N41CX

Part: SKIN — CRACKED (RT WING) · airframe 91,805 hrs · 24,437 cycles

RT WING UPPER SKIN CRACKED AT XRS 22.750 S17. PERFORMED MAJOR REPAIR IAW SRM 57-2-1 FIGURE 8. TRIMMED OUT CRACK ON RT WING UPPER SKIN IAW SRM 57-2-1. FABRICATED DOUBLER 0.190", FILLER 0.200" IAW SRM 57-2-1. CLEANED, TREATED AND PRIMED FABRICATED PARTS AND AREA IAW SRM 51-1-8B. APPLIED SEALANT PR1422 AROUND REPAIRED PARTS EDGES AND SURFACE IAW SRM 51-1-11. INSTALLED REPAIRED PARTS IAW SRM 51-1-20D.

Part: PANEL — DAMAGED (RT WING TE FLAP) · airframe 91,805 hrs · 24,437 cycles

RT WING OTBD FLAP LOWER PANEL WITH SEVERAL DENTS AND SCRATCHES XF 415 - 452. PERFORMED MAJOR REPAIR IAW SRM 57-7-1, FIG 4, TR 57-94. REMOVED OTBD FLAP LOWER PANEL IAW SRM 51-3-0. REMOVED EXISTING DAMAGED PANEL IAW SRM 51-1-21. FABRICATED NEW PANEL PLATING 0.020", FINGER DOUBLER 0.025" BOTH FROM 2024 T3 IAW SRM 57-7-1. BONDED PANEL PLATING AND FINGER DOUBLER WITH ADHESIVE IAW SRM 51-1-9 TR 51-142. CLEANED, TREATED AND PRIMED NEW PANEL PLATING AND AREA IAW SRM 51-1-8B. INSTALLED NEW PANEL PLATING IAW SRM 51-1-21. REINSTALLED OTBD FLAP LOWER PANEL IAW SRM 51-3-0, SRM 51-3-1.

Part: FITTING — CORRODED (BS 1530) · airframe 91,805 hrs · 24,437 cycles

AFTER CARGO COMPARTMENT - INTERIOR BATHTUB FITTING CORRODED AT STA 1530.000, L-32R (AFTER PART). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3, NOV 15, 2012, DWG ED-5546 NOV 15, 2012. REMOVED CORRODED FITTING IAW SRM 51-1-20D, SRM 51-1-21. FABRICATED FITTING (AL 7075 T651) IAW DWG ED 5546 NOV 15, 2012, FAA 8110-3 NOV 15, 2012. CLEANED, TREATED AND PRIMED FITTING AND AREA IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-1-21, SRM 51-1-20D. TORQUED IAW SRM 51-3-1.

Part: FITTING — CORRODED (BS 1530) · airframe 91,805 hrs · 24,437 cycles

AFTER ACCESSORY COMPARTMENT INTERIOR BATHTUB FITTING CORRODED AT STA 1530.000 L-34R (AFTER PART). PERFORMED MAJOR REPAIR IAW FORM 8110-3 DWG NR ED-5546 NOV 15,2012. REMOVED CORRODED FITTING IAW SRM 51-1-20D, SRM 51-1-21. FABRICATED FITTING AL 7075T651 IAW DWG ED-5546 NOV 15, 2012. CLEANED, TREATED AND PRIMED FITTING AND AREA IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-1-21, SRM 51-1-20D. TORQUED IAW SRM 51-3-1.

Part: LONGERON — CRACKED (BS 879 L24R) · airframe 91,805 hrs · 24,437 cycles

LONGERON 24R, HORIZONTAL LEG CRACKED 2 INCHES AT FS 879.375. PERFORMED MAJOR REPAIR IAW SRM 53-2-2, FIG 5 TR 53-123. REMOVED FASTENERS FROM REPAIRED AREA IAW SRM 51-1-20D.

Part: LONGERON — CRACKED (BS 879 L24L) · airframe 91,805 hrs · 24,437 cycles

LONGERON 24L, HORIZONTAL LEG CRACKED 1 INCH AT FS 879.375. PERFORMED MAJOR REPAIR IAW SRM 53-2-2, FIG 5, TR 53-123.

Part: SKIN — CORRODED (RUDDER) · airframe 91,805 hrs · 24,437 cycles

RUDDER SKIN-LT PANEL SHOWS CORROSION FROM STA ZR 140.750 TO STA ZR 150.750. PERFORMED MAJOR REPAIR IAW SRM 55-6-1, FIG 1. REMOVED EXISTING DAMAGED PANEL IAW SRM 51-1-21, SRM 55-1-0. FABRICATED NEW PANEL PLATING 0.016" AND BONDED DOUBLER 0.016" BOTH FROM AL 2024T3 IAW SRM 55-6-1, FIG 1, DPS 4.710, REV "L". BONDED BOTH PARTS WITH ADHESIVE IAW SRM 51-1-9, TR 51-142, SRM 51-1-9A, TR 51-141, DPS 1.950 REV "AR" R-1. CLEANED, TREATED NEW PANEL AND DAMAGED AREA WITH ALODINE AND PRIMED IAW SRM 51-1-8B. INSTALLED REPAIRED PARTS (NEW PANEL) IAW SRM 51-1-21.

Part: SKIN — DAMAGED (RT WING) · corrosion level 2 · airframe 91,805 hrs · 24,437 cycles

RT WING L/E NR 4 STUB WING CORRODED, XW 454 - XW 485. REMOVED FASTENERS FROM REPAIRED AREA IAW SRM 51-1-21. REMOVED CORROSION FROM DAMAGED AREA IAW SRM 51-1-8. TRIMMED OUT DAMAGED AREA IAW DWG ED-5545 NOV 14, 2012. FABRICATED DOUBLER 0.071" FILLER 0.063" BOTH FROM AL7075 T6 IAW DWG ED-5545 NOV 14,2012, SRM 51-1-4. CLEANED, TREATED AND PRIMED DOUBLER, FILLER AND AREA IAW SRM 51-1-8B, DWG ED-5545 NOV 14, 2012. INSTALLED REPAIRED PARTS IAW DWG ED-5545, SRM 51-1-21, SRM 51-1-20D.

Part: CONNECTOR — DIRTY (EGT) · airframe 90,871 hrs · 24,268 cycles

NR 1 EGT FLUCTUATED RAPIDLY AND THEN DROPPED TO ZERO DURING TAKEOFF ROLL. TAKEOFF ABORTED AT APPROX 40 KNOTS. ACFT RETURNED TO BLOCKS. INSPECTED THERMOCOUPLE HARNESS JUNCTIONS. NO DEFECTS NOTED. REMOVED, CLEANED AND INSPECTED EGT HARNESS PYLON CONNECTOR. INDICATION OPS CHECKED GOOD ON ENGINE RUN IAW ENGINE RUN HANDBOOK 70.01 AND MM 77-28-0. COMPLIED WITH GMM 3.124. ENGINE RUN PERFORMED BY CREW.

Part: GYRO — FAILED (HSI) · airframe 90,792 hrs · 24,253 cycles

CAPTAINS HSI AND ADI FAILED AFTER INITIAL CLIMBOUT AND LEVEL OFF AT CRUISE ALTITUDE. RETURNED TO ORIGINATING STATION. R & R NR 1 FOG GYRO IAW MM 34-11-25. OPS CHECKED GOOD.

Part: AMPLIFIER — FAILED (HSI) · airframe 90,792 hrs · 24,254 cycles

CAPTAINS HSI AND ADI FAILED AFTER TAKEOFF. RETURNED TO ORIGINATING STATION. PERFORMED OVERWEIGHT LANDING INSP IAW MM 5-50-0 AND MM 13.01.05. NO DISCREPANCIES NOTED. R & R INSTRUMENT AMPLIFIER IAW MM 34-23-00. OPS CHECKED GOOD.

Part: SWITCH — LEAKING (ZONE 400) · airframe 90,111 hrs · 24,132 cycles

NR 3 ENGINE STARTED SLOWLY LEAKING OIL. AT 1418Z WITH NR 3 OIL QUANTITY INDICATION OF 1 GALLON AND NR 3 OIL TEMP SLOWLY STARTING TO INCREASE, NR 3 ENGINE WAS SHUTDOWN AS A PRECAUTION. AFTER SHUTDOWN, NR 3 ENGINE OIL QUANTITY CONTINUED TO DECREASE TO ZERO WITH WINDMILLING OIL PRESSURE OF 29 PSI. LANDED WITHOUT FURTHER INCIDENT. FOUND NR 3 DIFFERENTIAL OIL PRESSURE SWITCH CRACKED AND LEAKING AROUND ELECTRICAL CONNECTOR. R & R NR 3 DIFFERENTIAL OIL PRESSURE SWITCH IAW MM 79-33-1. NR 3 ENGINE OIL TANK SERVICED TO FULL, 16 QUARTS ADDED. MAIN AND SCAVENGE OIL FILTERS REMOVED, INSPECTED AND REINSTALLED WITH NO DEFECTS FOUND IAW OVHM 72-00. GMM 3.124 COMPLIED WITH. ENGINE RUN PERFORMED BY FLIGHT CREW. ACFT RETURNED TO SERVICE.

Part: BATTERY — INOPERATIVE (FLASHLIGHT) · airframe 90,032 hrs · 24,118 cycles

DURING PREFLIGHT INSPECTION, FOUND RT EMERGENCY FLASHLIGHT INOPERATIVE. MX REPLACED EMERGENCY FLASHLIGHT BATTERY. OPS CHECKED GOOD IAW MM 25-60-0.

Part: FAN — FAILED (RECIRCULATION) · airframe 89,296 hrs · 23,989 cycles

DURING DESCENT, FLIGHT CREW SWITCHED ON RT RECIRCULATION FAN AND NOTICED A STRONG ELECTRICAL ODOR. FAN WAS SUBSEQUENTLY TURNED OFF AND ELECTRICAL ODOR DISSIPATED. MX TROUBLESHOT AND R & R RT RECIRCULATION FAN IAW MM 21-21-1.

Part: TRANSCEIVER — DEFECTIVE (WX RADAR) · airframe 89,182 hrs · 23,969 cycles

DURING CLIMB OUT, THE WEATHER RADAR FAILED. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED WEATHER RADAR TRANSCEIVER, OPS CHECK GOOD IAW MM 34-40-02. ACFT WAS RETURNED TO SERVICE.

Part: SKIN — CORRODED (VERTICAL STAB) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP, FOUND VERTICAL STABILIZER RT LATERAL SKIN CORRODED AT STA ZR 35.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 51-1-8, SRM 55-2-0, SRM 51-1-21A, SRM 55-1-0 PAGE 1, SRM 55-5-1, FIG 1 ITEM "K" VIEW "A", DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-3-0, SRM 51-1-20D, SRM 51-1-21A, AND SRM 51-3-1.

Part: SPAR — CORRODED (VERTICAL STAB) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP FOUND RT VERTICAL STABILIZER REAR SPAR CORRODED AT STA ZR 45.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED STRAP AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FORM 8110-3, DATED 09/09/11, DWG ED-5402, DATED 08/23/11, SRM 51-1-8, NDT SPM PART 06-10-01-001, SRM 55-5-1, FIG 2, SHEET 5 ITEM "A", SRM 51-2-0, FIG 50, SHEET 52, DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP, FOUND LT WING T/E UPPER SKIN CORRODED AT STA XW 761.695 - 736.500. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLER. BONDED REPAIR PARTS AS NEEDED. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM CHAPTER 57-3-2 FIG 31, SRM 51-1-8, SRM 57-2-0, SRM 51-1-21, SRM 57-1-0 FIG 1, SRM 57-8-1, FIG 4 ITEM "A", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, AND SRM 51-1-21.

Part: ANGLE — CRACKED (ZONE 100) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK, INSP FOUND NR 60 ACCESS DOOR BEAM AFT PRESS BULKHEAD CRACKED BOTTOM LINE-0. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. PERFORMED STOP HOLE AT CRACK END. FABRICATED ANGLES FORMED AND PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-20D, SRM 53-2-5, SRM 53-2-5, FIG 26 SHEETS 1/4/6/7/8/9 SECTIONS "J-J" VIEW "D"-7013 CONFIGURATION, DPS 4.710 REV "L", SRM 51-1-1, DPS 7.00-1 REV "BL", USED SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-20D, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — CRACKED (ZONE 600) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP, FOUND RT INBD AILERON UPPER SKIN CRACKED AT STATION XA 603.000. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLER. BONDED PARTS AS NEEDED. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. PERFORMED RT INBD AILERON BALANCE. FOUND WITHIN LIMITS MOMENT: 3,313.2 IN-LBS. INSTALLED REPAIR PARTS IAW SRM 51-1-21, SRM 57-1-0 PAGE 1, SRM 57-8-1, FIG 4, ITEM "E" & "L", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, SRM 51-1-21, AND SRM 51-4-3 PAGES 1-3.

Part: SKIN — CRACKED (ZONE 600) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP, FOUND RT OTBD AILERON LOWER SKIN CRACKED AT STA XA 610.000. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLER. BONDED PARTS AS NEEDED. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. PERFORMED RT OTBD AILERON BALANCE. FOUND WITHIN LIMITS MOMENT: 3,349.3 IN-LBS. INSTALLED REPAIR PARTS IAW SRM 51-1-21, SRM 57-1-0 PAGE 1, SRM 57-8-1, FIG 4, ITEM "E" & "L", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, SRM 51-1-21, AND SRM 51-4-3 PAGES 1-3.

Part: SKIN — CORRODED (LT WING) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP FOUND LT WING UPPER SKIN AFT PART CORRODED AT STA XRS 70.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, REPAIR DOUBLER AND MACHINE TAPERED DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 DATED 09/09/11, DWG ED-5398 DATED 08/20/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 57-3-2 FIG 15 ITEM "J", SRM 51-10-0 FIG 1, SHEET 21, DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-1-20D, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP FOUND LT WING UPPER SKIN CORRODED AT STATION XRS 358.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, REPAIR DOUBLER AND MACHINE TAPERED DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 DATED 09/09/11, DWG ED-5399 DATED 08/18/11, SRM 51-1-8, SRM 57-2-0, NDT SPM PART 06-10-01-001, SRM 57-3-2 FIG 15 ITEM "J", SRM 51-10-0, FIG 1 SHEET 21, DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 200) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP FOUND EXTERNAL SKIN CORRODED AT STA 1100.000 LONGERON 21 RT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, REPAIR DOUBLER AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 DATED 09/09/11, DWG ED-5401 DATED 08/15/11, SRM 51-1-8, SRM 53-2-0, NDT SPM PART 06-10-01-001, DC8 SRM 53-4-1 FIG 21E ITEM "A", DPS 4.710 REV "L", DC8 SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 200) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK, FOUND EXTERNAL SKIN CORRODED AT BS 902.00- 910.000 LONGERON 19 - 21RT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCIES FOUND. FABRICATED NEW SKIN, REPAIR DOUBLER AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 51-1-8, SRM 53-2-0, NDT SPM PART 06-10-01-001, SRM 53-4-1, FIG 21E, ITEM "A", DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CRACKED (BS 260) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP FOUND FUSELAGE NOSE SECTION LOWER SKIN CRACKED AT STA 260.000, LONGERON 34 RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, REPAIR DOUBLER AND FINGER DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 09/09/11, DWG ED-5394 DATED 08/16/11, NDT SPM PART 06-10-01-001, SRM 53-3-2 FIG 1 ITEM "A", DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 100) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP FOUND FORWARD CARGO COMPARTMENT INTERNAL SKIN CORRODED AT STA 600.000, LONGERON 36. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO DISCREPANCY FOUND. FABRICATED NEW SKIN, REPAIR DOUBLER AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 DATED 09/09/11, DWG ED-5395 DATED 08/16/11, SRM 51-1-8, SRM 53-2-0, NDT SPM PART 06-10-01-001, SRM 53-4-1 FIGURE "5B" ITEM "B", DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CRACKED (BS 208 L33L) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP, FOUND NLG CORNER LOWER SKIN CRACKED AT STATION 208.000, LONGERON 33 LT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 09/09/11, DWG ED-5393 DATED 08/18/11, SRM 51-1-21, SRM 51-1-20D, NDT SPM PART 06-10-01-001, SRM 53-3-2 FIG 1 ITEM "A", DPS 4.710 REV "L", DC8 SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: STRUCTURE — MISREPAIRED (BS 255 L33.5R) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP, FOUND IMPROPER REPAIR AT STA FS 255 LONGERON 33.5 RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLER, FILLER, AND FINGER DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 09/09/11, DWG ED-5394 DATED 08/16/11, NDT SPM PART 06-10-01-001, SRM 53-3-2 FIG 1 ITEM "A", AND DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-4 REV "AP", SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: ANGLE — CRACKED (ZONE 100) · airframe 89,109 hrs · 23,952 cycles

DURING ROUTINE C-CHECK INSP, FOUND ANGLE CRACKED AT STA FS 975 LONGERON 24 LT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR ANGLE. CLEANED, TREATED, PRIMED AREA AND REPAIR. INSTALLED NEW FASTENERS AND REPAIR ANGLE IAW SRM CHAP 53-2-2, FIG 5 SHEETS 21/24/25/27 TR 53-123, DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-5 REV "U", SRM 51-1-8B, SRM 51-1-20D, DPS 4.710 REV "L", AND SRM 51-3-1.

Part: COUPLER — DEFECTIVE (HF RADIO) · airframe 88,247 hrs · 23,749 cycles

DURING CRUISE, NR1 HF RADIO WILL NOT CHANNELIZE AND HAD NO RECEPTION, NR 2 HF RADIO WOULD NOT WORK. THE CREW RETURNED TO DEPARTURE WITH OUT FURTHER INCIDENT. MX REPLACED NR1 ACCESSORY COUPLER AND 2 COAX CONNECTORS ON THE NR2 ACCESSORY COUPLER. OPS CHECK GOOD IAW MM 23-10-0. ACFT WAS RETURNED TO SERVICE.

Part: DUCT — DISCONNECTED (PNUMATIC SYS) · airframe 88,069 hrs · 23,706 cycles

DURING CRUISE, NR 4 ENGINE GENERATOR UNPARALLEL LIGHT FOLLOWED BY GENERATOR DRIVE OIL LIGHT, MANIFOLD PRESSURE LIGHT ILLUMINATED WITH HIGH PRESSURE MANIFOLD AIR PRESSURE OVERTEMP LIGHT CAME ON, LOSS OF EGT INDICATION, ZERO FUEL FLOW AND ZERO EPR. THE CREW SHUTDOWN NR 4 ENG AND RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE INSPECTED ENGINE AND FOUND ELBOW DUCT ON PNEUMATIC PRESSURE REGULATOR DISCONNECTED AND NUMEROUS WIRES DAMAGED. THEY RECONNECTED ELBOW DUCT AND REPAIRED DAMAGED WIRES. OPERATIONAL CHECK GOOD IAW DC8 MAINTENANCE MANUAL 36-11-11, BOEING SWPM 20-10-01, 20-10-03, WD 24-2-4, 28-5-0 AND 72-2-0. AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (BS 255 L33-34L) · airframe 87,961 hrs · 23,681 cycles

DURING INSP, FOUND SKIN CRACKED AT STA 255 BETWEEN LONGERONS 33 AND 34 RT SIDE. INSTALLED INTERIM REPAIR IAW REA D853-60270.

Part: O-RING — DAMAGED (HYD SYSTEM) · airframe 86,728 hrs · 23,406 cycles

DURING CRUISE, ACFT LOST HYD FLUID TO THE STANDPIPE LEVEL. CREW DIVERTED AND LANDED WITHOUT INCIDENT. MX INSPECTED THE HYD SYS AND FOUND THE O-RING ON THE NR 2 SYS HYD PUMP PRESSURE LINE LEAKING. THE O-RING WAS REPLACED, THE LEAK AND OPS CHECKS WERE GOOD AND THE ACFT WAS RETURNED TO SERVICE.

Part: ENGINE — POWER LOSS (NR 4) · airframe 86,666 hrs · 23,395 cycles

DURING TAKEOFF FROM WSAP NR 4 ENG FAILED TO PRODUCE TAKEOFF PWR. THE CREW REJECTED TAKEOFF AND RETURNED TO BLOCKS WITHOUT FURTHER INCIDENT. MX PERFORMED POWER RUN AND ACCELERATION CHECK. OPS CHECK GOOD IAW ERH 72.01.1. ACFT WAS RETURNED TO SERVICE.

Part: PRBC — DRY (ENGINE) · airframe 86,545 hrs · 23,374 cycles

DURING CLIMB OUT, THE CREW HEARD A LOUD BANG, F/A REPORTED A FLASH ON LT SIDE. THEY RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX INSPECTED BOTH NR 1 AND NR 2 ENGINE'S, LUBED THE PRBC'S. OPS CHECK GOOD IAW MM 72-00, ERH 70.01, ERH 75.01, AND MM 12-80-0. ACFT WAS RETURNED TO SERVICE.

Part: RESERVOIR — LOW (HYDRAULIC SYSTEM) · airframe 86,275 hrs · 23,324 cycles

DURING CLIMB OUT FROM RJTY THE CREW NOTICE HYDRAULIC FLUID DROPPED TO STANDPIPE WITH RESERVOIR LOW PRESSURE LIGHT ON, THE CREW RETURNED TO RJTY WITHOUT FURTHER INCIDENT. MAINTENANCE SERVICED HYDRAULIC RESERVOIR. OPERATIONAL CHECK GOOD IAW MM 12-30-1, ERH 70.01. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FAN — DEFECTIVE (LT RECIRC) · airframe 86,197 hrs · 23,305 cycles

DURING C CHECK TEST FLIGHT FROM SPLP THE LEFT HAND RECIRCULATION FAN EMITTED ELECTRICAL ODOR. THE CREW TURNED OFF LEFT RECIRCULATION FAN. THEY RETURNED TO SPLP WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED THE LEFT HAND RECIRCULATION FAN. OPERATIONAL CHECK GOOD IAW MAINTENANCE MANUAL 21-21-1.

Part: SKIN — CORRODED (BS 960 L18-19R) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C-CHECK INSP, FOUND FUSELAGE EXTERNAL SKIN CORRODED AT STA 960.000 LONGERON 18-19 RT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASETNERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. PERFORMED NDT INSP. NO CRACK OR CORROSION FOUND. FABRICATED REPAIR DOUBLER. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FORM 8110-3 DATED 09/18/09, DWG ED-4981 DATED 08/24/09, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 FIGURE 1F SHEET 3, SRM 51-1-20D, NDT SPM PART 06-10-01-001, SRM 51-1-4, SRM 51-1-8B, SRM 51-1-11, AND SRM 51-3-1.

Part: SKIN — CRACKED (LT WING AILERON) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LT WING INBOARD AILERON UPPER SKIN CRACKED AT STATION XW 563.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-8-1 FIGURE 1, SRM 51-1-21, SRM 51-1-9 TR 51-142, AND SRM 51-1-8B.

Part: SKIN — CORRODED (RUDDER) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RUDDER LT SKIN CORRODED AT STATION ZR 238.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING SKIN. FABRICATED NEW SKIN AND BONDED DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 51-1-8 PAGES 17-18, SRM 55-2-0 FIGURE 6, SRM 51-1-21, SRM 55-1-0 PAGE 1, SRM 55-6-1 FIGURE 1 ITEM "A", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-8B, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — DENTED (LT WING AILERON) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT WING INBOARD AILERON UPPER SKIN DENTED AT STATION XA 515.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM CHAPTER 57-8-1 FIGURE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-9 TR 51-142, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (ZONE 100) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND MAIN CARGO COMPARTMENT SUB FLOOR FITTING CRACKED AT STATION 798.000 LBL 24". REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, SRM 51-3-0, DC8 SRM 51-1-8B, 51-3-0, SRM 51-3-1, ATI REPAIR SPECIFICATION NUMBER 2003-05, AND SEMAN-FORM-07 IPI NUMBER 2009628.

Part: FITTING — CORRODED (ZONE 100) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND MAIN CARGO COMPARTMENT RIGHT HAND AFT BATHTUB FITTING CORRODED AT STATION 1530.000 LONGERON 30RIGHT. REMOVED CORRODED FITTING. CLEANED, TREATED, AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW SRM 51-1-21, SRM 51-3-1, SRM 51-1-20D, AND SRM 51-1-8B.

Part: ANGLE — CORRODED (ZONE 100) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND MAIN CARGO COMPARTMENT AFT RING ANGLE CORRODED AT STATION 1530.000 LONGERON 26-28 LT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR ANGLE. FABRICATED REPAIR ANGLE SPLICE. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR ANGLE IAW SRM 51-1-8 PAGES 17-18, SRM 53-2-0, SRM 51-1-21, SRM 51-3-0, SRM 53-2-5, SRM 51-1-1, SRM 51-1-8B, AND SRM 51-3-1.

Part: FITTING — CORRODED (ZONE 100) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND MAIN CARGO COMPARTMENT RIGHT HAND AFT BATHTUB FITTING CORRODED AT STATION 1530.000 LONGERON 30RIGHT. REMOVED CORRODED FITTING. CLEANED, TREATED, AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW SRM 51-1-21, SRM 51-3-1, SRM 51-1-20D, AND SRM 51-1-8B.

Part: SKIN — CORRODED (ZONE 600) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C-CHECK INSP FOUND RT WING L/E LWR SKIN CORRODED AT STA XFS 566.250. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO CRACK OR CORROSION. FABRICATED DOUBLER, AND FILLER. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FORM 8110-3 RPT 09-08021 REV "IR" DATED 09/03/09, DWG ED-4975 REV "IR" DATED 09/11/09, SRM 51-1-8 PAGES 17-18, SRM 57-2-1 FIG 2G, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-20D, SRM 51-1-21, AND SRM 51-3-1.

Part: SPAR CAP — CORRODED (ZONE 600) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C-CHECK INSP, FOUND RUDDER RT SIDE FRONT SPAR CAP CORRODED AT STA ZR 323.000. REMOVED CORROSION, FOUND OUT OF LIMITS. REMOVED DAMAGED SPAR CAP. FABRICATED NEW SPAR CAP. CLEANED, TREATED, AND PRIMED AREA AND NEW SPAR CAP. INSTALLED NEW SPAR CAP IAW DWG 5655068 REV "N", SRM 51-1-8 PAGES 17-18, SRM 55-2-0 FIG 6, SRM 51-1-21, SEMAN IPI NR 2009637, REPAIR SPEC NR 2003-05, SRM 51-1-8B, SRM 51-1-21, SRM 51-3-0, SRM 51-1-20D, DWG 56555068, AND SRM 51-3-1.

Part: LONGERON — CORRODED (ZONE 100) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND MAIN CARGO COMPARTMENT CORROSION ON LONGERON 22 RT AT STATION 1530.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED LONGERON. CLEANED, TREATED, AND PRIMED AREA AND LONGERON. INSTALLED NEW LONGERON IAW SRM CHAPTER 53-5-2 FIGURE 5 SHEET 1, SRM 51-1-8 PAGES 17-18, 53-2-0 PAGE 2P, SRM 51-1-21, 51-1-20D, SRM 51-1-8B, AND SRM 51-3-1.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C-CHECK INSP FOUND FUSELAGE TAIL SEC FLOORBEAM UPPER FLANGE CRACKED AT STA 1540.000 LT BOTTOM LINE 39. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED EXTRUSION REPAIR CHANNEL, FILLERS, AND SPACERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 51-2-1 FIGURE 1 TR 51-130, SRM 51-1-21 SRM 51-1-20D, SRM 51-1-8B, SRM 51-3-0, AND SRM 51-3-1.

Part: CARGO TRACK — CORRODED (BS 1050) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C-CHECK INSP, FOUND MAIN CARGO COMPARTMENT RT SIDE NR 7 TRACK CORRODED AT STA 1050.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING SPLICE FWD SIDE AND DAMAGED TRACK SEGMENT. FABRICATED SPLICES. PERFORMED HEAT TREATMENT. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS AND TRACK SEGMENT. INSTALLED NEW TRACK SEGMENT AND SPLICES IAW SRM CHAPTER 53-2-3 FIGURE 14 SHEETS 1-2, SRM 51-1-8 PAGES 17-18, SRM 53-2-3 FIGURE 12, SRM 53-7-2, SRM 51-2-0, SRM 51-1-4, SRM 51-1-1, DPS 7.00-1 REV "BL", SRM 51-1-8B, SRM 51-3-0, AND SRM 51-3-1.

Part: FITTING — CRACKED (ZONE 200) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 742.250 LONGERON 19 LEFT. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, SRM 51-1-21, DC8 SRM 51-1-8B, AND SRM 51-3-1.

Part: SUPPORT — CRACKED (BS 857 L19L) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND MAIN CARGO COMPARTMENT INTERCOSTAL SUPPORT CRACKED AT STATION 857.125 LONGERON 19 LT. REMOVED CRACKED INTERCOSTAL SUPPORT. INSTALLED NEW INTERCOSTAL SUPPORT IAW DC8 SRM 51-1-20D, SRM 51-1-21, DC8 SRM 51-1-20D, SRM 51-3-1, ATI REPAIR SPECIFICATION 2003-05, AND SMN FORM-07 IPI2009618.

Part: FITTING — CRACKED (ZONE 200) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 912.000 LONGERON 1. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-3-1, ATI REPAIR SPECIFICATION 2003-05, SMN-FORM-07 IPI2009624, DC8 SRM 51-1-20D, SRM 51-1-21, DC8 SRM 51-1-8B,

Part: FITTING — CRACKED (BS 822) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 822.000 LEFT BUTTOCK LINE 24. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-3-1, ATI REPAIR SPECIFICATION 2003-05, SMN-FORM-07 IPI2009625, DC8 SRM 51-1-20D, SRM 51-1-21, AND DC8 SRM 51-1-8B.

Part: SKIN — BROKEN (LT WING TE FLAP) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HAND OUTBOARD FLAP EXTERNAL SKIN UPPER PART BROKEN AT STATION XF 409.000.REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 57-7-1 FIGURE 4 TR 57-94 ITEM "P" AND "Q", SRM 51-1-9 TR 51-142, SRM 51-1-8B, SRM 51-1-21.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HAND INBOARD FLAP PANEL UPPER SKIN HAS SEVERAL DENTS AT STATION XW 2.000 - STATION XW 84.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLER. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-7-1 FIGURE 1, SRM 51-1-21, SRM 57-7-1 FIGURE 1, SRM 51-1-9 TR 51-142, SRM 51-1-8B, AND SRM 51-1-21.

Part: SKIN — DAMAGED (LT WING AILERON) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT HAND INBOARD AILERON EXTERNAL LOWER SKIN PART BROKEN AT STATION XRS 624.000.REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-21, SRM 57-1-0 PAGE 1, DC8 SRM 57-8-1 FIGURE 1 ITEMS "B" & "K", DPS 4.710 REV "L", DC8 SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DPS 1.950 REV "AR" R-1, DC8 SRM 51-1-21A, DC8 SRM 51-1-21.

Part: FITTING — CRACKED (ZONE 100) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 680.000 LONGERON 14 LT. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: FITTING — CRACKED (ZONE 100) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 680.000 LONGERON 11 RIGHT. REMOVED CRACKED FITTING. CLEANED, TREATED, AND PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (ZONE 600) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT WING LEADING EDGE UPPER SKIN CORRODED AT STATION XW 406.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORRODED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS. IAW SRM 57-3-2 FIGURE 5 SHEET 1, SRM 51-1-8 PAGES 17-18, SRM 57-2-1 FIGURE 2G T/R 57-95, SRM 57-3-2 FIG 5 SHEET 1, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, SRM 51-1-11, AND SRM 51-3-1.

Part: SKIN — CORRODED (RT WING) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HAND WING LEADING EDGE UPPER SKIN CORRODED AT STATION XFS 253.500. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. FABRICATED NEW SKIN, FILLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 09-03-09, DRAWING ED-4973 DATED 08-11-09, SRM 51-1-8 PAGES 17-18, SRM 57-2-1 FIGURE 2G, IAW SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-520D, SRM 51-1-11, SRM 51-1-26, AND SRM 51-3-1.

Part: SKIN — CORRODED (RT WING) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HAND WING LEADING EDGE UPPER SKIN CORRODED AT STATION XFS 207.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENER AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN AND INTERNAL AND EXTERNAL DOUBLERS. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-2-1 FIGURE 38 TR 57-85, SRM 51-1-8 PAGES 17-18, SRM 57-2-1 FIGURE 2G TR 57-95, SRM 51-1-21, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, SRM 57-2-1, AND SRM 51-3-1.

Part: SKIN — CORRODED (RT WING) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RIGHT HAND OUTER WING OUTBOARD LEADING EDGE UPPER SKIN CORRODED AT STATION XFS 730.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN INTERNAL AND EXTERNAL DOUBLERS. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-2-1 FIGURE 38 TR 57-85, SRM 51-1-8 PAGES 17-18, SRM 57-2-0, SRM 57-2-1, SRM 51-1-21, SRM 51-1-8B, SRM 57-2-1, SRM 51-1-11, SRM 51-1-21, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — CORRODED (CENTER WING) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HAND WING CENTER LEADING EDGE UPPER SKIN CORRODED AT STATION XFS 423.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-3-2 FIGURE 5 SHEET 1, SRM 51-1-8 PAGES 17-18, SRM 57-2-1 FIGURE 2G T/R 57-95, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, SRM 51-1-11, AND SRM 51-3-1.

Part: FITTING — CORRODED (ZONE 700) · airframe 86,195 hrs · 23,304 cycles

DURING ROUTINE C-CHECK INSP FOUND RT MLG WHEEL WELL FITTING CORRODED AT STA 940.000 LONGERON 24 RT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED FITTING. FABRICATED SPLICES, DOUBLER, AND FILLERS. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 53-2-0 FIGURE 8 SHEETS 1, 2, 5, AND 6 PAGES 43-44 AND 49-53, SRM 51-1-8 PAGES 17-18, SRM 53-2-0 PAGE 2P, SRM 53-1-0 PAGE 1, SRM 51-1-20D, REPAIR SPEC NR 2003-05, FORM-07 IPI NR 2009607, SRM 51-1-8B, AND SRM 51-3-1.

Part: ENGINE — POWER LOSS (NR 2) · airframe 85,837 hrs · 23,202 cycles

DURING CRUISE FROM BGTL NR 2 ENGINE LOST POWER, THE ENGINE DID NOT RESPOND TO THROTTLE MOVEMENT AND THERE WAS AN AUDIBLE ENGINE STALL. THE GENERATOR DID NOT GO OFF LINE AND OIL PRESSURE LIGHT DID NOT ILLUMINATE THE IGNITION OFF. THE CREW SHUTDOWN NUMBER TWO ENGINE. THE CREW LANDED IN KBWI WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED THE NUMBER TWO ENGINE. OPERATIONAL CHECK GOOD IAW J/C 7001, J/C 7002 J/C 7102, ATI ERH 70.01. AIRCRAFT WAS RETURNED TO SERVICE.

Part: INDICATOR — DEFECTIVE (NR 3 N2) · airframe 85,684 hrs · 23,158 cycles

DURING TAKEOFF ROLL FROM KWRI NUMBER THREE ENGINE N2 ROLLED BACK, EPR FLUCTUATED. THE CREW REJECTED TAKEOFF AND RETURNED TO BLOCKS WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED N2 INDICATOR. OPERATIONAL CHECK GOOD IAW DACO MAINTENANCE MANUAL 77-12-0. AIRCRAFT WAS RETURNED TO SERVICE.

Part: CONTROL VALVE — DEFECTIVE (CABIN PRESSURE) · airframe 85,573 hrs · 23,127 cycles

DURING CRUISE FROM KBWI TO LPLA THE CREW WAS UNABLE TO MAINTAIN CABIN PRESSURE ON ONE PACK. THE CREW HAD TO DESCEND TO 10,000 FEET. THE CREW LANDED IN KWRI WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED LEFT FLOW CONTROL VALVE. OPERATIONAL CHECK GOOD IAW DACO MAINTENANCE MANUAL 21-31-0, AND ATI MAINTENANCE MANUAL 21-04-26. AIRCRAFT WAS RETURNED TO SERVICE.

Part: RECEPTACLE — SHORTED (NR 1 VHF SYS) · airframe 85,714 hrs · 23,015 cycles

DURING CRUISE, FLT ENGINEER TRIED TO SEND DEPARTURE MESSAGE, BUT BOTH VHF 1 AND 2 WOULD NOT TRANSMIT. THE CREW UNPLUGGED CAPTAIN, FO, AND FLT ENGINEER MIC’S. NR 1 VHF WOULD WORK IF FO MIC WAS NOT PLUGGED IN. FO RECEIVED A SHOCK WHEN MIC WAS UNPLUGGED. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED FO’S MIC JACK, NR 1 VHF TRANSCEIVER, AND FO’S INTERPHONE CONTROL PANEL MOUNT AND CONNECTOR PLUGS. OPS CHECK GOOD IAW DACO 23-41-1, WD 23-04-02, 23-20-0, AND 23-41-0. ACFT WAS RETURNED TO SERVICE.

Part: BEAM — CRACKED (BS 902) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO LOWER FLANGE BEAM CRACKED AND CORROSION AT STATION 902.000 LEFT BOTTOM LINE 51". REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION AFTER INSPECTION. FABRICATED INTERNAL AND EXTERNAL DOUBLER. PERFORMED HEAT TREATMENT TO REPAIR PARTS AS NEEDED. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM FAA 8100-9 DATED 02-19-08, MESSAGE BOEING 1-766871200-5 DATED 02-19-08, MESSAGE BOEING NUMBER 1-752696686-5 DATED 01-30-08, ROD SKETCH 200801240024, SEMAN DRAWING ED-4692, DC8 SRM 51-1-8, PAGES 17-18, DC8 SRM 53-2-3 PAGES 2P, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06.10-01.001, DC8 SRM 51-1-6, DC8 51-1-1 PAGE 1, 13, 17, DC8 SRM 51-1-8B, AND DC-8 SRM 51-3-1.

Part: SKIN — CORRODED (LT ELEVATOR) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND CORROSION AND DENTS ON LEFT ELEVATOR LOWER SKIN AT STATION XE 28.800 TO STATION XE 127.900. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS. BONDED PART AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. PERFORMED BALANCE LEFT ELEVATOR FOUND AT THE MOMENT WITH IN TOLERANCE MOMENT=1509.5 INCH POUND. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 55-4-1 FIGURE 1 SHEET 1 AND 2, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 55-2-0 PAGE 12, DC8 SRM 55-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 55-4-1 FIGURE 1 SHEET 1AND 2 PAGE 2AND3 ITEM "E" AND "F", DRAWING DOUGLAS 5654970, DC8 SRM 51-1-9A TR NUMBER 51-141 DATED 04-03-06, 51-1-9 TR NUMBER 51-142 DATED 04-05-06, DC8 SRM 51-1-8B, DC8 SRM 51-4-4 PAGE 1- 4 AND RT 51-116, 51-4-4 PAGE 2 OF 3, AND DC8 SRM 51-1-21.

Part: SKIN — CORRODED (ZONE 500) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND CORROSION ON LEFT WING ON LEADING EDGE OUTER UPPER PART AT STATION XFS 822.500. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGE AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION NOTED AFTER INSPECTION. FABRICATED REPAIR DOUBLER, AND FILLER CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08030 DATED 01-22-08, SEMAN DRAWING NUMBER ED-4690 DATED 01-16-08, DC8 SRM 51-1-21, 51-1-20D, 51-3-0, DC8 SRM 51-1-8 PAGES 17AND18, DC8 SRM 57-2-1 FIGURE 2G, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, 51-3-0, 51-1-21A, AND 51-3-1.

Part: SKIN — CORRODED (LT ELEVATOR) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT ELEVATOR CORRODED ON LOWER SKIN AT STATION XE 104.310 TO STATION XE 108.843. REMOVED CORROSION FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN, INTERNAL, AND EXTERNAL DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. PERFORMED BALANCE RIGHT ELEVATOR FOUND AT THE MOMENT WITH IN TOLERANCE MOMENT 1506-5 INCH POUND INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 55-4-1 FIGURE 1 SHEET 1 AND 2, DC8 SRM 51-1-8 PAGES 17 AND 18, DC8 SRM 55-2-0 PAGE 12, DC8 SRM 55-1-0 PAGE 1, SRM DC8 51-1-21, DC8 SRM 55-4-1 FIGURE 1 SHEET 1AND 2 PAGES 2 AND 3 ITEM "E" AND "F", DRAWING DOUGLAS 5654970, DC8 SRM 51-1-9A TRH 51-141 DATED 04-03-06, SRM 51-1-9 T/R NUMBER 51-142 DATED 04-05-06, DC8 SRM 51-1-8B, DC8 SRM 51-4-4 PAGES 1 AND 4, AND RT 51-116, 51-4-4 PAGES 2 OF 3.

Part: SPLICE — CRACKED (ZONE 700) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT MAIN LANDING GEAR WHEEL WELL SPLICE CRACKED AT STATION 879.375. REMOVED FASTENERS AS TO PERFORM REPAIR. REMOVED CRACKED SPLICE. FABRICATED NEW SPLICE. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 53-2-0 FIGURE 8 SHEET 1, 3, 6, SRM 53-1-0 PAGE 1, 51-1-20D, SRM 51-1-8B, AND 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LT WING UPPER SKIN CORRODED AROUND FASTENERS AT STATION XRS 420.000 STRINGER 5. REMOVED FASTENER AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED EXISTING REPAIR APPLIED SEALANT ON BLEND OUT AREA. PERFORMED INSPECTION NDT NO CRACK, NO CORROSION. FABRICATED REPAIR DOUBLER TAPERED REPAIR DOUBLER CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08030 DATED 01-22-08, SEMAN DRAWING NUMBER ED-4687 DATED 01-15-08, DC8 SRM 51-1-20D, DC8 SRM 51-1-8B PAGES 17-18, DC8 SRM 57-2-0 PAGE 16, DC8 SRM 51-1-14, DC8 NDT SPM PART 06-10-01.001, AND DC8 SRM 51-1-12 PAGE 7,

Part: SKIN — DENTED (RT WING) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING DENTED AT UPPER LEADING EDGE AT STA XFS 7.5000. PERFORMED DETAILED VISUAL INSPECTION. NO CRACK, NO CORROSION FOUND. PERFORMED MEASUREMENT DIAMETER FOUND WITHIN ALLOWABLE LIMITS APPLIED PRO-SEAL 735 IAW DC8 SRM 57-2-1 FIGURE 2, AND DC8 SRM 51-1-9 PAGE 13 FIGURE 13.

Part: FITTING — CRACKED (BS 702) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 702.000 LEFT BOTTOM LINE 24" (CENTER WING AREA). REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, SRM 51-3-0 AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (TE FLAP) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT INBOARD FLAP LOWER SURFACE HAS IMPROPER REPAIR AT STATION XW 59.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-21, 51-1-11, DC8 SRM 57-7-1 FIGURE 1 ITEM "B" AND "L", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-9 TR NUMBER 51-142 DATED 04-05-06, DC8 SRM 51-1-9A TR NUMBER 51-141 DATED 04-03-06, AND DC8 SRM 51-1-8B.

Part: SKIN — WORN (ZONE 100) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND OUTER FUSELAGE WORN AT STATION FS 443.000 L21L. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTENT REPAIR. REMOVED DAMAGE AREA. PERFORMED NDT INSPECTION. NO CRACK NO CORROSION DETECTED AFTER INSPECTION. FABRICATED REPAIR DOUBLERS, REPAIR TRIPLERS, FILLERS, AND FINGER DOUBLERS. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-9 DATED 02-01-08, MANUFACTURER MESSAGES 1-760836333-2 DATED 02-01-08 AND 1-752082423-7 DATED 01-22-08, AD-2006-03-04, SB 53-079 REVISION 2, DRAWING SR08530027, ROD SKETCH 200801150024, DRAWING ED-4684-1, SRM 51-1-20D, NDT SPM PART 06-10-01-001.

Part: FITTING — CRACKED (BS 822) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 822.500 LEFT BOTTOM LINE 24" (CENTER WING AREA). REMOVED CRACKED FITTING. CLEANED TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-3-0, 51-1-20D, 51-3-1, DC8 SRM 51-3-0, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE SKIN HAS IMPROPER REPAIR AT STATION 485.000 LONGERON 26 RIGHT. REMOVED EXISTING REPAIR. REMOVED DAMAGE AREA. PERFORMED INSPECTION NDT. NO CRACK, NO CORROSION AFTER INSPECTION. FABRICATED REPAIR DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, 51-3-1, FAA FORM 8110-3 NUMBER 08033 DATED 01-23-08, SEMAN DRAWING NUMBER ED-4691 DATED 01-17-08, DC8 SRM 51-1-21, 51-3-0, DC8 NDT SPM PART 06.10.001, DC8 SRM 51-1-8B.

Part: SKIN — DENTED (BS 186) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING OUTER FLAP LOWER PANEL SKIN DENTED AT STATION 164.000 TO STATION XF 186.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 4 TR NUMBER 57-94, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 TR NUMBER 57-94 DATED 10-01-02 ITEM "P" AND "Q", DC8 SRM 51-1-9 TR NUMBER 51-1-42, DC8 SRM 51-1-9A AND TR 51-1-41, DC8 51-1-8B, DC8 SRM 51-1-11 AND 51-1-21.

Part: SKIN — WORN (ZONE 100) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CABIN COMPARTMENT SKIN WORN AT STATION FS 340 L21L. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTENT REPAIR. REMOVED DAMAGE AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION DETECTED AFTER INSPECTION. FABRICATED REPAIR DOUBLERS, REPAIR TRIPLERS, FILLERS, AND FINGER DOUBLERS. CLEANED, TREATED, PRIMED AREA, AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-9 DATED 02-01-08, MESSAGES 1-760836333-2 DATED 02-01-08 AND 1-752082423-7 DATED 01-22-08, AD-2006-03-04 S/B 53-079 REVISION 2, DRAWING SR08530027, ROD SKETCH 200801150024, DRAWING ED-4684-1, SRM 51-1-20D, NDT SPM PART 06-10-01-001,

Part: FITTING — CRACKED (BS 759) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 759.000 LEFT BOTTOM LINE 24" (CENTER WING AREA). REMOVED CRACK FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, SRM 51-3-0 AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (BS 485) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE SKIN HAS IMPROPER REPAIR AT STATION 485.000 LONGERON 25 RIGHT. REMOVED EXISTING REPAIR. REMOVED DAMAGE AREA. PERFORMED INSPECTION NDT. NO CRACK, NO CORROSION AFTER INSPECTION. FABRICATED REPAIR DOUBLER, AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, 51-3-1, FAA FORM 8110-3 NUMBER 08033 DATED 01-23-08, SEMAN DRAWING NUMBER ED-4691 DATED 01-17-08, DC8 SRM 51-1-21, 51-3-0, DC8 NDT SPM PART 06.10.001, AND DC8 SRM 51-1-8B.

Part: SUPPORT — CRACKED (BS 460 S29L) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD CARGO PANELS SUPPORT CRACK AT STATION 460 LONGERON 29LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. FABRICATED ANGLE DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-20D, 51-1-21, DC8 SRM 53-2-0 PAGE 2E AND 2F, DC8 SRM 51-1-8B, AND 51-3-1.

Part: SKIN — DELAMINATED (NR 4 SPOILER) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING NUMBER 4 SPOILER DELAMINATED. REMOVED DAMAGED SPOILER. INSTALLED NEW RIGHT SPOILER IAW DC8 MAINTENANCE MANUAL 27-60-1 PAGES 201-207. PERFORMED OPERATIONAL CHECK TO ALL FLIGHT CONTROLS, GOOD IAW DC8 MAINTENANCE MANUAL 27-11-0 PAGES 10-14, DC8 27-21-0 PAGES 5-9, 27-30-0 PAGES 4-7, 27-40-0 PAGES 1-2, 27-40-1 PAGES 10-13, 27-51-0 PAGES 10-12, 27-61-0 PAGES 5-7, 27-70-0 PAGES 1-2, AND 27-80-0 PAGES 4.

Part: SKIN PANEL — CRACKED (ZONE 100) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD CARGO PANELS SUPPORT CRACK AT STATION 460 LONGERON 30 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. FABRICATED ANGLE DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-20D, 51-1-21, DC8 SRM 53-2-0 PAGE 2E AND 2F, DC8 SRM 51-1-8B, AND 51-3-1.

Part: DOOR — DELAMINATED (MLG) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING (MLG/FUSELAGE) UPPER DOOR DELAMINATED SKIN. REMOVED DAMAGED DOOR. INSTALLED NEW DOOR. PERFORMED OPS CHECK FOR HYD SYSTEM LEAKS GOOD IAW DC8 MAINTENANCE MANUAL 32-12-1 PAGE 401, DC8 27-10-0, 27-20-0, 27-40-0, 27-50-0, 27-60-0, 27-80-0, 27-00, 32-30-0, 32-42-0, 32-50-0, 52-36-1 AND 78-30-0.

Part: FRAME — CRACKED (ZONE 100) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT CRACK ON FRAME FLANGE AT STATION 240.000 LONGERON 21RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED FRAME. FABRICATED FRAME AND SPLICE AND ANGLE PERFORMED HEAT TREATMENT. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 53-2-0 FIGURE 2 SHEETS 2, AND 6, DC8 SRM 51-1-20D, DC8 SRM 53-4-1 FIGURE 41 SHEETS 7 AND 8, DC8 SRM 53-2-0 FIGURE 2 SHEET 1, DC8 SRM 51-2-0 FIGURE 50 SHEET 49A, DC8 SRM 57-2-0 FIGURE 2 SHEET 7 AND 8 TR NUMBER 53-110 DATED 11-10-00, DC8 SRM 51-1-1 PAGES 1, 13 AND 17, DC8 SRM 51-1-8B, AND 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LT WING UPPER SKIN CORRODED AROUND FASTENERS AT STATION XRS 278.000 STRINGER10. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. FILLED WITH SEALANT REWORKED AREA. PERFORMED NDT NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER. TAPERED REPAIR DOUBLER CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTNERS AND REPAIR PARTS IAW FAA FORM 8110-3 NR 08042 DATED 01-29-08 DRAWING ED-4688 DATED 01-17-08, SRM 51-1-21, 51-3-0, SRM 51-1-8 PAGES 17-18, SRM 57-2-0 PAGE 16, SRM 51-1-11, NDT SPM PART 06-10-01-001, SRM 51-1-12 PAGE 7, SRM 51-1-20D, AND 51-3-1.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE NOSE SECTION CRACKED AT PNEUMATIC AIR INLET DOOR FRAME INNER REVERSE. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE AREA. FABRICATED FILLER AND DOUBLER. CLEANED, TREATED AND PRIMED AREA, AND REPAIR PARTS. INSTALLED NEW FASTENERS AN REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 SRM 53-2-0 FIGURE 1B, AND DC8 SRM 51-1-8.

Part: SKIN — DELAMINATED (ZONE 600) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING (MLG/FUSELAGE) MIDDLE DOOR, DELAMINATED SKIN. REMOVED DAMAGED SKIN. INSTALLED NEW SKIN CENTER DOOR ON RIGHT MAIN LANDING GEAR FUSELAGE. PERFORMED OPERATIONAL CHECK FOR HYD SYSTEM LEAKS, GOOD IAW DC8 MINATENANCE MANUAL 27-10-0, 27-20-0, 27-40-0, 27-50-0, 27-60-0, 27-80-0, 27-00, 32-30-0, 32-42-0, 32-50-0, 52-36-1 AND 78-30-0, AND DC8 32-12-1 PAGES 401-404.

Part: FLANGE — CRACKED (RT NACELLE) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT COWLING AFT FLANGE CRACK STATION YN 181.000. REMOVED SPLICE CRACKED. FABRICATED SPLICE. CLEANED, TREATED AND PRIMED REPAIR PART INSTALLED REPAIR PART IAW DC8 SRM 51-1-21, DC8 SRM 54-3-2 FIGURE 33, BOEING MESSAGE NUMBER 1-763536571 DATED 02-05-08, AND DC8 SRM 51-1-8B.

Part: DOOR — DELAMINATED (MLG) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING (MLG/FUSELAGE) UPPER DOOR DELAMINATED SKIN. REMOVED RIGHT MAIN LANDING GEAR OUTBOARD DOOR. INSTALLED NEW DOOR. PERFORMED OPS CHECK FOR HYD SYSTEM LEAKS GOOD IAW DC8 MM 32-12-1 PAGE 404, DC8 MAINTENANCE MANUAL 32-12-1 PAGE 401 01-07-08, DC8 MM 27-10-0, 27-20-0, 27-40-0, 27-50-0, 27-60-0, 27-80-0, 27-00, 32-30-0, 32-42-0, 32-50-0, 52-36-1 AND 78-30-0.

Part: SKIN — DELAMINATED (MLG) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING (MLG/FUSELAGE) MIDDLE DOOR DELAMINATED SKIN. REMOVED DELAMINATED DOOR. INSTALLED NEW MID DOOR. PERFORMED OPS CHECK FOR HYD SYSTEM LEAKS GOOD IAW DC8 MM 32-12-1 PAGE 404, DC8 MM 27-10-0, 27-20-0, 27-40-0, 27-50-0, 27-60-0, 27-80-0, 27-00, 32-30-0, 32-42-0, 32-50-0, 52-36-1 AND 78-30-0.

Part: SKIN — CORRODED (ZONE 500) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LT WING UPPER SKIN CORRODED AROUND FASTENERS AT STATION XRS 358.000 -371.000, STRINGER 5 TO STRINGER 8. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGE AREA. FABRICATED REPAIR DOUBLER AND FILLER PLUG. TAPERED BOTH SIDES OF REPAIR DOUBLER. PERFORMED NDT INSPECTION. NO CRACK, OR CORROSION FOUND. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-2-1 FIGURE 29, SRM 51-1-20D, SRM 51-1-8 PAGES 17-18, SRM 57-2-0 PAGE 16, NDT SPM PART 06-10-01-001, SRM 51-1-12 PAGE 7, AND SRM 51-3-1.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING JOINT FLAP DELAMINATED. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE AREA. FABRICATED NEW SKIN. REMOVED CORE AND CLEANED AREA. INSTALLED CORE AND NEW FASTENERS AND REPAIRED PARTS IAW DC8 SRM 57-7-1 PAGE 2, SRM 51-1-9 T/R 51-142, AND DC8 SRM 51-1-9 PAGE 1.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING JOINT FLAP DELAMINATED SKIN. REMOVED DAMAGED JOINT FLAP. INSTALLED NEW JOINT FLAP IAW DC8 SRM 51-3-0, 51-3-1.

Part: TAB — DELAMINATED (AILERON) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING CONTROL TAB AILERON DELAMINATED. REMOVED REPLACE AILERON CONTROL TAB IAW DC8 MM 27-11-4 PAGES 201-205, PERFORMED OPS CHECK TO ALL FLIGHT CONTROLS GOOD IAW DC8 MM 27-11-0 PAGES 10-14, DC8 MM 27-21-0 PAGES 5-9, MM 27-30-0 PAGES 4-7, MM 27-40-0 PAGES 1-2, MM 27-40-1 PAGES 10-13, MM 27-51-0 PAGES 10-12, MM 27-61-0 PAGES 5-7, MM 27-70-0 PAGES 1-2, MM 27-80-0 PAGES 4.

Part: PANEL — CRACKED (ZONE 600) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND WING FUSELAGE PANEL NUMBER 716 FILLET PANEL RIGHT SIDE CRACKED AT STATION 690.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR REMOVED DAMAGED AREA. FABRICATED FILLER AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 53-8-1 PAGES 3-4, DC8 SRM 51-1-9 PAGE 1, DC8 SRM 53-2-4 PARAGRAPH 3, 51-1-9 PARAGRAPH 3AND 2.

Part: PANEL — DELAMINATED (LT WING) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING LOWER PANEL DELAMINATED AT STATION XF 219 TO XF 339.000. REMOVED DAMAGED PANEL. INSTALLED NEW PANEL IAW DC8 SRM 51-3-0, 51-3-1.

Part: SKIN — CORRODED (ZONE 500) · airframe 83,204 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND CORROSION ON LEFT WING CENTER LEADING EDGE OUTER LOWER SKIN AT STATION XFS 304.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGE AREA. PERFORMED NDT INSPECTION. NO CRACK OR CORROSION DETECTED AFTER TEST. FABRICATED REPAIR DOUBLER AND FILLER CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08030 DATED 01-22-08, SEMAN DRAWING NUMBER ED-4686 DATED 01-12-08, DC8 SRM 51-1-21, 51-1-20D, 51-3-0, DC8 SRM 51-1-8 PAGES 17-18, DC8 SRM 57-2-1, FIGURE 2G, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND 51-3-1.

Part: SKIN — CRACKED (LT WING) · airframe 83,234 hrs · 22,524 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING LOWER SKIN CENTRAL LEADING EDGE CRACKED AT STATION XF 428.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE AREA. PERFORMED NDT INSPECTION. NO CRACK OR CORROSION DETECTED AFTER TEST. FABRICATED REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08030 DATED 01-22-08, SEMAN DRAWING ED-4685 DATED 01-12-08, DC8 SRM 51-1-21, 51-1-20D, 51-3-0, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B,DC8 SRM 51-1-11, 51-1-20D, AND 51-3-1.

Part: B-NUT — LOOSE (ENGINE OIL) · airframe 82,523 hrs · 22,307 cycles

DURING CRUISE FROM KBWI NUMBER THREE ENGINE OIL QUANITY SLOWLY DECREASED UNTIL INDICATING ZERO. PRESSURE AND TEMPERATURE REMAINED NORMAL UNTIL THE OIL PRESSURE BEGAN TO FLUCTUATE APPROXIMATELY 15 PSI WITH NR 3 OIL PRESSURE LIGHT COMING ON AND OFF. THE CREW SHUTDOWN NR 3 ENGINE AT 1317Z WINDMILLING OIL PRESSURE 15PSI. ON DESCENT OIL PRESSURE WENT TO ZERO AT 1445Z. THE CREW LANDED AT BGTL WITHOUT INCIDENT. MAINTENANCE INSPECTED NR 3 ENGINE FOR OIL LEAKS AND FOUND LOOSE B-NUT FITTING ON ENGINE OIL FILTER HOUSING. MAINTENANCE TIGHTENED B-NUT IAW DACO MAINTENANCE MANUAL CHAPTER 20-10. MAINTENANCE ACCOMPLISHED OPERATIONAL CHECK WAS GOOD AIRCRAFT RETURNED TO SERVICE.

Part: FIRE LOOP — MALFUNCTIONED (NR 2) · airframe 82,504 hrs · 22,302 cycles

DURING TAKEOFF FROM TAPA, THE NUMBER TWO FIRE WARNING INDICATION LIGHT AND BELL CAME ON, THE LIGHT AND BELL WENT OUT WHEN THE CREW RETARDED POWER LEVERS TO IDLE. THE CREW RETURNED TO BLOCKS AT TAPA WITHOUT INCIDENT. MAINTENANCE REPLACED THE NUMBER TWO LOWER FIRE LOOP AND PERFORMED OPERATIONAL CHECK WAS GOOD IAW DACO DC8 MAINTENANCE MANUAL 26-10-1, AIRCRAFT WAS RETURNED TO SERVICE.

Part: HF COMM — DEFECTIVE (NR 1) · airframe 81,558 hrs · 22,064 cycles

DURING FLIGHT FROM KBWI THE NR 1 AND NR 2 HF SYSTEM FAILED. THE CREW DID ALL NECESSARY PROCEDURES AND RETURNED TO KBWI LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE NR 1 AND NR 2 HF SYSTEM, RESEATED THE NR 1 HF SYSTEM OPERATIONAL CHECK GOOD. REPLACED NR 2 HF ACC COUPLER OPERATIONAL CHECK GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: LINE — LEAKING (HYDRAULIC SYS) · airframe 81,058 hrs · 21,925 cycles

DURING CLIMB FROM FHAW, THE CREW NOTICED THE HYDRAULIC QUANTITY BEGAN DECREASING. THE CREW RAN THE HYDRAULIC LOSS OF QUANTITY CHECK LIST AND RETURNED TO FHAW AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE NUMBER THREE ENGINE HYDRAULIC HIGH PRESSURE LINE LEAKING. MAINTENANCE REPLACED THE LINE, SERVICED THE HYDRAULIC RESERVOIR. THE OPERATIONAL AND LEAK CHECKS WERE GOOD. THE AIRCRAFT WAS RETURNED TO SERVICE IAW DACO DC8 MM 29-10-12.

Part: LANDING GEAR — OUT OF ADJUST · airframe 80,892 hrs · 21,879 cycles

DURING CLIMB-OUT OF KCOF WHILE PERFORMING THE GEAR UPLATCH CHECK THE DOOR NOT LATCH LIGHT ILLUMINATED. THE CREW FOLLOWED PROCEDURES AND RETURNED TO KCOF AND LANDED WITHOUT INCIDENT. MAINTENANCE TROUBLESHOT THE SYSTEM AND ADJUSTED THE MAIN GEAR FOLLOW UP MECHANISM. THE GEAR WAS SWUNG AND THE OPERATIONAL CHECK WAS SATISFACTORY. THE AIRCRAFT WAS RETURNED TO SERVICE IAW DC8 MM 32-31-5.

Part: SKIN — CORRODED (FUSELAGE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, EXTERNAL FUSELAGE SKIN CORRODED BETWEEN STA 902.000 L11 AND L12R.

Part: SKIN — CORRODED (FLAP VANE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING.- OTBD VANE T/E CORRODED AND CRACKED, XOLDI 6.224.

Part: SKIN — CORRODED (RT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, RT OTBD AILERON LWR SKIN CORRODED, XA 752.000 - XA 678.000.

Part: SKIN — CORRODED (LT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT HAND WING AILERON UPPER SKIN WITH SPOTS OF CORROSION FROM STATION XA 737.000 TO STATION XA 767.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-8-1 FIGURE 4. REMOVED CORROSION IAW DC8 SRM 51-18 PAGES 17, 18. FOUND OUT OF LIMITS IAW DC8 SRM 57-2-0 PAGE 16. REMOVED CORRODED SKIN IAW DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21. FABRICATED NEW SKIN FROM, AL2024T3 0.020, AND DOUBLER FROM, AL 2024T3 0.016 IAW DC8 SRM 57-8-1 FIG 4 ITEM F, G. BONDED BOTH PARTS WITH HYSOL IAW DC8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA, AND NEW SKIN INTERNAL SURFACE IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED NEW SKIN IAW DC8 SRM 51-1-21.

Part: SKIN PANEL — DELAMINATED (T/E FLAP) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD FLAP PANEL UPPER SKIN DELAMINATED AND HOLES ELONGATED, XW 2.000.

Part: SKIN — CRACKED (LT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, 'LT CTR L/E EXTERNAL PLATING SKIN CORRODED, CRACKED 1"; XOLDI 6.22 - XW 408.000.

Part: SKIN — CORRODED (LT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING T/E UPPER EXTERNAL SKIN CORRODED ON SOME AREAS STA XRS 74.000.

Part: SKIN — CORRODED (RT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING.- INBD L/E UPPER SKIN CORRODED BETWEEN XFS 207.000 AND XFS 211.000.

Part: SKIN — DENTED (LT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING OTBD AILERON LWR SKIN DENTED, XA 647.000.

Part: REPAIR — IMPROPER (RT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, RT OTBD AILERON LWR SKIN NON STANDARD REPAIR, XA 680.000 - XA 685.000.

Part: SKIN — DENTED (LT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING.- OTBD AILERON LWR SKIN DENTED , XA 661.000.

Part: SKIN — CRACKED (RT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING.- INBD L/E UPPER SKIN CRACKED 2" APPROX BETWEEN XFS 204.000 AND XFS 207.000.

Part: SKIN — DENTED (LT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING OTBD AILERON LWR SKIN DENTED, XA 618.000.

Part: STRUCTURE — DENTED (HORIZ STAB) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, RT HORIZONTAL STABILIZER WITH 02 DENTS , XFS 103.760 - XFS 141.750.

Part: SKIN — DENTED (LT ELEVATOR) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT HORIZONTAL STABILIZER.- ELEVATOR UPPER SKIN DENTED XE 60.125.

Part: SKIN PANEL — DENTED (T/E FLAP) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD FLAP PANEL UPPER SKIN DENTED, XW 45.000.

Part: SKIN — DENTED (LT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING.- OTBD AILERON UPPER SKIN DENTED, XA 669.000.

Part: SKIN — DENTED (RT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING.- OTBD AILERON UPPER SKIN DENTED , XA 737.000 - XA 755.000.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, EXT FUSELAGE "D" BELLY DOOR FWD LWR JAMB CORNER CRACKED 1 1/2" STA 1240.000 L-32R.

Part: SKIN — DENTED (LT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING OTBD AILERON LWR SKIN DENTED, XA 640.000.

Part: SKIN — DENTED (LT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING OTBD AILERON LWR SKIN DENTED, XA 715.000.

Part: SKIN — DENTED (LT AILERON) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING OTBD AILERON UPPER SKIN DENTED, XA 662.000.

Part: SKIN — DENTED (T/E FLAP) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION FOUND LEFT HAND WING FLAP PANEL UPPER SKIN DENTED AT STATION XF 364.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-7-1 FIGURE 4 TR NUMBER 5794 DATED 10-01-02. REMOVED DAMAGED PANEL SKIN IAW DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21. FABRICATED NEW PANEL SKIN, AND DOUBLER IAW DC8 SRM 57-7-1 FIG 4 TR NUMBER 5794 ITEM A, AND Q. BONDED BOTH PARTS WITH HYSOL IAW DC8 SRM 51-1-9. CLEANED, TREATED AND PRIMED AREA, AND NEW PANEL SKIN INTERNAL PART IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED NEW SKIN IAW DC8 SRM 51-1-21.

Part: SKIN — CORRODED (RT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING CTR L/E UPPER SKIN CORRODED BETWEEN XW 257.000 AND XW 261.000.

Part: SKIN PANEL — DAMAGED (T/E FLAP) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD FLAP PANEL UPPER SKIN HOLES ELONGATED, XW 40.000.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION FOUND AFT FUSELAGE LONGERON 17 LEFT CRACKED ½ INCH AT STATION 1620.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 53-5-2 FIGURE 5, SHEET 1. REMOVED CRACKED LONGERON IAW DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-20D. FABRICATED NEW LONGERON, AND SPLICES, LOCATED, DRILLED, TRIMMED CLEANED, TREATED AND PRIMED AREA, AND NEW LONGERON IAW DC8 SRM 51-1-8B. INSTALLED NEW LONGERON EXTRUSION P/N 51616757, AND SPLICES IAW DC8 SRM 53-5-2 FIG 5, SHEET 1 ITEM B, DC8 SRM 51-2-0 FIG 50, SHEET 37, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1.

Part: FITTING — CRACKED (FUSELAGE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, FWD CARGO CMPT, LT TUNNEL SPLICE FITTING CRACKED 3, STA 600.000 - STA 620.000 L-26L. REPAIRED PER ALL APPROVED DATA.

Part: PANEL — CORRODED (LT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD L/E UPPER SLANT PANEL CORRODED ON SOME AREAS (STA XFS 126.000 - 145.000)

Part: PANEL — CRACKED (LT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD L/E UPPER SLANT PANEL CORRODED ON SOME AREAS, STA XFS 194.000. REPAIRED PER ALL APPROVED DATA.

Part: SKIN — CORRODED (LT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING OTBD L/E OUTER SECTION UPPER SKIN CORRODED ON SOME AREAS , STA XFS 747.000.

Part: SKIN — CORRODED (LT STUB WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, NR 1 LT STUB WING UPPER SKIN CORRODED ON SOME AREAS, STA XFS 554.000.

Part: PANEL — CRACKED (LT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD L/E UPPER SLANT PANEL CORRODED ON SOME AREAS, STA XFS 194.000. REPAIRED PER ALL APPROVED DATA.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION FOUND FUSELAGE LONGERON 17 RIGHT CRACKED ½ INCH, AT STATION 1620.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 53-5-2 FIGURE 5, SHEET 1. REMOVED DAMAGED LONGERON IAW DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-20D. FABRICATED NEW LONGERON, AND SPLICES, LOCATED, DRILLED, TRIMMED, CLEANED, TREATED AND PRIMED AREA AND NEW LONGERON IAW DC8 SRM 51-1-8B. INSTALLED NEW LONGERON. EXTRUSION P/N 51616757 IAW DC8 SRM 53-5-2 FIGURE 5 SHEET 1, ITEM B, DC8 SRM 51-2-0 FIG 50 SHEET 37, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 SRM 51-3-1.

Part: PANEL — CRACKED (LT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD L/E UPPER SLANT PANEL CORRODED ON SOME AREAS, STA XFS 80.000. REPAIRED PER ALL APPROVED DATA.

Part: SUPPORT FITTING — CRACKED (RT MLG) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION RT MLG SUPPORT FITTING UPPER PART EDGE , STA 902.000 CRACKED 1 1/2" APPROX. REPAIRED PER ALL APPROVED DATA.

Part: SKIN — CORRODED (LT STUB WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, NR 1 LT STUB WING UPPER SKIN CORRODED ON SOME AREAS, STA XFS 530.000.

Part: FITTING — CRACKED (FUSELAGE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, AFT FUSELAGE.- RT SPLICE FITTING CRACKED 1", L-10R, STA 1566.000. REPAIRED PER ALL APPROVED DATA.

Part: FITTING — CRACKED (FUSELAGE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, AFT FUSELAGE.- SPLICE FITTING CRACKED 1", L-17L, STA 1566.000. REPAIRED PER ALL APPROVED DATA.

Part: SKIN — CORRODED (LT WING) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING OTBD L/E OUTER SECTION UPPER SKIN CORRODED ON SOME AREAS, STA XFS 803.000.

Part: FITTING — CRACKED (FUSELAGE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, FRAME FITTING CRACKED 1" APPROX , STA 960.000 L-24R.

Part: FITTING — CRACKED (FUSELAGE) · airframe 80,233 hrs · 21,696 cycles

DURING ROUTINE C CHECK INSPECTION, AFT FUSELAGE SPLICE FITTING CRACKED 1", L17R, STA 1566.000. REPAIRED PER ALL APPROVED DATA.

Part: FAN — MALFUNCTIONED (CABIN) · airframe 80,035 hrs · 21,657 cycles

DURING CRUISE FROM OBBI LEFT RECIRC FAN WAS SHUTDOWN AND CIRCUIT BREAKERS WERE PULLED DUE TO ELECTRICAL FUMES. CREW LANDED WITHOUT INCIDENT. MAINTENANCE PLACED THE RECIRC FAN ON DMI AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: TRANSCEIVER — BROKEN (COCKPIT) · airframe 76,488 hrs · 20,959 cycles

DURING FLIGHT FROM KSUU TO PHIK, HF NR 1 AND NR 2 RADIO REPORTED TO HAVE LOUD BACKGROUND SQUEAL AND IS UNREADABLE. CREW RETURNED AIRCRAFT TO KSUU AND LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED NR 1 HF ACCESSORY COUPLER AND NR 2 HF R/T. OPERATIONAL CHECKS WERE GOOD PER ALL APPLICABLE MANUALS.

Part: HOSE — WORN (HYD SYSTEM) · airframe 76,481 hrs · 20,955 cycles

DURING TAKEOFF FROM KMCC, AIRCRAFT LOST HYDRAULIC PRESSURE. HYDRAULIC QUANTITY DROPPED TO AUX LEVEL. CREW RETURNED AIRCRAFT TO KMCC AND LANDED WITHOUT INCIDENT. AN INSPECTION IS ON GOING. AS SOON AS INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE REMOVED AND REPLACED NR 2 PRESS LINE TO PUMP, SERVICED HYDRAULIC SYSTEM BLEED AIRCRAFT FLIGHT CONTROLS DURING ENGINE RUN. THE OPERATIONAL CHECK WAS GOOD PER ALL APPLICABLE MANUALS.

Part: CONTROL BOX — BURNED (MLG) · airframe 76,470 hrs · 20,951 cycles

DURING LANDING, ON GEAR EXTENSION NO GREEN LIGHTS FOR GEAR DOWN AND LOCKED. C/B ON DC BUS 1 RESET NO HELP. VISUAL INDICATORS ON WING AND NOSE GEAR DOWN ALL CHECKED, GEAR DOWN AND LOCKED. CREW LANDED THE AIRCRAFT WITHOUT INCIDENT. AN INSPECTION IS ON GOING. WHEN MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE FOUND CONNECTOR P1-44 DISCONNECTED AT F/O'S INSTRUMENT PANEL AND RECONNECTED. REPLACED L/G PROXIMITY BOX AND THE SYSTEMS OPERATIONAL CHECK WAS NORMAL IAW ALL APPLICABLE MANUALS.

Part: LONGERON — CORRODED (FUSELAGE)

FWD CARGO COMPT AT Y STA 360.0, LONGERON 28R CORRODED.

Part: FILLET — DELAMINATED (LT WING) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING FILLET PANEL (NUMBER 1612) DELAMINATED. REPLACED PANEL PER ALL APPLICABLE DATA.

Part: DOUBLER — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND AIR START ACCESS DOOR CUTOUT DOUBLER CRACKED. REPLACED DOUBLER PER ALL APPLICABLE DATA.

Part: FRAME — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME CORRODED AT STATION Y181, -X35, BETWEEN LONGERONS 21 RIGHT AND 32 RIGHT. REPLACED FRAME SECTION PER ALL APPLICABLE DATA.

Part: SKIN — BULGED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND SKIN BULGING AT STATION 1582 BETWEEN LONGERONS 27 LEFT AND 28 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: LONGERON — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 24 RIGHT CORRODED FROM STATION Y879.375 TO STATION Y402.000. REPAIRED LONGERON PER ALL APPLICABLE DATA.

Part: GUIDE — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND ROLLER GUIDE DOOR ANGLE CRACKED AT STATION Y500, LONGERON 29 RIGHT. REPLACED ROLLER GUIDE PER ALL APPLICABLE DATA.

Part: LONGERON — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 23 RIGHT CORRODED BETWEEN STATION Y1000 AND STATION Y1020. REPAIRED PER ALL APPLICABLE DATA.

Part: LONGERON — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 29 LEFT CORRODED FROM STATION Y510 TO STATION Y490. REPAIRED PER ALL APPLICABLE DATA.

Part: LONGERON SPLICE — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FORWARD CARGO COMPARTMENT LONGERON SPLICE CRACKED BETWEEN STATIONS 600, AND STATION 620 LONGERON 31 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — DENTED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND SKIN DENTED AT STATION Y1190 BETWEEN LONGERONS 31 LEFT AND 33 LEFT. REPAIRED SKIN PER ALL APPLICABLE DATA.

Part: PANEL — DELAMINATED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING TRAILING EDGE DIHEDRAL PANEL DELAMINATED. REPLACED PANEL PER ALL APPLICABLE DATA.

Part: PANEL — CORRODED (LT WING)

LT WING, INNER WING T/E UPPER PANEL WITH HEAVY CORROSION.

Part: DOUBLER — MISINSTALLED (XONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING OUTBOARD AILERON REPAIR SHORT ONE RIVET FROM STATION XA661 TO XA671. REPLACED PER ALL APPLICABLE DATA.

Part: ANGLE — WORN (TE FLAP) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP HINGE FITTING ANGLE WORN AT STATION XF218. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (LT WING TE)

RT AND LT WING TRAILING EDGE SUPPORT, CANOE FITTING OB/IB HOLES ID CORRODED AT STA XF=97.906, STA XF=219.498 AND STA XF=399.723.

Part: FITTING — CORRODED (FUSELAGE)

MAIN CARGO CABIN FROM Y STA 960 TO Y STA 980 FITTINGS, CORRODED.

Part: SKIN — CORRODED (TAIL SECTION) · airframe 76,459 hrs · 20,947 cycles

FUSELAGE TAIL SECTION, FROM Y STA 1530 TO Y STA 1633 BETWEEN LONGERON 24L AND LONGERON 32L UPPER AND LOWER FUSELAGE SKIN CORRODED.

Part: FLOORBEAM — CRACKED (FUSELAGE)

MAIN CARGO CABIN Y, STA 1380 FLOORBEAM UPPER CAP AFT FLANGE CRACKED.

Part: FITTING — CORRODED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER ELEVATOR HINGE STA XE 140 SUPPORT HOLE CORRODED.

Part: SKIN — CORRODED (RT WING)

RT WING LEADING EDGE SLOT SKIN CORRODED, BETWEEN XW 329.25 AND XW 359.0.

Part: FLOORBEAM — CRACKED (MAIN CABIN)

MAIN CARGO CABIN Y STA 360.0, FLOORBEAM UPPER CAP CRACKED AT +X 31.25.

Part: COVER — DAMAGED (MAIN CABIN)

MAIN CARGO CABIN Y STA 119, Z0, -X 20 COVER, DAMAGED.

Part: FITTING — CRACKED (TE FLAP) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING IN BOARD FLAP FITTING CRACKED AT STATION XW97. REPLACED FITTING PER ALL APPLICABLE DATA.

Part: PANEL — CORRODED (LT WING)

LT WING, FIXED PANEL NR 571, PN 5648891-1, WITH CORROSION AND DELAMINATED AT SEVERAL PLACES.

Part: FITTING — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FITTING CORRODED AT STATION Y1280 LONGERON 33 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: LONGERON — CRACKED (ZONE100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 25 RIGHT CRACKED AT STATION Y390. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — DEBONDED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT ELEVATOR UPPER SKIN TRAILING EDGE DEBONDED AND CORRODED FROM STATION XE260 TO XE280. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE SKIN CORRODED AT STATION XFS61. REPAIRED PER ALL APPLICABLE DATA.

Part: WEB — CRACKED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT ELEVATOR WEB CRACKED AT STATION XE77. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y1340 AT LONGERON 7 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: LONGERON — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND CRACKED LONGERON AT STATION Y1500 LONGERON 24 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME WITH A DOUBLE DRILLED HOLE AT STATION Y1060 AT LONGERON 7 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME WITH A DOUBLE DRILLED HOLE AT STATION Y640 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME SPLICE WITH A DOUBLE DRILLED HOLE AT STATION Y1500 AT LONGERON 7 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: ANGLE — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND A CORRODED ANGLE AT STATION 1500 LONGERON 23 LEFT STRUCTURE BOX. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING OUTBOARD FLAP TRAILING EDGE PANEL FITTING CRACKED AT STATION XW375. REPLACED FITTING PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE SKIN CORRODED BETWEEN STATIONS XRS710 TO XRS761. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER FITTING CRACKED AT STATION XFS47 BETWEEN STRINGERS 1 AND 2. REPLACED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND CORRODED FITTING FROM STATION Y960 TO Y980, -Z10, +X25. REPLACED FITTING PER ALL APPLICABLE DATA.

Part: INTERCOSTAL — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND CORRODED INTERCOSTAL FROM STATION Y460 TO Y480, BETWEEN LONGERONS 34 LEFT AND 35 LEFT REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND CRACKED FITTING AT STATION 781, -Z1, +X25. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 764,602 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME WITH A DOUBLE DRILLED HOLE AT STATION Y1480 AT LONGERON 7 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FITTING CRACKED AT STATION 798, -Z1, -X25. REPLACED FITTING PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND CRACKED FITTING AT STATION Y798, -Z1, +X25. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND CRACKED FITTING AT STATION 781, -Z1, -X25. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,647 cycles

DURING ROUTINE C CHECK, FOUND A CRACKED FITTING AT STATION 759, +X25, -Z1. REPAIRED PER ALL APPLICABLE DATA.

Part: RIB — CRACKED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING AUXILIARY TANK RIB CRACKED AT STATION XFS20. REPAIRED PER ALL APPLICABLE DATA.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND SEAT TRACK AND FLOOR PANEL WITH A HOLE AT STATION Y1500 +X45. REPAIRED PER ALL APPLICABLE DATA.

Part: SUPPORT — WORN (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT AFT ENTRY DOOR UPPER HINGE SUPPORT WORN. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — DENTED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING OUTBOARD AILERON SKIN DENTED FROM STATION XA646 TO XA674. REPLACED PER ALL APPLICABLE DATA.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND SEAT TRACK CORRODED FROM STATION Y420 TO Y560, -X25. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y1000 AT LONGERON 13 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — DEBONDED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RUDDER RIGHT SIDE SKIN DEBONDED AND A LOOSE RIVET FROM STATION ZR59 TO ZR87. REPLACED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING OUT BOARD FLAP HINGE FITTING CORRODED AT STATION XF97. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (TE FLAPS) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP HINGE FITTING CORRODED AT STATION XF219. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING OUTBOARD FLAP HINGE FITTING CORRODED AT STATION XF219. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING OUTBOARD FLAP HINGE FITTING CORRODED AT STATION XT340. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP HINGE FITTING CORRODED AT STATION XF97. REPAIRED PER ALL APPLICABLE DATA

Part: SKIN — DEBONDED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING INBOARD FLAP SKIN DEBONDED AT STATION XW115. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — BENT (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT SIDE RUDDER SKIN BENT FROM STATION ZR208 TO ZR239. REPLACED PER ALL APPLICABLE DATA.

Part: SKIN — DEBONDED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RUDDER SKIN DEBONDED AND CORRODED FROM STATION ZR150 TO ZR115. REPLACED PER ALL APPLICABLE DATA.

Part: RIB — CRACKED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE UPPER RIB CRACKED AT STATION XFS384. REPAIRED PER ALL APPLICABLE DATA.

Part: ATTACH FITTING — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON FITTING CRACKED AT STATION 1530 LONGERON 34 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CRACKED (TE FLAPS) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP TRAILING EDGE SKIN CRACKED AT STATION XF300. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING FLAP HINGE BASE FITTINGS CORRODED AT STATIONS XW219 AND XW97. REPAIRED PER ALL APPLICABLE DATA.

Part: DOUBLER — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND DOUBLER CORRODED AT STATION 198, -X61, -Z10. REPAIRED PER ALL APPLICABLE DATA

Part: SKIN — DEBONDED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RUDDER SKIN DEBONDED AND CORRODED FROM STATION ZR59 TO ZR115. REPLACED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (TE FLAP) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING FLAP HINGE FITTINGS CORRODED AT STATIONS XW219 AND XW97. REPAIRED PER ALL APPLICABLE DATA.

Part: WINDOW FRAME — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND WINDOW CUT OUT CORRODED FROM STATION 1280 TO 1300 LEFT SIDE. REPAIRED PER ALL APPLICABLE DATA.

Part: WINDOW FRAME — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND WINDOW CUT OUT CORRODED FROM STATION 1320 TO 1340 LEFT SIDE. REPAIRED PER ALL APPLICABLE DATA.

Part: WINDOW FRAME — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND WINDOW CUT OUT CORRODED FROM STATION 1240 TO 1260 LEFT SIDE. REPAIRED PER ALL APPLICABLE DATA.

Part: WINDOW FRAME — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND WINDOW CUT OUT FRAME CORRODED FROM STATION Y1400 TO STATION Y1420 RIGHT HAND SIDE. REPAIRED PER ALL APPLICABLE DATA.

Part: WINDOW FRAME — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND WINDOW CUT OUT CORRODED FROM STATION 1240 TO 1260 RIGHT SIDE. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — CORRODED (HORIZONTAL STAB)

EMPENNAGE RT STAB LOWER SECTION STRINGER NR 4 WITH CRACK AT XFS 47 AND CORROSION AT XFS 45.

Part: DOOR FRAME — CRACKED (Y STA)

MAIN CARGO CABIN Y STA 480 AFT JAMB BETWEEN LONGERON 21 LT AND LONGERON 19 LT, FRAME WITH WEAR AND CRACKED.

Part: STRUT — CORRODED (RT MLG)

RT MLG SHOCK STRUT RETRACT PIN BOSS, INNER SURFACE CORRODED.

Part: DOUBLER — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND DOUBLER CORRODED FROM STATION 188 TO 208 AT Z=0 BETWEEN -X45 AND -X62. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (FUSELAGE)

FUSELAGE FWD SECTION Y STA 498 AND Y STA 522 LONGERON 34 RT LEVEL SKIN CORRODED.

Part: SKIN — CRACKED (FUSELAGE)

FUSELAGE NOSE SECTION, Y STA 215 FWD PASSENGER ENTRANCE DOOR, HOLD OPEN PIN-CUTOUT SKIN CRACKED.

Part: PANEL — CRACKED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER STA XFS 47 NR 1 UPPER STRINGER CRACKED.

Part: PANEL — DEBONDED (VERTICAL STAB)

VERTICAL STABILIZER TRAILING EDGE SECTION, UPPER AND LOWER PANELS WITH SKIN DEBONDING.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FLOORBEAM UPPER CHORD CRACKED AT STATION Y1542, -X37 TO -X43. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE SKIN CORRODED BETWEEN STATION XW257 AND XW223. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE LOWER SKIN CORRODED BETWEEN STATION XFS710 AND XFS635. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 600) · airframe 20,947 hrs

DURING ROUTINE C CHECK, FOUND RIGHT WING SKIN CORRODED AT STATION XOLDI6.224. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — WORN (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING SKIN WORN AT STATION XOLDO67. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE SKIN CORRODED BETWEEN STATION XW257 AND XW408. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE SKIN CORRODED BETWEEN STATION XW454 AND XW485. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING UPPER SKIN CORRODED BETWEEN STATION XW0 AND XRS74. REPAIRED PER ALL APPLICABLE DATA.

Part: ANGLE — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND ANGLE CORRODED AT STATION Y110, +Z3, +X48. REPAIRED PER ALL APPLICABLE DATA.

Part: SUPPORT FITTING — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND AIR CONDITIONING FLOORBEAM SUPPORT FITTING CRACKED AT STATION Y267, -X45. REPLACED FITTING PER ALL APPLICABLE DATA.

Part: SUPPORT FITTING — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND AIR CONDITIONING FLOORBEAM SUPPORT FITTING CRACKED AT STATION Y253, +X45. REPLACED FITTING PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT ELEVATOR LOWER SURFACE SKIN CORRODED AT STATION XE32.398. REPAIRED PER ALL APPLICABLE DATA.

Part: BUSHING — CORRODED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER ELEVATOR SUPPORT BUSHING CORRODED AT STATION XE 140. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER SUPPORT FITTING CRACKED AT STATION XFS72 BETWEEN STRINGER 2 AND FRONT SPAR. REPLACED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (LT ELEVATOR) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT ELEVATOR INTERNAL FINGER DOUBLER AND SKIN CORRODED AT STATION XE38. REPAIRED PER ALL APPROVED DATA.

Part: SKIN — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT ELEVATOR TRAILING EDGE UPPER AND LOWER SKIN BULGED FROM STATION XE263 TO XE280. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CRACKED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT ELEVATOR LOWER SKIN CRACKED AND CORRODED FROM STATION XE137 TO XE181. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING RIGHT CENTER FUEL TANK FITTING PLATE CRACKED AT STATION XWC23 BETWEEN STRINGERS 1 AND 2. REPLACED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (RT ELEVATOR) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT ELEVATOR LOWER SURFACE SKIN CORRODED AT STATION XE246. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (LT ELEVATOR) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT ELEVATOR LOWER SKIN INTERNAL "TEE" AND SKIN CORRODED AT STATION XE40. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — BULGED (LT ELEVATOR) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT ELEVATOR LOWER SKIN TRAILING EDGE BULGED FROM STATION XE246 TO XE318. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — DEBONDED (RT ELEVATOR) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT ELEVATOR LOWER SKIN SURFACE CORRODED AND DEBONDED AT STATION XE205.687. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME CORRODED AT STATION 188 BETWEEN LONGERONS 3 RIGHT AND 11 RIGHT, ALSO 3 LEFT AND 11 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER FRONT SPAR SUPPORT FITTING CORRODED AT STATION XFS72. REPAIRED PER ALL APPLICABLE DATA.

Part: SPAR — CRACKED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER LOWER REAR SPAR CRACKED AT STATION XE40. REPAIRED PER ALL APPLICABLE DATA

Part: STRAP — CORRODED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP LEADING EDGE STRAP CORRODED AND WORN. REPAIRED PER ALL APPLICABLE DATA.

Part: HOUSING — CRACKED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER LINKAGE HOUSING CRACKED AT STATION XRS218. REPAIRED PER ALL APPLICABLE DATA.

Part: ANGLE — CORRODED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT SIDE VERTICAL STABILIZER TO FUSELAGE SKIN ATTACH ANGLE CORRODED AT STATION Y1606. REPAIRED PER ALL APPLICABLE DATA.

Part: SUPPORT — CRACKED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER LOWER SPAR CAP SUPPORT CRACKED AT STATION XFS62. REPAIRED PER ALL APPLICABLE DATA.

Part: SUPPORT — CRACKED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER LOWER SECTION SUPPORT CRACKED AT STATION XFS47. REPAIRED PER ALL APPLICABLE DATA.

Part: STRINGER — CRACKED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER LOWER STRINGER CRACKED AT STATION XFS47. REPAIRED PER ALL APPLICABLE DATA.

Part: HOUSING — CRACKED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LINKAGE HOUSING CRACKED ON LEFT HAND HORIZONTAL STABILIZER AT STATION XRS136. REPLACED PER ALL APPLICABLE DATA.

Part: STRAP — CRACKED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER CLOSING SPAR STRAP SCRATCHED AND CRACKED BETWEEN STATION XRS176 TO XRS215. REPAIRED PER ALL APPLICABLE DATA.

Part: SUPPORT FITTING — CRACKED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER SUPPORT FITTING CRACKED AT STATION XFS72 BETWEEN STRINGERS 6 AND 7. REPLACED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND DOUBLE DRILLED HOLES AT STATION 600 AT LONGERONS 7 LEFT AND 14 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y560 AT LONGERON 14 RIGHT. REPAIRED PER ALL PPLICABLE DATA

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 764,650 hrs · 2,994 cycles

DURING ROUTINE C CHECK, FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y902 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y380 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: SPAR CAP — CORRODED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT ELEVATOR LOWER SPAR CAP CORRODED FROM STATION XE32 TO XE285. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y1120 AT LONGERON 14 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y600 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y834 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y600 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y500 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA

Part: DOUBLER — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND DOUBLER BULGING AND CRACKED ON LEFT HAND HORIZONTAL STABILIZER AT STATION XRS250. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y660 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y1280 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y781 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA

Part: LONGERON SPLICE — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 24 RIGHT SPLICE CORRODED AT STATION Y406. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y420 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y500 AT LONGERON 14 RIGHT. REPAIRED PER ALL APPLICABLE DATA

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE221 TO XE272 BULGED AND RIVET SHEARED. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y834 LONGERON 7 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FLOOR SUPPORTS CORRODED FROM STATION YT200 TO Y240, Z=0 BETWEEN +X40 AND -X40. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND DOUBLE DRILLED HOLE IN FRAME FLANGE AT STATION 640, LONGERON 7 LEFT. REPAIRED PER ALL APPLICABLE DATA

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y1120 AT LONGERON 7 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: CAP — CRACKED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER STATION XRS54 TEE CAP CRACKED. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION Y860 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 2,994 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER TRAILING EDGE LOWER PANEL BETWEEN STATION XE221 TO XE149 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: BOSS — CORRODED (ZONE 700) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT MAIN LANDING GEAR SHOCK STRUT RETRACT PIN BOSS INNER SURFACE CORRODED. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 24 RIGHT END FITTING CORRODED AT STATION Y212. REPAIRED PER ALL APPLICABLE DATA.

Part: SUPPORT FITTING — CRACKED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND AIR CONDITIONING FLOORBEAM SUPPORT FITTING CRACKED AT STATION Y253, +X45, -Z1. REPLACED FITTING PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND NUMBER 4 MAIN FUEL TANK FITTING CRACKED AT STATION 239.793 BETWEEN FRONT SPAR AND STRINGER 18. REPAIRED PER ALL APPLICABLE DATA.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND A CORRODED LONGERON AT STATION Y267 LONGERON 22 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — DENTED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND SKIN DENTED AT STATION Y1287 BETWEEN LONGERONS 34 LEFT AND 35 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: BEAM — CRACKED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND UPPER TRANSVERSAL BEAM CRACKED AT STATION Y260 +X45. REPAIRED PER ALL APPLICABLE DATA.

Part: BEAM — CRACKED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND UPPER TRANSVERSAL BEAM CRACKED AT STATION Y260 -X45. REPAIRED PER ALL APPLICABLE DATA.

Part: WEB — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND WEB CORRODED AT STATION Y169, +X52, -Z11. REPAIRED PER ALL APPLICABLE DATA.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND ANGLE CORRODED AT STATION Y190 LONGERON 33 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: WEB — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND WEB CORRODED AT STATION Y148, +X52, -Z11. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 27 RIGHT END FITTING CORRODED AT STATION Y270. REPAIRED PER ALL APPLICABLE DATA.

Part: SUPPORT — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND CEILING SUPPORT CORRODED AT STATION Y101, +X45. REPAIRED PER ALL APPLICABLE DATA.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A CRACKED LONGERON FROM STATION Y1580 TO Y1586 AT LONGERON 15 LEFT. REPAIRED LONGERON PER ALL APPLICABLE DATA.

Part: WEB — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND WEB CORRODED AT STATION Y169, -X52 AND -X58, -Z11. REPAIRED PER ALL APPLICABLE DATA.

Part: FLOOR PANEL — CRACKED (CARGO BAY) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FORWARD CARGO COMPARTMENT FLOOR PANEL CRACKED FROM STATION Y480 TO Y500. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND END FITTING CRACKED AT LONGERON 22 RIGHT STATION Y990. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 23 LEFT END FITTING CRACKED AT STATION Y990. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A FITTING WITH A DOUBLE HOLE AT STATION 1740 BETWEEN LONGERONS 10 LEFT AND 11 LEFT. REPLACED FITTING PER ALL APPLICABLE DATA.

Part: ANGLE — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND ANGLE CORRODED IN THE LEFT SIDE NOSE LANDING GEAR TUNNEL AT STATION Y102. REPAIRED PER ALL APPLICABLE DATA.

Part: FILLET — DELAMINATED (WING) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND WING FILLET PANEL NUMBER 162V DELAMINATED. REPAIRED PANEL PER COOPESA EO COO-CMP-8-53-273-04 DATED 07/15/2004.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FLOOR PANEL CORRODED, WITH LOOSE RIVETS AND A DOUBLE HOLE. REPLACED FLOOR PANEL PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND CRACKED FITTING ST STATION Y101, +X20. REPAIRED PER ALL APPLICABLE DATA.

Part: RIB — CRACKED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING TRAILING EDGE RIB CRACKED AT STATION XW36. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LONGERON 24 RIGHT FITTING CORRODED AT STATION Y910, -Z10. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — DELAMINATED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING TRAILING EDGE FIXED PANEL DELAMINATED AND NICKED AT STATIONS XW10, XW40, AND XW75. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — DENTED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING INBOARD FLAP UPPER LEADING EDGE SKIN DENTED AT STATION XW58. REPAIRED SKIN PER ALL APPLICABLE DATA.

Part: SKIN — DENTED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING OUTBOARD AILERON UPPER SKIN DENTED AT STATION XW671. REPLACED PER ALL APPLICABLE DATA.

Part: SKIN — DENTED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING INBOARD FLAP TRAILING EDGE SKIN DENTED FROM STATION XRS172 TO XRS220. REPLACED SKIN PER ALL APPLICABLE DATA.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FLOOR PANEL CORRODED AND LOOSE FASTENERS BETWEEN STATION Y1520 AND Y1542 AND BETWEEN -X40 AND +X40. REPLACED FLOOR PANEL PER ALL APPLICABLE DATA.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FLOOR PANEL CORRODED BETWEEN STATIONS Y1542 AND Y1580 AT -X40 AND +X40. REPLACED FLOOR PANEL PER ALL APPLICABLE DATA.

Part: SKIN — DENTED (TE FLAP) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP LOWER SKIN DENTED AT STATION XF208. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — TOOL DAMAGE (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND A DOUBLE HOLE IN THE LEFT WING OUTBOARD AILERON AT STATION XW698. REPLACED PER ALL APPLICABLE DATA.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND TRACK CORRODED FROM STATION Y1000 TO Y1100, Z0, -X60. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — DENTED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING OUTBOARD FLAP UPPER SKIN DENTED AT STATION XF440. REPAIRED PER ALL APPLICABLE DATA.

Part: LONGERON SPLICE — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A CRACKED LONGERON SPLICE BETWEEN STATION 600 AND 620 AT LONGERON 31 LEFT. REPLACED LONGERON SPLICE PER ALL APPLICABLE DATA.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FORWARD CARGO COMPARTMENT DOOR FRAME CRACKED AT THE UPPER AFT CORNER. REPAIRED DOOR FRAME PER ALL APPLICABLE DATA.

Part: RIB — CRACKED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE CAVITY RIB CRACKED AT STATION XFS780. REPLACED PER ALL APPLICABLE DATA.

Part: RIB — CRACKED (ZONE 500) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT WING LEADING EDGE CAVITY RIB CRACKED AT STATION XFS842. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RUDDER LEFT SIDE AFT SKIN PANEL BULGED FROM STATION ZR100 TO ZR110. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER TRAILING EDGE LOWER PANELS AT STATIONS ZR267.218, ZR276.531, AND ZR284.75 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND SKIN CRACKED AT STATION 215 BETWEEN LONGERONS 15 LEFT AND 16 LEFT, (FORWARD ENTRANCE DOOR HOLD OPEN PIN CUTOUT). REPAIRED PER ALL APPLICABLE DATA.

Part: SPAR — CORRODED (VERTICAL STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND VERTICAL STABILIZER RIGHT SIDE REAR SPAR INTERNAL AREA CORRODED AT STATION ZV299. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND SKIN CRACKED AND SHEARED FASTENERS AT STATION Y1589 BETWEEN LONGERONS 15 LEFT AND 17 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — DENTED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C-CHECK FOUND WING FILLET PANEL NUMBER 162C DENTED. REPLACED OUTER SKIN AND HONEYCOMB SECTION PER COOPESA EO COO-CMP-8-53-260-04 DATED 07/14/2004.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND CRACKED FLOORBEAM AT STATION Y360 AT +X28 AND +X32. REPAIRED PER COOPESA EO COO-8-53-264-04 DATED 6/15/04.

Part: SKIN — CORRODED (ZONE 600) · airframe 79,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD SLOT AREA UPPER SURFACE SKIN CORRODED. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND SKIN BULGED AND CRACKED FROM STATION 1460 TO STATION 1480 BETWEEN LONGERONS 31 RIGHT AND 33 RIGHT. REPAIRED PER COOPESA EO COO-8-53-244-04 DATED 6/8/04.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A SEAT TRACK WITH AN ELONGATED HOLE AT STATION 827.5 X=0, Z=0. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FORMER CRACKED AT STATION 380 BETWEEN LONGERONS 31 RIGHT HAND AND 32 RIGHT HAND. REMOVED DAMAGE, MANUFACTURED, AND INSTALLED REPAIR PARTS PER ALL APPLICABLE DATA.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FLOOR BEAM CRACKED AT STATION 1420, Z0, -X45. REPAIRED PER COOPESA EO COO-8-53-243-04 DATED 7/7/04.

Part: SKIN — CORRODED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING UPPER IN BOARD PANEL (DIHEDRAL) SKIN, CORRODED. REPAIRED PER ALL APPLICABLE DATA.

Part: FILLET — DELAMINATED (WING) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND WING FILLET PANEL NUMBER 262K DELAMINATED AND CORRODED. REPLACED PANEL PER COOPESA EO COO-8-53-304-04.

Part: SKIN — CORRODED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE UPPER SKIN CORRODED AT STATION XFS335.25. REPAIRED PER ALL APPLICABLE DATA.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 20,947 hrs · 2,994 cycles

DURING ROUTINE C CHECK FOUND A SEAT TRACK WORN OUT OF LIMITS BETWEEN STATIONS Y400 AND Y420 AT -X45. REPLACED SEAT TRACK PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 600) · airframe 20,947 hrs · 2,994 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE SKIN CORRODED AT STATIONS XFS -11.250 THRU XFS63.750. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE UPPER SKIN CORRODED FROM STATION XW257 TO XW260. REPAIRED PER ALL APPLICABLE DATA.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FLOORBEAM UPPER FLANGE CORRODED AT STATION 420 BETWEEN -X29 AND -X42. REPAIRED FLOORBEAM PER ALL APPLICABLE DATA.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND SEAT TRACK WORN OUT OF LIMITS BETWEEN STATION Y717 TO Y742 AT -X25. REPAIRED PER ALL APPLICABLE DATA.

Part: FILLET — DELAMINATED (WING) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND WING FILLET PANEL NUMBER 262F DELAMINATED AND CORRODED AT AFT FACE. REPLACED PANEL PER COOPESA EO NUMBER COO-8-53-304-04 DATED 08/06/2004.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FLOORBEAM UPPER FLANGE CRACKED AT STATION 380, +X32. REPAIRED PER COOPESA EO COO-8-53-245-04 DATED 6/10/04.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER LEADING EDGE CORRODED FROM STATION XFS60 TO XFS142. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — SCRATCHED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE SKIN SCRATCHED AT STATION 268.5 AT LONGERON 24 LEFT HAND. REPAIRED PER COTNEY DRAWING WO8-R14 DATED 7-20-04.

Part: SKIN — DENTED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT HORIZONTAL STABILIZER LEADING EDGE DENTED AT STATION XFS239. REPAIRED PER ALL APPLICABLE DATA.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND SEAT TRACK CORRODED FROM STATION 1270 TO STATION 1420 AT +X40, Z=0. REPAIRED PER ALL APPLICABLE DATA.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT WHEEL WELL FORWARD BULKHEAD SUPPORT CORRODED AT STATION 857, +X56 AND -Z25. REPLACED SUPPORT PER ALL APPLICABLE DATA.

Part: CARGO TRACK — CORRODED (CARGO BAY) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND TRACK CORRODED FROM STATION Y990 TO Y1020 AT TX45 TO Z 0. REPLACED DAMAGED TRACK PER ALL APPLICABLE DATA.

Part: CARGO TRACK — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND TRACK CORRODED FROM STATION 990 TO STATION 1380 + X17 AT LONGERON 33 LEFT HAND. REPLACED CARGO TRACK SECTION FROM STATION 1140 TO STATION 1380 + X17 PER ALL APPLICABLE DATA.

Part: SKIN — BULGED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FUSELAGE SKIN EXISTING DOUBLER BULGED AT STATION Y1530 BETWEEN LONGERONS 29 LEFT AND 32 LEFT. REMOVED CORROSION, MANUFACTURED AND INSTALLED REPAIR PARTS PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE SKIN CORRODED AT STATION XW250. REPAIRED PER ALL APPLICABLE DATA.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND SEAT TRACK CORRODED AT STATION 1150 Z0 X0. REPLACED SEAT TRACK FROM STATION 1120 TO 1197 Z0 X0 PER ALL APPLICABLE DATA.

Part: CARGO TRACK — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND CARGO TRACK AND SUPORT CHANNEL CORRODED FROM STATION 990 TO STATION 1120 - X 17 AT LONGERON 33 RIGHT HAND. REMOVED CORROSION ON CARGO TRACK, WITH IN LIMITS. REPLACED CARGO TRACK SUPPORT CHANNEL PER ALL APPLICABLE DATA.

Part: CHANNEL — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FLOOR CHANNELS CORRODED AND CRACKED FROM STATION 990 TO STATION 1120 -X7, AND +X7. REPLACED FLOOR CHANNELS FROM STATION 990 TO STATION 1120 -X7 AND+X7, PER ALL APPLICABLE DATA.

Part: FRAME — CORRODED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME CORRODED ON UPPER CHORD LOWER FACE AT STATION 1100 BETWEEN LONGERON 33 LEFT AND 33 RIGHT. REMOVED CORROSION, MANUFACTURED AND INSTALLED REPAIR PARTS PER ALL APPLICABLE DATA.

Part: SKIN — BULGED (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND EXTERNAL FUSELAGE SKIN BULGED AT STATION 522 AT LONGERON 34 RIGHT HAND. REPAIRED PER COTNEY DRAWING W08-R08 DATED 7/22/04.

Part: RIB — CRACKED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE CAVITY LOWER RIB CORRODED AND CRACKED AT STATION XFS360.25. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — SCRATCHED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND EXTERNAL FUSELAGE SKIN SCRATCHED AT STATION 557.5 BETWEEN LONGERONS 29 RIGHT HAND AND 30 RIGHT HAND. REPAIRED PER COTNEY DRAWING W08-R12 DATED 7-22-04

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A FRAME WITH A DOUBLE DRILLED HOLE AT STATION 460 LONGERON 21 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND CEILING SUPPORTS CORRODED IN SEVERAL PLACES FROM STATION 1380 -28 BETWEEN -X41 AND +X41. REMOVED CORROSION AND REPLACED SUPPORTS AS NEEDED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND END FITTING CRACKED AT STATION Y1530 LONGERON 21 RIGHT. REMOVED DAMAGED END FITTING. LOCATED, DRILLED, TREATED, PRIMED, AND INSTALLED NEW END FITTING AT STATION Y1530 LONGERON 21 RIGHT IAW DC8 SRM 51-1-20D, AND 53-2-0.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 76,460 hrs · 2,994 cycles

DURING ROUTINE C CHECK, FOUND FLOOR SUPPORTS CORRODED BETWEEN STATION 1540 AND STATION 1620 FROM X40 AND -X4, Z0. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE LOWER SKIN CORRODED FROM STATION XFS735 TO XFS885. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND END FITTING CRACKED AT STATION Y1530 LONGERON 26 LEFT. REPLACED DAMAGED END FITTING WITH NEW PER APPLICABLE DATA.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FLOOR SUPPORTS CORRODED AT STATION 1580 BETWEEN X35 AND -X35, Z0. REPLACED FLOOR SUPPORTS PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND A DOUBLE DRILLED HOLE AT STATION 1240 BETWEEN LONGERONS 10 LEFT AND 11 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (ZONE 100) · airframe 46,129 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND END FITTING CRACKED AT STATION Y1530 LONGERON 23 RIGHT. REPLACED DAMAGED END FITTING, AND FASTENERS AT STATION Y1530 LONGERON 23 RIGHT IAW DC8 SRM 53-2-0, AND 51-1-20D.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION 1460 LONGERON 9 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FLOOR SUPPORTS CORRODED AT STATION Y1540, X40 AND -X40 AT Z0. REPLACED FLOOR SUPPORTS PER ALL APPLICABLE DATA.

Part: ANGLE — CRACKED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING TEE ANGLE CRACKED AT STATION XRS162. REPAIRED PER ALL APPLICABLE DATA.

Part: RIB — CRACKED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING LEADING EDGE RIB CRACKED AT STATION XFS773. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CRACKED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LONGERON 20 LEFT END FITTING CRACKED AT STATION Y1530. REPAIRED PER ALL APPLICABLE DATA

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND A DOUBLE DRILLED HOLE AT STATION 1080 LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 960 LONGERON 7 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 857.1 LONGERON 14 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 20,947 hrs · 2,994 cycles

DURING ROUTINE C CHECK FOUND FRAME WITH A DOUBLE DRILLED HOLE AT STATION Y759 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LONGERON 8 RIGHT CORRODED BETWEEN STATIONS Y300 TO Y348. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 2,994 cycles

DURING ROUTINE C CHECK FOUND FRAME WITH A DOUBLE DRILLED HOLE AT STATION Y742 AT LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND A DOUBLE DRILLED HOLE AT STATION 960 LONGERON 14 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 2,994 cycles

DURING ROUTINE C CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 900 TO 902 LONGERON 14 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 822.5 LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND INTERCOSTAL CORRODED FROM STATION Y270 TO Y255 BETWEEN LONGERONS 6 LEFT AND 7 LEFT. REPAIRED PER ALL APPLICABLE DATA

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C-CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 1000 LONGERON 14 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND A DOUBLE DRILLED HOLE AT STATION 1140 LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND DOUBLE DRILLED HOLE AT STATION 822.5 LONGERON 14 LEFT. REPAIRED FRAME PER ALL APPLICABLE DATA.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND CORRODED INTERCOSTAL FROM STATION Y702.75 TO Y717.75 AT LONGERON 20 LEFT. REPLACED INTERCOSTAL PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 1060 LONGERON 14 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 880 LONGERON 14 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 1120 LONGERON 14 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: DOUBLER — CORRODED (ZONE100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND DOUBLER ATTACH FRAME CORRODED AT STATION Y255. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 920 LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 100) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND A FRAME RADIUS WITH A HOLE AT STATION 1400 LONGERON 14 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — WORN (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND FRAME WORN IN SEVERAL PLACED AT STATION 480 BETWEEN LONGERONS 20 LEFT AND 21 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND A DOUBLE DRILLED HOLE AT STATION 940 LONGERON 7 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — TOOL DAMAGE (ZONE 200) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND A DOUBLE DRILLED HOLE AT STATION 1120 LONGERON 7 RIGHT. REPAIRED PER ALL APPLICABLE DATA.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND FRAME FLANGE WITH A DOUBLE DRILLED HOLE AT STATION 864.5 LONGERON 14 LEFT. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — CORRODED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER UPPER SKIN FROM FRONT SPAR TO REAR SPAR AT STATION XE28.843 CORRODED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT HORIZONTAL STABILIZER TRAILING EDGE LOWER PANEL BETWEEN STATION XE149 TO XE77 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER TRAILING EDGE LOWER PANEL BETWEEN STATION XE221 TO XE272 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE149 TO XE77 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — DENTED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING INBOARD AILERON LOWER SKIN DENTED AND SCRATCHED AT STATION XA524. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — CORRODED (ZONE 600) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING TRAILING EDGE LOWER PANEL CORRODED AROUND SCREWS AT STATION XRS169. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER TRAILING EDGE LOWER PANEL BETWEEN STATION XE272 TO XE312.5 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER TRAILING EDGE LOWER PANEL BETWEEN STATION XE221 TO XE272 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE221 TO XE272 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT HORIZONTAL STABILIZER TRAILING EDGE LOWER PANEL BETWEEN STATION XE149 TO XE272 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER TRAILING EDGE LOWER PANEL BETWEEN STATION XE77 TO XE28.843 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE272 TO XE312.5 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE149 TO XE221 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND RIGHT HAND HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE28.843 TO XE77 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT HORIZONTAL STABILIZER TRAILING EDGE SECTION BETWEEN STATION XE272 TO XE312 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE300) · airframe 76,460 hrs · 20,947 cycles

LEFT HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE149 TO XE77 BULGED AND DENTED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER TRAILING EDGE LOWER PANEL BETWEEN STATION XE149 TO XE221 BULGED AND DENTED. REPAIRED PER ALL APPLICABLE DATA.

Part: FITTING — CORRODED (TE FLAPS) · airframe 76,460 hrs · 2,947 cycles

DURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP HINGE FITTING CORRODED AT STATION XF340. REPAIRED PER ALL APPLICABLE DATA

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER TRAILING EDGE LOWER PANEL BETWEEN STATION XE77 TO XE149 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE149 TO XE221 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE272 TO XE312.5 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (HORIZ STAB) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK FOUND LEFT HAND HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE221 TO XE272 BULGED AND RIVET SHEARED. REPAIRED PER ALL APPLICABLE DATA.

Part: PANEL — BULGED (ZONE 300) · airframe 76,460 hrs · 20,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER TRAILING EDGE UPPER PANEL BETWEEN STATION XE77 TO XE28.843 BULGED. REPAIRED PER ALL APPLICABLE DATA.

Part: SKIN — SCRATCHED (ZONE 300) · airframe 76,460 hrs · 2,947 cycles

DURING ROUTINE C CHECK, FOUND LEFT HORIZONTAL STABILIZER LEADING EDGE LOWER SKIN SCRATCHED AT STATION XFS139.250. REPAIRED PER ALL APPLICABLE DATA.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 75,948 hrs · 20,802 cycles

ONE HOUR AND A HALF INTO CRUISE FROM KBWI THE CAPTAINS WINDSHIELD CRACKED. CREW RETURNED THE AIRCRAFT TO KBWI AND LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED WINDSHIELD AND HEAT CONTROLLER PER ALL APPLICABLE MANUALS. OPERATIONAL CHECK WAS GOOD. AIRCRAFT WAS RETURNED TO SERVICE.

Part: COMPRESSOR — STALLED (NR 3 ENGINE) · airframe 75,662 hrs · 20,720 cycles

ON TAKE OFF FROM TAPA AT 115KTS NR 3 ENGINE COMPRESSOR STALLED AND POWER ROLLED BACK. CREW REJECTED TAKE OFF. 1 TIRE WAS FLAT AND THERMALED 3 MAIN ON RIGHT GEAR. MAINTENANCE INSPECTED NR 3 ENGINE FOR FOD/BIRD STRIKE PER ALL APPLICABLE MANUALS, AND NO DEFECTS WERE NOTED. AIRCRAFT WAS RETURNED TO SERVICE.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 77,243 hrs · 20,302 cycles

DURING CLIMB OUT OF WRI COPILOTS WINDSHIELD CRACKED. CREW ELECTED TO RETURN TO WRI AND MADE AN UNEVENTFULL LANDING.

Part: SKIN — CORRODED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FUSELAGE STATION 902 STRINGER 11. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND DRAWING Q95-R01

Part: SKIN — CORRODED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED AT STATION 922 AND LONGERON 20L. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL

Part: SKIN — CORRODED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FUSELAGE FUSELAGE STATION 742.250 LONGERON 21R BELOW FORWARD EMERGENCY DOOR. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLATION OF FINGER DOUBLER AND DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL

Part: WINDOW FRAME — CORRODED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FOURTH LEFT CABIN WINDOW FRAME FUSELAGE STATION 490 LONGERON 16L. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL

Part: WINDOW FRAME — CORRODED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FIRST LEFT CABIN WINDOW FRAME FUSELAGE STATION 300 LONGERON 16L. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IAW DOUGLAS SRM.

Part: STRUCTURE — DAMAGED (CARGO DOOR) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION AND DENTS WERE DISCOVERED ON THE C-3 DOOR SCUFF PLATE. REPAIR ACCOMPLISHED, REMOVAL OF SCUFF PLATE AND DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER AND TRIPLER AND NEW SCUFF PLATE IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING AUTHORIZATION 28298-5632-02-139

Part: SKIN — CRACKED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE FORWARD COMPARTMENT DOOR CUT OUT LOWER CORNER AFT SECTION. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLATION OF BELLY SKIN FROM STATION 270 TO 390 IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — CORRODED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FUSELAGE SKIN STATION 1000 LONGEORN 19L. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLAION OF REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING DRAWING 53-02491-1.

Part: SKIN — CORRODED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FUSELAGE AT FUSELAGE STATION 1030 LONGERON 21R. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IAW THE DOUGLAS SRM AND ENGINEERING DRAWING 53-02491-3.

Part: DRAIN MAST — CORRODED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE BASE OF THE DRAIN MAST AT STATION 1574 LONGERON 28R. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL

Part: SKIN — CORRODED (LT WING) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE LEFT WING LEADING EDGE AT XW 485. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLATION OF FILLER AND EXTERNAL DOUBLER IAW THE DOUGLAS SRM.

Part: SKIN — CORRODED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION AND CRACKS WERE DETECTED UNDER AN EXISTING REPAIR ON THE FUSELAGE AT STATION 1530 LONGERON 21L TO LONGERON 21R. REPAIR ACCOMPLISHED, REMOVED DAMAGED AREA AND EXISTING DOUBLER, FABRICATION AND INSTALLATION OF NEW REPAIR DOUBLER, FILLER AND FINGER DOUBLER IAW THE DOUGLAS SRM AND EA 28298-5209-02-125

Part: FRAME — CRACKED (TAIL) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE AFT TAIL COMPARTMENT RT CIRCUMFERENTIAL FRAME, AFT AND ABOVE ACCESS PANEL 62 ZONE 37. REPAIR ACCOMPLISHED, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL

Part: SKIN — CORRODED (LT WING) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE LEFT WING LEADING EDGE OUTBOARD XW488. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATED AND INSTALLED REPAIR FILLER AND DOUBLER IAW THE DOUGLAS SRM AND EA 28298-5269-02-129

Part: SKIN — CRACKED (FUSELAGE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DISCOVERED ON THE FUSELAGE STATION 1210 LONGERON 19L FORWARD OF THE AFT EMERGENCY EXIT DOOR. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IAW THE DOUGLAS SRM AND DRAWING 53-02491-2.

Part: SKIN — CRACKED (LT WING LE) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON A SCREW HOLE ON THE LEFT WING OUTBOARD LEADING EDGE STA XFS 710. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGE, FABRICATION AND INSTALLATION OF REPAIR FILLER AND DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL

Part: SKIN — CORRODED (RUDDER) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE RUDDER TRAILING EDGE ABOVE THE TAB. REPAIR ACCOMPLISHED, REMOVED SURFACE CORROSION IAW THE DOUGLAS SRM.

Part: SKIN PANEL — CORRODED (RT WING) · airframe 73,466 hrs · 20,110 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE RIGHT WING UPPER LEADING EDGE PANEL BY THE NUMBER FOUR PYLON. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IAW THE DOUGLAS SRM AND DRAWING 57-02491.

Part: MECHANISM — STIFF (GEAR) · airframe 72,907 hrs · 19,284 cycles

AFTER TAKE OFF FROM HIK, THE LANDING GEAR NOT LATCHED LIGHT ILLUMINATED FOLLOWING LANDING GEAR RETRACTION. THE FLIGHT CREW CYCLED THE GEAR BUT THE WARNING INDICATION REMAINED THE SAME. THE FLIGHT RETURNED TO HIK FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE LEFT MAIN LANDING GEAR UPLATCH MECHANISM LACKING LUBRICATION. MAINTENANCE LUBRICATED THE UPLATCH MECHANISM AND PERFORMED A SUCCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: TERMINAL — LOOSE (GEAR DOOR) · airframe 72,906 hrs · 19,283 cycles

AFTER TAKEOFF FROM HIK, THE GEAR DOOR NOT LATCHED AND THE GEAR NOT LATCHED LIGHT ILLUMINATED AFTER GEAR RETRACTION. THE FLIGHT CREW CYCLED THE LANDING GEAR BUT THE WARNING INDICATION REMAINED THE SAME. THE FLIGHT RETURNED TO HIK FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED A LOOSE TERMINAL AT THE RIGHT HAND MAIN GEAR DOOR PROXIMITY SWITCH. MAINTENANCE TIGHTENED THE TERMINAL AND PERFORMED A SUCCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: LINKAGE — DRY (TAIL) · airframe 72,154 hrs · 19,805 cycles

DURING CLIMB FROM QPG TO DNA, THE FLIGHT CREW WAS UNABLE TO MAINTAING CABIN PRESSURIZATION. THE FLIGHT CREW DECLAIRED AND EMERGENCY AND FOLLOWED COMPANY PROCEDURES AND RETURNED TO QPG FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WITH NO DISCREPANCIES NOTED. MAINTENANCE LUBRICATED THE OUTFLOW VALVE LINKAGE AND PERFOMRED A SUCCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: UPLOCK — MISRIGGED (MLG) · airframe 70,452 hrs · 19,409 cycles

EN ROUTE FROM HIK TO SUU, THE GEAR DOOR NOT LATCH LIGHT ILLUMINATED DURING THE LANDING GEAR UPLATCH CHECK. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURE, PLACED THE GEAR LEVER IN THE UP POSITION DETENT AND CONTINUED TO SUU FOR AN UNEVENTFULL LANDING. MAINTENANCE INSPECTED THE LANDING GEAR, PERFORMED AN OPERATIONAL CHECK WHICH REVEALED THE LEFT MAIN DOOR UPLATCH MECHANISM OUT OF ADJUSTMENT. A RIG OF THE LEFT GEAR DOOR UPLATCH MECHANISM IN ACCORDANCE WITH THE MAINTENANCE MANUAL. MAINTENANCE PERFORMED A SUCCESSFUL OPERATIONAL CHECK. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SENSOR — DEFECTIVE (MLG DOOR) · airframe 70,447 hrs · 19,408 cycles

EN ROUTE FROM QPG TO HIK, THE LANDING GEAR DOOR NOT LATCH LIGHT ILLUMINATED DURING CRUISE. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES AND CONTINUED TO HIK FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE GEAR DOOR WARNING INDICATION SYSTEM WHICH LOCATED A DEFECTIVE LEFT MAIN GEAR DOOR POSITION SENSOR. MAINTENANCE REPLACED THE SENSOR AND PERFORMED A SUCCESSFUL OPERATIONAL CHECK. THE AIRCRAFT WAS RETURNED TO SERVCE.

Part: CONTROL VALVE — MISRIGGED (RT MLG WW) · airframe 70,090 hrs · 19,330 cycles

EN ROUTE FROM GSO TO TOL FOLLOWING ROUTINE MAINTENANCE, THE RIGHT MAIN LANDING GEAR FAILED TO RETRACT AFTER TAKEOFF. THE FLIGHT CREW CYCLED THE GEAR WITH NO SUCCESS. THE FLIGHT RETURNED TO GSO FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE LANDING GEAR SYSTEM WHICH REVEALED DISCREPANCIES ASSOICATED WITH THE LANDING GEAR HYDRAULIC CONTROL SYSTEM. MAINTENANCE RIGGED THE LANDING GEAR CONTROL AND HYDRAULIC SELECTOR SYSTEMS IN ACCORDANCE WITH THE MAINTENANCE MANUAL AND PERFORMED A SUCCESSFUL OPERATIONAL CHECK. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: PUMP — MALFUNCTIONED (LT AFT LAV)

EN ROUTE FROM HIK TO SUU, THE LEFT AFT LAVATORY EMITTED AN ELECTRICAL BURNING ODOR WHEN THE LAV WAS FLUSHED. THE LAVATORY COMPARTMENT WAS CLOSED OFF FOR THE REMAINDER OF THE FLIGHT. MAINTENANCE OPERATED THE PUMP NUMEROUS TIMES, WITH NO DEFECTS NOTED. MAINTENANCE REMOVED THE PUMP AND VISUALLY INSPECTED, WITH NO DISCREPANCIES NOTED. MAINTENANCE REPLACEDTHE PUMP AS A PRECAUTIONARY MEASURE.

Part: SOCKET — SHORTED (GLARESHIELD)

EN ROUTE, A BURNT ODOR WAS SENSED WHEN THE COCKPIT WHITE LIGHTING WAS TURNED ON. THE COCKPIT LIGHTING WAS TURNED OFF FOR THE REMAINDER OF THE FLIGHT. MAINTENANCE INVESTIGATED AND FOUND A GLARESHIELD FLUORESCENT LIGHT SOCKET SHORTED. MAINTENANCE DEACTIVATED AND DEFERRED THE GLARESHIELD LIGHTING.

Part: FAN — FAILED (COCKPIT)

EN ROUTE, A BURNT ODOR WAS SENSED IN THE COCKPIT WITH THE LEFT RECIRCULATION FAN OPERATING. THE FAN WAS SHUT OFF FOR THE REMAINDER OF THE FLIGHT. MAINTENANCE FOUND THE FAN DEFECTIVE. MAINTENANCE DEFERRED THE LEFT RECIRCULATION FAN.

Part: PANEL — CORRODED (LT HORZ STAB)

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE LEFT HORIZONTAL STABILIZER UPPER PANEL, INNER BEADED SKIN BETWEEN STATION XE150 TO 250. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN INTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED SKETCH C59-R10 AND ENGINEERING ORDER 55-DC8-696.

Part: SLOT DOOR — CRACKED (RT WING)

DURING ROUTINE C-CHECK INSPECTION, TWO CRACKS WERE FOUND ON THE RIGHT WING INBOARD LEADING EDGE SLOT DOOR. REPAIR ACCOMPLISHED STOP DRILLING THE ENDS OF THE CRACKS, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING 97-002 AND ENGINEERING ORDER 27-DC8-693.

Part: PLATING — CRACKED (BS 1730)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON THE EXTERNAL PLATING AT FUSELAGE STATION 1730, LONGERON 36. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED SKETCH C59-R09 AND ENGINEERING ORDER 51-DC8-690.

Part: PLATING — CRACKED (BS 1500)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON THE EXTERNAL PLATING JUST FORWARD OF OUTFLOW VALVE OPENING AT FUSELAGE STATION 1500, BETWEEN LONGERON 35 AND 36 LEFT. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED SKETCH C59-R07 AND ENGINEERING ORDER 53-DC8-689.

Part: PLATING — CORRODED (BS 185)

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE EXTERNAL PLATING AT FUSELAGE STATION 185, LONGERON 31 LEFT. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED SKETCH C59-R03 AND ENGINEERING ORDER 51-DC8-685.

Part: PLATING — CORRODED (RT WING)

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE LEFT WING LOWER LEADING EDGE AT STATION XFS 710. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED SKETCH C59-R02 AND ENGINEERING ORDER 57-DC8-684.

Part: BEAM — CORRODED (BS 1440)

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE FLOOR SUPPORT BEAM AT RIGHT BUTT LINE 45.0, AT FUSELAGE STATION 1440. REPAIR ACCOMPLISHED CORROSION REMOVAL, FABRICATION AND INSTALLATION OF TWO REPAIR DOUBLERS IN ACCORDANCE WITH DER APPROVED SKETCH C59-R06 AND ENGINEERING ORDER 51-DC8-588.

Part: PLATING — CRACKED (BS 1530)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND PROTRUDING TO A RIVET HOLE FROM STATION 1530, LONGERON 31 RIGHT. REPAIR ACCOMPLISHED VERIFICATION THAT THE CRACK DID NOT PROGRESS PASS RIVET HOLE, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED SKETCH C59-R01 AND ENGINEERING ORDER 53-DC8-683.

Part: PLATING — CRACKED (BS 1460)

DURING ROUTINE C-CHECK INSPECTION, THE LOWER FORWARD CORNER OF LEFT AFT PASSENGER ENTRY DOOR WAS FOUND TO BE CRACKED AT FUSELAGE STATION 1460. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS DRAWING 97-05-15-008, DOUGLAS ACTION LETTER 332357, AND ENGINEERING ORDER 53-DC8-700.

Part: PLATING — CORRODED (BS 211)

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE EXTERNAL PLATING AT FUSELAGE STATION 211, LONGERON 28 RIGHT. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREAS, FABRICATION AND INSTALLATION OF INTERNAL FILLERS AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED SKETCH C59-R04 AND ENGINEERING ORDER 53-DC8-868.

Part: PRESSURE PANEL — CRACKED (BS 680)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON THE RIGHT LOWER PRESSURE WEB PANEL AT FUSELAGE STATION 680. REPAIR ACCOMPLISHED REMOVAL AND INSTALLATION OF A NEW WEB PANEL IN ACCORDANCE WITH DOUGLAS AIRCRAFT COMPANY SRM 53-1-0, 51-1-20D, AND 51-1-21.

Part: ATTACH FITTING — CRACKED (NR 3 PYLON)

DURING ROUTINE C-CHECK INSPECTION, THE NR 3 PYLON FOOTSTOOL FITTING WAS FOUND TO BE CRACKED. THE FITTING WAS REMOVED AND REPLACED IN ACCORDANCE WITH THE DOUGLAS STRUCTURE REPAIR MANUAL 51-3-0, 51-1-20D AND 51-1-21.

Part: FAN — FAILED (AC BAY)

IN FLIGHT, WHEN THE LEFT HAND RECIRCULATION FAN WAS TURNED ON, A BURNING ODOR WAS VERY NOTICEABLE, THE FAN WAS TURNED OFF FOR THE REMAINDER OF THE FLIGHT. AFTER AN UNEVENTFUL LANDING, MAINTENANCE DEFERRED THE FAN AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: WATER HEATER — FAILED (RT AFT LAV)

DURING DESCENT, THE FLIGHT ATTENDANT REPORTED VIA INTERPHONE TO COCKPIT, THAT THE RIGHT AFT LAVATORY SMOKE DETECTOR WAS SOUNDING AND A SMELL OF SMOKE. THE FLIGHT ENGINEER WAS DISPATCHED TO INVESTIGATE. THE FLIGHT ATTENDANT DISCHARGED A PORTABLE FIRE EXTINGUISHER UNDER THE SINK AND TOILET AREA, WHILE THE FLIGHT ENGINEER REMOVED ELECTRICAL POWER BY OPENING THE CIRCUIT BREAKERS OF THE LAVATORY. THE FLIGHT ENGINEER REPORTED SMOKE WAS DIMINISHING AND A UNEVENTFUL LANDING WAS MADE. MAINTENANCE IDENTIFIED THE SOURCE OF SMOKE TO BE FROM THE LAVATORY WATER HEATER. MAINTENANCE REPLACED THE DEFECTIVE WATER HEATER AND NO FUTHER DISCREPANCES WERE NOTED.

Part: FIRE DETECT AMP — MALFUNCTIONED (NR 3 ENGINE)

EN ROUTE QPG TO OKO, THE NR 3 ENGINE FIRE WARNING LIGHTS ILLUMINATED. CREW SHUT THE ENGINE DOWN AND SEQUENCED THE FIRE BOTTLE FOR THAT ENGINE ON A PRECAUTIONARY BASIS. AIRCRAFT RETURNED QPG WITH AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE FOR EVIDENCE OF A FIRE, NO EVIDENCE WAS FOUND. MAINTENANCE REPLACED THE FIRE BOTTLE, FIRE DETECTOR AMPLIFIER AND CLEANED THE FIRE DETECTOR CONNECTORS. A SUCCESSFUL ENGINE RUN WAS COMPLETED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (M)

Part: UPLATCH — LACK OF LUBE (LT/RT MLG DOOR)

ON DEPARTURE OUT OF RODN, THE GEAR DOOR 'NOT LATCHED' LIGHT ILLUMINATED. THE LANDING GEAR WAS CYCLED, AND THE WARNING LIGHT EXTINGUISHED. IN RJTY, MAINTENANCE CLEANED THE MLG DOOR UPLATCH SWITCHES, CLEANED AND LUBRICATED THE MLG DOOR UPLATCH ROLLERS IAW THE DC-8 MM. THE INDICATION AND DOOR UPLOCK OPERATION WERE NORMAL, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (M)

Part: ANGLE — CRACKED (LT VERT STAB)

DURING THE C-CHECK INSPECTION, THE VERTICAL STAB TO FUSELAGE ATTACH ANGLE WAS FOUND CORRODED AND CRACKED ON THE LT FROM FORWARD OF THE FRONT SPAR TO CENTER SPAR. A REPAIR WAS PERFORMED PER ATI E.O. 53-DC8-223, AND DRAWING SKA95253-5, REV: A, DATED 1-23-96. THIS REPAIR WAS APPROVED ON FAA FORM 8110-3. (X)

Part: DOOR FRAME — CORRODED (FS 1190)

DURING THE C-CHECK INSPECTION, CORROSION WAS FOUND AT THE RT JET ESCAPE DOOR LOCATED ON THE FWD LOWER CORNER. A REPAIR WAS PERFORMED PER ATI E.O. 53-DC8-224, AND DRAWING SKA95253-6, REV: IR, DATED 1-6-96. (X)

Part: SEAT TRACK — DAMAGED (FS 530)

DURING THE C-CHECK INSPECTION, A SEAT TRACK AT FS 530 WAS FOUND DAMAGED. A REPAIR WAS PERFORMED TO THE TRACK BY THE INSTALLATION OF A PLUG PER ATI E.O. 53-DC8-219, AND DRAWING SKA95253-2, REV: IR, SHEETS 1 AND 2, DATED 1-4-96. THIS REPAIR WAS APPROVED BY FAA FORM 8110-3. (X)

Part: SEAT TRACK — DAMAGED (FS 440)

DURING THE C-CHECK INPSECTION, A SEAT TRACK AT FS 440 WAS FOUND DAMAGED. A REPAIR WAS PERFORMED TO THE TRACK BY THE INSTALLATION OF A PLUG PER ATI E.O. 53-DC8-220, AND DRAWING SKA95253-1, REV: IR, SHEETS 1 AND 2, DATED 1-4-96. THIS REPAIR WAS APPROVED BY FAA FORM 8110-3. (X)

Part: FRAME — DAMAGED (FS 740)

DURING THE C-CHECK INSPECTION, FOUND A MISDRILLED HOLE IN FRAME AT FS 740R. THIS HOLE WAS REPAIRED PER ATI E.O. 53-DC8-221 AND ATI DRAWING SKA95253-3, REV: IR, DATED 1-16-96 WHICH WAS APPROVED ON FAA FORM 8110-3. (X)

Part: FRAME — DAMAGED (FS 460)

DURING THE C-CHECK INSPECTION, FOUND A MISDRILLED HOLE IN FRAME AT FS 460R. THIS HOLE WAS REPAIRED PER ATI E.O. 53-DC8-222, AND ATI DRAWING SKA95253-4, REV: IR, DATED 1-6-96 AND IS APPROVED BY FAA FORM 8110-3. (X)

Part: FRAME — DAMAGED (FS 500)

DURING THE C-CHECK INSPECTION, THE FRAME AT FS 500, LONGERON L35R WAS FOUND DAMAGED. A REPAIR WAS ACCOMPLISHED PER ATI DRAWING SKA95253-7, REV: IR, DATED 1-20-96 AND WAS APPROVED BY FAA FORM 8110-3. (X)

Part: FITTING — CORRODED (FS 490-500)

DURING THE C-CHECK INSPECTION, EXFOLIATED CORROSION WAS FOUND AT FS 490 TO FS 500 LOCATED IN THE FWD LOWER CARGO BILGE, LONGERON 33L-34L INSIDE THE TORQUE BOX TO SKIN ATTACH ANGLES. INSTALLED NEW FITTING AT FS 492 AND LONGERONS 33L-34L IAW DACO SRM 51-1-8 AND SRM 53-2-0. A REPAIR WAS PERFORMED PER THE ATI DRAWING SKA95253-7 AND WAS APPROVED ON FAA FORM 8110-3. (X)

Part: BRAKES — OUT OF ADJUST (NLG)

CUF/WRI - DURING FLIGHT BETWEEN CUF AND WRI, CREW REPORTED BURNING RUBBER ODOR IN AIRCRAFT. MAINTENANCE ADJUSTED THE NOSE WHEEL BRAKE PADS, WHICH CAUSED THE RUBBER ODOR, AND CLIMINATED A PNEUMATIC LEAK AT NR 2 CABIN COMPRESSOR DUCT. THE AIRCRAFT WAS RETURNED TO SERVICE. (X)

Part: ENGINE — BIRD STIKE (NR 1)

ON DEPARTURE OUT OF DIEGO GARCIA, A SEA BIRD WAS OBSERVED TO ENTER THE NR 1 ENGINE, CAUSING SUBSTANTIAL FOREIGN OBJECT DAMAGE TO THE ENGINE GAS PATH. INGESTION OF THE SEA BIRD ALSO CAUSED DAMAGE TO THE NOSE COWL, BULLET, AND FAN DUCTS. THE AIRCRAFT RETURNED TO DIEGO GARCIA FOR MAINTENANCE, WHERE AN UNEVENTFUL LANDING WAS ACCOMPLISHED. ARRANGEMENTS WERE MADE TO REPLACE THE ENGINE AT THE LOCATION.