N822BX

Part: SKIN — CORRODED (BS 73 L31R) · airframe 95,218 hrs · 40,070 cycles

DURING ROUTINE B-CHECK, INSP FOUND CORROSION ON FUSELAGE SKIN AT STA 73 LONGERON 31 RT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORRODED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 53-2-1 FIG 7 SHEETS 15, SRM 53-2-2 FIG 4B.

Part: VALVE — LEAKING (ZONE 100) · airframe 94,483 hrs · 39,676 cycles

DURING CRUISE, THE RT HYD PRESSURE WAS AT ZERO AND THE LT HYD WAS FLUCTUATING. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX FOUND RESERVOIR DEPRESSURIZTION VALVE LEAKING. REPLACED RESERVOIR DEPRESSURIZATION VALVE. OPS CHECK GOOD IAW UAL MM29-13-35, UAL MM 29-13-43 PAGE 202 AND ERH 29.06.01-3 APPENDIX "A". ACFT WAS RETURNED TO SERVICE.

Part: PUMP — CRACKED (HYDRAULIC SYSTEM) · airframe 94,443 hrs · 39,654 cycles

DURING CRUISE, THE AILERON AND RUDDER REVERSION LIGHT CAME ON, THE CREW ALSO NOTICED LOSS OF HYD PRESSURE AND QUANTITY. CREW ACCOMPLISHED PROCEDURES IAW QRH NR 27. DECLARED EMERGENCY LANDING WITHOUT FURTHER INCIDENT. MX FOUND CABIN AIR CHECK VALVE CLOGGED AND RT ENGINE HYD PUMP LEAKING FROM CASE DRAIN. THEY REPLACED RT ENG HYD PUMP AND CLEANED CABIN AIR CHECK VALVE. OPS CHECK GOOD IAW UAL MM 29-13-35 AND 29-14-11. ACFT WAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (ZONE 600) · airframe 94,427 hrs · 39,645 cycles

RT WING LOWER SKIN CRACKED BETWEEN FWD AND AFT OF STRINGER 62. REPAIRED SKIN IAW SRM 57-2-1.

Part: SKIN — CRACKED (ZONE 500) · airframe 94,427 hrs · 39,645 cycles

LT WING LOWER SKIN CRACKED AT STATION 428.0. REPAIRED SKIN IAW CASTLE SKETCH 20100104028.

Part: STRINGER — CRACKED (ZONE 600) · airframe 94,427 hrs · 39,645 cycles

RT WING FOUND STRINGER 62 CRACKED. REPAIRED STRINGER 62 IAW SRM 57-2-2.

Part: STRINGER — CRACKED (ZONE 500) · airframe 94,427 hrs · 39,645 cycles

LT WING STRINGER 62 CRACKED. REPAIRED STRINGER IAW SRM 57-2-1 AND CASTLE SKETCH 20100104018.

Part: STRINGER — CRACKED (ZONE 500) · airframe 94,427 hrs · 39,645 cycles

LT WING STRINGER 63 CRACKED. REPAIRED STRINGER 63 IAW SRM 57-2-1 AND CASTLE SKETCH 20100104018.

Part: ADI — DEFECTIVE (COCKPIT) · airframe 94,426 hrs · 39,643 cycles

DURING CLIMB OUT, CAPTAIN’S FLIGHT DIRECTOR INDICATOR READ’S DIFFERENT FROM THE F/O FLIGHT DIRECTOR INDICATOR, ALSO READ’S DIFFERENT IN FLIGHT LEVEL AND DESCENT. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED CAPTAIN’S FLIGHT DIRECTOR INDICATOR. OPS CHECK GOOD IAW MM 34-20-0. ACFT WAS RETURNED TO SERVICE.

Part: RELIEF VALVE — DEFECTIVE (HYD SYSTEM) · airframe 94,415 hrs · 39,637 cycles

DURING CLIMB OUT, HYD PRESSURE DROPPED TO ZERO, AILERON AND MANUAL REVERSION LIGHTS ILLUMINATED. THE CREW ACCOMPLISHED ALL PROCEDURES IAW QRH, NO LOSS OF HYD QUANTITY. THE CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX INSPECTED AND REPLACED DUAL FILTERS AND RELIEF VALVE. OPS CHECK GOOD IAW WD 29-01-05, MM 29-10-5, 29-10-18 AND 29-10-16. ACFT WAS RETURNED TO SERVICE.

Part: RMI — DEFECTIVE (NR 2) · airframe 94,229 hrs · 39,503 cycles

DURING CRUISE, THE COMPASS CARD ON NR 2 RADIO MAGNETIC INDICATOR FROZE IN POSITION. AFTER SEVERAL MINUTES THE COMPASS CARD STARTED MOVING BUT IS 180 DEGREE OFF OF AIRCRAFT HEADING. THE CREW RETURNED TO KLRD WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED NR 2 RADIO MAGNETIC INDICATOR. OPERATIONAL CHECK GOOD IAW DC8 MAINTENANCE MANUAL 34-01. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FIRE LOOP — DEFECTIVE (NR 4 NACELLE) · airframe 94,160 hrs · 39,460 cycles

DURING CLIMB OUT, NR 4 FIRE WARNING HORN SOUNDED, THEN SILENCED AND SOUNDED AGAIN. THE CREW DISCHARGED BOTH BOTTLES AND SHUTDOWN NR 4 ENGINE. CREW RETURNED TO DEPARTURE WITHOUT FURTHER INCIDENT. MX REPLACED CORE FIRE LOOP, CORE LOOP CONNECTORS AND BOTH FIRE BOTTLES. OPS CHECK GOOD IAW MM 26-20-1, 26-10-1 AND ERH 70.01. ACFT WAS RETURNED TO SERVICE.

Part: RADIO — DEFECTIVE (VHF COMM) · airframe 94,160 hrs · 39,459 cycles

DURING CLIMB OUT, NR 2 VHF RADIO WILL NOT TRANSMIT FROM ANY POSITION. THE CREW RETURNED TO DEPARTURE AND LANDED WITHOUT INCIDENT. MX REPLACED FIRST OBSERVERS AUDIO SELECT PANEL AND VHF/FM COMM TRANSCEIVER. OPS CHECK GOOD IAW MM 23-20-1, AND 23-50-1. ACFT WAS RETURNED TO SERVICE.

Part: WIRE — DEFECTIVE (RUDDER) · airframe 93,828 hrs · 39,221 cycles

DURING CRUISE FROM KPHL, BOTH AILERON AND RUDDER MANUAL LIGHTS CAME ON, HYDRAULIC SYSTEM PRESSURE INDICATED ZERO, HYDRAULIC QUANTITY SHOWS FULL. THE CREW ACCOMPLISHED LOSS OF HYDRAULICS CHECKLIST IN DC-8 QRH. THE CREW LANDED IN KTOL WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED JUMPER WIRE M107C22. OPERATIONAL CHECK GOOD IAW ATI WD MAINTENANCE MANUAL 29-10-05. AIRCRAFT WAS RETURNED TO SERVICE.

Part: FIRE LOOP — FALSE ACTIVATION (ZONE 400) · airframe 93,772 hrs · 39,196 cycles

DURING CLIMB FROM MGUM NR 4 ENGINE SHORT CIRCUIT LIGHT ILLUMINATED, FIRE WARNING WOULD NOT TEST. THE CREW SHUTDOWN NUMBER FOUR ENGINE PER COM PROCEDURES. WIND MILLING OIL PRESSURE WAS 3PSI. THE CREW LANDED IN KNGU WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED FORWARD OUTBOARD FIRE LOOP. OPERATIONAL CHECK GOOD IAW DC8 MAINTENANCE MANUAL 26-10-1. AIRCRAFT WAS RETURNED TO SERVICE.

Part: GROUND WIRE — BROKEN (NR 1 NACELLE)

AFTER TAKEOFF FROM KIAH, NR 1 ENGINE FIRE WARNING SOUNDED, FIRE HANDLE LIGHT, AND MASTER FIRE WARNING LIGHT ILLUMINATED. WARNING HORN COULD BE SILENCED BUT CAME BACK ON THREE TIMES. ENGINE FIRE HANDLE SUBSEQUENTLY PLACED IN SELECT AGENT POSITION; LIGHT AND HORN SILENCED. ACFT RETURNED TO KIAH WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND AND REPAIRED A BROKEN GROUND WIRE ON RT SIDE UPPER HOT SECTION FIRE LOOP IAW MM 20-50-1. ADDITIONALLY, NR 1 ENGINE FIRE DETECTOR SYSTEM OPERATIONAL CHECK GOOD IAW MM 26-11-16. (A)

Part: FITTING — CRACKED (BS 70) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT NUMBER 5 TRACK NUT BARRIER FITTING CRACKED AT STATION 70.000. REMOVED CRACKED FITTING. FABRICATED NEW FITTING. PERFORMED MAGNETIC PARTICLE INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 51-3-0, DC8 SRM 51-3-1, DC8 SRM 51-3-0, ATI REPAIR SPECIFICATION 2003-05, DRAWING DOUGLAS 3774645, NDT SPM PARA 07-00-02/07, AND DC8 SRM 51-1-8B.

Part: SKIN — CRACKED (ZONE 600) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING CENTER LEADING EDGE LOWER INNER SKIN INBOARD SPLICE CRACKED AT STATION XFS 341.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED NEW SKIN, INTERNAL, AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XFS 297.500 TO STATION XFS 341.500 IAW DC8 SRM 51-1-11, DC8 SRM 51-3-1, FAA FORM 8110-3 NUMBER 08086 DATED 02-27-08, SEMAN DRAWING NUMBER ED-4706 DATED 02-09-08, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (LT ELEVATOR) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR LOWER SKIN DENTED AT STATION XE 246.875. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE SKIN. FABRICATED NEW SKIN, FINGER DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. BALANCED, AND FOUND TO BE WITHIN LIMITS MOMENT OF 1473.4 INCH-POUND. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION XE 246.000 TO XH 285.000 IAW DC8 SRM 51-1-11, DC8 SRM 55-4-1 FIGURE 1 SHEETS 1, 2 ITEMS "E" AND "F", DC8 SRM 55-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-4-4 PAGE 1-3, DC8 SRM 51-1-9 T/R 51-142, DC8 SRM 51-1-9A T/R 51-141, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (BS 1690-1890) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK, FOUND AT EXTERNAL DOUBLER AFT LOWER FUSELAGE BELLY TAIL SKID FAIRING HAS IMPROPER REPAIR AT STATION FS 1745 LONGERON 35.5 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT STATION FS 1690.000 TO STATION FS 1890.000 IAW DC8 SRM 53-5-1 FIGURE 1 ITEM "E", BOEING MESSAGE 1-756217773-2 DATED 01/22/08, DC8 SRM 53-1-0 PAGE 1, DC8 SRM 51-1-21, AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (RT AILERON) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT INBOARD AILERON UPPER SKIN HAS DENT AND NO STANDARD REPAIR AT STATION XA 580.000 TO XA 610.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE SKIN. FABRICATED NEW SKIN, AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIRED PARTS. BALANCED AND FOUND MOMENT WITHIN LIMITS MOMENT: 3331.3 INCH POUND. INSTALLED NEW FASTENERS AND REPAIRED PARTS IAW DC8 SRM 51-1-11, DC8 SRM 57-8-1 FIGURE 1, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-8-1 FIGURE 4 ITEM "B" AND "K", DC8 SRM 51-1-9 T/R 51-142, DC8 SRM 51-1-9A T/R 51-141, DC8 SRM 51-1-8B, AND DC8 SRM 51-4-1 PAGE 1 AND 2,

Part: FITTING — CRACKED (BS 857 L1) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 857.000 LONGERON 1. REMOVED CRACKED FITTING. FABRICATED FITTING PERFORMED LIQUID PENETRANT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING DC8 SRM 51-3-1, DC8 SRM 51-1-20D, DC8 SRM 51-1-8B, ATI REPAIR SPECIFICATION NUMBER 2003-05, DRAWING DOUGLAS 3779900, AND SPM PART 08-00-02 TO 07.

Part: SKIN — CRACKED (ZONE 200) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT FUSELAGE TAIL SECTION PLATING CRACKED AT STATION FS 1766.000 TO STATION 1781.000 LONGERON10 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, AND INTERNAL FINGER DOUBLER, AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-11, SRM 51-1-20D, SRM 51-3-1, SRM 53-2-1 FIGURE 7 SHEETS 1, 4, 5, SRM 51-1-21, SRM 53-2-1 FIGURE 7 SHEETS 1, 4, 5, 53-5-1 FIGURE 1 ITEM "A", AND SRM 51-1-8B.

Part: SKIN — DENTED (ZONE 500) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT WING INBOARD AFT LOWER FLAP SKIN SHOWS DENTS AT STATION XE 2.000 TO STA XE 91.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE SKIN. FABRICATED NEW SKIN, AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIRED PARTS. INSTALLED NEW FASTENERS AND REPAIRED PARTS IAW SRM 51-1-11, SRM 57-1-0 PAGE 1, SRM 51-1-21, SRM 57-7-1 FIG 1 ITEMS "B" AND "L", SRM 51-1-9 T/R 51-142, SRM 51-1-9A T/R 51-141, AND SRM 51-1 8B.

Part: SKIN — DENTED (ZONE 500) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT INBOARD FLAP LOWER FORWARD PANEL PLATING DENTED AT STATION XW 2.000 - STA XW 91.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE SKIN. FABRICATED NEW SKIN, AND BONDED DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 1 ITEM "B" AND "L", DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-9 T/R 51-142, 51-1-9A T/R 51-141, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING LEADING CENTER LEADING EDGE OUTER SKIN LOWER SHOWS IMPROPER REPAIR AT STATION XFS 385.200. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, FILLERS, INTERNAL SPLICE DOUBLER SEGMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 51-3-0, DC8 SRM 51-3-1, FAA FORM 8110-3 NUMBER 08086 DATED 02-27-08, SEMAN DRAWING NUMBER ED-4706 DATED 02-09-08, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (BS 879 L18R) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO FRAME FITTING CRACKED AT STATION 879.000 LONGERON 18 RIGHT TO LONGERON-19 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED FITTING. PERFORMED NDT INSPECTION. NO CRACK NO CORROSION FOUND. PERFORMED STOP HOLE ON CRACK END. FABRICATED SPLICE ANGLE, FILLERS. PERFORMED HEAT TREATMENT TO REPAIR PARTS AS NEEDED. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08086 DATED 02/27/08, DRAWING ED 4702 DATED 02/09/08, DC8 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-1 PAGES 1, 13, 17, ATI REPAIR SPECIFICATION 2003-05, DRAWING DOUGLAS NUMBER 3779874 AND 3779978, DRAWING ED 4702, AND NDT SPM PART 08-00-02 TO 07.

Part: SUPPORT FITTING — CRACKED (ZONE 100) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FUSELAGE TAIL SKID SUPPORT FITTING CRACKED AT STATION 1734.000 LONGERON36. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-3-1, DC8 SRM 51-1-20D, DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (FUSELAGE) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO INTERCOSTAL END CLIP CRACKED AT STATION 857.000 LONGERON 18 RIGHT. REMOVED CRACKED INTERCOSTAL END CLIP. FABRICATED INTERCOSTAL END CLIP. PERFORMED HEAT TREATMENT. CLEANED, TREATED AND PRIMED AREA AND INTERCOSTAL END CLIP. INSTALLED NEW INTERCOSTAL END CLIP IAW DC8 SRM 51-1-21, ATI REPAIR SPECIFICATION NUMBER 2003-05, DC8 SRM 51-1-1 PAGES 1, 13 AND 17, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (RT WING) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING CENTER LEADING EDGE LOWER OUTER SKIN SHOWS IMPROPER REPAIR AT STATION XFS 304.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSP. NO CRACK, NO CORROSION FOUND. FABRICATED NEW SKIN, INTERNAL, AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS AT XFS 297.500 - STA XFS 341.500 IAW DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 51-3-1, FAA FORM 8110-3 NUMBER 08086 DATED 02-27-08, SEMAN DRAWING NUMBER ED-4706 DATED 02-09-08, DC8 SRM 51-1-21, DC8 SRM 51-3-0, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (BS 1690 L28R) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT ACCESSORY COMPARTMENT FITTING CRACKED AT STATION 1690.000 LONGERON 28 RIGHT. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW SRM 51-1-21, SRM 51-3-1, SRM 51-1-20D, AND SRM 51-1 8B.

Part: FRAME — CRACKED (FUSELAGE) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND FORWARD CARGO COMPARTMENT FRAME LOWER FLANGE CRACKED AT STATION 480.000 LONGERON 34 RIGHT. REMOVED DAMAGED AREA. FABRICATED NEW FRAME SEGMENT, SPLICES, ANGLES. HEAT TREATED EXTRUSION FRAME SEGMENT. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED REPAIR PARTS IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, DC8 SRM 53-2-0 FIGURE 2 SHEET 1, 2, 6, DC8 SRM 53-4-1 FIGURE 40 SHEET 14-15, DC8 SRM 51-2-0 FIGURE 50 SHEET 49A, DC8 SRM 53-2-0 FIGURE 2 SHEET 7-8, T/R NR 53-110 DATED 11-10-00, DC8 SRM 51-1-1 PAGE 1, 13, 17, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (RT WING) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING CENTER LEADING EDGE LOWER OUTER SKIN SHOWS IMPROPER REPAIR AT STATION XOLDI 6.2246. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED NEW SKIN, INTERNAL, AND EXTERNAL DOUBLERS. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 DATED 02-27-08 NUMBER 08086, SEMAN DRAWING NUMBER ED-4707 DATED 02-08-08, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-3-0, AND DC8 SRM 51-3-1.

Part: FLAP — DENTED (T/E FLAP) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBD FLAP UPPER PART SHOWS DENTS AT STATION XF 375.000 TO STA XF 404.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN, DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 57-7-1 FIGURE 4 T/R 57 - 94 ITEM "U" AND "Q".DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-9 T/R 51, 142, DC8 SRM 51-1-9A T/R 51, 141, AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (LT ELEVATOR) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND ELEVATOR LEFT UPPER SKIN SHOWS DENTS AND CORROSION AT DIFFERENT POINTS AT STATION XE 146.000 AND XE 270.000. REMOVED CORROSION. FOUND TO BE OUT OF LIMITS. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN, AND FINGER DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. BALANCED AND FOUND TO BE WITHIN LIMITS MOMENT: 1473.4 INCH-POUND. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 51-1-8 PAGES 17 AND 18, DC8 SRM 55-2-0 PAGE 12, DC8 SRM 55-1-0 PAGE 1, SRM 51-1-21, DC8 SRM 55-4-1 FIGURE 1 SHEETS 1 AND 2 ITEMS "E" AND "F", DC8 SRM 51-1-9 T/R 51-142, DC8 SRM 51-1-9A T/R 51-141, DC8 SRM 51-1-8B, AND DC8 SRM 51-4-4 PAGE 1-3.

Part: SKIN — DENTED (TE FLAP) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT OUTBOARD FLAP LOWER AFT SKIN HAS DENTS AT STATION XF 434.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 T/R 57 - 94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 T/R 57 - 94 ITEM "U" AND "Q", DC8 SRM 51-1-9 T/R 51 - 142 AND 51-1-9A T/R 51, 141, AND DC8 SRM 51-1-8B.

Part: SKIN — SCRATCHED (LT ELEVATOR) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT ELEVATOR UPPER SKIN SHOWS SCRATCHES AT STATION XE 273.000 TO STATION XE 283.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED AREA. FABRICATED NEW SKIN, FINGER DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. BALANCED AND FOUND TO BE WITHIN LIMITS, MOMENT: 1473.4 INCH-POUND. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 55-4-1 FIGURE 1 SHEET 1 AND 2 ITEM "E" AND "F", DC8 SRM 55-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-9 T/R 51-142, DC8 SRM 51-1-9A T/R 51-141, DC8 SRM 51-1-8B, AND DC8 SRM 51-4-4 PAGE 1-3.

Part: SKIN — DENTED (T/E FLAP) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD FLAP LOWER SKIN FORWARD SHOWS DENTS BETWEEN STATION XF 160.000 - XF 213.000. PERFORMED DETAILED VISUAL INSPECTION. NO CRACK NO CORROSION FOUND. PERFORMED MEASUREMENT DIA 2.00 BY 0.008" DEPTH WITHIN PERMISSIBLE LIMITS. APPLIED PRO-SEAL. CLEANED, TREATED, PRIMED AND PAINTED AREA IAW DC8 SRM 51-1-8B, DC8 57-1-0 PAGE 1, DC8 SRM 51-1-9 FIGURE 13B,

Part: FITTING — CRACKED (CARGO BAY) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 847.000 LONGERON1. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-1-8-B, DC8 SRM 51-1-20D, AND DC8 SRM 51-3-1.

Part: FITTING — CRACKED (CARGO BAY) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 690.000 LONGERON 1. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (BS 680 L11L) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO FITTING CRACKED AT STATION 680.000 LONGERON 11 RIGHT. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-0, DC8 SRM 51-1-21, AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (T/E FLAP) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD FLAP LOWER SKIN SHOWS DENTS AT STATION XF 434.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE SKIN. FABRICATED NEW SKIN, AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 57-7-1 FIGURE 4 T/R 57 - 94 ITEM "U" AND "Q", DC8 SRM 57-1-0 PAGE 1, 51-1-21, DC8 SRM 51-1-9 T/R 51-142 DATED 04-05-06, DC8 SRM 51-1-9A T/R 51-141 DATED 04-03-06, AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (ZONE 500) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD FLAP LOWER SKIN DENTS AT STATION XF 169.000 - XF 213.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 T/R 57-94 DATED 10-01-02, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 4 T/R 57 - 94 ITEM "P" AND "Q", DC8 SRM 51-1-9 T/R 51-142, DC8 SRM 51-1-9A T/R 51 141, AND DC8 SRM 51-1-8B.

Part: FITTING — CORRODED (BS 960-980) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CORRODED AT STATION 960.000 TO STATION 980.000 LEFT BUTTOCKS LINE 45. REMOVED CORRODED FITING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, AND DC8 SRM 51-1-8B.

Part: LONGERON — CRACKED (BS 1766 L17R) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EMPENNAGE LONGERON 17 RIGHT CRACKED AT STATION 1766.00. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CRACKED LONGERON SEGMENT. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FASTENERS AND LONGERON SEGMENT IAW DC8 SRM 53-5-1 FIGURE 7 SHEET 37 PAG 22, DC8 SRM 51-2-0 FIGURE 50 SHEET 37, 51-3-0, 51-3-1, DC8 SRM 53-5-1 FIGURE 7 SHEET 1 PAG 22, DC8 SRM 51-1-21, 51-1-20D, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (FUSELAGE) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FORWARD FITTING CRACKED AT STATION 759.000 LONGERON 11 RIGHT. REMOVED (CRACKED) FITTING. CLEANED, TREATED AND PRIMED AREA INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (CARGO BAY) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO COMPARTMENT FITTING CRACKED AT STATION 680.000 LONGERON 1. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (ZONE 300) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT HORIZONTAL STABILIZER FITTING INTERCOSTAL SIDE CRACKED AT STATION XFS 60.000. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, 51-1-21, DC8 SRM 51-1-8B, AND 51-3-1.

Part: SKIN — SCRATCHED (AILERON) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LEFT OUTBOARD AILERON LOWER SKIN SCRATCHED BETWEEN STATION XA 737.000 AND XA 763.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE SKIN. FABRICATED NEW SKIN AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. PERFORMED BALANCE FOUND AT MOMENT WITHIN TOLERANCE MOMENT 3324.57 INCH POUND. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 51-4-3 PAGES 1 AND 3, DC8 SRM 57-8-1 FIGURE 4 ITEM "E" AND "L", DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-9 T/R 51-142, AND DC8 SRM 51-1-9A T/R 51-141, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (ZONE 300) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT HORIZONTAL STABILIZER FITTING INTERCOSTAL SIDE CRACKED XFS 60.000. REMOVED CRACKED FITTING. PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-1-20D, 51-1-21, DC8 SRM 51-1-8B, DC8 SRM 51-1-14, AND 51-3-1.

Part: SKIN — MISREPAIRED (RT ELEVATOR) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT ELEVATOR UPPER SKIN SHOWS IMPROPER REPAIR AT STATION XE 50.000 TO XE 132.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. FABRICATED NEW SKIN AND FINGER DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. BALANCED RIGHT ELEVATOR. FOUND MOMENT WITHIN TOLERANCE 1449.3 INCH POUND. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 51-1-21, DC8 SRM 55-4-1 FIGURE 1 SHEET 1 AND 2 ITEMS "E" AND "F", DC8 SRM 55-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 51-1-9 T/R 51-142, DC8 SRM 51-1-9A T/R 51-141, DC8 SRM 51-1-8B, DC8 SRM 51-4-4 PAGE 2 AND 3, AND T/R 51-116 DATED 11/03/00.

Part: FITTING — CRACKED (BS 680 L20L) · airframe 92,877 hrs · 38,753 cycles

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

Part: SUPPORT ANGLE — CRACKED (ZONE 200) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO FORMER CRACKED AT STATION 1766.000 LONGERON1. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. PERFORMED STOP HOLE ON END CRACK. FABRICATED ANGLE DOUBLER. PERFORMED HEAT TREATMENT CLEANED, TREATED AND PRIMED AREA AND ANGLE DOUBLER. INSTALLED NEW FASTENERS AND ANGLE DOUBLER IAW SRM 51-1-20D, 51-3-1, SRM 53-2-0 PAGE 2P, SRM 51-1-1 PAGES 1 13 AND 17, AND SRM 51-1-8B.

Part: FITTING — CRACKED (CARGO BAY) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND MAIN CARGO FITTING CRACKED AT STATION 960.000 LONGERON19 LEFT. REMOVED CRACKED FITTING. FABRICATED FITTING. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA AND FITTING. INSTALLED FITTING IAW DC8 SRM 51-1-20D, 51-3-1, DC8 SRM 51-1-20D, ATI REPAIR SPECIFICATION NUMBER 2003-05, DRAWING DOUGLAS 3779874, NDT SPM PART 08-00-02 TO 07, AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (RUDDER) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RUDDER RIGHT SKIN SIDE DENTED AT STATION ZR 276.531 TO ZR 267.218. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE PANEL PLATING. FABRICATED NEW SKIN AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. BALANCED RUDDER MOMENT WITHIN TOLERANCE. MOMENT: 2503.25 INCH POUND. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-11, SRM 55-1-0 PAGE 1, SRM 51-1-21, SRM 55-6-1 FIGURE 1 ITEM "A", SRM 51-1-9 T/R 51-142, SRM 51-1-9A T/R 51-141, SRM 51-1-8B, AND SRM 51-4-6 PAGES 1 AND 2.

Part: FITTING — CRACKED (CARGO BAY) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK, FOUND MAIN CARGO COMPARTMENT AFT FITTING CRACKED AT STATION 759 LONGERON 11 RIGHT. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALL NEW FITTING IAW DC8 SRM 51-1-20D, DC8 SRM 51-3-1, AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (TE FLAP) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LT WING FLAP INBOARD UPPER SKIN SHOWS DENTS BETWEEN STATION XW 3.000 - XW 91.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGED SKIN. FABRICATED NEW SKIN, DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-11, DC8 SRM 51-1-21, SRM 57-7-1 FIGURE 1 ITEM "A" AND "L", 57-1-0 PAGE 1, SRM 51-1-21, AND SRM 51-1-8B.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AFT LOWER FUSELAGE BELLY AFT OF OUTFLOW VALVE "SUGAR SCOOP" AT STATION FS 1682 LONGERON 35.6 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND CORROSION FOUND. FABRICATED REPAIR DOUBLER, REPAIR TRIPLER, SKIN FILLER, AND INTERNAL DOUBLER FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-21, 51-1-20D, 51-3-1, FAA FORM 8110-3 NUMBER 08110 DATED 03-13-08, SEMAN DRAWING ED-4699 DATED 02-13-08, 51-3-0, DC8 NDT SPM PART 06-10-01-001, AND DC8 SRM 51-1-8B.

Part: FITTING — CRACKED (ZONE 100) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND AFT ACCESSORY COMPARTMENT FITTING CRACKED AT STATION 1690.000 LONGERON 28 LEFT. REMOVED CRACKED FITTING. CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW FITTING IAW DC8 SRM 51-3-1 PAGE 2A, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (ZONE 600) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING INBOARD FLAP LOWER SKIN HAS DENTS AT STATION XW 3.000 - 91.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE PANEL PLATING. FABRICATED NEW SKIN AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIRED PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 57-7-1 FIGURE 1, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, DC8 SRM 57-7-1 FIGURE 1 ITEM "B" AND "L", DC8 SRM 51-1-9 T/R 51-142, DC8 SRM 51-1-9A T/R 51-141, AND DC8 SRM 51-1-8B.

Part: SKIN — DENTED (ZONE 600) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND RIGHT WING RIGHT INBOARD FLAP UPPER SKIN HAS DENTS BETWEEN STATION XW 3.000 AND XW 91.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED DAMAGE PANEL PLATING. FABRICATED NEW SKIN, AND DOUBLER. BONDED PARTS AS NEEDED WITH HYSOL. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, DC8 SRM 57-7-1 FIGURE 1, DC8 SRM 57-1-0 PAGE 1, DC8 SRM 51-1-21, SRM 57-7-1 FIGURE 1 ITEM "A" AND "L", DC8 SRM 51-1-9 T/R 51-142, DC8 SRM 51-1-9A T/R 51-141, DC8 SRM 51-1-8B,

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXTERNAL DOUBLER LOWER FUSELAGE BELLY AFT EDGE OF A-PIT BASKET DOOR HAS IMPROPER REPAIR AT STATION FS 330 LONGERON 34 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK OR CORROSION FOUND. FABRICATED REPAIR DOUBLER, TRIPLER, FILLER SKIN. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08110 DATED 03-13-08, SEMAN DRAWING ED-4700 DATED 02-12-08, DC8 SRM 51-1-21, 51-3-0, 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, AND 51-3-1.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR SIDE SKIN LAP JOINT FORWARD OF AFT PRESSURE BULKHEAD AT LONGERON 28. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER, FINGER DOUBLERS, FILLER. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8100-9 DATED 02-14-08, AD 2007-02-02, S/B DC8-53A080 DATED 06-22-04, DRAWING DOUGLAS SR08530032 AND BOEING SKETCH 200802070028-0001, DC8 SRM 51-1-21, 51-3-0, 51-1-20D, AND DC8 NDT SPM PART 06-10-01-.001.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXTERNAL DOUBLER RIGHT FORWARD FUSELAGE FORWARD OF B-PIT DOOR HAS IMPROPER REPAIR AT STATION FS 466, LONGERON 25.5 RIGHT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND AFTER INSPECTION. FABRICATED REPAIR DOUBLER, TRIPLER, FILLER SKIN, INTERNAL FINGER DOUBLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PART. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8110-3 NUMBER 08086 DATED 02-27-08, SEMAN DRAWING ED-4701 DATED 02-05-08, DC8 SRM 51-1-21, DC8 SRM 51-1-20D, DC8 NDT SPM PART 06-10-01-001, DC8 SRM 51-1-8B, DC8 SRM 51-1-11, AND 51-3-1.

Part: SKIN — MISREPAIRED (BS 1733 S26L) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND EXTERNAL DOUBLER AFT LOWER FUSELAGE AFT OF L-2 DOOR WITH IMPROPER REPAIR AT STATION FS 1733 LONGERON 26 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK AND CORROSION FOUND. FABRICATED REPAIR DOUBLER, FINGER DOUBLERS, FILLER. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW 51-3-1, DC8 SRM 51-1-21, 51-3-0, 51-1-20D, DC8 NDT SPM PART 06-10-01.001, DOUGLAS DRAWING SR08530032, SKETCH 200802070028-0001, AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT EXTERNAL DOUBLER LEFT AFT FUSELAGE SIDE FORWARD OF AFT PRESSURE BULKHEAD AT STATION FS 1742, LONGERON 16.5 LEFT. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGE AREA. FABRICATE REPAIR DOUBLER, INTERNAL FINGER DOUBLER, FILLER CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 51-1-11, SRM 51-3-1, DC8 SRM 53-2-1 FIGURE 7 SHEETS 1, 3, 5, DC8 SRM 53-5-1 FIGURE 1 ITEM "E", DC8 SRM 51-1-21, DC8 SRM 51-1-20D, AND DC8 SRM 51-1-8B.

Part: LONGERON — MISREPAIRED (BS 1742 L16L) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT EXTERNAL DOUBLER LEFT AFT FUSELAGE SIDE FORWARD OF AFT PRESSURE BULKHEAD AT STATION FS 1742, LONGERON 16.5 LEFT. REMOVED FASTENER AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. FABRICATED REPAIR DOUBLER, FILLER, INTERNAL FINGER DOUBLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, SRM 51-3-1, DC8 SRM 53-2-1 FIGURE 7 SHEETS 1, 3, AND 5, DC8 SRM 51-1-21, 51-1-20D, DC8 SRM 53-5-1 FIGURE 1 ITEM D, DC8 SRM 51-1-8B,

Part: SKIN — DENTED (LT ELEVATOR) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND LT ELEVATOR UPPER SKIN SHOWS DENTS AND CORROSION AT SEVERAL POINTS BETWEEN STATION XE 50.000 AND STA XE 132.000. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED CORROSION. FOUND OUT OF LIMITS. REMOVED DAMAGED SKIN. FABRICATED SKIN, FINGER DOUBLER. BONDED PARTS AS NEEDED. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS. BALANCED AND FOUND TO BE WITHIN LIMITS WITH A MOMENT OF 1473.4 INCH-POUND. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW SRM 51-1-11, SRM 55-4-1 FIGURE 1 SHEET 1-2 ITEM "E" AND "F", SRM 51-1-8 PAGE 17-18, DC8 SRM 55-2-0 PAGE 12, SRM 55-1-0 PAGE 1, SRM 51-1-21, SRM 51-1-9, T/R NUMBER 51-142, SRM 51-1-9A, T/R 51-141, SRM 51-1-8B, AND SRM 51-4-4 PAGE 1-3.

Part: LONGERON — MISREPAIRED (BS 1747 L16R) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT EXTERNAL DOUBLER RIGHT AFT LOWER FUSELAGE FORWARD OF AFT PRESSURE BULKHEAD AT STATION FS 1747, LONGERON 16-5 RIGHT. REMOVED FASTENERS AS A NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGE AREA. FABRICATED REPAIR DOUBLER, INTERNAL FINGER DOUBLER, AND FILLER. CLEANED, TREATED, PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW DC8 SRM 51-1-11, SRM 51-3-1, DC8 SRM 53-2-1 FIGURE 7 SHEETS 1, 3, AND 5, DC8 SRM 51-1-21, SRM 51-1-20D, DC8 SRM 53-5-1 FIGURE 1 ITEM "D", AND DC8 SRM 51-1-8B.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 92,877 hrs · 38,753 cycles

DURING ROUTINE C CHECK INSPECTION, FOUND IMPROPER REPAIR AT FUSELAGE SKIN FORWARD OF FLAT AFT PRESSURE BULKHEAD AT LONGERON 28. REMOVED FASTENERS AS NEEDED TO PERFORM REPAIR. REMOVED EXISTING REPAIR DOUBLER. REMOVED DAMAGED AREA. PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED NEW SKIN, INTERNAL, EXTERNAL DOUBLERS. CLEANED, TREATED, AND PRIMED AREA AND REPAIR PARTS. INSTALLED NEW FASTENERS AND REPAIR PARTS IAW FAA FORM 8100-9 DATED 02-14-08, AD 2007-02-02, S/B DC8-53A080 DATED 06-22-04, DRAWING DOUGLAS SR08530032 AND BOEING SKETCH 200802070028-0001, DC8 SRM 51-1-21, 51-3-0, 51-1-20D, AND DC8 NDT SPM PART 06-10-01-.001.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 92,358 hrs · 38,502 cycles

LOWER D PIT DOOR HAS NON-STANDARD REPAIR PER AD2005-18-07 AND SB DC8-53-078. REMOVED EXISTING SKIN PANEL. LOCATED, DRILLED, TRIMMED, TREATED AND PRIMED NEW SKIN PANEL, APPLIED SEALANT TO FAYING SURFACES. INSTALLED NEW SKIN PANEL AT LOWER D PIT DOOR FROM STATION 1350 TO STATION 1490 AND FROM LONGERON 31 LEFT TO LONGERON 31 RIGHT IAW DACO DC8 SRM 51-1-20, 51-1-21, 51-1-5, 51-1-8, 51-1-11, 51-1-14, 51-1-15, 53-1-0 AND 53-4-0, OPS CHECK WITH PRESSURIZATION IAW DACO DC8 MM 21-22-0. NO LEAKS NOTED.

Part: BOLT — OUT OF ADJUST (MLG) · airframe 90,078 hrs · 37,559 cycles

DURING TAKEOFF FROM KTOL, GEAR UPLATCH CHECK UNSATISFACTORY DOORS LIGHT AND LANDING GEAR UNSAFE LIGHT CAME ON IN UPLATCH POSITION. CYCLED GEAR DOWN AND UP, SAME RESULTS CREW RETURNED AIRCRAFT TO KTOL AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND STRUT TO UNIVERSAL BOLT SAFETY BOLT CONTACTING SIDE BRACE LINK, REPOSITIONED BOLT, NO DEFECTS NOTED. FOUND BOTH ACTUATING CYLINDERS NOT BOTTOMED OUT IN CYLINDER, ADJUSTED. PERFORMED EXTENSION RETRACTION SYSTEM AND A SYSTEMS CHECK WAS GOOD PER ALL APPLICABLE MANUALS AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: LANDING GEAR — FAILED (NOSE) · airframe 90,880 hrs · 37,532 cycles

WHEN LANDING GEAR LEVER IS SELECTED TO UPLATCH CHECK POSITIONS, DOOR LIGHTS AND LANDING GEAR UNSAFE LIGHTS ILLUMINATE. SAME RESULTS AFTER GEAR RECYCLE. THE NOSE GEAR DOOR STAYED CLOSED WHEN GEAR LEVER IS RETURNED TO UP POSITION BOTH LIGHTS GO OUT. ALSO THE LANDING GEAR LEVER IS VERY HARD TO MOVE. MAINTENANCE DEFFERED THIS TO DMI 32746 AND 32747. THE AIRCRAFT WAS RETURNED TO SERVICE. AS MORE INFORMATION BECOMES AVAILABLE IT WILL BE PROVIDED.

Part: SKIN — CORRODED (XS250.089) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING IB L/E UPPER PART EXTERNAL SKIN CORRODED XS 250.089. PERFORMED MAJOR REPAIR IAW SRM, TR NR 57-85, EO SEMAN NR 2005984 DATE 06-18-05. REMOVED FASTENERS IAW SRM 51-1-21 PAGE 1, SRM. REMOVED CORROSION IAW SRM. FOUND OUT OF LIMITS IAW SRM. REMOVED CORRODED AREA IAW SRM 57-2-1 FIG. 38. PERFORMED VISUAL INSPECTION NO CRACK, CORROSION FOUND. FABRICATED DOUBLER (ALCLAD 7075 T6 0.071) + FILLER (ALCLAD 7075 T6 0.063) IAW SRM 57-2-1 FIG. 38, SRM 57-3-1 FIG. 3. CLEANED, TREATED AND PRIMED AREA + REPAIR PART INTERNAL PART IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS WITH NEW FASTENERS IAW SRM, TORQUED IAW SRM 51-3-1.

Part: VANE — IMPROPER (XOLDO 67.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING. OB VANE SLOT HAS INTERIM REPAIR XOLDO 67.000. PERFORMED MAJOR REPAIR, REMOVED EXISTING REPAIR DOUBLER IAW SRM 51-1-21 PAGE 1. REMOVED THE DAMAGED AREA IAW DWG NR ED 4022, PERFORMED NDT INSPECTION. IAW NDT SPM PART 06-10-01-001. NO CRACK, NO CORROSION FOUND. FABRICATED EXTERNAL REPAIR DOUBLER (ALCLAD 7075 T6 0.071) + FILLER (ALCLAD 7075 T6 0.063) + INTERNAL DOUBLER (ALCLAD 7075 T6 0.063) IAW SEMAN DWG ED 4022, SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS INTERNAL PART IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW DWG ED 4022, SRM. TORQUED IAW SRM 51-3-1.

Part: FRAME — CRACKED (STA 55.00 L-24R) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C-CHECK INSPECTION, FWD ACCES COMPT. FRAME CRACKED 2” STA 55.000 L-24R. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-0 FIG. 2 SHEET 5, TR 53-125 DATE 08-31-01, DC-8 SRM 53-2-0 FIG. 2 (SHEET 6) EO SEMAN NR 20051015 DATE 06-29-05. REPAIRED PER SRM.

Part: SKIN — CORRODED (STA665.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, MID ACCESSORY COMPARTMENT L-31R CORRODED, STA 665.000. PERFORMED MAJOR REPAIR IAW SRM 53-2-2 FIG. 11, EO SEMAN NR 20051003 DATE 06-27-05. REMOVED FASTENERS IAW SRM 51-1-20D PAGE 21. REMOVED CORROSION IAW SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SRM 53-2-0 PAGE 2P. FABRICATED REPAIR ANGLE DOUBLER (EXTRUSION 7075 T6 511 0.130”) IAW SRM 53-2-2 FIG. 11. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW SRM 53-2-2- FIG. 11 SHEET 3,4,5,6, SRM 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: SKIN — CRACKED (XS250.000-240.00) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING. STUB WING UPPER SURFACE STA XS 250.000 XS 240.000 HAS TWO CRACKS OF .5 INCH. PERFORMED MAJOR REPAIR IAW SRM 57-2-1 FIG. 38, TR NR 57-85, EO SEMAN NR 2005983 DATE 06-18-05. REMOVED FASTENERS IAW SRM 51-1-21 PAGE 1. TRIMMED OUT DAMAGED AREA IAW SRM 57-2-1 FIG. 38. PERFORMED VISUAL INSPECTION, NO CRACK, CORROSION FOUND. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.071) + FILLER (ALCLAD 7075 T6 0.063) IAW SRM 57-2-1 FIG. 38, SRM 57-3-1 FIG. 3. CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER INTERNAL PART IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR PARTS IAW SRM 57-2-1 FIG. 38, SRM 51-3-0 PAGE 1, SRM 51-1-20D PAGE 9. TOR

Part: PAN — CRACKED (XFS 520.168) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING. CTR L/E ZEE PAN CRACKED 2 INCHES, XFS 520.168. REMOVED AND REPLACED ZEE PAN ON RT WING CTR. L/E XFS 520.168 IAW SRM 51-1-21, SRM 51-1-20 PAGE 9, 21.

Part: SKIN PANEL — CORRODED (XFS38.750-70.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING. SLANT PANEL UPPER PART CORRODED, XFS 38.750 - XFS 70.000. PERFORMED MAJOR REPAIR IAW SRM 57-2-1 FIG. 37, EO NR 20051004 DATE 06-16-05. REMOVED FASTENERS IAW SRM 51-1-21 PAGE 1, SRM 51-1-20D PAGE 21. SMOOTHED AND PERFORMED BLEND OUT TO CORRODED AREA IAW SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SRM 57-2-1. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.125) IAW SRM 57-2-1 FIG. 37. CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER INTERNAL PART (NEW) IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-12. INSTALLED REPAIR DOUBLER AND NEW FASTENERS IAW SRM 57-2-1 FIG. 37, SRM 51-1-21 PAGE 1, SRM 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: SKIN — DEFORMED (XFS-11.250-23.75) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INBD L/E UPPER SURFACE DEFORMED, STA XFS -11.250 TO XFS -23.750. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 05259, SEMAN DWG ED 4016, EO SEMAN 2005948.

Part: SKIN — DAMAGED (XF197.000-213.00) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT OB FLAP FWD UPPER PLATING NON STANDARD REPAIRS (03 EA) AND WEAR DAMAGES BETWEEN STA XF 197.000 - XF 213.000PERFORMED MAJOR REPAIR IAW SRM 57-1-0 PAGE 1, SRM 57-7-1 FIG. 4 TR NR 57-94, EO SEMAN NR 2005912 DATE 06-18-05. REMOVED DAMAGED PLATING WITH INTERIM REPAIR IAW SRM 51-1-21 PAGE 1. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.040”) IAW SRM 57-7-1 FIG. 4 ITEM C. CLEANED, TREATED AND PRIMED AREA AND NEW PLATING INTERNAL PART IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED NEW PLATING IAW SRM 51-1-21 PAGE 1, SRM 51-3-0 PAGE 1. TORQUED IAW SRM 51-3-1.

Part: SKIN — IMPROPER (XFS520.168) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING. CTR L/E SKIN FWD PART HAS NON STANDARD REPAIR. PERFORMED MAJOR REPAIR IAW SRM 57-1-0 PAGE 1, SRM 57-3-1 FIG. 5 SHEET 1, EO SEMAN NR 2005910 DATE 06-18-05. REMOVED DAMAGED PLATING WITH INTERIM REPAIR IAW SRM 51-1-21 PAGE 1. FABRICATED NEW PLATING (ALCLAD 7075 T6 0.063”) IAW SRM 57-3-1 FIG. 5 SHEET 1 ITEM (G). CLEANED, TREATED AND PRIMED AREA AND NEW PLATING INTERNAL PART IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 1. INSTALLED NEW PLATING IAW SRM 51-1-21 PAGE 1, SRM 51-3-0 PAGE 1, SRM 51-1-20D. TORQUED IAW SRM 51-3-1.

Part: SKIN — IMPROPER (XF45.000-87.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT IB FLAP LOWER UPPER PLATING NON STANDARD REPAIRS (02 EA) STA XF 45.000 - XF 87.000. PERFORMED MAJOR REPAIR IAW SRM 57-2-5 FIG. 1, EO NR 2005947. REMOVED FASTENERS IAW SRM 51-1-21 PAGE 1. REMOVED DAMAGED AREA IAW SRM 57-2-5 FIG. 1 SHEET 1,2. PERFORMED NDT INSPECTION. IAW NDT SPM PART 06-10-01-001. NO CRACK, NO CORROSION FOUND. FABRICATED PLATING SEGMENT (02 EA) (NEW) (ALCLAD 2024 T3 0.050”) + INTERNAL SPLICE (03 EA) (ALCLAD 2024 T3 0.063) IAW SRM 57-2-5 FIG. 1, SRM 57-7-1 FIG. 1 ITEM A,1. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED REPAIR PARTS IAW SRM.

Part: GATE — IMPROPER (FS 55.000 L-29L) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, EXTERNAL FUSELAGE. FREON SYSTEM EXHAUST GATE NON STANDARD REPAIR FS 55.000 L-29L. PERFORMED MAJOR REPAIR IAW SRM, EO SEMAN NR 2005946 DATE 06-21-05. REMOVED EXISTING REPAIR DOUBLER IAW SRM. FABRICATED REPAIR DOUBLER (ALCLAD 2024 T3 0.071), FILLER (ALCLAD 2024 T3 0.063) IAW SRM SHEET. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS IAW SRM. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM. INSTALLED REPAIR PARTS AND TORQUED IAW SRM.

Part: SKIN — CRACKED (-17.500-11.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C-CHECK INSPECTION, LT WING INTERIOR ANGLE DEFORMED, STA XFS -17.500 TO XFS -11.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 # 05259 DATE 06-24-05, SEMAN DWG ED 4016 DATE 06-20-05, EO SEMAN NR 2005948 DATE 06-24-05.

Part: SKIN — IMPROPER (ZONE 800) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, FWD.- PASSENGER DOOR UPPER PART HAS INTERIN REPAIR. PERFORMED MAJOR REPAIR IAW DC-8 SRM 52-2-0 FIG. 4, EO SEMAN NR 20051011 DATE 06-28-05. REMOVED INTERIM REPAIR IAW DC-8 SRM 51-1-21 PAGE 1. PERFORMED DETAILED VISUAL INSPECTION, NO CRACK, CORROSION FOUND. FABRICATED REPAIR DOUBLER (ALCLAD 2024 T3 0.050”) IAW DC-8 SRM 52-2-0 FIG. 4 (SHEET 3), DC-8 SRM 53-3-1 FIG. 1 ITEM L, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA AND REPAIR DOUBLER IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED REPAIR DOUBLER IAW DC-8 SRM 52-2-0 FIG. 4, DC-8 SRM 51-1-21 PAGE 1.

Part: SKIN — DENTED (XW131.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LH INBD FLAP UPPER PART DENTED, XW 131.000 PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 57-7-1 FIG. 1, EO SEMAN Nº 20051010 DATE 06-28-05. REMOVED DAMAGED PLATING IAW DC-8 SRM 51-1-21 PAGE 1. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.025”) + BONDED DOUBLER (ALCLAD 2024 T3 0.020”) IAW DC-8 SRM 57-7-1 FIG. 1 ITEM “A”, “L”. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9 BONDED DOUBLER. IAW DC-8 SRM 51-1-9 (HYSOL). INSTALLED NEW PANEL IAW DC-8 SRM 51-1-21 PAGE 1.

Part: SKIN — WORN (XF226.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT OTBD FLAP FWD UPPER PLATING WORN, STA XF 226.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05258 DATE 06-24-05, SEMAN DWG ED 4005 DATE 06-20-05, EO SEMAN 2005913 DATE 06-24-05. REMOVED FASTENERS IAW DC-8 SRM 51-3-0 PAGE 1, C-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 21. REMOVED DAMAGED PLATING IAW SEMAN DWG ED 4005, PERFORMED NDT INSPECTION. IAW DC-8 NDT SPM PART 06-10-01-001. NO CRACK, NO CORROSION FOUND. FABRICATED NEW PLATING SEGMENT + INTERNAL SPLICE + EXTERNAL DOUBLERS IAW SEMAN DWG ED 4005, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 S

Part: VANE — MISREPAIRED (XOLDI6.235) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING SLOT VANE NON STANDARD REPAIR, STA XOLDI 6.235. REMOVED EXISTING REPAIR DOUBLER IAW SRM 51-1-21 PAGE 1. REMOVED DAMAGED AREA IAW SEMAN DWG ED 4003, PERFORMED NDT INSPECTION. NO CRACK, NO CORROSION FOUND. FABRICATED EXTERNAL REPAIRS DOUBLER (ALCLAD 7075 T6 0.071) + FILLER (ALCLAD 7075 T6 0.063) + INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.063”) IAW SEMAN DWG ED 4003, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS INTERNAL PART IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4003, SRM 51-1-21 PAGE 1, SRM 51-3-0 PAGE 1, SRM 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: SKIN — BROKEN (XFS51.250-57.500) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING IB L/E UPPER SURFACE BROKEN, STA XFS 51.250 - 57.500. PERFORMED MAJOR REPAIR IAW SRM 57-2-1 FIG. 25, EO SEMAN NR 2005908 DATE 06-15-05. REMOVED DAMAGED AREA IAW SRM 57-2-1 FIG. 21. PERFORMED NDT INSPECTION IAW NDT SPM PART 06-10-01-001. FABRICATED INTERNAL REPAIR DOUBLER (ALCLAD 2024 T3 0.090”) + FILLER (ALCLAD 2024 T3 0.063”) IAW SRM 57-2-1 FIG. 21. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS INTERNAL PART IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-12. INSTALLED REPAIR PARTS IAW SRM 57-2-1 PAGE 21, SRM 51-1-21 PAGE 1.

Part: SKIN — DENTED (XW2.000-20.000) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECTION, LT IB FLAP UPPER PART WITH SEVERAL DENTS XW 2.000 - XW 20.000. PERFORMED MAJOR REPAIR IAW SRM 57-2-5 FIG. 1, EO NR 20051013 DATE 06-29-05. REMOVED FASTENERS IAW SRM 51-1-21 PAGE 1, SRM 51-3-0PAGE 1. REMOVED PLATING SEGMENT (DAMAGED) IAW SRM 57-2-5 FIG. 1. PERFORMED NDT INSPECTION IAW NDT SPM PART 06-10-01-001. NO CRACK, CORROSION FOUND. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.050”) + INTERNAL SPLICE (ALCLAD 2024 T3 0.063”) IAW SRM 57-2-5 FIG. 1 (SHEET 1,3), SRM 57-7-1 FIG. 1 ITEM A. CLEANED, TREATED AND PRIMED AREA + NEW PLATING INTERNAL PART IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW SRM. TORQUED IAW SRM 51-3-1.

Part: SKIN PANEL — IMPROPER (XF 134.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C-CHECK INSPECTION, RH. INBD. FLAP.- FWD UPPER PLATING HAS INTERIN REPAIR, XF 134.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 57-7-1 FIG. 1, EO SEMAN 20051009 DATE 06-28-05. REMOVED PLATING WITH INTERIM REPAIR IAW DC-8 SRM 51-1-21 PAGE 1. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.050”) IAW DC-8 SRM 57-7-1 FIG. 1 ITEM F. CLEANED, TREATED AND PRIMED AREA AND NEW PLATING INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED NEW PLATING IAW DC-8 SRM 51-1-21 PAGE 1.

Part: DOUBLER — CORRODED (35.000-70.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, FUSELAGE EXTERIOR INTERNAL DOUBLER CORRODED , STA 35.000 - 70.000 BETWEEN L - 28 TO L 31. PERFORMED MAJOR REPAIR IAW SRM 53-1-0 PAGE 1, SRM 53-3-1 FIG. 1, EO SEMAN NR 2005877 DATE 06-22-05. REMOVED CORROSION IAW SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SRM 53-2-0 PAGE 2P. REMOVED CORRODED INTERNAL DOUBLER IAW SRM 51-1-21 PAGE 1. FABRICATED NEW INTERNAL DOUBLER (ALCLAD 7075 T6 0.025”) IAW SRM 53-3-1 FIG. 1 ITEM D. CLEANED, TREATED AND PRIMED AREA AND INTERNAL DOUBLER IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED NEW INTERNAL DOUBLER IAW SRM 51-1-21 PAGE 1.

Part: ANGLE — DEFORMED (XFS17.500 -11.00) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING INTERIOR ANGLE DEFORMED, STA XFS -17.500 TO XFS -11.000. PERFORMED MAJOR REPAIR, EO MFG NR 2005948 DATE 06-24-05. REMOVED FASTENERS IAW SRM. REMOVED DAMAGED AREA IAW DWG NR ED 4016, PERFORMED NDT INSPECTION. IAW NDT. FABRICATED NEW LWR. STANT PANEL SEGMENT (PLATE 7075 T6 51) + (04 EA) ANGLE REPAIR DOUBLERS (PLATE 7075 T6 51) + (01 EA) REPAIR ANGLE DOUBLER (TITANIUM 651-4V 0.032”) + EXTERNAL REPAIR DOUBLER (ALCLAD 7075 T6 0.071”) +(02 EA) + CLIP (EXTRUSION 7075 T6 51) + SHIM (ALCLAD 7075 T6) IAW DWG ED 4016. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS IAW SRM. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM. INSTALLED REPAIR PARTS AND TORQUED IAW SRM.

Part: SKIN — IMPROPER (XF415.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSP, RT OB FLAP FWD UPPER PLATING NON STANDARD REPAIR AT STA XF 415.000. PERFORMED MAJOR REPAIR IAW SRM 57-1-0 PAGE 1, SRM 57-7-1 FIG. 4 TR NR 57-94, EO SEMAN NR 2005914 DATE 06-18-05. REMOVED DAMAGED PLATING IAW SRM 51-1-21 PAGE 1. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.032”) IAW SRM 57-7-1 FIG. 4 ITEM P. CLEANED, TREATED AND PRIMED AREA AND NEW PLATING INTERNAL PART IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED NEW PLATING IAW SRM 51-1-21 PAGE 1.

Part: SKIN PANEL — CORRODED (70.000-115.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, EXTERNAL FUS CORRODED, STA. 70.000 STA. 115.000, L-35L - L-35R. PERFORMED MAJOR REPAIR IAW SRM 53-1-0 PAGE 1, SRM 53-3-1 FIG. 1 ITEM A, EO NR 2005864 DATE 06-13-05. REMOVED CORROSION IAW SRM 51-1-8 PAGES 17, 18, FOUND OUT OF LIMITS IAW SRM 53-2-0 PAGE 2P. REMOVED CORRODED PLATING SEMENT IAW SRM 51-1-21 PAGE 1. FABRICATED EXTERNAL SPLICES (02 EA) (ALCLAD 7075 T6 0.063”) + (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) + (02 EA) INTERNAL DOUBLER (ALCLAD 7075 T6 0.050) IAW SRM, CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW SRM. APPLIED SEALANT TO FAYING SURFACES IAW SRM. INSTALLED NEW PLATING SEGMENT (PN 5613862-15N1) + REPAIR PARTS AND TORQUED IAW SRM.

Part: FITTING — CORRODED (1215.000 L-31L) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, AFT. LWR. CARGO BILGE INTERIOR. NR 3 DOOR HOUSING LWR FITTING CORRODED (INTERNAL STRUCTURE), STA. 1215.000, L-31LREMOVED 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 PAGE 21. FABRICATED NEW FITTING IAW DWG DOUGLAS NR 3750248 (ALCLAD 7075 T6 51). PERFORMED HEAT TREATMENT IAW SRM 51-1-11 PAGES 1,13,17. PERFORMED NDT INSPECTION IAW NDT SPM PART 08-00-02 TO 07. NO CRACK, CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA + NEW FITTING IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: FITTING — CRACKED (1766.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, AFT. ACCESSORY COMPARTMENT FITTING CRACKED L-28R, STA 1766.000 REMOVED CRACKED FITTING IAW SRM 51-1-20D PAGE 21. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-1-20D PAGE 1. TORQUED IAW SRM 51-3-0.

Part: FITTING — CRACKED (1690.000 L-30L) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, AFT ACCESSORY COMPARTMENT BATHTUB FITTING CRACKED, STA 1690.000 L - 30L. REMOVED CRACKED BATHTUB FITTING IAW SRM 51-1-20D PAGE 21. FABRICATED NEW FITTING (ALCLAD 7075 T6 51) IAW DWG 4641324. PERFORMED HEAT TREATMENT IAW SRM 51-1-1 PAGES 1,13,17. PERFORMED NDT 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 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: FITTING — CRACKED (8.000 L33L) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, NOSE SECTION FITTING CRACKED 5 INCHES, STA. 8.000 L-33L. REMOVED CRACKED FITTING IAW SRM 51-1-20D PAGE 21. FABRICATED NEW FITTING IAW DWG NR 4645453 (ALCLAD 7075 T6 51), EO SEMAN NR 2005939. PERFORMED HEAT TREATMENT IAW SRM 51-1-11 PAGS 1,13,17. PERFORMED NDT 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 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1. AT STA 8.000 L-33L.

Part: ANGLE — CRACKED (XW129.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT IB FLAP INTERNAL ANGLE CRACKED 3 INCH, STA XW 129.000. REMOVED CRACKED ANGLE IAW SRM 51-1-21. FABRICATED NEW ANGLE (A EXTRUSION S-1656396) IAW SRM 57-2-0 PAGE 1. CLEANED, TREATED AND PRIMED AREA + NEW ANGLE IAW SRM 51-1-8B. INSTALLED NEW ANGLE IAW SRM 51-1-21 PAGE 1.

Part: FITTING — CRACKED (STA 8.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, NOSE SECTION STA. 8.000 RT SIDE FITTING CRACKED 5 INCHES (L-33R) REMOVED CRACKED FITTING IAW SRM 51-1-20D PAGE 21. FABRICATED NEW FITTING IAW DWG DOUGLAS NR 4645453 (ALCLAD 7075 T6 51), EO SEMAN NR 2005938. PERFORMED HEAT TREATMENT IAW SRM 51-1-11 PAGS 1,13,17. PERFORMED NDT 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 51-1-20D PAGE 9, SRM 51-3-1. TORQUED IAW SRM 51-3-1.

Part: FITTING — CORRODED (1690.00 L-36) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO CMPT. FITTING CORRODED AT STA. 1690.00, L-36 REMOVED CORROSION IAW SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SRM 53-2-0 PAGE 21. REMOVED CORRODED FITTING IAW SRM 51-1-20D PAGE 21. FABRICATED NEW FITTING IAW DWG NR 4641324 (ALCLAD 7075 T6 51). PERFORMED HEAT TREATMENT IAW SRM 51-1-11 PAGES 1,13,17. PERFORMED NDT 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 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: FITTING — CRACKED (1690.000 L-34R) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, AFT ACCESSORY COMPARTMENT BATHTUB FITTING CRACKED, STA 1690.000 L-34R. REMOVED CRACKED BATHTUB FITTING IAW SRM 51-1-20D PAGE 21. FABRICATED NEW BATHTUB FITTING (ALCLAD 7075 T6 51) IAW DWG 4641324. PERFORMED HEAT TREATMENT IAW SRM 51-1-1 PAGES 1,13,17. PERFORMED NDT 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 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: FITTING — CRACKED (1690.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, AFT ACCESSORY COMPARTMENT BATHTUB FITTING, CRACKED STA 1690.000 L-34L. REMOVED CRACKED BATHTUB FITTING IAW SRM 51-1-20D PAGE 21. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. INSTALLED NEW BATHTUB FITTING IAW SRM 51-1-20D PAGE 1. TORQUED IAW SRM 51-3-1.

Part: FITTING — CORRODED (STA 70.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, ACND. CMPT. LT FITTING CORRODED STA 70.000, L-31R. 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 PAGE 21. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: LONGERON — CORRODED (XS 1690.00 L-36) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO CMPT.- L-36 CORRODED, STA. 1690.00 - STA. 1700.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-2 FIG. 4A, EO SEMAN Nº 2005937 DATE 06-22-05. 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 LONGERON SEGMENT IAW DC-8 SRM 53-2-2 FIG. 4. PERFORMED DETAILED VISUAL INSPECTION PAST LONGERON SEGMENT TRIM. NO CRACK, CORROSION FOUND. FABRICATED NEW LONGERON SEGMENT IAW DC-8 SRM 53-2-2 FIG. 4A, DC-8 SRM 53-5-11 FIG. 7, ITEM A, DC-8 SRM 51-2-0 FIG. 50 + SPLICE IAW DC-8 SRM 53-2-2 FIG. 10, TR NR 53-193, DC-8 SRM 53-2-2 FIG. 10 TR NR 53-153. PERFORMED HEAT TREATMENT TO SPLICE IAW DC-8 SRM 51-1-1 PAGES 1,13,7. CLEANED,

Part: SKIN PANEL — IMPROPER (XW84.00-91.00) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT IB FLAP FWD UPPER PLATING NON STANDARD REPAIRS (02 EA ) STA XW 84.00 -XW 91.00. PERFORMED MAJOR REPAIR IAW NR 05258 DATE 06-24-05, DWG ED 4004, EO NR 2005911 DATE 06-24-05. REMOVED FASTENERS IAW SRM. REMOVED PLATING SEGMENT (DAMAGED) IAW DWG NR ED 4004, PERFORMED NDT INSPECTION. IAW NDT SPM PART. NO CRACK, NO CORROSION FOUND. FABRICATED NEW PLATING SEGMENT (ALCLAD 2024 T3 0.040”) + INTERNAL SPLICE (ALCLAD 2024 T3 0.050) + EXTERNAL DOUBLERS (02 EA) (ALCLAD 2024 T3 0.050) IAW DWG ED 4004, SRM. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS INTERNAL PART IAW SRM. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM. INSTALLED REPAIR PARTS AND TORQUED IAW SRM.

Part: LONGERON — CORRODED (1726.000 L-28R) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, MAIN CARGO CMPT.- L-28R CORRODED, STA. 1726.000. REMOVED CORROSION IAW SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW SRM 53-2-0 PAGE 2. REMOVED CORRODED LONGERON IAW SRM 51-1-20D PAGE 1, DC-8 SRM 51-1-21 PAGE 1. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. INSTALLED NEW LONGERON IAW SRM 51-1-21 PAGE 1, SRM 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: LONGERON — CRACKED (1690.000 L-34R) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, AFT ACCESSORY COMPARTMENT, L -34R CRACKED STA 1690.000. PERFORMED MAJOR REPAIR IAW SRM 53-1-0 PAGE 1, SRM 53-5-1 FIG. 7, EO SEMAN NR 2005863 DATE 06-18-05. REMOVED CRACKED LONGERON SEGMENT + EXISTING SPLICES IAW SRM 51-1-20D PAGE 21. CLEANED, TREATED AND PRIMED AREA + SPLICES IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED NEW LONGERON SEGMENT (PN 51415997) REINSTALLED SPLICES IAW SRM 53-5-1 FIG. 7 PAGE 22 ITEM A, SRM 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: FITTING — CRACKED (220.000 240.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, FWD CARGO COMPT, FITTING CRACKED 1 INCH AT STA 220.000 - 240.000 L-31R. REMOVED DAMAGED FITTING IAW SRM 51-1-20D PAGE 21. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-1-20D PAGE 1. TORQUED IAW SRM 51-3-1.

Part: SKIN — DELAMINATED (ZONE 600) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING, T/E LWR PANEL EXTERNAL , INTERNAL SKIN DELAMINATED, XW 0.000 - XW 90.000. REMOVED AND REPLACED PANEL ON RT WING T/E, XW 0.000 XW 90.000 IAW DC-8 SRM 51-3-0 PAGE 1, DC-8 SRM 51-1-21 PAGE 14. TORQUED IAW DC-8 SRM 51-3-1.

Part: SKIN — NICKED (XF 226.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSP, LT OB FLAP L/E NICKED, XF 226.000 (UPPER PART) PERFORMED MAJOR REPAIR, DWG NR ED 3987 DATE 06-20-05, EO. REMOVED FASTENERS IAW SRM. REMOVED DAMAGED PLATING SEGMENT IAW DWG ED 3987. PERFORMED NDT INSP IAW SPM. NO CRACK, CORROSION FOUND. FABRICATED NEW PLATING SEGMENT (ALCLAD 2024 T3 0.071) + INTERNAL SPLICE (ALCLAD 2024 T3 0.080) + (02 EA) EXTERNAL DOUBLERS (ALCLAD 2024 T3 0.071”) IAW DWG ED 3987, SRM. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS (INTERNAL PART) IAW SRM. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 3987, SRM 51-1-21 PAGE 1, SRM 51-3-0 PAGE 1, SRM 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, AFT CARGO CMPT L-36 CORRODED, STA 1540.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-2 FIG 4A, EO SEMAN NR 2005846 DATE 06-18-05. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 53-2-0 PAGE 2P. REMOVED CORRODED LONG SEGMENT IAW DC-8 SRM 53-2-2 FIG 4A. PERFORMED DETAILED VISUAL INSPECT. NO CRACK, CORROSION FOUND FAST LONGERON SEGMENT CUT. FAB`D NEW LONGERON SEGMENT (PN 52597242-3-14400 EXTRUSION) IAW DC-8 SRM 53-2-2 FIG 4A, DC-8 SRM 53-4-1 FIG 42 (SHEET 2) ITEM “Q”, SPLICE (02 EA) (ALCLAD 7075 T651) IAW DC-8 SRM 53-2-2 FIG 10 (SHEET 4), TR # 53-193 IAW DC-8 SRM 53-2-2 FIG 10 (SHEET 2) TR # 53-153. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC-8 SR

Part: FITTING — CRACKED (STA 1420.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, AFT LWR CARGO BILGE INTERIOR.- NR 4 DOOR INTERNAL SUPPORT CTR FITTING CRACKED, STA 1420.000. REMOVED CRACKED FITTING IAW DC-8 SRM 51-1-21 PAGES 1 CLEANED, TREATED AND PRIMED AREA DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-21 PAGE 21.

Part: FRAME — CRACKED (ZONE 100) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, NOSE SECTION, DOUPLER ANTENNA FRAME WITH 02 CRACKS 2" EACH ONE. REMOVED DOUPLER ANTENNA FRAME (CRACKED) IAW DC-8 SRM 51-1-21 PAGE 1. FABRICATED NEW DOUPLER ANTENNA CAP IAW DWG DOUGLAS NR 561601 (ALCLAD 7075 T6 0.125). PERFORMED HEAT TREATMENT IAW DC-8 SRM 51-1-1 PAGES 1,13,17. CLEANED, TREATED AND PRIMED IAW DC-8 SRM 51-1-8B. INSTALLED NEW CAP IAW DC-8 SRM 51-1-2 PAGE 1.

Part: SKIN — DELAMINATED (ZONE 500) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT LWR WING T/E NR 546 ACCESS DOOR EXTERNAL SKIN DELAMINATED. REMOVED AND REPLACED EXTERNAL PANEL IN LT LWR WING T/E NR 546 ACCESS DOOR IN ACCORDANCE WITH DPS 367-15.

Part: FITTING — CRACKED (440.000-460.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, FWD CARGO CMPT.- SPLICE FITTING CRACKED 2", STA 440.000 - 460.000 L-31R. REMOVED CRACKED SPLICE FITTING IAW DC-8 SRM 51-1-20D PAGES 21. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED SPLICE FITTING IAW DC-8 SRM 51-1-20D PAGE 9, DC-8 SRM 51-1-15 PAGE 1, DC-8 SRM 51-3-0 PAGE 1. TORQUED IAW DC-8 SRM 51-3-1.

Part: SKIN — CRACKED (ZONE 800) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECTION, RT MLG REMOVE AND INSTALL CTR DOOR (LWR SKIN CRACKED). REMOVED AND REPLACED CTR MAIN PANEL ON RT MLG IN ACCORDANCE WITH DC-8 MM 32-12-1 PAGE 401. FOR OPS CHECK SEE J/C 74204.

Part: SKIN — WORN (XW104.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LH INBOARD FLAP UPPER PART SKIN WORN, XW 104.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 57-7-1 FIG. 1, EO SEMAN NR 2005850 DATE 06-18-05. REMOVED DAMAGED PLATING IAW DC-8 SRM 51-1-21 PAGE 1. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.040”) IAW DC-8 SRM 57-7-1 FIG. 1 ITEM “D”. CLEANED, TREATED AND PRIMED AREA + NEW PLATING INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED NEW PLATING IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-3-0 PAGE 1. TORQUED IAW DC-8 SRM 51-3-1.

Part: FITTING — CORRODED (1215.000 L-31L) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C-CHECK INSPECTION, AFT LOWER CARGO COMPT. INTERIOR.- FITTING CORRODED IN NR 3 DOOR HOUSING , STA 1215.000 NEAR TO L-31L. 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 PAGE 21. FABRICATED NEW FITTING IAW DWG DOUGLAS 3750248 (ALCLAD 7075 T651) PERFORMED HEAT TREATMENT IAW DC-8 SRM 51-1-11 PAGES 1, 13, 17. PERFORMED NDT INSPECTION IAW NDT SPM PART 08-00-02 TO 07. NO CRACK CORROSION FOUND. CLEANED, TREATED AND PRIMED AREA + NEW FITTING IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-20D PAGE 9. TORQUED IAW DC-8 SRM 51-3-1.

Part: VANE — ELONGATED (XW 454.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C-CHECK INSPECTION, LT WING.- VANE SLOT REPAIR HOLE ELONGATED, XW 454.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3, SEMAN DWG ED 3982, EO SEMAN 2005835. REMOVED FASTENERS IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 21. TRIMMED OUT DAMAGED AREA IAW SEMAN DWG EO 3982. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM. NO CRACK, NO CORROSION FOUND FAST STOP DRILL. FABRICATED EXTERNAL REPAIR DOUBLER, FILLER, INTERNAL DOUBLER IAW SEMAN DWG ED 3982. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS IAW DC-8 SRM. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 3982, DC-8 SRMS. TORQUED IAW DC-8 SRM.

Part: WEB — CRACKED (XCW 69.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING T/E WEB UPPER PART CRACKED 1/2, XCW 69.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-2-6 FIG. 15, EO SEMAN NR 2005836 DATE 06-25-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-20D PAGE 21. REMOVED DAMAGED AREA IAW DC-8 SRM 57-2-6 FIG. 15. PERFORMED NDT INSPECTION IAW NDT SPM PART 06-10-01-001. FABRICATED REPAIR DOUBLER, FILLERS (02 EA) IAW DC-8 SRM 57-2-6 FIG. 15. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW DC-8 SRM 57-2-6 FIG. 15, DC-8 SRM 51-3-0 PAGE 1, DC-8 SRM 51-1-20D PAGE 9. TORQUED IAW DC-8 SRM 51-3-1.

Part: PANEL — CORRODED (XW 6.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LH WING.- SLANT PANEL UPPER PART CORRODED, XW 6.000 PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-2-1 FIG. 37, EO SEMAN Nº 2005847 DATE 06-16-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 21. SMOOTHED, PERFORMED BLEND OUT TO CORRODED AREA IAW DC-8 SRM 51-1-8 PAGES 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-1 PAGES 11, 12. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.125”) IAW DC-8 SRM 57-2-1 FIG. 37. CLEANED, TREATED AND PRIMED AREA NEW REPAIR DOUBLER INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-12. INSTALLED REPAIR DOUBLER WITH NEW FASTENERS IAW DC-8 SRM 57-2-1 FIG. 37, DC-8 SRM 51-1-20D PAGE 9, DC-8 SRM 51

Part: SKIN — IMPROPER (XW 132.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LH INBD FLAP UPPER PART SKIN NON STANDARD REPAIR, XW 132.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-1-0 PAGE 1, DC-8 SRM 57-7-1 FIG. 1, EO SEMAN NR 2005851 DATE 06-18-05. REMOVED PLATING WITH IMPROPER REPAIR IAW DC-8 SRM 51-1-21 PAGE 1. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.050”) IAW DC-8 SRM 57-7-1 FIG. 1 ITEM “F”. CLEANED, TREATED AND PRIMED AREA + NEW PLATING INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED NEW PLATING IAW DC-8 SRM 51-1-21 PAGE 1.

Part: SKIN — CRACKED (LT WING) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, LT WING, SKIN UPPER PART WITH 02 CRACKS 1", 1/2", XRS 74.000 S-9 - S10. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-2-1 FIG 10, EO SEMAN NR 2005833 DATE 06-14-05. REMOVED DAMAGED AREA IAW DC-8 SRM 57-2-1 FIG 10 (SHEET 3). PERFORMED NDT INSPECT IAW DC-8 NDT SPM PART 06-10-01-001. NO CRACK, CORROSION FOUND. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.125), (02 EA) FILLERS PLUG (ALCLAD 7075 T6 0.175) PART DOUBLER FROM 0.125 TO 0.080 OVER 4 LENGTH (TYP BOTH ENDS) IAW DC-8 SRM 57-2-1 FIG 10 (SHEET 3). CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PG 9. INSTALLED REPAIR PARTS IAW DC-8 SRM 57-2-1 FIG 10 (SHEET 3), DC-8

Part: WING — CORRODED (XFS 212.000) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, LT WING NR 2 STUB WING UPPER PART CORRODED, XFS 212.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-2-1 FIG 38. TR NR 57-85, EO SEMAN NR 2005848 DATE 06-18-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-21 PG 1, DC-8 SRM 51-1-20D PG 21. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PG 17-18. FOUND OUT OF LIMITS IAW DC-8 SRM 57-2-1 PG 11-12. REMOVED CORRODED AREA IAW DC-8 SRM 57-2-1 FIG 38. PERFORMED VISUAL INSPECT NO CRACK FOUND, NO CORROSION FOUND. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.071”), FILLER (ALCLAD 7075 T6 0.063) IAW DC-8 SRM 57-2-1 FIG 38, DC-8 SRM 57-3-1 FIG 3. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW

Part: SKIN — CRACKED (XRS) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, RT WING UPPER SKIN HAS 2 CRACKS OF 1" EACH AT XRS 74. 869, S-15 AND S-16. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 # 05280 DATE 07-04-05, SEMAN DWG # ED 3981 DATE 06-29-05, EO SEMAN NR 2005834 DATE 07-04-05. REMOVED EXISTING REPAIR DOUBLERS IAW DC-8 SRM 51-1-20D PAGE 21. REMOVED DAMAGED AREA IAW SEMAN DWG ED 3981. PERFORMED NDT INSPECT IAW DC-8 SPM PART 06-10-01-001. FAB`D EXTERNAL REPAIR DOUBLER (ALCLAD 7075 T6 0.160”), (03 EA) FILLER PLUG (ALCLAD 7075 T6) IAW SEMAN DWG ED 3981. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS (INTERNAL PART) IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 3981, DC-8 SRM

Part: SKIN PANEL — DENTED (LT WING) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECTION, LT OTBD FLAP L/E DENTED, XF 213.000 (UPPER PART. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-1-0 PG 1, DC-8 SRM 57-7-1 FIG 4, TR NR 57-94, EO SEMAN NR 2005852 DATE 06-18-05. REMOVED DAMAGED PLATING IAW DC-8 SRM 51-1-21 PG 1, DC-8 SRM 51-3-0 PG 1. FAB`D NEW PLATING (ALCLAD 2024 T3 0.040”) IAW DC-8 SRM 57-7-1 FIG 4, TR 57-94 ITEM “C”. CLEANED, TREATED AND PRIMED AREA, NEW PLATING INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PG 9. INSTALLED NEW PLATING IAW DC-8 SRM 51-1-21 PG 1, DC-8 SRM 51-3-0 PG 1. TORQ`D IAW DC-8 SRM 51-3-1.

Part: SKIN — MISREPAIRED (XF304.000-309.00) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT OB FLAP NON STANDARD REPAIR, XF 304.000 -XF 309.000 (UPPER PART). PERFORMED MAJOR REPAIR IAW SRM 57-1-0 PAGE 1, SRM 57-7-1 FIG. 4, TR NR 57-94, EO SEMAN NR 2005854 DATE 06-18-05. REMOVED PLATING WITH IMPROPER REPAIR IAW SRM 51-1-21 PAGE 1. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.050”) IAW SRM 57-7-1 FIG. 4, TR 57-94 ITEM A. CLEANED, TREATED AND PRIMED AREA + NEW PLATING INTERNAL PART IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED NEW PLATING IAW SRM 51-1-21 PAGE 1.

Part: SKIN — MISREPAIRED (XF 345.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT OB FLAP, NON STANDARD REPAIR, XF 345.000 (UPPER PART) PERFORMED MAJOR REPAIR IAW SRM 57-1-0 PAGE 1, SRM 57-7-1 FIG. 4, TR NR 57-94, EO SEMAN NR 2005856 DATE 06-18-05. REMOVED PLATING WITH IMPROPER REPAIR IAW SRM 51-1-21 PAGE 1. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.063”) IAW SRM 57-7-1 FIG. 4 ITEM B. CLEANED, TREATED AND PRIMED AREA + NEW PLATING INTERNAL PART IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED NEW PLATING IAW SRM 51-1-21 PAGE 1, SRM 51-3-0 PAGE 1. TORQUED IAW SRM 51-3-1.

Part: SKIN — IMPROPER (LT WING) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECTION, LT OTBD FLAP L/E UPPER PART NON STANDARD REPAIR, XF 415.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-1-0 PG 1, DC-8 SRM 57-7-1 FIG 4, TR # 57-94, EO SEMAN NR 2005857 DATE 06-18-05. REMOVED PLATING WITH IMPROPER REPAIR IAW DC-8 SRM 51-1-21 PG 1. FAB`D NEW PLATING (ALCLAD 2024 T3 0.032”) IAW DC-8 SRM 57-7-1 FIG. 4, TR 57-94 ITEM “P”. CLEANED, TREATED AND PRIMED AREA, NEW PLATING INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED NEW PLATING IAW DC-8 SRM 51-1-21 PAGE 1.

Part: SKIN — IMPROPER (XF 415.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT IB FLAP REPAIR IMPROPER, XF 415.000 (UPPER PART) PERFORMED MAJOR REPAIR IAW SRM 57-2-5 FIG. 1. EO SEMAN NR 2005858 DATE 06-18-05. REMOVED DAMAGED PLATING IAW SRM 57-2-5 FIG. 1(SHEET 1,2). PERFORMED DETAILED VISUAL INSPECTION TO AREA, NO CRACK FOUND, NO CORROSION FOUND. FABRICATED NEW PLATING (ALCLAD 2024 T3 0.050”) + FILLER (ALCLAD 2024 T3 0.020”) IAW DC-8 SRM 57-2-5 FIG. 1 (SHEET 1,2), SRM 57-7-1 FIG. 4 ITEM Q AND U. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS INTERNAL PART IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW SRM 57-2-7 FIG. 1, SRM 51-1-21 PAGE 1, SRM 51-3-0 PAGE 1. TORQUED IAW SRM 51-3-1.

Part: WING — ELONGATED (XS) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, LT WING, NR 2 STUB WING VANE SLOT HOLE ELONGATED, XS 247.000. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 # 05270 DATE 06-29-05, SEMAN DWG # 3986 DATE 06-28-05, EO SEMAN # 2005849 DATE 06-29-05. REMOVED DAMAGED AREA IAW SEMAN DWG ED 3986. PERFORMED NDT INSPECT IAW DC-8 NDT SPM PART 06-10-01-001. FAB`D EXISTING REPAIR DOUBLER (ALCLAD 7075 T6 0.071”), FILLER (ALCLAD 7075 T6 0.063”) IAW SEMAN DWG # 3986. CLEANED, TREATED AND PRIMED AREA, REPAIRS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PG 9. INSTALLED REPAIR PARTS IAW SEMAN DWG # 3986, DC-8 SRM 51-3-0 PG 1, DC-8 SRM 51-1-21 PG 1, DC-8 SRM 51-1-20D PG 9. TORQUED IAW DC-8 SRM 51-3-1.

Part: WING — CRACKED (XRS 74. 869 S-10) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING UPPER SKIN CRACKED 1INCH, STA. XRS 74. 869, S-10. REMOVED EXISTING REPAIR DOUBLERS SRM 51-1-20D PAGE 21. REMOVED DAMAGED AREA IAW SEMAN DWG ED 3981. PERFORMED NDT INSPECTION IAW SPM PART 06-10-01-001. FABRICATED EXTERNAL REPAIR DOUBLER (ALCLAD 7075 T6 0.160”) + (03 EA) FILLER PLUG (ALCLAD 7075 T6) IAW SEMAN DWG ED 3981. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS (INTERNAL PART) IAW SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 3981, SRM 51-1-20D PAGE 9. TORQUED IAW SRM 51-3-1.

Part: SKIN — CRACKED (ZONE 500) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT WING NR 5 SPOILER LWR SKIN WITH 02 CRACKS 2", XRS 367.000 - XRS 421.000. REMOVED REPLACED NR 5 SPOILER PANEL ON LT WING XRS 367.000 XRS 421.000 IN ACCORDANCE WITH DC-8B MM 27-61-1 PAGES 201-205.

Part: FLAP — IMPROPER (XF 333.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT OB FLAP L/E REPAIR IMPROPER, XF 333.000 (UPPER PART) PERFORMED MAJOR REPAIR IAW NR 05259 DATE 06-24-05, DWG NR ED 3988, EO NR 2005855 DATE 06-24-05. REMOVED FASTENERS IAW SRM. REMOVED DAMAGED PLATING SEGMENT IAW DWG ED 3988. PERFORMED NDT INSPECTION IAW SPM. NO CRACK, CORROSION FOUND. FABRICATED NEW PLATING SEGMENT (ALCLAD 2024 T3 0.071”) + INTERNAL SPLICE (ALCLAD 2024 T3 0.080”) + (02 EA) EXTERNAL DOUBLERS (ALCLAD 2024 T3 0.071) IAW DWG ED 3988, SRM. CLEANED, TREATED AND PRIMED REPAIR PARTS (INTERNAL PART) + AREA IAW SRM. APPLIED SEALANT TO FAYING SURFACES IAW SRM. INSTALLED REPAIR PARTS IAW DWG ED 3988, SRM. TORQUED IAW SRM.

Part: FITTING — CRACKED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, MLG W/W FITTING CRACKED 4 INCHES, STA 940.000, RBL 5 INCHES. REMOVED CRACKED FITTING IAW SRM 51-1-20D. FABRICATED NEW FITTING IAW DWG NR 3643758 (ALCLAD 7075 T6 51). PERFORMED HEAT TREATMENT IAW SRM 51-1-11. PERFORMED NDT INSPECTION IAW NDT SPM PART 08-00-02 TO 07. CLEANED, TREATED AND PRIMED AREA + NEW FITTING IAW SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW SRM 51-1-11. INSTALLED NEW FITTING IAW SRM 51-1-20D. TORQUED IAW SRM 51-3-1.

Part: STRUCTURE — CRACKED (MLG WW) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, MLG W/W L-24 CRACKED 2", STA 980.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-2 FIG 5 TR NR 53-123 DATE 05-15-01, EO SEMAN NR 2005831 DATE 06-16-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-20D PAGE 21. PERFORMED SLOP HOLE ON CRACK END IAW DC-8 SRM 53-2-2 FIG 5 SHEET 21. PERFORMED NDT INSPECT IAW DC-8 NDT SPM PART 06-10-01-001. NO CRACK, CORROSION FOUND. FAB`D REPAIR ANGLE (ALCLAD 2024 T3 0.125”) + WASHERS (ALCLAD 2024 T3 0.090) IAW DC-8 SRM 53-2-2 FIG 5 SHEET 24 IAW DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW DC-8 SRM 53-2-2 FIG 5 SHEET 21, 24,

Part: ANTENNA — DETERIORATED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, RT AFT FUS STA FS 1346.000, L-35.5R. ONLY 2 ROWS OF RIVETS IN OLD ANTENNA DOUBLER ADD 3RD ROWS OF RIVETS UTILIZING SRM RIVET SPACING OR UPGRADE REPAIR DOUBLER, STA 1346.000 L-35.5R (REF 822BX-R14). PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-1 FIG 7 SHEET 1, 3, EO SEMAN # 2005868 DATE 06-13-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PG 1. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.090) + (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.050”) IAW DC-8 SRM 53-2-1 FIG 7 SHEET 1,3, DC-8 SRM 53-4-1 FIG 16 SHEET 1 ITEM E, DC-8 SRM 51-10-0 FIG 2 SHEET 5, DC-8 SRM 51-9-0 FIG 68A, DC-8 SRM 51-1-4 PG 1. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT

Part: SKIN — CORRODED · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPEC, LWR FWD FUS BELLY AFT NLG W/W SIDE 2 AND 4 EXCEED AVG PITCH, SIDE 2 AND 3 EXCEED MAX PITCH, STA 15.000 L-36. ADD RIVETS TO BRING AVG AND MAX PITCH INTO LIMITS PER SRM OR REWORK. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-1-0 PG 1, DC-8 SRM 53-3-1 FIG 1 ITEM A, EO SEMAN # 2005864 DATE 06-13-05. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PGS 17, 18, FOUND OUT OF LIMITS IAW DC-8 SRM 53-2-0 PG 2P. REMOVED CORRODED PLATING SEMENT IAW DC-8 SRM 51-1-21 PG 1. FAB`D EXTERNAL SPLICES (02 EA) (ALCLAD 7075 T6 0.063), (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032), (02 EA) INTERNAL DOUBLER (ALCLAD 7075 T6 0.050) IAW SEMAN DC-8 SRM 53-2-1 (SHEET 1,2), DC-8 SRM 53-2-1 FIG 8 SHEET 3, TR # 53-173, DC-8 S

Part: SKIN — DETERIORATED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, REPAIR ON UAL DRAIN DOUBLER MUST BE UPGRADED. REPAIR MUST HAVE 3 ROWS OF RIVETS STA 1270.000, L-35.5L. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 # 05259 DATE 06-24-05, SEMAN DWG ED 4000 DATE 06-20-05, EO SEMAN # 2005902 DATE 06-24-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PG 1, DC-8 SRM 51-1-20D PG 21. TRIMMED OUT DAMAGED AREA IAW SEMAN DWG NR EO 4000. PERFORMED NDT INSPECT IAW DC-8 NDT SPM PART 06-10-01-001. NO CRACK, CORROSION FOUND. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.063), REPAIR TRIPLER (ALCLAD 7075 T6 0.071), (05 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032) AND (02 EA) FOLLERS (ALCLAD 7075 T6 0.125) IAW SEMAN ED 4000, DC-8 SRM 51-1-4 PG 1. CLEANED, TREATED

Part: FITTING — CORRODED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, MLG W/W FITTING FRAME CORRODED, STA 879.375 AND L-24. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-0 FIG. 8, EO SEMAN NR 2005843 DATE 06-23-05. 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 PAGE 21. FABRICATED SPLICES (02 EA) (ALCLAD 7075 T7 351), (02 EA) SHIMS (ALCLAD 7075 T6 0.071”) IAW DC-8 SRM 53-2-0 FIG 8 (SHEET 1, 3, 6). CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. INSTALLED NEW FRAME FITTING (PN 3641 00 4 U 504) + NEW DOUBLER (PN 5802677-7N) + (04 EA) SPLICES + (06 EA) SHIMS IAW DC-8 SRM 53-2-0 FIG 8 SHEET 1, 3, 6, DC-8 SRM 51-1-20D PAGE 9.

Part: SKIN — DAMAGED (FUSLEAGE) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, EXTERNAL DOUBLER ON FWD FUSELAGE BELLY SKIN, MUST BE UPGRADED, REPAIR MUST HAVE THREE ROWS OF RIVETS AT STA FS 401.000 L-35.75 (REF. 822BX-R47). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05271 DATE 06-29-05, SEMAN DWG ED 3997 DATE 06-24-05, EO SEMAN NR 2005899 DATE 06-29-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1 AND DC-8 SRM 51-1-20D PAGE 21. REMOVED DAMAGED AREA IAW SEMAN DKW ED 3997. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM 06-10-01-001. NO CRACK, CORROSION FOUND. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.080”) + INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) IAW SEMAN DWG ED 3997. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 S

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECTION, EXTERNAL DOUBLER ON FWD FUSELAGE BELLY SKIN MUST BE UPGRADED, REPAIR MUST HAVE THREE ROWS OF RIVETS, STA FS 543.000 L-3.75R (REF. 822BX-R50). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05271 DATE 06-29-05, SEMAN DWG ED 3998 DATE 06-22-05, EO SEMAN NR 2005900 DATE 06-29-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1 AND DC-8 SRM 51-1-20D PAGE 21. PERFORMED DETAILED VISUAL INSPECTION NO CRACK FOUND, NO CORROSION FOUND. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.100”) + INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) IAW SEMAN DWG ED 3998. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-1

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, EXTERNAL DOUBLER ON FWD FUSELAGE BELLY SKIN, MUST BE UPGRADED, REPAIR MUST HAVE THREE ROWS OF RIVETS AT STA FS 1135.000 L-35.5R. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-1 FIG 7 EO SEMAN Nº 2005870 DATE 06-13-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1. REMOVED DAMAGED AREA IAW DC-8 SRM 53-2-1 FIG. 7 (SHEET 1,3). FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.160”) + (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.050”) IAW DC-8 SRM 53-2-1 FIG 7 SHEET 1, 3, DC-8 SRM 53-4-1 FIG 16 SHEET 1, ITEM D, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTA

Part: SKIN — DAMAGED (RT WING) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING INBD L/E UPPER SKIN NON STANDARD REPAIR BETWEEN STA XFS 113.750 - XF 120.000. PERFORMED MAJOR REPAIR IAW DC-8 SRM 57-2-1 FIG. 2J, EO SEMAN NR 2005970 DATE 06-23-05. REMOVED DAMAGED PLATING IAW DC-8 SRM 57-2-1 FIG. 2J. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM PART 06-10-01-001. FABRICATED INTERNAL REPAIR DOUBLER (ALCLAD 2024 T3 0.090”) + FILLERS (ALCLAD 2024 T3 0.063”) IAW DC-8 SRM 57-2-1 FIG. 2J. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS INTERNAL PART IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-12 PAGE 9. INSTALLED REPAIR PARTS IAW DC-8 SRM 57-2-1 FIG. 2J, DC-8 SRM 51-1-21 PAGE 1.

Part: SKIN — INADEQUATE (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXTERNAL DOUBLER FWD FUSELAGE BELLY SKIN MUST BE UPGRADED, REPAIR MUST HAVE THREE ROWS OF RIVETS, STA FS 543.000 L-3.75R (REF. 822BX-R50). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05271 DATE 06-29-05, SEMAN DWG ED 3998 DATE 06-22-05, EO SEMAN NR 2005900 DATE 06-29-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1 DC-8 SRM 51-1-20D PAGE 21. PERFORMED DETAILED VISUAL INSPECT NO CRACK FOUND, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.100”) + INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) IAW SEMAN DWG ED 3998. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INS

Part: SKIN — CRACKED (RT WING) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, RT WING INBD OUTER L/E LWR SKIN CRACKED 1/2", XFS 591.250. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05270 DATE 06-29-05, SEMAN DWG ED 4017 DATE 06-28-05, EO SEMAN NR 2005969 DATE 06-29-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-21 PAGE 1. REMOVED DAMAGED AREA IAW SEMAN DWG ED 4017. PERFORMED NDT INSPECT IAW DC-8 NDT SPM PART 06-60-01-001. NO CRACK, CORROSION FOUND. FAB`D EXTERNAL REPAIR DOUBLER (ALCLAD 7075 T6 0.063”) + FILLER (ALCLAD 7075 T6 0.050”) IAW SEMAN DWG ED 4017. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11 PAGE 9. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 4017, DC-8 SRM 51-1-21 PAGE

Part: DOOR — WORN (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXTERNAL FUS "C" BELLY DOOR LWR PART WORN. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05283 DATE 07-06-05, SEMAN DWG ED 4002 DATE 07-01-05, EO SEMAN NR 2005971 DATE 07-06-05. REMOVED FASTENERS IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 1. REMOVED DAMAGED AREA IAW SEMAN DWG ED 4020. PERFORMED NDT INSPECT IAW DC-8 NDT SPM PART 06-60-01-001. FAB`D NEW SKIN SEGMENT (ALCLAD 7075 T6 0.071”) + (05 EA) INTERNAL SPLICE DOUBLER (ALCLAD 7075 T6 0.071”) + INTERNAL STRAP DOUBLER (TITANIUM GAL-UV 0.032”) IAW SEMAN DWG ED 4020, DC-8 SRM 52-4-1 FIG 1 ITEM “Q”. CLEANED, TREATED AND PRIMED AREA AND REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING S

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXT DOUBLER LT AFT FUSELAGE MUST BE UPGRADED REPAIR MUST HAVE THREE ROWS OF RIVETS, STA FS 1695.000 L-30.5L (REF. 822BX-R67). PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-1 FIG 7, EO SEMAN NR 2005872 DATE 06-13-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 21. TRIMMED OUT DAMAGED AREA IAW DC-8 SRM 53-2-1 FIG 7 (SHEET 1, 5) PERFORMED DETAILED VISUAL INSPECT. NO CRACK, CORROSION FOUND. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.063”) + INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) + FILLER (ALCLAD 7075 T6 0.050”) IAW DC-8 SRM 53-2-1 FIG 7 (SHEET 1,5), DC-8 SRM 53-5-1 FIG 1 ITEM E, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA + REPAIR PAR

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECTION, EXTERNAL DOUBLER LEFT AFT FUSELAGE BELOW L-2 DOOR. REPAIR FAILED ASSESSMENT DOUBLER NOT THICK ENOUGH, SIDES 2 UPPER AND 4 LOWER EXCEED AVERAGE RIVET SPACING SIDES 1 FWD, 2 UPPER, 3 AFT, 4 LOWER EXCEED MAX RIVET SPACING. UPGRADE REPAIR PER DACO DC-8 SRM (STA FS 1670). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05283 DATE 07-06-05, SEMAN DWG ED 4002 DATE 07-01-05, EO SEMAN NR 2005904 DATE 07-06-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1. PERFORMED DETAILED VISUAL INSPECTION. NO CRACK FOUND, NO CORROSION FOUND. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.050”) + INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) IAW SEMAN DWG ED 4002, DC-8 SRM 51-1-4 PAGE 1. C

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXTERNAL DOUBLER ON FWD LOWER FUSELAGE, STA FS 173, L-35.5R REPAIR MUST BE UPGRADED. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05271 DATE 06-29-05, SEMAN DWG ED 3993 DATE 06-22-05, EO SEMAN NR 2005862 DATE 06-29-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1. FAB`D DOUBLER (ALCLAD 7075 T6 0.063”) + (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032) IAW SEMAN ED 3993 AND DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA ALSO REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 3993, DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 9. TORQUED IAW DC-8 SRM 51-3-1.

Part: FITTING — CORRODED (FUSLEAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, MLG W/W FRAME FITTING CORRODED, STA 960.000 L-24. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-1-0 PG 1, DC-8 SRM 53-2-0 FIG. 8 (SHEET 1), EO SEMAN # 2005845 DATE 06-27-05. REMOVED CORROSION IAW DC-8 SRM 51-1-8 PG 17, 18, FOUND OUT OF LIMITS IAW DC-8 SRM 53-2-0 FIG 1F (SHEET 3) PAGE 2P. REMOVED CORRODED FRAME FITTING IAW DC-8 SRM 51-1-20D PG 21. FAB`D FRAME FITTING (NEW) (ALCLAD 7075 T6 51) IAW DWG DOUGLAS NR 3647117, EO SEMAN # 2005842. PERFORMED HEAT TREATMENT IAW DC-8 SRM 51-1-1 PG 1, 13, 17. PERFORMED NDT INSPECT IAW DC-8 SPM PART 08-00-02 TO 07. CLEANED, TREATED AND PRIMED AREA, NEW FRAME FITTING IAW DC-8 SRM 51-1-8B. TRIMMED OUT NEW FITTING TO INSTALL IAW DC-8 SRM 53-2-0 FIG 8 (SHEE

Part: SKIN — DAMAGED (FS 1346.000) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT AFT FUSELAGE STA FS 1346.000, L-35.5R. ONLY 2 ROWS OF RIVETS IN OLD ANTENNA DOUBLER ADD THIRD ROWS OF RIVETS UTILIZING SRM RIVET SPACING OR UPGRADE REPAIR DOUBLER, STA 1346.000 L-35.5R (REF 822BX-R14). PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-1 FIG. 7 SHEET 1, 3, EO SEMAN 2005868 DATE 06-13-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.090”) (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.050”) IAW DC-8 SRM 53-2-1 FIG. 7 SHEET 1,3, DC-8 SRM 53-4-1 FIG. 16 SHEET 1 ITEM E, DC-8 SRM 51-10-0 FIG. 2 SHEET 5, DC-8 SRM 51-9-0 FIG. 68A, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA REPAIR PARTS IAW DC-8 S

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXTERNAL DOUBLER SKIN SPLICE FROM LONG 28 LT TO 28 RT; AFT EDGE RIVET SPACING EXCEEDS SRM LIMITS AFT SKIN SPLICE NON DOUG SRM UPGRADE REPAIR TO CONFORM TO DACO DC-8 SRM; FS 1696 L-36. (REF. 822BX-R68). PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-1 FIG 8 (SHEET 1,2), EO SEMAN # 2005905 DATE 06-27-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PG 1. REMOVED DAMAGED AREA IAW DC-8 SRM 53-2-1 FIG 8 (SHEET 1,2) PERFORMED NDT INSPECT IAW NDT SPM PART 06-10-01-001. FAB`D NEW SKIN SEGMENT (ALCLAD 7075 T6 0.050) IAW DC-8 SRM 53-5-1 PG 2, FIG 1 ITEM “E”, EXTERNAL SPLICE DOUBLER (ALCLAD 7075 T6 0.063), (08 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032), (08 EA) INTERNAL DOUBLER (ALCLAD 7

Part: SKIN — DAMAGED · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXT DOUBLER FWD LWR BASKET DOOR OPENING FWD EDGE REPAIR LACKS ENOUGH RIVETS ALL SIDES OF CUT OUT STA FS 279.000 L-31.5R. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 # 05270 DATE 06-29-05, SEMAN DWG ED 3995 DATE 06-25-05, EO SEMAN # 2005897 DATE 06-29-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PG 1. REMOVED DAMAGED AREA IAW SEMAN DKW ED 3995. PERFORMED NDT INSPECT IAW DC-8 NDT SPM 06-10-01-001. NO CRACK, CORROSION FOUND. FAB`D EXT REPAIR DOUBLER (ALCLAD 7075 T6 0.080), EXTERNAL REPAIR TRIPLER (ALCLAD 7075 T6 0.100), FILLER (ALCLAD 7075 T6 0.071) IAW SEMAN DWG ED 3995 AND DC-8 SRM 51-1-4 PG 1. CLEANED, TREATED AND PRIMED AREA, REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SE

Part: SKIN — DELAMINATED (RT ELEVATOR) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C-CHECK INSPECTION, RT ELEVATOR. REMOVE AND REINSTALL GEARED TAB (EXTERNAL SKIN DELAMINATED). REMOVED GEARED TAB FROM RT ELEVATOR IAW MM 27-30-3. INSTALLED GEARED TAB (OVERHAULED CONDITION) IAW MM 27-30-3. FOR OPS CHECK SEE NR 0818.

Part: ANTENNA — DETERIORATED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, RT AFT FUS AFT FS 1290.000, L-35.5R; ONLY 2 ROWS OF RIVETS IN OLD OMEGA ANTENNA DOUBLER ADD THIRD ROW OF RIVETS UTILIZING SRM RIVET SPACING OR UPGRADE REPAIR DOUBLER (REF 822BX-R13). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 # 05259 DATE 06-24-05, SEMAN DWG ED 4000 DATE 06-20-05, EO SEMAN # 2005902 DATE 06-24-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PG 1, DC-8 SRM 51-1-20D PG 21. REMOVED DAMAGED AREA IAW SEMAN DWG NR EO 4000. PERFORMED NDT INSPECT IAW DC-8 NDT SPM PART 06-10-01-001. NO CRACK, CORROSION FOUND. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.063”), REPAIR TRIPLER (ALCLAD 7075 T6 0.071), (05 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032) AND (02 EA) FOLLERS (AL

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXTERNAL DOUBLER FWD LOWER FUSELAGE, STA FS 114.000, L-35.5L MUST BE UPGRADED. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-1 FIG. 7, EO SEMAN NR 2005869 DATE 06-13-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1. TRIMMED OUT DAMAGED AREA IAW DC-8 SRM 53-2-1 FIG. 7 (SHEET 1,3). PERFORMED DETAILED VISUAL INSPECT NI CRACK, CORROSION FOUND. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.080”) + (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.050”) IAW DC-8 SRM 53-2-1 FIG 7 SHEET 1,3, DC-8 SRM 53-4-1 FIG 16 SHEET 2 ITEM B, DC-8 SRM 51-9-0 FIG 68A, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED SEALANT TO FAYING SURFACES IAW DC-8 S

Part: SKIN — DAMAGED (AILERON TAB) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, LT AILERON REMOVE AND REINSTALL TRIM TAB (UPPER SKIN HAS HOLES). REMOVED TRIM TAB FROM LT ALEIRON IAW DC-8 MM 27-13-1 PAGES 201-203. INSTALLED TRIM TAB ON LT AILERON IAW DC-8 MM 27-13-1 PAGES 203-208 (REPAIRED CONDITION). FOR OPS CHECK SEE NR 0818.

Part: FITTING — CRACKED (MLG WW) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, MLG W/W FITTING CRACKED 4", STA 857.725 , RBL 46". REMOVED CRACKED FITTING IAW DC-8 SRM 51-1-20D PAGE 21. CLEANED, TREATED AND PRIMED AREA IAW DC-8 SRM 51-1-8B. INSTALLED NEW FITTING IAW DC-8 SRM 51-1-20D PAGE 9. TORQUED IAW DC-8 SRM 51-3-1.

Part: SKIN — DAMAGED · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXTERNAL DOUBLER ON AFT LOWER FUSELAGE, STA FS 1540.000, L-35.5L REPAIR MUST BE UPGRADED. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05271 DATE 06-29-05, SEMAN DWG ED 4001 DATE 06-22-05, EO SEMAN NR 2005903 DATE 06-29-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 21. PERFORMED DETAILED VISUAL INSPECT NO CRACK, CORROSION FOUND. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.080”) + INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) IAW SEMAN ED 4001. 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 PAGE 9. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 40001 DC-8 SRM 51-1-21 PAGE 1,

Part: CLIP — CRACKED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C-CHECK INSPECTION, MLG W/W CLIP CRACKED 5 INCHES , STA 857.725 AND RBL 46 INCHES. REMOVED CRACKED FITTING IAW SRM 51-1-21 PAGE 1. CLEANED, TREATED AND PRIMED AREA IAW SRM 51-1-8B. INSTALLED NEW FITTING IAW SRM 51-1-20D PAGE 9.

Part: SKIN — DAMAGED · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECT, UAL DRAIN DOUBLER AT FWD LWR FUSELAGE FS 77, L-35.5R MUST BE UPGRADED, REPAIR MUST HAVE THREE ROWS OF RIVETS (REF. 822BX-R29). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05258 DATE 06-24-05, SEMAN DWG ED 3992 DATE 06-21-05, EO SEMAN NR 2005896 DATE 06-24-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 21. TRIMMED OUT DAMAGED AREA IAW SEMAN DWG NR EO 3992. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM PART 06-10-01-001. NO CRACK, CORROSION FOUND. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.063) + (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) IAW SEMAN ED 3992. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED

Part: SKIN — DELAMINATED (RT WING) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, RT WING UPPER T/E PANEL EXTERNAL SKIN DELAMINATED, XA 613.000 - XA 681.000. REMOVED AND REPLACED UPPER T/E PANEL ON RT WING XA 613.000 XA 681.000 IAW DC-8 SRM 51-3-0, DC-8 SRM 51-1-21 PAGE 1. TORQUED IAW DC-8 SRM 51-3-1.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, UAL DRAIN DOUBLER ON FWD LOWER FUSELAGE, STA FS 224.000, L-35.75R REPAIR MUST BE UPGRADED. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05258 DATE 06-24-05, SEMAN DWG ED 3994 DATE 06-22-05, EO SEMAN NR 2005832 DATE 06-24-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 21. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.080”) + (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) IAW SEMAN ED 3994 AND DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW SEMAN DWG ED 3994, DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXTERNAL DOUBLER LWR FUSELAGE, STA FS 238.000, L-31R REPAIR EXCEEDS MAX RIVETS SPACING ON SIDES 1 FWD, 2 UPPER AND 4 LOWER ADD ADDITIONAL RIVETS OR REWORK SIDES 1,2 AND 4 TO BRING INTO LIMITS PER SRM BELOW 1.400” SPACING (REF. 822BX-R35). PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-1 FIG 7 EO SEMAN NR 2005866 DATE 06-13-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-20D PAGE 21, DC-8 SRM 51-1-21 PAGE 1. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.080”) + (02 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.050”) IAW DC-8 SRM 53-2-1 FIG 7 SHEET 1, 4, DC-8 SRM 53-4-1 FIG 1. ITEM “B”, DC-8 SRM 51-9-0 FIG 68A, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SR

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECTION, EXTERNAL DOUBLER ON WINDOW BELT AREA ABOVE C-PIT BASKET DOOR OLD UNITED AIRLINES INSUFFICIENT SIZE OF LOWER EXTENSION UPGRADE DOUBLER TO CONFORM TO THE CURRENT DACO DC-8 SRM REQUIREMENTS (REF. 822BX-R59), STA FS 1400.000 L-15.5R. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-0 FIG 22A TR # 53-170 DATE 09-20-03, EO SEMAN NR 2005878 DATE 06-13-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 21. FABRICATED REPAIR DOUBLER (ALCLAD 7075 T6 0.190”) IAW DC-8 SRM 53-2-0 FIG 22A SHEET 1, 7, TR NR 53-170, DC-8 SRM 53-4-1 FIG 19 ITEM B, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA + REPAIR DOUBLER IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAY

Part: SKIN — CORRODED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING ROUTINE C CHECK INSPECTION, EXTERNAL DOUBLER/TRIPLER FWD BASKET DOOR FWD LEFT UPPER CORNER. REPAIR DOES NOT CONFORM TO EVA 33-2614 USED FOR INSTALLATION. EVALUATE REPAIR FOR SRM CONFORMITY (53-2-0 FIG. 19, SHEET 1). PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 NR 05270 DATE 06-29-05, SEMAN DWG ED 3996 DATE 06-27-05, EO SEMAN NR 2005898 DATE 06-29-05. REMOVED EXISTING REPAIR DOUBLER + TRIPLER IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 9. PERFORMED NDT INSPECTION IAW DC-8 NDT SPM PART 06-10-01-001. NO CRACK, CORROSION FOUND. FAB`D EXISTING REPAIR DOUBLER (ALCLAD 7075 T6 0.090), EXISTING REPAIR TRIPLER (ALCLAD 7075 T6 0.125) IAW SEMAN ED 3996, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED ARE

Part: DOUBLER — OUT OF LIMITS (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, LT FWD FUS ABOVE AND AFT TURBO COMPRESSOR, SIDE 1 (FWD) BELOW, MIN EDGE DISTANCE FOR RIVETS, REPAIR DOUBLER RATIO ABOVE LIMITS TO THICK, STA FS 116.000 L-21.5L. UPGRADE REPAIR BY REPLACING EXISTING DOUBLER WITH 0.071AND ENSURE MIN EDGE DISTANCE IS WITHIN SRM LIMITS ON SIDE 1. PERFORMED MAJOR REPAIR IAW FAA FORM 8110-3 # 05280 DATE 07-04-05, SEMAN DWG # ED 3991 DATE 06-28-05, EO SEMAN NR 2005895 DATE 07-04-05. REMOVED EXISTING REPAIR DOUBLERS IAW DC-8 SRM 51-1-21 PAGE 1, DC-8 SRM 51-1-20D PAGE 21. PERFORMED NDT INSPECT IAW DC-8 SPM PART 06-10-01-001. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.071”) + REPAIR TRIPLER (ALCLAD 7075 T6 0.080”) + (03 EA) INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.03

Part: FITTING — CORRODED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C-CHECK INSPECT, MLG WW FRAME FITTING CORRODED, STA 940.000, L-24. PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-0, EO SEMAN NR 2005844. REMOVED CORROSION IAW DC-8 SRM 51-1-8. FOUND OUT OF LIMITS IAW DC-8 SRM 53-2-0. REMOVED CORRODED FRAME FITTING IAW DC-8 SRM 51-1-20D. FAB`D NEW FRAME FITTING IAW DWG DOUG 3646956, EO SEMAN 2005841, 4 SPLICE , DOUBLER (ALCLAD 7075 T6 0.190), (02 EA) FILLERS (ALCLAD 7075 T6 0.160) IAW DC-8 SRM 53-2-0 FIG 8 (SHEET 1,2,5,6. PERFORMED HEAT TREATMENT TO NEW FRAME FITTING, FILLER, DOUBLER IAW DC-8 SRM 51-1-1 PAGES 1, 13, 17. PERFORMED NDT INSPECTION TO NEW FRAME FITTING IAW DC-8 NDT SPM PART 08-00-02 TO 07. CLEANED, TREATED AND PRIMED AREA , REPAIR PARTS IAW DC-8 SRM 51-1-8B

Part: SKIN — DAMAGED (FUSELAGE) · airframe 89,890 hrs · 37,461 cycles

DURING C CHECK INSPECT, EXTERNAL DOUBLER UAL DRAIN DOUBLER, RT AFT FUSELAGE SIDE. REPAIR MUST BE UPGRADED, REPAIR MUST HAVE 3 ROWS OF RIVETS STA FS 1693, L-30.5R (REF.- 822BX-R71). PERFORMED MAJOR REPAIR IAW DC-8 SRM 53-2-1 FIG 7, EO SEMAN NR 2005871 DATE 06-13-05. REMOVED EXISTING REPAIR DOUBLER IAW DC-8 SRM 51-1-21 PAGE 1. FAB`D REPAIR DOUBLER (ALCLAD 7075 T6 0.063”) + INTERNAL FINGER DOUBLER (ALCLAD 7075 T6 0.032”) IAW DC-8 SRM 53-2-1 FIG 7 (SHEET 1,5), DC-8 SRM 53-5-1 FIG 1 ITEM E, DC-8 SRM 51-1-4 PAGE 1. CLEANED, TREATED AND PRIMED AREA + REPAIR PARTS IAW DC-8 SRM 51-1-8B. APPLIED PRC SEALANT TO FAYING SURFACES IAW DC-8 SRM 51-1-11. INSTALLED REPAIR PARTS IAW DC-8 SRM 53-2-1 FIG 7, DC-8 SRM 51-1-21 PAGE

Part: CONTROL VALVE — LEAKING (RUDDER) · airframe 89,005 hrs · 36,960 cycles

ON DESCENT FROM KPDX TO KBFI, RUDDER CONTROL LIGHT ILLUMINATED WITH HYDRAULIC SYSTEM PRESS READ ZERO AND HYDRAULIC QUANTITY DOWN TO 6 GALS. COMPLETED QR4 PROCEDURE (LOSS OF HYDRAULIC). CREW ABORTED DESCENT AND RETURNED TO KPDX. LANDED WITHOUT INCIDENT. AN INVESTIGATION IS ON GOING. AS SOON AS INFORMATION IS AVAILABLE IT WILL BE PROVIDED. MAINTENANCE FOUND SLOT CONTROL VALVE LEAKING. REMOVED, REPACKED AND REINSTALLED VALVE. THE OPERATIONAL AND LEAK CHECK WAS GOOD ON THE ENGINE RUN PER ALL APPLICABLE MANUALS. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: COUPLER — CORRODED (HF SYSTEM) · airframe 87,949 hrs · 36,437 cycles

DURING CRUISE HF SYS WAS NOT RECEIVING, ELECTED TO RETURN. MX FOUND INCORRECT P/N'S INSTALLED FOR ACCESS COUPLER & TUNER COUPLERS. REMOVED & REPLACED COUPLERS. MX FOUND RECEIVE LINES FOR HF 1 & 2 FROM LIGHT ARRESTOR TO ACCESS COUPLERS CORRODED & SHORTED TO OUTER SHIELD. RAN NEW TO COAX CABLE FROM ARRESTOR TO ACCESS & REPLACED COAX FOR HF 1 & 2 FROM LIGHTING ARRESTOR TO ACCESS COUPLER. INSTALLED NEW CONNECTORS ON BOTH ENDS OF COAX TESTED SYS & DISCOVERED HF NR 1 TUNER WOULD NOT CHANNELIZE, NR 2 WOULD NOT TRANSMIT, HF 2 COUPLER WOULD NOT RECEIVE. REINSTALLED ORIGINAL EQUIPMENT & SYSTEM CHECKS GOOD PER ALL APPLICABLE MANUALS. RECIEVE 5X5 BY DIEGO HF AND AIRCRAFT EN ROUTE. AIRCRAFT RETURNED TO SERVICE.

Part: PRECOOLER — CRACKED (ENGINE) · airframe 86,836 hrs · 34,911 cycles

DURING CLIMB FROM KGSO TO KTOL NR 2 ENGINE PNEUMATIC SYSTEM OVERHEATS WITH LOW OR HIGH STAGE BLEED WITH CLIMB POWER SET AND LT PACK AT MIN FLOW. CREW RETURNED TO KGSO AND LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED NR 2 PRECOOLER CONTROL VALVE PER ALL APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.

Part: HEAT EXCHANGER — FAILED (PNEU SYS) · airframe 86,835 hrs · 34,910 cycles

DURING CLIMB FROM KGSO TO KTOL NR 2 ENGINE PNEUMATIC SYSTEM OVERHEATED WITH LOW OR HIGH STAGE BLEED AND PACK FLOW AT MIN. CREW RETURNED TO KGSO AND LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED NR 2 PRECOOLER PER ALL APPLICABLE MANUALS. AIRCRAFT RETURNED TO SERVICE.

Part: RADIO — FAILED (NR 1 & 2 HF) · airframe 87,377 hrs · 36,220 cycles

DURING CLIMB NR 1 AND NR 2 HF WOULD NOT TRANSMIT. CREW RETURNED AIRCRAFT AND LANDED AT FJDG WITHOUT INCIDENT. AN INSPECTION IS ON GOING. WHEN MORE INFORMATION IS AVAILABLE IT WILL BE PROVIDED.MAINTENANCE PERFORMED PRESSURE CHECK OF CABIN SENSING LINE FOR ANTENNA COUPLER PER ALL APPLICABLE MANUALS. OPERATIONAL AND LEAK CHECK GOOD. AIRCRAFT WAS RETURNED TO SERVICE.

Part: GEAR — DIRTY (RUDDER) · airframe 87,364 hrs · 36,217 cycles

DURING LANDING TO RJTY RUDDER TRIM BOUND. CREW COULD NOT CENTER RUDDER TRIM, IT BOUND AT 3 UNITS LEFT. AFTER LANDING ROTATED RUDDER TRIM TO FULL LEFT DEFLECTION. CREW NOTED METALLIC NOISE FROM PEDESTAL AREA AND RUDDER TRIM CENTERED OKAY. MAINTENANCE FOUND DEBRIS IN RUDDER TRIM GEAR TEETH. THE DEBRIS WAS REMOVED AND AN OPERATIONAL CHECK FOR THE RUDDER TRIM SYSTEM WAS GOOD ON GROUND PER ALL APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.

Part: WIRE HARNESS — FAULTY (NR 3 ENGINE) · airframe 87,364 hrs · 36,217 cycles

CREW DID AIR RETURN TO RJTY FOR AN ERRATIC EGT ON NR 3. EGT FLUCUATES BETWEEN +/- 30 DEGREES. CREW SHUTDOWN ENGINE AND OIL PRESSURE WAS ZERO PSI. CREW THEN RETURNED THE AIRCRAFT TO RJTY AND LANDED WITHOUT INCIDENT. MAINTENANCE TROUBLESHOT NR 3 ENGINE EGT SYSTEM AND FOUND BAD CFM 56-2C1 EGT HARNESS. MAINTENANCE THEN REMOVED AND REPLACED HARNESS PER ALL APPLICABLE MANUALS. AIRCRAFT WAS RETURNED TO SERVICE.

Part: SUPPRESSOR — FAULTY (RADIO) · airframe 87,363 hrs · 36,216 cycles

DURING CRUISE FROM RJTY TO VTBU CREW NOTED NR 2 HF INOP WHEN KEYING MIC TO TUNE RADIO. TONE WAS FUZZY. CREW RETURNED AIRCRAFT TO RJTY AND LANDED WITHOUT INCIDENT. MAINTENANCE TROUBLESHOT TO FAULTY LIGHTNING ARRESTOR AND FAULTY TRANSMIT COAX. MAINTENANCE REPAIRED COAX AND REPLACED LIGHTING ARRESTOR PER ALL APPLICABLE MANUALS. OPERATIONAL CHECK GOOD ON GROUND. AIRCRAFT WAS RETURNED TO SERVICE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 85,324 hrs · 35,317 cycles

DURING A ROUTINE MAINTENANCE PREFLIGHT INSPECTION, A CRACK WAS DETECTED ON THE OUTER PLATING AT FUSELAGE STATION 25, LONGERON 33 RIGHT. THE REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION A REPAIR FILLER AND A EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH THE STRUCTURAL REPAIR MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: ACTUATOR — LEAKING (T/E FLAP) · airframe 84,635 hrs · 35,058 cycles

DURING DESCENT FROM DXB TO BRU, THE FLIGHT CREW NOTICED A DECLINE IN THE THE HYDRAULIC QUANTITY SYSTEM. THE FLIGHT CREW FOLLOWED COMPANY PROCEDURES AND CONTINUED TO BRU FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND LOCATED A DEFECTIVE FLAP ACTUATOR ON THE LEFT INBOARD SIDE. MAINTENANCE REPLACED THE ACTUATOR AND PERFORMED AN OPERATIONAL CHECK IN ACCORDANCE WITH THE DACO MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: ELEMENT — DEFECTIVE (ENGINE) · airframe 84,264 hrs · 34,900 cycles

ENROUTE FROM LAX TO TOL, DURING CRUISE THE NUMBER FOUR FIRE WARNING LIGHT ILLUMINATED ACCOMPANIED BY THE WARNING BELL. THE FLIGHT CREW FOLLOWED COMPANY EMERGENCY PROCEDURES, SECURED THE ENGINE AND DISCHARGED BOTH BOTTLES. THE FLIGHT RETURNED TO LAX FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE WITH NO EVIDENCE OF A FIRE. FURTHER INSPECTION REVEALED THREE FIRE SENSEING ELEMENTS DEFECTIVE AND A ELECTRICAL CONNECTOR. MAINTENANCE REPLACED THE ELEMENTS AND ELECTRICAL CONNECTOR AND PERFORMED A SUCCESSFUL OPERATIONAL CHECK. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: AMPLIFIER — DEFECTIVE (COCKPIT) · airframe 84,263 hrs · 34,899 cycles

ENROUTE FROM TOL TO LAX, DURING CRUISE THE NUMBER FOUR ENGINE FIRE WARNING LIGHT ILLUMATED ACCOMPANIED BY THE WARNING BELL. THE FLIGHT CREW FOLLOW COMPANY EMERGENCY PROCEDURES, SECURED THE ENGINE AND DISCHARGED ONE BOTTLE. THE FLIGHT CONTINUED TO LAX FOR AN UNEVENTFUL LANDING.MAINTENANCE INSPECTED THE ENGINE WITH NO EVIDENCE OF A FIRE. MAINTENANCE TESTED THE SYSTEM WHICH REVEALED A DEFECTIVE FIRE WARNING AMPLIFIER AND WAS REPLACED. MAINTENANCE PERFORMED A SUCCESSFUL OPERATIONAL TEST IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: LONGERON — CRACKED (LOWER FUSELAGE) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON LONGERON 36 AT FUSELAGE STATION 621. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION NEW LONGERON SPLICE FITTING IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 53-DC8-3023.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON FORWARD PIT LONGERON 36 BETWEEN FUSELAGE STATION 590 AND 610. REPAIR ACCOMPLISHED REMOVAL OF LONGERON SECTION, FABRICATION AND INSTALLATION OF A NEW LONGERON SECTION AND SPLICE IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 51-DC8-3030.

Part: FRAME — CRACKED (TAIL CONE) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED IN THE TAIL CONE FRAME AT FUSELAGE STATION 1992 LEFT SIDE BEHIND THE CROSS BRACE. REPAIR ACCOMPLISHED FABRICATION AND INSTALLATION OF REPAIR ANGLES IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 53-DC8-3051.

Part: HINGE FITTING — CRACKED (R/H WING) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE RIGHT WING AILERON MECHANISM AREA LOWER SUPPORT HINGE FITTING "L" ANGLE. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED ANGLE, FABRICATION AND INSTALLATION OF NEW REPAIR ANGLE IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL, DRAWING 5705518 AND ENGINEERING ORDER 57-DC8-3043.

Part: DOUBLER — CORRODED (R/H WING L/E) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE RIGHT WING LEADING EDGE INTERIOR DOUBLER AT THE LIFT TRANSDUCER, STATION 380. REPAIR ACCOMPLISHED REMOVAL OF DEFECTIVE DOUBLER, FABRICATION AND INSTALLATION OF NEW DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 57-DC8-3040.

Part: RIB — MISDRILLED (RIGHT WING) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, MISDRILLED HOLES WERE DETECTED IN THE RIGHT WING LEADING EDGE RIB AT WING STATION 763, ACCESS PANEL 517B. REPAIR ACCOMPLISHED REMOVAL OF DEFECTIVE DOUBLER, FABRICATION AND INSTALLATION OF NEW REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 57-DC8-3038.

Part: DOOR FRAME — DAMAGED (EMERGENCY EXIT) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, ON THE LEFT HAND AFT OVERWING EMERGENCY EXIT DOOR FRAME BOTTOM SIDE FORWARD DOOR KEEPER STOP WAS FOUND DAMAGED. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED KEEPER, FABRICATION AND INSTALLATION OF NEW CLIP IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL, DACO DRAWING 2779323 AND ENGINEERING ORDER 52-DC8-3037.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED AT THE LEFT HAND LEADING EDGE HORIZONTAL STABILIZER INBOARD SIDE INTERIOR PANEL 2ND RIB. REPAIR ACCOMPLISHED STOP DRILLED CRACK, FABRICATION AND INSTALLATION REPAIR ANGLE IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 55-DC8-3025.

Part: SPAR CAP — CRACKED (VERTICAL STAB) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED AT THE VERTICAL STABILIZER REAR SPAR LEFT HAND CAP AT STATION ZR 265. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED CAP. FABRICATION AND INSTALLATION OF NEW CAP IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL, DAC DRAWING 5611409 AND ENGINEERING ORDER 55-DC8-3048.

Part: SKIN — GOUGED (ELEVATOR) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A GOUGE WAS DETECTED ON THE LEFT ELEVATOR UPPER SKIN AT STATION XE 176. REPAIR ACCOMPLISHED FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 55-DC8-3046.

Part: DOOR FRAME — CRACKED (CARGO DOOR) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE C-PIT BASKET DOOR FORWARD CENTER DOOR PAN FRAME. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA. FABRICATION AND INSTALLATION OF DOOR PAN AND SPLICE IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL, DAC DRAWING 5704349 AND ENGINEERING ORDER 52-DC8-3052.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED AT THE LEFT HAND LEADING EDGE HORIZONTAL STABILIZER INBOARD SIDE INTERIOR PANEL 16TH RIB. REPAIR ACCOMPLISHED STOP DRILLED CRACK, FABRICATION AND INSTALLATION REPAIR ANGLE IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 55-DC8-3024.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A GOUGE WAS DETECTED IN THE A-PIT BASKET EXTERNAL DOOR PLATING RIGHT HAND AFT CORNER. REPAIR ACCOMPLISHED FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 52-DC8-3054.

Part: SKIN — DENTED (FUSELAGE) · airframe 84,173 hrs · 34,855 cycles

DURING ROUTINE C-CHECK INSPECTION, A DENT WAS FOUND AT FUSELAGE STATION Y+1400.000 BETWEEN LONGERONS 26R AND 27R. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF DOUBLER AND FILLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING ORDER 53-DC8-3053.

Part: FUEL TANK — CONTAMINATED (WING) · airframe 82,827 hrs · 34,254 cycles

EN ROUTE FROM MHZ TO WRI, DURING CRUISE THE NUMBER TWO AND THREE ENGINE FLAMED OUT. THE FLIGHT CREW FOLLOWED COMPANY EMERGENCY PROCUDERS, DECLAIRED EMERGENCY AND RETURNED TO MHZ FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE WITH NO EXTERNAL DISCREPANCIES NOTED. MAINTENANCE ACCOMPLISHED ALL CFMI MAINTENANCE MANUAL PROCEDURE FOR ENGINE FAILURES. REMOVED EXCESSIVE MOISTURE FROM THE FUEL TANKS. MAINTENANCE ACCOMPLISHED ALL APPLICABLE MAINTENANCE MANUAL ENGINE POWER ASSURANCE PERFORMANCE WITH NO DISCREPANCIES NOTED. THE AIRCRAFT WAS RETURNED TO SERVICE.

Part: FUEL CELL — CONTAMINATED (FUSELAGE)

EN ROUTE FROM ONT TO SAN, THE NUMBER ONE ENGINE FLAMED OUT AT THE TOP OF CLIMB. THE FLIGHT CREW RELIT THE ENGINE FOLLOWING COMPANY PROCEDURES, THE FLIGHT CONTINUED TO SAN FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE IN ACCORDANCE WITH THE CFM MAINTENANCE MANUAL WHICH REVEALED MOISTURE IN THE NUMBER ONE MAIN FUEL TANK AND FILTER ASSEMBLY. MAINTENANCE REMOVED THE MOISTURE AND REPLACED THE MAIN FUEL FILTER AS PRECAUTIONARY. MAINTENANCE PERFORMED A MAXIMUM POWER ASSURANCE CHECK IN ACCORDANCE WITH THE COMPANY JRH BOOK WITH NO DISCREPANCIES NOTED.

Part: PACK — MALFUNCTIONED (RIGHT)

EN ROUTE FROM TOL TO DFW, THE RIGHT AIR CONDITIONING PACK HAD ZERO FLOW, RUNS HOT AND EMITTED A BURNING ODOR WHEN FULL COLD SELECTED. THE FLIGHT CONTINUED TO DFW FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE RIGHT PACK SYSTEM IN ACCORDANCE WITH THE MAINTENANCE MANUAL WITH NO DISCREPANCIES NOTED. MAINTENANCE PERFORMED A SYSTEM OPERATIONAL TEST IN ACCORDANCE WITH THE MAINTENANCE MANUAL WITH NO DISCREPANCIES NOTED.

Part: CONNECTOR — CORRODED (LT MLG DOOR)

DURING CLIMBOUT FROM A MISSED APPROACH, THE CREW RETRACTED THE LANDING GEAR, THE LANDING GEAR DOOR WARNING REMAINED ILLUMINATED. THE CREW CYCLED THE GEAR WITH THE DOOR WARNING INDICATION REMAINING THE SAME. MAINTENANCE INSPECTED THE LANDING GEAR DOOR SWITCHES WHICH REVEALED THE LEFT MAIN GEAR DOOR SWITCH CANNON PLUG CORRODED. MAINTENANCE CLEANED THE DOOR SWITCH AND THE CANNON PLUG. MAINTENANCE PERFORMED A SUCCESSFUL OPERATIONAL TEST.

Part: DOUBLER — CRACKED (BS 1160-1680)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON AN INTERNAL REPAIR DOUBLER BETWEEN FUSELAGE STATION 1160 AND 1680, LONGERON 27 AND 28 RIGHT. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF NEW REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING 853-206-97 AND ENGINEERING ORDER 53-DC8-720.

Part: FITTING — CRACKED (BS 345)

DURING ROUTINE C-CHECK INSPECTION, LONGERON 32 RIGHT WAS FOUND CRACKED AT FUSELAGE STATION 345. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A LONGERON FILLER AND SPLICE FITTING IN ACCORDANCE WITH DER APPROVED DRAWING 853-218-97 AND ENGINEERING ORDER 53-DC8-728 AND 53-DC8-744.

Part: FITTING — CORRODED (BS 1746)

DURING ROUTINE C-CHECK INSPECTION, TWO LONGERON SPLICE FITTINGS WERE FOUND CORRODED AT FUSELAGE STATION 1746, LONGERON 31 RIGHT AND 31 LEFT. REPAIR ACCOMPLISHED REMOVAL OF CORRODED FITTINGS, FABRICATION AND INSTALLATION IN ACCORDANCE WITH DOUGLAS AIRCRAFT COMPANY SRM 53-2-0 FIGURE 2.

Part: LONGERON — CORRODED (BS 480)

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON LONGERON 31 LEFT, OUTBOARD FLANGE, AT FUSELAGE STATION 480. REPAIR ACCOMPLISHED CORROSION REMOVAL, FABRICATION AND INSTALLATION OF A REPAIR ANGLE IN ACCORDANCE WITH DER APPROVED DRAWING 853-223-97 AND ENGINEERING ORDER 53-DC8-732.

Part: LONGERON — CRACKED (BS 1690)

DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS FOUND ON LONGERON 34 RIGHT, AT FUSELAGE STATION 1690. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION LONGERON FILLER AND A SPLICE DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING 853-211-97A AND ENGINEERING ORDER 53-DC8-273.

Part: SPLICE — CORRODED (BS 600)

DURING ROUTINE C-CHECK INSPECTION, FOUND LONGERON 27 LEFT, SPLICE FITTING WITH CORROSION BETWEEN FUSELAGE STATION 600 AND 620. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED FITTING, FABRICATION AND INSTALLATION OF NEW FITTING IN ACCORDANCE WITH DER APPROVED DRAWING 853-212-97 AND ENGINEERING ORDER 53-DC8-725.

Part: BULKHEAD WEB — CRACKED (BS 1766)

DURING ROUTINE C-CHECK INSPECTION, THE AFT PRESSURE BULKHEAD WEB WAS FOUND CRACKED AT FUSELAGE STATION 1766, TX26 AND TZ67. REPAIR ACCOMPLISHED STOP DRILLING OF CRACK, FABRICATION AND INSTALLATION OF A REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS AIRCRAFT COMPANY SRM 53-2-5, FIGURE 14A.

Part: SPAR CAP — CRACKED (LT WING)

DURING ROUTINE C-CHECK INSPECTION, THE LEFT WING UPPER AUXILIARY SPAR CAP WAS FOUND CRACKED. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED CAP, FABRICATION AND INSTALLATION OF NEW SPAR CAP IN ACCORDANCE WITH DER APPROVED DRAWING 853-239-97, DOUGLAS AIRCRAFT DRAWING 561507, REVISION K, AND ENGINEERING ORDER 53-DC8-729.

Part: PLATING — CORRODED (BS 360)

DURING ROUTINE C-CHECK INSPECTION, A CORROSION BULGE WAS FOUND ON THE EXTERNAL PLATING AT FUSELAGE STATION 360, LONGERON 35 RIGHT. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING 853-208-97 AND ENGINEERING ORDER 53-DC8-721.

Part: FITTING — CRACKED (LT MLG WW)

DURING ROUTINE C-CHECK INSPECTION, THE LEFT MAIN GEAR SUPPORT FITTING WAS FOUND TO BE CRACKED. REPAIR ACCOMPLISHED REMOVAL AND INSTALLATION OF A NEW MLG SUPPORT FITTING IN ACCORDANCE WITH DOUGLAS AIRCRAFT COMPANY SERVICE BULLETIN 57-94, REVISION 2.

Part: PLATING — CORRODED (BS 321)

DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON THE EXTERNAL PLATING OF THE FORWARD BASKET DOOR AT FUSELAGE STATION 321. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS AIRCRAFT COMPANY SRM 52-2-0, FIGURE 4, 51-1-8, AND 51-1-21.

Part: PLATING — CRACKED (WS 341.5)

DURING ROUTINE C-CHECK INSPECTION, THE LEFT WING LOWER LEADING EDGE PLATING WAS FOUND CRACKED AT STATION 341.500. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING 857-227-97 AND ENGINEERING ORDER 57-DC8-738.

Part: ANGLE — CORRODED (WS 857)

DURING ROUTINE C-CHECK INSPECTION, THE WEB SUPPORT ANGLE ON REAR SPAR UPPER CHORD WAS FOUND TO BE CORRODED AT STATION 857. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED ANGLE, FABRICATION AND INSTALLATION OF TWO REPAIR ANGLES IN ACCORDANCE WITH DER APPROVED DRAWING 857-222-97 AND ENGINEERING ORDER 57-DC8-737.

Part: FITTING — CRACKED (WS 339.723)

DURING ROUTINE C-CHECK INSPECTION, THE RIGHT WING FLAP SUPPORT FITTING WAS FOUND CRACKED AT STATION 339.723. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED FITTING, INSTALLATION OF A NEW FITTING IN ACCORDANCE WITH DOUGLAS AIRCRAFT COMPANY DC-8 SERVICE BULLETIN 27-249, REVISION 1, SECTION 2, GROUP 2, AND MAINTENANCE MANUAL 25-51-05.

Part: MEC SENSE LINE — OBSTRUCTED (NR 4 ENGINE)

EN ROUTE OAK TO TOL AT FL 37, SAT MINUS 48, FUEL QTY OF RESPECTIVE TANK 8000 LBS, NR 4 ENGINE FLAMED OUT. CREW ACCOMPLISHED SUCCESSFUL RESTART IAW COMPANY PROCEDURES. FLIGHT CONTINUED WITH NO FURTHER EVENTS. MAINTENANCE TROUBLESHOT THE EVENT IAW CFMI MM FAULT 57. MAINTENANCE FOUND AND CLEANED AND OBSTRUCTION FROM THE CDP AND CBP LINES, REPLACED THE ENGINE FUEL FILTER, AND OPERATIONALLY CHECKED THE ENGINE PRIOR TO RETURNING THE AIRCRAFT TO SERVICE. (M)

Part: ENGINE — FAILED (NR 4)

EN ROUTE KPOB TO KICT, A PRECAUTIONARY SHUTDOWN OF THE NR 4 ENGINE WAS ACCOMPLISHED DUE TO HEAVY VIBRATION, LOSS OF OIL PRESSURE AND FLUCTUATING FUEL FLOW. THE ENGINE WAS REMOVED AND REPLACED, AND AIRCRAFT WAS RETURNED TO SERIVICED. (M)