N567WN
Registered owner: SOUTHWEST AIRLINES CO, TX (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| SOUTHWEST AIRLINES CO | Operator | 2024-04-03 – 2024-04-03 | Operator named in NTSB report |
| SOUTHWEST AIRLINES, CO. (SWAA) | Operator | 2024-04-03 – 2024-04-03 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
EMERGENCY BATTERY PACK AT 14 DEF M1669 FAILED CAPACITY CHECK. R&R CABIN EMERGENCY BATTERY PACK IAW AMM 33-51-06.
AFT. OF L2 DOOR EXTERIOR EMERGENCY LIGHTS INOP<[01] RELAMPED L2 EXTERIOR EMERGENCY LIGHT AND CHECK GROUND WIRES. PER AMM 33-51-04. REMOVED AND REPLACED L2 DOOR SLIDE EMERGENCY LIGHT BATTERY PACK AND CHARGER ASSY PER AMM 33-51-06.
FWD SERVICE DOOR GIRT HANGING LOW. SECURED THE GIRT BAR IAW AMM 25-66-01.
EMERGENCY LIGHT AT SEAT ROW 14ABC INOPERATIVE.<[01] REMOVED AND REPLACED EMERGENCY LIGHT LAMP AT SEAT ROW 14ABC. REF AMM 33-51-01. OPERATIONAL CHECK GOOD.
EMERGENCY LIGHT AT SEAT ROW 6DEF INOPERATIVE.<[01] REMOVED AND REPLACED EMERGENCY LIGHT LAMP AT SEAT ROW 6DEF. REF AMM 33-51-01. OPERATIONAL CHECK GOOD.
SEATS RECLINING AT EMERGENCY EXIT ROW 12D; 12F. ADJUSTED 12D; 12F SEAT RECLINE REF AMM 25-22-00
R2 DOOR ESCAPE SLIDE DRAGS ON THE FLOOR<[01]. PROPERLY INSTALLED R2 DOOR ESCAPE SLIDE IAW AMM 25-66-01-400-801;[02] VERIFIED CORRETIVE ACTION ENTRY 1.
EMERGENCY LIGHTS RELATED TO BATTERY PACK M2355 FAIL TEST<[01] REPLACED EMERGENCY BATTERY PACK M2335; PERFORMED GOOD EMEREGENCY LIGHT TEST PER AMM 33-51-06-960-805;[02] VERIFIED CORRECTIVE ACTION. CARD COMPLETE.
FWD ESCAPE EMEREGENCY LIGHT OUTSIDE FWD MAIN ENTRY DOOR INOP (L731)<[01] INSTALLED NEW LIGHT AT FWD ESCAPE EMEREGENCY OUTSIDE FWD MAIN ENTRY DOOR; PERFORMED GOOD TEST PER AMM 33-51-04-960-801.;[02] VERIFIED COMPLETION CORRECTIVE ACTION 1 AND MEASUREMENT TABLE.
AFT AND FWD SCUFF PLATES (CORNERS) MISSING AT FWD CARGO BAY<[01] 01 - REMOVED AND REPLACED PER [AMM 53-11-02-420-801-NG (CARGO DOOR SCUFF PLATE - INSTALLATION - PERMANENT)];[02] VERIFIED ACTION 1.<BR>JOB COMPLETE.
CRACKED PANEL BREAK BS 540 BL 0 - RBL 25 WL 207 (MARKED)<[01] REMOVED AND REPLACED PANEL BREAK AT BS540 BL0-RBL25 WL207 PER SRM 51-40-02 AND DWG:143A0060 REV:A;[02] VERIFIED ACTION 1.<BR>JOB COMPLETE.
CRACKED PANEL BREAK BS 540 BL 0 - LBL 25 WL 207 (MARKED)<[01] REMOVED AND REPLACED PANEL BREAK AT BS540 BL0-LBL25 WL207 PER SRM 51-40-02 AND DWG:143A0060 REV:A;[02] VERIFIED ACTION 1.<BR>JOB COMPLETE.
CORROSION ON SEAT TRACK LBL 24.75 BS500A+8; BS500A+11; BS500A+14.5; BS500A+17; BS500D+9.5; BS 520+5.5 TO BS520+11 WL 208 (MARKED)<[01] BS 480 TO BS 520 LBL25 SEAT TRACK WILL REPLACE DUE TO MECHANICAL DAMAGE ACCORDING TO CUST# TTG8Q00Y9C8F.<BR>UPON FURTHER INVESTIGATION NO CORROSION ON SEAT TRACK LBL 25 BS520+5.5 TO BS520+11 WL 208.;[02] VERIFIED ITEM 1
CORROSION ON SEAT TRACK LBL 45.5 BS480+16.5; BS500A+5; BS500A+8; BS500B+16; BS500B+18.5; BS00D+9.5 WL 208 (MARKED)<[01] SEAT TRACK WILL REPLACE DUE TO MECHANICAL DAMAGE ACCORDING TO CUSTOMER # TTG8Q00Y9C43.;[02] VERIFIED ITEM 1
CRACK ON RH LOWER HORIZONTAL STABILIZER SKIN AT STAB STA 193.90; 18.5' FROM FWD EDGE; .35' IN LENGTH (MARKED) <[01]. REPAIRED R/H HORIZONTAL STAB LOWER SKIN AT STAB STA 193.90 IAW SRM 55-10-01-2R-11 REPAIR 11.; [02] VERIFIED ACTION ITEMS AND TASK CARD COMPLETED.
RIGHT WING T/E UPPER SURFACE PANEL AT ORSS 276; TRANSVERSE WEB IS CRACKED AT O/B UPPER FASTENER<[01] REMOVED R/W T/E UPPER SURFCE PANEL TRANSVERSE WEB AT ORSS 276 IAW SRM 51-40-02-OG-0 PARA. 4.;[02] VERIFIED ITEM 1
L-CLIP COMMON TO L/W I/B SIDE OF DEFLECTION CONTROL RIB AND UPPER SURFACE PANEL ORSS 271 IS CRACKED <[01]. REMOVED AND REPLACED L- CLIP COMMON TO L/W I/B SIDE OF DEFLECTION CONTROL RIB AND UPPER SURFACE PANEL AT ORSS 271 IAW SRM 51-40-02-0G-0 PARA. 4.;[02] VERIFIED ITEM 1.
FLOOR PANEL 231ZF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FLOOR PANEL 231ZF; WITH UPPER SKIN AREAS OF PULLED STRANDS WAS REPLACED WITH A NEWLY FABRICATED FLOOR PANEL IAW SRM 53-00-50-2R-0.;[02] JOB COMPLETE.
FLOOR PANEL 231YF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FLOOR PANEL 231YF UPPER SKIN WITH AREAS OF PULLED STRANDS WAS REPLACED WITH A SERVICEABLE FLOOR PANEL PER SRM 51-10-02-0G-0 PARA 9.A.1 DUE TO AMOUNT OF ALL DAMAGE.;[02] ADDED PART INSTALL INFO.
FLOOR PANEL 231XF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FLOOR PANEL 231XF UPPER SKIN WITH AREAS OF PULLED STRANDS WAS REPLACED WITH A SERVICEABLE FLOOR PANEL PER SRM 51-10-02-0G-0 PARA 9.A.1 DUE TO AMOUNT OF ALL DAMAGE.;[02] JOB COMPLETE.
LEFT HORIZONTAL STAB REMOVABLE L/E 331B RIB #5 IS CRACKED<[01] REMOVED AND REPLACED L/H HORIZONTAL STAB. L/E #5 RIB IAW SRM 51-40-02-0G-0 PARA. 4.;[02] VERIFIED COMPLETION CORRECTIVE ACTION 1 AND MEASUREMENT TABLE.
LEFT HORIZONTAL STAB REMOVABLE L/E 331B RIB #3 IS CRACKED<[01] 1. KENNETH RUDIO (TECHNICIAN); 24-JAN-2025 22:07 UTC<BR>REMOVED AND REPLACED L/H HORIZONTAL STAB. L/E #3 RIB IAW SRM 51-40-02-0G-0 PARA. 4.;[02] VERIFIED COMPLETION CORRECTIVE ACTION 1 AND MEASUREMENT TABLE.
PANEL 241DF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] PANEL 241DF WITH UPPER SKIN HAS AREAS OF PULLED STRANDS WAS REPLACED WITH A NEWLY FABRICATED FLOOR PANEL DUE TO AMOUNT OF ALL DAMAGE IAW SRM 53-00-50-2R-0; DWG 144A5810 ID:0128.;[02] JOB COMPLETE.
FLOOR PANEL 242AF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FLOOR PANEL 242AF; UPPER SKIN WITH AREAS OF PULLED STRANDS WAS REPLACED WITH A NEWLY FABRICATED FLOOR PANEL IAW SRM 53-00-50-2R-0.;[02] JOB COMPLETE.
FLOOR PANEL 241AF UPPER SKIN HAS AREAS OF PULLED STRANDS.<[01] FLOOR PANEL 241AF UPPER SKIN; WITH AREAS OF PULLED STRANDS WAS REPLACED WITH A NEWLY FABRICATED FLOOR PANEL IAW SRM 53-00-50-2R-0.;[02] JOB COMPLETE.
RIGHT WING L/E PANEL 621HB HAS DISBOND AT I/B FWD CORNER<[01] 04 - REPAIRED PER [SRM 51-70-05-2R-6-A00737 (REPAIR 6 - REPAIR OF DAMAGE TO THE EDGEBAND OF A HONEYCOMB PANEL - AIRFRAME - PERMANENT)];[02] VERIFEID CORRECTIVE ACTION 1
CRACK IN RH HORIZONTAL PRESSURE DECK BS 664.5 WL 202 RBL 43. CRACK IS .250 INCHES LONG AND MARKED IN RED INK.<[01] REMOVED THE DAMAGE PART OF THE WEB AT BS 663.75 - 6BS75; RBL38 - 60; WL 202; PER SRM 53-40-51-2R-2 PAR. 4. C. FIG. 202.<BR><BR>INSTALLED REPAIR RH HORIZONTAL PRESSURE DECK AT BS 663.75 - 6BS75; RBL38 - 60; WL 202; PER SRM 53-40-51-2R-2 PAR. 4. L. AND DWG 144A7700.;[02] VERIFIED CORRECTIVE ACTION ENTRY 1.
AFT CARGO SUBTHRESHOLD WEB HAVE CORROSION MULTIPLE AREAS.<[01] REMOVE AND REMPLACE AFT CARGO SUBTHRESHOLD WEB SRM 51-40-02 DWG 146A8340 ID:0024 REV: A;[02] REMOVED AND REMPLACED AFT CARGO SUBTHRESHOLD WEB BETWEEN BS 794 TO BS 847 PER SRM 51-40-02 DWG 146A8340 ID:0024 REV: A;[03] VERIFIED COMPLETION CORRECTIVE ACTION 2 AND MEASUREMENT TABLE.
AFT CARGO BAY TENSION STRAP HAS CORROSION APPROX BS802; RBL25.<[01] CORROSION ON TENSION STRAP AT ACB BS 806 ; RBL 25 IN L=2' X W=1' X D=0.030' FROM ORIGINAL THICKNESS 0.100' THEREFORE FOUND TO BE OUT OF LIMITS; TENSION STRAP WILL BE REPAIRED BY REPLACEMENT OF PART PER SRM 53-60-15-1A-1 FIG 103 DETAIL G AND SRM 51-10-02 PAR 9.<BR> <BR>USED TOOL: ID:PER2335; DUE:06/2025;[02] VERIFIED CORRECTIVE ACTION 1;[03] REMOVED AND REPLACED TENSION STRAP AT ACB BETWEEN BS 767+7' TO BS 847+13' ;RBL 25' PER SRM 51-40-02 ; DWG:146A8120 REV-; DWG: 146A8340 REV-; DWG: 146A0081 REV A;[04] VERIFIED RII ITEMS COMPLETE
CRACK IN LH HORIZONTAL PRESSURE DECK BS 672 WL 202 LBL35. CRACK IS .650 INCHES IN LENGTH. MARKED IN RED INK.<[01] REPAIRED LH HORIZONTAL PRESSURE DECK WEB AT BS 663 TO BS 675 LBL 30 TO LBL 60 PER SRM 53-40-51-2R-2 REPAIR 2 FIG. 202.;[02] TASK CARD COMPLETED.;[03] TASK CARD COMPLETED.
FWD CARGO SUBTHRESHOLD HAS CORROSION IN MULTIPLE AREAS<[01] UPON FURTHER INVESTIGATION; FOUND TO BE OUT OF LIMIT AS PER SRM 53-30-15-1A-1. REPAIR BY REPLACEMENT.;[02] UPDATED STEP 4;[03] UPDATED STEP 5;[04] REPLACED FWD CARGO BAY SUB THRESHOLD IAW SRM 51-40-02 AND DWG 143A8330 REV A;[05] VERIFIED COMPLETION CORRECTIVE ACTION 4 AND MEASUREMENT TABLE.
CRACKED VAPOR BARRIER IN THE MAIN WHEEL WELL BS663 LBL15 WL147. MARKED <[01]. CRACKED VAPOR BARRIER BS663 LBL15 WL147 WAS REPAIRED IAW SRM 51-70-04-2R-10;[02] VERIFIED CORRECTIVE ACTION.
AFT CARGO FWD SCUFF PLATE IS CRACKED <[01]. WELDED THE CORNER SCUFF PLATE USING ER4043 FILLER ROD LOT NUMBER 1131216 PER SRM 53-60-15-2R-1 PARA 4.B.(4). REFERRED TO BAC 5975. EQUIPMENT USED; WELDING MACHINE I.D. 10583; CAL DATE 01/2025; APPLIED CHEMICAL CONVERSION COATING ON SCUFFPLATE PER SOPM 20-43-03; APPLIED PROTECTIVE COATING TO INNER SURFACE OF SCUFFPLATE PER AMM 51-21-72-370-804. SCUFFPLATE WILL BE PREPPED AND INSTALLED ON CUSTOMER CARD TTG8Q00Y5CAP; [02] VERIFIEC CORRECTIVE ACTION.
CUSTOMER REQUEST: DOUBLER AT BS 407 BETWEEN S-1 AND S-2L REQUIRES REMOVAL AND REPAIR DOUBLER AT BS 407 STR 1 - STR 2L/H <[01]. `THE DAMAGE WAS REPAIRED PER EA 25-153-00120. CONTINUED AIRWORTHINESS REQUIREMENTS ARE TRACKING ON EA 25-153-00120-DTI.' ENSURE THE 'EA-GENERAL' REPAIR REFERENCE IS SELECTED.; [02] CARD COMPLETED; [03] CARD COMPLETED; [04] RII STEPS COMPLETED.
R1 DOOR SLIDE GIRT IS NOT SECURED WITH VELCRO<[01] RE-SECURED R1 DOOR SLIDE GIRT WITH VELCRO PER AMM 25-66-01.
KEEL BEAM ACCESS PANEL 192E FWD RH ATTACH HANGAR BRACKET IS CRACKED.<[01] REMOVED AND REPLACED KEEL BEAM ACCESS PANEL 192E FWD R/H ATTACH HANGER BRACKET PER SRM 51-40-02
LEFT OVERWING EMERGENCY LIGHTS INOP<[01] REMOVED AND REPLACED LEFT OVERWING EMERGENCY LIGHTS PSU BATTERY PACK. TEST OK. REF AMM. 33-51-06.
AFT CEILING EMERGENCY EXIT SIGN BROKEN<[01] 01 - REMOVED AND REPLACED PER [AMM 33-51-01-960-802-NG (EXIT SIGN - LIGHT ASSEMBLY REPLACEMENT - PERMANENT)]
CUSTOMER WALK - R-2 DOOR AFT GIRT BAR FLOOR FITTING LOOSE.<[01] RESECURED R 2 DOOR AFT GIRT BAR FLOOR FITTING AS PER REF B737AMM 25-66-01-000-804;[02] VERIFIED 1.
PER CUSTOMER WALK- L-1 DOOR AFT ASSIST HANDLE LOOSE.<[01] SECURED L-1 DOOR AFT ASSIST HANDLE AS PER AMM 25-21-31-420-802;[02] VERIFIED 1.
R2 DOOR EXTERIOR EMERGENCY LIGHT INOP.<[01] RECONNECTED R2 DOOR EXTERIOR EMERGENCY LIGHT AS PER REF B737 AMM 33-51-04-960-801. TEST OK.;[02] VERIFIED STEP#1
SEVERAL EMERGENCY LIGHTS FAILED OPERATIONAL TEST THROUGHOUT THE CABIN.<[01] REMOVED AND REPLACED AT LOCATIONS M1673; M1670 AND M1669 PERFORMED OPERATIONAL TEST NORMAL AS PER REF B737 AMM 33-51-06-960-805;[02] CORRECTION FOR STEP # 1 REMOVED AND REPLACED EMERGENCY BATTERY PACK AT LOCATIONS M1673; M1670 AND M1669 PERFORMED OPERATIONAL TEST NORMAL AS PER REF B737 AMM 33-51-06-960-805;[03] VERIFIED 2.
LH HORIZONTAL STABILIZER PANEL 333AT TRACK ASSY FOUND CRACKED<[01] REMOVED PANEL 333AT AT LT HORIZONTAL STABILIZER FOR ACCESS TO DAMAGE IN AS PER B 737-700 SRM 51-40-02-0G-0;[02] REMOVED KEYWORD TRACK AT LT HORIZONTAL STABILIZER OF UPPER SIDE FOR DAMAGE IN AS PER B 737-700 SRM 51-40-02-0G-0;[03] RECEIVED NEW KEYWORD TRACK P/N 181A8060-15 PO# 1728471;[04] LOCATED AND DRILLED NEW KEYWORD TRACK AT LT HORIZONTAL STABILIZER AT UPPER SIDE IN AS PER B 737-700 SRM 51-40-05-0G-0;[05] VERIFIED 1-4. OK TO INSTALL NEW TRACK.;[06] INSTALLED NEW TRACK AT LT HORIZONTAL STABILIZER AT UPPER SIDE IN AS PER B 737-700 SRM 51-40-02-0G-0;[07] VERIFIED 6.;[08] OK TO INSTALL/CLOSE ACCESS PANEL 333AT.;[09] INSTALLED PANEL 333AT AT LT HORIZONTAL STABILIZER FOR ACCESS TO DAMAGE AS PER B 737-700 SRM 51-40-02-0G-0;[10] (FINAL) REMOVED AND REPLACED LH HORIZONTAL STABILIZER PANEL 333AT TRACK ASSY AS PER SRM 51-40-02-0G-0.;[11] VERIFIED STEPS#9 AND #10.
COCKPIT 1ST OBS SEAT BOTTOM CRACKED ON RIGHT LWR SURFACE. 8-50<[01] REMOVED FLIGHT DECK 1ST OBS. SEAT AS PER B737 AMM 25-1102-000-801;[02] ACCOMPLISHED REPAIR DOUBLER TO 1ST OBSERVER SEAT AS PER EA-M-22-125-00561; WORK T/C: TTG8Q00HW8W5.;[03] VERIFIED AND INSPECTED STEP #1 AND #2.;[04] OK TO REINSTALL 1ST OBS SEAT.;[05] REINSTALLED FLIGHT DECK 1ST OBSERVER SEAT AS PER B737 AMM 25-11-02-400-801.;[06] VERIFIED 5.
AFT LH WINDSCREEN : BATTERIES AT EMERGENCY FLASHLIGHTS DO NOT WORK (2 EACH)<[01] FLASHLIGHT BATTERIES AT AFT LH WINDSCREEN REMOVED AND REPLACED IAW CMM 25-60-02;[02] VERIFIED STEP 1.
FWD LH WINDSCREEN : BATTERIES AT EMERGENCY FLASHLIGHTS DO NOT WORK (2 EACH)<[01] FLASHLIGHT BATTERIES AT FWD LH WINDSCREEN REMOVED AND REPLACED IAW CMM 25-60-02;[02] VERIFIED STEP 1.
F/O FWD I/B SEAT TRACK HAS CORROSION ON LWR SURFACE. 8-36<[01] RECEIVED PART; NEW TRACK INSTALLED ON TASK CARD TTG8Q001YDLC.;[02] VERIFIED 1;
CAPT. FWD O/B SEAT TRACK HAS CORROSION ON LWR SURFACE. 8-35<[01] RECEIVED PART; NEW TRACK INSTALLED ON TASK CARD TTG8Q001YDLC;[02] VERIFIED 1;
F/O FWD O/B SEAT TRACK HAS CORROSION ON LWR SURFACE. 8-34<[01] RECEIVED PART; NEW SEAT TRACK INSTALLED ON TASK CARD TTG8Q001YDLC.;[02] PARTS TRANS ACTION;[03] FINAL INSPECTION; RECEIVED NEW SEAT TRACK. WILL BE INSTALL ON TTG8Q001YDLC.
LEFT OB CABIN SEAT TRACK HAS EXFOLIATING CORROSION BS 375. 8-26<[01] REMOVED FASTENERS FOR ACCESS TO REMOVE SEAT TRACK CORROSION PER B737-700 SRM 51-40-02-0G-0.;[16] VERIFIED STEP NO15. (FINAL) REMOVED CORROSION AT LEFT O/B CABIN SEAT TRACK BS 375 PER B737-700 SRM 51-10-02-0G-0. EVALUATED AREA; ORIGINAL MATERIAL 0.230'; MATERIAL REMOVED 0.045'; MATERIAL REMAINING 0.185'; MAXIMUM ALLOWABLE AT THE BOTTOM OF THE TRACK 0.040'; FOUND OUT OF LIMITS PER B737-700 SRM 53-00-52-1A-1 FIG. 103 A-A AND BAC1520-2789. TOOL USED B/C: 170642; CAL. DATE: 10/12/2022; CAL. DUE: 10/12/2023. REMOVED AND REPLACED SEAT TRACK PO#1792296 AS PER SRM 51-40-02-0G-0 AND IPC 53-42-11-17A.
RT BS 663 VAPOR BARRIER CRACK RBL 45.<[01] MEASUREMENTS;[02] PERFORMED VISUAL INSPECTION ON R/H VAPOR BARRIER AND FOUND CRACK OF 9' PER B737 NDTM 51-05-01;[03] PERFORMED STOP DRILL SIZE 0.25 DIAMETER AT THE END OF THE CRACK PER B737 SRM 57-10-10-2R-2 STEP 6.B;[04] PREPARED DAMAGED AREA ON VAPOR BARREIR FOR REPAIR PER B737 SRM 51-70-04-2R-10 AND 51-70-04-2R-0 PARAGRAPH 4.E;[05] VERIFIED STEP # 1;2; 3 AND 4;[06] OK TO INSTALL REPAIR;[07] REPAIRED R T BS 663 VAPOR BARRIER AS PER B737 SRM 51-70-04-2R-10 MATERIAL USED PO.1800112 AND PO.1690463;[08] VERIFIED STEP 7. OK TO APPLY TOP COAT.;[09] APPLIED PRIMER AND TOPCOAT ON RT VAPOR BARRIER REF B 737 AMM 21-21-81-370-801 AND 51-21-72-370-804;[10] LOCATED AND DRILLED VAPOR BARRIER AT BS 663 RBL 45 PER REF SRM 51-40-05-0G-0.;[11] VERIFIED STEPS #9 AND #10.;[12] FINAL INSPECTION; VAPOR BARRIER REPAIRED. ALL WORK PERFORMED.;[13] INSTALLATION OF VAPOR BARRIER AT STA 663 RBL 45 WILL BE ACCOMPLISH ON TASK CARD #TTG8Q00HL9HJ.;[14] ADD TO STEP #12. <BR> INSTALLATION OF VAPOR BARRIER AT STA 663 RBL 45 WILL BE ACCOMPLISH ON TASK CARD #TTG8Q00HL9HJ.
RIGHT HORIZONTAL STILIZER RIB 4 CRACKED AT STIFFENER 2 LOWER RADIUS.<[01] REMOVED THE DAMAGE PART OF THE RIB 4 STIFFENER 2 LOWER RADIUS AS SHOW IN FIG. 202 PARA.4 LETTER B REF. SRM 55-10-09-2R-4 REPAIR 4;[02] PERFORMED HFEC INSP ON REWORKED; IAW B 737 NDT PART 6 51-00-00 PROCE 23. TOOL NORTEC 600. BC 166316. CALIB DUE 10-17-23. NO CRACKS FOUND.;[03] PERFORMED HFEC ROTO INSP ON FASTENER OPEN HOLES NEAR TO REWORKED AREA; IAW B 737 NDT PART 6 51-00-00 PROCE 16. TOOL NORTEC 600. BC 166316. CALIB DUE 10-17-23. NO CRACKS FOUND.;[04] VERIFIED STEP # 1;[05] LOCATED AND DRILLING PARTS OF THE REPAIR OF KIT P/N 55100003-01 PO#1792296 ON THE RIB 4 OF STIFFENER 2 LOWER RADIUS REF. SRM 55-10-09-2R-4 REPAIR 4 LETTERS (G;H;I;J);[06] VERIFIED STEP #5.<BR> OK TO TREAT AND PRIME DRILLED HOLES AND REPAIR PARTS AND AREA.;[07] (RII) PERFORMED A GENERAL VISUAL INSPECTION (GVI) OF ALL AREAS WITHIN THE REPAIR AREA; (INCLUDING UNDERLYING STRUCTURE) FOR CORROSION; EXISTING REPAIR OR ANY OTHER DEFECTS.;[08] APPLIED TREAT AND PRIMER TO PARTS OF THE REPAIR AND THE RIB 4 OF THE STIFFENER 2 LOWER RADIUS REF. SRM 55-10-09-2R-4 REPAIR 4 PARA. 4 LETTERS (K;L);[09] ADD TO STEP #7.<BR> PER REF. SRM 55-10-09-2R-4 STEP 4 E.;[10] (RII) VERIFIED STEP #8.<BR> OK TO INSTALL NEW REPAIR PARTS.;[11] INSTALLED REPAIR ON THE RIB 4 STIFFENER 2 LOWER RADIUS REF. SRM 55-10-09-2R-4 REPAIR 4 PARA. 4 LETTERS (M;N;O;P;Q;R);[12] (RII) FINAL INSPECTION; RIB REPAIR ACCOMPLISHED.
AFT CARGO FLOOR SUPPORT 22' RIGHT 'Z' CHANNEL IS CORRODED AT B/S 727E-767<[01] FOUND EXFOLIATED CRACKED CORROSION AT AFT CARGO FLOOR SUPPORT Z-CHANNEL PER REF SRM 51-10-02-0G-0;[02] LOCATED AND DRILLED NEW R/H Z-CHANNEL FROM STA 727 TO 767 PER REF SRM 51-40-05-0G-0 MATERIAL USED: BAC1496-377 7075 T6 P.O.: 1782284;[03] EDIT STEP #1 : FOUND EXFOLIATED CRACKED CORROSION AT AFT CARGO FLOOR SUPPORT R/H Z CHANNEL STA 727E-767 OUT OF LIMITS PER SRM 53-00-53-1A-2;[04] VERIFIED AND INSPECTED STEP #2 AND #3.;[05] TREATED AND PRIMED NEW R/H Z CHANNEL STA 727-767 PER AMM 51-21-41-370-803 AND AMM 51-21-72-370-804;[06] VERIFIED STEP #5.<BR> OK TO INSTALL NEW NUT PLATES.;[07] INSTALLED NEW FASTENER NUTPLATES AT NEW R/H Z CHANNEL STA 727-767 PER SRM 51-40-02-0G-0;[08] VERIFIED STEP #7. NEW FASTENER NUT PLATES INSTALLED.;[09] FINAL INSPECTION; WORK PERFORMED.
AFT CARGO FLOOR SUPPORT 22' RIGHT 'Z' CHANNEL IS CORRODED AT B/S 727C-727E<[01] AFT CARGO R/H Z CHANNEL WILL BE REPLACED FROM STA 727-767 FOR WORK ACCOMPLISHED REFERENCE TASK CARD #TTG8Q00HKAET;[02] VERIFIED STEP #1.
FLOOR PNL 242SF HAS CRACK ON UPPER SURFACE. 8-25<[01] RECEIVED NEW PANEL 242SF PO#2005895. PANEL WILL BE INSTALLED ON TTG8Q00H2URQ.;[02] VERIFIED AND INSPECTED STEP #1.
LH VAPOR BARRIER SEAL RETAINER FOUND CRACKED<[01] RECIEVED; LOCATED AND DRILLED NEW L/H VAPOR BARRIER SEAL RETAINER PN: 111A1512U1 PO:1792296 PER REF SRM 51-40-05-0G-0.;[02] TREATED AND PRIMED NEW HOLES PER REF AMM 51-21-41-370-803 AND AMM 51-21-72-370-804;[03] FINAL INSPECTION; VERIFIED STEPS #1 AND #2.
AFT CARGO FLOOR SUPPORT 22' LEFT 'Z' CHANNEL IS CORRODED AT B/S 727-727B<[01] FOUND EXFOLIATED CRACKED CORROSION AT AFT CARGO FLOOR SUPPORT L/H Z CHANNEL STA 727-727B PER SRM 51-10-02-0G-0;[02] LOCATED AND DRILLED NEW L/H Z CHANNEL FROM STA 727- 847 PER REF SRM 51-40-05-0G-0 MATERIAL USED: BAC 1496-377 7075 T6 P.O:1782284;[03] EDIT STEP #1 : FOUND EXFOLIATED CRACKED CORROSION AT AFT CARGO FLOOR SUPPORT L/H Z CHANNEL STA 727-727B OUT OF LIMITS PER SRM 53-00-53-1A-2;[04] VERIFIED AND INSPECTED STEP #2 AND #3.;[05] TREATED AND PRIME REWORKED AREA PER AMM 51-21-41-370-803 AND AMM 51-21-72-370-804;[06] EDIT STEP #5 : TREATED AND PRIME NEW L/H Z CHANNEL STA 727 TO 847 PER AMM 51-21-41-370-803 AND AMM 51-21-72-370-804;[07] VERIFIED STEP #6.<BR> OK TO INSTALL NEW FASTENER NUT PLATES.;[08] INSTALLED NEW FASTENER NUTPLATES AT NEW L/H Z CHANNEL STA 727-847 PER SRM 51-40-02-0G-0;[09] FINAL INSPECTION; WORK PERFORMED.
AFT CARGO FLOOR SUPPORT 22' LEFT 'Z' CHANNEL IS CORRODED AT B/S 77B-727E<[01] AFT CARGO L/H Z CHANNEL WILL BE REPLACED FROM STA 727-847 FOR WORK ACCOMPLISHED REFERENCE TASK CARD # TTG8Q00HKADG;[02] VERIFIED STEP #1.
RIGHT 'Z' CHANNEL AT FWD END B/S 727 ATTACHMENT IS BROKEN<[01] AFT CARGO R/H Z CHANNEL WILL BE REPLACED FROM STA 727-767 FOR WORK ACCOMPLISHED REFERENCE TASK CARD # TTG8Q00HKAET;[02] FINAL INSPECTION; AFT CARGO R/H Z CHANNEL WILL BE REPLACED FROM STA 727-767 FOR WORK ACCOMPLISHED REFERENCE TASK CARD # TTG8Q00HKAET.
LH VAPOR BARRIER SUPPORT BRACKET FOUND CRACKED AROUND FASTENER HOLE<[01] RECEIVED NEW BRACKET P/N 276A9183-5 AND LOCATED AND DRILL PER REF SRM 51-40-05-0G-0;[02] TREATED AND PRIME NEW FASTENER HOLES; PER REF AMM 51-21-41-370-803 AND AMM 51-21-72-370-804;[03] OK TO INSTALL NEW BRACKET;[04] VERIFIED. STEP 2;[05] INSTALLED SUPPORT BRACKED AT LH VAPOR BARRIER PER REF DWG NUMBER 111A1000;[06] VERIFIED STEP # 5
RT WING TRAIL EDGE RIB WBL 201.90 HAS AFT UPPER FITTING CRACKED THRU. 8-24<[01] REMOVED AND REPLACED AFT UPPER FITTING AT RT WING TRAIL EDGE RIB WBL 201.90 PER REF SRM-51-40-02-0G-0.;[02] FINAL INSPECTION; T/E RIB REPLACED.
PASSENGER CABIN FLOOR PANEL #241XF; UPPER SURFACE DELAMINATED DOT 223-PCF241XF.<[01] RECEIVED NEW PANEL 241XF; PO#2005897. PANEL WILL BE INSTALLED ON TTG8Q00H2SLP.;[02] VERIFIED AND INSPECTED STEP #1.
AFT CARGO FLOOR SUPPORT 22' LEFT 'Z' CHANNEL IS CORRODED AT B/S 767-807<[01] AFT CARGO L/H Z CHANNEL WILL BE REPLACED FROM STA 727-847 FOR WORK ACCOMPLISHED REFERENCE TASK CARD # TTG8Q00HKADG;[02] VERIFIED STEP #1.
COMP- REPAIR LH VAPOR BARRIER CRACK<[01] MEASUREMENTS.;[02] REMOVED THE DAMAGED PLIES AND PREPARED DAMAGED AREA TO APPLY THE GLASS FABRIC REPAIR PLIES; DRILLED 0.25 INHC DIAMETER STOP HOLES AT THE CRACK END. REF B737 SRM 51-70-04-2R-10 PARAGRAP 4 AND SRM 57-10-10-2R-2 PARAGRAPH 3 A.;[03] VERIFIED REMOVAL OF THE DAMAGED PLIES AND PREPARED DAMAGED AREA TO APPLY THE GLASS FABRIC REPAIR PLIES; DRILLED 0.25 INHC DIAMETER STOP HOLES AT THE CRACK END. REF B737 SRM 51-70-04-2R-10 PARAGRAP 4 AND SRM 57-10-10-2R-2 PARAGRAPH 3 A. OK TO INSTALL THE REPAIR.;[04] REPAIRED DAMAGED AREA AND TAP TEST INSPECTION AT LH VAPOR BARRIER AS PER B737SRM 51-70-04-2R-10 AND NTM 51-05-01 MATERIAL USE RESIN PO#1800112 FIBERGLASS PO#1690463;[05] VERIFIED STEP NO 4. OK TO DRILL HOLES.;[06] LOCATED AND DRILLED REPAIRED VAPOR BARRIER PER REF SRM 51-40-05-0G-0;[07] PRIMER AND TOPCOAT APPLICATION REF TASKCARD #TTG8Q00HH5FG;[08] VERIFIED 6-7.;[09] CORRECTION TO STEP #5.<BR>RII<BR>VERIFIED STEP NO 4. OK TO DRILL HOLES.;[10] (RII) FINAL INSPECTION; WORK PERFORMED.
EGPR INTERNAL DOUBLER CRACKED AT FWD LOWER CORNER.<[01] REMOVED PAINT BY STRIPPING AT FUSELAGE SKIN R/H SIDE EGPR AREA REF B737-700 AMM 51-21-11-150-810.; LOCATED AND DRILLED NEW EGPR INTERNAL DOUBLER REF B737-700 SRM 51-40-05-0G-0.;[07] TREATED AND PRIMED DRILLED HOLES ON NEW EGPR INTERNAL DOUBLER REF B737-700 SRM 51-20-01-0G-0.;[08] VERIFIED STEPS 6 AND 7. OK TO INSTALL NEW EGPR DOUBLER.;[09] MIXED BMS 5-95 SEALANT 22:00 2/1/23. SQUEEZE OUT TIME BY 06:00 2/5/23.;[10] INSTALLED 90% OF FASTENERS AT EGPR INTERNAL DOUBLER REF B737-700 SRM 51-40-02-0G-0 AND DWG# 146A0640.;[11] COMPLETED INSTALLATION OF EGPR INTERNAL DOUBLER REF B737-700 SRM 51-40-02-0G-0 AND DWG# 146A0640.;[12] VERIFIED STEP # 10 AND 11;[13] VERIFIED STEP #9; SQUEEZE OUT TIME 100%; ALL FASTENERS INSTALLED.;[14] CORRECTION STEP 11 : COMPLETED INSTALLATION OF EGPR INTERNAL DOUBLER REF B737-700 SRM 51-40-02-0G-0 AND DWG# 141A0640 AND 141A3702.;] APPLIED TOP COAT AT FUSELAGE SKIN ON EGPR AREA REF B737-700 AMM 51-21-73-370-803.;[18] VERIFIED DRAWINGS STEP 14-15.;[19] VERIFIED 16-17.;[20] REMOVED AND REPLACED EGPR INTERNAL DOUBLER REF B737-700 SRM 51-40-02-0G-0 AND DWG# 141A0640.;[21] FINAL 20.
RIGHT HORIZONTAL STABILIZER RIB 4 CRACKED AT STIFFENER 3 LOWER RADIUS.(51-025)<[01] REMOVED THE DAMAGE PART OF THE RIB 4 AT STIFFENER 3 LOWER RADIUS AS SHOW IN FIG. 202 PARA.4 LETTER B REF. SRM 55-10-09-2R-4 REPAIR 4;[02] VERIFIED 1. ACCOMPLISHED GVI OF REPAIR AREA PER SRM 55-10-09-2R-4 STEP 4.E. NO OTHER DEFECTS NOTED.;[03] PERFORMED HFEC INSP. OF THE CUT EDGES OF THE STIFFENER AND WEB IAW B737 NDT PART 6; 51-00-00; PROCEDURE 23. NO CRACKS NOTED<BR>TOOL: NORTEC 600 B/C: 166317 DUE: 10/31/23;[04] PERFORMED HFEC ROTO INSP. OF ALL EXISTING FASTENER HOLES WITHIN THE REPAIR AREA ON RIB#4; STIFFENER #3 IAW B737 NDT PART 6; 51-00-00; PROCEDURE 16. NO CRACKS NOTED <BR>TOOL: NORTEC 600 B/C: 166317 DUE: 10/31/23<BR>TOOL: OLYMPUS MINIMITE B/C: 172542 DUE: 09/02/23;[05] LOCATED AND DRILLING PARTS OF THE REPAIR OF KIT P/N 55100003-01 PO# 1728471 ON THE RIB 4 OF STIFFENER 3 LOWER RADIUS REF. SRM 55-10-09-2R-4 REPAIR 4 PARA. 4 LETTERS (G;H;I;J);[06] VERIFIED LOCATION AND DRILLING IN STEP # 5;[07] OK TO ALODINE AND PRIME REPAIR AREA.;[08] APPLIED TREAT AND PRIME TO PARTS OF THE REPAIR AND THE RIB 4 OF THE STIFFENER 3 LOWER RADIUS REF. SRM 55-10-09-2R-4 REPAIR 4 PARA. 4 LETTERS (K;L);[09] VERIFIED STEP # 8;[10] OK TO INSTALL REPAIR PARTS;;[11] INSTALLED REPAIR ON THE RIB 4 STIFFENER 3 LOWER RADIUS REF. SRM 55-10-09-2R-4 REPAIR 4 PARA. 4 LETTERS (M;N;O;P;Q;R);[12] VERIFIED STEP # 11;[13] JOB IS COMPLETE;[14] VERIFIED STEPS 5; 7;8; 10 AND 11 NOTE: RII
RT BS 663 VAPOR BARRIER UPPER SUPPORT ANGLE CRACKED.<[01] BEGAN REMOVED FASTENERS AT RT VAPOR BARRIER UPPER SUPPORT ANGLE BS 663 IN AS PER SRM 51-40-02-0G-0;18] COMPLETED INSTALLATION OF NEW REPAIR PARTS OF RT UPPER SUPPORT WING CENTER SECTION VAPOR BARRIER FROM RBL 5.00 TO RBL 65.00 IN AS PER SRM 51-40-02-0G-0 AND 57-10-10-2R-5 FIG 202 SHEET 3;[19] REINSTALLED SUPPORT STRAP; REMOVED ON STEP 2 FROM RBL 45.00 TO RBL 65.00 IN AS PER SRM 51-40-02-0G-0 AND 57-10-10-2R-5;[20] COMPLETED PERMANENT REPAIR VAPOR BARRIER UPPER SUPPORT ANGLES AT RT STA 663.75 AS PER B737-700 SRM 57-10-10-2R-5 FIG 202 SHEET 3.;[21] (RII) VERIFIED STEPS #16; #17; #18; #19. SQUEEZE OUT TIME AND 100% FASTENER INSTALLATION AND STRAP REINSTALLATION.;[22] (RII) FINAL INSPECTION; VAPOR BARRIER UPPER SUPPORT ANGLE REPAIRED ACCOMPLISHED. WORK PERFORMED.
L/W REAR SPAR FIXED T/E DEFLECTION CONTROL RIB PANEL O/B SUPPORT ATTACHMENT POINT LOCATION ' A' ELONGATED HOLES ;EXCESSIVE PLAY MKD DOTS<[01] REMOVED HARDWARE AT L/W REAR SPAR FIXED T/E DEFLECTION CONTROL RIB PANEL O/B SUPPORT ATTACHMENT POING LOCATION 'A'AS PER B737-700 SRM 51-40-02-0G-0.[16] REMOVED AND REPLACED L/W REAR SPAR FIXED T/E DEFLECTION CONTROL RIB BEAM AS PER B737 SRM 51-40-05-0G-0.;[17] FINAL INSPECTION; REAR SPAR FIX T/E DEFLECTION CONTROL RIB BEAM REPLACED AND ADJUSTED.
MID FORWARD BODY FAIRING PANEL #191D; ALL FASTENER HOLES ELONGATED OR/AND SURFACE PROTRUDING DOT 223-MFF191D.<[01] PERFORMED VISUAL INSPECTION ON PANEL #191D AND FOUND NO ENTRY OF WATER; OIL; FUEL; OR OTHER UNWATED MATERIAL PER B737 NDTM 51-05-01;[02] PREPARED DAMAGED FASTENER HOLES FOR REPAIR ON PANEL #191D PER B737 SRM 51-70-04-2R-9 PARA 4.C;[03] VERIFIED STEP # 1 AND 2;[04] OK TO REPAIR;[05] REPAIRED PANEL #191D AT DAMAGED FASTENER HOLES PER B737 SRM 51-70-04-2R-9 PARA D-G. MATERIALS USED RESIN P/O#1800112 CLOTH P/O#1690463;[06] VERIFIED STEP # 5;[07] OK TO PAINT REPAIRED AREA;[08] PAINTED PANEL #191D PER B737 AMM 51-21-99-300-801. MATERIALS USED BLUEHEART PAINT P/O#1768107; WHITE PAINT P/O#1779132;[09] FINAL INSPECTION; VERIFIED STEP #8. WORK PERFORMED.
L/W REAR SPAR FIXED T/E LOWER PANEL 551GB I/B ATTACHED ANGLE FWD FASTENER HOLE ELONGATED AND BUSING ; BOLT ; NUT MISSING MKD DOT<[01] REMOVED DAMAGE ANGLE AT LT WING T/E LOWER PANEL 551GB I/B SIDE PER REF B737 SRM 51-40-02-0G-0;[02] LOCATED AND DRILLED NEW ANGLE AT LT WING T/E LOWER PANEL 551GB I/B SIDE PER REF B737 SRM 51-40-05-0G-0;[03] VERIFIED STEPS #1 AND #2; LOCATED AND DRILLED NEW ANGLE. <BR> OK TO INSTALL NEW ANGLE.;[04] INSTALLED NEW ANGLE AT LT WING T/E LOWER PANEL 551GB I/B SIDE PER REF B737 SRM-51-40-02-0G-0.;[05] VERIFIED STEP #4; NEW ANGLE INSTALLED.;[06] REMOVED PREVIOUSLY INSTALLED ANGLE PART3 115A2759-13 REF B737-700 SRM 51-40-02-0G-0.;[07] LOCATED AND DRILLED NEW ANGLE PART# 115A2759-5 REF B737-700 SRM 51-40-05-0G-0 AND DWG# 115A2714.;[08] VERIFIED STEPS #6 AND #7; LOCATED AND DRILLED NEW ANGLE. <BR> OK TO INSTALL NEW ANGLE.;[09] INSTALLED NEW ANGLE AT PANEL # 551GB REF B737-700 SRM 51-40-02-0G-0 AND DWG# 115A2714.;[10] VERIFIED STEP #9; INSTALLED NEW ANGLE P/N: 115A2759-5.;[11] INSTALLED NEW BOLT AND NUT MISSING AT I/B FWD ATTACHED ANGLE REF B737-700 SRM 1-40-02-0G-0 AND DWG# 115A2714.;[12] CORRECTING STEP 11: SRM REF 51-40-02-0G-0.;[13] VERIFIED STEPS #11 AND #12.;[14] REMOVED AND REPLACED FIXED T/E LOWER PANEL 551GB I/B ATTACHED ANGLE AND INSTALLED MISSING BOLT AND NUT REF B737-700 SRM 51-40-02-0G-0 AND DWG# 115A2714.;[15] FINAL 14.
CRACK FOUND AT LEFT HORIZONTAL STABILIZER LOWER IN-SPAR SKIN AT STATION 193.90 ; 17' FROM FRONT SPAR ; I/B ROW . CRACK LENGTH : 0.75' CRACK FOUND AT LEFT HORIZONTAL STABILIZER LOWER IN-SPAR SKIN AT STATION 193.90 17' FROM FRONT SPAR I/B ROW .CRACK LENGTH : 0.75'.<[01] REMOVED PAINT BY STRIPPING SKIN CRACK AREA AT LEFT HORIZONTAL STABILIZER LOWER IN- SPAR SKIN AT STA 193.90; 17' FROM FRONT SPAR; I/B ROW AS PER B737-700 AMM 51-21-11-150-810.[15] INSTALLED REPAIR PARTS AT LT HORIZONTAL STAB LOWER SKIN STA 193.90 REF B737-700 SRM 55-10-01-2R-11 FIG 204.;[16] VERIFIED 14-15.;[17] APPLIED TOP COAT AT REPAIR AREA REF B737-700 AMM 51-21-73-370-803.;[18] ACCOMPLISHED PERMANENT REPAIR AT LT HORIZONTAL STAB LOWER SKIN STA 193.90 REF B737-700 SRM 55-10-01-2R-11 FIG 204.;[19] FINAL INSPECTION; LOWER IN-SPAR SKIN REPAIR. ALL WORK PERFORMED.
SEAT 11F RECLINES IN FRONT OF EXIT-SEAT 11F UNUSABLE SEAT 11F RECLINES IN FRONT OF EXIT-SEAT 11F UNUSABLE*** DO NOT CARRY ***<[01] ADJUSTED SEAT 11F HYDROLOCK TO DISABLE RECLINE IAW AMM 25-22-00. THIS CLEARS MEL.
ROW 12C TRAY TABLE WILL NOT STAY UP & PAX UNIT LIGHT FIXTURE MOVES.<[01] ADJUSTED TRAY TABLE @ 12C PER SIP. 12C READING LIGHT ASSEMBLY FOUND TO BE SECURE; FOUND 12C AIR OUTLET TO BE DAMAGED AND LOOSE. R&R 12C PSU AIR OUTLET PER AMM 21-24-04.
FWD GALLEY MEGAPHONE RESTRAINT LOOSE / [01] R/R?D FWD GALLEY MEGAPHONE BRACKET PER S.I.P
FIRST OFICER'S SLIDING WINDOW FAILS EMERGENCY EXIT RELEASE HANDLE OPS CHECK. / [01] ADJUSTED FIRST OFFICERS SLIDING WINDOW EMERGENCY EXIT RELEASE MECHANISM PER M/M 56-12-11.
FOWARD ENTRY DOOR ESCAPE SLIDE DISLODGED FROM IT'S CONTAINER / [01] REMOUNTED FWD DOOR ESCAPE SLIDE IAW S.I.P.
AFT ENTRY DOOR EMERGENCY LIGHTS INOP / [01] REPLACED THE AFT L/H EMERGENCY LIGHT BATTERY PACK REF AMM 33-51-06. OPS CHECK GOOD
EMERGENCY LIGHT AFT OF L2 DOOR INOP / [01] R&R EMERGENCY LIGHT AFT OF L2 DOOR IAW AMM 33-51-04. OPS CHECK GOOD.
FWD CEILING EMERGENCY LIGHT INOP ; / [01] RELAMPED FWD CEILING AREA EMERGENCY LIGHT PER AMM 33-51-03. OPS CK GOOD
FWD ENTRY DOOR UPPER STRAP NEEDS ADJUSTMENT ; / [01] REPLACED ATTACH SCREW PER SIP
FSD ESCAPE SLIDE FELL FROM CLAM SHELL HOUSING ; FSD ESCAPE SLIDE FELL FROM CLAM SHELL HOSING / [01] REPACKED AND MOUNTED FSD ESCAPE SLIDE IAW AMM 25-66-01.
SUPPLEMENTAL INFORMATION: 193D PANEL HAS CRACKED HOLES / [01] REPLACED PANEL 193D PER AMM 53-51-21
SUPPLEMENTAL INFORMATION: 194E PANEL HAS CRACKED AND ELONGATED HOLES / [01] REPLACED PANEL 194E PER AMM 53-51-21
ON APPROACH CABIN AIR TEMPERATURE BECAME HOT. SMELL ACCOMPANIED THAT THROUGHOUT AIRCRAFT. AFTER LANDING; LEFT PACK TRIP OFF ILLUMINATED. ; / [01] C/W FUMES CONDITIONAL INSP IAW FIM 21-00 TASK 806; FOUND LH PACK CAUSING SMELL; OK TO CONTINUE PER MEL 21-1-01 SP1 AUTHORIZATION CODE 18262; [02] R&R LEFT HAND ACM PER AMM 21-51-04 REQUIRES CLAMP PART # BACC10CT2-400 ACM TO COLESSER BAG. REQUIRES LEAK CHECK AND OPS TO CLEAR MEL; [03] REF LOG PAGE 1651685 FOR WORK ACCOMPLISHED; REMOVED AND REPLACED LH ACM PER AMM 21-51-04. REQUIRES CLAMP ON BACC10CT2-400 ACM TO COALESCED BAG AND LEAK; OPS CHECK TO CLEAR MEL; [04] R&R CLAMP #1PACK ACM AT COALESCE BAG.OPS CHECH AND LEAK CHECK GOOD; [05] CERTIFIED
FWD SERVICE DOOR SLIDE GIRT NEEDS ADJUSTMENT AND CLIP TIGHTED ADJUSTED SLIDE GIRT AND TIGHTENED CLIP ON FWD SERVICE PER AMM256601
EMERGENCY LIGHT LENSE AND BEZEL BROKEN AT 16 D-E-F / OK TO CONTINUE PER MEL 25-10-01 SP1B TRACKING #70711
FWD SERVICE DOOR EXIT SIGN NOT INSTALLED / R/R RIGHT ASSY PER AMM 33-51-01
QA WALK*** R2 DOOR ESCAPE SLIDE SKIRT RUB SCUFF PLATE WHEN CLOSING. / ADJUSTED R2 DOOR SLIDE SKIRT RUB AS PER TASK CARD 8725-61-06
R1 DOOR RIDES HARD ON AFT UPPER LATCH RECEIVER WHEN CLOSING / PERFORMED R1 DOOR ADJUSTMENT PER B737 AMM 52-41-00-820-801 ALL OPS NORMAL PERFORMED PRESSURIZATIONAL LEAK TEST OF R1 DOOR REF B737 AMM 25-51-91-790-801; NO LEAKS FOUND
VERT STAB HAS ANGLE CRACKED ABOVE AND ON AFT SIDE OF FWD LEFT ATTACH LUG. / REMOVED AND REPLACED VERTICAL STAB LWR ANGLE ON FWD SIDE OF ATTACH LUG REF B737-700 SRM 51-40-02-0G-0 AND DWG #176A3101
CABIN PANEL 241 RF IS DELAMINATED AT AFT RIGHT HAND CORNER. / ACCOMPLISHED PERMANENT REPAIR AT CABIN FLOOR PANEL 241RF AFT RIGHT HAND CORNER PER REF B737 SRM 53-00-50-2R-9
AFT CARGO COMPARTMENT; SHROUD 142NWA FOUND DAMAGED DURING INSPECTION. / RECEIVED NEW SHROUD 142NWA FROM STOCK .INSTALLATION WILL BE COMPLETED CUSTOMER CARD # JPANEL-141-CLOSE .
CORROSION***ON LWR SURFACE OF LWR CTR WING SKIN AROUND 2 FWD BOLTS LBL 56 BS 541. / ACCOMPLISHED REPAIR OF CORROSION FOUND ON LWR SURFACE OF WING SKIN AROUND 2 FWD BOLTS LBL 56 BS 541 PER INSTRUCTIONS ON AAR RES-WI 2016690-11 REV IR AND SOUTHWEST EA 21-157-00233 REV IR. THIS IS AN INTERIM REPAIR AND MUST BE INSPECTED AT DEFINED INTERVALS.
FWD CARGO COMPARTMENT;GUSSET SUPPORT IS CRACKED AT STA 500D S-19LH. / REMOVED AND REPLACED GUSSET SUPPORT AT FWD CARGO COMP. AT STA 500D S-19LH AND TREATED ASS FASTENERS HOLES WITH ALODINE AND PRIME IN REF B737-700 SRM 51-40-02-0G-0; 51-20-01-0G-0 AND DWG# 143A7902.
FWD CARGO COMPARTMENT HAS CRACKED BRACKET AFT SIDE OF FRAME BS 500C S-26L. / REMOVED AND REPLACED BRACKET AT FWD CARGO COMP AT BS 500C; S-26L AND TREATED ALL FASTNERS HOLES WITH ALODINE AND PRIMER IN REF BB 737-700 SRM 51-40-02-0G-0; 51-20-01-0G-0 AND DWG # 143A7505; 51-40-05-0G-0
COCKPIT; CAPTIANS RACEWAYFOUND CRACKED. / REMOVED AND REPLACED COCKPIT; CAPTAINS RACEWAY WITH NEW RACEWAY AS PER REF B737-7 SRM 51-40-02-0G-0
RT WING UPPER T/E PNL AFT OF PYLON HAS CTR AFT RIB CRACKED AT FWD LWR BOLT HOLE. / REMOVED AND REPLACED CENTER AFT RIB AT RT. WING AFT OF PYLON IAW SRM 51-40-02-0G-0
FUSELAGE BULKHEAD FITTING LUG BS 1016 FOR VERTICAL STAB FRONT RIGHT ATTACHMENT HAS BUSHING OUT OF LIMITS. [0.8840'] [MAX ALLOWED 0.8835' TASK 55-30-00-200-801] / REMOVED AND REPLACED BUSHING AT FUSELAGE BULKHEAD FITTING LUG BS 1016 FOR VERTICAL STAB FRONT RIGHT ATTACHMENT AS PER EA 21-155-00122 REV IR RES 2016690-3A IR REV; VENDOR PREMIER AEROSPACE FABRICATED AND INSTALLED BUSHING RFF PO 1706834 ; PO 1707075
CABIN HAS CHORD CRACKED AT END RADIUS BS 312 S5L-S6L. / CUT OUT DAMAGE AT CABIN CHORD AT END RADIUS BS 312 S5L-S6L; PERFORMED HFEC AND ROTO INSP NO CRACK NOTE AS PER NTM PART 6 51-00-00 PROCEDURE 23; FABRICATED ANGLE REPAIR MAT USED 7075-0 0.063 CLAD PO #1668003; PERFORMED HEAT TREAT; CONDUCTIVITY AND HARDNESS INSP AS PER BAC5946 FOUND IN LIMITS; DRILLED; DE-BURRED; TREAT; PRIMER AND INSTALLED REPAIR PART AS PER REF B737-700 SRM 53-10-07-2R-1 FIG A REPAIR 1; PERFORMED FPI SOPM 20-20-02; SRM 51-40-05-0G-0; AMM 51-21-41-701; AMM
F/O AFT OB SEAT TRACK GOUGED ON EDGE. / REMOVED AND REPLACED F/O AFT O/B SEAT TRACK IAW B737 AMM 25-11-11-400-801.
CAPT AFT OB SEAT TRACK GOUGED ON EDGE. / REMOVED AND REPLACED CAPT AFT O/B SEAT TRACK IAW B737 AMM 25-11-11-400-801
AFT OF AFT CARGO COMPMT. BILGE SUPPORT BRACKET CRACKED AT S-26L STA 867 BELOW WASTE TANK SUPPORT POST MKD DOT 60-014 / REMOVED AND REPLACED AFT CARGO COMPARTMENT BILGE SUPPORT BRACKET AT S-26L STA 87 BELOW WASTE TANK SUPPORT IAW B737-700 SRM 51-40-02-0G-0. PART USED: PO # 1698700
FUSELAGE - BS 540 S-22L REF FIG 2 CIRCLE NOTE 1 AD 2019-11-06; EO 14516. CRACK INDICATION FOUND. REF B737 NDT PART 4 53-20-02. B/C19498. REQ. REMOVE FASTENERS AND PERFORM A OHEC PROCEDURE TO VERIFY CRACK INDICATION IAW B737 NDT PART 6; 51-00-00 PROC. 16. / ACCOMPLISHED FUSELAGE BS 540 S22L DRAG LINE AND SKIN REPAIR PER INSTRUCTIONS ON EO 5331-E-14519-NG
FWD CARGO COMPARTMENT;HAS CRACKED ANGLE AT STA 500C;S-25 LH. / REMOVED AND REPLACED ANGLE AT FWD CARGO COMP AT STA 500C STR26; LH AND TREATED FASTENERS HOLES WITH ALODINE AND PRIME IN REF B737-700 SRM 51-40-02-0G-0; 51-20-01-0G-0 AND DWG# 143A7505
FWD WET AREA UNDER FLOOR PANEL 221BF AT STA # 300 LBL-55 INNER WEB WITH A CRACK. DOT # 208-61 / DAMAGED INNER CHORD AT L1 DOOR ON FWD WET AREA IT WAS REPLACED ON N.R W197743
LOWER BODY FAIRING SUPPORT HAS DEEP CHAFE RBL 27 BS 663 -675. / REMOVED AND REPLACED NEW SUPPORT FRAME IAW B737-700 SRM 51-40-02-0G-0
VERTICAL STAB FRONT SPAR LEFT FUSELAGE BULKHEAD ATTACH FITTING HAS PITTING CORROSION ON AFT SIDE OF AFT LUG AROUND BUSHING. / REMOVED CORROSION FROM VERTICAL STAB FRONT SPAR LEFT FUSELAGE BULKHEAD ATTACH FITTING AFT SIDE FACE AND REPLACED BUSHING ON ATTACH FITTING AS PER EA 21-153-00132 IR AND RES 2016690-5 REV IR. OUTSIDE VENDOR PREMIER AEROSPACE FABRICATED BUSHING AND INSTALLED BUSHING PO 1706328 ; PO 1706834. THIS IS A INTERIM REPAIR AND MUST BE INSPECTED AT DEFINED INTERVAL. AND PO 1707077
**CORROSION** FWD WET AREA UNDER FLOOR PANEL 221DF INNER WEB ALONG L-1 DOOR CORRODED. DOT # 208-60 / CORROSION AT FWD WET AREA UNDER FLOOR PANEL 221DF INNER AREA OF L-1 DOOR FOUND LOCATED ON INNER CHORD (DOT 208-60). L1 DOOR INNER CHORD WILL BE REPLACED ON NR W197743
FWD CARGO COMPARTMENT;GUSSET SUPORT IS CRACKED AT STA 500D;S-19 RH. / REMOVED AND REPLACED GUSSET AT FWD CARGO COMP. AT STA 500D STR 19RH AND TREATED ALL FASTENERS HOLES WITH ALODINE & PRIMED IN REF B737-700 SRM 57-40-02-0G-0 AND DWG #143A7902; 51-20-01-0G-0
FWD CARGO COMPARTMENT FLANGE SUPPORT FLOOR PANEL HAS CORROSION AT STA 490 CUTOUT TO STA 500B S-26 RT.
AFT CABIN FLOOR STRUCTURE INTERCOSTAL CRACKED 2 EA PLACES BETWEEN BS 947.5 TO BS 927 BL-0 .MKD 126-32. / REMOVED INTERCOSTAL AT AFT CABIN FLOOR STRUCTURE BETWEEN STA 947.5 TO BS 927 BL-0 PER REF B737-700 SRM 51-40-02-0G-0. REMOVED AND REPLACED INTERCOSTAL'S CHORD PER REF B737-700 SRM 51-40-02-0G-0 AND DWG #147A5400. INSTALLED INTERCOSTAL AT AFT CABIN FLOOR STRUCTURE BETWEEN STA 947.5 TO BS 927 BL-0 PER REF B737-700 SRM 51-40-00-0G-0 AND DWG# 147A5400
FWD WET AREA BELOW FLOOR PANEL 222BF AT STA # 315 RBL-31 INTERCOSTAL HAS A CRACK. DOT # 208-57 / REMOVED AND REPLACED INTERCOSTAL AT FWD WET AREA BELOW FLOOR PANEL 222BF AT STA 315 RBL-31' AND LOCATED AND DRILL NEW INTERCOSTAL AND TREATED ALL FASTENERS HOLES WITH ALODINE AND PRIMED IN REF B737-700 SRM 51-40-05-0G-0 AND 51-20-01-0G-0 AND DWG # 141A5400
LOWER BODY FAIRING SUPPORT HAS DEEP CHAFE LBL 27 BS 663 -675. / AFTER EVLAUATION OF LOWER BODY FAIRING SUPPORT ATLBL 27BS 663-675; THE FRAME WAS FOUND OUT OF LIMITS IAW B737-700 SRM 53-40-71-1A-1. REMOVED ;REPLACED ;LOCATED AND DRILLED AND INSTALLED NEW FAIRING SUPPORT IAW B737-700 SRM 51-40-02-0G-0; SRM 51-40-05-0G-0; AND BOEING DWG#149A7216. MATERIAL USED: 149A7214-19; PO#1705074.
FWD PASSENGER CABIN FLOOR PANEL 221DF DELAMINATED. / THIS ITEM CLOSED; NEW PANEL WILL INSTALLED ON REFERENCE CUSTOMER CARD #JPANEL-221-CLOSE; PANEL HAS BEEN RECEIVED
LH FUSELAGE FIN TO BODY INTERFACE CLOSURE ANGLE IS WORN TO STA 1030.00 THRU STA 1132.02. / REMOVED AND REPLACED L/H FUSELAGE FIN TO BODY INTERFACE CLOSURE ANGLE STA 1030.00 THRU STA 1132.02 PER REF B737-700 SRM 51-40-02-0G-0 AND DWG #148A8300
L1 DOOR LOWER SILL INNER CHORD CRACKED AT FASTENER HOLE STA 312. / REMOVED AND REPLACED INNER CHORD AT L1 DOOR LOWER SILL BETWEEN STA 270 AND STA 360 LBL 55 WL 208 REF B737-700 SRM 51-40-02-0G-0 AND DWG #141A8110
RH FUSELAGE FIN TO BODY INTERFACE CLOSURE ANGLE IS WORN TO STA 1016.00 THRU STA 1006.00. / REMOVED ANDREPLACED R/H FUSELAGE FIN TO BODY INTERFACE CLOSURE ANGLE STA 1006 TO STA 1016 PER REF DWG 147A0030 AND B737-700 SRM 51-40-02-0G-0
LH FUSELAGE FIN TO BODY INTERFACE CLOSURE ANGLE IS WORN TO STA 1016.00 THRU STA 1006.00 / REMOVED AND REPLACED L/H FUSELAGE FIN BODY INTERFACE CLOSURE ANGLE STA 1006 TO STA 1016 PER REF DWG 147A0030 AND B737-700 SRM 51-40-02-0G-0
FWD PASSENGER CABIN FLOOR PANEL 221AF DELAMINATED. / RECEIVED FWD PASSENEGER CABIN FLOOR PANEL 221AF. INSTALLATION WILL BE ACCOMPLISHED IN CUSTOMER CARD #JPANEL-221-CLOSE
FWD PASSENGER CABIN FLOOR PANEL 221CF DELAMINATED. / RECEIVED FWD PASSENGER CABIN FLOOR PANEL 221CF. INSTALLATION WILL BE ACCOMPLISHED IN CUSTOMER CARD #JPANEL-221-CLOSE.
FWD PASSENGER CABIN FLOOR PANEL 221GF DELAMINATED. / RECEIVED FWD PASSENGER CABIN FLOOR PANEL 221GF; INSTALLATION WILL BE ACCOMPLISHED IN CUSTOMER CARD #JPANEL-221-CLOSE.
FWD PASSENGER CABIN FLOOR PANEL 221FF DELAMINATED. / RECEIVED FWD PASSENGER CABIN FLOOR PANEL 221FF; INSTALLATION WILLL BE ACCOMPLISHED IN CUSTOMER CARD #JPANEL-221-CLOSE
FWD PASSENGER CABIN FLOOR PANEL 221BF DELAMINATED. / RECEIVED CABIN FLOOR PANEL 221BF. INSTALLATION WILL BE ACCOMPLISHED ON T/C JPANEL-221-CLOSE
FWD PASSENGER CABIN FLOOR PANEL 221EF DELAMINATED. / RECEIVED FWD PASSENGER CABIN FLOOR PANEL 221FF. INSTALLATION WILL BE ACCOMPLISHED IN CUSTOMER CARD #JPANEL-221-CLOSE.
FWD PASSENGER CABIN FLOOR PANEL 222AF DELAMINATED. / RECEIVED FWD PASSENGER CABIN FLOOR 222AF. INSTALLATION WILL BE COMPLETED IN CUSTOMER CARD #JPANEL-222-CLOSE.
FWD PASSENGER CABIN FLOOR PANEL 222BF DELAMINATED. / RECEIVED FWD PASSENGER CABIN FLOOR 222BF. INSTALLATION WILL BE ACCOMPLISHED IN CUSTOMER CARD #JPANEL-222-CLOSE.
FWD PASSENGER CABIN FLOOR PANEL 222CF DELAMINATED. / RECEIVED FWD PASSENGER CABIN FLOOR 222CF. INSTALLATION WILL BE ACCOMPLISHED IN CUSTOMER CARD #JPANEL-222-CLOSE.
FWD PASSENGER CABIN FLOOR PANEL 222DF DELAMINATED. / RECEIVED FWD PASSENGER CABIN FLOOR PANEL 222DF; INSTALLATION WILL BE ACCOMPLISHED IN CUSTOMER CARD #JPANEL-222-CLOSE.
MAIN CABIN FLOOR SEAT TRACK CROWN AREA LBL-45.5 BS 520 WEAR MARK AT .MKD 126-031. / ACCOMPLISHED PERMANENT SEAT TRACK REPAIR AT MAIN CABIN BETWEEN STA 521.5 AND STA 500C+10.5' LBL 45.5 REF B737-700 SRM 53-00-52-2R-4 AND EA 1-A53-11779 REV 1
MAIN CABIN FLOOR SEAT TRACK CROWN AREA LBL-24.7 BS 520 WEAR MARK AT .MKD 126-030 / ACCOMPLISHED PERMANENT REPAIR AT MAIN CABIN SEAT TRACK BETWEEN STA 500C+10.5' AND STA 521.5 LBL 24.7 REF B737-700 SRM 53-00-52-2R-4
**CORROSION** FWD WET AREA STA # 344 LBL-62 UNDER FLOOR PANEL 221GF STRUCTURE HAS CORROSION. DOT # 208-53 / CORROSION FWD WET AREA STA 344 LBL 62 UNDER FLOOR PANEL 221GF LOCATE AT INNER CHORD L1 DOOR. INNER CHORD REPLACED ON NR W197743
FLIGHT DECK FLOOR WEB DAMAGE AT BS 260 / ACCOMPLISHED PERMAMENT FLIGHT DECK FLOOR WEB REPAIR REF EA 1-A53-33179 REV 1 BETWEEN STA 254 AND STA 270 LBL 20 AND RBL5.
CORROSION>>>>> LT WING REAR SPAR BOOST PUMP TANK 1 AFT UPPER BONDING STRAP EVIDENCE OF SURFACE CORROSION. / REMOVED AND REPLACED BONDING STRAP TO LT WING REAR SPARE BOOST PUMP TANK 1 AFT UPPER SURFACE IAW B737-700 AMM 28-22-41-000-802 / 28-22-41-400-802
AISLE EMERGENCY LIGHTS INOP AT ROWS 6;9; & 11 ON LT SIDE OF AIRCRAFT. / REMOVED & REPLACED EMERGENCY LIGHTS BATTERY PACK M2335 AT STA 500C+7.5 WL 213 LBL 67 I.A.W. AMM 33-51-06. OPS CHECK GOOD; ALL EMERGENCY LIGHT OPERATIVE AT THIS TIME.
SUPPORT BRACKET FOR R1 AND R2 DOOR SEAL DRAINS IN AFT AREA BEHIND AFT CARGO BULKHEAD CRACKED / REMOVED AND REPLACED SUPPORT BRACKET REF SRM 51-40-02
FWD LAV SMOKE DETECTOR ALARM SOONDED DURING DESCENT. NO SMOKE DETECTED. OK TO CONTINUE PER MEL 26-15-02 SP1B TRACKING NO. 37069 / REMOVED AND REPLACED FWD LAV SMOKE DETECTOR PER M/M 26-14-01. CL #37111
L/H INTERIOR EMERGENCY AISLE LIGHT INOP AT ROW 6. / RELAMPED LIGHT PER AMM.
R2 DOOR EMERGENCY LIGHT INOP. / RELAMPED LIGHT PER AMM.
R1 DOOR SLIDE OUT OF POSITION. REPOSITIONED GIRT BAR PER MT.
AFT FLT ATT PANEL EMERGENCY LIGHT SWITCH COVER BROKEN. R&R COVER IAW CMM.
LT OVERWING EXIT SIDEWALL LIGHTS DIM. R&R BULBS PER AMM.
LT OVERWING EXIT SIDEWALL LIGHTS DIM. R&R LENS PER AMM.
RT OVERWING EXIT SIDEWALL LIGHTS DIM. R&R LENS PER AMM.
RT OVERWING EXIT SIDEWALL LIGHTS DIM. R&R BULBS PER AMM.
L2 DOOR EMERGENCY SLIDE COVER SCREWS CAME LOOSE. REATTACHED HARDWARE PER AMM.
L2 DOOR EMERGENCY SLIDE COVER LOOSE. SECURED BOLT IAW AMM.
FORWARD LT WINDSCREEN 1 FLASHLIGHT CHARGE INDICATOR WOULD NOT FLASH. R&R BATTERY IAW AMM.
LT M1675 EMERGENCY BATTERY PACK WILL NOT CHARGE. R&R BATTERY PACK IAW AMM.
AFT LT OF OVERWING EMERGENCY EXIT DOOR LIGHT LENS AND MOUNT CRACKED. R&R LIGHT IAW AMM.
AFT RT OF OVERWING EMERGENCY EXIT DOOR LIGHT LENS AND MOUNT CRACKED. R&R LIGHT IAW AMM.
G1 GALLEY EXIT LIGHT BASE AND LENS CRACKED. R&R LENS IAW AMM.
G1 GALLEY EXIT LIGHT BASE AND LENS CRACKED. R&R LIGHT IAW AMM.
RT FORWARD LOWER OVERWING EXIT INDICATOR LENS PLASTIC MOUNT TAB BROKEN. R&R COVER IAW AMM.
REFERENCE DTIP NRC X898080: REPAIR ON FUSELAGE SKIN AT STA 460 STR 1 REQUIRES REPLACEMENT / REMOVED AND REPLACED FUSELAGE SKIN DOUBLER FROM STA 450-STA 465 S-1 IAW EA 190140 IR AND SWA EA NO. 1-753-34376 REV. IR.
AFT PIT FLOOR SUPPORT TRACK VERTICAL FLANGE CRACKED AT BS 727E, RBL 13.84. R&R TIE DOWN TRACK IAW SRM AND DWG.
REFERENCE DTIP NRC X898088- REPAIR ON AFT CARGO FLOOR SUPPORT CHANNEL AT STA 772.5 RBL 8.1 REQUIRES REPLACEMENT / REMOVED AND REPLACED REPAIR ON AFT CARGO FLOOR SUPPORT CHANNEL AT STA 772.5 RBL 8 IAW B737-700 E.A 1-A53-4982 REV. 3 AND SRM 53-00-53 REPAIR 2; 4
REFERENCE DTIP NRC X898084- REPAIR ON AFT CARGO FLOOR SUPPORT CHANNEL AT STA 772.5 LBL 12.5 REQUIRES REPLACEMENT / REMOVED AND REPLACED REPAIR ON AFT CARGO FLOOR SUPPORT CHANNEL AT STA 772.5 LBL 12.5 IAW B737-700 E.A 1-A53-4982 REV 3; AND SRM 53-00-53 REPAIR 2; 4
REFERENCE DTIP NRC X898085- REPAIR ON AFT CARGO FLOOR SUPPORT CHANNEL AT STA 772.5 LBL 8.1 REQUIRES REPLACEMENT / REMOVED AND REPLACED REPAIR ON AFT CARGO FLOOR SUPPORT CHANNEL AT STA 772.5 LBL 8.1 IAW B737-700 E.A 1-A53-4982 REV.3 AND SRM 53-00-53 REPAIR 2; 4
REFERENCE DTIP NRC X898086- REPAIR ON AFT CARGO FLOOR SUPPORT CHANNEL AT STA 772.5 LBL 3.0 REQUIRES REPLACEMENT / REMOVED AND REPLACED REPAIR ON AFT CARGO FLOOR SUPPORT CHANNEL AT STA 772.5 LBL 3. IAW B737-700 E.A 1-A53-4982 REV 3; SRM 53-00-53 REPAIR 2 AND 4
REFERENCE DTIP NRC X898083- REPAIR ON AFT CARGO TIE DOWN TRACK AT STA 772.5 LBL 17.25 REQUIRES REPLACEMENT / REMOVED AND REPLACED REPAIR ON AFT CARGO TIE DOWN TRACK @ STA 772.5 LBL 17.25 IAW EA#1-A53-4982 + SRM 53-00-53-2R-3 (PER SA-M 735 SHAWN CHIRAYIL E104352)
FORWARD CARGO AFT CORNER SCUFF PLATE CRACKED. REPAIRED SCUFF PLATE IAW EA AND AMM.
LT SHEAR WEB CRACKED UNDER L2 CREASE BEAM, BS 986. R&R SHEAR WEB IAW DWG.
FLOORBEAM UPPER FLANGE CORRODED AT BS 986, BETWEEN LBL 29 TO LBL 43. REPAIRED FLANGE IAW SRM AND EA.
AFT PIT DOOR RH CUTOUT ATTACH ANGLE IS CORRODED / REPLACED AFT PIT R/H CUTOUT ATTACH ANGLE W/NEW P/N 453A2611-1 ATAG A18227 IAW BOEING DWG 453A2600 REV
AFT PIT DOOR LH CUTOUT ATTACH ANGLE IS CORRODED / NO ALLOWABLE LIMITS FOUND IN SRM; RECIEVED 1EA-2 AFT PIT DOOR LH CUTOUT ATTACH ANGLE PER DWG # 454A2611 SHEET 2 REV C ATAG A89285
AFT PIT FLOOR PANEL 140AF HAS CORROSION / REMOVED CORROSION IAW SEM 5-10-02-06-D EVALUATED FOUND TO BE OUT OF LIMITS IAW SRM 53-000-53-1A-A FABRICATED PANEL 140AF IAW 51-40-05 PG 1 TASK 4A TREATED AND PRIMED IAW AMM 51-21-72-370-804
LOWER VAPOR BARRIER FOUND UPPER ATTACH ANGLE CRACKED AT BS 663, LBL 9. REPAIRED ANGLE IAW EA.
AFT PIT PANEL BOTTOM ATTACH STRIPS ARE CORRODED / RECEIVED 1EA-11 CAP STRIP FOR THE AFT CARGO PIT PANEL; NO ALLOWABLE LIMITS FOUND IN SRM PER DWG# 453A2600 SHEET 21 REV D ATAG A65014
AFT CARGO FLOOR BOARD SPLICE T CORRODED BS 887 RBL 10' TO RBL 20'. / PART VERIFIED AS P/N:140A7401-37 FOR NEW T. SPLICE IAW B737-700 DRWG #; A46A7500 REV 6 - 39 T.SPLICE & FLOOR BOARD TO BE INSTALLED ON JPANEL - 141-CLOSE CARD W/0 #:38953/1600/0006
AFT CARGO FLOOR BOARD T SPLICE AT BS 767 + 6' LBL 4' TO 10' CORRODED. / PART VERIFIED AS P/N:146A9401-4 FOR NEW T-SPLICE IAW B737-700 DRWG #:146A7500 REV. T -4 T.SPLICE & FLOOR BOARD TO BE INSTALLED ON JPANEL 141-CLOSE CARD W/O #:38953/1600/0006.
AFT CARGO RT Z ANGLE CORRODED BETWEEN BS 727C+10 TO BS 767, RBL 22. REPAIRED Z ANGLE IAW SRM AND DWG.
RIGHT ENGINE O/B FAN COWL; SUPPORT BRACKET AFT OF OIL ACCESS DOOR IS CRACKED. / REMOVED AND REPLACED R/H ENGINE O/B FAN COWL SUPPORT BRACKET AFT OF OIL DOOR IAW SRM 51-40-02-0G-0 AND CMM 71-13-30 A TAG A13657
#1 ENGINE FAN COWL AT 414 AR DOOR SURROUND VERTICAL WEB CRACKED. / REMOVED AND REPLACED VERTICAL WEB AT #1ENG FAN COWL 414AR DOOR SURROUND IAW B737 SRM 51-40-02-0G-0 & CMM 71-13-30
LT MAIN LANDING GEAR WHEEL WELL LOWER LT VAPOR BARRIER WEB CRACKED AT BS 663, BETWEEN LBL 31 TO LBL 40. REPAIRED VAPOR BARRIER IAW SRM & DWG.
LEFT WING TO BODY FAIRING 193AL EXTERIOR SURFACE OUTER LAYER IS DELAMINATED AND PEELING AT FORWARD EDGE / REPAIRED OUTER MOST (LAYER FOIL MESH PLY) I/A/W SRM 51-70-14-2R-4 PAR 5 REV 66 ON LEFT WING TO BODY FAIRING 193AL EXTERIOR SURFACE FWD EDGE AS MARKED
FORWARD CARGO COMPARTMENT FLOOR PANEL 120AF HAS CORROSION ALONG EDGES / REMOVED CORROSION ON FWD CARGO COMPT FLOOR PANEL 120AF IAW SRM 51-10-02-0G-0. VISUAL INSPECTION WITH 10X MAG GLASS NO DEFECTS BLENDING AREAS EXCEED THE MAX ALLOW ABLE ; OUT OF LIMITS IAW SRM 53-00-53-1A-1; STEP 5A (1)(B)(1). - FABRICATED A REPLACEMENT PANEL 120AF IAW BOEING DWG- 453A1610 SHT 9 REV F. P/N 453A1610-14 TOOL 36646 CAL 02OCT19 ATAG A74221
RH FLAP UPPER SHELF PANEL DEFLECTION RIB SERRATED PLATE AREA CRACKED AT FASTENER HOLES / REPAIRED SHELF PANEL DEFLECTION RIB SERRATED PLATE AREA PER SRM 57-51-02-2R-1
L/H T/E REAR UPPER FIXED T/E PANEL HAS CRACKED SEAL RETAINER ABOVE #1 ENGINE PYLON AFT FAIRING / REMOVED AND REPLACED SEAL RETAINING BRACKET PER SRM 51-40-02
RH FLAP UPPER SHELF PANEL FOR DEFLECTION RIB SEAL RETAINER CRACKED AT FASTENER HOLE / INSTALLED NEW RIB SEAL RETAINER ON RH FLAP UPPER SHELF PANEL PER SRM 51-40-02
LT WHEEL WELL LOWER STIFFENER CRACKED AT BS 663, LBL 25. R&R STIFFENER PER SRM.
DIVERSION, ON TAKE-OFF GOT INTERMITTENT "LE FLAP TRANSIT" LIGHT ALONG WITH AN INTERMITTENT "GREEN EXT" LIGHT ON THE NR 3 LE FLAP. R&R NR 3 KRUGER FLAP EXTEND SENSOR PER MM.
EMERGENCY BATTERY FAILED CAPACITY CHECK AT LOCATION M1672. R&R BATTERY PER AMM & DWG.
AFT CABIN EMERGENCY EXIT LIGHTS INOP. R&R BATTERY PACK PER AMM.
AFT OF L2 DOOR LT EXTERIOR EMERGENCY EXIT LIGHT INOP. R&R LAMP PER AMM.
WING TO BODY FAIRING AT R/H AFT WHEEL WELL PART NUMBER 149A7656-6 IS BROKEN / REMOVED AND REPLACED WING TO BODY FAIRING PANEL AT R/H AFT MWW PART # 149A7656-6 IAW SRM 51-40-02-0G-0
BS 727 +2.7 RBL 35 FAIRING SUPPORT STRUCTURE PART NUMBER 149A7511-6 IS CRACKED / BS 727 & 2.7 RBL35 FAIRING SUPPORT STRUCTURE PART NUMBER 149A7511-6 WITH A CRACK WAS REPAIRED IAW SRM 51-70-05-2R-7
WING TO BODY FAIRING FORMER AT BS 727 +2.7 RBL 35 IS BROKEN / REMOVED AND REPLACED WING TO BODY FAIRING FORMER B.S 727 + 2.7 RBL 35 MWW IAW SRM 51-40-02-0G-0 AND DWG #149A7502
R1 DOOR EMERGENCY ESCAPE SLIDE ATTACHMENT TO GIRT BAR OUT OF ADJUST. ADJUSTED GIRT BAR IAW AMM.
R1 DOOR EMERGENCY EVAC SLIDE GIRT BAR STUCK WILL NOT STOW CORRECTLY. CLEANED GIRT BAR IAW SIP.
L/H WING FLAP SEAL RETAINING BRACKET UNDER PNL 551GB IS CRACKED / REMOVED AND REPLACED L/H WING FLAP SEAL RETAINING BRACKET UNDER PANEL 551GB IAW SRM#51-40-02
PANEL 194BR AFT CORNER BROKEN. / REPAIRED PANEL 194 BR IAW B737-700 SRM 51-70-05-2R-10 REV 62 RESTORED FINISH IAW B737 AMM 51-21-99-300-801 PARA E (6) TABLE 701
R1 DOOR EMERGENCY EVAC SLIDE CABLE LOOSE. SECURED LANYARD PER SIP.
LT MAIN LANDING GEAR WHEEL WELL CENTER WING SECTION LOWER LT WEB VAPOR BARRIER CRACKED BETWEEN LBL 31.83 TO LBL 24.92 STIFFENERS. REPAIRED WEB PER SRM.
R2 DOOR EXTERIOR EMERGENCY LIGHT INOPERATIVE. REPLACED THE LAMP IAW AMM.
AFT GALLEY EMER EXIT SIGN BROKEN. R & R SIGN IAW AMM.
R2 DOOR EVAC SLIDE LOOSE. SECURED SLIDE ASSEMBLY IAW MM.
DECLARED EMER, DURING APPROACH, LANDING GEAR HANDLE WOULD NOT MOVE FROM THE OFF POSITION. CYCLED, NO HELP. R & R LANDING GEAR CONTROL LEVER MODULE IAW AMM.
L1 DOOR EMER EVAC SLIDE LIGHT WIRE INOPERATIVE. REPAIRED WIRE IAW SWPM & MM.
WEB CORRODED BETWEEN BS 500 - 500A, STRINGER 26R. R & R WEB IAW SRM.
R1 DOOR FWD FRAME LOWER CORNER CRACKED AT LOWER INBD FASTENER BS 295, WL 208. R & R FRAME IAW AMM & SRM.
LEFT MAIN WW SURROUND FAIRING AFT OF WW CRACKED AT BS 727, LBL 48. R & R FAIRING IAW SRM & DWG.
FUSELAGE STRINGER CORRODED AT STATION 312 - 328, STRINGER 29L. R & R STRINGER SECTION IAW SRM.
INTERCOSTAL CRACKED BETWEEN BS 277 TO 294.5, WL 208. R & R INTERCOSTAL IAW SRM & DWG.
FRAME CRACKED AT BS 360, STRINGER 8R. REPAIRED FRAME IAW EA.
FUSELAGE FRAME CRACKED AT STATION 360, STRINGER 8L. REPAIRED FRAME IAW EA.
FRAME CRACKED AT BS 827, STRINGER 9L. REPAIRED FRAME IAW EA.
FRAME CRACKED AT BS 747, STRINGER 9L. REPAIRED FRAME IAW EA.
FRAME CRACKED AT BS 727D, STRINGER 9L. REPAIRED FRAME IAW EA.
INTERCOSTAL CRACKED BETWEEN BS 344 TO 360, BL 0. R & R INTERCOSTAL IAW SRM.
INTERCOSTAL CORRODED AT BS 991, STRINGER 21L. R & R INTERCOSTAL IAW SRM.
AFT CARGO BAY ON SUB THRESHOLD INBD STRAP CORRODED BETWEEN BS 792 - 847, RBL 19. R & R STRAP IAW SRM & DWG.
AFT CARGO BAY ON SUB THRESHOLD WEB CORRODED BETWEEN BS 792 - 847, BETWEEN RBL 20 - RBL 28. R & R WEB IAW SRM & DWG.
CREASE BEAM WEB CRACKED BETWEEN BS 927 TO 947, WL 208 RT. R & R WEB IAW SRM & DWG.
AFT CARGO BAY ON INTERCOSTAL CORRODED BETWEEN BS 747 - 767, STRINGER 25R. R & R INTERCOSTAL IAW SRM.
AFT CARGO BAY ON FLOOR TO SIDEWALL SUPPORT PLATE CORRODED BETWEEN BS 887 TO 907, RBL 22. R & R PLATE IAW SRM.
AFT CARGO BAY ON FLOOR TO SIDEWALL SUPPORT PLATE CORRODED BETWEEN BS 727+4 TO BS 767, RBL 21. R & R SUPPORT IAW SRM.
AFT CARGO BAY ON FLOOR TO SIDEWALL SUPPORT PLATE CORRODED BETWEEN BS 727+4 TO BS 847, LBL 21. REPAIRED PLATE IAW SRM.
INTERIOR SEAT TRACK FLANGE FWD OF BS 727B, RBL 45 INBD AFT HOLE CRACKED. REPAIRED FLANGE IAW ER & EA.
INTERIOR SEAT TRACK FLANGE FWD OF BS 727B, RBL 25, BOTH AFT HOLES CRACKED. REPAIRED FLANGE IAW ER & EA.
INTERIOR SEAT TRACK FLANGE FWD OF BS 727B, LBL 45 BOTH AFT HOLES CRACKED. REPAIRED FLANGE IAW ER & EA.
INTERIOR SEAT TRACK FLANGE FWD OF BS 727B, LBL 25 BOTH AFT HOLES CRACKED. REPAIRED FLANGE IAW ER & EA.
RIGHT WING FIXED TE SUPPORT RIB CRACKED ABOVE DEFLECTION ROLLER SUPPORT BETWEEN INBD & OTBD FLAPS. R & R RIB IAW SRM.
FORWARD CARGO BAY ON INTERCOSTAL CORRODED BETWEEN BS 500B TO 500C, STRINGER 26R. R & R INTERCOSTAL IAW SRM & DWG.
FORWARD CARGO BAY ON FLOOR TO SIDEWALL SUPPORT PLATE CORRODED BETWEEN BS 480 TO 500D, LBL 23. R & R SUPPORT IAW SRM.