N8674B

Part: ANGLE — CRACKED (ZONE 500) · airframe 31,512 hrs · 15,472 cycles

OUTER ATTACHMENT CLIP FOR SUPPORT RIB UNDER LEFT WING PANEL 551GB CRACKED<[01] REMOVED + REPLACED OUTER ATTACHMENT CLIP FOR SUPPORT RIB UNDER LEFT WING PANEL 551GB IAW SRM 51-40-02.

Part: SUPPORT — CRACKED (ZONE 500) · airframe 31,512 hrs · 15,472 cycles

SUPPORT RIB UNDER LEFT WING PANEL 551GB CRACKED AT UPPER RIVET ROW<[01] REMOVED + REPLACED SUPPORT RIB UNDER LEFT WING PANEL 551GB IAW SRM 51-40-02.

Part: SKIN — DELAMINATED (ZONE 500 FLAP) · airframe 30,285 hrs · 14,826 cycles

L/H WING O/B AFT FLAP DELAMINATED AT THE I/B AFT CORNER AT LOWER SKIN. MARKED<[01] 01 - REMOVED AND REPLACED PER [AMM 27-51-22-400-801-NG (OUTBOARD AFT FLAP INSTALLATION - PERMANENT)];[02] VERIFIED 01 - REMOVED AND REPLACED PER [AMM 27-51-22-400-801-NG (OUTBOARD AFT FLAP INSTALLATION - PERMANENT)]

Part: SEAL — CRACKED (ZN 300 STABILIZE) · airframe 30,285 hrs · 14,826 cycles

R-HORIZONTAL STABILIZER UPPER SLIDDING SEAL CRACKED DOT# J802<[01] REMOVED AND REPLACED UPPER SLIDING SEAL IAW B737-800 AMM 53-31-31-401. FUNCTION CHECK GOOD;[02] 02 - INSPECTED PER [AMM 53-31-31-401 CONFIG 1-NG (STABILIZER TO BODY FRONT SPAR SLIDING SEAL - REMOVAL/INSTALLATION - PERMANENT)]

Part: SEAL — CRACKED (ZN 300 STABILIZE) · airframe 30,285 hrs · 14,826 cycles

L-HORIZONTAL STABILIZER UPPER SLIDING SEAL CRACKED DOT# J804<[01] REMOVED AND REPLACED UPPER SLIDING SEAL IAW B737-800 AMM 53-31-31-401. FUNCTION CHECK GOOD;[02] 02 - INSPECTED PER [AMM 53-31-31-401 CONFIG 1-NG (STABILIZER TO BODY FRONT SPAR SLIDING SEAL - REMOVAL/INSTALLATION - PERMANENT)]

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 30,285 hrs · 14,826 cycles

MAIN CABIN FLOOR PANEL 241AF IS BURNT/DELAMINATED<[01] REMOVED AND REPLACED FLOOR PANEL ASSY 241AF IAW B737-800 AMM 53-21-00-400-801. DISPALCED & REINSTALLED TO F.O.M. SEATS 14ABC; 15ABC; 16ABC; & 17ABC IAW B737-800 AMM 25-22-00-400-802; SUBTASK 25-22-00-420-410 & SUBTASK 25-22-00-420-451. REMOVED AND REPLACED FLOOR PANEL ASSY 241AF IAW B737-800 AMM 53-21-00-400-801.. DISPALCED & REINSTALLED TO F.O.M. SEATS 14ABC; 15ABC; 16ABC; & 17ABC IAW B737-800 AMM 25-22-00-400-802; SUBTASK 25-22-00-420-410 & SUBTASK 25-22-00-420-451.

Part: ANGLE — CRACKED (ZN 100 FUS LOWER) · airframe 30,285 hrs · 14,826 cycles

L/H VAPOR LOWER ANGLE BARRIER CRACKS (2) FOUND @ STA 663.75<[01] REMOVED ANGLE PER B737-800 SRM51-40-02. FABRICATED NEW ANGLE PER DWG 111A1322 REV A. INSTALLED NEW ANGLE PER DWG 111A1000 AND B737-800 SRM 51-40-02;[02] REMOVED ANGLE PER B737-800 SRM51-40-02. FABRICATED NEW ANGLE PER DWG 111A1322 REV A. INSTALLED NEW ANGLE PER DWG 111A1000 AND B737-800 SRM 51-40-02<BR>PREDEFINED ACTIONS:

Part: ANGLE — CRACKED (ZONE 100) · airframe 30,285 hrs · 14,826 cycles

CR -- L/H VAPOR BARRIER ANGLE REQUIRES GVI INSP FOR CRACKS<

Part: ANGLE — CRACKED (ZONE 100) · airframe 30,285 hrs · 14,826 cycles

CR -- R/H VAPOR BARRIER ANGLE REQUIRES GVI INSP FOR CRACKS<

Part: ANGLE — CRACKED (ZONE 100) · airframe 30,285 hrs · 14,826 cycles

CRACK FOUND ON R/H VAPOR BARRIER LOWER BRACKET @ STA 663.75<[01] REMOVED AND REPLACED ANGLE PER DWG 111A1000 AND B737-800 SRM 51-40-02;[02] REMOVED AND REPLACED ANGLE PER DWG 111A1000 AND B737-800 SRM 51-40-02

Part: MEGAPHONE — INOPERATIVE (ZONE 200) · airframe 29,662 hrs · 14,482 cycles

AFT MEGAPHONE SOUNDS WEAK PER INSPECTION<[01] REPLACED BATTERIES ON MEGAPHONE PER AMM 25-64-00. OPS CHECK GOOD REPLACED PLACARD NEXT INSPECTION DUE DATE SEP 25

Part: SEAT BACK — OUT OF ADJUST (ZONE 200) · airframe 29,428 hrs · 14,364 cycles

PASSENGER SEAT 15D EMERGENCY EXIT ROW SHOULD NOT RECLINE.<[01] ADJUSTED HYDROLOCK IAW AMM 25-22-00

Part: SIGN — MISSING (ZONE 200) · airframe 29,422 hrs · 14,361 cycles

MISSING EXIT SIGN IN THE MID CABIN.<[01] REPLACED MID CABIN ?EXIT? SIGN ASSEMBLY AND LENS PER <BR>AMM 33-51-01. OPS CHECK GOOD.

Part: SLIDE — DISLODGED (ZONE 800) · airframe 29,302 hrs · 14,292 cycles

CAPTAINS SIDE AFT SLIDE MATERIAL HANGING OUT.<[01] REPOSITIONED SLIDE AND ACCOMPLISHED MT 725-61-06.

Part: LENS — DETACHED (EMERGENCY LIGHTS) · airframe 28,469 hrs · 13,820 cycles

MID CABIN OVERHEAD EMERGENCY EXIT SIGN LENS KNOCKED DOWN<[01] REINSTALLED LENS PER AMM 33-51-01

Part: COVER — MISSING (EMERGENCY LIGHT) · airframe 28,410 hrs · 13,795 cycles

MIDDLE AISLE EMERGENCY SIGN MISSING COVER<[01] REPLACED MIDDLE AISLE EMERGENCY SIGN IAW AMM 11-32-01.

Part: LENS — MISSING (EMERGENCY LIGHT) · airframe 28,052 hrs · 13,595 cycles

OVERWING EMERGENCY EXIT SIGN MISSING LENS.<[01] REINSTALLED OVERWING EMERGENCY EXIT LIGHT LENS PER AMM 33-51-01.

Part: COVER — DETACHED (EMERGENCY LIGHT) · airframe 27,441 hrs · 13,241 cycles

EXIT LIGHT COVER TO THE LEFT OF STARBOARD SIDE FWD GALLEY DOOR WONT STAY ON.<[01] R&R'D R1 DOOR EMERGENCY LIGHT LENS PER AMM 33-51-01.

Part: LENS — MISSING (ZN 200 FUS TOP) · airframe 26,914 hrs · 12,955 cycles

EXIT SIGN FRONT COVER MISSING MID CABIN<[01] RESECURED LENS AS REQUIRED PER SIP.

Part: COWL DOOR — CRACKED (ZN 400 NACELLE/P) · airframe 26,653 hrs · 12,812 cycles

NUMBER 1 ENGINE I/B FAN COWL HAS CRACK FWD OF THE FORWARD LATCH APPROXIMATELY 9 INCHES LONG GOING THROUGH 2 RIVETS<[01] REMOVED AND REPLACED #1 I/B FAN COWL PER AMM 71-11-02;[02] VERIFIED THE FOLLOWING:<BR>REMOVED AND REPLACED #1 I/B FAN COWL PER AMM 71-11-02

Part: SCUFF PLATE — CRACKED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

AFT CARGO LOWER MAIN SEAL SCUFF PLATE REQUIRES REPLACEMENT<[01] INSTALLED NEW SCUFFPLATE IAW AMM 53-11-02.;[02] INSTALLED NEW SCUFFPLATE IAW AMM 53-11-02. INSP C/W;[03] INSPECTION C/W INSTALLED NEW SCUFF PLATE IAW AMM 53-11-02. LEAK CHECK GOOD PER STEP 1

Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 26,522 hrs · 12,730 cycles

SEVERAL EMERGENCY BULLNOSE LIGHTS INOP IN CABIN.<[01] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. OPS CHECK GOOD. REF AMM 33-51-06.;[02] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. OPS CHECK GOOD. REF AMM 33-51-06.;[03] CORRECTIVE ACTIONS 1 AND 2 ENTERED IN ERROR. INCORRECT SIGN OFF.;[04] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. REF AMM 33-51-06.;[05] VERIFIED SIGNOFF 1&2 CLOSED IN ERROR. CORRECTIVE ACTIONS 1 AND 2 ENTERED IN ERROR. INCORRECT SIGN OFF.<BR>REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. REF AMM 33-51-06.C/W INSPECTION;[06] REMOVED AND REPLACED 5 EACH EMERGENCY LIGHT BATTERY PACKS PER MM 33-51-06. OPS CHECKS GOOD PER MM 33-51-00;[07] INSPECTED WORK PERFORMED. SEE STEPS AND C/A?S FOR ALL WORK PERFORMED. REMOVED AND REPLACED 5 EACH EMERGENCY LIGHT BATTERY PACKS PER MM 33-51-06. OPS CHECKS GOOD PER MM 33-51-00

Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 26,522 hrs · 12,730 cycles

SEVERAL EMERGENCY BULLNOSE LIGHTS INOP IN CABIN.<[01] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. OPS CHECK GOOD. REF AMM 33-51-06.;[02] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. OPS CHECK GOOD. REF AMM 33-51-06.;[03] CORRECTIVE ACTIONS 1 AND 2 ENTERED IN ERROR. INCORRECT SIGN OFF.;[04] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. REF AMM 33-51-06.;[05] VERIFIED SIGNOFF 1&2 CLOSED IN ERROR. CORRECTIVE ACTIONS 1 AND 2 ENTERED IN ERROR. INCORRECT SIGN OFF.<BR>REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. REF AMM 33-51-06.C/W INSPECTION;[06] REMOVED AND REPLACED 5 EACH EMERGENCY LIGHT BATTERY PACKS PER MM 33-51-06. OPS CHECKS GOOD PER MM 33-51-00;[07] INSPECTED WORK PERFORMED. SEE STEPS AND C/A?S FOR ALL WORK PERFORMED. REMOVED AND REPLACED 5 EACH EMERGENCY LIGHT BATTERY PACKS PER MM 33-51-06. OPS CHECKS GOOD PER MM 33-51-00

Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 26,522 hrs · 12,730 cycles

SEVERAL EMERGENCY BULLNOSE LIGHTS INOP IN CABIN.<[01] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. OPS CHECK GOOD. REF AMM 33-51-06.;[02] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. OPS CHECK GOOD. REF AMM 33-51-06.;[03] CORRECTIVE ACTIONS 1 AND 2 ENTERED IN ERROR. INCORRECT SIGN OFF.;[04] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. REF AMM 33-51-06.;[05] VERIFIED SIGNOFF 1&2 CLOSED IN ERROR. CORRECTIVE ACTIONS 1 AND 2 ENTERED IN ERROR. INCORRECT SIGN OFF.<BR>REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. REF AMM 33-51-06.C/W INSPECTION;[06] REMOVED AND REPLACED 5 EACH EMERGENCY LIGHT BATTERY PACKS PER MM 33-51-06. OPS CHECKS GOOD PER MM 33-51-00;[07] INSPECTED WORK PERFORMED. SEE STEPS AND C/A?S FOR ALL WORK PERFORMED. REMOVED AND REPLACED 5 EACH EMERGENCY LIGHT BATTERY PACKS PER MM 33-51-06. OPS CHECKS GOOD PER MM 33-51-00

Part: BATTERY PACK — INOPERATIVE (ZN 200 FUS TOP) · airframe 26,522 hrs · 12,730 cycles

SEVERAL EMERGENCY BULLNOSE LIGHTS INOP IN CABIN.<[01] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. OPS CHECK GOOD. REF AMM 33-51-06.;[02] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. OPS CHECK GOOD. REF AMM 33-51-06.;[03] CORRECTIVE ACTIONS 1 AND 2 ENTERED IN ERROR. INCORRECT SIGN OFF.;[04] REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. REF AMM 33-51-06.;[05] VERIFIED SIGNOFF 1&2 CLOSED IN ERROR. CORRECTIVE ACTIONS 1 AND 2 ENTERED IN ERROR. INCORRECT SIGN OFF.<BR>REPLACED 4 BATTERY PACKS. 2 FWD LEFT AND RIGHT AND 2 AFT LEFT AND RIGHT. REF AMM 33-51-06.C/W INSPECTION;[06] REMOVED AND REPLACED 5 EACH EMERGENCY LIGHT BATTERY PACKS PER MM 33-51-06. OPS CHECKS GOOD PER MM 33-51-00;[07] INSPECTED WORK PERFORMED. SEE STEPS AND C/A?S FOR ALL WORK PERFORMED. REMOVED AND REPLACED 5 EACH EMERGENCY LIGHT BATTERY PACKS PER MM 33-51-06. OPS CHECKS GOOD PER MM 33-51-00

Part: PANEL — DELAMINATED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

WING TO BODY PANEL 194FL HAS A SMALL DENT WITH DELAMINATION. DAMAGE IS MARKED<[01] REMOVED DAMAGE PER SRM 51-70-05-2R-1. POTTED CORE PER SRM 51-70-05-2R-11.;[02] INSPECTED WORK PERFORMED ON C/A #1;[03] INSTALLED REPAIR PLIES IAW SRM 51-70-05-2R;[04] INSPECTED WORK PERFORMED;[05] APPLIED RESIN SEALER PER SRM 51-70-08.;[06] RESTORED SURFACE FINISH PER AMM 51-51-99.<BR>REPAIRED PER SRM 51-70-05-2R-1.;[07] RESTORED SURFACE FINISH PER AMM 51-51-99.<BR>REPAIRED PER SRM 51-70-05-2R-1.

Part: STRINGER — SEPARATED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

BS 727 INNER CHORD AT STRINGER 18A LEFT SIDE HAS .008 INCH GAP AS MEASURED DURING 5311-I-14576-NG STEP 9<[01] CORRECTED EXCESSIVE GAP WITH COMPLETION OF EO 5311-E-14577-NG.;[02] CORRECTED EXCESSIVE GAP WITH COMPLETION OF EO 5311-E-14577-NG.

Part: STRINGER — SEPARATED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

INSPECTION OF BS 727 INNER CHORD AT STRINGER 18A RIGHT SIDE HAS .008 GAP BETWEEN STRINGER AND CHORD AS MEASURED DURING 5311-I-14624-NG STEPS 8 & 9<[01] CORRECTED EXCESSIVE GAP WITH COMPLETION OF EO 5311-E-14625-NG.;[02] CORRECTED EXCESSIVE GAP WITH COMPLETION OF EO 5311-E-14577-NG.

Part: SCUFF PLATE — CRACKED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

AFT CARGO AFT CORNER SCUFF PLATE CRACKED.<[01] INSTALLED NEW CORNER SCUFFPLATE IAW AMM 53-11-02.;[02] INSTALLED NEW CORNER SCUFFPLATE IAW AMM 53-11-02. INSP. C/W;[03] INSPECTION C/W INSTALLED NEW CORNER SCUFF PLATE IAW AMM 53-11-02 AND ACCOMPLISHED CABIN PRESSURE LEAK CHECK. NO LEAKS NOTED. REF AMM 05-51-91-790-801

Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

AFT CARGO STA 767-747 RBL 23 TRANSITION ANGLE HAS CORROSION AROUND NUT PLATE HOLES.<[01] REMOVED CORROSION FROM AREA PER SRM 53-00-53-1A-2 (REMAINING THICKNESS 0.037'). TRANSITION ANGLE IS OUT OF WITHIN LIMITS PER<BR>SRM 53-00-53-1A-2.;[02] REMOVED RH TRANSITION ANGLE FROM STA 727G+10 TO STA 767.;[03] LOCATED HOLES ON NEW TRANSITION ANGLE PER SRM 51-40-02.;[04] INSPECTED WORK PERFORMED ON C/A #3;[05] TREATED AND PRIMED TRANSITION ANGLE PER SRM 51-20-01 AND <BR>SOPM 20-41-02.;[06] INSTALLED BONDED NUTPLATES TO TRANS ANGLE FROM 727G TO 767 PER SRM 51-40-10. INSTALLED TIME 0300 10-06-2023 24HR FOR FULL CURE;[07] C/W CA#6 INSTALLED BONDED NUTPLATES TO TRANS ANGLE FROM 727G TO 767 PER SRM 51-40-10. INSTALLED TIME 0300 10-06-2023 24HR FOR FULL CURE;[08] FABRICATED TRANSITION ANGLE REPAIR PARTS PER SRM 53-00-53-2R-6.;[09] RII: INSPECTED WORK ACCOMPLISHED IN C/A # 8. CARLOS FLOREZ (TECHNICIAN); 06-OCT-2023 12:45 UTC FABRICATED TRANSITION ANGLE REPAIR PARTS PER SRM 53-00-53-2R-6.<BR><BR>RII: OK TO INSTALL REPAIR PARTS.<BR><BR>SEE STEP 1 FOR NUTPLATE INSTALLATION PUSH CHECK. (REF C/A #'S 6 AND 7);[10] REPAIRED TRANSITION ANGLE STA 727G+10' TO STA 767; RBL 23 PER SRM 53-00-53-2R-6.;

Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

AFT CARGO STA 767-787 RBL 23 TRANSITION ANGLE HAS CORROSION AROUND NUT PLATE HOLES.<[01] REMOVED CORROSION FROM AREA PER SRM 53-60-15-1A-1 (REMAINING THICKNESS 0.045'). TRANSITION ANGLE IS OUT OF WITHIN LIMITS PER<BR>SRM 53-60-15-1A-1.;[02] REMOVED RH TRANSITION ANGLE (SHIELD) STA 767-787; RBL 23.;[03] LOCATED HOLES ON NEW TRANSITION ANGLE (SHIELD) PER SRM 51-40-02.;[04] 3. CARLOS FLOREZ (TECHNICIAN); 02-OCT-2023 16:52 UTC<BR>LOCATED HOLES ON NEW TRANSITION ANGLE (SHIELD) PER SRM 51-40-02.<BR>C/W INSPECTION.;[05] OK TO INSTALL R/H TRANSITION ANGLE FROM CORRECTIVE ACTION #3.;[06] REMOVED AND REPLACED TRANSITION ANGLE (SHIELD) PER SRM 51-40-02 AND <BR>SRM 53-60-15-1A-1.;[07] INSPECTED WORK PERFORMED

Part: ANGLE — CORRODED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

AFT CARGO STA 727J-727I RBL 23 TRANSITION ANGLE HAS CORROSION AROUND NUT PLATE HOLES.<[01] REMOVED CORROSION FROM AREA PER SRM 53-00-53-1A-2 (REMAINING THICKNESS 0.037'). TRANSITION ANGLE IS OUT OF WITHIN LIMITS PER<BR>SRM 53-00-53-1A-2.;[02] REMOVED RH TRANSITION ANGLE FROM STA 727G+10 TO STA 767.;[03] FABRICATION AND INSTALLATION OF REPAIR ACCOMPLISHED ON NON ROUTINE TTG8Q00NML6F.;[04] FABRICATION AND INSTALLATION OF REPAIR PER SRM 53-00-53-2R-6 AND <BR>SRM 53-00-53-1A-2 ACCOMPLISHED ON NON ROUTINE TTG8Q00NML6F.;[05] RII: INSPECTED WORK PERFORMED. FABRICATION AND INSTALLATION OF REPAIR PER SRM 53-00-53-2R-6 AND SRM 53-00-53-1A-2 ACCOMPLISHED ON NON ROUTINE TTG8Q00NML6F.

Part: WEB — CORRODED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

AFT CARGO STA 776-849 RBL 27 THRESHOLD WEB HAS CORROSION.<[01] REMOVED CORROSION FOUND TO BE OUT OF LIMITS PER SRM 53-60-15-1A-1;[02] REMOVED WEB PER SRM 51-40-02;[03] LOCATED AND DRILLED HOLES FOR WEB PER SRM 51-40-05;[04] C/W INSP. LOCATED AND DRILLED HOLES FOR WEB PER SRM 51-40-05;[05] COUNTERSANK FOR NUTPLATES PER SRM 51-40-08 INSTALLED NUTPLATES TO WEB PER SRM 51-40-02;[06] C/W INSPECTION C/A 5. COUNTERSANK FOR NUTPLATES PER SRM 51-40-08 INSTALLED NUTPLATES TO WEB PER SRM 51-;[07] DEBURR AND APPLIED ALODINE PER SRM 51-20-01.APPLLIED PRIMER TO CUT EDGES PER SOPM 20-51-02;[08] COUNTER SANK FASTENER HOLES PER SRM 51-40-08 SEE ALSO STEP 1;[09] APPLLIED PRIMER TO CUT EDGES PER SOPM 20-41-02 FOR STEP 7 C /A;[10] C/W INSPECTION OF DEBURR; ALODINE APPLICATION AND PRIMER APPLICATION PER SRM 51-20-01 & 51-40-08 AND SOPM 20-41-02 REF C/A LINE 7; 8 & 9;[11] OK TO INSTALL WEB;[12] OK TO INSTALL WEB;[13] INSTALLED WEB PER SRM 51-40-02.;[14] INSTALLED WEB PER SRM 51-40-02.;[15] INSTALLED WEB PER SRM 51-40-02.

Part: FLOORBEAM — CORRODED (ZN 100 FUS LOWER) · airframe 26,522 hrs · 12,730 cycles

AT BS 947; RBL 14 TIE DOWN LUG HAS CORROSION.<[01] REMOVED CORROSION FROM FLOOR BEAM AT STA 947; RBL 26 TO 27 AND FOUND DAMAGE TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1. TIE DOWN LUG IS AT RBL 26;[02] REMOVED DAMAGED SECTION OF UPPER CHORD I.A.W SRM 53-70-51-2R-5 ALTERNATIVE 2.;[03] REMOVED DAMAGED SECTION OF UPPER CHORD I.A.W SRM 53-70-51-2R-5 ALTERNATIVE 2. C/W INSPECTION;[04] FLAP PEENED CUT OUT AREA I.A.W SRM 53-70-51-2R-5.;[05] FLAP PEENED CUT OUT AREA I.A.W SRM 53-70-51-2R-5. C/W INSPECTION;[06] DRILLED REPAIR PARTS PER SRM 53-70-51-2R-5;[07] C/W INSPECTION OF ITEM #6 DRILLED REPAIR PARTS;[08] ALODINE AND PRIMED REPAIR PARTS PER SRM 51-20-01. NEED OK TO INSTALL.;[09] CW INSPECTION OF ITEM 8. OK TO INSTALL.;[10] INSTALLED FASTENERS ON THE SPLICES I.A.W SRM 53-70-51-2R-5;[11] VERIFIED REPAIR MATERIAL 7075 T6 .100;[12] INSTALLED FASTENERS IN T-CHORD PER SRM 53-70-51-2R-5;[13] FABRICATED FILLERS PER SRM 53-70-51-2R-5<BR>MATERIAL 7075 T6 .100;[14] REPAIRED PER SRM 53-70-51-2R-5;[15] INSPECTED WORK PERFORMED

Part: FLAP — DELAMINATED (ZN 500 LEFT WING) · airframe 26,522 hrs · 12,730 cycles

L/H WING ; O/B FLAP; AFT FLAP IS DELAMINATED AT I/B AFT CORNER.<[01] REMOVED L/H WING ; O/B FLAP; AFT FLAPIAW AMM 27-51-22;[02] OK TO INSTALL SERVICEABLE L/H WING ; O/B FLAP; AFT FLAP;[03] INSTALLED SERVICEABLE L/H WING ; O/B FLAP; AFT FLAP ASSY IAW AMM 27-51-22-400-801.;[04] INSPECTED INSTALLED SERVICEABLE L/H WING ; O/B FLAP; AFT FLAP ASSY;[05] REMOVED AND REPLACED L/H WING ; O/B FLAP; AFT FLAP IAW AMM 27-51-22;[06] REMOVED AND REPLACED L/H WING ; O/B FLAP; AFT FLAP IAW AMM 27-51-22;[07] RII: INSPECTED WORK PERFORMED. SEE STEPS AND C/A?S FOR ALL WORK PERFORMED. REMOVED AND REPLACED L/H WING ; O/B FLAP; AFT FLAP IAW AMM 27-51-22.

Part: BATTERY PACK — INOPERATIVE (ZN 800 DOOR) · airframe 25,998 hrs · 12,423 cycles

FWD ENTRY DOOR EXIT SIGN AND EXIT LOCATOR SIGN INOP<[01] REMOVED AND REPLACED BATTERY PACK M1675 PER AMM 33-51-01. OPS CHECK GOOD.

Part: BATTERY — WEAK (ZN 200 FUS TOP) · airframe 25,446 hrs · 12,105 cycles

FORWARD MEGAPHONE WEAK TRANSMIT<[01] R&R BATTERIES PER M/M 25-64-00

Part: ACCESS PANEL — CRACKED (RT WING) · airframe 24,194 hrs · 11,401 cycles

PANEL 621 PB RT WING CRACKED<[01] DRILLED; COUNTERSUNK AND INSTALLED PANEL PER SRM 51-40-05; AND 51-40-02

Part: STRUCTURE — CRACKED (ZONE 100) · airframe 24,046 hrs · 11,320 cycles

RIGHT BREAK PANEL ASSEMBLY CRACKED. RT BREAK ASSY AT STA. 520 BELOW FLOOR BOARD 231UF REMOVED REF SRM 51-40-02. REPLACED RT BREAK ASSY PER SRM 51-40-02.

Part: STRUCTURE — CRACKED (ZONE 100) · airframe 24,046 hrs · 11,320 cycles

LT BRAKE ASSY AT BS 520 CRACKED L/H BREAK ASSY. LT BRAKE ASSY AT STA. 520 BELOW FLOORBOARD 231UF REMOVED REF SRM 51-40-02. L/H BREAK ASSY AT STA. 520 BELOW FLOOR BOARD 231UF REMOVED REF SRM 51-40-02. REPLACED L/H BRAKE ASSY AT STA. 520 ON EXPANTION AREA PER SRM 51-40-02.

Part: SIGN — DETACHED (CABIN) · airframe 23,746 hrs · 11,161 cycles

OVERWING EXIT SIGN MID CABIN IS MISSING. INSTALLED OVERWING EXIT SIGN @ MID CABIN?S AFT FACING & FWD FACING COVER PER S.I.P.

Part: BATTERY PACK — INOPERATIVE (L2 DOOR) · airframe 23,387 hrs · 10,968 cycles

L2 OVER DOOR EXIT SIGN; L2 ESCAPE SLIDE LIGHT; AFT CABIN LOCATOR SIGN; AND 2 AFT CABIN AISLE LIGHTS INOP. / [01] R/R BATTERY PACK AT POWER SUPPLY M1673. REF AMM 33-51-06. OPS CHK OK.

Part: SIGN — MISSING (PAX CABIN) · airframe 22,915 hrs · 10,715 cycles

MISSING OVERHEAD EXIT SIGN ABOVE EXIT ROWS / [01] REPLACED MISSING EXIT SIGN LENS IAW AMM 33-51-04

Part: STRIP — LOOSE (L/H CABIN) · airframe 21,404 hrs · 9,878 cycles

FLOOR ILLUMINATION STRIP AT SEAT 12C LOOSE / [01] RE-INSTALLED FLOOR STRIP AT SEAT 12C PER SIP

Part: BATTERY PACK — INOPERATIVE (CABIN) · airframe 20,443 hrs · 9,348 cycles

EMERGENCY WXIT LIGHT BATTERY PACK M2816 IS DEAD ; / [01] REPLACED FWD M2816 EMERGENCY LIGHT BATTERY PACK IAW AMM 33-51-06-960-805. TESTS GOOD; [02] VERIFIED STEP 1<BR>C/W

Part: FAIRING — CRACKED (LT WING TE FLAP) · airframe 20,443 hrs · 9,348 cycles

#3 FLAP TRACK FAIRING 542BB FORWARD OUTBOARD EDGE CRACKED. ; / [01] EVALUATED AND FOUND FWD O/B EDGE CRACKED AS MARKED. TAP TEST GOOD AROUND DAMAGE. FOUND TO BE REPAIRABLE IAW SRM 57-53-70-2R-4 REPAIR 4 TABLE 201 AND SRM 51-70-04-2R-10.<BR><BR>CLEANED AND PREPPED IAW SRM 51-70-04-2R-10 STEP 4 A-C AND SRM 51-70-04-2R-0 REPAIR GENERAL STEP A-B; D-E.<BR><BR>VERIFIED MATERIAL IAW SRM 51-70-04-2R-0 REPAIR GENERAL TABLE 203. FABRIC (A10273); RESIN (A41789).<BR><BR>BONDED REPAIR IAW SRM 51-70-04-2R-10 STEP 4 D-G. CURED AT 200 DEGREES (AAR 30347 EXP 4-29-22). TAP TEST GOOD.<BR><BR>REQUESTING OK TO APPLY DECORATIVE FINISH; [02] STEP 1 OK. OK TO PAINT; [03] APPLIED DECORATIVE FINISH IAW AMM 51-21-99-300-801 TABLE 701. PAINT (A99201); [04] REPAIRED AND APPLIED DECORATIVE FINISH ON #3 FLAP TRACK FAIRING 542BB FWD O/B EDGE IAW SRM 51-70-04-2R-10; SRM 51-70-04-2R-0 REPAIR GENERAL AND AMM 51-21-99-300-801.; [05] STEP 3 AND 4 OK

Part: NONE — CRACKED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO FLOOR STRUCTURE; BAFFLE/INTERCOSTAL AT STATION 500H INBOARD SIDE SUPPORT CLIP CRACKED. DOT 234/10 ; / [01] DRILLED AND REMOVED CRACKED R/H STA500H CLIP IAW SRM 51-40-02-0G-0; [02] VERIFIED NEW CLIP STA 500H R/H SIDE AS P/N 143A7502-158 IAW BOEING DWG 143A7505 REV:-; [03] 'A' TAG NUMBER 'A' 573 FOR STEP 2 ABOVE CLIP P/N 143A7502-158; [04] VERIFIED STEP 2 AND 3; [05] LOCATED AND DRILLED NEW R/H STA 500H CLIP IAW SRM 51-40-05-0G-0; [06] INSPECTION CW STEP 5; [07] OK TO INSTALL; [08] INSTALLED NEW R/H STA500H CLIP IAW SRM 51-40-02-0G-0 ALSO BOEING DWG 143A7505 REV:-; [09] CLIP IS INSTALLED AND APPLIED CIC TO AREA IAW AMM 51-21-91-701; [10] RII CW; [11] STEP 8 -9 INSPECTION CW

Part: NONE — CRACKED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO FLOOR STRUCTURE; BAFFLE /INTERCOSTAL AT STATION 500H; LEFT SIDE; CLIP CRACKED ON FWD SIDE OF FRAME. DOT 234/11 ; / [01] DRILLED AND REMOVED CLIP STA 500H L/H SIDE IAW SRM 51-40-02-0G-0; [02] VERIFIED NEW CLIP AS P/N 143A7502-159 'A' TAG A66315 IAW BOEING DWG 143A7505 REV:-; [03] INSPECTION VERIFIED STEP 2; [04] LOCATED AND DRILLED NEW L/H SIDE STA 500H CLIP IAW SRM 51-40-05-0G-0; [05] VERIFIED STEP 4<BR><BR>OK TO INSTALL; [06] INSTALLED NEW CLIP AT STA 500H L/H SIDE IAW SRM 51-40-02-0G-0 ALSO BOEING DWG 143A7505 REV:-; [07] CLIP INSTALLATION IS COMPLETED APPLIED CIC TO AREA IAW AMM 51-21-91-701; [08] RII CW; [09] INSPECTION CW STEPS 6-7

Part: ANGLE — CRACKED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A-061 DOT 003 AFT CARGO PIT WASTE TANK ENCLOSURE VERTICAL BEAM AT STA 847+18' LBL 10 LOWER ATTACH ANGLE CRACKED ; / [01] REMOVED CRACKED CLIP IAW SRM 51-40-02.; [02] LOCATED/DRILLED NEW CLIP; 149A8109U114; IAW SRM 51-40-05. A TAG # A94253.; [03] OK TO INSTALL CLIP 149A8109U114.; [04] VERIFIED STEPS 1-3. OK TO INSTALL CLIP; [05] INSTALLED NEW CLIP; 149A8109U114; IAW BOEING DWG# 149A8109 REV. B & SRM 51-40-02.; [06] APPLIED CIC IAW AMM 51-21-91.; [07] REMOVED AND REPLACED LOWER CLIP AT VETICAL BEAM; STA 847+18 LBL 10; IAW SRM 51-40-02 & DWG # 149A8109 REV. B.; [08] VERIFIED STEPS 5-7<BR>AUDIT C/W

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO BAY RT Z-ANGLE CORRODED AROUND FASTNER HOLES BS 500E-500G, RBL 25, WL 158. BEGAN REMOVING CORROSION ON THE Z ANGLE, ORIGINAL .040' LOSS OF .008' REMAINING .032', FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. ALL WORK FOR FWD CARGO COMPARTMENT RH Z-ANGLE REPLACEMENT FROM BS 500A-500I AT RBL 25 WL 158 WAS ACCOMPLISHED ON FAULT TTG8Q009CUJ0.

Part: SHIELD — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.RH FLOOR SHIELD CORRODED AROUND FASTNER HOLES STA.500-500A RBL25 WL.158. BEGAN REMOVING CORROSION ON SPLASH SHIELD AT STA 500 TO 500A; RBL 25 AND WL 158; ORIGINAL .032' LOSS OF .007' REMAINING .025' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. REMOVED DAMAGED SHIELD AT FWD CARGO R/H SIDE BS 500 - 500A IAW SRM 51-40-02-0G-O. LOCATED AND DRILL ALL FASTENER HOLES ALSO INSTALLED NEW NUTPLATES INTO NEW FLOOR SHIELD IAW SRM 51-40-05-0G-0 ALSO BOEING DWG 143A0080 REV:- INSPECTION CW STEP 7. INSTALLED NEW R/H SIDE FWD PIT AFT OF DR SHIELD IAW SRM 51-40-02-0G-0 ALSO DWG 143A0080 REV-.

Part: SHIELD — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.RH FLOOR SHIELD CORRODED AROUND FASTNER HOLES STA.500-500A RBL25 WL.158 ; / [01] BEGAN REMOVING CORROSION ON SPLASH SHIELD AT STA 500 TO 500A; RBL 25 AND WL 158; ORIGINAL .032' LOSS OF .007' REMAINING .025' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [02] INSPECTION VERIFIED STEP 1; [03] REMOVED DAMAGED SHIELD AT FWD CARGO R/H SIDE STA 500 TO STA 500A IAW SRM 51-40-02-0G-O; [04] INSPECTION VERIFIED REMOVAL; [05] VERIFIED NEW FWD CARGO R/H AFT OF DR SHIELD AS P/N 143A8126-38 'A 'TAG AP6360 IAW BOEING DWG 143A0080 REV:-; [06] VERIFIED STEP 5; [07] LOCATED AND DRILL ALL FASTENER HOLES ALSO INSTALLED NEW NUTPLATES INTO NEW FLOOR SHIELD IAW SRM 51-40-05-0G-0 ALSO BOEING DWG 143A0080 REV:-; [08] INSPECTION CW STEP 7; [09] OK TO INSTALL; [10] INSTALLED NEW R/H SIDE FWD PIT AFT OF DR SHIELD IAW SRM 51-40-02-0G-0 ALSO BOEING DWG 143A0080 REV:-; [11] INSPECTION CW STEP 10; [12] RII REQUIREMENTS CW; [13] VERIFIED ALL STEPS COMPLETE

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-93 A113-93 AFT CARGO COMPARTMENT STA 727I TO STA 727J R/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW SRM 51-10-02-0G-0. FOUND ORIGINAL THICKNESS .040'; LOSS .015' REMAINING MATERIAL .025' AROUND FASTENER HOLES; OUT OF LIMITS IAW SRM 53-00-53-1A-2.; [02] ALL WORK FOR REPLACEMENT OF RH Z-ANGLE FROM BS 727G + 10' - BS 767 ACCOMPLISHED ON FAULT TTG 8Q009CUBC. IAW SRM 53-00-53-2R-5; [03] INSPECTION VERIFIED STEP 2. AUDIT CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-86 AFT CARGO COMPARTMENT STA 747 TO STA 767 R/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW SRM 51-10-02-0G-0. FOUND ORIGINAL THICKNESS .040'; LOSS ..016' REMAINING MATERIAL .024' AROUND FASTENER HOLES; OUT OF LIMITS IAW SRM 53-00-53-1A-2.; [02] C/W; [03] VERIFIED MATERIAL FOR Z-ANGLE AS BAC1496-377 7075T6 ATAG A80775 IAW SRM 53-00-53-2R-5.; [04] LOCATED AND DRILLED AND FABRICATED NEW Z-ANGLE IAW SRM 53-00-53-2R-5.; [05] VERIFIED ITEMS 3 AND 4 (-1 ZEE CHANNEL SIDE PLATE AND -2 SPLICE SIDEPLATE <BR><BR>OK TO TREAT AND PRIME REPAIR PARTS; [06] TREATED AND PRIMED RH Z-ANGLE IAW AMM 51-21-72-370-804.; [07] INSPECTION CW STEP 6; OK TO INSTALL; [08] INSTALLED Z-ANGLE RH SIDE AT RBL 22 BS 727G + 10' - 767 IAW SRM 53-00-53-2R-5 REPAIR 5; AND BOEING DWG 146A7500 REV-. ID 225-226.<BR>ALL STEPS 1-8 COMPLETE.; [09] INSPECTION CW STEP 8; [10] OK TO CIC; [11] CIC RH Z-ANGLE FROM BS 727G-767 AT RBL 22; IAW AMM 51-21-91-620-802.; [12] INSPECTION CW STEP 11; [13] RII INSPECTION CW; [14] AUDIT CW; [15] CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-91 AFT CARGO COMPARTMENT STA 727I TO STA 727J L/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW B737 SRM 51-10-02-OG 0; [02] ORIGINAL .040' LOSS .011' REM .029'; OUT OF LIMITS I/A/W SRM 53-00-53-1A-1 FIG 103 VIEW A-A. TOOL# 36649 DUE 12AUG22; [03] CONCUR; [04] NEED TO ADD MEASURMENTS; [05] REM0VED L/H Z ANGLE STA. 727H +10-787+10IAW B737 SRM 53-00-53-2R-5 REPAIR 5; [06] MATERIAL FOR REPAIR VERIFIED ASBAC1496-377-7075-T62 IAW B737 SRM 53-00-53-2R-5 REPAIR 5. TABLE 201. A TAG #A35899; [07] VERIFIED STEP 5 AND 6; [08] LOCATED AND DRILLED REPAIR PARTS IAW B737 SRM 53-00-53-2R-5 REPAIR 5; [09] INSPECTION CW STEP 8; [10] OK TO TREAT AND PRIME; [11] TREATED AND PRIMED REPAIR PARTS IAW B737 ARM 53-00-53-2R-5 REPAIR 5. AND B737 AMM 51-21-72-37-801; [12] INSPECTION CW STEP 11; [13] OK TO CIC; [14] APPLIED CIC TO LOWER SURFACE OF ANGLE IAW B737 AMM 51-21-91-620-802; [15] VERIFIED STEP 14<BR><BR>OK TO INSTALL; [16] INSTALLED REPAIR PARTS IAW B737 ARM 53-00-53-2R 5 REPAIR 5; [17] VERIFIED STEP 16<BR><BR>OK TO CIC; [18] APPLIED CIC TO ANGLE IAW B737 AMM 51-21-91-620-802; [19] INSPECTION CW STEP 18; [20] RII REQUIREMENTS CW; [21] AUDIT CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.AFT BULKHEAD BOTTOM ANGLE CORRODED STA.500I LBL25-RBL25 WL 158 #185-011 ; / [01] BEGAN REMOVING CORROSION ON FWD PIT; AFT BH LOWER SUPPORT ANGLE; ORIGINAL .071' LOSS OF .027' REMAINING .044'; MIN ALLOWED .056' FOUND OUT OF LIMITS IAW SRM 53-30-08-1A-1. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [02] INSPECTION VERIFIED STEP 1; [03] REMOVED AFT BH LOWER SUPPORT ANGLE IAW B737 SRM 51-40-02-0G-0; [04] VERIFIED NEW FWD PIT AFT LOWER BULKHEAD ANGLE AS P/N 143A9485 -35 'A'TAG WN8761 IAW BOEING DWG 143A9481 REV:-; [05] VERIFIED STEP 4; [06] LOCATED AND DRILLED NEW FLOOR BULKHEAD ANGLE IAW SRM 51-40-05-0G-0 ALSO BOEING DWG 143A9481 REV:-; [07] OK TO INSTALL; [08] INSTALLED NEW BULKHEAD ANGLE FOR FWD PIT IAW SRM 51-40-02-0G-0 ALSO BOEING DWG 143A9481 REV:-; [09] INSPECTION CW STEP 8; [10] OK TO CIC; [11] COMPLETED INSTALL OF ANGLE AND APPLIED CIC IAW AMM 51-21-91-701; [12] INSPECTION CW STEP 11. AUDIT CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.RH Z-ANGLE CORRODED AROUND FASTNER HOLES STA.500G-500I RBL 25 WL 158 #185-010 ; / [01] BEGAN REMOVING CORROSION ON RH Z ANGLE AT STA 500G TO 500I RBL 25 AND WL 158; ORIGINAL .040' LOSS OF .007' REMAINING .033' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22;[16] INSTALLED -2 SPLICE PLATE TO Z ANGLE IAW B737 SRM 53-00-53-2R-5; [17] -2 SPLICE PLATE RII INSP C/W; [18] OK TO CIC; [19] OK TO INSTALL REPAIR PARTS IN AIRCRAFT REF STEP 4; [20] BEGIN INSTALLING RH Z-ANGLE STA 500A-500I IAW SRM 51-40-02.; [21] INSTALLED RH Z-ANGLE STA 500A-500I IAW SRM 51-40-02 AND 143A7500 TY:DWG ID:0083 REV:-; [22] INSTALLED FASTENERS IN AFT RH SUPPORT ANGLE; THAT WERE DISPLACED IN ITEM 3; IAW B737 SRM 51-40-02-0G-0; AND BOEING DWG 143A9481.<BR>ALL STEPS 1-22 COMPLETED.; [23] VERIFIED STEPS 20. AND 21.; [24] VERIFIED STEP 22.<BR>AUDIT C/W

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.LH Z-ANGLE CORRODED AROUND FASTNER HOLES STA.500H-500I LBL25 WL158 #185-012 / [01] BEGAN REMOVING CORROSION ON LH Z ANGLE AT STA 500H-500I LBL 25 AND WL 158; ORIGINAL .040' LOSS OF .005' REMAINING .035' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [02] INSPECTION VERIFIED STEP 1; [03] REMOVED Z-ANGLE ON LEFT SIDE; STA 500D+10 TO STA 500I; IAW SRM 51-40-02.; [04] VERIFY MATERIAL FOR REPAIR SPLICE; AND REPLACEMENT SECTION OF Z-ANGLE FOR STA 500D + 10' TO STA 500I TO BE BAC1496-444 7075-T62 ATAG # A67396 IAW SRM 53-00-53-2R-5 REPAIR 5 TABLE 201.; [05] STEP 4 OK; [06] FABRICATED; LOCATED AND DRILLED REPLACEMENT 'Z' CHANNEL SIDEPLATE AND REPAIR SPLICE IAW SRN 53-00-53-2R-5 REPAIR 5 FIG 202.; [07] STEP 6 OK. OK TO TREAT AND FIND; [08] STEP 6 OK. OK TO TREAT AND PRIME; [09] TREATED AND PRIMED REPAIR PARTS I/A/W SRM 53-00-53-2R-5 STEPS I AND J; [10] VERIFIED TREAT AND PRIME<BR><BR>OK TO INSTALL SPLICE; NOT PLATES AND CIC; [11] INSTALLED SPLICE PLATE; INSTALLED NUT PLATES; AND APPLIED CIC TO Z-ANGLE IAW SRM 53-00-53-2R-5 REPAIR 5.; [12] ISPECTION CW STEP 11; [13] INSPECTION CW STEP 11; [14] NEED OK TO INSTALL NEW SIDE PLATE - Z-ANGLE STA500D TO STA 500I; [15] OK TO INSTALL Z-ANGLE; [16] COMPLETED INSTALL OF NEW Z-ANGLE L/H SIDE STA 500D TO STA 500I IAW SRM 51-40-02-0G-0 ALSO SRM 53-00-53-2R-5 APPLIED CIC TO AREA IAW AMM 51-21-91-701; [17] VERIFIED STEP 16.; [18] AUDIT C/W

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.RH Z-ANGLE CORRODED AROUND FASTNER HOLES STA.500B-500C RBL 25 WL 158 ; / [01] BEGAN REMOVING CORROSION ON RH Z ANGLE AT STA 500B-500C RBL 25 AND WL 158; ORIGINAL .029' LOSS OF .011' REMAINING .029' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [02] INSPECTION VERIFIED STEP 1; [03] ALL WORK FOR FWD CARGO COMPARTMENT RH Z-ANGLE REPLACEMENT FROM BS 500A-500I AT RBL 25 WL 158 WAS ACCOMPLISHED ON FAULT TTG8Q009CUJ0; [04] VERIFIED STEP 3.<BR>AUDIT C/W

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.LH Z-ANGLE CORRODED AROUND FASTNER HOLES STA.500E-500D LBL25 WL158 #185-013 ; / [01] BEGAN REMOVING CORROSION ON L/H Z ANGLE AT STA 500D TO STA 500E; LBL 25 AND WL 158; ORIGINAL .040' LOSS OF .010' REMAINING .030' FOUND TO BE OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [02] INSPECTION CW STEP 1; [03] REMOVED DAMAGED SECTION OF Z-ANGLE FROM STA 500D+10 TO 500I IAW SRM 51-40-02.; [04] ALL MAINTENANCE COMPLETED ON JOB CARD 42981-1400-0039; [05] Z-ANGLE IS COMPLETED; APPLIED CIC TO AREA IAW AMM 51-21-91-701 JOB CARD 42981-1400-0039 ANDTTG8Q009CUK7; [06] VERIFIED STEPS 4. AND 5.; [07] AUDIT C/W

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-94 AFT CARGO COMPARTMENT STA 727H TO STA 727I L/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW B737 SRM 51-10-02-OG-0; [02] ORIGINAL .040' LOSS .008' REM .032'; OUT OF LIMITS I/A/W SRM 53-00-53-1A-1 FIG 103 VIEW A-A. TOOL# 36649 DUE 12AUG22; [03] CONCUR; [04] Z ANGLE REPAIRED ON FAULT TTG8Q009CVDM; [05] INSPECTION CONFIRMED. AUDIT CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-85 AFT CARGO COMPARTMENT STA 767 TO STA 787 L/H Z ANGLE IS CORRODED. ; / [01] REMOVEDCORROSION IAW B737 SRM 5110-02-OG 0; [02] ORIGINAL .040' LOSS .008' REM .032'; OUT OF LIMITS I/A/W SRM 53-00-53-1A-1 FIG 103 VIEW A-A. TOOL# 36649 DUE 12AUG22; [03] CONCUR; [04] Z ANGLE REPAIRED ON FAULT TTG8Q009CVDM; [05] INSPECTION CONFIRMED. AUDIT CW

Part: PANEL — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A125-04 FWD CARGO PANEL 120 DF CORRODED ; PANEL 120DF / [01] BEGAN REMOVING CORROSION ON FWD CARGO FLOOR PANEL 120DF; FOUND OUT OF LIMITS; DAMAGE EXCEEDS MAX LENGTH IAW B737 SRM 53-00-53-1A-1 FIG 102. CORROSION STILL EXISTS; [02] VERIFIED MATERIAL FOR FWD CARGO FLOOR PANEL 120DF AS 2024 T3 .071''; ATAG A104323 IAW B737 AMM 25-52-01-201-801; [03] VERIFIED STEPS 1 AND 2 C/W; [04] FABRICATED NEW FWD CARGO FLOOR PANEL 120DF IAW B737 AMM 25-52-01-201-801; [05] VERIFIED STEP 4.<BR>OK TO TREAT AND PRIME; [06] TREATED AND PRIMED LOWER SURFACE OF FWD CARGO FLOOR PANEL 120DF IAW B737 AMM 51-21-41-370-803 AND B737 AMM 51-21-72-370-804; [07] ALL WORK C/W<BR>AUDIT C/W

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-87 A113-87 AFT CARGO COMPARTMENT STA 747 TO STA 767 L/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW B737 SRM 51-10-02-OG-0; [02] ORIGINAL .040' LOSS .009' REM .031'; OUT OF LIMITS I/A/W SRM 53-00-53-1A-1 FIG 103 VIEW A-A. TOOL# 36649 DUE 12AUG22; [03] CONCUR; NEED MEASUREMENTS ADDED; [04] Z ANGLE REPAIRED ON FAULTTTG8Q009CVDM; [05] INSPECTION CONFIRMED; [06] AUDIT CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-85 AFT CARGO COMPARTMENT STA 767 TO STA 787 L/H Z ANGLE IS CORRODED. ; / [01] REMOVEDCORROSION IAW B737 SRM 5110-02-OG 0; [02] ORIGINAL .040' LOSS .008' REM .032'; OUT OF LIMITS I/A/W SRM 53-00-53-1A-1 FIG 103 VIEW A-A. TOOL# 36649 DUE 12AUG22; [03] CONCUR; [04] Z ANGLE REPAIRED ON FAULT TTG8Q009CVDM; [05] INSPECTION CONFIRMED. AUDIT CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.RH Z-ANGLE CORRODED AROUND FASTNER HOLES STA.500C-500E RBL 25 WL 158 #185-008 ; / [01] BEGAN REMOVING CORROSION ON RH Z ANGLE AT STA 500B-500C RBL 25 AND WL 158; ORIGINAL .040' LOSS OF .011' REMAINING .029' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [02] BEGAN REMOVING CORROSION ON RH Z ANGLE AT STA 500C-500E RBL 25 AND WL 158; ORIGINAL .040' LOSS OF .011' REMAINING .029' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [03] INSPECTION VERIFIED STEPS 1-2

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-90 AFT CARGO COMPARTMENT STA 72J7 +14' R/H Z ANGLE IS CORRODED. ; / [01] REMOVED CORROSION IAW SRM 51-10-02-0G-0. FOUND ORIGINAL THICKNESS .040'; LOSS .020' REMAINING MATERIAL .020' AROUND FASTENER HOLES; OUT OF LIMITS IAW SRM 53-00-53-1A-2.; [02] ALL WORK FOR REPLACEMENT OF RH Z-ANGLE FROM BS 727G + 10' - BS 767 ACCOMPLISHED ON FAULT TTG 8Q009CUBC. IAW SRM 53-00-53-2R-5; [03] INSPECTION VERIFIED STEP 2

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.RH Z-ANGLE CORRODED AROUND FASTNER HOLES STA.500B-500C RBL 25 WL 158. BEGAN REMOVING CORROSION ON RH Z ANGLE, ORIGINAL .029' LOSS OF .011' REMAINING .029' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. ALL WORK FOR FWD CARGO COMPARTMENT RH Z-ANGLE REPLACEMENT FROM BS 500A-500I AT RBL 25 WL 158 WAS ACCOMPLISHED ON FAULT TTG8Q009CUJ0 VERIFIED STEP 3.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.RH Z-ANGLE CORRODED AROUND FASTNER HOLES STA.500C-500E RBL 25 WL 158 #185-008 ; / [01] BEGAN REMOVING CORROSION ON RH Z ANGLE AT STA 500B-500C RBL 25 AND WL 158; ORIGINAL .040' LOSS OF .011' REMAINING .029' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [02] BEGAN REMOVING CORROSION ON RH Z ANGLE AT STA 500C-500E RBL 25 AND WL 158; ORIGINAL .040' LOSS OF .011' REMAINING .029' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [03] INSPECTION VERIFIED STEPS 1-2; [04] ALL WORK FOR FWD CARGO COMPARTMENT RH Z-ANGLE REPLACEMENT FROM BS 500A-500I AT RBL 25 WL 158 WAS ACCOMPLISHED ON FAULT TTG8Q009CUJ0; [05] VERIFIED STEP 4.<BR>AUDIT C/W

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-88 AFT CARGO COMPARTMENT STA 727J TO STA 747 L/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW WITH B737 SRM 51-10-02-OG 0; [02] ORIGINAL .040' LOSS .006' REM .034'; OUT OF LIMITS I/A/W SRM 53-00-53-1A-1 FIG 103 VIEW A-A. TOOL# 36649 DUE 12AUG22; [03] CONCUR; [04] Z ANGLE REPAIRED ON FAULT TTG8Q009CVDM; [05] INSPECTION CONFIRMED

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-87 A113-87 AFT CARGO COMPARTMENT STA 747 TO STA 767 L/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW B737 SRM 51-10-02-OG-0; [02] ORIGINAL .040' LOSS .009' REM .031'; OUT OF LIMITS I/A/W SRM 53-00-53-1A-1 FIG 103 VIEW A-A. TOOL# 36649 DUE 12AUG22; [03] CONCUR; NEED MEASUREMENTS ADDED; [04] Z ANGLE REPAIRED ON FAULTTTG8Q009CVDM; [05] INSPECTION CONFIRMED; [06] AUDIT CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-88 AFT CARGO COMPARTMENT STA 727J TO STA 747 L/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW WITH B737 SRM 51-10-02-OG 0; [02] ORIGINAL .040' LOSS .006' REM .034'; OUT OF LIMITS I/A/W SRM 53-00-53-1A-1 FIG 103 VIEW A-A. TOOL# 36649 DUE 12AUG22; [03] CONCUR; [04] Z ANGLE REPAIRED ON FAULT TTG8Q009CVDM; [05] INSPECTION CONFIRMED

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-95 AFT CARGO COMPARTMENT STA 727H TO STA 727I R/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW SRM 51-10-02-0G-0. FOUND ORIGINAL THICKNESS .040'; LOSS .018' AROUND FASTENER HOLES; OUT OF LIMITS IAW SRM 53-00-53-1A-2.; [02] REMAINING MATERIAL IS .022'; [03] ALL WORK FOR REPLACEMENT OF RH Z-ANGLE FROM BS 727G + 10' - BS 767 ACCOMPLISHED ON FAULT TTG 8Q009CUBC. IAW SRM 53-00-53-2R-5; [04] INSPECTION VERIFIED STEP 3. AUDIT CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A113-86 AFT CARGO COMPARTMENT STA 747 TO STA 767 R/H Z ANGLE HAS SEVERAL AREAS OF CORROSION. ; / [01] REMOVED CORROSION IAW SRM 51-10-02-0G-0. FOUND ORIGINAL THICKNESS .040'; LOSS ..016' REMAINING MATERIAL .024' AROUND FASTENER HOLES; OUT OF LIMITS IAW SRM 53-00-53-1A-2.; [02] C/W; [03] VERIFIED MATERIAL FOR Z-ANGLE AS BAC1496-377 7075T6 ATAG A80775 IAW SRM 53-00-53-2R-5.; [04] LOCATED AND DRILLED AND FABRICATED NEW Z-ANGLE IAW SRM 53-00-53-2R-5.; [05] VERIFIED ITEMS 3 AND 4 (-1 ZEE CHANNEL SIDE PLATE AND -2 SPLICE SIDEPLATE <BR><BR>OK TO TREAT AND PRIME REPAIR PARTS; [06] TREATED AND PRIMED RH Z-ANGLE IAW AMM 51-21-72-370-804.; [07] INSPECTION CW STEP 6; OK TO INSTALL; [08] INSTALLED Z-ANGLE RH SIDE AT RBL 22 BS 727G + 10' - 767 IAW SRM 53-00-53-2R-5 REPAIR 5; AND BOEING DWG 146A7500 REV-. ID 225-226.<BR>ALL STEPS 1-8 COMPLETE.; [09] INSPECTION CW STEP 8; [10] OK TO CIC; [11] CIC RH Z-ANGLE FROM BS 727G-767 AT RBL 22; IAW AMM 51-21-91-620-802.; [12] INSPECTION CW STEP 11; [13] RII INSPECTION CW; [14] AUDIT CW; [15] CW

Part: ANGLE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

FWD CARGO COMP.RH Z-ANGLE CORRODED AROUND FASTNER HOLES STA.500E-500G RBL 25 WL 158 #185-009 ; / [01] BEGAN REMOVING CORROSION ON RH Z ANGLE AT STA 500E TO 500G RBL 25 AND WL 158; ORIGINAL .040' LOSS OF .008' REMAINING .032' FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-2. CORROSION STILL EXISTS. TOOLING 36646 CAL DUE 10-06-22; [02] INSPECTION VERIFIED STEP 1; [03] ALL WORK FOR FWD CARGO COMPARTMENT RH Z-ANGLE REPLACEMENT FROM BS 500A-500I AT RBL 25 WL 158 WAS ACCOMPLISHED ON FAULT TTG8Q009CUJ0.; [04] VERIFIED STEP 3.<BR>AUDIT C/W

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A125-04 FWD CARGO FLOOR PANEL 120DF CORRODED ; / [01] REMOVED CORROSION ON PANEL 120DF IAW SRM 51-10-02. PANEL IS OUT OF LIMITS IAW SRM 53-00-53-1A-1 FIGURE 102. EXCEDES MAXIMUM LENGTH DAMAGE.; [02] INSPECTION VERIFIED OUT OF LIMITS; [03] MATERIAL VERIFIED TO BE 2024-T3-.071 A# A84102; [04] VERIFIED MATERIAL IN ITEM 3 IS CORRECT; [05] FABRICATED NEW FLOOR PANEL 140DF; [06] C/W FABRICATION INSP. PANEL 120DF<BR>OK TO TREAT AND PRIME; [07] FABRICATED NEW FLOOR PANEL 120DF; [08] FABRICATED NEW FLOOR BOARD PANEL 120DF IAW AMM 25-52=01-201-801. TREATED AND PRIMED IAW AMM 51-21-72; [09] FINAL INSP C/W<BR>AUDIT C/W

Part: PANEL — CORRODED (AFT CARGO) · airframe 20,443 hrs · 9,348 cycles

A113-76 AFT CARGO COMPARTMENT PANEL 140BF EDGES HAVE CORROSION. ; / [01] CORROSION FOUND TO BE LONGER THAN 20IN & DEEPER THAN .10IN OUT OF LIMITS.; [02] INSPECTION VERIFIED LONGER THAN 20 IN.; [03] MATERIAL VERIFIED TO BE 2024-T3-.071 IAW AMM 25-52-01-201-801 A TAG #A84103; [04] CERTIFIED WORK PERFORMED ON STEPS 1 & 3; [05] INSPECTION VERIFIED STEPS 3-4; [06] FABRICATED NEW AFT CARGO FLOOR PANEL 140 BF IAW AMM 25-52-01-201-801; [07] VERIFIED STEP 6<BR><BR>OK TO TREAT AND PRIME; [08] TREATED AND PRIMED FLOOR PANEL 140BF IAW AMM 25-52-01-201-801. ALL STEPD COMPLETE 1-8.; [09] INSPECTION CW STEP 6; AUDIT CW

Part: FLOORBOARD — CORRODED (AFT CARGO) · airframe 20,443 hrs · 9,348 cycles

AFT CARGO COMPARTMENT FLOORBOARD 140EF L/H EDGE HAS SIGNS OF CORROSION. CORROSION FOUND TO BE LONGER THAN 20IN & DEEPER THAN .10IN OUT OF LIMITS. ALL WORK FOR AFT PIT FLOOR PANEL 140EF FABRICATION WAS ACCOMPLISHED ON TTG8Q009C1DC.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A125-03 FWD CARGO FLOOR PANEL 120CF CORRODED. REMOVED CORROSION ON PANEL 120CF IAW SRM 51-10-02. PANEL IS OUT OF LIMITS IAW SRM 53-00-53-1A-1 FIGURE 102. EXCEDES MAXIMUM LENGTH DAMAGE. INSPECTION VERIFIED OUT OF LIMITS IAW SRM 53-00-53-1A-1 STEP C. TRIMMED NEW FLOOR PANEL IAW AMM 25-52-01-201-801 STEP F & STARTED TO LOCATE & DRILL IAW SRM 51-40-05. COUNTERSUNK PANEL IAW SRM 51-40-08. TREATED AND PRIMED PANEL IAW AMM 51-21-72.

Part: NONE — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A125-04 FWD CARGO FLOOR PANEL 120DF CORRODED ; / [01] REMOVED CORROSION ON PANEL 120DF IAW SRM 51-10-02. PANEL IS OUT OF LIMITS IAW SRM 53-00-53-1A-1 FIGURE 102. EXCEDES MAXIMUM LENGTH DAMAGE.; [02] INSPECTION VERIFIED OUT OF LIMITS; [03] MATERIAL VERIFIED TO BE 2024-T3-.071 A# A84102; [04] VERIFIED MATERIAL IN ITEM 3 IS CORRECT; [05] FABRICATED NEW FLOOR PANEL 140DF; [06] C/W FABRICATION INSP. PANEL 120DF<BR>OK TO TREAT AND PRIME; [07] FABRICATED NEW FLOOR PANEL 120DF; [08] FABRICATED NEW FLOOR BOARD PANEL 120DF IAW AMM 25-52=01-201-801. TREATED AND PRIMED IAW AMM 51-21-72; [09] FINAL INSP C/W<BR>AUDIT C/W

Part: PANEL — CORRODED (FUSELAGE) · airframe 20,443 hrs · 9,348 cycles

A125-03 FWD CARGO FLOOR PANEL 120CF CORRODED ; / [01] REMOVED CORROSION ON PANEL 120CF IAW SRM 51-10-02. PANEL IS OUT OF LIMITS IAW SRM 53-00-53-1A-1 FIGURE 102. EXCEDES MAXIMUM LENGTH DAMAGE.; [02] INSPECTION VERIFIED OUT OF LIMITS; [03] VERIFIED MATERIAL 2024-T3-071 IAW SRM 53-00-53-1A-1 STEP C.; [04] IAW AMM 25-52-01-201-801 STEP C.; [05] A TAG # A104324; [06] VERIFIED STEPS 3. TO 5.; [07] TRIMMED NEW FLOOR PANEL PER SAMPLE IAW AMM 25-52-01-201-801 STEP F AND STARTED TO LOCATE/DRILL IAW SRM 51-40-05.; [08] VERIFIED STEP 7.; [09] COMPLETED LOCATE/DRILL IAW SRM 51-40-05 & COUNTERSUNK PANEL IAW SR. 51-40-08.; [10] OK TO TREAT/PRIME LOWER SURFACE OF PANEL 120CF.; [11] VERIFIED STEP 9 AND 10 C/W<BR><BR>OK TO TREAT AND PRIME; [12] TREATED AND PRIMED PANEL IAW AMM 51-21-72.; [13] PANEL 120CF EXCEDES LENGTH DAMAGE AND IS OUT OF LIMITS IAW SRM 53-00-53-1A-1. FABRICATED NEW PANEL PER SAMPLE IAW AMM 25-52-01-201-801 STEP F; [14] VERIFIED STEPS 12. AND 13.<BR>AUDIT C/W

Part: SIGN — BROKEN (CABIN) · airframe 20,175 hrs · 9,206 cycles

EMERGENCY EXIT SIGN MID-CABIN BROKEN. / REINSTALLED COVERS PER SIP.

Part: LENS — MISSING (CABIN) · airframe 9,091 hrs · 19,952 cycles

CENTER ISLE OVERWING EXIT SIGN LENSE FELL OFF / REINSTALLED LENSE COVER PER SIP OPS CHECK GOOD

Part: LENS — MISSING (CABIN) · airframe 18,176 hrs · 8,160 cycles

MID CABIN AISLE EXIT SIGN MISSING A LENSE / INSTALLED NEW EMER EXIT LENS AT MID CABIN CEILING AFT SIDE REF MM 33-51-01

Part: COVER — DETACHED (EMERGENCY LIGHT) · airframe 18,132 hrs · 8,138 cycles

CENTER AISLE; AFT-FACING OVERHEAD EMERGENCY EXIT SIGN DETACHED / RESECURED CENTER WING AFT EXIT SIGN COVER PER 'SIP'

Part: SKIN — GOUGED (FUSELAGE) · airframe 17,453 hrs · 7,771 cycles

GOUGE IN RIGHT HAND SIDE FUSELAGE AFT OF STATION 727H BETWEEN STRINGERS 25R AND 26R. FOUND TO BE OUT OF LIMITS IN AREA B, PER TABLE 107 PER SRM 53-00-01-1A-5. PERMANENT REPAIR REQUIRED WITHIN 50 FLIGHT HOURS. A/C 8674 IS PRE SERVICE BULLETIN 737-21-1149. REPAIRED DAMAGED SKIN, PER SRM 53-00-01-2R-3 REPAIR 3. FOLLOW UP INSPECTIONS ON SAM 943T, IAW SRM 53-00-01-2R-3 REPAIR 3 TABLE 205. SA-M 326 A1190373 SA-M 943T V012378/V012379.

Part: FAIRING — CRACKED (NR 2 STRUT) · airframe 16,496 hrs · 7,280 cycles

#2 AFT STRUT FAIRING CRACKED ON AFT INBD FITTINGSTOPPED DRILLED CRACK ON #2 AFT STRUT FAIRING ON AFT INBD FITTING PER EA 20-154-01348 INSPECTOR: E40330ACCOMPLISH OPTION 1 OR OPTION 2. OPTION 1: PERFORM 737-800 SRM 54-50-70-2R-6; REPAIR 6 TO REPAIR THE CRACKED FLANGE IF ALL OTHER CRITERIA OF 737-800 SRM 54-50-70-2R-6; REPAIR 6 CAB BE MET. OPTION 2: REPLACE AFT FAIRING TRAILING EDGE ASSY. (P/N: 313A2752-1) OR THE REPLACEMENT PANEL (P/N: 313A2752-2).PERMANENT ACTION REQUIRED. / AFT STRUT FAIRING REPLACED. REFERENCE SA-M 767 H13905; M/M 54-52-04 AND SRM 51-40-02

Part: FAIRING — CRACKED (NR 2 STRUT) · airframe 16,465 hrs · 7,264 cycles

#2 AFT STRUT FAIRING CRACKED ON AFT INBD FITTING / STOPPED DRILLED CRACK ON #2 AFT STRUT FAIRING ON AFT INBD FITTING PER EA 20-154-01348

Part: SIGN — MISSING (CABIN) · airframe 15,596 hrs · 6,838 cycles

EMERGENCY EXIT SIGN (MID CABIN) MISSING RE-INSTALLED EMERGENCY EXIT SIGN IAW AMM 33-51-03

Part: LENS — DETACHED (EMERGENCY LIGHT) · airframe 14,679 hrs · 6,437 cycles

MID CABIN CEILING EMERGENCY LIGHT LENS CAME OFF. / SECURED LENS PER SIP.

Part: LENS — LOOSE (EMERGENCY LIGHT) · airframe 13,967 hrs · 6,137 cycles

EMERGENCY EXIT LIGHT LENS FACING AFT, OVER CENTER ISLE IN CABIN DETACHED. SECURED LENS PER AMM.

Part: GIRT BAR — MISSING (R2 DOOR) · airframe 13,165 hrs · 5,761 cycles

R2 DOOR GIRT BAR STOP MISSING. INSTALLED GIRT BAR PER AMM.

Part: LENS — LOOSE (EMERGENCY LIGHT) · airframe 12,708 hrs · 5,561 cycles

MID CABIN OVERHEAD EXIT LIGHT LENS LOOSE. / REINSTALLED LENS IAW SIP AND AMM.

Part: COVER — UNSECURE (CABIN) · airframe 12,559 hrs · 5,494 cycles

LT EMERGENCY EXIT LIGHT COVER CAME OFF EXIT ROW. REINSTALLED COVER PER AMM.

Part: LENS — UNSECURE (EXIT SIGN) · airframe 10,925 hrs · 4,764 cycles

MID CABIN CEILING EMERGENCY EXIT SIGN FELL OUT. SECURED LENS PER SIP.

Part: LENS — MISSING (EXIT SIGN) · airframe 10,058 hrs · 4,368 cycles

FORWARD OVERWING CEILING EXIT SIGN LENS MISSING. INSTALLED LENS IAW SIP.

Part: FLASHLIGHT ASSY — INOPERATIVE (AFT CABIN) · airframe 8,732 hrs · 3,800 cycles

AFT EMERGENCY FLASHLIGHT INOPERATIVE. R & R THE FLASHLIGHT ASSY IAW MM.

Part: SWITCH — INOPERATIVE (BOOST PUMP) · airframe 8,206 hrs · 3,576 cycles

LEFT WING FUEL IMBALANCE IN FLIGHT. DECLARED AN EMERGENCY. FOUND CENTER TANK FUEL PUMP INOPERATIVE. R & R THE CENTER LT BOOST PUMP SWITCH IAW AMM.

Part: SEAL — CRACKED (HORIZONTAL STAB) · airframe 6,584 hrs · 2,856 cycles

LEFT HORIZONTAL STABILIZER UPPER SLIDING SEAL CRACKED / REMOVED AND REPLACED LEFT HORIZONTAL STABILZER UPPER SLIDING SEAL PER AMM CH. 53-31-31.AMT 114914INSP 49017

Part: BRACKET — CRACKED (LEFT WING) · airframe 6,584 hrs · 2,856 cycles

LT WING T/E UPPER FIXED PANEL AFT OF #1 PYLON; HAS A CRACKED SUPPORT BRACKET / R&R LT WING T/E UPPER FIXED PANEL AFT OF #1 PYLON SUPPORT BRACKET IAW SRM 51-40-02AMT 98409INSP 27721

Part: SUPPORT BRACKET — CRACKED (LT WING) · airframe 6,299 hrs · 2,740 cycles

LT WING TRAILING EDGE UPPER FIXED PANEL AFT OF NR 1 PYLON SUPPORT BRACKET CRACKED. R&R BRACKET IAW SRM.

Part: LIGHT — INOPERATIVE (ROW 15) · airframe 5,905 hrs · 2,572 cycles

L/H OVERWING EMERGENCY EXIT LIGHT INOP AT ROW 15. R & R LIGHT ASSEMBLY IAW MM.

Part: GLOWSTRIP — DAMAGED (CABIN) · airframe 4,725 hrs · 2,086 cycles

FORWARD RT PHOTO LUMINESCENT TRACK LIGHT STRIP DAMAGED. R&R STRIP IAW AMM.