N220WN
Registered owner: SOUTHWEST AIRLINES CO, TX (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
R1 DOOR SLIDE FELL OUT OF DOOR ONTO FLOOR IN GALLEY. REINSTALLED R1 SERVICE DOOR SLIDE IAW AMM 25-66-00 AND T/C 725-61-06-FS.
NG DOOR SLIDE COVER GIRT BAR RETAINER CLIP MISSING FASTENERS - PERMANENT REPAIR. REMOVED TEMP REPAIR AND INSTALLED FASTENER PER SRM 51-40-02 AND AIPC 25-66-00-13.
FWD ENTRY DOOR GIRT BAR RETAINER LOOSE. C/W ALL EA M-23-125-01839.
FORWARD SERVICE DOOR GIRT BAR STORAGE HOOKS LOOSE. TIGHTENED GIRT BAR STORAGE HOOKS AS REQUIRED PER SIP. ACFT OK FOR SERVICE.
EMERGENCY BATTERY PACK FAILED CAPACITY CHECK AT 20 ABC M1670. R & R EMERGENCY BATTERY PACK PER AMM 33-51-06;[02] INSPECTED PER AMM 33-51-06
EMER LT LENS FWD OF LH EMER EXIT DOOR FELL OFF<[01] RESECURED EMER LT LENS PER MM 33-51-01
FA REPORTS FWD LEFT GIRT BAR DIFFICULT TO ARM & DISARM. CLEANED GIRT BAR RETAINER IAW SIP.
CUSTOMER REQUEST LIGHTBULBS BURNT OUT AT L1 AND R1 DOOR EMERGENCY EXIT LIGHTS. REPLACED LIGHTBULBS BURNT OUT AT L1 AND R1 DOOR EMERGENCY EXIT LIGHTS IAW AMM 33-51-01-960-801-NG TEST IS OK.
CRACK INSPAR RIB LOCATED STAB STA 129.50 AND 9 INCH FROM FRONT SPAR LT HORIZONTAL STAB. REPAIRED INSPAR RIB LOCATED STAB STA 129.50 AND 9 INCH FROM FRONT SPAR LT HORIZONTAL STAB IAW B737-700 SRM 55-10-09-2R-5 REPAIR 5 PARAGRAPH 4;FIGURE 203.
CRACK ON SCUFF PLATE AFT CORNER LOCATED AT FWD CARGO COMPARTMENT. REPAIRED THE AFT CORNER SCUFF PLATE OF FWD CARGO COMPARTMENT IAW BOEING 737-700 SRM 53-30-15-2R-1 REPAIR 1 AND BAC 5975.
CRACK ON SUPPORT BRACKET LOCATED INTERNAL AREA BTW BS188 TO BS203 AT LOWER NOSE COMPARTMENT. REPLACED SUPPORT BRACKET LOCATED INTERNAL AREA BTW BS188 TO BS203 AT LOWER NOSE COMPARTMENT IAW SRM 51-10-02-0G PARAGRAPH 9; SRM 51-40-02-0G AND DWG: 141A9194 SHEET: 4 REV: D.
CRACK SUPPORT BRACKET BS 663.75 AND RBL 54 AT LOWER FUSELAGE 2025-204843<[01] TOOL USED: TEMPERATURE CONTROLLER P/N P3015GOES00000 S/N 142811019 DUE DATE 29 JAN 26.;[02] TOOL USED: POWER PACK P/N FMK0007096 S/N PE0414/70786 DUE DATE 03 JUN 25; THERMOMETER P/N FLUKE 566 S/N 54500056WS DUE DATE 08 JAN 26; MULTIMETER P/N FLUKE 87-Y S/N 65700232 DUE DATE 10 JAN 26.;[03] SUPPORT BRACKET LOCATED BS 663.75 AND RBL 54 AT LOWER FUSELAGE IAW B737-700 SRM 51-10-02-0G-0 PARAGRAPH 9 ;SRM 51-40-02-0G-0 AND DWG 111A1001 SHEET 270 REV- SEE INDIVIDUAL SIGNS OFF BELOW.;[04] CORRECTED STEP 3 <BR>REPLACED SUPPORT BRACKET LOCATED BS 663.75 AND RBL 54 AT LOWER FUSELAGE IAW B737-700 SRM 51-10-02-0G-0 PARAGRAPH 9 ;SRM 51-40-02-0G-0 AND DWG 111A1001 SHEET 270 REV- SEE INDIVIDUAL SIGNS OFF BELOW.;[05] CERTIFIED ACTION 4; COMPLETED
CRACK INDICATION FOUND ON LT HORIZONTAL STABILIZER LOWER SKIN PANEL. LOCATED AT STAB STA 193.9 RIB AND 24.0 INCH. FROM FRONT SPAR. INBOARD SIDE OF RIB. CRACK LENGTH = 0.350 INCH. APPROX. 2025-204861. REFER TO FAULT TTG8Q00ZF38D WHERE EA 25-155-00868 WAS ADDED AS A SUBTASK.
CRACK INDICATION FOUND ON LT HORIZONTAL STABILIZER LOWER SKIN PANEL. LOCATED AT STAB STA 193.9 RIB AND 16.0 INCH. FROM FRONT SPAR. INBOARD SIDE OF RIB. CRACK LENGTH = 1.00 INCH. APPROX. 2025-204860<[01] TOOL USED: ET EQUIPMENT; P/N: NORTEC600D; S/N: 210138103; CAL DUE DATE: 10-JUN-25;[02] REPAIR LOWER SKIN PANEL. ON LT HORIZONTAL STABILIZER LOCATED AT STAB STA 193.9 RIB AND 16.0 INCH. FROM FRONT SPAR. INBOARD SIDE OF RIB IAW B737-700 SRM 55-10-01-2R-11 REPAIR 11; SRM 51-40-02 AND EA NO:25-155-00868-WIP1 APPENDIX REV A. SEE INDIVIDUAL SIGN OFF BELOW.;[03] JOB COMPLETED AND CERTIFIED RII
CRACK INDICATION FOUND ON RT HORIZONTAL STABILIZER LOWER SKIN PANEL. LOCATED AT STAB STA 193.9 RIB AND 16.0 INCH. FROM FRONT SPAR. INBOARD SIDE OF RIB. CRACK LENGTH = 0.700 INCH. APPROX. 2025-204859<[01] TOOL USED ON STEP 5:EDDY CURRENT EQUIPMENT P/N: NORTEC 600D; S/N: 240524311; DUE DATE: 13/NOV/2025;[02] PERFORMED REPAIR LOCATED AT RT HORIZONTAL STABILIZER LOWER SKIN PANEL STAB STA 193.9 IAW B737-700 SRM 55-10-01-2R-11 REPAIR 11. SEE INDIVIDUAL SIGN OFFS BELOW.;[03] PERFORMED REPAIR LOCATED AT RT HORIZONTAL STABILIZER LOWER SKIN PANEL STAB STA 193.9 IAW B737-700 SRM 55-10-01-2R-11 REPAIR 11. SEE INDIVIDUAL SIGN OFFS BELOW.<BR>RII CERTIFIED.
CRACK ON STRINGER 22L LOCATED BS540 FWD CARGO COMPARTMENT. PERFORMED PERMANENT REPAIR ON STRINGER 22L LOCATED BS500D AND BS540 AT FWD CARGO COMPARTMENT IAW SRM 53-00-03-2R-1 REPAIR 1.
CRACK INSPAR RIB LOCATED STAB STA 129.50 AND 28 INCH FROM FRONT SPAR LT HORIZONTAL . PERFORMED PERMANENT REPAIR ON INSPAR RIB LOCATED STAB STA 129.50 AND 28 INCH FROM FRONT SPAR LT HORIZONTAL STAB IAW B737-700 SRM 55-10-09-2R-4 REPAIR 4.
CRACK ANGLE LOCATED BS 540 AND RBL 6 AT CENTER WING BOX REPLACED ANGLE LOCATED BS 540 AND RBL 6 AT CENTER WING BOX IAW B737-700 SRM 51-40-02 AND DWG 212A1101 SHEET: 3 REV: - . REMOVED EWIS PROTECTION LOCATED BS 540 AND RBL 6 AT CENTER WING BOX IAW B737-700 AMM 20-60-07-913-801.
DEBONDED OB AFT FLAP INBOARD SIDE AT RT WING. PERFORMED INTERIM REPAIR AT OB AFT FLAP INBOARD SIDE AT RT WING IAW B737-700 SRM 57-53-01-2R-16 REPAIR 16. AND THE REPAIR REQUIRED TAP TEST INSPECTION EVERY 6;875 CYCLES OR 30 MONTHS WHICHEVER COMES FIRST.
CRACK ON INTERCOSTAL LOCATED BTW BS 685 TO BS 706 AT LEVEL STR 14R AT PASSENGER CABIN. REPLACED WEB INTERCOSTAL LOCATED BTW BS 685 TO BS 706 AT LEVEL STR 14R AT PASSENGER CABIN I.A.W B737-700 SRM 51-10-02-0G-0 PARAGRAPH 9; B737-700 SRM 51-40-02-0G-0 AND DWG 144A7500 SHEET: 6 REV: A.
CRACK ON STRINGER 23L LOCATED BS540 FWD CARGO COMPARTMENT. PERFORMED PERMANENT REPAIR ON STRINGER 23L LOCATED BS500D AND BS540 AT FWD CARGO COMPARTMENT IAW B737-700 SRM 53-00-03-2R-1 REPAIR 1.
CRACK FLOOR STRUCTURE AFT SUPPORT ANGLE BETWEEN BS 907 TO BS 927 STRINGER 25R AND STRINGER 27R AT AFT CARGO COMPARTMENT. REPLACED AFT SUPPORT ANGLE (STIFFENER) BETWEEN BS 907 TO BS 927 STRINGER 25R AND STRINGER 27R AT AFT CARGO COMPARTMENT IAW B737-700 SRM 51-10-02-0G PARAGRAPH 9; SRM 51-40-02-0G AND DWG: 147A7221 SHEET: 24 REV: -.
CRACK FLOOR STRUCTURE FWD SUPPORT ANGLE BETWEEN BS 907 TO BS 927 STRINGER 25R AND STRINGER 27R AT AFT CARGO COMPARTMENT. REPLACED FWD SUPPORT ANGLE (STIFFENER) BETWEEN BS 907 TO BS 927 STRINGER 25R AND STRINGER 27R AT AFT CARGO COMPARTMENT IAW B737-700 SRM 51-10-02-0G PARAGRAPH 9; SRM 51-40-02-0G AND DWG: 147A7221 SHEET: 24 REV: -.
CRACK ON CLOUSURE ANGLE LOCATED BS1016 TO BS1088 AT LEVEL ST2L AND STR3L EXTERNAL SKIN AT UPPER FUSELAGE. REPLACED CLOUSURE ANGLE AND FASTENERS LOCATED BS1016 TO BS1121+ 10 INCHES APROX AT LEVEL ST2L AND STR3L EXTERNAL SKIN UPPER FUSELAGE IAW B737-700 SRM 51-10-02 AND BOEING DRAWING: 148A8300 SHEET 2 REV A; BOEING DRAWING: 148A3590 SHEET 99 REV-.
CORROSION SUPPORT ZEE BETWEEN BS 727D TO BS 767 AND RBL 21 AFT CARGO COMPARTMENT 2025-204674<[01] REPLACED SUPPORT ZEE LOCATED BETWEEN BS 727 TO BS 767 RBL21 AFT CARGO COMPARTMENT I.A.W B737-700 SRM 51-40-02; SRM 51-10-02 AND DWG 146A7500 SHEET: 85 REV: A; DWG 146A7502 SHEET: 26 REV: -. SEE INDIVIDUAL SIGN OFFS BELOW.;[02] TASK COMPLETED<BR><BR>SEE INDIVIDUAL SIGN OFFS BELOW
BROKEN BASE ON EMERGENCY EXIT LIGHT ON LAV B. REPLACED BASE ON EMERGENCY EXIT LIGHT ON LAV B IAW B737-700 AMM-33-51-01-960-802 STEP 3.A TO 3.C (6) AND (7). TESTED OK.
CRACK ON ANGLE - SUPPORT LOCATED BS727C AND LBL47 UPPER CEILING AREA AT AFT CARGO COMPARTMENT 2025-204643<[01] REPLACED ANGLE - SUPPORT AND FASTENERS LOCATED BTW BS727A TO 727E+10? AND LBL47 UPPER CEILING AREA AT AFT CARGO COMPARTMENT IAW B737-700 SRM 51-40-02-0G-0; SRM 51-10-02-0G-0 ITEM 9; DWG 149A9490 SHEET: 21 REV: -; DWG 149A9491 SHEET: 38 REV: - AND DWG 140A9861 SHEET: 31 REV: B. SEE INDIVIDUAL SIGN OFF BELOW;[02] CERTIFIED <BR>REPLACED ANGLE - SUPPORT AND FASTENERS LOCATED BTW BS727A TO 727E+10? AND LBL47 UPPER CEILING AREA AT AFT CARGO COMPARTMENT IAW B737-700 SRM 51-40-02-0G-0; SRM 51-10-02-0G-0 ITEM 9; DWG 149A9490 SHEET: 21 REV: -; DWG 149A9491 SHEET: 38 REV: - AND DWG 140A9861 SHEET: 31 REV: B. SEE INDIVIDUAL SIGN OFF BELOW
CRACK ON ANGLE BS663 UPPER POSITION RBL40 AT CENTER WING BOX. REPLACED ANGLE LOCATED BS 663.75 BTW RBL 5 T0 RBL 65 AT CENTER WING BOX IAW B737-700 SRM 51-10-02-0G-0 ITEM 9; B737-700 SRM 51-40-02-0G-0 AND DRAWING 111A1000; SHEET:171; REV: -. DRAWING 111A1000; SHEET:169; REV: -.
CRACK ON WEB FRAME LOCATED BS 259.5 BTW STR 8R TO STR 9R AT FWD GALLEY AREA 2025-204596<[01] ET EQUIPMENT USED P/N: NORTEC 600D; S/N: 240494307; DUE DATE: 27-AUG-25;[02] PERFORMED PERMANENT REPAIR ON WEB FRAME LOCATED BS 259.5 BTW STR 6R TO STR 11R AT FWD GALLEY AREA IAW EA NO. 25-153-00771-WIP2 REV A. SEE INDIVIDUAL SIGN OFFS BELOW.;[03] CORRECTED STEP 2. PERFORMED REPAIR ON WEB FRAME LOCATED BS 259.5 BTW STR 6R TO STR 11R AT FWD GALLEY AREA IAW EA NO. 25-153-00771-WIP2 REV A. SEE INDIVIDUAL SIGN OFFS BELOW.;[04] PERFORMED REPAIR ON WEB FRAME LOCATED BS 259.5 BTW STR 6R TO STR 11R AT FWD GALLEY AREA IAW EA NO. 25-153-00771-WIP2 REV A. SEE INDIVIDUAL SIGN OFFS BELOW.<BR>RII.
CRACK ON SUPPORT ANGLE LOCATED BTW BS 291.5 TO BS 294.5 AT LEVEL STR 17R AT FWD GALLEY AREA 2025-204581<[01] REPLACED ANGLE AND FASTENERS LOCATED BTW BS 291.5 TO BS 294.5 AT LEVEL STR 17R AT FWD GALLEY AREA IAW B737-700 SRM 51-40-02; B737-700 SRM 51-10-02 PARAGRAPH 9 AND DWG 141A8310 SHEET: 25 REV: - SEE INDIVIDUAL SIGN-OFF BELOW.;[02] TASK COMPLETED RII
CRACK ON SUPPORT ANGLE LOCATED BS 294.5 BTW STR 12L TO STR 14L AT FWD GALLEY AREA. REPLACED SUPPORT ANGLE LOCATED BS 294.5 BTW STR 12L TO STR 14L AT FWD GALLEY AREA IAW B737-700 SRM 51-10-02-0G-0 PARAGRAPH 9; SRM 51-40-02-0G-0 AND DWG 141A1311 SHEET 1 REV C.
CRACK ON TIE CLIP LOCATED BS 277 AT LEVEL STR 10R AT FWD GALLEY AREA. REPLACED TIE CLIP LOCATED BS 277 AT LEVEL STR 10R AT FWD GALLEY AREA IAW B737-700 SRM 51-40-02 ; B737-700 SRM 51-10-02 ITEM 9 AND DWG DWG 141A1110 SHEET 18 REV.
WEAR ON GIRT BAR FITTING HARDWARE AND PLATE ON FWD ENTRY AND SERVICE DOOR AT FWD GALLEY AREA 2025-204551<[01] REPLACED GIRT BAR FITTING HARDWARE AND PLATE ON FWD ENTRY AND SERVICE DOOR AT FWD GALLEY AREA IAW B737-700 AMM 25-66-02-400-801 AND INSTALLATION WILL BE DOCUMENTED ON TTG8Q003K4PL STEP 2.A(12).;[02] REPLACED GIRT BAR FITTING HARDWARE AND PLATE ON FWD ENTRY AND SERVICE DOOR AT FWD GALLEY AREA IAW B737-700 AMM 25-66-02-400-801 AND INSTALLATION WILL BE DOCUMENTED ON TTG8Q003K4PL STEP 2.A(12).
WEAR ON GIRT BAR FITTING HARDWARE AND PLATE ON AFT ENTRY AND SERVICE DOOR AT AFT GALLEY AREA 2025-204561<[01] REPLACED GIRT BAR FITTING HARDWARE AND PLATE ON AFT ENTRY AND SERVICE DOOR AT AFT GALLEY ARE IAW B737-700 AMM 25-66-02-000-801 AND AMM 25-66-02-400-801.;[02] REPLACED GIRT BAR FITTING HARDWARE AND PLATE ON AFT ENTRY AND SERVICE DOOR AT AFT GALLEY ARE IAW B737-700 AMM 25-66-02-000-801 AND AMM 25-66-02-400-801.
CRACK ON GUSSET LOCATED BS500D AND STR19R FWD CARGO COMPARTMENT 2025-204516<[01] REPLACED GUSSET LOCATED BS500D AND STR19R FWD CARGO COMPARTMENT IAW B737-700 SRM 51-10-02 PARAGRAPH 9; SRM 51-40-02-0G AND DWG: 143A7902 SHEET: 256 REV: B; SEE INDIVIDUAL SIGN-OFF BELOW;[02] REPLACED GUSSET LOCATED BS500D AND STR19R FWD CARGO COMPARTMENT IAW B737-700 SRM 51-10-02 PARAGRAPH 9; SRM 51-40-02-0G AND DWG: 143A7902 SHEET: 256 REV: B; SEE INDIVIDUAL SIGN-OFF BELOW<BR>RII CERTIFIED
CRACK ON GUSSET LOCATED BS500D AND STR19L FWD CARGO COMPARTMENT 2025-204510<[01] REPLACED GUSSET AND FASTENERS LOCATED BS500D AND STR19L FWD CARGO COMPARTMENT I.A.W B737-700 SRM 51-40-02-0G-0; DWG 143A7902 SHEET: 174 REV: - AND B737-700 SRM 51-10-02-0G-0 PARAGRAPH 9. SEE INDIVIDUAL SIGN OFF BELOW.;[02] REPLACED GUSSET AND FASTENERS LOCATED BS500D AND STR19L FWD CARGO COMPARTMENT I.A.W B737-700 SRM 51-40-02-0G-0; DWG 143A7902 SHEET: 174 REV: - AND B737-700 SRM 51-10-02-0G-0 PARAGRAPH 9. <BR>RII<BR>SEE INDIVIDUAL SIGN OFF BELOW.
BROKEN LENS EMERGENCY LIGHT ON BULL NOSE BIN POSITION 1 3 4 5 6 7 8 9 11 LH SIDE. REPLACED LENS EMERGENCY LIGHT ON BULL NOSE BIN POSITION 1; 3; 4; 5; 6; 7; 8; 9; 11 LH SIDE IAW B737-700 AMM 33-51-03-960-801 STEP 2.D(3) (A) AND (C).
CRACKED STIFFENER (PANEL BREAK) FLOOR STRUCTURE ON BS 540 BTW BL 0 AND RBL 24 AT PASSENGER CABIN. REPLACED STIFFENER FLOOR STRUCTURE ON BS 540 BTW BL 0 AND RBL 24 AT PASSENGER CABIN IAW B737-700 SRM 51-40-02 SRM 51-10-02 ITEM 9 AND DWG 143A0060 SHEET 44 REV A
DELAMINATED ACCESS PANEL 194BL BODY FAIRING AT LOWER FUSELAGE. REPAIRED ACCESS PANEL 194BL BODY FAIRING AT LOWER FUSELAGE IAW B737-700 SRM 51-70-05-2R-10 REPAIR 10.
CRACK ANGLE LOCATED BS420 AND LBL21 FWD CARGO COMPARTMENT. REPLACED ANGLE CLIP LOCATED BS420 AND LBL21 FWD CARGO COMPARTMENT IAW B737-700 SRM 51-10-02; SRM 51-40-02 AND DWG: 143A7505 SHEET: 2 REV B.
BROKEN LENS EMERGENCY LIGHT ON BULL NOSE BIN POSITIONS 3 4 5 6 7 8 9 RH SIDE 2025-204479<[01] REPLACED LENS EMERGENCY LIGHT ON BULL NOSE BIN POSITIONS 3; 4; 5; 6; 7; 8; 9 RH SIDE IAW B737-700 AMM 33-51-03-960-801 STEP 2.D(3) (A) AND (C).;[02] REPLACED LENS EMERGENCY LIGHT ON BULL NOSE BIN POSITIONS 3; 4; 5; 6; 7; 8; 9 RH SIDE IAW B737-700 AMM 33-51-03-960-801 STEP 2.D(3) (A) AND (C).
ELONGATED HOLE ACCESS PANEL 571 DB AT LT WING. REPAIRED ACCESS PANEL 571 DB AT LT WING IAW B737-700 SRM 51-70-04-2R-9 REPAIR 9.
BROKEN EMERGENCY EXIT LIGHT LENS UPPER CENTER POSITION AT FWD AREA GALLEY. REPLACED EMERGENCY EXIT LIGHT LENS UPPER CENTER POSITION AT FWD AREA GALLEY IAW B737-700 AMM 33-51-01-960-801 STEP 2.C(1)(A)1) AND STEP 2.C(4).
CORROSION PLATE LOC. ON FLOOR PANEL 140CF AREA BS 794.3 RH SIDE AT AFT CARGO COMPARTMENT. 2025-204366<[01] REPLACED PLATE LOC. ON FLOOR PANEL 140CF AREA BS 794.3 RH SIDE AT AFT CARGO COMPARTMENT I.A.W B737-700 SRM 51-10-02-0G-0 PARAGRAPH 9 AND DWG 453A2600 SHEET: 27 REV: D;[02] REPLACED PLATE LOC. ON FLOOR PANEL 140CF AREA BS 794.3 RH SIDE AT AFT CARGO COMPARTMENT I.A.W B737-700 SRM 51-10-02-0G-0 PARAGRAPH 9 AND DWG 453A2600 SHEET: 27 REV: D
CORROSION PLATE LOC. ON FLOOR PANEL 140CF AREA BS 847 RH SIDE AT AFT CARGO COMPARTMENT. 2025-204365<[01] REPLACED PLATE LOC. ON FLOOR PANEL 140CF AREA BS 847 RH SIDE AT AFT CARGO COMPARTMENT I.A.W B737-700 SRM 51-10-02-0G-0 PARAGRAPH 9 AND DWG 453A2600 SHEET: 27 REV: D;[02] TASK COMPLETED
MAIN ENTRY FOR ASSIST HANDLE BROKEN<[01] R&RD FWD ENTRY DOOR ASSIST HANDLE IAW MM 52-11-31
LEFT AFT ENTRY DOOR EXTERNAL EMERGENCY LIGHT INOP<[01] 01 - REMOVED AND REPLACED PER [AMM 33-51-04-960-801-NG (SLIDE/OVERWING LIGHT - LAMP REPLACEMENT - PERMANENT)]
FWD LAV HAS A FOWL ODOR THAT CLEANING COULD NOT FIX. NO DIRECT INDICATION OF CAUSE.<[01] R&R CREW. OPS CHECK AND FLUSH CHECK OF FWD LAV GOOD IAW MM 38-32-00. NO FOWL ODORS DETECTED.
EMX BATTERY PACK M01672 FAILS CAPACITANCE CHECK<[01] 01 - REMOVED AND REPLACED EMX BATTERY PACK M01672 PER [AMM 33-51-06-960-805-NG (POWER SUPPLY - BATTERY PACK REPLACEMENT - PERMANENT)]
EMX BATTERY PACK M01673 FAILS CAPACITANCE CHECK<[01] 01 - REMOVED AND REPLACED EMX BATTERY PACK M01673 PER [AMM 33-51-06-960-805-NG (POWER SUPPLY - BATTERY PACK REPLACEMENT - PERMANENT)]
EMX BATTERY PACK M01674 FAILS CAPACITANCE CHECK<[01] 01 - REMOVED AND REPLACED EMX BATTERY PACK M01674 PER [AMM 33-51-06-960-805-NG (POWER SUPPLY - BATTERY PACK REPLACEMENT - PERMANENT)]
EMX BATTERY PACK M01675 FAILS CAPACITANCE CHECK<[01] 01 - REMOVED AND REPLACED EMX BATTERY PACK M01675 PER [AMM 33-51-06-960-805-NG (POWER SUPPLY - BATTERY PACK REPLACEMENT - PERMANENT)]
MAIN CABIN DOOR WHITE HANDLE SUPER LOOSE<[01] RE SECURED MAIN CABIN DOOR WHITE HANDLE REF SIP ; NO DEFECTS NOTED.
FWD SVC DOOR PANEL WHERE DOOR HANDLE ATTACHES TO THE DOOR ( INTERIOR)<[01] RESECURED FWD SVC DOOR PANEL IAW AMM 52-41-31.
ON APPROACH THE T/E FLAPS STOPPED AT >10<15 WIHT FLAPS 15 SELECTED<[01] R&R FLAP POSITION TRANSMITTER IAW AMM 27-58-01. OP CHECK GOOD
L1 DOOR ASSIST HANDLE LOOSE.<[01] L1 DOOR ASSIST HANDLE TIGHTENED PER 52-11-31
RH PASSENGER CABIN SEATS 11DEF RECLINES. 'EMERGENCY EXIT ROW'<[01] ADJUSTED RECLINE TO COMPLETE STOP AS PER DRAWING 25220031(NOTE 52);[02] ADJUSTED RECLINE TO COMPLETE STOP AS PER B/E AEROSPACE CMM 25-23-46;[03] VERIFIED STEPS 1 AND 2.
SEVERAL PASSENGER INTERIOR AND EXTERIOR EMERGENCY LIGHTS INOPERATIVE.<[01] RE-LAMPED SEVERAL PASSENGER INTERIOR AND EXTERIOR EMERGENCY LIGHTS AND PERFORMED EMERGENCY LIGHTS - OPERATIONAL TEST AS PER B737 AMM 33-51-00-710-801. TEST OK.;[02] VERIFIED STEP 1.
AFT CARGO DOOR SCUFF PLATE AFT CORNER CRACKED<[01] ACCOMPLISHED REPAIR AT AFT CARGO DOOR SCUFF PLATE AFT CORNER PER B737-700 SRM 53-60-15-2R-1 REPAIR 1 AND BAC 5975 BY OUTSIDE VENDOR PO#413980. THIS SCUFF PLATE WILL BE INSTALLED ON FAULT #TTG8Q00JDXNP.;[02] VERIFIED STEP 1
FWD CARGO COMP. BULKHEAD PANEL 121HW HAS CORROSION.<[01] VERIFIED STEPS ACCOMPLISHED.
RT WING DEFLECTION PANEL; VERTICAL WEB TO DEFLECTION RIB ATTACH CLIP ANGLE CRACKED.<[01] VERIFIED.
MAIN CABIN FWD WET AREA FLOOR PANEL #221FF LARGE AREA TOP SKIN FIBERGLASS PEELING OFF<[01] REPLACED MAIN CABIN FLOOR PANEL #221FF REF. B737-700 AMM 53-21-00-400-801. THIS PANEL WILL BE INSTALL ON FAULT #TTG8Q00HHHPE;[02] VERIFIED STEP 1
FLOOR SUPPORT BETWEEN STA. 500D AND STA. 520; BL-0 UPPER ANGLE CRACKED.<[01] INSTALLED EWIS PROTECCION AT MAIN CABIN CENTER DRY AREA BETW. STA 500D THRU 520 FOR SHEETMETAL ANGLE REPLACEMENT PER B737-700 AMM 20-60-07-913-801;[02] VERIFIED STEP 1.;[03] INSTALLED FLOOR SUPPORT (ANGLE) AT MAIN CABIN CENTER AREA BETWEEN STA 500D THRU STA 520 BL-0 PER B737-700 SRM 51-40-02-0G-0;[04] REMOVED EWIS PROTECCION INSTALLED ON STEP #1 PER B737-700 AMM 20-60-07-913-801;[05] VERIFIED STEPS 3 AND 4.
EXIT SING COVER IS MISSING AT R/H SIDEWALL PANEL # 10.<[01] INSTALLED EXIT SING COVER AT R/H SIDEWALL PANEL # 10 IAW B737-700- AMM 33-51-01-96-801.;[02] VERIFIED STEP #1.
MAIN CABIN FWD WET AREA FLOOR PANEL #222BF TOP SKIN WITH LARGE AREA FIBERGLASS PEELING OFF<[01] REPLACED MAIN CABIN FLOOR PANEL #222BF WITH A NEW PANEL REF.B73<BR>7-700 AMM 53-21-00-400-801. FLOOR PANEL WILL BE INSTALL ON FAULT #TTG8Q00HHH8E;[02] VERIFIED STEP 1
***CORROSION*** AFT CARGO COMPARTMENT FLOOR SUPPORT STRAP AT STA 767+4 RBL:21; LBL:21; AND WL:150.8 CORRODED AT FASTENER HOLES (234-36) ***CORROSION*** AFT CARGO COMPARTMENT FLOOR SUPPORT STRAP AT STA 767+4 RBL:21 LBL:21 AND WL:155.5 CORRODED AT FASTENER HOLES.<[01] REMOVED CORROSION AT AFT CARGO FLOOR SUPPORT STRAP STA 767+4; FROM RBL 21 TO LBL 21; FOUND OUT OF LIMITS AS PER SRM 53-00-53-1A-2.<BR>ACCOMPLISHED INSTALLATION ON ITEM TTG8Q00JRFZM;[02] VERIFIED STEP 1.
DURING BUYBACK FOUND SUPPORT FITTING HAS 0.390' CRACK AT STR 16L BETWEEN STA 294.5 THRU 303.9 WL 208.1<[01] STARTED TO REMOVE FASTENERS AT SUPPORT FITTING LOCATED AT STR 16L BETWEEN STA 294.5 AND 303.9 WL 208.1 PER B737-700 SRM 51-40-02-0G-0;[02] REMOVED SUPPORT FITTING AT STR 16L BETWEEN STA 294.5 THRU 303.9 WL 208.1 PER B 737-700 SRM 51-40-02 0G-0.;[03] VERIFIED STEP 1; 2;[04] OK TO INSTALL SUPPORT FITTING (INTERCOSTAL;[05] REMOVED AND REPLACED SUPPORT FITTING (INTERCOSTAL) BETWEEN STA 294.5 AND STA 303.9 STR 16L PER B737-700 SRM 51-40-02-0G-0 AND DRWG #141A8181.;[06] VERIFIED STEP 5.
LT WING LOWER MID SPAN T/E PANEL ASSEMBLY 561CB INNER SKIN SHOWS FASTENER HOLES BULGING AS MARKED. 124-014<[01] REPAIRED DAMAGED AREA AT LT WING LOWER MID SPAN T/E PANEL ASSEMBLY 561CB INNER SKIN. REF B737 SRM 51-70-04-2R-9 PARAGRAPH 4. MATERIAL USED GLASS FABRIC REPAIR PLIES PO#: 1694548; RESIN EY3804AB PO#: 1800550 AND GRAY PAINT PO#:2003553.;[02] VERIFIED REPAIR.
PANEL 232QF DELAMINATED.<[01] REPLACED MAIN CABIN FLOOR PANEL #232QF REF. B737-700 AMM 53-21-00-400-801. FLOOR PANEL #232QF WILL BE INSTALL ON FAULT #TTG8Q00HHHG4;[02] VERIFIED.
FWD CARGO STA 500C LBL 23.5 S-26L WL 156 INTERCOSTAL SUPPORT BRACKET ON AFT SIDE OF FRAME IS CRACKED 124-006<[01] REMOVED AND REPLACED INTERCOSTAL SUPPORT BRACKET AT FWD CARGO STA 500C LBL 23.5 S-26L WL 156 PER B737-700 SRM 51-40-02-0G-0 & DRAWING NO. 143A7505
INTERCOSTAL UPPER CHORD (ANGLE) AT BETWEEN STA 380 AND STA 400 BL 0; HAS CRACKS AT FASTENERS HOLES;<[01] REMOVED AND REPLACED INTERCOSTAL UPPER CHORD (ANGLE) BETWEEN STA 380 AND STA 400 BL 0 PER B737-700 SRM 51-40-02-0G-0 AND DRWG #143A5400.;[02] VERIFIED STEP 1
FUSELAGE FRAME STA 312 BETWEEN S-5L AND S-6L CRACK AT EDGE.<[01] REPAIRED FRAME AT STA 312 BETWEEN STR 5L AND 6L EDGE AREA PER EA M-22-153-01244 ON FAULT #TTG8Q00JRCWL.;[02] VERIFIED 1.
INTERCOSTAL UPPER CHORD (ANGLE) AT BETWEEN STA 380 AND STA 400 RBL 10; HAS CRACKS AT FASTENERS HOLES;<[01] REMOVED AND REPLACED INTERCOSTAL UPPER CHORD (ANGLE) BETWEEN STA 380 AND STA 400 RBL 10 PER B737-700 SRM 51-40-02-0G-0 AND DRWG #143A5400.;[02] VERIFIED STEP 1
CABIN SEAT TRACK AT STA 380 LBL 44.50 SPOT OF CORROSION. CORRECTION FAULT. CABIN SEAT TRACK AT STA 380 LBL 45.5 SPOT OF CORROSION.<[01] REMOVED CORROSION AT CABIN SEAT TRACK AT STA 380; LBL 45.5 AS PER SRM 51-10-02-0G-0;[02] VERIFIED STEP 1.;[03] EVALUATED REWORKED AREA. MATERIAL LOST 0.010'; MAXIMUN MATERIAL LOST ALLOWED 0.040'. FOUND WITHIN LIMTIS AS PER SRM 53-00-52-1A-1.<BR>TOOL USED B/C 173737 CAL. DUE 5-11-2023;[04] VERIFIED STEP 3.;[05] TREATED AND PRIMED REWORKED AREA AS PER REFERENCE AMM 51-21-41-370-803 AND SOPM 20-41-04.;[06] VERIFIED AND INSPECTED STEP #5.
FOUND A CRACK AT STA 328 TO 312 RBL 30 WL 208.1 INTERCOSTAL<[01] OK TO INSTALL NEW INTERCOSTAL.
CORROSION SPOTS AT LOWER MAIN SILL ASSY L2 DOOR INNER CHORD<[01] FOUND DEEP CORROSION EXFOLIATION AT L2 DOOR LOWER SILL INNER CHORD BETWEEN STA 951 AND STA 986. FOUND OUT OF LIMITS AS PER SRM 53-70-15-1A-1;[02] STARTED L2 DOOR LOWER SILL INNER CHORD REMOVAL AS PER SRM 51-40-02-0G-0<BR>PERFORMED BY O.P 4041;[03] ACCOMPLISHED L2 DOOR LOWER SILL INNER CHORD REMOVAL AS PER SRM 51-40-02-0G-0<BR>PERFORMED BY O.P 4041;[04] VERIFIED AND INSPECTED STEP #1; #2 AND #3.;[05] STARTED LOCATE AND DRILL OF NEW L2 DOOR INNER CHORD AS PER REFERENCE SRM 51-40-05-0G-0.;[06] CONTINUED LOCATE AND DRILL OF NEW L2 DOOR INNER CHORD AS PER REFERENCE SRM 51-40-05-0G-0.;[07] ACCOMPLISHED LOCATE AND DRILL OF NEW L2 DOOR INNER CHORD AS PER REFERENCE SRM 51-40-05-0G-0.;[08] TREATED AND PRIMED COUNTERSUNK HOLES AS PER REFERENCE AMM 51-21-41-370-803 AND 51-21-72-370-804;[09] VERIFIED AND INSPECTED STEP #5; #6; #7 AND #8.;[10] OK TO INSTALL NEW INNER CHORD.;[11] MIXED SEALANT BMS 5-95 AT 12:00AM 3-17-2023; SQUEEZE OUT AND FASTENER INSTALLATION VERIFICATION DUE BY 8:00AM 3-20-2023;[12] STARTED INSTALLATION OF NEW L2 DOOR INNER CHORD AS PER REFERENCE SRM 51-40-02-0G-0;[13] CONTINUED INSTALLATION OF NEW L2 DOOR INNER CHORD AS PER REFERENCE SRM 51-40-02-0G-0 AND DGW 147A8501;[14] ACCOMPLISHED INSTALLATION OF NEW L2 DOOR INNER CHORD AS PER REFERENCE SRM 51-40-02-0G-0 AND DGW 147A8501;[15] VERIFIED STEPS 11; 12; 13 AND 14.
CORROSION ** BETWEEN STA 306.9 AND STA 312 AT ANGLE INNER BEAM WL 208<[01] INSTALLED EWIS PROTECTION AT L1 DOOR LOWER SILL INNER CHORD AREA PER B737-700 AMM 20-60-07-913-801.;[02] EVALUATED CORROSION AND FOUND OUT OF LIMITS PER B737-700 SRM 53-10-15-1A-1; CORROSION ALL THE WAY THRU.
CORROSION** AT LOWER SIDE FRAME STA 303.9; LBL 64; WL 208.1 CORROSION** AT LOWER SIDE FRAME STA 303.9 LBL64 WL 208.1<[01] REMOVED CORROSION AT LOWER SIDE FRAME AT FRAME STA 306.9 LBL 64 PER B737-700 SRM 51-10-02-0G-0;[02] PERFORMED VISUALLY INSPECTION AT FRAME PER B737-700 SRM 51-10-02-0G-0;[03] VERIFIED STEP 1 AND 2 AND PERFORMED GVI OF BLENDED AREA;[04] DAMAGE HAS BEEN REPAIRED PER EA 23-153-00948 WIP 1 [TTG8Q00JZPDD] <BR>WIP 2 [TTG8Q00K21ZJ] FINAL EA [TTG8Q00K6QF5] REFERENCE BOEING SERVICE REQUEST ID 4-5767628680 AND BOEING MESSAGE PRO-SWA-23-0039-02B WITH FAA FORM 8100-9 [STAGE 1 & 2].;[05] THERE ARE NO SPECIFIC LIMITS OR REPAIRS WITHIN THE 737-700 SRM FOR THE SUBJECT DAMAGE. DAMAGE HAS BEEN REPAIRED PER EA 23-153-00948 WIP 1 [TTG8Q00JZPDD] WIP 2 [TTG8Q00K21ZJ] FINAL EA [TTG8Q00K6QF5] REFERENCE BOEING SERVICE REQUEST ID 4-5767628680 AND BOEING MESSAGE PRO-SWA-23-0039-02B WITH FAA FORM 8100-9 [STAGE 1 & 2].;[06] VERIFIED STEP 5
MAIN CABIN CENTER AREA BETW. STA 727B THRU 727E FLOOR PANEL #241KF TOP SKIN PEELING OFF SOME AREAS<[01] REMOVED FLOOR PANEL # 241KF IAW B737-700 AMM 53-21-00-000-801.;[02] REMOVED THE DAMAGED FACESHEET AND PREPARED DAMAGED AREA AT MAIN CABIN CENTER AREA BETW STA 727B THRU 727E FLOOR PANEL # 241KF REF : B 737 SRM 53-00-50-2R-1 PARAGRAPH 3;[03] VERIFIED 1. AND 2. <BR>OK FOR REPAIR.;[04] APPLIED REPAIR AT DAMAGED AREA FLOOR PANEL #241 KF REF: B737 SRM 53-00-50-2R-1 PARAGRAPH 3 AND RESIN PO# 1799598; CLOTH PO# 1690463;[05] VERIFIED STEP 4.;[06] FLOOR PANEL # 241KF WILL BE INSTALLED ON TASK CARD TTG8Q00K0YMI;[07] TTG8Q00K0YM1
MAIN CABIN L/H SIDE FLOOR PANEL #221BF MISSING MATERIAL AT O/B CORNER<[01] FABRICATED MAIN CABIN FWD WET AREA FLOOR PANEL #221BF BY OUTSIDE VENDOR (AERO MARINE) WITH P.O #2011815 REF. DRAWING #141A5810. THIS PANEL WILL BE INSTALL ON FAULT #TTG8Q00HHHPN;[02] VERIFIED STEP 1
CORROSION AT STA 312 LBL 50 TOP SIDE OF FLOOR BEAM WL 208.1<[01] REMOVED CORROSION AT STA 312 LBL 50 TOP SIDE OF FLOOR BEAM PER B737-700 SRM 51-10-02-0G-0.;[02] VERIFIED STEP 1.;[03] ACCOMPLISHED REPAIR AT MAIN CABIN FLOOR BEAM STA 312 LBL 50 PER EA #23-153-00921;[04] VERIFIED STEP 3 REPAIR PER EA #23-153-00921
CORROSION AT STA 312 TO 294.5 LBL 10; WL 208.1; LAVATORY BASE SUPPORT INTERCOSTAL<[01] REMOVED AND REPLACED INTERCOSTAL BETWEEN STA 294.5 AND STA 312 LBL 10 PER B737-700 SRM 51-40-02-0G-0 AND DRWG #141A5600.;[02] VERIFIED REPLACEMENT OF INTERCOSTAL BETWEEN STA 294.5 AND STA 312 LBL 10
MAIN CABIN AFT AREA BETW. STA 827 THRU 887 FLOOR PANEL #241UF TOP SKIN PEELING OFF SOME AREAS<[01] REMOVED THE FACESHEET AND PREPARED DAMAGED AREA AT MAIN CABIN CENTER AREA BETW STA 727B TRUR 727E FLOOR PANEL #241KF REF: B 737 SRM 53-00-50-2R-1 PARAGRAPH 3;[02] VERIFIED 1.<BR>OK TO REPAIR.;[03] CORRECTION STEP #1; REMOVED THE FACESHEET AND PREPARED DAMAGED AREA AT MAIN CABIN AFT AREA BETW. STA 827 TRUR 887 FLOOR PANEL #241UF REF: B 737 SRM 53-00-50-2R-1 PARAGRAPH 3;[04] APPLIED REPAIR AT DAMAGED AREA FLOOR PANEL #241UF REF: B737 SRM 53-00-50-2R-1 PARAGRAPH 3 AND RESIN PO# 1799598 CLOTH PO# 1690463;[05] VERIFIED 3. AND 4.
CORROSION FOUND AT AFT WET AREA UNDER PANEL 242VF FROM STA 986.5 TO 1006; RBL 24 TO RBL 25; WL 208.1<[01] AFTER INSPECTION OF FLOOR STRUCTURE UNDER PANEL 242VF. FOUND CORROSION AT WEB BETWEEN STA 986.5 AND STA 1006; RBL 38. FOUND OUT OF LIMITS. NO DAMAGE IS PERMITTED AS PER SRM 53-70-51-1A-1. REMOVED AND REPLACED WEB AT CABIN AFT WET AREA BETWEEN STA 986.5 AND STA 1016; RBL 38 AS PER SRM 51-40-02-0G AND DWG 147A5730.;[02] VERIFIED STEP 1.
FUSELAGE SKIN EXTERNAL SPOT OF CORROSION AT STA 747+10 BETWEEN S1 AND S-2R (ON SKIN AND AROUND OF ADJACENT RIVETS)<[01] C/W INSTRUCTIONS
CORROSION AROUND FASTENER HOLE AT STA 986.5; RBL 45; WL 208.1<[01] JOB WAS ACCOMPLISHED ON ITEM TTG8Q00KBMYQ;[02] VERIFIED STEP 1.
R2 DOOR LH SIDE INNER CORE HAS SEVERAL SPOTS OF CORROSION. DOT 82-006. CORROSION LOWER MAIN SILL ASSY INNER CHORD<[01] FOUND DEEP CORROSION EXFOLIATION AT R2 DOOR LOWER SILL INNER CHORD STA 980 APPROX. FOUND OUT OF LIMITS AS PER SRM 53-70-15-1A-1;[02] STARTED R2 DOOR LOWER SILL INNER CHORD REMOVAL AS PER SRM 51-40-02-0G-0;[03] REMOVED R2 DOOR LOWER SILL INNER CHORD AS PER SRM 51-40-02-0G-0;[04] STARTED R2 DOOR INNER CHORD LOCATED AND DRILLED AS PER REF SRM 51-40-05-0G-0;[05] CONTINUED R2 DOOR INNER CHORD LOCATED AND DRILLED AS PER REF SRM 51-40-05-0G-0;[06] LOCATED AND DRILLED R2 DOOR INNER CHORD AS PER REF SRM 51-40-05-0G-0;[07] TREATED AND PRIMED COUNTERSUNK HOLES AS PER REFERENCE AMM 51-21-41-370-803 AND 51-21-72-370-804;[08] VERIFIED STEP NO 1- 7. OK TO INSTALL R2 DOOR INNER CHORD.;[09] STARTED R2 DOOR INNER CHORD. INSTALLATION AS PER SRM 51-40-02-0G-0 AND DWG 147A8501<BR>PERFORMED BY AJ 35462;[10] MIXED SEALANT BMS 5-95 AT 22:00 3-22-2023. SQUEEZE OUT AND FASTENER INSTALLATION DUE BY 0700 3-26-2023.;[11] CONTINUED R2 DOOR INNER CHORD. INSTALLATION AS PER SRM 51-40-02-0G-0 AND DWG 147A8501<BR>PERFORMED BY AJ 35462;[12] CONTINUED R2 DOOR INNER CHORD. INSTALLATION AS PER SRM 51-40-02-0G-0 AND DWG 147A8501;[13] INSTALLED R2 DOOR LOWER INNER CHORD. AS PER SRM 51-40-02-0G-0 AND DWG 147A8501;[14] RII.... VERIFIED STEPS 9; 10; 11; 12 AND 13.
FOUND SEVERAL SPOTS OF LIGHT SURFACE CORROSION AT AFT WET AREA FROM STA 1016+ UNDER FLOOR PANEL 241AEF. DOT 82-001 CORROSION AT FLOOR SURFACE FIXED SKIN FROM STA 1016 TO STA 1040 FROM LBL 0 TO LBL 40 WL 208.1.<[01] NO DAMAGE PERMITTED AT WEB AREA AS PER REFERENCE SRM 53-70-51-1A-1. FOUND OUT OF LIMITS.;[02] REMOVED AFT WET AREA FLOOR WEB FROM STA 1006 TO STA 1016 BL0 TO LBL 34 AS PER REFERENCE SRM 51-40-02-0G-0.;[03] VERIFIED STEP #1 AND #2.;[04] APPLIED FILLET SEALANT AT EDGE AREA OF AFT WET AREA FROM STA 1006 THRU STA 1016 WEB PER B737-700 AMM 51-31-00-390-804;[05] REMOVED AND REPLACED FLOOR WEB AT AFT WET AREA STA 1006 TO STA 1016 BL0 TO LBL 34 AS PER REFERENCE SRM 51-40-02-0G-0.
CORROSION AROUND FASTENER HOLES AT STA 986.5; FROM RBL 44 TO LBL44; WL 208.1<[01] FOUND DEEP CORROSION EXFOLIATION OF SEVERAL FASTENER HOLES UPPER AND LOWER FLANGE AT FLOOR BEAM STA 986.5 BETWEEN LBL-40 AND RBL-40. 100% MATERIAL LOST. OUT OF LIMITS AS PER SRM 53-70-51-1A-1;[02] CABIN STA 968.5 FROM RBL 44 TO LBL 44; WL 208.1. ACCOMPLISHED PER EA 23-153-00836 ON ITEM TTG8Q00KBMYQ;[03] VERIFIED STEP 1 AND STEP 2.
MAIN CABIN CENTER FLOOR PANEL BETW. STA 480 THRU 500 231GF TOP SKIN PEELING OFF<[01] REMOVED THE DAMAGED FACESHEET AND PREPARED AREA AT MAIN CABIN CENTER AREA BETW. STA 480 THRU 500 FLOOR PANEL # 231GF REF : B 737 53-00-50-2R-1 PARAGRAPH 3;[02] VERIFIED STEP 1.;[03] APPLIED REPAIR AT DAMAGE AREA FLOOR PANEL #231 GF; REF: B 737 SRM 53-00-50-2R-1 PARAGRAPH 3 AND RESIN PO#1799598; CLOTH PO#1690463;[04] VERIFIED STEP 3
MAIN CABIN CENTER FLOOR PANEL BETW. STA 420 THRU 480 #231DF TOP FIBERGLASS SKIN PEELING OFF ON SOME AREAS<[01] REMOVED THE DAMAGED FACESHEET AND PREPARED DAMAGED AREA AT MAIN CABIN CENTER FLOOR PANEL #231DF REF : B737 SRM 53-00-50-2R-1 PARAGRAPH 3;[02] VERIFIED STEP 1.;[03] APPLIED REPAIR AT DAMAGE AREA FLOOR PANEL #231 DF; REF: B 737 SRM 53-00-50-2R-1 PARAGRAPH 3 AND RESIN PO#1799598; CLOTH PO#1690463;[04] VERIFIED STEP 3;[05] OK TO INSTALL FLOOR PANEL #231DF
MAIN CABIN CENTER SECTION L/H SIDE FLOOR PANEL #231JF TOP FIBERGLASS SKIN PEELING OFR ON CENTER AREA BTW. STA 480 THRU 500<[01] PREPARED DAMAGED AREA FOR REPAIR; AT L/H SIDE FLOOR PANEL#231JF AS PER B737 SRM 53-00-50-2R-1;[02] REPAIRED DAMAGED AREA AT L/H SIDE FLOOR PANEL#231JF AS PER B737 SRM 53-00-50-2R-1 MATERIAL USED PO#1799598 PO#1690463;[03] VERIFIED STEPS 1 AND 2.
CORROSION AROUND FASTENER HOLE AT STA 986.5; LBL 45; WL 208.1<[01] JOB WAS ACCOMPLISHED ON ITEM TTG8Q00KBMYQ;[02] VERIFIED STEP 1.
MAIN CABIN FLOOR PANEL BETW. STA 500 THRU 520 #231KF TOP FIBERGLASS SKIN PEELING OFF SOME AREAS<[01] REMOVED THE DAMAGED FACESHEET AND PREPARED DAMAGED AREA AT MAIN CABIN FLOOR PANEL #231KF REF: B737 SRM 53-00-50-2R-1 PARAGRAPH 3;[02] VERIFIED STEP 1.;[03] APPLIED REPAIR AT DAMAGE AREA FLOOR PANEL #231 KF; REF: B 737 SRM 53-00-50-2R-1 PARAGRAPH 3 AND RESIN PO#1799598; CLOTH PO#1690463;[04] VERIFIED STEP 3
MAIN CABIN FWD WET AREA FLOOR PANEL #221EF TOP SKIN LARGE AREA FIBERGLASS PEELING OFF<[01] REPLACED MAIN CABIN FLOOR PANEL #221EF WITH A NEW PANEL REF.B73<BR>7-700 AMM 53-21-00-400-801. FLOOR PANEL WILL BE INSTALL ON FAULT #TTG8Q00HHHPG;[02] VERIFIED STEP 1
AFTER REMOVED LEFT WING LOWER INBOARD FIXED TRALING EDGE PANEL #551GB FOUND GIGGLE PLATE AT INNER WING EDGE WITH CRACK<[01] REMOVED; REPLACED AND INSTALLED GIGGLE PLATE AT WING PANEL #551GB.
AFTER REMOVED LEFT WING INBOARD LOWER TREALING EDGE PANEL 561AB; FOUND SUPPORT TO ATTACH PANEL WITH 0.500'CRACK AT END AREA<[01] REMOVED AND REPLACED SUPPORT.
SEATS BACKS 11DEF MOVE AFT ( IN FRONT OF EMERGENCY EXIT ROW ) SEATS BACKS 11DEF MOVE AFT ( IN FRONT OF EMERGENCY EXIT ROW ) NEEDS ADJUSTMENT<[01] ADJUSTED SEATS 11 DEF PER AMM 25-22-00 PER SEAT BACK LIMIT BREAK FORCE OVER
OVERWING EMERGENCY EXIT LIGHT INOP. FO SIDE. FO SIDE OVERWING EMERGENCY EXIT LIGHT OPS CHECKED GOOD PER AMM 33-51-01.
DOT A24-100 LH WING L/E WING TO BODY FAIRING SUPPORT STRUCTURE CRACKED. LOCATED AT FWD LOWER CORNER OF PANEL 195AL. / [01] REMOVED DAMAGED ANGLE IAW SRM 51-40-02-0G-0.;[02] AUDIT C/W
DOT A24-10 MID CABIN FLOOR BOARD 231XF HAS PULLED COMPOSITE FIBERS ON UPPER SURFACE. / [01] EVALUATED DAMAGE; TOP SIDE OF PANEL IS REPAIRABLE IAW B737 SRM 53-00-50-2R-1 REPAIR 1; TAP TEST GOOD NO DELAMINATION NOTED. <BR><BR>CLEANED; PREPPED DAMAGED AREAS IAW B737 SRM 53-00-50-2R-1 PAR 3 STEPS A;C;E; AND J. <BR><BR>VERIFIED REPAIR MATERIALS IAW B737 SRM 53-00-50-2R-1 TABLE 201; RESIN EPOCAST50A(A150262)); FIBERGLASS CLOTH BMS9-3(A150508); <BR><BR>REQUIRES OKAY TO BOND.;[02] VERIFIED STEP 1 AND OK TO BOND;[03] BONDED REPAIR IAW SRM 53-00-50-2R-1 STEP 3 K-M. CURED AT 150 DEGREES (AAR 30347 EXP 4-30-23). TAP TEST GOOD.;[04] REPAIRED MID CABIN FLOOR BOARD 231XF UPPER SURFACE IAW SRM 53-00-50-2R-1 AND SRM 53-00-50-2R-0 REPAIR GENERAL.;[05] VERIFIED STEPS 3-4
DOT A24-11 MID CABIN FLOOR BOARD 242BF HAS PULLED COMPOSITE FIBERS ON UPPER SURFACE. / [01] EVALUATED DAMAGE; TOP SIDE OF PANEL IS REPAIRABLE IAW B737 SRM 53-00-50-2R-1 REPAIR 1; TAP TEST GOOD NO DELAMINATION NOTED. <BR><BR>CLEANED; PREPPED DAMAGED AREAS IAW B737 SRM 53-00-50-2R-1 PAR 3 STEPS A;C; E AND J. <BR><BR>VERIFIED REPAIR MATERIALS IAW B737 SRM 53-00-50-2R-1 TABLE 201; RESIN EPOCAST50A(A150262)); FIBERGLASS CLOTH BMS9-3(A150508); <BR><BR>REQUIRES OKAY TO BOND.;[02] VERIFIED STEP 1 AND OK TO BOND;[03] BONDED REPAIR IAW SRM 53-00-50-2R-1 STEP 3 K-M. CURED AT 150 DEGREES (AAR 30347 EXP 4-30-23). TAP TEST GOOD.;[04] REPAIRED MID CABIN FLOOR BOARD 242BF UPPER SURFACE IAW SRM 53-00-50-2R-1 AND SRM 53-00-50-2R-0 REPAIR GENERAL.;[05] VERIFIED STEPS 3-4
DOT A24-12 MID CABIN FLOOR BOARD 241BF HAS PULLED COMPOSITE FIBERS ON UPPER SURFACE. / [01] EVALUATED AND FOUND MISSING PLIES ON UPPER SURFACE. NO DAMAGE TO COMPOSITE SUBSTRATE. FOUND TO BE REPAIRABLE IAW SRM 53-00-50-2R-1.<BR><BR>CLEANED AND PREPPED IAW SRM 53-00-50-2R-1 STEP 3 A; C; E-F.<BR><BR>APPLIED POTTING COMPOUND IAW SRM 53-00-50-2R-1 STEP 3 G-J. CURED AT 120 DEGREES (OVEN B0-06 EXP 2-4-23). POTTING COMPOUND (A153167)<BR><BR>VERIFIED MATERIAL IAW SRM 53-00-50-2R-1 TABLE 201. RESIN (A147958); FABRIC (A150508).<BR><BR>REQUEST OK TO BOND;[02] VERIFIED STEP 1 AND OK TO BOND;[03] BONDED REPAIR IAW SRM 53-00-50-2R-1 STEP 3 K-M. CURED AT 150 DEGREES (AAR 30347 EXP 4-30-23). TAP TEST GOOD.;[04] REPAIRED MID CABIN FLOOR BOARD 241BF UPPER SURFACE IAW SRM 53-00-50-2R-1 AND SRM 53-00-50-2R-0 REPAIR GENERAL.;[05] VERIFIED STEPS 3-4
A-240 DOT 001 #2 ENGINE OUTBD FAN COWL ATTACH ANGLE AFT SIDE OF OIL SERVICE DOOR OPENING CRACKED. / [01] REMOVED #2 ENG OUTBD FAN COWL ATTACH ANGLE IAW SRM 51-40-02;[02] VERIFIED ACTION 1;[03] OK TO INSTALL NEW #2 ENGINE OTBD FAN COWL ATTACH ANGLE;[04] INSTALLED NEW SHIELD ANGLE ON #2 ENGINE O/B FAN COWL AT AFT SIDE OF OIL SERVICE DOOR IAW SRM 51-40-02-0G-0 AND CMM 71-13-30.;[05] VERIFIED STEP 4<BR>AUDIT CW
CRACK FOUND ON UPPER ATTACH ANGLE STA 663 RBL 8 (WL 167) / [01] VERIFIED ITEM 2 OF STEP 8;[02] VERIFIED STEP 9;[03] LEAK CHECKED REPAIR AREA NO LEAK NOTED I.A.W MM 28-11-00-400-801;[04] LEAK CHECK GOOD<BR>AUDIT C/W
CRACK FOUND ON UPPER ATTACH ANGLE STA 663 LBL 8 (WL 167) / [01] VERIFIED ITEM 2 OF STEP 5;[02] VERIFIED ITEM 2 OF STEP 8;[03] VERIFIED STEP 9;[04] LEAK CHECKED REPAIR AREA NO LEAK NOTED I.A.W MM 28-11-00-400-801;[05] NO LEAKS NOTED<BR>AUDIT C/W
SLIDE LOOSE ON R-2 DOOR. R-2 DOOR SLIDE CHECKED FOR SECURITY IAW MMMM 25-66-01. OK FOR SERVICE.
FOUND #2 SLAT UPPER SKIN CRACKED @ SLAT STATION 327 DURING BIRD STRIKE INSPECTION DENT IS L= 10.0 W= 2.5CRACK IS 2.25 / [01] REMOVED #2 LE SLAT IAW AMM 27-81-21. NEEDS INSTALL AND RIG CHECK.;[02] INSPECTED CAN HOUSING AND FOUND NO DEBRIS OR FOD. INSPECTED HARDWARE AND FOUND 3 EA STOP FITTINGS BAD. ALL OTHER HARDWARE OK TO INSTALL PER AMM 27-81-21;[03] BEGAN INSTALLATION OF #2 LE SLAT IAW AMM 27-81-21. TEMP INSTALLED HARDWARE ON MAIN SLAT TRACKS AND AUXILIARY SLAT TRACKS. WING ANTI-ICE TELESCOPING DUCT STILL NEEDS TO BE TORQUED. SLAT ACTUATOR STILL NEEDS TO BE INSTALLED.;[04] PERFORMED AMM 27-81-21 FROM STEP G (4) THRU H(14) ON LH #2 SLAT. PERFORMED AMM 27-81-00-820-803 UPTO STEP H(6). REMAINDER OF AMM TASK 27-81-00-820-803 FOR LEADING EDGE SLATS ADJUSTMENT IS REQ;[05] INSPECTED ACCOMPLISHMENT OF AMM 27-81-21 FROM STEP G (4) THRU H(14) ON LH #2 SLAT. PERFORMED AMM 27-81-00-820-803 UPTO STEP H(6). REMAINDER OF AMM TASK 27-81-00-820-803 FOR LEADING EDGE SLATS ADJUSTMENT IS REQ;[06] REMOVED REPLACEMENT #2 SLAT AND FOUND INCORRECT SLAT TRACK LENGTHS ON THE INBOARD AND OUTBOARD. THIS INSTALL MUST BE RE-ACCOMPLISHED REFERENCING APPLICABLE STEPS IN AMM 27-81-21.;[07] INSTALLED NEW #2 SLAT IAW AMM 27-81-21. RIGGING AND OPS CHECK GOOD. REMOVED SLAT P/N 114A5020-5 DOES NOT EXIST IN MXI. SERIAL NUMBER 001770 IS THE CORRECT REMOVED SERIAL NUMBER.;[08] C/W RII OF INSTALL OF NEW #2 SLAT IAW AMM 27-81-21
LOWER PYLON FAIRING BELOW ACCESS PANEL 434BL SHOWS FRETTING WEAR FROM PYLON DRAIN TUBE / [01] REMOVED AND REPLACED LOWER PYLON FAIRING AT PYLON DRAIN TUBE PER SRM 51-40-02 AND SRM 51-40-05.
LH MLG CENTER DOOR FWD LOWER ATTACH POINT BRACKET IS CRACKED /
LH WING T/E CAVITY TO I/B FLAP SEAL SUPPORT BRACKET IS CRACKED BEHIND #1 PYLON / [01] REMOVED AND REPLACED LH WING T/E CAVITY TO I/B FLAP SEAL SUPPORT BRACKET PER SRM 51-40-02 AND AMM 20-50-11
RH MLG CENTER DOOR FWD LOWER MOUNTING ATTACH WEB HAS A 1.0' CRACK /
SUPPLEMENTAL INFORMATION: AT FL370 APU LIGHT LOW OIL PRESSURE ILLUMINATED SHUT DOWN PER QRH OTS - APU & #2 GEN INOP_APU - COMPLIED WITH FIM 49-90 803 TASK. SERVICED OIL TANK. NO CURRENT FAULTS.R&R APU BTC CO803 IN REF TO AMM 24 - 21 - 41 R&R #2 ENGINE BTC CO802 IN REF TO AMM 24 - 21 - 41 R&R AC SYS GEN OVHD PANEL P54 IN REF TO AMM 24 - 21 - 51 OPS CHECK IS OK_ / OK TO CONTINUE ON MEL 24 - 1 - 02 SP NUMBER ONE AUTHORIZATION NUMBER 36950 UPDATE VERIFIED PANEL WAS BAD FOUND A BAD SWITCH REMOVED AND REPLACED APU BUS TIE CONTACTOR CO803 IN REFERENCE TO AIRCRAFT MAINTENANCE MANUAL 24 - 21 - 41 REMOVED AND REPLACED #2 ENGINE BUS TIE CONTACTOR CO802 IN REFERENCE TO AIRCRAFT MAINTENANCE MANUAL 24 - 21 - 41 REMOVED AND REPLACED AC SYSTEM GENERATOR OVERHEAD PANEL P54 IN REFERENCE TO AIRCRAFT MAINTENANCE MANUAL 24 - 21 - 51 OPS CHECK IS OK
SUPPLEMENTAL INFORMATION: AT FL370 APU LIGHT LOW OIL PRESSURE ILLUMINATED SHUT DOWN PER QRH OTS - APU & #2 GEN INOP_APU - COMPLIED WITH FIM 49-90 803 TASK. SERVICED OIL TANK. NO CURRENT FAULTS.R&R APU BTC CO803 IN REF TO AMM 24 - 21 - 41 R&R #2 ENGINE BTC CO802 IN REF TO AMM 24 - 21 - 41 R&R AC SYS GEN OVHD PANEL P54 IN REF TO AMM 24 - 21 - 51 OPS CHECK IS OK_ / OK TO CONTINUE ON MEL 24 - 1 - 02 SP NUMBER ONE AUTHORIZATION NUMBER 36950 UPDATE VERIFIED PANEL WAS BAD FOUND A BAD SWITCH REMOVED AND REPLACED APU BUS TIE CONTACTOR CO803 IN REFERENCE TO AIRCRAFT MAINTENANCE MANUAL 24 - 21 - 41 REMOVED AND REPLACED #2 ENGINE BUS TIE CONTACTOR CO802 IN REFERENCE TO AIRCRAFT MAINTENANCE MANUAL 24 - 21 - 41 REMOVED AND REPLACED AC SYSTEM GENERATOR OVERHEAD PANEL P54 IN REFERENCE TO AIRCRAFT MAINTENANCE MANUAL 24 - 21 - 51 OPS CHECK IS OK
SUPPLEMENTAL INFORMATION: AT FL370 APU LIGHT LOW OIL PRESSURE ILLUMINATED SHUT DOWN PER QRH OTS - APU & #2 GEN INOP_APU - COMPLIED WITH FIM 49-90 803 TASK. SERVICED OIL TANK. NO CURRENT FAULTS.R&R APU BTC CO803 IN REF TO AMM 24 - 21 - 41 R&R #2 ENGINE BTC CO802 IN REF TO AMM 24 - 21 - 41 R&R AC SYS GEN OVHD PANEL P54 IN REF TO AMM 24 - 21 - 51 OPS CHECK IS OK_ / OK TO CONTINUE ON MEL 24 - 1 - 02 SP NUMBER ONE AUTHORIZATION NUMBER 36950 UPDATE VERIFIED PANEL WAS BAD FOUND A BAD SWITCH REMOVED AND REPLACED APU BUS TIE CONTACTOR CO803 IN REFERENCE TO AIRCRAFT MAINTENANCE MANUAL 24 - 21 - 41 REMOVED AND REPLACED #2 ENGINE BUS TIE CONTACTOR CO802 IN REFERENCE TO AIRCRAFT MAINTENANCE MANUAL 24 - 21 - 41 REMOVED AND REPLACED AC SYSTEM GENERATOR OVERHEAD PANEL P54 IN REFERENCE TO AIRCRAFT MAINTENANCE MANUAL 24 - 21 - 51 OPS CHECK IS OK
RH HORIZONTAL LE PANEL 331B; 3RD RIB LE STA 95.96 FROM INBD EDGE; HAS A CRACK AT UPPER MOST AFT FASTENER ; PANEL 341B NOT 331B / APPLIED CIC TO RIB IAW AMM 51-21-91; REMOVED AND REPLACED RH STAB LE RIB CHORD AT LE STA 95.96 IAW DWG 186A1303 REV 1; SRM 51-40-02-0G-0; INSPECTION CW. AUDIT CW
R/H OVERWING EXIT EMERGENCY EXIT LOCATOR LIGHT L1358 IS INOP ; / REPLACED LAMPS IN R/H OVERWING EXIT EMERGENCY EXIT LOCATOR LIGHT L1358; OPS CHECK GOOD IAW AMM 33-51-01-960-801.<BR>ATAG A69819; ALL WORK C/W<BR>AUDIT C/W
LEFT OVERWING ESCAPE LIGHT (L7) INOP ; RIGHT OVERWING ESCAPE LIGHT (L7) INOP / REPLACED BATTERY PACK AND BATTERY PACK CHARGER M1669 IAW AMM 33-51-06-960-805 AND AMM 33-51-06-960-806. RIGHT OVERWING ESCAPE SLIDE LIGHT OPS CHECK GOOD.; REPLACED BATTERY PACK AND BATTERY PACK CHARGER M1669 IAW AMM 33-51-06-960-805 AND AMM 33-51-06-960-806. RIGHT OVERWING ESCAPE SLIDE LIGHT (L7) OPS CHECK GOOD.; ALL WORK C/W<BR>AUDIT C/W
LH HORZ STAB RIB 120.30; CRACKED O/B LOWER FLANGE AT FWD END IN RADIUS ; / APPLIED CIC TO REPAIR AREA & OEM RIB IAW AMM 51-21-91; REMOVED DAMAGE ON L/H HORIZ STAB RIB 120.3 FWD LOWER O/B END IAW B737 SRM 55-10-09-2R-5. ACCOMPLISHED REPAIR PER EA 21-155-01399-WIP1; VERIFIED STEP 15 & 16 C/W<BR>FINAL AUDIT C/W
LEFT OVERWING ESCAPE LIGHT (L6) INOP / REPLACED BATTERY PACK AND BATTERY PACK CHARGER M1668 IAW AMM 33-51-06-960-805 AND AMM 33-51-06-960-806. LEFT OVERWING ESCAPE SLIDE LIGHT OPS CHECK GOOD.; ALL WORK C/W<BR>AUDIT C/W
LEFT OVERWING ESCAPE LIGHT (L6) INOP / REPLACED BATTERY PACK AND BATTERY PACK CHARGER M1668 IAW AMM 33-51-06-960-805 AND AMM 33-51-06-960-806. LEFT OVERWING ESCAPE SLIDE LIGHT OPS CHECK GOOD.; ALL WORK C/W<BR>AUDIT C/W
LEFT OVERWING ESCAPE LIGHT (L7) INOP ; RIGHT OVERWING ESCAPE LIGHT (L7) INOP / REPLACED BATTERY PACK AND BATTERY PACK CHARGER M1669 IAW AMM 33-51-06-960-805 AND AMM 33-51-06-960-806. RIGHT OVERWING ESCAPE SLIDE LIGHT OPS CHECK GOOD.; REPLACED BATTERY PACK AND BATTERY PACK CHARGER M1669 IAW AMM 33-51-06-960-805 AND AMM 33-51-06-960-806. RIGHT OVERWING ESCAPE SLIDE LIGHT (L7) OPS CHECK GOOD.; ALL WORK C/W<BR>AUDIT C/W
RIGHT WING INBOARD MAIN FLAP TRAILING EDGE SKIN DISBONDED AT OUTBOARD END / REPAIRED AREA OF DELAMINATION ON I/B R/W MAIN FLAP LOWER SKIN. IAW B737-700 SRM 57-53-01-2R-7;SRM 51-70-10-2R-4; SRM 51-70-10-2R-0; AMM 51-21-99-300-801.; STEP 12 OK; SUMMARY STATEMENT AND AUDIT OK
LH HORIZ STAB RIB AT ST A 120.3 FWD LOWER FLANGE COMMON TO SKIN I/B FASTENER HOLE CRACKED 3RD FROM FWD (MARKED) ; / REMOVED DAMAGED AREA FROM LH HORIZ STAB RIB AT STA 120.3 FWD LOWER FLANGE COMMON TO SKIN I/B FASTENER HOLE PER B737 SRM 51-10-02-0G-0. REPAIRED FLANGE PER EA 21-155-01399-WIP1 REV P1 AND FINAL; VERIFIED STEP 6 C/W IAW EA-21-155-01399 P1 AND FINAL<BR>FINAL AUDIT C/W; FINAL AUDIT C/W
LH HORIZ STAB RIB AT ST A 120.3 FWD LOWER FLANGE COMMON TO SKIN I/B FASTENER HOLE CRACKED 3RD FROM FWD (MARKED) ; / COMPLETED EA 21-155-01399 FINAL; FINAL AUDIT C/W
LH HORIZ STAB RIB AT ST A 120.3 FWD LOWER FLANGE COMMON TO SKIN I/B FASTENER HOLE CRACKED 3RD FROM FWD (MARKED) ; / ACCOMPLISHED EA 21-155-01399-WIP1; VERIFIED EA 21-155-01399-WIP1 ALL STEPS COMPLETE; FINAL AUDIT C/W
RIGHT HORIZONTAL STAB RIB STA 129.5 FWD UPPER FLANGE COMMON TO UPPER SKIN CRACKED ; / REMOVED DAMAGE; FABRICATED REPAIR PARTS AND INSTALLED REPAIR TO RH HORIZONTAL STAB RIB STA 129.5 FWD UPPER FLANGE IAW EA 21-155-01361; VERIFIED ITEM 29 AND 30; AUDIT C/W
AFT CARGO COMP. AFT BULKHEAD LOWER BULKHEAD STRAP CORRODED STA.947 APPROX STR 21R TO STR 25R WL 158 ; / FOUND MATERIAL LSS TO BE 100%; REMOVED AND REPLACED AFT CARGO AFT BULKHEAD RH SUPPORT RAIL BS 947 IAW SRM 51-40-02-0G-0; DWG 149A8117 REV -; RESTORED CIC IAW AMM 51-21-91; VERIFIED STEPS 7; 8 AND 9; AUDIT C/W
RIGHT HORIZONTAL STAB RIB STA 129.5 FWD UPPER FLANGE COMMON TO UPPER SKIN CRACKED ; / AUDIT C/W
FWD CARGO COMPT STA 500B - 500C LBL25 BAFFLE IS BENT AND AFT ANGLE IS CRACKED. DOT A-21-071 ; / VERIFIED ITEM 4.<BR>OK TO INSTALL.; INSTALLED BAFFLE STA 500B-C FWD PIT IAW SRM 51-40-02 & BOEING DWG 143A7510 REV B; INSPECTION CW CORROSION PROTECTION CW REF SWA WORK CARD 5330-E-16461-NG AUDIT CW 1. JASON EPPERSON (TECHNICIAN), 19-MAY-2021 02:10 UTC REMOVED BAFFLE AND ATTACH ANGLE BS 500B-500C LBL 25 IAW SRM 51-40-02-0G-0 2. FRED SKAGGS (TECHNICIAN), 19-MAY-2021 17:08 UTC NEW PART NO. IS 143A7510-11 IAW DWG 143A7505 REV B A TAG A49363 3. MARK COOPER (TECHNICIAN), 19-MAY-2021 17:30 UTC VERIFIED NEW BAFFLE IN ITEM 2 4. FRED SKAGGS (TECHNICIAN), 19-MAY-2021 18:39 UTC DRILLED NEW BAFFLE IAW BOEING DWG 143A7507 & SRM 51-40-05 5. BARRY ANDERSCH (TECHNICIAN), 19-MAY-2021 18:56 UTC VERIFIED ITEM 4. OK TO INSTALL. 6. FRED SKAGGS (TECHNICIAN), 19-MAY-2021 19:54 UTC INSTALLED BAFFLE STA 500B-C FWD PIT IAW SRM 51-40-02 & BOEING DWG 143A7510 REV B 7. ALFRED GUGLIELM (TECHNICIAN), 19-MAY-2021 20:15 UTC INSPECTION CW CORROSION PROTECTION CW REF SWA WORK CARD 5330-E-16461-NG AUDIT CW
STA 927-947 RBL 25 INTERCOSTAL FOUND CRACKED ; / REMOVED AND REPLACED INTERCOSTAL BS 927-947 RBL 20 IAW DWG 147A7500 REV C; SRM 51-40-02-0G-0. RESTORED CIC IAW AMM 51-21-91-620-802; ALL WORK C/W; AUDIT C/W
R1 DOOR CUTOUT STA 291+9; FWD UPPER STUB FRAME ABOVE UPPER HINGE HAS CRACK IN FASTENER HOLE COMMON TO UPPER HOLE IN SEAL DEPRESSOR. MARKED ; / REMOVED AND REPLACED R1 IAW SRM 51-40-02-0G-0 AND BOEING DWG 141A8370 REV C DOOR UPPER STUB FRAME; VERIFIED STEP 9; AUDIT C/W
RIGHT HORIZONTAL STAB RIB STA 129.5 FWD UPPER FLANGE COMMON TO UPPER SKIN CRACKED ; / VERIFIED TRIMMED DAMAGED AREA I.A.W EA21-155-01361 STEP1 COMPLETE; EA C/W; AUDIT C/W
RIGHT HORIZONTAL STABILIZER; RIB STA 92.7; RIB STIFFENER #1 CRACKED ABOVE LOWER FLANGE. CUT OUT DAMAGE AREA ON #1 STIFFENER STA.92.70 HORIZONTAL STAB RIB IAW SRM 55-10-09-2R-4 REPAIR4 VERIFIED MATERIAL ID FOR REPAIR PARTS 55100003-01 TAG #WN 4752 IAW DWG 55100003 REV B VERIFIED DAMAGE REMOVAL PER SRM 55-10-09-2R-4 AND VERIFIED MATERIAL FOR REPAIR PARTS ITEMS 1 AND 2 VERIFIED ITEMS 1; 2; AND 3 HFEC CUTOUT IAW B737 NDT PART 6; 51-00-00 PROC23.REMOVED DAMAGE AND REPAIRED RH HORIZONTAL STAB STA 92.7 RIB AT #1 STIFFENER IAW SRM 55-10-09-2R-4.
DOT-125-01 RIGHT HORIZONTAL STABILIZER RIB STA 129.5; FWD LOWER FLANGE CRACKED.
DURING REMOVAL OF RIGHT HAND HORIZONTAL STAB STA 92.70 RIB WAS CRACKED AT UPPER FORWARD CORNER ; / ADDING P1 AND FINAL TO ITEM 12. EA 21-155-01364-WIP 1 REV P1 AND FINAL COMPLETE; VERIFIED COMPLETION OF EA 21-155-01364-WIP1 REV P1 AND FINAL; VERIFIED STEPS 12; 13; 14; 15 & 16 COMPLETE. IAW EA 21-155-01364-P1 AND FINAL<BR>FINAL AUDIT C/W
DURING REMOVAL OF RIGHT HAND HORIZONTAL STAB STA 92.70 RIB WAS CRACKED AT UPPER FORWARD CORNER ; / VERIFIED STEPS ALL STEPS COMPLETE. IAW EA 21-155-01364-P1 AND FINAL<BR>FINAL AUDIT C/W
DURING REMOVAL OF RIGHT HAND HORIZONTAL STAB STA 92.70 RIB WAS CRACKED AT UPPER FORWARD CORNER ; / SUMMARY EA 21-155-01364 HAS BEEN APPROVED; ACTIVATED; AND ADDED AS A SUBTASK OF THE FAULT.<BR><BR>NOTE: THE TYPICAL WORK STEP ENG SIGN OFF WAS OMITTED FROM THE WIP1; THEREFORE THIS LABOR ROW WAS ADDED TO ACCOUNT FOR SWA ENGINEERING VERIFICATION THAT A SUMMARY EA WAS ISSUED.; COMPLETED ALL EA #21-155-01364-WIP1 STEPS; VERIFIED ALL STEPS COMPLETED<BR>FINAL AUDIT C/W
APU COWL DOOR; 38' AFT OF FWD EDGE; RIGHT SIDE FRAME; DEEP GOUGE. ; / N/A'D REQUIRED STEPS; VERIFIED ITEMS 9 AND 10<BR>AUDIT C/W; VERIFIED ITEMS 9 AND 10<BR>AUDIT C/W
CORROSION ON LOWER SURFACE OF Z ANGLE WL 156 RBL 20 STA 727C TO 767 AROUND NUT PLATES ; / VERIFIED LIMITE ON R/H Z-ANGLE; STA 727C TO STA 767. ORIG 'T' .040. REM 'T' .031; LOSS .009. FOUND TO BE OUT OF LIMITS IAW. SRM 51-10-02-0G-0; VERIFIED MATERIAL LOSS IS OUT OF LIMITS; VERIFIED LIMITS ON R/H Z-ANGLE; STA727C TO STA 767; ORIG 'T'.040; REM 'T' .031; LOSS .009. FOUND TO BE OUT OF LIMITS. IAW. SRM 53-00-53-1A-2
DOT# A45-013; AFT CARGO PIT; FLOOR SUPPORT RAIL HAS CORROSION; WL: 156; RBL: 14; STA: 767 TO 807. ; / REMOVED CORROSION IAW B737 SRM 51-10-02-0G-0. ORIGINAL T .071' REMAINING .058'; LOSS OF .013. OUT OF LIMITS IAW B737 SRM 53-00-53-1A-2 FIG 103 VIEW A-A. AAR TOOL # 32351 CAL DUE 01/12/22; REMOVED DAMAGED SECTION OF TRACK AT RBL 14 STA 747+10- STA 887 IAW B737 SRM 51-40-02-0G-0; VERIFIED REMOVAL OF CORROSION AND VERIFIED REMOVAL OF SEAT TRACK FROM STA 747 TO STA 887
DOT# A45-018; AFT CARGO PIT; FLOOR SUPPORT RAIL HAS CORROSION; WL: 156; LBL: 2.5; STA: 767+6. ; / REMOVED CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-00-53-1A-2 REMOVED DAMAGE AND REPAIRED IAW SRM 53-00-53-2R-2 APPLIED CIC TO AREA IAW AMM 51-21-91-620-802; TASK COMPLETE; FINAL AUDIT C/W
DOT# A45-006; AFT CARGO PIT; DOOR CUTOUT THRESHOLD WEB; UPPER SURFACE HAS CORROSION. WL: 156; RBL: 26; STA: 787+11 TO 827+10. ; / REMOVED CORROSION IAW SRM 51-10-02-0G-0; ORIGINAL T .045' REMAINING .036' LOSS OF .009'. OUT OF LIMITS IAW B737 SRM 53-60-15-1A-1 FIG 103 VIEW A-A. AAR TOOL 36649 CAL DUE 08/04/21; INSPECTED DAMAGE REMOVAL; VERIFIED MATERIAL LOSS TO BE OUT OF LIMITS.; REMOVED AFT CRGO DOOR SILL WEB IAW B737 SRM 51-40-02-0G-0
AFT CARGO PIT; RH FLOOR SHIELD HAS CORROSION; WL:156; RBL:22; STA: 767-787. REMOVED CORROSION ON AFT CARGO FORWARD FLOOR SHIELD ORIGINAL THICKNESS .050 REMAINING .030 REMOVED .020 SHIELD WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-60--15-1A-1 TOOL 36649 DUE 8-4-21; VERIFIED MEASUREMENTS; VERIFIED STEPS 1 & 2
DOT# A45-008; AFT CARGO PIT DOOR CUTOUT; RH INTERCOSTAL HAS CORROSION ON UPPER AND LOWER SURFACE; WL: 156; RBL: 19; 767 TO 767+8. ; / REMOVED CORROSION ON R/H INTERCOSTAL AT STATION 767 ORIGINAL THICKNESS .056 REMOVED .016 REMAINING .040 INTERCOSTAL WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-60-15-1A-1 VERIFIED BY TOOL 36649 DUE 8-4-21; VERIFIED CORROSION REMOVAL; FOUND TO BE OUT OF LIMITS.
DOT# A45-011; AFT CARGO PIT; LH Z-ANGLE HAS CORROSION; WL: 154; LBL: 20; STA: 727 TO 727C+10. REMOVE Z-ANGLE LH BS 727-727C + 10' IAW SRM 51-40-02-0G-0.; VERIFIED MATERIAL FOR Z-ANGLE AS PN BAC1496-377 7075 T6; 'A' TAG A81056 IAW SRM 53-60-53-01-2 FIG 2.; VERIFIED NEW PART EFFECTIVITY
DOT# A45-012; AFT CARGO PIT; LH Z-ANGLE HAS CORROSION; WL: 156; LBL: 21; STA: 727C+10 TO 807+10. ; / VERIFIED NEW PART EFFECTIVITY.; CONTINUED LOCATING AND DRILLING NEW Z-ANGLE IAW SRM 53-00-53-2R-5.; VERIFIED IN PROCESS STEP
DOT# A45-009; AFT CARGO PIT; RH Z-ANGLE HAS CORROSION; WL: 156; RBL: 20; STA: 727C+10 TO 767. ; / VERIFIED NEW Z-ANGLE MATERIAL AS PN BAC1496-377-7075 T6. A TAG A73414; IAW BOEING 737 SRM 53-60-53-01-2 FIGURE 2.; VERIFIED NEW PART EFFECTIVITY.; CONTINUED TO LOCATE AND DRILL Z-ANGLE IAW SRM 53-00-53-2R-5.
DOT# A45-020; AFT CARGO PIT; FLOOR SUPPORT RAIL HAS CORROSION; WL: 156; RBL: 8; STA: 767+6. ; / REMOVED CORROSION FROM FLOOR SUPPORT RAIL AT STA 767+6' RBL 8 MEASURED MATERIAL LOSS USING TOOL #1714 CAL DUE 10/6/21 ORIGINAL MATERIAL THICKNESS .071 LOSS OF .031 WITH .040 REMAINING IS OUT OF LIMITS IAW SRM 53-00-53-1A-2; VERIFIED ITEM 1.; UPDATED CORROSION MEASUREMENTS
RIGHT HORIZONTAL STAB RIB STA 92.70; RIB STIFFENER #3 IS CRACKED 1' ABOVE LOWER FLANGE. CRACK VERIFIED BY HFEC. DOT 177A-001 ; / CUT OUT DAMAGED AREA ON R/H HORZ STAB RIB ON #3STIFFENER I.A.W SRM55-10-09-2R-4.<BR>FABRICATED AND DRILLED REPAIR KIT I.A.W SRM55-10-09-2R-4.<BR>INSTALLED REPAIR PARTS I.A.W SRM55-10-09-2R-4; VERIFIED ITEM 22; AUDIT C/W
185-016 AFT CARGO;FLOOR PANEL SPLICE PLATE CORRODED AROUND FASTNER HOLES STA 887 LBL 16-RBL 16 WL 158 ; / REMOVED CORR0SION FROM AFT CARGO FLOOR SUPPORT PANEL SPLICE AT STA 887 LBL 16 RBL 16 VERIFIED OUT OF LIMITS DUE TO NO PUBLISHED LIMITS VERIFIED NEW PART P/N 140A9401-39 IAW DWG 146A9401 LOCATED AND DRILLED UP NEW PART IAW DWG 146A7500 AND SRM 51-40-05; VERIFIED STEP 10 COMPLETE; VERIFIED STEP 8 AND 1O<BR>AUDIT CW
DOT# A45-010; AFT CARGO PIT; RH Z-ANGLE HAS CORROSION; WL: 154; RBL: 20; STA: 727 TO 727C+10. ; / REMOVED CORROSION IAW RH STA 727-727C VERIFIED WITTH 10X MAGNIFY GLASS IAW SRM 53-00-53-1A-2. VERIFIED MATERIAL LOSS ORIGINAL THICKNESS .040' LOSS .008'; REMAINING MATERIAL .032' OUT OF LIMITS IAW SRM 530-00-53-1A-2. REMOVED; FABRICATED AND INSTALLED REPLACEMENT SECTION FROM STA 727-727C+10IAW SRM 51-40-02-0G-0 AND BOEING DWG 146A7500 REV B; SRM 53-00-53-2R-5; INSPECTION CW; CORROSION PROTECTION CW REF SWA WORK CARD 5360-E-16462-NG; AUDIT CW
185-015 AFT CARGO;RH FLOOR SHIELD CORRODED AROUND FASTNER HOLES STA 847-867 RBL 16 WL 158 ; / INSTALLED NEW SHIELD IAW SRM 51-40-02-0G-0 AND BOEING DWG 146A0081 REV A; VERIFIED INSTALLATION ON STEP 8; VERIFIED ITEMS 8 & 9.<BR>AUDIT COMPLETE.
185-019 AFT CARGO COMP.AFT BULKHEAD BOTTOM ANGLE CORRODED AROUND FASTNER HOLES STA.947 LBL 16-RBL 16 WL 158 ; / REMOVED CORROSION FROM AFT BULKHEAD LOWER SUPPORT RAIL. ORIGINAL T.080' REMAINING .062' LOSS OF .018' OUT OF LIMITS IAW SRM 53-00-53-1A-2 FIG 103 VIEW A-A; INSTALLED NEW AFT CARGO AFT BUKLHEAD SUPPORT ANGLE IAW SRM 51-40-02-G-0; DWG 149A8117 REV -; RESTORED CIC IAW AMM 51-21-91; VERIFIED STEP 9 AND 10; AUDIT C/W
DOT# A45-019; AFT CARGO PIT; FLOOR SUPPORT RAIL HAS CORROSION; WL: 156; RBL: 13; STA: 767+6. ; / REMOVED AND REPLACED TRACK SECTION RBL 13.8 BS 747+10-887 IN FAULT TTG8Q004YWLS; C/W; AUDIT C/W
DOT# A45-015; AFT CARGO PIT; RH Z-ANGLE; LOWER SIDE ATTACH CLIP IS CRACKED IN RADIUS; WL: 155; RBL: 21; STA: 727+5. ; / CLIP REMOVAL & INSTALLATION ACCOMPLISHED ON FAULT TTG8Q004YWGX; FABRICATED NEW CLIP P/N 146A7505-4; ON SHOP W/O 42136-1600-0004. LOCATED AND DRILLED IAW BOEING DWG 146A7504 REV A AND SRM 51-40-05-0G-0. APPLIED FINISHES IAW AMM 51-21-41-370-803 AND AMM 51-21-72-370-801; AMM 51-21-99-300-804. CLIP REMOVAL & INSTALLATION ACCOMPLISHED ON FAULT TTG8Q004YWGX; STEPS 14; 15 C/W; AUDIT C/W
DOT# A45-021; AFT CARGO PIT; FLOOR SUPPORT RAIL HAS CORROSION; WL: 156; RBL: 2.5; STA: 767+6. ; / REMOVED CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-00-53-1A-2 REMOVED DAMAGE AND REPAIRED IAW SRM 53-00-53-2R-2 APPLIED CIC TO AREA IAW AMM 51-21-91-620-802; TASK COMPLETE; FINAL AUDIT C/W
AFT CARGO PIT; RH ATTACH ANGLE ON LOWER SURFACE OF FLOOR SHIELD HAS CORROSION; WL:156; RBL:22; STA: 767+4. ; / REMOVED CORROSION ON ATTACH ANGLE AT STATION 767+4 ORIGINAL THICKNESS .050 VERIFIED BY TOOL 36649 DUE 8-4-21MATERIAL REMOVED .012 REMAINING .038 ANGLE WAS FOUND TO BE OUT OF LIMITS IAW B737 SRM 53-60-15-1A-1. REMOVED AND REPLACED ATTACH BRACKET SRM 51-40-02-0G-0; DWG 146A7500 REV A; ALL WORK C/W; AUDIT C/W
DOT-42-A22; CABIN STA 538; RBL1; FLOOR BBOARD SPLICE PLATE CRACKED @ INBD/AFT CORNER. ; / AUDIT CW; AUDIT CW; FOUND COMPLETE
DOT# A45-027; AFT CARGO PIT; RH INTERCOSTAL UNDER Z-ANGLE HAS CORROSION; WL:156; RBL:22; STA: 747-767. ; / [01] REMOVED CORROSION ON R/H INTERCOSTAL AT STATION 747-767 ORIGINAL THICKNESS .032 REMOVED .007 REMAINING .025 INTERCOSTAL WAS FOUND TO BE OUT OF LIMITS IAW B737 SRM 53-00-53-1A-2 VERIFIED BY TOOL 36649 DUE 8-4-21; [02] VERIFIED ITEM 1; [03] VERIFIED PART; INTERCOSTAL; P/N 146A7505-8 IAW BOEING DWG 146A7502 REV-<BR>ATAG WN4904; [04] VERIFIED STEP 3 COMPLETE; [05] REMOVED INTERCOSTAL AT STA 747-767 IAW SRM 51-40-02-0G-0; [06] VERIFIED STEP 5 IS COMPLETE; [07] VERIFIED ITEMS 3;4;5 AND 6; [08] LOCATED AND DRILLED NEW PART IAW SRM 51-40-05-0G-0 AND BOEING DWG 146A7500 REV A; [09] VERIFIED STEP 8 IS COMPLETE; [10] VERIFIED DRILL & LOCATE PER DWG 146A7500 REV A; [11] OK TO INSTALL INTERCOSTAL; [12] INSTALLED NEW INTERCOSTAL IAW SRM 51-40-02-0G-0 AND BOEING DWG 146A7500 REV A; [13] VERIFIED STEP 12 IS COMPLETE; [14] INSPECTION CW STEPS12-13; [15] REMOVED AND REPLACE ATTACH ANGLE TO R/H INTERCOSTAL AT STATION 767 IAW BOEING DWG 146A8123 AND B737 SRM 51-40-02; [16] EIE STEP 15 WAS NOT ATTACH ANGLE TO INTERCOSTAL; [17] VERIFIED STEPS 15 AND 16 ARE COMPLETE; [18] OK; [19] SUMMARY AND AUDIT OK
DOT# A45-014; AFT CARGO PIT DOOR CUTOUT; INTERCOSTAL LOWER ATTACH STRAP HAS CORROSION; WL: 156; RBL: 19; STA: 787+12. ; / [01] REMOVED STRAP FROM STATION 787+12 TO REMOVE CORROSION IAW B737 SRM 51-40-02; [02] REMOVED CORROSION ON STRAP AT STATION 787+12 ORIGINAL MATERIAL THICKNESS .040 VERIFIED BY UT 36649 DUE 8-4-21 MATERIAL REMOVED .009 MATERIAL REMAINING .031 STRAP WAS FOUND TO BE OUT OF LIMITS IAW B737 SRM 53-60-15-1A-1 TOOL 36649 DUE 8-4-21; [03] VERIFIED ITEMS 1 AND 2; [04] VERIFIED MEASUREMENT CHANGED FOR PRIMARY STRUCTURE AND CORROSION LEVEL; [05] PART VERIFIED AS P/N 146A8128-18 IAW BOEING DWG 146A8340 REV- ATAG A48323. LOCATED AND DRILLED IAW B737 SRM 51-40-05-0G-0; [06] INSPECTION COMPLETED CARD STEP 5.<BR>OK TO INSTALL STRAP.; [07] INSTALLED NEW STRAP IAW B737 SRM 51-40-02-0G-0 AND DWG 146A8340 REV-; [08] REMOVED AND REPLACED INTERCOSTAL LOWER ATTACH STRAP IN AFT CARGO COMPARTMENT BS 787+12' IAW B737 SRM 51-40-02-0G-0 AND DWG 146A8340 REV-; [09] INSPECTED INSTALLATION; [10] AUDIT. CW
R1 DOOR SURROUND;FWD TOP CORNER INSIDE THE FRAME BEHIND THE T/T LATCH RECEIVER EVIDENCE OF A CRACK AT FASTNER (MARKED) ; / TASK COMPLETE; FINAL AUDIT C/W; FINAL AUDIT C/W
DOT 18_A22: LEFT HORIZONTAL STAB RIB STA 120.30; LOWER FLANGE CRACKED JUST FWD OF #4 STIFFENER ; / REMOVED AND REINSTALLED LEFT HORIZONTAL STAB RIB STA 120.30 IAW SRM 51-40-02-0G-0; DWG 002A0001. REPAIRED IAW EA 21-155-01399; VERIFIED STEP 30 RII; AUDIT COMPLETE
VERTICAL STAB PANEL 324AL LOWER BRACKET IS CRACKED DOT A-21-13 ; / INSTALLED NEW RETAINER ON PANEL 324AL IAW B737 SRM 51-40-02-0G-0; DWG 172A6123 REV A; REMOVED AND REPLACED RETAINER ON PANEL 324AL IAW SRM 51-40-02-0G-0; DWG 172A6123 REV A; COMPLETED INSPECTION CARD STEPS 5 AND 6. JOB COMPLETE.<BR>AUDIT C/W
DOT# 31 A-186 FWD PIT SILL WEB CORRODED STA 440-480 RBL 28 WL156 ; / AUDIT CW; VERIFIED STEP C/W; VERIFIED ITEM #5<BR>AUDIT CW
DOT#30 A-186 FWD PIT FLOOR CORRODED STA 420+16 LBL18 WL 156 ; / UPDATED MEASUREMENTS; VERIFIED MEASUREMENTS; ALL WORK C/W <BR>AUDIT C/W
DOT#26 A-186 FWD PIT FWD SHILD CORRODED STA 420-440 RBL24 WL156 ; / VERIFIED STEPS 2; 3; 10; 11 AND 21 COMPLETE; REMOVED CORROSION LOSS OF .010 IS OUT OF LIMITS DUE TO NO DOCUMENTED LIMITS REMOVED AND REPLACED SHIELD IAW SRM 51-40-02 AND DWG 143A0080; VERIFIED ITEM 23.<BR>AUDITED
DOT#25 A-186 FWD PIT FLOOR RAIL CORRODED STA 40[+2 LBL 18 WL 156 ; / UPDATED MEASUREMENTS; VERIFIED MEASUREMENTS; ALL WORK C/W <BR>AUDIT C/W
DOT 23-A22; CABIN SEAT TRACK STA 463-466; LBL25; WL208; LIGHT CORROSION IN BASE OF SEAT TRACK ; / CORRECTIVE ACTION SHOULD READ: FAULT RAISED IN ERROR DUPLICATE WRITE UP TO TTG8Q004YCAQ; VERIFIED CORRECTIVE ACTION SHOULD READ: FAULT RAISED IN ERROR DUPLICATE WRITE UP TO TTG8Q004YCAQ; FAULT RAISED IN ERROR <BR>DUPLICATE WRITE UP TO TTG8Q004YCAQ
DOT 22-A22; CABIN SEAT TRACK STA 400-404; LBL22.5; WL208; LIGHT CORROSION IN BASE OF SEAT TRACK ; / UPDATED MEASUREMENTS; CERTIFIED STEP C/W; VERIFIED <BR>AUDIT C/W
DOT#32 A-186 FWD PIT FLOOR RAIL CORRODED STA 480+16 LBL 18 WL 156 ; / UPDATED MEASUREMENTS; VERIFIED MEASUREMENTS; ALL WORK C/W<BR>AUDIT C/W
DOT#48 A-186 FWD PIT PNL 120CF DAMAGE AT FASTENER HOLES ; / FOUND FWD CARGO PANEL 120 CF TO BE OUT OF LIMTS IAW SRM 53-00-53-1A-1 STEP 5 B 1; VERIFIED ITEM 1
DOT# 27 A-186 FWD PIT FLOOR RAIL CORRODED STA 400+ 18 RBL 14 WL156 ; / UPDATED MEASUREMENTS; VERIFIED MEASUREMENTS; ALL WORK C/W <BR>AUDIT C/W
DOT 21-A-22; RIGHT HORIZONTAL STAB RIB STA 129.50; RIB STIFFENER #3 CRACKED 1' ABOVE LOWER FLANGE ; / C.I.CED AREA I.A.W MM51-21-91-620-802; REMOVED RIB TO REPAIR CRICKET # 3 STIFFENER AT R /H HORZ STAB STA129.5 I.A.W ARM 51-40-02-0G-0<BR>REMOVED DAMAGED AREA FROM #3 STIFFENER I.A.W SRM55-10-09-2R-4.<BR>FABRICATED REPAIR PARTS I.A.W SRM55-10-09-2R-4.<BR>INSTALLED REPAIR PARTS I.A.W SRM55-10-09-2R-4.<BR>REINSTALLED RIB I.A.W SRM51-40-02-0G-0 AND BOEING DWG 182A1500 SHT11 REV :A; CIC AND SUMMARY OK AUDIT OK
DOT 20-A-22; RIGHT HORIZONTAL STAB RIB STA 92.70; RIB STIFFENER #2 CRACKED 1' ABOVE LOWER FLANGE ; / C.I.CED RIBI.A.W MM51-21-91-620-802; REINED RIB AT R/H HORZ STAB STA92.70 TO REPAIR #2 RIB STIFFENER I.A.W SRM51-40-02-0G-0.<BR>REMOVED DAMGE AT #2 RIB STIFFENER I.A.W SRM 55-10-09-2R-4<BR>FABRICTED REPAIR PARTS I.A.W SRM55-10-09-2R-4.<BR>INSTALLED REPAIR PARTS I.A.W SRM55-10-09-2R-4.<BR>REINSTALLED RIB I.A.W SRM51-40-02-0G-0 AND BOEING DWG 002A0001 REV:C; CIC AND SUMMARY OK AUDIT OK
DOT 19_A22: LEFT HORIZONTAL STAB; RIB STA 120.30; RIB STIFFENER #3 CRACKED 1' ABOVE LOWER FLANGE. ; / REMOVED DAMAGE FROM L/H HORIZ STAB RIB STA 120.3; RIB STIFFENER #3 CRACKED 1' ABOVE LOWER FLANGE IAW B737 SRM 55-10-09-2R-4. REPAIRED PER 55-10-09-2R-4 CIC APPLIED AFTER COMPLETION OF EA 21-155-01399-WIP1 REV P1 AND FINAL (TTG8Q0054PWX & TTG8Q005858J); VERIFIED STEP 18 C/W; FINAL AUDIT C/W
DOT0 21-A061 SEAT TRACK BASE HAS CORROSION FROM STA 727E+18' TO STA 747+1' RBL 45 WL ; / UPDATE MEASUREMENTS; I.A.W SRM 53-00-52-1A-1<BR>UPDATED STEP 7; VERIFIED STEPS 7; 8; AND 9<BR>AUDIT C/W
CABIN FLOOR PANEL 241FF HAS EDGE DAMAGE. DOT A-21-11 ; / REPAIRED EDGE DAMAGE ON FLOOR PANEL 241FF WITH POTTING COMPOUND I/A/W SRM 53-00-50-2R-10 STEP 3A-G (REV 73); VERIFIED STEPS 1-4; AUDIT CW
DOT 020-A061 SEAT TRACK BASE HAS CORROSION FROM STA 727C+16' TO STA 727D+10 RBL 45 WL 208 ; / UPDATE MEASUREMENTS; VERIFIED STEP 7 AND 8 COMPLETE AND AUDIT COMPLETE; OK
DOT 009_A061 CABIN FLOOR BOARD 241AF UPPER SURFACE HAS PULLED FIBERS ; / REPAIRED DAMAGE TO UPPER SURFACE OF PANEL 241AF. IAW B 737-700SRM 53-00-50-2R-1;SRM 53-00-50-2R-0; OK; STEP 4 & 5 OK. AUDIT COMPLETE
DOT 008-A061 CABIN FLOOR BOARD 242DF UPPER SURFACE PULLED FIBERS ; / REPAIRED CABIN FLOOR BOARD 242DF UPPER SURFACE PULLED FIBERS IAW SRM 53-00-50-2R-1 AND 53-00-50-2R-0 REPAIR GENERAL.; OK; VERIFIED STEP 3 AND 4 COMPLETE AND AUDIT COMPLETE
DOT002-A061 CABIN FLOOR BOARD 242AF AFT INBD CORNER DAMAGED ; / INSTALLED INSERTS IAW BOEING DRAWING 144A5810-189 REV. A AND BAC5085 STEP 8.4.2.2 CURED 1 HOUR AT 150 DEGREES. TOOLING--AAR 30347 DUE 4-29-22; REPAIRED DAMAGE TO AFT EDGE OF FLOORBOARD 242AF IAW SRM 53-00-50-2R-10 REV. 73; SRM 53-00-50-2R-0 REPAIR GENERAL REV. 73; BOEING DRAWING 144A5810 AND BAC5085; STEPS 3 AND 4 OK AUDIT COMPLETE
DOT 006-A061 CABIN FLOOR BOARD 242AF UPPER SURFACE PULLED FIBERS ; / BONDED REPAIR PLIES; CURED 3 HOURS AT 150 DEGREES IAW SRM 53-00-50-2R-1 REV. 73 STEPS 3J;K;L;M AND SRM 53-00-50-2R-0 REPAIR GENERAL REV. 73. TOOLING--OVEN B0-06 DUE 5-26-21. TAP TEST GOOD.; REPAIRED DAMAGE TO UPPER SURFACE ON FLOORBOARD 242AF IAW SRM 53-00-50-2R-1 REV. 73 AND SRM 53-00-50-2R-0 REPAIR GENERAL REV. 73 TAP TEST GOOD.; STEPS 4 AND 5 COMPLETE AUDIT OK
DOT 003 A061 CABIN FLOOR BOARD 241EF HAS DAMAGE TO THE LEADING EDGE ; / BONDED REPAIR ON LEADING EDGE AREA ON FLOORBOARD PANEL 241EF I/A/W SRM 53-00-50-2R-1 STEP 3A-N (REV 73); REPAIRED LEADING EDGE DAMAGE ON FLOORBOARD 241EF I/A/W SRM 53-00-50-2R-1 STEP 3A-N (REV 73); VERIFIED REPAIR. TAP TEST GOOD<BR>AUDIT C/W
DOT 001-A061 CABIN FLOOR BOARD 232SF AFT INBD CORNER DAMAGED ; / EVALUATED AND FOUND DAMAGE TO CORE AT AFT I/B CORNER AS MARKED. FOUND TO BE REPAIRABLE IAW SRM 53-00-50-2R-10 REV 73.<BR><BR>CLEANED AND PREPPED IAW SRM 53-00-50-2R-10 STEP 3 A-D. <BR><BR>APPLIED POTTING COMPOUND IAW SRM 53-00-50-2R-10 STEP 3 E-G. CURED FOR 5 HOURS AT 120 DEGREES (OVEN B0-06 EXP 5-26-21); REPAIRED CABIN FLOOR BOARD 232SF AT AFT I/B CORNER IAW SRM 53-00-50-2R-10 AND SRM 53-00-50-2R-0 REPAIR GENERAL.; STEP 1 AND 2 OK AND AUDIT COMPLETE
DOT 005-A061 CABIN FLOOR BOARD 232SF UPPER SURFACE PULLED FIBERS ; / REPAIRED CABIN FLOOR BOARD 232SF UPPER SURFACE IAW B737 SRM 53-00-50-2R-1; OK; STEP 4 & 5 OK AUDIT COMPLETE
SKIN DAMAGE AT STA 1008 1.5' ABOVE STR 15L ; / N/A MEASUREMENT TABLE DUE TO NO DENT IN AREA; VERIFIED DENT TABLE MEASUREMENTS ARE N/A'D DUE TO DENT BEING PREVIOUSLY REPAIRED; VERIFIED AND AUDITED.
CABIN FLOOR PANEL 241CF EDGE HAS DAMAGE. DOT A-21-09 ; / VERIFIED STEPS 1;2;3 TAP TESTED GOOD; REPAIRED EDGE DAMAGE ON CABIN FLOOR PANEL 241CF I/A/W SRM 53-00-50-2R-10 TAP TEST GOOD; VERIFIED ITEM 5. TAP TEST GOOD<BR>AUDIT C/W
CABIN FLOOR PANEL 231ZF EDGE HAS DAMAGE. DOT A-21-08 ; / RII STEPS; BONDED REPAIR AT EDGE DAMAGE ON FLOORBOARD PANEL 231ZF I/A/W SRM 53-00-50-2R-1 3A-N &REV 73); RII C/W FINAL INSPECTION; AUDIT C/W
CABIN FLOOR PANEL 241CF HAS PEELED FIBERS. DOT A-21-10 ; / REPAIRED PEELED FIBERS ON CABIN FLOOR PANEL 241CF I/A/W SRM 53-00-50-50-2R-1 (3) A-M (REV73) TAP TEST GOOD; VERIFIED ITEMS 1;2;3;4; AND 7<BR>AUDIT C/W; CLOSING INDEPENDENT INSPECTION THAT WAS SELECTED IN ERROR
CABIN FLOOR PANEL 231WF EDGE HAS DAMAGE. DOT A-21-07 ; / APPLIED POTTING COMPOUND TO INBOARD FWD AND AFT CORNERS CORE ONLY. CURED FOR 5 HOURS AT 125 DEGREES WITH HEAT LAMP I/A/W 53-00-50-2R-10 (3) A-G REV73; REPAIRED INBOARD FWD AND AFT EDGE DAMAGE ON CABIN FLOOR PANEL 231WF I/A/W SRM 53-00-50-2R-10 REV 73; VERIFIED STEPS 1-4<BR>AUDIT COMPLETE
AFT CARGO; FWD BULKHEAD PNL 141LW CRACKED; DOT A-193-11 / VERIFIED PART AS 453A2510-20; SI#7254212; ITEM# 45; IAW AIPC 25-52-19-01A. PANEL TO BE INSTALLED ON W/O 42133-1000-0233.; A TAG # FOR PART IS WN1222; ALL WORK C/W<BR>AUDIT C/W
AFT PIT PANEL 140CF HAS CORROSION AROUND FASTENER HOLES LEFT AND RIGHT SIDES A172-0003 ; / VERIFIED STARTING FABRICATION OF PANEL; STARTED FABING FLOOR PANEL. 140CF IAW AMM 25-52-01-201-801; EVALUATED CORROSION ON AFT CARGO FLOOR PANEL 140CF FLOOR PANEL WAS FOUND TO BE OUT OF LIMITS EXCEEDED 20'' IAW SRM 53-00-53-1A
EMERGENCY LIGHTS IN FWD GALLEY INOPERATIVE. REMOVED AND REPLACED BATTERY PACK IN FWD GALLEY OVERHEAD LT SIDE IAW AMM 33-51-06.
F/OS FLTDECK SEAT AFT INBD SEAT TRACK WORN TO CHECK LIMITS / REMOVED AND REPLACED FLTDECK SEAT TRACK PER AMM 25-11-11
CAPTS FLTDECK SEAT AFT INBD SEAT TRACK WORN TO CHECK LIMITS / REMOVED AND REPLACED FLTDECK SEAT TRACK PER AMM 25-11-11
PASSENGER CABIN FWD GALLEY TO ROW 2DEF PHOTO ILLUMINES STRIPS WORN AND HAVE MOISTURE UNDER COVER BOTH SIDES / R&R PHOTO ILLUMINES STRIPS PER AMM 25-27-31
193B PANEL HAS SEVERAL DAMAGE ON OUTER SURFACE- SKIN (DENTS;CRACKS & HOLES) / REPLACED 193B PANEL PER AMM 53-51-21
R/H OVERWING EMERGENCY EXIT SIGN LENS FELL OFF. / INSTALLED COVER PER AMM.
R/H OVERWING EXIT EXTERIOR EMERGENCY LIGHT INOP. / RELAMPED LIGHT PER AMM.
EXIT SIGN AT EXIT ROW OVER FIRST OFFICER'S WING FELL OFF. SECURED RIGHT EMERGENCY OVERWING EXIT SIGN PER SIP.
R1 EXTERIOR EMERGENCY ESCAPE LIGHT AND L1 OVERHEAD EXIT LIGHTS ARE INOP. R&R BATTERY PACK PER AMM.
L2 DOOR SLIDE FOLD CATCHES ON THE DOOR SILL, (OUT OF ADJUST). / ADJUSTED SLIDE PER AMM.
EMERGENCY EXIT LIGHTS ATTACHED TO EMERGENCY EXIT LIGHT BATTERY PACK M1674 INOP. / R&R BATTERY PACK IAW AMM.
R2 DOOR AFT WALL EMERGENCY EXIT SIGN INDICATOR FAULTY. / R&R SIGN PER AMM.
***CORROSION*** FWD. CARGO BAY R/H FLOOR SHIELD AT BS 480- BS 500 HAS AREAS OF CORROSION; WL156; RBL23 / REMOVED AND REPLACED FWD CARGO BAY R/H FLOOR SHIELD AT BS 480-BS500A ITEM 7531855 PO #744712. LOCATED AND DRILLED IAW SRM 51-40-05; DWG 143A0080 AND SRM 51-40-02 80641U 28MAY19
FWD CARGOBAY BAFFLE AT BS 500B- BS 500C; RBL23 IS CRACKED ON / REMOVED AND REPLACED BAFFLE AND CLIP AT BS 500B- BS500C RBL 23 IAW SRM 51-40-02-0G-0.
LH WING WIGGLE PLATE FOR 561BB I/B CORNER IS BROKEN / REMOVED; FABRICATE; AND INSTALLED SERVICEABLE WIGGLE PLATE ON LW LWR SKIN AT T/E; I/B END OF PANEL 561BB PER BOEING DWG 115A3750; AMM 51-21-41-370-802; STEP 3E; AMM 51-21-72-370-804 STEP 5.E; AMM 51-21-99-300-801; STEP 2.E.(6); AND SRM 51-40-02-0G-0; STEP 4; MATERIAL IS BAC1491-7; LOT #1394289-1. BONDED RUB STRIP PER SOPM 20-50-12; STEP 4.BB.
THIS IS A RE-WRITE OF NR# C636655 DUE TO INCORRECT STRINGER LOCATION. ON WALKAROUND FOUND DENT @ STA 659 1' BELOW STRINGER 8R MEASURES .04 DEEP X 1.5 WIDE A/Y RATIO OF 37.5 WHICH IS WITHIN LIMITS PER SRM 53-00-01-1A-1. NO REINSPECT REQUIRED. (REFERENCE SI 14238) / REPAIRED DENT DAMAGE AT B.S 659 1' BELOW STR 8R IAW EA. NO. 1-753-34972 REV IR DATED 01JUN2019 AND ATS ER NO. 19-03337 REV IR DATEDED 01-JUN2019
FLOOR BEAM UPPER CHORD CORRODED AT BS. 270, BETWEEN LBL 11 TO RBL 11. / REPAIRED FLOOR BEAM PER EA.
AFT CARGO BAY FWD CORNER THRESHOLD IS CRACKED / REPAIRED AFT CARGO BAY FWD CORNER THRESHOLD PER EA 1-A53-2076
COCKPIT FLOOR SUPPORT STRUCTURE CORRODED BETWEEN BS. 260 TO BS. 270, BETWEEN RBL 3 TO LBL 3. / R&R SUPPORT CHANNEL IAW SRM & DWG.
***CORROSION*** AFT CARGO BAY FLOOR CAP COVER BS 794 RBL 22 WL 155 / INSTALLED NEW CAP STRIP AT AFT CARGO BAY FLOOR PANEL BS 794 RBL 22 WL 155 IAW AMM 25-52-10-400-801 STEP 3E (11)(12) 92929U 05/24/2019
L/W T/E ORSS 271 BULB SEAL RETAINER IS CRACKED. / REMOVED & REPLACED L/W T/E ORSS 271 BULB SEAL RETAINER IAW SRM 51-40-02-0G-0. 55941U 05/23/2019 & IAW AIPC 57-50-00-25.
R/W T/E ORSS 271 BULB SEAL RETAINER IS CRACKED.. / REMOVED & REPLACED R/W T/E BULB SEAL RETAINER @ ORSS 271 IAW SRM 51-40-02-0G-0; SRM 51-40-05-0G-0 & AIPC 57-50-00-25.
***CORROSION*** FWD CARGO BAY R/H FLOOR TO SIDE WALL SUPPORT HAS AREAS OF CORROSION STA 500A TO 500B / UPON INVESTIGATION FOUND FLOOR TO SIDEWALL SUPPORT TO BE OUT OF LIMITS BS 500A-500B 1'X0.75'X0.005 FROM ORIGINAL THICKNESS OF 0.040 PER SRM 53-00-53-1A-2. REPLACED FCB R/H FLOOR TO SIDEWALL SUPPORT BS 500A-500D IAW SRM 51-40-02-0G-0 92929U 05/29/2019 REFERENCING BOEING DRAWING 143A7500 SH 58
***CORROSION*** FWD CARGO BAY L/H FLOOR TO SIDE WALL SUPPORT HAS AREAS OF CORROSION STA 400 TO STA 500D / BLENDED MULTIPLES AREAS AROUND FLOOR TO SIDEWALL SUPPORT STA 400-500D 1' X 1' X .005' ORIGINAL THICKNESS .040' IAW SRM 53-00-53-1A-2 BLEND FOUND TO BE OUT OF LIMITS. FABRICATED FCB L/H FLOOR TO SIDEWALL SUPPORT BS400-500D. MATERIAL BAC1496-444 #7075T62 AND SPLICE SIDEPLATE MATERIAL BAC 1496- 444 #7075-T62 LOT 1391220-2 IAW SRM 53-00-53-2R-6. LOCATED AND DRILLED IDW SRM 51-40-05 AND SRM 53-00-53-2R-6. APPLIED CHEMICAL CONVERSION COATING AND PRIMER IAW AMM 51-21-44 AND SRM 21-20-01. INSTALLED FCB L/H FLOOR TO SIDEWALL SUPPPORT BS 400-500D IAW DWG 143A7500 AND SRM 51-40-02; SRM 51-40-10.
RIGHT WING TRAILING EDGE PANEL 651GB AFT SEAL RETAINER O/B SIDE IS CRACK. / REMOVED OLD DAMAGED SEAL RETAINER FROM RT WING TRAILING EDGE PANEL #651GB AND INSTALLED NEW REPLACEMENT SEAL RETAINER IAW SRM 51-40-02-0G-0
SEAT TRACK CORRODED BETWEEN BS. 480 TO BS. 520, LBL 45. R&R SEAT TRACK IAW DWG & SRM.
SKIN DAMAGED AT BS. 1010, 1" BELOW STR. 14L. / REPAIRED SKIN DAMAGE IAW EA & ER.
AFT CARGO DOOR AFT CORNER SCUFF PLATE CRACKED IN UPPER SURFACE APPROX. 1" AND LOWER SURFACE APPROX. 1.5". REPAIRED SCUFF PLATE PER EA.
R1 DOOR CRACKED INDICATION ON THE LOWER BEAM (#4). REPAIRED BEAM #4 ON RO & AMM.
FORWARD CARGO DOOR AFT CORNER SCUFF PLATE CRACKED. REPAIRED SCUFF PLATE IAW EA.
SEAT TRACK CORRODED BETWEEN BS. 540 TO BS. 727B, RBL 45. R&R SEAT TRACK IAW SRM AND DWG.
AFT CARGO BAY CENTER THRESHOLD IS CRACKED AT PREVIOUS WELDS / REMOVED DAMAGED CARGO BAY THRESHOLD IAW AMM 53-11-02-020-801 STEPS 2.F. 03MAY19 59168U INSTALLED NEW ACB CENTER THRESHOLD IAW AMM 53-11-02-420-801. PART REPAIRED PER EA NO: 1-A53-2076. 56085U 27MAY19
RT OVERWING EMERGENCY EXIT FORWARD LIGHT BULB BURNED OUT. RELAMPED BULB IAW AMM.
LT OVERWING EMERGENCY EXIT LIGHT BULB BURNED OUT. RELAMPED BULB PER AMM.
R1 DOOR AFT GIRT BAR RETAINING FASTENER BROKEN. R&R CLIP IAW DWG.
RT AFT EMERGENCY LIGHTING FAILED CAPACITY CHECK AT LOCATION M1672. R&R POWER SUPPLY PER AMM.
LT AFT EMERGENCY LIGHTING FAILED CAPACITY CHECK AT LOCATION M1673. R&R POWER SUPPLY PER AMM.
FWD CARGO FWD CORNER THRESHOLD IS CRACKED / REMOVED AND REPLACED PER AMM.53-11-02
L1 DOOR GIRT BAR OUT OF POSITION. R&R SLIDE PER MT.
R1 DOOR GIRT BAR STOPPER ON THE RIGHT SIDE BROKEN. R&R GIRT BAR IAW AMM.
LT EMERGENCY EXIT HANDLE COVER LOOSE. SECURED HANDLE PER AMM.
RT OVERWING EXIT SAFETY LANYARD OUT OF POSITION. REPOSITIONED LANYARD PER AMM.
LT EMERGENCY LIGHTS EXTERIOR IN THE CABIN INOP AT BS 727C. R&R BATTERY PACK PER AMM.
LT EMERGENCY LIGHTS IN THE CABIN INOP AT BS 727C. R&R BATTERY PACK PER AMM.
SUPPLEMENTAL INFORMATION: RUDDER COUNTER BALANCE WEIGHT HAS EXCESSIVE CORROSION ON UPR. AND LWR. SURFACES. / REMOVED AND REPLACED RUDDER BALANCE ARM WEIGHT PER SRM 51-60-07
VERTICAL STAB LEFT LOWER ATTACH FITTING LUG CORRODED. REPAIRED THE ATTACH FITTING IAW EA.
VERTICAL STAB RT LOWER ATTACH FITTING LUG CORRODED. REPAIRED THE ATTACH FITTING IAW EA.
RIGHT AFT VERTICAL STAB ATTACH FITTING HAS PITTING CORROSION. REPAIRED THE FITTING IAW EA.
LEFT AFT VERTICAL STAB ATTACH FITTING HAS PITTING CORROSION. REPAIRED THE ATTACH FITTING IAW EA.
LEFT FWD VERTICAL STAB ATTCH FITTING HAS PITTING CORROSION. REPAIRED THE ATTACH FITTING IAW EA.
LEFT FWD VERTICAL STAB DRAG BRACE FITTING CORRODED AT OUTBD LUG. R & R THE DRAG BRACE FITTING IAW EA.
LEFT AFT VERTICAL STAB DRAG BRACE FITTING CORRODED AT INBD LUG. R & R THE DRAG BRACE FITTING IAW EA.
RIGHT FWD VERTICAL STAB DRAG BRACE FITTING CORRODED AT MAIN LUG. R & R THE DRAG BRACE FITTING IAW EA.
RIGHT AFT VERTICAL STAB DRAG BRACE FITTING CORRODED AT MAIN LUG. R & R THE DRAG BRACE FITTING IAW EA.
LEFT AFT VERTICAL STAB DRAG BRACE FITTING CORRODED AT OUTBD LUG. R & R THE DRAG BRACE FITTING IAW EA.
RIGHT FWD VERTICAL STAB ATTCH FITTING LUG HAS PITTING CORROSION. REPAIRED THE LUG IAW EA.
LEFT FWD VERTICAL STAB DRAG BRACE FITTING CORRODED AT INBD LUG. R & R THE DRAG BRACE FITTING IAW EA.
VERTICAL STAB; RH FWD ATTACH BOLT HOLE HAS ERROSION MEASURED AT 1.0' BEFORE DAMAGE REMOVAL. / REPAIRED PER EA 1-755-4082.
VERTICAL STAB. LH FWD ATTACH BOLT HOLE HAS EROSION. MEASURED AT 1.O' BEFORE DAMAGE REMOVAL / REPAIRED PER EA 1-755-4082
TRANSFERRED FROM LOG PAGE 0671970 - AFT FLIGHT ATTENDANT REPORTS KNOCKING SOUND COMING FROM REAR CABIN OF PLANE (A THUMP THUMP SOUND) / FOUND BROKEN FLOOR STRAP P/N 147A5410-3 AT BS 867 - 947 LBL 24. R&R STRAP PER SRM 51-40-02 & 51-10-02. SEE ATTACHEDK SAM 326 FOR OPEN/CLOSE FOR ACCESS.
L1 DOOR SLIDE GIRT BAR LOOSE. SECURED THE GIRT BAR IAW AMM.
MID CABIN OVERWING EMERGENCY EXIT SIGN LOOSE. R&R LIGHT ASSEMBLY PER AMM.
L1 DOOR LOWER EXIT LIGHT COVER MISSING. INSTALLED LENS PER MM.
MAIN WHEEL WELL TEE FITTING WORN AT BS 663.75, LBL 28. R & R THE TEE FITTING IAW SRM AND DWG.
LT HORIZONTAL STABILIZER ACCESS PANEL 331B LEADING EDGE RIB CRACKED RIB AT STA 105.26. R&R RIB IAW SRM AND DWG.
FORWARD CARGO COMPARTMENT WEB INTERCOSTAL CRACKED BETWEEN BS 500D TO BS 520, STR 28R. R&R INTERCOSTAL IAW SRM AND DWG.
BULKHEAD WEB CRACKED AT BS 663.75, RBL 35. REPAIRED THE BULKHEAD WEB IAW SRM.
AFT CARGO COMPARTMENT TRACK CRACKED AT BS 747, RBL 13.80. REPAIRED CARGO TRACK IAW SRM.
AFT CARGO COMPARTMENT SUPPORT ZEE CORRODED BETWEEN BS 727D TO BS 787, LBL 21.0. REPAIRED SUPPORT ZEE IAW SRM.
WEB INTERCOSTAL CRACKED BETWEEN BS 500 TO BS 500A, STR 26L. R&R INTERCOSTAL IAW SRM AND DWG.
FLOOR STRUCTURE WEB INTERCOSTAL CRACKED BETWEEN BS 312 TO BS 328, LBL 46. R&R WEB INTERCOSTAL IAW SRM AND DWG.
BULKHEAD FRAME CRACKED AT BS 540, STRINGER 22L. REPAIRED THE FRAME IAW EA.
FLOOR STIFFENER CRACKED AT BS 540, LBL 1.5. R & R THE STIFFENER IAW SRM & DWG.
L1 DOOR SLIDE LOOSE. SECURED THE SLIDE IAW MT.
RIGHT WING NR 6 FLAP TRACK FAIRING CRACKED. REPAIRED THE FAIRING IAW SRM AND EA.
SUPPORT ANGLE CRACKED AT BS 695, RBL 1. R & R THE SUPPORT ANGLE IAW SRM AND DWG.
RIGHT OVERWING EMERGENCY EXIT SIGN MISSING. INSTALLED SIGN ASSEMBLY IAW AMM.
L1 DOOR EMERGENCY EVAC SLIDE GIRT BAR RETAINER CLIP LOOSE. R & R RETAINER ASSEMBLY IAW SRM.
FLIGHT ATTENDANT REPORTS "BURNING PLASTIC" SMELL FROM AFT GALLEY & STRONG "BURNING PLASTIC" SMELL FROM WHEEL CHAIR COMPARTMENT. R&R NR 1 COFFEEMAKER PER MM.
CEILING EMERGENCY EXIT SIGN FELL OFF. REINSTALLED SIGN IAW AMM.
OVERWING CEILING EXIT LIGHT SIGN LOOSE. SECURED SIGN IAW AMM.
R1 DOOR GIRT BAR LOOSE FROM SLIDE. SECURED GIRT BAR IAW SIP.
LEFT OVERWING EMER BATTERY PACK FAILED CAPACITY FUNCTIONAL CHECK. R & R BATTERY IAW AMM.
CENTER CABIN CEILING EMER EXIT SIGN LIGHT LOOSE. SECURED SIGN IAW AMM.
FORWARD GALLEY ENTRY EMER INOPERATIVE. R & R BATTERY PACK IAW MM.
LEFT HORIZONTAL STABILIZER STAB RIB CRACKED VERTICAL STIFFENER AT STATION 120.30 FWD STIFFENER. REPAIRED RIB IAW SRM.
SIDE SKIN PANEL CRACKED AT BS 1039, STRINGER 4R. REPAIRED SKIN IAW EA.
LEFT HORIZONTAL STABILIZER 4TH VERTICAL STIFFENER CRACKED AT STABILIZER STATION 129.50, LOWER RADIUS. REPAIRED STIFFENER IAW SRM.
AFT ACCESSORY STRINGER CLIP DAMAGED AT BS 1040, AT STRINGER 15L. REPAIRED CLIP IAW SRM.
AFT ACCESSORY SHEAR TIE DAMAGED AT BS 1040, BETWEEN STRINGER 15L TO 16L. REPAIRED SHEAR TIE IAW SRM.
LEFT HORIZONTAL STABILIZER, 3RD VERTICAL STIFFENER AT STABILIZER STATION 92.70, CRACKED AT LOWER RADIUS. REPAIRED STIFFENER IAW SRM.
AFT ACCESSORY SHEAR TIE DAMAGED AT BS 1040, BETWEEN STRINGER 16L TO 7L. REPAIRED SHEAR TIE IAW SRM.
LEFT HORIZONTAL STABILIZER 1ST VERTICAL STIFFENER CRACKED AT STABILIZER STATION 92.70, LOWER RADIUS. REPAIRED STIFFENER IAW SRM.
LEFT HORIZONTAL STABILIZER 2ND VERTICAL STIFFENER CRACKED AT STABILIZER STATION 92.70, LOWER RADIUS. REPAIRED STIFFENER IAW SRM.
AFT ACCESSORY SHEAR TIE DAMAGED AT BS 1040, BETWEEN STRINGER 14L TO 15L. REPAIRED SHEAR TIE IAW SRM.
AFT ACCESSORY STRINGER CLIP DAMAGED AT BS 1040 AT STRINGER 14L. REPAIRED CLIP IAW SRM.
SKIN CRACKED AT BS 1039, STRINGER 4R. REPAIRED SKIN IAW EA.
LEFT EMER EXIT HATCH ESCAPE STRAP CORRODED ON HOOK AT END OF ROPE. R & R STRAP ASSEMBLY IAW AMM.
RIGHT EMER EXIT HATCH ESCAPE STRAP CORRODED ON HOOK AT END OF ROPE. R & R STRAP ASSEMBLY IAW AMM.
LEFT HORIZONTAL STABILIZER LOWER SKIN ALONG RIB CRACKED AT STABILIZER STATION 129.50, 17" AFT OF FORWARD SPAR. REPAIRED RIB IAW SRM.
LEFT HORIZONTAL STABILIZER LOWER SKIN ALONG RIB CRACKED AT STABILIZER STATION 157.10, 30" AFT OF FORWARD SPAR. REPAIRED RIB IAW SRM.
FLIGHT ATTENDANTS NOTICED A BURNING PLASTIC SMELL IN FWD CABIN. WE TURNED OFF RECIRCULATION FAN & FLIGHT ATTENDANTS SAID SMELL STOPPED. R & R RECIRCULATION FAN IAW MM.
LEFT WW FWD BULKHEAD VERTICAL PRESS WEB CRACKED AT BS 663.75, LBL 33.83. REPAIRED WEB IAW EA.
R1 DOOR EMER EVAC SLIDE COVER CRACKED. REPAIRED COVER IAW MT.
LEFT CTR FLOOR SUPPORT CRACKED ABOVE AIR CONDITIONING DISTRIBUTION BAY AT STATION 540. R & R PANEL IAW SRM.
RIGHT CTR FLOOR SUPPORT CRACKED ABOVE AIR CONDITIONING DISTRIBUTION BAY AT STATION 540. R & R PANEL IAW SRM.
LEFT WING LOWER FIXED TE PANEL INBD OF NR 3 FLAP FAIRING WIGGLE PLATE CRACKED. R & R WIGGLE PLATE IAW SRM.
RIGHT WING FIXED UPPER TE PANEL AFT OF NR 2 PYLON CRACKED ANGLE ON OTBD SUPPORT BRACKET. R & R ANGLE IAW DWG & SRM.
FORWARD ENTRY EMER LIGHTS BATTERY PACK FAILED CAPACITY CHECK. R & R BATTERY PACK IAW AMM.
AFT ENTRY DOOR EMERGENCY EXIT LIGHT BROKEN. R&R LIGHT ASSEMBLY IAW MM.
AFT SERVICE DOOR EMERGENCY EXIT LIGHT BROKEN. R&R LIGHT ASSEMBLY IAW MM.
L ANGLE ATTACH BRACKET CRACKED AT STATION 665, RBL 50. R&R BRACKET IAW SRM.
FWD GALLEY FLOOR STRUCTURE INTERCOSTAL FRAME CRACKED BETWEEN STATION 294 TO STATION 312, RBL 15. R&R INTERCOSTAL IAW SRM.
LT EF CONTROL CABIN WINDOW POST CRACKED AT 2ND LOWER CORNER FASTENER HOLE. REPAIRED FRAME ASSEMBLY, IAW EA.
FWD GALLEY FLOOR STRUCTURE INTERCOSTAL FRAME CRACKED BETWEEN STATION 328 TO STATION 344, LBL 44. R&R INTERCOSTAL IAW SRM.
INTERCOSTAL CRACKED BETWEEN STATION 344 TO STATION 360, BL 0. R&R INTERCOSTAL IAW SRM.
INTERCOSTAL CRACKED BETWEEN STATION 344 TO STATION 360, LBL 11. R&R INTERCOSTAL IAW SRM.
INTERCOSTAL CRACKED BETWEEN STATION 344 TO STATION 360, RBL 12. R&R INTERCOSTAL IAW SRM.
INTERCOSTAL CRACKED BETWEEN STATION 344 TO STATION 360, RBL 33. R&R INTERCOSTAL IAW SRM.
INTERCOSTAL CRACKED BETWEEN STATION 294 TO STATION 312, BL 0. R&R INTERCOSTAL IAW SRM.
FWD GALLEY FLOOR STRUCTURE INTERCOSTAL FRAME CRACKED BETWEEN STATION 315 TO STATION 328, LBL 44. R&R INTERCOSTAL IAW SRM.
INTERCOSTAL CRACKED BETWEEN STATION 294 TO STATION 312, RBL 31. R&R INTERCOSTAL IAW SRM.
RT HORIZONTAL STABILIZER SKIN CRACKED AT STABILIZER STATION 98. REPAIRED SKIN IAW SRM.
RT HORIZONTAL STABILIZER LOWER SKIN CRACKED ALONG RIB STABILIZER STATION 101.9, 29" FWD OF AFT SPAR. REPAIRED SKIN IAW SRM.
RT HORIZONTAL STABILIZER LOWER SKIN CRACKED ALONG RIB STABILIZER STATION 101.9, 20" FWD OF AFT SPAR. REPAIRED SKIN IAW SRM.
LT HORIZONTAL STABILIZER LOWER SKIN CRACKED ALONG RIB STABILIZER STATION 147.9. REPAIRED SKIN IAW SRM
LAVATORY CONTROL MODULE INTERCOSTAL CRACKED. REPAIRED INTERCOSTAL IAW EA.
LAVATORY CONTROL MODULE INTERCOSTAL CRACKED. REPAIRED INTERCOSTAL IAW SWA EA.
AFT GALLEY EMERGENCY EXIT LIGHT LENS BROKEN. R&R LIGHT ASSEMBLY IAW MM.
RT OVERWING EMERGENCY EXIT LIGHT CRACKED. R&R LENS PER SIP.
LEFT CENTER EMERGENCY LIGHT BATTERY PACK FAILED LONG TEST. REMOVED AND REPLACED BATTERY PACK ASSY PER MM.
RIGHT CENTER EMERGENCY LIGHT BATTERY PACK FAILED LONG TEST. REMOVED AND REPLACED BATTERY PACK ASSY PER MM.
RIGHT AFT EMERGENCY LIGHT BATTERY PACK FAILED LONG TEST. REMOVED AND REPLACED BATTERY PACK ASSY PER MM.
LEFT LOWER HORIZONTAL STABILIZER IN SPAR SKIN CRACKED AT STA 138.70. REPAIRED SKIN PER SRM.
R2 DOOR EMERGENCY EVAC SLIDE GIRT BAR RETAINING CLIP BROKEN. REMOVED AND REPLACED GIRT BAR PER AMM.
FORWARD GALLEY SIDEWALL EMERGENCY EXIT LIGHT COVER FELL OFF. REMOVED AND REPLACED LIGHT ASSY PER MM.
R2 DOOR EMERGENCY EVAC SLIDE LOOSE. SECURED SLIDE PER MM.
INFLIGHT SHUT DOWN AND AIR TURNBACK WITH DECLARED EMERGENCY. ON DEPARTURE NR 1 ENGINE EXHAUST WAS DARKER. NR 1 EGT WAS APPROXIMATELY 50 DEG ABOVE NR 2 F FLOW WAS SLIGHTLY HIGHER. ABOVE 10,000FT NR 1 BLEED TRIP OFF CAME ON RAN CHECK LIST, WOULD NOT GO OUT. NR 1 ENGINE OVERHEAT CAME ON. REMOVED AND REPLACED NR 1 ENGINE BLEED AIR REGULATOR, BLEED AIR CHECK VALVE, NR 1 ENG LT CORE FIRE DETECT ASSY, NR 1 ENGINE PNEUMATIC HIGH STAGE PRESSURE REGULATOR, NR 1 ENGINE PNEUMATIC PRSOV, NR 1 ENG HIGH STAGE VALVE PER MM.
LT EEPLS LOOSE AT ROW 1. SECURED EELPS PER MM.
DURING SCHEDULED 6Y CHECK, FOUND CENTER WING BOX STIFFENER CRACKED AT BS 547.5, LBL 7. REMOVED AND REPLACED STIFFENER PER SRM.
DURING SCHEDULED 6Y CHECK, FOUND CENTER WING BOX STIFFENER CRACKED AT BS 547.5, LBL 15. REMOVED AND REPLACED STIFFENER PER SRM.
DURING SCHEDULED HC2 CHECK FOUND, LT HORIZONTAL STABILIZER LOWER SKIN CRACKED AT STA 101.9. REPAIRED SKIN PER SRM.
DURING SCHEDULED RON CHECK, FOUND LT EEPLS LENS CRACKED AT ROW 10. REMOVED AND REPLACED LENS PER MM.
DURING SCHEDULED MV2 CHECK, FOUND EEPLS INOP. REMOVED AND REPLACED EEPLS PER MM.
LT EEPLS COVER CRACKED AT ROW 1. REMOVED AND REPLACED COVER PER MM.
DURING SCHEDULED CV CHECK, FOUND EEPLS COVER MISSING AT ROW 11. INSTALLED COVER PER MM.
DURING SCHEDULED CV CHECK, FOUND EEPLS COVER CRACKED AT ROW 1. REMOVED AND REPLACED COVER PER MM.
L1 DOOR EMERGENCY EVAC SLIDE FELL OUT OF CONTAINER, DID NOT DEPLOY. RE-INSTALLED SLIDE PER MM.
R1 DOOR EMERGENCY EVAC SLIDE FELL OUT, DID NOT DEPLOY. RE-INSTALLED SLIDE PER MT.
DURING SCHEDULED HC2 CHECK, EMERGENCY EXIT LIGHT BATTERIES FAILED CAPACITY CHECK. REMOVED AND REPLACED BATTERY PACKS PER MM.
R1 DOOR EMERGENCY EXIT LIGHT LENS OUT OF POSITION. REMOVED AND REPLACED LENS PER MM.
FWD GALLEY EMERGENCY EXIT LIGHT COVER BROKEN. REMOVED AND REPLACED LAMP ASSY PER MM.
FOUND LT AFT FLASHLIGHT INOP. R&R BATTERY PER MM.
FOUND RT AFT FLASHLIGHT INOP. R&R BATTERY PER MM.
FOUND RT EEPLS STRIP MISSING LENS. REPLACED LENS PER MM.
FOUND LT EEPLS STRIP MISSING LENS. REPLACED LENS PER MM.
FOUND LT EEPLS LIGHT LENS MISSING. INSTALLED LENS PER MM.
FOUND RT EEPLS LIGHT LENS MISSING. INSTALLED LENS PER MM.
EEPLS LENS LOOSE AT ROW 1 ABC. SECURED LENS PER MM.
DURING SCHEDULED MV1 CHECK, FOUND L1 DOOR EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED LIGHT BULB PER MM.
R1 DOOR EMERGENCY EVAC SLIDE FWD GIRT BAR HOOK LOOSE. SECURED HOOK PER MM.
EEPLS INOP BETWEEN ROW 5 ABC AND ROW 7 ABC. FOUND LOOSE WIRE. SECURED WIRE PER MM.
EEPLS LENS LOOSE AT ROW 1 ABC. REMOVED AND REPLACED LENS PER MM.
EEPLS LENS LOOSE AT ROW 1 ABC. REMOVED AND REPLACED LENS PER MM.
EEPLS COVER LOOSE AT ROW 1 ABC. SECURED COVER PER MM.