N13113

Part: LIGHT — NO DISCREPANCY (ZONE 200) · airframe 107,040 hrs · 25,548 cycles

EMERGENCY LIGHTS - OPERATIONAL TEST WITH THE TEST SWITCH PROCEDURE - EMERGENCY LIGHT INOP ABOVE SEAT 3DEF/ 4DEF. REPLACED LIGHT ASSY NO HELP, NEED MORE TIME TO T/S, REQUEST MEL 3351A APPROVED COMPLIED MEL 3351A, STICKER APPLIED. PERFORMED EMERGENCY LIGHTS OPERATIONAL TEST PER AMM 33-51-00-715-039, EMERGENCY LIGHTS OPS CKS GOOD. PLACARD REMOVED. PIC ADDED.

Part: GIRT BAR — FOD (ZONE 800) · airframe 106,288 hrs · 25,396 cycles

DOOR 4L WILL NOT ARM AND WILL NOT NOW DISARM ARM. FOUND DEBRIS IN THE GIRT BAR CAUSING TO DOOR TO HAVE ISSUES ARMING AND DIS-ARMING, WATCHED SLIDE RENDER SAFTEY CHECKLIST. OPS CHECK OF DOOR PER AMM 25-66-01.

Part: IDG — FAULTY (NR 1 ENGINE) · airframe 106,008 hrs · 25,341 cycles

IN FLT AT FL330 LEFT GEN DRIVE EICAS LT CAME ON. 30 SEC LATER LE FT GEN DISCONNECTED. DEBRIEFED CREW - IN CRUISE APPROX FL310 NR. 1 GEN DRIVE EICAS MESSAGE AND LIGHT ILLUMINATED. GEN AUTOMATICALLY DISCONNECTED. BPCU BITE INDICATES MULTIPLE FAULTS, INCLUDING HIGH RISE TEMP, OVERTEMP REPLACE IDG, DISCONNECT TRIP, LOW FREQ. TRIP, ETC. FOUND OIL LEVEL INDICATING OK, DIFFERENTIAL PRESSURE/ BYPASS INDICATOR ON FILTER HOUSING IS TRIPPED. UPDATED L/P TO REQUIRE SFR TO SDR REMOVED AND REPLACED # 1 ENG IDG AS PER AMM 24-11-01-424-002. PERFORMED OPS AND LEAK CHECK . NO FAULTS OR LEAK NOTED AT THIS TIME

Part: GIRT BAR — FOD (ZONE800) · airframe 105,345 hrs · 25,205 cycles

DOOR 1R WONT ARM APPEARS TO BE BINDING REMOVED DEBRIS OBSTRUCTING GIRT BAR MOVEMENT, CLEANED AREA AND OPS CHECK OPENING, CLOSING AND ARMING DOOR 1R SLIDE. CHECKS GOOD AS PER AMM 52-11-00, 52-71-00

Part: UNKNOWN — ODOR (CABIN) · airframe 104,765 hrs · 25,078 cycles

FA REPORTS BURNING PLAST IC TYPE SMELL FROM AREA 2L LAV AND LAST ROW OF 1 ST AND START OF ECONOM CREW REPORTED SMELL DISSAPATED UPON RETURNING TO THE GATE. RAN BOTH PACKS AND BOTH ENGINES. NO BURING ODERS NOTED. AC OK FOR SERVICE.

Part: FILTER — CLOGGED (ZONE 200) · airframe 104,765 hrs · 25,078 cycles

FA REPORTED SAME SMELL AS DID FLIGHT DECK AND P AX. DSCRBD AS IROINIG SMELL OF IRONING CLOTHES T/S PER FIM 21-00-01/301. AFTER RUNNING BOTH ENGINES AT HIGH POWER WITH PACKS ON AND RECIRC FANS ON COULD NOT DETECT ANY UNUSUAL SMELL IN HE COCKPIT OR THE MAIN CABIN. TOMC REQUEST, REPLACED THE LH AND RH RECIRC FAN HEPA FILTERS REF AMM 21-25-02-404-174, OPS CHKS GOOD RAN PACKS NO ABNORMAL SMELLS IN CABIN.P PERFORMED ENGINE RUN AND REPLACED THE LH AND RH RECIRC HEPA FILTERS REF FIM 21-00-01-301. RAN BOTH PACKS SEVERAL TIMES , NO ABNORMAL SMELLS IN CABIN.

Part: ELEC CONNECTOR — FAULTED (RT ENGINE) · airframe 104,791 hrs · 25,085 cycles

A/T DIDNT ENGAGE ON TKF RH ENG CAME UP ONLY TO 1.3EPR 50N1/LH EN G CAME UP TO 1.6ERRCREW DE-BRIEF. TOP SPEED REACHED WAS 90 KNOTS. AUTO THROTTLE DID NOT ENGAGE, CREW MANUALLY RAISED THROTTLES TO REDUCED TAKE OFF. WITH THROTTLES MATCHED E1 100% N1 AND E2 AT 50% N1 AND 1.4 EPR. FOLLOWING FIM 71-06 TASK 810 - BITE CHECK OF #2 EEC SHOWS FAULT CODE 35 "LVDT AND TORQUE MOTOR FAULT DETECTED DURING POWER UP". REF. FIM 7321 TASK 802. AND EEC FAULT CODE TABLE 301 REF. 73-21-00/301 ADD FAULT: 35 ACCOMPLISHED EEC2 BITE PER FIM 73-21- FT 802 AND VERIFIED FAULT CODE 35. NO OTHER CODES DISPLAYED. WORKING FIM 73-21-00/301 FOUND COMNNECTOR D1370 NOT ENGAGED TO RECEPTACLE. INSPECTED CONNECTOR. NO DEFECTS FOUND. CLEANED AND REINSTALLED. NEED TO ACCOMPLISH ENGINE RUNUP TEST FOR REPAIR CONFIRMATION. ACCOMPLISHED MCDP AUTO THROTTLE TEST 10 PER AMM TASK 22-00-02-742-011. TEST GOOD. ACCOMPLISHED #2 ENGINE TAKEOFF POWER TEST # 13 AND ACCELERATION/ DECCELERATION TEST # 11 PER AMM 71-00-00. TEST GOOD. RECHECKED EEC FOR FAULTS. FAULT 35 PRESENT ON F0 AND F3. REINSPECTED FFG 2 CONNECTORS. FOUND D1370 LOOSE AGAIN. NEED TO REPLACE CONNECTOR. CORRECTION ON TRIM MOTOR POSITION TRANSMITTER CONNECTOR NUMBER. SHOULD READ D1372. REPLACED CONNECTOR D1372P REF WDM71-51-22 AND SWPM 20-63-00. NEED RUN ACCOMPLISHED #2 ENGINE TAKEOFF POWER TEST # 13 PER AMM 71-00-00. TEST GOOD, RECHECKED CONNECTOR PLUG VERIFIED SECURED, ACPD SEVERAL GROUND IDLE STARTS AND CLEARED EEC AND VERIFIED NO FAULTS REF MM 73-21-00

Part: COFFEEMAKER — FAILED (ZONE 900) · airframe 104,763 hrs · 25,077 cycles

FORWARD GALLEY LEFT COFFEE MAKER DOES NOT WORK AND ELECTRICAL BURN SMELL WHEN TURNED ON FOUND COFFEMAKER HOTPLATES ON WITH POTS ON AND NO LIQUID. TURNED OFF HOTPLATES, RAN A COUPLE OF BREW CYCLES. OPS CHKS NORMAL, NO ELECTRICAL SMELL.

Part: LANYARD — OUT OF POSITION (ZONE 800) · airframe 104,661 hrs · 25,051 cycles

DOOR 1L WONT ARM FOUND LANYARD STUCK IN DOOR GIRT BAR MECHANISM. REPOSITIONED LANYARD BACK IN PLACE, ARMED AND DISARMED DOOR SEVERAL TIMES AND NO DEFECTS NOTED. USED RENDER SAFE CHECKLIST AS REQUIRED. ADD EMP:U246571

Part: ENGINE — VIBRATION (RIGHT) · airframe 104,579 hrs · 25,033 cycles

R ENG N1 VIBRATION REACHED 5.0 FOR 20 MINS PER CREW, AT FL340 IN WEATHER AND RIGHT BEFORE THEY GOT A VIBRATION INDICATION, THEY SMELT OZONE, WHICH THEY SAID WAS THE FIRST INDICTION OF CRYSTAL ICING. VIB LEVEL AT THIS POINT WAS 2.5. FIRST STEP IN QRH WAS ENG HEAT WHICH THEY TURNED ON. BY THE TIME THEY WERE HALFWAY THROUGH QRH, VIB LEVEL WAS UP TO 5 AND THEY FELT WHAT THEY DESCRIBED AS A RUMBLE. THEY TURNED TO GET OUT OF THE WEATHER AND THE VIBE LEVEL SLOWLY CAME DOWN. THEY WERE ABEAM MIA AND VIBES WERE DOWN TO 3.5. PERFORMED ICE CRYSTAL ICING ENGINE INSPECTION REF AMM 05-51-60-200-802-002 . FOUND NO DAMAGE TO THE NOSE CONE, LP COMPRESSOR BLADES , ENGINE INLET COWL OR EXHAUST SYSTEM. PERFORMED VIBRATION SURVEY TEST 6 REF AMM 71-00-00-715-327-R03 ALL OF THE VIBRATION NUMBERS WERE ALL WITHIN LIMITS SEE ATTACHED PICTURE. E2 EA 7231-01258 OP1 FAN BLADE LUBE TASK CARD 7231-01258-001 ACCOMPLISHED IN MCO MARCH 06, 2025, PER JOB CARD 19-0572-8-0140 VIBE SURVEY ACCOMPLISHED ALL CHECKS GOOD.

Part: GIRT BAR — FOD (ZONE 800) · airframe 104,405 hrs · 24,994 cycles

DOOR 1R WILL NOT ARM CLEARED DEBRI UNDER GERT BAR, ARMED AND DISARMED DOOR , OP'S CK NORMAL,

Part: CONTACT — DIRTY (ZONE 800) · airframe 104,297 hrs · 24,971 cycles

DOOR 1L SLIDE LIGHT NOT ILLUMNATING VERIFIED GIRT BAR MECHANISM FOR FREEDOM OF MOVEMENT AND SECURITY. REF TASK 25-66-10-202-039. CLEANED CONTACTS. SLIDE ARMED. OK TO CONTINUE.

Part: CONE — MISSING (ZONE 400) · airframe 104,115 hrs · 24,923 cycles

GAP FAIRING AFT SIDE OF #1 PYLON IB SIDE JUST ABOVE ENGINE EXAUST CONE MISSING/ DAMAGED REPLACED MISSING GAP FAIRING WITH NEW AT AFT SIDE OF #1 PYLON IB PER IPC 71-00-02-04.

Part: LAMP — INOPERATIVE (ZONE 200) · airframe 103,579 hrs · 24,790 cycles

EMERGENCY LIGHTS (USING CONTROL SWITCHES) OPERATIONAL CHECK {MULT-33-3-0001} - R/H EMERGENCY OVERWING LIGHT INOP REMOVED AND REPLACED OVERWING EMERGENCY LIGHT IN REFERENCE WITH AMM 33-51-06. OPS CHECK GOOD

Part: LAMP — INOPERATIVE (ZONE 200) · airframe 103,579 hrs · 24,790 cycles

EMERGENCY LIGHTS (USING CONTROL SWITCHES) OPERATIONAL CHECK {MULT-33-3-0001} - #2 L/H DOOR EMERGENCY SLIDE LIGHT INOP REMOVED AND REPLACED LIGHT IN REFERENCE WITH AMM 33-51-06. NO HELP. ALSO CHECKED BATTERY PACK FUSES FOR CONTINUITY, ALL 4 FUSES ARE GOOD. REMOVED AND REPLACED L2 DOOR EMERGENCY SLIDE LIGHT AS PER AMM 33-51-06-962-001-001, CLEANED DIRT INSIDE LIGHT BULB CONTACT. OPS CHK GOOD

Part: ELEC CONNECTOR — UNSECURE (TRIM MOTOR SENSO) · airframe 103,579 hrs · 24,790 cycles

REPEAT WRITE UP RTO 80 KTS ENGINE 2 WILL NOT GO ABOVE 1.5 EPR REFERENCE FIM 71-06 TASK 807 FOR TROUBLESHOOTING. TOMC-MEREDITH CARRIED OUT TROUBLE SHOOTING AS PER FIM 73-21-00-301. EEC BITE CARRIED OUT PER FIM 73-21-00-902-001-R01, BITE SHOWS FAULT CODE 35 (LVDT TORQUE MOTOR FAULT DURING POWER UP). ALL WIRING CHECKS CARRIED OUT WITH NORMAL RESULTS. DURING TROUBLE SHOOTING CONNECTOR D1372 (TRIM MOTOR POSITION SENSOR T5027) FOUND TO BE VERY LOOSE. CONNECTOR REFITTED CORRECTLY AND TEST 13 TAKE OFF POWER ASSURANCE TEST CARRIED OUT AS PER AMM TASK 71-00-00-715-223-R03. ENGINE POWER VERIFIED TO BE NORMAL. INSPECTED RT ENGINE FUEL FLOW GOVERNOR CONNECTOR D1372 INSTALLATION AND ALL CHECKED GOOD WITH REF TO AMM 73-21-00/401.

Part: ACTUATOR — FAILED (SLAT SYS) · airframe 102,510 hrs · 24,572 cycles

LEADING EDGE SLAT DISAGREE AFTER TAKEOFF, FLAPS STUCK BETWEEN UP & 1 UNTIL ALT SYS USE. PERFORMED T/S WITH TECH SUPPORT AND FIM 27-51 FAULT TREE 805 SLAT DISAGREE, FOUND MESSAGE #310, DURING INSPECTION FOUND L/E PDU OVERLOAD INDICATOR ON LT & RT PDU TORQUE LIMITER TRIPPED, RESET INDICATOR, INSPECTED LT WING ROTARY ACTUATORS OVERLOAD INDICATOR SPRING FOUND NOT TRIPPED, INSPECTED RT WING ROTARY ACTUATOR OVERLOAD INDICATOR SPRING, FOUND OVERLOAD INDICATOR SPRING TRIP AT RT #9 INBD ROTARY ACTUATOR. PERFORMED VISUAL INSPECTION OF ROTARY ACTUATOR #9 SLAT INBOARD OVERLOAD SPRING IMDICATOR FOUND TRIPPED PER FIM 27-81 FT 803 BLOCK 18. NEED TO R & R ROTARY ACTUATOR PER FIM. COMPLIED WITH RII STEPS FOR INSTALLATION OF #9 SLAT INBD ROTARY ACTUATOR OVERLOAD SPRING INDICATOR IAW AMM 27-81 18-424-019 UP TO & INCLUDING STEP 3(E)(5)(Q). REMOVE ROTARY ACTUATOR FOR LE SLATS #9. IAW AMM R & R #9 SLAT INBOARD ROTARY ACTUATOR OVERLOAD SPRING INDICATOR. CONTINUE WITH INSTALLATION. IAW AMM 27-81-18-424-019 UP TO & INCLUDING STEP 3(E)(5)(Q). COMPLETED INSTALLATION OF #9 SLAT ROTARY IB ACTUACTOR IAW AMM 27-81-18-424-019 FROM STEP 3(E)(6) TO THE END, OPS CHKD GOOD.

Part: LAVATORY — HANDLER ERROR (ALL) · airframe 100,825 hrs · 24,201 cycles

ALL LAVS OVER SERVICED. SERVICED LAVS AS REQUIRED. OPS CHECK GOOD REF AMM TASK 12-17-01-613-001 ADD EMP:U348948

Part: TRANSMITTER — FAULTY (LE SLAT) · airframe 100,614 hrs · 24,147 cycles

LE SLAT DISAGREE. INSPECTED INSTALLATION, AND CORRECT RIG OF LH LEADING EDGE SLAT TRANSMITTER, REF AMM 27-58-01-501, NO DEFECTS NOTED. LOCKING UNLOCK REPLACED LEFT HAND LEADING EDGE SLAT POSITION TRANSMITTER. OPS CHECK GOOD. REF. AMM 27-88-01-024-001. TRANSMITTER, LE OFF 19-2781-9-0009 0113 ON 19-2781-9-0009 3120 TRANSMITTER, LE OFF 19-2781-9-0009 0113 ON 0000 DURING TROUBLESHOOTING EXISTING FAULTS ON FSEU 1 KEPT DISPLAYING HARD FAULT OF RH AND LH SLAT TRANSMITTER WITH FAULT CODES 222 AND 223. FSEU 2 AND 3 SHOWED NO FAULTS. AFTER RPL AND RIG OF LT SLAT TRANSMITTER FSEU 1 SHOWS NO FAULTS AND FLAP SLATS OPS NORMAL WITH NO EICAS MSGS. REF FIM 27-51 FAULT TREE 805. PARTS USED: 1114686,QTY :1 ROTABLE PARTS CHANGE WAS INDICATED - TT # 1114686 SN OFF 0113.

Part: ACCUMULATOR — UNKNOWN (HYDRAULIC MOTOR) · airframe 99,087 hrs · 23,788 cycles

HYDRAULIC MOTOR GENERATOR ACCUMULATOR GAUGE IS AT "0" PSI IN THE HYDRAULICS BAY ACCESS. PLEASE SEE ATTACHED PICTURES. HYDRAULIC MOTOR GENERATOR INOP, COMPLIED WITH MEL. COMPLIED WITH MEL. ADD EMP: U162957, U116736 DISPATCH DESK: 3392 NAME: KB DATE: 05-SEP-23- NOC DESK: 757 NAME: ERIC DATE: 05-SEP-23- TOMC APPROVES HYDRAULIC MOTOR GENERATOR (HMG) INOPERATIVE AND DEACTIVATED PER MEL 2425A SERVICED HMG ACCUMULATOR, REF. AMM-12-15-06-613-001-002. ACCUMULATOR PRESSURE DROPPED 700PSI IN LESS THAN 30 MINS. R&R HMG ACCUMULATOR AS PER AMM24-25-01 WITH NO HELP. FOUND ACCUMULATOR AIR PRESSURE LINE LEAKING. R&R ACCUMULATOR, OPS CHECK GOOD. NO LEAKS NOTED. REF. IPC24-25-52-01, ITEM# 145. DDP REVERSED, MEL CLOSED. PARTS USED: 1275147,QTY :1 ROTABLE PARTS CHANGE WAS INDICATED - TT # 1275147 SN OFF 1605 ACCUMULATOR, AS OFF 19-3241-9-9001 1605 ON 19-3241-9-9001 8972.

Part: SKIN — DAMAGED (STA 580) · airframe 98,691 hrs · 23,701 cycles

DAMAGE OCCURRED TO AIRCRAFT FROM BOARDING STAND LEFT SIDE OF FUSELAGE 10 INCHES AFT OF STA 580 AT STRINGER 20L. .057" WIDTH 1.10" A/Y=19.2 ALLOWABLE A/Y=30. REPAIRED AREA IAW 0100-0191. B757-200 SRM 53-00-01-2R-28 REPAIR 28. ACCOMPLISHED ON AMES NR EVALUATED DAMAGE AND FOUND TO BE OUT OF B757-200 SRM LIMITS IAW B757-200 SRM 53-00-01-1A-1 ALLOWABLE DAMAGE 1 DETAIL III DEPTH.

Part: FLANGE — CORRODED (APU RAM AIR INL) · airframe 98,691 hrs · 23,701 cycles

FLANGE CORRODED ON THE APU RAM AIR INLET DOOR BOX REMOVED AND REPLACED FWD STRAP AT THE APU RAM AIR INLET DOOR BOX AT STA 1785. THE SSFR WAS COMPLETED AND UP DATED.

Part: FRAME — CRACKED (STA 760) · airframe 98,691 hrs · 23,701 cycles

FRAME CRACKED AT STA 760 BELOW STR 8-R UPPER CABIN AT ATTACH BRACKET RIVET HOLE FOR OVER HEAD STOWAGE BINS. V931857

Part: FRAME — CRACKED (STA 760) · airframe 98,691 hrs · 23,701 cycles

CRACK ON FRAME WEB ATTACH BRACKET FOR OVERHEAD BIN @ STA 760 L/H @ STRNGR 8. D. OSBORNE V921218 (M). CRACK ON FRAME WEB ATTACH BRACKET FOR OVERHEAD BIN @ STA 760 L/H @ STRNGR 8. D. OSBORNE V921218 (M). ADD EMP:V931845

Part: UNKNOWN — CRACKED (STA 1120) · airframe 98,691 hrs · 23,701 cycles

FRAME ATTACH BRACKET FOR OVERHEAD BIN IS CRACKED @ STA. 1120 L/H STRINGER 8. D. OSBORNE V921218 (M). FRAME ATTACH BRACKET FOR OVERHEAD BIN IS CRACKED @ STA. 1120 L/H STRINGER 8. D. OSBORNE V921218 (M). ADD EMP:V921218

Part: UNKNOWN — CORRODED (STA 720) · airframe 98,691 hrs · 23,701 cycles

CORROSION FOUND ON TOP OF FLOOR BEAM AT STA 720 BL 20R. DOCUMENTED ON AMES NR 159536-0200-0147. CORROSION FOUND ON TOP OF FLOOR BEAM AT STA 720 BL 20R. DOCUMENTED ON AMES NR 159536-0200-0147. ADD EMP:V921493

Part: FRAME — CRACKED (STA 1120 LH STRI) · airframe 98,691 hrs · 23,701 cycles

FRAME ATTACH BRACKET FOR OVERHEAD BIN IS CRACKED @ STA. 1120 L/H STRINGER 8. D. OSBORNE V921218 (M). FRAME ATTACH BRACKET FOR OVERHEAD BIN IS CRACKED @ STA. 1120 L/H STRINGER 8. D. OSBORNE V921218 (M). ADD EMP:V921218

Part: FRAME — CRACKED (STA 760 LH STRNG) · airframe 98,691 hrs · 23,701 cycles

CRACK ON FRAME WEB ATTACH BRACKET FOR OVERHEAD BIN @ STA 760 L/H @ STRNGR 8. D. OSBORNE V921218 (M). CRACK ON FRAME WEB ATTACH BRACKET FOR OVERHEAD BIN @ STA 760 L/H @ STRNGR 8. D. OSBORNE V921218 (M). ADD EMP:V931845

Part: FLOORBEAM — CORRODED (STA 720 BL 20R) · airframe 98,691 hrs · 23,701 cycles

CORROSION FOUND ON TOP OF FLOOR BEAM AT STA 720 BL 20R. DOCUMENTED ON AMES NR 159536-0200-0147. CORROSION FOUND ON TOP OF FLOOR BEAM AT STA 720 BL 20R. DOCUMENTED ON AMES NR 159536-0200-0147. ADD EMP:V921493

Part: WARNING LIGHT — ILLUMINATED (L HYD QTY) · airframe 97,061 hrs · 23,297 cycles

LEFT HYD QTY EICAS MSG WHEN ACFT WAS ON THE RUNWAY AND THROTTLES MOVED UP. SHOWED .27 THEN RECOVERED. PER CREW THE ACFT WAS 3 KNOTS OR LESS WHEN EVENT OCCURRED.NO LOW PRESSURE OR OVERHEAT INDICATIONS. PERFORMED LEFT HYDRAULIC SYSTEM QUANTITY CHECK. REF AMM 29-33-00-735-001, SUB TASK 29-33-00-615-034. OPERATES NORMAL.

Part: SHUTOFF VALVE — LOOSE (RH ENG) · airframe 95,992 hrs · 23,061 cycles

R BLEED EICAS ON TAKEOFF WHEN THRUST SET. REJECTED T/O AT 50KTS FOUND LOOSE MUSCLE LINE ON HIGH PRESSURE SHUTOFF VALVE. SECURED LINE RAN ENGINE AT MULTIPLE POWER SETTING NO FAULTS FOUND. OPS NORMAL ADD EMP:012816

Part: SEAT TRACK — CRACKED (STA1540LBL44) · airframe 95,049 hrs · 22,860 cycles

SEAT TRACK AT STA 1540 LBL 44 FOUND CRACKED REPORTED BY V921297 REMOVED AND REPLACED SEAT TRACK @ STA 1540 LBL 44 IAW UAL EC/RA 5300-02793, B757 SRM 51-40-02 PARA 7, AND BOEING B757 DWG 146N51 20 & REA 47485FAB01 REF NR 142974-0200-0060 FOR DETAILS

Part: LIFE RAFT — UNLACED (LT OVERWING) · airframe 88,205 hrs · 21,398 cycles

FOUND THE LEFT OVERWING EMERGENCY EXIT RAFT, ROW 21 ABC, LACING UNDONE. REPLACED THE RAFT.

Part: THRUST REVERSER — FAILED (RIGHT) · airframe 86,666 hrs · 21,082 cycles

RIGHT REVERSER FAILED TO DEPLOY ON LANDING, SEVERAL ATTEMPTS MADE. DEPLOYED ON TAXIWAY. BLED HYDRAULIC SYSTEM FOR THE NR 2 ENGINE THRUST REVERSER IAW AMM 78-31-20-085-R04. THRUST REVERSER IS OPERATING NORMAL.

Part: SMOKE DETECTOR — FALSE ACTIVATION (LAVATORY) · airframe 86,255 hrs · 20,998 cycles

DURING CLIMB EICAS DISPLAYED LAVATORY SMOKE. AFT RIGHT LAVATORY SMOKE ALARM SOUNDED. NO SMOKE OR ODOR PRESENT. EMERGENCY DECLARED. REMOVED AND REPLACED SMOKE AFT RIGHT REF TASK 26-14-00-735-001 OPS CK OK.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 83,932 hrs · 20,524 cycles

CORROSION ON THE FWD CARGO COMPARTMENT FLOOR STRUCTURE INTERCOSTAL LOWER ATTACH ANGLE BETWEEN BS 740 AND BS 760 RBL 10.75. REMOVED UNSERVICEABLE INTERCOSTAL FWD CARGO BS 740-760 RBL 10.75 IAW SRM 51-40-02 PAR 4, FABRICATED NEW INTERCOSTAL AND INSTALLED IAW SRM 51-30-01 FIG 8, 51-40-02 PAGE 4 AND 7.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 83,932 hrs · 20,524 cycles

FLOOR WEB AT BS 1400 RT BL 70 HAS SURFACE CORROSION. EVALUATED CORROSION ON FLOOR WEB AT BS 1400 RBL 70 AND FOUND SMALL AREA OF 100% MAX LOSS. REMOVED, FABRICATED, LOCATED , DRILLED AND INSTALLED NEW -46 WAS IAW SRM 51-40-02 PAR 7 FIG 1 2 AND DRAWING 146N5590.

Part: SKIN — GOUGED (BS 1580) · airframe 83,932 hrs · 20,524 cycles

LEFT FUSELAGE SKIN BS 1580 ABOVE STRINGER 15L HAS TWO GOUGES AND ALSO DENTED. CUT AND REMOVED DAMAGED AREA, AND REPAIRED IAW SRM 53-00-01, REPAIR 3, FIG 201.

Part: DOUBLER — DAMAGED (BS 600) · airframe 83,932 hrs · 20,524 cycles

EXTERNAL SKIN DOUBLER DAMAGED BS 608 ABOVE 17L. THE DOUBLER WAS REMOVED AND REPLACED IAW SRM 53-00-01, REPAIR 3, FIG 201, REPAIR STEPS 1-5, REPAIR 3.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 83,932 hrs · 20,524 cycles

CORROSION FOUND IN AFT CARGO COMPT BILGE INTERCOSTAL BETWEEN BS1320 AND 1340 LBL11 VALUATED CORROSION ON AFT CARGO INTERCOSTAL BTWN BS1320 & 1340 LBL 11. FOUND TO BE OUT OF ALLOWABLE LIMITS IAW SRM 53-00 -04 FIG 101 DETAIL 2. REMOVED AND REPLACED INTERCOSTAL IAW SRM 51-40-02 PAR 4 AND 7 FIGS 3,8 AND 12.

Part: STRAP — CORRODED (BS720 RBL15-45) · airframe 83,932 hrs · 20,524 cycles

CORROSION ON THE MAIN CABIN FLOOR STRUCTURE REPAIR DOUBLER BS 720 BETWEEN RBL 15.5 AND RBL 45.5 UPPER SURFACE EVALUATED CORROSION ON MAIN CABIN FLOOR STRUCTURE REPAIR DOUBLER BS 720 AT RBL 15.5 TO RBL 45.5. ORIGINAL MAT THICKNESS IS .071 MATERIAL REMOVED .059 AND IS FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED .3 STRAP IAW DWG NR 95-030 AND SRM 51-40-02 PAR 7.

Part: FLOOR SUPPORT — BROKEN (BS 480-500) · airframe 83,932 hrs · 20,524 cycles

MAIN CABIN FLOOR SUPPORT UPPER ATTACH ANGLE IS BROKEN BETWEEN BS 480 AND 500 RBL. 10.5. REPAIRED IAW SRM 51-40-02 PARA 7 FIG 12, AND SRM 51-40-05, PARA 4 FIG 1.

Part: UNKNOWN — ODOR (OVEN) · airframe 82,262 hrs · 20,191 cycles

AFT OVEN 412 GETTING AN ELECTRICAL ODOR WITH OVEN POWERED OFF. PULLED THE CIRCUIT BREAKER NO CHANGE. OVEN REMOVED AND AREA INSPECTED WITH NO FINDINGS OR ODOR. ALL OVEN CONTROLLER BOX UNPLUGGED AND CIRCUIT BREAKER PULLED AND COLLERED. OTHER GALLEY EQUIPMENT TESTED FOR SEVERAL MINUTES AND NO EVIDANCES VEN DEFFERED IAW NEF 2525P. OF ELECTRICAL ODOR.

Part: INDICATOR — FAILED (ALTIMETER) · airframe 81,904 hrs · 20,121 cycles

AT 100 FEET AGL DURING DEPARTURE, THE LEFT ALTIMETER FAILED. OFF FLAG IN VIEW UNTIL APPROX 100 FEET. REMOVED AND REPLACED THE LT ADC IAW AMM 34-12-01. REMOVED AND REPLACED CAPTAIN`S ALTIMETER IAW AMM 34-13-01. NO OFF FLAG PRESENT.

Part: LINE — LEAKING (HYDRAULIC SYS) · airframe 81,474 hrs · 20,035 cycles

LEFT HYD QTY INDICATES ZERO. EICAS MESSAGES LT HYD QTY AND POWER TRANSFER UNIT ILLUMINATED. LEFT HYD SYSTEM WAS SELECTED OFF WHEN LEFT HYD QTY READ 30%. REMAIN OFF FOR THE REMIANING OF THE FLIGHT. BOTH DOWNLOCK LINES REPLACED, SERVICED HYDRAULICS, CHECKED LINES FOR LEAKS, NONE NOTED, ACTUATED ALL FLIGHT CONTROLS, RESERVICED HYDRAULICS TO FULL.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 80,285 hrs · 19,803 cycles

RIGHT ENG REVERSER LIGHT ILLUMINATED ON THE TAKEOFF R LL. INITIATED & COMPLETED A LOW SPEED REJECTED TAKEOFF AT 70 KNTS, OFF TIME WAS 1122 Z. COOLED BRAKES FOR 10 MINS BEFORE TAXIING. PLACARDED NR 2 ENG THRUST REVERSER INOPERATIVE. MX PLACED REVERSER ON MEL 7831F, LOCKED OUT IN FWD THRUST POSITION.

Part: WARNING LIGHT — INTERMITTENT (COCKPIT) · airframe 74,863 hrs · 18,759 cycles

INTERMITTENT APU DOOR LIGHT, APU STOPPED. EMER DECLARED. RAN APU SEVERAL TIMES NO FAULTS NOTED. R & R ECU PRECAUTION. ACFT PLACED ON ETOPS VERIFICATION LP 7928692.

Part: BULB — INOPERATIVE (EMERGENCY LIGHTS) · airframe 72,723 hrs · 18,348 cycles

EMERGENCY ESCAPE PATH LIGHTS HAVE BURNED OUT BULBS AT L2 DOOR LOWER PROXIMITY FWD, ROW 20 LT OVERWING LOWER PROXIMITY EXIT SIGN OVER THE OVERWING LT HAS 14 BURNED OUT BULBS. REPLACED BULBS IAW AMM 33-51-10, TESTED OK.

Part: SKIN — DENTED (BS 510) · airframe 72,723 hrs · 18,348 cycles

DENT IN LOWER LT FUSELAGE BETWEEN STRINGERS 26 - 27L BS 510. FOUND TO BE WITHIN SRM 53-00-01 LIMITS. ACCOMPLISHED DOUBLER REPAIR BETWEEN BS 503 - 513 & STRINGERS 26 - 28L IAW ECRA 5331-01843.

Part: CONNECTOR — INOPERATIVE (EMERGENCY LIGHTS) · airframe 72,723 hrs · 18,348 cycles

FIRST CLASS SEAT SHROUD EMERGENCY LIGHT INOPERATIVE. R & R CONNECTOR. PERFORMED OPS TEST OF EMERGENCY LIGHTS, CHECKED NORMAL IAW SWPM 20-61-28 & AMM 33-51-00.

Part: FRAME — DENTED (FUSELAGE) · airframe 72,723 hrs · 18,348 cycles

AFT CARGO PIT BS 1540 DENTED BETWEEN STRINGER 26L - 27L. FABRICATED DOUBLER FRAME REPAIR AT BS 1540 BETWEEN STRINGER 26L - 27L. TREATED & PRIMED TOP COATED CYCLES IAW SRM 53-00-07 FIG 201 TABLE II. REPAIR DOUBLER IAW SRM 51-20-01, INSTALLED NEW FRAME REPAIR IAW SRM 53-00-02 CATEGORY B REQUIREMENTS.

Part: FRAME — DENTED (FUSELAGE) · airframe 72,723 hrs · 18,348 cycles

AFT CARGO PIT BS 1460 FRAME HAS MULTIPLE DENTS BETWEEN STRINGER 25L - 26L. FABRICATED DOUBLER FRAME REPAIR AT BS 1460 BETWEEN STRINGER 25L - 26L. TREATED & PRIMED TOP COATED REPAIR CYCLES AFTER THAT IAW SRM 53-00-07 FIG 201TABLE II IR DOUBLER AS PER SRM 51-20-01. INSTALLED NEW FRAME REPAIR IAW SRM 53-00-02 CATEGORY B.

Part: SKIN — DENTED (FUSELAGE) · airframe 72,723 hrs · 18,348 cycles

STR15L TO STR16L AREA, FUSELAGE SKIN DENT MARK FOUND. FOUND TO BE WITH IN LIMITS IAW SRM 53-00-01. ACCOMPLISHED REPAIR DOUBLER AS USING LFEC AS PER B757-2 SRM 53-00-01, REPAIR, TABLE V, PER B757-2 SRM 53-00-01 FIG 201, REPAIR 3, DETAIL I.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHT) · airframe 68,603 hrs · 17,580 cycles

EMERGENCY LIGHTS BY DOOR 1R INOPERATIVE. FOUND ALL LIGHTS POWERED BY CHARGER M730 INOPERATIVE. REPLACED M730 CHARGER IAW AMM 33-51-07-862-054.

Part: SKIN — DENTED (BS 1486) · airframe 39,394 hrs · 11,729 cycles

DENT IN SKIN AT BS 1486 BETWEEN S23- 24R. DENT IS APROX .025" DEEP APROX 1" IN DIA. REMOVED DAMAGED SECTION OF SKIN. FABRICATED DOUBLER. TREATED AND PRIMED AND INSTALLED IN REF TO SRM 53-00-01, FIG 201.

Part: SKIN — PUNCTURED (L4 DOOR) · airframe 61,324 hrs · 16,287 cycles

L4 ENTRY DOOR UPPER HINGE CUTOUT INNER SKIN HAS PUNCTURE. TRIMMED OUT DAMAGE AND INSTALLED REPAIR DOUBLER IAW EC/RA 520-02239,STEPS 1 THRU 12.

Part: BATTERY — FAULTY (MAIN) · airframe 64,298 hrs · 16,819 cycles

STATUS MESSAGE "MAIN BAT CHGR". REPEAT WRITE-UP. AIR RETURN TO EWR. PERFORMED T/S PER FIM 24-31-00-815-802 PG 2; BLOCK 19. HARD FAULT REMOVED. REPLACED MAIN & APU BAT. AS PRECAUTIONARY ACMX MEASURE PER TOMC MAA #7993 IAW 777-200 AMM TASK 24-31-01 & 03. ALSO R&R'D MAIN BAT. SHUNT BLOCK PN MS91586-7AS PRECAUTIONARY. SYSTEM TEST GOOD. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1474345 S/N OFF 05981 TT # 1485303 S/N OFF 02005 BATTERY, AIRCRAFT OFF 99-2431-9-9001 5981 ON 99-2431-9-9001 0424 BATTERY, AIRCRAFT OFF 99-2431-9-9001 2005 ON 99-2431-9-9001 6796.

Part: CHARGER — INOPERATIVE (CABIN) · airframe 63,477 hrs · 16,673 cycles

EMERGENCY EXIT LIGHTS BETWEEN ROWS 7 & 14 LEFT INOP. FAULT TRACED TO INOP BATT CHARGER AT 9DEF. CHARGER REPLACED OPS CHECK OK IAW 33-51-07. SER NO OFF 36675 ON 41040 TAG NO GRN12374 9.

Part: SKIN — DENTED (FUSELAGE) · airframe 61,324 hrs · 16,287 cycles

LOWER EXTERNAL FUSELAGE, DENT JUST AFT & TO THE LEFT OF FWD ACCESS DOOR STA 253 LBL 13 REPAIRED DENT REF EC/RA 5330-04113 PLACED ON DIP FOR DTA PER ECRA 5330-04113 ORIG, PART 1, STEP 9, ACCOMPLISH A PERMANENT REPAIR WITHIN 24 CALENDAR MONTHS OF MARCH, 16 2011. NOTE TO PLANNING. CONTACT ENGINEERING AFTER 22 CALENDAR MONTHS BUT WITHIN 23 CALENDAR MONTHS FOR INSPECTION REQUIREMENTS.

Part: SKIN — DAMAGED (TE FLAP) · airframe 61,324 hrs · 16,287 cycles

LEFT WING NR 3 FLAP TRACK AFT FAIRING FWD I/B MOUNTING BRACKET HOLES IN FLAP ARE ELONGATED. REPAIRED MOUNTING HOLES IN FLAP AND REPLACED BRACKET PER EC/RA 5750-04368 STEPS 1 THRU 18. INITIATED DIP PER EC/RA 5750-04368 STEP 19.

Part: SKIN — DENTED (FUSELAGE) · airframe 61,324 hrs · 16,287 cycles

LT LOWER EXTERNAL FUSELAGE, 2 DENTS SIDE BY SIDE AT STA 430 AT 22L COMPLIED WITH ECRA 5330-04110 STEPS A, B AND C 1 THROUGH 8. INITIATED DIP TO ACCOMPLISH A PERMANENT REPAIR PER PART 3 WITHIN 24 MONTHS. PER ECRA 5330-04110 ORIG, PART 1, STEP C, 8, ACCOMPLISH A PERMANENT REPAIR PER PART 3 WITHIN 24 CALENDAR MONTHS. NOTE TO PLANNING. CONTACT ENGINEERING AFTER 22 CALENDAR MONTHS BUT BEFORE 23 CALENDAR MONTHS FOR PERMANENT REPAIR INSTRUCTIONS.

Part: STRUCTURE — CRACKED (R1 DOOR) · airframe 61,324 hrs · 16,287 cycles

DOOR HAS A .25 INCH CRACK AT EDGE OF LWR AFT LIGHTENING HOLE. TRIMMED OUT DAMAGE AND INSTALLED REPAIR DOUBLER PER EC/RA 5210- 02238,STEPS 1 THRU 15.

Part: SKIN — DENTED (FUSELAGE) · airframe 61,324 hrs · 16,287 cycles

LT LOWER EXTERNAL FUSELAGE, DENT AT STA 459 STR 23 LT COMPLETED ALL STEPS OF REPAIR TO LOWER FUSELAGE SKIN AT STA 459 STR 23 LT REF SRM 53-00-01 REPAIR 2.

Part: SUPPORT BRACKET — UNKNOWN (R1 DOOR) · airframe 45,229 hrs · 12,977 cycles

R1 DOOR WILL NOT CLOSE AND LATCH. REPAIRED IAW AMM 52-11-04.

Part: STRINGER — CORRODED (BS 1467) · airframe 39,394 hrs · 11,729 cycles

INSPECTION FOUND FLOOR STRINGERS AT CROSS STRAP IN AFT BAG BIN CORRODED AT STA 1467, LBL 26. THE CORROSION WAS REMOVED AND ONE AREA WAS OUT OF LIMITS. A REPAIR WAS INSTALLED IAW SRM 51-70-11, FIGURE 1. THE OTHER AREAS WITHIN LIMITS WERE TREATED AND PRIMED IAW SRM 53-00-53.

Part: FLOORBEAM — CORRODED (BS 1640) · airframe 39,394 hrs · 11,729 cycles

INSPECTION FOUND UPPER AND LOWER SURFACE OF FLOORBEAM CORRODED AT STA 1640, RBL 8. THE FLOORBEAM WAS REPAIRED IAW SRM 53-00-51.

Part: CREASE BEAM — CORRODED (BS 1600) · airframe 39,394 hrs · 11,729 cycles

INSPECTION FOUND CREASE BEAM INNER CHORD CORRODED AT STA 1600, LBL 63. A REPAIR DOUBLER WAS INSTALLED IAW SRM 51-70-12 AND ECRA 5310-04501.

Part: PAN — CORRODED (STA 1340-1620) · airframe 39,394 hrs · 11,729 cycles

INSPECTION FOUND AFT LAV PAN CORRODED AT AFT SIDE, STA 1340-1620, RBL 2 TO RBL 20. THE CORRODED LAV SERVICE PAN DOUBLER WAS REMOVED AND A NEW PAN DOUBLER WAS INSTALLED IAW SRM 51-40-02 AND ENGINEERING DRAWING 146N3650.

Part: FLOORBEAM — CORRODED (STA 1640) · airframe 39,394 hrs · 11,729 cycles

INSPECTION FOUND FLOORBEAM UPPER CHORD CORRODED AT STA 1640, RBL 57. THE CORROSION WAS BLENDED OUT AND REPAIRED IAW ECRA 5321-01316.

Part: FLOOR SUPPORT — CORRODED (STA) · airframe 37,197 hrs · 11,244 cycles

INSPECTION FOUND CABIN FLOOR SUPPORT CORRODED AT STA 720, RBL 44 TO RBL 48. REPAIRED IAW SRM 53-00-51, REPAIR 3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 37,197 hrs · 11,244 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 720, LBL 45.50 TO 51.50. REPAIRED IAW SRM 53-00-51, REPAIR 3.

Part: SEAL · airframe 29,318 hrs · 8,294 cycles

NOISE FROM L1 DOOR. INSTALLED SEAL IN TRACK TOP FORWARD DOOR

Part: SLAT — DELAMINATED (#6 POSITION) · airframe 29,237 hrs · 8,265 cycles

INSPECTION FOUND #6 SLAT WEDGE SKIN DELAMINATED. THE #6 SLAT WAS REMOVED AND REPLACED IAW MM 27-81-01.

Part: FUSE — BLOWN (BATTERY PACK) · airframe 29,228 hrs · 8,263 cycles

THE EMERGENCY ESCAPE PATH LIGHTING ON SEATS FROM ROW 15ABC TO 25ABC WERE FOUND INOPERATIVE. MAINTENANCE FOUND THAT THE LOAD FUSE HAD RUPTURED AT BATTERY PACK M10699. THE LOAD FUSE WAS REPLACED AND EMERGENCY ESCAPE PATH LIGHTING TEST WAS GOOD IAW MM 33-51-00.

Part: PANEL — CRACKED (WS 421-471)

INSPECTION FOUND A 10 AND 6 INCH CRACK IN LT WING FIXED LEADING EDGE PANEL AFT OF NR 4 L/E SLAT, WS 421-471. A FIBERGLASS REPAIR WAS INSTALLED IAW ECRA 5720-01668. A DIP WAS ISSUED TO ACCOMPLISH A PERMANENT REPAIR WITHIN 18 MONTHS OR NEXT C-CHECK.

Part: PANEL — CRACKED (WS 421-471)

INSPECTION FOUND A 6 AND 7 INCH CRACK IN RT WING FIXED L/E PANEL AT WS 421-471. REPAIRED IAW ECRA 5720-01668. A DIP WAS INITIATED TO REINSPECT THE AREAS EVERY 1000 HOURS AND ACCOMPLISH A PERMANENT REPAIR WITHIN 18 MONTHS OR NEXT C-CHECK.

Part: INTERCOSTAL — CORRODED (BS 1620-1640)

INSPECTION FOUND INTERCOSTAL ON FLOOR STRUCTURE CORRODED AT BS 1620-1640. THE INTERCOSTAL WAS REMOVED AND REPLACED IAW BOEING DRAWINGS 146N5300 AND 143N5554-6.

Part: SEAT TRACK — CORRODED (BS 377-440)

INSPECTION FOUND I/B SEAT TRACK CORRODED AT BS 377-400, LBL 25 AND O/B SEAT TRACK WAS CORRODED AT BS 377-440, LBL 45. THE SEAT TRACKS WERE REPLACED IAW SRM 53-10-00 AND BOEING DRAWING 141N5130.

Part: SKIN — DENTED (BS 610)

IMPACT DAMAGE (1)ON LEFT SIDE FUSELAGE STATION 610 BETWEEN STRINGERS 15 AND 16 LEFT. REPAIRED PER SRM 53-00-01 FIG 208.

Part: COMPRESSOR — FAILED (NR 2 ENGINE)

THE NR 2 ENGINE EXPERIENCED COMPRESSOR STALL ACCOMPANIED BY HIGH EGT JUST AFTER TAKEOFF FROM LAS. THE AIRCRAFT WAS RETURNED TO LAS WHERE IT LANDED WITHOUT INCIDENT. THE NR 2 ENGINE WILL BE REMOVED AND REPLACED. THE HIGH PRESSURE COMPRESSOR DAMAGE REPORTED DURING THE BORESCOPE IN LAS WAS CONFIRMED ON MODULE STRIP. A 90 DEGREE ARC OF STAGE 2 ROTOR PATH LINING HAD EVACUATED AND MOST PROBABLY CAUSED THE DAMAGE FROM STAGE 2 DOWNSTREAM. THIS CONDITION CAUSED A REDUCTION IN COMPRESSOR EFFICIENCY THAT RESULTED IN A SIGNIFICANT REDUCTION IN SURGE MARGIN THUS INCREASING THE POTENTIAL EXPOSURE TO A SURGE CONDITION.

Part: ENGINE — FAILED (NR 2)

THE NR 2 ENGINE FAILED ON FINAL APPROACH TO LAX. THE ENGINE SHUT DOWN WITH NO FIRE WARNING. THE AIRCRAFT LANDED WITHOUT INCIDENT. THE NR 1 ENGINE WAS REMOVED AND REPLACED DUE TO SUBSEQUENT ENGINE PROBLEMS. REVEALED DURING ENGINE INSPECTION.

Part: TRANSMISSION — INOPERATIVE (NR 8 TE FLAP)

THE TRAILING EDGE FLAP DISAGREE EICAS APPEARED WHILE GOING FROM UP TO FIVE DEGREES. THE FLAPS WERE LOWERED ALTERNATELY IAW THE TRAILING EDGE FLAP DISAGREE CHECKLIST AND A 20 DEGREE FLAP LANDING WAS MADE AT EWR. MAINTENANCE FOUND THE NR 8 FLAP TRANSMISSION TORQUE LIMITER PIN POPPED. THE NR 8 FLAP TRANSMISSION WAS REMOVED AND REPLACED IAW MM 27-51-17, OPERATION AND INDICATIONS CHECKED GOOD.

Part: BRAKE — LEAKING (RT MLG)

THE EICAS MESSAGE LEFT HYDRAULIC QUANTITY STATUS PAGE SHOWED .46RF DURING GEAR EXTENSION FOR LANDING. THE RIGHT HYDRAULIC QUANTITY LOW CAME ON SHOWING .73RF DURING TAXI IN. MAINTENANCE FOUND THE NR 8 BRAKE LEAKING. THE NR 8 BRAKE WAS REMOVED AND REPLACED. THE LEFT AND RIGHT HYDRAULIC SYSTEMS WERE SERVICED TO FULL, LEAK AND OPERATIONAL CHECKS WERE GOOD.