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 = 'UH12E' 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 = 'UH12E' 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 2022FA0000286Hub · crackedA CRACK WAS FOUND ON THE OUTSIDE OF M/R HUB ORIGINATING FROM INBOARD TT PIN HOLE. THE CRACK EXTENDS FROM THE INSIDE DIAMETER OF THE BORE TO THE OUTSIDE OF THE HUB. AFTER CLOSE EXAMINATION IT SEEMS THAT THERE ARE ROUGH MACHINING MARKS THAT CAUSED A STRESS CONCESDR BHHR20190607001Housing · crackedA CRACK WAS FOUND IN TRANSMISSION LOWER HOUSING JUST BELOW THE CYCLIC BELLCRANK BRACKET P/N 33031 MOUNTING FACE. THE CRACK WAS LOCATED IN THE AFT LOWER MOUNTING BOSS FOR THE CYCLIC BRACKET IN THE FILLET OF THE LOWER HOUSING. SEE ATTACHED PICTURES. CORRECTIVE ASDR BHHR201710030002Gear · spalledENGINE WAS REMOVED FROM SERVICE DUE TO CHIP LIGHTS AND AN AUDIBLE WHINE HEARD OVER THE RUNNING AIRCRAFT. THIS GEARBOX WAS ASSEMBLED IN-HOUSE AFTER A 3500 HOUR OVERHAUL INSPECTION OF THE GEARS WAS PERFORMED AN AUTHORIZED REPAIR FACILITY. PTO GEAR SHOWED SIGSDR BHHR201710030001Drive Gear · spalledA TEAR-DOWN INSPECTION OF A 250-C20B ENGINE GEARBOX WAS PERFORMED. THIS GEARBOX WAS REMOVED FROM SERVICE DUE TO CHIP LIGHTS AND AN AUDIBLE WHINE HEARD OVER THE RUNNING AIRCRAFT. THIS GEARBOX WAS ASSEMBLED IN-HOUSE AFTER A 3500 HOUR OVERHAUL INSPECTION OF THSDR BHHR20170201001Fork · mismanufacturedDISCOVERED THE OUTBOARD TENSION TORSION PIN BORES ARE MISALIGNED. DISCOVERED BORES NOT BEING CONCENTRIC BY MANUFACTURING A WORKAID THAT FIT INTO OUTBOARD TT PIN BORE AND MEASURED T.I.R. WITH A LAST-WORD INDICATOR.SDR 2015FA0000448Fork · crackedAFTER DETERMINING WHAT MAY HAVE CAUSED SN 11513P TO CRACK, WE CHECKED WHICH WAS UNDERGOING MAINTENANCE. WE FOUND SN 11527P TO HAVE A 1" LONG CRACK IN THE SAME PLACE. THIS CRACK STARTED AT THE TOP OF THE FORWARD TT PIN HOLE. THE CRACK LOOKS LIKE IT PROPAGATEDSDR CA120605011Crosstube · broken(CAN) FWD CROSSTUBE WAS FOUND BROKEN AT THE LT SIDE INBD BOLT HOLE UPON INSPECTION AFTER BEING TRAILERED TO A JOB SITE.SDR CA100824006Pin · brokenTENSION TORSION PIN BROKE OFF AT MAIN ROTOR HEAD WHERE DRAG BRACE ATTACHES TO PIN. ACFT WAS IN CRUISE FLIGHT PERFORMING AERIAL SPRAY APPLICATION. ACFT STARTED TO SHAKE AND VIBRATE. PILOT PERFORMED EMERGENCY LANDING IN SPRAY BLOCK ON A PREVIOUSLY CLEARED LANSDR 2010FA0000071Fork · damagedFOUND DURING AN INCOMING INSPECTION THE FOLLOWING DEFECTS ON 4EA NEW FAA PMA PARTS SN 11566P/11567P/ 11568P & 11569P AS FOLLOWS; EDGE RADIUS OF ALL FORK BLADE PIN BORES DO NOT HAVE A SUFFICIENT RADIUS TO LET BLADE ATTACHMENT PIN TO SEAT AGAINST THE TOP SURFACSDR 2009FA0000332Hub · crackedMAIN ROTOR HUB PN 51437-11 SN 20074 SHOWED SIGNS OF POSSIBLE CRACK DURING PREFLIGHT, PERFORMED DYE PENETRANT INSP, AS PRECAUTIONARY MEASURE, CRACK INDICATION PRESENT. REMOVED PART FROM FURTHER SERVICE, AND INSTALLED SERVICEABLE PART IN ITS PLACE. CRACK INDICSDR CA090220003Spar · cracked(CAN) DURING INSP IAW AWD 97-10-16 (A) CONTROL ROTOR PN 36209-3, SN 449. FOUND CRACKED AT LOWER BOLT HOLE .600 FROM END OF SPAR.SDR 2009FA0000580Blade · separatedDURING CRUISE FLIGHT, 1 OR 2 CONTROL ROTOR BLADE ASSEMBLIES SEPARATED FROM ROTOR HEAD. ROTOR CONTROL BLADE ASSY TUBE BROKE OTBD OF 2 BOLTS ATTACHING IT TO CUFF ASSY. THIS CAUSED A VIOLENT VIBRATION AND MINIMMAL CONTROL OF ACFT. LOWERED COLLECTIVE AND TRIEDSDR 2008FA0000372Retainer · mismanufacturedRETAINER SUSPECTED LOCALLY MADE INSTALLATION WORD "UP" IS NOT STAMPED ON PART BUT ETCHED ON BY HAND. THICKNESS OF RETAINER IS .045, ACTUAL PART THICKNESS OF NEW RETAINER IS .051. FOUND SHAFTS THAT ARE SHIMMED WITH BAD RETAINERS TO BE SHIMMED IMPROPERLY DUE TOSDR CA080314019Bearing · failed(CAN) CHIP LIGHTS METAL CONTAMINATION ENGINE SHOP DETERMINED NR 5 BEARING FAILURE. (TC NR 20080314019)SDR 2006FA0000900Cable · brokenLT TAIL ROTOR CABLE FAILED. OPERATOR OPERATES IN VERY DUSTY ENVIRONMENT. BUILD UP OF DUST AND OILY SUBSTANCE FROM PRODUCT FOR SPRAYING CAUSE A FINE ABRASIVE SUBSTANCE ON CABLES AT PULLEYS. CABLE NEEDS PROTECTION FROM ENVIRONMENT AND MORE FREQUENT INSPECTION ANSDR 2006FA0000427Hub · crackedM/R HUB DYE CHECK INSPECTION. HUB WAS FOUND TO BE CRACKED. RETIREMENT LIFE, 2500 HOURS. (K)SDR 2005FA0000824Mast · crackedHELICOPTER EXPERIENCED A PROGRESSIVE LATRIAL VIBRATION. SUBSEQUENT INSPECTION FOUND 2 CRACKS FROM THE PITCH PIN SLOT AREA OF THE MAST. ONE CRACK FROM THE TOP OF ONE SLOT AND ANOTHER CRACK FROM THE BOTTOM OF THE SAME SLOT PROGRESSING THE OPPOSITE DIRECTION. SDR AUS20030449Control Cable · failed(AUS) TAIL ROTOR CONTROL CABLE FAILED. CABLE RUNS FROM RT PEDAL TO FIREWALL LOCATED BEHIND THE PILOT SEAT. CABLE HAD BEEN SUBJECTEDTO HEAT SOURCE, POSSIBLY CONTACT WITH CIRCUIT BREAKER LOCATED IN CENTER TUNNEL WHEN TENSION WAS RELEASED DURING MAINTENANCE. PERSSDR AUS20020789Screw · failed(AUS) ENGINE ACCESSORY DRIVE GEAR PNO 67609 TO STARTER DRIVE GEAR PNO 67583 ATTACHMENT STUDS (6OFF) PNO STD-2208 AND DOWELS (3OFF) PNO72139 SHEARED.SDR AUS20010648Gear · failed(AUS) ENGINE DRIVE GEAR PNO 67583 HAD SHEARED ALL THE BOLTS ATTACHING IT TO ACCESSORY DRIVE PNO 67609.SDR 20010531CW001Blade · delaminatedDOUBLER DELAMINATION NO SIGNS OF CORROSION OR IMPACT WHICH MIGHT CAUSE DELAMINATION. CAUSE UNKNOWNSDR AU001151Hub · cracked(AUS) MAIN ROTOR HUB SEVERELY CRACKED IN AN AREA NOT KNOWN FOR CRACKING. FOLLOWING TAKEOFF CONTROL WAS ALMOST IMPOSSIBLE AND THE MASSIVE VIBRATION CAUSED THE FORE/AFT ENGINE MOUNT TO BE TORN FROM ITS HOUSING AND THE SHAFT TO CRACK. THE CRACK WAS OPENINGUP UNDESDR 20001113SH006Hub · crackedPRIOR TO THE INSTALLATION OF MAIN ROTOR HEAD ASSY, SN 493, AD 73-20-03 WAS ACCOMPLISHED. THE MAIN ROTOR HUB, SN 493, WAS FOUND CRACKED INSIDE THE HUB IN THE AREA OF THE CONTROL ROTOR STUDS. METHOD OF INSPECTION WAS DYE PENETRANT. THE ASSY RECORDS INDICATE TSDR AU000500Cuff · cracked(AUS) MAIN ROTOR CUFF CRACKED FROM BOLT HOLE. CRACK LENGTH 10MM (0.393IN). FOUND DURING DYE PENETRANT INSPECTION IAW AD/HIL12/17(SB 36-1).SDR 20000601SH010Blade · delaminatedBLADE WAS RETURNED TO BLADE SHOP FOR REPAIR OF SKIN TO TRAILING EDGE DISBOND. UPON INSPECTION, APPEARS THAT CLEANING AND/OR METAL PREP PROCESS FAILED CAUSING SKIN AND TRAILING EDGE TO SEPARATE. SUBMITTER RECOMMENDED INSPECTING ALL BLADES IN METAL PREP BATCH SDR 99ZZZX4550Cuff · failedCONTROL ROTOR CUFF SPLIT IN TWO AT THE INBOARD BOLT HOLE. OUTBOARD SECTION AND CONTROL ROTOR TUBE ASSEMBLY SEPARATED FROM HELICOPTER CAUSING LOSS OF CONTROL. CRACK APPEARS TO HAVE STARTED AT INBOARD BOLT HOLE. BOTH HALVES OF CUFF SENT TO NTSB LAB FOR ANALYSSDR CA991103012Oil Pump · seized(CAN) TRANSMISSION OIL PUMP HAD FAILED, FAILING TO LUBRICATE THE LOWER MAIN ROTOR TRANSMISSION RGB CAUSING IT TO SEIZE. TEAR DOWN TO FOLLOW.SDR 99ZZZX211Mount · separatedRUBBER MOUNT SEPARATION FROM MOUNTING FLANGE. RUBBER CURE DATE 11-95, MFG BY LORD. PART HAS BEEN IN SERVICE 12 MONTHS.SDR 98ZZZX3262Terminal · crackedDURING OVERHAUL NDT INSPECTION, FOUND CRACKED TERMINAL BORE. CRACK ABOUT .100 INCH INTO THE BORE AND ACROSS THE CLEVIS FACE. REF: CHI WO C7289. WORKSHEET 7-2-98 ITEM 37.SDR 98ZZZX3261Hub · crackedDURING OVERHAUL NDT INSPECTION, FOUND THE 4 CRACKS FROM THE T.T. PIN BORES.SDR CA980507004Damper Arm · fractured(CAN) A COMPLETE FRACTURE OCCURRED CAUSING THE ARM TO FAIL IN 2 PIECES. THE DAMPER ARM HOLDS A VIBRATION ABSORBING WEIGHT TO A FLIGHT CONTROL. THE FAILURE OF THE ARM DOES NOT AFFECT CONTROLLABILITY EXCEPT FOR INCREASED CYCLIC CONTROL VIBRATION, HOWEVER, THE LISDR AU971422Pin · cracked(AUS) MAIN ROTOR HEAD TENSION/TORSION PIN CRACKED.SDR 97ZZZX3544Bearing · mismanufacturedNEW REPLACEMENT BEARING RECEIVED WITH INSTRUCTIONS FROM MRC (BEARING MFG), AND HILLER SL UH12-25-1 DESCRIBING INSTALLATION INSTRUCTIONS WITH REGARDS TO THE FILING NOTCHES AND BEARING MARKINGS ON THE OUTER RACE. THESE INSTRUCTIONS ORIENT THE BEARING SO THE MAJSDR AU970991Gear · damaged(AUS) MAIN ROTOR TRANSMISSION UPPER PLANETARY RING GEAR TOOTH CHIPPED - MINOR DAMAGE TO ONE UPPER PLANETARY GEARSDR CA970716002Bolt · sheared(CAN) ENGINE FAILED IN FLIGHT. ON DISASSEMBLY IT WAS FOUND THAT THE CAMSHAFT GEAR SCREWS HAD SHEARED EXCEPT FOR ONE THAT WAS STILL INTACT, BUT LYING IN THE OIL SUMP. THE LOCKTABS WERE STILL BENT OVER. IT APPEARS THAT EITHER A LOCKTAB BROKE LETTING A BOLT COME SDR CHI1789Shaft Spline · crackedUPPER AND LOWER TRANSMISSION COUPLING SPLINE SHAFT HAS ONE SPLINE CRACKED NEAR OUTER END OF SPLINE. REPLACED CRACKED SHAFT WITH SERVICEABLE UNIT. (X)SDR 97ZZZX2037Piston Pin · defectiveAD 97-01-03 AND LYC SB 527B DO NOT REFERENCE VO540 ENGINES IN MODELS AFFECTED, BUT 4 OF 6 PISTON PINS IN ENGINE HAD TO BE REPLACED IN C/W THE SB REQUIRED ACTION. NOTE: 6-CYLINDER HELICOPTER ENGINES ARE LISTED IN WARRANTY LABOR ALLOWANCE AND A VO540 ENGINE ISSDR 97ZZZX2838Intake Valve · wornTHE VALVE STEM UNDER THE KEEPER'S WAS HEAVILY WORN. THIS CONDITION WAS ALSO FOUND ON 4 OTHER VALVES (INTAKE) ALL HAVING THE SAME TOTAL TIME AND PART NUMBER. THE 6TH VALVE WAS A LYCOMING WITH THE SAME TIME AND INSTALLATION DATE. NO PROBLEM FOUND.SDR 97ZZZX1825Valve · failedTHE HELICOPTER WAS RUNNING ROUGH SO A COMPRESSION CHECK WAS RUN. THE NR 2 CYLINDER HELD NO COMPRESSION AND WAS REMOVED FOR INSPECTION. NOTED A .1250 INCH BY .25 INCH SECTION OF THE VALVE FACE WAS MISSING. THE MISSING SECTION WAS IRREGULAR IN SHAPE AND APPEASDR 97ZZZX1680Cuff · crackedIAW AD 77-07-05(S) AND HILLER SB 36-1 REV 3, PARA 2(G). FOUND CRACK AT CONTROL BLADE CUFF INBOARD BOLT HOLE DURING 100-HOUR REPETATIVE DYE-PENETRANT INSPECTION. NOTE: 6,860 HOUR LIFE-LIMIT.SDR 97ZZZX1679Cuff · crackedIAW AD 77-07-05(S) AND HILLER SB 36-1 REV 3, PARA 2(G). FOUND CRACK AT CONTROL BLADE CUFF INBOARD BOLT HOLE DURING 100-HOUR REPETATIVE DYE-PENETRANT INSPECTION. NOTE: 6,860 HOUR LIFE-LIMIT.SDR AU970349Stud · broken(AUS) NO2 CYLINDER HOLD DOWN STUDS BROKEN - INVESTIGATION FOUND SIX CYLINDER BASE NUTS MISSING, THIRTY NUTS LOOSE AND ONLY TWELVE NUTS TO BE TIGHT - CRANKCASE PARTING SURFACES AND CYLINDER MOUNT PADS FRETTED - NUMEROUS INTERNAL WRENCHING. CYLINDER BASE NUTLANDSDR 97ZZZX1133Cylinder · not to specDURING ASSEMBLY OF ENGINE, MEASURED DRY TAPPET CLEARANCE FROM .107 INCH TO .187 INCH. LYC OHM REQUIRES .028 INCH TO .080 INCH. RETURNED 6 CYLINDERS TO EC/SW WHERE THEY CUT/REMOVED MATERIAL FROM THE CYL FLANGE. CYLINDERS WERE RE-INSTALLED. THESE CYLINDERS JSDR 97ZZZX95Driveshaft · crackedDURING POST-FLIGHT INSPECTION, PILOT FOUND 1 INCH CRACKS EMANATING FROM RIVETS THAT ATTACH BALANCE WEIGHTS TO INTERIOR TO DRIVESHAFT. SUBMITTER RECOMMENDS THIS AREA BE DYE-PENETRANT INSPECTED DURING 1800 HR INSPECTION OF DRIVESHAFT. SHAFT INSTALLED ON TURBINSDR 96ZZZX5942Hub · crackedCRACK FOUND INSIDE CONICAL SURFACE DURING PRE-FLIGHT INSPECTION. CRACKING IN THIS AREA IS COMMON.SDR 96ZZZX5941Bolt · failedIN CLIMB-OUT FROM LOG LANDING WITH EXT LOAD AT AN ALT OF APPROX 400 FEET AND 69.5 PSI TORQ, PILOT HEARD A 'BANG' FOLLOWED BY A HIGH FREQ VIBR. AFTER CHECKING ALL INST (NORMAL) PILOT JETTISONED EXT LOAD AND LONG LINE. PILOT EXECUTED A PRECAUTIONARY LANDING TOSDR 96ZZZX5940Bolt · failedIN CLIMB-OUT FROM LOG LANDING WITH EXT LOAD AT AN ALT OF APPROX 400 FEET AND 69.5 PSI TORQ, PILOT HEARD A 'BANG' FOLLOWED BY A HIGH FREQ VIBR. AFTER CHECKING ALL INST (NORMAL) PILOT JETTISONED EXT LOAD AND LONG LINE. PILOT EXECUTED A PRECAUTIONARY LANDING TOSDR 96ZZZX5154Ballast Weight · dislodgedON SEPTEMBER 12, 1996, A HILLER MODEL UH-12 ET OPERATED BY SUMMIT HELICOPTERS CRASHED, COMPLETELY DESTROYING THE HELICOPTER AND SERIOUSLY INJURING THE PILOT. THE CAUSE OF THE CRASH WAS BALLAST WEIGHT P/N 62244-15 MADE CONTACT WITH TAIL ROTOR BLADES CAUSING LOSDR AU960746Control Rotor · cracked(AUS) MAIN ROTOR HEAD CONTROL ROTOR CRACKED AT SPAR END THROUGH THE FIRST BOLT HOLE FOR APPROXIMATELY 50% OF CIRCUMFERENCE - FOUND DURING INSPECTION IAW AD/HIL12/17 AMDT4SDR 96ZZZX2945Hub · crackedHUB FOUND CRACKED INSIDE HUB AT CONTROL ROTOR TRUNNION STUD HOLE. CRACK FOUND AT 50-HOUR DYE PENETRANT INSPECTION DURING C/W AD 73-20-3. SUBMITTER STATED CRACKS IN THIS AREA OCCUR ON OCCASION.
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