N620DL
Service difficulty reports · 107
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 = 'N620DL' 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 = 'N620DL' 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 IXXA20190401002Gcu · unsecureFLIGHT DEPARTED, ENROUTE ON INITIAL CLIMB, PILOT REPORTED A LOSS OF CAPTAIN EFIS DISPLAY, TOP EICAS DISPLAY, AND LEFT FLIGHT MANAGEMENT COMPUTER SYSTEM. FORWARD EQUIPMENT OVERHEAT INDICATION. LOSS OF FLAP AND BRAKE PRESSURE INDICATIONS. LEFT AND CENTER INSDR IXXA20180621029Stringer · corrodedSTRINGER 27L WAS CORRODED, BS 1455. REMOVED AND REPLACED THE STRINGER IAW SRM 53-00-03, AND REA 46971REA64.SDR IXXA20180621028Stringer · corrodedBS 1455, STRINGER 28L WAS CORRODED. REMOVED AND REPALCED THE STRINGER IAW SRM 53-00-003, FIG 201, AND REA 46971REA64,SDR IXXA20161213198Floorbeam · corrodedAIRCRAFT GROUNDED FOR HEAVY MAINTENANCE. FLOORBEAM LOWER HORIZONTAL FLANGE CORRODED AT STATION 740 LBL 18. REPAIR LOWER CHORD STATION 740 LBL 18 IN ACCORDANCE WITH SRM 53-00-51.SDR IXXA20161213197Web · crackedAIRCRAFT GROUNDED FOR HEAVY MAINTENANCE. NR 1 SLAT AFT SIDE COVE STRUCTURE HAS 2 CRACKS, LOCATED ABOVE THE INBOARD MAIN TRACK FITTING. ONE CRACK IS ABOUT 2 1/4" AND THE OTHER IS ABOUT 1 3/8" IN LENGTH, AT APPROXIMATELY OUTBOARD SLAT STATION 737. REMOVED AND RESDR IXXA20161213196Web · crackedAIRCRAFT GROUNDED FOR HEAVY MAINTENANCE. NR 1 SLAT AFT SIDE COVE STRUCTURE HAS 2 CRACKS, LOCATED ABOVE THE INBOARD MAIN TRACK FITTING. ONE CRACK IS ABOUT 2 1/4" AND THE OTHER IS ABOUT 1 3/8" IN LENGTH, AT APPROXIMATELY OUTBOARD SLAT STATION 737. REMOVED AND RESDR IXXA20161213195Attach Bracket · crackedAIRCRAFT GROUNDED FOR HEAVY MAINTENANCE. NUMBER 1 PYLON, LINK AT FORWARD LEFT SIDE OF HYDRAULIC BAY, LOWER ATTACH BRACKET BROKEN.SDR IXXA20150723083Battery Pack · inoperativeDURING THE COURSE OF DAILY CHECK, EMERGENCY EXIT LIGHTING FOUND TO BE INOPERATIVE. R & R BATTERY POWER SUPPLY IAW AMM 33-51-07. OPERATIONAL CHECKED SATISFACTORY. ACFT RELEASED TO SERVICE.SDR IXXA20150518080Rod · bentL1 ENTRY DOOR ROLLERS DO NOT ALWAYS ENGAGE, UPPER LOCK ROD BENT. R & R UPPER ROD IAW AMM 52-12-00. OPERATIONAL CHECKED SATISFACTORY. ACFT RELEASED TO SERVICE.SDR IXXA20141231038Engine · making metalDURING CLIMB OUT AT FL300, RT ENG OIL PRESS DROPPED INTO RED FOLLOWED BY EICAS MSG. PRECAUTIONARY SHUTDOWN OF NR 2 ENG. ACFT RETURNED, GNDED NO OPS. CHIP DETECTORS PULLED. MASTER CHIP DETECTOR & MAIN GEARBOX CHIP DETECTOR WERE CONTAMINATED WITH CHIPS. DETSDR IXXA20141001023Valve · defectiveMAIN CARGO DOOR WARNING LIGHT DISPLAYED & CABIN PRESS NOT WITHIN PARAMETERS. CREW NOTED PRESSURIZATION AS DECREASING. BITE CHECK OF BOTH CABIN PRESS CONTROLLERS ACCOMPLISHED IAW FIM 21-30 FT 802. SYSTEMS CHECKED SATISFACTORY, NO FAULTS NOTED. HOLDING VLV ASSDR IXXA20140829019Metering Unit · malfunctionedDURING THE TAKE OFF, BEFORE COMPLETE RETRACTION OF THE FLAPS, EICAS MESSAGE DISPLAYED "L HYD PRESSURE" FOLLOWED BY FURTHER MESSAGES INDICATING A LEFT HYDRAULIC SYS PRESS. UPON EVALUATION OF SYSTEM FAULT WAS ISOLATED TO A SEPERATION OF AUTOBRAKE ACTUATOR FROM BSDR IXXA20140814015Module · defectiveON DAILY CHECK FOUND EMER LIGHT UNARMED. ANNUNCIATOR LIGHT INTERMITTENT. EMER LIGHT ANNUNCIATOR LIGHT LENS CAP MODULE R & R IAW AMM 33-16-02 201. OPERATIONAL CHECKED SATISFACTORY.SDR IXXA201306120002Skin Panel · corrodedCORROSION WAS DISCOVERED ON THE RT WING UPPER SKIN PANEL AT FSS404 FWD OF FRONT SPAR. REMOVED CORROSION IAW SRM 57-20-01. PERFORMED HFEC INSP OF BLENDED AREA IAW NDT MANUAL 51-00-19. NO DEFECTS NOTED. FABRICATED REPAIR DOUBLER FROM .071" 7075-T6 AND INSTALSDR IXXA20130612001Skin Panel · corrodedCORROSION WAS DISCOVERED ON THE RT WING UPPER SKIN PANEL AT WS285.65. DAMAGE IS LOCATED NEAR THE AFT EDGE OF THE SKIN PANEL BETWEEN THE REAR SPAR AND STRINGER S-1. REMOVED CORROSION IAW SRM 57-20-01. PERFORMED HFEC INSPECTION OF BLENDED AREA IAW NDT MANUAL 5SDR IXXA20130612032Seat Track · crackedPILOTS AFT OTBD SEAT TRACK IS CRACKED AT THE AFT STOP. R & R THE CAPTAINS AFT OTBD SEAT TRACK IAW AMM 25-11-01.SDR IXXA201306120007Stanchion · corrodedLOWER SECTION OF STANCHION AT BS 1440, RBL 19 CORRODED. FABRICATED STANCHION IAW DWG 284N1695 USING EXTRUSION AND 10140-2002 7075-T6511. RT STANCHION IAW DWG 284N1695.SDR IXXA201306120006Floor Support · corrodedCORROSION WAS DISCOVERED ON THE UPPER CARGO FLOOR SUPPORT BS 1075, LBL 47, FLOOR AREA INBD SURFACE. BLENDED AREA OF CORROSION IAW SRM 53-00-52. PERFORMED ULTRASONIC INSPECTION OF AREA IAW NDT MM PART 4, 51-00-10. MATERIAL REMOVED IS OUT OF LIMITS. FABRICATESDR IXXA201306120005Seat Track · corrodedCORROSION WAS DISCOVERED ON THE UPPER CARGO SEAT TRACK UPPER CHORD AT STATION 1180-1580, RBL 24. DAMAGE CAUSED BY CORROSION IN SEVERAL AREAS ALONG THE UPPER SURFACE WERE FOUND TO BE BEYOND ALLOWABLE AND REPAIRABLE LIMITATIONS. FABRICATED NEW SEAT TRACK SECTISDR IXXA201306120004Sill · corrodedINNER CHORD OF AFT LOWER CARGO DOOR LOWER SILL CORRODED. THE DAMAGE WAS ISOLATED TO THE LOWER HORIZONTAL FLANGE OF THE CHORD SPANNING FROM STATION 1340 - 1440 AT S27R. CORROSION WAS REMOVED IAW SRM 53-60-15, FIG 101, EXCEEDING PUBLISHED LIMITS. A HFEC OPESDR IXXA201306120003Skin · corrodedFUSELAGE EXTERIOR SKIN CORRODED AT AFT LOWER CARGO DOOR CUTOUT THRESHOLD AT STATION 1401 S27R - S28R. CORROSION WAS REMOVED IAW SRM 53-00-01, FIG 101, EXCEEDING PUBLISHED LIMITS. THE DAMAGED SKIN WAS TRIMMED OUT AND A FILLER WAS FABRICATED. A HFEC OPEN HOLSDR IXXA130512ILN025SCargo Track · brokenUPPER CARGO TRACK AT BS 1100, RBL 24 IS BROKE OUT ON UPPER FLANGE AT NUTPLATE. ALSO 3 AREAS OF POSSIBLE CRACKS. REMOVED SEAT TRACK CROWN AT BS 1100 RBL 24 FOR REPLACEMENT. FABRICATED SEAT TRACK. INSTALLED SEAT TRACK IAW SRM 51-40-02.SDR IXXA130512ILN022SSupport Angle · crackedSUPPORT ANGLE CRACKED AT FORWARD LOWER CARGO FWD DOOR FRAME JUST INBD OF THE THIRD DOOR STOP DOWN AT BS 560. REMOVED CRACKED ANGLE AND FABRICATED NEW ANGLE. HEAT TREATED ANGLE IAW 5602, REV AF 28 DATED AUG 2001. TREATED, PRIMED AND PAINTED ANGLE IAW SRM 51-SDR IXXA20130613033Skin · corrodedRT WING REAR SPAR AT WBL 95 HAS CORROSION ON WING SKIN. REMOVED CORROSION FROM WING SKIN IAW SRM 57-20-01. PERFORMED HFEC INSPECTION OF BLENDED AREA IAW NDT MANUAL 51-00-19. NO DEFECTS NOTED. PERFORMED THICKNESS CHECK OF BLENDED AREA IAW NDT MANUAL 51-00-1SDR IXXA20130612031Frame · corrodedCORROSION WAS FOUND IN THE AFT LOWER CARGO COMPARTMENT, ON THE FWD SIDE OF THE FRAME AT BS 1480 BETWEEN S26-27R. BLENDED AREA OF CORROSION IAW SRM 53-00-07, FIG 101. COMPLIED WITH HFEC SURFACE SCAN IAW NDT MM 51-00-19, PART 6. NO DEFECTS NOTED. FABRICATED SDR FOTR3519821257Skin · debondedLT WING FIXED L/E UPPER SURFACE IS DISBONDED WS 231.0, REPAIRED BY REMOVED DAMAGE, CLEAN AND PREPPED LT WING FIXED L/E UPPER SURFACE, APPLIED REPAIR 23" X 18" AND RESTORED FINISH IAW SRM 51-70-07.SDR C8GA201111150026Warning Light · false activationDURING TAKEOFF, SPOILER CAUTION LIGHT ILLUMINATED WITH THE TAKEOFF WARNING HORN AND THE SPOILER EICAS MESSAGE DISPLAYED. ACFT RETURNED TO THE BLOCKS WITHOUT INCIDENT. POST FLIGHT INSPECTION PERFORMED. CONDUCTED CONFIGURATION TAKE OFF TEST, UNABLE TO DUPLICSDR C8GA2011000010Pitot Tube · obstructedDURING TAKEOFF ROLL IT WAS NOTED THAT THERE WAS NO AIRSPEED INDICATION ON THE CAPTAINS SIDE. THE TAKEOFF WAS ABORTED WITH LIGHT BRAKING. ACFT RETURNED TO THE BLOCKS WITHOUT INCIDENT. POST FLIGHT INSPECTION WAS PERFORMED NOTING THAT THE CAPTAINS PITOT TUBE WASSDR C8GA2011000002AControl Valve · inoperativeDURING CRUISE OPERATION AN EICAS MESSAGE APPEARED " R PACK OFF" & R ENG BLEED OFF" MESSAGES APPEARED. THE ACFT DIVERTED WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP WAS PERFORMED AND WAS RELEASED TO SERVICE, FURTHER INVESTIGATION LEAD TO THE REMOVAL ANDSDR C8GA201000058Unknown · unknownDURING TAKEOFF ROLL WITH THROTTLES ADVANCED AND EPR CALLED, THE THROTTLERS DID NOT ENGAGE FOR TAKEOFF. THE TAKEOFF WAS ABORTED. POST FLIGHT INSP WAS PERFORMED WITH NO DEFECTS NOTED. ACFT WAS RETURNED TO SERVICE.SDR ABXR201006272010Flap Track · corrodedDURING MX, THE LEFT OTBD FLAP, OTBD TRACK WAS BLEEDING RUST. UPON DISASSEMBLY, THE TRACK WAS FOUNDED CORRODED. THE CORROSION WENT BEYOND THE CMM LIMITS. MFG ENGINEERING ISSUED AN REA TO FURTHER CLEAN THE CORROSION WITH ADDITIONAL LIMITS ESTABLISHED. THE CORROSDR ABXR201006270020Skin · delaminatedDURING MX, THE BOTTOM WEDGE OF THE NR 10 SLAT WAS FOUND DELAMINATED ON INBD END. REPAIRED DELAMINATED AREA IAW THE SRM. REPAIR FOUND TO COMPLY WITH SB 757-57A0038, REV 6. ITEM RETURNED TO SERVICE.SDR ABXR201006270019Intercostal · corrodedDURING MX, INTERCOSTAL BETWEEN S29L-S30L STA 1400-1420 FOUND CORRODED. CORROSION OUTSIDE OF SRM LIMITS. REMOVED AND FABRICATED NEW INTERCOSTAL WITH 7075 T-6 0.032". REINSTALLED INTERCOSTAL IAW THE SRM. ITEM RETURNED TO SERVICE.SDR ABXR201006270018Frame · corrodedDURING MX, THE LT WING AILERON WAS FOUND DELAMINATED. REMOVED CONDUCTIVE FRAME. FABRICATED NEW FRAME FROM 6061 T4 0.020" AND INSTALLED FRAME IAW THE SRM. REMOVED FIBERGLASS ISOLATION PLY, NO FURTHER DAMAGE NOTED. REPLACED ISOLATION PLY. PREPPED AND PAINTED ASDR ABXR201006270017Floorbeam · crackedDURING MX, A FLOOR SUPPORT LBL 46-LBL 62 BS 1060 FOUND CRACKED. ISSUED FOR FABRICATION INSTRUCTIONS. FABRICATED THE CRACKED FLOOR SUPPORT/INTERCOSTAL FROM 7075-0 0.050" HAND HEAT TREATED. REINSTALLED INTERCOSTAL AND ITEM RETURNED TO SERVICE.SDR ABXR201006270016Support Fitting · corrodedDURING MX, CORROSION WAS FOUND ON A SEAT TRACK SUPPORT FITTING (CHORD). CORROSION WAS FOUND OUT OF SRM LIMITS. ISSUED WITH GREATER CLEANUP ALLOWED. ITEM RETURNED TO SERVICE.SDR ABXR201006270015Attach Fitting · corrodedDURING MX, CORROSION WAS FOUND ON A FLOOR PANEL ATTACH CHORD ADJACENT TO NUTPLATES. THE CORROSION WAS BEYOND MFG LIMITS AND THE DAMAGE CHORD REMOVED. FABRICATED NEW CHORD FROM EXTRUSION BAC 1506-1108 EXTRUSION. INSTALLED THE NEW CHORD SECTION IAW THE SRM. ITEMSDR ABXR201006270014Frame · corrodedDURING MX, CORROSION WAS FOUND ON THE FLC AFT BULKHEAD LOWER CTR FRAME. CUTOUT CORROSION DAMAGE AND REPAIRED DAMAGE IAW THE SRM USING 7075 T6 0.050" AND 7075-T6 0.063". ITEM RETURNED TO SERVICE.SDR ABXR201006270013Floor Support · corrodedDURING A MAINTENANCE INSPECTION EVENT, CORROSION WAS FOUND ON A FLOOR SUPPORT ANGLE AT FS 780 BL0. THE CORROSION WAS FOUND BEYOND LIMITS. FABRICATED A NEW SUPPORT ANGLE FROM 7075-0, 0.063". HEAT TREATED ANGLED. CORROSION TREATED ANGLE AND REINSTALLED. ITEM RETSDR ABXR201006270012Floor Support · corrodedDURING A MX, CORROSION WAS FOUND ON A FLOOR SUPPORT ANGLE AT FS 780 LBL 6. THE CORROSION WAS FOUND BEYOND LIMITS. FABRICATED A NEW SUPPORT ANGLE FROM 7075-0, 0.063". HEAT TREATED ANGLED. CORROSION TREATED ANGLE AND REINSTALLED. ITEM RETURNED TO SERVICE.SDR ABXR201006220005Skin · corrodedDURING A HEAVY MX INSP EVENT, THE FUSELAGE SKIN WAS FOUND BULGED AT STA 1460 BETWEEN STRINGERS 27L & 30L. DEFECT WAS FOUND TO BE CORROSION ON THE STRINGERS AND INTERCOSTAL. R & R STRINGERS, FABRICATED INTERCOSTAL AND INSTALLED IAW SRM. ITEM WAS RETURNED TO SERSDR ABXR201006210004Stringer · corrodedDURING A HEAVY MX INSP EVENT THE FUSELAGE SKIN WAS BULGED AT STATION 1466, STRINGER 29L. DEFECT WAS FOUND TO BE CORROSION OF THE STRINGER AND INTERCOSTAL BETWEEN STA 1400 AND STA 1420. R & R STRINGER, FABRICATED INTERCOSTAL AND INSTALLED. ITEM WAS RETURNED TO SDR ABXR20100621005Skin · corrodedDURING A HEAVY MX INSP EVENT CORROSION BETWEEN STR 29L AND THE FUSELAGE SKIN AT STA 1467. THE UNDERLYING SKIN WAS ALSO CORRODED RESULTING IN A 2.4"LONG X 1.0" WIDE CUT OUT LOCATED AT STA 1467, S29L. AN ADDITIONAL SKIN CUT OUT WAS REQUIRED AT STA 1484, S29L THSDR C8GA20090195Shutoff Valve · malfunctionedFLT 165 FROM MIA TO TOL WHILE CLIMBING THROUGH FL340 EICAS MSG "L" ENGINE BLEED OFF CAUTION APPEARED. WHILE PERFORMING APPROPRIATE PROCEDURES THE EICAS "R" ENGINE BLEED OFF CAUTION LIGHT APPEARED. APPROPRIATE PROCEDURES WERE PERFORMED AND AN EMERGENCY WAS DECLSDR C8GA20090177Bleed Valve · crackedDURING CLIMB OUT THE NR 2 ENG EXCEEDED THE EGT LIMIT OF 657 DEG FOR 16 SEC THIS DID NOT OCCUR DURING A SURGE. ACFT RETURNED TO DEPARTURE WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP WAS PERFORMED. THE 14TH STAGE BLEED VALVE WAS REMOVED AND REPLACED PN 5SDR DL757090865Acoustic Panel · delaminatedDURING SHOP VISIT, LARGE DELAMINATIONS WERE FOUND ON THE PN 314N3011-170, ENGINE INLET ACOUSTIC PANEL, REQUIRING REPLACEMENT OF THE DELAMINATED SKINS. REPAIRED IAW ERA 474812-14.SDR C8GA20080032Engine · damagedFLT 201 FROM MIA TO CCS - AFTER TAKEOFF WITH FLAPS RAISED APPROX 1800 FEET AND CLIMB THRUST SELECTED, 3 QUICK COMPRESSOR STALLS WERE HEARD AND FELT FROM THE NR 1 ENGINE. APPROPRIATE CHECKLIST WAS PERFORMED, EMERGENCY WAS DECLARED AND THE AIRCRAFT RETURNED TO SDR C8G2008F00007Door · out of adjustDURING CLIMB OPERATION THE FWD ENTRY DOOR EICAS MESSAGE APPEARED WITH THE ASSOCIATED OVERHEAD LIGHT. THE ACFT RETURNED WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSP REVEALED THAT THE FWD ENTRY DOOR WAS NOT CENTERED IN THE DOOR FRAME WHEN CLOSED. THE FWSDR C8G2008F00004Hinge · damagedDURING CLIMB OPERATION THE FWD ENTRY DOOR EICAS MESSAGE APPEARED WITH THE ASSOCIATED OVERHEAD LIGHT. THE AC RETURNED TO DEPARTURE WHERE IT LANDED WITHOUT INCIDENT. POST FLIGHT INSPECTION REVEALED THAT THE FWD ENTRY DOOR WAS NOT CENTERED IN THE DOOR FRAME WHESDR C8GA20080017Eec · malfunctionedFLT P0002 FROM PTY TO MFA. DURING CLIMB OPERATION OIL PSI WENT TO -4, N1=0, N2=0 ENG SHUTDOWN. ACFT RETURNED TO PTY WHERE IT LANDED WITHOUT INCIDENT. TROUBLESHOT SYSTEM AND FOUND EEC TO BE AT FAULT. REMOVED AND REPLACED EEC, OPS CHECKS GOOD. NO FURTHER DE
Back to N620DL