING CLIMB AT 5,000 FEET ALTITUDE. AIRCRAFT LANDED SAFELY. ALL ENGINE INDICATION INDICATES NORMAL DURING TAKEOFF AND CLIMB UP TO 5,000 FEET ALTITUDE. MECHANIC ON DUTY, PERFORMED ENGINE BOROSCOPE SDR CA120626016Fitting · cracked(CAN) WHEN COMPLETING A PHASE 5 INSPECTION WING AREA, IT WAS NOTICED THAT THE AFT PORTION OF THE UPPER STRUT FITTING WAS CRACKED. THE FITTING EAR WAS CRACKED WITH ONLY ABOUT A .2500 INCH OF MATERIAL LEFT. THE CRACKED STRUT HAS AN INTERVAL OF 10,000 HRS FOR EDSDR CA120523017Relief Valve · failed(CAN) CHECK NUT LOOSENS ON VALVE ASSY CAUSING VALVE TO DISSASSEMBLE. VALVE DISSASSEMBLES AT VARYING TIMES IN SERVICE RANGING FROM 16 HRS THROUGH 82 HRS.SDR CA120222003Plate · cracked(CAN) RT WING PITOT TUBE FOUND TO BE CRACKED FORWARD OF ITS MOUNTING PLATE.SDR CA120218002Seal · leaking(CAN) ENGINE TORQUE WOULD NOT STAY AT 1865 RPM, ENGINE REMOVED FOR SHOP VISIT SUSPECT LEAK BY TORQUE SHAFT SEAL.SDR CA120127012Pulley · damaged(CAN) DURING PRE-FLIGHT CHECK THE ELEVATOR WAS STUCK IN TAKEOFF POSITION AND REQUIRED CONSIDERABLE FORCE TO MOVE TO NEUTRAL POSITION. INSPECTION REVEALED THAT THE PULLEY ON THE PITCH SERVO MOUNT CABLE ATTACH POINT WAS DAMAGED, THEREBY ALLOWING THE CABLE ATTACSDR BSYA2011036Regulator · failedAFTER DEPARTING BHM THE PILOT'S TURN-COORDINATOR FAILED AND THE STBY ALTERNATOR FAIL LIGHT CAME ON, DIVERTED BACK TO BHM. REMOVED AND REPLACED BOTH TURN-COORDINATOR AND STBY VOLT REGULATOR. OPS CHECKED GOOD. STBY ALT REG.SDR RJWR20111130003Bungee · seizedDURING PREFLIGHT PILOT WAS UNABLE TO MOVE RUDDER, FOUND NOSE STEERING BUNGEE/SPRING ASSY SEIZED. REPLACED ASSY AND FUNCTIONAL CHECKED GOOD.SDR CA111030002Engine · malfunctioned(CAN) DURING LANDING ROLL, THE ACFT DEPARTED THE SIDE OF THE RUNWAY RT AND CAME TO A STOP 10 METERS FROM THE RUNWAY EDGE WITH THE NOSE GEAR COLLAPSED. THERE WERE NO INJURIES, AND THE ENGINE WAS ORIGINALLY BELIEVED TO BE A NON CONTRIBUTOR TO THIS EVENT. HOWEVESDR CA110822014Gps · burned(CAN) ON T/O, CREW NOTICED A HOT ODOR AND ABORTED TAKEOFF. NO SMOKE WAS OBSERVED BY THE FLIGHT CREW. INVESTIGATION REVEALED THE GPS UNIT SMELLED HOT OR BURNING ODOR AND WAS REPLACED WITH ANOTHER UNIT. THE AFFECTED UNIT WAS SENT OUT FOR INVESTIGATION AND REPSDR CA110617002Plunger · out of adjustPILOT REPORTED THE CARGO DOOR OPEN INDICATION ILLUMINATED IN FLIGHT. THE DOOR DID NOT OPEN. NO PASSENGERS, CARGO BARRIER WAS INSTALLED. ON LANDING CONFIRMED THAT THE HANDLE WAS DOWN IN OPEN POSITION. LAB AIR WAS CALLED TO INVESTIGATE AND MAKE REPAIRS. REF ASDR CA110611001B-Nut · brokenTHE ACFT LANDED AND WAS PROCEEDING DOWN THE RUNWAY NORMALLY UNTIL THE PILOT APPLIED THE BRAKES IN PREPARATION FOR LT TURN ONTO TAXIWAY, THE ACFT STARTED TURNING TO THE LT AND PROCEEDED OFF THE RUNWAY AND DOWN AN EMBANKMENT JUST BEFORE THE TAXIWAY TURNOFF. THESDR HSYA2011042511Tire · failedDURING LANDING ROLL OUT, THE NOSE WHEEL TIRE ASSY HAD VIBRATION AT APPROX 60 KNOTS AND GOT WORSE AS ACFT SLOWED. THE ACFT / PILOT CLEARED ACTIVE RUNWAY AND SHUTDOWN ON THE TAXIWAY. MX WAS NOTIFIED AND MEET THE ACFT. MX FOUND THE NOSE WHEEL ASSY HAD GONE FLASDR 2011F00042Spar · bentDURING PHASE 10 INSP FOUND THE HORIZ STAB FWD FACE OF THE MAIN SPAR BENT AND CRACKED IN THE CTR OF THE WEB AREA IN BETWEEN THE MAIN ATTACHMENT POINTS TO FUSELAGE STRUCTURE WITH THE STABILIZER REMOVED FROM THE ACFT TAILCONE.SDR 2011FA0000145Spar · crackedACTC=4354, DURING PHASE 10 INSP, FOUND HORIZONTAL STAB FWD SPAR BENT AND CRACKED, IN THE CENTER WEB AREA, IN BETWEEN THE FWD ATTACH POINTS. MFG CUSTOMER SERVICE AND ENGINEERING WERE CONTACTED AND SENT PHOTOS. OPERATOR SUSPECTS ACFT CLEANING PERSONNEL STANDINSDR 2010FA0001269Shaft · failedNOTICING HIGH FAILURE RATE BETWEEN SHAFT (PN 2601267-2) AND GEAR (PN 3100450-01) LESS THAN 1,000 HRS. WHEN REPLACING GEAR WITH MFG O/H GEAR, NEW SHAFT DOES NOT FIT INTO GEAR. TRIED OTHER ACFT MFG NEW AIR CONDITIONER DRIVE SHAFTS AND THEY INSTALLED WITH NO PRSDR CA100617011Hose · crackedDURING A ANNUAL INSP, A FUEL HOSE IN THE FUEL DISTRIBUTION SYS WAS FOUND TO BE CRACKED EXTERNALLY. WHEN REMOVED THE INTERIOR OF THE HOSE WAS ALSO SHOWING SIGNS OF STRESS. THE HOSE WAS MFG IN 4Q 92, ALMOST 18 YEARS OLD. HOSE REPLACED WITH NEW.SDR CA100706006Skin · crackedVERTICAL STAB SKIN CRACKED MID HEIGHT ALONG SPAR.SDR CA100706005Stringer · crackedSTRINGER, CRACKED ALONG RADIUS. PART R & R WITH NEW.SDR CA100706004Bulkhead · cracked(CAN) BULKHEAD CRACKED AT LOWER LIGHTENING HOLES.SDR CA100112003Oil Filter · failed(CAN) INNER CONE (SCREEN) SEAMS ARE BECOMING UNGLUED. (TC NR 20100112003)SDR CA091211011Attach Fitting · corroded(CAN) THE FLOATS ARE FITTED TO A ACFT. THE FWD FLYING WIRE ATTACH BRACKET WAS FOUND CORRODED. PART REPLACED WITH NEW UNIT.SDR CA100121007Coupling · broken(CAN) AFTER NORMAL FLIGHT WAS COMPLETED AND ACFT SHUTDOWN, ATTEMPT WAS MADE TO LOWER FLAPS FOR ACFT WASHING. PRIMARY FLAP MOTOR OPERATED BUT FLAPS DID NOT MOVE. UPON INSP, PRIMARY FLAP MOTOR COUPLING WAS FOUND FAILED, DISCONNECTING MOTOR FROM FLAP ACTUATOR ASSDR CA090924010Skin · corroded(CAN) WHILE AIRCRAFT WAS UNDERGOING A PHASE INSPECTION, IT WAS NOTICED SOME CORROSION POWDER AT ELEVATOR MASS BALANCE AREA. FURTHER INPECTION REVEALED MASS BALANCE WEIGHT SPAR CORRODED BEYOND REPAIR. PART WAS REPLACED WITH FACTORY NEW UNIT. ELEVATOR WAS BALANCSDR CA090804001Shaft · sheared(CAN) FCU INPUT SHAFT BEARING DISINTEGRATED AND FCU INPUT SHAFT COUPLING SHEARED. ENG LOST CONTROLLABILITY DURING TAXI OUT FOR TAKEOFF. FCU SHOWED NO PREVIOUS INDICATION OF BEARING DISTRESS ON ANY OF THE BEARING WASH OUT INSPECTIONS. LAST PREVIOUS INSP WAS 85SDR CA090730006Spring · wrong partPROP INSTALLED ON ACFT HAD PROP ZERO PITCH LATCH KIT INSTALLED IAW STC SP96-1. THE PROP HAD A HARD TIME COMING OFF LATCHES. PROP WAS DISMANTLED TO THE EXTENT NECESSARY TO DETERMINE THAT THE WRONG FLYWEIGHT SPRINGS HAD BEEN INSTALLED AT THE PREVIOUS O/H. SPRSDR BSYA2009029Fuel Control · malfunctionedAIRCRAFT EN ROUTE FROM CPS TO BHM WHEN THE ENGINE WAS FLUCTUATING 100LBS TORQUE IN CLIMB IN TURBULENCE, THEN IN CRUISE IN SMOOTH AIR TORQUE DROPPED 400LBS PILOT THEN ELECTED TO LAND AT MWA. REMOVED AND REPLACED FUEL CONTROL, OPS CHECKS GOOD.SDR 2009FA0000366Turbine · failedON LANDING THE PILOT SAID HE HEARD A POP AND THE ENGINE STARTED TO SPOOL DOWN. HE PULLED OFF THE RUNWAY AND STOPPED BUT THEN SAW SMOKE COMING FROM THE EXHAUST AND THOUGHT IT WAS RESIDUAL FUEL. HE THEN MOTORED THE ENGINE AND THE SMOKE TURNED BLACK. HE CALLED SDR 2009FA0000448Check Valve · failedUPON INTERNAL INSP OF HEADER TANK FOUND SWING CHECK VALVES FRAGMENTING AND FALLING OFF PARENT MATERIAL. REPLACED ALL SWING VALVES WITH NEW AND CLEANED INTERNAL HEADER TANK. (K)SDR CA090415008Fitting · corroded(CAN) THE STRAIGHT FLOATS ARE FITTED TO ACFT. THE FWD FLYING WIRE ATTACH BRACKET WAS FOUND CORRODED. THIS ACFT HAS STAINLESS FLYING WIRES AND CLEVIS ENDS FITTED FROM THE MFG. IT APPEARS NO CORROSION PREVENTATIVE PRODUCTS WERE USED ON ASSEMBLY. THE DISSIMILAR SDR CA090407016Tube · split(CAN) ACFT WAS SITTING AT THE HANGER OVERNIGHT. IN THE MORNING THE PILOTS PREPARED THE ACFT FOR THE MORNING FLIGHT. THEY TAXIED TO THE RUNWAY AND ALIGNED THE ACFT ON RUNWAY 28 FOR DEPARTURE WHEN THE LT MAIN TIRE WENT FLAT. MX WAS CALLED AND THE TIRE REPLACED. SDR CA090310014Tube · damaged(CAN) ACFT LANDED WITH A FLAT TIRE. THE WHEEL ASSY WAS CHANGE ON THE RUNWAY. WHEN THE TIRE WAS REMOVED IT WAS DISCOVERED THAT THE BALANCE PATCHES (2) WERE LOOSE IN THE TIRE. THE PATCHES LOOKED WORN, INDICATING THAT THEY HAD BEEN LOOSE FOR SOME TIME. SUSPECT THSDR CA100202008Collar · loose(CAN) AT INSPECTION SOME COLLARS ON HIGH SHEAR RIVETS PN NAS1054-6-10 WHICH ATTACH THE STRUT SUPPORT ASSY TO THE WING SPAR WERE FOUND ABLE TO ROTATE. 4 ON LT WING AND 7 ON RT WING. THE RIVETS ARE HIGH SHEAR AND PRESSED FIT AND SHOWED NO SIGNS OF MOVEMENT. THERSDR CA081222006Filter Element · flaking(CAN) DURING INSPECTION OF OIL PRESSURE POWER ELEMENT, IT WAS NOTED THAT SMALL FLAKES APPEARED IN THE OIL SAMPLE FROM THE FILTER CASING AND THAT THE PLATINA APPEARED TO BE ABLE TO FLAKE OFF THE ELEMENT WITH FINGER NAIL PRESSURE. ELEMENT WAS REPLACED WITH NEW SDR CA081222005Wire · burned(CAN) DURING INSPECTION IT WAS FOUND THAT THE ELECTRICAL CONNECTER AND APPROX 3 INCH OF WIRE FORWARD OF THE VANISTER. IN THE PROP DE-ICE CCT WAS BURNED AND THE WIRE HAD BECOME SEPARATED FROM THE VANISTON LEAVING THE PROP DE-ICE SYSTEM IN-ACTIVE. FLIGHT CREW SDR 2008FA0000657Cowling · crackedTHE SECONDARY EXHAUST COWLING WAS FOUND TO HAVE A 5.5 INCH LONG CRACK NEXT TO THE CENTER EXHAUST HANGER ROD END BRACKET. (K)SDR CA080922003Adapter · cracked(CAN) DURING LEAK TEST AFTER CLEANING LEAKAGE NOTED AT THE HEAD FUEL NOZZLE ADAPTER.SDR CA080917004Coupling · failed(CAN) FLAP COUPLING FAILED DURING NORMAL LANDING PROCEDURES. UPON FAILING, THE PART BROKE INTO 2 PIECES, DISCONNECTING THE FLAP MOTOR FROM THE ACTUATOR ASSEMBLY. THIS RESULTED IN THE FLAPS STOPPING WHILE PARTIALLY EXTENDED. THE FLAPS WERE LEFT PARTIALLY EXTENDSDR CA080826007Indicator · defective(CAN) OIL PRESSURE NEEDLE INDICATES HIGH OIL PRESSURE WHEN ENGINE IS OPERATING (100- 105 PSI) READS OFF OF ZERO WHEN ENGINE IS NOT OPERATING (10-15 PSI) 106.5 HRS SINCE OVERHAUL.SDR 2008FA0000602Oil Cooler · crackedUPPER MOUNTING FLANGE HAS A 1.25 INCH CRACK AGAINST OIL COOLER BODY. (K)SDR CA080813008Wire · chafed(CAN) PILOT REPORTED INTERMITTENT "DE-ICE PRESSURE" ANNUNCIATOR ILLUMINATION WHEN DE-ICE WAS NOT SELECTED. ON INVESTIGATION A CHAFED WIRE WAS FOUND IN ZONE 527. THE WIRE HAD CHAFED ON THE LT CABIN ENTRY LIGHT FIXTURE CAUSING AN INTERMITTENT SHORT TO GROUND ACTSDR CA080916002Roll Pin · sheared(CAN) DURING ROUTINE INSPECTION, STANDBY FLAP SYSTEM OPS DISCOVERED INOPERATIVE (MOTOR TURNING - NO FLAP MOVEMENT). UPON FURTHER INVESTIGATION, ROLL PIN SECURING STANDBY DRIVE TO WARM GEAR WAS FOUND TO BE SHEARED RENDERING STAND BY FLAP OPS U/S. SUSPECT FAILURSDR T652008F00000Mount · damagedDURING AIRCRAFT CORROSION INSPECTION IT WAS NOTICED THAT THE AIR CONDITIONING CONDENSER DUCT CLAMP WAS CUTTING INTO THE ENGINE MOUNT ON THE LT TRUSS. THE TRUSS WAS ALSO RUBBING AGAINST THE CONDENSER DUCT. THERE ARE (4) CUTS MEASURING AS FOLLOWS: ( LENGTH 9/3
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