N520UA

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 72,368 hrs · 27,105 cycles

AFT CABIN FLOORBEAM STA 1640 RBL 12 TO LBL 20, UPPER AND LOWER SURFACE CORRODED AT NUT PLATE HOLES. REMOVED CORROSION IAW SRM 53- 00-51. REMAINING DAMAGE WAS OUT OF LIMITS. PERFORMED T-CAP REPAIR IAW ECRA 5310-05536.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,368 hrs · 27,105 cycles

MAIN CABIN FLOOR AT STA 324 TO 336 RBL 40 INTERCOSTAL UPPER SURFACE HAS MULTIPLE AREAS OF CORROSION. REMOVED CORROSION IAW SRM 53-00-04, FOUND OUT OF LIMITS IAW SRM 53-00-04. REMOVED & REPLACED INTERCOSTAL STA 324 TO 336 RBL 40. REPLACED INTERCOSTAL IAW SRM51-40-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,368 hrs · 27,105 cycles

MAIN CABIN FLOOR STRUCTURE STA 324 RBL 45 TO RBL 61 FLOORBEAM UPPER FLANGE UPPER AND LOWER SURFACE HAS CORROSION. REMOVED CORR, REMAINING MATERIAL OUT OF LIMIT. FAB T-CAP IAW SRM 53-10-08. INSTALLED REPAIR IAW 51-40-02 AND SRM 53-00-01.

Part: SPLICE PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,368 hrs · 27,105 cycles

AFT CABIN FLOOR, STA 1680 BL 0, FLOOR PAN TO INTERCOSTAL, SPLICE PLATE CORRODED UPPER SURFACE. BLENDED CORR FROM SPLICE PLATE. REMAINING DAMAGE OUT OF LIMIT. FAB NEW SPLICE PLATE IAW GNMM 1-0-0-023 AND BOEING DWG 146N5230-40. INSTALLED SPLICE PLATE IAW SRM 51-40-02.

Part: PAN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,368 hrs · 27,105 cycles

AFT PASSENGER CABIN FLOOR PAN WEB STA 1680 LBL 10 TO RBL 55 UPPER SURFACE CORR BULGING BETWEEN WEB AND FLOOR BEAM AT NUT PLATE HOLES 2EA PLACES. REMOVED CORR, FOUND REMAINING DAMAGE OUT OF LIMIT. REPAIRED DAMAGE AT STA 1680 IAW SRM 53-60 -51 REPAIR 3.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,368 hrs · 27,105 cycles

INTERNAL EMPENNAGE TAIL COMP BETWEEN STA 1787 TO 1825, JUST ABOVE STR 5R SKIN IS CORRODED UNDER APU INLET ATTACH FLANGE. REMOVED CORR, FOUND REMAINING DAMAGE OUT OF LIMIT. REPAIRED DAMAGE AT STA 1680 IAW SRM 53-60-51 REPAIR 3.

Part: SKIN — CORRODED (FUSELAGE) · airframe 72,368 hrs · 27,105 cycles

EMPENNAGE TAIL COMP FWD STA 1825 BETWEEN 3R & 5R STR SKIN HAS CORROSION UNDER APU INLET ATTACH FLANGE. MAJOR REPAIR ACCOMPLISHED: REMOVED CORROSION AT STA 1825 BETWEEN STR 3R & 5R ON HINGE STRAP, INNER STRAP ORIGINAL T .100 REMAINING 0 LOSS 100% FOUND OUT OF LIMITS IAW SRM 53-80-15 TABLE 101 ACCOMPLISHED REPAIR I DETAIL II FIG 202, SRM 53-80-15.

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,368 hrs · 27,105 cycles

MAIN CABIN FLOOR STRUCTURE STA 301 RBL 60 CREASE BEAM INNER CORD ANGLE HAS CORROSION. INSTALLED NEW CORD ANGLE IAW DWS141N8422 AND SRM 51-40-02.

Part: STIFFENER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,368 hrs · 27,105 cycles

PASSENGER COMP BS 1664+9 RBL 61 THRESHOLD SUPPORT HAS UPPER SURFACE CORROSION AROUND FASTENER HOLE. MAJOR REPAIR ACCOMPLISHED. REMOVED AND REPLACED NEW STIFFENER AT STA 1664+9 IAW BOEING DWG 146N8732, SRM 51-40-02, SRM 51-40-05, SRM 51-20-01 AND SRM 51-20-05.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 72,368 hrs · 27,105 cycles

PASSENGER COMP BS 1681.8 MINUS 10" LBL 61 THRESHOLD ATTACH FITTING CORRODED. REMOVED & REPLACED ATTACH FITTING P-N 146N8769U47 ATA9-A26091.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,368 hrs · 27,105 cycles

PASSENGER COMP BS 1681.8 MINUS 10' LBL 61 THRESHOLD ATTACH FITTING CORRODED. REMOVED & REPLACED ATTACH FITTING P/N 146N8769U47 ATA9-A26091 IAW DWG 146N8722 AND SRM 51-40-02 AND SRM 51-40-05.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 72,279 hrs · 27,072 cycles

EMERGENCY LIGHTS OVERHEAD 6A, 3, E, F INOPERATIVE.

Part: STRUCTURE — CRACKED (RT EXHAUST) · airframe 72,153 hrs · 27,022 cycles

CRACK NOTED ON RIGHT SIDE EXHAUST AREA ON LEFT ENGINE. MEASURED LENGTH OF CRACK DETERMINED TO BE 1.75 INCHES. REF SRM 54-31-01 THIS IS WITHIN SERVICEABLE LIMITS. WILL COVER AREA WITH SPEED TAPE TO PROTECT FORM MOISTURE.

Part: DOOR — OBSTRUCTED (L4) · airframe 71,995 hrs · 26,967 cycles

DOOR 4L NOT ARMING CORRECTLY. CLEANED OBSTRUCTION ON BOTTOM OF DOOR SILL, OPERATED DOOR SEVERAL TIMES, OKAY.

Part: BYPASS VALVE — LEAKING (FUEL/OIL COOLER) · airframe 71,303 hrs · 26,733 cycles

FOUND RT ENGINE FUEL OIL COOLER LEAKING. REMOVED AND REPLACED RT FUEL/OIL COOLER BYPASS VALVE. OPS CHECKED GOOD.

Part: DUCT — CRACKED (LT A/C PACK) · airframe 71,233 hrs · 26,713 cycles

LEFT PACK HOT AIR LINE FROM CONDENSOR TO COMPRESSOR OUTLET DUCT IS CRACKED AND ALSO TUBE THAT CONNECTS TO CONDENSOR HAS A HOLE WORN THROUGH IT BLOWING HOT AIR.

Part: IDG — FAULTED (NR 2) · airframe 71,077 hrs · 26,654 cycles

RIGHT GEN FAIL ON TAKEOFF ROLL AT 75 KNOTS. SERVICED IDG OIL TO FULL, RAN NR 2 ENG FOR IDG TEST, OPS CHECKS OKAY. CF CREATED TO RE-CHECK OIL LEVEL IN IDG WITHIN 25 FLT HOURS DUE TO QTY NEEDED TO BRING IDG TO FULL LEVEL. STARTED RT ENGINE. RT GEN DRIVE LIGHT STAYED ON AND RT GEN EICAS STAYED ILLUMINATED. RIGHT ENGINE IDG CHECKED FULL. APU SERVICED TO FULL. REPLACED NR 2 ENGINE IDG PER MM.

Part: TRANSMITTER — FAILED (NR 2 ENGINE) · airframe 71,021 hrs · 26,638 cycles

ENGINE OIL PRESSURE READS 9 PSI STATIC ENG :REF: MIT 79-32-00-500A. OIL TRANSMITTER REPLACED 25 HRS. REPLACED NR 2 ENGINE OIL PRESSURE TRANSMITTER, LEAK CHECKED GOOD.

Part: ACCESSORY UNIT — MALFUNCTIONED (CABIN) · airframe 69,841 hrs · 26,203 cycles

CABIN INTERPHONE INOPERATIVE. REPLACED AUDIO ACCESSORY UNIT, CHECKS OKAY OPBLM.

Part: COUPLING — LEAKING (FUEL SYSTEM) · airframe 69,601 hrs · 26,120 cycles

FUEL LEAKING FROM NR 1 ENGINE. FOUND FUEL LEAKING FROM COUPLING O-RING. REMOVED GAMA COUPLING FOUND SEALING SURFACES GALLED. MM 28-22-07 PG 617 ITEM (D). REMOVED FUEL LINE FROM FWD SPAR TO THE NEXT FWD COUPLING. INSTALLED TUBE ASSY WITH NEW PACKINGS. LEAK CHECKED GOOD.

Part: O-RING — FAILED (HYD SYSTEM) · airframe 69,530 hrs · 26,097 cycles

LEFT HYD SYS INOPERATIVE, RETURNED TO FIELD. LOW QUANTITY. REPLACED LE SLAT BYPASS VALVE. FOUND O-RING ON FITTING DESTROYED. SERVICED HYD TO FULL CYCLED ALL FLIGHTS CONTROLS, NO LEAKS NOTED.

Part: OIL SYSTEM — LEAKING (ENGINE) · airframe 67,713 hrs · 25,414 cycles

CREW REPORTED OIL QUANTITY IS 13 ON RIGHT ENGINE. WITH THE HELP OF THE FLT CREW RAN ENGINE FOR 5 MIN, CHECKED OIL LEVEL AFTER RUN, LEVEL RECOVERED TO DISPATCH LEVEL (20 PLUS QTS) O.K. TO CONTINUE.

Part: LIGHT — FAULTY (CABIN) · airframe 66,701 hrs · 25,052 cycles

LEFT ENGINE START AT GATE, ALL PARAMETERS NORMAL, UPON PUSHBACK PAX ALERTED FLIGHT CREW THAT SMOKE HAD FILLED THE CABIN. CREW SHUTDOWN LT ENGINE AND SOON AFTER SMOKE HAD CLEARED. RAN NO SMOKE NOTED FOR 10 MIN. WALK THROUGH CABIN FOUND NOTICEABLE SMOKE ODOR ABOVE CEILING AREA STARTING FROM ROWS 30 AND AFT. ODOR SIMILAR TO BALLAST TYPE. RT LAST ROW SIDE WALL LIGHT INOP. REPLACED LIGHT ASSY AND RELAMPED OPS CHECKED OK. NR 2 LT DOOR CEILING LIGHT INOP. REPLACED BALLAST AND RELAMPED, OPS CHECKED OKAY.

Part: CONTROL PANEL — MALFUNCTIONED (FUEL SYSTEM) · airframe 66,655 hrs · 25,036 cycles

DURING CLIMB WHEN THE CTR FUEL PUMPS WERE TURNED OFF, GOT ALL 4 MAIN TANK PUMP LOW PRESS. 4 MAIN TANK LOW PRESSURE LIGHT CAME ON FOR ABOUT 5 SECONDS. REPLACED FUEL MANAGEMENT CONTROL PANEL IAW MM. TESTED OK. ALL FUEL PRESSURE LIGHTS ARE INDICATING NORMAL.

Part: SKIN — PUNCTURED (DOOR) · airframe 66,507 hrs · 24,979 cycles

4L MED HAS INNER SKIN PUNCTURED AT UPPER HINGE. REPAIR ACCOMPLISHED ON 8130 TRACKING NR 377899, DAMAGED WAS REPAIR IAW REO- G13451 REV A DATED 1-5-11.

Part: LONGERON — CRACKED (BS 426 S4L) · airframe 65,626 hrs · 24,631 cycles

FUSELAGE CRACK STA 426, STR 4L,11"LONG. MAJOR REPAIR ACCOMPLISHED: REPAIRED IAW EVA 80084. REPAIR IS APPROVED FOR STATIC STRENGTH. A NEW 8100-9 MUST BE ISSUED PRIOR TO SEP 17 2012 OR A-C WILL BECOME UNAIRWORTHY. THIS REPAIR APPROVED FOR STATIC STRENGTH. COMPLIANCE TO 14CFR 26.43(D) AND 25.571 IS DF'D FOR PERIOD NOT TO EXCEED 24 MONTHS FROM 9-17-2010. A NEW 8100-9 MUST BE ISSUED FINDING COMPLIANCE.

Part: SKIN — CRACKED (BS 426 S4L) · airframe 65,623 hrs · 24,630 cycles

FUSELAGE CRACK ON UPPER CROWN AREA. CRACK MEASURES 10.75 INCHES. LOCATED AT STA 426 STRINGER S4L AND ABOVE FIRST PAX WINDOW LT SIDE. ACCOMPLISHED HFEC INSP OF CUT OUT PER NDT, ALSO ACCOMPLISHED EXISTING FASTENER HOLES PER NDT PART 6. NO CRACK INDICATIONS NOTED AT THIS TIME. MFG & INSTALLED STRUCTURAL FILLERS, DOUBLER AND TRIPLER, DRILL, ALODINE AND PRIME PER UA-EVA-80084. ACCOMPLISHED INSP OF REPAIR PARTS AS REQUIRED PER EVA 80084.

Part: SMOKE DETECTOR — FAULTY (AFT CABIN) · airframe 65,032 hrs · 24,418 cycles

AFT CABIN AFT SMOKE DETECTOR WILL NOT SHUTOFF. DISCONNECTED SMOKE DETECTOR. REPLACED DETECTOR, OPS NORMAL.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 64,074 hrs · 24,053 cycles

FOUND FWD OF AFT LAV EMERGENCY EGRESS LIGHTING NOT WORKING. REPLACED EGRESS LIGHTING STRIP FWD OF AFT LAV.

Part: LIGHT — BROKEN (CABIN) · airframe 63,102 hrs · 23,676 cycles

EMERGENCY LIGHT STRIP BROKE AT FIRST CLASS CLOSET AS ADVISED BY CREW. REPLACED EMERGENCY LIGHT STRIP AND FEEDER CABLE, OP CKS GOOD.

Part: ATTACH BRACKET — BROKEN (EVAC SLIDE) · airframe 60,924 hrs · 22,856 cycles

DOOR L1 SLIDE LWR ATTACH BRACKET IS BROKEN. INSTALLED NEW ATTACH BRACKET.

Part: PANEL — DELAMINATED (THRUST REVERSER) · airframe 60,436 hrs · 22,651 cycles

NR 2 ENG OUTBOARD & INBOARD RVSR BIFURCATION PANELS ARE DELAMINATED. PANEL REMOVED & REPAIRED ON R&R 82729 AND RE-INSTALLED IN NR 2 ENGINE RT REVERSER UPPER ASSY.

Part: PANEL — DAMAGED (THRUST REVERSER) · airframe 60,436 hrs · 22,651 cycles

NR 2 ENG OUTBOARD & INBOARD RVSR BIFURCATION PANELS ARE DAMAGED.

Part: BATTERY — DISCHARGED (CABIN) · airframe 59,462 hrs · 22,264 cycles

THE 1R DOOR EMERGENCY LIGHT INOP. REPLACED BATTERY POWER PACK FOR M730. OPS CHECKS GOOD.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 58,981 hrs · 22,075 cycles

DOOR 1R EMERGENCY SLIDE LIGHT, EXIT LOCATOR, PASS EXIT SIGN, CL DIV EXIT LIGHT AND 1 EMER AISLE LIGHT INOP. REPLACED BATTERY ASSY FOR M730. OPS CHECKS GOOD.

Part: LIGHT — NO TEST (L2 DOOR SLIDE) · airframe 58,659 hrs · 21,963 cycles

SLIDE LIGHT DOOR 2L NO LONGER ILLUMINATED. *S/D* MISSING HARDWARE REQUIRED TO ARM MECHANISM (UNKNOWN DAMAGE). REPLACED MISSING HARDWARE FOR AFT ROD END THAT ARMS THE DOOR. INSTALLED, OPS CHECKS GOOD.

Part: ENGINE — BIRD INGESTION (NR 2) · airframe 56,811 hrs · 21,276 cycles

RTFL UNDER AMBER ALERT DUE TO BIRD INJESTION IN THE NR 2 ENGINE. ENGINE SHUT DOWN AFTER LANDING.

Part: SKIN — DENTED (BS 1794 S22-23R) · airframe 56,163 hrs · 21,046 cycles

FUSELAGE EXTERNAL SURFACE DENTED AT BS 1794 BETWEEN STR 22R-23R. 10-9-07 MAJOR REPAIR ACCOMPLISHED. REMOVED DAMAGE AND INSTALLED REPAIR.

Part: SKIN — DAMAGED (NR 2 NACELLE) · airframe 56,163 hrs · 21,046 cycles

NR 2 PYLON FWD I/B SIDE SKIN AT NAC STA 125 HAS EXISTING FASTENER HOLE ELONGATED. HFEC INSPECTED, NO DEFECTS NOTED. INSTALLED 2EA FREEZE PLUGS.

Part: WIRE — BROKEN (EMERGENCY LIGHTS) · airframe 56,163 hrs · 21,046 cycles

DOOR 4L EMERGENCY LIGHT SWITCH OVER DOOR IS INOP.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 56,163 hrs · 21,046 cycles

R-1 DOOR EXTERNAL EMERGENCY LIGHT IS INOP. 10-9-07 TROUBLESHOOTING THE SYSTEM, FOUND BROKEN GROUND JIFFY SPLICE WIRE , REPAIRED SPLICE ON DOOR 4L EMERGENCY LIGHT TEST SWITCH, ALSO REPLACED BATTERY PACK DOOR 4L FWD CEILING.

Part: ARM — MISINSTALLED (R4 DOOR) · airframe 56,163 hrs · 21,046 cycles

DOOR 4R EMERGENCY POWER ASSIST BOTTLE HAS TRIGGER ARM IMPROPERLY INSTALLED. 10-11-07 THIS ASSIST BOTTLE PREVIOUSLY DISCHARGED. INSTALLED NEW EMERGENCY POWER RESERVOIR FOR DOOR 4L FOUND CABLE INSTALLED PROPERLY; THE BOTTLE HAVING BEEN DISCHARGED HAD THE APPEARANCE OF INCORRECT INSTALLATION.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 56,163 hrs · 21,046 cycles

AFT PIT STA 1398 ABOVE 27R FLOOR SUPPORT CORRODED. MAJOR REPAIR ACCOMPLISHED. REMOVED CORROSION AND CHECKED LIMITS - MATERIAL THICKNESS FOUND 0.063. REMAINING MATERIAL 0.044 WAS OUT OF LIMITS OF SRM. REMOVED STRINGER AND FABRICATED NEW STRINGER, APPLIED ALODINE, PRIMED AND INSTALLED REPAIR PER SRM, PAINTED AND SANDED.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 56,163 hrs · 21,046 cycles

RIGHT EXTERNAL FUSELAGE STA 1180, BETWEEN STR 27R- 28R, STRINGER SHEAR TIE CRACKED, AFT SIDE OF RIGHT W/W.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 56,163 hrs · 21,046 cycles

LEFT EXTERNAL FUSELAGE, STA 1180 BETWEEN STR 27L- 28L, SHEAR TIE HAS CRACK INDICATION INBOARD AREA AT RADIUS.

Part: DOUBLER — DENTED (FUSELAGE) · airframe 56,163 hrs · 21,046 cycles

FUSELAGE SKIN DOUBLER REPAIR DENTED AT UPPER LT CORNER STA 750 BETWEEN STR 15L AND 16L.

Part: SKIN — DAMAGED (BS 690 S2-3L) · airframe 56,163 hrs · 21,046 cycles

EXTERNAL FUSELAGE HAS HOLE IN SKIN AT BS 690 BETWEEN STR 2L-3L.

Part: SMOKE DETECTOR — FAULTY (FWD CARGO BAY) · airframe 56,071 hrs · 21,013 cycles

STATUS MSG: FWD CARGO DETECTOR 2.

Part: CONTROL VALVE — MALFUNCTIONED (CABIN COOLING) · airframe 55,763 hrs · 20,903 cycles

UNABLE TO COOL CABIN. TEMP IN CABIN ABOVE 85 DEGREES. TRIED ALL CONFIGURATIONS. TRIM AIR OFF, STDBY COLD, ONE PACK AT A TIME, BOOSTING ENGINE BLEEDS, ALL NO HELP. [08-08-07] DURING PACK OPERATIONAL TEST FOUND LEFT PACK TEMP CONTROL VALVE FAULT ON BITE BOX. REPLACED PACK, NOW OPERATES NORMAL.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 55,147 hrs · 20,670 cycles

RECEIVED FLAPS DISAGREE INDICATION ON APPROACH. [SUP 06-06-07] FLAPS FAILED TO MOVE. TRAILING EDGE LIGHT ILLUMINATED. EICAS MESSAGE 'TE FLAP DISAGREE' DISPLAYED. FLAPS OPERATE NORMALLY ON ALTERNATE SYSTEM. CONDUCTED OPERATION CHECKS OF THE FLAP AND LEADING EDGE SYSTEM, COULD NOT DUPLICATE PROBLEM AND CAUSE OF DISCREPANCY NOT ESTABLISHED.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 55,109 hrs · 20,658 cycles

EEL STRIP IN FRONT OF FWD AFT LAV INOPERATIVE. [SUP 05-08-07] REPLACED EEL STRIP. OPS CHK OK.

Part: TRIM SYSTEM — MALFUNCTIONED (STABILIZER) · airframe 53,988 hrs · 20,257 cycles

UNCOMMANDED STAB TRIM DURING CLIMBOUT. NOSE DOWN TRIM WAS FELT. SAM HAD NO FAULT BALLS LATCHED. DETERMINED THE PROBLEM TO LEFT SAM. REPLACED LEFT SAM STABILIZER-TRIM /AILERON LOCKOUT UNIT.

Part: WARNING MESSAGE — ILLUMINATED · airframe 53,310 hrs · 20,006 cycles

LANDED ORD UNDER AMBER ALERT DUE TO HYDRAULIC SYSTEM EICAS MESSAGE. LT HYD QTY INDICATION DROPPED TO 0.45 WITH ASSOCIATED REFILL AND LOW QTY ON EICAS. LT SYSTEM HYD PUMPS CURRENTLY TURNED "OFF" PER FLIGHT MANUAL TO CONSERVE REMAINING FLUID FOR APPROACH & LANDING. FLUID LEVEL STABLE AT 0.45 AT THIS TIME WITH PUMPS "OFF". REPLACED DAMAGED O-RING ON LT HYD ACMP REDUCER. FILLED RESERVOIR AND OPERATED LT HYD SYSTEM USERS.

Part: UNKNOWN — PEELING (UNKNOWN) · airframe 50,786 hrs · 19,043 cycles

LT WING NR 5 LEADING EDGE SLAT TRAILING EDGE WEDGE DAMAGED, PNL ON TOP OF WING JUST AFT OF NR 5 SLAT ALSO DAMAGED. ENGINEERING IS CONDUCTING ADDITIONAL INVESTIGATIONS FOR CAUSES OF THIS TYPE OF FAILURE. FAILURE OF THE LAMINATE ON WING. LE SLATS IS A SYSTEMIC PROBLEM. ROOT CAUSE FOR FAILURE IS ATTRIBUTED TO EITHER MOISTURE INGRESSION/SATURATION OF TE WEDGE, VIBRATION AND/OR AERODYNAMIC FLUTTER, AND/OR RIGGING. ALTHOUGH MOISTURE AND FLUTTER CAUSES REQUIRE NO ELABORATION, RIGGING CAN LEAD TO SLAT BEING SUBJECTED TO DEFORMATION WHEN CYCLED THAT RESULTS IN FAILURE OVER TIME.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 50,639 hrs · 18,990 cycles

EEL INOP AT AND AROUND DOOR 3L.

Part: POWER SUPPLY — ACTIVATED (CABIN) · airframe 50,152 hrs · 18,800 cycles

THE FOLLOWING EMERGENCY LIGHTS ARE INOP: EXTERIOR, LEFT FWD OVERWING, DOOR 4L. INTERIOR, EXIT SIGN OVER DOOR 4L, EXIT MARKERS AT DOORS 4L & 4R, OVERHEAD EXIT SIGN IN AFT GALLEY, AISLE LIGHTS AT ROWS 29 & 32. LEFT AFT HATCH ILLUMINATION LIGHTS, AFT LIGHT IN RIGHT FWD HATCH ILLUMINATION. REPLACED M10818 POWER SUPPLY.

Part: COFFEEMAKER — SHORTED (GALLEY) · airframe 49,220 hrs · 18,443 cycles

COFFEEMAKER DELIVERED SHOCK TO FLIGHT ATTENDANT IN REAR GALLEY. UNIT TESTED ONLY AFTER BURST HEATER WAS REPLACED. CAN ONLY SPECULATE BURST HEATER CARTRIDGE IN WATER MAY HAVE BEEN SOURCE OF STRAY CURRENT. UNIT BONDING OK.

Part: TRIM SYSTEM — MALFUNCTIONED (RUDDER) · airframe 45,758 hrs · 17,120 cycles

PLANE HAD RIGHT RUDDER TRIM PROBLEM. ADDITIONAL PROBLEMS WITH SPOILERS. FAILED RUDDER TRIM ACTUATOR INHIBITED ABILITY TO TRIM RUDDER. REMOVED AND REPLACED SUBJECT RUDDER TRIM ACTUATOR WITH NEW SERVICABLE ACTUATOR. THE NR 9 SPOILER ACTUATOR WAS REPLACED TO ADDRESS ASSOCIATED SPOILER PROBLEMS.

Part: LINE — CRACKED (RT PYLON) · airframe 41,385 hrs · 15,561 cycles

ON LANDING, LOST RT HYDRAULICS. THE NR 2 ENGINE REVERSER HYDRAULIC PRESSURE TUBE WORE THRU AND LEAKED. CAUSE OF THE TUBING WEAR WAS FROM A DEGRADED CLAMP RUBBER SLEEVE CAUSED BY ENGINE VIBRATION. TUBE WAS REPLACED AND A NEW CLAMP WAS INSTALLED.

Part: LINE — LEAKING (NR 2 ENGINE) · airframe 40,405 hrs · 15,172 cycles

LOW OIL INDICATION ON NR 2 ENGINE. ON DOWNWIND LEG, OIL PRESSURE AND QUANTITY DROPPED TO ZERO. WINDMILLED FOR ABOUT 7 MINS PER CREW. FOUND MAIN OIL PRESSURE TRANSMITTER LINE LEAKING. SECURED LINE, CHANGED OIL FILTER AND CHECKED CHIP DETECTORS. CHIP DETECTORS CHECKED OKAY AND CLEANED. SERVICE ENG OIL TO FULL ADDED 18 QTS, ALL LEAK CHECKS GOOD. ENGINE WAS NOT REPLACED.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 38,086 hrs · 14,310 cycles

CABIN FLOORBEAM CORRODED BETWEEN RBL 6 AND RBL 56, STA 365. MAJOR REPAIR ACCOMPLISHED. SPLICED IN NEW T-CAP.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 38,086 hrs

CABIN FLOORBEAM HAS EXCESSIVE CORROSION BETWEEN RBL 6 - RBL 56 STATION 365. MAJOR REPAIR ACCOMPLISHED. INSTALLED T-CAP SPLICE.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 38,086 hrs · 14,310 cycles

CABIN FLOOR BEAM CORRODED BETWEEN RBL6 TO RBL 56. SUPPLEMENTAL DATA UPDATE MAJOR REPAIR ACCOMPLISHED.REPLACED T-CAP.

Part: SKIN — DENTED · airframe 38,086 hrs · 14,310 cycles

FUSELAGE SKIN DENT STATION 1717 STRINGER 14L. MAJOR REPAIR ACCOMPLISHED. DAMAGED REMOVED DOUBLER AND FILLER INSTALLED, SKIN LAP AREA BEHIND DOOR 4L.

Part: FRAME — CRACKED (FUSELAGE) · airframe 38,086 hrs · 14,310 cycles

AFT PIT STA 1400 JUST ABOVE STRINGER 25L, UPPER CHORD IS DENTED AND CRACKED. MAJOR REPAIR ACCOMPLISHED. INSTALLED REPAIR SPLICE ON FRAME.

Part: CLIP · airframe 38,086 hrs · 14,310 cycles

FRAME STATION 1400 STRINGER 25L CLIP REPLACE DUE TO FRAME SPLICE REPAIR. MAJOR REPAIR ACCOMPLISHED. REPLACED STRINGER CLIP.

Part: CLIP · airframe 38,086 hrs · 14,310 cycles

FRAME STATION 1400 STRINGER 26L CLIP REPLACE DUE TO FRAMESPLICE REPAIR. MAJOR REPAIR ACCOMPLISHED.REPLACED STRINGER 26L CLIP.

Part: FRAME — DENTED · airframe 38,086 hrs · 14,310 cycles

AFT PIT FRAME AT STATION 1420 DENTED BETWEEN STRINGER 25L AND 26L. MAJOR REPAIR ACCOMPLISHED.FORMED DOUBLER WAS INSTALLED ON FRAME.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 39,086 hrs · 14,310 cycles

AFT CABIN FLOORBEAM WEB CORRODED STA 1685, RBL 51. MAJOR REPAIR ACCOMPLISHED. INSTALLED UPPER SURFACE DOUBLER STA 1685, RBL 47.5 TO RBL 54.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 38,086 hrs · 14,310 cycles

CABIN FLOORBEAM AT STA 297, RBL 34 CORRODED. MAJOR REPAIR ACCOMPLISHED. INSTALLED UPPER SURFACE STRAP REPAIR STA 297, RBL 41 TO RBL 47.5.

Part: FAN — FAILED (CABIN)

AIRCRAFT DIVERTED TO DEN DUE TO STRONG ELECTRICAL SMELL IN CABIN. *S/D* SMELL WAS CAUSED BY A FAILED RT RECIRCULATION FAN. RT FAN WAS REPLACED AND NO FURTHER DISCREPANCIES WERE NOTED.

Part: TUBE — LEAKING (SLIDE)

SLIDE FAILED AIR RETENTION TEST DURING SHOP VISIT. *S/D* POROSITY CAUSED SEAM LEAK. UNIT WAS SENT TO VENDOR FOR EVALUATION AND REPAIR.

Part: SLIDE — DISASSEMBLED (DOOR 4R)

AT DEPARTURE TIME FOUND APPROXIMATELY 15 FEET OF GREEN CORD HANGING OUT OF DOOR 4R. SLIDE REPLACED. *S/D* CAUSE UNKNOWN. REPLACED DOOR SLIDE.

Part: STATOR VANE — FAILED (ENGINE)

AT FLIGHT LEVEL 370 EXPERIENCED MULTIPLE COMPRESSOR STALLS. FLIGHT DIVERTED TO ORD. *S/D* 15TH STAGE STATOR VANE SEGMENT FAILED. REPLACED 15TH STAGE VANE AT SHOP VISIT.

Part: HPC ROTOR — FRACTURE (NR 2 ENGINE)

NR 2 ENGINE REMOVED FOR HPT T1 BLADE DISTRESS, DISCOVERED DURING BORESCOPE INSPECTION. DISASSEMBLY OF THE ENGINE REVEALED FOD DAMAGE THROUGHOUT ALL STAGES OF THE COMPRESSOR 6TH THROUGH 17. *S/D* C6 BLADES OLD STYLE RECEIVED FOD, DEBRIS FROM C6 BLADES CAUSED ADDITIONAL DAMAGE DOWNSTREAM THROUGH C17. ALL BLADES REPLACED WITH NEW AND OPERATION CHECKS NORMAL.

Part: COMPRESSOR — STALLED (NR 1 ENGINE)

NUMBER ONE ENGINE HAD A COMPRESSOR STALL IN FLIGHT. ENGINE RECOVERED AND CONTINUED OPERATING. PRIOR TO STALL ENGINE WAS DECELERATING. *S/D* PERFORMED ENGINE BORESCOPE, 6TH THROUGH 9TH STAGE COMPRESSOR BLADES AND 2ND, 3RD STAGE LOW PRESSURE TURBINE, ALL CHECK OK.

Part: WIRE — WORN (FUEL CONTROL)

DURING CLIMB-OUT FROM PHL, RECEIVED EICAS MESSAGE ON LEFT ENGINE PRIMARY CONTROL, ACCOMPANIED BY LENGTHY SECONDARY CONTROL MESSAGE. FLIGHT DIVERTED TO ORD. CONNECTOR W2P7 ON FUEL CONTROL HAD LOOSE BACKSHELL. WIRES WERE TWISTED IN BUNDLE INSIDE BACKSHELL. ONE WIRE HAD INSULATION WORN THROUGH. REPAIRED INSULATION AND INSTALLED CONNECTOR. OPERATION CHECKS NORMAL.

Part: LIGHT STRIP — INOPERATIVE (CABIN)

EMERGENCY ESCAPE LIGHTING INOP ROWS 24A THROUGH 31A. REPLACED DEFECTIVE LIGHT STRIP, OPERATION CHECKS NORMAL.

Part: CONNECTOR — LOOSE (CABIN)

EMERGENGY ESCAPE LIGHTING INOP ROWS 24 TO 32 ABC. SECURED LEAD IN CONNECTOR AND OPERATION CHECKS NORMAL.

Part: LAMP — INOPERATIVE (CABIN)

SEAT 34C OVERHEAD EMERGENCY LAMP INOP. RELAMPED.

Part: EEL — INOP (CABIN)

EMERGENCY EXIT LIGHT AT ROW TWO INOP. REPLACED LIGHT, CHECKS OK.