N277WA

Part: BATTERY PACK — FAULTED (CABIN)

EMERGENCY LIGHT TEST FAIL: NR 1 BATTERY PACK FAULTED. REMOVED AND REPLACED NR 1 BATTERY PACK.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 47,213 hrs · 8,392 cycles

DURING T-10 FOUND EMERGENCY FLOOR LIGHTING INOP FOR B ZONE ROW 14 THRU 18 LT SIDE.

Part: BATTERY PACK — FAILED (CABIN) · airframe 45,917 hrs · 8,142 cycles

EMERGENCY LIGHT TEST FAIL NR 3 BATTERY. REMOVED AND REPLACED NR 3 EMERGENCY LIGHT BATTERY SUPPLY IAW MD-11 AMM 33-51-01. OPS CHECK GOOD.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 45,994 hrs · 8,160 cycles

CORROSION - STA 1986 L50L TO L50R, LOWER SHEAR TIE P/N AGA8007-9 CORROSION. NRC U05110 ISSUED.

Part: PAN — CORRODED (BS 19 S51L/R) · airframe 45,994 hrs · 8,160 cycles

CORROSION AT STA 19 S51L-51R WASTE TANK DRAIN PAN CORROSION.

Part: SEAT TRACK — CORRODED (CARGO BAY) · airframe 45,994 hrs · 8,160 cycles

STA 495 X=75 LT CURVED SEAT TRACK CORRODED.

Part: WEB — CRACKED (FUSELAGE) · airframe 45,994 hrs · 8,160 cycles

CRACK - IN CTR CARGO AT STA 1841 X = -62 VERTICAL WEB P/N AGA7125-3 CRACK. NRC U05084 ISSUED.

Part: SKIN — CRACKED (NR 2 NACELLE) · airframe 45,994 hrs · 8,160 cycles

CRACKED NR 2 INLET LIP OUTER SKIN CRACK AT 5-7 O'CLOCK.

Part: SKIN — DENTED (BS 430-440) · airframe 45,994 hrs · 8,160 cycles

DENT AT STA 430-440 L36R-S38R DENT ON SKIN.

Part: SEAT TRACK — CORRODED (CARGO BAY) · airframe 45,994 hrs · 8,160 cycles

CORROSION AT X=785 Y=104 SEAT TRACK S4929148 CORROSION.

Part: STOP FITTING — CRACKED (FUSELAGE) · airframe 45,994 hrs · 8,160 cycles

CRACK - IN CTR CARGO STA 1841 X=-62 STOP FITTING P/N AGA71971 CRACK. NRC U05083 ISSUED.

Part: FRAME — CORRODED (FUSELAGE) · airframe 45,994 hrs · 8,160 cycles

CORROSION - STA 1986 L50L TO L50R LOWER FRAME CORROSION, NRC U05111 ISSUED.

Part: CARGO TRACK — CORRODED (CGO COMP) · airframe 45,994 hrs · 8,160 cycles

CORROSION - MAIN DECK FLOOR STA 495 X=-75 RT CURVED SEAT TRACK CORROSION.

Part: TEE FITTING — CORRODED (FUSELAGE) · airframe 45,994 hrs · 8,160 cycles

CORROSION - 1EA TEE P/N AGA800219 LOC STA1975 BETWEEN L50L AND L50R CORROSION, NRC U05072 ISSUED.

Part: SKIN — CRACKED (NR 2 NACELLE) · airframe 45,994 hrs · 8,160 cycles

CRACK AT NR 2 ENG INLET LIP INNER SKIN INNER SURFACE CRACK AT 6 O'CLOCK.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 45,540 hrs · 8,073 cycles

EMERGENCY LIGHT TEST FAILED NR 4 BATTERY PACK. REMOVED AND REPLACED NR 4 BATTERY PACK.

Part: ENGINE — FAILED (NR 1)

DURING CLIMBOUT, NR 1 ENGINE FAILED CAUSING DAMAGE TO THE LEFT INBOARD AILERON AND LEFT OUTBOARD HORIZONTAL STABILIZER LEADING EDGE. REPLACED NR 1 ENGINE, LEFT INBOARD AILERON, AND LEFT OUTBOARD SECTION OF THE HORIZONTAL STABILIZER LEADING EDGE.

Part: ENGINE — VIBRATION (NR 1)

NR 1 ENGINE HI VIBRATION/LOW RPM IN INITIAL CLIMB OUT. HIGH EGT 917C. DURING SHUTDOWN ENGINE FIRE AGENT DISCHARGED.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

DURING C3 CHECK IN TPE INSPECTION FOUND: CORROSION ON THE PANEL SUPPORT OF CABIN FLOOR AT STA Y=860 & X=61 (REF EGAT N/R U05037). REMOVED THE DAMAGED PANEL SUPPORTS PER MD-11 SRM 51-35-01 VOL 2 REV 40. FABRICATE NEW SUPPORT IAW EGAT EI W2009P53B-374 REV 00. REINSTALL SUPPORT IAW MD-11 SRM 51-35-01 VOL 2 REV 40. JOB COMPLETED AND CHECK NORMAL.

Part: DOUBLER — CRACKED (LT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND: CRACK ON THE DB DOUBLER FASTENER AREA OF THE LEFT WING OUTBOARD FIXED CAVITY AT STA XOS627 (REF EGAT N/R U05035). REPAIR THIS CRACKED AREA B PER MD-11 SRM 57-00-01 VOL 1 FIG 10 REV 40. PERFORM ET INSPECTION FOR CUTOUT AREA AND ANGLE PARTS HEAT TREAT. REFER TO JOB CARD ATTACHING SHEET NR 079580. JOB COMPLETED AND CONDITION CHECK NORMAL.

Part: WEB — CRACKED (NR 1 PYLON)

DURING C3 CHECK IN TPE INSPECTION FOUND: CRACK ON NR 1 ENG PYLON INTERNAL WEB CRACK AT STA 300 (REF GET N/R U05024). REPAIRED THIS CRACKED AREA PER MD-11 SRM 57-00-01 VOL 1 FIG 10 REV 40 AND JOB CARD ATTACH SHEET 079586. JOB COMPLETED AND CONDITION CHECK NORMAL.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

DURING C3 CHECK IN TPE INSPECTION FOUND: CORROSION ON THE PANEL SUPPORT OF CABIN FLOOR AT STA Y=775 & X=85 (REF EGAT N/R U05038). REMOVED THE DAMAGED PANEL SUPPORTS PER MD-11 SRM 51-35-01 VOL 2 REV 40. REPLACE NEW SUPPORT PER MD-11 SRM 51-35-01 VOL 2 REV 40. JOB COMPLETED AND CHECK NORMAL.

Part: STIFFENER — CRACKED (LT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND: CRACK ON ZEE STIFFENERS OF LT WING FIXED L/E UPPER PNL 516ET (REF EGAT N/R U05031). REMOVED THE DAMAGED STIFFENERS (ARB2440-503/503) 2EA PER MD-11 SRM 51-35-01 VOL 2 REV 40. STOP DRILLED WITH 0.25 INCH DIA HOLE AT ENDS OF CRACK. FABRICATED REPAIR STIFFENERS PER MD-11 SRM 57-10-00 FIG 35 VOL 1 REV 40. HEAT TREATED REPAIR STIFFENERS 7075-0 0.040 CLAD TO 7075 T62 0.040 CLAD (REFER TO JOB CARD 079569 - ATTACHED). INSTALLED REPAIR STIFFENERS PER MD-11 SRM 51-35-01 VOL 1 REV 4. JOB COMPLETED AND CHECK NORMAL.

Part: RIB — CRACKED (RT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND: CRACK ON RIGHT WING FIXED L/E CAVITY XOS1025 - LOWER RIB CRACKED FROM FASTENERS AREA (REF EGAT N/R U50534). REPAIR THIS CRACKED RIB PER MD-11 SRM 57-00-01 VOL 1 FIG 10 REV 40. JOB COMPLETED AND CONDITION CHECK NORMAL.

Part: STIFFENER — CRACKED (RT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND: CRACK ON ZEE STIFFENERS OF RT WING FIXED L/E UPPER PNL 616ET (REF EGAT N/R U05027). REMOVED THE DAMAGED STIFFENERS (ARB2440-504/506) 2EA PER MD-11 SRM 51-35-01 VOL 2 REV 40. STOP DRILLED WITH 0.25 INCH DIA HOLE AT ENDS OF CRACK. FABRICATED REPAIR STIFFENERS PER MD-11 SRM 57-10-00 FIG 35 VOL 1 REV 40. HEAT TREATED REPAIR STIFFENERS 7075-0 0.040 CLAD TO 7075 T62 0.040 CLAD (REFER TO JOB CARD 079570 - ATTACHED). INSTALLED REPAIR STIFFENERS PER MD-11 SRM 51-35-01 VOL 1 REV 40. JOB COMPLETED AND CHECK NORMAL.

Part: ANGLE — CRACKED (NR 3 PYLON)

DURING C3 CHECK IN TPE INSPECTION FOUND: CRACK ON NR 3 ENG PYLON INTERNAL ANGLE AT STA 180 (REF GET N/R U05032). REPLACED THE INTERNAL ANGLE PER MD-11 SRM 51-35-01 VOL 2 REV 40. JOB COMPLETED AND CONDITION CHECK NORMAL.

Part: SUPPORT BRACKET — DEFORMED (RT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND DEFORM ON THE GND JACKS SUPPORT BRACKET INSIDE OF RT WING FUELING STATION (REF EGAT N/R U05025). REMOVED BRACKET IAW SRM 51-35-01 VOL 2 REV 40, FABRICATED SUPPORT BRACKET IAW EGAT EI W2009P57B-350 REV 00, INSTALLED THIS SUPPORT BRACKET IAW SRM 51-35-01 VOL 2 REV 40, AND JOB COMPLETE & COND CHK NORM.

Part: DOUBLER — CRACKED (LT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON DOUBLER OF LT WING FIXED L/E CAVITY UPPER RIB AT STA XOS789. REMOVED THIS CRACKED CHORD DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, FABRICATED DOUBLER IAW EGAT EI W2009P57B-357 REV 00, INSTALLED THIS DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, AND JOB COMPLETE & COND CHECKED NORMAL.

Part: SUPPORT BRACKET — CRACKED (RT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON LWR PANEL SUPPORT BRACKET OF RIGHT WING T/E AT STA XOSP465.027 (REF EGAT N/R U05023). REMOVED SUPPORT BRACKET IAW SRM 51-35-01 VOL 2 REV 40, FABRICATED SUPPORT BRACKET IAW EGAT EI W2009P57B-350 REV 00, INSTALLED THIS SUPPORT BRACKET IAW SRM 51-35-01 VOL 2 REV 40, AND JOB COMPLETE & COND CHECKED NORMAL.

Part: WEDGE — DEBONDED (LT AILERON)

DURING C3 CHECK IN TPE INSPECTION FOUND EGAT LT OUTBOARD AILERON WEDGE DISBOND AT XOA 842. REMOVE AND CLEANUP AREA. REPAIR THIS WEDGE PER DRAWING SG11570003. CHECK REPAIRED AREA WAS SATISFIED, CALCULATED THE REWORK BALANCE MOMENT IS 66.65 LB-IN PER SRM 57-50-00 VOL 2 REV 40. RECORD THIS NEW MOMENT DATA ON ACFT. JOB COMPLETED.

Part: STEP — CRACKED (CAC BAY)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON RT STEP SUPPORT OF CAC COMPARTMENT. REMOVED SUPPORT BRACKET IAW SRM 51-35-01 VOL 2 REV 40, FABRICATED SUPPORT BRACKET IAW EGAT EI W2009P57B-339 REV 00, INSTALLED THIS SUPPORT BRACKET IAW SRM 51-35-01 VOL 2 REV 40, AND JOB COMPLETE & COND CHECKED NORMAL.

Part: FITTING — CRACKED (FUSELAGE)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON 1EA RT CLIP OD CAC COMPARTMENT. REMOVE THIS DAMAGED CLIP PER SRM 51-33-01 VOL 2 REV 40, FABRICATE THIS CLIP PER EGAT EI W2009P53B-354 REV 00, INSTALLED THIS CLIP PER SRM 51-33-01 VOL 2 REV 40, AND JOB COMPLETED - CONDITION CHECKED NORMAL.

Part: STEP — CRACKED (E&E BAY)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON STEP PANEL OF AVIONICS COMPARTMENT LADDER AT STA 348 (REF EGAT N/R U05026). REMOVED AND FABRICATED NEW PANEL IAW EGAT EI W2009P57B-351 REV 00, INSTALLED PANEL IAW SRM 51-35-01 VOL 2 REV 40, AND JOB COMPLETE & COND CHECKED NORMAL.

Part: RIB — CRACKED (LT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON LWR CHORD OF LT WING FIXED L/E NOSE CAVITY NEARBY FASTENER AT STA XOS546. REMOVED THIS CRACKED CHORD DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, FABRICATED DOUBLER IAW EGAT EI W2009P57B-338 REV 00, INSTALLED THIS DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, AND JOB COMPLETE & COND CHECKED NORMAL.

Part: SEAT TRACK — CORRODED (FUSELAGE)

DURING C3 CHECK IN TPE INSPECTION FOUND CABIN SEAT TRACK HAD CORROSION AT STA 846 X=43. REPAIRED THIS CORRODED SEAT TRACK IAW SRM 53-70-00 VOL 1 FIG 1 REV 40, JOB COMPLETED AND CONDITION CHECK NORMAL.

Part: SEAL — CRACKED (LT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON LEFT WING T/E BEAM SEAL LAND Y=1474 Z=-100. REPLACE THIS CRACK SEAL LAND IAW SRM 51-35-01 AND 51-33-01 VOL 2 REV 40, JOB COMPLETED AND CONDITION CHECK NORMAL.

Part: RIB — CRACKED (FUSELAGE)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON RT RIB OF RT MLG GR JAMB INSTALLED AT Y-1474 Z=-100. REMOVE RT RIB OF RT MLG JAMB PER SRM 51-33-01 VOL 2 REV 40, INSTALLED NEW RIB PER MD-11 SRM 31-33-01 VOL 2 REV 40, JOB COMPLETED AS NORMAL.

Part: DOUBLER — CRACKED (RT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON DOUBLER OF RIGHT WING FIXED L/E CAVITY UPPER RIB AT STA XOS789 (REF EGAT N/R U05018). REMOVED THIS CRACKED CHORD DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, FABRICATED DOUBLER IAW EGAT EI W2009P57B-358 REV 00, INSTALLED THIS DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, AND JOB COMPLETE & COND CHECKED NORMAL.

Part: FITTING — CRACKED (FUSELAGE)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON 1EA RT CLIP OD CAC COMPARTMENT. REMOVE THIS DAMAGED CLIP PER SRM 51-33-01 VOL 2 REV 40, FABRICATE THIS CLIP PER EGAT EI W2009P53B-354 REV 00, INSTALLED THIS CLIP PER SRM 51-33-01 VOL 2 REV 40, AND JOB COMPLETED - CONDITION CHECKED NORMAL.

Part: DOOR — CRACKED (RT MLG)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON FLIPPER DOOR FWD EDGE OF RT MLG GR - ABOUT .5 INCH (REF EGAT N/R U05029). REMOVED THIS CRACKED FLIPPER DOOR PER AMM 32-14-08-000-801, REPAIRED THE FLIPPER DOOR IAW SRM VOL 1 52-10-00 FIG 18 REV 40, REINSTALLED AND SWING TEST FOR FLIPPER DOOR REFER TO JOB CARD ATTACHING SHEET 079555 ITEM 2 & 3 AND JOB COMPLETE AND CHECKED NORMAL.

Part: DOUBLER — CRACKED (RT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON DOUBLER OF RIGHT WING FIXED L/E CAVITY UPPER RIB AT STA XOS667. REMOVED THIS CRACKED CHORD DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, FABRICATED DOUBLER IAW EGAT EI W2009P57B-358 REV 00, INSTALLED THIS DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, AND JOB COMPLETE & COND CHECKED NORMAL.

Part: DOOR — CRACKED (LT MLG)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON FLIPPER DOOR FWD UPPER EDGE OF LT MLG GR - ABOUT .5 INCH (REF EGAT N/R U05028). REMOVED THIS CRACKED FLIPPER DOOR PER AMM 32-14-08-000-801, REPAIRED THE FLIPPER DOOR IAW SRM VOL 1 52-10-00 FIG 18 REV 40, RE-INSTALLED AND SWING TEST FOR FLIPPER DOOR REFER TO JOB CARD ATTACHING SHEET 079555 ITEM 2 & 3 AND JOB COMPLETE AND CHECKED NORMAL.

Part: VANE — DEBONDED (TE FLAP)

DURING C3 CHECK IN TPE INSPECTION FOUND LT INBOARD FLAP VANE HAS DISBOND AT XIFH196 AND XIFH249. PER AMM 27-50-22-000-081 & 27-50-24-000-081 REV 63. REMOVED THIS DISBONED FLAP VANE, REPAIRED THE FLAP VANE AS JOB CARD ATTACHMENT SHEET 079554, PER AMM 27-50-22-000-081 & 27-50-24-000-081 REV 63. INSTALLED THIS REPAIRED FLAP VANE - CONDITION CHECK NORMAL, PER AMM 27-50-00-860-801 REV 63 PERFORMED OPERATION TEST OF FLAP - RESULT SATISFIED.

Part: SEAT TRACK — CORRODED (FUSELAGE)

DURING C3 CHECK IN TPE INSPECTION FOUND SEAT TRACK CORROSION AT STA 859. REPAIRED THIS CORRODED SEAT TRACK IAW SRM 53-70-00 VOL 1 FIG 1 REV 40, JOB COMPLETED AND CONDITION CHECK NORMAL.

Part: DOUBLER — CRACKED (LT WING)

DURING C3 CHECK IN TPE INSPECTION FOUND CRACK ON DOUBLER OF LT WING FIXED L/E CAVITY UPPER RIB AT STA XOS667. REMOVED THIS CRACKED CHORD DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, FABRICATED DOUBLER IAW EGAT EI W2009P57B-355 REV 00, INSTALLED THIS DOUBLER IAW SRM 51-35-01 VOL 2 REV 40, JOB COMPLETE & COND CHECKED NORMAL.

Part: DOUBLER — CRACKED (CENTER MLG WW)

CENTER MLG WW RT BULKHEAD CUTOUT DOUBLER CRACKED AT RT FWD CORNER.

Part: OVEN — DEFECTIVE (GALLEY)

OKBK/EDDP. OVEN 509 MID GALLEY INOP BURNING SMELL WHEN USED. REMOVED AND REPLACED MID GALLEY OVEN 509 REF MM 25-33-00. DMI CLOSED.

Part: ANGLE — CORRODED (FUSELAGE)

DURING C-CHECK INSPECTION FOUND CORROSION ON LOWER CHORD AT STA Y=1964 L48L. BLENDED CORROSION, AREA MEASURED WITHIN LIMITS PER SRM VOL.1 53-00-01 FIG.3 REV.40.

Part: SEAT TRACK — CORRODED (FUSELAGE)

DURING C-CHECK INSPECTION FOUND SEAT TRACK CORROSION AT STA Y=840 TO 859 X=14. BLENDED CORROSION, WITHIN ALLOWABLE LIMITS PER MD11 SRM VOL.1 53-00-01 FIG.3 REV.40. REF EGAT NRCU 05022.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

DURING C-CHECK INSPECTION FOUND AFT FUSELAGE FLOOR SUPPORT CORROSION AT STA Y=2007, X= 56.65. REPLACED AFT FLOOR SUPPORT PER MD11 SRM VOL.II 51-35-01 FIG.1 REV.40.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

DURING C-CHECK INSPECTION FOUND AFT FUSELAGE FLOOR SUPPORT CORROSION AT STA Y=2000, X= -56.65. REPLACED AFT FUSELAGE FLOOR SUPPORT PER MD-11 SRM VOL.II 51-35-01 FIG.1 REV.40.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

DURING C-CHECK INSPECTION FOUND AFT FUSELAGE FLOOR SUPPORT CORROSION AT STA Y=2007, X=27.5. REPLACED AFT FLOOP SUPPORT PER MD-11 SRM VOL.II 51-35-01 FIG.1 REV.40.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

DURING C-CHECK INSPECTION FOUND AFT FUSELAGE FLOOR SUPPORT CORROSION AT STA Y=2007, X= -23.5. REPLACED AFT FUSELAGE FLOOR SUPPORT PER MD-11 SRM VOL.II 51-35-01 FIG.1 REV.40.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

DURING C-CHECK INSPECTION FOUND AFT FUSELAGE FLOOR SUPPORT CORROSION AT STA Y=2007, X= 23.5. REPLACED AFT FLOOR SUPPORT PER MD-11 SRM VOL.II 51-35-01 FIG.1 REV.40.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

DURING C-CHECK INSPECTION FOUND AFT FUSELAGE FLOOR SUPPORT CORROSION AT STA Y=2007, X= -27.5. REPLACED AFT FUSELAGE FLOOR SUPPORT PER MD-11 VOL.II 51-35-01 FIG.1 REV.40.

Part: ACCESS PANEL — CRACKED (RT WING)

DURING C-CHECK INSPECTION FOUND RT WING OUTBOARD SLAT DRIVE MECHANISM ACCESS PANEL SKIN CRACKED. REPAIRED RT WING ACTUATOR ACCESS DOOR OUTER SKIN AT XOS STA 490.85 PER EGAT EI NR W2008A57B-022.

Part: SKIN — CRACKED (A/C BAY DOOR)

DURING C-CHECK INSPECTION FOUND CRACK ON RIGHT FWD AIR CONDITION COMPARTMENT DOOR OUTER SKIN UPPER EDGE APPROX 4.5 INCHES. REPAIRED PER MD-11 SRM 52-10-00 VOL.I REV.40.

Part: UNKNOWN — SMOKE (COCKPIT)

TO+15 MIN SMOKE & FUMES IN COCKPIT, UNKNOWN SOURCE. COCKPIT DOOR POWER & RECIRC FANS TURNED OFF. SMOKE DISSIPATED SOME. RETURN TO ORIGIN. CHECKED RECIRC FANS, ALL CHECKED GOOD, CHECKED MUX SYSTEM OPS CHECK GOOD. CHECKED WIRING IN OVERHEAD, FOUND NO PROBLEMS. CHECKED WIRING IN CAC ALL CHECKED GOOD. CHECK AVIONIC BAY NO SMELL OR SMOKE NOTED. NO APPARENT BURNT WIRING. RAN ALL 3 ENG OPERATED PACKS NO SMELLS NOTED. PERFORMED VISUAL WALKAROUND OF OUTSIDE OF ACFT NO DEFECTS NOTED. NO POPPED C/B'S OR WARNINGS DETECTED, ACFT OK FOR FURTHER FLIGHT.

Part: SKIN PANEL — DENTED (BS 765-791)

REF WOA ERA 06-05-013R1 (LT SIDE OF FUSELAGE DAMAGED AT FS 765 TO FS 791 STR 38L-39L.) EXA 06-15-013R1 TO INSTALL PERMANENT REPAIR (SECTION 3 OF ERA). REMOVED TEMPORARY REPAIR AND INSTALLED PERMANENT REPAIR IAW SRM.

Part: SLIDE — NO TEST (L4 DOOR)

DURING 4C CHECK IN TPE, L4 DOOR SLIDE DEPLOYMENT FAILED DURING TESTING. REMOVED AND REPLACED SLIDE PER AMM

Part: LOCK — BURNED (COCKPIT DOOR)

DURING CRUISE (ABOUT 5 HR,S AFTER T/O), THE CREW DETECTED A STRONG ELECTRCAL ODOR WITH LIGHT SMOKE. A DECISION WAS MADE TO DIVERT THE AIRPLANE TO PANC, A NORMAL LANDING WAS MADE, CREW FOLLOWED THE STANDARD EMERGENCY PROCEDURE. MAINTENANCE AT PANC INSPECTED WIRING AND COMPONENTS ABOVE OVERHEAD C/B PANEL AND ELEC CONTROL PANEL WIRING AND FWD ELE BAY, NO DEFECTS NOTED. FOUND MELTED INSULATION AT CKPT DOOR LOCK. PULLED THE CKPT DOOR C/B AND DEFERRED THE COCKPIT AUTOMATIC LOCKING SYSTEM PER MD-11 MEL PROCEDURES.

Part: BATTERY — DISCHARGED (ZONE 100)

DURING REGULAR LINE MAINTENANCE CHECK ON AIRCRAFT N272WA AT LAX, MAINTENANCE FOUND THE EMERGENCY LIGHT TEST BATTERY NR 1 WAS LOW. MAINTENANCE AT LAX REMOVED AND REPLACED THE BATTERY & THE CONTROLLER PER MD-11 MM 33-51-00 & 31-42-00, OP'S CHECK GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: CYLINDER — UNDERSERVICED (RT MLG)

GEAR HANDLE LOCKED IN FLIGHT. AIR RETURN TO LAX. RESET HANDLE FUSE PER MAINTENANCE MANUAL 32-37-01 AND REBLEED BOGEY TRIM CLYINDER PER THE SAME MAINTENANACE MANUAL REFERENCE, GEAR HANDLE OPERATION IS NORMAL. LEAK CHECK OK.

Part: SENSOR — MALFUNCTIONED (NR 2 ENGINE)

AFTER TAKEOFF APPROX 800 FT LEVEL 3, NR 2 ENGINE ANTI-ICE DUCT ILLUMINATED TRI TONE SOUND. SHUT DOWN ENGINE NR 2 AS PER VOLUME 1, DUMPED FUEL AS PER VOLUME 1 RETURNED TO FIELD, DEPARTURE FIELD JTY. REPLACED NR 2 ANTI-ICE VALVE. SWAPPED NR 2 AND NR 3 PRESSURE SWITCHES. CHECKED DUCT DAMAGE NOT FOUND ANY DAMAGE. ESC RTS TEST PASSED. ANNUNCIATE LIGHT TEST (R2-5527 RESET) AND THEN ENGINE RUN-UP CHECKED (GROUND IDLE RUN EPR 1.21) ANTI-ICE SYSTEM NORMAL. THE DUCT OVERHEAT SENSORS WERE REPLACED IN LAX D1-91 AND D1-89. (M)

Part: TRANSMITTER — FAILED (NR 2 WHEEL)

ABORTED TAKEOFF AT 80 KNOTS DUE TO TIRE PRESSURE ANNUNCIATION ON TIRE NR 2. INTERROGATED BTMTP NO CURRENT FAULTS SHOWN. FAULT HISTOR SHOWS NR 2 TIRE FAILURE. INSPECTED NR 2 MWA AND NR 2 MWA TIRE PRESSURE, BOTH NORMAL AND WITHIN LIMITS. PLACED TIRE PRESSURE INDICATION ON MEL 32-46-1-2 DMI M32AP08-16 INSTALLED PLACARD CAT C ITEM ENTERED IN DMI LOG BTM/TPI SYSTEM CIRCUIT BREAKER PULLED AND COLLARED PER MEL. REPLACED TIRE PRESSURE TRANSMITTER. (M)

Part: AILERON — MALFUNCTIONED (WING)

AILERON DEFLECT DISAGREE LEVEL 2 ALERT, AIRCRAFT RETURNED TO ATL. RAN FLAPS THROUGH 28 DEGREES. NO AILERON DEFLECTION NOTED. (M)

Part: ACTUATOR — FAILED (AILERON)

AIRCRAFT HAS AILERON CONTROL PROBLEM. AIRCRAFT RETURNED TO SNN WERE THE AILERON SYSTEM WAS CHECKED. REMOVED AND REPLACED AILERON DEFLECTION ACTUATOR OUTBOARD. FOLLOW PROCEDURE IAW MM 27-43-00 RTS TEST FCC 1/FCC 2 ALL PASSED. OPS CHECK MM. NO FAULTS. (M)

Part: INDICATOR — INOPERATIVE (NR 3)

NR 3 OIL INDICATION WENT FROM 9 QUARTS AT LEVEL OFF TO 3 QUARTS IN TWO MINUTES, SHUT DOWN ENGINE AND RETURNED BASE. SERVICED 1 QT DEFERRED NR 3 OIL QUANTITY INDICATION PER MEL M70MR10-17 MR MEL 79-31-1. NR 3 ENGINE OIL PRESSURE INDICATED NORMAL EN ROUTE WIMM-OEJN NO OIL ADDED IND. ON DISPLAY 28 QUARTS IND SYSTEM NORMAL DMI CLEARED. THE NR 3 DISPLAY ELECTRONIC UNIT WAS ON MEL 31-61-1 REF THE ATTACHED MD 11 MEL PAGE. LANDING WAS PRECAUTIONARY TO ASSURE PROPER OIL QUANTITY. (M)

Part: SEAL — DISLODGED (CARGO DOOR)

ON TAKEOFF ROLL AT APPROXIMATELY 120-125 KNOTS AN AIRFLOW NOISE WAS HEARD IN THE COCKPIT IN THE VICINITY OF THE PEDESTAL AND CENTER INSTRUMENT PANEL ACCOMPANIED BY A MASTER CAUTION LIGHT AND A LEVEL 2 CARGO DOOR ALERT. TAKEOFF WAS ABORTED AT 140 KNOTS AND THE AIRCRAFT RETURNED TO THE DEPARTURE GATE. MX PERSONNEL INSPECTED THE EXTERIOR AVIONICS DOOR, THE NLG DOORS AND THE ACCESS DOOR TO THE REAR OF THE AVIONICS BAY. NO DISCREPANCIES WERE FOUND. INSPECTION OF THE LOWER CENTER CARGO DOOR SHOWED A SMALL PORTION OF THE DOOR SEAL OUT OF THE RETAINER. THE SEAL WAS INSTALLED AND THE INSPECTIONS COMPLETED. THE AIRCRAFT WAS RETURNED TO SERVICE AND DEPARTED WITHOUT FURTHER INCIDENT. (M)

Part: BULLET — DELAMINATED (NR 1 ENGINE)

UPON DEPARTURE, AIRCRAFT EXPERIENCED ENGINE VIBRATION OF UNKNOWN ORIGIN IN NR 1 POSITION. EMERG PROCEDURES C/W, AND ACFT RETURNED TO DEPARTURE STA WITHOUT INCIDENT. UPON INSP BY WORLD AIRWAY MAINT REP, DISCOVERED THE NOSE CONE (SPINNER) ON NR 1 ENGINE HAD DELAMINATED AND MATERIAL INGESTED INTO THE ENGINE (NR 1 POS) DAMAGING ALL THE FAN BLADES, TWO INLET GUIDE VANES, AND ENGINE NOSE COWL. FAN BLADES, INLET GUIDE VANES, AND SPINNER HAVE BEEN REPLACED. ENGINE RUN-UP AND BLADE TRIM BALANCE ACCOMPLISHED SATISFACTORY. REPAIRS TO DAMAGED NOSE COWL MADE USING DATA FURNISHED BY MFG. (X)

Part: ANTENNA — FAILED (WX RADAR)

WEATHER RADAR SYSTEM NR 1 FAILED FOUR MINUTES AFTER TAKEOFF. SYSTEM NR 2 FAILED 16 MINUTES INTO FLIGHT. AIRCRAFT DIVERTED TO BRU WHERE ANTENNA WAS REPLACED. OPERATIONAL TEST OK AFTER ANTENNA CHANGE. (X)

Part: COMPUTER — FAILED (E/E BAY)

AUTOPILOT NR 1 AND NR 2 FAILED ON DEPARTURE FROM PGUM. AIRCRAFT RETURNED TO PCUM FOR CORRECTIVE ACTION. REMOVED AND REPALCED NR 2 FCC. RETURN TO SERVICE TEST SATISFIED. DEFERRED NR 1 AUTOPILOT PER MEL 22-10-1. AIRCRAFT DOWNGRADED TO CAT II SINGLE LAND. AIRCRAFT RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. (X)

Part: SEAT TRACK — CORRODED (FUSELAGE)

DURING PERFORMANCE OF "1C" CHECK, MAINTENANCE PERSONNEL FOUND CORROSION IN SEAT TRACKS AT LAVATORIES A, B, C, D, E, F, M. REPAIRED SEAT TRACKS AND STRUCTURE IAW MD 11 SRM 53. CORROSION WAS DETERMINED TO BE LEVEL 1. (M)

Part: SEAT TRACK — CORRODED (FUSELAGE)

DURING PERFORMANCE OF 1C CHECK, MAINTENANCE PERSONNEL FOUND CORROSION UNDER MOON MAT AND STRUCTURE AT GALLEY'S G3, G4, G5, AND G8. REPAIRED SEAT TRACKS AND STRUCTURE IAW MD11 SRM 53. CORROSION WAS DETERMINED TO BE LEVEL1. (M)

Part: ENGINE — MALFUNCTIONED (NR 1)

DURING INITIAL CLIMB AFTER TAKEOFF ON FLIGHT NR WOA972, FLIGHT CREW RECEIVED NOTIFICATION FROM AIRPORT TOWER THAT 'TWO FIREBALLS' WERE NOTED EXITING FROM THE NR 1 ENGINE DURING DEPARTURE. FLIGHT CREW NOTED THAT ALL ENGINES PARAMETERS WERE NORMAL. FLIGHT CREW ELECTED TO RETURN TO POINT OF DEPARTURE. AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE NOTED THAT THERE WERE NO 'OPEN FAULTS' IN THE CENTRAL FAULT DISPLAY SYSTEMS THAT WOULD INDICATE A MALFUNCTION WITH THE NR 1 ENGINE. ENGINE WAS RUN WITH ALL PARAMETERS NORMAL, AND WITH NO FAULTS NOTED IN THE CFDS. AIRCRAFT WAS RETURNED TO SERVICE. (M)

Part: RELAY — CORRODED (NR 3 ENGINE)

DURING INITIAL TAKEOFF ROLL, NR 3 ENGINE EXPERIENCED HIGH EGT (661 DEGREES CELSIUS). FLIGHT CREW ELECTED TO ABORT TAKEOFF (80 KNOTS). AIRCRAFT RETURNED TO GATE WITHOUT FURTHER INCIDENT. MAINTENANCE PERSONNEL FOUND 2.95 BLEED VALVE STUCK IN THE OPEN POSITION. FURTHER INVESTIGATION FOUND THE BLEED VALVE RELAY CORRODED AND FROZEN. REPLACED RELAY AS A PRECAUTION, REPLACED BLEED VALVE SOLENOID. ENGINE HOT SECTION WAS BOROSCOPED PER MM REQUIREMENTS WITH NO FAULTS NOTED. PERFORMED HIGH POWER GROUND RUNS WITH NOT FAULTS NOTED. AIRCRAFT RETURNED TO SERVICE. (M)

Part: COMPUTER — INOPERATIVE (NR 1 AUTO-PILOT)

DURING TAXIING, AIRCRAFT WOULD NOT PASS FLIGHT CONTROL POSITION TEST. AIRCRAFT RETURNED TO GATE WITH FURTHER INCIDENT. MAINTENANCE PERSONNEL REMOVED AND REPLACED NR 1 FLIGHT CONTROL COMPUTER. PERFORMED RETURN TO SERVICE CHECK. OPS CHECKED NORMAL. AIRCRAFT RETURNED TO SERVICE. (M)

Part: DOOR ACTUATOR — FAILED (APU EXHAUST)

DURING TAXI FOR TAKEOFF, FLIGHT CREW RECEIVED A 'APU INLET/EXHAUST DOOR ALERT', FAIL TO CLOSE INDICATION. DUE TO MEL RESTRICTIONS, FLIGHT CREW ELECTED TO RETURN TO GATE FOR MAINTENANCE ACTION. AIRCRAFT RETURNED TO GATE WITHOUT FURTHER INCIDENT. MAINTENANCE REP COMPLIED WITH MEL PROCEDURES AND ASSIGNED DEFERRAL TO APU INLET/EXHAUST DORS INOPERATIVE. INITIAL INDICATIONS ARE THAT APU DOOR ACTUATOR HAS FAILED. AIRCRAFT RETURNED TO SERVICE. (M)

Part: RCCB — TRIPPED (E/E COMPT)

DURING INITIAL CLIMB, FLIGHT CREW RECEIVED 'RIGHT EMERGENCY BUS FAIL' INDICATION. FLIGHT CREW ELECTED TO RETURN TO POINT OF DEPARTURE FOR MAINTENANCE ACTION. AIRCRAFT RETURNED TO POINT OF DEPARTURE, AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE PERSONNEL UNABLE TO DUPLICATE FAULT. RESET RCCB'S AND PERFORMED GROUND RUN WITH NO FAULTS NOTED. ALL OPERATIONS NORMAL. AIRCRAFT RETURNED TO SERVICE. (M)

Part: CONNECTOR — FAILED (NR 3 HYD SYSTEM)

DURING TAXIING FOR DEPARTURE AND PERFORMING FUNCTIONAL CHECKS PER CHECK LIST, FLIGHT CREW RECEIVED FAILURE INDICATION FOR HYDRAULIC SYSTEM TEST. (NR 3 LT ENGINE DRIVEN PUMP) WOULD NOT DEPRESSURIZE. AIRCRAFT RETURNED TO GATE WITHOUT FURTHER INCIDENT. MAINTENANCE PERSONNEL FOUND CANNON PLUG TO NR 3 LT ENGINE DRIVEN PUMP DEPRESSURIZATION CANNON PLUG BAD. PART NOT AVAILABLE. DEFERRED PER MEL 29-11-1. (X)

Part: AILERON CONTROLS — FAILED TEST (RIGHT)

DURING TAXIING OUT, FLIGHT CREW NOTED RIGHT OUTBOARD AILERON FAILED CONTROL TEST. FLIGHT CREW ELECTED TO RETURN TO GATE. AIRCRAFT RETURNED TO GATE WITHOUT FURTHER INCIDENT. MAINTENANCE CREW PERFORMED AILERON TEST SEVERAL TIMES, EACH TIME SYSTEM PASSED WITH NO FAULTS NOTED. MAINTENANCE COULD NOT IDENTIFY ANY FAULT WITH FLIGHT CONTROL SYSTEM. AIRCRAFT RETURNED TO SERVICE. (X)