N603AL

Part: PIN — SHEARED (ZONE 700) · airframe 102,117 hrs · 33,549 cycles

DURING CLIMB OUT, AFTER GEAR RETRACTION, CREW NOTICED AN UNSAFE GEAR LIGHT INDICATION. ACCOMPLISHED UPLATCH CHECK, AND WHEN CYCLING THE GEARS FELT A VIOLENT SHUDDER AND THE LT MLG DOWN LIGHT ILLUMINATED INTERMITTENTLY. RETURNED TO DEPARTURE AND LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED LANDING GEARS AND FOUND THE LT GEAR RETRACT PIN SHEARED. THEY PERFORMED INSP FOR FERRY FLIGHT IAW GMM 3.117. MX REPLACED THE LT GEAR RETRACT PIN. OPS CHECK GOOD IAW SB 32-102 AND MM 32-32-2, TEMP REV 32-121.

Part: CONNECTOR — LOOSE (FIRE DETECTOR) · airframe 102,029 hrs · 33,497 cycles

DURING CRUISE NR 1 ENGINE FIRE WARNING AND BELL FLICKERED MOMENTARILY AT 410, SAT -50, TAT -21, MANIFOLD PRESSURE 32, MANIFOLD AIR TEP 150. THE CREW TESTED FIRE WARNING AND SHORT CIRCUIT WERE NORMAL CONDITION, REMAINED NORMAL REST OF FLIGHT. THEY LANDED IN KSJC WITH NO FURTHER INCIDENT. MX INSPECTED AND FOUND RT PYLON TOP LOOP GROUND STUD LOOSE AND LT FWD LOOP AFT CONNECTOR LOOSE, THEY TIGHTENED BOTH CONNECTION. OPS CHECK GOOD IAW MM 26-00 70 SERIES, GMM 3.124. ACFT WAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (BS 1400 S36) · airframe 102,011 hrs · 33,490 cycles

DURING WALK AROUND, FOUND A CRACK ON BELLY CTR LINE LONGERON 36 AT STA 1400. MX REPAIRED IAW SRM 53-2-1 CLASS 3. ACFT WAS RETURNED TO SERVICE.

Part: COMPRESSOR — BIRD INGESTION (ZONE 400) · airframe 101,526 hrs · 33,249 cycles

DURING TAKEOFF, CREW EXPERIENCE A COMPRESSOR STALL ON RT SIDE. THEY ABORTED TAKEOFF AND RETURNED TO BLOCKS. MX INSPECTED BOTH NR (3) AND NR (4) ENGINE AND FOUND EVIDENCE OF A BIRD STRIKE ON NR (4) ENGINE. THEY PERFORMED BORESCOPE INSP, COMPLIED WITH CFM 56, FAULT 41 INSP AND RAN ENGINES. OPS CHECK GOOD IAW MM 71-00-00, ERH 70.01, ATI J/C 13.01-3, J/C 13.01-4, J/C 13.01-5 AND J/C 7203. ACFT WAS RETURNED TO SERVICE.

Part: PIN — BROKEN (MLG) · airframe 101,242 hrs · 33,114 cycles

DURING CLIMBOUT, ON GEAR RETRACTION, THE CREW HEARD LOUD BANG, BOTH DOORS NOT LATCH LIGHT AND GEAR NOT LATCH LIGHT REMAINED ON. THEY RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX INSPECTED AND FOUND RT MLG RETRACT CYL ATTACH PIN BROKE. THEY REPLACED RETRACT PIN. OPS CHECK GOOD IAW S/B 32-102 R7 DATED 8/11/09 AND MM 32-32-2, 32-30-0. ACFT WAS RETURNED TO SERVICE.

Part: UPLOCK — FAILED (MLG) · airframe 101,119 hrs · 33,068 cycles

DURING UPLATCH CHECK, GEAR NOT LATCH LIGHT CAME ON, CREW CYCLED THE GEAR AND GEAR NOT LATCH LIGHT REMAINED ON THE REMAINDER OF FLIGHT. THEY LANDED WITHOUT FURTHER INCIDENT. MX DEFERRED MAIN UPLATCH SYS, IAW MEL 32-16-01. MX FOUND THE LT AND RT MAIN GEAR ACTUATING CYLINDER NOT BOTTOMED OUT. THEY BOTTOMED OUT BOTH ACTUATING CYLINDERS. OPS CHECK GOOD IAW MM 32-32-2 AND 32-30-00. ACFT WAS RETURNED TO SERVICE.

Part: SWITCH — DEFECTIVE (MLG) · airframe 101,108 hrs · 33,064 cycles

DURING UPLATCH CHECK, GEAR NOT LATCH LIGHT CAME ON, THE CREW CYCLED GEARS AND THE GEAR NOT LATCH LIGHT REMAINED ON THE REMAINDER OF FLIGHT. THEY LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED AND FOUND NLG UPLATCH OVER CTR MECHANISM BINDING, NOT GOING OVER CTR, CLEANED AND LUBED UPLATCH. ALSO FOUND LT MLG DOOR PULL TEST LOW, ADJUSTED LT MLG LOCK SPRING. REPLACED LT MLG DOWN AND LOCKED SWITCH. OPS CHECK GOOD IAW MM 32-30-0, 32-31-4, 32-60-0. ACFT WAS RETURNED TO SERVICE.

Part: UPLOCK — MALFUNCTIONED (ZONE 700) · airframe 101,104 hrs · 33,063 cycles

DURING CLIMB OUT, DOOR NOT LATCH LIGHT ILLUMINATED, THE CREW CYCLED THE GEAR AND DOOR NOT LATCH LIGHT CAME ON AGAIN. WHEN GEAR HANDLE IS PLACED IN UPLATCH CHECK POSITION, THE GEAR HANDLE IN UP POSITION THE LIGHT WENT OUT AND STAYED OUT REMAINDER OF FLIGHT. THEY LANDED WITHOUT FURTHER INCIDENT. MX JACKED ACFT AND CYCLED THE GEARS SEVERAL TIMES. OPS CHECK GOOD IAW MM 32-30-0 AND 7-11-0. ACFT WAS RETURNED TO SERVICE.

Part: UPLOCK — NO TEST (MLG) · airframe 101,087 hrs · 33,055 cycles

DURING "C" CHECK INSP TEST FLIGHT, GEAR UPLATCH CHECK FAILED AFTER TAKEOFF, THE CREW CYCLED GEAR AND UPLATCH CHECK FAILED A SECOND TIME WITH GEAR RED LIGHT STAYED ON. THEY RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX PERFORMED LANDING GEAR EXTENSION AND RETRACTION TEST, AND FOUND NLG DOES NOT PERFORM UPLATCH PROCEDURE. MX ADJUSTED NOSE LANDING GEAR DOOR. OPS CHECK GOOD IAW MM 32-22-1, PAGE 501-504, 32-30-0. ACFT WAS RETURNED TO SERVICE.

Part: WEB — CRACKED (ZONE 500) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP FOUND LT WING INBD LOWER SLOT DOOR WEB BROKEN. REMOVED DAMAGED WEB. FABRICATED NEW WEB. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 51-3-0, SRM 57-1-0 PAGE 1, SRM 57-3-3 FIGURE 22 ITEM "G", DPS 4.710 REV "L", SRM 51-1-8B, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — DAMAGED (ZONE 600) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP FOUND RT WING NR 3 INBD SLOT VANE HOLES ELONGATED AT STA XW 257.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLER, FILLERS, INTERNAL DOUBLERS. CLEANED, TREATED, RIMED AREA AND REPAIR AREA. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/11/10, DWG ED-5079 DATED 01/30/10, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, ED-5074, NDT SPM PART 06-10-01-001, SRM 51-1-8B, AND SRM 51-3-1.

Part: SKIN — CORRODED (RUDDER) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP FOUND RUDDER LT EXTERNAL SKIN CORRODED AT STA ZR 155.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED CORRODED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. PERFORMED RUDDER BALANCE. FOUND WITHIN LIMITS MOMENT 2455.82 IN-POUNDS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 55-6-1 FIGURE 1 PAGE 2, SRM 51-1-8 PAGE17-18, SRM 55-2-0 FIGURE 6, SRM 51-1-21 PAGE 1, SRM 55-6-1 FIGURE 1 ITEM "A", SRM 51-1-9 TR NR 51-142, SRM 51-1-9A TR NR 51-141, SRM 51-1-8B, SRM 51-1-21 PAGE 1-6, AND SRM 51-4-6 PAGES 1-4.

Part: WEB — CRACKED (RUDDER) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP FOUND RUDDER WEB INTERIOR CRACKED AT STA ZR 163.000. REMOVED CRACKED WEB. FABRICATED WEB. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. APPLIED SEALANT TO FAYING SURFACES. PERFORMED RUDDER BALANCE. FOUND WITHIN LIMITS MOMENT 2455.82 IN-POUNDS. INSTALLED NEW WEB IAW SRM 55-6-1 FIGURE 2 SHEET 2, SRM 51-1-8B, SRM 51-1-1 PAGES 1, 3, & 13, SRM 51-1-11, SRM 51-1-21, SRM 51-3-0, SRM 51-3-1, AND SRM 51-4-6 PAGES 1-4.

Part: DOUBLER — CRACKED (ZONE 500) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP FOUND NR 2 MAIN TANK TOP ACCESS DOOR NR 505F DOUBLER CRACKED AT STA XRS 22.270 STR 6. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO CRACK, NO CORROSION FOUND. FABRICATED EXTERNAL, INTERNAL REPAIR DOUBLERS AND FILLER. HEAT TREATED. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. APPLIED (PRC) SEALANT TO FAYING SURFACE. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-21 FIGURE 36, NDT SPM PART 08, SRM 57-2-1 FIGURE36, DPS 4.710 REV "L", SRM 51-1-1 PAGES 1, 13, 17, SRM 51-1-12 PAGES 7-10, SRM 51-1-8B, SRM 51-1-12 TR NR 51-133, SRM 51-1-20D, SRM 51-1-20B, SRM 51-1-21, SRM 51-1-15, AND SRM 51-3-1 PAGE 2A.

Part: DOUBLER — CRACKED (ZONE 800) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP FOUND NR 2 MAIN TANK TOP ACCESS DOOR NR 506C DOUBLER CRACKED AT STA XRS 22.750 STR 13. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED INTERNAL AND EXTERNAL DOUBLERS AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/11/10, DWG ED-5078 DATED 01/29/10, SRM 51-1-20D, SRM 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-21, SRM 51-3-0, AND SRM 51-3-1.

Part: DOOR FRAME — CRACKED (BS 1400 L26-27R) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP, FOUND FUSELAGE EXTERIOR "D" CARGO DOOR FWD UPPER JAMB CORNER CRACKED AT STA 1400.000 LONGERON 26 RT LONGERON 27 RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLER, REPAIR TRIPPLER , AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DWG SR08530019, SRM 51-1-21, SRM 51-1-20D, NDT SPM PART 06-10-01-001, SRM 51-1-8B, AND SRM 51-3-1.

Part: SKIN — CRACKED (LT WING TE FLAP) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP, FOUND LT WING INBD FLAP T/E PANEL CRACKED AT STA XW 35.000 REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLERS. BONDED PARTS AS NEEDED WITH ADHESIVE. CLEANED, TREATED, PRIMED AREA AND REPAIRED PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 57-7-1 FIGURE1 ITEM "B" AND "L", DPS 4.710 REV "L",SRM 51-1-9 TR NR 51-142, SRM 51-1-9A TR NR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, SRM 51-3-0 PG.1, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (BS 1447 L29R) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP FOUND IMPROPER REPAIR AT STA FS 1447 LONGERON 29 RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. PERFORMED INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLER, FILLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/19/10, DWG ED-5070 DATED 01/26/10, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP, FOUND IMPROPER REPAIR AT STA FS 36.5 LONGERON 30.5 LT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. PERFORMED INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLER, FILLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/19/10, DWG ED-5070 DATED 01/26/10, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (BS 615 L36) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP FOUND IMPROPER REPAIR AT STA FS 615 LONGERON 36. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. PERFORMED INSP. NO DISCREPANCY FOUND. FABRICATED REPAIR DOUBLER, FILLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02/19/10, DWG ED-5070 DATED 01/26/10, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-0, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-3-0, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (BS 1480 L33R) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP, FOUND IMPROPER REPAIR AT STA FS 1480 LONGERON 33.5R RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED INTERNAL, EXTERNAL, DOUBLERS AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 53-2-1, FIGURE 7, SHEET 1, 2, 3, 4, 23, 24 TR NR 53-203 DATED 01-21-08, SRM 51-1-21 PAGE1, SRM 51-1-20D PAGE1, SRM 53-4-1 FIGURE 17D SHEET 2 ITEM B, SRM 51-9-0 FIGURE 68, DPS 4-710 REV"L", SRM 51-1-8B, SRM 51-1-11, SRM 51-1-21 PAGE 1-6, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (BS 1465 L17R) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP FOUND IMPROPER REPAIR AT STA FS 1765 LONGERON 17.5 RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED INTERNAL, EXTERNAL, DOUBLERS AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 53-2-1 FIGURE 7 SHEET 1, 2, 3, 4, 23, 24 TR NR 53-203 DATED 01-21-08, SRM 51-1-21 PAGE1, SRM 51-1-20D PAGE1, SRM 53-4-1 FIGURE 17D SHEET 2 ITEM B, SRM 51-9-0 FIGURE 68, DPS 4-710 REV"L", SRM 51-1-8B, SRM 51-1-11, SRM 51-1-21 PAGE 1-6, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (BS 668) · airframe 101,087 hrs · 33,054 cycles

DURING ROUTINE C-CHECK INSP, FOUND IMPROPER REPAIR AT STATION FS 668 LONGERON 36. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED REPAIR DOUBLER, REPAIR TRIPLER, FILLERS AND FINGER DOUBLERS. PERFORMED NDT INSP. NO DISCREPANCY FOUND. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA 8110-3 DATED 03/03/10, DWG ED-5072 DATED 02/01/10, SRM 51-1-21, SRM 51-1-20D, NDT SP PART 06-10-01-001, SRM 51-1-8B, AND SRM 51-3-1.

Part: CONNECTOR — DIRTY (MLG) · airframe 100,990 hrs · 33,011 cycles

ON FINAL APPROACH, WHEN MLG WAS EXTENDED THE LT MLG LIGHT STAYED OUT. THE CREW RECYCLED MAIN GEARS AND ALL WAS NORMAL. THEY LANDED WITHOUT FURTHER INCIDENT. MX REMOVED, CLEANED AND INSPECTED THE LT MAIN GEAR DOWN LOCK LIMIT SWITCH CONNECTOR. OPS CHECK GOOD IAW MM 20-50-1 AND 32-60-0. ACFT WAS RETURNED TO SERVICE.

Part: SWITCH — BROKEN (MLG DOOR) · airframe 100,803 hrs · 32,936 cycles

DURING CLIMBOUT, MLG DOOR NOT LATCHED LIGHT CAME ON, THE CREW RECYCLED LANDING GEAR AND ACCOMPLISHED UPLATCH CHECK THE DOOR NOT LATCHED LIGHT STAYED ON. THEY LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED MLG AND FOUND RT GEAR DOOR SWITCH BROKEN. MX REPLACED SWITCH. OPS CHECK GOOD IAW ATI WD MM 32-01-2. ACFT WAS RETURNED TO SERVICE.

Part: HSI — DEFECTIVE (COCKPIT) · airframe 100,470 hrs · 32,783 cycles

DURING CLIMB OUT F/O ATTITUDE DIRECTOR INDICATOR AND HORIZONTAL SITUATION INDICATOR WENT BLANK. CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED F/O HORIZONTAL SITUATION INDICATOR AND ATTITUDE DIRECTOR INDICATOR. OPS CHECK GOOD IAW MM 34-01-47, 34-01-48. ACFT WAS RETURNED TO SERVICE.

Part: FAN — DEFECTIVE (CABIN) · airframe 100,090 hrs · 32,637 cycles

DURING CRUISE FROM KPHL, THE CREW DETECTED SMOKE FROM THE RECIRCULATION FAN AND NOISY. THE CREW TURNED OFF RECIRCULATION FAN SMOKE ODOR DISSIPATED. THE CREW LANDED IN KEWR WITHOUT FURTHER INCIDENT. MAINTENANCE IN KEWR REPLACED THE RECIRCULATION FAN. OPERATIONAL CHECK GOOD IAW MM 21-20-4. AIRCRAFT WAS RETURNED TO SERVICE.

Part: UPLOCK — DEFECTIVE (LT MLG) · airframe 99,733 hrs · 32,463 cycles

DURING CLIMBOUT FROM BGTL DOOR NOT LATCH LIGHT ILLUMINATED AFTER RAISING MAIN LANDING GEAR. THE CREW ACCOMPLISHED COM PROCEDURE AND THE LIGHT STAYED ON. BOTH ALTERNATING MAIN LANDING GEAR LIGHTS WERE OUT AND TESTED GOOD. THE CREW LANDED IN KTOL WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED LEFT UPLATCH CYLINDER. JACKED AIRCRAFT AND SWUNG GEAR NUMEROUS TIMES. OPERATIONAL CHECK GOOD IAW DACO MAINTENANCE MANUAL 32-30-0. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FIRE WARNING — ACTIVATED (NR 3 NACELLE) · airframe 99,529 hrs · 32,362 cycles

FLT NR: 744/ETAR TO OJAM/. DESCENDING INTO OJAM NR 3 ENGINE FIRE WARNING LIGHT CAME ON AND RED LIGHT IN FIRE HANDLE CAME ON. THE CREW DISCHARGED BOTH BOTTLES AND RED LIGHT IN FIRE HANDLE WAS STILL ON AND FIRE WARNING WAS INTERMITTENT. THE CREW LANDED IN OJAM WITHOUT FURTHER INCIDENT. CORRECTIVE ACTION IN WORK. (A)

Part: FIRE WARNING — ACTIVATED (NR 3 NACELLE) · airframe 99,529 hrs · 32,362 cycles

FLT NR: 744/ETAR TO OJAM/. DESCENDING INTO OJAM NR 3 ENGINE FIRE WARNING LIGHT CAME ON AND RED LIGHT IN FIRE HANDLE CAME ON. THE CREW DISCHARGED BOTH BOTTLES AND RED LIGHT IN FIRE HANDLE WAS STILL ON, AND FIRE WARNING WAS INTERMITTENT. THERE LANDED IN OJAM WITHOUT FURTHER INCIDENT. CORRECTIVE ACTION IN WORK. (A)

Part: ELEMENT — MALFUNCTIONED (NR 3 NACELLE) · airframe 99,529 hrs · 32,362 cycles

FLIGHT NUMBER: 744/ETAR TO OJAM - DESCENDING INTO OJAM NUMBER THREE FIRE WARNING LIGHT AND RED LIGHT IN FIRE HANDLE CAME ON. THE CREW DISCHARGED BOTH BOTTLES AND RED LIGHT IN FIRE HANDLE WAS STILL ON, AND FIRE WARNING WAS INTERMITTENT. THE CREW LANDED IN OJAM WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED FIRE DETECTOR ELEMENT, LT FAN SENSING ELEMENT, AND BOTH FIRE BOTTLES. OPERATIONAL CHECK GOOD IAW DACO DC8 MAINTENANCE MANUAL 26-10-1, AND 26-20-1. AIRCRAFT WAS RETURNED TO SERVICE. (A)

Part: ENGINE — FIRE (NR 3)

DURING FLIGHT, NR 3 ENGINE FIRE WARNING LIGHT ILLUMINATED MOMENTARILY. FLIGHT CREW RETARDED THE THROTTLES AND SHUTDOWN THE ENGINE. THE FIRE LIGHT AND WARNING WENT OUT. APPROX 30 MINUTES LATER FIRE WARNING CAME BACK ON. FLIGHT CREW FIRED (1) BOTTLE AND AGENT DISCHARGED LIGHT WENT OUT AND NEVER CAME BACK ON. AC FLEW DIRECT TO DESTINATION AND LANDED WITHOUT FURTHER INCIDENT. (OPEN) (K)

Part: FIRE WARNING — MALFUNCTIONED (NR 3 NACELLE)

DURING FLIGHT, NR 3 ENGINE FIRE WARNING LIGHT ILLUMINATED MOMENTARILY. FLIGHT CREW RETARDED THE THROTTLES AND SHUTDOWN THE ENGINE. THE FIRE LIGHT AND WARNING WENT OUT. APPROX 30 MINUTES LATER FIRE WARNING CAME BACK ON. FLIGHT CREW FIRED ONE BOTTLE AND AGENT DISCHARGED. LIGHT WENT OUT AND NEVER CAME BACK ON. AC FLEW DIRECT TO ARRIVAL AIRPORT AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED ALL FIRE SENSING ELEMENT ON NR 3 ENGINE. OPS CHECK GOOD IAW MM 26-10-16. AIRCRAFT WAS RETURNED TO SERVICE. (K)

Part: CONNECTOR — LOOSE (FIRE LOOP) · airframe 98,799 hrs · 32,086 cycles

DURING CRUISE FROM KTOL NUMBER THREE FIRE WARNING LIGHT STARTED TO FLICKER AND HORN SOUNDED. THE CREW TESTED NUMBER THREE ENGINE FIRE WARNING NO BELL OR LIGHT, PERFORMED FIRE DAMAGED CHECK LIST PULL FIRE HANDLE FORWARD TEST FIRE WARNING TESTED GOOD ALL ENGINE PARAMETERS GOOD THE CREW SHUT DOWN ENGINE. THE CREW LANDED AT KMEM WITHOUT INCIDENT. MAINTENANCE INSPECTED NUMBER THREE ENGINE FIRE LOOP, NO ABNORMALITIES FOUND, CLEANED AND RECONNECTED FIRE LOOPS CONNECTORS, DEGREASED SECTION OF LOOPS AS REQUIRED, ENSURE GOOD INSULATION ON ALL CONNECTION POINTS OPERATIONAL CHECK WAS GOOD IAW DC -8 MAINTENANCE MANUAL 26-10-1. AIRCRAFT WAS RETURNED TO SERVICE.

Part: WARNING SYSTEM — MALFUNCTIONED (ZONE 700) · airframe 98,499 hrs · 31,938 cycles

DURING CLIMB-OUT FROM KDFW TO KIAH, AFTER GEAR RETRACTION THE CREW NOTICED DOOR NOT LATCH LIGHT STAYED ON UNTIL THE CREW RECYCLED THE GEARS AND LIGHT WENT OUT. CREW LANDED AT KIAH WITHOUT INCIDENT. MAINTENANCE INSPECTED MAIN LANDING GEAR DOOR TARGET AND STRIKERS, CLEANED OPERATIONAL CHECK GOOD IAW DC8 MAINTENANCE MANUAL 32-60-0. AIRCRAFT WAS RETURNED TO SERVICE.

Part: ACTUATOR — OUT OF ADJUST (LT MLG) · airframe 98,159 hrs · 31,818 cycles

DURING CLIMB-OUT FROM KTOL, THE GEAR DOORS NOT LATCHED LIGHT ILLUMINATED. THE CREW PERFORMED AN UP-LATCH CHECK AND THE LEFT MAIN GEAR DOOR OPEN YELLOW LIGHT ILLUMINATED. THE CREW RECYCLED GEAR AND HAD A SUCCESSFUL UPLATCH CHECK BUT DOOR NOT LATCHED LIGHT REMAINED ON. THE CREW RETURNED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE GEAR SYSTEM AND FOUND THE LEFT MAIN LANDING GEAR ACTUATOR OUT OF ADJUSTMENT. MAINTENANCE ADJUSTED THE ACTUATOR IAW DACO MM 32-32-2. MAINTENANCE JACKED THE AIRCRAFT AND CYCLED THE GEAR SEVERAL TIMES WITH NO FURTHER PROBLEMS. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: PANEL — DEFORMED (TE FLAP) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION; FOUND RIGHT WING INBOARD FLAP LEADING EDGE UPPER PANEL DEFORMED BETWEEN STATION XW 123.000 AND STATION XW 136.000. REMOVED DAMAGED AREA. FABRICATED NEW SKIN AND DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 1 PAGE 2 ITEM "F", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-8B, AND DC8 51-1-11.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT FLIGHT STATION 160 LONGERON 32.5 LEFT DOUBLER FORWARD LOWER FUSELAGE LEFT SIDE OF BELLY ADF ANTENNAS REPAIR SIDE 2 AND 4 EXCEED MAXIMUM FASTENER SPACING. REMOVED FASTENERS. REMOVED DAMAGED AREA. FABRICATED EXTERNAL DOUBLER AND INTERNAL DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 53-2-1 FIGURE 7 SHEETS 1, 3, AND 5, DC8 SRM 51-1-21, SRM 53-4-1 FIGURE 4 ITEM A, SRM 51-9-0 FIGURE 68A, DC8 SRM 51-1-8B, DC8 51-1-11, 51-1-20D, AND 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT FLIGHT STATION 341 LONGERON 33LEFT DOUBLER FORWARD LOWER FUSELAGE LEFT SIDE ACROSS FROM A-PIT DOOR OPENING SIDE 1 AND 3 FORWARD AND AFT. REMOVED FASTENERS AND EXISTING REPAIR. FABRICATED NEW SKIN, EXTERNAL DOUBLER AND INTERNAL DOUBLER. CLEANED,TREATED, AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW DC8 SRM 53-2-1 FIGURE 7 SHEET 1 AND 3, DC8 SRM 51-1-21, SRM 53-4-1 FIGURE 4 ITEM "C", SRM 51-9-0 FIGURE 68A, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, 51-1-20D AND 51-3-1,

Part: LONGERON — BROKEN (ZONE 200) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IN MAIN CARGO COMPARTMENT FLANGE ON LONGERON 19 RIGHT BROKEN AT STATION 200.000 TO 212.000. LONGERON FLANGE FROM AT STATION 200.000 TO 212.000, LONGERON19 RIGHT WAS TRIMMED OFF IN PRODUCTION. NO REPAIR IS REQUIRED. FOUND NO ADDITIONAL DAMAGE, IAW MESSAGE BOEING NUMBER 1-397537201-2 OF DATA 06-29-07, AND DRAWING 5702880.

Part: SKIN — MISREPAIRED (RUDDER) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR ON RUDDER RIGHT SIDE OUTER SKIN FROM STATION ZR 293.938, TO ZV 315.000 AND ZV 330.250. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENER AT STATION ZR 271.000 TO ZR 335.260. PERFORMED RUDDER BALANCE FOUND WITHIN LIMITS (MOMENT= 2484.8 IN-LBS) IAW DC8 SRM 55-6-1 FIGURE 1, DC8 SRM 55-1-0 PAGE 1 AND SRM 51-1-21, DC8 SRM 51-1-9 TR NUMBER 51-142 AND SRM 51-1-9A TR NUMBER 51-141, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND DC8 SRM 51-4-6 PAGES 1 AND 3.

Part: FITTING — CRACKED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IN MIDSHIP ACCESSORY COMPARTMENT A FITTING CRACKED STATION 660.000 LONGERON 36. REMOVED CRACKED FITTING. INSTALLED NEW FITTING. IAW DC8 SRM 51-1-20D, AND SRM 51-3-1.

Part: SILL — MISREPAIRED (FUSELAGE) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT MAIN CARGO DOOR COVER SILL AT FS235 LONGERON 21 LT. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, OR CORROSION FOUND. FABRICATED REPAIR PARTS. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING AREAS. INSTALLED REPAIR PARTS IAW FORM FAA 8100-9 DATED 07-27-07, BOEING MESSAGE NUMBER 1-41443541-4 DATED 07-16-07, MESSAGE NUMBER 1-441363702-5 DATED 07-27-07, SERVICE BULLETIN, DC8-53-079 REV 2, DRAWING DOUGLAS NR SR08530027, SEMAN DRAWING NUMBER ED 4569-2, ADJUST SEMAN FORM NUMBER 242-2, DC8 SRM 51-1-21, 51-1-20, AND DC8 NDT SPM PART NUMBER 6-10-01.001.

Part: SILL — MISREPAIRED (BS 235 L21L) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT LONGERON 21 LEFT AT FS 235 MAIN CARGO DOOR LOWER AFT SILL TO AFT JAMB CORNER. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA REPAIR PARTS. INSTALLED REPAIR PART FROM STATION FS 120.000 TO STATION FS 280.000 IAW DC-8 SRM 51-3-0, DC-8 SRM 51-3-1, FORM FAA 8100-9 DATED 07-27-07, BOEING MESSAGE NUMBER 1-41443541-4 DATED 07-16-07, MESSAGE NUMBER 1-441363702-5 DATED 07-27-07, SERVICE BULLETIN DC8-53-079 REV 2, DRAWING DOUGLAS NUMBER SR08530027, SEMAN DRAWING NUMBER ED 4569-2, ROD SKETCH JCTO4203, DC8 SRM 51-1-21, 51-1-20D, DC8 NDT SPM PAR

Part: LONGERON — MISREPAIRED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT FLIGHT STATION 680 LONGERON 33 RIGHT DOUBLER, RIGHT FORWARD FUSELAGE AT WING TO BODY FAIRING ATTACH SCREWS. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACKS OR CORROSION FOUND. FABRICATED NEW SKINS EXTERNAL DOUBLER AND INTERNAL DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW FAA FORM 8110-3 DATED 07-05-07 SEMAN DRAWING ED 4572 DATED 06-27-07, DC8 SRM 51-1-20D, SRM 51-3-0, NDT SPM PART 06-10-01-001, FORM SMN 242-2,DC8 SRM 51-1-8B,DC8 SRM 51-1-11, DC8 SRM 51-1-21, AND SRM 51-3-1.

Part: FITTING — CRACKED (BS 660) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MID SHIP ACCESSORY COMPARTMENT FITTING CRACKED AT STATION 660.000 LONGERON 35LEFT. REMOVED CRACKED FITTING. INSTALLED NEW FITTING BETWEEN STATION 660.000 AND LONGERON 35LEFT IAW DC8 SRM 51-1-20D, 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 300) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR ON LEFT ELEVATOR ON LOWER SKIN AT STATION XE 39.188. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN AND FINGER DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS AND NEW FASTENERS FROM STATION XAR 0 TO STATION XE 132.000. PERFORMED BALANCE TO LEFT ELEVATOR AND FOUND TO BE WITHIN ALLOWABLE TOLERANCE LIMITS. MOMENT 1450.87 IN LBS IAW DC8 SRM 51-4-4 PAGES 1-2. DC8 SRM 55-1-0 FIGURE 1, DC8 SRM 51-1-21, DC8 SRM 55-4-1 FIGURE 1 SHEETS 1AND2 ITEM "E" AND "F", DOUGLAS DRAWING NUMBER 5654970-5, DC8 SRM 51-1-9, DC8 SRM 51-1-8B,

Part: SKIN — CORRODED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND CORROSION AT FLIGHT STATION 1510 LONGERON 27 TO 31 RIGHT, DOUBLER AFT FUSELAGE SIDE, AFT OF D-PIT DOOR. REMOVED DAMAGED AREA. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS AND NEW FATNERS IAW SRM 53-2-1 FIGURE 7 SHEET 1, FAA FORM 8110-3 NR 07284 DATED 06-27-07 SEMAN DRAWING NUMBER ED-4052 REV "1" DATED 06-23-07, DC8 SRM 51-1-21, SRM 51-1-20D, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND DC8 SRM 51-3-1.

Part: SKIN — DENTED (LT ELEVATOR) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND DENTS ON LEFT ELEVATOR UPPER SKIN BETWEEN STATION XE 161.375 AND STATION XE 176.156. REMOVED DAMAGED AREA. FABRICATED NEW SKIN, DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS AND NEW FASTENERS FROM STATION XE 132.000 TO STATION XE 246.000. PERFORMED BALANCE TO LEFT ELEVATOR FOUND WITHIN ALLOWABLE TOLERANCE LIMITS MOMENT 1450.87 IN LBS IAW DC8 SRM 55-4-1 FIGURE 1 SHEETS1, 2, ITEM "E" AND "F", DC8 SRM 57-1-0 PAGE 1 AND DC8 SRM 51-1-21, DC8 SRM 51-1-9, T/R 51-141, SRM 51-142 DATED 04-03-06 AND 04-05-06, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND DC8 SRM 51-4-4 PAGES 1

Part: STRINGER — CRACKED (WS 190 S58) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND NR 4 MAIN TANK CRACKED STRINGER AT STATION XRS 190.000 AND STRINGER 58. ACCESS THROUGH 505D DOOR. REMOVED FUEL PUMP MOUNT BRACKET. REMOVED DAMAGED AREA AT UPPER HORIZONTAL AND VERTICAL FLANGES. PERFORMED NDT INSPECTION. AFTER CUT NO CRACK, OR CORROSION AFTER NDT INSPECTION. FABRICATED ZETA REPAIR AND CHANNEL REPAIR. PERFORMED HEAT TREATMENT. CLEANED AND APPLIED POLYURETHANE TO COATING YELLOW. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS IAW FAA FORM 8100-9 DATED 07/25/07, BOEING MESSAGE NUMBER1-441074632-2 DATED 07-25-07 AND MESSAGE NUMBER 1-405802251-5 DATED 07-11-07 SKETCH JCTO4211, SEMAN DRAWING ED-4588-1, DC8 SRM 51-1-20D, DC8 NDT SPM PAR 06-

Part: FITTING — CRACKED (ZONE 200) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE FITTING HAS A CRACK LONGERON 17 LEFT STATION 1768.000. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-21, 51-1-20D, 51-3-0, SRM 51-1-8B, DC8 SRM 51-1-21, 51-1-20D, 51-3-0, AND DC8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR ON LEFT WING INBOARD AILERON LOWER SKIN FROM STATION XA 542.000 TO STATION XA 603.000. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN AND DOUBLER. BONDED BOTH PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS AND NEW FASTENERS FROM STA XW 563.000 TO STA XA 542.000. PERFORMED BALANCE TO INBOARD AILERON FOUND WITHIN ALLOWABLE TOLERANCE LIMITS MOMENT 3323.3 IN LBS IAW DC8 SRM 57-8-1 FIGURE 1 ITEM "B" AND "K", DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 51-1-9 T/R 51-141, SRM 51-142 DATED 04-03-06 AND 04-05-06, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND DC8 SRM 51-4-1.

Part: FITTING — CRACKED (BS 660) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND THE MID ACCESSORY COMPARTMENT FITTING CRACKED BETWEEN STATION 660.000 LONGERON 36 LT. REMOVED CRACKED FITTING. FABRICATED FITTING. PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED FITTING IAW DC8 SRM 51-1-20D AND 51-3-1, REPAIR SPECIFICATION NUMBER 2003-05, DOUGLAS DRAWING NUMBER 3750497, NDT SPM PART 08-00-02 TO 07, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT LOWER CARGO COMPARTMENT A CRACKED FITTING AT STATION 1180.000 LONGERON 34 RIGHT, AND LONGERON 35 RIGHT. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT FLIGHT STATION 511 LONGERON 36 DOUBLER, FORWARD LOWER FUSELAGE BELLY FORWARD OF B-PIT DOOR. REMOVED EXISTING REPAIR. FABRICATED NEW SKINS, INTERNAL FINGER DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW FAA FORM 8110 NUMBER 07284 DATED 06-27-07, SEMAN DRAWING NUMBER ED-4050 REVISION "I" DATED 06-22-07,DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, SRM 51-1-21, AND 51-3-1.

Part: VANE — MISREPAIRED (ZONE 600) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING INTERIM HAD IMPROPER REPAIR AT OUTBOARD VANE SLOT XOLDO 067 AT STATION XFS 566.250. REMOVED EXISTING REPAIR. CUT DAMAGED AREA.PERFORMED NDT INSPECTION. NO CRACK OR CORROSION AFTER CUT. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA, AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 07330 DATED 07-18-07, SEMAN DRAWING NUMBER ED 4576 DATED 06-29-07. DC8 SRM 51-1-21, 51-3-0, DC8 NDT SPM PART 06-10-01-001, SMN 242-2, DC8 SRM 51-1-8B, 51-1-20D, AND SRM 51-3-1.

Part: FITTING — CRACKED (ZONE 200) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 1760.000 TO 1766.000 LONGERON 10 RIGHT. REMOVED CRACKED FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, 51-3-1.

Part: FITTING — CRACKED (ZONE 200) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT FUSELAGE FITTING CRACKED AT LONGERON 17 RIGHT AT STATION 1768.000. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-21, 51-3-0, 51-3-1, DC8 SRM 51-1-21, 51-3-0, AND SRM 51-1-8B.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT FS 380 LONGERON 33RIGHT, RIGHT FORWARD FUSELAGE JUST AFT OF A-PIT DOOR OPENING. AVERAGE AND MAXIMUM RIVET SPACING EXCEEDED. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION AFTER CUT. FABRICATED NEW SKIN, EXTERNAL, AND INTERNAL DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW FAA FORM 8110-3 NUMBER 07330 DATED 07-18-07, DRAWING SEMAN NUMBER ED 4570 REVISION "04" DATED 06-25-07, DC8 SRM 51-1-21, SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, FORM SEMAN 242-2, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND SRM

Part: SKIN — DENTED (ZONE 300) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LT ELEVATOR LOWER SKIN SHOWS DENT AT STATION XE 55.062. REMOVED FASTENER AS NEEDED TO PERFORM REPAIR AND DAMAGED AREA. FABRICATED NEW SKIN AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS FROM STATION XAR 0 TO STATION XE 132.000. PERFORMED BALANCE TO LT ELEVATOR IAW DC8 SRM 51-4-4 PAGES 1-2. FOUND WITHIN ALLOWABLE TOLERANCE LIMITS. MOMENT 1450.87 IN LBSDC8 SRM 55-4-1 FIGURE 1 SHEETS 1 AND 2, DC8 SRM 55-1-0 FIGURE 1, DC8 SRM 51-1-21, DC8 SRM 55-4-1 FIGURE 1 SHEETS 1 AND 2 ITEM "E" AND "F", DRAWING DOUGLAS NR 5654970-5, DC8 SRM 51-1-9, DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (ZONE 300) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR HAD IMPROPER REPAIR ON LOWER SKIN AT STATION XE 84.968. REMOVED EXISTING. FABRICATED NEW SKIN AND DOUBLER. BONDED BOTH PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED REPAIR PARTS AND NEW FASTENERS FROM STATION XAR 0 TO STATION XE 132.000. PERFORMED BALANCE TO LEFT ELEVATOR FOUND WITHIN ALLOWABLE TOLERANCE LIMITS. MOMENT 1450.87 IN LBS IAW DC8 SRM 55-1-0 FIGURE 1, DC8 SRM 51-1-21,DC8 SRM 55-4-1 FIGURE 1 SHEETS 1 AND 2 ITEM "E" AND "F. DRAWING DOUGLAS NUMBER 5654970-5, DC8 SRM 51-1-9, DC8 SRM 51-1-8B, AND DC8 SRM 51-4-4 PAGES 1 AND 2.

Part: STRUCTURE — CRACKED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT FUSELAGE NOSE SECTION ACS MODIFICATION DOUBLER HEAT EXCHANGER COMPARTMENT LOWER AFT IAMB CORNER CRACKED AT FLIGHT STATION 12.000 LONGERON 27 RIGHT. REMOVED FASTENER AS NEEDED TO PERFORMED REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK OR CORROSION AFTER DAMAGED REMOVED. FABRICATED REPAIR PARTS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS AND NEW FASTENERS IAW FAA FORM 8110-3 NUMBER 07330 DATED 07-18-07, SEMAN DRAWING NUMBER ED-4575, DC8 SRM 51-1-21, DC8 NDT SPM PART 06-10-01-001, SRN 242-2, DC8 SRM 51-1-2B, SRM 51-1-8B, SRM 51-1-11, 51-1-20D, AND SRM 51-3-1.

Part: SKIN — DENTED (ZONE 500) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND DENTS LEFT WING OUTBOARD AILERON LEADING EDGE SKIN BETWEEN STATION 680.000 AND XA 674.000. REMOVED DAMAGED AREA. FABRICATED NEW SKIN AND DOUBLERS. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS FROM STATION XA 674.000 TO XW 698.000. PERFORMED BALANCE TO OTBD AILERON FOUND WITHIN ALLOWABLE TOLERANCE LIMITS. MOMENT: 3341.7 IN LBS IAW DC8 SRM 57-8-1 FIGURE 4, DC8 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 57-8-1 FIGURE 4 ITEM "H", DC8 SRM 51-1-8B,DC8 SRM 51-1-11, DC8 SRM 51-4-3.

Part: FLOORBEAM — CORRODED (BS 1520) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IN AFT CARGO COMPARTMENT FLOORBEAM UPPER FLANGE SHOWS CORROSION AT STATION 1520.000 RIGHT BOTTOM LINE 44". REMOVED DAMAGED AREA. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES INSTALLED REPAIR PART IAW DC8 SRM 51-1-21 IAW DC8 SRM 57-7-1 FIGURE 1 PAGE 2 ITEM "F", DC8 SRM 57-1-0 PAGE 1 DC8 SRM 51-1-8B, AND, DC8 51-1-11.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR ON LEFT WING OUTBOARD AILERON LOWER SKIN FROM STATION XW 546.000 TO STATION XA 630.000. REMOVED SKIN WITH NON STANDARD REPAIR. FABRICATED NEW SKIN, EXTERNAL DOUBLER, AND INTERNAL DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACE. INSTALLED REPAIR PARTS AND NEW FASTENER. AT STATION XW546.000 AND STATION XA 630.000. PERFORMED BALANCE TO OUTBOARD AILERON. FOUND WITHIN ALLOWABLE TOLERANCE LIMITS MOMENT 3341.7 IN LBS IAW DC8 SRM 57-8-1 FIGURE 4, DC8 SRM 57-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 57-8-1 FIGURE 4 ITEM "E" AND "L", DC8 SRM 51-1-9 T/R 51-141, SRM 51-142 DATED 04-03-06

Part: SKIN — DENTED (ZONE 300) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION; FOUND DENTS ON LEFT ELEVATOR UPPER SKIN AT STATION EX. 135.750. REMOVED DAMAGED AREA. FABRICATED NEW SKIN AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSON. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. APPLIED SEALANT TO FAYING SURFACE INSTALLED REPAIR PARTS FROM STATION EX. 132.000 TO STATION EX. 246.000. PERFORMED BALANCE TO LEFT ELEVATOR FOUND WITHIN ALLOWABLE TOLERANCE LIMITS MOMENT 1450.87 IN LBS IAW DC8 SRM 55-4-1 FIGURE 1 SHEETS 1 AND 2, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 55-4-1 FIGURE 1 SHEETS 1 AND 2 ITEM "E" AND "F", DC8 SRM 51-1-9, T/R 51-141, SRM 51-142 DATED 04-03-06 AND 04-05-06, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND DC8 SRM 51-4-4 PAGES 1 AN

Part: BRACKET — CRACKED (ZONE 100) · airframe 98,143 hrs · 31,809 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND NUMBER 1 ALT FUEL TANK BOOSTER PUMP SUPPORTS CRACKED AT STRINGER 59 STATION XW 456.000. REMOVED CRACKED BRACKET. INSTALLED NEW BRACKET AT STATION XW 456.000, STRINGER 59 IAW DC8 SRM 51-1-20D AND 51-3-1.

Part: WIRE — BROKEN (ZONE 700) · airframe 98,004 hrs · 31,765 cycles

DURING APPROACH FOR LANDING, THE CREW NOTICE THE RIGHT LANDING GEAR DOWN LIGHT DID NOT ILLUMINATE WHEN GEAR LEVER WAS SELECTED IN THE DOWN POSITION FOR LANDING. THE CREW ACCOMPLISH ALL NECCESSARY PROCEDURES, AND LANDED IN KLAX WITHOUT INCIDENT. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND A BROKEN WIRE AT TERMINAL STRIP S3-188 30X. MAINTENANCE REPAIRED THE BROKEN WIRE, AND PERFORMED OPERATIONAL CHECK WAS GOOD, IAW DACO MAINTENANCE MANUAL 20-50-1. AIRCRAFT RETURNED TO SERVICE.

Part: ANTI-SKID SYS — FAILED · airframe 97,334 hrs · 31,425 cycles

DURING TAKEOFF, AFTER GEAR RETRACTION THE ANTISKID INOP LIGHT ILLUMINATED. THE CREW RECYCLED THE GEAR, RECYCLED THE ANTISKID SWITCH, RESET THE CIRCUIT BREAKERS, AND CYCLED THE PARKING BRAKE LEVER, ALL ACTIONS DID NOT EXTINGUISH THE ANTISKID INOP LIGHT. DUE TO THE RUNWAY BEING WET DUE TO RAIN, THE CREW ELECTED TO RETURN TO DEPARTURE WHERE THEY LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE ANTI-SKID LAMP CONTROL BOX. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: LINK ROD — BROKEN (MLG DOOR) · airframe 95,380 hrs · 30,997 cycles

3 HOURS INTO FLIGHT, A POP WAS HEARD, FOLLOWED BY AIR NOISE AND VIBRATION FROM NOSE GEAR AREA. CREW RETURNED AIRCRAFT TO DEPARTURE AIRPORT AND LANDED WITH OUT INCIDENT. INSPECTION IS ON GOING. WHEN INFORMATION IS AVAILABLE IT WILL BE PROVIDED. UPON INSPECTION FOUND LT AND RT FORWARD DOOR RODS INTERNAL LATCH BROKEN. REMOVED AND REPLACED FORWARD DOOR RODS AND THE OPERATIONAL CHECK WAS GOOD IAW ALL APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FRAME — CRACKED (BS 55) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C-CHECK INSPECTION, FWD ACCY CMPT- FRAME CRACKED, STA 55, L-24R. PERFORMED MAJOR REPAIR. REMOVED FASTENERS. TRIMMED OUT DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK CORROSION FOUND AROUND TRIMMED AREA. FABRICATED NEW SEGMENT FRAME (EXTRUSION P/N S2641520) 7075.0.0.071. (02EA) ANGLES (AL 7075.0.0.071) IAW DC8 SRM 53-2-0 FIG 2 (SHEET 5) TR 53-125, DC8 SRM 53-2-0 FIG 2 (SHEET 6), DC8 SRM 53-2-0 FIG 2 (SHEET 7, 8) TR 53-110, DC8 SRM 51-1-4 PAGE 1. PERFORMED HEAT TREATMENT FROM 7075.0 TO 7075 T6 (FRAME SEGMENT, ANGLES) IAW DC8 SRM 51-1-1 PAGES 1, 13, 17. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS.

Part: FRAME — CORRODED (BS 80) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C-CHECK INSPECTION, FWD CARGO CMPT FRAME CORRODED, STA 80.000, L-26L. PERFORMED MAJOR REPAIR. REMOVED FASTENERS. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FRAME SEGMENT (CORRODED). PERFORMED NDT INSPECTION. NO CRACK, CORROSION FOUND AROUND TRIMMED AREA. FABRICATED NEW SEGMENT FRAME. ANGLE SPLICE. PERFORMED HEAT TREATMENT TO FRAME SEGMENT, ANGLE & SPLICE. PERFORMED NDT INSPECTION REPORT TO NEW FRAME SEGMENT. INSTALLED REPAIR PARTS.

Part: FITTING — CRACKED (BS 1690) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C CHECK INSPECTION, AFT ACCY CMPT BATHTUB FITTING CRACKED 1, STA 1690.000, L-28R. REMOVED CRACKED FITTING IAW DC8 SRM 51-1-20D PG 21. CLEANED, TREATED AND PRIMED AREA IAW DC8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D PG 9 AND DC8 SRM 51-3-1 (TORQUE).

Part: SKIN — CRACKED (RT WING) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C-CHECK INSPECTION, RIGHT WING UPPER SKIN CRACKED 1, STA XW 74 STR 9. PERFORMED MAJOR REPAIR. REMOVED FASTENERS IAW DC-8 SRM 51-1-20D PAGE 21. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM PART 06-10-01-001. FABRICATED REPAIR DOUBLER & FILLER PLUG. MADE TAPE DOUBLER. OVER 4 INCHES LENGTH TYPICAL CHANFER BOTH ENDS. INSTALLED REPAIR PARTS IAW DC-8 SRM 57-2-1 FIG 10 , DC-8 SRM 51-1-20D PAGE 9 , TORQUED IAW DC-8 SRM 51-3-1.

Part: BEAM — CORRODED (BS 50) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C-CHECK INSPECTION, FWD ACCY CMPT BEAM CORRODED AT STA 50, RBL 4. PERFORMED MAJOR REPAIR. REMOVED FASTENERS. REMOVED CORROSION, FOUND OUT OF LIMITS. REMOVED CORRODED AREA. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM, PART 06-10-01-001. NO CRACK CORROSION FOUND. FABRICATED REPAIR ANGLE, FILLER (EXTRUSION PN S132S214/7075T6511) IAW DC8 SRM 51-2-1 FIG 1 (SHEET 7, 12), DC8 SRM 53-7-3 FIG 6 SHEET 1, ITEM S DC8 SRM 51-2-0 FIG 50 (SHEET 73). CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW DC-8 SRM 51-1-20D PG 9, DC8 SRM 51-1-21 PAGE 1. TORQUED IAW DC8 SRM 51-3-1, DC8 SRM 51-2-1.

Part: ACCESS DOOR — CRACKED (RT WING) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C-CHECK INSPECTION, RIGHT WING SLOT DOOR CRACKED 1, STA XILD 7095 XS 250.089. REMOVED AND REPLACED INBOARD SLOT UPPER DOOR (NEW CONDITION) ON RIGHT WING IAW DC-8 MM 27-80-02 PAGES 201-204.

Part: SKIN — DAMAGED (BS 255) · airframe 94,807 hrs · 30,875 cycles

DURING C-CHECK INSPECT, RT FWD FUSELAGE JUST FWD OF A-PIT DOOR OPENING DOUBLER THICKNESS RATIO EXCEEDED MAX ALLOWED. DOUBLER THICKNESS 0.135", SKIN 0.071". REWORK REPAIR TO BRING INTO SRM LIMITATIONS WITH LOCK FASTENERS IN LONGERONS, STA FS 255 L-36. PERFORMED REPAIR IAW FAA 8110.3 05367 DATED 08-19-05, SEMAN DWG ED 4046 DATED 08-15-05 AND EO SEMAN NR 20051123 DATED 08-19-05. REMOVED EXISTING REPAIR DOUBLER IAW DC8 SRM 51-1-20D PAGE 21, DC8 SRM 51-1-21 PG 1. REMOVED DAMAGED AREA IAW SEMAN DWG ED 4046. PERFORMED NDT INSPECT IAW DC-8 NDT SPM, PART 06-10-01-001. FABRICATED REPAIR DOUBLER, REPAIR TRIPLER, FILLER & FILLER IAW SEMAN DWG ED 4046, DC8 SRM. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4046, DC-8 SRM.

Part: SKIN — OUT OF LIMITS (ZONE- 800) · airframe 94,807 hrs · 30,875 cycles

DURING C-CHECK INSPECT, DOUBLER BEHIND D-PIT DOOR OPENING ON SKIN SPLICE, SIDES 2 AND 3 EXCEED MAX RIVET SPACING, ALUMINUM & JO-BOLTS IN LONGERONS. ADD ADDITIONAL RIVETS TO BRING UNDER MAX SPACING OF 1.400, STA FS 1520 L-29R. PERFORMED REPAIR IAW FAA FORM 8110-3 NR 05366, SEMAN DWG ED-4052 DATED 08-11-05 AND EO SEMAN NR 20051130 DATED 8-19-05. REMOVED EXISTING REPAIR DOUBLER IAW DC8 SRM 51-1-21 PG 1 AND DC8 SRM 51-1-20D PG 21. PERFORMED DETAILED VISUAL INSPECT. NO CRACK OR CORROSION FOUND. FABRICATED REPAIR DOUBLER INTERNAL FINGER DOUBLERS IAW SEMAN DWG ED-4050 AND DC8 SRM 51-1-4 PG 1. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4052, DC8 SRM 51-1-21 PG 1, DC8 SRM 51-1-20D PG 9, AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (BS 1260-1280) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C-CHECK INSPECTION, AFT CARGO COMPT SPLICE FITTING CRACKED 6, STA 1260.000 STA 1280.000 L-34L. REMOVED CRACKED SPLICE FITTING IAW DC8 SRM 51.1.20D PAGE 21. CLEANED, TRETAED AREA IAW DC8 SRM 51-1-8B. INSTALLED NEW SPLICE FITTING IAW DC8 SRM 51-1-20D PAGE 9 DC8 SRM 51-3-1.

Part: SKIN — DAMAGED (BS 195) · airframe 94,807 hrs · 30,875 cycles

DURING C-CHECK INSPECT, RT FWD FUSELAGE BELOW FWD STATIC PORT, DOUBLER THICKNESS RATIO EXCEEDED MAX ALLOWED, ALUMINUM RIVETS USED IN LONGERONS. REWORK REPAIR IAW TO BRING INTO CONFORMANCE, STA FS 195, L-35R. PERFORMED MAJOR REPAIR IAW FAA 8110-3 NR 05367 DATED 08-19-05, SEMAN DWG ED 4045 DATED 08-12-05 AND EO SEMAN NR 20051122 DATED 08-19-05. REMOVED EXISTING REPAIR DOUBLER IAW DC8 SRM 51-1-21 PG 1, DC8 SRM 51-1-20D PAGE 21. TRIMMED OUT DAMAGED AREA IAW SEMAN DWG ED 4045. PERFORMED NDT INSPECT IAW DC-8 NDT SPM, PART 06-10-01-001. FAB`D REPAIR DOUBLER, INTERNAL FINGER DOUBLER & FILLER IAW SEMAN DWG ED 4045, DC8 SRM 51-1-4 PAGE 1. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4045, DC-8 SRM 51-1-20D PG 9, DC8

Part: SKIN — CORRODED (BS 80) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C CHECK INSPECTION, FWD CARGO COMPT INTERNAL SKIN CORRODED, STA 80.000, L-31R. DURING ROUTINE C CHECK INSPECTION, FWD CARGO COMPT INTERNAL SKIN CORRODED, STA 80.000 , L-31R. REMOVED SKIN IAW DC-8 SRM 51-1-21 PAGE 1. REMOVED LEVEL I CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18. MEASURED: BLEND OUT 0,002. MATERIAL MUCKINESS 0,063" REMAINING MATERIAL 0,061". FOUND WITHIN ALLOWABLE LIMITS IAW DC-8 SRM 53-2-0 FIG 1F. CLEANED, TREATED AND PRIMED IAW DC-8 SRM 51-1-8B.

Part: SKIN — CRACKED (BS 10) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C CHECK INSPECTION, EXTERNAL FUSELAGE AFT HEAT EXCHANGER RT LWR CORNER CRACKED 1, STA 10.000, L-27L. PERFORMED MAJOR REPAIR IAW FAA 8110.3 NR 05367 DATED 08-19-05, SEMAN DWG ED 4055 DATED 08-14-03 AND EO SEMAN NR 20051140 DATED 08-19-05. REMOVED FASTENERS IAW DC8 SRM 51-1-21 PAGE 1, DC8 SRM 51-1-20D PAGE 21. REMOVED DAMAGED AREA IAW SEMAN DWG ED 4055. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM, PART 06-10-01-001. FAB`D REPAIR DOUBLER (AL 2024T3 0.050) + REPAIR TRIPLER (AL 2024T3 0.063) + FILLER (AL 2024T3 0.100) IAW SEMAN DWG ED 4055, DC8 SRM 51-1-4 PAGE 1 (FORMING). CLEANED, TREATED AND PRIMED REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9.

Part: FITTING — CRACKED (BS 300) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C CHECK INSPECTION, FWD CARGO COMPT FITTING CRACKED .500 INCHES, STA 300.000 , L-32R L-33R. REMOVED CRACKED FITTING IAW DC-8 SRM 51-1-21 PAGE 1. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING WITH FASTENERS (HILOKS) IAW DC-8 SRM 51-1-20D PAGE 9. TORQUED IAW DC-8 SRM 51-3-1.

Part: VANE — DAMAGED (LT WING) · airframe 94,807 hrs · 30,875 cycles

DURING C-CHECK INSPECT, LT WING, VANE SLOT L/E HAS INTERIM REPAIR, XOLDI 6.225. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05368 DATED 08-19-05, DWG SEMAN ED-4054 DATED 08-15-05 AND EO SEMAN NR 20051136 DATED 08-19-05. REMOVED NON STANDARD REPAIR IAW DC8 SRM 51-1-21 PG 1 AND DC8 SRM 51-1-20D PG 21. REMOVED DAMAGED AREA IAW DWG ED-4054. PERFORMED NDT INSPECTION DC8 NDT SPM PART 06-10-01-001. FABRICATED EXTERNAL REPAIR DOUBLER, FILLER IAW SEMAN DWG ED-4054 AND DC8 SRM 51-1-4 PG 1. INSTALLED REPAIR PARTS IAW SEMAN DWG ED-4054, DC8 SRM 51-1-21 PG 1 AND DC8 SRM 51-3-0 PG 1, DC8 SRM 51-1-20D PG 9, AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (BS 340) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C CHECK INSPECTION, FWD CARGO COMPT FITTING CRACKED .5 INCHES STA 340.000 , L-32R L-33R. REMOVED AND REPLACED CRACKED FITTING ON FWD CARGO CMPT, STA 340.000, L32R-L33R IAW DC8 SRM 51.1.20D PAGES 9, 21. TORQUED IAW DC8 SRM 51-3-1.

Part: SKIN — DELAMINATED (LT WING) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING.- T/E UPPER PANEL EXTERNAL SKIN DELAMINATED, XW 0.000 XW 47.000. REMOVED DELAMINATED PANEL AND REPLACED ON LH WING T/E UPPER PANEL EXTERNAL SKIN, XW 0.000 – XW 47.000 IAW DC8 SRM 51-3-0

Part: SKIN — CRACKED (LT WING) · airframe 94,807 hrs · 30,875 cycles

DURING C CHECK INSPECTION, LT WING, UPPER SKIN HAS 03 CRACKS, XRS 74.000 S-9 S-10. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-2-1 FIG 17, EO SEMAN NR 20051135 DATE 08-10-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-20D PAGE 21. REMOVED DAMAGED AREA IAW DC-8 SR, 57-2-1 FIG 17. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM, PART 06-10-01-001. FAB`D REPAIR DOUBLER (7075T6 AL 0.160) + (03EA) FILLERS PLUG (AL 7075T6 0.175) IAW DC8 SRM 57-2-1FIG 17, DC8 SRM 57-3-3 FIG 12 ITEM A. MAKE TAPER DOUBLER FROM 0.160 TO 0.080 IAW DC8 SRM 51-10-0 FIG 1 (SHEET 20). CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW DC8 SRM 57

Part: SKIN — DELAMINATED (NR 3 FLAP VANE) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING, NR 3 VANE FLAP LWR. SKIN DELAMINATED. REMOVED AND REPLACED NR 3 FLAP VANE ON RT WING (REPAIRED CONDITION) IAW DC8 MM 27-51-14 PAGES 201-202.

Part: SKIN — DELAMINATED (ZONE 500) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING NR 4 VANE FLAP LWR SKIN DELAMINATED. REMOVED AND REPLACED NR 4 FLAP VANE (LT WING) IN REPAIRED CONDITION IAW DC8 MM 27-51-14 PAGE 201-202.

Part: ACCESS DOOR — CRACKED (LT WING) · airframe 94,807 hrs · 30,875 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING, SLOT ACCESS DOOR CRACKED 1, XILD 7095 XS 250.089. REMOVED AND REPLACED INBD SLOT UPPER DOOR ON LT WING IAW DC-8 MM 27-80-02 PAGES 201-204.

Part: ENGINE — MALFUNCTIONED (NR 4) · airframe 93,687 hrs · 30,400 cycles

DURING TAKEOFF, NR 4 ENGINE OIL PRESSURE FLUXING 45-35PSI WITH OIL QUANTITY DROPPING SHUT DOWN ENGINE WINDMILLING OIL PRESSURE OPSI AT 1302 (LANDING WEIGHT 270.0) AN INSPECTION IS ON GOING. AS SOON AS INFORMATION BECOME AVAILABLE IT WILL BE PROVIDED.

Part: DOOR — OPEN (NLG) · airframe 92,883 hrs · 30,265 cycles

AFTER TAKE OFF WITH THE GEAR UP THE CREW HEARD EXCESSIVE NOISE COMING FROM THE NOSE GEAR AREA. CREW CYCLED GEAR AND SOUND CONTINUED UPON INVESTIGATING NOSE GEAR AREA FOUND LT FWD GEAR DOOR OPEN, RESET DOOR IAW DC-8. OPS CHECK NORMAL NO DAMAGE NOTED.

Part: PANEL — CORRODED (RT WING) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION RT WING INBD L/E SLANT PANEL UPPER SKIN SURFACE CORRODED, STA XCW 69.000 AND XFS 207.000. REPAIR ACCOMPLISHED BY PERFORMING MAJOR REPAIR IAW DC8 SRM 57-1-0 PG 1, FAX TIN-N 043, BOEING MESSAGE DATE 03/31/2004. REMOVED CORROSION IAW DC8 SRM 51-1-I PG 17-18, FOUND OUT OF LIMITS IAW DC8 SRM 57-2-1 PG 11. REMOVED SLANT PANEL IAW DC8 SRM 51-1-21 PG 1, DC8 SRM 51-3-0 PG 1. TRIMMED OUT HOLE LOCATIONS ON NEW SLANT PANEL, FABRICATED FILLER, DOUBLER IAW BOEING MESSAGE 03-31-04, CLEANED, TREATED AND PRIMED AREA, FILLER, DOUBLER IAW DC8 SRM 51-1-8B. INSTALLED FILLER, DOUBLER ON NEW SLANT PANEL IAW DC8 SRM 51-1-21 PG 1, DC8 SRM 51-1 20D PG 9, DC8 SRM 51-3-0 PG 1, DC8 SRM 51-1-21 PG 1.

Part: SKIN — CORRODED (RT WING LE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION FOUND RT WING OB L/E OUTER SECTION UPPER SKIN SURFACE CORRODED, STA. XW 761.000. REPAIRS WERE ACCOMPLISHED BY REMOVING FASTENERS IAW SRM 51-1-20D PG. 21, SRM 51-3-0 PG. 1, SRM 51-1-21 PG. 1, REMOVED CORROSION IAW SRM 51-1-8 PG. 17-18 FOUND OUT OF LIMITS IAW SRM 57-2-1 PG. 11 REMOVED DAMAGED SECTION IAW DWG: V22-R15, PERFORMED NDI INSP. IAW DC8 NDI SPM PART 6-10-01-001 FABRICATED FILLER + DOUBLER IAW DWG: V22-R15 CLEANED, TREATED AND PRIMED AREA + INNER FACE OF FILLER + DOUBLER IAW DC8 SRM , 51-1-8B APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PG. 9, INSTALLER FILLER, DOUBLER & NEW FASTENERS IAW DWG: V22-R15 SRM 51-1-21 PG. 1, DC8 SRM 51-120D PG. 9 SRM 51-3-0.

Part: SKIN — CORRODED (LT WING) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION LT OB WING L/E IB SECTION LWR SKIN SURFACE CORRODED, STA XFS. 710.000. REPAIRS WERE ACCOMPLISHED IAW APPROVAL DOCUMENT, REMOVED FASTENERS, REMOVED CORROSION FOUND OUT OF LIMITS IAW SRM 57-2-1 PAGE 11 REMOVED DAMAGED AREA, PERFORMED NDT INSPECTION IAW NOT SPM PART 6-10-01-001, CLEANED TREATED AND PRIMED AREA IAW SRM 51-1-8B, FABRICATED AND REPAIR DOUBLER AND TWO FILLERS IAW DWG V22-RO4, CLEANED TREATED AND PRIMED THE REPAIR DOUBLER INTERIOR SURFACE AND FAYING SURFACES IAW SRM 51-1-11 PAGE 4, INSTALLED DOUBLER + FILLERS USING NEW FASTENERS IAW DWG V22-R04, SRM 51-1-21 PAGE 1, 51-1-20D PAGE 9 AND 51-3-0 PAGE. 1.

Part: SKIN — CORRODED (RT WING) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION FOUND RT WING OB L/E INNER SECTION UPPER SKIN SURFACE CORRODED, STA XW 485.000. REPAIRS WERE ACCOMPLISHED IAW APPROVAL DOCUMENT DWG V22-R02, REMOVED FASTENERS IAW SRM 51-1-21 PAGE 1, 51-1-20D PAGE 21, 51-3-0 PAGE 1, REMOVED CORROSION IAW DC8 SRM 51-1-8 PAGE 17-18, FOUND OUT OF LIMITS IAW SRM 57-2-1 PAGE 11 TRIMMED OUT THE DAMAGED AREA IAW DWG V22-RO2, PERFORMED NOT INSPECTION IAW DC8 NOT SPM PART 6-10-01.001, CLEANED TREATED AND PRIMED AREA IAW SRM 51-1-8B, FABRICATED A REPAIR DOUBLER AND A FILLER.

Part: FLANGE — CORRODED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

C-CHECK INSP MAIN CARGO COMP WEB, BEAM LOWER FLANGE CORRODED STA 960 RBL 58 - 64. REMOVED FASTENERS, CORROSION FOUND OUT OF LIMITS. REMOVED DAMAGED CORROSION AREA & SECTION OF FLANGE. FABBED FILLER & DOUBLER. PERFORMED NDT INSP, FABBED EXTERNAL REPAIR DOUBER, 2 INTERNAL REPAIR DOUBLER, FILLER, 03 SHIMS, OTHER SHIM FROM AN INTERNAL DOUBLER & 2 Z-REINFORCEMENTS. CLEANED, TREATED AND PRIMED REPAIR PARTS EXCEPT 2 Z-REINFORCEMENT STEEL, APPLIED PRC SEALANT ON FAYING SURFACES, INSTALLED FILLER, DOUBLER FOR FLANGE AREA. INSTALLED EXTERNAL, INTERNAL REPAIR DOUBLERS, FILLER, SHIMS & 2 Z-REINFORCEMENTS. REPAIRED RT FUSELAGE FITTING P/N 3647117 AT PANEL PRIOR ACCOMPLISHING WEB & FLOORBEAM REPAIR.

Part: SKIN — CORRODED (LT WING LE) · airframe 9,190 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION FOUND LT WING OB L/E OUTER SECTION LWR SKIN SURFACE CORODED, STA. XFS 710.000. REPAIRS WERE ACCOMPLISHED BY REMOVING FASTERNERS IAW DC8 SRM 51-120D PG. 21, SRM 51-1-21 PG. 1, SRM 51-3-0 PG.1, REMOVED CORROSION IAW SRM 51-1-8 PG. 17-18, FOUND OUT OF LIMITS IAW SRM 57-2-1 PG. 11, REMOVED DAMAGED SECTION IAW DWG: V22-R05, PERFOMRED NDT INSP. IAW NDT SPM PART 6-10-01-001 FABRICATED FILLER + DOUBLER IAW DWG: V22-RO5 CLEANED, TREATED AND PRIMED AREA + INNER FACE OF FILLER + DOUBLER IAW SRM 51-1-8B APPLIED (PRC) SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PG. 9 INSTALLED FILLER + DOUBLER + NEW FASTNERS IAW DWG: V22 RDS, SRM 51-1-21 PG. 1, SRM 51-1-20D PG. 9, SRM 51-3-0 PG. 1.

Part: JOINT — CRACKED (RT WING TE FLAP) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION RT WING INBD JOINT FLAP BRACE CRACKED. REPAIR IS ACCOMPLISHED BY PERFORMING MAJOR REPAIR IAW DC8 SRM 57-1-0 PAGE 1. REMOVED CRACKED JOINT FLAP BRACE IAW DC9 SRM 51-1-21 PAGE 1. CLEANED, TREATED, PRIMED AREA IAW DC8 SRM 51-1-80 PAGE 1. INSTALLED NEW BRACE IAW DC8 SRM 51-1-21.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION, LT FUSELAGE AFT PRESSURE BULKHEAD STRUCTURE HAS CRACK. REPAIR ARE ACCOMPLISHED BY PERFORMING MAJOR REPAIRS IAW SRM 53-2-5 FIG 9, AT STA. XW 130.00, IAW SRM 51-1-20D PAGE 21 PERFORMED CRACK END, SRM 53-2-5 PAGE 15-16 AND PERFORMED HEAT TREATMENT 53-2-5 FIG. 9 SRM 51-1-1 PAGE 1, 13, 17, CLEANED, TREATED, AND PRIMED AREA AND DOUBLER, INSTALLED DOUBLER IAW SRM 51-1-8B, IAW SRM 53-2-5 PAGES 15, 16 SRM 51-2-20.

Part: SKIN — WORN (RT WING TE FLAP) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION RT OUTBD FLAP UPPER PLATING DOUBLER WORN OUT OF LIMITS (STA 226.000-333.000) MAJOR REPAIRS. REPAIR IS ACCOMPLISHED BY PERFORMING MAJOR REPAIRS IAW DC8 SRM 57-1-0 PG 1, DC8 SRM 57-7-1 FIG 4. REMOVED WORN PLATING IAW DC8 SRM 51-1-21 PG 1, FABRICATED NEW PAINTING IAW DC8 SRM 57-1-0 PG 1, DC8 SRM 57-7-1 FIG 4, CLEANED TREATED AND PRIMED PLATING INNER SIDE & INSTALLED NEW PLATING IAW DC8 SRM 51-1-21 PG 1, DC8 SRM 51-1-8B.

Part: FRAME — CRACKED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION MAIN CARGO COMPT FRAME CRACKED 3 INCHES STAT. 1580.000, L-21R, MAJOR REPAIR. REPAIRS ARE ACCOMPLISHED BY PERFORMING IAW DC8 SRM 53-2-0 PAGE2 OF 2 FIG 2, REMOVED DAMAGED AREA IAW SRM 53-2-0 PAGES 2 OF 2 FIG. 2, FABRICATED FRAME IAW SRM 53-2-0 PAGES 2 OF 2 FIG. 2, PERFORMED HEAT TREATMENT IAW SRM 51-1-1, PAGES 1, 13, 17 CLEANED, TREATED AND PRIMED AREA + FRAME + SPLICES IAW SRM 51-1-8B INSTALLED FRAME + SPLICES IAW SRM 51-1-20D.

Part: SKIN PANEL — DAMAGED (RT WING) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION RT WING INBD VANE SLOT UPPER SKIN HAS ELONGATED HOLES AT STA XS 247.000 (MAJOR REPAIR). REPAIR IS ACCOMPLISHED PERFORMED MAJOR REPAIR IAW DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-3-3 FIG 10 PAGE 22. REMOVED DETERIORATED SKIN IAW DC8 SRM 51-3-0 PAGE 1, SRM 51-1-21 PAGE 1. FABRICATED NEW SKIN IAW DC8 SRM 57-3-3 PAGE 22 FIG 10, CLEANED TREATED AND PRIMED AREA & SKIN INTERIOR IAW DC8 SRM 51-1-83. INSTALLED NEW SKIN IAW DC8 SRM 51-3-0, SRM 51-1-21 PAGE 1.

Part: SKIN — CRACKED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND FWD FUSELAGE EXTERNAL SKIN HAS IMPROPER REPAIR IAW DWG V22-R19. REPAIR ACCOMPLISHED. TEMPORARY REPAIR WAS REMOVED. FABRICATION AND INSTALLATION OF FINGER DOUBLER FILLER AND DOUBLER IAW STRUCTURAL REPAIR MANUAL. CLEANED, TREATED AND PRIMED. PRC SEALANT WAS APPLIED TO FAYING SURFACES. NEW FASTNERS FOR FINGER DOUBLER, FILLER, AD DOULBER WERE ISNTALLED IAW DWG V22-R19, SRM 51-1-21 PG 1, SRM 51-1-20DPG 9.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION RT WING CENTER SECTION UPPER FLOORBEAM FLANGE CORRODED, STA. 980.000 RBL 10 INCHES. REPAIR ARE ACCOMPLISHED, PERFORMED MAJOR REPAIR IAW SRM 51-2-1 FIG. 1, REMOVED CORROSION FROM UPPER FLOORBEAM FLANGE, STA 980.000 RBL. 10 INCHES IAW DC8 SRM 51-1-8 PG. 18, FOUND OUT OF LIMITS IAW SRM 53-2-0 PG. 2M, CUT OUT DAMAGED SECTION, FABRICATED FILLER & DOUBLER IAW SRM 51-2-1 FIG. 1, PERFORMED NDT INSP. IAW NDT SPM PART 08-00-02/07 CLEANED, TREATED AND PRIMED AREA, FILLER, DOUBLER IAW DC8 SRM 51-1-8B INSTALLED FILLER, DOUBLER IAW DC8 SRM 51-2-1 FIG. 7, DC8 SRM 51-1-20D PG. 9, DC8 SRM 51-1-21 PG.7, DC8 SRM 51-3-0 PG. 1.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE INSPECTION RT OUTBOARD FLAP HAS INTERIM REPAIR ON UPPER PANEL (STA SF 415.000-440.000) MAJOR REPAIR. REPAIRS ARE ACCOMPLISHED BY PERFORMING MAJOR REPAIR IAW DC8 SRM 57-1-0 PG 1, DC8 SRM 57-7-4 FIG 4. REMOVED UPPER SKIN WITH INTERIM REPAIR ON IT IAW DC8 SRM 51-1-21 PG 1, FABRICATED NEW SKIN IAW DC8 SRM 57-7-1 FIG 4. CLEANED, TREATED AND PRIMED AREA & INNER FACE OF NEW SKIN IAW DC8 SRM 51-1-8B. INSTALLED NEW SKIN IAW DC8 SRM 51-1-21 PG 1.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION RT WING CTR FLOORBEAM FLANGE, STA 798.000 LBL 10 IAW DC8 SRM 51-1-8 PG 17-18, IAW DC8 SRM 53-2-0 PG 2M. REMOVED DAMAGED SECTION AND FABRICATED (7075-T651 0.250) IAW DC8 SRM 51-1-21 FIG 1. PERFORMED NDT INSP, CLEANED, TREATED AND PRIMED AREA & FILLER & DOUBLER, INSTALLED FILLER & DOUBLER IAW DC8 SRM 51-2-1 FIG 1, DC8 SRM 51-1-21 PG 1, DC8 SRM 51-3-D PG 1.

Part: HINGE FITTING — CRACKED (RT WING TE FLAP) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION RT WING INBD FLAP HINGE SUPPORT FITTING CRACKED 4 INCHES STA XW 97-906. REPAIRS ARE ACCOMPLISHED BY PERFORMING MAJOR REAIR IAW DC8 SRM 57-1-0 PAGE 1. REMOVED CRACKED FITTING IAW DC8 SRM 51-3-0 PAGE 1. CLEANED, TREATED AND PRIMED AREA IAW DC8 SRM 51-1-8B, INSTALLED NEW FITTING IAW DC8 SRM 51-3-0 PAGE 1 AND DC8 SRM 51-1-21 PAGE 1.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION RT WING OUTBOARD FLAP UPPER FORWARD PLATING INTERIM REPAIR BETWEEN STA XF 415.000 TO XF 440.00. REPAIR IS ACCOMPLISHED BY REPLACEMENT WAS ACCOMPLISHED IN ACCORDANCE WITH DC8 SRM CHAPTERS 57-1-0 PG 1, 57-7-1 FIG 4 TR 57-94, 51-1-21 AND N/R 3024.

Part: SKIN — CORRODED (ZONE 600) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE INSPECTION RIGHT WING CTR L/E UPPER SKIN SURFACE CORRODED (STA XFS 341.500-416.500) MAJOR REPAIR. REMOVED FASTENERS IAW DC8 SRM 51-1-21 PG 1, DC8 SRM 51-1-20D, REMOVED CORROSION FROM UPPER SKIN SURFACE OF LT WING CIR L/E IAW DC8 SRM 51-1-8 PG 17-18, FOUND OUT OF LIMITS IAW DC8 SRM 51-2-1 PG 11-12, REMOVED DAMAGED SKIN SEGMENT IAW DC8 SRM 57-2-1 PG 44, FABRICATED DOUBLER IAW DC8 SRM 57-2-1 PG 44, CLEANED, TREATED AND PRIMED AREA AND DOUBLER INNER SIDE IAW DC8 SRM 51-1-21 PG 1, DC8 SRM 51-1-20D PG 9.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C CHECK INSPECTION FOUND RT HORIZONTAL STAB L/E SURFACE SHOWS CORROSION AND A 1 INCH CRACK. REPAIR ACCOMPLISHED. PERFORMED MAJOR REPAIR IAW DWG V22-R18. REMOVED FASTENERS , REMOVED CORROSION AND FOUND OUT OF LIMITS. REMOVED THE DAMAGED AREA IAW DWG V22-R18, PERFORMED NDT INSECTION, CLEANED, TREATED AND PRIMED AREA. FABRICATED A REPAIR DOUBLER AND TWO FILLERS. CLEANED TREATED AND PRIMED THE REPAIR DOUBLER INTERIOR SURFACE AND FILLERS IAW DC8 SRM 51-1-8B. APPLIED PRC SEALANT ON FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED THE REPAIR DOUBLER AND FILLERS WITH THE NEW FASTENERS IAW DWG V22-R18 AND DC8 SRM 51-1-20D,51-1-21 AND 51-3-0 PG 1.

Part: SKIN — DAMAGED (ZONE 600) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION FOUND RT WING INBD FLAP UPPER PANEL HAS INTERM REPAIR, STA XW 28.000-XW 86.000 MAJOR REPAIR. REPAIRS ARE ACCOMPLISHED BY PERFORMING MAJOR REPAIR IAW DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIG 2 PAGE 2. REMOVED INTERM REPAIR IAW DC8 SRM 51-1-21 PAGE 1. CLEANED, TREATED AND PRIMED AREA IAW DC8 SRM 51-1-8B, FABRICATED NEW SKIN (202473 0.040) IAW DC8 SRM 57-7-1 PAGE 2, FIG 1. CLEANED, TREATED AND PRIMED NEW SKIN INTERIOR IAW DC8 SRM 51-1-8B, APPLIED PRC SEALANT OF FAYING SURFACE IAW DC8 SRM 51-1-15 PAGE 1. INSTALLED NEW SKIN WITH FASTENERS IAW DC8 SRM 51-1-21 PAGE 1.

Part: SKIN — CORRODED (ZONE 600) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C-CHECK CORROSION WAS DETECTED ON RT WING OUTBOARD LEADING EDGE INNER SECTION UPPER SKIN SURFACE. MAINTENANCE REMOVED DAMAGED SKIN, FABRICATED DOUBLER, CLEANED, TREATED AND PRIMED AREA AT INNER FACE OF DOUBLER. MAINTENANCE THEN INSTALLED DOUBLER AND NEW FASTENERS IN ACCORDANCE WITH STRUCTURAL REPAIR MANUAL TEMPORARY REPAIR REVISION 57-102.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION AFT PASSENGER DOOR RT UPPER JAMB CORNER WITH .5 INCH CRACK IN IT, STA 1660.000. REPAIRS ARE ACCOMPLISHED BY PERFORMING MAJOR REPAIR IAW DC8 SRM 53-2-0 FIG 18, FABRICATED FILLER, DOUBLER, TRIPLER IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11 PG 11. INSTALLED FILLER, DOUBLER & TRIPLER WITH NEW FASTENERS IAW DC8 SRM 53-2-0 FIG 18, DC8 SRM 51-1-20D PG 9.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION FOUND TEMPORARY REPAIR OF FUSELAGE EXTERIOR SKIN STATION 1459.000-1512.000 L-31L TO L-34L. REPAIR ACCOMPLISHED, REMOVED DAMAGED AREA IAW DC8 SRM 53-2-1 PG 107-108 FIG 7. FABRICATED FILLER & DOUBLER & FINGER DOUBLER IAW DC8 SRM 53-2-1 PG 99-100 FIG 7. CLEANED, TREATED AND PRIMED AREA PLUS FILLER, DOUBLER AND FINGER DOUBLER IAW DC8 SRM 51-1-8B. INSTALLED FILLER, DOUBLER AND FINGER DOUBLER IAW DC8 SRM 53-2-1 PG 107-108 FIG 7, SRM 51-1-20D PG 9, AND DC8 SRM 51-1-21.

Part: SKIN — WORN (T/E FLAP) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C-CHECK INSPECTION RIGHT INBOARD FLAP UPPER PANEL DOUBLER HAS WEAR OUT OF LIMITS STA XW.104.000-110.000 MAJOR REPAIR. MAINTENANCE PERFORMED MAJOR REPAIR IN ACCORDANCE WITH DC8 STRUCTURAL REPAIR MANUAL 51-1-21A PG 1-4. FABRICATED NEW PLATING (2024T30.040") IN ACCORDANCE WITH 57-7-1 PG 2. CLEANED, TREATED AND PRIMED AREA AND INNER FACE OF PLATING IN ACCORDANCE WITH DC8 STRUCTURAL REPAIR MANUAL 57-7-1 PG 2, DC8 STRUCTURAL REPAIR MANUAL 51-1-21A PG 1-4, DC8 STRUCTURAL REPAIR MANUAL 51-3-0 PG 1.

Part: FITTING — CORRODED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C CHECK FOUND A-CARGO DOOR FITTING CORRODED AT STA 300.00 L34R TO L33R. REPAIR ACCOMPLISHED. REMOVED CORROSION ON CARGO DOOR FITTING STATION 300.00 IAW 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW SRM 53-2-0 PG.2M, REMOVED FITTING, FABRICATED NEW FITTING IAW REPAIR SPECIFICATION NR 2003-05 DWG ED-3622. PERFORMED NDT INSP IAW NDT SPM PART 08-00-02-07. FABRICATED DOUBLER IAW SRM 53-2-0 PG 17-18 FIG. 2D CLEANED, TREATED AND PRIMED DOUBLER AND FITTING IAW SRM 51-1-8B. INSTALLED FITTING AND DOUBLER IAW SRM 51-1-20DPG.9 SRM 53-2-0 PG 17-18 FIG 2D.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C CHECK INSPECTION FOUND RT FUSELAGE AFT LOWER CARGO COMPARTMENT FWD DOOR PLATING LOWER SIDE CRACKED AND WEAR DAMAGE BETWEEN STA 1160.00 TO 1220.00.REPAIR WAS ACCOMPLISHED. PERFORMED MAJOR REPAIR IAW DWG V22-R12. REMOVED DAMAGE SKIN SEGMENT AND EXTERNAL SPLICE DOUBLER IAW DWG V22-R12, DC8 SRM 51-1-21 PG 1, 51-1-20D PG 21. PERFORMED NDT INSPECTION IAW NDT SPM PART 6-10-01-0001. FABRICATED NEW SKIN SEGMENT + INTERNAL SPLICE DOUBLER IAW DC8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN SEGMENT + SPLICE DOUBLER ( INTERNAL) + NEW FASTENERS IAW DWG V22-R12, DC9 SRM 51-1-21 PG 1, 51-1-20D PG 9.

Part: PLATE — ELONGATED (LT SLOT VANE) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND LT OB SLOT VANE UPPER SURFACE ELONGATEED HOLES STA X0200 67.000 (ON REPAIR DOUBLER). REPAIR WAS ACCOMPLISHED. FASTENERS AND THE EXISTING REPAIR DOUBLER WERE REMOVED IAW DC8 SRM 51-1-21 PG 1 AND 51-3-0 PG 1. DAMAGED SKIN WAS REMOVED IAW DWG. V22-R16. NDT INSPECTION WAS PERFORMED IAW DC8 SPM PART 6-10-01-001 CLEANED, TREATED AND PRIMED AREA IAW DC8 SRM 51-1-8B. FABRICATED A REPAIR DOUBLER AND FILLER IAW DWG V22-12. CLEANED TREATED AND PRIMED THE REPAIR DOUBLER AND THE FILLER. APPLIED PRC SEALANT ON FAYING SURFACES IAW DC8 SRM 51-1-11 PG1. INSTALLED DOUBLER AND FILLER USING NEW FASTENERS IAW DWG V22-R16 AND DC8 SRM 51-1-21PG 1 AND 51-3-0 PG.1

Part: SKIN — DAMAGED (LT WING) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION FOUND L/E HOLES ELONGATED ON UPPER SKIN SURFACE, STA XFS 526.000. REPAIR ACCOMPLISHED PERFORMED MAJOR REPAIR IAW DC8 SRM 57-1-1 PG 1, DC8 SRM 57-3-3. REMOVED UPPER SKIN SURFACE OF LT WING CTR L/E STA SXF 526.00 IAW DC8 SRM 51-1-21 PG 1, DC8 SRM 51-3-0 PG 1, DC8 SRM 51-1-20D PG 21. FABRICATED AND INSTALLED NEW SKIN IAW DC8 SRM 57-3-3 PG 12. CLEANED, TREATED AND PRIMED INNER FACE OF NEW SKIN IAW DC8 SRM 51-1-8B, 51-1-21 PG 1, 51-3-0 PG 1, 51-1-20D, REFER TO NR 0275 FOR REMOVAL/REINSTALLATION OF LW WING CNT L/E.

Part: SKIN — CORRODED (LT WING LE) · airframe 91,910 hrs · 30,097 cycles

DURING C CHECK INSP FOUND LT WING IB LE UPPER SKIN SURFACE CORRODED STA XFS 207.00-212.00. REPAIR WAS ACCOMPLISHED. DAMAGED SKIN ALONG WITH FASTENERS AND CORROSION WERE REMOVED AND FOUND OUT OF LIMITS IAW DC8 SRM. AN NDT INSPECTION WAS PERFORMED IAW DC8 NDT SPM PART 6-10-01.001, CLEANED, TREATED AND PRIMED AREA IAW DC8 SRM 51-1-8B. FABRICATED A REPAIR DOUBLER AND TWO FILLERS IAW DWG V22-R17. CLEANED, TREATED AND PRIMED THE REPAIR DOUBLER INTERIOR SURFACE AND FILLERS IAW DC8 SRM 51-1-8B. PRC SEALANT WAS APPLIED ON FAYING SURFACES IAW DC8 SRM 51-1-11PG 1. INSTALLED DOUBLER & FILLERS USING NEW FASTENERS IAW DWG V22-R17 AND DC8 SRM 51-1-21 PG 1, AND 51-3-0PG. 1.

Part: SKIN — WORN (T/E FLAP) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C-CHECK FOUND RIGHT OUTBOARD FLAP UPPER PANEL DOUBLER HAS WEAR OUT OF LIMITS, STATION 159.00 - 213.00. MAINTENANCE REMOVED SKIN SEGMENT WITH DOUBLER ON IT. IN ACCORDANCE STRUCTURAL REPAIR MANUAL CHAPTER 57-1-0 AND 57-7-1 FIG 4 AREA WAS CLEANED, TREATED AND PRIMED. FABRICATION AND INSTALLATION ON NEW SKIN WAS DONE IN ACCORDANCE WITH DC8 STRUCTURAL REPAIR MANUAL 51-1-8B AND 51-1-21.

Part: PLATE — CORRODED (HORIZONTAL STAB) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT HORIZONTAL STABILIZER LE EXTENAL PART CORRODED STA XFS 341.250. REPAIR WAS ACCOMPLISHED. FASTENERS AND CORROSION WERE REMOVED ALONG WITH THE DAMAGED AREA AND FOUND OUT OF LIMITS IAW DC8 SRM 51-1-20D PG1, 51-1-21 PG. 1, 51-1-8 PG. 17-18, 55-2-1 PGS. 15,16 AND DWG V22-R08. AN NDT INPSECTION WAS PERFORMED IAW NDT SPM PART 6-10-01-001. FABRICATED FILLER & DOUBLER IAW DWG V22-R08. CLEANED TREATED AND PRIMED AREA, FILLER & DOUBLER IAW DC8 SRM 51-1-8B. PRC SEALANT WAS APPLIED ON FAYING SURFACES IAW DC8 SRM 51-1-11 PG. 9. INSTALLED FILER & DOUBLER AND FASTENERS IAW DWG. V22-R08,DC8 SRM 51-1-21 PG. 1,51-3-0 PG.1 AND 51-1-20D PG 9.

Part: SKIN — CORRODED (FUSLAGE) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C-CHECK RT FUSELAGE FORWARD LOWER CARGO COMPARTMENT FWD DOOR PLATING LOWER SIDE INTERIM REPAIR BETWEEN STA FS 280.00 AND FS 340.00. REPAIR ACCOMPLISHED. REMOVED TEMPORARY REPAIR IAW DC8 SRM 51-1-21 PG 1. PERFORMED NDT INSPECTION IAW NDT SPM PART 6-10-01-001, FABRICATED NEW SKIN SEGMENT IAW DWG V22-R13. CLEANED, TREATED AND PRIMED AREA, NEW SKIN, SPLICE( INTERNAL) IAW DC8 SRM 51-1-8B. APPLIED PRC SEALANT ON SPLICE & SKIN AND INSTALLED IAW DWG V22-R13, DC8 SRM 51-1-21 PG1, SRM 51-1-15 , SRM 51-1-20D PG 9, SRM 51-1-21A PGS 1-4. LEAK CHECK ACCOMPLISHED.

Part: PLATE — CORRODED (ZONE 600) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND CORROSION ON RT OUTER WING IB L/E OUTER PLATING AROUND STA XFS 710.00. REPAIR WAS ACCOMPLISHED. REMOVED FASTENERS IAW SRM 51-1-20D PG 21, 51-1-21 PG. 1,51-3-0 PG 1. THE CORROSION AND DAMAGED SKIN WAS REMOVED AND FOUND OUT OF LIMITS. IAW DWG V22-R03 AND SRM 57-2-1 PG. 11. NDT INSPECTION WAS PERFORMED PER NDT SPM PART 6-10-01.001. CLEANED, TREATED AND PRIMED AREA, FABRICATED A REPAIR DOUBLER AND FILLER IAW DWG. V22-R03. THE REPAIR DOUBLER WAS CLEANED, TREATED AND PRIMED. PRC SEALANT WAS APLIED ON FAYING SURFACES IAW SRM 51-1-11 PG.9. INSTALLED DOUBLER AND FILLER USING NEW FASTENERS IAW DWG V22-R03 AND SRM 51-1-20D PG 9, 51-1-21 PG. 1 AND 51-3-0 PG. 1..

Part: SKIN — CORRODED (LT WING) · airframe 91,910 hrs · 30,097 cycles

DURING C-CHECK INSPECTION FOUND LEFT OUTBOARD WING L/E INBOARD SECTION WITH CORROSION ON SEVERAL AREAS OF UPPER SKIN SURFACE (STA XW 485.000-XPS 710.000). PERFORMANCE MAJOR REPAIR IN ACCORDANCE WITH DC8 STRUCTURAL REPAIR MANUAL 56-2-1 FIG 44. REMOVED CORROSION FOUND OUTER LIMITS, REPAIR ACCOMPLISHED, REMOVED DAMAGED SKIN IN ACCORDANCE WITH DC8 STRUCTURAL REPAIR MANUAL 57-2-1 FIG 44, FABRICATED DOUBLER, CLEANED TREATED AND PRIMED THEN APPLIED SEALANT TO FRAYING SURFACE IN ACCORDANCE WITH DC8 STRUCTURAL REPAIR MANUAL 51-1-15 PAGE 1. INSTALLED DOUBLER WITH NEW FASTENERS, IAW DC8 SRM 57-2-1 FIG 44, 51-1-21 PAGE 1, 51-1-20D PAGE 9.

Part: VANE — CORRODED (RT WING LE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION FOUND RT WING L/E OB VANE CORRODED, ELONGATED HOLES AROUND STA. XOLDS 6.224. REPAIRS WERE ACCOMPLISHED IAW DWG V22-RO6, REMOVED FASTENERS IAW SRM 51-1-21 PAGE 1, SRM 51-1-20D PAGE 21, REMOVED CORROSION IAW SRM 51-1-8 PAGE 11 17.18. FOUND OUT OF LIMITS IAW SRM 57-2-1 PAGE 11 REMOVED DAMAGED AREA IAW DWG V22-R06, PERFORMED NDT INSPECTION IAW DC8 NDT SPM PART 6-10-01 001 FABRICATED FILLER & DOUBLER IAW DWG V22-RO6 CLEANED, TREATED AND PRIMED AREA, FILLER, DOUBLER & INTERNAL PARTS IAW SRM 51-1-8B APPLIED PRC SEALANT TO FAHING SURFACES IAW SRM 51-1-11 PAGE 9 INSTALLED KILLER DOUBLER WITH NEW FASTENERS IAW DWG V22-R06 IAW SRM 51-1-21 PAGE 1, SRM 51-1-20D PAGE 9, SRM 51-3-0 PAGE 1.

Part: SKIN — CORRODED (RT WING LE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RT WING OB L/E INNER SECTION UPPER SKIN SURFACE CORRODED , STA. XW 485.000. REPAIR WAS ACCOMPLISHED. CORROSION, FASTENERS AND THE DAMAGED AREA WAS REMOVED IAW DC8 SRM 51-1-21 PG1, 51-1-20D PG21,51-3-0 PG.1, 51-1-8 PG 17-18, 57-2-1 PG.11, AND DWG. V22-R02. NDT INSPECTION WAS PERFORMED IAW NDT SPM PART 6-10-01.001. AREA WAS CLEANED, TREATED AND PRIMED. FABRICATED A REPAIR DOUBLER AND FILLER IAW DWG V22-R02. THE REPAIR DOUBLER INTERIOR SURFACE AND FILLER WAS CLEANED, TREATED AND PRIMED IAW APPLICABLE MANUALS. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED DOUBLER AND FILLER USING NEW FASTENERS IAW DWG V22-R02 AND SRM 51-1-21 PG 1 51-1-20DPG 9 AND 51-3-0 PG 1.

Part: PLATE — CORRODED (RT WING) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C CHECK INSPECTION FOUND RT INNER WING CTR. LE SLOT OUTER PLATING CORRODED. STA.XW257.000-XFS 310.250. REPAIR WAS ACCOMPLISHED. FASTENERS AND CORROSION WERE REMOVED ALONG WITH THE DAMAGED AREA AND FOUND OUT OF LIMITS IAW DC8 SRM 51-1-21 PG. 1, 51-3-0 PG.1, 51-1-20D PG. 9, 51-1-8 PG.17-18, 57-2-1 PG. 11 AND DWG V22-R14. NDT INSPECTION WAS PERFORMED IAW NDT SPM PART 6-10-01-001. FABRICATED DOUBLER & 2 FILLERS IAW DC8 DRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11 PG. 9. INSTALLED DOUBLER & FILLERS AND NEW FASTENERS IAW DWG V22-R14, DC8 SRM 51-1-21 PG 1, 51-3-0 PG. 1 51-1-20D PG. 9.

Part: SKIN — CRACKED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C CHECK FUSELAGE EXTERIOR SKIN WITH 1INCH CRACK AND CORROSION IN IT, STA 1080.000 L-34R. REPAIR WAS ACCOMPLISHED. REMOVED FASTENERS ALONG WITH THE CORROSION. FOUND OUT OF LIMITS IAW SRM 53-2-0 PG 2M. REMOVED THE DAMAGED SECTION IAW DWG V22-R09, PERFORMED NDT INSP INAW DC8 NDT SRM PART 6-10-01-001. FABRICATED FILLER AND DOUBLER IAW DWG V22-R09 CLEANED TREATED AND PRIMED AREA. FILLER DOUBLER IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11 PG 9. INSTALLED FILLER, DOUBLER & NEW FASTENERS IAW SRM 51-1-20D, SRM 51-1-21 PG 7.

Part: SKIN — CORRODED (RT WING LE) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C CHECK RT WING OB L/E OUTER SECTION UPPER SKIN SURFACE CORRODED, STA. XW 761.000. REPAIR WAS ACCOMPLISHED. FASTENERS AND CORROSION WERE REMOVED ALONG WITH THE DAMAGED AREA IAW SRM 51-1-20D PG 21., 51-3-0 PG. 7, 51-1-21 PG 1. AN NDT INSPECTION WAS PERFORMED IAW NDT SPM PART 6-10-01-011. FABRICATED FILLER & DOUBLER IAW DWG. V22-R15 CLEANED, TREATED AND PRIMED AREA, INNER FACE OF FILLER & DOUBLER IAW SRM 51-1-8B. APPLIED SEALANT ( PRC) TO FAYING SURFACES IAW DC8 SRM. 51-1-11 PG. 9 INSTALLED FILLER & DOUBLER AND NEW FASTENERS IAW DWG. V22-R15. SRM 51-1-21 PG.1, 51-2-20D PG. 9, 51-3-03 PG.1

Part: PLATE — CORRODED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C CHECK INSPECTION FOUND CORROSION AND CRACK DAMAGE IN FUSELAGE FORWARD CTR. SECTION LOWER PLATING STA. 580.00 L-36. REPAIR WAS ACCOMPLISHED. CORROSION WAS REMOVED AND FOUND OUT OF LIMITS IAW SRM 53-2-0 PG2M. REMOVED FASTENERS AND DAMAGED SECTION IAW DWG V22-R10. PERFORMED NDT INSPECTION IAW DC8 NDT PART 6-10-01-001. FABRICATED FILLER, FINGER DOUBLER IAW DWG V22-R10.CLEANED, TREATED AND PRIMED AREA. FINGER DOUBLER & FILLER AND INSTALLED. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PG9.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK FOUND FUSELAGE NOSE FWD PASSENGER DOOR UPPER FWD CORNER HAS INTERIM REPAIR STATION 25.0001-9L. REPAIR ACCOMPLISHED IAW DC8 SRM 53-2-0, PAGE 2-5. TR 53-182. REMOVED INTERIM REPAIR IAW SRM 51-1-21 PG 1. MEASURED CRACK 5.250 INCH, FOUND OUT OF LIMITS IAW DC8 SRM 53-2-0 FIG 15 TR 53-182, CONTINUED REPAIR, TIN-LIT 04-00016. MARCH 05, 2004 AND TIN-LIT 04 00017H MARCH 08, 2004 WITH FORM 8110-3. REMOVED CRACKED SKIN IAW DC8 SRM 53-2-0 FIG 15 FABRICATED DOUBLER, TRIPLER AND FILLER IAW DC8 SRM 53-2-0 FIG 15. CLEANED, TREATED AND PRIMED DOUBLER AND TRIPLER AND FILLER IAW DC8 SRM 51-1-8B. INSTALLED FILLER & DOUBLER & TRIPLER IAW DC8 SRM 53-2-0 FIG 15 SRM 51-1-20D, PAGE 9, SRM 51-1-21 PAGE 1 SRM

Part: SKIN — CORRODED (RT WING) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK FOUND RT WING OUTBOARD L/E INNER SECTION UPPER SKIN SURFACE CORRODED, STATION XW 485.000- XFS 710. REPAIR IS ACCOMPLISHED. REMOVED FASTENER IAW DC8 SRM 51-1-21 PG 1, DC8 SRM 57-2-1 FIG 44. REMOVED CORROSION FROM UPPER SKIN SURFACE OF RT WING OUTBD L/E INNER SECTION IAW DC8 SRM 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW DC8 SRM 57-2-1 PG 11. REMOVED DAMAGED SKIN SECTION IAW DC8 SRM 57-2-1 FIG 44, FABRICATED DOUBLER IAW DC8 SRM 57-2-1. CLEANED, TREATED AND PRIMED AREA & INNER FACE OF DOUBLER IAW DC8 SRM 51-1-8B. INSTALLED DOUBLER AND NEW FASTENERS IAW DC8 SRM 57-2-1 FIG 44, DC8 SRM 51-1-21 PG 1, DC8 SRM 51-1-20D PG 9.

Part: SKIN — CORRODED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C CHECK INSPECTION FOUND LT OB WING LE OB SECTION SKIN CORRODED STA XW 761.000. REPAIR WAS ACCOMPLISHED. REMOVED FASTENERS AND CORROSION ALONG WITH THE DAMAGED AREA AND FOUND OUT OF LIMITS IAW DC8 SRM 51-1-20D PG 21, 51-1-21 PG.1, 51-3-0 PG.1, 51-1-8 PG 17-18, 57-2-1 PG. 11 AND DWG V22-R07. NDT INSPECTION WAS PERFORMED IAW NTD SPM PART 6-10-01-001. FABRICATED FILLER & DOUBLER IAW DWG V22-R07. CLEANED, TREATED AND PRIMED INNER FACE OF FILLER & DOUBLER IAW DC8 SRM 51-1-8B. PRC SEALANT WAS APPLIED TO FAYING SURFACES IAW DC8 SRM 51-1-11. PG 9. INSTALLED FILLER, DOUBLER AND NEW FASTENERS IAW DWG V22-R07, SC8 SRM 51-1-21 PG ., 51-1-20D PG 9 AND 51-3-0 PG.1

Part: SKIN — CORRODED (LT WING LE) · airframe 91,910 hrs · 30,097 cycles

DURING A ROUTINE C CHECK INSPECTION FOUND LT WING OB L/E INNER SECTION UPPER SKIN SURFACE CORRODED, STA.XW. 485.000. REPAIR WAS ACCOMPLISHED. REMOVED DAMAGED AREA IAW DWGV22-R01 INCLUDING FASTENERS AND CORROSION AND FOUND OUT OF LIMITS IAW SRM 51-1-21 PG.1, 51-1-20D PG. 21 AND SRM 51-1-8 PG. 17-18. NDT INSPECTION WAS PERFORMED IAW NDT SPM PART 6-10-01.001 AREA WAS CLEANED, TREATED AND PRIMED. FABRICATED A REPAIR DOUBLER AND FILLER . CLEANED, TREATED AND PRIMED THE REPAIR DOUBLER INTERIOR SURFACE AND THE FILLER IAW SRM 51-1-8B. APPLIED PRC SEALANT ON FAYING SURFACES IAW DCI SRM 51-1-11 PG 9. INSTALLED THE REPAIR DOUBLER AND FILLER USING THE NEW FASTENERS IAW DWG. V22-R01 AND DC8 SRM 51-1-21 PG 1 AND 51-1-20D P

Part: SKIN — CRACKED (FUSELAGE) · airframe 91,910 hrs · 30,097 cycles

DURING ROUTINE C-CHECK INSPECTION A CRACK WAS DETECTED AT THE RIGHT FUSELAGE TAIL SECTION BETWEEN STATION 1750.00 AND 1752.00, L14R-L15R. REPAIR ACCOMPLISHED, REMOVED FASTENERS AND DAMAGE AREA IN ACCORDANCE WITH DC8 STRUCTURAL REPAIR MANUAL 53-2-1 FIGURE 7. FABRICATED DOUBLER, FINGER DOUBLER AND FILLER IN ACCORDANCE WITH DC8 STRUCTURAL MANUAL 53-2-1 FIG 7, CLEANED, TREATED AND PRIMED DOUBLER, FINGER DOUBLER AND FILLER. INSTALLED ALL IN ACCORDANCE WITH DC8 STRUCTURAL REPAIR MANUAL 53-2-1 FIG 7, 51-2-20D PAGE 9, AND 51-1-21 PAGE 1.

Part: DOOR — UNSECURE (CARGO BAY) · airframe 91,884 hrs · 30,084 cycles

CREW HAD MASTER WARNING LIGHT/BELLY DOOR LIGHT AT 90 KNOTS. CREW REJECTED TAKEOFF AND RETURNED TO BLOCKS. MAINTENANCE COMPLIED WITH REJECTED TAKEOFF INSPECTION AND NO DEFECTS WERE NOTED. MAINTENANCE THEN INSPECTED BELLY DOORS AND FOUND THE -B- PIT DOOR AJAR. THE DOOR WAS CYCLED AND BELLY DOOR LIGHTS SYTEMS TESTED NORMAL PER ALL APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.

Part: WIRE HARNESS — FAILED (NR 2 ENGINE) · airframe 91,423 hrs · 29,901 cycles

UPON CLIMBOUT FROM KLRD CREW NOTED NR 2 ENGINE EXHAUST GAS TEMP (EGT) CLIMBING ABNORMALLY. AS A PRECAUTIONARY MEASURE CREW ELECTED TO RETURN TO KLRD AND MADE AN UNEVENTFUL LANDING. MAINTENANCE IS INVESTIGATING. AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE TROUBLE SHOT IAW CGM MM 71-00-00. NO DEFECTS WERE NOTED. EGT SYSTEM WAS INSPECTED WITH NO DEFECTS NOTED. MAINTENANCE REMOVED AND REPLACED EGT HARNESS AND 2 THERMOCOULPES PER ALL APPLICABLE MANUALS. MAINTENANCE ALSO REMOVED AND REPLACED CIT SENSOR PER ALL APPLICABLE MANUALS. OPERATIONAL CHECK GOOD. AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — FLUCTUATES (NR 3) · airframe 91,225 hrs · 29,794 cycles

DURING CLIMB FROM KTOL TO KBNA THE NR 3 ENGINE EGT BEGAN TO FLUCUATE BOTH ANALOG AND DIGITAL +/- 50 DEGREES C. CREW RETURNED AIRCRAFT TO KTOL AND FLUCUATION CONTINUED THROUGH DESCENT AND LANDING. AIRCRAFT LANDED IN KTOL WITHOUT INCIDENT. AN INSPECTION IS ON GOING. AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED.

Part: PROXIMITY SWITCH — WORN (ZONE 700) · airframe 91,190 hrs · 29,763 cycles

WHEN MLG WAS EXTENDED NO LEFT GEAR OR DOOR UNLATCHED LIGHTS NOTED.PERFORMED ABNORMAL PROCEDURE PER ATI COM, NO HELP. AFTER SEVERAL GEAR CYCLES ALL LIGHTS INDICATED NORMALLY. CREW LANDED WITHOUT INCIDENT IN KTOL.UPON INSEPCTION MAINTENANCE NOTED L/H MLG DOWNLATCH SWITCH CONDITION DETERIORATED AND REPLACED THIS COMPONENT. MAINTENANCE PERFORMED CHECK AND ALL INDICATIONS WERE WITHIN LIMITS. ALL WORK COMPLETED PER APPLICABLE MANUALS AND AIRCRAFT RETURNED TO SERVICE.

Part: PIN — BROKEN (MLG) · airframe 94,277 hrs · 30,617 cycles

AFTER TAKEOFF WHEN GEAR WAS RAISED THE DOORS NOT LATCHED LIGHT, GEAR NOT LATCHED LIGHT AND SECONDARY RIGHT DOOR LIGHT STAYED ILLUMINATED. RECYCLED LANDING GEAR. GEAR DOWN INDICATIONS NORMAL RIGHT GEAR SEEMED TO INDICATE DOWN VERY QUICKLY. GEAR WAS RAISED WITH SAME INDICATIONS AS BEFORE. FLIGHT WAS CONTINUED USING GEAR EXTENED PROCEDURES. CREW LANDED AIRCRAFT AT HKJK WITHOUT INCIDENT. MAINTENANCE INSPECTED THE RIGHT MAIN LANDING GEAR AND FOUND RETRACT PIN BROKEN. REMOVED AND REPLACED PIN PER ALL APPLICABLE MANUALS AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: SWITCH — LOOSE (LEFT GEAR) · airframe 90,093 hrs · 29,342 cycles

ENROUTE FROM DFW TO TOL, THE LANDING GEAR LIGHT REMAINED ILLUMINATED FOLLOWING LANDING GEAR EXTENSION. THE FLIGHT CREW RECYCLED THE GEAR AND THE LIGHT FLICKERED THEN REMAINED ILLUMINATED. THE CREW FOLLOWED COMPANY PROCEDURES AND CONTINUED FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND A LOOSE CONNECTION AT THE LEFT GEAR SWITCH. MAINTENANCE SECURED THE CONNECTION AND PERFORMED A SUCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE DOUGLAS REPAIR MANUAL

Part: SUPPORT — CRACKED (Y-1745 BL-0) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO FLOOR SUPPORT ON L/H FLANGE AT STA Y-1745 AND BL-0, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-24, 51-1-20D AND 51-1-21.

Part: ANGLE — CRACKED (FS 55 X+44) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE MAIN CABIN FLOOR BEAM ATTACH ANGLE FWD SIDE AT FS 55 X+44, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 51-1-20D.

Part: DOUBLER — CORRODED (D PIT DOOR) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE UNDER DOOR SCUFF PLATE ON THE FUSELAGE EXTERIOR D CARGO COMPT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW EO PD08-53-085 AND SRM 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: STRUCTURE — CRACKED (RT INLET SCOOP) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK AND BREAK TO THE OUTER SHROUD OF THE RT SCOOP INLET DUCT IN THE FWD NOSE COMPT AT STA 165, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-2.

Part: SEAT TRACK — CORRODED (STA 930-1130) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE SEAT TRACK AT STA 930-1130 AND RBL-X45, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED REPAIR AND INSTALLED IAW DC-8 SRM 53-2-3 FIG 8A. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SEAT TRACK — CORRODED (STA930-1130 X45) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE SEAT TRACK AT STA 930-1130 -X45, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 53-2-3 FIG 8A. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM)

Part: ANGLE — CRACKED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE CUSP ANGLE AT STA 822-834.5 X-45, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-4-1 AND 51-1-21.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO MAIN CABIN FLOOR PANEL ATTACH ANGLE AT STA 717-742 AND LBL 65, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-4, 51-1-21.

Part: FRAME — CRACKED (STA 1700) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE FRAME AT STA 1700 AND BETWEEN L12L AND L14L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0, 51-1-21 AND 51-1-8.

Part: STRUT — CORRODED (NLG) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE LOWER END OF NOSE STRUT ABOUT 5 INCHES FROM BOTTOM, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 MM 32-40-2 AND 32-21-4.

Part: FITTING — CRACKED (STA 70 RBL 45) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE T FITTING UNDER SEAT TRACK AT STA 70 RBL 45, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND 51-1-21.

Part: FITTING — CRACKED (STA X=147.9) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE BATH TUB FITTING OF AFT LWR RIB CAP AT ELEVATOR HINGE SUPPORT AT STA XE 147.9, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW FITTING AND INSTALLED IAW DC-8 SRM 51-1-24.

Part: FRAME — CRACKED (FWD LAV.) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE FRAME ON THE FWD LAV TOILET FRAME ASSY BOTTOM I/B LEG, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-5, 51-1-22 AND 51-1-12.

Part: FITTING — CRACKED (STA 68X45.50) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE SUPPORT FITTING ON THE R/H I/B CARGO TRACK AT STA 68X-45.50, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC-8 SRM 51-1-24 AND 51-1-20D.

Part: ANGLE — CRACKED ('C' BAGGAGE DOOR) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE "J" EXTRUSION OF THE "C" BAGGAGE DOOR PROTECTOR THRESHOLD GATE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW PD 08-53-089.

Part: FITTING — CRACKED (STA 798 L19R) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE LONGERON 19R FITTING AT STA 798, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 51-1-21 AND DWG M20-R01.

Part: FITTING — CRACKED (STA XE 147.9) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE L/HORIZ STAB BATH TUB AREA OF AFT UPPER RIB CAP AT ELEVATOR HINGE SUPPORT AT STA XE 147.9, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8S RM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 51-1-21 AND 51-1-21A.

Part: CHANNEL — CRACKED ('C' BAGGAGE DOOR) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE "C" BAGGAGE DOOR PROTECTOR THRESHOLD GATE FWD END CHANNEL, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW PART IAW DC-8S RM 51-1-21.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE LWR FWD CARGO AFT DOOR LWR JAMB AT FS 542, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED REPAIR AND INSTALLED IAW PD 08-53-091.

Part: LONGERON — CRACKED (STA 1781 L2L) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE AFT FUSELAGE INTERIOR AT STA 1781 AND L2L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW EA PD 08-53-083.

Part: FLANGE — CORRODED (STA Y=1745 RBL23) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE LOWER SIDE OF TOP FLANGE OF FLOOR SUPORT AT CLIP NUTS AT STA Y=1745 AND RBL 23, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21, 51-1-20 FIG 6 AND 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CORRODED (FWD CARGO) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE LWR FWD CARGO DOOR LWR JAMB AFT LATCH FITTING, DAMAGE EXCEEDED LIMITATIONS IAW DC-8S RM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 51-1-20 AND 51-1-24. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (STA 1726) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE UNDER SIDE OF TOP FLANGE OF LOOR SUPPORT ANGLE AT STA Y=1726 FROM RBL10 TO LBL10, DAMAGE EXCEEDED LIMITATIONS IAW DC-8S RM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW PART IAW DC-8 SRM 51-3-0, 83-7-3, 53-2-0, 51-2-0, 51-1-21A AND 51-1-4 FIG 1. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — NICKED (LT WING TE FLAP) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND NICKS TO THE LEFT WING I/B FLAP CENTER T/E, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-7-0 AND 51-1-21A.

Part: SEAT TRACK — WORN (STA 1395 X=24.75) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 1395-1402 X=24.75, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW TRACK IAW DC-8 SRM 51-2-0 AND 51-1-24.

Part: SEAT TRACK — WORN (STA 950-957 BL-0) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 950-957 BL-0, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW PART IAW DC-8 SRM 53-2-3 FIG 8A, 51-1-20, 51-1-24, 51-3-0, 51-9-0 AND 51-1-20 FIG 4A.

Part: SEAT TRACK — WORN (ST X=24.75) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA X=24.75, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 53-2-3.

Part: SEAT TRACK — WORN (STA 1216 X+24075) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 1216-1223 X=24.75, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-3 AND 53-2-3 FIG 8A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE EMERGENCY OVER WING EXIT DOOR FRAME RT SIDE AFT AT STA 798, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REPAIRED IAW COTNEY COMPANY DWG M20-R01.

Part: SEAT TRACK — WORN (COCKPIT SEAT) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND WORN SEAT TRACKS L/H & R/H IN THE COCKPIT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND 51-3-0.

Part: SEAT TRACK — WORN (FE'S SEAT) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT FE'S STA IN COCKPIT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 51-1-24, 51-1-12 AND 51-1-5.

Part: SEAT TRACK — WORN (STA X=24.75-1581) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA X=24.75-1581, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW PART IAW DC-8 SRM 53-2-3 AND 51-1-24.

Part: ANGLE — CORRODED (STA 834.5) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FLOOR PANEL ATTACHING ANGLE IN THE MAIN CABIN R/H SIDE BETWEEN STA'S 834.5 AND 857 AND L65R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (STA 206-220) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FLOOR PANEL ATTACHING ANGLE R/H SIDE AT STA 200 AND 220 BL 65R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW PART IAW DC-8 SRM 53-2-0 FIG 1B. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (STA 798) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANC EVISIT FOUND CORROSION DAMAGE TO THE FLOOR PANEL ATTACHING ANGLE IN THE MAIN CABIN R/H SIDE BETWEEN STA'S 798 AND 822 AND L65R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (STA 822) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FLOOR PANEL ATTACHING ANGLE IN THE MAIN CABIN R/H SIDE BETWEEN STA'S 822 AND 834.5 AND L65R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 51-1-21. AND 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: TRACK — WORN (STA 1485 BL-0) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 1485 BL-0, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-3 AND 51-1-24.

Part: SEAT TRACK — WORN (STA X=45.5 L/H) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA X=45.5, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW PART IAW DC-8 SRM 51-1-24 AND 53-2-3.

Part: SEAT TRACK — WORN (STA X=24.75) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA X=24.75, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW PART IAAW DC-8 SRM 53-2-3.

Part: ANGLE — CORRODED (STA 759 L65R) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FLOOR PANEL ATTACHING ANGLE IN THEMAIN CABIN R/H SIDE BETWEEN STA'S 279 AND 781.5 AND L65R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 53-2-0 FIG 1. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SEAT TRACK — WORN (STA 148 X-24) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 148-156 X-24.756, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 52-2-3.

Part: SEAT TRACK — WORN (STA 506-514) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 506-514 X24.750, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-3.

Part: SEAT TRACK — WORN (STA 69) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 69 L/H X24-156, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW TRACK AND INSTALLED IAW DC-8 SRM 53-2-3.

Part: SEAT TRACK — WORN (STA 595-603) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 595-603 X-45.50, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-3, 53-2-34 AND 51-1-12.

Part: SEAT TRACK — WORN (STA 328) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 328 X24.720, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 51-3-0 AND 51-1-24.

Part: SEAT TRACK — WORN (STA 68 X-45.50) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 68X-45.50, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 51-1-29, 51-30-02 AND 51-1-21.

Part: SEAT TRACK — WORN (STA 683) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN CARGO TRACK AT STA 683 AND 693 X-45.50, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-3 AND 51-1-12.

Part: SEAT TRACK — WORN (STA 328) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 328 X24.750, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-3.

Part: SEAT TRACK — WORN (STA 506-513) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 506-513 X-45.50, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-34 AND 51-1-12.

Part: RIB — CRACKED (L/W #3 FLT SPOIL) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE RIB IN RADIUS ON THE LT WING T/E, FLAPWELL BELOW #3 FLT SPOILER O/B SIDE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW PD08-27-015.

Part: SEAT TRACK — WORN (STA 772-779) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 772-779 X45.50, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW TRACK IAW DC-8 SRM 51-1-20 AND 51-1-22.

Part: SEAT TRACK — WORN (STA 418-425) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 418-425, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 51-1-30, 51-1-24 AND 51-1-20D.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE TRACK UNDER LAV AT STA 52-62 RT X-59 343, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW TRACK AND INSTALLED IAW DC-8 SRM 53-2-3, 51-1-24.

Part: SEAT TRACK — WORN (STA 510-520) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 510-520 X0, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-7, 53-2-3 AND 51-30-0.

Part: SEAT TRACK — WORN (STA 595-603) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK BETWEEN STA'S 595-603 X45.50, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 51-3-0 AND 51-1-21.

Part: SEAT TRACK — WORN (STA 772-780) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A WORN SEAT TRACK AT STA 772-780 X-24.750, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-3.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE SEAT TRACK BETWEEN STA'S 52-62 RT X-59.343, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW TRACK AND INSTALLED IAW DC-8 SRM 53-2-3 AND 51-1-24.

Part: ANGLE — CORRODED (STA 920 BL-65L) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FLOOR PANEL ATTACHING ANGLE L/H SIDE AT STA 902-920 AND BL-65, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-4 FIG G. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (STA 540-560 BL65) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FLOOR PANEL ATTACHING ANGLE AT STA 560 BL 65L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-0, 51-2-0 FIG 1F. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — GOUGED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A GOUGE IN FUSELAGE EXT SKIN BETWEEN STA 260-280 RT SIDE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REPAIRED SKIN IAW EA PD08-53-088 AND DC-8 SRM 53-2-0.

Part: DOUBLER — GOUGED (STA 52-32) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A LARGE GOUGE TO THE NLG DOOR FUSELAGE EXT R/H SIDE AT STA 52-32, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 52-2-0, 51-1-5 AND 51-1-21.

Part: STRUCTURE — DAMAGED (RT WING TIP) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A 1/4 INCH HOLE IN THE RIGHT WING TIP CAP RT O/B NEAR THE CENTER, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REPAIRED HOLE IAW PD 05-57-047.

Part: SKIN — CRACKED (R/H SIDE SVC DR) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE RIGHT SIDE FUSELAGE EXT SKIN AT FWD SERVICE DOOR LOWER AFT CORNER, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-20D, 51-1-14 AND PD08-53-080.

Part: ANGLE — CORRODED (C-PIT FWD CORNER) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE BOTTOM CORNER OF DOOR CUTOUT ON T-ANGLE IN THE CARGO COMPT PIT 'C', DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PART AND INSTALLED IAW DC-8 SRM 53-2-0, 51-3-2 AND 51-1-2D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CRACKED (FS14 L33R) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE LONGERON END AT FS 14 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED NEW PART AND INSTALLED IAW DC-8 SRM 51-1-24.

Part: DOUBLER — CRACKED (RT WING TIP) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND DENTS AND CRACKS TO THE RT WING O/B EDGE OF WING TIP ASSY, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 57-2-1.

Part: SKIN — CORRODED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FUSELAGE EXTERIOR SKIN AT FS 318-325 AND L30L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW EA PD 08-53-082.

Part: SKIN — BULGED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE FUSELAGE SKIN AT STA 1260 AND L32L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 53-2-1, 51-1-20D AND EO NR 00-199 WITH APPROVED 8110-3 DATED 8-1-00. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — DAMAGED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND THAT THE TEMP REPAIR NEEDED A PERMANENT REPAIR AT STA 1220 AND STR 35R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW EO NR 00-199 WITH APPROVED 8110-3 DATED 7-31-00.

Part: SKIN — CORRODED (TE FLAP) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND PITTING ON THE UPPER SURFACE ON THE RT O/B FLAP O/B AT STA 340, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM.

Part: SKIN — CORRODED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND PITTING TO THE UPPER SURFACE OF THE RIGHT O/B FLAP O/B AT STA 340, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED REPAIR AND INSTALLED IAW DC-8 SRM 57-2-0 AND EO NR 00-199 WITH APPROVED 8110-3 DATED 7-31-00.

Part: FITTING — CORRODED (RT WING) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORRISION DAMAGE ON THE SIDE BRACE MOUNTING BOSS ON THE RT WING LWR REAR SPAR FLAP FITTING AT STA 219, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8. RECEIVED REPAIR AND INSTALLED IAW DC-8 SRM 27-51-8 AND EO NR 0-199 WITH APPROVED 8110-3 DATED 7-27-00. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CORRODED (LT WING) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE ON THE SIDE BRACE MOUNT BOSS ON THE LT WING LWR REAR SPAR FLAP FITTING AT STA 219, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED, PRIMED AND PAINTED AREA IAW DC-8 SRM 51-1-8. RECEIVED REPAIR AND INSTALLED IAW DC-8 SRM 27-51-1 AND EO NR 00-199 WITH APPROVED 8110-3 DATED 7-27-00. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: RIB — CRACKED (RT WING) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A SMALL DOUBLER CRACKED ON THE RIGHT O/B, I/B FLAP SCISSOR AREA LWR SURFACE AFT CORNER OF RIB, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21, 51-1-4 AND 51-1-21.

Part: SKIN — BENT (RT TE FLAP) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND THE EXHAUST GATE BENT ON THE RIGHT O/B FLAP O/B LWR CORNER, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 57-2-1 AND 51-1-20A.

Part: SKIN — GOUGED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND WORN/GOUGED RIGHT O/B LEADING EDGE BETWEEN STA 340 - 410, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 57-2-1, 51-1-4 AND 51-1-20.

Part: SKIN — CANNING (WING) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND OIL PANNING ON THE RIGHT O/B FLAP I/B TRAILING EDGE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 57-2-1.

Part: SKIN — DAMAGED (RT WING) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A PIECE OF DOUBLER BROKEN OFF ON THE RIGHT O/B FLAP DOUBLER FOR ICE SCRAPER AT STA 340, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 51-1-21 AND 57-2-0.

Part: SKIN — CRACKED (AFT) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A CRACK TO THE I/B AFT CORNER EXHAUST GATE ON THE RIGHT O/B FLAP, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW DC-8 SRM 57-2-1, 51-1-18, 51-1-21 AND 51-1-21A.

Part: FITTING — CORRODED (TE FLAP) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE ON SIDE BRACE MOUNT BOSS ON THE LT WING LWR REAR SPAR FLAP FITTING AT STA 219, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM.

Part: FITTING — CORRODED (TE FLAP) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO THE LWR REAR SPAR FLAP FITTING ON SIDE BRACE MOUNTING BOSS ON THE RT WING AT STA 219, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM.

Part: SKIN — BENT (TE FLAP) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A BENT EXHAUST GATE ON THE O/B LWR CORNER OF THE RIGHT O/B FLAP, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT FOUND A PIECE OF DOUBLER BROKEN OFF ON THE RIGHT O/B FLAP DOUBLER FOR ICE SCRAPER AT STA 340, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 88,537 hrs · 28,578 cycles

DURING A MAINTENANCE VISIT NEED TO REMOVE TEMP. REPAIR AND INSTALL PERMANENT REPAIR AT STA 1220 STR 35R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM.

Part: FIRE DETECTOR — MALFUNCTIONED (NR 2 ENGINE)

FIRE INDICATION NR 2 ENGINE PER QRH CHECKLIST ALL NR 2 SYSTEMS SHUT DOWN, OUTBOARD AGENT WOULD NOT DISCHARGE, DISCHARGED INBOARD. FOUND BOTH BOTTLES DISCHARGED OUTBOARD BOTTLE HAD BROKEN WIRE AT AGENT LOW LIGHT SWITCH REPAIRED WIRE. REMOVED AND REPLACED LEFT SIDE INBD AND OUTBOARD FIRE BOTTLES. NR 2 FIRE WARNING WOULD NOT TEST. REPLACED RT AFT FIRE LOOP, NO DEFECTS NOTED.

Part: O RING — LEAKING (OIL CAP)

DURING CLIMB-OUT, NR 1 ENG OIL QUANTITY DROPPED TO 4 QTS. OIL PRESS FLUCTUATE AT 30-35 PSI, OIL TEMP 80DEG C. PULLED NR 1 THROTTLE TO IDLE, OIL QUANTITY CONTINUED TO 3QTS AND STEADY. DUMPED FUEL TO MAX LANDING WEIGHT AND RETURNED TO KFLL. UPON INSPECTION FOUND CUT OIL CAP O-RING. REPLACED O-RING, SERVICE ENGINE OIL TANK. NO LEAKS ON ENG RUN UP.

Part: CHANNEL — CORRODED (BS 1220)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON RIGHT HAND FLOOR STRUT TO FLOOR BEAM CHANNEL AT STA 1220. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. REMOVED AND REPLACED CHANNEL IAW DC8 SRM 51-1-20 AND DAC DWG 9754002. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: SKIN — CORRODED (BS 1260-1280)

DURING A MAINTENANCE VISIT, FOUND FUSELAGE, INTERIOR SKIN WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM, AT STA 1260 TO STA 1280 AND LONGERON 36. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05269.

Part: SKIN — DENTED (BS 70-130)

DURING A MAINTENANCE VISIT, FOUND FUSELAGE EXTERIOR SKIN WITH MULTIPLE DENTS IN VARIOUS ARES, DAMAGED IS BEYOND LIMITS IAW DC-8 SRM, AT STA 70 TO STA 130 LEFT SIDE. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLERS IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05277.

Part: SKIN — CRACKED (WS 526.76)

DURING A MAINTENANCE VISIT, FOUND RIGHT WING, LEADING EDGE, LOWER SKIN SURFACE WITH .55 INCH CRACK, AT STA XFS 526.76. REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05316.

Part: FITTING — DAMAGED (MLG WW)

DURING A MAINTENANCE VISIT, FITTING (P/N 5616132-2), AT WHEEL WELL AND LONGERON 24 RIGHT FOUND DAMAGED. REMOVED FITTING, FABRICATED NEW FITTING BY MATERIAL SUBSTITUTION. ORIGINAL MATERIAL 7075-T411, SUBSTITUTED WITH 7075T-T6 IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05079. FABRICATED AND INSTALLED NEW FITTING IAW DWG 5616132 AND DWG 5616429 AND DPS4.999.

Part: FLFOORBEAM — CORRODED (BS 1200)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON UPPER LEG ON FLOORBEAM FWD AT STA 1280, BL 60R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR TO DAMAGED FLOORBEAM IAW TIMCO DWG DC-8-53-051-509 AND DC8 SRM 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: STIFFENER — CORRODED (BS 970-980)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON STIFFENER AND MISSING LOWER FLANGE CORNER AT STA 970 TO 980, BL 30R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FRAME IAW DAC DRG 5646444 AND DC8 SRM 51-1-24 AND 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FRAME — MISDRILLED (BS 980)

DURING A MAINTENANCE VISIT, FOUND FRAME WITH MISDRILLED HOLE, AT STA 980 AND LONGERON 7 LEFT. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-0149.

Part: FRAME — CORRODED (BS 520)

DURING A MAINTENANCE VISIT, FOUND FRAME CHANNEL, WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 520 AND LONGERON 36. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05142.

Part: FLOORBEAM — DAMAGED (BS 1480-1600)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM, UPPER FLANGE WITH MULTIPLE ELONGATED HOLES, AT STA 1480 TO 1600. FABRICATED AND INSTALLED REPAIR DOUBLERS IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05150.

Part: FLOORBEAM — CORRODED (BS 200)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 200 AND BLR 45. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05159.

Part: FLOORBEAM — CORRODED (BS 620)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 620. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05169.

Part: FRAME — CORRODED (BS 1120)

DURING A MAINTENANCE VISIT, FOUND FRAME LOWER SURFACE WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 1120 AND LONGERON 33 RIGHT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05177.

Part: DOOR — CRACKED (FUS PNEU ACCESS)

DURING A MAINTENANCE VISIT, FOUND GROUND PNEUMATIC ACCESS DOOR, INTERNAL DOUBLER CORRODED AND CRACKED. REMOVED CORRODED REPAIR DOUBLER, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NEW DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05072.

Part: FRAME — CORRODED (BS 1460)

DURING A MAINTENANCE VISIT, FOUND INBOARD FLANGE OF FLOORBEAM AND FRAME, STRUT WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 1460, BLR. REMOVED DAMAGED SECTION, TREATED AREA IAW DC08 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05098.

Part: FLOORBEAM — CORRODED (BS 822)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM, UPPER SURFACE WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 822 AND BLL 15. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05170.

Part: FLOORBEAM — CORRODED (BS 834)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM, UPPER SURFACE WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 834 AND BLL 24. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05201.

Part: ANGLE — CORRODED (BS 180)

DURING A MAINTENANCE VISIT, FOUND FRAME ANGLE CORRODED BEYOND LIMITS IAW DC-8 SRM, AT STA 180 AND LONGERON 30 LEFT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05145.

Part: FLOORBEAM — CORRODED (BS 1580)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM, UPPER SURFACE WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 1580 AND BLL 50. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05200.

Part: FASTENER — TRAPPED (NR 2 PYLON)

DURING A MAINTENANCE VISIT, TRAPPED FASTENER UNDER DRAG ANGLE AND A FASTENER INTERFERS WITH REPLACEMENT OF FOOTSTOOL FITTING AT NR 2 PYLON. DELTED TRAPPED FASTENER FROM FOOTSTOOL, INSTALLED AND MODIFIED FOOTSTOOL TO AVOID INTERFERENCE IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05152.

Part: FLOORBEAM — CORRODED (BS 380)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM TO FRAME STRUT WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 380, BLL. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05178.

Part: FASTENER — TRAPPED (NR 3 PYLON)

DURING A MAINTENANCE VISIT, TRAPPED FASTENER UNDER DRAG ANGLE AND A FASTENER INTERFERS WITH REPLACEMENT OF FOOTSTOOL FITTING AT NR 3 PYLON. DELTED TRAPPED FASTENER FROM FOOTSTOOL, INSTALLED AND MODIFIED FOOTSTOOL TO AVOID INTERFERENCE IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05153.

Part: FRAME — CORRODED (BS 1080)

DURING A MAINTENANCE VISIT, FOUND FRAME LOWER SURFACE WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 1080 AND LONGERON 36. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05171.

Part: FLOORBEAM — CORRODED (BS 1520)

DURING A MAINTENANCE VISIT, FOUND FLANGE OF FLOORBEAM AND FRAME, STRUT WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 1520, BLR. REMOVED DAMAGED SECTION, TREATED AREA IAW DC08 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05099.

Part: FRAME — CORRODED (BS 1060)

DURING A MAINTENANCE VISIT, FOUND FRAME LOWER SURFACE WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 1060 AND LONGERON 35 LEFT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05172.

Part: FITTING — DAMAGED (BS 834)

DURING A MAINTENANCE VISIT, FITTING (P/N 3755840-1), AT STA 834 AND LONGERON 21 RIGHT FOUND DAMAGED. REMOVED FITTING, FABRICATED NEW FITTING BY MATERIAL SUBSTITUTION. ORIGINAL MATERIAL 7075-T411, SUBSTITUTED WITH 7075T-T6 IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05192. FABRICATED AND INSTALLED NEW FIITING IAW DWG 5615040 AND DPS4.999.

Part: PLATING — CRACKED (NR 3 PYLON)

DURING A MAINTENANCE VISIT, FOUND NUMBER 3 PYLON, LEADING EDGE WITH .5 INCH CRACK. REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05083.

Part: HINGE — GOUGED (RT TE FLAP)

DURING A MAINTENANCE VISIT, FOUND RIGHT INBOARD FLAP, HINGE, (P/N 5642960), GOUGED. REPAIRED HINGE BY BLENDOUT, FABRICATED 6 FILLERS, 4 RUB STRAPS AND INSTALLED IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05139.

Part: FLOORBEAM — CORRODED (BS 781.5)

DURING A MAINTENANCE VISIT, FOUND FLOORBEAM WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 781.5 AND BLL 2 TO BLL 10. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05135.

Part: FLOORBEAM — DAMAGED (BS 380)

DURING A MAINTENANCE VISIT, FOUND INBOARD FLANGE OF FLOORBEAM AND FRAME, STRUT WITH TOOL DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 380, BLL. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05129.

Part: FITTING — DAMAGED (BS 832)

DURING A MAINTENANCE VISIT, FITTING (P/N 3616944-2), AT STA 832 AND LONGERON 21 RIGHT FOUND DAMAGED. REMOVED FITTING, FABRICATED NEW FITTING BY MATERIAL SUBSTITUTION. ORIGINAL MATERIAL 7075-T411, SUBSTITUTED WITH 7075T-T6 IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05130. FABRICATED AND INSTALLED NEW FIITING IAW DWG 3616944-2 AND DPS4.999.

Part: FRAME — CORRODED (BS 1280)

DURING A MAINTENANCE VISIT, FOUND INBOARD FRAME, STRUT WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 1240, BLL. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05118.

Part: WEB — CORRODED (BS 270-280)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON WEB ON TORQUE BOX AT LONGERON 31R AT STA 270O 280. DAMAGED BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED WEB IAW DAC DWG 5753892. LOCATED HOLES IN NEW WEB IAW DC-8 SRM 51-1-24 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: WEB — CORRODED (BS 270-280)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON WEB ON TORQUE BOX AT LONGERON 31R AT STA 270O 280. DAMAGED BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED WEB IAW DAC DWG 5753892. LOCATED HOLES IN NEW WEB IAW DC-8 SRM 51-1-24 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: WEB — CORRODED (BS 270-280)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON WEB ON TORQUE BOX AT LONGERON 31R AT STA 270O 280. DAMAGED BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED WEB IAW DAC DWG 5753892. LOCATED HOLES IN NEW WEB IAW DC-8 SRM 51-1-24 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: WEB — CORRODED (BS 270-280)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON WEB ON TORQUE BOX AT LONGERON 31R AT STA 270O 280. DAMAGED BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED WEB IAW DAC DWG 5753892. LOCATED HOLES IN NEW WEB IAW DC-8 SRM 51-1-24 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: WEB — CORRODED (BS 270-280)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON WEB ON TORQUE BOX AT LONGERON 31R AT STA 270O 280. DAMAGED BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED WEB IAW DAC DWG 5753892. LOCATED HOLES IN NEW WEB IAW DC-8 SRM 51-1-24 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: WEB — CORRODED (BS 270-280)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON WEB ON TORQUE BOX AT LONGERON 31R AT STA 270O 280. DAMAGED BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED WEB IAW DAC DWG 5753892. LOCATED HOLES IN NEW WEB IAW DC-8 SRM 51-1-24 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOORBEAM — CORRODED (BS 1480)

DURING A MAINTENANCE VISIT, FOUND INBOARD FLANGE OF FLOORBEAM AND FRAME, STRUT WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 1480, BLR. REMOVED DAMAGED SECTION, TREATED AREA IAW DC08 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05094.

Part: WEB — CORRODED (BS 270-280)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON WEB ON TORQUE BOX AT LONGERON 31R AT STA 270O 280. DAMAGED BEYOND LIMITS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED WEB IAW DAC DWG 5753892. LOCATED HOLES IN NEW WEB IAW DC-8 SRM 51-1-24 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 1050-1084.5)

DURING A MAINTENANCE VISIT, FOUND SKIN/PLATING WITH CORROSION DAMAGE BEYOND LIMITS IAW DC-8 SRM, AT STA 1050 TO 1084.5 AND LONGERON 35 LEFT. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05103.

Part: FLOORBEAM — CORRODED (BS 1320)

DURING A MAINTENANCE VISIT, FOUND INBOARD FLANGE OF FLOORBEAM AND FRAME, STRUT WITH CORROSION DAMAGED BEYOND LIMITS IAW DC-8 SRM AT STA 1320, BLR. REMOVED DAMAGED SECTION, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TIMCO DER ENGINEERING SKETCH REO-05111.

Part: FITTING — DAMAGED (BS 980)

DURING A MAINTENANCE VISIT, FITTING (P/N 5615040-2), AT STA 980 AND LONGERON 22 RIGHT FOUND DAMAGED. REMOVED FITTING, FABRICATED NEW FITTING BY MATERIAL SUBSTITUTION. ORIGINAL MATERIAL 7075-T411, SUBSTITIUTED WITH 7075T-T6 IAW FAA APPROVED TIMCO ENGINEERING SKETCH REO-05079. FABRICATED AND INSTALLED NEW FITTING IAW DWG 56150T0 AND DWG 5615041 AND DPS4.999.

Part: SPLICE — CORRODED (BS 50-280)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON FLOOR BOARD SPLICE AT MAIN CABIN STA 50 TO 280, LBL AFT 62. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED AND INSTALLED NEW SPLICE IAW DAC DRG 5892159 AND DC8 SRM 51-3-2. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: SPLICE — CORRODED (BS 50-250)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON FLOOR BOARD SPLICE CLIP AT MAIN CABIN STA 50 TO 280, BL 55. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED AND INSTALLED NEW SPLICE IAW DC8 SRM 3-53-7-3 FIG 3E AND DC8 SRM 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: SPLICE — CORRODED (BS 580-880)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON FLOOR PANEL G SPLICE ANGLES AT STA 580 TO 880, LBL 20. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED AND INSTALLED NEW SPLICES IAW DAC DWG 5892159. INSTALLED AAW DC8 SRM 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: SPLICE — CORRODED (BS 880-1000)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON TWO SPLICE CLIPS AT MAIN CABIN STA 880 TO 1000, LBL AFT 62. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED TWO SPLICE CHANNELS IAW DAC DWG 5892159. INSTALLED GANG CHANNEL ANCHOR NUTS IAW DC8 SRM 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: ANGLE — CORRODED (BS 1060-1080)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON T ANGLE IN AFT PIT AT STA 1060 TO 1080, LONG 35L. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED NEW ANGLE IAW DC8 SRM 51-1-8, 51-1-22, AND DAC DWG 9758507. TO BE INSTALLED ON N/R 40776. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORRODED (BS 578-580)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON FRAME TO CUSP FITTING AT MAIN CABIN STA 578 TO 580, BL 21R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. INSTALLED NEW FITTING IAW DC8 SRM 51-3-0 AND 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORRODED (BS 120)

DURING A MAINTENANCE VISIT, FOUND CORROSION ATTACH POINT ON RT FRAME ATTACH FITTING AT STA 120, BL 21R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. DRILLED NEW FITTING IAW DAC DWG 4597643 AND DC8 SRM 51-3-2. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORROSION (BS 458-460)

DURING A MAINTENANCE VISIT, FOUND CORROSION FRAME TO CUSP FITTING SHIM IN MAIN CABIN AT STA 458 TO 460, BL 21R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: SPLICE — CORRODED (BS 1000-1300)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON FLOOR BOARD SPLICE AT MAIN CABIN PLANK G STA 1000 TO 1300, BL 30R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED AND INSTALLED NEW SPLICE IAW DAC DWG 5892159. INSTALLED IAW DC8 SRM 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FRAME — CORRODED (BS 478-480)

DURING A MAINTENANCE VISIT, FOUND CORROSION FRAME TO CUSP FITTING SHIM IN MAIN CABIN AT STA 478 TO 480, BL 21R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FRAME — CORRODED (BS 1540)

DURING A MAINTENANCE VISIT, FOUND CORROSION EMITTING FROM NUT PLATES ON FRAME CAP AT STA 1540, ABOVE 33L. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED FILLER, -15 FILLER AND -13 ANGLE. DRILLED NEW CAP IAW DC8 SRM 51-1-24. INSTALLED IAW RED-05214. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORRODED (BS 1195)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON C-3 DOOR BACKUP FITTING AT STA 1195, LONG 30R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. REPLACED FITTING WITH REPAIR FITTINGS IAW DC8 SRM 53-2-0 FIG 2D (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORRODED (BS 1180)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON DOOR BACKUP FITTING AT STA 1180, BL 30R DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. REMOVED AND REPLACED FITTINGS IAW DC8 SRM 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORRODED (BS 1210)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON C-3 DOOR BACKUP FITTING AT STA 1210, LONG 30R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. REMOVED AND REPLACED FITTING WITH REPAIR FITTINGS IAW DC8 SRM 53-2-0 FIG 2D (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FRAME — CORRODED (BS 1540)

DURING A MAINTENANCE VISI, FOUND CORROSION ON BULKHEAD FRAME ABOVE AFT ACCESSORY COMPARTMENT DOOR AT STA 1540, LONG 35R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. REMOVED AND REPLACED WITH NEW SECTION OF FRAME IAW DC8 SRM 51-1-21, 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORRODED (BS 880)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON TOP OF FRAME FITTING AT STA 880, X+60, Z-10. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED AND INSTALLED NEW FITTING IAW DC8 SRM 53-7-1, 51-3-2, AND 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORRODED (BS 1170)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON C-3 DOOR BACKUP FITTING AT STA 1170, LONG 30R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. LOCATED AND DRILLED NEW FITTINGS IAW DC8 SRM 53-2-0 FIG 2D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: ANGLE — CORRODED (BS 960-940)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON KEEL BEAM, TOP AREA, AT STA 960 TO 940, X+6, Z-45. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR ANGLE IAW DAC DRG 5892159 AND DC8 SRM 53-2-0, 51-1-21, AND 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: KEEL BEAM — CORRODED (BS 900)

DURING A MAINTENANCE VISIT, FOUND CORROSION INSIDE KEEL BEAM (UPPER CORNER) AT STA 900, Z-36. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. FABRICATED REPAIR ANGLES FOR CRACKED ON WEB IAW DC8 SRM 51-2-0 FIG 1B. INSTALLED BRACKET, WEB, AND REPAIR ANGLES IAW DC8 SRM 51-1-8, 51-1-21, AND 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORRODED (BS 1220)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON Z FITTING IN AFT PIT AT STA 1220, LONG 33R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. REMOVED AND REPLACED WITH NEW Z FITTING IAW DC8 SRM 53-2-0 FIG 2D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: FITTING — CORRODED (BS 1230)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON Z FITTING IN AFT PIT AT STA 1230, LONG 33R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8. REMOVED AND REPLACED WITH NEW Z FITTING IAW DC8 SRM 53-2-0 FIG 2D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)

Part: ANGLE — CORRODED (BS 1540)

DURING A MAINTENANCE VISIT, FOUND CORROSION ON BOTTOM AFT ACCESSORY DOOR LANDING AT STA 1540, LONG 34L TO 34R. DAMAGE EXCEEDED LIMITATIONS IAW DC8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC8 SRM 51-1-8.INSTALLED REPAIR ANGLE IAW DC8 SRM 51-1-21. INSTALLED GIL LINER ATTACH ANGLE IAW SRM DC8-51-1-21A. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM.)