# Service difficulty reports: N446FE, cancelled Jul 29, 2013

A list on [N446FE, cancelled Jul 29, 2013](https://openairdocs.org/deregistered/N446FE-2013-07-29.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 · 97 reports

- [SDR FDEA201002150424](https://openairdocs.org/sdr/FDEA201002150424.md): Transmitter · malfunctioned · Feb 15, 2010 · N446FE · Airbus A310222 · Engine Oil Pressure
  > AFTER TOGA POWER SET ON T/O, GOT A NR 1 ENG HIGH OIL PRESS LIGHT. REJECTED T/O. ALSO DURING START THE NR 1 ENG HIGH OIL PRESSURE LIGHT CAME ON FOR 1 MIN. GROUND RAN ENGINE IAW JRH SEVERAL TIMES. OIL PRESSURE FOR NR 1 ENG NEVER EXCEEDED 50 PSI. ALL ENGINE PA
- [SDR FDEA200911244202](https://openairdocs.org/sdr/FDEA200911244202.md): Switch · malfunctioned · Nov 24, 2009 · N446FE · Airbus A310222 · Landing Gear Position and Warning
  > ON APPROACH, NO NOSE GEAR INDICATION ON NR 1 SYS (FRONT PANEL) NR 2 SYS (OVERHEAD PANEL) GOOD, DID A GO AROUND AND ON DOWNWIND, NOSE GEAR LIGHT CAME BACK AND INDICATED NORMAL. WHEN LIGHT WAS NOT INDICATING, DID ALL LIGHTS CHECK AND IT CHECKED GOOD. RELEASED
- [SDR 07FDEA04248](https://openairdocs.org/sdr/07FDEA04248.md): Spar · failed · Sep 24, 2007 · N446FE · Airbus A310322 · Horizontal Stabilizer, Spar/Rib
  > LEFT HORIZONTAL STAB ON UPPER REAR SPAR BETWEEN RIBS 4/5 REPAIR STRAP IN WRONG MATERIAL TYPE. REMOVE AND REPLACE AS REQUIRED REMOVED STRAP IAW A310-200 FX SRM 55-11-21. FABRICATED NEW STRAP IAW FX A310-200 SRM 55-11-21 FIG 214 AND PG 285. INSTALLED NEW ST
- [SDR 07FDEA04251](https://openairdocs.org/sdr/07FDEA04251.md): Spar · damaged · Sep 24, 2007 · N446FE · Airbus A310322 · Horizontal Stabilizer, Spar/Rib
  > LEFT HORIZONTAL STAB ON UPPER REAR SPAR BETWEEN RIBS 10 AND 11 REPAIR STRAP REQUIRES REMOVAL FOR MATERIAL TYPE VERIFICATION REMOVED STRAP IAW A310-200 SRM 55-11-21 PG 202. FABRICATED NEW STRAP IAW A310-200 SRM 55-11-21 FIG 214 AND PG 285. INSTALLED NEW STRAP
- [SDR 07FDEA04247](https://openairdocs.org/sdr/07FDEA04247.md): Spar · damaged · Sep 24, 2007 · N446FE · Airbus A310222 · Horizontal Stabilizer, Spar/Rib
  > RIGHT HORIZONTAL STAB ON UPPER REAR SPAR BETWEEN RIBS 9 AND 10 REPAIR STRAP REQUIRES REMOVAL FOR MATERIAL TYPE VERIFICATION REMOVED STRAP REF A310-200 SRM 51-40-21. FABRICATED STRAP IAW FED ED A310-200 SRM 55-11-21 FIG 215 AND PG 285. INSTALLED REPAIR STRAP
- [SDR 07FDEA03758](https://openairdocs.org/sdr/07FDEA03758.md): Stringer Splice · misrepaired · Sep 14, 2007 · N446FE · Airbus A310222 · Fuselage Main, Longeron/Stringer
  > STGR SPLICE REPAIR BETWEEN FRAME 72/73 ON STGR 56R REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA VISUALLY INSPECTED STGR SPLICE REPAIR BETWEEN FRAME 72/73 AT STGR 56 RT AND FOUND MATERIAL TYPE FOR STGR
- [SDR 07FDEA03783](https://openairdocs.org/sdr/07FDEA03783.md): Strap · misinstalled · Sep 14, 2007 · N446FE · Airbus A310222 · Horizontal Stabilizer Structure
  > LEFT HORIZ STAB ON UPPER REAR SPAR BETWEEN RIBS 5 AND 8 REPAIR STRAP REQUIRES REMOVAL FOR MATERIAL TYPE VERIFICATION REMOVED DOUBLER STRAP DUE INCORRECT MATL IN REF A310 SRM 55-11-21 PG 202. REPLACED STRAP DOUBLER IAW A310 SRM 55-11-21 FIG 214.
- [SDR 07FDEA03788](https://openairdocs.org/sdr/07FDEA03788.md): Frame · cracked · Sep 14, 2007 · N446FE · Airbus A310222 · Fuselage Main, Frame
  > FRAME CRACKED IN FASTENER HOLE AT FRAME 43A LOWER HOLE COMMON TO CRUCIFORM FITTING LT SIDE SEE JOB CARD 41X5271ALI FROM CABIN SIDE 1ST LAYER RUNNING IN THE 5 O`CLOCK DIRECTION.075 DEEP AND RUNNING TO THE 2ND LAYER 100 PERCENT ON SCREEN AMPLITUDE REMOVED AND R
- [SDR 07FDEA03786](https://openairdocs.org/sdr/07FDEA03786.md): Frame · cracked · Sep 14, 2007 · N446FE · Airbus A310222 · Fuselage Main, Frame
  > FRAME CRACKED IN FASTENER HOLE AT FRAME 42A LOWER HOLE COMMON TO CRICIFORM FITTING SEE JOB CARD 41 BY 5271ALI. RT SIDE FROM CABIN SIDE THE FIRST LAYER RUNNING IN THE 6 O`CLOCK AND 9 O`CLOCK DIRECTIONS APPROX.100 DEEP TO THE 2ND LAYER 100 PERCENT + AMPLITUDE
- [SDR 07FDEA03753](https://openairdocs.org/sdr/07FDEA03753.md): Strap · cracked · Sep 14, 2007 · N446FE · Airbus A310222 · Fuselage Miscellaneous Structure
  > LT FWD PAX/CREW DOOR CUTOUT, HFEC INSPECTION INDICATES CRACK/CORROSION IN 5 LOCATIONS ALONG EDGE OF LOWER CORNER STRAPS AS FOLLOWS; (1) FWD LOWER CORNER- ONE 1/2" LONG AND ONE 1.0" LONG AND, (2) AFT LOWER CORNER - ONE 2 1/4" LONG, ONE 3/8" LONG AND ONE 2" LO
- [SDR 07FDEA03749](https://openairdocs.org/sdr/07FDEA03749.md): Strap · cracked · Sep 14, 2007 · N446FE · Airbus A310222 · Fuselage Miscellaneous Structure
  > AREA IS RT FWD PAX/CREW DOOR CUTOUT. 1 1/8 INCH CRACK WITH POSSIBLE EXFOLIATION CORROSION EXISTS ALONG TOP EDGE OF FWD CORNER STRAP, BEGINNING APPROX 1 1/8 INCH FROM AFT EDGE OF CORNER STRAP, LOWER, FWD CORNER OF DOOR CUTOUT BEHIND FAILSAFE RING. AREA MARK
- [SDR 07FDEA03727](https://openairdocs.org/sdr/07FDEA03727.md): Strap · cracked · Sep 14, 2007 · N446FE · Airbus A310322 · Fuselage Miscellaneous Structure
  > AREA IS RT FWD PAX/CREW DOOR CUTOUT, 3 5/8 INCH CRACK WITH POSSIBLE EXFOLIATION CORROSION EXISTS ALONG TOP EDGE OF AFT CORNER STRAP, BEGINNING 1" FROM FWD EDGE OF CORNER STRAP. (LOWER, AFT CORNER OF DOOR CUTOUT BEHIND FAIL/SAFE RING) AREA MARKED IN RED. SEE
- [SDR 07FDEA03131](https://openairdocs.org/sdr/07FDEA03131.md): Seat Track · sheared · Aug 26, 2007 · N446FE · Airbus A310222 · Fuselage, Seat/Cargo Attach Fittings
  > MAIN CABIN RIGHT SEAT TRACK Y-1959 AT FRAME 47 LUGS ARE BROKE OUT.
- [SDR 07FDEA03053](https://openairdocs.org/sdr/07FDEA03053.md): Seat Track · damaged · Aug 22, 2007 · N446FE · Airbus A310222 · Fuselage, Seat/Cargo Attach Fittings
  > MAIN CABIN RT SEAT TRACK NR Y-1456 AT FRAME C63 LUGS BROKEN OUT. 09-11-07 REMOVED DAMAGED SECTION OF SEAT TRACK IAW A310 SRM 53-10-16. INSTALLED NEW SECTION OF SEAT TRACK AND SPLICE IAW A310 SRM 53-10-16
- [SDR 07FDEA02155](https://openairdocs.org/sdr/07FDEA02155.md): Controller · failed · Jun 16, 2007 · N446FE · Airbus A310222 · Cabin Pressure Controller
  > ON CLIMB-OUT, AIRCRAFT DID NOT PRESSURIZE. BOTH FWD AND AFT REG NR 2 VALVES WERE STUCK FULL OPEN AND SHOWING AMBER ON THE ECAM. DUPLICATED PROBLEM AT GATE, REPLACED NR 2 CABIN PRESSURE CONTROLLER PER A310-200 AMM21-31-11-4, OPERATIONAL CHECK NORMAL. PREMAT
- [SDR 06FDEA04328](https://openairdocs.org/sdr/06FDEA04328.md): Switch · failed · Dec 27, 2006 · N446FE · Airbus A310222 · Engine Thrust Reverser
  > NR 2 ENG REV UNLK LIGHT AND ECAM WARNING CAME ON AT FL 360, STAYED ON AFTER LANDING AND SHUTDOWN. REPEAT GRIP, FOUND THE MASTER ACTUATOR SECONDARY LOCK SWITCH RT SIDE FAILED CLOSED. REMOVED AND INSTALLED SAME REF A310-200 MM 78-31-16-4. OPS CHECKS GOOD SAME
- [SDR 06FDEA2559](https://openairdocs.org/sdr/06FDEA2559.md): Engine · unknown · Jul 13, 2006 · N446FE · Airbus A310222 · Engine (Turbine/Turboprop)
  > ON INITIAL POWER-UP FOR TAKEOFF NUMBER 2 ENG WAS VERY SLOW TO ACCELERATE. TERMINATED THE TAKEOFF AT APPROXIMATELY 20 KTS AND CLEARED THE RUNWAY. TAXI'D BACK TO RUNWAY HELD THE BRAKES AND PUT NR 1 ENG TO 40 PERCENT N1. THE INDEX POINTER ON THE NR 1 THROTTLE
- [SDR 05FDEA01850](https://openairdocs.org/sdr/05FDEA01850.md): Wire · broken · Jul 7, 2005 · N446FE · Airbus A310222 · Power Lever
  > ABORTED TAKEOFF DUE TO ENG NR 2 FAILED TO STABILIZE AT 40 PERCENT POWER, WITH NR 1 ENG THROTTLE SET NORMALLY TO PRODUCE 40 PERCENT N1 THE NR 2 THROTTLE WAS THREE KNOB WIDTHS AHEAD AND STILL ONLY PRODUCING 25 PERCENT N1. FOUND WIRE BROKEN INSIDE RING TERMINAL.
- [SDR 05FDEA01044](https://openairdocs.org/sdr/05FDEA01044.md): Terminal Block · loose · Apr 17, 2005 · N446FE · Airbus A310222 · Turbine Engine System Wiring
  > ON CLIMB-OUT, NOTICED NR 2 EGT NEEDLE/ANALOGUE GAUGE FLUCTATING-RECEIVED ECAM FOR NR 2 ENG OVERLIMITS. PULLED POWER BACK. GAUGE STABILIZED THEN STARTED TO FLUCTUATE AGAIN. RAN QRH, DECIDED TO RETURN. BURNED DOWN FUEL TO MAX LNBW. NORMAL LANDING, TAXI IN.
- [SDR 05FDEA00998](https://openairdocs.org/sdr/05FDEA00998.md): Arm · gouged · Apr 14, 2005 · N446FE · Airbus A310 · Rudder Miscellaneous Structure
  > NR 7 RUDDER HINGE ATTACHMENT BRACE ( A-FRAME) HAS GOUGE MARKS AND WEAR MARKS AT ATTACHMENT BOLT. REMOVED AND REPLACED NR 7 HINGE ARM IAW A310-200 AMM 55-36-47-4-01 AND 27-21-21-4-01.
- [SDR 05FDEA00603](https://openairdocs.org/sdr/05FDEA00603.md): Structure · corroded · Mar 18, 2005 · N446FE · Airbus A310222 · Cargo/Baggage Doors
  > CORROSION FOUND UNDER THE NR 9 LATCH ROLLER FOR FWD CARGO DOOR. COMPLIED WITH EA 6-5310-86132.
- [SDR 05FDEA00602](https://openairdocs.org/sdr/05FDEA00602.md): Skin · cracked · Mar 18, 2005 · N446FE · Airbus A310222 · Wing, Plate/Skin
  > LEFT WING T/E BOTTOM SKIN HAS INDICATION OF CRACK ON I/B CORNER SIDE CUTOUT PANEL 581AB AS MARKED. COMPLIED WITH EA 6-5710-86028.
- [SDR 05FDEA00574](https://openairdocs.org/sdr/05FDEA00574.md): Skin · corroded · Mar 16, 2005 · N446FE · Airbus A310 · Fuselage Main, Plate/Skin
  > CORR B/T STR 34-35 FROM FS 39 AFT APPROX 8 IN LT REF N00850. COMPLIED WITH EA 6-5315-86078.
- [SDR 05FDEA00493](https://openairdocs.org/sdr/05FDEA00493.md): Floor Support · corroded · Mar 10, 2005 · N446FE · Airbus A310222 · Fuselage Miscellaneous Structure
  > BULK PIT FLOOR SUPPORT AT FR67 FROM 12 INCHES TO LT CTR TO 36 INCHES TO LT OF CTR, 4EA AREAS OF CORROSION EXTENDING UNDER FASTENER HEADS AS MARKED. REMOVED AND REPLACED CROSS BEAM FLOOR SUPPORT IAW 51-72-10. REMOVED 4EA AREAS OF CORROSION IAW SRM 51-74-10.
- [SDR 05FDEA00492](https://openairdocs.org/sdr/05FDEA00492.md): Rib · damaged · Mar 10, 2005 · N446FE · Airbus A310222 · Elevator, Spar/Rib
  > UPON REMOVAL OF EXISTING REPAIR ON N/R N00817 ON RT ELEVATOR INBOARD T/E LWR SURFACE FOUND 2EA AREAS OF CORROSION.5 X.5 INCH 1 ON INBOARD SIDE OF REPAIR, 1 ON OUTBOARD SIDE OF REPAIR (RIB 5 AND RIB 9). REMOVED CORROSION PER A310-200 SRM 51-74-10, 1EA AREA I
- [SDR 05FDEA00439](https://openairdocs.org/sdr/05FDEA00439.md): Panel · damaged · Mar 8, 2005 · N446FE · Airbus A310 · Wing, Plate/Skin
  > RT WING PANEL 650JB HAS 4 EA ELONGATED REF N00522. REPAIRED PANEL 650JB IAW EA 6-5710-86051.
- [SDR 05FDEA00425](https://openairdocs.org/sdr/05FDEA00425.md): Rib · cracked · Mar 8, 2005 · N446FE · Airbus A310 · Wing, Rib/Bulkhead
  > RT WING 4 IN IB OF RIB 30 L/E AREA AFT PANEL LANDING IS CRACKED REF N00636. REMOVED AND REPLACED LANDING IAW SRM 51-40-21 AND 51-72-10 AND DRW A57243955.
- [SDR 05FDEA00447](https://openairdocs.org/sdr/05FDEA00447.md): Skin · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Fuselage Main, Plate/Skin
  > BULK PIT UNDER FLOOR AREA FS 69 STR 48 LT HAS AN AREA THAT EXTEND 2 INCHES FWD OF FS 69 OF CORROSION EXTENDING UNDER SHEAR TIE. REMOVED SHEAR TIE AND STRINGER SECTION IAW A310-200 SRM 53-10-14. INSTALLED SHEAR TIE AND STRINGER SECTION IAW A310-200 SRM 53-10-
- [SDR 05FDEA00477](https://openairdocs.org/sdr/05FDEA00477.md): Skin · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Fuselage Main, Plate/Skin
  > BULK PIT UNDER FLOOR AREA FR69 STG48L HAS AN AREA THAT EXTEND 2" FWD OF FR 69 OF CORROSION EXTENDING UNDER SHEAR TIE. REMOVED SHEAR TIE AND STRINGER SECTION IAW A310-200 SRM 53-10-14. INSTALLED SHEAR TIE AND STRINGER SECTION IAW A310-200 SRM 53-10-14.
- [SDR 05FDEA00453](https://openairdocs.org/sdr/05FDEA00453.md): Angle · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Horizontal Stabilizer Structure
  > THS ACTUATOR STRUCTURAL HOUSING HAS APPROX 12 INCH OF CORROSION (10 EA. AREAS). REMOVED CORROSION IN 10 EA AREAS ON THS ACTUATOR STRUCTURAL HOUSING. ALL AREAS WERE WITHIN LIMITS EXCEPT AREA 10 WHICH WAS OUT OF LIMITS IAW A310-200 SRM 53-10-00. REMOVED L-AN
- [SDR 05FDEA00452](https://openairdocs.org/sdr/05FDEA00452.md): Shear Tie · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Fuselage Internal Mounting Structure
  > BULK PIT UNDER FLOOR STG 55L FROM FS 65 TO FS 66 HAS CORROSION AND CORROSION. EXTENDS BETWEEN SPLICE ANGLE AND STG AND UNDER SHEAR TIE AT FS 66. REMOVED CORROSION IAW A310-200 SRM 51-74-10. STRINGER CORRODED BEYOND ALLOWABLE LIMITS AS PER A310-200 SRM 51-10
- [SDR 05FDEA00451](https://openairdocs.org/sdr/05FDEA00451.md): Floorbeam · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Fuselage Main, Floor Beam
  > AFT PIT FLOOR FS 66 10 INCH TO RT OF CTR HAS A 5 INCH BY 2 INCH AREA OF CORROSION. REMOVED CORROSION PER A310-200 SRM 51-74-10. CORROSION OUT OF LIMITS PER SRM 51-10-00. REMOVED CORRODED FLOORBEAM AND INSTALLED NEW BEAM PER A310-200 SRM 51-72-10. REPROTECT
- [SDR 05FDEA00450](https://openairdocs.org/sdr/05FDEA00450.md): Skin · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Fuselage Main, Plate/Skin
  > AFT PIT UNDER FLOOR 16 INCH FWD OF FS 54.1, STG 47R HAS CORROSION. REMOVED CORROSION IAW A310-200 SRM 51-74-10. AREA WAS OUT OF LIMITS IAW A310-200 SRM 53-10-00. REMOVED AND REPLACED DAMAGED AREA IAW A310-200 SRM 53-10-14. TREATED, PRIMED, TOPCOATED IAW A3
- [SDR 05FDEA00449](https://openairdocs.org/sdr/05FDEA00449.md): Shear Tie · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Fuselage Internal Mounting Structure
  > BULK PIT UNDER FLOOR STG 53R FROM 1 INCH FWD OF 66 TO FR 67 HAS CORROSION EXTENDING UNDER SHEAR TIE AT FR 66 AND EXTENDING UNDER FASTENERS IN SEVERAL AREAS. REMOVED CORROSION, CHECK LIMITS MAT'L LOSS EXCEEDED LIMITS IAW A310-200 SRM 53-10-00 FIG 104. REMOVE
- [SDR 05FDEA00448](https://openairdocs.org/sdr/05FDEA00448.md): Structure · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Fuselage Main, Structure
  > AFT PIT UNDER FLOOR FROM 12 INCH FWD OF FS 59 TO 3 INCHES FWD OF FS 59 STG44L HAS CORROSION. REMOVED CORROSION IAW A310-200 SRM 51-74-10. THE AREA WAS FOUND OUT OF LIMITS IAW A310-200 SRM 53-10-00. REPAIRED STRINGER IAW A310-200 SRM 53-10-14. TREATED, PRIME
- [SDR 05FDEA00443](https://openairdocs.org/sdr/05FDEA00443.md): Flap Track · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Trailing Edge Flaps
  > RT WING FLAP O/B UPPER SURFACE AT NR 3 FLAP TRACK AND NR 4 FLAP TRACK HAS 2 EA AREAS OF NOTED CORROSION REF N00771. REMOVED CORR IAW SRM 51-74-10, FOUND IN LIMITS IAW SRM 57-53-12.
- [SDR 05FDEA00442](https://openairdocs.org/sdr/05FDEA00442.md): Skin · punctured · Mar 8, 2005 · N446FE · Airbus A310 · Trailing Edge Flaps
  > RT WING I/B FLAP UPPER SURFACE 3.9 IN FROM T/E AND 30 IN FROM I/B END SKIN PUNCTURED REF N00914. REPAIRED FLAP IAW SRM 57-52-12 FIG 4D.
- [SDR 05FDEA00441](https://openairdocs.org/sdr/05FDEA00441.md): Attach Fitting · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Vertical Stabilizer, Attach Fittings
  > VERTICAL STAB UPPER EDGE LEFT AND RIGHT FORE TO AFT HAS CORROSION AROUND CAP ATTACH FASTENER HOLES REF N00734. REMOVED AND REPLACED RT CHORD IAW SRM 51-40-21 AND DRW A55371360 AND REPAIRED LT CHORD IAW SRM 51-74-40 FIG 201
- [SDR 05FDEA00440](https://openairdocs.org/sdr/05FDEA00440.md): Doubler · damaged · Mar 8, 2005 · N446FE · Airbus A310 · Elevator, Plate/Skin
  > REPAIR ON RT ELEVATOR I/B T/E LOWER SURFACE REQUIRES EVALUATION REF N00817. REMOVED EXISTING REPAIR AND INSTALLED CORRECT REPAIR IAW SRM 55-21-11 CONF 1 FIG 203 AND EA 6-5510-86111.
- [SDR 05FDEA00438](https://openairdocs.org/sdr/05FDEA00438.md): Panel · damaged · Mar 8, 2005 · N446FE · Airbus A310 · Wing, Plate/Skin
  > RT WING PANEL 650KB HAS 4 EA ELONGATED HOLES REF N00521. REPAIRED PANEL IAW EA 6-5710-86051.
- [SDR 05FDEA00437](https://openairdocs.org/sdr/05FDEA00437.md): Panel · damaged · Mar 8, 2005 · N446FE · Airbus A310 · Wing, Plate/Skin
  > LT WING PANEL 550HB HAS 2 EA ELONGATED HOLES REF N00520. REPAIRED HOLES IAW EA 6-5710-85051.
- [SDR 05FDEA00436](https://openairdocs.org/sdr/05FDEA00436.md): Panel · damaged · Mar 8, 2005 · N446FE · Airbus A310 · Wing, Plate/Skin
  > RT WING PANEL 650HB HAS 3 EA ELONGATED HOLES REF N00523. REPAIRED PANEL 650HB IAW EA 6-5710-86051.
- [SDR 05FDEA00426](https://openairdocs.org/sdr/05FDEA00426.md): Rib · cracked · Mar 8, 2005 · N446FE · Airbus A310 · Wing, Rib/Bulkhead
  > RT WING L/E UPPER SIDE OF PANEL LANDING, LANDING FOR PANEL HAS 2 EA CRACKS AT 11 IN I/B OF RIB 14 AND 11 IN O/B OF RIB 14 REF N00631. REMOVED AND REPLACED PANEL LANDING IAW SRM 51-40-21 AND DRW A57244165.
- [SDR 05FDEA00424](https://openairdocs.org/sdr/05FDEA00424.md): Door · damaged · Mar 8, 2005 · N446FE · Airbus A310 · Landing Gear Doors
  > NOSE LANDING GEAR DOORS HAS STRUCTURAL DAMAGE REF N00748. REPAIRED RT GEAR DOORS IAW SRM 52-82-11 C1 FIG 201.
- [SDR 05FDEA00423](https://openairdocs.org/sdr/05FDEA00423.md): Skin · cracked · Mar 8, 2005 · N446FE · Airbus A310 · Wing, Plate/Skin
  > RT WING T/E SKIN HAS A.4 CRACK ON IB CORNER OF CUTOUT FOR PANEL 681 AB REF N00265. REPAIRED SKIN IAW EA 6-5710-86028.
- [SDR 05FDEA00422](https://openairdocs.org/sdr/05FDEA00422.md): Skin · damaged · Mar 8, 2005 · N446FE · Airbus A310 · Elevator, Plate/Skin
  > REPAIR FUSELAGE AT LT ELEVATOR T/E AFT FROM OB END HAS NO DATA REF N00806. REMOVED AND INSTALLED CORRECT REPAIR IAW EA 6-5100-87090 REF A310 SRM 55-21-11, REPAIR NR 5 G.
- [SDR 05FDEA00421](https://openairdocs.org/sdr/05FDEA00421.md): Seat Track · corroded · Mar 8, 2005 · N446FE · Airbus A310 · Fuselage, Seat/Cargo Attach Fittings
  > NR 4 SEAT TRACK LT OF CENTER FROM FS 16 TO FS 18 HAS CORROSION REF N00519. REMOVED AND REPLACED SEAT TRACK FROM FS 16 TO FS 18 IAW SRM 51-40-21 AND EA 6-5310-86038.
- [SDR 05FDEA00420](https://openairdocs.org/sdr/05FDEA00420.md): Seat Track · corroded · Mar 8, 2005 · N446FE · Airbus A310222 · Fuselage, Seat/Cargo Attach Fittings
  > MDC NR 4 SEAT TRACK RT OF CENTER AT FR19 ON I/B SPLICE HAS CORROSION ON UPPER SURFACE. REMOVED AND REPLACED SPLICE ANGLE AT FR19 IAW SRM 51-40-21.
- [SDR 05FDEA00419](https://openairdocs.org/sdr/05FDEA00419.md): Plate · corroded · Mar 8, 2005 · N446FE · Airbus A310222 · Fuselage Miscellaneous Structure
  > BULK CARGO DOOR CUTOUT ON LWR FWD TOP EDGE OF SCUFF PLATE SURFACE CORROSION. REMOVED SCUFF PLATE AND REMOVED CORROSION IAW SRM 51-74-10 FOUND IN LIMITS IAW SRM 53-10-00. RESTORED FINISH AND REINSTALLED SCUFF PLATE IAW SRM 53-10-18-4.
- [SDR 05FDEA00418](https://openairdocs.org/sdr/05FDEA00418.md): Panel · cracked · Mar 8, 2005 · N446FE · Airbus A310222 · Wing, Plate/Skin
  > UPON REMOVAL OF LANDING AT RT WING HINGE PANEL ON L/E FOUND PANEL LANDING CRACKED REF N00915. REMOVED AND REPLACED PANEL LANDING IAW SRM 51-40-21 AND DRW A572-434548.

Next page: https://openairdocs.org/deregistered/N446FE-2013-07-29/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 = 'N446FE' AND deregistration_id = 'N446FE-2013-07-29'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N446FE-2013-07-29/reports

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