N429WN

Part: WEB — CORRODED (ZONE 100) · airframe 72,793 hrs · 43,149 cycles

CORROSION ON UPPER WEB LOCATED BTW BS460 TO BS480 RBL70 WL197 AT FWD CARGO COMPARTMENT. REPLACED UPPER SILL WEB LOCATED BTW BS440 TO BS494 AT LEVEL STR18R RBL70 WL197 AT FWD CARGO COMPARTMENT I.A.W B737-700 SRM 41-40-02 AND DWG 143A8111 SHEET 12 REV-A. 143A0081 SHEET 38 REV-B.

Part: PLATE — CRACKED (ZONE 600) · airframe 72,793 hrs · 43,149 cycles

CRACK CORRUGATED PLATE TRAILING EDGE LOCATED ORSS275 AT RT WING. REPLACED CORRUGATED PLATE TRAILING EDGE LOCATED ORSS275 AT RT WING IAW SRM B737-700 51-10-02 SRM 51-40-02 AND DRAWING 115A 2001; SHEET 29; REV.-. MEASURE OF CRACK IS: 1.313.

Part: SCUFF PLATE — CRACKED (ZONE 100) · airframe 72,793 hrs · 43,149 cycles

CRACK ON CORNER SCUFF PLATE FWD POSITION AT FWD CARGO COMPARTMENT. REPAIRED CORNER SCUFF PLATE FWD POSITION AT FWD CARGO COMPARTMENT I.A.W. BOEING 737-700 SRM 53-30-15-2R-1 REPAIR 1; AND BAC 5975.

Part: PLATE — CRACKED (ZONE 600) · airframe 72,793 hrs · 43,149 cycles

CRACK CORRUGATED PLATE TRAILING EDGE LOCATED ORSS261 AT RT WING 2025-390051<[01]. REPLACED CORRUGATED PLATE TRAILING EDGE LOCATED ORSS261 AT RT WING IAW SRM B737-700 51-10-02; SRM B737-700 51-40-02 AND DRAWING # 115A 2001; SHEET 29; REV.-. MEASURE OF CRACK IS: 1.259? TOOL USED: PN: 500-752-20; SN: B21034763; DUE DATE: 17-OCT-25.; [02] JOB COMPLETED.

Part: ANGLE — CRACKED (ZONE 600) · airframe 72,793 hrs · 43,149 cycles

CRACK ON ANGLE LOCATED ACCESS PANEL 651FB TRAILING EDGE AT RT WING 2025-390049 <[01]. REPLACED ANGLE LOCATED ON ACCESS PANEL 651FB TRAILING EDGE AT RT WING IAW B737-700 SRM 51-40-02 AND DWG 115A2710; SHEET 6 REV: B. LENGTH OF CRACK IS: 0.371? TOOL USED CALIPER PN: 500-193-30; S/N:0058147 AND DUE DATE: 17-FEB-26; [02] REPLACED ANGLE LOCATED ON ACCESS PANEL 651FB TRAILING EDGE AT RT WING IAW B737-700 SRM 51-40-02 AND DWG 115A2710; SHEET 6 REV: B. LENGTH OF CRACK IS: 0.371? TOOL USED CALIPER PN: 500-193-30; S/N:0058147 AND DUE DATE: 17-FEB-26.

Part: PLATE — CRACKED (ZONE 500) · airframe 72,793 hrs · 43,149 cycles

CRACK CORRUGATED PLATE TRAILING EDGE LOCATED ORSS236 AT LT WING 2025-390053 <[01]. REPLACED CORRUGATED PLATE AND FASTENERS LOCATED ORSS236 AT LT WING IAW B737-700 SRM 51-40-02 AND DWG: 115A2001 SHEET: 49; REV: - TOOK LENGTH OF CRACK ON CORRUGATED IS 0.765 INCH TOOL USED CALIPER P/N: 500-197-30; S/N: A23304029 AND DUE DATE: 10-NOV-25; [02] COMPLETED

Part: STRUCTURE — CORRODED (ZONE 500) · airframe 72,793 hrs · 43,149 cycles

CORROSION AROUND OF BOOST PUMP LOCATED TRAILING EDGE AT LEVEL IRSS 145 AT LT WING. PERFORMED REWORK AND EVALUATED AREA ON AROUND OF FUEL BOOST PUMP LOCATED TRAILING EDGE AT LEVEL IRSS145 AT LT WING AND FOUND WITHIN LIMITS IAW SRM 57-20-10-1A-3 ALLOWABLE DAMAGE 3.

Part: PLATE — CRACKED (ZONE 500) · airframe 72,793 hrs · 43,149 cycles

CRACK CORRUGATED PLATE TRAILING EDGE LOCATED ORSS 261 AT LT WING. REPLACED CORRUGATED PLATE TRAILING EDGE LOCATED ORSS 261 AT LT WING IAW SRM 51-40-02 AND SRM 51-10-02 ITEM 9. LENGTH OF CRACK IS:0.467.

Part: SUPPORT ANGLE — CRACKED (ZONE 600) · airframe 72,793 hrs · 43,149 cycles

CRACK ON SUPPORT ANGLE OF ACCESS PANEL 651GB LOCATED TRAILING EDGE AT RT WING 2025-390033 <[01]. REPLACED SUPPORT ANGLE OF ACCESS PANEL 651GB LOCATED TRAILING EDGE AT RT WING IAW B737-700 SRM 51-40-02 AND SRM 51-10-02 Ï¿½TEM 9 AND DWG 115A2714 SHEET 6 REV-. MEASURE OF CRACK IS: 1.100?. TOOL USED ELECTRONIC CALIPER P/N: 500-752-20; S/N: B21034763 AND DUE DATE: 17-OCT-25;[02] TASK COMPLETED.

Part: PANEL — ELONGATED (ZONE 500) · airframe 72,793 hrs · 43,149 cycles

ELONGATED HOLE FITTING ON ACCESS PANEL 551GB TRAILING EDGE AT LT WING 2025-390023 <[01]. REPLACED BRACKET ON ACCES PANEL 551GB TRAILING EDGE AT LT WING IAW B737-700 SRM 51-10-02-0G; 51-40-02-0G AND DWG: 115A2714; SHEET: 6; REV: -; [02] COMPLETED JOB.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 72,793 hrs · 43,149 cycles

CRACK BREAK PANEL ON FLOOR STRUCTURE LOCATED STA 540 BTW BL 0 TO RBL 24.75 AT PASSENGER CABIN. REPLACED BREAK PANEL LOCATED ON FLOOR STRUCTURE LOCATED ON STA 540 BTW BL 0 TO RBL 24.75 AT PASSENGER CABIN IAW SRM 51-40-02 AND DWG 143A5240; SHEET: 13 AND REV: -. <BR>TOOK MEASURE OF CRACK; L=0.996.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 72,793 hrs · 43,149 cycles

CRACK ANGLE FLOOR STRUCTURE LOCATED STA 695 AND LBL 24.75 AT PASSENGER CABIN. REPLACED SUPPORT BRACKET AND NEW FASTENERS ON FLOOR STRUCTURE LOCATED STA 695 AND LBL 24.75 AT PASSENGER CABIN IAW SRM 51-40-02; SRM 51-10-02 ITEM 9 AND DWG 273A9110 SHEET 6 REV: A.

Part: CREASE BEAM — CORRODED (ZONE 200) · airframe 72,793 hrs · 43,149 cycles

CORROSION CREASE BEAM AT LEVEL STA 639 RBL 64 AND WL 208.1 AT PASSENGER CABIN. REPLACED CREASE BEAM (INNER CHORD) AND FASTENERS AT LEVEL BTW STA 613 TO BS 664 RBL 64 AND WL 208.1 AT PASSENGER CABIN IAW SRM 51-40-02; SRM 51-10-02 Ï¿½TEM 9 AND DWG 144A5901 SHEET 20 AND SHEET 21 REV-A.

Part: RIB — CRACKED (ZONE 300) · airframe 72,793 hrs · 43,149 cycles

CRACK INSPAR RIB 5 (STAB STA 129.50) AT 26.5 INCHES FROM LEADING EDGE LT HORIZONTAL STAB. PERFORMED REPAIR LOCATED STAB STA 129.50) AT 26.5 INCHES FROM LEADING EDGE LT HORIZONTAL STAB IAW SRM 55-10-09-2R-4 REPAIR 4.

Part: LIGHT — BROKEN (ZONE 200) · airframe 72,793 hrs · 43,149 cycles

BROKEN PHOTOLUMINESCENT STRIP RH SIDE AT PASSENGER CABIN (6 EA) 2025-389875<[01] THE REPLACEMENT PHOTOLUMINESCENT STRIP RH SIDE AT PASSENGER CABIN (6 EA) SEE TASK 733-50-01 (TTG8Q00FRFA6).;[02] COMPLETED JOB

Part: LIGHT — BROKEN (ZONE 200) · airframe 72,793 hrs · 43,149 cycles

BROKEN PHOTOLUMINESCENT STRIP LH SIDE AT PASSENGER CABIN (5 EA) THE REPLACEMENT PHOTOLUMINESCENT STRIP LH SIDE AT PASSENGER CABIN (5 EA) SEE TASK 733-50-01 (TTG8Q00FRFA6).;[02] COMPLETED JOB

Part: ANGLE — CRACKED (ZONE 500) · airframe 72,793 hrs · 43,149 cycles

CRACK ANGLE TRAILING EDGE LOCATED AFT POSITION AT LEVEL ORSS 270 AT LT WING 2025-389821<[01]. REPLACED ANGLE ON TRAILING EDGE LOCATED AFT POSITION AT LEVEL ORSS 270 AT LT WING IAW B737-700 SRM 51-40-02 AND DWG 115A2930 SHEET 7 REV:-. LENGTH OF CRACK IS: 1.056? TOOL USED CALIPER P/N:500-197-30; S/N: A23304029 AND DUE DATE: 10-NOV-25;[02] REPLACED ANGLE ON TRAILING EDGE LOCATED AFT POSITION AT LEVEL ORSS 270 AT LT WING IAW B737-700 SRM 51-40-02 AND DWG 115A2930 SHEET 7 REV:-. LENGTH OF CRACK IS: 1.056? TOOL USED CALIPER P/N:500-197-30; S/N: A23304029 AND DUE DATE: 10-NOV-25

Part: ANGLE — CRACKED (ZONE 600) · airframe 72,793 hrs · 43,149 cycles

CRACK ANGLE TRAILING EDGE LOCATED AFT POSITION AT LEVEL ORSS 270 AT RT WING 2025-389818 <[01]. REPLACED ANGLE TRAILING EDGE LOCATED AFT POSITION AT LEVEL ORSS 270 AT RT WING IAW B737-700 SRM 51-40-02; SRM 51-10-02 ITEM 9 AND DWG 115A2930 SHEET 8 REV-.TOOL USED DIGITAL CALIPER P/N: 500-197-30; S/N: A23304055 AND DUE DATE: 10-NOV-25.; [02] REPLACED ANGLE TRAILING EDGE LOCATED AFT POSITION AT LEVEL ORSS 270 AT RT WING IAW B737-700 SRM 51-40-02; SRM 51-10-02 ITEM 9 AND DWG 115A2930 SHEET 8 REV-.TOOL USED DIGITAL CALIPER P/N: 500-197-30; S/N: A23304055 AND DUE DATE: 10-NOV-25.; [03] CORRECTED MEASUREMENTS FAILURE TYPE TO YES.

Part: ANGLE — CRACKED (ZONE 500) · airframe 72,793 hrs · 43,149 cycles

CRACK ANGLE TRAILING EDGE LOCATED ORSS 279 AT LT WING. REPLACED ANGLE LOCATED ON TRAILING EDGE LOCATED ORSS 279 AT LT WING. IAW B737-700 SRM 51-10-02; ITEM 9. SRM 51-40-02 AND DWG 115A6200; SHEET: 10 AND REV: -.

Part: BATTERY PACK — INOPERATIVE (ZONE 200) · airframe 72,793 hrs · 43,149 cycles

INOP BATTERY PACK LH SIDE AT FWD GALLEY AREA (1EA). REPLACED BATTERY PACK LH SIDE AT FWD GALLEY AREA (1EA) IAW B737-700 AMM 33-51-06-960-805. INSTALLATION TEST IS OK.

Part: LIGHT — INOPERATIVE (ZN 200 FUS TOP) · airframe 72,793 hrs · 43,149 cycles

INOP EMERGENCY LIGHT LAV A AT FWD GALLEY AREA. REPLACED EMERGENCY LIGHT LAV A AT FWD GALLEY AREA IAW B737-700 AMM-33-51-01-960-802. PERFORMED OPERATIONAL TEST IS OK;

Part: PRESSURE DECK — CRACKED (ZONE 100) · airframe 72,793 hrs · 43,149 cycles

CRACK INDICATION FOUND ON HORIZONTAL PRESSURE DECK WEB AT RBL 42 BETWEEN STA 663 TO STA 675 AT MAIN WHEEL WELL COMPARTMENT. CRACK LENGTH: 0.500 IN. APPROX 2025-389846<[01] TOOL USED ON STEP 6; 7 AND 8. ET EQUIPMENT: P/N: NORTEC 600D; S/N: 60007161486; CAL DUE DATE: 06-SEP-25;[02] PERFORMED PERMANENT REPAIR ON PRESSURE DECK WEB RBL 30 TO RBL 60 STA 663 TO STA 675 AT PASSENGER CABIN IAW B737-700 SRM 53-40-51-2R-2 REPAIR 2; SEE INDIVIDUAL SIGNOFF BELOW;[03] CERTIFIED ACTION 2; COMPLETED<BR>RII

Part: PRESSURE DECK — CRACKED (ZN 100 FUS LOWER) · airframe 72,793 hrs · 43,149 cycles

CRACK INDICATION FOUND ON HORIZONTAL PRESSURE DECK WEB AT LBL 31 BETWEEN STA 663 TO STA 675 AT MAIN WHEEL WELL COMPARTMENT. CRACK LENGTH: 0.250 IN. APPROX. REWORKED AREA OF TOOLING MARK LOCATED ON WEB AT LBL 60 BTW STA 663 TO STA 675 AND FOUND WITHIN LIMITS DUE TO NOT EXCEED 10% OF ALLOWABLE DAMAGE I.A.W B737-700 SRM 53-40-13-1A-1. ALLOWABLE DAMAGE 1. STEP 4.C.(2)(A); FIGURE ?G?. MEASURE OF REWORKED AREA ARE: L= 2.477? ;W= 0.663? AND Y= 0.006. VERIFIED NOMINAL THICKNESS OF WEB IS: 0.063? I.A.W B737-700 SRM 53-40-51-0I-2; IDENTIFICATION 2. FIGURE 3; TABLE 3; ITEM 19.; PERFORMED PERMANENT REPAIR ON PRESSURE DECK WEB LBL 30 TO LBL 60 STA 663 TO STA 675 AT PASSENGER CABIN IAW SRM 53-40-51-2R-2 REPAIR 2.

Part: ANGLE — CRACKED (ZONE 600) · airframe 72,793 hrs · 43,149 cycles

CRACK ANGLE TRAILING EDGE LOCATED FWD POSITION AT LEVEL ORSS 270 AT RT WING. REPLACED ANGLE TRAILING EDGE LOCATED FWD POSITION AT LEVEL ORSS 270 AT RT WING IAW SRM 51-10-02; ITEM 9 AND SRM 51-40-02. MEASURE OF CRACK IS 0.995.

Part: SIGN — INOPERATIVE (ZONE 200) · airframe 72,628 hrs · 43,053 cycles

AFT FL.ATT. CALL LT INOP <[01]. OKAY TO CONT. PER M.E.L> 23-19-03 SP#1B. AUTH. # 256009; [02] REMOVED AND REPLACED AFT EMER EXIT SIGN LIGHT ASSY PER AMM 33-51-01.

Part: TRAY — OUT OF ADJUST (ZONE 200) · airframe 72,142 hrs · 42,754 cycles

TRAY TABLE LATCHES INSTALLED AT SEAT ROWS 11BC ARE NOT EMERGENCY EXIT ONLY F/T LATCHS. <[01] REMOVED AND INSTALLED LH ONE WAY EMERGENCY EXIT ONLY F/T LATCHES REF CMM 25-21-42.

Part: SLIDE — OUT OF ADJUST (ZN 800 DOOR) · airframe 71,002 hrs · 42,049 cycles

FA ADVISED FRWD ENTRY DOOR YELLOW SLIDE PLACARD IS NOT IN CORRECT LOCATION. IT SEEMS TO EITHER BE TOO SHORT OR IN WRONG LOCATION.<[01] ADJUSTED PULL STRAP COVER ON FWD ENTRY DOOR SLIDE IAW AMM 25-66-00; NO FURTHER DEFECTS.

Part: SIGN — LOOSE (ZN 200 FUS TOP) · airframe 70,910 hrs · 42,000 cycles

AFT GALLEY EXIT SIGN LOOSE<[01] RESECURED AFT GALLEY OVERHEAD EXIT SIGN IAW AMM 35-51-01.;[02] INCORRECT REFERENCE USED READS RESECURED AFT GALLEY OVERHEAD EXIT SIGN IAW AMM 35-51-01.<BR>SHOULD READ: RESECURED AFT GALLEY OVERHEAD EXIT SIGN IAW AMM 33-51-01.<BR>EMPLOYEE TELECOM

Part: SLIDER — CRACKED (ZONE 300) · airframe 70,766 hrs · 41,910 cycles

LEFT HORIZONTAL STAB FWD LOWER SLIDER IS CRACKED.<[01] 01 - REMOVED AND REPLACED SLIDER PER [AMM 20-50-11-201-NG (STANDARD TORQUE VALUES - MAINTENANCE PRACTICES - PERMANENT)]

Part: SLIDE — EXPOSED (ZONE 800) · airframe 70,743 hrs · 41,898 cycles

R2 AFT RH SERVICE DOOR EMERGENCY SLIDE EXPOSED ON BOTTOM.<[01] REPACKED ESCAPE SLIDE PACK AND INSTALLED ON R2 SERVICE DOOR IAW AMM 25-66-01 AND MT 725-61-06. NO FURTHER DEFECTS NOTED.

Part: SLIDE — OUT OF ADJUST (ZONE 200) · airframe 69,963 hrs · 41,396 cycles

FWD SERVICE DOOR SLIDE OUT OF PANEL<[01] REMOVED AND REPLACED FS EMERGENCY ESCAPE SLIDE PER MM 25-66-01

Part: FAIRING — CRACKED (ZONE 500) · airframe 69,813 hrs · 41,312 cycles

#3 FLAP FAIRING TIP APPEARS TO HAVE A STRESS ALONG THE OUTBOARD SIDE<[01] R&R'D #3 FLAP FAIRING TIP IAW AMM 27-51-18;[02] VERIFIED THE FOLLOWING:<BR>R&R'D #3 FLAP FAIRING TIP IAW AMM 27-51-18

Part: BATTERY PACK — FAILED (ZN 200 FUS TOP) · airframe 68,509 hrs · 40,520 cycles

EMX BATT PACK M01669 FAILS CAPACITANCE CHECK<[01] REMOVED AND REPLACED EMX BATT M01669 PER AMM 33-51-06

Part: SEAT TRACK — ELONGATED (COCKPIT) · airframe 68,509 hrs · 40,520 cycles

FIRST OFFICERS SEAT I/B AFT TRACK FAILS ADJUSTMENT HOLE INSPECTION<[01] REMOVED AND REPLACED FIRST OFFICERS SEAT I/B AFT TRACK PER AMM 25-11-11

Part: CARGO TRACK — OUT OF ADJUST (ZN 100 FUS LOWER) · airframe 68,509 hrs · 40,520 cycles

CAPT I/B AFT SEAT TRACK FAILS ADJUSTMENT HOLE INSPECTION<[01] REMOVED AND REPLACED CAPT I/B AFT SEAT TRACK PER AMM 25-11-11

Part: BATTERY PACK — FAILED (ZN 200 FUS TOP) · airframe 68,509 hrs · 40,520 cycles

EMX BATT M01672 FAILS CAPACITANCE CHECK<[01] REMOVED AND REPLACED EMX BATT PACK M01672 PER AMM 33-51-06

Part: SEAL — CRACKED (ZN 300 STABILIZE) · airframe 68,509 hrs · 40,520 cycles

L/H HORIZONTAL STABILIZER FWD UPPER SLIDE SEAL CRACKED<[01] REMOVED AND REPLACED L/H HORIZONTAL STABILIZER FWD UPPER SLIDE SEAL IAW BOEING 737 AMM 53-31-31.

Part: SEAL — CRACKED (ZN 300 STABILIZE) · airframe 68,509 hrs · 40,520 cycles

R/H HORIZONTAL STABILIZER FWD UPPER SLIDE SEAL CRACKED<[01] REMOVED AND REPLACED R/H HORIZONTAL STABILIZER FWD UPPER SLIDE SEAL IAW BOEING 737 AMM 53-31-31. OPS CHECK GOOD.

Part: SIGN — OUT OF ADJUST (ZN 200 FUS TOP) · airframe 67,598 hrs · 39,953 cycles

FWD SERVICE DOOR EXIT LIGHT COVER FELL OFF / [01] REPLACED FWD SERVICE DOOR EMERGENCY EXIT SIGN ASSY OPS CHECK GOOD AMM 33-51-01

Part: GIRT BAR — LOOSE (ZN 800 DOOR) · airframe 67,358 hrs · 39,808 cycles

R1 DOOR SLIDE GIRT BAR BRACKETS LOOSE.<[01] TIGHTENED GIRT BAR BRACKETS PER S.I.P.

Part: FUEL SYS — VENTING (RT WING) · airframe 67,210 hrs · 39,714 cycles

ON TAXI OUT FUEL VENTED FROM F/O WING. RECOMMEND ACCOMPLISHING AUTO-SHUTOFF VALVE TEST TO MAKE SURE THIS DOES NOT HAPPEN AGAIN. THIS WAY WE CAN MAKE SURE THE FLOAT SWITCH WORKS AS WELL AS THE VALVE. RIGHT WING WAS AT 8800 ON THE STICK THEY MOVED 200 LBS TO THE CENTER QUANTITY INDICATIONS WERE NORMAL IN COCKPIT VS THE STICKS SO NO INDICATION ISSUES. OK TO CONTINUE PER MEL 28-10-03. SP1 AND SP1B C/W. AUTHORIZATION #158528. PERFORMED PRESSURE FUELING SYSTEM TEST IAW AMM 28-21-00. OPERATES NORMAL

Part: SENSOR — POWER LOSS (ZN 200 FUS TOP) · airframe 66,607 hrs · 39,321 cycles

ON APPROACH; WHEN SETTING FLAPS 15 FLAP ASSYMETRY OCCURED; FLAPS 10 ON LEFT WING; FLAPS 15 ON RIGHT WING *CALL MOC SO WE CAN UPDATE THE LOGPAGE AND PAGE #*<[01] VERIFIED INTEGRITY OF WIRING FROM #7 & 8 SKEW SENSORS TO D43104J PER WDM 27-53-21<BR>REPLACED #7 SKEW SENSOR DUE TO POWER LOSS TO #8 SKEW SENSOR PER MM 27-59-01

Part: SENSOR — SPLIT (ZN 200 FUS TOP) · airframe 66,605 hrs · 39,318 cycles

TEF FLAP ASYMMETRY. BOTH L AND R TEF INDICATORS LESS THAN 1 (AND SPLIT INDICATION)<[01] REMOVED AND REPLACED #8 FLAP SKEW SENSOR PER AMM 27-59-01

Part: LIGHT — INOPERATIVE (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

EMERGENCY LIGHT AT AFT GALLEY DOOR HAS BURNED OUT BULB<[01] RE-LAMPED EMERGENCY LIGHT AT AFT GALLEY DOOR PER AMM 33-51-01-960-801. OPS CHECK GOOD.;[02] VERIFIED CORRECTIVE ACTION 1

Part: LIGHT — INOPERATIVE (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

AFT RH SERVICE DOOR EXTERIOR EMERGENCY LIGHT INOP<[01] REMOVED AND REPLACED AFT RH SERVICE DOOR EXTERIOR EMERGENCY LIGHT LAMP IAW AMM 33-51-04-960-801;[02] CERTIFIED ACTION 1;[03] VERIFIED CORRECTIVE ACTION 1

Part: MEGAPHONE — BROKEN (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

AFT MEGAPHONE HANDLE IS BROKEN<[01] REPLACED AFT MEGAPHONE PER AMM 25-64-00-710-801 STEP 6. C; AND 7. OPS CHECK IT'S GOOD.;[02] VERIFIED CORRECTIVE ACTION #1.

Part: BAFFLE — CRACKED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

FWD CARGO BAY BAFFLE IS CRACKED AT BS 500B-500C RBL 21 WL 156<[01] VERTIFY APPLICABILITY PER SRM 53-30-53-0I-2 IDENTIFICATION NOT ALLOWABLE DAMAGE PARTS THAT DO NOT HAVE ENTRIES ARE CALLED REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02 STEP 9C;[02] RECEIVED NEW BAFFLE ON FWD CARGO BAY BS 500B-BS 500C RBL 21 WL 156 P/N143A7510-12 PO# 833831. LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG143A75402<BR>OK TO INSTALL;[03] REMOVED ON FWD CARGO BAY BAFFLE AT BS 500B TO BS 500C RBL21 WL156 IAW SRM 51-40-02;[04] VERIFIED CORRECTIVE ACTION 1-3. OK TO INSTALL;[05] INSTALLED ON FWD CARGO BAY BAFFLE AT BS 500B TO BS 500C RBL21 WL 156 IAW SRM 51-40-02 AND DWG143A7505;[06] VERIFIED CORRECTIVE ACTION #5.<BR>VERIFIED MEASUREMENTS.

Part: SKIN — CORRODED (ZN 300 STABILIZE) · airframe 66,602 hrs · 39,316 cycles

LITE SURFACE CORROSION ON UPPER CROWN SKIN UNDER VERTICAL STAB BETWEEN FUSELAGE STATION 1016 AND 1040 AND STRINGERS 2L AND 2R.<FOUND TO BE OUT OF LIMITS DUE TO MORE THAN THREE AREAS HAVING DAMAGED REMOVAL AROUND THREE FASTENERS OUT OF A GROUP OF TEN IAW SRM 53-00-01-1A-1 ALLOWABLE DAMAGE 1 DETAIL D;[06] VERIFIED CORRECTIVE ACTION 5;[07] REQUESTED UT REMAINING THICHNESS OF THE BLENDED AREAS;[08] ACCOMPLISHED UT INSPECTION OF BLEND AREA'S LOWEST THICKNESS IN ORIGINAL .080 IS .076; IN .063 LOWEST IS .061 IAW 737 NDTM PART 4; 51-00-00 PROCEDURE 2 TOOL ID ATS2031 CAL. DUE 05/2024.;[09] UPDATED GRID FOR MEASUREMENTS ILLEGIBLE NUMBERS;[10] COMPLETED STEP 1. INSTALLED FASTENERS AT DISCREPANCY AREA PER EA NO:23-153-01748; DWG#148A3110; AND SRM 51-40-02;[11] VERIFIED STEP 1;[12] ACCOMPLISHED UT INSPECTION OF BLEND AREA'S LOWEST THICKNESS IN ORIGINAL .080 IS .073; IN .063 LOWEST IS .061 IAW 737 NDTM PART 4; 51-00-00 PROCEDURE 2 TOOL ID ATS2031 CAL. DUE 05/2024. ATS UT LEVEL III TERRY HARRIS;[13] UPDATED MEASUREMENT FIELD;[14] AS PER EA 23-153-01748; THE DAMAGE IS ACCEPTABLE AS A CONTINUE-IN-SERVICE CONDITION WITHOUT REPETITIVE INSPECTIONS AND NO TERMINATING ACTION REQUIREMENTS.;[15] VERIFIED MEASUREMENT TABLE AND CORRECTIVE ACTION 14

Part: SCUFF PLATE — CRACKED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

AFT CARGO BAY AFT CORNER SCUFF PLATE IS CRACKED<[01] WELDED CRACK ON AFT CARGO BAY AFT CORNER SCUFF PLATE USING ER4043 FILLER ROD LOT NUMBER 1131216 PER SRM 53-60-15-2R-1 REPAIR 1 PARA 4.B. (2) AND (4)<BR>EQUIPMENT USED: WELDING MACHINE E10583; CALIBRATION DUE 01/2024;[02] VERIFIED CORRECTIVE ACTION ITEM 1.;[03] DYE PENETRANT INSPECTED WELDED AREA PER SOPM 20-20-02. NO DEFECTS NOTED. EQUIPMENT USED DLM-1000 RADIOMETER; ID # ATS2561; CAL DUE: 08/31/2023;[04] SANDED WELD AREA PER SRM 53-60-15-2R-1 REPAIR 1 PARAGRAPH 4.B. (5);[05] VERIFIED CORRECTIVE ACTION ITEM 4.;[06] ALL MAINTENANCE ACTION ARE COMPLETE REQUEST FINAL BUY OFF.;[07] VERIFIED MEASUREMENT TABLE

Part: PANEL — CRACKED (ZN 600 RIGHT WIN) · airframe 66,602 hrs · 39,316 cycles

RT WING T/E PANEL 661BB AFT FASTENER HOLES ARE CRACKING AROUND EDGES<DAMAGE TO BE REPAIRED IAW SRM 51-70-04-2R-9 AS DIRECTED BY SRM 57-51-01-2R-1 PARA 4 B (2) TABLE 202.<BR><BR>REMOVED DAMAGE TO (52EA) FASTENER HOLES ALL TO A MEASURE OF .5'DIA; CLEANED; WITH NO CONTAMINATION NOTED IAW 51-70-04-2R-9 PARA 4 A-C.;[02] VALIDATED APPLICABILITY OF DAMAGE TO BE REPAIRED IAW SRM 51-70-04-2R-9.;[03] VERIFIED CORRECTIVE ACTION ITEMS 1-2 AND MEASUREMENTS TABLE.;[04] MIXED RESIN BMS8-301 CL1 LOT#JH2EAA8895 AND CHOPPED FIBERS AND APPLIED TO DAMAGED AREA IAW 51-70-04-2R-9 PAR 4 D-E.;[05] RESIN MIXTURE CURED THEN COMPLETED THE SURFACE PREPARATION & CLEANING PROCESS IAW SRM 51-70-04-2R-9 PARA 4. STEPS F-I. REF CAL TOOL HOT BONDER ID ATS2802 CAL DUE 10/2023;.USING BMS9-3 STYLE 1581 GLASS LOT 1522395-2 & BMS8-301/EA9390 RESIN LOT JH2EAA8895. FABRICATE D REPAIR PLIES; THEN LAID UP THE REPAIR; VACUUM BAGGED; LEAK CHECKED THEN SET TO CURE IAW SRM 51-70-04-2R-9 PARA 4. STEPS J; K & L. REF CAL TOOL HOT BONDER ID ATS2802 CAL DUE 10/2023.;[09] REPAIR PLIES CURED IAW SRM 51-70-04-2R-9 PARA 4. M. PER GENERAL REPAIR SECTION SRM 51-70-04-2R-0 PARA 4. N. (2). FIGURE 214. PAGE 39.<BR>REF CAL TOOL HOT BONDER ID ATS2802 CAL DUE 10/2023.<BR>REQUEST POST REPAIR EXAMINATION IAW SRM 51-70-04-2R-9 PARA 4. O. COMPLETED REFINISHING OUTER SURFACE OF PANEL 661BB IAW SRM 51-70-04-2R-9 PAR 4.P.;[15] VERIFIED CORRECTIVE ACTION ITEMS 12-14.

Part: PANEL — CRACKED (ZN 600 RIGHT WIN) · airframe 66,602 hrs · 39,316 cycles

RT WING T/E PANEL 661BB AFT FASTENER HOLES ARE CRACKING AROUND EDGES<[01] IDENTIFIED PANEL 661BB IAW SRM 57-51-01-0I-1 FIGURE 3; TABLE 2; ITEM (9).<BR><BR>PANEL IS BEYOND ALLOWABLE DAMAGE LIMITS IAW SRM 57-51-01-1A-1 PARA 4 B (5)(A).<BR><BR>DAMAGE TO BE REPAIRED IAW SRM 51-70-04-2R-9 AS DIRECTED BY SRM 57-51-01-2R-1 PARA 4 B (2) TABLE 202.<BR><BR>REMOVED DAMAGE TO (52EA) FASTENER HOLES ALL TO A MEASURE OF .5'DIA; CLEANED; WITH NO CONTAMINATION NOTED IAW 51-70-04-2R-9 PARA 4 A-C.;[08] USING BMS9-3 STYLE 1581 GLASS LOT 1522395-2 & BMS8-301/EA9390 RESIN LOT JH2EAA8895. FABRICATE D REPAIR PLIES; THEN LAID UP THE REPAIR; VACUUM BAGGED; LEAK CHECKED THEN SET TO CURE IAW SRM 51-70-04-2R-9 PARA 4. STEPS J; K & L. REF CAL TOOL HOT BONDER ID ATS2802 CAL DUE 10/2023.;[09] REPAIR PLIES CURED IAW SRM 51-70-04-2R-9 PARA 4. M. PER GENERAL REPAIR SECTION SRM 51-70-04-2R-0 PARA 4. N. (2). FIGURE 214. PAGE 39.<BR>REF CAL TOOL HOT BONDER ID ATS2802 CAL DUE 10/2023.<BR>REQUEST POST REPAIR EXAMINATION IAW SRM 51-70-04-2R-9 PARA 4. O

Part: FLAP — DELAMINATED (ZN 500 LEFT WING) · airframe 66,602 hrs · 39,316 cycles

LT WING O/B AFT FLAP HAS AREA OF DELAMINATION ON UPPER SURFACE NEAR I/B AFT CORNER.<[01] IDENTIFIED AFT FLAP IAW SRM 57-53-01-0I-4; FIG 2; TABLE 2; ITEM 2.<BR><BR>DAMAGE IS BEYOND ALLOWABLE DAMAGE LIMITS IAW SRM 57-53-01-1A-4 PARA 4.A (5).<BR><BR>DAMAGE IS REPAIRABLE IAW SRM 51-70-10-2R-4 AS DIRECTED BY SRM 57-53-01-2R-4 PARA 3.B.<BR><BR>STARTED DAMAGE REMOVAL OF UPPER SKIN (APPROX 10' X 10') IAW SRM 51-70-10-2R-4 PARA 3.A.;[02] FLAP ASSEMBLY WILL BE REMOVED AND REINSTALLED ON TTG8Q00L4LDF.;[03] UPDATED PARTS REQUIREMENT;[04] /LT WING O/B AFT FLAP WAS REPLACED AND WILL BE REMOVED AND INSTALLED ON THE AIRCRAFT ON FAULT TTG8Q00L4LDF.;[05] VERIFIED CORRECTIVE ACTION STEPS 1-4. TASK CARD COMPLETE.

Part: FRAME — CRACKED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

BS 312 FRAME CRACKED AT FED HEADER FRAME<[01] ACCOMPLISHED REPAIR PER EA#M-22-153-01244 ON FAULT#TTG8Q00L4U7D;[02] VERIFIED CORRECTIVE ACTION 1 AND MEASUREMENT TABLE

Part: INTERCOSTAL — CRACKED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

INTERCOSTAL CRACKED AT BS 259.5; WL 207; LBL 5<[01] RECIVED FABRICATED INTERCOSTAL FROM OSS LOT # 1528128-1 CUSTOMER RO NO 920188-SWA; AND LOCATED AND DRILLED NEW PART IAW SRM 51-40-05-0G-0 DGW 141A5100; APPLIED CHEMICAL CONVERSION COATING IAW SRM 51-20-01-0G-0 OK TO PRIMER;[02] VERIFIED CORRECTIVE ACTION ITEM 1.<BR>OKAY TO PRIME AND PART MARK NEW INTERCOSTAL.;[03] APPLIED PRIMER ON NEW INTERCOSTAL IAW AMM 51-21-72-370-804.<BR>OK TO INSTALL.;[04] REJECTION OF CORRECTIVE ACTION 3: NEW INTERCOSTAL HAS AREAS OF MISSING PRIMER. SEE STEP 1;[05] PARTIAL STEP 1;[06] VERIFIED STEP 1 AND CORRECTIVE ACTION 3. OK TO INSTALL.;[07] INSTALLED NEW INTERCOSTAL AT STA-259.5 LBL-15.332 TO LBL-3.6 WL 207.540 IAW SRM 51-40-02-0G-0 AND DWG:141A5100.<BR>REFER TO EA-23-153-01625-WIP1 STEP 4 CUSTOMER CARD: TTG8Q00L55TN.;[08] VERIFIED CORRECTIVE ACTION 7;[09] UPDATE ITEM 2: ACCOMPLISHED PART MARKING ON NEW STIFFENER IAW EA-23-153-01625-WIP1 STEP 3.;[10] VERIFIED STEP 2 AND CORRECTIVE ACTION 9;[11] INTERCOSTAL CRACKED AT BS 259.5; WL 207; LBL 5 WAS REPAIRED IAW EA 23-153-01625;[12] VERIFIED MEASUREMENTS.

Part: INTERCOSTAL — CRACKED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

INTERCOSTAL AT AFT INNER RADIUS IS CRACKED BS 947; RBL 23; WL 165. (MARKED)<[01] REMOVED INTERCOSTAL FROM AFT CARGO BAY BS 927 TO BS 947 RBL 23 WL 165 IAW SRM 51-40-02-0G-0;[02] VERIFY APPLICABILITY PER SRM NOT ALLOWABLE DAMAGE DO NOT HAVE ENTRIES ARE CALLED REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02 STEP 9 C;[03] RECEIVED NEW INTERCOSTAL P/N 147A7500-22 LOT#1524304-2.LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG147A7500.<BR>OK TO INSTALL;[04] CORRECTION IDENTIFICATION SRM 53-70-53-0I-2;[05] VERIFIED CORRECTIVE ACTION ITEMS 2 AND 3. <BR>OKAY TO INSTALL NEW INTERCOSTAL IS GIVEN.;[06] INSTALLED NEW INTERCOSTAL FROM BS 927 TO BS 947 RBL23 WL 165 IAW SRM 51-40-02 AND DWG 147A7500;[07] VERIFIED MEASUREMENT TABLE;[08] VERIFIED CORRECTIVE ACTION 6

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 232RF UPPER SURFACE HAS PULLED STRANDS.<[01] IDENTIFIED FLOOR PANEL 232RF MATERIAL IAW SRM 53-00-50-0I-1 FIGURE 4 TABLE 4. DAMAGE EXCEEDS ALLOWABLE DAMAGE LIMITS IAW SRM 53-00-50-1A-1 PARAGRAPH 4.F. DAMAGE TO FLOOR PANEL IS BEYOND ECONOMICAL REPAIR AND MAY BE REPLACED BY FABRICATING A NEW PANEL IAW SRM 53-00-50-2R-0 PARAGRAPH 1.A (NOTE).<BR><BR>FABRICATED NEW FLOOR PANEL AND LOCATED INSERT HOLES USING BMS4-17 TYVI LOT# 1526676 IAW SRM 53-00-50-2R-0 PARAGRAPH 5.S(1) (A-C)AND 4.A(1); AND BAC DWG 144A5810 ID:0004;[02] INSTALLED ALL INSERTS USING BMS5-107 LOT#AK2KP8383K-1 AND CURED USING HEAT LAMP AND THERMOMETER ATS2208 CAL DUE DATE 10/2023 THEN PART MARKED PANEL IAW SRM 53-00-50-2R-0 PARA 5S AND BOEING DWG 144A5810-4.;[03] VERIFIED CORRECTIVE ACTIONS 1 AND 2<BR><BR>VERIFIED MEASUREMENTS TABLE;[04] PANEL WAS REPLACED WITH NEW FABRICATED FROM RAW STOCK IAW SRM 53-00-50-2R-0 AND DRAWING 144A5810. <BR><BR>UPLOADED CURE SHEET. <BR><BR>JOB COMPLETE.;[05] VERIFIED CORRECTIVE ACTION 4

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 242DF UPPER SURFACE HAS PULLED STRANDS.<[01] PANEL DAMAGE TO MARKED AREA WITH PULLED STRANDS EXCEEDS ALLOWABLE DAMAGE LIMITS IAW SRM 53-00-50-1A-1 PAR. 4. F.<BR><BR>FABRICATING NEW FLOORBOARD IAW SRM 53-00-50-2R-0 PAR. 1. A. NOTE:<BR><BR>FABRICATED NEW FLOORBOARD USING BMS4-23 TY II LOT# 1525675-1; SANDED EDGES; LOCATED ALL INSERT HOLES AND CLEANED AND PART MARKED FOLLOWING DWG DOC:144A5810 ID: 0003 IAW SRM 53-00-50-2R-0 PAR. 4.A.(2) TABLE 204 AND PAR. 5. E. (1)<BR><BR>INSTALLED ALL INSERTS USING BMS5-107 EPIBOND 420 LOT# AK2KP8383K-1 AND CURED UNDER HEAT LAMP MONITORED BY THERMOMETER ID: ATS2209 CAL/DUE: 10/2023 AND CLEANED IAW SRM 53-00-50-2R-0 PAR. 5. S. (1) (D) - (H);[02] UPLOADED CURE SHEET. JOB COMPLETE.;[03] VERIFIED CORRECTIVE ACTION ITEMS 1-2 AND MEASUREMENTS TABLE.

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 241FF UPPER SURFACE HAS PULLED STRANDS.<[01] DUE TO EXTENT OF THE DAMAGE FABRICATED NEW FLOOR PANEL 241FF FROM BMS4-17 TYPE 6 LOT#1526676-1; LOCATED AND INSTALLED ALL INSERTS USING BMS5-107 LOT# AK2KP8383K-1; CURED INSERTS USING HEAT LAMP AND THERMOMETER ATS2208 CAL DUE DATE 10/2023 AND PART MARKED PANEL IAW SRM 53-00-50-2R-0 PARA 1A(NOTE) PARA 4 TABLE 204; PARA 5S AND BOEING DWG 144A5810-13.;[02] VERIFIED CORRECTIVE ACTION 1<BR><BR>VERIFIED MEASUREMENTS TABLE;[03] UPLOADED CURE SHEET. JOB COMPLETE;[04] VERIFIED CORRECTIVE ACTION 3

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 232SF UPPER SURFACE HAS PULLED STRANDS.<[01] IDENTIFIED FLOOR PANEL 232SF MATERIAL IAW SRM 53-00-50-0I-1 FIGURE 4 TABLE 4. DAMAGE EXCEEDS ALLOWABLE DAMAGE LIMITS IAW SRM 53-00-50-1A-1 PARAGRAPH 4.F. DAMAGE TO FLOOR PANEL IS BEYOND ECONOMICAL REPAIR AND MAY BE REPLACED BY FABRICATING A NEW PANEL IAW SRM 53-00-50-2R-0 PARAGRAPH 1.A (NOTE).<BR><BR>FABRICATED NEW FLOOR PANEL AND LOCATED INSERT HOLES USING BMS4-17 TYVI LOT# 1526676-1 IAW SRM 53-00-50-2R-0 PARAGRAPH 5.S(1) (A-C) AND 4.A(1); AND BAC DWG 144A5810 ID:0159;[02] INSTALLED ALL INSERTS USING BMS5-107 LOT#AK2KP8383K-1 AND CURED USING HEAT LAMP AND THERMOMETER ATS2208 CAL DUE DATE 10/2023 THEN APPLIED TAPE AND PART MARKED PANEL IAW SRM 53-00-50-2R-0 PARA 5S AND BOEING DWG 144A5810-159.;[03] VERIFIED CORRECTIVE ACTIONS 1 AND 2<BR><BR>VERIFIED MEASUREMENTS TABLE;[04] UPLOADED CURE SHEET. JOB COMPLETE.;[05] VERIFIED CORRECTIVE ACTION 4

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 231ZF UPPER SURFACE HAS PULLED STRANDS.<[01] IDENTIFIED FLOOR PANEL 231ZF MATERIAL IAW SRM 53-00-50-0I-1 FIGURE 4 TABLE 4 AND BAC DWG 144A5810 ID: 0160. DAMAGE TO UPPER SURFACE EXCEEDS ALLOWABLE DAMAGE LIMITS IAW SRM 53-00-50-1A-1 PARAGRAPH 4.F. FLOOR PANEL DAMAGE IS BEYOND ECONOMICAL REPAIR AND MAY BE REPLACED IAW SRM 53-00-50-2R-0 PARAGRAPH 1.A NOTE.<BR><BR>ROUGH CUT FLOOR PANEL AND LOCATED INSERT HOLES USING BMS4-17 TY6 LOT#1526676-1 IAW SRM 53-00-50-2R-0 PARAGRAPH 1.A NOTE; AND PARAGRAPH 4.A TABLE 204; AND PARAGRAPH 5.S(1)(A-D).;[02] INSTALLED INSERTS USING BMS5-107 LOT#AK2KP8383K-1 AND CURED USING THERMOMETER ID: ATS2208 CAL DUE: 10/2023. APPLIED TAPE BMS8-283 LOT# OCN056838; AND PART MARKED FLOOR PANEL AS REQUIRED IAW SRM 53-00-50-2R-0 PARAGRAPH 5.S(1)(D-H); AND BAC DWG 1144A5810 ID: 0160.;[03] VERIFIED CORRECTIVE ACTIONS 1 AND 2<BR><BR>VERIFIED MEASUREMENTS TABLE;[04] FLOOR PANEL WAS REPLACED WITH NEW FABRICATED FROM RAW STOCK IAW SRM 53-00-50-2R-0 AND DRAWING 144A5810.<BR><BR>UPLOADED CURE SHEETS.<BR><BR>JOB COMPELTE.;[05] CORRECTION FOR LINE 2; 'DWG 1144A5810 ID: 0160.' SHOULD READ 'DWG 144A5810 ID: 0160.';[06] VERIFIED CORRECTIVE ACTIONS 4 AND 5

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 242CF UPPER SURFACE HAS PULLED STRANDS.<[01] PART/MATERIAL IDENTIFIED PER SRM 53-00-50-0I-1 FIGURE 4 TABLE 4 SECTION 44. <BR>UPPER SURFACE DAMAGE EXCEEDS THE ALLOWABLE LIMITS AS GIVEN IN SRM 53-00-50-1A-1 PARA 4 SECTION. 44.<BR>DAMAGED FLOOR PANEL WILL BE REPLACED IAW SRM 53-00-50-2R-0 PARA 1. A. NOTE:;[02] USING BMS4-23 TYPE II GILFLOOR PANEL MATERIAL LOT 1525675-1 FABRICATED A NEW PANEL TRIMMED & LOCATED INSERT FASTENER HOLES BY BACK DRILLING THROUGH THE DEFECTIVE PANEL & USING THE DWG 144A5810-6 FOR FASTENER LOCATION & IDENTIFICATION. THROUGH INSERTS SL5107A3-410.<BR>INSTALLED THE INSERTS USING BMS5-107 ADHESIVE LOT AK2KP8383K-1 THEN CURED IAW SRM 53-00-50-2R-0 PER FIGURE 213 PAGE 30. REF CAL TOOL THERMOMETER ID ATS2402 CAL DUE 07/2023.<BR>APPLIED THE APPLICABLE PART MARK & INSTALLED BMS8-283 FOAM TAPE PER DWG 144A5810-6 .;[03] VERIFIED CORRECTIVE ACTIONS 1 AND 2<BR><BR>VERIFIED MEASUREMENTS TABLE;[04] UPLOADED CURE SHEET. JOB COMPLETE;[05] VERIFIED CORRECTIVE ACTION 4

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 241AF UPPER SURFACE HAS PULLED STRANDS.<[01] IDENTIFIED PANEL 241AF MATERIAL IAW SRM 53-00-50-0I-1 FIG 4 AND TABLE 4.<BR><BR>DAMAGE TO PANEL 241BF IS OUT OF ALLOWABLE LIMITS IAW SRM 53-00-50-1A-1 PARA 4. F. AND BEYOND ECONOMICAL REPAIR.<BR><BR>NEW PANEL WILL BE FABRICATED FROM NEW STOCK.<BR><BR>CUT AND DRILLED NEW FLOOR PANEL USING STOCK MATERIAL BMS 4-17 TY 6; LOT# 1526676-1 IAW SRM 53-00-50-2R-0 PARA 1. A. NOTE; TABLE 204 AND BOEING DWG 143A5810 ID: 0008.;[02] INSTALLED ALL INSERTS USING BMS 5-107 LOT#AK2KP8383K-1; CURED WITH THERMOMETER ID: ATS2209 CAL DUE 10/2023; PART MARKED; APPLIED TAPE AND PLACARDS IAW SRM 53-00-50-2R-0 PARA 5.S AND BOEING DWG 144A5810 ID: 0008.;[03] FLOOR PANEL REPLACED WITH NEW PANEL FABRICATED FROM RAW STOCK IAW SRM 53-00-50-2R-0 AND DRAWING 144A5810. JOB COMPLETE.;[04] VERIFIED CORRECTIVE ACTIONS 1-3<BR><BR>VERIFIED MEASUREMENTS TABLE;[05] JOB COMPLETE

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 242AF UPPER SURFACE HAS PULLED STRANDS.<[01] IDENTIFIED PANEL MATERIAL IAW SRM 53-00-50-0I-1 SHEET 1; FIGURE 4; TABLE 4; AND DWG DOC: 144A5810 ID: 0189<BR><BR>PANEL UPPER SURFACE DAMAGE EXCEEDS ALLOWABLE DAMAGE LIMITS IAW SRM <BR>53-00-50-1A-1 PAR. 4. C. & F. DUE TO THE SEVERITY OF DAMAGE FABRICATING NEW FLOORBOARD IAW SRM 53-00-50-2R-0 PAR. 1. A. NOTE: <BR><BR>FABRICATED NEW FLOOR BOARD USING BMS4-17 TY 6 LOT# 1526676-1; SANDED EDGES; LOCATED AND DRILLED ALL INSERT HOLES AND CLEANED FOLLOWING DWG DOC:144A5810 ID: 0189 IAW SRM 53-00-50-2R-0 PAR. 4.A.(1) TABLE 204 AND PAR. 5. E. (1) NEED TO INSTALL INSERTS.;[02] INSTALLED ALL INSERTS USING BMS5-107 EPIBOND 420 LOT# AK2KP8383K-1 AND CURED UNDER HEATLAMP MONITORED BY THERMOMETER ID: ATS2209 CAL/DUE: 10/2023; IAW SRM 53-00-50-2R-0 PAR. 5. S. (1) (D) - (H). INSTALLED PLACARDS PART MARKED AND COMPLETED IAW SRM 53-00-50-2R-0 DWG DOC: 144A5810 ID: 0189;[03] VERIFIED CORRECTIVE ACTIONS 1 AND 2<BR><BR>VERIFIED MEASUREMENTS TABLE;[04] UPLOADED CURE SHEET. JOB COMPLETE.;[05] VERIFIED CORRECTIVE ACTION 4

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 241XF UPPER SURFACE HAS PULLED STRANDS. PANEL SHOULD BE 231XF DUE TO THE FAULT DETAILS ON THIS DEFECT MENTIONING THE OPEN OF PANEL 231XF.<[01] IDENTIFIED FLOOR PANEL 231XF MATERIAL IAW SRM 53-00-50-0I-1 FIGURE 4 TABLE 4 AND BAC DWG 144A5810 ID: 0126. DAMAGE TO UPPER SURFACE EXCEEDS ALLOWABLE DAMAGE LIMITS IAW SRM 53-00-50-1A-1 PARAGRAPH 4.F. FLOOR PANEL DAMAGE IS BEYOND ECONOMICAL REPAIR AND MAY BE REPLACED IAW SRM 53-00-50-2R-0 PARAGRAPH 1.A NOTE.<BR><BR>ROUGH CUT FLOOR PANEL AND LOCATED INSERT HOLES USING BMS4-17 TY6 LOT#1526676-1 IAW SRM 53-00-50-2R-0 PARAGRAPH 1.A NOTE; AND PARAGRAPH 4.A TABLE 204; AND PARAGRAPH 5.S(1)(A-D).;[02] INSTALLED INSERTS USING BMS5-107 LOT#AK2KP8383K-1 AND CURED USING THERMOMETER ID: ATS2208 CAL DUE: 10/2023. APPLIED TAPE BMS8-283 LOT# OCN056838; AND PART MARKED FLOOR PANEL AS REQUIRED IAW SRM 53-00-50-2R-0 PARAGRAPH 5.S(1)(D-H); AND BAC DWG 1144A5810 ID: 0126.;[03] VERIFIED CORRECTIVE ACTIONS 1 AND 2<BR><BR>VERIFIED MEASUREMENTS TABLE;[04] PANEL WAS REPLACED WITH NEW PANEL FABRICATED FROM RAW STOCK IAW SRM 53-00-50-2R-0 AND DRAWING 1445810.<BR><BR>UPLOADED CURE SHEET.<BR><BR>JOB COMPLETE.;[05] VERIFIED CORRECTIVE ACTION 4;[06] CORRECTION FOR LINE 2; ' BAC DWG 1144A5810' SHOULD READ ' BAC DWG 144A5810'.;[07] VERIFIED CORRECTION TO CORRECTIVE ACTION 2

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 241DF UPPER SURFACE HAS PULLED STRANDS.<[01] DUE TO THE EXTENT OF DAMAGE; FABRICATED NEW FLOOR PANEL 241DF USING BMS 4-17TY6 LOT#1526676-2; INSTALLED INSERTS USING BMS 5-107 LOT#AK2KP8383K; CURED WITH THERMOMETER ID:ATS2208 CAL DUE 10/2023; PART MARKED AND APPLIED TAPE IAW SRM 53-00-50-2R-0 PARA 1.A(NOTE); 5.S AND BOEING DWG 144A5810 SHEET 128.;[02] VERIFIED CORRECTIVE ACTION 1<BR><BR>VERIFIED MEASUREMENTS TABLE;[03] UPLOADED CURE SHEET. JOB COMPLETE;[04] VERIFIED CORRECTIVE ACTION 3

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 241BF UPPER SURFACE HAS PULLED STRANDS.<[01] IDENTIFIED PANEL 241BF MATERIAL IAW SRM 53-00-50-0I-1 FIG 4 AND TABLE 4.<BR><BR>DAMAGE TO PANEL 241BF IS OUT OF ALLOWABLE LIMITS IAW SRM 53-00-50-1A-1 PARA 4. F. AND BEYOND ECONOMICAL REPAIR.<BR><BR>NEW PANEL WILL BE FABRICATED FROM NEW STOCK.<BR><BR>CUT AND DRILLED NEW FLOOR PANEL USING STOCK MATERIAL BMS 4-17 TY 6; LOT# 1526676-1 IAW SRM 53-00-50-2R-0 PARA 1. A. NOTE; TABLE 204 AND BOEING DWG 143A5810 ID: 0189.;[02] INSTALLED ALL INSERTS USING BMS 5-107 LOT#AK2KP8383K-1; CURED WITH THERMOMETER ID: ATS2209 CAL DUE 10/2023; PART MARKED; APPLIED TAPE AND PLACARDS IAW SRM 53-00-50-2R-0 PARA 5.S AND BOEING DWG 144A5810 ID: 0189.;[03] FLOOR PANEL REPLACED WITH NEW PANEL FABRICATED FROM RAW STOCK IAW SRM 53-00-50-2R-0 AND DRAWING 144A5810.JOB COMPLETE.;[04] VERIFIED CORRECTIVE ACTIONS 1-3<BR><BR>VERIFIED MEASUREMENTS TABLE;[05] JOB COMPLETE

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 241EF UPPER SURFACE HAS PULLED STRANDS.<[01] DUE TO EXTENT OF THE DAMAGE FABRICATED NEW FLOOR PANEL 241EF FROM BMS4-17 TYPE 6 LOT#1526676-1; LOCATED AND INSTALLED ALL INSERTS USING BMS5-107 LOT# AK2KP8383K-1; CURED INSERTS USING HEAT LAMP AND THERMOMETER ATS2208 CAL DUE DATE 10/2023; APPLIED TAPE AND PART MARKED PANEL IAW SRM 53-00-50-2R-0 PARA 1A(NOTE) PARA 4 TABLE 204; PARA 5S AND BOEING DWG 144A5810-129.;[02] VERIFIED CORRECTIVE ACTION 1<BR><BR>VERIFIED MEASUREMENTS TABLE;[03] UPLOADED CURE SHEET. JOB COMPLETE;[04] VERIFIED CORRECTIVE ACTION 3

Part: FLOOR PANEL — PULLED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

FLOOR PANEL 241CF UPPER SURFACE HAS PULLED STRANDS.<[01] DUE TO THE EXTENT OF DAMAGE; FABRICATED NEW FLOOR PANEL 241CF USING BMS 4-17TY6 LOT#1526676-2; INSTALLED INSERTS USING BMS 5-107 LOT#AK2KP8383K; CURED WITH THERMOMETER ID:ATS2208 CAL DUE 10/2023 AND PART MARKED IAW SRM 53-00-50-2R-0 PARA 1.A(NOTE); 5.S AND BOEING DWG 144A5810 SHEET 12.;[02] VERIFIED CORRECTIVE ACTION 1;[03] UPLOADED CURE SHEET. JOB COMPLETE;[04] VERIFIED CORRECTIVE ACTION 3<BR><BR>VERIFIED MEASUREMENTS TABLE

Part: SIDEWALL SUPPORT — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

FORWARD CARGO COMPARTMENT - MULTIPLE AREA OF CORROSION ON AFT BULKHEAD SIDE WALL SUPPORT BS500C+18.25 STRG 19L TO STR 25L. (MARKED)<[01] REMOVED CORROSION ON AFT BULKHEAD SIDE WALL SUPPORT BS500C+18.25 STRG 19L TO STR 25L. PER REF SRM 53-30-08-1A-1 L=1;W=1<BR><BR>BLEND OUT EVALUATION ORIGINAL MATERIAL IS .071'' REMAINING THICKNESS IS .040'' .THEREFORE FOUND TO BE OUT OF LIMITS PER REF SRM 53-30-08-1A-1;[02] SRM 53-30-08-0I-1 IDENTIFICATION AND SRM 53-30-08-1A-1 ALLOWABLE DAMAGE ARE APPLICABLE;[03] RECEIVED NEW ON FORWARD CARGO COMPARTMENT AFT BULKHEAD SIDEWALL SUPPORT BS500C+18.25 STR19L TO STR 25L P/N 143A9485-30 PO#921400;[04] VERIFIED CORRECTIVE ACTION 3;[05] PART WILL BE INSTALLED IN COSTUMNER CARD #5330-E-16461-NG;[06] VERIFIED CORRECTIVE ACTION 5

Part: SHIELD — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON FWD SHIELD AT ACB BS767 - BS787 RBL21 WL158.<[01] CORROSION ON FWD SHIELD AT AFT CARGO BAY; LOCATED BETWEEN BS767 - BS 787; FOUND TO BE OUT OF LIMIT DUE TO NO ALLOWABLE DAMAGE ON SRM; PART WILL BE REPAIRED BY REPLACEMENT IAW SRM 51-10-02-0G-0 PAR-9.C.;[02] VERIFIED CORRECTIVE ACTION 1;[03] LOCATED AND DRILLED NEW SHIELD P/N 146A8127-12 LOT: 1521252-1; AT ACB LOCATED BETWEEN BS767 - BS787 RBL 21 WL 158 IAW SRM 51-40-05-0G-0 AND DWG 146A0081.;[04] VERIFIED CORRECTIVE ACTION 3;[05] VERIFIED MEASUREMENT TABLE EXCEPT ITEMS 2; 3; 17; AND 18;[06] VERIFIED RII INSPECTION REQUIREMENTS ARE MET.;[07] VERIFIED THE MEASUREMENT TABLE. WORKSCOPE IS COMPLETE.

Part: SIDEWALL SUPPORT — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

MULTIPLE AREA OF CORROSION ON FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT AT RBL 21 BS 500A-500D<[01] REMOVED CORROSION ON FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT AT RBL 21 BS 500A-500D PER REF SRM 53-00-53-1A-2;[02] BLEND OUT EVALUATION ORIGINAL MATERIAL THICKNESS IS .040'' AND THE REMAINING THICKNESS IS .033'' THEREFORE FOUND TO BE OUT OF LIMITS PER REF SRM 53-00-53-1A-2;[03] TOOLING USED <BR><BR>ID: ATS401<BR>DUE DATE:10/2023;[04] CORRECTION ON ENTRY 1 : L=1 W=1;[05] COMPLETED STEPS 1-4. CORROSION OUT OF LIMITS;[06] FABRICATED NEW FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT FROM MATERIAL BAC1496-444 7075-T6 CLAD SHEET LOT NBR 1506362-1 PER REF SRM 53-30-53-0I-2<BR><BR>OK TO APPLY CHEMICAL CONVERSION COATING AND PRIME ON NEW SECTION;[07] VERIFIED CORRECTIVE ACTION 6. OK TO TREAT AND PRIME GIVEN;[08] APPLIED CHEMICAL CONVERSION COATING AND PRIMER AT NEW PART PER REF SRM 51-20-01 AND SOPM 20-41-02 <BR><BR>INSTALLED NUT PLATES ON FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT PER REF SRM 51-40-02 AND DWG NBR 143A7501;[09] VERIFIED CORRECTIVE ACTION STEP 8. VERIFIED MEASUREMENT TABLE AND TASK CARD COMPLETE.

Part: SIDEWALL SUPPORT — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

MULTIPLE AREA OF CORROSION ON FWD CARGO BAY FLOOR TO SIDEWALL SUPPORT AT LBL 21 BS 500-500D<[01] VERIFIED APPLICABILITY SRM 53-30-53-0I-2 FOR IDENTIFICATION <BR>AND SRM 53-00-53-1A-2 FOR ALLOWABLE DAMAGE.;[02] REMOVED CORROSION IAW SRM 51-10-02.<BR>ON FWD CARGO BAY TO SIDEWALL SUPPORT LBL 21 BS 500+14<BR>EVALUATED BLENDED AREA L=1.00' W=0.800' <BR>ORIGINAL THICKNESS 0.040' PER BAC 1496-444<BR>REMAINING 0.030' LOSS 0.010'; MAX MAT REMOVED 0.004'<BR>FOUND TO BE OUT OF LIMITS<BR>IAW SRM 53-00-53-1A-2 PARA 4A (2) FIG 103 DETAIL D.<BR>TOOL ID: ATS 1738 S/N: UNKNOWN DUE: 10/2023;[03] VERIFIED CORRECTIVE ACTION 1 AND 2.;[04] FABRICATED LOCATED AND DRILLED<BR>NEW FLOOR TO SIDEWALL SUPPORT AND NEW SPLICE<BR>FROM BS427 TO BS500D LBL 21 WL 156<BR>IAW SRM 51-40-05-0G-0; SRM 53-00-53-2R-6 AND DWG 143A7500 MATERIAL USED BAC1496-444#7075T62 LOT: 1524635-1<BR>OK TO TREAT AND PRIME ON<BR>NEW FLOOR TO SIDEWALL SUPPORT AND NEW SPLICE;[05] VERIFIED CORRECTIVE ACTION 4; OK TO TREAT AND PRIME.;[06] TREATED AND PRIMED REPAIR SPLICE AND SIDEWALL SUPPORT ANGLE PER SRM 51-20-01 AND PRIMER SOPM 20-41-02<BR>OK TO INSTALL REPAIR SPLICE;[07] VERIFIED CORRECTIVE ACTION 6<BR>OK TO INSTALL REPAIR SPLICE GIVEN;[08] INSTALLED REPAIR SPLICE BETWEEN BS 480 TO BS 500 LBL 21 WL 156 AT L/H FLOOR TO SIDEWALL SUPPORT PER SRM 53-00-53-2R-6<BR>ALL STEPS COMPLETED;[09] VERIFIED CORRECTIVE ACTION 8.;[10] VERIFIED THE MEASUREMENT TABLE.

Part: SHIELD — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

FORWARD CARGO COMPARTMENT - MULTIPLE AREA OF CORROSION ON AFT DOOR SHIELD BS 480+12 TO BS 500D RBL 24.75<[01] THE STRUCTURAL ITEM DOES NOT HAVE ALLOWABLE DAMAGE ENTRIES. THEREFORE; MUST BE REPAIRED BY REPLACEMENT PER REF SRM 51-10-02-0G-0;[02] REPLACED ;LOCATED AND DRILLED NEW PART PER REF SRM 51-40-05 AND DWG 143A0080;[03] VERIFIED CORRECTIVE ACTION STEPS 1 AND 2. VERIFIED MEASUREMENT TABLE AND TASK CARD COMPLETE.

Part: SIDEWALL SUPPORT — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

FORWARD CARGO COMPARTMENT - MULTIPLE AREA OF CORROSION ON AFT BULKHEAD SIDE WALL SUPPORT BS500C+18.25 STRG 19R TO STR 25R. (MARKED)<[01] REMOVED CORROSION ON AFT BULKHEAD SIDE WALL SUPPORT BS500C+18.25 STRG 19R TO STR 25R. PER REF SRM 53-30-08-1A-1<BR><BR>BLEND OUT EVALUATION ORIGINAL MATERIAL IS .071'' REMAINING THICKNESS IS .045'' .THEREFORE FOUND TO BE OUT OF LIMITS PER REF SRM 53-30-08-1A-1;[02] SRM 53-30-08-0I-1 IDENTIFICATION AND SRM 53-30-08-1A-1 ALLOWABLE DAMAGE ARE APPLICABLE;[03] RECEIVED NEW ON FORWARD CARGO COMPARTMENT AFT BULKHEAD SIDE WALL SUPPORT BS500C+18.25 STR 19R TO STR 25R P/N143A9485-34 PO# 921150. LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG 143A9481;[04] VERIFIED CORRECTIVE ACTION 2 AND 3; AS WELL AS VERIFIED THE MEASUREMENT TABLE.

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON CLIP AT ACB BS727D RBL7 WL151.<[01] EVALUATED CORROSION DAMAGE ON CLIP AT ACB BS 727D; RBL7 WL 151 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] REMOVED CLIP AT ACB BS 727D RBL7 IAW SRM 51-40-02-0G-0;[03] OBTAINED NEW STRINGER CLIP AT ACB BS727D S-27R RBL7 P/N 146A1320-81 LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG # 166A1320 ; OK TO INSTALL;[04] VERIFIED CORRECTIVE ACTION ITEMS 1; 2; 3.<BR>OKAY TO INSTALL NEW CLIP GIVEN.;[05] INSTALLED NEW STRINGER CLIP AT ACB BS727D S-27R RBL7 P/N 146A1320-81 IAW SRM 51-40-05 AND DWG #146A7810;[06] INSTALLED NEW STRINGER CLIP AT ACB BS727D S-27R RBL7 P/N 146A1320-81 IAW SRM 51-40-02 AND DWG #146A7810;[07] UPDATE MEASUREMENT TABLE;[08] VERIFIED MEASUREMENT TABLE;[09] VERIFIED CORRECTIVE ACTION 5 AND 6

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON CLIP AT ACB BS727D+8 LBL5 WL152.<[01] EVALUATED CORROSION DAMAGE ON CLIP AT ACB BS 727D+8; LBL5 WL 152 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] REMOVED CLIP AT ACB BS 727D+8; LBL5 WL 152 IAW SRM 51-40-02-OG-0;[03] FABRICATED A CLIP AT ACB BS727D LBL5 WL152 FROM BAC1493-672#7075T62 LOT#1472647-1. TREATED IAW SRM 51-40-05 AND IAW DWG#146A7735. OK TO PRIME;[04] CORRECTIVE DWG# ON ITEM 3 ABOVE.....FABRICATED A CLIP AT ACB BS727D LBL5 WL152 FROM BAC1493-672#7075T62 LOT#1472647-1. TREATED IAW SRM 51-40-05 AND IAW DWG#146A7734. OK TO PRIME;[05] VERIFIED CORRECTIVE ACTION ITEMS 1; 2; 4.<BR>OKAY TO PRIME NEW CLIP GIVEN.;[06] APPLIED TWO LAYERS OF BMS 10-11; TYPE I PRIMER TO THE SURFACE OF NEW CLIP AT ACB BS727D LBL5 WL152 REFER TO SOPM 20-41-02.;[07] OK TO INSTALL;[08] VERIFIED CORRECTIVE ACTION 6 AND 7 OK TO INSTALL;[09] INSTALLED CLIP AT ACB BS727D+8 LBL5 IAW SRM 51-40-02 AND IAW DWG#146A7730;[10] VERIFIED MEASUREMENT TABLE;[11] VERIFIED CORRECTIVE ACTION 9

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON CLIP AT ACB BS727D+10 LBL7 WL152.<[01] EVALUATED CORROSION DAMAGE ON CLIP AT ACB BS 727D+10; LBL7 WL 152 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] REMOVED CLIP AT ACB BS 727D+10; LBL7 WL 152 IAW SRM 51-40-02-0G-0;[03] FABRICATED A CLIP AT ACB BS727D LBL7 WL152 FROM BAC1493-672#7075T62 LOT#1472647-1. TREATED IAW SRM 51-40-05 AND IAW DWG#146A7734. OK TO PRIME;[04] VERIFIED CORRECTIVE ACTION ITEMS 1; 2; 3.<BR>OKAY TO PRIME NEW CLIP GIVEN.;[05] APPLIED TWO LAYERS OF BMS 10-11; TYPE I PRIMER TO THE SURFACE OF NEW CLIP AT ACB BS727D LBL7 WL152 REFER TO SOPM 20-41-02.;[06] OK TO INSTALL;[07] VERIFIED CORRECTIVE ACTION 5 AND 6 OK TO INSTALL;[08] INSTALLED CLIP AT ACB BS727D+10 LBL7 IAW SRM 51-40-02 AND IAW DWG#146A7730;[09] VERIFIED MEASUREMENT TABLE;[10] VERIFIED CORRECTIVE ACTION 8

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON CLIP AT ACB BS727D+5 LBL5 WL152.<[01] EVALUATED CORROSION DAMAGE ON CLIP AT ACB BS 727D+5; LBL5 WL 152 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] REMOVED CLIP ACB AT BS 727D+5 LBL 5 WL 152 IAW SRM 51-40-02-0G-0;[03] FABRICATED NEW ACB CLIP BS727D+5 LBL5 WL152 FROM BAC1493-672#7075T62 LOT#1472647-1 IAW SRM 51-40-05 AND DWG#146A7735 ; OK TO TREAT AND PRIME;[04] VERIFIED CORRECTIVE ACTION 1-3;[05] APPLIED A CHEMICAL CONVERSION COATING AND PRIMER TO THE NEW ACB CLIP BS727D+5 LBL5 WL152 IAW SRM 51-20-01 AND SOPM 20-41-02 ; OK TO INSTALL;[06] VERIFIED CORRECTIVE ACTION 5 OK TO INSTALL;[07] INSTALLED NEW ACB CLIP BS727D+5 LBL5 WL152 IAW SRM 51-40-02-0G-0 AND DWG#146A7730.;[08] VERIFIED CORRECTIVE ACTION #7.<BR>VERIFIED MEASUREMENTS.

Part: SIDEWALL SUPPORT — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON FLOOR TO SIDEWALL SUPPORT AT ACB BS767 - BS727A RBL21 WL158.<[01] VERIFY APPLICABILITY PER SRM 53-60-53-0I-2 AND SRM 53-00-53-1A-2<BR>REMOVED CORROSION ON DISCREPANCY AREA L=3.5'; W=1.7'; D=0.007'. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-53-1A-2 STEPS 4A(2)(A) FIG 103 TOOL USED ID:ATS2827 ; DUE:01/2024;[02] VERIFIED CORRECTIVE ACTION STEP 1.;[03] RECIVED NEW FLOOR TO SIDEWALL ITEM 146A7502-51 LOT 1519356/1 LOCATED AND DRILLED NEW FLOOR TO SIDEWALL AT BS 727 TO BS 767 WL 158; IAW 737-700 SRM 51-40-05-0G-0 DWG 146A7500.-;[04] VERIFIED CORRECTIVE ACTION 3;[05] VERIFIED MEASUREMENT TABLE;[06] UPDATE PART REQUIREMENT;[07] CARD COMPLETE

Part: SIDEWALL SUPPORT — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON FLOOR TO SIDEWALL SUPPORT AT ACB BS796 - BS727D LBL21 WL158.<[01] VERIFIED SRM 53-60-53-0I-2 FOR IDENTIFICATION AND SRM 53-00-53-1A-2 FOR ALLOWABLE DAMAGE.<BR><BR>REMOVED CORROSION ON FLOOR TO SIDEWALL SUPPORT AT BS 727E+10 LBL 21 WL 158 IAW SRM 51-10-02<BR><BR>EVALUATED BLENDED AREA L=2.0' W=1.2' ORIGINAL THICKNESS 0.040' PER BAC1496-377 REMAINING 0.030' LOSS 0.010'; MAX MAT REMOVED ALLOWED 0.004'; FOUND TO BE OUT OF LIMITS IAW SRM 53-00-53-1A-2 PARA 4A (2) FIG 103 DETAIL D.<BR>TOOL ID: ATS 2827 S/N: UNKNOWN DUE:01/31/24;[02] VERIFIED CORRECTIVE ACTION 1 AND COMPLETED STEPS 1-3;[03] FABRICATED;LOCATED AND DRILLED NEW FLOOR TO SIDEWALL SUPPORT AT LBL22;BS727 TO BS847;AND SPLICE SIDEPLATE BETWEEN BS727E-BS747;MATERIAL USED BAC1496-377#7075T62;LOT#1521599-1;IAW SRM 53-00-53-2R-5 REPAIR 5 FIG 202;SRM 51-40-05 AND DWG#146A7500.OK TO TREAT AND PRIME.;[04] VERIFIED CORRECTIVE ACTION 3. OK TO TREAT AND PRIME.;[05] APPLIED CHEMICAL CONVERSION COATING AND PRIMER ON FLOOR TO SIDEWALL SUPPORT AT;BS727 TO BS847;AND SPLICE SIDEPLATE BETWEEN BS727E-BS747 LBL21 WL158..- IAW 737-700; AMM 51-21-72-370-804; AMM 51-21-41-370-802;INSTALLED SPLICE REPAIR LOCATED BETWEEN BS727E-BS747 TO SIDEWALL SUPPORT AT;BS727 TO BS847 I.A.W SRM 53-00-53-2R-5 REPAIR 5 FIG 202;SRM 51-40-05 AND DWG#146A7500.THE NEW FLOOR TO SIDEWALL SUPPORT AT ACB LBL21 WL158 BS 727 TO BS 847 WILL BE INSTALLED ON FAULT [TTG8Q004B4F5]

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON STRINGER CLIP AT ACB BS787 S-26R RBL15.<[01] EVALUATED CORROSION DAMAGE ON STRINGER CLIP AT ACB BS 787; S-26R RBL15 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] REMOVED STRINGER CLIP AT ACB BS787 S-26R RBL15 IAW SRM 51-40-02-0G-0;[03] OBTAINED NEW STRINGER CLIP AT ACB BS787 S-26R RBL15 P/N 146A1010-27 LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG # 166A1010 ; OK TO INSTALL;[04] VERIFIED CORRECTIVE ACTION ITEMS 1; 2; 3.<BR>OKAY TO INSTALL NEW STRINGER CLIP GIVEN.;[05] INSTALLED NEW STRINGER CLIP AT ACB BS787 S-26R RBL15 P/N 146A1010-27 IAW SRM 51-40-02 AND DWG 146A1262;[06] UPDATE MEASUREMENT TABLE;[07] VERIFIED MEASUREMENT TABLE;[08] VERIFIED CORRECTIVE ACTION 5

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON CLIP AT ACB BS807 LBL7 WL154.<[01] EVALUATED CORROSION DAMAGE ON CLIP AT ACB BS 807; LBL7 WL 154 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] REMOVED CLIP AT ACB BS 807 LBL7 WL 154 IAW SRM 51-40-02-0G-0;[03] FABRICATED A CLIP AT ACB BS807 LBL7 WL154 FROM BAC1490-2815#7075T62 CLAD LOT#1455934-1. TREATED IAW SRM 51-40-05 AND IAW DWG#146A1320. OK TO PRIME;[04] VERIFIED CORRECTIVE ACTION ITEMS 1; 2; 3.<BR>OKAY TO PRIME NEW CLIP GIVEN.;[05] APPLIED TWO LAYERS OF BMS 10-11; TYPE I PRIMER TO THE SURFACE OF NEW CLIP AT ACB BS 807 LBL7 WL 154 REFER TO SOPM 20-41-02.;[06] OK TO INSTALL;[07] VERIFIED CORRECTIVE ACTION 5 AND 6 OK TO INSTALL;[08] INSTALLED CLIP AT ACB BS807 LBL7 IAW SRM 51-40-02 AND IAW DWG#146A7810;[09] VERIFIED MEASUREMENT TABLE;[10] VERIFIED CORRECTIVE ACTION 8

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON STRINGER CLIP AT ACB BS827 S-27L LBL6.<[01] EVALUATED CORROSION DAMAGE ON STRINGER CLIP AT ACB BS 827 S-27L LBL6 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] REMOVED STRINGER CLIP AT ACB BS 827 S-27L LBL6 IAW SRM 51-40-02-0G-0;[03] OBTAINED NEW STRINGER CLIP AT ACB BS827 S-27L LBL6 P/N 146A1010-10 LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG # 166A1010 ; OK TO INSTALL;[04] VERIFIED CORRECTIVE ACTION ITEMS 1; 2; 3.<BR>OKAY TO INSTALL NEW CLIP GIVEN.;[05] INSTALLED NEW STRINGER CLIP AT ACB BS827 S-27L LBL6 P/N 146A1010-10 IAW SRM 51-40-02 AND DWG # 146A1280;[06] VERIFIED MEASUREMENT TABLE;[07] VERIFIED CORRECTIVE ACTION 5

Part: INTERCOSTAL — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON INTERCOSTAL AT ACB BS867+2 LBL10 WL162.<[01] CORROSION ON INTERCOSTAL AT AFT CARGO BAY; LOCATED BETWEEN BS.867+2' - LBL10; WL.162 FOUND TO BE OUT OF LIMIT DUE TO NOT HAS ENTRIES ALLOWABLE DAMAGE IN SRM; PART WILL BE REPAIRED BY REPLACEMENT IAW SRM 51-10-02-0G-0 PAR-9. C.;[02] REMOVED INTERCOSTAL AT AFT CARGO BAY; LOCATED BETWEEN BS 867+2 LBL 10; WL.162 IAW SRM 51-40-02-0G-0.;[03] RECIEVED NEW/SERVICABLE INTERCOSTAL FORMED OUT OF 7075 T0 .050' CLAD LOT #1526802-1 PER DRAWING #146A9403(-142) AND HEAT TREATED TO T62 CONDITION PER BAC5602 AS REQUIRED PER CUSTOMER RO #920983; JOB #560152.;[04] VERIFIED CORRECTION ACTION ITEM 3.;[05] LOCATED AND DRILLED NEW AFT CARGO BAY INTERCOSTAL BS 867 TO BS 887 LBL 10 IAW SRM 51-40-05-0G-0 AND DWG#146A7943 AND APPLIED CHEMICAL CONVERSION COATING IAW SREM 51-20-01-0G-0 OK TO PRIME;[06] VERIFIED CORRECTIVE ACTION #5. <BR>VERIFIED OK TO PRIME.;[07] PRIMED NEW INTERCOSTAL IAW SRM 51-20-01-0G-0 OK TO INSTALL;[08] VERIFIED CORRECTIVE ACTION #7.<BR>VERIFIED OK TO INSTALL NEW INTERCOSTAL.;[09] INSTALLED NEW AFT CARGO BAY INTERCOSTAL BS 867 TO BS 887 LBL 10 IAW SRM 51-40-02 AND DWG 146A7943.;[10] VERIFIED CORRECTIVE ACTION 9;[11] VERIFIED MEASUREMENT TABLE

Part: FRAME — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON FRAME AT ACB BS947 LBL9 WL180..<[01] VERIFIED APPLICABILITY OF SRM 53-70-07-01-1 FOR IDENTIFICATION AND SRM 53-00-07-1A-1 FOR ALLOWABLE LIMIT;[02] REMOVED CORROSION FROM AFT CARGO BAY FRAME INNER CHORD BS 947 LBL9 WL 180 IN AREA OF 5' X 1.25' ORIGINAL MATERIAL THICKNESS 0.063' IAW SRM 51-10-02-0G-0;FRAME IS CRACKED AT BS 947 LBL 9 ON INNER CHORD FLANGE. CRACK IS 1.1 INCHES LONG AND MARKED IN RED INK.;[06] ORIGINAL MATERIAL THICKNESS 0.063' REMAINING MATERIAL THICKNESS 0.056' UP ON FARTHER INVESTIGATION WE FOUND CRACK 1.1' LONG AT INNER CHORD OF FRAME BS 947 LBL 8 FOUND TO BE OUT OF LIMIT IAW SRM 53-00-07-0G-0 PAR 4A(1); REMOVED ACB FRAME BS 947 BETWEEN STR 23L AND STR 23R IAW SRM 51-40-02;[09] LOCATED AND DRILLED NEW AFT CARGO BAY FRAME ITEM#147A1047U48 LOT#1528039-1 AT BS 947 BETWEEN STR 23L AND STR 23R IAW SRM 51-40-05-0G-0 AND DWG#147A1047; OK TO INSTALL NEW FRAME.INSTALLED NEW AFT CARGO BAY FRAME P/N 147A1047-48; LOT#1528039-1 AT BS 947 LBL 23 TO RBL 23 WL 180 IAW SRM 51-40-2-0G-0 AND DWG#147A1047;[12] VERIFIED CORRECTIVE ACTION #11.;[13] VERIFIED MEASUREMENTS.

Part: SHIELD — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON FWD SHIELD AT ACB BS767 - BS787 RBL21 WL158.<[01] CORROSION ON FWD SHIELD AT AFT CARGO BAY; LOCATED BETWEEN BS767 - BS 787; FOUND TO BE OUT OF LIMIT DUE TO NO ALLOWABLE DAMAGE ON SRM; PART WILL BE REPAIRED BY REPLACEMENT IAW SRM 51-10-02-0G-0 PAR-9.C.;[02] VERIFIED CORRECTIVE ACTION 1;[03] LOCATED AND DRILLED NEW SHIELD P/N 146A8127-12 LOT: 1521252-1; AT ACB LOCATED BETWEEN BS767 - BS787 RBL 21 WL 158 IAW SRM 51-40-05-0G-0 AND DWG 146A0081.;[04] VERIFIED CORRECTIVE ACTION 3;[05] VERIFIED MEASUREMENT TABLE EXCEPT ITEMS 2; 3; 17; AND 18;[06] VERIFIED RII INSPECTION REQUIREMENTS ARE MET.;[07] VERIFIED THE MEASUREMENT TABLE. WORKSCOPE IS COMPLETE.

Part: FRAME — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON FRAME AT ACB BS947 LBL9 WL180..<[01] VERIFIED APPLICABILITY OF SRM 53-70-07-01-1 FOR IDENTIFICATION AND SRM 53-00-07-1A-1 FOR ALLOWABLE LIMIT;[02] REMOVED CORROSION FROM AFT CARGO BAY FRAME INNER CHORD BS 947 LBL9 WL 180 IN AREA OF 5' X 1.25' ORIGINAL MATERIAL THICKNESS 0.063' IAW SRM 51-10-02-0G-0;CRACK IS 1.1 INCHES LONG AND MARKED IN RED INK.;[06] ORIGINAL MATERIAL THICKNESS 0.063' REMAINING MATERIAL THICKNESS 0.056' UP ON FARTHER INVESTIGATION WE FOUND CRACK 1.1' LONG AT INNER CHORD OF FRAME BS 947 LBL 8 FOUND TO BE OUT OF LIMIT IAW SRM 53-00-07-0G-0 PAR 4A(1);[07] VERIFIED CORRECTIVE ACTIONS STEP 6.;[08] REMOVED ACB FRAME BS 947 BETWEEN STR 23L AND STR 23R IAW SRM 51-40-02;[09] LOCATED AND DRILLED NEW AFT CARGO BAY FRAME ITEM#147A1047U48 LOT#1528039-1 AT BS 947 BETWEEN STR 23L AND STR 23R IAW SRM 51-40-05-0G-0 AND DWG#147A1047; OK TO INSTALL NEW FRAME.;[10] VERIFIED CORRECTIVE ACTION 9. OK TO INSTALL.;[11] INSTALLED NEW AFT CARGO BAY FRAME P/N 147A1047-48; LOT#1528039-1 AT BS 947 LBL 23 TO RBL 23 WL 180 IAW SRM 51-40-2-0G-0 AND DWG#147A1047;[12] VERIFIED CORRECTIVE ACTION #11.;[13] VERIFIED MEASUREMENTS.

Part: TRACK — CRACKED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CRACKED TRACK AT ACB BS767 RBL13 WL156.<[01] CRACKED TRACK AT ACB BS767 RBL13 WL156 FOUND TO BE OUT OF LIMITS DUE TO CRACKS ARE NOT PERMITTED PER SRM 53-00-53-1A-2;[02] VERIFIED CORRECTIVE ACTION 1;[03] REMOVED TRACK AT ACB FROM BS 727 TO BS 887 RBL13 WL 156 IAW SRM 51-40-02;[04] RECEIVED NEW TRACK AT ACB BS727 - BS 887 ITEM 654A0004-1350 PO#915408. LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG 146A7500;[05] VERIFIED CORRECTIVE ACTION 4 AND THE MEASUREMENT TABLE. OK TO INSTALL NEW CARGO TIE DOWN TRACK ASSY.;[06] LOCATED AND DRILLED NEW CARGO TRACK SPLICE REPAIR IAW SRM 53-00-53-2R-3 REPAIR 3 PART 4.I TO 4.J FIG.203.<BR>OK TO INSTALL;[07] UPDATE ITEM 6: CARGO TRACK SPLICE REPAIR P/N: 146A7506-20 IAW SRM 53-00-53-2R-3 REPAIR 3 TABLE 201;[08] VERIFIED APPLICABILITY OF SRM 53-00-53-2R-3 REPAIR 3 - CARGO TRACK REPAIR BETWEEN FRAMES.;[09] VERIFIED CORRECTIVE ACTION 8;[10] VERIFIED CORRECTIVE ACTIONS 6 AND 7. OK TO INSTALL.;[11] INSTALLED NEW TRACK AT ACB FROM BS 727 TO BS 887 RBL13 WL156 IAW SRM 51-40-02 ;DWG 146A7500 AND INSTALLED CARGO TRACK SPLICE AT BS747+10 RBL13. IAW SRM 53-00-53-2R-3 REPAIR 3;[12] VERIFIED CORRECTIVE ACTION 11

Part: TRACK — CRACKED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CRACKED TRACK AT ACB BS767 RBL13 WL156.<[01] CRACKED TRACK AT ACB BS767 RBL13 WL156 FOUND TO BE OUT OF LIMITS DUE TO CRACKS ARE NOT PERMITTED PER SRM 53-00-53-1A-2;[02] VERIFIED CORRECTIVE ACTION 1;[03] REMOVED TRACK AT ACB FROM BS 727 TO BS 887 RBL13 WL 156 IAW SRM 51-40-02;[04] RECEIVED NEW TRACK AT ACB BS727 - BS 887 ITEM 654A0004-1350 PO#915408. LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG 146A7500;[05] VERIFIED CORRECTIVE ACTION 4 AND THE MEASUREMENT TABLE. OK TO INSTALL NEW CARGO TIE DOWN TRACK ASSY.;[06] LOCATED AND DRILLED NEW CARGO TRACK SPLICE REPAIR IAW SRM 53-00-53-2R-3 REPAIR 3 PART 4.I TO 4.J FIG.203.<BR>OK TO INSTALL;[07] UPDATE ITEM 6: CARGO TRACK SPLICE REPAIR P/N: 146A7506-20 IAW SRM 53-00-53-2R-3 REPAIR 3 TABLE 201;[08] VERIFIED APPLICABILITY OF SRM 53-00-53-2R-3 REPAIR 3 - CARGO TRACK REPAIR BETWEEN FRAMES.;[09] VERIFIED CORRECTIVE ACTION 8;[10] VERIFIED CORRECTIVE ACTIONS 6 AND 7. OK TO INSTALL.;[11] INSTALLED NEW TRACK AT ACB FROM BS 727 TO BS 887 RBL13 WL156 IAW SRM 51-40-02 ;DWG 146A7500 AND INSTALLED CARGO TRACK SPLICE AT BS747+10 RBL13. IAW SRM 53-00-53-2R-3 REPAIR 3;[12] VERIFIED CORRECTIVE ACTION 11

Part: SUPPORT ANGLE — CRACKED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CRACKED SUPPORT ANGLE AT ACB BEHIND WATER SERVICE PANEL BS914 RBL11 WL171.<[01] REMOVED SUPPORT ANGLE AT ACB BS 914 RBL 11 WL 171 IAW SRM 51-40-02-0G-0. NO ALLOWABLE DAMAGE ; PART WILL BE REPAIRABLE BY REPLACEMENT IAW 51-10-02-0G-0 STEP 9.;[02] LOCATED AND DRILLED NEW SUPPORT ANGLE AT ACB BS 914 RBL 11 WL 171 IAW SRM 51-40-05-0G-0 AND DWG 147A7221; OK TO INSTALL;[03] OKAY TO INSTALL NEW ANGLE GIVEN.;[04] INSTALLED NEW SUPPORT ANGLE AT ACB BS 914 RBL 11 WL 171. IAW 737-700 SRM 51-40-02-0G-0; DWG 147A7221. REV: C.;[05] VERIFIED CORRECTIVE ACTIONS 2; 4; AND MEASUREMENT TABLE

Part: CARGO TRACK — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON TRACK AROUND FASTENER HOLE AT ACB BS727A+10 RBL13 WL156.<[01] ACB TRACK RBL13WILL BE REPLACED ON FAULT [TTG8Q00L09TA];[02] VERIFIED CORRECTIVE ACTION 1 AND MEASUREMENT TABLE

Part: SUPPORT ANGLE — CRACKED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CRACKED SUPPORT ANGLE AT ACB BEHIND WATER SERVICE PANEL BS918 RBL11 WL171.<[01] REMOVED SUPPORT ANGLE AT ACB BS 918 RBL 11 WL 171 IAW SRM 51-10-02-0G-0. NO ALLOWABLE DAMAGE; PART WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0.;[02] LOCATED AND DRILLED NEW SUPPORT ANGLE AT ACB BS 918 RBL 11 WL 171 IAW SRM 51-40-05-0G-0 AND DWG 147A7221; OK TO INSTALL;[03] OKAY TO INSTALL NEW ANGLE GIVEN.;[04] INSTALLED NEW SUPPORT ANGLE AT ACB BS 918 RBL 11 WL 171. IAW 737-700 SRM 51-40-02-0G-0; DWG 147A7221. REV: C.;[05] VERIFIED CORRECTIVE ACTIONS 2; 4; AND MEASUREMENT TABLE.

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON CLIP AT ACB BS787;767; 747; 727E; 727D; 727C; 727B LBL7 WL152. MARKED<[01] EVALUATED CORROSION DAMAGE ON CLIP AT BS 787; 767; 747; 727E; 727D; 727C; 727B; LBL7 WL 152 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] PAERTIAL STEPS 1-7;[03] PARTIALLY UPDATED STEP 2;[04] VERIFIED CORRECTIVE ACTION ITEM 1.<BR>PROVIDED PARTIAL UPDATE FOR STEP 2.;[05] COMPLETED STEP 2;[06] COMPLETED STEP 2;[07] PARTIALLY UPDATED STEP 1 AND STEPS 3 THRU 7;[08] PARTIAL UPDATE STEPS 1 AND 3-7- FABRICATION AND OK OT TREAT AND PRIME.;[09] PARTIALLY UPDATED STEP 1 AND STEPS 3 THRU 7;[10] PARTIAL- STEP 1 AND STEPS 3 THRU 7- OK TO INSTALL STR CLIPS;[11] COMPLETED STEPS 1 ; 6 AND 7;[12] VERIFIED STEPS 1;6;7; COMPLETE.;[13] COMPLETED STEPS 3;4 AND 5.;[14] VERIFIED STEPS 3-5;[15] VERIFIED THE MEASUREMENT TABLE.

Part: SHIELD — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

FORWARD CARGO COMPARTMENT - MULTIPLE AREA OF CORROSION ON FWD DOOR SHIELD BS 420+12 TO BS 440 RBL 24.75<[01] THE STRUCTURAL ITEM DOES NOT HAVE ALLOWABLE DAMAGE ENTRIES. THEREFORE; MUST BE REPAIRED BY REPLACEMENT PER REF SRM 51-10-02-0G-0;[02] REPLACED;LOCATED AND DRILLED NEW PART PER REF SRM 51-40-02 AND DWG NBR 143A0080;[03] CORRECTION ENTRY 2 :ADDITIONAL SRM 51-40-05;[04] VERIFIED CORRECTIVE ACTION STEPS 1;2 AND 3. VERIFIED MEASUREMENT TABLE AND TASK CARD COMPLETE.

Part: STRAP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

FORWARD CARGO COMPARTMENT - MULTIPLE AREA OF CORROSION ON TENSION STRAP BS 420 TO BS 480+12 RBL 21.75 (MARKED)<[01] VERIFIED SRM APPLICABILITY FOR IDENTIFICATION AN ALLOWABLE DAMAGE. SRM 53-30-15-0I-1 IDENTIFICATION 1 AND ALLOWBLE DAMAGE SRM 53-30-15-1A-1;[02] REMOVED CORROSION ON TENSION STRAP BS 420 TO BS 480+12 RBL 21.75 PER REF SRM 53-30-15-1A-1 <BR><BR>BLEND OUT EVALUATION ; THE MATERIAL LOST IS MORE THAN 50% .THEREFORE;FOUND TO BE OUT OF LIMITS PER REF SRM 53-30-15-1A-1;[03] VERIFIED CORRECTIVE ACTION 1 AND 2;[04] REMOVED TENSION STRAP BS 420 TO BS 480+12 RBL 21.75 PER REF SRM 51-40-02;[05] RECEIVED NEW TENSION STRAP ON FORWARD CARGO COMPARTMENT FROM BS 420 TO BS 500A RBL 21.75 P/N143A8125-1 PO#921153. LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG 143A8120 ; DWG143A8330;[06] OK TO INSTALL;[07] VERIFIED CORRECTIVE ACTION 6<BR>OK TO INSTALL TENSION STRAP GIVEN;[08] PARTIAL INSTALLTION ON FORWARD CARGO COMPARTMENT OF TENSION STRAP FROM BS 420 TO BS 500A RBL 21.75 IAW SRM 51-40-02 AND DWG143A8120; DWG143A8330;[09] INSTALLED NEW ON FORWARD CARGO COMPARTMENT TENSION STRAP FROM BS 420 TO BS 500A RBL 21.75 IAW SRM 51-40-02 AND DWG 143A8120;DWG 143A8330;[10] VERIFIED CORRECTIVE ACTION 8 AND 9.;[11] VERIFIED MEASUREMENT TABLE

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON STRINGER CLIP AT ACB BS807 S-26L LBL14. MARKED.<[01] EVALUATED CORROSION DAMAGE ON STRINGER CLIP AT ACB BS 807 S-26L LBL14 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] REMOVED STRINGER CLIP AT ACB BS 807 S-26L LBL14 IAW SRM 51-40-02-0G-0;[03] FABRICATED A STR CLIP AT ACB BS807 STR 26L FROM BAC1493-856#7075T62 CLAD LOT#1214483-1. TREATED IAW SRM 51-40-05 AND IAW DWG#146A1010. OK TO PRIME;[04] VERIFIED CORRECTIVE ACTION ITEMS 1; 2; 3.<BR>OKAY TO PRIME NEW CLIP GIVEN.;[05] APPLIED TWO LAYERS OF BMS 10-11; TYPE I PRIMER TO THE SURFACE OF NEW STGR CLIP AT ACB BS807 STR 26L REFER TO SOPM 20-41-02;[06] OK TO INSTALL;[07] VERIFIED CORRECTIVE ACTION 5 AND 6 OK TO INSTALL;[08] INSTALLED STRINGER CLIP AT ACB BS807 STR 26L IAW SRM 51-40-02 AND IAW DWG#146A1263;[09] VERIFIED MEASUREMENT TABLE;[10] VERIFIED CORRECTIVE ACTION 8

Part: ATTACH ANGLE — CRACKED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CRACKED BULKHEAD PANEL SUPPORT ATTACH ANGLE AT ACB BS847+19 LBL10 WL167.<[01] RECIVED NEW ATTACH ANGLE ITEM P/N 149A8109-114 LOCATED AND DRILLED NEW ATTACH ANGLE AT ACB BS 847+19 LBL10 WL167; IAW B 737-700 SRM 51-40-05-0G-0 DWG 149A8102 REV:A;[02] VERIFIED CORRECTIVE ACTION 1 AND THE MEASUREMENT TABLE. OK TO INSTALL.;[03] OK TO INSTALL NEW BULKHEAD PANEL SUPPORT ATTACH ANGLE;[04] OK TO INSTALL NEW BULKHEAD PANEL SUPPORT GIVEN;[05] INSTALLED NEW BULKHEAD PANEL SUPPORT ATTACH ANGLE IAW SRM 51-40-02 AND DWG # 149A8102;[06] VERIFIED CORRECTIVE ACTION STEP 5.;[07] VERIFIED MEASUREMENT TABLE AND TASK CARD COMPLETE.

Part: FLOOR SUPPORT — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

FORWARD CARGO COMPARTMENT - MULTIPLE AREA OF CORROSION ON MIDDLE FLOOR SUPPORT BS 500C+18.25 RBL 14; RBL 20. (MARKED)<[01] REMOVED CORROSION ON MIDDLE FLOOR SUPPORT BS 500C+18.25 RBL 14; RBL 20. PER REF SRM 53-30-08-1A-1 L=1;W=1<BR><BR>BLEND OUT EVALUATION ORIGINAL MATERIAL IS .071'' REMAINING THICKNESS IS .040'' .THEREFORE FOUND TO BE OUT OF LIMITS PER REF SRM 53-30-08-1A-1;[02] RECEIVED NEW ON FORWARD CARGO COMPARTMENT MIDDLE FLOOR SUPPORT BS 500C+18.25 RBL 23 TO LBL 23 P/N 143A9485-35 PO#920984. LOCATED AND DRILLED IAW SRM51-40-05 AND DWG143A9481;[03] SRM 53-30-08-0I-1 IDENTIFICATION AND SRM 53-30-08-1A-1 ALLOWABLE DAMAGE ARE APPLICABLE;[04] VERIFIED CORRECTIVE ACTION 1; 2 AND 3 AS WELL AS VERIFIED THE MEASUREMENT TABLE.

Part: STRINGER CLIP — CORRODED (ZN 100 FUS LOWER) · airframe 66,602 hrs · 39,316 cycles

CORROSION ON STRINGER CLIP AT ACB BS847 S-27L LBL6.<[01] EVALUATED CORROSION DAMAGE ON STRINGER CLIP AT ACB BS 847 S-27L LBL6 FOUND TO BE OUT OF LIMITS DUE NOT LIMITS IN SRM PARTS WILL BE REPAIRABLE BY REPLACEMENT IAW SRM 51-10-02-0G-0;[02] REMOVED STRINGER CLIP AT ACB BS 847 S-27L LBL6 IAW SRM 51-40-02-0G-0;[03] OBTAINED NEW STRINGER CLIP AT ACB BS847 S-27L LBL6 P/N 146A1010-10 LOCATED AND DRILLED IAW SRM 51-40-05 AND DWG # 166A1010 ; OK TO INSTALL;[04] VERIFIED CORRECTIVE ACTION ITEMS 1; 2; 3.<BR>OKAY TO INSTALL NEW CLIP GIVEN.;[05] INSTALLED NEW STRINGER CLIP AT ACB BS847 S-27L LBL6 P/N 146A1010-10 IAW SRM 51-40-02 AND DWG # 146A1281;[06] VERIFIED MEASUREMENT TABLE;[07] VERIFIED CORRECTIVE ACTION 5

Part: PANEL — CRACKED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

CRACKED BREAK PANEL AT FASTENER BS 540; LBL 1; WL 207<[01] REMOVED BREAK PANEL AT BS 540 BL 0 TO LBL 24 WL 207 IAW SRM 51-40-02-0G-0;[02] LOCATED AND DRILLED NEW BREAK PANEL AT BS 540 BL 0 TO LBL 24 WL 207 IAW SRM 51-40-05-0G-0; DWG 143A0060; OK TO INSTALL;[03] VERIFIED CORRECTIVE ACTION 2. OK TO INSTALL GIVEN;[04] INSTALLED NEW BREAK PANEL AT BS 540 BL 0 TO LBL 24 WL 207 IAW SRM 51-40-02-0G-0; DWG 143A0060; CARD IS COMPLETED;[05] VERIFIED CORRECTIVE ACTION 4 INSTALLATION AND MEASUREMENT TABLE

Part: ATTACH ANGLE — CRACKED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

CABLE INTERCOSTAL ATTACH ANGLE IS CRACKED AT FASTENER BS 688+9; RBL 24; WL 203<[01] REMOVED CABLE INTERCOSTAL ATTACH ANGLE AT FASTENER BS 688+9; RBL 24; WL 203; IAW SRM 51-40-02-0G-0;[02] REQ. SEND MATERIAL BAC1490-2782#7075-0 LOT# 1482151-1; TO OSS FOR HT TR TO T73 IAW DWG 273A9112;[03] RECEIVED NEW ATTACH ANGLE FROM O.S.S HEAT TREATED TO T73 ON CUSTOMER RO# 920254-SWA ; LOCATED AND DRILLED NEW ATTACH ANGLE BS 688+9; RBL 24; WL 203 IAW SRM 51-40-05 AND DWG# 273A9112 ; OK TO TREAT AND PRIME;[04] VERIFIED CORRECTIVE ACTION 3. OK TO TREAT AND PRIME.;[05] APPLIED A CHEMICAL CONVERSION COATING AND PRIMER TO THE NEW ATTACH ANGLE IAW SRM 51-20-01 AND SOPM 20-41-02 ; OK TO INSTALL;[06] VERIFIED CORRECTIVE ACTION 5; OK TO INSTALL.;[07] INSTALLED CABLE INTERCOSTAL ATTACH ANGLE AT FASTENER BS 688+9; RBL 24; WL 203; IAW SRM 51-40-02-0G-0 AND DWG#273A9111;[08] OK TO INSTALL FLOOR PANEL# 241AF ON STEP 1;[09] VERIFIED CORRECTIVE ACTION 7 AND MEASUREMENT TABLE;[10] COMPLETED STEP 1.;[11] OK TO CLOSE PANEL 241AF;[12] CLOSED FLOOR PANEL 241AF; IAW AMM 53-21-00-400-801; USED SCREW TORQUE 25.0 IN PDS.<BR>ID:ATS674<BR>S/N:UNKNOWN<BR>DATE:10/2022<BR>DUE:10/2023.;[13] VERIFIED CORRECTIVE ACTION 12<BR><BR>VERIFIED MEASUREMENT TABLE

Part: PANEL — CRACKED (ZN 200 FUS TOP) · airframe 66,602 hrs · 39,316 cycles

CRACKED BREAK PANEL BS 540; RBL 1; WL 207<[01] REMOVED BREAK PANEL AT BS 540 BL 0 TO RBL 24 WL 207 IAW SRM 51-40-02-0G-0;[02] LOCATED AND DRILLED NEW BREAK PANEL AT BS 540 BL 0 TO RBL 24 WL 207 IAW SRM 51-40-05-0G-0; DWG 143A0060; OK TO INSTALL;[03] VERIFIED CORRECTIVE ACTION 2. OK TO INSTALL GIVEN;[04] INSTALLED NEW BREAK PANEL AT BS 540 BL 0 TO RBL 24 WL 207 IAW SRM 51-40-02-0G-0; DWG 143A0060; CARD IS COMPLETED;[05] VERIFIED CORRECTIVE ACTION 4 INSTALLATION;[06] VERIFIED MEASUREMET TABLE. TASK COMPLETE

Part: ANGLE — CORRODED (ZN 500 LEFT WING) · airframe 66,602 hrs · 39,316 cycles

L/W #1 TANK FWD BOOST PUMP UPPER BONDING JUMPER ATTACH POINT IS CORRODED ON FRONT SPAR<[01] SRM 57-20-10-1A-3 IS APPLICABLE TO THIS REPAIR.[05] REMOVED CORROSION ON LEFT WING FRONT SPAR AROUND BOOST BUMP UPPER BONDING JUMPER L= 4.6' W = 2.4' IAW SRM 57-20-10-1A-3 ALLOWABLE DAMAGE 3;[06] VERIFIED CORRECTIVE ACTION 5 DAMAGE REMOVED;[07] FLUORESCENT PENETRANT INSPECTION REQUEST AT REWORKED AREA TO ENSURE THAT THERE IS NOT OTHER DAMAGE IAW SRM 57-20-10-1A-3;[08] PT INSPECTED AREA IAW SOPM 20-20-02. <BR>CORROSION NOTED WITHIN BLENDED AREA. MARKED AREAS. <BR>EQUIP USED: <BR>-RADIOMETER ID: ATS2504-A; B; C CAL DUE: 05/23;[09] REMOVED CORROSION ON MARKED AREAS IAW SRM 57-20-10-1A-3;[10] FLUORESCENT PENETRANT INSPECTION REQUEST AT REWORKED AREA TO ENSURE THAT THERE IS NOT OTHER DAMAGE IAW SRM 57-20-10-1A-3;[12] PT INSPECTED AREA IAW SOPM 20-20-02.<BR>NO CORROSION NOTED.<BR>EQUIP USED:<BR>-RADIOMETER ID: ATS2504-A; B; C CAL DUE: 05/23;[13] UT REQUEST TO VERIFY THE REMAINING THICKNESS AT REWORKED AREA. ORIGINAL THICKNESS 0.480'; SEE GRID MAP. ATTACHED 0.250' X 0.250';[15] MEASUREMENT TABLE UPDATED.;[16] REMOVED WING LEADING EDGE DUCT; L/W INBORD LEADING EDGE SECTION PER AMM 36-13-01-000-803;

Part: ANGLE — CORRODED (ZN 500 LEFT WING) · airframe 66,602 hrs · 39,316 cycles

L/W #1 TANK FWD BOOST PUMP UPPER BONDING JUMPER ATTACH POINT IS CORRODED ON FRONT SPAR<[01] SRM 57-20-10-1A-3 IS APPLICABLE TO THIS REPAIR.[08] PT INSPECTED AREA IAW SOPM 20-20-02. <BR>CORROSION NOTED WITHIN BLENDED AREA. MARKED AREAS. <BR>EQUIP USED: <BR>-RADIOMETER ID: ATS2504-A; B; C CAL DUE: 05/23;[09] REMOVED CORROSION ON MARKED AREAS IAW SRM 57-20-10-1A-3;[10] FLUORESCENT PENETRANT INSPECTION REQUEST AT REWORKED AREA TO ENSURE THAT THERE IS NOT OTHER DAMAGE IAW SRM 57-20-10-1A-3;[11] VERIFIED CORRECTIVE ACTION 9;[12] PT INSPECTED AREA IAW SOPM 20-20-02.<BR>NO CORROSION NOTED.<BR>EQUIP USED:<BR>-RADIOMETER ID: ATS2504-A; B; C CAL DUE: 05/23;REPAIRED L/W #1 TANK FWD BOOST PUMP UPPER BONDING JUMPER ATTACH POINT ON FRONT SPAR IAW SWA EA 23-157-01624 22. 09-JUL-2023 15:40 UTC. CORRECTION: ANGLE P/N:PART 654A0004-527, BN 211565 WAS NOT INSTALLED ON THIS AIRCRAFT.

Part: DOOR — OUT OF ADJUST (ZN 800 DOOR) · airframe 66,602 hrs · 39,316 cycles

FWD ENTRY DOOR REQUIRES ADJUSTMENT.<[01] FWD ENTRY DOOR ADJUSTMENT WILL BE ACCOMPLISHED ON TASK CARD TTG8Q00KPBBY;[02] VERIFIED CORRECTIVE ACTIONS 1<BR>FWD ENTRY DOOR ADJUSTMENT WILL BE ACCOMPLISHED ON TASK CARD TTG8Q00KPBBY

Part: SLIDE — OUT OF POSITION · airframe 66,327 hrs · 39,121 cycles

ESCAPE SLIDE NEEDS ADJUSTMENT / [01] ADJUSTED L1 DOOR SLIDE IAW AMM 25-66-00.

Part: SLIDE — OUT OF POSITION · airframe 66,327 hrs · 39,121 cycles

FWD SERVICE DOOR ESCAPE SLIDE NEEDS ADJUSTMENT / [01] INSPECTED FWD SERVICE DOOR SLIDE PER MM 25-66-01; NO DEFECTS NOTED.

Part: LENS — MISSING (R/H CABIN) · airframe 66,186 hrs · 39,021 cycles

OVERHEAD BIN BULLNOSE EMERG. EXIT LIGHT LENS MISSING @ ROW 2-3 DEF / [01] TEMPORARILY SECURED AND OK TO CONTINUE PER MEL25-10-01 SP1B C/W AUTH # 86987;[02] INSTALLED LIGHT LENS PER AMM 33-51-03.

Part: SLIDE — OUT OF TOLERANCE (L1 DOOR) · airframe 65,546 hrs · 38,600 cycles

CREW REPORTS L1 DOOR SLIDE PRESSURE IN RED BAND / [01] R&R L1 DOOR SLIDE IAW MM 25-66-01 & MT 725-61-06 (FE).

Part: BATTERY PACK — INOPERATIVE (MID L/H CABIN) · airframe 65,137 hrs · 38,334 cycles

MID L/H EMERGENCY LIGHT BATTERY PACK INOP. M1668 / [01] R&R MID L/H EMERGENCY LIGHTS BATTERY PACK PER AMM 33-51-06.

Part: LIGHT — OUT OF POSITION · airframe 64,909 hrs · 38,191 cycles

CEILING MOUNTED EMERGENCY EXIT SIGN MID CABIN HANGING DOWN / [01] R&RD LIGHT ASSY PER AMM 33-51-01.

Part: BATTERY PACK — INOPERATIVE (CABIN) · airframe 64,388 hrs · 37,873 cycles

FWD EMERGENCY LIGTHS INOP ; / [01] R/R M1674 BATTERY PACK IAW AMM 33-51-06

Part: MEGAPHONE — INOPERATIVE (CABIN)

FORWARD HAND MEGAPHONE INOP ; / [01] R&R FWD MEGAPHONE PER AMM 25-64-00

Part: MEGAPHONE — INOPERATIVE (CABIN)

FWD MEGAPHONE INOP ; / [01] DUE TO MEGAPHONE BAD FROM STOCK ROBBED MEGAPHONE FROM A/C 560 R&R FWD MEGAPHONE PER AMM 25-64-00

Part: CONNECTOR — FAILED (CABIN) · airframe 63,512 hrs · 37,352 cycles

SUPPLEMENTAL INFORMATION: L2 DOORSLIDE EXTERIOR EMERGENCY LIGHT FAILS OPS CHECK / [01] REMOVED AFT ENTRY DOORWAY SIDEWALL LINING I/A/W 25-21-25-020-801. RESEATED CONNECTION TO CONNECTOR D11086 I/A/W 33-51-04-960-801.; [02] INSPECTION CW; VERIFIED OPS CHECK; OK TO CLOSE; [03] REINSTALLED AFT ENTRY DOORWAY SIDEWALL LINING I/A/W AMM 25-21-25-420-801. PERFORMED OP CHECK OF AFT ENTRY SLIDE LIGHT I/A/W AMM 33-51-04-960-801. OP CHECK GOOD; [04] INSPECTION CW STEP 3; [05] AUDIT CW

Part: LANYARD — MISSING (FWD CARGO DOOR) · airframe 63,007 hrs · 37,039 cycles

FWD CARGO DOOR CLOSING ASSIST LANYARD MISSING LOWER HALF ; / [01] REBUILT FWD CARGO DOOR ASSIST HANDLE PER AMM 52-31-00

Part: HANDLE — MISSING (AFT CARGO DOOR) · airframe 63,007 hrs · 37,039 cycles

AFT CARGO DOOR ASSIST HANDLE MISSING LOWER PORTION ; / [01] REBUILT AFT CARGO DOOR ASSIST HANDLE PER AMM 52-31-00

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 62,861 hrs · 36,950 cycles

SEAT ROW 1ABC EMERGENCY BULLNOSE LIGHT INOP ; / [01] R/R LAMP HOUSING ASSY. BATTERY AND CHARGER. OPS CHECK GOOD. PER AMM 33-51-01.

Part: SLIDE — LOOSE (L1 DOOR) · airframe 61,546 hrs · 36,184 cycles

L1 DOOR SLIDE MANUAL DEPLOY COVER LOOSE / REPACKED L1 DOOR SLIDE PER MT 725-61-06; COVER NON INSTALLED CORRECTLY

Part: CONNECTOR — DISCONNECTED (EMEGENCY LIGHTS) · airframe 61,054 hrs · 35,875 cycles

AFT GALLEY LEFT EMERGENCY EXIT LIGHT INOPERABLE. REINSTALLED ELECTRICAL CONNECTORS ON AFT GALLEY LEFT EMERGENCY EXIT LIGHT, AS PER B737 AMM 33-51-01-960-802. TEST OK, AS PER B737 AMM 33-51-00-720-801 AND 33-51-00-710-801.

Part: FUSE — INOPERATIVE (EMERGENCY LIGHTS) · airframe 61,054 hrs · 35,875 cycles

CABIN AREA OVERWING EXIT DOOR LOWER EMERGENCY SIGNS FWD AND AFT INOPERABLE. SECURED FUSE FOR OUTPUT PIN 9 AND PIN 10 OF POWER SUPPLY M1669 AND TEST OF THE ALL OVERWING DOOR EMERGENCY EXIT SIGNS FOUND NORMAL, PER B737 REF WDM 33-51-13 AND WDM 33-51-06-960-804.

Part: CONNECTOR — DAMAGED (EMERGENCY LIGHTS) · airframe 61,054 hrs · 35,875 cycles

CABIN AREA OVERWING EXIT DOOR LOWER EMERGENCY SIGNS FWD AND AFT INOPERABLE. SECURED FUSE FOR OUTPUT PIN 9 AND PIN 10 OF POWER SUPPLY M1669 AND TEST OF THE ALL OVERWING DOOR EMERGENCY EXIT SIGNS FOUND NORMAL, PER B737 REF WDM 33-51-13 AND WDM 33-51-06-960-804.

Part: WEB — CORRODED (BS 787) · airframe 61,054 hrs · 35,875 cycles

CORROSION FOUND IN AFT CARGO BILGE AREA ON INTERCOASTAL WEB AT STA 787 +8 AND RBL 8 WL 148.5. REMOVED AND REPLACED INTERCOSTAL WEB AT AFT CARGO COMP BILGE AREA FS 787 +8 RBL 8, IAW B737-700 SRM 51-40-02-0G-0.

Part: GUIDE ARM — OUT OF ADJUST (R2 DOOR) · airframe 61,054 hrs · 35,875 cycles

SERVICE DOOR R2 IS SAGGING. ACCOMPLISHED R2 DOOR GUIDE ARM ADJUSTMENT FOUND NORMAL, AS PER B737-700 AMM 52-41-00-820-801.

Part: PLATE — CRACKED (LT WING) · airframe 61,054 hrs · 35,875 cycles

LEFT WING AFT LOWER I/B FIXED TRAILING EDGE PANEL #551GB FWD WIGGLE PLATE CRACKED (102-001) / REPLACE FWD WIGGLE PLATE @ LEFT WING AFT LOWER I/B FIXED TRAILING EDGE FWD OF PANEL 551GB AS PER B737-700 SRM 51-40-02-0G-0

Part: DOOR SILL — CORRODED (BS 293-329 RBL56) · airframe 61,054 hrs · 35,875 cycles

CORROSION-STA 293 TO STA 329; RBL56 TO RBL59 AND WL208.1: R1 DOOR SILL HAS EVIDENCE OF CORROSION; DOT56-12. / REMOVED AND INSTALLED NEW R-1 DOOR LOWER SILL REF B737-7 SRM 51-40-02-0G-0 AND DWG#141A8310

Part: ANGLE — DAMAGED (R1 DOORWAY) · airframe 61,054 hrs · 35,875 cycles

R1 DOOR CUTOUT LOWER SILL ANGLE AFT SPLICE HAS HOLE DAMAGED / REMOVED AND REPLACED LOWER SILL ANGLE AFT SPLICE AT R1 DOOR CUTOUT PER B737-700 SRM 51-40-02-0G-0 AND DRAWING # 143A5900

Part: SKIN — DAMAGED (FUSELAGE) · airframe 61,054 hrs · 35,875 cycles

UPPER EXTERNAL FUSELAGE SKIN UNDER ADF NR 1 ANTENNA LOCATION SHOWS 2 EA DAMAGED NUTPLATES AT FEED THROUGH ACCESS HOLE, MARKED. REMOVED AND REPLACED NUT PLATES AT UPPER ADF NR 1 ANTENNA LOCATION AND INSTALLED REPAIR, REF B737-7 SRM 53-40-01-2R-1 REPAIR 1.

Part: LENS — BROKEN (EMERGENCY LIGHT) · airframe 61,054 hrs · 35,875 cycles

R2 HEADER PANEL EMERGENCY LIGHT LEN BROKEN. REMOVED AND REPLACED R2 HEADER PANEL EMERGENCY LIGHT LEN ASSEMBLY, AS PER REF B737-7 AMM 33-51-01-960-802. OPERATIONAL CHECK WILL BE ACCOMPLISH ON CUSTOMER ORDER/CARD NR J712-00-03 STEP 11.

Part: STIFFENER — CRACKED (HORIZONTAL STAB) · airframe 61,054 hrs · 35,875 cycles

LT HORIZONTAL STAB RIB NR 4 AT STIFFENER NR 4 CRACK. INSTALLED LT HORIZONTAL STABILIZER MACHINED RIB NR 4 LOWER CHORD AND VERTICAL STIFFENER NR 4 CRACK REPAIR, PER REF B737-700 SRM 55-10-09-2R-5 REPAIR 5.

Part: STIFFENER — CRACKED (HORIZONTAL STAB) · airframe 61,054 hrs · 35,875 cycles

LT HORIZONTAL STAB RIB NR 4 AT STIFFENER NR 2 CRACK. INSTALLED LT HORIZONTAL STABILIZER MACHINED RIB NR 4 LOWER CHORD AND VERTICAL STIFFENER NR 2 CRACK REPAIR, PER REF B737-700 SRM 55-10-09-2R-5 REPAIR 5.

Part: BEAR STRAP — CRACKED (BS 294.5) · airframe 61,054 hrs · 35,875 cycles

CABIN R1 DOOR BEAR STRAP AT STA 294.5 STR 8R-STR 9R HAS CRACK INDICATION AT FASTENER HOLE. CUTOUT DAMAGE AREA AT R1 DOOR BEAR STRAP STA 294.5 STR 8R-STR 9R & INSTALLED SKIN REPAIR, REF B737-7 SRM 53-10-01-2R-6 REPAIR 6. THIS IS A CATEGORY B REPAIR.

Part: PLATE — CORRODED (FWD CARGO) · airframe 61,054 hrs · 35,875 cycles

R/H FWD CARGO COMPARTMENT STA 492 -STA 500A RBL21; WL155 SIDE PLATE CORRODED. (18-029) / REMOVED AND REPLACED SIDE PLATE AT FWD CARGO COMP. R/H SIDE STA 492 TO 500A RBL 21 AS PER B737-7 SRM 51-40-02-0G-0; DRAWING # 143A8126.

Part: STIFFENER — CRACKED (HORIZONTAL STAB) · airframe 61,054 hrs · 35,875 cycles

RT HORIZONTAL STAB RIB NR 4 STIFFENER NR 4 HAS A CRACK. INSTALLED HORIZONTAL STABILIZER MECHANICAL INSPAR RIB STIFFNER CRACK REPAIR AT STIFFENER NR 4 RIB NR 4, PER REF B737-700 SRM 55-10-9-2R-4.

Part: STIFFENER — CRACKED (HORIZONTAL STAB) · airframe 61,054 hrs · 35,875 cycles

RT HORIZONTAL STAB RIB NR 4, STIFFENER NR 2 HAS CRACK. INSTALLED HORIZONTAL STABILIZER MECHANICAL INSPAR RIB STIFFENER CRACK REPAIR AT STIFFNER NR 2 RIB NR 4 RT HORIZONTAL STAB, PER REF B737-700 SRM 55-10-09-2R-4.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 61,054 hrs · 35,875 cycles

RT HORIZONTAL STAB RIB NR 4 INBOARD FLANGE FWD UPPER CORNER HAS CRACK. REPAIRED RT HORIZONTAL STABILIZER INSPAR RIB STA 120.30 FWD UPPER INBOARD FLANGE, PER REF B737-700 RES 2016287-4 AND EA 20-155-01965 REV IR.

Part: CHANNEL — CORRODED (AFT CARGO) · airframe 61,054 hrs · 35,875 cycles

AFT CARGO COMPARTMENT FLOOR; LH SIDE PLATE CHANNEL (Z-ANGLE) LBL 21 HAS SEVERAL CORROSION SPOTS FROM STA 727A+15 TO STA 847. / REMOVED CORROSION ON AFT CARGO COMP L/H SIDE PLATE CHANNEL ON SEVEREL SPOTS FROM STA: 727A+15' TO STA: 847'; W.L. 151.5; ORIGNAL MATERIAL .0040' MAXIMUM MAT LOST FROM STA 727A+15' TO 727C+10' AND STA: 797' TO 847:; .001' MAT REAMAINING .039' AREA WITHIN LIMITS PER REF B737 SRM 53-1A-2 FIG 103; DETAIL 'D'; FROM STA: 727C+10' TO 797'; MAT LOST .010' MAT REMAINING .030' AREA OUT OF LIMITS PER REF B737 SRM 53-1A-2 FIG DETAIL 'D'; REMOVED SECTION FROM ECITING SPLICES; STA: 727C+10' AND 797' LOCATED AND DRILLED NEW Z CHANNEL PER REF SRM 51-40-05-0G-0; TREATED AMD PRIMED RII AREAS USED NEW SECTION PER REF AMM 51-21-41-370-804; INSTALLED NEW SECTIONN BETWEEN EXISTING SLPICES PER REF B737 SRM 51-4002-0G-0.

Part: FLOOR SUPPORT — CORRODED (AFT CARGO) · airframe 61,054 hrs · 35,875 cycles

AFT CARGO COMPARTMENT FLOOR; RH SIDE FLOOR SUPPORT CHANNEL RBL 21 HAS SEVERAL CORROSION SPOTS (MARKED) FROM STA 767 TO STA 797. WL 151.5 / REMOVED AND REPLACED AFT CARGO COMPT FLOOR; RH SIDE FLOOR SUPPORT CHANNEL RBL 21 FROM STA 767 TO STA 797 WL 151.5; PER REF B737 SRM 51-40-02-0G-0

Part: CHANNEL — CORRODED (BS 727A-767) · airframe 61,054 hrs · 35,875 cycles

AFT CARGO COMPARTMENT FLOOR RT SIDE PLATE CHANNEL (Z ANGLE) RBL 21 HAS SEVERAL CORROSION SPOTS FROM STA 727A+15 TO STA 767, WL 151.5. REMOVED AND REPLACED WITH A NEW RT SIDE PLATE (Z CHANNEL) SECTION FROM STA 727 TO STA 767 RBL 21, PER REF B737-700 SRM 51-40-02-0G-0.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 61,054 hrs · 35,875 cycles

PASSENGER CABIN FLOOR PANEL 221GF DAMAGED. (227-025) / CLEANED AND REPAIRED DAMAGE AREA AT PASSENGER CABIN FLOOR PANEL 221GF PER B737-700 SRM 53-00-50-2R-2 (REPAIR 2). MATERIAL USED PO 1150387; PO# 1685357 AND PO 1614988

Part: TIE DOWN — CORRODED (AFT CARGO) · airframe 61,054 hrs · 35,875 cycles

AFT CARGO COMPARTMENT FLOOR; PANEL TIE DOWN STRAP AT STA 887 HAS SURFACE CORROSION AT LBL15. W.L 151.5 / REMOVED CORRORED 'T' STRAP AND INSTALLED NEW 'T' STRAP; AT AFT CARGO COMPARTMENT STA 887; LBL 15 TO RBL 15 PER REF SRM 51-40-02-06-0 AND DRAWING NO 146A7500

Part: STRUCTURE — CORRODED (R2 DOOR) · airframe 61,054 hrs · 35,875 cycles

CORROSION FOUND R2 DOOR INNER CORD FROM STA 947.5 TO STA 986.5 RBL 45 & WL 208.1. REMOVED CORRODED R2 DOOR INNER CORD AND INSTALLED NEW INNER CARD FROM STA 887 TO STA 1010, PER REF SRM 51-40-02 AND DRAWING NR 147A8501.

Part: DOOR SILL — CORRODED (R1) · airframe 61,054 hrs · 35,875 cycles

CORROSION-STA 293 TO STA 329; RBL56 TO RBL59 AND WL208.1: R1 DOOR SILL HAS EVIDENCE OF CORROSION; DOT56-12. / REMOVED AND INSTALLED NEW R-1 DOOR LOWER SILL REF B737-7 SRM 51-40-02-0G-0 AND DWG#141A8310

Part: PRESSURE BLKHD — CRACKED (BS 663) · airframe 61,054 hrs · 35,875 cycles

CRACK INDICATION FOUND AT EXTERIOR SIDE (WHEEL WELL INTERIOR) OF LEFT MAIN WHEEL WELL SPAR VERTICAL PRESSURE WEB AT STA 663 LBL BETWEEN LBL 24.92 AND LBL 31.83 WITH APPROXIMATE LENGTH - 0.118''. REMOVED EXISTING DOUBLER AT VERTICAL PRESSURE WEB REPAIR STA 663 BETWEEN LBL 25 TO LBL 45. CUTOUT DAMAGE AREA AND INSTALLED REPAIR FROM LBL 15 TO LBL 47, REF B737-7 SRM 57-10-10-2R-3 REPAIR 3 ALTERNATIVE 3. THIS IS A CATEGORY B REPAIR.

Part: FLOOR SUPPORT — CORRODED (BS 294-332) · airframe 61,054 hrs · 35,875 cycles

CORROSION, STA 294 TO STA 332 RBL 60 WL 208.1, FLOOR SUPPORT HAS CORROSION. DOT 56-10 ON DOT 56-10. REPLACED CORRODED FLOOR SUPPORT ANGLE AT STA 294 & STA 332 RBL 60 WL 208.1, AS PER B737-700 SRM 51-40-02-0G-0.

Part: FLOORBEAM — CORRODED (AFT CABIN) · airframe 61,054 hrs · 35,875 cycles

CORROSION FOUND AFT CABIN FLOOR FRAME AT STA 986.5 RBL 43 & WL 208.1. INSTALLED UPPER CHORD FLOOR BEAM REPAIR AT STA 986.5 FROM LBL 2' TO RBL 50', PER REF 737-700 SRM 53-70-51-2R-4 REP 4 ALTERNATIVE 1.

Part: PRESSURE DECK — DAMAGED (COCKPIT) · airframe 61,054 hrs · 35,875 cycles

FLIGHT DECK FLOOR @ BS 260 DAMAGED. / CUTOUT DAMAGED AREA AT FLIGHT DEECK FLOOR BS 260 AND INSTALLED REPAIR AS PER EA NO. 1-A53-33179 REV1.

Part: FLOOR SUPPORT — CORRODED (BS 947.5) · airframe 61,054 hrs · 35,875 cycles

CORROSION FOUND AFT CABIN FLOOR STRUCTURE AT STA 947.5 +12 RBL 46 & WL 208.1. REMOVED AND REPLACED CORRODED FLOOR STRUCTURE SUPPORT AT STA 947.5+12 RBL 46, PER REF SRM 51-40-02-0G-0 AND DRAWING NR 147A5760.

Part: CHANNEL — CORRODED (FWD CARGO) · airframe 61,054 hrs · 35,875 cycles

FWD CARGO COMPT BETWEEN STA 440 TO STA 500D LT 'Z' CHANNEL WITH SURAFACE CORROSION (MK) LBL21 ; WL 155 / REMOVED AND REINSTALLED NEW Z CHANNEL AT FWD CARGO COMP L/H SIDE STA 396 TO 500D AND REMOVED AND REINSTALLED FLOOR SUPPORT STA 396 LBL 26' TO RBL 26' FOR ACCESS AS PER B737-7 SRM 51-40-02-0G-0; DRAWING # 143A7500.

Part: CHANNEL — CORRODED (FWD CARGO) · airframe 61,054 hrs · 35,875 cycles

FWD CARGO COMPT BETWEEN STA 500A TO STA 500D RT 'Z' CHANNEL WITH SURFACE CORROSION (MK) RBL 21; WL 155 / REPLACED Z CHANNEL @ FWD CARGO COMPT. BETWEEN STA 500A TO STA 500D R/H SIDE AS PER B737-700 SRM 51-40-02-0G-0

Part: FLOOR SUPPORT — CRACKED (MAIN CABIN) · airframe 61,054 hrs · 35,875 cycles

CABIN FLOOR INTERCOSTAL HAS VISUAL CRACK INDICATION AT CLIPNUT HOLE BS 322 LBL 46' (51-001). REMOVED AND REPLACED AT CABIN FLOOR INTERCOSTAL AT BS 322 LBL 46', IN REF B737-700 SRM 51-40-02-0G-0. DOCUMENT NUMBER 141A5410.

Part: FLOOR SUPPORT — CRACKED (MAIN CABIN) · airframe 61,054 hrs · 35,875 cycles

CABIN FLOOR INTERCOSTAL HAS VISUAL CRACK INDICATION AT CLIPNUT HOLE BS 336 LBL 46' (51-002). REMOVED AND REPLACED AT CABIN FLOOR INTERCOSTAL BS 336 LBL 46', IN REF B737-700 SRM 51-40-02-0G-0 DOCUMENT NUMBER 141A5410.

Part: GUSSET — CRACKED (BS 500D S19R) · airframe 61,054 hrs · 35,875 cycles

FWD CARGO RH AT STA 500D S-19R GUSSET BRACKET CRACK. / REMOVED AND REPLACED CRACKED GUSSET AT FWD CARGO R/H; F.S. 500D; S-19R; IAW B737-700 SRM 51-40-02-0G-0

Part: RETAINER — BROKEN (LT WING) · airframe 61,054 hrs · 35,875 cycles

L/H WING T/E @ WS 228.25 - WS 253.00 FIXED STRUCTURE HAS ( 1EACH ) SEAL RETAINER BROKEN. / REMOVED AND INSTALL NEW WEB P/N 115A2982-9 AT LT WING T/E WS 228.25 REF B737-700 SRM 51-40-02-0G-0

Part: GUSSET — CRACKED (BS 500D S19L) · airframe 61,054 hrs · 35,875 cycles

FWD CARGO LH AT STA 500D S-19L GUSSET BRACKET CRACK. / REMOVED AND REPLACED CRACKED GUSSET AT FWD CARGO COMP. L/H STA 500D; S19L; IAW B737-700 SRM 51-40-02-0G-0

Part: BULKHEAD — CRACKED (AFT CARGO) · airframe 61,054 hrs · 35,875 cycles

AFT CARGO FWD BULKHEAD PANEL 141 LW CRACK; P/N 453A2510-20 / RECEIVED NEW PANEL 141LW AT AFT CARGO COMPARTMENT P/N 453A2510-20; NEW PANEL TO BE INSTALLED ON T/C JPANEL-141-CLOSE

Part: GUSSET — CRACKED (BS 500D S21R) · airframe 61,054 hrs · 35,875 cycles

FWD CARGO RH AT STA 500D S-21R GUSSET BRACKET CRACK. / REMOVED AND INSTALLED GUSSSET AT FWD CARGO RT SIDE STA 500D STR 21R REF B737-7 SRM 51-40-02-0G-0

Part: STIFFENER — CRACKED (HORIZONTAL STAB) · airframe 61,054 hrs · 35,875 cycles

LT HORIZONTAL STAB RIB NR 4 STIFFENER NR 3 CRACK. INSTALLED HORIZONTAL STABILIZER MACHINED INSPAR RIB STIFFNER CRACK REPAIR ON LT HORIZONTAL STABILIZER NR 4 AT STIFFNER NR 3, PER REF 737-700 SRM 55-10-09-2R-4 REP 4.

Part: STIFFENER — CRACKED (HORIZONTAL STAB) · airframe 61,054 hrs · 35,875 cycles

RT HORIZONTAL STAB RIB NR 4 STIFFENER NR 3 CRACK. INSTALLED RT HORIZONTAL STAB MACHINE INSPAR RIB STIFFENER CRACK REPAIR AT RIB NR 4 STIFFENER NR 3, PER REF 737-700 SRM 55-10-09-2R-4 REP 4.

Part: SUPPORT STRAP — CORRODED (FWD CARGO) · airframe 61,054 hrs · 35,875 cycles

FWD CARGO COMP FLOOR PANEL 120CF SUPPORT STRAP FWD R/H POSITION HAS EVIDENCE OF SURFACE CORROSION.MKD 126-041<RECEIVED NEW FLOOR SUPPORT PLATE TEG # A84671 P.O.# 1694134- REMOVED AND REPLACED FLOOR SUPPORT STRAP AT FWD CARGO COMP; PANEL # 120CF (R/H FWD POSITION) IAW B737-700 SRM 51-40-02-0G-0.

Part: GUSSET — CRACKED (BS 500D S21L) · airframe 61,054 hrs · 35,875 cycles

FWD CARGO LH AT STA 500D S-21L GUSSET BRACKET CRACK. / REMOVED AND REPLACED GUSSET AT FWD CARGO L/H F.S. 500D; S-21L; IAW B737-700 SRM 51-40-02-0G-0.

Part: PLATE — WORN (LT WING) · airframe 61,054 hrs · 35,875 cycles

LT WING OUTBOARD TRAILING EDGE DEFLECTION CONTROL RIB, FIXED UPPER PANEL ATTACHED FASTENERS ARE LOOSE AND SERRATED PLATE HAS SIGN OF WEAR. ACCOMPLISHED LT WING OUTBOARD TRAILING EDGE DEFLECTOR CONTROL RIB FIXED UPPER PANEL REPAIR, REF B737-700 SRM 57-51-02-2R-4 FIG 202 DETAIL 4A.

Part: SKIN — GOUGED (TAIL) · airframe 61,054 hrs · 35,875 cycles

TAIL JACK HOLE PREVIOUS REPAIR DOUBLER HAS GOUGED. REPAIRED SECTION SKIN ON TAIL JACK HOLE POINT, PER REF B737-700 EA 1-753-33580 REV 1R.

Part: PANEL — LOOSE (RT WING) · airframe 61,054 hrs · 35,875 cycles

RT WING TRAILING EDGE DEFLECTION CONTROL RIB UPPER FIXED PANEL ATTACHED FASTENERS LOOSE, SERRATE PLATE SIGN OF WEAR. ACCOMPLISHED RT WING TRAILING EDGE DEFLECTOR CONTROL RIB FIXED UPPER PANEL REPAIR, REF B737-7 SRM 57-51-02-2R-4 FIG 202 DETAIL 4-A.

Part: ANGLE — CRACKED (RT WING) · airframe 60,825 hrs · 35,738 cycles

RT. WING UPPER PANEL - INBD SUPPORT BAR - FWD ANGLE BRACKET CRACKED THROUGH. / R&R BRACKET REF. SRM 51-40-02

Part: SKIN — BENT (L1 DOOR) · airframe 59,617 hrs · 35,003 cycles

FWD ENTRY DOOR AFT UPPER CORNER SKIN BENT L= 1' W=1' B= 1/4' NO LOOSE FASTENERS MOD / COMPLIED WITH FWD ENTRY DOOR AFT UPPER CORNER SKIN PERMANENT REPAIR PER EA 1-752-2678 AND SRM 51-40-02

Part: COVER — MISSING (EMERGENCY LIGHT) · airframe 58,671 hrs · 34,391 cycles

FIRST OFFICERS OVERWING EMERGENCY EXIT COVER MISSING. / INSTALLED COVER PER MM.

Part: SKIN — CRACKED (LT MLG DOOR) · airframe 57,040 hrs · 33,299 cycles

LT MAIN LANDING GEAR CENTER GEAR DOOR SURFACE CRACKED ON THE 2ND STIFFENER. R&R CENTER DOOR PER MM.

Part: BRACKET — CRACKED (RT WING) · airframe 57,040 hrs · 33,299 cycles

RIGHT WING TRAILING EDGE FLAP WEB BRACKET ABOVE #6 PYLON IS CRACKED (MARKED). / REMOVED AND REPLACED WEB BRACKET PER SRM 51-40-02

Part: SKIN — CRACKED (LT MLG DOOR) · airframe 57,040 hrs · 33,299 cycles

LT MAIN LANDING GEAR CENTER GEAR DOOR SURFACE CRACKED ON THE 2ND STIFFENER. R&R INTER DOOR PER MM.

Part: VALVE — FAULTY (NR 2 HIGH STAGE) · airframe 56,801 hrs · 33,138 cycles

AIR TURNBACK, PILOT REPORTED DUCT PRESSURE GAUGE HAD A 20% SPLIT WITH #2 INDICATING LOWER PRESSURE. R&R #2 ENGINE HIGH STAGE VALVE PER AMM.

Part: VALVE — FAULTY (NR 2 ENGINE) · airframe 56,801 hrs · 33,138 cycles

AIR TURNBACK, PILOT REPORTED DUCT PRESSURE GAUGE HAD A 20% SPLIT WITH #2 INDICATING LOWER PRESSURE. R&R PRECODER CONTROL VALVE PER AMM.

Part: REGULATOR — FAULTY (NR 2 HIGH STAGE) · airframe 56,801 hrs · 33,138 cycles

AIR TURNBACK, PILOT REPORTED DUCT PRESSURE GAUGE HAD A 20% SPLIT WITH #2 INDICATING LOWER PRESSURE. R & R NR 2 ENGINE HIGH STAGE PRESSURE REGULATOR PER AMM.

Part: LIGHT — BUCKLED (CABIN) · airframe 56,746 hrs · 33,100 cycles

EMERGENCY LIGHT STRIP BUCKLED AT ROW 9. / SECURED STRIP PER SIP.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 56,162 hrs · 32,732 cycles

LT OVERHEAD BIN EMERGENCY EXIT LIGHT INOP BETWEEN ROW 9 TO ROW 12. R&R CHARGER ASSEMBLY PER SIP.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 56,162 hrs · 32,732 cycles

LT OVERHEAD BIN EMERGENCY EXIT LIGHT INOP BETWEEN ROW 9 TO ROW 12. R&R BATTERY PACK PER SIP.

Part: LIGHT — LOOSE (CABIN) · airframe 55,546 hrs · 32,341 cycles

RT REAR GALLEY EMERGENCY EXIT LIGHT STRIP LOOSE. SECURED STRIP PER SIP.

Part: SLIDE — OUT OF POSITION (L2 DOOR) · airframe 55,385 hrs · 32,230 cycles

L2 DOOR SLIDE GAUGE OUT OF POSITION. REPOSITIONED SLIDE ASSEMBLY PER MT.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 55,385 hrs · 32,230 cycles

EMERGENCY LIGHTS BATTERY PACK INOP AT LOCATION M1674. R&R BATTERY PACK PER AMM.

Part: SCUFF PLATE — CRACKED (AFT CARGO) · airframe 55,385 hrs · 32,230 cycles

AFT CARGO BAY AFT SCUFF PLATE CRACKED / REMOVED AND REPLACED ACB AFT SCUFF PLATE PER: AMM 53-11-02-020-801; AMM 53-11-02-420-801 REF: IPC 53-13-00-05A

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 55,385 hrs · 32,230 cycles

R1 DOOR EMERGENCY EXIT LIGHT INOP. R&R BATTERY PACK PER AMM.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 55,385 hrs · 32,230 cycles

RT WING EMERGENCY EXIT LIGHT INOP. R&R BATTERY POWER SUPPLY PER AMM.

Part: BATTERY — DISCHARGED (CABIN) · airframe 55,385 hrs · 32,230 cycles

R1 DOOR EMERGENCY LIGHTS INOP. R&R BATTERY POWER SUPPLY PER AMM.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 55,385 hrs · 32,230 cycles

RT EMERGENCY LIGHT INOP BETWEEN ROW 3 TO ROW 6. R&R BATTERY PACK PER AMM.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 55,385 hrs · 32,230 cycles

RT OVERWING EXIT SLIDE LIGHT INOP. R&R BATTERY POWER SUPPLY PER AMM.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 55,385 hrs · 32,230 cycles

R1 DOOR LOWER SIDEWALL EMERGENCY EXIT LIGHT INOP. R&R BATTERY PACK PER AMM.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 55,385 hrs · 32,230 cycles

RT WING SIDEWALL SIGN LIGHT INOP. R&R BATTERY POWER SUPPLY PER AMM.

Part: SCUFF PLATE — CRACKED (AFT CARGO) · airframe 55,385 hrs · 32,230 cycles

AFT CARGO BAY AFT SCUFF PLATE IS CRACKED / SCUFF PLATE REPAIRED PER EA NO 1-A53-2076 REV 11

Part: PANEL — ELONGATED (LOWER EXT FUSELA) · airframe 55,385 hrs · 32,230 cycles

FASTENER HOLE IS ELONGATED ON WING TO BODY PANEL 194HR (MARKED). / REPAIRED ELONGATED FASTENER HOLE ON WING TO BODY PANEL 194HR IAW SRM 51-70-05-2R-9

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

FORWARD CARGO BAY FLOOR-TO-SIDEWALL SUPPORT CORRODED BETWEEN BS 500A TO BS 500D, RBL 23. R&R SUPPORT PER SRM MM & DWG.

Part: SHIELD — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

FORWARD CARGO BAY, SHIELD CORRODED BETWEEN BS 492 TO BS 500A, RBL 23. R&R SHIELD PER SRM AND DWG.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

FORWARD CARGO BAY FLOOR-TO-SIDEWALL SUPPORT CORRODED BETWEEN BS 490 TO BS 500D, LBL 23. R&R SUPPORT PER SRM AND DWG.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

FORWARD CARGO BAY, AFT BULKHEAD SUPPORT, LOWER ANGLE CORRODED AT BS 500D, BETWEEN LBL 24 TO RBL 24. R&R ANGLE PER SRM AND DWG.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

FORWARD CARGO BAY FLOOR TO SIDEWALL SUPPORT CORRODED BETWEEN BS 400 TO BS 490, LBL 21. R&R SUPPORT PER SRM & DWG.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

AFT CARGO FLOOR TO SIDEWALL SUPPORT CORRODED BETWEEN BS 727A TO BS 797, LBL 21. R&R SUPPORT PER SRM & DWG.

Part: SHIELD — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

AFT CARGO RT FLOOR TO SIDEWALL SUPPORT SHIELD CORRODED BETWEEN BS 787 TO BS 795, RBL 21. R&R SHIELD PER SRM & DWG.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

AFT CARGO RT FLOOR TO SIDEWALL SUPPORT CORRODED BETWEEN BS 727A TO BS 767, RBL 21. R&R SUPPORT PER SRM & DWG.

Part: SHIELD — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

FORWARD CARGO BAY FLOOR TO SIDEWALL SUPPORT SHIELD CORRODED BETWEEN BS 420 TO BS 440, RBL 21. R&R SHIELD PER SRM AND DWG.

Part: STRAP — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

AFT DOORWAY LOWER SUB THRESHOLD INBOARD CHORD LOWER SURFACE STRAP CORRODED BETWEEN BS 840 TO BS 847, RBL 17. R&R STRAP PER SRM AND DWG.

Part: WEB — CORRODED (FUSELAGE) · airframe 55,385 hrs · 32,230 cycles

AFT DOORWAY LOWER SUB THRESHOLD WEB CORRODED BETWEEN BS 795 TO BS 847, RBL 21. R&R WEB PER SRM AND DWG.

Part: PRESSURE PANEL — CRACKED (RT MLG WW) · airframe 55,385 hrs · 32,230 cycles

MAIN WHEEL WELL VERTICAL PRESSURE WEB CRACKED AT BS 663, RBL 27. REPAIRED WEB PER EA.

Part: PRESSURE WEB — CRACKED (WHEEL WELL) · airframe 55,385 hrs · 32,230 cycles

MAIN WHEEL WELL VERTICAL PRESSURE WEB CRACKED AT BS 663 RBL 40 WL 197 / THE DAMAGE IS REWORKED UNDER ATS ER 18-04700 REV IR AND EA 1-757-15660 REV IR. REFER TO NRC T847271 FOR TRACKING. 56040C 03NOV18

Part: ATTACH ANGLE — CRACKED (RT MLG WW) · airframe 55,385 hrs · 32,230 cycles

LOWER COMPOSITE BULKHEAD UPPER ATTACH ANGLE CRACKED AT BS 663M RBL 10. REPAIRED ANGLE PER EA.

Part: ATTACH ANGLE — CRACKED (LT MLG WW) · airframe 55,385 hrs · 32,230 cycles

LOWER COMPOSITE BULKHEAD UPPER ATTACH ANGLE CRACKED AT BS 663, LBL 10. REPAIRED ANGLE PER EA.

Part: SLAT — CRACKED (L/H WING) · airframe 55,385 hrs · 32,230 cycles

FOUND A CRACK ON LEFT WING #2 SLAT IB OF ACTUATOR ATTACH 524DB. / REMOVED AND REPLACED L/WING #2 524DB COVE PANEL L/B OF ACTUATOR IAW SOPM 20-50-01 84036U 27OCT18

Part: SLAT — CRACKED (L/H WING) · airframe 55,385 hrs · 32,230 cycles

LEFT WING LOWER SURFACE OF THE #2 LEADING EDGE SLAT NOSE TO SKIN AT ACTUATOR RIBS; FOUND TO HAVE A CRACK. MARKED / REPAIRED LT WING #2 SLAT LOWER BULL NOSE SKIN COMMON TO ACTUATOR RIBS PER SRM 57-42-01-2R-8

Part: FAIRING — DELAMINATED (RIGHT WING) · airframe 55,273 hrs · 32,158 cycles

#8 FLAP TRACK FIXED FAIRING HAS A DELAM DAMAGE AT I/B LOWER CORNER / REMOVED + REPLACED #8 FLAP TRACK FAIRING FWD IAW AMM 27-51-28-000-801 STEP 2D(2) + AMM 27-51-28-400-801 STEP 3F(2)-(4) (POS:#8; TAG NO:371869; P/N OFF:113A9110-2; S/N OFF:NS0035; P/N ON:113A9110-2; S/N ON:1698)

Part: SEAL — CRACKED (HORIZONTAL STAB) · airframe 55,272 hrs · 32,157 cycles

LEFT HORIZONTAL STABILIZER LOWER FORWARD SLIDING SEAL BENT AND CRACKED. / REMOVED AND REPLACED LEFT LOWER SLIDER SEAL REF AMM 53-31-31.

Part: SLIDE — OUT OF POSITION (R1 DOOR) · airframe 54,342 hrs · 31,552 cycles

R1 DOOR SLIDE OUT OF POSITION. REPOSITIONED SLIDE IAW MT.

Part: SLIDE — LOOSE (L2 DOOR) · airframe 54,150 hrs · 31,428 cycles

L2 DOOR SLIDE LOOSE. REINSTALLED SLIDE IAW MT.

Part: LIGHT — NOT SEATED (CABIN) · airframe 53,565 hrs · 31,052 cycles

RT OVERHEAD BIN EMERGENCY LIGHT INOP AT ROW 8. RESEATED LIGHT IAW AMM.

Part: VAPOR BARRIER — CRACKED (RT WHEEL WELL) · airframe 52,166 hrs · 30,155 cycles

RH WHEEL WELL FWD WALL FIBERGLASS VAPOR BARRIER CRACK IN BAY 8R MEASURING 8' LONG. TRANSFERRED FROM DIS #G470190 / APPLIED INTERIM PATCH REPAIR TO AFT SIDE OF VAPOR BARRIER PER EA 1-757-14405 AND SRM 57-10-10-2R-2 PARAGRAPH 6.

Part: FAN — FAULTY (CABIN) · airframe 20,624 hrs · 12,286 cycles

ELECTRICAL SMELL OUT OF FORWARD GALLEY GASPER AIR OUTLET. R&R RECIRCULATION FAN PER AMM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 50,141 hrs · 28,901 cycles

EMERGENCY LIGHT BATTERY PACK M1670 INOPERATIVE. R & R THE BATTERY PACK IAW MM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 50,141 hrs · 28,901 cycles

EMERGENCY LIGHT BATTERY PACK M1674 INOPERATIVE. R & R THE BATTERY PACK IAW MM.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

FUSELAGE SKIN CREASED BETWEEN BS 500+4 TO BS 500+7, STR 17L. REPAIRED SKIN PER ER & EA.

Part: STRINGER — CORRODED (BS 540) · airframe 50,141 hrs · 28,901 cycles

STRINGER 25R CORRODED AT BS 540. REPAIRED THE STRINGER IAW SRM.

Part: STRINGER CLIP — CRACKED (BS 277) · airframe 50,141 hrs · 28,901 cycles

STRINGER 24L CLIP CRACKED AT BS 277. R & R THE STRINGER CLIP IAW SRM.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

STRINGER CORRODED AT BS 540, STR 26L. REPAIRED STRINGER PER SRM.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

STRINGER CORRODED AT BS 540, STR 23L. REPAIRED STRINGER PER SRM.

Part: BAFFLE — CRACKED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

FORWARD CARGO BAY BAFFLE CRACKED BETWEEN BS 500 TO BS 500A, STR 26L. R&R BAFFLE PER SRM & DWG.

Part: WEB — CORRODED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

FORWARD CARGO BAY SUBTHRESHOLD WEB CORRODED. REPAIRED WEB IAW SRM.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

FORWARD CARGO BAY SUPPORT CLIP CRACKED AT BS 500A, STR 26L. R&R CLIP PER SRM & DWG.

Part: GUSSET — CRACKED (BS 500D) · airframe 50,141 hrs · 28,901 cycles

FORWARD CARGO BAY GUSSET CRACKED AT BS 500D, STRINGER 19L. R & R THE GUSSET IAW SRM.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

FORWARD CARGO BAY SUPPORT CLIP CRACKED AT BS 500B, STR 26L. R&R CLIP PER SRM AND DWG.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

FORWARD CARGO BAY SUPPORT CLIP CRACKED AT BS 500C, STR 26L. R&R CLIP PER SRM.

Part: SKIN — CORRODED (BS 887-927) · airframe 50,141 hrs · 28,901 cycles

FUSELAGE SKIN CORRODED BETWEEN BS 887 TO 927, STRINGER 23L. REPAIRED THE SKIN IAW ER AND EA.

Part: SKIN — CORRODED (BS 942-950) · airframe 50,141 hrs · 28,901 cycles

FUSELAGE SKIN CORRODED BETWEEN BS 942 TO 950, STRINGER 23L. REPAIRED THE SKIN IAW SRM AND EA.

Part: SKIN PANEL — CORRODED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

SKIN PANEL CORRODED BETWEEN BS 178 TO BS 259, BETWEEN STR 24L TO STR 24R. R&R SKIN PANEL PER SRM AND DWG.

Part: SKIN — CORRODED (E&E DOOR) · airframe 50,141 hrs · 28,901 cycles

MAIN E-BAY DOOR EXTERIOR SURFACE SKIN CORRODED. REPAIRED SKIN PER SRM.

Part: SKIN — CORRODED (BS 259-360) · airframe 50,141 hrs · 28,901 cycles

SKIN PANEL CORRODED BETWEEN BS 259 TO 360, BETWEEN STRINGERS 24 - 28L. R & R THE SKIN IAW SRM AND DWG.

Part: SKIN — CORRODED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

LT EXTERIOR SKIN PANEL CORRODED BETWEEN BS 178 TO BS 259, STR 24L TO THE COCKPIT WINDOW FRAME. REPAIRED SKIN PER SRM AND DWG.

Part: SKIN — CORRODED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

FUSELAGE SKIN CORRODED BETWEEN BS 360 TO BS 540, BETWEEN STR 14L TO STR 24L. REPAIRED SKIN PER SRM AND DWG.

Part: SKIN — CORRODED (BS 259-360) · airframe 50,141 hrs · 28,901 cycles

FUSELAGE SKIN PANEL CORRODED BETWEEN BS 259 TO 360, BETWEEN STRINGERS 14 TO 24L. R & R THE SKIN PANEL IAW ER AND EA.

Part: SKIN — CORRODED (BS 360-540) · airframe 50,141 hrs · 28,901 cycles

FUSELAGE SKIN PANEL CORRODED BETWEEN BS. 360 TO BS 540, STRINGERS 24L - 27R. REPAIRED THE SKIN PANEL IAW SRM & EA.

Part: SKIN PANEL — CORRODED (FUSELAGE) · airframe 50,141 hrs · 28,901 cycles

LT EXTERIOR SKIN PANEL CORRODED BETWEEN BS 178 TO BS 211, BELOW COCKPIT WINDOW FRAME. REPAIRED SKIN PER SRM AND DWG.

Part: SKIN — CORRODED (BS 280-392) · airframe 50,141 hrs · 28,901 cycles

SKIN CORRODED BETWEEN BS 280 TO 392, BETWEEN STRINGERS 25 - 26L. R & R THE SKIN IAW SRM.

Part: LIGHT — DELAMINATED (CABIN FLOOR) · airframe 49,692 hrs · 28,625 cycles

RIGHT FWD EMERGENCY LIGHT STRIP DELAMINATED. R & R THE EMERGENCY LIGHT MM.

Part: LIGHT — DELAMINATED (CABIN FLOOR) · airframe 49,692 hrs · 28,625 cycles

LEFT FWD EMERGENCY LIGHT STRIP DELAMINATED. R & R THE EMERGENCY LIGHT IAW MM.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 49,692 hrs · 28,625 cycles

AFT CARGO FLOOR SUPPORT CORRODED BETWEEN BS 767 TO BS 787+6, STR 26R, UPPER AND LOWER SURFACES. R&R SUPPORT PER SRM.

Part: STRAP — CORRODED (FUSELAGE) · airframe 49,692 hrs · 28,625 cycles

AFT CARGO FLOOR STRAP CORRODED AT BS 767+6. REPAIRED FLOOR STRAP PER SRM.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 49,692 hrs · 28,625 cycles

MAIN CABIN SEAT TRACK CORRODED BETWEEN BS 827 TO BS 867, RBL 45.5. REPAIRED SEAT TRACK PER EA.

Part: SLAT — DEFECTIVE (RT WING) · airframe 49,692 hrs · 28,625 cycles

RT WING NR 7 SLAT AT FASTENER DEFECTIVE AT STA 322.71. REPAIRED SLAT PER SRM.

Part: SLAT — DEFECTIVE (RT WING) · airframe 49,692 hrs · 28,625 cycles

RT WING NR 8 SLAT AT FASTENER DEFECTIVE AT STA 451.97. REPAIRED SLAT PER SRM.

Part: STRAP — MISSING (FLASHLIGHT) · airframe 49,131 hrs · 28,275 cycles

AFT GALLEY FLASHLIGHT SECURITY STRAP MISSING. R & R STRAP ASSEMBLY IAW AMM.

Part: LENS — UNKNOWN (CABIN) · airframe 49,043 hrs · 28,231 cycles

L1 DOOR EMERGENCY EXIT LIGHT LENS & BASE. R & R LENS ASSEMBLY IAW MM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 47,595 hrs · 27,394 cycles

AFT CABIN LT BATTERY PACK FAILED CAPACITY CHECK. R & R BATTERY PACK IAW AMM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 47,595 hrs · 27,394 cycles

FORWARD CABIN RT BATTERY PACK FAILED CAPACITY CHECK. R & R BATTERY PACK IAW AMM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 47,595 hrs · 27,394 cycles

AFT CABIN RT BATTERY PACK FAILED CAPACITY CHECK. R & R BATTERY PACK IAW AMM.

Part: SIGN — UNSECURE (EXIT SIGN) · airframe 46,091 hrs · 26,544 cycles

R2 DOOR EMER EXIT SIGN LIGHT LENS FELL OFF. R & R SIGN IAW MM.

Part: COVER — BROKEN (CABIN) · airframe 44,945 hrs · 250,904 cycles

FORWARD ENTRY EXIT LIGHT COVER BROKEN. R & R LIGHT ASSEMBLY IAW MM.

Part: INTERCOSTAL — BROKEN (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

INTERCOSTAL BROKEN AT STATION 540, BETWEEN BL 0 & LBL 24.75. R & R INTERCOSTAL IAW SRM.

Part: STRAP — CORRODED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

AFT CARGO FLOOR STRAP CORRODED AROUND NUTPLATE HOLES AT BS 772. R & R STRAP IAW SRM.

Part: STRAP — CORRODED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

AFT CARGO FLOOR STRAP CORRODED AROUND NUTPLATE HOLES AT BS 727D+5. R & R STRAP IAW SRM.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

VERTICAL ATTACH ANGLE CRACKED AT BS 692, RBL 1. R & R ANGLE IAW DWG.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FRAME CRACKED AT BS 400, BETWEEN STRINGER 8L TO 9L. REPAIRED FRAME IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FRAME CRACKED AT BS 400, BETWEEN STRINGER 8L TO 9L. REPAIRED FRAME IAW EA.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

L1 DOOR Z ANGLE CRACKED AT FWD CUT OUT ATTACH POINT. REPAIRED Z ANGLE IAW SRM.

Part: STIFFENER — CRACKED (LT HORIZ STAB) · airframe 43,158 hrs · 24,869 cycles

LEFT HORIZONTAL STABILIZER STAB STATION 92.70, NR 3 VERTICAL STIFFENER CRACKED. REPAIRED STIFFENER IAW SRM.

Part: STIFFENER — CRACKED (LT HORIZ STAB) · airframe 43,158 hrs · 24,869 cycles

LEFT HORIZONTAL STABILIZER STAB STATION 92.70, NR 1 VERTICAL STIFFENER CRACKED. REPAIRED STIFFENER IAW SRM.

Part: STIFFENER — CRACKED (LT HORIZ STAB) · airframe 43,158 hrs · 24,869 cycles

LEFT HORIZONTAL STABILIZER STAB STATION 92.70, NR 2 VERTICAL STIFFENER CRACKED. REPAIRED STIFFENER IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FRAME CRACKED AT BS 400R, BETWEEN STRINGER 8R TO 9R. REPAIRED FRAME IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FRAME CRACKED AT BS 400L, BETWEEN STRINGER 8R TO 9R. REPAIRED FRAME IAW SRM.

Part: THRESHOLD — CORRODED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

AFT CARGO COMPARTMENT DOOR THRESHOLD WEB CORRODED BETWEEN BS 797 TO 812. R & R WEB IAW SRM.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

AFT CARGO COMPARTMENT BULKHEAD LOWER PANEL SUPPORT ANGLE CRACKED AT BS 727, RBL 4. R & R ANGLE IAW SRM.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

AFT CARGO COMPARTMENT FLOOR SUPPORT CORRODED AT BS 727D+6, RBL 3. REPAIRED SUPPORT IAW EA.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FLOOR SUPPORT WEB CRACKED BETWEEN BS 312 TO 328, RBL 32. R & R WEB IAW SRM.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FORWARD OTBD SEAT TRACK FLANGE CRACKED AT BS 727B, LBL 45.5, BOTH FASTENER HOLES. REPAIRED SEAT TRACK IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FRAME CRACKED AT BS 727D, STRINGER 8L. REPAIRED FRAME IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

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

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FLOOR SUPPORT WEB CRACKED BETWEEN BS 294.5 TO 312. R & R WEB IAW SRM.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FORWARD OTBD SEAT TRACK FLANGE CRACKED AT BS 727B, RBL 24.75, BOTH FASTENER HOLES. REPAIRED SEAT TRACK IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FORWARD INBD SEAT TRACK FLANGE CRACKED AT BS 727B, RBL 45.5, BOTH FASTENER HOLES. REPAIRED SEAT TRACK IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FORWARD OTBD SEAT TRACK FLANGE CRACKED AT BS 727B, LBL 24.75, BOTH FASTENER HOLES. REPAIRED SEAT TRACK IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FORWARD INBD SEAT TRACK FLANGE CRACKED AT BS 727B, LBL 45.5, BOTH FASTENER HOLES. REPAIRED SEAT TRACK IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FORWARD OTBD SEAT TRACK FLANGE CRACKED AT BS 727B, RBL 45.5, BOTH FASTENER HOLES. REPAIRED SEAT TRACK IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

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

Part: PRESSURE DECK — CRACKED (LT MLG WW) · airframe 43,158 hrs · 24,869 cycles

LEFT WW UPPER PRESS DECK VERTICAL WEB CRACKED AT BS 663, BETWEEN LBL 31 TO 34. REPAIRED WEB IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FRAME CRACKED AT BS 907, STRINGER 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FRAME CRACKED AT BS 787, STRINGER 8L. REPAIRED FRAME IAW EA.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

LEFT NR 1 WINDOW FRAME CRACKED. REPAIRED WINDOW IAW EA.

Part: FLAP — DELAMINATED (RT WING) · airframe 43,158 hrs · 24,869 cycles

RIGHT WING OTBD AFT FLAP INBD LOWER CORNER DELAMINATED. R & R AFT FLAP IAW MM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

FORWARD GALLEY DOOR CUT OUT STUB FRAME FWD LOWER CORNER ANGLE CRACKED FWD SIDE. R & R ANGLE IAW SRM & EA.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

STRINGER CLIP CRACKED AT BS 284, STRINGER 11R. R & R CLIP IAW SRM.

Part: STRUCTURE — DELAMINATED (VERTICAL STAB) · airframe 43,158 hrs · 24,869 cycles

VERTICAL STABILIZER LE DELAMINATED APPROX 4 INCHES FROM LOWER EDGE. REPAIRED STABILIZER IAW EA.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 43,158 hrs · 24,869 cycles

OUTBOARD LOWER ANGLE CRACKED AT BS 693, INBD OF RBL 24.75. R & R ANGLE IAW SRM.

Part: SIGN — BROKEN (CABIN) · airframe 42,283 hrs · 24,393 cycles

OVERWING DOOR EMER EXIT SIGN LIGHT COVER BROKEN. R & R SIGN IAW AMM.

Part: SIGN — MISSING (CABIN) · airframe 42,059 hrs · 24,251 cycles

RIGHT LOWER OVERWING EMER EXIT SIGN MISSING. INSTALLED SIGN ASSEMBLY IAW AMM.

Part: COVER — MISSING (EMERGENCY LIGHT) · airframe 40,920 hrs · 23,605 cycles

R2 DOOR EMERGENCY EXIT LENS COVER MISSING. INSTALLED COVER IAW SIP.

Part: LIGHT — BROKEN (EXIT SIGN) · airframe 40,653 hrs · 23,447 cycles

FWD ENTRY DOOR EXIT SIGN LIGHT ASSEMBLY BROKEN. R & R LIGHT ASSEMBLY IAW AMM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 38,866 hrs · 22,368 cycles

LT EMERGENCY LIGHTING FAILED CAPACITY TEST. R&R BATTERY PACKS IAW MM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 38,866 hrs · 22,368 cycles

RT EMERGENCY LIGHTING FAILED CAPACITY TEST. R&R BATTERY PACKS IAW MM.

Part: LENS — MISSING (CABIN) · airframe 36,946 hrs · 21,251 cycles

EMERGENCY LIGHT LENS MISSING AT OVERHEAD BIN BULLNOSE ROW 9 ABC. REMOVED AND REPLACED LIGHT ASSY PER MM.

Part: PLATE — CRACKED (RT WING) · airframe 36,449 hrs · 20,929 cycles

RIGHT WING T/E FLAP WELL BEHIND NR 2 ENGINE, WIGGLE PLATE IS CRACKED. REMOVED AND REPLACED RIGHT WING T/E FLAP WELL BEHIND NR 2 ENGINE, WIGGLE PLATE PER SRM 51-40-02 AND MM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 36,449 hrs · 20,929 cycles

EMERGENCY BATTERY PACK FAILED CHECK AT M01672 AND M01669. REMOVED AND REPLACED EMERGENCY BATTERY PACK AT LOCATION M01672 AND M01669 PER SSM AND PER MM.

Part: RETAINER — CRACKED (RT WING) · airframe 36,449 hrs · 20,929 cycles

RIGHT WING, LARGE SEAL RETAINER ATTACHED TO UPPER T/E SHELF PANEL, O/B OF NR 7 GROUND SPOILER IS CRACKED. REMOVED AND REPLACED SEAL RETAINER PER M/M.

Part: RETAINER — CRACKED (RT WING) · airframe 36,449 hrs · 20,929 cycles

RIGHT WING, SMALL SEAL RETAINER IN FLAP WELL O/B OF NR 7 GROUND SPOILER IS CRACKED. REMOVED AND REPLACED SEAL RETAINER PER SRM 51-40-02.

Part: RETAINER — CRACKED (TE FLAP) · airframe 36,449 hrs · 20,929 cycles

LEFT WING AFT INBOARD FLAP OUTBOARD UPPER LEADING EDGE SEAL RETAINER IS CRACKED AT LOWER FASTENER HOLE. REMOVED AND REPLACED SEAL RETAINER PER MM.

Part: SKIN — CRACKED (LE SLAT) · airframe 36,449 hrs · 20,929 cycles

LEFT WING NR 3 LEADING EDGE SLAT SKIN IS CRACKED 0.6 INCH OUT OF OUTBOARD AFT FASTENER HOLE AT ACTUATOR ATTACH FITTING. REMOVED AND REPLACED NR 3 SLAT PER M/M. TAG NO: 536093 P/N ON: 114A5030-3 S/N ON: 000116 P/N OFF: S/N OFF: 001264

Part: SEAL — CRACKED (KRUEGER FLAP) · airframe 36,449 hrs · 20,929 cycles

NR 3 K-FLAP O/B ICE SEAL IS CRACKED. REPLACED ICE SEAL PER M/M.

Part: PANEL — CRACKED (FUSELAGE) · airframe 36,347 hrs · 20,868 cycles

PANEL BREAK STA 540 RBL 0 TO RBL 25 CRACKED. REMOVED AND REPLACED PANEL IAW SRM AND DWG.

Part: SKIN — CRACKED (RT HORIZ STAB) · airframe 36,347 hrs · 20,868 cycles

RIGHT HORIZ STAB LOWER SKIN AT STA 157 AND 8 INCHES FROM TRAILING EDGE HAS CRACK. REMOVED AND REPLACED SKIN IAW SRM.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 36,347 hrs · 20,868 cycles

LEFT HORIZONTAL STABILIZER AT STAB STA 101 AND 20 INCHES FROM LEADING EDGE HAS ONE INCH CRACK. REPAIRED IAW SRM 55-10-01-2R-11.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 36,347 hrs · 20,868 cycles

LEFT HORIZONTAL STABILIZER LOWER SKIN AT STAB STA 138 AND 16 INCHES FROM LEADING EDGE HAS ONE INCH CRACK. REPAIRED IAW SRM 55-10-01-2R-11 REPAIR 11.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 36,347 hrs · 20,868 cycles

LEFT HORIZONTAL STABILIZER LOWER SKIN AT STAB STA 147 AND 10 INCHES FROM TRAILING EDGE HAS ONE INCH CRACK. REPAIRED IAW SRM 55-10-01-2R-11.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 36,347 hrs · 20,868 cycles

LEFT HORIZONTAL STABILIZER AT STAB STA 129 AND 11 INCHES FROM TRAILING EDGE HAS ONE INCH CRACK. REPAIRED IAW SRM 55-10-01-2R-11 REPAIR 11.

Part: FLAP — DELAMINATED (LT WING) · airframe 36,347 hrs · 20,868 cycles

LEFT WING O/B AFT FLAP DELAMINATED AT LOWER I/B CORNER. REMOVED AND REPLACED AFT FLAP IAW SRM.

Part: SLIDE — OUT OF ADJUST (R1 DOOR) · airframe 34,451 hrs · 19,801 cycles

R1 DOOR EMERGENCY EVAC SLIDE OUT OF ADJUST. ADJUSTED SLIDE PER M/M.

Part: SKIN — CRACKED (HORIZ STAB) · airframe 34,214 hrs · 19,674 cycles

RT HORIZONTAL STABILIZER LOWER SKIN CRACKED AT STA 96.00. REPAIRED SKIN PER SRM AND EA.

Part: LENS — LOOSE (CABIN) · airframe 33,533 hrs · 19,294 cycles

L1 DOOR EMERGENCY EXIT LIGHT LENS LOOSE AT OVERHEAD BIN. SECURED LENS PER MM.

Part: FITTING — CORRODED (LT MLG TRUNNION) · airframe 32,870 hrs · 18,920 cycles

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

Part: FITTING — CORRODED (RT MLG TRUNNION) · airframe 32,870 hrs · 18,920 cycles

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

Part: COVER — BROKEN (CABIN) · airframe 32,295 hrs · 18,561 cycles

FWD EEPLS COVER BROKEN. REMOVED AND REPLACED COVER IAW MM.

Part: SKIN — CRACKED (LE SLAT) · airframe 31,924 hrs · 18,346 cycles

DURING SCHEDULED HC2 CHECK, FOUND RT WING NR 7 SLAT LOWER SKIN L/E CRACKED. REPAIRED SKIN PER EA.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 30,700 hrs · 17,615 cycles

DURING SCHEDULED MV2 CHECK, FOUND LT OVERWING EXIT LIGHT INOP. RELAMPED PER MM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 30,170 hrs · 17,317 cycles

DURING SCHEDULED MV3 CHECK, FOUND EGRESS LIGHTS INOP AT ROWS 18, 19 AND 20. REMOVED AND REPLACED LAMPS PER MM.

Part: CONNECTOR — BROKEN (CABIN) · airframe 29,252 hrs · 16,800 cycles

DURING SCHEDULED 8Y CHECK, FOUND RT OVERWING EMERGENCY EXIT LIGHT BALLST FWD CONNECTOR BROKEN. REMOVED AND REPLACED LIGHT BALLAST PER MM.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 29,252 hrs · 16,800 cycles

DURING SCHEDULED 8Y CHECK, FOUND FLOORBEAM UPPER CAP CORRODED AT BS 986.5, RBL 16. REPAIRED BEAM PER SRM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 27,384 hrs · 15,695 cycles

DURING SCHEDULED HC2 CHECK, AFT EMERGENCY EXIT BATTERY FAILED CAPACITY TEST. REMOVED AND REPLACED BATTERY PACK PER MM.

Part: SLIDE — OUT OF POSITION (R1 DOOR) · airframe 26,569 hrs · 15,206 cycles

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

Part: SKIN — CRACKED (HORIZ STAB) · airframe 25,343 hrs · 14,442 cycles

DURING SCHEDULED HC1 CHECK, FOUND RT HORIZONTAL STABILIZER LOWER IN SPAR SKIN CRACKED BETWEEN STA 101.90 TO STA 129.50. REPAIRED SKIN PER SRM.

Part: LENS — MISSING (EXIT SIGN) · airframe 24,922 hrs · 14,187 cycles

L1 DOOR EMERGENCY EXIT SIGN LENS MISSING. REMOVED AND REPLACED SIGN ASSY PER MM.

Part: SLIDE — LOW PRESSURE (L2 DOOR) · airframe 23,237 hrs · 13,199 cycles

DURING SCHEDULED MV1 CHECK, FOUND L2 DOOR EMERGENCY EVAC SLIDE PRESSURE GAUGE NEEDLE IN THE RED RANGE. REMOVED AND REPLACED SLIDE PER MM.

Part: LENS — LOOSE (CABIN) · airframe 20,604 hrs · 11,610 cycles

EEPLS LENS LOOSE AT ROW 3 ABC. SECURED LENS PER MM.

Part: COVER — BROKEN (CABIN) · airframe 19,348 hrs · 10,865 cycles

DURING SCHEDULED MV1 CHECK, FOUND EEPLS COVER BROKEN AT ROW 4 ABC. REMOVED AND REPLACED COVER PER MM.

Part: SLIDE — LOW PRESSURE (R1 DOOR) · airframe 15,801 hrs · 8,797 cycles

R1 DOOR EMERGENCY EVAC SLIDE PRESSURE GAUGE INDICATED OUT OF LIMITS. REMOVED AND REPLACED EVAC SLIDE PER MM.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 15,749 hrs · 8,765 cycles

DURING SCHEDULED MV1 CHECK, FOUND EEPLS INOP AT ROW 3 ABC. REMOVED AND REPLACED LIGHT BULB PER MM.

Part: COVER — BROKEN (CABIN) · airframe 14,539 hrs · 8,097 cycles

DURING SCHEDULED MV2 CHECK, FOUND EEPLS COVER BROKEN AT ROW 1 ABC. REMOVED AND REPLACED COVER PER MM.

Part: LENS — LOOSE (CABIN) · airframe 13,385 hrs · 7,436 cycles

EEPLS LIGHT LENS LOOSE AT ROW 1 ABC. SECURED LIGHT LENS PER MM.

Part: LIGHT — LOOSE (CABIN) · airframe 11,759 hrs · 6,497 cycles

EEPLS TRACK LOOSE AT FWD END. SECURED EEPLS PER MM.

Part: COVER — LOOSE (EMERGENCY LIGHT) · airframe 11,648 hrs · 6,433 cycles

EEPLS TRACK COVER LOOSE AT FWD END. SECURED COVER PER MM.

Part: COVER — CRACKED (EMERGENCY LIGHT) · airframe 10,868 hrs · 6,006 cycles

EEPLS TRACK COVER CRACKED AT FWD END. REMOVED AND REPLACED COVER PER MM.

Part: LIGHT — CRACKED (ROW 12 ABC) · airframe 10,858 hrs · 6,000 cycles

DURING SCHEDULED HC1 CHECK, FOUND EEPLS STRIP CRACKED BETWEEN ROW 12 ABC AND ROW 21 ABC. REMOVED AND REPLACED STRIP SECTION IAW MM.

Part: SLIDE — OUT OF ADJUST (L2 DOOR) · airframe 10,858 hrs · 6,000 cycles

DURING SCHEDULED HC1 CHECK, FOUND L2 DOOR EVACUATION SLIDE OUT OF ADJUST. REINSTALLED SLIDE ASSY IAW MM.

Part: ENGINE — CONTAMINATED (NR 1) · airframe 10,471 hrs · 5,791 cycles

INFLIGHT SHUTDOWN/DECLARED EMERGENCY. NR 1 ENGINE OIL FILTER BYPASS LIGHT ILLUMINATED. SHUT DOWN NR 1 ENGINE BYPASS LIGHT EXTINGUISHED. FOUND METAL PARTICLES IN OIL FILTER. REMOVED AND REPLACED NR 1 ENGINE PER MM.

Part: LIGHT — LOOSE (ROW 1 ABC) · airframe 10,405 hrs · 5,751 cycles

EEPLS TRACK AT ROW 1 ABC LOOSE. SECURED TRACK PER MM.

Part: LENS — MISSING (EMERGENCY LIGHT) · airframe 10,340 hrs · 5,711 cycles

EEPLS TRACK LENS MISSING. INSTALLED LENS PER MM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 9,648 hrs · 5,336 cycles

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

Part: COVER — CRACKED (CABIN) · airframe 8,419 hrs · 4,648 cycles

EEPLS LIGHT COVER CRACKED AT EMERGENCY OVERWING EXIT. REMOVED AND REPLACED EEPLS LIGHT COVER PER MM.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 7,352 hrs · 3,993 cycles

EEPLS INOP AT FWD END. RELAMPED EEPLS PER MM.

Part: COVER — BROKEN (EMERGENCY LIGHT) · airframe 7,080 hrs · 3,844 cycles

DURING SCHEDULED MV2 CHECK, FOUND EEPLS COVER STRIPS BROKEN AT ROWS 22, 13, 11, 3 AND 1. REMOVED AND REPLACED COVER STRIPS PER MM.

Part: COVER — BROKEN (EMERGENCY LIGHT) · airframe 4,819 hrs · 2,640 cycles

EEPLS COVERS AT ROW 1 RT AND ROW 10 LT, BROKEN. REMOVED AND REPLACED EEPLS COVERS PER MM.

Part: COVER — CRACKED (CABIN) · airframe 3,516 hrs · 1,947 cycles

DURING SCHEDULED C3 CHECK, FOUND EEPLS COVERS CRACKED AT ROWS 17, 23, 16, 14, 2, AND 1. REMOVED AND REPLACED TRACK COVERS PER MM.

Part: COVER — LOOSE (CABIN FLOOR) · airframe 347 hrs · 194 cycles

EEPLS COVER LOOSE AT FWD END. SECURED COVER PER MM.