N672FE
Service difficulty reports · 288
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 = 'N672FE' 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 = 'N672FE' 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 FDEA201603110901Generator · malfunctionedNR 1 GENERATOR FAULT DURING TAKEOFF ROLL, REJECTED TAKEOFF. COMPLIED WITH QRH. NR 1 GENERATOR WOULD NOT RESET. PERFORMED GVI OF IDG, IDG HARNESS & IDG SYS ALSO RECONNECTED IDG IAW MM 24-11-00-00-01, NO FAULTS NOTED, NO EVIDENCE OF OIL LOSS 24-11-00-00-01.SDR FDEA201511213746Brake · hotREJECT CYMX DUE TO HOT BRAKE. EXITED RUNWAY, WAITED FOR BRAKES TO COOL. RT BRAKE NR 7 RTO 95 KTS. AFTER BLOCK IN & CREW DEBRIEF, INSPECTED ALL BRAKES ON SAME TRUCK, FOUND NO SIGNS OF HEAT DAMAGE. ECAM WHEEL PAGE TEMP INDICATION WERE ALL WITHIN 30 DEGREES. SDR FDEA201502080477Skin · dentedFUSELAGE EXTERNAL SKIN FRAME 35, STRINGER 40R 0.5 INCHES FOUND ONE EACH DENT. COMPLIED WITH EA 6-5330-T0315007. THIS REPAIR WAS CATEGORY B, REQUIRED INSPECTION AT 41600 FC AFTER REPAIR. THE INTERVAL & INSPECTION METHOD WERE TBD IAW RAS 80021897 003 2015. TSDR FDEA201501140165Fitting · crackedRIGHT FUSE CTR WING BOX OF REAR SPAR I HOLE FOUND CRACK SIGNAL. COMPLIED WITH EA 6-5710-T0314943 P1 TITLE:WINGS-BASIC WING STRUCTURE -AD 2014- 20-18-FR47 RT FASTENER HOLES CRACKED (SB A300-57-6049 R06/EO 6-5710-7-3305 PT2)SDR FDEA201501140164Fitting · crackedRIGHT FUSE CTR WING BOX OF REAR SPAR N HOLE FOUND CRACK SIGNAL. COMPLIED WITH EA 6-5710-T0314943 P1 TITLE:WINGS-BASIC WING STRUCTURE -AD 2014- 20-18-FR47 RT FASTENER HOLES CRACKED (SB A300-57-6049 R06/EO 6-5710-7-3305 PT2)SDR FDEA201501090102Floorbeam · crackedAFT CARGO FRAME 64, Y-1153 FLOORBEAM CRACKED. CUT OUT THE CRACKED AREA AND TRIMED CUT OUT IAW SRM 53-10-15 FIG 211 MANUFACTURED THE REPAIR PROFILE IAW SRM 53-10-15 FIG 211 PERFORMED NDT INSPECTION AND NO CRACK FOUND. INSTALLED THE REPAIR IAW SRM 51-40-21 SDR FDEA201501090105Structure · crackedRIGHT CTR WING JOINT AT FRAME 40 MID HOLE FOUND CRACKED SIGNAL. COMPLIED WITH EA 6-5710-T0314976 P 1. MAJOR REPAIR IAW GMM 6-2-100.SDR FDEA201501090104Structure · crackedRIGHT CTR WING JOINT AT FRAME 40 LOWER HOLE FOUND CRACKED SIGNAL. COMPLIED WITH EA 6-5710-T0314976 P 1. MAJOR REPAIR IAW GMM 6-2-100.SDR FDEA201409162618Door · not closedDURING TAKEOFF ROLL, MULTIPLE AMBER ECAMS FOR RT FWD COMPARTMENT DOOR. FOUND FWD LWR RT HAND E&E DOOR NOT FULLY LATCHED. CLOSED DOOR AS REQ'D. INDICATION OPS CHECKS GOOD.SDR FDEA201404260901Unknown · malfunctionedAUTOPILOT FAILED TO CAPTURE ALT SEVERAL TIMES DURING CLIMB OUT IN PROFILE. RATE OF CLIMB WAS BETWEEN 3000 & 4000 FT PER MIN. ALSO, CAPTURES ALT VERY SLUGGISH, TENDS TO FLUCTUATE - 500 FEET FOR ABOUT A MIN BEFORE FINALLY CAPTURING ALT. DURING DESCENT IN PROFSDR FDEA201402200376Rib · corrodedLEFT MLG RIB 5 HAS CORROSION IN BORE & FWD & AFT FACE. REPAIRED IAW EA 6-5710-T0306355SDR FDEA201402200377Rib · corrodedRIGHT MLG RIB 5 FWD LUG HAS CORROSION IN THE BORE, FWD FACE & AFT FACE. REPAIRED IAW EA 6-5710-T0306368.SDR FDEA201303210639Engine · inoperativePER FLIGHT CREW DEBRIEF, THE NR 1 ENGINE ON TAXI OUT HAD ECAM ENGINE FAILURE AND ASSOCIATED PARAMETERS WINDING DOWN. IAW CAPTAIN, AFTER BEING NOTIFIED BY MEM TOWER OF SMOKE FROM NR 1 ENG THEY PULLED FIRE HANDLE BUT DIDN'T DISCHARGE BOTTLE AND THEN DEPARTED ACSDR FDEA201301110070Landing Gear · malfunctionedON DEPARTURE MLG WOULD NOT RETRACT, TRIED SYS 1 AND SYS 2 AND FOLLOWED RED TAB. GEAR HANDLE WOULD NOT GO PAST DETENT.SDR FDEA201207242660Adapter · wornM/D FLOOR STRUCTURE OF ADAPTER CROWN BROKEN AT FR32 / Y1456 , Y 1959 POSITION. REPLACED WITH NEW ADAPTER IAW AB6F SRM 51-72-10. THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.SDR FDEA201207242662Adapter · wornM/D FLOOR STRUCTURE OF ADAPTER CROWN BROKEN AT FR 31/ Y 1456, Y1959 POSITION REPLACED WITH NEW ADAPTER I.A.W. AB6F SRM 51-72-10. THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.SDR FDEA201207242661Adapter · wornMAIN DECK FLOOR STRUCTURE OF ADAPTER CROWN BROKEN AT FR 21 BETWEEN LT NR 3, NR 4 SEAT TRACK ( Y 1456,Y 1959) REPLACED WITH NEW ADAPTER IAW AB6F SRM 51-72-10. THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.SDR FDEA201207162588Frame Splice · damagedEO E6-5310-7-5017B, PT2 FUSELAGE FRAME 47 SPLICE FITTING BETWEEN STR 24 AND 26 LT/RT FOUND INITIAL HOLE "N" IS OVERSIZED. REPAIRED IAW EA 6-5315-157934SDR FDEA201207162583Skin · dentedLOWER FUSELAGE SKIN HAS A DENT BETWEEN FR 0 AND FR 1 LOWER SIDE AT Z-1561, POSITION. MEASURE THE MAX. DEPTH 0.023" AND DIMENSION 3"X1.5" (LXW) WITHIN ALLOWABLE LIMIT IAW SRM 53-11-12. NDI WAS COMPLETED. NO CRACK WAS FOUND IAW NTM 51-10-08 P.B.6.SDR FDEA201010134065Floorbeam · damagedAFT CARGO COMPARTMENT, UPPER DOOR CUTOUT AT FRAME 61 RT SIDE, HAS A DOUBLE DRILLED HOLE IN THE FLOORBEAM. THE HOLE IS FOR THE INSTALLATION OF THE UPPER PROFILE. REPAIRED IAW EA 6-5310-136713; "FUSELAGE - FRAME FITTING AT FRAME 61 AND STRINGER 26".SDR FDEA201009303816Floor Panel · damagedMAIN CABIN FLOOR PANEL 252 YG IS DAMAGED. FABRICATED NEW FLOOR PANEL 252 YG IAW DWG SRZ 25-005, REV "H".SDR FDEA201009303815Floor Panel · damagedMAIN CABIN FLOOR PANEL 252 XG IS DAMAGED. FABRICATED NEW FLOOR PANEL 252 XG IAW DWG SRZ 25-005, REV "H".SDR FDEA201009303814Floor Panel · damagedMAIN CABIN FLOOR PANEL 252 VH IS DAMAGED. FABRICATED NEW FLOOR PANEL 252 VH IAW DWG SRZ 25-005, REV "H".SDR FDEA201009303813Floor Panel · damagedMAIN CABIN FLOOR PANEL 252 UH IS DAMAGED. FABRICATED NEW FLOOR PANEL 252 UH IAW DWG SRZ 25-005, REV "H".SDR FDEA201009303812Floor Panel · damagedMAIN CABIN FLOOR PANEL 251 UH IS DAMAGED. FABRICATED NEW FLOOR PANEL 251 UH IAW DWG SRZ 25-005, REV "H".SDR FDEA201009303811Floor Panel · damagedMAIN CABIN FLOOR PANEL 231, QH IS DAMAGED. FABRICATED NEW FLOOR PANEL 231 QH IAW DWG SRZ 25-005, REV "H".SDR FDEA201009293789Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 49 TO FRAME 50, LBL 58. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS IS 0.140 IAW SRM 51-31-20. REMAINING THICKNESS 0.126. MATERIAL LOSS 0.014 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16. ALODINED IAW SSDR FDEA201009293788Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 52 TO FRAME 53, LBL 76. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS IS 0.140 IAW SRM 51-31-20. REMAINING THICKNESS 0.133. MATERIAL LOSS 0.007 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16. ALODINED IAW SDR FDEA201009293787Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 55 TO FRAME 56, RBL 38. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS IS 0.140 IAW SRM 51-31-20. REMAINING THICKNESS 0.105. MATERIAL LOSS 0.035 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16. ALODINED IAW SSDR FDEA201009293786Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 54 TO FRAME 55, RBL 38. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS IS 0.140 IAW SRM 51-31-20. REMAINING THICKNESS 0.111. MATERIAL LOSS 0.029 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16. ALODINED IAW SDR FDEA201009293785Floor Support · crackedMAIN CABIN FLOOR SUPPORT IS CRACKED AT FRAME 48-FRAME 48. REMOVED CRACKED FLOOR SUPPORT AT FRAME 48 AND INSTALLED NEW LINK SUPPORT FITTING PN A5381206720100, PO 692522.1 IAW SRM 51-40-21, PG 1.SDR FDEA201009273742Frame · gougedRIGHT CABIN MAIN FRAME IS GOUGED AT FRAME 47 FROM STRINGER 12R TO STRINGER 13R. COMPLIED WITH EA 6-5310-121266A.SDR FDEA201009273741Frame · gougedLT CABIN MAIN FRAME IS GOUGED AT FRAME 47 FROM STRINGER 8L TO STRINGER 9L. COMPLIED WITH EA 6-5310-136715.SDR FDEA201009233672Floorboard · damagedFWD CARGO COMPARTMENT FLOORBOARD 131 QC HAS EDGE DAMAGE AT MULTIPLE PLACES. DAMAGE REPAIRED IAW DWG SRZ 25-005, REV "H".SDR FDEA201009233681Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 30 - 31; LBL 45. REMOVED CORROSION IAW SRM 51-74-10 TO WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. PAINTED IAW SRM 51-75-10. MAXIMUM ALLOWABLE MATERIAL LOSS ISDR FDEA201009233680Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED IN 2 AREAS FROM FRAME 31 - 34; RBL 12. REMOVED CORROSION IAW SRM 51-74-10. MAXIMUM ALLOWABLE MATERIAL LOSS IS 0.040. REMOVED 0.029. REMAINING MATERIAL IS WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10SDR FDEA201009233679Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED AT APPROX FRAME 31 - 32; BL 60. REMOVED CORROSION IAW SRM 51-74-10. MAXIMUM ALLOWABLE MATERIAL LOSS IS 0.040. REMOVED 0.023. REMAINING MATERIAL IS WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10. PRIMSDR FDEA201009233678Seat Track · corrodedMAIN CABIN CROSS TRACK IS CORRODED AT FRAME 30; RBL 32. REMOVED CORROSION IAW SRM 51-74-10. MAXIMUM ALLOWABLE MATERIAL LOSS IS 0.028. REMOVED 0.011. REMAINING MATERIAL IS WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10. PRIMED IAW SRSDR FDEA201009233677Seat Track · corrodedMAIN CABIN CROSS TRACK IS CORRODED AT FRAME 29; RBL 32. REMOVED CORROSION IAW SRM 51-74-10. MAXIMUM ALLOWABLE MATERIAL LOSS IS 0.040 AND 0.025. REMOVED 0.012 AND .014. REMAINING MATERIAL IS WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-SDR FDEA201009233676Seat Track · corrodedMAIN CABIN CROSS TRACK IS CORRODED AT FRAME 28; RBL 32. REMOVED CORROSION IAW SRM 51-74-10. MAXIMUM ALLOWABLE MATERIAL LOSS IS 0.024. REMOVED 0.013. REMAINING MATERIAL IS WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10. PRIMED IAW SRSDR FDEA201009233673Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED AT BS 1979, BL 0. REMOVED CORROSION IAW SRM 51-74-10. MAXIMUN MATERIAL LOSS IS 0.040. REMOVED 0.022. REMAINING MATERIAL IS WITHIN ALLOWABLE LIMITS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-2310. PAISDR FDEA201009233687Intercostal · corrodedMAIN CABIN FLOORBEAM INTERCOSTAL IS CORRODED ON THE UPPER AND LOWER SURFACE FROM STA 1230 - 1239; FRAME 15A, LBL 197 CM. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS 0.078 IAW SRM 51-30-20. REMAINING THICKNESS IS 0.068. MATERIAL LOSS 0.010 FOUND SDR FDEA201009233686Intercostal · corrodedMAIN CABIN FLOORBEAM INTERCOSTAL IS CORRODED ON THE UPPER SURFACE AT STA 1204; FROM FRAME 14A - 15, LBL 197 CM. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS 0.078 IAW SRM 51-30-20. REMAINING THICKNESS IS 0.073. MATERIAL LOSS 0.005 FOUND TO BE WITSDR FDEA201009233685Intercostal · corrodedMAIN CABIN FLOORBEAM INTERCOSTAL IS CORRODED ON THE UPPER SURFACE AT STA 1173; FROM FRAME 14 - 14A, LBL 197 CM. REMOVED CORROSION IAW SRM 51-74-10. ORIGINAL THICKNESS 0.078 IAW SRM 51-30-20. REMAINING THICKNESS IS 0.074. MATERIAL LOSS 0.004 FOUND IN LIMISDR FDEA201009233684Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 57 - 57.1; LBL 38. REMOVED CORROSION IAW SRM 51-74-10, PG 201. ORIGINAL THICKNESS 0.140 IAW SRM 51-30-20. REMAINING THICKNESS IS 0.126. MATERIAL LOSS 0.014 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16, FIG 101, PG SDR FDEA201009233683Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 57 - 58; LBL 38. REMOVED CORROSION IAW SRM 51-74-10, PG 201. ORIGINAL THICKNESS 0.140 IAW SRM 51-30-20. REMAINING THICKNESS IS 0.127. MATERIAL LOSS 0.013 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16, FIG 101, PG SDR FDEA201009233682Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 74 - FRAME 75; LBL 17. REMOVED CORROSION IAW SRM 51-74-10, PG 201. ORIGINAL THICKNESS 0.140 IAW SRM 51-30-20. REMAINING THICKNESS IS 0.121. MATERIAL LOSS 0.019 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16, FIG 101,SDR FDEA201009233674Seat Track · corrodedMAIN CABIN SEAT TRACK IS CORRODED FROM FRAME 28 TO FRAME 29; RBL 57. REMOVED CORROSION IAW SRM 51-74-10, PG 201. ORIGINAL THICKNESS 0.078 IAW SRM 51-30-20. REMAINING THICKNESS IS 0.071. MATERIAL LOSS 0.007 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16, FOG 10, SDR FDEA201009223647Floor Panel · damagedMAIN CABIN CARGO COMPARTMENT FLOOR PANEL 231 LG IS BROKEN. FABRICATED NEW FLOOR PANEL 231 LG IAW DWG SRZ 25-005, REV "H".SDR FDEA201009223646Floor Panel · damagedMAIN CABIN CARGO COMPARTMENT FLOOR PANEL 231 TG IS BROKEN. FABRICATED NEW FLOOR PANEL 231 TG IAW DWG SRZ 25-005, REV "H".
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