N965WN

Part: HOOK — LOOSE (GIRT BAR) · airframe 44,960 hrs · 27,702 cycles

FWD ENTRY DOOR GIRT BAR HOOK LOOSE. REPLACED FASTENER IAW AMM 51-40-02.

Part: COVER — DETACHED (ZONE 200) · airframe 44,902 hrs · 27,665 cycles

EXIT LIGHT COVER ON FO SIDE OVER WING EXIT FELL OFF. SECURED THE COVER IAW AMM SIP.

Part: COVER — DETACHED (ZONE 200) · airframe 44,839 hrs · 27,623 cycles

RIGHT OVERWING EXIT LIGHTED EMERGENCY EXIT COVER FELL OFF. RESECURED COVER IAW AMM 33-51-01.

Part: FITTING — CRACKED (ZONE 400) · airframe 44,832 hrs · 27,619 cycles

NUMBER 1 ENGINE OTBD FAN COWL AFT HOLD OPEN ROD STOW PIN FIITING CRACKED. REMOVED AND REPLACED NR 1 OTBD FAN COWL AFT HOLD OPEN ROD STOW PIN FITTING PER AMM 51-40-02-0G-0. AFT HOLD OPEN ROD STOW PIN FITTING REPLACED WHEN THE FAN COWL WAS REPLACED ON SWA NON-ROUTINE TTG8Q014EP7W.

Part: PLATE — CRACKED (ZONE 500) · airframe 44,832 hrs · 27,619 cycles

LEFT WING T/E INBD WAFFLE PLATE FOR PANEL 551EB CRACKED. REMOVED & REPLACED LT WING T/E INBD WAFFLE PLATE FOR PANEL 551EB IAW SRM 51-40-05-0G-0 & DWG115A2001 & DWG 115A2713.

Part: PANEL — CRACKED (ZONE 300) · airframe 44,832 hrs · 27,619 cycles

PANEL 324BL CRACKED ON EDGE NEAR FASTENER HOLE. REPAIRED VERTICAL STAB TRAILING EDGE PANEL 324BL IAW SRM 55-30-01-2R-9, SRM 51-70-04-2R-6, AND SRM 51-70-04-2R-0 REPAIR GENERAL.

Part: BULKHEAD — CRACKED (ZONE 100) · airframe 44,832 hrs · 27,619 cycles

LEFT SIDE VERTICAL 663 BULKHEAD LOWER VAPOR BARRIER FOUND CRACKED WITH TEMP REPAIR; CUSTOMER REQUEST TO ACCOMPLISH PERMEANT REPAIR. REPAIRED L/H VERTICAL 663 BULKHEAD LOWER VAPOR BARRIER IAW SRM 51-70-04-2R-0 AND SRM 51-70-04-2R-10.

Part: SEAT BACK — OUT OF ADJUST (ZONE 200) · airframe 44,832 hrs · 27,619 cycles

EMERGENCY EXIT ROW SEAT RECLINES AT 11D. ADJUSTED HYDRAULIC LOCK TO PREVENT RECLINE AT SEAT 11D IAW CMM 25-21-45, REPAIR STEPS 3.G.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 44,832 hrs · 27,619 cycles

MAIN CABIN L/H SEAT TRACK LBL45 AT STA 685+12' TO 727+13' LOWER SIDE OF CROWN HAS EVIDENCE OF CORROSION. REPAIRED IAW SRM 53-00-52-1A-1-A00026.

Part: FITTING — CRACKED (ZONE 500) · airframe 44,832 hrs · 27,619 cycles

A71-40 LEFT WING TRAILING EDGE CAVITY. FIXED TRAILING EDGE SUPPORT BRACKET 10' I/B OF DEFLECTION CONTROL RIB; HAS A CRACK AT BULB SEAL ATTACH BRACKET. REMOVED LT WING T/E SUPPORT BRACKET IAW SRM 51-40-02-0G-0. DRILLED FASTENERS HOLES IAW SRM 51-40-02-0G-0 AND BOEING DWG 115A2930. APPLIED TOPCOAT IAW AMM 51-21-73-370-801.INSTALLED BRACKET ASSY IAW SRM 51-40-02-0G-0 AND DWG 115A2930.

Part: FLOOR PANEL — DEFORMED (ZN 100 FUS LOWER) · airframe 44,832 hrs · 27,619 cycles

FWD CARGO FLOOR PANEL 120BF IS WAVY BETWEEN FLOORBEAMS. COMPLETED FABRICATION OF A NEW FLOOR PANEL 120BF IAW AMM 25-52-01-201-801.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 44,832 hrs · 27,619 cycles

MAIN CABIN LT SEAT TRACK LBL 45 AT BS 520 UPPER SIDE OF CROWN HAS EVIDENCE OF WEAR. REMOVED DAMAGE; MATERIAL LOSS OF 0.026' IS OUT OF LIMITS IAW SRM 53-00-52-1A-1. REMOVED DAMAGED SECTION OF SEAT TRACK BETWEEN STA 500C + 10' AND BS 520 LBL 45. LOCATED AND DRILLED UP NEW SECTION OF SEAT TRACK AND INSTALLED IAW SRM 51-40-02 AND SRM 53-00-52-2R-4.

Part: LAMP — DIM (ZONE 200) · airframe 44,345 hrs · 27,330 cycles

L/H OVERWING EMERGENCY EXIT DOOR LIGHT IS DIM. RELAMPED PER AMM 33-51-01. INSPECTED PER [AMM 33-51-01-201-NG.

Part: SHIELD — CORRODED (ZONE 100) · airframe 43,742 hrs · 26,971 cycles

POSSIBLE CORROSION IN AFT CARGO PIT ON LOWER SCREWS HOLES FOR PANEL 142FW <[01]. REMOVED AND REPLACED AFT CARGO PIT PART CALLED A SHIELD UNDER PANEL 142FW WHICH HAD MINOR CORROSION. REPLACING THE PART REMOVED ALL AND ANY CORROSION. REF SRM 51-40-02.

Part: VAPOR BARRIER — CRACKED (ZONE 100) · airframe 43,088 hrs · 26,556 cycles

CENTER WING REAR SPAR VAPOR WEB IS CRACKED ON THE LEFT SIDE OF THE KEEL; JUST FORWARD OF THE HYDRAULIC FLOW REGULATOR VALVE. CENTER WING REAR SPAR VAPOR WEB IS CRACKED ON THE LEFT SIDE OF THE KEEL JUST FORWARD OF THE HYDRAULIC FLOW REGULATOR VALVE.<[01] REVIEWED ALL DOCUMENTATION AND DAMAGE TO ENSURE ACCURACY; DAMAGE IDENTIFICATION; AND DIMENSIONS ARE CORRECT AND PRESENT; REFERENCE DOCUMENTATION AND TLD REQUIREMENTS ARE CORRECT; AND ANY NDT REQUIREMENTS HAVE BEEN ACCOMPLISHED AS PER MPM 52.7.1 AND MPM 52.7.1.1<BR><BR>CHOSE SRM SELECT REFERENCE 57-10-10-1A-2 FOR 1200 FLIGHT CYCLE REINSPECT;[02] PERFORMED INTERIM REPAIR IAW SRM 57-10-10-1A-2 AND EA M-21-157-00675. REQUIRES REINSPECT OF AREA EVERY 1200 FLIGHT CYCLES OR MORE FREQUENTLY.

Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 43,088 hrs · 26,556 cycles

OVERHEAD BIN EMERGENCY LIGHTS AT SEAT 3DEF AND 6DEF INOP.<[01] REMOVED AND REPLACED M1674 EMERGENCY LIGHT CRADLE AND BATTERY PACK IN FWD GALLEY CEILING PANEL UNDER LIGHT. ASSY OPS CHECKED GOOD REF B737 AMM 33-51-06

Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 43,088 hrs · 26,556 cycles

OVERHEAD BIN EMERGENCY LIGHTS AT SEAT 3DEF AND 6DEF INOP.<[01] REMOVED AND REPLACED M1674 EMERGENCY LIGHT CRADLE AND BATTERY PACK IN FWD GALLEY CEILING PANEL UNDER LIGHT. ASSY OPS CHECKED GOOD REF B737 AMM 33-51-06

Part: SLIDE — DISLODGED (L1 DOOR) · airframe 40,658 hrs · 25,034 cycles

L1 DOOR SLIDE IS NO LONGER IN PLASTIC COVER.<[01] REINSTALLED FWD ENTRY DOOR ESCAPE SLIDE PER MT 725-61-06 AND AMM 25-66-01. NO FURTHER DEFECTS NOTED. A/C OK FOR SERVICE.;[02] C/W

Part: SLIDE — DISLODGED (R1 DOOR) · airframe 40,506 hrs · 24,954 cycles

RAMP REPORTS R1 DOOR SLIDE FELL OUT OF HOLDER. REINSTALLED FWD ENTRY DOOR SLIDE PER AMM 25-66-01 AND MT 725-66-06.

Part: SLIDE — DISLODGED (ZN 800 DOOR) · airframe 40,490 hrs · 24,942 cycles

FWD ENTRY DOOR SLIDE FELL OUT OF CONTAINER<[01] REINSTALLED FWD ENTRY SLIDE PER MT 725-61-06 AND REF AMM 25-61-06

Part: LIGHT — INOPERATIVE (ZN 200 FUS TOP) · airframe 39,414 hrs · 24,270 cycles

AFT GALLEY CENTER AISLE ENTRANCE L/H EMERGENCY EGRESS STRIP DELAMINATED<[01] R&R CABIN PHOTOLUMINESCENT STRIP PER AMM 33-51-15

Part: LIGHT — INOPERATIVE (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

EMERGENCY EXIT SLIDE LIGHT AT THE FORWARD ENTRY DOOR DOES NOT ILLUMINATE.<[01] REPLACED EMERGENCY EXIT SLIDE LIGHT AT FWD ENTRY AND PERFORMED GOOD FUNCTIONAL TEST PER AMM 33-51-04-960-801.;[02] CERTIFY CORRECTIVE ACTION 1;[03] VERIFIED CORRECTIVE ACTION #1.

Part: SIGN — INOPERATIVE (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

RIGHT OVERWING HATCH AFT INDICATOR SIGN HAS INOPERATIVE LAMPS.<[01] REPLACED AND PERFORMED GOOD FUNCTIONAL TEST ON THE RIGHT OVERWING HATCH AFT INDICATOR SIGN PER AMM 33-51-01-960-801.;[02] CERTIFY CORRECTIVE ACTION 1;[03] RELAMP THREE BULBS ON THE RIGHT OVERWING HATCH AFT EMERGENCY INDICATOR SIGN PER AMM 33-51-01-960-801 AND PERFORMED GOOD FUNCTIONAL TEST ON THE RIGHT OVERWING HATCH AFT EMERGENCY INDICATOR SIGN PER AMM 33-51-01-960-801.;[04] CERTIFY CORRECTION FOR ACTION 3.;[05] VERIFIED CORRECTIVE ACTION STEP 3. TASK CARD COMPLETE.

Part: SUPPORT CHANNEL — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

AFT CARGO BAY FWD BULKHEAD R/H LOWER SUPPORT CHANNEL CRACKED.<[01] RECEIVED NEW SUPPORT CHANNEL<BR>ITEM# : 144A9401U20<BR>PO# : 869550/1;[02] REMOVED AND REPLACED AFT CARGO BAY FWD BULKHEAD R/H LOWER SUPPORT CHANNEL IAW SRM 51-40-02-0G-0 AND DWG 144A2600 ID:0959 REV:-;[03] VERIFIED CORRECTIVE ACTION #2

Part: ATTACH ANGLE — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

O2 BOTTLE FWD SUPPORT BRACKET; LOWER ATTACH ANGLE IS CRACKED AT O/B FASTENER; BS 360+2; LBL 18; WL 164<[01] ENTERED MEASUREMENTS;[02] REMOVED DAMAGED CREW OXYGEN SUPPORT RING IAW SOPM 20-50-01.<BR>RECEIVED NEW SUPPORT RING FROM STORES. REF: PO 929464.<BR>INSTALLED NEW SUPPORT RING IAW SOPM 20-50-01;[03] VERIFIED CORRECTIVE ACTION 2 AND MEASUREMENT TABLE;[04] COMPLETED STEP 1

Part: PANEL — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

WING BOX CENTER SECTION BREAK PANEL CRACKED AT BS 540; RBL 1; WL 207<[01] UPDATED PARTS TABLE;[02] REMOVED BREAK PANEL AT BS 540; RBL 1 WL 208 IAW SRM 51-40-02-0G-0. LOCATED AND DRILLED NEW BREAK PANEL IAW SRM 51-40-05-0G-0.;[03] OK TO INSTALL.;[04] LOCATED AND DRILLED IAW DWG 143A5240 SH3;[05] CERTIFIED ACTIONS 2;4;[06] VERIFIED CORRECTION ACTION ITEM 2;3;4;5; OK TO INSTALL GIVEN.;[07] INSTALLED PANEL BREAK AT BS 540 RBL1 WL 207 IAW SRM 51-40-02-0G-0; DWG 143A5240 SH3;[08] UPDATED PARTS. FAULT COMPLETE;[09] VERIFIED CORRECTIVE ACTION ITEM 7-8; AND MEASUREMENT FIELDS; CARD COMPLETE.

Part: FRAME — CRACKED (ZN 800 DOOR) · airframe 38,362 hrs · 23,630 cycles

STA 312 FRAME INNER RADIUS IS CRACKED JUST ABOVE L1 DOOR CUT-OUT.<[01] UPDATED MEASURMENTS;[02] CARD WILL BE WORK ON CARD TTG8Q00M68NT.;[03] VERIFIED CORRECTIVE ACTION 2 AND MEASUREMENT TABLE

Part: PANEL — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

AREA ABOVE WING BOX CENTER SECTION BREAK PANEL CRACKED AT BS 540; LBL 1; WL 207<[01] UPDATED REFERENCE TABLE;[02] REMOVED BREAK PANEL AT BS 540; LBL 1 IAW SRM 51-40-02-0G-0. LOCATED AND DRILLED NEW BREAK PANEL IAW SRM 51-40-05-0G-0.;[03] OK TO INSTALL;[04] LOCATED AND DRILLED IAW DWG 143A5240 SH3.;[05] CERTIFY ACTIONS 2;4;[06] VERIFIED CORRECTION ACTION ITEM 2;3;4;5; OK TO INSTALL GIVEN.;[07] INSTALLED PANEL BREAK AT BS 540 LBL1 WL 207 IAW SRM 51-40-02-0G-0; DWG 143A5240 SH3;[08] UPDATED PARTS. FAULT COMPLETE;[09] VERIFIED CORRECTIVE ACTION ITEM AND MEASUREMENT FIELDS; CARD COMPLETE.

Part: SKIN — CHAFED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

CHAFING ON INNER FUSELAGE SKIN AT FWD CABIN BS277+5; 3'OB OF S-2L LBL10.<[01] UPDATED MEASUREMENT TABLE.<BR>VERIFIED SRM 53-00-01-2R-38 IS APPLICABLE TO REPAIR SMALL DAMAGE IN FUSELAGE SKIN.<BR>DRILLED OUT DAMAGE TO A .125 DIAMETER PER SRM 53-00-01-2R-38 PARA. 4C2;[02] VERIFIED CORRECTIVE ACTION 1;[03] REQUEST NDI TO HFEC HOLE PROBE INSPECT TO ENSURE A CRACK FREE CONDITION.;[04] ACCOMPLISHED HFEC OPEN HOLE INSPECTION IAW 737 NDTM PART 6 CHAPTER 51-00-00 PROCEDURE 16. NO CRACKS NOTED.<BR><BR>EQUIPMENT USED: NORTEC 600 ID: ATS1465 CAL DUE: 09/2023;[05] UPDATED MEASUREMENT TABLE.<BR>OVERSIZED FASTENER HOLE TO .1875 AND APPLIED CHEMICAL CONVERSION COATING PER SRM 53-00-01-2R-38 PARA. 4E4.;[06] VERIFIED CORRECTIVE ACTION 5;[07] INSTALLED FASTENER PER SRM 53-00-01-2R-38 PARA. 4E(5C);[08] VERIFIED CORRECTIVE ACTIONS STEP 7.;[09] COMPLETE

Part: INTERCOSTAL — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CRACKED INTERCOSTAL AT PASSENGER CABIN BS380+14 BL0 WL208.<[01] FOUND CRACK ONLY AT UPPER ANGLE OF INTERCOSTAL. SRM DOES NOT HAVE ALLOWABLE DAMAGE LIMITS FOR CRACKED ANGLE. OUT OF LIMITS. REMOVE AND REPLACE IAW SRM 51-10-02-0G-0 STEP #9.;[02] REMOVED ANGLE FROM INTERCOSTAL AT PASSENGER CABIN BS 380- BS 400 BL 0 WL 208 PER SRM 51-40-02-0G-0.;[03] RECEIVED FROM TOOL ROOM NEW ANGLE P/N 143A5410-170 S/N BN 392603. LOCATED AND DRILLED NEW ANGLE PER SRM 51-40-05-0G-0 AND DWG 143A5400. REQUEST OK TO INSTALL.;[04] VERIFIED CORRECTIVE ACTION #3.<BR>VERIFIED OK TO INSTALL NEW INTERCOSTAL.;[05] INSTALLED NEW ANGLE AT PASSENGER CABIN BS 380- BS 400 BL 0 WL 208 PER SRM 51-40-02-0G-0 AND DWG 143A5400.;[06] VERIFIED CORRECTIVE ACTION #5.;[07] VERIFIED MEASUREMENTS.

Part: BRACKET — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

LEFT ECS BAY HAS CRACKED DUCT SUPPORT BRACKET (212A1116) ACCESS PANEL 192CL BS540+6 LBL8.<[01] REMOVED AND REPLACED ECS BAY DUCT SUPPORT BRACKET 212A1116 IAW SOPM 20-50-01;[02] VERIFIED PARTS REQUIREMENTS.;[03] VERIFIED CORRECTION ACTION 1;2 AND MEASUREMENT TABLE COMPLETE; CARD COMPLETE.

Part: INTERCOSTAL — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CRACKED INTERCOSTAL AT PASSENGER CABIN BS380+14 RBL9 WL208.<[01] FOUND CRACK ONLY AT UPPER ANGLE OF INTERCOSTAL. SRM DOES NOT HAVE ALLOWABLE DAMAGE LIMITS FOR CRACKED ANGLE. OUT OF LIMITS. REMOVE AND REPLACE IAW SRM 51-10-02-0G-0 STEP #9.;[02] REMOVED ANGLE FROM INTERCOSTAL AT PASSENGER CABIN BS 380- BS 400 RBL 9 WL 208 PER SRM 51-40-02-0G-0.;[03] RECEIVED FROM TOOL ROOM NEW ANGLE P/N 143A5410-170 S/N BN 392604. LOCATED AND DRILLED NEW ANGLE PER SRM 51-40-05-0G-0 AND DWG 143A5400. REQUEST OK TO INSTALL.;[04] VERIFIED CORRECTIVE ACTION #3.<BR>VERIFIED OK TO INSTALL NEW INTERCOSTAL.;[05] INSTALLED NEW ANGLE AT PASSENGER CABIN BS 380- BS 400 RBL 9 WL 208 PER SRM 51-40-02-0G-0.;[06] CORRECTIVE ACTION 5. INSTALLED NEW ANGLE AT PASSENGER CABIN BS 380- BS 400 RBL 9 WL 208 PER SRM 51-40-02-0G-0 AND DWG 143A5400.;[07] VERIFIED CORRECTIVE ACTION #6.;[08] VERIFIED MEASUREMENTS.

Part: SEAT TRACK — CORRODED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CABIN SEAT TRACK IS CORRODED AT BS 380+19; 420+14; LBL 45; WL 208<[01] VERIFIED APPLICABILITY FOR 737-700 SRM 53-00-52-1A-1.;[02] REMOVED CORROSION FROM PASSENGER CABIN SEAT TRACK AT LBL 45 WL 208 BS 380+19 L: 3' W: .90' D:.051' FOUND SEAT TRACK TO BE OUT LIMITS PER SRM 53-00-52-1A-1 FIG. 103. USED TOOL ID: ATS1738 DUE: 10/2023.;[03] CONCUR WITH APPLICABILITY OF SRM 53-00-52-1A-1.<BR>VERIFIED DAMAGED REMOVED FROM SEAT TRACK AT LBL 45 WL 208 BS 380+19 AND REMOVED MATERIAL IS OUT OF LIMITS PER SRM 53-00-52-1A-1 FIG. 103.;[04] REMOVED CABIN SEAT TRACK AT BS 380+14 LBL 45 WL 208 IAW SRM 51-40-04-0G-0;[05] RECIEVED NEW SEAT TRACK FABRICATED IAW DWG 143A5310-51. LOCATED AND STARTED DRILLING UP IAW SRM 51-40-05-0G-0; DWG 143A5300 -49 SH 55.;[06] FINISHED LOCATING; DRILLING AND COUNTERSINK NEW SEAT TRACK PER SRM 51-40-05-0G-0; SRM 51-40-08-0G-0 AND DWG 143A5300 SH 55. REQUEST OK TO INSTALL.;[07] VERIFIED CORRECTIVE ACTIONS 5 & 6.;[08] STARTED INSTALL OF SEAT TRACK IAW DWG 143A5300 SH 55.;[09] CONTINUED INSTALLATION OF SEAT TRACK PER DWG 143A5300 SH55 AND DWG 141A5300 SH22.;[10] COMPLETED INSTALL OF SEAT TRACK IAW DWG 143A5300 SH55 AND DWG 141A5300 SH22. TOOL ID: ATS2328 DUE DATE: 04/2024; <BR>TOOL ID: ATS1299 DUE DATE: 12/31/23.;[11] VERIFIED CORRECTIVE ACTION #10.;[12] VERIFIED MEASUREMENTS.

Part: ATTACH ANGLE — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

AFT CARGO BAY FWD SHIELD ATTACH ANGLE CRACKED BS 767 - BS 787 RBL 21<[01] REMOVED AFT CARGO BAY FWD ATTACH ANGLE BS 767-BS 787 RBL 21 IAW SRM 51-40-02-0G-0.;[02] RECEIVED NEW ANGLE P/N:146A8125-53 LOT:1527393-1. LOCATED; DRILLED AND ATTACHED NUTPLATES ON NEW ANGLE IAW SRM 51-40-02-0G-0 AND DWG146A8123 ID:0016 REV:-.;[03] THERE IS NO SRM ALLOWABLE DAMAGE FOR ACB FWD SHIELD ATTACH ANGLE. PART TO BE REPAIRED BY REPLACEMENT IAW SRM 51-10-02-0G-0;[04] RECEIVED NEW ANGLE P/N:146A8125-53 LOT:1527393-1.<BR>LOCATED AND DRILLED NEW ANGLE IAW SRM 51-40-05-0G-0 AND DWG 146A8123 ID:0016 REV:-<BR>INSTALLED NUTPLATES IAW SRM 51-40-02-0G-0<BR><BR>OK TO INSTALL NEW ANGLE;[05] VERIFIED CORRECTIVE ACTION ITEM 4.<BR>OKAY TO INSTALL NEW ANGLE GIVEN.;[06] INSTALLED ACB FWD SHIELD ATTACH ANGLE IAW SRM 51-40-02-0G-0; DWG 146A8123 ID:0016 REV:- AND DWG 146A0081 ID:0043 REV:-;[07] RII VERIFIED CORRECTIVE ACTION ITEM 6.;[08] VERIFIED CORRECTIVE ACTION ITEMS AND MEASUREMENT FIELDS; CARD COMPLETE.

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FWD CABIN FLOOR PANEL 221BF HAS PULLED STRANDS ON UPPER SURFACE<[01] VERIFIED STEP 9;[02] FWD CABIN FLOOR PANEL 221BF WITH PULLED STRANDS ON UPPER SURFACE WAS REPAIRED PER SRM 53-00-50-2R-1.;[03] VERIFIED ALL STEPS COMPLETE;[04] VERIFIED ALL STEPS COMPLETE AND MEASUREMENT TABLE

Part: ATTACH ANGLE — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

AFT CARGO BAY FWD SHIELD ATTACH ANGLE CRACKED BS 787- BS 794 RBL 21<[01] ADDED MEASUREMENTS;[02] REMOVED AFT CARGO FWD SHIELD ATTACH ANGLE. IAW SRM 51-40-02;[03] RECEIVED REPLACEMENT PART. CUSTOMER RO NO. 928460-SWA. JOB NUMBER 561649.;[04] VERIFIED CORRECTIVE ACTION #3;[05] DRILLED AND LOCATED REPLACEMENT PART. APPLIED CHEMICAL CONVERSION COATING. IAW SRM 51-40-05; SRM 51-40-06; SRM 51-20-01. OK TO PRIME.;[06] VERIFIED CORRECTIVE ACTION #5;[07] APPLIED PRIMER ON REPLACEMENT PART.IAW SRM 51-20-01. OK TO INSTALL.;[08] VERIFIED CORRECTIVE ACTION #7;[09] INSTALLED ATTACHE ANGLE IAW SRM 51-40-02; DWG 146A0081 ID0046 REV-;[10] VERIFIED MEASUREMENTS<BR>VERIFIED CORRECTIVE ACTION #9

Part: SUPPORT ANGLE — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

CRACKED SUPPORT ANGLE FOR CHANNEL; BS 692.5 - 694 RBL 24 WL 203<[01] UPDATED MEASUREMENTS TABLE;[02] REMOVED DAMAGED SUPPORT ANGLE FOR CHANNEL FROM BS 692.5 TO BS 694; RBL 24; WL 203 IAW SRM 51-40-02-0G-0;[03] CERTIFY;[04] SRM DOESN'T HAVE ALLOWABLE DAMAGE/REPAIR FOR CRACKED ANGLE. FOUND ANGLE TO BE OUT OF LIMITS. REMOVE AND REPLACE IAW SRM 51-10-02-0G-0 STEP #9.;[05] RECEIVED FROM TOOL ROOM HEAT TREATED ANGLE ITEM: HFAB53-AN-012 LOT: 1534692-1. LOCATED AND DRILLED NEW ANGLE PER SRM 51-40-05-0G-0 AND BOEING DWG 273A9110. APPLIED CHEMICAL CONVERSION COATING TO NEW ANGLE. REQUEST OK TO APPLY PRIMER.;[06] VERIFIED MEASUREMENT TABLE AND CORRECTIVE ACTIONS 4 AND 5. OK TO APPLY PRIMER.;[07] APPLIED CHEMICAL CONVERSION COATING PER SOPM 20-40-03 AND PRIMER PER SOPM 20-41-02 TO THE NEW ANGLE. REQUEST OK TO INSTALL.;[08] VERIFIED CORRECTIVE ACTION 7. OK TO INSTALL.;[09] INSTALLED NEW ANGLE FOR CHANNEL AT BS 692.5 - 694; RBL 24; WL 203 PER SRM 51-40-02-0G-0; SOPM 20-50-01; SRM 51-40-04-0G-0 AND BOEING DWGS 273A9110 AND 111A6000. USED TOOL ID: ATS2657 DUE: 08/2023.;[10] CERTIFIED CORRECTIVE ACTION 9;[11] VERIFIED CORRECTIVE ACTION 9 AND 10

Part: INTERCOSTAL — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CRACKED INTERCOSTAL AT FWD CABIN BS344+9 LBL12 WL208.<[01] REMOVED INTERCOSTAL AT FWD CABIN BS 344+9 LBL12 WL208 IAW SRM 51-40-02;[02] UPDATED MEASUREMENT TABLE;[03] CERTIFY ACTION #1;[04] SRM DOES NOT HAVE REPAIR LIMITS FOR CRACKED INTERCOSTALS. OUT OF LIMITS. REMOVE AND REPLACE IAW SRM 51-10-02-0G-0 STEP #9.;[05] LOCATED AND DRILLED NEW INTERCOSTAL AT BS344- BS360 LBL12 WL208 IAW SRM 51-40-05-0G-0; DWG 141A5400 SHT 43; OK TO INSTALL;[06] VERIFIED CORRECTIVE ACTION ITEMS 4 AND 5.<BR>OKAY TO INSTALL NEW INTERCOSTAL IS GIVEN.;[07] STARTED FASTENER INSTALLATION IAW SRM 51-40-02-0G-0;[08] INSTALLED 100% OF FASTENERS AT NEW INTERCOSTAL AT BS 344 TO BS 360 LBL12 WL 208 PER SRM 51-40-02-0G-0; DWG 141A5400 SHT 43.;[09] VERIFIED CORRECTIVE ACTION 8;[10] VERIFIED MEASUREMENT TABLE

Part: INTERCOSTAL — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CRACKED INTERCOSTAL AT FWD CABIN BS344+5 RBL12 WL208.<[01] UPDATED MEASUREMENT TABLE;[02] REMOVED INTERCOSTAL AT BS 344- BS360 RBL 12; WL 208 IAW SRM 51-40-02-0G-0;[03] REMOVED INTERCOSTAL AT BS 344- BS 360 BL0 FOR ACCESS ONLY IAW SRM 51-40-02-0G-0;[04] LOCATED AND DRILLED INTERCOSTAL AT BS 344- BS360 RBL 12 WL208 IAW SRM 51-40-05-0G-0; OK TO INSTALL;[05] VERIFIED CORRECTIVE ACTION ITEM 4. OKAY TO INSTALL NEW INTERCOSTAL IS GIVEN.;[06] SRM DOES NOT HAVE REPAIR LIMITS FOR CRACKED INTERCOSTALS. OUT OF LIMITS. REMOVE AND REPLACE IAW SRM 51-10-02-0G-0 STEP #9.;[07] CERTIFY CORRECTIVE ACTION 3 AND 6;[08] REINSTALLED INTERCOSTAL ACCESSED IN ACTION STEP #3 IAW SRM 51-40-02-0G-0;[09] INSTALLED INTERCOSTAL AT BS 344- BS 360 RBL 12 WL 208 IAW SRM 51-40-02-0G-0; DWG 141A5400 SHT 13;[10] UPDATED PART REQUIREMENT;[11] VERIFIED CORRECTIVE ACTION 9;[12] VERIFIED MEASUREMENT TABLE

Part: INTERCOSTAL — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CRACKED INTERCOSTAL AT FWD CABIN BS328+7 LBL46 WL208.<[01] UPDATED MEASUREMENT TABLE;[02] REMOVED DAMAGED INTERCOSTAL IAW SRM 51-40-02-0G-0;[03] LOCATED; DRILLED NEW INTERCOSTAL AT BS 328 - 344 LBL 46 IAW SRM 51-40-05-0G-0. OK TO INSTALL.;[04] VERIFIED CORRECTIVE ACTION ITEM 3.<BR>OKAY TO INSTALL INTERCOSTAL GIVEN.;[05] INSTALLED INTERCOSTAL IAW AMM 51-40-02-0G-0; DWG 141A5400 SHT 44;[06] RII VERIFIED CORRECTIVE ACTION ITEM 5;[07] VERIFIED CORRECTIVE ACTION ITEM 5 AND MEASUREMENT FIELDS; CARD COMPLETE.

Part: INTERCOSTAL — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CRACKED INTERCOSTAL AT FWD CABIN BS291 BL0 WL208.<[01] VERIFIED APPLICABILITY FOR SRM 53-10-51-1A-1 ALLOWABLE DAMAGE 1.;[02] CRACK FOUND TO BE OUT OF LIMITS PER SRM 53-10-51-1A-1; PAR. 4.B.(1).(A). FIG. 105; DETAIL A.<BR>REMOVED INTERCOSTAL FROM BS277 - BS294; WL208; BL0 PER SRM 51-40-02-0G-0.<BR>RECEIVED FROM; TOOL ROOM NEW INTERCOSTAL P/N 141A5410U3.<BR>LOCATED AND DRILLED PER SRM 51-40-05-0G-0 AND BOEING DWG 141A5400; OK TO INSTALL.;[03] MEASUREMENTS TABLE UPDATED.;[04] VERIFIED CORRECTIVE ACTION #1; #2.<BR>VERIFIED OK TO INSTALL NEW INTERCOSTAL.;[05] INSTALLED INTERCOSTAL BETWEEN BS277 - BS294; WL208; BL0 PER SRM 51-40-02-0G-0 AND BOEING DWG. 141A5400.;[06] VERIFIED CORRECTIVE ACTION #5.;[07] VERIFIED MEASUREMENTS.

Part: FLOORBEAM — CORRODED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CORROSION ON FLOOR BEAM AT AFT CABIN BS986 LBL43 WL208.<[01] VERIFIED SRM 53-70-51-1A-1 IS APPLICABLE FOR ALLOWABLE DAMAGE TO SECT. 47 FLOOR STRUCTURE.;[02] CONCUR WITH APPLICABILITY OF SRM 53-70-51-1A-1.;[03] REMOVED CORROSION FROM UPPER FLANGE OF BS 986.5 FLOOR BEAM; LBL 43-LBL 44; WL 208 IN AN AREA OF 1'X.8'X.050' PER SRM 51-10-02. CORROSION STILL EXISTS; ORIGINAL THICKNESS .150' FOUND TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1 PARA. 4D FIG. 103 DETAIL C.;[04] TOOL ID# FOR CORRECTIVE ACTION 3; ATS2472; CAL. DUE 12/31/23.;[05] VERIFIED SRM 53-70-51-2R-6 IS APPLICABLE FOR REPAIR OF SMALL CORROSION DAMAGE TO THE UPPER CHORD OF THE BS 986.5 FLOOR BEAM.<BR>INSTALLED FOD PROTECTION UNDER REPAIR AREA PER AMM 20-60-07.<BR>REMOVED 1EA FASTENER COMMON TO REPAIR AREA PER SRM 53-70-51-2R-6 PARA. 4A(2).<BR>PERFORMED DVI IN AREA OF REPAIR PER SRM 53-70-51-2R-6 PARA. 4B. NO DEFECTS NOTED.<BR>CUT AND REMOVED DAMAGED AREA OF FLOOR BEAM 1.2'X.9' PER SRM 53-70-51-2R-6. PARA. 4C(2A).FABRICATED REPAIR PARTS<BR>MATERIALS USED: <BR>FILLER: 0.150 IN. THICK 7075-T6 CLAD SHEET LOT#:1227016<BR>ANGLE: BAC1490-2887#7075T62-C LOT#: 1517291-1<BR>STRAP:0.100 IN. THICK 7075-T6 CLAD SHEET LOT:1517301-2<BR> IAW SRM 53-70-51-2R-6<BR>APPLIED CHEMICAL CONVERSION COATING APPLIED PRIMER IAW AMM 51-21-72-370-804 FLAP PEENED THE CUT EDGE WITH 100% COVERAGE PER SRM 53-70-51-2R-6 PAR 4. C. (2)(C) ] INSTALLED FLOOR BEAM REPAIR PARTS AT BS986; LBL36 - LBL46 PER SRM 53-70-51-2R-6

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 241RF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FLOOR PANEL 241RF UPPER SKIN WITH AREAS OF PULLED STRANDS WAS REPLACED WITH A NEWLY FABRICATED FLOOR PANEL DUE TO AMOUNT OF ALL DAMAGE PER SRM 53-00-50-2R-0 PARA 1. A. NOTE AND DWG 146A5810 SHEET 466. ATTACHED CURE SHEET TO THIS FAULT RECORD.;[02] JOB COMPLETE.

Part: INTERCOSTAL — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CRACKED INTERCOSTAL AT FWD CABIN BS312+5 RBL30 WL208.<[01] VERIFIED APPLICABILITY FOR SRM 53-10-51-1A-1 ALLOWABLE DAMAGE 1;[02] CRACK FOUND TO BE OUT OF LIMITS PER SRM 53-10-51-1A-1 PAR. 4.B.(1).(A). FIG 105; DETAIL A.<BR>REMOVED INTERCOSTAL FROM BS312 - BS328; RBL30; WL208 PER SRM 51-40-02-0G-0.<BR>RECEIVED FROM TOOL ROOM NEW INTERCOSTAL P/N 141A5410U12.<BR>LOCATED AND DRILLED PER SRM 51-40-05-0G-0 AND BOEING DWG. 141A5400; OK TO INSTALL.;[03] VERIFIED CORRECTIVE ACTION #1; #2.<BR>VERIFIED OK TO INSTALL NEW INTERCOSTAL.;[04] INSTALLED INTERCOSTAL BETWEEN BS312 - BS328; RBL30; WL208 PER SRM 51-40-02-0G-0 AND BOEING DWG 141A5400.;[05] VERIFIED CORRECTIVE ACTION #4.;[06] VERIFIED MEASUREMENTS.

Part: STUB FRAME — CRACKED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FWD CABIN SERVICE DOOR SURROUND LOWER STUB FRAME CRACKED BS294 RBL54 WL209.<[01] VERIFIED SRM 53-10-15-1A-2 IS APPLICABLE FOR ALLOWABLE DAMAGE TO FSD SURROUND STRUCTURE.;[02] CONCUR WITH APPLICABILITY OF SRM 53-10-15-1A-2.;[03] REMOVED CLIP P/N 141A8312-3 PER SRM 51-40-02 FOR ACCESS.<BR>REQUEST NDI TO VERIFY CRACK(S) AND MARK ENDS.;[04] HFEC INSPECTED AREA IAW 737 NDTM PART 6; 51-00-00 PROCEDURE 23.<BR>NO CRACKS NOTED.<BR>EQUIP USED:<BR>-NORTEC 600 ID: ATS1465 CAL DUE: 09/23;[05] UPDATED MEASUREMENT TABLE.<BR>UPON FURTHER INVESTIGATION; NO CRACK FOUND IN FSD BS 294 STUB FRAME; RBL 54; WL 209.;[06] REQUEST OK TO REINSTALL CLIP P/N 141A8312-3.;[07] OK TO REINSTALL CLIP P/N 141A8312-3 GIVEN.;[08] INSTALLED CLIP PER SRM 51-40-02; DWG# 141A8310 REV-; AND DWG# 140A9810 REV A.;[09] VERIFIED CORRECTIVE ACTION 8;[10] VERIFIED MEASUREMENT TABLE

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 231GF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FABRICATED FLOOR PANEL 231GF IAW SRM 53-00-50-2R-0 AND BAC DWG 143A5810-575;[02] UPDATED MEASUREMENTS TABLE;[03] VERIFIED CORRECTIVE ACTIONS 1 AND 2<BR><BR>VERIFIED MEASUREMENTS TABLE

Part: INTERCOSTAL — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

CRACKED INTERCOSTAL AT FWD CABIN BS344+5 RBL50 WL208.<[01] REQUEST HFEC INSPECTION OF SUSPECTED CRACK AREA.;[02] HFEC INSPECTED SUSPECTED CRACK AREA IAW 737 NDTM PART 6; 51-00-00 PROCEDURE 23.<BR>.3' CRACK NOTED. MARKED LOCATION<BR>EQUIP USED:<BR>-NORTEC 600 ID: ATS1465 CAL DUE: 09/23;[03] UPDATED MEASUREMENT TABLE.<BR>INSTALLED EWIS/FOD PROTECTION IN REPAIR AREA BS 344-380; RBL 45 - RBL 65; WL 204 PER AMM 20-60-07.;[04] CUT OUT THE DAMAGE AT BS344+5 RBL50 WL208 PER SRM 53-10-51-2R-6 4. C. FIG. 202.;[05] RECEIVED 1 EA HFAB53-FTG-012 FITTING P0# 929560/1;[06] REQUEST NDI FOR FREE CRACK CONDITION;[07] VERIFIED CORRECTION ACTION; ITEM NO. 4 & 5; COMPLETED.;[08] HFEC INSPECTED CUT OUT AREA IAW 737 NDTM PART 6; 51-00-00 PROCEDURE 23.<BR>NO CRACKS NOTED.<BR>EQUIP USED:<BR>-NORTEC 600 ID: ATS1465 CAL DUE: 09/23;[09] FABRICATED REPAIR PARTS [1] FILLER FROM CLAD 7076T6 0.063' LOT# 1498631-1; [5] FILLER FROM CLAD 7076T6 0.020' LOT# 1353253-2; [7] FITTING HFAB53-FTG-012 FITTING P0# 929560/1 PER SRM 53-10-51-2R-6;[11] FABRICATED [6] FITTING HFAB53-FTG-012COSTUMER RO#929498-SWA.;[12] UPDATED STEP 1;[13] VERIFIED CORRECTIVE ACTIONS 9;10;11 AND 12 COMPLETE.;[14] FABRICATED [3] REPAIR ANGLE FROM 60-5872#7075T6 LOT #509308-1 PER SRM 53-10-51-2R-6 FIG. 203 DETAIL D. APPLIED CHEMICAL CONVERSION COATING TO REPAIR PART PER SRM 53-10-51-2R-6. AMM 51-21-41-370-802.

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 231LF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] UPLOADED CURE SHEET AND VERIFIED COMPLETION OF PANEL 231LF FABRICATION IAW SRM 53-00-50-2R-0 AND BOEING DWG: 143A5810 ID: 0579.;[02] FINAL INSPECTION. JOB COMPLETE.

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 231ZF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FABRICATED NEW FLOOR PANEL 231ZF IAW SRM 53-00-50-2R-0.;[02] ATTACHED CURE SHEET TO THIS FAULT RECORD.;[03] VERIFIED CORRECTIVE ACTION 1; 2; CURE SHEETS AND MEASUREMENTS

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 241UF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] UPLOADED CURE SHEET AND VERIFIED FABRICATION OF PANEL 241UF IAW SRM 53-00-50-2R-0 AND BOEING DWG:146A5810 ID:0470.;[02] VERIFIED CORRECTIVE ACTION 1

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 241NF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FLOOR PANEL 241NF UPPER SKIN WITH AREAS OF PULLED STRANDS WAS REPLACED WITH A NEWLY FABRICATED FLOOR PANEL DUE TO AMOUNT OF ALL DAMAGE PER SRM 53-00-50-2R-0 PARA 1. A. NOTE AND DWG 146A5810 SHEET 461. ATTACHED CURE SHEET TO THIS FAULT RECORD.;[02] JOB COMPLETE.

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 241WF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] UPLOADED CURE SHEET AND VERIFIED FABRICATION OF PANEL 241WF IAW SRM 53-00-50-2R-0 AND DWG 146A5810 SHEET 471;[02] FINAL INSPECTION. JOB COMPLETE.

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 241TF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] UPLOADED CURE SHEET AND VERIFIED FABRICATION OF PANEL 241TF IAW SRM 53-00-50-2R-0 AND DWG 146A5810 SHEET 467;[02] FINAL INSPECTION. JOB COMPLETE.

Part: TENSION TIE — CORRODED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CORROSION ON TENSION STRAP AT AFT CABIN BS1016+12 RBL18 WL208.<[01] REMOVED TENSION STRAP AT AFT CABIN BS1016+12 RBL18 WL208 PER SRM 51-40-02-0G-0.;[02] UPDATED MEASUREMENTS TABLE.;[03] SRM DOES NOT HAVE ALLOWABLE DAMAGE FOR CORROSION ON TENSION STRAP. OUT OF LIMITS. REMOVE AND REPLACE PER SRM 51-10-02-0G-0. STEP #9.;[04] RECEIVED FROM TOOL ROOM NEW TENSION STRAP PNLOCATED AND DRILLED TENSION STRAP 147A5744U2 PER SRM 51-40-05-0G-0 AND DWG #147A5730. REQUEST OK TO INSTALL.;[05] CORRECTION ON ITEM 4: RECEIVED FROM TOOL ROOM NEW TENSION STRAP PN: 147A5744U2 LOT#1533494-1. LOCATED AND DRILLED TENSION STRAP PER SRM 51-40-05-0G-0 AND DWG #147A5730. REQUEST OK TO INSTALL.;[06] VERIFIED CORRECTIVE ACTION #5;[07] INSTALLED TENSION STRAP AT AFT CABIN BS1016+12 RBL18 WL208 PER SRM 51-40-02-0G-0 AND DWG#147A5730.;[08] VERIFIED CORRECTIVE ACTION 7;[09] VERIFIED MEASUREMENT TABLE

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 242NF UPPER SKIN HAS PULLED STRANDS.<[01] FLOOR PANEL 242NF UPPER SKIN WITH PULLED STRANDS WAS REPLACED WITH A NEWLY FABRICATED FLOOR PANEL PER SRM 53-00-50-2R-0 PARA 1. A. NOTE. AND ATTACHED CURE SHEET TO THIS FAULT RECORD.;[02] JOB COMPLETE.

Part: SUPPORT ANGLE — CORRODED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CORROSION ON FSD MOP SILL THRESHOLD SUPPORT ANGLE BS305 - BS323 RBL57 WL209.<REMOVED CORROSION ALONG FSD MOP SILL THRESHOLD SUPPORT ANGLE AT RBL57; WL209 BS 291.5 + 12' L:1.5' X W:1';<BR>BS312 L1:5' X W:1'; <BR>BS312 +5' L1:5' X W:1'; <BR>BS312 +8' L1:5' X W:1'; <BR>BS312 +12' L1:5' X W:1'; <BR>PER SRM 53-10-15-1A-2;[03] VERIFIED ITEM 1; 2 CORRECTIVE ACTIONS.;[04] REQUEST NDI FOR REMAINING THICKNESS;[05] NDT UT INSPECTED BLENDED AREAS IAW 737 NDTM PART 4 51-00-00 PROC 2. <BR>LOWEST READING IS 0.076' IN THE 4 EA AREAS OF DAMAGE REMOVAL. <BR>EQUIP USED: EPOCH 650 ID: ATS2031 DUE 05/24;[06] REMOVED CORROSION ALONG FSD MOP SILL THRESHOLD SUPPORT ANGLE AT RBL57; WL209 BS 291.5 + 12' L:1.5' X W:1' D: 0.012' FROM ORIGINAL THICKNESS 0.090' ALLOWABLE MATERIAL REMOVED IS 0.10' FOUND OUT WITHIN LIMITS PER SRM 53-10-15-1A-2. MICROMETER ID IS0000686 DUE DATE: MAR-231-2024;[07] REMOVED ON FSD MOP SILL THRESHOLD SUPPORT ANGLE BS 296 TO BS 328 RBL 57 IAW SRM 51-40-02;[08] RECEIVED NEW ON FSD MOP SILL THRESHOLD SUPPORT ANGLE BS 296 TO BS 328 RBL 57 P/N 141A8312-5 LOT#1522637. LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG 141A8310;[] INSTALLED NEW THRESHOLD SUPPORT ANGLE FSD MOP SILL BS 305-BS 323 RBL WL 209 IAW SRM 51-40-02-0G-0 AND DWG #141A8310;[15] CERTIFY;[16] VERIFIED CORRECTIVE ACTIONS STEP 14.;[17] VERIFIED MEASUREMENTS TABLE.;[18] COMPLETE

Part: SILL DRAIN — CORRODED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CORROSION ON FSD MOP SILL BS294+7; BS326 - BS346 RBL56 WL208.<[01] VERIFIED APPLICABILITY OF SRM 53-10-15-1A-2;[02] REMOVED CORROSION ALONG FSD MOP SILL <BR>AT RBL56; WL208 BS 291.5 + 11' - BS312 + 10' L:20' X W:1'; REMOVED CORROSION ALONG FSD MOP SILL AT RBL56; WL208; BS328 + 2'; L: 2 X W:1' D: 0.002' FROM ORIGINAL THICKNESS IS 0.080' FOUND WITHIN LIMITS PER SRM 53-10-15-1A-1 FIG. 103 DETAIL D.;[08] REMOVED CORROSION ALONG FSD MOP SILL AT RBL56; WL208; BS 291.5 + 11' - BS312 + 10' L:20' X W:1'; D: 0.005' FROM ORIGINAL THICKNESS IS 0.080' REMOVED MATERIAL AROUND THAN MORE THREE FASTENERS IN ALL GROUPS OF TEN; FOUND WITHOUT LIMITS PER SRM 53-10-15-1A-1 FIG. 103 DETAIL G. DAMAGE IS BEYOND LIMITS DUE TO REMOVED MATERIAL AROUND THAN MORE THREE FASTENERS IN ALL GROUPS OF TEN; FOUND WITHOUT LIMITS PER SRM 53-10-15-1A-1 FIG. 103 DETAIL G. DAMAGE IS BEYOND LIMITS DUE TO REMOVED MATERIAL AROUND THAN MORE THREE FASTENERS IN ALL GROUPS OF TEN; FOUND WITHOUT LIMITS PER SRM 53-10-15-1A-2 FIG. 103 DETAIL G.;[11] HFEC ROTARY INSPECTED OPEN HOLES IN BLENDED AREA PER 737NDT PART 6 51-00-00 PROCEDURE 16. NO CRACKS FOUND. TOOL N500 IS000681 DUE 04/2024.;[12] UT INSPECTED BLENDED AREA IAW 737 NDTM PART 4; 51-00-00 PROCEDURE 2.<BR>REMAINING MATERIAL THICKNESS IS 0.074' ADJACENT TO 0.080'. <BR>SEE ATTACHED GRID.<BR>EQUIP USED: <BR>-EPOCH 650 ID: ATS2342 CAL DUE: 07/23;[13] COMPLETE;[14] VERIFIED MEASUREMENT TABLE AND CORRECTIVE ACTION 13

Part: SILL DRAIN — CORRODED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CORROSION ON FED MOP SILL BS294+9; BS317 - BS342 LBL56 WL208.<[01] VERIFIED APPLICABILITY FOR SRM 53-10-15-1A-1;[02] REMOVED CORROSION ALONG FED MOP SILL<BR>AT LBL56; WL208; BS294.5 + 10'; L: 2 X W:1'<BR>BS312 + 5'; L: 2.5' X W:1'<BR>BS312 + 9'; L: 1.5' X W:1'<BR>BS328 + 3'; L:5' X W:1'<BR>BS328 + 10'; L:2' X W:1'<BR>BS328 + 14'; L:3' X W:1'REMOVED CORROSION ALONG FED MOP SILL AT LBL56; WL208; BS328 + 3'; L:5' X W:1' D: 0.002' FROM ORIGINAL THICKNESS IS 0.090' REMOVED MATERIAL AROUND THAN MORE THREE FASTENERS IN ALL GROUPS OF TEN; FOUND WITHOUT LIMITS PER SRM 53-10-15-1A-1 FIG. 108 DETAIL H.;[10] VERIFIED CORRECTIVE ACTION ITEMS 8 AND 9. DAMAGE IS BEYOND LIMITS DUE TO REMOVED MATERIAL AROUND THAN MORE THREE FASTENERS IN ALL GROUPS OF TEN; FOUND WITHOUT LIMITS PER SRM 53-10-15-1A-1 FIG. 108 DETAIL H.;[11] HFEC ROTARY INSPECTED OPEN HOLES IN BLENDED AREA PER 737NDT PART 6 51-00-00 PROCEDURE 16. NO CRACKS FOUND. TOOL N500 IS000681 DUE 04/2024.;[12] UT INSPECTED BLENDED AREA IAW 737 NDTM PART 4; 51-00-00 PROCEDURE 2.<BR>REMAINING MATERIAL THICKNESS IS 0.087' ADJACENT TO 0.090'.<BR>SEE ATTACHED GRID.<BR>EQUIP USED:<BR>-EPOCH 650 ID: ATS2342 CAL DUE: 07/23

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 241VF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] UPLOADED CURE SHEET AND VERIFIED FABRICATION OF PANEL 241VF IAW SRM 53-00-50-2R-0 PAR. 5. S. (1) (A) - (D) AND BOEING DWG: 146A5810 ID: 0469.;[02] FINAL INSPECTION. JOB COMPLETE.<BR><BR>VERIFIED MEASUREMENTS TABLE.

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FALOOR PANEL 241KF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FLOOR PANEL 241KF UPPER SKIN WITH AREAS OF PULLED STRANDS WAS REPLACED WITH A NEWLY FABRICATED FLOOR PANEL DUE TO AMOUNT OF ALL DAMAGE PER SRM 53-00-50-2R-0 PARA 1. A. NOTE AND DWG 146A5810 SHEET 505. ATTACHED CURE SHEET TO THIS FAULT RECORD.;[02] JOB COMPLETE.

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 231UF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FABRICATED NEW FLOOR PANEL 231UF IAW SRM 53-00-50-2R-0.;[02] ATTACHED CURE SHEET TO THIS FAULT RECORD.;[03] VERIFIED CORRECTIVE ACTION 1; 2; CURE SHEETS AND MEASUREMENTS

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 231HF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FABRICATED NEW FLOOR PANEL 231HF IAW SRM 53-00-50-2R-0.;[02] ATTACHED CURE SHEET TO THIS FAULT RECORD.;[03] VERIFIED CORRECTIVE ACTION 1; 2; CURE SHEETS AND MEASUREMENTS

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 231DF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FABRICATED FLOOR PANEL 231DF IAW SRM 53-00-50-2R-0 AND BAC DWG 143A5810-513;[02] UPDATED MEASUREMENTS TABLE;[03] VERIFIED CORRECTIVE ACTIONS 1 AND 2

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR PANEL 231KF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] IDENTIFIED FLOOR PANEL 231KF MATERIALS IAW SRM 53-00-50-0I-1 FIG 3 TABLE 3.<BR><BR>DUE TO EXTENT OF THE DAMAGE FABRICATED NEW 231KF FLOOR PANEL FROM BMS4-23 TYPE 2 LOT#1531001-1; INSTALLED INSERTS USING BMS5-107 LOT#AK2KP8383K-1 AND CURED USING HEAT LAMP AND THERMOMETER ATS2209 CAL DUE DATE 10/2023 THEN PART MARKED AND APPLIED TAPE IAW SRM 53-00-50-2R-0 PARA 1A(NOTE) PARA 5S AND BOEING DWG 143A5810 ID: 0580.;[02] VERIFIED CORRECTIVE ACTION 1<BR><BR>VERIFIED MEASUREMENTS TABLE;[03] UPLOADED CURE SHEET. VERIFIED FABRICATION OF PANEL 231KF IAW SRM 53-00-50-2R-0 PARA 1A(NOTE) AND BOEING DWG 143A5810 ID: 0580.;[04] VERIFIED CORRECTIVE ACTION 3

Part: FLOOR PANEL — DAMAGED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FWD CABIN FLOOR PANEL 221GF FORWARD O/B CORNER (TANG) BROKEN<[01] COMPLETED STEPS 11 AND 12.;[02] FWD CABIN FLOOR PANEL 221GF O/B CORNER (TANG) REPAIRED IAW SRM 53-00-50-2R-6;[03] VERIFIED CORRECTIVE ACTION 2;[04] VERIFIED CORRECTIVE ACTION 2

Part: FLOOR PANEL — DAMAGED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FWD CABIN FLOOR PANEL 221BF AFT O/B CORNER (TANG) IS BROKEN<[01] FWD CABIN FLOOR PANEL 221BF WITH AFT O/B CORNER (TANG) BROKEN WAS REPAIRED PER SRM 53-00-50-2R-1. ATTACHED CURE SHEETS TO THIS FAULT RECORD.;[02] VERIFIED CORRECTIVE ACTION 1;[03] VERIFIED CORRECTIVE ACTION 1

Part: SUPPORT — CORRODED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

FLOOR TO SIDEWALL SUPPORT CORROSION BS 727A+9 - 767 RBL 20 WL 156<[01] UPDATE MEASUREMENTS TABLE;[02] SRM 53-00-53-1A-2 IS APPLICABLE FOR THIS;[03] BLENDED CORROSION ON FLOOR TO SIDEWALL SUPPORT CORROSION BS 727A+9 - 767 RBL 20 WL 156;<BR>WORK AREA <BR>BS 727A+12'; L 1.2' X W 0.700' X D 0.009';<BR>BS 727B+2'; L 1.2' X W 0.800' X D 0.011';<BR>BS 727C+2'; L1.0' X W 0.700' X D 0.011'<BR>FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2'<BR>USED DEPTH GAGE; ID: ATS2472; DUE: 12/31/2023;[04] REMOVED FLOOR TO SIDEWALL SUPPORT CORROSION BS 727A+9 - 767 RBL 20 WL 156 IAW SRM 51-40-02-0G-0;[05] VERIFIED ITEMS 2;3.<BR>VERIFIED OUT OF LIMITS.;[06] ROMOVED FLOOR TO SIDEWALL SUPPORT FROM BS 727 - 767 RBL 20 WL 156 IAW SRM 51-40-02-0G-0;[07] FABRICATED ; LOCATED AND DRILLED NEW SIDEWALL SUPPORT FROM BS 727+4 TO BS 767 ;RBL 20; WL 156 IAW SRM 51-40-05-0G-0 AND DWG 146A7502;ID:0049;REV:-;MATERIAL BAC1496-377 7075-T62; LOT#1526048-1.<BR>APPLIED CHEMICAL CONVERTION IAW AMM 51-21-41-370-802; REQUEST OK TO APPLY PRIMER;[08] VERIFIED CORRECTIVE ACTION 7.<BR>OK TO PRIME;[09] APPLIED PRIMER ON NEW FLOOR TO SIDEWALL SUPPORT IAW AMM 51-21-72-370-804; REQUES OK TO INSTALL ADHESIVELY BONDED NUTPLES

Part: STRINGER — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

AREA AFT OF FWD CARGO BAY HAS A CRACKED STRINGER AT THE AFT FASTENER; STR. 23L BS 520-540 WL 156<[01] EVALUATED CRACKAT FCB STRINGER 23L;BS 539 DAMAGE FOUND TO BE OUT LIMITS IAW SRM 53-00-03-1A FIG 103 DETAIL A.;[02] EVALUATED CRACK AT FCB STRINGER 23L;BS 539 DAMAGE FOUND TO BE OUT LIMITS IAW SRM 53-00-03-1A FIG 103 DETAIL A.;[03] VERIFIED APPLICABILITY FOR STRINGER 23 L/H IAW SRM 53-00-03-2R-1 PAR 4. FIG 205.;[04] VERIFIED APPLICABILITY FOR STRINGER 23 L/H IAW SRM 53-00-03-2R-1 PAR 4. FIG 205.;[05] VERIFIED CORRECTIVE ACTION STEPS 1-4;[06] CUTOUT AND REMOVED DAMAGE AT STRINGER SECTION 23L BETWEEN BS 500D+11' TO BS 539 IAW 53-00-03-2R-1 PAR 4 STEP A-B;[07] VERIFIED CORRECTIVE ACTION STEP 6;[08] UPDATE STEP 1.;[09] PERFOM HFEC INSPECTION TO DAMAGE CUTOUT AT FCB STRINGER 23L BS 500D+11' AND ALL OPEN HOLES COMMON TO REPAIR AREA.;[10] PERFORM HFEC INSPECTION TO DAMAGE CUTOUT AT FCB STRINGER 23L BS 500D+11' AND ALL OPEN HOLES COMMON TO REPAIR AREA; RECEIVED NEW STRINGER REPAIR PARTS FROM OUTSIDE LOCATED AND DRILLED REPAIR PARTS IAW SRM 53-00-03-2R-1 AND SRM 51-40-05-0G-0.APPLIED PRIMER IAW AMM 51-21-72-370-804. INSTALLED REPAIR PARTS IAW DWG 143A3210; SRM 53-00-03-2R-1 AND SRM 51-40-02.

Part: STRINGER — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

AREA AFT OF FWD CARGO BAY HAS A CRACKED STRINGER AT THE AFT FASTENER; STR. 26L BS 520-540 WL 156<[01] EVALUATED CRACK AT FCB STRINGER 26L;BS 539 DAMAGE FOUND TO BE OUT LIMITS IAW SRM 53-00-03-1A FIG 103 DETAIL A.;CUTOUT AND REMOVED DAMAGE AT STRINGER SECTION 26L BETWEEN BS 500D+11' TO BS 539 ; WL 156 IAW 53-00-03-2R-1 PAR 4 STEP A-B;[06] VERIFIED STEP 5;[07] UPDATE STEP 1-2.;[08] PERFOM HFEC INSPECTION TO DAMEGE CUOUT AT FCB STRINGER 26L BS 500D+11';[09] PERFOM HFEC INSPECTION TO DAMAGE CUTOUT AT FCB STRINGER 26L BS 500D+11'.;[10] HFEC INSPECTED TRIMMED EDGE OF DAMAGE CUTOUT PER 737NDT PART 6 51-00-00 PROCEDURE 23. NO CRACKS FOUND. TOOL N500 IS000681 DUE 04/2024.;[11] RECEIVED NEW STRINGER SECTION P/N:HFAB53-STR-011; LOT:1533433-1;PO/N:927775/1 AND HAT SECTION P/N:88-78188-14 AND LOCATED AND DRILLED NEW STRINGER SECTION AT FCB BETWEEN BS 500D+11' TO BS 539 STR 26L/H AND HAT SECTION BETWEEN BS 500D+5' TO 500D+17' IAW SRM 53-00-03-2R-1 PAR 4 STEPS D TO H FIG 205.;[12] APPLIED CHEMICAL CONVESRSION COATING ON REPAIR PARTS AND BARE SURFACE TO INITIAL PARTS. IAW SRM 53-00-03-2R-1 PAR 4 STEP I AND SRM 51-20-01..APPLIED PRIME ON REPAIR PARTS AND ON BARE SURFACE TO INITIAL PARTS IAW SOPM 20-41-02INSTALLED STRINGER SECTION AT FCB BETWEEN BS 500D+11' TO BS 539 STR 26L/H AND HAT SECTION BETWEEN BS 500D+5' TO 500D+17' IAW SRM 53-00-03-2R-1 FIG: 205;[20] FINAL INSPECTION. JOB COMPLETE. LOOKS GOOD!<BR><BR>VERIFIED MEASUREMENTS TABLE.

Part: STRINGER — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

AREA AFT OF FWD CARGO BAY HAS A CRACKED STRINGER AT THE AFT FASTENER; STR. 24R BS 520-540 WL 156<[01] EVALUATED CRACK AT FCB STRINGER 24R/H BS 539 DAMAGE FOUND TO BE OUT LIMITS IAW SRM 53-00-03-1A FIG 103 DETAIL A.;[02] VERIFIED APPLICABILITY FOR STR 24R/H AT FCB IAW SRM 53-00-03-2R-1 PAR 4. FIG 205;[03] CUTOUT AND REMOVED DAMAGE AT STRINGER SECTION 24R/H BETWEEN BS 500D+11' TO BS 539 IAW SRM 53-00-03-2R-1 PAR 4 STEPS A-B.;[04] UPDATE STEP 1 AND 2.RECEIVED NEW STRINGER SECTION P/N:HFAB53-STR-011;LOT:1533645-1;PO/N:927987/1 AND LOCATED AND DRILLED AT FCB STR 24R/H BETWEEN BS 500D+11' TO BS 539 AND APPLIED CHEMICAL CONVERISON COATING ON STRINGER SECTION IAW SRM 53-00-03-2R-1 FIG 205. REQUEST OK TO PRIME STRINGER SECTION.;[11] RECEIVED NEW STRINGER SECTION P/N:HFAB53-STR-011;LOT:1533645-1;PO/N:927987/1 ANDLOCATED AND DRILLED NEW PART IAW SRM 53-00-03-2R-1 REPAIR 1 AND SRM 51-40-05-0G-0.<BR>APPLIED CONVERSION COATING IAW AMM 51-21-41-370-803.<BR>APPLIED PRIMER IAW AMM 51-21-72-370-804.;[16] VERIFIED CORRECTION ACTION ITEM 15.;] INSTALLED REPAIR PARTS AT FCB BETWEEN BS 500D+5' TO BS 539 STRINGER 24 R/H IAW SRM 53-00-03-2R-1 REPAIR 1; FIG 205.

Part: STRINGER — CORRODED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

AREA AFT OF FWD CARGO BAY HAS A CRACKED STRINGER AT THE AFT FASTENER; STR. 23R BS 520-540 WL 156<[01] EVALUATED CRACK AT FCB STRINGER 23R/H BS 539 DAMAGE FOUND TO BE OUT LIMITS IAW SRM 53-00-03-1A FIG 103 DETAIL A;[02] VERIFIED APPLICABILITY FOR STR 23R/H AT FCB IAW SRM 53-00-03-2R-1 PAR 4. FIG 205;[03] CUTOUT AND REMOVED DAMAGE AT STRINGER SECTION 23R/H BETWEEN BS 500D+11' TO BS 539 IAW SRM 53-00-03-2R-1 PAR 4 STEPS A-B.;[04] UPDATE STEP 1;[05] VERIFIED APPLICABILITY FOR STR 23R/H AT FCB IAW SRM 53-00-03-2R-1 PAR 4. FIG 205;RECIVED NEW STRINGER SECTION P/N:HFAB53-STR-011;LOT:1533642-1;PO/N:927988/1 AND HAT SECTION P/N:HFAB53-HS-011;LOT:1533701-1;PO/N:927991/1.;[10] UPDATE STEP 2;[11] LOCATED AND DRILLED NEW STRINGER SECTION AT FCB STR 23R/H BETWEEN BS 500D+11' TO BS 539 AND HAT SECTION BETWEEN BS 500D+5' TO BS 500D+17' AND APPLIED CHEMICAL CONVERSION COATING ON REPAIR PARTS IAW SRM 53-00-03-2R-1; PAR 4 STEPS D TO I; FIG 205. REQUEST OK TO PRIME;[12] VERIFIED CORRECTIVE ACTION #11;[13] APLLIED PRIME ON REPAIR PARTS IAW SOPM 20-41-02;PARTIALLY INSTALLED REPAIR PARTS IAW DWG 143A3250 AND SRM 51-40-02. BMS5-95 C-20 SEALANT APPLIED AT 20:00 UTC (1:00PM LOCAL);[17] UPDATE STEPS 1 AND 2. INSTALLED REPAIR PARTS AT FCB STR 23R/H BETWEEN 500D+5' TO 539 IAW SRM SRM 53-00-03-2R-1; FIG 205.;[21] INSTALLED REPAIR PARTS AT FCB STR 23R/H BETWEEN 500D+5' TO 539 IAW SRM 53-00-03-2R-1;PAR 4; FIG 205

Part: SUPPORT — CORRODED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

FLOOR TO SIDEWALL SUPPORT HAS CORROSION BS 727E+13 - 787+19 RBL 20 WL 156<[01] UPDATED MEASUREMENTS TABLE;[02] FOUND UNDER INVESTIGATION LOCATION IS BS 727E+13 TO BS 747+19; RBL 20; WL 156;[03] SRM 53-00-53-1A-2 IS APPLICABLE FOR THIS;[04] BLENDED CORROSION ON FLOOR TO SIDEWALL SUPPORT HAS CORROSION BS 727E+13 - 747+19 RBL 20 WL 156;<BR>WORK AREA : BS 727E+1.5'; L 0.600' X W 0.600' X D 0.010'.<BR>BS 727E+2'; L 0.900' X W 0.700' X D 0.010; <BR>BS 727E+19'; L1.0' X W 0.600' X D 0.010'.<BR>BS 747+2'; L 1.0' X W 0.800' X D 0.009'.<BR>BS 747+10'; L 1.0' X W 0.700' X D 0.011'.<BR>BS 747+19'; L 1.0' X W 0.700' X D 0.0900'; FOUND OUT OF LIMITS IAW SRM 53-00-52-1A-2.<BR>USED DEPTH GAGE : ID:ATS2472;DUE: 12/31/2023;[05] WORK WILL BE ACCOMPLISH ON CUSTOMER CARD NBR: TTG8Q00M0TZB;[06] VERIFIED ITEMS 2;3;4. <BR>VERIFIED OUT OF LIMITS.;[07] VERIFIED CORRECTIVE ACTION 5 AND MEASUREMENT TABLE

Part: SHIELD — CORRODED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

FWD SHIELD IS CORRODED FROM BS 767-767+16 RBL 20 WL 157<[01] UPDATED MEASUREMENTS TABLE;[02] NOT FOUND ALLOWABLE ON SRM; PART WILL BE REPLACE PER SRM 51-10-02-0G-0; STEP 9;[03] REMOVED FWD SHIELD FROM AFT CARGO COMPARTMENT FROM BS 767 TO BS 794.25 IAW SRM 51-40-02-0G-0.<BR>LOCATED AND DRILLED NEW FWD SHIELD IAW SRM 51-40-05-0G-0 AND DWG 146A0081;ID:0025; REV:A; REQUEST OK TO INSTALL;[04] VERIFIED MEASUREMENT TABLE. OK TO INSTALL PART;[05] OK TO INSTALL PART;[06] STARTED TO INSTALL IAW SRM 51-40-02 DWG 146A0081;ID:0025; REV:A;[07] APPLIED TOP COAT BMS-10-11 TYPE 2 IAW AMM 51-21-73-370-804 AT SHIELD BEFORE INSTALLED;[08] VERIFIED CORRECTIVE ACTION 7;[09] APPLIED CIC AT SHIELD IAW SOPM 20-41-05.REQ. OK TO INSTALL SHIELD;[10] VERIFIED CORRECTIVE ACTION 9.<BR>OK TO INSTALL SHIELD;[11] INSTALLED NEW SHIELD IAW SRM 51-40-02-0G-0 AND DWG 146A0081 REV:A;[12] VERIFIED CORRECTIVE ACTION 11;[13] VERIFIED MEASUREMENT TABLE

Part: INTERCOSTAL — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

CRACKED INTERCOSTAL IN UPPER AFT RADIUS BS 947 RBL 17 WL 179<[01] VERIFIED APPLICABILITY OF SRM 53-70-53-01-2 IDENTIFICATION 2 - SECTION 47 AND SRM 53-00-53-1A-2 ALLOWABLE DAMAGE 2.;[02] VERIFIED ITEM 1 CORRECTIVE ACTIONS.;[03] MEASURED CRACK ON INTERCOSTAL IS 1;100' AND IS FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2 ALLOWABLE DAMAGE 2; FIG. 103.<BR>REMOVED ACB INTERCOSTAL FROM BS 727 TO BS 747; RBL 17 IAW SRM 51-40-02-0G-0.<BR>UPDATED MEASUREMENT TABLE.;[04] VERIFIED OUT OF LIMITS.;[05] VERIFIED ITEM 1 CORRECTIVE ACTIONS.;[06] VERIFIED ITEM 3 CORRECTIVE ACTIONS.;[07] LOCATED AND DRILLED NEW INTERCOSTAL P/N 147A7500-22 IAW SRM 51-40-05-0G-0; AN DWG. # 147A7500; REV. -.;[08] REQ. OK TO INSTALL NEW INTERCOSTAL.;[09] VERIFIED CORRECTIVE ACTION 7. <BR>OK TO INSTALL;[10] OK TO TREAT AND PRIME;[11] ENTERED IN ERROR;[12] INSTALLED NEW INTERCOSTAL P/N 147A7500-22 IAW SRM 51-40-02-0G-0; AND DWG. # 147A7500; REV. -.;[13] VERIFIED CORRECTIVE ACTION 12;[14] VERIFIED MEASUREMENT TABLE

Part: SUPPORT — CORRODED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

FLOOR TO SIDEWALL SUPPORT HAS CORROSION BS 727A+5 - 727E+3 LBL 20 WL 156<[01] VERIFIED APPLICABILITY FOR ALLOWABLE DAMAGE LIMITS OF ACB FLOOR TO SIDEWALL SUPPORT; BS727A+5 727E+3 LBL 20 WL 156 IAW SRM 53-00-53-1A-2 ALLOWABLE DAMAGE 2.;[05] FABRIACATED LOCATED AND DRILLED ON AFT CARGO BAY L/H NEW FLOOR TO SIDEWALL SUPPORT BS 727 TO BS 847;LBL 20 WL 156 MATERIAL USED BAC 1496-377#7075T62 LOT#1526048-1;AND SPLICE BTW BS 727'E' TO 747;LBL 20 WL 156 ;MATERIAL USED BAC1496-377#7075T62 LOT#1526048-1;IAW SRM 51-40-05 ;SRM 53-00-53-2R-6 REPAIR 6 AND DWG 146A7502 REV:- OK TREAT AND PRIME.;[06] VERIFIED CORRECTIVE ACTION 5.<BR>OK TO TREAT AND PRIME[08] INSTALLED SPLICE SIDEPLATE BETWEEN 727E AND 747 ZEE CHANNEL SIDEPLATES AND ATTACH FITTINGS AND NUT PLATES IAW SRM 53-00-53-2R-6; SRM 51-40-10-2R-0 & DWG146A7502 REV:-.;[17] PARTIALLY INSTALLED NEW FLOOR TO SIDEWALL SUPPORT AT BS 727A - BS847 LBL 20 WL 156 IAW SRM 51-40-02-0G-0 & DWG 146A7500 ID: 0181 REV:- & DWG 146A7502 ID:0001 REV:A.;[18] COMPLETED INSTALLATION OF NEW FLOOR TO SIDEWALL SUPPORT AT BS727 TO BS847 LBL20 WL156 IAW SRM 51-40-02-0G-0; DWG 146A7500 ID: 0181 REV:- & DWG 146A 7502 ID:0001 REV:A.;[19] VERIFIED ITEM 18 CORRECTIVE ACTIONS.;[20] VERIFIED STEPS 1;2 COMPLETE. <BR>VERIFIED MEASUREMENTS.

Part: STRAP — CORRODED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

CORROSION ON THRESHOLD TIE STRAP AT FASTENER HOLES BS 787+8 - 807+13 RBL 20 WL 159<[01] VERIFIED APPLICABILITY IAW SRM 53-60-15-01-1 AND SRM 53-60-15-1A-1;[09] OK TO INSTALL NEW THRESHOLD TIE STRAP.;[10] OKAY TO INSTALL GIVEN.;[11] STARTED INSTALLATION OF THRESHOLD TIE STRAP IAW SRM 51-40-02 AND DWG 146A8340 REV-; DWG 146A8120 REV A; DWG 146A0081 REV C;[12] EDIT TO CORRECTIVE ACTION 11<BR>APPLIED SEALANT AT 7:00 PM/11-JUL-2023 02:00 UTC<BR>BMS 5-95 TY 1 CL C 20;[13] INSTALLED THRESHOLD TIE STRAP AT ACB BETWEEN BS 767+6' TO BS 847+13' RBL20 WL 159IAW SRM 51-40-02 AND DWG:146A8120 AND DWG:146A0081.;[14] FINAL INSPECTION. JOB COMPLETE.

Part: STRINGER — CORRODED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

AREA AFT OF FWD CARGO BAY HAS A CORRODED STR. R25 BS500-540; WL 156<[01] EVALUATED CORROSION AT FCB STRINGER 25R/H BS 539 DAMAGE FOUND TO BE OUT LIMITS IAW SRM 53-00-03-1A FIG 103 DETAIL B;[02] VERIFIED APPLICABILITY FOR STR 25R/H AT FCB IAW SRM 53-00-03-2R-1 PAR 4. FIG 206;[03] CUTOUT AND REMOVED DAMAGE AT STRINGER SECTION 25R/H BETWEEN BS 500D+11' TO BS 539 IAW SRM 53-00-03-2R-1 PAR 4 STEPS A-B;[04] VERIFIED APPLICABILITY FOR STR 25R/H AT FCB IAW SRM 53-00-03-2R-1 PAR 4. FIG 206;[05] UPDATE STEPS 1 AND 2;[06] VERIFIED CORRECTIVE ACTION #1; 2; 3; 4;[07] PERFORM HFEC INSPECTION TO DAMAGE TO CUTOUT AT STRINGER 25R/H BS 500D+11';[08] ACCOMPLISHED HFEC SURFACE SCAN OF CUT EDGE IAW 737 NDTM PART 6 CHAPTER 51-00-00 PROCEDURE 23. NO CRACKS NOTED.<BR><BR>EQUIPMENT USED: NORTEC 600 ID: ATS1465 CAL DUE: 09/2023;[09] WHILE PERFORMING STRINGER REPAIR. ADDITIONAL DAMAGED NOTED ON EXISTING STRINGER. REMOVED 3 FASTENERS COMMON TO STRINGER AND SKIN FOM.<BR><BR>CUTOUT ADDITIONAL DAMAGED ON STRINGER SECTION 25R/H STA 500D+7 IAW SRM 53-00-03-2R-1 PAR 4 STEPS A-B;[10] VERIFIED CORRECTIVE ACTION 9;[11] UPDATED MEASUREMENT TABLE;[12] RECEIVED NEW STRINGER SECTION (1EA)P/N:HFAB53-ST-010; LOT:1534363-2; PO/N:929199/2; NEW ANGLE (1EA)P/N: HFAB53-AN-010; LOT:1534359-4;PO/N:929199/4; NEW CHANNEL (2EA) P/N:HFAB53-CN-010; LOT:1534356-6;PO/N:929199/6.;[13] UPDATE STEP 5.;[14] UPDATE STEPS 1;2;5.;[15] REPAIRED STR 25R IAW EA 23-153-02120;[16] VERIFIED CORRECTIVE ACTION 15.

Part: SHIELD — CORRODED (ZN 200 FUS TOP) · airframe 38,362 hrs · 23,630 cycles

CORROSION ON AFT SHIELD AT BS 500-500A RBL 25 WL 156<[01] ENTERED MEASUREMENTS;[02] SRM 53-00-53-1A-2 IS APPLICABLE FOR THIS DAMAGE EVALUATION.<BR>NO ALLOWABLE DAMAGE FOUND IN 737-700 SRM FOR THIS PART.<BR>REPAIR BY REPLACEMENT SRM 51-10-02-0G-0 STEP 9;[03] VERIFIED CORRECTIVE ACTION STEP 2;[04] VERIFIED MEASUREMENT TABLE;[05] DRILLED AND LOCATED AND INSTALLED A-NUTS ON REPLACEMENT PART. IAW DWG 143A0080 ID0041; SRM 51-40-05; SRM 51-40-06; SRM 51-40-08; SRM 51-40-02.;[06] REQUEST OK TO INSTALL NEW SHIELD.;[07] VERIFIED CORRECTIVE ACTION #5.<BR>VERIFIED OK TO INSTALL NEW SHIELD.;[08] INSTALLED NEW SHIELD AT FCB BETWEEN BS 492 TO 500A ;RBL 25 ; WL 156 IAW SRM 51-40-02 AND DWG:143A0080; ID: 0041 ;REV:-;[09] VERIFIED CORRECTIVE ACTION #8.

Part: SUPPORT — CHAFED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

CHAFING DAMAGE ON FWD BULKHEAD SUPPORT BS400 LBL24 WL156<[01] REMOVED DAMAGE IAW SRM 51-10-02.<BR>DAMAGED AREA MEASURES 0.30' X 0.80';[02] VERIFIED CORRECTIVE ACTION #1;[03] NOT FOUND ALLOWABLE DAMAGE ON THE SRM REPAIR BY REPLACEMENT IAW SRM 51-10-02-0G-0 PARAG. 9;[04] RECIVED NEW FRAM ASSY; LOT.1485708-1; LOCATED AND DRILLED IAW SRM 51-40-05-0G-0.FRAME IS GOING TO BE INSTALLED ON TTG8Q00M091V;[05] UPDATED MEASUREMENT TABLE;[06] VERIFIED CORRECTIVE ACTIONS 3; 4 AND MEASUREMENT TABLE

Part: SCUFF PLATE — CRACKED (ZN 100 FUS LOWER) · airframe 38,362 hrs · 23,630 cycles

FWD CARGO BAY AFT CORNER SCUFF PLATE CRACKED<[01] WELDED CRACK ON FCB; AFT CORNER SCUFF PLATE USING ER4043 ALUMINUM FILLER ROD LOT NUMBER 1131216 PER SRM 53-30-15-2R-1 PARAGRAPH 4.B.(2) AND (4). REPAIR AREA STILL REQUIRES A DYE PENETRANT INSPECTION.<BR>EQUIPMENT USED: WELDING MACHINE E10583; CALIBRATION DUE DATE 01/2024;[02] VERIFIED CORRECTIVE ACTION 1;[03] PT INSPECTED AREA IAW SOPM 20-20-02. <BR>NO CRACKS NOTED. <BR>EQUIP USED: <BR>-RADIOMETER ID: ATS2561-1; 2; 3 CAL DUE: 08/23;[04] SANDED REPAIR WELD AREA PER SRM 53-30-15-2R-1 PARAGRAPH 4.B.(5);[05] VERIFIED CORRECTIVE ACTION 4;[06] APPLIED CHEMICAL CONVERSION COATING; PRIMER AND PARTING AGENT. IAW SOPM 20-43-03; SOPM 20-41-02; SOPM 20-50-19;[07] INSTALLATION WILL BE COMPLETED ON TTG8Q002LUPG;[08] VERIFIED CORRECTIVE ACTIONS 6; 7 AND MEASUREMENT TABLE

Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 38,005 hrs · 23,399 cycles

EMERGENCY AISLE LIGHTS AT ROW 11CB AND 9ABC INOP.<[01] REMOVED AND REPLACED BATTERY PACK AT LH STATION 727C IAW AMM 33-51-06. OP CHECK GOOD.

Part: FUSE — INOPERATIVE (ZN 200 FUS TOP) · airframe 38,005 hrs · 23,399 cycles

EMERGENCY AISLE LIGHT AT ROW 7ABC INOP.<[01] REMOVED AND REPLACED EMERGENCY LIGHTS POWER SUPPLY FUSE REF: AMM 33-51-06. OPS CHECK GOOD.

Part: LIGHT — INOPERATIVE (ZN 200 FUS TOP) · airframe 37,825 hrs · 23,285 cycles

AFT R/H SERVICE DOOR EMER EXTERIOR LIGHT INOP<[01] REMOVED AND REPLACED AFT SERVICE DOOR EXTERIOR EMER LIGHT BULB PER AMM 33-51-04. OPS TEST GOOD.

Part: SLIDE — DETACHED (FWD SERVICE DOOR) · airframe 36,976 hrs · 22,711 cycles

FORWARD GALLEY SERVICE DOOR PARTIALLY OPENED WITH GIRT BAR ARMED<[01] INSPECTED DOOR SLIDE FOUND TO BE PULLED FROM COVER WAS NOT DEPLOYED REPACKED SLIDE REF AMM25-66-01 AC OK FOR SERVICE

Part: SKIN — CRACKED (ZN 600 RIGHT WIN) · airframe 36,467 hrs · 22,369 cycles

FOUND .5 CRACK AT LOCATION IDENTIFIED AS FIRST DENT LOCATED AT WS 271; AT APPROXIMATELY 21 FROM TRAILING EDGE. PERFORMED HFEC AS REQUIRED PER NDT MANUAL PART 6 51-00-00 PROC 23. AT BOTH DENTS IDENTIFIED IN DISCREPANCY. FOUND .5 CRACK AT LOCATION AT IDENTIFIED AS FIRST DENT LOCATED AT WS 271 AT APPROXIMATELY 21 FROM FLAP TRAILING EDGE. LOCATION IDENTIFIED AS SECOND DENT HAS NO CRACK INDICATIONS. / [01] COMPLIED WITH EA22-157-03293<BR>REF. TTG8Q00FXFRE

Part: LIGHT — INOPERATIVE (CABIN) · airframe 36,151 hrs · 22,147 cycles

FWD LEFT STOWBIN BULLNOSE EMEERGENCY EXIT LIGHTS ARE INOP. FOUND FUSE BLOWN ON EMERGENCY BATTERY POWER SUPPLY FOR FWD BULLNOSE LIGHTS; ALSO FOUND FWD BULLNOSE LIGHT ASSEMBLY BAD. REPLACED LIGHT ASSEMBLY IAW AMM 33-51-03-960-802 AND FUSE IAW AMM 33-51-06-960-804; EMERGENCY LIGHT CHECK GOOD. VERIFIED STEP 1<BR>C/W

Part: SLIDING SLEEVE — TORN (RH HOR STAB) · airframe 35,818 hrs · 21,909 cycles

RT HORZ UPPER FWD SLIDING SEAL TORN / [01] R&R R/H UPPER SLIDER PER AMM 53-31-31

Part: SLIDE — OUT OF ADJUST (R1 DOOR) · airframe 35,614 hrs · 21,769 cycles

UNABLE TO READ GAUGE ON FWD SERVICE DOOR SLIDE / [01] READJUSTED FWD SERVICE DOOR SLIDE IN REFERENCE TO AMM 25-66-01. GAUGE IS NOW VISIBLE

Part: FLASHLIGHT — BROKEN (AFT CABIN) · airframe 35,494 hrs · 21,688 cycles

AFT INBOARD FLASHLIGHT BROKEN / [01] R&R AFT INBOARD FLASHLIGHT ASSY REF CMM 25-60-13

Part: BATTERY PACK — INOPERATIVE (AFT CABIN) · airframe 35,436 hrs · 21,643 cycles

EMERGENCY LIGHTS L733;L1223 AFT RIGHT SLIDE;AFT ENTRY INOP / [01] REPLACED M1672 POWER SUPPLY BATTERY PACK PER AMM 33-51-06

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 32,936 hrs · 20,041 cycles

EMERGENCY LIGHTS ASSOCIATED WITH BATTERY PACK M1675 ARE INOP ; / [01] REMOVED; REPLACED; AND PERFORMED GOOD INSTALLATION TEST OF EMERGENCY LIGHT BATTERY PACK AT M1675 PER AMM 33-51-06-960-805.; [02] VERIFIED CORRECTIVE ACTION 1 PER AMM 33-51-06-960-805.

Part: GUSSET — CRACKED (BS 500D S19R) · airframe 32,936 hrs · 20,041 cycles

FCB R/H GUSSET CRACKED BS 500D STR 19R WL 188 ; / [01] REMOVED GUSSET BS 500D; STR 19R; WL 188 IAW SRM 51-40-02.; [02] LOCATED; DRILLED AND DEBURRED NEW FCB R/H GUSSET BS 500D; STR 19R; WL 188 IAW SRM 51-40-05-0G-0 AND DWG 143A7902; [03] VERIFIED; [04] LOCATED; DRILLED AND DEBURRED NEW FCB R/H GUSSET BS 500D; STR 19R; WL 188 IAW SRM 51-40-05-0G-0 AND DWG 143A7902; OK TO INSTALL; [05] VERIFIED; [06] VERIFIED LOCATE AND DRILL UP OF NEW GUSSET PER SRM 51-40-05 AND DWG 143A7902; OK TO INSTALL.; [07] INSTALLED NEW FCB R/H GUSSET BS 500D; STR 19R; WL 188 IAW SRM 51-40-02-0G-0 AND DWG 143A7902; [08] VERIFIED; [09] RII INSPECTED INSTALLATION OF NEW GUSSET PER SRM 51-40-02 AND DWG 143A7902.; [10] INSPECTION COMPLETE

Part: GUSSET — CRACKED (BS 500D S19D) · airframe 32,936 hrs · 20,041 cycles

FCB GUSSET CRACKED BS 500D STR 19L WL 188 ; / [01] REMOVED GUSSET BS 500D STR-19L WL 188. IAW. SRM 51-40-02.; [02] LOCATED AND DRILLED FCB GUSSET AT B.S 500D STR 19L PER SRM51-40-05-0G-0;DWG 143A7902. O.K TO INSTALL.; [03] OKAY TO INSTALL FCB GUSSET; [04] INSTALLED FCB GUSSET AT B.S 500D STR 19L PER SRM51-40-02-0G-0;DWG 143A7902.; [05] VERIFIED INSTALLATION OF FCB GUSSET AT BS 500D STR 19L PER SRM 51-40-02-0G-0;DWG 143A7902.; [06] ADDED N/A TO BLOCK 4 OF MEASUREMENT'S FIELD AND CHECKED BLOCK 6 AS PRIMARY STRUCTURE.; [07] VERFIED; [08] INSPECTION OF INSTALLATION HAS BEEN ACCOMPLISHED. <BR><BR>NO FURTHER ACTIONS REQUIRED.; [09] FCB GUSSET AT BS500D; S-19L; WL188 HAS BEEN REPLACED.<BR><BR>NO FURTHER ACTIONS REQUIRED.

Part: BULKHEAD WEB — CRACKED (BS 663) · airframe 32,936 hrs · 20,041 cycles

RIGHT HAND B.S. 663 VAPOR BARRIER HAS A CRACKED FASTENER HOLE AT O/B EDGE ; / IDENTIFIED B.S. 663 RIGHT HAND VAPOR BARRIER MATERIAL IAW SRM 57-10-10-0I-2 TABLE 2 FIGURE 2 ITEM 4. DAMAGED FASTENER HOLE EXCEEDS ALLOWABLE DAMAGE LIMITS IAW SRM 57-10-10-1A-2 PARAGRAPH 4.D(1). DAMAGE IS REPAIRABLE PER SRM 51-70-04-2R-10 DIRECTED BY SRM 57-10-10-2R-2. <BR><BR>REMOVED .75' X .75' AREA OF DAMAGED SKIN AT DISCREPANT LOCATION AND PREPARED AREA FOR REPAIR PLIES. FABRICATED REPAIR PLIES FROM BMS9-3 STYLE 1581 LOT# 1458851-1. OKAY TO INSTALL REPAIR PLIES IAW SRM 51-70-04-2R-10 PARAGRAPH 4. A-D.; [02] VALIDATED REPAIR IAW SRM 51-70-04-2R-10; [03] VERIFIED CORRECTIVE ACTION 1 PER SRM 57-10-10-0I-2; SRM 57-10-10-1A-2; AND SRM 51-70-04-2R-10 <BR> <BR>VALIDATED REPAIR IAW SRM 51-70-04-2R-10 <BR>OK TO INSTALL REPAIR PLIES; [04] INSTALLED REPAIR PLIES USING RESIN BMS8-301 CL2 LOT#1464454-1; VACUUM BAGGED REPAIR; LEAK CHECKED GOOD USING VACUUM GAUGE ID: ATS2107 SN: UNKNOWN; AND SET TO CURE IAW SRM 51-70-04-2R-10 PARAGRAPH 4.D-E. VERIFIED CORRECTIVE ACTION 4 PER SRM 51-70-04-2R-10;CURED REPAIR PLIES USING THERMOMETER ID: ATS2208 SN: 43300740WS AND VACUUM GAUGE ID: ATS2107 SN: UNKNOWN; REMOVED VACUUM BAG; AND LIGHTLY SANDED IAW SRM 51-70-04-2R-10 PARAGRAPH 4.F VERIFIED CORRECTIVE ACTION 6 PER SRM 51-70-04-2R-10 UT INSPECTED POST CURE IAW 737 NDTM PART 4 51-00-02; NO DISBONDS NOTED. EQUIP ID#: ATS2341 S/N: 190848104 REFINISHED REPAIR AREA IAW SRM 51-70-04-2R-10 PARA 4H.

Part: BULKHEAD WEB — DAMAGED (BS 663) · airframe 32,936 hrs · 20,041 cycles

RIGHT HAND B.S. 663 VAPOR BARRIER HAS MISALIGNED FASTENER HOLES AT I/B LOWER EDGE ; / [01] IDENTIFIED B.S. 663 RIGHT HAND VAPOR BARRIER MATERIAL IAW SRM 57-10-10-0I-2 TABLE 2 FIGURE 2 ITEM 4. DAMAGED FASTENER HOLES EXCEED ALLOWABLE DAMAGE LIMITS IAW SRM 57-10-10-1A-2 PARAGRAPH 4.D(1). DAMAGE IS REPAIRABLE PER SRM 51-70-04-2R-10 DIRECTED BY SRM 57-10-10-2R-2. <BR><BR>REMOVED DAMAGED SKIN WITHIN A 3' X 5' AREA TO INCLUDE MULTIPLE FASTENER HOLES; AND PREPARED AREA FOR PLIES AT DISCREPANT LOCATION. FABRICATED REPAIR PLIES FROM BMS9-3 STYLE 1581 LOT# 1458851-1. OKAY TO INSTALL REPAIR PLIES IAW SRM 51-70-04-2R-10 PARAGRAPH 4. A-D.; [02] VALIDATED REPAIR IAW SRM 51-70-04-2R-10; 04] INSTALLED REPAIR PLIES USING RESIN BMS8-301 CL2 LOT#1464454-1; VACUUM BAGGED REPAIR; LEAK CHECKED GOOD USING VACUUM GAUGE ID: ATS2438 SN: UNKNOWN; AND SET TO CURE IAW SRM 51-70-04-2R-10 PARAGRAPH 4.D-E.; [05] VERIFIED CORRECTIVE ACTION 4 PER SRM 51-70-04-2R-10; [06] CURED REPAIR PLIES USING THERMOMETER ID: ATS2208 SN: 43300740WS AND VACUUM GAUGE ID: ATS2438 SN: UNKNOWN; REMOVED VACUUM BAG; AND LIGHTLY SANDED IAW SRM 51-70-04-2R-10 PARAGRAPH 4.F;; [08] UT INSPECTED POST CURE IAW 737 NDTM PART 4 51-00-02; NO DISBONDS NOTED. EQUIP ID#: ATS2341 S/N: 190848104; [09] REFINISHED REPAIR AREA IAW SRM 51-70-04-2R-10 PARA 4H.

Part: ATTACH ANGLE — CRACKED (BS 663 RBL 8) · airframe 32,936 hrs · 20,041 cycles

R/H VAPOR BARRIER UPPER ATTACH ANGLE IS CRACKED; BS 663 RBL 8 W/L 164. ; / [01] VERIFIED APPLICABILITY IAW SRM 57-10-10-2R-5; [02] REMOVED 8 EA FASTENERS COMMON TO FUEL TANK AT BS 663 BETWEEN RBL 7 TO 20; WL 164 AND CUT OUT DAMAGE ANGLE IAW SRM 57-10-10-2R-5; [03] SRM 57-10-10-2R-5 STEP 4; A AND B.; [04] ET INSPECTED HOLES IAW 737 NDTM PART 6 51-00-00 PROCEDURE 16; NO CRACKS NOTED.<BR>CAL ID IS000450 N500D; [05] VERIFIED REMOVED 8 EA FASTENERS COMMON TO FUEL TANK AT BS 663 BETWEEN RBL 7 TO 20; WL 164 AND CUT OUT DAMAGE ANGLE IAW SRM 57-10-10-2R-5 STEPS 4 A AND B; [08] LOCATED AND DRILLED: REPLACEMENT ANGLE; CUSTOMER RO NO. ATSHFAB-101-354 JOB NUMBER 5405554; AND SPLICE ANGLE CUSTOMER RO NO ATSHFAB-101-355 JOB NUMBER 540681 IAW SRM 51-40-05 AND SRM 57-10-10-2R-5; FIG 202 SHEET 4.; [09] VERIFIED LOCATED AND DRILLED: REPLACEMENT ANGLE; CUSTOMER RO NO. ATSHFAB-101-354 JOB NUMBER 5405554; AND SPLICE ANGLE CUSTOMER RO NO ATSHFAB-101-355 JOB NUMBER 540681 IAW SRM 51-40-05 AND SRM 57-10-10-2R-5; FIG 202 SHEET 4; [10] APPLIED CHEMICAL CONVERSION AND PRIME AT REPAIR PARTS AND REPAIR AREA IAW SRM 51-21-01 AND SOPM 20-41-02; [16] INSTALLED REPAIR PARTS AND 8 EA FASTENERS COMMON TO FUEL TANK AT BS 663 WL 164;RBL 7 TO 20 IAW SRM 57-10-10-2R-5 REPAIR 5 FIG.202 SHEET 4 AND SRM 51-40-02; [17] VERIFIED INSTALL OF REPAIR PART AND FASTENERS PER SRM.(STEP 16) FABRICATED AS REQUIRED PER SRM 57-10-10-2R-5 PRIOR TO LOCATING AND DRILLING.

Part: BRACKET — BROKEN (RH WING TE PANEL) · airframe 32,936 hrs · 20,041 cycles

R/W T/E PANEL 651FB FWD SIDE; O/B END TIE ROD BRACKET IS BROKEN ; / [01] REMOVED P/N 115A2353-2 CLIP ASSY IAW SRM 51-40-02; [02] RECEIVED NEW CLIP P O # 834153; [03] VERIFIED RECEIPT OF 115A2353-2 CLIP ASSY AND VERIFIED IT MEETS THE DWG REQUIREMENTS FOR FABRICATION AND FINISH.; [04] LOCATED HOLES IN NEW CLIP PER PER DRAWING # 115A2353 SHT 1 REV B AND OK TO PRIME; [05] VERIFIED LOCATE AND DRILL PER DRAWING # 115A2353 SHT 1 REV B. OK TO PRIME; [06] APPLIED PRIMER AND ENAMEL FINISH COATS TO CLIP PER DRAWING # 115A2353 SHT 4 OF 20 REV E; [07] VERIFIED PRIMER AND PAINT PER DRAWING # 115A2353 SHT 4 OF 20 REV E; [08] INSTALLED BUSHINGS PER DRAWING 115A2353 SHT 1 REV B AND FLAG NOTE 2. INSTALLED NEW CLIP ONTO 651FB FWD SIDE; O/B END IAW SRM 51-40-02; [09] VERIFIED CORRECTIVE ACTION 8 PER DRAWING 115A2353 SHT 1 REV B AND FLAG NOTE 2 AND SRM 51-40-02

Part: SUPPORT — CORRODED (FWD CARGO) · airframe 32,936 hrs · 20,041 cycles

CORROSION FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT BS 500A TO BS 500D RBL 23 WL 156 ; / REMOVED FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT BS 500A TO BS 500D RBL 23 WL 156 IAW SRM 51-40-02; REMOVED FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT BS 500A TO BS 500D RBL 23 WL 156 IAW SRM 51-40-02; REMOVED CORROSION FROM FCB LH FLOOR TO SIDEWALL SUPPORT AT MULTIPLE SPOTS; DEEPEST SPOT AT BS 462 IN AN AREA OF L=1' X W=1' X D=.038' UPON FURTHER INVESTIGATION FOUND R/H FLOOR TO SDIEWALL SUPPORT BS 500A - 500D RBL 23 WL 156 TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. CORROSION WAS REMOVED IN A 54' L X 1' W X .005' D FROM ORIGINAL THICKNESS OF .040 VERIFIED UPON FURTHER INVESTIGATION FOUND R/H FLOOR TO SDIEWALL SUPPORT BS 500A - 500D RBL 23 WL 156 TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. CORROSION WAS REMOVED IN A 54' L X 1' W X .005' D FROM ORIGINAL THICKNESS OF .040'. FABRICATED NEW FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT BS500A TO BS BS500D RBL23 WL 256 ; IAW DWG 143A7501 SH 127 AND SRM 51-40-02 ; ITEM BAC1496-444#7075T62; LOT 1457271-1; APPLIED CHEMICAL CONVERSION COAT PER AMM 51-21-41-370-801 AND PRIMER PER AMM 51-21-72-370-804;AND APPLIED CHEMICAL CONVERSION COAT PER AMM 51-21-41-370-801 AND PRIMER PER AMM 51-21-72-370-804; OK TO INSTALL FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT BS 500A TO BS 500D ; RBL 23 ; WL 156 INSTALLED FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT BS 500A TO BS 500 RBL 23; WL 156 IAW SRM 51-40-02-0G-0; DWG 143A7500 AND DWG 143A7505

Part: SUPPORT — CORRODED (FWD CARGO) · airframe 32,936 hrs · 20,041 cycles

CORROSION FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT BS 480 TO BS 500D LBL 25 WL 156 ; / REMOVED FCB L/H FLOOR TO SIDE WALL SUPPORT IAW SRM 51-40-02REMOVED CORROSION FROM FCB LH FLOOR TO SIDEWALL SUPPORT AT MULTIPLE SPOTS; DEEPEST SPOT AT BS 462 IN AN AREA OF L=1' X W=1' X D=.038' REMOVED CORROSION ON FWD CARGO BAY L/H FLOOR TO SIDEWALL SUPPORT IN A 114'L X 1' W X .005' AREA FROM ORIGINAL THICKNESS OF .040. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. PINPOINT MICROMETER ID ATS1672 SN 65092939 FABRICATED FCB L/H FLOOR TO SIDEWALL SUPPORT BS 396 TO BS 500D FROM MATERIAL BAC1496-<BR>444#7075T62 LOT : 1466234-1.<BR>FABRICATED SPLICE B/N BS 480 TO BS 500 FROM MATERIAL BAC1496-444#7075T62 LOT : 1466234-1.<BR>APPLIED CHEMICAL CONVERSION COATING PER SRM 53-00-53-2R-6APLLIED PRIMER ON FCB L/H FLOOR TO SIDEWALL SUPPORT BS 396 TO 500D AND SPLICE REPAIR IAW. SRM 51-20-01-0G-0 . OK TO INSTALL SPLICE REPAIR BS 480 TO BS 500.;] INSTALLED SPLICE REPAIR ON FCB L/H FLOOR TO SIDEWALL SUPPORT BS 480 TO 500 IAW. SRM 53-00-53-2R-6 INSTALLED FCB L/H FLOOR TO SIDEWALL SUPPORT BS 396 TO 500D IAW. DWG:143A7500

Part: SHIELD — CORRODED (BS 435 RBL 24) · airframe 32,936 hrs · 20,041 cycles

CORROSION FWD CARGO BAY FWD SHIELD BS 435 RBL 24 WL 156 ; / [01] REMOVED FWD CARGO BAY FWD SHIELD BS 435 RBL 24 WL 156 IAW SRM 51-40-02; [02] REMOVED FWD CARGO BAY FWD SHIELD BS 435 RBL 24 WL 156 IAW SRM 51-40-02; [03] NOT FOUNDED LIMITS ON SRM REPLACE PART FOR REPAIR IAW SRM 51-10-02; [04] LOCATED AND DRILLED NEW PART P/N:143A8126 IAW SRM 51-40-02 AND BOEING DWG 143A0080 REV:-; [05] VERIFIED PART LOCATED FASTENERS HOLES AND DRILLED PER SRM 51-40-02; AND BOEING DWG 143A0080 REV-; [06] OK TO INSTALL FWD CARGO BAY FWD SHIELD BS 435 RBL 24 WL 156; [07] OK TO INSTALL FWD CARGO BAY FWD SHIELD BS 435 RBL 24 WL 156; [08] OK TO INSTALL GIVEN; [09] INSTALLED FWD CARGO BAY FWD SHIELD BS 435 RBL 24 WL 156 IAW SRM 51-40-02 AND DWG 143A8126 AND DWG 143A0080; [10] INSTALLED FWD CARGO BAY FWD SHIELD BS 435 RBL 24 WL 156 IAW SRM 51-40-02 AND DWG 143A8126 AND DWG 143A0080; [11] VERIFIED INSTALLED FWD CARGO BAY FWD SHIELD BS 435 RBL 24 WL 156 IAW SRM 51-40-02-0G-0 AND DWG 143A8126 AND DWG 143A0080; [12] UPDATED MEASUREMENTS

Part: WEB — CORRODED (FWD CARGO) · airframe 32,936 hrs · 20,041 cycles

CORROSION FWD CARGO BAY THRESHOLD SUBWEB BS 448 TO BS 480 RBL 28 WL 156 ; / [01] REMOVED FCB SUB THRESHOLD WEB IAW SRM 51-40-02; [02] CORROSION ON FWD CARGO BAY THRESHOLD SUBWEB AT BS448 TO BS480 RBL28 WL156 MEASURES 32'L X 0.4'W X 0.008'D. ORIGINAL MATERIAL THICKNESS IS 0.045' DAMAGE FOUND TO BE OUT OF ALLOWABLE DAMAGE LIMITS IAW SRM 53-30-15-1A-1; PARA 4H (1)(B)1) FIGURE 103; DETAIL D. REPAIR BY REPLACEMENT IAW SRM 51-10-02-0G-0 PARA 9A (1-2); [03] LOCATED; DRILLED AND COUNTERSINK NEW WEB P/N 654A0003-58 PO#1465408 IAW SRM 51-40-05; 51-40-08 AND DWG 143A8330 REV.-A; [04] VERIFIED CORRECTIVE ACTION ENTRIES 2 AND 3.; [05] OK TO INSTALL; [06] OK TO INSTALL; [07] CERTIFY; [08] OKAY TO INSTALL; [09] INSTALLED FWD CARGO BAY ENTRY THRESHOLD SUB WEB STA 440 TO 492.4 RBL 28 WL156; IAW DWG 143A8330 SH 42 REV A; AND SRM 51-40-02; [10] PART UPDATE; [11] VERIFIED CORRECTIVE ACTION ENTRY 9.; [12] VERIFIED CARD COMPLETE; [13] UPDATED MEASUREMENTS

Part: SUPPORT ANGLE — CORRODED (BS 500D R-LBL 23) · airframe 32,936 hrs · 20,041 cycles

CORROSION FWD CARGO BAY AFT CENTER PANEL LOWER SUPPORT ANGLE BS 500D LBL 23 TO RBL 23 WL 156 ; / [01] REMOVED FWD CARGO BAY AFT CENTER PANEL LOWER SUPPORT ANGLE BS 500D LBL 230 TO RBL 230 WL 156 IAW SRM 51-40-02; [02] REMOVED FWD CARGO BAY AFT CENTER PANEL LOWER SUPPORT ANGLE BS 500D LBL 230 TO RBL 230 WL 156 IAW SRM 51-40-02; [03] NO ALLOWABLE DAMAGE LIMITS FOUND IN SRM FOR FCB AFT BULKHEAD CENTER SUPPORT PART TO BE REPAIRED BY REPLACEMENT PER SRM 51-10-02-0G-0; [04] NO ALLOWABLE DAMAGE LIMITS FOUND IN SRM FOR FCB AFT BULKHEAD CENTER SUPPORT PART TO BE REPAIRED BY REPLACEMENT PER SRM 51-10-02-0G-0; [05] VERIFIED CORRECTIVE ACTION ENTRY 3.; [06] RECEIVED REPLACEMENT FCB AFT CENTER BULKHEAD SUPPORT; LOCATED AND DRILLED PER SRM 51-40-05-0G-0; SRM 51-40-08-0G-0 AND DWG 143A9485; [07] RECEIVED REPLACEMENT FCB AFT CENTER BULKHEAD SUPPORT; LOCATED AND DRILLED PER SRM 51-40-05-0G-0; SRM 51-40-08-0G-0 AND DWG 143A9485; [08] VERIFIED CORRECTIVE ACTION ENTRY 6.; [09] OK TO INSTALL; [10] INSTALLED FWD CARGO BAY AFT CENTER PANEL LOWER SUPPORT ANGLE BS 500D ;LBL 23 TO RBL 23 ; WL 156 IAW SRM 51-40-02-0G-0; DWG 143A9481( VIEW 1A7 AND 1A5 ) AND DWG 143A 7902; [11] VERIFIED; [12] UPDATED MEASUREMENT TABLE; [13] VERIFIED; [14] VERIFIED ACTION 9; OK TO INSTALL (ACCOMPLISHED PRIOR TO ACTION 10); [15] VERIFIED ACTION 10; [16] PARTS UPDATE; [17] VERIFIED JOB COMPLETE

Part: SUPPORT — CORRODED (BS 947) · airframe 32,936 hrs · 20,041 cycles

CORROSION ON AFT CARGO BAY CENTER PANEL LOWER SUPPORT AT B.S. 947; WL 156; LBL 23 TO RBL 23 ; / [01] REMOVED AFT CARGO BAY AFT BKHD LOWER SUPPORT BS 947 WL156 LBL 23 TO RBL 23 PER SRM 51-40-02.; [02] REMOVED AFT CARGO BAY AFT BKHD LOWER SUPPORT BS 947 WL156 LBL 23 TO RBL 23 PER SRM 51-40-02; [03] NO ALLOWABLE LIMITS FOUND IN SRM. REPAIR PART BY REPLACEMENT IAW 51-10-02-0G-0; PARAGRAPH 9; C; [04] OK TO INSTALL; [05] OK TO INSTALL; [06] INSTALLED ACB BULKHEAD LOWER SUPPORT BS 947 WL156 LBL23 TO RBL 23 IAW DWG 149A8117 REV-; SRM 51-40-02-0G-0; [07] INSTALLED ACB BULKHEAD LOWER SUPPORT BS 947 WL156 LBL23 TO RBL 23 IAW DWG 149A8117 REV-; DWG 149A8118 REV:A; AND SRM 51-40-02-0G-0; [08] VERIFIED; [09] VERIFIED ACTION 7; [10] UPDATED MESUREMENT TABLE; [11] VERIFIED

Part: SHIELD — CORRODED (`BS 780-807) · airframe 32,936 hrs · 20,041 cycles

CORROSION ON AFT CARGO BAY FWD SHIELD AT B.S. 780 TO 807; LBL 23; WL 156 ; / [01] REMOVED ACB FWD SHIELD BS 780-807 RBL23 PER SRM 51-40-02-0G-0; [02] NO ALLOWABLE DAMAGE LIMITS FOUND IN SRM FOR ACB FWD SHIELD (BS787-807 RBL 23); PART TO BE REPAIRED BY REPLACEMENT PER SRM 51-10-02; [03] PART REMOVAL AND OUT OF LIMITS; [04] VERIFIED NO ALLOWABLE DAMAGE LIMITS FOUND IN SRM FOR ACB FWD SHIELD (BS787-807 RBL 23); PART TO BE REPAIRED BY REPLACEMENT PER SRM 51-10-02; [05] RECEIVED NEW MATERIAL;PART NUMBER 7531132 PO. NUMBER 821453. LOCATED AND DRILLED NEW SHIELD AT BS 780 TO 807; LBL 230 WL 156 IAW SRM 51-40-05; [06] VERIFIED CORRECTIVE ACTION ENTRY 5.; [07] RECEIVED NEW MATERIAL;PART NUMBER 7531132 PO. NUMBER 821453. LOCATED AND DRILLED NEW SHIELD AT BS 780 TO 807; LBL 230 WL 156 IAW SRM 51-40-05; [08] REQUEST OK TO INSTALL ACB FWD SHIELD BS 780-807 LBL 230 WL 156; [09] REQUEST OK TO INSTALL ACB FWD SHIELD BS 780-807 LBL 230 WL 156; [10] OK TO INSTALL GIVEN; [11] INSTALLED ACB FWD SHIELD BS 780-807 LBL 23 WL 156 PER SRM 51-40-02 AND DWG #146A0081.; [12] INSTALLED ACB FWD SHIELD BS 780-807 LBL 23 WL 156 PER SRM 51-40-02 AND DWG #146A0081; [13] VERIFIED CORRECTIVE ACTION ENTRY 11.; [14] VERIFIED CARD COMPLETE; [15] UPDATED MEASUREMENTS

Part: SHIELD — CORRODED (BS 493-500A) · airframe 32,936 hrs · 20,041 cycles

CORROSION FWD CARGO BAY AFT SHIELD BS 493 TO BS 500A RBL 25 WL 156 ; / [01] REMOVED FWD CARGO BAY AFT SHIELD BS 493 TO BS 500A RBL 25 WL 156 IAW SRM 51-40-02; [02] REMOVED FWD CARGO BAY AFT SHIELD BS 493 TO BS 500A RBL 25 WL 156 IAW SRM 51-40-02; [03] LOCATED AND DRILLED FWD CARGO BAY AFT SHIELD BS 493 TO BS 500A RBL 25 WL 156 USING ATSHFAB-103-303 FORMED SHIELD BLANK FCB BS 492-500 LOT:1385046 IAW SRM 51-40-05 AND BOEING DWG 143A8126 ID:0018 AND 143A0080 ID:0006.; [04] VERIFIED RECIEVED PART LOCATE AND DRILL; [05] FCB AFT SHIELD FOUND TO BE OUT OF LIMITS DUE TO NO ALLOWABLE DAMAGE LIMITS FOUND IN SRM. PART TO BE REPAIRED BY REPLACMENT PER SRM 51-10-02 ITEM 9; [06] OKAY TO INSTALL; [07] INSTALLED FWD CARGO BAY AFT SHIELD BS 493 TO BS 500A RBL 25 WL 156 IAW SRM 51-40-02 AND DWG 143A8126 ID:0018 AND 143A0080 ID:0041; [08] INSTALLED FWD CARGO BAY AFT SHIELD BS 493 TO BS 500A RBL 25 WL 156 IAW SRM 51-40-02 AND DWG 143A8126 ID:0018 AND 143A0080 ID:0041; [09] FCB AFT SHIELD FOUND TO BE OUT OF LIMITS DUE TO NO ALLOWABLE DAMAGE LIMITS FOUND IN SRM. PART TO BE REPAIRED BY REPLACMENT IAW SRM 51-10-02 ITEM 9; [10] VERIFIED CORRECTIVE ACTION ENTRY 5.; [11] VERIFIED CORRECTIVE ACTION ENTRY 7.; [12] VERIFIED CARD COMPLETE

Part: SUPPORT — CORRODED (BS 727-787) · airframe 32,936 hrs · 20,041 cycles

CORROSION ON AFT CARGO COMPARTMENT FLOOR TO SIDEWALL SUPPORT FROM B.S. 727 TO 787; RBL 23; W.L. 156 ; / [01] REMOVED ACB R/H FLOOR TO SIDEWALL SUPPORT BS 727-787 PER SRM 51-40-02-0G-0; [02] REMOVED CORROSION FROM ACB R/H FLOOR TO SIDEWALL SUPPORT AT BS 787-3' MEASURED 3' X 1.5' DEPTH OF 0.025'. ORIGINAL THINKNESS OF 0.040' FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-1<BR><BR>CALIBRATED TOOL ID:<BR>DIAL DEPTH GAUGE <BR>ATS2472<BR>S/N:UNKNOWN<BR>06/2021<BR>06/2022; [03] VERIFIED PART REMOVAL AND OUT OF LIMITS CORROSION REMOVAL; [04] VERIFIED REMOVED CORROSION FROM ACB R/H FLOOR TO SIDEWALL SUPPORT AT BS 787-3' MEASURED 3' X 1.5' DEPTH OF 0.025'. ORIGINAL THINKNESS OF 0.040' FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-1<BR><BR>CALIBRATED TOOL ID:<BR>DIAL DEPTH GAUGE<BR>ATS2472<BR>S/N:UNKNOWN<BR>06/2021<BR>06/2022<BR>3. JERAD HEDAL (CERTIFIER); 12-AUG-2021 05:52 UTC; [05] RECEIVED NEW FLOOR TO SIDEWALL SUPPORT<BR>ITEM 146A7502-51<BR>PO# 830535/1; [06] LOCATED AND DRILLED NEW FLOOR TO SIDEWALL SUPPORT IAW SRM 51-40-05-0G-0 AND DWG 146A7502 REV:-; [07] OKAY TO INSTALL; [08] INSTALLED ACB FLOOR TO SIDEWALL SUPPORT FROM BS 727 TO BS 767 RBL 23 WL 156 IAW SRM 51-40-02-0G-0 AND DWG 146A7500 REV:-; [09] VERIFIED CORRECTIVE ACTION ENTRY 8.; [10] VERIFIED CARD COMPLETE; [11] UPDATED MEASUREMENTS

Part: SUPPORT — CORRODED (BS 727-847) · airframe 32,936 hrs · 20,041 cycles

CORROSION ON AFT CARGO COMPARTMENT FLOOR TO SIDEWALL SUPPORT FROM B.S. 727 TO 847; LBL 23; W.L. 156 ; / [01] REMOVED ACB FLOOR TO SIDEWALL SUPPORT L/H FROM BS 727-847 PER SRM 51-40-02.; [02] REMOVED ACB FLOOR TO SIDEWALL SUPPORT L/H FROM BS 727-847 PER SRM 51-40-02.; [03] FABRICATED ACB FLOOR TO SIDEWALL SUPPORT BS 727- 847; LBL 23 FROM MATERIAL BAC1496-377 #7075T62 LOT#1464391-1; IAW SRM 51-40-05; DWG#146A7500.<BR>FABRICATED SPLICE ANGLE B/N BS 727E-747 FROM MATERIAL BAC1496-377 #7075T62 LOT#1464391-1 PER SRM 53-00-53-2R-5.<BR>APPLIED CHEMICAL CONVERSION COATING PER SRM 51-20-01. OK TO PRIME; [04] REMOVED CORROSION FROM ACB FLOOR TO SIDEWALL SUPPORT AT BS 767; LBL 23; MATERIAL LOSS MORE THAN 20% FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.; [05] TOOLING USED; DIAL DEPTH GAUGE ID:ATS2473; S/N:UNKNOWN; [06] VERIFIED REMOVED ACB FLOOR TO SIDEWALL SUPPORT L/H FROM BS 727-847 PER SRM 51-40-02 DUE TO DAMAGE BEING OUT OF LIMITS.; [07] VERIFIED FABRICATED ACB FLOOR TO SIDEWALL SUPPORT BS 727- 847; LBL 23 FROM MATERIAL BAC1496-377 #7075T62 LOT#1464391-1; IAW SRM 51-40-05; DWG#146A7500. <BR>FABRICATED SPLICE ANGLE B/N BS 727E-747 FROM MATERIAL BAC1496-377 #7075T62 LOT#1464391-1 PER SRM 53-00-53-2R-5. <BR>APPLIED CHEMICAL CONVERSION COATING PER SRM 51-20-01. OK TO PRIME; [08] APPLIED PRIMER IAW AMM 51-21-72-370-804; [09] VERIFIED APPLIED PRIMER IAW AMM 51-21-72-370-804; [10] OK TO INSTALL REPAIR PARTS

Part: SUPPORT — CRACKED (BS 540) · airframe 32,936 hrs · 20,041 cycles

CRACKED FLOOR SUPPORT AT B.S. 540 B.L. 0 - L.B.L. 24.5; W.L. 208.1. ; / [01] NO LIMITS FOR CRACKS TO P/N 143A5240-33. REPAIR BY REPLACEMENT. IAW SRM CH 51-10-02 REMOVED DAMAGED SUPPORT IAW SRM CH 51-40-02 LOCATED AND DRILLED NEW SUPPORT IAW SRM CH 51-40-05. OK TO INSTALL.; [02] VERIFIED NO LIMITS FOR CRACKS TO P/N 143A5240-33. REPAIR BY REPLACEMENT. IAW SRM CH 51-10-02 REMOVED DAMAGED SUPPORT IAW SRM CH 51-40-02 LOCATED AND DRILLED NEW SUPPORT IAW SRM CH 51-40-05. OK TO INSTALL.; [03] INSTALLED SUPPORT AT BS 540 BL-0 THROUGH LBL 24.5 WL 208 IAW SRM CH 51-40-02. AND DRAWING # 143A0060 ID. 36; [04] VERIFIED INSTALLATION OF FLOOR SUPPORT AT BS 540 BL-0 THROUGH LBL 24.5 WL 208 IAW SRM 51-40-02; AND DRAWING # 143A0060 ID. 36; [05] VERIFIED JOB COMPLETE OF REPLACEMENT OF FLOOR SUPPORT AT BS 540 BL-0 THROUGH LBL 24.5 WL 208 IAW SRM 51-40-02; AND DRAWING # 143A0060 ID. 36

Part: SUPPORT — CRACKED (BS 540) · airframe 32,936 hrs · 20,041 cycles

CRACKED FLOOR SUPPORT AT B.S. 540 B.L. 0 - R.B.L. 24.5; W.L. 208.1. ; / [01] DRILLED NEW PART PER SRM 51-40-05-0G-0. <BR>OK TO INSTALL FLOOR SUPPORT; [02] VERIFIED; [03] VERIFIED DRILL UP PER SRM AND VERIFIED OK TO INSTALL.; [04] INSTALLED FLOOR SUPPORT PER SRM 51-40-02-0G-0 AND DRILLED FLOOR BOARD HOLES PER SRM 51-40-05-0G-0.; [05] VERIFIED; [06] INSTALLED FLOOR SUPPORT PER SRM 51-40-02-0G-0 AND BOEING DWG 143A0060.<BR> DRILLED FLOOR BOARD HOLES PER SRM 51-40-05-0G-0.; [07] VERIFIED; [08] VERIFIED INSTALLATION OF FLOOR SUPPORT AT BS 540 (537); BL 0 - RBL 24.5; WL 208.1 IAW SRM 51-40-02-0G-0 AND DWG 143A0060.; [09] VERIFIED TASK IS COMPLETE.

Part: PRESSURE DECK — DENTED (BS 255 RBL 4) · airframe 32,936 hrs · 20,041 cycles

FLIGHT DECK FLOOR IS DENTED AT B.S. 255; R.B.L. 4 - L.B.L. 14; W.L. 207.54. ; / [01] FLIGH DECK FLOOR AT BS 255; RBL4 TO LBL14 WL297.54; FOUND OUT LIMITS AT STA 256 LBL4 WL207.54 SHARP CREASES ARE NOT PERMITED IAW SRM 53-10-51-1A-1 STEP 4.JILIL(3); [02] CERTIFY; [03] VERIFIED FLIGH DECK FLOOR AT BS 255; RBL4 TO LBL14 WL297.54; FOUND OUT LIMITS AT STA 256 LBL4 WL207.54 SHARP CREASES ARE NOT PERMITED IAW SRM 53-10-51-1A-1 STEP 4.JILIL(3); [04] INSTALLED EWIS PROTECTION UNDER THE REPAIR AREA IAW AMM20-60-07-913-801; [05] CERTIFY EWIS INSTALLATION; [06] INSTALLED ALL PERMANENT AND TEMPORARY FASTENERS BEFORE SEALANT CURE TIME. BMS 5-95 C-20 MIXED AT 0300 UTC 08/13/2021 IAW EA 221-153-00734.; [07] VERIFIED CORRECTIVE ACTION ITEMS 4-6; [08] COMPLETED THE INSTALLATION OF THE COCKPIT FLOOR REPAIR IN CONJUNCTION WITH TTG8Q006428K EA 21-153-00734 REMOVED EWIS PROTECTION IAW AMM CH 20-60-07.; [09] CORRECTION FOR EA ON ITEM 6; ACTUAL EA IS 21-152-00734; [10] VERIFIED JOB TASK IS COMPLETED.

Part: SEAT TRACK — CORRODED (BS 827) · airframe 32,936 hrs · 20,041 cycles

CORROSION ON PASSENGER CABIN SEAT TRACK AT B.S. 827+16; L.B.L. 45.5; W.L. 208.1. ; / [01] REMOVED CORROSION FROM TRACK WITH A MAX MATERIAL LOSS OF .017 IN THE BOTTOM OF THE TRACK AND .022 ON THE TOP. MEASURED USING TOOL ID #ATS1225 CAL. DUE 07/2022 FOUND TO BE OUT OF LIMITS IAW SRM CH 53-00-52-1A-1; [02] VERIFIED CORRECTIVE ACTION ITEM 1; [03] REMOVED DAMAGED SEAT TRACK AT BS727B-887 LBL 45 PER SRM 51-40-02.; [04] NEW SEAT TRACK FABRICATED PER BOEING DWG 146A5350 SH 36; REFER TO ATS BUILD RECORD NO. 531818.; [05] PART MARKED NEW TRACK IN ACCORDANCE WITH ATS QCM 4.35.26.; [06] VERIFIED DAMAGED SEAT TRACK REMOVED; NEW SEAT TRACK FABRICATED PER BOEING DWG 146A5350 SH 36; REFER TO ATS BUILD RECORD NO. 531818; AND PART MARKED NEW TRACK IAW ATS QCM 4.35.26.; [07] LOCATED AND DRILLED NEW SEAT TRACK AT BS727B-887; LBL 45.5 PER DWG 146A5300 AND SRM 51-40-05.; [08] REQUEST VERIFY LOCATION AND DRILL; OK TO INSTALL NEW SEAT TRACK.; [09] VERIFIED LOCATED AND DRILLED. OKAY TO INSTALL NEW SEAT TRACK AT BS727B-887; LBL 45.5 PER DWG 146A5300 AND SRM 51-40-05; [10] INSTALLED SEAT TRACK BS 727B-887 LBL 45.5 WL 208.1 PER SRM 51-40-02 AND DWG 146A5300 SH145; SH146; SH147.; [11] VERIFIED INSTALLED SEAT TRACK BS 727B-887 LBL 45.5 WL 208.1 PER SRM 51-40-02 AND DWG 146A5300 SH145; SH146; SH147.

Part: BULKHEAD WEB — CRACKED (BS 663) · airframe 32,936 hrs · 20,041 cycles

B.S. 663 LOWER COMPOSITE BULKHEAD IS CRACKED AT R.B.L. 31; W.L. 150. ; / FOUND DAMAGE TO BE OUT OF ALLOWABLE LIMITS IAW SRM 57-10-10-1A-2 PARA 4.D.(1)(A)(1). REMOVED DAMAGE (AT MULTIPLE LOCATIONS) AND CONTAMINATION; PREPARED SURFACE; AND CLEANED REPAIR AREA IAW SRM 51-70-04-2R-10 PARA 4A-C. FABRICATED REPAIR PLIES FROM BMS9-3TYH2CL7 LOT 1458851-1 IAW SRM 51-70-04-2R-10 PARA 4.D OK TO INSTALL REPAIR PLIES. INSTALLED PLIES WITH BMS8-301 CLASS1 LOT JH9LAC5098 VACUUM BAGGED AND VERIFIED 5X5 IS GOOD WITH VACUUM GAUGE ID: ATS2438 S/N: UNKNOWN IAW SRM 51-70-04-2R-10 PARA 4.D-E.; [07] VERIFIED CORRECTIVE ACTION ITEM 6; [08] SET PLIES TO CURE USING HOTBONDER ID: ATS883 S/N: 15112530 IAW SRM 51-70-04-2R-10 PARA 4.F.; [09] CURED; UNBAGGED; TRIMMED; AND CLEANED REPAIR PLIES IAW SRM 51-70-04-2R-10 PARA 4F. REQUEST POST CURE NDI. <BR>HOTBONDER ATS883 SN: 15112530; [10] INSPECTED ACTION 8;9; [11] UT INSPECTED REPAIR IAW 737 NDTM PART 4 51-00-02; NO DISBONDS NOTED.<BR>CAL ID ATS2031 E650; REPAIRED CRACKED B.S. 663 LOWER COMPOSITE BULKHEAD AT R.B.L 31; W.L 150 IAW 51-70-04-2R-10; [13] REPAIRED CRACKED B.S. 663 LOWER COMPOSITE BULKHEAD AT R.B.L 31; W.L 150 IAW 51-70-04-2R-10 <BR><BR>CHANGED TO REPAIRED CRACKED B.S. 663 LOWER COMPOSITE BULKHEAD AT R.B.L 31; W.L 150 IAW SRM 51-70-04-2R-10; [14] VERIFIED CORRECTIVE ACTION 12 AND 13 PER AMM 51-21-72-370-802 AND SRM 51-70-04-2R-10.<BR><BR>VERIFIED COMPLETION OF B.S. 663 LOWER COMPOSITE BULKHEAD AT R.B.L 31; W.L 150 PER SRM 51-70-04-2R-10 REPAIR

Part: TRUNNION — CORRODED (RT MLG) · airframe 31,941 hrs · 19,490 cycles

R/H MLG FWD TRUNNION SUPPORT FITTING UPPER O/B LUG; OUTER FACE HAS EVIDENCE OF CORROSION. / REPAIRED PER EA NO: 1-A57-3246 REV 12

Part: TRUNNION — CORRODED (LT MLG) · airframe 31,941 hrs · 19,490 cycles

L/H MLG FWD TRUNNION SUPPORT FITTING UPPER I/B LUG. OUTER FACE HAS EVIDENCE OF CORROSION. / REPAIRED PER EA NO: 1-A57-3246 REV 12

Part: TRUNNION — CORRODED (RT MLG) · airframe 31,941 hrs · 19,490 cycles

R/H MLG FWD TRUNNION SUPPORT FITTING; LOWER I/B LUG; OUTER FACE HAS EVIDENCE OF CORROSION / REPAIRED PER EA NO: 1-A57-3246 REV 12

Part: TRUNNION — CORRODED (RT MLG) · airframe 31,941 hrs · 19,490 cycles

R/H MLG FWD TRUNNION SUPPORT FITTING UPPER I/B LUG; OUTER FACE HAS EVIDENCE OF CORROSION / REPAIRED PER EA NO: 1-A57-3246 REV 12

Part: SLIDE — OUT OF POSITION (R1 DOOR) · airframe 31,792 hrs · 19,399 cycles

FWD SERVICE DOOR SLIDE PRESS INDICATOR OUT OF POSITION. / RE-POSITIONED DOOR SLIDE WITH OUT OPENING CASE PER S.I.P.

Part: SIGN — DAMAGED (CABIN) · airframe 29,899 hrs · 18,249 cycles

AFT SERVICE DOOR AND AFT EMERGENCY EXIT SIGN DAMAGED. REMOVED AND REPLACED LIGHT ASSEMBLY IAW AMM 33-51-01.

Part: FAN — MALFUNCTIONED (CABIN) · airframe 29,794 hrs · 18,187 cycles

WITH APU ON FLIGHT ATTENDANT REPORTED SMOKE WITH BURNING SMELL / PERFORMED SMOKE OR FUMES IN CABIN (CONDITIONAL INSP) PER AMM 05-51-56-200-801 & FIM TASK 21-00 TASK 806. FOUND RECIRC FAN BAD. R/R RECIRC FAN PER AMM 21-25-02 RAR #5302 POS; ONLY PN OFF/ON; 645405-2 SN OFF; 5271 SN ON; 4027 TAG# 649553

Part: GIRT BAR — OUT OF POSITION (R1 DOOR) · airframe 28,688 hrs · 17,464 cycles

R1 DOOR SLIDE GIRT BAR WOULDN'T STOW ON HANGERS. / REPOSITIONED GIRT BAR PER AMM.

Part: GIRT BAR — DIRTY (R1 DOOR) · airframe 28,655 hrs · 17,444 cycles

R1 DOOR GIRT BAR WILL NOT LATCH. / CLEANED GIRT BAR AND LATCHED PER SIP

Part: ENGINE — POWER LOSS (NR 1) · airframe 28,511 hrs · 17,336 cycles

SUPPLEMENTAL INFORMATION, AIR TURNBACK/INFLIGHT SHUTDOWN/DECLARED EMERGENCY. AT V1 THE NR 1 ENGINE MADE A LOUD NOISE AND ROLLED BACK BUT DID NOT SHUT DOWN. ALTHOUGH THE TEMP ROSE ABOVE 800 THERE WAS NO FIRE INDICATION OR SMOKE IN THE CABIN. ALL OTHER SYSTEMS WERE NORMAL. R&R NR 1 ENGINE PER MT.

Part: SEAL — CRACKED (RT HORIZ STAB) · airframe 27,703 hrs · 16,797 cycles

RT HORIZONTAL STABILIZER FWD ATTACH LUG; UPPER SLIDER SEAL CRACKED. / REMOVED AND REPLACED RIGHT HORIZ. STAB FWD SLIDING SEAL IAW AMM 53-31-31

Part: SEAL — CRACKED (LT HORIZ STAB) · airframe 27,703 hrs · 16,797 cycles

LEFT HORIZONTAL STABILIZER FWD ATTACH LUG; UPPER SLIDER SEAL CRACKED. / REMOVED AND REPLACED LEFT HORIZ. STAB FWD SLIDING SEAL IAW AMM 53-31-31

Part: WEB — CORRODED (AFT CARGO) · airframe 27,703 hrs · 16,797 cycles

AFT CARGO THRESHOLD WEB HAS CORROSION OUT OF LIMITS NEEDS REPLACEMENT. / REMOVED AND REPLACED AFT CARGO THRESHOLD WEB PER SRM 51-40-02

Part: ANGLE — CORRODED (FUSELAGE) · airframe 27,703 hrs · 16,797 cycles

RT Z-ANGLE CORRODED BETWEEN BS. 962 TO BS. 986. REPAIRED Z ANGLE PER SRM.

Part: FLOOR SUPPORT — CORRODED (BS 767-887) · airframe 27,703 hrs · 16,797 cycles

AFT CARGO COMPARTMENT CORROSION ON THE UPPER SURFACE OF CARGO COMPARTMENT FLOOR BEAM BETWEEN BS. 767+11 TO BS. 887, RBL 16. / R&R FLOOR BEAM SECTION PER SRM.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 27,703 hrs · 16,797 cycles

CABIN FLOOR STRUCTURE INTERCOSTAL CRACKED AT BS. 322, RBL 35. R&R INTERCOSTAL PER SRM.

Part: SUPPORT — CRACKED (HORIZONTAL STAB) · airframe 27,703 hrs · 16,797 cycles

HORIZONTAL PANEL 343DB TE SUPPORT CRACKED (MARKED) / REMOVED AND REPLACED TE SUPPORT ON PANEL 343DBIAW SRM 51-40-02

Part: SUPPORT — CRACKED (HORIZONTAL STAB) · airframe 27,703 hrs · 16,797 cycles

HORIZONTAL PANEL 333CB TE SUPPORT CRACKED (MARKED) / REMOVED AND REPLACED TRAILING EDGE SUPPORT ON PANEL 333CB PER SRM 51-40-02.

Part: SCUFF PLATE — CRACKED (FWD CARGO THRESH) · airframe 27,703 hrs · 16,797 cycles

FWD CARGO; AFT CORNER THRESHOLD CRACKED. / REMOVED AND REPLACED AFT CORNER THRESHOLD PER AMM53-11-02

Part: SCUFF PLATE — CRACKED (FWD CARGO THRESH) · airframe 27,703 hrs · 16,797 cycles

FWD CARGO; FWD CORNER THRESHOLD CRACKED. / REMOVED AND REPLACED FWD CORNER THRESHOLD PER AMM53-11-02

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 27,703 hrs · 16,797 cycles

CABIN FLOOR STRUCTURE INTERCOSTAL CRACKED AT BS. 322, LBL 45. R&R INTERCOSTAL PER SRM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 27,703 hrs · 16,797 cycles

L ANGLE CRACKED AT BS. 294, STR. 17R ON FORWARD SIDE OF R1 DOOR SURROUND FORWARD FRAME JUST OUTBOARD OF THRESHOLD Z-ANGLE. R&R ANGLE PER SRM.

Part: SCUFF PLATE — CRACKED (AFT CARGO THRESH) · airframe 27,703 hrs · 16,797 cycles

AFT CARGO DOOR CUTOUT; AFT CORNER SCUFF PLATE IS CRACKED. / INSTALLED NEW SCUFF PLATE PER AMM 53-11-02. TO BE LEAK CHECKED ON SWA TASK CARD 721-000-00-01.

Part: TRACK — CHAFED (CABIN) · airframe 27,703 hrs · 16,797 cycles

PASSENGER SEAT TRACK LBL 45 (#1) SEAT TRACK UPPER CROWN AREA IS CHAFFED FROM SEAT MOUNT CONTACT AT STA 520. MARKED / ACCOMPLISHED SEAT TRACK #1 SPLICE REPAIR FROM STA 500C+10 TO STA 520 IAW SRM 53-00-52-2R-4 AND EA 1-A53-11779.

Part: SCUFF PLATE — CRACKED (AFT CARGO THRESH) · airframe 27,703 hrs · 16,797 cycles

AFT CARGO DOOR CUTOUT; FWD. CORNER SCUFF PLATE IS CRACKED IN 2 PLACES. / INSTALLED NEW SCUFF PLATE PER AMM 53-11-02. TO BE LEAK CHECKED ON SWA TASK CARD 721-000-00-01.

Part: TRACK — CHAFED (CABIN) · airframe 27,703 hrs · 16,797 cycles

PASSENGER SEAT TRACK LBL 25 (#2) SEAT TRACK UPPER CROWN AREA IS CHAFFED FROM SEAT MOUNT CONTACT AT STA 520. MARKED / SEE WIP ENTRY #4 FOR REPAIRED SEAT TRACK PER EA 1-A53-11779 AND SRM 53-00-52-2R-4.

Part: FAIRING — CRACKED (LEFT WING) · airframe 27,703 hrs · 16,797 cycles

#3 CANOE HAS A SMALL CRACK ON THE INSIDE SURFACE / ACCOMPLISHED REPAIR TO CANOE REF EA# 1-A57-6168.

Part: LIGHT — INOPERATIVE (R1 DOOR) · airframe 24,845 hrs · 14,979 cycles

R1 DOOR EMERGENCY EXIT LIGHT INOP. RELAMPED LIGHT IAW PER AMM.

Part: LIGHT — INOPERATIVE (L1 DOOR) · airframe 24,845 hrs · 14,979 cycles

L1 DOOR EMERGENCY EXIT LIGHT INOP. RELAMPED LIGHT IAW PER AMM.

Part: SLIDE — UNSERVICEABLE (L1 DOOR) · airframe 24,755 hrs · 14,922 cycles

L1 DOOR SLIDE FAILED INSPECTION. R&R SLIDE PER MT.

Part: BATTERY — FAILED (CABIN) · airframe 24,684 hrs · 14,877 cycles

RT FORWARD EMERGENCY LIGHT BATTERY FAILED CAPACITY CHECK. R&R BATTERY PER AMM.

Part: SUPPORT ANGLE — CRACKED (RT WING) · airframe 22,515 hrs · 13,471 cycles

RT WING TRAILING EDGE TOP FIXED PANEL INBOARD OF DEFLECTION CONTROL RIB, SUPPORT ANGLE CRACKED AT OUTBOARD FASTENER HOLE. R&R WEB PER SRM.

Part: STRUCTURE — CRACKED (R1 DOOR) · airframe 22,514 hrs · 13,470 cycles

R1 DOOR CRACKED IN RADIUS BELOW CAM BOX ASSEMBLY NEXT TO FORWARD INBOARD MOUNTING BOLT. R&R DOOR PER AMM.

Part: LIGHT — INOPERATIVE (EXTERIOR) · airframe 21,465 hrs · 12,792 cycles

L2 DOOR EXTERIOR EMERGENCY LIGHT INOP. R&R LIGHT PER AMM.

Part: STRIP — CORRODED (AFT CARGO BAY) · airframe 20,975 hrs · 12,489 cycles

AFT CARGO R/H TRANSITION ANGLE HAS CORROSION STA 727-767. / REMOVED AND REPLACED R/H TRANSITION ANGLE FROM STA.727 TO STA.767 PER SRM 51-40-02.

Part: BULKHEAD — CRACKED (RT MLG WW) · airframe 20,975 hrs · 12,489 cycles

CENTER WING BOX BULKHEAD CRACKED AT BS 663, RBL 37.5, FORWARD OF THE "B" HYDRAULIC RESERVOIR HI-PRESSURE FILTER ASSEMBLY. REPAIRED BULKHEAD PER SRM.

Part: STRIP — CORRODED (AFT CARGO BAY) · airframe 20,975 hrs · 12,489 cycles

AFT CARGO L/H TRANSITION ANGLE HAS CORROSION STA 727-847. / INSTALLED L/H TRANSITION ANGLE FROM STA 727+4' TO STA 847 PER SRM 51-40-02.

Part: STRIP — CORRODED (AFT CARGO BAY) · airframe 20,975 hrs · 12,489 cycles

AFT CARGO R/H TRANSITION ANGLE HAS CORROSION STA 767-787. / REMOVED AND REPLACED AFT CARGO R/H TRANSITION ANGLE STA 767-787 IAW SRM 51-40-02.

Part: FLOOR PANEL — CRACKED (FLIGHT DECK) · airframe 20,975 hrs · 12,489 cycles

PANEL 211B IS CRACKED ON BACK SIDE MARKED / R & R PANEL PER SRM 51-40-02

Part: SLIDE — UNSECURE (R2 DOOR) · airframe 20,597 hrs · 12,262 cycles

R2 DOOR EMERGENCY EVAC SLIDE INADVERTENTLY FELL OUT, DID NOT DEPLOY, STILL OPERATIONAL. REINSTALLED SLIDE ASSEMBLY PER MT.

Part: FUSE — INOPERATIVE (EMERGENCY LIGHTS) · airframe 18,928 hrs · 11,249 cycles

RIGHT OVERWING EXIT LIGHT INOPERATIVE. R & R BATTERY PACK FUSE IAW MM.

Part: VAPOR BARRIER — CRACKED (RT MLG WW) · airframe 18,823 hrs · 11,184 cycles

RT WHEEL WELL FORWARD VAPOR BARRIER CRACKED BETWEEN RBL 31.83 TO RBL 40.00. REPAIRED BARRIER PER SRM.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 18,185 hrs · 10,781 cycles

LEFT OVERWING EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED THE LAMP IAW AMM.

Part: COVER — LOOSE (L1 DOOR) · airframe 17,093 hrs · 10,119 cycles

L1 DOOR SLIDE EMERGENCY EVAC SLIDE COVER BOTH GIRT BAR HANGER ATTACH HARDWARE LOOSE. R & R COVER IAW SRM.

Part: GLOWSTRIP — DAMAGED (CABIN) · airframe 17,093 hrs · 10,119 cycles

FORWARD CABIN RT PHOTOLUMINESCENT FLOOR LIGHTING DAMAGED BETWEEN BS 328 TO BS 630. R & R STRIP IAW AMM.

Part: LENS — LOOSE (CABIN) · airframe 17,093 hrs · 10,119 cycles

RT FORWARD CABIN LOWER SIDEWALL EMERGENCY EXIT LIGHT ASSEMBLY LOOSE AT ROW 12. SECURED LENS IAW MM.

Part: LIGHT — LOOSE (CABIN) · airframe 15,952 hrs · 9,446 cycles

CENTER AISLE OVERHEAD EMER EXIT LIGHT BAR LOOSE. SECURED LIGHT ASSEMBLY IAW SIP.

Part: BATTERY PACK — FAILED (CABIN) · airframe 13,776 hrs · 8,153 cycles

EMERGENCY BATTERY PACKS FAILED CAPACITY CHECK AT M1670. R & R EMER BATTERY PACK IAW AMM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 13,776 hrs · 8,153 cycles

EMERGENCY BATTERY PACKS FAILED CAPACITY CHECK AT M1673. R & R EMER BATTERY PACK IAW AMM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 13,776 hrs · 8,153 cycles

EMERGENCY BATTERY PACKS FAILED CAPACITY CHECK AT M1672. R & R EMER BATTERY PACK IAW AMM.

Part: LENS — BROKEN (CABIN) · airframe 11,871 hrs · 7,091 cycles

RIGHT OVERWING EXIT LIGHT LENS BROKEN. R & R LENS IAW SIP.

Part: MOUNT — BROKEN (CABIN) · airframe 9,385 hrs · 5,647 cycles

MID CABIN EMER EXIT SIGN MOUNT BROKEN. R & R LIGHT ASSEMBLY IAW MM.

Part: LENS — LOOSE (CABIN) · airframe 5,380 hrs · 3,274 cycles

RIGHT FWD SERVICE DOOR LOWER EMERGENCY LIGHT LENS FELL LOOSE. REMOVED & REPLACED LIGHT ASSY PER AMM.

Part: COVER — LOOSE (CABIN) · airframe 5,318 hrs · 3,239 cycles

EMERGENCY FLOOR LIGHTING COVER LOOSE. REMOVED AND REPLACED COVER PER MM.

Part: SIGN — BROKEN (CABIN) · airframe 5,290 hrs · 3,219 cycles

FORWARD EXIT SIGN BROKEN. REMOVED AND REPLACED LIGHT ASSY PER MM.

Part: WINDOW — CRACKED (R1 DOOR) · airframe 4,523 hrs · 2,740 cycles

R1 GALLEY DOOR SLIDE VIEWING WINDOW CRACKED. REMOVED AND REPLACED PER AMM, R1 GALLEY DOOR SLIDE VIEWING WINDOW C/W T/C 725-61-06.

Part: COVER — BROKEN (EXIT SIGN) · airframe 4,385 hrs · 2,664 cycles

RIGHT OVERWING EXIT SIGN BROKEN. REMOVED AND REPLACED LIGHT COVER IAW M/M.

Part: COVER — MISSING (EMERGENCY LIGHT) · airframe 1,474 hrs · 886 cycles

R2 DOOR EMERGENCY EXIT SIGN COVER MISSING. INSTALLED COVER PER MM.

Part: LENS — BROKEN (CABIN) · airframe 154 hrs · 98 cycles

FWD EEPLS LENS BROKEN. SECURED LENS PER MM.