N310NW

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 79,725 hrs · 36,043 cycles

DURING EMERGENCY LIGHT SYSTEM TEST, FOUND RIGHT POWER SUPPLY UNIT INOPERATIVE. REPLACED THE BATTERY PACK AND POWER SUPPLY.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 79,585 hrs · 35,986 cycles

RT FWD EMERGENCY OVERWING HANDLE EMERGENCY LIGHT INOPERATIVE, REPLACED THE LAMP.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 79,585 hrs · 35,986 cycles

RT AFT OVERWING HANDLE EMERGENCY LIGHT INOPERATIVE, REPLACED THE LAMP.

Part: SKIN — DAMAGED (PAX DOOR) · airframe 79,479 hrs · 35,939 cycles

EVIDENCE REWORK PASSENGER CREW DOOR 832 EXTERNAL SKIN LOCATED 15" FROM LOWER EDGE AND 30.5" FROM FWD EDGE AT AFT GALLEY AREA. PERFORMED PERMANENT REPAIR ON PASSENGER CREW DOOR 832 EXTERNAL SKIN LOCATED 15" FROM LOWER EDGE AND 30.5 FROM FWD EDGE AT AFT GALLEY AREA AS PER SRM 52-10-00 PARAGRAPH 5F FIG 206

Part: ACCESS PANEL — CORRODED (RT WING) · airframe 79,476 hrs · 35,938 cycles

CORROSION ON ACCESS PANEL 640JB ON RT WING. REPLACED ACCESS PANEL 640JB ON RT WING

Part: ACCESS PANEL — CORRODED (LT WING) · airframe 79,476 hrs · 35,938 cycles

CORROSION ON ACCESS PANEL 540PB FUEL TANK ON LT WING. REPLACED ACCESS PANEL 540PB ON LT WING.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 79,476 hrs · 35,938 cycles

EXISTING REWORK ON EXTERNAL SKIN AT LOWER FUSELAGE TO FRAME 31+17" BETWEEN STRINGER 42R TO STRINGER 43R, PERFORMED PERMANENT REPAIR ON EXTERNAL SKIN BTW FR31TO FR32 AND BTW STR41R TO STR 44 AT LOWER FUSELAGE AS PER SRM 53-00-11 PARAGRAPH 4 W AND FIG 238.

Part: LIGHT — BROKEN (CABIN) · airframe 78,312 hrs · 35,328 cycles

ROW 7ABC EMERGENCY SEAT LIGHT INOPERATIVE, REPAIRED BROKEN .

Part: WIRE — BROKEN (EMERGENCY LIGHTS) · airframe 74,766 hrs · 33,625 cycles

DURING NON-ROUTINE CHECK, FOUND CABIN EMERGENCY LIGHTS INOPERATIVE AT SEAT ROW 7AB. T/S AND FOUND BROKEN WIRE AT CABIN SEAT ROW 7 A/B. SPLICED WIRE AND FUNCTIONAL CHECK WAS NORMAL.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 70,960 hrs · 31,766 cycles

DURING CHECK, FOUND SEAT 7ABC EMERGENCY SEAT LIGHT INOPERATIVE. REPAIRED A BROKEN WIRE UNDER SEAT. FUNCTIONAL CHECKED NORMAL.

Part: WIRE — BROKEN (EMERGENCY LIGHT) · airframe 69,006 hrs · 30,761 cycles

DURING IINSPECTION, FOUND EMERGENCY PATH LIGHT AT SEAT 6 WIRE BROKEN UNDER 6A. MX RECONNECTED WIRE AT 6A AND FUNCTIONAL CHECK WAS NORMAL.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO FLOOR PANEL 152QF DAMAGED WITH DIM OF DAMAGED L=2" X W=1.5". FABRICATED NEW FLOOR PANEL IAW AMM 25-50-00-340-007.

Part: SILL — CORRODED (CARGO DOOR) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO PIT DOOR SILL HAS CORROSION IN SEVERAL PLACES AS MARK NR 130/54. REMOVED CORROSION IAW SRM 51-74-00, NO ESTABLISH LIMITS. REMOVED DOOR SILL PLATE IAW SRM 51-42-11, FABRICATED SILL PLATE FROM MATERIAL 2024-T3 .100' IAW SRM 53-21-29 AND DWG D532231322. FABRICATED 1EA DOUBLER ON STAM TRAVELER T12/974692. ASSOCIATED ER/A 32-509267 ADDED FOR AC 3210. INSTALLED DOOR SILL PLATE IAW SRM 51-42-11. REPAIR OF DOOR SILL THRESHOLD WEB AND DOOR SURROUND SILL PLATE ACCOMPLISHED ON FINAL ERA 509267-14, SECTION 1.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO FLOOR PANEL 152RF DAMAGED AND DAMAGE DIM L=3" X W=2". FABRICATED NEW FLOOR PANEL IAW AMM 25-50-00-340-007.

Part: SUPPORT ANGLE — CORRODED (DOOR FRAME) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LT FWD OVERWING EMERGENCY EXIT DOOR AFT VERTICAL FRAME ANGLE SUPPORT CORRODED. REMOVED VERTICAL FRAME ANGLE SUPPORT IAW SRM 51-42-11. RECEIVED NEW ANGLE SUPPORT, PN D5227905420400 BATCH NR: 0002049167. INSTALLED NEW VERTICAL FRAME ANGLE SUPPORT IAW SRM 51-42-11.

Part: BEAM — CORRODED (EMERGENCY EXIT) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD LT OVERWING EMERGENCY EXIT DOOR CURVED BEAM HAS CORROSION. REMOVED CORROSION FROM CURVED BEAM IAW SRM 51-74-00 AND CHECK LIMITS ORIG THICK .039" AFTER REWORK .033" MAT. LOSS .006" NO ESTABLISH LIMITS IN SRM. BLENDED AREA L=5.5" W=3.5" D=.006" IAW SRM 52-20-00, TABLE 103. RECEIVED NEW CURVED BEAM, PN D5227902820400 BATCH NR 0002370531. INSTALLED NEW CURVED BEAM IAW SRM 51-42-11 AND 52-20-00, FIG 201.

Part: ATTACH FITTING — CHAFED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND CHAFED MARK ON LT AFT PAX DOOR ASSIST CYLINDER ATTACHMENT FITTING. BLENDED OUT DAMAGE IAW SRM 51-73-00. DIM OF REWORK L=.4", W=.2", D=.008", NO ALLOWABLE LIMITS PROVIDED. HFEC ACCOMPLISHED IAW NTM 51-10-08, NO CRACKS OR OTHER DISCREPANCIES REPORTED. NO ADDITIONAL DAMAGE TO ADJACENT STRUCTURE DETECTED AND CAUSE WAS UNABLE TO BE DETERMINED. COMPLY WITH FINAL ER/A 509270-14 REV ORIGINAL SECTION I PERMANENT REPAIR.

Part: PLATE — DAMAGED (LT WING LE SLAT) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LT WING SLAT TRACK NR 6, CLOSING PLATE CHAFING WITH SLAT LOWER T/E. BLENDED OUT CHAFE DAMAGE IAW SRM 51-73-00. DIM OF REWORK L=3.2", W=.25", D=.012". FOUND OUT OF LIMITS IAW SRM 57-40-00, FIG 106. ACCOMPLISHED DVI IAW NTM 51-90-00 AND HFEC IAW NTM 51- 10-08, NO ADDITIONAL DISCREPANCIES NOTED. COMPLIED WITH FINAL ER/A 509268-14 REV. ORIGINAL SECTION I PERMANENT REPAIR.

Part: FRAME — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND RT AFT PASSENGER DOOR SILL AFT FRAME 66, UPPER SURFACE AROUND NUT PLATE HOLES HAS CORROSION. BLENDED OUT CORROSION IAW SRM 51-74-00. DIM. L=2", W=1.3", D=.035". FOUND OUT OF LIMITS IAW SRM 53-41-14, FIG1, SH2. ACCOMPLISHED ROTO PROBE IAW NTM 51-10-01 AND HFEC IAW NTM 51-10- 02 AND 51-10-08, NO ADDITIONAL DISCREPANCIES. REPAIRED CUT-OUT IAW SRM 53-41-14, FIG 201, PRINCIPLE I AND ER/A 506770-14 REV0. FABRICATED REPAIR ANGLE ON STAM TRAVELER T12/973259, SHIM AND FILLER OUT OF 2024T3 .160". COMPLIED WITH FINAL ER/A 506770-14 REV ORIGINAL.

Part: RIB — CORRODED (LT WING TE FLAP) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LT OTBD FLAP, INBD RIB L/E HAS 2 AREAS OF PITTING AFTER RUB STRIP REMOVAL. BLENDED CORROSION IAW SRM 51-74-00, AREA L 1 =1.5" W=1.0 "D =0.028"AREA 55"W=0.070" D=0.030". ACCOMPLISHED ER/A 508976-14 REV ORIGINAL SECTION I PERMANENT REPAIR STEPS 1-8.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FLOOR PANEL 241AF IS SOFT AND SPONGY. REMOVED CABIN FLOOR PANEL IAW MM 53-12-12-000-001-A. FABRICATED FLOOR PANEL IAW SRM 53-02-00, FIG 209 & INSTALLED IAW AMM 53-12-12000-001-A.

Part: PANEL — DAMAGED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO SLOPE PANEL 151HF HAS EDGE DAMAGE BEYOND ALLOWABLE LIMITS. SLOPE PANEL FABRICATED IAW 53-02-00. DAMAGE LOCATED AT EDGE OF CUTOUT 2.00" LONG W=2.0 OUT OF LIMITS IAW SRM 53-02-00.

Part: PANEL — PUNCTURED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO SLOPE PANEL 162EF MULTIPLE PUNCTURES. SLOPE PANEL FABRICATED IAW FIG 209, DIAMETER OF PUNCTURE .350 AREA (1) .400 AREA (2) FOUND OUT OF LIMITS IAW SRM 53-02-00.

Part: PANEL — CRACKED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO SLOPE PANEL 151CF CRACKED 6.0 INCHES LONG. SLOPE PANEL FABRICATED IAW SRM 53-02-00, FIG 209 L=6.0, W=.100 OUT OF LIMITS IAW 53-02-00.

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO BAY AT FRAME 58, STR 44 BEAM HAS CORROSION. REMOVED CORROSION IAW 51-74-00. AREA MEASURES L=1.0"X W=.80"X D=.012" ORG MAT .079, NO LIMITS FOUND IN SRM. R & R BEAM AT STR 44 BETWEEN FR 58 AND 59 IAW SRM 51-42-11.

Part: ATTACH BRACKET — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO COMPT FRAME 58, STR 36-38L, SEAL PLATE ATTACHMENT BRACKET HAS CORROSION. FOUND AFTER SEAL PLATE REMOVAL. REMOVED CORROSION IAW SRM 51-74-00 L=.600, W=.250, D=.100. ORIG MAT .120 NO LIMITS FOUND IAW SRM. REMOVED FITTING IAW SRM 51-42-11. LOCATED AND DRILLED NEW FITTING IAW SRM 51-44-11. INSTALLED NEW FITTING IAW SRM 51-42-11.

Part: CARRIAGE — GOUGED (NR 1 FLAP TRACK) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND RT WING NR 1 FLAP TRACK, FLAP CARRIAGE FWD LOWER TRACK HAS GOUGE (2 EA). ACCOMPLISHED RT WING NR 1 FLAP TRACK, FLAP CARRIAGE FWD LWR TRACK REPAIR BY BLENDING AREA IAW SRM 51-73-00, OTBD L=1.400"W=.250"D =.003", INBD L=1.400"W=.250"D=.003"& ACCOMPLISHED FINAL ER/A 509266-14, REV ORIGINAL.

Part: FLOOR PANEL — CORRODED (ZONE 100) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD UTILITY FLOOR PANEL 221FF CORRODED ON LWR SURFACE 3.5" X 2.0". REPLACED FLOOR PANEL IAW SRM 51-72-00.

Part: WEB — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FORWARD CABIN RT SIDE AT FR 16 STRINGER 23 UPPER SURFACE WEB HAS CORROSION. REMOVED CORROSION IAW SRM 51-74-00. CHECKED LIMITS L=1", W=1.3", D=.062. NO ESTABLISH LIMITS IN SRM. R & R WEB IAW SRM 51-42-11. PAINTED FASTENERS IAW SRM 51-75-12.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND RT SIDE LOWER AFT FUSELAGE FR 69,S28-29R EXTERNAL SKIN SURFACE HAS PRE-EXISTING TOOL MARK (APPEARS TO BE FROM FASTENER REPLACEMENT). REMOVED TOOL MARKS IAW SRM 51-73-00. CHECKED DAMAGE L=.8", W=.7", D=.012". FOUND TO BE OUT OF LIMITS IAW SRM 53-41-11 DIAGRAM 102. CUT-OUT THE DAMAGE SKIN IAW SRM 53-41-11 PAR 5.M.E.L=.88" X .83". FABRICATED DOUBLER IAW SRM 53-41-11, FIG. 216 FROM 2024-T3. 071C BATCH 0002027003, FABRICATED (2EA) REPAIR FILLERS FROM 2024-T3 .063C BATCH 0002339436 IAW SRM 53-41-11, FIG 216. INSTALLED REPAIR DOUBLER AND (2EA) FILLERS IAW SRM 53-41-11, FIG 216. INSTALLED IDENTIFICATION TAG IAW PS 900-5-1, NR 04. PAINTED REPAIR AREA IAW SRM 51-75-12.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD UTILITY FLOOR PANEL 221EF CRACKED 4.0" X 1.0". AND FWD UTILITY PANEL 221EF. REPLACED IAW SRM 51-72-00.

Part: HINGE PIN — CORRODED (LT SPOILER) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LT WING SPOILER NR 5 CENTER HINGE INBD PIN CORROD PIN INSTALLED ON JIC 5770-1010S-LT.

Part: HINGE PIN — CORRODED (SPOILER) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LT WING SPOILER NR 4 CENTER HINGE INBD PIN CORRODED. RECEIVED NEW CTR PIN TO BE INSTALLED ON JIC 5770-1010S-LT.

Part: HINGE PIN — CORRODED (SPOILER) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND RT WING NR 5 SPOILER BOTH INBD AND OTBD CTR HINGE PIN HAS CORROSION AND THREAD DAMAGED. RECEIVED NEW CTR PINS INSTALLED ON JIC 5770-1010S-RT.

Part: THRESHOLD — CORRODED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO THRESHOLD PANEL 152KF CORRODED.3.5 X 3.5. REPLACED AFT CARGO THRESHOLD PANEL IAW SRM 51-72-00.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY FLOOR PANEL 262FF CORRODED 3.0" X 3.0". REPLACED FLOOR PANEL IAW SRM 51-72-00.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LOWER FUSELAGE HAS LIGHTNING STRIKE ON THIRD FASTENER ON STRINGER 42R FWD OF FR 31. REMOVED FASTENER & REAMED HOLE IAW SRM 53-21-11, FIG 213. COLD WORK FASTENER HOLE IAW SRM 51-48-00. INSTALLED FASTENER IAW SRM 51-42-11. PERFORMED SURFACE REPROTECTION IAW SRM 51-75-12.

Part: FLOOR PANEL — PUNCTURED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD UTILITY FLOOR PANEL 222CF PUNCTURED "2.5 X 3.0". FABRICATED FLOOR PANEL IAW DWG 3D25-37498.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND COCKPIT FLOOR SUPPORT BETWEEN FR 8-11 Y-765 WEB CRACKED. REMOVED WEB FROM FR8 TO FR11 Y-765 IAW SRM 51-42-11. RECEIVED NEW WEB PN D5311332220102 BATCH 2364974 AND INSTALLED NEW WEB FROM FR8 TO FR11 IAW SRM 51-42-11.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY FLOOR PANEL 262EF WITH MULTIPLE CORRODED INSERTS. FABRICATED FLOOR PANEL IAW DWG 3D25-37498.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY FLOOR PANEL 261EF WITH CORRODED INSERTS. FABRICATED FLOOR PANEL IAW DWG 3D25-37498.

Part: FLOOR PANEL — PUNCTURED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY FLOOR PANEL PUNCTURED 261DF 4.0" X 4.0". FABRICATED FLOOR PANEL IAW DWG.

Part: FLOOR PANEL — PUNCTURED · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT UTILITY FLOOR PANEL 262AB PUNCTURED 2.0" X 2.0". FABRICATED FLOOR PANEL IAW DWG.

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND MAIN CABIN FLOOR PANEL 231YF CRACKED 7.0" LONG. FABRICATED FLOOR PANEL IAW DWG 3D25-37498.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 152CF DAMAGED 4.0" X 5.0". FABRICATED SLOPE PANEL 152CF ON STAM TRAVELER T12/971268 IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND FWD CARGO SLOPE PANEL 131CF DAMAGED 4.5" X 4.5". FABRICATED SLOPE PANEL 131CF ON STAM TRAVELER T12/971010 IAW DWG 3D25-37705 A320).

Part: PANEL — DELAMINATED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 151RF DELAMINATED 3.5" X 4.0". FABRICATED SLOPE PANEL 151RF ON STAM TRAVELER NR T12/971275 IAW DWG 3D25-37705 (A320).

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUNTINE CHECK, FOUND AFT CARGO SLOPE PANEL 161CF DAMAGED 4.5" X 5.0". FABRICATED SLOPE PANEL 161CF ON STAM TRAVELER T12/971277 IAW DWG 3D25-37705.

Part: PANEL — DELAMINATED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 161BF DELAMINATED AT EDGE 4.0" X 4.0". FABRICATED SLOPE PANEL 161BF ON STAM TRAVELER T12/971278 IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 152FF DAMAGED 5.0" X 5.0". FABRICATED SLOPE PANEL 152FF ON STAM TRAVELER T12/971261 IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 152BF DAMAGED 6.5" X 6.5". FABRICATED SLOPE PANEL 152BF ON STAM TRAVELER T12/971269 IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 151QF DAMAGED 5.0" X 5.0". FABRICATED SLOPE PANEL 151QF ON STAM TRAVELER NR T12/971276 IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 151BF DAMAGED 4.0" X 4.0". FABRICATED SLOPE PANEL 151BF ON STAM TRAVELER T12/971271 IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 152EF DAMAGED 3.0" X 3.0". FABRICATED SLOPE PANEL 152EF ON STAM TRAVELER T12/971263 IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 151FF DAMAGED 6.0" X 6.0". FABRICATED SLOPE PANEL 151FF ON STAM TRAVELER NR T12/971272 IAW DWG NR 3D25-37705.

Part: PANEL — DAMAGED (CARGO BAY) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND AFT CARGO SLOPE PANEL 151EF DAMAGED AREA 4.0" X 4.0". FABRICATED SLOPE PANEL 151EF ON STAM TRAVELER NR T12/971273 IAW DWG NR 3D25-37705.

Part: SKIN — DENTED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LOWER FUSELAGE AT STR 31L BET FR 20 AND 21 DENTED .018" DEEP .437" WIDE OUT OF EDGE LIMITS IAW SRM 53-00-11, PG 101-LP 2472695. DENT FOUND OUT LIMITS IAW SRM 53-11-11. CUTOUT DAMAGE L=1.90 0"W=1.0"& FABRICATED DOUBLER AND REPAIR PARTS IAW SRM 53-11-11, FIG 213. INSTALLED DOUBLER AND REPAIR PARTS IAW SRM 53-11-11. 213. INSPECT AREA AT 60000FC IAW SRI 53-11-11, TABLE 204.

Part: FLOOR SUPPORT — CORRODED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING NON ROUTINE CHECK, FOUND FORWARD CABIN FLOORBEAM BETWEEN FR 18 TO FR 20 Y-254 UPPER FLANGE HAS CORROSION. BLENDED AREA ON FLOOR SUPPORT Y-254 IAW SRM 51-74-00, ORIG MATERIAL 155"L=.36"W=1"D=.030". NO ALLOWABLE DAMAGE WAS FOUND IN SRM. REPLACED FLOORBEAM, PN D5311282120020, BATCH 0002363289 IAW SRM 51-42-11 & TRM 53-21-01..

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO FLOOR PANEL 151GF DAMAGED 6.5" X 6.0". FABRICATED FLOOR PANEL IAW DWG 3D25-37705.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO FLOOR PANEL 151DF DAMAGED 7.0" X 7.0". FABRICATED FLOOR PANEL IAW DWG 3D25-37705.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO FLOOR PANEL 151PF DAMAGED ON EDGE 4.5" X 5.0". FABRICATED FLOOR PANEL IAW DWG 3D25-37705.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO FLOOR PANEL 151AF EDGE DAMAGE 4.0" X 4.0" NR. 150/52. FABRICATED FLOOR PANEL IAW DWG 3D25-37705.

Part: FITTING — CORRODED (PAX DOOR FRAME) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LT FWD PAX DOOR FRAME, LOWER AFT FITTING CORNER HAS CORROSION. NO ESTABLISHED LIMITS ON LOWER AFT FITTING CORNER OF L1 PAX DOOR FRAME. REPLACED AFT CORNER FITTING IAW SRM 51-42-11.

Part: SEAL DEPRESSOR — CORRODED (PAX DOOR) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LT FWD PAX DOOR FRAME, MID SEAL SHAPE HAS CORROSION. REPLACED MID SEAL SHAPE IAW A320 SRM 51-42-11. NO LIMITS IAW SRM 53-11-14 PG BLK 101 DAMAGE DIM. L=1.60" W=1.50" D=0.006".

Part: SKIN — DENTED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LT SIDE LOWER AFT FUSELAGE FR 58, S23LTO S24L EXTERNAL SKIN SURFACE HAS DENT. PERFORMED DETAILED INSP, FOUND NOT TO BE DENTED BUT INDENTATION FROM PREVIOUSLY REPLACED FASTENER. CUTOUT DAMAGED AREA L=1.8" W=.750" IAW SRM 53-00-11, FIG 205, PG 231/232. HFEC IAW NTM 51-10-08 PT 6. NO NOTED DEFECT. FAB'D & INSTALLED REPAIR DOUBLER & FILLER IAW SRM 53-00-11, FIG 205. THIS REPAIR REQUIRES ULTRASONIC/EDDY CURRENT INSP WITHIN 55000 FC AFTER. REPAIR EMBODIMENT IAW SRI 53-00-11, TABLE 242, PG. 382.

Part: PANEL — DELAMINATED (AFT CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT CARGO SLOPE PANEL 151MF DELAMINATED 5.0"X5.0". SLOPE PANEL FABRICATED IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO SLOPE PANEL 131FF DAMAGED 6.0"X5.0". FORWARD CARGO SLOPE PANEL FABRICATED NEW IAW DWG 3D25-37705.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND CABIN FLOOR PANEL 232WF CRACKED. FLOOR PANEL FABRICATED IAW SRM 53-02-00 FIG 209 DWG 3D25-37498 DAMAGE DIM. L=2.0"X2.0".

Part: FLOOR PANEL — PUNCTURED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND MAIN CABIN FLOOR PANEL 231FF PUNCTURED 1.5" X 1.5". FLOOR PANEL FABRICATED IAW SRM 53-02-00, FIG 209, DWG 3D25-37498.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND MAIN CABIN FLOOR PANEL 232FF CRACKED 4 INCHES LONG. FLOOR PANEL FABRICATED IAW SRM 53-02-00, FIG 209, DWG 3D25-37498.

Part: PANEL — DAMAGED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO SLOPE PANEL 131KF DAMAGED 3.0" X 3.0". SLOPE PANEL FABRICATED IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO SLOPE PANEL 132JF DAMAGED 4.5"X 3.5. SLOPE PANEL FABRICATED IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO SLOPE PANEL 131GF DAMAGED 4.0"X4.0". SLOPE PANEL FABRICATED NEW IAW DWG 3D25-37705.

Part: PANEL — DELAMINATED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO SLOPE PANEL 131BF DELAMINATED 5.0" X 5.0". SLOPE PANEL FABRICATED IAW DWG 3D25-37705.

Part: PANEL — DELAMINATED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO SLOPE PANEL 132FF DELAMINATED 3.0" X 4.0". SLOPE PANEL FABRICATED IAW DWG 3D25-37705.

Part: FLOOR PANEL — DAMAGED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO FLOOR PANEL 131HF DAMAGED 2.0"X 2.5". FLOOR PANEL FABRICATED IAW DWG 3D25-37705.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY FLOOR PANEL 261FF CORRODED 4.0"X4.0". AFT UTILITY FLOOR PANEL 261FF REPLACED IAW SRM 51-72-00.

Part: PANEL — DELAMINATED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO SLOPE PANEL 132GF DELAMINATED 4.0" X 4.0". SLOPE PANEL FABRICATED NEW IAW DWG 3D25-37705.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD UTILITY FLOOR PANEL 222EF HAS EDGE DAMAGE 4.0" X 4.0". FLOOR PANEL FABRICATED IAW SRM 53-02-00, FIG 209, DWG 3D25-37498.

Part: FLOOR PANEL — DELAMINATED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO FLOOR PANEL 131AF DELAMINATED 3.0"X3.0". FLOOR PANEL FABRICATED IAW DWG 3D25-37705.

Part: PANEL — DAMAGED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO SLOPE PANEL 132KF DAMAGED 4.5" X 4.5". SLOPE PANEL FABRICATED IAW DWG 3D25-37705.

Part: PANEL — DELAMINATED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO SLOPE PANEL 131JF DELAMINATED 6.0" X 6.0". SLOPE PANEL FABRICATED NEW IAW DWG 3D25-37705.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD UTILITY FLOOR PANEL 222FF CORRODED ON UPPER SURFACE 2.5"X 3.5". FLOOR PANEL REPLACED IAW SRM 51-72-00.

Part: FLOOR PANEL — DAMAGED (FWD CARGO) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FWD CARGO FLOOR PANEL 131EF DAMAGED 5.0"X5.0". FLOOR PANEL FABRICATED IAW DWG 3D25-37705.

Part: FLOOR SUPPORT — CRACKED (COCKPIT) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND COCKPIT FLOOR SUPPORT BTW FR 8-11 Y765 WEB CRACKED. REMOVED CRACKED WEB IAW SRM 51-42-11 CRACK MAX, LIMIT REPAIR=.31". LENGTH OF CRACK=.65". OUT OF LIMITS IAW SRM 53-11-14, FIG 205 SHT 1. REPLACED CRACKED WEB IAW SRM 51-42-11 AND 51-44-11.

Part: WEB — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FORWARD CABIN RT SIDE BTW FR 20 TO FR 21 STGR 23 UPPER SURFACE WEB HAS CORROSION. SSI 531184. REMOVED CORROSION IAW SRM 51-74-00. CHECKED LIMITS L=3", W=2",D=.010", ORIGINAL MATERIAL .075". FOUND TO BE OUT OF LIMITS IAW SRM 53-11-14, FIG 7 DEPTH GAGE USED TR83340. REPLACED WEB ON RT SIDE OF CABIN FROM FR20-FR24 IAW SRM 51-42-11.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LOWER FUSELAGE DOUBLER REPAIR AT FR 23, LT SIDE, LWR AFT CORNER IS BENT AND HAS DENT AFT OF DOUBLER BETWEEN STRINGER 24 AND 25L . CUT-OUT DAMAGE AREA IAW SRM 53-11-11, FIG 214. L=9.250" W=4.250". HFEC IAW NTM 51-10-08, PB 6. NO DEFECTS NOTED. FABRICATED DOUBLER AND FILLER FROM MATERIAL 2024-3.080C BATCH NR 1905598 IAW SRM 53-11-11, FIG 214 UNDER TRAVELER NR T12/972401. TOTAL WEIGHT OF REPAIR PARTS 1.62LBS. INSTALLED DOUBLER AND FILLER IAW SRM 51-42-11 AND SRM 53-11-11 FIG 214.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY AREA FLOOR SUPPORT BTW FR 64 -65 Y1292 UPPER FLANGE HAS CORROSION. REMOVED CORROSION IAW SRM 51-74-00. ORIG MAT. .080" DAMAGE DIM. L=1.300" W=.810" D=.035". FOUND TO BE OUT OF LIMITS IAW TRM 53-41-15. REPLACED Y1292 FLOOR SUPPORT IAW SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FORWARD CABIN FLOOR SUPPORT BETWEEN FR 18 TO FR 21 Y254 UPPER FLANGE HAS CORROSION & SCRIBE LINE AS MARKED. REMOVED CORROSION IAW SRM 51-74-00, DIM L=2.7" W= 1.5" D= .045" ORIG MAT .079" FOUND TO BE OUT OF LIMITS IAW SRM 53-11-14, FIG 105. REPLACED Y254 FLOOR SUPPORT FR 12-24, PN D5311281820401 IAW SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

AFT UTILITY AREA FLOOR SUPPORT BTW FR 65 TO FR 66 Y465 UPPER FLANGE HAS CORROSION AND 2 EA MISDRILLED HOLES. BLENDED AREA IAW SRM 51-74-00. ORIG MAT .079" L=1" W=1" D=.074" FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14. REPLACED FLOOR SUPPORT IAW SRM 51-42-11.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FORWARD CABIN FLOOR SUPPORT BETWEEN FR 24-25 Y254 UPPER FLANGE CRACKED. CUT OUT DAMAGED L=3.5"W=.900" IAW SRM 53-00-14 FIG 204. HFE IAW NTM 51-10-08 NO CRACK INDICATIONS NOTED. FABRICATED REPAIR ANGLE. FABRICATED FILLER IAW SRM 53-00-14, FIG 201 WEIGHED REPAIR ANGLE .32LBS TR 09638 INSTALLED REPAIR ANGLE AND FILLER IAW SRM 51-42-11.

Part: FITTING — CORRODED (DOOR SILL) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND LT AFT PASSENGER DOOR ENTRANCE CENTER SEAL SHAPED FITTING ATTACHED TO DOOR SILL HAS CORROSION. REMOVED L2 DOOR SHAPED SILL IAW SRM 51-42-11. INSTALLED NEW SHAPE SILL IAW SRM 51-42-11. NO SPECIFIC LIMITS IAW SRM 53-00-29.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY AREA FLOOR SUPPORT BETWEEN FR 68 TO FR 69 Y1292 UPPER FLANGE AND HARD POINT HOLES HAS CORROSION. BLENDED AREA IAW SRM 51-74-00 L=.385"W=0.275"D=0.064" ORIGI NAL MAT 0.157"FOUND TO BE OUT OF LIMITS IAW TRM 53-41-15. REPLACED FLOOR SUPPORT IAW SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FORWARD CABIN FLOOR SUPPORT BETWEEN FR 20 TO FR 23 Y-189 UPPER FLANGE HAS CORROSION. BLENDED AREA FOUND TO BE OUT OF LIMITS ORIG MAT .079 DAMAGE DIM L=2.0" W=1.5" D=.013" TR83340. NO ESTABLISHED LIMITS IAW SRM 53-11-15. INSTALLED NEW FLOOR SUPPORT Y-189 IAW SRM 51-42-11.

Part: WEB — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND FORWARD CABIN LT SIDE AT FR 20 STRINGER 23 UPPER SURFACE WEB HAS CORROSION. REMOVED CORROSION IAW SRM 51-74-00 L=3.5 W=2.0 D=.063 ORIG .071 NO ESTABLISHED LIMITS AVAILABLE IAW SRM 53-11-14. INSTALLED NEW WEB IAW SRM 51-42-11.

Part: TRACK — CRACKED (COCKPIT WINDOW) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND COCKPIT CAPTAIN UPPER CENTER SLIDING WINDOW RAIL CRACKED. CUT OUT DAMAGE AREA OF THE RAIL AND DEBURR THE EDGES IAW SRM 53-11-12, FIG 203, SHEET 1 OPTION 1 REPAIR. HFEC IAW NTM 51-10-08 P-6 NO DEFECT NOTED. TREATED & PRIMED REWORK AREA IAW SRM 51-21-11. TOP COAT REWORK AREA IAW SRM 51-75-12.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND RT SIDE LOWER AFT FUSELAGE FR 63 S28R - S29R EXTERNAL SKIN SURFACE HAS A BLENDED AREA IAW SRM 51-73-00, CHECKED LIMIT L=1.65" W=0.700" D=0.019", FOUND OUT OF LIMITS IAW SRM 53-41-11, DIAGRAM 102. CUTOUT DAMAGED SKIN (L=1.65" W=.700"). HFEC IAW NTM 51-10-08, NO CRACK INDICATIONS NOTED. FABRICATED DOUBLER AND TWO FILLERS. INSTALLED REPAIR DOUBLER & FILLERS IAW SRM 53-00-11 FIG 205.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY AREA FLOOR SUPPORT BETWEEN FR 66 TO FR 70 Y765, UPPER FLANGE AND HARD POINT HOLES HAS CORROSION. BLENDED FLOOR SUPPORT ORIG. MAT. .130" DAMAGE DIM. L=2.0" W=1.5" D=.80". FOUND TO BE OUT OF LIMITS IAW TRM 53-41-15. REPLACED FLOOR SUPPORT IAW SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY AREA FLOOR SUPPORT BETWEEN FR 68 TO FR 70 Y254, HARD POINT HOLES HAS CORROSION. REMOVED CORROSION FROM FLOOR SUPPORT AND FOUND DAMAGE TO BE OUT OF LIMITS IAW SRM 53-00-14. REPLACED FLOOR SUPPORT IAW SRM 51-42-11,

Part: SILL — CORRODED (PAX DOOR) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND RT AFT PASSENGER DOOR ENTRANCE CENTER SEAL SHAPE FITTING ATTACHED TO DOOR SILL CORRODED. REMOVED R2 DOOR CENTER FITTING IAW SRM 51-42-11. INSTALLED R2 NEW DOOR CENTER FITTING IAW SRM 51-42-11. NO SPECIFIED LIMITS IAW SRM 53-00-29.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY AREA FLOOR SUPPORT BETWEEN FR 65 TO FR 66 Y765, UPPER FLANGE HAS CORROSION. REMOVED CORROSION ORIG. MAT .130", DAMAGE DIA L=1.7" W=.900" D=.040" FOUND TO BE OUT OF LIMITS IAW TRM 53-41-15. REPLACED FLOOR SUPPORT IAW SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY AREA FLOOR SUPPORT BETWEEN FR 66 TO FR 70 Y 765. UPPER FLANGE AND HARD POINT HOLES HAS CORROSION. BLENDED FLOOR SUPPORT ORIG MAT .130" DAMAGE DIM. L=2.0" W=1.5" D=.80", FOUND TO BE OUT OF LIMITS IAW TRM 53-41-15. REPLACED FLOOR SUPPORT IAW SRM 51-42-11.

Part: FITTING — CORRODED (R2 DOOR) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND RT AFT PASSENGER DOOR ENTRANCE CTR SEAL SHAPE FITTING ATTACHED TO DOOR SILL CORRODED. REMOVED R2 DOOR CENTER FITTING IAW SRM 51-42-11. RECEIVED CENTER FITTING . INSTALLED R2 NEW DOOR CENTER FITTING IAW SRM 51-42-11. NO SPECIFIED LIMITS IAW SRM 53-00-29.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND AFT UTILITY AREA FLOOR SUPPORT BETWEEN FR 68 TO FR 70 Y254 HARD POINT HOLES HAS CORROSION. REMOVED CORROSION FROM FLOOR SUPPORT AND FOUND DAMAGE TO BE OUT OF LIMITS IAW SRM 53-00-14. REPLACED FLOOR SUPPORT IAW SRM 51-42-11.

Part: FLOOR PANEL — BROKEN (CABIN) · airframe 68,007 hrs · 30,286 cycles

DURING INSPECTION, FOUND CABIN FLOOR PANEL 251FF BETWEEN FR 51 AND 53 CENTER ISLE IS BROKEN. FABRICATED NEW FLOOR PANEL IAW SRM 53-02-00, FIG 209.

Part: BATTERY PACK — FAULTED (EMERGENCY LIGHT) · airframe 67,990 hrs · 30,274 cycles

DURING NON ROUTINE CHECK, FOUND BATTERY PACK EMERGENCY LIGHT TEST FAULTING. MX REPLACED FWD LT EMERGENCY BATTERY AND FUNCTIONAL CHECKED NORMAL.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 5,654 hrs · 2,523 cycles

DURING NON ROUTINE CHECK, FOUND THE EMERGENCY ESCAPE PATH LIGHT AT AT SEAT 19B INOPERATIVE. MAINTENANCE REPAIRED LIGHT ASSEMBLY AND FUNCTIONAL CHECK WAS NORMAL. AIRCRAFT RETURNED TO SERVICE.

Part: WIRE HARNESS — DEFECTIVE (CABIN) · airframe 5,182 hrs · 2,303 cycles

DURING NON ROUTINE CHECK, FOUND EMERGENCY FLOOR PATH LIGHT AT ROW 9 INOPERATIVE. MAINTENANCE REPLACED EMERGENCY ESCAPE PATH HARNESS AND FUNCTIONAL CHECK WAS NORMAL. AIRCRAFT RETURNED TO SERVICE.

Part: CONNECTOR — DAMAGED (CABIN) · airframe 62,624 hrs · 27,722 cycles

DURING EMERGENCY LIGHT TEST FOUND PATH LIGHT AT ROW 14 INOPERATIVE AND WIRES PULLED FROM CONNECTOR. NEW CONNECTOR INSTALLED AND TESTS OK.(2011-00082)

Part: PROFILE — CRACKED (EMERGENCY EXIT) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND CRACK IN FORWARD RIGHT OVERWING EMERGENCY EXIT DOOR LEFT LOAD TRANSMITTING PROFILE. REPAIRED PER SRM 51-42-11.

Part: PROFILE — CRACKED (EMERGENCY EXIT) · airframe 61,982 hrs · 27,447 cycles

DURING L CHECK FOUND CRACK IN FORWARD LEFT OVERWING EMERGENCY EXIT DOOR RIGHT LOAD TRANSMITTING PROFILE. REPAIRED PER SRM 51-42-11 & SRM 51-44-11.

Part: PROFILE — CRACKED (EMERGENCY EXIT) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND CRACK IN FORWARD LEFT OVERWING EMERGENCY EXIT DOOR LEFT LOAD TRANSMITTING PROFILE. REPAIRED PER SRM 51-42-11.

Part: SLAT — GOUGED (WING) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND GOUGE IN NR 2 SLAT INBOARD TRAILING EDGE IN 4 LOCATIONS. REPAIRED PER SRM 51-21-11, SRM 57-43-21 FIGURE 204 SHEET 2.

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND DAMAGE TO CARGO FLOOR PANEL 151LF. REPAIRED PER SRM 51-42-11, SRM 53-02-00 FIGURE 209 & AMM 53-42-14-420-050.

Part: PROFILE — CRACKED (EMERGENCY EXIT) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND CRACK IN FORWARD RIGHT OVERWING EMERGENCY EXIT DOOR LOAD TRANSMITTING PROFILE. REPAIRED PER SRM 51-42-11, SRM 51-75-12.

Part: FLOOR PANEL — DELAMINATED (CARGO BAY) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND DELAMINATION IN 3 AREAS ON CARGO FLOOR PANEL 151DF. REPAIRED PER SRM 51-42-11, SRM 53-02-00 FIGURE 209 & AMM 53-42-14-420-050.

Part: FLOOR PANEL — DELAMINATED (CARGO BAY) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND DELAMINATION ON CARGO FLOOR PANEL 151GF. REPAIRED PER SRM 51-42-11, SRM 53-02-00 FIGURE 209 & AMM 53-42-14-420-050.

Part: PROFILE — CRACKED (EMERGENCY EXIT) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND CRACK IN AFT LEFT OVERWING EMERGENCY EXIT DOOR RIGHT LOAD TRANSMITTING PROFILE. REPAIRED PER SRM 51-44-11, SRM 51-42-1 & SRM 51-75-12.

Part: PROFILE — CRACKED (FUSELAGE) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND CRACK IN AFT RT OVERWING EMERGENCY EXIT DOOR LT LOAD TRANSMITTING PROFILE. REPAIRED IAW SRM 51-44-11, SRM 51-42-1 & SRM 51-75-12.

Part: PROFILE — CRACKED (FUSELAGE) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND CRACK IN AFT RT OVERWING EMERGENCY EXIT DOOR RT LOAD TRANSMITTING PROFILE. REPAIRED IAW SRM 51-44-11, SRM 51-42-1 & SRM 51-75-12.

Part: PROFILE — CRACKED (EMERGENCY EXIT) · airframe 61,982 hrs · 27,447 cycles

DURING L-CHECK FOUND CRACK IN AFT LEFT OVERWING EMERGENCY EXIT DOOR LEFT LOAD TRANSMITTING PROFILE. REPAIRED PER SRM 51-44-11, SRM 51-42-1 & SRM 51-75-12.

Part: FLOORBOARD — DAMAGED (CARGO BAY) · airframe 61,553 hrs · 27,268 cycles

FOUND FWD CARGO FLOORBOARDS DAMAGED BEYOND SRM LIMITS. R & R CARGO FLOORBOARDS 131AE AND 131EG IAW AMM 53-22-14.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 61,324 hrs · 27,166 cycles

DURING FWD A&G ANTENNA INSTALLATION SKIN BETWEEN FR25 & FR26 AND BETWEEN STRINGER 43L & STRINGER 42L HAD (2) .7500 HOLES AND (6) NR10 HOLES DRILLED IN WRONG LOCATION DUE TO INCORRECT MANUFACTURED DOUBLER. REPAIRED IAW SRM 53-21-11, FIG 214, SHEET 1.

Part: SEAL — LEAKING (CARGO DOOR) · airframe 57,674 hrs · 25,633 cycles

PASSING 10,000 ON CLIMB-OUT NOTED EXCESSIVE CABIN RATE OF CLIMB OF 1600-1800 FPM. WATCHED CABIN ALTITUDE CLIMB TO 9000 FT PASSING 18,000 FT MSL. ECAM MESSAGE CAB PR EXCESS CAB ALT AT 9500 FT CABIN ALTITUDE. IMMEDIATELY DESCENDED AIRCRAFT TO CONTROL CABIN ALTITUDE. MAX CABIN ALTITUDE 9500 FT. REINSTALLED FWD CARGO DOOR SEAL, CHECKS OK.

Part: SLIDE — FAULTY (L2 DOOR) · airframe 54,276 hrs · 24,022 cycles

WHILE PERFORMING EMERGENCY LIGHT SYSTEM CHECK PER LINE CHECK "EXT LOADS AFT L" MESSAGE, REF L/P 4273412. REMOVED AND REPLACED 2L EVACUATION SLIDE. CHECKS GOOD.

Part: FRAME — CORRODED · corrosion level 2 · airframe 35,322 hrs · 15,361 cycles

In M check, found corrosion in nutplate hole on FR 68 R/H, 1 inch from inboard flange and 1 inch above door threshold. Repaired per EA32-184166.

Part: ROLLER — OUT OF ADJ (PAX DOOR) · airframe 33,589 hrs · 14,616 cycles

UPON ARRIVAL AT THE GATE, THE GATE AGENT HAD DIFFICULTY PULLING DOOR 1L OPEN WITHOUT ASSISTANCE BY A FLIGHT ATTENDANT FROM THE AIRCRAFT INTERIOR. MAINTENANCE TROUBLESHOOTING REVEALED THE FORWARD UPPER DOOR ROLLER WAS NOT CLEARING THE CAM ON THE DOOR FRAME OPENING. MAINTENANCE ADJUSTED THE CAM AND THE DOOR OPENED AND CLOSED NORMALLY.

Part: ACTUATOR — LOCKED (LT LE FLAP)

DURING APPROACH, CREW RECEIVED MESSAGES F/CTL SLATS LOCK AND F/CTL SLATS FAULT. AFTER DISCUSSION WITH MAINTENANCE CONTROL, CREW DECLARED AN EMERGENCY. FOLLOWED COCKPIT OPERATING MANUAL AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE LEFT WING NR 3 SLAT ACTUATOR, OPERATIONAL CHECK OK.

Part: STRUT — LOW PRESSURE (NLG)

DURING CLIMBOUT AFTER LANDING GEAR RETRACTION, THE NOSE LANDING GEAR DOORS DID NOT INDICATE CLOSED. FOLLOWED COCKPIT OPERATING MANUAL PROCEDURES AND RETURNED TO MSP AND LANDED WITHOUT INCIDENT. MAINTENANCE SERVICED THE NOSE LANDING GEAR STRUT AND THE GREEN HYDRAULIC SYSTEM. LANDING GEAR EXTENSION AND RETRACTION REVEALED NO DISCREPANCIES.

Part: FEEL SOLENOID — FAILED (RUDDER)

DURING FINAL APPROACH IN LIGHT ICING CONDITIONS, THE RUDDER PEDALS WERE RESTRICTED IN THE NEUTRAL POSITION. WING AND ENGINE ANTI-ICE WERE OPERATING AT THE TIME. AUTO PILOT WAS NOT ENGAGED. AIRCRAFT LANDED WITHOUT INCIDENT. RUDDER MOVEMENT RETURNED TO NORMAL DURING TAXI. MAINTENANCE REPLACED THE RUDDER ARTIFICIAL FEEL SOLENOID, OPS CHECKED OK.

Part: NUT — IMPROPER CONFIG (LT ENG FWD MOUNT)

DURING LINE CHECK DIRECTED INSPECTION, FOUND ONE IMPROPER CONFIGURATION NUT ON THE LEFT ENGINE FORWARD ENGINE MOUNT, FORWARD OUTBOARD ATTACH BOLT (P/N LH7461T144D). REPLACED NUT WITH (P/N VN401B144) PER MM 71-00-00 PG 436.

Part: LONGERON — CORRODED (FS 14300-14834)

DURING IL CHECK, FOUND CORROSION ON STR 44 BETWEEN FRAMES 33 TO 34. REPAIRED STRINGER (P/N D532-31521-200), PER EA 32-104280.

Part: LONGERON — CORRODED (FS 13767-15367)

DURING IL CHECK, FOUND CORROSION IN STR 43R BETWEEN FRAMES 32 TO 35. REPAIRED STRINGER (P/N D532-31511-201), PER EA 32-104278, -104279.

Part: FITTING — CORRODED (4L DOOR FRAME)

DURING IL CHECK, FOUND CORROSION ON THE 4L DOOR FRAME CORNER FITTING. REPLACED FITTING.