# Service difficulty reports: N411FE, cancelled Apr 23, 2020

A list on [N411FE, cancelled Apr 23, 2020](https://openairdocs.org/deregistered/N411FE-2020-04-23.md).

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

Page 1 of 2 · 62 reports

- [SDR FDEA201111225002](https://openairdocs.org/sdr/FDEA201111225002.md): Duct · leaking · Nov 22, 2011 · N411FE · Airbus A310203 · Air Intake Anti/De-Ice System
  > DURING CLIMB ECAM ALERT RECEIVED FOR NR 1 BLEED LEAK COMPLIED WITH ECAM QRH. DIVERTED TO AVOID ICING. REMOVED AND REPLACED NR 1 SYS ANTI-ICE DUCT IN PYLON PER AMM 20-26-00-000. PERFORMED LEAK CHECK WITH APU AIR, FOUND NO LEAKS AT DUCT. ACFT OK FOR SERVICE
- [SDR FDEA201111225003](https://openairdocs.org/sdr/FDEA201111225003.md): Warning Light · illuminated · Nov 22, 2011 · N411FE · Airbus A310203 · Pneumatic Distribution System
  > DURING CLIMB, ECAM ALERT RECEIVED FOR NR 1 BLEED LEAK, COMPLIED WITH ECAM QRH. DIVERTED TO AVOID ICING. OPEN
- [SDR FDEA201108243464](https://openairdocs.org/sdr/FDEA201108243464.md): Bellcrank · failed · Aug 24, 2011 · N411FE · Airbus A310203 · Landing Gear Retraction/Extension System
  > DURING LANDING GEAR FREE FALL EXTENTION TEST PROCEDURES, THE LT AND RT MLG FAILED TO EXTEND AFTER HANDLE REACHED MAXIMUM ALLOWABLE TURNS OF 20.5. REMOVED AND REINSTALLED FLOOR PANELS FOR ACCESS IAW AMM 53-23-04. R & R FREE FALL CONTROL BELL CRANK IAW SRM 51-
- [SDR FDEA201108243463](https://openairdocs.org/sdr/FDEA201108243463.md): Skin · corroded · Aug 24, 2011 · N411FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > CENTER WING BOX LT FR 49 HAS OXIDATION AT UPPER SURFACE BETWEEN STR 27-28. BELOW SEAT TRACK 6L DEFECT MEASURES 8 SQ INCHED IN THE CORNER. CLEANED UPPER SURFACE OF CWT BOX FR 49 STR 27-28 AT ST 6L IAW SRM 51-74-10. R & R FASTENER IAW SRM 51-40-21. REMOVED A
- [SDR FDEA201108243458](https://openairdocs.org/sdr/FDEA201108243458.md): Attach Fitting · corroded · Aug 24, 2011 · N411FE · Airbus A310203 · Fuselage Main, Attach Fittings
  > CTR WING BOX BETWEEN SEAT TRACK L5-L6 HYD LINES ATTACHMENT FITTING CORRODED FR 49-50. CLEANED 6 EA LINES AND FITTING FOUND TO BE OUT OF LIMIT IAW AMM 12-21-12-02 R & R 6EA FITTING IAW 51-40-10 PRESSURE AND LEAK CK SATISFACTORY IAW AMM29 10-00-04.
- [SDR FDEA201108153281](https://openairdocs.org/sdr/FDEA201108153281.md): Fitting · failed · Aug 15, 2011 · N411FE · Airbus A310203 · Landing Gear Door Retract Section
  > NLG LEG DOOR LOWER RT ATTACHMENT FORK BROKEN. R & R NLG LEG DOOR RT FITTING AND ATTACHMENT FORK,OPS CHECKED GOOD ALL IAW 32-22-15-04.
- [SDR FDEA201108133264](https://openairdocs.org/sdr/FDEA201108133264.md): Floor Panel · delaminated · Aug 13, 2011 · N411FE · Airbus A310203 · Fuselage Floor Panel
  > FLOOR PANEL 242UJ HAS IMPACT DAMAGE. CUTOUT DAMAGE, & FABRICATED REPLACEMENT FLOOR PANEL 242UJ IAW DWG SRZ 25-005, REV J.
- [SDR FDEA201108123247](https://openairdocs.org/sdr/FDEA201108123247.md): Adapter · failed · Aug 12, 2011 · N411FE · Airbus A310203 · Fuselage Main, Attach Fittings
  > CLEVIS ADAPTOR AT FRAME 43 BETWEEN SEAT TRACKS 2R AND 3R BROKEN. REMOVED AND REPLACED CLEVIS ADAPTOR AT FRAME 43 BETWEEN SEAT TRACKS 2R AND 3R IAW SRM 51-40-21 & 51-72-10.
- [SDR FDEA201107273001](https://openairdocs.org/sdr/FDEA201107273001.md): Spring · bent · Jul 27, 2011 · N411FE · Airbus A310203 · Landing Gear Retraction/Extension System
  > LT MLG 2 DOWNLOCK SPRINGS BENT. REPLACED BENT SPRINGS LT MAIN GEAR LOCK LINK IAW AMM 32-11-19-04.
- [SDR FDEA201107273000](https://openairdocs.org/sdr/FDEA201107273000.md): Spring · bent · Jul 27, 2011 · N411FE · Airbus A310203 · Landing Gear Retraction/Extension System
  > RT MLG DOWNLOCK SPRINGS (2 EA) BENT. REPLACED BENT SPRINGS FOR RT MLG LOCK LINK IAW AMM 32-11-19-04.
- [SDR FDEA201011034246](https://openairdocs.org/sdr/FDEA201011034246.md): Switch · failed · Nov 3, 2010 · N411FE · Airbus A310203 · Landing Gear Position and Warning
  > ON DEPARTURE RECEIVED LANDING GEAR RETRACTION FAULT. DOWN AND LOCKED "GREEN" LIGHTS NEVER WENT OUT. FOUND ACFT IN SYS 2 ON ARRIVAL. TALKED TO CAPTAIN OF INBD FLIGHT. TRIED SYS NR1 AS WELL AS SYS NR 2. NO RETRACTION OF LANDING GEAR. ACFT IAW MM 07-11-00-00
- [SDR FDEA201009303801](https://openairdocs.org/sdr/FDEA201009303801.md): Fitting · corroded · Sep 30, 2010 · N411FE · Airbus A310203 · Fuselage Main, Attach Fittings
  > 134AR ACCESS DOOR SURROUNDING INTEGRAL FITTING FOUND CORROSION (FR23- 24, STGR49R-STGR54L) REMOVE CORROSION IAW SRM 51-74-10. MEASURE THE REMAINING THICKNESS IAW NTM51-10-04 AND NTM51-10-08 CHECK FOR CRACK. MAKE THE REPAIR PARTS IAW SRM53-13-12-201 REPAIR
- [SDR FDEA201009293798](https://openairdocs.org/sdr/FDEA201009293798.md): Fitting · corroded · Sep 29, 2010 · N411FE · Airbus A310203 · Fuselage Main, Attach Fittings
  > 136 AR ACCESS DOOR SURROUNDING INTEGRAL FITTING FOUND CORROSION (FR38.1- FR38.2, STGR49R-STGR54L) REMOVE CORROSION IAW SRM51-74-10. MEASURE THE REMAINING THICKNESS IAW NTM51-10-04 AND NTM51-10-08 CHECK FOR CRACK. MAKE THE REPAIR PARTS IAW SRM53-14-12-201 RE
- [SDR FDEA201009273730](https://openairdocs.org/sdr/FDEA201009273730.md): Beam · cracked · Sep 27, 2010 · N411FE · Airbus A310203 · Fuselage Main, Structure
  > LT AFT CREW DOOR FRAME FR73A TO FR75A, STRINGER 11 LONGITUDINAL BEAM NDT FOUND CRACK INDICATION FROM 5 FASTENER HOLES. REMOVE THE COVER PLATE AND DOOR FRAME BEAM IAW SRM51-40-21. DRILL FASTENER HOLES ON THE NEW PART IAW SRM51-40-40. INSTALL THE NEW PART AND
- [SDR FDEA201009273729](https://openairdocs.org/sdr/FDEA201009273729.md): Frame · damaged · Sep 27, 2010 · N411FE · Airbus A310203 · Fuselage Main, Frame
  > 2 DISTORTIONS FOUND ON FR54.2 FRAME BETWEEN STGR13L-15L 1.CUT OUT THE DAMAGED SECTION OF FRAME 54.1 BETWEEN STGR13L-15L AND MAKE THE REPAIR PART IAW SRM53-10-13-201, PARA6 AND EA6-5310-141632. INSTALL THE REPAIR PART IAW SRM 53-10-13-201, PARA6 AND EA 6-5310-
- [SDR FDEA201009273728](https://openairdocs.org/sdr/FDEA201009273728.md): Frame · gouged · Sep 27, 2010 · N411FE · Airbus A310203 · Fuselage Main, Frame
  > GOUGE FOUND ON FR54.1 FRAME BETWEEN STGR13L-14L 1.CUT OUT THE DAMAGED SECTION OF FRAME 54.1 BETWEEN STGR13L-15L AND MAKE THE REPAIR PART IAW SRM53-10-13-201, PARA6 AND EA6-5310-141632. INSTALL THE REPAIR PART IAW SRM53-10-13-201 PARA6 AND EA6-5310-141632.
- [SDR FDEA200811144882](https://openairdocs.org/sdr/FDEA200811144882.md): Housing · broken · Nov 14, 2008 · N411FE · Airbus A310203 · Landing Gear Position and Warning
  > ON ARRIVAL INTO MEM, THE NOSE GEAR INDICATED UNSAFE ON BOTH SYSTEM 1 AND 2. COMPLIED WITH QRH AND USED THE MLG GRAVITY EXTEND CHECKLIST. WHEN THAT WAS COMPLETED THE UNSAFE WARNING REMAINED. THEN WENT DOWNSTAIRS TO VISUALLY CHECK. IT INDICATED DOWN AND LOCK
- [SDR 08FDEA04882](https://openairdocs.org/sdr/08FDEA04882.md): Housing · cracked · Nov 14, 2008 · N411FE · Airbus A310203 · Landing Gear Position and Warning
  > ON ARRIVAL, NOSE GEAR INDICATED UNSAFE ON BOTH SYSTEM 1 AND 2. COMPLIED WITH QRH AND USED MLG GRAVITY EXTEND CHECKLIST. WHEN COMPLETED UNSAFE WARNING REMAINED, VISUALLY CHECKED. INDICATED DOWN AND LOCKED. LANDED WITH INDICATION. FOUND SWITCH 40 GB HOUSING B
- [SDR 07FDEA03423](https://openairdocs.org/sdr/07FDEA03423.md): Transmitter · malfunctioned · Sep 5, 2007 · N411FE · Airbus A310203 · Hydraulic Quantity Sensor
  > DURING CRUISE, GREEN HYDRAULICS SHOWED "0" PRESSURE AND "LO RSVR QUANTITY" ON ECAM. QUANTITY CONFIRMED ON OVERHEAD PANEL. DIVERTED TO ATL. DURING MANUAL GEAR EXTENSION, QUANTITY RETURNED TO GREEN BAND (BELOW TOP HAT). INSTALLED ALL THREE GEAR PINS IN AIRCR
- [SDR 07FDEA03392](https://openairdocs.org/sdr/07FDEA03392.md): Transmitter · leaking · Sep 5, 2007 · N411FE · Airbus A310203 · Hydraulic Quantity Sensor
  > DURING CRUISE, GREEN HYDRAULICS SHOWED "0" PRESSURE AND "LO RSVR QUANTITY" ON ECAM. QUANTITY CONFIRMED ON OVERHEAD PANEL. DURING MANUAL GEAR EXTENSION, QUANTITY RETURNED TO GREEN BAND (BELOW TOP HAT). FOUND HYD PRESSURE TRANSMITTER IN LT WHEEL WELL LEAKING.
- [SDR 07FDEA01653](https://openairdocs.org/sdr/07FDEA01653.md): Skin · misrepaired · Apr 27, 2007 · N411FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > PREVIOUS REPAIR LOCATED ON R/SIDE FUSELAGE SKIN BETWEEN FR 66 TO 67 BETWEEN STR 35TO 38 RT HAS AN EXTERNAL REPAIR DOUBLER MEASURING 8.8 BY 11.9. REPAIR REVIEWED AND FOUND NOT TO BE IAW A310-200 SRM 53-10-12 FIG 226 SHEET 2. REWORKED REPAIR IAW A310-200 SRM 5
- [SDR 07FDEA01655](https://openairdocs.org/sdr/07FDEA01655.md): Skin · misrepaired · Apr 27, 2007 · N411FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > PREVIOUS REPAIR LOCATED ON L-SIDE FUSELAGE SKIN BETWEEN FR 21-22 BETWEEN STR 34-36 LT AT LAP SEAM HAS AN EXTERNAL DOUBLER MEASURING 6.25 BY 9 IN REPAIR DETERMINED NOT TO BE IAW A310-200 SRM 53-10-12 FIG 205, REPAIR REWORKED IAW A310-200 SRM EA 6-5330-110187.
- [SDR 07FDEA01241](https://openairdocs.org/sdr/07FDEA01241.md): Floorbeam · cracked · Apr 2, 2007 · N411FE · Airbus A310203 · Fuselage Main, Floor Beam
  > 1 CRACK EXIST IN FLOORBEAM VERTICAL STIFFENER AT FR 36 BETWEEN SEAT TRACK L4 AND L5, MEASURING 0.450" P/N 537B1041000 A310-200 AMM 53-10-15-6. REMOVED 1 CRACK IN FLOORBEAM VERTICAL STIFFENER AT FRAME 36 BETWEEN SEAT TRACK L4 AND L5 IAW A310-200 SRM 53-10-15 F
- [SDR 07FDEA01185](https://openairdocs.org/sdr/07FDEA01185.md): Floorbeam · cracked · Mar 29, 2007 · N411FE · Airbus A310203 · Fuselage Main, Floor Beam
  > 1 CRACK EXIST IN FLOORBEAM VERTICAL STIFFENER AT FRAME 36 BETWEEN SEAT TRACK L2 AND L3 MEASURING.5" REF R537B1041000 A310-200 AMM 53-10-15-6. REMOVED CRACK PER A310 SRM SUPP 53-10-15 FIG 201. NDT C/W PER NTM 51-10-08, NO CRACK INDICATIONS NOTED. FABBED RE
- [SDR 07FDEA01184](https://openairdocs.org/sdr/07FDEA01184.md): Floorbeam · cracked · Mar 29, 2007 · N411FE · Airbus A310203 · Fuselage Main, Floor Beam
  > 1 CRACK FOUND.75" IN UPPER SUPPORT LEG ON AFT SIDE OF FLOORBEAM FR 58 BETWEEN SEAT TRACK 4L AND 5L EXTENDING INTO FLOORBEAM WEBBING UNDER CLS ADAPTER IAW A310-200 AMM 53-16-11-6. REMOVED DAMAGED AREA AND REPAIRED IAW AB DWG R53270150 AND EA 6-5310-107708.
- [SDR 07FDEA01080](https://openairdocs.org/sdr/07FDEA01080.md): Floorbeam · cracked · Mar 22, 2007 · N411FE · Airbus A310203 · Fuselage Main, Floor Beam
  > FORWARD CARGO COMPARTMENT, FLOORBEAM (C25) FORWARD FACE OF BEAM LOCATED BETWEEN R2 AND R3 SEAT TRACK HAS A.400 INCH CRACK IN VERTICAL STIFFENER. REPAIRED FLOORBEAM IAW A310/200 SRM SUPPLEMENT 53-10-15. REMOVED AND REINSTALLED FLOORBOARD IAW A310/200 AMM SUP
- [SDR 07FDEA01078](https://openairdocs.org/sdr/07FDEA01078.md): Floorbeam · cracked · Mar 22, 2007 · N411FE · Airbus A310203 · Fuselage Main, Floor Beam
  > FWD CARGO COMPARTMENT, OVER HEAD FLOORBEAM [ C34 ] FWD FACE OF BEAM, LOCATED BETWEEN L4 AND L5 SEAT TRACK HAS A 0.425 INCH CRACK IN VERTICAL STIFFENER. REMOVED AND REINSTALLED FLOOR BOARD 231KF AND 231QF TO FOM REPAIR IAW A310-200 AMM 53-10-25-4. REPAIRED F
- [SDR 07FDEA01076](https://openairdocs.org/sdr/07FDEA01076.md): Track · misrepaired · Mar 22, 2007 · N411FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > PREVIOUS REPAIR LOCATED ON AFT CARGO ROLLER TRACK LEFT NR 2 HAS A 9 INCH LONG REPAIR SECTION WITH 2 REPAIR ANGLES ON THE OUTBD SIDE MEASURING 7 INCH LONG EACH BETWEEN FRAMES 54.3 TO55/58 PREVIOUSLY INSTALLED REPAIR WAS DETERMINED NOT TO BE IAW A310 SRM 53-1
- [SDR 06FDEA04243](https://openairdocs.org/sdr/06FDEA04243.md): Control Unit · malfunctioned · Dec 14, 2006 · N411FE · Airbus A310203 · Landing Gear Brake System
  > ON CLIMB-OUT, AUTO BRAKE FAIL LIGHT CAME ON, LIGHT STAYED ON UNTIL LEVEL OFF AND THEN AFTER A PERIOD OF TIME THE LIGHT WENT OUT. LIGHT THEN CAME ON AFTER A PERIOD OF TIME. CYCLE REPEATED ITSELF OFF AND ON SEVERAL TIMES. PERFORMED BITE TEST ON BSCU FAULT COD
- [SDR 06FDEA2663](https://openairdocs.org/sdr/06FDEA2663.md): Pitot Tube · dirty · Jul 23, 2006 · N411FE · Airbus A310 · Pitot/Static System
  > RIGHT AFTER ROTATION BOTH ATS LEVERS DROPPED OFF. ADC FAILED ON CAPT SIDE SWITCHED OVER TO OTHER SYSTEM REENGAGED ATS LEVERS AS PER ECAM THROTTLE RETARDED TO IDLE AS SOON AS ATHR BUTTON PUSHED. NO ECAM FOR ADC. ALSO NR 1 FLT DIRECTOR FAILED. CAPTS ALTIMETE
- [SDR 06FDEA2659](https://openairdocs.org/sdr/06FDEA2659.md): Adc · failed · Jul 22, 2006 · N411FE · Airbus A310 · Air Data Computer
  > JUST AFTER ROTATION BOTH ATS LEVERS DROPPED OFFLINE AND WOULD NOT RESET. YAW DAMP DROPPED OFF, WOULD NOT RESET. CAPTS PFD, ADC FAILED. SWITCHED OVER TO F/O SYSTEM. HAD NUMEROUS AIRSPEED WINDSHEAR VMO MMO WARNINGS EVEN THOUGH USING STBY SYSTEMS. AT THAT PO
- [SDR 06FDEA1782](https://openairdocs.org/sdr/06FDEA1782.md): Computer · faulted · May 11, 2006 · N411FE · Airbus A310203 · Rudder Control System
  > ON T/O AT LAX, DID A RTO AT 90 KTS THE ECAM ALERT WAS BOTH PITCH 1/2 AND BOTH RUDDERS 1/2 FAULTED. REMOVED AND REPLACED NR 1 AND NR 2 FEEL LIMITATION COMPUTERS PER M/M 27-23-26-4. OPS CK'S NORMAL. PERFORMED AFTER BRAKE OVERHEAT INSP REF MM 05-51-16-0-01.
- [SDR 05FDEA04399](https://openairdocs.org/sdr/05FDEA04399.md): Indicator · smoke · Dec 22, 2005 · N411FE · Airbus A310203 · Rudder Tab Control System
  > N CRUISE BURNING SMELL IN COCKPIT, DIVERTED AND LANDED. STRONGEST SMELL FROM THROTTLE QUADRANT AREA, FIRE CREW TEMP DETECTOR SHOWED HIGHEST HEAT IN THAT LOCATION. NEVER ANY VISIBLE SPARKS OR FLAMES, SOME SMOKE. INSPECTED THROTTLE QUADRANT AREA AND FOUND THE
- [SDR 05FDEA01899](https://openairdocs.org/sdr/05FDEA01899.md): Access Panel · damaged · Jul 12, 2005 · N411FE · Airbus A310 · Wing, Plate/Skin
  > ACCESS PANEL 650GB HAS 1 ELONGATED HOLE, COMPLIED WITH EA6-5710-90863.
- [SDR 05FDEA01898](https://openairdocs.org/sdr/05FDEA01898.md): Access Panel · damaged · Jul 12, 2005 · N411FE · Airbus A310 · Wing, Plate/Skin
  > ACCESS PANEL 650 FB HAS 1 ELONGATED HOLE, COMPLIED WITH EA6-5710-90863.
- [SDR 04FDEA02798](https://openairdocs.org/sdr/04FDEA02798.md): Angle · corroded · Sep 21, 2004 · N411FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > BULK CARGO COMPT FLOOR STRUCTURE FS 67 2EA AREAS OF CORROSION NOTED ON TOP AND BOTTOM SURFACES. REMOVED AND REPLACED PROFILE ANGLE IAW A310 SRM 51-40-21.
- [SDR 04FDEA02797](https://openairdocs.org/sdr/04FDEA02797.md): Floorbeam · corroded · Sep 21, 2004 · N411FE · Airbus A310203 · Fuselage Main, Floor Beam
  > BULK CARGO COMPT FLOOR STRUCTURE FS 65 ON LT SIDE, MID AND RT SIDE AREA NOTED CORROSION ON TOP AND UNDERNEATH SURFACES. REMOVED AND REPLACED BEAM IAW A310 SRM 53-10-15.
- [SDR 04FDEA02796](https://openairdocs.org/sdr/04FDEA02796.md): Seat Track · corroded · Sep 21, 2004 · N411FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > MDCC SEAT TRACK L4 FRAME 74-80 HAS 5EA CORRODED AREAS. REPAIRED SEAT TRACK BY SPLICING IAW A310 SRM 51-22-00, 51-40-21 AND 53-10-16.
- [SDR 04FDEA02795](https://openairdocs.org/sdr/04FDEA02795.md): Floorbeam · corroded · Sep 21, 2004 · N411FE · Airbus A310 · Fuselage Main, Floor Beam
  > AFT CARGO COMPT FS 63 FLOOR STRUCTURE, ON LEFT SIDE 3EA AREAS OF CORROSION ON TOP SURFACE AND UNDERNEATH FLOOR STRUCTURE. REMOVED AND REPLACED FLOOR STRUCTURE BEAM IAW A310 SRM 51-40-21.
- [SDR 04FDEA02794](https://openairdocs.org/sdr/04FDEA02794.md): Structure · corroded · Sep 21, 2004 · N411FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > AFT CARGO COMPT FWD OF FS 54.2 BILGE AREA NOTED SPOT OF CORROSION AROUND THE HOLE PLUG. REPAIRED BILGE AREA IAW EA 6-5330-55370.
- [SDR 04FDEA02793](https://openairdocs.org/sdr/04FDEA02793.md): Seat Track · corroded · Sep 21, 2004 · N411FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > MDCC SEAT TRACK R1 BETWEEN FRAME 73-80 HAS 7EA DISCREPANT AREAS 5EA AREAS THAT ARE CORRODED AND GOUGED AND 2EA AREAS THAT ARE GOUGED. REMOVED AND REPLACED R1 SEAT TRACK FRAME 73-80 IAW A310 SRM 51-40-21 AND SRM 53-10-16.
- [SDR 04FDEA02724](https://openairdocs.org/sdr/04FDEA02724.md): Seat Track · cracked · Sep 17, 2004 · N411FE · Airbus A310 · Fuselage, Seat/Cargo Attach Fittings
  > MDCC SEAT TRACK SECTION AT R2, BETWEEN FR54 TO 8 INCHES AFT OF FR54.1 HAS DAMAGE TO THE SCALLOP LUGS. (ON EDGES AND BENEATH LUGS) REMOVED DAMAGE AND FOUND TO BE CRACKED IAW SRM 51-73-10. REMOVED AND REPLACED SEAT TRACK IAW SRM 51-40-21.
- [SDR 04FDEA02698](https://openairdocs.org/sdr/04FDEA02698.md): Floorbeam · cracked · Sep 16, 2004 · N411FE · Airbus A310203 · Fuselage Main, Floor Beam
  > FWD CARGO FLOORBEAM STRUCTURE FR33 NOTED INDICATION OF CRACK. REMOVED DAMAGED AREA IAW A310 SRM 53-10-15, AND REPAIRED BY INSTALLING A DOUBLER IAW A310 SRM 53-10-15.
- [SDR 04FDEA02697](https://openairdocs.org/sdr/04FDEA02697.md): Adapter · cracked · Sep 16, 2004 · N411FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > TRACK ADAPTER AT FR61 Y-450 IS CRACKED APPROX 6 INCHES LONG. REMOVED AND REPLACED TRACK ADAPTER IAW A310 SRM 51-40-21.
- [SDR 04FDEA02696](https://openairdocs.org/sdr/04FDEA02696.md): Adapter · cracked · Sep 16, 2004 · N411FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > TRACK ADAPTER AT FR61 Y-450 IS CRACKED APPROX 6 INCHES LONG. REMOVED AND REPLACED TRACK ADAPTER IAW A310 SRM 51-40-21.
- [SDR 04FDEA02695](https://openairdocs.org/sdr/04FDEA02695.md): Seat Track · gouged · Sep 16, 2004 · N411FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > SEAT TRACK AT FR 36 AFT APPROX 8 INCHES IS GOUGED. BLENDED AREA PER A310 SRM 51-22-00 AND FOUND TO BE OUT OF LIMITS PER A310 SRM 53-10-16. REPAIRED BY REMOVING DAMAGED SECTION OF TRACK AND SPLICING IN A REPAIR SECTION PER A310 SRM 51-40-21 AND 53-10-16.
- [SDR 04FDEA02694](https://openairdocs.org/sdr/04FDEA02694.md): Seat Track · corroded · Sep 16, 2004 · N411FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > SEAT TRACK 0, SECTION BETWEEN FR73 TO FR80 HAS TWO DISCREPANT AREAS. TRACK 0 AT APPROX 12 INCHES AFT FROM FR 77 HAS 2 GOUGES INSIDE OF SCALLOPED AREA. TRACK 0 APPROX 10 INCHES AFT OF FR78 HAS CORROSION ON TOP OF TRACK AND IN SCALLOPED AREA. REMOVED CORROSIO
- [SDR 04FDEA02693](https://openairdocs.org/sdr/04FDEA02693.md): Floorbeam · cracked · Sep 16, 2004 · N411FE · Airbus A310203 · Fuselage Main, Floor Beam
  > BULK CARGO COMPT FLOOR STRUCTURE ON FR67 AT RT SIDE CORNER UNDERNEATH NOTED CRACK. REMOVED AND REPLACED BEAM IAW A310 SRM 51-40-21.
- [SDR 04FDEA02692](https://openairdocs.org/sdr/04FDEA02692.md): Floor Support · corroded · Sep 16, 2004 · N411FE · Airbus A310 · Fuselage Miscellaneous Structure
  > BULK CARGO COMPT. FLOOR STRUCTURE FR66 LT SIDE, MID AND RT SIDE AREA NOTED CORROSION ON TOP AND UNDERNEATH SURFACE. REMOVED CORROSION IAW SRM 51-74-10, AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16. REMOVED AND REPLACED BEAM IAW SRM 51-40-21.**** S/D C
- [SDR 04FDEA02691](https://openairdocs.org/sdr/04FDEA02691.md): Floor Support · corroded · Sep 16, 2004 · N411FE · Airbus A310 · Fuselage Miscellaneous Structure
  > BULK CARGO COMPT. FLOOR STRUCTURE, ON RT SIDE FR 66 TO FR 63 CORROSION ON TOP AND BENEATH SURFACE. REMOVED CORROSION IAW SRM 51-70-10 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16. REMOVED AND REPLACED BEAM IAW SRM 51-40-21.**** S/D COMING ****

Next page: https://openairdocs.org/deregistered/N411FE-2020-04-23/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
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 = 'N411FE' AND deregistration_id = 'N411FE-2020-04-23'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N411FE-2020-04-23/reports

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