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 = 'S64F' 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 = 'S64F' 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 JYDR20201013282Attach Bolt · brokenPILOTS SUDDENLY FELT A VIBRATION AND HEARD A HOWLING NOISE. THEY RETURNED TO THE LANDING SITE AND SHUT DOWN. AT INSPECTION, MAINTENANCE FOUND 1 OF 3 NAS628-15 BOLT BROKEN IN HALF ON THE NR 2 HIGH SPEED SHAFT ON THE FORWARD END, WHERE IT ATTACHES TO THE FREE SDR JYDR20201008218Engine · overtempAIRCRAFT WAS ON SHORT FINAL AT 50 FT AGL WHEN NR 1 ENGINE LOW SPEED CHIME CAME ON. PILOT NOTED DECREASING N1 RPM WITH RISING T% (ROLLBACK). PROPER ENGINE IDENTIFIED AND SHUT DOWN. RECORDING T5 INDICATOR CHECKED AND FOUND ENGINE HAD REACHED 784C FOR 4 SECONDSDR JYDR20180713190Disc · crackedDURING INSPECTION IAW AD 97-02-13 USING AMOC LETTER. 6 CRACKS WERE FOUND AT THE TIE BOLT THROUGH HOLES. CRACKS WERE FOUND WITH BOTH FPI AND EDDY CURRENT. AD STATES THAT DISK IS TO BE INSPECTED AT OR BEFORE 3000 HOURS TT AND 1500 HOURS THEREAFTER. THIS DISK HASDR JYDR20170922257Cylinder Damper · crackedDURING OVERHAUL, A CRACK WAS FOUND IN THE DAMPER BARREL EXTENDING HOLE TO HOLE AND INTO THE CHECK VALVE BORE.SDR JYDR20170831240B-Nut · looseWHEN AIRCRAFT TOUCHED DOWN DURING HOVER LANDING A VIBRATION (IMBALANCE) WAS FELT IN THE ROTOR SYSTEM. PILOT SHUT DOWN AIRCRAFT AND IT WAS TOWED TO MAINTENANCE BASE. MECHANICS FOUND THE B NUT ON THE DAMPER HYDRAULIC ACCUMULATOR QUICK DISCONNECT LOOSE WITH A LOSSDR JYDR20170609239Blade · crackedMAIN ROTOR BLADE WAS REMOVED FOR BIM INDICATION. BLADE INSPECTED AND A 2.3 INCH CRACK WAS FOUND ON THE SPAR, ON BOTTOM OF BLADE, UNDER POCKET 17, 167.25 INCHES FROM ROOT END.SDR JYDR20170316074Axle · failedAIRCRAFT JUST STARTED TO TAXI. AS PILOT RELEASED NOSE WHEEL LOCK THE NOSE WHEEL AXLE BROKE CAUSING LOSS OF NOSE WHEEL. AIRCRAFT WAS STILL ON GROUND AND HAD JUST STARTED TO MOVE. AIRCRAFT SHUT DOWN RESTING ON NOSE LANDING GEAR STRUT.SDR JYDR20160422098Bearing Race · crackedFOUND HORIZONTAL HINGE PIN INNER BEARING RACE CRACKED DURING REPAIR. MRH HAD 292.3 HRS. REMAINING TO O/H. MFG HAS BEEN INFORMED.SDR JYDR2013110801239Servo · wornDURING A SCHEDULED MAIN GEAR BOX CHANGE, THE LT LATERAL PRIMARY SERVO WAS FOUND TO HAVE A SEVERELY WORN BOLT AND BUSHING AT THE LOWER PIVIT FOLLOW UP ARM. SERVO WAS REMOVED FROM SERVICE AND RETURNED TO THE REPAIR STATION FOR INVESTIGATION. THE MFG IS PARTICIPSDR JYDR2013110800239Servo · wornDURING A SCHEDULED MAIN GEAR BOX CHANGE, THE LT LATERAL PRIMARY SERVO WAS FOUND TO HAVE A SEVERELY WORN BOLT AND BUSHING AT THE LOWER PIVIT FOLLOW UP ARM. SERVO WAS REMOVED FROM SERVICE AND RETURNED TO THE REPAIR STATION FOR INVESTIGATION. THE MFG IS PARTISIPSDR 2006FA0001136Bearing · cracked(REF NR MDR06-089) THE IGB CHIP DETECTOR INDICATED A CHIP LIGHT. IGB WAS REMOVED AND THE INNER RACE WAS FOUND TO BE CRACKED THROUGH AND SPALLED. PROBABLE CAUSE: UNKNOWN. (K)SDR 2005FA0001553Stator · sheared(REF NR MDR05-080) INSPECTION WAS PERFORMED ON 1ST STAGE STATOR AND SHOWED SIGNS OF FOD. UPON FURTHER INSPECTION IST WAS DETERMINED THAT TWO RIVETS (MFG HEAD) HAD SHEARED ON STIFFENER RING OF THE 1ST STATOR AND WERE INGESTED CAUSING MINOR DAMAGE TO THE LATER SDR 2005FA0000819Gear · crackedTGB AND SERVO ASSY REMOVED FROM ACRFT FOR MAKING METAL. GEARBOX DISASSEMBLED AND DURING VISUAL INSP OF OUTPUT GEAR, ONE TOOTH FOUND CRACKED. FRIVE SIDE OF TOOTH SHOWS THE MAJORITY OF CRACKING, STARTING FROM IB TO ALMOST MIDWAY ON TOOTH EXTENDING ACROSS TIP LSDR 2005FA0000820Turbine Blades · brokenCOMPRESSOR ASSY WAS REMOVED FROM AC FOR FAILING VIBRATION ANALYSIS. DURING THE PRELIMINARY INSPECTION IT WAS NOTED THAT A PIECE OF 2ND STAGE TURBINE BLADE OUTER SHROUD KNIFE EDGE WAS MISSING. THE MISSING PIECE WAS APPROXIMATELY .500 INCH LONG AND FROM THE AFSDR 2005FA0000340Bearing Race · cracked(MDR05-072) THE MRH SLEEVE AND SPINDLE ASSY DEVELOPED AN OIL LEAK WHILE ON AIRCRAFT AND WAS NOTED DURING ROUTE INSPECTION. UPON REMOVAL AND REPLACEMENT WITH A SERVICEABLE ASSY, A CRAK WAS FOUND ON THE INNER RACE. VISUAL INSPECTION SHOWS WEAR AND CORROSION TYSDR JYDRMDR04069Housing · crackedMGB WAS REMOVED FOR MAIN SHAFT REPLACEMENT AND OVERHAUL. AFTER DISASSEMBLY OF GEAR BOX, THE UPPER HOUSING WAS LOCALLY BLENDED, ETCHED UNDER THE INPUTS AND INSPECTED BY FPI. THE HOUSING WAS REJECTED FOR CRACKS ON THE LT AND RT SIDE. POOR REWELD QUALITY OF CASDR 2005FA0000000Bevel Gear · crackedDURING NDT INSPECTION, GEAR WAS MPI`D AND REJECTED FOR CRACKS. LOCATION OF CRACKS WERE IN ATTACHMENT FLANGE BOLT HOLES (18 EACH). EVERY HOLE HAS APPROXIMATELY .1250 INCH LONG CRACK STARTING ON THE GEAR TO SHAFT ATTACHMENT SIDE EXTENDING DOWN INTO THE HOLE. SDR MDR03032Bleed Valve · obstructedNR 1 ENG OIL PRESS WAS INDICATING LOWER THAN NR 2 ENG. PRESS INDICATED 45 PSI. ADJUSTED PRESS VALVE TO INCREASE CHECK AT NEXT FLT. NR 1 ENG WAS STARTED, INDICATED NML GROUND IDLE. ACCELERATING TO 70 PERCENT N2, OIL PRESS DROPPED OFF, CAUTION LIGHT ILLUM, PSDR 2004F00284Spacer · crackedCOMPRESSOR ASSY WAS REMOVED FROM AN AIRCRAFT FOR A 1000 HOURS SCHEDULED HOT SECTION INSPECTION. DURING TEST RUN, THE ENGINE EXPERIENCED VIBES WHICH WERE OUT OF ACCEPTABLE LIMITS. THE ENGINE WAS DISASSEMBLED AND CHECKED FOR BALANCE AND WAS FOUND TO BE OUT OF SDR 2004F00335Seal · brokenCOMPRESSOR ASSY REMOVED FROM A/C FOR A 1000 TSO SCHED HOT SECTION INSP. DURING INSP, EVIDENCE RUBBING BETWEEN OUTER SHROUD OF 1ST STAGE N1 BLADES & 1ST STATE OUTER AIRSEAL KNIFE EDGES. 1 BLADE BROKEN OUTER SHROUD. CONTACT BETWEEN DAMAGED TO OUTER SHROUD OF BSDR MDR03036Housing · crackedTHE TGB CENTER HOUSING WAS FOUND CRACKED WHILE INSTALLED ON THE AIRCRAFT. IT WAS REMOVED PREMATURELY ON DECEMBER 20, 2000. THE SHOP DETECTED THE CRACK VISUALLY. THE CRACK BEGAN AT THE SECOND ROSAN STUD CLOCKWISE FROM THE ROSAN SEAT PAD LOCATED 34 DEGREES FRSDR MDR03029Housing · crackedTGB CTR HSG FOUND CRACKED WHILE INSTALLED ON AC. IT WAS REMOVED PREMATURELY HAVING A TSO OF 974.7 HR. VISUALLY DETECTED INDIC IN OB WEB OF LT MOUNTING LUG. HSG WAS LOCALLY FPI INSPECTED TO VERIFY. NO IND WAS NOTED. AREA WAS STRIPPED, LIGHTLY ABRADED WITH SSDR MDR03034Gear · crackedTAIL ROTOR GEARBOX WAS REMOVED FROM AC FOR MAKING METAL. TAIL ROTOR GEARBOX WAS DISASSEMBLED IN THE OVERHAUL SHOP AND VISUALLY FOUND A CRACKED GEAR TOOTH ON THE OUTPUT GEAR. DURING THE MPI INSPECTION, WAS CONFIRMED THE TOOTH WAS CRACKED AND NO OTHER CRACKS WESDR MDR03031Bearing · failedCREW REMOVED M/R HEAD AFTER LOCK SCREW SECURING LOCK SHEARED FOR SECOND TIME ON SPINDLE ASSY DESIGNATED AS GREEN. DURING TEARDOWN OF GREEN SPINDLE ASSY AFTER REMOVING NUT, SECURING HORIZ HINGE PIN. IT WAS NOTICED BONDED SPLIT LINERS WERE DEBONDED FROM SPINDLSDR MDR03030Plate · crackedDURING THE MAGNETIC PARTICLE INSPECTION OF THE 2ND STAGE PLANETARY PLATE, A CRACK WAS DETECTED. THE CRACK IS LOCATED IN THE .125 INCH R. FROM THERE, IT TRAVELS TOWARDS THE SPLINE AT A 45 DEGREE ANGLE. THEN IT TRAVELS DOWN THE DRIVE SIDE TOOTH FILLET OF THESDR MDR03028Strap · crackedTHE STRAP IS CRACKED ON THE INBOARD SIDE OF THE BLADE APPROXIMATELY 9.25 INCHES FROM THE TRAILING EDGE OF THE FAIRING. THE CRACK STARTS AT THE CUFF END OF THE BLADE APPROXIMATELY 1.5 INCHES. THE CRACK STARTS WHERE THE LEADING EDGE OF THE FAIRING, PN 65161-00SDR MDR03027Strap · crackedON THE INBOARD SIDE OF THE BLADE, THERE IS A CRACK IN THE STRAP AND POCKET. THE CRACK STARTS AT THE ROOT END SIDE OF THE STRAP AND EXTENDS 3.75 INCHES TOWARD THE TIP END, INTO THE POCKET. THE CRACK IS 9.25 INCHES FROM THE TRAILING EDGE OF THE FAIRING. CAUSESDR MDR03024Fitting · crackedUPON POST-FLIGHT INSPECTION, FIELD MAINTENANCE PERSONNEL DISCOVERED THE LOWER FITTING TGB, PN 6420-66345-101, CRACKED AT THE AFT LOWER LEFT-HAND CORNER. THE CRACK IS APPROXIAMTELY .5000 INCH IN LENGTH AND TRAVELS THROUGH THE THICK WEB AND TURNS TOWARDS THE LOSDR MDR03018Strap · crackedTHE STRAP IS CRACKED N THE OUTBOARD SIDE OF THE BLADE, APPROXIMATELY 9.125 INCHES FROM THE TRAILING EDGE. THE CRACK STARTS AT THE CUFF END OF THE BLADE AND EXTENDS APPROXIMATELY 1.25 INCHES TOWARDS THE TIP END OF THE BLADE. THE CRACK STARTS WHERE THE BACK WASDR JYD2003F00001Pressure Panel · crackedPRESSURE PLATE (PN 65101-11016-041) FOUND CRACKED. MAIN ROTOR HEAD (MRH) REMOVED FROM SERVICE DUE TO SEVERE STORM DAMAGE WITH A TT 3772.9 AND A TSO 754. DURING OVERHAUL OF MRH, A CRACK INDICATION WAS DETECTED IN PRESSURE PLATE (PN 65101-11016-041) DURING FLUSDR JYD2002F00001Support · cracked3 CRACKS WERE FOUND IN LWR SUPPT E MODEL MN GEARBOX WAS REMOVED FROM SERVICE FOR O/H IN1995. IN DECEMBER OF 2001, SUPPT WAS MACHINED TO REMOVE CORROSION. AFTER MACHINING, CRACK WAS VISUALLY DETECTED IN MOUNTING LUG HOLE NR 4 AS INSTALLED ON AC. FLUORESCENT SDR 2002F00105Support · cracked3 CRACKS WERE FOUND IN LOWER SUPPORT OF MAIN ROTOR GEARBOX.SDR 20010613CW018Blade · crackedREMOVED FROM AIRCRAFT FOR BIM INDICATION. PERFORMED LEAK CHECK. DETECTED LEAK AND FOUND CRACK. CRACK IS CHORDWISE, AND .5000 INCH LONG WITH CORROSION PIT LOCATED IN CENTER. LOCATION OF CRACK IS 23.5 INCHES FROM TIP END ON BOTTOM SIDE OF BLADE AND 4 INCHES SDR JYD2001F00000Hinge Pin · crackedS-64F MAIN ROTOR HEAD HINGE PINS DO OCCASIONALLY CRACK FROM DAMPER NUT SAFETY HOLES (APPROX 15 PER CENT OF THE TIME), BUT TYPICALLY THE CRACKS TRAVEL OUTBOARD TO THE EDGE OF THE HINGE PIN. HINGE PIN SN A04100236 CRACKED INBOARD THROUGH THE THREADS INTO THE THSDR 20010606CW005Hinge Pin · crackedS-64F MAIN ROTOR HEAD HINGE PINS DO OCCASIONALLY CRACK FROM DAMPER NUT SAFETY HOLES (APPROX. 15 PERCENT OF THE TIME), BUT TYPICALLY THE CRACKS TRAVEL OUTBOARD TO THE EDGE OF THE HINGE PIN. HINGE PIN SN A041-00236 CRACKED INBOARD THROUGH THE THREADS INTO THE TSDR 20010427CW007Shaft · crackedDURING OVERHAUL, MAGNETIC PARTICLE INSPECTION REVEALED MULTIPLE INDICATION IN THE LOWER SPLINE AREA OF MAIN ROTOR SHAFT. LONGEST INDICATION MEASURED APPROX .500 INCH IN LENGTH, BEGINNING IN THE ROOT AREA EXTENDING OVER SPLINE FACE, DOWN TO THE NEXT ADJACENT RSDR 20001018SH029Gear · failed1ST STAGE PLANETARY PINION GEAR, PN 6435-20411-102, SN 1524, UNKNOWN TT, FAILED IN MAIN GEARBOX, PN 6435-20500-049, SN A6-165, LEAVING LARGE FRAGMENT OF FERROUS METAL IN SUMP, SUMP SCREEN. TEARDOWN INSP REVEALED ENTIRE TOOTH FRACTURED AT JUNCTION OF CASE TO CSDR 20000511SH040Planetary Gear · fractured1ST STAGE PLANETARY PINION GEAR, PN 6435-20411-102, SN 1477, HAVING AN UNKNOWN TT, FAILED IN MAIN GEARBOX, PN 6435-20500-048, SN A6-161. INSP REVEALED TWO-THIRDS OF A 1ST STAGE PLANETARY PINION GEAR TOOTH FRACTURED CAUSING REPLACMENT OF THE FOLLOWING ITEMS DUSDR 98ZZZX3342Bearing · damagedBEARING REMOVED FROM AN ENGINE DURING REPAIR WITH A TOTAL BEARING TIME OF 1,449.4 HOURS WITH NO PREVIOUS OVERHAULS. NO OTHER BEARING IN THE ENGINE WAS DISCREPANT. DURING OVERHAUL, THE BEARING WAS INSPECTED AND ONE UNUSUAL CONDITION WAS FOUND: THE BALLS EXHISDR 98ZZZX2812Rollers · wornSUBMITTER STATED THIS MDR AFFECTS S-64E MODEL. ACFT WAS FLYING UNDER NORMAL CONDITIONS WHEN NR 1 AND NR 2 GEN WENT OFF-LINE AND INVERTER POWER WAS NEEDED FOR A/C TO RETURN TO LANDING. INITIAL INSP REVEALED ALL WIRES CONNECTED AND CB'S IN CORRECT POSITIONS. SDR 98ZZZX2832Blade · failedNOTE: THE ACRONYM 'BIM' STANDS FOR BLADE INSPECTION METHOD AND IS A TERM REGISTERED BY SIKORSKY. THE INDICATOR SENSES PRESSURE WITHIN THE BLADE SPAR AND CHANGES COLOR TO DENOTE A LEAK WHICH MAY BE CAUSED BY A CRACKED SPAR INDICATING THIS MDR SUBJECT HAS AIRWSDR 98ZZZX2255Blade · fracturedON 4-24-98, AIRCRAFT WAS ON A FIRE FIGHTING MISSION. DURING CLIMB-OUT, A LOUD 'BANG' SOUND OCCURRED, FOLLOWED BY A LEFT YAW. THE LOAD OF WATER WAS JETTISONED AND PILOTS PUSHED MAXIMUM BEEP ON BOTH ENGINES. THE NR 1 ENG WAS CARRYING THE LOAD. THE NR 2 ENG RSDR 98ZZZX1742Blade · crackedMAIN ROTOR SPAR IS CRACKED 72.81 INCHES FROM TIP UNDER THE NR 6 POCKET, CLOSE (APPROXIMATELY .1 INCH) TO THE SPACE BETWEEN THE NR 6 AND NR 7 POCKETS. THE CRACK RUNS CHORDWISE BETWEEN THE POCKET LEADING EDGE GROOVE, AND THE BACKWALL RADIUS. IT DOES NOT APPEARSDR 98ZZZX1743Center Housing · crackedTAIL ROTOR GEARBOX WAS REMOVED FROM AIRCRAFT DUE TO A CRACK IN THE TAIL GEARBOX CENTER HOUSING WEB ADJACENT TO THE LOWER LEFT GEARBOX ATTACHMENT LUG. ENGINEERING REQUESTED THE QUALITY DEPARTMENT HELP FIND THE CRACKED AREA BECAUSE IT WAS NOT MARKED ON THE PARTSDR 98ZZZX68Case · crackedWHILE INSTALLED, AFT FLANGE OF CASE SN 225 FRACTURED 360 DEGREES WITHIN THE FLANGE WELD JOINT. FRACTURING OF AFT FLANGE ASSY ELIMINATED THE AFT MOUNT FROM ENG SUPPORT. ENG FREE TO MOVE VERTICALLY, LATERALLY, AND FORE AND AFT, UNRESTRAINED BY AFT MOUNT. THISSDR 97ZZZX4347Bracket Bolt · crackedDURING OVERHAUL OF THE MAIN ROTOR HEAD, A FLUORESCENT MAGNETIC PARTICLE INSPECTION REVEALED A TOTAL OF 4 CRACK INDICATIONS IN BOLT HEAD TO SHANK RADIUS. LARGEST CRACK IS 0.200 INCH IN LENGTH RADIALLY AROUND SHANK. THREE SMALL CRACKS ARE 0.040 INCH LONG EACH.SDR 97ZZZX3377Main Shaft · crackedPART WAS MPI'D AND FOUND TO HAVE ONE CRACK INDICATION LOCATED AT THE UPPER END OF THE LOWER SPLINES. THE INDICATION EXTENDS FROM THE SPLINE RADIUS AND GOES TOWARD THE TOOTH FACE AT APPROXIMATELY A 45 DEGREE ANGLE. LENGTH OF INDICATION IS APPROXIMATELY 0.050 SDR 97ZZZX3013Blade · crackedBLADE OPERATED BY ERICKSON FOR APPROXIMATELY 350.0 HOURS AND WAS REMOVED FOR A BLACK BIM INDICATION. A NITROGEN LEAK WAS DETECTED BETWEEN BLADE POCKETS NR 24 AND NR 25 ON THE LOWER SPAR SURFACE. IT APPEARED TO ORIGINATE UNDER AN APPROVED MILITARY APPLIED PATSDR JYDR970328Main Shaft · crackedCRACKS FOUND IN LOWER SPLINES. CRACKS APPEAR TO START IN SPLINE RADIUS AND TRAVEL AT 45 DEGREES TOWARD THE SPLINE TOOTH. INDICATIONS ARE ON THE LOAD SIDE JUST AT OR BELOW ENGAGEMENT AREA. ELEVEN SPLINES WITH INDICATIONS. LONGEST INDICATION IS 0.150 INCH LOSDR 97ZZZX2478Main Shaft · crackedMGB MAIN SHAFT INSPECTION, CRACKS FOUND IN LOWER SPLINES. CRACKS APPEAR TO START IN SPLINE RADIUS AND TRAVEL AT 45 DEGREES TOWARD THE SPLINE TOOTH. INDICATIONS ARE ON THE LOAD SIDE JUST AT OR BELOW ENGAGEMENT AREA. ELEVEN SPLINES WITH INDICATIONS. LONGEST
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