N68041

Part: CADC — MALFUNCTIONED · airframe 91,352 hrs · 34,030 cycles

ABORTED AT 85 KTS DUE TO NO AIRSPEED INDICATION ON CAP SIDE. REMOVED AND REPLACED CADC IN ACCORDANCE WITH M/M 34-16-01. OPERATIONAL CHECK GOOD IN ACCORDANCE WITH M/M 34-16-00 AND M/M 34-11-00.

Part: ENGINE — FLAMED OUT (NR 1) · airframe 91,322 hrs · 34,012 cycles

NR 1 ENGINE FLAMED OUT; ENGINE FAILED/SHUTDOWN IN FLIGHT CHECKLIST COMPLETED (ENGINE VIBRATION STOPPED) SHUTDOWN O505Z; WINDMILLING O.P. 10 PSI. TROUBLESHOOT FUEL SYSTEM AND FOUND METAL DEBRIE IN FUEL FILTER. REMOVED AND REPLACED FUEL PACKAGE IN ACCORDANCE WITH M/M 73-12-01; FOUND SHROUDED FUEL TUBE AT 6 O'CLOCK DAMAGE. REMOVED AND REPLACED FUEL SHROUDED TUBE IN ACCORDANCE WITH M/M 73-13-02. OPERATIONAL CHECK NORMAL, NO LEAKS FOUND.

Part: CONNECTOR — DAMAGED (HEATER CONTROL) · airframe 91,256 hrs · 33,973 cycles

LEFT STATIC PORT HEAT AND RIGHT STATIC PORT HEAT AND LEFT ANGLE OF ATTACK C/B`S POPPED WITH LIGHT SMOKE FROM AROUND THE FIRE HANDLES. REMOVED AND REPLACED CONNECTOR FROM HEATER CONTROLLER IN ACCORDANCE WITH M/M 20-30-02, AND REMOVED AND REPLACED HEATER CONTROLLER MONITOR IN ACCORDANCE WITH M/M 30-35-01. OPERATIONAL CHECK NORMAL IN ACCORDANCE WITH M/M 30-30-00.

Part: OUTFLOW VALVE — LACK OF LUBE (CABIN PRESSURE) · airframe 91,244 hrs · 33,969 cycles

WITH ALL 3 PACKS OPERATING, UNABLE TO MAINTAIN CABIN ALTITUDE BELOW 10,000. OUTFLOW VALVE FULL CLOSED (MANUALLY). FOUND THRUST RECOVERY VALVE LOCKED OPEN; LUBED OUTFLOW VALVE MECHANISM; CHECK MANUALLY OPERATION NORMAL ON GROUND IN ACCORDANCE WITH DC-10 M/M 21-31-04 AND 21-30-00. TRANSFERED TO DMI NR 20774.

Part: HOSE — DAMAGED (HYD SYSTEM) · airframe 91,028 hrs · 33,835 cycles

DEPARTING MNMG, LOST HYDRAULIC PRESSURE AND QUANTITY NR 3 SYSTEM; PERFORMED APPLICABLE CHECKLIST, AND CONTINUED TO MROC. REMOVED AND REPLACED RT MAIN LANDING GEAR TRIM CYLINDER HYDRAULIC HOSE ASSEMBLY IN ACCORDANCE WITH M/M 20-40-02; SERVICED NR 3 HYDRAULIC SYSTEM IN ACCORDANCE WITH M/M 12-13-02. OPERATIONAL CHECK MAIN HYDRAULIC SYSTEM IN ACCORDANCE WITH M/M 29-00-00 AND 29-02-00, NO LEAK NOTED; RETURN LANDING GEAR HANDLE TO ITS NORMAL OPERATION IN ACCORDANCE WITH M/M 32-30-00.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 90,892 hrs · 33,749 cycles

DURING CRUISE RT WINDSHIELD CRACKED. REMOVED AND REPLACED RT WINDSHIELD PANEL IN ACCORDANCE WITH M/M 56-11-00. OPERATIONAL CHECK PERFORMED IN ACCORDANCE WITH M/M 30-41-00 AND M/M 30-42-00, FOUND NORMAL OPERATION.

Part: WINDOW — DISLODGED (COCKPIT) · airframe 90,842 hrs · 33,720 cycles

ON TAKEOFF ROLL ,F/O SLIDING WINDOW CAME OFF TRACK CAUSING LOW SPEED ABORT. PREFLIGHT INSPECTION OVER CENTER LOCKED AND NORMAL. LUBRICATED INSPECTED AND ADJ. SLIDING WINDOW CHECKED OPERATION SEVERAL TIMES AND FOUND NORMAL IAW DC-10 MM 56-12-00.

Part: FRAME — CORRODED (LT WING) · corrosion level 2 · airframe 90,449 hrs · 33,501 cycles

DURING AN "A" CHECK INSPECTION, THE FOLLOWING WAS FOUND; LT MAIN LANDING WHEEL WELL AT STATION 1381; SLANT PANEL PRESSURE BULKHEAD SHIMS INSTALLED AROUND CAP ANGLE/STRUCTURAL FRAME ARE DISPLACED DUE TO PRESENT CORROSION AND BROKEN RIVETS; FRAME STRUCTURE INBOARD SIDE LOWER CORNER FOUND WITH CORROSION.

Part: FITTING — CORRODED (RT WING) · corrosion level 2 · airframe 90,449 hrs · 33,501 cycles

DURING AN "A" CHECK, THE FOLLOWING WAS FOUND; RT MAIN LANDING GEAR WHEEL WELL STATION 1381; SLANT PANEL PRESSURE BULKHEAD CAP ANGLE/STRUCTURAL FRAME HAS CORROSION ON BOTH INBOARD AND OUTBOARD LOWER CORNERS; WING CENTER SECTION REAR SPAR JOINT WITH RT PANEL, THE VERTICAL FITTING BETWEEN BOTH PARTS HAS CORROSION AT THE UPPER AREA.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 90,431 hrs · 33,490 cycles

NR 1 ENGINE FAILED TO ACCELERATE PASS 80 PERCENT N1; ABORTED TAKEOFF AT 75 KTS. REMOVED AND REPLACED MAIN FUEL PUMP AND FUEL CONTROL ASSEMBLY IN ACCORDANCE WITH M/M 73-12-01; PERFORMED LEAK CHECK, NO LEAKS NOTED; PERFORMED ENGINE RUN AND TRIM IN ACCORDANCE WITH M/M 71-00-00; OPERATIONAL CHECK WITHIN LIMITS AT THIS TIME.

Part: PUMP — UNKNOWN (FUEL SYS) · airframe 90,179 hrs · 33,351 cycles

NR 2 ENGINE WOULD NOT SPOOL UP ON THE RUNWAY. REMOVED AND REPLACED NR 2 ENGINE MEC/FUEL PUMP PACKAGE IN ACCORDANCE WITH M/M 73-45-01 AND M/M 73-20-01; FOUND NORMAL ON ENGINE RUN-UP IN ACCORDANCE WITH M/M 71-00-00.

Part: ENGINE — ERRATIC (EGT) · airframe 90,021 hrs · 33,256 cycles

DURING INITIAL CLIMBOUT OF MIAMI, ENGINE NR 1 EGT BECAME VERY ERRATIC AND FLUCTUATED INTO AN OVERTEMP CONDITIONS; RESET C/B, NO HELP. REMOVED AND REPLACED NR 1 ENGINE IAW ARROW AIR MSG-3 DC10 J/C 141R7101M. OPERATIONAL CHECK NORMAL IAW M/M 72-00-00.

Part: ANTENNA — FAILED (WX RADAR SYSTEM) · airframe 90,005 hrs · 33,248 cycles

BOTH RADARS INOPERATIVE, ANTENNA FAIL DISPLAYED ON BOTH RADAR SCREENS. REMOVED AND REPLACED WEATHER ANTENNA IAW MM 34-41-01 GROUND TEST (OPERATIONAL CHECK) NORMAL IAW MM 34-41-00.

Part: ENGINE — STALLED (COMPRESSOR) · airframe 89,742 hrs · 33,106 cycles

LOG PAGE NR 117483. NR 3 ENGINE COMPRESSOR STALLED. SHUTDOWN ENGINE. (SEE LOG PAGE NR 117486) REMOVED NR 3 ENGINE DUE TO COMPRESSOR STALLED AND REPLACED NR 3 ENGINE IAW ARROW AIR MM CHECK CARD NR 143-R7101; RUN UP CHECK GOOD. ACCOMPLISHED RED BORDER NR 18948; OPERATIONAL CHECK NORMAL.

Part: FITTING — BROKEN (RT MLG DOOR) · airframe 89,645 hrs · 33,063 cycles

LOG PAGES NR 116686 AND NR 116688. ON SERVICE CHECK FOUND LT MAIN LANDING GEAR DOOR ROLLER ASSEMBLY LOWER SUPPORT FITTING BROKEN. REMOVED AND REPLACED LT MAIN LANDING GEAR DOOR IAW MM 32-14-01. OPERATIONAL CHECK NORMAL IAW MM 32-10-01.

Part: CABLE — DAMAGED (DOOR MECHANISM) · airframe 89,239 hrs · 32,892 cycles

MAIN CABIN L1 DOOR WITH DOOR OPEN, NO WARNING LIGHT. UPON INSPECTION OF DOOR MECHANISM FOUND DAMAGED CABLES AT AFT SECTION OF L1 DOOR. REMOVED DAMAGED SECTIONS IAW M/M 52-10-02; INSTALLED PASSENGER DOOR DRIVE CABLE IAW M/M 52-10-02. OPERATIONAL CHECK OK.

Part: WIRE HARNESS — DAMAGED (EGT LEAD)

NR 2 EGT FAILED IN FLIGHT. REMOVED AND REPLACED EGT LEAD JUNCTION IN ACCORDANCE WITH M/M 77-21-02. SYSTEM TESTED IN ACCORDANCE WITH M/M 77-21-01 AND 77-21-00; FOUND NORMAL.

Part: TARGET — OUT OF ADJUST (MLG DOOR) · airframe 88,627 hrs · 32,595 cycles

AFTER GEAR RETRACTION LEFT GEAR; LIGHT REMAINED ILLUMINATED; PERFORMED CHECK LIST, NO HELP, OBSERVED SPEED LIMITS (GEAR). PERFORMED T/S FOUND TARGET SWITCH BROKEN. REMOVED AND REPLACED TARGET BRACKET IN ACCORDANCE WITH M/M 32-14-01. PERFORMED MAIN LANDING GEAR EXTENSION AND RETRACTION, FOUND NORMAL IN ACCORDANCE WITH M/M 32-30-0.

Part: IGNITER — DEFECTIVE (NR 1 ENGINE) · airframe 88,541 hrs · 32,560 cycles

DURING ENGINE START NR 1 ENGINE IGNITION -A- INOPERATIVE; TRANSFER TO DMI NR 19182 AS PER MEL 74-1-1 CATEGORY-C. REMOVED AND REPLACED NR 1 ENGINE -A- IGNITOR IN ACCORDANCE WITH M/M 74-20-02; OPERATIONAL CHECK NORMAL.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 88,519 hrs · 32,550 cycles

ON POST FLIGHT, FOUND EVIDENCE OF HYDRAULIC LEAK AT RT WING ROOT AREA AT TOP OF RT MAIN LANDING GEAR AREA. CUT; FABRICATED; AND INSTALLED PERMANENT LINE AT RT WING ROOT AT TOP OF RT MAIN LANDING GEAR IN ACCORDANCE WITH M/M 20-10-01. NO LEAKS NOTED.

Part: WIRE — BROKEN (AIRSPEED IND) · airframe 88,360 hrs · 32,482 cycles

DURING INITIAL TAKEOFF ROLL, NO AIR SPEED INDICATION ON CAPTAIN'S SIDE, ABORTED TAKEOFF AT 90 KNOTS. REPAIRED BROKEN WIRE AT CAPTAIN'S AIRSPEED INDICATION CONNECTOR (P1-102T) IN ACCORDANCE WITH M/M 20-30-00. PERFORMED DADC BITE TEST IN ACCORDANCE WITH M/M 34-13-00, FOUND NORMAL.

Part: SWITCHING UNIT — MALFUNCTIONED (COCKPIT) · airframe 88,232 hrs · 32,411 cycles

AIRSPEED FLAGGED AT HOLDING POINT RUNWAY 9, BARBER POLE STUCK AT 250 IAS NEEDLE FLUCTUATES BETWEEN ZERO (O) AND SIXTY (60) KTS. REMOVED AND REPLACED CADC SWITCHING UNIT IN ACCORDANCE WITH MM 34-16-03. OPERATIONAL CHECK NORMAL IN ACCORDANCE WITH MM 34-16-00.

Part: DOOR — UNSECURE (E/E BAY) · airframe 88,072 hrs · 32,338 cycles

AFTER TAKEOFF UNABLE TO PRESSURIZE. SECURED AFT AVIONICS DOOR IN ACCORDANCE WITH MM 52-00-00 AND PRESSURIZED AIRCRAFT IN ACCORDANCE WITH MM 21-30-00. OPERATIONAL CHECK NORMAL.

Part: ENGINE — FAILED (NR 2) · airframe 88,069 hrs · 32,336 cycles

NR 2 ENGINE FAILED ON ROTATION. ENGINE SHUTDOWN IN ACCORDANCE WITH CHECKLIST. AIRCRAFT RETURNED TO MSLP WITHOUT ANY FURTHER INCIDENT. ACCOMPLISHED RED BORDER 019056; REMOVED AND REPLACED NR 2 ENGINE IN ACCORDANCE WITH ARROW AIR DC-10 WORK CARD 142R7101M. PERFORMED ENGINE RUN IN ACCORDANCE WITH MM 11-00-00; ALL SYSTEMS INVOLVED OPERATIONAL CHECK OK.

Part: ADC — MALFUNCTIONED (COCKPIT) · airframe 88,055 hrs · 32,327 cycles

ABORTED TAKEOFF AT 75 KTS DUE TO NO AIRSPEED INDICATION AND FLAG ON FIRST OFFICER'S AIRSPEED INDICATOR. RESET ANALOGUE DIGITAL CONVERTER (ADC) AND PERFORMED TEST ACCORDING TO MM 34-130. OPERATIONAL CHECK NORMAL.

Part: ENGINE — FAILED (NR 1) · airframe 86,824 hrs · 31,842 cycles

AFT V1 NR 1 ENGINE EGT WENT TO 910 DEG, N1 FELL TO 82 PERCENT, N2 FELL TO 85 PERCENT, FUEL FLOW INCREASED TO ABOUT 15,000LBS PER HR. NO LIMITS OR RED LINES WERE APPROACH EWD. LEVELED OFF AT 18,000FT, EGT AND FUEL FLOW CONTINUED TO INCREASE. EVENTUALLY PULLED THROTTLE TO IDLE TO KEEP EGT BELOW 880 DEG C. AFTER LANDING DISCOVERED ENGINE IS SEIZED. REMOVED AND REPLACED NR 1 ENG I/A/W MEO149, IDLE AND LEAK CHECK NORMAL.

Part: ACTUATOR — FAILED (RT AILERON) · airframe 86,529 hrs · 31,711 cycles

AS ACFT SPEED INCREASES ACFT WANTS TO ROLL TO THE RIGHT FLAPS/SLATS RETRACTED. REMOVED AND REPLACED RIGHT INBOARD AILERON ACTUATOR IAW DC-10 MM 27-13-01 PAGES 401 - 407. OPS AND LEAK CHECKS GOOD.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 86,514 hrs · 31,705 cycles

SEVERAL HOLES IN FLOOR CENTER OF POSITIONS 3R & 3L & AFT OF BALLMAT (FACING AFT). *S/D* INSTALLED NR 3 POS CENTER PNL IAW DC-10 M/M 25-50-67.

Part: ANGLE — BROKEN (MLG DOOR STRIKER) · airframe 86,514 hrs · 31,705 cycles

RIGHT LANDING GEAR RED LIGHT ON AFTER GEAR RETRACT. WHILE T/S FOUND DOOR STRIKER BROKEN OFF. REPLACED DOOR STRIKER, PERFORMED OPS CHECK IAW DC-10-10 M/M 32-34-03 ITEMS 17, 18, 19, 20, SYS OPS CHECKS GOOD.

Part: MOTOR — INOPERATIVE (R-3 DOOR)

THE R-3 DOOR FAILED PNEUMATIC CHECK. THE R-3 DOOR AIR MOTOR WAS REMOVED AND REPLACED AND OPERATION CHECKED GOOD.

Part: APU — MALFUNCTIONED (AFT FUSELAGE)

THE AIRCRAFT HAD A BRIEF HISTORY OF SMOKE APPEARING IN THE COCKPIT AND CABIN MOMENTARILY WHILE IN FLIGHT. THE SMOKE DISSIPATED QUICKLY ONCE THE EFFECTED PACK WAS TURNED OFF. THE APU WAS REMOVED AND REPLACED IAW MM 49-00-00, PAGES 401-415. OPERATIONAL CHECKS WERE GOOD WITH NO SMOKE DETECTED.

Part: FLOORBEAM — CORRODED (BS 1841)

INTERIOR LOWER LOBE AFT CARGO BILGE CORROSION ON FLOORBEAM STA 1841 UPPER SIDE ABOVE AND UNDER BETWEEN RBL 50 AND LBL 50. TRIMMED OUT CORRODED AREA. FABRICATED AND INSTALLED DOUBLER AND ANGLE PER SRM 57-60-01, 53-16-01, 51-20-00, 53-00-01.

Part: LATCH — FAILED (OXYGEN COMPT)

OXYGEN COMPARTMENT DOORS DID NOT OPEN ABOVE THE FOLLOWING SEATS, 1A 1D 1E 2D 16A 16E AND 34G. REPLACED DOORS PER MM 35-20-00.

Part: SKIN — CORRODED (BS 1280-1305)

OVERWING SECTION SWELLING ON UPPER SURFACE LBL 90 BETWEEN STA 1280 TO 1305. SWELLING SKIN TRIMMED OUT, REWORKED AREA, TREATED, PRIMED AND INSTALLED UPPER AND LOWER DOUBLER PER SRM 51-21-01 AND 51-31-01.

Part: BULKHEAD ANGLE — CRACKED (AFT PRESS BLKHD)

AFT UPPER FUSELAGE AFT BULKHEAD LOWER LEFT ANGLE CRACKED. INSTALLED NEW ANGLE PER SRM 53-40-00 FIG 6 VOL 1.

Part: ANGLE — CRACKED (LT WING)

LT WING FUEL STA CRACK (2) AT RT FWD SIDE BETWEEN HI-LOCKS. CRACKED AREA TRIMMED AND BLENDED OUT. INSTALLED DOUBLER PER SRM 57-10-00 AND 51-33-01.

Part: BULBS — FAILED (CABIN)

EMERGENCY LIGHTS INOP NEAR FLT ATTEND SEAT 2L, IVS CLOSET, B-ZONE SEATS 29K TO 36K, ABOVE 26K RT OF B-ZONE AND SEATS IN A ZONE. REPLACED BURNT BULBS PER MM 33-50-00.

Part: SUPPORT — CRACKED (BS 1921)

FLOOR SUPPORT CRACKED (2) UNDER AFT GALLEY STA 1921 LBL 20 RBL 20. REMOVED CRACKED SUPPORT SECTION. FITTED NEW SECTION PER SRM 51-20-00 AND 51-35-01.

Part: ANGLE — CRACKED (LT MLG WW)

CRACK (2) ON LOWER ANGLE OF LONGERON AT AFT LEFT GEAR WHEEL WELL. REMOVED ANGLE, FABRICATED NEW ANGLE, TREATED, PAINTED, AND INSTALLED PER SRM 53-53-1 FIG 4, 51-20-00, AND 51-31-01.

Part: ANGLE — CRACKED (RT MLG WW)

CRACK (2) ON SUPPORT ANGLE OF AFT SIDE FITTING (AFT LONGERON) AT RIGHT MAIN LANDING GEAR WHEEL WELL. REMOVED CRACKED ANGLE, FABRICATED, TREATED, PRIMED, AND INSTALLED NEW ANGLE PER SRM 53-53-01, 51-20-00, AND 51-31-01.

Part: ANGLE — CRACKED (LT MLG WW)

CRACK (2) IN VERTICAL ANGLE LEFT MLG WHEEL WELL AFT BULKHEAD. REMOVED CRACKED ANGLE, FABRICATED, TREATED, PAINTED, AND INSTALLED NEW ANGLE PER SRM 53-53-01, 51-20-00 AND 51-31-01.

Part: ANGLE — CRACKED (RT MAIN WW)

CRACK ON VERTICAL ANGLE OF RIGHT MAIN L/G WHEEL WELL AFT BULKHEAD. REMOVED CRACKED ANGLE, FABRICATED, TREATED, PAINTED, AND INSTALLED NEW ANGLE PER SRM 53-53-01, 51-20-00 AND 51-31-01.

Part: RIB — CRACKED (NR 1 LE SLAT)

FOUND CRACK (2) IN SLAT NUMBER 1 RT. CRACKED RIB REMOVED, INSTALLED NEW RIB ARB1566-502 AS ORIGINAL PER SRM 51-31-01.

Part: SUPPORT — CORRODED (BS 1884-2007)

SUPPORT UNDER AFT GALLEY CORRODED STA 1884 TO 2007 RBL 24. REMOVED CORRODED PARTS, FABRICATED NEW PART, TREATED AND INSTALLED PER SRM 53-16-01, 53-60-01, 51-20-00, AND 51-31-01.

Part: HYD PUMP — FAILED (NR 1 ENGINE)

THE NR 1 ENGINE HYDRAULIC PUMP PRESSURE LOW LIGHT ILLUMINATED WHILE ON APPROACH. THERE WAS NO CHANGE IN HYDRAULIC PRESSURE OR QUANTITY. THE HYDRAULIC SYSTEM LOSS CHECKLIST WAS ACCOMPLISHED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 1 ENGINE LEFT HYDRAULIC PUMP HAD A SHEARED SHAFT. THE PUMP WAS REMOVED AND REPLACED IAW MM 29-11-01. LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: BOLT — SHEARED (NR 1 ENGINE)

THE NR 1 ENG FAILED DURING CLIMBOUT AT FL 190. THE ACFT WAS RETURNED TO GUM WHERE IT LANDED WITHOUT INCIDENT. THE NR 1 ENG WAS REMOVED AND REPLACED. *S/D* DISASSEMBLY OF THE ENG FOUND ONE HPT STAGE 1 NOZZLE SUPPORT BOLT LIBERATED. THE LIBERATED BOLT MOST LIKELY IMPACTED THE HPT STAGE 1 BLADE RETAINER AND SUBSEQUENTLY KNOCKED OFF THE RETAINER ATTACHING STUDS. A LARGE SECTION OF THE BLADE RETAINER EXITED THE ENG THROUGH THE COMPRESSOR REAR FRAME. SEVERAL PIECES OF THE BLADE RETAINER AND ATTACHING STUDS WERE RETRIEVED. THE LIBERATED NOZZLE SUPPORT BOLT WAS NOT LOCATED. THE REMAINING SUPPORT BOLTS WERE INTACT AND FOUND IN SATISFACTORY CONDITION.

Part: ACM — INOPERATIVE (NR 1/2)

THE NR 2 PACK OVERHEATED ON APPROACH TO SPN AND THE NR 1 PACK OVERHEATED AFTER LANDING. THE OVERHEATING WAS ACCOMPANIED BY A STRONG BURNING ODOR ASSOCIATED WITH BOTH PACKS. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 1 AND NR 2 ACM'S FROZEN. THE NR 1 AND NR 2 ACM'S WERE REMOVED AND REPLACED. IN ADDITION, THE NR 2 PNEUMATIC CONTROLLER WAS REPLACED AS A PRECAUTIONARY MEASURE. LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: SPAR — CRACKED (BS 233)

INSPECTION FOUND A 1.5 INCH CRACK IN NR 3 PYLON FIREWALL LOWER SPAR AT STA 233. REPAIRED IAW ECRA 5410-01423.

Part: ANGLE — CRACKED (VERT STAB)

INSPECTION FOUND AN 8 INCH CRACK IN COWL TO VERTICAL STABILIZER Z-ANGLE AT ACCESS 364QR. THE CRACKED AREA WAS REMOVED, A REPLACEMENT PART WAS FABRICATED AND INSTALLED IAW SRM 55-31-01 AND 51-31-01.

Part: FAIRING — CRACKED (NR 2 ENGINE)

INSPECTION FOUND A 4.5 INCH CRACK IN NR 2 ENGINE FAIRING TRAILING EDGE PANEL WITH SECTION MISSING, RT SIDE. THE TRAILING EDGE PANEL WAS REMOVED, A NEW PART WAS FABRICATED AND INSTALLED IAW SRM 54-32-02 AND 51-21-01.

Part: SKIN — CRACKED (NR 3 PYLON)

INSPECTION FOUND A 1 INCH CRACK ON WEB STIFFENER AND EXTERIOR SKIN OF NR 3 ENGINE PYLON AFT PANEL NR 488EL. THE CRACK WAS STOP DRILLED, DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 54-00-01, 54-31-01, AND 51-31-01.

Part: STRINGER — CRACKED (WS 372)

INSPECTION FOUND A 1.5 INCH CRACK IN LT WING STRINGER 36 AT XORS 372. THE STRINGER WAS REPAIRED IAW ECRA 5710-01791.

Part: ANGLE — BROKEN (ELEVATOR)

INSPECTION FOUND A BROKEN ANGLE ON RT INBOARD ELEVATOR AT INBOARD LEADING EDGE UPPER SIDE. A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 55-22-01 AND 51-31-01.

Part: PANEL — CRACKED (NR 2 ENGINE)

THE NR 2 ENGINE NACELLE UPPER RT SKIRT PANEL WAS FOUND BENT AND TORN WITH A 6.5 CRACK. THE DAMAGED AREA WAS TRIMMED OUT, DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 54-20-00 AND 51-31-01.

Part: SKIN — CRACKED (NR 2 LE SLAT)

INSPECTION FOUND A 2 INCH CRACK IN NR 2 RT SLAT SKIN AT UPPER SURFACE OUTBOARD END. A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW ECRA 5750-02618.

Part: LONGERON — CRACKED (BS 989)

INSPECTION FOUND A 2.5 INCH CRACK IN LONGERON 37L IN FORWARD CARGO COMPARTMENT AT F.S. 989. THE CRACKED AREA WAS REMOVED. A LONGERON SPLICE AND FITTING WERE FABRICATED AND INSTALLED IAW SRM 53-13-01 AND SRM 53-10-00.

Part: ANGLE — CORRODED (RT WING)

INSPECTION FOUND RT WING AFT ATTACH ANGLE CORRODED UNDER PANEL NR 641JB. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 57-22-01, 51-10-00 AND 51-31-01.

Part: RIB — CRACKED (NR 2 NACELLE)

INSPECTION FOUND 3 CRACKS AT RIB AND SPLICE DOUBLER OF NR 2 AFT ENGINE FAIRING (SECOND RIB FROM BOTTOM FORWARD SECTION OF FAIRING). THE CRACKED SECTION WAS REMOVED. A NEW RIB SECTION AND SPLICE DOUBLER WERE FABRICATED AND INSTALLED IAW SRM 54-32-02 AND SRM 51-31-01.

Part: STIFFENER — CRACKED (LT HORIZ STAB)

INSPECTION FOUND A 12.5 INCH CRACK IN LT HORIZONTAL STABILIZER LEADING EDGE OUTBOARD RIB UPPER STIFFENER. THE STIFFENER WAS REMOVED AND A NEW STIFFENER WAS INSTALLED IAW SRM 51-31-01.

Part: ANGLE — CORRODED (BS 1601)

INSPECTION FOUND LT WING TO BODY FAIRING SUPPORT RIB ANGLE CORRODED AT STA 1601. THE RIB ANGLE WAS REMOVED AND REPLACED IAW SRM 53-31-01.

Part: SUPPORT BEAM — CRACKED (BS 281)

INSPECTION FOUND A 5.6 INCH CRACK IN FLOOR SUPPORT BEAM AT STA 281 ON RIGHT SIDE UNDER PANEL NR 262BF. THE CRACKED AREA WAS CUT OUT. A SPLICE REPAIR WAS FABRICATED AND A NEW BEAM SECTION WAS INSTALLED IAW SRM 51-31-01.

Part: FAIRING — CORRODED (NR 2 ENGINE)

INSPECTION FOUND RT SIDE AFT NR 2 ENGINE FAIRING SKIN CORRODED WITH PULLED FASTENERS. THE SKIN WAS REMOVED AND REPLACED IAW SRM 54-32-01A AND 51-31-01.

Part: SKIN — CRACKED (VERTICAL STAB)

INSPECTION FOUND A .25 INCH CRACK JUST FORWARD OF RT FAN COWL HINGE AREA IN VERTICAL STABILIZER SKIN PANEL. A DOUBLER REPAIR WAS FABRICATED AND INSTALLED IAW SRM 55-33-01, 55-00-01 AND 51-31-01.

Part: INTERCOSTAL — CRACKED (BS 1964)

INSPECTION FOUND A CRACK IN INTERCOSTAL AT FS 1964, LBL 1. THE CRACK LENGTH WAS NOT IDENTIFIED. THE INTERCOSTAL WAS REPLACED IAW SRM 53-16-01 AND 51-31-01.

Part: CHANNEL — CORRODED (BS 1903-1921)

INSPECTION FOUND L-ANGLE AND U-CHANNEL CORRODED AT STA 1903 TO 1921, RBL 74. THE CHANNEL AND ANGLE WERE REMOVED AND REPLACED IAW SRM 53-16-01 AND 53-30-01.

Part: DOUBLER — CORRODED (BS 889)

INSPECTION FOUND FORWARD JAMB WEB DOUBLER CORRODED IN FORWARD CARGO COMPARTMENT AT FS 889, LONGERON 38R. THE DOUBLER WAS REMOVED, A NEW DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-13-01, FIGURE 14.

Part: DOUBLER — CORRODED (BS 1853)

INSPECTION FOUND DOUBLER CORRODED IN AFT CARGO COMPARTMENT AT FS 1853, LONGERON 27-28. THE DOUBLER WAS REMOVED, A NEW DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 51-35-01, 51-21-01 AND 51-33-01.

Part: FRAME — CORRODED (BS 535-555)

INSPECTION FOUND LOWER T-CHORD LOWER WEB LOWER FRAME CORRODED AT NR 1 ACM STA 535-541 AND 547-555. THE CORRODED AREAS WERE REMOVED AT EACH LOCATION AND REPAIRS WERE FABRICATED AND INSTALLED IAW SRM 53-12-01, 51-21-01 AND 51-31-01.

Part: BRACKET — CORRODED (BS 1853)

INSPECTION FOUND BRACKET CORRODED JUST BELOW FORWARD CORNER OF L-4 DOOR CUTOUT, STA 1853, LONGERON 27L. THE BRACKET WAS REMOVED, A NEW BRACKET WAS FABRICATED AND INSTALLED IAW SRM 53-16-00, 51-35-01, AND 51-21-01.

Part: WEB — CORRODED (BS 1903-1921)

INSPECTION FOUND WEB CORRODED AT FLOOR LEVEL AFT OF R-4 DOOR, STA 1903 TO 1921, RBL 74. THE WEB WAS REPAIRED IAW SRM 53-00-01.

Part: SKIN — DENTED (NR 1 LE SLAT)

INSPECTION FOUND A DENT IN INBOARD END OF NR 1 RT SLAT SKIN. A DOUBLER, SPLICE STRAP AND SKIN INSERT WERE FABRICATED AND INSTALLED IAW SRM 57-10-00, FIGURE 43, 51-21-01 AND 51-31-01.

Part: ANGLE — CORRODED (BS 1781)

INSPECTION FOUND SIDEWALL ANGLE CORRODED AROUND FASTENER HOLES AT CENTER AFT CARGO COMPARTMENT LT FLOOR LEVEL, STA 1781, LONGERON 43L. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 53-42-01, FIGURE 4, 51-30-01, AND 51-21-01.

Part: SUPPORT — CORRODED (BS 1701)

INSPECTION FOUND FLOOR SUPPORT CORRODED IN CENTER CARGO AREA AT STA 1701, LBL 4-25. A NEW FLOOR SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 53-15-01 AND 51-35-01.

Part: SKIN — CRACKED (WS 562)

INSPECTION FOUND A .75 INCH CRACK IN LT WING LEADING EDGE SKIN AT STA XORS 562. THE CRACKED AREA WAS CUT OUT, A SKIN PATCH, DOUBLER, AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 57-10-00 AND 51-30-2.

Part: DOUBLER — CORRODED (WS 264)

INSPECTION FOUND LT WING INBOARD WING UPPER SURFACE EXTERNAL DOUBLER CORRODED AND DELAMINATED AT STA 264. THE DOUBLER WAS REMOVED, A REPAIR PART WAS FABRICATED AND INSTALLED IAW SRM 57-31-01, 51-21-01, AND 51-31-01.

Part: ANGLE — CORRODED (BS 1701)

INSPECTION FOUND LOWER FLANGE OF CENTER CARGO TOP FLOOR ANGLE CORRODED AT FS 1701, LONGERON 47R. THE ANGLE WAS REMOVED IAW SRM 51-30-01, A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 53-15-01, 51-21-01, AND 51-33-01.

Part: SKIN — DENTED (LT TE FLAP)

INSPECTION FOUND A DENT IN LOWER SURFACE INBOARD END OF LT OUTBOARD FLAP. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-00-01, PAGE 12.

Part: SUPPORT — CORRODED (BS 427)

INSPECTION FOUND FLOORBOARD SUPPORT CORRODED AT FS 427, LBL 23. THE CORRODED AREA WAS REMOVED, A REPAIR STRAP AND FILLER WERE FABRICATED AND INSTALLED IAW SRM 53-70-00, FIGURE 18.

Part: BRACKET — CORRODED (BS 1519)

INSPECTION FOUND SUPPORT BRACKET ABOVE STRINGER 51R CORRODED AT STA 1519 IN CENTER CARGO PIT. THE CORROSION WAS REMOVED, A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-14-01, 53-00-01 AND 51-21-01.

Part: INTERCOSTAL — CORRODED (BS 1239-1256)

INSPECTION FOUND INTERCOSTAL CORRODED FROM STA 1239 TO 1256, LONGERON 7L. THE INTERCOSTAL WAS REMOVED, A NEW INTERCOSTAL WAS FABRICATED AND INSTALLED IAW SRM 53-14-01, 51-10-00, AND 51-30-01.

Part: SUPPORT — CORRODED (BS 795)

INSPECTION FOUND FLOORBOARD SUPPORT CORRODED AT FS 795, LBL 36-76 AND LBL 3-26. THE FLOOR SUPPORT WAS REMOVED IAW SRM 51-31-01, A NEW FLOOR SUPPORT WAS FABRICATED AND INSTALLED IAW SRM 51-31-01.

Part: BRACKET — CORRODED (BS 1519)

INSPECTION FOUND SUPPORT BRACKET CORRODED IN CENTER CARGO COMPARTMENT AT STA 1519. THE BRACKET WAS REMOVED, A NEW BRACKET WAS FABRICATED AND INSTALLED IAW SRM 51-35-01, 53-15-01, AND 51-31-01.

Part: ANGLE — CORRODED (BS 1701)

INSPECTION FOUND CENTER CARGO SUPPORT ANGLE CORRODED AT FS 1701, RBL 52. THE SUPPORT ANGLE WAS REMOVED AND REPLACED IAW SRM 51-35-01, 53-15-01, AND 51-31-01.

Part: ANGLE — CORRODED (BS 1601)

INSPECTION FOUND CENTER CARGO TOP FLOOR RT FLOORBOARD HORIZONTAL SUPPORT ANGLE CORRODED AT FS 1601 BETWEEN LONGERON 44 AND 46. THE SUPPORT ANGLE WAS REMOVED, A NEW SUPPORT ANGLE WAS FABRICATED AND INSTALLED IAW SRM 51-35-01 AND 51-21-01.

Part: SUPPORT — CORRODED (BS 879)

INSPECTION FOUND FLOORBOARD SUPPORT CORRODED AT STA 879. THE SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-21-01 AND 53-16-01.

Part: INTERCOSTAL — CORRODED (BS 1868)

INSPECTION FOUND INTERCOSTAL CORRODED AT FS 1868, LONGERON 11L. A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 51-21-01, 51-10-00, AND 51-31-01.

Part: SKIN — DENTED (BS 1942)

INSPECTION FOUND FUSELAGE SKIN DENTED AT STA 1942, LONGERON 28R. THE DENTED AREA WAS REMOVED IAW SRM 53-20-00, REPAIR DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 53-20-00.

Part: SUPPORT — CORRODED (BS 1871)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 1871, LBL 3. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-10-00 AND 51-31-01.

Part: SKIN — DENTED (BS 1921)

INSPECTION FOUND FUSELAGE SKIN DENTED AT FS 1921, LONGERON 25L. THE DAMAGED AREA WAS REMOVED AND PARTS WERE FABRICATED AND INSTALLED IAW SRM 53-20-00, FIGURE 6.

Part: ANGLE — CRACKED (BS 1781)

INSPECTION FOUND A 4 INCH CRACK IN LOWER WALL ATTACH ANGLE IN CENTER CARGO COMPARTMENT AT F.S. 1781, RBL 9. THE ANGLE WAS REMOVED AND A REPLACEMENT ANGLE WAS FABRICATED AND INSTALLED IAW SRM'S 51-21-01, 51-10-00, 51-31-06, 51-31-01, AND 53-15-01, FIGURE 9A.

Part: FAIRING CAP — CRACKED (NR 2 ENGINE)

INSPECTION FOUND A 1.5 INCH CRACK IN NR 2 ENGINE AFT NACELLE FIN (TRAILING EDGE FAIRING). THE TRAILING EDGE FAIRING CAP WAS REMOVED. A REPLACEMENT PART WAS FABRICATED AND INSTALLED IAW SRM'S 54-32-02, 54-12-02, AND 51-31-01.

Part: RIB — CRACKED (LT HORIZ STAB)

INSPECTION FOUND A 2.5 INCH CRACK IN FORWARD RIB OF LT HORIZONTAL STABILIZER TIP. THE CRACK WAS STOP DRILLED. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 55-00-01, FIGURE 2 AND SRM 51-31-01.

Part: GUSSET — CRACKED (NR 2 ENG PYLON)

KUL - INSPECTION FOUND A 1.5 INCH CRACK IN NR 2 ENGINE PYLON RIGHT GUSSET. THE GUSSET WAS REPAIRED IAW ECRA 5410-01393. (M)

Part: LONGERON — CORRODED (BS 1786)

KUL - INSPECTION FOUND LONGERON 38R AND 39R CORRODED AT STATION 1786. THE AREA WAS REPAIRED IAW SRM 53-20-00. (M)

Part: FLOOR SUPPORT — CORRODED (STATION 1811)

KUL - INSPECTION FOUND FLOOR SUPPORT BEAM CORRODED ON RIGHT SIDE NEAR DOOR R-4, STATION 1811. THE BEAM WAS REPLACED IAW SRM 51-31-01 AND 53-24-15, FIGURE 4, ITEM 85. (M)

Part: BRACKET — CORRODED (BS 999)

KUL - INSPECTION FOUND THE FLOOR SUPPORT BRACKET CORRODED AT DOOR SILL, STATION 999. THE FLOOR SUPPORT BRACKET WAS REPLACED IAW SRM 51-13-01. (M)

Part: FLOOR SUPPORT — CORRODED (REAR GALLEY 2A)

KUL - INSPECTION FOUND REAR GALLEY 2A OUTBOARD FLOOR SUPPORT BEAM CORRODED. THE BEAM WAS REPLACED IAW SRM 53-60-07, FIGURE 1. (M)

Part: FLOOR SUPPORT — CORRODED (REAR GALLEY 2B)

KUL - INSPECTION FUOND THE REAR GALLEY 2B INBOARD FLOOR SUPPORT BEAM CORRODED. THE BEAM WAS REPLACED IAW SRM 53-60-07, FIGURE 1. (M)

Part: SKIN — CORRODED (NR 1 SLAT)

KUL - INSPECTION FOUND INNER SKIN OF NR 1 SLAT CORRODED AROUND TRACK FITTING NR 1 AND NR 2. THE SLAT SKIN WAS REPAIRED IAW SRM 57-10-00, FIGURE 31. (M)

Part: FORMER — CRACKED (WS 862)

KUL - INSPECTION FOUND A .5 INCH CRACK IN WING LEADING EDGE FORMER AT STATION XOS 862. THE FORMER WAS REPAIRED IAW SRM 57-20-00, FIGURE 1. (M)

Part: FORMER — CRACKED (WS 981)

KUL - INSPECTION FUOND A .75 INCH CRACK IN WING LEADING EDGE FORMER AT STATION XOS 981. THE FORMER WAS REPAIRED IAW SRM 57-20-00, FIGURE 1. (M)

Part: FORMER — CRACKED (WS 879)

KUL - INSPECTION FOUND A 1 INCH CRACK IN WING LEADING EDGE FORMER AT STATION XOS 879. THE FORMER WAS REPAIRED IAW SRM 57-20-00, FIGURE 1. (M)

Part: FORMER — CRACKED (WS 987)

KUL - INSPECTION FOUND A 1 INCH CRACK IN WING LEADING EDGE FORMER AT STATION XOS 987. THE FORMER WAS REPAIRED IAW SRM 57-20-00, FIGURE 1. (M)

Part: FORMER — CRACKED (WS 709)

KUL - INSPECTION FOUND A 1 INCH CRACK IN WING LEADING EDGE FORMER AT STATION XOS 709. THE FORMER WAS REPAIRED IAW SRM 57-20-00, FIGURE 1. (M)

Part: FORMER — CRACKED (WS 867)

KUL - INSPECTION FOUND A .5 INCH CRACK IN WING LEADING EDGE FORMER AT STATION XOS 867. THE FORMER WAS REPAIRED IAW SRM 57-20-00, FIGURE 1. (M)

Part: FORMER — CRACKED (WS 928)

KUL - INSPECTION FUND A 1 INCH CRACK IN WING LEADING EDGE FORMER AT STATION XOS 928. THE FORMER WAS REPAIRED IAW SRM 57-20-00, FIGURE 1. (M)

Part: FORMER — CRACKED (WS 873)

KUL - INSPECTION FOUND A .75 INCH CRACK IN WING LEADING EDGE FORMER AT STATION XOS 873. THE FORMER WAS REPAIRED IAW SRM 57-20-00, FIGURE 1. (M)

Part: EEL WIRING — FAILED (CABIN)

KUL - INSPECTION FOUND THE EMERGENCY ESCAPE PATH LIGHTING INOPERATIVE AT ROW 1-3. MAINTENANCE FOUND AND OPEN CIRCUIT IN THE WIRING AND THREE BLOWN FUSES IN THE POWER PACK ASSEMBLY. THE WIRING WAS SPLICED AND THE FUSES WERE REPLACED. OPERATION OF THE EMERGENCY ESCAPE PATH LIGHTING WAS RESTORED. (Z)