N17105

Part: FANWHEEL — SEIZED (NR 1 ENGINE) · airframe 113,078 hrs · 26,502 cycles

ENG EGT 941 2 MIN AFTER NORMAL ENG START. LOCKED FOR POSITIVE FIX PER CREW COMMENT, #1 ENGINE STARTED NORMALLY, THEN 2 MINUTES AFTER ENGINE START EGT SPIKED. CREW IMMEDIATELY SHUTDOWN ENGINE. ON VISUAL EXAMINATION, EXHAUST HAS NO DEBRIS, THE FAN DISK IS SEIZED. REPLACED NR 1 ENGINE IAW WC 19-0572-8-0271.

Part: DOUBLER — NOT REPORTED (ZONE 200) · airframe 112,664 hrs · 26,419 cycles

REPAIR FOUND ON LEFT FUSELAGE APPROX LOCATION OF BS 1787.45 + 27.5 TO BS 1830 LOCATED OVER LT HORIZONTAL STAB ABOUT 10" DOWN FROM VERTICAL STAB.REQUIRES REPLACEMENT DUE TO NO DOCUMENTATION OR DIP INFO FOR REP INSPECTIONS. REMOVED AND REPLACED DOUBLER STA 1787.45 L 10IN BELOW VERT STAB REF SRM 53-00-01-2R-29.SEE N/R 002832379 FOR REPAIR WORK SIGN OFFS AND ELB 6377566 FOR REP INSP REQUIREMENT DIP.

Part: WEB — DAMAGED (ZONE 400) · airframe 112,664 hrs · 26,419 cycles

NR 1 ENGINE TOP OF PYLON HYDRAULIC LINE BRACKET WORE INTO BOW TIE STRAP ON TOP OF PYLON. REPAIRED UPPER PLYLON WEB REF ECRA 5450-03044.

Part: HANDLE — WORN (ZONE 800) · airframe 112,664 hrs · 26,419 cycles

L1 ENTREY DOOR UNABLE TO OPEN DOOR BY THE EXTERIOR HANDLE REMOVED L1 DOOR HANDLE ASSY, REPLACED CAM BASKET AND WORN HANDLE PARTS REF AMM 52-11-13

Part: BELLOWS — TORN (NR 1 ENGINE) · airframe 112,464 hrs · 26,375 cycles

L ENG OVHT EICAS. EXTINGUISHED AT 1.30 EPR. PILOTS VERBALLY REPORTED,AT CRUISE, EICAS MESSAGE ALERT.THOTTLE MOVED TO IDLE EICAS GOES AWAY. RETURNED WHEN THROTTLE WAS MOVED JUST ABOVE IDLE. FOUND RIP IN PRECOOLER BELLOWS, FOUND FIRE ELEMENT IN CONTACT WITH SUPPORT BRACKET, REPOSITIONED SAME. WRAPPED IN ALUMINUM FOIL FOR RUN TEST REMOVED AND REPLACED TORN #1 ENG PRECOOLER BELLOWS. REF CMM 36-10-01. REF IPC 78-31-20-04. ACCOMPISHED RUN OF #1 ENGINE AT MAX BLEED PRESSURE. NO FAULTS NOTED. FOIL ON BLEED DUCTS NEEDS TO BE INSPECTED AND REMOVED. REMOVED FOIL AND CHECKED FOR LEAKS NO LEAKS NOTED.

Part: LIGHT — INOPERATIVE (ZONE 200) · airframe 112,243 hrs · 26,330 cycles

AISLE ILLUMINATION EMERGENCY LIGHTS FROM ROW 34 TO 41 WONT LIGHT UP DURING EMERGENCY LIGHT TEST SWAPPED AFT BATTERIES PACKS TO IDENTIFY FAULT. NO HELP. MAY REQUIRE A NEW POWER SUPPLY. REMOVED AND REPLACED EMERGENCY LIGHT POWER SUPPLY IAW MM 33-51-07-022-020 OPERATIONAL CHECK SATISFACTORY OK TO CONTINUE

Part: LAVATORY — FULL (ZONE 900) · airframe 112,182 hrs · 26,315 cycles

ALL LAVS FULL, NEEDS LAV SERVICE ALL LAVS SERVICED AND OPERATIONAL

Part: TRANSMISSION — FAULTED (TE FLAPS) · airframe 112,016 hrs · 26,281 cycles

TE FLAP ASYM DURING 15 TO 20 EXTN ON APP. SPD 180IAS. PER CREW VERBAL EICAS MSG CLEARED AND BOTH SIDES WERE AT FLAPS 20. T/S PER FIM 27-51 FAULT TREE 805. FSEU 1 HAS RT FLAP XMT AS EXISTING FAULT. LEG 0 FAULT HISTORY SHOWS RT FLAP DRIVE FAULT MSG 315, FDE:FLAP ASYMETRY. FOUND LEFT O/B AND RIGHT O/B FLAP TRANSMISSIONS OVERLOAD INDICATORS POPPED. ALSO FOUND RIGHT OUTBOARD TORQUE TUBE CAN BE MANUALLY ROTATED BY HAND. NO FAULTS ON FSEU 2 OR FSEU 3. PER TECH SUPPORT, RECOMMEND REPLACING BOTH TRANSMISSIONS. UPDATED MATERIALS LIST SEE L/P 4828663 FOR REPLACEMENT OF TORQUE TUBE TO # 8 TRAILING EDGE FLAP TRANSMISSION, L/P 4825478 FOR REPLACEMENT OF # 1 FLAP TRANSMISSION AND L/P 4825482 FOR REPLACEMENT OF # 8 FLAP TRANSMISSION. PERFORMED OPERATIONAL TEST OF TRAILING EDGE FLAP SYSTEM AS PER MM-27-51-00-715-001. ALL CHECKS GOOD UPDATE FOR SFR

Part: CHARGER — INOPERATIVE (ZONE 200) · airframe 112,016 hrs · 26,281 cycles

EMERGENCY LIGHTS - OPERATIONAL TEST WITH THE TEST SWITCH PROCEDURE - ROW 34 TO ROW 41 SEAT EMERGECY LIGHT INOP DURING TEST REPLACED BATTERY PACK AND POWER SUPPLY AT AFT LOCATION M736 PER AMM 33-51-07-902-001 AND 33-51-07-862-054.AFTER OPS TEST FOUND TO BE WORKING PROPERLY.NO FURTHER DEFECT NOTED.

Part: BOTTLE — LOW PRESSURE (ZONE 800) · airframe 111,871 hrs · 26,250 cycles

1L PRESS LOW IN RED INSPECTED L1 PRESSURE GAGE FOR THE INFLATION CYLINDER REF AMM TASK 25-66-01-206-041, STILL WITHIN LIMITS. OK TO CONTINUE.

Part: DOOR — MALFUNCTIONED (ZONE 800) · airframe 111,702 hrs · 26,216 cycles

DOOR 2L NEEDS SOME TLC. MX NEEDING TO SLAM IT SHUT TO GET ENTRY DOOR LITE 2 GO OUT EWR+PDX OPERATED DOOR SEVERAL CYCLES. NO DEFECTS NOTED. EICAS WARNING AND OVERHEAD DOOR WARNING LIGHT EXTINGUISHED WITH DOORS CLOSED.

Part: HOSE — FAULTY (TOILET) · airframe 109,534 hrs · 25,700 cycles

FWD LAV HAD CONTINUOUS BLUE JUICE LEAK IN FWD LEFT CORNER OF LAV . REMOVED TOILET SHROUD FROM LAV "A". TOILET FOUND TO BE NOT OVERSERVICED. TOILET FLUSHES NORMALLY WITH NO LEAKS NOTED AT LAV TANK AND FLUSH COMPONENTS ON TOP OF LAV TANK. HAD LAV DUMPED AND AND SERVICED FROM REMOTE EXTERIOR SERVICING PANEL. FOUND HOSE LEAKING DURING FILLING OF LAV TANK. HOSE IDENTIFIED WHICH CONNECTS FROM PUMP/FILTER ASSY TO RINSE/FILL VALVE ASSY ON TOP OF LAV TANK. CLEANED UP RESIDUAL FLUID THAT WAS MAINTAINED ABOVE CABIN FLOOR. DDP APPLIED. LAV UN USEABLE. DOOR CLOSED AND LOCKED. LAV CLEAN UP WILL BE ADDRESSED ON ANOTHER LOG PAGE DISPATCH DESK: 91 NAME: AW DATE: 21-AUG-24- NOC DESK: 757 NAME: DONNY DATE: 21-AUG-24- LAV TANK TO REMAIN EMPTY TILL SOURCE OF INFLIGHT LEAK IS REPAIRED LAV PLACED ON MEL ADDED HOSE PART # NEEDED 19-3832-3-0025 (HOSE) REMOVED AND REPLACE RINSE FILL LINE HOSE SYSTEM. PERFORMED TEST OF THE TOILET SYSTEM REFERENCE: TASK 38-32-00-725-001. NO LEAKS NOTED. OK TO CONTINUE.PARTS USED: 19-3832-3-0025,QTY :1

Part: WARNING MESSAGE — ILLUMINATED (THRUST REVERSERS) · airframe 108,570 hrs · 25,503 cycles

ON CLIMBOUT RECEIVED YELLOW REV ICON ABOVE RIGHT ENGINE EPR GAUG E REQUEST MEL FOR RIGHT ENG THRUST REVERSER INOP. PLACED RIGHT ENG T/R ON MEL DDP CW. RIGHT ENGINE THRUST REVERSER DEACTIVATED I.A.W. MEL 7831F. MEL AND DDP REQUIREMENTS CONTAINED IN 7831F COMPLIED WITH.

Part: SKIN — CORRODED (BS 1400 S25L) · airframe 107,450 hrs · 25,255 cycles

B757-06-3-0241, AFT CARGO COMPARTMENT LH INTERNAL STRUCTURE STA 1400 AND NEXT TO STGR 25LH WITH CORROSION SPOT. REMOVED DAMAGED PARTS IAW B757 SRM 51-40-02, PERFORMED SURFACE A , 51-21-14 AND 51-21-15. ND OPEN HOLES HFEC INSPECTION IAW B757 NTM PART 6 51-00-19, FABR ICATED AND INSTALLED REPAIR PARTS IAW EA#757-5360-13-A3521 PREM 1 AND 2, RESTORED SURFACE PROTECTION IAW B757 AMM 51-21-04, INSTALLED REPAIR PARTS IAW EC/RA #5360-01766 PRELIM 1 & 2.

Part: WEB — CORRODED (BS 1862) · airframe 107,450 hrs · 25,255 cycles

EXFOLIATION CORROSION AT STA 1862 BELOW ELEVATOR AUTOPILOT SERVOS ON WEB SHELF. REMOVED AND REPLACED WEB PLATE P/N 148N9203-16 AT STA 1862 B/W R BL30 TO LBL30 IAW SRM 51-40-02 AND DWG 148N9203. REINSTALLED 4EA FITTINGS FROM STA 1862 IAW SRM 51-40-02. PERFORMED RII INSPECTION

Part: SHELF — CORRODED (BS 1862) · airframe 107,450 hrs · 25,255 cycles

B757-06-3-0272: EXFOLIATION CORROSION AT STA 1862 THROUGH ELEVST OR CONTROL ACCESS DOOR ON WEB SHELF. REMOVED AND REPLACED CHORD AT RBL30 STA 1862 IAW SRM 51-40-02 BATCH #0004239868 P/N 148N2122-1 DWG 148N9203 REV D. PERFORMED RII INSPECTION

Part: OIL FILTER — WARNING MESSAGE (RH ENG) · airframe 106,487 hrs · 25,021 cycles

R OIL FILTER ADVISORY DISPLAYED ON CLIMB OUT AT APPROX 800 AGL REF LOGPAGE # 5962383 R ENG OIL FILTER BYPASS MEL APPLIED AND DAILY MAINTENANCE HAS BEEN ACCOMPLISHED PER MEL 7935B. DAILY MAINTENANCE REQUIREMENTS MUST BE COMPLIED WITH AS CONTAINE D IN LOG PAGE NUMBER 5962383, UPDATING DEFERRAL LOGPAGE NOT REQU IRED. EFFECTIVE GMT DATE: 17OCT23 TEXT FROM PARENT LOG PAGE: R OIL FILTER EICAS ON AT 6000 WENT OUT AT 10000 DAILY LOG PUSHED TO FL 2497 ARR ORD ON 16OCT23 23:51Z DAILY MAINTENANCE REQUIREMENT R ENG OIL FILTER BYPASS INDICATION HAS BEEN ACCOMPLISHED 10-16-2023 PER MEL 7935B. NO FURTHER MAINTENANCE IS REQUIRED BEFORE FLIGHT.

Part: STRINGER — DAMAGED (STA680-700) · airframe 104,897 hrs · 24,715 cycles

REF L/P4612658. STR24L BETWEEN STA680-700 DAMAGED CUT AND REMOVED STR24L FROM STA640-710 REF SRM53-00-03-2R-1 VERIFIED CUTOUT OF S24L STRINGER. PER AVO10784 REV A. C/W RR GMM PERFORMED HFEC PER AVO10784 REV A STEP 12. NO CRACKS INDICATION VERIFIED .040" INSURANCE CUT REF AVO10784 REV A STEP 12A. C/W REQUIREMENTS. NOTED. OK TO TRIM OUT BY .040 AS AN INSURANCE CUT. C/W RII GMM RII GMM REQUIREMENTS REQUIREMENTS CUT AND REMOVED STR24L FROM STA660 TO 710 IN REF TO AVO10784 REV NEED TO ACCOMPLISH HFEC OF STR24L TRIMMED END REF AVO10784 REV A PERFORMED .040" INSURANCE CUT REF AVO10784 REV A STEP 12A A STEP 11 STEP 12, OK TO PERFORM .040 INSURANCE CUT STEP 12A OF AVO1084 REV A VERIFY FWD STRINGER SPLICE MATERIAL AS BAC1498-203 PO#2012730 AND AFT STRINGER SPLICE AS BAC1498-204 PO#2717159 REF AVO10784 REV C PART C STEP 3 AND 4 OF FABRICATION VERIFIED SPLICE MATERIAL VERIFIED STRINGER REPLACEMENTS AS STATED ABOVE OK TO TREAT, PRIME AND INSTALL REPAIR SECTIONS FOR STRINGER 24L SECTIONS AND SPLICES. VERIFY STRINGER REPLACEMENTS FOR FWD -3 PART REPAIR TAG R23006 FABRICATED STRINGER 24L SECTIONS AND SPLICES IN REF TO SRM FABRICATED STRINGER 24L SECTIONS AND SPLICES IN REF TO SRM FABRICATED STRINGER 24L SECTIONS AND SPLICES IN REF TO SRM AND AFT -4 PART REPAIR TAG R23007 REF AVO10784 REV D PART C 53-00-03-2R-1, NEED OK TO TREAT, PRIME AND INSTALL REPAIR 53-00-03-2R-1, NEED OK TO TREAT, PRIME AND INSTALL REPAIR 53-00-03-2R-1, NEED OK TO TREAT, PRIME AND INSTALL REPAIR FABRICATION STEP 1 AND 2

Part: SKIN — DAMAGED (FWD LAV) · airframe 104,897 hrs · 24,715 cycles

LAV SERVICE VEHICLE MADE CONTACT WITH AIRCRAFT WHILE SERVICING LAVATORY. GROUND DAMAGE SUSTAINED. DAMAGE SUSTAINED AROUND AFT LAV SERVICE PANEL. CORRECTION, DAMAGE SUSTAINED AT FWD LAV SERVICE PANEL NOT AFT LAV SERVICE PANEL AS PREVIOUSLY REPORTED. THE DAMAGE IS BY THE MID LAV SERVICING PANEL. PICS UPLOADED CUT AND REMOVED DAMAGED SKIN FROM STA680-720 STR23L TO 25L REF SRM51-10-02 VERIFIED COMPLETION OF STEPS 1 TO 5 OF AVO10784 REV A. C/W RII VERIFIED STEPS 9 AND 10 OF AVO10784 REV A. C/W RII GMM REQUIREMENTS. REF LP 4635555 REQUIREMENTS. RII REQUIRE AVO# 10784 STEP 1- NEED TO ACCOMPLISH AN EXTERNAL DETAILED AVO# 10784 STEP 2 C/W - GAINED ACCESS TO THE INTERNAL SIDE OF AVO# 10784 STEP 3 - NEED TO ACCOMPLISH AN INTERNAL DETAILED AVO# 10784 STEP 4 - TRIMMED OUT THE PUNCTURE TO THE FUSELAGE AVO# 10784 STEP 5 - REMOVED AT LEAST 5 ROWS OF FASTENERS BEYOND AVO# 10784 STEP 6 - NEED TO ACCOMPLISH AN HFEC INSPECTION OF THE AVO# 10784 STEP 7 - NEED TO ACCOMPLISH AN HFEC INSPECTION OF ALL AVO# 10784 STEP 8 - NEED TO ACCOMPLISH AN HFEC COUNTERSINK AVO# 10784 STEP 6.A. - PERFORMED .040 INSURANCE CUT TO TRIM OUT REF LP 4635555 FOR COMPLETION OF STEPS 1 TO 5 OF AVO10784 REV A. PERFORMED HFEC PER AVO10784 REV A STEPS 6, 7 AND 8. NO CRACK ACCOMPLISHED AND SENT TO ESC ATTACHED IMAGE OF DIMENSIONS REF VISUAL INSPECTION OF THE SURROUNDING FUSELAGE SKIN WITHIN A 20" THE SKIN COMMON TO THE DAMAGE LOCATION. VISUAL INSPECTION OF THE SURROUNDING FUSELAGE SKIN WITHIN A 20" SKIN IAW SRM 51-10-02. CUTOU

Part: FLAP SYSTEM — NONE (TE FLAPS) · airframe 104,108 hrs · 24,549 cycles

TE FLAP DISAGEE LANDED FLAPS 20 FOUND ALT. FLAPS SET AT 20 AND TE & LE SWITCHES PUSH IN, RESET IT TO NORMAL, AND PERFORMED TASK 27-51-00-715-001 OPS CHECK GOOD

Part: FLAP — GOUGED (LH WING L/E OB) · airframe 102,312 hrs · 24,136 cycles

B757-06-3-0319: LEFT WING OUTBOARD MAIN FLAP, OUTBOARD LEADING EDGE GOUGED. TRANSCRIBED FROM HAECO GSO NRC# 9280692 REPAIRED LEFT WING O/B MAIN FLAP O/B L/E SKIN PER B757-200 SRM 5 7-53-01-2R-3. THE INSTALLED BLIND RIVETS REQUIRE INSPECTION EVER Y 2500 FLIGHT CYCLES. TRANSCRIBED FROM HAECO GSO MECH V932673 / INSP QC315 INTERVALS IAW SRM 57-53-01-2R-3. REPAIR ACCOMPLISHED ON HAECO - GSO NR# 9280692. CURRENT FC=24136. DIP CREATED FOR LH WING OUTBOARD MAIN FLAP OUTBOARD LEADING EDGE REPAIR. BLIND RIVETS TO BE INSPECTED AT 2500 FLIGHT CYCLE OKAY TO CARRY FORWARD WITH A LEFT WING OUTBOARD TRAILING EDGE TOMC-APPROVAL FROM SC1ELBYC COMMENT FLAP BLIND RIVET REPAIR ACCOMPLISHED ON THE MAIN FLAP NOSE SKIN IN ACCORDANCE WITH SRM 57-53-01-2R-3 REPAIR 3. THIS REPAIR REQUIRE INSPECTION OF THE BLIND RIVITS EVERY 2500 FLIGHT CYCLES (FC) AND REPAIR OR REPLACED IF BLIND RIVET FASTENER DEGRADATION IS NOTED. ARMENTA TOMC INSPECTIONS CREATED BY AUTODIP PENDING AIRCRAFT RECORDS AUDIT & UPDATE.

Part: FRAME — CRACKED (FRAME 1540) · airframe 102,312 hrs · 24,136 cycles

B757-53-3-0571 FRAME 1540LH - PSU SUPPORT TRAIL ATTACHMENT CLIP TO FRAME INTERFACE - INBD RIVET - FRAME AFT SIDE HOLE CRACKED EXTENDING FROM RIVET HOLE. TRANSCRIBED FROM HAECO GSO NR 9281089 REPAIRED CRACKED FRAME AT STA 1540 BETWEEN STR BL - 9L IAW B757- 200 SRM 53-00-07-2R-8, REPAIR B. HAECO GSO MECH V893980 INSP QC4 67 REPAIR CHANNEL). REPAIRED THE ADDITIONAL 2 EA HOLES IAW B757-200 WHICHEVER COMES FIRST. HAECO GSO MECH V901143 INSP QC302 SRM 53-00-07-1A-3 AT STA 1540 FRAME BTW 8L-9L, BOTH REPAIRS ARE CATEGORY B AND REQUIRE SUPPLEMENTAL INSPECTIONS AT 12,000 FLIGH T CYCLES FROM REPAIR INSTALL OR 50,000 AIRFRAME FLIGHT CYCLES REPAIRED CRACKED FRAME AT STA 1540 BTW STR 8L-9L IAW B757-200 SR M 53-00-07-2R-0 REP 8. DURING PROCESS OF LOCATING AND DRILLING R EPAIR FASTENER HOLES, 2 EA ADDITIONAL HOLES WERE DRILLED IN THE INBOARD CHORD OF THE FRAME (1 EA ABOVE AND 2 EA BELOW THE -2 HOLES, 2EA ADD HOLES LOCATED ON THE I/B CHORD OF FRAME. REPAIRE 540 FRAME BTW STR 8L & 9L. BOTH REPAIRS ARE CATEGORY B & REQUIRE FRAME FC, WHICEVER COMES FIRST(INITIAL), REPEATS EVEY 12,000 FC D THE 2EA ADDITIONAL HOLES IAW B757-200 SRM53-00-07-1A-3 AT STA1 SUPPLEMENTAL INSPECTIONS AT 12,000 FC FROM REPAIR OR 50,000 AIR (ZONE 3). REPAIRED CRACKED FRAME AT STA1540 BTW STR 8L & 9L IAW B757-2SRM5 3-00-07-2R-8 REPAIR 8. WHILE LOCATING & DRILLING REPAIR FASTENER INSPECTED FRAME AND 2EA ADDITIONAL HOLE REPAIRS WITH NO DEFECTS NOTED.

Part: FRAME — CRACKED (FRAME 1580RH) · airframe 102,312 hrs · 24,136 cycles

B757-53-3-0577 FRAME 1580RH - PSU SUPPORT RAIL ATTACHMENT CLIP T O FRAME INTERFACE - INBD RIVET, FRAME AFT SIDE HOLE CRACKED EXTE NDING FROM RIVET HOLE. TRANSCRIBED FROM HAECO GSO NR 9281088 THE ADDITIONAL 3 EA HOLES IAW B757-200 SRM 53-00-07-1A-3 AT STA HAECO GSO MECH V901143 INSP QC302 1580 BETWEEN STR 8R-9R. BOTH REPAIRS ARE CATEGORY B AND REQUIRE SUPPLEMENTAL INSPECTIONS 12,000 FLIGHT CYCLES FROM REPAIR INSTAL L, OR 50,000 AIRFRAME FLIGHT CYCLES, WHICHEVER COMES FIRST. REPAIRED FRAME IAW B757-200 SRM 53-00-07-2R-8 REPAIR 8. DURING T HE PROCESS OF LOCATING AND DRILLING THE REPAIR FASTENER HOLES, 3 EA. ADDITIONAL HOLES WERE DRILLED IN THE INBOARD CHORD OF THE F RAME (1 EA ABOVE AND 2 EA BELOW THE -2 REPAIR CHANNEL). REPAIRED /B CHORD OF FRAME. REPAIRED 3EA HOLES IAW B757-200 SRM53-00-07-1 & REQUIRE SUPPLEMENTAL INSPECTIONS, 12,000 FC FROM REPAIR INSTAL PEATS EVERY 12,000FC (ZONE 3). A-3 AT STA1580 BETWEEN STR 8R & 9R. BOTH REPAIRS ARE CATEGORY B L OR 50,000 AIRFRAME FC, WHICHEVER COMES FIRST (INITIAL), AND RE REPAIRED FRAME IAW B757-200 SRM53-00-07-2R-8. WHILE LOCATING & D RILLING REPAIR FASTENER HOLES, 3EA ADDITIONAL HOLES LOCATED ON I INSPECTED THE REPAIRED FRAME AND ADDITIONAL HOLES WITH NO DEFECT S NOTED.

Part: FLAP — WORN (R WING) · airframe 102,312 hrs · 24,136 cycles

B757-06-3-0324 RIGHT WING IB MAIN FLAP LE AREA WORN NUMEROUS SPO TS, TRANSCRIBED FROM HAECO GSO NR 9280660

Part: FLAP — GOUGED (L WING) · airframe 102,312 hrs · 24,136 cycles

B757-06-3-0322 LEFT WING, INBOARD MAIN FLAP, LEADING EDGE GOUGED . TRANSCRIBED FROM HAECO GSO NR 9280709

Part: BRACKET — CRACKED (FRAME 1580RH) · airframe 102,312 hrs · 24,136 cycles

B757-53-3-0577 FRAME 1580RH - PSU SUPPORT RAIL ATTACHMENT CLIP T O FRAME INTERFACE - INBD RIVET, FRAME AFT SIDE HOLE CRACKED EXTENDING FROM RIVET HOLE. TRANSCRIBED FROM HAECO GSO NR 9281088

Part: FRAME — CRACKED (FRAME 1540LH) · airframe 102,312 hrs · 24,136 cycles

B757-53-3-0571 FRAME 1540LH - PSU SUPPORT TRAIL ATTACHMENT CLIP TO FRAME INTERFACE - INBD RIVET - FRAME AFT SIDE HOLE CRACKED EXTENDING FROM RIVET HOLE. TRANSCRIBED FROM HAECO GSO NR 9281089 REPAIRED CRACKED FRAME AT STA 1540 BETWEEN STR BL - 9L IAW B757- 200 SRM 53-00-07-2R-8, REPAIR B. HAECO GSO MECH V893980 INSP QC4 67

Part: SEAT TRACK — CORRODED (STA 365-418) · airframe 102,312 hrs · 24,136 cycles

SUPPORT TASK SEAT TRACK SUPPORT (P/N 141N5131-4) LOCATED BETWEEN STA 365-418 RBL 45 HAS CORROSION ON UPPER SURFACE TRANSCRIBED F ROM HAECO GSO NR 9280829

Part: SEAT TRACK — CORRODED (STA365-418RBL24) · airframe 102,312 hrs · 24,136 cycles

SUPPORT TASK SEAT TRACK SUPPORT PN 141N511-4 LOCATED BETWEEN STA 365-418 RBL 24 HAS CORROSION ON UPPER, TRANSCRIBED FROM HAECO G SO NR 9280828 NEW SUPPORT AND INTERCOSTAL IAW B757-200 SRM 51-40-02, BAC DW 14 1N5162 REV A AND 141N5130 REV E. HAECO GSO MECH V896606 INSP QC0 21 REMOVED SEAT TRACK SUPPORT AND INTERCOSTAL IAW B757-200 SRM 51-4 0-02. LOCATED, DRILLED, COUNTRESUNK AND DEBURRED NEW SEAT TRACK SUPPORT PN 654N0243-8, PO#1032749.1 IAW B757-200 SRM 51-40-05 AN D BAC DWG 141N5162 REV A AND BAC DWG 141N513 REV E. INSTALLED

Part: DOUBLER — CORRODED (STA 1500-1520) · airframe 102,312 hrs · 24,136 cycles

EA-5100-02129-001 ANTENNA DOUBLER LOCATED AT STA 1500-1520 STR -2 8R IS CORRODED AND GOUGED ON INTERNAL SIDE, TRANSCRIBED FROM HAE CO GSO NR LP 9281209 AF343-2108-00 REV D. HAECO GSO MECH V898621 INSP QC467 REMOVED DAMAGED DOUBLER STA 1500-1520 S28R -S29R IAW B757-200 SR M 51-40-02. FABRICATED NEW DOUBLER IAW GTE AIRFONE DWG AFP42-004 4-00. ALODINED AND PRIMED IAW B757-200 SRM 51-20-01. APPLIED TOP COAT IAW B757-200 AMM 51-24-22. INSTALLED NEW DOUBLER IAW

Part: BEAM — CORRODED (STA1630) · airframe 102,312 hrs · 24,136 cycles

(SUPPORT TASK) CORROSION ON CREASE BEAM INNER CHORD AT LBL64 APP ROX STA 1630, TRANSCRIBED FROM HAECO GSO NRC 9280931

Part: PRESSURE PLATE — CORRODED (STA1681) · airframe 102,312 hrs · 24,136 cycles

(SUPPORT TASK) LIGHT SURFACE CORROSION ON AFT DECK PRESSURE PLATE UPPER UPPER SURFACE LOCATED AT STA 1681 APPROX. RBL 60, TRANSCRIBED FROM HAECO GSO NR 9280939

Part: GENERATOR — NONE (E1) · airframe 101,515 hrs · 23,959 cycles

CONTROL EICAS MESSAGE (L,R) GEN OFF DISPLAYED. (01=L,02=R) GEN O FF LGT ON AND (FAILED TO RESET, GEN RESET THEN RETRIPPED) 01 RESET L GEN AND IT TRIPPED AGAIN. PERFORMEDVISUAL INSPECTION OF LEFT IDG. LEFT IDG FEEDER CABLES BE PLACED ON MEL. LEFT IDG PLACED ON MEL2400P. DDP CW SHOWS EVIDENCE OF OVERHEAT. (SEE ATTACHED IMAGES). REQUEST IDG DISPATCH DESK: 26 NAME: NESS DATE: 27-FEB-22- NOC DESK: 757 NAME: DEVORE DATE: 27-FEB-22- MEL 2400P APPROVED FOR THE LEFT GENERATOR. PERFORMED DDP, IDG DISCONNECTED. HMG OPS CHECK GOOD IAW AMM 24-25-00/501. LIGHT LENS COVERS INSTALLED

Part: SKIN — SCRATCHED (L2 DOOR) · airframe 99,302 hrs · 23,415 cycles

MOVE CREW FOUND SCRATCHES ON LEFT SIDE FORWARD OF DOOR 2L JUST AFT OF WING SCAN LIGHT LENS. AS REQUESTED BY ENGNR AND SM, PERFORMED NDT ULTRASONIC PER NTM PT 4-00-04-02, OLYMPUS 35 THICKNESS MEASUREMENT. PICTURES OF RESULTS ATTACHED BLENDED THE SKIN GOUGES IN ACCORDANCE WITH 757-200 .SRM 53-00-01 AD1 FROM AVO 8998 DISPOSITION 4 THE REFERENCE THAT WAS USED FOR BLENDING OUT THE GOUGES WERE ACP HFEC INSP IAW 757 NTM PT 6 51-00-19. IAW AVO 8998 STEP3. NO DEFECTS NOTED AT THIS TIME. ADDITIONAL DAMAGE NOTED REF AVO8998 DISPOSITION 1. ACCOMPLISHED DVI OF INTERNAL STRUCTURE AND EXTERNAN NO ACCOMPLISHED STEPS 7,8,10&11 OF AVO 8998 REV A. C/W REQ INSPECTION OF STEPS 7-11 OF AVO 8998 REV A. PERFORMED EWIS AROUND REPAIR AREA AND REMOVED FASTNERS THAT WERE BLENDED OVER PER STEP 9, DENT SHOWED NO EVIDENCE OF PULLED ,LOOSE,MISSING,OR ENLONGATED FASTENER HOLES PER STEP 12 OF AVO 8998 REV A. 8998. OF THOSE HOLES TO ENSURE NO CRACKS EXIST PER STEP 14 OF AVO REMOVED FASTENERS COMMON TO REPAIR AREA. NEED TO ACCOMPLISH HFEC NEED QC TO PERFORM EXTERIOR SPOT PROBE MFEC INSP FOR ANY EVIDENCE OF CRACKS ALONG THE CHEM-MILLED STEP(S) OF SKIN PANEL OR IF ACCESSIBLE ON INTERIOR, PERFORM HFEC AT CHEM-MILLED STEP RADIUS PER STEP 15 OF AVO 8998. A. C/W REQUIRED INSPECTION OF STEP 1, 9, 12, AND 13 REF AVO8998 REV REQUIRE MATERIAL VERIFICATION FOR NEW REPAIR DOUBLER OF 0.063" THICK 2024-T3 CLAD SHEET PER AVO8998 AVO8998 REV. A OF STEPS A.(17) COLD FORM BACK THE DENTED SKIN TO IT''S ORIGINAL CONTOUR PER

Part: UNKNOWN — NOISE (CABIN) · airframe 96,240 hrs · 22,671 cycles

CREW REPORTS LOUD NOISE UNDER FLOOR JUST AFT OF FLIGHT DECK DOOR. TRIED TURNING OFF RH AND LH RECIRC FANS NO HELP OPBLM HANN FLIGHT CREW REPORTED VERBALLY TO TECH SOUND COMING FWD OF FLT DECK DOOR. INSPECTED BOTH E&E COMPARTMENTS FOUND NO OBVIOUS DAMAGE WHEN RUNNING A/C SYSTEMS. OPENED GEAR DOORS AND INSPECTED NOSE GEAR COMPARTMENT FOUND NO OBVIOUS DEFECTS. INSPECTED AUXILLARY EQUIPMENT COOLING FAN BLADES WHILE OFF, LOCATED ON LH ADD EMP:U181242 SIDE OF E&E FOUND NO DEFECTS PRESSURIZED AIRCRAFT USING APU ONLY. AT 2.9 PSI NOTICED LOUD HUM NOTICED. PER FIM21-20-00-810-801 STEP E NOTE 2 NEEDTO CONTINUE ANDVIBRATION FROM BEHIND CAPTAINS SEAT. NO THUMP SOUND WAS ADD EMP:109227 AT STEP G TECH SUPPORT UPDATE-RECOMMENDS LOOKING AT OVERBOARD EXHAUST VALVE, SUSPECT IT IS NOT FULLY CLOSING WHEN ABOVE 2.8 DELTA P CAUSING THE STATED VIBRATION THE FLAPPER IS AERODYNAMICALLY INTERIOR AND EXTERIOR SURFACES OF THE OVERBOARD EXHAUST VALVE IS SHAPED TO "FLY SHUT" WHEN THE DIFFERENTIAL PRESSURE BETWEEN THE GREATER THAN 2.8 PSI. PRESURIZED AIRCRACT AT 3.0 GOT LOUD HUM NOISE AT STATION 340 BUL FOUND. VENT BEHIND CAPTAINS SEAT.CHECKED INTEGRITY OF DUCT NO DEFECTS B ZONE DUCT TEMP FLIGHT DECK.ASLO NOISE IN FLIGHT DECK AFT FLOOR -05-414-008 STILL NEEDS PRESSURIZATION TO CONFIRM FIX ROTABLE PARTS CHANGE WAS INDICATED - TT # 1078695 SN OFF 6037 VALVE, AIR SHUT OFF 75-2125-9-0001 6037 ON 75-2125-9-0001 5752 REPLACED EQUIPMENT COOLING OVERBOARD EXHAUST VALVE REF AMM 21-58 FOUND BROKEN HOSE CLA

Part: SHIM — MIGRATED (LT WING) · airframe 95,610 hrs · 22,536 cycles

SUPPORT TASK EA 5720-0341 REV A STEP 3 OF THIS EA SHIM MIGRATED 0.360, SHIM MIGRATION GREATER THEN 0.20 REQUIRES REPAIR THRU REF ST ENG N/R 0070121 ACCOMPLISHED ECRA 5720-03131 REV. A ON LH WING DRAG FITTING SHIM MIGRATION AND UPPER SKIN BLEND PART 1 INTERIM REPAIR AREA FREE OF FOD, WORK WAS ACCOMPLISHED BY V919728 CREATED DIP TO ACCOMPLISH PERMANENT REPAIR ON OR BEFORE 24 MONTHS FROM 09/17/19. PLANNING TO CONTACT ENGINEERING AFTER 22 MONTHS BUT BEFORE 23 MONTHS FOR THE PERMANENT REPAIR. APPROVED FOR DIP TO ACCOMPLISH PERMANENT REPAIR ON OR BEFORE 24 MONTHS FROM SEPT 17, 2019. PLANNING TO CONTACT ENGINEERING AFTER 22 MONTHS BUT BEFORE 23 MONTHS FOR PERMANENT REPAIR REF ECRA 5720-03131 TOMC-APPROVAL FROM SC1ELBYC COMMENT QC REVIEW RECORDS UPDATE QC REVIEW INIT: >22MONTHS<23MONTHS PLN/ENG T/A: 24 MONTHS....BK245861

Part: FRAME — CORRODED (FUSELAGE) · airframe 95,610 hrs · 22,536 cycles

SUPPORT TASK EA5310-07027 (AD 2017-24-10) DURING PREPARATION (CL EANING) FOUND EXFOLIATION CORROSION ON FRAME OUTTER CHORD UNDER DOOR SWITHCH FITTING AT STA 1380 BETWEEN STR 23R AND STR 24R AS MARKED 034-036. REF ENG N/R 0069975 CHECKED LIMITS TO FRAME AT STA 1380 BETWEEN S-23R AND S-24R; L=4 .5 W=3.0 D=.080. OUT OF LIMITS IAW SRM 53-00-07 FIG 101 DETAIL II. REPAIRED FRAME IAW SRM 53-00-07 REPAIR 2 FI G 201 PG201. THIS IS REPAIR IS A CATEGORY B INSPECTION THRESHOLD IS 37,500 AIRFRAME FLT CYCLES, INTERVALS OF EVERY 3000 FLT CYCLES, CURRENT CYCLES IS 22,536.

Part: GIRT BAR — WORN (L2 DOOR) · airframe 95,610 hrs · 22,536 cycles

SUPPORT TASK EA 2560-02123 REV D L2 DOOR GIRT BAR FAILED MESUREMENT CHECK AT FWD POSITION. REF ST-SAA NR 0069614. REMOVED AND REPLACED L2 DOOR GIRT BAR IAW AMM 25-66-10-402-022 AREA FREE OF FOD.

Part: GIRT BAR — WORN (L4 DOOR) · airframe 95,610 hrs · 22,536 cycles

SUPPORT TASK EA 2560-02123 REV D L4 DOOR GIRT BAR FAILED MEASURE MENT CHECK AT FWD AND AFT POSITION. REF ST-ENG N/R 0069612 L4 DOOR GIRT BAR FAILED MEASUREMENT CHECK AT FORWARD AND AFT POSITION. REMOVED AND REPLACED L4 DOOR GIRT BAR IAW AMM 25-66-10-002-001 AND 25-66-10-402-022 ADJUSTMENT TEST IAW AMM 52-11-25/501 TEST OK.

Part: STRUCTURE — DENTED (AFT CARGO DOOR) · airframe 95,610 hrs · 22,536 cycles

(B757-06-3-0356) AFT CARGO DOOR FWD LWR CORNER HAS A DENT AS MAR KED 50-072. REF. ST. ENGINEERING N/R 0069791 REMOVED AND REPLACED AFT CARGO DOOR SEAL DEPCORNER PN NO. 654NO2 44-633 BATCH NO. 0003531247 PO NO SOS 1920075 IAW B757-200 SRM 5 1-40-02 AND B757-200 IPC 52-34-01-22. AREA IS FREE OF FOD. THIS IS TRANSCRIBED INFORMATION ACCOMPLISHED AND RECORDED ON ST-SAA N R0069791. WORK ACCOMPLISHED BY V922187 AND INSPECTED BY V921092.

Part: SKIN — DAMAGED (BS 418) · airframe 95,610 hrs · 22,536 cycles

FOUND DAMAGE AT STA 418 STR 14R TO 15R. DENT MEASURE .040 DEPTH BY 1.2 BY .7 A/Y=17.5 PER SRM 53-0 0-01. REPAIRED IAW SRM 53-00- 01 REPAIR 29. THIS IS A CATAGORY B REPAIR.

Part: ALTIMETER — STICKS (COCKPIT) · airframe 88,781 hrs · 21,103 cycles

STBY ALT STUCK AT 37500 FOR 500 FEET DURING DESCENT B4 IT BROKE FREE. REMOVED UNSERVICEABLE STBY ALT AND INSTALLED SERVICEABLE STBY ALTIMETER REF AMM 34-13-06-404-002, OPS CHECKED NORMAL.

Part: WIRE HARNESS — FAULTY (EMERGENCY LIGHTS) · airframe 88,421 hrs · 21,031 cycles

EXTERIOR EMERGENCY LIGHTING SYSTEM HAS ONE INOPERATIVE LIGHT LOCATED ON AFT CARGO DOOR. REPLACED WIRE HARNESS D41168P IAW WDM 33-27-21. OPS CHECKED NORMAL

Part: COVER — DETACHED (EMERGENCY LIGHT) · airframe 88,284 hrs · 21,003 cycles

L1 DOOR EXIT SIGN COVER DETACHED. INSTALLED THE COVER.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHTS) · airframe 84,353 hrs · 20,221 cycles

LEFT HALF OF EMERGENCY LIGHTS UNARMED LIGHT INOPERATIVE. REPLACED THE LAMP, OPS NORMAL.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHTS) · airframe 84,202 hrs · 20,192 cycles

EMERGENCY LIGHTS INOPERATIVE AT POSITIONS R1 & R2 DOORS. LT OVERWING, AND AFT DOOR. REPLACED THE LAMPS AND PERFORMED AN OPS CHECK, FOUND NORMAL IAW AMM 33-51-00, AND AMM 33-51-06.

Part: SKIN — DAMAGED (BS 1500) · airframe 84,202 hrs · 20,192 cycles

DURING PREFLIGHT, FOUND A DENT AT BS 1500 BELOW STRINGER 22R, FOUND WITHIN LIMITS IAW SRM 53-00-01.

Part: FRAME — DAMAGED (BS 1360) · airframe 84,202 hrs · 20,192 cycles

FOUND A DENT ON THE FRAME BS 1360 STRINGERS 25-26L OUT OF LIMITS IAW SRM 53-00-07 FIG 101, CUTOUT DAMAGED AREA, FABRICATED A J REPAIR IAW SRM 53-00-07 REP 5 FIG 201. TREATED, PRIMED, TOP COATED DOUBLER AND FRAME AREA IAW AMM 51-21-04, 51-21-14 AND 51-21-15. INSTALLED THE REPAIR IAW SRM 53-00-07 REP 5 FIG 201.

Part: FRAME — DENTED (BS 1400) · airframe 84,202 hrs · 20,192 cycles

FRAME DENTED AT BS 1400, STRINGERS 25-26L. FOUND OUT OF LIMITS IAW SRM 53-00-07 FIG 101, CUTOUT DAMAGED SECTION OF FRAME. FABRICATED AN ANGLE SECTION REPAIR IAW SRM 53-00-07 REP J FIG 201. TREATED, PRIMES AND TOP COATED DOUBLER REPAIR ON FRAME IAW SRM 53-00-07 REP 5 FIG 201.

Part: FRAME — DENTED (BS 600) · airframe 84,202 hrs · 20,192 cycles

FRAME DENTED AT BS 600 STRINGER 24-25L. INSTALLED A FRAME REPAIR IAW SRM 53-00-07, FIG 201 REPAIR 5.

Part: FRAME — DAMAGED (BS 680) · airframe 84,202 hrs · 20,192 cycles

FRAME DENTED AT BS 680, STRINGERS 23-24R. CUTOUT FRAME DAMAGED SECTION, FABRICATED A REPAIR IAW SRM 53-00-07 REPAIR 5 FIG 201 DETAIL I.

Part: FRAME — CRACKED (BS 1580 BULKHEAD) · airframe 84,202 hrs · 20,192 cycles

VISUAL CRACK INDICATION ON BS 1580 FRAME AT OVERHEAD BIN RAIL ATTACH BRACKET BETWEEN STRINGERS 8 AND 9L. CUTOUT DAMAGED SECTION OF FRAME, TRIMMED OUT, FABRICATED A REPAIR IAW SRM 53-00-07 REP 1 FIG 202 HEAT TREATED IAW 5602, TREATED AND PRIMED REPAIR AND CUTOUT IAW AMM 51-21-04 AND 51-21-14. INSTALLED THE REPAIR IAW SRM 53-00-07 REP 1 FIG 202.

Part: BEAM — CORRODED (BS 876) · airframe 84,202 hrs · 20,192 cycles

LEFT CREASE BEAM INNER ANGLE CORRODED AT BS 876. INSTALLED A REPAIR IAW SRM 53-00-1 3, FIG 201.

Part: BEAM — NOT REPORTED (BS 760) · airframe 84,202 hrs · 20,192 cycles

FABRICATED REPAIR AT CABIN FLOOR LT CREASE BEAM ANGLE BS 760 INBD IAW SRM 53-00-13, 53-30-13 AND AMM 51-21-14-370-801. FABRICATED REPAIR IAW SRM 53-00-13, 53-30-13 AND AMM 51-21-14-370-801 .

Part: CIRCUIT BREAKER — POPPED (COCKPIT) · airframe 82,390 hrs · 19,837 cycles

ONCE AUTO THROTTLE WAS SELECTED, RT IRU EICAS ON DC WITH RT FMC FAILURE. CB BUS RT SECT 2 POPPED U080913 FOR INPUT ONLY NORMAL AFTER RESET. REPLACED CB P6 PANEL 115VAC BUS R SECT 2 PRECAUTIONARY WDM 24-51-22.

Part: OVEN — DIRTY (GALLEY) · airframe 80,126 hrs · 19,427 cycles

FOR SDR REPORTING, SDR REPORTED FOR SMOKE FROM OVEN. FOOD RESIDUE, OVEN PLACARDED.

Part: LANDING GEAR — FIRE · airframe 80,014 hrs · 19,402 cycles

ON TAXI OUT ACFT BEHIND REPORTED SMOKE & FLAMES FROM LT MAIN. RUCKS REPORTED NO FLAMES & SMOKE, NO FIRE INDICATION ON EICAS. APPEARS BRAKE LOCKED UP ON LT REAR OTBD, MAIN TEMP WENT TO 3, EICAS ANTI-SKID LIGHT CAME ON AFTER STOP. FOUND NR 5 TIRE BEARING & CAP MISSING. INSTALLED AXLE, INSTALL BOTH AXLE SLEEVES, REPLACED NR 5 BRAKE TRANSDUCER & INSTALLED NR 6 TRANSDUCER, INSTALL NR 5 & 6 BRAKES & TIRES.

Part: LIGHT — INOPERATIVE (EXTERIOR) · airframe 73,887 hrs · 18,279 cycles

SUPPORT TASK R4 EXTERIOR EMERGENCY LIGHT INOPERATIVE. RELAMPED R4 EXTERIOR EMERGENCY LIGHT & PERFORMED OPERATIONS CHECK FOUND NORMAL AS PER IAW B757 AMM 33-51-06 & 33-51-00.

Part: UNKNOWN — MALFUNCTIONED (TE FLAP) · airframe 67,132 hrs · 17,136 cycles

ON APPROACH GOING TO FLAP POS 25 GOT THE T/E FLAP DISAGREE ICAS. RAN CHECK LIST AND LANDED FLAPS 20 T-S IAW FIM 27-51-00-815-809 PERFORMED A BITE OF THE FSEU NO FAULTS NOTED AT THIS TIME. RAN FLAPS DOWN AND UP. NO FAULTS NOTED. OK TO CONTINUE.

Part: LENS — DETACHED (L2 DOOR) · airframe 64,342 hrs · 16,653 cycles

EMERGENCY EXIT SIGN AT DOOR 2L DETACHED EXIT SIGN RE-ATTACHED.

Part: ACTUATOR — LEAKING (EVAC SLIDE) · airframe 62,841 hrs · 16,369 cycles

RT OVERWING SLIDE FAILED OPS CHECK, ACTUATOR LEAKING (WILL NOT HOLD PRESSURE) REMOVED AND REPLACED RT OVERWING ESCAPE SLIDE ACTUATOR REF AMM 25-65-05. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1446488 S/N OFF 00967 IPC REFERENCE NUMBER 25-65-05-01 ACTUATOR, WING OFF 19-2565-9-0004 0967 ON 19-2565-9-0004 1189.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 62,838 hrs · 16,368 cycles

LT FUSELAGE SKIN DENTED AT EXISTING PATCH REPAIR. LOCATION STA 590-600 JUST UNDER STR 16. INSTALLED REPAIR DOUBLERS AND INIATED DIP07709 TO "ACCOMPLISH INSPECTIONS PRIOR TO 35,800 TOTAL AIRCRAFT CYCLES PER ECRA 5330 -04075, PART 2, CONTACT ENGINEERING AFTER 33,000 FLIGHT CYCLES BUT BEFORE 34,000 FLIGHT CYCLES FOR INSPECTION REQUIREMENTS. (SEE ALL WIPS BELOW FOR WORK ACCOMPLISHED) //QC// "ACCOMPLISH INSPECTIONS PRIOR TO 35,800 TOTAL FLIGHT CYCLES PER ECRA 5330-04075, PART 2. PLANNING IS TO CONTACT ENGINEERING AFTER 33,000 FLIGHT CYCLES BUT BEFORE 34,000 FLIGHT CYCLES FOR THE INSPECTION REQUIREMENTS. DIP CTL NUMBER 07709.

Part: BEAM — CORRODED (FUSELAGE) · airframe 62,838 hrs · 16,368 cycles

BELTFRAME AT STA 345 HAS CORROSION FROM STA BL-0 TO LBL-24. CORROSION OUT OF LIMITS. REWORKED CORRODED SECTION OF THE FLOORBEAM REF SRM 523-10-51. TREATED AND APPLIED TO UPPER CHORD WHERE REWORKED. FILLED VOIDS WITH BMS5-95. ACCOMPLISHED ALL REWORK PROCEDURE, REF EC/RA 5320-02000.

Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 59,256 hrs · 15,703 cycles

(MULT-33-3-0004) EMERGENCY LIGHTS ASSOCIATED WITH POWER SUPPLY M730 INOP IN FWD CABIN AREA. REMOVED AND REPLACED M730 EMERGENCY LIGHT POWER SUPPLY REF MM 33-51-07. OPS CHECKS NORMAL.

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 58,298 hrs · 15,523 cycles

EMERGENCY FLASHLIGHT AT L1 DOOR NOT TESTING. REMOVED AND REPLACED FLASHLIGHT BATTERY. OPS CHECK GOOD.

Part: HOSE — RUPTURED (HYD SYSTEM) · airframe 53,265 hrs · 14,571 cycles

LOST LEFT HYDRAULIC QUANTITY INFLIGHT LANDED AT 227,440 POUNDS VERTICAL SPEED - 264. FOUND DOWNLOCK ACTUATOR HYDRAULIC LINE RUPTURED ON RIGHT-HAND SIDE. REMOVED AND REPLACED RIGHT-HAND DOWNLOCK ACTUATOR, PRESSURE AND RETURN LINES REF AMM 20-10-10. LEAK CHECK GOOD. PERFORMED CONDITIONAL 1 REF AMM 29-11-00. NO DEFECTS NOTED. PERFORMED PHASE 1 OVERWEIGHT INSPECTION REF AMM 05-51-35. NO DEFECTS NOTED, A/C OK FOR CONTINUED SERVICE.

Part: FLOORBEAM — CORRODED (STA) · airframe 39,592 hrs · 11,773 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT STA 720, RBL 20.5 TO RBL 50.5. REPAIRED IAW SRM 53-00-51.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 39,592 hrs · 11,773 cycles

INSPECTION FOUND INTERCOSTAL CORRODED BETWEEN BS 680 AND 700, RBL 56, WL 208.1. THE INTERCOSTAL WAS REPLACED IAW SRM 51-40-02.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 39,592 hrs · 11,773 cycles

INSPECTION FOUND SEAT TRACK SECTIONS CORRODED BETWEEN STA 720 AND 740, AT RBL 25 AND RBL 45.5. THE SEAT TRACK SECTIONS WERE REPLACED IAW SRM 51-40-02 AND 51-40-05.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 39,592 hrs · 11,773 cycles

INSPECTION FOUND GALLEY SUPPORT INTERCOSTAL CORRODED AT BS 365-377, RBL 60. THE INTERCOSTAL WAS REPLACED IAW SRM 51-40-02.

Part: LIGHT — INOPERATIVE (ROW 32)

THE EMERGENCY PATH LIGHTING ON SEATS 11, 32, AND 34 WERE FOUND INOPERATIVE. THE MODULE AT SEAT 11 WAS TIGHTENED. THE CONNECTOR AT ROW 34 WAS RECONNECTED. THE LIGHT FIXTURE AT ROW 32 WAS REMOVED AND REPLACED. OPERATION OF THE EMERGENCY PATH LIGHTING CHECKED GOOD.

Part: SKIN — DENTED (BS 600)

INSPECTION FOUND FUSELAGE SKIN DENTED AT STA 600 BETWEEN STRINGERS 18L AND 19L. THE SKIN WAS REPAIRED IAW ECRA 5331-01051.

Part: CHORD — CRACKED (BS 1147)

INSPECTION FOUND A 1 INCH CRACK IN LT MLG WHEEL WELL CHORD AT STA 1147. THE CHORD WAS REPLACED IAW BOEING DRAWING 149N7222.

Part: PANEL — DELAMINATED (LEFT WING)

INSPECTION FOUND LT WING PANEL NR 551BB DELAMINATED. THE PANEL WAS REMOVED, REPAIRED AND REINSTALLED IAW SRM 51-70-05 AND 57-51-01.

Part: PANEL — DELAMINATED (WS 370)

INSPECTION FOUND RT FIXED L/E PANEL DELAMINATED OUTBOARD OF PYLON AT WS 370. THE PANEL WAS REMOVED, REPAIRED AND REINSTALLED IAW SRM 51-70-08 AND MM 51-40-02.

Part: PANEL — DELAMINATED (RIGHT WING)

INSPECTION FOUND RT WING INBOARD L/E PANEL NR 611HB DELAMINATED. THE PANEL WAS REMOVED, REPAIRED AND REINSTALLED IAW SRM 51-70-08 AND 51-41-01.

Part: CHANNEL — CRACKED (RT MLG WW)

INSPECTION FOUND A .25 INCH CRACK IN RT MLG WHEEL WELL FORWARD SEAL RETAINER SUPPORT CHANNEL. THE SEAL RETAINER SUPPORT CHANNEL WAS REPAIRED IAW SRM 51-70-11.

Part: PANEL — DELAMINATED (LEFT WING)

INSPECTION FOUND LT WING LEADING EDGE PANEL NR 511DB DELAMINATED AT ATTACHMENT HOLES. THE PANEL WAS REMOVED, REPAIRED AND REINSTALLED IAW SRM 51-70-04 AND MM 51-40-02.

Part: PANEL — DELAMINATED (WS 320)

INSPECTION FOUND LT FIXED L/E PANEL DELAMINATED OUTBOARD OF PYLON AT WS 320. THE PANEL WAS REMOVED, REPAIRED AND REINSTALLED IAW SRM 51-70-08 AND MM 51-40-02.

Part: SKIN — DELAMINATED (WS 590)

INSPECTION FOUND LT FIXED LEADING EDGE PANEL DELAMINATED AT WS 590 BETWEEN SLATS NR 1 AND 2. THE L/E PANEL WAS REPAIRED IAW SRM 51-70-07.

Part: SKIN — GOUGED (LT TE FLAP)

INSPECTION FOUND LT WING OUTBOARD FLAP INBOARD UPPER PANEL GOUGED BY SPOILER FITTING BOLTS. THE FLAP UPPER PANEL WAS REPAIRED IAW SRM 51-70-10, PAGE 10 AND ECRA 5753-01062.

Part: SKIN — DELAMINATED (WS 397)

INSPECTION FOUND THE LT FIXED LEADING EDGE PANEL DELAMINATED AT WS 397. THE L/E PANEL WAS REPAIRED IAW SRM 51-70-07.

Part: SKIN — GOUGED (RT TE FLAP)

INSPECTION FOUND THE RT WING OUTBOARD FLAP INBOARD UPPER PANEL GOUGED BY SPOILER FITTING BOLTS. THE FLAP UPPER PANEL WAS REPAIRED IAW SRM 51-70-10, PAGE 10 AND ECRA 5753-01062.

Part: SKIN — GOUGED (BS 620-640)

INSPECTION FOUND FUSELAGE SKIN GOUGED BETWEEN STA 620 AND 640 AT S16L AND S17L. AN EXTERNAL DOUBLER REPAIR WAS INSTALLED IAW SRM 53-00-01, FIGURE 204. A DIP WAS ISSUED TO INSPECT BLIND RIVETS EVERY 2500 FLIGHT CYCLES AND TO REPLACE THE REPAIR NO LATER THAN 12,00 FLIGHT CYCLES PER SRM 53-00-01, FIGURE 204.

Part: SKIN — CRACKED (BS 595)

A PERMANENT FLUSH REPAIR TO FUSELAGE SKIN AT STA 595, BETWEEN S17L AND S16L WAS INSTALLED IAW ECRA 5331-01050. THE AREA HAD PREVIOUSLY BEEN REPAIRED FOR A .375 CRACK AND HAD BEEN PLACED ON DIP.

Part: SKIN — DAMAGED (BS 780)

INSPECTION FOUND IMPACT DAMAGE TO FUSELAGE SKIN PANEL AT STA 780, STRINGER 15L. A FLUSH REPAIR WAS INSTALLED IAW SRM 53-00-01.

Part: BEAM — DAMAGED (CARGO DOOR)

INSPECTION FOUND IMPACT DAMAGE TO AFT CARGO DOOR LOWER EDGE BEAM AND FORWARD CORNER PIECE. THE LOWER EDGE BEAM AND FORWARD CORNER PIECE WERE REPLACED IAW BOEING DRAWING 143N6603 AND SRM 52-30-02.

Part: BEAM — DAMAGED (CARGO DOOR)

INSPECTION FOUND IMPACT DAMAGE TO AFT VERTICAL EDGE BEAM, LOWER BEAM, AFT AND FORWARD CORNER PIECES OF FORWARD CARGO DOOR. THE BEAMS AND CORNER PIECES WERE REPLACED IAW BOEING DRAWING 143N6603 AND SRM 52-3-02.

Part: ANGLE — CORRODED (BS 1376-1443)

INSPECTION FOUND AFT HOLD THRESHOLD ATTACHMENT ANGLE CORRODED AT BS 1376.5 TO 1443.5. THE ATTACHMENT ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 53-60-53.

Part: PANEL — CRACKED (LT WING)

INSPECTION FOUND A 9 INCH CRACK IN LT WING UPPER SURFACE OF LEADING EDGE COMPOSITE PANEL AT SLAT NR 3, NR 4 STA OSS 421. REPAIR PLIES WERE CUT OUT AND INSTALLED IAW ECRA 5720-01661. A DIP WAS ISSUED TO INSPECT THE REPAIR EVERY SIX DAYS UNTIL PERMANENT REPAIR IS ACCOMPLISHED WITHIN 30 DAYS OR 50 CYCLES.

Part: PANEL — CRACKED (RT WING)

INSPECTION FOUND A 3, 8 AND 2.5 INCH CRACK IN RT WING UPPER SURFACE OF LEADING EDGE COMPOSITE PANEL AT SLAT NR 7, NR 8, STA OSS 421. REPAIR PLIES WERE CUT OUT, SANDED, AND INSTALLED IAW ECRA 5720-01661. A DIP WAS ISSUED TO INSPECT THE REPAIR EVERY SIX DAYS UNTIL PERMANENT REPAIR IS ACCOMPLISHED WITHIN 30 DAYS OR 50 CYCLES.

Part: WIRE — SHORTED (CABIN)

INSPECTION FOUND EMERGENCY TRACK LIGHTS INOPERATIVE FROM ROW 15 TO 25. MAINTENANCE FOUND A SHORTED WIRE UNDER SEAT 17 THAT WAS BLOWING FUSE ON BATTERY CHARGER. THE WIRE WAS SPLICED AND THE FUSE WAS REPLACED. OPERATION OF THE EMERGENCY TRACK LIGHTS WAS RESTORED.