N661FE

Service difficulty reports · 318

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 = 'N661FE' 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.

SDR 08FDEA01721Seat Track · crackedTHE SEAT TRACK ADAPTER AT FRAME 29; RBL 40 IS CRACKED. REMOVED SEAT TRACK ADAPTER IAW A300-600 SRM 51-40-21; PARA E-7. RECEIVED NEW SEAT TRACKADAPTER P/N A5378193720100 PO 577701.4. DRILLED HOLES IAW A300-600 SRM 51-40-44. INSTALLED NEW SEAT TRACK ADAPTEMay 1, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01720Floor Support · crackedTHE INTERCOSTAL END FITTING IS CRACKED AT FRAME 10 IN THE FWD AVIONICS BAY; RT TUNNEL. REMOVED RT AFT COCKPIT FLOOR PANEL IAW SRM 51-40-21. REMOVED CRACKED SUPPORT ANGLE IAW SRM 51-40-21. HEAT TREAT IAW SRM 51-31-00. FABRICATED ; LOCATED & DRILLED ANGLE IMay 1, 2008 · N661FE · Airbus A300F4605R · Fuselage Main, StructureSDR 08FDEA01719Web · crackedTHE FWD CARGO PIT FROM FRAME 21 - 22 HAS A CRACKED WEB AT THE FWD UPPER AND AFT LOWER CORNERS ABOVE STRINGER 44L. REMOVED WEB & RAIL ASSEMBLY IAW SRM 51-40-21. REMOVED CRACKED WEB IAW SRM 51-40-21. INSTALLED NEW WEB IAW SRM 51-40-21. REINSTALLED WEB & RAIMay 1, 2008 · N661FE · Airbus A300F4605R · Fuselage Main, FrameSDR 08FDEA01666Seat Track · corrodedMAIN DECK FLOOR TRACK AT RBL 38, FRAME 52 HAS CORROSION IN THE CENTER OF THE TRACK. ORIGINAL ADAPTER WAS FOUND TO BE OUT OF LIMITS REF 53-16-10; SRM. INSTALLED NEW ADAPTER REF SRM 51-40-21; PARA 7.Apr 29, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01665Seat Track · corrodedMAIN DECK FLOOR TRACK RBL 80, FRAME 44 HAS CORROSION AT THE UPPER CENTER OF THE TRACK. REMOVED CORRODED TRACK RAIL IAW SRM 51-72-10. LOCATED NEW TRACK RAIL IAW SRM 51-72-10 AND AIRBUS DWG 15A53813871. INSTALLED NEW TRACK RAIL IAW SRM 51-72-10 AND DWG 15A538Apr 29, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01667Seat Track · corrodedMAIN DECK FLOOR TRACK AT RBL 20, FRAME 42 HAS CORROSION IN THE CENTER OF THE SEAT TRACK. REMOVED AND REPLACED SEAT TRACK IAW SRM 51-40-21 PARA 6 & 7.Apr 29, 2008 · N661FE · Airbus A300F4605R · Fuselage Main, StructureSDR 08FDEA01668Seat Track · corrodedMAIN DECK FLOOR AT BL 0, FRAME 44, CENTER TRACK IS CRACKED AND CORRODED. REMOVED CORROSION ; OUT OF LIMITS IAW SRM 53-10-16 FIG 101. 100% MATERIAL LOSS. REPLACED WITH A NEW SEAT TRACK P/N 5327400500053, IAW SRM 51-40-44 & 51-40-21.Apr 29, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01664Seat Track · gougedMAIN CARGO COMPT SEAT TRACK SCALLOPS ARE GOUGED AND ELONGATED AT FRAME C 58, 15 INCHES, RBL 37 INCHES. REMOVED AND REPLACED THE SEAT TRACK SECTION IAW SRM 51-40-21 PARAGRAPH 7.Apr 29, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01663Seat Track · corrodedMAIN CARGO COMPT HAS CORROSION ON THE BOTTOM OF THE SEAT TRACK AT RBL 38 INCHES AND FRAME 56, 10 INCHES, AND ANOTHER SPOT 20 INCHES AFT OF IT. REMOVED AND REPLACED THE SEAT TRACK SECTION REF SRM 53-10-16 SHEET 1. ORIGINAL SEAT TRACK FOUND TO BE OUT OF LIMITS Apr 29, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01669Seat Track · corrodedMAIN CARGO COMPT SEAT TRACK AT LBL 97 HAS CORROSION SPOTS IN THE BOTTOM OF THE TRACK FROM STA 1393 TO 1658. REMOVED & REPLACED SEAT TRACK IAW SRM 51-40-21.Apr 29, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01659Panel · unsecureVERTICAL STAB L/E PANEL 322 CL HOIST POINT IS NOT SECURED ON THE INTERIOR SIDE. REPAIRED CRACKED POTTING WITH NEW POTTING EC 3500 MB / A IAW DWG 33-A53373311 AMM 55-32-11 AND SRM 51-35-10 PG 17.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01658Panel · damagedVERTICAL STAB L/E PANEL 322 CL IS DAMAGED ON THE L/E 6 INCHES FROM THE LOWER END. REPAIRED ERROSION STRIP LOWER END ON VERTICAL LE PANEL 300 CL IAW AMM 55-32-11-8 & SRM 55-32-00.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01657Panel · debondedVERTICAL STAB L/E PANEL 322 CL IS DISBONDED AROUND THE HOIST POINT. REPAIRED VERTICAL SATBILIZER L / E PANEL 322 CL HOIST POINT AREA BY TRIMMING BURRS & RESEALING IAW AMM 55-32-11-8.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01656Panel · erodedVERTICAL STAB L/E PANEL 322 CL LEFT SIDE IS ERODED JUST AFT OF THE L/E. REMOVED ERRODED PAINT FOUND NO SIGNS OF DELAMINATION IAW SRM 55-32-00.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01655Panel · debondedVERTICAL STAB L/E PANEL 322 CL LEADING EDGE IS DISBONDED. REPAIRED ERROSION STRIP LOWER END OF THE VERTICAL L / E PANEL 322 CL IAW AMM 55-32-11-8.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01654Panel · damagedVERTICAL STAB L/E 322 AL HAD GOUGES ABOVE THE HOIST POINT ON THE LEFT AND RIGHT SIDES. REMOVED GOUGED PAINT AND REFINISHED AREA IAW SRM 55-32-00 & 51-75-10.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01653Panel · damagedVERTICAL STAB L/E 322 AL HAS DAMAGE. REPAIRED VERTICAL STABILIZER L/E PANEL 322 AL BY REMOVING & BONDING A NEW SECTION OF ERROSION STRIP IAW AMM 55-32-11-8.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01652Panel · erodedVERTICAL STAB L/E PANEL 322 AL HAS AREAS OF EROSION. REMOVED ERRODED PAINT AND REFINISHED AREA IAW SRM 55-32-00 & 51-75-10.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01651Panel · debondedVERTICAL STAB L/E PANEL 322 BL IS DISBONDING AROUND THE HOIST POINT AND THE UPPER LEFT CORNER. REMOVED AND REPLACED THE ERROSION STRIP IAW AMM 55-32-11-8 AND EA 6-5530-118505.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01650Panel · damagedVERTICAL STAB L/E PANEL 322 BL IS DAMAGED ON THE LEADING EDGE. REMOVED AND REPLACED THE ERROSION STRIP IAW AMM 55-32-11-8 AND E.A. 6-5530-118505.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01649Panel · damagedVERTICAL STAB L/E PANEL 322 BL IS DAMAGED ON THE LEADING EDGE. REMOVED AND REPLACED THE ERROSION STRIP IAW AMM 55-32-11-8 AND E.A. 6-5530-118505.Apr 29, 2008 · N661FE · Airbus A300F4605R · Vertical Stabilizer, Plate/SkinSDR 08FDEA01774Frame · gougedMAIN CABIN FRAME 40 BETWEEN STRINGERS 15R AND STRINGER 16R ARE GOUGED. SMOOTH BLEND OUT THE DAMAGED AREA IAW EA 6-5310-118485 "FUSELAGE - FRAME 40 AT STRINGER 15 AND 16 LT AND RT GOUGE REPAIR".Apr 28, 2008 · N661FE · Airbus A300F4605R · Fuselage Main, FrameSDR 08FDEA01773Frame · gougedMAIN CABIN FRAME 40 L BETWEEN STRINGER 15L AND STRINGER 16 L THE FRAME IS GOUGED. PERFORMED SMOOTH BLENDOUT FOR THE DAMAGED AREA IAW EA 6-5312-118485 "FUSELAGE FRAME 40 AT STRINGER 15L AND STRINGER 16L GOUGE REPAIR". RESTORED THE SURFACE PROTECTION IAW EA 6Apr 28, 2008 · N661FE · Airbus A300F4605R · Fuselage Main, FrameSDR 08FDEA01638Seat Track · crackedMAIN DECK FLOOR, BL O, AT FRAME 51 THE CENTER OF THE TRACK IS CRACKED AND CORRODED. REMOVED CORROSION; OUT OF LIMITS IAW A300-600 SRM 53-10-16; FIG 101. ORIGINAL MATERIAL 0.134. MATERIAL LOSS 0.055. MATERIAL REMAINING 0.079. REMOVED AND REPLACED WITH A NEApr 28, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01642Angle · crackedAFT OF R/WING REAR SPAR, CRACKED ANGLE AT T/E TOP PANEL SUPPORT ANGLE, OUTBD SIDE OF RIB 9, FWD OF SPOILER NR 3 INBD HINGE PIN. REMOVED CRACKED ANGLE IAW A300-600 SRM 51-40-21. RECEIVED NEW BRACKET P/N A5724007120100, P/O NR 617032.1. INSTALLED NEW BRACKET Apr 27, 2008 · N661FE · Airbus A300F4605R · Wing Miscellaneous StructureSDR 08FDEA01603Skin · dentedLEFT WING INBD FLAP HAS TWO DENTS LOCATED 65 1/2 INCH AND 61 1/2 INCH OUTBD END AND 14 INCH AND 16 1/4 INCH FROM THE T/E THAT HAVE BEEN FOUND OUT OF LIMITS ON N/R N00417, LABELED D/E ON N/R N00417. FABRICARED DOUBLER & FILLER IAW SRM 57-50-00 FIG 205 PG 219. Apr 25, 2008 · N661FE · Airbus A300F4605R · Trailing Edge FlapsSDR 08FDEA01601Flap · dentedLEFT WING INBD FLAP HAS TWO DENTS LOCATED 55" AND 57 1/4 " FROM THE INBD ENDAND 7 3/4 " & 5" FROM THE T / E THAT HAVE BEEN FOUND OUT OF LIMITS ON N/R N00417. LABELED A & B ON N/R N00417. FABRICATED DOUBLER IAW SRM 57-50-00; FIG 205; PG 219. LOCATED &Apr 25, 2008 · N661FE · Airbus A300* · Trailing Edge FlapsSDR 08FDEA01567Panel · wornRIGHT WING LEADING EDGE PANEL NR 612 BB INNER SKIN LAMINATE IS WORN/TORN AROUND THE FASTENERS. APPLIED ANTI-ERROSION TAPE 7 PRIMED IAW A300-600 SRM 51-75-10; PG 213.Apr 25, 2008 · N661FE · Airbus A300F4605R · Wing, Plate/SkinSDR 08FDEA01604Skin · dentedLEFT WING FLAP HAS A DENT LOCATED 62 INCHES FROM THE OUTBD END AND 26 INCHES FROM THE T/E THAT HAVE BEEN FOUND TO BE OUT OF LIMITS ON N/R N00417. FABRICATED DOUBLER IAW SRM 57-50-00. LOCATED & DRILLED IAW SRM 57-50-00. ALODINED IAW SRM 51-21-10. PRIMED IAW Apr 25, 2008 · N661FE · Airbus A300F4605R · Trailing Edge FlapsSDR 08FDEA01600Panel · wornNR 2 PYLON PANEL NR 424 CR IS WORN FROM FRETTING AROUND THE EXTERIOR FASTENER HOLES. REMOVED DAMAGE REF A300-600 SRM 51-73-10. ORIGINAL THICKNESS .078. REMAINING THICKNESS .032. REMOVED .046. BEYOND LIMITS REF A300-600 SRM 54-52-51. FABRICATED DOUBLER ANApr 25, 2008 · N661FE · Airbus A300F4605R · Nacelle/Pylon Miscellaneous StructureSDR 08FDEA01597Panel · wornNR 2 PYLON PANEL NR 423 CL IS WORN FROM FRETTING AT TWO LOCATIONS FRONT AND BACK. REMOVED DAMAGE REF A300-600 SRM 51-73-10. ORIGINAL THICKNESS .078. REMAINING THICKNESS .052. REMOVED .026. BEYOND LIMITS REF A300-600 SRM 54-52-51. FABRICATED DOUBLER AND FApr 25, 2008 · N661FE · Airbus A300F4605R · Nacelle/Pylon Miscellaneous StructureSDR 08FDEA01585Panel · delaminatedPANEL 344 HT IS DELAMINATED. REPAIRED PANEL BY REMOVING THE DAMAGE ; CLEANING; PREPARING AREA; POTTING AND APPLYING A FIBERGLASS LAY-UP REPAIR IAW SRM 51-77-72; PARA 2-A; FIG 202 AND SRM 51-77-10; PARA 3. RESTORED SURFACE REPAIR IAW SRM 51-77-12; PARA Apr 25, 2008 · N661FE · Airbus A300F4605R · Horizontal Stabilizer, Plate/SkinSDR 08FDEA01584Floor Panel · damagedPANEL 121SF HAS EDGE DAMAGE. FABRICATED NEW FLOOR PANEL 121 SF; POTTED EDGES; COMPLETED CURE & SANDED EDGE POTTING; INSTALLED INSERTS; APPLIED NON-SKID & PART MARKED. REMOVED HAREWARE FROM THE OLD PANEL & REINSTALLED ON THE NEW PANEL IAW DWG SRZ 25-005; Apr 25, 2008 · N661FE · Airbus A300F4605R · Fuselage Floor PanelSDR 08FDEA01583Panel · delaminatedPANEL 334 BT IS DELAMINATED ON THE UPPER AND LOWER SIDES. RECEIVED SERVICEABLE SLIDE TO BE INSTALLED ON W / C 68S1500CP; STEP 5B.Apr 25, 2008 · N661FE · Airbus A300F4605R · Horizontal Stabilizer, Plate/SkinSDR 08FDEA01582Panel · delaminatedPANEL 334 FT IS DELAMINATED. REPAIRED PANEL 334 FT BY DRILLING OUT DAMAGED AREA AND APPLYING ADHESIVE / FIBERGLASS OVERLAY REPAIR IAW SRM 51-77-12; PG 225 & 55-13-13 PG 215. APPLIED CONDUCTIVE COAT IAW SRM 51-23-20. PRIMED & PAINTED IAW AMM 51-23-10-0.Apr 25, 2008 · N661FE · Airbus A300F4605R · Horizontal Stabilizer, Plate/SkinSDR 08FDEA01581Panel · delaminatedPANEL 344 EP DELAMINATED. REPAIRED PANEL 344 EP BY REMOVING THE DAMAGE; CLEANING; CLEANING THE AREA, POTTING REPAIR AND APPLYING A FIBERGLASS WET LAY UP REPAIR IAW SRM 51-77-12 PARA 2-A (2) FIG 202 AND SRM 51-77-10 PARA 3. RESTORED SURFACE REPAIR IAW SRM Apr 25, 2008 · N661FE · Airbus A300F4605R · Horizontal Stabilizer StructureSDR 08FDEA01580Panel · delaminatedPANEL 334 AT IS DELAMINATED AS MARKED. REPAIRED PANEL 334AT BY REMOVING THE BRUSH SEAL; CONDUCTIVE PLATE & OUTER SKIN DAMAGE IAW SRM 55-13-13 & 51-77-10. APPLIED FIBERGLASS OVERLAY REPAIR TO THE OUTER SKIN; FABBED & BONDED NEW CONDUCTIVE PLATE & WASHERS IAWApr 25, 2008 · N661FE · Airbus A300F4605R · Horizontal Stabilizer, Plate/SkinSDR 08FDEA01577Panel · delaminatedPANEL 344FT DELAMINATED 2 AREAS. REPAIRED PANEL 344 FT BY REMOVING THE DAMAGE; CLEANING; PREPARING THE AREA; POTTING AND APPLYING A FIBERGLASS WET LAY-UP REPAIR IAW ARM 51-77-12; PARA 2-A (2); FIG 202 AND SRM 51-77-10; PARA 3. RESTORED SURFACE REPAIRApr 25, 2008 · N661FE · Airbus A300F4605R · Horizontal Stabilizer, Plate/SkinSDR 08FDEA01576Panel · erodedPANEL 612 CB MATING SURFACES ARE ERODED. REPLACED ERRODED FOIL ON PANEL 612 CB MATING SURFACE IAW SRM 57-41-12.Apr 25, 2008 · N661FE · Airbus A300F4605R · Wing, Plate/SkinSDR 08FDEA01575Intercostal · bentEMPENAGE FR 86 STRINGER 34 RT INTERCOSTAL BENT. REMOVED & REPLACED INTERCOSTAL IAW SRM 51-72-10 & 51-40-21.Apr 25, 2008 · N661FE · Airbus A300F4605R · Fuselage Miscellaneous StructureSDR 08FDEA01574Panel · crackedPANEL 612 CB LEADING EDGE IS CRACKED AND ERODED. REPAIRED CRACK & ERROSION ON PANEL 612 CB L/E WITH WET LAY UP IAW SRM 57-41-12.Apr 25, 2008 · N661FE · Airbus A300F4605R · Wing, Plate/SkinSDR 08FDEA01573Intercostal · bentEMPENNAGE FR 86 STRINGER 34 LT INTERCOSTAL BENT. REMOVED AND REPLACED INTERCOSTAL IAW SRM 51-72-10 AND 51-40-21.Apr 25, 2008 · N661FE · Airbus A300F4605R · Fuselage Miscellaneous StructureSDR 08FDEA01572Access Door · delaminatedACCESS DOOR 313 AL AFT OUTBD CORNER IS DELAMINATED. REPAIRED ACCESS DOOR 313 AL BY REMOVING THE DAMAGED SKIN PLIES & THE PREVIOUS REPAIR. APPLIED A WET LAYED UP FIBERGLASS REPAIR TO THE INNER & OUTER SURFACES & REFINISHED IAW SRM 51-77-12.Apr 25, 2008 · N661FE · Airbus A300F4605R · DoorsSDR 08FDEA01571Seat Track · corrodedMAIN CABIN, FR14C TO FR18, LBL19, SEAT TRACK CORRODED. REMOVED DAMAGED SEAT TRACK IAW SRM 51-40-21. RECEIVED NEW SEAT TRACK, LOCATED; DRILLED & INSTALLED IAW SRM 51-40- 21.Apr 25, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01570Cover · damagedR-1 DOOR INTERIOR HINGE MECHANISM COVER IS DAMAGED. REMOVED DAMAGE; CLEANED & PREPPED FOR WET LAY UP. LAYED UP REPAIR PLIES & STARTED CURE, COMPLETED CURE & LIGHTLY SANDED, CLEANED & PREPPED FOR FINISH COAT; APPLIED FINISH COAT IAW SRM 51-77-10 & 51-77-11.Apr 25, 2008 · N661FE · Airbus A300F4605R · Fuselage, Door HingeSDR 08FDEA01569Seat Track · corrodedMAIN CABIN, FR 15B TO FR 18, LBL 38, SEAT TRACK CORRODED. REMOVED DAMAGED SEAT TRACK IAW SRM 51-40-21. RECEIVED NEW SEAT TRACK P/N A5361252410000, PO 617268.2. LOCATED; DRILLED & INSTALLED IAW SRM 51-40- 21 & 51-72-13.Apr 25, 2008 · N661FE · Airbus A300F4605R · Fuselage, Seat/Cargo Attach FittingsSDR 08FDEA01568Panel · damagedCABIN LAVATORY COVER PANEL IS DAMAGED. REMOVED DAMAGE. PREPPED SURFACE FOR REPAIR; POTTED; LAYED UP WET LAY-UP REPAIR & REFINISHED SURFACE IAW SRM 51-77-12.Apr 25, 2008 · N661FE · Airbus A300F4605R · Fuselage Miscellaneous StructureSDR 08FDEA01566Panel · wornRIGHT WING LEADING EDGE PANEL NR 612 DB HAS LANDING AREA INTERIOR LAMINATE WORN/TORN. REPAIRED THE DAMAGED AREA BY APPLYING ALUMINUM FOIL IAW SRM 57-41-12. REMOVED & REATTACHED THE PANEL RESTRAINING CORDS REF AMM 57-41-41-4. PREPPED THE BONDING SURFACE FOR THApr 25, 2008 · N661FE · Airbus A300F4622R · Wing, Plate/SkinSDR 08FDEA01565Panel · wornRIGHT WING LEADING EDGE PANEL NR 612 GB HAS LANDING AREA SKIN LAMINATE WORN/TORN. REPAIRED DAMAGED AREA IAW SRM 57-41-12; FIG 208. REMOVED & RE-ATTACHED THE PANEL RESTRAINT CORDS REF AMM 57-41-41-4; PG 1.PREPARED THE BONDING SURFACE FOR THE FOIL APPLICAApr 25, 2008 · N661FE · Airbus A300F4605R · Wing, Plate/SkinSDR 08FDEA01564Panel · erodedRIGHT WING LEADING EDGE PANEL NR 623 HB IS ERODED AT THE FWD EDGE. REPAIRED ERRODED AREAS BY APPLYING FIBREGLASS OVERLAYS IAW SRM 57-41-12 & 51-77-12. REAPPLIED FOIL IAW SRM 57-41-12; FIG 208. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. RESTORED PAINApr 25, 2008 · N661FE · Airbus A300F4605R · Wing, Plate/Skin
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