N783SW

Part: SLIDE — OUT OF POSITION · airframe 71,258 hrs · 42,265 cycles

STBD AFT A/C SERVICE DOOR SLIDE PULL HANDLE VISIBLE AND EXPOSED WHEN DOOR IS ARMED. REPOSITIONED MANUAL HANDLE COVER FOR AFT SERVICE DOOR ESCAPE SLIDE IAW AMM 25?66-01. OPS CHECKS NORMAL.

Part: FLASHLIGHT — INOPERATIVE (FWD GALLEY) · airframe 70,882 hrs · 42,038 cycles

FA FOUND FWD GALLEY UPPPER EMER FLASHLIGHT NOT BLINKING / [01] R&R EMER FLASHLIGHT PER AMM 25-64-00

Part: SLIDE — LOW (FWD SERVICE DOOR) · airframe 70,431 hrs · 41,748 cycles

FORWARD RIGHT SERVICE DOOR SLIDE INDICATOR GAUGE SHOWING LOW. SLIDE PART REQUEST IS BUILT INTO THE SUBTASK / [01] R&R?D FWD SERVICE (R1)DOOR EMERGENCY ESCAPE SLIDE PER MT 725-61-06-FS

Part: SUPPORT ANGLE — CRACKED (RH WING) · airframe 69,590 hrs · 41,192 cycles

RIGHT WING TRAILING EDGE DEFLECTION CONTROL RIB PANEL SEAL SUPPORT ANGLE CRACKED AT WEB ATTACH POINT. REMOVED DAMAGE SEAL SUPPORT ANGLE AT R/H WING TRAILING EDGE DEFLECTION CONTROL PANEL PER REF B737-700 SRM 51-40-02-0G-0. LOCATED AND DRILLED NEW PART WEB ANGLE AT R/H WING TRAILING EDGE PER B-737-700 REF SRM 51-40-05-0G-0; TREATED AND PRIMED HOLES PER B-737-700 REF SRM 51-21-41-370-802 AND 51-21-72-370-804. NEW SEAL SUPPORT ANGLE.INSTALLED WEB ANGLE AT R/H WING TRAILING EDGE DEFLECTION CONTROL RIB PANEL SEAL SUPPORT PER B-737-700 REF SRM 51-40-02-0G-0. REMOVED AND INSTALLED SEAL SUPPORT ANGLE AT R/H WING TRAILING EDGE DEFLECTION CONTROL PANEL PER REF B737-700 SRM 51-40-02-0G-0.

Part: SUPPORT ANGLE — CRACKED (LH WING) · airframe 69,590 hrs · 41,192 cycles

LEFT WING DEFLECTION CONTROL RIB PANEL VERTICAL SEAL SUPPORT ANGLE CRACKED AT THE FORWARD SIDE OF WEB. / [01] REMOVED AND REPLACED SEAL SUPPORT ANGLE AT FWD SIDE OF WEB ON L/W DEFLECTION CONTROL PANEL PER REF B737-700 SRM 51-40-02-0G-0.;[02] VERIFIED STEP 1.

Part: WEB — CRACKED (RH WING) · airframe 69,590 hrs · 41,192 cycles

RIGHT WING TRAILING EDGE DEFLECTION CONTROL RIB PANEL SUPPORT WEB CRACKED AT OUTBOARD ATTACH FASTENER HOLE. REMOVED DAMAGE WEB ANGLE AT R/H WING TRAILING EDGE DEFLECTION CONTROL PANEL PER REF B737-700 SRM 51-40-02-0G-0. LOCATED AND DRILLED NEW PART WED ANGLE AT R/H WING TRAILING EDGE PER B-737-700 REF SRM 51-40-05-0G-0; TREATED AND PRIMED HOLES B-737-700 REF SRM 51-21-41-370-802 AND 51-21-72-370-804; INSTALLED WEB ANGLE AT R/H WING TRAILING EDGE DEFLECTION CONTROL PANEL PER REF B737-700 SRM 51-40-02-0G-0. REMOVED AND INSTALLED NEW WEB ANGLE AT R/H WING TRAILING EDGE DEFLECTION CONTROL PANEL PER REF B737-700 SRM 51-40-02-0G-0.

Part: LIGHT — MISSING (R2 DOOR) · airframe 68,934 hrs · 40,794 cycles

EMERGENCY EXIT LIGHT LENS NOT INSTALLED AT R2 DOOR / [01] REMOVED & REPLACED EMERGENCY EXIT LIGHT ASSY; AT R2 DOOR; PER AMM 33-51-01.

Part: SENSOR — FAULTY (LT WING TE FLAP) · airframe 68,781 hrs · 40,711 cycles

CREW REPORTED FLAP LOCK OUT ON LANDING ; / [01] REPLACED SLAT #1 INBOARD PROXIMITY SENSOR PER AMM 27-88-11; OPS CHECK GOOD.

Part: BULB — INOPERATIVE (CABIN) · airframe 68,060 hrs · 40,258 cycles

L-1 DOOR UPPER EMERGENCY LIGHT WITH 2EA BULBS INOP ; / [01] RECITED BULBS (2EA) AT L-1 DOOR UPPER EMERGENCY LIGHT AS PER REF B737 AMM 33-51-01-960-801 PERFORMED OPERATIONAL TEST FOUND NORMAL; [02] VERIFIED STEP 1

Part: GIRT BAR — OUT OF POSITION (L1 DOOR) · airframe 68,060 hrs · 40,258 cycles

L-1 DOOR GIRT BAR HITTING AFT DOOR CUTOUT (WHEN OPENING DOOR) ; / [01] REMOVED R1 DOOR SLIDE REF MT 725-61-06; [02] REPOSITIONED GIRT BAR FOR L1 DOOR REF B737 MM 25-66-01-400-803; [03] REMOVED L1 DOOR SLIDE REF MT 725-61-06; [04] EDIT WORK CAPTURE STEP 1 (& 3)- REMOVED L1 DOOR SLIDE (NOT R1) REF MT 725-61-06. NOTE: R1 DOOR SLIDE REMOVAL ON TTG8Q006YF3B. NO MAINTENANCE AT R1 DOOR ON THIS NR.; [05] OK TO INSTALL L1 DOOR SLIDE.; [06] REINSTALLED L1 DOOR SLIDE REF MT 725-61-06 & MM 25-66-01-400-803.; [07] VERIFIED STEP 6. L1 DOOR SLIDE.

Part: GIRT BAR — OUT OF POSITION (R1 DOOR) · airframe 68,060 hrs · 40,258 cycles

R-1 DOOR GIRT BAR HITTING DOOR CUTOUT WHEN CLOSING ON AFT CORNER ; / [01] REMOVED R1 DOOR SLIDE REF MT 725-61-06; [02] REPOSITIONED GIRT BAR FOR R1 DOOR REF B737 MM 25-66-01-400-803; [03] OK TO INSTALL R1 DOOR SLIDE.; [04] REINSTALLED R1 DOOR SLIDE REF MT 725-61-06 & MM 25-66-01-400-803; [05] VERIFIED R1 DOOR SLIDE INSTALLATION.

Part: NONE — POPPED (CABIN) · airframe 68,060 hrs · 40,258 cycles

PASSENGER CABIN LIGHTING EMERGENCY CHARGER FWD C/B POPPING AT P18. ; PASSENGER CAIN LIGHTING EMERGENCY CHARGER FWD CB POPPING AT P18. / [01] PERFORMED TROUBLESHOOTING PASSENGER CABIN LIGHTING CHARGER FWD C/B AS PER WDM 33-51-11; FOUND BATTERY CHARGER M1875 AT FAULT. REMOVED FROM THE AIRCRAFT.; [02] PERFORMED TROUBLESHOOTING PASSENGER CABIN LIGHTING CHARGER FWD C/B AS PER WDM 33-51-11; FOUND BATTERY CHARGER M1875 AT FAULT. REMOVED FROM THE AIRCRAFT PER AMMS 33-51-06-960-806 AND 33-51-06-960-805; [03] INSTALLED POWER SUPPLY M1875; P/N D717-02-030; S/N: 8980; AS PER REFERENCE B737 AMM 33-51-06-960-806. INSTALLED BATTERY PACK P/N D717-01-100SWA; S/N: WN0388; AS PER REFERENCE B737 AMM 33-51-06-960-805; PERFORMED OPERATIONAL TEST; NORMAL OPERATION.; [04] VERIFIED 3

Part: LIGHT — INOPERATIVE (CABIN) · airframe 68,060 hrs · 40,258 cycles

OVERHEAD BIN EMERGENCY LIGHT INOP BY ROW 4 LH ; OVERHEAD IN EMERGENCY LIGHT INOP Y ROW 4 LH / [01] RE-SECURED CONNECTOR D11090 IN AISLE LIGHT L1065; AS PER REFERENCE B737 WDM 33-51-12; PERFORMED OPERATIONAL TEST AS PER REFERENCE B737 AMM 33-51-00-710-801; NORMAL OPERATION.; [02] VERIFIED 1

Part: SCUFF PLATE — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CARGO FWD SCUFF PLATE CRACKED ; / [01] RECEIVED WELDED SCUFF PLATE ON TAG #397070; ISSUE TAG #HZ896; P.O.#1734696. WILL BE INSTALLED ON CARD 3 # TTG8Q004G7HY; [02] VERIFIED STEP 1

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FOUND PANEL 212DC DELAMONATE AT CORNER ; / [01] PREPARED FOR REPAIR AT PANEL 212 DC AS PER B737-700-SRM 51-70-06-2R-6; [02] VERIFIED STEP 1. OK TO INSTALL REPAIR.; [03] ACCOMPLISHED REPAIR OF DELAMINATION OF THE EDGEBAND OF HONEYCOMB OF FLIGHT DECK CEILING PANEL 212DC IAW B737-700 SRM 51-70-06-2R-6 REPAIR 6; USING MATERIAL P.O.# 1731939 & 1694548. WORK ACCOMPLISHED BY FERNANDO GOLAN X269658.; [04] FINAL INSPECTION; CEILING PANEL DELAMINATION REPAIR.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FOUND CAPTAIN FWD I/B AND O/B SEAT TRACKS WITH CORROSION ; / [01] RECEIVED CAPTAIN FWD I/B AND O/B SET TRACKS TO BE INSTALLED ON CARD TTG8Q0036K4C; [02] RECEIVED CAPTAIN FWD I/B AND O/B SET TRACKS TO BE INSTALLED ON CARD TTG8Q0036K4C

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FOUND FIRST OFFICER FWD I/B AND O/B SEAT TRACKS WITH CORROSION ; / [01] 1ST OFFICER FWD I/B AND O/B SEAT TRACKS WERE REMOVED ON TASKCARD TTG8Q0036K60.; [02] VERIFIED STEP 1. OK TO INSTALL NEW FWD SEAT TRACKS.; [03] INSTALLED NEW 1ST OFFICER FWD I/B AND O/B SEAT TRACKS I.A.W BOEING 737 AMM 25-11-11-400-801.; [04] 1ST OFFICER FWD I/B AND O/B SEAT TRACKS WERE REMOVED ON TASKCARD TTG8Q0036K60 AND INSTALLED NEW 1ST OFFICER FWD I/B AND O/B SEAT TRACKS I.A.W BOEING 737 AMM 25-11-11-400-801.; [05] VERIFIED STEP 4.

Part: NONE — CORRODED (R/H VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

CORROSION.>>>>>VERTICAL FIN FWD R/H ATTACHMENT FITTING LUGS STA 1016 INNER BORE EVIDENCE OF PITTI CORROSION. ; / [01] REMOVED CORROSION ON VERTICAL FIN FWD R/H ATTACHMENT FITTING LUGS STA. 1016 PER REF. 737 SRM 51-10-02-0G-0; BY REAMING HOLE TO FINAL SIZE; 1.040;( ON FUSELAGE); [02] VERIFIED STEP 1.; [03] PREVIOUS HOLE SIZE ENTERED IN ERROR; ACTUAL FINAL HOLE SIZE IS 1.015'; CALIPER B/C #163379-A; DUE DATE 17JUL22; [04] PERFORMED AN HFEC HOLE PROBE INSPECTION OF THE BORES PER 737 NDT MANUAL PART 6; 51-00-00; PROCEDURE 16; USING 0.03 NOTCH CALIBRATION. NO CRACKS.<BR>[NORTEC 500D; B/C 172390; CALIB.DUE -7/22]; [05] PERFORMED EA 21-153-02990. REF FAULT TTG8Q006HQ4R).; [06] VERIFIED STEP 3; [07] VERIFIED STEP 5

Part: NONE — CORRODED (L/H VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

CORROSION >>>>>>>VERTICAL FIN FRONT SPAR R/H FITTING LUG HAVE SIGN OF PITTI CORROSION AT INNER BORE. ; / [01] REMOVED CORROSION ON VERTICAL FIN FRONT SPAR R/H FITTING LUG; PER REF. 737 SRM 51-10-02-0G-0; BY REAMING HOLE TO FINAL SIZE ; 1.040 (0N VERTICAL); [02] VERIFIED STEP 1.; [03] PREVIOUS HOLE SIZE ENTERED IN ERROR; ACTUAL FINAL HOLE SIZE IS 1.015'; CALIPER B/C #163379-A; DUE DATE 17JUL22; [04] ALL WORK WAS ACCOMPLISHED ON TASKCARD TTG8Q006V6S5.; [05] VERIFIED STEP 3; [06] VERIFIED STEP 4

Part: NONE — CORRODED (L/H VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

CORROSION >>>>>>>VERTICAL FIN FRONT SPAR L/H FITTING LUG HAVE SIGN OF PITTI CORROSION AT INNER BORE. ; / [01] REMOVED CORROSION ON VERTICAL FIN FRONT SPAR L/H FITTING LUG ; PER REF. 737 SRM 51-10-02-0G-0; BY REAMING HOLE TO FINAL SIZE ; 1.040;( ON VERTICAL); [02] VERIFIED STEP 1.; [03] PREVIOUS HOLE SIZE ENTERED IN ERROR; ACTUAL FINAL HOLE SIZE IS 1.015'; CALIPER B/C #163379-A; DUE DATE 17JUL22; [04] ALL WORK WAS ACCOMPLISHED ON TASKCARD TTG8Q006V6S5.; [05] VERIFIED STEP 3; [06] VERIFIED STEP 4

Part: ANGLE — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

CABIN PASSENGER STATION 616 LBL 60 CRACK AT FASTENER HOLE ; / [01] INSTALLED EWIS PROTECTION AT LT SIDE BETWEDN STA 540 TO 639 REF B737-7 AMM 20-60-07-913-801; [02] REMOVED CABIN PASSENGER INNER CHORD CREASE BEAM AT LT SIDE LBL 60 FROM STA 530 TO STA671 REF B737-7 SRM 51-40-02-0G-0; [03] VERIFIED STEP 1 AND 2.; [04] LOCATED AND DRILLED NEW CREASE BEAM AT CABIN LT SIDE BETWEEN STA 530-TO 673 REF B737-7 SRM 51-40-05-0G-0 AND DWG #144A5901; [05] PERFORMED COUNTERSINK AT NEW CREASE BEAM ANGLE REF B737-7 SRM 51-40-08-0G-0; [06] CERIFIED STEPS 4 AND 5; [07] OK TO TREAT AND PRIME FACRICATED PART; [08] TREATED AND PRIME CREASE BEAM ANGLE REF B737-7 SRM 51-20-01-0G-0; [09] VERIFIED STEP 8; [10] OK TO INSTALL CREASE BEAM ANGLE; [11] INSTALLED NEW CREASE BEAM ANGLE AT LT SIDE BETWEEN STA 530 TO STA 673 LBL 60' REF B737-7 SRM 51-40-02-0G-0 AND DWG #144A5901; [12] REMOVED EWIS PROTECTION AT LT SIDE FROM STA 530 TO STA 773 LBL 60' REF B737-7 AMM 20-60-07-913-801; [13] REMOVED AND REPLACED NEW CREASE BEAM ANGLE AT MAIN CABIN LBL 60' BETWEEN STA 530 TO STA 673 REF B737-7 SRM 51-40-02-0G-0 AND DWG #144A5901; [14] VERIFIED STEP 13

Part: ANGLE — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

CABIN PASSENGER STATION 616 LBL 60 CRACK AT FASTENER HOLE ; / [01] INSTALLED EWIS PROTECTION AT LT SIDE BETWEDN STA 540 TO 639 REF B737-7 AMM 20-60-07-913-801; [02] REMOVED CABIN PASSENGER INNER CHORD CREASE BEAM AT LT SIDE LBL 60 FROM STA 530 TO STA671 REF B737-7 SRM 51-40-02-0G-0; [03] VERIFIED STEP 1 AND 2.; [04] LOCATED AND DRILLED NEW CREASE BEAM AT CABIN LT SIDE BETWEEN STA 530-TO 673 REF B737-7 SRM 51-40-05-0G-0 AND DWG #144A5901; [05] PERFORMED COUNTERSINK AT NEW CREASE BEAM ANGLE REF B737-7 SRM 51-40-08-0G-0; [06] CERIFIED STEPS 4 AND 5; [07] OK TO TREAT AND PRIME FACRICATED PART; [08] TREATED AND PRIME CREASE BEAM ANGLE REF B737-7 SRM 51-20-01-0G-0; [09] VERIFIED STEP 8; [10] OK TO INSTALL CREASE BEAM ANGLE; [11] INSTALLED NEW CREASE BEAM ANGLE AT LT SIDE BETWEEN STA 530 TO STA 673 LBL 60' REF B737-7 SRM 51-40-02-0G-0 AND DWG #144A5901; [12] REMOVED EWIS PROTECTION AT LT SIDE FROM STA 530 TO STA 773 LBL 60' REF B737-7 AMM 20-60-07-913-801; [13] REMOVED AND REPLACED NEW CREASE BEAM ANGLE AT MAIN CABIN LBL 60' BETWEEN STA 530 TO STA 673 REF B737-7 SRM 51-40-02-0G-0 AND DWG #144A5901; [14] VERIFIED STEP 13

Part: SKIN — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

AFT UPPER FUSELAGE AT STA 1016 - STA 1088 STR 3L - STR 3R WL 308.5 HAS SURFACE CORROSION. REMOVED CORROSION ON UPPER FUSELAGE FROM BS 1016 TO 1088, BETWEEN STRINGER 3L AND 3R, WL 308.5 IAW SRM 51-10-02-0G-0. NO MATERIAL LOST AREAS WITHIN LIMITS IAW SRM 53-00-01-1A-1DETAIL C & FIG. 104. TREATED AND PRIMED AREA IAW AMM 51-21-41-370-802 & 51-21-72-370-804. INSTALLED FASTENERS AND SUPPORT BRACKET IAW SRM 51-40-02-0G-0.

Part: NONE — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER ; LEFT FRON SPAR FITTING CORROSION ; / [01] REMOVED BUSHING AT VERTICAL STABILIZER LEFT FRONT SPAR FITTING AS PER B737-700 SOPM 20-50-03; [02] REMOVED CORROSION AT VERTICAL STABILIZER LEFT FROM SPAR FITTING REF B737-7 SRM 51-10-02-0G-0 STEP 4.D(2); [05] CORRECTION ON STEP# 4 MIN. THICKNESS IS .850'; [06] REMOVED CORROSION AT VERTICAL STAB. LEFT FROM SPAR FITTING FWD AND AFT FACES REF B737-7 SRM 51-10-02-0G-0 STEP 4.D(2); [07] VERIFIED STEP 1;2 AND 6.; [08] CORRECTION:REMOVED CORROSION REF B737-7 SRM 51-10-02-0G-0 STEP 15.A(3); [09] VERIFIED STEP 8 FOR CORRECTION ENTRY ON PREVIOUS STEPS 2 AND 6.; [10] L/H FITTING MAX. MAT. REMOVAL FWD SIDE 0.008'; AFT SIDE 0.009'; [11] PREVIOUS FITTING LOSS MEAUREMENTS ENTERED IN ERROR ---- CORRECT MEASUREMENT IS L/H FWD SIDE 0.011'; [12] PERFORMED PENETRANT INSP ON VERTICAL STAB LEFT FRONT SPAR FITTING IAW B737 SOPM 20-20-02; NO CRACKS<BR>TOOL USED : TFS4 B/C 170330 CALDUE: 01/22; [13] NOTE TO ADD DETAILED DIMENSIONS: VERTICAL STAB LEFT FRONT SPAR FITTING FWD FACE SPOTFACE DIMENSION 1.755' AND AFT FACE SPOTFACE DIMENSION 1.770'.; [14] VERIFIED 13; [15] ISSUED SUMMARY EA 21-155-03013; [16] REMAINING WORK WAS ACCOMPLISHED ON TASKCARD TTG8Q006V6S5 AND TTG8Q006WK7R.; [17] VERIFIED STEPS 10 AND 11; [18] VERIFIES STEP 16

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER CENTER SECTION; LEFT FRON SPAR FITTINGS CORROSION ; /

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER CENTER SECTION; RIGHT I/B REAR SPAR FITTINGS PITTING CORROSION ; / [01] EA EA-GENERAL (EA ATTACHED TO AN AIRCRAFT FAULT); [02] EA EA-GENERAL (EA ATTACHED TO AN AIRCRAFT FAULT); [03] ISSUED SUMMARY EA 21-153-02759; [04] C/W

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER CENTER SECTION; LEFT O/B REAR SPAR FITTINGS CORROSION ; / [01] PERFORMED CORRECTIVE ACTION ON BARCODE TTG8Q006LXMS. REF FAULT TTG8Q006KMKF; [02] PERFORMED CORRECTIVE ACTION ON BARCODE TTG8Q006LXMS. REF FAULT TTG8Q006KMKF

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER CENTER SECTION; LEFT O/B REAR SPAR FITTINGS CORROSION ; /

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER CENTER SECTION; RIGHT O/B REAR SPAR FITTINGS PITTING CORROSION ; / [01] PERFORMED CORRECTIVE ACTION ON BARCODE TTG8Q006LXMS. REF FAULT TTG8Q006KMKF; [02] PERFORMED CORRECTIVE ACTION ON BARCODE TTG8Q006LXMS. REF FAULT TTG8Q006KMKF

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER CENTER SECTION; LEFT I/B REAR SPAR FITTINGS CORROSION ; /

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER ; LEFT FRON SPAR FITTING CORROSION ; /

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER CENTER SECTION; RIGHT O/B REAR SPAR FITTINGS PITTING CORROSION ; /

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER ; RIGHT I/B REAR SPAR FITTINGS PITTING CORROSION ; / [01] REMOVED BUSHINGS AT RIGHT VERTICAL STABILIZER I/B REAR SPAR AS P[ER B737-700 SOPM 20-50-03; [02] AFTER BUSHING REMOVAL ; INSPECTED AREA AT VERTICAL STABILIZER; RIGHT I/B REAR SPAR FITTING ;NO CORROSION FOUND .; [03] VERIFIED STEP 2; [04] OK TO INSTALL BUSHINGS; [05] INSTALLED SERVICEABLE BUSHINGS AT VERTICAL STABILIZER; RIGHT I/B REAR SPAR FITTING AS PER B737-700 SOPM 20-50-03 AND AS PER DRAWING TOLERANCES PL 172A161-2; [06] REMOVED AND REPLACED BUSHINGS AT VERTICAL STABILIZER; RIGHT I/B REAR SPAR FITTING AS PER B737-700 SOPM 20-50-03 AND AS PER DRAWING TOLERANCES PL 172A161-2; [07] INSPECTED INSTALLATION

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER CENTER SECTION; LEFT I/B REAR SPAR FITTINGS CORROSION ; / [01] PERFORMED CORRECTIVE ACTION ON BARCODE TTG8Q006LXMS. REF FAULT TTG8Q006KMKF; [02] PERFORMED CORRECTIVE ACTION ON BARCODE TTG8Q006LXMS. REF FAULT TTG8Q006KMKF

Part: FITTING — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER; RIGHT FRON SPAR FITTING PITTING CORROSION ; /

Part: FITTING — CORRODED (VERTICAL STAB) · airframe 68,060 hrs · 40,258 cycles

VERTICAL STABILIZER LEFT I/B REAR SPAR FITTINGS CORRODED. REMOVED BUSHINGS AT LEFT VERTICAL STABILIZER I/B REAR SPAR AS PER B737-700 SOPM 20-50-03, AFTER BUSHING REMOVAL, INSPECTED AREA, NO CORROSION FOUND. INSTALLED SERVICEABLE BUSHINGS SOPM 20-50-03 AND DRAWING TOLERANCES PL 172A161-2.

Part: NONE — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER; RIGHT FRON SPAR FITTING PITTING CORROSION ; / [01] REMOVED BUSHING AT VERTICAL STABILIZER RIGHT FRONT SPAT FITTING AS PER B737-700 SOPM 20-50-03; [02] REMOVED CORROSION AT VERTICAL STABILIZER RIGHT FROM SPAR FITTING REF B737-7 SRM 51-10-02-0G-0 STEP 4.D(2); [03] PERFORMED HFEC INSP. ON REWORKED AREA IAW B737 NDT PART 6; 51-00-00; PROCEDURE 23. NO CRACKS NOTED <BR>TOOL: NORTEC 600 B/C: 166316 DUE: 10/01/21; [04] PERFORMED UT THICKNESS INSP. ON REWORKED AREA IAW B 737 NDT PART 4; 51-00-00; PROCEDURE 3. MIN.THICKNESS .853'<BR>TOOL: OLYMPUS 27MG B/C: 172139 DUE: 04/01/22; [05] CORRECTION ON STEP# 4 MIN. THICKNESS IS .850'; [06] REMOVED CORROSION AT VERTICAL FIN RIGHT FROM SPAR FITTING FWD AND AFT FACES REF B737-7 SRM 51-10-02-0G-0; [07] CORRECTION: REMOVED CORROSION REF B737-7 SRM 51-10-02-0G-0 STEP 15.A(3); [08] VERIFIED STEPS 2 AND 6 AND 7.; [09] R/H FITTING MAX. MAT. REMOVAL FWD SIDE 0.004'; AFT SIDE 0.008'; [10] PREVIOUS FITTING LOSS MEAUREMENTS ENTERED IN ERROR ---- CORRECT MEASUREMENT IS R/H FWD SIDE 0.0.13'; [11] PERFORMED PENETRANT INSP ON VERTICAL STAB RIGHT FRONT SPAR FITTING IAW B737 SOPM 20-20-02; NO CRACKS<BR>TOOL USED : TFS4 B/C 170330 CALDUE: 01/22; [12] NOTE TO ADD DETAILED DIMENSIONS: VERTICAL STAB RIGHT FRONT SPAR FITTING FWD FACE SPOTFACE DIMENSION 1.750' AND AFT FACE SPOTFACE DIMENSION 1.775'.; [13] VERIFIED 12; [14] PERFORMED EA 21-155-03013. REF FAULT TTG8Q006KM87; [15] VERIFIED STEP 1; [16] VRIFIED STEP 10 AND 11

Part: NONE — CORRODED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

>>> CORROSION >> VERTICAL STABILIZER CENTER SECTION; LEFT FRON SPAR FITTINGS CORROSION ; / [01] REMOVED BUSHINGS AT VERTICAL STABILIZER CENTER SECTION LEFT FRONT SPAR AS PER B737-700 SOPM 20-50-03; [02] REMOVED CORROSION AT VERTICAL FIN LT FITTING REF B737-7 SRM 51-10-02-0G-0 STEP 4.D(2); [08] ACCOMPLISHED UT THICKNESS ON REWORKED AREA OF LEFT AFT FITTING IAW NDTM PART 4;51-00-00 PROCEDURE 3. MINIMUM FOUND : 0.479'.<BR>[27MG; B/C 172139;CALIB.DUE 4/22]; [09] PERFORMED HFEC ON REWORKED AREAS OF LEFT FWD AND LEFT AFT FITTINGS IAW NDTM PART 6; 51-00-00 PROCEDURE 23. NO CRACKS.<BR>[NORTEC 600; B/C 166316; CALIB.DUE- 10/21];11] L/H FITTING FWD CLEVIS MAX. MAT. REMOVAL FWD SIDE 0.006'; AFT SIDE 0.011'.<BR>AFT CLEVIS MAX. MAT. REMOVAL FWD SIDE 0.008'; AFT SIDE 0.009'; [12] PREVIOUS FITTING LOSS MEAUREMENTS ENTERED IN ERROR ---- CORRECT MEASUREMENTS ARE L/H FWD SIDE CLEVIS AFT SIDE 0.011' AND AFT CLEVIS FWD SIDE 0.008'; [13] PERFORMED PENETRANT INSP ON VERTICAL STAB CENTER SECTION LT FRONT SPAR FITTING IAW B737 SOPM 20-20-02; NO CRACKS <BR>TOOL USED : TFS4 B/C 170330 CALDUE: 01/22; [14] ACCOMPLISHED FLAP PEEN ON ALL REWORKED AREA OF VERTICAL STAB. CENTER SECTION L/H FRONT SPAR FUSELAGE BS 1016 ATTACH FITTING; PER REF. SOPM 20-10-03 AND TASK DETAILS 21-153-03006-WIP1; [15] VERIFIED 14; [16] ISSUED SUMMARY EA 21-153-03006; [17] REMAINING WORK WAS ACCOMPLISHED ON TASKCARD TTG8Q006V03D.;

Part: GUSSET — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CARGO COMP GUSSET IS CRACKED BETWEEN FRAME BS 500D AND STGR 22L ; / [01] PARTIALLY FARICATED GUSSET 143A9401-13 REF DGW#143A9401; [02] FABRICATED FWD CARGO COMPARMENT GUSSET MATERIAL USED 7075-0.040' PO#19567B9 TO TH-T6 CONDITION REF BAC5602 AAR CONTROL TAG #410631 AND DWG #143A9401; [03] LOCATED AND DRILLED FABRICATED GUSSET REF B737-7 SRM 51-40-05-0G-0; [04] VERIFIED STEP 1; 2 AND 3; [05] OK TO TREAT AND PRIME AREA; [06] TREATED AND PRIME GUSSET REF B737-7 SRM 51-20--01-0G-0; [07] VERIFIED STEP 6; [08] OK TO INSTALL GUSSET; [09] INSTALLED GUSSET AT FWD CARGO COMPARTMENT STA 500D STR 22L REF B737-7 SRM 51-40-02-0G-0 AND DWG#1T3A9481; [10] REMOVED AND REPLACED GUSSET AT FWD CARGO COMP. STA 500D STR 22L REF B737-7 SRM 51-40-02-0G-0 AND DWG#143A9401 AND 143A9481; [11] VERIFIED WORK PERFORMED

Part: GUSSET — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CARGO COMP GUSSET IS CRACKED BETWEEN FRAME BS 500D AND STGR 19R ; / [01] REMOVED AND DRILLED NEW GUSSET AT FWD CARGO COMPARTMENT FS 500D AND STRINGER 19L IN REF B737-700 SRM 51-40-02-0G-0; [02] VERIFIED STEP 1; [03] OK TO TREAT AND PRIME HOLES; [04] TREATED AND APPLIED PRIMER AT GUSSET IN REF B737-700 SRM 51-20-01-0G-0; [05] VERIFIED STEP 4; [06] OK TO INSTALL GUSSET; [07] ACTUALL STRINGER IS 19R; [08] REMOVED AND REPLACED FWD CARGO GUSSET STA.500D STR.19R REF. B737-7 SRM 51-40-02-0G-0; AND DRAWING 143A7902; [09] VERIFIED INSTALLATION

Part: GUSSET — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CARGO COMP GUSSET IS CRACKED BETWEEN FRAME BS 500D AND STGR 21L ; / [01] REMOVED CRACK GUSSET IN REF B737-700 SRM 51-40-02-0G-0; [02] LOCATED AND DRILLED NEW GUSSET REF. B737-7 SRM #51-40-05-0G-0; [03] VEERIFIED STEP 1 AND 2; [04] OK TO TREAT AND PRIME HOLES; [05] TREATED AND PRIMED FASTENER HOLES ON GUSSET REF. B737-7 SRM #51-20-01-0G-0; [06] VERIFIED STEP 5; [07] OK TO INSTALL GUSSET; [08] REMOVED AND INSTALLED FWD CARGO GUSSET STA.500D STR.21L; REF. B737-7 SRM 51-40-02-0G-0 AND DRAWING 143A7902; [09] VERIFIED STEP 8

Part: ANGLE — CRACKED (VERT. STAB.) · airframe 68,060 hrs · 40,258 cycles

VERTICAL FIN; FWD TERMINAL FITTING ASSY AFT FACE HORIZONTAL T ANGLE CRACKED 2 EA PLACES ; / [01] PERFORMED HFEC INSP ON VERTICAL FIN FWD TERMINAL FITTING ASSY AFT FACE HORIZ T ANGLE IAW B737 NDT P6 51-00-00 PROC.23; CRACKS NOTED MARKED.<BR>TOOL USED : NORTEC 600 B/C 172389 CALDUE: 02-JUL-22; [02] REMOVED DAMAGED HORIZONTAL SPRING ANGLE; FROM VERTICAL STAB.; PER REF. B737 SRM 51-40-02-0G-0; [03] LOCATED AND DRILLED NEW HORIZONTAL SPRING ANGLE; PER REF. B737 SRM 51-40-05-0G-0; [04] VERIFIED STEPS 2 AND 3; OK TO INSTALL SPRING ANGLE.; [05] INSTALLED NEW SPRING ANGLE ON VERTICAL FIN LOWER SECTION; PER REF. B737 SRM 51-40-02-0G-0; [06] VERIFIED COMPLETION.

Part: NONE — BROKEN (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

FOUND LEFT UPPER STABILIZER-TO-BODY FRONT SPAR SLIDING SEAL BROKEN ; / [01] REMOVED LEFT UPPER STABLIZER -TO- BODY FRONT SPAR SLIDING SEAL AS PER BOEING 737 AMM 53-31-31-000-801; [02] LOCATED AND DRILLED LEFT UPPER STABLIZER -TO- BODY FRONT SPAR SLIDING SEAL AS PER BOEING 737 SRM 51-40-05-0G-0; [03] VERIFIED STEP 1 AND 2. OK TO INSTALL NEW SLIDING SEAL.; [04] INSTALLED EXISTING HARDWARE ON NEW SIDING SEAL PER REF. 737 SRM 51-40-02-0G-0; [05] VERIFIED STEP 4.; [06] INSTALLED LEFT UPPER STABLIZER -TO- BODY FRONT SPAR SLIDING SEAL AS PER BOEING 737 AMM 53-31-31-400-801; [07] VERIFIED 6

Part: NONE — BROKEN (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

FOUND RIGHT UPPER STABILIZER-TO-BODY FRONT SPAR SLIDING SEAL BROKEN ; / [01] REMOVED RIGHT UPPER STABLIZER -TO- BODY FRONT SPAR SLIDING SEAL AS PER BOEING 737 AMM 53-31-31-000-801; [02] REMOVED EXISTING HARDWARE AND LOCATED AND DRILLED NEW SLIDING PER REF. 737 SRM 51-40-02-0G-0 AND 51-40-05-0G-0; [03] VERIFIED STEP 1 AND 2. OK TO REINSTALL HARDWARE.; [04] REINSTALLED HARDWARE ON NEW SLIDING IN REF SRM 51-40-02-0G-0; [05] VERIFIED STEP 4. OK TO INSTALL NEW SLIDING SEAL.; [06] INSTALLED RIGHT UPPER STABLIZER -TO- BODY FRONT SPAR SLIDING SEAL AS PER BOEING 737 AMM 53-31-31-401-801; [07] VERIFIED 6

Part: GUSSET — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CARGO COMP GUSSET IS CRACKED BETWEEN FRAME BS 500D AND STGR 24L ; / [01] REMOVED GUSSET AT FWD CARGO COMPARTMENT FS 500D;STRINGER 24L;IN REF B737-700 SRM 51-40-02-OG-0;LOCATED AND DRILLED GUSSET IN REF B737-700 SRM 51-40-05-0G-0; [02] VERIFIED STEP #1. OK TO TREAT AND PRIME GUSSET.; [03] TREATED AND PRIMED FASTENER HOLES REF B737-7 SRM 51-20-01-0G-0; [04] VERIFIED STEP 3. OK TO INSTALL GUSSET; [05] INSTALLED GUSSET AT FWD CARGO COMPARTMENT FS 500D STRINGER 24L IN REF B737-7-- SRM 51-40-02-0G-0; [06] VERIFIED INSTALLATION

Part: GUSSET — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CARGO COMP GUSSET IS CRACKED BETWEEN FRAME BS 500D AND STGR 19L ; / [01] REMOVED GUSSET AT FWD CARGO COMPARTMENT AT FS 500D STRINGER 19L;FOUND OUT OF LIMITS IN REF B737-700 SRM 51-2=10-023-0G-0; LOCATED AND DRILLED NEW GUSSET IN REF B737-700 SRM 51-40-05-0G-0; [02] VERIFIED STEPP 1; [03] OK TO TREAT AND PRIME HOLES; [04] TREATED AND APPLIED PRIMER AT GUSSET FWD CARGO IN REF B737-700 SRM 51-20-01-0G-0; [05] VERIFIED STEP 4; [06] OK TO INSTALL GUSSET; [07] INSTALLED GUSSET AT FWD CARGO COMPARTMENT FS 500D STRIONGER 19L ;IN REF B737-700 SRMO 51-40-02-0G-0; [08] VERIFIED INSTALLATION

Part: VAPOR BARRIER — CRACKED (CENTER WING) · airframe 68,060 hrs · 40,258 cycles

R/H VAPOR BARRIER STA.663; RBL 6-10; CRACKED I/B SIDE ; / [01] MEASUREMENTS; [02] STOP DRILL AT END CRACK ON VAPOR BARRIER PER B737 51-10-02; [03] PREPARED DAMAGE AREA AT R\H VAPOR BARRIER TO APPLY DRY OUT PROCESS PER B737 SRM 51-70-04-2R0 PARAGRAPH 4.D; [04] VERIFIED STEPS 1;2 AND 3; [05] OK YO APPLY DRY OUT PROCESS; [06] APPLIED DRY PROCESS AT R/H VAPOR BARRIER ON REPAIR AREA PER B737 SRM 51-70-04-2R-0 PARAGRAPH 4.D AND PREPARED AREA FOR APPLY REPAIR PER B737SRM 51-70-04-2R-10 PARAGRAPH 4.E; [07] VERIFIED STEP 6 RII; [08] OK TO INSTALL REPAIRB RII; [09] REPAIRED DAMAGED AREA AT R\H BARRIER ON STA663 PER B737 SRM 51-70-04-2R-10 MATERIAL USED EY 3804 PO#1731939;<BR>FIBER GLASS PO#1690463 AND PERFORMED TAP TEST ON REPAIR AREA NO DELAMINATION PER B737 NTM PART 51-05-01; [10] VERIFIED STEP 9; [11] OK TO PAINT VAPOR BARRIER; [12] APPLIED TOP COAT TO R/H VAPOR BARRIER REF. B737-7 AMM 51-21-73-370-803; [13] REPAIRED R/H VAPOR BARRIER STA. 663; AND APPLIED TOP COAT REF. USED B737-7 SRM 51-70-04-2R-0; & AMM 51-21-73-370-803; [14] VERIFIED REPAIR

Part: SPAR — CORRODED (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; CENTER SECTION REAR SPAR CLEVIS 'E' WORNOUT AND CORROSION ; / [01] SUMMARY EA 21-155-02705 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSWB.; [02] SUMMARY EA 21-155-02705 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSWB.; [03] SUMMARY EA 21-155-02705 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSWB.

Part: SPAR — CORRODED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

LEFT HORIZONTAL STABILIZER; REAR SPAR CLEVIS 'H' PITTING CORROSION ; / [01] SUMMARY EA 21-155-02690 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSVP.; [02] SUMMARY EA 21-155-02690 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSVP.; [03] SUMMARY EA 21-155-02690 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSVP.

Part: NONE — CORRODED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

LEFT HORIZONTAL STABILIZER CENTER SECTION; FRONT SPAR CLEVIS 'A' WORN AND CORROSION ; / [01] SUMMARY EA 21-155-02689 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSUB.; [02] SUMMARY EA 21-155-02689 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSUB.; [03] SUMMARY EA 21-155-02689 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSUB.

Part: NONE — CORRODED (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; FRON SPAR CLEVIS 'B' WORNOUT CORROSION ; / [01] SUMMARY EA 21-155-02719 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUQL. <BR>EA-GENERAL AS REPAIR REFERENCE TO CLOSE THE OPEN FAULT ( TTG8Q006HUQL).; [02] SUMMARY EA 21-155-02719 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUQL. <BR>EA-GENERAL AS REPAIR REFERENCE TO CLOSE THE OPEN FAULT ( TTG8Q006HUQL).

Part: NONE — CORRODED (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; REAR SPAR CLEVIS 'H' PITTING CORROSION ; / [01] SUMMARY EA 21-155-02693 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPT.; [02] SUMMARY EA 21-155-02693 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPT.; [03] SUMMARY EA 21-155-02693 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPT.

Part: NONE — CORRODED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

LEFT HORIZONTAL STABILIZER CENTER SECTION; FRONT SPAR CLEVIS 'B' WORN AND CORROSION ; / [01] SUMMARY EA 21-155-02704 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUMV.; [02] SUMMARY EA 21-155-02704 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUMV.; [03] SUMMARY EA 21-155-02704 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUMV

Part: NONE — CORRODED (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; CENTER SECTION REAR SPAR CLEVIS 'C' WORNOUT AND CORROSION ; / [01] SUMMARY EA 21-155-02687 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPK.; [02] SUMMARY EA 21-155-02687 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPK.; [03] VERIFIED STEP 1 AND 2

Part: SPAR — CORRODED (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; REAR SPAR CLEVIS 'K' PITTING CORROSION ; / [01] SUMMARY EA 21-155-02742 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPY.; [02] SUMMARY EA 21-155-02742 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPY.; [03] SUMMARY EA 21-155-02742 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPY.

Part: SPAR — CORRODED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

LEFT HORIZONTAL STABILIZER; REAR SPAR CLEVIS 'K' CORROSION ; / [01] SUMMARY EA 21-155-02739 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUNW.; [02] SUMMARY EA 21-155-02739 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUNW.; [03] VERIFIED STEP 1 AND 2

Part: SPAR — CORRODED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

LEFT HORIZONTAL STABILIZER; FRONT SPAR CLEVIS 'F' CORROSION ; / [01] SUMMARY EA 21-155-02692 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUND.; [02] SUMMARY EA 21-155-02692 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUND.; [03] VERIFIED STEP 1 AND 2

Part: SPAR — CORRODED (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; FRON SPAR CLEVIS 'G' CORROSION ; / [01] SUMMARY EA 21-155-02738 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUQF.; [02] SUMMARY EA 21-155-02738 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUQF.; [03] VERIFIED STEPS 1 AND 2

Part: SPAR — CORRODED (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; REAR SPAR CLEVIS 'J' CORROSION ; / [01] SUMMARY EA 21-155-02726 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPV.; [02] SUMMARY EA 21-155-02726 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPV.; [03] VERIFIED STEPS 1 AND 2

Part: SPAR — CORRODED (RL/H HORIZ. STAB) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; FRON SPAR CENTER SECTION CLEVIS 'A' WORNOUT CORROSION ; / [01] SUMMARY EA 21-155-02691 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUQJ.

Part: NONE — CORRODED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

LEFT HORIZONTAL STABILIZER; CENTER SECTION REAR SPAR CLEVIS 'E' CORROSION ; / [01] SUMMARY EA 21-155-02721 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSVZ.; [02] SUMMARY EA 21-155-02721 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSVZ.; [03] SUMMARY EA 21-155-02721 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSVZ.

Part: NONE — CORRODED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

LEFT HORIZONTAL STABILIZER; CENTER SECTION REAR SPAR CLEVIS 'D' WORNOUT AND CORROSION ; / [01] SUMMARY EA 21-155-02706 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUP3.; [02] SUMMARY EA 21-155-02706 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUP3.; [03] SUMMARY EA 21-155-02706 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUP3.

Part: SPAR — CORRODED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

LEFT HORIZONTAL STABILIZER; REAR SPAR CLEVIS 'J' PITTING CORROSION ; / [01] SUMMARY EA 21-155-02720 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUNS.; [02] SUMMARY EA 21-155-02720 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUNS; [03] SUMMARY EA 21-155-02720 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUNS

Part: FITTING — CORRODED (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; FRON SPAR CLEVIS 'F' PITTING CORROSION ; / [01] SUMMARY EA 21-155-02699 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSWT.; [02] SUMMARY EA 21-155-02699 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HSWT.; [03] VERIFIED STEP 1AND 2

Part: SPAR — CORRODED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

LEFT HORIZONTAL STABILIZER; FRONT SPAR CLEVIS 'G' CORROSION ; / [01] SUMMARY EA 21-155-02741 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUNG.; [02] SUMMARY EA 21-155-02741 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUNG; [03] VERIFIED STEP 1 AND 2

Part: SPAR — CORRODED (R/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

RIGHT HORIZONTAL STABILIZER; CENTER SECTION REAR SPAR CLEVIS 'D' WORNOUT AND CORROSION ; / [01] SUMMARY EA 21-155-02723 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPH.; [02] SUMMARY EA 21-155-02723 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPH.; [03] SUMMARY EA 21-155-02723 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK TO FAULT TTG8Q006HUPH.

Part: NONE — DELAMINATED (RUDDER) · airframe 68,060 hrs · 40,258 cycles

RUDDER L/E BY CENTER AREA WEIGHT BALANCE PANEL DELAMINATED ; / [01] REMOVED RUDDER WEIGHTBALANCE AS PER B737-700 CMM 55-40-09; [02] PERFORMED WIEGHT THE REMOVED BALANCE WEIGHT FOUND WEIGHT= 43.40 LBS; [03] PERFORMED WIEGHT THE NEW SERVISEABLE RUDDER BALANCE WEIGHT;WEITGHT =45.00 LBS.SCALE USED B/C-161060; [04] VERIFIED STEPS 1 ; 2 AND 3; [05] OK TO INSTALL RUDDER WEIGHT BALANCE; [06] INSTALLED NEW SERVICEABLE WEIGHT BALANCE (WEIGHT=50 LBS) AS PER B737-700 CMM 55-40-09; [07] REMOVED AND REPLACED RUDDER WEIGHT BALANCE AS PER B737-700 CMM 55-40-09; [08] VERIFIED WORK PERFORMED

Part: NONE — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CARGO; LEFT Z CHANNEL; BETWEEN STA 500 AND 500A; SURFACE CORROSION AROUND FASTENER HOLES ; LBL-21 WL-156 / [01] CORROSION IS ON AND AROUND FASTENER HOLES; FOUND OUT OF LIMITS REF. B737-7; SRM #53-00-53-1A-2; [02] DRILLED NEW ZEE CHANNEL FROM STA 400 TO 500D; AND SPLICE; REF. B737-7 SRM 53-00-53-2R-6 REPAIR 6; AND 51-40-05-0G-0; [03] OK TO TREAT AND PRIME ZEE CHANNEL; [04] TREATED AND APPLIED PRIMER AT Z-CHANNEL AT FWD CARGO COMPARTMENT L/H BETWEEN FS 396-500D IN REF B737-700 SRM 51-20-01-0G-0; [05] CORRECTED STATIONS STA.396-500D; [06] VERIFIED STEP 4 AND 5; [07] FABRICATED NEW ZEE CHANNEL AT FWD CARGO COMPARTMENT L/H BETWEEN FS 396-500D IN REF B737-700 SRM 53-00-53-2R-6; [08] VERIFIED STEP 7

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

R/H FLIGHT COMPARTMENT CONSOLE PANEL 212BW DELAMINATED AT THE CORNER ; / [01] REMOVED DE DAMAGED PLIES AND PREPARED AREA TO APPLY REPAIR AT CONSOLE PANEL 212BW REF B737-700 AMM 25-00-00-300-801 PARAGRAPH F.; [02] OK TO INSTALL REPAIR; [03] APPLIED REPAIR AT DAMAGED AREA ON CONSOLE PANEL 212BW REF B737-700 AMM 25-00-00-300-801 PARAGRAPH F.; [04] VERIFIED STEP 3

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

LEFT HAND PANEL 211CW DELAMINATECONTROL CABIN) ; / [01] APPLIED REPAIR AT ACCESS PANEL 211CW REF SRM 51-70-04-2R-13 REPAIR 13 PARAGRAPH 4.; [02] VERIFIED STEP 1

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

R/H FLIGHT COMPARTMENT CONSOLE PANEL 212BW DELAMINATED AT THE CORNER ; / [01] REMOVED DE DAMAGED PLIES AND PREPARED AREA TO APPLY REPAIR AT CONSOLE PANEL 212BW REF B737-700 AMM 25-00-00-300-801 PARAGRAPH F.; [02] OK TO INSTALL REPAIR; [03] APPLIED REPAIR AT DAMAGED AREA ON CONSOLE PANEL 212BW REF B737-700 AMM 25-00-00-300-801 PARAGRAPH F.; [04] VERIFIED STEP 3

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

R/H FLIGHT COMPARTMENT CONSOLE PANEL 212CW DELAMINATED ; / [01] PREPARED FOR REPAIRED AT PANEL 212 CW AS PER B737-700 AMM 25-00-00-30-802; [02] REMOVED;PREPARED FOR REPAIR AT PANEL 212CW AS PER B737-700- SRM 51-70-06-2R-6; [03] VERIFIED STEPS 1 AND 2; [04] REPAIRED AT PANEL 212 CW AS PER B737-700 SRM 51-70-06-2R-6; [05] VERIFIED STEP 4; [06] REMOVED;PREPARED AND REPAIRED AT PANEL 212 CW AS PER B737-700-SRM 51-70-06-2R-6 MATERIAL USED PO.1707887 AND PO.1150387; [07] VERIFIED STEP 6

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

AFT CABIN FLOOR PANEL 242RF TOP SURFACE LAYERS DELAMINATED AT STA 890 R/H SIDE ; / [01] MEASUREMENTS; [02] REMOVED TOP SURFACE DAMAGE AND CLEANED FLOOR PANEL FOR REPAIR AS PER B737 SRM 53-0050-2R-7; [03] VERIFIED 1 & 2<BR>OK TO INSTALL REPAIR; [04] REPAIRED TOP SURFACE DAMAGE ON TOP LAYER OF MAIN CABIN FLOOR PANEL 242RF AS PER B737 SRM 53-00-50-2R-7 MATERIAL USED PO#1694548 AND PO#1714421; [05] VERIFIED REPAIR

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CABIN FLOOR SUPPORT INTERCOSTAL CRACKED AT BL-0 BETWEEN STA 380 AND STA 400; WL208.1 ; / [01] INSTALLED EWIS PROTECTION AS PER B737-700 AMM 20-60-07-913-801.; [02] REMOVED FLOOR SUPPORT ANGLE AS PER B737-700 SRM 51-40-02-0G-0.; [03] LOCATED AND DRILLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 BL 0 WL 208.1 REF B737-700 SRM 51-40-05-0G-0 AND DWG# 143A5400.; [04] VERIFIED STEP 3; [05] OK TO INSTALL SERVICEABLE INTERCOSTAL ANGLE.; [06] INSTALLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 BL 0 WL 208.1 REF B737-700 SRM 51-40-02-0G-0 AND DWG# 143A5400.; [07] REMOVED EWIS PROTECTION AT MAIN CABIN BETWEEN STA 380 AND STA 400 BL 0 WL 280.1 REF B737-700 AMM 20-60-07-913-801.; [08] VERIFIED STEP 6 AND 7; [09] REMOVED AND REPLACED INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 BL 0 WL 208.1 REF B737-700 SRM 51-40-02-0G-0 AND DWG# 143A5400.; [10] VERIFIED INSTALLATION

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

AFT CABIN WET AREA FLOOR PANEL 242UF HAS MISSING INSERTS AND TOP SURFACE DELAMINATED ; / [01] REMOVED THE INSERTS IN THE DAMAGED AREA; REMOVED THE DELAMINATED FACESHEET PLIES IN DAMAGED AREA; NO WATER NOTE AND PREPARED DAMAGE AREA TO APPLY REPAIR PLIES. REF B737-700 SRM 53-00-50-2R-7 REPAIR 7 PARAGRAPH 3 A;B;C;E AND F; SRM 53-00-50-2R-0 REPAIR GENERAL.; [02] VERIFIED; [03] OK TO INSTALL REPAIR AND NEW INSERTS; [04] APPLIED THE REPAIR PLIES AND INSTALLED NEW INSERTS AT FLOOR PANEL 242UF. REF B737-700 SRM 53-00-50-2R-7 REPAIR 7 PARAGRAPH 3 G;H;I; AND J; SRM 53-00-50-2R-0 REPAIR GENERAL.; [05] VERIFIED STEP 4; [06] VERIFIED STEP 4 RII

Part: NONE — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

AFT CABIN CENTER AISLE FLOOR PANEL HAS SMALL CRACKS AT UPPER SURFACE BETWEEN STA 827 AND STA 887 ; FROM LBL25 TO RBL 45 WL 208 ; / [01] PERFORMED VISUAL INSPECTION AND TAP TEST INSPECTION AT FLOOR PANEL 241UF B737 NDT PART 1 51-05-01 . DAMAGED AREA MORE 4.0 SQUARE INCHES; FOUND FLOOR PANEL OUT LIMITS REF B737-700 SRM 53-00-50-1A-1 PARAGRAPH 4 B AND E (2).; [02] VERIFIED STEP 1; [03] REMOVED DAMAGED FLOOR PANEL #241UF; FROM MAIN CABIN PER REF. B737 AMM 53-21-00-000-801; [04] RECEIVED NEW FLOOR PANEL P/N 146A5810-54;(241UF); [05] VERIFIED STEP 3 AND 4.; [06] OK TO INSTALL NEW FLOOR PANEL.; [07] INSTALLED NEW FLOOR PANEL #241UF; PER REF. B737 AMM 53-21-00-400-801; [08] VERIFIED STEP 7.; [09] REMOVED DAMAGE FLOOR PANEL; AND INSTALLED NEW PANEL P/N 146A5810-54 ; ( 241UF) PER REF 737 AMM 53-21-00-000-801 AND 53-21-00-400-801; [10] VERIFIED STEP 9.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CABIN FLOOR SUPPORT INTERCOSTAL CRACKED AT FASTENER HOLE LBL-15 BETWEEN STA 380 AND STA 400; WL208.1 ; / [01] INSTALLED EWIS PROTECTION AT MAIN CABIN BETWEEN STA 380 AND STA 400 LBL 1 WL 208.1 REF B737-700 AMM 20-60-07-913-80.; [02] REMOVED INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 LBL 15 WL 208.1 REF B737-700 SRM 51-40-02-0G-0.; [03] LOCATED AND DRILLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 LBL 15 WL 208.1 REF B737-700 SRM 51-40-05-0G-0 AND DWG# 143A5400.; [04] VERIFIED STEP 1;2 AND 3; [05] OK TO REAT AND PRIME HOLES; [06] TREATED AND PRIMED NEW HOLES REF B737-700 SRM 51-20-01-0G-0.; [07] VERIFIED STEP 6; [08] OK TO INSTALL INSTERCOSTAL; [09] INSTALLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 LBL 15 WL 208.1 REF B737-700 SRM 51-40-02-0G-0 AND DWG# 143A5400.; [10] REMOVED EWIS PROTECTION AT MAIN CABIN BETWEEN STA 380 AND STA 400 LBL 1 WL 208.1 REF B737-700 AMM 20-60-07-913-80.; [11] VERIFIED STEPS 9 AND 10; [12] REMOVED AND REPLACED INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 LBL 15 WL 208.1 REF B737-700 SRM 51-40-02-0G-0 AND DWG# 143A5400.; [13] VERIFIED STEP 12

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CABIN FLOOR SUPPORT INTERCOSTAL CRACKED AT FASTENER HOLE RBL 42 BETWEEN STA 380 AND STA 400; WL208.1 ; / [01] INSTALLED EWIS PROTECTION AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 42 WL 208.1 REF B737-700 AMM 20-60-07-913-801.; [02] REMOVED INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 42 WL 208.1 REF B737-700 SRM 51-40-02-0G-0.; [03] LOCATED AND DRILLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 42 WL 280.1 REF B737-700 SRM 51-40-05-0G-0 AND DWG# 143A5400.; [04] VERIFIED STEP 1; [05] VERIFIED STEP 2 AND 3; [06] TREATED AND PRIMED NEW FASTENER HOLES REF B737-700 SRM 51-20-01-0G-0.; [07] VERIFIED STEP 6; [08] OK TO INSTALL NEW INTERCOSTAL; [09] INSTALLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 42 WL 280.1 REF B737-700 SRM 51-40-02-0G-0 AND DWG#143A5400.; [10] REMOVED EWIS PROTECTION AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 42 WL 208.1 REF B737-700 AMM 20-60-07-913-801.; [11] VERIFIED STEP 9 AND 10; [12] REMOVED AND REPLACED INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 42 WL 280.1 REF B737-700 SRM 51-40-02-0G-0 AND DWG#143A5400.; [13] VERIFIED STEP 12.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CABIN FLOOR SUPPORT INTERCOSTAL CRACKED AT FASTENER HOLE AT RBL-12 BETWEEN STA 380 AND STA 400; WL208.1 ; / [01] INSTALLED EWIS PROTECTION AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 12 WL208.1 REF B737-700 AMM 20-60-07-913-801.; [02] REMOVED INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 12 WL 208.1 REF B737-700 SRM 51-40-02-0G-0.; [03] LOCATED AND DRILLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 12 WL 208.1 REF B737-700 SRM 51-40-05-0G-0 AND DWG #1434A5400.; [04] VERIFIED STEPS 1;2; AND 3; [05] OK TO INSTALL NEW ANGLE.; [06] INSTALLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 12 WL 208.1 REF B737-700 SRM 51-40-02-0G-0 AND DWG #1434A5400.; [07] REMOVED AND REPLACED INTERCOSTAL AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 12 WL 208.1 REF B737-700 SRM 51-40-02-0G-0 AND DWG #1434A5400.; [08] REMOVED EWIS PROTECTION AT MAIN CABIN BETWEEN STA 380 AND STA 400 RBL 12 WL208.1 REF B737-700 AMM 20-60-07-913-801.; [09] VERIFIED STEPS # 6 ;7 & 8

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

AFT CABIN FLOOR PANEL # 241XF TOP SURFACE LAYERS DELAMINATED ; / [01] PERFORMED VISUAL INSPECTION AND TAP TEST INSPECTION AT FLOOR PANEL 241XF B737 NDT PART 1 51-05-01 . DAMAGED AREA MORE 4.0 SQUARE INCHES; FOUND FLOOR PANEL OUT LIMITS REF B737-700 SRM 53-00-50-1A-1 PARAGRAPH 4 B AND E (2).; [02] VERIFIED STEP 1; [03] FABRICATED NEW FLOOR PANEL 241XF PER REF DRAWING 147A5810 AND SRM 53-00-50-01-1; [04] VERIFIED STEP 3.; [05] FABRICATED NEW FLOOR PANEL 241XF PER REF 737SRM 53-00-50-01-1 AND DRAWING 147A5810; [06] (RII) VERIFIED STEP 3.; [07] (RII) VERIFIED STEP 5.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

CORROSION--MAIN CABIN RH SEAT TRACK HAS CORROSION AT STA 727E-11' WL 208 DOT NO7 ; / [01] REMOVE CORROSION ON SEAT TRACK; RBL 24.75; STA: 727E - 11.0'; WL 208; IS ACCOMPLISHED ON N/R BARCODE TTG8Q006F30L; [02] VERIFIED STEP 1

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

ITEM TO ADD MISSING MEASUREMENTS FOR ITEM RH SEAT TRACK @ RBL 24.75 ; HAS CORROSION AT ABOUT STA.887+13' WATER LINE 208; AS NOTED - DOT# 9 ; / [01] ADDED MISSING MEASUREMENT ON CORROSION TABLE; [02] C/W

Part: NONE — CRACKED (CENTER WING) · airframe 68,060 hrs · 40,258 cycles

MAIN CABIN CENTER WING FLOOR SUPPORT BREAK CRACKED @ LBL-2 STA 540. MKD DOT ; / [01] REMOVED FLOOR SUPPORT BREAK STA.540; LBL2 REF.B737-7 SRM 51-40-02-0G-0; [02] VERIFIED STEP 1; [03] OK TO DRILL HOLES; [04] LOCATED AND DRILLED NEW FLOOR BREAK REF. B737-7 SRM 51-40-05-0G-0; [05] VERIFIED STEP 4; [06] OK TO INSTALL FLOOR SUPPORT; [07] TREATED AND PRIMED HOLES REF. B737-7 SRM 51-20-01-0G-0; [08] LATE ENTRY - REMOVED FLOOR PANEL #231UF FOR ACCESS REF. B737-7 AMM 53-21-00-000-801; [09] INSTALLED FLOOR SUPPORT BREAK STA.540 LBL2 REF. B737-7 SRM 51-40-02-0G-0 AND DRW.#143A5240; [10] VERIFIED STEPS 7; 8 AND 9; [11] OK TO INSTALL FLOOR PANEL; [12] INSTALLED FLOOR PANEL #231UF REF B737-7 AMM 53-21-00-400-801; [13] REMOVED AND REPLACED FLOOR SUPPORT BREAK STA. 540; LBL2 REF. B737-7 SRM 51-40-02-0G-0 AND DRW.#143A5240; [14] VERIFIED STEPS 12 & 13 RII

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CABIN WET AREA INTERCOSTAL CRACKED BETWEEN STA 277 AND STA 294 BL-0 ; / [01] INSTALLED EWIS PROTECTION AT MAIN CABIN BETWEEN STA 277 & STA 294 BL-0 REF B737-700 AMM 20-60-07-913-801.; [02] REMOVED DAMAGED INTERCOSTAL AT MAIN CABIN BETWEEN STA 277 & STA 294 BL-0 WL 208 REF B737-700 SRM 51-40-02-0G-0.; [03] LOCATED AND DRILLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 277 & STA 294 BL-0 WL 208 REF B737-700 SRM 51-40-05-0G-0 AND DWG# 141A5410.; [04] VERIFIED STEPS 1;2 AND 3 <BR>OK TO TREAT AND PRIME DRILLED HOLES.; [05] TREATED AND PRIMED AT NEW FASTENER HOLES REF B737-700 SRM 51-20-01-0G-0.; [06] VERIFIED STEP 4<BR>OK TO INSTALL SERVICEABLE INTERCOSTAL.; [07] INSTALLED NEW INTERCOSTAL AT MAIN CABIN BETWEEN STA 277 & STA 294 BL-0 WL 208 REF B737-700 SRM 51-40-02-0G-0 AND DWG# 141A5400.; [08] REMOVED EWIS PROTECTION AT MAIN CABIN BETWEEN STA 277 & STA 294 BL-0 REF B737-700 AMM 20-60-07-913-801.; [09] VERIFIED STEPS 7 AND 8.; [10] REMOVED AND REPLACED INTERCOSTAL AT MAIN CABIN BETWEEN STA 277 & STA 294 BL-0 WL 208 REF B737-700 SRM 51-40-02-0G-0 AND DWG# 141A5400.; [11] VERIFIED WORK PERFORMED

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

MAIN CABIN FLOOR PANEL # 232SF UPPER SURFACE LAYERS DELAMINATED ; / [01] PERFORMED VISUAL INSPECTION AND TAP TEST INSPECTION AT FLOOR PANEL 232SF FOUND TOP LAYER DELAMINATION IS 48 SQUARE INCHES REF B737 NDT PART 1 51-05-01 PARAGRAPH 5. FLOOR PANEL IS OUT LIMITS REF B737-700 SRM 53-00-50-1A-1 PARAGRAPH 4 A;B AND E (2) (A).; [02] VERIFIED STEP 1; [03] REPLACED MAIN CABIN FLOOR PANEL #232SF; TAG #WN6972; P.O.# 1728471; PANEL BEING INSTALLED ON CARD # TTG8Q005VZN5; [04] PRIOR ENTRY ENTERED IN ERROR; [05] FABRICATED NEW MAIN FLOOR PANEL # 232SF IN REF SRM 53-00-50-01-1; [06] FABRICATED NEW MAIN FLOOR PANEL # 232SF IN REF SRM 53-00-50-0I-1; [07] (RII) VERIFIED CORRECTED STEP 6.; [08] FABRICATED NEW FLOOR PANEL # 232 SF ; IN REF. 373 SRM 53-00-50-01-1; [09] FABRICATED NEW FLOOR PANEL # 232 SF ; IN REF. 373 SRM 53-00-50-01-1; [10] STEP 8 WAS WRITTEN IN ERROR; [11] PERFORMED VISUAL INSPECTION AND TAP TEST INSPECTION AT FLOOR PANEL 232SF FOUND TOP LAYER DELAMINATION IS 48 SQUARE INCHES REF B737 NDT PART 1 51-05-01 PARAGRAPH 5. FLOOR PANEL IS OUT LIMITS REF B737-700 SRM 53-00-50-1A-1 PARAGRAPH 4 A;B AND E (2) (A) AND FABRICATED NEW MAIN FLOOR PANEL # 232SF IN REF SRM 53-00-50-0I-1.; [12] THIS STEP WAS WRITTEN IN ERROR.; [13] (RII) VERIFIED STEP 11.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 68,060 hrs · 40,258 cycles

MAIN CABIN CENTER AISLE FLOOR PANEL 241AF UPPER SURFACE LAYERS DELAMINATED ; / [01] PERFORMED VISUAL INSPECTION AND TAP-TEST AT FLOOR PANEL#241AF FOUND DELAMINATION AND MULTIPLE DAMAGE PER<BR>B737 NTM 51-05-01 FLOOR PANEL OUT LIMITS PER B737SRM 53-00-50-1A-1; [02] VERIFIED STEP 1; [03] OK TO INSTALL REPAIR; [04] REPAIRED AT PANEL#241 AF AS PER B737-700 SRM 53-00-50-2R-7 MATERIAL USED P.O.1715777 AND PO.1150387

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

MAIN CABIN CENTER AISLE FLOOR PANEL 241DF UPPER SURFACE LAYERS DELAMINATED ; / [01] PERFORMED VISUAL INSPECTION AND TAP-TEST AT FLOOR PANEL#241DF FOUND DELAMINATION AND MULTIPLE DAMAGE PER<BR>B737 NTM 51-05-01 FLOOR PANEL OUT LIMITS PER B737SRM 53-00-50-1A-1; [02] VERIFIED STEP 1; [03] REPLACED MAIN CABIN FLOOR 241DF; TAG #WN9123; P.O.# 1728471; FLOOR BEING INSTALLED ON CARD # TTG8Q005VZL5; [04] VERIFIED STEP 3

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

CABIN SEAT TRACK @ RBL 24.75... ; CAIN SEAT TRACK @ RBL 24.75 HAS EARLY STAGE OF CORROSION AT AOT STA.663 - 4' AS NOTED - DOT #4 / [01] FAULT WAS GENERATED INCORRECTLY. NEW FAULT WAS GENERATED <BR>REFTTG8Q006GGRO

Part: SCUFF PLATE — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

FWD CARGO DOOR FWD CORNER SCUFF PLATE CRACKED . ; / [01] RECEIVED SERVICEABLE FWD CARGO DOOR CORNER SCUFF PLATE PART CONTROL TAG #410965 ISSUE TAG #HZ805; [02] VERIFIED STEP 1; [03] THIS CARD WIIL BE ACCOMPLISHED ON CARD #TTG8Q0036JVP STEP 15; [04] VERIFIED STEP 3

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

CRACK INDICATIONS OBTAINED EMANATING FROM FASTENER HOLE OPPOSITE FITTING LATCH AT R1 DOOR CUTOUT STA 294.5 BETWEEN S-8R AND S-9R. THERE ARE 2 CRACKS (1) LENGTH 0.197' AND (2) 0.118' ; / [01] INSTALLED EWIS PROTECTION AT RT FUSELAGE REPAIR AREA REF BI37-7 AMM 20-60-07-913-801; [02] REMOVED 2EA RAIN GUTTER AT RT FUSELAGE REPAIR ACCESS REF B737-7 SRM 53-10-01-2R-6 STEP 4.A; [10] CUT AND REMOVE THE DAMEGED INNER BEARSTRAP REF B737-7 SRM 53-10-01-2R-6STEP 4.C(1)(2); [11] VERIFIED STEP 10; [12] PERFORMED HFEC INSP. ON R1 DOOR CUTOUT STA 294.5 BETWEEN S-8R AND S-9R IAW B737 NDT PART 6 51-00-00 PROC. 23. NO CRACKS. EQUIP: NORTEC 600 CAL DUE: 10/21 B/C 166317; [13] PERFORMED COUNTERSINK ROTO INSP. ON EXISTING FASTENER HOLES @ FWD GALLEY DOOR (R1) BEAR STRAP; BS 290-296 BETWEEN S-8R AND S-9R IAW B737 NDT PART 6 51-00-00 PROC. 16. NO CRACK. EQUIP: NORTEC 600 B/C 166317 CAL DUE: 10/21.; [14] STARTED FABRICATION REPAIR PARTS; DOUBLER AND TRIPLE R-1 DOOR FUSELAGE SKIN REPAIR REF B737-7 SRM 53-10-01-2R-6 STEP 4.E TABLE 201; [15] VERIFIED STEP 14; [16] FABRICATED SKIN DOUBLER REPAIR MATERIAL USED DOUBLER 2024-T3 0.100'PO#1646552;TRIPLER 2024-T3 0.63' PO#1717744; TRIPLER FILLER 2024-T3 0.63; BEARSTRAP FILLER 2024T3- O.090' PO1727238;REF B737-7 SRM 53-10-01-2R-6 STEP 4.E TABLE 201 FIG 202; [31] INSTALLED SKIN AND BEARSTRAP DOUBLER REPAIR AT RT FUSELAGE R-1 DOOR FWD UPPER AREA REF B737-7 SRM 53-10-01-2R-6 STEP 4;

Part: NONE — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

AFT PASSENGER COMPARTMENT FLOOR STRUCTURE; FLOOR BEAM TOP SURFACE HAVE SURFACE CORROSION BETWEEN BS 986.5 AND RBL-24.7 TO RBL 46.MKD 126. ; / [01] REMOVED CORROSION AT AFT WET AREA FLOOR BEAM UPPER FLANGE STA 986.5 FROM RBL 24.7 TO RBL 46 PER REF B737-700 SRM 51-10-02-0G-0.; [22] (RII) VERIFIED STEPS 20 AND 21.; [23] REMOVED CORROSION ON FLOOR BEAM STA. 986.5 PER REF. SRM 51-10-02-0G-0; MINIMUM THICKNESS FOUND;.090; FOUND OUT OF LIMITS PER SRM 53 70-51-1A-1; 0N EXISTING FLOOR BEAM REPAIR FROM LBL 7.93 TO RBL 50; AND REMOVED EXISTING T CHORD REPAIR AND INSTALLED NEW T CHORD ; USING EXISTING SPLICES REPAIR FROM LBL 7.93 TO RBL 50PER REF.737 SRM 53-70-51-2R-4 FIG 204; [24] (RII) VERIFIED STEP 23.; [25] VERIFIED ALL STEPS COMPLETED.

Part: NONE — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

ITEM TO ADD MISSING MEASUREMENT FOR ITEM CORROSION AFT PASSENGER COMPARTMENT FLOOR STRUCTURE; FLOOR BEAM TOP SURFACE HAVE SURFACE CORROSION BETWEEN BS 986.5 AND RBL -24.7 TO RBL 46. [TTG8Q006ELS6] ; / [01] ADDED MISSING CORROSION MEASUREMENTS FOR TASKCARD TTG8Q006ELS6.; [02] VERIFIED STEP 1.

Part: NONE — CRACKED (L/H HORIZ. STAB.) · airframe 68,060 hrs · 40,258 cycles

L/H HORIZONTAL STABILIZER L/E FAIRING RIB # 3 CRACKED AT END ; / [01] PERFORMED HFEC INSP ON LH HORIZ STAB L/E FAIRING RIB#3 IAW B737 NDT P6 51-00-00 PROC.23; CRACK NOTED MARKED.<BR>TOOL USED : NORTEC 600 B/C 172389 CALDUE: 02-JUL-22; [02] REMOVED CRACK RIB ON L/H HORIZONTAL L/E # 3 PER REF 737 SRM 51-40-02-0G-0; [03] VERIFIED. REMOVAL.; [04] LOCATED AND DRILLED NEW RIB PER REF. 737 SRM 51-40-05-02-0G-0; [05] VERIFIED STEP 4 ; OK TO INSTALL RIB.; [06] INSTALLED NEW RIB AT L/H HORIZONTAL L/E PER REF. 737 SRM 51-40-02-0G-0 AND DRAWING 186A1001; [07] VERIFIED STEP 6; INSTALLATION OF #3 RIB.; [08] REMOVED AND REPLACED CRACK RIB #3 ON L/H HORIZONTAL STAB. L/E PER REF. 737 SRM 51-40-02-0G-0 AND DRAWING 186A1001; [09] VERIFIED ALL STEPS COMPLETED.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

AFT CARGO COMPARTMENT FLOOR PANEL 140DF CRACKED. ; / [01] FABRICATE NEW AFT CARGO COMPARMENT FLOOR PANE 140DF IN REF AMM 25-52-01-201-801; [02] VERIFIED FABRICATION OF PANEL.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

AFT CARGO COMPARTMENT FLOOR PANEL 140AF CRACKED. ; / [01] FABRICATED NEW FLOOR PANEL 140AF; AFT CARGO COMPARTMENT PER REF. 737 AMM 25-52-01-201-801; USING REMOVED PANEL AS TEMPLATE

Part: PANEL — CORRODED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

CENTER TANK SUMP DRAIN PNL 192F; ON ANTENNA LOCATIONS (3EA) SURFACE CORROSION ; / [01] REMOVED AND REPLACED PANEL 192F;FOUND OUT OF LIMITS IN REFB737-700 SRM 51-10-02-0G-0; [02] NEW PANEL ISSUE TAG NUMBER E70672 P.O #1737029; [03] VERIFIED WORK PERFORMED

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 68,060 hrs · 40,258 cycles

AFT CARGO COMPARTMENT FLOOR PANEL 140BF CRACKED. ; / [01] FABRICATED NEW FLOR PANEL # 140BF; USING REMOVED LINER AS A TEMPLATE; PER REF. B737 AMM 25-52-01=201-801; [02] VERIFIED FABRICATION OF PANEL.

Part: VAPOR BARRIER — CRACKED (CENTER WING) · airframe 68,060 hrs · 40,258 cycles

RR/H STA 663 VAPOR BARRIER LOWER I/B SIDE CRACKED@ RBL6-10 ; / [01] PARTIALLY REMOVED VAPOR BARRIER AS PER B737-700 SRM 51040-02-0G-0.; [02] COMPLETED THE REMOVAL OF R/H VAPOR BARRIER WEB AS PER B737-700 SRM 51-40-02-0G-0.; [03] OK TO INSTALL VAPOR BARRIER; [04] 80 HR. SEALANT MIX TIME : 1500; 9/20/21; [05] PARTIALLY INSTALLED VAPOR WEB AS PER B737-700 SRM 51-40-02-0G-0.; [06] COMPLETED INSTALLATION OF VAPOR BARRIER WEB REF. B737-7 SRM 51-40-02-0G-0; AND DRAWING # 111A1001; [07] APPLIED CAP SEAL TO FASTENER HEADS REF. B737-7; SRM 51-20-05-0G-0; [08] REMOVED AND INSTALLED VAPOR BARRIER WEB FOR REPAIR REF. B737-7 SRM 51-40-02-0G-0; AND DRAWING # 111A1001; [09] INSPECTED WORK PERFORMED

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 67,775 hrs · 40,087 cycles

EMERGENCY LIGHT BATTERIES FAILED CAPACITY TEST AT LOCATIONS M1672. / R&R EMERGENCY LIGHT BATTERIES PER AMM.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 67,775 hrs · 40,087 cycles

EMERGENCY LIGHT BATTERIES FAILED CAPACITY TEST AT LOCATIONS M1670. / R&R EMERGENCY LIGHT BATTERIES PER AMM.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 67,775 hrs · 40,087 cycles

EMERGENCY LIGHT BATTERIES FAILED CAPACITY TEST AT LOCATIONS M1673. / R&R EMERGENCY LIGHT BATTERIES PER AMM.

Part: BATTERY — NO TEST (EMERGENCY LIGHT) · airframe 67,775 hrs · 40,087 cycles

EMERGENCY LIGHT BATTERIES FAILED CAPACITY TEST AT LOCATIONS M1668. / R&R EMERGENCY LIGHT BATTERIES PER AMM.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 67,775 hrs · 40,087 cycles

EMERGENCY LIGHT BATTERIES FAILED CAPACITY TEST AT LOCATIONS M1675. / R&R EMERGENCY LIGHT BATTERIES PER AMM.

Part: LIGHT — CRACKED (CABIN) · airframe 67,775 hrs · 40,087 cycles

CABIN PHOTO LUMINESCENT STRIP LEFT AND RIGHT OF CENTER AISLE, FORWARD OF AFT GALLEY CRACKED. / R&R CABIN PHOTO LUMINESCENT STRIPS PER MM.

Part: TRUNNION — OUT OF TOLERANCE (LT MLG) · airframe 67,615 hrs · 39,991 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER INBOARD LUG BORE OUT OF TOLERANCE. / ACCOMPLISHED E.A 1-A57-3246 ON LOWER INBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (LT MLG) · airframe 67,615 hrs · 39,991 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG OUTBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A. 1-A57-3246 ON LOWER OUTBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (RT MLG) · airframe 67,615 hrs · 39,991 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER INBOARD LUG OUTBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A 1-A57-3246 ON LOWER INBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (RT MLG) · airframe 67,608 hrs · 39,988 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER INBOARD LUG INBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A 1-A57-3246 ON LOWER INBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (LT MLG) · airframe 67,608 hrs · 39,988 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER OUTBOARD LUG OUTBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A. 1-A57-3246 ON UPPER OUTBOARD TRUNNION FITTING LUG.

Part: TRUNNION — OUT OF TOLERANCE (RT MLG) · airframe 67,608 hrs · 39,988 cycles

R/H MLG FWD TRUNNION FITTING UPPER OUTBOARD LUG BORE OUT OF TOLERANCE / ACCOMPLISHED E.A. 1-A57-3246 ON UPPER OUTBOARD TRUNNION FITTING LUG. REF D&M ENTERPRISES W.O. SSR# 1210

Part: TRUNNION — CORRODED (RT MLG) · airframe 67,608 hrs · 39,988 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG INBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A 1-A57-3246 ON LOWER OUTBOARD TRUNNION FITTING LUG.

Part: TRUNNION — OUT OF TOLERANCE (LT MLG) · airframe 67,608 hrs · 39,988 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER INBOARD LUG BORE OUT OF TOLERANCE. / ACCOMPLISHED E.A. 1-A57-3246 ON UPPER INBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (LT MLG) · airframe 67,608 hrs · 39,988 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER INBOARD LUG OUTBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A. 1-A57-3246 ON LOWER INBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (RT MLG) · airframe 67,608 hrs · 39,988 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER OUTBOARD LUG OUTBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A 1-A57-3246 ON UPPER OUTBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (RT MLG) · airframe 67,608 hrs · 39,988 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER INBOARD LUG OUTBOARD FACE HAD CORROSION. / ACCOMPLISHED EA. 1-A57-3246 ON UPPER INBOARD LUG, TRUNNION FITTING.

Part: TRUNNION — CORRODED (LT MLG) · airframe 67,608 hrs · 39,988 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG INBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A. 1-A57-3246 ON LOWER OUTBOARD TRUNNION FITTING LUG.

Part: TRUNNION — OUT OF TOLERANCE (LT MLG) · airframe 67,608 hrs · 39,988 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER OUTBOARD LUG BORE OUT OF TOLERANCE. / ACCOMPLISHED E.A 1-A57-3246 ON UPPER OUTBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (LT MLG) · airframe 67,608 hrs · 39,988 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER INBOARD LUG INBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A. 1-A57-3246 ON UPPER INBOARD TRUNNION FITTING LUG.

Part: TRUNNION — OUT OF TOLERANCE (RT MLG) · airframe 67,608 hrs · 39,988 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG BORE OUT OF TOLERANCE. / ACCOMPLISHED E.A. 1-A57-3246 ON LOWER OUTBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (LT MLG) · airframe 67,608 hrs · 39,988 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER INBOARD LUG OUTBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A. 1-A57-3246 ON UPPER INBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (LT MLG) · airframe 67,608 hrs · 39,988 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER INBOARD LUG INBOARD FACE HAD CORROSION. / ACCOMPLISHED E.A 1-A57-3246 ON LOWER INBOARD TRUNNION FITTING LUG.

Part: TRUNNION — OUT OF TOLERANCE (RT MLG) · airframe 67,608 hrs · 39,988 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER INBOARD LUG BORE WAS OUT OF TOLERANCE. / ACCOMPLISHED E.A. 1-A57-3246 ON LOWER INBOARD TRUNNION FITTING LUG.

Part: TRUNNION — OUT OF TOLERANCE (RT MLG) · airframe 67,608 hrs · 39,988 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER INBOARD LUG BORE OUT OF TOLERANCE. / ACCOMPLISHED E.A. 1-A57-3246 ON UPPER INBOARD LUG. TRUNNION FITTING LUG.

Part: TRUNNION — OUT OF TOLERANCE (LT MLG) · airframe 67,608 hrs · 39,988 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG BORE OUT OF TOLERANCE. / ACCOMPLISHED E.A. 1-A57-3246 ON LOWER OUTBOARD TRUNNION FITTING LUG.

Part: TRUNNION — CORRODED (RT MLG) · airframe 67,608 hrs · 39,988 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG O/N FACE HAD CORROSION. / ACCOMPLISHED E.A 1-A57-3246 ON LOWER OUTBOARD TRUNNION FITTING LUG.

Part: VAPOR BARRIER — CRACKED (WHEEL WELL RH) · airframe 65,886 hrs · 38,896 cycles

R/H W/W 663 VAPOR BARRIER HAS A CRACK AT RBL 16.54. CRACK MEASURES 4' IN LENGTH. / ACCOMPLISHED INTERIM REPAIR IAW SRM 57-10-10-1A-2.

Part: PANEL — ELONGATED (LOWER EXT FUSELA) · airframe 65,211 hrs · 38,472 cycles

193 B FAIRING PANEL ELONGATED FASTENER HOLES AT LOCATION 1 THRU 7; 15; 27 THRU 33; AND 34 THRU 38 / REMOVED AND REPLACED 193B PANEL PER ENGINEERING ORDER 14108 AND SIP

Part: LIGHT — INOPERATIVE (CABIN) · airframe 63,787 hrs · 37,561 cycles

LT EMERGENCY EXIT DOOR LIGHT INOP. RELAMPED LIGHT IAW AMM.

Part: CONTROL PANEL — FAULTY (COCKPIT) · airframe 63,752 hrs · 37,534 cycles

DIVERSION, CARGO COMPARTMENT FIRE EXTINGUISHER DISCHARGE ("DISC") LIGHT ILLUMINATED FOR APPROXIMATELY 20 MINUTES IN FLIGHT. R&R CARGO FIRE PROTECTION CONTROL PANEL PER MM.

Part: BEAM — CRACKED (R1 DOOR) · airframe 63,023 hrs · 37,042 cycles

R1 DOOR BEAM CRACKED. R&R NR 5 BEAM IAW EO AND DWG.

Part: COVER — MISSING (CABIN) · airframe 62,811 hrs · 36,898 cycles

L1 DOOR EMERGENCY LIGHT MISSING RED ARROW. INSTALLED COVER PER AMM.

Part: COVER — MISSING (R1 DOOR) · airframe 62,811 hrs · 36,898 cycles

R1 DOOR EMERGENCY LIGHT MISSING RED ARROW. INSTALLED COVER PER AMM.

Part: FSEU — FAULTY (E&E BAY) · airframe 62,803 hrs · 36,893 cycles

AIR TURNBACK/DECLARED EMERGENCY, STICK SHAKER ACTIVATED DURING TAKEOFF ROTATION AIRBORNE AT VR-FLAPS 5Ï¿½ STALL WARNING LOGIC EXCESSIVELY HIGH THROUGHOUT FLIGHT. DURING APPROACH A FLAPS 40Ï¿½ YELLOW STALL STICK SHAKER BAND WAS 1 KNOT BELOW CALCULATED V REF SPEED LANDING WEIGHT 128.0 PER INDICATIONS. R&R FLAP SLAT ELECTRONIC UNIT PER AMM.

Part: TRANSMITTER — FAULTY (TE FLAP) · airframe 62,803 hrs · 36,893 cycles

AIR TURNBACK/DECLARED EMERGENCY, STICK SHAKER ACTIVATED DURING TAKEOFF ROTATION AIRBORNE AT VR-FLAPS 5Ï¿½ STALL WARNING LOGIC EXCESSIVELY HIGH THROUGHOUT FLIGHT. DURING APPROACH A FLAPS 40Ï¿½ YELLOW STALL STICK SHAKER BAND WAS 1 KNOT BELOW CALCULATED V REF SPEED LANDING WEIGHT 128.0 PER INDICATIONS. R&R LT FLAP POSITION TRANSMITTER PER AMM.

Part: TRANSMITTER — FAULTY (TE FLAP) · airframe 62,803 hrs · 36,893 cycles

AIR TURNBACK/DECLARED EMERGENCY, STICK SHAKER ACTIVATED DURING TAKEOFF ROTATION AIRBORNE AT VR-FLAPS 5Ï¿½ STALL WARNING LOGIC EXCESSIVELY HIGH THROUGHOUT FLIGHT. DURING APPROACH A FLAPS 40Ï¿½ YELLOW STALL STICK SHAKER BAND WAS 1 KNOT BELOW CALCULATED V REF SPEED LANDING WEIGHT 128.0 PER INDICATIONS. R&R RT FLAP POSITION TRANSMITTER PER AMM.

Part: LENS — LOOSE (EXTERIOR LIGHT) · airframe 62,745 hrs · 36,856 cycles

RT EXTERNAL FUSELAGE OVERWING ESCAPE LIGHT LENS LOOSE AT BS 651, WL 226. R&R LENS ASSEMBLY IAW AMM.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 62,745 hrs · 36,856 cycles

FORWARD CABIN EMERGENCY LIGHT INOP. R&R BATTERY PACK IAW AMM.

Part: FITTING — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

AFT SIDE OF FRAME BELOW Z ANGLE CLIP CRACKED AT BS 500C. R&R CLIP IAW SRM AND DWG.

Part: PANEL — CRACKED (LEFT WING) · airframe 62,745 hrs · 36,856 cycles

LH WING # 3 LEADING EDGE SLAT COVE PANEL 523DB IS CRACKED AT LWR INBD CORNER. / REMOVED AND REPLACED LH WING #3 SLAT PANEL 523DB IAW B737 SRM 51-40-02-0G-0; DWG 114A8131 REV B; AMM 51-21-73-370-803; TAG LC1288

Part: BATTERY — DISCHARGED (CABIN) · airframe 62,745 hrs · 36,856 cycles

PASSENGER CABIN RT SIDE JUST FORWARD OF THE OVERWING EMERGENCY EXIT LIGHT BATTERY INOP AT BS 600. R&R BATTERY IAW AMM.

Part: BAFFLE — CRACKED (FWD CARGO BAY) · airframe 62,745 hrs · 36,856 cycles

BAFFLE IS CRACKED AT STA 400 TO 420 RBL 26 / REMOVED CRACKED BAFFLE AT FWD CARG AT STA400 TO 420 RBL26 I.A.W. SRM 51-40-02-0G-00. FABRICATED AND DRILLED NEW BAFFLE AND CLIPS I.A.W. SRM 51-40-05-0G-00. INSTALLED BAFFLE AND CLIPS I.A.W. SRM 51-40-02-0G-00 AND BOEING DWG 143A7505

Part: FLOOR PANEL — DELAMINATED (AFT FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

AFT CABIN FLOOR PANEL 241ADF IS DELAMINATED AT AFT OTBD CORNER. / REPAIRED AFT CABIN FLOOR PANEL 241ADF AS REQ IAW B737 SRM 57-00-50-2R-8 PARA 9 (A;C;E;K-M) REV 64.

Part: FLOOR PANEL — DELAMINATED (AFT FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

AFT CABIN FLOOR PANEL 241ABF IS DELAMINATED ALONG OTBD EDGE. / REPAIRED DELAMINATION O LOWER SURFACE ALONG OTBD EDGE PER B737 SRM 53-00-50-2R-7.

Part: DOOR SILL — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

R1 DOOR LOWER FLOOR SILL WEB CRACKED. R&R WEB PER SRM.

Part: SEAT TRACK — CRACKED (FLIGHT DECK) · airframe 62,745 hrs · 36,856 cycles

COCKPIT FLOOR CAPTAIN'S FWD INBD SEAT TRACK IS CRACKED AT FWD END STOP PIN HOLE. / REMOVED & REPLACED FWD INBD CAPT'S FLOOR SEAT TRACK SRM 51-40-02 AND AMM 25-11-11-400-801

Part: FITTING — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

LT AFT SIDE OF FRAME BELOW Z ANGLE CLIP CRACKED AT BS 500C. R&R CLIP IAW SRM AND DWG.

Part: BEAM — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

ELECTRONIC EQUIPMENT COMPARTMENT STUB BEAM CORRODED AT BS 328+7.5, STR 23L. R&R LOWER FLANGE IAW DWG.

Part: NONE — CRACKED (CABIN) · airframe 62,745 hrs · 36,856 cycles

PASSENGER CABIN STA 663 LBL 45-LBL 60 FLOOR PANEL BREAK IS CRACKED / REMOVED REPLACED FLOOR PANEL BREAK AT STA 663 CIH LBL 45 TO LBL 60 IAW SRM 51-40-02 AND DWG 144A5702 REV A ATAG LC1224

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

ATTACH ANGLE CRACKED AT BS 663, RBL 35. R&R ANGLE IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

RT FUSELAGE LOWER STUB FRAME CRACKED AT STA 294, WL 108. R&R FRAME PER SRM.

Part: SHIELD — CORRODED (FWD CARGO RH) · airframe 62,745 hrs · 36,856 cycles

FWD CARGO; RH SIDE SPLASH SHIELD AFT OF CARGO DOOR HAS MULTIPLE AREAS OF CORROSION AROUND NUTPLATE HOLES FROM STA 492 TO 500A / REMOVED CORROSION IAW SRM 51-10-02-0G-0 AT STA 492-500A IT VERIFIED WITH 10X MAGNIFICATION ORIGINAL THICKNESS .032' AFTER REWORK .023' .009' MATERIAL LOSS OUT OF LIMITS IAW SRM 53-30-15-1A-1 DETAIL D. AAR TOOL #18173 CAL DUE 11/27/18 REMOVED AND REPLACED SHIELD STA 492-500A RH ALL IAW SRM 51-40-02-0G-0 AND DWG #143A8126 REVA ATG #LC1216

Part: ANGLE — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

FORWARD CARGO LT Z-ANGLE CORRODED BETWEEN BS 500+14 TO BS 500A. R&R Z ANGLE IAW SRM.

Part: ANGLE — CORRODED (FWD CARGO COMPT) · airframe 62,745 hrs · 36,856 cycles

FWD CARGO; STA 500D LOWER BULKHEAD SUPPORT ANGLE HAS MULTIPLE AREAS OF CORROSION ON VERTICAL AND HORIZONTAL FLANGE FROM RH Z-ANGLE TO LH Z-ANGLE / INSTALLED/REPLACED NEW BULKHEAD SUPPORT ANGLE ON FWD PIT AFT CENTER BULKHEAD LWR AREA. I.A.W. B737-700 SRM 51-40-02-0G & BOEING DWG #143A9481; TY: DWG; ID: 0008; REV: A. REMOVED CORROSION & NO ALLOWABLE DAMAGE GIVEN IN THE SRM.

Part: WEB — CORRODED (FWD CARGO THRESH) · airframe 62,745 hrs · 36,856 cycles

FWD CARGO DOOR CUTOUT; SILL PLATE HAS MULTIPLE AREAS OF CORROSION FROM STA 440 TO 492. REMOVED CORROSION IAW SRM 51-10-02; OUT OF LIMITS IAW SRM 53-30-15-1A-1. REMOVED LOWER SILL WEB IAW B737 SRM 51-40-02. VERIFIED NEW WEB AS P/N 143A8122-10 PER DWG NO 143A8120 REV:A. LOCATED AND DRILLED IAW BOEING DWG ENG. DWG. NO 143A8120 REV:A; COUNTERSANK HOLES IAW B737 SRM 51-40-08; INSTALLED NUT PLATES IAW B737 SRM 51-40-02-0G-0. INSTALLED WEB IAW BOEING ENG DWG. NO. 143A8120 REV:A AND B737 SRM 51-40-02. APPLIED CIC IAW B737 AMM 51-21-91-620-8. INSTALLED NUT PLATES IAW B737 SRM 51-40-02-0G-0. INSTALLED WEB IAW BOEING ENG DWG. NO. 143A8120 REV:A AND B737 SRM 51-40-02. APPLIED CIC IAW B737 AMM 51-21-91-620-802.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,745 hrs · 36,856 cycles

CABIN FLOOR PANEL 222DF FWD OTBD CORNER IS DELAMINATED. / UPON EVALUATION NOTED DELAMAINTATION ON FWD OTBD ANDINBD CORNER'S REPAIRED PER B737 SRM 53-00-50-27-7.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,745 hrs · 36,856 cycles

CABIN FLOOR PANEL 221GF IS CRUSHED; DELAMINATED AT FWD OTBD CORNER. / REPAIRED LWER SKIN OF FWD OTBD CORNER OF FLOOR PANEL 221GF AS REQ IAW B737 SRM 53-00-50-2R-1 REPAIR 1 PAR 3 (G-M) REV 64. A49525; A11393; A76111.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 62,745 hrs · 36,856 cycles

CABIN FLOOR PANEL 221EF UPPER SURFACE IS CRUSHED; DELAMINATED AT 2' FROM AFT SIDE; 8' FROM RH SIDE. / REPAIRD CRUSHED AND DELAMINATED AREA 2' FROM AFT SIDE 8' FROM R/H SIDE ON UPPER SURFACE PER B737 SRM 53-00-50-2R-7

Part: WEB — CORRODED (AFT CARGO THRESH) · airframe 62,745 hrs · 36,856 cycles

CORROSION INDICATED UNDER AFT CARGO DOOR SCUFF PLATE. AREAS MARKED ON WEB ONLY / EVALUATED CORROSION ON AFT CARGO WEB SILL 100% MATERIAL LOSS FOUND TO BE OUT OF LIMITS IAW SRM 53-60-15-15-1A-1 REMOVED AND REPLACED AFT CARGO; APPLIED CIC TO SILL WEB IAW AMM 51-21-91-620 ATG #LC1194

Part: FLOOR PANEL — PULLED (CABIN) · airframe 62,745 hrs · 36,856 cycles

MAIN CABIN FLOORBOARD 242SF HAS PULLED FIBERS. / REPAIRED MAIN CABINFLOORBOARD 242SF TOP SURFACE I/A/W 757-700 SRM 53-00-50-212-1 REV 64; SRM 53-00-50-2R-0 GENERAL REV 64.

Part: SUPPORT BRACKET — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

FEEDER CABLE SUPPORT BRACKET CRACKED AT BS 867, STR 3R. R&R BRACKET IAW SRM AND DWG.

Part: SCUFF PLATE — CORRODED (AFT CARGO THRESH) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO PIT DOORWAY FORWARD CARGO HOLD DOWN PLATE IS CORRODED AS MARKED. / REPLACED AFT CARGO FWD CARGO HOLD DOWN PLATE W/NEW P/N 453A2611-1 IAW BOEING DWG 453A2611 REV D A TAG A82504

Part: STRAP — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO COMPARTMENT STRAP JUST INBOARD OF SILL WEB AT CARGO ENTRY CORRODED. R&R STRAP IAW DWG & SRM.

Part: SCUFF PLATE — CORRODED (AFT CARGO THRESH) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO PIT DOORWAY AFT CARGO HOLD DOWN PLATE IS CORRODED AS MARKED. / REPLACED AFT CARGO AFT CARGO HOLD DOWN PLATE WITH NEW P/N 453A2611-2 IAW BOEING DWG 453A2600 REV D A TAG A45693

Part: SUPPORT BRACKET — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

FORWARD SIDE OF FRAME SUPPORT BRACKET CRACKED AT BS 294.5, STR 13L. R&R BRACKET IAW SRM AND DWG.

Part: FLOOR PANEL — PULLED (CABIN) · airframe 62,745 hrs · 36,856 cycles

MAIN CABIN FLOORBOARD 241ZF HAS PULLED FIBERS. / REMOVED MAIN CABIN FLOORBOARD 241ZF I/A/W 7737-700 SRM 53-00-50-2R-1 REV 64; SRM 53-00-50-2R-0 GENERAL REV 64.

Part: FLOOR PANEL — PULLED (CABIN) · airframe 62,745 hrs · 36,856 cycles

MAIN CABIN FLOORBOARD PANEL 242UF HAS NUMEROUS PULLED FIBERS. / REPAIRED MAIN CABIN 242UF FLOORPANEL I/A/W 737-700 SRM 53-00-50-2R-1 REV 64; SRM 53-00-50-2R-0 GENERAL REV 64.

Part: FITTING — CRACKED (RT WING) · airframe 62,745 hrs · 36,856 cycles

RT WING FIXED TRAILING EDGE, UPPER FIXED PANEL INBOARD OF THE INBOARD DEFLECTOR RIB, INTERCOSTAL STIFFENER ANGLE CRACKED. R&R CLIP IAW SRM & DWG.

Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

R2 DOOR CUTOUT THRESHOLD SUPPORT BRACKET CORRODED AT BS 978. R&R BRACKET IAW SRM AND EA.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

STRINGER CLIP CORRODED AT STA 767, STR 26R. R&R CLIP PER SRM.

Part: INTERCOSTAL — CORRODED (AFT CARGO COMPT) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY BETWEEN STA 747 AND 767 UNDER R/H Z ANGLE INTERCOASTAL IS CORRODED AS MARKED / BLENDED CORROSION IAW SRM 51-10-02-0G-0 AND SRM 53-00-53-1A-2. 100% MATERIAL LOSS. OUT OF LIMITS IAW SRM 53-00-53-1A-2 DETAIL D. REMOVED OUT OF LIMITS BAFFLE AND INSTALLED NEW BAFFLE PART: 146A7505-8 ATAG:LC1201 AT STA 747 TO 767 RH UNDER Z-ANGLE IAW SRM 51-40-02-0G-0 AND DWG 146A7505 REV-. ATAG:LC1201

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

R2 DOOR CREASE BEAM INBOARD CHORD CUTOUT CORRODED BETWEEN BS 944 TO BS 990. R&R CREASE BEAM IAW DWG AND SRM.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY RT Z ANGLE CORRODED BETWEEN BS 887 TO BS 907. R&R Z ANGLE IAW SRM AND DWG.

Part: CREASE BEAM — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

LT INNER CREASE BEAM CHORD CRACKED AT BS 302. R&R CREASE BEAM PER DWG AND SRM.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY LT Z ANGLE CORRODED BETWEEN BS 767 TO BS 787. R&R Z ANGLE IAW SRM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

AFT CABIN FLOORBEAM UPPER FLANGE CORRODED AT BS 967, RBL 41. R&R FLOORBEAM IAW SRM AND EA.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY RT Z ANGLE CORRODED BETWEEN BS 767 TO BS 727C. R&R Z ANGLE IAW SRM AND DWG.

Part: INTERCOSTAL — CRACKED (CABIN) · airframe 62,745 hrs · 36,856 cycles

PASSENGER CABIN FWD WET AREA BETWEEN STA 312 AND 328 INTERCOSTAL AT RBL 31 IS CRACKED/ BROKEN / REMOVED AND REPLACED PASSENGER CABIN FWD WET AREA BETWEEN STA 312 AND 328 INTERCOSTAL AT RBL 31. I/A/W BOEING DWG 141A5400 REV -. 737-700 SRM 51-40-02-0G-0; AND 737 AMM 51-21-91-620-802

Part: PLATE — CORRODED (AFT CARGO COMPT) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY STA 727D + 5' FLOOR SUPPORT TRANSITION STRIP PLATE IS CORRODED INCLUDING NUTPLATES / REPLACED AFT CARGO STA 727D + 5 FLOOR TRANSITION PLATE IAW BOEING DWG 146A7500 REV C P/N 146A9401-8 A TAG A83102

Part: INTERCOSTAL — CRACKED (CABIN) · airframe 62,745 hrs · 36,856 cycles

PASSENGER CABIN FWD WET AREA BETWEEN STA 312 AND 328 LBL 48 INTERCOSTAL IS CRACKED / CABIN CRACKED INTERCOSTAL AT LBL 48 BETWEEN STA 312 TO STA 328. REMOVED CRACKED INTERCOSTAL I/A/W SRM 51-40-02-0G-0. LOCATED AND DRILLED NEW INTERCOSTAL I/A/W SRM 51-40-05-0F-0 ALSO BOEING DWG 141A5400 REV -. INSTALLED NEW INTERCOSTAL I/A/W SRM 51-40-02-0G-0 ALSO BOEING DWG 141A5400 REV -. APPLIED CIC ITO AREA I/A/W AMM 5-21-91-620-802

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

INTERCOSTAL CRACKED BETWEEN BS 344 TO BS 360, LBL 02. R&R INTERCOSTAL IAW DWG AND SRM.

Part: INTERCOSTAL — CRACKED (CABIN) · airframe 62,745 hrs · 36,856 cycles

PASSENGER CABIN FWD WET AREA BETWEEN STA 294.5 AND 277 RBL 02 INTERCOSTAL IS CRACKED / REMOVED AND REPLACED RBL 02 INTERCOSTAL AT PASSENGE CABIN FWD WET AREA STA 294.5 AND 277. IAW B737-700 SRM 51-40-02-0G-0.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

INTERCOSTAL CRACKED BETWEEN BS 344 TO BS 360, LBL 13. R&R INTERCOSTAL IAW DWG AND SRM.

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

RT INNER CREASE BEAM CHORD CORRODED BETWEEN BS 290 TO BS 344. R&R CREASE BEAM IAW DWG.

Part: STRIP — CORRODED (AFT CARGO COMPT) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY STA 772 BETWEEN STR 25R AND 25L FLOOR PNL SUPPORT TRANISTION STRIP PLATE IS CORRODED TOP AND BOTTOM SIDES / AFT CARGO STA 772 FLOOR PNL SUPPORT TRANSITION STRIP FOUND TO BE 100% OUT OF LIMITS IAW SRM 53-00-53-1A-2 REPLACED WITH NEWPNL SUPPORT STRIP PN 146A9401-4 IAW AIPC 53-42-11-30 AND AMM 25-52-10-400-801 ( REMOVED AND REPLACED TRANSITION STRIP) ATAG WN 0696

Part: BRACKET — CRACKED (AFT CARGO COMPT) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY STA 865 BETWEEN STR 27L AND 26L BRACKET FOR WASTE WATER BULKHEAD LOWER FRAME IS CRACKED IN 2 EA AREAS AS MARKED / REMOVED AND REPLACED BRACKET PN 149A8109U114 A TAG # A74756 ON AFT CARGO BAY STA. 865 BETWEEN STR 27L AND 26L FOR WASTE WATER BULK LEAD LOWER FRAME IAW BOEING DWG # 149A8102 REV. C. AND SRM 51-40-02-0G-0.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

FUSELAGE INTERCOSTAL CORRODED AT STA 847 TO STA 856, STR 27R. R&R INTERCOSTAL PER SRM.

Part: SHIELD — CORRODED (AFT CARGO COMPT) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY BETWEEN STA 787 AND 767 STR 25R AREA FWD FLOOR SHIELD IS CORRODED TOP AND BOTTOM SURFACES / REMOVED CORROSION AT AFT CARGO FWD SHIELD STA 767-787 STR 25R IAW B737-700 SRM 51-10-02-0G-0 PARAGRAPH 15.A.(3) EVALUATED SHIELD ORIGINAL .050'; LOSS OF .012'; REMAINING OF .038'; FOUND TO BE OUT OF LIMITS IAW B737-700 SRM 53-00-53-1A-2 FIG 103; DETAIL E. REMOVED & REPLACED FWD SHIELD IAW B737-700 SRM 51-40-02-0G-0 AND DWG NO. 146A0081 REV:A ATAG:WN2907

Part: ANGLE — PULLED (AFT CARGO COMPT) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY AT STA 807 AND 827 L/H Z ANGLE HAS RIVETS PULLED THROUGH AND WORKING AT FRAMES / REMOVED AND REPLACED L/H Z ANGLE FROM STA 727 TO 847 ON NR 780266 CONTINUATION SA-M 326 E2570699 ITEM 2.

Part: INTERCOSTAL — CORRODED (AFT CARGO COMPT) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY BETWEEN STR 767 AND 787 STR 27R AREA INTERCOASTAL IS CORRODED IN SEVERAL AREAS AS MARKED / REMOVED AND REPLACED INTERCOSTAL @ STA .767 AND 787 STR .27R IAW BOEING DWG # 146A8130 SHEET 12 REV B ORIG 'T' .032 ; 100% MATERIAL LOSS IAW SRM 53-60-15-0-1 TABLE 6 AND SRM 53-60-15-A1-1

Part: STRAP — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

RT INNER CREASE BEAM CHORD STRAP CORRODED BETWEEN BS 294.5 TO BS 301. R&R STRAP IAW DWG.

Part: CARGO TRACK — CORRODED (CARGO BAY) · airframe 62,745 hrs · 36,856 cycles

AFT CARGO BAY FLOOR TRACK CORRODED BETWEEN BS 727 TO BS 727C, BETWEEN STR 27R TO STR 26R. R&R TIE DOWN TRACK IAW DWG & SRM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

CABIN FLOORBEAM UPPER SURFACE CORRODED AT STA 294, BETWEEN RBL 31 AND RBL 53. REPAIRED BEAM PER EA.

Part: STRAP — MISSING (FLASHLIGHT) · airframe 62,745 hrs · 36,856 cycles

PASSENGER CABIN FORWARD LAV OUTBOARD FLASHLIGHT MISSING "EMERGENCY USE ONLY" STRAP. R&R STRAP IAW AMM.

Part: STRAP — MISSING (FLASHLIGHT) · airframe 62,745 hrs · 36,856 cycles

PASSENGER CABIN INBOARD FORWARD LAV FLASH LIGHT MISSING "EMERGENCY USE ONLY" STRAP. R&R STRAP IAW AMM.

Part: PRESSURE DECK — CRACKED (LT MLG WW) · airframe 62,745 hrs · 36,856 cycles

HORIZONTAL PRESSURE DECK WEB CRACKED AT BS 665, LBL 33. REPAIRED WEB IAW EA.

Part: STRAP — BROKEN (FLASHLIGHT) · airframe 62,745 hrs · 36,856 cycles

AFT CLOSET FLASHLIGHT BROKEN "EMERGENCY USE ONLY" STRAP. R&R STRAP IAW AMM.

Part: STRIP — CORRODED (AFT CARGO COMPT) · airframe 62,745 hrs · 36,856 cycles

AFT PIT STA 887 FLOOR TRANSITION STRIP CORRODED / NO CORROSION LIMITS PUBLISHED IN SRM FOR STA 887 FLOOR TRANSITION STRIP. THEREFORE PART IS OUT OF LIMITS. REMOVED OUT OF LIMITS FLOOR TRANSITION STRIP AT STA 887 AND INSTALLED NEW FLOOR TRNSITION STRIP RT NO: 146A9401U39 ATG: WN6233 IAW SRM 51-40-02-0G-0 AND DWG: 146A7500 REV C. ATAG: WN6233

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

FORWARD CARGO, BAFFLE INTERCOSTAL UNDER LT Z-ANGLE CRACKED AT FORWARD UPPER CORNER BETWEEN BS 500A TO BS 500B, LBL 24. R&R INTERCOSTAL IAW EA.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

FWD CARGO COMPT RT FUSELAGE Z-ANGLE CRACKED AT STA 420. REPAIRED ANGLE PER SRM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

FORWARD CARGO BAFFLE INTERCOSTAL BELOW LT Z-ANGLE CRACKED AT FORWARD UPPER CORNER AT BS 500. R&R Z ANGLE IAW SRM & DWG.

Part: DOUBLER — CORRODED (FWD CARGO BAY) · airframe 62,745 hrs · 36,856 cycles

FWD CARGO; INTERNAL ANTENNA DOUBLER HAS CORROSION ON UPPER SURFACE AND RH SIDE VERTICAL FLANG AT BL 0; STA 500+10 / FWD CARGO INTERNAL ANTENNA DOUBLER HAS CORROSION ON UPPER SURFACE AND RH SIDE VERT FLANG AT BL 0 STA 500+10 BLENDED CORROSION AND FOUND ORIG 'T' .040' REMAINING 'T' .035 WITH A LOSS OF .005' FOUND TO BE OUT OF LIMITS IAW SRM 53-00-01-1A-5 REMOVED AND REPLACED WITH NEW DOUBLER PN 143A3233-4 IAW SRM 51-40-02-0G-0 AND IAW BOEING DWG # 143A3233 REV -

Part: SUPPORT FRAME — CRACKED (LWR FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

R/H EXTERIOR FUSELAGE FWD WING-TO-BODY PANEL SUPPORT CRACKED AT STA 500D BETWEEN STR18R AND STR 19R. / R/H EXTERIOR FUSELAGE FWD WING TO BODY PANEL SUPPORT; REMOVED AND REPLACED FRAME P/N 116A3118010 ATAG A81-366; IAW BOEING DWG 116A3110 REV - INSTALLED IAW SRM 51-4002-0G-0 AND B737 DWS 116A3110 REV- & 116A4008 REV A.

Part: GUSSET — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

FORWARD CARGO STRINGER CLIP GUSSET CRACKED AT BS 500D, STR 19L. R&R GUSSET IAW SRM AND DWG.

Part: INTERCOSTAL — CRACKED (FWD CARGO BAY) · airframe 62,745 hrs · 36,856 cycles

FWD CARGO; BAFFLE INTERCOSTAL UNDER LH Z-ANGLE IS CRACKED AT FWD UPPER CORNER AT STA 500B / REMOVED CRACKED FWD CARGO; BAFFLE INTERCOSTAL UNDER L/H Z-ANGLE FWD UPPER CORNER AT STA 500B AND REPLACVE WITH NEW BAFFLE P/N 143A7510-11; LOCATED DRILLED AND INSTALLED NEW PART IAW SRM 51-40-02-0G AND DWG 143A7505 REV B; SRM 51-40-05

Part: DOUBLER — CORRODED (FWD CARGO BAY) · airframe 62,745 hrs · 36,856 cycles

FWD CARGO; INTERNAL ANTENNA DOUBLER HAS CORROSION ON UPPER SURFACE AND LH VERTICAL FLANGE AT BL0; STA 500A+14 / REMOVED AND REPLACED INTERNAL ANTENNA DOUBLER @ STA .500A+14 BLD PER DWG #143A3230; NO LIMITS FOUND IN SRM

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

STRINGER CLIP CRACKED AT STA 500D, STR 19R. R&R CLIP PER SRM.

Part: BALANCE WEIGHT — CORRODED (LT WING) · airframe 62,745 hrs · 36,856 cycles

LH AILERON HAS 2 BALANCE WEIGHTS THAT ARE CORRODED 10' OTBD OF ACT ROD. / REPLACED 2 BALANCE WEIGHTS ON LT AILERON 10 INCHES OTBD OF ACT ROD IAW BOEING CMM 57-50-26 ASSEMBLY STEP 2.C A-TAG# LC1165; LC1166

Part: ANGLE — CRACKED (FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

RT AIR CONDITION BAY OUTBOARD OF THE KEELBEAM WEB ''L'' ANGLE CRACKED AT BS 663. R&R "L" ANGLE IAW EA.

Part: SUPPORT BRACKET — CRACKED (LT WING) · airframe 62,745 hrs · 36,856 cycles

LH WING UPR FIXED TE PNL; LWR SUPT BRKT CRACKED AT LWR FASTENER; 10' OTBD OF #6 SPOILER. / REMOVED CRACKED SUPPORT BRACKET FROM LEFT WING UPPER T/E PANEL; O/B OF #6 SPOILER IAW SRM 51-40-02 STEP 9. INSTALLED SUPPORT BRACKET; 115A2982-9; IAW SRM 51-40-02 STEP 9.B. ATAG# A82496

Part: SUPPORT BRACKET — CRACKED (RT WING) · airframe 62,745 hrs · 36,856 cycles

R/H WING UPPER FIXED T/E SUPPORT BRACKET 10' IB OF #7 SPOILER OB EDGE HAS CRACK AT LOWER BOLT / REMOVED DAMAGED WEB ASSY; IDENTIFIED NEW PART AS P/N 115A2982-10. LOCATED AND DRILLED NEW PART; APPLIED TOP COAT. INSTALLED NEW WEB ASSY. IAW B737-700 SRM 51-40-02-0G-0.

Part: PANEL — DELAMINATED (RT WING) · airframe 62,745 hrs · 36,856 cycles

RH WING LEADING EDGE PANEL 621JB; FWD CORNER OF PANEL IS DELAMINATED. / REPAIRED R/H L/E PANEL 621JB; FWD CORNER I/A/W 737-700 SRM 51-70-04-2R-13 REV 64 PER SRM 57-41-01-2R-1 TABLE 202 REV 64.

Part: PANEL — BROKEN (RT WING) · airframe 62,745 hrs · 36,856 cycles

RH WING LEADING EDGE PANEL 621DB; FWD INBOARD CORNER HAS COMPOSITE SECTION BROKEN OFF. / REPAIR BONDED FWD INBOARD CORNER SECTION MISSING FIBER LAYERS AND RESTORED DECORATIVE FINISH ON RH WING L/E PNL 621DB. IAW B737-800 SRM 51-70-04-2R-6 REV 64; SRM 51-70-04-2R-0 REV 64; SRM 57-41-01-2R-1 REV 64; AMM 51-21-99-300-802 REV 65. AMM 51-21-99-300 100-80-1 REV 65 (A83649) (A94393) (A71074) (A22509)

Part: FAIRING — ELONGATED (LWR FUSELAGE) · airframe 62,745 hrs · 36,856 cycles

PANEL 193AR HAS 2EA ENLARGED HOLES ON LOWER SIDE OF PANEL. / PREPAIRED PANEL 193AR 2 EACH FASTNER HOLES AS MARKED I/A/W 737-700 SRM 51-70-05-2R-8 REV 64 PAR SRM 53-40-70-2R-1 PAR 2. B (1) B REV 64.

Part: PANEL — DELAMINATED (LT WING) · airframe 62,745 hrs · 36,856 cycles

LH WING LEADING EDGE PANEL 521EB; FWD OUTBOARD CORNER IS DELAMINATED / BONDED DELAMINATION FWD OUBOARD CORNER AND RESTORED DECORATIVE FINISH TO LH WING L/E PANLE 521 EB IAW B77-700 SRM 51-0-04-2R-12 REV 64 SRM 51-70-04-2R-0 REV 64; AMM 51-21-99-300-802 REV 65; AMM 51-21-99-300-801 REV 65 (A40165) (A22569) (A71074)

Part: FLOOR PANEL — CRACKED (AFT CARGO COMPT) · airframe 62,182 hrs · 36,518 cycles

AFT CARGO FLOOR CRACKED AT BS 780 - CRACK MEASURES 16'. / R&R CARGO FLOOR PANEL IAW M/M 25-52-10.

Part: RETAINER — LOOSE (R1 DOOR GIRT BAR) · airframe 61,071 hrs · 35,795 cycles

R1 DOOR ESCAPE SLIDE GIRT BAR RETAINER LOOSE. ADJUSTED THE GIRT BAR RETAINER IAW MM.

Part: STRAP — MISSING (FLASHLIGHT) · airframe 61,003 hrs · 35,757 cycles

AFT GALLEY EMERGENCY FLASHLIGHT MISSING STRAP. INSTALLED STRAP PER SIP.

Part: BATTERY — INOPERATIVE (FLASHLIGHT) · airframe 60,772 hrs · 35,597 cycles

FORWARD UPPER FLASHLIGHT INOPERATIVE. R & R THE FLASHLIGHT BATTERY IAW AMM.382

Part: SLIDE — LOOSE (L1 DOOR) · airframe 60,582 hrs · 35,463 cycles

L1 DOOR EMERGENCY EVAC SLIDE LOOSE. SECURED SLIDE PER MT.

Part: COFFEEMAKER — MALFUNCTIONED (GALLEY) · airframe 60,162 hrs · 35,197 cycles

FLIGHT ATTENDANTS REPORT HEARING A POP FOLLOWED BY SMELLING ELECTRICAL FUMES IN AFT GALLEY. FUMES DISSIPATED AFTER TURNING GALLEY POWER OFF. R&R NR 2 AFT COFFEE MAKER PER MM.

Part: COFFEEMAKER — MALFUNCTIONED (GALLEY) · airframe 60,162 hrs · 35,197 cycles

FLIGHT ATTENDANTS REPORT HEARING A POP FOLLOWED BY SMELLING ELECTRICAL FUMES IN AFT GALLEY. FUMES DISSIPATED AFTER TURNING GALLEY POWER OFF. R&R NR 1 AFT COFFEE MAKER PER MM.

Part: GIRT BAR — OUT OF ADJUST (R1 DOOR SLIDE) · airframe 60,153 hrs · 35,191 cycles

R1 DOOR SLIDE GIRT BAR OUT OF ADJUST. ADJUSTED THE GIRT BAR IAW MMM.

Part: ANGLE — CRACKED (ASD) · airframe 60,066 hrs · 35,139 cycles

AFT SERVICE DOOR; LOWER PAN ATTACH ANGLES ARE CRACKED. / R&R PAN AS PER AMM 52-41-31.

Part: LIGHT — LOOSE (EXIT SIGN) · airframe 59,555 hrs · 34,825 cycles

MID-CABIN EMERGENCY EXIT SIGN LOOSE. R&R LIGHT IAW AMM.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHTS) · airframe 58,121 hrs · 33,972 cycles

LEFT WING TO BODY FAIRING EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED THE LAMP IAW AMM.

Part: COVER — CRACKED (OVERWING EXIT) · airframe 57,869 hrs · 33,820 cycles

LT OVERWING EXIT RED PULL STRAP COVER CRACKED. R&R COVER PER AMM.

Part: BRACKET — CRACKED (LT WING) · airframe 57,869 hrs · 33,820 cycles

LT WING ANGLE BRACKET ATTACHED TO INBOARD SIDE OF THE FLAP DEFLECTION ROLLER BEAM CRACKED. R&R BRACKET IAW SRM.

Part: SKIN — DELAMINATED (LT WING SLAT) · airframe 56,729 hrs · 33,123 cycles

LEFT WING INBOARD AND OUTBOARD EDGE OF NR 1 SLAT DELAMINATED. R & R THE NR 1 SLAT IAW AMM.

Part: CONNECTOR — DISCONNECTED (CABIN) · airframe 56,729 hrs · 33,123 cycles

OVERWING EMERGENCY EXIT DOOR SIGN INOPERATIVE. CONNECTED CONNECTOR IAW AMM.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 56,729 hrs · 33,123 cycles

RIGHT FORWARD GALLEY EMERGENCY EXIT SIGN INOPERATIVE. R & R BATTERY PACK IAW AMM.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 56,729 hrs · 33,123 cycles

RIGHT AFT GALLEY AREA EMERGENCY EXIT SIGN INOPERATIVE. R & R BATTERY PACK IAW AMM.

Part: FAIRING — DELAMINATED (LT WING) · airframe 56,729 hrs · 33,123 cycles

LEFT WING FLAP TRACK NR 1 FAIRING DELAMINATED. REPAIRED THE FAIRING IAW SRM.

Part: FAIRING — CRACKED (RT WING) · airframe 56,729 hrs · 33,123 cycles

RIGHT WING, NR 6 FAIRING CRACKED ON INTERNAL AREA ON LOWER SURFACE. REPAIRED NR 6 FAIRING IAW SRM.

Part: FAIRING — CRACKED (RT WING) · airframe 56,729 hrs · 33,123 cycles

RIGHT WING NR 8 FAIRING CRACKED ON INTERNAL AREA. REPAIRED FAIRING IAW EA.

Part: FAIRING — DELAMINATED (LT WING) · airframe 56,729 hrs · 33,123 cycles

LEFT WING NR 1 FAIRING INTERNAL AREA LOWER SURFACE DELAMINATED. REPAIRED NR 1 FAIRING IAW EA.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 56,729 hrs · 33,123 cycles

RIGHT HORIZONTAL STABILIZER RIB CRACKED AT HSS 92.70, 29 INCHES FROM FRONT SPAR. REPAIRED THE RIB WEB IAW EA.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 56,729 hrs · 33,123 cycles

RIGHT HORIZONTAL STABILIZER RIB CRACKED AT HSS 92.70, 38 INCHES FROM THE FRONT SPAR. REPAIRED THE RIB IAW SRM.

Part: STIFFENER — CRACKED (LT HORIZ STAB) · airframe 56,729 hrs · 33,123 cycles

LEFT HORIZONTAL STABILIZER INSPAR RIB VERTICAL STIFFENER CRACKED ON STABILIZER STA. 92.70, 20" FROM FRONT SPAR. REPAIRED INSPAR RIB VERTICAL STIFFENER IAW SRM.

Part: RIB — CRACKED (RT HORIZ STAB) · airframe 56,729 hrs · 33,123 cycles

RT HORIZONTAL STABILIZER RIB CRACKED ON STABILIZER STA 92.70, 20" FROM FRONT SPAR. REPAIRED RIB IAW SRM.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 56,729 hrs · 33,123 cycles

R/H HORIZONTAL STABILIZER RIB CRACKED AT HSS 92.70, 10 INCHES FROM FRONT SPAR. REPAIRED THE RIB IAW SRM.

Part: STIFFENER — CRACKED (LT HORIZ STAB) · airframe 56,729 hrs · 33,123 cycles

LEFT HORIZONTAL STABILIZER INSPAR RIB VERTICAL STIFFENER CRACKED ON STABILIZER STA 92.70, 29 FROM FRONT SPAR. REPAIRED INSPAR RIB VERTICAL STIFFENER IAW SRM.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 56,729 hrs · 33,123 cycles

LEFT HORIZONTAL STABILIZER INBD SPAR RIB LOWER FLANGE CRACKED AT HSS 129.50, 9 INCHES FROM FRONT SPAR. REPAIRED THE RIB IAW EA.

Part: FLASHLIGHT — CRACKED (GALLEY) · airframe 56,729 hrs · 33,123 cycles

FORWARD GALLEY AREA FLASHLIGHT CRACKED. R & R THE FLASHLIGHT IAW CMM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 56,729 hrs · 33,123 cycles

AFT CARGO COMPARTMENT LOWER FRAME WEB CRACKED AT BS 727, STR 17R. REPAIRED WEB IAW EA.

Part: FASTENER — LOOSE (EVAC SLIDE) · airframe 54,828 hrs · 32,027 cycles

R1 DOOR EMER EVAC SLIDE LOOSE. R & R FASTENER IAW SRM.

Part: HOUSING — CRACKED (FUSELAGE) · airframe 54,622 hrs · 31,916 cycles

EXTERNAL POWER RECEPTACLE HOUSING, CRACKED FWD FLANGE, JUST BELOW BOTTOM DOOR HINGE. REPAIRED FLANGE IAW SRM.

Part: VAPOR BARRIER — CRACKED (RT MLG WW) · airframe 54,622 hrs · 31,916 cycles

RIGHT MAIN WW FWD BULKHEAD VAPOR BARRIER CRACKED AT BS 663. REPAIRED BARRIER IAW EA.

Part: SKIN — CRACKED (LT NACELLE) · airframe 53,757 hrs · 31,446 cycles

LEFT ENG COWL SKIN CRACKED FROM 9 O CLOCK POSITION UP TO 12 O CLOCK POSITION. REPAIRED SKIN IAW EA.

Part: COVER — MISSING (EXIT SIGN) · airframe 51,196 hrs · 29,979 cycles

RIGHT OVERWING EMER EXIT SIGN COVER MISSING. R & R SIGN IAW MM.

Part: RIB — DAMAGED (LT HORIZ STAB) · airframe 50,319 hrs · 29,468 cycles

LEFT HORIZONTAL STABILIZER IN SPAR RIB STIFFENER DAMAGED AT STATION 138.87 RIB 32 INCHES FWD OF REAR SPAR. REPAIRED RIB IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

SEAT TRACK UPPER CHORD CRACKED AT BS 727B LBL 24.75. REPAIRED SEAT TRACK IAW EA.

Part: BEAM — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

BEAM CRACKED AT BS 727B RBL 45.5. REPAIRED BEAM IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

FORWARD SEAT TRACK INBD FLANGE CRACKED AT BS 727B LBL 24.75. REPAIRED FLANGE IAW EA.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

FLOORBEAM CRACKED AT BS 727B LBL 41.75. REPAIRED BEAM IAW EA.

Part: POST — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

LEFT NR 3 WINDOW FRAME E - F POST FASTENER HOLE NR 7 CRACKED. REPAIRED POST IAW ACO.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

SEAT TRACK CRACKED AT BS 727B RBL 45.5. REPAIRED SEAT TRACK IAW EA.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

FLOORBEAM CRACKED AT BS 727B LBL 45.5. REPAIRED BEAM IAW EA.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

ANGLE CRACKED AT BS 727B LBL 45.5. REPAIRED ANGLE IAW EA.

Part: STRAP — BROKEN (L1 DOOR) · airframe 50,319 hrs · 29,468 cycles

L1 DOOR EMER EVAC SLIDE COVER RETAINER PIN STRAP BROKEN. R & R STRAP IAW AMM & SIP.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

FORWARD SEAT TRACK CRACKED AT BS 727B RBL 24.75. REPAIRED SEAT TRACK IAW EA.

Part: POST — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

RIGHT NR 3 WINDOW FRAME E - F POST FASTENER HOLE NR 6 CRACKED. REPAIRED POST IAW ACO.

Part: BRACKET — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

BRACKET CRACKED AT BS 727B LBL 24.75. REPAIRED BRACKET IAW EA.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

FLOORBEAM CRACKED AT BS 727B LBL 24.75. REPAIRED BEAM IAW EA.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

FLOORBEAM CRACKED AT BS 727B RBL 45.5. REPAIRED BEAM IAW EA.

Part: POST — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

RIGHT NR 3 WINDOW FRAME E - F POST FASTENER HOLE NR 8 CRACKED. REPAIRED POST IAW ACO.

Part: POST — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

LEFT NR 3 WINDOW FRAME E - F POST FASTENER HOLE NR 8 CRACKED. REPAIRED POST IAW ACO.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

FORWARD SEAT TRACK CRACKED AT BS 727B LBL 24.75. REPAIRED SEAT TRACK IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

FORWARD SEAT TRACK CRACKED AT BS 727B LBL 45.5. REPAIRED SEAT TRACK IAW EA.

Part: POST — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

LEFT NR 3 WINDOW FRAME E - F POST FASTENER HOLE NR 9 CRACKED. REPAIRED POST IAW ACO.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 50,319 hrs · 29,468 cycles

FLOORBEAM CRACKED AT BS 727B RBL 24.75. REPAIRED BEAM IAW EA.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 50,319 hrs · 29,468 cycles

LEFT HORIZONTAL STABILIZER LOWER IN SPAR SKIN CRACKED AT STATION 129.50, RIB 18 INCHES FWD OF REAR SPAR. REPAIRED SKIN IAW SRM.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 50,319 hrs · 29,468 cycles

LEFT HORIZONTAL STABILIZER LOWER IN SPAR SKIN CRACKED AT STATION 101.90, RIB 11 INCHES FWD OF REAR SPAR. REPAIRED SKIN IAW SRM.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 50,319 hrs · 29,468 cycles

LEFT HORIZONTAL STABILIZER LOWER IN SPAR SKIN CRACKED AT STATION 129.50, RIB 10.5 INCHES FWD OF REAR SPAR. REPAIRED SKIN IAW SRM.

Part: STRAP — OUT OF POSITION (L1 DOOR) · airframe 50,319 hrs · 29,468 cycles

L1 DOOR EMER EVAC SLIDE STOWAGE PIN RETAINER STRAP OUT OF POSITION ON FWD SIDE OF SLIDE CONTAINER. REPOSITIONED STRAP IAW MM.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 50,319 hrs · 29,468 cycles

LEFT HORIZONTAL STABILIZER LOWER IN SPAR SKIN CRACKED AT STATION 138.70 RIB 32 INCHES FWD OF REAR SPAR. REPAIRED SKIN IAW SRM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 49,009 hrs · 28,681 cycles

BULLNOSE EMERGENCY EXIT LIGHT AT 16 DEF INOPERATIVE. R & R LIGHT ASSEMBLY IAW MM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 49,009 hrs · 28,681 cycles

LEFT OVERWING DOOR EMERGENCY EXIT LIGHTS INOPERATIVE. RELAMPED IAW MM.

Part: LENS — LOOSE (EXIT SIGN) · airframe 46,263 hrs · 27,037 cycles

R1 DOOR LOWER EMERGENCY EXIT SIGN LENS ATTACH BASE LOOSE. SECURED LENS IAW EA.

Part: BATTERY — FAILED (CABIN) · airframe 44,664 hrs · 26,072 cycles

LEFT OVERWING EMERGENCY LIGHT BATTERY FAILED CAPCITY CHECK. REMOVED AND REPLACED LEFT OVERWING EMERGENCY LIGHT BATTERY LOCATION M01668 PER MM AND SSM.

Part: GROUND WIRE — LOOSE (CABIN) · airframe 44,429 hrs · 25,920 cycles

EMERGENCY EXIT LIGHT AT 15RT OVERHEAD INOP. FOUND LOOSE GROUND. RE-TERMINATED GROUND WIRE PER WDM AND SWPM. OPS CHECK OK.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 747R, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 440, STR 8R. REPAIRED FRAME IAW EA NO.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FLOORBEAM CORRODED AT BS 294, BETWEEN RBL 36 TO RBL 46. REPAIRED BEAM IAW EA AND EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 500C, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 907, STR 8L. REPAIRED FRAME IAW ACO AND EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 480, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 827, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 400, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 727B, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 907, STR 8R. REPAIRED FRAME IAW AAR EA AND EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 867, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 400, STR 8L. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 727D, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 867, STR 8L. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 360, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 747, STR 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 787, STR 8R. REPAIRED FRAME IAW EA.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FLOORBEAM CORRODED AT BS 327.5, RBL 48. REPAIRED BEAM IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 747, STR 8L. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 827, STR 8L. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,650 hrs · 25,427 cycles

FRAME CRACKED AT BS 907, STR 8L. REPAIRED FRAME IAW EA.

Part: HOLDER — BROKEN (CABIN) · airframe 43,650 hrs · 25,427 cycles

FORWARD RIGHT EMERGENCY EXIT BATTERY PACK BASE FUSE HOLDER BROKEN AT BS 322. REMOVED AND REPLACED HOLDER IAW AMM.

Part: SIGN — DAMAGED (CABIN) · airframe 43,650 hrs · 25,427 cycles

FORWARD GALLEY EMERGENCY EXIT SIGN ASSEMBLY DAMAGED. REMOVED AND REPLACED SIGN ASSY IAW AMM.

Part: LIGHT — BROKEN (CABIN) · airframe 43,650 hrs · 25,427 cycles

FORWARD LAV EMERGENCY EXIT LIGHT BROKEN. REMOVED AND REPLACED LIGHT ASSY IAW AMM.

Part: POST — CRACKED (WINDOW FRAME) · airframe 43,650 hrs · 25,427 cycles

RIGHT WINDOW FRAME O/B UPPER POST CRACKED. REMOVED AND REPLACED FRAME PER ACO.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 43,650 hrs · 25,427 cycles

LEFT HORIZONTAL STABILIZER LOWER SKIN CRACKED AT STA 138.70. REPAIRED SKIN IAW SRM AND MM.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 43,650 hrs · 25,427 cycles

LEFT HORIZONTAL STABILIZER LOWER SKIN CRACKED AT STA 175.50. REPAIRED SKIN IAW SRM.

Part: SKIN — CRACKED (RT HORIZ STAB) · airframe 43,650 hrs · 25,427 cycles

RIGHT HORIZONTAL STABILIZER LOWER SKIN CRACKED AT STA 101.90, 9. REPAIR SKIN IAW SRM.

Part: POST — CRACKED (WINDOW FRAME) · airframe 43,650 hrs · 25,427 cycles

LEFT WINDOW FRAME O/B UPPER POST CRACKED. REMOVED AND REPLACED FRAME PER ACO.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 43,227 hrs · 25,152 cycles

R1 DOOR EMERGENCY EXIT LIGHT INOP. RELAMPED LIGHT PER M/M.

Part: FITTING — LOOSE (R1 DOOR) · airframe 42,999 hrs · 25,031 cycles

R1 DOOR EMERGENCY EVAC SLIDE FWD AND AFT GIRT BAR RETAINING CLIPS LOOSE. SECURED CLIP PER MM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 42,967 hrs · 25,014 cycles

FORWARD EEPLS INOP. REMOVED AND REPLACED EEPLS PER MM.

Part: LIGHT — DEFECTIVE (CABIN) · airframe 42,841 hrs · 24,938 cycles

BURNING SMELL BETWEEN ROW 9 TO ROW 13. REMOVED AND REPLACED LIGHT ASSY PER MM.

Part: REGULATOR — MALFUNCTIONED (BLEED AIR SYS) · airframe 42,232 hrs · 24,571 cycles

AIR TURNBACK - LT BLEED TRIP IN CLIMBOUT RESET THEN TRIP-OFF AGAIN. REMOVED AND REPLACED NR 1 HIGH STAGE PRESSURE REGULATOR & PRECOOLER CONTROL VALVE.

Part: BATTERY — FAILED (CABIN) · airframe 40,830 hrs · 23,784 cycles

DURING SCHEDULED HC2 CHECK, RT AFT GALLEY EMERGENCY BATTERY FAILED LONG TEST. REMOVED AND REPLACED BATTERY PER MM.

Part: BATTERY — FAILED (CABIN) · airframe 40,830 hrs · 23,784 cycles

DURING SCHEDULED HC2 CHECK, RT OVERWING GALLEY EMERGENCY BATTERY FAILED LONG TEST. REMOVED AND REPLACED BATTERY PER MM.

Part: CHARGER — FAILED (CABIN) · airframe 40,830 hrs · 23,784 cycles

DURING SCHEDULED HC2 CHECK, RT AFT GALLEY EMERGENCY BATTERY CHARGER FAILED LONG TEST. REMOVED AND REPLACED CHARGER PER MM.

Part: CHARGER — FAILED (CABIN) · airframe 40,830 hrs · 23,784 cycles

DURING SCHEDULED HC2 CHECK, RT OVERWING GALLEY EMERGENCY BATTERY CHARGER FAILED LONG TEST. REMOVED AND REPLACED CHARGER PER MM.

Part: FLAP — PUNCTURED (RT WING) · airframe 39,043 hrs · 22,755 cycles

DURING SCHEDULED MV1 CHECK FOUND, RT WING I/B AFT FLAP PUNCTURED. REPAIRED AFT FLAP PER EA.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 38,887 hrs · 22,665 cycles

DURING SCHEDULED MV1 CHECK FOUND, RT EMERGENCY EXIT LIGHT INOP AT ROW 15. RELAMPED PER MM.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 36,514 hrs · 21,257 cycles

DURING SCHEDULED 10Y CHECK, FOUND INTERCOSTAL IN COCKPIT CORRODED AT BS 268. REMOVED AND REPLACED INTERCOSTAL PER EA.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 36,514 hrs · 21,257 cycles

DURING SCHEDULED 10Y CHECK, FOUND ANGLE IN COCKPIT CORRODED AT BS 268, BETWEEN LBL 2 TO LBL 6. REMOVED AND REPLACED INTERCOSTAL PER EA.

Part: FITTING — CRACKED (CENTER WING BOX) · airframe 36,498 hrs · 21,247 cycles

DURING SCHEDULED 10Y CHECK, FOUND CENTER WING BOX UPPER SKIN FITTING CRACKED AT BS 540, RLB 41. REMOVED AND REPLACED FITTING PER SRM.

Part: FITTING — CORRODED (LT MLG TRUNNION) · airframe 35,149 hrs · 20,473 cycles

DURING SCHEDULED MV2 CHECK FOUND, LT MLG TRUNNION FITTING LUG FACES CORRODED. REPAIRED FITTING PER EA.

Part: FITTING — CORRODED (RT MLG TRUNNION) · airframe 35,149 hrs · 20,473 cycles

DURING SCHEDULED MV2 CHECK FOUND, RT MLG TRUNNION FITTING LUG FACES CORRODED. REPAIRED FITTING PER EA.

Part: LIGHT — INOPERATIVE (EXTERIOR) · airframe 34,817 hrs · 20,273 cycles

DURING SCHEDULED MV2 CHECK, FOUND R1 DOOR EXTERIOR EMERGENCY EXIT LIGHT INOP. RELAMPED PER MM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 34,046 hrs · 19,778 cycles

DURING SCHEDULED HC1 CHECK, EMERGENCY EXIT BATTERIES FAILED CAPACITY TEST. REMOVED AND REPLACED BATTERY PACK PER MM.

Part: SLIDE — UNSERVICEABLE (L2 DOOR) · airframe 33,127 hrs · 19,196 cycles

L2 DOOR EMERGENCY EVAC SLIDE PRESSURE INDICATOR OUT OF LIMITS. REMOVED AND REPLACED SLIDE PER MT.

Part: SLIDE — OUT OF POSITION (R1 DOOR) · airframe 30,950 hrs · 17,936 cycles

R1 DOOR EMERGENCY EVACUATION SLIDE OUT OF POSITION. REPOSITIONED SLIDE PER MM.

Part: LIGHT — BROKEN (CABIN) · airframe 29,973 hrs · 17,344 cycles

DURING SCHEDULED 8Y CHECK, FOUND FWD LAV AFT O/B WALL EMERGENCY EXIT LIGHT BROKEN. REMOVED AND REPLACED LIGHT PER MM.

Part: LIGHT — BROKEN (CABIN) · airframe 29,973 hrs · 17,344 cycles

DURING SCHEDULED 8Y CHECK, FOUND EMERGENCY EXIT LIGHT BROKEN ON G4 O/B AFT WALL. REMOVED AND REPLACED LIGHT PER MM.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 29,973 hrs · 17,344 cycles

DURING SCHEDULED 8Y CHECK, FOUND LT EMERGENCY EXIT HATCH LIGHT INOP. REMOVED AND REPLACED BATTERY CHARGER PER MM.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 29,973 hrs · 17,344 cycles

DURING SCHEDULED 8Y CHECK, FOUND SHEAR TIE CRACKED AT BS 540, RBL 32. REMOVED AND REPLACED SHEAR TIE PER SRM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 29,561 hrs · 17,077 cycles

DURING SCHEDULED HC1 CHECK, RT AFT CABIN EMERGENCY EXIT BATTERY PACK FAILED LONG TEST. REMOVED AND REPLACED BATTERY PACK PER MM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 29,561 hrs · 17,077 cycles

DURING SCHEDULED HC1 CHECK, EMERGENCY EXIT BATTERY PACK AT ROW 16 ABC FAILED LONG TEST. REMOVED AND REPLACED BATTERY PACK PER MM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 29,561 hrs · 17,077 cycles

DURING SCHEDULED HC1 CHECK, LT MID CABIN EMERGENCY EXIT BATTERY PACK FAILED LONG TEST. REMOVED AND REPLACED BATTERY PACK PER MM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 28,503 hrs · 16,420 cycles

DURING SCHEDULED MV2 CHECK, FOUND RT OVERWING EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED LIGHT BULB PER MM.

Part: WINDOW — ARCED (COCKPIT) · airframe 27,736 hrs · 15,957 cycles

FLIGHT DECK L2 WINDOW ARCED AND CRACKED PASSING FL 230. REMOVED AND REPLACED WINDOW AND WINDOW HEAT CONTROLLER PER MM.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 27,072 hrs · 15,534 cycles

DURING SCHEDULED HC2 CHECK, FOUND R2 DOOR EMERGENCY EXIT EXTERIOR LIGHT INOP. REMOVED AND REPLACED BATTERY PACK PER MM.

Part: LENS — LOOSE (EMERGENCY LIGHTS) · airframe 26,832 hrs · 15,387 cycles

EEPLS LENS LOOSE AT ROW 8 ABC. SECURED LENS PER MM.

Part: FITTING — LOOSE (R1 DOOR GIRT BAR) · airframe 26,274 hrs · 15,058 cycles

R1 DOOR EMERGENCY EVAC SLIDE FWD GIRT BAR FITTING LOOSE. SECURED FITTING PER MM.

Part: BRACKET — LOOSE (R1 DOOR GIRT BAR) · airframe 26,265 hrs · 15,053 cycles

R1 DOOR EMERGENCY EVAC SLIDE FWD GIRT BAR BRACKET LOOSE. SECURED BRACKET PER MM.

Part: SLIDE — OUT OF ADJUST (L2 DOOR) · airframe 26,092 hrs · 14,942 cycles

L2 DOOR EMERGENCY EVAC SLIDE OUT OF ADJUST. ADJUSTED EVAC SLIDE PER MM.

Part: BATTERY — FAILED (EMERGENCY LIGHT) · airframe 24,678 hrs · 14,161 cycles

DURING SCHEDULED HC1 CHECK, EMERGENCY EXIT BATTERY PACKS FAILED LONG TEST. REMOVED AND REPLACED BATTERY PACKS PER MM.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 22,455 hrs · 12,873 cycles

DURING SCHEDULED MV3 CHECK, FOUND EMERGENCY EXIT EXTERIOR LIGHT INOP RT AFT FUSELAGE. REMOVED AND REPLACED LIGHT BULB PER MM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 18,370 hrs · 10,549 cycles

DURING SCHEDULED MV2 CHECK, FOUND RT FWD CABIN EMERGENCY EXIT LIGHTS INOP. REMOVED AND REPLACED BATTERY PACK PER MM.

Part: SLIDE — OUT OF ADJUST (R2 DOOR) · airframe 17,219 hrs · 9,895 cycles

DURING SCHEDULED HC2 CHECK, FOUND R2 DOOR EMERGENCY EVAC SLIDE OUT OF ADJUST. ADJUSTED SLIDE PER MM.

Part: FUSE — INOPERATIVE (EMERGENCY LIGHT) · airframe 16,151 hrs · 9,279 cycles

DURING SPV, FOUND LT OVERWING EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED FUSE PER MM.

Part: LENS — LOOSE (EVAC SLIDE) · airframe 13,479 hrs · 7,711 cycles

R2 DOOR EVAC SLIDE PRESSURE GAUGE VIEWING LENS LOOSE. SECURED R2 DOOR LENS PER MM.

Part: LIGHT — INOPERATIVE (ROW 21) · airframe 11,880 hrs · 6,800 cycles

DURING SCHEDULED MS CHECK, FOUND EEPLS INOP AT ROW 21. RELAMPED EEPLS PER MM.

Part: ACTUATOR — FAULTY (LT/RT WING L/E) · airframe 11,210 hrs · 6,401 cycles

T/E FLAPS WOULD NOT RETRACT ON T/O AND NR 6 L/E SLAT STUCK. REMOVED AND REPLACED ALL L/E SLAT ACTUATORS PER MM.

Part: FSEU — FAULTY (E/E COMP) · airframe 11,207 hrs · 6,399 cycles

AIR TURN BACK, L/E SLATS WILL NOT RETRACT. REMOVED AND REPLACED FSEU PER MM.

Part: LENS — OUT OF POSITION (CABIN) · airframe 10,467 hrs · 5,989 cycles

RT OVERWING EMERGENCY EXIT LIGHT LENS FELL OFF. REINSTALLED LENS PER MM.

Part: GIRT BAR — LOOSE (ESCAPE SLIDE) · airframe 10,358 hrs · 5,922 cycles

DURING SCHEDULED C1 CHECK, FOUND FWD ENTRY DOOR EMERGENCY EVAC SLIDE GIRT BAR HOOKS LOOSE. REMOVED AND REPLACED HOOK FASTENERS PER SRM.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 8,466 hrs · 4,882 cycles

DURING SCHEDULED RON CHECK, FOUND FWD SVC DOOR OVERHEAD EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED BATTERY PACK PER MM.

Part: BALLAST — FAILED (CABIN) · airframe 6,689 hrs · 3,892 cycles

DURING SCHEDULED SERVICE CHECK, FOUND LT OVERWING EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED EXIT LIGHT BALLAST PER MM.

Part: BALLAST — FAILED (CABIN) · airframe 3,918 hrs · 2,300 cycles

DURING SCHEDULED C3 CHECK, FOUND LT OVERWING INTERIOR EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED LIGHT BALLAST PER MM.

Part: LIGHT — INOPERATIVE (EXTERIOR) · airframe 2,113 hrs · 1,202 cycles

DURING SCHEDULED SERVICE CHECK, FOUND EXTERNAL EMERGENCY LIGHT INOP AT RT WING. RELAMPED LIGHT ASSY PER MM.