N643FE
Service difficulty reports · 350
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 = 'N643FE' 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 = 'N643FE' 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 FDEA201410313433Warning Light · false activationSLIDE LIGHT ILLUMINATED. ON ACFT ARRIVAL FOUND SLIDE CYLINDER PRESS IS IN GREEN BAND & MICRO JACK WAS CONNECTED. SLIDE RAFT CYLINDER PRESS TESTED OK IAW AMM 25-61-06-5. ACFT OK FOR SERVICE.SDR FDEA201406221507Handle · lack of lubeAFTER TAKEOFF WITH GEAR LEVER UP & IN THE FOUR GEAR INDICATOR LIGHTS ADJACENT TO GEAR HANDLE & ON CONFIG PAGE REMAINED ILLUMINATED RED. GEAR HANDLE RECHECKED UP & IN BUT NO CHANGE. ACCOMPLISHED QRH PROCEDURE, LOWERED GEAR WITH FOUR GREEN THEN RETRACTED GEAR.SDR FDEA201404280869Gcu · inoperativeCLIMBING THRU FL 260, NR 1 GENERATOR OFF ILLUMINATED. WHILE WORKING THAT PROBLEM, NR 3 GENERATOR ALERT ILLUMINATED, FOLLOWED BY TR 1 FAIL & BATTERY DISCHARGING ALERTS. DIVERTED. R & R NR 3 TR IAW AMM 24-31-01-2.SDR FDEA201309132204Skin · crackedSIX FASTENER HOLES FOUND TO HAVE CRACK INDICATIONS, DURING OPEN-HOLE HFEC INSPECTION ON RT WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN XORS 690 AND XORS 700. REPAIRED IAW EA 1-5710-T0302389 PART 1. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 117.SDR FDEA201309132203Skin · crackedTHREE FASTENER HOLES FOUND TO HAVE CRACK INDICATIONS DURING OPEN-HOLE HFEC INSPECTION ON LT WING LOWER SKIN ACCESS DOOR CUTOUT, BETWEEN XORS 690 AND XORS 700. REPAIRED IAW EA 1-5710-T0302390B PART 1. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 11SDR FDEA201309122187Frame · dentedFRAME FOUND DENTED AT BS 1641, LONGERON 12 RIGHT. REPAIRED IAW SRM 53-00-07 FIGURE 201 REPAIR 2 REVISION 53. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 117.SDR FDEA201309072155Attach Bracket · corrodedRIGHT WING INBD FLAP, INBD DRIVE LINK ATTACH BRACKET BORE, FLAP SIDE, FOUND CORRODED. DRIVE LINK ATTACH BRACKET BORE (FLAP SIDE) REWORKED IAW SRM 51-21-01 REVISION 53. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 117.SDR FDEA201309072154Attach Bracket · corrodedLEFT WING INBD FLAP, INBD DRIVE LINK, ATTACH BRACKET BORE, FLAP SIDE, FOUND CORRODED. REWORKED CORROSION IAW SRM 51-21-01REVISION 53. REPAIRED IAW EA 1-5750-T0302436 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 117.SDR FDEA201309072153Hinge Fitting · corrodedRT WING INBD FLAP AFT HINGE BRACKET PIVOT INBD LUG BORE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMITS IAW CMM 57-52-03 REVISION 76. BLEND OUT CARRIED OUT IAW SRM 57-00-00 REVISION 53. REPAIRED IAW EA 1-5750-T0302386 PART 1 STEP 1,3,4,5,7 AND 8. REPAIR SDR FDEA201309072152Hinge Fitting · corrodedRT WING INBD FLAP AFT HINGE BRACKET PIVOT OTBD LUG BORE FOUND CORRODED. FOUND EXCEED LIMITS IAW CMM 57-52-03 REVISION 76. BLEND OUT CARRIED OUT IAW SRM 57-00-00 REVISION 53. REPAIRED IAW EA 1-5750- T0302386 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2SDR FDEA201309062145Hinge Fitting · corrodedLEFT WING INBD FLAP, AFT HINGE BRACKET PIVOT INBD LUG BORE FOUND CORRODED. REPAIRED IAW EA 1- 5750-T0302385 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 117.SDR FDEA201309062144Hinge Fitting · wornLEFT WING INBD FLAP, AFT HINGE BRACKET PIVOT OTBD LUG BORE FOUND DAMAGED. FLAP AFT HINGE BRACKET PIVOT OUTBOARD LUG BORE REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-52-03 REVISION 76. REPAIRED IAW EA 1-5750-T0302385 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMSDR FDEA201309062143Frame · dentedFRAME BS 1661 LONGERON 12 LT, FOUND DENTED. REPAIRED IAW SRM 53-00-07 FIGURE 201 REPAIR 2 REVISION 53. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 117.SDR FDEA201309062141Frame · dentedFRAME BS 1641, LONGERON 12 LT, FOUND DENTED. REPAIRED IAW SRM 53-00-07 FIGURE 201 REPAIR 2 REVISION 53. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 117.SDR FDEA201309062142Frame · dentedFRAME BS 1641, LONGERON 12 LT, FOUND DENTED. REPAIRED IAW SRM 53-00-07 FIGURE 201 REPAIR 2 REVISION 53. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 117.SDR FDEA201309062140Frame · dentedFRAME BS 1681, LONGERON 12R FOUND DENTED. REPAIRED IAW SRM 53-00-07 FIGURE 201 REPAIR 2 REVISION 53. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 117.SDR FDEA201309062139Frame · dentedBS 1661, LONGERON 12R. FRAME FOUND DENTED. REPAIRED IAW SRM 53-00-07 FIGURE 201 REPAIR 2 REVISION 53. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 117.SDR FDEA201309052124Seat Track · damagedBS 1124, X = -47.5 SEAT TRACK CROWN FOUND DAMAGED. REPAIRED BY SECTIONAL REPLACEMENT FROM BS 1089 TO 1129 IAW SRM 53-00-52 FIGURE 201 REPAIR 1 REVISION 53. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 117.SDR FDEA201305020898Fmu · faulted"FADEC ALT" MANUAL THROTTLES AT T/O NR 2 WOULD NOT ACHIEVE "MAX POWER" AT FADEC BAR, BOTH EPR & N1 NOTED BELOW NR 1 & 3 ENG. FADEC MODE IN NORMAL AND ALT. ALL ENGINE PARAMETERS WITHIN SPECIFIED LIMITS OUTLINED IN JRH. PERFORMED MAX POWER ASSURANCE RUN. NOTSDR FDEA201304080744Engine · failedON DOWN WIND DTW 4000, 190 KTS HEARD BANG AND FELT VIBRATIONS NR 3 RPM LO ALERT DISPLAYED" N1 18 PERCENT, EGT 540 N2 :45 PERCENT COMPLIED WITH ENG RPM LO CHECKLIST AND SHUTDOWN ENGINE. R & R NR 3 ENGINE. EA 1-7100-167353 COMPLIED WITH. OPS CHECKED GOOD.SDR FDEA201303090531Tank · overheatedDURING, PERFORMED MX "A" CHECK ITEM 11,B) FOUND EVIDENCE OF BURNED CARGO FOAM STORAGE TANK SURROUNDING COVER, PROBABLY HEATING COIL WAS SHORTED. DETAILED INSPECTION OF NR 2 GENERATOR FEEDER LINE, CARGO FOAM HEATER CIRCUIT BREAKER (NOT TRIPPED) AND OTHER WIRSDR FDEA201301110068Spar Cap · cracked1.625" CRACK RT WING AT STATION XROS 1042. REMOVED AND TEMP INSTALLED TANK PLATE 639EB. REQUIRES HFEC SURFACE PROBE INSPECTION OF R/S CAP HORIZONTAL AND VERTICAL FLANGES FOR DISCONTINUITIES. REPORT TO ENGINEERING IF ANY FINDINGS. PERFORMED HFEC REF SIDSDR FDEA201205302017Control Panel · burnedSHORTLY AFTER TAKE OFF, HAD AN UNCOMMANDED LIGHT ON EFB 1 (CAPTS) POWER START STOP SWITCH. IT WAS NOT SELECTED AS IT WAS ALREADY DEFERRED, POWER LIGHT WENT ON/OFF MOMENTARILY FOR ONLY FEW SEC'S. FAINT ACRID/ELECTRICAL ODOR NOTED FOR BRIEF TIME. NOTED NO SSDR FDEA201202280702Control Handle · dirtyON APPROACH, COULD NOT OBTAIN SAFE GEAR INDICATION. ALL GEAR INDICATED UNSAFE ON BOTH THE GEAR HANDLE & CONFIG DISPLAY. EXECUTED MISSED APPROACH. RECYCLED & WERE FINALLY ABLE TO OBTAIN A SAFE GEAR INDICATION ON BOTH THE GEAR HANDLE & CONFIG DISPLAY. PERFORSDR FDEA201110224619Skin · dentedLT WING SLAT NR 12 FOUND TOP SURFACE NICKED DURING GROUND CREW CHECK NR1 SLAT (LT) NR B6224-509, SN 48476, SRM 57-00-00, FIGURE 202, LT WING NR 1 SLAT XIS 188 NICK BLENDOUT TO 1.0" RADIUS. DEEPEST MEASURED 0.033" AND REPROTECTED IAW SRM 51-21-01, REV 47. ACSDR FDEA201110214605Access Panel · unknownACFT SUMP PANEL PHYSICAL CONFIG FOUND DIFFERENT FRM AMM 06-00-00 FIGURE. ACCOMPLISHED EA 1-5330-153383, . CLASSIFIED AS MAJOR ALTERATION IAW GMM 6-2-100, REV 113.SDR FDEA201110164537Attach Bracket · corrodedFORWARD CARGO BETWEEN STA 959 AND 979, X = -46, ROLLER FOUND CORRODED AFTER PIVOT BRACKET ATTACHMENT REMOVAL. CORROSION REMOVED IAW SRM 51-21-01 REV 47 AND FOUND EXCEEDED LIMIT AS PER SRM 53-00-00 REV 47, FIGURE 205. ORIGINAL MATERIAL THICKNESS 0.109 INCH, SDR FDEA201110164536Channel · corrodedFORWARD CARGO ROLLER TRAY CHANNEL AT BS 1059-6-0, X -25 FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMITS IAW SRM 53-00-00 REV 47, FIGURE 205 REPAIR CARRIED OUT AS PER EA 1-2550-153365, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REV 113.SDR FDEA201110164535Channel · corrodedFORWARD CARGO ROLLER TRAY CHANNEL AT BS 979-1059, X -25 FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMITS IAW SRM 53-00-00 REV 47, FIGURE 205. ORIGINAL MATERIAL THICKNESS 0.109 INCH, MATERIAL REMOVED 0.049 INCH, MATERIAL REMAINED 0.060 INCH. REPSDR FDEA201110164534Channel · corrodedFORWARD CARGO ROLLER TRAY CHANNEL AT BS 806-899, X -25 FOUND CORRODED. CORROSION REMOVED, DEEPEST DEPTH 0.10 INCH, ORIGINAL MATERIAL THICKNESS 0.109 INCH, MATERIAL REMAINED 0.099 INCH, FOUND WITHIN LIMITS IAW SRM 53-00-00 REV 47 FIGURE 205. REPAIR CLASSISDR FDEA201110164533Channel · corrodedFWD CARGO BAY ROLLER TRAY CHANNEL AT BS 1130 -6-70, X = -25.0 FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT IAW SRM 53-00-00 REV 47, FIGURE 205. ORIGINAL MATERIAL THICKNESS 0.109 INCH, MATERIAL REMOVED 0.040 INCH, MATERIAL REMAINED 0.069 INCH. SDR FDEA201110164532Channel · corrodedFORWARD CARGO, PARTIAL LOAD LATCH CHANNEL AT BS 780 TO 795, X = -25.0 CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMITS IAW SRM 51-21-01 REV 47 FIGURE 205. ORIGINAL MATERIAL THICKNESS 0.109 INCH, MATERIAL REMOVED 0.040 INCH. MATERIAL REMAINING 0.069SDR FDEA201110014260Fitting · corrodedLT WING NR3 SLAT MIDDLE ATTACHMENT FITTING FOUND CORRODED AFTER SLAT REMOVAL. REWORKED AND FOUND WITHIN LIMIT AS PER MD-11 SRM 57-40-02 REV 47, FIGURE 201. ORIGINAL DIAMETER = 0.5015 INCH, REWORKED DIAMETER = 0.5785 INCH, MAXIMUM DIAMETER = 0.625 INCH. REPASDR FDEA201110014253Panel · corrodedCORROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = 8 TO X = 27.5. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.052 INCH; MATERIAL REMAINED = 0.120 INCH - FOUND EXCEEDED SDR FDEA201110014252Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO STA 1239, X = 8 TO X = -8. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.035 INCH; MATERIAL REMAINED = 0.137 INCH - FOUND EXCEEDED LISDR FDEA201110014248Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = -75 TO X = -107. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.027 INCH; MATERIAL REMAINED = 0.142 INCH - FOUND EXCEEDEDSDR FDEA201110014242Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1256 TO 1273, X = -98 TO X = -107. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.285 INCH; MATERIAL REMOVED = 0.012 INCH; MATERIAL REMAINED = 0.273 INCH - FOUND EXCEEDEDSDR FDEA201110014241Panel · corrodedCABIN - COROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO 1239, X = 75 TO X =107. COROSSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.132 INCH; MATERIAL REMAINED = 0.040 INCH - FOUND EXSDR FDEA201110014258Fuel Cell · corrodedCOROSION ON CENTER WING TANK TOP PANEL SURFACE AT STA 1210 , X = -8 TO X = - 27.5. CORROSION REMOVED AS PER SRM 51-21-01, REV 47. ORIGINAL MATERIAL THICKNESS = 0.170 INCH; MATERIAL REMOVED = 0.011 INCH; MATERIAL REMAINED = 0.159 INCH - FOUND WITHIN LIMIT ASDR FDEA201110014257Structure · corrodedCORROSION ON CTR WING TANK TOP PANEL SURFACE AT STA 1210 , X = -8 TO X = 8. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.008 INCH; MATERIAL REMAINED = 0.112 INCH - FOUND EXCEEDED LIMIT AS PER MDSDR FDEA201110014246Skin · crackedRT WING FIXED L/E LOWER SURFACE AT REFUELLING ACCESS DOOR INBD SIDE FOUND CRACKED. CRACK TRIMMED OUT AS PER SRM 57-40-02 REV 47, FIGURE 201 REPAIR 7. REPAIR FILLER AND DOUBLER FABRICATED AND INSTALLED AS PER SRM 57-40-02 REV 47, FIGURE 201 REPAIR 7. REPAISDR FDEA201110014259Panel · corrodedCORROSION ON CTR WING TANK TOP PANEL SURFACE AT STA 1210 , X = -47.5TO X = -75. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.170 INCH; MATERIAL REMOVED = 0.011 INCH; MATERIAL REMAINED = 0.159 INCH - FOUND EXCEEDED LIMIT AS PERSDR FDEA201110014256Panel · corrodedCORROSION ON CTR WING TANK TOP PANEL SURFACE AT STA 1210 , X =47.5 TO X =75. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.170 INCH; MATERIAL REMOVED = 0.010 INCH; MATERIAL REMAINED = 0.160 INCH - FOUND EXCEEDED LIMIT AS PER SRSDR FDEA201110014255Panel · corrodedCORROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = 75 TO X = 107. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.024 INCH; MATERIAL REMAINED = 0.148 INCH - FOUND EXCEEDED LIMSDR FDEA201110014254Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = 27.5 TO X = 47.5. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.043 INCH; MATERIAL REMAINED = 0.129 INCH - FOUND EXCEEDESDR FDEA201110014251Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = -8 TO X = -27.5. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.031 INCH; MATERIAL REMAINED = 0.141 INCH - FOUND EXCEEDED LISDR FDEA201110014250Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = -27.5 TO X = -47.5. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.041 INCH; MATERIAL REMAINED = 0.131 INCH - FOUND EXCEEDESDR FDEA201110014249Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X = -47.5 TO X = -75. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.176 INCH; MATERIAL REMOVED = 0.015 INCH; MATERIAL REMAINED = 0.161 INCH - FOUND EXCEEDED LISDR FDEA201110014247Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1229 TO 1239, X =47.5 TO X =75. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.027 INCH; MATERIAL REMAINED = 0.145 INCH - FOUND EXCEEDED LIMITSDR FDEA201110014245Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1209 TO 1219, X =107. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.193 INCH; MATERIAL REMOVED = 0.031 INCH; MATERIAL REMAINED = 0.162 INCH - FOUND EXCEEDED LIMIT AS PER
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