N770SA

Part: MEGAPHONE — INOPERATIVE (FWD CABIN) · airframe 72,011 hrs · 42,805 cycles

FORWARD CABIN FLIGHT ATTENDANT MEGAPHONE INOP. R & R FWD GALLEY MEGAPHONE PER AMM 25-64-00.

Part: LENS — UNSECURE (EXIT SIGN) · airframe 71,894 hrs · 42,731 cycles

THE LOWER EXIT SIGN COVER AT THE LEFT OVER WING EXIT IS NOT SECURE. RE-INSTALLED COVER PER SIP

Part: SENSOR — POPPED (L/H FLAP SKEW) · airframe 70,184 hrs · 41,576 cycles

FLAPS DID NOT EXTEND WHEN FLAPS 5 SELECTED. ALTERNATED ALTERNATE FLAP EXTENSION. ONLY RH SIDE FLAPS MOVED. LEFT STAYED UP. PERFORMED A NO FLAP LAND. UNEVENTFUL LANDING PSEU ILLUMINATED AFTER LANDING. / [01] BITE CHECKED FSEU FOUND FAULT MSG #27-53279 & LEFT T/E FLAP POS/SKEW SENSOR CIRCUIT BREAKER POPPED; WOULD NOT RESET; FLAPS WOULD NOT EXTEND WITH HYDRAULICS OR ELECTRIC. MANUALLY EXTENDED FLAPS; FOUND LH #3 FLAP SKEW SENSOR CAUSING C.B. TO POP. R&R?ED SKEW SENSOR PER AMM 27-59-01; FLAPS OPS CHECK NORMAL. ALSO CLEANED & INSPECTED CANNON PLUG D40024J ON LEFT WING DISCONNECT BRACKET; NO DESCREPANCIES NOTED ON THAT CANNON PLUG. C.B. RESET; FLAP SKEW DETECTION SYSTEM FUNCTIONAL TEST NORMAL IAW AMM 27-59-00.

Part: SENSOR — FAULTY (R/H WING) · airframe 70,182 hrs · 41,575 cycles

FLAPS DID NOT COME DOWN WHEN SELECTING FLAPS TO 5. WHEN USING ALTERNATE FLAP EXTENSION; ONLY RIGHT SIDE FLAPS STARTED MOVING. LEFT SIDE FLAPS STAYED AT UP POSITION. FLAPS DID NOT COME DOWN WHEN SELECTING FLAPS TO 5. WHEN USING ALTERNATE FLAP EXTENSION ONLY RIGHT SIDE FLAPS STARTED MOVING. LEFT SIDE FLAPS STAYED AT UP POSITION. PERFORMED A NO FLAP LANDING PER QRH. LANDED UNEVENTFUL. PSEU LIGHT ILLUMINATED AFTER LANDING. / [01] PERFORMED FSEU BITE CHECK; FIM 27-51 TASK 801; FOUND FAULT CODE 27-53279.<BR>FOUND FL TE FLAP POS/SKEW SNSR & IND LEFT CIRCUIT BREAKER OUT. RESET CIRCUIT BREAKER. OPS CHECK NORMAL.<BR>PSEU LIGHT EXTINGUISHED.

Part: BULB — INOPERATIVE (R1 DOOR) · airframe 70,180 hrs · 41,573 cycles

BULBS OUT ON EMERGENCY EXIT LIGHTS JUST FORWARD OF FED & FSD. / [01] REMOVED AND RELAMPED FLIGHT ENTRY DOOR EMERGENCY EXIT LIGHT BULB (1) EACH AND PERFORMED GOOD INSTALLATION TEST PER AMM 33-51-01-960-801 STEP 2.C.(1)(A);(C);(2).;[02] REMOVED AND REPLACED FOWARD SERVICE DOOR EMERGENCY EXIT LIGHT ASSEMBLY AND PERFORMED GOOD INSTALLATION TEST PER AMM 33-51-01-960-802 STEP 3.C.(2);(5)(D)(6);(7);[03] VERIFIED CORRECTIVE ACTION 1 AND 2

Part: BULB — INOPERATIVE (L1 DOOR) · airframe 70,180 hrs · 41,573 cycles

BULBS OUT ON EMERGENCY EXIT LIGHTS JUST FORWARD OF FED & FSD. / [01] REMOVED AND RELAMPED FLIGHT ENTRY DOOR EMERGENCY EXIT LIGHT BULB (1) EACH AND PERFORMED GOOD INSTALLATION TEST PER AMM 33-51-01-960-801 STEP 2.C.(1)(A);(C);(2).;[02] REMOVED AND REPLACED FOWARD SERVICE DOOR EMERGENCY EXIT LIGHT ASSEMBLY AND PERFORMED GOOD INSTALLATION TEST PER AMM 33-51-01-960-802 STEP 3.C.(2);(5)(D)(6);(7);[03] VERIFIED CORRECTIVE ACTION 1 AND 2

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 70,180 hrs · 41,573 cycles

CRACKED FLOOR SUPPORT AT STA 540; RBL 1; WL 208. / [01] REMOVED AND REPLACED FLOOR SUPPORT AT STA 540; RBL1; WL 208 IAW SRM 51-40-02 AND BOEING DWG 143A0060. MATCH DRILLED FLOOR BOARD HOLES IAW 51-40-05.;[02] VERIFIED;[03] VERIFIED CORRECTIVE ACTION STEP 1. VERIFIED MEASUREMENTS AND TASK COMPLETE.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 70,180 hrs · 41,573 cycles

CRACKED FLOOR SUPPORT AT STA 540; LBL 1; WL 208. / [01] REMOVED AND REPLACED FLOOR SUPPORT AT STA 540; LBL1; WL 208 IAW SRM 51-40-02 AND BOEING DWG 143A0060. MATCH DRILLED FLOOR BOARD HOLES IAW 51-40-05.;[02] VERIFIED;[03] VERIFIED CORRECTIVE ACTION STEP 1.VERIFIED MEASUREMENTS AND TASK COMPLETE.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: CORROSION FOUND ON STR28R AT 364 ; / [01] REMOVED PAINT BY STRIPPING AT LWR FUSELAGE SKIN S-28R BETWEEN STA 360 AND STA 400 REF B737-700 AMM 51-21-11-150-810.; [02] REMOVED FASTENERS AT LWR FUSELAGE SKIN S-28R BETWEEN STA 360 AND STA 400 TO GAIN ACCESS REF B737-700 SRM 51-40-02-0G-0.; [03] CUT AND REMOVED DAMAGED S-28R SECTION AT LWR FUSELAGE SKIN BETWEEN STA 360 AND STA 400 REF B737-700 SRM 51-10-02-0G-0 AND 53-00-03-2R-1 FIG 205.; [04] (RII) VERIFIED STEP #3; DAMAGE REMOVAL.; [05] PERFORMED HFEC INSP ON CUTOUT AREA IAW B737 NDT P6 51-00-00 PROC.23; NO CRACKS<BR>TOOL USED : NORTEC 600 B/C 172389 07/22; [06] PERFORMED ROTO INSP ON ALL OPEN HOLES AT LOWER FUSELAGE SKIN S28R STA360-400 IAW B737 NDT P6 51-00-00 PROC.16; NO CRACKS<BR>TOOL USED : NORTEC 600 B/C 172389 07/22; [07] FABRICATED NEW STRINGER SPLICE AND DRILLED NEW STRINGER SECTION TO ACCOMPLISHED REPAIR PER REF B737 SRM 53-00-03-2R-1 FIG 205.;

Part: BATTERY PACK — INOPERATIVE (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

EXTERIOR EMERGENCY LIGHT L/H AT EMERGENCY EXIT DOOR INOP. ; EXTERIOR EMERGENCY LIGHT LH AT EMERGENCY EXIT DOOR INOP. / [01] REMOVED AND REPLACED EMERGENCY BATTERY PACK POSITION M1668 AS REPORTED IN TASK CARD NO. TTG8Q009WZ6W; AS PER REFERENCE B737 AMM B737 AMM 33-51-06-960-805. PERFORMED OPERATIONAL TEST; TEST NORMAL OPERATION.

Part: BATTERY PACK — INOPERATIVE (CABIN) · airframe 69,290 hrs · 41,022 cycles

EMERGENCY BATTERY PACK POSITION M1664 INOP. REMOVED AND REPLACED EMERGENCY BATTERY PACK POSITION M1668 AS PER REF B737- AMM- 33-51-06-960-805.OPERATIONAL TEST FOUND NORMAL..

Part: STRINGER SPLICE — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

***CORROSION*** FOUND ON THE E&E STA 354 STR28R TWO RIVETS ; / [01] REMOVED DAMAGE EXISTING SPLICE AT E&E STA 354 S-28R REF B737-700 SRM 51-40-02-0G-0.; [02] FABRICATED NEW STRINGER SPLICE P/N 141A3531-5 FROM 7075-0 0.040' IAW DWG #141A3531.;

Part: BRACKET — OUT OF POSITION (ZONE 200) · airframe 69,290 hrs · 41,022 cycles

DURING P-18 WALL INSTALLATION FOUND TWO SUPPORT BRACKETS (STGR-6L AND STGR 8L) OUT OF POSITION. ; / [01] REMOVED P-18 SUPPORT BRACKETS AT STR 6L AND STR 8L; REINSTALLED AT RIGHT LOCATION IN IAW SRM 51-40-02-0G-0 AND DWG# 141A0720; [02] VERIFIED STEP 1

Part: SKIN — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

FUSELAGE SKIN UNDER DORSAL HAS MINOR CORROSION SPOTS BS 882-893 LBL 6- RBL 5. 8-143. REMOVED MINOR CORROSION ON AREAS IAW SRM 51-10-02-0G-0. PERFORMED UT THICKNESS INSP ON REWORKED AREAS IAW NDT P4 51-00-00 PROC.3. FOUND WITHIN LIMITS IAW SRM 53-00-01-1A-1 FIG. 103 A-A. TREATED AND PRIMED AREAS IAW SRM-51-21-72-370-801.

Part: SHEAR TIE — CRACKED (BS 225) · airframe 69,290 hrs · 41,022 cycles

FOUND SHEAR TIE CRACKED AT FLIGHT DECK STA 225 RBL 40 ; / [01] INSTALLED EWS PROTECTION AT FLIGHT DECK R/H SIDE BETWEEN STA 220 AND STA 230 REF B737-700 AMM 20-60-07-913-801.; [02] REMOVED DAMAGE SHEAR TIE AT FLIGHT DECK R/H SIDE BETWEEN STA 219.8 AND STA 224.8 WL 208 REF B737-700 SRM 51-40-02-0G-0.; [03] FABRICATED AND HEAT TREATED NEW SHEAR TIE MATERIAL USED 2024-O 0.040' PO# 1732885. REF DWG# 141A5137 AND FORM OP 84.; [04] LOCATED AND DRILLED NEW SHEAR TIE AT FLIGHT DECK R/H SIDE BETWEEN STA 219.8 AND STA 224.8 WL 208 REF B737-700 SRM 51-40-05-0G-0 AND DWG# 141A0640.; [05] VERIFIED 1-4. OK TO TREAT AND PRIME.; [06] TREATED AND PRIMED NEW SHEAR TIE REF B737-700 SRM 51-20-01-0G-0.; [07] VERIFIED 6. OK TO INSTALL SHEAR TIE.; [08] INSTALLED NEW SHEAR TIE AT FLIGHT DECK R/H SIDE BETWEEN STA 219.8 AND STA 224.8 WL 208 REF B737-700 SRM 51-40-05-0G-0 AND DWG# 141A0640.; [09] STEP #8 SRM REF 51-40-02-0G-0.; [10] REMOVED AND REPLACED SHEAR TIE AT FLIGHT DECK R/H SIDE BETWEEN STA 219.8 AND STA 224.8 WL 208 REF B737-700 SRM 51-40-02-0G-0 AND DWG# 141A0640.; [11] REMOVED EWIS PROTECTION AT FLIGHT DECK R/H SIDE BETWEEN STA 220 AND STA 230 REF B737-700 AMM 20-60-07-913-801.; [12] VERIFIED STEPS 10;11.

Part: BULKHEAD WEB — CRACKED (BS 663) · airframe 69,290 hrs · 41,022 cycles

FUEL VAPOR BARRIER WEB LOWER EDGE CLIP CRACKED RBL 25.0 STA 663 ; / [01] REMOVED LOWER EDGE CLIP AT FUEL VAPOR BARRIER WEB; RBL 25.0 STA 663 AS PER B737-700 SRM 51-40-02-0G-0; [02] FABRICATED LOWER EDGE CLIP IAW.B-737-700 DWG# 111A1304; [03] VERIFIED STEPS 1 AND 2.; [04] TREATED(ANODIZING PART 111A1304-2 OUT SIDE VENDOR PREMIER AEROSPACE)WC:413205; [05] VERIFIED STEP 4.; [06] OK TO INSTALLLOWER EDGE CLIP.; [07] LATE ENTRY: OK TO PRIME CLIP; [08] PRIMED LOWER EDGE CLIP AT FUEL VAPOR BARRIER WEB; RBL 25.0 STA 663 AS PER B737-700 SRM 51-20-01-0G-0; [09] INSTALLED LOWER EDGE CLIP AT FUEL VAPOR BARRIER WEB; RBL 25.0 STA 663 AS PER B737-700 SRM 51-40-02-0G-0; [10] VERIFIED STEP 8 AND 9.

Part: SEAT TRACK — CORRODED (CABIN) · airframe 69,290 hrs · 41,022 cycles

F/O LH FWD SEAT TRACK HAS CORROSION ON LOWER SURFACE. 8-133 ; / [01] RECEIVED NEW F/O LEFT FWD FROM STOCK. PART WILL BE INSTALLED ON ROUTINE CARD TTG8Q001RUZP.; [02] CORRECTING STATEMENT - RECEIVED NEW F/O LEFT FWD SEAT TRACK FROM STOCK. PART WILL BE INSTALLED ON ROUTINE CARD TTG8Q001RUZP.; [03] FINAL INSPECTION; SEAT TRACK RECEIVED.

Part: FITTING — CORRODED (VERT TO FUSE) · airframe 69,290 hrs · 41,022 cycles

VERTICAL STAB FRONT SPAR RIGHT FWD FUSELAGE FITTING BORE HAS PITTING ; / [01] REMOVED CORROSION AT VERTICAL STAB. FUSELAGE FRONT SPAR RH SIDE LUG BORE ; REAM HOLE FITTING FWD 1.1195'' AS PER B737 SRM 51-10-02-0G-0.; [02] VERIFIED 1.; [03] NEW BUSHING WAS FABRICATED AND INSTALLED AS PER EA 21-153-03537. BUSHING WAS FABRICATED BY PREMIER AEROSPACE PO- 1748138.; [04] ''PERFORMED EA 21-153-03537. REF. FAULT TTG8Q009DJAZ.'; [05] VERIFIED STEPS 3 AND 4.

Part: SEAT TRACK — CORRODED (COCKPIT) · airframe 69,290 hrs · 41,022 cycles

CAPT LH FWD SEAT TRACK HAS CORROSION ON LOWER SURFACE. 8-135 ; / [01] REPLACED CAPTAIN'S L/H FWD SEAT TRACK REF AMM 25-11-11-200-801-NG . REFER TO CUSTOMER BARCODE#TTG8Q009DU9K FOR INSTALLATION.; [02] CORRECTING STATEMENT - REPLACED CAPTAIN'S L/H FWD SEAT TRACK REF AMM 25-11-11-200-801-NG . REFER TO CUSTOMER BARCODE#TTG8Q001RUZP FOR INSTALLATION.; [03] FINAL INSPECTION; SEAT TRACK REPLACED.

Part: FITTING — CORRODED (VERT TO FUSE) · airframe 69,290 hrs · 41,022 cycles

VERTICAL STAB FRONT SPAR RIGHT FWD FUSELAGE FITTING FWD SURFACE HAS LIGHT PITTING ON SURFACE. ; / [01] PERFORMED PENETRANT INSPECTION ON VERTICAL STAB.FRONT SPAR RIGHT FWD FUSELAGE FITTING FWD.SURFACE IAW SOPM 20-20-02. NO CRACKS.; [02] PERFORMED HFEC ROTO ON VERTICAL STAB.FRONT SPAR RIGHT FWD FUSELAGE FITTING IAW NDTM PART 6;51-00-00 PROCEDURE 16. NO CRACKS.; [03] REMOVED BUSHING AT FUSELAGE VERTICAL STAB. FRONT SPAR . RIGHT SIDE FWD FITTING AS PER B737 SOPM 20-50-03.; [04] REMOVED CORROSION AS FUSELAGE VERTICAL STAB . RIGHT SIDE FWD FITTING FWD FACE ; SPOT FACE AREA ; ORIGINAL MATERIAL 0.5000'' ; MATERIAL REMOVED IS 0.0050'' AND SPOT FACE SIZE IS 1.7000'' ; FITTING THICKNESS REMAINING IS 0.4950'' AS PER SRM 51-10-02-0G-0.; [05] CORRECTION -------<BR>REMOVED CORROSION AS FUSELAGE VERTICAL STAB . RIGHT SIDE FWD FITTING FWD FACE ; SPOT FACE AREA ; ORIGINAL MATERIAL 0.5700'' ; MATERIAL REMOVED IS 0.0012'' AND SPOT FACE SIZE IS 1.7000'' ; FITTING THICKNESS REMAINING IS 0.4950'' AS PER SRM 51-10-02-0G-0.; [06] CORRECTION FOR STEP 5<BR>ORIGINAL MATERIAL - 0.5100'' <BR><BR>MATERIAL REMOVE - 0.0150''; [07] VERIFIED 3; 5; 6.; [08] ISSUED SUMMARY EA 21-153-03537; [09] CORROSION REMOVED AND AREA INSPECTED ; SHOT/FLAP PEEN AS PER EA 21-153-03537.; [10] NEW BUSHING WAS FABRICATED AND INSTALLED AND AREA WHERE CORROSION WAS REMOVED WAS LEFT AS IS AS PER EA 21-153-03537. - BUSHING WAS FABRICATED BY PREMIER AEROSPACE PO -1748138.; [11] VERIFIED 9 AND 10.

Part: FITTING — CORRODED (VERTICAL TO FUSE) · airframe 69,290 hrs · 41,022 cycles

VERTICAL STAB FRONT SPAR LEFT FWD FUSELAGE FITTING FWD SURFACE HAS LIGHT PITTING ON SURFACE. ; / [01] PERFORMED PENETRANT INSPECTION ON VERTICAL STAB.FRONT SPAR LEFT FWD FUSELAGE FITTING FWD.SURFACE IAW SOPM 20-20-02. NO CRACKS.; [02] PERFORMED HFEC ROTO ON VERTICAL STAB.FRONT SPAR LEFT FWD FUSELAGE FITTING IAW NDTM PART 6;51-00-00 PROCEDURE 16. NO CRACKS.; [03] REMOVED VERTICAL STAB FUSELAGE LEFT SIDE FWD FITTING BUSHING AS PER B737 SOPM 20-50-03.<BR><BR><BR>REMOVED CORROSION AT FUSELAGE VERTICAL STAB. FRONT SPAR LEFT SIDE FWD FITTING FWD FACE ; SPOT FACE AREA ; ORIGINAL MATERIAL 0.5000'' ; REMOVED MARTIAL 0.0090'' ; SPOT FACE SIZE IS 1.700'' AND REMAINING THICKNESS IS 0.4910'' AS PER SRM 51-10-02-0G-0.; [04] VERIFIED 3.; [05] REMOVED CORROSION ON LEFT SIDE VERTICAL STAB AFT FITTING AFT FACE ; SHOT PEEN AREA ; THREATED AND PRIME ; THICKNESS OF CLEVIS WILL BE LEFT AS IS AS PER EA 21-153-03538.; [06] NEW BUSHING WAS FABRICATED AND INSTALLED ON VERTICAL STAB LH SIDE AFT FITTING AFT FACE AS PER EA 21-153-03538.; [07] -CORRECTON - REMOVED CORROSION ON LEFT SIDE VERTICAL STAB FWD FITTING FWD FACE ; SHOT PEEN AREA ; THREATED AND PRIME ; THICKNESS OF CLEVIS WILL BE LEFT AS IS AS PER EA 21-153-03538.; [08] CORRECTION - NEW BUSHING WAS FABRICATED AND INSTALLED ON VERTICAL STAB LH SIDE FWD FITTING FWD FACE AS PER EA 21-153-03538.; [09] VERIFIED STEPS 5 THRU 8;

Part: FITTING — CORRODED (VERT TO FUSE) · airframe 69,290 hrs · 41,022 cycles

VERTICAL STAB FRONT SPAR LEFT FWD FUSELAGE FITTING BORE HAS PITTING ; / [01] REMOVED CORROSION AT VERTICAL STAB. FUSELAGE FRONT SPAR LH SIDE LUG BORE ; REAM FITTING HOLE FWD 1.2040'' AND AFT 1.1197'' AS PER B737 SRM -51-10-02-0G-0; [02] CORRECTION FOR STEP 1 <BR><BR>HOLE FWD - 1.1197''<BR>HOLE AFT - 1.2040''; [03] VERIFIED 1-2.; [04] REAM FITTING HOLE FWD 1.2040'' AND AFT 1.1197'' AS PER SRM 51-10-02-0G-0 AND EA 21-153-03538 ; AND NEW BUSHING AS FABRICATED AND INSTALLED AS PER EA 21-153-03538.; [05] VERIFIED STEP 5; [06] TOOLING INFO ONLY : BC 15463 09 MAR 22 CAL DATE

Part: ANGLE — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S-21L AND-23L AT STA 336 APPX. FOUND CORROSION ON ANGLE CHORD. ; / [01] REMOVED EXFOLIATED ANGLE E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S21L AND S23L AT STA 336 APPX. IAW SRM 51-40-02-0G-0.; [02] REMOVED ANGLE CHORD AT E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S21L AND S23L AT STA 336 APPX. FOUND OUT OF LIMITS IAW SRM 53-10-15-1A-1; 4.D.; [03] LOCATED AND DRILLED NEW ANGLE CHORD AT E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S21L AND S23L AT STA 336 APPX. PER B737-700 SRM 51-40-05-0G-0 AND DWG# 141A8240.

Part: TEE ANGLE — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

CORROSION ON E&E COMPARTMENT LOWER AUXILIARY SILL S-23L FROM BS 294.5 TO 312 . REMOVED EXFOLIATED TEE ANGLE IAW SRM 51-40-02-0G-0. PERFORMED PENETRANT INSP ON FABRICATED ANGLE IAW SOPM 20-20-02; NO CRACKS NOTED. A NEW TEE ANGLE FABRICATED AND INSTALLED THE NEW TEE ANGLE IAW SRM 51-40-02-0G-0 AND DWG 141A8131.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

E&E COMPARTMENT LOWER AUXILIARY SILL BETWEEN S-21L AND-23L AT STA 320. FOUND CORROSION ON ANGLE. REMOVED EXFOLIATED ANGLE CHORD AT E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S21L AND S23L AT STA 320 APPX. IAW SRM 51-40-02-0G-0. REMOVED ANGLE CHORD AT E&E BAY LOWER SILL. FOUND OUT OF LIMITS IAW SRM 53-10-15-1A-1; 4.A. LOCATED AND DRILLED NEW ANGLE. FOUND OUT OF LIMITS IAW SRM 51-40-05-0G-0 AND DWG#141A8240. TREATED AND PRIMED DRILLED HOLES. INSTALLED NEW ANGLE IAWSRM 51-20-01-0G-0 AND DWG#141A8240.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S-21L AND-23L AT STA 320 FOUND CORRODED ON ANGLE. REMOVED EXFOLIATED ANGLE IAW SRM 51-40-02-0G-0. PERFORMED PENETRANT INSP ON FABRICATED ANGLE IAW SOPM 20-20-02, NO CRACKS NOTED. NEW ANGLE FABRICATED. LOCATED AND DRILLED NEW ANGLE IAW SRM 51-40-05-0G-0. APPLIED ALODINE AND PRIMER IAW SRM 51-20-01-0G-0. INSTALLED NEW ANGLE IAW SRM 51-40-05-0G-0; SRM 51-40-02-0G-0; AND DWG #141A1180.

Part: BEAR STRAP — DAMAGED (BS291-295 S9-10R) · airframe 69,290 hrs · 41,022 cycles

DURING REPAIR OF R1 BEAR STRAP AT STA 291 TO 295 SR 9R AND 10R 4 FASTENER HOLE WHERE FOUND ELONGATED. ; / [01] CLEANED UP DAMAGE FROM HOLES 4 (EA) LOCATED AT R1 DOOR BEAR STRAP AT STA 291 TO STA 295 STR 9R AND 10R BY REAMING TO FIRST OVERSIZE 0.201' FOR TRANSITION FIT INSTALLATION OF HEX BOLT. FINAL INSTALLATION OF FASTENERS WILL BE ACCOMPLISHED DURING INSTALLATION OF BEAR STRAP REPAIR ON FAULT TTG8Q0094F9V; [02] VERIFIED STEP # 1; [03] JOB IS COMPLETE INSTALLATION OF FASTENER ON TTG8Q0094F9V; [04] PERFORMED EA 21-153-03281. REF FAULT TTG8Q0094F9V

Part: PANEL — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

CORROSION ON FLIGHT DECK ENTRY FLOOR PANEL 211AF MATING SURFACE MKD DOT ; / [01] RECEIVED NEW PANEL 211AF ;THIS PANEL WILL BE INSTALL ON FAULY TTG8Q006JDOU; [02] VERIFIED STEP 1

Part: PANEL — CRACKED · airframe 69,290 hrs · 41,022 cycles

PNL 193D HAS CRACKS AT 8 EACH AFT EDGE FASTENER HOLES. REPAIR THE PANEL PER SRM 53-40-70 OR CONTACT ENGINEERING VIA TSR FOR INSTRUCTIONS. REF CARD 5351-I-14642-NG; AD 2020-03-10 (CONTINUED BELOW)8-108 ; AFTER REPAIR IS COMPLETED SIGN OFF STEP 17 OF REF CARD. / [01] TAPERED SAND AROUND THE HOLES TO REMOVE THE DAMAGE. PERFORMED DRY OUT FOR 24 HOURS; NO WATER NOTE; THE REPAIR AREA IS FULLY DRY. REF SRM 53-40-70-2R-1 AND SRM 51-70-05-2R-8 REPAIR 8 PARAGRAPH 4 B; AND D.; [02] VERIFIED STEP 1; <BR>OK TO INSTALL REPAIR; [03] APPLIED REPAIR AT DAMAGED AREA ON PNL 193D ON AFT EDGE FASTENERS HOLE. REF B737-700 SRM 53-40-70-2R-1 AND SRM 51-70-05-2R-8 PARAGRAPH 4.; [04] VERIFIED STEP 3.

Part: BRACKET — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: **CORROSION**JACKSCREW COMPARTMENT BEHIND ACCESS 311BL; APU'S INLET PLENUM AFT ATTACHING BRACKETS TO STRUCTURE; CORRODED. DOT#208-26 ; BS 1088 RT SIDE FWD AT PLENUM CUTOUT AT ALL 4 SIDES / [01] REMOVED CORROSION AT JACKSCREW COMPARTMENT BEHIND ACCESS 311 BL APU INLET PLENUM AFT ATTACHING BRACKETS TO STRUCTURE STA 1088 RT SIDE IN REF B 737-700 SRM 51-10-02-0G-0; [02] VERIFIED 1.; [03] AFTER RE-INSPECTED STIFFENER UP POSITION PN# 148A2488-5 FOUND EXFOLIATION CORROSION OUT OF LIMITS IN IAW SRM 53-80-08-1A-1; [04] VERIFIED STEP 3; [05] LATE ENTRY: TO ADD ON STEP #3 MATERIAL ORIGINAL 0.071' MATERIAL LOST 0.043' MATERIAL REMAINING 0.028' FOUND OUT LIMITS IN IAW SRM 53-80-08-1A-1 ( TOOL USED CALIPER B/C 172990; [06] RECEIVED NEW STIFFENER P/N 148A2488-5 LOCATED AND DRILLED IN IAW SRM 51-40-05-0G-0; [07] VERIFIED STEPS 5AND 6.<BR>OK TOO INSTALL STIFFNER; [08] INSTALLED STIFFENER UP POSITION P/N#148A2488-5 AT JACKSCREW COMPARTMENT BULLHEAD STRUCTURE STA 1088 RT SIDE RBL 20' IN IAW DWG# 148A0924 AND 51-40-02-0G-0; [[14] LATE ENTRY: TO ADD ON STEP #3 MATERIAL ORIGINAL 0.071' MATERIAL LOST 0.043' MATERIAL REMAINING 0.028' FOUND OUT LIMITS IN IAW SRM 53-80-08-1A-1 ( TOOL USED CALIPER B/C 172990; [15] REMOVED AND REPLACED STIFFENER UP POSITION P/N#148A2488-5 AT JACKSCREW COMPARTMENT BULKHEAD STRUCTURE STA 1088 RT SIDE RBL 20' IN IAW SRM 51-40-02-0G-0 AND DWG#148A0924; [16] FINAL INSPECTION; STIFFENER REPLACED.

Part: GUSSET — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

FWD CARGO GUSSET CRACKED AT BS 500D S-19R. 8-105 ; / [01] REMOVED FWD CARGO GUSSET AT BS 500D S-19R AS PER B737-700 SRM 51-40-02-0G-0; [02] LOCATED AND DRILLED NEW GUSSSET AT BS 500D S-19R B737-700 SRM 51-40-05-0G-0; [03] VERIFIED STEP 1 AND 2.<BR>OK TO INSTALL PART.; [04] INSTALLED NEW FWD CARGO GUSSET AT BS 500D S-19R AS PER B737-700 SRM 51-40-02-0G-0 DWG 143A7902; [05] REMOVED AND REPLACED FWD CARGO GUSSET AT BS 500D S-19R AS PER B737-700 SRM 51-40-02-0G-0; [06] VERIFIED STEP 4 AND 5.

Part: PANEL — CRACKED · airframe 69,290 hrs · 41,022 cycles

PNL 194E HAS CRACK ON AFT EDGE AT 3RD HOLE FROM THE LEFT. REPAIR THE PANEL PER SRM 53-60-70 OR CONTACT ENGINEERING VIA TSR FOR INSTRUCTIONS. REF CARD 5351-I-14642-NG; AD 2020-03-10 8-100 ; AFTER REPAIR IS COMPLETED SIGN OFF STEP 8 ON REF CARD. / [01] MEASUREMENTS; [02] TAPERED SAND AROUND THE HOLES TO REMOVE THE DAMAGE. PERFORMED DRY OUT FOR 24 HOURS; NO WATER NOTE; THE REPAIR AREA IS FULLY DRY. REF SRM 53-40-70-2R-1 AND SRM 51-70-05-2R-8 REPAIR 8 PARAGRAPH 4 B; AND D.; [03] VERIFIED STEP 1 AND 2; [04] OK TO INSTALL REPAIR; [05] APPLIED REPAIR AT DAMAGED AREA ON PNL 194E ON AFT EDGE AT 3RD HOLE FROM THE LEFT. REF B737-700 SRM 53-40-70-2R-1 AND SRM 51-70-05-2R-8 PARAGRAPH 4.; [06] VERIFIED STEP 5; [07] OK TO APPLY DECORATIVE FINISH.; [08] APPLIED FINISH AT REPAIR AREA REF B737-700 SRM 53-40-70-2R-1 AND SRM 51-70-05-2R-8 PARAGRAPH 4.; [09] VERIFIED STEP 8.

Part: ATTACH BRACKET — CRACKED (BS 273 S10L) · airframe 69,290 hrs · 41,022 cycles

P-18 ATTACH BRACKET CRACKED BS 273 AT S-10L. 8-92 ; / [01] REMOVED ATTACH BRACKET AT BS 273;S-10L AS PER B737-700 SRM 51-40-02-0G-0; [02] FABRICATED P-18 ATTACH BRACKET IAW. DWG. #141A9502-10; [03] VERIFIED 1-2. OK TO TREAT AND PRIME.; [04] TREATED AND PRIME P-18 ATTACH BRACKET IAW. B-737-700 SRM. 51-20-01-0G-0 AND B-737-700 AMM. 51-21-72-370-804; [05] VERIFIED 4.; [06] (LATE ENTRY) PERFORMED HEAT TREAT ON BRACKET(CLIP) AS PER DWG#141A9502 BAC5602; FORM OP84; [07] VERIFIED 6.; [08] OK TO INSTALL.; [09] INSTALLED P-18 ATTACH BRACKET AT BS.273; STR. 10L. IAW. B-737-700 SRM. 51-40-02 AND DWG #141A0720; [10] INSTALLED P-18 ATTACH BRACKET AT BS.273; STR. 10L. IAW. B-737-700 SRM. 51-40-02-0G-0 AND DWG #141A0720; [11] VERIFIED STEP 9AND 10.

Part: ATTACH BRACKET — CRACKED (BS 273 S8L) · airframe 69,290 hrs · 41,022 cycles

P-18 ATTACH BRACKET CRACKED BS 273 AT S-8L. 8-91 ; / [01] REMOVED ATTACH BRACKET AT BS 273;S-8L AS PER B737-700 SRM 51-40-02-0G-0; [02] FABRICATED P-18 ATTACH BRACKET IAW. DWG #141A0720; [03] TO CORRECTING STEP # 2 DWG# 141A9502-5; [04] TREATED AND PRIME P-18 ATTACH BRACKET IAW. B-737-700 SRM. 51-20-01-0G-0 AND B-737-700 AMM. 51-21-72-370--804; [05] VERIFIED 1-4.; [06] (LATE ENTRY) PERFORMED HEAT TREAT ON BRACKET(CLIP) AS PER DWG#141A9502 BAC5602; FORM OP84; [07] VERIFIED 6.; [08] OK TO INSTALL;; [09] INSTALLED P-18 ATTACH BRACKET AT BS.273; STR. 8L. IAW. B-737-700 SRM. 51-40-02 AND DWG #141A0720; [10] INSTALLED P-18 ATTACH BRACKET AT BS.273; STR. 8L. IAW. B-737-700 SRM. 51-40-02-0G-0 AND DWG #141A0720; [11] VERIFIED STEP 9AND 10.

Part: FRAME — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: ABOVE L1 CUTOUT LWR END OF FRAME BS 312 APPEARS TO BE CRACKED AT RADIUS BETWEEN S-5L AND S-6L. 8-95 ; / [01] REMOVED EXISTING FASTENERS FOR ACCESS TO REPAIR IN IAW SRM 51-40-02-0G-0; [19] INSTALLED REPAIR ANGLE AT L-1 CUTOUT LWR OF FRAME BS 312 BETWEEN S-5L AND S-6L IN IAW SRM 53-10-07-2R-1 FIG 202 AND 203 SHEET 1; [20] APPLIED A LAYER OF BMS 3-23; TYPE LL CORROSION INHIBITING COMPOUND ON THE SURFACE OF REPAIR AREA IN IAW AMM 51-21-91-620-801; [21] FABRICATED AND INSTALLED REPAIR ANGLE AT L-1 CUTOUT LWR OF FRAME BS 312 BETWEEN S-5L AND S-6L IN IAW SRM 53-10-07-2R-1 FIG 202 AND 203 SHEET 1; [22] VERIFIED STEPS 18;19;20 AND 21.

Part: LUG — CORRODED (LT WING SPAR) · airframe 69,290 hrs · 41,022 cycles

VERTICAL LEADING EDGE LEFT I/B AND O/B FRONT SPAR FITTING LUG FACE AREA PITTING/CORROSION NOTED.

Part: WEB — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S-21L AND-23L AT STA 336 APPX. FOUND CORROSION ON WEB. REMOVED WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S-21L AND S-23L PER B737-700 SRM 51-40-02-0G-0; [02] VERIFIED STEP #1. FABRICATED WEB P/N 141A1180-25 MAT USED 7075-O CLAD 0.040 PO#1696337 REF DWG#141A1180. LOCATED AND DRILLED NEW WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S-21L AND S-23L PER B737-700 SRM 51-40-05-0G-0 AND DWG #141A1180. INSTALLED NEW WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S-21L AND S-23L PER B737-700 SRM 51-40-02-0G-0 AND DWG# 141A1180.

Part: WEB — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

E&E COMPARTMENT LOWER AUXILIARY SILL; BETWEEN S-21L AND-23L AT STA 320 APPX. FOUND CORROSION ON WEB. REMOVED WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL IAW SRM 51-40-02-0G-0. INSTALLED NEW WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL IAW SRM 51-40-02-0G-0 AND DWG 141A1180.

Part: FITTING — CRACKED (VERT STAB SPAR) · airframe 69,290 hrs · 41,022 cycles

VERTICAL FIN FRONT SPAR FITTING; FIX LEADING EDGE SPRING ANGLE CRACK NOTED. ; / [01] REMOVED FIX LEADING EDGE SPRING ANGLE AT VERTICAL FIN FRONT SPAR FITTING IAW SRM 51-40-02-0G-0.; [02] VERIFIED STEP #1; [03] LOCATED AND DRILLED NEW FITTING FIX LEADING EDGE VERTICAL FIN FRONT SPAR SPRING ANGLE IAW B737-700 SRM 51-40-05-0G-0 AND DWG# 176A3101.; [04] (RII) VERIFIED STEP #3; [05] OK TO INSTALL NEW REPLACEMENT FIX L/E SPRING ANGLE.; [06] MIXED 0870C080BM654SKN40 SEALANT 17:00 12-01-21 SQUEEZE OUT TIME BY 03:00 12-05-21; [07] INSTALLED NEW FITTING FIX LEADING EDGE VERTICAL FIN FRONT SPAR SPRING ANGLE IAW B737-700 SRM 51-40-02-0G-0AND DWG# 176A3101; [08] (FINAL) REMOVED FIX LEADING EDGE SPRING ANGLE AT VERTICAL FIN FRONT SPAR FITTING IAW SRM 51-40-02-0G-0. LOCATED AND DRILLED NEW FITTING FIX LEADING EDGE VERTICAL FIN FRONT SPAR SPRING ANGLE IAW B737-700 SRM 51-40-05-0G-0 AND DWG# 176A3101. INSTALLED NEW FITTING FIX LEADING EDGE VERTICAL FIN FRONT SPAR SPRING ANGLE IAW B737-700 SRM 51-40-02-0G-0AND DWG# 176A3101; [09] (RII) FINAL INSPECTION; FIX L/E SPRING ANGLE REPLACED.

Part: ATTACH FITTING — BROKEN (BODY PANEL) · airframe 69,290 hrs · 41,022 cycles

LT BODY PNL 192BL ATTACH FLANGES HAVE 8 BROKEN RECPTICALS. 8-80 ; / [01] REMOVED RECPTICALS AT LT BODY PNL 192BL ATTACH FLANGES AS PER B737 SRM 51-40-02-0G-0; [02] REMOVED AND REPLACED 8 ATTACHED FLANGES AT LT BODY PNL 192BL IAW SRM 51-40-02-0G-0; [03] VERIFIED STEP 1 AND 2.

Part: ATTACH FITTING — BROKEN (BODY PANEL) · airframe 69,290 hrs · 41,022 cycles

RT BODY PNL 192BR ATTACH FLANGES HAVE 2 BROKENRECPTICALS IN FWD AREA. 8-81 ; / [01] REMOVED AND REPLACED 2 ATTACHED FLANGES AT RT BODY PNL 192BR IAW SRM 51-40-02-0G-0; [02] VERIFIED STEP 1.

Part: SKIN — BULGED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: SKIN HAS BULGE AT RIVET BS 397 S-20R. 8-72 ; / [01] REMOVED RIVET AT FUSELAGE SKIN BS 397 S-20R PER REF B737 SMR 51-40-02-0G-0;[08] ACCOMPLISHED DVI ON STRUCTURE AT INTERNAL AND EXTERNAL AREAS OF BULGE. FOUND STRINGER 20R WITH DENT AND TOOLING MARKS ON AFT SIDE OF WHERE FASTENER WAS REMOVED PER B737-700 SRM 51-10-04-0G-0; [10] PERFORMED HFEC ROTOR INSP ON FASTENER OPEN HOLE. IAW B 737 NDT PART 6 51-00-00 PROC 16. TOOL NORTEC 600. BC 166316. CALIB DUE 10-8-22. NO CRACKS FOUND.;[24] FABRICATED AND HEAT TREAT REPLACEMENT STRINGER CLIPS P/N 143A1010-19 AND 143A1010-74 FOR S-20R REF ADD 21-153-03573.; [25] VERIFIED 24. OK TO TREAT AND PRIME CLIPS.; [26] TREATED AND PRIMED NEW CLIPS REF B737-700 SRM 51-20-01-0G-0.; [27] INSTALLED 95% OF FASTENERS AT S-20R BETWEEN STA 380 AND STA 420 REF B737-700 SRM 53-00-03-2R-1 FIG 203.; [30] INSTALLED NEW REPLACEMENT STRINGER CLIPS P/N 143A1010-19 AND 143A1010-74 AT S-20R REF ADD 21-153-03573.; [31] COMPLETED INSTALLATION REPAIR PARTS AT S-20R BETWEEN STA 380 AND STA 420 REF B737-700 SRM 53-00-03-2R-1 FIG 203 TABLE 202.; [37] AFTER FURTHER EVALUATION OF DAMAGE AREA ON SKIN S-20R AT BS 397 FOUND STRINGER 20R WITH DENT AND TOOLING MARKS ON AFT SIDE OF WHERE FASTENER WAS REMOVED; ACCOMPLISHED REPAIR OF DAMAGE STRINGER PER EA 21-153-03573; [38] VERIFIED STEPS 36 AND 37.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 69,290 hrs · 41,022 cycles

CABIN FLOOR PNL 221EF HAS CRACK IN FWD LT AREA. 8-70 ; / [01] CLEANED AND PREPARED FOR REPAIR THE FIBERGLASS AT CABIN FLOOR PANEL 221 EF AS PER B737-700 SRM.53-00-50-2R-2; [02] VERIFIED.; [03] REPAIRED AT CABIN FLOOR PANEL 221 EF AS PER B 737 -700 SRM. 53-00-50-2R-2 MATERIAL USED PO.1711677 ;PO.1150387 AND PO.1713932; [04] VERIFIED STEP 3.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 69,290 hrs · 41,022 cycles

RIGHT HORIZONTAL STABILIZER INSPAR RIB ASSY. #4 (STAB STA 120.30) STIFFENER #3; LOWER AREA CRACK NOTED. ; / [01] CUT AND REMOVED THE DAMAGE FROM THE VERTICAL #3 STIFFENER OF THE RIB AND CUT AND REMOVED THE DAMAGE FROM THE WEB. MADE THE CORNER RADII OF THE WEB CUTOUT A MINIMUM OF 0.167 IN IN IAW SRM 55-10-09-2R-4 FIG202 SHEET1; [02] VERIFIED STEP 1; [03] PERFORMED HFEC INSP ON CUTOUT AREA. IAW B 737 NDT PART 6 51-00-00 PROCE 23. TOOL NORTEC 600. BC 166316. CALIB DUE 10-8-22. NO CRACKS FOUND.; [04] CHECKED SURFACE FINISH ON CUT OUT AREA FOUND TO BE SMOOTHER THAN 63 MICRO INCHES RA REF B737 SRM 51-20-13.; [05] LOCATED AND DRILLED REPAIR PARTS FROM KIT 55100003-01 PER REF B737 SRM 51-40-02-0G-0; [06] TOOL USED FOR SURFACE FINISH; ROUGHNESS CHECK ID 172329; [07] ACCOMPLISHED GVI OF ALL THE AREAS WITHIN THE REPAIR PER SRM 55-10-09; NO DEFECTS NOTED.; [08] VERIFIED STEPS 4; 5 AND 6.; [09] OK TO INSTALL REPAIR PARTS TO RIB ASSY #4; STIFFENER #3.; [10] MIXED PRC BMS5-95 ON 12/13/21 AT 10:00AM; SQUEEZE OUT TIME BY 12/13/21 AT 12:00 PM; INSTALLED REPAIR PARTS PER RE B737 SRM 55-10-09-2R-4; [11] ACCOMPLISHED PERMANENT REPAIR OF RT HORZ STAB RIB ASSY #4 STA 120.3 STIFFENER #3 PER REF B737 SRM 55-10-09-2R-4; [12] VERIFIED STEP 11; [13] LATE ENTRY: VERIFIED STEP 10.; [14] RII STEP 10 AND 11 C/W; [15] C/W; [16] C/W

Part: WEB — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 312 TO STA 325.38 APPX. FOUND CORROSION ON WEB. REMOVED WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 312 TO STA 325.38 PER SRM 51-40-02-0G-0. WEB REMOVED ON STEP #1 CORROSION EXFOLIATE. FOUND OUT OF LIMITS PER SRM 53-10-15-1A-1. LOCATED AND DRILLED NEW WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 312 TO STA 325.38 IAW SRM 51-40-05-0G-0 & DWG #141A8131. TREATED AND PRIMED DRILLED HOLES ON NEW WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 312 TO STA 325.38 IAW SRM 51-20-01-0G-0. INSTALLED NEW WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 312 TO STA 325.38 IAW SRM 51-40-02-0G-0 AND DWG#141A8131.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 69,290 hrs · 41,022 cycles

CABIN FLOOR PNL 221BF DELAMINATED BY IB AFT LAV MOUNT. CLEANED AND PREPARED AREA FOR REPAIR AS PER B737-700 SRM 53-00 50 2R-7 VERIFIED. REPAIRD CABIN FLOOR PANEL 221BF AS PER B737-700 SRM 53-00-50-2R-7 MATERIAL USED PO#1711677 PO#1150387 PO#1713932 VERIFIED 3.

Part: WEB — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 294.5 TO STA 312 APPX. FOUND CORROSION ON WEB. REMOVED WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 294.5 TO STA 312 PER B737-700 SRM 51-40-02-0G-0. FOUND OUT OF LIMITS PER B737-700 SRM 53-10-15-1A-1. LOCATED AND DRILLED NEW WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 294.5 TO STA 312 PER B737-700 SRM 51-40-05-0G-0 AND DWG# 141A8131. TREATED AND PRIMED NEW DRILLED HOLES IAW SRM 51-20-01-0G-0. INSTALLED NEW WEB AT E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 294.5 TO STA 312 PER SRM 51-40-02-0G-0 AND DWG# 141A8131.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 294.5 TO STA 344 APPX. CORROSION NOTED ON OUTER CHORD (ANGLE). ; / [01] INSTALLED PROTECTION EWIS ON AREAS AT E/E COMPARTMENT LOWER AUX SILL S-23L FRONT STA 294.5 TO STA 344 AS PER REF B 737-700 AMM 20-60-07-913-801; [02] REMOVED EXFOLIATED OUTER CHORD ANGLE AT E&E COMPARTMENT LOWER AUXILIARY SILL AT S23L FROM STA 294.5 TO STA 344 APPX. IAW SRM 51-40-02-0G-0.; [03] (RII) VERIFIED STEPS #1 AND #2; [04] LOCATED AND DRILLED OUTER CHORD (ANGLE) AT E&E COMPARTMENT LOWER AUXILIARY SILL AT S23L FROM STA 294.5 TO STA 344 IAW B737-700 SRM 51-40-05-0G-0 AND DWG # 141A8240.

Part: WEB — CORRODED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

E&E COMPARTMENT LOWER AUXILIARY SILL; S-23L FROM STA 330.62 TO STA 344 APPX. FOUND CORROSION ON WEB. REMOVED WEB AT E/E COMPARTMENT LOWER AUXILIARY SILL IAW SRM 51-40-02-0G-0. FOUND OUT OF LIMITS IAW SRM 53-10-15-1A-1. LOCATED AND DRILLED NEW WEB AT E/E COMPARTMENT LOWER AUXILIARY SILL IAW SRM 51-40-05-0G-0 AND DWG 141A8131.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: CABIN FLOOR INTERCOSTAL BS 344-360 BL 0 CRACKED BY FWD SCREW HOLE. 8-54 ; / [01] INSTALLED EWIS PROTECTION DURING MAINTENANCE IN THE AREA OF WORK IN IAW AMM 20-60-07-913-801; [02] REMOVED INTERCOSTAL AT MAIN CABIN FROM BS 344 TO 360 BL 0 IN REF B737-700 SRM 51-40-02-0G-0; [03] LOCATED AND DRILLED NEW INTERCOSTAL AT CABIN FLOOR BS 344 TO 360 BL 0 IN IAW SRM 51-40-02-0G-0 P/N: 141A5410U23; [04] VERIFIED STEPS 1 ;2; AND 3 ;OK TO TREAT PRIME HOLES; [05] TREATED WITH ALODINE AND PRIMED ALL FASTENERS HOLES IN IAW SRM 51-20-01-0G-0 AND 51-21-72-370-804; [06] VERIFIED STEP 5 AND OK TO INSTALL NEW INTERCOSTAL; [07] INSTALLED NEW INTERCOSTAL AT CABIN FLOOR FROM BS 344 TO 360 BL-0 IN IAW SRM 51-40-02-0G-0 AND DWG # 141A5400; [08] REMOVED EWIS PROTECTION OF AREA IN REF IN IAW AMM 20-60-07-913-801; [09] REMOVED AND REPLACED INTERCOSTAL AT CABIN FLOOR FROM BS 344-360 BL 0 IN IAW SRM 51-40-02-0G-0 AND DWG# 141A5400; [10] RII VERIFIED STEPS 8 AND 9

Part: RIB — CRACKED (VERTICAL STAB) · airframe 69,290 hrs · 41,022 cycles

DORSAL FIN INTERNAL FWD (#1) RIB; CRACK NOTED. ; / [01] REMOVED RIB #1 AT INTERNAL FWD DORSAL FIN REF B737-700 SRM-51-40-02-0G-0.; [02] FABRICATED RIB #1 P/N 174A1108-1 MAT USED 2024-O 0.040 CLAD P/O# 1679582 REF DWG#174A1108.; [03] VERIFIED STEP #1 AND #2.; [04] OK TO HEAT TREAT FABRICATED PART (FORM OP84).; [05] HEAT TREATED NEW RIB P/N 174A1108-1 FROM 2024-O TO 2024-T42 REF BAC5602 AND AAR FORM OP 84 REV7.; [06] (RII) VERIFIED ALUMINUM HEAT TREATMENT; RES 2017978-23; ATTACHED FORMS OP84; OP63 WITH PARTS CONTROL #410649.; [07] LOCATED AND DRILLED FABRICATED FWD RIB (#1) AT DORSAL FIN INTERNAL AS PER B 737-700 SRM 51-40-05-0G-0; [08] (RII) VERIFIED STEP #7; [09] (RII) OK TO TREAT AND PRIME FABRICATED RIB.; [10] TREATED AND PRIMED FABRICATED RIB (#1) AT DORSAL FIN INTERNAL AS PER B 737-700 SRM 51-20-01-0G-0; [11] VERIFIED STEP 10.; [12] OK TO INSTALL PART.; [13] INSTALLED FABRICATED FWD RIB (#1) AT DORSAL FIN INTERNAL ASPER B737-700 SRM 51-40-02-0G-0 DWG #174A1008; [14] REMOVED AND REPLACED FWD RIB (#1) AT DORSAL FIN INTERNAL ASPER B737-700 SRM 51-40-02-0G-0; [15] VERIFIED STEPS 13 AND 14

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: CABIN FLOOR INTERCOSTAL HAS CRACK AT SCREW HOLE LBL 45 BS 322. 8-42 ; / [01] REMOVED CABIN FLOOR INTERCOSTAL AT LBL 45 BS 322. AS PER B737 SRM 51-40-02-0G-0; [02] RECEIVE NEW INTERCOSTAL AND LOCATED AND DRILLED AS PER B737 SRM 51-40-05-0G-0; [03] VERIFIED 1-2. OK TO INSTALL NEW INTERCOSTAL.; [04] CABIN FLOOR INTERCOSTAL INSTALLED NEW AT LBL 45 BS 322. AS PER B737 SRM 51-40-02-0G-0 AND DRW 141A5400; [05] VERIFIED 4.

Part: FLOOR PANEL — BROKEN (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: CABIN FLOOR PNL 222CF HAS CORNER BROKEN. 8-52 ; / [01] CLEANED AND PREPARED AREA FORD RIPAIRED FIBERGLAS AS PER B737- 700 SRM 53-00-50-2R-9; [02] TO CORRECTING ON STEP # 1 (AREA FOR REPAIR ); [03] VERIFIED STEP 1 AND 2. OK TO INSTALL REPAIR.; [04] REPAIRED CABIN FLOOR PANEL 222 CF AS PER B737-700 SRM 53-00-50-2R-9 MATERIAL USED PO#1715777 PO#1150387; [05] VERIFIED STEP 4.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: FWD WET AREA FLOOR INTERCOSTAL CRACKED AT SCREW HOLE BS 284 BL O. 8-44 ; / [01] REMOVED FWD WET AREA FLOOR INTERCOSTAL AT BS 284 BL 0. AS PER B737 SRM 51-40-02-0G-0; [02] LOCATED AND DRILLED NEW INTERCOSTAL AT BS 284 BL 0 AS PER B737-700 SRM 51-40-05-0G-0; [03] VERIFIED STEP 1 & 2 OK TO TREAT AND PRIME; [04] INSTALLED NEW INTERCOSTAL AT BS 284 BL 0 AS PER B737-700 SRM 51-40-02-0G-0 DWG #141A5410-3; [05] REMOVED AND REPLACED INTERCOSTAL AT BS 284 BL 0 AS PER B737-700 SRM 51-40-02-0G-0 DWG #141A5410-3; [06] LATE ENTRY ; OK TO INSTALL NEW INTERCOSTAL RII; [07] LATE ENTRY; TREATED AND PRIMED NEW INTERCOSTAL AT BS 284 BL 0 AS PER B737-700 SRM 51-20-01-0G-0; [08] RII VERIFIED STEPS 4 AND 5; [09] VERIFIED STEPS 6 & 7

Part: NONE — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: CABIN FLOOR INTERCOSTAL BS 380-400 BL 0 HAS CRACK AT MID SCREW HOLE. 8-58 ; / [01] REMOVED CABIN FLOOR INTERCOSTAL ANGLE AT BS 380-400 BL 0 AS PER B737-700 SRM 51-40-02-0G-0; [02] LOCATED AND DRILLED NEW INTERCOSTAL ANGLE AT BS 380-400 BL 0 AS PER B737-700 SRM 51-40-05-0G-0; [03] VERIFIED STEPS 1 & 2 AND OK TO INSTALL NEW INTERCOSTAL; [04] INSTALLED NEW INTERCOSTAL ANGLE AT BS 380-400 BL 0 AS PER B737-700 SRM 51-40-02-0G-02 DWG #143A5400; [05] REMOVED AND REPLACED INTERCOSTAL ANGLE AT BS 380-400 BL 0 AS PER B737-700 SRM 51-40-02-0G-0; [06] RI I VERIFIED STEPS 4 AND 5

Part: NONE — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: CABIN FLOOR INTERCOSTAL BS 380-400 RBL 10 HAS CRACK AT AFT SCREW HOLE. 8-57 ; / [01] REMOVED INTERCOSTAL AT FWD CABIN BS 380-400 RBL 10 AS PER B737-700 SRM 51-40-02-0G-0; [02] LOCATED AND DRILLED NEW INTERCOSTAL AT FWD CABIN BS 380 -400 RBL 10 AS PER B737-700 SRM 51-40-05-0G-0; [03] VERIFIED STEPS 1 AND 2; [04] OK TO TREAT AND PRIME DRILLED HOLES; [05] OK TO INSTALL NEW ANGLE; [06] TREATED AND PRIMED DRILLED HOLES AT INTERCOASTAL ANGLE ; FWD CABIN BS 380-400 RBL 10 AS PER B737-700 SRM 51-20-01-0G-0; [07] INSTALLED NEW INTERCOSTAL ANGLE AT FWD CABIN BS 380-400 RBL 10 AS PER B737-700 SRM 51-40-02-0G-0 DWG # 143A5400; [08] REMOVED AND REPLACED INTERCOSTAL ANGLE AT FWD CABIN BS 380-400 RBL 10 AS PER B737-700 SRM 51-40-02-0G-0; [09] RII VERIFIED STEPS 7 AND 8; [10] VERIFIED STEP 6

Part: STUB FRAME — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

R1 DOOR FWD UPPER STOP FRAME CRACKED ; R1 DOOR CUT OUT FWD UPPER STUB FRAME CRACKED. / [01] REMOVED UPPER STUB FRAME AT R1 DOOR AS PER SRM 51-40-02-0G-0; [02] LOCATED AND DRILL HOLE NEW STUB FRAME AS PER SRM 51-40-05-0G-0; [03] VERIFIED 1-2. OK TO TREAT; PRIME AND PAINT.; [04] TREATED PRIMER AND PAINTED STUB FRAME AS PER SRM 51-20-01 0G-0 AMM 51-21-72-370-804 AND 51-51-73; [05] VERIFIED 4. OK TO INSTALL NEW STUB FRAME.; [06] INSTALLED NEW STUB FRAME AS PER DWG N0. 141A8370; [07] VERIFIED STEP # 6

Part: BEAR STRAP — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

R1 BEAR STRAP CRACK CONTINUES FROM 2ND UPPER AFT FASTENER TO THE EDGE APROX. 0.500'. / [01] PERMANENT REPAIR OF DAMAGE FOUND AT R1 DOOR CUT OUT BEAR STRAP 2ND UPPER AFT FASTENER WAS ACCOMPLISHED ON FAULT TTG8Q0094F9V; [02] VERIFIED 1; [03] PERFORMED EA 21-153-03281.

Part: BEAR STRAP — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

R1 BEAR STRAP HAS CRACK EMINATING FWD FROM 2ND UPPER AFT FASTENER 0.394' LENGTH. CUT DAMAGED AREA AT BEARSTRAP R1 DOOR AS PER SRM 53-10-01-2R 6 REPAIR 6; PERFORMED HFEC INSP ON CUT OUT AREA. IAW NDT PART 6 51-00-00 PROCE 23. PERFORMED HFEC ROTOR INSP ON FASTENERS OPEN HOLES. IAW NDT PART 6 51-00-00 PROCE 16. NO CRACKS FOUND. PERFORMED HFEC COUNTERSUNK INSP IAW NDT PART 6 53-30-00 PROCE 3. NO CRACKS FOUND. .040 IN INSURANCE CUT ALONG ALONG EDGE OF TRIM IAW SRM 53-10-01-2R-6 REPAIR 6; ACCOMPLISHED DETAILED INSPECTION STRUCTURE REPAIR AREA NO DEFECT NOTED. FABRICATED REPAIR PARTS & FILLER IAW SRM 53-10-01-2R-6 REPAIR 6. ACCOMPLISHED REPAIR OF CRACK IAW EA 21-153-03281.

Part: SKIN — DELAMINATED (NR 1 NACELLE TE) · airframe 69,290 hrs · 41,022 cycles

#1 ENGINE IB THRUST REV MID TRAILING EDGE AREA DELAMINATED. 8-25 ; / [01] CUT OUT THE DAMAGED SKING A CIRCULAR SHAPE; NO CORE DAMAGED AT #1 ENG IB TRUST REVERSER MID TRAILING EDGE. REF B737-700 SRM 54-30-01-2R-1 PARAGRAPH 4 C (2). PREPARED AREA TO APPLY DRY OUT AT REPAIR AREA. REF B737-700 SRM 51-70-04-2R-6 PARAGRAPH 4 C.; [02] VERIFIED STEP 1 AND OK TO APPLY DRY OUT AT REPAIR AREA; [03] PREPARED THE DAMAGED AREA TO APPLY THE FABRIC REPAIR PLIES . REF B737-700 SRM 51-70-04-2R-6 PARAGRAPH 4 D.; [04] APPLIED DRY OUT AT REPAIR AREA. REF B737-700 SRM 51-70-04-2R-6 PARAGRAPH 4 C.; [05] VERIFIED 3-4. OK TO INSTALL REPAIR.; [06] APPLIED THE FABRIC REPAIR PLIES AT DAMAGED AREA . REF B737-700 SRM54-30-01-2R-1 AND SRM 51-70-04-2R-6 PARAGRAPH 4 E; FAND G. PERFORMED VISUAL INSPECTION AND TAP TEST INSPECTION ARROUND THE REPAIR AREA NO DELALAMINATION FOUND REF B737-700 NDT PART 1 51-05-01 PARAGRAPH 5 TAP TEST TOOL ST 8842.; [07] VERIFIED STEP 6; [08] OK TO APPLY FINISH; [09] APPLIED FINISH AT REPAIR AREA ON #1 ENG IB TRUST REVERSER MID TRAILING EDGE. REF B737-700 SRM 51-70-04-2R-6 PARAGRAPH 4 P.; [10] VERIFIED STEP 9

Part: SKIN — CRACKED (RT NR 7 SLAT) · airframe 69,290 hrs · 41,022 cycles

#7 SLAT THE LOWER SURFACE OF THE WING LEADING EDGE SLAT NOSE SKIN AT THE ACTUATOR RIBS APPEARS TO BE CRACKED ON THE SKIN AROUND 3RD OB FASTENER THAT ATTACH THE ACTUATOR FITTING AT SLAT STATION 322.71. ; DOT 8-32 / [01] REMOVED ACCESS PANEL 624 DR. AND 1EA. FASTENER FOR NDT. INSPECTION AT R/W. #7 SLAT L/E. NOSE SKIN THAT ATTACH THE ACTUATOR FITTING AT SLAT SAT.322.71. IAW. B-737-700 SRM. 51-40-02-0G-0; [02] PERFORMED HFEC ROTOR INSP ON FASTENER OPEN HOLE. IAW B 737 NDT PART 6 51-00-00 PROCE 16. TOOL NORTEC 600. BC 172389. 7-2-22. NO CRACKS FOUND.; [03] PERFORMED HFEC COUNTERSINK INSP ON FASTENER OPEN HOLE. IAW B 737 NDT PART 6 53-30-00 PROCE 4. TOOL NORTEC 600. BC 172389. CALIB DUE 7-2-22. CRACK INDICATION FOUND.; [04] VERIFIED 1.; [05] REMOVED ACCESS PANEL#624EB; 624CB; AND FLEX PANEL AT R/W. SLAT #7 IAW. B-737-700 SRM. 51-40-02-0G-0; [06] CUT-OUT DAMAGE AREA IAW. B-737-700 SRM. 57-42-01-2R-8 FIGURE 202 PAGE 7; [07] PERFORMED HFEC INSP ON CUTOUT AREA. IAW B 737 NDT PART 6 51-00-00 PROCE 23. TOOL NORTEC 600. BC 166316. CALIB DUE 10-8-22. NO CRACKS FOUND.; [08] PERFORMED HFEC ROTOR INSP ON FASTENERS OPEN HOLES NEAR TO CUTOUT AREA. IAW B 737 NDT PART 6 51-00-00 PROCE 16. TOOL NORTEC 600. BC 166316. NO CRACKS FOUND.; [09] PERFORMED HFEC COUNTERSINK INSP ON FASTENERS OPEN HOLES NEAR TO CUTOUT AREA. IAW B 737 NDT PART 6 53-30-00 PROCE 3. TOOL NORTEC 600. BC 166316. NO CRACKS FOUND.; [10] FABRICATED REPAIR PART IAW. B-737-700 SRM.57-42-01-2R-8 FIGURE 202;

Part: SKIN — CRACKED (LT NR 1 SLAT) · airframe 69,290 hrs · 41,022 cycles

LT WING #1 SLAT HAS LWR SKIN CRACKED AT 3 EACH FASTENERS THAT ATTACH THE ACTUATOR FITTING AT SLAT STATION 451.97. 3-23 ; / [01] REMOVED 3EA. FASTENERS FOR NDT. INSPECTION IAW. B-737-700 SRM. 51-40-02-0G-0; [02] VERIFIED STEP 1; [03] PERFORMED HFEC INSP. ON SKIN AROUND 3EA. EXISTING FASTENER HOLES IAW B737 NDT PART 6; 51-00-00; PROCEDURE 23. CRACK CONFIRMED <BR>TOOL: NORTEC 600 B/C: 166316 DUE: 10/08/22; [04] PERFORMED HFEC ROTO INSP. OF 3EA EXISTING FASTENER HOLES IAW B737 NDT PART 6; 51-00-00; PROCEDURE 16. CRACKS NOTED <BR>TOOL: NORTEC 600 B/C: 166316 DUE: 10/08/22<BR>TOOL: OLYMPUS MINIMITE B/C: 172542 DUE: 08/20/2022; [05] PERFORMED HFEC ROTO COUNTER INSP. OF 3EA EXISTING FASTENER HOLES IAW B737 NDT PART 6; 53-30-00; PROCEDURE 3. CRACKS NOTED <BR>TOOL: NORTEC 600 B/C: 166316 DUE: 10/08/22<BR>TOOL: OLYMPUS MINIMITE B/C: 172542 DUE: 08/20/2022; [06] REMOVED L//W. PANELS #525EB; 525CB; 525DAB; 525DBB AND FLEXIBLE PANEL FOR ACCESS TO REPAIR IAW. B-737-700 SRM.51-40-02-0G-0; [07] CUT-OUT DAMAGE AREA AT L/W. #1 SLAT LWD. SKIN IAW. B-737-700-SRM. 57-42-01-2R-8 FIGURE202;[10] PERFORMED HFEC ROTO INSP. OF ALL INITIAL EXISTING FASTENER HOLES IN THE REPAIR AREA IAW B737 NDT PART 6; 51-00-00; PROCEDURE 16. CRACKS NOTED <BR>TOOL: NORTEC 600 B/C: 166316 DUE: 10/08/22 <BR>TOOL: OLYMPUS MINIMITE B/C: 172542 DUE: 08/20/2022; [11] FABRICATED REPAIR PART IAW. B-737-700 SRM. 57-42-01-2R-8 FIGURE 202;

Part: VAPOR BARRIER — CRACKED (CENTER WING) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: RH SIDE STA 663 VAPOR BARRIER HAS A CRACK . ; / [01] STOP DRILL AT THE END CRACK AT VAPOR BARRIER ON STA 663 PER B737 SRM 57-10-10-2R PARAGRAPH 6.B PERFORMED VISUAL INSPECTION AND TAP TEST FOUND CRACK SIZE 12''PER B737 NTM 51-05-01; [02] PREPARED DAMAGE AREA AT VAPOR BARRIER TO APPLY DRY-OUT PROCESS PER B737SRM 51-70-04- PARAGRAPH 4.D; [03] VERIFIED 1-2. OK TO DRY OUT.; [04] MEASUREMENT; [05] ACCOMPLISHED DRY OUT PROCESS AT RH SIDE STA 663 VAPOR BARRIER; 24 HOUR AT 180 F; AS PER B737 SRM 51-70-04-2R-0 PARAGRAPH 4.D.; [06] VERIFIED STEP #5; [07] OK TO REPAIR DAMAGE AREA.; [08] REPAIRED DAMAGED AREA AT R/H SIDE VAPOR BARRIER ON STA 663 AND PERFORMED TAP TEST ON REPAIRED AREA PER B737 SRM 51-70-04-2R-10 AND B737 NTM 51-05-01. MATERIALS USED RESIN P/O#1731939 AND FIBERGLASS P/O#1694548; [09] VERIFIED 4; 8. OK TO PAINT.; [10] PAINTED ON R/H SIDE STA 663 VAPOR BARRIER AS PER B 737-700 AMM 51-21-73-370-803; [11] VERIFIED 10.

Part: NONE — CRACKED (FUSELAGE) · airframe 69,290 hrs · 41,022 cycles

SUPPLEMENTAL INFORMATION: CRACK FOUND ON HORIZONTAL PRESSURE DECK WEB LBL 34 AT STA 663. LENGTH OF CRACK :0.394' ; CRACK FOND ON HORIZONTAL PRESSRE DECK WE LBL 34 AT STA 663. LENGTH OF CRACK :0.394' / [01] REMOVED FASTENERS AT L/H SIDE HORIZONTAL PRESSURE DECK WEB BETWEEN STA 663.75 AND STA 675 FROM LBL 30 TO LBL 60 REF B737-700 SRM 51-40-02-0G-0.;[22] ACCOMPLISHED PERMANENTED REPAIR AT MAIN CABIN L/H SIDE PRESSURE DECK WEB BETWEEN STA 663.75 AND STA 675 FROM LBL 30 TO LBL 60 REF B737-700 SRM 53-40-51-2R-2 FIG 203 TABLE 202.; [23] VERIFIED STEP 19; 21 AND 22; [24] JOB IS COMPLETE

Part: VAPOR BARRIER — CRACKED (WHEEL WELL) · airframe 68,019 hrs · 40,207 cycles

RIGHT WHEEL WELL VAPOR BARRIER HAS 10 INCH CRACK FROM OUTBOARD CORNER OF HEAT EXCHANGER EXHAUST TOWARDS UPPER RIGHT CORNER / TRANSFERRED TO NR # D184474

Part: FILTER — LEAKING (HYD SYSTEM) · airframe 67,762 hrs · 40,059 cycles

LOSS OF SYSTEM A HYD. R & R THE A SYSTEM ACOUSTIC FILTER TO HYDRAULIC MODULE LINE AND CASE DRAIN FILTER PER AMM. DECLARED EMERGENCY.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 66,960 hrs · 39,541 cycles

LT BULL NOSE EMERGENCY EXIT LIGHT INOP AT ROW 23. R&R LAMP IAW AMM.

Part: TRUNNION — CORRODED (RT MLG) · airframe 66,599 hrs · 39,303 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER OUTBOARD LUG OUTER FACE HAD CORRODED. REPAIRED LUG FACE PER EA.

Part: TRUNNION — CORRODED (RT WING) · airframe 66,599 hrs · 39,303 cycles

R/H MAIN LANDING GEAR. FORWARD TRUNNION FITTING UPPER INBOARD LUG OUTER FACE HAD CORRODED. / REPAIRED LUG FACE PER EA.

Part: TRUNNION — CORRODED (LT MLG) · airframe 66,599 hrs · 39,303 cycles

LEFT MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER OUTBOARD LUG INNER FACE HAD CORRODED. REPAIRED LUG FACE PER SRM.

Part: TRUNNION — CORRODED (LT MLG) · airframe 66,599 hrs · 39,303 cycles

LEFT MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER INBOARD LUG INNER FACE HAD CORRODED. REPAIRED LUG FACE PER SRM.

Part: TRUNNION — CORRODED (RT MLG) · airframe 66,599 hrs · 39,303 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG OUTER FACE HAD CORRODED. / REPAIRED LUG FACE PER EA.

Part: TRUNNION — CORRODED (LT MLG) · airframe 66,599 hrs · 39,303 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER OUTBOARD LUG OUTER FACE CORRODED. REPAIRED LUG FACE PER EA.

Part: TRUNNION — CORRODED (LT MLG) · airframe 66,599 hrs · 39,303 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING UPPER INBOARD LUG OUTER FACE CORRODED. REPAIRED LUG FACE PER EA.

Part: TRUNNION — CORRODED (RT MLG) · airframe 66,599 hrs · 39,303 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER INBOARD LUG OUTER FACE HAD CORRODED. REPAIRED LUG FACE PER EA.

Part: TRUNNION — CORRODED (LT MLG) · airframe 66,599 hrs · 39,303 cycles

LT MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG OUTER FACE HAD CORRODED. REPAIRED LUG FACE PER EA.

Part: TRUNNION — CORRODED (RT MLG) · airframe 66,599 hrs · 39,303 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG INNER FACE HAD CORRODED. REPAIRED LUG FACE PER SRM.

Part: TRUNNION — CORRODED (RT MLG) · airframe 66,599 hrs · 39,303 cycles

R/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER INBOARD LUG INNER FACE HAD CORRODED. / REPAIRED LUG FACE PER SRM.

Part: TRUNNION — CORRODED (LT MLG) · airframe 66,599 hrs · 39,303 cycles

LEFT MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER OUTBOARD LUG INNER FACE HAD CORRODED. REPAIRED LUG FACE PER SRM.

Part: TRUNNION — CORRODED (LT MLG) · airframe 66,599 hrs · 39,303 cycles

L/H MAIN LANDING GEAR FORWARD TRUNNION FITTING LOWER INBOARD LUG INNER FACE HAD CORRODED. REPAIRED LUG FACE PER SRM.

Part: TRUNNION — CORRODED (LT MLG) · airframe 66,599 hrs · 39,303 cycles

LT MAIN LANDING GEAR TRUNNION FITTING LOWER INBOARD LUG OUTER FACE HAD CORRODED. REPAIRED LUG FACE PER EA.

Part: DOOR — CRACKED (RT MLG) · airframe 66,599 hrs · 39,303 cycles

RH MAIN LANDING GEAR MIDDLE STRUT GEAR DOOR CRACKED ABOVE FORWARD HINGE ASSEMBLY. / R&R DOOR PER MM.

Part: LENS — UNSECURE (CABIN) · airframe 65,612 hrs · 38,708 cycles

RT EMERGENCY EXIT LIGHT LENS FELL OFF. R&R LENS IAW SIP.

Part: FLAP — DELAMINATED (RT WING) · airframe 65,541 hrs · 38,657 cycles

RT OUTBOARD TRAILING EDGE FLAP INBOARD, UPPER EDGE DELAMINATED. R&R AFT FLAP PER AMM.

Part: RIB — CRACKED (TE FLAP) · airframe 65,541 hrs · 38,657 cycles

LT FLAP DEFLECTION RIB TAB CRACKED. R&R LT FLAP DEFLECTION RIB PER SRM.

Part: LENS — CRACKED (EXIT SIGN) · airframe 64,829 hrs · 38,168 cycles

R2 DOOR EXIT SIGN CRACKED. R&R LENS PER AMM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 63,326 hrs · 37,217 cycles

RT OVERHEAD BIN EMERGENCY AISLE LIGHT INOP AT ROW 6. RELAMPED LIGHT IAW AMM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 63,326 hrs · 37,217 cycles

R2 DOOR HEADER PANEL EMERGENCY EXIT LIGHT INOP. R&R LIGHT HOUSING ASSEMBLY IAW AMM AND WDM.

Part: CAP SEAL — CRACKED (AFT CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO PIT L/H AFT CAPSTRIP AT PANEL 140AF IS BROKEN / VERIFIED NEW CAP STRIP P/N 453A2611-6 PER 737 AIPC 25-52-10-02 INSTALLED NEW CAP STRIP IAW B 737 AMM 25-52-10-400-801

Part: FLOOR SPLICE — CRACKED (AFT CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO PIT FLOOR SPLICE AT STA 767 CRACKED / REPLACED AFT CARGO FLOOR SPLICE AT STA 767 VERIFIED PART AS 146A9401-4 IAW BOEING DWG 146A7500 REV C APPLIED CIC TO FLOOR SPLICE IAW AMM 51-21-91-620-802 (PART NOT INSTALLED)

Part: FLOOR PANEL — CORRODED (AFT CARGO) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO FLOOR PANEL SPLICE AT STA 727D+5' IS CORRODED / REPLACED FLOOR SPLICE AT STA 727D + 5 AFT CARGO PN 146A9401-8 IAW AIPC 53-42-11-30 ATAG WN8722

Part: FLOOR PANEL — BROKEN (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FWD WET AREA FLOOR PANEL 221GF HAS BROKEN EDGE / EVALUATED BROKEN EDGE DAMAGE ON FWD WET AREA FLOOR PANEL (221 GF) & FOUND DAMAGE WAS THROUGH (1) FACESHEET WITH NO CORE DAMAGE. REPAIR BOARD WITH WET-LAY-UP WITHIN LIMIS OF (REPAIR 1) I/A/W B737 - SRM 53-00-50-2R-1

Part: FITTING — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

BAFFLE CLIP CRACKED AT BS 500, STR 26L. R&R BAFFLE CLIP IAW DWG AND SRM.

Part: TRACK — CRACKED (FLIGHT DECK FLOO) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: FLIGHT DECK; FWD INBOARD SEAT TRACK IS CRACKED AT HOLE FOR FWD STOP LUG. FOR CAPTAINS SEAT / REMOVED AND REPLACED FLIGHT DECK; FWD INBOARD SEAT TRACK OF THE CAPTAIN SEAT IAW AMM 25-11-11-400-801 STEP D (1)-(8) ATAG WN3811

Part: FLOOR PANEL — CRUSHED (CABIN) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: PASSENGER CABIN FLOOR PANEL 242DF FWD EDGE HAS AN AREA CRUSHED / REPAIRED CRUSHED AREA ON FWD EDGE OF CABIN FLOOR PANEL 242DL PER B737 53-00-50-2R-4

Part: SHEAR WEB — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

SHEAR WEB CRACKED BETWEEN BS 986 TO BS 1006, RBL 40. R&R SHEAR WEB IAW DWG AND SRM.

Part: BEAM — CRACKED (R1 DOOR) · airframe 63,326 hrs · 37,217 cycles

R1 DOOR NR 4 DOOR BEAM CRACKED AT MOST INBOARD BEAM ATTACH BOLT HOLE. R&R BEAM IAW DWG & SRM.

Part: FAIRING — CRACKED (RIGHT WING) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: RIGHT WING AFT FLAP TRACK FAIRING 644BB; BOTTOM L/E IS GOUGED/CRACKED. / REPAIRED AND APPLIED DECORATIVE FINISH ON RIGHT WING AFT FLAP TRACK FAIRING 644BB BOTTOM L/E IAW B737 RM 57-53-70-1A-1 REV 64 FIG 106 SHEET 3 DETAIL E AND B737 AMM 51-21-99-300-801 TABLE 701. A22570

Part: FITTING — CRACKED (AFT CARGO COMPT) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: AFT CARGO PIT ATTACH FITTING AT STA 947 LBL 10 AT FLOOR LINE CRACKED / IN AFT CARGO AT STA 947; LBL10 FLOOR LINE REMOVED AND REPLACED CRACKED FITTING MPN 149A8113-6 IAW DWG 149A8103 REV- AND B737-700 SRM 51-40-02-0G-0 STEP 7 AND SRM 51-40-05-0G-0. APPLIED CIC IAW B737-700 AMM 51-21-91-620-802. TAG A66472

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

LT OUTBOARD SEAT TRACK CORRODED BETWEEN BS 580 TO BS 663. REPAIRED SEAT TRACK IAW SRM.

Part: PLATE — CORRODED (AFT CARGO COMPT) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: AFT PIT TIEDOWN PLATE IS CORRODED / REPLACED CORRODED TIE DOWN PLATE IN AFT PIT W/H NEW PLATE P/N 453A2611-2 ATAG #A35905 I/A/W BOEING DWG 453A2600 SHEET 27 REV D. TIE DOWN PLATE HAS NO PUBLISHED LIMITS IN THE SRM.

Part: FLOOR PANEL — CORRODED (AFT CARGO COMPT) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: AFT PIT PANEL 140 CF IS CORRODED / VERIFIED FLOOR BOARD PANEL 140 CF 100% OUT OF LIMITS IAW B737-700 SRM 53-00-53-1A-1. VERFIED NEW PANEL 140CF PART #7252490 IAW B737-700 AIPC 25-52-10-5 DWG # 453A2610 REV D. A-TAG: WN1034

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

LT INBOARD SEAT TRACK CORRODED BETWEEN BS 540 TO BS 580. R&R SEAT TRACK IAW SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FRAME CRACKED AT BS 294, STR 17R. R&R FRAME IAW SRM AND DWG.

Part: BRACKET — CRACKED (RIGHT WING) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: RIGHT WING T/E PANEL 651GB; SEAL SUPPORT BRACKET IS WORN/CRACKED AT O/B END. / REMOVED DAMAGED SEAL SUPPORT BRACKET AT R/H WING T/E PNL 651GB I.A.W SRM 51-40-02-0G-00. INSTALLED NEW SEAL SUPPORT BRACKET I.A.W. SRM 51-40-02-0G-00 AND BOEING DWG 115A2714

Part: NONE — CORRODED (FWD CARGO COMPT) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: FWD PIT CAPSTRIPS ARE BENT AND HAVE LIGHT CORROSION 4 EA / THERE ARE NO LIMITS IN SRM ALL 4 FWD PIT CAP STRIPS WERE REPLACED WITH NEW IAW BOEING DWG 453A1600 P/N'S 453A1611-12 453A1611-11 453A1611-10 AND 453A1611-5

Part: NONE — CRACKED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: FWD CARGO PIT STA 500C LBL 23 BAFFLE CLIP CRACKED ON AFT SIDE / REMOVED AND REPLACED BAFFLE CLIP IN FWD CARGO PIT STA 500C; LBL 23 IAW SRM 51-40-02; 51-40-05; AND DWG 143A7505 REV A ARAG A66464

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FLOOR STRUCTURE INTERCOSTAL CRACKED BETWEEN BS 328 TO BS 344, LBL 46. R&R INTERCOSTAL IAW SRM AND DWG.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: PASSENGER CABIN AFT WET AREA FLOOR BOARD 241ABF AFT OTBD CORNER HAS MULTIPLE INSERTS PULLED THROUGH CAUSING THE FLOOR BOARD TO DELAM / REPAIRED PNL 241ABF AFT OTBD CORNER MULTIPLE PULLED INSERTS AND DAMAGE INSERT HOLES; AND INSTALLED NEW INSERTS IAW B737-700 SRM 53-0050-2R-1 REV 64 SRM 53-00-50-2R-0 REV 64 (INSERTS 9EA) INSTALL BOARD 241ABF AFTER 3AM ON 25MAY18 A17133; A06044; A86613; A49522; A59144; A80188

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FLOOR STRUCTURE INTERCOSTAL CRACKED BETWEEN BS 312 TO BS 328, LBL 46. R&R INTERCOSTAL IAW SRM AND DWG.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FLOOR SUPPORT CORRODED AT BS 270, BETWEEN LBL 35 TO LBL 53. REPAIRED INTERCOSTAL IAW SRM AND EA.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FLIGHT DECK FLOOR CORRODED BETWEEN BS 261 TO BS 270, BETWEEN LBL 37 TO LBL 53. R&R SHEAR TIE IAW SRM.

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

CREASE BEAM INNER CHORD CORRODED AT BS 270, LBL 48. R&R CREASE BEAM IAW DWG.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FLOOR STRUCTURE INTERCOSTAL CRACKED BETWEEN BS 277 TO BS 294.5, RBL 1. R&R INTERCOSTAL IAW SRM AND DWG.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: PASSENGER CABIN AFT WET AREA FLOOR BOARD 242UF IS PUNCTURED AND DELAMED / REPAIRED AND REPLACED 1 EA INSERT ON PASSENGER CABIN AFT WET AREA FLOOR BOARD 242UF AT 16' AFT OF FWD EDGE AND 12' FROM O/B EDGE IAW B737 SRM 53-00-50-2R-3 AND B737 SRM 53-00-50-2R-0. A94393 A49522 A59144 A06044 A17133 A86613

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: PASSENGER CABIN AFT WET AREA FLOOR BOARD 241AAF AFT INSERT IS PULLED THROUGH CAUSING THE FLOORBOARD TO DELAMED / REPAIRED PASSENGER CABIN AFT WET AREA FLOORBOARD 241AAF AT AFT INSERT HOLE I/A/W 737-700 SRM 53-00-50-2R-4 REV 64; SRM 53-00-50-2R-0 REV 64.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

T-CAP CORRODED AT BS 986, BETWEEN RBL 5 TO RBL 38. R&R T CHORD IAW SRM.

Part: SUPPORT BRACKET — CORRODED (MAIN CABIN) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: PASSENGER ENTRY DOOR CUTOUT (L1); I/B THRESHOLD SUPPORT BRACKET IS CORRODED STA 315-344. / REMOVED L 1 I/B THRESHOLD SUPPORT DUE TO DAMAGE THAT WAS OUT OF LIMITS IAW BOEING SRM 53-10-15-1A-1 ALLOWABLE DAMAGE 1 INSTALLED NEW THRESHOLD SUPPORT IAW BOEING DWG 141A8110 ID 0008 REV A

Part: SUPPORT BRACKET — CORRODED (MAIN CABIN) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: PASSENGER ENTRY DOOR CUTOUT (L1); O/B THRESHOLD SUPPORT BRACKET IS CORRODED STA 315-344. / REMOVED L 1 O/B THRESHOLD SUPPORT DUE TO DAMAGE THAT WAS OUT OF LIMITS IAW BOEING SRM 737-700 53-10-15-1A-1 ALLOWABLE DAMAGE 1 INSTALLED SUPPORT IAW BOEING DWG 141A8110 ID 0008 REV A

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FLOOR STRUCTURE CREASE BEAM INNER CHORD CORRODED BETWEEN BS 312 TO BS 350, LBL 58. R&R CREASE BEAM IAW DWG.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

INTERCOSTAL CRACKED BETWEEN BS 344 TO BS 360, RBL 11. R&R INTERCOSTAL IAW SRM & DWG.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FLOORBEAM UPPER FLANGE CORRODED AT BS 328, RBL 46. R&R FLOORBEAM IAW SRM.

Part: SIGN — BROKEN (CABIN) · airframe 63,326 hrs · 37,217 cycles

CENTER CABIN EMERGENCY EXIT SIGN FRAME BROKEN. R&R SIGN IAW AMM.

Part: ACCESS PANEL — DELAMINATED (LT WING) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: LEFT WING ACCESS PANEL 521WB FWD I/B CORNER IS DELAMINATED. / REPAIRED DELAMINATION TO EROSION STRIP AT FWD I/B CORNER OF LEFT WING ACCESS PANEL 521 WB PER B737 SR; 57-41-01-2R-6

Part: CREASE BEAM — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

L2 CREASE BEAM CORRODED. R&R CREASE BEAM IAW SRM & DWG.

Part: ACCESS PANEL — DELAMINATED (LT WING) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: LEFT WING ACCESS PANEL 521DB IS DELAMINATED AT FWD EDGE. / REPAIRED DELAMINATED TO EROSSION STRIP AT FWD EDGE OF LEFT WING ACCESS PANEL 521 DB PER B737 SRM 57-41-01-2R-6

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FLOOR STRUCTURE INTERCOSTAL CRACKED BETWEEN BS 312 TO BS 328, RBL 31. R&R INTERCOSTAL IAW DWG & SRM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

LT AIR CONDITION BAY AFT WALL KEEL BEAM WEB, VAPOR BARRIER UPPER ANGLE CRACKED AT BS 663, LBL 8.6. R&R ANGLE IAW EA.

Part: ANGLE — CRACKED (LT WING) · airframe 63,326 hrs · 37,217 cycles

LT WING TRAILING EDGE, VERTICAL STIFFENER INTERCOSTAL, OUTBOARD ATTACH ANGLE, COMMON TO INBOARD DEFLECTOR RIB CRACKED. R&R ANGLE IAW DWG.

Part: BAFFLE — CRACKED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

FWD CARGO COMPARTMENT STA 500B AT STR. 26L BAFFLE CLIP CRACKED / REMOVED AND REPLACED BAFFLE CLIP STA 500B 26L IAW B737-700 SRM 51-40-02-0-0G DWG 143A7505 REV:G

Part: BAFFLE — CRACKED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

FWD CARGO COMPARTMENT STA 500C AT STR. 26L BAFFLE CLIP CRACKED. / REMOVED AND REPLACED BAFFLE CLIP STA 500C 26L IAW B737-700 SRM 51-40-02-0-0G DWG 14A7505 REV:G

Part: GUSSET — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

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

Part: CHANNEL — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 767+6, RBL 8. REPAIRED V CHANNEL IAW SRM AND EA.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 767+6, LBL 12. REPAIRED STRUCTURE IAW SRM.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 767+6, LBL 3. REPAIRED SUPPORT IAW SRM AND EA.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR ANGLE AT AFT BULKHEAD CORRODED AT BS 947, BETWEEN STR 25L TO STR 25R. R&R ANGLE IAW DWG AND SRM.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 727D+6, RBL 3. REPAIRED STRUCTURE IAW SRM & EA.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 767+6, LBL 8. REPAIRED STRUCTURE IAW SRM AND EA.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT PIT RT Z- ANGLE CORRODED BETWEEN BS 727 TO BS 727D. R&R Z ANGLE IAW SRM.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

RT AIR CONDITION BAY AFT WALL KEEL BEAM WEB VAPOR BARRIER STIFFENER ANGLE CRACKED AT BS 663. R&R ANGLE IAW SRM & DWG.

Part: FRAME — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FRAME CORRODED AT BS 947, LBL 10. R&R FRAME IAW DWG AND SRM.

Part: SHIELD — CORRODED (AFT CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

SUPPLEMENTAL INFORMATION: AFT PIT R/H SHIELD FWD OF CARGO DOOR STA. 767-787 HAS 9 EACH SCREW HOLES CORRODED (MARKED) / REMOVED CORROSION FROM AFT PIT SHIELD FORWARD OF CARGO DOOR IAW B737 SRM 63-60-15-1A-1; ORIG; .050' REMAIN .022' LOSS OF .028' OUT OF LIMITS. REMOVED AND REPLACED SHIELD IAW BOEING DWG 146A0081 REV A.

Part: FLOOR SUPPORT — CORRODED (AFT CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE AT 767 + 6' RBL 3 HAS CORROSION AT SPLICE (MARKED / EVALUATED CORROSION ON AFT CARGO PIT FLOOR SUPPORT AT STA 767+6' RBL 3 FOUND CORROSION ON REPAIR PART. NO LIMITS. REMOVED V CHANNEL FABRICATED AND INSTALLED I/A/W SRM 53-00-53-2R-2 AND S/W EA 1-A53-4982 REV 3

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 767+6, LBL 17. R&R STRUCTURE IAW SRM & EA.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BILGE STRINGER CLIP CORRODED AT BS 747, STR 26R. R&R CLIP IAW DWG.

Part: PLATE — CRACKED (LT WING) · airframe 63,326 hrs · 37,217 cycles

LT WING TRAILING EDGE PANEL 551GB ATTACH WAFFLE PLATE INBOARD OF PYLON CRACKED. R&R WAFFLE PLATE IAW SRM AND DWG.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 727D+6, LBL 12. REPAIRED STRUCTURE IAW SRM AND EA.

Part: STRINGER CLIP — CORRODED (AFT CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY BILGE STA. 787 S-26L CLIP HAS CORROSION AT RIVIT (MARKED) / REMOVED & REPLACED STRINGER CLIP @ STA 787 STR 26L IAW BOEING DWG 146A1262 REV - AMM 51-21-91-620-802 FOR APPLYING CIC.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 727D+6, LBL 8. REPAIRED STRUCTURE IAW EA.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 727D+6, LBL 3. REPAIRED STRUCTURE IAW EA.

Part: GUSSET — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

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

Part: ANGLE — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

RT AIR CONDITION BAY AFT WALL KEEL BEAM WEB, VAPOR BARRIER UPPER ANGLE CRACKED AT BS 663, RBL 8.6. R&R ANGLE IAW EA.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO PIT LT Z- ANGLE CORRODED BETWEEN BS 727B TO BS 727D. R&R Z-ANGLE IAW SRM.

Part: INTERCOSTAL — CORRODED (AFT CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR STRUCTURE INNER COSTAL STA. 787 - 807 RBL 8 HAS AREA OF CORROSION (MARKED) / AFT CARGO INTERCOSTAL @ STA 787 TO 807 RBL 8 EXFOLIATED OUT OF LIMITS IAW SRM 53-60-15-1A-1 REMOVED AND REPLACED INTERCOSTAL IAW SRM 51-40-02-0G-0 AND DWG # 146A8130 SHEET 12 REV B

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO BAY FLOOR SUPPORT STRUCTURE CORRODED AT BS 727D+6, RBL 8. REPAIRED STRUCTURE IAW SRM AND EA.

Part: BAFFLE — CRACKED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

FWD CARGO COMPARTMENT STA 500 TO STA 500A AT STR. 26L BAFFLE CRACKED / REMOVED AND REPLACED BAFFLE IN FWD CARGO COMPARTMENT AT STA 500-500A; STR 26R. IAW SRM 51-40-02; 51-40-05 AND DWG 143A7505 REV - ATAG A65905

Part: BRACKET — CRACKED (RT WING) · airframe 63,326 hrs · 37,217 cycles

RIGHT WING FIXED TRAILING EDGE I/B OF DEFLECTION RIB CURVE ANGLE BRACKET CRACKED. / REPLACED RIGHT WING FIXED TRAILING EDGE I/B OF DEFLECTION RIB CURVE ANGLE BRACKET IAW B737-700 SRM 51-40-02-0G-0 DWG:115A2930 REV:-

Part: VAPOR BARRIER — CRACKED (LT WHEEL WELL) · airframe 63,326 hrs · 37,217 cycles

NEED TO REPAIR STA 663 L/H LOWER VAPOR BARRIER WEB (COMPOSITE) ITS CRACKED AT LBL 18' / REPAIRED CRACKED STA 663 L/H VAPOR BARRIER IAW SRM 51-70-04-2R-10 PAR. D - F REV 64 AND SRM 57-10-10-2R-2 PAR 2C.

Part: VAPOR BARRIER — CRACKED (LT WHEEL WELL) · airframe 63,326 hrs · 37,217 cycles

NEED TO REPAIR STA 663 R/H LOWER VAPOR BARRIER WEB (COMPOSITE)_DUE TO CRACK IN WEB / REPAIRED STA 663 RH LOWER VAPOR BARRER WEB (COMPOSITE) IAW SRM 57-10-10-2R-2 AND SRM 51-70-04-2R-2 AND SRM 51-70-04-2R-10 PAR. 4 D - F REV 64.

Part: SUPPORT — CORRODED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

FWD CARGO COMPARTMENT STA 500D LBL 24 O/B LOWER EDGE OF CENTER PANEL SUPPORT HAS SURFACE CORROSION. / REMOVED AND REPLACED FWD CARGO COMPARTMENT STA 500D LBL 24 O/B LOWER EDGE OF CENTER PANEL SUPPOT. IAW SRM 51-40-02; 51-40-05 AND DWGS 143A9481 REV A; BLENDED CORROSION IAW SRM 51-10-02; STEP 15. NO PUBLISHED ALLOWABLE LIMITS TO BE FOUND. OUT OF LIMITS. ATAG KD1472

Part: SCUFF PLATE — CRACKED (AFT CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO PIT FWD CORNER SCUFF PLATE CRACKED / AFT CARGO PIT FWD COVER SCUFF PLATE REPAIRED I/A/W SWA EA # 1-A53-2076 REV 11

Part: LIGHT — BROKEN (CABIN) · airframe 63,326 hrs · 37,217 cycles

AFT ENTRY OVERHEAD EMERGENCY EXIT LIGHT BROKEN. R&R LIGHT IAW AMM.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FORWARD CARGO COMPARTMENT RT "Z" ANGLE CORRODED BETWEEN BS 500A TO BS 500D. REPAIRED Z ANGLE IAW SRM AND DWG.

Part: SHIELD — CORRODED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

FWD CARGO COMPARTMENT AFT SHIELD HAS SURFACE CORROSION. / REMOVED CORROSION AT FWD PIT AFT SHIELD VERIFIED LIMITS ORIGINAL MATERIAL .032'; REMAINING .020' LOSS .012' 'FOUND TO BE OF LIMITS'; REMOVED SHIELD; LOCATE DRILLED AND INSTALLED NEW PAINT AND APPLIED CIC AREA IAW B737-700 SRM 51-40-02-0G-0 DWG: 143A0080 REV.- TAG: WN1923

Part: PANEL SUPPORT — CORRODED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

FWD CARGO COMPARTMENT STA 500D LBL 25 I/B LOWER EDGE OF L/H PANEL SUPPORT HAS SURFACE CORROSION. / REMOVED DAMAGED FWD CARGO LOWER PANEL SUPPORT STA 500D & REPLACED WITH NEW. NO PUBLISHED ALLOWABLE LIMITS FOUND IN BOEING 737-700 SRM 53-00-53-1A-2 INSTALLED NEW PART IAW BOEING DWG 143A9481 ID:0008 REV:A

Part: SHIELD — CORRODED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

FWD CARGO COMPARTMENT FWD SHIELD HAS SURFACE CORROSION. / BLENDED CORROSION ON FWD CARGO COMPARTMENT FWD SHIELD. ORIGINAL 0.032' REMAINING 0.024' WITH MAX LOSS 0.008' MATERIAL FOUND TO BE OUT OF LIMITS IAW B737-700 SRM 53-00-53-1A-2 FIG 103; DETAIL D. REMOVED AND REPLACED SHIELD ASSY MPN 143A8126-21 IAW DWG 143A0080 REV G AND B737-700 SRM 51-40-02-0G-0. APPLIED CIC TO NEW SHIELD ASSY IAW B737-700 AMM 51-21-91-620-802. TAG WN4985

Part: SCUFF PLATE — CRACKED (AFT CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

AFT CARGO PIT CENTER SCUFF PLATE CRACKED / AFT CARGO PIT CENTER SCUFF PLATE REPAIRED I/A/W SWA EA# 1-A53-2076 REV 11

Part: SUPPORT ANGLE — CORRODED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

FWD CARGO COMPARTMENT STA 500D O/B OF STR 26R O/B PANEL SUPPORT HAS SURFACE CORROSION. / REMOVED CORROSION; IAW B737-700 SM 53-00-523-1A-2. EVALUATED MATERIAL LOSS; NO PUBLIHED ALLOWBLE LIMITS FOUND IN B737-700 SRM 53-00-53-1A-2 PART IS OUT OF LIMITS. RECIEVED NEW ANGLE RAIL AS P/N 7530202 IAW BOEING DWG. #143A9481 REV A. LOCATED DRILLED AND INSTALLED IAW B737-700 SRM 51-40-05 AND 51-40-02 APPLIED CIC IAW B737-700 AMM 51-21-91-620-802 ALL WORK ACCOMPLSHED IN FWD CARGO COMP. STA 500D O/B OF STR 26R.

Part: ANGLE — CORRODED (FWD CARGO BAY) · airframe 63,326 hrs · 37,217 cycles

FWD CARGO COMPARTMENT L/H 'Z' ANGLE STA 500 + 10' TO STA 500C + 13' HAS SURFACE CORROSION. / REMOVED CORROSION IN AREA AND FOUND OUT LIMITS ORIG. 7. 0.040'; LOSS OF 0.014:; REMAINING T OF 0.026' AND CUT OUT SECTION AND INSTALLED NEW SECTION P/N BAC1496-444 7075-T62 ATAG# A48425 PO # 1539104 AND RESTORED FINISH. IAW B737-700 SRM 53-00-53-2R-G REPAIR #6. CORROSION BLENDED FROM STA 500+10' TO STA 500C +13' L/H Z ANGLE

Part: VAPOR BARRIER — CRACKED (LT MLG WW) · airframe 63,326 hrs · 37,217 cycles

LT MAIN WHEEL WELL BULKHEAD VAPOR BARRIER CRACKED AT BS 663. REPAIRED BARRIER IAW SRM AND DWG.

Part: VAPOR BARRIER — CRACKED (RT MLG WW) · airframe 63,326 hrs · 37,217 cycles

RT MAIN WHEEL WELL BULKHEAD LOWER COMPOSITE VAPOR BARRIER CRACKED AT BS 663. REPAIRED WEB IAW SRM AND DWG.

Part: STIFFENER — CRACKED (LT MLG WW) · airframe 63,326 hrs · 37,217 cycles

LT MAIN WHEEL WELL, STATION 663 BULKHEAD, ''U'' SHAPED STIFFENER ABOVE AIR CONDITION PACK EXHAUST DUCT CRACKED. R&R STIFFENER IAW SRM AND DWG.

Part: STIFFENER — CRACKED (RT MLG WW) · airframe 63,326 hrs · 37,217 cycles

RT MAIN WHEEL WELL BULKHEAD, ''U'' SHAPED STIFFENER CRACKED AT BS 663. R&R STIFFENER IAW SRM & DWG.

Part: THRESHOLD — CORRODED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FORWARD CARGO DOOR CUTOUT THRESHOLD WEB CORRODED ALONG UPPER SURFACE. R&R WEB IAW SRM AND DWG.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 63,326 hrs · 37,217 cycles

FORWARD CARGO DOOR CUTOUT ATTACH ANGLE CRACKED AT BS 440, RBL 22. R&R ANGLE IAW SRM AND DWG.

Part: SKIN — CRACKED (LE SLAT) · airframe 63,326 hrs · 37,217 cycles

RT WING LEADING EDGE NR 5 SLAT LOWER SKIN AT ACTUATOR ATTACH FITTING CRACKED. REPAIRED SKIN IAW SRM.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 63,014 hrs · 37,018 cycles

RIGHT OVERWING EXIT EXTERIOR EMERGENCY LIGHT INOPERATIVE. REPLACED THE LAMPS IAW AMM.

Part: LENS — MISSING (EXIT SIGN) · airframe 62,836 hrs · 36,913 cycles

R2 DOOR EMERGENCY EXIT SIGN LENS MISSING. INSTALLED LENS PER EA.

Part: LIGHT — BROKEN (CABIN) · airframe 62,209 hrs · 36,517 cycles

FORWARD LAV EMERGENCY EXIT LIGHT BROKEN. R&R LIGHT PER AMM.

Part: STIFFENER — CRACKED (NLG WHEEL WELL) · airframe 61,962 hrs · 36,370 cycles

STATION 663 LBL 26 VERTICAL STIFFENER CRACKED OTBD OF TURBINE EXHAUST DUCT. / REMOVED AND REPLACED STIFFENER PER SRM 51-40-02

Part: STRIP — CORRODED (AFT CARGO BAY) · airframe 61,962 hrs · 36,370 cycles

AFT CARGO STA887 FLOOR TRANSITION IS CORRODED / REMOVED AND REPLACED AFT CARGO STA 887 FLOOR TRANSITION PER SRM 51-40-02

Part: TRANSMISSION — FAULTY (TE FLAP) · airframe 61,808 hrs · 36,272 cycles

DECLARED EMERGENCY, GOING FROM FLAPS 5 TO 15, FLAPS STAYED IN 5 POSITION WITH ASYMMETRY. FLAPS WOULD NOT RETRACT AFTER LANDING. R&R TRANSMISSION IAW AMM.

Part: PROXIMITY SENSOR — FAULTY (LANDING GEAR) · airframe 61,326 hrs · 35,982 cycles

AIR TURNBACK, LANDING GEAR HANDLE WOULD NOT MOVE TO UP POSITION AFTER T10. R&R S1050 PROXIMITY SENSOR PER MM.

Part: GIRT BAR — LOOSE (R2 DOOR) · airframe 60,646 hrs · 35,559 cycles

R2 DOOR ESCAPE SLIDE GIRT BAR FLAPPER LOOSE. R&R GIRT BAR ASSEMBLY PER MT.

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHT) · airframe 60,114 hrs · 35,233 cycles

EMERGENCY LIGHT BATTERY FAILED CAPACITY TEST AT LOCATIONS M1671. R & R THE BATTERY PACK IAW AMM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 60,114 hrs · 35,233 cycles

EMERGENCY LIGHT BATTERY FAILED CAPACITY TEST AT LOCATIONS M1673. R&R BATTERY PACK PER AMM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 60,114 hrs · 35,233 cycles

EMERGENCY LIGHT BATTERY FAILED CAPACITY TEST AT LOCATIONS M1675. R&R BATTERY PACK PER AMM.

Part: BATTERY PACK — FAILED (CABIN) · airframe 60,114 hrs · 35,233 cycles

EMERGENCY LIGHT BATTERY FAILED CAPACITY TEST AT LOCATIONS M1669. R&R BATTERY PACK PER AMM.

Part: SLIDE — LOOSE (L1 DOOR) · airframe 58,825 hrs · 34,451 cycles

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

Part: LENS — MISSING (EMERGENCY LIGHT) · airframe 58,542 hrs · 34,277 cycles

L1 DOOR EXIT SIGN LENS MISSING. R & R THE SIGN ASSY IAW MM.

Part: TRANSMITTER — FAULTY (TE FLAP) · airframe 57,100 hrs · 33,413 cycles

DIVERSION, DECLARED EMERGENCY AFTER TAKEOFF FLAPS STUCK AT POSITION 1. RECYCLED HANDLE, NO EFFECT CIRCUIT BREAKERS NORMAL. R & R RT FLAP POSITION TRANSMITTER IAW MM.

Part: TRANSMITTER — FAULTY (TE FLAP) · airframe 57,100 hrs · 33,413 cycles

DIVERSION, DECLARED EMERGENCY AFTER TAKEOFF FLAPS STUCK AT POSITION 1. RECYCLED HANDLE, NO EFFECT CIRCUIT BREAKERS NORMAL. R & R LT FLAP POSITION TRANSMITTER IAW MM.

Part: PRESSURE PANEL — CRACKED (RT MLG WW) · airframe 57,073 hrs · 33,399 cycles

MAIN WHEEL WELL HORIZONTAL BEADED PRESSURE WEB CRACKED AT BS 665, BETWEEN RBL 38 TO RBL 61. R & R WEB IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

FRAME CRACKED AT BS 500C, STRINGER 8L. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

FRAME CRACKED AT BS 500A, STRINGER 8L. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

FRAME CRACKED AT BS 500A, STRINGER 8R. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 57,073 hrs · 33,399 cycles

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

Part: PRESSURE PANEL — CRACKED (RT MLG WW) · airframe 57,073 hrs · 33,399 cycles

MAIN WHEEL WELL VERTICAL PRESSURE WEB CRACKED AT BS 663, RBL 40.5. REPAIRED WEB IAW SRM.

Part: SLIDE — UNSECURE (R1 DOOR) · airframe 56,539 hrs · 33,065 cycles

R1 DOOR EMER EVAC SLIDE INADVERTENTLY FELL OUT, DID NOT DEPLOY, STILL OPERATIONAL. REINSTALLED SLIDE IAW MT.

Part: SLIDE — LOW PRESSURE (R2 DOOR) · airframe 55,861 hrs · 32,692 cycles

R2 DOOR EMER EVAC SLIDE PRESS LOW. R & R SLIDE IAW MT.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 55,408 hrs · 32,425 cycles

COPILOT NR 1 WINDOW FRAME, OTBD UPPER CORNER CRACKED ON EXTERIOR, INBD & INTERIOR SURFACES. REPAIRED FRAME IAW ACO.

Part: BATTERY — FAILED (CABIN) · airframe 54,045 hrs · 31,628 cycles

LEFT AFT EMER BATTERY FAILED CAPACITY TEST. R & R BATTERY IAW MM.

Part: LIGHT — UNSECURE (CABIN) · airframe 54,026 hrs · 31,619 cycles

OVERWING CEILING EMER LIGHT ASSEMBLY FELL OFF MOUNT. INSTALLED RT OTBD RETAINING CLIP & HARDWARE IAW MM.

Part: ACTUATOR — FAULTY (FUEL SYSTEM) · airframe 52,985 hrs · 31,031 cycles

DIVERSION, DECLARED EMER. FUEL IMBALANCE LIGHT ON INFLIGHT WITH XFEED OPEN & LT CTR PUMP ON. 1100 LBS IMBALANCE NOTED. IMBALANCE INCREASED SPORADICALLY TO 1900 LBS WITH XFEED CLOSED & CTR PUMPS OFF. MAIN PUMPS REMAINED ON FOR ENTIRE FLIGHT. FUEL FLOWS WERE EQUAL & NO VISIBLE SIGNS OF LEAK. IMBALANCE STABILIZED AT 1900 LBS FOR LAST 20 MINUTES OF FLIGHT. R & R ENG FUEL FEED ACTUATOR IAW MM.

Part: SKIN — CRACKED (FUSELAGE) · airframe 52,615 hrs · 30,825 cycles

SKIN CRACKED AT BS 540, STRINGER 22L. REPAIRED SKIN IAW EA.

Part: GIRT BAR — OUT OF ADJUST (R1 DOOR) · airframe 52,366 hrs · 30,670 cycles

R1 DOOR EMER EVAC SLIDE GIRT BAR OUT OF ADJUSTMENT. ADJUSTED GIRT BAR IAW MM.

Part: HANDLE — LOOSE (L2 DOOR) · airframe 51,397 hrs · 30,076 cycles

L2 DOOR SLIDE PULL HANDLE FLAP LOOSE. SECURED HANDLE IAW MT.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 50,730 hrs · 29,701 cycles

L2 DOOR EMER EXIT LIGHT BULB INOPERABLE. RELAMPED LIGHT IAW AMM.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 50,623 hrs · 29,639 cycles

NUMBER 3 RT WINDOW FRAME CRACKED AT THE SECOND FASTENER HOLE. REPAIRED FRAME ASSEMBLY IAW EA.

Part: STRAP — CRACKED (FUSELAGE) · airframe 50,623 hrs · 29,639 cycles

SEAT TRACK SPLICE STRAP CRACKED AT BS 727B, LBL 24.75. REPAIRED STRAP IAW EA.

Part: STRAP — CRACKED (FUSELAGE) · airframe 50,623 hrs · 29,639 cycles

SEAT TRACK SPLICE STRAP CRACKED AT BS 727B, LBL 45.5. REPAIRED STRAP IAW EA NO.

Part: STRAP — CRACKED (FUSELAGE) · airframe 50,623 hrs · 29,639 cycles

SEAT TRACK SPLICE STRAP CRACKED AT BS 727B, RBL 24.75. REPAIRED STRAP IAW EA.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 50,623 hrs · 29,639 cycles

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

Part: STRAP — CRACKED (FUSELAGE) · airframe 50,623 hrs · 29,639 cycles

SEAT TRACK SPLICE STRAP CRACKED AT BS 727B, RBL 24.75. REPAIRED STRAP IAW SRM.

Part: SKIN — CRACKED (LE SLAT) · airframe 50,623 hrs · 29,639 cycles

RIGHT WING NR 8 LE SLAT LOWER SKIN CRACKED. REPAIRED SKIN IAW SRM.

Part: WINDOW FRAME — CRACKED (FUSELAGE) · airframe 49,583 hrs · 29,054 cycles

CAPTAIN`S FWD OUTER WINDOW FRAME CRACKED BELOW UPPER LT UPPER EDGE OF FRAME. REPAIRED FRAME IAW EA.

Part: LIGHT — LOOSE (COCKPIT) · airframe 46,678 hrs · 27,333 cycles

FIRST OFFICER SIDE PLASTIC EXIT COVER NEAR FLOOR SIDE EXIT ROW LOOSE. REMOVED AND REPLACED LIGHT ASSY PER AMM.

Part: SLIDE — OUT OF POSITION (L1 DOOR) · airframe 44,298 hrs · 25,837 cycles

L1 DOOR EMERGENCY EVAC SLIDE INADVERTANTLY FELL OUT, DID NOT DEPLOY, STILL OPERATIONAL. RE-INSTALLED SLIDE IAW MT.

Part: HOOK — LOOSE (L1 DOOR) · airframe 43,979 hrs · 25,644 cycles

L1 DOOR EMERGENCY EVAC SLIDE COVER GIRT BAR HOOKS LOOSE. REMOVED AND REPLACED HOOK ASSY PER SRM.

Part: LENS — LOOSE (EVAC SLIDE) · airframe 43,979 hrs · 25,644 cycles

R1 DOOR SLIDE EMERGENCY EVAC LENS LOOSE. REMOVED AND REPLACED LENS PER AMM.

Part: HOOK — LOOSE (R1 DOOR) · airframe 43,979 hrs · 25,644 cycles

R1 DOOR EMERGENCY EVAC SLIDE COVER GIRT BAR HOOKS LOOSE. SECURED HOOK ASSY PER SRM.

Part: LENS — LOOSE (EVAC SLIDE) · airframe 43,979 hrs · 25,644 cycles

L1 DOOR EMERGENCY EVAC SLIDE LENS LOOSE. REMOVED AND REPLACED LENS PER AMM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 43,739 hrs · 25,499 cycles

R2 DOOR EMERGENCY LIGHT BULB INOP. REMOVED AND REPLACED BULB IAW M/M.

Part: FUSE — BLOWN (EMERGENCY LIGHTS) · airframe 43,739 hrs · 25,499 cycles

LEFT EMERGENCY EXIT LIGHT BATTERY PACK INOP. REMOVED AND REPLACED FUSE PER AMM.

Part: RIB — CRACKED (RT HORIZ STAB) · airframe 43,739 hrs · 25,499 cycles

RIGHT HORIZONTAL STABILIZER RIB CRACKED AT STA 92.70. REMOVED AND REPLACED RIB IAW SRM.

Part: RIB — CRACKED (RT HORIZ STAB) · airframe 43,739 hrs · 25,499 cycles

RIGHT HORIZONTAL STABILIZER LEADING EDGE 4TH RIB FROM I/B END CRACKED. REMOVED AND REPLACED RIB PER SRM.

Part: RIB — CRACKED (RT HORIZ STAB) · airframe 43,739 hrs · 25,499 cycles

RIGHT HORIZONTAL STABILIZER LEADING EDGE SUPPORT RIB 3RD FROM I/B END CRACKED. REMOVED & REPLACED RIB PER SRM.

Part: RIB — CRACKED (RT HORIZ STAB) · airframe 43,739 hrs · 25,499 cycles

RIGHT HORIZONTAL STABILIZER LEADING EDGE 5TH RIB FROM I/B END CRACKED. REMOVED AND REPLACED RIB PER SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,739 hrs · 25,499 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,739 hrs · 25,499 cycles

FRAME CRACKED AT BS 440, STR 8L. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,739 hrs · 25,499 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,739 hrs · 25,499 cycles

FRAME CRACKED AT BS 440, STR 8L. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,739 hrs · 25,499 cycles

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

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,739 hrs · 25,499 cycles

FRAME CRACKED AT BS 380, STR 8L. REPAIRED FRAME IAW EA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 43,739 hrs · 25,499 cycles

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

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 43,739 hrs · 25,499 cycles

FLOORBEAM CORRODED AT BS 973.5, LBL 42. REPAIRED BEAM PER SRM.

Part: WEB — CORRODED (FUSELAGE) · airframe 43,739 hrs · 25,499 cycles

FLOOR WEB CORRODED AT BS 1016, LBL 39. REMOVED AND REPLACED WEB PER DWG AND SRM.

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 43,739 hrs · 25,499 cycles

LEFT HORIZONTAL STABILIZER LOWER SKIN CRACKED AT STA 175.5. REPAIRED SKIN PER SRM.

Part: SKIN — CRACKED (RT HORIZ STAB) · airframe 43,739 hrs · 25,499 cycles

RIGHT HORIZONTAL STABILIER LOWER SKIN CRACKED AT STA 101.9. REPAIRED SKIN IAW SRM.

Part: LENS — MISSING (CABIN) · airframe 42,822 hrs · 24,971 cycles

R2 DOOR EMERGENCY EXIT LIGHT LENS MISSING. REMOVED AND REPLACED LIGHT ASSY PER MM.

Part: COVER — MISSING (CABIN) · airframe 41,939 hrs · 24,450 cycles

LEFT EMERGENCY EXIT LIGHT COVER MISSING ON LOWER FWD CORNER. INSTALLED COVER PER MM.

Part: PRESSURE PANEL — CRACKED (FUSELAGE) · airframe 37,085 hrs · 21,641 cycles

DURING SCHEDULED 10Y CHECK, FOUND MAIN CABIN PRESSURE DECK WEB CRACKED AT BS 663, LBL 33. REPAIRED WEB PER EA.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 37,085 hrs · 21,641 cycles

DURING SCHEDULED 10Y CHECK, FOUND STEP ASSY INTERCOSTAL CORRODED AT BS 270, BL 0. REPAIRED INTERCOSTAL PER EA.

Part: FITTING — CORRODED (RT MLG TRUNNION) · airframe 34,744 hrs · 20,162 cycles

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

Part: FITTING — CORRODED (LT MLG TRUNNION) · airframe 34,744 hrs · 20,162 cycles

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

Part: BATTERY PACK — FAILED (CABIN) · airframe 34,187 hrs · 19,811 cycles

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

Part: SLIDE — OUT OF POSITION (R1 DOOR) · airframe 34,151 hrs · 19,792 cycles

DURING SCHEDULED MV2 CHECK, FOUND R1 DOOR EMERGENCY EVAC SLIDE INADVERTENTLY FELL OUT OF CONTAINER, DID NOT DEPLOY. RE-INSTALLED SLIDE PER MM.

Part: SLIDE — OUT OF POSITION (R1 DOOR) · airframe 33,511 hrs · 19,409 cycles

R1 DOOR EMERGENCY EVAC SLIDE GIRT OUT OF POSITION. REMOVED AND REPLACED SLIDE PER MT.

Part: COVER — BROKEN (CABIN) · airframe 32,605 hrs · 18,868 cycles

DURING SCHEDULED MV1 CHECK, FOUND FWD ENTRY LOWER EMERGENCY EXIT SIGN COVER BROKEN. REMOVED AND REPLACED COVER PER MM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 29,542 hrs · 16,964 cycles

DURING SCHEDULED HC1 CHECK, FOUND RT OVERWING EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED LIGHT BULB PER MM.

Part: GLOWSTRIP — WORN (CABIN) · airframe 29,542 hrs · 16,964 cycles

DURING SCHEDULED HC1 CHECK, FOUND EEPLS PHOTOLUMINESCENT STRIP WORN AT ROW 15 DEF. REMOVED AND REPLACED STRIP PER MM.

Part: SLIDE — OUT OF ADJUST (R2 DOOR) · airframe 29,542 hrs · 16,964 cycles

DURING SCHEDULED HC1 CHECK, FOUND R2 DOOR EMERGENCY EVAC SLIDE OUT OF ADJUST. ADJUSTED EVAC SLIDE PER MM.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 28,180 hrs · 16,167 cycles

DURING SCHEDULED MV2 CHECK, FOUND LT MID CABIN EMERGENCY EXIT LIGHTS INOP. REMOVED AND REPLACED BATTERY PACK AND CHARGER PER MM.

Part: CHARGER — INOPERATIVE (EMERGENCY LIGHTS) · airframe 27,927 hrs · 16,015 cycles

DURING SCHEDULED MV2 CHECK, FOUND LT CABIN EMERGENCY EXIT LIGHTS INOP. REMOVED AND REPLACED BATTERY CHARGER PER MM.

Part: CHARGER — INOPERATIVE (EMERGENCY LIGHTS) · airframe 27,905 hrs · 15,998 cycles

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

Part: SLIDE — OUT OF ADJUST (L1 DOOR) · airframe 27,059 hrs · 15,509 cycles

DURING SCHEDULED HC2 CHECK, FOUND L1 DOOR EMERGENCY EVAC SLIDE OUT OF ADJUST. ADJUSTED EVAC SLIDE PER MM.

Part: BATTERY — FAILED (EMERGENCY LIGHTS) · airframe 24,576 hrs · 14,075 cycles

DURING SCHEDULED HC1 CHECK, LEFT OVERWING EMERGENCY BATTERY PACK FAILED LONG TEST. REMOVED AND REPLACED BATTERY PACK PER MM.

Part: BATTERY — FAILED (EMERGENCY LIGHTS) · airframe 24,576 hrs · 14,075 cycles

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

Part: BATTERY — FAILED (EMERGENCY LIGHT) · airframe 22,116 hrs · 12,656 cycles

DURING SCHEDULED HC2 CHECK, FWD CABIN EMERGENCY EXIT LIGHTS FAILED TEST. REMOVED AND REPLACED EMERGENCY EXIT LIGHT BATTERY PACKS PER MM.

Part: SLIDE — OUT OF ADJUST (R1 DOOR) · airframe 22,116 hrs · 12,656 cycles

DURING SCHEDULED HC2 CHECK, FOUND R1 DOOR EMERGENCY EVAC SLIDE OUT OF ADJUST. ADJUSTED EVAC SLIDE PER MM.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 22,116 hrs · 12,656 cycles

DURING SCHEDULED HC2 CHECK, FOUND EMERGENCY EXIT LIGHT INOP AT ROW 4 DEF. REMOVED AND REPLACED LIGHT ASSY PER MM.

Part: BULB — INOPERATIVE (EMERGENCY EXIT) · airframe 19,548 hrs · 11,193 cycles

DURING SCHEDULED MV2 CHECK, FOUND L1 DOOR EXTERIOR EMERGENCY EXIT LIGHT INOP. RELAMPED LIGHT PER MM.

Part: SWITCH — INOPERATIVE (EMERGENCY LIGHT) · airframe 18,626 hrs · 10,684 cycles

DURING SCHEDULED 5Y CHECK, ALL EMERGENCY LIGHTS ILLUMINATED WITH NO ELECTRICAL POWER ON & COCKPIT LIGHT SWITCH OFF. REMOVED AND REPLACED EMERGENCY LIGHT SWITCH PER WDM & MM.

Part: WINDOW — CRACKED (COCKPIT) · airframe 18,547 hrs · 10,636 cycles

R2 COCKPIT WINDOW STARTED ARCING, THEN SHATTERED. REMOVED AND REPLACED R2 WINDOW & HEAT CONTROLLER PER MM.

Part: BATTERY — FAILED (EMERGENCY LIGHT) · airframe 17,361 hrs · 9,943 cycles

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

Part: SLIDE — OUT OF ADJUST (L2 DOOR) · airframe 17,361 hrs · 9,943 cycles

DURING SCHEDULED HC2 CHECK, FOUND L2 DOOR EVAC SLIDE OUT OF ADJUST. ADJUSTED L2 DOOR EVAC SLIDE PER MM.

Part: COVER — EXPOSED (CABIN) · airframe 8,055 hrs · 4,793 cycles

EEPLS WIRES EXPOSED AT OVERWING EXIT. INSTALLED EEPLS COVER PER MM.