N8685B
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 | 2025-06-18 – 2025-06-18 | Operator named in NTSB report |
| SOUTHWEST AIRLINES, CO. (SWAA) | Operator | 2025-06-18 – 2025-06-18 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
FWD RIGHT EMERGENCY LIGHTS INOPERATIVE. REMOVED AND REPLACED THE BATTERY BACK AND PERFORMED A GOOD OPS CHECK IAW AMM 33-51-06-960-805.
AFT GALLEY CEILING EXIT SIGN NEEDS TO BE SECURED. SECURED SCREWS IAW AMM 33-51-01-201-NG.
IN THE PASSENGER CABIN; THE EMERGENCY EXIT LIGHT FWD OF THE LEFT HAND FWD MID EXIT DOOR IS INOP. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY PACK M1694 PER AMM 33-51-06. ALL ASSOCIATED EMERGENCY LIGHTS OPS CHECK GOOD PER AMM 33-51-06.
IN THE CABIN ABOVE THE FWD ENTRY DOOR, THE EXIT LIGHT HAS ONE INOP BULB. REMOVED AND REPLACED LAMP OPS CHECK OK PER AMM 33-25-00.
IN THE PASSENGER CABIN; THE EMERGENCY EXIT LIGHT FWD OF THE RIGHT HAND FWD MID EXIT DOOR IS INOP. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY PACK M1694 PER AMM 33-51-06. ALL ASSOCIATED EMERGENCY LIGHTS OPS CHECK GOOD PER AMM 33-51-06.
LEFT HORIZONTAL UPPER FORWARD SLIDER SEAL IS CRACKED; TORN ON FORWARD TRACK. REMOVED LH HORIZONTAL UPPER FWD SLIDING SEAL PER AMM 53-31-31. REPLACED LH HORIZONTAL UPPER FWD SLIDING SEAL PER AMM 53-31-31.
ANGLE ASSY CRACKED I/B OF LH DEFECTION RIB (MPN 115A2156-17). REMOVED ANGLE PER SRM 51-40-02. LOCATED AND DRILLED NEW FASTENER HOLES IN NEW ANGLE PER SRM 51-40-05. INSTALLED REPLACEMENT ANGLE PER SRM 51-40-02. INSPECTED PER SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT).
ANGLE CRACKED I/B OF LH DEFECTION RIB (MPN 115A2156-7). REMOVED ANGLE PER SRM 51-40-02. LOCATED AND DRILLED FASTENER HOLES IN NEW ANGLE PER SRM 51-40-05. INSTALLED REPLACEMENT ANGLE PER SRM 51-40-02.
RH HORIZONTAL STABILIZER FWD UPPER SLIDING SEAL CRACKED.<[01] INFO: PARTS ORDERED 5/15/25. AMM REFERENCE IS 53-31-31.;[02] INSTALLED ATTACH FITTING ON SEAL PER SRM 51-40-02.;[03] VERIFIED INSTALLED ATTACH FITTING ON SEAL PER SRM 51-40-02.;[04] INSTALLED RH HORIZONTAL STABILIZER FWD UPPER SLIDING SEAL IAW AMM 53-31-31 OPS CK NORMAL.;[05] 02 - INSPECTED PER [AMM 53-31-31-400-802-NG (STABILIZER-TO-BODY UPPER FRONT SPAR SLIDING SEAL INSTALLATION - PERMANENT)];[06] 02 - INSPECTED PER [AMM 53-31-31-400-802-NG (STABILIZER-TO-BODY UPPER FRONT SPAR SLIDING SEAL INSTALLATION - PERMANENT)]
CAPT'S FWD I/B SEAT TRACK HAS POSSIBLE CORROSION AT FWD MOUNT BOLT AREA. REMOVED CAPT. FWD INBD. SEAT TRACK IN REFERENCE TO SRM 51-40-02.
CAPT'S FWD O/B SEAT TRACK HAS POSSIBLE CORROSION AT FWD MOUNT BOLT AREA. REMOVED CAPT. FWD. OTBD. SEAT TRACK IN REFERENCE TO SRM 51-40-02. REMOVED AND REPLACED PER [AMM 25-11-11-400-801-NG
F.O.'S FWD O/B SEAT TRACK HAS POSSIBLE CORROSION AT FWD MOUNT BOLT AREA. MRKD<[01] REMOVED FO'S FWD. OTBD. SEAT TRACK IN REFERENCE TO SRM 51-40-02;[02] 01 - REMOVED AND REPLACED PER [AMM 25-11-11-400-801-NG (FLIGHT COMPARTMENT SEAT TRACKS - INSTALLATION AND ALIGNMENT - PERMANENT)]
F.O.'S FWD I/B SEAT TRACK HAS POSSIBLE CORROSION AT FWD MOUNT BOLT AREA. MRKD<[01] REMOVED FO'S FWD. INBD. SEAT TRACK IN REFERENCE TO SRM 51-40-02;[02] 01 - REMOVED AND REPLACED PER [AMM 25-11-11-400-801-NG (FLIGHT COMPARTMENT SEAT TRACKS - INSTALLATION AND ALIGNMENT - PERMANENT)]
CRACKS FOUND AT BS 663 VAPOR BARRIER UPPER ATTACH ANGLE RBL 9 & 32.<[01] MATCH DRILLED BS 663 VAPOR BARRIER UPPER ATTACH ANGLE PER SRM 51-40-02 & DWG 111A1000. NEED OK TO INSTALL ANGLE.;[02] REMOVED 663 VAPOR BARRIER ANGLE PER SRM 51-40-02.;[03] C/W RII INSPECTION OF CA #1;[04] INSTALLED FASTENERS COMMON TO FUEL TANK PER SRM 51-40-02 & DWG 111A1000.;[05] C/W INSPECTION OF C/A #4; INSTALLED FASTENERS COMMON TO FUEL TANK PER SRM 51-40-02 & DWG 111A1000.;[06] REPLACED R/H BS 663 VAPOR BARRIER UPPER ATTACH ANGLE PER SRM 51-40-02 & DWG # 111A1000.;[07] C/W RII INSPECTION OF C/A #6;[08] CHANGED RII MEASUREMENT FROM NO TO YES;[09] ALL RII INSPECTION COMPLETED
RIGHT WING OUTBOARD AFT FLAP HAS DELAM ON UPPER INBOARD AFT SURFACE.<[01] REMOVED R/H WING O/B AFT FLAP PER AMM 27-51-22.;[02] OK TO INSTALL RIGHT WING OTBD FLAP.;[03] INSTALLED SERVICEABLE R/H O/B AFT FLAP PER AMM 27-51-22.;[04] VERIFIED RII WORK ACCOMPLISHED IN CORRECTIVE ACTION #3
BRACKET CRACKED I/B OF RH DEFECTION RIB. REMOVED CRACKED SUPPORT ANGLE BRACKET PER SRM 51-40-02. THE CRACKED SUPPORT ANGLE BRACKET HAS BEEN VERIFIED AS BEING REMOVED AS STATED IN ITEM #1. LOCATED; DRILLED AND DEBURRED REPLACEMENT SUPPORT ANGLE BRACKET PER SRM 51-40-05. INSTALLED REPLACEMENT SUPPORT ANGLE BRACKET PER SRM 51-40-02.
CRACK FOUND AT L/H BS 663 VAPOR BARRIER UPPER ATTACH ANGLE AT LBL 9<[01] FABRICATED REPAIR PARTS PER SRM 57-10-10-2R-5. NEED OK TO INSTALL PARTS.;[02] REMOVED R/H A/C DISTRIBUTION DUCTING F.O.M.;[03] C/W RII INSPECTION OF C/A #1;[04] INSTALLED REPAIR PER SRM 57-10-10-2R-5;[05] VERIFIED FASTENERS INSIDE CENTER TANK PRIOR TO CAP SEALING PER SRM 57-10-10-2R-5.;[06] SEE TASK CARD TTG8Q010QRES FOR C/A # 2 SING OFF.;[07] LINE #4 & #5<BR>INSPECTED AS REQUIRED;[08] LINE #4 & #6<BR>INSPECTED AS REQUIRED;[09] TASK CARD COMPLETE SEE ADDITIONAL STEPS FOR WORK ACCOMPLISHED<BR>INSPECTED AS REQUIRED
FLIGHT ATTENDANTS REPORT PLASTIC BURNING FUMES AT ROWS 2-4. RAN SMOKE; FIRE OR FUMES QRH. FUMES EXTINGUISHED. RESTORED PWR TO ALL SWITCHES NO FUMES NOTED REMAINDER OF FLIGHT WAS NORMAL<[01] ACCOMPLISHED SMOKE/FUMES IN CABIN CONDITIONAL INSPECTION REF AMM 05-51-56; NO FUMES/ABNORMAL SMELL NOTED OK FOR CONT SERVICE
PASSENGER EMERGENCY EXIT SEAT 15C; 15B RECLINE NOT LOCKED OUT<[01] LOCKED OUT EMR EXIT SEATS 15C AND 15B RFE AMM 25-22-00
CABIN EMERGENCY LIGHTS L/H FWD CABIN STA 500C BATTERY PACK INOP<[01] REMOVED AND REPLACED BATTERY PACK PER AMM 33-51-06.;[02] INSPECTED WORK PERFORMED. REMOVED AND REPLACED BATTERY PACK PER AMM 33-51-06.;[03] OPS CHECKED GOOD PER AMM 33-51-06.;[04] REMOVED AND REPLACED BATTERY PACK PER AMM 33-51-06.;[05] INSPECTED WORK PERFORMED. REMOVED AND REPLACED BATTERY PACK PER AMM 33-51-06.
FWD CABIN R/H OVERWING EMERGENCY LIGHTS AT STA 565 BATTERY PACK IS INOP<[01] REMOVED AND REPLACED BATTERY PACK PER AMM 33-51-06.;[02] OPS CHECK GOOD PER AMM 33-51-06.;[03] REMOVED AND REPLACED BATTERY CHARGER ASSY PER AMM 33-51-06. <BR>OPS CHECK GOOD PER AMM 33-51-06.;[04] INSPECTED WORK PERFORMED. REMOVED AND REPLACED BATTERY CHARGER ASSY PER AMM 33-51-06.
R/H WING FUELING PANEL BRACKET FOR CENTER FUEL TANK HAS CORROSION.<[01] REPLACED P15 REFUELING PANEL PLATE PER SOPM 20-50-01 AND MM 28-41-61. P15 REFUELING PANEL OPS CHECKED GOOD PER MM 28-21-00-400-801;[02] VERIFIED INSTALLATION OF P15 REFUELING PANEL PLATE PER SOPM 20-50-01 AND MM 28-41-61. VERIFIED P15 REFUELING PANEL OPS CHECKED GOOD PER MM 28-21-00.
REPLACE LH AFT CARGO SIDE PLATE FORM STA 727H +11 TO 800 DUE TO CORROSION<LOCATED; DRILLED AND COUNTERSUNKED NEW LH SIDE PLATE FROM STA 727H + 11 TO 800 PER SRM 51-40-05 ; 51-40-08 AND 53-00-53-2R-6;[03] CW INSP STEP #2;- REMOVED AND REPLACED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)]<BR>REMOVED AND REPLACED L/H TRANSITION ANGLE FROM STA 727H +11 TO STA 800 PER SRM 51-40-02.PERFORMED NUT PLATES PUSH TEST GOOD.;[11] 01 - REMOVED AND REPLACED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)]<BR> REMOVED AND REPLACED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)]<BR>REMOVED AND REPLACED L/H TRANSITION ANGLE FROM STA 727H +11 TO STA 800 PER SRM 51-40-02.PERFORMED NUT PLATES PUSH TEST GOOD PER SRM 51-40-10.;[12] VERIFIED REPLACEMENT OF SIDE PLATE AND PUSH TEST GOOD.
PASSENGER CABIN FLOOR SUPPORT CRACKED AT ATTACH FASTENER STA. 540 RBL 1.<[01] REMOVED BROKEN CABLIN FLOOR SUPPORT BRAKE ASSY AT STA. 540 RBL1;[02] 01 - REMOVED AND REPLACED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)];[03] 01 - REMOVED AND REPLACED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)];[04] RII INSPECTED AS REQUIRED. CORRECTIVE ACTION #2 AND #3
PASSENGER CABIN FLOOR SUPPORT CRACKED AT ATTACH FASTENER STA.540 LBL 1.<[01] REMOVED BROKEN CABLIN FLOOR SUPPORT BRAKE ASSY AT STA. 540 LBL 1.;[02] 01 - REMOVED AND REPLACED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)];[03] 01 - REMOVED AND REPLACED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)];[04] RII INSPECTED AS REQUIRED. CORRECTIVE ACTION #2 AND #3
WALL SUPPORT STA. 986.5 + 4 HAS CORROSION ON UPPER SURFACE I/B END<[01] CORROSION AT Z-ANGLE(WALL SUPPORT) AT APPROXIMATELY STA. 987+5' ; LBL 33' IS OUT OF LIMITS PER SRM 53-70-51-1A-1. PARENT THICKNESS IS .050'. REMAINING THICKNESS IS .000'. REMOVED ANGLE PER SRM 51-40-02. LOCATED AND DRILLED REPLACEMENT ANGLE PER SRM 51-40-05. OK TO INSTALL NEW ANGLE PER SRM 51-40-02.;[02] OK TO INSTALL;[03] INSTALLED NEW Z-ANGLE(WALL SUPPORT) ON AFT WET FLOOR AT STA. 987+5' FROM LBL 33' TO LBL 44' PER SRM 51-40-02. EDGE SEALED NEW PART PER AMM 51-31-00.;[04] INSPECTED WORK ABOVE
AFT CARGO SIDE PLATE CHANNEL AT LBL 21; STA 727H-727I HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED)<[01] REMOVED SURFACE CORROSION ON L/H SIDE PLATE FROM STA 727I-727J LBL21 PER SRM 51-10-02; FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2 MATERIAL REMOVED 0.007 AND REMAINING MATERIAL THICKNESS .033.;[02] 01 - REMOVED AND REPLACED PER [SRM 51-10-02-0G-0-B00070 (GENERAL - INSPECTION AND REMOVAL OF DAMAGE - AIRFRAME - PERMANENT)]<BR>REMOVED AND REPLACED L/H TRANSITION ANGLE FROM STA 727H TO STA 800 WORK ACCOMPLISHED ON CARD # TTG8Q00SRNB5.;[03] VERIFIED WORK ACCOMPLISHED ON ACCOMPLISHED ON CARD # TTG8Q00SRNB5.
AFT CARGO SIDE PLATE CHANNEL AT RBL 21; STA 727D-727E HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED)<[01] REMOVED SURFACE CORROSION ON AFT CARGO SIDE PLATE CHANNEL AT RBL 21; STA 727D-727E PER SRM 51-10-02. REMAINING THICKNESS .035'. FOUND TO BE OUT OF LIMITS PER SRM 53-0053-1A-2. FOR COMPANY CONVENIENCE R/H TRANSITION ANGLE TO BE REPLACED ON NON-ROUTINE TTG8Q00SNQ8J FROM STA 727 + 4 TO STA 767;[02] INSPECTED WORK ABOVE
FWD CARGO DOOR LOWER SILL THRESHOLD WEB HAS CORROSION.<[01] REMOVED CORROSION MATERIAL LOSS .005 AND FOUND TO BE OUT OF LIMITS. REMAINING THICKNESS .040. PER SRM 53-00-53. REMOVED FORWARD CARGO THRESHOLD WEB FOR REPLACEMENT PER SRM 51-40-02.;[02] VERIFIED WEB MATERIAL OUT OF LIMITS.;[03] LOCATED AND DRILLED THE NEW REPLACEMENT WEB AND INSTALLED NUT PLATES PER SRM 51-40-02.;[04] OK TO CLOSE/INSTALL THRESHOLD WEB;[05] 01 - REMOVED AND REPLACED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)]<BR>REMOVED AND REPLACED FWD CARGO DOOR LOWER SILL THRESHOLD WEB PER SRM 51-10-02;AND SRM 51-40-02.;[06] RII: INSPECTED WORK PERFORMED. REMOVED AND REPLACED FWD CARGO DOOR LOWER SILL THRESHOLD WEB PER SRM 51-10-02;AND SRM 51-40-02.
STA 986.5 FLOOR BEAM UPPER FLANGE HAS CORROSION AROUND FLOOR PANEL ATTACH HOLE AT LBL 30.5.<[01] BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1. ORIGINAL THICKNESS=.150?; REMAINING THICKNESS=.125?.;[02] BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1. ORIGINAL THICKNESS=.150?; REMAINING THICKNESS=.125?;[03] TSR 2024002406 SUBMITTED;[04] REPAIRED PER SRM 53-70-51-2R-6;[05] 02 - INSPECTED PER [SRM 53-70-51-2R-6-B00676 (REPAIR 6 - SECTION 47 - SMALL CORROSION DAMAGE ON THE UPPER CHORD OF THE FLOOR BEAM AT STA 986.5 - PERMANENT)];[06] 02 - INSPECTED PER [SRM 53-70-51-2R-6-B00676 (REPAIR 6 - SECTION 47 - SMALL CORROSION DAMAGE ON THE UPPER CHORD OF THE FLOOR BEAM AT STA 986.5 - PERMANENT)]
STA 986.5 FLOOR BEAM UPPER FLANGE HAS CORROSION AROUND NUTPLATE HOLE AT LBL 43.<[01] BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1.;[02] BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1.;[03] REMOVED DAMAGE STA 986.5 FLOOR BEAM LBL 43 PER SRM 53-70-51-2R-6 ALTERNATIVE 4FLAP PEENED REPAIR AREA PER SRM 53-70-51-2R-6 PAR 4.E MATERIAL VERIFICATION FOR REPAIR PART [1] STRAP IS .100X7075T6 BN 308391; REPAIR PART [2] ANGLE BAC1490-2887 BN 1980746; REPAIR PART [3] FILLER USING A CUT OUT OF TOP OF BEAM BAC1518-1211 BN 1988076 PER SRM 53-70-51-2R-6 ALTERNATIVE 4 TABLE 204 AND SRM 53-70-51-0I-1 TABLE 6;[09] FABRICATED; LOCATED; DRILLED; AND DEBURRED REPAIR PARTS [1] STRAP; [2] ANGLE; [3] FILLER PER SRM 53-70-51-2R-6 ALTERNATIVE 4;[10] VERIFIED CORRECTIVE ACTION STEPS #8 & #9. INSTALLED REPAIR PARTS PER SRM 53-70-51-2R-6 ALTERNATE 4.;[14] RII: INSPECTED WORK ACCOMPLISHED IN C/A #11 AND #12. NICHOLAS AYLOR (TECHNICIAN); 13-APR-2024 14:03 UTC EDIT C.A. 11 TREATED AND APPLIED 2 COATS OF PRIMER TO REPAIR PARTS AND FLOOR BEAM REPAIR AREA PER SRM 53-70-51-2R-6 ALTERNATIVE 4.;[15] RII: INSPECTED WORK ACCOMPLISHED IN C/A # 13. TIMOTHY ENRIGHT (TECHNICIAN); 17-APR-2024 13:21 UTC INSTALLED REPAIR PARTS PER SRM 53-70-51-2R-6 ALTERNATE 4.;[16] RII: INSPECTED WORK PERFORMED. REPAIRED PER SRM 53-70-51-2R-6 ALTERNATE 4. SEE C/A?S AND STEPS FOR ALL WORK PERFORMED.
AFT GALLEY LAV E O/B AND AFT TIE DOWN FITTING POSSIBLE CORROSION UNDER FITTING. (MARKED)<BLENDED CORROSION PER SRM 51-10-02. MAX MATERIAL REMOVED 0.075?. DAMAGE REMOVAL IS OUT OF LIMITS PER SRM 53-70-51-1A-1;REMOVED DAMAGED SECTION OF FLOOR BEAM UPPER FLANGE PER SRM 53-70-51-2R-5; ALTERNATIVE 2 FLAP PEENED THE CUT EDGE OF 947 FLOOR BEAM PER SRM 53-70-51-2R-5 AND SOPM 20-10-03.;[05] INSPECTED AS REQUIRED. CORRECTIVE ACTION #4;[06] TRIMMED; LOCATED; AND FLAP PEENED 947 FLOOR BEAM T CHORD REPAIR SECTION PER SRM 53-70-51-2R-5 AND SOPM 20-10-03 FABRICATED (-2) SPLICE REPAIR ANGLES; (-3) SPLICE REPAIR STRAPS; AND (-4) FILLERS PER SRM 53-70-51-2R-5.;[0914-APR-2024 20:57 UTC FABRICATED (-2) SPLICE REPAIR ANGLES; (-3) SPLICE REPAIR STRAPS; AND (-4) FILLERS PER SRM 53-70-51-2R-5.TREATED AND PRIMED T CHORD REPAIR SECTION AND (-2) SPLICE REPAIR ANGLES; (-3) SPLICE REPAIR STRAPS; AND (-4) FILLERS ALL PER SRM 53-70-51-2R-5.;[12] DEBURRED ALL FASTENER HOLES; TREATED AND PRIMED ON REPAIR AREA OF AIR CRAFT ALL PER SRM 53-70-51-2R-5.RII-INSTALLED REPAIR ANGLES; STRAPS; AND T-CHORD BETWEEN BL 0? TO RBL 43? AND BETWEEN RBL 56? TO RBL 60? PER SRM 53-70-51-2R; ALTERNATIVE 2.;[16] RII: VERIFIED CORRECTIVE ACTION #15; INSTALLED REMAINING FASTENERS IN T-CHORD BETWEEN RBL 43 AND RBL 56. VERIFIED T-CHORD AND REPAIR PARTS ARE INSTALLED COMPLETE PER SRM 53-70-51-2R; ALTERNATIVE 2;[18] RII: C/W INSPECTION OF C/A #17;CLOSED PARTS SECTION;[20] C/W INSPECTION;[21] C/W INSPECTION
AFT CARGO SIDE PLATE CHANNEL AT LBL 21; STA 767-787+2 HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED) AFT CARGO SIDE PLATE CHANNEL AT LBL 21 STA 767-787+2 HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED)<[01] REMOVED SURFACE CORROSION ON L/H SIDEPLATE FROM STA-767-787+2 LBL21 PER SRM 51-10-02; FOUND TO BE WITHIN ALLOWABLE LIMITS PER SRM 53-00-53-1A-2 MATERIAL REMOVED 0.003 AND REMAINING MATERIAL THICKNESS .037.;[02] 01 - REMOVED AND REPLACED PER [SRM 51-10-02-0G-0-B00070 (GENERAL - INSPECTION AND REMOVAL OF DAMAGE - AIRFRAME - PERMANENT)]<BR>REMOVED AND REPLACED L/H TRANSITION ANGLE FROM STA 727H TO STA 800 WORK ACCOMPLISHED ON CARD # TTG8Q00SRNB5.;[03] VERIFIED WORK ACCOMPLISHED ON ACCOMPLISHED ON CARD # TTG8Q00SRNB5.
AFT GALLEY SERVICE DOOR (R2) HANDLE CAM PLATE LOOSE<[01] SECURED CAM PLATE ATTACHING HARDWARE PER M/M REF 52-41-11;[02] SECURED CAM PLATE ATTACHING HARDWARE PER M/M REF 52-41-11
L/H O/B AFT FLAP DELAMINATED LOWER I/B CORNER LOWER SURFACE<[01] REMOVED L/H O/B AFT FLAP IAW AMM 27-51-22;[02] OK TO INSTALL;[03] INSTALLED L/H OB AFT FLAP PER AMM 27-51-22 THROUGH STEP 3.(5)(G).;[04] C/W RII INSPECTION OF OUTBD FLAP INSTALL;[05] REMOVED AND REPLACED AFT FLAP PER AMM 27-51-22.;[06] 02 - INSPECTED PER [AMM 27-51-22-401-NG (OUTBOARD AFT FLAP - REMOVAL/INSTALLATION - PERMANENT)];[07] 02 - INSPECTED PER [AMM 27-51-22-401-NG (OUTBOARD AFT FLAP - REMOVAL/INSTALLATION - PERMANENT)];[08] 02 - INSPECTED PER [AMM 27-51-22-401-NG (OUTBOARD AFT FLAP - REMOVAL/INSTALLATION - PERMANENT)]
AFT CARGO SIDE PLATE CHANNEL AT RBL 21; STA 767-787 HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED)<[01] 01 - REMOVED AND REPLACED PER [SRM 51-10-02-0G-0-B00070 (GENERAL - INSPECTION AND REMOVAL OF DAMAGE - AIRFRAME - PERMANENT)] REMOVED CORROSION ON FASTENER HOLE LOCATIONS ON AFT CARGO SIDE PLATE CHANNEL (SHIELD)PER SRM 51-10-02 AND SRM 53-00-53-1A-2; FOUND TO BE OUT OF TOLERANCE LIMITS; REMOVED 0.005' REMAINING THICKNESS IS 0.035';[02] 04 - REPAIRED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)] INSTALLED PART #146A8127U12 IAW SRM 51-40-02;[03] 02 - INSPECTED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)]
AFT CARGO SIDE PLATE CHANNEL AT RBL 21; STA 747-767 HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED)<[01] REMOVED SURFACE CORROSION ON AFT CARGO SIDE PLATE CHANNEL AT RBL 21; STA 747-767 PER SRM 51-10-02. REMANNING THICKNESS .030; FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] LOCATED; DRILLED AND COUNTERSUNK FASTENER ON NEW AFT CARGO RH SIDE PLATE FROM STA 727 TO 767 PER SRM 51-40-05 AND SRM 51-40-08;[03] INSPECTED WORK ABOVE;[04] OK TO INSTALL NEW AFT CARGO RH SIDE PLATE FROM STA 727 TO 767.;[05] INSTALLED NEW AFT CARGO RH SIDE PLATE FROM STA 727 TO 767 PER SRM 51-40-02.;[06] C/W INSPECTION OF INSTALLED NEW AFT CARGO RH SIDE PLATE FROM STA 727 TO 767 PER SRM 51-40-02.
AFT CARGO SIDE PLATE CHANNEL AT LBL 21; STA 727J-747 HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED)<[01] REMOVED SURFACE CORROSION ON AFT CARGO L/H SIDE PLATE CHANNEL PER SRM 51-10-02; FOUND TO BE WITHIN ALLOWABLE LIMITS PER SRM 53-00-53-1A-2. MATERIAL REMOVED .003 AND REMAINING THICKNESS .037.;[02] CORRECTION LINE 1. REMOVED SURFACE CORROSION ON AFT CARGO L/H SIDE PLATE CHANNEL AT LBL 21; STA 727J-747 PER SRM 51-10-02; FOUND TO BE WITHIN ALLOWABLE LIMITS PER SRM 53-00-53-1A-2. MATERIAL REMOVED .003 AND REMAINING THICKNESS .037.;[03] 01 - REMOVED AND REPLACED PER [SRM 51-10-02-0G-0-B00070 (GENERAL - INSPECTION AND REMOVAL OF DAMAGE - AIRFRAME - PERMANENT)]<BR>REMOVED AND REPLACED L/H TRANSITION ANGLE FROM STA 727H TO STA 800 WORK ACCOMPLISHED ON CARD # TTG8Q00SRNB5.;[04] VERIFIED WORK ACCOMPLISHED ON ACCOMPLISHED ON CARD # TTG8Q00SRNB5.
AFT CARGO SIDE PLATE CHANNEL AT RBL 21; STA 727J-747 HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED)<[01] REMOVED SURFACE CORROSION ON AFT CARGO SIDE PLATE CHANNEL AT RBL 21; STA 727J-747 PER SRM 51-10-02. REMANNING THICKNESS .033; FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. FOR COMPANY CONVENIENCE R/H TRANSITION ANGLE TO BE REPLACED ON NON-ROUTINE TTG8Q00SMQ8J. FROM STA. 727 PLUS 4 TO STA. 767.;[02] INSPECTED WORK ABOVE
AFT CARGO SIDE PLATE CHANNEL AT RBL 21; STA 727I-727J HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED)<[01] REMOVED SURFACE CORROSION ON AFT CARGO SIDE PLATE CHANNEL AT RBL 21; STA 727I-727J PER SRM 51-10-02. REMANNING THICKNESS .033; FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. FOR COMPANY CONVENIENCE R/H TRANSITION ANGLE TO BE REPLACED ON NON-ROUTINE TTG8Q00SMQ8J. FROM STA. 727 PLUS 4 TO STA. 767.;[02] INSPECTED WORK ABOVE
AFT CARGO SIDE PLATE CHANNEL AT LBL 21; STA 747-767 HAS VARIOUS AREAS OF SURFACE CORROSION VISIBLE. (MARKED)<[01] REMOVED SURFACE CORROSION ON AFT CARGO L/H SIDE PLATE CHANNEL PER SRM 51-10-02; FOUND TO BE WITHIN ALLOWABLE LIMITS PER SRM 53-00-53-1A-2. MATERIAL REMOVED .002 AND REMAINING THICKNESS .038.;[02] CORRECTION LINE 1. REMOVED SURFACE CORROSION ON AFT CARGO L/H SIDE PLATE CHANNEL AT LBL 21; STA 747-767 PER SRM 51-10-02; FOUND TO BE WITHIN ALLOWABLE LIMITS PER SRM 53-00-53-1A-2. MATERIAL REMOVED 0.002 AND REMAINING THICKNESS 0.038.;[03] 01 - REMOVED AND REPLACED PER [SRM 51-10-02-0G-0-B00070 (GENERAL - INSPECTION AND REMOVAL OF DAMAGE - AIRFRAME - PERMANENT)]<BR>REMOVED AND REPLACED L/H TRANSITION ANGLE FROM STA 727H TO STA 800 WORK ACCOMPLISHED ON CARD # TTG8Q00SRNB5.;[04] VERIFIED WORK ACCOMPLISHED ON ACCOMPLISHED ON CARD # TTG8Q00SRNB5.
BETWEEN STATION 380 AND 400; THE INTERCOSTAL AT LBL 14 HAS EVIDENCE OF CRACKS AT BOTH THE FASTENER HOLES AND THE UPPER ANGLE INNER RADIUS.<[01] REMOVED AND REPLACED UPPER ANGLE PER SRM 51-40-02.;[02] RII C/W INSPECTION AS REQUIRED
AFT WET AREA- CORROSION ON FLOOR WEB AT STA 986 +3; LBL +33 MARKED; BLENDED CORROSION PER SRM 51-10-02. REMOVED .030' OF MATERIAL. REMAINING THICKNESS IS .010'. DAMAGE REMOVAL IS OUT OF LIMITS PER SRM 53-70-51-1A-1. BLENDED CORROSION PER SRM 51-10-02. REMOVED .030' OF MATERIAL. REMAINING THICKNESS IS .010'. DAMAGE REMOVAL IS OUT OF LIMITS PER SRM 53-70-51-1A-1.;REMOVED DAMAGED WEB FROM STA. 986.5 TO STA. 1016; LBL 30' TO LBL 46' PER SRM 51-40-02.;[04] LOCATED AND DRILLED NEW SHEAR WEB PER SRM 51-40-05. OK TO INSTALL PER SRM 51-40-02. INSPECTED REMOVAL OF WEB & LOCATION & DRILL OF NEW SHEAR WEB PER SRM 51-40-05. OK TO INSTALL (RII);[06] RII-INSTALLED NEW SHEAR WEB FROM STA. 986.5 TO STA. 1016; LBL 30? TO LBL 46' PER SRM 51-40-02. APPLIED EDGE SEAL AND CAP SEAL PER AMM 51-31-00.
AFT WET AREA- CORROSION ON FLOORBEAM AT HOLE- STA 987; RBL +44. REMOVED CORROSION IAW SRM 51-10-02. DAMAGE REMOVAL APPROX .065' OUT OF LIMITS PER SRM 53-70-51-1A-1. CUT & REMOVED DAMAGED PART OF FLOORBEAM IAW SRM 53-70-51-2R-6, REPAIR 6, ALTERNATIVE 4. VERIFIED DAMAGE REMOVAL PER SRM 53-70-51-2R-6, REPAIR 6, ALTERNATIVE 4. C/W NDT INSPECTION PER SRM 53-70-51-2R-6, REPAIR 6, ALTERNATIVE 4. NDT PART 6; 51-00-00 PROCEDURE 23, NDT PART 6; 51-00-00 PROCEDURE 16, FLAP PEENED BLENDED AREA IAW SOPM 20-10-03, FABRICATED & LOCATED/DRILLED FASTENER HOLES IN -1 STRAP, FABRICATED & LOCATED/DRILLED FASTENER HOLES IN -2 ANGLE AND -3 FILLER. INSTALLED REPAIR , APPLIED PRIMER TO FASTENER HEADS; AND FILLET SEAL PER SRM 53-70-51-2R-6 ALTERNATIVE 4.
AFT WET AREA- CORROSION ON FLOOR PAN WEB AT STA 1006 +3; LBL +38. DRILLED UP NEW WEB PER SRM 51-40-02.;[02] BLENDED CORROSION ON FLOOR PAN WEB AT STA. 1006+3'; LBL 38' IAW SRM 51-10-02. REMOVED .012' OF MATERIAL. REMAINING THICKNESS IS .028. DAMAGE REMOVAL OUT OF LIMITS PER SRM 53-70-51-1A-1.
AFT WET AREA- CORROSION ON FLOOR PAN WEB AT STA 1006 +8; LBL +38. DRILLED UP NEW WEB PER SRM 51-40-02. BLENDED CORROSION ON FLOOR PAN WEB AT STA. 1006+8'; LBL 38' PER SRM 51-10-02. REMOVED .008' OF MATERIAL. REMAINING THICKNESS IS .032. DAMAGE REMOVAL OUT OF LIMITS PER SRM 53-70-51-1A-1.
AFT WET AREA- CORROSION ON FLOOR BEAM AT STA 947 +4; LBL +25. BLENDED CORROSION PER SRM 51-10-02. DAMAGE REMOVAL FOUND TO BE OUT OF LIMITS PER SRM 53-70-51-1A-1. BLENDING WAS DONE ON INTERCOSTAL WHICH IS OUT OF LIMITS. REMOVED DAMAGED INTERCOSTAL FROM STA. 947 TO STA. 967 AT LBL 24? PER SRM 51-40-02. REMOVED AND REPLACED DAMAGED INTERCOSTAL PER SRM 51-40-02.
FWD CARGO FLOOR STRUCTURE SIDE PLATE HAS LIGHT CORROSION AROUND FASTENER HOLES FROM STA 500F TO 500I LBL 24.<[01] BLENDED AREAS; REMOVED .005' MATERIAL; FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. THIS SECTION TO BE REPLACED FROM STA 500B + 10 TO 500I ON NR # TTG8Q00SLBEU.;[02] 02 - INSPECTED PER [SRM 53-00-53-1A-2-B00297 (PERMANENT (NON-DENT DAMAGE TYPES))]
FWD CARGO FLOOR STRUCTURE SIDE PLATE HAS LIGHT CORROSION AROUND FASTENER HOLES FROM STA 500D TO 500F LBL 24.<[01] THIS SECTION TO BE REPLACED FROM STA 500B + 10 TO 500I ON NR # TTG8Q00SLBEU;[02] BLENDED AREAS; REMOVED .009' MATERIAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2;[03] BLENDED AREAS; REMOVED .009' MATERIAL FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2. THIS SECTION TO BE REPLACED FROM STA 500B + 10 TO 500I ON NR # TTG8Q00SLBEU;[04] 01 - REMOVED AND REPLACED PER [GENERAL FAULT RESOLVED ON OTHER FAULT (FAULT WAS RESOLVED ON ANOTHER FAULT)] SEE TTG8Q00SLBEU FOR ALL WORK ACCOMPLISHED.
FWD CARGO FLOOR STRUCTURE SIDE PLATE HAS LIGHT CORROSION AROUND FASTENER HOLES FROM STA 500A TO 500D LBL 24.<[01] BLENDED AREAS; REMOVED .008' MATERIAL. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2;[02] BLENDED AREAS; REMOVED .008' MATERIAL. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2;[03] LOCATED; DRILLED; AND INSTALLED NEW SIDE PLATE PER SRM 53-00-53-2R-5 FROM STA. 500B + 10 TO 500I.;[04] LOCATED; DRILLED; AND INSTALLED NEW SIDE PLATE P/N BAC1496-364 BA#299262 PER SRM 53-00-53-2R-5 FROM STA. 500B + 10 TO 500I.;[05] 02 - INSPECTED PER [SRM 53-00-53-2R-5-B00308 (REPAIR 5 - CARGO COMPARTMENT SIDEPLATE REPAIR BETWEEN FLOOR PANEL SPLICES - PERMANENT)]
FWD CARGO FLOOR STRUCTURE SIDE PLATE HAS LIGHT CORROSION AROUND FASTENER HOLES FROM STA 500 TO 500A RBL 24.<[01] BLENDED AREAS; REMOVED .030' MATERIAL. FOUND TO BE OUT OF LIMITS PER SRM 53-00-53-1A-2.;[02] REMOVED AND REPLACED SHIELD PER SRM 51-40-02.;[03] 02 - INSPECTED PER [SRM 51-40-02-0G-0-B00069 (GENERAL - FASTENER INSTALLATION AND REMOVAL - AIRFRAME - PERMANENT)]
RH HORIZONTAL STABILIZER FRONT SPAR UPPER SLIDING SEAL IS CRACKED.<[01] REMOVED AND REPLACED RH HORIZONTAL STABILIZER FRONT SPAR UPPER SLIDING SEAL PER AMM 53-31-31.
RH WING OUTBD AFT FLAP INBD SIDE IS DELAMINATED L=19.5X W=10.75<[01] REMOVED AND REPLACED R/H WING OUTBOARD AFT FLAP PER AMM 27-51-22 OPS RIG CK NORMAL;[02] REMOVED AND REPLACED R/H WING OUTBOARD AFT FLAP PER AMM 27-51-22 OPS RIG CK NORMAL
MULTIPLE EMERGENCY LIGHTS ARE INOP THROUGHOUT THE CABIN AND EXTERIOR. / [01] REMOVED AND REPLACED AFT LEFT BATTERY PACK; ROW 21 ABC; AND ROW 21 DEF BATTERY PACKS IN REFERENCE TO AMM 33-51-06. EMERGENCY LIGHTING SYSTEM OPS CHECKS GOOD.
RH FWD OVERWING & TWO RH FWD AISLE EMERGENCY LIGHTS ARE INOP<[01] REPLACED R/H FWD AISLE EMERGENCY BATTERY IAW AMM 33-51-06. OPS CHECK GOOD
L1 DOOR EXTERIOR LIGHT; LOWER WALL AND EMERGENCY EXIT SIGN ON L1 DOOR INOP<[01] R/R LH FWD EMERGENCY LIGHT POWER SUPPLY BATTERY PACK IAW AMM 33-51-06
EMERGENCY EXIT LIGHT OVER AFT GALLEY SERVICE DOOR INOP<[01] R&R EMERGENCY LIGHT CHARGER AND BATTERY PACK AT R/H POSITION IN AFT GALLEY FDR CEILING COMPARTMENT IAW AMM 33-51-06
AFT PIT FWD SHIELD SUPPORT ANGLE AT STA 767+7 WL 155 RBL 22 HAS CORROSION ON UPPER SURFCE / [01] REMOVED CORRODED FWD SHIELD SUPPORT ANGLE BS 767-787 RBL 22 IAW SRM 51-40-02-0G-0;[02] VERIFIED NEW FWD SHIELD SUPPORT ANGLE BS 767-787 RBL 22 IAW DWG 146A0081 REV A P/N 146A8125-53 ATAG WN15434;[03] VERIFIED NEW PART;[04] LOCATED AND DRILLED FWD SHIELD IAW SRM 51-40-05-0G-0 DWG 146A0081 REV A;[05] EDIT TO ITEM 4. LOCATED AND DRILLED FWD SHIELD SUPPORT ANGLE IAW SRM 51-40-05-0G-0 DWG 146A0081 REV A;[06] VERIFIED STEPS 4 AND 5<BR>OK TO INSTALL<BR>OK TO CIC;[07] INSTALLED NEW FWD SHIELD SUPPORT ANGLE IAW SRM 51-40-02-0G-0 DWG 146A0081 REV A;[08] REMOVED AND REPLACED AFT PIT FWD SHIELD SUPPORT ANGLE AT STA 767-787 RBL 22 IAW SRM 51-40-02-0G-0 AND DWG 146A0081 REV A;[09] VERIFIED STEPS 7 AND 8 <BR>AUDIT C/W
DOT#65-186 AFT PIT Z ANGLE CORRODED STA 727I+7' TO 807 LBL 22 WL 156 / [01] REMOVED CORROSION. EVALUATED MATERIAL LOSS; ORIGINAL T .040; REMAINING .030; LOSS OF .010. OUT OF LIMITS IAW B737 SRM 53-00-53-1A-2.FIG 103 VIEW A-A. AAR TOOL #32351 CAL DUE 12/10/22.;[02] REMOVED L/H Z ANGLE FROM STATION 727H+10 TO 787+13 IAW B737 SRM 53-00-53-2R-5; REPAIR 5. NO CORROSION NOTED AFT OF STATION 787+13.;[03] VERIFIED STEP 1 & 2 C/W.;[04] MATERIAL FOR REPLACEMENT ANGLE VERIFIED AS BAC1496-377 7075-T6 IAE B737 SRM 53-00-53-2R-5; REPAIR 5; TABLE 201. A TAG# A101696.;[05] VERIFIED STEP 4;[06] LOCATED; DRILLED AND TRIMMED REPAIR ANGLE AND 2 EA SPLCES IAW B737 SRM 53-00-53-2R-5 REPAIR 5; STEP 4; ITEMS E-H.;[07] VERIFIED STEP 6;[08] OK FOR STEPS I;J ALODINE AND PRIME FOR SRM 53-00-53-2R REPAIR 5;[09] OK TO TREAT/PRIME;[10] ALODINED AND PRIMED L/H SIDE AFT CARGO NEW SECTION OF Z-ANGLE ;SPLICE ANGLES; CUT ENDS OF OEM Z-ANGLE IAW SRM 53-00-53-2R-5 REPAIR 5 STEPS 4 I;J;[11] VERIFIED STEP 10;[12] INSTALLING REPAIR PARTS ONTO NEW SECTION OF Z-ANGLE ONLY FOR STEP 4 L OF SRM 53-00-53-2R-5;[13] VERIFIED STEP 12;[14] NEED OK TO INSTALL ON A/C;[15] OK TO INSTALL<BR>OK TO CIC LOWER SURFACE<BR>VERIFIED CIC ON BOTTOM SURFACE;[16] INSTALLED NEW SECTION OF Z-ANGLE AT L/H SIDE STA 727H+10' TO STA 787+13' AND APPLIED FINISH TO REPAIR AREA ALSO APPLIED CIC FOR STEP 4 L;M;N OF SRM 53-00-53-2R-5 REPAIR 5;[17] VERIFIED STEPS 16<BR>AUDIT C/W
DOT#66-186 AFT PIT FWD SHIELD CORRODED STA 767+7 RBL 22 WL 156 / [01] REMOVED CORROSION FROM FWD SHIELD; ORIG T= .050' LOSS OF .008' REM T= .042' FOUND TO BE OUT OF LIMITS IAW SRM 53-60-151A-1 TOOLING INFO AAR 32351 CAL DUE 12/12/22;[02] VERIFIED STEP 1;[03] REMOVED FWD SHIELD IAW SRM 51-40-02-0G-0;[04] VERIFIED NEW FWD SHIELD AS P/N 146A8172-12 ATAG WN14463 IAW DWG 146A0081 REV A;[05] VERIFIED NEW PART;[06] LOCATED AND DRILLED NEW SHIELD IAW SRM 51-40-05-0G-0; DWG 146A0081 REV A;[07] VERIFIED STEP 6<BR>OK TO INSTALL<BR>OK TO CIC;[08] INSTALLED NEW AFT PIT FWD SHIELD I/A/W B737-800 SRM 51-40-02-0G-0 AND BOEING DWG 146A0081 REV. A;[09] VERIFIED STEP 8;[10] REMOVED CORROSION FROM FWD SHIELD; ORIG T= .050' LOSS OF .008' REM T= .042' FOUND TO BE OUT OF LIMITS IAW SRM 53-60-151A-1 TOOLING INFO AAR 32351 CAL DUE 12/12/22; REMOVED FWD SHIELD IAW SRM 51-40-02-0G-0; INSTALLED NEW AFT PIT FWD SHIELD I/A/W B737-800 SRM 51-40-02-0G-0 AND BOEING DWG 146A0081 REV. A;[11] VERIFIED STEP 10;[12] JOB COMPLETE; AUDIT C/W
DOT#67-186 AFT PIT LAV TANK LOWER BKHD STANTION (LEEK) ANGLE CRACKED STA 867 LBL 11 WL 156 / [01] REMOVED AND REPLACED CRACKED CLIP IN AFT CARGO COMPARMENT AT AFT BULKHEAD STA 850; LBL 11 IAW SRM 51-40-02-0G-0 AND BOEING DWG 149A8102 ID:0015 REV:A;[02] VERIFIED STEPS 1<BR>AUDIT C/W
DOT#68-186 AFT PIT FLOOR SPLICE STRAP CORRODED STA 887 LBL 3 TO RBL 4 WL 156 / [01] VERIFIED REPLACEMENT PART AS P/N 149A9401-39; ITEM #650;IAW AIPC 53-42-11-26. A-TAG # WN15356.;[02] REMOVED DAMAGED PART FROM A/C IAW AMM 25-52-10-000-801.;[03] VERIFIED STEPS 1 AND 2;[04] LOCATED AND DRILLED FASTENER HOLES IAW SRM 51-40-05-0G-0. NEED OK TO CIC.;[05] VERIFIED STEP 4<BR>OK TO CIC;[06] APPLIED CIC IAW AMM 51-21-91-620-802.;[07] VERIFIED STEP 6;[08] OK TO INSTALL STRAP BS 887;[09] INSTALLED AFT PIT FLOOR SPLICE STRAP AT STA 887; IAW AMM 25-52-10-400-801.;[10] VERIFIED STEP 9<BR>AUDIT C/W
FWD CARGO RH Z ANGLE CORRODED WL 156; BS 500A TO 500I ; RBL 25 A225-00I / [01] REMOVED CORROSION IAW SRM 51-10-02 10X MAGNIFY ORIGINAL THICKNESS.040 .010 MATERIAL REMOVED .030 MATERIAL REMAINS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-53-1A-2 AAR TOOL NO.36644 DUE DATE 08/20/22;[02] VERIFIED STEP IS COMPLETE;[03] VERIFIED ITEM 2;[04] REMOVED RH Z ANGLE IAW SRM 51-40-02;[05] VERIFIED STEP 1; 2; 3 & 4.;[06] VERIFY MATERIAL USED FOR Z ANGLE REPAIR BAC1496-444 7075-T6 ATAG A67397;[07] Z ANGLE REPAIR SRM 53-00-53-2R-5;[08] VERIFIED STEPS 6 & 7.;[09] STARTED FABBING REPAIR PARTS IAW SRM 53-00-53-2R-5;[10] FINISHED TO FABRICATE Z ANGLE REPAIR PARTS IAW SRM 53-00-53-2R-5 REPAIR 5;[11] VERIFIED STEP 10;[12] VERIFIED STEPS 9;10;11<BR>OK TO TREAT AND PRIME;[13] CUT OUT AREA IS BETWEEN STA 500D - 500E IAW SRM 53-00-53-2R-5 REPAIR 5;[14] APPLIED ALODINE AND PRIMER ON REPAIR PARTS IAW SRM 51-20-0G-0 AND AMM 51-21-72-370-804;[15] VERIFIED STEPS 13 AND 14;[16] VERIFIED STEP 13;14;15;[17] OK GIVEN TO INSTALL NEW Z ANGLE REPAIR PARTS;[18] INSTALLED Z ANGLE REPAIR PARTS IAW SRM 53-00-53-2R-5 REPAIR 5;[19] VERIFIED STEP 18;[20] VERIFIED ITEMS 18 AND 19. OK TO CIC;[21] APPLIED CIC ON Z ANGLE REPAIR AREAS IAW AMM 51-21-91-620-802;[22] VERIFIED STEP 21;[23] VERIFIED STEPS 21 AND 22 CIC APPLIED;[24] JOB COMPLETE; AUDIT C/W
FWD CARGO FLOOR PANEL 120 AF HAS CORROSION ALONG EDGE A225-003 / [01] BLENDED DAMAGE ON FWD CARGO FLOOR PANEL 120AF; DAMAGE EXCEEDS MAXIMUM ALLOWABLE DAMAGE OF 20 INCHES. FOUND TO BE OUT OF LIMITS I/A/W B737-800 SRM 53-00-53-1A-1;[02] VERIFIED MATERIAL TO BE USED TO FABRICATE FLOOR PANEL 120AF TO BE 2024-T3 .071' I/A/W B737-800 AMM 25-52-01-201-801<BR><BR>A-TAG#122577;[03] VERIFIED ITEM 1 AND 2;[04] BEGAN FABRICATING; LOCATING AND DRILLING NEW FLOOR BOARD PANEL 120AF I/A/W B737-800 AMM 25-52-01-201-801 SECTION 1.F.;[05] VERIFIED STEP 4 BEGAN FABRICATING;[06] COMPLETED FABRICATION; LOCATED AND DRILLED NEW FLOOR BOARD PANEL 120AF I/A/W B737-800 AMM 25-52-01-201-801 SECTION 1.F.;[07] VERIFIED STEP 6;;[08] OK GIVEN TO TREAT AND PRIME;[09] TREATED AND PRIMED PANEL 120AF I/A/W B737-800 AMM 51-21-41-370-802 AND 51-21-72-370-804.;[10] VERIFIED ITEM 9
FWD CARGO FLOOR PANEL 120 BF HAS CORROSION ALONG EDGE A225-004 / [01] EVALUATED CORROSION EXCEED MORE 20 INCH MAXIMUM ALLOWED FOUND OUT OF LIMITS IAW SRM 53-00-53-1A-1 FIG 102;[02] VERIFIED STEP 1;[03] VERIFIED STEPS 1 AND 2;[04] VERIFIED. MATERIAL ID FOR FLOOR PANEL IS 2024 T3 .071 TAG #A122578 IAW AMM 25-52-01-201-801;[05] VERIFIED STEP 4;[06] FABRICATED 120BF FLOOR PANEL IAW AMM 25-52-01-201-801;[07] VERIFIED ITEM 6; OK TO TREAT AND PRIME;[08] APPLIED ALODINE AND PRIMER ON FLOOR PANEL IAW SRM 51-21-01-0G-0 AND AMM 51-21-72-370-804;[09] JOB COMPLETE; AUDIT C/W
FWD CARGO FLOOR PANEL 120 DF HAS CORROSION ALONG EDGE A225-005 / [01] REMOVED CKORROSION IAW SRM 53-00-53-1A-1. ORIGINAL THICKNESSS .071'; LOSS .020' REMAINING MATERIAL .051'; FOUND TO BE OUT OF LIMITS IAW SRM 53-00-53-1A-1. AAR TOOL 32351 CAL DUE DATE 12/10/22.;[02] VERIFIED MATERIAL AS 2024 T3 .071' A-TAG A122583 IAW AMM 25-52-01-201-801.;[03] VERIFIED STEP 2;[04] FABRICATED FLOOR PANEL 120DF IAW AMM 25-52-01-201-801.;[05] OK TO TREAT AND PRIME BACK SIDE OF PANEL 120DF;[06] VERIFIED STEPS 4 & 5;[07] TREATED AND PRIMED BACKSIDE OF PANEL IAW AMM 51-21-41 AND AMM 51-21-73. PANEL COMPLETE ALL STEPS 1-7 C/W.;[08] VERIFIED STEP 7<BR>AUDIT C/W
FWD CARGO AFT SHIELD CORRODED WL 156; BS 500 TO 500A ; RBL 25 A225-004 / [01] REMOVED CORROSION IAW SRM 51-10-02 10X MAGNIFY ORIGINAL THICKNESS .040 .015 MATERIAL REMOVED .052 MATERIAL REMAINS OUT OF LIMITS IAW SRM 53-00-53-1A-2 AAR TOOL NO.36644 DUE DATE 08/20/22;[02] VERIFIED STEP 1 IS COMPLETE;[03] REMOVED CORROSION IAW SRM 51-10-02 10X MAGNIFY ORIGINAL THICKNESS .040 .015 MATERIAL REMOVED .025' MATERIAL REMAINS OUT OF LIMITS IAW SRM 53-00-53-1A-2 AAR TOOL NO.36644 DUE DATE 08/20/22;[04] VERIFIED ITEMS 1 THROUGH 3;[05] REMOVED AFT SHIELD FWD PIT IAW SRM 51-40-02 VERIFY NEW SHIELD P/N 143A8126-38 ATAG WN15353 IAW BOEING DWG 143A0080 REV-;[06] VERIFIED ITEM 5;[07] DRILLED UP NEW FWD CARGO AFT SHIELD I/A/W SRM 51-40-02-0G-0 AND BOEING DWG 143A0080 REV -;[08] VERIFIED STEP 7<BR>OK TO INSTALL;[09] INSTALLED NEW FWD CARGO AFT SHIELD I/A/W SRM 51-40-02-0G-0 AND BOEING DWG 143A0080;[10] VERIFIED STEP 9<BR>OK TO CIC;[11] APPLIED CIC I/A/W AMM 51-21-91-620-802;[12] REMOVED AND INSTALLED NEW FWD CARGO AFT SHIELD I/A/W SRM 51-40-02-0G-0 AND BOEING DWG 143A0080;[13] VERIFIED STEPS 11 AND 12<BR>AUDIT C/W
FWD CARGO AFT BLKD LOWER SUPPORT ANGLE CORRODED WL 156; BS 500I; RBL 25 TO LBL25 A225-003 / [01] REMOVED CORROSION IAW SRM 51-10-02 10X MAGNIFY MINIMUM ALLOWABLE MATERIAL REMAINING .056 .050 MATERIAL REMAINS FOUND TO BE OUT OF LIMITS IAW SRM 53-30-08-1A-1 AAR TOOL NO. 36644 DUE DATE 08/20/22;[02] VERIFIED STEP 1 IS COMPLETE;[03] VERIFIED ITEMS 1 AND 2;[04] VERIFY NEW ANGLE P/N 143A9485-35 ATAG WN12803 IAW BOEING DWG 143A9481 REV-;[05] VERIFIED STEP 4;[06] VERIFIED STEPS 4 AND 5; PART VERIFIED AS CORRECT;[07] OK TO INSTALL;[08] INSTALLED RAIL ASSEMBLY IAW BOEING DWG 143A9481 REV- AND SRM 51-40-02 P/NO. 143A9485-35;[09] INSTALLATION COMPLETE;[10] VERIFIED STEPS 8 AND 9; JOB COMPLETE; AUDITS C/W
FWD CARGO LH Z ANGLE CORRODED WL 156; BS 500B - 8' TO 500I ; LBL 25 A225-006 / [01] REMOVED CORROSION IAW SRM 51-10-02 10X MAGNIFY ORIGINAL THICKNESS.040 .003 MATERIAL WAS REMOVED .037 MATERIAL REMAINS FOUND TO BE IN LIMITS IAW 53-00-53-1A-2 AAR TOOL NO.36644 DUE DATE 08/20/22;[02] VERIFIED STEP IS COMPLETE;[03] CORRECTION TO ITEM 1. FOUND MATERIAL LOSS BETWEEN STATION 500C AND 500D OUT OF LIMITS WITH .031' REMAINING 40 ORIGINAL; LOSS OF .009'. AREA OUT OF LIMITS IAW 53-00-03-1A-2;[04] REMOVED DAMAGED Z ANGLE IAW SRM 53-00-53-2R-5;[05] VERIFIED STEP 4;[06] VERIFIED STEPS 1; 2; 3; 4 & 5.;[07] VERIFY MATERIAL USED FOR Z ANGLE REPAIR BAC1496-444 7075-T6 ATAG A67397 IAW SRM 53-00-53-2R-5;[08] VERIFIED STEP 7.;[09] STARTED FABBING REPAIR PARTS IAW SRM 53-00-53-2R-5;[10] FINISHED TO FABRICATE Z ANGLE REPAIR PARTS IAW SRM 53-00-53-2R -5 REPAIR 5;[11] VERIFIED STEP 10;[12] VERIFIED STEP 9;10 11<BR>OK TO TREAT AND PRIME;[13] CUT OUT AREA IS BETWEEN STA.500C-500D AND 500C-500B IAW SRM 53-00-53-2R-5 REPAIR 5;[14] APPLIED ALODINE AND PRIMER REPAIR PARTS IAW SRM 51-20-01-0G-0 AND AMM 51-21-72-370-804;[15] VERIFIED STEPS 13 AND 14;[16] VERIFIED STEP 13;14;15;[17] OK GIVEN TO INSTALL NEW Z ANGLE REPAIR PARTS;[18] INSTALLED Z ANGLE REPAIR PARTS IAW SRM 53-00-53-2R-5 REPAIR 5;[19] VERIFIED STEP 18;
STRINGER CLIP CRACKED AT LOWER RIVET (FRAME ATTACH) BS 500I; WL 153; S26RH. UNDER Z ANGLE A225-001 / [01] REMOVED S26R STR CLIP SRM SRM 51-40-02-0G-0;[02] VERIFIED NEW STR CLIP AS P/N 143A1010-48 ATAG A02631 IAW DWG 143A1234 REV A;[03] VERIFIED STEP 2;[04] LOCATED AND DRILLED NEW STR CLIP IAW BOEING DWG # 143A1234 REV A & SRM 51-40-05.;[05] VERIFIED STEP 4<BR>OK TO INSTALL;[06] INSTALLED STR CLIP IAW B DWG #1431234 REV A AND SRM 51-40-02-0G-0.;[07] VERIFIED STEP 6 AT BS 500I; STRINGER 26R;[08] AUDIT CW
STRINGER CLIP CRACKED AT LOWER RIVET (FRAME ATTACH) BS 500I; WL 153; S26LH. UNDER Z ANGLE A225-002 / REMOVED SECTION OF L/H Z-ANGLE STA 500D TO STA 500 I FOR ACCESS IAW SRM 51-40-02-0G-0;DISPLACED L/H SIDE AFT END OF BAFFLE STA 500I AT STR 26 FOR ACCESS IAW SRM 51-40-02-0G-0 DISPLACED LOWER BULKHEAD STRUCTURE AT STA500I STR 24 TO STIR 27 IAW SRM 51-40-02-0G-0;REMOVED 1 QTY FASTENER AT SHEAR TIE FOR ACCESS AT STA 500I BETWEEN STR 26 AND 25 IAW SRM 51-40-02-0G-0 REMOVED CRACKED STR CLIP AT STA 500I STR 26 IAW SRM 51-40-02-0G-0;LOCATED AND DRILLED NEW -28 STR CLIP IAW BOEING DWG 143A1234 REV A;INSTALLED NEW -28 STR CLIP IAW BOEING DWG 143A1234 REV A SRM 51-40-02-0G-0;INSTALLED DISPLACED L/H SIDE AFT END OF BAFFLE STA 500I AT STR 26 IAW SRM 51-40-02-0G-0;INSTALLED 1 QTY FASTENER AT SHEAR TIE AT STA 500I BETWEEN STR 26 AND 25 IAW SRM 51-40-02-0G-0 BOEING DWG 143A1234 REV AAPPLIED CIC ON NEW -28 STR CLIP IAW AMM51-21-91-620-802; INSTALLED L/H Z-ANGLE STA 500D TO STA 500I IAW SRM 51-40-02-0G-0 BOEING DWG 143A7500 REV- REJECT- 1EA FASTENER MISSING FROM LH Z ANGLE AT STA 500I JUST AFT OF BLKHD PANEL LOWER SUPPORT REINSTALLED BULK HEAD STRUCTURE AT STA 500I STR 27L TO STIR 25L IAW SRM 51-40-02-0G-0 REINSTALLED DISPLACED INSULATION L/H SIDE STA 500C TO STA 500I AT STR 26L IAW AMM 25-80-00-400-801 ALSO INSTALLED 1 QTY CHERRYMAX RIVET AT Z-ANGLE BEHIND BULKHEAD STR 26L IAW SRM 51-40-02-0G-0;
AFT CARGO FLOOR BOARD 140 DF CORRODED ALONG EDGE A225-004 / [01] EVALUATED CORROSION DAMAGE; FOUND TO BE OUT OF LIMITS DUE TO TOTAL ACCUMULATED DAMAGE BEING MORE THAN THE 20' MAX ALLOWED IAW SRM 53-00-53-1A-1;[02] MATERIAL VERIFIED FOR NEW PNL FAB; 2024-T3 .071'; IAW AMM 25-52-01-201-801<BR>ATAG A105084;[03] VERIFIED STEPS 1 AND 2;[04] FABRICATED NEW PNL 140DF IAW AMM 25-52-01-201-801;[05] VERIFIED STEP 4;[06] OK GIVEN TO TREAT AND PRIME;[07] TREATED IAW AMM 51-21-41-370-802 AND PRIMED IAW AMM 51-21-72-370-804;[08] VERIFIED STEP 7;[09] JOB COMPLETE; AUDIT C/W
AFT CARGO FLOOR BOARD 140 BF CORRODED ALONG EDGE A225-002 / [01] EVALUATED CORRODED AREA ON FLOOR PNL 140BF FOUND LENGTH OF CORROSION MORE THEN 20' IS OUT OF LIMITS I.A.W SRM 53-00-53-1A-1;[02] VERIFIED MATERIAL FOR NEW PNL AS 2024-T3 .071 <BR>A TAG#A122584 I.A.W MM 25-52-01-201-801;[03] VERIFIED ITEMS 1 AND 2;[04] STARTED DRILLING AND TRIMMING NEW PNL I.A.W MM 25-52-01-201-801;[05] FINISHED DRILLING AND TRIMMING NEW FLOOR PNL I.A.W MM 25-52-01-201-801;[06] VERIFIED STEP 4 AND 5;[07] OK GIVEN TO TREAT AND PRIME;[08] ALODINED TOP AND BOTTOM SIDE OF FLOOR PNL AND PRIMED BOTTOM SIDE OF FLOOR PNL I.A.W MM 51-21-72-370-802;[09] JOB COMPLETE; AUDIT C/W
AFT CARGO FLOOR BOARD 140 EF CORRODED ALONG EDGE A225-001 / [01] CORROSION ON PANEL 140EF EXCEEDS THE 20' MAX LIMIT. PANEL FOUND OUT OF LIMITS IAW B-737 AMM 25-52-00-200-803.;[02] MATERIAL VERIFIED AS 0.071' 2024-T3 IAW B-737 AMM 25-52-01-201-801. A-TAG A122585;[03] VERIFIED STEPS 1 AND 2 MATERIAL VERIFIED AS 0.071' 2024-T3; CORROSION OUT OF LIMITS;[04] NEW PANEL 140EF FABRICATED IAW B-737 AMM 25-52-01-201-801.;[05] VERIFIED STEP 4;[06] OK GIVEN TO TREAT AND PRIME;[07] TREATED AND PRIMED FLOOR BOARD 140EF I/A/W B737-800 AMM 51-21-41 AND 51-21-72.;[08] JOB COMPLETE; AUDIT C/W
AFT CARGO FORWARD BULKHEAD 142 NWB CRACKED A225-006 / [01] VERIFIED AND REPLACED AFT CARGO FWD BULKHEAD PANEL # 142NWB ON PARTS RACK IAW IPC 25-52-19-01B AND BOEING DWG# 453A25110 ID:0001 REV:C;[02] VERIFIED STEP 1 COMPLETE<BR>AUDIT C/W
AFT CARGO FLOOR BOARD 140 CF CORRODED ALONG EDGE A225-005 / [01] REMOVED CORROSION IAW SRM 53-00-53-1A-1. ORIGINAL THICKNESS .071' LOSS .020'; REMAINING MATERIAL .051' OUT OF LIMITS IAW SRM 53-00-53-1A-1. AAR TOOL 32351 CAL DUE DATTE 12/10/22.;[02] VERIFIED MATERIAL AS 2024 T3 .071' A-TAG A122583 IAW AMM 25-52-01-201-801.;[03] VERIFIED STEPS 1 AND 2;[04] STARTED FABRICATION OF PANEL IAW AMM 25-52-01201-801.;[05] FINISHED FABRICATION OF NEW PNL 140CF IAW AMM 25-52-01-201-801;[06] VERIFIED STEPS 4 AND 5;[07] OK TO TREAT AND PRIME;[08] TREATED IAW AMM 51-21-41-370-802 AND PRIMED IAW AMM 51-21-73-370-804;[09] JOB COMPLETE; AUDIT C/W
AFT CARGO FLOOR BOARD 140 AF CORRODED ALONG EDGE A225-003 / [01] EVALUATED PANEL AND FOUND PUNCTURE AND CORROSION EXCEEDING 20'. THIS IS OUT OF LIMITS IAW SRM 53-00-53-1A.;[02] VERIFIED ITEM 1<BR>VERIFIED MATERIAL AS 2024 T3 .071' IAW AMM 25-52-01-201-801;[03] FABRICATED NEW FLOOR PANEL 140AF IAW AMM 25-52-01-201.;[04] VERIFIED STEP 3;[05] OK GIVEN TO TREAT AND PRIME;[06] APPLIED ALODINE AND PRIMED BACK SIDE OF PANEL IAW AMM 25-52-01-201. JOB IS COMPLETE.;[07] JOB COMPLETE; AUDIT C/W
LEFT WING OUTBD SUPPORT CLIP FROM DEFLECTION CONTROL RIB TO AFT WEB BRACKET CRACKED. ; / [01] REMOVED AND REPLACED CLIP REF SRM 51-40-02
EXTERNAL AIR DOOR HINGE BROKEN ( MX NOTE ) DOOR SPEED TAPE CLOSED / R&R'D THE FWD FAIRING ACCESS DOOR; REF AMM 52-49-01. REF LOG PAGE 0458850
HFEC CRACK INDICATION ON DAMAGE BLENDED AREA AT BS 787+11' STR 3R. (ORIGINAL RIGHT UP NR # D352660) / ACCOMPLISHED PERMANENT REPAIR PER EA# 21-153-00223
FWD MEGA PHONE NOT WORKING AND HANDLE IS LOOSE. REPLACED MEGA PHONE PER SIP.
DAMAGE FOUND DURING WALK AROUND ON #1 ENG BLADE # 16. DENT/GOUGE LOCATED 2 DIFFERENT LOCATIONS ON LEADING EDGE BLADE SEQ. REPLACEMENT / REMOVED AND REPLACED #1 ENG BLADE #16 IAW MT 772-21-19 AND AMM 72-21-02 A/C OK FOR SERVICE ACCOMPLISHED MT 772-21-22P/N OFF 340-001-036-0 P/N ON 340-001-038-0S/N OFF DM123297-4 S/N ON DC611134
RT FORWARD CABIN PHOTO LUMINESCENT LIGHT INOP AT ROW 1. R&R STRIP PER AMM.