N73283

Part: STRINGER — CRACKED (WING) · airframe 66,963 hrs · 24,978 cycles

INSIDE FUEL PANEL 632RB OPENING STRINGER U9 HAS CRACK IN END OF STRINGER AND APPEARS TO END AT LAST FASTENER REQUESTING ENGINEERING ASSISTANCE. SUPPORT TASK NSA EMX N/R 00074. ESFR COMPLETED REPAIRED 49 STRINGER INSIDE PANEL 632RB IAW UAL ECRA 5720-03572 REV A AND UAL ECRA 5720-03572 REV ORIGINAL AND UAL AVO # INT-101 32025-0283-1 AND -1A.

Part: FITTING — CRACKED (ZONE 200) · airframe 66,962 hrs · 24,977 cycles

SHEAR FITTING AT BS 540 AND LBL 32.40 IS CRACKED. REMOVED AND REPLACED SHEAR FITTING AT BS 540 AND LBL 32.40 IAW B737-800 SRM 51-40-02 AND BAC DWG 111A2000 REV ORIGINAL FOR WORK ACCOMPLISHED SEE NSA EMX N/R 00080 AND HANGER N/R 6482033.

Part: FITTING — CRACKED (STA540) · airframe 66,962 hrs · 24,977 cycles

SHEAR FITTING AT BS 540, LBL 6.14 CRACKED. REMOVED AND REPLACED SHEAR FITING AT BS 540, LBL 6.14 IAW SRM 51-40-02 & DWG 111A2000 REV ORIG.

Part: FITTING — CRACKED (STA540) · airframe 66,963 hrs · 24,978 cycles

SHEAR FITTING AT STATION 540 AND RBL 15.04 IS CRACKED. REMOVED AND REPLACED SHEAR FITTING AT STATION 540 AND RBL 15.04 IAW B737-800 SRM 51-40-02 AND BAC DWG 111A2000 REV ORIGINAL

Part: FITTING — CRACKED (ZONE 200) · airframe 66,962 hrs · 24,977 cycles

SHEAR FITTING AT BS 540 AND LBL 15.04 IS CRACKED. REMOVED AND REPLACED SHEAR FITTING AT STATION 540 AND LBL 15.04 IAW SRM 51-40-02 & DWG 111A2000 REV ORIG.

Part: FITTING — CRACKED (ZONE 200) · airframe 66,962 hrs · 24,977 cycles

SHEAR FITTING AT STATION 540 AND RBL 32.40 IS CRACKED. REMOVED AND REPLACED SHEAR FITTING AT STATION 540 AND RBL 32.40 IAW B737-800 SRM 51-40-02 AND BAC DWG 111A2000 REV ORIGINAL

Part: FITTING — CRACKED (ZONE 200) · airframe 66,962 hrs · 24,977 cycles

SHEAR FITTING AT STATION 540 AND RBL 6.14 IS CRACKED. REMOVED AND REPLACED SHEAR FITTING AT BS 540, RBL 6.14 IAW SRM 51-40-02 AND BAC DWG 111A2000 REV ORIG.

Part: CONTROL MODULE — FAULTED (ZONE 200) · airframe 66,962 hrs · 24,977 cycles

APU FAULT/APU DET INOP FOUND DETECTION MODULE FAULTED, REPLACED ENGINE AND APU FIRE CONTROL MODULE REF AMM 26-10-01, GRD OPS TEST REF AMM TASK 26-11-00-710-801 AND 26-15-00-710-801 NO FAULTS NOTED

Part: WARNING MESSAGE — FALSE ACTIVATION · airframe 66,955 hrs · 24,974 cycles

BELOW 80 KNOT REJECT DUE TO OVHT/DET ILLUMINATED ON INITIAL TAKEOFF POWER REG AMM TASK P5-51-07-210-801 HIGH ENERGY STOP NO DEFECTS NOTED, AIRCRAFT OK TO CONTINUE

Part: INDICATION SYS — MALFUNCTIONED (ZONE 700) · airframe 66,776 hrs · 24,879 cycles

NOSE GEAR RED LITE ON CONTINUOUSY UPDATED MAA CODE FIX USING VENDOR MAA SCREEN PLEASE CONTACT TOMC BEFORE COMMENCING ANY WORK. ON THE GROUND ALL THREE GEAR INDICATE DOWN AND LOCKED. CHECKED PSEU FOR FAULTS, NO FAULTS. CREW INDICATED TO ME THE GEAR WAS RETRACED AND THE DOORS WERE CLOSED. PERFORMED T-SHOOTING IN REF. FIM 32-30 TASK 811 TO THE STEP D.(8)3). OPERATE NLG MULTIPLE TIMES RED NOSE GEAR LIGHT GOES OUT, AND THE GREEN NOSE GEAR LIGHT IS NOT ON! SIGNED OFF IN REFERENCE TO. STEP D.(8)(B).

Part: LIGHT — INOPERATIVE (ZONE 200) · airframe 66,579 hrs · 24,787 cycles

TEST FLIGHT DISCREPANCY - EMERGENCY EXIT DOOR LIGHT AT 21 LEFT FLICKERS (REF AAR N/R 9984029) REMOVED AND REPLACED EMERGENCY EXIT DOOR LIGHT AT 21 LEFT AS PER AMM 33-51-01-960-801, TEST FOUND NORMAL.

Part: WEB — CORRODED (ZONE 100) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

FWD CARGO THRESHOLD WEB HAS SPOTS OF CORROSION. REMOVED AND REPLACED THRESHOLD WEB AT FWD CARGO COMPT PER REF SRM 51-40-02-0G-0 AND DWG# 143A8120.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

AREA AFT OF FORWARD COMPARTMENT CORROSION FOUND AT STRINGER 27R B.S. 540. APPLIED CORROSION INHIBITING COMPOUND, TO THE INTERNAL SURFACES OF THE REPAIR AREA PER AMM 51-21-91-620-802. ACCOMPLISHED REPAIR AT STRINGER 27R, BS 500I TO 540 IAW EC/RA 5330-07576. INSTALLED REPLACEMENT STRINGER 27RT & REPAIR SPLICE AT BS 540 TO STA 500I+10 & FRAME SHEAR TIE PER SRM 51-40-02-0G -0 , SRM 53-00-03-2R-1 AND EC/RA 5330-07576.

Part: SKIN — DAMAGED (ZONE 100) · airframe 66,576 hrs · 24,786 cycles

LIGHTNING STRIKE STATIC DISCHARGE NOTED AT SKIN STA 1040 +16" AND 0.5" ABOVE STR 25R, LOWER EXTERNAL FUSELAGE SECTION 48 DOT 223-030. REF AAR N/R 9983881 ACCOMPLISHED REPAIR AT LIGHTNING STRIKE DAMAGE FUSELAGE SKIN BETWEEN STA 1040 - 1064 AT STRINGER 25R PER EC/RA: 5380-01426. WORK ACCOMPLISHED BY V891530 AAR INSP-223 ESFR IS COMPLIED WITH. WORKED WAS PERFORMED ON AAR NR 9983881. THE RII WAS COMPLIED WITH BY AAR INSPECTOR V898247. ACCOMPLISHED REPAIR AT LIGHTNING STRIKE DAMAGE FUSELAGE SKIN BETWEEN STA 1040 - 1064 AT STRINGER 25R PER EC/RA: 5380-01426.

Part: RIB — CRACKED (ZONE 300) · airframe 66,576 hrs · 24,786 cycles

RIGHT HORZONTAL STAB LEADING EDGE RIB NR 5 CRACKED. REMOVED AND REPLACED RIB NR 5 AT RT HORIZONTAL STAB LEADING EDGE IAW SRM 51-40-02-0G AND DWG 186A1305.

Part: SUPPORT ANGLE — CRACKED (WNG-BDY FAIRING) · airframe 66,576 hrs · 24,786 cycles

LEFT FWD FRONT SPAR WING TO BODY FAIRING AT FIXED L/E I/B SUPPORT ANGLE CRACKED. R & R SUPPORT ANGLE AT LT WING FRONT SPAR WING TO BODY FAIRING AT FIXED L/E I/B SIDE IAW SRM 51-40-02-0G-0.

Part: SKIN — CRACKED (RT NR 7 SLAT) · airframe 66,576 hrs · 24,786 cycles

RIGHT WING NR 7 SLAT LOWER L/E SKIN LOOSE FASTENERS 4EA AT ACTUATOR AT ACTUATOR ATTACHED RIB. ACCOMPLISHED DOUBLER REPAIR ON RT NR 7 SLAT L/E SKIN IAW SRM 57-42-01-2R-8 ALTERNATIVE 3.

Part: SKIN — CRACKED (NR 2 SLAT) · airframe 66,576 hrs · 24,786 cycles

LEFT WING NR 2 SLAT ASSY LOWER L/E SKIN HAS 4 LOOSE FASTENERS AT ACTUATOR ATTACHED RIB. COMPLETED LT WING NR 2 SLAT ASSY LOWER L/E SKIN REPAIR SRM 57-42-2R-8 REPAIR,SRM 51-20-10,SRM 51-40-08-0G-0, SRM 51-40-02-0G-0 AND SOPM 20-50-19. ACCOMPLISHED DOUBLER REPAIR AT LEFT WING NR 2 SLAT ASSY LOWER L/E SKIN IAW SRM 57-42-2R-8 REPAIR 8 FIG 202, SRM 57-42-2R-8 ALTRNATIVE 3, SRM 57-42-2R-8 FIG,202 ALTERNATIVE 1 SHEET 2 , SRM 51-40-02-0G-0 AND SOPM 20-50-19.

Part: INTERCOSTAL — CRACKED (ZONE 100) · airframe 66,576 hrs · 24,786 cycles

AREA AFT OF FORWARD CARGO COMPARTMENT INTERCOASTAL IS BENT AND REPLACE CRACKED B.S. 500L TO 520 STRINGER 28L. REF AAR N/R 9983846 REMOVED AND INSTALLED NEW INTERCOASTAL BETWEEN STA 500L AND STA S20 ABOVE STRINGER 28L PER B737-800 SRM 51-40-02-0G-0 AND BOEING DRAWING 143A7902. REMOVED AND INSTALLED NEW INTERCOSTAL BETWEEN STA 500L AND STA S20 ABOVE STRINGER 28L PER SRM 51-40-02-0G-0 AND BOEING DRAWING 143A7902.

Part: SKIN — WORN (ZONE 600 LE) · airframe 66,576 hrs · 24,786 cycles

RIGHT WING FIXED L/E PANEL 611A WORN. REMOVED AND INSTALLED NEW PANEL 611A IAW SRM 51-40-02-0G-0 AND DWG 116A4008.

Part: DOOR — CRACKED (ZONE 800) · airframe 66,576 hrs · 24,786 cycles

LEFT MAIN LANDING GEAR,MID DOOR FWD LOWER CORNER APPEARS TO BE CRACKED. ACCOMPLISHED REPAIR AT L/H MLG MID DOOR IAW SRM 52-80-02-3R-3 REPAIR 3.

Part: SKIN — DAMAGED (ZONE 800) · airframe 66,576 hrs · 24,786 cycles

REMOVE AND REPLACE FWD CARGO DOOR EXTERIOR SKIN AS REF AAR N/R 9983191 REMOVED AND REPLACE FORWARD CARGO DOOR SKIN REF DWG 143A6110, SRM 52-30-01-2R-3 AND SRM 51-40-02-0G-0. REMOVED AND REPLACED FWD CARGO DOOR EXTERNAL SKIN PER SRM 51-40-02-0G-0 SRM 52-30-01-2R-3 AND DWG#143A6110.

Part: SKIN — DENTED (ZONE 800) · airframe 66,576 hrs · 24,786 cycles

REMOVE AND REPLACE AFT CARGO DOOR EXTERNAL SKIN. REMOVED AND REPLACED AFT CARGO EXTERAL DOOR SKIN IAW SRM 52-30-01-2R-3 AND 51-40-02-0G-0.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

FOUND CORROSION AT MAIN CABIN LT OTBD SEAT TRACK UPPER COWL LBL 45.5 BS 887 - 907. REMOVED AND REPLACED SEAT TRACK AT LBL 45.50 FROM STA 887 TO STA 927 PER SRM 51-40-02-0G-0 AND DWG 10N00633.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

FOUND CORROSION AT MAIN CABIN LH I/B SEAT TRACK 727A. ACCOMPLISHED I/B SEAT TRACK REPAIR LBL 24.75" FROM STA 727+9 TO STA 727B IN REF SRM 53-00-52-2R-2, AND BOEING DRAWING 144A5300.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

FOUND CORR. AT FASTENERS HEADS MAIN CABIN L/H O/B SEAT TRACK UPPER CROWN WEB LBL 45.5 STA 827 TO 847 MKD DOT 119 REF AAR N/R 9983579 REMOVED EWIS PROTECTION AT WORKING AREA PER AMM 20-60-07-913-801. WORK ACCOMPLISHED BY V903719 REMOVED CORROSION AT SEAT TRACK STA 827 TO STA 847 FOUND OUT OF LIMITS. REMOVED SEAT TRACK AND FABRICATED NEW SEAT TRACK INSTALLED NEW SEAT TRACK AND REPAIR PARTS IN REF TO SRM 51-40-02 AND SRM 53-00-52 AND DWG 146A5300. REMOVED CORROSION AT SEAT TRACK STA 827 TO STA 847 FOUND OF LIMITS.REMOVED SEAT TRACK AND FABRICATED NEW SEAT TRACK INSTALLED NEW SEAT TRACK AND REPAIR PART IN REF TO SRM 51-40-02 ,SRM 53-00-52 AND DWG 146A5300.

Part: BAFFLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

AFT CARGO BAFFLE UNDER RH Z-CHANNEL BETWEEN STA 747-767 AT RBL 21 FOUND CRACKED. REMOVED AND REPLACED BAFFLE UNDER RH Z-CHANNEL BETWEEN STA 747-767 AT RBL 21 PER SRM 51-40-02-0G-0 AND DWG 146A7505.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

FOUND CORROSION AT MAIN CABIN LT OTBD SEAT TRACK UPPER CROWN LBL 45.5, BS 767. REMOVED CORROSION AT SEAT TRACK. FABRICATED NEW SEAT TRACK & INSTALLED WITH REPAIR PARTS IAW SRM 51-40-02, SRM 53-00-52 & DWG # 146A5300.

Part: ATTACH ANGLE — CRACKED (ZONE 100) · airframe 66,576 hrs · 24,786 cycles

RIGHT LOWER REAR SPAR VAPOR BARRIER UPPER ATTACH ANGLE CRACKED AT BS 663.5 RBL 7. ACCOMPLISHED REPAIR OF RT VAPOR BARRIER UPPER ATTACH ANGLE & SPLICE ANGLE AT BS 663.5 RBL 5 TO RBL 25 IAW SRM 57-10-10-2R-5.

Part: DOOR FRAME — CORRODED (ZONE 200) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

FOUND TWO AREA OF INTER-GRANULAR CORROSION, NEXT TOO THE R1 DOOR(INNER-CHORD) REF AAR N/R 9983208 COMPLETED INSTALLATION OF FASTENERS AT INNER CHORD OF R-1 DOOR REF SRM 51-40-02-0G-0, DWG 141A8310. WORK ACCOMPLISHED BY V935074 AND INS-223. ESFR CREATED AND SUBMITTED COMPLETED INSTALLATION OF FASTENERS AT INNER CHORD OF R-1 DOOR REF SRM 51-40-02-0G-0, DWG 141A8310. WORK ACCOMPLISHED BY V935074 AND INS-223. ESFR CREATED 1296 INSP C/W

Part: ATTACH ANGLE — CRACKED (ZONE 100) · airframe 66,576 hrs · 24,786 cycles

LEFT LOWER FUSE REAR SPAR VAPOR BARRIER UPPER ATTACH ANGLE CRACKED AT BS 663.5 LBL 7. ACCOMPLISHED REPAIR OF L/H VAPOR BARRIER UPPER ATTACHED REPLACEMENT ANGLE AND SPLICE ANGLE AT STA 663.5 LBL 5 TO LBL 25 PER SRM 57-10-10-2R-5.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

STA 967+5/LBL 15... ELONGATED HOLES AND CORROSION. REMOVED AND REPLACED FLOOR SUPPORT BETWEEN STA 967 AND 986.35LBL 15 INCHES PER SRM 51-40-02-0G-0 AND DWG 140A9870 WORK ACCOMPLISHED BY V935074 AND INS 223

Part: FLOORBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 66,576 hrs · 24,786 cycles

CORROSION AROUND FASTENER HOLE/BEAM UPPER SURFACE AT STA328 RBL 40.

Part: FLOORBEAM — DAMAGED (ZONE 200) · airframe 66,576 hrs · 24,786 cycles

STA 947/LBL 4'-11' STA 947/RBL 5' ELONGATED HOLES AND CORROSION. ACCOMPLISHED REPAIR AT STA 947.50 FROM LBL 4 - LBL 11 IAW EC/RA 5370-01181, B737/800 SRM 53-00-51-2R-1.

Part: FLOOR SUPPORT — CRACKED (ZONE 200) · airframe 66,576 hrs · 24,786 cycles

FOUND FLOOR SUPPORT INTERCOSTAL T CHORD CRACKED AT LBL 14 BETWEEN STA 380 AND 400 REF AAR N/R 9983624 ESFR INFORMATION ENTERED.

Part: FLOOR SUPPORT — CRACKED (ZONE 200) · airframe 66,576 hrs · 24,786 cycles

FOUND FLOOR SUPPORT INTERCOSTAL T CHORD CRACKED AT BL 0 BETWEEN STA 380 AND 400. REMOVED AND REPLACED FLOOR SUPPORT INTERCOASTAL T CHORD AT BL 0 BETWEEN STA 380 AND STA 400. IN REF TO SRM 51-40-02.

Part: FLOOR SUPPORT — CRACKED (ZONE 200) · airframe 66,576 hrs · 24,786 cycles

FOUND FLOOR SUPPORT INTERCOSTSL T CHORD CRACKED AT RBL 9 BETWEEN STA 380 AND 400. REMOVED AND REPLACED FLOOR SUPPORT INTERCOASTAL CHORD AT RBL 9 BETWEEN STA 380 AND STA 400.IN REF TO SRM 51-40-02.

Part: LAMP — INOPERATIVE (ZONE 200) · airframe 65,618 hrs · 24,353 cycles

"EMERGENCY LIGHT ARMED" ANNUNCIATOR LIGHT LAMP INOP REPLACED "EMERGENCY LIGHT ARMED" ANNUNCIATOR LIGHT LAMP WITH REF TO AMM: 33-11-00/201 OPS CHK GOOD.

Part: HANDLE — OUT OF ADJUST (ZONE 800) · airframe 64,265 hrs · 23,693 cycles

AFT ENTRY DOOR LIGHT ON TAKEOFF DOOR HANDLE NOT SECURED, DEBREFED CREW, L2 DOOR LIGHT WAS ON. CALLED AFT FLT ATTENDENT & DOOR HANDLE WAS NOT IN CLOSED POSITION. FLT ATTENDENT PUT HANDLE DOWN & LIGHT EXTINGUISHED. REMOVED L2 DOOR SLIDE, SAFTIED GIRT BAR & INSTALLED INFLATION CYLINDER DEACTIVATION PIN, REMOVED L2 DOOR LINING, ADJUSTED UPPER & LOWER GATE CONTROL RODS &HORIZONTAL CONTROL RODS AS DOOR FLUSHNESS WAS NOT IN SPEC & DOOR WAS NOT LATCHING CLOSED NORMALLY. NO SUCCESS IN ADJUSTMENTS, DOOR HANDLE EITHER POPPED OPEN ON ITS OWN OR WAS EXTREMELY DIFFICULT TO UNLATCH, BOTH CONDITIONS MADE SKIN FLUSHNESS DISCREPANCY WORSE OR THE SAME. WORK DONE REF AMM 52-13-00-820-801 CORRECT REFERENCE FOR WORK PREFORMED SHOLUD BE AMM 52-13-00-820-802. ADJUSTED AFT ENTERY DOOR,ADJUSTED UPPER LATCH TORQUE TUBE ROD & BOTH UPPER AND LOWER GATE RODS REF AMM 52-13-00-820-802 FROM STEP F.(1) TO & INCLUDING STEP F (F) 5) B). VERIFIED ADJUSTMENT OF AFT ENTERY DOOR, UPPER LATCH TORQUE TUBE ROD & BOTH UPPER AND LOWER GATE RODS IAW AMM 52-13-00-820-802 FROM STEP F.(1) TO & INCLUDING STEP F (F) 5) B). ADJUSTMENTS ARE WITH IN LIMITS. OK TO CONTINUE. COMPLETED AFT ENTRY DOOR (SOFT UNVERIFIED COMPLETION OF AFT ENTRY DOOR (SOFT UNLATCHING) PER AMM 52-13-00-820-802 STEPS F.(5) UP TO & INCLUDING F.(8). ALL STEPS COMPLIED WITH. REF. GMM 09-25-05.OPS CHECKS GOOD.

Part: SENSOR — FAULTED (LE FLAP) · airframe 63,837 hrs · 23,496 cycles

LE FLAPS TRANSIT LIGHT ON. REPLACED LE FLAP 4 RETRACK SENSOR S174. REF AMM 27--88-11-000-801., SYS OPS CHECKS OK.

Part: WIRE — SHORTED (CONNECTOR) · airframe 61,898 hrs · 22,579 cycles

ANTISKID INOP PERFORMED AACU BITE FIM 32-42 TASK 801.ON INITIAL BIT FOUND MESSAGE ADIRU L AND XDCR1.THIS SENDS YOU TO FIM 32-42 TASK 824 AND 32-42 TASK 806.PERFORMED AUTO SPEED BRAKE/ANTISKID INTERFACE TEST 27-62 TASK 801.BLUE LITE FOR DS2 L OUTBOARD DID NOT COME REMOVED AND REPLACED ANTISKID/AUTOBRAKE CONTROL UNIT IAW AMM 32-42-21-000-801, OPS CK FAIL, FURTHER T/S REQUIRE, FOLLOWED FIM TASK 32-42- TASK 806. RETURNED A/C TO NORMAL. E/E COMP DOOR SECURED CLOSED. FOLLOWED FIM TASK 32-42 TASK 806 UP TO AND INCLUDED STEP F ITEM 2(D), T/S IAW FIM 32-42 TASK 806 FOUND SHORT ON WIRE W7230-2211R-20 FROM CONNECTOR D46028P TO D46004J (PIN 1), NEEDS WIRE REPLACEMENT. WDM 32-41-11. R & R WIRE W7230-2211R/B-20 FROM CONNECTOR D46028P TO CONNECTOR D46004J, IAW WDM 32-41-11-1, COMPLETED INSTALATION OF WIRE W7230-2211R/B-20 REF WDM 32-41-11- 1. ALSO REPLACED CONNECTOR D46029P REF SWPM 20-61-11. OPS CHECK/ BITE GOOD REF FIM 32-42 TASK 806 STEP F-(2)D.

Part: TIRE — FAILED (NR 2 MLG) · airframe 61,251 hrs · 22,295 cycles

NR 2 MAIN TIRE BLEW ON TAKEOFF. REPLACED #2 MLG TIRE AND WHEEL ASSEMBLY PER AMM 32-45-11-000-801 AND 32-45-11-400-801. WHEEL, TIRE, AS OFF 60-3249-9-0002 1445 ON 60-3249-9-0002 4197. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1708729 SN OFF 1445. NEEDS CONDITIONAL INSPECTION FOR BURST #2 TIRE. PERFORMED TIRE TREAD LOSS OR TIRE BURST CONDITIONAL INSPECTION REF AMM 05-51-54-210-801. ALL DAMAGE NOTED. SHREDDING THE TIRE AND DAMAGING THE AFT FLAP. TIRE DEBRIS AND FLAP DEBRIS WAS RECOVERED FROM THE RUNWAY IN MFR. PANEL 551BB HAS DENT WITH DELAMINATION ON LWR SURFACE OF LH WING JUST FWD OF MLG DOOR CUTOUT. REMOVED PANEL 551BB TO FOM. INSTALLED NEW PANEL 551BB REQUIRES PAINT PARTS USED: 00-0593-3-1524,QTY :1 58-5351-3-0050,QTY :1. PAINTED PANEL. AFT ATTACH BEAM FOR LOWER LH WING PANEL 551FB IS BENT. INSTALLED PANEL 551FB REF AMM 57-50-02-400-801. STILL NEED TRANSFER RODS FROM OLD PANEL TO NEW PANEL. INSTALLED PANEL 551FB REF AMM 57-50-02-400-801. LH WING LOWER PANEL 551FB JUST ART OF LH GEAR DAMAGED. REF IPC 57-50-00-26 AND IPC 57-50-00-38, ITEM 580, 29-5750-3-0057. STARTED TO INSTALL PANEL 551FB REF AMM 57-50-02-400-801. WHILE TRANSFERRING HOLE ON PANEL MISALIGNED THE HOLE. WAITING FOR ENGINEERING. INSTALLED NEW PANEL 551 FB REF AMM 57-50-02-400-801 REQUIRES FLAP RIGGING, AND A GEAR SWING TO CLEAR ITEM. LH INBD TRAILING EDGE FLAP HAS DENT ON LWR SKIN OF FWD SEGMENT OF FLAP. EVALUATED DENT PER SRM 57-53-01-1A-1. DENT IS 4.25"X 4.58X0.032 DEPTH. A/Y= 132. DENT LOCATION 42.5" FROM INBD EDGE AND 4" FROM AFT EDGE PANEL # 6 ( 0.125 2024T3) REF SRM 57-53-01-1A-1 IDENT. DENT IS SMOOTH AND CREASE FREE, NO CRACKS NOTED. REMOVED INBD TRAILING EDGE FLAP AND AFT FLAP AS ONE REMOVAL AMM 27-51-11-000-801. ADD EMP:037425. REMOVED INBD AND OTBD CARRIAGE ASSEMBLIES ON LH INBD FLAP SO THAT CARRIAGES CAN BE INSTALLED ON NEW FLAP, REF AMM 27-51-13-000-801 FOR OTBD CARRIAGE AND AMM 27-51-13-000-802 FOR INBD CARRIAGE. ADD EMP:U009243, U106536. VERIFIED FLAP PN AND CLEARANCE TO INSTALL. ACP RII INSP OF INITIAL INSTALL THRU SUBTASK 27-51-11-420-002. INSTALLED LEFT HAND INBOARD FLAP UP UNTIL SUBTASK 27-51-11-080-001. PARTS INFO ONLY. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1602178 SN OFF 1190 COMPLETED UP TO SUBTASK 27-51-11-420-002 2(B). PART # UPLOADED. FLAP, B737NG, L OFF 29-5753-9-0011 1190 ON 0000 FLAP, B737NG, L OFF 29-5753-9-0011 1190 ON 29-5753-9-0011 1129 COMPLETED I /B FLAP INSTALL UPTO SUB TASK 27-51-11-860-013. CONTINUED INBOARD TRAILING EDGE FLAP INSTALL REF AMM 27-51-11-400-801. COMPLETED SUBTASK 27-51-11-210-005 AND SUBTASK 27-51-11-820-015. COMPLETED UP TO SUBTASK 27-51-11-420-006. ADD EMP:U398024 ACP RII INSP FROM SUBTASK 27-51-11-420-002 2(B) THRU SUBTASK 27-51-11-820-015 IAW AMM 27-51-11-400-801. PARA. H (2) THRU H(11). INSPECTED PER GMM 09-25-05. SEE LOG PAGE 5180481 FOR FLAP ADJUSTMENT TASK 27-51-11-820-801. INSTALLED LEFT HAND I/B FLAP ASSY REF AMM 27-51-11-400-801, RIGGING OF THE FLAP WILL BE ACCOMPLISHED ON LOG 5180481. LH INBD TRAILING EDGE AFT FLAP SEGMENT HAS MULTIPLE DENTS ON LWR SURFACE AND RAISED AREA ON UPPER SKIN. REMOVED L/H INBOARD TRAILING EDGE AFT FLAP. REF AMM 27-51-11-000-801 ADD EMP:U408174 PARTS INFO ONLY. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1403328 SN OFF 0507 INSPECTION REQUIRED TO INSTALL.INSPECTION REQUIRED FOR INSTALL. CLEARANCE TO INSTALL GRANTED BY QC221916. VERIFIED CORRECT PN# AND ATTACH FITTINGS OK PER GMM. INSTALLED LEFT HAND I/B AFT FLAP REF AMM 27-51-12-400-801 UPTO STEP ( G ) 2. PUSH ROD BUSHING ON ORDER. FLAP, B737NG, L OFF 60-5753-9-0003 0507 ON 60-5753-9-0003 2611 FLAP, B737NG, L OFF 60-5753-9-0003 0507 ON 0000 VERIFIED LH INBOARD AFT FLAP ADJUSTMENTS, FINAL SAFETY AND SECURITY OK PER AMM 27-51-12-400-801 AND RII 09-25-05 REQUIRE INSPECTION TO VERIFY ADJUSTMENTS AND CLEARANCE TO INSTALL OUTBOARD SUPPORT. ADD EMP:U398024.COMPLETED PANEL INSTALL PER AMM 27-51-12-400-801 UP TO STEP I RETURN PLANE TO NORMAL CONDITION. 1 ROD SAFETY KEY MISSING ON INSTALL AND IS REFERED TO IN LOG PAGE 5168564. LH SPOILER CABLE HAS BENT ROD END AT APPROX LH W/S 156. VERIFIED NEW CABLE PN AND CLEARANCE TO INSTALL. ACP RII INSP OF NEW CABLE INSTALL PER AMM 20-10-91-400-801. DISTURBED CABLE WSA1, AND NEW CABLE WSA2, NEED ADJUSTMENT AND SAFETY PER AMM 27-61-00-820-801. REMOVED AND REPLACED LH SPOILER CONTROL CABLE WSA2-L2 REFERENCE "FIGURE 207. SPOILER CONTROL CABLES SHEET 1 TASK 27-09-14-860-801" IN ACCORDANCE WITH "AMM TASK 20-10-91-400-801 THROUGH STEP 3. CONTROL CABLE INSTALLATION / E. PREFABRICATED ADD EMP:U398795 TURNBUCKLES FOR CABLES WSA2 AND WSA1 REQUIRE IGGING/ADJUSTMENT PER "AMM TASK 20-10-91-400-801 CONTROL CABLES INSTALLATION." CABLES WSA2 AND WSA1 SET TO PRE-REMOVAL AND PRE-LOOSEN TENSIONS, WSA2 @ 65LBS AND WSA1 @ 40LBS. ADD EMP:U398795 CABLE INSTALLATION / (D) KEEP LIGHT TENSION ON THE NEW CABLE. TURNBUCKLE FOR WSA1 CABLE LOOSENED TO FACILITATE MAINTENANCE FOR CABLE REPLACEMENT. PERFORMED SPOILER CONTROL CABLE ADJUSMENT REF AMM 27-61-00-820-801 UP TO STEPS H.(4). ADD EMP:U104419, U384621,U369162 VERIFIED ADJUSTMENT, SAFETY AND TURNBUCKLE LOCKSTITCH OF SPOILER CABLES WSA1 AND WSA2 PER AMM 27-61-00-820-801 AND RII 09-25-05 COMPLETED SPOLIER CABLE RIG PER AMM 27-61-00-820-801 FROM 3H(4) THRU 3H 10. ADD EMP:U112702 VERIFIED CABLE RIG AND SPOILER CONTROL OPERATIONAL CHECK OK PER AMM 27-61-00-820-801 COMPLETED CABLE RIG AND SPOILER CONTROL OPS TEST PER AMM 27-61-00-820-801 ,OPS TEST GOOD. #6 GROUND SPOILER HAS DAMAGE AND DELAMINTION ON INBD LWR SURFACE. REMOVED DAMAGED #6 GROUND SPOILER. AMM 27-62-12-000-801. VERIFIED CORRECT SPOILER PN# AND VERIFIED ATTACH FITTINGS OK FOR INSTALL PER GMM RII 09-25-05. NEED OK TO INSTALL #6 GROUND SPOILER. NEED OK TO INSTALL #6 GROUND SPOILER. PART INFO ONLY ROTABLE PARTS CHANGE WAS INDICATED - TT # 1145421 SN OFF 0130 PARTS INFO ONLY.ROTABLE PARTS CHANGE WAS INDICATED - TT # 1445421 SN OFF 0130 COMPLETED INSTALL OF THE # 6 GROUND SPOILER REF AMM 27-62-12-400-801 UPTO STEP H 10 (4). PARTS USED: 29-5742-9-0001,QTY :1 SPOILER, B737, OFF 29-5742-9-0001 0130 ON 29-5742-9-0001 0952 SPOILER, B737, OFF 29-5742-9-0001 0130 ON 0000 ACP RII INSP IAW AMM 27-62-12-400-801 PARA. F1 THRU STEP H 10(4) SAFETY & SECUIRTY . GMM 09-25-05. ACP RII INSPECTION FOR #6 GND SPOILER ADJ IAW AMM 27-62-00-820-804 AND VERIFIED RESULTS AND VISUAL OPERATION OF FUNCTIONAL CK / TEST IAW AMM 27-62-12-000-802 . RESULTS WITHIN ALLOWABLE LIMITS. INSPECTED IAW GMM 09-25-05. COMPLETED AMM 27-62-12-400-801 STEPS H(5) THRU H(12). IN FULL ADJUSTED #6 GROUND SPOILER PER AMM 27-62-00-820-804 AND ACCOMPLISHED INBOARD GROUND SPOILER FUNCTIONAL TEST PER AMM 27-62-12-000-802. FOUND WITHIN ALLOWABLE LIMITS. BODY PANEL 194DL HAS TWO AREAS OF DELAMINATION. JUST AFT OF LH WHEEL WELL CUTOUT. REMOVED PANEL 194 DL REF AMM 53-51-21 INSTALLED PANEL 194DL REF AMM 53-51-21. REQUIRES AERODYNAMIC SEALANT WHEN ALL OTHER PANELS ARE INSTALLED. 194DL IS INSTALLED AND DOES NOT REQUIRE AERODYNAMIC SEALANT. HYDRAULIC BREAKLINE STABLIZING BRACKET BENT. REPLACED HYDRAULIC BREAKLINE STABIZING BRACKET. LEFT WHEEL WELL FORWARD SUPPORT BEAM BRACKET CRACKED. ADDED PARTS IPC 57-50-00-34 ITEM 25. PN 115A5582-1 REMOVED CRACKED BRACKET(CLIP), CLECOED NEW CLIP IN PLACE, NEED TO UP SIZE HOLES, NEW HARDWEAR ON ORDER, REF IPC 57-50-00-34 ITEM 25, PLZ RETURN SHEETMETAL KIT TO TOOLING. PARTS USED: 58-5750-3-0113, QTY :1 DRILLED UP NEW BRACKET AND INSTALLED REF SRM 51-50-02. PARTS USED: 00-0596-3-0294, QTY :1. DURING CONDITIONAL INSPECTION FOUND BRAKELINE STABILIZING BRACKET BENT. ADDED PARTS IPC 57-50-00-50 ITEM 10. 29-5750-3-0059. REPLACED BRACKET ASSY. FOUND 3 AILERON FAIRLEADS BROKEN. PARTS INFO. REF IPC 27-11-00-17. FAIRLEAD - 251A1381-38, FAIRLEAD- 251A1381-21, FAIRLEAD - 251A1381-13 REPLACED ONE FAIRLEAD 4 INCHES IB OF LH MLG FWD TRUNION, SEE PHOTO. REPLACED -13 ITEM 145 REF IPC 27-11-00-17. STARTED REMOVING -38, ITEM 105. INSTALLED FAIRLEAD 251A1381-13 REF IPC 27-11-00-17. ALL FAIRLEADS HAVE BEEN REPLACED AT THIS TIME. FOUND HYDRAULIC RETURN LINE BRACKET AT WING ROOT DAMAGED. SEE PICTURES FOR MORE INFP ADDED PARTS 29-2911-3-0097. REMOVED AND REPLACED DAMAGED HYDRAULIC RETURN LINE BRACKET AT WING ROOT. LEFT WHEEL WELL FORWARD SUPPORT BEAM BRACKET CRACKED. ADDED PARTS IPC 57-50-00-34 ITEM 25. PN 115A5582-1 REMOVED CRACKED BRACKET(CLIP), CLECOED NEW CLIP IN PLACE, NEED TO UP SIZE HOLES, NEW HARDWEAR ON ORDER, REF IPC 57-50-00-34 ITEM 25, PLZ RETURN SHEETMETAL KIT TO TOOLING. PARTS USED: 58-5750-3-0113, QTY :1. DRILLED UP NEW BRACKET AND INSTALLED REF SRM 51-50-02. PARTS USED: 00-0596-3-0294, QTY :1. BODY PANEL 194CL HAS MULTIPLE AREAS FROM TREAD THROWN HAVE DELAMINATION. REMOVED PANEL FOR REPAIR. REMOVED PANEL 194CL DUE TO DAMAGE REF LOG PAGE 5132923. REPLACED PANEL 194CL REFERENCED AMM 53-51-21-400-801. ORIGINAL SUBMISSION DATE: 7/14/2023

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 59,556 hrs · 21,506 cycles

LEFT HORIZONTAL STAB LOWER SKIN WAS CRACK AT HSS 184.70 CRACK 0.4. REMOVED DAMAGED CRACK AND REPAIRED AREA AT LT HORIZONTAL STAB IAW SRM 55-10-01 REP 11 TABLE 204 INSP THRESHOLD AT LOWER SKIN STA 184.70 IAW B737-800 SRM 55-10-01-2R-11, AMM 56,000. PERFORMED NDT IAW 9,000 FLT CYCLES PER STEP 5.A PART 6 51 -00-00 PROC 23 WORK ACCOMPLISHED AT AAR RFD ON HANGAR TOMC APPROVED DIP FOR LEFT HORIZONTAL STAB LOWER SKIN CRACK TOMC APPROVED DIP FOR LEFT HORIZONTAL STAB LOWER SKIN CRACK TOMC-APPROVAL FROM SC1ELBYC COMMENT REPAIRED PER SRM 55-10-01-2R-11, REF TABLE 204, REPAIR TO HAVE REPAIRED PER SRM 55-10-01-2R-11, REF TABLE 204.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 59,556 hrs · 21,506 cycles

LH HORIZONTAL STAB LOWER SKIN HAS 2 CRACKS. CRACK 1- STA 138.70 L= .500". CRACK 2 - STA 120.30 = .400". 01 AMM 51-21-73-370-801, AMM 51-21-00-100-801, PERFORMED NDT IAW PART 6, 51-00-00 PROC 16 PROC 23, HFEC NDT INSPECTION ACCOMPLISHED ON ALL 3 CUTOUTS AND ALL OUTER FASTENER HOLES DIP PER ABOVE REQUIREMENTS. REMOVED PREVIOUS REPAIR AT STA 120-136 IAW SRM 55-10-01 REP 11 TABLE 204.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 59,556 hrs · 21,506 cycles

NDT-5 INDICATION NOTED ON LT HORIZONTAL LWR SKIN AT HSS 184.70. REMOVED THE CRACK AND REPAIRED THE AREA IAW SRM 55-10-01-2R-11, AMM 51-21-1 1-150-801, SRM 51-20-01, AND EA 22068. PERFORMED NDT IAW PART 6 51-00-00, PROC 23.

Part: BATTERY PACK — DISCHARGED (EMERGENCY LIGHTS) · airframe 59,556 hrs · 21,506 cycles

MULTIPLE EMERGENCY LIGHTS INOP, EXTERIOR LIGHT DOOR L1, OVER DOOR L1 EXIT LIGHT, FWD ENTRY LIGHT DOOR L1 DOME LIGHT. REMOVED AND INSTALLED NEW BATTERY PACK (M1675) FWD ENTRY LIGHT DOOR L1, TEST GOOD.

Part: B-NUT — BACKED OUT (ENGIEN OIL SYS) · airframe 54,134 hrs · 19,251 cycles

OIL QTY NUMBER 2 ENG READ ZERO AFTER TAKE OFF INITIAL INSPECTION, FOUND B-NUT LINE BACKED OFF FROM OIL PRESSURE SENSOR. LINE IS MARKED WITH YELLOW TAPE. SEE PICTURE AND ADDED 18 QTS MJ2 OIL TO FULL RE-SECURED B-NUT ON OIL PRESSURE MANIFOLD. ACCOMPLISHED 10 MINUTES PART POWER LEAK CHECK PER AMM TASK 71-00-00-700-823-F00. NO LEAKS NOTED

Part: UNKNOWN — ODOR (CABIN) · airframe 52,521 hrs · 18,641 cycles

FA NOTED AFT GALLEY BURN SMELL. NO OVENS POWERED, SMELL DISIPATED QUICKLY, NO OTHER SIGNS NOTED. PRESSURIZE AIRCRAFT WITH APU POWER, TURN ON AFT GALLEY OVENS, COFFEE MAKERS, COFFEE WARMERS. NO EVIDENCE OF ELECTRICAL BURN SMELL. REPRESSURIZE AIRCRAFT WITH ENGINE RUNNING, FOUND BURN SMELL COMING FROM CABIN VENTS.

Part: FRAME — DENTED (FUSELAGE) · airframe 52,491 hrs · 18,630 cycles

FRAME DENTED AT BS 5OOG INNER CORD AT S-24L TO S-26L FRAME AT STA 500G REPAIRED PER EC/RA5311-02279 REF FLEET CYCLE L OG PG.9702467 FOR ALL WORK PERFORMED. INITIATE D.I.P PER EC/RA 5 311-02279 STEP 11 TO "ACCOMPLISH INSPECTION REQUIREMENTS ON OR BEFORE THE AIRCRAFT REACHING 75,000 TOTAL FLIGHT CYCLES. PLANNIN G TO CONTACT ENGINEEING AFTER 68,000 TOTAL FLIGHT CYCLES BUT BEF ORE 69,000 TOTAL FLIGHT CYCLES FOR THE INSPECTION REQUIREMENTS" OK TO DIP FRAME AT STA 500G REPAIRED PER EC/RA5311-02279 REF FLEET CYCLE L OG PG.9702467 FOR ALL WORK PERFORMED. INITIATE D.I.P PER EC/RA 5 311-02279 STEP 11 TO "ACCOMPLISH INSPECTION REQUIREMENTS ON OR BEFORE THE AIRCRAFT REACHING 75,000 TOTAL FLIGHT CYCLES. PLANNIN G TO CONTACT ENGINEEING AFTER 68,000 TOTAL FLIGHT CYCLES BUT BEF ORE 69,000 TOTAL FLIGHT CYCLES FOR THE INSPECTION REQUIREMENTS TOMC-APPROVAL FROM SC1ELBYC COMMENT QC REVIEWED RECORDS UPDATE...UK/U354344 QC REVIEWED INIT: PLN/ENG >68,000<69,000 TAFC TA: 75,000 TAFC...UK/U354344

Part: BEAM — CORRODED (FUSELAGE) · airframe 52,491 hrs · 18,630 cycles

CORROSION FOUND IN APU COMPARTMENT LOWER LEFT FLANGE BETWEEN MIDDLE DOOR LATCH AND FWD DOOR LATCH NEAR NUT PLATE . REPAIRED REF ECRA5311-02282 . INITIATE A DIP TO ACCOMPLISH INSPECTION REQUIREMENTS ON OR BEFORE THE AIRCRAFT REACHING 75.000 TOTAL FLIGHT CYCLES.PLANNING TO CONTACT ENGINEERING AFTER 68.000 TOTAL FLIGHT CYCLES BUT BEFORE 69.000 TOTAL FLIGHT CYCLES FOR THE INSPECTION REQUIREMENTS ACCOMPLISH INSPECTION REQUIREMENTS ON OR BEFORE THE AIRCRAFT REACHING 75,000 TOTAL FLIGHT CYCLES. PLANNING TO CONTACT ENGINEERING AFTER 68,000 TOTAL FLIGHT CYCLES BUT BEFORE 69,000 TOTAL FLIGHT CYCLES FOR THE INSPECTION REQUIREMENTS. TOMC-APPROVAL FROM SC1ELBYC COMMENT SFR 1022844 WAS CREATED AND ITEM WAS REPAIRED PER ECRA 5311-0228 2 AND DIP WAS INITIATED FOR INSPECTIONS BEFORE 75000 CYCLES Q/C REVIEWED. Q/C REVIEWED. RECORDS UPDATE INIT: PLN/ENG >68,000 <69,000 TAFC T/A: 75,000 TAFC.....................LT/U224600

Part: SKIN — CRACKED (RT HORIZ STAB) · airframe 52,491 hrs · 18,630 cycles

REF EA5510-01843 REV H . FOUND A CRACK RH SIDE HORIZONTAL STAB LOWER SKIN AT STAB STA 157.1,MEASURED FROM THE AFT SPAR GOING FWD 9 INCHES . TE CRACK MEASURES 3/4 INCH IN LENGHT . REF FLEET CYCLE N/R 9700274 FOR ALL WORK PERFORMED PER SRM 55-10 -01 REPAIR 11 . INITIATED A DIP TO PERFORMAND INSPECTION THRESHO LD 56.000 TOTAL FLIGHT CYLES AND REPEAT INSPECTIONS AT INTERVAL OF 9.000 FLIGHT CYLES DETAIL VISUAL INPECTION AND 9.000 FLIGHT CYLCES LFEC INSPECTION . REF SRM 55-10-01 REPAIR 11 PAGE 223 TAB LE 204. TOMC APPROVE DIP PER SRM 55-10-01 REPAIR 11 PAGE 223. INITIAL INSPECTION AT 56000 TOTAL FLIGHT CYCLES. REPEAT DVI AND LFEC AT 9000 FLIGHT CYLES THERE AFTER. TOMC-APPROVAL FROM SC1ELBYC COMMENT VERIFIED. QC REVIEWED QC REVIEWED RECORDS UPDATE INIT: 56,000 TAFC OC: (-2526) WILL ITO TO RIR (-2527) RIR: 9,000 F/C DVI & LFEC

Part: SKIN — CRACKED (LT HORIZ STAB) · airframe 52,491 hrs · 18,630 cycles

EA 5510-01843 REV H; FOUND ON LEFT SIDE HORIZONTAL STAB, LOWER S KIN, AT STAB STA 129.5 MEASSURED FROM THE AFT SPAR GOING FORWARD 10 INCHES. THE CRACK MEASURES 3/4 INCH IN LENGTH. MARKED. REF F LEET CYCLE NON ROUTINE 9700271. COMMON DOUBLER INSTALLED ON L/H HORIZ STAB INSPAR LOWER SKIN BETWEEN STA''S 120.30 AND 129.50 IAW SRM 55-10-01 REP 11 INSP THRESHOLD AT 56,000 TOT FLT CYC''S FOLLOWED BY REPEAT INTERVALS AT EACH 9,000 FLT CYC''S PER STEP 5.A. TABLE 204 REF F/C N/R''S 9700271 AND 9700494 COMMON DOUBLER INSTALLED ON L/H HORIZ STAB INSPAR LOWER SKIN BETWEEN STA''S 120.30 AND 129.50 IAW SRM 55-10-01 REP 11 INSP THRESHOLD AT 56,000 TOT FLT CYC''S FOLLOWED BY REPEAT LFEC AT INTERVALS AT 9,000 FLT CYCLES PER STEP 5.A. TOMC-APPROVAL FROM SC1ELBYC COMMENT REPAIR IS COMPLETE AND DIP ISSUED. QC REVIEW QC REVIEW RECORDS UPDATE INIT: 56,000 TAFC WILL ITO TO RIR (-2536) RIR: LFEC 9,000.............LT/U224600

Part: FITTING — CRACKED (L1 WINDOW) · airframe 52,491 hrs · 18,630 cycles

L-1 WINDOW POST CRACKED AT UPPER LEFT CORNER L-1 WINDOW POST HAS BEEN REPAIRED IAW ECRA 5311-02271 ACCOMP AN INITIAL INSP PER PART 2 SECTION A ON OR BEFORE THE AIRCRAFT REACHING 50000 TOTAL FLT CYC''S. ACCOMP REPETITIVE INSP''S PER PART 2. SECTION A AT INTERVALS NOT TO EXCEED 18000 FLT CYC''S THEREAFTER REPAIRED PER ECRA 5311-02271 FLEET CYCLE LOG 9702465. ACCOMPLISH AN HFEC INSPECTION PER ECRA 5311-02271 PART 2 SECTION A AT OR BEFORE 50,000 PTC AND AT INTERVALS OF 18,000 CYCLES THEREAFTER TOMC-APPROVAL FROM SC1ELBYC COMMENT VERIFIED APPROVAL. QC REVIEW RECORDS UPDATE QC REVIEW INIT: 50K TAFC INIT WILL ITO TO RIR (-4734) RIR: 18K FC..DB/U359554

Part: SKIN — CORRODED (BS 917) · airframe 52,491 hrs · 18,630 cycles

REF FCD 5100-02772 LAV VENT PORT HAS CORROSION STA 917L BETWEEN STRINGERS 21L AND 22L FUSELAGE SKIN AT STA 917 BETWEEN STR''S 21L AND 22L HAVE BEEN REPAIRED IAW SRM 53-70-01 REP 3 INSP THRESHOLD @ 50,000 TOT F/C FOLLOWED BY REPEAT INTERVALS AT EACH SUBSEQUENT 5,000 F/C PER STEP 5.A.TABLE 202 TOMC APPROVED FOR ONE TIME INSPECTION AT 50,000 CYCLES WITH SUBSEQUENT INSPECTIONS AT 5000 CYCLE INTERVALS.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 52,491 hrs · 18,630 cycles

REF EA 5510-01843 REV H FOUND ON R/H HORIZ STAB LOWER SKIN AT STA 101.90 CRACK MEASURING 10" FWD AF AFT SPAR 1" IN LENGTH R/H HORIZ STAB LOWER INSPAR SKIN STA 101.90 HAS BEEN REPAIRED IAW SRM 55-10-01 REP 11 REF F/C N/R 9700272 INSP THRESHOLD AT 56''000 TOT F/C FOLLOWED BY REPEAT INSP EACH SUBSEQUENT 9,000 FLT CYC''S PER STEP 5.A. TABLE 204 TOMC APPROVED. PERFORM INITIAL INSPECTION AT 56000 CYCLES AND REPEAT INSPECTIONS EVERY 9000 CYCLES THEREAFTER. TOMC-APPROVAL FROM SC1ELBYC COMMENT VERIFIED. QC REVIEWED QC REVIEWED INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.

Part: SKIN — CRACKED (HORIZONTAL STAB) · airframe 52,491 hrs · 18,630 cycles

REFERENCE EA 5510-01843 REV H; FOUND ON RIGHT SIDE HORIZONTAL ST AB , LOWER SKIN, AT STAB STA 120.3 MEASURED FROM THE AFT SPAR GO ING FORWARD 10 INCHES. THE CRACK MEASURES 1/2 INCH IN LENGHT.MAR KED. REF FLEET CYCLE NON ROUTINE 9700273. R/H HORIZ STAB LOWER INSPAR SKIN STA 120.30 HAS BEEN REPAIRED IAW SRM 55-10-01 REP 11 COMMON DOUBLER INSTALLED JOINING PREVIOUS REPAIR AT STA 129.50 REF N/R 9700273 AND 9878044 INSP THRESHOLD AT 56,000 TOT F/C''S FOLLOWED BY REPEAT INTERVALS AT EACH SUBSEQUENT 9,000 FLT CYC''S PER STEP 5.A.TABLE 204 TOMC APPROVED, PERFORM INITIAL INSPECTION AT 56000 CYCLES AND THEN EVERY 9000 CYCLES AFTER THAT PER SRM 55-10-01 REPAIR 11. TOMC-APPROVAL FROM SC1ELBYC COMMENT VERIFIED. QC REVIEWED QC REVIEWED INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.

Part: SENSOR — FAULTED (TE FLAPS) · airframe 46,320 hrs · 16,234 cycles

LEADING EDGE FLAPS TRANSIT LIGHT STAYS ON 1. EMERGENCY DECLARED. PERFORMED VISUAL INSPECTION OF FLAP AND SLATS, WITH FLAPS EXTENDED PERFORMED HARNESS SHAKE DOWN, NO DEFECTS NOTED. IAW FIM TA SK 27-51-00 PERFORMED FSEU BITE, NO FCURRENT FUALTS NOTED. ON FAULT HISTORY LEG 006 AND 010 FOUND MESSAGE 27-53279. IAW FIM TASK 27- 51-00-810-822, FOUND TO BE WITHIN LIMITS. CYCLED FLAPT SEVERAL TIMES AND PERFORMED FSEU BITE, TEST PASSED. REMOVED AND REPLACED THE INBOARD FLAP INBOARD SKEW SENSOR IAW MM 27-59-01-000-804, AND MM 27-59-01-400-804. OPS TEST OF THE FLAP SKEW DETECTION SYSTEM, ALL CHECKED GOOD. NO DEFECTS NOTED. IAW MM 27-59-00-730-801.

Part: LIGHT — INOPERATIVE (SEAT 20A) · airframe 46,140 hrs · 16,163 cycles

EMERGENCY EXIT SIGN DOES NOT TURN ON 20A. RESET THE LIGHT ASSY.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 45,707 hrs · 15,982 cycles

M1694, M1695, M1676, M1671 EMERGENCY LIGHTS POWER SUPPLY BATTERIES FAIL CAPACITY CHECK PER W/C 29-3350-1-7100. REPLACED CHARGER ASSY M1671 IAW AMM 33-51-06. REPLACED BATTERY PACKS IN CHARGERS M1671, M1676, M1694, M1695 IAW AMM 33-51-06.

Part: SKIN — DAMAGED (BS 227) · airframe 42,678 hrs · 14,791 cycles

FUSELAGE SKIN DAMAGE AT EXTERNAL POWER DOOR CUT OUT, FWD EDGE AT LOWER HINGE AREA. THE SKIN AT BS 227 WL 180 HAS BEEN REPAIRED IAW ECRA 5330-04930 PART 3, AND SRM 53-10-15 REP. 5.

Part: TRIM MOTOR — FAILED (HORIZ STAB) · airframe 39,676 hrs · 13,768 cycles

MAIN ELEC TRIM & AUTOPILOT TRIM FAILED IN FLIGHT. FLAPS 15 LANDING, SOFT & BELOW MAX LANDING WEIGHT. TRIM SWITCH CONFIGURATION LEFT IAW QRH CHECKLIST. R & R STABILIZER TRIM MOTOR IAW AMM 27-41-71-400-801. REF FORM 44-0008 FOR WORK PERFORMED. OPERATIONS CHECK IS GOOD.

Part: FRAME — CRACKED (FUSELAGE) · airframe 34,199 hrs · 11,834 cycles

FRAME AT STATION 867 BETWEEN STRINGER 8RT & STRINGER 9RT FOUND TO HAVE A 1/8 INCH CRACK USING MFEC AT INBD RIVET FOR AIR CONDITIONING RAIL BRACKET. CUTOUT DAMAGE AT STATION 867 LOCATED BETWEEN STRINGER 8R & STRINGER 9R. INSTALLED ANGLES TWO EACH & SEALED AREA IAW EA5310-04716 & NDT PART 6.

Part: FRAME — CRACKED (FUSELAGE) · airframe 34,199 hrs · 11,834 cycles

FRAME AT STATION 727D BETWEEN STRINGER 8RT & STRINGER 9RT FOUND TO HAVE 1/2 INCH CRACK USING MFEC AT INBD FASTENER HOLE FOR AIR CONDITIONING RAIL BRACKET. CUT OUT DAMAGE AT STATION 727D LOCATED BETWEEN STRINGER 8RT & STRINGER 9RT. INSTALLED REPAIR ANGLES TWO EACH & SEALED AREA IAW EA5310-04716 FIG 3 STEPS 1-13 & NDT PART 6.

Part: FRAME — CRACKED (FUSELAGE) · airframe 34,199 hrs · 11,834 cycles

FRAME AT STATION 400 BETWEEN STRINGER 8RT & STRINGER 9RT FOUND TO HAVE A 1/2 INCH CRACK FOUND VISUALLY & CONFIRMED USING MFEC AT INBD RIVET FOR AIR CONDITIONING RAIL BRACKET CABIN. ACCOMPLISHED ANGLE REPAIR IAW EA 5310-04716 REV F, FIG 3.

Part: FRAME — CRACKED (FUSELAGE) · airframe 34,199 hrs · 11,834 cycles

FRAME AT STATION 787 BETWEEN STRINGER 8RT & STRINGER 9RT FOUND TO HAVE A 1/8 CRACK. FOUND USING MFEC AT INBD RIVET FOR AIR CONDITIONING RAIL BRACKET. REPAIR OF FRAME AT STATION 787 BETWEEN STRINGER 8RT & STRINGER 9RT IAW EA 5310-04716 REV F FIGURE 3.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 32,613 hrs · 11,239 cycles

EMERGENCY LIGHTS EXIT L1 DOOR & EXIT LIGHT ABOVE COCKPIT DOOR STAY ON ONLY 3-4 SECONDS. THIS IS SFR ITEM. R & R POWER SUPPLY BATTERY PACK AT L1 DOOR IAW AMM 33-51-06-960-8 05. OPERATIONS CHECKED GOOD.

Part: SKIN — CRACKED (HORIZ STAB) · airframe 24,431 hrs · 8,380 cycles

SUPPORT TASK - RT HORIZONTAL STAB LOWER INSPAR SKIN SHOW CRACK AT STA. 175.50 APPROX 6 INCHES AFT OF DRAIN HOLE. CRACK 1 INCH LENGHT. (MARKED) C-SCAN. REPAIRED AND REFINISHED PER EC/RA 5510-02166 AND ISSUED DIP TO INSPECT REPAIR IN 56,000 FLIGHT CYCLES PER SRM 55-10-01 REPAIR II TABLE 204 AND AT 9000 FLIGHT CYCLES INTERVALS THEREAFTER DIP 55-DIP CONTROL NUMBER 010233. RT HORIZ STAB LWR SKIN CRACKED. PER ECRA 5510-02166 COMPLETED REPAIR. INSPECT REPAIR AT 56,000 TOTAL FLT CYC`S PER PART 2 OF ECRA, THERAFTER INSP REPAIR EVERY 9,000 FLT CYC`S PER PART 2 OF ECRA 1) INIT: W/I 56K TOTAL A/C F/C. INIT WILL AUTO-ITO TO 2) RIR: W/I EVERY 9K F/C THEREAFTER (M&E 58-9955-8-1099)-ODEE

Part: SKIN — CRACKED (HORIZ STAB) · airframe 24,431 hrs · 8,380 cycles

SUPPORT TASK LT HORIZONTAL STAB LOWER SKIN SHOW CRACK AT STA 101.90 JUST I/B OF DRAIN HOLE. APROX 1 INCH IN LENGHT (MARKED) C-SCAN. REPAIRED AD REFINISHED PER EC/RA 5510-02165 AND ISSUED DIP TO INSPECT REPAIR IN 56,000 FLIGHT CYCLES PER SRM 55-10-01 REPAIR II TABLE 204 AND AT 9000 FLIGHT CYCLE INTERVALS THERE AFTER. DIP # 55-DIP CONTROL # 010234 LT HORIZ STAB LWR SKIN CRACKED.PER ECRA 5510-02165 COMPLETED REPAIR. INSP REPAIR AT 56,000 TOTAL FLT CYCS PER PART 2 OF ECRA THEREAFTER EVERY 9,000 FLT CYCS PER PART 2 OF ECRA . 1) INIT: W/I 56K TOTAL A/C F/C. INIT WILL AUTO-ITO TO 2) RIR: W/I EVERY 9K F/C THEREAFTER (M&E 58-9955-8-1101)-ODEE

Part: FRAME — DAMAGED (FUSELAGE) · airframe 17,788 hrs · 5,968 cycles

FBB RT WS 500D AT STRINGER 25R HAS DAMAGE. COMPLIED WITH EC/RA 5310-04909 ON FRAME REPAIR AT STA 500D AT STR 24RT TO STR 25RT.