N610FE
Service difficulty reports · 497
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.
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 n_number = 'N610FE' AND registry_match = 'registration' 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 n_number = 'N610FE' AND registry_match = 'registration' 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 04FDEA01685Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP I/B HINGE I/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGE 2 - 4. ORIGINAL THICKNESS = 0.412, REMAINING = THICKNESS = 0.410, MATERIAL REMOVED = 0.002. COMPLIED WITH FEDEX EA 1-5750-76738, WINGS - LESDR 04FDEA01684Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP I/B HINGE I/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.190. COMPLIED WITH FEDEX EA 1-5750-76738, LEFT AND RIGHT OUTBOARD FLAP - INBOARD HINGE BRSDR 04FDEA01683Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B PIVOT BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGE 2 - 4. ORIGINAL THICKNESS = 0.513, REMAINING = THICKNESS = 0.511, MATERIAL REMOVED = 0.002. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RIGSDR 04FDEA01682Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B PIVOT BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGE 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.092. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BRACKSDR 04FDEA01681Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B PIVOT BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGE 2 - 4. ORIGINAL THICKNESS = 0.497, REMAINING THICKNESS = 0.495, MATERIAL REMOVED = 0.002. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RIGHT SDR 04FDEA01680Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B PIVOT BORE HOLE CORRODED. CORROSSION REMOVED AS PER CMM 20-11-02, PAGE 2 - 4. ORIGINAL DIAMETER = 1.094, FINAL DIAMETER = 1.128. COMPLIED WITH FEDEX EA #1-5750-76739, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE SDR 04FDEA01679Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B ACTUATOR BORE SPOTFACE CORRODED. CORROSSION REMOVED AS PER CMM 20-11-02, PAGE 2 - 4. ORIGINAL THICKNESS = 0.0417, REMAINING = THICKNESS = 0.415, MATERIAL REMOVED = 0.002. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT ASDR 04FDEA01678Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGE 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.189. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BSDR 04FDEA01677Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGE 2 - 4. ORIGINAL THICKNESS = 0.402, REMAINING THICKNESS = 0.402, MATERIAL REMOVED = 0.002. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RSDR 04FDEA01676Hinge · corrodedLEFT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B ACTUATOR BORE HOLE CORRODED. CORROSSION REMOVED AS PER CMM 20-11-02, PAGE 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.190. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGESDR 04FDEA01675Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE O/B PIVOT BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.508, REMAINING THICKNESS=0.506, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76738, WINGS - LEFTSDR 04FDEA01674Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE O/B PIVOT BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG DIA 1.063, FINAL DIA 1.095. REPAIR CARRIED OUT AND FABRICATED BUSHING INSTALLED AS PER FEDEX EA 1-5750-76738, WINGS - LEFT AND RIGHT SDR 04FDEA01673Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE I/B PIVOT BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.490, REMAINING THICKNESS=0.488, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76738, WINGS - LEFT ASDR 04FDEA01672Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE I/B PIVOT BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.094, FINAL DIAMETER = 1.128. COMPLIED WITH FEDEX EA 1-5750-76738, WINGS - LEFT AND RIGHT OUTBOARD FLAP - INBOARD HSDR 04FDEA01671Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE O/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.408, REMAINING THICKNESS=0.406, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76738, WINGS - LESDR 04FDEA01670Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE O/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.190. COMPLIED WITH FEDEX EA 1-5750-76738, WINGS - LT AND RT OUTBOARD FLAP - INBOARD HISDR 04FDEA01669Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE I/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.404, REMAINING THICKNESS=0.402, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76738, WINGS - LESDR 04FDEA01668Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE I/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.190. COMPLIED WITH FEDEX EA 1-5750-76738, WINGS - LEFT AND RIGHT OUTBOARD FLAP - INBOARSDR 04FDEA01667Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B PIVOT BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.500, REMAINING THICKNESS=0.498, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76739, LEFT AND RIGHSDR 04FDEA01666Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B PIVOT BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.096. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BSDR 04FDEA01665Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B PIVOT BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.490, REMAINING THICKNESS=0.488, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76739, LEFT AND RIGSDR 04FDEA01664Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B PIVOT BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.094, FINAL DIAMETER = 1.127. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BSDR 04FDEA01663Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.404, REMAINING THICKNESS=0.402, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76739, LEFT AND RSDR 04FDEA01662Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG DIA 1.063, FINAL DIA 1.189. REPAIR CARRIED OUT AND FABRICATED BUSHING INSTALLED AS PER FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOASDR 04FDEA01661Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.402, REMAINING THICKNESS=0.400, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76739, LEFT AND SDR 04FDEA01660Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG DIA 1.063, FINAL DIA 1.189. REPAIR CARRIED OUT AND FABRICATED BUSHING INSTALLED AS PER FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOASDR 04FDEA01654Seat Track · damagedCABIN SEAT TRACK DAMAGED AT STA 635 LBL 47.5. EXISTING SPLICE REPAIR SEAT TRACK REMOVED AS PER SRM 51-31-01 VOL II. NEW SEAT FABRICATED AS PER DWG ACA7399 AND INSTALLED AS PER SRM 51-33-01 VOL II. NEW SEAT TRACK FABRICATED AS PER DWG ACA7399 AND INSTALLEDSDR 04FDEA01653Seat Track · damagedCABIN STA 1119 LBL 55 SEAT TRACK FOUND DAMAGED. CUT & REMOVED AT STA 1109 & STA 6-40 LBL 47.5 AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II RESPECTIVELY. REPAIR SEAT TRACK FABRICATED & INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-33-01 VOL II.SDR 04FDEA01652Seat Track · damagedCABIN STA 6-30 LBL 55 SEAT TRACK FOUND DAMAGED. CUT & REMOVED AT STA 1109 & STA 6-40 LBL 47.5 AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II RESPECTIVELY. REPAIR SEAT TRACK FABRICATED & ISNTALLED AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-33-01 VOL II.SDR 04FDEA01628Stop Fitting · crackedLEFT WING O/B FLAP STOP FITTINGS FOUND CRACKED. LT WING O/B FLAP STOP FITTING REMOVED AS PER SRM 51-31-01 VOL II AND INSTALLED NEW FITTING AT LEFT HAND WING OUTBOARD FLAP AS PER SRM 51-33-01 VOL II.SDR 04FDEA01627Stop Fitting · crackedRIGHT WING O/B FLAP STOP FITTINGS FOUND CRACKED. RT WING O/B FLAP REMOVED AND REPLACED, REFER TO SNRM 1134.SDR 04FDEA01626Rib · crackedRT WING, SLAT TRACK NR 16 INBOARD RIB SUSPECT CRACKED.SDR 03FDEA02182Fitting · leakingAIRBORNE 1.5 HRS AT FL333 HYD SYSTEM 1 FLUID LEVEL DROPPED TO 0.0 LEVEL II HYD 1 FAIL ILLUMINATED, QRH REVIEWED. FOUND NIPPLE FITTING LEAKING, FWD OUTBOARD FITTING ON THE TOP OF HYD MANIFOLD WHERE THE 4 FILTERS ARE LOCATED. REMOVED RT PUMP'S PRESSURE LINE TSDR 03FDEA01454Seal · deformedDURING CLIMB FROM RJBB, A VERY LOUD NOISE OCCURRED AT THE CAPTAINS WINDOW. NOISE WAS SO LOUD THAT AN INFLT RETURN WAS NECESSARY. UPON DESCENT, NOISE CEASED AT 4.4 DIFFERENTIAL PRESSURE. RETURN WAS NECESSARY DUE TO SAFETY OF FLIGHT DUE TO DIFFICULTY IN COMMUNICSDR 01FDEA00251Aileron · malfunctionedAT 8000 FT ON DEPART RECEIVED A LEVEL 2 AIL DEFLECT DISAG ALERT ON CONFIG PAGE, LEFT AILERON WAS DROOPING, CREATING A RIGHT TURN. ADJUSTED LOB TO NEUTRAL POS PER MM 27-10-00. CYCLED FLAPS AND AILERONS 3X''S, NIL ALERTS AND SYNOPTIC DISPLAY SHOW NEUTRAL.SDR 00FDEA00717Engine · flamed outNR 1 ENGINE FLAMED OUT DURING HEAVY RAIN. FOUND NO FAULT. AC OK FOR SERVICE. CLOSE AND SECURED NR 1 ENG FAN COWL.SDR 00FDEA00631Beam · crackedNR 2 ENGINE LT REVERSER UPPER T-HINGE AFT CORNER CRACKED APPROX .5 INCH.SDR 00FDEA00630Beam · crackedNR 2 ENG RT REVERSER UPPER T-HINGE AFT CORNER CRACKED APPROX .5 INCH.SDR 00FDEA00626Intercostal · crackedAFT CABIN CARGO COMPARTMENT FLOOR PANEL INTERCOSTAL SUPPORT AT BS 1887, LBL 2 FOUND WITH CRACK APPROX 3 INCHES LONG. *S/D* REMOVED AND REPLACED PER MM 20-50-02, 51-31-01, 53-21-04-4.SDR 00FDEA00627Intercostal · crackedAFT CABIN CARGO COMPT FLOOR PANEL INTERCOSTAL SUPPORT AT BS 1887, LBL 21 FOUND WITH CRACK APPROX 3 INCHES LONG. *S/D* REMOVED AND REPLACED PER MM 20-50-02, 51-31-01, 53-21-04-4.SDR 00FDEA00629Beam · crackedNR 3 ENGINE RT REVERSER UPPER T-HINGE AFT CORNER CRACKED APPROX .5 INCH. *S/D* REMOVED AND REPLACED PER EA 1-7830-52102.SDR 00FDEA00632Seat Track · crackedMAIN DECK CARGO COMP FLOOR TRACK AT BS 755, LBL 47.5. FOUND WITH CRACK APPROX 4 INCHES LONG. *S/D* FAB AND INSTALL PER SRM 51-33-01 VOL II.SDR 00FDEA00628Beam · crackedNR 1 ENGINE RT REVERSER TRANSLATING SLEEVE UPPER T-HINGE CRACKED AT AFT PORTION APPROX 1 INCH. *S/D* REMOVED AND REPLACED PER EA 1-7830-52101 RT HINGE BEAM CRACK REPAIRED FUNCTIONAL TEST PER MM 78-30-00-5. FOUND SATISFACTORY.SDR 99FDEA00337Control Cable · brokenWING INBOARD FLAP BUS CABLE ON RT WHEEL WELL FOUND BROKEN AT ONE TERMINAL END DURING SYS NR 2 PRESSURE ON. *S/D* RT I/B FLAP BUS CABLE REMOVED AND REPLACED PER MM 27-51-10-4. SATISFACTORY PER MM 27-50-00-5.SDR 99FDEA00329Seat Track · crackedMAIN DOCK UPPER FUSELAGE SEAT TRACK FOUND CRACK AT BS 635 X=8.5 RT. - 3.2 IN, AT BS 635 X 27.5 RT. - 3.5. AT BS 635 X 47.5 RT -4.3 IN, AT BS 635 X = 47.5 LH-4.5. *S/D* FASTENERS REMOVED AND SEAT TRACK TRIMMED & REWORKED PER SRM 53-42-01.SDR 99FDEA00069Fcc · inop99-0052 - ASYMMETRICAL SLAT ON SLAT RETRACTION 230 KTS. REMOVED AND REPLACED BOTH NR 1 AND NR 2 FLT CONTROL COMPUTERS IAW MM 22-01-03-4 PERF RTS TEST, OPS CK GOOD. PERF CADC TEST RTS IAW MM 34-16-01-3. OPS CK NORM. NOTED ON ALL (3) CADC.SDR 97FDEA00036Oil Temp Ind · malfunctionedNR 3 ENG SHUTDOWN IN CRUISE DUE TO HIGH OIL TEMP AND FALLING OIL QTY, OIL TEMP REACHED 185 DEGREES AFTER SHUTDOWN, OIL THEN BECAME ERRATIC AND FLUCTUATED FROM HIGH TO LOW. WHEN A/C ARRIVED IT HAD 14 QTS OF OIL SERV OIL SYS WITH 3 QUARTS AND READ FULL. CKD AL
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