N629VA

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,746 hrs · 18,418 cycles

LH STR 32L BETWEEN FR63 AND FR62 HAS SEVERAL SPOTS OF CORROSION GROUNDED - YES. EVALUATED CORROSION ON S32L AT FR 62-FR 63, ORIGINAL MATERIAL 0.071", REMOVED 0.045",REMAINING MATERIAL 0.026" FOUND TO BE OUT OF LIMITS DUE TO NO LIMITS GIVEN IN A320 SRM MAJOR REPAIR ACCOMPLISHED - FUSELAGE STRINGER S-32L, BETWEEN FR62 AND FR63, CORROSION DAMAGE REPAIR PERFORMED IN ACCORDANCE WITH AIRBUS DOSSIER 81312718 WITH APPROVAL PER AIRBUS RDAF 81312718/003/2023 #B DATED 19-DEC-2023 PER EA A320-53EA-02-022 REV 00 DATED 12/19/2023THIS IS A CATEGORY "A" REPAIR

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,746 hrs · 18,418 cycles

LH STR 36L BETWEEN FR63 AND FR64 HAS SURFACE CORROSION IS SEVERAL SPOTS GROUNDED - YES. LH STR 36L CORRODED. CORROSION FOUND TO BE OUT OF LIMITS. CORROSION REMOVED. RFTS GENERATED AND REPAIR ACCOMPLISHED IAW A320-53EA-01997. ORIGINAL THICKNESS=.080" REMOVED=.029 REMAINING=.051. OUT OF LIMITS IAW A320 SRM 53-41-13-283-002 T82241 CAL DUE 04/26/2024

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

LH STR 30L BETWEEN FR64 AND FR63 HAS SURFACE CORROSION GROUNDED - YES. NO LIMITS FOUND FOR AREA. LOCATED, DRILLED AND DEBURRED MATERIAL DAN50B13P.O. 1074939.1 AND A53986219DAN2001T79511 P.O. 1074961.1 IAW A320 SRM51-44-11 AND A320 SRM 53-00-13. BHFEC OPEN HOLES AND HFEC SURFACE IAW NTM51-10-08 WITH NO DEFECTS NOTED.REMOVED AND REPLACED STRINGER AND COUPLINGIAW A320 SRM 53-00-13 AND A320 SRM 51-42-11. ALODINED AND PRIMED REPAIR IAWA320 SRM 51-21-11. TOPCOATED IAW A320 SRM 51-75-00. REMOVED AND INSTALLEDSTRINGER CLIP AND SPLICE IAW A320 SRM 51-42-11.

Part: DOOR SILL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,745 hrs · 18,418 cycles

R2 DOOR LOWER SILL REQUIRES REMOVAL AND REPLACEMENT GROUNDED - YES. REMOVED AND REPLACED R2 DOOR CUTOUT LOWER SILL IAW A320 SRM 51-72-- AND DWG 53480505. SILL FOUND TO BE OUT OF LIMITS ON G1829852AND G1829679. ORIG THICKNESS .063", REMOVED .023, REMAINING .040. MAX ALLOWABLE MAT LOSS .015". (G1829852).ORIG THICKNESS .058", REMOVED .047, REMAINING .051, MAX ALLOWABLE 25% OR .0245 (G1829679)

Part: FRAME — PUNCTURED (UNKNOWN) · airframe 48,746 hrs · 18,418 cycles

WHILE REMOVAL OF PROFILE IN AFT PIT L/H FRAME 54 NEAR STRINGER 38 INADVERTENTLY DRILLED THROUGH RADIUS OF FRAME. GROUNDED - YES. REMOVED AND REPLACED FRAME SECTION AT L/H FRAME 54 P/N D5347055320200 PO# 1070959.1 IAW AIRBUS DWG D53470330 ISSUE E AND A320 SRM 51-42-11.

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

AFT WET AREA LH SIDE STR 30 AT FR65 TO FR67 HAS CORROSION GROUNDED - YES. NO LIMITS FOUND FOR AREA .ANNEALED MATERIAL DAN50B08 PO 1069688.1 IAW A320 SRM 51-25-00FORMED IAW A320 SRM 51-25-00 AND AIRBUS DWG # D53480505.HEAT TREATED IAW A320 SRM 51-25-00.LOCATED, DRILLED AND DEBURRED IAW A320 SRM 51-44-11.ALODINED AND PRIMED IAW A320 SRM 51-21-11.TOPCOAT APPLIED IAW A320 SRM REMOVED AND REPLACED STRINGER IAW A320 SRM 51-42-11 AND AIRBUS DWG # D53480505.REMOVED AND INSTALLED 2EA STRINGER SPLICES AND 1EA STRINGER CLIP IAW A320 SRM 51-42-11

Part: FLOOR PANEL — CORRODED (UNKNOWN) · airframe 48,746 hrs · 18,418 cycles

MAIN CABIN FLOOR PANEL 262KG HAS CORRODED INSERTS GROUNDED - YES. REMOVED AND REPLACED FLOOR PNL 262KG WITH NEW IAW A320 AMM 53-00-00-400-801APO# 1070186.1

Part: SUPPORT — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,746 hrs · 18,418 cycles

FRAME SUPPORT AT LH STRINGER 26 BETWEEN FR69 AND FR70 HAS CORROSION. GROUNDED - YES. NO LIMITS FOR FRAME SUPPORT FOUND. LOCATED, DRILLED AND DEBURRED FRAME SUPPORT P/N D5347112620000 P.O. 1069870.1 AND 1EA ANGLE P/N D53471174200000 P.O.1070801.3 AND 1EA ANGLE P/N D5347117520000 P.O.1070801.4 IAW A320 SRM 51-44-11. REMOVED AND REPLACED FRAME SUPPORT AND 2EA ANGLES IAW A320 SRM 51-42-11 AND AIRBUS DWG# D53470100

Part: SHEAR TIE — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

FRAME SUPPORT AT LH STRINGER 31 BETWEEN FR69 AND FR 70 HAS CORROSION GROUNDED - YES. NO LIMITS FOUND FOR AREA.LOCATED DRILLED AND DEBURRED P/N D534711320200 PO 1069870.2ANGLE P/N D5347117620090 PO 1069866.2 AND ANGLE P/N D5347117620090 PO.1069806.2 IAW A320 SRM 57-44-11 AND AIRBUS DEG # D53470100 REMOVED AND REPLACED SUPPORT AND 2 EA ANGLES IAW A320 SRM 51-42-11 AND AIRBUS DWG # 053470100

Part: SUPPORT — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

FRAME SUPPORT AT LH STRINGER 28 BETWEEN FR69 AND FR70 HAS CORROSION GROUNDED - YES. NO LIMITS FOUND FOR AREA LOCATED, DRILLED AND DEBURRED SUPPORT P/N D53471128L0000 P.O. 1069556.3. AND ANGLE P/N D5347117420000 P.O. 1069556..3 IAW A320 SRN 51-44-11 AND AIRBUS DWG#D55470100. INSTALLED SUPPORT. ANGLE AND EXISTING ANGLE IAW A320 SMM 51-42-11 AND AIRBUS DWG#D53470100.

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

AFT WET AREA LH SIDE STR 34 AT FR65 TO FR66 HAS CORROSION GROUNDED - YES. NO LIMITS FOUND FOR AREA. AMALED MATERIAL DAN50B08 P.O. 1069688.1 IAW A320SRM 51-25-00. CONTURED AND JOGGLED MATERIAL IAW AIRBUS DWG#D53480030. HEATTREATED STRINGER IAW A320 SRM 51-25-00. LOCATED, DRILLED AND DEBURREDSTRINGER IAW A320 SRM 51-44-11. ALODINED AND PRIMED IAW A320 SRM 51-21-11.APPLIED TOPCOAT IAW A320 SRM 51-75-12. REMOVED AND REPLACED STRINGER IAWA320 SRM 51-42-11 AND AIRBUS DWG #D53480030. REMOVED AND INSTALLED SPLICEIAW A320 SRM 51-42-11.

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

AFT WET AREA LH SIDE STR 36 AT FR67 TO FR68 HAS CORROSION GROUNDED - YES. NO LIMITS FOUND FOR AREA.ANALED MATERIAL DAN50BC8 PO. 1069950.1 IAW A320 SRM 51-25-00.JOGGLED STRINGER IAW AIRBUS DWG #D53480030.HEAT TREATED STRINGER IAW A320 SRM 51-25-00.LOCATED DRILLED AND DEBURRED STRINGER AND MATERIAL ABS5058A306 PO. 1070915.1 IAW A320 SRM 51-44-11.ALODINED AND PRIMED IAW A320 SRM 51-21-11.APPLIED TOPCOAT IAW A320 SRM 51-21-11.REMOVED AND REPLACED STRINGER AND SPLICE IAW A320 SRM 53-41-13.REMOVED AND INSTALLED SHEAR TIE AND CLIP IAW A320SRM 51-42-11

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

AFT WET AREA LH SIDE STR 29 AT FR65 TO FR69 HAS CORROSION GROUNDED - YES. NO LIMITS FOUND FOR AREA.LOCATED DRILLED AND DEBURRED MATERIAL DAN 50808 PO. 1069688.1 IAW A320 SRM 51-44-11 AND AIRBUS DWG D53480052.ALODINED AND PRIMED IAW A320 SRM 51-21-11.TOPCOATED IAW A320 SRM 51-23-11.REMOVED AND REPLACED 2EA SECTOPMS FROM FR64-FR70 IAW A320 SRM 51-42-11 AND AIRBUS DWG # D53480052.REMOVED AND INSTALLED 2EA SPLICES AND 1EA STRINGER CLIP IAW A320 SRM 51-42-11 AND AIRBUS DWG # D53480052.

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

AFT WET AREA LH SIDE STR 31 AT FR65 TO FR69 HAS CORROSION GROUNDED - YES. NO LIMITS FOUND FOR AREASLOCATED DRILLED AND DEBURRED MATERIAL DAN50B08 PO 1069688.1 IAW A320 SRM 51-44-11 AND AIRBUS DWG # D53480046 ALODINED AND PRIMED IAW A320 SRM 51-21-11.TOPCOAT APPLIED IAW A320 SRM 51-75-12.REMOVED AND REPLACED SECTIONS S31L FROM FR64-FR69 IAW A320 SRM 51-42-11 AND AIRBUS DWG # D53480046

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

AFT WET AREA LH SIDE STR 28 AT FR65 TO FR69 HAS CORROSION GROUNDED - YES. NO LIMITS FOR AREA. LOCATED, DRILLED AND DEBURRED STRINGER MATERIAL DA50BC8 P.O. 1069950.1 IAW A320 SRM 53-41-13. LOCATED, DRILLED AND DEBURRED MATERIAL 2024-T351 P.O. 1070120.1 IAW A320 SRM 51-44-11. MECHANICAL MATERIAL IAW A320 DWG #D53480046. ALODINED AND PRIMED STRINGER SECTIONS ANDSPLICE IAW A320 SRM 51-21-01. TOPCOAT APPLIED IAW A320 SRM53-41-13. REMOVED AND REPLACED STRINGER SECTIONS AND SPLICE IAW A320 SRM 51-42-11 AND AIRBUS DWG#D53480505. REMOVAL AND INSTALLED FWD SPLICE AND 2EA STRINJER CLIPS IAW A320 SRM 51-42-11 AND AIRBUS DWG #D53480505.

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

AFT WET AREA LH SIDE STR 26 AT FR67 TO FR68 HAS CORROSION GROUNDED - YES. NO LIMITS FOR STRINGERS FOUND. REMOVED STRINGER AND 4EA STRINGER CLIPS IAW A320 SRM 51-42-11. ANNOTED MATERIAL DAV 50B08 NO. 1069688.1 IAW A320 SRM 51-25-00. FORMED STRINGER SECTIONS IAW A320 SRM 51-72-11. HEAT TREATED SECTIONS IAW A320 SRM 51-25-00. LOCATED AND FILLED AND DEBONDED IAW AMC SRM 53-41-13. ALODINED AND PRIMED IAW A320 SRM 51-21-11. TOP COATED IAW A320 SRM 51-23-11. FABRICATED REPAIR COUPLER MAT. DAN 51B6/4B5 5058A306 IAW A320 SRM 53-41-13. ALODINED AND PRIMED IAW A320 SRM 51-21-11. TOPCOATED APPLIEDIAW A320 SRM 51-23-11. INSTALLED 526L FROM FR64 TO FR67 IAW A320 SRM 51-21-11. INSTALLED 4EA CLIPS AND COUPLER IAW A320 SRM 51-42-11.REMOVED AND INSTALLED 3EA AIR DUCTS IAW A320 AMM 21-20-00 AND 1EA WASTE TUBE IAW A320 AMM 38-58-00

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,746 hrs · 18,418 cycles

AFT WET AREA LH SIDE STR 27 AT FR65 TO FR69 HAS CORROSION GROUNDED - YES. NO LIMITS FOR STRINGER REMMOVED STRINGER 27, FR-64 TO FR-69 AND SPLICES IAW IAW A320 SRM 51-42-11. ANNEALED MATERIAL DAN 50808 P.O. 1069688.1 IAW A320 SRM 51-25-00. FORMED SECTIONS IAW A320 SRM 51-22-11. HEAT TREAT IAW A320 SRM 51-25-00. LOCATED DRILLED AND DEBURRED SECTIONS IAW A320 SRM 51-44-11.ALODINED AND PRIMED IAW A320 SRM 51-21-11. TOPCOAT APPLIED IAW A320 SRM 51-23-11. INSTALLED SECTIONS AND SPLICE IAW A320 SRM 51-42-11 AND A320 SRM 53-41-13.

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,746 hrs · 18,418 cycles

AFT WET AREA LH SIDE STR 35 AT FR65 TO FR68 HAS CORROSION GROUNDED - YES. NO LIMITS FOUND CORRODED STRINGER CUTOUT STRINGER SECTION 53JL AT FR64-FR66 IAW A320 SRM 53-41-14. RECIVED NEW STRINGER MATERIAL DAN5058A306 P.O.1070915.1 HFEC CUT IAW NTM 51-10-08 NO DAMAGE NOTED T#78257F. LOCATED, DRILLED AND DE-BURRED. IAW A520 SMM 55-41-13. ALODINED IAW A320-SRM 51-21-11. PRIMED & TOPCOATED IAW AW SRM 53-41-13. INSTALLED STRINGER IAW A320 SRM 53-41-13. ALODINED IAW A320 SRM 51-21-11. PRIMED AND TOPCOATED IAW A320 SRM 53-41-13. INSTALLED IAW A320SRM 53-41-13. REMOVED AND INSTALLED 2EA SHEAR TIES IAW A320 SRM 51-42-11 AND AIRBUS DWG#D53480054.

Part: STRINGER — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

AFT WET AREA LH SIDE STR 33 AT FR65 TO FR69 HAS CORROSION GROUNDED - YES. NO LIMITS GIVEN IN SRM FOR THIS AREA.LOCATED, DRILLED AND DEBURRED NEW STR 33L MATERIAL DAN50B08 PO# 1069688.1 IAW ASA A320 SRM 51-72-11-911-001 AND SRM 51-44-11.ALODINED, PRIMED AND PAINTED NEW STRINGER IAW ASA A320 SRM 51-21-11/001.REMOVED AND REPLACED STR 33L SECTION FROM FR 64-69 IAW ASA A320 SRM 51-72-11-911-001 AND AIRBUS DWG # 53480008.REMOVED AND REINSTALLED 3 EA STRINGER CLIPS 1 EA ELECTRICAL BRACKET AND STR 33L CONNECTING SPLICE AT FR64L IAW ASAA320 SRM 51-42-11 AND AIRBUS DWG #D53480008.

Part: FLOOR SUPPORT — CORRODED (FRMS 66-70) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

AFT WET AREA FLOOR BEAM -969 HAS CORROSION AROUND AFT HARDPOINT GROUNDED - YES. BEAM-LONGIITUDINAL AT -969, NO DAMAGE ALLOWED AT HARDPOINTS, FOUND TO BE OUT OF LIMITS REF. A320 SRM 53-41-14-283-009. REMOVED AND REPLACED BEAM-LONGITUDINAL P/N D5347219320200, PO: 1068255.1 REF AIRBUS DWGS D53472040 REV. A (FR66) TO (FR70) AND A320 SRM 51-42-11

Part: FLOOR PANEL — DELAMINATED (UNKNOWN) · airframe 48,676 hrs · 18,384 cycles

MAIN CABIN FLOOR PANEL 231XF IS DELAMINATED GROUNDED - YES. EVALUATED AND REPAIRED DELAMINATED AREA OF FIBERGLASS TOP LAYER ON MAIN CABIN FLOOR PANEL 231XF IAW A320-200 SRM REV 146 53-02-00-283-001 AND A320-200 SRM 53-02-00-300-013 THIS IS A CATEGORY A PERMENANT REPAIR FH-48745:53 FC-18418 WV-010

Part: WEB — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

LH SIDE FR69 TO FR70 AT STR23 SHEAR WEB THAT ATTACHES TO SHEAR PLATE HAS MULTIPLE AREAS OF CORROSION ON BOTTOM SIDE GROUNDED - YES. NO LIMITS FOUND FOR SHEAR WEB FOUND. LOCATED, DRILLED AND DEBURRED WEB P/N D5347112320200 P.O.907924.4. IAW A320SRM 51-44-11. REMOVED AND REPLACED SHEAR WEB IAW A320 SRM 51-42-11 AND AIRBUS DWG# D53470100.

Part: STRAP — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,676 hrs · 18,384 cycles

LH FR70 HAS A CORRODED STRAP FROM STR24 TO STR28 GROUNDED - YES. NO ALLOWABLE LIMITS IN A320 SRM FOR FRAME STRAP. REMOVED AND REPLACED STRAP IAW A320 SRM 51-42-11 AND A320 DWG D53570020

Part: BEAM — CORRODED (DOOR SILL) · airframe 48,676 hrs · 18,384 cycles

DOOR SILL AT FR68 HAS CORROSION GROUNDED - YES. REMOVED CORROSION FROM L2 DOOR SIL AT FR68, REMOVED 0.032", ORIGINAL MATERIAL 0.063", REMAINING MATERIAL 0.031" FOUND TO BE OUT OF LIMITS IAW A320 SRM 53-41-14-283-002. "MAJOR REPAIR ACCCOMPLISHED- LH FUSELAGE AFT PASSENGER (L2) SILL BEAM, FR68 SRM REPAIR EDGE DISTANCE DEVIATION-REPAIR PERFORMED IN ACCORDANCE WITH AIRBUS DOSSIER 81291182 WITH APPROVAL PER RDAF 81291182/003/2023 ISSUA A DATED 06-NOV-2023. THIS IS A CATEGORY "A" REPAIR.

Part: FLOOR PANEL — DELAMINATED (UNKNOWN) · airframe 48,745 hrs · 18,418 cycles

MAIN CABIN FLOOR PANEL 231KF IS DELAMINATED GROUNDED - YES. EVALUATED AND REPAIRED 2EA AREAS OF DELAMINATED FIBERGLASS TOP LAYER ON MAIN CABIN FLOOR PANEL 231KF IAW A320-200 SRM 53-02-00-283-001 AND A320-200 SRM 53-02-00-300-013. FH-48745:53 FC-18418 WV-010 THIS IS A CATEGORY A PERMENANT REPAIR.

Part: BEAM — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,742 hrs · 18,417 cycles

FWD WET AREA FR18-FR20 CORROSION ON TOP SURFACE OF CENTER RIGHT AXIS Y-254 LONGITUDINAL BEAM GROUNDED - YES. EVALUATED CORROSION ON BEAM, FOUND TO BE OUT OF LIMITS IAW A320 SRM 53-11-14-283-007. REMOVED AND REPLACED LONGITUDINAL BEAM IAW AIRBUS DWG D53111461 ISSUE A & A320 SRM 51-42-11.

Part: BEAM — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,745 hrs · 18,418 cycles

FWD WET AREA FR16-FR20 CORROSION ON TOP SURFACE OF CENTER LEFT AXIS Y254 LONGITUDINAL BEAM GROUNDED - YES. REMOVED CORROSION FROM LONGITUDINAL BEAM (TRACK) BETWEEN FR16-FR20,CENTER LEFT AXIS Y254, ORIGINAL THICKNESS 0.071", REMOVED 0.029", REMAINING MATERIAL 0.042" BLEND AREA. 2.0"W AND 18.0"L. FOUND TO BE OUT OF LIMITS REF A320 SRM 53-11-14-283-007: REMOVED AND REPLACED LONGITUDINAL BEAM (TRACK) P/N D5311281820401 PO: 1068071.1 REF AIRBUS DWG D53112816 REV G AND A320 SRM 51-42-11

Part: BEAM — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,745 hrs · 18,418 cycles

MAIN CABIN AFT WET AREA R/H LONGITUDINAL BEAM BETWEEN FRAMES 69 ABD 70 AXIS -Y160.5 CORRODED ON UPPER SURFACE. GROUNDED - YES. REMOVED CORROSION FROM MAIN CABIN AFT WET AREA R/H LONGITUDINAL BEAM BETWEEN FRAMES 69 AND 70. AXIS -Y160..5, ORIGINAL THICKNESS 0.150", REMOVED 0.117", REMAINING MATERIAL 0.033" FOUND TO BE OUT OF LIMITS REF. A320 SRM 53-91-14-283-009. REMOVED AND REPLACED LONGITUDINAL BEAM P/N D5347219720200, PO: 1067617.1 REF. AIRBUS DWG. D53472040 REV,.A AND A320 SRM 51-24-11.

Part: WEB — CORRODED (UNKNOWN) · corrosion level 2 · airframe 48,746 hrs · 18,418 cycles

MAIN CABIN AFT WET AREA L/H LATERAL SHEAR PLATE BETWEEN FRAMES 69 AND 70, CORRODED ON UPPER SURFACE GROUNDED - YES. SHEAR PLATE FOUND OUT OF LIMITS DUE TO NO LIMITS FOUND. REMOVED SHEAR PLATE IAW A320 51-42-11. LOCATED DRILLED AND DEBURRED SHEAR PLATE P/N D534711242020000 P.O. 1067609.3 IAW A320 SRM 51-44-11 AND DWG# D53470100. INSTALLED SHEAR PLATE IAW A320 SRM 51-42-71 AND DWG# D53470100.

Part: STRINGER — CORRODED (FRAMES 56-57) · corrosion level 2 · airframe 45,956 hrs · 16,867 cycles

AFT CARGO COMPT STRINGER HAD CORROSION AT FR 56-57 STRINGER 42L. GROUNDED - YES. ACCOMPLISHED SPLICE REPAIR ON AFT CARGO COMPT STRINGER 42L AT FR 56-57, IAW EA A320-53EA-00614.

Part: STRINGER — CORRODED (FRAMES 56-57) · corrosion level 2 · airframe 45,956 hrs · 16,867 cycles

AFT CARGO COMPT STRINGER HAD CORROSION AT FR 56-57 STRINGER 43L. GROUNDED - YES. ACCOMPLISHED SPLICE REPAIR OF AFT CARGO COMPT STRINGER 43L AT FR 56-57, IAW EA A320-53EA-00614.

Part: DOOR SILL — CORRODED (FRAMES 16-17) · corrosion level 2 · airframe 41,440 hrs · 15,060 cycles

L1 DOOR SURROUND LWR SILL HAS CORROSION AT FWD GIRT BAR FITTING AFT O/B ATTACH HOLE. GROUNDED - YES. REWORKED L1 DOOR LOWER SILL FWD GIRT BAR ATTACH FITTING ATTACH HOLE (O/B AFT) IAW AIRBUS SRM 53-11-14-283-005.

Part: DOOR SILL — CORRODED (FRAMES 19-20) · corrosion level 2 · airframe 41,440 hrs · 15,060 cycles

L1 DOOR SURROUND LWR SILL HAS CORROSION AT AFT GIRT BAR FITTING FWD ATTACH HOLES. GROUNDED - YES. REWORKED L1 DOOR LOWER SILL AFT GIRT BAR ATTACH FITTING FWD ATTACH HOLES IAW AIRBUS SRM 53-11-14-283-005.

Part: FITTING — CORRODED (R1 GIRT BAR) · corrosion level 2 · airframe 41,440 hrs · 15,060 cycles

R1 DOOR CORROSION UNDER FWD GIRT BAR FITTING. GROUNDED - YES. REWORKED R1 DOOR LOWER SILL FWD GIRT BAR ATTACH FITTING ATTACH HOLES (3EA) IAW AIRBUS SRM 53-11-14-283-005.

Part: SEAT TRACK — CORRODED (FRAMES 12-24) · corrosion level 2 · airframe 41,440 hrs · 15,060 cycles

MAIN CABIN R/H SEAT TRACK AT-Y1292 HAS CORROSION AT FR20. GROUNDED - YES. REMOVED AND REPLACED BEAM IAW A320 SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FRAME 16) · corrosion level 2 · airframe 41,440 hrs · 15,060 cycles

MAIN CABIN FWD WET AREA LH FLOOR SUPPORT AT Y254 HAS CORROSION AT FR16. GROUNDED - YES. REPAIRED FLOOR SUPPORT IAW A320 SRM 53-00-14-300-007 AND ALASKA EC/TC 5311.000033.

Part: FLOOR SUPPORT — CORRODED (FRAME 68) · corrosion level 2 · airframe 41,440 hrs · 15,060 cycles

MAIN CABIN FLOOR SUPPORT AT Y1165 HAS CORROSION AT FR68. GROUNDED - YES. REMOVED AND REPLACED R2 DOOR LOWER SILL IAW A320 SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FRAME 16) · corrosion level 2 · airframe 41,440 hrs · 15,060 cycles

MAIN CABIN FWD WET AREA FLOOR STRUCTURE AT Y509 HAS CORROSION AT FR16. GROUNDED - YES. REMOVED AND REPLACED BEAM IAW A320 SRM 51-42-11.

Part: SHEAR PLATE — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 41,440 hrs · 15,060 cycles

RIGHT HAND AFT WET AREA FLOOR STRUCTURE-SHEAR PLATE FR69-FR70 HAS CORROSION. GROUNDED - YES. REMOVED AND REPLACED FRAME SUPPORT IAW A320 SRM 51-42-11.

Part: GIRT BAR — OBSTRUCTED (L2 DOOR SLIDE)

DURING TROUBLESHOOTING OF RMA 1828, INTERMITTENT RESIDUAL CABIN PRESSURE INDICATION, FOUND MOORING LINE OBSTRUCTING GIRT BAR SEATING WHEN L2 DOOR IS ARMED MOORING LINE SHOWS SIGNS OF WEAR. REPLACED L2 DOOR ESCAPE SLIDE PACK ASSY, OPS CHECKED GOOD IAW AMM 256244PB401. ALL OPERATIONS WERE VERIFIED NORMAL AND THE ACFT OPERATES WITHOUT REPEAT DEFECT AT THIS TIME. ACCORDING TO THE OPERATORS RECORDS, ALL AIRWORTHINESS DIRECTIVES, SERVICE BULLETINS, STC`S AND PMA`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REQUIREMENTS.

Part: FAN — DAMAGED (EXTRACT)

FLIGHT EXPERIENCED AN EXTRACT FAN FAULT MESSAGE ON ECAM AND ELECTRICAL BURNING ODOR, THE FLIGHT CREW DECLARED AN EMERGENCY AND LANDED SAFELY. DURING FLIGHT, A LOUD HUM FROM AVIONICS BAY ACCOMPANIED BY A FAINT ODOR OF BURNING ELECTRICAL. ACCOMPLISHED INSPECTION IAW TSM 05-50-00-81-08-31A, ODOR OF SMOKE IAW ITEM 22-62-60-203. VENT EXTRACT FAULT INFLIGHT MASTER CAUTION. BENT EXTRACT FAN DAMAGE.

Part: ECU — FAULTY (CABIN) · airframe 33,427 hrs · 12,469 cycles

ELECTRICAL ODOR IN FIRST CLASS AREA. COMING FROM SEAT 1A-1C. PERFORMED INSPECTION IAW TSM 05-50-00-810-831-A, FOUND ODOR COMING FROM SEAT 1A-1C. PLACED SEATS ON NEF 25-0061, MDDR 37766, MOC NOTIFIED, UPDATED NEF LOG. NO FURTHER REPORTS OF ODOR. ECU IS SCHEDULED TO BE REPLACED NEXT MAINTENANCE OPPORTUNITY. ALL OPS WERE VERIFIED NORMAL AND THE AIRCRAFT OPERATES WITHOUT REPEAT DEFECT AT THIS TIME.

Part: BUSHING — WORN (GUST LOCK)

ACFT ARRIVED, MAINTENANCE RECEIVED A VERBAL REPORT OF THE GUST LOCK ON R1 DOOR NOT LOCKING. MAINTENANCE IDENTIFIED NYLON BUSHINGS WERE WORN. REPLACED IAW AMM 52-11-12-00-802. ACFT RETURNED TO SERVICE.

Part: BUSHING — WORN (GUST LOCK)

REPORT THAT THE GUST LOCK ON R1 DOOR NOT LOCKING. NYLON BUSHINGS WERE WORN, REPLACED THE BUSHINGS IAW AMM 52-11-12-00-802. ACFT RETURNED TO SERVICE.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 24,850 hrs · 27,588 cycles

DURING THE IN-FLIGHT CABIN CHECK, AFT MONUMENT RED EMERGENCY LIGHT ASSY WAS FOUND DISLODGED AND DISCOVERED WIRE BROKEN AT CONNECTOR 7704VS. WIRE REPAIRED IAW ESPM 20-48-24 AND RECONNECTED, THE LIGHT ASSY WAS SECURED BACK INTO ITS MOUNT. CHECKED IAW AMM 33-51-00 WITH NO FAULTS. THE ACFT WAS RELEASED TO SERVICE, NO FURTHER ISSUES NOTED.

Part: WIRE HARNESS — FAILED (EMERGENCY LIGHT) · airframe 22,390 hrs · 9,279 cycles

DURING A DAILY CHECK, EMERGENCY LIGHT AT SEAT ROW 19A-C INOPERATIVE. TTROUBLESHOT TO AN IN-SEAT HARNESS. NEW HARNESS INSTALLED. THE SEAT EMERGENCY LIGHT OPERATED NORMALLY.

Part: SILL — CORRODED

RT AFT DOOR SILL HAS TWO AREAS OF CORROSION BETWEEN FR 67-68, ST 23-24 AT RBL 56. EXTENT OF DAMAGE IS 1" LENGTH 1.250 WIDTH AND .045" DEPTH. THE SECOND AREA IS 1" LENGTH 1.300 WIDTH AND .066 DEPTH. REPAIRED IAW SRM 53-41-14, FIG 201.

Part: SHEAR PLATE — CORRODED (FUSELAGE)

RT AFT SHEAR PLATE BETWEEN FR 69-70, ST 23-24 RT, CORRODED BEYOND LIMITS. EXTENT OF DAMAGE 4" L X 2" W X .070 D.

Part: FITTING — CRACKED (NR 1 PYLON)

WHILE PERFORMING TASK 545172-01-1L, A CRACK WAS IDENTIFIED ON THE NR 1 PYLON OTBD FITTING AT RIB 11. REPORTED TO BE .50". REPLACED INBD AND OTBD PYLON CORNER FITTINGS AT RIB 11.

Part: FITTING — CRACKED (NR 2 PYLON)

PERFORMING TASK 5545172-01-1R. CRACK WAS IDENTIFIED ON THE NR 2 ENG PYLON INBD FITTING AT RIB 11, REPORTED TO BE .50". REPLACEED INBD AND OTBD PYLON CORNER FITTINGS AT RIB 11.

Part: DISPLAY — MALFUNCTIONED (COCKPIT) · airframe 20,003 hrs · 8,561 cycles

CREW REPORTED "NR 1 MCDU WENT BLANK AND HAD MINOR SMOKE" ON LOG PAGE 675912. THE CREW LATER STATED THAT IT WAS MORE OF AN ODOR OF SMOKE COINCIDING WITH THE MCDU GOING BLANK. THE ACFT WAS IN FLIGHT AT THE TIME, DECLARED AN EMERGENCY, AND RETURNED TO THE POINT OF DEPARTURE WITHOUT FURTHER INCIDENT. THE FAILED MCDU FROM FLIGHT 210, PN 4077880-982, SN 00062162 WAS ON ITS FIRST FLIGHT LEG INSTALLED IN THE ACFT. IT HAD BEEN INSTALLED AFT THE PREVIOUS FLIGHT HAD A FAILURE OF ITS MCDU WHILE ENROUTE, NO SMOKE OR OTHER ABNORMALITIES OTHER THAN THE MCDU BEING INOPERATIVE WERE REPORTED ON THAT FLIGHT LEG, LOG PAGE 675911. THE FIRST MCDU THAT FAILED WAS PN 4089740-961, SN 32199899. FINALLY, A 2ND REPLACEMENT MCDU WAS INSTALLED, PN 4077880-982, SN 31902805. ALL OPS WERE VERIFIED NORMAL AND THE ACFT OPERATES WITH OUT REPEAT DEFECT AT THIS TIME.

Part: HYDRAULIC LINE — LEAKING (HYDRAULIC SYS)

ACFT WAS OPERATING FLIGHT. APPROX AN HOUR PRIOR TO ARRIVAL AT DESTINATION, THE CREW SENT AN ACARS MESSAGE STATING LOSS OF GREEN HYD SYS QUANTITY AT 2056Z. MC RESPONDED WITH QUESTIONS OF QUANTITY AND IF ANY OTHER ECAM RELATED MESSAGES. REPLY FROM CREW STATED NO QUANTITY AND MULTIPLE INOP SYS ASSOCIATED. CREW REQUESTED RUNWAY 25R AND MEET FROM MX/TOW CREW. A CONFIRMATION FROM THE DISPATCHER WAS RECEIVED AT 2141Z THAT THE CREW HAD DECLARED AN EMERGENCY. THE ACFT MADE AN UNEVENTFUL LANDING AT 2212Z, WAS MET BY THE TOW TEAM AND MX AND PULLED INTO THE GATE. BRAKES SET AT 2247Z. INSPECTION REVEALED A PINHOLE LEAK ON THE GREEN SYS NR 1 ENGINE HOSE, REF IPC 29-13-49-01A, ITEM 220C, PN 112441-507. THE HOSE AND CLAMP WERE REPLACED ALONG WITH THE GREEN SYS HYD FILTER. THE SYS STILL HAD 2.5 GALLONS REMAINING. THE LANDING GEAR EXTENSION SYS WAS RE-SYNCHED AND PLACED BACK TO NORMAL CONFIGURATION IAW AMM 32-00-00-860-003. ALL OTHER REQUIRED LEAK AND OPS CHECKS WERE CARRIED OUT. THE ACFT WAS RETURNED TO SERVICE.

Part: SLIDE — DISLODGED (R2 DOOR)

R2 DOOR SLIDE UNRAVELED. FOUND ON GROUND AFTER CATERING WAS LEAVING THROUGH R2 DOOR AND COULD NOT GET DOOR CLOSED. AFTER INSP BY MX, FOUND SLIDE HANGING DOWN FROM ITS PACKING. SLIDE WAS NOT BLOWN AND GIRT BAR DID NOT APPEAR TO BE PULLED OUT, R & R SLIDE AS REQUIRED. SLIDE SENT TO SHOP FOR INVESTIGATION.