N606AL

Part: CONNECTOR — DIRTY (LANDING LIGHT) · airframe 99,822 hrs · 33,155 cycles

ON FINAL APPROACH WITH LANDING GEAR LEVER DOWN, RT LANDING LIGHT DID NOT ILLUMINATE. THE CREW CYCLED THE GEAR AND GEAR LIGHT ILLUMINATED 10 SECONDS AFTER GEAR CYCLE. THEY LANDED WITHOUT FURTHER INCIDENT. MX REMOVED AND CLEANED THE CONNECTOR PLUG ON THE DOWN LIMIT SWITCH. OPS CHECK GOOD IAW MM 32-60-0. ACFT WAS RETURNED TO SERVICE.

Part: MEC — DEFECTIVE (ZONE 400) · airframe 99,396 hrs · 32,989 cycles

AT THE TOP OF CLIMB OUT AT FLIGHT LEVEL 36,000 FT WHEN THROTTLES WERE PULLED BACK FROM CLIMB POWER TO CRUISE POWER NR 3 ENG MOMENTARILY COMPRESSOR STALLED. ALL OTHER ENGINES PARAMETERS WERE NORMAL AND NR 3 COMPRESSOR STALLED AGAIN 10 MINUTES LATER AT CRUISE WHEN THROTTLES WERE PULLED BACK FOR DESCENT FROM 36.0 TO 35.0. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED (MEC), OPS CHECK GOOD IAW MM 73-20-1, AERT 73.01.09.01. ACFT WAS RETURNED TO SERVICE.

Part: SENSOR — DEFECTIVE (ZONE 400) · airframe 99,360 hrs · 32,982 cycles

DURING CRUISE NR 3 ENG COMPRESSOR STALLED. CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED (CIT) SENSOR. OPS CHECK GOOD IAW CFM MM 73-21-20. ACFT WAS RETURNED TO SERVICE.

Part: ENGINE — FLAMED OUT (NR 3) · airframe 99,269 hrs · 32,949 cycles

AFTER TAKEOFF, WHEN THROTTLES WERE RETARDED AT FL 37.0 NR 3 ENGINE FLAMED OUT. BEFORE THE CREW COULD ACCOMPLISH FLAME OUT CHECK LIST, THE ENG RELIT WITH NO PROBLEMS THE REMAINDER OF THE FLIGHT, LANDED WITHOUT FURTHER INCIDENT. MX ACCOMPLSHED TREE FAULT 51 WITH NO FAULT FOUND, REPLACED FUEL FILTERS AND CLEANED CDP TUBE. OPS CHECK GOOD IAW MM 71-00-00, 73-11-10, ERH 70.01, CFM 73-21-10 AND GMM 3.124. ACFT WAS RETURNED TO SERVICE.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 99,104 hrs · 32,889 cycles

DURING TAKEOFF ROLL, ACFT PULLED HARD LEFT. CREW WAS UNABLE TO MAINTAIN DIRECTIONAL CONTROL WITH FULL RT RUDDER. THEY ABORTED TAKEOFF AND RETURNED TO BLOCKS WITH OUT FURTHER INCIDENT. MX INSPECTED THE NOSE GEAR, WHEELS, BRAKES, NOSE WHEEL STEERING, NOSE STEERING ACCUMULATOR, RUDDER FEEL AND ACCOMPLISHED REJECTED TAKEOFF INSP WITH NO DEFECTS NOTED. ACFT WAS RETURNED TO SERVICE.

Part: SPAR CAP — CRACKED (RT WING) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP FOUND RT WING T/E SPAR CAP UPPER PART CRACKED AT STA XRS 74.000. REMOVED CRACKED UPPER SPAR CAP. FABRICATED NEW UPPER SPAR CAP. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. INSTALLED NEW UPPER SPAR CAP IAW DWG 5611440, 5616128, 5615057, SRM 57-1-0 PAGE 1, SRM 51-1-20D, SRM 51-3-0, SRM 51-1-8B, DWG 5611440, 5616128, & 5615057, SRM 51-9-0, SRM 51-3-1, REPAIR SPEC NR 2003-05 AND FORM 07 IPI NR 2010643.

Part: SKIN — CRACKED (ZONE 500) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND LT WING OUTER WING OTBD L/E LOWER SKIN CRACKED AT STA XFS 847.500. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. PERFORMED NDT INSP. NO CRACKS OR CORROSION NOTED. FABRICATED NEW SKIN, FILLERS AND DOUBLERS. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 10/15/10, DWG ED-5259 DATED 09/28/10, EO 2010571, SRM 51-1-20D, SRM 51-1-21, NDT SPM PART 06, . SRM 57-2-0, SRM 51-1-4, SRM 51-1-8B, SRM 51-1-11, SRM 51-1-20D, SRM 51-1-26, SRM 51-1-21, SRM 51-1-22, SRM 51-3-1, AND SRM 51-3-2.

Part: SUPPORT ANGLE — CORRODED (ZONE 600) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND RT WING UPPER PANEL SUPPORT ANGLE CORRODED AT STA XW 5.000. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED ANGLE. FABRICATED NEW ANGLE. CLEANED, TERATED, AND PRIMED AREA. INSTALLED NEW FASTENERS AND NEW ANGLE IAW SRM 51-1-8, SRM 57-2-0, SRM 51-1-21, SRM 51-1-8B, SRM 51-1-21 AND SRM 57-2-0 AND SMN FORM NR 2010639.

Part: SKIN — DAMAGED (LT WING) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND LT WING NR 2 STUB WING LOWER SKIN ELONGATED HOLES AT STA XFS 247.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED SPLICE DOUBLER AND NEW SKIN. PERFORMED NDT INSP. NO CRACKS OR CORROSION NOTED. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 10/19/10, DWG ED-5258, DATED 09/24/10, SRM 57-2-0, SRM 57-3-3, SRM 51-1-4, NDT PART 06, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-22, SRM 51-1-26, SRM 51-1-11, SRM 51-1-15, SRM 51-1-20D, SRM 51-3-1, AND SRM 51-3-2.

Part: SKIN — CRACKED (LT WING) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP FOUND LT WING NR 2 STUB WING LOWER SKIN CRACKED AT STA XFS 200.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED SPLICE DOUBLER AND NEW SKIN. PERFORMED NDT INSP. NO CRACKS OR CORROSION NOTED. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 10/19/10, DWG ED-5258 DATED 09/24/10, SRM 57-2-0, SRM 57-3-3, SRM 51-1-4, NDT PART 06, SRM 51-1-8B, SRM 51-1-21, SRM 51-1-22, SRM 51-1-26, SRM 51-1-11, SRM 51-1-15, SRM 51-1-20D, SRM 51-3-1, AND SRM 51-3-2.

Part: FITTING — CRACKED (BS 1370 L31L) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND AFT CARGO COMPARTMENT SPLICE FITTING CRACKED AT STA 1370.000, LONGERON 31 LT. R & R SPLICE FITTING IAW SRM 51-1-20D AND SRM 51-3-1.

Part: FITTING — CRACKED (LT WING) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND LT WING T/E UPPER FITTING CRACKED AT STATION XRS 409.000. R & R CRACKED FITTING IAW SRM 51-1-21.

Part: FITTING — CRACKED (ZONE 100) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND AFT CARGO COMPARTMENT SPLICE FITTING CRACKED AT STA 1390.000 LONGERON 30 LT. REMOVED CRACKED FITTING. FABRICATED NEW SPLICE FITTING. CLEANED, TREATED, PRIMED AREA AND SPLICE FITTING. INSTALLED NEW SPLICE FITTING IAW SRM 53-2-0, SRM 51-1-8B, SRM 51-1-20D AND SRM 51-3-1.

Part: SKIN — CRACKED (LT AILERON) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND LT OTBD AILERON LOWER SKIN CRACKED AT STA 761.695. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED SKIN. FABRICATED NEW SKIN AND DOUBLERS BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. PERFORMED LT OTBD AILERON BALANCE. FOUND WITHIN LIMITS MOMENT 3329.9 IN-LBS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-21, SRM 57-1-0 PAGE 1, SRM 57-8-1 FIG 4, ITEM "E", "L", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, SRM 51-1-21, AND SRM 51-4-3, PAGES 1-3.

Part: FRAME — CRACKED (BS 1580 L20-21R) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP FOUND MAIN CARGO COMPARTMENT FRAME FLANGE CRACKED AT STA 1580.000 LONGERON20-21 RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED FRAME. FABRICATED FRAME SEGMENT. PERFORMED HEAT TREATMENT. CLEANED,TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAP 53-2-0 FIG 2, SRM 53-2-0, SRM 51-1-21, SRM 51-1-20D, SRM 53-2-0 FIG 2, SRM 51-1-1, SRM 51-1-8B, SRM 53-2-0 FIG 2, SRM 51-1-20D, AND SRM 51-3-1.

Part: DOUBLER — CRACKED (ZONE 500) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP FOUND LT WING NR 2 STUB WING EXTERNAL LOWER REPAIR DOUBLER CRACKED. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED DOUBLER. FABRICATED EXTERNAL AND INTERNAL DOUBLERS. PERFORMED HEAT TREATMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 57-2-1A FIG 1, SRM 57-2-0, SRM 57-2-1A, SRM 51-1-1, DPS 7.00-1 REV "BL", SRM 51-1-8B, SRM 51-1-20D AND SRM 51-3-1.

Part: SKIN — CRACKED (LT WING TE FLAP) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP FOUND LT WING INBD FLAP LOWER EXTERNAL SKIN CRACKED AT STATION XCW 64.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED SKIN. FABRICATED NEW SKIN AND DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED PANEL NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-21, SRM 57-1-0 PAGE 1, SRM 57-7-1 FIG 1 ITEMS "A" - "L", DPS 4.710 REV "L", DPS 57-2-0, SRM 51-1-9, TR 51-142, SRM 51-1-9A, TR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, AND SRM 51-1-21.

Part: SKIN — CORRODED (RT WING TE FLAP) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP FOUND RT OTBD FLAP UPPER SKIN CORRODED AT STATION XF 304.000 - 333.0000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORRODED SKIN. FABRICATED NEW SKIN AND DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-21, SRM 57-1-0 PAGE 1, SRM 57-7-1, FIG 4, TR 57-94 ITEM "P", "Q", DPS 4.710 REV "L", SRM 51-1-9 TR 51-142, SRM 51-1-9A TR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, AND SRM 51-1-21.

Part: WEB — CRACKED (NR 4 PYLON) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP FOUND NR 4 PYLON TEE DOUBLER HORIZ FLANGE CRACKED IN UPPER INTERNAL PART AT STA YN 335.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO CRACKS OR CORROSION NOTED. FABRICATED SPACER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8100-9 DATED 10/18/10, CASTLE SKETCH 201009240156-001, DWG ED-5257, DATED 09/23/10, SRM 51-1-20D, NDT SPM PART 06-10-01-001, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND LT WING INBD FLAP UPPER EXTERNAL SKIN DENTED AT STATION XW 104.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-21, SRM 57-1-0 PAGE 1, SRM 57-7-1 FIG 1 ITEM "D", DPS 4.710 REV "L", SRM 51-1-4, DPS 3.69-5 REV "U", SRM 51-1-8B, AND SRM 51-1-21.

Part: SUPPORT FITTING — CRACKED (ZONE 700) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP FOUND RT WING MLG SUPPORT FITTING EXTERNAL FACE CRACKED. R & R RT MLG SUPPORT FITTING IAW AD 89-10-04, DACO S/B, DC8-57-094, REV 04 DATED 03-24-2000, DWG 5611021, 5611440, 5611425, 5616128, 5641112, 5893930, AND EO NR 2010556.

Part: SKIN — WORN (LT WING TE FLAP) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP FOUND LT WING INBD FLAP UPPER EXTERNAL SKIN WORN AT STA XW 104.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN AND BONDED DOUBLERS. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAP 57-7-1 FIG 1, SRM 51-1-21, SRM 57-1-0 PAGE 1, SRM 51-1-9 TR 51-142, 51-1-9A TR 51-141, DPS 1.950 REV "AR" R-1, SRM 51-1-8B, AND SRM 51-1-21.

Part: SKIN — CORRODED (ZONE 100) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND EXTERNAL FUSELAGE LOWER PART BUTT JOINT SKIN CORRODED AT STA 1690.000 BETWEEN LONGERON 34 RT- LONGERON 34 LT. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED AREA. FABRICATED NEW SKIN, DOUBLERS, FINGER DOUBLERS AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW SRM 53-2-1 FIG 7 SHEETS 5/23/24 TR 53-203, SRM 51-1-8, SRM 53-2-0, SRM 51-1-8B, SRM 51-1-20D, SRM 51-1-21, 51-1-11, AND SRM 51-3-1.

Part: SKIN — WORN (RT WING TE FLAP) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND RT INBD FLAP SKIN WORN AT STA XW 104.000 - 115.0000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-21, SRM 57-7-1, AND SRM 51-1-8B.

Part: DOUBLER — MISREPAIRED (BS 1560 L20R) · airframe 98,880 hrs · 32,802 cycles

DURING ROUTINE C-CHECK INSP, FOUND IMPROPER REPAIR AT STATION FS 1560, LONGERON 20.5 RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. FABRICATED NEW SKIN, INTERNAL AND EXTERNAL DOUBLERS AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM CHAPTER 52-2-1 PAGE 10, SRM 51-1-20D, SRM 53-2-1 FIG 10 SHEETS 1-2 TR 53-204, FIG 7 SHEETS 7,23-24, TR 53-203, SRM 51-1-8B, SRM 51-1-20D, AND SRM 51-3-1.

Part: SWITCH — BROKEN (MLG) · airframe 98,869 hrs · 32,796 cycles

DURING CLIMBOUT, AFTER GEAR RETRACTION, THE "DOOR NOT LATCH" LIGHT REMAINED ON. CREW CYCLED THE GEARS AND WAS UNABLE TO DETERMINE CONDITION OF MAIN GEAR DOORS. THEY CONTINUED FLIGHT AND LANDED WITHOUT FURTHER INCIDENT. MX INSPECTED THE MAIN GEAR DOOR WARNING SYS AND FOUND THE RT MAIN GEAR DOOR SWITCH ARM BROKEN. THEY REPLACED SWITCH. OPS CHECK GOOD IAW MM 32-60-0, PAGE 201. ACFT WAS RETURNED TO SERVICE.

Part: GENERATOR — FAILED (ZONE 400) · airframe 98,259 hrs · 32,460 cycles

DURING CLIMB OUT FROM DEPARTURE NR 3 GENERATOR BUSS FAILURE, VOLTS AND FREQUENCIES AT ZERO. THE CREW ACCOMPLISHED COM PROCEDURES AND RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX RESET NR 3 GENERATOR BUS FAULT RESET SWITCH. OPS CHECK GOOD IAW MM 24-20-0. ACFT WAS RETURNED TO SERVICE.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 97,970 hrs · 32,302 cycles

DURING INSP IAW AD2007-21-18 AND SB DC8-53A081 FOUND AFT PRESSURE BULKHEAD TEE FITTING CRACKED AT LONGERON 9 RT TO LONGERON 10 RT. STOP DRILLED CRACK IAW SRM 53-2-5.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 97,970 hrs · 32,302 cycles

DURING INSP IAW AD2007-21-18 AND SB DC8-53A081 FOUND AFT PRESSURE BULKHEAD TEE FITTING CRACKED AT LONGERON 11 LT TO LONGERON 13 LT. STOP DRILLED CRACK IAW DACO DC8 SRM 53-2-5.

Part: CABLE — DEFECTIVE (ZONE 400) · airframe 97,715 hrs · 32,185 cycles

DURING CLIMB-OUT FROM KTOL NUMBER TWO ENGINE EGT WENT TO 914 DEGREE FOR TWO TO FIVE SECONDS. THE CREW RETARDED THE THROTTLE AND EGT INDICATOR DECREASED AND ALL OTHER ENGINES PARAMETER WERE NORMAL. THE CREW RETURNED TO KTOL AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE PERFORMED TROUBLESHOOTING FOR FAULT NUMBER 48, AND FOUND VSV CABLE TRAVEL CHECK FAILED. MAINTENANCE REPLACED VSV CABLE. OPERATIONAL CHECK GOOD IAW MAINTENANCE MANUAL 75-32-20. AIRCRAFT WAS RETURNED TO SERVICE.

Part: TUBE — CLOGGED (NR 2 ENGINE) · airframe 97,541 hrs · 32,104 cycles

DURING DESCENT INTO ETAR NUMBER 2 ENGINE FLAME OUT. WITH THROTTLE REDUCTION, MILD VIBRATION, AND FUEL FLUCTUATION. THE CREW LANDED IN ETAR WITHOUT FURTHER INCIDENT. MAINTENANCE ACCOMPLISHED CFM TROUBLESHOOTING TREE FAULT 51 AND FOUND CDP TUBES CLOGGED. MAINTENANCE CLEANED TUBES. OPERATIONAL CHECK GOOD IAW CFM MAINTENANCE MANUAL 73-21-00, 71-00-00. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FIRE LOOP — SHORTED (ZONE 400) · airframe 96,585 hrs · 31,702 cycles

DURING CRUISE FROM KTOL, NUMBER THREE ENGINE FIRE WARNING LIGHT AND BELL CAME ON INTERMITTENTLY. THE CREW ACCOMPLISHED THE ENGINE FIRE CHECKLIST AND DISCHARGED BOTH BOTTLES. AFTER BOTH BOTTLES WERE DISCHARGED THE FIRE WARNING CAME ON STEADY AND STAYED ON JUST PRIOR TO LANDING. THE CREW LANDED IN KICT WITHOUT INCIDENT. MAINTENANCE INSPECTED NUMBER THREE ENGINE INTERNALLY AND REPLACED LEFT AND RIGHT FIRE LOOP CORE DETECTOR, AND LEFT AND RIGHT FIRE LOOP FAN DETECTOR'S. MAINTENANCE ALSO REPLACED BOTH FIRE BOTTLES. OPERATIONAL CHECK GOOD IAW DACO DC-8 MAINTENANCE MANUAL 26-00, 26-10-0, AND 26-20-1. AIRCRAFT WAS RETURNED TO SERVICE.

Part: SWITCH — DEFECTIVE (MLG DOOR) · airframe 96,268 hrs · 31,574 cycles

DURING CLIMB FROM KTOL, AFTER GEAR WAS RETRACTED DOOR NOT LATCH LIGHT CAME ON, THE CREW CYCLED THE GEAR THE LIGHT STAYED ON. THE CREW ACCOMPLISHED UPLATCH CHECK AND CYCLED THE GEAR A SECOND TIME THE LIGHT STAYED ON. THE CREW CLIMB TO 32,000 FEET CYCLED THE GEAR A THIRD TIME IN LEVEL FLIGHT AND LIGHT STAYED ON, THE LIGHT IS EXTINGUISHED WITH GEAR EXTENDED. THE CREW RETURNED TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED GEAR DOOR SWITCH IAW DACO DC-8 MAINTENANCE MANUAL 32-60-0. OPERATIONAL CHECK GOOD. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FITTING — CORRODED (BS 80) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO LT CUSP EXTRUSION, FITTING WITH CORROSION AT STA 80.000, L-21L.

Part: STRUCTURE — MISREPAIRED (BS 1345 L30L) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, FS 1345, LONGERON 30.5 LEFT. DOUBLER BELOW AND AFT OF AFT EMERGENCY EXIT DOOR. REPAIR NUMBER 606 AL-R36. PROBLEM: SIDE 2, 2ND ROW EXCEEDS MAS RIVET SPACING. DISPOSITION: ADD RIVETS TO BRING INTO LIMITS OR UPGRADE.

Part: LONGERON — MISREPAIRED (BS 1367 L30L) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, FS 1367, LONGERON 30.5 LEFT, DOUBLER BELOW AND AFT OF AFT EMERGENCY EXIT DOOR. REPAIR NUMBER 606AL-R37. PROBLEM: SIDE 2 ENDS ON LONGERON WITHOUT FINGER DOUBLER. DISPOSITION: UPGRADE IAW SRM.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, LT HORIZONTAL STABILIZER, POINTS OF CORROSION ON UPPER SKIN FROM STA XE 28.843 TO STA XE 30.000.

Part: SPAR — CRACKED (RT WING) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, NR 1 MAIN TANK CTR SPAR WEB LWR SIDE, CRACK 4" AT STA XRS 255.000 BETWEEN S-61 AND S-62.

Part: FITTING — CRACKED (ZONE 100) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO CMPT AFT FITTING SHOWS CRACK 2" BETWEEN STA 1220.000 AND L-19R. REPLACED CRACKED FITTING WITH NEW FITTING IAW DC8 SRM 51-1-20D.

Part: FITTING — CRACKED (BS 1152 L20R) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO CMPT FWD FITTING SHOWS CRACK 1" BETWEEN STA 1152.000 AND L-20R.

Part: SPAR — CRACKED (RT WING) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, NR 1 MAIN TANK, CTR SPAR LWR CAP, CRACKED 3" AT STA XRS 255.000 BETWEEN S-61 AND S-62.

Part: LONGERON SPLICE — CRACKED (BS 1690 L36) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO CMPT LONGERON SPLICE FITTING CRACKED AT STA 1690.000 L-36.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD FLAP UPPER SKIN SHOWS DENT AT XW 88.000.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INNER FLAP, UPPER SKIN SHOWS DENT BETWEEN STA XF 112.000 TO STA XF 120.000.

Part: SPAR — CRACKED (WING) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, NR 2 MAIN TANK WEB OF CENTRAL SPAR (LWR SIDE) CRACKED 2 1/2" AT STA XRS 172.000 BETWEEN S-61 AND S-62.

Part: FITTING — CRACKED (BS 759 L18L) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO CMPT AFT FITTING SHOWS CRACK 2" AT STA 759.000 AND L-18.8L.

Part: SPAR CAP — CRACKED (WING) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, NR 2 MAIN TANK LOWER CAP OF CENTER SPAR 3" CRACKED AT STA ZRS 172.000 BETWEEN S-61 AND S-62.

Part: FITTING — CRACKED (HORIZONTAL STAB) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, RT HORIZ STABILIZER FITTING SHOWS CRACK 2" FRONT PART AT STA NFS 60.000.

Part: SKIN — DENTED (RT ELEVATOR) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, RT ELEVATOR OIL CANNING LOWER PANEL, PLATING AT STA XE 279.000 STA XE 306.000.

Part: BEAM — DENTED (BS 50) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, ACCESS CMPT CORROSION ON BEAM AT STA 50.000 AND RBL 35".

Part: FLOORBEAM — CRACKED (BS 180) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, FWD BELLY PIT UPPER FLANGE OF FLOORBEAM, CRACKED AT STA BS 180.000, RBL 46".

Part: STRUCTURE — CRACKED (NLG DOOR) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, RT AFT NLG DOOR, AFT DOOR STRUCTURE ATTACH ARM HAS CRACK FWD UPPER AREA (CRACKS IN FILLER PNL NOT DOOR HINGE) FILLER PNL REMOVED.

Part: BULKHEAD — CRACKED (BS 1766 S9-10L) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, AFT BULKHEAD.-TEE CAP OF LT SIDE PRESS WALL UPPER PART BETWEEN L-9L AND L-10L, STA 1766.000 SHOWS CRACK 1".

Part: SKIN — DENTED (BS 97-103) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, HORIZ STABILIZER EMPENNAGE INBD L/E EXT SKIN SHOWS (01EA) DENTS AT STA XFS 97.500 AND STA XFS 103.000.

Part: SKIN — DENTED (LWS 247) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING NON STANDARD REPAIR ON INBD SLOT VANE AT STA XS 247.000.

Part: SKIN — CORRODED (RUDDER) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, RUDDER EXT SKIN WITH CORROSION AT STA ZR -253.000 RT SIDE.

Part: SKIN — DENTED (BS 980) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, EXT FUSELAGE UPPER SKIN WITH DENT AT STA FS 980.000 AND L-7 LT.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING OTBD FLAP LWR SKIN PANEL SHOWS (04EA) DENTS BETWEEN STA XF 415.000 AND STA XF 453.000.

Part: SKIN — CORRODED (RUDDER) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, RUDDER EXT SKIN WITH CORROSION AT STA ZR -162.000 RT SIDE.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD FLAP UPPER FWD PLATING SHOWS DENT BETWEEN STA XW 28.000 TO STA XW 91.000.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING OTBD FLAP AFT PANEL PLATING LWR SKIN SHOWS (04EA) DENTS BETWEEN STA XF 415.000 AND STA XF 453.000.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING OTBD FLAP AFT PANEL LWR SKIN SHOWS (03EA) DENTS BETWEEN STA XF 375.000 AND STA XF 405.000.

Part: SKIN — MISREPAIRED (RT WING TE FLAP) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING INB FLAP PANEL LWR SKIN SHOWS (03EA) NON STANDARD REPAIR FROM STA XW 2.000 TO STA XW 92.000.

Part: SKIN — MISREPAIRED (RT WING TE FLAP) · airframe 95,905 hrs · 31,424 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING INBD FLAP UPPER SKIN SHOWS NON STANDARD REPAIR AND DENT BETWEEN STA XW 2.000 AND STA XW 92.000.

Part: PROXIMITY SWITCH — DEFECTIVE (MLG DOOR) · airframe 95,510 hrs · 31,205 cycles

AFTER GEAR RETRACTION,THE LANDING GEAR DOORS NOT LATCHED LIGHT ILLUMINATED. THE CREW RECYCLED THE GEAR AND THE LIGHT REMAINED ON, UNTIL THE GEAR WAS EXTENDED. THE CREW CONTINUED AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE GEAR AND FOUND SEVERAL LOOSE HI-LOKS ALONG THE KEELBEAM TEE FITTINGS. MAINTENANCE REPLACED THE LOOSE HI-LOKS AND ALSO REPLACED THE LT PROXIMITY SWITCH. THE OPERATIONAL CHECK WAS GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: DOOR SEAL — DAMAGED (NLG) · airframe 95,481 hrs · 31,177 cycles

AFTER TAKEOFF OUT OF KIAH, THE CREW FELT A SEVERE VIBRATION AND LOUD NOISE COMING FROM THE NOSE GEAR AREA, WITH THE GEAR UP OR DOWN. THE CREW RETURNED TO KIAH AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE LANDING GEAR AND FOUND THE LEFT FORWARD NOSE GEAR DOOR SEAL AFT HALF MISSING. MAINTENANCE REMOVED REMAINING GEAR DOOR SEAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: DOOR — LACK OF LUBE (LANDING GEAR) · airframe 95,476 hrs · 31,173 cycles

AFTER TAKEOFF FROM KPHL UPON RAISING THE GEAR, THE DOORS "NOT LATCH" LIGHT REMAINED ON. THE CREW CYCLED GEAR PER THE CHECKLIST "DOORS NOT LATCH LIGHT "ON, WITH EXCESSIVE VIBRATION AND NOISE GEAR NOT LATCH "LIGHT" CAME ON. THE CREW RETURNED TO KPHL AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE LANDING GEAR AND LUBED THE NOSE LANDING GEAR AND DOORS, LUBED MAIN LANDING GEAR UP-LATCH MECHANISMS. MAINTENANCE INSPECTED THE SWITCHES, JACKED THE AIRCRAFT AND CYCLED GEAR SEVERAL TIMES IAW DACO DC8 MM 32-30-0, THE OPERATIONAL CHECK WAS GOOD.

Part: REPAIR — MISINSTALLED (ZONE 100) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C-CHECK INSPECTION, EXTERNAL FUS FREON AFT + FWD LWR CORNER EXTERNAL IS NOT IAW SRM, STA 45.000 L-30L. PERFORMED MAJOR REPAIR IAW DC8 SRM 53-2-0 FIG 13. REMOVED NON STANDARD REPAIR IAW DC8 SRM 51-1-20D, DC-8 SRM 51-3-0. REMOVED DAMAGED AREA IAW DC8 SRM 53-2-0 FIG 13 (SHEET 1). FABRICATED REPAIR DOUBLER (AL 2024 T3 0.071) + FILLER (AL 2024 T3 0.063) IAW DC8 SRM 53-2-0 FIG 13 (SHEET 1, 5) DC-8 SRM 53-2-0 FIG 13 T/R 53-169. CLEANED, TREATED, PRIMED AREA + REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 53-2-0 FIG 13 (SHEET 1, 5) DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).

Part: SUPPORT — CRACKED (LT TE FLAP) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C-CHECK INSPECTION, LT FLAP SUPPORT, STA 3.000 CRACKED 4. REMOVED AND REPLACED SUPPORT ASSY AT STA 3.000 (LT FLAP) IAW DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1, OPS CHECK.

Part: DRAIN MAST — PLUGGED (ZONE 100) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C-CHECK INSPECTION, INSTALLATION OF FWD LAV DRAIN MAST AT LWR CENTERLINE. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 ATI DWG H74-102 REV A, EO SEMAN 2006102 DATED 01-13-06. REMOVED EXISTING DRAIN MAST IAW DC8 SRM 51-3-0. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.125) IAW ATI DWG H74-102. CLEANED, TREATED AND PRIMED AREA & REPAIR DOUBLER IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED EXTERNAL REPAIR DOUBLER IAW ATI DWG H74-102, DC-8 SRM 51-3-0, DC8 SRM 51-3-1 (TORQUE).

Part: FITTING — CORRODED (BS 1308 L21L) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO MPT FITTING FRAME, BEAM CORRODED STA 1308.000 L21L. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 53-2-0 PAGE 2P. REMOVED CORRODED FITTING IAW DC-8 SRM 51-1-20D. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-20D, DC-8 SRM 51-3-0, DC-8 SRM 51-3-1 (TORQUE).

Part: SKIN — DAMAGED (T/E FLAP) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C CHECK INSPECTION, RT IB FLAP UPPER SKIN HAS INTERN REPAIR XW 105.000. PERFORMED MAJOR REPAIR IAW SRM 57-7-1 PAGE 1. REMOVED DAMAGED PLATING SEGMENT IAW SRM 57-1-0 PAGE 1, SRM 51-1-21. FABRICATED NEW PLATING SEGMENT (AL2024T3 0.040”) IAW SRM 57-7-1 FIG 1 ITEM (D). CLEANED, TREATED AND PRIMED AREA + INNER FACE OF NEW PLATING SEGMENT IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED NEW PLATING SEGMENT IAW SRM 51-1-21.

Part: SKIN — DENTED (T/E FLAP) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C-CHECK INSPECTION, RT OUTBOARD FLAP SKIN LWR PART DENTED AT SEVERAL SPOTS XF 345.000 - XF 404.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-7-1 FIG 4, TR 57-94 DATED 10-01-02. REMOVED DAMAGED PLATING IAW DC8 SRM 57-1-0, DC-8 SRM 51-1-21. FABRICATED NEW PLATING IAW DC-8 SRM 57-7-1 FIG 4 ITEM A (ALCLAD 2024 T3 0.050). CLEANED, TREATED, PRIMED AREA AND NEW PLATING INTERNAL PARTS IAW DC8 SRM 51-1-8B. APPLIED NEW SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED NEW PLATING IAW DC8 SRM 51-1-21.

Part: FRAME — CORRODED (FUSELAGE) · airframe 94,114 hrs · 30,547 cycles

DURING C-CK, ALT CARGO MPT FRAME CORRODED STA 13.000 L.35R L.35 L.. PERFORMED REPAIR. REMOVED FASTENERS. REMOVED CORROSION. FOUND OUT OF LIMITS. TRIMMED OUT CORRODED FRAME SEGMENT. FABRICATED NEW FRAME SEGMENT, FABRICATED ANGLE & SPLICE IAW SRM. CLEANED, TREATED, PRIMED AREA & REPAIR PARTS. APPLIED SEALANT TO FAYING SURFACES. INSTALLED REPAIR PARTS. ALL WORK PERFORMED IAW APPLICABLE SRMS.

Part: SKIN PANEL — CORRODED (L/E SLAT) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C-CHECK INSPECTION, OUTBOARD OUTER L/E CORRODED XFS 710.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-2-1 FIG 38, TR 5785 DATED 11-22-00. REMOVED CORROSION IAW DC8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-1 FIG 2G. REMOVED DAMAGED SECTION IAW DC8 SRM 57-2-1 FIG 38. FABRICATED REPAIR DOUBLER (AL 7075 T6 0.063) AND FILLER (AL 7075 T6 0.050) IAW DC8 SRM 57-2-1 FIG 38, DC-8 SRM 57-3-3-FIG 7 ITEM -F-. CLEANED, TREATED, PRIMED AREA AND INNER FACE OF REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 57-2-1 FIG 38, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-3-1.

Part: SKIN — DAMAGED (T/E FLAP) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C-CHECK INSPECTION, RIGHT OUTBOARD FLAP UPPER SKIN HAS INTERN REPAIR XF 210.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-2-1 FIG 2Q. REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED DAMAGED AREA. FABRICATED EXTERNAL REPAIR DOUBLER (AL2024T3 0.040) IAW DC8 SRM 57-2-1 FIG 2Q, DC8 SRM 57-7-1 FIG 4, TR 57-94 ITEM -C-. CLEANED, TREATED, PRIMED EXTERNAL REPAIR DOUBLER INTERNAL PARTS IAW DC8 SRM 51-1-8B. INSTALLED EXTERNAL REPAIR DOUBLER IAW DC8 SRM 57-2-1 FIG 2Q, DC8 SRM 51-1-9 (HYSOL), DC8 SRM 51-1-21.

Part: SKIN — CRACKED (STA 14.000) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C-CHECK INSPECTION, EXTERNAL FUSE HEAT EXCHANGER CORNER CRACKED STA 14.000 L27R. PERFORMED MAJOR REPAIR. REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED DAMAGED AREA IAW SEMAN DWG ED-4156. PERFORMED NDT INSPECTION IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FABRICATED REPAIR DOUBLER (ALCLAD 2024 T3 0.050) & REPAIR TRIPLER (ALCLAD 2024 T3 0.063) & FILLER (ALCLAD 2024 T3 0.100) IAW SEMAN DWG ED 4156. CLEANED, TREATED AND PRIMED AREA & REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4156, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1 (TORQUE).

Part: SKIN — DENTED (LT WING) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING UPPER SKIN SCRATCHED AND DENTED ON INBD FLAP BETWEEN XW 104.000 AND XW 122.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-7-1 PAGE 2. REMOVED DAMAGED PLATING IAW DC-8 SRM 57-1-0, DC-8 SRM 51-1-21. FABRICATED NEW PLATING (AL2024T3 0.040”) IAW DC8 SRM 57-7-1 FIG 1 ITEM “D”. CLEANED, TREATED AND PRIMED AREA + INNER FACE OF NEW PLATING IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED NEW PLATING IAW DC8 SRM 51-1-21.

Part: DOUBLER — WORN (WING) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C-CHECK INSPECTION, NR 1 STUB WING DOUBLER LWR PART WORN STA XOLDO 67.750. PERFORMED MAJOR REPAIR IAW SRM 57-2-1A FIG 1. REMOVED WORN DOUBLER IAW SRM 51-1-21, SRM 51-1-20D. PERFORMED STOP DRILL. FABRICATED EXTERNAL REPAIR DOUBLER IAW SRM 57-2-1A FIG 1. CLEANED, TREATED AND PRIMED AREA & INNER FACE OF EXTERNAL REPAIR DOUBLER IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED EXTERNAL REPAIR DOUBLER IAW SRM 57-2-1A FIG 1, SRM 51-1-21, SRM 51-1-20D, SRM 51-3-1.

Part: SKIN — DENTED (TE FLAP) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING OUTBOARD FLAP SKIN LWR PART DENTED 1 STA XF 390.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-2-5 FIG 2 (SHEET 3), TR NR 57-91 DATED 09-30-01. REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED DAMAGED SECTION. FABRICATED REPAIR DOUBLER (AL2024T3 0.040) IAW DC8 SRM 57-2-5 FIG 2 (SHEET 3), DC8 SRM 57-7-1 FIG 4 ITEM Q, U, TR#57-94 DATED. CLEANED, TREATED AND PRIMED REPAIR DOUBLER INNER FACE IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR DOUBLER IAW DC8 SRM 57-2-5 FIG 2 (SHEET 3, 4), DC8 SRM 51-1-1 (HYSOL), DC8 SRM 51-1-21.

Part: FITTING — CRACKED (BS 857.125) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C CHECK INSPECTION, LT MLG WW FITTING CRACKED STA 857.125 BETWEN L.23 AND L.24. REMOVED CRACKED FITTING IAW DC-8 SRM 51-1-20D. FABRICATED NEW FITTING IAW ATI REPAIR SPECIFICATION NR 2003-05, DWG DOUG NR 3646772. PERFORMED HEAT TREAMENT IAW DC-8 SRM 51-1-1 PAGES 1, 13, 17. PERFORMED NON-DESTRUCTIVE INSPECTION IAW NDT SPM PART 08-00-02 TO 07. CLEANED, TREATED AND PRIMED AREA, NEW FITTING IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-3-0, DC-8 51-1-20D AND DC-8 SRM 51-3-1 (TORQUED).

Part: BEAM — CRACKED (BS 1756) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C CHECK INSPECTION, NR 4 TRACK JOINT ANGLE WITH VERTICAL BEAM CRACKED 3, STA 1756.000 BL.0. REMOVED CRACKED JOINT ANGLE (FITTING) IAW DC-8 51-3-0. CLEANING, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW ANGLE (FITTING) IAW DC-8 SRM 51-3-0, DC-8 SRM 51-3-1 (TORQUE).

Part: SKIN — CRACKED (BS 1400) · airframe 94,114 hrs · 30,547 cycles

DURING C CHECK, EXT FUS D BELLY DOOR UPPER CORNER CRACKED ½ STA 1400.000 L.26. PERFORMED REPAIR IAW AD 2004-06-06, DOUG DWG SR 08530019, DWG 5750776, SB DC-8 53-078, DC-8 SRM 53-2-0. REMOVED FASTENERS IAW DC8 SRM 51-1-20D. TRIMMED OUT DAMAGED AREA IAW DC-8 SRM 53-2-0 FIG 21, DC-8 SRM 53-2-0 FIG 21 TR NR 53-140 DATE JANUARY 23, 2002. FAB`D REPAIR DOUBLER, REPAIR DOUBLER, FILLER IAW DC8 SRM 53-2-0 FIG 21, DC-8 SRM 53-2-0 FIG 21. TR NR 53-188 DATE 09-20-03, DC-8 SRM 53-4-1, DC-8 SRM 51-9-0. CLEANED, TREATED, PRIMED AREA, REPAIR PARTS IAW DC8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SRMS.

Part: SKIN — CRACKED (FUSELAGE) · airframe 94,114 hrs · 30,547 cycles

DURING C-CK, EXTERNAL FUS HEAT EXCHANGER CORNER WITH 03 CRACKS STA 14.000 STA 24.000 L27L. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 06018 DATE 01-17-06, SEMAN DWG NR ED 4155 DATE 01-11-06, EO SEMAN 2006040 DATE 01-17-06. REMOVED FASTENERS IAW DC-8 SRM 51-1-21. REMOVED DAMAGED AREA IAW SEMN DWG ED-4155. PERFORMED NDT INSPECT IAW DC-8 NDT IAW DC-8 NDT SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER + REPAIR TRIPLER + (03 EA) FILLERS IAW SEMAN DWG ED 4155. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4155, DC-8 SRM 51-1-21, DC-8 SRM 51-1-20D, DC-8 SRM 51-3-1.

Part: FLOORBEAM — CORRODED (STA 640.000) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO MPT. ATTACH FITTING FRAME AND FLOOR BEAN CORRODED STA 640.000 L.216. REMOVED CORROSION IAW SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SRM 53-2-0 PAGE 2P. REMOVED CORRODED FITTING IAW SRM 51-1-20D. CLEAN AND TREATED AND PRIMED AREA IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-1-20D, SRM 51-3-0, DC-8 SRM 51-3-1 (TORQUE).

Part: SKIN — DENTED (TE FLAP) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C-CHECK INSPECTION, DENT ON LWR SURFACE RT OUTBOARD FLAP STA XW 404.000 - 406.000. PERFORMED MAJOR REPAIR IAW DC8 SRM 57-2-5 FIG 2 (SHEET 2), TR 57-91 DATED 09-30-01. REMOVED FASTENERS IAW DC8 SRM 51-1-21. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER (AL 2024 T3 0.050) IAW DC8 SRM 57-2-5 FIG 2 (SHEET 2), DC-8 SRM 57-7-1 FIG 4 ITEM P, Q. CLEANED, TREATED, PRIMED AREA REPAIR DOUBLER INTERNAL PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC8 SRM 57-2-5 FIG 2 (SHEET 2, 4), DC8 SRM 51-1-9A (HYSOL), DC8 SRM 51-1-21.

Part: SKIN — DENTED (T/E FLAP) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE CORRECTIVE ACTION, PERFORMED MAJOR REPAIR IAW DC8 SRM 57-2-1 FIG 2Q. REMOVED FASTENERS IAW DC8 SRM 51-1-21. TRIMMED OUT DAMAGED AREA. FABRICATED EXTERNAL REPAIR DOUBLER (AL 2024 T3 0.040) IAW DC-8 SRM 57-2-1 FIG 2Q, DC-8 SRM 57-7-1 FIG 4, TR 57-94 ITEM -U & Q-. CLEANED, TREATED, PRIMED EXTERNAL REPAIR DOUBLER INTERNAL PARTS IAW DC8 SRM 51-1-8B. INSTALLED EXTERNAL REPAIR DOUBLER IAW DC8 SRM 57-2-1 FIG 2Q, DC8 SRM 51-1-9, DC8 SRM 51-1-21, DC8 SRM 51-3-1 (TORQUE). C-CHECK INSPECTION, SURFACE RT OUTBOARD FLAP STA XW427.000 430.000.

Part: FITTING — CRACKED (FUSELAGE) · airframe 94,114 hrs · 30,547 cycles

DURING ROUTINE C CHECK INSPECTION, MAIR CARGO MPT - NR 1 TRACK ATTACH FITTING CRACKED + FLOOR SUPPORT ANGLE CRACKED STA 1580.000 LBL.60. REMOVED CRACKED FITTING IAW SRM 51-3-0. FABRICATED NEW FITTING (ALCLAD 7075 T6 51) IAW ATI REPAIR SPECIFICATION NR 2005-05, DWG NR 5772399. PERFORMED HEAT TREAMENT IAW SRM 51-1-1 PAGES 1,13,17. PERFORMED NON DESTRUCTIVE INSPECTION IAW NDT SPM PART 08-00-02 TO 07. CLEANED, TREATED AND PRIMED AREA + NEW FITTING IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-3-0, DC-8 SRM 51-3-1 (TORQUED) THE FLOOR SUPPORT ANGLE IS NOT CRACKED BY EDDY CURRENT INSPECTION.

Part: INSULATOR — BROKEN (FIRE LOOP) · airframe 91,796 hrs · 29,929 cycles

DURING CRUISE FROM FJDG TO RJTY NR 2 ENGINE SHORT CIRCUIT LIGHT ILLUMINATED, NO ASSOCIATED FIRE WARNING OR BELL. FIRE WARNING WOULD NOT TEST. CREW PERFORMED A PRECAUTIONARY SHUTDOWN OF NR 2 ENGINE. SHORT CIRCUIT LIGHT EXTINGUISHED WITH ENGINE SHUTDOWN. CREW LANDED AIRCRAFT IN RJTY WITHOUT INCIDENT. MAINTENANCE CLEANED DIRT AND CORROSION FROM BOTH ENDS OF FIRE DETECTOR LOOPS. REVERSED BOTH CONNECTORS. ALSO FOUND BROKEN CLIP INSULATOR. REPLACED INSULATOR SYSTEM AND THE OPERATIONAL CHECK WAS GOOD PER ALL APPLICABLE MANUALS, AIRCRAFT WAS RETURNED TO SERVICE.

Part: FRAME — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND CRACK ON MAIN CARGO COMPARTMENT FRAME FLANGE 1 INCH AT STA 340.000 L-20L. MAJOR REPAIR ACCOMPLISHED BY REMOVAL OF CRACKED FRAME SEGMENT. FABRICATED NEW FRAME SEGMENT AND SPLICES. HEAT TREATED SPLICES. CLEANED, TREATED AND PRIMED AREA AND NEW FRAME SEGMENT AND SPLICES. APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW FRAME SEGMENT AND SPLICES IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, LT FUSELAGE LONGERON 24 FITTINGS FRAME REMOVED AND INSTALLED FOR NR 3484 AT STA 940.000. REPAIR ACCOMPLISHED REMOVAL OF FITTING IN ORDER TO GAIN ACCESS FOR REPAIR. FABRICATED SPLICES, DOUBLER AND FILLERS. HEAT TREATED DOUBLER AND FILLER, CLEANED, TREATED AND PRIMED AREA AND SPLICES, DOUBLER , FILLER AND FITTING. APPLIED SEALANT TO FAYING SURFACES AND INSTALLED FILLERS, DOUBLER AND SPLICES ON FITTING. REINSTALLED IN ACCORDANCE WITH DOUGLAS STRUCTURAL MANUAL.

Part: WEB — CRACKED (FUSLAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK, RT FUSELAGE WELL MLG WEB CRACK DAMAGE BETWEEN STA Y=857.125 AND XCW=25.000. REPAIR ACCOMPLISHED, REMOVED FASTENERS, REMOVED WEB DAMAGED SEGMENT. PERFORMED NDT INSPECTION. FABRICATED NEW WEB SEGEMENT AND EXTERNAL REPAIR DOUBLER AND INTERNAL REPAIR DOUBLER. CLEANED, TREATED AND PRIMED REPAIR PARTS. APPLIED PRC SEALANT TO FAYING SURFACES INSTALLED NEW WEB SEGMENT AND INTERNAL/EXTERNAL REPAIR DOUBLER WITH NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL AND DRAWING W43-R01

Part: SKIN PANEL — CORRODED (TE FLAP) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, INTERIM REPAIR FOUND ON LOWER SURFACE OF LT OUTBOARD FLAP STA XF 420.000. REPAIR ACCOMPLISHED REMOVAL OF SKIN WITH THE INTERIM REPAIR ON IT. FABRICATED NEW SKIN PLUS FINGER DOUBLER. BONDED FINGER DOUBLER ON SKIN. CLEANED, TREATED AND PRIMED INNER FACE OF NEW SKIN PANEL. INSTALLED NEW SKIN PANEL PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, TEE CRACK DAMAGE WAS FOUND RT FUSELAGE STRUCTURE MLG COMPARTMENT AROUND STA 960.000. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED SECTION. FABRICATED TEE ANGLE, HEAT TREATED AND PERFORMED NDT INSPECTION. FABRICATED SPLICES. APPLIED PRC SEALANT TO FAYING SURFACES. CLEANED, TREATED AND PRIMED SPLICE AND TEE ANGLE. INSTALLED SPLICES AND TEE ANGLE PER DOUGLAS STRUCTURAL REPAIR AND ATI REPAIR SPECIFICATION NR 2003-05, DPS 7.00-1.

Part: FRAME — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND CORROSION DAMAGE ON RT FUSELAGE STRUCTURE MAIN CARGO COMPARTMENT ZEE FRAME AROUND STATION 240.000, L-33R AND L-34R. REPAIR ACCOMPLISHED THE REMOVAL OF THE CORRODED FRAME SEGMENT. FABRICATED NEW FRAME SEGMENT AND SPLICES. HEAT TREATED SPLICES, CLEANED, TREATED AND PRIMED AREA AND NEW FRAME SEGMENT AND SPLICES. APPLIED PRC SEALANT TO FAYING SURFACES AND INSTALLED NEW FRAME SEGMENT AND SPLICES PER DOUGLAS STRUCTURAL REPAIR MANUAL, DPS 3.69-4 REV "AM", DPS 7.00-1 REV "BJ".

Part: LONGERON — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND CRACKED L-34 RT AFT CARGO COMPARTMENT STA FS1400.00 TO FS 1420.000. REPAIR ACCOMPLISHED REMOVAL OF CRACKED LONGERON SEGMENT. CLEANED, TREATED AND PRIMED AREA. FABRICATED SPLICE FILLING LONGERON. PERFORMED HEAT TREATMENT TO LONGERON AND SPLICES. CLEANED TREATED AND PRIMED. APPLIED PRC SEALANT TO FAYING SURFACES AND INSTALLED REPAIRED PARTS IAW DOUGLAS SRMS AND ATI REPAIR SPECIFICATION 2003-05.

Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, LT FUSELAGE NOSE SECTION PRESSURE PANEL CORROSION DAMAGE BETWEEN STA FS 8.00 AND STA FS -67.00 LBL 40.30 TO LBL 56.00. REPAIR ACCOMPLISHED. REMOVED FASTENERS WITHIN REPAIR AREA. REMOVED THE CORROSION AND FOUND OUT OF LIMITS. PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA. FABRICATED A NEW SEGMENT PANEL, FIVE EXTERNAL REPAIR DOUBLER, TWO INTERNAL REPAIR DOUBLER. CLEANED, TREATED AND PRIMED THE REPAIR PARTS. APPLIED PRC SEALANT TO FAYING SURFACES, INSTALLED THE REPAIR PARTS ON THE NOSE SECTION PRESSURE PANEL USING NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL, FAA FORM 8110-3 DWG W43-R20 AND EO NR 2004484.

Part: LONGERON — CORRODED (FUSLEAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION FOUND RT FUSELAGE LONGERON 24 CORROSION DAMAGE BETWEEN STA 920.00 AND STA 960.000. REPAIR ACCOMPLISHED REMOVAL OF CORROSION. FOUND OUT OF LIMITS. CLEANED, TREATED AND PRIMED. FABRICATED ANGLES. CLEANED, TREATED AND PRIMED. APPLIED PRC SEALANT TO FAYING SURFACES AND INSTALLED ANGLES IAW DOUGLAS SRM AND BOEING MESSAGE 1-M3W2D.

Part: SKIN — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION, FOUND RT FUSELAGE NOSE SECTION STRUCTURE FLIGHT COMPARTMENT HAS DAMAGE FROM CORROSION AT STA -67.000. REPAIR ACCOMPLISHED. REMOVED CORROSION AND FOUND OUT OF LIMITS. REMOVED THE CORRODED FRAME SEGMENT AND FABRICATED A NEW FRAME SEGMENT. HEAT TREATED NEW FRAME, CLEANED, TREATED AND PRIMED AREA AND NEW FRAME SEGMENT. INSTALLED NEW FRAME SEGMENT PER DOUGLAS STRUCTURAL REPAIR MANUAL, DPS 3.69-4 REV "AM", DPS 7.00-1 REV. "BJ"

Part: SKIN — DAMAGED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND DAMAGE ON THE FUSELAGE EXTERNAL SKIN AT STA 125.000 - 275.000 L-21L. MAJOR REPAIR ACCOMPLISHED REMOVAL OF DAMAGED SECTION. PERFORMED AN NDT INSPECTION, FABRICATED EXTERNAL REPAIR DOUBLER, FILLERS, FINGER DOUBLERS AND REPAIR TRIPLER. CLEANED, TREATED, PRIMED AREA, DOUBLERS, FILLERS, FINGER DOUBLER AND TRIPLERS. APPLIED PRC SEALANT TO FAYING SURFACES. INSTALLED THE DOUBLERS, FILLERS, FINGER DOUBLER AND TRIPLERS PER THE DOUGLAS STRUCTURAL REPAIR MANUAL, ATI DWG W43-R15, REV IR DATED 10/6/04 AND FAA FORM 8110-3.

Part: VANE — DAMAGED (L/E SLAT) · airframe 92,146 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT WING EXTENDED LEADING EDGE INBOARD VANE PLATING INTERIM REPAIR AROUND STA XS 247.000. MAJOR REPAIR ACCOMPLISHED BY REMOVAL OF THE FASTENERS WITHIN REPAIR AREA AND THE EXISTING INTERIM REPAIR. REMOVED THE DAMAGED SKIN AREA AND PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA. FABRICATED AND EXTERNAL REPAIR DOUBLER AND INTERNAL DOUBLER. CLEANED, TREATED AND PRIMED THE EXTERNAL REPAIR DOUBLER INTERIOR SURFACE, INTERNAL DOUBLER AND FILLER. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED THE REPAIR PARTS ON RT WING EXTENDED L/E INBOARD VANE SLOT USING NEW FASTENERS IAW THE DOUGLAS STRUCTURAL REPAIR MANUAL, ATI DWG W43-R07, FAA FORM 8110-3.

Part: PLATE — DAMAGED (LT WING) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT WING EXTENDED LEADING EDGE OUTBOARD VANE PLATING INTERIM REPAIR STA XOLDO 67.000. REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND EXISTING INTERIM REPAIR. REMOVED THE DAMAGED SKIN AREA AND PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA. FABRICATED A REPAIR DOUBLER, A FILLER AND AN INTERNAL DOUBLER. CLEANED, TREATED AND PRIMED THE EXTERNAL REPAIR DOUBLER INTERIOR SURFACE, INTERNAL DOUBLER AND FILLER. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED THE REPAIR PARTS WITH NEW FASTENERS IAW DOUGLAS SRM, ATI DWG W43-R06 AND FAA FORM 8110-3.

Part: SKIN — DAMAGED (RT WING) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, RT WING INBOARD VANE SLOT HAS INTERIM REPAIR AT STA XILD 7095.00. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED SECTION. PERFORMED NDT INSPECTION. FABRICATED EXTERNAL REPAIR DOUBLER, FILLER, AND INTERNAL DOUBLER. CLEANED, TREATED AND PRIMED INNER FACE OF DOUBLER-INTERNAL/EXTERNAL, FILLER. APPLIED PRC SEALANT TO FAYING SURFACES. INSTALLED EXTERNAL REPAIR DOUBLER AND FILLER AND INTERNAL DOUBLER PER DOUGLAS STRUCTURAL REPAIR MANUAL AND DWG W43-R04.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION MAIN CARGO COMP BEAM WEB CORROSION & 2 INCH CRACK STA 920.000 LBL 64-69". REPAIR ACCOMPLISHED REMOVAL OF CORROSION AND FOUND OUT OF LIMITS. REMOVED DAMAGED AREA ON BEAM. FABRICATED FILLER REPAIR AND REPAIR ANGLES. CLEANED, TREATED AND PRIMED AREA. APPLIED PRC SEALANT TO FAYING SURFACES AND INSTALLED REPAIRED PARTS PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND LOWER EXTERNAL FUSELAGE SKIN CORRODED AT STA 1410.000 L-35. MAJOR REPAIR ACCOMPLISHED REMOVAL OF THE CORROSION. FOUND OUT OF LIMITS AND REMOVED THE DAMAGED PLATING. CLEANED, TREATED AND PRIMED AREA. APPLIED THE PRC SEALANT TO FAYING SURFACES AND INSTALLED NEW PLATING IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — DAMAGED (L/E SLAT) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT OUTER WING INBOARD EXTENDED LEADING EDGE OUTER LOWER PLATING WITH INTERIM REPAIR AROUND STA XFS 710.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF INTERIM REPAIR. THE DAMAGED SECTION WAS REMOVED AND A NDT INSPECTION WAS PERFORMED. FABRICATED REPAIR DOUBLER AND FILLERS. CLEANED, TREATED AND PRIMED INNER FACE OF DOUBLER AND FILLERS. APPLIED PRC SEALANT TO FAYING SURFACES. INSTALLED NEW DOUBLER AND FILLERS IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND CORROSION DAMAGE ON RT FUSELAGE NOSE SECTION PRESSURE PANEL BETWEEN STA FS 8.00 AND STA FS -67.00, RBL 28.78 TO RBL 56. REPAIR ACCOMPLISHED REMOVAL OF FASTENERS AND CORROSION. FOUND OUT OF LIMITS, REMOVED DAMAGED SEGMENT. PERFORMED NDT INSPECTION. FABRICATED NEW PRESSURE PANEL SEGMENT, EXTERNAL REPAIR DOUBLER AND INTERNAL REPAIR DOUBLER. CLEANED, TREATED AND PRIMED AREA AND NEW PRESSURE PANEL SEGMENT. APPLIED RC SEALANT TO FAYING SURFACE. INSTALLED NEW PRESSURE PANEL SEGMENT AND INTERNAL/EXTERNAL REPAIR DOUBLERS WITH NEW FASTENERS PER ALL APPLICABLE MANUALS AND DRAWINGS.

Part: SKIN — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION FOUND TAIL SECTION FUSELAGE EXTERNAL SKIN CRACKED .75 INCH STA 1755.000-L-13 TO L14. REPAIR ACCOMPLISHED REMOVAL OF FASTENERS WITH THE REPAIR AREA AND EXISTING REPAIR DOUBLER. REMOVED DAMAGED SECTION. PERFORMED NDT INSPECTION, CLEANED, TREATED AND PRIMED AREA. FABRICATED A REPAIR DOUBLER, SHINS AND TWO INTERNAL FINGER DOUBLER. CLEANED TREATED AND PRIMED THE REPAIR PARTS. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED THE REPAIR PARTS ON TAIL SECTION EXTERNAL SKIN USING NEW FASTENERS PER DOUGLAS STRUCTURAL MANUAL, ATI DWG W43-R13 AND FAA FORM 8110-3.

Part: VANE — DAMAGED (L/E SLAT) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND LT WING EXTENDED LEADING EDGE O/B VANE PLATING HAS DAMAGE. MAJOR REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA. AN NDT INSPECTION WAS PERFORMED. FABRICATED REPAIR DOUBELR, FILLER INTERNAL DOUBLER. CLEANED, TREATED AND PRIMED REPAIR DOUBLER, INTERNAL PART, FILLER INTERNAL DOUBLER. APPLIED PRC SEALANT TO FAYING SURFACES AND INSTALLED REPAIR PARTS WITH NEW FASTENERS IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL, ATI DWG W43-R05.

Part: PLATE — CORRODED (HORIZONTAL STAB) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, RT HORIZONTAL STAILIZER OUTBOARD LEADING EDGE UPPER PLATING CORROSION DAMAGE BETWEEN STA XFS 172.000 AND XFS 335.000. REPAIR ACCOMPLISHED. REMOVED FASTENERS AND CORROSION. FOUND OUT OF LIMITS, REMOVED CORROSION, CLEANED, TREATED AND PRIMED AREA. FABRICATED A REPLACEMENT, AN EXTERNAL REPAIR DOUBLER AND TWO FILLERS. CLEANED, TREATED AND PRIMED THE REPLACED SECTION OF SKIN DOUBLER INTERIOR SURFACE AND FILLERS. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED THE REPAIR PART ON RT HORIZ STAB O/B L/E UPPER PLATING USING NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL, BOEING ROD SKETCH 04-9-23-004 AND BOEING MESSAGE 1-PPR41, 1-Q821M A1-PPR43H,

Part: SKIN — CRACKED (L/E SLAT) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT WING EXTENED LEADING EDGE OUTBOARD VANE PLATING REPAIR DOUBLER WITH ELONGATED HOLES AND CRACK DAMAGE BETWEEN STA XOLDO 67.000 AND XS 497.491. MAJOR REPAIR ACCOMPLISHED REMOVAL OF EXISTING REPAIR DOUBLER AND REMOVAL OF THE DAMAGED AREA. PERFORMED A NDT INSPECTION AND FABRICATED NEW SKIN SEGMENT, INTERNAL DOUBLER AND EXTERNAL SPLICE. CLEANED, TREATED AND PRIMED NEW SKIN SEGMENT, INTERNAL PART AND INTERNAL DOUBLER ALONG WITH THE EXTERNAL SPLICE. APPLIED PRC SEALANT TO FAYING SURFACES AND INSTALLED REPAIR PART WITH NEW FASTENERS IN ACCORDANCE WITH ATI DWG W43-R08 AND DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, INTERIM REPAIR ON FUSELAGE EXTERIOR SKIN FROM FS 685.000 - 779.000 L-35 LT TO L-34 RT AND CORROSION DAMAGE. REPAIR ACCOMPLISHED REMOVAL OF ALL FASTENERS WITHIN THE REPAIR AREA. REMOVED CORROSION AND FOUND OUT OF LIMITS. PERFORMED NDT INSPECTION, CLEANED, TREATED, AND PRIMED AREA. FABRICATED A NEW SEGMENT PANEL, A REPAIR DOUBLER, AND A REPAIR TRIPLER. CLEANED, TREATED AND PRIMED THE NEW SEGMENT PANEL AND REPAIR DOUBLER AND TRIPLER. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED THE REPAIR PARTS ON FUSELAGE EXTERIOR SKIN USING NEW FASTENERS IAW DOUGLAS SRM, ATI DWG W43-R21 AND FAA FORM 8110-3.

Part: FITTING — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT FUSELAGE LONGERON 24 FITTING FRAME HAS CORROSION DAMAGE ON LOWER SIDE AT STA 960.000. REPAIR ACCOMPLISHED REMOVAL OF THE CORRODED AREA AND FOUND OUT OF LIMITS. FABRICATED NEW FITTING. FABRICATED SPLICES, DOUBLER AND FILLERS. HEAT TREATED DOUBLER AND FILLERS. CLEANED, TREATED AND PRIMED AREA AND SPLICES DOUBLER AND FILLERS. APPLIED SEALANT TO FAYING SURFACES, INSTALLED SPLICES AND FILLER AND DOUBLER ON FITTING. INSTALLED NEW FITTING IAW DOUGLAS SRM AND REPAIR SPECIFICATION 2003-05 AND DWG 3647117.

Part: FRAME — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT FUSELAGE STRUCTURE MAIN CARGO COMPARTMENT ZEE FRAME CRACK DAMAGE AROUND STA FS 260.000, L-20 RT. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED FRAME SEGMENT. CLEANED, TREATED AND PRIMED AREA. FABRICATED FRAME SEGMENT AND SPLICES. PERFORMED HEAT TREATMENT TO FRAME SEGMENT AND SPLICES. PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED. APPLIED PRC SEALANT TO FAYING SURFACES AND INSTALLED REPAIR PARTS IAW DOUGLAS SRM, DPS 3.69-4 REV 'AM' DPS 7.00 1 REV BJ.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, CRACK DAMAGE WAS FOUND AT LT FUSELAGE STRUCTURE MAIN CARGO COMPARTMENT FLOORBEAM LOWER SIDE CRACK DAMAGE AT STA FS 980.000 LBL 40. REPAIR ACCOMPLISHED REMOVED OF "T" ANGLE SEGMENT, CLEANED, TREATED AND PRIMED AREA. FABRICATED "T" ANGLE SEGMENT AND SPLICES. PERFORMED HEAT TREATMENT, CLEANED, TREATED AND PRIMED "T" ANGLE SEGMENT AND SPLICES. APPLIED PRC SEALANT ON FAYING SUFACES. INSTALLED NEW "T" ANGLE SEGMENT AND SPLICES PER DOUGLAS STRUCTURAL REPAIR MANUAL,

Part: FITTING — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT FUSELAGE LONGERON 24 FITTING FRAME HAS CORROSION DAMAGE AT STATION 940.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF FITTING. CLEANED, TREATED AND PRIMED AREA. FABRICATED SPLICES, DOUBLER AND FILLER. PERFORMED HEAT TREATMENT TO DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED REPAIR PARTS. INSTALLED REPAIR PARTS WITH NEW FASTENERS AND INSTALLED NEW FITTING IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: PLATE — DAMAGED (LT WING) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT OUTER WING OUTBOARD EXTENDED LEADING EDGE PLATING WITH INTERIM REPAIR AT STA XFS 710.000. REPAIR ACCOMPLISHED REMOVAL OF ALL FASTENERS WITHIN THE REPAIR AREA AND THE EXISTION INTERIM REPAIR. REMOVED THE DAMAGED SKIN AREA AND PERFORMED A NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA. FABRICATED A REPAIR DOUBLER AND FILLER. CLEANED, TREATED AND PRIMED THE REPAIR DOUBLER INTERIOR SURFACE AND FILLER. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED THE REPAIR PARTS ON LT OUTER WING OUTBOARD LEADING EDGE STA XFS 710.000 USING NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL, ATI DRAWING W43-R14, AND FAA FORM 8110-3.

Part: RIB — CRACKED (LT WING) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT STUB WING NR 1 STRUCTURE RIB WITH CRACK DAMAGE AT STA XS 520.000. REPAIR ACCOMPLISHED, REMOVED CRACKED RIB. FABRICATED RIB AND PERFORMED HEAT TREATMENT. PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW RIB ON LT WING NR 1 STUB WING PER DOUGLAS STRUCTURAL MANUAL, REPAIR SPEC NR 2003-05 AND DRAWING NR 9753297.

Part: FITTING — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT MAIN LANDING GEAR FRAME FITTING CRACK DAMAGE AT STA 98.000, BETWEEN L-19R AND L-24. REPAIR ACCOMPLISHED. REMOVED THE CRACKED FITTING, CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT FUSELAGE AFT CENTER SECTION FLOORBEAM INTERIM REPAIR STA 1560.000, LBL 45 INCH. REPAIR ACCOMPLISHED, REMOVED INTERIM REPAIR. PERFORMED BLEND OUT ON DAMAGE AREA, FOUND OUT OF LIMITS. FABRICATED FILLER AND REPAIR ANGLE, CLEANED, TREATED AND PRIMED AREA + FILLER + REPAIR ANGLE. APPLIED PRC SEALANT ON FAYING SURFACES, INSTALLED FILLER, REPAIR ANGLE AND NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND TH FUSELAGE FORWARD CENTER SECTION FLOORBEAM CAP UPPER CORROSION DAMAGE STA 857.000, LBL 32 INCH. REPAIR ACCOMPLISHED. REMOVED CORROSION AND FOUND OUT OF LIMITS. REMOVED THE CORRODED AREA AND FABRICATED FILLER AND REPAIR ANGLE. CLEANED, TREATED, PRIMED AND APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED FILLER AND REPAIR ANGLE WITH NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: RIB — WORN (RT WING) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT STUB WING NR 4 STRUCTURE RIB WEAR DAMAGE AT STA XS 520.000. REPAIR ACCOMPLISHED, REMOVED WORN RIB. FABRICATED RIB AND PERFORMED HEAT TREATMENT. PERFORMED NDT INSPECTION. CLEANED, TREATED AND PRIMED. INSTALLED NEW RIB ON RT WING NR 4 STUB WING PER DOUGLAS STRUCTURAL REPAIR MANUAL, REPAIR SPECIFICTION NR 2003-05, AND DRAWING NR 9753797.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT FUSELAGE TAIL SECTION LONGERON CRACK DAMAGE AT STA 1785.00 L-17 LT. REPAIR WAS ACCOMPLISHED IAW DC8 SRM 53-1-0 PG1, DC8 SRM 53-5-3 FIG 5 SHEET 1. REMOVED CRACKED LONGERON 171 IAW DC8 SRM 51-1-21 PG 1. FABRICATED NEW LONGERON ( EXTRUSION S 1616757) IAW DDC8 SRM 53-5-3 FIG 5 SHEET 1. CLEANED, TREATED AND PRIMED IAW DC8 SRM 51-1-8B. INSTALLED NEW LONGERON IAW DC8 SRM 51-3-0 PG 1-2 DC8 SRM 51-1-21 PG 1 DC8 SRM 51-1-20D PG9.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, REMOVED MAIN CARGO COMPT FRAME FITTING AT STA920.00 L-23L TO L24L IN ORDER TO COMPLY WITH N/R 3484. REPAIR ACCOMPLISHED. REMOVED FITTING TO GAIN ACCESS TO STRUCTURAL REPAIR. FRABRICATED SPLICES, DOUBLER AND FILLERS. CLEANED, TREATED AND PRIMED SPLICES, DOUBLER AND FILLERS AND FITTING. APPLIED PRC SEALANT TO FAYING SURFACES AND INSTALLED REPAIR PART TO FITTING. REINSTALLED FITTING PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: FITTING — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND FUSELAGE AT SECTION FITTING CORROSION DAMAGE BETWEEN STA 1680.00 AND 1690.00, L-36. REPAIR ACCOMPLISHED, REMOVED CORRODED FITTING AND THE CORROSION. FOUND OUT OF LIMITS. CLEANED, TREATED AND PRIMED AREA AND INSTALLED NEW FITTNG PER DOUGLAS STRUCTURAL REAPIR MANUAL.

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, LT WING OUTBOARD FLAP LOWER PLATING HAS INTERIM REPAIR AT STA XF 1340.000. MAJOR REPAIR ACCOMPLISHED. REMOVED SKIN WITH INTERIM REPAIR ON IT IAW DC8 SRM 51-1-21 PG 1 DC8 SRM 51-3-0 PG1. FABRICATED NEW SKIN (AL2024130.050") IAW DC8 SRM 57-7-1 PG 2 FIG 4 TR NR 57-94. CLEANED, TREATED AND PRIMED AREA + INNER FACE OF SKIN IAW DC8 SRM 51-1-8B. INSTALLED NEW SKIN AND FASTENERS IAW EC8 SRM 51-1-21 PG1 DC8 SRM 51-3-0 PG1.

Part: SKIN — CRACKED (RT WING) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, RT WING TOP PANEL PLATING HAS CRACK DAMAGE STA XRS 74.000, S-9. MAJOR REPAIR ACCOMPLISHED IAW DC8 SRM 57-2-1 FIG 17 PG 87, 88 1. REMOVED FASTENERS IAW DC8 SRM 51-1-20D PG 21. REMOVED DAMAGED AREA IAW DC8 SRM 57-2-1 PAGES 87, 88 FIG 17. FABRICATED DOUBLER (AL 7075 T6 0.160") IAW SRM 57-2-1 PGS 87, 88 FIG 17. CLEANED, TREATED AND PRIMED DOUBLER, FILLER AREA IAW DC8 SRM 51-1-8B. APPLIED PRC SEALANT ON FAYING SUFACES IAW DC8 SRM 51-1-11 PG 9. INSTALLED DOUBLER AND FILLER WITH NEW FASTENERS IAW DC8 SRM 51-1-20D PG 9.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND FLOORBEAM CORROSION ON RT FUSELAGE AFT CENTER SECTION AT STA 15000.000 RBL 48 INCH. MAJOR REPAIR ACCOMPLISHED IAW DC8 SRM 51-2-1 FIG 1 PAGES 8-14 (SHEET 7,12) TR NR 51-1-30. REMOVED CORROSION IAW DC8 SRM 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW DC8 SRM 53-2-0 PG 2P. REMOVED CORRODED AREA IAW DC8 SRM 51-2-1 FIG 1 PG 8-14 (SHEET 7). FABRICATED FILLER (AL 7075.+6 0.125") + REPAIR ANGLE (EXTRUSION 7075-T.6 0.150") IAW DC8 SRM 51-2-1 FIG PAGES 8-14 (SHEET 7). CLEANED, TREATED AND PRIMED AREA + FILLER + REPAIR ANGLE IAW DC8 SRM 51-1-8B APPLIED PRC SEALANT ON FAYING SURFACES IAW DC8 SRM 51-1-11 PG 9 INSTALLED FILLER + REPAIR ANGLE WITH NEW FASTENERS IAW DC8 SRM 51-1-1 F

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION A CORRODED BEAM WAS FOUND AT STA FS 1360.00 RBL 47". REPAIR WAS ACCOMPLISHED, CORROSION WAS REMOVED. FABRICATED FILLER & REPAIR ANGLE. CLEANED, TREATED AND PRIMED AREA. APPLIED PRC SEALANT ON FAYING SURFACES AND INSTALLED FILLER AND REPAIR ANGLE WITH NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, THE RT FUSELAGE AFT CENTER SECTION FLOORBEAM HAS CORROSION DAMAGE AT STA 1300.000 RBL 48 INCH. MAJOR REPAIR WAS ACCOMPLISHED. REMOVED CORROSION IAW DC8 SRM 51-1-8 PGS 17-18. FOUND OUT OF LIMITS IAW EC8 SRM 53-2-0 PAGE 2P. REMOVED CORRODED AREA IAW DC8 SRM 51-2-1 FIG 1 PAGES 8-14 (SHEET 7). FABRICATED FILLER (AL 7075 76. 0.125"0 )+ REPAIR ANGLE (EXTRUSION 7075.TG 5110.0150") IAW DC8 SRM 51-2-1 FIG 1 (SHEET 7). CLEANED TREATED AND PRIMED AREA, FILLER & REPAIR ANGLE IAW DC8 SRM 51-1-8B APPLIED PRC SEALANT ON FAYING SURFACES IAW DC8 SRM 51-1-11 PAGE 9. INSTALLED FILLER AND REPAIR ANGLE WITH NEW FASTENERS IAW DC8 SRM 51-2-1 FIG 1(SHEET 7,12) DC8 SRM 51-1-20D PG 9.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION, LT FUSELAGE LONGERON 24 FITTING FRAME WAS REMOVED AND INSTALLED TO COMPLY WITH N/R 3484 SID 960.000L-24 TO L-23L. REPAIR ACCOMPLISHED, REMOVED FRAME FITTING, CLEANED, TREATED AND PRIMED AREA. FABRICATED SPLICES AND DOUBLER AND FILLERS. PERFORMED HEAT TREATMENT TO FILLERS AND DOUBLER. CLEANED TREATED AND PRIMED. REPAIRED PARTS. INSTALLED FRAME FITTING REPAIR PARTS WITH NEW FASTENERS AFTER COMPLIED WITH N/R 3484 PER THE DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND FLOORBEAM CORRODED AT STA 1400.00 RBL 45". REPAIR WAS ACCOMPLISHED, CORROSION WAS REMOVED. FABRICATED FILLER & REPAIR ANGLE. CLEANED, TREATED AND PRIMED. APPLIED PRC SEALANT TO FAYING SURFACES. INSTALLED FILLER & ANGLE DOUBLER PER THE DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING ROUTINE C-CHECK INSPECTION RT FUSELAGE AFT CENTER SECTION FLOORBEAM CORRSION DAMAGE STA 1460.000, RBL 48 WAS FOUND. REMOVED CORROSION IAW DC8 SRM 51-1-1 PAGES 17, 18, FOUND OUT OF LIMITS IAW DC8 SRM 53-2-0 PGS 20. REMOVED CORRODED AREA IAW DC8 SRM 51-2-1 FIG 1, PAGES 8-14 (SHEET 3). FABRICATED FILLER (AL 7075 T6 0.125) + REPAIR ANGLE (EXTRUSION 7075T6 0.150) IAW DC8 SRM 51-2-18 FIG 1 (SHEET 7). CLEANED, TREATED AND PRIMED AREA AND FILLER AND REPAIR ANGLE IAW DC8 SRM 51-1-8B. APPLIED PRC SEALANT ON FAYING SURFACE IAW DC8 SRM 51-1-11 PG 9. INSTALLED FILLER AND REPAIR ANGLE WITH NEW FASTENERS IAW DC8 SRM 51-2-1 FIG 1 (SHEET 7, 12) DC8 SRM 51-1-21 PAGE 1, DC8 SRM 51-1-20D PAGE 9.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION RT FUSELAGE AFT CENTER SECTION FLOORBEAM CORROSION DAMAGE STA 1480.000, RBL 47. MAJOR REPAIR ACCOMPLISHED. REMOVED CORROSION IAW DC8 SRM 51-1-8 PAGES 17, 18. FOUND OUT OF LIMITS IAW DC8 SRM 53-2-0 PG 2P. REMOVED CORRODED AREA IAW DC8 SRM 51-2-7 FIG 1 PAGES 8-14 (SHEET 7). FABRICATED FILLER (AL 7075 T6 599-0.150) IAW DC8 SRM 51-2-1 FIG 1 (SHEET 1). CLEANED, TREATED AND PRIMED AREA FILLER AND REPAIR ANGLE IAW DC8 SRM 51-1-8B. APPLIED PRC SEALANT ON FAYING SURFACES IAW SC8 SRM 51-1-11 PAGE 9. INSTALLED FILLER REPAIR ANGLE WITH NEW FASTENERS IAW DC8 SRM 51-2-1 FIG 1 PAGE 8-14 (SHEET 7-12), DC8 SRM 51-1-21 PAGE 1 DC9 SR, 51-1-20D PAGE 9.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND FLOORBEAM CORRODED AFT CARGO COMPARTMENT AT STA FS 1520.000. A MAJOR REPAIR WAS PERFORMED. REMOVED THE CORRODED AREA AND FOUND OUT OF LIMITS IAW DC8 SRM 51-1-8 PG 17, 18 AND SRM 53-2-0 PG 2P. FABRICATED FILLER ( AL 7075 T6 0.425) + REPAIR ANGLE (EXTENSION 7075 T6 511 0.150) IAW DC8 SRM 51-2-1 PG 1 SHEET. CLEANED, TREATED AND PRIMED AREA, FILLER REPAIR ANGLE IAW DC8 SRM 51-1-8B. APPLIED PRC SEALANT ON FAYING SURFACE IAW DC8 SRM 51-1-11 PG 9. INSTALLED FILLER REPAIR ANGLE WITH NEW FASTENERS IAW DC8 SRM 51-2-1 FIG 18-14 SHEET IAW DC8 SRM 51-1-21 PG 1 DC8 SRM 51-1-20D PG 9.

Part: DOUBLER — CRACKED (WING) · airframe 91,246 hrs · 29,801 cycles

DURING ROUTINE C-CHECK INSPECTION PERFORMED MAJOR REPAIR IAW DC8 SRM 57-2-1 FIG 36 PG 133-134. REMOVED FASTENERS IAW DC8 SRM 51-1-21 PG 1, PERFORMED STOP HOLE ON CRACK END IAW DC8 SRM 57-2-1 PAGES 133, 134 FIG 36. FABRICATED EXTERNAL DOUBLER (AL 707576 0-160) INTERNAL DOUBLER (AL 7075 160. 063) IAW DC8 SRM 57-2-1 PAGES 133, 134 FIG 36. CLEANED, TREATED AND PRIMED AREA AND INTERNAL AND EXTERNAL DOUBLER IAW DCI SRM 51-1-8B. APPLIED PRC SEALANT ON FAYING SURFACES IAW DC8 SRM 51-1-11 PG 9. INSTALLED EXTERNAL AND INTERNAL DOUBLER WITH NEW FASTENERS IAW DC8 SRM 1-1-21 PG 1, SRM 51-1-29 PAGE 1, DC8 SRM 57-1-1 PG 133, 134, FIG 36.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION, EXTERNAL FUSELAGE AFT PASSENGER DOOR UPPER CORNER DOOR JAMB CRACKED .5 INCH AT STA 1660.000 L-9 TO L-101. PERFORMED MAJOR REPAIR. REMOVED FASTENER, DAMAGED AREA AND FABRICATED FILLER, DOUBLER, AND TRIPLER. CLEANED, TREATED AND PRIMED AREA + FILLER + DOUBLER + TRIPLER. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED FILLER, DOULBER AND TRIPLER WITH NEW FASTENERS PER ALL APPLICABLE MANUALS.

Part: SKIN — DAMAGED (T/E FLAP) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND LT INBOARD FLAP WITH TEMP REPAIR ON UPPER SURFACE STA XW 90.000. MAJOR REPAIR ACCOMPLISHED REMOVAL OF PLATING WITH THE TEMP REPAIR ON IT. FABRICATED NEW PLATING. CLEANED, TREATED AND PRIMED AREA AND THE INNER FACE OF THE NEW PLATING. INSTALLED THE NEW PLATING IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK MAINTENANCE FOUND RT OUTBOARD FLAP L/E HAS INTERIM REPAIR ON UPPER SKIN, STA XF 418.000. PERFORMED MAJOR REPAIR IAW DCI SRM 57-1-0 PG 1 DC8, SRM 57-7-1 FIG 4 (TR 5794). REMOVED PLATING WITH INTERIM REPAIR ON IT, IAW DC8 SRM 51-1-21 PG 1. FABRICATED NEW PLATING ( 2024T3 0.32) IAW DC8 SRM 57-7-1 FIG 4 (TR 57-94). CLEANED, TREATED AND PRIMED AREA + INNER FACE OF NEW PLATNG IAW DC8 SRM 51-1-8B. INSTALLED NEW PLATING IAW DC8 SRM 51-1-21 PG 1 DC8, SRM 51-1-185 PG 1.

Part: SKIN — CORRODED (VERTICAL STAB) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION MAINTENANCE PERFORMED A MAJOR REPAIR ON VERTICAL STABILIZER L/E UPPER SKIN. FOUND CORROSION AT STA ZFS 179.000. REMOVED CORROSION FROM VERTICAL STABILIZER L/E UPPER SKIN STA ZFS 179.000 IAW DC8 SRM 51-1-8 PGS 17, 18. FOUND OUT OF LIMITS IAW DC8 SRM 55-2-1 FIG 3 PGS 15, 16. REMOVED DAMAGED AREA IAW DC8 SRM 55-2-1 FIG 4 PAGE 17. FABRICATED FILLER (AL 7075 T6- 0.050) + DOUBLER (AL 707516 0.050) IAW DC8 SRM 55-2-1 FIG 4 PAGE 17. CLEANED, TREATED AND PRIMED FILLER AND DOUBLER INTERNAL PART IAW DC8 SRM 51-1-8B. INSTALLED FILLER AND DOUBLER IAW DC8 SRM 55-2-1, SRM 51-1-21 PAGE 1, DC8 SRM 51-1-20D PAGE 9, DC8 SRM 51-1-11 PAGE 1.

Part: SKIN — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION FOUND RT FUSELAGE AFT CENTER SECTION LOWER PLATING CORROSION DAMAGE AROUND STA 1340.000, L-31 RT. PERFORMED MAJOR REPAIR. REMOVED FASTENERS IAW DC8 SRM 51-1-21 PG 1 DC8, SRM 51-1-20D PG 21. REMOVED CORROSION IAW DC8 51-1-8 PAGES 17 & 18. FOUND OUT OF LIMITS IAW DC8 SRM 53-2-0 PAGE 2. REMOVED CORRODED AREA IAW DC8 SRM 53-2-1 FIG 7 SHEET 3. CLEANED, TREATED & PRIMED. FABRICATED FINGER DOULBER, FILLER DOUBLER. CLEANED, TREATED AND PRIMED FINGER DOULBER, FILLER AND DOUBLER IAW DC8 SRM 51-1-8B. INSTALLED SPACER IAW DC8 SRM 51-1-26. INSTALLED FILLER FINGER DOUBLER, DOUBLER WITH NEW FASTENERS.

Part: SKIN — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION, EXTERNAL FUSELAGE CRACKED .75 INCH FROM STA 1718.000 TO STA 1719.000. MAINTENANCE PERFORMED MAJOR REPAIR IAW DC8 DRM 53-2-1 FIG 7. REMOVED FASTENERS IAW DC8 SRM 51-1-21 PG 1. REMOVED CRACKED AREA IAW DC8 SRM 51-1-21 PG 1. REMOVED CRACKED AREA IAW DC8 SRM 53-2-1 (SHEET3, 5). FABRICATED DOUBLER (AL 707576 0.63), FINGER DOUBLER (AL 707516 0.32), FILLER (AL 707516 0.050) IAW DC8 SRM 53-2-1 FIG 7 (SHEET 1, 3, 5). CLEANED, TREATED AND PRIMED AREA, FINGER DOUBLER FILLER AND DOUBLER IAW DC8 SRM 51-1-8B, INSTALLED DOUBLER, FINGER DOUBLER AND FILLER WITH NEW FASTENERS IAW DC8 SRM 53-2-1 FIG 7 (SHEET 1, 3, 5) DC8 SRM 51-1-1 PG 1, DC8 SRM 51-1-200 PG 9, DC8 SRM 51-1-11 PAGE 9.

Part: PANEL — DAMAGED (RT WING) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT INNER WING EXTENDED LEADING EDGE SLANT PANEL UPPER CAP INTERIM REPAIRS BETWEEN STATIONS XFS. 32.500 AND XFS. 182.500. REPAIR ACCOMPLISHED. REMOVED DAMAGED SLANT PANEL UPPER CAP IAW EC8 SRM 51-1-20D PG 21, DC8 SRM 51-1-21 PG 1. CLEANED, TREATED AND PRIMED AREA IAW DC8 SRM 51-1-21 PG1 DC8 SRM 51-1-20D PG 9.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT FUSELAGE FWD CENTER SECTION LOWER PLATING HAS INTERIM REPAIR BETWEEN STA FS 470.00 AND 480.00, L-31LH. REPAIR WAS ACCOMPLISHED. REMOVED DAMAGED SECTION, FABRICATED FINGER DOUBLERS AND FILLER AND DOUBLER. CLEANED, TREATED, AND PRIMED FINGER DOUBLERS AND FILLER AND DOUBLER. APPLIED PRC SEALANT TO FAYING SURFACES AND INSTALLED FINGER DOUBLERS, FILLER & DOUBLER WITH NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND RT FUSELAGE AFT CENTER SECTION LOWER SKIN, REMOVED DOUBLER, FOUND SKIN CRACKED 4.500" STA 1520.00, L-29R AT FRAME AND ATTACH CLIP. REPAIR WAS ACCOMPLISHED. REMOVED DOUBLER IAW DC8 SRM 51-1-21 PG 1. REMOVED THE DAMAGED SKIN IAW DC8 SRM 53-2-1 PG 103-104 FIG 7 (SHEET 3) FABRICATED FINGER DOUBLER FILLER, IAW DC8 SRM 53-2-1 PG 99-100 FIG 7 (SHEET 1) CLEANED, TREATED AND PRIMED AREA, FINGER DOUBLER, FILLER & DOUBLER IAW DC8 SRM 51-1-8B. INSTALLED CONICAL SPACERS IAW DC8 SRM 51-1-26. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC8 SRM 51-1-11 PG 9. INSTALLED FINGER DOUBLER, FILLER & DOUBLER IAW DC8 SRM 53-2-1 PG 99-100 FIG 7 ( SHEET1) DC8 SRM 51-1-20D PG 9, DC8 SRM 51-1

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 912,462 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, LT FUSELAGE FORWARD PASSENGER DOOR UPPER FORWARD JAMB CORNER INTERIM REPAIR AROUND STA 25.000, L-8L TO L-10L. REPAIR ACCOMPLISHED, REMOVED INTERIM REPAIR, FABRICATED DOUBLER AND TRIPLER. CLEANED, TREATED AND PRIMED AREA. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED DOUBLER AND TRIPLER WITH NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL AND DRAWINGS DACO SR 08530021 AND 5750776.

Part: SKIN PANEL — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION, FOUND LT FUSELAGE FORWARD AND AFT CENTER SECTION PRESSURE PANEL CORROSION DAMAGE BETWEEN STA FS 980.000 AND FS 857.000. REPAIR ACCOMPLISHED. REMOVED FASTENERS, AND REMOVED CORROSION. FOUND OUT OF LIMITS. PERFORMED NDT INSPECTION. FABRICATED NEW PANEL SEGMENT, EXTERNAL REPAIR DOUBLER AND INTERNAL REPAIR DOUBLERS. CLEANED, TREATED AND PRIMED AREA, NEW PANEL SEGMENT, EXTERNAL REAPIR DOUBLER AND INTERNAL REPAIR DOUBLER. APPLIED PRC SEALANT TO FAYING SURFACES. INSTALLED NEW PANEL SEGMENT, EXTERNAL REPAIR DOUBLER AND INTERNAL REPAIR DOUBLER WITH NEW FASTENERS PER DOUGLAS SRM, DRWG W43-R12, AND EO 2004423

Part: SKIN — DAMAGED (TE FLAPS) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C-CHECK INSPECTION, RT WING OUTBOARD FLAP UPPER FORWARD PLATING INTERIM REPAIR AROUND STA XF. 226.000. REPAIR ACCOMPLISHED. REMOVED ALL FASTENERS WITHIN REPAIR AREA. REMOVED THE DAMAGED AREA. PERFORMED NDT INSPECTION, CLEANED, TREATED AND PRIMED AREA. FABRICATED A NEW SKIN SEGMENT AND INTERNAL SPLICE. CLEANED, TREATED AND PRIMED THE NEW SKIN SEGMENT INTERIOR SURFACE AND INTERNAL SPLICE. APPLIED REC SEALANT ON FAYING SURFACES. INSTALLED THE REPAIR PARTS ON RT O/B FLAP STA XF. 226.000 USING NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL, FAA FORM 8110-3 AND EO NR 2004414 AND DRAWING W43-R10.

Part: FITTING — CRACKED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LT FUSELAGE LONGERON 24 FITTING FRAME CRACK DAMAGE AT STA 879.000. REPAIR ACCOMPLISHED. REMOVED FITTING. FABRICATED SHIMS, DOUBLER AND SPLICES. HEAT TREATED SHIMS AND DOUBLER. CLEANED, TREATED AND PRIMED AREA AND SHIMS, DOUBLER AND SPLICES. APPLIED PRC SEALANT TO FAYING SURFACES INSTALLED SPLICES, DOUBLER, SHIM AND NEW FITTING PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, RT FUSELAGE STRUCTURE FOWARD CENTER SECTION PRESSURE ATTACH ANGLE HAS CORROSION DAMAGE AT STA Y=857.125(XCW 44). REPAIR ACCOMPLISHED. REMOVED CORROSION AND FOUND OUT OF LIMITS. REMOVED THE CORRODED ANGLE, CLEANED TREATED AND PRIMED AREA. INSTALLED NEW ANGLE WITH NEW FASTENERS PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND LOWER CARGO COMPARTMENT FORWARD DOOR OUTER SKIN DENT, NICK DAMAGES AND INTERIM REPAIR AT STA 320.0000. REPAIR ACCOMPLISHED, REMOVED DAMAGED PLATING IAW DC8 SRM 51-1-21 PG 1. FABRICATED NEW PLATING (2014T60 0.050"(P.N5779925-3N) IAW DC8 SRM 52-4-1 PG 3. CLEANED TREATED AND PRIMED AREA AND NEW PLATING IAW DC8 SRM 51-1-15 PG 1. APPLIED PRC SEALANT ON FAYING SURFACES AW DC8 SRM 51-1-15 PG1. INSTALLED NEW PLATING PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 91,246 hrs · 29,801 cycles

DURING A ROUTINE C CHECK INSPECTION, FOUND AFT LOWER CARGO COMPARTMENT FORWARD DOOR PLATING WERE DAMAGE AND INTERIM REPAIRS STA 1160.000 AT 1220.000. REPAIR ACCOMPLISHED, REMOVED EXTERNAL PLATING WITH INTERIM REPAIR, CLEANED, TREATED AND PRIMED AREA. APPLIED PRC SEALANT ON FAYING SURFACES. INSTALLED NEW PLATING PER DOUGLAS STRUCTURAL REPAIR MANUAL.

Part: WARNING LIGHT — WILL NOT TEST · airframe 91,127 hrs · 29,736 cycles

DURING DESCENT, NR 1 ENG FIRE WARNING SYSTEM SHORT LIGHT ILLUMINATED AND FIRE WARNING WOULD NOT TEST. NR 1 ENGINE SHUT DOWN IN FLIGHT. MAINTENANCE NOTED ENGINE IS WITHIN LIMITS PER ALL APPLICABLE MANUALS. MAINTENANCE CLEANED AND RESECURED WIRING CONNECTORS ON UPPER ENGINE HOT SECTION FIRE LOOP. OPS CHECK GOOD IAW DACO 70 SERIES MM CHAPTER 26-10-1.

Part: WARNING LIGHT — ILLUMINATED (NR 1 ENGINE OIL) · airframe 66,339 hrs · 17,195 cycles

DURING TAKEOFF FROM TAPA CREW REJECTED TAKEOFF DUE TO NR 1 ENGINE OIL LOW PRESSURE LIGHT ILLUMINATING AT 110KNTS. CREW RETURNED TO REMOTE PARKING WITHOUT INCIDENT. BRAKE ENERGY CHART CHECKED. MAINTENANCE DEFERRED IN ACCORDANCE WITH MEL 79-7 CAT "D".

Part: ENGINE — FLAMED OUT (NR 1) · airframe 90,814 hrs · 29,571 cycles

DURING FLIGHT AT 34.0 FL AT 88 PERCENT N1, RPM FLUXED APPROX. 8 PERCENT ROM 80 TO 88 PERCENT ON NR 1 ENGINE, ENGINE FLAMED OUT. DESCENDED TO FL250 ATTEMPTED RESTART WITH PMC ON ENG WOULD NOT RESTART, SECOND ATTEMPT WITH PMC OFF ENGINE RELIGHTED, CONTINUED REMAINDER OF FLIGHT WITH PMC OFF. CREW LANDED IN KNGU WITHOUT INCIDENT. MAINTENANCE DEFERRED THIS ITEM PER MEL 73-01.CAT-C WITH NO FLY DATE 04/09/04. AIRCRAFT WAS RETURNED TO SERVICE.

Part: WARNING LIGHT — ILLUMINATED (ANTI SKID SYSTEM) · airframe 90,372 hrs · 29,416 cycles

WHEN LANDING GEAR WAS EXTENDED THE ANTI-SKID INOP LIGHT AND LAO AND LAI LIGHTS ILLUMINATED. LAO AND LAI LIGHT REMAINED ILLUMINATED IN MANUAL ON THE SKID MONITOR PANEL. RECYCLED MAIN LANDING GEAR, ANTI-SKID CONTROL SWITCH AND RESET CIRCUIT BREAKER, NO HELP. CREW HAD TO OVER FLY KEWR FOR ANTI-SKID INOP, AND LANDED AIRCRAFT AT KBDL WITHOUT INCIDENT. MAINTENANCE AT KBDL DEFERRED ANTI-SKID AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: WARNING LIGHT — FALSE INDICATION (CARGO DOOR) · airframe 90,097 hrs · 29,290 cycles

CREW REJECTED TAKE-OFF FROM KEWR WHEN BELLY DOOR OPEN LIGHT CAME ON DURING TAKE-OFF ROLL. LIGHT EXTINGUISHED AFTER REJECT. MAINTENANCE INSPECTED ALL DOORS AND SWITCHES IAW ALL APPLICABLE MANUALS AND NO DEFECTS WERE NOTED. AIRCRAFT WAS RETURNED TO SERVICE.

Part: PROXIMITY SWITCH — LOOSE (MLG) · airframe 89,611 hrs · 29,062 cycles

DURING TAKEOFF FROM KRFD TO KLRD SELECTED GEAR UP AND " DOORS NOT LATCHED" LIGHT REMAINED ILLUMINATED. ALT LIGHTS WERE OUT. TEST SWITCH SHOWED LEFT HAND DOOR AT FAULT. RAN CHECKLIST, CYCLED GEAR, BOTH THE ALTERNATE AND MAIN DOOR LIGHT WOULD NOT EXTINGISH. FLIGHT CONTINUED TO KLRD WITH AN UNEVENTFUL LANDING.MAINTENANCE FOUND LOOSE HARDWARE ON LEFT MAIN DOOR UPLATCH SWITCH. HARDWARE WAS RESECURED IN ACCORDANCE WITH DOUGLAS DC-8 MAINTENANCE MANUAL.OPERATIONAL CHECK GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: CONNECTOR — LOOSE (NR 4 ENG EGT) · airframe 89,601 hrs · 29,055 cycles

DURING CRUISE FROM TOL ENROUTE TO DFW NR 4 EGT ROSE ABNORMALLY, THEN DROPPED TO "0". AS A PRECAUTIONARY MEASURE FLIGHT CREW ELECTED TO SHUTDOWN NR 4 ENGINE. AN UNEVENTFUL LANDING WAS MADE IN DFW. UPON INSPECTION MAINTENANCE DISCOVERED LOOSE CONNECTOR ON HARNESS. THIS WAS SECURED AND SYSTEM OPERATIONALLY CHECKED GOOD. ALL WORK COMPLETED PER APPLICABLE MANUALS AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: WARNING LIGHT — ILLUMINATED (MLG) · airframe 89,467 hrs · 28,999 cycles

DURING CLIMB FROM KEWR TO KTOL GEAR RETRACTION DOOR NOT LATCHED LIGHT STAYED ILLUMINATED. CREW USED MAIN GEAR ISOLATION SWITCHES SELECTED TO LT AND LATCH LIGHT WENT OUT. RT SELECTED LATCHED LIGHT STAYED ON AND THE ALTERNATE MAIN LANDING GEAR DOOR LIGHTS REMAINED OUT. GEAR WAS CYCLED. INSPECTION IS ON GOING. AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED.

Part: PROXIMITY SWITCH — OUT OF ADJUST (MLG) · airframe 89,454 hrs · 28,987 cycles

DURING CLIMB FROM KTOL TO KMCO THE CREW RAISED GEAR DOOR AND THE NOT LATCHED LIGHT STAYED ILLUMINATED. GEAR WAS RECYCLED, LEFT LIGHT WENT OUT AND RIGHT LIGHT STAYED ON. MAINTENANCE REMOVED RIGHT MAIN LANDING GEAR DOOR PROXIMITY SWITCH AND BRACKET. FABRICATED AND INSTALLED DOUBLER AND FILLER FOR PROXIMITY SWITCH. THEN SWAPPED PROXIMITY BOXES, REINSTALLED AND OPERATIONALLY CHECKED PROXIMITY SWITCH IN ACCORDANCE WITH DOUGLAS AIRCRAFT MAINTENANCE MANUEL. OPERATIONAL CHECK GOOD. AIRCRAFT RETURNED TO SERVICE.

Part: HINGE — WORN (MLG DOOR) · airframe 89,432 hrs · 28,978 cycles

DURING TAKEOFF FROM KTOL TO KLAX ON GEAR RETRACTION HANDLE UP DOOR UNLATCHED LIGHT STAYS ILLUMINATED. UP LATCH CHECK LIGHT STAYED ILLUMINATED AND REMAINED ILLUMINATED WITH HANDLE UP. INSPECTION IS ON GOING AND AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE REMOVED AND REPLACED MULTIPLE PARTS. OPERATIONAL CHECK GOOD IN ACCORDANCE WITH THE DOUGLAS AIRCRAFT MAINTENANCE MANUEL. AIRCRAFT RETURNED TO SERVICE.

Part: LIGHT — ILLUMINATED · airframe 89,402 hrs · 28,974 cycles

DURING FLIGHT, LANDING GEAR DOOR NOT LATCHED LIGHT STAYED ILLUMINATED IN FLIGHT. UPLATCH CHECK OKAY. CREW CYCLED GEAR AND LIGHT FAILED TO EXTINGUISH. INSPECTION IS ON GOING, AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE PERFORMED A GEAR UP ENGAGEMENT FUNCTIONAL TEST IN ACCORDANCE WITH ATI MEL SPECIAL PROCEDURE 32.8, OPERATIONAL CHECK GOOD. MULTIPLE EXTENSIONS AND RETRACTIONS WERE PERFORMED ALONG WITH A GEAR POSITION INDICATING AND WARNING SYSTEM TEST. OPERATIONAL CHECKS WERE GOOD IN ACCORDANCE WITH THE DOUGLAS AIRCRAFT MAINTENANCE MANUAL AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: PROXIMITY SWITCH — DIRTY · airframe 89,354 hrs · 28,962 cycles

!AFTER DEPARTURE FROM ATL ENROUTE TO MCO. DURING GEAR RETRACTION CREW NOTED MLG "GEAR DOOR NOT LATCHED" LIGHT ILLUMINATED.CREW CYCLED GEAR AND LIGHT FAILED TO EXTINGUSH. **INSPECTION IS ONGOING AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED. MAINTENANCE FOUND RIGHT HAND MAIN LANDING GEAR DOOR SWITCH CANNON PLUG DIRTY. CANNON PLUG WAS REMOVED, CLEANED AND REINSTALLED IN ACCORDANCE WITH DOUGLAS AIRCRAFT MAINTENANCE MANUAL. OPERATIONAL CHECK GOOD.

Part: MECHANISM — OUT OF ADJUST (MLG UPLOCK) · airframe 89,349 hrs · 23,958 cycles

AFTER DEPARTURE FROM BGTL TO KWRI DURING GEAR RETRACTION CREW NOTED DOOR NOT LATCHED LIGHT ILLUMINATED. CREW CYCLED GEAR, LIGHT EXTINGUISHED AND GEAR PASSED UPLATCH CHECK. CREW MADE UNEVENTFUL LANDING IN KWRI. MAINTENANCE PLACED ITEM ON MEL. AIRCRAFT WAS MOVED TO GSO FOR T/S OF MEL ITEM. GSO MAINTENANCE ADJUSTED RT MLG UPLATCH INTERLOCK MECHANISM AND ACHEIVED A GOOD OPERATIONAL CHECK. ALL WORK COMPLETED PER APPLICABLE MANUALS AND AIRCRAFT RETURNED TO SERVICE.

Part: WARNING LIGHT — ILLUMINATED (MLG DOORS) · airframe 89,302 hrs · 28,945 cycles

AFTER DEPARTURE FROM TOL EN ROUTE TO LAX. DURING UPLATCH CHECK CREW NOTED DOORS NOT LATCHED LIGHT ILLUMINATED. CREW FOLLOWED PROCEDURE AND CYCLED LANDING GEAR. DOORS NOT LATCHED LIGHT REMAINED ILLUMINATED. APPROX 15 MINUTES LATER LIGHT EXTINGUSHED. FLIGHT PROCEEDED TO LAX FOR AN UNEVENTFUL LANDING. MAINTENANCE PERFORMED CHECK OF THIS SYSTEM PER APPLICABLE MANUALS AND WAS UNABLE TO DUPLICATE. AIRCRAFT WAS RETURNED TO SERVICE.

Part: LUBRICATION UNIT — FAULTY (NR 2 ENGINE) · airframe 89,298 hrs · 28,944 cycles

AFTER DEPARTURE FROM PDX DURING CRUISE EN ROUTE TO EWR CREW NOTED OIL PRESSURE INDICATION FLUCTUATING ON THE NR 2 ENGINE. POWER WAS RETARDED, OIL PRESSURE WARNING ILLUMINATED AND NR 2 ENGINE WAS SHUTDOWN. CREW ELECTED TO CONTINUE TO TOL AND MADE AN UNEVENTFUL LANDING. UPON INSPECTION MAINTENANCE FOUND A DEFECTIVE LUBE UNIT. THIS COMPONENT WAS REPLACED AND A GOOD OPERATIONAL CHECK WAS COMPLETED. ALL MAINTENANCE PERFORMED IAW APPLICABLE MANUALS AND AIRCRAFT RETURNED TO SERVICE.

Part: CONTROL VALVE — FAILED (MLG DOOR) · airframe 89,229 hrs · 28,916 cycles

AFTER TAKEOFF CREW NOTED DOORS NOT LATCHED LIGHT ILLUMINATED. CREW CYCLED LANDING GEAR AND LIGHT REMAINED ILLUMINATED. AFTER APPROX 30 MINUTES LIGHT EXTINGUISHED. AFTER AN UNEVENTFUL LANDING IN BFI MAINTENANCE INSPECTED SYSTEM AND DETERMINED PROBLEM IS INDICATION ONLY. ALL WORK PERFORMED PER APPLICABLE MANUALS. ITEM WAS DEFERRED UNDER MEL AND AIRCRAFT RETURNED TO SERVICE. IN ORDER TO CLEAR THIS MEL ITEM MAINTENANCE REMOVED AND REPLACED THE RT MLG DOOR ACTUATOR CONTROL VALVE. AFTER NUMEROUS OPERATIONAL CHECKS IT WAS DETERMINED THIS ITEM IS CORRECTED. ALL WORK COMPLETED PER APPLICABLE MANUALS, MEL ITEM CLEARED AND AIRCRAFT RETURNED TO SERVICE.

Part: SWITCH — FAILED · airframe 89,143 hrs · 28,883 cycles

AFTER DEPARTURE FROM BFI DURING GEAR RETRACTION CREW NOTED RIGHT HAND MAIN LANDING GEAR DOOR WARNING LIGHT ILLUMINATED. DURING GEAR RECYCLE IT WAS ADDITIONALLY NOTED THAT THE RIGHT HAND MAIN LANDING GEAR DOWN AND LOCKED LIGHT FAILED TO ILLUMINATE. UPON COMPLETION OF LANDING GEAR RECYCLE ALL INDICATIONS WERE NORMAL. THE CREW PROCEED TO PDX FOR AN UNEVENTFUL LANDING. DURING INSPECTION MAINTENANCE NOTED THE RIGHT HAND MAIN LANDING GEAR DOWNLOCK INDICATING SWITCH HAD FAILED. MAINTENANCE REPLACED THIS SWITCH AND PERFORMED GEAR RETRACT CHECK PER THE AIRPLANE MAINTENANCE MANUAL. ALL OPERATION CHECKED GOOD AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SOCKET — LOOSE (COCKPIT) · airframe 89,095 hrs · 28,855 cycles

DURING CLIMB FROM DFW CREW NOTED LANDING GEAR DOOR NOT LATCHED LIGHT ILLUMINATED. THE GEAR WAS CYCLED AND AN UPLATCH CHECK PERFORMED. THE UPLATCH CHECK INDICATED THE GEAR SAFELY STOWED BUT LIGHT REMAINED ILLUMINATED. CREW CONTINUED TO LRD FOR AN UNEVENTFUL LANDING. UPON INSPECTION BY MAINTENANCE, THE INDICATING LIGHT SOCKET WAS FOUND TO BE INSECURE. THE LIGHT SOCKET WAS PROPERLY SECURED PER THE AIRCRAFT MAINTENANCE MANUAL, A SUCCESSFUL OPERATIONAL CHECK PERFORMED AND THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 88,277 hrs · 28,555 cycles

AFTER TAKEOFF FROM MEM, THE FLIGHT CREW NOTICED NR 1 ENGINE INDICATIONS STARTED FLUCTUATING. AFTER ENGINE IDLE DOWN NO CHANGE IN ENGINE INDICATION, THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES AND SHUTDOWN THE NR 1 ENGINE. THE FLIGHT CONTINUED TO DFW FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND PERFORMED VISUAL AND MAINTENANCE CHECKS IN ACCORDANCE WITH DOUGLAS MAINTENANCE MANUAL AND THE GENERAL ELECTRIC CFM56 MAINTENANCE MANUAL WITH NO FAULTS NOTED. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: ACTUATOR — DEFECTIVE (MLG DOOR UPLOCK) · airframe 88,900 hrs · 28,787 cycles

EN ROUTE FROM DFW TO IAH, THE DOOR NOT LATCHED LIGHT REMAINED ILLUMINATED DURING THE GEAR UP LATCH CHECK. THE FLIGHT CREW CYCLED THE LANDING GEAR BUT THE WARNING INDICATION REMAINED THE SAME. THE FLIGHT CONTINUED TO IAH FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND DISCOVERED THE RT UPLOCK ACTUATOR DEFECTIVE. MAINTENANCE REPLACED THE UPLOCK ASSEMBLY AND PERFORMED SUCCESSFUL OPERATIONAL CHECKS IN ACCORDANCE WITH THE DOUGLAS REPAIR MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: CYLINDER — DEFECTIVE (GEAR DOOR) · airframe 88,897 hrs · 28,786 cycles

ENROUTE FROM LAX TO TOL, THE LANDING GEAR DOOR NOT LATCHED LIGHT REMAINED ILLUMINATED FOLLOWING LANDING GEAR RETRACTION. THE FLIGHT CREW CYCLED THE GEAR AND THE LIGHT EXTINGUISHED. THE FLIGHT CONTINUED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE GEAR DOOR ACTUATOR CYLINDER DEFECTIVE. MAINTENANCE REPLACED THE CYLINDER AND PERFORMED A SUCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE

Part: STRIKER — DIRTY (GEAR DOOR) · airframe 88,644 hrs · 28,729 cycles

AFTER TAKE OFF FROM RMS, THE LANDING GEAR DOOR NOT LATCHED LIGHT REMAINED ILLUMINATED FOLLOWING LANDING GEAR RETRACTION. THE FLIGHT CREW CYCLED THE GEAR AND THE LIGHT WAS EXTINGUISHED. THE FLIGHT CONTINUED TO GSO FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT, CLEANED THE SWITCHES AND STRICKER AND PERFORMED OPERATIONAL CHECKS WITH NO DEFECTS NOTED IN ACCORDANCE WITH THE DOUGLAS MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: WARNING SYSTEM — MALFUNCTIONED (COCKPIT) · airframe 88,549 hrs · 28,693 cycles

AFTER TAKE OFF FROM BRO, THE LANDING GEAR DOOR NOT LATCHED LIGHT REMAINED ILLUMINATED FOLLOWING LANDING GEAR RETRACTION. THE FLIGHT CREW CYCLED THE GEAR AND THE LIGHT EXTINGUISHED. THE FLIGHT CONTINUED TO MEM FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND PERFORMED OPERATIONAL CHECKS WITH NO DEFECTS NOTED IN ACCORDANCE WITH THE DOUGLAS MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: GYRO — DEFECTIVE (COCKPIT) · airframe 88,286 hrs · 28,560 cycles

EN ROUTE FROM TOL, THE FLIGHT CREW NOTICED THE PITCH AND ROLL FLAGS DISPLAYED ON THE CAPTAINS AND FIRST OFFICERS ELECTRONIC ATTITUDE DIRECTION INDICATOR. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES AND RETURNED TO TOL FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND BOTH FOG GYROS TO BE DEFECTIVE. MAINTENANCE REMOVED AND REPLACED THE FOG GYROS IN ACCORDANCE WITH THE MAINTENANCE MANUAL AND PERFORMED SUCCESSFUL OPERATIONAL CHECKS. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — CORRODED (STA-21TO70) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO BELLY SKIN AT STA.-21TO70 AND L31L-L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DHSK 606-485. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SPLICE PLATE — CORRODED (STA1580-1600) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO AFT ACCY COMPARTMENT SPLICE PLATE AT STA.1580-1600 AND LBL46, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-1-0, 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — DENTED (STA. XFS157-163) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DENT DAMAGE TO L/H WING AUX TANK UPPER SKIN AT STA. XFS157-163, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DHSK 606-294.

Part: INTERCOSTAL — CORRODED (STA970-980) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO 4 INTERCOSTALS AT STA.970-980 AND RBL48-55 AND R/H W/W AFT FRAME, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-1-0, 51-1-21, 51-1-21A. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CRACKED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FRAME AT STA.55 AND L24L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 53-2-0 FIG.2.

Part: DOUBLER — CRACKED (LT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO LT WING L/E INTERNAL DOUBLER AT STA. XFS572.51, 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 51-1-21, 51-1-20D.

Part: ANGLE — CRACKED (STA1160 L33L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO C-PIT CROSS SLIDE FWD JAMB TRACK GUIDES AT STA. 1160 AND L33L-L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0 AND DHSK606-071.

Part: SKIN — DAMAGED (XRS210 LH WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTANCE VISIT FOUND DAMAGE TO L/H WING T/E SKIN AT STA. XRS210, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 57-2-0 FIG2A.

Part: SKIN — CORRODED (STA1400 L33-34R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO D-PIT LOWER R/H FUSELAGE SKIN AT STA.1400 AND L34R-L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DHSK 606-616.

Part: SKIN — CRACKED (WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO LOWER WING SKIN STRINGER 64L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DMSK606-470.

Part: LONGERON — CORRODED (STA320 L29L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON AT STA.320 AND L29L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-2-2 FIG10 AND DWG#9754913. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CRACKED (STA.55 L24R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FRAME AT STA.55 AND L24R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D, 51-1-11, 53-2-0 FIG2.

Part: WEDGE — DENTED (STA340-410) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DENTED DAMAGE TO L/H O/B FLAP T/E WEDGE AT STA.340-410, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21.

Part: ANGLE — CRACKED (D-PIT DOOR JAMB) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO ANGLE AT D-PIT DOOR JAMB LOWER SEAL DEPRESSOR, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-21A.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO INTERCOSTAL AT STA.355, 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 51-1-21, 57-3-3, 51-1-20D.

Part: DOUBLER — CHAFED (NR 3 ENG COWL) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CHAFF DAMAGE TO NR 3 ENGINE I/B FAN COWL INNER DOOR, 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 71-2-8 PAR.5C.

Part: VANE — CORRODED (LT WING TE FLAP) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LT WING NR 1 FLAP VANE FITTING, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTAKLLED IAW DC-8 MM 27-51-10.

Part: DOUBLER — DAMAGED (LH IB SLOT VANE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND SCREWS PULLING THRU INBOARD END OF L/H INBOARD SLOT VANE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 51-1-26, 51-3-0.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND ELONGATION DAMAGE TO A-PIT CROSS SLIDE TORQUE BOX BATH TUB FITTING HOLES AT STA.320 AND L29L, 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 53-20-0FIG2D.

Part: FITTING — CRACKED (STA.270 L30R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FITTING AT STA.270 AND L30R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-20D.

Part: FITTING — CRACKED (STA.339) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO L/H FLAP BASE FITTING AT STA.339, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0, 27-2-4 FIG5.

Part: PANEL — CORRODED (XRS-6 TO XRS20) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO L/H UPPER SKIN FORWARD OF CENTER SPAR AT STA. XRS-6 TO XRS20, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DHSK606-880. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: PANEL — DELAMINATED (STA.219) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DELAMINATION DAMAGE TO L/H WING LWR T/E PANEL INBOARD OF FLAP HINGE AT STA.219, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CORRODED (STA310 L32-33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT BATH TUB FITTING AT STA.310 AND L32R-L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-2-0 FIG2D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: STIFFENER — CORRODED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO HORIZONTAL STIFFNERS IN RT MLG W/W AT STA.980, 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 51-1-20D AND DWG 5640915.

Part: STIFFENER — CORRODED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO HORIZONTAL STIFFNERS IN RT MLG W/W AT STA.980, 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 51-1-20D AND DWG 5640915.

Part: FRAME — CORRODED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT CROSS SLIDE DOOR JAMB FLOOR SUPPORT AT STA.280 AND L32L, 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 51-3-0, 51-1-21.

Part: FITTING — CORRODED (STA315-340 L32R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO BATH TUB FITTING AT STA.315-340 AND L32R-L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 53-2-0 FIG2D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SPLICE — CORRODED (STA1020 L30L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FRAME AT STA.1020 AND L30L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 53-2-0, 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CORRODED (STA1100 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FRAME AT STA.1100 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20A&D, 51-1-21, AND DWG#5764343. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CRACKED (STA.313 L33R-L32) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO BATH TUB FITTING AT STA.313 AND L33R-L32R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-2-0 FIG2D, 51-1-21.

Part: PANEL — DELAMINATED (STA.410) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DELAMINATION DAMAGE TO L/H WING LOWER T/E PANEL I/B OF FLAP HINGE AT STA.410, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21. (CORROSION DAMAGE RECORDE IN EWA CORROSION PROGRAM).

Part: DOUBLER — CRACKED (STA.35-70 L34L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO INTERNAL DOUBLER AT STA.35-70 AND L34L-L34R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21 AND DWG#5623836.

Part: SHEAR TIE — CORRODED (STA35 L34L-L34R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO SHEAR TIE AT STA.55 AND L34L-L34R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21 AND DWG#5613836. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SHEAR TIE — CORRODED (STA.35 L34L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO DOOR PAN SHEAR TIE AT STA.35 AND L34L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21 AND DWG#5613836. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SEAT TRACK — WORN (STA.1480 BL.0) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND WORN DAMAGE TO SEAT TRACK AT STA.1480 AND BL.0, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-2-3 FIG8A.

Part: DOUBLER — CORRODED (STA.8-70 L30L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION TO L/H INTERNAL DOUBLER AT STA.8-70 AND L30L-L34R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-1-0, 51-1-20D, 51-1-21 AND DWG#5613862. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SEAT TRACK — WORN (STA.513 RBL25) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND WORN DAMAGE TO SEAT TRACK AT STA.513 AND RBL25, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-2-3 FIG8A.

Part: ANGLE — CORRODED (STA.1750-1790) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO R/H SIDE OF VERT. STAB LWR SKATE ANGLE AT STA.1750-1790, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-0-25 FIG16A. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: RIB — CHAFED (LT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CHAFF DAMAGE TO LT WING CENTER L/E RIB AT STA. XS510, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 57-2-0 FIG2A.

Part: PAN — CORRODED (STA320 L32R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT CROSS SLIDE DOOR PAN AT STA.320 AND L32R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 52-2-0 FIG2 AND 52-1-0, 51-3-0, 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CORRODED (STA.1000 L36) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FRAME AT STA.1000 AND L36, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 51-1-20D, 51-1-21 AND DHSK606-605. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: WEB — CRACKED (STA35-40 L24-25L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO WEB AT STA.35-40 AND L24L-L25L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-1-0, 51-1-20D AND DWG#5709134.

Part: STRUCTURE — CRACKED (RT WING TE FLAP) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO RTO/B FLAP I/B TEE ANGLE AT STA. XF164, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 57-2-0 FIG2.

Part: RIB — CHAFED (LT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CHAFF DAMAGE TO LT WING L/E RIB AT STA. XS250, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 57-2-0 FIG2.

Part: FLOORBEAM — CORRODED (RBL24) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOORBEAM ATS STA.1700 AND RBL 24, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DHSK606-343. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (VERT STAB RH ANG) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO VERTICAL STAB R/H ATTACH ANGLE 10" FWD OF FWD SPAR, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 55-2-0 FIG.6. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: TRACK — CRACKED (DOOR FRAME) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO C-PIT CROSS SLIDE AFT JAMB TRACK GUIDE AT STA.1220 AND L32L, 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 51-1-21, 51-1-20D, 51-3-0 AND DHSK606-070-1.

Part: FITTING — CRACKED (C-PIT) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO C-PIT CROSS SLIDE DOOR FWD UPPER CUTOUT SUPPORT FITTING, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DWG#3757794.

Part: HINGE — CRACKED (STA219 RH FLAP) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H O/B FLAP SPRING PANEL I/B HINGE AT STA.219, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-3-0.

Part: DOUBLER — CRACKED (AILERONPANEL#541) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO L/H I/B AILERON PANEL #541 INTERNAL DOUBLER. DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DHSK606-513.

Part: SKIN — CORRODED (XW408 STR.6) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LT WING UPPER SKIN AT STA. XW408 AND STR.6, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-2-1 FIG21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CRACKED (XRS261 STR13) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO LT. WING UPPER SKIN AT STA. XRS261 AND STR.13, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-2-1 FIG11.

Part: PANEL — GOUGED (STA.410) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND GOUGED DAMAGE TO L/H FLAP AT STA.410, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 51-3-0.

Part: INTERCOSTAL — GOUGED (STA515-520 L31R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND GOUGED DAMAGE TO B-PIT DOOR FWD JAMB INTERCOSTAL AT STA.515-520 AND L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D, AND DWG#5616520.

Part: WEB — MISDRILLED (FWD ENTRY DOOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DRILL DAMAGE TO FWD ENTRY DOOR INNER SKIN FWD LOWER WEB, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21 AND DWG#5615405.

Part: WEB — TOOL DAMAGE (STA70 L11L-L12L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DRILLED DAMAGE TO FWD ENTRY DOOR TORQUE BOX WEB AT STA.70 AND L11L-L22L, 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 51-1-21, 51-1-20D AND DWG 5597646-111.

Part: WEB — CORRODED (STA515-520) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO B-PIT TORQUE BOX WEB AT STA515-520, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-4, 51-1-20D AND DWG#5616520. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (XRS22.750 STR#3) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO R/H UPPER WING SKIN AT STA. XRS22.750 AND STR#3, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-2-0 FIG.7. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: INTERCOSTAL — TOOL DAMAGE (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DRILL DAMAGE TO D-PIT TORQUE BOX WEB INTERCOSTAL AT STA.1440 AND L32R-L34R, 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 53-2-0 FIG.1F AND DWG 5640231 AND DWG 5616674.

Part: FITTING — CORRODED (STA340 L31R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT FRAME BANNANA FITTING AT STA.340 AND L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0, 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SUPPORT — CORRODED (STA340 L32L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT CROSS SLIDE DOOR JAMB FLOOR SUPPORT AT STA.340 AND L32L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DHSK606831. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SEAT TRACK — WORN (FO'S SEAT TRACK) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND WORN DAMAGE TO FIRST OFFICERS SEAT TRACK I/B AND O/B, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0.

Part: FRAME — CRACKED (STA1395 L28R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FRAME AT STA.1395 AND L28R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 53-2-0 FIG.1B.

Part: LONGERON — CRACKED (STA45 L34R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FWD ACCY COMPARTMENT LONGERON AT STA.45 AND L34R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DWG#4615293.

Part: DOUBLER — CRACKED (STA. XS461.372) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING CENTER L/E AT STA. XS461.372, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND 57-2-0 FIG.2.

Part: LONGERON — CRACKED (STA8-70 L33L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO LONGERON AT STA. 8-70 AND L33L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 51-1-21 AND 51-1-20D.

Part: FITTING — CRACKED (STA1280 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO INTERCOSTAL ATTACH FITTING AT STA. 1280 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D.

Part: LONGERON — CRACKED (L17R #60 HOLE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FITTING AT L17R AND IN #60 HOLE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21 AND DWG#51616751.

Part: INTERCOSTAL — CRACKED (L/H AFT NLG DOOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO L/H AFTNLG DOOR INTERCOSTAL AT L32L-L33L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-20D.

Part: DOUBLER — TOOL DAMAGE (PAX DOOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DRILL DAMAGE TO FWD ENTRY DOOR FWD LOWER CORNER, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 53-2-3 FIG.1, 52-2-2 FIG.7, 51-1-21.

Part: SEAT TRACK — WORN (CAPT'S SEAT TRAC) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND WORN DAMAGE TO SEAT TRACK AT CAPTAINS SEAT UPPER I/B AND O/B, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0.

Part: BRACKET — CRACKED (PNUE DUCT SUPPOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H I/B L/E PNEUMATIC DUCT SUPPORT BRACKET, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-20D, DWG#56555.

Part: LONGERON — CORRODED (STA55-70 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FWD ACCY COMPARTMENT LONGERON AT STA.55-70 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-20D AND DWG#3642838. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SLIDE — CORRODED (STA280 L32R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT FLOOR SUPPORT DOOR JAMB AT STA.280 AND L32R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CRACKED (LH WING #1 SPOIL) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO LEFT WING UPPER #1 T/E SPOILER OUTBOARD HINGE FITTING, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-20D.

Part: ANGLE — CORRODED (STA1220-1228) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO C-PIT ANGLE AT STA.1220-1228 AND L27R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-20D AND DWG#9754947. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CHAFED (CARGO DOOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CHAFF DAMAGE A-PIT CROSS SLIDE LOWER LATCHES, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. RECEIVED PARTS AND INSTALLED IAW DC-8 SRM 53-20-0 FIG1F, 51-1-21.

Part: STRAP — CORRODED (STA35-55 LBL48) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A/C BAY SUB-FLOOR AT STA.35-55 AND LBL48, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 51-3-0 AND DHSK606673. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CRACKED (STA70 LBL30) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FLOOR BEAM SUPPORT ANGLE STA.70 AND LBL30, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0 AND DWG#5641543.

Part: FITTING — CORRODED (STA1320 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO SEAT TRACK SUPPORT FITTING AT STA.1320 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DWG#5758571. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: DOUBLER — CRACKED (RH WING DOUBLER) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING O/B L/E INBOARD INTERNAL DOUBLER, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-20D.

Part: DOUBLER — CORRODED (STA1640-1670) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO AFT ACCY COMPARTMENT INTERNAL SKIN DOUBLER AT STA.1640-1670 AND L31R-L32R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DHSK606-832. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SEAT TRACK — WORN (STA505 RBL45) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND WORN DAMAGE TO SEAT TRACK SCALLOP AT STA.505 AND RBL45, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-2-3 FIG.8A.

Part: INTERCOSTAL — CRACKED (STA440 L31R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO B-PIT INTERCOSTAL AT STA.440 AND L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DWG#5750726.

Part: FITTING — CRACKED (STA440-460 L31R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO B-PIT SPLICE FITTING AT STA.440-460 AND L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D.

Part: ANGLE — TOOL DAMAGE (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DRILL DAMAGE TO FWD ENTRY DOOR TORQUE BOX DOOR JAMB AT STA.70 AND L18L-L19L, 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 51-1-21, 51-1-20D AND DSK606-944.

Part: PANEL — CRACKED (STA. XW3) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO RT WING LOWER T/E PANEL I/B OF #1 SPOILER AT STA.XW3, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-20D.

Part: CLIP — CRACKED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO CTR KEEL LOWER DOOR FRAME ATTACH CLIP AT STA.958, 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 51-1-21, 51-1-20D.

Part: PANEL — DAMAGED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND HOLE DAMAGE TO FUSELAGE PANEL BETWEEN MLG WW DOORS AT STA.857-980, 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 SRM51-1-21, 51-20D.

Part: ANGLE — CORRODED (STA400 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO B-PIT FRAME AT STA.400 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 53-2-0 FIG.2. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CORRODED (STA980 BL60) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO RT WW FITTING AT STA.980 AND BL60, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — DENTED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DENT DAMAGE TO SKIN AT STA.165 AND L35R, 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 53-2-0 FIG.2.

Part: SEAT TRACK — WORN (STA952 LBL25) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND WORN DAMAGE TO SEAT TRACK SCALLOPS AT STA.952 AND LBL25, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM51-1-20D, 51-3-0, 53-2-3 FIG.8.

Part: SEAT TRACK — WORN (STA300 LBL60) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND WORN DAMAGE TO SEAT TRACK SCALLOPS AT STA.300 AND LBL60, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D, 51-3-0, 53-2-3 FIG.8.

Part: FITTING — CORRODED (STA1180 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO D-PIT DOOR JAMB TORQUE BOX FITTING AT STA.1180 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DHSK606-072. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: BRACKET — CRACKED (RH WING FIRE BOT) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING I/B AND O/B FIRE BOTTLE BRACKET, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-11 AND DC-8 MM 26-20-1 AND DWG#5640236.

Part: FITTING — CORRODED (STA320 L33R-L34R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT CROSS SLIDE TORQUE BOX BATHTUB FITTING AT STA.320 AND L33R-L34R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-11, 51-1-20D, 53-2-0 FIG.1F. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CORRODED (STA1060L31R-L34R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FRAME UPPER FRAME AT STA1060 AND L31R-L34R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D, 51-1-21, 53-2-0 FIG.2. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: INTERCOSTAL — TOOL DAMAGE (PAX DOOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DRILL DAMAGE TO FWD ENTRY DOOR TORQUE BOX, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-21D AND DWG 5597646.

Part: STRUCTURE — DAMAGED (TORQUE BOX) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DRILL DAMAGE TO FWD ENTRY DOOR TORQUE BOX TEE, 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 51-1-20D, 51-1-20, AND DWG 4614602.

Part: SEAT TRACK — WORN (STA160 LBL25) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND WORN DAMAGE TO SEAT TRACK AT STA.160 AND LBL25, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 53-2-3, 51-3-0.

Part: DOUBLER — CHAFED (LT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CHAFED DAMAGE TO LT I/B SLOT UPPER DOOR AT STA. XS250, 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 51-1-20D, 57-2-0 FIG.6.

Part: FITTING — CORRODED (STA270 L32R-L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT FWD TORQUE BOX BATHTUB FITTING AT STA.270 AND L32R-L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-11, 51-1-20D, 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CORRODED (STA447-453 L30R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO SPLICE FITTING AT STA. 447-453 AND L30R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DWG#4646163. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SPLICE — CRACKED (STA450 L33L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO B-PIT FITTING SPLICE AT STA.450 AND L33L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM51-1-21.

Part: INTERCOSTAL — CRACKED (STA620 L33L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO B-PIT INTERCOSTAL AT STA.620 AND L33L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-1-20D, 53-1-0, DWG#570837.

Part: DOUBLER — CORRODED (STA1560 LBL50) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FLOOR BEAM AT STA.1560 AND LBL50, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM51-1-20D AND DWG#606-316. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CRACKED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FITTING AT STA.1230 AND L33R, 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 51-1-20D.

Part: GUSSET — CORRODED (STA440-460 L30R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO GUSSET AT STA.440-460 AND L30R-L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DWG#4779940. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: DOUBLER — PUNCTURED (NR 4 ENGINE COWL) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND PUNCTURE DAMAGE TO NR 4 ENGINE O/B T/R COWL INNER HEAT, 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 51-1-20D AND DC-8 MM 78-31-10 FIG.806.

Part: FITTING — CRACKED (STA. 1180) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO MAIN CABIN R/H CUSP FITTING AT STA.1180, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D.

Part: ANGLE — CORRODED (STA1640 LBL32) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO AFT ACCY COMPARTMENT FLOOR BEAM AT STA.1640 AND LBL32, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-11, 51-1-20D AND DHSK606-453. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CRACKED (RH SERVICE DOOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H FWD UPPER CORNER OF FWD R/H SERVICE DOOR, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-3-0, 51-1-21A, 53-2-0 FIG14.

Part: DOUBLER — CORRODED (STA70 LBL24) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TOGALLEY BASE AT STA.70 AND LBL24, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21 AND DWG#5841414-95. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CRACKED (STA1240 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO INTERCOSTAL FRAME ATTACH FITTING AT STA.1240 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-11, 51-1-20D.

Part: DOUBLER — CRACKED (R/H SERV. DOOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO UPPER FWD CORNER OF FWD R/H SERVICE DOOR, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-3-0, 51-1-21A, 53-2-0 FIG.14.

Part: ANGLE — GOUGED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND GOUGED DAMAGE TO RT O/B FLAP PANEL, LT HINGE ANGLE AT STA.410, 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 51-1-21 AND DWG 5761745-39.

Part: SEAT TRACK — WORN (STA338 LBL45) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND WORN DAMAGE TO MAIN CABIN SEAT TRACK SCALLOPS AT STA.338 AND LBL45, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0, 53-2-0 FIG.8A, 51-1-20D.

Part: DOUBLER — CHAFED (LT MLG DOOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CHAFFED DAMAGE TO L/H MLG DOOR LOWER AFT STMP AND CORNER OF DOOR, 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 51-1-21, 52-2-0, 51-1-20A AND DWG 5616307.

Part: FITTING — CRACKED (STA.1140 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TOINTERCOSTAL ATTACH FITTING AT STA.1140 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-20-20D AND DWG#4758514-517.

Part: FITTING — CRACKED (STA270 L30R-L31R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO A-PIT FRAME FITTING AT STA.270 AND L30R-L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D, 51-1-3.

Part: FITTING — CRACKED (STA.1240 L35R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO INTERCOSTAL ATTACH FITTING AT STA.1240 AND L35R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D.

Part: ANGLE — CRACKED (STA. 910) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO L/H AFT WING TO BODY FAIRING SUPPORT BRACKETT, LOWER FORWARD ANGLE AT STA.910, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0, 51-1-11 AND DWG#3710351.

Part: FRAME — CORRODED (STA1120 L31R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO UPPER LIP OF FRAME AT STA.1120 AND L31R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 53-2-0 FIG.7 AND DWG#2537715. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CRACKED (STA1660 L21R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO AFT ACCY. COMPARTMENT FLOOR BEAM FITTING AT STA1660 AND L21R, 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 51-1-21, 51-1-20D, 51-3-0.

Part: SPLICE — BROKEN (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND BROKEN DAMAGE TO MAIN CABIN SEAT TRACK SCALLOPS AT STA.540 AND RBL60, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PART IAW DC-8 SRM 53-2-3.

Part: LONGERON — CORRODED (STA.660 L31L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LONGERON 31L AT STA.660, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D, 53-1-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: INTERCOSTAL — CRACKED (STA1520-1540) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO D-PIT INTERCOSTAL AT STA.1520-1540 AND L33L AND UNDER CARGO TRACK, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 51-3-0, 51-1-20D, 51-1-21A AND DWG#5751516.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO AFT ACCY. COMPARTMENT FLOOR BEAM AT STA.1660 AND RBL31, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 51-1-11 AND DHSK 600-456.

Part: BRACKET — CRACKED (RT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO RT AFT WING TO BODY FAIRING SUPPORT BRACKET LOWER FORWARD ANGLE BRACKET AT STA.910, 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 51-1-11, 51-3-0 AND DWG#5710351.

Part: RIB — CRACKED (XFS 785) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING L/E RIB AT STA. XFS785, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-2-0 FIG.2, 51-1-21.

Part: ANGLE — CRACKED (NR 2 NACELLE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO NR 2 ENGINE INLET COWL I/B STRAKE ON LOWER LATCH, 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 51-3-0, 51-1-21 AND DWG D51B11810.

Part: SKIN — GOUGED (STA. XRS340) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND GOUGED DAMAGE TO L/H O/B FLAP BELOW FLAP HINGE AT STA. XRS340, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 57-2-1 FIG.2.

Part: DOUBLER — BROKEN (RT ELEVATOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND BROKEN DAMAGE TO RT ELEVATOR O/B TIP CORNER BROKEN OFF, 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 55-2-0, 51-3-0, 51-1-21.

Part: PANEL — PUNCTURED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND PUNCTURE DAMAGE TO FLOOR PANEL AT STA.1760, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 53-2-3, 51-1-21.

Part: SKIN — CRACKED (LT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO LT WING O/B L/E LOWER SKIN AT STA.XFS597.5 AND DRAIN HOLE, 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 57-2-0 FIG.2A.

Part: RIB — CRACKED (RT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING O/B L/E UPPER RIBS AT STA. XFS716.25, 728.75, 735, 741.25, 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 51-1-20D, 57-2-0 FIG.2.

Part: SKIN — PUNCTURED (#1 ENG T/R COWL) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND PUNCTURE DAMAGE TO #1 ENGINE I/B T/R COWL INNER HEAT SHIELD, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DC-8 MM 78-31-10.

Part: RIB — CRACKED (XFS 778.25) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING O/B L/E RIB AT STA. XFS778.25, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-2-0 FIG.2.

Part: FRAME — MISDRILLED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND MISSDRILLED HOLE DAMAGE TO MAIN CABIN LT LOWER SIDE OF FRAME AT STA.1560, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 53-2-0 FIG.1F, 51-1-21.

Part: RIB — CRACKED (LT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO LT WING O/B L/E LOWER RIBS AT STA. XFS660-641.25-653.75, 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 51-1-21, 51-1-20D, 51-3-0.

Part: SPLICE — CRACKED (STA.610 L31L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO SPLICE AT STA.610 AND L31L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D, 53-1-01 AND DWG#3750257.

Part: DOUBLER — CRACKED (XFS 337) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING CENTER L/E INTERNAL DOUBLER LOCATED AT DRAIN HOLE AT STA. XFS337, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-120D, 51-1-21, 51-3-0 AND DHSK606-143.

Part: RIB — CRACKED (LT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACKED DAMAGE TO LT WING L/E UPPER RIB AT STA. XFS 610, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-2-0 FIG.2, 51-1-21.

Part: RIB — CRACKED (XFS616.25-622.5) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING O/B L/E UPPER RIB AT STA.XFS616.25-622.5, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-2-0 FIG.2.

Part: SKIN — CHAFED (HORIZONTAL STAB) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CHAFFING DAMAGE TO LT HORIZ STAB FIXED LOWER FAIRING AT AFT END, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DHSK 606-648.

Part: RIB — CRACKED (XFS 653.75) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING L/E LOWER RIB AT STA. XFS653.75, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-2-0.

Part: DOUBLER — CRACKED (LT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO L/H WING O/B L/E LWR INTERNAL DOUBLER AT STA.XFS597.5, 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 51-1-21, 51-1-20D AND DWG 5769600.

Part: SKIN — DENTED (STA.340) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DENT DAMAGE TO L/H O/B LOWER T/E WEDGE LOWER SURFACE AT STA. 340, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-7-1 FIG.4, 51-1-21A.

Part: SKIN — CORRODED (A-PIT DOOR RAMP) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO A-PIT DOOR RAMP SKIN, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21D AND DWG#9754058. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: INTERCOSTAL — CRACKED (A-PIT DOOR RAMP) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO A-PIT DOOR RAMP FORWARD INTERCOSTAL SUPPORT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DWG#9754058.

Part: WEB — DENTED (FWD ENTRY DOOR) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND DENT DAMAGE TO AFT LOWER CORNER WEB AT FORWARD ENTRY DOOR, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 51-1-21 AND DWG#5615403.

Part: SKIN — TORN (LT WING TOP T/E) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND TORN SKIN DAMAGE TO L/H WING UPPER T/E SKIN AT #1 SPOILER O/B HINGE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 57-2-0 FIG.2A, 51-1-21, 51-1-21A, 51-3-0.

Part: RIB — CRACKED (LT WING) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO LT WING O/B L/E LOWER RIB AT STA. XFS622.5, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 51-1-21, 51-3-0, 57-2-0 FIG.2.

Part: FRAME — CORRODED (STA460 L27R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO FRAME AT STA.460 AND L27R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED CORROSION AND FOUND TO BE WITHIN LIMITS IAW DC-8 SRM 51-1-8, 53-2-0 FIG.1F. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CRACKED (STA1260 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FLOOR SUPPORT ANGLE AT STA.1260 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D.

Part: RIB — CRACKED (XFS672.5-678.5) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING O/B L/E RIBS AT STA. XFS672.5-678.5, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. NDT HFCC INSP IAW SPM06-10-01.001. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-2-0 FIG.2, 51-1-20D.

Part: SKIN — CORRODED (STA1390 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CORROSION DAMAGE TO LOWER R/H FUSELAGE SKIN AT STA.1390 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 53-2-1 FIG.7. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CRACKED (R/H I/B FLAP) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H I/B FLAP I/B L/E IN TWO AREAS, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 57-7-1 FIG.2.

Part: RIB — CRACKED (XFS 610-566.25) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H WING O/B L/E UPPER RIB AT STA.XFS610-566.25, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. HFCC INSPECTION IAW SPM 06-10-01.001. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 57-2-0 FIG.2, 51-1-20D.

Part: RIB — CRACKED (STA.XFS691.25) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO L/H WING L/E UPPER RIB AT STA.XFS691.25, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DC-8 SRM 57-2-0 FIG.2.

Part: CHANNEL — CRACKED (A-PIT DOOR XSLID) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO A-PIT CROSS SLIDE DOOR RAMP AT HOLD OPEN STRUT ATTACH ANGLE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DWG#9754058.

Part: ANGLE — CRACKED (A-PIT DOOR RAMP) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO A-PIT DOOR RAMP I/B SUPPORT, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-20D AND DWG#9754058.

Part: ANGLE — CRACKED (STA.1280 L31L) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FLOOR SUPPORT ANGLE AT STA.1280 AND L31L, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DHSK606-749.

Part: SKIN — SCRATCHED (LT WING TE FLAP) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND SCRATCH DAMAGE TO LT WING O/B FLAP LOWER SKIN AT STA. XRS410, 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 57-2-0, 51-1-26, 51-1-21A, 57-2-0 FIG.2A.

Part: ANGLE — CRACKED (STA1300 L33R) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO FLOOR SUPPORT ANGLE AT STA.1300 AND L33R, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED REPAIR AND INSTALLED IAW DHSK 606-749.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO AFT ACCY COMP. CUSP MEMBRANCE AT STA.158-1600 AND RBL48, 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 51-1-21, 53-2-0 FIG.1D.

Part: FITTING — CRACKED (STA993 BL0-BL7) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TOR/H WW STIFFNER AT STA.933 AND BL0-BL7, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-3-0, 51-1-21 AND DWG#2718809.

Part: ANGLE — CRACKED (RH I/B FLAP) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO R/H INBOARD FLAP O/B END Z ANGLE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 57-7-1.

Part: CLIP — GOUGED (LT WING #4 SPOIL) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND GOUGED DAMAGE TO L/H WING #4 SPOILER O/B HINGE FITTING CLIP, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 57-1-0, 51-1-21.

Part: AILERON — CRACKED (L/H I/B AILERON) · airframe 88,247 hrs · 28,534 cycles

DURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO L/H INBOARD AILERON T/E WEDGE BETWEEN TRIM AND CONTROL TAB, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21, 57-8-1, 51-1-4, 51-1-11.

Part: TRANSFORMER — FAILED (COCKPIT LIGHT) · airframe 87,589 hrs · 28,214 cycles

ELECTRICAL SMOKE IN THE COCKPIT APPEARS TO COME OUT OF THE F/E PANEL. REMOVED AND REPLACED TRANSFORMER PER DC-8 M/M 33-00 ON FIRST OFFICERS SIDE. ALSO DEFECTED AREA UPPER F/E''S DESK PANEL. FOUND ALL COMPONENTS AND WIRING SECURE, NO DEFECTS.

Part: RADOME — LIGHTNING STRIKE (FUSELAGE) · airframe 87,201 hrs · 28,020 cycles

DURING CLIMBOUT, LIGHTNING STRIKE TO NOSE SECTION. DURING LIGHTNING STRIKE INSPECTION FOUND RADOME UNSERVICEABLE DUE TO LIGHTNING STRIKE. REMOVED AND REPLACED RADOME IAW DC-8 MM CHAPTER 53-50-1.

Part: STRUCTURE — LIGHTNING STRIKE (HORIZONTAL STAB) · airframe 87,188 hrs · 28,104 cycles

EN ROUTE FROM ORD TO HDY EB035 WAS STRUCK BY LIGHTNING. UPON INSPECTION OF ACFT IN HDY, A HOLE IN THE HORIZONTAL STAB WAS DISCOVERED. *S/D* REPAIRED DAMAGED AREA AS PER BOEING COMPANY SERVICE ENGINEERING CUSTOMERS SUPPORT MESSAGE EAF-ILN-00-00194H. THIS REPAIR CLASSIFIED AS A TEMPORARY REPAIR ACCEPTABLE FOR USE UNTIL NEXT ''C'' CHECK.

Part: INDICATOR — INOPERATIVE (COCKPIT) · airframe 87,149 hrs · 28,001 cycles

DURING CLIMBOUT FOUND NR 3 EGT GAUGE INOP (ANALOG ZERO, DIGITAL BLANK). SECURED ENGINE PER QRH. RESECURED BACK ON EGT HARNESS NR 3 ENG SYSTEM CHECKS NORMAL ON ENG RUN IAW DC-8 MM 77-20-0, CSD RECONNECTED. ENGINE CAL NR 3 SECURE AFTER OPENING.

Part: TRANSCEIVER — FAILED (COCKPIT)

WX RADAR FAILED IN FLT. REPLACED XCVR AND RADAR SCOPE, OPS CHECKS GOOD ON GROUND, NO DEFECTS NOTED AT THIS TIME.

Part: FLOORBEAM — CORRODED (BS 1700)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FLOORBEAM UNDER SEAT TRACK 3 ABOVE LONGERON 32 LEFT AT STA 1700. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR STRAP IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO- 99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CRACKED (WS 710)

DURING A MAINTENANCE VISIT FOUND A .25 INCH CRACK, RIGHT WING, EXTENDING FROM SCREW HOLE RIGHT WING O/B L/E I/B SEGMENT O/B EDGE AT STA XFS 710. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED FILLER AND DOUBLER IAW DC8 SRM 51-2-1 AND INSTALLED IAW DC8 SRM 57-2-1.

Part: SKIN — WORN (RT WING)

DURING A MAINTENANCE VISIT FOUND SCREWS MISSING, RIGHT WING, L/E DOUBLER O/B END OF O/B SLOT, MISSING, LOOSE, AND PULLING THROUGH. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: PIN — CORRODED (RT MLG)

DURING A MAINTENANCE VISIT FOUND CORROSION, RT MLG, RETRACT CYL. A PIN REPAIR PER CUSTOMER REQUEST IAW MA AI 3210-01:03 S/B 32-102, REF AD 71-25-09. ACCOMPLISHED INSPECTION, FOUND CORROSION, IN PIN BOSS. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC8 SRM 51-1-8. REPAIRED IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3 DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CRACKED (WS 878.75)

DURING A MAINTENANCE VISIT FOUND CORROSION AND CRACKS, RIGHT WING, I/B L/E O/B SEGMENT LOWER SURFACE AT XFS 878.750. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED DOUBLER AND FILLER IAW DC8 SRM 57-2-1 AND INSTALLED IAW DC8 SRM 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 1746)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, SKIN, JUST FWD OF TAIL SKID AT STA 1746, LONGERON 36. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED FILLER AND DOUBLER IAW DC8 SRM 53-2-1, INSTALLED FILLER AND DOUBLER IAW DC8 SRM 51-1-21 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CRACKED (BS 280)

DURING A MAINTENANCE VISIT FOUND A CRACK, FUSELAGE, LOWER ATTACH FITTING IN BOX FRAME AT STA 280, LONGERON 27 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED AND REPLACED FITTING IAW DC8 SRM 51-1-8 AND 51-1-21.

Part: SKIN — CORRODED (BS 717)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, BOTTOM SKIN AT STA 717, LONGERON 36. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLERS IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 710)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, O/B L/E O/B SEGMENT I/B EDGE AT STA XFS 710. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED FILLER AND DOUBLER IAW DC8 SRM 57-2-1 AND INSTALLED IAW DC8 SRM 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CRACKED (WS 227.335)

DURING A MAINTENANCE VISIT FOUND A CRACK, NR 3 STUB WING, UPPER SURFACE EMANATING FROM RIVET 2 FWD OF FRONT SPAR AT STA XS 227.335. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLER AND DOUBLER IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: SKIN — DAMAGED (TE FLAP)

DURING A MAINTENANCE VISIT FOUND DAMAGE, NR 1 LT FLAP WEDGE LOWER SKIN. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLERS IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: LONGERON — CORRODED (BS 1726 - 1745)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, LONGERON 36 BETWEEN STA 1726 AND STA 1745. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. INSTALLED REPAIR SPLICE IAW DC8 SRM 53-2-1 AND 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — DELAMINATED (RUDDER)

DURING A MAINTENANCE VISIT FOUND DELAMINATION, RUDDER TUB DELAMINATED LT SIDE AFT OF LOWER HINGE. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED AND REPLACED RUDDER TAB IAW DC8 M/M 27-21-1.

Part: FLANGE — CRACKED (TE FLAP)

DURING A MAINTENANCE VISIT FOUND A CRACK, RIGHT WING, O/B FLAP, NR 3 WEDGE I/B LOWER MOUNTING FLANGE. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED NUT PLATE IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: FLOORBEAM — CORRODED (BS 1746)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FLOOR SUPPORT UNDER CLIP NUTS AT STA 1746 BETWEEN BL 1-1/2 LEFT AND 20-1/2. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REPLACED H CHANNEL AND INSTALLED IAW DC8 SRM 51-1-21 AND 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CHAFFED (FUSELAGE)

DURING A MAINTENANCE VISIT FOUND PANEL 86 RUBBING ON FUSELAGE LT SIDE OF LOWER RUDDER. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM.. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. BLENDED OUT IAW DC8 SRM 51-1-8, LIMITS ACCEPTABLE PER FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: FLANGE — CRACKED (WING)

DURING A MAINTENANCE VISIT FOUND A CRACK, NR 2 STUB WING, 9.75 LEFT WING NR 2 STUB WING I/B FLANGE. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLER AND DOUBLER IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: FASTENER — DAMAGED (WS 463)

DURING A MAINTENANCE VISIT FOUND DAMAGE, RIGHT WING, FASTENER DAMAGED INSIDE NR 4 ALT FUEL TANK BY NR 4 PYLON AT XW 463 STR 58 LOWER SURFACE. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. FASTENER OK AS IS IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO- 99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: FITTING — CORRODED (BS 8)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, LONGERON 33 RIGHT END TIE FITTING IN FWD ACCESSORY BAY AT STA 8.00. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FITTING IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO- 99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CRACKED (TE FLAP)

DURING A MAINTENANCE VISIT FOUND A CRACK, LEFT WING, O/B FLAP LOWER SURFACE SKIN BULGED AND 2 CRACK 3 BELOW L/E, JUST UNDER CENTER HINGE. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: SKIN — CORRODED (LE FALP)

DURING A MAINTENANCE VISIT FOUND CORROSION, LEFT WING L/E, IMPROPER REPAIR LEFT WING O/B L/E O/B SECTION LWR SURFACE BETWEEN STA 822.50 TO XFS 841.250. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER AND FILLER IAW DC8 SRM 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CRACKED (NR 1 PYLON)

DURING A MAINTENANCE VISIT FOUND A CRACK, NR 1 PYLON, I/B TRIPLER (ANGLE) CRACKED 1.5. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM.. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED AND REPLACED ANGLES IAW DC8 SRM 51-1-6 AND 51-1-7, 51-1-20D.

Part: FLOORBEAM — CRACKED (BS 1680)

DURING A MAINTENANCE VISIT FOUND CORROSION CRACKS, FUSELAGE, FLOOR SUPPORTS, AT STA 1680 BL 35 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REPLACED H CHANNEL AND INSTALLED IAW DC8 SRM 51-1-21 AND 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOORBEAM — CORROSION (FUSELAGE)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FLOOR SUPPORT AT STA 1726, BL 31 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REPLACED H CHANNEL AND INSTALLED IAW DC8 SRM 51-1-21 AND 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CORRODED (BS 360)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FRAME, AT STA 360, AFT SIDE ABOVE LONGERONS 31 RIGHT AND LONGERON 29 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR ANGLE IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO- 99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 385 - 388)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, L/E BETWEEN NR 3 AND NR 4 ENG JUST O/B OF STALL WARNING TRANSDUCER BETWEEN XSF 385 AND XFS 388. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLERS AND DOUBLERS IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 304 - 397)

DURING A MAINTENANCE VISIT FOUND CORROSION, LEFT WING L/E, AROUND SCREW HOLES LEFT WING L/E CENTER SECTION UPPER SURFACE BETWEEN XFS 304.000 TO XFS 397.750. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: GUARD — CRACKED (BS 210)

DURING A MAINTENANCE VISIT FOUND A CRACK, CABIN, LONG SECTION OF MAIN CARGO SEAL GUARD BUMP RAIL AT STA 210 (EO). DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. WELDED CRACKED AREA IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3 DATED MAY 21, 1999.

Part: PIN — DAMAGED (LT MLG)

DURING A MAINTENANCE VISIT FOUND SPIRALED TOP AND BOTTOM HOLES, LEFT MLG RETRACT PIN BOSS THROUGH BOLT HOLE. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. SMOOTHED BORE, FLAP PEENED HOLE IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3 DATED MAY 21, 1999.

Part: SKIN — CORRODED (BS 680 - 702)

DURING A MAINTENANCE VISIT FOUND CORROSION, BOTTOM OF FUSELAGE BEACON ANTENNA FROM BASE AND AROUND SKIN BETWEEN STA 680 AND STA 702. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER AND FINGER DOUBLER IAW DC8 SRM 53-2-1. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 460 - 480)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, B-PIT LEFT FWD BETWEEN STA 460 AND STA 480 LEFT AT LONGERON 31 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLERS AND DOUBLERS IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOAT BOX — TWISTED (RT WING)

DURING A MAINTENANCE VISIT FOUND TUBE TWISTED, RIGHT WING, NR 4 A FLOAT BOX WELDED TUBE TWISTED. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED FLOAT BOX, WELDED TUBE IN PLACE IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999, INSTALLED FLOAT BOX IAW DC8 SRM 28-21-14.

Part: FLOORBEAM — CRACKED (BS 1680)

DURING A MAINTENANCE VISIT FOUND CORROSION CRACKS, FUSELAGE, FLOOR SUPPORTS, AT STA 1680, BL 14 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED NEW SUPPORT AND INSTALLED IAW DC8 SRM 51-1-21 AND 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CRACK (BS 280)

DURING A MAINTENANCE VISIT FOUND A CRACK, FUSELAGE A PIT FRAME DOOR BETWEEN BOLTS AT STA 280, BETWEEN LONGERONS 26 RIGHT AND LONGERON 27 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED FRAME PER DWG NR 2772795 AND INSTALLED IAW DC8 SRM 51-1-21.

Part: SKIN — CORRODED (WS 151 - 157)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING L/E, I/B L/E TANK UPPER SURFACE AROUND SCREW HOLES BETWEEN XFS 151.205 AND XFS 157.500. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLER AND DOUBLERS IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (BS 560)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, RT UPPER CUSP FRAME 560 AT STA 560 ATTACH ANGLE. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED AND REPLACED ATTACH ANGLE IAW DC8 SRM 51-1-21 AND 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 95 -101.25)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING L/E, TANK UPPER SURFACE AT SCREW HOLES BETWEEN STA XFS 95.000 AND XFS 101.250. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. /////CORRECTIVE ACTION///// REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLER AND DOUBLERS IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH #EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CRACKED (WS 566.25 - 603)

DURING A MAINTENANCE VISIT FOUND CORROSION AND CRACKS, RIGHT WING, O/B L/E I/B SEGMENT UPPER SURFACE BETWEEN STA XFS 566.250 TO XFS 603.750. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED FILLER AND DOUBLER IAW DC8 SRM 57-2-1 AND INSTALLED IAW DC8 SRM 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 7.50 - 26.25)

DURING A MAINTENANCE VISIT FOUND CORROSION, LEFT WING, I/B L/E UPPER SURFACE AT SCREW HOLES BETWEEN XFS 7.50 TO XFS 26.250.. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLERS AND DOUBLERS IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO- 99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SUPPORT — CRACKED (FUSELAGE)

DURING A MAINTENANCE VISIT FOUND A CRACK, FUSELAGE, C/D PIT DIVIDER AND SUPPORT FORMER CRACKED AND TORN. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED PARTITION IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO- 99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: PANEL — CORRODED (ELEVATOR)

DURING A MAINTENANCE VISIT FOUND CORROSION, AREA UNDER PANEL 69 LT ELEV INSIDE THROUGHOUT AREA BETWEEN XE 32.937 TO XE 50.000 FWD. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REPAIRED CORROSION IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 193.675)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, I/B L/E UPPER SURFACE AT XFS 193.675. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED FILLER AND DOUBLER IAW DC8 SRM 57-2-1 AND INSTALLED IAW DC8 SRM 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CRACKED (WS 491 & 503)

DURING A MAINTENANCE VISIT FOUND CRACKS, RIGHT WING, L/E JUST FWD O/B SLOT AT STA XFS 503.789 AND STA XFS 491.193. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. CRACKS ACCEPTABLE AS IS PER FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999.

Part: FITTING — GOUGED (ELEVATOR)

DURING A MAINTENANCE VISIT FOUND GOUGE, RIGHT ELEV, RT GEAR TAB ASSY, I/B FITTING GOUGED. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. BLENDED GEARED TAB I/B FITTING IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3 DATED MAY 21, 1999.

Part: SKIN — CORRODED (WS 7.50 - 26.25)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, I/B L/E UPPER SURFACE AT SCREW HOLES BETWEEN XFS 7.50 AND XFS 26.250. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED FILLER AND DOUBLER IAW DC8 SRM 57-2-1 AND INSTALLED IAW DC9 SRM 57-2-1 AND 51-1-12. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 878.750)

DURING A MAINTENANCE VISIT FOUND CORROSION, LEFT WING, O/B L/E O/B SEGMENT LOWER SURFACE AT XFS 878.750. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED DOUBLER AND FILLER AND INSTALLED IAW DC8 SRM 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 80)

DURING A MAINTENANCE VISIT FOUND CORROSION, LAV SERVICE DOOR FROM HINGE AT STA 80, LONGERON 24 RIGHT, FUSELAGE SKIN UNDER HINGE. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO- 99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOORBEAM — CRACKED (BS 1700)

DURING A MAINTENANCE VISIT FOUND CORROSION CRACKS, FUSELAGE, FLOOR SUPPORTS AT STA 1700 BL 29 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REPLACED H CHANNEL AND INSTALLED IAW DC8 SRM 51-1-21 AND 51-1-8. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 702)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, BOTTOM FUSELAGE SKIN AT STA 702, LONGERON 36. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLERS IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO- 99-085 WITH APPROVED 8110-3 DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: PIN — CORRODED (LT MLG)

DURING A MAINTENANCE VISIT FOUND CORROSION, LT MLG, RETRACT CYL A-PIN REPAIR PER CUSTOMER REQUEST IAW MA A13210-01:03 S/B 32-102 REF. AD 71-25-09. ACCOMPLISHED INSPECTION FOUND CORROSION IN PIN BOSS.. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REPAIRED IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO- 99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOAT BOX — CRACKED (LT WING)

DURING A MAINTENANCE VISIT FOUND A CRACK, LEFT WING, NR 1 ALT FLOAT BOX 2.5 CRACK IN WELD. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. REMOVED FLOAT BOX, WELDED CRACK SECTION IAW FAA APPROVED TENNESSEE TECH SERVICES DER ENGINEERING SKETCH NR EO-99-085 WITH APPROVED 8110-3, DATED MAY 21, 1999, INSTALLED FLOAT BOX IAW DC8 M/M 28-21-14.

Part: DOUBLER — CORRODED (BS 460 - 480)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FINGER DOUBLER, B-PIT, LEFT FWD BETWEEN STA 460 AND STA 480 AT LONGERON 31 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FINGER DOUBLER AND FILLER IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR EO 99-085. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CORRODED (BS 1700)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FLOOR TRACK NR 4 SUPPORT FITTING AT STA 1700, BL 35 LEFT, LONGERON 21 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FITTING IAW DAC DWG NR 2652479 AND DC8 SRM 51-1-2, 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FRAME — CORRODED (BS 640)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, MID AC COMPARTMENT ACCESS DOOR FRAME, FWD SIDE AROUND CAM LOCK HOLES, AT STA 640, BETWEEN BL 12 RIGHT AND BL 24 RIGHT, AT WL 45 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER AND FILLER IAW DC8 SRM 51-1-21 AND 51-1-0, 52-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 1746)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, SKIN FORWARD OF TAIL SKID AT STA 1746, LONGERON 36. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW DC8 SRM 51-1-21 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 540)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, SKIN EDGE AND SCREW HOLES AT WING O/B LEADING EDGE I/B SECTION OF STA XS 540 BETWEEN + 38 AND +45 FORWARD OF FRONT SPAR. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER IAW DC8 SRM 57-2-1 AND 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: WEB — CORRODED (WS 32)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT ELEVATOR INBOARD LIGHTNING HOLES AT STA XE 32.9. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW DC8 SRM 55-2-1. REPAIR INDEX 2E AND 51-2-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SHIM — CORRODED (BS 380)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, LT UPPER CUSP AT STA 380 FROM FRAME ATTACH ANGLE SHIM, LONGERON 21 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED SHIM IAW DC8 SRM 51-1-4 AND 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOORBEAM — CORRODED (BS 1746)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FLOOR SUPPORT UNDER CLIP NUTS, AT STA 1746, BETWEEN BL 1.5 LEFT AND BL 20.5 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FLOORBEAM SUPPORT IAW DC8 SRM 51-1-21 AND 51-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOORBEAM — CORRODED (BS 1746)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FLOOR SUPPORT UNDER CLIP NUTS AT STA 1746, BETWEEN BL 7-1/2 RIGHT AND BL 23 1/2 RIGHT AT LONGERON 21 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED SUPPORT IAW DC8 SRM 51-2-0, 53-4-1, AND 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 304 - 397)

DURING A MAINTENANCE VISIT FOUND CORROSION, LEFT WING, AROUND SCREW HOLES, L/E CENTER SECTION UPPER SURFACE BETWEEN STA XFS 304 AND STA XFS 397.750. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER AND FILLER IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR EO 99085. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 95 - 101.25)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, L/E TANK UPPER SURFACE AT SCREW HOLES BETWEEN STA XFS 95.000 AND STA XFS 101.250. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR EO 99-085. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CORRODED (BS 8)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, LONGERON 33 RIGHT END TIE FITTING AT STA 8.00. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FITTING IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR 99 085. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (BS 560)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, RT UPPER CUSP FRAME AT STA 560 ATTACH ANGLE, LONGERON 21 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED IAW DAC DWG 5753488 AND DC8 SRM 51-1-21 AND 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 286)

DURING A MAINTENANCE VISIT FOUND CORROSION, LEFT WING, IN SCREW HOLES, LEADING EDGE CENTER SECTION LOWER SURFACE, 46 FORWARD OF FRONT SPAR AT STA XFS 286.250. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER AND FILLER IAW DC8 SRM 57-2-1. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 660 - 702)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, BOTTOM OF FUSELAGE MARKER BEACON ANTENNA FROM BASE AROUND SKIN BETWEEN STA 680 AND STA 702 AT LONGERON 36. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FINGER DOUBLER IAW DC8 SRM 53-2-1. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SHIM — CORRODED (BS 400)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, LT UPPER CUSP AT STA 400 FRAME ATTACH ANGLE SHIM FROM UNDER SHIM MARKED 12 NR 83. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED SHIM IAW DC8 SRM 51-1-21 AND 51-1-4. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: LONGERON — CORRODED (BS 1726 - 1745)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, SPLICE, LONGERON 36, BETWEEN STA 1726 AND STA 1745. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR SPLICE AND LONGERON SECTION IAW DC8 SRM 53-2-9, 51-1-2 AND 51-1-22. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SHIM — CORRODED (BS 360)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, LT UPPER CUSP FRAME AT STA 360 FROM SHIM AT ATTACH ANGLE, LONGERON 21 LEFT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED SHIM AND FITTING IAW DC8 SRM 51-1-20D AND 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 878.75)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, O/B L/E O/B SEGMENT O/B END LWR SURFACE 22 FWD OF FRONT SPAR AT STA XFS 878.750. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER IAW DC8 SRM 51-1-21 AND 57-2-1. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (BS 1320)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, ATTACH ANGLE, LOWER AFT CARGO COMPARTMENT AT STA 1320, LONGERON 21 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER AND SUPPORT ANGLE IAW DC8 SRM 53-2-0 AND 51-1-20D. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 7.5 - 26.25)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, I/B L/E UPPER SURFACE AT SCREW HOLES BETWEEN STA XFS 7.50 AND XFS 26.25. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW DC8 SRM 52-2-1. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 710)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, IN SCREW HOLES O/B LEADING EDGE OUTBOARD SEGMENT INBOARD EDGE AT STA XFS 710. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER IAW DC8 SRM 57-2-1 AND 57-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 7.5 - 26.25)

DURING A MAINTENANCE VISIT FOUND CORROSION, LEFT WING, I/B L/E UPPER SURFACE AT SCREW HOLES BETWEEN STA XFS 7.50 AND STA XFS 26.250. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLERS AND FILLERS IAW FAA APROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR EO 99-085 AND DC8 SRM 57-2-1 FIG 37. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 566 & 603)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, IN SCREW HOLES O/B LEADING EDGE, I/B SEGMENT UPPER SURFACE AT FRONT SPAR BETWEEN STA XFS 566.250 AND STA XFS 603.750. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER AND FILLER IAW DC8 SRM 57-2-1, 51-1-21, AND 51-1-21A. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 151.25 - 157)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, I/B L/E TANK UPPER SURFACE AROUND SCREW HOLES BETWEEN STA XFS 151.250 AND XFS 157.500. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLER AND DOUBLER IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR EO 99-085 AND DC8 SRM 51-1-12. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WING)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, O/B SLOT UPPER I/B PANEL AT L/E, STA XFS.

Part: SKIN — CORRODED (WS 710)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, O/B LEADING EDGE I/B SEGMENT O/B EDGE AT STA XFS 710. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER IAW DC8 SRM 57-2-1 AND 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 259 - 269)

DURING A MAINTENANCE VISIT FOUND CORROSION, LT ELEVATOR, 3 SPOTS BETWEEN STA XE259 AND STA XE 269. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FINGER DOUBLERS TO TRAILING EDGE IAW DC8 SRM 51-1-1 TABLE B AND 51-1-2. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 32 - 50)

DURING A MAINTENANCE VISIT FOUND CORROSION, LT ELEVATOR, AREA UNDER PANEL 69 BETWEEN STA XE 32.937 AND STA XE 50.00. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR EO 99-085 AND DC8 SRM 55-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 191.625)

DURING A MAINTENANCE VISIT FOUND CORROSION, RIGHT WING, I/B L/E UPPER SURFACEO/B END AT STA XFS 191.625. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER IAW DC8 SRM 51-1-21 AND 51-1-20A. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: CHANNEL — CORRODED (BS 980 - 1140)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FLOOR ATTACH CHANNEL BETWEEN STA 980 AND STA 1140 AT LONGERON 33 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FLOOR CHANNEL IAW DC8 SRM 51-1-21 AND 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: CHANNEL — CORRODED (BS 980 - 1140)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FLOOR ATTACH CHANNEL BETWEEN STA 980 AND STA 1140 AT LONGERON 33 LEFT.. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FLOOR CHANNEL IAW DC8 SRM 51-1-4 AND 51-3-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 100 - 120)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, LAV SERVICE DOOR PANEL BETWEEN STA 100 AND STA 120 RIGHT AND BETWEEN LONGERONS 24 RIGHT AND LONGERON 28 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR EO 99-085/6256 AND 8110-3. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 717)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, BOTTOM SKIN AT STA 717 AND LONGERON 36. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLERS IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR EO 99-085. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FLOORBEAM — CORRODED (BS 1700)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, FLOORBEAM UNDER SEAT TRACK 3 ABOVE LONGERON 32 LEFT AT STA 1700. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR STRAP IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR EO 99-085. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (BS 360)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, ATTACH ANGLE, FRAME AT STA 360, AFT SIDE ABOVE BETWEEN LONGERONS 31 RIGHT AND LONGERON 29 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR ANGLE IAW FAA APPROVED TENNESSEE TECHNIDAL SERVICES DER ENGINEERING SKETCH NR 99-085. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (BS 702)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, BOTTOM SKIN AT STA 702 BETWEEN LONGERONS 34 LEFT AND LONGERON 34 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED DOUBLER IAW FAA APPROVED TENNESSEE TECHNICAL SERVICES DER ENGINEERING SKETCH NR II-085 AND DC8 SRM 53-2-0. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 878.75)

DURING A MAINTENANCE VISIT FOUND CORROSION, LEFT WING, O/B L/E O/B SEGMENT LWR SURFACE AT STA XFS 878.750. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER IAW DC8 SRM 57-2-1 AND 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: FITTING — CORRODED (BS 460)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, ATTACH FITTING AT STA 460, LONGERON 21 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED REPLACEMENT ATTACH FITTING IAW DC8 SRM 51-3-0 AND 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: ANGLE — CORRODED (BS 640)

DURING A MAINTENANCE VISIT FOUND CORROSION, FUSELAGE, ATTACH ANGLE AT NUT PLATES STA 640 BETWEEN LONGERONS 27 LEFT AND LONGERON 27 RIGHT. DAMAGE EXCEEDED LIMITS IAW DC-8 SRM. REMOVED DAMAGED, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED AND INSTALLED FILLER AND DOUBLER IAW DC8 SRM 53-2-0 AND 51-1-21. (CORROSION DAMAGE RECORDED IN EWA CORROSION PROGRAM).

Part: SKIN — CORRODED (WS 75)

DURING ACCEPTANCE INSPECTION, FOUND LT WING UPPER SKIN CORROSION TO BE .130 DEEP AT XRS=75 AND 18 INCHES OF REAR SPAR.