# Service difficulty reports: N676FE

A list on [N676FE](https://openairdocs.org/aircraft/N676FE.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 4 · 178 reports

- [SDR FDEA202603050313](https://openairdocs.org/sdr/FDEA202603050313.md): Panel · damaged · Mar 5, 2026 · N676FE · Airbus A300F4605R · Nacelle/Pylon, Plate/Skin
  > AT NR 2 PYLON INBD SIDE PANEL 415AL, HAD A LARGE CRACK. REMOVED AND REPLACED THE NR 2 PYLON INBD SIDE PANEL 415AL, NO FURTHER DEFECTS.
- [SDR FDEA202602190246](https://openairdocs.org/sdr/FDEA202602190246.md): Bar · broken · Feb 19, 2026 · N676FE · Airbus A300F4605R · Escape Slide
  > L1 DOOR SLIDE INTERNAL LOCK BAR BROKE. PREMATURE REMOVAL/INSTALLATION OFF MPN: D31023-101 POS: L1 SRL: 0371TH ON MPN: D31023-101. AMM: 25-61-21-04 REMOVED AND REPLACED L(1) DOOR SLIDE REF A300 AMM 25-61-21-04, OPERATIONAL CHECK NORMAL. A/C OK FOR SE
- [SDR FDEA202510292104](https://openairdocs.org/sdr/FDEA202510292104.md): Light · inoperative · Oct 29, 2025 · N676FE · Airbus A300F4605R · Emergency Lighting
  > L1 DOOR EMERGENCY EXIT SPOT LIGHT DOES NOT ILLUMINATE. AMM: 33-51-13-04 SERVICED L1 DOOR EMERGENCY LIGHT OPS GOOD OK FOR SVC.
- [SDR FDEA202505090732](https://openairdocs.org/sdr/FDEA202505090732.md): Skin · delaminated · May 9, 2025 · N676FE · Airbus A300F4605R · Spoilers
  > LH WING #5 SPOILER CENTER I/B & O/B HINGE ARM UPR SKIN FOUND DELAMINATION. SIZE: (1)40MM*18MM, DEPTH: 2.40MM (2)83MM*40MM, DEPTH: 2.38MM COMPLIED WITH EA: 6-5750-T0383299 P1. TITLE: WING - FLIGHT SURFACES - LH #5 SPOILER TOP SKIN UPPER SURFACE DELAMINATION
- [SDR FDEA202505040713](https://openairdocs.org/sdr/FDEA202505040713.md): Door · cracked · May 4, 2025 · N676FE · Airbus A300F4605R · Cargo/Baggage Doors
  > MAIN DECK CARGO DOOR UPR EDGE AT PT1 BETWEEN FR23 AND FR24 FOUND CRACK SIGNAL ON 3EA FASTENER HOLES COMPLIED WITH EA: 6-5230-T0383235 P1. TITLE: DOORS - CARGO DOOR/HYD SYS - CRACKED HOLES ON MAIN DECK CARGO DOOR UPPER LONGERON. REPAIRED THE MAIN DECK CARGO
- [SDR FDEA202504240640](https://openairdocs.org/sdr/FDEA202504240640.md): Crossbeam · unknown · Apr 24, 2025 · N676FE · Airbus A300F4605R · Fuselage Main, Structure
  > MAIN DECK CARGO COMPARTMENT - EXISTING CROSSBEAM REPAIR FROM Y1959 TO Y2462 BETWEEN FR54.1 AND FR54.2 REQUIRES EVALUATION TO DETERMINE IF MAJOR OR MINOR AND IF THE REPAIR CONFORMS TO FAA APPROVED DATA THE EXISTING CROSSBEAM REPAIR FROM Y1959 TO T2462 BETWE
- [SDR FDEA202504220624](https://openairdocs.org/sdr/FDEA202504220624.md): Cargo Track · broken · Apr 22, 2025 · N676FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach Fittings
  > MAIN DECK CARGO FR42-FR43 Y953 SEAT TRACK BROKEN REPLACED THE MAIN DECK CARGO BROKEN SEAT TRACK AT Y953 BETWEEN FR40 AND FR45 WITH A FABRICATED PART PER A300-600 SRM51-40-21 AND DWG A53832020(ISSUE: G). THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM
- [SDR FDEA202504170609](https://openairdocs.org/sdr/FDEA202504170609.md): Floor Support · unknown · Apr 17, 2025 · N676FE · Airbus A300F4605R · Fuselage Miscellaneous Structure
  > EXISTING REPAIR ON MAIN DECK CARGO COMPARTMENT FR11 - FR13A FLOOR SUPPORT AT Y232 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR ON MAIN DECK CARGO COMPARTMENT FR11-FR13A FLOOR SUPPORT AT Y232 WAS EVALUATED AND FOUND NOT IN CONFORMITY WITH A300-60
- [SDR FDEA202504170607](https://openairdocs.org/sdr/FDEA202504170607.md): Floor Support · corroded · Apr 17, 2025 · N676FE · Airbus A300F4605R · Fuselage Miscellaneous Structure
  > MAIN DECK FR11-FR13A Y730 FLOOR SUPPORT CORRODED. REPLACED THE CORRODED FLOOR SUPPORT AT MAIN DECK FR11-FR13A Y730 WITH NEW PART PER A300-600F SRM51-40-21. THIS IS CATEGORY A REPAIR. MINOR REPAIR IAW FEDEX GMM6-2-100
- [SDR FDEA202504170606](https://openairdocs.org/sdr/FDEA202504170606.md): Skin · no discrepancy · Apr 17, 2025 · N676FE · Airbus A300F4605R · Trailing Edge Flaps
  > EXISTING REPAIR ON RH WING CENTER FLAP LOWER SKIN RIB16-RIB17 BETWEEN FRONT SPAR AND S2.3 REQUIRES EVALUATION FOR CONFORMITY. EXISTING REPAIR ON RH WING CENTER FLAP LOWER SKIN RIB16-RIB17 BETWEEN FRONT SPAR AND S2.3 WAS EVALUATED AND FOUND NOT IN CONFORMIT
- [SDR FDEA202504170605](https://openairdocs.org/sdr/FDEA202504170605.md): Skin · damaged · Apr 17, 2025 · N676FE · Airbus A300F4605R · Trailing Edge Flaps
  > EXISTING REPAIR ON RH WING CENTER FLAP LOWER SKIN RIB15-RIB18 BETWEEN S2.2 AND REAR SPAR REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR ON RH WING CENTER FLAP LOWER SKIN RIB15-RIB18 BETWEEN S2.2 AND REAR SPAR WAS EVALUATED AND FOUND NOT IN CONFOR
- [SDR FDEA202504170604](https://openairdocs.org/sdr/FDEA202504170604.md): Skin · no discrepancy · Apr 17, 2025 · N676FE · Airbus A300F4605R · Trailing Edge Flaps
  > EXISTING REPAIR ON RH WING CENTER FLAP LOWER SKIN RIB10-RIB12 BETWEEN S2.2 AND REAR SPAR REQUIRES EVALUATION FOR CONFORMITY. EXISTING REPAIR ON RH WING CENTER FLAP LOWER SKIN RIB10-RIB12 BETWEEN S2.2 AND REAR SPAR WAS EVALUATED AND FOUND NOT IN CONFORMITY
- [SDR FDEA202504160599](https://openairdocs.org/sdr/FDEA202504160599.md): Bearing · not reported · Apr 16, 2025 · N676FE · Airbus A300F4605R · Cargo/Baggage Doors
  > COMPLY WITH EO 6-5230-E0378588 B P5 FOR MAIN DECK CARGO DOOR ACTUATOR BEARING FITTINGS REPLACEMENT. COMPLIED WITH EO 6-5230-E0378588 B P5. TITLE: DOORS - CARGO DOOR/HYD SYS - DETAILED VISUAL INSPECTION OF THE MAIN DECK CARGO DOOR (MDCC) ACTUATOR BEARING FI
- [SDR FDEA202504160598](https://openairdocs.org/sdr/FDEA202504160598.md): Frame · cracked · Apr 16, 2025 · N676FE · Airbus A300F4605R · Fuselage Main, Frame
  > CENTER WING BOX - INSPECTION OF REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE FR47 RH SIDE, FASTENER "I" HOLE FOUND CRACK SIGNAL COMPLIED WITH EO 6-5710-E0342809 D P2. TITLE: WINGS - CENTER WING BOX - INSPECTION OF REAR SPAR AND BOTTOM PANEL AT JU
- [SDR FDEA202504160597](https://openairdocs.org/sdr/FDEA202504160597.md): Fitting · cracked · Apr 16, 2025 · N676FE · Airbus A300F4605R · Fuselage Main, Structure
  > CENTER WING BOX - INSPECTION OF REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE FR47 LH SIDE, FASTENER "I" HOLE FOUND CRACK SIGNAL COMPLIED WITH EO 6-5710-E0342809 D P1. TITLE: WINGS - CENTER WING BOX - INSPECTION OF REAR SPAR AND BOTTOM PANEL AT JU
- [SDR FDEA202504160596](https://openairdocs.org/sdr/FDEA202504160596.md): Hinge Arm · delaminated · Apr 16, 2025 · N676FE · Airbus A300F4605R · Spoilers
  > LH WING #3 SPOILER CENTER I/B & O/B HINGE ARM UPR SKIN FOUND DELAMINATION. SIZE: (1)14MM*7MM, DEPTH: 1.46MM (2)35MM*10MM, DEPTH: 1.56MM COMPLIED WITH EA: 6-5750-T0383024 P1. TITLE: WING - FLIGHT SURFACES - LH #3 SPOILER CENTER HINGE ARM AREA DELAMINATION.
- [SDR FDEA202504160595](https://openairdocs.org/sdr/FDEA202504160595.md): Hinge Arm · delaminated · Apr 16, 2025 · N676FE · Airbus A300F4605R · Spoilers
  > LH WING #3 SPOILER CENTER O/B HINGE ARM OUTSIDE SURFACE FOUND 2EA LOCATIONS DELAMINATION. SIZE: (1)25MM*25MM, DEPTH: 1.94MM (2)30MM*25MM, DEPTH: 1.51MM COMPLIED WITH EA: 6-5750-T0383024 P1. TITLE: WING - FLIGHT SURFACES - LH #3 SPOILER CENTER HINGE ARM ARE
- [SDR FDEA202504160594](https://openairdocs.org/sdr/FDEA202504160594.md): Seat Track · broken · Apr 16, 2025 · N676FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach Fittings
  > MAIN DECK FR33-FR34 -Y1959 SEAT TRACK BROKEN. REPAIRED THE MAIN DECK BROKEN SEAT TRACK AT -Y1959 BETWEEN FR33 AND FR34 PER A300- 600F SRM53-10-16-201 FIG.201. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2- 100
- [SDR FDEA202504150608](https://openairdocs.org/sdr/FDEA202504150608.md): Seat Track · no discrepancy · Apr 15, 2025 · N676FE · Airbus A300F4605R · Standard Practices/Structures
  > EXISTING REPAIR ON MAIN DECK CARGO COMPARTMENT FR20 - FR21 SEAT TRACK AT Y1959 REQUIRES EVALUATION FOR CONFORMITY THE EXISTING REPAIR ON MAIN DECK CARGO COMPARTMENT FR20 - FR21 SEAT TRACK AT Y1959 WAS EVALUATED AND FOUND IN CONFORMITY WITH EA: 6-5313-10250
- [SDR FDEA202308201465](https://openairdocs.org/sdr/FDEA202308201465.md): Transmitter · failed · Aug 20, 2023 · N676FE · Airbus A300* · Hydraulic Power System
  > PDIS 676 29-01 2402 19AUG23 MEM OPEN U GREEN HYD RSVR LO LEVEL ECAM MESSAGE IN CRUISE. COMPLIED WITH ECAM AND QRH PROCEDURES. DIVERTED TO MEM. GREEN HYD QUANTITY GAUGE SHOWED APPROXIMATELY 2 NEEDLE WIDTHS LOW FROM HAT. GAP GREW TO 4 NEEDLE WI
- [SDR FDEA202308081374](https://openairdocs.org/sdr/FDEA202308081374.md): Hose · leaking · Aug 8, 2023 · N676FE · Airbus A300* · Hydraulic System, Main
  > YELLOW HYD SYS LO PR ECAM CLIMBING THROUGH FL260. COMPLIED WITH ECAM AND QRH. YELLOW SYSTEM RESERVOIR QUANTITY INDICATOR FLUCTUATION IN YELLOW ABOVE AND BELOW RED DOT. ECAM QUANTITY INDICATES STEADY. COORDINATED WITH GOC AND MOC VIA ATLANTA RADIO AND ACAR
- [SDR FDEA202307121742](https://openairdocs.org/sdr/FDEA202307121742.md): Fitting · corroded · Jul 12, 2023 · N676FE · Airbus A300F4605R · Standard Practices/Structures
  > CORROSION FOUND IN THE RIB 5 FITTING. REPAIR PER AIRBUS REPAIR INSTRUCTIONS R57240425
- [SDR FDEA202301190138](https://openairdocs.org/sdr/FDEA202301190138.md): Crossbeam · cracked · Jan 19, 2023 · N676FE · Airbus A300F4605R · Fuselage Main, Structure
  > MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR64, BETWEEN Y1456 AND Y1959. REPAIRED THE CRACKED CROSSBEAM IN THE MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE AT FR64 BETWEEN Y1456 AND Y1959 PER A300-600F SRM53-10-15-201 PARA.14.
- [SDR FDEA202301190137](https://openairdocs.org/sdr/FDEA202301190137.md): Crossbeam · cracked · Jan 19, 2023 · N676FE · Airbus A300F4605R · Fuselage Main, Structure
  > MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR61, BETWEEN -Y1456 AND -Y1959. REPAIRED THE CRACKED CROSSBEAM IN THE MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE AT FR61 BETWEEN -Y1456 AND -Y1959 PER A300-600F SRM53-10-15-201 PARA.14.
- [SDR FDEA202301190136](https://openairdocs.org/sdr/FDEA202301190136.md): Crossbeam · cracked · Jan 19, 2023 · N676FE · Airbus A300F4605R · Fuselage Main, Structure
  > MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR32, BETWEEN -Y450 AND -Y953. COMPLIED WITH EA: 6-5310-T0372499 P1. MAJOR REPAIR IAW FEDEX GMM6-2-100
- [SDR FDEA202301190135](https://openairdocs.org/sdr/FDEA202301190135.md): Crossbeam · cracked · Jan 19, 2023 · N676FE · Airbus A300F4605R · Fuselage Main, Structure
  > MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR31, BETWEEN -Y450 AND -Y953. COMPLIED WITH EA: 6-5310-T0372501 P1. MAJOR REPAIR IAW GMM6-2-100
- [SDR FDEA202301190134](https://openairdocs.org/sdr/FDEA202301190134.md): Crossbeam · cracked · Jan 19, 2023 · N676FE · Airbus A300F4605R · Fuselage Main, Structure
  > MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR28, BETWEEN -Y450 AND -Y953. COMPLIED WITH EA: 6-5310-T0372502 P1. MAJOR REPAIR IAW GMM6-2-100
- [SDR FDEA202301090053](https://openairdocs.org/sdr/FDEA202301090053.md): Unknown · unknown · Jan 9, 2023 · N676FE · Airbus A300* · Hydraulic Power System
  > EMERGENCY DECLARED: RECEIVED GREEN HYD LOW LVL. COMPLIED WITH ECAM AND QRH DECLARED EMERGENCY AND PERFORMED LANDING GEAR GRAVITY EXTEND. 1. PER AMM 29-21-00-03 PRESSURED THE GREEN HYD SYS AND CHECK THE LEAKAGE. RESULT: LEAKAGE FOUND AT THREE POSITIONS. (1)
- [SDR FDEA202301080051](https://openairdocs.org/sdr/FDEA202301080051.md): Transmission · inoperative · Jan 8, 2023 · N676FE · Airbus A300* · Hydraulic Power System
  > EMERGENCY DECLARED RECEIVED GREEN HYD LOW LVL. COMPLIED WITH ECAM AND QRH DECLARED EMERGENCY AND PERFORMED LANDING GEAR GRAVITY EXTEND. PRESS'D THE GRN HYD SYS AND CK THE LEAKAGE. FOUND LEAK AT 3 POSITON.1) ELBOW OF GRN HYD SYS HP MAINFOLD.2) HYD LINE OF
- [SDR FDEA202212152923](https://openairdocs.org/sdr/FDEA202212152923.md): Hydraulic System · malfunctioned · Dec 15, 2022 · N676FE · Airbus A300F4605R · Hydraulic System, Main
  > AT BEGINNING OF DESCENT, RECEIVED ECAM GREEN HYD LOW LEVEL. INDICATION WAS ON THE RED. AFTER MANUALLY LOWERING MLG, GREEN QTY RETURNED TO NORMAL. EMERGENCY DECLARED. AMM 12-12-29-00, AMM 29-10-00-03, AMM: 27-00-00-05, AMM 12-14-29-00, AND JRH CH5. IN FL
- [SDR FDEA202209102718](https://openairdocs.org/sdr/FDEA202209102718.md): Skin · not reported · Sep 10, 2022 · N676FE · Airbus A300F4605R · Fuselage Main, Plate/Skin
  > CENTER SKIN SECTION NEEDS REMOVED FROM FR78.5 TO FR72 STRINGER 52L TO 52R REPLACED CENTER SKIN SECTION FROM FR72 TO FR80 STRINGER 51L TO 51R IAW E.A. 6-5330- T0370451 PART 2 STEPS 11 AND 12. THIS IS A MAJOR REPAIR. SEE JPF FOR WORK STEPS. SEE N95 FOR INSTAL
- [SDR FDEA202209092732](https://openairdocs.org/sdr/FDEA202209092732.md): Frame · dented · Sep 9, 2022 · N676FE · Airbus A300F4605R · Fuselage Main, Frame
  > FR77 CENTER FRAME AT STRINGER 47R AND 48R IS DEFORMED 0000433443: PATE, ROBERT L - 05-NOV-2022 06:14 REMOVED AND REPLACED LEFT-HAND STUB FRAME, RIGHT-HAND STUB FRAME AND CENTER MILLED FRAME SECTION AT FR77 IAW EA 6-5330-T0370451 PART 2 STEP 17 AND A300-60
- [SDR FDEA202209042699](https://openairdocs.org/sdr/FDEA202209042699.md): Skin · deformed · Sep 4, 2022 · N676FE · Airbus A300F4605R · Fuselage Main, Plate/Skin
  > SKIN DEFORMATION AT FR 77 AT STR 47R (MEASURED 0.142? TO 0.172?) REPAIRED SKIN DEFORMATION AT FR76 AND FR77 STRINGER 47R IAW EA 6-5330-T0370451 PART 2 STEPS 13 AND STEP14. THIS IS A MAJOR REPAIR.
- [SDR FDEA202209032708](https://openairdocs.org/sdr/FDEA202209032708.md): Skin · deformed · Sep 3, 2022 · N676FE · Airbus A300F4605R · Fuselage Main, Plate/Skin
  > SKIN DEFORMATION AT FR 77 AT STR 47L (MEASURED 0.082? TO 0.087?) REPAIRED SKIN DEFORMATION AT FRAME 76.5 TO FR77.5 STRINGER 47L TO 51L IAW EA 6-5330- T0370451 PART 2 STEPS 15,10 REF FIGURE 3 OF 3 FOUND IN STEPS 3. SEE N109 FOR EDGE SEALING AND PAINT SEE JPF
- [SDR FDEA202208171990](https://openairdocs.org/sdr/FDEA202208171990.md): Power Supply · failed · Aug 17, 2022 · N676FE · Airbus A300F4605R · Emergency Lighting
  > MDIS 676 33-50 1687 17AUG22 BUR FACT U COURIER AREA EMERGERNCY LIGHTING WILL NOT TEST OR TURN ON R/I 17AUG22 19:12 BUR U REASON CODE: PREMATURE REMOVAL/INSTALLATION OFF MPN: AD-3214-30 POS: 3 SRL: 59192 ON MPN
- [SDR FDEA202110182558](https://openairdocs.org/sdr/FDEA202110182558.md): None · none · Oct 18, 2021 · N676FE · Airbus A300* · Engine Fuel and Control
  > PDIS 676 73-35 0791 18OCT21 OKC OPEN U IN CRUISE FLIGHT AT FL340 ABOUT AN HOUR AFTER TAKEOFF WE GOT ECAM WARNING OF ENG #1 FUEL FILTER CLOG. WE ALSO GOT THE FUEL CLOG LITE FOR THE #1 ENGINE. WE FOLLOWED THE QRH PROCEDURE AND REDUCED THE #1 TH
- [SDR FDEA202109142301](https://openairdocs.org/sdr/FDEA202109142301.md): Handle · failed · Sep 14, 2021 · N676FE · Airbus A300F4605R · Landing Gear Selector
  > PDIS 676 32-30 0707 14SEP21 AFW OPEN U GEAR WOULD NOT RETRACT AFTER TAKEOFF (GEAR HANDLE STOPPED IN MIDDLE POSITION) - TRIED POS 1 AND 2 WITH NO DIFFERENCE. PLACED GEAR HANDLE DOWN AND LANDED. SHGN 14SEP21 10:30 AFW U PERFORMED GVI OF BOT
- [SDR FDEA2020072431636](https://openairdocs.org/sdr/FDEA2020072431636.md): Floor Panel · cracked · Jul 23, 2020 · N676FE · Airbus A300F4605R · Fuselage Floor Panel
  > AFT CARGO FLOOR PANEL 152PF CRACKED AND DELAMINATED.(PANEL RACK) FABRICATED NEW FLOOR PANEL 152PF ON VTMAE TRAVELER # T20/1503455 IAW FEDEX DWG SRZ-25-005R, MAJOR REPAIR.
- [SDR FDEA2020072311613](https://openairdocs.org/sdr/FDEA2020072311613.md): Floor Panel · cracked · Jul 21, 2020 · N676FE · Airbus A300F4605R · Fuselage Floor Panel
  > FLOOR PANEL 151PF CRACKED, FABRICATED FLOOR PANEL 151PF FROM TRAVELER TD/000437 IAW DWG SRZ-25-005R, CATEGORY "A" AND MAJOR REPAIR.
- [SDR FDEA202007211609](https://openairdocs.org/sdr/FDEA202007211609.md): Skin · cracked · Jul 21, 2020 · N676FE · Airbus A300F4605R · Trailing Edge Flaps
  > FOUND RH CENTER FLAP CRACKED AT RIB 17 APPROX 5" AFT OF FRONT SPAR LOWER SKIN. AFTER FURTHER INVESTIGATIONI OF X-RAY FILM AND BORESCOPE OF THE SUSPECTED AREA AREA, NO CRACK WAS NOTED ON RIB 17 OF THE RH FLAP. CUT LOWER SKIN 6" X 3" FOR ACCESS IAW SRM 57-5
- [SDR FDEA202007171575](https://openairdocs.org/sdr/FDEA202007171575.md): Skin · delaminated · Jul 17, 2020 · N676FE · Airbus A300F4605R · Elevator, Plate/Skin
  > LEFT ELEVATOR HAD WATER ENTRAPMENT 30 7/8 INCHES FROM THE OTBD EDGE OF ER13, APPROXIMATELY 21 INCHES FROM THE TRALING EDGE AND MEASURES 1 X 1 INCH IN SIZE. REPAIRED THE LT ELEVATOR IAW SRM 55-21-12, PARA 5H. MAJOR REPAIR.
- [SDR FDEA202007171574](https://openairdocs.org/sdr/FDEA202007171574.md): Skin · delaminated · Jul 17, 2020 · N676FE · Airbus A300F4605R · Elevator, Plate/Skin
  > LEFT ELEVATOR HAD WATER ENTRAPMENT 12 INCHES FROM THE OUTBD EDGE OF ER2, APPROXIMATELY 21 1/4 INCHES FROM THE TRALING EDGE AND MEASURES 1 1/4 X 1 3/8 INCHES IN SIZE. REPAIRED THE LT ELEVATOR IAW SRM 55-21-12, PARA 5H, MAJOR REPAIR.
- [SDR FDEA202007171573](https://openairdocs.org/sdr/FDEA202007171573.md): Skin · delaminated · Jul 17, 2020 · N676FE · Airbus A300F4605R · Elevator, Plate/Skin
  > LEFT ELEVATOR HAD WATER ENTRAPMENT 19 1/2 INCHES FROM THE OUTBD EDGE OF ER2, APPROXIMATELY 21 3/8 INCHES FROM THE TRAILING EDGE AND MEASURES 5/8 X 3/4 INCH IN SIZE. REPAIRED THE LT ELEVATOR IAW SRM 55-21-12, PARA 5H. MAJOR REPAIR.
- [SDR FDEA202007171572](https://openairdocs.org/sdr/FDEA202007171572.md): Skin · delaminated · Jul 17, 2020 · N676FE · Airbus A300F4605R · Elevator, Plate/Skin
  > RIGHT ELEVATOR HAD WATER ENTRAPMENT ON THE LT EDGE OF ER13 APPROIMATELY 12 3/4 INCHES FROM THE TRAILING EDGE AND MEASURES 1 5/8 INCHES X 2 INCHES IN SIZE. REPAIRED THE RT ELEVATOR IAW SRM 55-21-12 PARA 5H, FIG 212. MAJOR REPAIR.
- [SDR FDEA2020072361546](https://openairdocs.org/sdr/FDEA2020072361546.md): Floor Panel · delaminated · Jul 16, 2020 · N676FE · Airbus A300F4605R · Fuselage Floor Panel
  > BULK CARGO FLOOR PANEL 161GF WAS DELAMINATED. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005R. CAT A MAJOR REPAIR.
- [SDR FDEA2020071761552](https://openairdocs.org/sdr/FDEA2020071761552.md): Skin · cracked · Jul 16, 2020 · N676FE · Airbus A300F4605R · Trailing Edge Flaps
  > FOUND A CRACK ON THE RT CENTER FLAP AT RIB 18, APPROX 5 INCHES FWD OF REAR SPAR ON UPPER SKIN. CUT THE SKIN ON LOWER SURFACE FOR ACCESS AND REPAIRED THE CRACK IAW SRM 57-50-00, FIG 201. INSTALLED A DOUBLER IAW SRM 57-50-00, FIG 205. CATAGORY A MAJOR REPAIR.
- [SDR FDEA2020071761551](https://openairdocs.org/sdr/FDEA2020071761551.md): Skin · cracked · Jul 16, 2020 · N676FE · Airbus A300F4605R · Trailing Edge Flaps
  > FOUND A CRACK ON THE RT CENTER FLAP, AT RIB 16 APPROX 4.8 INCHES FWD OF REAR SPAR UPPER SKIN. CUT THE SKIN ON LOWER SURFACE FOR ACCESS AND REPAIRED THE CRACK IAW SRM 57-50-00, FIG 201. INSTALLED A DOUBLER IAW SRM 57-50-00, FIG 205. CATAGORY -A- MAJOR REPAIR
- [SDR FDEA2020071761550](https://openairdocs.org/sdr/FDEA2020071761550.md): Skin · cracked · Jul 16, 2020 · N676FE · Airbus A300F4605R · Trailing Edge Flaps
  > FOUND A CRACK ON THE RT CENTER FLAP AT RIB 12, APPROX 5.1 INCHES FWD OF REAR SPAR, ON UPPER SKIN. ACCESSED AND REPAIRED THE DAMAGE IAW SRM 57-50-00, FIG 201. INSTALLED A DOUBLER ON THE LOWER SKIN IAW SRM 57-50-00, FIG 205, AND SRM 51-40-21. CATAGORY -A- MA
- [SDR FDEA2020071761549](https://openairdocs.org/sdr/FDEA2020071761549.md): Skin · cracked · Jul 16, 2020 · N676FE · Airbus A300F4605R · Trailing Edge Flaps
  > FOUND A CRACK ON THE RT CENTER FLAP AT RIB 11, LOCATED APPROX 5 INCHES FWD OF REAR SPAR IN THE UPPER SKIN. ACCESSED AND REPAIRED THE DAMAGE IAW SRM 57-50-00, FIG 201. INSTALLED A DOUBLER ON LOWER THE SKIN IAW SRM 57-50-00, FIG 205, AND SRM 51-40-21. CATAGO
- [SDR FDEA2020071761548](https://openairdocs.org/sdr/FDEA2020071761548.md): Floor Panel · delaminated · Jul 16, 2020 · N676FE · Airbus A300F4605R · Fuselage Floor Panel
  > BULK CARGO FLOOR PANEL 161AF WAS DELAMINATED. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005R. CATAGOY -A- MAJOR REPAIR.

Next page: https://openairdocs.org/aircraft/N676FE/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 = 'N676FE' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N676FE/reports

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.